@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 - A319 RUDDER DEBOND INSPECTION

MODIFICATION No.: None

This page transmits Revision No.01 of Service Bulletin No.A320-55-1037

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 551037- 832-848-001-Inspection

Subtask 551037-941-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 551037-941-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

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REVISION TRANSMITTAL SHEET

Subtask 551037-832-201-003 SUBTASK SOLUTION DELETED FOR

APPLICABLE MSN

D

Subtask 551037-832-202-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

NOTE UPDATED

REFERENCES UPDATED

R

Subtask 551037-832-203-002 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

NOTE UPDATED

R

Subtask 551037-942-201-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 551037-942-201-001 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 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

Fig. A-GAEAA FIGURE SOLUTION UPDATED R

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 2

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REVISION TRANSMITTAL SHEET

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.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 3

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REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

6

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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 - A319 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 A319 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.: A320-55-1037

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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) :

03X 06U 17W 27V 31X 42W 47W 52U 52W 53U 53Z 57W 59U

60V 69X 80X 91X 93V 95W AAF AAW ABQ ACA AFL AFR AHY

AJM AMC AMU AUA AVA AWW AZA BAB BAW BEL BER BGF BGH

BHP BKP BMA BRS BTV CCA CCM CEB CEF CES CHH CQN CSA

CSC CSN CSZ CTN CYP DAL DCS DGA DKH DLH DNJ DRA DRK

ETD EZY FFT FIN G4I G8E GFA GWI HHI HMS IAC IBE ISS

IZM JET KBR KFR KNE KZR LAN LBY LHT LZB MAU MDL MLM

MXA NKS NLY PAL QAF QTR R1T RBA RJA RNV SAA SAS SBI

SDM SHJ SLK SVW SWR TAE TAI TAM TAP TAR TGW THY TWJ

UAL UEA UKN USA VOI VRD WGT WHT

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU 55.40.00.004

OEB None

AOT 55A1038

55A1039

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER OIT 999.0092/08; SBIT 914.0808/09

NATURE OF THE WORK

AIRCRAFT NO

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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SUMMARY

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 551037-832-848-001: Inspection

TOTAL MANHOURS 2.00

**CONF 002

Task 551037-832-848-001: Inspection

TOTAL MANHOURS 2.00

APPENDICES

**CONF ALL

None

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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.: A320-55-1037

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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 - A319 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

319-111 319-112 319-113 319-114 319-115 319-131 319-132 319-133

(2) Effectivity by MSN

0546 0572 0578 0588 0598 0600 0608-0610 0612 0616 0618 0621 0623 0625 0627

0629 0634 0636-0637 0639 0641 0644 0646-0647 0649 0651 0654 0656 0660 0670

0672 0679 0682 0686 0688-0691 0693-0695 0697 0700 0711 0713 0717 0719 0721

0723 0727-0729 0732 0734 0736 0738 0740 0742 0744 0748 0750 0752 0755 0757

0759 0763 0767 0769 0773 0779 0783 0785 0788 0790 0794 0798 0800 0804 0813

0817 0821 0825 0829 0831 0833 0837 0840 0843 0845 0847 0850 0853 0858 0860

0862 0867 0869 0871 0873 0875 0880 0882 0885 0889-0890 0893 0896 0898 0904

0906 0910 0913 0917 0922 0924 0929 0931 0933 0938 0944 0946 0948-0949 0952

0965 0972 0976 0979-0980 0985 0989 0997-0998 1000 1002 1010 1016 1018-1020

1022 1025 1029 1031 1033-1034 1036 1038 1040 1043 1046 1048-1049 1051 1053

1055-1056 1058 1062 1064 1066 1068-1069 1071 1073-1074 1077-1078 1082 1084

1086 1088-1092 1095-1098 1100 1102-1103 1106-1107 1109 1111 1113 1115-1116

1118 1120 1122 1124 1126-1127 1129 1131 1135-1136 1139-1140 1142 1145 1147

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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1149 1151 1154-1155 1157 1159-1160 1164-1165 1167 1169-1170 1172 1176 1178

