# @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 -A318 and A321 RUDDER DEBOND INSPECTION MODIFICATION No.: None This page transmits Revision No.01 of Service Bulletin No.A320-55-1036 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 551036- 832-848-001-Inspection Subtask 551036-941-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 1 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 551036-941-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R
Subtask 551036-832-201-002 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 551036-832-202-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED NOTE UPDATED REFERENCES UPDATED R

Subtask 551036-832-203-002 SUBTASK SOLUTION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED NOTE UPDATED R

Subtask 551036-942-201-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R
Subtask 551036-942-201-001 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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 2 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Fig. A-GACAA Sheet 23 SHEET ADDED N Fig. A-GACAA Sheet 24 SHEET ADDED N Fig. A-GAEAA FIGURE SOLUTION UPDATED R Fig. A-GAEAA Sheet 02 SHEET UPDATED R Fig. A-GAEAA Sheet 03 SHEET UPDATED R Fig. A-GAEAA Sheet 06 SHEET ADDED N FILLING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS No previous revision REVISION SEQUENCE ORIGINAL: Feb 17/10 REVISION No. : 01 - Jul 02/10

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 3 6

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

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

This Page Intentionally Left Blank

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 4 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft. ATA SYSTEM: 55 

# TITLE: STABILIZERS - RUDDER -A318 and A321 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 A318 and A321 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 DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 1 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY
EVALUATION TABLE POTENTIAL AD YES A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO NOTE(1): Service Bulletin 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) :

15V 39Z 42V 51U 64U 79W 99W AAF AAR ABQ ACA AEE AFL AFR AJM AMU AUA AZA BAW BER BIE BMA BMM CCA CES CSA CSC CSN DLH EIN EZY FFT FHY FIN GFA HDA HVN IAC IBE IRM JAG JKK JST KFR KKK KNE KYV KZR LAN LBT LTU LVG MEA MLM MON MSR MXA NKS NLY NVR OHY QTR RJA RKM ROT SAS SHY SVR SVW SWR TAI TAM TAP TCX THY TNA TOM TRK USA VKG VUN 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 YES EQUIPMENT NO

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 2 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY
HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 551036-832-848-001: Inspection TOTAL MANHOURS 2.00 **CONF 002 Task 551036-832-848-001: Inspection TOTAL MANHOURS 2.00 APPENDICES **CONF ALL None

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 3 6

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

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

This Page Intentionally Left Blank

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 4 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 ATA SYSTEM: 55 

# TITLE: STABILIZERS - RUDDER -A318 and A321 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 318-111 318-112 318-121 321-111 321-112 321-131 321-211 321-212 321-213 321-231 321-232 (2) Effectivity by MSN 0364 0385 0412 0434 0458 0468 0473-0474 0477 0484 0488 0493-0495 0498 0502 0505 0509 0513-0522 0524 0526 0529 0532 0535 0538 0541 0544 0550 0552 0555 0557 0560 0563-0564 0567 0570 0576 0581 0583 0586 0591 0593 0595 0597 0599 0604 0606 0614 0620 0631 0633 0642 0652 0663-0664 0666 0668 0674-0675 0677 0680 0684 0687 0692 0699 0715 0725 0731 0746 0761 0765 0771 0775 0777 0781 0787 0792 0796 0802 0806 0808 0810-0811 0815 0819 0823 0827 0835 0841 0848 0852 0855 0864 0878 0887 0891 0901 0908 0915 0920 0926 0935 0940-0941 0954 0956 0959 0961 0963 0968 0970 0974 0983 0987 0991 0993 0995 1004 1006 1008 1012 1015 1017 1021 1023-1024 1027 1042 1045 1060 1080 1094 1133 1144 1153 1161 1174 1185 1188 1195 1199 1202 1204 1207 1214 1218-1220 1227 1233 1238 1241 1250 1260 1273 1276 1293 1299 1307 1333 1356 1366 1399 1403 1408 1412 DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 1 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

1417 1421 1425 1428 1431 1433 1436 1438 1442 1447 1451 1455 1458 1462 1465 1472 1476 1481 1487 1492 1496 1499 1503 1511 1517 1519 1521 1525 1531 1536 1539 1554 1572 1587 1596 1599 1602 1607 1611 1614 1619 1623 1629 1632 1636 1638 1642 1651 1658 1660 1666 1670 1675 1681 1690-1691 1695 1701 1704 1707 1711 1713 1716 1720 1724 1726 1734 1748 1763 1772 1776 1783 1788 1794 1798 1807 1811 1817 1836 1843 1848 1850 1859 1869 1878 1881 1887 1905 1921 1926 1928 1932 1939 1941 1946 1950 1953 1956 1960 1966-1967 1970 1972 1974 1977-1978 1984 1988 1991 1994-1995 2005 2017 2021 2035 2041 2045 2051 2055 2059-2060 2064 2067 2071 2076 2080-2081 2100 2105 2107 2109-2110 2115 2117 2190 2208 2211 2216 2218 2220 2226 2234 2247 2255 2261 2267 2270 2276 2290 2303 2305 2309 2315 2317 2320 2323-2324 2328 2330 2333 2337 2342 2344 2350-2351 2357-2358 2363 2367 2377 2381 2394 2410 2462 2472 2476 2480 2488 2521 2523 2530 2536 2543-2544 2549 2552-2553 2563 2575 2582 2590 2599 2601 2610 2653 2682 2686-2687 2707 2713 2726 2730 2736 2741 2750 2756 2759 2767 2793 2799 2809 2823 2862 2868 2882 2895 2903 2910 2912 2916 2918-2919 2927 2931 2933 2936 2951 2955 2957 2965 2967 2971-2972 2974 2996 2999 3001 3005 3009 3013 3015 3022 3030 3034 3038 3051 3062 3067 3070 3075 3081 3098 3100 3106 3110 3112 3120 3126 3130 3146 3163 3191 3198 3207 3212 3214 3216-3217 3220 3222 3225 3229 3233 3235 3238 3241 3247 3249 3251 3254 3262 3265 3267 3274 3283 3290 3294 3297 3302 3307 3315 3322 3326 3329 3333-3334 3339-3340 3350 3355 3360 3363 3367 3369 3371-3372 3382 3387 3390 3397 3399 3401 3405 3419 3429 3434 3438 3441 3458-3459 3462 3469 3471 3493 3498 3504 3507 3509 3512 3522-3523 3525 3527 3530 3539 3546 3552 3557 3566 3573 3575 3583-3585 3587 3592-3593 3600 3602 3606 3612 3617 3619 3623 3625 3629 3633 3635-3637 3639 3642 3645 3653 3655 3665 3669 3673 3678 3681-3682 3688 3708 3712 3717 3722 3725 3730 3737-3738 3740 3749 3751-3752 3761 3764 3766 3784 3792 3796 3806 3814 3816 3820 3830 3847 3858 3862 3864 3867 3869 3878-3879 3881 3884 3886 3893 3899 3916 3920 3924 3926 3928 3930 3932 3934 3936 3938 3940 3944 3948 3951 3955 3960 3964 3966 3969 3973 3977 3981 3985 3987 3989 3993 3996 (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 15V 3333 39Z 0956 42V 3985 51U 3617 64U 3932 79W 3751 99W 3038 AAF 0808 0823 1006 1451 AAR 0802 1227 1356 1511 1636 1734 2041 2045 2110 2226 2247 2290 3297 ABQ 1008 1199 1218 ACA 1602 1611 1623 1632 1638 1726 1748 1772 1783 1811 AEE 3462 3527 3820 3878
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 2 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

