@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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 55

TITLE: STABILIZERS - RUDDER SIDE SHELL SANDWICH REPAIR

INSPECTION

MODIFICATION No.: None

This page transmits Revision No.01 of Service Bulletin No.A320-55-1041

ADDITIONAL WORK

**CONF ALL

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision 01 issued to embody the local sanding procedure and change the compliance to Mandatory

further to the issuance of AD 2013-0302.

CHANGES

FRONT MATTER

STABILIZERS - RUDDER SIDE SHELL

SANDWICH REPAIR INSPECTION

CONFIGURATION UPDATED R

SUMMARY

GENERAL EVALUATION GENERAL EVALUATION TABLE UPDATED R

EFFECTIVITY OPERATOR LIST UPDATED R

REFERENCES / REPERCUSSIONS REFERENCES/REPERCUSSIONS TABLE

UPDATED

R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition

CONF 001 CONFIGURATION DEFINITION UPDATED R

COMPLIANCE

Classification CLASSIFICATION UPDATED R

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

MANPOWER MANPOWER UPDATED R

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 1

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

REFERENCES REFERENCED DOCUMENTATION UPDATED R

MATERIAL INFORMATION

LIST OF MATERIALS - OPERATOR

SUPPLIED

Consumable Materials

Consumable CMLD01 CONSUMABLE MATERIAL SET UPDATED

CONSUMABLE UPDATED

R

ACCOMPLISHMENT INSTRUCTIONS

TASK 551041- 832-848-001-Inspection TASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 551041-910-201-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 551041-941-201-001 SUBTASK SOLUTION UPDATED R

Subtask 551041-832-201-001 SUBTASK SOLUTION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 551041-832-202-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 551041-832-203-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 551041-832-204-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

QUANTITY UPDATED

FIGURE REFERENCE UPDATED

NOTE UPDATED

CONFIGURATION UPDATED

MATERIAL LIST UPDATED

R

Subtask 551041-832-205-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

REFERENCED DOCUMENTATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 551041-832-206-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

FIGURE REFERENCE UPDATED

NOTE UPDATED

MATERIAL LIST UPDATED

R

Subtask 551041-832-207-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 2

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 551041-833-201-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

CONSUMABLE UPDATED

REFERENCED DOCUMENTATION UPDATED

MATERIAL LIST UPDATED

R

Subtask 551041-832-208-001 SUBTASK SOLUTION ADDED N

Fig. A-GBFAA

Fig. A-GBFAA Sheet 02 SHEET UPDATED R

Fig. A-GBHAA FIGURE SOLUTION UPDATED R

Fig. A-GBHAA Sheet 01 SHEET UPDATED R

Fig. A-GBHAA Sheet 02 SHEET UPDATED R

Fig. A-GBHAA Sheet 03 SHEET UPDATED R

Fig. A-GBHAA Sheet 04 SHEET ADDED N

Fig. A-GFAAA FIGURE SOLUTION UPDATED R

Fig. A-GFAAA Sheet 01 SHEET UPDATED R

Fig. A-GFAAA Sheet 02 SHEET UPDATED R

Fig. A-GFAAA Sheet 03 SHEET UPDATED R

Fig. A-GFAAA Sheet 04 SHEET UPDATED R

Fig. A-GFAAA Sheet 05 SHEET UPDATED R

Fig. A-GFAAA Sheet 06 SHEET ADDED N

Fig. A-GABAA

Fig. A-GABAA Sheet 04 SHEET UPDATED R

Fig. A-GABAA Sheet 08 SHEET UPDATED R

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: Nov 26/12

REVISION No. : 01 - Feb 24/14

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 3

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 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.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 55

TITLE: STABILIZERS - RUDDER SIDE SHELL SANDWICH REPAIR

INSPECTION

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

On AIRBUS Single Aisle, Long Range and Wide Body 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 case of skin damage was reported on a composite side panel of a

rudder installed on an A310 aircraft. Investigations have shown that the damage started from a skin

panel area previously repaired in-service. This repair was performed as per A310 SRM 55-41-12 Fig.

204 procedure. The new damage has been identified as a damage between the core and the skin in

the repaired area. This new damage has developed during normal operations due to the variation of

pressure during ground-air-ground cycles.

Following the above mentioned damage scenario, it has been identified that SRM procedures need to

be improved to ensure an adequate repair quality. An improper bonding between skin and core during a

repair may lead to a damage initiation and propagation, which may not be detectable visually. A large

rudder damage, resulting from an undetected damage growth, could affect the handling quality of the

aircraft.

This Service Bulletin details the inspection procedure to inspect affected rudders fitted on

A318/A319/A320/A321 aircraft for potential damage.

Different inspection procedures are necessary:

- Pulse thermography inspection

- Elasticity Laminate Checker (ELCH) inspection

- Ultrasonic Testing (UT) inspection

- Tap test inspection.

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 1

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SERVICE BULLETIN

SUMMARY

The accomplishment of this Service Bulletin will contribute to detect potential damage around in-service

repairs accomplished on rudders made of Carbon Fiber Reinforced Plastic (CFRP) and Glass Fiber

Reinforced Plastic (GFRP) with a honeycomb core.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

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 must be accomplished.

MATERIAL PRICE INFORMATION

No Material

EFFECTIVITY

This Service Bulletin is applicable to this (these) operator(s) :

03X 09S 11S 15S 15T 17S 17W 19R 26S 27V 29S 31V 31X

35U 36R 38W 39Q 46U 52T 53Z 56W 59Z 62X 66X 69X 73W

74T 79W 80X 83W 85T 86W 86Z 89T 91X 93V 94W 95V 95W

98W AAF AAR AAW AAY ABL ABQ ABY ACA ACI ADH ADR AEE

AFL AFR AGC AGY AHY AIB AIC AIJ ALK AMC AMU ANA ANR

ANZ APZ ARR ART ARU AUA AUH AVA AWC AWM AWW AXM AZA

AZI AZW B2V BAW BEC BEL BER BGF BGH BGY BHP BIE BJN

BKP BQB BRS C9G CBJ CCA CCM CEB CEF CES CHH CIB CQH

CQN CSA CSC CSN CSZ CTN CTV CYP DAL DCS DKH DLH DNV

DQA DRK EAA EDW EIN ETD ETJ EVA EZD EZY F2I FFT FHY

FIN FLI FPY FRN FTZ G2X G4I G8E GAF GAP GCR GFA GLG

GMI GMR GOW GWI GZQ HAY HDA HKJ HRM HVN I2L I2T IAW

IBE IBS IGO IND IRA IRM ISR ISS IZG JAT JAV JBU JSA

JST JZR KAC KCA KFR KGL KHO KHV KKK KMF KNE KZR LAN

LBT LFO LJB LLC LLM LLP LMJ LMU LZB MAC MAU MDL MEA

MJF MJN MLD MLM MLR MMA MML MON MSC MSR MXA MYX NIA

NKS NLV NLY NMA NMB NVD NVR NWS OAL OAW OBS OHY ONE

ORF OZW PAL PIC PTR QAF QTR R1T RBA RBG RCT RFJ RJA

RJD RNV ROT RYW RZO S2A SAA SAI SAS SBI SDM SFJ SFW

SGG SGX SHJ SHU SKU SLK SMX SND SNX SOL SRQ SUD SVA

SVR SVW SWM SWR SYA SYR TAE TAI TAK TAM TAP TAR TBJ

TBZ TCW TCX TGW THY TJS TNA TVS TWJ TXP UAL UEA UKN

ULG UNA USA UZB VAR VIM VIP VIV VJC VKG VLE VLG VLK

VOI VRD VRE VVC WAU WGT WHT WOW WRC WTJ WZZ XLF

CONCURRENT REQUIREMENTS

None

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 2

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SERVICE BULLETIN

SUMMARY

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER OIT 999.0017/10 OIT 999.0060/10 OIT 999.0130/06 OIT

999.0067/12 AD 2013-0302

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 551041-832-848-001: Inspection

TOTAL MANHOURS 38.00

APPENDICES

None

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 3

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SERVICE BULLETIN

SUMMARY

**CONF ALL

RUDDER SHELL

TO BE INSPECTED

N_SB_551041_6_SAAA_01_00

B

A

Z326

B A

RH SHOWN LH SHOWN

Figure A-GSAAA - Sheet 01

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 55

TITLE: STABILIZERS - RUDDER SIDE SHELL SANDWICH REPAIR

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 is applicable to all rudders with the Serial Number (SN)

TS-1001 to TS-1639, SN TS-2001 to TS-5890 and TS-5927.

NOTE: Repairs of rudder side shells which have been accomplished in accordance

with a SRM procedure older than SRM February 2010 revision, must be

inspected in accordance with this Service Bulletin.

NOTE: In the case of a rudder originally fitted on one aircraft (refer to AIR delivery

document) that has been removed and installed on another aircraft, it is the

responsibility of the operator to apply the required instructions contained in

this Service Bulletin to the new aircraft.

NOTE: In case of doubt, contact AIRBUS.