1180 1182 1184 1190-1191 1193 1197 1201 1203 1205 1209 1211-1212 1216

1222-1223 1225 1228 1230 1232 1236 1239 1243 1245 1247 1249 1252 1254 1256

1258 1261 1263 1265 1267 1269 1271 1275 1277 1279 1281 1283 1285 1287 1289

1291 1295 1297 1301 1303 1305 1309 1311 1313 1315 1317 1319 1321 1323-1326

1328-1329 1331 1335-1336 1338 1340 1342 1344 1346 1348 1350 1352 1354 1358

1360 1362 1364 1369 1371 1373 1375 1377-1378 1380 1382 1384 1386 1388-1389

1391-1393 1395 1397 1401 1404 1406 1410 1414-1415 1420 1423 1426 1429 1434

1440 1444-1445 1449 1453 1456 1460 1463 1466 1468 1471 1474 1477 1479 1483

1485 1488 1490 1494 1498 1501 1505 1507 1510 1513 1515 1520 1522 1524 1527

1529 1534 1537 1541 1543 1545 1547 1549 1551-1552 1556 1558 1560 1562-1563

1565 1567 1569-1570 1573-1577 1579 1581-1583 1585 1589-1590 1592 1594 1598

1600-1601 1603-1604 1606 1608 1612 1616 1618 1622 1625 1627 1630 1634 1640

1643 1645 1647 1649 1653-1654 1656 1659 1662 1664 1668 1671 1673 1677 1679

1683-1685 1688 1693 1698-1699 1703 1706 1709 1714 1718 1722 1727 1729 1731

1733 1737-1738 1740 1742-1743 1745-1746 1750 1752-1753 1756 1758-1759 1761

1765-1766 1768 1770 1774 1778-1779 1781 1786 1790-1791 1795-1796 1800-1801

1803 1805 1808 1810 1815 1819-1820 1824 1826 1828 1831 1833 1837 1839 1841

1844 1846 1851 1853 1855 1863 1866 1870 1872 1875-1876 1880 1882 1884 1886

1890 1893 1897 1901 1908 1912 1916 1923 1925 1934 1936 1938 1943 1947 1952

1955 1959 1962-1963 1971 1976 1980 1982 1986 1990 1997 1999-2000 2002 2004

2007-2008 2010 2012-2013 2015 2019 2023 2026 2028 2030 2032-2033 2037 2039

2043 2047 2050 2052-2053 2057 2062 2066 2069 2072 2074 2078 2083 2086-2087

2089 2091 2093 2095-2096 2098 2101 2103 2113 2119-2120 2122 2124 2126-2127

2129 2131 2170 2172 2174 2176 2179 2181 2184 2186 2188 2192 2194 2196 2198

2200 2202-2203 2205 2209 2213-2214 2222 2224 2228 2230 2232 2236-2237

2240-2241 2243 2245 2249 2251 2253 2258 2260 2262-2266 2268-2269 2271 2273

2277 2279 2281 2283 2285 2287 2289 2293 2295-2296 2298 2300 2302 2304 2306

2308 2311 2313 2318-2319 2321 2326 2332 2335 2339 2341 2346 2348 2353 2355

2360 2362 2365 2369-2371 2373 2375 2378-2380 2382-2383 2385 2387 2389 2392

2396 2398 2400 2402 2404 2406 2408 2412 2414 2416 2418 2420-2421 2424

2426-2427 2429 2431 2433 2435-2436 2438 2440 2442 2444 2446 2448 2450 2452

2454 2456 2458 2460 2463-2471 2473-2474 2477 2481 2483 2485 2487 2490 2492

2494-2495 2497 2499 2501 2503 2505 2507-2508 2510 2512 2514 2516 2518-2519

2525 2527-2528 2532 2534 2538 2541 2545-2548 2550-2551 2554-2561 2565

2567-2568 2570 2572 2574 2578-2579 2581 2585-2586 2588 2592-2593 2595 2597

2603 2605 2607 2611 2614-2615 2617-2618 2621-2622 2624-2625 2628-2629

2631-2632 2634 2636 2638-2639 2641 2643-2644 2646 2648 2650 2652 2655 2657

2659-2660 2662 2664 2666-2667 2669 2672-2673 2675 2677 2679 2681 2684

2690-2691 2693-2694 2697-2698 2700 2702 2704 2706 2709 2711 2715-2716 2718

2720 2723 2727 2729 2733 2735 2738-2739 2742 2744 2746 2748 2751 2754 2757

2762-2763 2765 2769 2771 2773-2774 2777 2779-2780 2782 2784 2786 2788 2790

2795 2797 2801 2803 2805-2806 2811-2813 2815 2818-2819 2821 2825 2827 2829

2831 2833 2836-2837 2839 2841 2843 2845 2847 2849-2850 2852 2854 2857-2858

2860 2864 2866 2870 2872-2873 2876 2878-2879 2884 2886-2894 2897-2898 2901

2905 2907 2913 2921 2923 2925 2929 2935 2938 2940 2942 2946 2948-2949 2954

2959 2961 2963 2969 2976 2978-2979 2981 2983 2985 2997 3003 3007 3011 3017

3019-3020 3024 3026 3028 3032 3036 3041 3043 3045-3046 3049 3053-3054 3057

3059 3061 3065 3069 3073 3077-3078 3082 3084-3085 3088 3090 3094 3096 3102

3104 3108 3114 3116 3118 3122 3124 3128 3133-3134 3137 3139 3142 3144 3165

3168-3169 3171-3172 3175-3176 3179 3181 3184 3186 3188 3193 3195 3200 3202

3204 3209 3226 3231 3243 3245 3248 3250 3252-3253 3255 3258 3260 3269 3271

3276 3279 3281 3285 3288 3292 3298 3300 3305 3309 3311 3317 3320 3324 3331

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3336 3342 3344 3346-3347 3352 3356 3358 3364 3375 3377 3380 3385 3388 3393

3395 3403 3406-3407 3411 3413 3415 3417 3421 3424 3426 3428 3432 3436

3442-3443 3445 3447 3450 3452 3454 3463 3466-3467 3491 3500 3513 3518 3520

3533-3534 3537 3542 3544 3548 3551 3555 3560-3561 3564 3569 3571 3578 3580

3586 3588-3590 3595 3604 3608 3614-3615 3620 3632 3634 3638 3647 3651 3657

3660-3661 3663 3671 3675 3680 3683-3687 3689 3691 3694 3700 3702 3704-3705

3710 3720 3727-3728 3733 3735 3742 3744 3746 3754 3757 3759 3763 3768 3770

3772 3774 3779 3788 3790 3794 3799 3801 3803 3808 3810 3818 3822 3824 3826

3828 3832 3834 3836 3838-3839 3841-3842 3844-3845 3849 3851 3853-3854 3856

3860 3865 3872 3874 3876 3888 3890 3892 3895 3897 3901 3903 3905 3911 3914

3918 3942 3950 3957-3958 3962 3970 3982-3983 3994 3998 4000

(3) Effectivity by Operator

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

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

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

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

OPERATOR MSN

03X 2421

06U 3957

17W 3046

27V 3826

31X 2192

42W 3513

47W 1494

52U 3542

52W 3243

53U 1727 1880 3142 3252 3317 3895 3905 3950

53Z 1468

57W 1999

59U 2706 3073

60V 3632

69X 0588

80X 2748

91X 2837

93V 1589

95W 2949

AAF 0639 1846 2296 2870

AAW 3615 3657

ABQ 3385 3388

ACA 0546 0572 0634 0656 0670 0672 0682 0688 0691 0693 0695 0697

0711 0719 0721 0728 0732 0736 0740 0742 0752 0757 0769 0773

0779 0785 0800 0813 0817 0829 0831 0840 0845 1562 1577

AFL 2052 2069 2072 2091 2093 2179 2222 2243 3281 3298 3336 3794

3838 3942 3998

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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OPERATOR MSN