OPERATOR MSN AFL 2330 2337 2342 2903 2912 2957 2965 3191 3267 3334 AFR 0498 0509 0521 0529 0544 0777 0796 1133 1299 1476 1658 1691 1859 2035 2059 2071 2081 2100 2109 2317 2344 2350 2582 2601 2686 2750 2918 2951 2967 2972 3009 3051 3098 3372 3399 3401 3419 3441 3814 3884 3930 AJM 1503 AMU 0557 0597 0620 0631 0908 1850 1926 AUA 0552 0570 0581 0920 0935 1458 AZA 0434 0477 0488 0494 0495 0513 0514 0515 0516 0524 0526 0532 0576 0583 0586 0593 0599 0765 0819 0848 0940 0959 1220 BAW 2305 2320 2323 2324 2351 2363 2536 3081 3235 3254 3290 BER 1629 1966 1988 1994 2005 3708 3749 BIE 0517 0519 0535 0642 0827 0891 2707 BMA 0835 1174 1690 1711 2190 2653 2799 3512 3926 BMM 2064 2076 2726 3070 CCA 3307 3329 3523 3623 3653 3655 3665 3678 3722 3725 3766 3806 3940 3973 CES 2309 2315 2543 2549 2882 2895 3233 3247 3249 3262 3471 3593 3612 3639 3682 3969 CSA 0674 0684 CSC 0550 0591 0878 0915 1060 1293 3583 3730 3893 3996 CSN 1596 1614 1776 1788 1974 1995 2067 2080 2521 2530 2713 2741 2759 2767 2809 2936 2971 3067 3075 3112 3217 3241 3251 3459 3493 3507 3552 3566 3587 3645 3681 3764 3784 3847 3867 3920 3934 3938 3951 3981 DLH 0412 0458 0468 0473 0474 0484 0493 0502 0505 0518 0560 0563 0564 0567 0595 0652 0692 0699 0887 0901 1080 1161 1188 1214 1260 1273 3265 3339 3360 3387 3434 3592 3625 3864 3936 3987 EIN 0815 0841 0926 0991 1023 1094 EZY 1869 2462 2682 3106 FFT 1660 1939 1991 2017 2051 2218 2276 3110 3163 FHY 0771 0855 FIN 0941 0961 1185 1241 1978 2208 GFA 0675 0761 HDA 0633 0993 1024 1695 1984 2021 HVN 2255 2261 2267 2303 2480 2974 3005 3013 3022 3198 3315 3355 3600 3737 3862 3964 3966 IAC 3130 3146 3212 3326 3340 3367 3498 3557 3573 3619 3752 3792 3955 IBE 1021 1027 1554 1572 1681 1716 1836 2115 2220 2270 2357 2381 2472 2488 2563 2599 2736 2756 2996 IRM 1202 JAG 3886 JKK 1276 1333 1366 1843 1946 JST 1195 1408 3717 3899 3916 3948 KFR 2916 2919 2927 2933 3034 3120 3302 3322 KKK 060406140968 0974 1438 DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 3 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

OPERATOR MSN KNE 3238 3530 KYV 2117 KZR 1042 1204 LAN 3001 3030 3062 3214 3216 3371 3390 3438 3469 3509 3585 3602 3606 3635 3642 LBT 0970 0995 LTU 1607 LVG 0792 1950 1970 MEA 1878 1953 1956 1967 1977 2055 MLM 2910 3363 MON 0864 0983 1015 1045 1153 1207 1428 1433 1707 1763 1794 1941 2105 2234 3546 3575 MSR 0680 0687 0715 0725 MXA 2328 2333 2358 2367 2377 2394 2523 2544 2552 2575 NKS 2476 2590 NLY 3504 3830 NVR 2211 2216 2410 OHY 0364 0385 0663 0668 0787 0954 0963 1004 1421 QTR 1487 1928 2107 3274 3369 3397 3636 3669 RJA 2730 2793 3458 3522 RKM 1599 ROT 2931 2955 3220 3225 SAS 1587 1619 1642 1675 1798 1807 1817 1848 SHY 0811 1670 SVR 1012 1720 SVW 3100 SWR 0520 0522 0541 0664 0987 1144 TAI 2553 2610 2687 2862 3869 TAM 3222 3229 3294 3761 3816 TAP 1307 1399 1713 TCX 0677 1238 1250 2060 THY 0806 0810 1219 1233 2823 2868 2999 3015 3126 3207 3283 3350 3382 3405 3429 3525 3539 3637 3673 3688 3738 TNA 0538 0555 0606 0731 0746 TOM 0781 0852 TRK 0666 0775 1905 USA 1403 1412 1417 1425 1431 1436 1442 1447 1455 1462 1465 1472 1481 1492 1496 1499 1517 1519 1521 1525 1531 1536 1539 1651 1666 1701 1704 1724 3584 3629 3633 3712 3740 3796 3858 3879 3881 3924 3928 3944 3960 3977 3989 3993 VKG 1881 1887 1921 1932 1960 1972 VUN 1017

