# Airbus Mandatory Service Bulletin A330-55-3042 Copy: No revision named ("U.S. DOT/FAA - Service Bulletin - A330-55-3042"), 78 pages: PDF https://openairdocs.org/files/sha256/f3/8e/f38ea30d63a578ca2982a606a8b19056bf60af11f6c8e981854c273b7b125a83; text https://openairdocs.org/service-documents/airbus/a330-55-3042/file/f38ea30d63a5.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2011-0387; AD 2011-18-22 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. ## Details - Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md) - Type: Service bulletin (Mandatory Service Bulletin) - Number: A330-55-3042 - Page: https://openairdocs.org/service-documents/airbus/a330-55-3042 ## ADs that cite it (1) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2011-18-22](https://openairdocs.org/ad/2011-18-22.md), effective Oct 18, 2011: No revision named Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a330-55-3042/proposed.md). ## Text (78 pages) Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2011-0387; AD 2011-18-22 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. This text is 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 (OCR) G4330 SERVICE BULLETIN SUMMARY # AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft. MANDATORY MANDATORY MANDATORY ATA SYSTEM: 55 TITLE: STABILIZER - RUDDER- А330 RUDDER DEBOND INSPECTION **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES On AIRBUS Single Aisle and Long Range 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 debonding in a rudder shell was found on the rudder of an A319 and an A321 aircraft. A large rudder debond, resulting from an undetected damage growth, could affect the handling quality of the aircraft. Under specific conditions, a large debond could lead to aircraft in-flight instability. A review of the production records revealed that the debonding reported on both rudders correspond to This Service Bulletin details the inspection procedure to inspect the reworked areas on affected rudders fitted on A330 aircraft for potential debonding. Due to the different areas on the rudder to be inspected, different inspection procedures are necessary: - Vacuum loss inspection - Elasticity Laminate Checker (ELCH) inspection - Tap test inspection - Thermography inspection - Ultrasound (US) inspection. The accomplishment of this Service Bulletin will ensure the detection of potential debonding in the reworked areas. 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 1 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 2 (OCR) GA330 SERVICE BULLETIN SUMMARY GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO MATERIAL PRICE INFORMATION **CONF 001 No Material **CONF 002 No Material EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operators) : 26U 44W 46W 78V 97X 99Y AAR AAW ACA ACI AEA AFL AFR ALK ARA ASY AVA AZA BEC BEL BMA BTV I CAL CCA CES CHH GRK CRL OSC CSN CYP DAH DAL DGA DLH EDW SEEZ EIN ETD EVA FIN FWI GFA GIA GRL HAL HDA HFY HVN 12L TAG IWD IYE JAI UST KAL KER KKK KLM LTU LVG MAS MAU MEA MON MSR MXA OBS OHY OMA PAL QAF QFA QTR RSF _ SAA SAS SGX SIA STZ SVA SWR TAM TAP TCX THA THY TSC UAE UAF USA VIR VKG VLK XAX XLF CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 55.41.13.001 OEB None AOT 55-3040 SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER SBIT 914.0808/09 NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 2 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 3 (OCR) GA330 SERVICE BULLETIN AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel: (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 MANDATORY MANDATORY MANDATORY ATA SYSTEM: 55 TITLE: STABILIZER - RUDDER- А330 RUDDER DEBOND 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 (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 (2) Effectivity by MSN 0012 0017 0030 0037 0045 0050 0054-0055 0059-0060 0062 0064-0067 0069-0073 0077 0082-0083 0086-0087 0095-0096 0098-0100 0102 0106-0107 0109-0113 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 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 1 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 4 (OCR) DA330 SERVICE BULLETIN 0591 0593 0595 0597 0600 0602-0603 0605 0607 0609-0610 0612 0614 0616 0618 0620-0621 0623 0625 0627 0629 0631-0638 0640-0642 0644-0645 0647-0650 0652-0659 0661-0667 0669-0671 0673-0676 0678-0680 0682-0684 0686-0688 0690-0693 0695-0697 0699-0701 0703-0705 0707-0709 0711-0714 0716-0718 0720-0722 0724-0726 0728-0730 0732-0735 0737-0739 0741-0743 0745-0747 0749-0752 0754-0756 0758-0760 0769-0770 0772-0774 0776-0778 0780-0782 0784-0786 0788-0789 0791-0792 0795-0797 0799 0801-0803 0805-0807 0809-0811 0813-0815 0817-0828 0830-0834 0836 0838-0843 0845 0847 0849-0855 0857-0863 0865-0869 0871 0873-0877 0879 0881-0885 0887-0893 0895-0896 0898-0901 0903-0909 0911 0913-0916 0918-0920 0922-0923 0925-0928 0930-0932 0934-0937 0939-0952 0954 0956-0959 0961-0971 0973-0980 0982-0986 0988-0992 0994-1003 1006-1016 1018-1026 1028-1029 1031 1033-1039 1041-1049 1052-1055 1057-1061 1063 1065-1067 1069 1071-1078 1080-1082 1084-1090 1093-1101 1103-1108 1110 1112 1114 1116 1118 1120 1123-1124 1126-1127 1129-1133 1135 1137-1138 1141 1143 1145-1147 1149-1151 1153 1155-1157 1159-1161 1163 1165 1167-1174 1177-1178 1181 1183-1184 1186-1189 1191-1192 1195-1196 1198-1199 1202 1204-1205 1208 1212 1214 1217 1220 1222-1223 (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 26U 0996 44W 0943 0962 0970 0979 1019 46W 0871 0925 78V 1033 1046 97X 1053 99Y 0747 0951 AAR 0640 0676 0708 0772 0803 0845 1001 1055 1151 AAW 0999 1024 1043 ACA 0277 0279 0284 0344 0400 0408 0412 0419 ACI 0507 0510 AEA 0733 0745 0749 0814 0931 0950 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 ALK 0303 0306 0311 0313 ARA 1002 ASY 0969 1036 1183 AVA 0948 0967 1009 1016 1073 1208 AZA 0272 0339 1123 1135 BEC 0863 BEL 0030 0037 0045 0082 BMA 0398 0401 0404 BTV 0205 0330 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 2 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 5 (OCR) DA330 SERVICE BULLETIN OPERATOR MSN CAL 0602 0607 0641 0671 0675 0691 0699 0707 0714 0725 0752 0769 0805 0823 0838 0861 0920 1177 COA 0750 0756 0759 0780 0785 0797 0810 0815 0839 0860 0867 0873 0884 0890 0903 0909 0930 0941 0944 0957 1087 1110 1130 1187 1199 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 1159 1168 1178 CPA 0012 0017 0071 0083 0099 0102 0109 0113 0118 0121 0155 0244 0386 0389 0393 0418 0420 0421 0423 0439 0539 0548 0565 0669 0673 0679 0776 0850 0855 0895 0915 0959 1163 1196 1222 CRK 1031 1034 1039 1042 1054 1059 CRL 0285 0320 OSC 1082 1138 CSN 0649 0652 0656 0664 0818 0840 0879 0889 0908 0935 0937 0954 0958 0964 1096 1116 1129 1202 1220 CYP 0505 0526 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 0369 EEZ 0665 0802 0822 EIN 0059 0269 0397 0841 0847 0985 1025 1106 ETD 0658 0688 0717 0724 0729 0730 0737 0788 0809 0824 0832 0852 0854 0868 0975 1071 1081 1167 1205 EVA 0530 0535 0555 0573 0587 0634 0655 0661 0678 0693 0755 FIN 0994 1007 1013 1023 1067 1078 1088 1173 FWI 0253 0758 9960 1021 GFA 0276 0281 0286 0287 0334 0340 0527 0529 0532 0992 GIA 0138 0140 0144 0148 0153 0165 0988 1020 1028 1052 1184 1214 GRL 0230 HAL 1104 1114 1171 1217 HDA 0106 0132 0234 0405 0479 0512 0581 0654 0662 0692 0716 0741 0786 HFY 0096 1008 HVN 0087 0255 0262 0275 0294 0299 0366 N12L 0211 TAC 0353 0362 IWD 0072 0670 0833 1097 IYE 0625 0632 JAI 0751 0807 0825 0831 0882 0885 0888 0901 0923 0932 0947 0956 JST 0506 0508 0513 0522 0842 0853 0945 1174 1198 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 3 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 6 (OCR) GA330 SERVICE BULLETIN OPERATOR MSN KAL 0162 0172 0206 0219 0222 0226 0241 0256 0258 0267 0338 0350 0351 0368 0425 0428 0484 0490 0550 1133 1155 KER 0874 0891 0927 0939 0946 KKK 0358 0364 KLM 0682 0686 0703 0738 0770 0801 0811 0819 0834 0900 1161 LTU 0120 0127 0171 0403 0432 0444 0454 0469 0476 0493 0739 0828 0911 LVG 0551 0597 0627 MAS 0067 0069 0073 0077 0095 0100 0107 0110 0116 0119 0143 0290 0296 0300 MAU 0883 1057 MEA 0926 0984 0995 0998 MON 0261 0265 MSR 0600 0610 0666 0683 0696 0709 0726 1143 MXA 0966 0971 OBS 0461 OHY 0098 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 0940 0976 1061 1094 1169 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 RSF 0980 SAA 1191 1223 SAS 0496 0497 0515 0568 SGX 0407 SIA 0978 0983 0986 0997 1006 1010 1012 1015 1085 1098 1099 1105 1107 1124 1132 1146 1149 1156 1157 STZ 0324 SVA 1108 1127 1137 1141 1147 1153 1189 1192 SWR 0229 0249 0288 0291 0322 0343 1000 1018 1026 1029 1084 1089 1101 1145 1181 1188 TAM 0232 0238 0247 0259 0361 0466 0472 0477 0486 0700 0869 0876 0949 0961 0968 0977 1112 1118 TAP 0181 0195 0223 0305 0308 0312 0317 0877 0899 0904 0914 0934 TCX 0254 0266 0301 0427 0456 0795 THA 0050 0060 0062 0064 0065 0066 0112 0122 0209 0224 0231 0346 0990 1003 1035 1037 1060 1074 1086 1090 THY 0463 0504 0697 0704 0742 0754 0774 1150 1160 1170 1172 1204 1212 TSC 0111 0177 0250 0271 0480 UAE 0248 0251 0283 0293 0295 0314 0316 0326 0328 0345 0348 0365 0372 0382 0384 0392 0396 0409 0437 0451 0452 0455 0462 0491 0494 0509 0518 0525 0536 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 4 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 7 (OCR) DA330 SERVICE BULLETIN OPERATOR MSN UAF 1080 1186 USA 0315 0323 0333 0337 0342 0370 0375 0380 0388 1011 1022 1041 1069 1076 1095 1100 VIR 1195 VKG 0309 0349 0356 0357 VLK 0055 0070 0086 XAX 0054 0952 0974 1048 1066 1075 1126 1131 1165 XLF 0501 0635 6 DATE: Apr 22/10 SERVICE BULLETIN No.: А330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 8 (OCR) DA330 SERVICE BULLETIN (4) Configuration by MSN MSN CONFIGURATION 0012 0017 0030 0037 0045 0050 0054 0055 0059 0060 0062 001 0064 0065 0066 0067 0069 0070 0071 0072 0073 0077 0082 0083 0086 0087 0095 0096 0098 0099 0100 0102 0106 0107 0109 0110 0111 0112 0113 0116 0118 0120 0121 0122 0127 0132 0138 0140 0143 0144 0148 0153 0155 0162 0165 0171 0172 0177 0181 0183 0184 0188 0189 0191 0195 0198 0200 0203 0205 0206 0209 0211 0219 0222 0223 0224 0226 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 0925 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 9 (OCR) ©A330 SERVICE BULLETIN MSN CONFIGURATION 0926 0927 0928 0930 0931 0932 0934 0935 0936 0937 0939 001 1060 0060 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 1024 1025 1026 1028 1029 1031 1033 1034 1035 1036 1037 1038 1039 1041 1042 1043 1044 1045 1046 1047 1048 1049 1052 1053 1054 1055 1057 1058 1059 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 1131 1132 1133 1135 1137 1138 1141 1143 1145 1146 1147 1149 1150 1151 1153 1155 1156 1157 1159 1160 1161 1163 1165 1167 1168 1169 1170 1171 1172 1173 1174 1177 1178 1181 1183 1184 1186 1187 1188 1189 1191 1192 1195 1196 1198 1199 1202 1204 1205 1208 1212 1214 1217 1220 1222 1223 0229 002 (5) Configuration definition **CONF 001 is valid for aircraft with rudders which might have reworked areas to be inspected. **CONF 002 is valid for aircraft with rudders which were already inspected one time during the sampling. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Consumable CMLD01 B. CONCURRENT REQUIREMENTS None DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 10 (OCR) • A330 SERVICE BULLETIN C. REASON (1) History On AIRBUS Single Aisle and Long Range 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 debonding in a rudder shell was found on the rudder of an A319 and an A321 aircraft. A large rudder debond, resulting from an undetected damage growth, could affect the handling quality of the aircraft. Under specific conditions, a large debond could lead to aircraft in-flight instability. A review of the production records revealed that the debonding reported on both rudders correspond to areas that had been reworked in production. (2) Objective/Action This Service Bulletin details the inspection procedure to inspect the reworked areas on affected rudders fitted on A330 aircraft for potential debonding. Due to the different areas on the rudder to be inspected, different inspection procedures are necessary: - Vacuum loss inspection - Elasticity Laminate Checker (ELCH) inspection - Tap test inspection - Thermography inspection - Ultrasound (US) inspection. (3) Advantages The accomplishment of this Service Bulletin will ensure the detection of potential debonding in the reworked areas. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 553042-832-848-001: Inspection (1) Do the rudder special detailed inspection on aircraft with rudders which will not exceed 13000 FC within 21 months after the issue of this Service Bulletin (2) Do the rudder special detailed inspection on aircraft with rudders which have exceeded or will exceed 13000 FC within 21 months after the issue of this Service Bulletin 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 8 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 11 (OCR) GA330 SERVICE BULLETIN **CONF 002 Task 553042-832-848-001: Inspection (1) Do 2 additional special detailed inspections (ELCH) **CONF ALL E. COMPLIANCE (1) Classification MANDATORY (2) Accomplishment Timescale **CONF 001 Table 1. Config. 001 - Rudder special detailed inspection on aircraft with rudders which will not exceed 13000 Flight Cycles (FC) within 21 months after the issue of this Service Bulletin. Area to be Condition Action Compliance time Repetitive interval inspected N/A N/A Identify the Serial Within 21 months N/A Number of the after the issue of installed rudder this SB Area 1 N/A Vacuum loss Within 21 months N/A inspection in after the issue of accordance with this SB Subtask 553042-832-201 -002 Area 1 Damage Report to AIRBUS Before next flight N/A indications found during vacuum loss inspection Area 1 No damage Report to AIRBUS Within 10 days IN/A indications found after the vacuum during vacuum loss loss inspection inspection Area 1 No damage Temporary option Before next flight, if IN/A indications found 1: Close the the temporary during vacuum loss inspection noles option 2 or the inspection with adhesive tape permanent restoration have not been accomplished 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 9 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 12 (OCR) GA330 SERVICE BULLETIN Area to be Condition Action Compliance time Repetitive interval inspected Area 1 No damage Temporary option NIA At intervals not indications found 1: Do a detailed exceeding 900 FH during vacuum loss inspection of the inspection restored area for loose or lost adhesive tape Area 1 Loose or lost tape Temporary option Before next flight, if N/A found 1: Close the the temporary inspection holes option 2 or the again with permanent adhesive tape restoration have not been accomplished Area 1 No damage Temporary option Within 21 months N/A indications found 1: Do the after the vacuum during vacuum loss permanent loss inspection inspection restoration. Do a thermography or ultrasound inspection before the resin injection Area 1 No damage Temporary option Before next flight, it IN/A indications found 2: Close the the temporary during vacuum loss inspection holes option 1 or the inspection with resin and permanent adhesive tape. Do restoration have a thermography or not been ultrasound accomplished inspection before the resin injection Area 1 Damage Temporary option Before next flight N/A indications found 2: Report to during AIRBUS thermography or ultrasound inspection Area 1 No damage Temporary option Within 21 months NA indications found 2: Restore the after the vacuum auring surface protection loss inspection thermography or ultrasound inspection 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 10 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 13 (OCR) DA330 SERVICE BULLETIN Area to be Condition Action Compliance time Repetitive interval inspected Area 1 No damage Permanent Before next flight N/A indications found restoration: Do a after the vacuum during vacuum loss thermography or loss inspection or inspection ultrasound within 21 months inspection before after the vacuum the resin injection loss inspection if the temporary option 1 or the temporary option 2 has been accomplished Area 1 Damage Permanent Before next flight N/A indications found restoration: Report during to AIRBUS thermography or ultrasound Inspection Area 1 No damage No further action N/A N/A indications found after during accomplishment of thermography or the permanent ultrasound restoration inspection Area 2 N/A ELCH inspection in Within 21 months N/A accordance with after the issue of Subtask this SB 553042-832-201 -002 Area 2 Damage Re-examine the Before next flight N/A indications found damage indications during ELCH as per tap test inspection inspection and report to AIRBUS Area 2 No damage Report to AIRBUS Report within 10 ELCH inspection indications found and do 2 additional days after the 1. within intervals during ELCH repetitive ELCH ELCH inspection between 4000 and inspection inspections 4500 FC Area 2 Damage Re-examine the Before next flight IN/A indications found damage indications during the 1. or 2. as per tap test additional repetitive inspection and ELCH inspection report to AIRBUS Area 2 No damage Report to AIRBUS Report within 10 IN/A indications found No further action days after the during the 2 ELCH inspection additional repetitive ELCH inspections 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 11 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved ### Page 14 (OCR) GA330 SERVICE BULLETIN Table 2. Config. 001 - Rudder special detailed inspection on aircraft with rudders which have already exceeded 13000 FC or will exceed 13000 FC within 21 months after the issue of this Service Bulletin. Area to be Condition Action Compliance time Repetitive interval inspected N/A N/A Identity the Serial Within 1800 Flight N/A Number of the Hours (FH) after installed rudder the issue of this SB Area 1 N/A Vacuum loss Within 1800 FH N/A inspection in after the issue of accordance with this SB Subtask 553042-832-202 -002 Area 1 Damage Report to AIRBUS Before next flight N/A indications found during vacuum loss inspection Area 1 No damage Temporary option Before next flight, if NA indications found 1: Close the the temporary during vacuum loss inspection holes option 2 or the inspection with adhesive tape permanent restoration have not been accomplished Area 1 No damage Temporary option N/A At intervals not indications found 1: Do a detailed exceeding 900 FH during vacuum loss inspection of the inspection restored area for loose or lost adhesive tape Area 1 Loose or lost tape Temporary option Before next flight, if N/A found 1: Close the the temporary inspection holes option 2 or the again with permanent adhesive tape restoration have not been accomplished Area 1 No damage Temporary option Within 21 months N/A indications found 1: Do the after the vacuum during vacuum loss permanent loss inspection inspection restoration. Do a thermograpny or ultrasound inspection before the resin injection DATE: Apr 22/10 SERVICE BULLETIN No.: А330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 12 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 15 (OCR) ©A330 SERVICE BULLETIN Area to De Condition Action Compliance time Repetitive interval Inspected Area 1 No damage Temporary option Before next flight, it IN/A indications found 2: Close the the temporary during vacuum loss inspection holes option 1 or the inspection with resin and permanent adhesive tape. Do restoration have a thermography or not been ultrasound accomplished inspection before the resin injection Area 1 Damage Temporary option Before next flight N/A indications found 2: Report to during AIRBUS thermography or ultrasound inspection Area 1 No damage Temporary option Within 21 months N/A indications found 2: Restore the after the vacuum during surface protection loss inspection thermography or ultrasound inspection Area 1 No damage Permanent