@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

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

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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

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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

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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

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SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

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

ATA SYSTEM: 55

TITLE: STABILIZERS - RUDDER - 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

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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

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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

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SUMMARY

This Page Intentionally Left Blank

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

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

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SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

ATA SYSTEM: 55

TITLE: STABILIZERS - RUDDER - 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

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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

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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 0604 0614 0968 0974 1438

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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

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(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

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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

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- 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

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Area to be

inspected

Condition Action Compliance time Repetitive interval

Area 1 N/A Vacuum loss

inspection in

accordance with

Subtask

551036-832-202-001

At the latest of

these 2 conditions:

-Before the rudder

reaches 17000 FC

since new, without

exceeding 20

months from SB

Rev. 00 issue date

OR,

-Within 200 days

from SB Rev. 00

issue date

N/A

Area 1 Damage

indications found

during vacuum loss

inspection

Report to AIRBUS Before next flight N/A

Area 1 No damage

indications found

during vacuum loss

inspection

Temporary option

1: Close the

vacuum loss

inspection holes

with adhesive tape

Before next flight, if

the temporary

option 2 or the

permanent

restoration have

not been

accomplished

N/A

Area 1 No damage

indications found

during vacuum loss

inspection

Temporary option

1: Do a detailed

inspection of the

restored area for

loose or lost tape

N/A At intervals not

exceeding 750 FC

or 100 days,

whichever occurs

first

Area 1 Loose or lost tape

found

Temporary option

1: Close the

vacuum loss

inspection holes

again with

adhesive tape

Before next flight, if

the temporary

option 2 or the

permanent

restoration have

not been

accomplished

N/A

Area 1 No damage

indications found

during vacuum loss

inspection

Temporary option

1: Do the

permanent

restoration. Do a

thermography or

ultrasound

inspection before

the resin injection

Within 4500 FC

from the vacuum

loss inspection

N/A

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

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

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Area to be

inspected

Condition Action Compliance time Repetitive interval

Area 1 Damage

indications found

during

thermography or

ultrasound

inspection

Temporary option

1: Report to

AIRBUS

Before next flight N/A

Area 1 No damage

indications found

during vacuum loss

inspection

Temporary option

2: Close the

vacuum loss

inspection holes

with resin and

adhesive tape. Do

a thermography or

ultrasound

inspection before

the resin injection

Before next flight, if

the temporary

option 1 or the

permanent

restoration have

not been

accomplished

N/A

Area 1 Damage

indications found

during

thermography or

ultrasound

inspection

Temporary option

2: Report to

AIRBUS

Before next flight N/A

Area 1 No damage

indications found

during

thermography or

ultrasound

inspection

Temporary option

2: Restore the

surface protection

Within 4500 FC

from the vacuum

loss inspection

N/A

Area 1 No damage

indications found

during vacuum loss

inspection

Permanent

restoration: Do a

thermography or

ultrasound

inspection before

the resin injection

Before next flight

after the vacuum

loss inspection or

within 4500 FC

after the vacuum

loss inspection, if

the temporary

option 1 has been

accomplished.

N/A

Area 1 Damage

indications found

during

thermography or

ultrasound

inspection

Permanent

restoration: Report

to AIRBUS

Before next flight N/A

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

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

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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

551036-832-202-001

Within 20 months

from Rev. 00 issue

date

N/A

Area 2 Damage

indications found

during ELCH

inspection

Re-examine the

damage indications

as per tap test

inspection and

report to AIRBUS

Before next flight N/A

Area 2 No damage

indications found

during ELCH

inspection

Report to AIRBUS Within 10 days

from the 1. ELCH

inspection

N/A

Area 2 No damage

indications found

during ELCH

inspection

Do 2 additional

repetitive ELCH

inspections

N/A ELCH inspection

within intervals

between 4000 and

4500 FC from

previous inspection

Area 2 Damage

indications found

during the 1. or 2.

additional repetitive

ELCH inspection

Re-examine the

damage indications

as per tap test

inspection and

report to AIRBUS

Before next flight N/A

Area 2 No damage

indications found

during the 2

additional repetitive

ELCH inspections

Report to AIRBUS

after each ELCH

inspection

No further action

Report within 10

days from the

ELCH inspection

N/A

Table 3. Config. 001 - Rudder special detailed inspection on aircraft with rudders to be

inspected on Area 3 (refer to Figure A-GAAAA, Sheet 10).

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

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

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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

551036-832-202-001

At the latest of

these 2 conditions:

-Before the rudder

reaches 17000 FC

since new, without

exceeding 20

months from SB

Rev. 00 issue date

OR,

-Within 200 days

from SB Rev. 00

issue date

N/A

Area 3 Damage

indications found

during ELCH

inspection

Re-examine the

damage indications

as per tap test

inspection and

report to AIRBUS

Before next flight N/A

Area 3 No damage

indications found

during ELCH

inspection

Report to AIRBUS Within 10 days

from 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

551036-832-202-001

Within 20 months

from SB Rev. 00

issue date

N/A

Area 3 Damage

indications found

during vacuum loss

inspection

Report to AIRBUS Before next flight N/A

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

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

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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

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Area to be

inspected

Condition Action Compliance time Repetitive interval

Area 3 Damage

indications found

during

thermography or

ultrasound

inspection

Temporary option

2: Report to

AIRBUS

Before next flight N/A

Area 3 No damage

indications found

during

thermography or

ultrasound

inspection

Temporary option

2: Restore the

surface protection

Within 4500 FC

from the vacuum

loss inspection

N/A

Area 3 No damage

indications found

during vacuum loss

inspection

Permanent

restoration. Do a

thermography or

ultrasound

inspection before

the resin injection

Before next flight

after the vacuum

loss inspection or

within 4500 FC

from the vacuum

loss inspection, if

the temporary

option 1 has been

accomplished.

N/A

Area 3 Damage

indications found

during

thermography or

ultrasound

inspection

Permanent

restoration: Report

to AIRBUS

Before next flight N/A

Area 3 No damage

indications found

during

thermography or

ultrasound

inspection

No further action

after

accomplishment of

the permanent

restoration

N/A N/A

Accomplishment of this Service Bulletin is expected to be rendered mandatory by the

issue of an Airworthiness Directive (AD) published by the European Aviation Safety

Agency (EASA). It is anticipated that the AD will confirm the (thresholds and/or intervals

and/or date) given above but reference should be made to the AD for confirmation of the

mandated accomplishment timescale.

**CONF 002

Table 1. Config. 002 - Special detailed inspection (ELCH) on aircraft with rudders which

have already been inspected during the sampling

Area to be

inspected

Condition Action Compliance time Repetitive interval

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

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

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Area 2 N/A Identify the Serial

Number of the

installed rudder.

Within 4000 FC

from the 1.

sampling

inspection

N/A

Area 2 No damage

indications found

during sampling (1.

ELCH inspection)

2 additional

repetitive ELCH

inspections in

accordance with

subtask

551036-832-203-002

N/A Within intervals

between 4000 and

4500 FC from the

1. sampling

inspection

Area 2 Damage

indications found

during the 1. or 2.

additional repetitive

ELCH inspection

Re-examine the

damage indications

as per tap test

inspection and

report to AIRBUS

Before next flight N/A

Area 2 No damage

indications found

during the 2

additional repetitive

ELCH inspections

Report to AIRBUS

after each ELCH

inspection

No further action

Report within 10

days from the

ELCH inspection

N/A

Accomplishment of this Service Bulletin is expected to be rendered mandatory by the

issue of an Airworthiness Directive (AD) published by the European Aviation Safety

Agency (EASA). It is anticipated that the AD will confirm the (thresholds and/or intervals

and/or date) given above but reference should be made to the AD for confirmation of the

mandated accomplishment timescale.

**CONF ALL

F. APPROVAL

Approved under EASA Design Organisation Approval No. EASA 21J.031.

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

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

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

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

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

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

included.

**CONF 001

Task 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

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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

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**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 06-41-55 12-34-24 29-10-00

55-33-13 55-40-00

Consumable Material List (CML)

Non Destructive Test Manual (NTM) 51-10-03 51-10-19 51-10-24

51-10-25 51-10-26 51-10-28

Structural Repair Manual (SRM) 51-75-12 51-77-10 51-77-11

**CONF 002

Aircraft Maintenance Manual (AMM) 06-41-55 12-34-24 29-10-00

55-33-13 55-40-00

Consumable Material List (CML)

Non Destructive Test Manual (NTM) 51-10-03 51-10-19 51-10-26

**CONF ALL

K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 55-40-10

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

REVISION No.: 01 - Jul 02/10 Page: 16

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2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

None

This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign.

