@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: 55

TITLE: STABILIZERS - RUDDER SIDE SHELL SANDWICH REPAIR

INSPECTION

MODIFICATION No.: None

This page transmits Revision No.01 of Service Bulletin No.A330-55-3043

ADDITIONAL WORK

**CONF ALL

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

REASON

Revision No. 01 issued to embody the local sanding procedure.

CHANGES

NOTE: Revision bars against references not identified in the CHANGES paragraph appear due

to format changes introduced by new authorities’ rules.

FRONT MATTER

STABILIZERS - RUDDER SIDE SHELL

SANDWICH REPAIR INSPECTION

CONFIGURATION UPDATED R

SUMMARY

EFFECTIVITY OPERATOR LIST UPDATED R

REFERENCES / REPERCUSSIONS REFERENCES/REPERCUSSIONS TABLE

UPDATED

R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition

CONF 001 CONFIGURATION DEFINITION UPDATED R

COMPLIANCE

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

MANPOWER MANPOWER UPDATED R

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 1

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

REFERENCES REFERENCED DOCUMENTATION UPDATED R

MATERIAL INFORMATION

LIST OF MATERIALS - OPERATOR

SUPPLIED

Consumable Materials

Consumable CMLD01 CONSUMABLE MATERIAL SET UPDATED

CONSUMABLE UPDATED

R

TOOLING

Tools TOOLS UPDATED R

ACCOMPLISHMENT INSTRUCTIONS

TASK 553043- 832-848-001-Inspection TASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 553043-910-201-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 553043-941-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

NOTE UPDATED

REFERENCES UPDATED

R

Subtask 553043-832-202-001 SUBTASK SOLUTION UPDATED

FIGURE REFERENCE UPDATED

NOTE UPDATED

R

Subtask 553043-832-201-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

FIGURE REFERENCE UPDATED

NOTE UPDATED

R

Subtask 553043-832-203-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

FIGURE REFERENCE UPDATED

NOTE UPDATED

R

Subtask 553043-832-204-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

FIGURE REFERENCE UPDATED

NOTE UPDATED

CONFIGURATION UPDATED

MATERIAL LIST UPDATED

R

Subtask 553043-832-206-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

REFERENCED DOCUMENTATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 2

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 553043-832-205-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

FIGURE REFERENCE UPDATED

NOTE UPDATED

MATERIAL LIST UPDATED

R

Subtask 553043-832-207-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

FIGURE REFERENCE UPDATED

NOTE UPDATED

R

Subtask 553043-833-201-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

CONSUMABLE UPDATED

REFERENCED DOCUMENTATION UPDATED

MATERIAL LIST UPDATED

R

Subtask 553043-832-208-001 SUBTASK SOLUTION ADDED N

Subtask 553043-942-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Fig. A-GBAAA

Fig. A-GBAAA Sheet 01 SHEET UPDATED R

Fig. A-GBFAA

Fig. A-GBFAA Sheet 02 SHEET UPDATED R

Fig. A-GBHAA FIGURE SOLUTION UPDATED R

Fig. A-GBHAA Sheet 01 SHEET UPDATED R

Fig. A-GBHAA Sheet 02 SHEET UPDATED R

Fig. A-GBHAA Sheet 03 SHEET UPDATED R

Fig. A-GBHAA Sheet 04 SHEET UPDATED R

Fig. A-GBHAA Sheet 05 SHEET UPDATED R

Fig. A-GBHAA Sheet 06 SHEET UPDATED R

Fig. A-GBHAA Sheet 07 SHEET UPDATED R

Fig. A-GBHAA Sheet 08 SHEET UPDATED R

Fig. A-GBHAA Sheet 09 SHEET UPDATED R

Fig. A-GBHAA Sheet 10 SHEET UPDATED R

Fig. A-GBHAA Sheet 11 SHEET UPDATED R

Fig. A-GBHAA Sheet 12 SHEET UPDATED R

Fig. A-GBHAA Sheet 13 SHEET UPDATED R

Fig. A-GBHAA Sheet 16 SHEET ADDED N

Fig. A-GFAAA FIGURE SOLUTION UPDATED R

Fig. A-GFAAA Sheet 01 SHEET UPDATED R

Fig. A-GFAAA Sheet 02 SHEET UPDATED R

Fig. A-GFAAA Sheet 03 SHEET UPDATED R

Fig. A-GFAAA Sheet 04 SHEET UPDATED R

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 3

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@A330

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Fig. A-GFAAA Sheet 05 SHEET UPDATED R

Fig. A-GFAAA Sheet 06 SHEET ADDED N

Fig. A-GAAAA

Fig. A-GAAAA Sheet 01 SHEET UPDATED R

Fig. A-GABAA

Fig. A-GABAA Sheet 04 SHEET UPDATED R

Fig. A-GABAA Sheet 08 SHEET UPDATED R

Fig. A-GABAA Sheet 09 SHEET UPDATED R

FILLING INSTRUCTIONS

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

Replace the complete document.

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

HISTORY OF PREVIOUS REVISIONS

No previous revision

REVISION SEQUENCE

ORIGINAL: Feb 07/13

REVISION No. : 01 - Aug 20/14

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 4

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@A330

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 55

TITLE: STABILIZERS - RUDDER SIDE SHELL SANDWICH REPAIR

INSPECTION

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

On AIRBUS Single Aisle, Long Range and Wide Body family aircraft, the rudder side shell is a

sandwich structure made of Carbon Fiber Reinforced Plastic (CFRP) and Glass Fiber Reinforced Plastic

(GFRP) with a honeycomb core. A case of skin damage was reported on a composite side panel of a

rudder installed on an A310 aircraft. Investigations have shown that the damage started from a skin

panel area previously repaired in-service. This repair was performed as per A310 SRM 55-41-12 Fig.

204 procedure. The new damage has been identified as a damage between the core and the skin in

the repaired area. This new damage has developed during normal operations due to the variation of

pressure during ground-air-ground cycles.

Following the above mentioned damage scenario, it has been identified that SRM procedures need to

be improved to ensure an adequate repair quality. An improper bonding between skin and core during a

repair may lead to a damage initiation and propagation, which may not be detectable visually. A large

rudder damage, resulting from an undetected damage growth, could affect the handling quality of the

aircraft.

This Service Bulletin details the inspection procedure to inspect affected rudders fitted on A330 aircraft

for potential damage.

Different inspection procedures are necessary:

- Pulse thermography inspection

- Elasticity Laminate Checker (ELCH) inspection

- Ultrasonic Testing (UT) inspection.

- Tap test inspection.

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 1

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@A330

SERVICE BULLETIN

SUMMARY

The accomplishment of this Service Bulletin will contribute to detect potential damage around in-service

repairs accomplished on rudders made of Carbon Fiber Reinforced Plastic (CFRP) and Glass Fiber

Reinforced Plastic (GFRP) with a honeycomb core.

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.

MATERIAL PRICE INFORMATION

No Material

EFFECTIVITY

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

11S 31V 36V 38W 39V 69X AAR AAW ABD ACA ACI AEA AFL

AFR AIB AIC ALK ARA ARG ASY AVA AZA BEC BEL BER CAL

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

EDW EIN ETD EVA EVE FIN FWI GFA GIA GRL HAL HDA HFY

HVN I2L ISS IYE JAI JAV JST KAL KLM MAS MAU MEA MON

MSR OHY OMA PAL QAF QFA QTR RJA RSF RSY SAI SAS SIA

SVA SWR SYA TAE TAM TAP TCX THA THY TOW TSC UAE UAF

USA VKG VOZ WRC XAX XLF

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER OIT 999.0017/10 OIT 999.0071/10 OIT 999.0130/06 OIT

999.0067/12 AD 2014-0033

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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@A330

SERVICE BULLETIN

SUMMARY

SOFT NO

OBRM NO

MANPOWER

Task 553043-832-848-001: Inspection

TOTAL MANHOURS 38.00

APPENDICES

None

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 3

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@A330

SERVICE BULLETIN

SUMMARY

**CONF ALL

Z326

A

G_SB_553043_6_SAAA_01_00

RUDDER SHELL

TO BE INSPECTED

B

B A

RH SHOWN LH SHOWN

Figure A-GSAAA - Sheet 01

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 4

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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: 55

TITLE: STABILIZERS - RUDDER SIDE SHELL SANDWICH REPAIR

INSPECTION

MODIFICATION No.: None

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

NOTE: This Service Bulletin is applicable to all rudders with the Serial Number (SN)

from TS-1001 to TS-1043, SN TS-2001 to TS-2074, SN TS-3000 to TS-3525,

SN TS-4001 to TS-4170, or SN TS-6001 to TS-6246.

NOTE: Repairs of rudder side shells which have been accomplished in accordance

with a SRM procedure older than SRM April 2010 revision, must be inspected

in accordance with this Service Bulletin.

NOTE: In the case of a rudder originally fitted on one aircraft (refer to AIR delivery

document) that has been removed and installed on another aircraft, it is the

responsibility of the operator to apply the required instructions contained in

this Service Bulletin to the new aircraft.

NOTE: In case of doubt, contact AIRBUS.

(1) Models

330-202 330-203 330-223 330-243 330-301 330-302 330-303 330-321

330-322 330-323 330-341 330-342 330-343

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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@A330

SERVICE BULLETIN

(2) Effectivity by MSN

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

0903-0909 0911 0913-0916 0918-0920 0922-0923 0926-0928 0930-0932 0934-0937

0939-0952 0954 0956-0959 0961-0971 0973-0980 0982-0986 0988-0992 0994-1003

1006-1016 1018-1023 1025-1026 1028-1029 1031 1033 1035-1038 1041-1049

1052-1053 1055 1057-1058 1060-1061 1063 1065-1067 1069 1071-1078 1080-1082

1084-1090 1093-1101 1103-1108 1110 1112 1114 1116 1118 1120 1123-1124

1126-1127 1129-1130 1132-1133 1135 1137-1138

(3) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the time

of issue in accordance with the information available to AIRBUS. Any future changes

resulting from transfer of an aircraft from one operator to another will not be reflected in

this list unless the Service Bulletin is revised for another reason.

OPERATOR MSN

11S 1053

31V 0205

36V 0437 0451

38W 0401

39V 0939

69X 0494

AAR 0640 0676 0708 0772 0803 0845 1001 1055

AAW 0999 1043

ABD 0343

ACA 0277 0279 0284 0344 0400 0408 0412 0419

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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@A330

SERVICE BULLETIN

OPERATOR MSN

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

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

0567 0584 0657

AIB 0871

AIC 0353 0362

ALK 0303 0306 0311 0313 0404 0456 0627

ARA 0874 0891 0927

ARG 0290 0300 0358 0364

ASY 0747 0951 0969 1036

AVA 0948 0967 1009 1016 1073

AZA 0272 0339 1123 1135

BEC 0863

BEL 0030 0037 0045 0082 0095 0229 0249 0324

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

0828 0911

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

0823 0838 0861 0920

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

0884 0890 0903 0909 0930 0941 0944 0957 1087 1110 1130

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

0836 0851 0862 0866 0916 0928 0936 0942

CHH 0875 0881 0906 0919 0982

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

0548 0565 0679 0776 0850 0855 0895 0915 0959

CRK 1031 1042

CRL 0285 0320

CSA 0425

CSC 0462 1082 1138

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

0958 0964 1096 1116 1129

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

EDW 0291

EIN 0269 0397 0841 0847 0985 1025 1106

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

0825 0831 0832 0852 0854 0868 0885 0888 0923 0975 0991 1071

1081

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

EVE 0833

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SERVICE BULLETIN

OPERATOR MSN

FIN 0994 1007 1013 1023 1067 1078 1088

FWI 0253 0758 0965 1021

GFA 0276 0281 0286 0287 0334 0340

GIA 0138 0140 0144 0148 0153 0165 0988 1020 1028 1052

GRL 0230

HAL 1104 1114

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

0479 0512 0581 0654 0669 0673

HFY 0096 0127 0211 0262 1008

HVN 0275 0294 0299 0366 0943 0946 0962 1019

I2L 0527 0532 0725

ISS 0802

IYE 0625 0632

JAI 0947 0956

JAV 0255

JST 0506 0508 0513 0522 0842 0853 0940 0945

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

0351 0368 0428 0484 0490 0550 1133

KLM 0682 0686 0703 0738 0770 0801 0811 0819 0834 0900

MAS 0067 0116 0119

MAU 0883 1057

MEA 0926 0984 0995 0998

MON 0261 0265

MSR 0600 0610 0666 0683 0696 0709 0726

OHY 0072 0087 0098 0143

OMA 1038 1044 1049 1063 1093 1120

PAL 0183 0184 0188 0189 0191 0198 0200 0203

QAF 0487 0605

QFA 0553 0558 0564 0574 0593 0595 0603 0695 0705 0712 0887 0892

0898 0976 1061 1094

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

RJA 0970 0979 1002

RSF 0980 0996

RSY 0120 0171

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

SVA 1108 1127 1137

SWR 1000 1018 1026 1029 1084 1089 1101

SYA 0345

TAE 0348

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

0949 0961 0968 0977 1112 1118

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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@A330

SERVICE BULLETIN

OPERATOR MSN

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

TCX 0254 0266 0301 0398

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

0990 1003 1035 1037 1060 1074 1086 1090

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

TOW 1033 1046

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

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

1069 1076 1095 1100

VKG 0309 0349 0356 0357

VOZ 0365 0372

WRC 0296

XAX 0054 0330 0662 0692 0716 0741 0786 0952 0974 1048 1066 1075

1126

XLF 0501 0635

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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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 0067 0070 0071 0072 0082 0083 0086 0087 0095

0096 0098 0099 0102 0106 0109 0111 0112 0113 0116 0118

0119 0120 0121 0122 0127 0132 0138 0140 0143 0144 0148

0153 0155 0162 0165 0171 0172 0177 0181 0183 0184 0188

0189 0191 0195 0198 0200 0203 0205 0206 0209 0211 0219

0222 0223 0224 0226 0229 0230 0231 0232 0234 0238 0240

0241 0244 0247 0248 0249 0250 0251 0253 0254 0255 0256

0258 0259 0261 0262 0265 0266 0267 0269 0271 0272 0275

0276 0277 0279 0281 0283 0284 0285 0286 0287 0288 0290

0291 0293 0294 0295 0296 0299 0300 0301 0303 0305 0306

0308 0309 0311 0312 0313 0314 0315 0316 0317 0320 0322

0323 0324 0326 0328 0330 0333 0334 0337 0338 0339 0340

0342 0343 0344 0345 0346 0348 0349 0350 0351 0353 0356

0357 0358 0361 0362 0364 0365 0366 0368 0369 0370 0372

0375 0380 0382 0384 0386 0388 0389 0392 0393 0396 0397

0398 0400 0401 0403 0404 0405 0407 0408 0409 0412 0418

0419 0420 0421 0422 0423 0425 0427 0428 0432 0437 0439

0441 0443 0444 0448 0451 0452 0454 0455 0456 0458 0461

0462 0463 0465 0466 0469 0472 0473 0476 0477 0479 0480

0481 0484 0486 0487 0489 0490 0491 0493 0494 0496 0497

0498 0500 0501 0502 0503 0504 0505 0506 0507 0508 0509

0510 0511 0512 0513 0515 0516 0518 0519 0521 0522 0524

0525 0526 0527 0529 0530 0532 0533 0535 0536 0539 0542

0548 0549 0550 0551 0552 0553 0555 0558 0564 0565 0567

0568 0570 0571 0573 0574 0576 0578 0579 0581 0584 0587

0588 0591 0593 0595 0597 0600 0602 0603 0605 0607 0609

0610 0612 0614 0616 0618 0620 0621 0623 0625 0627 0629

0631 0632 0633 0634 0635 0636 0637 0638 0640 0641 0642

0644 0645 0647 0648 0649 0650 0652 0653 0654 0655 0656

0657 0658 0659 0661 0662 0663 0664 0665 0666 0667 0669

0670 0671 0673 0674 0675 0676 0678 0679 0680 0682 0683

0684 0686 0687 0688 0690 0691 0692 0693 0695 0696 0697

0699 0700 0701 0703 0704 0705 0707 0708 0709 0711 0712

0713 0714 0716 0717 0718 0720 0721 0722 0724 0725 0726

0728 0729 0730 0732 0733 0734 0735 0737 0738 0739 0741

0742 0743 0745 0746 0747 0749 0750 0751 0752 0754 0755

0756 0758 0759 0760 0769 0770 0772 0773 0774 0776 0777

0778 0780 0781 0782 0784 0785 0786 0788 0789 0791 0792

0795 0796 0797 0799 0801 0802 0803 0805 0806 0807 0809

0810 0811 0813 0814 0815 0817 0818 0819 0820 0821 0822

0823 0824 0825 0826 0827 0828 0830 0831 0832 0833 0834

0836 0838 0839 0840 0841 0842 0843 0845 0847 0849 0850

0851 0852 0853 0854 0855 0857 0858 0859 0860 0861 0862

0863 0865 0866 0867 0868 0869 0871 0873 0874 0875 0876

0877 0879 0881 0882 0883 0884 0885 0887 0888 0889 0890

0891 0892 0893 0895 0896 0898 0899 0900 0901 0903 0904

0905 0906 0907 0908 0909 0911 0913 0914 0915 0916 0918

0919 0920 0922 0923 0926 0927 0928 0930 0931 0932 0934

001

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 6

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SERVICE BULLETIN

MSN CONFIGURATION

0935 0936 0937 0939 0940 0941 0942 0943 0944 0945 0946

0947 0948 0949 0950 0951 0952 0954 0956 0957 0958 0959

0961 0962 0963 0964 0965 0966 0967 0968 0969 0970 0971

0973 0974 0975 0976 0977 0978 0979 0980 0982 0983 0984

0985 0986 0988 0989 0990 0991 0992 0994 0995 0996 0997

0998 0999 1000 1001 1002 1003 1006 1007 1008 1009 1010

1011 1012 1013 1014 1015 1016 1018 1019 1020 1021 1022

1023 1025 1026 1028 1029 1031 1033 1035 1036 1037 1038

1041 1042 1043 1044 1045 1046 1047 1048 1049 1052 1053

1055 1057 1058 1060 1061 1063 1065 1066 1067 1069 1071

1072 1073 1074 1075 1076 1077 1078 1080 1081 1082 1084

1085 1086 1087 1088 1089 1090 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

1132 1133 1135 1137 1138

001

(5) Configuration definition

**CONF 001

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

standard configuration.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLD01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

On AIRBUS Single Aisle, Long Range and Wide Body family aircraft, the rudder side

shell is a sandwich structure made of Carbon Fiber Reinforced Plastic (CFRP) and

Glass Fiber Reinforced Plastic (GFRP) with a honeycomb core. A case of skin damage

was reported on a composite side panel of a rudder installed on an A310 aircraft.

Investigations have shown that the damage started from a skin panel area previously

repaired in-service. This repair was performed as per A310 SRM 55-41-12 Fig. 204

procedure. The new damage has been identified as a damage between the core and the

skin in the repaired area. This new damage has developed during normal operations due

to the variation of pressure during ground-air-ground cycles.

Following the above mentioned damage scenario, it has been identified that SRM

procedures need to be improved to ensure an adequate repair quality. An improper

bonding between skin and core during a repair may lead to a damage initiation and

propagation, which may not be detectable visually. A large rudder damage, resulting

from an undetected damage growth, could affect the handling quality of the aircraft.

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 7

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SERVICE BULLETIN

(2) Objective/Action

This Service Bulletin details the inspection procedure to inspect affected rudders fitted

on A330 aircraft for potential damage.

Different inspection procedures are necessary:

- Pulse thermography inspection

- Elasticity Laminate Checker (ELCH) inspection

- Ultrasonic Testing (UT) inspection.

- Tap test inspection.

(3) Advantages

The accomplishment of this Service Bulletin will contribute to detect potential damage

around in-service repairs accomplished on rudders made of Carbon Fiber Reinforced

Plastic (CFRP) and Glass Fiber Reinforced Plastic (GFRP) with a honeycomb core.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

NOTE: The listed subtasks are not in sequence with the work steps.

To accomplish this Service Bulletin it is necessary to :

Task 553043-832-848-001: Inspection

(1) Check the rudder repair records

(2) Identify the type, location and size of in-service repairs on the rudder side shell

CFRP areas in case of complete repair records since rudder Entry Into Service (EIS) are

available

(3) Do a pulse thermography inspection on the complete rudder side shell CFRP areas

to identify possible rudder in-service repairs in case of repair records are not complete or

not available

(4) Do the corrective actions in case of fluid ingress detected

(5) Do the ELCH and/or UT inspection around identified repairs/fluid ingress

(6) Do terminating actions in case of no damage detected

(7) Inspect the rudder side shell upper GFRP areas

(8) Close the holes in case of drilling thru the outer skin during paint thickness

measurement

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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SERVICE BULLETIN

(9) Identify the repair size by local sanding

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.