Before next flight N/A indications found restoration: Do a after the vacuum during vacuum loss thermography loss inspection or inspection inspection before within 21 months the resin injection after the vacuum loss inspection if the temporary. option 1 or the temporary option 2 has been accomplished Area 1 Damage Permanent Before next flight N/A indications found restoration: Report during to AIRBUS thermography or ultrasound inspection Area 1 No damage No further action N/A ¡N/A indications found after during accomplishment of thermography or the permanent ultrasound restoration inspection 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 13 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved ### Page 16 (OCR) GA330 SERVICE BULLETIN Area to be Condition Action Compliance time Repetitive interval inspected Area 2 N/A ELCH inspection in Within 21 months N/A accordance with after the issue of Subtask this SB 553042-832-202 -002 Area 2 Damage Re-examine the Before next flight N/A indications found damage indications during ELCH as per tap test inspection inspection and report to AIRBUS Area 2 No damage Report to AIRBUS Report within 10 ELCH inspection indications found and do 2 additional days after the 1. within intervals during ELCH repetitive ELCH ELCH inspection between 4000 and inspection inspections 4500 FC Area 2 Damage Re-examine the Before next flight N/A indications found damage indications during the 1. or 2. as per tap test additional repetitive inspection and ELCH inspection report to AIRBUS Area 2 No damage Report to AIRBUS Report within 10 N/A indications found No further action days after the during the 2 ELCH inspection additional repetitive ELCH inspections Accomplishment of this Service Bulletin is expected to be rendered mandatory by the Issue of an Airworthiness Directive (AD) published by the European Aviation. Safety Agency (EASA). It is anticipated that the AD will confirm the (thresholds and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. **CONF 002 Table 1. Config. 002 - special detailed inspection (ELCH) on aircraft with rudders which have already been inspected during the sampling Area to be Condition Action Compliance time Repetitive interval inspected N/A N/A Identify the Serial Within 4000 FC N/A Number of the after the 1. installed rudder sampling inspection Area 2 No damage 2 additional N/A Within intervals indications found repetitive ELCH between 4000 and during sampling (1. inspections in 4500 FC ELCH inspection) accordance with subtask 553042-832-203-002 6 DATE: Apr 22/10 SERVICE BULLETIN No.: А330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 14 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 17 (OCR) GA330 SERVICE BULLETIN Area 2 Damage Re-examine the Before next flight indications found damage indications during the 1. or 2. as per tap test additional repetitive inspection and ELCH inspection report to AIRBUS Area 2 No damage Report to AIRBUS Report within 10 N/A indications found No further action days after the during the 2 ELCH inspection additional repetitive ELCH inspections Accomplishment of this Service Bulletin is expected to be rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). It is anticipated that the AD will confirm the (thresholds and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. **CONF ALL F. APPROVAL Approved under EASA 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 **CONF 001 Task 553042-832-848-001: Inspection Get Access 1.00 On Aircraft . Do the rudder special detailed inspection on aircraft with rudders which will not exceed 13000 FC within 21 months after the issue of this Service Bulletin Do the rudder special detailed inspection on aircraft with rudders which have exceeded or will exceed 13000 FC within 21 months after the issue of this Service Bulletin Close-Up 1.00 TOTAL MANHOURS 2.00 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 15 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved ### Page 18 (OCR) GA330 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 (39.37 in.) for the different inspection procedures: Steps Manhours Elapsed time Number of persons Get access 1.00 0.75 2 Rudder SN 0.25 0.25 identification Vacuum loss 2.00 1.50 2 inspection Thermography 0.25 0.25 2 inspection Ultrasound 0.25 0.25 inspection ELCH inspection 0.75 0.75 Tap test inspection 0.25 0.25 Close-up 1.00 0.75 2 **CONF 002 Task 553042-832-848:001: Inspection Get Access 1.00 On Aircraft Do 2 additional special detailed inspections (ELCH) Close-Up 1.00 TOTAL MANHOURS 2.00 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 (39.37 in.) for the different inspection procedures: Steps Manhours Elapsed time Number of persons Get access 1.00 0.75 2 ELCH inspection 0.75 0.75 Tap test inspection 0.25 0.25 Close-up 1.00 0.75 **CONF ALL H. WEIGHT AND BALANCE Not Changed ELECTRICAL LOAD DATA Not Changed 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 16 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 19 (OCR) SERVICE BULLETIN J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 99-10-90 12-34-24 29-10-00 55-40-00 Consumable Material List (CML) Non Destructive Test Manual (NTM) 51-10-19 12-01-19 9801-19 92-01-19 87-01-19 Structural Repair Manual (SRM) 21-92-19 01-22-19 51-77-11 **CONF 002 Aircraft Maintenance Manual (AMM) 06-41-55 12-34-24 00-01-62 55-33-13 55-40-00 Consumable Material List (CML) Non Destructive Test Manual (NTM) 51-10-03 51-10-19 51-10-26 **CONF ALL K. PUBLICATION AFFECTED None L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 17 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 20 (OCR) ©A330 SERVICE BULLETIN This Page Intentionally Left Blank 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 18 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 21 (OCR) ©A330 SERVICE BULLETIN 2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign. (2) Price and Availability None B. INDUSTRY SUPPORT INFORMATION AIRBUS will credit the manhours indicated in this Service Bulletin for inspections that are performed on aircraft in warranty at the time of such inspection. Credit will be at the operator's agreed in-house warranty labor rate. Claims for labor allowance should be received not later than 90 days after completion of the last affected warranted aircraft. This Service Bulletin is subject of specific support provided by AIRBUS. For details please contact your Customer Support Director. For the organisation of this retrofit, operators are kindly requested to contact AIRBUS retrofit management department. AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX France Tel : (33) 5 67 19 06 22 E-mail : monitored.retrofit@airbus.com Fax : (33) 5 61 93 27 45 C. LIST OF COMPONENTS No Kit D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLD01 TEM DESCRIPTION REFERENCE TO CML QTY PER A/C SEE MAT. No. NOTES Self-Adhes. Disks 05-052 As required Self Adhesive Aluminium Tape 08-052 As required Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required Wet Lay Up Resin 20-022 As required (2) Components None 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 19 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved ### Page 22 (OCR) ©A330 SERVICE BULLETIN (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability None (2) Tools To find the correct tool-PN for the different inspection tools, refer to the subsequent table: Inspection tool PN NTM reference ELCH Elasticity Laminate MBBBT100 51-10-26 Checker Kit Vacuum loss Vacuum cup TL3AMB1420T28L 51-10-28 Thermography Thermography kits 99A55407320000 51-10-25 (Camera and monitor) and 99A55407321000 (complementary tooling including hot air blower) Ultrasound US-equipment EPOCH4PLUS 51-10-24 and search unit K1SM and reference block MBBGCFRPHC200 and cable PKLL2 Tap test Tap test inspection tool 98A57103013000 51-10-03 or 99A55209001000 Tap test Function test block 99A55407291000 51-10-19 and and Woodpecker WP632 or WP632AM For more detailed information, refer to the related NTM chapter. (3) Special Tools None 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 20 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 23 (OCR) GA330 SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS Task 553042-832-848-001 - Inspection WARNING MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE RELATED DOORS - COMPONENTS THAT MOVE. WARNING MAKE SURE THAT THE FLIGHT CONTROL SAFETY-LOCKS AND THE WARNING NOTICES ARE IN POSITION. CAUTION: DO NOT CAUSE DAMAGE TO THE SURFACES, THE COMPONENTS ARE MADE OF CARBONFIBER REINFORCED PLASTIC. Task Associated Data **CONF 001 Manpower TOTAL MANHOURS 2.00 **CONF 002 Manpower TOTAL MANHOURS 2.