(2) Price and Availability

None

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will credit the manhours indicated in this Service Bulletin for inspections that are

performed on aircraft in warranty at the time of such inspection. Credit will be at the

operator’s agreed in-house warranty labor rate. Claims for labor allowance should be received

not later than 90 days after completion of the last affected warranted aircraft.

This Service Bulletin is subject of specific support provided by AIRBUS. For details please

contact your Customer Support Director.

For the organisation of this retrofit, operators are kindly requested to contact AIRBUS retrofit

management department. AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point

Maurice Bellonte 31707 BLAGNAC CEDEX France Tel : (33) 5 67 19 06 22 E-mail :

monitored.retrofit@airbus.com Fax : (33) 5 61 93 27 45

C. LIST OF COMPONENTS

No Kit

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Self-Adhes. Disks 05-052 As required

Self Adhesive Aluminium Tape 08-052 As required

Solvent General Purpose 11-026 As required

Lint-Free Cotton Cloth 19-003 As required

Wet Lay Up Resin 20-022 As required

(2) Components

None

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

REVISION No.: 01 - Jul 02/10 Page: 17

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(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

To find the correct tool-PN for the different inspection tools, refer to the subsequent

table:

Inspection tool PN NTM reference

ELCH Elasticity Laminate

Checker Kit

MBBBT100 51-10-26

Vacuum loss Vacuum cup TL3AMB1420T38L 51-10-28

Thermography Thermography kits 99A55407320000

(Camera and monitor)

and

99A55407321000

(complementary tooling

including hot air blower)

51-10-25

Ultrasound US-equipment EPOCH4PLUS

and

search unit K1SM

and

reference block

MBBGCFRPHC200

and

cable PKLL2

51-10-24

Tap test tap test inspection tool 98A57103013000

or

99A55209001000

51-10-03

Tap test Function test block

and

Woodpecker

99A55407291000

and

WP632

or

WP632AM

51-10-19

For more detailed information, refer to the related NTM chapter.

(3) Special Tools

None

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

REVISION No.: 01 - Jul 02/10 Page: 18

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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

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Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

Lint-Free Cotton Cloth 19-003 As required

References

Aircraft Maintenance Manual (AMM) 06-41-55, Page Block 001

Consumable Material List (CML)

(a) For location of the access panels, (Refer to AMM 06-41-55, Page Block 001).

(b) For the specification of consumable materials (Mat. No.) that you must use in this

Service Bulletin, (Refer to Consumable Material List (CML)).

(c) Clean the areas to be inspected with

Solvent General

Purpose

11-026 As required

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

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

Lint-Free Cotton Cloth 19-003 As required

References

Aircraft Maintenance Manual (AMM) 06-41-55, Page Block 001

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

REVISION No.: 01 - Jul 02/10 Page: 20

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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

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(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

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(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 the rudder special detailed inspection on aircraft

with rudders which are affected by hot-curing rework outside autoclave in

production

Manpower Resources

Manhours 0

Minimum number of person 0

Subtask elapsed time 0

Skills NON DESTRUCTIVE

TESTING

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Self-Adhes. Disks 05-052 As required

Self Adhesive Aluminium

Tape

08-052 As required

Solvent General Purpose 11-026 As required

Wet Lay Up Resin 20-022 As required

References

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

Task 51-10-19-280-801

Task 51-10-24-270-801

Task 51-10-25-290-801

Task 51-10-25-290-802

Task 51-10-26-220-801

Task 51-10-28-220-801

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

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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 Para 5.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 on Fig. 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

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(c) Compare the rudder SN with the rudder SNs in the rudder SN - MSN reference list

Fig. A-GACAA Sheet 01 thru Fig. A-GACAA Sheet 24.

NOTE: The rudder SN-MSN relationship is provided for information only

and is based on the information available at AIRBUS at time of SB

issue. Any changes resulting from movement from an aircraft to

another or from spare is not reflected, it is the responsibility of the

operator to assess the rudder SN-MSN relationship.

1 If you find a different SN against the MSN as detailed in the rudder SN - MSN

reference list, contact AIRBUS for further instructions.

2 If the rudder SN is not part of the rudder SN - MSN reference list, refer to the

Close-up para 3.E. No further action is necessary.

3 If the rudder is part of the rudder SN - MSN reference list with the same

indicated MSN, continue with the below instructions.

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

inspected and includes information about the vacuum loss inspection holes, if

necessary.

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

reference list Fig. A-GACAA Sheet 01 thru Fig. A-GACAA Sheet 24 to find the

MSN related Technical Disposition (TD) No.

2 To get the TD, refer to the SB BOOKLET-link on the index page of this

Service Bulletin on the Air@Nav Engineering page in AIRBUS WORLD and

use ’SB BOOKLET-TD-K45-S2-XXXXX’.

For additional information, refer to SBIT SEMB 914.0808/09

3 Inspection method for reworked areas:

- For reworked area astride AREA 2 and AREA 3, if TD provides vacuum

loss hole location then rework must be treated as if in AREA 3 only.

- For reworked area astride AREA 2 and AREA 3, if TD does not provide

vacuum loss hole location then rework must be treated as if in AREA 2

only.

- For reworked area astride AREA 1 and AREA 3, the rework must be

treated as if in AREA 1 only.

(e) If there are only areas on the trailing edge shown as ’AREA 2’ on the Fig. AGAAAA Sheet 10, to be inspected, refer to Para (h).

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

be inspected, refer to Para (i).

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

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

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

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

1 Do the vacuum loss inspection (Refer to NTM Task 51-10-28-220-801).

a Temporarily install adhesive foil on the areas to be inspected.

b Mark the grid of holes on the adhesive foil.

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 or disks, close the holes again with

Self Adhesive

Aluminium Tape

08-052 As required

or

Self-Adhes. Disks 05-052 As required

d This temporary restoration must be replaced by the permanent

restoration after 4500 FC latest.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

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3

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN

YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS

AND PAINTS: THESE MATERIALS ARE DANGEROUS.

WARNING: WEAR THE CORRECT PROTECTIVE GLOVES, GOGGLES

AND FILTER MASKS WHEN YOU USE CLEANING AGENTS,

ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS

ARE DANGEROUS.

Temporary restoration of the vacuum loss inspection holes option 2:

a Before the resin injection:

<1> Identify the skin thickness of the areas to be inspected, refer to Fig.

A-GAAAA Sheet 13 and Fig. A-GAAAA Sheet 14.

<2> If the skin thickness of the affected areas, defined by the

TD, does not exceed 1.5 mm (0.06 in.), do a thermography

inspection as detailed in NTM Task 51-10-25-290-801 or NTM Task

51-10-25-290-802

AND/OR

If the skin of the affected areas, defined by the TD, is thicker than

1.5 mm (0.06 in.), do an ultrasound inspection as detailed in NTM

Task 51-10-24-270-801.

NOTE: During the ultrasound inspection, the vacuum loss

inspection holes must be closed with thin adhesive

tape (Material No 08-052 - basic) to prevent couplant

ingress into the holes.

b In case of damage indications contact AIRBUS for further instructions

before next flight.

c Prepare and dry the restoration area (Refer to SRM 51-77-11 Para

4.M.(2)).

d Prepare

Wet Lay Up Resin 20-022 As required

(Refer to SRM 51-77-11 Para 4.A.(3)).

NOTE: The data sheets for each adhesive, resin or low density

compound states the maximum quantity that can be

safely mixed at one time without causing an exotherm

reaction. Always refer to the appropriate data sheet

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

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

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

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

leaking out of the inspection hole.

g Close the filled holes with

Self Adhesive

Aluminium Tape

08-052 As required

or

Self-Adhes. Disks 05-052 As required

h Let the resin cure for a minimum of 6 hours at room temperature.

If the room temperature is below 18 ̊C (64F), extend the curing time and

perform a gelation test outside the restoration area. After resin gelation

plus 2 h, the aircraft can be released to operations again.

