# @A318/A319/A320/A321
SERVICE BULLETIN REVISION TRANSMITTAL SHEET
AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 ATA SYSTEM: 55 

# TITLE: STABILIZERS - RUDDER - A320 RUDDER DEBOND INSPECTION MODIFICATION No.: None This page transmits Revision No.01 of Service Bulletin No.A320-55-1035 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON This revision has been issued to improve the reference list, to correct the tool PN, to improve the wording and to introduce some changes in the compliance time frame. CHANGES SUMMARY GENERAL EVALUATION GENERAL EVALUATION TABLE UPDATED R EFFECTIVITY OPERATOR LIST UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R
COMPLIANCE Classification CLASSIFICATION UPDATED R Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R MANPOWER MANPOWER UPDATED R MATERIAL INFORMATION TOOLING Tools TOOLS UPDATED R ACCOMPLISHMENT INSTRUCTIONS TASK 551035- 832-848-001-Inspection Subtask 551035-941-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R

Subtask 551035-941-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 1 6

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# @A318/A319/A320/A321
SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 551035-832-201-030 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 551035-832-202-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED NOTE UPDATED REFERENCES UPDATED R

Subtask 551035-832-203-001 SUBTASK SOLUTION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED NOTE UPDATED R

Subtask 551035-942-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R

Subtask 551035-942-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R
Fig. A-GAAAA FIGURE SOLUTION UPDATED R Fig. A-GAAAA Sheet 01 SHEET UPDATED R Fig. A-GAAAA Sheet 02 SHEET UPDATED R Fig. A-GAAAA Sheet 09 SHEET UPDATED R Fig. A-GAAAA Sheet 14 SHEET UPDATED R Fig. A-GAAAA Sheet 15 SHEET ADDED N Fig. A-GACAA FIGURE SOLUTION UPDATED R Fig. A-GACAA Sheet 01 SHEET UPDATED R Fig. A-GACAA Sheet 02 SHEET UPDATED R Fig. A-GACAA Sheet 03 SHEET UPDATED R Fig. A-GACAA Sheet 04 SHEET UPDATED R Fig. A-GACAA Sheet 05 SHEET UPDATED R Fig. A-GACAA Sheet 06 SHEET UPDATED R Fig. A-GACAA Sheet 07 SHEET UPDATED R Fig. A-GACAA Sheet 08 SHEET UPDATED R Fig. A-GACAA Sheet 09 SHEET UPDATED R Fig. A-GACAA Sheet 10 SHEET UPDATED R Fig. A-GACAA Sheet 11 SHEET UPDATED R Fig. A-GACAA Sheet 12 SHEET UPDATED R Fig. A-GACAA Sheet 13 SHEET UPDATED R Fig. A-GACAA Sheet 14 SHEET UPDATED R Fig. A-GACAA Sheet 15 SHEET UPDATED R Fig. A-GACAA Sheet 16 SHEET UPDATED R Fig. A-GACAA Sheet 17 SHEET UPDATED R Fig. A-GACAA Sheet 18 SHEET UPDATED R Fig. A-GACAA Sheet 23 SHEET ADDED N Fig. A-GACAA Sheet 24 SHEET ADDED N
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 2 6

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# @A318/A319/A320/A321
SERVICE BULLETIN REVISION TRANSMITTAL SHEET Fig. A-GAEAA FIGURE SOLUTION UPDATED R Fig. A-GAEAA Sheet 02 SHEET UPDATED R Fig. A-GAEAA Sheet 03 SHEET UPDATED R Fig. A-GAEAA Sheet 06 SHEET ADDED N FILLING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS No previous revision REVISION SEQUENCE ORIGINAL: Feb 17/10 REVISION No. : 01 - Jul 02/10

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 3 6

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# @A318/A319/A320/A321
SERVICE BULLETIN REVISION TRANSMITTAL SHEET

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# @A318/A319/A320/A321
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. ATA SYSTEM: 55 

# TITLE: STABILIZERS - RUDDER - A320 RUDDER DEBOND INSPECTION **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES On A320 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. This Service Bulletin details the inspection procedure to inspect the reworked areas on affected rudders fitted on A320 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. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED NO
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 1 6

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# @A318/A319/A320/A321
SERVICE BULLETIN SUMMARY
EVALUATION TABLE RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO NOTE(1): Service Bulletin recommended to be accomplished to prevent significant operational disruptions. MATERIAL PRICE INFORMATION **CONF 001 No Material **CONF 002 No Material EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

46U 47W 47Y 50X 51X 53U 62X 69X 76U 82U 83X 86W 86Z 95V 96W 98X AAF AAN AAR AAW ABQ ABY ACA ACI ADH ADR AEE AEU AFL AFR AHY AIJ AJM ALK AMC AMU ANA ANZ ART ATC AUA AUH AVA AWW AXM AZA BAB BAW BEC BER BGH BHP BIE BKP BMA BTV C9G CCA CCM CEB CES CIB CQH CQN CSA CSC CSN CSZ CTN CYP D2F DAL DKH DLH EDW EEZ EIN ETD EZD EZY F2I FFT FHY FIN G2X G8E GFA GOW GWY HDA HEJ HVN I2L IAC IBE IGO IRA ISR IWD IZM JAV JBU JET JKK JSA JST JZR KAC KBR KFR KGL KKK KNE KZR LAN LBT LBY LFO LMJ LMU LTU LZB M2I MAC MDL MEA MHS MJN MLD MLR MMA MNJ MON MSC MSR MXA NIA NLY O2X OHY ORF OZW PAL PIC QAF QTR RBA RJA RNV RYW RZO SBI SDM SFJ SHY SLK SSV STB STZ SUD SVR SWR SYR TAE TAI TAM TAP TAR TAS TCW TCX TGW THY TNA TOM TRK UAL UDC USA VIM VKG VKH VLE VLG VLK VOI VRD WAN WAU WHT WVL WZZ XLF CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 55.40.00.004 OEB None AOT 55A1038 55A1039 SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 2 6

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# @A318/A319/A320/A321
SERVICE BULLETIN SUMMARY
OTHER OIT 999.0092/08; SBIT 914.0808/09 NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 551035-832-848-001: Inspection TOTAL MANHOURS 2.00 **CONF 002 Task 551035-832-848-001: Inspection TOTAL MANHOURS 2.00 APPENDICES **CONF ALL None

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 3 6

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# @A318/A319/A320/A321
SERVICE BULLETIN SUMMARY

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# @A318/A319/A320/A321
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 ATA SYSTEM: 55 

# TITLE: STABILIZERS - RUDDER - A320 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 NOTE: This Service Bulletin has been issued with fleet wide effectivity due to potential interchangeability between rudders. All MSN could potentially be affected due to rudder exchange between one MSN to another after aircraft Entry Into Service (EIS). (1) Models 320-111 320-211 320-212 320-214 320-216 320-231 320-232 320-233 (2) Effectivity by MSN 00030005 0007-0008 0012 0014 0016 0019 0029 00390042-0059 0061-0078 0080-0090 0093-0097 0099 0102-0104 0109-0128 0130 0132 0135-01760178-0224 0226-0237 0239-0270 0272-0279 0281-0303 0305-0312 0314 0316-0337 0339-0362 0365-0373 0375-0384 0386-0396 0398-0411 0413-0432 0435-0444 0446-0457 0459-0466 0469-0472 0475-0476 0478-0480 0482-0483 0485-0487 0489-0492 0496-0497 0499-0501 0503-0504 0506-0508 0510-0512 0523 0525 0527-0528 0530-0531 0533-0534 0537 0539-0540 0542-0543 0545 0548-0549 0551 0553-0554 0556 0558-0559 0561-0562 0565-0566 0568-0569 0571 0573-0575 0577 0579-0580 0582 0584-0585 0587 0589-0590 0592 0594 0596 0601 0603 0605 0607 0611 0613 0615 0617 0619 0622 0624 0626 0628 0630 0635 0638 0640 0643 0645 0648 0650 0653 0655 0657-0659 0661-0662 0665 0667 0669 0671 0673 0676 0678 0681 0683 0685 0696 0698 0701-0707 0709-0710 0712 0714 0716 0718 0720 0722 0724 0726 0730 0733 0735 0737 0739 0741 0743 0745 0747 0749 0751 0754 0756 0758 0760

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 1 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

0762 0764 0766 0768 0770 0772 0774 0776 0778 0780 0782 0784 0786 0791 0793 0795 0797 0799 0801 0803 0805 0807 0809 0812 0814 0816 0818 0820 0822 0824 0826 0828 0830 0832 0834 0836 0838-0839 0842 0844 0846 0849 0851 0854 0856-0857 0859 0861 0863 0865-0866 0868 0870 0872 0874 0876-0877 0879 0881 0883-0884 0886 0888 0892 0894-0895 0897 0899-0900 0902-0903 0905 0907 0909 0911-0912 0914 0916 0918-0919 0921 0923 0925 0927-0928 0930 0932 0934 0936-0937 0939 0942-0943 0945 0947 0950-0951 0953 0955 0957-0958 0960 0962 0964 0966-0967 0969 0971 0973 0975 0977-0978 0981-0982 0984 0986 0988 0990 0992 0994 0996 0999 1001 1003 1005 1007 1009 1011 1013-1014 1026 1028 1030 1032 1035 1037 1039 1041 1047 1050 1052 1054 1057 1059 1061 1063 1065 1067 1070 1072 1075-1076 1079 1081 1083 1085 1087 1093 1099 1101 1104-1105 1108 1110 1112 1114 1117 1119 1121 1123 1125 1128 1130 1132 1134 1137-1138 1141 1143 1146 1148 1150 1152 1156 1158 1162-1163 1166 1168 1171 1173 1175 1177 1179 1181 1183 1187 1189 1192 1194 1196 1198 1200 1206 1208 1210 1213 1215 1217 1221 1224 1226 1229 1231 1234-1235 1237 1240 1242 1244 1246 1248 1251 1253 1255 1257 1259 1262 1264 1266 1268 1270 1272 1274 1280 1282 1284 1286 1288 1290 1292 1294 1296 1298 1300 1302 1304 1306 1308 1310 1312 1314 1316 1318 1320 1322 1327 1330 1332 1334 1337 1339 1341 1343 1345 1347 1349 1351 1353 1355 1357 1359 1361 1363 1365 1367-1368 1370 1372 1376 1379 1381 1383 1385 1387 1390 1394 1396 1398 1400 1402 1405 1407 1409 1411 1413 1416 1418-1419 1422 1424 1427 1430 1432 1435 1437 1439 1441 1443 1446 1448 1450 1452 1454 1457 1459 1461 1464 1467 1469-1470 1473 1475 1478 1480 1482 1484 1486 1489 1491 1493 1495 1497 1500 1502 1504 1506 1508-1509 1512 1514 1516 1518 1523 1526 1528 1530 1532-1533 1535 1538 1540 1542 1544 1546 1548 1550 1553 1555 1557 1559 1561 1564 1566 1568 1571 1578 1580 1584 1586 1588 1591 1593 1595 1597 1605 1609-1610 1613 1615 1617 1620-1621 1624 1626 1628 1631 1633 1635 1637 1639 1641 1644 1646 1648 1650 1652 1655 1657 1661 1663 1665 1667 1669 1672 1674 1676 1678 1680 1682 1686-1687 1689 1692 1694 1696-1697 1700 1702 1705 1708 1710 1712 1715 1717 1719 1721 1723 1725 1728 1730 1732 1735-1736 1739 1741 1744 1747 1749 1751 1754-1755 1757 1760 1762 1764 1767 1769 1771 1773 1775 1777 1780 1782 1784-1785 1787 1789 1792-1793 1797 1799 1802 1804 1806 1809 1812 1814 1816 1818 1821 1823 1825 1827 1829 1832 1834-1835 1838 1840 1842 1845 1847 1849 1852 1854 1856-1858 1860-1862 1864-1865 1867-1868 1871 1873-1874 1877 1879 1883 1885 1888-1889 1891-1892 1894-1896 1898-1900 1902-1904 1906-1907 1909-1911 1913-1915 1917-1918 1920 1922 1924 1927 1929 1931 1933 1935 1937 1940 1942 1944-1945 1948-1949 1951 1954 1957-1958 1961 1964-1965 1968-1969 1973 1975 1979 1981 1983 1987 1989 1993 1996 1998 2001 2003 2006 2009 2011 2014 2016 2018 2020 2022 2024 2027 2029 2031 2034 2036 2038 2040 2042 2044 2046 2048-2049 2054 2056 2058 2061 2063 2065 2068 2070 2073 2075 2077 2079 2082 2084-2085 2088 2090 2092 2094 2097 2099 2102 2104 2106 2108 2112 2114 2116 2118 2121 2123 2125 2128 2130 2132-2169 2171 2173 2175 2177-2178 2180 2182-2183 2185 2187 2189 2191 2193 2195 2197 2199 2201 2204 2206-2207 2210 2212 2215 2217 2219 2221 2223 2225 2227 2229 2231 2233 2235 2238-2239 2242 2244 2246 2248 2250 2252 2254 2256-2257 2259 2272 2274-2275 2278 2280 2282 2284 2286 2288 2291-2292 2294 2297 2299 2301 2307 2310 2312 2314 2316 2322 2325 2327 2329 2331 2334 2336 2338 2340 2343 2345 2347 2349 2352 2354 2356 2359 2361 2364 2366 2368 2372 2374 2376 2384 2386 2388 2390-2391 2393 2395 2397 2399 2401 2403 2405 2407 2409 2411 2413 2415 2417 2419 2422-2423 2425 2428 2430 2432 2434 2437 2439 2441 2443 2445 2447 2449 2451 2453 2455 2457 2459 2461 2475 2478-2479 2482 2484 2486 2489 2491 2493 2496 2498 2502 2504 2506 2509 2511 2513 2515 2517 2520 2522 2524 2526 2529 2531 2533 2535 2537 2539-2540 2542 2562 2564 2566 2569 2571 2573 2576-2577 2580 2583-2584 2587 2589 2591 2594 2596 2598 2600
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 2 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

2602 2604 2606 2608-2609 2612-2613 2616 2619-2620 2623 2626-2627 2630 2633 2635 2637 2640 2642 2645 2647 2649 2651 2654 2656 2658 2661 2663 2665 2668 2670-2671 2674 2676 2678 2680 2683 2685 2688-2689 2692 2695-2696 2699 2701 2703 2705 2708 2710 2712 2714 2717 2719 2721 2724-2725 2728 2731-2732 2734 2737 2740 2743 2745 2747 2749 2752-2753 2755 2758 2760-2761 2764 2766 2768 2770 2772 2775-2776 2778 2781 2783 2785 2787 2789 2791-2792 2794 2796 2798 2800 2802 2804 2807-2808 2810 2814 2816-2817 2820 2822 2824 2826 2828 2830 2832 2834-2835 2838 2840 2842 2844 2846 2848 2851 2853 2855-2856 2859 2861 2863 2865 2867 2869 2871 2874-2875 2877 2880-2881 2883 2885 2896 2899-2900 2902 2904 2906 2908-2909 2911 2914-2915 2917 2920 2922 2924 2926 2928 2930 2932 2934 2937 2939 2941 2943-2945 2947 2950 2952-2953 2956 2958 2960 2962 2964 2966 2968 2970 2973 2975 2977 2980 2982 2984 2986-2995 2998 3000 3002 3004 3006 3008 3010 3012 3014 3016 3018 3021 3023 3025 3027 3029 3031 3033 3035 3037 3039-3040 3042 3044 3047-3048 3050 3052 3055-3056 3058 3060 3063-3064 3066 3068 3071-3072 3074 3076 3079-3080 3083 3086-3087 3089 3091 3093 3095 3097 3099 3101 3103 3105 3107 3109 3111 3113 3115 3117 3119 3121 3123 3125 3127 3129 3131-3132 3135-3136 3138 3140-3141 3143 3145 3147-3162 3164 3166-3167 3170 3173-3174 3177-3178 3180 3182-3183 3185 3187 3189-3190 3192 3194 3196-3197 3199 3201 3203 3205-3206 3208 3210-3211 3213 3215 3218-3219 3221 3223-3224 3227-3228 3230 3232 3234 3236-3237 3239-3240 3242 3244 3246 3256-3257 3259 3261 3263-3264 3266 3268 3270 3272-3273 3275 3277-3278 3280 3282 3284 3286-3287 3289 3291 3293 3295-3296 3299 3301 3303-3304 3306 3308 3310 3312-3314 3316 3318-3319 3321 3323 3325 3327-3328 3330 3332 3335 3337-3338 3341 3343 3345 3348-3349 3351 3353-3354 3357 3359 3361-3362 3365-3366 3368 3370 3373-3374 3376 3378-3379 3381 3383-3384 3386 3389 3391-3392 3394 3396 3398 3400 3402 3404 3408-3410 3412 3414 3416 3418 3420 3422-3423 3425 3427 3430-3431 3433 3435 3437 3439-3440 3444 3446 3448-3449 3451 3453 3455-3457 3460-3461 3464-3465 3468 3470 3472-3490 3492 3494-3497 3499 3501-3503 3505-3506 3508 3510-3511 3514-3517 3519 3521 3524 3526 3528-3529 3531-3532 3535-3536 3538 3540-3541 3543 3545 3547 3549-3550 3553-3554 3556 3558-3559 3562-3563 3565 3567-3568 3570 3572 3574 3576-3577 3579 3581-3582 3591 3594 3596-3599 3601 3603 3605 3607 3609-3611 3613 3616 3618 3621-3622 3624 3626-3628 3630-3631 3640-3641 3643-3644 3646 3648-3650 3652 3654 3656 3658-3659 3662 3664 3666-3668 3670 3672 3674 3676-3677 3679 3690 3692-3693 3695-3699 3701 3703 3706-3707 3709 3711 3713-3716 3718-3719 3721 3723-3724 3726 3729 3731-3732 3734 3736 3739 3741 3743 3745 3747-3748 3750 3753 3755-3756 3758 3760 3762 3765 3767 3769 3771 3773 3775-3778 3780-3783 3785-3787 3789 3791 3793 3795 3797-3798 3800 3802 3804-3805 3807 3809 3811-3813 3815 3817 3819 3821 3823 3825 3827 3829 3831 3833 3835 3837 3840 3843 3846 3848 3850 3852 3855 3857 3859 3861 3863 3866 3868 3870-3871 3873 3875 3877 3880 3882-3883 3885 3887 3889 3891 3894 3896 3898 3900 3902 3904 3906-3910 3912-3913 3915 3917 3919 3921-3923 3925 3927 3929 3931 3933 3935 3937 3939 3941 3943 3945-3947 3949 3952-3954 3956 3959 3961 3963 3965 3967-3968 3971-3972 3974-3976 3978-3980 3984 3986 3988 3990-3992 3995 3997 3999 (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.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 3 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