AFR 0598 0600 0608 0618 0625 0637 0938 0985 0998 1000 1020 1025

1036 1151 1169 1176 1190 1201 1216 1267 1271 1344 1404 1415

1444 1449 1471 1505 1524 1616 1622 1640 1645 1677 1699 1733

1938 2213 2228 2279 2456 2716 2938 2961 3065

AHY 2487 2516 2588 2788

AJM 3331

AMC 2113 2122 2186 2332 2382

AMU 1758 1790 1893 1912 1962

AUA 2131 2174 2262 2416 2494 2547 2652

AVA 3467 3518 3647 3691

AWW 1853

AZA 1722 1740 1745 1770 1779 2033 2057 2074 2083 2086 2101 2127

BAB 2700 2763

BAW 1082 1115 1118 1142 1193 1197 1222 1225 1232 1236 1239 1258

1261 1279 1295 1329 1338 1380 1384 1423 1440 1445 1466 1510

1513 1529 1537 1558 1574 1590 1594 1604 1606

BEL 0644 1086 1160 1336 1388

BER 2383 2467 2468 3202 3245 3346 3415 3447 3586 3661 3689 3700

3704 3728 3865

BGF 3188

BGH 3139

BHP 3604

BKP 3421 3424 3454 3694 3759 3911

BMA 2098 2188 2194 2389 2429 2466 2694 2697 2720 2981 3049

BRS 2263

BTV 2648 2660

CCA 1654 1679 1753 2000 2007 2015 2172 2202 2205 2237 2269 2285

2293 2298 2454 2499 2508 2525 2532 2545 2551 2559 2614 2643

2805 2819 2839 2847 2890 3195 3200 3226 3250

CCM 1068 1145

CEB 2556 2586 2625 2638 2786 2790 2821 2831 2852 2876

CEF 2801 3085

CES 1285 1303 1377 1386 1541 1551 1601 1603 1778 1786 2693 2757

2825 3168 3186

CHH 3520 3548 3561 3578 3580 3638 3768 3842 3849 3851 3914 3958

3982

CQN 3836 3876 3901

CSA 3043 3094 3406 3436 3452 3660 3892

CSC 2313 2348 2396 2431 2510 2534 2597 2639 3114 3116 3124 3680

3962

CSN 1971 1986 2004 2008 2200 2203 2232 2273 2371 2408 2426 2435

2505 2519 2541 2546 2554 2555 2558 2574 2579 2667 2815 2901

2940 2948 2969 3020 3144 3258 3269 3311 3342 3828 3860 3890

3903 3983

CSZ 2672 2684 2841 2905 2935

CTN 0767 0833 1029 1252

CYP 1729 1768 2718

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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OPERATOR MSN