OR

Cure the resin at 60 ̊C (140F) for 45 minutes. Install a heating blanket

with a vacuum bag on the rudder surface (Refer to SRM 51-77-11 Para

5.D.(1).(i)), and control the temperature by means of thermocouples

(Refer to SRM 51-77-11 Figure 14).

i Within the next 4500 FC, do the final surface restoration:

<1> Remove the self adhesive tape from the restoration areas.

<2> Inspect the restoration (Refer to SRM 51-77-10 Para 5.).

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

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

<4> Clean the restoration areas with

Solvent General

Purpose

11-026 As required

(Refer to SRM 51-77-11 Para 4.E).

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

4 Permanent restoration of the vacuum loss inspection holes:

a Before the resin injection:

<1> Identify the skin thickness of the areas to be inspected, refer to Fig.

A-GAAAA Sheet 13 and Fig. A-GAAAA Sheet 14.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

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<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

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g Close the filled holes with a self adhesive tape.

h Let the resin cure for a minimum of 12 hours at room temperature.

If the room temperature is below 18 ̊C (64F), extend the curing time and

perform a gelation test outside the restoration area.

After resin gelation plus 4 h, continue with the subsequent steps:

<1> Remove the self adhesive tape from the restoration areas.

<2> Inspect the restoration (Refer to SRM 51-77-10 Para 5.).

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

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

<4> Clean the restoration areas with

Solvent General

Purpose

11-026 As required

(Refer to SRM 51-77-11 Para 4.E).

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

(h) If there are areas on the trailing edge, shown as ’AREA 2’ on the Fig. A-GAAAA

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

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

1 Do the ELCH inspection (Refer to NTM Task 51-10-26-220-801).

a For the ELCH inspection behind the fasteners, use one grid line with a

distance of 50 mm (1.97 in.) between the inspection points, as shown on

Fig. A-GAAAA Sheet 09, View K and View L, area 2.

<1> The assessment criteria for the ELCH inspection behind the

fasteners are:

Yellow value 0.30 mm (0.012 in.)

Red value 0.40 mm (0.016 in.)

For the adjustment of the ELCH, refer to NTM Task

51-10-26-220-801.

b If the ELCH inspection extends ahead of the fasteners, use an inspection

grid of 50 mm X 50 mm (1.97 in.) between the inspection points, as

shown on Fig. A-GAAAA Sheet 09, View K and View L, area 3.

<1> The assessment criteria for the ELCH inspection ahead of the

fasteners are:

Yellow value 0.25 mm (0.010 in.)

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

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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 to Fig. A-GAAAA Sheet 03.

a In case of damage indications during the additional ELCH inspection, reexamine the findings as per tap test inspection (Refer to NTM Task

51-10-03-280-801 or NTM Task 51-10-19-280-801), and contact AIRBUS

for further instructions before next flight.

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

report to AIRBUS within 10 days.

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

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

Flow Chart Fig. A-GAAAA Sheet 11 within 200 days after the issue of The Rev. 00

of this Service Bulletin, and do the vacuum loss inspection within 20 months after

the issue of the Rev. 00 of this Service Bulletin.

For the vacuum loss inspection, refer to Para (j).

NOTE: The ELCH inspection is not required if the vacuum loss inspection

is done within 200 days after the issue of the Rev. 00 of this

Service Bulletin.

1 To do the ELCH inspection, refer to NTM Task 51-10-26-220-801.

a For the inspection in front of the fasteners, use up to 3 grid lines with a

distance of 50 mm (1.97 in.) between the inspection points, as shown on

Fig. A-GAAAA Sheet 09, View K and View L, area 3.

<1> The assessment criteria for the ELCH inspection in front of the

fasteners are:

Yellow value 0.25 mm (0.010 in.)

Red value 0.35 mm (0.014 in.)

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

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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 the Fig. A-GAAAA Sheet 01 and

Fig. A-GAAAA Sheet 02:

1 To do the vacuum loss inspection refer to NTM Task 51-10-28-220-801.

a Temporarily install adhesive foil on the areas to be inspected.

b Mark the grid of holes on the adhesive foil.

c

CAUTION: DRILL PENETRATION INTO THE SANDWICH

STRUCTURE HAS TO BE LIMITED TO 20 mm (0.8 in.)

TO PREVENT INNER SKIN DAMAGE.

Drill the 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

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b Do a detailed inspection of the restored area within every 750 FC or 100

days, whichever occurs first. Inspect the restored area for loose or lost

adhesive disks or tape.

c In case of loose or lost tape or disks, close the holes again with

Self Adhesive

Aluminium Tape

08-052 As required

or

Self-Adhes. Disks 05-052 As required

d This temporary restoration must be replaced by the permanent

restoration after 4500 FC latest.

3

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN

YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS

AND PAINTS: THESE MATERIALS ARE DANGEROUS.

WARNING: WEAR THE CORRECT PROTECTIVE GLOVES, GOGGLES

AND FILTER MASKS WHEN YOU USE CLEANING AGENTS,

ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS

ARE DANGEROUS.

Temporary restoration of the vacuum loss inspection holes option 2:

a Before the resin injection:

<1> Identify the skin thickness of the areas to be inspected, refer to Fig.

A-GAAAA Sheet 13 and Fig. A-GAAAA Sheet 14.

<2> If the skin thickness of the affected areas, defined by the

TD, does not exceed 1.5 mm (0.06 in.), do a thermography

inspection as detailed in NTM Task 51-10-25-290-801 or NTM Task

51-10-25-290-802

AND/OR

If the skin of the affected areas, defined by the TD, is thicker than

1.5 mm (0.06 in.), do an ultrasound inspection as detailed in NTM

Task 51-10-24-270-801.

NOTE: During the ultrasound inspection, the vacuum loss

inspection holes must be closed with thin adhesive

tape (Material No 08-052 - basic) to prevent couplant

ingress into the holes.

b In case of damage indications contact AIRBUS for further instructions

before next flight.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

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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

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<4> Clean the restoration areas with

Solvent General

Purpose

11-026 As required

(Refer to SRM 51-77-11 Para 4.E).

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

4 Permanent restoration of the vacuum loss inspection holes:

a Before the resin injection:

<1> Identify the skin thickness of the areas to be inspected, refer to Fig.

A-GAAAA Sheet 13 and Fig. A-GAAAA Sheet 14.

<2> If the skin thickness of the affected areas, defined by the

TD, does not exceed 1.5 mm (0.06 in.), do a thermography

inspection as detailed in NTM Task 51-10-25-290-801 or NTM Task

51-10-25-290-802

AND/OR

If the skin of the affected areas, defined by the TD, is thicker than

1.5 mm (0.06 in.), do an ultrasound inspection as detailed in NTM

Task 51-10-24-270-801.

NOTE: During the ultrasound inspection, the vacuum loss

inspection holes must be closed with thin adhesive

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

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(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 to Fig. A-GAAAA Sheet 04.

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

AIRTAC

Customer Services

AIRBUS Central Entity

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

REVISION No.: 01 - Jul 02/10 Page: 36

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FRANCE

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

Fax: +33(0)5 61 93 3500

Mailto: airtac@airbus.com

and in case of damage indications or no damage indications to

Structure Engineering Support

Customer Services - SEES1

AIRBUS Central Entity

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

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

**CONF 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

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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 on Fig. A-GAEAA Sheet

05.

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

instructions.

(c) Compare the rudder SN with the rudder SNs in the rudder SN - MSN reference list

Fig. A-GACAA Sheet 01 thru Fig. A-GACAA Sheet 24.

NOTE: The rudder SN-MSN relationship is provided for information only

and is based on the information available at AIRBUS at time of SB

issue. Any changes resulting from movement from an aircraft to

another or from spare is not reflected, it is the responsibility of the

operator to assess the rudder SN-MSN relationship.

1 If you find a different SN against the MSN as detailed in the rudder SN - MSN

reference list, contact AIRBUS for further instructions.

2 If the rudder SN is not part of the rudder SN - MSN reference list, refer to the

Close-up para 3.E. No further action is necessary.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

REVISION No.: 01 - Jul 02/10 Page: 38

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3 If the rudder is part of the rudder SN - MSN reference list with the same

indicated MSN, continue with the below instructions.

(d) For the areas on the trailing edge, shown as ’AREA 2’ on the Fig. A-GAEAA Sheet

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

detailed inspections (ELCH) are necessary:

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

inspected.