OPERATOR MSN 46U 2906 2982 3275 3296 3332 3674 3734 3986 47W 0764 3164 47Y 0394 50X 0543 0661 19181969 51X 03250375 53U 3162 3316 3748 3812 3990 62X 3402 69X 0444 76U 0302 82U 0438 83X 18231896 86W 1571 86Z 0409046604971400 1523 95V 3379 96W 1240125714641785 98X 0342 0662 AAF 0244 0888 3852 AAN 0430 0527 AAR 2397 2459 2808 2840 2943 3244 3437 3483 3496 3641 3873 AAW 3224 3236 ABQ 0443 0760 3974 ABY 2158 2166 2278 2349 2712 2764 2930 2964 3044 3152 3218 3444 3476 3626 3802 3840 3925 ACA 0059 0068 0073 0084 0122 0126 0127 0141 0149 0150 0154 0159 0174 0175 0183 0210 0231 0232 0233 0242 0248 0253 0254 0255 0265 0277 0284 0290 0309 0324 0330 0341 0378 0403 0404 1719 1864 1874 1940 2018 2145 ACI 2152 ADH 31383161350235153532 ADR 0043 AEE 3033 3066 3074 3365 3392 3423 3439 3478 3526 3709 3714 3745 3753 3773 3785 3829 3850 AEU 0136 AFL 2106 2116 2133 2144 2151 2163 2233 2875 2920 2947 3052 3063 3157 3373 3410 3511 3545 3574 3627 3631 3640 3644 3699 3711 3778 3786 3789 3823 3835 3923 3954 AFR 0005 0007 0012 0014 0016 0019 0044 0061 0062 0063 0102 0115 0128 0130 0144 0145 0155 0156 0184 0186 0187 0188 0214 0226 0227 0228 0235 0236 0237 0239 0270 0278 0285 0286 0287 0337 0352 0377 0491 1502 1873 1879 1885 1894 1900 1924 1949 2140 2705 2721 3008 3420 3470 3777 3795 3825 3859 AHY 0331 284628652991 AIJ 1132 1162 1179 1244 1259 1308 1322 3149 3160 3286 3312 3508 3514 3667 3690 AJM 0624 0626 0628 1213 1390 1747 1751 ALK 0169 2564 2908 2914 AMC 2142 2189 2291 2665 2768 3056 3068
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 4 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

OPERATOR MSN AMU 0805 0928 ANA 0139 0151 0167 0170 0196 0212 0219 0245 0300 0328 0365 0383 0413 0482 0501 0507 0531 0534 0549 0554 0658 0669 0685 2061 2998 3099 3147 3148 3189 ANZ 2085 2090 2112 2130 2148 2153 2173 2257 2297 2533 2594 2663 ART 0142 02830310 0311 03330359 0726 ATC 0630 AUA 0768 0776 0797 1137 1150 1189 1387 1478 AUH 2403 AVA 3408 3664 3961 3980 3988 3992 AWW 0446 AXM 2612 2633 2656 2683 2699 2760 2816 2826 2842 2881 2885 2926 2944 2956 2989 3000 3018 3064 3117 3140 3154 3173 31823194 3201 3223 3232 3261 32773291 32993327 33383353 3370 3394 3404 3427 3448 3477 3486 348935053521 3536 3549 3568 3576 3582 36103628 364836793701 3715372937653776 38133875 39633997 AZA 0951 0999 1138 1168 1217 1448 1457 1473 1480 1489 2869 2932 2995307630793080311531783213 3295 3328 33433362 3412 3464 3482 3563 3598360936433666 3695 3732 3815 3831 3846 3885 3906 3921 3956 3976 3978 BAB 0579 0645 3861 BAW 0039 0042 0103 0109 0120 1661 1665 1687 1689 1696 1708 1754 1760 1782 1814 1829 1871 1883 1899 1907 1910 1958 2038 2040 3301 3314 3351 3468 3499 3550 3607 3649 3697 3703 3721 3726 3912 BEC 3199 BER 2685 2696 2820 2835 3093 3121 3242 3289 3945 3995 BGH 0221 0294 0305 0349 BHP 2968 3006 3021 3055 3422 BIE 0293 BKP 2254 2310 2509 BMA 1014 1177 1418 1424 1697 1732 1922 1987 2441 BTV 0168 0441 0449 0460 0461 0710 1676 C9G 0246 CCA 0707 0724 0876 0921 1296 3215 3221 3337 3461 3506 3601 CCM 0533 0548 3882 3952 CEB 2419 2439 2994 3048 3272 3433 3472 3487 3646 3762 3767 CES 0665 0754 0799 0828 0838 0854 0883 0897 0909 0914 0925 0939 0967 0984 0986 1005 1028 1030 1041 1070 1072 1093 1108 1312 1316 1330 1345 1357 1361 1532 1542 1639 1906 1911 1964 1981 2022 2034 2036 2049 2056 2068 2155 2171 2182 2199 2212 2219 2221 2235 2239 2244 2274 2437 2451 2478 2493 2498 2562 2591 2606 2627 3170 3197 3481 3559 3611 3613 3650 3677 3692 3716 3775 3793 3797 3870 3904 3929 3937 3965 CIB 0774 0809 0884 0894 0905 0957 0971 1381 1402 1416 1437 1968 CQH 0879 0978 1286 1372 1686 1769 1852 1920 2939 3014 3023 3747 3819
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 5 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

OPERATOR MSN CQN 0696 0698 0704 0705 CSA 1439 1450 2719 2758 2789 3031 3060 3097 CSC 0540 0551 0556 0573 0582 0872 0874 0902 0912 0919 1007 1013 1500 3158 3167 3196 3210 3386 3449 3591 CSN 0709 0712 0718 0720 0722 0849 0859 0881 0895 0900 0950 0966 1035 1039 1057 2275 2334 2343 2345 2354 2361 2484 2506 2511 2637 2680 2689 2701 2708 2714 2743 2770 2772 2796 2824 2834 2855 2861 2877 2899 2915 2950 2960 2986 3910 3941 3959 3999 CSZ 0994 2909 2973 2980 3131 3132 3153 3206 3366 3383 3435 3440 3456 3528 3599 3696 3698 3756 3848 3855 3887 3898 3935 3971 CTN 0258 0671 1009 1237 CYP 0180 0256 0295 0316 2359 D2F 0211 024302510299 0376 0407 DAL 0118 0121 0125 0152 0153 0160 0171 0192 0197 0206 0208 0213 0262 0263 0272 0273 0281 0282 0297 0298 0306 0307 0318 0319 0329 0339 0340 0355 0358 0360 0367 0372 0380 0381 0387 0388 0399 0408 0410 0417 0418 0766 0778 0786 0801 0807 0818 0830 0832 0846 0903 0907 0911 0923 0962 0964 0981 0988 0996 1011 1037 1535 1633 1641 1646 1789 1812 2082 2092 DKH 2975 3027 3234 3268 3368 3485 3596 3605 3967 3984 DLH 0069 0070 0071 0072 0078 0083 0086 0093 0094 0104 0110 0111 0116 0117 0135 0137 0147 0161 0162 0172 0200 0201 0202 0209 0216 0217 0218 0267 0268 0269 0346 0382 0401 1337 1365 1367 EDW 0942 0947 1026 EEZ 0737 0749 1125 1715 1723 1937 1983 2001 2102 EIN 1242 1394 1443 1467 2191 2206 2217 2250 2256 2272 2294 2364 2374 2399 2409 2411 2432 2486 2542 2583 2635 2810 3129 3136 3318 3345 3501 3755 3781 3857 ETD 0350 1944 1945 2167 3004 3050 3676 3693 3713 3902 EZD 2141 2147 3621 EZY 1993 2137 2157 3805 3843 3871 3909 3913 3922 3946 3953 3975 3979 3991 F2I 0008 0193 FFT 1806 2325 3389 3431 FHY 0132 0288 0580 2524 FIN 1405 1470 1544 1588 1678 1712 1735 1913 1989 2065 2146 2154 G2X 0234 0289 1973 G8E 0003 1546155716501961 GFA 0419 0459 0537 3706 GOW 3256 3306 3597 3616 3798 3827 3900 3915 GWY 1198 1564 1615 1725 1860 1867 HDA 0756 0784 0812 0930 1253 1721 2229 2238 2428 HEJ 0087 0088 HVN 0590 0594 0601 0605 0607 0611 0617 0619 0648 0650 I2L 04960814 1780

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 6 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

OPERATOR MSN IAC 0045 0046 0047 0048 0049 0050 0051 0056 0057 0058 0074 0075 0080 0089 0090 0095 0096 0097 0247 0257 0308 0314 0326 0327 0336 0344 0354 0362 0386 0396 0398 0411 0416 0423 0431 0432 0451 0469 0478 0480 0486 0490 0492 0499 IBE 0158 0173 0176 0207 0223 0224 0266 0274 0323 0356 1047 1059 1067 1087 1099 1101 1119 1208 1229 1255 1262 1288 1292 1318 1347 1516 1530 1540 1655 1674 1694 1736 1793 1809 2104 2143 2225 2242 2248 2347 2391 2776 2807 IGO 2844 2863 2883 2911 2958 2990 3086 3159 3192 3227 3335 3357 3414 3453 3457 3497 3541 3618 3782 3863 3943 IRA 0303 0312 0345 0530 0575 0857 2054 ISR 0384 0426 IWD 11302011 2745 3758 3868 3889 3933 IZM 1730 2118 JAV 0029 JBU 1123 1156 1173 1235 1270 1280 1302 1327 1398 1446 1452 1506 1528 1610 1705 1739 1784 1849 1861 1898 1904 1915 1917 1927 1948 2006 2020 2031 2042 2063 2075 2099 2125 2132 2136 2149 2150 2159 2160 2177 2201 2215 2231 2246 2259 2280 2284 2286 2307 2314 2336 2352 2368 2384 2386 2415 2447 2449 2461 2489 2491 2504 2520 2535 2577 2580 2640 2647 2671 2710 2725 2755 2781 2802 2814 2832 2848 2871 2880 2900 2945 2970 2977 2992 3029 3039 3072 3091 3119 3150 3190 3228 3263 3287 3348 3381 3416 3451 3479 3488 3517 3554 3572 3622 3659 3707 3724 3760 3800 3811 JET 0163 0204 0215 0371 0421 0542 0816 0877 JKK 1183 1349 1383 1407 1497 1631 1682 1749 1862 1914 1933 1979 1998 2027 2168 2210 2223 2479 2589 JSA 215621642316 2356 2395 2401 2453 2457 2604 JST 2169 2185 2197 2292 2299 2322 2329 2338 2423 2455 2475 2515 2526 2537 2573 2587 2600 2608 2642 2651 2703 2717 2766 2787 3474 3495 3547 3668 3743 3783 3917 JZR 2569 2584 2792 2822 3016 3349 3656 3670 3919 3939 KAC 0181 0182 0195 2046 KBR 0937 14541597 KFR 2366 2376 2413 2443 2496 2502 2522 2531 2576 2645 2670 2676 2731 2747 2753 2817 2856 2874 2922 3012 3089 3105 3270 KGL 2029 2077 KKK 0640 0676 KNE 2123 2165 3361 3396 3425 3475 3787 3817 3894 KZR 2016 2128 2828 2987 3141 3484 3519 LAN 1304 1332 1351 1355 1491 1512 1526 1548 1568 1626 1854 1858 1877 1903 3280 3319 3535 3556 LBT 0222 0301 0348 0400 0793 1121 1175 1744 3480 LBY 0558 0561 LFO 0659 LMJ 1868 LMU 0932 0943
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 7 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

OPERATOR MSN LTU 1385 1441 1493 1504 1553 1797 1838 1931 2009 2539 2619 2654 3516 LZB 2540 2596 3780 M2I 1411 MAC 3246 3809 3833 MDL 0391 3264 3330 3524 3543 MEA 3736 3804 3837 MHS 1300 1353 MJN 3723 MLD 0249 0622 0741 MLR 0977 MMA 0113 0114 MNJ 0615 MON 0379 0389 0392 1081 1370 MSC 2937 2966 3282 3323 MSR 0165 0166 0178 0194 0198 0322 0351 0366 2070 2073 2079 2088 2094 MXA 0164 0179 0252 0259 0260 0261 0275 0276 0291 0292 0296 0320 0321 0332 0347 0353 0357 0361 0368 0369 0373 0405 0406 0428 0447 0566 3123 3304 3374 NIA 3183 3219 NLY 2529 2668 2749 2867 2902 O2X 1605 OHY 0455 0471 091614821509 ORF 2566 OZW 0429 PAL 0706 0745 0936 1171 1210 2162 2183 3087 3107 3187 3205 3273 3310 3455 3553 3579 3652 3731 PIC 0990 QAF 0927 QTR 1566 1648 1773 1895 1957 2097 2121 2138 2161 2288 3071 RBA 2135 2139 RJA 2598 2649 2692 2953 RNV 0229 07723492 RYW 0569 RZO 0795 2390 2425 3891 SBI 2623 3446 3473 3490 3494 3866 3880 SDM 0427 0525 1578 1657 1767 SFJ 2620 2658 2695 3025 SHY 0138 0148 1194 SLK 0899 0969 1422 1561 2058 2252 2517 2775 3570 3821 SSV 1965 2003 STB 01120415 STZ 0190 027903950420 0436 SUD 3040 SVR 0140 0157 0203 0220 0735 1063 1152 1484 1777 2175 2187 2327
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 8 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