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 4 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
(4) Configuration by MSN MSN CONFIGURATION 0364 0385 0412 0434 0458 0468 0473 0474 0477 0484 0488 0493 0494 0495 0498 0502 0505 0509 0513 0514 0515 0516 0517 0518 0519 0520 0521 0522 0524 0526 0529 0532 0535 0538 0541 0544 0550 0552 0555 0557 0560 0563 0564 0567 0570 0576 0581 0583 0586 0591 0593 0595 0597 0599 0604 0606 0614 0620 0631 0633 0642 0652 0663 0664 0666 0668 0674 0675 0677 0680 0684 0687 0692 0699 0715 0725 0731 0746 0761 0765 0771 0775 0777 0781 0787 0792 0796 0802 0806 0808 0810 0811 0815 0819 0823 0827 0835 0841 0848 0852 0855 0864 0878 0887 0891 0901 0908 0915 0920 0926 0940 0941 0954 0956 0959 0961 0963 0968 0970 0974 0983 0987 0991 0993 0995 1004 1006 1008 1012 1015 1017 1021 1023 1024 1027 1042 1045 1060 1080 1094 1133 1144 1153 1161 1174 1185 1188 1195 1199 1202 1204 1207 1214 1218 1219 1220 1227 1233 1238 1241 1250 1260 1273 1276 1293 1299 1307 1333 1356 1366 1399 1403 1408 1412 1417 1421 1425 1428 1431 1433 1436 1438 1442 1447 1451 1455 1458 1462 1465 1472 1476 1481 1487 1492 1496 1499 1503 1511 1517 1519 1521 1525 1531 1536 1539 1554 1572 1587 1596 1599 1602 1607 1611 1614 1619 1623 1629 1632 1636 1638 1642 1651 1658 1660 1666 1670 1675 1681 1690 1691 1695 1701 1704 1707 1711 1713 1716 1720 1724 1726 1734 1748 1763 1772 1776 1783 1788 1794 1798 1807 1811 1817 1836 1843 1848 1850 1859 1869 1878 1881 1887 1905 1921 1926 1928 1932 1939 1941 1946 1950 1953 1956 1960 1966 1967 1970 1972 1974 1977 1978 1984 1988 1991 1994 1995 2005 2017 2021 2035 2041 2045 2051 2055 2059 2060 2064 2067 2071 2076 2080 2081 2100 2105 2107 2109 2110 2115 2117 2190 2208 2211 2216 2218 2220 2226 2234 2247 2255 2261 2267 2270 2276 2290 2303 2305 2309 2315 2317 2320 2323 2324 2328 2330 2333 2337 2342 2344 2350 2351 2357 2358 2363 2367 2377 2381 2394 2410 2462 2472 2476 2480 2488 2521 2523 2530 2536 2543 2544 2549 2552 2553 2563 2575 2582 2590 2599 2601 2610 2653 2682 2686 2687 2707 2713 2726 2730 2736 2741 2750 2756 2759 2767 2793 2799 2809 2823 2862 2868 2882 2895 2903 2910 2912 2916 2918 2919 2927 2931 2933 2936 2951 2955 2957 2965 2967 2971 2972 2974 2996 2999 3001 3005 3009 3013 3015 3022 3030 3034 3038 3051 3062 3067 3070 3075 3081 3098 3100 3106 3110 3112 3120 3126 3130 3146 3163 3191 3198 3207 3212 3214 3216 3217 3220 3222 3225 3229 3233 3235 3238 3241 3247 3249 3251 3254 3262 3265 3267 3274 3283 3290 3294 3297 3302 3307 3315 3322 3326 3329 3333 3334 3339 3340 3350 3355 3360 3363 3367 3369 3371 3372 3382 3387 3390 3397 3399 3401 3405 3419 3429 3434 3438 3441 3458 3459 3462 3469 3471 3493 3498 3504 3507 3509 3512 3522 3523 3525 3527 3530 3539 3546 3552 3557 3566 3573 3575 3583 3584 3585 3587 3592 3593 3600 3602 3606 3612 3617 3619 3623 3625 3629 3633 3635 3636 3637 3639 3642 3645 3653 3655 001

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 5 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

MSN CONFIGURATION 3665 3669 3673 3678 3681 3682 3688 3708 3712 3717 3722 3725 3730 3737 3738 3740 3749 3751 3752 3761 3764 3766 3784 3792 3796 3806 3814 3816 3820 3830 3847 3858 3862 3864 3867 3869 3878 3879 3881 3884 3886 3893 3899 3916 3920 3924 3926 3928 3930 3932 3934 3936 3938 3940 3944 3948 3951 3955 3960 3964 3966 3969 3973 3977 3981 3985 3987 3989 3993 3996 001

0935 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 As required 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 A318 and A321 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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 6 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
- 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 551036-832-848-001: 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 551036-832-848-001: Inspection (1) Do 2 additional repetitive special detailed inspections (ELCH) **CONF ALL E. COMPLIANCE (1) Classification RECOMMENDED: Service Bulletin recommended to be accomplished to prevent significant operational disruptions. (2) Accomplishment Timescale **CONF 001 Table 1. Config. 001 - Rudder special detailed inspection on aircraft with rudders to be inspected on Area 1 (refer to Figure A-GAAAA, Sheet 10). Area to be inspected Condition Action Compliance time Repetitive interval Area 1 N/A Identify the Serial Number of the installed rudder Within 200 days from SB Rev. 00 issue date N/A

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 7 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

Area to be inspected Condition Action Compliance time Repetitive interval Area 1 N/A Vacuum loss inspection in accordance with Subtask 551036-832-202-001At the latest of these 2 conditions: -Before the rudder reaches 17000 FC since new, without exceeding 20 months from SB Rev. 00 issue date OR, -Within 200 days from SB Rev. 00 issue date N/A

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

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.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 8 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

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.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 9 6

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

# @A318/A319/A320/A321 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 551036-832-202-001Within 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.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 10 6

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

# @A318/A319/A320/A321 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 551036-832-202-001At the latest of these 2 conditions: -Before the rudder reaches 17000 FC since new, without exceeding 20 months from SB Rev. 00 issue date OR, -Within 200 days from SB Rev. 00 issue date N/A

Area 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 each 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 551036-832-202-001Within 20 months from SB Rev. 00 issue date N/A

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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 11 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

Area to be inspected Condition Action Compliance time Repetitive interval Area 3 No damage indications found during vacuum loss inspection 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

Within 20 months after the issue of the Rev. 00 of this SB 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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 12 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 13 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

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 551036-832-203-002N/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 underEASA Design Organisation ApprovalNo. EASA21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. **CONF 001 Task 551036-832-848-001: Inspection Get Access 1.00

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 14 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
Task 551036-832-848-001: 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 551036-832-848-001: Inspection Get Access 1.00 On Aircraft Do 2 additional repetitive special detailed inspections (ELCH) 0 Close-Up 1.00 TOTAL MANHOURS 2.00 NOTE: Manhours and elapsed time depend on the size of the area to be inspected. Find below a table with the information for the manhours, elapsed time and number of persons per 1 m (39.37 in.) for the different inspection procedures: Steps Manhours Elapsed time Number of persons Get access 1.00 0.75 2 ELCH inspection 0.75 0.75 1 Tap test inspection 0.25 0.25 1 Close-up 1.00 0.75 2

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 15 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**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.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 16 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses None This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign. (2) Price and Availability None B. INDUSTRY SUPPORT INFORMATION AIRBUS will credit the manhours indicated in this Service Bulletin for inspections that are performed on aircraft in warranty at the time of such inspection. Credit will be at the operator’s agreed in-house warranty labor rate. Claims for labor allowance should be received not later than 90 days after completion of the last affected warranted aircraft. This Service Bulletin is subject of specific support provided by AIRBUS. For details please contact your Customer Support Director. For the organisation of this retrofit, operators are kindly requested to contact AIRBUS retrofit management department. AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX France Tel : (33) 5 67 19 06 22 E-mail : monitored.retrofit@airbus.com Fax : (33) 5 61 93 27 45 C. LIST OF COMPONENTS No Kit D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLD01 ITEMDESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Self-Adhes. Disks 05-052 As required Self Adhesive Aluminium Tape 08-052 As required Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required Wet Lay Up Resin 20-022 As required (2) Components None
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 17 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
(3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability None (2) Tools To find the correct tool-PN for the different inspection tools, refer to the subsequent table: Inspection tool PN NTM reference ELCH Elasticity Laminate 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.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 18 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS Task 551036-832-848-001 - 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 551036-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 19 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
Material necessary to do the job Consumable CMLD01 ITEMDESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required References Aircraft Maintenance Manual (AMM) 06-41-55, Page Block 001 Consumable Material List (CML) (a) For location of the access panels, (Refer to AMM 06-41-55, Page Block 001). (b) For the specification of consumable materials (Mat. No.) that you must use in this Service Bulletin, (Refer to Consumable Material List (CML)). (c) Clean the areas to be inspected with Solvent General Purpose 11-026 As required