DAL 1058 1062 1191 1230 1249 1324 1325 1346 1392 1414 1434 1453

1456 1483 1498 1501 1520 1543 1549 1567 1570 1582 1659 1662

1683 1685 1693 1709 1714 1738 1746 1752 1766 1774 1796 1800

1810 1815 1820 1824 1828 1833 1839 1875 1897 1923 1959 1976

1982 1990 2002 2013 2026 2039 2047 2087 2095

DCS 1053

DGA 1485 1556

DKH 2879 2913

DLH 0609 0610 0616 0623 0627 0636 0641 0646 0651 0654 0679 0689

0694 0700 0717 0723 0729 0738 0744 0794 0853 0860 0875 1016

1172

DNJ 1963

DRA 2557 2561 2581 2611 2617 2644 2733 2746 2849 2891 2985 3285

DRK 2306 2346

ETD 1947 1955

EZY 2037 2043 2050 2053 2062 2119 2120 2129 2170 2176 2181 2184

2196 2214 2224 2230 2245 2249 2251 2265 2271 2283 2289 2300

2319 2353 2360 2370 2378 2380 2385 2387 2398 2402 2412 2420

2427 2436 2442 2446 2450 2460 2463 2471 2477 2481 2492 2495

2503 2512 2514 2527 2528 2538 2548 2565 2578 2605 2636 2646

2677 2681 2691 2702 2709 2715 2727 2729 2735 2742 2744 2754

2765 2769 2777 2779 2782 2795 2803 2812 2818 2827 2829 2854

2860 2866 2873 2884 2923 2946 2959 3003 3036 3041 3053 3059

3061 3082 3084 3088 3090 3118 3122 3134 3137 3176 3184 3411

3413 3426 3432 3442 3466 3537 3544 3555 3569 3571 3608 3634

3675 3683 3702 3720 3735 3742 3746 3754 3763 3774 3788 3799

3808 3810 3824 3844 3845 3854 3888

FFT 1515 1579 1583 1684 1759 1781 1803 1841 1943 1980 1997 2010

2012 2019 2030 2103 2198 2209 2236 2240 2241 2253 2258 2260

2287 2318 2392 2400 2406 2448 2465 2483 2497 2518 2751 2806

2836 2857

FIN 1073 1107 1184 1309 1352 1364 1791 1808 1916 2124 2266

G4I 1157 1795 2507

G8E 2762

GFA 1884 1901

GWI 1077 1084 1089 1136 1147 1155 1170 1209 1277 2607 2628 2632

2813 2833 2976 3011 3128 3172 3193 3352 3358 3375 3500 3534

3839 3841

HHI 3364 3403 3533 3560 3589 3818 3853 3872

HMS 3309 3564

IAC 1668 1718 2593 2624 2629 2907 3271 3288 3300 3305 3344 3551

3620 3687 3822 3874 3918 3970

IBE 1154 1180 1247 1362 2264 2311 2365 2843 2889 2897 3054 3078

3102 3169 3179 3209 3255 3320 3377 3380 3443 3651 3744

ISS 1048 1102 1283 1305

IZM 2404 2414 2452

JET 0647 0660 2424 2698 2723

KBR 3171

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 5

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SERVICE BULLETIN

OPERATOR MSN

KFR 2621 2634 2650 2664

KNE 1124 1886

KZR 3614

LAN 2089 2096 2295 2304 2321 2572 2585 2845 2858 2864 2872 2886

2887 2892 2894 3663 3671 3770 3772 3779

LBY 2335

LHT 3897

LZB 3028

MAU 1592 1936

MDL 2784 2797

MLM 2592 3356

MXA 1429 1598 1612 1618 1625 1630 1634 1673 1706 1742 1750 1805

1866 1872 1882 1925 2066 2078 2126 2662 3790

NKS 2433 2470 2473 2485 2490 2560 2567 2603 2622 2673 2679 2704

2711 2893 2898 2929 2942 2963 2978 2983 3007 3017 3026 3165

3393 3395

NLY 3019 3407

PAL 2878 2925 2954 3108

QAF 1335 3994

QTR 1656 2341

R1T 1908

RBA 2023 2032

RJA 3428 3685 3803 3832

RNV 0913 2277 2362 3834

SAA 2268 2281 2308 2326 2355 2375 2379 2418 2438 2469 2501

SAS 2850 2888 3231 3292

SBI 1071 1078 1090 1091 1126 1129 1131 1149 1164 1167 1819 1870

2028 2369 2373 2464 2474 2618 2641

SDM 0649 1488 1560 1743 1761 1851 1863 1876 1890

SHJ 0910

SLK 1074 1098 1228 1698 2568 3104

SVW 2921 3133 3856

SWR 0578 0612 0621 0713 0727 0734 1018

TAE 2659

TAI 1066 1113 1934 1952 2339 2444 3057 3248 3276

TAM 0976 1010 1092 1096 1103 1139 1575 1608 1703 1801 1826 1831

1837 1855 3032 3588 3595 3710 3727 3733 4000

TAP 0629 0750 0755 0763 0790 0821 0837 0906 0917 0933 0979 1034

1100 1106 1120 1127 1165 1756 1765

TAR 0869 0880 1479 3096

TGW 3757 3801

THY 1002 2631 2655 2738 2739

TWJ 2550

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 6

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SERVICE BULLETIN

OPERATOR MSN

UAL 0686 0690 0748 0759 0783 0788 0798 0804 0825 0843 0847 0850

0858 0862 0867 0871 0873 0882 0893 0898 0944 0948 0952 0965

0980 0989 1022 1031 1211 1243 1291 1321 1401 1420 1426 1460

1474 1477 1507 1522 1545 1569 1573 1581 1585 1600 1627 1647

1649 1653 1664 1671 1688 1731 1737

UEA 0946 0949 1263 2774 3024

UKN 3260

USA 0885 0889 0890 0896 0904 0922 0924 0929 0931 0972 0997 1019

1033 1038 1040 1043 1046 1049 1051 1055 1056 1064 1069 1088

1095 1097 1109 1111 1116 1122 1135 1178 1182 1203 1205 1223

1245 1254 1265 1269 1275 1281 1287 1289 1297 1301 1311 1313

1315 1317 1319 1323 1326 1328 1331 1340 1342 1348 1350 1354

1358 1360 1369 1371 1373 1375 1378 1382 1389 1391 1393 1395

1397 1406 1410 1463 1490 1527 1534 1547 1552 1563 1565 1576

1643 1844 2302 2458 2570 2595 2615 2669 2690

VOI 1140 1159 2657 2666 2771 2780 2979 2997 3045 3069 3077 3175

3253 3279 3450 3463 3491 3590 3705

VRD 2773 2811 3181 3204 3324 3347 3417 3445 3684 3686

WGT 1212

WHT 1256 2440 2675

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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SERVICE BULLETIN