(1) Models

318-111 318-112 318-121 318-122 319-111 319-112 319-113 319-114

319-115 319-131 319-132 319-133 320-211 320-212 320-214 320-216

320-231 320-232 320-233 321-111 321-112 321-131 321-211 321-212

321-213 321-231 321-232

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 1

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SERVICE BULLETIN

(2) Effectivity by MSN

0029 0045-0047 0049-0057 0059 0061 0063-0078 0080-0088 0090 0093-0096 0099

0104 0110-0119 0121-0127 0135 0137-0138 0140-0142 0147-0150 0152-0155

0157-0162 0164-0168 0171-0176 0178-0179 0181-0183 0185 0189-0190 0192

0194-0195 0197-0203 0205-0214 0216-0220 0223-0224 0229-0235 0237 0239-0244

0248-0256 0258-0270 0272-0279 0281-0282 0284-0285 0287 0289-0303 0306-0309

0311-0312 0314 0316-0325 0328-0335 0339-0343 0345-0347 0349-0351 0353-0362

0364 0366-0368 0370-0373 0375-0376 0378 0380-0388 0390-0391 0393 0395-0396

0398-0410 0412-0424 0426-0432 0434-0436 0438-0442 0444-0445 0447-0452

0454-0466 0468-0477 0479-0480 0482-0535 0537-0546 0548-0589 0591-0600

0603-0614 0616-0623 0625 0627 0629-0631 0633-0670 0672-0707 0709 0711-0752

0754-0788 0790-0955 0957-1043 1045-1112 1114-1185 1187-1217 1219-1277

1279-1332 1334-1373 1375-1463 1465-1659 1661-1675 1677-1728 1730-1767

1769-1812 1814-1821 1823-1829 1831-1918 1920-1929 1931-1938 1940-1984

1986-1990 1993-2024 2026-2050 2052-2110 2112-2217 2219-2275 2277-2423

2425-2499 2501-2721 2723-3037 3039-3091 3093-3109 3111-3162 3164-4391

(3) Effectivity by Operator

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

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

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

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

OPERATOR MSN

03X 2421

09S 1300 1353

11S 4211

15S 1589

15T 0764 1494 2910 3164

17S 3333

17W 3046

19R 0421

26S 0368 0424 0438

27V 3826

29S 0291 0292

31V 0164 0332 0420 0436 0605 1048 1873

31X 2192 4319

35U 0088 0199 0240 0241 0264

36R 1305

38W 1194

39Q 0393

46U 2906 2952 2982 3275 3296 3332 3674 3734 3986 4053

52T 1599

53Z 1468

56W 0250 0334 0335 0440

59Z 1556

62X 3402

66X 0558 0561 1098 1283

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 2

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SERVICE BULLETIN

OPERATOR MSN

69X 0219 0449 0588 0733

73W 0087

74T 2165 4228

79W 3751

80X 2748

83W 4024

85T 0234

86W 0384

86Z 0168 0460 0461 0497 2874

89T 3356

91X 2837

93V 3932

94W 1818

95V 3379

95W 2949

98W 0441

AAF 0639 0808 1006 1846 2870 3136 3242 3289 3852 4268

AAR 0802 1174 1356 1511 1670 1734 2041 2110 2226 2247 2290 2397

2459 2808 2840 3244 3297 3437 3483 3496 3641 3873 4112 4142

AAW 3224 3236 3615 3657 4004 4203 4330

AAY 1229 1255 1262 1288 1292 1318 1347 2224 2319 2387

ABL 1227 1636 1970 2045 2943

ABQ 1467 3364 3385 3388 3403 3974

ABY 2764 3246 3444 3476 3626 3802 3840 3925 4061 4243 4310

ACA 0059 0068 0073 0084 0122 0126 0127 0141 0149 0150 0154 0159

0174 0175 0183 0210 0231 0232 0233 0242 0248 0253 0254 0255

0265 0277 0284 0290 0309 0324 0330 0341 0378 0403 0404 0546

0572 0634 0656 0670 0672 0682 0688 0691 0693 0695 0697 0711

0719 0721 0728 0732 0736 0740 0742 0752 0757 0769 0773 0779

0785 0800 0813 0817 0829 0831 0840 0845 1562 1577 1602 1611

1623 1632 1638 1673 1719 1726 1742 1748 1772 1783 1811 1853

1864 1874 1940 2018 2145

ACI 2152

ADH 3138 3161 3328 3502 3515 3532 3643 3666 3695

ADR 0444 4282 4301

AEE 2468 2828 3033 3066 3074 3162 3316 3365 3392 3423 3439 3462

3478 3526 3527 3709 3714 3745 3748 3753 3773 3785 3812 3820

3829 3850 3878 3990 4065 4094 4165

AFL 2052 2069 2072 2091 2106 2116 2133 2144 2151 2163 2179 2233

2243 2330 2337 2342 2875 2903 2912 2920 2947 2957 2965 3052

3063 3157 3191 3267 3334 3373 3410 3511 3545 3574 3627 3631

3640 3644 3699 3711 3778 3786 3789 3794 3823 3835 3838 3923

3942 3954 3998 4058 4074 4099 4103 4116 4133 4148 4160

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

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OPERATOR MSN

AFR 0061 0063 0115 0155 0214 0237 0239 0278 0285 0287 0491 0498

0509 0521 0529 0544 0598 0600 0608 0618 0625 0637 0777 0796

0938 0985 0998 1000 1020 1025 1036 1133 1151 1169 1176 1190

1201 1216 1267 1271 1299 1344 1404 1415 1444 1449 1471 1476

1502 1505 1524 1616 1622 1640 1645 1658 1677 1691 1699 1733

1859 1879 1894 1900 1924 1938 1949 2035 2059 2071 2081 2100

2109 2140 2317 2344 2350 2456 2582 2601 2686 2705 2716 2721

2750 2918 2938 2951 2961 2967 2972 3008 3009 3051 3098 3372

3399 3401 3419 3420 3441 3470 3777 3795 3814 3825 3859 3884

3930 4063 4084 4105 4137 4139 4241 4251 4267 4295 4298 4335

AGC 0190

AGY 0351

AHY 0331 2487 2516 2588 2685 2788 2846 2853 2865 2991 3006

AIB 0138

AIC 0045 0046 0047 0049 0050 0051 0056 0057 0074 0075 0080 0090

0095 0096 0396 0398 0416 0423 0431 0432 0451 0469 0486 0490

0492 0499 1668 1718 2593 2624 2629 2907 3130 3146 3212 3271

3288 3300 3305 3326 3340 3344 3367 3498 3551 3557 3573 3619

3620 3687 3752 3792 3822 3874 3918 3955 3970 4002 4009 4020

4029 4052 4078 4089 4096 4121 4138 4155 4164 4201 4212 4236

4237 4280

AIJ 0707 1132 1162 1179 1244 1259 1308 1322 1747 1780 2048 2189

2227 2539 3021 3123 3149 3160 3286 3304 3312 3374 3508 3514

3667 3690 4235 4304

ALK 2345 2564 2584 2908

AMC 2113 2122 2142 2291 2332 2382 2665 2768 3056 3068

AMU 0620 0631 0805 0908 0928 1758 1790 1850 1893 1912 1926 1962

4197

ANA 0167 0212 0300 0328 0383 0413 0482 0501 0507 0531 0534 0549

0554 0658 0669 0685

ANR 0726

ANZ 2085 2090 2112 2130 2148 2153 2173 2257 2297 2445 2533 2594

2663

APZ 0747

ARR 0913 1439

ART 0142 0244 0311 0333 0359 0426 0533 0936

ARU 0573 0582

AUA 0552 0570 0581 0768 0776 0797 0920 0935 1137 1150 1189 1385

1387 1458 1478 1504 1553 1678 1735 1931 1937 2009 2131 2174

2262 2416 2494 2547 2652

AUH 2403

AVA 1612 1634 2066 2328 2333 2358 2367 2377 2394 2523 2544 2552

2575 2662 3408 3467 3518 3647 3664 3691 3961 3980 3988 3992

4001 4011 4026 4046 4051 4100 4167 4175 4200 4281 4284 4345

4381

AWC 2791

AWM 0765

AWW 0557 0597 2919 3302 3322

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

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OPERATOR MSN

AXM 2425 2612 2633 2656 2683 2699 2760 2816 2826 2842 2881 2885

2944 2989 3000 3117 3140 3154 3173 3182 3194 3201 3223 3232

3261 3277 3291 3299 3327 3338 3353 3370 3394 3404 3427 3448

3477 3486 3489 3505 3521 3536 3549 3568 3576 3582 3610 3628

3648 3679 3701 3715 3729 3765 3776 3813 3875 3963 3997 4019

4035 4070 4079 4088 4098 4126 4147 4263 4278 4293 4302 4333

4346 4361 4367 4386 4390

AZA 0434 0477 0488 0494 0495 0513 0514 0515 0516 0524 0526 0532

0576 0583 0586 0593 0599 0819 0848 0940 0951 0959 0999 1138

1168 1217 1220 1448 1457 1473 1480 1489 1722 1740 1745 1770

1779 2033 2057 2074 2083 2086 2101 2127 2869 2932 3076 3079

3080 3115 3178 3213 3295 3343 3362 3412 3464 3482 3563 3598

3609 3732 3815 3831 3846 3885 3906 3921 3956 3976 3978 4075

4108 4119 4143 4152 4195 4249

AZI 0527

AZW 0630 1973

B2V 0185

BAW 1014 1082 1115 1118 1142 1177 1193 1197 1222 1225 1232 1236

1239 1258 1261 1279 1295 1329 1338 1380 1384 1418 1423 1424

1440 1445 1466 1510 1513 1529 1537 1558 1574 1590 1594 1604

1606 1661 1665 1687 1689 1690 1696 1708 1711 1754 1760 1782

1814 1829 1871 1883 1899 1907 1910 1958 1987 2038 2040 2098

2188 2190 2194 2305 2320 2323 2324 2351 2363 2389 2429 2441

2466 2536 2653 2694 2697 2720 2799 2981 3049 3081 3235 3254

3290 3301 3314 3351 3468 3499 3512 3550 3607 3649 3697 3703

3721 3726 3912 3926 4007 4039 4185 4238 4265 4306

BEC 3199

BEL 0644 1086 1102 1160 1336 1388 1441 1493 1797 1838 1885 1963

2196 2230 2392 2400 2810 3255 3790 4275

BER 1629 1966 1988 1994 2003 2005 2619 3055 3093 3121 3415 3447

3516 3661 3689 3708 3728 3749 3865 3945 4013 4101 4161 4269

4291 4329 4334

BGF 3188

BGH 0349 1087 2844 2863 3139

BGY 1450 1723 2118 2645

BHP 2968 3245 3422 3604 4033 4187 4294

BIE 0519 0827 0891

BJN 3617

BKP 2254 2310 2417 2509 2531 2634 2648 2660 2664 2783 3421 3424

3454 3694 3759 3911

BQB 1703

BRS 2263

C9G 0772 0976 1010 1727 2277 2335 3492

CBJ 4388

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 5

6

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SERVICE BULLETIN

OPERATOR MSN

CCA 0876 0921 1296 2000 2007 2015 2172 2202 2205 2237 2269 2285

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

2805 2819 2839 2847 2890 3195 3200 3215 3221 3226 3250 3307

3329 3337 3461 3506 3523 3601 3623 3653 3655 3665 3678 3722

3725 3766 3806 3940 3973 4022 4031 4062 4091 4131 4180 4221

4283 4317 4318 4348 4377

CCM 3882 3952

CEB 2556 2586 2625 2638 2786 2790 2821 2831 2852 2876 2994 3048

3272 3433 3472 3487 3646 3762 3767

CEF 2801 3085

CES 0665 0754 0828 0838 0854 0897 0909 0914 0925 0939 0967 0984

0986 1005 1028 1030 1041 1070 1072 1093 1108 1285 1303 1312

1316 1330 1345 1357 1361 1377 1386 1532 1541 1542 1551 1601

1603 1639 1906 1911 1964 1981 2022 2034 2036 2049 2056 2068

2155 2171 2182 2199 2212 2219 2221 2235 2239 2244 2274 2309

2315 2437 2451 2478 2493 2498 2543 2549 2562 2591 2606 2627

2693 2757 2825 2882 2895 3168 3170 3186 3197 3233 3247 3249

3262 3471 3481 3559 3593 3611 3612 3613 3639 3650 3677 3682

3692 3716 3775 3793 3797 3870 3904 3929 3937 3965 3969 4027

4037 4043 4045 4111 4144 4186 4198 4209 4220 4239 4240 4252

4297 4309 4340 4342 4355 4374

CHH 2475 2557 2561 2581 2611 2617 2644 2733 2746 2849 2891 2985

3240 3285 3520 3548 3561 3578 3580 3638 3768 3842 3849 3851

3914 3958 3982 4042 4262

CIB 0774 0809 0884 0894 0905 0957 0971 1381 1402 1416 1437 1607

1968

CQH 0978 1686 1769 1852 1920 2939 3014 3023 3747 3819 4072 4093

4168 4244 4331 4366 4373 4375

CQN 0696 0698 0704 0705 3836 3876 3901 3903 3941

CSA 2719 2758 2789 3031 3043 3060 3094 3097 3406 3436 3452 3660

3892 4258

CSC 0540 0550 0551 0556 0591 0878 0902 0912 0915 0919 1007 1013

2313 2348 2396 2431 2510 2534 2597 2639 3114 3116 3124 3158

3167 3196 3210 3386 3449 3583 3591 3680 3730 3893 3962 3996

4018 4068 4288 4326 4378

CSN 0709 0712 0718 0720 0722 0849 0859 0881 0895 0900 0950 0966

1035 1039 1057 1596 1614 1776 1788 1971 1974 1986 1995 2004

2008 2067 2080 2200 2203 2232 2273 2354 2361 2371 2408 2426

2435 2484 2505 2506 2511 2519 2521 2530 2541 2546 2554 2555

2558 2574 2579 2637 2667 2680 2689 2701 2708 2713 2714 2741

2743 2759 2767 2770 2772 2796 2809 2815 2824 2834 2855 2861

2877 2899 2901 2915 2936 2940 2948 2950 2960 2969 2971 2986

3020 3067 3075 3112 3144 3217 3241 3251 3258 3269 3311 3342

3459 3493 3507 3552 3566 3587 3645 3681 3764 3784 3828 3847

3860 3867 3890 3910 3920 3934 3938 3951 3959 3981 3983 3999

4003 4017 4036 4038 4071 4140 4172 4184 4189 4194 4205 4217

4224 4225 4230 4232 4248 4260 4266 4271 4274 4279 4290 4292

4299 4322 4325 4338 4341 4350 4362 4365 4369 4370 4387

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 6

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SERVICE BULLETIN

OPERATOR MSN

CSZ 2672 2684 2841 2905 2909 2935 2973 2980 3131 3132 3153 3206

3366 3383 3435 3440 3456 3528 3599 3696 3698 3756 3848 3855

3887 3898 3935 3971 4010 4028 4159 4176 4208 4214 4226 4300

4359

CTN 0258 0767 0833 1009 1029 1237 1252

CTV 0839 0892 1635 2598 2692 3147 3148 3861

CYP 0256 2108 2275 2334 2343 2359

DAL 0118 0121 0125 0152 0153 0160 0171 0192 0197 0206 0208 0213

0262 0263 0272 0273 0281 0282 0297 0298 0306 0307 0318 0319

0329 0339 0340 0355 0358 0360 0367 0372 0380 0381 0387 0388

0399 0408 0410 0417 0418 0766 0778 0786 0801 0807 0818 0830

0832 0846 0903 0907 0911 0923 0962 0964 0981 0988 0996 1011

1037 1058 1062 1191 1230 1249 1324 1325 1346 1392 1414 1434

1453 1456 1483 1498 1501 1520 1535 1543 1549 1567 1570 1582

1633 1641 1646 1659 1662 1683 1685 1693 1709 1714 1738 1746

1752 1766 1774 1789 1796 1800 1810 1812 1815 1820 1824 1828

1833 1839 1875 1897 1923 1959 1976 1982 1990 2002 2013 2026

2039 2047 2082 2087 2092 2095

DCS 1053 3243

DKH 2975 3027 3234 3268 3368 3485 3596 3605 3967 3984 4064 4102

4154 4276

DLH 0069 0070 0071 0072 0078 0083 0086 0093 0094 0104 0110 0111

0116 0117 0135 0137 0147 0161 0172 0200 0201 0202 0209 0216

0267 0268 0269 0346 0412 0458 0468 0473 0474 0484 0493 0502

0505 0518 0560 0563 0564 0567 0595 0609 0610 0616 0623 0627

0636 0641 0651 0652 0679 0689 0692 0694 0699 0700 0717 0723

0729 0738 0744 0853 0860 0875 0887 0901 1016 1080 1161 1172