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 553042-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 21 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved ### Page 24 (OCR) DA330 SERVICE BULLETIN Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENGE TO QTY PER A/C SEE GML MAL. No. NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required References Aircraft Maintenance Manual (AMM) 06-41-55, Page Block 001 Consumable Material List (CML) (a) For location of the access panels, (Refer to AMM 06-41-55, Page Block 001). (0) For the specification of consumable materials (Mat. No.) that you must use in this Service Bulletin, (Refer to Consumable Material List (CML)). (c) Clean the areas to be inspected with Solvent General 11-026 As required Purpose and Lint-Free Cotton 19-003 As required Cloth (2) Subtask 553042-839-201-001 - Documentation Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 553042-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the joo Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO TOTY PER A/C SEE CML MAT. No NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 22 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 25 (OCR) GA330 SERVICE BULLETIN References Aircraft Maintenance Manual (AMM) 06-41-55, Page Block 001 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.) that you must use in this Service Bulletin, (Refer to Consumable Material List (CML)). (c) Clean the areas to be inspected with Solvent General 11-026 As required Purpose and Lint-Free Cotton 19-003 As required Cloth (2) Subtask 553042-839-201-001 - Documentation Manpower Resources Skills INON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 553042-941-201-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-801 Task 29-10-00-864-001 Task 29-10-00-864-002 Task 29-10-00-864-003 55-33-13, Page Block 201 Task 55-40-00-210-001 (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-801). Check the documentation of the related aircraft for further repairs on the rudder during service. If you find documents about further repairs, contact AIRBUS. DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 23 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 26 (OCR) GA330 SERVICE BULLETIN (c) In the cockpit, put warning notices in position to tell persons not to operate the flight controls. (d) Open, safety and tag the circuit breakers as given in the rudder inspection/check Job Set-up procedure (Refer to AMM Task 55-40-00-210-001). (e) Depressurize the Green Hydraulic System (Refer to AMM Task 29-10-00-864-001). (f) Depressurize the Yellow Hydraulic System (Refer to AMM Task 29-10-00-864-002). (g) Depressurize the Blue Hydraulic System (Refer to AMM Task 29-10-00-864-003). (h) Put a warning notice in the cockpit to tell persons not to pressurize the hydraulic systems. (i) Put access platform(s) in position at the rudder. To open the access panels, (Refer to AMM 55-33-13, Page Block 201). **CONF 002 (1) Subtask 553042-941-201-001 - Job Set-up • Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-801 Task 29-10-00-864-001 Task 29-10-00-864-002 Task 29-10-00-864-003 55-33-13, Page Block 201 Task 55-40-00-210-001 (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-801). Check the documentation of the related aircraft for further repairs on the rudder during service. If you find documents about further repairs, contact AIRBUS. (c) In the cockpit, put warning notices in position to tell persons not to operate the flight controls. (d) Open, safety and tag the circuit breakers as given in the rudder inspection/check Job Set-up procedure (Refer to AMM Task 55-40-00-210-001). (e) Depressurize the Green Hydraulic System (Refer to AMM Task 29-10-00-864-001). (f) Depressurize the Yellow Hydraulic System (Refer to AMM Task 29-10-00-864-002). (g) Depressurize the Blue Hydraulic System (Refer to AMM Task 29-10-00-864-003). DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 24 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 27 (OCR) GA330 SERVICE BULLETIN (n) Put a warning notice in the cockpit to tell persons not to pressurize the hydraulic systems. Put access platform(s) in position at the rudder. To open the access panels, (Refer to AMM 55-33-13, Page Block 201). **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 553042-832-201-002 - Do the rudder special detailed inspection on aircraft with rudders which will not exceed 13000 FC within 21 months after the issue of this Service Bulletin Manpower Resources Manhours Minimum number of person Subtask elapsed time Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO QTY PER A/C SEE CML MAT. NO. NOTES Self-Adhes. Disks 05-052 As required Self Adhesive Aluminium 08-052 As required Tape Solvent General Purpose 11-026 As required Wet Lay Up Resin 20-022 As required References Non Destructive Test Manual (NTM) Task 51-10-03-280-801 Task 51-10-19-280-801 Task 51-10-24-270-801 Task 51-10-25-290-801 Task 51-10-25-290-802 Task 51-10-26-220-801 Task 51-10-28-220-801 Structural Repair Manual (SRM) 51-75-12 51-77-10 51-77-11 Para 4.M.(2) 51-77-11 Para 4.A.(3) 51-77-11 Para 5. 51-77-11 Para 4.E 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 25 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 28 (OCR) GA330 SERVICE BULLETIN References Fig. A-GAAAA Sheet 01 - Flow Chart 1, vacuum loss Rudder inspection inspection area 1 Sheet 02 - Vacuum loss inspection - damage assessment Sheet 03 - Flow Chart 2, ELCH inspection area 2 Sheet 05 - Reporting sheet Sheet 06 - Rudder SN identification Sheet 07 - Inspection areas Sheet 08 - Typical ELCH procedure Sheet 09 - Rudder skin thickness LH Sheet 10 - Rudder skin thickness RH Sheet 11 - Rudder skin thickness LH Sheet 12 - Rudder skin thickness RH Sheet 13 - Rudder skin thickness LH Sheet 14 - Rudder skin thickness RH Sheet 15 - Rudder skin thickness LH Sheet 16 - Rudder skin thickness RH Sheet 17 - Rudder skin thickness LH Sheet 18 - Rudder skin thickness RH Fig. A-GACAA Sheet 01 Rudder SN - MSN reference list Sheet 02 Sheet 03 (a) Identify the Serial Number (SN) of the rudder as shown on Fig. A-GAAAA Sheet 06. (b) If you do not find an SN placard on the rudder, contact AIRBUS for further instructions. (c) Compare the rudder SN with the rudder SNs in the rudder SN - MSN reference list Fig. A-GAGAA Sheet 01 thru Fig. A-GACAA Sheet 03 1 If you find a different SN against the MSN as detailed in the rudder SN - MSN reference list, contact AIRBUS for further instructions. If the rudder SN is not part of the rudder SN - MSN reference list, refer to the Close-up para 3.E. No further action is necessary. If the rudder SN is part of the rudder SN - MSN reference list with the same indicated MSN, continue with the below instructions. (d) The Technical Disposition (TD) details the location of the reworked area to be inspected and includes information about the vacuum loss inspection holes, if necessary. For the definition of the areas to be inspected, refer to the rudder SN - MSN reference list Fig. A-GACAA Sheet 01 thru Fig. A-GACAA Sheet 03 to find the 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 26 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 29 (OCR) © A330 SERVICE BULLETIN To get the TD, refer to the SB BOOKLET-link on the index page of this Service Bulletin on the Air@Nav Engineering page in AIRBUS WORLD and use 'SB BOOKLET-TD-K45-S3-XXXXX'. For additional information, refer to SBIT SEMB 914.0808/09. Inspection method for reworked areas: For reworked area astride AREA 1 and AREA 2, if TD provides vacuum loss hole location then rework must be treated as if in AREA 1 only. For reworked area astride AREA 1 and AREA 2, if TD does not provide vacuum loss hole location then rework must be treated as if in AREA 2 only. (e) If there are only areas on the trailing edge, shown as 'area 2' on the Fig. A-GAAAA Sheet 07, to be inspected, refer to Para (g). If there is the non-ventilated area, shown as 'area 1' on the Fig. A-GAAAA Sheet 07, to be inspected, do the subsequent inspection in accordance with the Flow Chart Fig. A-GAAAA Sheet 01 and Fig. A-GAAAA Sheet 02: Do the vacuum loss inspection within 21 months after the issue of this Service Bulletin (Refer to NTM Task 51-10-28-220-801). * Ten to head ed Temporarily install adhesive tape (Material No 08-052 - basic) on the Mark the grid of holes on the adhesive tape. CAUTION: DRILL PENETRATION INTO THE SANDWICH STRUCTURE HAS TO BE LIMITED TO 20 mm (0.8 in.) TO PREVENT INNER SKIN DAMAGE. Drill the inspection holes with DIA 1.5 mm (0.06 in.) through the outer skin only. Do the vacuum loss inspection (Refer to NTM Task 51-10-28-220-801). In case of damage indications, contact AIRBUS on the basis of a detailed referenced damage report for further instructions before next flight. In case of no damage indications, close the inspection holes as detailed in the subsequent instructions and report the result to AIRBUS within 10 days. 2 Temporary restoration of the inspection holes option 1: a Close the holes with Self Adhesive 08-052 As required Aluminium Tape 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 27 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 30 (OCR) DA330 SERVICE BULLETIN or Self-Adhes. Disks 05-052 As required Do a detailed inspection of the restored area at intervals not exceeding 900 FH. Inspect the restored area for loose or lost adhesive disks or tape. c In case of loose or lost tape or disks, close the holes again with Self Adhesive 08-052 As required Aluminium Tape or Self-Adhes. Disks 05-052 As required This temporary restoration must be replaced by the permanent restoration within 21 months after the vacuum loss inspection. For the permanent restoration, refer to Para (f)4. 3 WARNING: OBEY THE MANUFACTURER'S INSTRUCTIONS WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS ARE DANGEROUS. WARNING: WEAR THE CORRECT PROTECTIVE GLOVES, GOGGLES AND FILTER MASKS WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS ARE DANGEROUS. Temporary restoration of the inspection holes option 2: a Before the resin injection: <1> Identify the skin thickness of the areas to be inspected, refer to the subsequent table: Rudder SN Refer to Figure TS- 1014, TS-1042 Fig. A-GAAAA Sheet 09 and Fig. A-GAAAA Sheet 10 TS-2004, TS-2005 Fig. A-GAAAA Sheet 11 and Fig. A-GAAAA Sheet TS-2008 thru TS2010 12 TS-2022, TS-2023 TS-2028 thru TS-2030 TS-2032 thru TS-2034 TS-2041 TS-2044 thru TS-2046 TS-2048 thru TS-2050 TS-2057 TS-2067, TS-2068 TS-2071 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 28 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 31 (OCR) © A330 SERVICE BULLETIN Fig. A-GAAAA Sheet 13 and Fig. A-GAAAA Sheet 14 TS-3012 thru TS-3014 TS-3017 thru TS-3032 Ts-3034 thru TS-3042 TS-3046, TS-3047, TS-3049, TS-3054, TS-3055 TS-3058, TS-3060, TS-3062, TS-3063, TS-3065 TS-3067 thru TS-3070 TS-3077, TS-3078, TS-3080, TS-3081 TS-3086, TS-3089 TS-3092, TS-3093, TS-3095, TS-3096 TS-3098, TS-3099 TS-3101 thru TS-3105 TS-3108 thru TS-3112 TS-3114, TS-3116, TS-3117 TS-3120, TS-3128, TS-3131, TS-3132 TS-3212, TS-3323, TS-3330 Fig. A-GAAAA Sheet 15 and Fig. A-GAAAA Sheet TS-4020, TS-4022, TS-4023 16 TS-4025 thru TS-4027 TS-4029 thru TS-4031 TS-4038, TS-4047, TS-4049, TS-4066 TS-4083 Fig. A-GAAAA Sheet 17 and Fig. A-GAAAA Sheet 18 <2> If the skin thickness of the affected areas, defined by the TD, does not exceed 1.5 mm (0.06 in.), do a thermography inspection as detailed in NTM Task 51-10-25-290-801 or NTM Task 51-10-25-290-802, AND/OR If the skin of the affected areas, defined by the TD, is thicker than 1.5 mm (0.06 in.), do an ultrasound inspection as detailed in NTM Task 51-10-24-270-801. NOTE: During the ultrasound inspection, the vacuum inspection holes must be closed with thin adhesive tape (Material No 08-052 - basic) to prevent couplant ingress into the holes. In case of damage indications contact AIRBUS for further instructions before next flight. Prepare and dry the restoration area (Refer to SRM 51-77-11 Para 4.M.