Lint-Free Cotton Cloth 19-003 As required (2) Subtask 551036-839-201-001 - 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 551036-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLD01 ITEMDESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required References Aircraft Maintenance Manual (AMM) 06-41-55, Page Block 001
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 20 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

References Consumable Material List (CML) (a) For location of the access panels, (Refer to AMM 06-41-55, Page Block 001). (b) For the specification of consumable materials (Mat. No.) that you must use in this Service Bulletin, (Refer to Consumable Material List (CML)). (c) Clean the areas to be inspected with Solvent General Purpose 11-026 As required

Lint-Free Cotton Cloth 19-003 As required (2) Subtask 551036-839-201-001 - 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 551036-941-201-001 - 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.
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 21 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
(c) In the cockpit, put warning notices in position to tell persons not to operate the flight controls. (d) Open, safety and tag the circuit breakers as given in the rudder inspection/check Job Set-up procedure (Refer to AMM Task 55-40-00-210-001). (e) Depressurize the Green Hydraulic System (Refer to AMM Task 29-10-00-864-001). (f) Depressurize the Yellow Hydraulic System (Refer to AMM Task 29-10-00-864-002) (g) Depressurize the Blue Hydraulic System (Refer to AMM Task 29-10-00-864-003) (h) Put a warning notice in the cockpit to tell persons not to pressurize the hydraulic systems. (i) Put access platform(s) in position at the rudder. (j) To open the panels, (Refer to AMM Task 55-33-13-010-002). **CONF 002 (1) Subtask 551036-941-201-001 - 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)
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 22 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
(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 panels, (Refer to AMM Task 55-33-13-010-002). **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 551036-832-202-001 - Do therudder special detailed inspection on aircraft with rudders which are affected by hot-curing rework outside autoclave in production Manpower Resources Manhours 0 Minimum number of person 0 Subtask elapsed time 0 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLD01 ITEMDESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Self-Adhes. Disks 05-052 As required Self Adhesive Aluminium Tape 08-052 As required Solvent General Purpose 11-026 As required Wet Lay Up Resin 20-022 As required 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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 23 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

References 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 Figure 14 51-77-11 Para5.D.(1).(i) Fig. A-GAAAA Rudder inspection Sheet 01 - Flow Chart 1, vacuum loss inspection Sheet 02 - Vacuum loss inspection Sheet 03 - Flow Chart 2, ELCH inspection 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 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 onFig. A-GAAAA Sheet 05

. (b) If you do not find an SN placard on the rudder, contact AIRBUS for further instructions.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 24 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
(c) Compare the rudder SN with the rudder SNs in the rudder SN - MSN reference list Fig. A-GACAA Sheet 01thruFig. A-GACAA Sheet 24

. NOTE: The rudder SN-MSN relationship is provided for information only and is based on the information available at AIRBUS at time of SB issue. Any changes resulting from movement from an aircraft to another or from spare is not reflected, it is the responsibility of the operator to assess the rudder SN-MSN relationship. 1 If you find a different SN against the MSN as detailed in the rudder SN - MSN reference list, contact AIRBUS for further instructions. 2 If the rudder SN is not part of the rudder SN - MSN reference list, refer to the Close-up para 3.E. No further action is necessary. 3 If the rudder is part of the rudder SN - MSN reference list with the same indicated MSN, continue with the below instructions. (d) The Technical Disposition (TD) details the location of the reworked area to be inspected and includes information about the vacuum loss inspection holes, if necessary. 1 For the definition of the areas to be inspected, refer to the rudder SN - MSN reference listFig. A-GACAA Sheet 01thruFig. A-GACAA Sheet 24to find the MSN related Technical Disposition (TD) No. 2 To get the TD, refer to the SB BOOKLET-link on the index page of this Service Bulletin on the Air@Nav Engineering page in AIRBUS WORLD and use ’SB BOOKLET-TD-K45-S2-XXXXX’. For additional information, refer to SBIT SEMB 914.0808/09 3 Inspection method for reworked areas: - For reworked area astride AREA 2 and AREA 3, if TD provides vacuum loss hole location then rework must be treated as if in AREA 3 only. - For reworked area astride AREA 2 and AREA 3, if TD does not provide vacuum loss hole location then rework must be treated as if in AREA 2 only. - For reworked area astride AREA 1 and AREA 3, the rework must be treated as if in AREA 1 only. (e) If there are only areas on the trailing edge shown as ’AREA 2’ on theFig. AGAAAA Sheet 10, to be inspected, refer to Para (h). (f) If there are only other areas, shown as ’AREA 3’ on theFig. A-GAAAA Sheet 10, to be inspected, refer to Para (i).

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 25 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
(g) If there are reinforced areas, shown as ’AREA 1’ on theFig. A-GAAAA Sheet 10, to be inspected, do the subsequent inspection in accordance with the Flow ChartFig. A-GAAAA Sheet 01andFig. A-GAAAA Sheet 02: 1 Do the vacuum loss inspection (Refer toNTM Task 51-10-28-220-801).
a Temporarily install adhesive 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 vacuum loss inspection holes with DIA 1.5 mm (0.06 in.) through the outer skin only. d Do the Vacuum loss inspection (Refer to NTM Task 51-10-28-220-801).
e In case of damage indications, contact AIRBUS on the basis of a detailed referenced damage report for further instructions before next flight. f In case of no damage indications, close the vacuum loss inspection holes as detailed in the subsequent instructions and report the result to AIRBUS within 10 days. 2 Temporary restoration of the vacuum loss inspection 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 ordisks, close theholes again with Self Adhesive Aluminium Tape 08-052 As required

or Self-Adhes. Disks 05-052 As required d This temporary restoration must be replaced by the permanent restoration after 4500 FC latest.
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 26 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

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 toFig. A-GAAAA Sheet 13andFig. A-GAAAA Sheet 14

. <2> If the skin thickness of the affected areas, defined by the TD, does not exceed 1.5 mm (0.06 in.), do a thermography inspection as detailed in NTM Task 51-10-25-290-801 or NTM Task 51-10-25-290-802 AND/OR If the skin of the affected areas, defined by the TD, is thicker than 1.5 mm (0.06 in.), do an ultrasound inspection as detailed in NTM Task 51-10-24-270-801. NOTE: During the ultrasound inspection, the vacuum loss inspection holes must be closed with thin adhesive tape (Material No 08-052 - basic) to prevent couplant ingress into the holes. b In case of damage indications contact AIRBUS for further instructions before next flight.
c Prepare and dry the restoration area (Refer to SRM 51-77-11 Para 4.M.(2)). d Prepare Wet Lay Up Resin 20-022 As required (Refer to SRM 51-77-11 Para 4.A.(3)). NOTE: The data sheets for each adhesive, resin or low density 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).
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 27 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