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

MSN reference list Fig. A-GACAA Sheet 01 thru Fig. A-GACAA Sheet 24

to find the MSN related Technical Disposition (TD) No.

b To get the TD, refer to the SB BOOKLET-link on the index page of this

Service Bulletin on the Air@Nav Engineering page in AIRBUS WORLD

and use ’SB BOOKLET-TD-K45-S2-XXXXX’.

For additional information, refer to SBIT SEMB 914.0808/09

2 Do the ELCH inspection in accordance with the Flow Chart Fig. A-GAEAA

Sheet 02 at intervals not exceeding 4500 FC and not less than 4000 FC after

the first sampling inspection (refer to NTM Task 51-10-26-220-801).

a For the ELCH inspection behind the fasteners, use one grid line with a

distance of 50 mm (1.97 in.) between the inspection points, as shown on

Fig. A-GAEAA Sheet 03, View A, area 2.

<1> The assessment criteria for the ELCH inspection behind the

fasteners are:

Yellow value 0.30 mm (0.012 in.)

Red value 0.40 mm (0.016 in.)

For the adjustment of the ELCH, refer to NTM Task

51-10-26-220-801.

b If the ELCH inspection extends ahead of the fasteners, use an inspection

grid of 50 mm X 50 mm (1.97 in.) between the inspection points, as

shown on Fig. A-GAEAA Sheet 03, View A, area 3.

<1> The assessment criteria for the ELCH inspection ahead of the

fasteners are:

Yellow value 0.25 mm (0.010 in.)

Red value 0.35 mm (0.014 in.)

For the adjustment of the ELCH, refer to NTM Task

51-10-26-220-801.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

REVISION No.: 01 - Jul 02/10 Page: 39

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3 In case of damage indications, re- examine the findings as per tap

test inspection (Refer to NTM Task 51-10-03-280-801 or NTM Task

51-10-19-280-801), and contact AIRBUS for further instructions before next

flight.

4 In case of no damage indications during the additional ELCH inspections,

report to AIRBUS within 10 days.

(e) Fill in the reporting sheet, refer to Fig. A-GAEAA Sheet 04.

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

AIRTAC

Customer Services

AIRBUS Central Entity

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

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

Fax: +33(0)5 61 93 3500

Mailto: airtac@airbus.com

and in case of damage indications or no damage indications to

Structure Engineering Support

Customer Services - SEES1

AIRBUS Central Entity

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

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

**CONF ALL

D. TEST

**CONF 001

None

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

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

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**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

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(a) Make sure that the work areas are clean and clear of tools and other items of

equipment

(b) To close the access panels, (Refer to AMM Task 55-33-13-410-002).

(c) Remove the access platforms.

(d) Close the circuit breakers as given in the rudder inspection/check Close-up

procedure (Refer to AMM Task 55-40-00-210-001).

(e) Pressurize the Green Hydraulic System (Refer to AMM Task 29-10-00-863-001)

(f) Pressurize the Yellow Hydraulic System (Refer to AMM Task 29-10-00-863-002)

(g) Pressurize the Blue Hydraulic System (Refer to AMM Task 29-10-00-863-003)

(h) In the cockpit, remove all warning notices.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

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

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**CONF 001

INDICATION

FOUND

CLOSE INSPECTION HOLES

YES NO

REPORT TO AIRBUS

TO GET FURTHER

INSTRUCTIONS

BEFORE NEXT FLIGHT

IDENTIFY THE RUDDER SERIAL NUMBER VIA THE PLACARD ON THE RUDDER SPAR.

IN CASE OF NO EXISTING PLACARD CONTACT AIRBUS

AND REPORT TO AIRBUS

WITHIN 10 DAYS

AIRBUS INSTRUCTIONS

TO BE CARRIED OUT

BEFORE NEXT FLIGHT

NO FURTHER ACTION

REQUIRED

IN AREA 1 AND 3

TEMPORARY OPTION II PERMANENT RESTORATION

THERMOGRAPHY INSPECTION

TEMPORARY OPTION I

FREQUENT DETAILED

INSPECTION OF RESTORED

NOT EXCEEDING

750 FC / 100 DAYS

PERMANENT RESTORATION

THERMOGRAPHY INSPECTION

AS PER NTM 51−10−25

CONTACT AIRBUS

BEFORE FURTHER FLIGHT

IN CASE OF FINDINGS.

WITHIN 4500 FC

WITHIN 4500 FC

AREA, AT INTERVALS

REQUIRED BEFORE RESIN INJECTION.

THERMOGRAPHY INSPECTION

RESTORE FINAL

PROTECTION

OR

COMPARE YOUR RUDDER SERIAL NUMBER WITH THE

RUDDER SERIAL NUMBERS IN THE REFERENCE LIST

YES NO

DO THE SPECIAL DETAILED INSPECTION (VACUUM LOSS)

AS PER NTM 51−10−28

IN AREAS DEFINED IN SPECIFIC TECHNICAL DISPOSITION

FOR EACH RUDDER

NO FURTHER ACTION

REQUIRED IN

ACCORDANCE WITH

THIS INSPECTION SB

SERIAL NUMBER

FOUND IN REFERENCE

LIST

ULTRASOUND INSPECTION

AS PER NTM 51−10−24

AND/OR

AS PER NTM 51−10−25

CONTACT AIRBUS

BEFORE FURTHER FLIGHT

IN CASE OF FINDINGS.

REQUIRED BEFORE RESIN INJECTION.

ULTRASOUND INSPECTION

AS PER NTM 51−10−24

AND/OR

AS PER NTM 51−10−25

CONTACT AIRBUS

BEFORE FURTHER FLIGHT

IN CASE OF FINDINGS.

REQUIRED BEFORE RESIN INJECTION.

ULTRASOUND INSPECTION

AS PER NTM 51−10−24

AND/OR

NOTE:

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

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**CONF 001

DAMAGE ASSESSMENT BY VACUUM LOSS INSPECTION:

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

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

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

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

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

THROUGH THE OUTER SKIN ONLY.

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

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

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

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

THE CUP, DURING EACH MEASUREMENT.

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

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

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

PROCEDURE AS DETAILED ABOVE.

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

INSPECTION HOLES, WHICH DO NOT INDICATE A VACUUM LOSS.

OVERALL LENGTH

OVERALL

WIDTH

25.0mm

(0.98in.)

ADD−ON INSPECTION 1

ADD−ON INSPECTION 2

ADD−ON INSPECTION 3

BASIC INSPECTION RESULTS

DIRECTION OF

ADD−ON INSPECTION RESTRICTED AREA

OVERALL DAMAGE SIZE

DEBONDING

DEBONDING AREA

HOLES TO BE INSPECTED IN CASE OF FINDINGS.

RESULTS OF VACUUM LOSS INSPECTION NO LEAKAGE

LEAKAGE DETECTED

WARNING: DRILLING IN THE RESTRICTED AREA CAN DAMAGE THE INNER SKIN AND IS NOT ALLOWED.

NOTE: FOR THE INSPECTIONS A NORMAL PAINT CONDITION AND AN ADEQUATE FLAT SURFACE IS

EXPECTED. IF INTENSIVE PAINT CRACKING OR SURFACE WAVINESS IS PRESENT A LOCAL 

SURFACE POLISHING BY SANDING IS ADVISABLE. FOR THE SANDING OPERATION USE CLOTH 280

OR 400 GRADE. BY THE SANDING OPERATION NEITHER THE SURFACE PRIMER NOR THE OUTER 

FABRIC LAYER MUST BE DAMAGED.

N_SB_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

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**CONF 001

IDENTIFY THE RUDDER SERIAL NUMBER VIA THE PLACARD

ON THE RUDDER SPAR.