(2)). d Prepare Wet Lay Up Resin 20-022 As required (Refer to SRM 51-77-11 Para 4.A. (3)). 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 29 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 32 (OCR) GA330 SERVICE BULLETIN NOTE: The data sheets for each adhesive, resin or low density compound states the maximum quantity that can be safely mixed at one time without causing an exotherm reaction. Always refer to the appropriate data sheet before mixing the chosen material. Warm up the mixed resin to a maximum temperature of 45°C (113 F). Put the resin in a syringe volume 10 ml with a needle DIA 1.0 mm (0.04 in.) and inject the resin through the hole into the cells of the honeycomb core. Start the injection at the cell bottom and finish when the resin is leaking out of the inspection hole. g Close the filled holes with Self Adhesive 08-052 As required Aluminium Tape or Self-Adhes. Disks 05-052 As required Let the resin cure for a minimum of 6 hours at room temperature. If the room temperature is below 18°C (64F), extend the curing time in accordance with the resin manufacturer recommendations and perform a gelation test outside the restoration area. After resin gelation plus 2 h, the aircraft can be released to operations again. 1 Within 21 months after the vacuum loss inspection, do the final surface restoration: <1> Remove the self adhesive tape from the restoration areas. <2> Inspect the restoration (Refer to SRM 51-77-11 Para 5.). <3> Remove any surplus resin from the border area of the restoration. Use abrasive cloth. Start with 280 grade and finish with 400 grade. <4> Clean the restoration areas with Solvent General 11-026 As required Purpose (Refer to SRM 51-77-11 Para 4.E). <5> Restore the surface protection (Refer to SRM 51-75-12). 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 30 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 33 (OCR) GA330 SERVICE BULLETIN 4 Permanent restoration of the inspection holes: a Before the resin injection: <1> Identify the skin thickness of the areas to be inspected, refer to the subsequent table: Rudder SN Refer to Figure TS-1014, TS-1042 Fig. A-GAAAA Sheet 09 and Fig. A-GAAAA Sheet TS-2004, TS-2005 Fig. A-GAAAA Sheet 11 and Fig. A-GAAAA Sheet TS-2008 thru TS2010 12 TS-2022, TS-2023 TS-2028 thru TS-2030 TS-2032 thru TS-2034 TS-2041 TS-2044 thru TS-2046 TS-2048 thru TS-2050 TS-2057 TS-2067, TS-2068 TS-2071 TS-3001 Fig. A-GAAAA Sheet 13 and Fig. A-GAAAA Sheet TS-3010 14 TS-3012 thru TS-3014 TS-3017 thru TS-3032 Ts-3034 thru TS-3042 TS-3046, TS-3047, TS-3049, TS-3054, TS-3055 TS-3058, .TS-3060, TS-3062, TS-3063, TS-3065 TS-3067 thru TS-3070 TS-3077, TS-3078, TS-3080, TS-3081 TS-3086, TS-3089 TS-3092, TS-3093, TS-3095, TS-3096 TS-3098, TS-3099 TS-3101 thru TS-3105 TS-3108 thru TS-3112 TS-3114, TS-3116, TS-3117 TS-3120, TS-3128, TS-3131, TS-3132 TS-3212; TS-3323, TS-3330 TS-4009 thru TS-4018 Fig. A-GAAAA Sheet 15 and Fig. A-GAAAA Sheet TS-4020, TS-4022, TS-4023 16 TS-4025 thru TS-4027 TS-4029 thru TS-4031 TS-4038, TS-4047, TS-4049, TS-4066 TS-4083 Fig. A-GAAAA Sheet 17 and Fig. A-GAAAA Sheet 18 <2> If the skin thickness of the affected areas, defined by the TD, does not exceed 1.5 mm (0.06 in.), do a thermography inspection as detailed in NTM Task 51-10-25-290-801 or NTM Task AND/OR 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 31 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 34 (OCR) GA330 SERVICE BULLETIN If the skin of the affected areas, defined by the TD, is thicker than 1.5 mm (0.06 in.), do an ultrasound inspection as detailed in NTM Task 51-10-24-270-801. NOTE: During the ultrasound inspection, the vacuum inspection holes must be closed with thin adhesive tape (Material No 08-052 - basic) to prevent couplant ingress into the holes. In case of damage indications contact AIRBUS for further instructions before next flight. THE MANUFACTURER'S INSTRUCTIONS WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS ARE WARNING: WEAR THE CORRECT PROTECTIVE GLOVES, GOGGLES AND FILTER MASKS WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS ARE DANGEROUS. Prepare and dry the restoration area (Refer to SRM 51-77-11 Para d Prepare Wet Lay Up Resin 20-022 As required (Refer to SRM 51-77-11 Para 4.A. (3)). THON The data sheets for each adhesive, resin or low density compound states the maximum quantity that can be safely mixed at one time without causing an exotherm reaction. Always refer to the appropriate data sheet before mixing the chosen material. e Warm up the mixed resin to a maximum temperature of 45°C (113 F). 1 Put the resin in a syringe volume 10 ml with a needle DIA 1.0 mm (0.04 in.) and inject the resin through the hole into the cells of the honeycomb core. Start the injection at the cell bottom and finish when the resin is leaking out of the inspection hole. g Close the filled holes with a self adhesive tape. 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 32 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 35 (OCR) GA330 SERVICE BULLETIN Let the resin cure for a minimum of 12 hours at room temperature. If the room temperature is below 18°C (64F), extend the curing time in accordance with the resin manufacturer recommendations and perform a gelation test outside the restoration area. After resin gelation plus 4h, continue with the subsequent steps: <1> Remove the self adhesive tape from the restoration areas. <2> Inspect the restoration (Refer to SRM 51-77-11 Para 5.). <3> Remove any surplus resin from the border area of the restoration. Use abrasive cloth. Start with 280 grade and finish with 400 grade. <4> Clean the restoration areas with Solvent General 11-026 As required Purpose (Refer to SRM 51-77-11 Para 4.E). <5> Restore the surface protection (Refer to SRM 51-75-12). (g) If there are areas on the trailing edge, shown as 'area 2' on the Fig. A-GAAAA Sheet 07, to be inspected, do a special detailed inspection (ELCH) in accordance with the Flow Chart Fig. A-GAAAA Sheet 03: Do the ELCH inspection within 21 months after the issue of this Service Bulletin (refer to NTM Task 51-10-26-220-801). a For the ELCH inspection behind the fasteners, use one grid line with a distance of 50 mm (1.97 in.) between the inspection points, as shown on Fig. A-GAAAA Sheet 08, View D and View E, area 2. <1> The assessment criteria for the ELCH inspection behind the fasteners are: Yellow value 0.30 mm (0.012 in.) Red value 0.40 mm (0.016 in.) For the adjustment of the ELCH, refer to NTM Task 51-10-26-220-801. If the ELCH inspection extends ahead of the fasteners, use an inspection grid of 50 mm X 50 mm (1.97 in.) between the inspection points, as shown on Fig. A-GAAAA Sheet 08, View D and View E, area 1. <1> The assessment criteria for the ELCH inspection ahead of the fasteners are: Yellow value 0.25 mm (0.010 in.) Red value 0.35 mm (0.014 in.) 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 33 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 36 (OCR) G A330 SERVICE BULLETIN For the adjustment of the ELCH, refer to NTM Task 51-10-26-220-801. In case of damage indications, re- examine the findings as per tap test inspection (Refer to NTM Task 51-10-03-280-801 or NTM Task 51-10-19-280-801), and contact AIRBUS for further instructions before next In case of no damage indications, report to AIRBUS within 10 days and do 2 additional repetitive ELCH inspections at intervals not exceeding 4500 FC and not less than 4000 FC. a In case of damage indications during the additional ELCH inspection, re- examine the findings as per tap test inspection (Refer to NTM Task 51-10-03-280-801 or NTM Task 51-10-19-280-801), and contact AIRBUS for further instructions before next flight. In case of no damage indications during the additional ELCH inspection, report to AIRBUS within 10 days. (h) Fill in the reporting sheet, refer to Fig. A-GAAAA Sheet 05. In case of damage indications, send the inspection report with a referenced mail to: AIRTAC Customer Services AIRBUS Central Entity 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE Phone: +33(0)5 61 93 3400 (24 hour) Fax: +33(0)5 61 93 3500 Mailto: airtac@airbus.com and in case of damage indications or no damage indications to Structure Engineering Support Customer Services - SEES1 AIRBUS Central Entity 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 34 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 37 (OCR) GA330 SERVICE BULLETIN FRANCE Fax: +33(0)5 61 93 36 14 (2) Subtask 553042-832-202-002 - Do the rudder special detailed inspection on aircraft with rudders which have exceeded or will exceed 13000 FC within 21 months after the issue of this Service Bulletin Manpower Resources Manhours Minimum number of person Subtask elapsed time Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO OTY PER A/C SEE CML MAT. No NOTES Self-Adhes. Disks 05-052 As required Self Adhesive Aluminium 08-052 As required Tape Solvent General Purpose 11-026 As required Wet Lay Up Resin 20-022 As required References Non Destructive Test Manual (NTM) Task 51-10-03-280-801 Task 51-10-19-280-801 Task 51-10-24-270-801 Task 51-10-25-290-801 Task 51-10-25-290-802 Task 51-10-26-220-801 Task 51-10-28-220-801 Structural Repair Manual (SRM) 51-75-12 51-77-10 51-77-11 Para 4.M.