Table 1, Config. 001 - Rudder special detailed inspection for repair detection

Condition Action Compliance time Repetitive interval

All aircraft Identify the Serial

Number of the installed

rudder in accordance

with the accomplishment

instructions Subtask

553043-832-202-001

Within 4 months from

original Service Bulletin

issue date

None

All aircraft Check the completeness

of the rudder repair

records

Within 4 months from

original Service Bulletin

issue date

None

All aircraft Report information

about the repair records

to AIRBUS

Within 4 months from

original Service Bulletin

issue date

None

Repair records are not

complete or not

available

Continue with the

actions given in table 2A

for CFRP areas

Refer to table 2A Refer to table 2A

Repair records are not

complete or not

available

Continue with the

actions given in table 2B

for GFRP areas

Refer to table 2B Refer to table 2B

Complete repair records

since rudder Entry Into

Service (EIS) are

available

Continue with the

actions given in table

2C for CFRP areas

Refer to table 2C Refer to table 2C

Complete repair records

since rudder EIS are

available

Continue with the

actions given in table

2D for GFRP areas

Refer to table 2D Refer to table 2D

Table 2A, Config. 001 - Repair records are not complete or not available (CFRP areas)

Condition Action Compliance time Repetitive interval

Repair records are not

complete or not

available

Report undocumented

rudder Serial Number

list to AIRBUS to get

related rudder

manufacturing rework

data

3 months in advance

before pulse

thermography inspection

is scheduled

None

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 9

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SERVICE BULLETIN

Table 2A, Config. 001 - Repair records are not complete or not available (CFRP areas)

Condition Action Compliance time Repetitive interval

Repair records are not

complete or not

available

Make sure that the paint

thickness in all areas to

be inspected does not

exceed the limits given

in the accomplishment

instructions Subtask

553043-832-203-001

Within 24 months from

original Service Bulletin

issue date, before the

pulse thermography

inspection

None

Repair records are not

complete or not

available

Do a pulse

thermography inspection

on the complete side

shells (LH/RH) to

identify repairs in

accordance with the

accomplishment

instructions Subtask

553043-832-203-001

Within 24 months from

original Service Bulletin

issue date

None

No repair detected Report to AIRBUS

No further action

necessary in

accordance with this

Service Bulletin

Within 1 month from the

pulse thermography

inspection

None

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

Report to AIRBUS Within 1 month from the

pulse thermography

inspection

None

Repairs in the booster

area > 55000 mm2

(85.25 sq.in.) or not in

the booster area

detected during pulse

thermography inspection

Do an ELCH and/or UT

inspection around the

identified repairs in

accordance with the

accomplishment

instructions Subtask

553043-832-206-001

Within 24 months from

original Service Bulletin

issue date

None

Fluid ingress detected

during pulse

thermography/UT

inspection

Continue with the

actions given in table 3

Refer to table 3 Refer to table 3

Damage detected during

ELCH and/or UT

inspection

Provide a detailed

damage report and

report to AIRBUS and

follow their instructions

Before next flight None

No damage detected

during ELCH and/or UT

inspection

Continue with the

actions given in table 4

Refer to table 4 Refer to table 4

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 10

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SERVICE BULLETIN

Table 2B, Config. 001 - Repair records are not complete or not available (GFRP areas)

Condition Action Compliance time Repetitive interval

Repair records are not

complete or not

available

Make sure that the paint

thickness in all areas to

be inspected does not

exceed the limits given

in the accomplishment

instructions

553043-832-207-001

Within 24 months from

original Service Bulletin

issue date, before the

pulse thermography

inspection

None

Repair records are not

complete or not

available

Do a pulse

thermography inspection

on the complete GFRP

area in accordance with

the accomplishment

instructions Subtask

553043-832-207-001

Within 24 months from

original Service Bulletin

issue date

None

Repair records are not

complete or not

available

In case of findings, mark

the repairs which are

not manufacturing

reworks

Within 24 months from

original Service Bulletin

issue date

None

Repair records are not

complete or not

available

Do a Tap test inspection

on the complete GFRP

area to identify skin to

core disbonding in

accordance with the

accomplishment

instructions Subtask

553043-832-207-001

Within 24 months from

original Service Bulletin

issue date

None

No skin to core

disbonding but repairs

identified

Do an ELCH and/or UT

inspection around the

identified repairs in

accordance with the

accomplishment

instructions Subtask

553043-832-206-001

Within 24 months from

original Service Bulletin

issue date

None

Fluid ingress detected

during pulse

thermography/UT

inspection

Continue with the

actions given in table 3

Refer to table 3 Refer to table 3

Damage detected during

Tap test/ELCH and/or

UT inspection

Provide a detailed

damage report and

report to AIRBUS and

follow their instructions

Before next flight None

No damage detected

during Tap test/ELCH

and/or UT inspection

Continue with the

actions given in table 4

Refer to table 4 Refer to table 4

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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SERVICE BULLETIN

Table 2C, Config. 001 - Repair records since rudder EIS are complete (CFRP areas)

Condition Action Compliance time Repetitive interval

No repair performed or

repair not to be

inspected in accordance

with this Service Bulletin

Report to AIRBUS

No further action

necessary in

accordance with this

Service Bulletin

Within 24 months from

original Service Bulletin

issue date

None

Repair is performed

since rudder EIS

Identify the repair type

in accordance with the

accomplishment

instructions Subtask

553043-832-201-001

Within 24 months from

original Service Bulletin

issue date

None

Repair identified as type

to be inspected

Make sure that the paint

thickness in all areas to

be inspected does not

exceed the limits given

in the accomplishment

instructions Subtask

553043-832-201-001

Within 24 months from

original Service Bulletin

issue date, before the

pulse thermography

inspection

None

Repair identified as type

to be inspected

Do a pulse

thermography inspection

on repair location in

accordance with the

accomplishment

instructions Subtask

553043-832-201-001

or

Identify the repair size

by local sanding, refer

to Subtask

553043-832-208-001

Within 24 months from

original Service Bulletin

issue date

None

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

during pulse

thermography inspection

or local sanding

Report to AIRBUS Within 1 month from

pulse thermography

inspection

None

Repairs in the booster

area > 55000 mm2

(85.25 sq.in.) or not in

the booster area

detected during pulse

thermography inspection

or local sanding

Do an ELCH and/or UT

inspection around the

identified repairs in

accordance with the

accomplishment

instructions Subtask

553043-832-206-001

Within 24 months from

original Service Bulletin

issue date

None

Fluid ingress detected

during pulse

thermography/UT

inspection

Continue with the

actions given in table 3

Refer to table 3 Refer to table 3

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 12

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SERVICE BULLETIN

Table 2C, Config. 001 - Repair records since rudder EIS are complete (CFRP areas)

Condition Action Compliance time Repetitive interval

Damage detected during

ELCH and/or UT

inspection

Provide a detailed

damage report, report to

AIRBUS and follow their

instructions

Before next flight None

No damage detected

during ELCH and/or UT

inspection

Continue with the

actions given in table 4

Refer to table 4 Refer to table 4

Table 2D, Config. 001 - Repair records since rudder EIS are complete (GFRP areas)

Condition Action Compliance time Repetitive interval

No repair performed or

repair not to be

inspected in accordance

with this Service Bulletin

Report to AIRBUS

No further action

necessary in

accordance with this

Service Bulletin

Within 24 months from

original Service Bulletin

issue date

None

Repair performed and

identified as type to be

inspected

Make sure that the paint

thickness in all areas to

be inspected does not

exceed the limits given

in the accomplishment

instructions Subtask

553043-832-207-001

Within 24 months from

original Service Bulletin

issue date, before the

pulse thermography

inspection

None

Repair identified as type

to be inspected

Do a pulse

thermography inspection

on repair location in

accordance with the

accomplishment

instructions Subtask

553043-832-207-001

or

Identify the repair size

by local sanding, refer

to Subtask

553043-832-208-001

Within 24 months from

original Service Bulletin

issue date

None

Repair type A-A

identified

Do a Tap test inspection

on the repair in

accordance with the

accomplishment

instructions Subtask

553043-832-207-001

Within 24 months from

original Service Bulletin

issue date

None

All other repairs Do an ELCH and/or UT

inspection around the

identified repairs in

accordance with the

accomplishment

instructions Subtask

553043-832-206-001

Within 24 months from

original Service Bulletin

issue date

None

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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SERVICE BULLETIN

Table 2D, Config. 001 - Repair records since rudder EIS are complete (GFRP areas)

Condition Action Compliance time Repetitive interval

Fluid ingress detected

during pulse

thermography/UT

inspection

Continue with the

actions given in table 3

Refer to table 3 Refer to table 3

Damage detected during

Tap test/ELCH and/or

UT inspection

Provide a detailed

damage report and

report to AIRBUS and

follow their instructions

Before next flight None

No damage detected

during Tap test/ELCH

and/or UT inspection

Continue with the

actions given in table 4

Refer to table 4 Refer to table 4

Table 3, Config. 001 - Fluid ingress detected

Condition Action Compliance time Repetitive interval

Fluid ingress detected Do an ELCH and/or UT

inspection around the

identified fluid ingress in

accordance with the

accomplishment

instructions Subtask

553043-832-206-001

Before next flight None

Damage detected

around the identified

fluid ingress

Report to AIRBUS and

follow their instructions

Before next flight None

Local single spot fluid

ingress =< 1500 mm2

(2.33 sq.in.) detected

(no damage detected

around the identified

fluid ingress)

Report to AIRBUS Within 1 month from

pulse thermography

inspection

None

Maximum of 5 local

single spots fluid ingress

per side shell > 1500

mm2 (2.33 sq.in.) and

=< 5000 mm2 (7.75

sq.in.) detected (no

damage detected

around the identified

fluid ingress)

Drain by core ventilation

in accordance with the

accomplishment

instructions Subtask

553043-832-204-001

Before next flight None

Core ventilation done Option 1:

Close the holes with

adhesive tape

Before next flight None

Holes closed with tape Option 1:

Do repetitive detailed

inspections of the

restored area for loose

or lost tape

Within 900 FH after

closing the holes

At intervals not

exceeding 900 FH

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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SERVICE BULLETIN

Table 3, Config. 001 - Fluid ingress detected

Condition Action Compliance time Repetitive interval

Loose or lost tape found Option 1:

Close the holes again

with adhesive tape or

refer to Option 2

Before next flight None

Core ventilation done Option 2:

Close the holes with

GFRP plies

Before next flight None

Maximum of 5 local

single spots fluid ingress

per side shell > 1500

mm2 (2.33 sq.in.) and

=< 5000 mm2 (7.75

sq.in.) detected (no

damage detected

around the identified

fluid ingress)

Option 1 and 2:

Repetitive thermography

inspections in

accordance with the

accomplishment

instructions Subtask

553043-832-204-001

Within 1000 FC after

closing the holes

Within intervals of 1000

FC until repair

Maximum of 5 local

single spots fluid ingress

per side shell > 1500

mm2 (2.33 sq.in.) and

=< 5000 mm2 (7.75

sq.in.) detected (no

damage detected

around the identified

fluid ingress)

Do the repair Within 4500 FC, but not

exceeding 24 months

from the first inspection

None

Maximum of 5 local

single spots fluid ingress

per side shell > 1500

mm2 (2.33 sq.in.) and

=< 5000 mm2 (7.75

sq.in.) detected (no

damage detected

around the identified

fluid ingress)

Report to AIRBUS Within 1 month from the

repair

None

More than 5 local single

spots fluid ingress per

side shell > 1500 mm2

(2.33 sq.in.) and =<

5000 mm2 (7.75 sq.in.)

detected (no damage

detected around the

identified fluid ingress)

Report to AIRBUS and

follow their instructions

Before next flight None

Local single spot fluid

ingress > 5000 mm2

(7.75 sq.in.) detected

(no damage detected

around the identified

fluid ingress)

Report to AIRBUS and

follow their instructions

Before next flight None

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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SERVICE BULLETIN

Tables 4.A thru 4.D, Config. 001: No damage detected during ELCH/UT inspection:

For an identified repair size of a maximum of 10000 mm2 (15.50 sq.in.), continue with

table 4.A.

For an identified repair size larger than 10000 mm2 (15.50 sq.in.) and up to 20000 mm2

(31.00 sq.in.), continue with table 4.B.

For an identified repair size larger than 20000 mm2 (31.00 sq.in.) and up to 80000 mm2

(124 sq.in.), continue with table 4.C.

For an identified repair size larger than 80000 mm2 (124 sq.in.), continue with table 4.D.

Table 4.A, Config. 001 - Identified repair size of a maximum of 10000 mm2 (15.50 sq.in.)

Condition Action Compliance time Repetitive interval

Repair size =< 10000

mm2 (15.50 sq.in.)

Provide detailed

information about the

identified repair and

report to AIRBUS

Within 1 month from

ELCH/UT inspection

None

Table 4.B, Config. 001 - Identified repair size larger than 10000 mm2 (15.50 sq.in.) and up to 20000

mm2(31.00 sq.in.)

Condition Action Compliance time Repetitive interval

Repair size > 10000

mm2 (15.50 sq.in.) and

=< 20000 mm2 (31.00

sq.in.)

Option 1:

Do the core ventilation

thru the inner skin in

accordance with the

accomplishment

instructions Subtask

553043-832-205-001

Before next flight None

Core ventilation done Option 1:

Hole closing option 1:

Close the holes with

adhesive tape

Before next flight None

Holes closed with tape Option 1:

Hole closing option 1:

Do repetitive detailed

inspections of the

restored area for loose

or lost tape

Within 900 FH after

closing the holes

At intervals not

exceeding 900 FH

Loose or lost tape found Option 1:

Hole closing option 1:

Close the holes again

with adhesive tape or

refer to hole closing

option 2

Before next flight None

Core ventilation done Option 1:

Hole closing option 2:

Close the holes with

GFRP plies

Before next flight None

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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SERVICE BULLETIN

Table 4.B, Config. 001 - Identified repair size larger than 10000 mm2 (15.50 sq.in.) and up to 20000

mm2(31.00 sq.in.)

Condition Action Compliance time Repetitive interval

Core ventilation done Option 1:

Report detailed

information about the

identified repair and the

planned terminating

action to AIRBUS

Within 1 month from first

ELCH/UT inspection

None

Core ventilation done Option 1:

Do the repair in

accordance with the

SRM at the identified

repair location

Within 4500 FC, not

exceeding 24 months,

from the first inspection

date

None

Repair size > 10000

mm2 (15.50 sq.in.) and

=< 20000 mm2 (31.00

sq.in.)

Option 2:

Do repetitive ELCH/UT

inspections around the

identified repair area in

accordance with the

accomplishment

instructions Subtask

553043-832-206-001

Within 900 FH from first

ELCH/UT inspection

Every 900 FH from last

ELCH/UT inspection

Findings during

repetitive ELCH/UT

inspections

Option 2:

Report to AIRBUS and

follow their instructions

Before next flight None

No findings during

repetitive ELCH/UT

inspections

Option 2:

Report detailed

information about the

identified repair and the

planned terminating

action to AIRBUS

Within 1 month from

ELCH/UT inspection

None

No findings during

repetitive ELCH/UT

inspections

Option 2:

Do the repair in

accordance with the

SRM at the identified

repair location

Within 4500 FC, not

exceeding 24 months,

from the first inspection

date

None

Table 4.C, Config. 001 - Identified repair size larger than 20000 mm2 (31.00 sq.in.) and up to 80000

mm2 (124 sq.in.)

Condition Action Compliance time Repetitive interval

Repair size > 20000

mm2 (31.00 sq.in.) and

=< 80000 mm2 (124

sq.in.)

Do the core ventilation

thru inner skin in

accordance with the

accomplishment

instructions Subtask

553043-832-205-001

Before next flight None

Core ventilation done Option 1:

Close the holes with

adhesive tape

Before next flight None

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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SERVICE BULLETIN

Table 4.C, Config. 001 - Identified repair size larger than 20000 mm2 (31.00 sq.in.) and up to 80000

mm2 (124 sq.in.)

Condition Action Compliance time Repetitive interval

Holes closed with tape Option 1:

Do repetitive detailed

inspections of the

restored area for loose

or lost tape

Within 900 FH after

closing the holes

At intervals not

exceeding 900 FH

Loose or lost tape found Option 1:

Close the holes again

with adhesive tape or

refer to Option 2

Before next flight None

Core ventilation done Option 2:

Close the holes with

GFRP plies

Before next flight None

Repair size > 20000

mm2 (31.00 sq.in.) and

=< 80000 mm2 (124

sq.in.)

Report detailed

information about the

identified repair and the

planned terminating

action to AIRBUS

Within 1 month from first

ELCH/UT inspection

None

Core ventilation done

and repair size =<

30000 mm2 (46.50

sq.in.)

Do the repair in

accordance with the

SRM at the identified

repair location

Within 4500 FC, not

exceeding 24 months,

from the first inspection

date

None

Core ventilation done

and repair size > 30000

mm2 (46.50 sq.in.) and

=< 80000 mm2 (124

sq.in.)

Do the repair in

accordance with the

SRM and additional

instructions from

AIRBUS

Within 4500 FC, not

exceeding 24 months,

from the first inspection

date

None

Table 4.D, Config. 001 - Identified repair size larger than 80000 mm2 (124 sq.in.)

Condition Action Compliance time Repetitive interval

Repair size > 80000

mm2 (124 sq.in.)

Do the core ventilation

thru inner skin in

accordance with the

accomplishment

instructions Subtask

553043-832-205-001

Before next flight None

Core ventilation done Option 1:

Close the holes with

adhesive tape

Before next flight None

Holes closed with tape Option 1:

Do repetitive detailed

inspections of the

restored area for loose

or lost tape

Within 900 FH after

closing the holes

At intervals not

exceeding 900 FH

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Table 4.D, Config. 001 - Identified repair size larger than 80000 mm2 (124 sq.in.)

Condition Action Compliance time Repetitive interval

Loose or lost tape found Option 1:

Close the holes again

with adhesive tape or

refer to Option 2

Before next flight None

Core ventilation done Option 2:

Close the holes with

GFRP plies

Before next flight None

Repair size > 80000

mm2 (124 sq.in.)

Report detailed

information about the

identified repair and the

planned terminating

action to AIRBUS

Within 1 month from first

ELCH/UT inspection

None

Repair size > 80000

mm2 (124 sq.in.)

Replace the affected

rudder shell

OR

Replace the rudder

No further action

necessary in

accordance with this

Service Bulletin

Within 4500 FC, not

exceeding 24 months,

from the first inspection

date

None

Table 5, Config. 001 - Hole closing in case of damaged outer skin during paint thickness

measurement

Condition Action Compliance time Repetitive interval

Sandwich structure

damaged

Option 1:

Close the holes with

resin and adhesive tape

Before next flight None

Holes closed Option 1:

Restore the surface

protection

Within 4500 FC from the

pulse thermography

inspection

None

Sandwich structure

damaged

Option 2:

Do the permanent

restoration procedure

Before next flight None

Table 6.A, Config. 001 - Identify the repair size by local sanding

Condition Action Compliance time Repetitive interval

Repair performed and

identified as type to be

inspected

Identify paint thickness

and primer

Within 24 months from

original Service Bulletin

issue date

None

Repair performed and

identified as type to be

inspected

Do local sanding on top

and around the repair

up to the initial basic

primer

Within 24 months from

original Service Bulletin

issue date

None

Largest repair ply is not

visible

Continue with the

actions given in table

6.B

Before next flight None

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Table 6.A, Config. 001 - Identify the repair size by local sanding

Condition Action Compliance time Repetitive interval

Largest repair ply is

visible

Remove the dust and

dry the area

Before next flight None

Largest repair ply is

visible

Inspect the sanded area

for damage

Before next flight None

Damage found Do the damage

assessment

Before next flight None

No damage found Mark the repair on the

rudder surface

Before next flight None

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

Restore the surface

protection

Before next flight None

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

Report to AIRBUS Within 1 month None

Repairs in the booster

area > 55000 mm2

(85.25 sq.in.) or not in

the booster area

detected

Do an ELCH and/or UT

inspection around the

identified repairs in

accordance with the

accomplishment

instructions Subtask

553043-832-206-001

Before next flight None

Fluid ingress detected

during UT inspection

Continue with the

actions given in table 3

Refer to table 3 Refer to table 3

Damage detected during

ELCH and/or UT

inspection

Provide a detailed

damage report, report to

AIRBUS and follow their

instructions

Before next flight None

No damage detected

during ELCH and/or UT

inspection

Continue with the

actions given in table 4

Refer to table 4 Refer to table 4

Table 6.B, Config. 001 - Identify the repair size by local sanding - largest repair ply not visible

Condition Action Compliance time Repetitive interval

Largest repair ply is not

visible

Continue local sanding

up to the pore

filler/adhesive

Before next flight None

Largest repair ply is

visible now

Remove the dust and

dry the area

Before next flight None

Largest repair ply is still

not visible

Continue with the

actions given in table

6.C for CFRP areas and

table 6.D for GFRP

areas

Before next flight None

Largest repair ply is

visible now

Inspect the sanded area

for damage

Before next flight None

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Table 6.B, Config. 001 - Identify the repair size by local sanding - largest repair ply not visible

Condition Action Compliance time Repetitive interval

Damage found Do the damage

assessment

Before next flight None

No damage found Mark the repair on the

rudder surface

Before next flight None

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

Restore the surface

protection

Before next flight None

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

Report to AIRBUS Within 1 month None

Repairs in the booster

area > 55000 mm2

(85.25 sq.in.) or not in

the booster area

detected

Do an ELCH and/or UT

inspection around the

identified repairs in

accordance with the

accomplishment

instructions Subtask

553043-832-206-001

Before next flight None

Fluid ingress detected

during UT inspection

Continue with the

actions given in table 3

Refer to table 3 Refer to table 3

Damage detected during

ELCH and/or UT

inspection

Provide a detailed

damage report, report to

AIRBUS and follow their

instructions

Before next flight None

No damage detected

during ELCH and/or UT

inspection

Continue with the

actions given in table 4

Refer to table 4 Refer to table 4

Table 6.C, Config. 001 - Do the pulse thermography inspection (CFRP areas)

Condition Action Compliance time Repetitive interval

Largest repair ply is still

not visible

Do a pulse

thermography inspection

on repair location in

accordance with the

accomplishment

instructions Subtask

553043-832-201-001

Before next flight None

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

during pulse

thermography inspection

Restore the surface

protection

Before next flight None

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

during pulse

thermography inspection

Report to AIRBUS Within 1 month None

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Table 6.C, Config. 001 - Do the pulse thermography inspection (CFRP areas)

Condition Action Compliance time Repetitive interval

Repairs in the booster

area > 55000 mm2

(85.25 sq.in.) or not in

the booster area

detected during pulse

thermography inspection

Do an ELCH and/or UT

inspection around the

identified repairs in

accordance with the

accomplishment

instructions Subtask

553043-832-206-001

Before next flight None

Fluid ingress detected

during pulse

thermography/UT

inspection

Continue with the

actions given in table 3

Refer to table 3 Refer to table 3

Damage detected during

ELCH and/or UT

inspection

Provide a detailed

damage report, report to

AIRBUS and follow their

instructions

Before next flight None

No damage detected

during ELCH and/or UT

inspection

Continue with the

actions given in table 4

Refer to table 4 Refer to table 4

Table 6.D, Config. 001 - Do the pulse thermography inspection (GFRP areas)

Condition Action Compliance time Repetitive interval

Repair identified as type

to be inspected

Do a pulse

thermography inspection

on repair location in

accordance with the

accomplishment

instructions Subtask

553043-832-207-001

Before next flight None

Repair type A-A

identified

Do a Tap test inspection

on the identified repair

in accordance with the

accomplishment

instructions Subtask

553043-832-207-001

Before next flight None

All other repairs Do an ELCH and/or UT

inspection around the

identified repairs in

accordance with the

accomplishment

instructions Subtask

553043-832-206-001

Before next flight None

Fluid ingress detected

during pulse

thermography/UT

inspection

Continue with the

actions given in table 3

Refer to table 3 Refer to table 3

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SERVICE BULLETIN

Damage detected during

Tap test/ELCH and/or

UT inspection

Provide a detailed

damage report, report to

AIRBUS and follow their

instructions

Before next flight None

No damage detected

during ELCH and/or UT

inspection

Continue with the

actions given in table 4

Refer to table 4 Refer to table 4

F. APPROVAL

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

Approval No. EASA.21J.031.

