# Airbus Service Bulletin A330-55-3043
Copy: Revision 1 ("FAA-2014-0928 SB A330-55-3043 R01"), 151 pages: PDF https://openairdocs.org/files/sha256/e9/6b/e96bf3d2cdc53016c4996c8b8d6ebdb6990a1c1fd99e513a02d70c21a44bb237; text https://openairdocs.org/service-documents/airbus/a330-55-3043/file/e96bf3d2cdc5.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2014-0928; AD 2015-24-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
## Details
- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: A330-55-3043
- Latest revision known: A330-55-3043, Revision 1, dated August 20, 2014 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/a330-55-3043
## ADs that cite it (1) (OpenAirDocs)
Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.
- [AD 2015-24-01](https://openairdocs.org/ad/2015-24-01.md), effective Jan 4, 2016: Revision 1
Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a330-55-3043/proposed.md).
## Text (151 pages)
Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2014-0928; AD 2015-24-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.
### Page 1
@A330
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
MANDATORY
MANDATORY
MANDATORY
ATA SYSTEM: 55
TITLE: STABILIZERS - RUDDER S IDE 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
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
### Page 2
@A330
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
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
### Page 3
@A330
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
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
### Page 4
@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
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
### Page 5
@A330
SERVICE BULLETIN
SUMMARY
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
This summary is for information only and is not approved for modification of the aircraft.
MANDATORY
MANDATORY
MANDATORY
ATA SYSTEM: 55
TITLE: STABILIZERS - RUDDER S IDE 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
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
### Page 6
@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
REVISION No.: 01 - Aug 20/14 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
### Page 7
@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
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
### Page 8
@A330
SERVICE BULLETIN
SUMMARY
**CONF ALL
Z326
AA
G_SB_553043_6_SAAA_01_00
RUDDER SHELL
TO BE INSPECTED
B
AB
LH SHOWNRH SHOWN
Figure A-GSAAA - Sheet 01
DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043
REVISION No.: 01 - Aug 20/14 Page: 4
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
### Page 9
@A330
SERVICE BULLETIN
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
MANDATORY
MANDATORY
MANDATORY
ATA SYSTEM: 55
TITLE: STABILIZERS - RUDDER S IDE 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
REVISION No.: 01 - Aug 20/14 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
### Page 10
@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
REVISION No.: 01 - Aug 20/14 Page: 2
6
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### Page 11
@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
DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043
REVISION No.: 01 - Aug 20/14 Page: 3
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
### Page 12
@A330
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
REVISION No.: 01 - Aug 20/14 Page: 4
6
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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
REVISION No.: 01 - Aug 20/14 Page: 5
6
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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
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
6
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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
REVISION No.: 01 - Aug 20/14 Page: 8
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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 Av iation Safety Agenc y (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 mm 2
(85.25 sq.in.) detected
Report to AIRBUS
Within 1 month from the
pulse thermography
inspection
None
Repairs in the booster
area > 55000 mm
2
(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
N os k i nt oc o r e
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
REVISION No.: 01 - Aug 20/14 Page: 11
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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 mm 2
(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 mm 2
(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
6
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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
REVISION No.: 01 - Aug 20/14 Page: 13
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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 mm 2
(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
REVISION No.: 01 - Aug 20/14 Page: 14
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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 mm 2
(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 mm 2
(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
REVISION No.: 01 - Aug 20/14 Page: 15
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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 mm 2 (15.50 sq.in.), continue with
table 4.A.
For an identified repair size larger than 10000 mm 2 (15.50 sq.in.) and up to 20000 mm 2
(31.00 sq.in.), continue with table 4.B.
For an identified repair size larger than 20000 mm 2 (31.00 sq.in.) and up to 80000 mm 2
(124 sq.in.), continue with table 4.C.
For an identified repair size larger than 80000 mm 2 (124 sq.in.), continue with table 4.D.
Table 4.A, Config. 001 - Identified repair size of a maximum of 10000 mm
2
(15.50 sq.in.)
Condition
Action
Compliance time
Repetitive interval
Repair size =< 10000
mm
2
(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 mm 2 (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
REVISION No.: 01 - Aug 20/14 Page: 16
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SERVICE BULLETIN
Table 4.B, Config. 001 - Identified repair size larger than 10000 mm
2
(15.50 sq.in.) and up to 20000
mm
2
(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 mm
2
(31.00 sq.in.) and up to 80000
mm
2
(124 sq.in.)