1188 1214 1260 1273 1337 1365 1367 3265 3339 3360 3387 3434

3592 3625 3864 3936 3987 4005 4016 4047 4054 4073 4085 4097

4120 4141 4153 4182 4191 4261 4289 4324 4332 4360 4363

DNV 1630 1805 1808 1841 2093 2241 2751 3065 3179

DQA 2347

DRK 2306 2346 3950

EAA 0386 0445

EDW 0942 0947 1026 2024

EIN 0926 1023 1094 1242 1394 1443 1983 2001 2191 2206 2217 2250

2256 2272 2294 2364 2374 2399 2409 2411 2432 2486 2542 2583

2635 3054 3102 3129 3169 3318 3345 3377 3501 3755 3781 3857

ETD 0350 1140 1159 1944 1945 1947 1955 2167 3004 3050 3676 3693

3713 3902 4066 4077 4124

ETJ 0325 0428

EVA 3363

EZD 0667 0743 0872 0874 1074 1286 2137 2141 2147 2576 2926 2956

3018 3064 3621

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 7

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SERVICE BULLETIN

OPERATOR MSN

EZY 2037 2043 2050 2053 2062 2120 2170 2181 2184 2245 2265 2271

2289 2300 2353 2360 2370 2385 2398 2402 2412 2420 2427 2450

2463 2471 2477 2481 2492 2495 2503 2512 2514 2527 2528 2538

2565 2578 2605 2636 2646 2677 2681 2691 2702 2709 2715 2727

2729 2735 2742 2744 2754 2765 2769 2777 2779 2782 2795 2803

2812 2818 2827 2829 2854 2860 2866 2873 2884 2923 2946 2959

3003 3036 3041 3053 3059 3061 3082 3084 3088 3090 3118 3122

3134 3137 3176 3184 3411 3413 3426 3432 3442 3466 3537 3544

3555 3569 3571 3608 3634 3675 3683 3702 3720 3735 3742 3746

3754 3763 3774 3788 3799 3805 3808 3810 3824 3843 3844 3845

3854 3871 3888 3909 3913 3922 3946 3953 3975 3979 3991 4006

4012 4014 4034 4040 4048 4056 4069 4076 4080 4087 4125 4129

4132 4157 4179 4196 4219 4233 4234 4250 4286 4313 4327 4380

4385

F2I 0085 0148 0220 0230 0243 0249 0251 0270 0294 0301 0373 0391

0400 0724 0758

FFT 1515 1579 1583 1615 1684 1759 1781 1786 1803 1806 1860 1943

1980 1997 2010 2012 2017 2019 2030 2103 2198 2209 2236 2240

2253 2258 2260 2287 2318 2325 2406 2448 2483 2518 2806 2836

2857 3205 3389 3431 4127 4204 4253 4254 4272 4307

FHY 0580 0771 0855 2524 2804 4207

FIN 0941 0961 1073 1107 1184 1185 1241 1309 1352 1364 1405 1470

1544 1588 1712 1913 1916 1978 1989 2065 2124 2146 2154 2208

2266

FLI 2186 3905

FPY 0112 0189 0279 0342 0395

FRN 0647 0660

FTZ 1068 1145 2176

G2X 0347 0674

G4I 1157 1795 2507

G8E 0594 2700 2763

GAF 3897 4060

GAP 0706 0745 2162 2183 3273

GCR 2338

GFA 4030 4059 4083 4146 4158 4188 4218 4255

GLG 1866 1872 1882 1925 2078 2126 4379

GMI 3019 3202 3407 3589 3818

GMR 1407 2128

GOW 3306 3597 3616 3798 3827 3900 3915

GWI 0162 0217 0218 0382 0401 0646 0654 0794 1077 1084 1089 1136

1147 1155 1170 1209 1277 2607 2628 2632 2813 2833 2976 3011

3128 3172 3193 3352 3358 3375 3500 3534 3839 3841 4166 4227

4256 4285

GZQ 1878

HAY 0716 0888 2745 3533 3560

HDA 0633 0756 0784 0812 0930 0993 1024 1253 1695 1721 1984 2021

2229 2238 2428 3369 3669 4023 4247

HKJ 2706 3073

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 8

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SERVICE BULLETIN

OPERATOR MSN

HRM 0293 0517 0535 0642 0666

HVN 0619 0648 0650 2255 2261 2267 2303 2974 3005 3013 3022 3198

3315 3355 3600 3737 3862 3964 3966 4136 4213 4277 4311 4315

I2L 0371 0579 0816 1004 2158 3834 3907

I2T 1631 1682

IAW 4044 4067

IBE 0158 0173 0176 0207 0223 0224 0266 0274 0323 0356 1021 1027

1047 1154 1362 1572 1655 1674 1681 1716 1793 1809 1836 2115

2220 2225 2242 2264 2270 2311 2357 2365 2381 2391 2472 2488

2563 2599 2736 2756 2889 2996 3078 3209 3320 3380 3443 3651

3744

IBS 1059 1067 1099 1101 1119 1516 1530 2104 2143 2248 2807

IGO 3357 3414 3453 3457 3497 3541 3618 3782 3863 3943 4008 4113

4156 4216 4312 4328 4384

IND 0357

IRA 0303 0312 0345 0530 0575 0857 2054

IRM 1202

ISR 4354

ISS 0737 0749 1125 1198 1823 1896 2102

IZG 0376 0407

JAT 2621 3252 3317

JAV 0029 2061

JBU 1123 1156 1173 1235 1240 1257 1270 1280 1302 1327 1398 1446

1452 1506 1528 1546 1557 1610 1650 1705 1739 1784 1785 1849

1861 1898 1904 1915 1917 1927 1948 2006 2020 2031 2042 2063

2075 2099 2125 2132 2136 2149 2150 2159 2160 2177 2201 2215

2231 2246 2259 2280 2284 2286 2307 2314 2336 2352 2368 2384

2386 2415 2447 2449 2461 2489 2491 2504 2520 2535 2577 2580

2640 2647 2671 2710 2725 2755 2781 2802 2814 2832 2848 2871

2880 2900 2945 2970 2977 2992 3029 3039 3072 3091 3119 3150

3190 3228 3263 3287 3348 3381 3416 3451 3479 3488 3517 3554

3572 3622 3659 3707 3724 3760 3800 3811

JSA 2316 2356 2423 2453 2604

JST 1195 1408 2169 2185 2197 2292 2299 2322 2329 2455 2515 2526

2537 2573 2587 2608 2642 2651 2703 2717 2766 2787 3474 3495

3547 3668 3717 3743 3783 3899 3916 3917 3948 4177 4178 4229

4245 4257 4303 4343 4356

JZR 2792 2822 3919 3939 4162

KAC 0181 0182 0195 2046 3957

KCA 0662

KFR 2650

KGL 0663 0668 0787 0852 0954 1060 1293 1554 2029 2077

KHO 0354 0414

KHV 2480

KKK 0604 0614 0675 0761 0823 0968 0974 1124 1438 1451 1503 1624

1730 1950 1953 2747 2753

KMF 0480

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 9

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SERVICE BULLETIN

OPERATOR MSN

KNE 1942 1965 2123 2569 2776 3218 3238 3256 3361 3396 3425 3475

3530 3787 3817 3868 3889 3894 3933 4055

KZR 1042 1204 3141 3484 3519 3614

LAN 1304 1332 1351 1355 1491 1512 1526 1548 1568 1626 1854 1858

1877 1903 2089 2096 2295 2304 2321 2572 2585 2845 2858 2864

2872 2886 2887 2892 2894 3264 3280 3319 3330 3535 3556 3663

3671 3770 3772 3779 4383

LBT 0793 0937 1121 1175 1597 1744 3480

LFO 0659

LJB 3985

LLC 0415 1715 2987

LLM 1054 1918 1956 1967 1969 1993 2413 2419 2439

LLP 0739 0883 1411 2016

LMJ 1868

LMU 0932 0943 0977 1366

LZB 2540 2596 3028 3309 3564 3780

MAC 3809 3833

MAU 1592 1936

MDL 2600

MEA 1977 2055 3736 3804 3837 4296 4339

MJF 4353

MJN 3723 4117

MLD 0622 0741

MLM 2592 4199

MLR 1946 2731 3106

MMA 0113 0114 0295 0316 0973 1180 1247 1791

MML 1706 1750

MON 0864 0983 1015 1045 1081 1153 1207 1320 1370 1413 1421 1428

1433 1571 1637 1707 1763 1794 1941 2105 2234 2730 2793 3546

3575

MSC 2937 2966 3282 3323

MSR 0165 0166 0178 0194 0198 0322 0366 0680 0687 0715 0725 2070

2073 2079 2088 2094

MXA 0252 0259 0260 0261 0275 0276 0296 0320 0321 0353

MYX 0566

NIA 3183 3219

NKS 2433 2470 2473 2476 2485 2490 2560 2567 2590 2603 2622 2673

2679 2698 2704 2711 2723 2797 2893 2898 2929 2942 2963 2978

2983 3007 3017 3026 3165 3393 3395 4206 4264 4321

NLV 1998 2210 2496 2502

NLY 2529 2668 2749 2867 2902 3504 3830 4231 4316 4368

NMA 1697 1732 2676

NMB 3346 3586

NVD 0211 0299 0375 0409 0419 0466 0528 1263 1778

NVR 2211 2216 2410

NWS 1219 1233 1276 1843 2649 2927 2933 3034 3120

OAL 3895

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 10

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SERVICE BULLETIN

OPERATOR MSN

OAW 1886

OBS 3758

OHY 0364 0385 0455 0471 0496 0543 0640 0661 0676 0792 0806 0810

0811 0835 0916 0963 0970 0995 1008 1482 1509 2571 2688

ONE 3001 3030 3062 3214 3216 3371 3390 3438 3469 3509 3585 3602

3606 3635 3642 4222 4287 4336

ORF 2566

OZW 0429 1922

PAL 2878 2925 2954 3087 3108 3187 3310 3455 3553 3579 3652 3731

PIC 0990 2331 2340 2670 2922 3012

PTR 0459 0537

QAF 0927 1335 3994 4114 4170

QTR 1487 1566 1648 1656 1773 1895 1928 1957 2097 2107 2121 2138

2161 2288 2341 3274 3397 3636 4110 4130 4173 4183 4382

R1T 1908

RBA 2023 2032 2135 2139 2195 3071

RBG 3152

RCT 1017

RFJ 0814

RJA 2953 3428 3522 3685 3803 3832

RJD 1618

RNV 0229

ROT 2931 2955 3220 3225

RYW 0569 3458

RZO 0795 2011 2390 3891

S2A 2366 2376

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

SAI 0542 0877 1497 2027 3089 3105 3270

SAS 1183 1383 1587 1619 1642 1675 1798 1807 1817 1848 2817 2850

2856 2883 2888 2911 2958 2990 3086 3159 3192 3227 3231 3292

3335

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

2028 2064 2076 2279 2369 2373 2464 2474 2618 2623 2641 2726

3070 3446 3473 3490 3494 3866 3880 4032 4150

SDM 0427 0525 0649 1130 1488 1560 1578 1654 1657 1679 1743 1753

1761 1767 1851 1863 1876 1890 2465 2497 2879 2913 2930 2964

3044

SFJ 2620 2658 2695 3025

SFW 0734 0994 1018

SGG 0799 0879 1390

SGX 1605

SHJ 0910

SHU 2222 3281 3298 3336

SKU 0179 0406 0447 1400 1523 2119 2129 2214 2249 2251 2283 2378

2380 2436 2460 2548

SLK 0899 0969 1228 1422 1561 1698 2058 2252 2517 2568 2775 3104

3570 3821 4118 4215 4259

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 11

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SERVICE BULLETIN

OPERATOR MSN

SMX 2995

SND 1880 1999

SNX 0289

SOL 0302

SRQ 3757 3801

SUD 3040

SVA 4015 4057 4081 4090 4092 4104 4115 4122 4135 4273 4314 4337

4349 4357 4364 4376 4391

SVR 0140 0157 0203 0735 0775 0815 0841 0991 1012 1063 1152 1199

1484 1720 1751 1777 1884 1901 1905 2117 2166 2175 2187 2278

2327 2349 2707 2998 3099 3107 3189

SVW 2921 3100 3133 3542 3856

SWM 0430 0476

SWR 0520 0522 0541 0545 0553 0559 0562 0574 0577 0578 0585 0596

0603 0612 0621 0635 0643 0664 0673 0681 0701 0703 0713 0727

0782 0987 1144 1762 1951 2134

SYA 3853 3872

SYR 0886 0918 1032 1076 1085 1117

TAE 0657 0934 0946 0949 1339 1368 1500 1934 2084 2659

TAI 1066 1334 1598 1625 1952 2282 2301 2339 2434 2444 2553 2610

2687 2862 2917 3042 3057 3103 3113 3248 3276 3378 3418 3510

3538 3577 3581 3869

TAK 2442 2446 3171 3331

TAM 1092 1096 1103 1139 1143 1158 1215 1246 1251 1376 1459 1486

1518 1575 1580 1591 1593 1595 1608 1613 1628 1652 1663 1672

1692 1717 1757 1771 1775 1801 1802 1804 1825 1826 1827 1831

1832 1835 1837 1855 1857 1888 1891 2014 2044 2372 2393 2467

2513 2661 2734 2737 2784 2838 2859 2896 2904 2924 3002 3032

3035 3047 3058 3111 3156 3180 3211 3222 3229 3266 3278 3284

3294 3313 3325 3391 3540 3565 3588 3594 3595 3630 3658 3662

3710 3727 3733 3750 3761 3816 3908 3972 4000 4163 4171 4192

4320 4352 4358 4389

TAP 0629 0750 0755 0763 0790 0821 0837 0870 0906 0917 0933 0945

0960 0979 0982 1034 1100 1106 1120 1127 1165 1181 1206 1231

1307 1399 1667 1713 1756 1765 1799 1816 2178 3769 3883 4021

4095 4106 4145

TAR 0119 0123 0124 0205 0370 0390 0402 0511 0869 0880 0958 0975

1187 1479 1700 3096 4344

TBJ 1485

TBZ 0361 0362 0405

TCW 0653 1787 1929 1975 2362

TCX 0677 1238 1250 1961 2060 2114

TGW 2724 2728 4181 4210

THY 1002 1856 1909 1996 2156 2164 2395 2401 2404 2414 2452 2522

2602 2609 2626 2631 2655 2738 2739 2823 2868 2916 2928 2934

2941 2984 2999 3010 3015 3126 3142 3185 3207 3208 3239 3257

3259 3283 3303 3308 3341 3350 3382 3405 3429 3525 3539 3558

3567 3603 3637 3654 3673 3688 3718 3719 3738 3896 3931 3949

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 12

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SERVICE BULLETIN

OPERATOR MSN

TJS 3513 3632 4169

TNA 0538 0555 0606 0731 0746 0791 0822 2914

TVS 2180

TWJ 2550

TXP 0607 0611 0617

UAL 0435 0439 0442 0450 0452 0454 0456 0457 0462 0463 0464 0465

0470 0472 0475 0479 0483 0485 0487 0489 0500 0503 0504 0506

0508 0510 0512 0523 0539 0568 0571 0587 0589 0592 0613 0638

0655 0678 0683 0686 0690 0702 0748 0751 0759 0780 0783 0788

0798 0804 0820 0824 0825 0826 0834 0836 0842 0843 0847 0850

0851 0858 0862 0865 0867 0871 0873 0882 0893 0898 0944 0948

0952 0955 0965 0980 0989 1001 1022 1031 1104 1105 1128 1146

1163 1192 1211 1243 1248 1266 1272 1282 1290 1291 1321 1341

1343 1359 1363 1401 1409 1420 1426 1427 1432 1435 1460 1469

1474 1475 1477 1495 1507 1508 1514 1522 1533 1538 1545 1555

1559 1569 1573 1581 1584 1585 1586 1600 1609 1617 1620 1627

1647 1649 1653 1664 1669 1671 1680 1688 1702 1728 1731 1737

1741 1755 1821 1840 1842 1845 1847 1865

UEA 2654 2696 2762 2774 2820 2835 3024 3706 4347

UKN 3260

ULG 0308 0314

UNA 3886

USA 0052 0053 0054 0055 0064 0065 0066 0067 0076 0077 0081 0082

0099 0317 0448 0565 0584 0762 0770 0803 0844 0856 0861 0863

0866 0868 0885 0889 0890 0896 0904 0922 0924 0929 0931 0953

0972 0997 1003 1019 1033 1038 1040 1043 1046 1049 1050 1051

1052 1055 1056 1061 1064 1065 1069 1075 1079 1083 1088 1095

1097 1109 1110 1111 1112 1114 1116 1122 1134 1135 1141 1148

1166 1178 1182 1196 1203 1205 1223 1224 1234 1245 1254 1264

1265 1268 1269 1274 1275 1281 1284 1287 1289 1294 1297 1298

1301 1310 1311 1313 1314 1315 1317 1319 1323 1326 1328 1331

1340 1342 1348 1350 1354 1358 1360 1369 1371 1373 1375 1378

1382 1389 1391 1393 1395 1397 1403 1406 1410 1412 1417 1419

1425 1431 1436 1442 1447 1455 1462 1463 1465 1472 1481 1490

1492 1496 1499 1517 1519 1521 1525 1527 1531 1534 1536 1539