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

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

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

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

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

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

included.

Task 553043-832-848-001: Inspection

Get Access 1.00

On Aircraft

Check the rudder repair records 4.00

Identify the type, location and size of in-service repairs

on the rudder side shell CFRP areas in case of

complete repair records since rudder Entry Into Service

(EIS) are available

0

Do a pulse thermography inspection on the complete

rudder side shell CFRP areas to identify possible

rudder in-service repairs in case of repair records are

not complete or not available

32.00

Do the corrective actions in case of fluid ingress

detected

0

Do the ELCH and/or UT inspection around identified

repairs/fluid ingress

0

Do terminating actions in case of no damage detected 0

Inspect the rudder side shell upper GFRP areas 0

Close the holes in case of drilling thru the outer skin

during paint thickness measurement

0

Identify the repair size by local sanding 0

Close-Up 1.00

TOTAL MANHOURS 38.00

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SERVICE BULLETIN

NOTE: Manhours and elapsed time depend on the size of the area to be inspected.

Find below a table with the information for the manhours, elapsed time

and number of persons per 1 m2 (1550 sq.in.) for the different inspection

procedures:

Steps Manhours Elapsed time Number of

persons

Get access 1.00 0.75 2

Rudder SN

identification

0.25 0.25 1

Pulse

thermography

inspection

1.00 0.50 2

UT inspection 1.25 1.25 1

ELCH inspection 1.50 0.75 1

Tap test inspection 0.25 0.25 1

Local sanding 1.00 1.00 1

Close-up 1.00 0.75 2

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-41-55 12-34-24 20-16-00

29-00-00 55-40-00 55-42-11

Consumable Material List (CML)

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

Non Destructive Test Manual (NTM) 51-10-03 51-10-19 51-10-24

51-10-25 51-10-26 55-40-09

55-40-50

Structural Repair Manual (SRM) 51-23-11 51-75-11 51-75-12

51-77-10 51-77-11

K. PUBLICATION AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

None

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

(2) Price and Availability

None

B. INDUSTRY SUPPORT INFORMATION

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

E-mail : monitored.retrofit@airbus.com

Tel : (33) 5 67 19 06 22

Fax : (33) 5 61 93 27 45

AIRBUS will provide specific industry support for inspection Service Bulletin completion. For

detailed information, please contact your AIRBUS Customer Support Director.

C. LIST OF COMPONENTS

No Kit

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Adhesive Film Tape-- Aluminium

Foil -

05RAB9 As required

Pressure Sensitive Tape 05RFB1 As required

Self-Adhes. Disks 05TNB1 As required

Non Aqueous Cleaner-General 08BAA9 As required

Methyl-Ethyl-Ketone 08BBF1 As required

Trichloroethane Legacy 08BBU9 As required

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Laminating Resin-Epoxy Srm Type

2 -

13EBC1 As required

Textile-Lint Free Cotton 14SBA1 As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

Not Applicable

(2) Tools

To find the correct tool-PN for the different inspection tools, refer to the subsequent

table:

Inspection tool PN

UT inspection UT-equipment Refer to NTM 51-10-24

Tap test inspection Tap test inspection tool Refer to NTM 51-10-03

Tap test inspection (with

Woodpecker)

Function test block

and

Woodpecker

Refer to NTM 51-10-19

ELCH inspection Elasticity Laminate Checker Kit Refer to NTM 51-10-26

Pulse thermography inspection Pulse thermography kit 99A55407324000

Thermography inspection Thermography kit Refer to NTM 51-10-25

Paint thickness measurement Paint Borer Kit Model 518 or 518S or 518MC

with drill measuring range 10 to

1000 and 20 to 2000 microns

To order the pulse thermography kit and the paint borer kit, contact:

For tools on loan:

AIRBUS Material, Logistics and Suppliers

Lease Tool Service

Weg beim Jaeger 150

D-22335 HAMBURG

Germany

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SERVICE BULLETIN

For ordering by internet: http.//spares.airbus.com

For ordering by E-mail: tool.lease@airbus.com

For ordering by fax: +49 40 5076 3225

For tools to buy:

AIRBUS Material, Logistics and Suppliers

IFD- In Flight Desk

Weg beim Jaeger 150

D-22335 HAMBURG

Germany

For ordering by internet: http.//spares.airbus.com

For ordering by E-mail: ifd.spares@airbus.com

For ordering by fax: +49 40 5076 4012

(3) Special Tools

None

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This Page Intentionally Left Blank

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 553043-832-848-001 - Inspection

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

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE CLEANING

AGENTS, ADHESIVES, SEALANTS AND PAINTS. THESE MATERIALS ARE

DANGEROUS.

WARNING: WEAR THE CORRECT PROTECTIVE GLOVES, GOGGLES AND FILTER MASKS

WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS.

THESE MATERIALS ARE DANGEROUS.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS:

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

NECESSARY ON WIRING AND COMPONENTS.

REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER

CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

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

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

operator has an accepted alternative procedure, the accepted alternative procedure

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

the procedure in the AIRBUS document must be used.

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

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

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

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

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

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

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

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

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

compliance times given in this Service Bulletin.

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

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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.

Task Associated Data

Manpower

TOTAL MANHOURS 38.00

A. GENERAL

(1) Subtask 553043-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-55, Page Block 001

Task 20-16-00-912-801

Consumable Material List (CML)

(a) For location of the access panels refer to AMM 06-41-55, Page Block 001.

(b) For the specification of consumable materials (Mat. No.) given in this Service

Bulletin refer to Consumable Material List (CML).

(c) For circuit breaker safety practices refer to AMM Task 20-16-00-912-801.

(d) The purpose of flow charts are for information only to show the vario/Repair phases

described in this Service Bulletin.

(2) Subtask 553043-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

B. PREPARATION

(1) Subtask 553043-941-201-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

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References

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

Task 29-00-00-864-801

Task 29-00-00-864-802

Task 29-00-00-864-803

55-40-00, Page Block 601

Task 55-42-11-000-801

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) In the cockpit, put warning notices in position to tell persons not to operate the flight

controls.

(c) Open, safety and tag the circuit breakers as given in the rudder inspection/check

Job Set-up procedure, refer to AMM 55-40-00, Page Block 601.

(d) Depressurize the Green Hydraulic System, refer to AMM Task 29-00-00-864-801.

(e) Depressurize the Blue Hydraulic System, refer to AMM Task 29-00-00-864-802.

(f) Depressurize the Yellow Hydraulic System, refer to AMM Task 29-00-00-864-803.

(g) Put a warning notice in the cockpit to tell persons not to pressurize the hydraulic

systems.

(h) Put access platform(s) in position at the rudder.

(i) To remove the access panel 326AL from rudders which have not embodied Mod.

No. 40904, refer to AMM Task 55-42-11-000-801.

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C. PROCEDURE

(1) Subtask 553043-832-202-001 - Check the rudder repair records

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills NON DESTRUCTIVE

TESTING

References

Fig. A-GBAAA

Rudder SN identification

Sheet 01

Sheet 02

Fig. A-GBCAA

Repair type identification

Sheet 01 - SRM list

Sheet 02 - RAS list

Fig. A-GBHAA

Report sheet and sketches

Sheet 01 - Pulse thermography report sheet

Sheet 02 - Repair records report sheet

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 16

Fig. A-GBJAA

GFRP area location

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Identify the Serial Number (SN) and the Part Number (PN) of the installed rudder.

1 Check the Aircraft Inspection Report and the maintenance records to verify the

rudder identification and a potential rudder swap since EIS.

2 In case of doubts, check the rudder identification plate on the aircraft, as

shown on Fig. A-GBAAA Sheet 01 for rudder before Modification No. 40904,

or as shown on Fig. A-GBAAA Sheet 02 for rudder after Modification No.

40904.

3 If you do not find a SN/PN placard on the rudder, contact AIRBUS for further

instructions.

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(b) Check the completeness of the rudder records and report the result to AIRBUS.

Use the report sheet Fig. A-GBHAA Sheet 02.

NOTE: This action is not necessary, if the information has been already

sent to AIRBUS in accordance with the OIT 999.0071/10 and the

situation did not change since then.

(c) Check the rudder records if repairs are recorded since rudder EIS.

1 Repairs not affected by this Service Bulletin are those which:

- have been covered by AIRBUS Repair Design Approval Sheet (RDAS)

after April 2010,

- have been done in accordance with the SRM revision April 2010 or later,

- have been accomplished in accordance with the SRM as listed in Fig. AGBCAA Sheet 01,

- are indicated in the AIRBUS Repair Approval Sheet (RAS) repair list Fig.

A-GBCAA Sheet 02 with "ISB inspection required: NO".

NOTE: If you find a RAS which is not listed in the RAS list, contact

AIRBUS and follow their instructions.

2 Report the result to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 02.

NOTE: This action is not necessary, if the information has been

already sent to AIRBUS in accordance with the OIT

999.0071/10 and the situation did not change since then.

3 If repairs are recorded and the repair records are complete, refer to:

- Subtask 553043-832-201-001 of this Service Bulletin for the rudder side

shell areas made of CFRP.

- Subtask 553043-832-207-001 of this Service Bulletin for the upper rudder

side shell areas made of GFRP.

NOTE: The outer skin ply of the upper area of the rudders is made

of GFRP. GFRP areas require different pulse thermography

inspection parameter than CFRP areas and additionally

Tap test inspection or Woodpecker inspection have to be

performed. For the identification of the GFRP areas, refer to

the subsequent table:

Rudder PN Refer to Figure

F55470000 Fig. A-GBJAA Sheet 02

F55471000

F55470005

Fig. A-GBJAA Sheet 03

A55471500 Fig. A-GBJAA Sheet 04

F55471002 Fig. A-GBJAA Sheet 05

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 33

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SERVICE BULLETIN

Rudder PN Refer to Figure

F55471084 Fig. A-GBJAA Sheet 06

4 If no repairs have been duly recorded, report the result to AIRBUS. Use the

report sheet Fig. A-GBHAA Sheet 02.

No further action is necessary in accordance with this Service Bulletin.

5 In case of any doubts about the accomplishment of repairs, refer to:

- Subtask 553043-832-203-001 of this Service Bulletin for the rudder side

shell areas made of CFRP.

- Subtask 553043-832-207-001 of this Service Bulletin for the upper rudder

side shell areas made of GFRP.

6 If the repair records are not complete or not available, refer to:

- Subtask 553043-832-203-001 of this Service Bulletin for the rudder side

shell areas made of CFRP.

- Subtask 553043-832-207-001 of this Service Bulletin for the upper rudder

side shell areas made of GFRP.

NOTE: The outer skin ply of the upper area of the rudders is made

of GFRP. GFRP areas require different pulse thermography

inspection parameter than CFRP areas and additionally

Tap test inspection or Woodpecker inspection have to be

performed. For the identification of the GFRP areas, refer to

the subsequent table:

Rudder PN Refer to Figure

F55470000 Fig. A-GBJAA Sheet 02

F55471000

F55470005

Fig. A-GBJAA Sheet 03

A55471500 Fig. A-GBJAA Sheet 04

F55471002 Fig. A-GBJAA Sheet 05

F55471084 Fig. A-GBJAA Sheet 06

(2) Subtask 553043-832-201-001 - Identify the type, location and size of in-service

repairs on the rudder side shell CFRP areas in case of complete repair records

since rudder Entry Into Service (EIS) are available

Manpower Resources

Manhours 0

Minimum number of person 2

Subtask elapsed time 0

Skills NON DESTRUCTIVE

TESTING

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 34

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SERVICE BULLETIN

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Non Destructive Test Manual (NTM) Task 55-40-50-290-801

Structural Repair Manual (SRM) 51-75-11

51-75-12

Fig. A-GBBAA

Repair type identification

Sheet 01

Sheet 02

Fig. A-GBDAA

Booster area definition

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Fig. A-GBEAA

Typical pulse thermography and

ELCH/UT inspection

Sheet 01

Sheet 02 - Repair size assessment

Sheet 03 - Repair size assessment

Sheet 04 - Boundary and grid of ELCH/UT

inspections

Sheet 05 - ELCH inspection grid

Fig. A-GBHAA

Report sheet and sketches

Sheet 01 - Pulse thermography report sheet

Sheet 02 - Repair records report sheet

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 16

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 35

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SERVICE BULLETIN

References

Fig. A-GFAAA

Flow Chart

Sheet 01 - Flow Chart 1

Sheet 02 - Flow Chart 2

Sheet 03 - Flow Chart 3

Sheet 04 - Flow Chart 4

Sheet 05 - Flow Chart 5

Sheet 06

Fig. A-GABAA

Paint borer instructions

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

(a) If no repair has been done or the recorded repair is not to be inspected in

accordance with this Service Bulletin, report to AIRBUS. Use the report sheet Fig.

A-GBHAA Sheet 02.

NOTE: This action is not necessary, if the information has been already

sent to AIRBUS in accordance with the OIT 999.0071/10 and the

situation did not change since then.

No further action is necessary in accordance with this Service Bulletin.

(b) If a repair must be inspected in accordance with this Service Bulletin, do the

subsequent work steps in accordance with the Flow Chart Fig. A-GFAAA Sheet 01:

1 Identify the repair type, refer to Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA

Sheet 02.

2 Make sure that the paint thickness in the areas to be inspected by pulse

thermography does not exceed:

- 800 microns.

- 400 microns below the decal foil if a decal foil is installed.

NOTE: It is the responsibility of the operator to ensure that the paint

thickness in all areas to be inspected is below or equal to the

limits given above.

a If the paint coating and/or logo application is too thick, abrade the paint in

accordance with the SRM 51-75-11 to a thickness below or equal to the

limits given above.

NOTE: Chemical paint stripping is not allowed.

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 36

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SERVICE BULLETIN

b In case of doubts about the paint thickness, measure the thickness using

a Paint Borer Kit, refer to the Figure Fig. A-GABAA Sheet 01 thru Fig. AGABAA Sheet 09.

<1>

CAUTION: DO NOT DRILL DEEPLY INTO THE BASE

MATERIAL (CFRP OR GFRP). DRILLING TOO

DEEP LEADS TO DAMAGE IN THE OUTER SKIN

If you damage the outer skin with the paint borer, refer to the

Subtask 553043-833-201-001 for repair instructions.

3 Clean the areas to be inspected with:

Non Aqueous

Cleaner-General

08BAA9 As required

and

Textile-Lint Free

Cotton

14SBA1 As required

4 Do a pulse thermography inspection to get the precise location and the size of

the repair, refer to NTM Task 55-40-50-290-801.

NOTE: As an alternative for the pulse thermography inspection, you

can identify the repair size by local sanding, refer to Subtask

553043-832-208-001.

NOTE: The pulse thermography inspection indicates the outer skin

repair ply geometry. The largest repair ply defines the

boundary of the repair area.

NOTE: In case of any findings (repair, damage, fluid ingress) during

the pulse thermography inspection, save the images and send

it together with the report sheet to AIRBUS.

5 Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02 and

Fig. A-GBEAA Sheet 03.

6 If fluid ingress has been detected during the pulse thermography inspection,

refer to Subtask 553043-832-204-001 of this Service Bulletin.

7 Identify the booster areas in accordance with the subsequent table:

Rudder PN Refer to Figure

F55470000 Fig. A-GBDAA Sheet 02 and Fig. A-GBDAA Sheet 03

F55471000

F55470005

Fig. A-GBDAA Sheet 04 and Fig. A-GBDAA Sheet 05

A55471500 Fig. A-GBDAA Sheet 06

F55471002 Fig. A-GBDAA Sheet 07 and Fig. A-GBDAA Sheet 08

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 37

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@A330

SERVICE BULLETIN

Rudder PN Refer to Figure

F55471084 Fig. A-GBDAA Sheet 09 and Fig. A-GBDAA Sheet 10

8 If repairs in the booster areas up to 55000 mm2 (85.25 sq.in.) have been

detected, report the findings to AIRBUS. Use the report sheet Fig. A-GBHAA

Sheet 01 and the rudder related sketches, refer to the subsequent table:

Rudder PN Refer to Figure (sketch)

F55470000 Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04

F55471000

F55470005

Fig. A-GBHAA Sheet 05 and Fig. A-GBHAA Sheet 06

A55471500 Fig. A-GBHAA Sheet 07 and Fig. A-GBHAA Sheet 08

F55471002 Fig. A-GBHAA Sheet 09 and Fig. A-GBHAA Sheet 10

F55471002 (enhanced version) Fig. A-GBHAA Sheet 11 and Fig. A-GBHAA Sheet 12

F55471084 Fig. A-GBHAA Sheet 13 and Fig. A-GBHAA Sheet 16

No further actions on these repairs in accordance with this Service Bulletin.

9 If repairs in the booster areas larger than 55000 mm2 (85.25 sq.in.) have been

detected, do the UT inspection around the repair in accordance with Subtask

553043-832-206-001 of this Service Bulletin.

10 If repairs not in the booster area have been detected, do the ELCH and/or UT

inspection in accordance with Subtask 553043-832-206-001 of this Service

Bulletin.

11 After the inspection, restore the paint coating in accordance with the SRM

51-75-12.

NOTE: Refer to OIT 999.0130/06 ’paint system - best practices’.

(3) Subtask 553043-832-203-001 - Do a pulse thermography inspection on the

complete rudder side shell CFRP areas to identify possible rudder in-service

repairs in case of repair records are not complete or not available

Manpower Resources

Manhours 32.00

Minimum number of person 2

Subtask elapsed time 16

Skills NON DESTRUCTIVE

TESTING

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 38

6

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

SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Textile-Lint Free Cotton 14SBA1 As required

References

Non Destructive Test Manual (NTM) Task 55-40-50-290-801

Structural Repair Manual (SRM) 51-75-11

51-75-12

Fig. A-GFAAA

Flow Chart

Sheet 01 - Flow Chart 1

Sheet 02 - Flow Chart 2

Sheet 03 - Flow Chart 3

Sheet 04 - Flow Chart 4

Sheet 05 - Flow Chart 5

Sheet 06

Fig. A-GBDAA

Booster area definition

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Fig. A-GBHAA

Report sheet and sketches

Sheet 01 - Pulse thermography report sheet

Sheet 02 - Repair records report sheet

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 16

Fig. A-GABAA

Paint borer instructions

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 39

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@A330

SERVICE BULLETIN

(a) Do the subsequent work steps in accordance with the Flow Chart Fig. A-GFAAA

Sheet 01:

1 Report undocumented rudder S/N list to AIRBUS.

a To get related rudder manufacturing rework data, provide AIRBUS

with the rudder P/N, S/N and aircraft MSN in accordance with the

accomplishment timescale instructions, refer to Para 1.E table 2A of this

Service Bulletin.

The manufacturing rework data will be provided through drawings

covered by Mod. 202490.

2 Make sure that the paint thickness in the areas to be inspected by pulse

thermography does not exceed:

- 800 microns.

- 400 microns below the decal foil if a decal foil is installed.

NOTE: It is the responsibility of the operator to ensure that the paint

thickness in all areas to be inspected is below or equal to the

limits given above.

a If the paint coating and/or logo application is too thick, abrade the paint in

accordance with the SRM 51-75-11 to a thickness below or equal to the

limits given above.

NOTE: Chemical paint stripping is not allowed.

b In case of doubts about the paint thickness, measure the thickness using

a Paint Borer Kit, refer to the Figure Fig. A-GABAA Sheet 01 thru Fig. AGABAA Sheet 09.

<1>

CAUTION: DO NOT DRILL DEEPLY INTO THE BASE

MATERIAL (CFRP OR GFRP). DRILLING TOO

DEEP LEADS TO DAMAGE IN THE OUTER SKIN

If you damage the outer skin with the paint borer, refer to the

Subtask 553043-833-201-001 for repair instructions.

3 Clean the areas to be inspected with:

Non Aqueous

Cleaner-General

08BAA9 As required

and

Textile-Lint Free

Cotton

14SBA1 As required

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 40

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@A330

SERVICE BULLETIN

4 Do a pulse thermography inspection on the complete side shell CFRP areas

(LH/RH) to identify repairs, refer to NTM Task 55-40-50-290-801.