IN CASE OF NO EXISTING PLACARD CONTACT AIRBUS

INDICATION

FOUND YES NO

REPORT TO AIRBUS

WITHIN 10 DAYS

REPORT TO AIRBUS

TO GET FURTHER

INSTRUCTIONS

BEFORE NEXT FLIGHT

RE−EXAMINE THE FINDINGS

AS PER TAP TEST INSPECTION

NTM 51−10−03 OR NTM 51−10−19

AND

INDICATION

FOUND YES NO

NO FURTHER ACTION

REQUIRED

IN AREA 2

AIRBUS INSTRUCTIONS

TO BE CARRIED OUT

BEFORE NEXT FLIGHT

DO 2 ADDITIONAL ELCH INSPECTIONS

AT INTERVALS NOT EXCEEDING

4500FC AND NOT LESS THAN 4000 FC

REPORT TO AIRBUS

WITHIN 10 DAYS

NO

YES

NO FURTHER ACTION

REQUIRED IN

ACCORDANCE WITH

THIS INSPECTION SB

SERIAL NUMBER

FOUND IN REFERENCE

LIST

FOR EACH RUDDER

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

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**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

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**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

PN

NSA9117−63D

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

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**CONF 001

TYPICAL TRAILING EDGE

ELCH INSPECTION

FASTENERS

AREA 3

AREA 2

K

MINIMUM DISTANCE FROM EDGE 75.0mm (2.95in.)

NOTE:

L

AREA 1

REINFORCED AREA

75.0 mm

(2.95 in)

50.0 mm

(1.97 in)

75.0 mm

(2.95 in)

50.0 mm

(1.97 in)

50.0 mm

(1.97 in)

AREA 3 AREA 2

L

N_SB_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

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**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

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**CONF 001

IDENTIFY THE RUDDER SERIAL NUMBER VIA THE PLACARD

ON THE RUDDER SPAR.

IN CASE OF NO EXISTING PLACARD CONTACT AIRBUS

REPORT TO AIRBUS

WITHIN 10 DAYS

DO REPETITIVE ELCH INSPECTIONS

AT INTERVALS NOT EXCEEDING

200 DAYS / 1500 FC UNTIL

VACUUM LOSS INSPECTION

IS PERFORMED

INDICATION

FOUND YES NO

REPORT TO AIRBUS

TO GET FURTHER

INSTRUCTIONS

BEFORE NEXT FLIGHT

RE−EXAMINE THE FINDINGS

AS PER TAP TEST INSPECTION

NTM 51−10−03 OR NTM 51−10−19

AND

INDICATION

FOUND YES NO

NO FURTHER ACTION

REQUIRED

IN AREA 3

AIRBUS INSTRUCTIONS

TO BE CARRIED OUT

BEFORE NEXT FLIGHT

NO

YES

NO FURTHER ACTION

REQUIRED IN

ACCORDANCE WITH

THIS INSPECTION SB

SERIAL NUMBER

FOUND IN REFERENCE

LIST

FOR EACH RUDDER

IN AREAS DEFINED IN SPECIFIC TECHNICAL DISPOSITION

NOTE:

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

DO THE REPETITIVE SPECIAL DETAILED 

INSPECTION (ELCH) AS PER NTM 51−10−26

N_SB_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

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**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

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**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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−1368 0364 00600

TS−1389 0385 00852

TS−1496 0483 00845

TS−1501 0506 00196

TS−1503 0489 00414

TS−1508 0496 00572

TS−1516 0500 00685

TS−1527 0512 00789

TS−1529 0523 01039

TS−1534 0528 00907

TS−1545 0542 00108

TS−1547 0543 00977

TS−1553 0546 00763

TS−1560 0554 00625

TS−1561 0572 00255

TS−1571 0565 00357

TS−1572 0566 00321

TS−1574 0568 00042

TS−1576 0569 00557

TS−1577 0571 00392

TS−1583 0575 00926

TS−1585 0588 00549

TS−1588 0586 00837

TS−1591 0584 00239

TS−1600 0599 00941

TS−1602 0594 00175

TS−1607 0602 01536

TS−1608 0604 00851

TS−1614 0611 00581

TS−1616 0613 00069

TS−1619 0614 00088

TS−1622 0619 00974

TS−1632 0630 01023

TS−1639 0634 01093

TS−2004 0633 00987

TS−2008 0639 00015

TS−2010 0642 00097

TS−2012 0653 00055

TS−2014 0655 00881

TS−2017 0657 00542

TS−2018 0649 00009

TS−2023 0661 01115

TS−2025 0656 00389

TS−2029 0666 00642

TS−2032 0663 00723

TS−2034 0668 00107

N_SB_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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

X

TS−2039 0676 01035

TS−2040 0674 00939

TS−2041 0675 00732

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2046 0683 00633

TS−2050 0696 00888

TS−2051 0684 00813

TS−2052 0698 00232

TS−2053 0686 00816

TS−2056 0688 00787

TS−2060 0690 00313

TS−2069 0695 00580

TS−2070 0708 01537

TS−2080 0716 00972

TS−2082 0718 00076

TS−2084 0720 00081

TS−2085 0719 00183

TS−2086 0722 00671

TS−2094 0730 00385

TS−2096 0725 00805

TS−2097 0733 01069

TS−2098 0732 00437

TS−2100 0735 00444

TS−2101 0737 00885

TS−2106 0740 00364

TS−2113 0749 00632

TS−2115 0751 00690

TS−2118 Spare 01538

TS−2126 0762 00844

TS−2130 0766 00603

TS−2131 0761 00838

TS−2132 0768 00383

TS−2134 0770 00680

TS−2136 0769 01102

TS−2140 0773 01005

TS−2141 0776 00679

TS−2143 0777 01096

TS−2144 0778 00982

TS−2145 0775 00853

TS−2149 0781 00091

TS−2152 0786 00620

TS−2154 0787 00806

TS−2155 0789 00574

TS−2159 0793 00061

TS−2163 0797 00248

TS−2168 0800 00377

TS−2169 0804 00817

X

N_SB_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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2170 0801 00463

TS−2172 0805 00672

TS−2175 0807 01014

TS−2177 0809 00154

TS−2179 0812 00030

TS−2182 0814 00265

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2183 0817 00406

TS−2185 0818 00534

TS−2192 0824 00294

TS−2193 0825 00833

TS−2195 0827 00164

TS−2199 0830 00268

TS−2200 0831 00879

TS−2204 0835 00462

TS−2206 0838 00618

TS−2208 0840 00966

TS−2209 0842 00407

TS−2210 1039 00024

TS−2211 0848 00094

TS−2213 0843 01006

TS−2216 0845 00118

TS−2217 0851 00409

TS−2218 0847 00947

TS−2220 0854 00459

TS−2221 0850 00756

TS−2222 0856 00208

TS−2223 0857 00375

TS−2227 0861 00160

TS−2228 0858 00275

TS−2230 0863 00330

TS−2231 0865 00111

TS−2232 0862 00441

TS−2234 0844 00098

TS−2235 0870 00536

TS−2236 0864 00990

TS−2238 0869 00648

TS−2240 0867 01544

TS−2242 0872 00142

TS−2244 0873 00654

TS−2245 0877 00298

TS−2248 0878 00942

TS−2250 0882 01002

TS−2251 0881 00413

TS−2252 0886 00468

TS−2254 0884 00696

TS−2258 0889 00439

N_SB_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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2259 0890 00130

TS−2260 0899 00381

TS−2261 0891 00272

TS−2262 0897 00374

TS−2265 0894 00567

TS−2268 0896 00657

TS−2269 0898 00181

TS−2271 0903 00306

TS−2272 0902 00073

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2274 0904 00288

TS−2276 0989 00953

TS−2279 0908 00490

TS−2280 0910 00156

TS−2281 0907 00482

TS−2284 0911 00882

TS−2285 0913 00771

TS−2286 0912 00456

TS−2293 0918 00901

TS−2295 0935 00078

TS−2297 0921 01075

TS−2298 0924 00961

TS−2299 0923 00973

TS−2302 0927 00509

TS−2303 0929 00110

TS−2304 0928 00984

TS−2305 0930 01062

TS−2307 0931 00776

TS−2310 0936 00796

TS−2311 0937 00149

TS−2312 0939 00215

TS−2313 0940 00211

TS−2315 0942 00688

TS−2316 0941 00122

TS−2317 0945 00155

TS−2319 0948 00416

TS−2320 0944 00759

TS−2321 0947 00174

TS−2322 0946 00780

TS−2323 0949 00753

TS−2325 0952 00969

TS−2326 0954 00457

TS−2327 0951 00575

TS−2330 0955 00712

TS−2331 0957 00285

TS−2332 0959 00850

TS−2333 0962 00417

N_SB_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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2334 0956 00731