(4) Configuration by MSN

MSN CONFIGURATION

0546 0572 0578 0588 0598 0600 0608 0609 0610 0612 0616

0618 0621 0623 0625 0627 0629 0634 0636 0637 0639 0641

0644 0646 0647 0649 0651 0654 0656 0660 0670 0672 0679

0682 0686 0688 0689 0690 0691 0693 0694 0695 0697 0700

0711 0713 0717 0719 0721 0723 0727 0728 0729 0732 0734

0736 0738 0740 0742 0744 0748 0750 0752 0755 0757 0759

0763 0767 0769 0773 0779 0783 0785 0788 0790 0794 0798

0800 0804 0813 0817 0821 0825 0829 0831 0833 0837 0840

0843 0845 0847 0850 0853 0858 0860 0862 0867 0869 0871

0873 0875 0880 0882 0885 0889 0890 0893 0896 0906 0910

0913 0917 0922 0924 0929 0931 0933 0938 0944 0946 0948

0949 0952 0965 0972 0976 0979 0980 0985 0989 0997 0998

1000 1002 1010 1016 1018 1019 1020 1022 1025 1029 1031

1033 1034 1036 1038 1040 1043 1046 1048 1049 1051 1053

1055 1056 1058 1062 1064 1066 1068 1069 1071 1073 1074

1077 1078 1082 1084 1086 1088 1089 1090 1091 1092 1095

1096 1097 1098 1100 1102 1103 1106 1107 1109 1111 1113

1115 1116 1118 1120 1122 1124 1126 1127 1129 1131 1135

1136 1139 1140 1142 1145 1147 1149 1151 1154 1155 1157

1159 1160 1164 1165 1167 1169 1170 1172 1176 1178 1180

1182 1184 1190 1191 1193 1197 1201 1203 1205 1209 1211

1212 1216 1222 1223 1225 1228 1230 1232 1236 1239 1243

1245 1247 1249 1252 1254 1256 1258 1261 1263 1265 1267

1269 1271 1275 1277 1279 1281 1283 1285 1287 1289 1291

1297 1301 1303 1305 1309 1311 1313 1315 1317 1319 1321

1323 1324 1325 1326 1328 1329 1331 1335 1336 1338 1340

1342 1344 1346 1348 1350 1352 1354 1358 1360 1362 1364

1369 1371 1373 1375 1377 1378 1380 1382 1384 1386 1388

1389 1391 1392 1393 1395 1397 1401 1404 1406 1410 1414

1415 1420 1423 1426 1429 1434 1440 1444 1445 1449 1453

1456 1460 1463 1466 1468 1471 1474 1477 1479 1483 1485

1488 1490 1494 1498 1501 1505 1507 1510 1513 1515 1520

1522 1524 1527 1529 1534 1537 1541 1543 1545 1547 1549

1551 1552 1556 1558 1560 1562 1563 1565 1567 1569 1570

1573 1574 1575 1576 1577 1579 1581 1582 1583 1585 1589

1590 1592 1594 1598 1600 1601 1603 1604 1606 1608 1612

1616 1618 1622 1625 1627 1630 1634 1640 1643 1645 1647

1649 1653 1654 1656 1659 1662 1664 1668 1671 1673 1677

1679 1683 1684 1685 1688 1693 1698 1699 1703 1706 1709

1714 1718 1722 1727 1729 1731 1733 1737 1738 1740 1742

1743 1745 1746 1750 1752 1753 1756 1758 1759 1761 1765

1766 1768 1770 1774 1778 1779 1781 1786 1790 1791 1795

1796 1800 1801 1803 1805 1808 1810 1815 1819 1820 1824

1826 1828 1831 1833 1837 1839 1841 1844 1846 1851 1853

1855 1863 1866 1870 1872 1875 1876 1880 1882 1884 1886

1890 1893 1897 1901 1908 1912 1916 1923 1925 1934 1936

1938 1943 1947 1952 1955 1959 1962 1963 1971 1976 1980

1982 1986 1990 1997 1999 2000 2002 2004 2007 2008 2010

2012 2013 2015 2019 2023 2026 2028 2030 2032 2033 2037

001

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 8

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SERVICE BULLETIN

MSN CONFIGURATION

2039 2043 2047 2050 2052 2053 2057 2062 2066 2069 2072

2074 2078 2083 2086 2087 2089 2091 2093 2095 2096 2098

2101 2103 2113 2119 2120 2122 2124 2126 2127 2129 2131

2170 2172 2174 2176 2179 2181 2184 2186 2188 2192 2194

2196 2198 2200 2202 2203 2205 2209 2213 2214 2222 2224

2228 2230 2232 2236 2237 2240 2241 2243 2245 2249 2251

2253 2258 2260 2262 2263 2264 2265 2266 2268 2269 2271

2273 2277 2279 2281 2283 2285 2287 2289 2293 2295 2296

2298 2300 2302 2304 2306 2308 2311 2313 2318 2319 2321

2326 2332 2335 2339 2341 2346 2348 2353 2355 2360 2362

2365 2369 2370 2371 2373 2375 2378 2379 2380 2382 2383

2385 2387 2389 2392 2396 2398 2400 2402 2404 2406 2408

2412 2414 2416 2418 2420 2421 2424 2426 2427 2429 2431

2433 2435 2436 2438 2440 2442 2444 2446 2448 2450 2452

2454 2456 2458 2460 2463 2464 2465 2466 2467 2468 2469

2470 2471 2473 2474 2477 2481 2483 2485 2487 2490 2492

2494 2495 2497 2499 2501 2503 2505 2507 2508 2510 2512

2514 2516 2518 2519 2525 2527 2528 2532 2534 2538 2541

2545 2546 2547 2548 2550 2551 2554 2555 2556 2557 2558

2559 2560 2561 2565 2567 2568 2570 2572 2574 2578 2579

2581 2585 2586 2588 2592 2593 2595 2597 2603 2605 2607

2611 2614 2615 2617 2618 2621 2622 2624 2625 2628 2629

2631 2632 2634 2636 2638 2639 2641 2643 2644 2646 2648

2650 2652 2655 2657 2659 2660 2662 2664 2666 2667 2669

2672 2673 2675 2677 2679 2681 2684 2690 2691 2693 2694

2697 2698 2700 2702 2704 2706 2709 2711 2715 2716 2718

2720 2723 2727 2729 2733 2735 2738 2739 2742 2744 2746

2748 2751 2754 2757 2762 2763 2765 2769 2771 2773 2774

2777 2779 2780 2782 2784 2786 2788 2790 2795 2797 2801

2803 2805 2806 2811 2812 2813 2815 2818 2819 2821 2825

2827 2829 2831 2833 2836 2837 2839 2841 2843 2845 2847

2849 2850 2852 2854 2857 2858 2860 2864 2866 2870 2872

2873 2876 2878 2879 2884 2886 2887 2888 2889 2890 2891

2892 2893 2894 2897 2898 2901 2905 2907 2913 2921 2923

2925 2929 2935 2938 2940 2942 2946 2948 2949 2954 2959

2961 2963 2969 2976 2978 2979 2981 2983 2985 2997 3003

3007 3011 3017 3019 3020 3024 3026 3028 3032 3036 3041

3043 3045 3046 3049 3053 3054 3057 3059 3061 3065 3069

3073 3077 3078 3082 3084 3085 3088 3090 3094 3096 3102

3104 3108 3114 3116 3118 3122 3124 3128 3133 3134 3137

3139 3142 3144 3165 3168 3169 3171 3172 3175 3176 3179

3181 3184 3186 3188 3193 3195 3200 3202 3204 3209 3226

3231 3243 3245 3248 3250 3252 3253 3255 3258 3260 3269

3271 3276 3279 3281 3285 3288 3292 3298 3300 3305 3309

3311 3317 3320 3324 3331 3336 3342 3344 3346 3347 3352

3356 3358 3364 3375 3377 3380 3385 3388 3393 3395 3403

3406 3407 3411 3413 3415 3417 3421 3424 3426 3428 3432

3436 3442 3443 3445 3447 3450 3452 3454 3463 3466 3467

3491 3500 3513 3518 3520 3533 3534 3537 3542 3544 3548

3551 3555 3560 3561 3564 3569 3571 3578 3580 3586 3588

3589 3590 3595 3604 3608 3614 3615 3620 3632 3634 3638

001

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

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SERVICE BULLETIN

MSN CONFIGURATION

3647 3651 3657 3660 3661 3663 3671 3675 3680 3683 3684

3685 3686 3687 3689 3691 3694 3700 3702 3704 3705 3710

3720 3727 3728 3733 3735 3742 3744 3746 3754 3757 3759

3763 3768 3770 3772 3774 3779 3788 3790 3794 3799 3801

3803 3808 3810 3818 3822 3824 3826 3828 3832 3834 3836

3838 3839 3841 3842 3844 3845 3849 3851 3853 3854 3856

3860 3865 3872 3874 3876 3888 3890 3892 3895 3897 3901

3903 3905 3911 3914 3918 3942 3950 3957 3958 3962 3970

3982 3983 3994 3998 4000

001

0898 0904 1295 002

(5) Configuration definition

**CONF 001

is valid for aircraft with rudders which might have reworked areas to be inspected.