1547 1552 1563 1565 1576 1621 1643 1644 1651 1666 1701 1704

1710 1724 1764 1792 1844 1935 2193 2302 2312 2405 2422 2430

2458 2482 2570 2595 2613 2615 2630 2669 2690 3584 3629 3633

3712 3740 3796 3858 3879 3881 3924 3928 3944 3960 3977 3989

3993 4025 4041 4050 4082 4086 4107 4123 4134 4149 4202 4242

UZB 4371

VAR 2383 2718

VIM 2732 3125 4270 4305

VIP 4151

VIV 2157 2443

VJC 2712 3739 3791 4049 4190 4193

VKG 1881 1887 1889 1921 1932 1954 1960 1972

VLE 1226

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 13

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SERVICE BULLETIN

OPERATOR MSN

VLG 0992 1171 1208 1210 1221 1349 1372 1396 1430 1461 1540 1550

1694 1736 1749 1862 1914 1933 1979 2168 2207 2223 2388 2407

2479 2589 2678 2761 2785 2794 2798 2843 2897 2962 2988 3083

3095 3109 3145 3151 3174 3203 3237 3293 3321 3376 3400 3529

3700 3704 3995 4128

VLK 0422 0714 0730 1200 1213 1379

VOI 2204 2296 2657 2666 2771 2780 2979 2997 3045 3069 3077 3175

3253 3279 3450 3463 3491 3524 3543 3590 3624 3672 3705

VRD 2616 2674 2740 2773 2778 2800 2811 2830 2851 2993 3016 3037

3101 3135 3155 3181 3204 3230 3324 3347 3349 3359 3398 3417

3445 3460 3465 3503 3656 3670 3684 3686

VRE 1429 2213 2228

VVC 1306 1454 1564 1725 1867

WAU 3531 3741

WGT 1212

WHT 1256 2440 2675

WOW 2457

WRC 0235 0645 0684 0760 0781 1869 2462 2682

WTJ 0548

WZZ 1834 1892 1902 2752 3127 3143 3166 3177 3354 3384 3409 3430

3562 3771 3807 3877 3927 3947 3968 4109 4174 4223 4246 4308

4323 4351 4372

XLF 0343

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 14

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SERVICE BULLETIN

(4) Configuration by MSN

MSN CONFIGURATION

0029 0045 0046 0047 0049 0050 0051 0052 0053 0054 0055

0056 0057 0059 0061 0063 0064 0065 0066 0067 0068 0069

0070 0071 0072 0073 0074 0075 0076 0077 0078 0080 0081

0082 0083 0084 0085 0086 0087 0088 0090 0093 0094 0095

0096 0099 0104 0110 0111 0112 0113 0114 0115 0116 0117

0118 0119 0121 0122 0123 0124 0125 0126 0127 0135 0137

0138 0140 0141 0142 0147 0148 0149 0150 0152 0153 0154

0155 0157 0158 0159 0160 0161 0162 0164 0165 0166 0167

0168 0171 0172 0173 0174 0175 0176 0178 0179 0181 0182

0183 0185 0189 0190 0192 0194 0195 0197 0198 0199 0200

0201 0202 0203 0205 0206 0207 0208 0209 0210 0211 0212

0213 0214 0216 0217 0218 0219 0220 0223 0224 0229 0230

0231 0232 0233 0234 0235 0237 0239 0240 0241 0242 0243

0244 0248 0249 0250 0251 0252 0253 0254 0255 0256 0258

0259 0260 0261 0262 0263 0264 0265 0266 0267 0268 0269

0270 0272 0273 0274 0275 0276 0277 0278 0279 0281 0282

0284 0285 0287 0289 0290 0291 0292 0293 0294 0295 0296

0297 0298 0299 0300 0301 0302 0303 0306 0307 0308 0309

0311 0312 0314 0316 0317 0318 0319 0320 0321 0322 0323

0324 0325 0328 0329 0330 0331 0332 0333 0334 0335 0339

0340 0341 0342 0343 0345 0346 0347 0349 0350 0351 0353

0354 0355 0356 0357 0358 0359 0360 0361 0362 0364 0366

0367 0368 0370 0371 0372 0373 0375 0376 0378 0380 0381

0382 0383 0384 0385 0386 0387 0388 0390 0391 0393 0395

0396 0398 0399 0400 0401 0402 0403 0404 0405 0406 0407

0408 0409 0410 0412 0413 0414 0415 0416 0417 0418 0419

0420 0421 0422 0423 0424 0426 0427 0428 0429 0430 0431

0432 0434 0435 0436 0438 0439 0440 0441 0442 0444 0445

0447 0448 0449 0450 0451 0452 0454 0455 0456 0457 0458

0459 0460 0461 0462 0463 0464 0465 0466 0468 0469 0470

0471 0472 0473 0474 0475 0476 0477 0479 0480 0482 0483

0484 0485 0486 0487 0488 0489 0490 0491 0492 0493 0494

0495 0496 0497 0498 0499 0500 0501 0502 0503 0504 0505

0506 0507 0508 0509 0510 0511 0512 0513 0514 0515 0516

0517 0518 0519 0520 0521 0522 0523 0524 0525 0526 0527

0528 0529 0530 0531 0532 0533 0534 0535 0537 0538 0539

0540 0541 0542 0543 0544 0545 0546 0548 0549 0550 0551

0552 0553 0554 0555 0556 0557 0558 0559 0560 0561 0562

0563 0564 0565 0566 0567 0568 0569 0570 0571 0572 0573

0574 0575 0576 0577 0578 0579 0580 0581 0582 0583 0584

0585 0586 0587 0588 0589 0591 0592 0593 0594 0595 0596

0597 0598 0599 0600 0603 0604 0605 0606 0607 0608 0609

0610 0611 0612 0613 0614 0616 0617 0618 0619 0620 0621

0622 0623 0625 0627 0629 0630 0631 0633 0634 0635 0636

0637 0638 0639 0640 0641 0642 0643 0644 0645 0646 0647

0648 0649 0650 0651 0652 0653 0654 0655 0656 0657 0658

0659 0660 0661 0662 0663 0664 0665 0666 0667 0668 0669

0670 0672 0673 0674 0675 0676 0677 0678 0679 0680 0681

0682 0683 0684 0685 0686 0687 0688 0689 0690 0691 0692

001

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 15

6

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

SERVICE BULLETIN

MSN CONFIGURATION

0693 0694 0695 0696 0697 0698 0699 0700 0701 0702 0703

0704 0705 0706 0707 0709 0711 0712 0713 0714 0715 0716

0717 0718 0719 0720 0721 0722 0723 0724 0725 0726 0727

0728 0729 0730 0731 0732 0733 0734 0735 0736 0737 0738

0739 0740 0741 0742 0743 0744 0745 0746 0747 0748 0749

0750 0751 0752 0754 0755 0756 0757 0758 0759 0760 0761

0762 0763 0764 0765 0766 0767 0768 0769 0770 0771 0772

0773 0774 0775 0776 0777 0778 0779 0780 0781 0782 0783

0784 0785 0786 0787 0788 0790 0791 0792 0793 0794 0795

0796 0797 0798 0799 0800 0801 0802 0803 0804 0805 0806

0807 0808 0809 0810 0811 0812 0813 0814 0815 0816 0817

0818 0819 0820 0821 0822 0823 0824 0825 0826 0827 0828

0829 0830 0831 0832 0833 0834 0835 0836 0837 0838 0839

0840 0841 0842 0843 0844 0845 0846 0847 0848 0849 0850

0851 0852 0853 0854 0855 0856 0857 0858 0859 0860 0861

0862 0863 0864 0865 0866 0867 0868 0869 0870 0871 0872

0873 0874 0875 0876 0877 0878 0879 0880 0881 0882 0883

0884 0885 0886 0887 0888 0889 0890 0891 0892 0893 0894

0895 0896 0897 0898 0899 0900 0901 0902 0903 0904 0905

0906 0907 0908 0909 0910 0911 0912 0913 0914 0915 0916

0917 0918 0919 0920 0921 0922 0923 0924 0925 0926 0927

0928 0929 0930 0931 0932 0933 0934 0935 0936 0937 0938

0939 0940 0941 0942 0943 0944 0945 0946 0947 0948 0949

0950 0951 0952 0953 0954 0955 0957 0958 0959 0960 0961

0962 0963 0964 0965 0966 0967 0968 0969 0970 0971 0972

0973 0974 0975 0976 0977 0978 0979 0980 0981 0982 0983

0984 0985 0986 0987 0988 0989 0990 0991 0992 0993 0994

0995 0996 0997 0998 0999 1000 1001 1002 1003 1004 1005

1006 1007 1008 1009 1010 1011 1012 1013 1014 1015 1016

1017 1018 1019 1020 1021 1022 1023 1024 1025 1026 1027

1028 1029 1030 1031 1032 1033 1034 1035 1036 1037 1038

1039 1040 1041 1042 1043 1045 1046 1047 1048 1049 1050

1051 1052 1053 1054 1055 1056 1057 1058 1059 1060 1061

1062 1063 1064 1065 1066 1067 1068 1069 1070 1071 1072

1073 1074 1075 1076 1077 1078 1079 1080 1081 1082 1083

1084 1085 1086 1087 1088 1089 1090 1091 1092 1093 1094

1095 1096 1097 1098 1099 1100 1101 1102 1103 1104 1105

1106 1107 1108 1109 1110 1111 1112 1114 1115 1116 1117

1118 1119 1120 1121 1122 1123 1124 1125 1126 1127 1128

1129 1130 1131 1132 1133 1134 1135 1136 1137 1138 1139

1140 1141 1142 1143 1144 1145 1146 1147 1148 1149 1150

1151 1152 1153 1154 1155 1156 1157 1158 1159 1160 1161

1162 1163 1164 1165 1166 1167 1168 1169 1170 1171 1172

1173 1174 1175 1176 1177 1178 1179 1180 1181 1182 1183

1184 1185 1187 1188 1189 1190 1191 1192 1193 1194 1195

1196 1197 1198 1199 1200 1201 1202 1203 1204 1205 1206

1207 1208 1209 1210 1211 1212 1213 1214 1215 1216 1217

1219 1220 1221 1222 1223 1224 1225 1226 1227 1228 1229

1230 1231 1232 1233 1234 1235 1236 1237 1238 1239 1240

1241 1242 1243 1244 1245 1246 1247 1248 1249 1250 1251

1252 1253 1254 1255 1256 1257 1258 1259 1260 1261 1262

001

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 16

6

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

SERVICE BULLETIN

MSN CONFIGURATION

1263 1264 1265 1266 1267 1268 1269 1270 1271 1272 1273

1274 1275 1276 1277 1279 1280 1281 1282 1283 1284 1285

1286 1287 1288 1289 1290 1291 1292 1293 1294 1295 1296

1297 1298 1299 1300 1301 1302 1303 1304 1305 1306 1307

1308 1309 1310 1311 1312 1313 1314 1315 1316 1317 1318

1319 1320 1321 1322 1323 1324 1325 1326 1327 1328 1329

1330 1331 1332 1334 1335 1336 1337 1338 1339 1340 1341

1342 1343 1344 1345 1346 1347 1348 1349 1350 1351 1352

1353 1354 1355 1356 1357 1358 1359 1360 1361 1362 1363

1364 1365 1366 1367 1368 1369 1370 1371 1372 1373 1375

1376 1377 1378 1379 1380 1381 1382 1383 1384 1385 1386

1387 1388 1389 1390 1391 1392 1393 1394 1395 1396 1397

1398 1399 1400 1401 1402 1403 1404 1405 1406 1407 1408

1409 1410 1411 1412 1413 1414 1415 1416 1417 1418 1419

1420 1421 1422 1423 1424 1425 1426 1427 1428 1429 1430

1431 1432 1433 1434 1435 1436 1437 1438 1439 1440 1441

1442 1443 1444 1445 1446 1447 1448 1449 1450 1451 1452

1453 1454 1455 1456 1457 1458 1459 1460 1461 1462 1463

1465 1466 1467 1468 1469 1470 1471 1472 1473 1474 1475

1476 1477 1478 1479 1480 1481 1482 1483 1484 1485 1486

1487 1488 1489 1490 1491 1492 1493 1494 1495 1496 1497

1498 1499 1500 1501 1502 1503 1504 1505 1506 1507 1508

1509 1510 1511 1512 1513 1514 1515 1516 1517 1518 1519

1520 1521 1522 1523 1524 1525 1526 1527 1528 1529 1530

1531 1532 1533 1534 1535 1536 1537 1538 1539 1540 1541

1542 1543 1544 1545 1546 1547 1548 1549 1550 1551 1552

1553 1554 1555 1556 1557 1558 1559 1560 1561 1562 1563

1564 1565 1566 1567 1568 1569 1570 1571 1572 1573 1574

1575 1576 1577 1578 1579 1580 1581 1582 1583 1584 1585

1586 1587 1588 1589 1590 1591 1592 1593 1594 1595 1596

1597 1598 1599 1600 1601 1602 1603 1604 1605 1606 1607

1608 1609 1610 1611 1612 1613 1614 1615 1616 1617 1618

1619 1620 1621 1622 1623 1624 1625 1626 1627 1628 1629

1630 1631 1632 1633 1634 1635 1636 1637 1638 1639 1640

1641 1642 1643 1644 1645 1646 1647 1648 1649 1650 1651

1652 1653 1654 1655 1656 1657 1658 1659 1661 1662 1663

1664 1665 1666 1667 1668 1669 1670 1671 1672 1673 1674

1675 1677 1678 1679 1680 1681 1682 1683 1684 1685 1686

1687 1688 1689 1690 1691 1692 1693 1694 1695 1696 1697

1698 1699 1700 1701 1702 1703 1704 1705 1706 1707 1708

1709 1710 1711 1712 1713 1714 1715 1716 1717 1718 1719

1720 1721 1722 1723 1724 1725 1726 1727 1728 1730 1731

1732 1733 1734 1735 1736 1737 1738 1739 1740 1741 1742

1743 1744 1745 1746 1747 1748 1749 1750 1751 1752 1753

1754 1755 1756 1757 1758 1759 1760 1761 1762 1763 1764

1765 1766 1767 1769 1770 1771 1772 1773 1774 1775 1776

1777 1778 1779 1780 1781 1782 1783 1784 1785 1786 1787

1788 1789 1790 1791 1792 1793 1794 1795 1796 1797 1798

1799 1800 1801 1802 1803 1804 1805 1806 1807 1808 1809

1810 1811 1812 1814 1815 1816 1817 1818 1819 1820 1821

1823 1824 1825 1826 1827 1828 1829 1831 1832 1833 1834

001

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 17

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

SERVICE BULLETIN

MSN CONFIGURATION

1835 1836 1837 1838 1839 1840 1841 1842 1843 1844 1845

1846 1847 1848 1849 1850 1851 1852 1853 1854 1855 1856

1857 1858 1859 1860 1861 1862 1863 1864 1865 1866 1867

1868 1869 1870 1871 1872 1873 1874 1875 1876 1877 1878

1879 1880 1881 1882 1883 1884 1885 1886 1887 1888 1889

1890 1891 1892 1893 1894 1895 1896 1897 1898 1899 1900

1901 1902 1903 1904 1905 1906 1907 1908 1909 1910 1911

1912 1913 1914 1915 1916 1917 1918 1920 1921 1922 1923

1924 1925 1926 1927 1928 1929 1931 1932 1933 1934 1935

1936 1937 1938 1940 1941 1942 1943 1944 1945 1946 1947

1948 1949 1950 1951 1952 1953 1954 1955 1956 1957 1958

1959 1960 1961 1962 1963 1964 1965 1966 1967 1968 1969

1970 1971 1972 1973 1974 1975 1976 1977 1978 1979 1980

1981 1982 1983 1984 1986 1987 1988 1989 1990 1993 1994

1995 1996 1997 1998 1999 2000 2001 2002 2003 2004 2005

2006 2007 2008 2009 2010 2011 2012 2013 2014 2015 2016

2017 2018 2019 2020 2021 2022 2023 2024 2026 2027 2028

2029 2030 2031 2032 2033 2034 2035 2036 2037 2038 2039

2040 2041 2042 2043 2044 2045 2046 2047 2048 2049 2050

2052 2053 2054 2055 2056 2057 2058 2059 2060 2061 2062

2063 2064 2065 2066 2067 2068 2069 2070 2071 2072 2073

2074 2075 2076 2077 2078 2079 2080 2081 2082 2083 2084

2085 2086 2087 2088 2089 2090 2091 2092 2093 2094 2095

2096 2097 2098 2099 2100 2101 2102 2103 2104 2105 2106

2107 2108 2109 2110 2112 2113 2114 2115 2116 2117 2118

2119 2120 2121 2122 2123 2124 2125 2126 2127 2128 2129

2130 2131 2132 2133 2134 2135 2136 2137 2138 2139 2140

2141 2142 2143 2144 2145 2146 2147 2148 2149 2150 2151

2152 2153 2154 2155 2156 2157 2158 2159 2160 2161 2162

2163 2164 2165 2166 2167 2168 2169 2170 2171 2172 2173

2174 2175 2176 2177 2178 2179 2180 2181 2182 2183 2184