OPERATOR MSN SWR 0545 0553 0559 0562 0574 0577 0585 0596 0603 0635 0643 0673 0681 0701 0703 0782 1762 1951 2024 2134 SYR 0886 0918 1032 1076 1085 1117 TAE 0657 0934 2084 TAI 1334 1624 2282 2301 2434 2791 2917 3042 3103 3113 3378 3418 3510 3538 3577 3581 TAM 0250 0334 0335 0440 0758 1143 1158 1215 1246 1251 1339 1368 1376 1459 1486 1518 1580 1591 1593 1595 1613 1628 1652 1663 1672 1692 1717 1757 1771 1775 1802 1804 1818 1825 1827 1832 1835 1857 1888 1891 2014 2044 2372 2393 2417 2445 2513 2602 2661 2734 2737 2783 2838 2859 2896 2904 2924 3002 3035 3047 3058 3111 3156 3180 3211 3240 3266 3278 3284 3313 3325 3391 3540 3565 3594 3630 3658 3662 3750 3908 3972 TAP 0185 0191 0870 0945 0960 0982 1181 1206 1231 1667 1799 1816 2178 3769 3883 TAR 0119 0123 0124 0205 0370 0390 0402 0511 0958 0975 1187 1700 TAS 0667 0739 0743 1054 TCW 0425 04530653 1306 1787 1929 1975 TCX 0424 0437 0476 0716 1942 2114 TGW 2195 2331 2340 2724 2728 2952 THY 1856 1909 1996 2609 2626 2928 2934 2941 2984 3010 3185 3208 3239 3257 3303 3341 3558 3567 3603 3654 3718 3719 38963931 3949 TNA 0791 0822 TOM 1320 1637 2180 TRK 2048 3259 3308 UAL 0435 0439 0442 0450 0452 0454 0456 0457 0462 0463 0464 0465 0470 0472 0475 0479 0483 0485 0487 0489 0500 0503 0504 0506 0508 0510 0512 0523 0539 0568 0571 0587 0589 0592 0613 0638 0655 0678 0683 0702 0751 0780 0820 0824 0826 0834 0836 0842 0851 0865 0955 1001 1104 1105 1128 1146 1163 1192 1248 1266 1272 1282 1290 1341 1343 1359 1363 1409 1427 1432 1435 1469 1475 1495 1508 1514 1533 1538 1555 1559 1584 1586 1609 1617 1620 1669 1680 1702 1728 1741 1755 1821 1840 1842 1845 1847 1865 UDC 0085 0230 0733 0747 USA 0052 0053 0054 0055 0064 0065 0066 0067 0076 0077 0081 0082 0099 0317 0448 0565 0584 0762 0770 0803 0844 0856 0861 0863 0866 0868 0953 1003 1050 1052 1061 1065 1075 1079 1083 1110 1112 1114 1134 1141 1148 1166 1196 1224 1234 1264 1268 1274 1284 1294 1298 1310 1314 1419 1621 1644 1710 1764 1792 1935 2193 2312 2405 2422 2430 2482 2613 2630 VIM 2108 2732 2804 3125 VKG 1889 1954 VKH 03930414 VLE 1226

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 9 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

OPERATOR MSN VLG 0143 0146 0199 0240 0241 0264 0992 1221 1396 1413 1430 1461 1550 2207 2227 2388 2407 2678 2761 2785 2794 2798 2962 2988 3083 3095 3109 3145 3151 3174 3203 3237 3293 3321 3376 3400 3529 VLK 0422 0528 0714 0730 1200 1379 VOI 3624 3672 VRD 2616 2674 2740 2778 2800 2830 2851 28532993 3037 3101 3135 3155 3230 3359 3398 3460 3465 3503 WAN 3739 3791 3907 WAU 35313741 WHT 2204 WVL 2571 3562 WZZ 0839 0892 1635 1834 1892 1902 2688 2752 3127 3143 3166 3177 3354 3384 3409 3430 3771 3807 3877 3927 3947 3968 XLF 0189 0343 0973

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 10 6

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# @A318/A319/A320/A321
SERVICE BULLETIN
(4) Configuration by MSN MSN CONFIGURATION 0003 0005 0007 0008 0012 0014 0016 0019 0029 0039 0042 0043 0044 0045 0046 0047 0048 0049 0050 0051 0052 0053 0054 0055 0056 0057 0058 0059 0061 0062 0063 0064 0065 0066 0067 0068 0069 0070 0071 0072 0073 0074 0075 0076 0077 0078 0080 0081 0082 0083 0084 0085 0086 0087 0088 0089 0090 0093 0094 0095 0096 0097 0099 0102 0103 0104 0109 0110 0111 0112 0113 0114 0115 0116 0117 0118 0119 0120 0121 0122 0123 0124 0125 0126 0127 0128 0130 0132 0135 0136 0137 0138 0139 0140 0141 0142 0143 0144 0145 0146 0147 0148 0149 0150 0151 0152 0153 0154 0155 0156 0157 0158 0159 0160 0161 0162 0163 0164 0165 0166 0167 0168 0169 0170 0171 0172 0173 0174 0175 0176 0178 0179 0180 0181 0182 0183 0184 0185 0186 0187 0188 0189 0190 0191 0192 0193 0194 0195 0196 0197 0198 0199 0200 0201 0202 0203 0204 0205 0206 0207 0208 0209 0210 0211 0212 0213 0214 0215 0216 0217 0218 0219 0220 0221 0222 0223 0224 0226 0227 0228 0229 0230 0231 0232 0233 0234 0235 0236 0237 0239 0240 0241 0242 0243 0244 0245 0246 0247 0248 0249 0250 0251 0252 0253 0254 0255 0256 0257 0258 0259 0260 0261 0262 0263 0264 0265 0266 0267 0268 0269 0270 0272 0273 0274 0275 0276 0277 0278 0279 0281 0282 0283 0284 0285 0286 0287 0288 0289 0290 0291 0292 0293 0294 0295 0296 0297 0298 0299 0300 0301 0302 0303 0305 0306 0307 0308 0309 0310 0311 0312 0314 0316 0317 0318 0319 0320 0321 0322 0323 0324 0325 0326 0327 0328 0329 0330 0331 0332 0333 0334 0335 0336 0337 0339 0340 0341 0342 0343 0344 0345 0346 0347 0348 0349 0350 0351 0352 0353 0354 0355 0356 0357 0358 0359 0360 0361 0362 0365 0366 0367 0368 0369 0370 0371 0372 0373 0375 0376 0377 0378 0379 0380 0381 0382 0383 0384 0386 0387 0388 0389 0390 0391 0392 0393 0394 0395 0396 0398 0399 0400 0401 0402 0403 0404 0405 0406 0407 0408 0409 0410 0411 0413 0414 0415 0416 0417 0418 0419 0420 0421 0422 0423 0424 0425 0426 0427 0428 0429 0430 0431 0432 0435 0436 0437 0438 0439 0440 0441 0442 0443 0444 0446 0447 0448 0449 0450 0451 0452 0453 0454 0455 0456 0457 0459 0460 0461 0462 0463 0464 0465 0466 0469 0470 0471 0472 0475 0476 0478 0479 0480 0482 0483 0485 0486 0487 0489 0490 0491 0492 0496 0497 0499 0500 0501 0503 0504 0506 0507 0508 0510 0511 0512 0523 0525 0527 0528 0530 0531 0533 0534 0537 0539 0540 0542 0543 0545 0548 0549 0551 0553 0554 0556 0558 0559 0561 0562 0565 0566 0568 0569 0571 0573 0574 0575 0577 0579 0580 0582 0584 0585 0587 0589 0590 0592 0594 0596 0601 0603 0605 0607 0611 0613 0615 0617 0619 0622 0624 0626 0628 0630 0635 0638 0640 0643 0645 0648 0650 0653 0655 0657 0658 0659 0661 0662 0665 0667 0669 0671 0673 0676 0678 0681 0683 0685 0696 0698 0701 0702 0703 0704 0705 0706 0707 0709 0710 0712 0714 0716 0718 0720 0722 0724 0726 0730 0733 0735073707390741 001

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 11 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

MSN CONFIGURATION 0743 0745 0747 0749 0751 0754 0756 0758 0760 0762 0764 0766 0768 0770 0772 0774 0778 0780 0782 0784 0786 0791 0793 0795 0797 0799 0801 0803 0805 0807 0809 0812 0814 0816 0818 0820 0822 0824 0826 0828 0830 0832 0834 0836 0838 0839 0842 0844 0846 0849 0851 0854 0856 0857 0859 0861 0863 0865 0866 0868 0870 0872 0874 0876 0877 0879 0881 0883 0884 0886 0888 0892 0894 0895 0897 0899 0900 0902 0903 0905 0907 0909 0911 0912 0914 0916 0918 0919 0921 0923 0925 0927 0928 0930 0932 0934 0936 0937 0939 0942 0943 0947 0950 0951 0953 0955 0957 0958 0960 0962 0964 0966 0967 0969 0971 0973 0975 0977 0978 0981 0982 0984 0986 0988 0990 0992 0994 0996 0999 1001 1003 1005 1007 1009 1011 1013 1014 1026 1028 1030 1032 1035 1037 1039 1041 1047 1050 1052 1054 1057 1059 1061 1063 1065 1067 1070 1072 1075 1076 1079 1081 1083 1085 1087 1093 1099 1101 1104 1105 1108 1110 1112 1114 1117 1119 1121 1123 1125 1128 1130 1132 1134 1137 1138 1141 1143 1146 1148 1150 1152 1156 1158 1162 1163 1166 1168 1171 1173 1175 1177 1179 1181 1183 1187 1189 1192 1194 1196 1198 1200 1206 1208 1210 1213 1215 1217 1221 1224 1226 1229 1231 1234 1235 1237 1240 1242 1244 1246 1248 1251 1253 1255 1257 1259 1262 1264 1266 1268 1270 1272 1274 1280 1282 1284 1286 1288 1290 1292 1294 1296 1298 1300 1302 1304 1306 1308 1310 1312 1314 1316 1318 1320 1322 1327 1330 1332 1334 1339 1341 1343 1345 1347 1349 1351 1353 1355 1357 1359 1361 1363 1365 1367 1368 1370 1372 1376 1379 1381 1383 1385 1387 1390 1394 1396 1398 1400 1402 1405 1407 1409 1411 1413 1416 1418 1419 1422 1424 1427 1430 1432 1435 1437 1439 1441 1443 1446 1448 1450 1452 1454 1457 1459 1461 1464 1467 1469 1470 1473 1475 1478 1480 1482 1484 1486 1489 1491 1493 1495 1497 1500 1502 1504 1506 1508 1509 1512 1514 1516 1518 1523 1526 1528 1530 1532 1533 1535 1538 1540 1542 1544 1546 1548 1550 1553 1555 1557 1559 1561 1564 1566 1568 1571 1578 1580 1584 1586 1588 1591 1593 1595 1597 1605 1609 1610 1613 1615 1617 1620 1621 1624 1626 1628 1631 1633 1635 1637 1639 1641 1644 1646 1648 1650 1652 1655 1657 1661 1663 1665 1667 1669 1672 1674 1676 1678 1680 1682 1686 1687 1689 1692 1694 1696 1697 1700 1702 1705 1708 1710 1712 1715 1717 1719 1721 1723 1725 1728 1730 1732 1735 1736 1739 1741 1744 1747 1749 1751 1754 1755 1757 1760 1762 1764 1767 1769 1771 1773 1775 1777 1780 1782 1784 1785 1787 1789 1792 1793 1797 1799 1802 1804 1806 1809 1812 1814 1816 1818 1821 1823 1825 1827 1829 1832 1834 1835 1838 1840 1842 1845 1847 1849 1852 1854 1856 1857 1858 1860 1861 1862 1864 1865 1867 1868 1871 1873 1874 1877 1879 1883 1885 1888 1889 1891 1892 1894 1895 1896 1898 1899 1900 1902 1903 1904 1906 1907 1909 1910 1911 1913 1914 1915 1917 1918 1920 1922 1924 1927 1929 1931 1933 1935 1937 1940 1942 1944 1945 1948 1949 1951 1954 1957 1958 1961 1964 1965 1968 1969 1973 1975197919811983 001

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 12 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

MSN CONFIGURATION 1987 1989 1993 1996 1998 2001 2003 2006 2009 2011 2014 2016 2018 2020 2022 2024 2027 2029 2031 2034 2036 2038 2040 2042 2044 2046 2048 2049 2054 2056 2058 2061 2063 2065 2068 2070 2073 2075 2077 2079 2082 2084 2085 2088 2090 2092 2094 2097 2099 2102 2104 2106 2108 2112 2114 2116 2118 2121 2123 2125 2128 2130 2132 2133 2134 2135 2136 2137 2138 2139 2140 2141 2142 2143 2144 2145 2146 2147 2148 2149 2150 2151 2152 2153 2154 2155 2156 2157 2158 2159 2160 2161 2162 2163 2164 2165 2166 2167 2168 2169 2171 2173 2175 2177 2178 2180 2182 2183 2185 2187 2189 2191 2193 2195 2197 2199 2201 2204 2206 2207 2210 2212 2215 2217 2219 2221 2223 2225 2227 2229 2231 2233 2235 2238 2239 2242 2244 2246 2248 2250 2252 2254 2256 2257 2259 2272 2274 2275 2278 2280 2282 2284 2286 2288 2291 2292 2294 2297 2299 2301 2307 2310 2312 2314 2316 2322 2325 2327 2329 2331 2334 2336 2338 2340 2343 2345 2347 2349 2352 2354 2356 2359 2361 2364 2366 2368 2372 2374 2376 2384 2386 2388 2390 2391 2393 2395 2397 2399 2401 2403 2405 2407 2409 2411 2413 2415 2417 2419 2422 2423 2425 2428 2430 2432 2434 2437 2439 2441 2443 2445 2447 2449 2451 2453 2455 2457 2459 2461 2475 2478 2479 2482 2484 2486 2489 2491 2493 2496 2498 2502 2504 2506 2509 2511 2513 2515 2517 2520 2522 2524 2526 2529 2531 2533 2535 2537 2539 2540 2542 2562 2564 2566 2569 2571 2573 2576 2577 2580 2583 2584 2587 2589 2591 2594 2596 2598 2600 2602 2604 2606 2608 2609 2612 2613 2616 2619 2620 2623 2626 2627 2630 2633 2635 2637 2640 2642 2645 2647 2649 2651 2654 2656 2658 2661 2663 2665 2668 2670 2671 2674 2676 2678 2680 2683 2685 2688 2689 2692 2695 2696 2699 2701 2703 2705 2708 2710 2712 2714 2717 2719 2721 2724 2725 2728 2731 2732 2734 2737 2740 2743 2745 2747 2749 2752 2753 2755 2758 2760 2761 2764 2766 2768 2770 2772 2775 2776 2778 2781 2783 2785 2787 2789 2791 2792 2794 2796 2798 2800 2802 2804 2807 2808 2810 2814 2816 2817 2820 2822 2824 2826 2828 2830 2832 2834 2835 2838 2840 2842 2844 2846 2848 2851 2853 2855 2856 2859 2861 2863 2865 2867 2869 2871 2874 2875 2877 2880 2881 2883 2885 2896 2899 2900 2902 2904 2906 2908 2909 2911 2914 2915 2917 2920 2922 2924 2926 2928 2930 2932 2934 2937 2939 2941 2943 2944 2945 2947 2950 2952 2953 2956 2958 2960 2962 2964 2966 2968 2970 2973 2975 2977 2980 2982 2984 2986 2987 2988 2989 2990 2991 2992 2993 2994 2995 2998 3000 3002 3004 3006 3008 3010 3012 3014 3016 3018 3021 3023 3025 3027 3029 3031 3033 3035 3037 3039 3040 3042 3044 3047 3048 3050 3052 3055 3056 3058 3060 3063 3064 3066 3068 3071 3072 3074 3076 3079 3080 3083 3086 3087 3089 3091 3093 3095 3097 3099 3101 3103 3105 3107 3109 3111 3113 3115 3117 3119 3121 3123 3125 3127 3129 3131 3132 3135 3136 3138 3140 3141 3143 3145 3147 3148 3149 3150 3151 3152 3153 3154 3155 3156 3157 3158 3159 3160 3161 3162 3164 3166 3167 3170317331743177 001

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# @A318/A319/A320/A321
SERVICE BULLETIN