(2) 51-77-11 Para 4.A. (3) 51-77-11 Para 5. 51-77-11 Para 4.E 6 DATE: Apr 22/10 SERVICE BULLETIN No.: А330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 35 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 38 (OCR) GA330 SERVICE BULLETIN References Fig. A-GAAAA Sheet 01 - Flow Chart 1, vacuum loss Rudder inspection inspection area 1 Sheet 02 - Vacuum loss inspection - damage assessment Sheet 03 - Flow Chart 2, ELCH inspection area 2 Sheet 05 - Reporting sheet Sheet 06 - Rudder SN identification Sheet 07 - Inspection areas Sheet 08 - Typical ELCH procedure Sheet 09 - Rudder skin thickness LH Sheet 10 - Rudder skin thickness RH Sheet 11 - Rudder skin thickness LH Sheet 12 - Rudder skin thickness RH Sheet 13 - Rudder skin thickness LH Sheet 14 - Rudder skin thickness RH Sheet 15 - Rudder skin thickness LH Sheet 16 - Rudder skin thickness RH Sheet 17 - Rudder skin thickness LH Sheet 18 - Rudder skin thickness RH Fig. A-GACAA Sheet 01 Rudder SN - MSN reference list Sheet 02 Sheet 03 (a) Identify the Serial Number (SN) of the rudder as shown on Fig. A-GAAAA Sheet 06. (b) If you do not find a SN placard on the rudder, contact AIRBUS for further instructions. (c) Compare the rudder SN with the rudder SNs in the reference list Fig. A-GACAA Sheet 01 thru Fig. A-GACAA Sheet 03. If you find a different SN against the MSN as detailed in the rudder SN - MSN reference list, contact AIRBUS for further instructions. 2 If the rudder SN is not part of the rudder SN - MSN reference list, refer to the Close-up para 3.E. No further action is necessary. If the rudder is part of the rudder SN - MSN reference list with the same indicated MSN, continue with the below instructions. (e) The fed and histole in ormation about the vacum thes necessary. For the definition of the areas to be inspected, refer to the rudder SN - MSN reference list Fig. A-GACAA Sheet 01 thru Fig. A-GACAA Sheet 03 to find the MSN related Technical Disposition (TD) No. 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 36 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 39 (OCR) DA330 SERVICE BULLETIN To get the TD, refer to the SB BOOKLET-link on the index page of this Service Bulletin on the Air@Nav Engineering page in AIRBUS WORLD and use 'SB BOOKLET-TD-K45-S3-XXXXX'. For additional information, refer to SBIT SEMB 914.0808/09. Inspection method for reworked areas: For reworked area astride AREA 1 and AREA 2, if TD provides vacuum loss hole location then rework must be treated as if in AREA 1 only. For reworked area astride AREA 1 and AREA 2, if TD does not provide vacuum loss hole location then rework must be treated as if in AREA 2 (e) If there are only areas on the trailing edge shown as 'area 2' on the Fig. A-GAAAA Sheet 07, to be inspected, refer to Para (g). If there is the non-ventilated area, shown as 'area 1' on the Fig. A-GAAAA Sheet 07, to be inspected, do the subsequent inspection in accordance with the Flow Chart Fiq. A-GAAAA Sheet 01 and Fig. A-GAAAA Sheet 02: Do the vacuum loss inspection within 1800 FH after the issue of this Service Bulletin (Refer. to NTM Task 51-10-28-220-801). a Temporarily install adhesive tape (Material No 08-052 - basic) on the areas to be inspected. Mark the grid of holes on the adhesive tape. CAUTION: DRILL PENETRATION INTO THE SANDWICH STRUCTURE HAS TO BE LIMITED TO 20 mm (0.8 in.) TO PREVENT INNER SKIN DAMAGE. Drill the inspection holes with DIA 1.5 mm (0.06 in.) through the outer skin only. d Do the vacuum loss inspection (Refer to NTM Task 51-10-28-220-801). In case of damage indications, contact AIRBUS on the basis of a detailed referenced damage report for further instructions before next flight. In case of no damage indications, close the inspection holes as detailed in the subsequent instructions and report the result to AIRBUS within 10 days. Temporary restoration of the inspection holes option 1: a Close the holes with Self Adhesive 08-052 As required Aluminium Tape DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 37 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 40 (OCR) GA330 SERVICE BULLETIN or Self-Adhes. Disks 05-052 As required Do a detailed inspection of the restored area at intervals not exceeding 900 FH. Inspect the restored area for loose or lost adhesive disks or tape. In case of loose or lost tape or disks, close the holes again with Self Adhesive 08-052 As required Aluminium Tape or Self-Adhes. Disks 05-052 As required This temporary restoration must be replaced by the permanent restoration within 21 months after the vacuum loss inspection. For the permanent restoration, refer to Para (f)4. WARNING: OBEY THE MANUFACTURER'S INSTRUCTIONS WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS ARE DANGEROUS. WARNING: WEAR THE CORRECT PROTECTIVE GLOVES, GOGGLES AND FILTER MASKS WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS ARE DANGEROUS. Temporary restoration of the inspection holes option 2: a Before the resin injection: <1> Identify the skin thickness of the areas to be inspected, refer to the subsequent table: Rudder SN Refer to Figure TS-1014, TS-1042 Fig. A-GAAAA Sheet 09 and Fig. A-GAAAA Sheet 10 TS-2004, TS-2005 Fig. A-GAAAA Sheet 11 and Fig. A-GAAAA Sheet TS-2008 thru TS2010 12 TS-2022, TS-2023 TS-2028 thru TS-2030 TS-2032 thru TS-2034 TS-2041 TS-2044 thru TS-2046 TS-2048 thru TS-2050 TS-2057 TS-2067, TS-2068 TS-2071 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 38 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 41 (OCR) GA330 SERVICE BULLETIN TS-3001 Fig. A-GAAAA Sheet 13 and Fig. A-GAAAA Sheet TS-3010 14 TS-3012 thru TS-3014 TS-3017 thru TS-3032 Ts-3034 thru TS-3042 TS-3046, TS-3047, TS-3049, TS-3054, TS-3055 TS-3058, TS-3060, TS-3062, TS-3063, TS-3065 TS-3067 thru TS-3070 TS-3077, TS-3078, TS-3080, TS-3081 TS-3086, TS-3089 TS-3092, TS-3093, TS-3095, TS-3096 TS-3098, TS-3099 TS-3101 thru TS-3105 TS-3108 thru TS-3112 TS-3114, TS-3116, TS-3117 TS-3120, TS-3128, TS-3131, TS-3132 TS-3212, TS-3323, TS-3330 TS-4009 thru TS-4018 Fig. A-GAAAA Sheet 15 and Fig. A-GAAAA Sheet TS-4020, TS-4022, TS-4023 16 TS-4025 thru TS-4027 TS-4029 thru TS-4031 TS-4038, TS-4047, TS-4049, TS-4066 TS-4083 Fig. A-GAAAA Sheet 17 and Fig. A-GAAAA Sheet 18 <2> If the skin thickness of the affected areas, defined by the TD, does not exceed 1.5 mm (0.06 in.), do a thermography inspection as detailed in NTM Task 51-10-25-290-801 or NTM Task AND/OR If the skin of the affected areas, defined by the TD, is thicker than 1.5 mm (0.06 in.), do an ultrasound inspection as detailed in NTM Task 51-10-24-270-801. NOTE: During the ultrasound inspection, the vacuum inspection holes must be closed with thin adhesive tape (Material No 08-052 - basic) to prevent couplant ingress into the holes. In case of damage indications contact AIRBUS for further instructions before next flight. Prepare and dry the restoration area (Refer to SRM 51-77-11 Para 4.M.(2)). d Prepare Wet Lay Up Resin 20-022 As required (Refer to SRM 51-77-11 Para 4.A. (3)). 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 39 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 42 (OCR) GA330 SERVICE BULLETIN NOTE: The data sheets for each adhesive, resin or low density compound states the maximum quantity that can be safely mixed at one time without causing an exotherm reaction. Always refer to the appropriate data sheet before mixing the chosen material. Warm up the mixed resin to a maximum temperature of 45°C (113 F). Put the resin in a syringe volume 10 ml with a needle DIA 1.0 mm (0.04 in.) and inject the resin through the hole into the cells of the honeycomb core. Start the injection at the cell bottom and finish when the resin is leaking out of the inspection hole. g Close the filled holes with Self Adhesive 08-052 As required Aluminium Tape or Self-Adhes. Disks 05-052 As required Let the resin cure for a minimum of 6 hours at room temperature. If the room temperature is below 18°C (64F), extend the curing time in accordance with the resin manufacturer recommendations and perform a gelation test outside the restoration area. After resin gelation plus 2h, the aircraft can be released to operations again. Within 21 months after the vacuum loss inspection, do the final surface restoration: <1> Remove the self adhesive tape from the restoration areas. <2> Inspect the restoration (Refer to SRM 51-77-11 Para 5.). <3> Remove any surplus resin from the border area of the restoration. Use abrasive cloth. Start with 280 grade and finish with 400 grade. <4> Clean the restoration areas with Solvent General 11-026 As required Purpose (Refer to SRM 51-77-11 Para 4.E). <5> Restore the surface protection (Refer to SRM 51-75-12). 