@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

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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

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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

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035

REVISION No.: 01 - Jul 02/10 Page: 4

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SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

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

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

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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

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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

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SUMMARY

This Page Intentionally Left Blank

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035

REVISION No.: 01 - Jul 02/10 Page: 4

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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

0003 0005 0007-0008 0012 0014 0016 0019 0029 0039 0042-0059 0061-0078

0080-0090 0093-0097 0099 0102-0104 0109-0128 0130 0132 0135-0176 0178-0224

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

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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

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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

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OPERATOR MSN

46U 2906 2982 3275 3296 3332 3674 3734 3986

47W 0764 3164

47Y 0394

50X 0543 0661 1918 1969

51X 0325 0375

53U 3162 3316 3748 3812 3990

62X 3402

69X 0444

76U 0302

82U 0438

83X 1823 1896

86W 1571

86Z 0409 0466 0497 1400 1523

95V 3379

96W 1240 1257 1464 1785

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 3138 3161 3502 3515 3532

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 2846 2865 2991

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

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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 0283 0310 0311 0333 0359 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 3182 3194

3201 3223 3232 3261 3277 3291 3299 3327 3338 3353 3370 3394

3404 3427 3448 3477 3486 3489 3505 3521 3536 3549 3568 3576

3582 3610 3628 3648 3679 3701 3715 3729 3765 3776 3813 3875

3963 3997

AZA 0951 0999 1138 1168 1217 1448 1457 1473 1480 1489 2869 2932

2995 3076 3079 3080 3115 3178 3213 3295 3328 3343 3362 3412

3464 3482 3563 3598 3609 3643 3666 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

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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 0243 0251 0299 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 1546 1557 1650 1961

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 0496 0814 1780

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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 1130 2011 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 2156 2164 2316 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 1454 1597

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

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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 0916 1482 1509

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 0772 3492

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 0112 0415

STZ 0190 0279 0395 0420 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

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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 0453 0653 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 3896 3931

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 0393 0414

VLE 1226

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035

REVISION No.: 01 - Jul 02/10 Page: 9

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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 2853 2993 3037 3101 3135

3155 3230 3359 3398 3460 3465 3503

WAN 3739 3791 3907

WAU 3531 3741

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

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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 0735 0737 0739 0741

001

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035

REVISION No.: 01 - Jul 02/10 Page: 11

6

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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 1975 1979 1981 1983

001

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035

REVISION No.: 01 - Jul 02/10 Page: 12

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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 3170 3173 3174 3177

001

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035

REVISION No.: 01 - Jul 02/10 Page: 13

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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

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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

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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

551035-832-202-001

At 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

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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

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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

551035-832-202-001

Within 20 months

from Rev. 00 issue

date

N/A

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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

551035-832-202-001

At 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

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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

551035-832-202-001

Within 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

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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

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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

551035-832-203-001

N/A Within intervals

between 4000 and

4500 FC from the

1. sampling

inspection

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035

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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 under EASA Design Organization Approval No. EASA 21J.031.

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

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

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

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

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

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

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

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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

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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

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This Page Intentionally Left Blank

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035

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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

ITEM DESCRIPTION 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

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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

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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

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Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

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

ITEM DESCRIPTION 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

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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).

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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.

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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 the rudder 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

ITEM DESCRIPTION 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

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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 Para 5.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 on Fig. 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 01 thru Fig. 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 list Fig. A-GACAA Sheet 01 thru Fig. A-GACAA Sheet 24 to 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 the Fig. AGAAAA Sheet 10, to be inspected, refer to Para (h).

(f) If there are only other areas, shown as ’AREA 3’ on the Fig. A-GAAAA Sheet 10, to

be inspected, refer to Para (i).

(g) If there are reinforced areas, shown as ’AREA 1’ on the Fig. A-GAAAA Sheet 10, to

be inspected, do the subsequent inspection in accordance with the Flow Chart Fig.

A-GAAAA Sheet 01 and Fig. A-GAAAA Sheet 02:

1 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.