NOTE: The pulse thermography inspection indicates the outer skin

repair ply geometry. The largest repair ply defines the

boundary of the repair area.

NOTE: In case of any findings (repair, damage, fluid ingress) during

the pulse thermography inspection, save the images and send

it together with the report sheet to AIRBUS.

5 If no repair has been detected during the pulse thermography inspection,

report the result to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 01.

No further action is necessary in accordance with this Service Bulletin.

6 If fluid ingress has been detected during the thermograhy inspection, refer to

Subtask 553043-832-204-001 of this Service Bulletin.

7 Identify the booster areas in accordance with the subsequent table:

Rudder PN Refer to Figure

F55470000 Fig. A-GBDAA Sheet 02 and Fig. A-GBDAA Sheet 03

F55471000

F55470005

Fig. A-GBDAA Sheet 04 and Fig. A-GBDAA Sheet 05

A55471500 Fig. A-GBDAA Sheet 06

F55471002 Fig. A-GBDAA Sheet 07 and Fig. A-GBDAA Sheet 08

F55471084 Fig. A-GBDAA Sheet 09 and Fig. A-GBDAA Sheet 10

8 If repairs in the booster areas up to 55000 mm2 (85.25 sq.in.) have been

detected which are not manufacturing rework, report the findings to AIRBUS.

Use the report sheet Fig. A-GBHAA Sheet 01 and the rudder related sketches,

refer to the subsequent table:

Rudder PN Refer to Figure (sketch)

F55470000 Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04

F55471000

F55470005

Fig. A-GBHAA Sheet 05 and Fig. A-GBHAA Sheet 06

A55471500 Fig. A-GBHAA Sheet 07 and Fig. A-GBHAA Sheet 08

F55471002 Fig. A-GBHAA Sheet 09 and Fig. A-GBHAA Sheet 10

F55471002 (enhanced version) Fig. A-GBHAA Sheet 11 and Fig. A-GBHAA Sheet 12

F55471084 Fig. A-GBHAA Sheet 13 and Fig. A-GBHAA Sheet 16

No further actions on these repairs in accordance with this Service Bulletin.

9 If repairs in the booster areas larger than 55000 mm2 (85.25 sq.in.) have been

detected which are not manufacturing rework, do the UT inspection around the

repairs in accordance with the Subtask 553043-832-206-001 of this Service

Bulletin.

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 41

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SERVICE BULLETIN

10 If repairs have been detected during the pulse thermography inspection which

are not manufacturing rework and not in the booster areas, do the ELCH

and/or UT inspection around the repairs in accordance with the Subtask

553043-832-206-001 of this Service Bulletin.

11 After the inspection, restore the paint coating in accordance with the SRM

51-75-12.

NOTE: Refer to OIT 999.0130/06 ’paint system - best practices’.

(4) Subtask 553043-832-204-001 - Do the corrective actions in case of fluid ingress

detected

Manpower Resources

Manhours 0

Minimum number of person 1

Subtask elapsed time 0

Skills NON DESTRUCTIVE

TESTING

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Adhesive Film Tape--

Aluminium Foil -

05RAB9 As required

Pressure Sensitive Tape 05RFB1 As required

Self-Adhes. Disks 05TNB1 As required

Methyl-Ethyl-Ketone 08BBF1 As required

Trichloroethane Legacy 08BBU9 As required

Laminating Resin-Epoxy

Srm Type 2 -

13EBC1 As required

References

Non Destructive Test Manual (NTM) 51-10-25

Task 55-40-50-290-801

Fig. A-GFAAA

Flow Chart

Sheet 01 - Flow Chart 1

Sheet 02 - Flow Chart 2

Sheet 03 - Flow Chart 3

Sheet 04 - Flow Chart 4

Sheet 05 - Flow Chart 5

Sheet 06

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 42

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SERVICE BULLETIN

References

Fig. A-GBHAA

Report sheet and sketches

Sheet 01 - Pulse thermography report sheet

Sheet 02 - Repair records report sheet

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 16

Fig. A-GBFAA

Core ventilation procedure

Sheet 01

Sheet 02

Sheet 03

Fig. A-GAAAA

Closing of ventilation holes

Sheet 01

Sheet 02

(a) If fluid ingress has been detected, continue with the subsequent work steps in

accordance with the Flow Chart Fig. A-GFAAA Sheet 03:

1 Around the identified fluid ingress, do the ELCH and/or UT inspection in

accordance with the Subtask 553043-832-206-001 of this Service Bulletin.

2 If a damage has been detected during the ELCH and/or UT inspection, contact

AIRBUS and follow their instructions. Use the report sheet Fig. A-GBHAA

Sheet 01.

3 If local single spots up to 1500 mm2 (2.33 sq.in.) with fluid ingress have been

detected, report the findings to AIRBUS. Use the report sheet Fig. A-GBHAA

Sheet 01 and the rudder related sketches, refer to the subsequent table:

Rudder PN Refer to Figure (sketch)

F55470000 Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04

F55471000

F55470005

Fig. A-GBHAA Sheet 05 and Fig. A-GBHAA Sheet 06

A55471500 Fig. A-GBHAA Sheet 07 and Fig. A-GBHAA Sheet 08

F55471002 Fig. A-GBHAA Sheet 09 and Fig. A-GBHAA Sheet 10

F55471002 (enhanced version) Fig. A-GBHAA Sheet 11 and Fig. A-GBHAA Sheet 12

F55471084 Fig. A-GBHAA Sheet 13 and Fig. A-GBHAA Sheet 16

No further actions on these local single spots of fluid ingress in accordance

with this Service Bulletin.

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 43

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@A330

SERVICE BULLETIN

4 If a maximum of 5 local single spots per side shell larger than 1500 mm2 (2.33

sq.in.) and up to 5000 mm2 (7.75 sq.in.) have been detected, do the ventilation

of the rudder core:

a

CAUTION: TO DRILL THE HOLES APPLY MODERATE

PRESSURE TO PREVENT DAMAGE TO THE SKIN, AT

THE END OF THE DRILLING OPERATION. DO NOT

DRILL THE OPPOSITE SHELL.

Drill the holes to a DIA of 3.0 mm (0.12 in.) through the outer and inner

skin in accordance with the dimensions shown on Fig. A-GBFAA Sheet

02 and Fig. A-GBFAA Sheet 03.

NOTE: Spots of fluid ingress behind the trailing edge screw line

must not be vented.

b Temporary restoration of the drain holes option 1:

<1> Close the drain holes with:

Adhesive Film

Tape-- Aluminium

Foil -

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

<2> Do repetitive detailed inspections of the restored area for loose or

lost adhesive disks or tape until the repair of the affected area has

been done.

<3> In case of loose or lost tape or disks, close the holes again with:

Adhesive Film

Tape-- Aluminium

Foil -

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

c Temporary restoration of the drain holes option 2:

<1> Close the drain holes in accordance with the instructions given in

the Figure Fig. A-GAAAA Sheet 01 and Fig. A-GAAAA Sheet 02.

<a> Consumable Material necessary to close the drain holes:

Pressure Sensitive

Tape

05RFB1 As required

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 44

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@A330

SERVICE BULLETIN

Laminating ResinEpoxy Srm Type 2 -

13EBC1 As required

Methyl-Ethyl-Ketone 08BBF1 As required

Trichloroethane

Legacy

08BBU9 As required

5 Do repetitive thermography inspections until the repair of the affected area

has been done, refer to NTM 51-10-25 (preferred)) or refer to NTM Task

55-40-50-290-801.

NOTE: In case of any findings during the pulse thermography

inspection, save the images and send it together with the

report sheet to AIRBUS.

6 Do the repair in accordance with the SRM.

Due to the pending availability of the SRM improved repair, contact AIRBUS

for detailed repair instructions.

7 Report the repair to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 02.

8 If more than 5 local single spots per side shell larger than 1500 mm2 (2.33

sq.in.) and up to 5000 mm2 (7.75 sq.in.) have been detected, report to

AIRBUS and follow their instructions. Use the report sheet Fig. A-GBHAA

Sheet 01.

9 If local single spots larger than 5000 mm2 (7.75 sq.in.) with fluid ingress have

been detected, report the findings to AIRBUS and follow their instructions. Use

the report sheet Fig. A-GBHAA Sheet 01.

(5) Subtask 553043-832-206-001 - Do the ELCH and/or UT inspection around identified

repairs/fluid ingress

Manpower Resources

Manhours 0

Minimum number of person 1

Subtask elapsed time 0

Skills NON DESTRUCTIVE

TESTING

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9

Textile-Lint Free Cotton 14SBA1

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 45

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@A330

SERVICE BULLETIN

References

Non Destructive Test Manual (NTM) 51-10-24

51-10-26

55-40-09 Para 2.C.

Fig. A-GBEAA

Typical pulse thermography and

ELCH/UT inspection

Sheet 01

Sheet 02 - Repair size assessment

Sheet 03 - Repair size assessment

Sheet 04 - Boundary and grid of ELCH/UT

inspections

Sheet 05 - ELCH inspection grid

Fig. A-GBGAA

Rudder skin thickness identification

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 12

Sheet 13

Sheet 14

Sheet 15

Fig. A-GBHAA

Report sheet and sketches

Sheet 01 - Pulse thermography report sheet

Sheet 02 - Repair records report sheet

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 16

(a) If necessary, clean the areas to be inspected with:

Non Aqueous

Cleaner-General

08BAA9 As required

and

Textile-Lint Free

Cotton

14SBA1 As required

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 46

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@A330

SERVICE BULLETIN

(b) Identify the skin thickness of the areas to be inspected, refer to the subsequent

table:

Rudder PN Refer to Figure

F55470000 Fig. A-GBGAA Sheet 02 and Fig. A-GBGAA Sheet 03

F55471000

F55470005

Fig. A-GBGAA Sheet 04 and Fig. A-GBGAA Sheet 05

A55471500 Fig. A-GBGAA Sheet 06 and Fig. A-GBGAA Sheet 07

F55471002 Fig. A-GBGAA Sheet 08 and Fig. A-GBGAA Sheet 09

F55471002 (enhanced version) Fig. A-GBGAA Sheet 12 and Fig. A-GBGAA Sheet 13

F55471084 Fig. A-GBGAA Sheet 14 and Fig. A-GBGAA Sheet 15

(c) If the skin thickness of the affected areas does not exceed 1.5 mm (0.06 in.), do an

ELCH inspection around the marked repair areas, refer to NTM 51-10-26.

1 For the ELCH inspection, use a grid of 75 mm x 75 mm from the boundary of

the largest repair ply up to 200 mm around the largest repair ply, refer to Fig.

A-GBEAA Sheet 04.

a For the adjustment of the ELCH, refer to NTM 51-10-26.

b For the assessment criteria (yellow and red values) for the ELCH

inspection, refer to NTM 55-40-09 Para 2.C..

(d) If the skin of the affected areas is thicker than 1.5 mm (0.06 in.), do an UT

inspection around the marked repair areas, refer to NTM 51-10-24.

1 Do the UT inspection in an area between the boundary of the largest repair

ply up to 75 mm around the largest repair ply, refer to Fig. A-GBEAA Sheet

04.

(e) If a damage has been detected during the ELCH/UT inspection, provide detailed

information of the identified repair, report to AIRBUS and follow their instructions.

Use the report sheet Fig. A-GBHAA Sheet 02 and the rudder related sketches,

refer to the subsequent table:

Rudder PN Refer to Figure (sketch)

F55470000 Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04

F55471000

F55470005

Fig. A-GBHAA Sheet 05 and Fig. A-GBHAA Sheet 06

A55471500 Fig. A-GBHAA Sheet 07 and Fig. A-GBHAA Sheet 08

F55471002 Fig. A-GBHAA Sheet 09 and Fig. A-GBHAA Sheet 10

F55471002 (enhanced version) Fig. A-GBHAA Sheet 11 and Fig. A-GBHAA Sheet 12

F55471084 Fig. A-GBHAA Sheet 13 and Fig. A-GBHAA Sheet 16

(f) If no damage has been detected during the ELCH/UT inspection, continue with the

steps given in the Subtask 553043-832-205-001 of this Service Bulletin.

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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(6) Subtask 553043-832-205-001 - Do terminating actions in case of no damage

detected

Manpower Resources

Manhours 0

Minimum number of person 1

Subtask elapsed time 0

Skills NON DESTRUCTIVE

TESTING

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Adhesive Film Tape--

Aluminium Foil -

05RAB9 As required

Pressure Sensitive Tape 05RFB1 As required

Self-Adhes. Disks 05TNB1 As required

Methyl-Ethyl-Ketone 08BBF1 As required

Trichloroethane Legacy 08BBU9 As required

Laminating Resin-Epoxy

Srm Type 2 -

13EBC1 As required

References

Fig. A-GBFAA

Core ventilation procedure

Sheet 01

Sheet 02

Sheet 03

Fig. A-GBHAA

Report sheet and sketches

Sheet 01 - Pulse thermography report sheet

Sheet 02 - Repair records report sheet

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 16

Fig. A-GFAAA

Flow Chart

Sheet 01 - Flow Chart 1

Sheet 02 - Flow Chart 2

Sheet 03 - Flow Chart 3

Sheet 04 - Flow Chart 4

Sheet 05 - Flow Chart 5

Sheet 06

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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References

Fig. A-GAAAA

Closing of ventilation holes

Sheet 01

Sheet 02

(a) If no damage has been detected, continue with the subsequent work steps in

accordance with the Flow Chart Fig. A-GFAAA Sheet 02:

1 If a repair up to 10000 mm2 (15.50 sq.in.) has been detected, provide detailed

information about the repair and report to AIRBUS. Use the report sheet Fig.

A-GBHAA Sheet 02 and the rudder related sketches, refer to the subsequent

table:

Rudder PN Refer to Figure (sketch)

F55470000 Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04

F55471000

F55470005

Fig. A-GBHAA Sheet 05 and Fig. A-GBHAA Sheet 06

A55471500 Fig. A-GBHAA Sheet 07 and Fig. A-GBHAA Sheet 08

F55471002 Fig. A-GBHAA Sheet 09 and Fig. A-GBHAA Sheet 10

F55471002 (enhanced version) Fig. A-GBHAA Sheet 11 and Fig. A-GBHAA Sheet 12

F55471084 Fig. A-GBHAA Sheet 13 and Fig. A-GBHAA Sheet 16

2 If a repair larger than 10000 mm2 (15.50 sq.in.) and up to 20000 mm2 (31.00

sq.in.) has been detected, do the ventilation of the core:

NOTE: Instead of the core ventilation procedure, you can do repetitive

ELCH and/or UT inspections around the repair areas until the

repair has been done, refer to Subtask 553043-832-206-001.

a

CAUTION: TO DRILL THE HOLES APPLY MODERATE

PRESSURE TO PREVENT DAMAGE TO THE SKIN, AT

THE END OF THE DRILLING OPERATION. DO NOT

DRILL THE OPPOSITE SHELL.

Drill the holes to a DIA of 3.0 mm (0.12 in.) through the outer and inner

skin in accordance with the dimensions shown on Fig. A-GBFAA Sheet

02 and Fig. A-GBFAA Sheet 03.

NOTE: Repairs behind the trailing edge screw line must not be

vented.

b Temporary restoration of the drain holes option 1:

<1> Close the drain holes with:

Adhesive Film

Tape-- Aluminium

Foil -

05RAB9 As required

or

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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Self-Adhes. Disks 05TNB1 As required

<2> Do repetitive detailed inspections of the restored area for loose or

lost adhesive disks or tape until the repair of the affected area has

been done.

<3> In case of loose or lost tape or disks, close the holes again with:

Adhesive Film

Tape-- Aluminium

Foil -

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

c Temporary restoration of the drain holes option 2:

<1> Close the drain holes in accordance with the instructions given in

the Figure Fig. A-GAAAA Sheet 01 and Fig. A-GAAAA Sheet 02.

<a> Consumable Material necessary to close the drain holes:

Pressure Sensitive

Tape

05RFB1 As required

Laminating ResinEpoxy Srm Type 2 -13EBC1 As required

Methyl-Ethyl-Ketone 08BBF1 As required

Trichloroethane

Legacy

08BBU9 As required

d Report the results and the planned terminating action to AIRBUS. Use

the report sheet Fig. A-GBHAA Sheet 02.

e Do the terminating action in accordance with the SRM.

Due to the pending availability of the SRM improved repair, contact

AIRBUS for detailed repair instructions.

NOTE: The new repair cutout is equal to the largest outer skin

repair ply.

3 If a repair larger than 20000 mm2 (31.00 sq.in.) and up to 80000 mm2 (124

sq.in.) has been detected, do the ventilation of the core:

a

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CAUTION: TO DRILL THE HOLES APPLY MODERATE

PRESSURE TO PREVENT DAMAGE TO THE SKIN, AT

THE END OF THE DRILLING OPERATION. DO NOT

DRILL THE OPPOSITE SHELL.

Drill the holes to a DIA of 3.0 mm (0.12 in.) through the outer and inner

skin in accordance with the dimensions shown on Fig. A-GBFAA Sheet

02 and Fig. A-GBFAA Sheet 03.

b Temporary restoration of the drain holes option 1:

<1> Close the drain holes with:

Adhesive Film

Tape-- Aluminium

Foil -

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

<2> Do repetitive detailed inspections of the restored area for loose or

lost adhesive disks or tape until the repair of the affected area has

been done.

<3> In case of loose or lost tape or disks, close the holes again with:

Adhesive Film

Tape-- Aluminium

Foil -

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

c Temporary restoration of the drain holes option 2:

<1> Close the drain holes in accordance with the instructions given in

the Figure Fig. A-GAAAA Sheet 01 and Fig. A-GAAAA Sheet 02.

<a> Consumable Material necessary to close the drain holes:

Pressure Sensitive

Tape

05RFB1 As required

Laminating ResinEpoxy Srm Type 2 -13EBC1 As required

Methyl-Ethyl-Ketone 08BBF1 As required

Trichloroethane

Legacy

08BBU9 As required

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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d Report the results and the planned terminating action to AIRBUS. Use

the report sheet Fig. A-GBHAA Sheet 02.

e Do the terminating action in accordance with the SRM.

NOTE: The new repair cutout is equal to the largest outer skin

repair ply.

NOTE: If the repair is larger than 30000 mm2 (46.50 sq.in.),

contact AIRBUS for additional instructions.

4 If a repair larger than 80000 mm2 (124 sq.in.) has been detected, do the

ventilation of the core:

a

CAUTION: TO DRILL THE HOLES APPLY MODERATE

PRESSURE TO PREVENT DAMAGE TO THE SKIN, AT

THE END OF THE DRILLING OPERATION. DO NOT

DRILL THE OPPOSITE SHELL.

Drill the holes to a DIA of 3.0 mm (0.12 in.) through the outer and inner

skin in accordance with the dimensions shown on Fig. A-GBFAA Sheet

02 and Fig. A-GBFAA Sheet 03.

b Temporary restoration of the drain holes option 1:

<1> Close the drain holes with:

Adhesive Film

Tape-- Aluminium

Foil -

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

<2> Do repetitive detailed inspections of the restored area for loose or

lost adhesive disks or tape until the repair of the affected area has

been done.

<3> In case of loose or lost tape or disks, close the holes again with:

Adhesive Film

Tape-- Aluminium

Foil -

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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SERVICE BULLETIN

c Temporary restoration of the drain holes option 2:

<1> Close the drain holes in accordance with the instructions given in

the Figure Fig. A-GAAAA Sheet 01 and Fig. A-GAAAA Sheet 02.

<a> Consumable Material necessary to close the drain holes:

Pressure Sensitive

Tape

05RFB1 As required

Laminating ResinEpoxy Srm Type 2 -

13EBC1 As required

Methyl-Ethyl-Ketone 08BBF1 As required

Trichloroethane

Legacy

08BBU9 As required

d Report the results and the planned terminating action to AIRBUS. Use

the report sheet Fig. A-GBHAA Sheet 02.

e Do the terminating action:

Replace the rudder in accordance with the grace period given in the

accomplishment timescale table

or

replace the affected rudder shell.

NOTE: The rudder shell replacement can be done only at

the AIRBUS Stade facility. Before sending the rudder,

contact:

AIRBUS

Department SBO5 Monitored Retrofit Campaign Account

MONITORED.RETROFIT@airbus.com

to validate the feasibility of the rudder shell replacement.

No further action is necessary in accordance with this Service Bulletin.

(7) Subtask 553043-832-207-001 - Inspect the rudder side shell upper GFRP areas

Manpower Resources

Manhours 0

Minimum number of person 1

Subtask elapsed time 0

Skills NON DESTRUCTIVE

TESTING

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Non Destructive Test Manual (NTM) Task 51-10-03-280-801

Task 51-10-19-280-801

Task 55-40-50-290-801

Structural Repair Manual (SRM) 51-75-11

51-75-12

Fig. A-GBBAA

Repair type identification

Sheet 01

Sheet 02

Fig. A-GFAAA

Flow Chart

Sheet 01 - Flow Chart 1

Sheet 02 - Flow Chart 2

Sheet 03 - Flow Chart 3

Sheet 04 - Flow Chart 4

Sheet 05 - Flow Chart 5

Sheet 06

Fig. A-GBEAA

Typical pulse thermography and

ELCH/UT inspection

Sheet 01

Sheet 02 - Repair size assessment

Sheet 03 - Repair size assessment

Sheet 04 - Boundary and grid of ELCH/UT

inspections

Sheet 05 - ELCH inspection grid

Fig. A-GABAA

Paint borer instructions

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

(a) If repairs in the rudder side shell upper GFRP area are recorded, do the

subsequent inspections in accordance with the Flow Chart Fig. A-GFAAA Sheet 04:

1 Make sure that the paint thickness in the areas to be inspected by pulse

thermography does not exceed:

- 400 microns.