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 toSRM 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 toFig. A-GAAAA Sheet 13andFig. A-GAAAA Sheet 14

.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 28 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
<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.
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.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 29 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

g Close the filled holes with a self adhesive tape. h Let the resin cure for a minimum of 12 hours at room temperature. If the room temperature is below 18 ̊C (64F), extend the curing time and perform a gelation test outside the restoration area. After resin gelation plus 4 h, continue with the subsequent steps: <1> Remove the self adhesive tape from the restoration areas. <2> Inspect the restoration (Refer to SRM 51-77-10 Para 5.). <3> Remove any surplus resin from the border area of the restoration. Use abrasive cloth. Start with 280 grade and finish with 400 grade. <4> Clean the restoration areas with Solvent General Purpose 11-026 As required (Refer to SRM 51-77-11 Para 4.E). <5> Restore the surface protection (Refer to SRM 51-75-12). (h) If there are areas on the trailing edge, shown as ’AREA 2’ on theFig. A-GAAAA Sheet 10, to be inspected, do a repetitive special detailed inspection (ELCH) in accordance with the Flow ChartFig. A-GAAAA Sheet 03: 1 Do the ELCH inspection (Refer toNTM Task 51-10-26-220-801).
a For the ELCH inspection behind the fasteners, use one grid line with a distance of 50 mm (1.97 in.) between the inspection points, as shown on Fig. A-GAAAA Sheet 09, View K and View L, area 2. <1> The assessment criteria for the ELCH inspection behind the fasteners are: Yellow value 0.30 mm (0.012 in.) Red value 0.40 mm (0.016 in.) For the adjustment of the ELCH, refer to NTM Task 51-10-26-220-801. b If the ELCH inspection extends ahead of the fasteners, use an inspection grid of 50 mm X 50 mm (1.97 in.) between the inspection points, as shown onFig. A-GAAAA Sheet 09, View K and View L, area 3. <1> The assessment criteria for the ELCH inspection ahead of the fasteners are: Yellow value 0.25 mm (0.010 in.)

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 30 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
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), and contact AIRBUS for further instructions before next flight. 3 In case of no damage indications, report to AIRBUS within 10 days and do 2 additional ELCH inspections at intervals not exceeding 4500 FC and not less than 4000 FC from the last inspection, refer toFig. A-GAAAA Sheet 03

. a In case of damage indications during the additional ELCH inspection, reexamine the findings as per tap test inspection (Refer to NTM Task 51-10-03-280-801 or NTM Task 51-10-19-280-801), and contact AIRBUS for further instructions before next flight. b In case of no damage indications during the additional ELCH inspections, report to AIRBUS within 10 days. (i) If there are other areas, shown as ’AREA 3’ on theFig. A-GAAAA Sheet 10, to be inspected, do a repetitive special detailed inspection (ELCH) in accordance with the Flow ChartFig. A-GAAAA Sheet 11within 200 days after the issue of The Rev. 00 of this Service Bulletin, and do the vacuum loss inspection within 20 months after the issue of the Rev. 00 of this Service Bulletin. For the vacuum loss inspection, refer to Para (j). NOTE: The ELCH inspection is not required if the vacuum loss inspection is done within 200 days after the issue of the Rev. 00 of this Service Bulletin. 1 To do the ELCH inspection, refer to NTM Task 51-10-26-220-801.
a For the inspection in front of the fasteners, use up to 3 grid lines with a distance of 50 mm (1.97 in.) between the inspection points, as shown on Fig. A-GAAAA Sheet 09, View K and View L, area 3. <1> The assessment criteria for the ELCH inspection in front of the fasteners are: Yellow value 0.25 mm (0.010 in.) Red value 0.35 mm (0.014 in.) For the adjustment of the ELCH, refer to NTM Task 51-10-26-220-801.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 31 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

2 In case of damage indications, re- examine the findings as per tap test inspection (Refer to NTM Task 51-10-03-280-801 or NTM Task 51-10-19-280-801), and contact AIRBUS for further instructions before next flight. 3 In case of no damage indications, report to AIRBUS within 10 days and do repetitive ELCH inspections at intervals not exceeding 1500 FC or 200 days, whichever occurs first, until the vacuum loss inspection is performed.
a In case of damage indications during the repetitive ELCH inspections, reexamine the findings as per tap test inspection (Refer to NTM Task 51-10-03-280-801 or NTM Task 51-10-19-280-801), and contact AIRBUS for further instructions before next flight. b In case of no damage indications during the repetitive ELCH inspections, report to AIRBUS within 10 days. (j) Do the vacuum loss inspection in accordance with theFig. A-GAAAA Sheet 01and 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 vacuum loss inspection holes with DIA 1.5 mm (0.06 in.) through the outer skin only. d Do the Vacuum loss inspection (Refer to NTM Task 51-10-28-220-801).
e In case of damage indications, contact AIRBUS on the basis of a detailed referenced damage report for further instructions before next flight. f In case of no damage indications, close the vacuum loss inspection holes as detailed in the subsequent instructions and report the result to AIRBUS within 10 days. 2 Temporary restoration of the vacuum loss inspection holes option 1:
a Close the holes with Self Adhesive Aluminium Tape 08-052 As required

or Self-Adhes. Disks 05-052 As required
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 32 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

b Do a detailed inspection of the restored area within every 750 FC or 100 days, whichever occurs first. Inspect the restored area for loose or lost adhesive disks or tape.
c In case of loose or lost tape ordisks, close theholes again with Self Adhesive Aluminium Tape 08-052 As required

or Self-Adhes. Disks 05-052 As required d This temporary restoration must be replaced by the permanent restoration after 4500 FC latest. 3 WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS ARE DANGEROUS. WARNING: WEAR THE CORRECT PROTECTIVE GLOVES, GOGGLES AND FILTER MASKS WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS ARE DANGEROUS. Temporary restoration of the vacuum loss inspection holes option 2:
a Before the resin injection: <1> Identify the skin thickness of the areas to be inspected, refer toFig. A-GAAAA Sheet 13andFig. A-GAAAA Sheet 14

. <2> If the skin thickness of the affected areas, defined by the TD, does not exceed 1.5 mm (0.06 in.), do a thermography inspection as detailed in NTM Task 51-10-25-290-801 or NTM Task 51-10-25-290-802 AND/OR If the skin of the affected areas, defined by the TD, is thicker than 1.5 mm (0.06 in.), do an ultrasound inspection as detailed in NTM Task 51-10-24-270-801. NOTE: During the ultrasound inspection, the vacuum loss inspection holes must be closed with thin adhesive tape (Material No 08-052 - basic) to prevent couplant ingress into the holes. b In case of damage indications contact AIRBUS for further instructions before next flight.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 33 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