**CONF 002

is valid for aircraft with rudders which were already inspected one time during the

sampling.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLD01 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 A319 aircraft for potential debonding.

Due to the different areas on the rudder to be inspected, different inspection procedures

are necessary:

- Vacuum loss inspection

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

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SERVICE BULLETIN

- Elasticity Laminate Checker (ELCH) inspection

- Tap test inspection

- Thermography inspection

- Ultrasound (US) inspection.

(3) Advantages

The accomplishment of this Service Bulletin will ensure the detection of potential

debonding in the reworked areas.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 551037-832-848-001: 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 551037-832-848-001: Inspection

(1) Do 2 additional special detailed repetitive ELCH inspections

**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).

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

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SERVICE BULLETIN

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

551037-832-202-001

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

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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

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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

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

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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

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SERVICE BULLETIN

Area to be

inspected

Condition Action Compliance time Repetitive interval

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

551037-832-202-001

Within 20 months

from Rev. 00 issue

date

N/A

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).

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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SERVICE BULLETIN

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

551037-832-202-001

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 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

551037-832-202-001

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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 15

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SERVICE BULLETIN

Area to be

inspected

Condition Action Compliance time Repetitive interval

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

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

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Area to be

inspected

Condition Action Compliance time Repetitive interval

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

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

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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

551037-832-203-002

N/A Within intervals

between 4000 and

4500 FC from the

1. sampling

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

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 Organisation 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 551037-832-848-001: Inspection

Get Access 1.00

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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Task 551037-832-848-001: Inspection

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:

Steps Manhours Elapsed time Number of

persons

Get access 1.00 0.75 2

Rudder SN

identification

0.25 0.25 1

Vacuum 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 551037-832-848-001: Inspection

Get Access 1.00

On Aircraft

Do 2 additional special detailed repetitive ELCH

inspections

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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

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.: A320-55-1037

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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

Composite 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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 551037-832-848-001 - 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 551037-910-201-001 - 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) Clean the areas to be inspected with

Solvent General

Purpose

11-026 As required

Lint-Free Cotton

Cloth

19-003 As required

(2) Subtask 551037-839-201-001 - 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 551037-910-201-001 - 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

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).

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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(b) Clean the areas to be inspected with

Solvent General

Purpose

11-026 As required

Lint-Free Cotton

Cloth

19-003 As required

(2) Subtask 551037-839-201-001 - 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 551037-941-201-001 - 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.

(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).

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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(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 551037-941-201-001 - 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.

(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.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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(j) To open the access panels, (Refer to AMM Task 55-33-13-010-002).

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 551037-832-202-001 - 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

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

51-77-11 Para 5.

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References

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 - General 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

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

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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.

(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 foil on the areas to be inspected.

b Mark the grid of holes on the adhesive foil.

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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 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 holes 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.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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Temporary restoration of the vacuum loss inspection holes 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

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 inspection hole.

g Close the filled holes with

Self Adhesive

Aluminium Tape

08-052 As required

or

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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).

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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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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.

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

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

in.) and inject the resin through the hole into the cells of the honeycomb

core. Start the injection at the cell bottom and finish when the resin is

leaking out of the inspection hole.

g Close the filled holes with a self adhesive tape.

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 51-77-11 Para 5.).

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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<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 special detailed repetitive ELCH inspection 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.

b 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.

c 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.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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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,

re- examine the findings as per tap 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 special detailed repetitive ELCH inspection 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.)

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

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,

re- examine the findings as per tap 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.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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b In case of no damage indications during the additional ELCH inspection,

report to AIRBUS within 10 days.

(j) Do the vacuum loss inspection in accordance with the 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 foil on the areas to be inspected.

b Mark the grid of holes on the adhesive foil.

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 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 holes 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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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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 holes 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

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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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before mixing the chosen material.

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

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

in.) and inject the resin through the hole into the cells of the honeycomb

core. Start the injection at the cell bottom and finish when the resin is

leaking out of the inspection hole.

g Close the filled holes with

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).

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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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.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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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 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 51-77-11 Para 5.).

<3> Remove any surplus resin from the border area of the restoration.

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

<4> Clean the restoration areas with

Solvent General

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).

(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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 40

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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 551037-832-203-002 - Do 2 additional special detailed repetitive ELCH

inspections

Manpower Resources

Manhours 0

Minimum number of person 0

Subtask elapsed time 0

Skills NON DESTRUCTIVE

TESTING

References

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

Task 51-10-19-280-801

Task 51-10-26-220-801

Fig. A-GACAA

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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 41

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References

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

times

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.

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) 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 special detailed

repetitive ELCH inspections 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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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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.

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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 43

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FRANCE

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

Fax: +33(0)5 61 93 3500

Mailto: airtac@airbus.com

and in case of damage indications or no damage indications to

Structure Engineering Support

Customer Services - SEES1

AIRBUS Central Entity

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

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

**CONF ALL

D. TEST

**CONF 001

None

**CONF 002

None

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 551037-942-201-001 - 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

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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.

**CONF 002

(1) Subtask 551037-942-201-001 - 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.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

6

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SERVICE BULLETIN

**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_551037_6_AAAA_01_07

Figure A-GAAAA - Sheet 01

Rudder inspection - Flow Chart 1, vacuum loss inspection area 1 and 3

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

6

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 001

DAMAGE ASSESSMENT BY VACUUM LOSS INSPECTION:

IF THE VACUUM LOSS INSPECTION REVEALS DAMAGE AN ADD−ON INSPECTION IN MIDFIELD

DIRECTION ONLY MUST BE PERFORMED TO DEFINE THE OVERALL DAMAGE SIZE.