- 400 microns below the decal foil if a decal foil is installed.

NOTE: It is the responsibility of the operator to ensure that the paint

thickness in all areas to be inspected is below or equal to the

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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SERVICE BULLETIN

limit of 400 microns.

a If the paint coating and/or logo application is too thick, abrade the paint in

accordance with the SRM 51-75-11 to a thickness below or equal to the

limit of 400 microns.

NOTE: Chemical paint stripping is not allowed.

b In case of doubts about the paint thickness, measure the thickness using

a Paint Borer Kit, refer to the Figure Fig. A-GABAA Sheet 01 thru Fig. AGABAA Sheet 09.

<1>

CAUTION: DO NOT DRILL DEEPLY INTO THE BASE

MATERIAL (CFRP OR GFRP). DRILLING TOO

DEEP LEADS TO DAMAGE IN THE OUTER SKIN

If you damage the outer skin with the paint borer, refer to the

Subtask 553043-833-201-001 for repair instructions.

2 Clean the areas to be inspected with:

Non Aqueous

Cleaner-General

08BAA9 As required

and

Textile-Lint Free

Cotton

14SBA1 As required

3 Do a pulse thermography inspection to get the precise location and size of the

repair, refer to NTM Task 55-40-50-290-801.

NOTE: As an alternative for the pulse thermography inspection, you

can identify the repair size by local sanding, refer to Subtask

553043-832-208-001.

NOTE: The pulse thermography inspection indicates the outer skin

repair ply geometry. The largest repair ply defines the

boundary of the repair area.

NOTE: Make sure that you use the pulse thermography inspection

parameters for GFRP, refer to NTM Task 55-40-50-290-801.

4 Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02 and

Fig. A-GBEAA Sheet 03.

5 If a repair type A-A, refer to Fig. A-GBBAA Sheet 02, has been identified, do a

Tap test inspection on the repair, refer to NTM Task 51-10-03-280-801 or

NTM Task 51-10-19-280-801 to identify a skin to core disbonding.

6 For all other repair types, do the ELCH and/or UT inspection around the

repair, refer to the Subtask 553043-832-206-001 of this Service Bulletin.

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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7 If fluid ingress has been detected, refer to Subtask 553043-832-204-001 of

this Service Bulletin.

8 For further actions continue with the instructions given in the Subtask

553043-832-205-001 and the actions in the Flow Chart Fig. A-GFAAA Sheet

02 of this Service Bulletin.

9 After the inspection, restore the paint coating in accordance with the SRM

51-75-12.

NOTE: Refer to OIT 999.0130/06 ’paint system - best practices’.

(b) If there is no information about repairs in the rudder side shell upper GFRP area,

do the subsequent inspections in accordance with the Flow Chart Fig. A-GFAAA

Sheet 04:

1 Make sure that the paint thickness in the areas to be inspected by pulse

thermography does not exceed:

- 400 microns.

- 400 microns below the decal foil if a decal foil is installed.

NOTE: It is the responsibility of the operator to ensure that the paint

thickness in all areas to be inspected is below or equal to the

limit of 400 microns.

a If the paint coating and/or logo application is too thick, abrade the paint in

accordance with the SRM 51-75-11 to a thickness below or equal to the

limit of 400 microns.

NOTE: Chemical paint stripping is not allowed.

b In case of doubts about the paint thickness, measure the thickness using

a Paint Borer Kit, refer to the Figure Fig. A-GABAA Sheet 01 thru Fig. AGABAA Sheet 09.

<1>

CAUTION: DO NOT DRILL DEEPLY INTO THE BASE

MATERIAL (CFRP OR GFRP). DRILLING TOO

DEEP LEADS TO DAMAGE IN THE OUTER SKIN

If you damage the outer skin with the paint borer, refer to the

Subtask 553043-833-201-001 for repair instructions.

2 Clean the areas to be inspected with:

Non Aqueous

Cleaner-General

08BAA9 As required

and

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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Textile-Lint Free

Cotton

14SBA1 As required

3 Do a pulse thermography inspection on the complete GFRP area to identify

repairs, refer to NTM Task 55-40-50-290-801.

NOTE: The pulse thermography inspection indicates the outer skin

repair ply geometry. The largest repair ply defines the

boundary of the repair area.

NOTE: Make sure that you use the pulse thermography inspection

parameters for GFRP, refer to NTM Task 55-40-50-290-801.

4 If repairs which are not manufacturing rework have been identified, mark the

boundary of the repair area, refer to Fig. A-GBEAA Sheet 02 and Fig. AGBEAA Sheet 03.

5 Do a Tap test inspection, refer to NTM Task 51-10-03-280-801 or NTM Task

51-10-19-280-801, on the complete GFRP area to identify a skin to core

disbonding.

6 Do the ELCH and/or UT inspection around the repair, refer to the Subtask

553043-832-206-001 of this Service Bulletin.

7 If fluid ingress has been detected, refer to Subtask 553043-832-204-001 of

this Service Bulletin.

8 For further actions continue with the instructions given in the Subtask

553043-832-205-001 and the actions in Flow Chart Fig. A-GFAAA Sheet 02 of

this Service Bulletin.

9 After the inspection, restore the paint coating in accordance with the SRM

51-75-12.

NOTE: Refer to OIT 999.0130/06 ’paint system - best practices’.

(8) Subtask 553043-833-201-001 - Close the holes in case of drilling thru the outer

skin during paint thickness measurement

Manpower Resources

Manhours 0

Minimum number of person 1

Subtask elapsed time 0

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Adhesive Film Tape--

Aluminium Foil -

05RAB9 As required

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Self-Adhes. Disks 05TNB1 As required

Non Aqueous CleanerGeneral08BAA9 As required

Laminating Resin-Epoxy

Srm Type 2 -

13EBC1 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Structural Repair Manual (SRM) 51-75-12

51-77-10 Para 5

51-77-11 Para 4.M.(2)

51-77-11 Para 4.A.(3)

51-77-11 Para 4.E

51-77-11 Para 5.D

51-77-11 Figure 14

(a) Hole closing procedure option 1:

1

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN

YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS

AND PAINTS: THESE MATERIALS ARE DANGEROUS.

WARNING: WEAR THE CORRECT PROTECTIVE GLOVES, GOGGLES

AND FILTER MASKS WHEN YOU USE CLEANING AGENTS,

ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS

ARE DANGEROUS.

Prepare and dry the restoration area in accordance with the SRM 51-77-11

Para 4.M.(2).

2 Prepare in accordance with the SRM 51-77-11 Para 4.A.(3):

Laminating ResinEpoxy Srm Type 2 -13EBC1 As required

NOTE: The data sheets for each adhesive, resin or low density

compound states the maximum quantity that can be safely

mixed at one time without causing an exotherm reaction.

Always refer to the appropriate data sheet before mixing the

chosen material.

3 Warm up the mixed resin to a maximum temperature of 45 ̊C (113 F).

4 Put the resin in a syringe volume 10 ml with a needle DIA 1.0 mm (0.04 in.)

and inject the resin through the hole into the cells of the honeycomb core.

Start the injection at the cell bottom and finish when the resin is leaking out of

the hole.

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5 Close the filled holes with

Adhesive Film

Tape-- Aluminium

Foil -

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

6 Let the resin cure for a minimum of 6 hours at room temperature.

If the room temperature is below 18 ̊C (64F), extend the curing time and

perform a gelation test outside the restoration area. After resin gelation plus 2

h, the aircraft can be released to operations again.

OR

Cure the resin at 60 ̊C (140F) for 45 minutes. Install a heating blanket with a

vacuum bag on the rudder surface in accordance with the SRM 51-77-11 Para

5.D, and control the temperature by means of thermocouples in accordance

with the SRM 51-77-11 Figure 14.

7 Do the final surface restoration in accordance with the compliance time given

in Para 1.E.(2), table 5:

a Remove the self adhesive tape from the restoration areas.

b Inspect the restoration in accordance with the SRM 51-77-10 Para 5.

c Remove any surplus resin from the border area of the restoration. Use

abrasive cloth. Start with 280 grade and finish with 400 grade.

d Clean the restoration areas in accordance with the SRM 51-77-11 Para

4.E. Use:

Non Aqueous

Cleaner-General

08BAA9 As required

and

Textile-Lint Free

Cotton

14SBA1 As required

e Restore the surface protection in accordance with the SRM 51-75-12.

(b) Hole closing procedure option 2:

1

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN

YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS

AND PAINTS: THESE MATERIALS ARE DANGEROUS.

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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WARNING: WEAR THE CORRECT PROTECTIVE GLOVES, GOGGLES

AND FILTER MASKS WHEN YOU USE CLEANING AGENTS,

ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS

ARE DANGEROUS.

Prepare and dry the restoration area in accordance with the SRM 51-77-11

Para 4.M.(2).

2 Prepare in accordance with the SRM 51-77-11 Para 4.A.(3):

Laminating ResinEpoxy Srm Type 2 -13EBC1 As required

NOTE: The data sheets for each adhesive, resin or low density

compound states the maximum quantity that can be safely

mixed at one time without causing an exotherm reaction.

Always refer to the appropriate data sheet before mixing the

chosen material.

3 Warm up the mixed resin to a maximum temperature of 45 ̊C (113 F).

4 Put the resin in a syringe volume 10 ml with a needle DIA 1.0 mm (0.04 in.)

and inject the resin through the hole into the cells of the honeycomb core.

Start the injection at the cell bottom and finish when the resin is leaking out of

the hole.

5 Close the filled holes with

Adhesive Film

Tape-- Aluminium

Foil -

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

6 Let the resin cure for a minimum of 12 hours at room temperature.

If the room temperature is below 18 ̊C (64F), extend the curing time and

perform a gelation test outside the restoration area.

After resin gelation plus 4 h, continue with the subsequent steps:

a Remove the self adhesive tape from the restoration areas.

b Inspect the restoration in accordance with the SRM 51-77-10 Para 5.

c Remove any surplus resin from the border area of the restoration. Use

abrasive cloth. Start with 280 grade and finish with 400 grade.

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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d Clean the restoration areas in accordance with the SRM 51-77-11 Para

4.E. Use:

Non Aqueous

Cleaner-General

08BAA9 As required

and

Textile-Lint Free

Cotton

14SBA1 As required

e Restore the surface protection in accordance with the SRM 51-75-12.

(9) Subtask 553043-832-208-001 - Identify the repair size by local sanding

Manpower Resources

Manhours 0

Minimum number of person 1

Subtask elapsed time 0

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 55-40-50

Structural Repair Manual (SRM) 51-23-11

51-75-11 Para 3.D

51-75-12

51-77-10

51-77-11 Para 4.D

51-77-11 Para 4.E

51-77-11 Para 4.G

Fig. A-GFAAA

Flow Chart

Sheet 01 - Flow Chart 1

Sheet 02 - Flow Chart 2

Sheet 03 - Flow Chart 3

Sheet 04 - Flow Chart 4

Sheet 05 - Flow Chart 5

Sheet 06

Fig. A-GBDAA

Booster area definition

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

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SERVICE BULLETIN

References

Fig. A-GBHAA

Report sheet and sketches

Sheet 01 - Pulse thermography report sheet

Sheet 02 - Repair records report sheet

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 16

Fig. A-GBEAA

Typical pulse thermography and

ELCH/UT inspection

Sheet 01

Sheet 02 - Repair size assessment

Sheet 03 - Repair size assessment

Sheet 04 - Boundary and grid of ELCH/UT

inspections

Sheet 05 - ELCH inspection grid

CAUTION: IT IS THE OPERATOR’S RESPONSIBILITY TO ENSURE THAT

STRUCTURAL SIDE SHELL OUTER SKIN PLY (CFRP OR GFRP) IN

ACCORDANCE WITH THE DESIGN DRAWING IS NOT DAMAGED

DURING THE LOCAL SANDING PROCESS.

REMARK: IN MOST OF THE RUDDER SURFACE THE OUTER

SKIN CONSISTS ONLY OF ONE CFRP OR GFRP PLY. IN

CASE OF SANDING DAMAGE IMMEDIATE REPAIR BEFORE NEXT

FLIGHT IS REQUIRED. AN AREA DAMAGED BY THE LOCAL

SANDING COMBINED WITH AN EXISTING REPAIR CAN LEAD

TO A NON-REPAIRABLE SIZE AND SUBSEQUENT SIDE SHELL

REPLACEMENT.

NOTE: The local sanding procedure is only valid for fully documented repairs.

(a) Do the subsequent work steps in accordance with the Flow Chart Fig. A-GFAAA

Sheet 01, beginning with the box ’LOCAL PAINT THICKNESS IDENTIFICATION’.

1 Identify the paint thickness and the initial basic primer on top of the repair and

beside the repair location.

NOTE: It is recommended to use a Paint Borer Kit Model 518, 518S

or 518MC.

2 Clean the previous repair area in accordance with the SRM 51-77-11 Para

4.E.

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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SERVICE BULLETIN

3 Do a local mechanical sanding on top and around the repair in accordance

with the SRM 51-75-11 Para 3.D on a step-by-step basis up to the initial basic

primer layer.

NOTE: The allowed maximum repair size is 1m2 (10.76sq.ft.) per local

repair.

4 If the largest repair ply is visible:

a Remove the dust and dry the area in accordance with the SRM 51-77-11

Para 4.G.

b Use a magnifying lens to inspect the sanded area for damage.

<1> In case of findings, do the damage assessment in accordance with

the SRM 51-77-10.

c Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02

and Fig. A-GBEAA Sheet 03.

d Identify the booster areas in accordance with the subsequent table:

Rudder PN Refer to Figure

F55470000 Fig. A-GBDAA Sheet 02 and Fig. A-GBDAA Sheet 03

F55471000

F55470005

Fig. A-GBDAA Sheet 04 and Fig. A-GBDAA Sheet 05

A55471500 Fig. A-GBDAA Sheet 06

F55471002 Fig. A-GBDAA Sheet 07 and Fig. A-GBDAA Sheet 08

F55471084 Fig. A-GBDAA Sheet 09 and Fig. A-GBDAA Sheet 10

e If repairs in the booster areas up to 55000 mm2 (85.25 sq.in.) have

been detected, report the findings to AIRBUS. Use the report sheet Fig.

A-GBHAA Sheet 02 and the rudder related sketches, refer to the

subsequent table:

Rudder PN Refer to Figure (sketch)

F55470000 Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04

F55471000

F55470005

Fig. A-GBHAA Sheet 05 and Fig. A-GBHAA Sheet 06

A55471500 Fig. A-GBHAA Sheet 07 and Fig. A-GBHAA Sheet 08

F55471002 Fig. A-GBHAA Sheet 09 and Fig. A-GBHAA Sheet 10

F55471002 (enhanced version) Fig. A-GBHAA Sheet 11 and Fig. A-GBHAA Sheet 12

F55471084 Fig. A-GBHAA Sheet 13 and Fig. A-GBHAA Sheet 16

<1> Restore the surface protection in accordance with the SRM

51-23-11.

No further actions on these repairs in accordance with this Service

Bulletin.

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 63

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f If repairs in the booster areas larger than 55000 mm2 (85.25 sq.in.) have

been detected, do the UT inspection around the repair in accordance with

Subtask 553043-832-206-001 of this Service Bulletin.

g If repairs not in the booster area have been detected, do the ELCH

and/or UT inspection in accordance with Subtask 553043-832-206-001 of

this Service Bulletin.

h If fluid ingress has been detected during the pulse thermography

inspection, refer to Subtask 553043-832-204-001 of this Service Bulletin.

i After the inspection, restore the paint coating in accordance with the

SRM 51-75-12 and SRM 51-23-11.

NOTE: Refer to OIT 999.0130/06 ’paint system - best practices’.

5 If the largest repair ply is not visible, continue the local mechanical sanding on

top and around the repair in accordance with the SRM 51-77-11 Para 4.D

on a step-by-step basis up to the pore filler or adhesive with a radius of

approximately 50.0mm (1.97in.) beyond the initial detected repair patch.

6 If the largest repair ply is visible now:

a Remove the dust and dry the area in accordance with the SRM 51-77-11

Para 4.G.

b Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02

and Fig. A-GBEAA Sheet 03.

c Use a magnifying lens to inspect the sanded area for damage.

d In case of findings, do the damage assessment in accordance with the

SRM 51-77-10.

e Identify the booster areas in accordance with the subsequent table:

Rudder PN Refer to Figure

F55470000 Fig. A-GBDAA Sheet 02 and Fig. A-GBDAA Sheet 03

F55471000

F55470005

Fig. A-GBDAA Sheet 04 and Fig. A-GBDAA Sheet 05

A55471500 Fig. A-GBDAA Sheet 06

F55471002 Fig. A-GBDAA Sheet 07 and Fig. A-GBDAA Sheet 08

F55471084 Fig. A-GBDAA Sheet 09 and Fig. A-GBDAA Sheet 10

f If repairs in the booster areas up to 55000 mm2 (85.25 sq.in.) have

been detected, report the findings to AIRBUS. Use the report sheet Fig.

A-GBHAA Sheet 02 and the rudder related sketches, refer to the

subsequent table:

Rudder PN Refer to Figure (sketch)

F55470000 Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 64

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SERVICE BULLETIN

Rudder PN Refer to Figure (sketch)

F55471000

F55470005

Fig. A-GBHAA Sheet 05 and Fig. A-GBHAA Sheet 06

A55471500 Fig. A-GBHAA Sheet 07 and Fig. A-GBHAA Sheet 08

F55471002 Fig. A-GBHAA Sheet 09 and Fig. A-GBHAA Sheet 10

F55471002 (enhanced version) Fig. A-GBHAA Sheet 11 and Fig. A-GBHAA Sheet 12

F55471084 Fig. A-GBHAA Sheet 13 and Fig. A-GBHAA Sheet 16

<1> Restore the surface protection in accordance with the SRM

51-23-11.

No further actions on these repairs in accordance with this Service

Bulletin.

g If repairs in the booster areas larger than 55000 mm2 (85.25 sq.in.) have

been detected, do the UT inspection around the repair in accordance with

Subtask 553043-832-206-001 of this Service Bulletin.

h If repairs not in the booster area have been detected, do the ELCH

and/or UT inspection in accordance with Subtask 553043-832-206-001 of

this Service Bulletin.

i If fluid ingress has been detected during the pulse thermography

inspection, refer to Subtask 553043-832-204-001 of this Service Bulletin.

j After the inspection, restore the paint coating in accordance with the

SRM 51-75-12 and SRM 51-23-11.

NOTE: Refer to OIT 999.0130/06 ’paint system - best practices’.

7 If the largest repair ply is still not visible:

a Remove the dust and dry the area in accordance with the SRM 51-77-11

Para 4.G.

b Do a pulse thermography inspection to get the precise location and the

size of the repair, refer to NTM 55-40-50.

NOTE: The pulse thermography inspection indicates the outer

skin repair ply geometry. The largest repair ply defines

the boundary of the repair area.

NOTE: In case of any findings (repair, damage, fluid ingress)

during the pulse thermography inspection, save the

images and send it together with the report sheet to

AIRBUS.

c Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02

and Fig. A-GBEAA Sheet 03.

d If fluid ingress has been detected during the pulse thermography

inspection, refer to Subtask 553043-832-204-001 of this Service Bulletin.

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 65

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SERVICE BULLETIN

e Identify the booster areas in accordance with the subsequent table:

Rudder PN Refer to Figure

F55470000 Fig. A-GBDAA Sheet 02 and Fig. A-GBDAA Sheet 03

F55471000

F55470005

Fig. A-GBDAA Sheet 04 and Fig. A-GBDAA Sheet 05

A55471500 Fig. A-GBDAA Sheet 06

F55471002 Fig. A-GBDAA Sheet 07 and Fig. A-GBDAA Sheet 08

F55471084 Fig. A-GBDAA Sheet 09 and Fig. A-GBDAA Sheet 10

f If repairs in the booster areas up to 55000 mm2 (85.25 sq.in.) have

been detected, report the findings to AIRBUS. Use the report sheet Fig.

A-GBHAA Sheet 02 and the rudder related sketches, refer to the

subsequent table:

Rudder PN Refer to Figure (sketch)

F55470000 Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04

F55471000

F55470005

Fig. A-GBHAA Sheet 05 and Fig. A-GBHAA Sheet 06

A55471500 Fig. A-GBHAA Sheet 07 and Fig. A-GBHAA Sheet 08

F55471002 Fig. A-GBHAA Sheet 09 and Fig. A-GBHAA Sheet 10

F55471002 (enhanced version) Fig. A-GBHAA Sheet 11 and Fig. A-GBHAA Sheet 12

F55471084 Fig. A-GBHAA Sheet 13 and Fig. A-GBHAA Sheet 16

<1> Restore the surface protection in accordance with the SRM

51-23-11.

No further actions on these repairs in accordance with this Service

Bulletin.

g If repairs in the booster areas larger than 55000 mm2 (85.25 sq.in.) have

been detected, do the UT inspection around the repair in accordance with

Subtask 553043-832-206-001 of this Service Bulletin.

h If repairs not in the booster area have been detected, do the ELCH

and/or UT inspection in accordance with Subtask 553043-832-206-001 of

this Service Bulletin.

i After the inspection, restore the paint coating in accordance with the

SRM 51-75-12 and SRM 51-23-11.

NOTE: Refer to OIT 999.0130/06 ’paint system - best practices’.

D. TEST

None

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 66

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SERVICE BULLETIN

E. CLOSE-UP

(1) Subtask 553043-942-201-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 29-00-00-863-801

Task 29-00-00-863-802

Task 29-00-00-863-803

55-40-00, Page Block 601

Task 55-42-11-400-801

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

equipment.

(b) To install the access panel 326AL on rudders, which have not embodied Mod. No.

40904, refer to AMM Task 55-42-11-400-801.

(c) Remove the access platforms.