Condition
Action
Compliance time
Repetitive interval
Repair size > 20000
mm
2
(31.00 sq.in.) and
=< 80000 mm
2
(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
REVISION No.: 01 - Aug 20/14 Page: 17
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Table 4.C, Config. 001 - Identified repair size larger than 20000 mm
2
(31.00 sq.in.) and up to 80000
mm
2
(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 mm 2 (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
DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043
REVISION No.: 01 - Aug 20/14 Page: 18
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Table 4.D, Config. 001 - Identified repair size larger than 80000 mm
2
(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
mm
2
(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
DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043
REVISION No.: 01 - Aug 20/14 Page: 19
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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 mm 2
(85.25 sq.in.) detected
Restore the surface
protection
Before next flight
None
Repairs in the booster
area =< 55000 mm 2
(85.25 sq.in.) detected
Report to AIRBUS
Within 1 month
None
Repairs in the booster
area > 55000 mm 2
(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
DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043
REVISION No.: 01 - Aug 20/14 Page: 20
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SERVICE BULLETIN
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 mm 2
(85.25 sq.in.) detected
Restore the surface
protection
Before next flight
None
Repairs in the booster
area =< 55000 mm 2
(85.25 sq.in.) detected
Report to AIRBUS
Within 1 month
None
Repairs in the booster
area > 55000 mm 2
(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 mm 2
(85.25 sq.in.) detected
during pulse
thermography inspection
Restore the surface
protection
Before next flight
None
Repairs in the booster
area =< 55000 mm
2
(85.25 sq.in.) detected
during pulse
thermography inspection
Report to AIRBUS
Within 1 month
None
DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043
REVISION No.: 01 - Aug 20/14 Page: 21
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SERVICE BULLETIN
Table 6.C, Config. 001 - Do the pulse thermography inspection (CFRP areas)
Condition
Action
Compliance time
Repetitive interval
Repairs in the booster
area > 55000 mm 2
(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
DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043
REVISION No.: 01 - Aug 20/14 Page: 22
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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
DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043
REVISION No.: 01 - Aug 20/14 Page: 23
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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 m 2 (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
DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043
REVISION No.: 01 - Aug 20/14 Page: 24
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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
T e l:( 3 3 )56 71 90 62 2
F a x:( 3 3 )56 19 32 74 5
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
REVISION No.: 01 - Aug 20/14 Page: 25
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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
DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043
REVISION No.: 01 - Aug 20/14 Page: 26
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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
DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043
REVISION No.: 01 - Aug 20/14 Page: 27
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This Page Intentionally Left Blank
DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043
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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, A DHESIVES, 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
DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043
REVISION No.: 01 - Aug 20/14 Page: 29
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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
DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043
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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.
DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043
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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.
DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043
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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. A-
GBCAA 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
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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 ar eas 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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Material necessary to do the job
Consumable CMLD01
ITEM
DESCRIPTION
REFERENCE TO
CML MAT. No.
QTY PER A/C
SEE
NOTES
Non Aqueous Cleaner-
General
08BAA9
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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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
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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. A-
GABAA 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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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 mm 2 (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 mm 2 (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 ’pai nt 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 Cleaner-
General
08BAA9
As required
DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043
REVISION No.: 01 - Aug 20/14 Page: 38
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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
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(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. A-
GABAA 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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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 mm 2 (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 mm 2 (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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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 ’pai nt 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
S r mT y p e2-
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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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 mm 2 (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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4
If a maximum of 5 local single spots per side shell larger than 1500 mm
2
(2.33
sq.in.) and up to 5000 mm
2
(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
.
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
6
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### Page 53
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SERVICE BULLETIN
Laminating Resin-
Epoxy 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 mm 2 (2.33
sq.in.) and up to 5000 mm 2 (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 mm 2 (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 Cleaner-
General
08BAA9
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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### Page 54
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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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### Page 55
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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
REVISION No.: 01 - Aug 20/14 Page: 47
6
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### Page 56
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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
S r mT y p e2-
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
REVISION No.: 01 - Aug 20/14 Page: 48
6
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### Page 57
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SERVICE BULLETIN
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 mm 2 (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 mm 2 (15.50 sq.in.) and up to 20000 mm 2 (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
REVISION No.: 01 - Aug 20/14 Page: 49
6
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### Page 58
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SERVICE BULLETIN
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
.
Consumable Material necessary to close the drain holes:
Pressure Sensitive
Tape
05RFB1
As required
Laminating Resin-
Epoxy 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 mm 2 (31.00 sq.in.) and up to 80000 mm 2 (124
sq.in.) has been detected, do the ventilation of the core:
a
DATE: Feb 07/13 SERVICE BULLETIN No.: A330-55-3043
REVISION No.: 01 - Aug 20/14 Page: 50
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### Page 59
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SERVICE BULLETIN
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
.
Consumable Material necessary to close the drain holes:
Pressure Sensitive
Tape
05RFB1
As required
Laminating Resin-
Epoxy 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
REVISION No.: 01 - Aug 20/14 Page: 51
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
### Page 60
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SERVICE BULLETIN
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 mm 2 (46.50 sq.in.),
contact AIRBUS for additional instructions.
4
If a repair larger than 80000 mm 2 (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
REVISION No.: 01 - Aug 20/14 Page: 52
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
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