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 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.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 34 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

<4> Clean the restoration areas with Solvent General Purpose 11-026 As required (Refer to SRM 51-77-11 Para 4.E). <5> Restore the surface protection (Refer toSRM 51-75-12). 4 Permanent restoration of the vacuum loss inspection holes:
a Before the resin injection: <1> Identify the skin thickness of the areas to be inspected, refer toFig. A-GAAAA Sheet 13andFig. A-GAAAA Sheet 14

. <2> If the skin thickness of the affected areas, defined by the TD, does not exceed 1.5 mm (0.06 in.), do a thermography inspection as detailed in NTM Task 51-10-25-290-801 or NTM Task 51-10-25-290-802 AND/OR If the skin of the affected areas, defined by the TD, is thicker than 1.5 mm (0.06 in.), do an ultrasound inspection as detailed in NTM Task 51-10-24-270-801. NOTE: During the ultrasound inspection, the vacuum loss inspection holes must be closed with thin adhesive tape (Material No 08-052 - basic) to prevent couplant ingress into the holes. b In case of damage indications contact AIRBUS for further instructions before next flight.
c WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS ARE DANGEROUS. WARNING: WEAR THE CORRECT PROTECTIVE GLOVES, GOGGLES AND FILTER MASKS WHEN YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS ARE DANGEROUS. Prepare and dry the restoration area (Refer to SRM 51-77-11 Para 4.M.(2)). d Prepare Wet Lay Up Resin 20-022 As required

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 35 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
(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 51-77-10 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). (k) Fill in the reporting sheet, refer toFig. A-GAAAA Sheet 04

. In case of damage indications, send the inspection report with a referenced mail to: AIRTAC Customer Services AIRBUS Central Entity 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 36 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

FRANCE Phone: +33(0)5 61 93 3400 (24 hour) Fax: +33(0)5 61 93 3500 Mailto: airtac@airbus.com and in case of damage indications or no damage indications to Structure Engineering Support Customer Services - SEES1 AIRBUS Central Entity 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE Fax: +33(0)5 61 93 36 14 **CONF 002 (1) Subtask 551036-832-203-002 - Do 2 additional repetitive special detailed inspections (ELCH) Manpower Resources Manhours 0 Minimum number of person 0 Subtask elapsed time 0 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-03-280-801 Task 51-10-19-280-801 Task 51-10-26-220-801

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 37 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

References Fig. A-GACAA Rudder SN - MSN reference list Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 Sheet 11 Sheet 12 Sheet 13 Sheet 14 Sheet 15 Sheet 16 Sheet 17 Sheet 18 Sheet 23 Sheet 24 Fig. A-GAEAA ELCH inspection Sheet 01 - Inspection areas Sheet 02 - Flow Chart Sheet 03 - Typical ELCH procedure Sheet 04 - Reporting sheet Sheet 05 - Rudder SN identification Sheet 06 -Overview of the compliance 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 onFig. A-GAEAA Sheet 05

. (b) If you do not find an SN placard on the rudder, contact AIRBUS for further instructions. (c) Compare the rudder SN with the rudder SNs in the rudder SN - MSN reference list Fig. A-GACAA Sheet 01thruFig. A-GACAA Sheet 24

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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 38 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

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 theFig. A-GAEAA Sheet 01, which have been inspected during the sampling, 2 additional repetitive special detailed inspections (ELCH) are necessary: 1 The Technical Disposition (TD) details the location of the reworked area to be inspected.
a For the definition of the areas to be inspected, refer to the rudder SN - MSN reference listFig. A-GACAA Sheet 01thruFig. A-GACAA Sheet 24 to find the MSN related Technical Disposition (TD) No. b To get the TD, refer to the SB BOOKLET-link on the index page of this Service Bulletin on the Air@Nav Engineering page in AIRBUS WORLD and use ’SB BOOKLET-TD-K45-S2-XXXXX’. For additional information, refer to SBIT SEMB 914.0808/09 2 Do the ELCH inspection in accordance with the Flow ChartFig. A-GAEAA Sheet 02at intervals not exceeding 4500 FC and not less than 4000 FC after the first sampling inspection (refer to NTM Task 51-10-26-220-801).
a For the ELCH inspection behind the fasteners, use one grid line with a distance of 50 mm (1.97 in.) between the inspection points, as shown on Fig. A-GAEAA Sheet 03, View A, area 2. <1> The assessment criteria for the ELCH inspection behind the fasteners are: Yellow value 0.30 mm (0.012 in.) Red value 0.40 mm (0.016 in.) For the adjustment of the ELCH, refer to NTM Task 51-10-26-220-801. b If the ELCH inspection extends ahead of the fasteners, use an inspection grid of 50 mm X 50 mm (1.97 in.) between the inspection points, as shown onFig. A-GAEAA Sheet 03, View A, area 3. <1> The assessment criteria for the ELCH inspection ahead of the fasteners are: Yellow value 0.25 mm (0.010 in.) Red value 0.35 mm (0.014 in.) For the adjustment of the ELCH, refer to NTM Task 51-10-26-220-801.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 39 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

3 In case of damage indications, re- examine the findings as per tap test inspection (Refer to NTM Task 51-10-03-280-801 or NTM Task 51-10-19-280-801), and contact AIRBUS for further instructions before next flight. 4 In case of no damage indications during the additional ELCH inspections, report to AIRBUS within 10 days. (e) Fill in the reporting sheet, refer toFig. A-GAEAA Sheet 04

. In case of damage indications, send the inspection report with a referenced mail to: AIRTAC Customer Services AIRBUS Central Entity 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE Phone: +33(0)5 61 93 3400 (24 hour) Fax: +33(0)5 61 93 3500 Mailto: airtac@airbus.com and in case of damage indications or no damage indications to Structure Engineering Support Customer Services - SEES1 AIRBUS Central Entity 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE Fax: +33(0)5 61 93 36 14 **CONF ALL D. TEST **CONF 001 None

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 40 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002 None **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 551036-942-201-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 29-10-00-863-001 Task 29-10-00-863-002 Task 29-10-00-863-003 Task 55-33-13-410-002 Task 55-40-00-210-001 (a) Make sure that the work areas are clean and clear of tools and other items of equipment (b) To close the access panels, (Refer to AMM Task 55-33-13-410-002). (c) Remove the access platforms. (d) Close the circuit breakers as given in the rudder inspection/check Close-up procedure (Refer to AMM Task 55-40-00-210-001). (e) Pressurize the Green Hydraulic System (Refer to AMM Task 29-10-00-863-001) (f) Pressurize the Yellow Hydraulic System (Refer to AMM Task 29-10-00-863-002) (g) Pressurize the Blue Hydraulic System (Refer to AMM Task 29-10-00-863-003) (h) In the cockpit, remove all warning notices. **CONF 002 (1) Subtask 551036-942-201-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 29-10-00-863-001 Task 29-10-00-863-002 Task 29-10-00-863-003 Task 55-33-13-410-002 Task 55-40-00-210-001 DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 41 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
(a) Make sure that the work areas are clean and clear of tools and other items of equipment (b) To close the access panels, (Refer to AMM Task 55-33-13-410-002). (c) Remove the access platforms. (d) Close the circuit breakers as given in the rudder inspection/check Close-up procedure (Refer to AMM Task 55-40-00-210-001). (e) Pressurize the Green Hydraulic System (Refer to AMM Task 29-10-00-863-001) (f) Pressurize the Yellow Hydraulic System (Refer to AMM Task 29-10-00-863-002) (g) Pressurize the Blue Hydraulic System (Refer to AMM Task 29-10-00-863-003) (h) In the cockpit, remove all warning notices.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 42 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