2185 2186 2187 2188 2189 2190 2191 2192 2193 2194 2195

2196 2197 2198 2199 2200 2201 2202 2203 2204 2205 2206

2207 2208 2209 2210 2211 2212 2213 2214 2215 2216 2217

2219 2220 2221 2222 2223 2224 2225 2226 2227 2228 2229

2230 2231 2232 2233 2234 2235 2236 2237 2238 2239 2240

2241 2242 2243 2244 2245 2246 2247 2248 2249 2250 2251

2252 2253 2254 2255 2256 2257 2258 2259 2260 2261 2262

2263 2264 2265 2266 2267 2268 2269 2270 2271 2272 2273

2274 2275 2277 2278 2279 2280 2281 2282 2283 2284 2285

2286 2287 2288 2289 2290 2291 2292 2293 2294 2295 2296

2297 2298 2299 2300 2301 2302 2303 2304 2305 2306 2307

2308 2309 2310 2311 2312 2313 2314 2315 2316 2317 2318

2319 2320 2321 2322 2323 2324 2325 2326 2327 2328 2329

2330 2331 2332 2333 2334 2335 2336 2337 2338 2339 2340

2341 2342 2343 2344 2345 2346 2347 2348 2349 2350 2351

2352 2353 2354 2355 2356 2357 2358 2359 2360 2361 2362

2363 2364 2365 2366 2367 2368 2369 2370 2371 2372 2373

2374 2375 2376 2377 2378 2379 2380 2381 2382 2383 2384

2385 2386 2387 2388 2389 2390 2391 2392 2393 2394 2395

2396 2397 2398 2399 2400 2401 2402 2403 2404 2405 2406

001

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 18

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

SERVICE BULLETIN

MSN CONFIGURATION

2407 2408 2409 2410 2411 2412 2413 2414 2415 2416 2417

2418 2419 2420 2421 2422 2423 2425 2426 2427 2428 2429

2430 2431 2432 2433 2434 2435 2436 2437 2438 2439 2440

2441 2442 2443 2444 2445 2446 2447 2448 2449 2450 2451

2452 2453 2454 2455 2456 2457 2458 2459 2460 2461 2462

2463 2464 2465 2466 2467 2468 2469 2470 2471 2472 2473

2474 2475 2476 2477 2478 2479 2480 2481 2482 2483 2484

2485 2486 2487 2488 2489 2490 2491 2492 2493 2494 2495

2496 2497 2498 2499 2501 2502 2503 2504 2505 2506 2507

2508 2509 2510 2511 2512 2513 2514 2515 2516 2517 2518

2519 2520 2521 2522 2523 2524 2525 2526 2527 2528 2529

2530 2531 2532 2533 2534 2535 2536 2537 2538 2539 2540

2541 2542 2543 2544 2545 2546 2547 2548 2549 2550 2551

2552 2553 2554 2555 2556 2557 2558 2559 2560 2561 2562

2563 2564 2565 2566 2567 2568 2569 2570 2571 2572 2573

2574 2575 2576 2577 2578 2579 2580 2581 2582 2583 2584

2585 2586 2587 2588 2589 2590 2591 2592 2593 2594 2595

2596 2597 2598 2599 2600 2601 2602 2603 2604 2605 2606

2607 2608 2609 2610 2611 2612 2613 2614 2615 2616 2617

2618 2619 2620 2621 2622 2623 2624 2625 2626 2627 2628

2629 2630 2631 2632 2633 2634 2635 2636 2637 2638 2639

2640 2641 2642 2643 2644 2645 2646 2647 2648 2649 2650

2651 2652 2653 2654 2655 2656 2657 2658 2659 2660 2661

2662 2663 2664 2665 2666 2667 2668 2669 2670 2671 2672

2673 2674 2675 2676 2677 2678 2679 2680 2681 2682 2683

2684 2685 2686 2687 2688 2689 2690 2691 2692 2693 2694

2695 2696 2697 2698 2699 2700 2701 2702 2703 2704 2705

2706 2707 2708 2709 2710 2711 2712 2713 2714 2715 2716

2717 2718 2719 2720 2721 2723 2724 2725 2726 2727 2728

2729 2730 2731 2732 2733 2734 2735 2736 2737 2738 2739

2740 2741 2742 2743 2744 2745 2746 2747 2748 2749 2750

2751 2752 2753 2754 2755 2756 2757 2758 2759 2760 2761

2762 2763 2764 2765 2766 2767 2768 2769 2770 2771 2772

2773 2774 2775 2776 2777 2778 2779 2780 2781 2782 2783

2784 2785 2786 2787 2788 2789 2790 2791 2792 2793 2794

2795 2796 2797 2798 2799 2800 2801 2802 2803 2804 2805

2806 2807 2808 2809 2810 2811 2812 2813 2814 2815 2816

2817 2818 2819 2820 2821 2822 2823 2824 2825 2826 2827

2828 2829 2830 2831 2832 2833 2834 2835 2836 2837 2838

2839 2840 2841 2842 2843 2844 2845 2846 2847 2848 2849

2850 2851 2852 2853 2854 2855 2856 2857 2858 2859 2860

2861 2862 2863 2864 2865 2866 2867 2868 2869 2870 2871

2872 2873 2874 2875 2876 2877 2878 2879 2880 2881 2882

2883 2884 2885 2886 2887 2888 2889 2890 2891 2892 2893

2894 2895 2896 2897 2898 2899 2900 2901 2902 2903 2904

2905 2906 2907 2908 2909 2910 2911 2912 2913 2914 2915

2916 2917 2918 2919 2920 2921 2922 2923 2924 2925 2926

2927 2928 2929 2930 2931 2932 2933 2934 2935 2936 2937

2938 2939 2940 2941 2942 2943 2944 2945 2946 2947 2948

2949 2950 2951 2952 2953 2954 2955 2956 2957 2958 2959

2960 2961 2962 2963 2964 2965 2966 2967 2968 2969 2970

001

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 19

6

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

SERVICE BULLETIN

MSN CONFIGURATION

2971 2972 2973 2974 2975 2976 2977 2978 2979 2980 2981

2982 2983 2984 2985 2986 2987 2988 2989 2990 2991 2992

2993 2994 2995 2996 2997 2998 2999 3000 3001 3002 3003

3004 3005 3006 3007 3008 3009 3010 3011 3012 3013 3014

3015 3016 3017 3018 3019 3020 3021 3022 3023 3024 3025

3026 3027 3028 3029 3030 3031 3032 3033 3034 3035 3036

3037 3039 3040 3041 3042 3043 3044 3045 3046 3047 3048

3049 3050 3051 3052 3053 3054 3055 3056 3057 3058 3059

3060 3061 3062 3063 3064 3065 3066 3067 3068 3069 3070

3071 3072 3073 3074 3075 3076 3077 3078 3079 3080 3081

3082 3083 3084 3085 3086 3087 3088 3089 3090 3091 3093

3094 3095 3096 3097 3098 3099 3100 3101 3102 3103 3104

3105 3106 3107 3108 3109 3111 3112 3113 3114 3115 3116

3117 3118 3119 3120 3121 3122 3123 3124 3125 3126 3127

3128 3129 3130 3131 3132 3133 3134 3135 3136 3137 3138

3139 3140 3141 3142 3143 3144 3145 3146 3147 3148 3149

3150 3151 3152 3153 3154 3155 3156 3157 3158 3159 3160

3161 3162 3164 3165 3166 3167 3168 3169 3170 3171 3172

3173 3174 3175 3176 3177 3178 3179 3180 3181 3182 3183

3184 3185 3186 3187 3188 3189 3190 3191 3192 3193 3194

3195 3196 3197 3198 3199 3200 3201 3202 3203 3204 3205

3206 3207 3208 3209 3210 3211 3212 3213 3214 3215 3216

3217 3218 3219 3220 3221 3222 3223 3224 3225 3226 3227

3228 3229 3230 3231 3232 3233 3234 3235 3236 3237 3238

3239 3240 3241 3242 3243 3244 3245 3246 3247 3248 3249

3250 3251 3252 3253 3254 3255 3256 3257 3258 3259 3260

3261 3262 3263 3264 3265 3266 3267 3268 3269 3270 3271

3272 3273 3274 3275 3276 3277 3278 3279 3280 3281 3282

3283 3284 3285 3286 3287 3288 3289 3290 3291 3292 3293

3294 3295 3296 3297 3298 3299 3300 3301 3302 3303 3304

3305 3306 3307 3308 3309 3310 3311 3312 3313 3314 3315

3316 3317 3318 3319 3320 3321 3322 3323 3324 3325 3326

3327 3328 3329 3330 3331 3332 3333 3334 3335 3336 3337

3338 3339 3340 3341 3342 3343 3344 3345 3346 3347 3348

3349 3350 3351 3352 3353 3354 3355 3356 3357 3358 3359

3360 3361 3362 3363 3364 3365 3366 3367 3368 3369 3370

3371 3372 3373 3374 3375 3376 3377 3378 3379 3380 3381

3382 3383 3384 3385 3386 3387 3388 3389 3390 3391 3392

3393 3394 3395 3396 3397 3398 3399 3400 3401 3402 3403

3404 3405 3406 3407 3408 3409 3410 3411 3412 3413 3414

3415 3416 3417 3418 3419 3420 3421 3422 3423 3424 3425

3426 3427 3428 3429 3430 3431 3432 3433 3434 3435 3436

3437 3438 3439 3440 3441 3442 3443 3444 3445 3446 3447

3448 3449 3450 3451 3452 3453 3454 3455 3456 3457 3458

3459 3460 3461 3462 3463 3464 3465 3466 3467 3468 3469

3470 3471 3472 3473 3474 3475 3476 3477 3478 3479 3480

3481 3482 3483 3484 3485 3486 3487 3488 3489 3490 3491

3492 3493 3494 3495 3496 3497 3498 3499 3500 3501 3502

3503 3504 3505 3506 3507 3508 3509 3510 3511 3512 3513

3514 3515 3516 3517 3518 3519 3520 3521 3522 3523 3524

3525 3526 3527 3528 3529 3530 3531 3532 3533 3534 3535

001

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 20

6

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

SERVICE BULLETIN

MSN CONFIGURATION

3536 3537 3538 3539 3540 3541 3542 3543 3544 3545 3546

3547 3548 3549 3550 3551 3552 3553 3554 3555 3556 3557

3558 3559 3560 3561 3562 3563 3564 3565 3566 3567 3568

3569 3570 3571 3572 3573 3574 3575 3576 3577 3578 3579

3580 3581 3582 3583 3584 3585 3586 3587 3588 3589 3590

3591 3592 3593 3594 3595 3596 3597 3598 3599 3600 3601

3602 3603 3604 3605 3606 3607 3608 3609 3610 3611 3612

3613 3614 3615 3616 3617 3618 3619 3620 3621 3622 3623

3624 3625 3626 3627 3628 3629 3630 3631 3632 3633 3634

3635 3636 3637 3638 3639 3640 3641 3642 3643 3644 3645

3646 3647 3648 3649 3650 3651 3652 3653 3654 3655 3656

3657 3658 3659 3660 3661 3662 3663 3664 3665 3666 3667

3668 3669 3670 3671 3672 3673 3674 3675 3676 3677 3678

3679 3680 3681 3682 3683 3684 3685 3686 3687 3688 3689

3690 3691 3692 3693 3694 3695 3696 3697 3698 3699 3700

3701 3702 3703 3704 3705 3706 3707 3708 3709 3710 3711

3712 3713 3714 3715 3716 3717 3718 3719 3720 3721 3722

3723 3724 3725 3726 3727 3728 3729 3730 3731 3732 3733

3734 3735 3736 3737 3738 3739 3740 3741 3742 3743 3744

3745 3746 3747 3748 3749 3750 3751 3752 3753 3754 3755

3756 3757 3758 3759 3760 3761 3762 3763 3764 3765 3766

3767 3768 3769 3770 3771 3772 3773 3774 3775 3776 3777

3778 3779 3780 3781 3782 3783 3784 3785 3786 3787 3788

3789 3790 3791 3792 3793 3794 3795 3796 3797 3798 3799

3800 3801 3802 3803 3804 3805 3806 3807 3808 3809 3810

3811 3812 3813 3814 3815 3816 3817 3818 3819 3820 3821

3822 3823 3824 3825 3826 3827 3828 3829 3830 3831 3832

3833 3834 3835 3836 3837 3838 3839 3840 3841 3842 3843

3844 3845 3846 3847 3848 3849 3850 3851 3852 3853 3854

3855 3856 3857 3858 3859 3860 3861 3862 3863 3864 3865

3866 3867 3868 3869 3870 3871 3872 3873 3874 3875 3876

3877 3878 3879 3880 3881 3882 3883 3884 3885 3886 3887

3888 3889 3890 3891 3892 3893 3894 3895 3896 3897 3898

3899 3900 3901 3902 3903 3904 3905 3906 3907 3908 3909

3910 3911 3912 3913 3914 3915 3916 3917 3918 3919 3920

3921 3922 3923 3924 3925 3926 3927 3928 3929 3930 3931

3932 3933 3934 3935 3936 3937 3938 3939 3940 3941 3942

3943 3944 3945 3946 3947 3948 3949 3950 3951 3952 3953

3954 3955 3956 3957 3958 3959 3960 3961 3962 3963 3964

3965 3966 3967 3968 3969 3970 3971 3972 3973 3974 3975

3976 3977 3978 3979 3980 3981 3982 3983 3984 3985 3986

3987 3988 3989 3990 3991 3992 3993 3994 3995 3996 3997

3998 3999 4000 4001 4002 4003 4004 4005 4006 4007 4008

4009 4010 4011 4012 4013 4014 4015 4016 4017 4018 4019

4020 4021 4022 4023 4024 4025 4026 4027 4028 4029 4030

4031 4032 4033 4034 4035 4036 4037 4038 4039 4040 4041

4042 4043 4044 4045 4046 4047 4048 4049 4050 4051 4052

4053 4054 4055 4056 4057 4058 4059 4060 4061 4062 4063

4064 4065 4066 4067 4068 4069 4070 4071 4072 4073 4074

4075 4076 4077 4078 4079 4080 4081 4082 4083 4084 4085

4086 4087 4088 4089 4090 4091 4092 4093 4094 4095 4096

001

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 21

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MSN CONFIGURATION

4097 4098 4099 4100 4101 4102 4103 4104 4105 4106 4107

4108 4109 4110 4111 4112 4113 4114 4115 4116 4117 4118

4119 4120 4121 4122 4123 4124 4125 4126 4127 4128 4129

4130 4131 4132 4133 4134 4135 4136 4137 4138 4139 4140

4141 4142 4143 4144 4145 4146 4147 4148 4149 4150 4151

4152 4153 4154 4155 4156 4157 4158 4159 4160 4161 4162

4163 4164 4165 4166 4167 4168 4169 4170 4171 4172 4173

4174 4175 4176 4177 4178 4179 4180 4181 4182 4183 4184

4185 4186 4187 4188 4189 4190 4191 4192 4193 4194 4195

4196 4197 4198 4199 4200 4201 4202 4203 4204 4205 4206

4207 4208 4209 4210 4211 4212 4213 4214 4215 4216 4217

4218 4219 4220 4221 4222 4223 4224 4225 4226 4227 4228

4229 4230 4231 4232 4233 4234 4235 4236 4237 4238 4239

4240 4241 4242 4243 4244 4245 4246 4247 4248 4249 4250

4251 4252 4253 4254 4255 4256 4257 4258 4259 4260 4261

4262 4263 4264 4265 4266 4267 4268 4269 4270 4271 4272

4273 4274 4275 4276 4277 4278 4279 4280 4281 4282 4283

4284 4285 4286 4287 4288 4289 4290 4291 4292 4293 4294

4295 4296 4297 4298 4299 4300 4301 4302 4303 4304 4305

4306 4307 4308 4309 4310 4311 4312 4313 4314 4315 4316

4317 4318 4319 4320 4321 4322 4323 4324 4325 4326 4327

4328 4329 4330 4331 4332 4333 4334 4335 4336 4337 4338

4339 4340 4341 4342 4343 4344 4345 4346 4347 4348 4349

4350 4351 4352 4353 4354 4355 4356 4357 4358 4359 4360

4361 4362 4363 4364 4365 4366 4367 4368 4369 4370 4371

4372 4373 4374 4375 4376 4377 4378 4379 4380 4381 4382

4383 4384 4385 4386 4387 4388 4389 4390 4391

001

(5) Configuration definition

**CONF 001

Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a

standard configuration.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLD01

B. CONCURRENT REQUIREMENTS

None

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 22

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C. REASON

(1) History

On AIRBUS Single Aisle, Long Range and Wide Body 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 case of skin damage

was reported on a composite side panel of a rudder installed on an A310 aircraft.