FOR ADD−ON INSPECTION 1, DRILL ONE ADDITIONAL ROW OF INSPECTION HOLES WITH A PITCH

OF 25.0mm (0.98in.) AND ONE EXTRA HOLE AT EACH END OF THE ROW PARALLEL TO THE DETECTED

LEAKAGE, AS PER SKETCH BELOW. DRILL INSPECTION HOLES WITH DIAMETER 1.5mm (0.06in)

THROUGH THE OUTER SKIN ONLY.

WARNING: DRILL PENETRATION INTO THE SANDWICH STRUCTURE HAS TO BE LIMITED TO

20.0mm (0.79in.), TO PREVENT INNER SKIN DAMAGE.

PERFORM VACUUM LOSS INSPECTION (SAME PROCEDURE AS APPLIED FOR BASIC INSPECTION),

POSITION THE VACUUM CUP IN A WAY THAT ONLY ONE OF THE NEW HOLES IS COVERED BY

THE CUP, DURING EACH MEASUREMENT.

IF NO EXTRA LEAKAGE IS FOUND, DOCUMENT THE DAMAGE, USING THE REPORTING SHEET.

IF MORE LEAKAGES ARE FOUND, PROCEED WITH ADD−ON INSPECTION 2 (AND IF REQUIRED

FURTHER STEPS UNTIL THE WHOLE DAMAGE EXTEND IS DETECTED), USING THE SAME 

PROCEDURE AS DETAILED ABOVE.

NOTE: THE OVERALL DAMAGE LENGTH AND WIDTH IS BOUNDED BY THOSE ROWS OF

INSPECTION HOLES, WHICH DO NOT INDICATE A VACUUM LOSS.

OVERALL LENGTH

OVERALL

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_551037_6_AAAA_02_05

Figure A-GAAAA - Sheet 02

Rudder inspection - Vacuum loss inspection - damage assessment

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

6

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 001

IDENTIFY THE RUDDER SERIAL NUMBER VIA THE PLACARD

ON THE RUDDER SPAR.

IN CASE OF NO EXISTING PLACARD CONTACT AIRBUS

INDICATION

FOUND 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

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_551037_6_AAAA_03_08

Figure A-GAAAA - Sheet 03

Rudder inspection - Flow Chart 2, ELCH inspection area 2

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 48

6

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 001

Inspection Report

Rudder Surface Inspection as per SB in area:

Aircraft type:

MSN:

Rudder S/N:

Rudder P/N:

Inspection date:

Operator:

FC:

FH:

Inspection method

Tap Test 

Thermography

ELCH Inspection

Vacuum Loss

Inspection

Inspection

Inspection

UT Inspection

No findings Findings as detailed

by sketch and photos

No findings Findings as detailed

by sketch and photos

No findings Findings as detailed

by sketch and photos

No findings Findings as detailed

by sketch and photos

No findings Findings as detailed

by sketch and photos

LH RH

Rudder Side

N_SB_551037_6_AAAA_04_04

* use sketch from the TD

Figure A-GAAAA - Sheet 04

Rudder inspection - Reporting sheet

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 49

6

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 001

325EL

325DL

325CL

325BL

325ER

325DR

325CR

325BR

Z325 B

NOTE:

OPEN ACCESS PANEL AS PER AMM 55−33−13 P. BLOCK 201.

CLOSE ACCESS PANEL AS PER AMM 55−33−13 P. BLOCK 201.

POSITION OF

RUDDER S/N PLACARD

AT MSN:

0529, 0532 AND

0537 − 9999

C

POSITION OF

RUDDER S/N PLACARD

AT MSN:

0001 − 0528,

0530 − 0531,

0533 − 0536

C

A

E

D K

MFR

DESCR.

SER. N °

CA CODE

MFG DATE

A/C

PN

NSA9117−63D

A

B

N_SB_551037_6_AAAA_05_04

D5547100XXXXX

TS−XXXX

Figure A-GAAAA - Sheet 05

Rudder inspection - Rudder SN identification

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

6

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 001

TYPICAL TRAILING EDGE

ELCH INSPECTION

FASTENERS

AREA 3

AREA 2

K

MINIMUM DISTANCE FROM EDGE 75.0mm (2.95in.)

NOTE:

L

AREA 1

REINFORCED AREA

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

L

N_SB_551037_6_AAAA_09_04

Figure A-GAAAA - Sheet 09

Rudder inspection - Typical ELCH procedure

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 51

6

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 001

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_551037_6_AAAA_10_02

Figure A-GAAAA - Sheet 10

Rudder inspection - Inspection areas

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 52

6

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 001

IDENTIFY THE RUDDER SERIAL NUMBER VIA THE PLACARD

ON THE RUDDER SPAR.

IN CASE OF NO EXISTING PLACARD CONTACT AIRBUS

REPORT TO AIRBUS

WITHIN 10 DAYS

DO REPETITIVE ELCH INSPECTIONS

AT INTERVALS NOT EXCEEDING

200 DAYS / 1500 FC UNTIL

VACUUM LOSS INSPECTION

IS PERFORMED

INDICATION

FOUND 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_551037_6_AAAA_11_04

Figure A-GAAAA - Sheet 11

Rudder inspection - Flow Chart 3, ELCH inspection area 3

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 53

6

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SERVICE BULLETIN

**CONF 001

N_SB_551037_6_AAAA_13_02

Figure A-GAAAA - Sheet 13

Rudder inspection - Rudder skin thickness LH

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 54

6

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 001

N_SB_551037_6_AAAA_14_02

Figure A-GAAAA - Sheet 14

Rudder inspection - Rudder skin thickness RH

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 55

6

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 001

AREA 1

(REINFORCED AREA)

AT THE LATEST OF THESE TWO CONDITIONS:

− BEFORE THE RUDDER REACHES 17000 FC

 SINCE NEW, WITHOUT EXCEEDING 20 MONTHS

 FROM ISB REV.00 ISSUE DATE.

OR

− WITHIN 200 DAYS FROM ISB REV.00 ISSUE DATE.