MSN CONFIGURATION 3178 3180 3182 3183 3185 3187 3189 3190 3192 3194 3196 3197 3199 3201 3203 3205 3206 3208 3210 3211 3213 3215 3218 3219 3221 3223 3224 3227 3228 3230 3232 3234 3236 3237 3239 3240 3242 3244 3246 3256 3257 3259 3261 3263 3264 3266 3268 3270 3272 3273 3275 3277 3278 3280 3282 3284 3286 3287 3289 3291 3293 3295 3296 3299 3301 3303 3304 3306 3308 3310 3312 3313 3314 3316 3318 3319 3321 3323 3325 3327 3328 3330 3332 3335 3337 3338 3341 3343 3345 3348 3349 3351 3353 3354 3357 3359 3361 3362 3365 3366 3368 3370 3373 3374 3376 3378 3379 3381 3383 3384 3386 3389 3391 3392 3394 3396 3398 3400 3402 3404 3408 3409 3410 3412 3414 3416 3418 3420 3422 3423 3425 3427 3430 3431 3433 3435 3437 3439 3440 3444 3446 3448 3449 3451 3453 3455 3456 3457 3460 3461 3464 3465 3468 3470 3472 3473 3474 3475 3476 3477 3478 3479 3480 3481 3482 3483 3484 3485 3486 3487 3488 3489 3490 3492 3494 3495 3496 3497 3499 3501 3502 3503 3505 3506 3508 3510 3511 3514 3515 3516 3517 3519 3521 3524 3526 3528 3529 3531 3532 3535 3536 3538 3540 3541 3543 3545 3547 3549 3550 3553 3554 3556 3558 3559 3562 3563 3565 3567 3568 3570 3572 3574 3576 3577 3579 3581 3582 3591 3594 3596 3597 3598 3599 3601 3603 3605 3607 3609 3610 3611 3613 3616 3618 3621 3622 3624 3626 3627 3628 3630 3631 3640 3641 3643 3644 3646 3648 3649 3650 3652 3654 3656 3658 3659 3662 3664 3666 3667 3668 3670 3672 3674 3676 3677 3679 3690 3692 3693 3695 3696 3697 3698 3699 3701 3703 3706 3707 3709 3711 3713 3714 3715 3716 3718 3719 3721 3723 3724 3726 3729 3731 3732 3734 3736 3739 3741 3743 3745 3747 3748 3750 3753 3755 3756 3758 3760 3762 3765 3767 3769 3771 3773 3775 3776 3777 3778 3780 3781 3782 3783 3785 3786 3787 3789 3791 3793 3795 3797 3798 3800 3802 3804 3805 3807 3809 3811 3812 3813 3815 3817 3819 3821 3823 3825 3827 3829 3831 3833 3835 3837 3840 3843 3846 3848 3850 3852 3855 3857 3859 3861 3863 3866 3868 3870 3871 3873 3875 3877 3880 3882 3883 3885 3887 3889 3891 3894 3896 3898 3900 3902 3904 3906 3907 3908 3909 3910 3912 3913 3915 3917 3919 3921 3922 3923 3925 3927 3929 3931 3933 3935 3937 3939 3941 3943 3945 3946 3947 3949 3952 3953 3954 3956 3959 3961 3963 3965 3967 3968 3971 3972 3974 3975 3976 3978 3979 3980 3984 3986 3988 3990 3991 3992 3995 3997 3999 001

0776 0945 1337 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.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 14 6

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# @A318/A319/A320/A321
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(6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Consumable CMLD01 1 B. CONCURRENT REQUIREMENTS None C. REASON (1) History On A320 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 A320 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 :

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 15 6

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# @A318/A319/A320/A321
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**CONF 001 Task 551035-832-848-001: Inspection (1) Do the rudder special detailed inspection on aircraft with rudders which are affected by hot-curing rework outside autoclave in production **CONF 002 Task 551035-832-848-001: Inspection (1) Do 2 additional repetitive special detailed inspections (ELCH) **CONF ALL E. COMPLIANCE (1) Classification RECOMMENDED: Service Bulletin recommended to be accomplished to prevent significant operational disruptions. (2) Accomplishment Timescale **CONF 001 Table 1. Config. 001 - Rudder special detailed inspection on aircraft with rudders to be inspected on Area 1 (refer to Figure A-GAAAA, Sheet 10). Area to be inspected Condition Action Compliance time Repetitive interval
Area 1 N/A Identify the Serial Number of the installed rudder Within 200 days from SB Rev. 00 issue date N/A

Area 1 N/A Vacuum loss inspection in accordance with Subtask 551035-832-202-001At the latest of these 2 conditions: -Before the rudder reaches 17000 FC since new, without exceeding 20 months from SB Rev. 00 issue date OR, -Within 200 days from SB Rev. 00 issue date N/A

Area 1 Damage indications found during vacuum loss inspection Report to AIRBUS Before next flight N/A

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 16 6

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Area to be inspected Condition Action Compliance time Repetitive interval
Area 1 No damage indications found during vacuum loss inspection Temporary option 1: Close the vacuum loss inspection holes with adhesive tape Before next flight, if the temporary option 2 or the permanent restoration have not been accomplished N/A

Area 1 No damage indications found during vacuum loss inspection Temporary option 1: Do a detailed inspection of the restored area for loose or lost tape N/A At intervals not exceeding 750 FC or 100 days, whichever occurs first Area 1 Loose or lost tape found Temporary option 1: Close the vacuum loss inspection holes again with adhesive tape Before next flight, if the temporary option 2 or the permanent restoration have not been accomplished N/A

Area 1 No damage indications found during vacuum loss inspection Temporary option 1: Do the permanent restoration. Do a thermography or ultrasound inspection before the resin injection Within 4500 FC from the vacuum loss inspection N/A

Area 1 Damage indications found during thermography or ultrasound inspection Temporary option 1: Report to AIRBUS Before next flight N/A

Area 1 No damage indications found during vacuum loss inspection Temporary option 2: Close the vacuum loss inspection holes with resin and adhesive tape. Do a thermography or ultrasound inspection before the resin injection Before next flight, if the temporary option 1 or the permanent restoration have not been accomplished N/A

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 17 6

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# @A318/A319/A320/A321
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Area to be inspected Condition Action Compliance time Repetitive interval
Area 1 Damage indications found during thermography or ultrasound inspection Temporary option 2: Report to AIRBUS Before next flight N/A

Area 1 No damage indications found during thermography or ultrasound inspection Temporary option 2: Restore the surface protection Within 4500 FC from the vacuum loss inspection N/A

Area 1 No damage indications found during vacuum loss inspection Permanent restoration: Do a thermography or ultrasound inspection before the resin injection Before next flight after the vacuum loss inspection or within 4500 FC after the vacuum loss inspection, if the temporary option 1 has been accomplished. N/A

Area 1 Damage indications found during thermography or ultrasound inspection Permanent restoration: Report to AIRBUS Before next flight N/A

Area 1 No damage indications found during thermography or ultrasound inspection No further action after accomplishment of the permanent restoration N/A N/A

Table 2. Config. 001 - Rudder special detailed inspection on aircraft with rudders to be inspected on Area 2 (refer to Figure A-GAAAA, Sheet 10). Area to be inspected Condition Action Compliance time Repetitive interval
Area 2 N/A Identify the Serial Number of the installed rudder Within 20 months from SB Rev. 00 issue date N/A

Area 2 N/A ELCH inspection in accordance with Subtask 551035-832-202-001Within 20 months from Rev. 00 issue date N/A

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 18 6

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# @A318/A319/A320/A321
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Area to be inspected Condition Action Compliance time Repetitive interval
Area 2 Damage indications found during ELCH inspection Re-examine the damage indications as per tap test inspection and report to AIRBUS Before next flight N/A

Area 2 No damage indications found during ELCH inspection Report to AIRBUS Within 10 days from the 1. ELCH inspection N/A

Area 2 No damage indications found during ELCH inspection Do 2 additional repetitive ELCH inspections N/A ELCH inspection within intervals between 4000 and 4500 FC from previous inspection Area 2 Damage indications found during the 1. or 2. additional repetitive ELCH inspection Re-examine the damage indications as per tap test inspection and report to AIRBUS Before next flight N/A

Area 2 No damage indications found during the 2 additional repetitive ELCH inspections Report to AIRBUS after each ELCH inspection No further action Report within 10 days from the ELCH inspection N/A

Table 3. Config. 001 - Rudder special detailed inspection on aircraft with rudders to be inspected on Area 3 (refer to Figure A-GAAAA, Sheet 10). Area to be inspected Condition Action Compliance time Repetitive interval
Area 3 N/A Identify the Serial Number of the installed rudder Within 200 days from Rev. 00 issue date N/A

Area 3 N/A ELCH inspection in accordance with Subtask 551035-832-202-001At the latest of these 2 conditions: -Before the rudder reaches 17000 FC since new, without exceeding 20 months from SB Rev. 00 issue date OR, -Within 200 days from SB Rev. 00 issue date N/A

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 19 6

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Area to be inspected Condition Action Compliance time Repetitive interval
Area 3 Damage indications found during ELCH inspection Re-examine the damage indications as per tap test inspection and report to AIRBUS Before next flight N/A

Area 3 No damage indications found during ELCH inspection Report to AIRBUS Within 10 days from the ELCH inspection N/A

Area 3 No damage indications found during ELCH inspection Do repetitive ELCH inspections N/A ELCH inspections within intervals of 200 days/ 1500FC from previous inspection until vacuum loss inspection is performed Area 3 No damage indications found during ELCH inspections Report to AIRBUS Within 10 days from each ELCH inspection N/A

Area 3 N/A Vacuum loss inspection in accordance with Subtask 551035-832-202-001Within 20 months from SB Rev. 00 issue date N/A

Area 3 Damage indications found during vacuum loss inspection Report to AIRBUS Before next flight N/A

Area 3 No damage indications found during vacuum loss inspection Temporary option 1: Close the vacuum loss inspection holes with adhesive tape Before next flight, if the temporary option 2 or the permanent restoration have not been accomplished N/A

Area 3 No damage indications found during vacuum loss inspection Temporary option 1: Do a detailed inspection of the restored area for loose or lost tape N/A At intervals not exceeding 750 FC or 100 days, whichever occurs first

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 20 6

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Area to be inspected Condition Action Compliance time Repetitive interval
Area 3 Loose or lost tape found Temporary option 1: Close the vacuum loss inspection holes again with adhesive tape Before next flight, if the temporary option 2 or the permanent restoration have not been accomplished N/A

Area 3 No damage indications found during vacuum loss inspection Temporary option 1: Do the permanent restoration. Do a thermography or ultrasound inspection before the resin injection Within 4500 FC from the vacuum loss inspection N/A

Area 3 Damage indications found during thermography or ultrasound inspection Temporary option 1: Report to AIRBUS Before next flight N/A

Area 3 No damage indications found during vacuum loss inspection Temporary option 2: Close the vacuum loss inspection holes with resin and adhesive tape. Do a thermography or ultrasound inspection before the resin injection Before next flight, if the temporary option 1 or the permanent restoration have not been accomplished N/A

Area 3 Damage indications found during thermography or ultrasound inspection Temporary option 2: Report to AIRBUS Before next flight N/A

Area 3 No damage indications found during thermography or ultrasound inspection Temporary option 2: Restore the surface protection Within 4500 FC from the vacuum loss inspection N/A

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 21 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

Area to be inspected Condition Action Compliance time Repetitive interval
Area 3 No damage indications found during vacuum loss inspection Permanent restoration. Do a thermography or ultrasound inspection before the resin injection Before next flight after the vacuum loss inspection or within 4500 FC from the vacuum loss inspection, if the temporary option 1 has been accomplished. N/A

Area 3 Damage indications found during thermography or ultrasound inspection Permanent restoration: Report to AIRBUS Before next flight N/A

Area 3 No damage indications found during thermography or ultrasound inspection No further action after accomplishment of the permanent restoration N/A N/A

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 inspected Condition Action Compliance time Repetitive interval
Area 2 N/A Identify the Serial Number of the installed rudder. Within 4000 FC from the 1. sampling inspection N/A

Area 2 No damage indications found during sampling (1. ELCH inspection) 2 additional repetitive ELCH inspections in accordance with subtask 551035-832-203-001N/A Within intervals between 4000 and 4500 FC from the 1. sampling inspection

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 22 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

Area 2 Damage indications found during the 1. or 2. additional repetitive ELCH inspection Re-examine the damage indications as per tap test inspection and report to AIRBUS Before next flight N/A

Area 2 No damage indications found during the 2 additional repetitive ELCH inspections Report to AIRBUS after each ELCH inspection No further action Report within 10 days from the ELCH inspection N/A

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 underEASA Design Organization ApprovalNo. EASA21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. **CONF 001 Task 551035-832-848-001: Inspection Get Access 1.00 On Aircraft Do the rudder special detailed inspection on aircraft with rudders which are affected by hot-curing rework outside autoclave in production 0

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:

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 23 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

Steps Manhours Elapsed time Number of persons Get access 1.00 0.75 2 Rudder SN identification 0.25 0.25 1
Vacuum loss inspection 2.00 1.50 2 Thermography inspection 0.25 0.25 2
Ultrasound inspection 0.25 0.25 1 ELCH inspection 0.75 0.75 1 tap test inspection 0.25 0.25 1 Close-up 1.00 0.75 2 **CONF 002 Task 551035-832-848-001: Inspection Get Access 1.00 On Aircraft Do 2 additional repetitive special detailed inspections (ELCH) 0 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 1 tap test inspection 0.25 0.25 1 Close-up 1.00 0.75 2 **CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 24 6

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# @A318/A319/A320/A321
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J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-41-55 12-34-24 29-10-00 55-33-13 55-40-00 Consumable Material List (CML) Non Destructive Test Manual (NTM) 51-10-03 51-10-19 51-10-24 51-10-25 51-10-26 51-10-28 Structural Repair Manual (SRM) 51-75-12 51-77-10 51-77-11 **CONF 002 Aircraft Maintenance Manual (AMM) 06-41-55 12-34-24 29-10-00 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

Maintenance Planning Document (MPD) 55-40-10 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 25 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 26 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses None This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign. (2) Price and Availability None B. INDUSTRY SUPPORT INFORMATION 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 ITEMDESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE 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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 27 6

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# @A318/A319/A320/A321
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(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 Checker Kit MBBBT100 51-10-26
Vacuum loss Vacuum cup TL3AMB1420T38L 51-10-28 Thermography Thermography kits 99A55407320000 (Camera and monitor) and 99A55407321000 (complementary tooling including hot air blower) 51-10-25

Ultrasound US-equipment EPOCH4PLUS and search unit K1SM and reference block MBBGCFRPHC200 and cable PKLL2 51-10-24

tap test tap test inspection tool 98A57103013000 or 99A55209001000 51-10-03

tap test Function test block and Woodpecker 99A55407291000 and WP632 or WP632AM 51-10-19

For more detailed information, refer to the related NTM chapter. (3) Special Tools None

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 28 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS Task 551035-832-848-001 - 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 551035-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 29 6

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# @A318/A319/A320/A321
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Material necessary to do the job
Consumable CMLD01 ITEMDESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE 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). (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 Purpose 11-026 As required

and Lint-Free Cotton Cloth 19-003 As required
(2) Subtask 551035-839-201-001 - 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 551035-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job
Consumable CMLD01 ITEMDESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 30 6

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# @A318/A319/A320/A321
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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 Purpose 11-026 As required

and Lint-Free Cotton Cloth 19-003 As required
(2) Subtask 551035-839-201-001 - 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 ALL B. PREPARATION **CONF 001 (1) Subtask 551035-941-201-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002 Task 29-10-00-864-001 Task 29-10-00-864-002 Task 29-10-00-864-003 Task 55-33-13-010-002 Task 55-40-00-210-001 (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-869-002).