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 or disks, close the holes again with

Self Adhesive

Aluminium Tape

08-052 As required

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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 to Fig.

A-GAAAA Sheet 13 and Fig. 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 to SRM 51-75-12).

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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 to Fig.

A-GAAAA Sheet 13 and Fig. 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 the Fig. A-GAAAA

Sheet 10, to be inspected, do a repetitive special detailed inspection (ELCH) in

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

1 Do the ELCH 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-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 on Fig. 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 to Fig. 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 the Fig. A-GAAAA Sheet 10, to be

inspected, do a repetitive special detailed inspection (ELCH) in accordance with the

Flow Chart Fig. A-GAAAA Sheet 11 within 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

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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 Chart Fig. A-GAAAA

Sheet 01 and Fig. 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.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035

REVISION No.: 01 - Jul 02/10 Page: 42

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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 or disks, close the holes 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 to Fig.

A-GAAAA Sheet 13 and Fig. 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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035

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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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035

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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 to SRM 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 to Fig.

A-GAAAA Sheet 13 and Fig. 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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035

REVISION No.: 01 - Jul 02/10 Page: 45

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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).

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035

REVISION No.: 01 - Jul 02/10 Page: 46

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<5> Restore the surface protection (Refer to SRM 51-75-12).

(k) Fill in the reporting sheet, refer to Fig. 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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035

REVISION No.: 01 - Jul 02/10 Page: 47

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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 on Fig. 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 01 thru Fig. 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

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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 the Fig. A-GAEAA Sheet

01, which have been inspected during the sampling, 2 additional repetitive special

detailed inspections (ELCH) are necessary:

1 The Technical Disposition (TD) details the location of the reworked area to be

inspected.

a For the definition of the areas to be inspected, refer to the rudder SN -

MSN reference list Fig. A-GACAA Sheet 01 thru Fig. 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 Chart Fig. A-GAEAA

Sheet 02 at 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 on Fig. 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

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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 to Fig. A-GAEAA Sheet 04.

In case of damage indications, send the inspection report with a referenced mail to:

AIRTAC

Customer Services

AIRBUS Central Entity

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

Phone: +33(0)5 61 93 3400 (24 hour)

Fax: +33(0)5 61 93 3500

Mailto: airtac@airbus.com

and in case of damage indications or no damage indications to

Structure Engineering Support

Customer Services - SEES1

AIRBUS Central Entity

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

Fax: +33(0)5 61 93 36 14

**CONF ALL

D. TEST

**CONF 001

None

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035

REVISION No.: 01 - Jul 02/10 Page: 50

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**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

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(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

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**CONF 001

INDICATION

FOUND

CLOSE INSPECTION HOLES

YES NO

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

YES NO

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

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**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

WIDTH

25.0mm

(0.98in.)

ADD−ON INSPECTION 1

ADD−ON INSPECTION 2

ADD−ON INSPECTION 3

BASIC INSPECTION RESULTS

DIRECTION OF

ADD−ON INSPECTION RESTRICTED 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

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**CONF 001

IDENTIFY THE RUDDER SERIAL NUMBER VIA THE PLACARD

ON THE RUDDER SPAR.

IN CASE OF NO EXISTING PLACARD CONTACT AIRBUS

INDICATION

FOUND YES NO

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 YES NO

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

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

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

PN

NSA9117−63D

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

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@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 3 AREA 2

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

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

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@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 YES NO

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 YES NO

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

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

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

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

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 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

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 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

TS−3244 1844 00994 X

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 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

TS−3669 2302 X XX 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

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SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL

01 02 AREA 1 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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

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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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN.

RUDDER SN MSN CONFIG. TD LH SIDE SHELL

01 02 AREA 1 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

LOSS

01

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

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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

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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 51−10−19

INDICATION

FOUND YES NO

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

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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 3 AREA 2

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

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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

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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

PN

NSA9117−63D

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

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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

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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 BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1035

REVISION No.: 01 - Jul 02/10 Page: 1

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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

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