(d) Close the circuit breakers as given in the inspection/check Close-up procedure,

refer to AMM 55-40-00, Page Block 601.

(e) Pressurize the Green Hydraulic System, refer to AMM Task 29-00-00-863-801.

(f) Pressurize the Blue Hydraulic System, refer to AMM Task 29-00-00-863-802.

(g) Pressurize the Yellow Hydraulic System, refer to AMM Task 29-00-00-863-803.

(h) In the cockpit, remove all warning notices.

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 67

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SERVICE BULLETIN

**CONF ALL

NOTE:

REMOVE AND INSTALL ACCESS PANEL

AS PER AMM 55−42−11. 

POSITION OF

RUDDER S/N PLACARD

Z326

A

326AL

MFR

DESCR.

SER. N °

CA CODE

MFG DATE

A/C

PN

NSA9117−63D

XXXXXXXXXXXXX

TS−XXXX

01

01

VALID FOR RUDDERS BEFORE

MODIFICATION NO.40904

A C

B

B

G_SB_553043_6_BAAA_01_06

Figure A-GBAAA - Sheet 01

Rudder SN identification

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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SERVICE BULLETIN

**CONF ALL

POSITION OF

RUDDER S/N PLACARD

VALID FOR RUDDERS AFTER

MODIFICATION NO.40904

02

NOTE:

02 USE A MIRROR OR FLEXIBLE ENDOSCOPE IF NECESSARY

C

B

G_SB_553043_6_BAAA_02_02

MFR

DESCR.

SER. N °

CA CODE

MFG DATE

A/C

PN

NSA9117−63D

XXXXXXXXXXXXX

TS−XXXX

B

Figure A-GBAAA - Sheet 02

Rudder SN identification

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

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SERVICE BULLETIN

**CONF ALL

Z326

A

A

LH SHOWN

RH SIMILAR

A

A

B

B

C

C

D

D

E

E

G_SB_553043_6_BBAA_01_02

F

F

Figure A-GBBAA - Sheet 01

Repair type identification

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 70

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SERVICE BULLETIN

**CONF ALL

OUTER SKIN WITH CORE CLOSING

OUTER SKIN AND CORE REPAIR

WITHOUT CORE CLOSING

OUTER SKIN AND CORE REPAIR

WITH CORE CLOSING

(SRM 55−41−00 PAGE BLOCK 201 FIG. 204/208/209/213/214)

DELAMINATION AND CORE DAMAGE WITH

CORE CLOSING (SRM 55−41−00 PAGE BLOCK 201 FIG.201/205)

A A

B B

C C

(SRM 55−41−00 PAGE BLOCK 201 FIG.203/207)

(SRM 55−41−00 PAGE BLOCK 201 FIG.204/208/211)

(SRM 55−41−00 PAGE BLOCK 201 FIG.204/208/211)

(SRM 55−41−00 PAGE BLOCK 201 FIG.204/208/211)

D D

E E

F F

OUTER SKIN WITHOUT CORE CLOSING

(SRM 55−41−00 PAGE BLOCK 201 FIG. 212)

(SRM 55−41−13 PAGE BLOCK 201 FIG. 203)

(SRM 55−41−13 PAGE BLOCK 201 FIG.204) (SRM 55−41−13 PAGE BLOCK 201 FIG.206)

BOTH SKIN AND CORE REPAIR

WITH AND WITHOUT CORE CLOSING /

REPAIR WITH ACCESS FROM ONE SIDE ONLY

BOTH SKIN AND CORE REPAIR WITH AND WITHOUT 

CORE CLOSING / REPAIR WITH ACCESS FROM BOTH SIDE

G_SB_553043_6_BBAA_02_06

Figure A-GBBAA - Sheet 02

Repair type identification

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 71

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SERVICE BULLETIN

**CONF ALL

REPAIR PROCEDURE

202

15.A., 15.C.

55−41−00

TEMPORARY REPAIR FOR LARGE DAMAGE.

55−41−13 5.B.

55−41−00 REPAIR FOR ABRASIONS AND SCRATCHES IN THE RUDDER ZONE "A,B". 11.A., 11.C.

55−41−00 206

55−41−00

5.A.

REPAIR FOR APEX STRIP IN THE RUDDER ZONE "D".

55−41−13 201

202

5.E. 205

REPAIR FOR ABRASIONS AND SCRATCHES IN THE RUDDER ZONE "J".

REPAIR FOR DEBONDING WITHOUT

CRACKS AND HOLES IN RUDDER ZONE "A,E,J,Q AND S".

55−41−00

55−41−13 REPAIR OF EDGE AT LOWER SHELL IN RUDDER ZONE "N".

PARA. FIG.

19.A 210

CHAPTER

A330 SRM ISSUE: 01. OCT 2009

NOTE:

REPAIRS ACCOMPLISHED IN ACCORDANCE WITH THE SRM PROCEDURES GIVEN IN THE LIST ABOVE,

ARE NOT AFFECTED BY THIS SERVICE BULLETIN.

G_SB_553043_6_BCAA_01_06

Figure A-GBCAA - Sheet 01

Repair type identification - SRM list

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 72

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SERVICE BULLETIN

**CONF ALL

FAM A/C TYP MSN Airline Rudder S/N Damage

report date

RAS Reference ISB Inspection

required

LR A330 301 MYT TS − 4054 4. DEC. 2004 RAS/DAHAM/4300075/2004 YesLR A330 349 MYT TS − 3161 24. MAR.2005 RAS/DAHAM/4019199/2005 YesLR A330 356 MYT TS − 3165 19. APR. 2005 RAS/DAHAM/4019344/2005 YesLR A330 357 MYT TS − 3167 13. MAY 2005 RAS/DAHAM/4019428/2005 Yes

LR A340 158 DLH not reported (TS − 3016) 14. Nov. 2002 RAS/DAHAM/4016147/2002 Yes

G_SB_553043_6_BCAA_02_04

Figure A-GBCAA - Sheet 02

Repair type identification - RAS list

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 73

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SERVICE BULLETIN

**CONF ALL

Z326

A

A

B D F G J

C E F H K

G_SB_553043_6_BDAA_01_02

Figure A-GBDAA - Sheet 01

Booster area definition

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 74

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SERVICE BULLETIN

**CONF ALL

DEFINITION OF

BOOSTER AREA

VALID FOR RUDDER

B LH SHOWN

1040.0 mm

(40.94 in)

1760.0 mm

(69.30 in)

2070.0 mm

(81.50 in)

BR1

BR2

BR3

BR4

BR5

BR6

BR7

F55470000

G_SB_553043_6_BDAA_02_06

Figure A-GBDAA - Sheet 02

Booster area definition

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 75

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SERVICE BULLETIN

**CONF ALL

DEFINITION OF

BOOSTER AREA

VALID FOR RUDDER

F55470000

1035.0 mm

(40.75 in)

2000.0 mm

(78.74 in)

1950.0 mm

(76.77 in)

BR1

BR2

BR3

BR4

BR5

BR6

BR7

C RH SHOWN

G_SB_553043_6_BDAA_03_06

Figure A-GBDAA - Sheet 03

Booster area definition

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 76

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SERVICE BULLETIN

**CONF ALL

DEFINITION OF

BOOSTER AREA

VALID FOR RUDDER

F55471000

F55470005

1070.0 mm

(42.13 in)

2100.0 mm

(82.68 in)

1890.0 mm

(74.41 in)

BR1

BR2

BR3

BR4

BR5

BR6

BR7

D LH SHOWN

G_SB_553043_6_BDAA_04_02

Figure A-GBDAA - Sheet 04

Booster area definition

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 77

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SERVICE BULLETIN

**CONF ALL

DEFINITION OF

BOOSTER AREA

VALID FOR RUDDER

F55471000

F55470005

1115.0 mm

(43.90 in)

2160.0 mm

(85.04 in)

1870.0 mm

(73.62 in)

BR1

BR2

BR3

BR4

BR5

BR6

BR7

E RH SHOWN

G_SB_553043_6_BDAA_05_02

Figure A-GBDAA - Sheet 05

Booster area definition

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 78

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SERVICE BULLETIN

**CONF ALL

DEFINITION OF

BOOSTER AREA

VALID FOR RUDDER

A55471500

LH SHOWN

RH SYMMETRICAL

675.0 mm

(26.57 in)

1060.0 mm

(41.73 in)

2950.0 mm

(116.14 in)

BR1

BR3

BR4

BR5

BR6

BR7

F

BR2

G_SB_553043_6_BDAA_06_02

Figure A-GBDAA - Sheet 06

Booster area definition

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 79

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SERVICE BULLETIN

**CONF ALL

BR1

BR2

BR3

BR4

BR5

BR6

BR7

BR8

DEFINITION OF

BOOSTER AREA

VALID FOR RUDDER

F55471002

LH SHOWN

3050.0 mm

(120.08 in)

1050.0 mm

(41.34 in)

G

1000.0 mm

(39.37 in)

G_SB_553043_6_BDAA_07_01

Figure A-GBDAA - Sheet 07

Booster area definition

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 80

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SERVICE BULLETIN

**CONF ALL

DEFINITION OF

BOOSTER AREA

VALID FOR RUDDER

F55471002

RH SHOWN

BR1

BR2

BR3

BR4

BR5

BR6

BR7

BR8

2850.0 mm

(112.20 in)

1200.0 mm

(47.24 in)

H

965.0 mm

(37.99 in)

G_SB_553043_6_BDAA_08_01

Figure A-GBDAA - Sheet 08

Booster area definition

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 81

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SERVICE BULLETIN

**CONF ALL

DEFINITION OF

BOOSTER AREA

VALID FOR RUDDER

F55471084

LH SHOWN

BR1

BR2

BR3

BR4

BR5

BR6

BR7

BR8A

995.0 mm

(39.17 in)

956.0 mm

(37.64 in)

3188.0 mm

(125.51 in)

J

G_SB_553043_6_BDAA_09_03

Figure A-GBDAA - Sheet 09

Booster area definition

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 82

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SERVICE BULLETIN

**CONF ALL

DEFINITION OF

BOOSTER AREA

VALID FOR RUDDER

F55471084

RH SHOWN

BR1

BR2

BR3

BR4

BR5

BR6

BR7

BR8A

944.0 mm

(37.17 in)

1179.0 mm

(46.42 in)

2824.0 mm

(111.18 in)

K

G_SB_553043_6_BDAA_10_03

Figure A-GBDAA - Sheet 10

Booster area definition

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 83

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SERVICE BULLETIN

**CONF ALL

Z326

A

A

B E

B E

G_SB_553043_6_BEAA_01_03

Figure A-GBEAA - Sheet 01

Typical pulse thermography and ELCH/UT inspection

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 84

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SERVICE BULLETIN

**CONF ALL

TYPICAL 

PULSE THERMOGRAPHY

INSPECTION

LH SHOWN B RH SYMETRICAL

C

D

G_SB_553043_6_BEAA_02_04

Figure A-GBEAA - Sheet 02

Typical pulse thermography and ELCH/UT inspection - Repair size assessment

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 85

6

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SERVICE BULLETIN

**CONF ALL

REPAIR SIZE = D2 x /4

100.0mm x 100.0mm

(3.93 in x 3.93 in)

(15.50 sq.in)

DAMAGE IN THE 

OUTER SKIN AND CORE

MAX. REPAIR PLY

REPAIR PLY

D

 (110.0mm)2 x /4

= (4.33 in2 x /4)

 ca. 10 000 mm2 =

DAMAGE IN THE 

OUTER SKIN AND CORE

MAX. REPAIR PLY

REPAIR PLIES

REPAIR SIZE = A x B

=

50.0mm x 200.0mm

(1.97 in x 7.87 in) =

OR

(15.50 sq.in)

10 000 mm2 =

B

A

EXAMPLE:

EXAMPLE:

D = 110.0mm DIA

C

D

02 THE NEW CUTOUT SIZE FOR THE REPAIR IS THE

SIZE OF THE FORMER OUTER SKIN REPAIR PLY.

02

02

G_SB_553043_6_BEAA_03_03

Figure A-GBEAA - Sheet 03

Typical pulse thermography and ELCH/UT inspection - Repair size assessment

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 86

6

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

SERVICE BULLETIN

**CONF ALL

TYPICAL 

ELCH/UT

INSPECTION

LH SHOWN

RH SYMETRICAL

MAX. REPAIR PLY

INSPECTION AREA

ELCH/UT

A

SKIN THICKNESS 1.5mm (0.23 in):

A=200.0mm (7.87 in) 

AROUND THE MAX. REPAIR PLY 

ELCH METHOD

GRID = 75.0mm x75.0mm (2.95 in x 2.95 in)

SKIN THICKNESS 1.5mm (0.23 in):

A=75.0mm (2.95 in) 

AROUND THE MAX. REPAIR PLY 

UT−METHOD

F

E

G_SB_553043_6_BEAA_04_03

Figure A-GBEAA - Sheet 04

Typical pulse thermography and ELCH/UT inspection - Boundary and grid of ELCH/UT inspections

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 87

6

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

SERVICE BULLETIN

**CONF ALL

TYPICAL TRAILING EDGE

ELCH INSPECTION

NOTE:

DISTANCE FROM EDGE 

F

75.0 mm

(2.95 in)

75.0 mm

(2.95 in)

EXISTING SCREW

75.0 mm

(2.95 in)

75.0 mm

(2.95 in)

75.0 mm

(2.95 in)

01

01

INSPECTION POINT

ELCH TOOL

TYPICAL TRAILING EDGE

ELCH INSPECTION

AROUND REPAIR AREA

75.0 mm

(2.95 in) 75.0 mm

(2.95 in)

MAX. REPAIR PLY

02

02

02 SCREWS AND ELCH TOOL ARE NOT DRAWN TO SCALE G_SB_553043_6_BEAA_05_08

Figure A-GBEAA - Sheet 05

Typical pulse thermography and ELCH/UT inspection - ELCH inspection grid

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 88

6

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

SERVICE BULLETIN

**CONF ALL

Z326

A

A

B

B

G_SB_553043_6_BFAA_01_01

Figure A-GBFAA - Sheet 01

Core ventilation procedure

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 89

6

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

SERVICE BULLETIN

**CONF ALL

MAX. RECTANGULAR REPAIR SIZE 100.0mm (3.94 in):

DRILL HOLES THRU INNER AND OUTER SKIN.

CAUTION: DO NOT DRILL THE OPPOSITE SHELL.

NOTE:

03

01

MIN. 90.0 mm

(3.54 in)

100.0 mm

(3.94 in)

02 REPAIR SIZE DETECTED BY THERMOGRAPHY

MAX. REPAIR PLY

02

APPLICABLE TO MAX. 6 HOLES

IN A ROW

TYPICAL 

CORE VENTING

IF REPAIR SIZE IS LARGER THAN 105 000mm2 (162.75 sq.in.),

CONTACT AIRBUS FOR FURTHER INSTRUCTIONS

MAX. 100.0 mm

(3.94 in)

03

C

DRILL 1 ROW IN THE MID OF THE REPAIR.

IF THE RECTANGULAR REPAIR SIZE IS LARGER THAN

100.0mm (3.94 in), DRILL 2 ROWS 

AS SHOWN IN FIG. A−GBFAA, SHEET 03.

05 CONFIRM BY AN ADDITIONAL INSPECTION THAT THE DRILL

HOLE HAS PENETRATED THE INNER SKIN.

(E.G. BY INSERTING A SUITABLE PIN DEEPER THAN NOMINAL

PANEL THICKNESS, OR BY ILLUMINATION OF THE RUDDER

FROM INSIDE THROUGH A HOLE IN THE SPAR AND VISUAL

INSPECTION THROUGH THE DRILL HOLE.)

A A

01

3.0 mm DIA

(0.12 in)

01

OUTER SKIN

INNER SKIN

OPPOSITE SHELL

MAX. REPAIR PLY

02

C D

A 05

A

50.0 mm

(1.97 in)

TE−SCREW

B

G_SB_553043_6_BFAA_02_08

Figure A-GBFAA - Sheet 02

Core ventilation procedure

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 90

6

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

SERVICE BULLETIN

**CONF ALL

IF THE RECTANGULAR REPAIR SIZE IS LARGER THAN

100.0 mm

(3.94 in)

NOTE:

04

MIN. 90.0 mm

(3.54 in) MIN. 90.0 mm (3.54 in)

100.0 mm

(3.94 in)

02 REPAIR SIZE DETECTED BY THERMOGRAPHY

MAX. REPAIR PLY

02

04

D

APPLICABLE TO MAX. 6 HOLES

IN A SQUARE GRID

IF REPAIR SIZE IS LARGER THAN 105 000mm2 (162.75 sq.in.),

CONTACT AIRBUS FOR FURTHER INSTRUCTIONS

G_SB_553043_6_BFAA_03_03

> 100.0 mm

(3.94 in)

100.0 mm (3.94 in), DRILL 2 ROWS.

Figure A-GBFAA - Sheet 03

Core ventilation procedure

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 91

6

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

SERVICE BULLETIN

**CONF ALL

Z326

A

A

B D F

H K

C E G

J L

M

N

G_SB_553043_6_BGAA_01_03

Figure A-GBGAA - Sheet 01

Rudder skin thickness identification

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 92

6

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

SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in) VALID FOR RUDDER

LH SHOWN

BR1

BR2

BR3

BR4

BR5

BR6

BR7

SKIN THICKNESS 

> 1.5mm (0.059 in)

SKIN THICKNESS 

NO INSPECTION

B

F55470000

G_SB_553043_6_BGAA_02_04

Figure A-GBGAA - Sheet 02

Rudder skin thickness identification

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 93

6

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

SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in)

VALID FOR RUDDER

RH SHOWN SKIN THICKNESS 

> 1.5mm (0.059 in)

SKIN THICKNESS 

NO INSPECTION

BR1

BR2

BR3

BR4

BR5

BR6

BR7

C

F55470000

G_SB_553043_6_BGAA_03_04

Figure A-GBGAA - Sheet 03

Rudder skin thickness identification

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 94

6

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

SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in) VALID FOR RUDDER

F55471000

LH SHOWN

SKIN THICKNESS 

F55470005

> 1.5mm (0.059 in)

SKIN THICKNESS 

NO INSPECTION

BR1

BR2

BR3

BR4

BR5

BR6

BR7

D

G_SB_553043_6_BGAA_04_02

Figure A-GBGAA - Sheet 04

Rudder skin thickness identification

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 95

6

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

SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in)

SKIN THICKNESS 

> 1.5mm (0.059 in)

SKIN THICKNESS 

NO INSPECTION

VALID FOR RUDDER

F55471000

RH SHOWN

F55470005

BR1

BR2

BR3

BR4

BR5

BR6

BR7

E

G_SB_553043_6_BGAA_05_02

Figure A-GBGAA - Sheet 05

Rudder skin thickness identification

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 96

6

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

SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in)

VALID FOR RUDDER

A55471500

LH SHOWN

BR1

BR2

BR3

BR4

BR5

BR6

BR7

33

38

10

SKIN THICKNESS 

LIGHTNING

PROTECTION

PLATE

LIGHTNING

PROTECTION

PLATE

LIGHTNING

PROTECTION

PLATE

NO INSPECTION

F

G_SB_553043_6_BGAA_06_02

Figure A-GBGAA - Sheet 06

Rudder skin thickness identification

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 97

6

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

SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER

A55471500

RH SHOWN

BR1

BR2

BR3

BR4

BR5

BR6

BR7

30

40

10

LIGHTNING

PROTECTION

PLATE

LIGHTNING

PROTECTION

PLATE

LIGHTNING

PROTECTION

PLATE

< 1.5mm (0.059 in)

SKIN THICKNESS 

NO INSPECTION

G

G_SB_553043_6_BGAA_07_02

Figure A-GBGAA - Sheet 07

Rudder skin thickness identification

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 98

6

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

SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in)

VALID FOR RUDDER

F55471002

LH SHOWN

SKIN THICKNESS 

> 1.5mm (0.059 in)

SKIN THICKNESS NO INSPECTION

BR1

H

BR2

BR3

BR4

BR5

BR6

BR7

BR8

G_SB_553043_6_BGAA_08_03

Figure A-GBGAA - Sheet 08

Rudder skin thickness identification

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 99

6

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

SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in)

VALID FOR RUDDER

F55471002

RH SHOWN

SKIN THICKNESS 

> 1.5mm (0.059 in)

SKIN THICKNESS NO INSPECTION

BR1

BR2

BR3

BR4

BR5

BR6

BR7

BR8

J

G_SB_553043_6_BGAA_09_03

Figure A-GBGAA - Sheet 09

Rudder skin thickness identification

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 100

6

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

SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in)

VALID FOR RUDDER

F55471002

LH SHOWN

SKIN THICKNESS 

> 1.5mm (0.059 in)

SKIN THICKNESS NO INSPECTION

BR1

BR2

BR3

BR4

BR5

BR6

BR7

BR8

K

(ENHANCED VERSION)

G_SB_553043_6_BGAA_12_01

Figure A-GBGAA - Sheet 12

Rudder skin thickness identification

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 101

6

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

SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in)

VALID FOR RUDDER

F55471002

RH SHOWN

SKIN THICKNESS 

> 1.5mm (0.059 in)

SKIN THICKNESS NO INSPECTION

BR1

BR2

BR3

BR4

BR5

BR6

BR7

BR8

(ENHANCED VERSION)

L

G_SB_553043_6_BGAA_13_01

Figure A-GBGAA - Sheet 13

Rudder skin thickness identification

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 102

6

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

SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in)

VALID FOR RUDDER

F55471084

LH SHOWN

SKIN THICKNESS 

> 1.5mm (0.059 in)

SKIN THICKNESS NO INSPECTION

BR1

BR2

BR3

BR4

BR5

BR6

BR7

BR8A

1

M

G_SB_553043_6_BGAA_14_02

Figure A-GBGAA - Sheet 14

Rudder skin thickness identification

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 103

6

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

SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in)

VALID FOR RUDDER

F55471084

RH SHOWN

SKIN THICKNESS 

> 1.5mm (0.059 in)

SKIN THICKNESS NO INSPECTION

BR1

BR2

BR3

BR4

BR5

BR6

BR7

BR8A

1

N

G_SB_553043_6_BGAA_15_02

Figure A-GBGAA - Sheet 15

Rudder skin thickness identification

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 104

6

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

SERVICE BULLETIN

**CONF ALL

REPAIR DETECTED WITH NIL DAMAGE

NO REPAIR DETECTED

PLEASE SEND REPORTING SHEET TO:

AIRBUS

CUSTOMER SERVICE STRUCTURE ENGINEERING

DEPARTMENT SEES2

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

Structure.sbinspectionresult@airbus.com

REPAIR DETECTED WITH DAMAGE

PLEASE SEND REPORTING SHEET TO:

DEPARTMENT SEOE1/2/3

NOTE: ATTACH ALSO THE INITIAL PUSLE THERMOGRAPHY PHOTOS.