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 31 6

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# @A318/A319/A320/A321
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(b) If an aircraft MSN is listed in the rudder SN-MSN reference list, check the documentation for further repairs on the rudder during service. The check of the documentation is to be done in the areas to be inspected (affected by production reworks), indicated in the individual Technical Disposition (MSN/rudder SN listed in the reference list). If you find documents about repairs, contact AIRBUS for further instructions. (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. (j) To open the access panels, (Refer to AMM Task 55-33-13-010-002). **CONF 002 (1) Subtask 551035-941-201-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002 Task 29-10-00-864-001 Task 29-10-00-864-002 Task 29-10-00-864-003 Task 55-33-13-010-002 Task 55-40-00-210-001 (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-869-002). (b) If an aircraft MSN is listed in the rudder SN-MSN reference list, check the documentation for further repairs on the rudder during service. The check of the documentation is to be done in the areas to be inspected (affected by production reworks), indicated in the individual Technical Disposition (MSN/rudder SN listed in the reference list). If you find documents about repairs, contact AIRBUS for further instructions. (c) In the cockpit, put warning notices in position to tell persons not to operate the flight controls.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 32 6

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(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. (j) To open the access panels, (Refer to AMM Task 55-33-13-010-002). **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 551035-832-202-001 - Do therudder special detailed inspection on aircraft with rudders which are affected by hot-curing rework outside autoclave in production Manpower Resources Manhours 0 Minimum number of person 0 Subtask elapsed time 0 Skills NON DESTRUCTIVE TESTING Material necessary to do the job
Consumable CMLD01 ITEMDESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Self-Adhes. Disks 05-052 As required Self Adhesive Aluminium Tape 08-052 As required Solvent General Purpose 11-026 As required Wet Lay Up Resin 20-022 As required

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 33 6

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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 51-77-10 Para 5. 51-77-11 Para 4.M.(2) 51-77-11 Para 4.A.(3) 51-77-11 Para 4.E 51-77-11 Para5.D.(1).(i) 51-77-11 Figure 14 Fig. A-GAAAA Rudder inspection Sheet 01 - Flow Chart 1, vacuum loss inspection area 1 and 3 Sheet 02 -Vacuum loss inspection - damage assessment Sheet 03 - Flow Chart 2, ELCH inspection area 2 Sheet 04 - Reporting sheet Sheet 05 - Rudder SN identification Sheet 09 - Typical ELCH procedure Sheet 10 - Inspection areas Sheet 11 - Flow Chart 3, ELCH inspection area 3 Sheet 13 - Rudder skin thickness LH Sheet 14 - Rudder skin thickness RH Sheet 15 -Overview of the compliance times Fig. A-GACAA Rudder SN - MSN reference List Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 Sheet 11 Sheet 12 Sheet 13 Sheet 14 Sheet 15 Sheet 16 Sheet 17 Sheet 18 Sheet 23 Sheet 24
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NOTE: For a general overview of the compliance times, refer to the Flow Chart Fig. A-GAAAA Sheet 15

. (a) Identify the Serial Number (SN) of the rudder as shown onFig. A-GAAAA Sheet 05

. (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-GACAA Sheet 01thruFig. A-GACAA Sheet 24

. NOTE: The rudder SN-MSN relationship is provided for information only and is based on the information available at AIRBUS at time of SB issue. Any changes resulting from movement from an aircraft to another or from spare is not reflected, it is the responsibility of the operator to assess the rudder SN-MSN relationship.
1 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. 3 If the rudder 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. 1 For the definition of the areas to be inspected, refer to the rudder SN - MSN reference listFig. A-GACAA Sheet 01thruFig. A-GACAA Sheet 24to find the MSN related Technical Disposition (TD) No.
2 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-S2-XXXXX’. For additional information, refer to SBIT SEMB 914.0808/09 3 Inspection method for reworked areas: - For reworked area astride AREA 2 and AREA 3, if TD provides vacuum loss hole location then rework must be treated as if in AREA 3 only. - For reworked area astride AREA 2 and AREA 3, if TD does not provide vacuum loss hole location then rework must be treated as if in AREA 2 only. - For reworked area astride AREA 1 and AREA 3, the rework must be treated as if in AREA 1 only.

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(e) If there are only areas on the trailing edge shown as ’AREA 2’ on theFig. AGAAAA Sheet 10, to be inspected, refer to Para (h). (f) If there are only other areas, shown as ’AREA 3’ on theFig. A-GAAAA Sheet 10, to be inspected, refer to Para (i). (g) If there are reinforced areas, shown as ’AREA 1’ on theFig. A-GAAAA Sheet 10, to be inspected, do the subsequent inspection in accordance with the Flow ChartFig. A-GAAAA Sheet 01andFig. A-GAAAA Sheet 02: 1 Do the vacuum loss inspection (Refer toNTM Task 51-10-28-220-801).

a Temporarily install adhesive tape (Material No 08-052 - basic) on the areas to be inspected. b Mark the grid of holes on the adhesive tape.

c CAUTION: DRILL PENETRATION INTO THE SANDWICH STRUCTURE HAS TO BE LIMITED TO 20 mm (0.8 in.) TO PREVENT INNER SKIN DAMAGE. Drill the vacuum loss 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).

e In case of damage indications, contact AIRBUS on the basis of a detailed referenced damage report for further instructions before next flight. f In case of no damage indications, close the vacuum loss inspection holes as detailed in the subsequent instructions and report the result to AIRBUS within 10 days.
2 Temporary restoration of the vacuum loss inspection hole option 1:

a Close the holes with Self Adhesive Aluminium Tape 08-052 As required

or Self-Adhes. Disks 05-052 As required b Do a detailed inspection of the restored area within every 750 FC or 100 days, whichever occurs first. Inspect the restored area for loose or lost adhesive disks or tape.

c In case of loose or lost tape ordisks, close theholes again with Self Adhesive Aluminium Tape 08-052 As required

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 36 6

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or Self-Adhes. Disks 05-052 As required d This temporary restoration must be replaced by the permanent restoration after 4500 FC latest. 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 vacuum loss inspection hole option 2:

a Before the resin injection: <1> Identify the skin thickness of the areas to be inspected, refer toFig. A-GAAAA Sheet 13andFig. A-GAAAA Sheet 14

. <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 loss inspection holes must be closed with thin adhesive tape (Material No 08-052 - basic) to prevent couplant ingress into the holes. b In case of damage indications contact AIRBUS for further instructions before next flight.

c 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
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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). 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 vacuum loss inspection hole.
g Close the filled holes with Self Adhesive Aluminium Tape 08-052 As required

or Self-Adhes. Disks 05-052 As required h Let the resin cure for a minimum of 6 hours at room temperature. If the room temperature is below 18 ̊C (64F), extend the curing time and perform a gelation test outside the restoration area. After resin gelation plus 2 h, the aircraft can be released to operations again. OR Cure the resin at 60 ̊C (140F) for 45 minutes. Install a heating blanket with a vacuum bag on the rudder surface (Refer to SRM 51-77-11 Para 5.D.(1).(i)), and control the temperature by means of thermocouples (Refer to SRM 51-77-11 Figure 14). i Within the next 4500 FC, do the final surface restoration: <1> Remove the self adhesive tape from the restoration areas. <2> Inspect the restoration (Refer to SRM 51-77-10 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 Purpose 11-026 As required
(Refer to SRM 51-77-11 Para 4.E). <5> Restore the surface protection (Refer toSRM 51-75-12).

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 38 6

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4 Permanent restoration of the vacuum loss inspection holes:

a Before the resin injection: <1> Identify the skin thickness of the areas to be inspected, refer toFig. A-GAAAA Sheet 13andFig. A-GAAAA Sheet 14

. <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 loss inspection holes must be closed with thin adhesive tape (Material No 08-052 - basic) to prevent couplant ingress into the holes. b In case of damage indications contact AIRBUS for further instructions before next flight.

c 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 refer to the appropriate data sheet before mixing the chosen material.

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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 vacuum loss inspection hole.
g Close the filled holes with a self adhesive tape. h Let the resin cure for a minimum of 12 hours at room temperature. If the room temperature is below 18 ̊C (64F), extend the curing time and perform a gelation test outside the restoration area. After resin gelation plus 4 h, continue with the subsequent steps: <1> Remove the self adhesive tape from the restoration areas. <2> Inspect the restoration (Refer to SRM 51-77-10 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 Purpose 11-026 As required
(Refer to SRM 51-77-11 Para 4.E). <5> Restore the surface protection (Refer to SRM 51-75-12). (h) If there are areas on the trailing edge, shown as ’AREA 2’ on theFig. A-GAAAA Sheet 10, to be inspected, do a repetitive special detailed inspection (ELCH) in accordance with the Flow ChartFig. A-GAAAA Sheet 03: 1 Do the ELCH inspection (refer toNTM 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 09, View K and View L, 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.

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b 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 onFig. A-GAAAA Sheet 09, View K and View L, area 3. <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.
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), contact AIRBUS for further instructions before next flight. 3 In case of no damage indications, report to AIRBUS within 10 days and do 2 additional ELCH inspections at intervals not exceeding 4500 FC and not less than 4000 FC from the last inspection, refer toFig. A-GAAAA Sheet 03

.
a In case of damage indications during the additional ELCH inspection, reexamine 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. b In case of no damage indications during the additional ELCH inspections, report to AIRBUS within 10 days. (i) If there are other areas, shown as ’AREA 3’ on theFig. A-GAAAA Sheet 10, to be inspected, do a repetitive special detailed inspection (ELCH) in accordance with the Flow ChartFig. A-GAAAA Sheet 11within 200 days after the issue of the Rev. 00 of this Service Bulletin, and do the vacuum loss inspection within 20 months after the issue of the Rev. 00 of this Service Bulletin. For the vacuum loss inspection, refer to Para (j). NOTE: The ELCH inspection is not required if the vacuum loss inspection is done within 200 days after the issue of the Rev. 00 of this Service Bulletin.
1 To do the ELCH inspection, refer to NTM Task 51-10-26-220-801.

a For the inspection in front of the fasteners, use up to 3 grid lines with a distance of 50 mm (1.97 in.) between the inspection points, as shown on Fig. A-GAAAA Sheet 09, View K and View L, area 3. <1> The assessment criteria for the ELCH inspection in front of the fasteners are: Yellow value 0.25 mm (0.010 in.) Red value 0.35 mm (0.014 in.) DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 41 6

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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. 3 In case of no damage indications, report to AIRBUS within 10 days and do repetitive ELCH inspections at intervals not exceeding 1500 FC or 200 days, whichever occurs first, until the vacuum loss inspection is performed.

a In case of damage indications during the repetitive ELCH inspections, reexamine the findings as per tap test inspection (Refer to NTM Task 51-10-03-280-801 or NTM Task 51-10-19-280-801), contact AIRBUS for further instructions before next flight. b In case of no damage indications during the repetitive ELCH inspections, report to AIRBUS within 10 days. (j) Do the vacuum loss inspection in accordance with the Flow ChartFig. A-GAAAA Sheet 01andFig. A-GAAAA Sheet 02: 1 To do the vacuum loss inspection 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. b Mark the grid of holes on the adhesive tape.

c CAUTION: DRILL PENETRATION INTO THE SANDWICH STRUCTURE HAS TO BE LIMITED TO 20 mm (0.8 in.) TO PREVENT INNER SKIN DAMAGE. Drill the vacuum loss 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).

e In case of damage indications, contact AIRBUS on the basis of a detailed referenced damage report for further instructions before next flight. f In case of no damage indications, close the vacuum loss inspection holes as detailed in the subsequent instructions and report the result to AIRBUS within 10 days.

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2 Temporary restoration of the vacuum loss inspection hole option 1:

a Close the holes with Self Adhesive Aluminium Tape 08-052 As required

or Self-Adhes. Disks 05-052 As required b Do a detailed inspection of the restored area within every 750 FC or 100 days, whichever occurs first. Inspect the restored area for loose or lost adhesive disks or tape.

c In case of loose or lost tape ordisks, close theholes again with Self Adhesive Aluminium Tape 08-052 As required

or Self-Adhes. Disks 05-052 As required d This temporary restoration must be replaced by the permanent restoration after 4500 FC latest. 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 vacuum loss inspection hole option 2:

a Before the resin injection: <1> Identify the skin thickness of the areas to be inspected, refer toFig. A-GAAAA Sheet 13andFig. A-GAAAA Sheet 14

. <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

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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 loss inspection holes must be closed with thin adhesive tape (Material No 08-052 - basic) to prevent couplant ingress into the holes. b In case of damage indications contact AIRBUS for further instructions before next flight.

c 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 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). 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 vacuum loss inspection hole.
g Close the filled holes with Self Adhesive Aluminium Tape 08-052 As required

or Self-Adhes. Disks 05-052 As required h Let the resin cure for a minimum of 6 hours at room temperature. If the room temperature is below 18 ̊C (64F), extend the curing time and perform a gelation test outside the restoration area. After resin gelation plus 2 h, the aircraft can be released to operations again. OR

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Cure the resin at 60 ̊C (140F) for 45 minutes. Install a heating blanket with a vacuum bag on the rudder surface (Refer to SRM 51-77-11 Para 5.D.(1).(i)), and control the temperature by means of thermocouples (Refer to SRM 51-77-11 Figure 14). i Within the next 4500 FC, do the final surface restoration: <1> Remove the self adhesive tape from the restoration areas. <2> Inspect the restoration (Refer to SRM 51-77-10 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 Purpose 11-026 As required
(Refer to SRM 51-77-11 Para 4.E). <5> Restore the surface protection (Refer toSRM 51-75-12).
4 Permanent vacuum loss inspection hole restoration:

a Before the resin injection: <1> Identify the skin thickness of the areas to be inspected, refer toFig. A-GAAAA Sheet 13andFig. A-GAAAA Sheet 14

. <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 loss inspection holes must be closed with thin adhesive tape (Material No 08-052 - basic) to prevent couplant ingress into the holes. b In case of damage indications contact AIRBUS for further instructions before next flight.

c

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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 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). 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 vacuum loss inspection hole.
g Close the filled holes with a self adhesive tape. h Let the resin cure for a minimum of 12 hours at room temperature. If the room temperature is below 18 ̊C (64F), extend the curing time and perform a gelation test outside the restoration area. After resin gelation plus 4 h, continue with the subsequent steps: <1> Remove the self adhesive tape from the restoration areas. <2> Inspect the restoration (Refer to SRM 51-77-10 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 Purpose 11-026 As required
(Refer to SRM 51-77-11 Para 4.E).
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<5> Restore the surface protection (Refer to SRM 51-75-12). (k) Fill in the reporting sheet, refer toFig. A-GAAAA 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 002 (1) Subtask 551035-832-203-001 - Do 2 additional repetitive special detailed inspections (ELCH) Manpower Resources Manhours 0 Minimum number of person 0 Subtask elapsed time 0 Skills NON DESTRUCTIVE TESTING

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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 Rudder SN - MSN reference List Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 Sheet 11 Sheet 12 Sheet 13 Sheet 14 Sheet 15 Sheet 16 Sheet 17 Sheet 18 Sheet 23 Sheet 24 Fig. A-GAEAA ELCH inspection Sheet 01 - Inspection areas Sheet 02 - Flow Chart Sheet 03 - Typical ELCH procedure Sheet 04 - Reporting sheet Sheet 05 - Rudder SN identification Sheet 06 -Overview of the compliance time NOTE: For a general overview of the compliance times, refer to the Flow Chart Fig. A-GAEAA Sheet 06

. (a) Identify the Serial Number (SN) of the rudder as shown onFig. A-GAEAA Sheet 05

. (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-GACAA Sheet 01thruFig. A-GACAA Sheet 24

. NOTE: The rudder SN-MSN relationship is provided for information only and is based on the information available at AIRBUS at time of SB issue. Any changes resulting from movement from an aircraft to another or from spare is not reflected, it is the responsibility of the operator to assess the rudder SN-MSN relationship.
1 If you find a different SN against the MSN as detailed in the rudder SN - MSN reference list, contact AIRBUS for further instructions.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 48 6

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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. 3 If the rudder is part of the SN - MSN reference list with the same indicated MSN, continue with the below instructions. (d) For the areas on the trailing edge, shown as ’AREA 2’ on theFig. 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 rudder SN - MSN reference listFig. A-GACAA Sheet 01thruFig. A-GACAA Sheet 24 to find the MSN related Technical Disposition (TD) No. b 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-S2-XXXXX’. For additional information, refer to SBIT SEMB 914.0808/09
2 Do the ELCH inspection in accordance with the Flow ChartFig. A-GAEAA Sheet 02at intervals not exceeding 4500 FC and not less than 4000 FC after the first sampling inspection (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-GAEAA Sheet 03, View A, 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. b 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 onFig. A-GAEAA Sheet 03, View A, area 3. <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. DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 49 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

3 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.
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 toFig. 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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 50 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF 002 None **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 551035-942-201-001 - 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 Task 55-33-13-410-002 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 Task 55-33-13-410-002). (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 551035-942-201-001 - 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 Task 55-33-13-410-002 Task 55-40-00-210-001
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 51 6

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# @A318/A319/A320/A321
SERVICE BULLETIN
(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 Task 55-33-13-410-002). (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.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 52 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF 001

INDICATION FOUND

CLOSE INSPECTION HOLES NO YES
REPORT TO AIRBUS

TO GET FURTHER

INSTRUCTIONS BEFORE NEXT FLIGHT IDENTIFY THE RUDDER SERIAL NUMBER VIA THE PLACARD ON THE RUDDER SPAR. IN CASE OF NO EXISTING PLACARD CONTACT AIRBUS

AND REPORT TO AIRBUS WITHIN 10 DAYS

AIRBUS INSTRUCTIONS

TO BE CARRIED OUT BEFORE NEXT FLIGHT

NO FURTHER ACTION REQUIRED IN AREA 1 AND 3 TEMPORARY OPTION II PERMANENT RESTORATION THERMOGRAPHY INSPECTION TEMPORARY OPTION I FREQUENT DETAILED INSPECTION OF RESTORED NOT EXCEEDING 750 FC / 100 DAYS

PERMANENT RESTORATION THERMOGRAPHY INSPECTION AS PER NTM 51−10−25

CONTACT AIRBUS BEFORE FURTHER FLIGHT

IN CASE OF FINDINGS. WITHIN 4500 FC

WITHIN 4500 FC AREA, AT INTERVALS

REQUIRED BEFORE RESIN INJECTION. THERMOGRAPHY INSPECTION

RESTORE FINAL

PROTECTION OR COMPARE YOUR RUDDER SERIAL NUMBER WITH THE RUDDER SERIAL NUMBERS IN THE REFERENCE LIST

NO YES DO THE SPECIAL DETAILED INSPECTION (VACUUM LOSS) AS PER NTM 51−10−28 IN AREAS DEFINED IN SPECIFIC TECHNICAL DISPOSITION FOR EACH RUDDER NO FURTHER ACTION REQUIRED IN ACCORDANCE WITH THIS INSPECTION SB SERIAL NUMBER FOUND IN REFERENCE LIST

ULTRASOUND INSPECTION

AS PER NTM 51−10−24 AND/OR AS PER NTM 51−10−25

CONTACT AIRBUS BEFORE FURTHER FLIGHT

IN CASE OF FINDINGS. REQUIRED BEFORE RESIN INJECTION. ULTRASOUND INSPECTION

AS PER NTM 51−10−24 AND/OR AS PER NTM 51−10−25

CONTACT AIRBUS BEFORE FURTHER FLIGHT

IN CASE OF FINDINGS. REQUIRED BEFORE RESIN INJECTION. ULTRASOUND INSPECTION

AS PER NTM 51−10−24 AND/OR

NOTE: FOR THE ACCOMPLISHMENT TIMESCALE. REFER TO PARA 1.E.(2) N_SB_551035_6_AAAA_01_10 

## Figure A-GAAAA - Sheet 01 Rudder inspection - Flow Chart 1, vacuum loss inspection area 1 and 3

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 53 6

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# @A318/A319/A320/A321
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. 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.