INDICATION FOUND
CLOSE INSPECTION HOLES NO YES REPORT TO AIRBUS

TO GET FURTHER

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

AND REPORT TO AIRBUS WITHIN 10 DAYS

AIRBUS INSTRUCTIONS

TO BE CARRIED OUT BEFORE NEXT FLIGHT

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

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

CONTACT AIRBUS BEFORE FURTHER FLIGHT

IN CASE OF FINDINGS. WITHIN 4500 FC

WITHIN 4500 FC AREA, AT INTERVALS

REQUIRED BEFORE RESIN INJECTION. THERMOGRAPHY INSPECTION

RESTORE FINAL

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

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

ULTRASOUND INSPECTION

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

CONTACT AIRBUS BEFORE FURTHER FLIGHT

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

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

CONTACT AIRBUS BEFORE FURTHER FLIGHT

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

AS PER NTM 51−10−24 AND/OR

NOTE: FOR THE ACCOMPLISHMENT TIMESCALE. REFER TO PARA 1.E.(2) N_SB_551036_6_AAAA_01_07 

## Figure A-GAAAA - Sheet 01 Rudder inspection - Flow Chart 1, vacuum loss inspection
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 43 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001 DAMAGE ASSESSMENT BY VACUUM LOSS INSPECTION:

IF THE VACUUM LOSS INSPECTION REVEALS DAMAGE AN ADD−ON INSPECTION IN MIDFIELD DIRECTION ONLY MUST BE PERFORMED TO DEFINE THE OVERALL DAMAGE SIZE. FOR ADD−ON INSPECTION 1, DRILL ONE ADDITIONAL ROW OF INSPECTION HOLES WITH A PITCH OF 25.0mm (0.98in.) AND ONE EXTRA HOLE AT EACH END OF THE ROW PARALLEL TO THE DETECTED LEAKAGE, AS PER SKETCH BELOW. DRILL INSPECTION HOLES WITH DIAMETER 1.5mm (0.06in) THROUGH THE OUTER SKIN ONLY. WARNING: DRILL PENETRATION INTO THE SANDWICH STRUCTURE HAS TO BE LIMITED TO 20.0mm (0.79in.), TO PREVENT INNER SKIN DAMAGE. PERFORM VACUUM LOSS INSPECTION (SAME PROCEDURE AS APPLIED FOR BASIC INSPECTION), POSITION THE VACUUM CUP IN A WAY THAT ONLY ONE OF THE NEW HOLES IS COVERED BY THE CUP, DURING EACH MEASUREMENT. IF NO EXTRA LEAKAGE IS FOUND, DOCUMENT THE DAMAGE, USING THE REPORTING SHEET. IF MORE LEAKAGES ARE FOUND, PROCEED WITH ADD−ON INSPECTION 2 (AND IF REQUIRED FURTHER STEPS UNTIL THE WHOLE DAMAGE EXTEND IS DETECTED), USING THE SAME PROCEDURE AS DETAILED ABOVE. NOTE: THE OVERALL DAMAGE LENGTH AND WIDTH IS BOUNDED BY THOSE ROWS OF INSPECTION HOLES, WHICH DO NOT INDICATE A VACUUM LOSS.

OVERALL LENGTH

OVERALL

WIDTH25.0mm (0.98in.)

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



### OVERALL DAMAGE SIZE DEBONDING

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

N_SB_551036_6_AAAA_02_05 

## Figure A-GAAAA - Sheet 02 Rudder inspection - Vacuum loss inspection
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 44 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

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

INDICATION

FOUND NO YES

REPORT TO AIRBUS WITHIN 10 DAYS

REPORT TO AIRBUS

TO GET FURTHER

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

INDICATION

FOUND NO YES

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

REPORT TO AIRBUS WITHIN 10 DAYS NO

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

FOR EACH RUDDER 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_551036_6_AAAA_03_08 

## Figure A-GAAAA - Sheet 03 Rudder inspection - Flow Chart 2, ELCH inspection
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 45 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001



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

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

Thermography

ELCH Inspection

Vacuum Loss Inspection

Inspection

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

No findings Findings as detailed by sketch and photos

No findings Findings as detailed by sketch and photos

No findings Findings as detailed by sketch and photos

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

* use sketch from the TD
N_SB_551036_6_AAAA_04_04 

## Figure A-GAAAA - Sheet 04 Rudder inspection - Reporting sheet
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 46 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

N_SB_551036_6_AAAA_05_04 

### 325EL

325DL
325CL

325BL

325ER

325DR

325CR

325BR Z325 

# B

NOTE: OPEN ACCESS PANEL AS PER AMM 55−33−13 P. BLOCK 201. CLOSE ACCESS PANEL AS PER AMM 55−33−13 P. BLOCK 201. POSITION OF RUDDER S/N PLACARD AT MSN: 0529, 0532 AND

0537 − 9999 

# C

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



# C **A**

**E**
**D K** 

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

# A

**B**

D5547100XXXXX TS−XXXX



## Figure A-GAAAA - Sheet 05 Rudder inspection - Rudder SN identification
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 47 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

TYPICAL TRAILING EDGE ELCH INSPECTION FASTENERS



# AREA 3 AREA 2

**K**

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 2 AREA 3



# L

N_SB_551036_6_AAAA_09_04 

## Figure A-GAAAA - Sheet 09 Rudder inspection - Typical ELCH procedure
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 48 6

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

# @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_551036_6_AAAA_10_02 

## Figure A-GAAAA - Sheet 10 Rudder inspection - Inspection areas
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 49 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

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

REPORT TO AIRBUS WITHIN 10 DAYS DO REPETITIVE ELCH INSPECTIONS

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

FOUND NO YES

REPORT TO AIRBUS

TO GET FURTHER

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

INDICATION

FOUND NO YES

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

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

FOR EACH RUDDER IN AREAS DEFINED IN SPECIFIC TECHNICAL DISPOSITION

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

N_SB_551036_6_AAAA_11_05 

## Figure A-GAAAA - Sheet 11 Rudder inspection - Flow Chart 3, ELCH inspection
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 50 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

N_SB_551036_6_AAAA_13_02 

## Figure A-GAAAA - Sheet 13 Rudder inspection - Rudder skin thickness LH
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 51 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

N_SB_551036_6_AAAA_14_02 

## Figure A-GAAAA - Sheet 14 Rudder inspection - Rudder skin thickness RH
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 52 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001