TS−2336 0963 00849

TS−2337 0965 01108

TS−2338 0971 00153

TS−2339 0960 00114

TS−2340 0966 00213

TS−2341 0964 00292

TS−2343 0967 00920

TS−2346 0969 00896

TS−2352 0987 00735

TS−2353 0981 00550

TS−2354 0977 01013

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2355 0978 00719

TS−2356 1001 01017

TS−2358 0993 00513

TS−2360 0984 00454

TS−2362 0995 00641

TS−2363 0986 00792

TS−2364 1002 00825

TS−2365 0997 00829

TS−2366 0990 00996

TS−2367 1028 00214

TS−2370 1012 00514

TS−2371 1007 00418

TS−2372 0992 00586

TS−2373 1004 00529

TS−2374 1008 01001

TS−2377 0996 00527

TS−2381 1015 00835

TS−2382 0982 00297

TS−2387 1005 01061

TS−2388 1019 00246

TS−2392 1022 00739

TS−2393 1011 00593

TS−2395 1013 00070

TS−2397 1026 00373

TS−2398 1027 00394

TS−2399 1032 00358

TS−2407 1035 01045

TS−2408 1038 00652

TS−2409 1040 00008

TS−2410 0868 00461

TS−2411 1042 00643

TS−2412 1043 00878

TS−2415 Spare 00090

TS−2417 1049 00460

N_SB_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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2421 1048 00360

TS−2422 1047 01018

TS−2423 1055 00583

TS−2427 1054 00588

TS−2428 1062 01008

TS−2435 1067 01110

TS−2437 1066 00818

TS−2440 1068 00244

TS−2444 1072 00895

TS−2446 1070 00216

TS−2447 1078 00819

TS−2453 1081 00446

TS−2455 1085 00836

TS−2458 1093 00353

TS−2460 1088 00016

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2463 1089 00427

TS−2466 1101 00717

TS−2467 1109 00766

TS−2471 1100 00556

TS−2472 1095 00287

TS−2474 1097 00831

TS−2476 1106 00035

TS−2477 1098 00167

TS−2478 1104 00447

TS−2481 1193 00445

TS−2482 1102 00305

TS−2483 1108 00971

TS−2484 1110 00486

TS−2486 1129 00650

TS−2488 1162 00309

TS−2491 1179 01064

TS−2493 1113 00395

TS−2494 1121 00804

TS−2498 1116 00403

TS−2499 1122 00782

TS−2501 1125 00289

TS−2505 1131 00820

TS−2506 1126 00428

TS−2508 1130 00676

TS−2510 1132 01024

TS−2512 1134 00802

TS−2514 1133 00644

TS−2517 1136 00868

TS−2518 1141 00668

TS−2521 1146 00308

TS−2522 1147 00565

N_SB_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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2527 1153 00449

TS−2529 1150 00404

TS−2532 1155 00524

TS−2536 1170 00526

TS−2540 1164 00760

TS−2544 1166 00296

TS−2545 1201 00517

TS−2547 1171 00630

TS−2551 1168 00847

TS−2552 1173 00903

TS−2553 1180 00528

TS−2554 1175 00622

TS−2555 1182 00043

TS−2558 1186 00740

TS−2562 1187 00624

TS−2563 1194 00890

TS−2566 1192 00983

TS−2568 1197 00178

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2570 1198 00979

TS−2571 1203 00267

TS−2572 1202 01047

TS−2573 1200 00093

TS−2574 1245 01049

TS−2575 1209 00521

TS−2576 1204 00247

TS−2579 1207 00930

TS−2580 1208 00415

TS−2581 1210 00162

TS−2583 1212 00604

TS−2584 1213 00442

TS−2585 1214 00535

TS−2586 1216 00786

TS−2587 1218 01080

TS−2590 1220 00578

TS−2591 1217 00095

TS−2592 1222 00516

TS−2593 1221 00378

TS−2596 1225 00258

TS−2597 1227 00380

TS−2601 1229 01070

TS−2602 1237 00319

TS−2603 1228 00745

TS−2605 1233 00450

TS−2606 1234 00402

TS−2611 1240 00335

TS−2612 1235 01015

N_SB_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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2614 1247 00510

TS−2615 1242 00709

TS−2616 1249 00962

TS−2617 1244 00429

TS−2620 1269 00411

TS−2625 1256 00952

TS−2626 1248 00905

TS−2628 1254 00221

TS−2629 1260 01534

TS−2630 1255 00801

TS−2631 1258 00320

TS−2632 1263 00870

TS−2634 1257 00569

TS−2635 1262 00322

TS−2636 1259 00886

TS−2637 1277 00814

TS−2640 1264 00344

TS−2641 1289 00006

TS−2642 1268 00052

TS−2644 1279 00553

TS−2647 1293 00484

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2648 1276 01000

TS−2650 1272 00224

TS−2651 1274 01020

TS−2653 1278 00323

TS−2656 1288 00453

TS−2657 1280 00913

TS−2658 1301 00018

TS−2659 1282 00638

TS−2662 1304 00710

TS−2664 1295 00134

TS−2665 1303 00492

TS−2666 1297 01052

TS−2667 1299 00120

TS−2668 1290 00669

TS−2671 1296 00631

TS−2674 1300 01055

TS−2675 1307 00998

TS−2676 1305 00958

TS−2677 1311 00139

TS−2679 1315 00141

TS−2680 1321 00458

TS−2681 1302 00978

TS−2682 1314 00512

TS−2683 1317 01088

TS−2685 1306 01022

N_SB_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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2688 1310 00639

TS−2689 1323 01094

TS−2691 1325 00781

TS−2695 1324 00443

TS−2697 1316 00605

TS−2698 1331 00231

TS−2699 1333 00552

TS−2700 1335 00815

TS−2701 1336 00212

TS−2707 1330 00908

TS−2710 1332 00472

TS−2711 1334 01076

TS−2712 1348 00226

TS−2713 1346 00613

TS−2714 1350 00785

TS−2715 1337 00975

TS−2716 1352 00741

TS−2717 1341 00200

TS−2719 1339 00152

TS−2722 1425 00928

TS−2724 1378 00655

TS−2725 1345 01551

TS−2726 1358 00158

TS−2727 1362 00101

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2728 1360 00192

TS−2732 1462 00222

TS−2734 1351 00464

TS−2735 1366 00582

TS−2736 1353 00960

TS−2738 1369 00176

TS−2739 1359 00515

TS−2740 1355 01019

TS−2741 1357 01553

TS−2742 1373 00651

TS−2743 1375 00967

TS−2744 1377 00031

TS−2745 1361 00612

TS−2747 1365 00485

TS−2749 1363 00025

TS−2751 1382 00165

TS−2753 1389 00606

TS−2754 1447 00940

TS−2755 1392 00169

TS−2756 1386 01009

TS−2757 1391 00014

TS−2758 1388 00274

N_SB_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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2759 1372 01058

TS−2760 1370 00228

TS−2762 1396 00533

TS−2765 1387 01077

TS−2771 1415 00182

TS−2772 1381 00147

TS−2773 1397 00317

TS−2775 1412 01552

TS−2776 1435 00279

TS−2778 1383 00667

TS−2779 1403 00645

TS−2780 1436 01065

TS−2782 1390 00922

TS−2783 1408 00489

TS−2784 1414 00564

TS−2785 1410 00170

TS−2786 1428 00083

TS−2788 1394 00627

TS−2790 1400 00138

TS−2791 1423 00616

TS−2792 1405 00144

TS−2793 1421 00733

TS−2794 1409 00480

TS−2795 1426 01103

TS−2796 1424 00431

TS−2797 1432 00539

TS−2799 1439 00576

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2801 1453 00314

TS−2803 1460 00202

TS−2804 1441 00049

TS−2805 1433 00505

TS−2807 1429 00401

TS−2808 1419 00311

TS−2810 1434 00036

TS−2811 1438 00734

TS−2812 1416 00626

TS−2813 1444 00750

TS−2814 1422 00473

TS−2815 1442 00199

TS−2816 Spare 01555

TS−2818 1443 00540

TS−2819 1440 00864

TS−2821 1445 00455

TS−2822 1458 00188

TS−2823 1427 00506

TS−2824 1430 01054

N_SB_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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2826 1437 00666