OVERALL LENGTH

OVERALL

WIDTH25.0mm (0.98in.)

ADD−ON INSPECTION 1 ADD−ON INSPECTION 2 ADD−ON INSPECTION 3 BASIC INSPECTION RESULTSDIRECTION OFADD−ON INSPECTIONRESTRICTED AREA



### OVERALL DAMAGE SIZE DEBONDING

DEBONDING AREA
HOLES TO BE INSPECTED IN CASE OF FINDINGS. RESULTS OF VACUUM LOSS INSPECTION NO LEAKAGE LEAKAGE DETECTED WARNING: DRILLING IN THE RESTRICTED AREA CAN DAMAGE THE INNER SKIN AND IS NOT ALLOWED. **NOTE:**FOR THE INSPECTIONS A NORMAL PAINT CONDITION AND AN ADEQUATE FLAT SURFACE IS EXPECTED. IF INTENSIVE PAINT CRACKING OR SURFACE WAVINESS IS PRESENT A LOCAL SURFACE POLISHING BY SANDING IS ADVISABLE. FOR THE SANDING OPERATION USE CLOTH 280 OR 400 GRADE. BY THE SANDING OPERATION NEITHER THE SURFACE PRIMER NOR THE OUTER FABRIC LAYER MUST BE DAMAGED.

N_SB_551035_6_AAAA_02_07 

## Figure A-GAAAA - Sheet 02 Rudder inspection - Vacuum loss inspection - damage assessment

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 54 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF 001
IDENTIFY THE RUDDER SERIAL NUMBER VIA THE PLACARD ON THE RUDDER SPAR. IN CASE OF NO EXISTING PLACARD CONTACT AIRBUS

INDICATION

FOUND NO YES

REPORT TO AIRBUS WITHIN 10 DAYS

REPORT TO AIRBUS

TO GET FURTHER

INSTRUCTIONS BEFORE NEXT FLIGHT RE−EXAMINE THE FINDINGS AS PER TAP TEST INSPECTION NTM 51−10−03 OR NTM 51−10−19 AND

INDICATION

FOUND NO YES

NO FURTHER ACTION REQUIRED IN AREA 2 AIRBUS INSTRUCTIONS TO BE CARRIED OUT BEFORE NEXT FLIGHT DO 2 ADDITIONAL ELCH INSPECTIONS AT INTERVALS NOT EXCEEDING 4500FC AND NOT LESS THAN 4000 FC

REPORT TO AIRBUS WITHIN 10 DAYS NO

YES NO FURTHER ACTION REQUIRED IN ACCORDANCE WITH THIS INSPECTION SB SERIAL NUMBER FOUND IN REFERENCE LIST

FOR EACH RUDDER DO THE REPETITIVE SPECIAL DETAILED INSPECTION (ELCH) AS PER NTM 51−10−26 IN AREAS DEFINED IN SPECIFIC TECHNICAL DISPOSITION

NOTE: FOR THE ACCOMPLISHMENT TIMESCALE. REFER TO PARA 1.E.(2) N_SB_551035_6_AAAA_03_13 

## Figure A-GAAAA - Sheet 03 Rudder inspection - Flow Chart 2, ELCH inspection area 2

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 55 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF 001



# Inspection Report
**Rudder Surface Inspection as per SB in area:**

Aircraft type: MSN: Rudder S/N: Rudder P/N: Inspection date: Operator: FC:
FH:

Inspection method Tap Test

Thermography

ELCH Inspection

Vacuum Loss Inspection

Inspection

Inspection UT Inspection No findings Findings as detailed by sketch and photos

No findings Findings as detailed by sketch and photos

No findings Findings as detailed by sketch and photos

No findings Findings as detailed by sketch and photos

No findings Findings as detailed by sketch and photos LH RH Rudder Side

N_SB_551035_6_AAAA_04_03 

### * use sketch from the TD



## Figure A-GAAAA - Sheet 04 Rudder inspection - Reporting sheet

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 56 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF 001

325EL

325DL

325CL

325BL

325ER

325DR

325CR

325BR Z325 

# B

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. POSITION OF RUDDER S/N PLACARD AT MSN: 0529, 0532 AND

0537 − 9999 

# C

POSITION OF RUDDER S/N PLACARD AT MSN: 0001 − 0528, 0530 − 0531, 0533 − 0536



# C **A**

**E**

**D K** 

MFR DESCR. SER. N ° CA CODE MFG DATE A/C PNNSA9117−63D 

# A

N_SB_551035_6_AAAA_05_03 

# B

D5547100XXXXX
TS−XXXX



## Figure A-GAAAA - Sheet 05 Rudder inspection - Rudder SN identification

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 57 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF 001

TYPICAL TRAILING EDGE ELCH INSPECTION FASTENERS



# AREA 3 AREA 2

**K**

75.0 mm (2.95 in) 50.0 mm (1.97 in)

75.0 mm (2.95 in) 50.0 mm (1.97 in) 50.0 mm (1.97 in) AREA 2 AREA 3

MINIMUM DISTANCE FROM EDGE 75.0mm (2.95in.) **NOTE:** 

# L



# AREA 1 REINFORCED AREA



# L

N_SB_551035_6_AAAA_09_04 

## Figure A-GAAAA - Sheet 09 Rudder inspection - Typical ELCH procedure

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 58 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF 001

N_SB_551035_6_AAAA_10_01 

# AREA 3

AREA 2

AREA 1

260.0 mm (10.24 in) 110.0 mm (4.33 in)

(50.0 mm) (1.97 in)

297.0 mm (11.69 in) 110.0 mm (4.33 in) OTHER AREAS

TRAILING EDGE AREA

REINFORCED AREA



## Figure A-GAAAA - Sheet 10 Rudder inspection - Inspection areas

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 59 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF 001

IDENTIFY THE RUDDER SERIAL NUMBER VIA THE PLACARD ON THE RUDDER SPAR. IN CASE OF NO EXISTING PLACARD CONTACT AIRBUS

REPORT TO AIRBUS WITHIN 10 DAYS DO REPETITIVE ELCH INSPECTIONS

AT INTERVALS NOT EXCEEDING 200 DAYS / 1500 FC UNTIL VACUUM LOSS INSPECTION IS PERFORMED INDICATION

FOUND NO YES

REPORT TO AIRBUS

TO GET FURTHER

INSTRUCTIONS BEFORE NEXT FLIGHT RE−EXAMINE THE FINDINGS AS PER TAP TEST INSPECTION NTM 51−10−03 OR NTM 51−10−19 AND

INDICATION

FOUND NO YES

NO FURTHER ACTION REQUIRED IN AREA 3 AIRBUS INSTRUCTIONS TO BE CARRIED OUT BEFORE NEXT FLIGHT NO

YES NO FURTHER ACTION REQUIRED IN ACCORDANCE WITH THIS INSPECTION SB SERIAL NUMBER FOUND IN REFERENCE LIST

FOR EACH RUDDER IN AREAS DEFINED IN SPECIFIC TECHNICAL DISPOSITION

NOTE: FOR THE ACCOMPLISHMENT TIMESCALE. REFER TO PARA 1.E.(2) DO THE REPETITIVE SPECIAL DETAILED INSPECTION (ELCH) AS PER NTM 51−10−26

N_SB_551035_6_AAAA_11_05 

## Figure A-GAAAA - Sheet 11 Rudder inspection - Flow Chart 3, ELCH inspection area 3

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 60 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF 001

N_SB_551035_6_AAAA_13_01 

## Figure A-GAAAA - Sheet 13 Rudder inspection - Rudder skin thickness LH

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 61 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF 001

N_SB_551035_6_AAAA_14_02 

## Figure A-GAAAA - Sheet 14 Rudder inspection - Rudder skin thickness RH

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 62 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF 001



# AREA 1 (REINFORCED AREA)

AT THE LATEST OF THESE TWO CONDITIONS: − BEFORE THE RUDDER REACHES 17000 FC SINCE NEW, WITHOUT EXCEEDING 20 MONTHS FROM ISB REV.00 ISSUE DATE. OR − WITHIN 200 DAYS FROM ISB REV.00 ISSUE DATE. 

# AREA 2 (TRAILING EDGE AREA)

WITHIN 20 MONTH FROM ISB REV.00 ISSUE DATE 

# AREA 3 (OTHER AREAS)

WITHIN 20 MONTH FROM ISB REV.00 ISSUE DATE

APPLY ACTIONS ACCORDING FLOW CHART SHOWN ON FIG. A−GAAAA, SHEET 01
ACCOMPLISHMENT OF THE ACTIONS ACCORDING FLOW CHART SHOWN ON FIG. A−GAAAA, SHEET 01, CANCELS THE INITIAL OR REPETITIVE ACTIONS AS PER FLOW CHART SHOWN ON FIG. A−GAAAA, SHEET 11. AND

APPLY ACTIONS ACCORDING FLOW CHART SHOWN ON FIG. A−GAAAA, SHEET 03 APPLY ACTIONS ACCORDING FLOW CHART SHOWN ON FIG. A−GAAAA, SHEET 01 APPLY ACTIONS ACCORDING FLOW CHART SHOWN ON FIG. A−GAAAA, SHEET 11 NOTE:

N_SB_551035_6_AAAA_15_01 

### AT THE LATEST OF THESE TWO CONDITIONS: − BEFORE THE RUDDER REACHES 17000 FC SINCE NEW, WITHOUT EXCEEDING 20 MONTHS FROM ISB REV.00 ISSUE DATE. OR − WITHIN 200 DAYS FROM ISB REV.00 ISSUE DATE.



## Figure A-GAAAA - Sheet 15 Rudder inspection - Overview of the compliance times

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 63 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X

X

X X X
X X
X X X X X

X X X X X

X X

X X
X
X X

X
X
X X
X X X X X

X

X X

X X
X

X

X X X X X X X
X X X X X X X X
X
X
X
X

X X TS−1368 0364 00600 TS−1389 0385 00852 TS−1496 0483 00845 TS−1501 0506 00196 TS−1503 0489 00414 TS−1508 0496 00572 TS−1516 0500 00685 TS−1527 0512 00789 TS−1529 0523 01039 TS−1534 0528 00907 TS−1545 0542 00108 TS−1547 0543 00977 TS−1553 0546 00763 TS−1560 0554 00625 TS−1561 0572 00255 TS−1571 0565 00357 TS−1572 0566 00321 TS−1574 0568 00042 TS−1576 0569 00557 TS−1577 0571 00392 TS−1583 0575 00926 TS−1585 0588 00549 TS−1588 0586 00837 TS−1591 0584 00239 TS−1600 0599 00941 TS−1602 0594 00175 TS−1607 0602 01536 TS−1608 0604 00851 TS−1614 0611 00581 TS−1616 0613 00069 TS−1619 0614 00088 TS−1622 0619 00974 TS−1632 0630 01023 TS−1639 0634 01093 TS−2004 0633 00987 TS−2008 0639 00015 TS−2010 0642 00097 TS−2012 0653 00055 TS−2014 0655 00881 TS−2017 0657 00542 TS−2018 0649 00009 TS−2023 0661 01115 TS−2025 0656 00389 TS−2029 0666 00642 TS−2032 0663 00723 TS−2034 0668 00107

N_SB_551035_6_ACAA_01_09 

## Figure A-GACAA - Sheet 01 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 64 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X X X X X X
X TS−2039 0676 01035 TS−2040 0674 00939 TS−2041 0675 00732 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X X
X X X

X

X X
X

X
X

X X X

X X X X

X X X X
X

X
X X

X
X X
X X

X

X X X X X
X X

X

X
X X X X X

X X

X
X X TS−2046 0683 00633 TS−2050 0696 00888 TS−2051 0684 00813 TS−2052 0698 00232 TS−2053 0686 00816 TS−2056 0688 00787 TS−2060 0690 00313 TS−2069 0695 00580 TS−2070 0708 01537 TS−2080 0716 00972 TS−2082 0718 00076 TS−2084 0720 00081 TS−2085 0719 00183 TS−2086 0722 00671 TS−2094 0730 00385 TS−2096 0725 00805 TS−2097 0733 01069 TS−2098 0732 00437 TS−2100 0735 00444 TS−2101 0737 00885 TS−2106 0740 00364 TS−2113 0749 00632 TS−2115 0751 00690 TS−2118 Spare 01538 TS−2126 0762 00844 TS−2130 0766 00603 TS−2131 0761 00838 TS−2132 0768 00383 TS−2134 0770 00680 TS−2136 0769 01102 TS−2140 0773 01005 TS−2141 0776 00679 TS−2143 0777 01096 TS−2144 0778 00982 TS−2145 0775 00853 TS−2149 0781 00091 TS−2152 0786 00620 TS−2154 0787 00806 TS−2155 0789 00574 TS−2159 0793 00061 TS−2163 0797 00248 TS−2168 0800 00377 TS−2169 0804 00817 X

N_SB_551035_6_ACAA_02_07 

## Figure A-GACAA - Sheet 02 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 65 6

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# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X X X X X X X X
X X X X
X TS−2170 0801 00463 TS−2172 0805 00672 TS−2175 0807 01014 TS−2177 0809 00154 TS−2179 0812 00030 TS−2182 0814 00265 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X

X

X

X
X X

X X X X
X
X

X X X
X

X

X X X

X X
X X X
X X

X X

X X
X X X X

X
X X X X
X X X
X X X X X X X
X X X X X X X X X X X X TS−2183 0817 00406 TS−2185 0818 00534 TS−2192 0824 00294 TS−2193 0825 00833 TS−2195 0827 00164 TS−2199 0830 00268 TS−2200 0831 00879 TS−2204 0835 00462 TS−2206 0838 00618 TS−2208 0840 00966 TS−2209 0842 00407 TS−2210 1039 00024 TS−2211 0848 00094 TS−2213 0843 01006 TS−2216 0845 00118 TS−2217 0851 00409 TS−2218 0847 00947 TS−2220 0854 00459 TS−2221 0850 00756 TS−2222 0856 00208 TS−2223 0857 00375 TS−2227 0861 00160 TS−2228 0858 00275 TS−2230 0863 00330 TS−2231 0865 00111 TS−2232 0862 00441 TS−2234 0844 00098 TS−2235 0870 00536 TS−2236 0864 00990 TS−2238 0869 00648 TS−2240 0867 01544 TS−2242 0872 00142 TS−2244 0873 00654 TS−2245 0877 00298 TS−2248 0878 00942 TS−2250 0882 01002 TS−2251 0881 00413 TS−2252 0886 00468 TS−2254 0884 00696 TS−2258 0889 00439

N_SB_551035_6_ACAA_03_07 

## Figure A-GACAA - Sheet 03 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 66 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X X X X X X X X X X X X
X X X X X
X

X X X X
X X TS−2259 0890 00130 TS−2260 0899 00381 TS−2261 0891 00272 TS−2262 0897 00374 TS−2265 0894 00567 TS−2268 0896 00657 TS−2269 0898 00181 TS−2271 0903 00306 TS−2272 0902 00073 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X X X