# AREA 1 (REINFORCED AREA)

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

# AREA 2 (TRAILING EDGE AREA)

WITHIN 20 MONTH FROM ISB REV.00 ISSUE DATE 

# AREA 3 (OTHER AREAS)

WITHIN 20 MONTH FROM ISB REV.00 ISSUE DATE

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

APPLY ACTIONS ACCORDING FLOW CHART SHOWN ON FIG. A−GAAAA, SHEET 03 APPLY ACTIONS ACCORDING FLOW CHART SHOWN ON FIG. A−GAAAA, SHEET 01 APPLY ACTIONS ACCORDING FLOW CHART SHOWN ON FIG. A−GAAAA, SHEET 11 NOTE: 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_551036_6_AAAA_15_01 

## Figure A-GAAAA - Sheet 15 Rudder inspection - General overview of the compliance times
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 53 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X

X

X X X X X X X X X X

X X X X X

X X

X X X X X

X X X X X X X X X

X

X X

X 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_551036_6_ACAA_01_09 

## Figure A-GACAA - Sheet 01 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 54 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 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_551036_6_ACAA_02_07 

## Figure A-GACAA - Sheet 02 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 55 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 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_551036_6_ACAA_03_06 

## Figure A-GACAA - Sheet 03 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 56 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 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_551036_6_ACAA_04_07 

## Figure A-GACAA - Sheet 04 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 57 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 X X X X X X X X X X X 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_551036_6_ACAA_05_04 

## Figure A-GACAA - Sheet 05 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 58 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 X X X X X X X X X X X X 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_551036_6_ACAA_06_04 

## Figure A-GACAA - Sheet 06 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 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 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 X X X X X X X X X X X X X X X X X X X X

X X

X

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_551036_6_ACAA_07_04 

## Figure A-GACAA - Sheet 07 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 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 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 X X X X X X X X X X X X X X X X X X X X X X

X

X X X X 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_551036_6_ACAA_08_05 

## Figure A-GACAA - Sheet 08 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 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 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 X X X X X X X X X X X X X X X X X X X X X X X X X

X X X

X

X X 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_551036_6_ACAA_09_04 

## Figure A-GACAA - Sheet 09 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 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 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X

X X X X X X X X X X X

X

X X X X X 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_551036_6_ACAA_10_05 

## Figure A-GACAA - Sheet 10 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 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 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X X X X X X X X X

X X

X X

X X X

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_551036_6_ACAA_11_04 

## Figure A-GACAA - Sheet 11 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 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 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X

X X X

X

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

X X X X

X X X X X X X X

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_551036_6_ACAA_12_04 

## Figure A-GACAA - Sheet 12 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 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 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X X

X X X

X X

X X X X X X X

X X X X X X X

X X X X X

X X

X X

X X 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_551036_6_ACAA_13_04 

## Figure A-GACAA - Sheet 13 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 66 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X

X

X X

X X

X X X X X X X

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

X

X X X X

X

X X

X

X X 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_551036_6_ACAA_14_04 

## Figure A-GACAA - Sheet 14 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 67 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X X X

X X X X

X X X X X

X X X X X X X X

X X X X X

X

X X X X X X

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_551036_6_ACAA_15_04 

## Figure A-GACAA - Sheet 15 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 68 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X

X X X X

X X X X

X X X X

X X X X X X

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

X X

X X

X

X

X

X

X X X X X X

X

X X X X X

X

X

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

N_SB_551036_6_ACAA_16_04 

## Figure A-GACAA - Sheet 16 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 69 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X

X X

X X X X X X X X X X X

X X X X

X

X

X X

X X X X X X

X

X X

X

X

X

X

X

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_551036_6_ACAA_17_04 

## Figure A-GACAA - Sheet 17 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 70 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 X XX TS−3669 2302 00186 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X

X X

X X

X

X

X X X X X X X X

X X X

X X X X X X X X

X X X X

X

X X

X X X X

X X X X X X X X X

X

X X X

X X X X

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

N_SB_551036_6_ACAA_18_04 

## Figure A-GACAA - Sheet 18 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 71 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

RUDDER SN MSN CONFIG. TD LH SIDE SHELL 01 AREA 1 02 AREA 2 AREA 3 RH SHELL SIDE
VACUUM ELCH LOSS ELCH/ VACUUM LOSS **NOTE:**THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP AT THE DATE OF THE AIRCRAFT DELIVERY.

**NOTE:**THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD. ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN 01 20 MONTH FROM THE ISSUE OF THE REV.00 OF THIS SERVICE BULLETIN. 01 AREA 1 AREA 2 AREA 3 VACUUM ELCH LOSS ELCH/ VACUUM LOSS01 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_551036_6_ACAA_23_04 X



## Figure A-GACAA - Sheet 23 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 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

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

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

N_SB_551036_6_ACAA_24_02 

## Figure A-GACAA - Sheet 24 Rudder SN - MSN reference list
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 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 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_551036_6_AEAA_01_01 

## Figure A-GAEAA - Sheet 01 ELCH inspection - Inspection areas
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 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 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 51−10−19INDICATION FOUND NO YES

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

REPORT TO AIRBUS

WITHIN 10 DAYS 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_551036_6_AEAA_02_04 

## Figure A-GAEAA - Sheet 02 ELCH inspection - Flow Chart
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 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 002

TYPICAL TRAILING EDGE ELCH INSPECTION FASTENERS



# AREA 3 AREA 2

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

# AREA 1 REINFORCED AREA 

# A

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

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



# A

N_SB_551036_6_AEAA_03_02 

## Figure A-GAEAA - Sheet 03 ELCH inspection - Typical ELCH procedure
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 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



# 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

* use sketch from the TD

N_SB_551036_6_AEAA_04_02 

## Figure A-GAEAA - Sheet 04 ELCH inspection - Reporting sheet
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 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

325EL

325DL
325CL

325BL

325ER

325DR

325CR

325BR Z325 

# B

NOTE: OPEN ACCESS PANEL AS PER AMM 55−33−13 P. BLOCK 201. CLOSE ACCESS PANEL AS PER AMM 55−33−13 P. BLOCK 201. POSITION OF RUDDER S/N PLACARD AT MSN: 0529, 0532 AND

0537 − 9999 

# C

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



# C **A**

**E**
**D K** 

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

# A

**B**

N_SB_551036_6_AEAA_05_01 

### D5547100XXXXX TS−XXXX



## Figure A-GAEAA - Sheet 05 ELCH inspection - Rudder SN identification
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 78 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 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_551036_6_AEAA_06_00 

## Figure A-GAEAA - Sheet 06 ELCH inspection - Overview of the compliance times
DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 79 6

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

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

# TITLE: STABILIZERS - RUDDER -A318 and A321 RUDDER DEBOND INSPECTION MODIFICATION No.: None Please complete the appropriate item (A or B): A - SB WILL BEembodied YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment:

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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 1 6

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

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

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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036 REVISION No.: 01 - Jul 02/10 Page: 1 6

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