PREVIOUS REPORTS PER SB55−3043 REV00 FIGURE A−GBHAA − SHEET 01/02/03 ARE VALID

AIRCRAFT

MSN

RUDDER S/N

INSPECTION DATE

FLIGHT CYCLES FC

FLIGHT HOURS FH

DATA

PULSE THERMOGRAPHY

COMPLETE INSPECTION LH AND RH SIDE

YES/NO

INSPECTION RESULT

REPAIR DETECTED

LH

RH

LIQUID INGRESS DETECTION

DAMAGE CHECK UT − ELCH INDICATION

SUMMARY

RUDDER SIDE SHELLS SANDWICH REPAIR PULSE THERMOGRAPHY REPORT

G_SB_553043_6_BHAA_01_07

Figure A-GBHAA - Sheet 01

Report sheet and sketches - Pulse thermography report sheet

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 105

6

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

SERVICE BULLETIN

**CONF ALL

PLEASE SEND REPORTING SHEET TO:

AIRBUS

CUSTOMER SERVICE STRUCTURE ENGINEERING

DEPARTMENT SEES2

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

Structure.sbinspectionresult@airbus.com

FIGURE A−GBHAA − SHEET 01 / REPORT SHEET AND SKETCHES − REPORT SHEET

PREVIOUS REPORTS PER SB55−3043 REV00 FIGURE A−GBHAA − SHEET 01 ARE VALID

AIRCRAFT

MSN

RUDDER S/N

RECORDS REVIEW DATE

DATA

RECORDS STATUS

REPAIR RECORDS COMPLETE SINCE ORIGINAL

YES/NO

REPAIR SCHEME

RUDDER FLIGHT CYCLES / FLIGHT HOURS

REPAIR DATE

LH OR RH SIDE SHELL

SRM FIGURE 2XX (SRM 55−41−00 AND/OR 55−41−13 PB201)

DAMAGE SIZE (CIRCULAR) DIAMETER IN mm

SUMMARY

RUDDER SIDE SHELLS SANDWICH REPAIR RECORDS

SRM (STRUCTURAL REPAIR MANUAL) REPAIR PERFORMED

REPAIR APPROVED BY LOCAL AIRWORTHINESS

DAMAGE SIZE (RECTANGULAR SHAPE) LENGTH AND WIDTH IN mm

DAMAGE SIZE (mm2)

REPAIR OUTER PLY SIZE (mm2) IF KNOWN FROM RECORDS

LOCATION AS PER SRM 55−41−00 PB101 FIGURE 103 ZONE CODE.

SERVICE BULLETIN NO.: A330−55−3043 REVXX

IN CASE OF MORE THAN 1 REPAIR, DUPLICATE THIS REPORTING SHEET

(0 FLIGHT CYCLES) EIS ENTRY INTO SERVICE

AUTHORITIES (NO AIRBUS APPROVAL)

G_SB_553043_6_BHAA_02_08

Figure A-GBHAA - Sheet 02

Report sheet and sketches - Repair records report sheet

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 106

6

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

SERVICE BULLETIN

**CONF ALL

Rudder Side Shell 

(Show damage location, size and type.)

Sandwich Repair Inspection

Damage 

location

Damage 

description / type

Damage 

size mm2 / sq.in.

Valid for rudder:

F55470000

BR1

BR2

BR3

BR4

BR5

BR6

BR7

NOTE:

01 FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER.

01

LH

G_SB_553043_6_BHAA_03_06

Figure A-GBHAA - Sheet 03

Report sheet and sketches

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 107

6

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

SERVICE BULLETIN

**CONF ALL

Rudder Side Shell 

(Show damage location, size and type.)

Sandwich Repair Inspection

RH

Damage 

location

Damage 

description / type

Damage 

size mm2 / sq.in.

Valid for rudder:

F55470000

NOTE:

01 FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER.

01

BR1

BR2

BR3

BR4

BR5

BR6

BR7

G_SB_553043_6_BHAA_04_04

Figure A-GBHAA - Sheet 04

Report sheet and sketches

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 108

6

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

SERVICE BULLETIN

**CONF ALL

Rudder Side Shell 

(Show damage location, size and type.)

Sandwich Repair Inspection

LH

Damage 

location

Damage 

description / type

Damage 

size mm2 / sq.in.

Valid for rudder:

F55471000

BR1

BR2

BR3

BR4

BR5

BR6

BR7

NOTE:

01 FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER.

01

F55470005

G_SB_553043_6_BHAA_05_04

Figure A-GBHAA - Sheet 05

Report sheet and sketches

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 109

6

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

SERVICE BULLETIN

**CONF ALL

Rudder Side Shell 

(Show damage location, size and type.)

Sandwich Repair Inspection

RH

Damage 

location

Damage 

description / type

Damage 

size mm2 / sq.in.

Valid for rudder:

F55471000

NOTE:

01 FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER.

01

F55470005

BR1

BR2

BR3

BR4

BR5

BR6

BR7

G_SB_553043_6_BHAA_06_03

Figure A-GBHAA - Sheet 06

Report sheet and sketches

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 110

6

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

SERVICE BULLETIN

**CONF ALL

Rudder Side Shell 

(Show damage location, size and type.)

Sandwich Repair Inspection

LH

Damage 

location

Damage 

description / type

Damage 

size mm2 / sq.in.

Valid for rudder:

A55471500

BR1

BR2

BR3

BR4

BR5

BR6

BR7

NOTE:

01 FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER.

01

LIGHTNING

PROTECTION

PLATE

LIGHTNING

PROTECTION

PLATE

G_SB_553043_6_BHAA_07_03

Figure A-GBHAA - Sheet 07

Report sheet and sketches

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 111

6

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

SERVICE BULLETIN

**CONF ALL

Rudder Side Shell 

(Show damage location, size and type.)

Sandwich Repair Inspection

RH

Damage 

location

Damage 

description / type

Damage 

size mm2 / sq.in.

Valid for rudder:

A55471500

NOTE:

01 FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER.

01

BR1

BR2

BR3

BR4

BR5

BR6

BR7

LIGHTNING

PROTECTION

PLATE

LIGHTNING

PROTECTION

PLATE

G_SB_553043_6_BHAA_08_03

Figure A-GBHAA - Sheet 08

Report sheet and sketches

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 112

6

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

SERVICE BULLETIN

**CONF ALL

Rudder Side Shell 

(Show damage location, size and type.)

Sandwich Repair Inspection

LH

Damage 

location

Damage 

description / type

Damage 

size mm2 / sq.in.

Valid for rudder:

F55471002

BR1

NOTE:

01 FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER.

01

BR2

BR3

BR4

BR5

BR6

BR7

BR8

G_SB_553043_6_BHAA_09_03

Figure A-GBHAA - Sheet 09

Report sheet and sketches

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 113

6

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

SERVICE BULLETIN

**CONF ALL

Rudder Side Shell 

(Show damage location, size and type.)

Sandwich Repair Inspection

RH

Damage 

location

Damage 

description / type

Damage 

size mm2 / sq.in.

Valid for rudder:

F55471002

NOTE:

01 FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER.

01

BR1

BR2

BR3

BR4

BR5

BR6

BR7

BR8

G_SB_553043_6_BHAA_10_03

Figure A-GBHAA - Sheet 10

Report sheet and sketches

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 114

6

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

SERVICE BULLETIN

**CONF ALL

Rudder Side Shell 

(Show damage location, size and type.)

Sandwich Repair Inspection

LH

Damage 

location

Damage 

description / type

Damage 

size mm2 / sq.in.

Valid for rudder:

F55471002

BR1

NOTE:

01 FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER.

01

BR2

BR3

BR4

BR5

BR6

BR7

BR8

(ENHANCED VERSION)

G_SB_553043_6_BHAA_11_03

Figure A-GBHAA - Sheet 11

Report sheet and sketches

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 115

6

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

SERVICE BULLETIN

**CONF ALL

Rudder Side Shell 

(Show damage location, size and type.)

Sandwich Repair Inspection

RH

Damage 

location

Damage 

description / type

Damage 

size mm2 / sq.in.

Valid for rudder:

F55471002

NOTE:

01 FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER.

01

(ENHANCED VERSION)

BR1

BR2

BR3

BR4

BR5

BR6

BR7

BR8

G_SB_553043_6_BHAA_12_05

Figure A-GBHAA - Sheet 12

Report sheet and sketches

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 116

6

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

SERVICE BULLETIN

**CONF ALL

Rudder Side Shell 

(Show damage location, size and type.)

Sandwich Repair Inspection

Damage 

location

Damage 

description / type

Damage 

size mm2 / sq.in.

Valid for rudder:

F55471084

BR1

NOTE:

01 FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER.

01

BR2

BR3

BR4

BR5

BR6

BR7

BR8A

LH

G_SB_553043_6_BHAA_13_05

Figure A-GBHAA - Sheet 13

Report sheet and sketches

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 117

6

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

SERVICE BULLETIN

**CONF ALL

Rudder Side Shell 

(Show damage location, size and type.)

Sandwich Repair Inspection

Damage 

location

Damage 

description / type

Damage 

size mm2 / sq.in.

Valid for rudder:

F55471084

NOTE:

01 FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER.

01

BR1

BR2

BR3

BR4

BR5

BR6

BR7

BR8A

RH

G_SB_553043_6_BHAA_16_00

Figure A-GBHAA - Sheet 16

Report sheet and sketches

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 118

6

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

SERVICE BULLETIN

**CONF ALL

Z326

A

A

G_SB_553043_6_BJAA_01_00

B C D E F

B C D E F

Figure A-GBJAA - Sheet 01

GFRP area location

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 119

6

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

SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER

F55470000

B LH SHOWN

378.0 mm

(14.88 in)

BR1

BR2

BR3

BR4

BR5

BR6

BR7

RH SYMMETRICAL

924.0 mm

(36.38 in)

GFRP AREA

CFRP AREA

G_SB_553043_6_BJAA_02_02

Figure A-GBJAA - Sheet 02

GFRP area location

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 120

6

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

SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER

F55471000

F55470005

BR1

BR2

BR3

BR4

BR5

BR6

LH SHOWN C RH SYMMETRICAL

422.0 mm

(16.61 in)

BR7 907.0 mm

(35.71 in)

GFRP AREA

CFRP AREA

G_SB_553043_6_BJAA_03_02

Figure A-GBJAA - Sheet 03

GFRP area location

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 121

6

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

SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER

A55471500

LH SHOWN

RH SYMMETRICAL

BR1

BR3

BR4

BR5

BR6

BR2

D

G_SB_553043_6_BJAA_04_00

512.0 mm

(20.16 in)

BR7 985.0 mm

(38.78 in)

GFRP AREA

CFRP AREA

Figure A-GBJAA - Sheet 04

GFRP area location

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 122

6

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

SERVICE BULLETIN

**CONF ALL

BR1

BR2

BR3

BR4

BR5

BR6

BR7

BR8

VALID FOR RUDDER

F55471002

LH SHOWN

G_SB_553043_6_BJAA_05_00

496.0 mm

(19.53 in)

1002.0 mm

(39.45 in)

GFRP AREA

CFRP AREA

E RH SYMMETRICAL

Figure A-GBJAA - Sheet 05

GFRP area location

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 123

6

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

SERVICE BULLETIN

**CONF ALL

VALID FOR RUDDER

F55471084

LH SHOWN

BR1

BR2

BR3

BR4

BR5

BR6

BR7

BR8A

F

561.0 mm

(22.09 in)

1012.0 mm

(39.84 in)

GFRP AREA

CFRP AREA

RH SYMMETRICAL

G_SB_553043_6_BJAA_06_01

Figure A-GBJAA - Sheet 06

GFRP area location

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 124

6

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

SERVICE BULLETIN

**CONF ALL

CHECK THE RUDDER RECORDS IF REPAIRS

(AIRBUS RAS , SRM AND OTHER ) 

NO YES

PERFORM PULSE THERMOGRAPHY

INSPECTION ON COMPLETE

REPORT THE INFORMATION TO AIRBUS.

01

PERFORMED

SINCE RUDDER EIS ?

REPAIR

DETECTED, WHICH

NO

YES

REPAIR 

YES NO

REPORT THE INFORMATION TO AIRBUS.

PERFORM ELCH AND/OR UT 

AROUND THE IDENTIFIED

NO FURTHER ACTION

REQUIRED IN ACCORDANCE

WITH THIS SB.

REFER TO FLOW CHART 2 FOR 

ACTIONS ON IDENTIFIED REPAIRS.

COMPLETE REPAIR

RECORDS AVAILABLE

SINCE RUDDER EIS ?

REPAIRS.

SIDE SHELLS TO IDENTIFY REPAIRS:

MARK THE REPAIRS.

YES

REPAIRS IN THE BOOSTER

AREA

REPAIR SIZE 55000mm2

03 LARGER THAN

(85.25 sq.in.)

NO

 ARE RECORDED SINCE RUDDER EIS AND

04

05

06

OR NOT IN THE BOOSTER

AREA. 03

REPORT UNDOCUMENTED RUDDER 

S/N LIST TO AIRBUS SEES2 TO GET

RELATED RUDDER MANUFACTURING

REWORK DATA 07

IS NOT MANUFACTURING

REWORK ?

08

12

FOR PAINT THICKNESS IDENTIFICATION

REFER TO FLOW CHART 5

FLUID

NO YES

NO FURTHER 

ACTIONS.

CONTINUE WITH

ACTIONS AS PER

FLOW CHART 3.

INGRESS

DETECTED

REPAIR TYPE

INSPECTED IN ACCORDANCE WITH THE SB.

02 IDENTIFIED TO BE REPORT THE

INFORMATION TO AIRBUS.

PERFORM PULSE THERMOGRAPHY ON REPAIR 

LOCATION TO PRECISE LOCATION AND SIZE.

YES

NO

NO

YES

REPORT THE INFORMATION TO AIRBUS.

MARK THE REPAIRS.

REPAIRS IN THE BOOSTER

AREA

REPAIR SIZE 55000mm2

03 LARGER THAN

(85.25 sq.in.) 06

OR NOT IN THE BOOSTER

AREA. 03

12

FOR PAINT THICKNESS IDENTIFICATION

REFER TO FLOW CHART 5

AND

PERFORM LOCAL SANDING ON TOP AND

REPAIR PLY

OF THE REPAIR

LARGEST 

VISIBLE?

YES

NO

AROUND THE PEPAIR UP TO PRIMER. 28

PERFORM LOCAL SANDING

ON TOP AROUND THE REPAIR

UP TO ADHESIVE. 24 25

REPAIR PLY

OF THE REPAIR

LARGEST 

VISIBLE?

YES

OR

NO

26

LOCAL PAINT THICKNESS IDENTIFICATION 27

MARK REPAIR SIZE ON SURFACE

22 23

25

G_SB_553043_6_FAAA_01_13

Figure A-GFAAA - Sheet 01

Flow Chart - Flow Chart 1

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 125

6

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

SERVICE BULLETIN

**CONF ALL

ACTIONS ON IDENTIFIED

REPAIRS

DAMAGE

DETECTED YES NO

PROVIDE DETAILED 

DAMAGE REPORT AND

REPAIR SIZE 

10000mm2, (15.50 sq.in.) −

PROVIDE DETAILED

INFORMATION TO AIRBUS 

AVAILABLE.

PERFORM REPETITIVE 

ELCH AND/OR UT

INSPECTION AROUND THE

IDENTIFIED REPAIR.

PERFORM CORE VENTING

THROUGH INNER SKIN, IN

ACCORDANCE WITH VENTING

SCHEME.

PERFORM CORE VENTING

THROUGH INNER SKIN, IN

ACCORDANCE WITH VENTING

SCHEME.

OR

ON IDENTIFIED REPAIR

DETAILED INFORMATION ON IDENTIFIED REPAIR IF

REPORT TO AIRBUS

AND FOLLOW THEIR

INSTRUCTIONS.

FINDINGS

YES NO

REPORT THE RESULTS AND PLANNED

TERMINATING ACTION ON IDENTIFIED 

REPAIR IN ACCORDANCE WITH

SRM AT THE IDENTIFIED

REPAIR LOCATION.

REPAIR IN ACCORDANCE WITH

SRM AND WITH ADDITIONAL 

INSTRUCTIONS FROM AIRBUS.

REPLACE AFFECTED 

RUDDER SHELL 

OR REPLACE THE RUDDER.

REFER TO FIGURE A−GFAAA, SHEET 06.

NOTE:

09

09 REPAIR SIZE 09 REPAIR SIZE 09 REPAIR SIZE 09

10

10

11

TO AIRBUS SEOE 1/2/3 OR

TERMINATING ACTION

10000mm2, (15.50 sq.in.). 20000mm2, (31.00 sq.in.). 20000mm2, (31.00 sq.in.) − 80000mm2, (124.00 sq.in.). 80000mm2, (124.00 sq.in.).

NO FURTHER ACTION

REQUIRED IN ACCORDANCE

WITH THIS SB.

AIRTAC AND FOLLOW

PERFORM CORE VENTING

THROUGH INNER SKIN, IN

ACCORDANCE WITH VENTING

SCHEME.

REPAIR TO AIRBUS SBO 5, COPY SEES2

REPORT THE RESULTS AND PLANNED

TERMINATING ACTION ON IDENTIFIED 

REPORT THE RESULTS AND PLANNED

TERMINATING ACTION ON IDENTIFIED 

TERMINATING ACTION

REPAIR SIZE 30000mm2, (46.50 sq.in.).

REPAIR SIZE 30000mm2, (46.50 sq.in.).

NO FURTHER ACTION

REQUIRED IN ACCORDANCE

REFER TO FIGURE A−GBEAA. WITH THIS SB.

THEIR INSTRUCTIONS

REPAIR TO AIRBUS SBO 5, COPY SEES2 REPAIR TO AIRBUS SBO 5, COPY SEES2

19

19

G_SB_553043_6_FAAA_02_11

Figure A-GFAAA - Sheet 02

Flow Chart - Flow Chart 2

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 126

6

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@A330

SERVICE BULLETIN

**CONF ALL

ACTIONS ON DETECTED FLUID INGRESS.

LOCAL SINGLE SPOT FLUID INGRESS

1500 mm2, (2.33 sq.in.) AND 

5000 mm2, (7.75 sq.in.)

LOCAL SINGLE SPOT FLUID INGRESS

1500 mm2, (2.33 sq.in.)

LOCAL SPOT FLUID INGRESS

5000 mm2, (7.75 sq.in.)

DRAIN BY CORE VENTING.

REPORT TO AIRBUS SEOE 1/2/3 OR AIRTAC

AND FOLLOW THEIR INSTRUCTIONS.

REPORT TO

AIRBUS.

NO FURTHER ACTION REQUIRED

IN ACCORDANCE WITH THIS ISB.

REPETITIVE THERMOGRAPHY

RE− INSPECTION.

DO THE REPAIR.

ACTIONS ON DETECTED FLUID INGRESS.

PERFORM ELCH AND/OR UT AROUND THE

IDENTIFIED FLUID INDICATION

DAMAGE

DETECTED YES

NO

THAN 5 SPOTS PER

NO REPORT TO AIRBUS SEOE 1/2/3 OR AIRTAC

AND FOLLOW THEIR INSTRUCTIONS.