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 40 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 43 (OCR) DA330 SERVICE BULLETIN 4 Permanent restoration of the inspection holes: a Before the resin injection: <1> Identify the skin thickness of the areas to be inspected, refer to the subsequent table: Rudder SN Refer to Figure TS-1014, TS-1042 Fig. A-GAAAA Sheet 09 and Fig. A-GAAAA Sheet 10 TS-2004, TS-2005 Fig. A-GAAAA Sheet 11 and Fig. A-GAAAA Sheet TS-2008 thru TS2010 12 TS-2022, TS-2023 TS-2028 thru TS-2030 TS-2032 thru TS-2034 TS-2041 TS-2044 thru TS-2046 TS-2048 thru TS-2050 TS-2057 TS-2067, TS-2068 TS-2071 TS-3001 Fig. A-GAAAA Sheet 13 and Fig. A-GAAAA Sheet TS-3010 TS-3012 thru TS-3014 TS-3017 thru TS-3032 Ts-3034 thru TS-3042 TS-3046, TS-3047, TS-3049, TS-3054, TS-3055 TS-3058,.TS-3060, TS-3062, TS-3063, TS-3065 TS-3067 thru TS-3070 TS-3077, TS-3078, TS-3080, TS-3081 TS-3086, TS-3089 TS-3092, TS-3093, TS-3095, TS-3096 TS-3098, TS-3099 TS-3101 thru TS-3105 TS-3108 thru TS-3112 TS-3114, TS-3116, TS-3117 TS-3120, TS-3128, TS-3131, TS-3132 TS-3212, TS-3323, TS-3330 TS-4009 thru TS-4018 Fig. A-GAAAA Sheet 15 and Fig. A-GAAAA Sheet TS-4020, TS-4022, TS-4023 16 TS-4025 thru TS-4027 TS-4029 thru TS-4031 TS-4038, TS-4047, TS-4049, TS-4066 TS-4083 Fig. A-GAAAA Sheet 17 and Fig. A-GAAAA Sheet 18 <2> If the skin thickness of the affected areas, defined by the TD, does not exceed 1.5 mm (0.06 in.), do a thermography inspection as detailed in NTM Task 51-10-25-290-801 or NTM Task 51-10-25-290-802, AND/OR 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 41 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 44 (OCR) DA330 SERVICE BULLETIN If the skin of the affected areas, defined by the TD, is thicker than 1.5 mm (0.06 in.), do an ultrasound inspection as detailed in NTM Task 51-10-24-270-801. NOTE: During the ultrasound inspection, the vacuum inspection holes must be closed with thin adhesive tape (Material No 08-052 - basic) to prevent couplant ingress into the holes. In case of damage indications contact AIRBUS for further instructions before next flight. WARNING: OBEY THE MANUFACTURER'S INSTRUCTIONS WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS ARE DANGEROUS. WARNING: WEAR THE CORRECT PROTECTIVE GLOVES, GOGGLES AND FILTER MASKS WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS ARE DANGEROUS. Prepare and dry the restoration area (Refer to SRM 51-77-11 Para 4.M.(2)). d Prepare Wet Lay Up Resin 20-022 As required (Refer to SRM 51-77-11 Para 4.A.(3)). NOTE: The data sheets for each adhesive, resin or low density compound states the maximum quantity that can be safely mixed at one time without causing an exotherm reaction. Always reter to the appropriate data sheet before mixing the chosen material. e Warm up the mixed resin to a maximum temperature of 45°C (113 F). f Put the resin in a syringe volume 10 ml with a needle DIA 1.0 mm (0.04 in.) and inject the resin through the hole into the cells of the honeycomb core. Start the injection at the cell bottom and finish when the resin is leaking out of the inspection hole. g. Close the filled holes with a self adhesive tape. 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 42 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 45 (OCR) GA330 SERVICE BULLETIN Let the resin cure for a minimum of 12 hours at room temperature. If the room temperature is below 18°C (64F), extend the curing time in accordance with the resin manufacturer recommendations and perform a gelation test outside the restoration area. After resin gelation plus 4h, continue with the subsequent steps: <1> Remove the self adhesive tape from the restoration areas. <2> Inspect the restoration (Refer to SRM 51-77-11 Para 5.). <3> Remove any surplus resin from the border area of the restoration. Use abrasive cloth. Start with 280 grade and finish with 400 grade. <4> Clean the restoration areas with Solvent General 11-026 As required Purpose (Refer to SRM 51-77-11 Para 4.E). <5> Restore the surface protection (Refer to SRM 51-75-12). (g) If there are areas on the trailing edge, shown as 'area 2' on the Fig. A-GAAAA Sheet 0Z, to be inspected, do a special detailed inspection (ELCH) in accordance with the Flow Chart Fig. A-GAAAA Sheet 03: 1 Do the ELCH inspection within 21 months after the issue of this Service Bulletin (refer to NTM Task 51-10-26-220-801). For the ELCH inspection behind the fasteners, use one grid line with a distance of 50 mm (1.97 in.) between the inspection points, as shown on Fig. A-GAAAA Sheet 08, View D and View E, area 2. The assessment criteria for the ELCH inspection behind the fasteners are: Yellow value 0.30 mm (0.012 in.) Red value 0.40 mm (0.016 in.) For the adjustment of the ELCH, refer to NTM Task 51-10-26-220-801. If the ELCH inspection extends ahead of the fasteners, use an inspection grid of 50 mm X 50 mm (1.97 in.) between the inspection points, as shown on Fig. A-GAAAA Sheet 08, View D and View E, area 1. <1> The assessment criteria for the ELCH inspection ahead of the fasteners are: Yellow value 0.25 mm (0.010 in.) Red value 0.35 mm (0.014 in.) 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 43 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 46 (OCR) GA330 SERVICE BULLETIN For the adjustment of the ELCH, refer to NTM Task 51-10-26-220-801. 2 In case of damage indications, re- examine the findings as per tap test inspection (Refer to NTM Task 51-10-03-280-801 or NTM Task 51-10-19-280-801), and contact AIRBUS for further instructions before next flight. In case of no damage indications, report to AIRBUS within 10 days and do 2 additional repetitive ELCH inspections at intervals not exceeding 4500 FC and not less than 4000 FC. a In case of damage indications during the additional ELCH inspection, re- examine the findings as per tap test inspection (Refer to NTM Task 51-10-03-280-801 or NTM Task 51-10-19-280-801), and contact AIRBUS In case of no damage indications during the additional ELCH inspections, report to AIRBUS within 10 days. (h) Fill in the reporting sheet, refer to Fig. A-GAAAA Sheet 05. In case of damage indications, send the inspection report with a referenced mail to: AIRTAC Customer Services AIRBUS Central Entity 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE Phone: +33(0)5 61 93 3400 (24 hour) Fax: +33(0)5 61 93 3500 Mailto: airtac@airbus.com and in case of damage indications or no damage indications to Structure Engineering Support Customer Services - SEES1 AIRBUS Central Entity 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 44 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 47 (OCR) GA330 SERVICE BULLETIN FRANCE Fax: +33(0)5 61 93 36 14 **CONF 002 (1) Subtask 553042-832-203-002 - Do 2 additional special detailed inspections (ELCH) Manpower Resources Manhours Minimum number of person Subtask elapsed time Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-03-280-801 Task 51-10-19-280-801 Task 51-10-26-220-801 Fig. A-GACAA Sheet 01 Rudder SN - MSN reference list Sheet 02 Sheet 03 Fig. A-GAEAA Sheet 01 - Inspection areas ELCH inspection Sheet 02 - Flow Chart Sheet 03 - Typical ELCH procedure Sheet 04 - Reporting sheet Sheet 05 - Rudder SN identification Identify the Serial Number (SN) of the rudder as shown on Fig. A-GAEAA Sheet 05. (0) If you do not find a SN placard on the rudder, contact AIRBUS for further instructions. (c) Compare the rudder SN with the rudder SNs in the reference list Fig. A-GACAA Sheet 01 thru Fig. A-GACAA Sheet 03 1 If you find a different SN against the MSN as detailed in the rudder SN - MSN reference list, contact AIRBUS for further instructions. If the rudder SN is not part of the rudder SN - MSN reference list, refer to the Close-up para 3.E. No further action is necessary. З If the rudder is part of the rudder SN - MSN reference list with the same indicated MSN, continue with the below instructions. 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 45 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 48 (OCR) GA330 SERVICE BULLETIN (a) For the areas on the trailing edge, shown as 'area 2' on the Fig. A-GAEAA Sheet 01, which have been inspected during the sampling, 2 additional repetitive special detailed inspections (ELCH) are necessary: 1 The Technical Disposition (TD) details the location of the reworked area to be inspected. a For the definition of the areas to be inspected, refer to the reference list Fig. A-GACAA Sheet 01 thru Fig. A-GACAA Sheet 03 to find the MSN related Technical Disposition (TD) No. To get the TD, refer to the SB BOOKLET-link on the index page of this Service Bulletin on the Air@Nav Engineering page in AIRBUS WORLD and use 'SB BOOKLET-TD-K45-S3-XXXXX. For additional information, refer to SBIT SEMB 914.0808/09. Do the ELCH inspection in accordance with the Flow Chart Fig. A-GAEAA Sheet 02 at intervals not exceeding 4500 FC and not less than 4000 FC (refer to NTM Task 51-10-26-220-801). For the ELCH inspection behind the fasteners, use one grid line with a distance of 50 mm (1.97 in.) between the inspection points, as shown on Fig. A-GAEAA Sheet 03, View A, area 2. The assessment criteria for the ELCH inspection behind the fasteners Yellow value 0.30 mm (0.012 in.) Red value 0.40 mm (0.016 in.) For the adjustment of the ELCH, refer to NTM Task 51-10-26-220-801. If the ELCH inspection extends ahead of the fasteners, use an inspection grid of 50 mm X 50 mm (1.97 in.) between the inspection points, as shown on Fig. A-GAEAA Sheet 03, View A, area 1. <1> The assessment criteria for the ELCH inspection ahead of the fasteners are: Yellow value 0.25 mm (0.010 in.) Red value 0.35 mm (0.014 in.) For the adjustment of the ELCH, refer to NTM Task 51-10-26-220-801. In case of damage indications, re- examine the findings as per tap test inspection (Refer to NTM Task 51-10-03-280-801 or NTM Task 51-10-19-280-801), and contact AIRBUS for further instructions before next DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 46 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 49 (OCR) GA330 SERVICE BULLETIN 4 In case of no damage indications during the additional ELCH inspections, report to AIRBUS within 10 days. (e) Fill in the reporting sheet, refer to Fig. A-GAEAA Sheet 04. In case of damage indications, send the inspection report with a referenced mail to: AIRTAC Customer Services AIRBUS Central Entity 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE Phone: +33(0)5 61 93 3400 (24 hour) Fax: +33(0)5 61 93 3500 Mailto: airtac@airbus.com and in case of damage indications or no damage indications to Structure Engineering Support Customer Services - SEES1 AIRBUS Central Entity 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE Fax: +33(0)5 61 93 36 14 **CONF ALL D. TEST **CONF 001 None **CONF 002 None 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 47 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 50 (OCR) © A330 SERVICE BULLETIN **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 553042-942-201-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 29-10-00-863-001 Task 29-10-00-863-002 Task 29-10-00-863-003 55-33-13, Page Block 201 Task 55-40-00-210-001 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) To close the access panels, (Refer to AMM 55-33-13, Page Block 201). (c) Remove the access platforms. (d) Close the circuit breakers as given in the rudder inspection/check Close-up procedure (Refer to AMM Task 55-40-00-210-001). (e) Pressurize the Green Hydraulic System (Refer to AMM Task 29-10-00-863-001) (f) Pressurize the Yellow Hydraulic System (Refer to AMM Task 29-10-00-863-002) (g) Pressurize the Blue Hydraulic System (Refer to AMM Task 29-10-00-863-003) (h) In the cockpit, remove all warning notices. **CONF 002 (1) Subtask 553042-942-201-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 29-10-00-863-001 Task 29-10-00-863-002 Task 29-10-00-863-003 55-33-13, Page Block 201 Task 55-40-00-210-001 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 48 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 51 (OCR) GA330 SERVICE BULLETIN (b) To close the access panels, (Refer to AMM 55-33-13, Page Block 201). (c) Remove the access platforms. (d) Close the circuit breakers as given in the rudder inspection/check Close-up procedure (Refer to AMM Task 55-40-00-210-001). (e) Pressurize the Green Hydraulic System (Refer to AMM Task 29-10-00-863-001) (f) Pressurize the Yellow Hydraulic System (Refer to AMM Task 29-10-00-863-002) (g) Pressurize the Blue Hydraulic System (Refer to AMM Task 29-10-00-863-003) (h) In the cockpit, remove all warning notices. 