Investigations have shown that the damage started from a skin panel area previously

repaired in-service. This repair was performed as per A310 SRM 55-41-12 Fig. 204

procedure. The new damage has been identified as a damage between the core and the

skin in the repaired area. This new damage has developed during normal operations due

to the variation of pressure during ground-air-ground cycles.

Following the above mentioned damage scenario, it has been identified that SRM

procedures need to be improved to ensure an adequate repair quality. An improper

bonding between skin and core during a repair may lead to a damage initiation and

propagation, which may not be detectable visually. A large rudder damage, resulting

from an undetected damage growth, could affect the handling quality of the aircraft.

(2) Objective/Action

This Service Bulletin details the inspection procedure to inspect affected rudders fitted

on A318/A319/A320/A321 aircraft for potential damage.

Different inspection procedures are necessary:

- Pulse thermography inspection

- Elasticity Laminate Checker (ELCH) inspection

- Ultrasonic Testing (UT) inspection

- Tap test inspection.

(3) Advantages

The accomplishment of this Service Bulletin will contribute to detect potential damage

around in-service repairs accomplished on rudders made of Carbon Fiber Reinforced

Plastic (CFRP) and Glass Fiber Reinforced Plastic (GFRP) with a honeycomb core.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

NOTE: The listed subtasks are not in sequence with the work steps.

To accomplish this Service Bulletin it is necessary to :

Task 551041-832-848-001: Inspection

(1) Check the rudder repair records

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 23

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(2) Identify the type, location and size of in-service repairs on the rudder side shell

CFRP areas in case of complete repair records since rudder Entry Into Service (EIS) are

available

(3) Do a pulse thermography inspection on the complete rudder side shell CFRP areas

to identify possible rudder in-service repairs in case of repair records are not complete or

not available

(4) Do the corrective actions in case of fluid ingress detected

(5) Do the ELCH and/or UT inspection around identified repairs

(6) Do terminating actions in case of no damage detected

(7) Inspect the rudder side shell upper GFRP areas

(8) Close the holes in case of a drilling thru the outer skin during paint thickness

measurement

(9) Identify the repair size by local sanding

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

Table 1, Config. 001 - Rudder special detailed inspection for repair detection

Condition Action Compliance time Repetitive interval

All aircraft Identify the Serial

Number of the installed

rudder in accordance

with the accomplishment

instructions Subtask

551041-832-201-001

Within 4 months from

original Service Bulletin

issue date

None

All aircraft Check the completeness

of the rudder repair

records

Within 4 months from

original Service Bulletin

issue date

None

All aircraft Report information

about the repair records

to AIRBUS

Within 4 months from

original Service Bulletin

issue date

None

Repair records are not

complete or not

available

Continue with the

actions given in table 2A

for CFRP areas

Refer to table 2A Refer to table 2A

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 24

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Table 1, Config. 001 - Rudder special detailed inspection for repair detection

Condition Action Compliance time Repetitive interval

Repair records are not

complete or not

available

Continue with the

actions given in table 2B

for GFRP areas

Refer to table 2B Refer to table 2B

Complete repair records

since rudder Entry Into

Service (EIS) are

available

Continue with the

actions given in table

2C for CFRP areas

Refer to table 2C Refer to table 2C

Complete repair records

since rudder EIS are

available

Continue with the

actions given in table

2D for GFRP areas

Refer to table 2D Refer to table 2D

Table 2A, Config. 001 - Repair records are not complete or not available (CFRP areas)

Condition Action Compliance time Repetitive interval

Repair records are not

complete or not

available

Report undocumented

rudder Serial Number

list to AIRBUS to get

related rudder

manufacturing rework

data

3 months in advance

before pulse

thermography inspection

is scheduled

None

Repair records are not

complete or not

available

Make sure that the paint

thickness in all areas to

be inspected does not

exceed the limits given

in the accomplishment

instructions Subtask

551041-832-203-001

Within 24 months from

original Service Bulletin

issue date, before the

pulse thermography

inspection

None

Repair records are not

complete or not

available

Do a pulse

thermography inspection

on the complete side

shells (LH/RH) to

identify repairs in

accordance with the

accomplishment

instructions Subtask

551041-832-203-001

Within 24 months from

original Service Bulletin

issue date

None

No repair detected Report to AIRBUS

No further action

necessary in

accordance with this

Service Bulletin

Within 1 month from the

pulse thermography

inspection

None

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

Report to AIRBUS Within 1 month from the

pulse thermography

inspection

None

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 25

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Table 2A, Config. 001 - Repair records are not complete or not available (CFRP areas)

Condition Action Compliance time Repetitive interval

Repairs in the booster

area > 55000 mm2

(85.25 sq.in.) or not in

the booster area

detected during pulse

thermography inspection

Do an ELCH and/or UT

inspection around the

identified repairs in

accordance with the

accomplishment

instructions Subtask

551041-832-205-001

Within 24 months from

original Service Bulletin

issue date

None

Fluid ingress detected

during pulse

thermography/UT

inspection

Continue with the

actions given in table 3

Refer to table 3 Refer to table 3

Damage detected during

ELCH and/or UT

inspection

Provide a detailed

damage report and

report to AIRBUS and

follow their instructions

Before next flight None

No damage detected Continue with the

actions given in table 4

Refer to table 4 Refer to table 4

Table 2B, Config. 001 - Repair records are not complete or not available (GFRP areas)

Condition Action Compliance time Repetitive interval

Repair records are not

complete or not

available

Make sure that the paint

thickness in all areas to

be inspected does not

exceed the limits given

in the accomplishment

instructions Subtask

551041-832-207-001

Within 24 months from

original Service Bulletin

issue date, before the

pulse thermography

inspection

None

Repair records are not

complete or not

available

Do a pulse

thermography inspection

on the complete GFRP

area in accordance with

the accomplishment

instructions Subtask

551041-832-207-001

Within 24 months from

original Service Bulletin

issue date

None

Repair records are not

complete or not

available

In case of findings, mark

the repairs which are

not manufacturing

reworks

Within 24 months from

original Service Bulletin

issue date

None

Repair records are not

complete or not

available

Do a Tap test inspection

on the complete GFRP

area to identify skin to

core disbonding in

accordance with the

accomplishment

instructions Subtask

551041-832-207-001

Within 24 months from

original Service Bulletin

issue date

None

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 26

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Table 2B, Config. 001 - Repair records are not complete or not available (GFRP areas)

Condition Action Compliance time Repetitive interval

No skin to core

disbonding but repairs

identified

Do an ELCH and/or UT

inspection on the

complete GFRP area in

accordance with the

accomplishment

instructions Subtask

551041-832-205-001

Within 24 months from

original Service Bulletin

issue date

None

Fluid ingress detected

during pulse

thermography/UT

inspection

Continue with the

actions given in table 3

Refer to table 3 Refer to table 3

Damage detected during

Tap test/ELCH and/or

UT inspection

Provide a detailed

damage report and

report to AIRBUS and

follow their instructions

Before next flight None

No damage detected Continue with the

actions given in table 4

Refer to table 4 Refer to table 4

Table 2C, Config. 001 - Repair records since rudder EIS are complete (CFRP areas)

Condition Action Compliance time Repetitive interval

No repair performed or

repair not to be

inspected in accordance

with this Service Bulletin

Report to AIRBUS

No further action

necessary in

accordance with this

Service Bulletin

Within 24 months from

original Service Bulletin

issue date

None

Repair is performed

since rudder EIS

Identify the repair type

in accordance with the

accomplishment

instructions Subtask

551041-832-202-001

Within 24 months from

original Service Bulletin

issue date

None

Repair identified as type

to be inspected

Make sure that the paint

thickness in all areas to

be inspected does not

exceed the limits given

in the accomplishment

instructions

551041-832-202-001

Within 24 months from

original Service Bulletin

issue date, before the

pulse thermography

inspection

None

Repair identified as type

to be inspected

Do a pulse

thermography inspection

on repair location in

accordance with the

accomplishment

instructions Subtask

551041-832-202-001

Within 24 months from

original Service Bulletin

issue date

None

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 27

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Table 2C, Config. 001 - Repair records since rudder EIS are complete (CFRP areas)

Condition Action Compliance time Repetitive interval

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

during pulse

thermography inspection

Report to AIRBUS Within 1 month from

pulse thermography

inspection

None

Repairs in the booster

area > 55000 mm2

(85.25 sq.in.) or not in

the booster area

detected during pulse

thermography inspection

Do an ELCH and/or UT

inspection around the

identified repairs in

accordance with the

accomplishment

instructions Subtask

551041-832-205-001

Within 24 months from

original Service Bulletin

issue date

None

Fluid ingress detected

during pulse

thermography/UT

inspection

Continue with the

actions given in table 3

Refer to table 3 Refer to table 3

Damage detected during

ELCH and/or UT

inspection

Provide a detailed

damage report, report to

AIRBUS and follow their

instructions

Before next flight None

No damage detected

during ELCH and/or UT

inspection

Continue with the

actions given in table 4

Refer to table 4 Refer to table 4

Table 2D, Config. 001 - Repair records since rudder EIS are complete (GFRP areas)

Condition Action Compliance time Repetitive interval

No repair performed or

repair not to be

inspected in accordance

with this Service Bulletin

Report to AIRBUS

No further action

necessary in

accordance with this

Service Bulletin

Within 24 months from

original Service Bulletin

issue date

None

Repair performed and

identified as type to be

inspected

Make sure that the paint

thickness in all areas to

be inspected does not

exceed the limits given

in the accomplishment

instructions Subtask

551041-832-207-001

Within 24 months from

original Service Bulletin

issue date, before the

pulse thermography

inspection

None

Repair identified as type

to be inspected

Do a pulse

thermography inspection

on repair location in

accordance with the

accomplishment

instructions Subtask

551041-832-207-001

Within 24 months from

original Service Bulletin

issue date

None

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 28

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Table 2D, Config. 001 - Repair records since rudder EIS are complete (GFRP areas)

Condition Action Compliance time Repetitive interval

Repair type A-A

identified

Do a Tap test inspection

on the identified repair

in accordance with the

accomplishment

instructions Subtask

551041-832-207-001

Within 24 months from

original Service Bulletin

issue date

None

All other repairs Do an ELCH and/or UT

inspection around the

identified repairs in

accordance with the

accomplishment

instructions Subtask

551041-832-205-001

Within 24 months from

original Service Bulletin

issue date

None

Fluid ingress detected

during pulse

thermography/UT

inspection

Continue with the

actions given in table 3

Refer to table 3 Refer to table 3

Damage detected during

Tap test/ELCH and/or

UT inspection

Provide a detailed

damage report, report to

AIRBUS and follow their

instructions

Before next flight None

No damage detected

during ELCH and/or UT

inspection

Continue with the

actions given in table 4

Refer to table 4 Refer to table 4

Table 3, Config. 001 - Fluid ingress detected

Condition Action Compliance time Repetitive interval

Fluid ingress detected Do an ELCH and/or UT

inspection around the

identified fluid ingress in

accordance with the

accomplishment

instructions Subtask

551041-832-205-001

Before next flight None

Damage detected

around the identified

fluid ingress

Report to AIRBUS and

follow their instructions

Before next flight None

Local single spot fluid

ingress =< 1500 mm2

(2.33 sq.in.) detected

(no damage detected

around the identified

fluid ingress)

Report to AIRBUS Within 1 month from

pulse thermography

inspection

None

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 29

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Table 3, Config. 001 - Fluid ingress detected

Condition Action Compliance time Repetitive interval

Maximum of 5 Local

single spots fluid ingress

per side shell > 1500

mm2 (2.33 sq.in.) and

=< 5000 mm2 (7.75

sq.in.) detected (no

damage detected

around the identified

fluid ingress)

Drain by core ventilation

in accordance with the

accomplishment

instructions Subtask

551041-832-204-001

Before next flight None

Core ventilation done Option 1:

Close the holes with

adhesive tape

Before next flight None

Holes closed with tape Option 1:

Do repetitive detailed

inspections of the

restored area for loose

or lost tape

Within 750 FC after

closing the holes

At intervals not

exceeding 750 FC

Loose or lost tape found Option 1:

Close the holes again

with adhesive tape or

refer to Option 2

Before next flight None

Core ventilation done Option 2:

Close the holes with

GFRP plies

Before next flight None

Maximum of 5 Local

single spots fluid ingress

per side shell > 1500

mm2 (2.33 sq.in.) and

=< 5000 mm2 (7.75

sq.in.) detected (no

damage detected

around the identified

fluid ingress)

Option 1 and 2:

Repetitive pulse

thermography

inspections in

accordance with the

accomplishment

instructions Subtask

551041-832-204-001

Within 1000 FC after

closing the holes

Within intervals of 1000

FC until repair

Maximum of 5 Local

single spots fluid ingress

per side shell > 1500

mm2 (2.33 sq.in.) and

=< 5000 mm2 (7.75

sq.in.) detected (no

damage detected

around the identified

fluid ingress)

Do the repair Within 4500 FC, but not

exceeding 24 months

from the first inspection

None

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 30

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Table 3, Config. 001 - Fluid ingress detected

Condition Action Compliance time Repetitive interval

Maximum of 5 Local

single spots fluid ingress

per side shell > 1500

mm2 (2.33 sq.in.) and

=< 5000 mm2 (7.75

sq.in.) detected (no

damage detected

around the identified

fluid ingress)

Report to AIRBUS Within 1 month from the

repair

None

More than 5 Local

single spots fluid ingress

per side shell > 1500

mm2 (2.33 sq.in.) and

=< 5000 mm2 (7.75

sq.in.) detected (no

damage detected

around the identified

fluid ingress)

Report to AIRBUS and

follow their instructions

Before next flight None

Local single spot fluid

ingress > 5000 mm2

(7.75 sq.in.) detected

(no damage detected

around the identified

fluid ingress)

Report to AIRBUS and

follow their instructions

Before next flight None

Tables 4.A thru 4.D, Config. 001: No damage detected during ELCH/UT inspection:

For an identified repair size of a maximum of 10000 mm2 (15.50 sq.in.), continue with

table 4.A.