MORE

SIDE SHELL YES

NO

DETECTED

THAN 5 SPOTS PER

SIDE SHELL YES

MORE

DETECTED

NO

G_SB_553043_6_FAAA_03_09

Figure A-GFAAA - Sheet 03

Flow Chart - Flow Chart 3

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 127

6

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@A330

SERVICE BULLETIN

**CONF ALL

INSPECT THE RUDDER SIDE SHELL

YES KNOWN IN THE NO

PERFORM 

ON REPAIR LOCATION AND 

YES TYPE A−A NO

IN CASE OF FINDINGS,

TAP TEST INSPECTION

OR WOODPECKER

ALL OTHER REPAIR TYPES:

PERFORM ELCH

IDENTIFIED REPAIRS

CONTINUE WITH

ACTIONS IN FLOW CHART 2

UPPER GFRP AREA

GFRP AREA

REPAIRS

PULSE THERMOGRAPHY INSPECTION

MARK THE REPAIR

REPAIR

REPORTED

PERFORM

INSPECTION

AND/OR UT

AROUND THE

PERFORM 

ON THE COMPLETE

PULSE THERMOGRAPHY INSPECTION

GFRP AREA

TAP TEST INSPECTION OR

WOODPECKER INSPECTION

PERFORM

ON THE COMPLETE GFRP AREA

MARK THE REPAIRS

YES CORE DISBONDING

NO

SKIN TO

IDENTIFIED

ALL OTHER REPAIR TYPES:

PERFORM ELCH

IDENTIFIED REPAIRS

AND/OR UT

AROUND THE

NOTE:

18 REFER TO FIGURE A−GFAAA, SHEET 06.

18

WHICH ARE NOT

MANUFACTURING REWORKS

20

21

G_SB_553043_6_FAAA_04_05

Figure A-GFAAA - Sheet 04

Flow Chart - Flow Chart 4

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 128

6

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@A330

SERVICE BULLETIN

**CONF ALL

PULSE THERMOGRAPHY PAINT

OPERATOR

IS SURE THAT THE 

NO

GFRP−AREA

400.00 microns

THICKNESS LIMITATION

RUDDER PAINT THICKNESS

IS BELOW THE GIVEN

LIMITS

YES

APPLY PAINT THICKNESS

MEASUREMENT TOOL

NO

LOCAL PAINT REMOVAL

RUDDER

PAINT THICKNESS

IS BELOW 

THE GIVEN

LIMITS

YES

CONTINUE WITH ACTIONS

DEFINED IN FLOW CHART 1 PAINT RESTORATION IS REQUIRED

AFTER PULSE THERMOGRAPHY

NOTE: AND/OR ELCH/UT INSPECTION

13 REFER TO FIGURE A−FAAA, SHEET 06

13 14

16

15 17

PAINT RESTORATION

IS REQUIRED AFTER

PULSE THERMOGRAPHY

AND/OR ELCH/UT

INSPECTION

CFRP−AREA

800.00 microns

OR

400.00 microns

BELOW DECAL FOIL

G_SB_553043_6_FAAA_05_07

Figure A-GFAAA - Sheet 05

Flow Chart - Flow Chart 5

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 129

6

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

SERVICE BULLETIN

**CONF ALL

SEE AIRBUS LIST WITH A/C MSN, RUDDER S/N

SEE AIRBUS DEFINITION OF REPAIR TYPES AFFECTED

BY THE ISB INSPECTION. REFER TO FIGURE A−GBBAA.

SEE AIRBUS BOOSTER DEFINITION. 

NOTE:

01

02

03

AND RAS NUMBER, REFER TO FIGURE A−GBCAA.

IF AN AIRCRAFT LISTED IN THE SB EFFECTIVITY HAS A

REPAIR EMBODIED THAT IS NOT OF AIRBUS ORIGIN, 

04

AND WHICH AFFECTS THE CONTENT OF THIS SB, THE

APPROVAL BY ITS AIRWORTHINESS AUTHORITY FOR

ANY ADAPTATION NECESSARY BEFORE 

THIS ACTION IS NOT NECESSARY, IF THE INFORMATION

HAS BEEN ALREADY SENT TO AIRBUS IN ACCORDANCE

05

NEXT STEP.

REFER TO FIGURE A−GBDAA.

OPERATOR IS RESPONSIBLE FOR OBTAINING THE

INCORPORATION OF THE SB.

WITH THE OIT SE 999.0071/10 CONTINUE WITH THE 

06 REPAIR SIZE DEFINED BY THE LARGEST REPAIR PLY.

ONLY MANUFACTURING HOT−CURING REWORKS ARE

DOCUMENTED IN AOT 55A3040 AND ISB 55−3042.

07

MANUFACTURING REWORK COMPLETE DATA.

AIRBUS MUST BE CONTACTED FOR

08 BASED ON PROVIDED AIRBUS EVALUATION OF RUDDER

S/N MANUFACTURING REWORK DATA.

12 FOR GFRP−AREA INSPECTION REFER TO FLOW CHART 4

REPAIR SIZE DEFINED BY THE LARGEST REPAIR PLY.

PENDING AVAILABILITY OF SRM IMPROVED REPAIR, AIRBUS IS TO BE

CONTACTED FOR INSTRUCTIONS.

SIDE SHELL REPLACEMENT CAN BE DONE ONLY AT THE AIRBUS STADE FACILITY.

09

10

11

REFER TO FIGURE A−GBEAA.

19 THE NEW REPAIR CUTOUT IS EQUAL TO

THE LARGEST OUTER SKIN REPAIR PLY.

18 REFER TO FIGURE A−GBBAA

20 IN CASE OF FLUID INGRESS REFER TO

FLOW CHART 3 FOR FURTHER INSTRUCTIONS

21 FOR PAINT THICKNESS IDENTIFICATION REFER TO

FLOW CHART 5

13 PRIOR TO THE APPLICATION OF THE PULSE THERMOGRAPHY

METHOD NTM 55−40−50 THE OPERATOR HAS TO CHECK

THE SIDE SHELL PAINT THICKNESS. IT IS THE 

OPERATORS RESPONSIBILITY TO ENSURE THAT THE

RUDDER SIDE SHELL PAINT THICKNESS IS BELOW THE

GIVEN LIMITS.

PLEASE CONSIDER THE INFORMATION FOR PAINT

RESTORATION PROVIDED WITH THE OIT 999.0130/06

DATED 21 NOV 2006.

SRM 51−75−11 RECOMMENDS ABRADING COMPOSITE

SURFACE UP TO THE FIRST PRIMER COATING IN ORDER

TO AVOID SURFACE DAMAGE OF THE COMPOSITE.

IN CASE OF A SMOOTH AND EVEN PAINT THICKNESS

DISTRIBUTION FIG. A−GABAA PROVIDE GUIDANCE

MATERIAL ABOUT A FEASIBLE PAINT BORER LOCATION 

DISTRIBUTION OVER THE SIDE SHELL.

IN CASE PAINT REMOVAL LARGER THAN 2m2 IS REQUIRED

IT IS RECOMMENDED TO REMOVE THE RUDDER FROM

THE A/C.

14

15

16

17

22 CLEAN THE PREVIOUS REPAIR AREA.

REFER TO SRM 51−77−11 PARA 4.E.

PERFORM A LOCAL MECHANICAL SANDING

A STEP BY STEP BASIS UP TO INITIAL BASIC PRIMER LAYER.

AS PER SRM 51−75−11 PARA 3.D. ON 

23

ON TOP/AROUND THE REPAIR

NO VISIBLE REPAIR: 

USING ABRASIVE CLOTH GRADE 100, 220, 280, 400.

MECHANICAL SANDING ON A STEP BY STEP BASIS

24

CONTINUE LOCAL SANDING UP TO PORE FILLER/ADHESIVE.

REFER TO SRM 51−77−11 PARA 4.D.

25 ENSURE NO DAMAGE TO CFRP OR GFRP BASE MATERIAL.

IF THE LARGEST REPAIR PLY IS NOT VISIBLE,

BEYOUND THE INITIAL DETECTED REPAIR PATCH.

26

CONTINUE LOCAL SANDING ON AND AROUND THE REPAIR WITH A RADIUS APPROX. 50.0mm (1.97in)

27 USE PAINT BORER TO ASSESS LOCAL PAINT SCHEME, THICKNESS AND INITIAL BASIC PRIMER

PRIOR SANDING. USE ON TOP OF REPAIR AND BESIDE REPAIR LOCATION.

28 MAX. 1m2 (10.76 sq.ft.) SANDED AREA PER LOCAL REPAIR IS ALLOWED.

SRM 51−77−10 AND SEND A DETAILED REFERENCE REPORT TO SEOE DEPARTMENT.

IN CASE OF DAMAGE, PERFORM ASSESSMENT AS PER

IT IS THE OPERATOR’S RESPONSIBILITY TO ENSURE THAT THE STRUCTURAL SIDE SHELL OUTER SKIN PLY

(CFRP OR GFRP) IN ACCORDANCE TO THE DESIGN DRAWING IS NOT DAMAGED DURING THE LOCAL 

SANDING PROCESS.

REMARK: IN MOST OF THE RUDDER SURFACE THE OUTER SKIN CONSISTS ONLY OF ONE CFRP OR GFRP PLY!

IN CASE OF SANDING DAMAGE IMMEDIATE REPAIR BEFORE NEXT FLIGHT IS REQUIRED. AN AREA DAMAGED

BY THE LOCAL SANDING COMBINED WITH AN EXISTING REPAIR CAN LEAD TO A NON−REPAIRABLE SIZE

AND SUBSEQUENT SIDE SHELL REPLACEMENT!

G_SB_553043_6_FAAA_06_03

Figure A-GFAAA - Sheet 06

Flow Chart

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 130

6

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

SERVICE BULLETIN

**CONF ALL

Closing of ventilation holes in outer skin

Method 1 − Application of a bonded cover

NOTE: This repair needs to be re−inspected. Correct cover application has to be ensured by frequent

detailed visual inspection during the application period at intervals not exceeding 900 FH.

1. Apply high speed tape over the ventilation hole, refer to Chapter 51−77−12 Paragraph 2.

Method 2 − Application of laminated cover

NOTE: This repair needs no re−inspection.

2. Prepare the repair area, refer to Chapter 51−77−11 Paragraph 4.M.(2)., apply only step

1 to 2 and 10 to 17.

3. Protect the area adjacent to the repair area with flash tape (Material No. 05RFB1), refer to

Chapter 51−77−11, Paragraph 3.B.(2).

4. Prepare the laminating resin (Material No. 13EBC1), refer to Chapter 51−77−11, Paragraph 

6.B.(2) and 4.A.(3).

5. Prepare the repair plies (MIL−C−9084C TYPE VIIIA or B − style 7781 dry glass fabric), refer to

Chapter 51−77−11, Paragraph 4.H. For ply dimensions and orientation refer to Figure 1.

NOTE: Round all corners with radii 12mm (0.5 in.) minimum.

6. Prepare the laminating resin, refer to Chapter 51−77−11, Paragraph 6.B.(2) and 4.A.(3).

7. Apply repair plies to the repair area as shown in Figure 1, refer to Chapter 51−77−11, 

Paragraph 5.A.

8. If the repair cure shall be accelerated by heat:

− Install the vaccum bag, refer to Chapter 51−77−11, Paragraph 5.D.(1), respect modificatons

shown on Figure 2 and the heating equipment.

− Allow repair to cure under vacuum pressure, refer to Chapter 51−77−11, Paragraph 5.E.,

use 22 in. of hg (560 mm of hg or 75 Kpa) minimum. Let the resin gel for one hour at room

temperature, then cure for 4 hours at 60 C, refer to Chapter 51−77−11, Paragraph 5.E.

− Remove the vacuum bag and the heating equipment.

− Continue with step 10.

9. If the repair cure shall be performed at room temperature:

− Install the vacuum bag, refer to Chapter 51−77−11, Paragraph 5.D.(1) and respect modifications

shown on Figure 2.

− Allow repair to cure under vacuum pressure, refer to Chapter 51−77−11, Paragraph 5.E.,

use 22 in. of hg (560 mm of hg or 75 Kpa) minimum. Let the resin cure for six hours at room

temperature or perform resin gelation test outside the repair area, after resin gelation perform

cure for two hours (the latter approach must be applied if RT is below 18 C (65 F)).

− Remove the vacuum bag and continue with step 10 during the next stop.

10. Remove the flash tape. Ensure that the glass ply is correctly located and cured, refer to

Chapter 51−77−10, Paragraph 5.

11. Remove any resin remnants from the border area of the glass ply, use abrasive paper. Start with

280 grade and finish with 400 grade.

WARNING: CLEANING AGENT (MATERIAL NO. 08BBF1 or 08BBU9) IS DANGEROUS.

12. Clean the repair area with cleaning agent (Material No. 08BBF1 or 08BBU9), refer to Chapter 51−

77−10, Paragraph 4.E.(1)(a).

13. Restore the surface protection, refer to Chapter 51−75−12.

G_SB_553043_6_AAAA_01_05

Figure A-GAAAA - Sheet 01

Closing of ventilation holes

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 131

6

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

SERVICE BULLETIN

**CONF ALL

Figure 1 − Ply lay−up

Ply 2 0/90 42 x 42mm

Ply 1 45 30 x 30mm

Ply 3 45 54 x 54mm

NON PERFORATING GLASS PLY FLASH TAPE

PARTING FILM

RUBBER CAUL

PLATE

BREATHER

DRY GLASS FABRIC

OR PEEL PLY

VACUUM GAGE VACUUM SOURCE

VACUUM BAG FILM

VACCUM BAG

SEALANT TAPE

NOTE:

01 RUBBER CAUL PLATE IS MANDATORY, 

01

REFER TO CHAPTER 51−77−11, PARAGRAPH 3.C.

Figure 2 − Bagging for curing process

G_SB_553043_6_AAAA_02_00

Figure A-GAAAA - Sheet 02

Closing of ventilation holes

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 132

6

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

SERVICE BULLETIN

**CONF ALL

PAINT THICKNESS MEASUREMENT USING THE PAINT BORER ON THE RUDDER SIDE SHELL

THE PAINT THICKNESS MUST BE DETERMINED FOR A CORRECT SETTING OF THE

PULSE THERMOGRAPHY INSPECTION PARAMETERS. IF THE THICKNESS IS UNKNOWN

DETERMINE THE THICKNESS WITH THE PAINT BORER.

DESCRIPTION

1. GENERAL

A. THIS PROCEDURE CONTAINS THE INSPECTION PROCEDURE DESCRIBING

PAINT THICKNESS MEASUREMENT USING THE PAINT BORER ON

THE RUDDER SIDE SHELL.

PROCEDURE

1 TASK SUPPORTING DATA

A. AREA OF APPLICABILITY

ALL RUDDER INSPECTED WITH NTM 55−40−50

B. DESCRIPTION OF POSSIBLE DAMAGE

THE PAINT THICKNESS MUST BE DETERMINED FOR A CORRECT SETTING OF THE

PULSE THERMOGRAPHY INSPECTION PARAMETERS. IF THE THICKNESS IS UNKNOWN

DETERMINE THE THICKNESS WITH THE PAINT BORER.

C. JOB SETUP INFORMATION

(1) TOOLING

PREFERRED TOOL: PAINT BORER 518MC WITH THE DRILLS IN TABLE 1

ALTERNATIVE TOOL: PAINT BORER 518 OR PAINT BORER 518S WITH THE DRILLS

 IN TABLE 1

ADDITIONAL DOCUMENT: OPERATING MANUAL PAINT BORER

TABLE 1 : DRILLS

G_SB_553043_6_ABAA_01_06

Figure A-GABAA - Sheet 01

Paint borer instructions

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 133

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SERVICE BULLETIN

**CONF ALL

2 PROCEDURE:

1. PREPARE THE PAINT BORER ACCORDING TO THE OPERATING

1. PLACE THE PAINT BORER ON THE AREA, WHERE THE THICKNESS OF THE

 RUDDER PAINT HAS TO BE MEASURED, SEE FIG. A−GABAA SHEET 3+4

2. DO THE DRILLING AND THE PAINT THICKNESS MEASUREMENT ACCORDING 

 PAINT BORER OPERATING INSTRUCTIONS, REFER ALSO

 CAUTION: DO NOT DRILL DEEPLY INTO THE BASE MATERIAL (CFRP OR GFRP). ONLY A

TINY BASE MATERIAL SPOT IS ENOUGH TO MEASURE THE PAINT

THICKNESS, REFER TO FIG. A−GABAA SHEET 5+6

3. APPLY A CONTRAST MARK (WITH A NON PERMANENT MARKER PEN) ON THE

 THE SPOT OF MEASUREMENT. IF THE RUDDER PAINT IS LIGHT (E.G. YELLOW, 

 WHITE ...), USE A DARK (BLACK) PEN TO ENHANCE CONTRAST OF THE TOP

 COATING, IN CASE OF A DARK TOP COAT USE A LIGHT (WHITE) PEN. SEE

A. PREPARATION FOR INSPECTION

B. INSTRUMENT ADJUSTMENT

1. NO

C: INSPECTION PROCEDURE

 INSTRUCTIONS.

4. RECORD ALL THE MEASURED PAINT THICKNESS VALUES FOR THE

 PULSE THERMOGRAPHY INSPECTION.

5. AFTER MEASUREMENT SEAL THE SPOT WHERE DRILLED − REFER TO

 SRM 51−75−10.

 FIG. A−GABAA SHEET 7+8

 TO FIGURE A−GABAA SHEET 3−8

− IF THE LAYER THICKNESS IS NOT KNOWN,

INITIALLY USE A DRILL WITH 20−2000 m ( CUT ANGLE: 45°)

TO BRING THE FULL SECTION INTO VIEW;

CHANGE TO 10−1000 m (CUT ANGLE: 26.6°) IF THICKNESS

TURNS OUT TO BE 1000 m OR LESS

μ 

μ 

μ 

CAUTION: IT IS IMPORTANT TO HAVE THE ABOVE SPECIFIED DRILLS AVAILABLE.

CONTACT DRILL SUPPLIER IF THE CUTTING ANGLE AND DRILL NUMBERING

CAUTION: DO NOT USE ULTRASONIC OR EDDY CURRENT BASED PAINT THICKNESS

MEASUREMENT DEVICES, AS EDDY CURRENT ONLY WORKS ON METALLIC

AND FOR ULTRASONIC BASED DEVICES THE NUMBER OF POSSIBLE PAINT

LAYERS IS TOO HIGH TO GET RELIABLE RESULTS.

IS UNKNOWN.

G_SB_553043_6_ABAA_02_06

Figure A-GABAA - Sheet 02

Paint borer instructions

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 134

6

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@A330

SERVICE BULLETIN

**CONF ALL

Z326

A

A

LH SHOWN

RH SIMILAR

CFRP

AREA

GFRP

AREA

C D E

B D E

G_SB_553043_6_ABAA_03_00

Figure A-GABAA - Sheet 03

Paint borer instructions

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 135

6

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

SERVICE BULLETIN

**CONF ALL

PAINT SYSTEM

DIFFERENT LAYERS

(E.G. FILLER, PRIMER,

TOP COAT, ...)

CFRP

HONEYCOMB

CORE

d

NOTE:

01 DRILL HOLE

01

d = PAINT SYSTEM

THICKNESS

SPOT DRILLING

DETERMINATION OF

PAINT THICKNESS

PAINT SYSTEM

DIFFERENT LAYERS

(E.G. FILLER, PRIMER,

TOP COAT, ...)

GFRP

HONEYCOMB

CORE

d 01

B

C

D E

F

G

G_SB_553043_6_ABAA_04_01

Figure A-GABAA - Sheet 04

Paint borer instructions

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 136

6

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@A330

SERVICE BULLETIN

**CONF ALL

F

1) NOT DRILLED DEEP

ENOUGH

2) GOOD DRILLED DEPTH 

(TINY CFRP SPOT)

3) DRILLED TO DEEP

(BIG CFRP SPOT)

7) DRILLED TO DEEP

(DAMAGE OF THE HONEYCOMB

6) DRILLED TO DEEP

(BIG CFRP SPOT)

5) GOOD DRILLED

DEPTH (TINY

4) NOT DRILLED

DEEP ENOUGH

CFRP SPOT) CORE)

G_SB_553043_6_ABAA_05_01

Figure A-GABAA - Sheet 05

Paint borer instructions

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 137

6

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

SERVICE BULLETIN

**CONF ALL

8) NOT DRILLED DEEP

ENOUGH

9) NOT DRILLED DEEP

ENOUGH

10) GOOD DRILLED

DEPTH

11) DRILLED TOO DEEP

(BIG GFRP SPOT)

12) GOOD DRILLED DEPTH

(DAMAGE OF THE

13) DRILLED TOO DEEP

(TINY GFRP SPOT)

14) DRILLED TOO DEEP

(DAMAGE OF THE

(TINY GFRP SPOT)

HONEYCOMB CORE) HONEYCOMB CORE)

G

G_SB_553043_6_ABAA_06_00

Figure A-GABAA - Sheet 06

Paint borer instructions

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 138

6

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@A330

SERVICE BULLETIN

**CONF ALL

G_SB_553043_6_ABAA_07_00

Figure A-GABAA - Sheet 07

Paint borer instructions

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 139

6

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

SERVICE BULLETIN

**CONF ALL

BR1

BR2

BR3

BR4

BR5

BR6

BR7

200.0mm (7.87in.) AFT OF BR7 RIVET CENTER

200.0mm (7.87in.) FWD OF HOIST POINT CENTER LINE

PROPOSAL:

1SPOT IN GFRP AREA

6SPOTS IN CFRP AREA

A

B

C

A

B

C

D

200.0mm (7.87in.) FWD OF HOIST POINT CENTER LINE

D

Valid for rudder:

F55470000

F55471000

F55470005

A55471500

600.0mm (23.62in.)

600.0mm (23.62in.)

200.0mm (7.87in.) FROM

BR2 RIVET CENTER LINE

G_SB_553043_6_ABAA_08_07

Figure A-GABAA - Sheet 08

Paint borer instructions

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 140

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@A330

SERVICE BULLETIN

**CONF ALL

200.0mm (7.87in.) AFT OF BR8/BR8A RIVET CENTER

200.0mm (7.87in.) FWD OF HOIST POINT CENTER LINE

PROPOSAL:

1SPOT IN GFRP AREA

6SPOTS IN CFRP AREA

A

B

C

200.0mm (7.87in.) FWD OF HOIST POINT CENTER LINE

D

BR1

BR2

BR3

BR4

BR5

BR6

BR7

BR8/BR8A

B

C

D

A

Valid for rudder:

F55471002

F55471084

600.0mm (23.62in.)

600.0mm (23.62in.)

200.0mm (7.87in.) FROM

BR2 RIVET CENTER LINE

G_SB_553043_6_ABAA_09_01

Figure A-GABAA - Sheet 09

Paint borer instructions

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 141

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SERVICE BULLETIN

REPORTING SHEET

TITLE: STABILIZERS - RUDDER SIDE SHELL SANDWICH REPAIR

INSPECTION

MODIFICATION No.: None

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 1

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@A330

SERVICE BULLETIN

QUALITY PERCEPTION FORM

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

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

improve the quality of our Service Bulletins.

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

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

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

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

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

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

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043

REVISION No.: 01 - Aug 20/14 Page: 1

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