X
X

X

X
X X X X X

X

X X
X X

X
X
X X X X
X
X X X X X X X X

X

X

X

X X X X X
X X X X
X X X X X X X
X
X

X
X

X

X

X TS−2274 0904 00288 TS−2276 0989 00953 TS−2279 0908 00490 TS−2280 0910 00156 TS−2281 0907 00482 TS−2284 0911 00882 TS−2285 0913 00771 TS−2286 0912 00456 TS−2293 0918 00901 TS−2295 0935 00078 TS−2297 0921 01075 TS−2298 0924 00961 TS−2299 0923 00973 TS−2302 0927 00509 TS−2303 0929 00110 TS−2304 0928 00984 TS−2305 0930 01062 TS−2307 0931 00776 TS−2310 0936 00796 TS−2311 0937 00149 TS−2312 0939 00215 TS−2313 0940 00211 TS−2315 0942 00688 TS−2316 0941 00122 TS−2317 0945 00155 TS−2319 0948 00416 TS−2320 0944 00759 TS−2321 0947 00174 TS−2322 0946 00780 TS−2323 0949 00753 TS−2325 0952 00969 TS−2326 0954 00457 TS−2327 0951 00575 TS−2330 0955 00712 TS−2331 0957 00285 TS−2332 0959 00850 TS−2333 0962 00417

N_SB_551035_6_ACAA_04_08 

## Figure A-GACAA - Sheet 04 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 67 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X X X X X X X X X X X X X
X

X X X X X
X
X X
X X X X X X X
X X X X X X TS−2334 0956 00731 TS−2336 0963 00849 TS−2337 0965 01108 TS−2338 0971 00153 TS−2339 0960 00114 TS−2340 0966 00213 TS−2341 0964 00292 TS−2343 0967 00920 TS−2346 0969 00896 TS−2352 0987 00735 TS−2353 0981 00550 TS−2354 0977 01013 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X X

X X

X
X X
X X X X X X X
X
X

X
X X X X
X X X X
X

X

X
X

X X

X X X X X
X

X

X
X
X X

X X X

X

X X TS−2355 0978 00719 TS−2356 1001 01017 TS−2358 0993 00513 TS−2360 0984 00454 TS−2362 0995 00641 TS−2363 0986 00792 TS−2364 1002 00825 TS−2365 0997 00829 TS−2366 0990 00996 TS−2367 1028 00214 TS−2370 1012 00514 TS−2371 1007 00418 TS−2372 0992 00586 TS−2373 1004 00529 TS−2374 1008 01001 TS−2377 0996 00527 TS−2381 1015 00835 TS−2382 0982 00297 TS−2387 1005 01061 TS−2388 1019 00246 TS−2392 1022 00739 TS−2393 1011 00593 TS−2395 1013 00070 TS−2397 1026 00373 TS−2398 1027 00394 TS−2399 1032 00358 TS−2407 1035 01045 TS−2408 1038 00652 TS−2409 1040 00008 TS−2410 0868 00461 TS−2411 1042 00643 TS−2412 1043 00878 TS−2415 Spare 00090 TS−2417 1049 00460

N_SB_551035_6_ACAA_05_06 

## Figure A-GACAA - Sheet 05 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 68 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X X X X X X X X X X X X X X X X

X

X X

X

X X X
X

X X X X X X X X

X X
X X TS−2421 1048 00360 TS−2422 1047 01018 TS−2423 1055 00583 TS−2427 1054 00588 TS−2428 1062 01008 TS−2435 1067 01110 TS−2437 1066 00818 TS−2440 1068 00244 TS−2444 1072 00895 TS−2446 1070 00216 TS−2447 1078 00819 TS−2453 1081 00446 TS−2455 1085 00836 TS−2458 1093 00353 TS−2460 1088 00016 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X

X
X X

X

X X X X

X X X X

X

X X X X

X
X X

X

X X X
X X
X X X

X X X X X X

X

X X X X X TS−2463 1089 00427 TS−2466 1101 00717 TS−2467 1109 00766 TS−2471 1100 00556 TS−2472 1095 00287 TS−2474 1097 00831 TS−2476 1106 00035 TS−2477 1098 00167 TS−2478 1104 00447 TS−2481 1193 00445 TS−2482 1102 00305 TS−2483 1108 00971 TS−2484 1110 00486 TS−2486 1129 00650 TS−2488 1162 00309 TS−2491 1179 01064 TS−2493 1113 00395 TS−2494 1121 00804 TS−2498 1116 00403 TS−2499 1122 00782 TS−2501 1125 00289 TS−2505 1131 00820 TS−2506 1126 00428 TS−2508 1130 00676 TS−2510 1132 01024 TS−2512 1134 00802 TS−2514 1133 00644 TS−2517 1136 00868 TS−2518 1141 00668 TS−2521 1146 00308 TS−2522 1147 00565

N_SB_551035_6_ACAA_06_06 

## Figure A-GACAA - Sheet 06 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 69 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X X X X X X X X X X X X X X X X X X X X

X X

X

X

X X X X

X

X X X X
X X

X X
X

X X
X
X
X

X X

X X TS−2527 1153 00449 TS−2529 1150 00404 TS−2532 1155 00524 TS−2536 1170 00526 TS−2540 1164 00760 TS−2544 1166 00296 TS−2545 1201 00517 TS−2547 1171 00630 TS−2551 1168 00847 TS−2552 1173 00903 TS−2553 1180 00528 TS−2554 1175 00622 TS−2555 1182 00043 TS−2558 1186 00740 TS−2562 1187 00624 TS−2563 1194 00890 TS−2566 1192 00983 TS−2568 1197 00178 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X
X

X X X X
X

X X
X X X
X X X X
X X X X

X

X

X X X X X
X X

X
X X X

X X X X X X TS−2570 1198 00979 TS−2571 1203 00267 TS−2572 1202 01047 TS−2573 1200 00093 TS−2574 1245 01049 TS−2575 1209 00521 TS−2576 1204 00247 TS−2579 1207 00930 TS−2580 1208 00415 TS−2581 1210 00162 TS−2583 1212 00604 TS−2584 1213 00442 TS−2585 1214 00535 TS−2586 1216 00786 TS−2587 1218 01080 TS−2590 1220 00578 TS−2591 1217 00095 TS−2592 1222 00516 TS−2593 1221 00378 TS−2596 1225 00258 TS−2597 1227 00380 TS−2601 1229 01070 TS−2602 1237 00319 TS−2603 1228 00745 TS−2605 1233 00450 TS−2606 1234 00402 TS−2611 1240 00335 TS−2612 1235 01015

N_SB_551035_6_ACAA_07_07 

## Figure A-GACAA - Sheet 07 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 70 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X X X X X X X X X X X X X X X X X X X X X X

X

X X X
X X X
X
X X

X X X X X X

X

X X X X
X

X

X X X
X X X TS−2614 1247 00510 TS−2615 1242 00709 TS−2616 1249 00962 TS−2617 1244 00429 TS−2620 1269 00411 TS−2625 1256 00952 TS−2626 1248 00905 TS−2628 1254 00221 TS−2629 1260 01534 TS−2630 1255 00801 TS−2631 1258 00320 TS−2632 1263 00870 TS−2634 1257 00569 TS−2635 1262 00322 TS−2636 1259 00886 TS−2637 1277 00814 TS−2640 1264 00344 TS−2641 1289 00006 TS−2642 1268 00052 TS−2644 1279 00553 TS−2647 1293 00484 X X X X X X X X X X X X X X X X X X X X X X X X X X

X

X

X
X X

X
X

X
X X

X
X X X
X

X
X
X X X X X X X

X
X X X X X X X
X
X
X X TS−2648 1276 01000 TS−2650 1272 00224 TS−2651 1274 01020 TS−2653 1278 00323 TS−2656 1288 00453 TS−2657 1280 00913 TS−2658 1301 00018 TS−2659 1282 00638 TS−2662 1304 00710 TS−2664 1295 00134 TS−2665 1303 00492 TS−2666 1297 01052 TS−2667 1299 00120 TS−2668 1290 00669 TS−2671 1296 00631 TS−2674 1300 01055 TS−2675 1307 00998 TS−2676 1305 00958 TS−2677 1311 00139 TS−2679 1315 00141 TS−2680 1321 00458 TS−2681 1302 00978 TS−2682 1314 00512 TS−2683 1317 01088 TS−2685 1306 01022

N_SB_551035_6_ACAA_08_07 

## Figure A-GACAA - Sheet 08 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 71 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X X X X X X X X X X X X X X X X X X X X X X X X X

X X X

X

X X X X

X X

X X
X

X

X

X X
X
X
X

X X X X X X
X X
X X TS−2688 1310 00639 TS−2689 1323 01094 TS−2691 1325 00781 TS−2695 1324 00443 TS−2697 1316 00605 TS−2698 1331 00231 TS−2699 1333 00552 TS−2700 1335 00815 TS−2701 1336 00212 TS−2707 1330 00908 TS−2710 1332 00472 TS−2711 1334 01076 TS−2712 1348 00226 TS−2713 1346 00613 TS−2714 1350 00785 TS−2715 1337 00975 TS−2716 1352 00741 TS−2717 1341 00200 TS−2719 1339 00152 TS−2722 1425 00928 TS−2724 1378 00655 TS−2725 1345 01551 TS−2726 1358 00158 TS−2727 1362 00101 X X X X X X X X X X X X X X X X X X X X X X X

X X
X X X
X X X X X X
X X X X
X X

X

X X X X X X X
X X X X X X X X

X

X TS−2728 1360 00192 TS−2732 1462 00222 TS−2734 1351 00464 TS−2735 1366 00582 TS−2736 1353 00960 TS−2738 1369 00176 TS−2739 1359 00515 TS−2740 1355 01019 TS−2741 1357 01553 TS−2742 1373 00651 TS−2743 1375 00967 TS−2744 1377 00031 TS−2745 1361 00612 TS−2747 1365 00485 TS−2749 1363 00025 TS−2751 1382 00165 TS−2753 1389 00606 TS−2754 1447 00940 TS−2755 1392 00169 TS−2756 1386 01009 TS−2757 1391 00014 TS−2758 1388 00274

N_SB_551035_6_ACAA_09_06 

## Figure A-GACAA - Sheet 09 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 72 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X

X
X X X X
X
X X X X X

X

X X X X
X
X
X X X

X
X X
X

X

X

X X

X
X X X

X X X X X

X

X
X TS−2759 1372 01058 TS−2760 1370 00228 TS−2762 1396 00533 TS−2765 1387 01077 TS−2771 1415 00182 TS−2772 1381 00147 TS−2773 1397 00317 TS−2775 1412 01552 TS−2776 1435 00279 TS−2778 1383 00667 TS−2779 1403 00645 TS−2780 1436 01065 TS−2782 1390 00922 TS−2783 1408 00489 TS−2784 1414 00564 TS−2785 1410 00170 TS−2786 1428 00083 TS−2788 1394 00627 TS−2790 1400 00138 TS−2791 1423 00616 TS−2792 1405 00144 TS−2793 1421 00733 TS−2794 1409 00480 TS−2795 1426 01103 TS−2796 1424 00431 TS−2797 1432 00539 TS−2799 1439 00576 X X X X X X X X X X X X X X X X X X X X

X
X

X

X
X X

X

X X X
X X X X

X X

X

X X X
X X X
X

X
X
X
X
X TS−2801 1453 00314 TS−2803 1460 00202 TS−2804 1441 00049 TS−2805 1433 00505 TS−2807 1429 00401 TS−2808 1419 00311 TS−2810 1434 00036 TS−2811 1438 00734 TS−2812 1416 00626 TS−2813 1444 00750 TS−2814 1422 00473 TS−2815 1442 00199 TS−2816 Spare 01555 TS−2818 1443 00540 TS−2819 1440 00864 TS−2821 1445 00455 TS−2822 1458 00188 TS−2823 1427 00506 TS−2824 1430 01054

N_SB_551035_6_ACAA_10_07 

## Figure A-GACAA - Sheet 10 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 73 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X X
X X X X
X X X

X X

X X

X X
X

X
X

X

X

X

X X
X X

X X X

X X X
X X X X
X
X X X X TS−2826 1437 00666 TS−2827 1473 00909 TS−2828 1465 00999 TS−2830 1450 01533 TS−2831 1448 00046 TS−2832 1468 00965 TS−2833 1446 00714 TS−2834 1466 00968 TS−2835 1452 01111 TS−2836 1481 00173 TS−2837 1476 00602 TS−2838 1472 00190 TS−2839 1474 01545 TS−2840 1477 01101 TS−2843 1454 00474 TS−2844 1457 00925 TS−2845 1459 01068 TS−2846 1461 01012 TS−2848 1483 00554 TS−2849 1501 00227 TS−2850 1469 00481 TS−2851 1487 01085 TS−2852 1467 00476 TS−2853 1485 00563 TS−2854 1492 00040 TS−2855 1488 00168 TS−2856 1496 00811 TS−2857 1470 00163 TS−2860 1494 00326 TS−2861 1482 00475 X X X X X X X X X X X X X X X X X X X X X X X X
X
X X X
X X
X
X X X X

X X X

X
X TS−2862 1478 00086 TS−2863 1498 01029 TS−2864 1480 00075 TS−2865 1499 00487 TS−2868 1505 00189 TS−2872 1491 00327 TS−2874 1533 00318 TS−2877 1515 00260 TS−2878 1495 01026 TS−2879 1517 00336 TS−2880 1497 00312 TS−2881 1500 00537 TS−2882 1519 00451 TS−2885 1504 00337 TS−2886 1506 00290 TS−2890 1524 00124

N_SB_551035_6_ACAA_11_04 

## Figure A-GACAA - Sheet 11 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 74 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X

X X X

X

X X
X X X X
X X
X X X X X X

X X
X
X

X X X X X X X X

X

X

X

X X
X

X X X X
X X
X X
X X
X
X
X X

X X X X TS−2891 1509 00249 TS−2892 1525 00310 TS−2893 1527 01030 TS−2896 1531 00295 TS−2897 1521 00161 TS−2898 1514 01011 TS−2899 1571 00251 TS−2900 1536 00340 TS−2903 1539 00233 TS−2904 1541 00761 TS−2906 1526 00584 TS−2907 1534 00479 TS−2908 1528 00263 TS−2909 1530 00706 TS−2910 1545 00587 TS−2911 1516 00585 TS−2913 1549 00331 TS−2914 1591 00559 TS−2916 1551 00329 TS−2917 1532 00019 TS−2919 1552 00508 TS−2920 1538 00039 TS−2922 1554 00937 TS−2923 1542 00571 TS−2924 1558 00865 TS−2925 1544 00400 TS−2927 1546 00662 TS−2928 1598 00045 TS−2929 1562 00737 TS−2930 1553 00619 TS−2932 1560 00963 TS−2933 1563 00821 TS−2934 1565 00873 X X X X X X X X X X X X X X
X X X X X X X X X X X
X
X
X
X
X TS−2935 1548 00661 TS−2937 1569 00995 TS−2938 1567 00861 TS−2939 1572 01046 TS−2943 1574 00518 TS−2944 1594 00293 TS−2946 1566 00621 TS−2948 1576 00649 TS−2949 1570 00171 TS−2950 1557 00020 TS−2951 1579 00420 TS−2953 1578 01059 TS−2954 1584 00332

N_SB_551035_6_ACAA_12_04 

## Figure A-GACAA - Sheet 12 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 75 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X
X

X
X

X X
X

X
X

X X X X X X X

X X X X X X X

X
X X X
X

X X

X X

X
X X
X

X
X
X

X X

X X X

X X X X X X X
X X

X

X X

X
X TS−2955 1612 00830 TS−2957 1583 00822 TS−2958 1564 01056 TS−2959 1585 00945 TS−2960 1587 00561 TS−2962 1590 00872 TS−2964 1588 01041 TS−2965 1592 00871 TS−2968 1589 00366 TS−2969 1596 00997 TS−2973 1605 00914 TS−2976 1617 00707 TS−2980 1603 00348 TS−2984 1606 00948 TS−2985 1607 00546 TS−2986 1620 01038 TS−2988 1621 00341 TS−2991 1627 01558 TS−2998 1635 00891 TS−3001 1619 00555 TS−3002 1639 00880 TS−3003 1641 01057 TS−3005 1644 00900 TS−3006 1646 00904 TS−3009 1648 00591 TS−3011 1630 01531 TS−3016 1655 00448 TS−3018 1657 00089 TS−3020 1661 00568 TS−3021 1640 00143 TS−3025 1667 00032 TS−3026 1643 00951 TS−3027 1645 01087 TS−3028 1669 01016 TS−3030 1647 01105 X X X X X X X X X X X X