TS−2827 1473 00909

TS−2828 1465 00999

TS−2830 1450 01533

TS−2831 1448 00046

TS−2832 1468 00965

TS−2833 1446 00714

TS−2834 1466 00968

TS−2835 1452 01111

TS−2836 1481 00173

TS−2837 1476 00602

TS−2838 1472 00190

TS−2839 1474 01545

TS−2840 1477 01101

TS−2843 1454 00474

TS−2844 1457 00925

TS−2845 1459 01068

TS−2846 1461 01012

TS−2848 1483 00554

TS−2849 1501 00227

TS−2850 1469 00481

TS−2851 1487 01085

TS−2852 1467 00476

TS−2853 1485 00563

TS−2854 1492 00040

TS−2855 1488 00168

TS−2856 1496 00811

TS−2857 1470 00163

TS−2860 1494 00326

TS−2861 1482 00475

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2862 1478 00086

TS−2863 1498 01029

TS−2864 1480 00075

TS−2865 1499 00487

TS−2868 1505 00189

TS−2872 1491 00327

TS−2874 1533 00318

TS−2877 1515 00260

TS−2878 1495 01026

TS−2879 1517 00336

TS−2880 1497 00312

TS−2881 1500 00537

TS−2882 1519 00451

TS−2885 1504 00337

TS−2886 1506 00290

TS−2890 1524 00124

N_SB_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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2891 1509 00249

TS−2892 1525 00310

TS−2893 1527 01030

TS−2896 1531 00295

TS−2897 1521 00161

TS−2898 1514 01011

TS−2899 1571 00251

TS−2900 1536 00340

TS−2903 1539 00233

TS−2904 1541 00761

TS−2906 1526 00584

TS−2907 1534 00479

TS−2908 1528 00263

TS−2909 1530 00706

TS−2910 1545 00587

TS−2911 1516 00585

TS−2913 1549 00331

TS−2914 1591 00559

TS−2916 1551 00329

TS−2917 1532 00019

TS−2919 1552 00508

TS−2920 1538 00039

TS−2922 1554 00937

TS−2923 1542 00571

TS−2924 1558 00865

TS−2925 1544 00400

TS−2927 1546 00662

TS−2928 1598 00045

TS−2929 1562 00737

TS−2930 1553 00619

TS−2932 1560 00963

TS−2933 1563 00821

TS−2934 1565 00873

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2935 1548 00661

TS−2937 1569 00995

TS−2938 1567 00861

TS−2939 1572 01046

TS−2943 1574 00518

TS−2944 1594 00293

TS−2946 1566 00621

TS−2948 1576 00649

TS−2949 1570 00171

TS−2950 1557 00020

TS−2951 1579 00420

TS−2953 1578 01059

TS−2954 1584 00332

N_SB_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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−2955 1612 00830

TS−2957 1583 00822

TS−2958 1564 01056

TS−2959 1585 00945

TS−2960 1587 00561

TS−2962 1590 00872

TS−2964 1588 01041

TS−2965 1592 00871

TS−2968 1589 00366

TS−2969 1596 00997

TS−2973 1605 00914

TS−2976 1617 00707

TS−2980 1603 00348

TS−2984 1606 00948

TS−2985 1607 00546

TS−2986 1620 01038

TS−2988 1621 00341

TS−2991 1627 01558

TS−2998 1635 00891

TS−3001 1619 00555

TS−3002 1639 00880

TS−3003 1641 01057

TS−3005 1644 00900

TS−3006 1646 00904

TS−3009 1648 00591

TS−3011 1630 01531

TS−3016 1655 00448

TS−3018 1657 00089

TS−3020 1661 00568

TS−3021 1640 00143

TS−3025 1667 00032

TS−3026 1643 00951

TS−3027 1645 01087

TS−3028 1669 01016

TS−3030 1647 01105

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−3031 1649 00452

TS−3032 1660 00647

TS−3033 1674 00422

TS−3034 1651 00103

TS−3035 1676 00544

TS−3037 1680 00545

TS−3038 1653 00126

TS−3040 1654 00738

TS−3043 1658 01092

TS−3046 1659 00127

TS−3049 1662 00596

N_SB_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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−3050 1694 01025

TS−3052 1696 00252

TS−3054 1697 00892

TS−3055 1668 00125

TS−3056 1700 00477

TS−3058 1702 00478

TS−3060 1784 01040

TS−3065 1677 01097

TS−3066 1712 00355

TS−3071 1719 00494

TS−3072 1681 00041

TS−3074 1684 00273

TS−3075 1723 00629

TS−3076 1683 00774

TS−3077 1688 00342

TS−3078 1832 00064

TS−3079 1730 01063

TS−3080 1690 00985

TS−3081 1708 00242

TS−3082 1732 00067

TS−3084 1728 00692

TS−3087 1698 00783

TS−3088 1739 00148

TS−3089 1693 01004

TS−3090 1741 00077

TS−3091 1695 00547

TS−3093 1691 00551

TS−3094 1747 01021

TS−3096 1706 00359

TS−3097 1749 00523

TS−3098 1707 00929

TS−3100 1699 00197

TS−3101 1754 01060

TS−3102 1785 01071

TS−3103 1755 00522

TS−3104 1711 00502

TS−3105 1757 00897

TS−3106 1709 00992

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−3107 1760 00887

TS−3108 1713 00839

TS−3109 1735 01042

TS−3110 1714 00742

TS−3111 1780 00902

TS−3112 1716 00943

TS−3113 1718 00765

TS−3114 1725 00250

N_SB_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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−3116 1720 00347

TS−3119 1767 00674

TS−3120 1769 00282

TS−3121 1722 00080

TS−3122 1726 00724

TS−3123 1727 00683

TS−3124 1771 00927

TS−3125 1733 00660

TS−3126 1773 00338

TS−3127 1731 00875

TS−3129 1734 00243

TS−3131 1737 00703

TS−3132 1738 00280

TS−3133 1789 00241

TS−3134 1787 00350

TS−3135 1792 00704

TS−3138 1797 00531

TS−3139 1799 00495

TS−3140 1743 00993

TS−3141 1742 01082

TS−3142 1763 00398

TS−3143 1802 01073

TS−3144 1804 00278

TS−3145 1745 00133

TS−3148 1806 00361

TS−3149 1748 00810

TS−3151 1750 00281

TS−3154 1814 00371

TS−3155 1753 00754

TS−3156 1816 00899

TS−3158 1818 00503

TS−3159 1729 00145

TS−3160 1777 00426

TS−3161 1758 00858

TS−3162 1761 00105

TS−3164 1759 00700

TS−3166 1765 00362

TS−3167 1795 00151

TS−3168 1774 00370

TS−3169 1778 00749

TS−3170 1770 00946

X

X

X

X

X

X

X

X

X

X

X

X

TS−3171 1827 00797

TS−3172 1796 00301

TS−3174 1766 00254

TS−3175 1779 00012

TS−3176 1783 00726

N_SB_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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−3177 1786 00762

TS−3178 1776 00079

TS−3179 1834 00916

TS−3180 1835 00257

TS−3181 1825 00354

TS−3182 1788 00421

TS−3183 1781 00579

TS−3184 1838 01036

TS−3185 1842 00689

TS−3186 1791 01050

TS−3188 1829 00678

TS−3189 1800 00276

TS−3191 1845 00718

TS−3193 1856 00399

TS−3194 1849 00423

TS−3195 1794 01099

TS−3198 1847 00799

TS−3200 1803 00954

TS−3201 1817 01067

TS−3202 1860 00037

TS−3204 1854 00259

TS−3205 1862 00543

TS−3207 1805 00166

TS−3210 1815 00466

TS−3215 1867 00601

TS−3216 1868 00615

TS−3217 1871 00424

TS−3218 1864 00038

TS−3219 1863 00755

TS−3221 1885 00425

TS−3222 1819 00430

TS−3223 1873 00229

TS−3224 1826 00743

TS−3226 1824 00504

TS−3227 1841 00744

TS−3232 1836 00351

TS−3234 1837 01084

TS−3235 1839 01031

TS−3236 1843 00924

TS−3237 1879 00677

TS−3240 1848 00277

TS−3241 1891 00798

TS−3242 1892 00159

TS−3243 1894 00970

X

X

X

X

X

X X

TS−3244 1844 00994 X

TS−3245 1850 00728

X

N_SB_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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−3247 1895 01053