For an identified repair size larger than 10000 mm2 (15.50 sq.in.) and up to 20000

mm2(31.00 sq.in.), continue with table 4.B.

For an identified repair size larger than 20000 mm2 (31.00 sq.in.) and up to 80000 mm2

(124 sq.in.), continue with table 4.C.

For an identified repair size larger than 80000 mm2 (124 sq.in.), continue with table 4.D.

Table 4.A, Config. 001 - Identified repair size of a maximum of 10000 mm2 (15.50 sq.in.)

Condition Action Compliance time Repetitive interval

Repair size =< 10000

mm2 (15.50 sq.in.)

Provide detailed

information about the

identified repair and

report to AIRBUS

Within 1 month from

ELCH/UT inspection

None

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 31

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Table 4.B, Config. 001 - Identified repair size larger than 10000 mm2 (15.50 sq.in.) and up to 20000

mm2(31.00 sq.in.)

Condition Action Compliance time Repetitive interval

Repair size > 10000

mm2 (15.50 sq.in.) and

=< 20000 mm2 (31.00

sq.in.)

Option 1:

Do the core ventilation

thru the inner skin in

accordance with the

accomplishment

instructions Subtask

551041-832-204-001

Before next flight None

Core ventilation done Option 1:

Hole closing option 1:

Close the holes with

adhesive tape

Before next flight None

Holes closed with tape Option 1:

Hole closing option 1:

Do repetitive detailed

inspections of the

restored area for loose

or lost tape

Within 750 FC after

closing the holes

At intervals not

exceeding 750 FC

Loose or lost tape found Option 1:

Hole closing option 1:

Close the holes again

with adhesive tape or

refer to hole closing

option 2

Before next flight None

Core ventilation done Option 1:

Hole closing option 2:

Close the holes with

GFRP plies

Before next flight None

Core ventilation done Option 1:

Report detailed

information about the

identified repair and the

planned terminating

action to AIRBUS

Within 1 month from first

ELCH/UT inspection

None

Core ventilation done Option 1:

Do the repair in

accordance with the

SRM at the identified

repair location

Within 4500 FC, not

exceeding 24 months,

from the first inspection

date

None

Repair size > 10000

mm2 (15.50 sq.in.) and

=< 20000 mm2 (31.00

sq.in.)

Option 2:

Do repetitive ELCH/UT

inspections around the

identified repair area in

accordance with the

accomplishment

instructions Subtask

551041-832-205-001

Within 750 FC from first

ELCH/UT inspection

Every 750 FC from last

ELCH/UT inspection

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 32

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Table 4.B, Config. 001 - Identified repair size larger than 10000 mm2 (15.50 sq.in.) and up to 20000

mm2(31.00 sq.in.)

Condition Action Compliance time Repetitive interval

Findings during

repetitive ELCH/UT

inspections

Report to AIRBUS and

follow their instructions

Before next flight None

No findings during

repetitive ELCH/UT

inspections

Option 2:

Report detailed

information about the

identified repair and the

planned terminating

action to AIRBUS

Within 1 month from

ELCH/UT inspection

None

No findings during

repetitive ELCH/UT

inspections

Do the repair in

accordance with the

SRM at the identified

repair location

Within 4500 FC, not

exceeding 24 months,

from the first inspection

date

None

Table 4.C, Config. 001 - Identified repair size larger than 20000 mm2 (31.00 sq.in.) and up to 80000

mm2 (124 sq.in.)

Condition Action Compliance time Repetitive interval

Repair size > 20000

mm2 (31.00 sq.in.) and

=< 80000 mm2 (124

sq.in.)

Do the core ventilation

thru inner skin in

accordance with the

accomplishment

instructions Subtask

551041-832-204-001

Before next flight None

Core ventilation done Option 1:

Close the holes with

adhesive tape

Before next flight None

Holes closed with tape Option 1:

Do repetitive detailed

inspections of the

restored area for loose

or lost tape

Within 750 FC after

closing the holes

At intervals not

exceeding 750 FC

Loose or lost tape found Option 1:

Close the holes again

with adhesive tape or

refer to Option 2

Before next flight None

Core ventilation done Option 2:

Close the holes with

GFRP plies

Before next flight None

Repair size > 20000

mm2 (31.00 sq.in.) and

=< 80000 mm2 (124

sq.in.)

Report detailed

information about the

identified repair and the

planned terminating

action to AIRBUS

Within 1 month from first

ELCH/UT inspection

None

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 33

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Table 4.C, Config. 001 - Identified repair size larger than 20000 mm2 (31.00 sq.in.) and up to 80000

mm2 (124 sq.in.)

Condition Action Compliance time Repetitive interval

Core ventilation done

and repair size =<

30000 mm2 (46.50

sq.in.)

Do the repair in

accordance with the

SRM at the identified

repair location

Within 4500 FC, not

exceeding 24 months,

from the first inspection

date

None

Core ventilation done

and repair size > 30000

mm2 (46.50 sq.in.) and

=< 80000 mm2 (124

sq.in.)

Do the repair in

accordance with the

SRM and additional

instructions from

AIRBUS

Within 4500 FC, not

exceeding 24 months,

from the first inspection

date

None

Table 4.D, Config. 001 - Identified repair size larger than 80000 mm2 (124 sq.in.)

Condition Action Compliance time Repetitive interval

Repair size > 80000

mm2 (124 sq.in.)

Do the core ventilation

thru inner skin in

accordance with the

accomplishment

instructions Subtask

551041-832-204-001

Before next flight None

Core ventilation done Option 1:

Close the holes with

adhesive tape

Before next flight None

Holes closed with tape Option 1:

Do repetitive detailed

inspections of the

restored area for loose

or lost tape

Within 750 FC after

closing the holes

At intervals not

exceeding 750 FC

Loose or lost tape found Option 1:

Close the holes again

with adhesive tape or

refer to Option 2

Before next flight None

Core ventilation done Option 2:

Close the holes with

GFRP plies

Before next flight None

Repair size > 80000

mm2 (124 sq.in.)

Report detailed

information about the

identified repair and the

planned terminating

action to AIRBUS

Within 1 month from first

ELCH/UT inspection

None

Repair size > 80000

mm2 (124 sq.in.)

Replace the affected

rudder shell

OR

Replace the rudder

No further action

necessary in

accordance with this

Service Bulletin

Within 4500 FC, not

exceeding 24 months,

from the first inspection

date

None

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 34

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Table 5, Config. 001 - Hole closing in case of damaged outer skin during paint thickness

measurement

Condition Action Compliance time Repetitive interval

Sandwich structure

damaged

Option 1:

Close the holes with

resin and adhesive tape

Before next flight None

Holes closed Option 1:

Restore the surface

protection

Within 4500 FC from the

pulse thermography

inspection

None

Sandwich structure

damaged

Option 2:

Do the permanent

restoration procedure

Before next flight None

Table 6.A, Config. 001 - Identify the repair size by local sanding

Condition Action Compliance time Repetitive interval

Repair performed and

identified as type to be

inspected

Identify paint thickness

and primer

Within 24 months from

original Service Bulletin

issue date

None

Repair performed and

identified as type to be

inspected

Do local sanding on top

and around the repair

up to the initial basic

primer

Within 24 months from

original Service Bulletin

issue date

None

Largest repair ply is not

visible

Continue with the

actions given in 6.B

Before next flight None

Largest repair ply is

visible

Remove the dust and

dry the area

Before next flight None

Largest repair ply is

visible

Inspect the sanded area

for damage

Before next flight None

Damage found Do the damage

assessment

Before next flight None

No damage found Mark the repair on the

rudder surface

Before next flight None

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

Restore the surface

protection

Before next flight None

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

Report to AIRBUS Within 1 month None

Repairs in the booster

area > 55000 mm2

(85.25 sq.in.) or not in

the booster area

detected

Do an ELCH and/or UT

inspection around the

identified repairs in

accordance with the

accomplishment

instructions Subtask

551041-832-205-001

Before next flight None

Fluid ingress detected

during UT inspection

Continue with the

actions given in table 3

Refer to table 3 Refer to table 3

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 35

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Table 6.A, Config. 001 - Identify the repair size by local sanding

Condition Action Compliance time Repetitive interval

Damage detected during

ELCH and/or UT

inspection

Provide a detailed

damage report, report to

AIRBUS and follow their

instructions

Before next flight None

No damage detected

during ELCH and/or UT

inspection

Continue with the

actions given in table 4

Refer to table 4 Refer to table 4

Table 6.B, Config. 001 - Identify the repair size by local sanding - largest repair ply not visible

Condition Action Compliance time Repetitive interval

Largest repair ply is not

visible

Continue local sanding

up to the pore

filler/adhesive

Before next flight None

Largest repair ply is

visible now

Remove the dust and

dry the area

Before next flight None

Largest repair ply is still

not visible

Continue with the

actions given in table

6.C for CFRP areas and

table 6.D for GFRP

areas

Before next flight None

Largest repair ply is

visible now

Inspect the sanded area

for damage

Before next flight None

Damage found Do the damage

assessment

Before next flight None

No damage found Mark the repair on the

rudder surface

Before next flight None

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

Restore the surface

protection

Before next flight None

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

Report to AIRBUS Within 1 month None

Repairs in the booster

area > 55000 mm2

(85.25 sq.in.) or not in

the booster area

detected

Do an ELCH and/or UT

inspection around the

identified repairs in

accordance with the

accomplishment

instructions Subtask

551041-832-205-001

Before next flight None

Fluid ingress detected

during UT inspection

Continue with the

actions given in table 3

Refer to table 3 Refer to table 3

Damage detected during

ELCH and/or UT

inspection

Provide a detailed

damage report, report to

AIRBUS and follow their

instructions

Before next flight None

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 36

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Table 6.B, Config. 001 - Identify the repair size by local sanding - largest repair ply not visible

Condition Action Compliance time Repetitive interval

No damage detected

during ELCH and/or UT

inspection

Continue with the

actions given in table 4

Refer to table 4 Refer to table 4

Table 6.C, Config. 001 - Do the pulse thermography inspection (CFRP areas)

Condition Action Compliance time Repetitive interval

Largest repair ply is still

not visible

Do a pulse

thermography inspection

on repair location in

accordance with the

accomplishment

instructions Subtask

551041-832-202-001

Before next flight None

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

during pulse

thermography inspection

Restore the surface

protection

Before next flight None

Repairs in the booster

area =< 55000 mm2

(85.25 sq.in.) detected

during pulse

thermography inspection

Report to AIRBUS Within 1 month None

Repairs in the booster

area > 55000 mm2

(85.25 sq.in.) or not in

the booster area

detected during pulse

thermography inspection

Do an ELCH and/or UT

inspection around the

identified repairs in

accordance with the

accomplishment

instructions Subtask

551041-832-205-001

Before next flight None

Fluid ingress detected

during pulse

thermography/UT

inspection

Continue with the

actions given in table 3

Refer to table 3 Refer to table 3

Damage detected during

ELCH and/or UT

inspection

Provide a detailed

damage report, report to

AIRBUS and follow their

instructions

Before next flight None

No damage detected

during ELCH and/or UT

inspection

Continue with the

actions given in table 4

Refer to table 4 Refer to table 4

Table 6.D, Config. 001 - Do the pulse thermography inspection (GFRP areas)

Condition Action Compliance time Repetitive interval

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 37

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Repair identified as type

to be inspected

Do a pulse

thermography inspection

on repair location in

accordance with the

accomplishment

instructions Subtask

551041-832-207-001

Before next flight None

Repair type A-A

identified

Do a Tap test inspection

on the identified repair

in accordance with the

accomplishment

instructions Subtask

551041-832-207-001

Before next flight None

All other repairs Do an ELCH and/or UT

inspection around the

identified repairs in

accordance with the

accomplishment

instructions Subtask

551041-832-205-001

Before next flight None

Fluid ingress detected

during pulse

thermography/UT

inspection

Continue with the

actions given in table 3

Refer to table 3 Refer to table 3

Damage detected during

Tap test/ELCH and/or

UT inspection

Provide a detailed

damage report, report to

AIRBUS and follow their

instructions

Before next flight None

No damage detected

during ELCH and/or UT

inspection

Continue with the

actions given in table 4

Refer to table 4 Refer to table 4

F. APPROVAL

The technical content of this document is approved under authority of 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.

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 38

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Task 551041-832-848-001: Inspection

Get Access 1.00

On Aircraft

Check the rudder repair records 4.00

Identify the type, location and size of in-service repairs

on the rudder side shell CFRP areas in case of

complete repair records since rudder Entry Into Service

(EIS) are available

0

Do a pulse thermography inspection on the complete

rudder side shell CFRP areas to identify possible

rudder in-service repairs in case of repair records are

not complete or not available

32

Do the corrective actions in case of fluid ingress

detected

0

Do the ELCH and/or UT inspection around identified

repairs

0

Do terminating actions in case of no damage detected 0

Inspect the rudder side shell upper GFRP areas 0

Close the holes in case of a drilling thru the outer skin

during paint thickness measurement

0

Identify the repair size by local sanding 0

Close-Up 1.00

TOTAL MANHOURS 38.00

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 m2 (1550 sq.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

Pulse

thermography

inspection

1.00 0.50 2

UT inspection 1.25 1.25 1

ELCH inspection 1.50 0.75 1

Tap test inspection 0.25 0.25 1

Local sanding 1.00 1.00 1

Close-up 1.00 0.75 2

H. WEIGHT AND BALANCE

Not Changed

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 39

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I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-41-55 12-34-24 20-16-00

29-10-00 55-33-13 55-40-00

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

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

51-10-25 51-10-26 55-40-09

55-40-50

Structural Repair Manual (SRM) 51-23-11 51-75-11 51-75-12

51-77-10 51-77-11

K. PUBLICATION AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 40

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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

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

management department:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

France

E-mail : monitored.retrofit@airbus.com

Tel : (33) 5 67 19 06 22

Fax : (33) 5 61 93 27 45

AIRBUS will provide specific industry support for inspection Service Bulletin completion. For

detailed information, please contact your AIRBUS Customer Support Director.