X
X
X
X X X X
X

X X X X

X X
X X TS−3031 1649 00452 TS−3032 1660 00647 TS−3033 1674 00422 TS−3034 1651 00103 TS−3035 1676 00544 TS−3037 1680 00545 TS−3038 1653 00126 TS−3040 1654 00738 TS−3043 1658 01092 TS−3046 1659 00127 TS−3049 1662 00596

N_SB_551035_6_ACAA_13_04 

## Figure A-GACAA - Sheet 13 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 76 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X

X

X
X

X X

X X X
X X X X

X
X X X X X
X X
X X X X
X

X

X
X
X X

X

X
X

X

X X X

X
X X
X

X X X

X X
X X X

X

X X
X X X X

X X

X X TS−3050 1694 01025 TS−3052 1696 00252 TS−3054 1697 00892 TS−3055 1668 00125 TS−3056 1700 00477 TS−3058 1702 00478 TS−3060 1784 01040 TS−3065 1677 01097 TS−3066 1712 00355 TS−3071 1719 00494 TS−3072 1681 00041 TS−3074 1684 00273 TS−3075 1723 00629 TS−3076 1683 00774 TS−3077 1688 00342 TS−3078 1832 00064 TS−3079 1730 01063 TS−3080 1690 00985 TS−3081 1708 00242 TS−3082 1732 00067 TS−3084 1728 00692 TS−3087 1698 00783 TS−3088 1739 00148 TS−3089 1693 01004 TS−3090 1741 00077 TS−3091 1695 00547 TS−3093 1691 00551 TS−3094 1747 01021 TS−3096 1706 00359 TS−3097 1749 00523 TS−3098 1707 00929 TS−3100 1699 00197 TS−3101 1754 01060 TS−3102 1785 01071 TS−3103 1755 00522 TS−3104 1711 00502 TS−3105 1757 00897 TS−3106 1709 00992 X X X X X X X X X X X

X X X X X X X X
X X X TS−3107 1760 00887 TS−3108 1713 00839 TS−3109 1735 01042 TS−3110 1714 00742 TS−3111 1780 00902 TS−3112 1716 00943 TS−3113 1718 00765 TS−3114 1725 00250

N_SB_551035_6_ACAA_14_04 

## Figure A-GACAA - Sheet 14 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 77 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X X X

X X X X

X X X X X

X X X X X X
X
X

X
X X
X X

X

X X X
X X
X

X

X

X X
X X X
X
X

X
X
X
X X

X X
X
X X

X X X X
X TS−3116 1720 00347 TS−3119 1767 00674 TS−3120 1769 00282 TS−3121 1722 00080 TS−3122 1726 00724 TS−3123 1727 00683 TS−3124 1771 00927 TS−3125 1733 00660 TS−3126 1773 00338 TS−3127 1731 00875 TS−3129 1734 00243 TS−3131 1737 00703 TS−3132 1738 00280 TS−3133 1789 00241 TS−3134 1787 00350 TS−3135 1792 00704 TS−3138 1797 00531 TS−3139 1799 00495 TS−3140 1743 00993 TS−3141 1742 01082 TS−3142 1763 00398 TS−3143 1802 01073 TS−3144 1804 00278 TS−3145 1745 00133 TS−3148 1806 00361 TS−3149 1748 00810 TS−3151 1750 00281 TS−3154 1814 00371 TS−3155 1753 00754 TS−3156 1816 00899 TS−3158 1818 00503 TS−3159 1729 00145 TS−3160 1777 00426 TS−3161 1758 00858 TS−3162 1761 00105 TS−3164 1759 00700 TS−3166 1765 00362 TS−3167 1795 00151 TS−3168 1774 00370 TS−3169 1778 00749 TS−3170 1770 00946 X X X X X X
X X
X X X X TS−3171 1827 00797 TS−3172 1796 00301 TS−3174 1766 00254 TS−3175 1779 00012 TS−3176 1783 00726

N_SB_551035_6_ACAA_15_04 

## Figure A-GACAA - Sheet 15 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 78 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X

X X X X

X X
X X

X X X
X

X X
X X X X

X X X X
X X
X X
X X X X
X
X X X X X X

X X

X
X

X

X

X

X

X
X X
X X
X

X

X X X X
X

X

X

X
X X
X X X X X X
X
X TS−3177 1786 00762 TS−3178 1776 00079 TS−3179 1834 00916 TS−3180 1835 00257 TS−3181 1825 00354 TS−3182 1788 00421 TS−3183 1781 00579 TS−3184 1838 01036 TS−3185 1842 00689 TS−3186 1791 01050 TS−3188 1829 00678 TS−3189 1800 00276 TS−3191 1845 00718 TS−3193 1856 00399 TS−3194 1849 00423 TS−3195 1794 01099 TS−3198 1847 00799 TS−3200 1803 00954 TS−3201 1817 01067 TS−3202 1860 00037 TS−3204 1854 00259 TS−3205 1862 00543 TS−3207 1805 00166 TS−3210 1815 00466 TS−3215 1867 00601 TS−3216 1868 00615 TS−3217 1871 00424 TS−3218 1864 00038 TS−3219 1863 00755 TS−3221 1885 00425 TS−3222 1819 00430 TS−3223 1873 00229 TS−3224 1826 00743 TS−3226 1824 00504 TS−3227 1841 00744 TS−3232 1836 00351 TS−3234 1837 01084 TS−3235 1839 01031 TS−3236 1843 00924 TS−3237 1879 00677 TS−3240 1848 00277 TS−3241 1891 00798 TS−3242 1892 00159 TS−3243 1894 00970 X X X X X X X X TS−3244 1844 00994 TS−3245 1850 00728

N_SB_551035_6_ACAA_16_05 X



## Figure A-GACAA - Sheet 16 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 79 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X

X
X

X X X X X X X
X X X X

X
X
X
X

X

X

X X

X
X X X X X

X

X X

X

X

X

X

X

X X X X X X X X

X X
X
X

X

X
X X X

X X

X
X
X

X X TS−3247 1895 01053 TS−3248 1896 00705 TS−3249 1851 00752 TS−3250 1853 00748 TS−3251 1855 00828 TS−3252 1859 01090 TS−3253 1904 00675 TS−3255 1883 01043 TS−3256 1899 00664 TS−3257 1902 00432 TS−3259 1875 00860 TS−3262 1869 00577 TS−3271 1913 00691 TS−3276 1915 00150 TS−3278 1917 00270 TS−3282 1920 01112 TS−3286 1897 01081 TS−3289 1924 00843 TS−3290 1908 00834 TS−3291 1905 00854 TS−3292 1929 00369 TS−3295 1933 00841 TS−3297 1916 00548 TS−3306 1936 00758 TS−3309 1951 01079 TS−3310 1948 00397 TS−3317 1928 00944 TS−3320 1964 00912 TS−3328 Spare 01559 TS−3388 2044 00842 TS−3392 2000 00859 TS−3395 2002 00352 TS−3429 2023 00493 TS−3441 2041 01098 TS−3516 2157 00488 TS−3561 2187 00716 TS−3567 2205 00368 TS−3574 2195 00628 TS−3590 2231 00840 TS−3591 2224 00751 TS−3595 2232 00777 TS−3598 2234 01089 TS−3609 2243 00177 TS−3625 2262 00185 TS−3638 2269 00501 TS−3650 2275 00102

N_SB_551035_6_ACAA_17_05 

## Figure A-GACAA - Sheet 17 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 80 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X XX TS−3669 2302 00186 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X
X

X X

X

X

X X
X X X X X X

X
X X

X X X
X
X X X X

X X X X

X

X
X

X X X X

X X
X X
X X X X X

X

X X X

X X
X
X

X X TS−3684 2307 00497 TS−3685 2315 00217 TS−3687 2317 00855 TS−3689 2318 00779 TS−3690 2312 00637 TS−3695 2323 00218 TS−3699 2326 00187 TS−3702 2330 00725 TS−3703 2327 00715 TS−3704 2332 00957 TS−3706 2333 00367 TS−3708 2334 00191 TS−3710 2337 00115 TS−3717 2343 00507 TS−3718 2346 00386 TS−3734 2362 00778 TS−3743 2364 00193 TS−3761 2386 00702 TS−3772 2398 00219 TS−3780 2406 01107 TS−3789 2418 00747 TS−3805 2436 00773 TS−3820 2454 00827 TS−3821 2443 00681 TS−3822 2462 01048 TS−3824 2463 00950 TS−3825 2450 00566 TS−3839 2480 01066 TS−3841 2469 00775 TS−3843 2508 00384 TS−3844 2467 01095 TS−3846 2457 00343 TS−3849 2474 01091 TS−3850 2459 00589 TS−3851 2477 00656 TS−3853 2481 00198 TS−3855 2478 00201 TS−3857 2485 00956 TS−3860 2479 00382 TS−3862 2482 01113 TS−3863 2490 00203 TS−3871 2489 00205 TS−3878 2520 00793 TS−3879 2504 00235 TS−3882 2502 00491

N_SB_551035_6_ACAA_18_04 

## Figure A-GACAA - Sheet 18 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 81 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS 01 X X X X X X X X TS−3883 2506 00206 TS−3885 2512 00433 TS−3910 2531 00469 TS−3914 2535 00345 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X X X

X
X X X

X

X X

X X

X

X X

X
X

X X X

X

X X

X X
X

X

X

X X

X
X X
X

X

X

X
X X X

X
X
X X

X X

X X TS−3921 2540 00695 TS−3924 2562 00558 TS−3928 2564 01114 TS−3936 2555 00862 TS−3939 2561 00772 TS−3942 2559 00874 TS−3950 2570 00767 TS−3958 2589 01010 TS−3961 2591 00434 TS−3968 2590 00933 TS−3987 2610 00560 TS−3993 2615 00784 TS−3995 2617 00234 TS−4003 2625 00237 TS−4027 2656 00435 TS−4031 2655 00823 TS−4087 2706 00955 TS−4099 2716 00438 TS−4118 2739 00128 TS−4145 2783 00570 TS−4146 2765 00867 TS−4147 2769 00770 TS−4163 2780 00869 TS−4167 2804 00884 TS−4175 2797 00768 TS−4178 2767 00209 TS−4181 2788 00959 TS−4186 2793 00932 TS−4195 2809 00935 TS−4212 2848 00893 TS−4232 2874 00230 TS−4271 2889 01104 TS−4331 2938 00736 TS−4345 2986 00701 TS−4366 2969 00525 TS−4396 3007 00034 TS−4401 3037 00594 TS−4420 3056 00412 TS−4461 3103 00595 TS−4480 3121 00261 TS−4636 3284 01034 TS−4651 3280 00708

N_SB_551035_6_ACAA_23_04 X



## Figure A-GACAA - Sheet 23 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 82 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF ALL

**NOTE:** THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE

VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:** THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 X X X X X X TS−4678 3294 00934 TS−4696 3330 00532 TS−4770 3409 00906

N_SB_551035_6_ACAA_24_02 

## Figure A-GACAA - Sheet 24 Rudder SN - MSN reference List

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 83 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF 002



# AREA 3

AREA 2

AREA 1

260.0 mm (10.24 in) 110.0 mm (4.33 in)

(50.0 mm) (1.97 in)

297.0 mm (11.69 in) 110.0 mm (4.33 in) OTHER AREAS

TRAILING EDGE AREA

REINFORCED AREA

N_SB_551035_6_AEAA_01_00 

## Figure A-GAEAA - Sheet 01 ELCH inspection - Inspection areas

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 84 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF 002

REPORT TO AIRBUS

TO GET FURTHER

INSTRUCTIONS BEFORE NEXT FLIGHT RE−EXAMINE THE FINDINGS AS PER TAP TEST INSPECTION NTM 51−10−03 OR NTM 51−10−19INDICATION FOUND NO YES

NO FURTHER ACTION REQUIRED IN ACCORDANCE WITH THIS INSPECTION SB AIRBUS INSTRUCTIONS TO BE CARRIED OUT BEFORE NEXT FLIGHT DO 2 ADDITIONAL ELCH INSPECTIONS AT INTERVALS NOT EXCEEDING 4500FC AND NOT LESS THAN 4000 FC

REPORT TO AIRBUS

WITHIN 10 DAYS

NOTE: FOR THE ACCOMPLISHMENT TIMESCALE. REFER TO PARA 1.E.(2) IDENTIFY THE RUDDER SERIAL NUMBER VIA THE PLACARD ON THE RUDDER SPAR. IN CASE OF NO EXISTING PLACARD CONTACT AIRBUS

NO

YES NO FURTHER ACTION REQUIRED IN ACCORDANCE WITH THIS INSPECTION SB SERIAL NUMBER FOUND IN REFERENCE LIST

N_SB_551035_6_AEAA_02_04 

### AS PER NTM 51−10−26



## Figure A-GAEAA - Sheet 02 ELCH inspection - Flow Chart

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 85 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF 002

TYPICAL TRAILING EDGE ELCH INSPECTION FASTENERS



# AREA 3 AREA 2

MINIMUM DISTANCE FROM EDGE 75.0mm (2.95in.) **NOTE:** 

# AREA 1 REINFORCED AREA 

# A

75.0 mm (2.95 in) 50.0 mm (1.97 in)

75.0 mm (2.95 in) 50.0 mm (1.97 in) 50.0 mm (1.97 in) AREA 2 AREA 3



# A

N_SB_551035_6_AEAA_03_02 

## Figure A-GAEAA - Sheet 03 ELCH inspection - Typical ELCH procedure

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 86 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF 002



# Inspection Report
**Rudder Surface Inspection as per SB in area:**

Aircraft type: MSN: Rudder S/N: Rudder P/N: Inspection date: Operator: FC:
FH:

Inspection method ELCH Inspection No findings Findings as detailed by sketch and photos LH RH Rudder Side

N_SB_551035_6_AEAA_04_02 

### * use sketch from the TD



## Figure A-GAEAA - Sheet 04 ELCH inspection - Reporting sheet

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 87 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF 002

325EL

325DL

325CL

325BL

325ER

325DR

325CR

325BR Z325 

# B

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. POSITION OF RUDDER S/N PLACARD AT MSN: 0529, 0532 AND

0537 − 9999 

# C

POSITION OF RUDDER S/N PLACARD AT MSN: 0001 − 0528, 0530 − 0531, 0533 − 0536



# C **A**

**E**

**D K** 

MFR DESCR. SER. N ° CA CODE MFG DATE A/C PNNSA9117−63D 

# A

**B**

N_SB_551035_6_AEAA_05_01 

### D5547100XXXXX
TS−XXXX



## Figure A-GAEAA - Sheet 05 ELCH inspection - Rudder SN identification

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 88 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN

**CONF 002

N_SB_551035_6_AEAA_06_00 

### 2 REPETITIVE ELCH INSPECTIONS AT TE−AREA AT INTERVALS NOT EXCEEDING 4500FC AND NOT LESS THAN 4000 FC SINCE LAST INSPECTION.

APPLY ACTIONS ACCORDING FLOW CHART SHOWN ON FIG. A−GAEAA, SHEET 02



## Figure A-GAEAA - Sheet 06 ELCH inspection - Overview of the compliance time

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 89 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN REPORTING SHEET 

# TITLE: STABILIZERS - RUDDER - A320 RUDDER DEBOND INSPECTION MODIFICATION No.: None Please complete the appropriate item (A or B): A - SB WILL BEembodied YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment:

B - SB HAS BEENembodied on aircraft:
Operator comments:

From Airline: Name/Title: Signature: Date: If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either: Modification OperationalImpact (MOI), if available YES/NO Or : Intermediate revision YES/NO Important Information: This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible revision, this will result in - Updating of maintenance documentation to show pre and post SB data. - Updating of maintenance and operational documentation to show post SB data after embodiment. If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include them in the manual revisions. Refer to SIL 00-037 for detailed information. Please return this completed sheet to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn: SDC32 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 e-mail: sb.reporting@airbus.com or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 1 6

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

# @A318/A319/A320/A321
SERVICE BULLETIN QUALITY PERCEPTION FORM Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score)
- Quality rating of this SB 4 3 2 1 - Quality rating of the Accomplishment Instructions 4 3 2 1 - Quality rating of the Illustrations 4 3 2 1 - Is this SB easy to understand ? Y / N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue.
Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials Operator Supplied X Mod/Inspection X Manpower X Industry support X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations
Comments:

Operator: Date: Name/Title: Please return this form to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035 REVISION No.: 01 - Jul 02/10 Page: 1 6

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