TS−3248 1896 00705

TS−3249 1851 00752

TS−3250 1853 00748

TS−3251 1855 00828

TS−3252 1859 01090

TS−3253 1904 00675

TS−3255 1883 01043

TS−3256 1899 00664

TS−3257 1902 00432

TS−3259 1875 00860

TS−3262 1869 00577

TS−3271 1913 00691

TS−3276 1915 00150

TS−3278 1917 00270

TS−3282 1920 01112

TS−3286 1897 01081

TS−3289 1924 00843

TS−3290 1908 00834

TS−3291 1905 00854

TS−3292 1929 00369

TS−3295 1933 00841

TS−3297 1916 00548

TS−3306 1936 00758

TS−3309 1951 01079

TS−3310 1948 00397

TS−3317 1928 00944

TS−3320 1964 00912

TS−3328 Spare 01559

TS−3388 2044 00842

TS−3392 2000 00859

TS−3395 2002 00352

TS−3429 2023 00493

TS−3441 2041 01098

TS−3516 2157 00488

TS−3561 2187 00716

TS−3567 2205 00368

TS−3574 2195 00628

TS−3590 2231 00840

TS−3591 2224 00751

TS−3595 2232 00777

TS−3598 2234 01089

TS−3609 2243 00177

TS−3625 2262 00185

TS−3638 2269 00501

TS−3650 2275 00102

N_SB_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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

TS−3669 2302 X XX 00186

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−3684 2307 00497

TS−3685 2315 00217

TS−3687 2317 00855

TS−3689 2318 00779

TS−3690 2312 00637

TS−3695 2323 00218

TS−3699 2326 00187

TS−3702 2330 00725

TS−3703 2327 00715

TS−3704 2332 00957

TS−3706 2333 00367

TS−3708 2334 00191

TS−3710 2337 00115

TS−3717 2343 00507

TS−3718 2346 00386

TS−3734 2362 00778

TS−3743 2364 00193

TS−3761 2386 00702

TS−3772 2398 00219

TS−3780 2406 01107

TS−3789 2418 00747

TS−3805 2436 00773

TS−3820 2454 00827

TS−3821 2443 00681

TS−3822 2462 01048

TS−3824 2463 00950

TS−3825 2450 00566

TS−3839 2480 01066

TS−3841 2469 00775

TS−3843 2508 00384

TS−3844 2467 01095

TS−3846 2457 00343

TS−3849 2474 01091

TS−3850 2459 00589

TS−3851 2477 00656

TS−3853 2481 00198

TS−3855 2478 00201

TS−3857 2485 00956

TS−3860 2479 00382

TS−3862 2482 01113

TS−3863 2490 00203

TS−3871 2489 00205

TS−3878 2520 00793

TS−3879 2504 00235

TS−3882 2502 00491

N_SB_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 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

NOTE: THE COLUMNS FOR THE AREAS TO BE INSPECTED REFLECT ONLY AN OVERVIEW ABOUT THE AREAS

AND INSPECTION METHODS. FOR DETAILS REFER TO THE RELATED INDIVIDUAL TD.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

X

X

TS−3883 2506 00206

TS−3885 2512 00433

TS−3910 2531 00469

TS−3914 2535 00345

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

X

TS−3921 2540 00695

TS−3924 2562 00558

TS−3928 2564 01114

TS−3936 2555 00862

TS−3939 2561 00772

TS−3942 2559 00874

TS−3950 2570 00767

TS−3958 2589 01010

TS−3961 2591 00434

TS−3968 2590 00933

TS−3987 2610 00560

TS−3993 2615 00784

TS−3995 2617 00234

TS−4003 2625 00237

TS−4027 2656 00435

TS−4031 2655 00823

TS−4087 2706 00955

TS−4099 2716 00438

TS−4118 2739 00128

TS−4145 2783 00570

TS−4146 2765 00867

TS−4147 2769 00770

TS−4163 2780 00869

TS−4167 2804 00884

TS−4175 2797 00768

TS−4178 2767 00209

TS−4181 2788 00959

TS−4186 2793 00932

TS−4195 2809 00935

TS−4212 2848 00893

TS−4232 2874 00230

TS−4271 2889 01104

TS−4331 2938 00736

TS−4345 2986 00701

TS−4366 2969 00525

TS−4396 3007 00034

TS−4401 3037 00594

TS−4420 3056 00412

TS−4461 3103 00595

TS−4480 3121 00261

TS−4636 3284 01034

TS−4651 3280 00708

N_SB_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.

01 ELCH INSPECTION WITHIN 200 DAYS, VACUUM LOSS INSPECTION WITHIN

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

RUDDER SN MSN CONFIG. TD LH SIDE SHELL

01 02 AREA 1 AREA 2 AREA 3

RH SHELL SIDE

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

NOTE: THE SUBSEQUENT RUDDER SN−MSN REFERENCE LIST REFLECTS THE RUDDER SN−MSN RELATIONSHIP

AT THE DATE OF THE AIRCRAFT DELIVERY.

01

AREA 1 AREA 2 AREA 3

VACUUM ELCH

LOSS

ELCH/

VACUUM

LOSS

01

X

X

X

X

X

X

TS−4678 3294 00934

TS−4696 3330 00532

TS−4770 3409 00906

N_SB_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 51−10−19

INDICATION

FOUND YES NO

NO FURTHER ACTION

REQUIRED IN

ACCORDANCE WITH

THIS INSPECTION SB

AIRBUS INSTRUCTIONS

TO BE CARRIED OUT

BEFORE NEXT FLIGHT

DO 2 ADDITIONAL ELCH INSPECTIONS

AT INTERVALS NOT EXCEEDING

4500FC AND NOT LESS THAN 4000 FC

REPORT TO AIRBUS

WITHIN 10 DAYS

IDENTIFY THE RUDDER SERIAL NUMBER VIA THE PLACARD

ON THE RUDDER SPAR.

IN CASE OF NO EXISTING PLACARD CONTACT AIRBUS

NO

YES

NO FURTHER ACTION

REQUIRED IN

ACCORDANCE WITH

THIS INSPECTION SB

SERIAL NUMBER

FOUND IN REFERENCE

LIST

AS PER NTM 51−10−26

N_SB_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

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SERVICE BULLETIN

**CONF 002

TYPICAL TRAILING EDGE

ELCH INSPECTION

FASTENERS

AREA 3

AREA 2

MINIMUM DISTANCE FROM EDGE 75.0mm (2.95in.)

NOTE:

AREA 1

REINFORCED AREA

A

75.0 mm

(2.95 in)

50.0 mm

(1.97 in)

75.0 mm

(2.95 in)

50.0 mm

(1.97 in)

50.0 mm

(1.97 in)

AREA 3 AREA 2

A

N_SB_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

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SERVICE BULLETIN

**CONF 002

Inspection Report

Rudder Surface Inspection as per SB in area:

Aircraft type:

MSN:

Rudder S/N:

Rudder P/N:

Inspection date:

Operator:

FC:

FH:

Inspection method

ELCH Inspection No findings Findings as detailed

by sketch and photos

LH RH

Rudder Side

* 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

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SERVICE BULLETIN

**CONF 002

325EL

325DL

325CL

325BL

325ER

325DR

325CR

325BR

Z325 B

NOTE:

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

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

POSITION OF

RUDDER S/N PLACARD

AT MSN:

0529, 0532 AND

0537 − 9999

C

POSITION OF

RUDDER S/N PLACARD

AT MSN:

0001 − 0528,

0530 − 0531,

0533 − 0536

C

A

E

D K

MFR

DESCR.

SER. N °

CA CODE

MFG DATE

A/C

PN

NSA9117−63D

A

B

N_SB_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

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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

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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 BE embodied YES/NO (if NO please comment)

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

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

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

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

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

Or : Intermediate revision YES/NO

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

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

the next feasible revision, this will result in

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

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

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

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

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

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

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

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

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SERVICE BULLETIN

QUALITY PERCEPTION FORM

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

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

improve the quality of our Service Bulletins.

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

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

- Quality rating of this SB 4 3 2 1

- Quality rating of the Accomplishment Instructions 4 3 2 1

- Quality rating of the Illustrations 4 3 2 1

- Is this SB easy to understand ? Y / N

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

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

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

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Feb 17/10 SERVICE BULLETIN No.: A320-55-1036

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

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