AREA 2

(TRAILING EDGE AREA)

WITHIN 20 MONTH FROM

ISB REV.00 ISSUE DATE

AREA 3

(OTHER AREAS)

WITHIN 20 MONTH FROM 

ISB REV.00 ISSUE DATE

APPLY ACTIONS

ACCORDING FLOW CHART

SHOWN ON FIG. A−GAAAA, 

SHEET 01

ACCOMPLISHMENT OF THE ACTIONS

ACCORDING FLOW CHART SHOWN ON

FIG. A−GAAAA, SHEET 01, 

CANCELS THE INITIAL OR REPETITIVE 

ACTIONS AS PER FLOW CHART SHOWN ON

FIG. A−GAAAA, SHEET 11.

AND

APPLY ACTIONS

ACCORDING FLOW CHART

SHOWN ON FIG. A−GAAAA, 

SHEET 03

APPLY ACTIONS

ACCORDING FLOW CHART

SHOWN ON FIG. A−GAAAA, 

SHEET 01

APPLY ACTIONS

ACCORDING FLOW CHART

SHOWN ON FIG. A−GAAAA, 

SHEET 11

NOTE:

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.

N_SB_551037_6_AAAA_15_01

Figure A-GAAAA - Sheet 15

Rudder inspection - General overview of the compliance times

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 56

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

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

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_551037_6_ACAA_01_09

Figure A-GACAA - Sheet 01

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 57

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

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_551037_6_ACAA_02_07

Figure A-GACAA - Sheet 02

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 58

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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_551037_6_ACAA_03_07

Figure A-GACAA - Sheet 03

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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 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_551037_6_ACAA_04_07

Figure A-GACAA - Sheet 04

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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 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_551037_6_ACAA_05_07

Figure A-GACAA - Sheet 05

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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 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_551037_6_ACAA_06_06

Figure A-GACAA - Sheet 06

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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 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_551037_6_ACAA_07_06

Figure A-GACAA - Sheet 07

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

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_551037_6_ACAA_08_07

Figure A-GACAA - Sheet 08

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

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_551037_6_ACAA_09_04

Figure A-GACAA - Sheet 09

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 65

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_551037_6_ACAA_10_05

Figure A-GACAA - Sheet 10

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

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_551037_6_ACAA_11_04

Figure A-GACAA - Sheet 11

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

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_551037_6_ACAA_12_04

Figure A-GACAA - Sheet 12

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

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_551037_6_ACAA_13_04

Figure A-GACAA - Sheet 13

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

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_551037_6_ACAA_14_04

Figure A-GACAA - Sheet 14

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

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_551037_6_ACAA_15_04

Figure A-GACAA - Sheet 15

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

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

X

N_SB_551037_6_ACAA_16_04

Figure A-GACAA - Sheet 16

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

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_551037_6_ACAA_17_04

Figure A-GACAA - Sheet 17

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

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_551037_6_ACAA_18_04

Figure A-GACAA - Sheet 18

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

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_551037_6_ACAA_23_04

X

Figure A-GACAA - Sheet 23

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

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_551037_6_ACAA_24_02

Figure A-GACAA - Sheet 24

Rudder SN - MSN reference list

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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 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_551037_6_AEAA_01_01

Figure A-GAEAA - Sheet 01

ELCH inspection - Inspection areas

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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 002

NOTE:

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

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

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

AS PER NTM 51−10−26

N_SB_551037_6_AEAA_02_04

Figure A-GAEAA - Sheet 02

ELCH inspection - Flow Chart

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 78

6

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 002

TYPICAL TRAILING EDGE

ELCH INSPECTION

FASTENERS

AREA 3

AREA 2

MINIMUM DISTANCE FROM EDGE 75.0mm (2.95in.)

NOTE:

AREA 1

REINFORCED AREA

A

75.0 mm

(2.95 in)

50.0 mm

(1.97 in)

75.0 mm

(2.95 in)

50.0 mm

(1.97 in)

50.0 mm

(1.97 in)

AREA 3 AREA 2

A

N_SB_551037_6_AEAA_03_02

Figure A-GAEAA - Sheet 03

ELCH inspection - Typical ELCH procedure

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 79

6

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 002

Inspection Report

Rudder Surface Inspection as per SB in area:

Aircraft type:

MSN:

Rudder S/N:

Rudder P/N:

Inspection date:

Operator:

FC:

FH:

Inspection method

ELCH Inspection No findings Findings as detailed

by sketch and photos

LH RH

Rudder Side

N_SB_551037_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.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 80

6

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 002

325EL

325DL

325CL

325BL

325ER

325DR

325CR

325BR

Z325 B

NOTE:

OPEN ACCESS PANEL AS PER AMM 55−33−13 P. BLOCK 201.

CLOSE ACCESS PANEL AS PER AMM 55−33−13 P. BLOCK 201.

POSITION OF

RUDDER S/N PLACARD

AT MSN:

0529, 0532 AND

0537 − 9999

C

POSITION OF

RUDDER S/N PLACARD

AT MSN:

0001 − 0528,

0530 − 0531,

0533 − 0536

C

A

E

D K

MFR

DESCR.

SER. N °

CA CODE

MFG DATE

A/C

PN

NSA9117−63D

A

B

N_SB_551037_6_AEAA_05_01

D5547100XXXXX

TS−XXXX

Figure A-GAEAA - Sheet 05

ELCH inspection - Rudder SN identification

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 81

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 002

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

N_SB_551037_6_AEAA_06_00

Figure A-GAEAA - Sheet 06

ELCH inspection - Overview of the compliance times

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

REVISION No.: 01 - Jul 02/10 Page: 82

6

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@A318/A319/A320/A321

SERVICE BULLETIN

REPORTING SHEET

TITLE: STABILIZERS - RUDDER - A319 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.: A320-55-1037

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

6

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@A318/A319/A320/A321

SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4 3 2 1

- Quality rating of the Accomplishment Instructions 4 3 2 1

- Quality rating of the Illustrations 4 3 2 1

- Is this SB easy to understand ? Y / N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1037

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

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