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 49 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 52 (OCR) G_SB_553042_6_AAAA_01_05 IDENTIFY THE RUDDER SERIAL NUMBER VIA THE PLACARD ON THE RUDDER SPAR NO FURTHER ACTION REQUIRED IN ACCORDANCE WITH THIS INSPECTION SB REPORT TO AIRBUS WITHIN 10 DAYS PERMANENT RESTORATION THERMOGRAPHY INSPECTION AS PER NTM 51-10-25 AND ULTRASOUND INSPECTION AS PER NTM 51-10-24 REQUIRED BEFORE RESIN INJECTION. CONTACT AIRBUS BEFORE FURTHER FLIGHT IN CASE OF FINDINGS. NO FURTHER ACTION REQUIRED IN AREA 1 IN CASE OF NO EXISTING PLACARD CONTACT AIRBUS COMPARE YOUR RUDDER SERIAL NUMBER WITH THE RUDDER SERIAL NUMBERS IN THE REFERENCE LIST I NO SERIAL NUMBER FOUND IN REFERENCE CLOSE INSPECTION HOLES TEMPORARY OPTION I! THERMOGRAPHY INSPECTION AS PER NTM 51-10-25 AND ULTRASOUND INSPECTION AS PER NTM 51-10-24 REQUIRED BEFORE RESIN INJECTION. CONTACT AIRBUS BEFORE FURTHER FLIGHT IN CASE OF FINDINGS. WITHIN 21 MONTHS AFTER THE VACUUM LOSS INSPECTION, RESTORE FINAL PROTECTION SERVICE BULLETIN No.: A330-55-3042 Page: 50 GA330 SERVICE BULLETIN DO THE SPECIAL DETAILED INSPECTION (VACUUM LOSS) AS PER NTM 51-10-28 IN AREAS DEFINED IN SPECIFIC TECHNICAL DISPOSITION FOR EACH RUDDER INDICATION FOUND TEMPORARY OPTION I FREQUENT DETAILED INSPECTION OF RESTORED AREA. AT INTERVALS NOT EXCEEDING 900 FH WITHIN 21 MONTHS AFTER THE VACUUM LOSS INSPECTION. PERFORM PERMANENT RESTORATION THERMOGRAPHY INSPECTION AS PER NTM 51-10-25 AND ULTRASOUND INSPECTION AS PER NTM 51-10-24 REQUIRED BEFORE RESIN INJECTION. CONTACT AIRBUS BEFORE FURTHER FLIGHT IN CASE OF FINDINGS. FOR THE ACCOMPLISHMENT TIMESCALE. REFER TO PARA 1.E.(2) Figure A-GAAAA - Sheet 01 Rudder inspection - Flow Chart 1, vacuum loss inspection area 1 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. REPORT TO AIRBUS TO GET FURTHER INSTRUCTIONS BEFORE NEXT FLIGHT AIRBUS INSTRUCTIONS TO BE CARRIED OUT BEFORE NEXT FLIGHT DATE: Apr 22/10 REVISION No.: 00 - Apr 22/10 **CONF 001 NOTE: ### Page 53 (OCR) GA330 SERVICE BULLETIN **CONF 001 DAMAGE ASSESSMENT BY VACUUM LOSS INSPECTION: IF THE VACUUM LOSS INSPECTION REVEALS DAMAGE AN ADD-ON INSPECTION IN MIDFIELD DIRECTION ONLY MUST BE PERFORMED TO DEFINE THE OVERALL DAMAGE SIZE. • FOR ADD-ON INSPECTION 1, DRILL ONE ADDITIONAL ROW OF INSPECTION HOLES WITH A PITCH OF 25.0mm (0.98in.) AND ONE EXTRA HOLE AT EACH END OF THE ROW PARALLEL TO THE DETECTED LEAKAGE, AS PER SKETCH BELOW. DRILL INSPECTION HOLES WITH DIAMETER 1.5mm (0.06in) THROUGH THE OUTER SKIN ONLY. WARNING: DRILL PENETRATION INTO THE SANDWICH STRUCTURE HAS TO BE LIMITED TO 20.0mm (0.79in.), TO PREVENT INNER SKIN DAMAGE. WARNING: DRILLING IN THE RESTRICTED AREA CAN DAMAGE THE INNER SKIN AND IS NOT ALLOWED. • PERFORM VACUUM LOSS INSPECTION (SAME PROCEDURE AS APPLIED FOR BASIC INSPECTION), POSITION THE VACUUM CUP IN A WAY THAT ONLY ONE OF THE NEW HOLES IS COVERED BY THE CUP, DURING EACH MEASUREMENT. • IF NO EXTRA LEAKAGE IS FOUND, DOCUMENT THE DAMAGE, USING THE REPORTING SHEET. • IF MORE LEAKAGES ARE FOUND, PROCEED WITH ADD-ON INSPECTION 2 (AND IF REQUIRED FURTHER STEPS UNTIL THE WHOLE DAMAGE EXTEND IS DETECTED), USING THE SAME PROCEDURE AS DETAILED ABOVE. NOTE: THE OVERALL DAMAGE LENGTH AND WIDTH IS BOUNDED BY THOSE ROWS OF INSPECTION HOLES, WHICH DO NOT INDICATE A VACUUM LOSS. RESULTS OF VACUUM LOSS INSPECTION O NO LEAKAGE • LEAKAGE DETECTED RESTRICTED AREA 25.0mm OVERALL LENGTH (0.98in.) DEBONDING BASIC INSPECTION RESULTS • ADD-ON INSPECTION OVERALL ADD-ON INSPECTION 1 DIRECTION OF WIDTH ADD-ON INSPECTION 2 ADD-ON INSPECTION 3 OVERALL DAMAGE SIZE DEBONDING AREA HOLES TO BE INSPECTED IN CASE OF FINDINGS. G_SB_553042_6_AAAA_02_02 Figure A-GAAAA - Sheet 02 Rudder inspection - Vacuum loss inspection - damage assessment 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 51 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 54 (OCR) DA330 SERVICE BULLETIN **CONF 001 IDENTIFY THE RUDDER SERIAL NUMBER VIA THE PLACARD ON THE RUDDER SPAR IN CASE OF NO EXISTING PLACARD CONTACT AIRBUS NO FURTHER ACTION SERIAL NUMBER REQUIRED IN FOUND IN REFERENCE ACCORDANCE WITH LIST THIS INSPECTION SB YES DO THE REPETITIVE SPECIAL DETAILED INSPECTION (ELCH) AS PER NTM 51-10-26 IN AREAS DEFINED IN SPECIFIC TECHNICAL DISPOSITION FOR EACH RUDDER INDICATION FOUND DO 2 ADDITIONAL ELCH INSPECTIONS REPORT TO AIRBUS AT INTERVALS NOT EXCEEDING WITHIN 10 DAYS 4500FC AND NOT LESS THAN 4000 FC RE-EXAMINE THE FINDINGS AS PER TAP INSPECTION YES INDICATION NTM 51-10-03 OR NTM 51-10-19 FOUND REPORT TO AIRBUS REPORT TO AIRBUS TO GET FURTHER WITHIN 10 DAYS INSTRUCTIONS BEFORE NEXT FLIGHT AIRBUS INSTRUCTIONS NO FURTHER ACTION TO BE CARRIED OUT REQUIRED BEFORE NEXT FLIGHT IN AREA 2 NOTE: FOR THE ACCOMPLISHMENT TIMESCALE. REFER TO PARA 1.E.(2) G_SB_553042_6 AAAA 03_04 Figure A-GAAAA - Sheet 03 Rudder inspection - Flow Chart 2, ELCH inspection area 2 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 52 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 55 (OCR) GA330 SERVICE BULLETIN **CONF 001 Inspection Report Rudder Surface Inspection as per SB in area: Aircraft type: Inspection date: MSN: Operator: Rudder S/N: FC: . Rudder P/N: FH: Rudder Side Inspection method LH RH Inspection Tap Test No findings Findings as detailed by sketch* and photos Thermography Inspection No findings Findings as detailed by sketch* and photos ELCH Inspection No findings Findings as detailed by sketch* and photos UT Inspection No findings by sketch* and photos Findings as detailed Inspection Vacuum Loss No findings Findings as detailed by sketch* and photos * use sketch from the TD G_SB_553042_6_AAAA_05_02 Figure A-GAAAA - Sheet 05 Rudder inspection - Reporting sheet DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 53 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 56 (OCR) GA330 SERVICE BULLETIN **CONF 001 2326 326CL 326AL POSITION OF RUDDER S/N PLACARD D AIRBUS A/C| MER # PN F5547XXXXXXXX DESCR. SER. N ° TS-XXXX CA CODE MFG DATE NOTE: OPEN ACCESS PANEL AS PER AMM 55-33-13 P. BLOCK 201. CLOSE ACCESS PANEL AS PER AMM 55-33-13 P. BLOCK 201. G_SB_553042_6_AAAA_06_01 Figure A-GAAAA - Sheet 06 Rudder inspection - Rudder SN identification DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 54 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 57 (OCR) GA330 SERVICE BULLETIN **CONF 001 BR> AREA 1 BR6- NON VENTILATED BR5- AREA 2 TRAILING EDGE AREA BR4- BR3 BR2: 50.0 mm (1.97 in) 466.0 mm (18.35 in) BRI G_SB_553042_6_AAAA_07_00 Figure A-GAAAA - Sheet 07 Rudder inspection - Inspection areas 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 55 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 58 (OCR) GA330 SERVICE BULLETIN **CONF 001 FASTENERS BR7 - BR6- AREA 1 BR5 S AREA 2 TYPICAL TRAILING EDGE AREA 1 AREA 2 ELCH INSPECTION 50.0 mm (1.97 in) BRA BR3 BRZ 50.0 mm (1.97 in): 75.0 mm (2.95 in) 75.0 mm BR 1- (2.95 in) NOTE: MINIMUM DISTANCE FROM EDGE 75.0mm (2.95in.) G_SB_553042_6_AAAA_08_01 Figure A-GAAAA - Sheet 08 Rudder inspection - Typical ELCH procedure 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 56 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 59 (OCR) GA330 SERVICE BULLETIN **CONF 001 LH SIDE OF RUDDER 18.35 (5.39 in.) 124 mm (4.88 in.) 42 mm (1.65 in.) 39.0 (1.54 in.) 38.0 mm (1.50 in.) 117 mm (4.61 in.) - 12 15 "(1.42 in.) 265.0 mm (13.46 in.) PROTECTION PLATE _ IGHTNING 36 mm 95.78 1.) BR6 PAS BLATECTION 96 mm 1.78 in BR4> BR3 i in. 14.84 BR 1027.0 m •43 in.) 115-0 m (4.17 106 mm in.) LIGHTNING PROTECTION PLATE T< 1.5mm (0.059in.) VALID FOR RUDDER NO INSPECTION A554-71500 G_SB_553042_6_AAAA_09_01 Figure A-GAAAA - Sheet 09 Rudder inspection - Rudder skin thickness LH 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 57 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 60 (OCR) GA330 SERVICE BULLETIN **CONF 001 RH SIDE OF RUDDER LIGHNING PLATECTION (23.82 605.0 mm 150 mm 18 5 15.T 91 (20.79 in.) 528.0 mm BRS SoR* BR3 140.43 A 89 (m.) 13 5 m.T 11835 10.5 BRI 10% (4.21 in.) LIGHTNING PROTECTION PLATE 8x T< 1.5mm (0.059in.) VALID FOR RUDDER NO INSPECTION A554-71500 G_SB_553042_6_AAAA_10_02 Figure A-GAAAA - Sheet 10 Rudder inspection - Rudder skin thickness RH 6 DATE: Apr 22/10 SERVICE BULLETIN No.: A330-55-3042 REVISION No.: 00 - Apr 22/10 Page: 58 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved The text continues at https://openairdocs.org/service-documents/airbus/a330-55-3042/file/f38ea30d63a5.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.