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

Adhesive Film Tape-- Aluminium

Foil

05RAB9 As required

Pressure Sensitive Tape 05RFB1 As required

Self-Adhes. Disks 05TNB1 As required

Non Aqueous Cleaner-General 08BAA9 As required

Methyl-Ethyl-Ketone 08BBF1 As required

Trichloroethane Legacy 08BBU9 As required

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 41

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ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Laminating Resin-Epoxy Srm Type

2

13EBC1 As required

Textile-Lint Free Cotton 14SBA1 As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

Not Applicable

(2) Tools

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

table:

Inspection tool PN

UT inspection UT-equipment Refer to NTM 51-10-24

Tap test inspection Tap test inspection tool Refer to NTM 51-10-03

Tap test inspection (with

Woodpecker)

Function test block

and

Woodpecker

Refer to NTM 51-10-19

ELCH inspection Elasticity Laminate Checker Kit Refer to NTM 51-10-26

Pulse thermography inspection Pulse thermography kit 99A55407324000

Paint thickness measurement Paint Borer Kit Model 518 or 518S or 518MC

with drill measuring range 10 to

1000 and 20 to 2000 microns

To order the pulse thermography kit and the paint borer kit, contact:

For tools on loan:

AIRBUS Material, Logistics and Suppliers

Lease Tool Service

Weg beim Jaeger 150

D-22335 HAMBURG

Germany

For ordering by internet: http.//spares.airbus.com

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 42

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For ordering by E-mail: tool.lease@airbus.com

For ordering by fax: +49 40 5076 3225

For tools to buy:

AIRBUS Material, Logistics and Suppliers

IFD- In Flight Desk

Weg beim Jaeger 150

D-22335 HAMBURG

Germany

For ordering by internet: http.//spares.airbus.com

For ordering by E-mail: ifd.spares@airbus.com

For ordering by fax: +49 40 5076 4012

(3) Special Tools

None

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 43

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This Page Intentionally Left Blank

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 44

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 551041-832-848-001 - Inspection

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER

CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words ’refer to’ are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words ’in accordance with’ are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: The purpose of flow charts is to supplement the information given in the Procedure

and Compliance paragraphs and not to serve as the primary source for tasks or

compliance times given in this Service Bulletin.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 45

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Task Associated Data

Manpower

TOTAL MANHOURS 38.00

A. GENERAL

(1) Subtask 551041-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

Task 20-16-00-912-001

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.) given in this Service

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

(c) For circuit breaker safety practices (Refer to AMM Task 20-16-00-912-001).

(d) The purpose of the flow charts are for information only to show the vario/Repair

phases described in this Service Bulletin.

(2) Subtask 551041-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

B. PREPARATION

(1) Subtask 551041-941-201-001 - 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

55-40-00, Page Block 601

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 46

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(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-869-002).

(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 55-40-00, Page Block 601).

(e) Depressurize the Green Hydraulic System (Refer to AMM Task 29-10-00-864-001).

(f) Depressurize the Yellow Hydraulic System (Refer to AMM Task 29-10-00-864-002).

(g) Depressurize the Blue Hydraulic System (Refer to AMM Task 29-10-00-864-003).

(h) Put a warning notice in the cockpit to tell persons not to pressurize the hydraulic

systems.

(i) Put access platform(s) in position at the rudder.

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

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 47

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C. PROCEDURE

(1) Subtask 551041-832-201-001 - Check the rudder repair records

Manpower Resources

Manhours 4.00

Minimum number of person 1

Subtask elapsed time 4.00

Skills NON DESTRUCTIVE

TESTING

References

Fig. A-GBAAA

Rudder SN identification

Sheet 01

Fig. A-GBCAA

Repair type identification

Sheet 01 - SRM list

Sheet 02 - RAS list

Fig. A-GBHAA

Report sheet and sketches

Sheet 01 - Pulse thermography report sheet

Sheet 02 - Repair records report sheet

Sheet 03

Sheet 04

Fig. A-GBJAA

GFRP area location

Sheet 01

Sheet 02

(a) Identify the Serial Number (SN) and the Part Number (PN) of the installed rudder.

1 Check the Aircraft Inspection Report and the maintenance records to verify the

rudder identification and a potential rudder swap since EIS.

2 In case of doubts, check the rudder identification plate on the aircraft, as

shown on Fig. A-GBAAA Sheet 01.

3 If you do not find a SN/PN placard on the rudder, contact AIRBUS for further

instructions.

(b) Check the completeness of the rudder records and report the result to AIRBUS.

Use the report sheet Fig. A-GBHAA Sheet 02.

NOTE: This action is not necessary, if the information has been already

sent to AIRBUS in accordance with the OIT 999.0060/10 and the

situation did not change since then.

(c) Check the rudder records if repairs are recorded since rudder EIS.

1 Repairs not affected by this Service Bulletin are those which:

- have been accomplished in accordance with SRM as listed in Fig. AGBCAA Sheet 01,

- are indicated in the AIRBUS Repair Approval Sheet (RAS) repair list Fig.

A-GBCAA Sheet 02 with "ISB inspection required: NO",

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 48

6

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- have been covered by AIRBUS Repair Design Approval Sheet (RDAS)

after February 2010,

- have been done in accordance with SRM revision February 2010 or later.

2 Report the result to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 02.

NOTE: This action is not necessary, if the information has been

already sent to AIRBUS in accordance with the OIT

999.0060/10 and the situation did not change since then.

3 If repairs are recorded and the repair records are complete, refer to:

- Subtask 551041-832-202-001 of this Service Bulletin for the rudder side

shell areas made of CFRP.

- Subtask 551041-832-207-001 of this Service Bulletin for the rudder side

shell areas made of GFRP.

NOTE: The outer skin ply of the upper area of the rudders is made

of GFRP. GFRP areas require different pulse thermography

inspection parameters and additionally Tap test inspection

or Woodpecker inspection have to be performed. For the

identification of the GFRP areas, refer to Fig. A-GBJAA Sheet

01 and Fig. A-GBJAA Sheet 02.

4 If no repairs have been duly recorded, report the result to AIRBUS. Use the

report sheet Fig. A-GBHAA Sheet 02.

No further action is necessary in accordance with this Service Bulletin.

5 In case of any doubts about the accomplishment of repairs, refer to:

- Subtask 551041-832-203-001 of this Service Bulletin for the rudder side

shell areas made of CFRP.

- Subtask 551041-832-207-001 of this Service Bulletin for the rudder side

shell areas made of GFRP.

6 If the repair records are not complete or not available, refer to:

- Subtask 551041-832-203-001 of this Service Bulletin for the rudder side

shell areas made of CFRP.

- Subtask 551041-832-207-001 of this Service Bulletin for the rudder side

shell areas made of GFRP.

NOTE: The outer skin ply of the upper area of the rudders is made

of GFRP. GFRP areas require different pulse thermography

inspection parameters and additionally Tap test inspection

or Woodpecker inspection have to be performed. For the

identification of the GFRP areas, refer to Fig. A-GBJAA Sheet

01 and Fig. A-GBJAA Sheet 02.

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 49

6

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SERVICE BULLETIN

(2) Subtask 551041-832-202-001 - Identify the type, location and size of in-service

repairs on the rudder side shell CFRP areas in case of complete repair records

since rudder Entry Into Service (EIS) are available

Manpower Resources

Manhours 0

Minimum number of person 2

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

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Non Destructive Test Manual (NTM) Task 55-40-50-290-801

Structural Repair Manual (SRM) 51-75-11

51-75-12

Fig. A-GBBAA

Repair type identification

Sheet 01

Sheet 02

Fig. A-GBDAA

Booster area definition

Sheet 01

Sheet 02

Fig. A-GBEAA

Typical pulse thermography and

ELCH/UT inspection

Sheet 01

Sheet 02 - Repair size assessment

Sheet 03 - Repair size assessment

Sheet 04 - Boundary and grid of ELCH/UT

inspections

Sheet 05 - ELCH inspection grid

Fig. A-GBHAA

Report sheet and sketches

Sheet 01 - Pulse thermography report sheet

Sheet 02 - Repair records report sheet

Sheet 03

Sheet 04

Fig. A-GFAAA

Flow Chart

Sheet 01 - Flow Chart 1

Sheet 02 - Flow Chart 2

Sheet 03 - Flow Chart 3

Sheet 04 - Flow Chart 4

Sheet 05 - Flow Chart 5

Sheet 06

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 50

6

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SERVICE BULLETIN

References

Fig. A-GABAA

Paint borer instructions

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

(a) If no repair has been done or the recorded repair is not to be inspected in

accordance with this Service Bulletin, report to AIRBUS. Use the report sheet Fig.

A-GBHAA Sheet 02.

NOTE: This action is not necessary, if the information has been already

sent to AIRBUS in accordance with the OIT 999.0060/10 and the

situation did not change since then.

No further action is necessary in accordance with this Service Bulletin.

(b) If a repair must be inspected in accordance with this Service Bulletin, do the

subsequent work steps in accordance with the Flow Chart Fig. A-GFAAA Sheet 01:

1 Identify the repair type, refer to Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA

Sheet 02.

2 Make sure that the paint thickness in the areas to be inspected by pulse

thermography does not exceed:

- 800 microns.

- 400 microns below the decal foil if a decal foil is installed.

NOTE: It is the responsibility of the operator to ensure that the paint

thickness in all areas to be inspected is below or equal to the

limits given above.

a If the paint coating and/or logo application is too thick, abrade the paint in

accordance with the SRM 51-75-11 to a thickness below or equal to the

limits given above.

NOTE: Chemical paint stripping is not allowed.

b In case of doubts about the paint thickness, measure the thickness using

a Paint Borer Kit, refer to the Figure Fig. A-GABAA Sheet 01 thru Fig. AGABAA Sheet 08.

<1>

CAUTION: DO NOT DRILL DEEPLY INTO THE BASE

MATERIAL (CFRP OR GFRP). DRILLING TOO

DEEP LEADS TO DAMAGE IN THE OUTER SKIN

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 51

6

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SERVICE BULLETIN

If you damage the outer skin with the paint borer, refer to the

Subtask 551041-833-201-001 for repair instructions.

3 Clean the areas to be inspected with:

Non Aqueous

Cleaner-General

08BAA9 As required

and

Textile-Lint Free

Cotton

14SBA1 As required

4 Do a pulse thermography inspection to get the precise location and the size of

the repair (Refer to NTM Task 55-40-50-290-801).

NOTE: The pulse thermography inspection indicates the outer skin

repair ply geometry. The largest repair ply defines the

boundary of the repair area.

NOTE: In case of any findings (repair, damage, fluid ingress) during

the pulse thermography inspection, save the images and send

it together with the report sheet to AIRBUS.

5 Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02 and

Fig. A-GBEAA Sheet 03.

6 If fluid ingress has been detected during the pulse thermography inspection,

refer to Subtask 551041-832-204-001 of this Service Bulletin.

7 Identify the booster areas in accordance with Fig. A-GBDAA Sheet 02.

8 If repairs in the booster areas up to 55000 mm2 (85.25 sq.in.) have been

detected, report the findings to AIRBUS. Use the report sheet Fig. A-GBHAA

Sheet 01 and the rudder related sketches, refer to Fig. A-GBHAA Sheet 03

and Fig. A-GBHAA Sheet 04.

No further actions on these repairs in accordance with this Service Bulletin.

9 If repairs in the booster areas larger than 55000 mm2 (85.25 sq.in.) have been

detected, do the UT inspection around the repair in accordance with Subtask

551041-832-205-001 of this Service Bulletin.

10 If repairs not in the booster area have been detected, do the ELCH and/or UT

inspection in accordance with Subtask 551041-832-205-001 of this Service

Bulletin.

11 After the inspection, restore the paint coating in accordance with the SRM

51-75-12.

NOTE: Refer to OIT 999.0130/06 ’paint system - best practises’.

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 52

6

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SERVICE BULLETIN

(3) Subtask 551041-832-203-001 - Do a pulse thermography inspection on the

complete rudder side shell CFRP areas to identify possible rudder in-service

repairs in case of repair records are not complete or not available

Manpower Resources

Manhours 32

Minimum number of person 2

Subtask elapsed time 16

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

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Non Destructive Test Manual (NTM) Task 55-40-50-290-801

Structural Repair Manual (SRM) 51-75-11

51-75-12

Fig. A-GFAAA

Flow Chart

Sheet 01 - Flow Chart 1

Sheet 02 - Flow Chart 2

Sheet 03 - Flow Chart 3

Sheet 04 - Flow Chart 4

Sheet 05 - Flow Chart 5

Sheet 06

Fig. A-GBDAA

Booster area definition

Sheet 01

Sheet 02

Fig. A-GBHAA

Report sheet and sketches

Sheet 01 - Pulse thermography report sheet

Sheet 02 - Repair records report sheet

Sheet 03

Sheet 04

Fig. A-GABAA

Paint borer instructions

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 53

6

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SERVICE BULLETIN

(a) Do the subsequent work steps in accordance with the Flow Chart Fig. A-GFAAA

Sheet 01:

1 Report undocumented rudder S/N list to AIRBUS.

a To get related manufacturing rework data, provide AIRBUS with the

rudder P/N, S/N and aircraft MSN in accordance with the accomplishment

timescale instructions, refer to Para 1.E table 2A of this Service Bulletin.

The manufacturing rework data will be provided through drawings

covered by Mod. 154173K16196.

2 Make sure that the paint thickness in the areas to be inspected by pulse

thermography does not exceed:

- 800 microns.

- 400 microns below the decal foil if a decal foil is installed.

NOTE: It is the responsibility of the operator to ensure that the paint

thickness in all areas to be inspected is below or equal to the

limits given above.

a If the paint coating and/or logo application is too thick, abrade the paint in

accordance with the SRM 51-75-11 to a thickness below or equal to the

limits given above.

NOTE: Chemical paint stripping is not allowed.

b In case of doubts about the paint thickness, measure the thickness using

a Paint Borer Kit, refer to the Figure Fig. A-GABAA Sheet 01 thru Fig. AGABAA Sheet 08.

<1>

CAUTION: DO NOT DRILL DEEPLY INTO THE BASE

MATERIAL (CFRP OR GFRP). DRILLING TOO

DEEP LEADS TO DAMAGE IN THE OUTER SKIN

If you damage the outer skin with the paint borer, refer to the

Subtask 551041-833-201-001 for repair instructions.

3 Clean the areas to be inspected with:

Non Aqueous

Cleaner-General

08BAA9 As required

and

Textile-Lint Free

Cotton

14SBA1 As required

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 54

6

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SERVICE BULLETIN

4 Do a pulse thermography inspection on the complete side shell CFRP

areas(LH/RH) to identify repairs, (Refer to NTM Task 55-40-50-290-801).

NOTE: The pulse thermography inspection indicates the outer skin

repair ply geometry. The largest repair ply defines the

boundary of the repair area.

NOTE: In case of any findings (repair, damage, fluid ingress) during

the pulse thermography inspection, save the images and send

it together with the report sheet to AIRBUS.

5 If no repair has been detected during the pulse thermography inspection,

report the result to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 01.

No further action is necessary in accordance with this Service Bulletin.

6 If fluid ingress has been detected during the thermograhy inspection, refer to

Subtask 551041-832-204-001 of this Service Bulletin.

7 Identify the booster areas in accordance with Fig. A-GBDAA Sheet 02.

8 If repairs in the booster areas up to 55000 mm2 (85.25 sq.in.) have been

detected which are not manufacturing rework, report the findings to AIRBUS.

Use the report sheet Fig. A-GBHAA Sheet 01 and the rudder related sketches,

refer to Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04.

No further actions on these repairs in accordance with this Service Bulletin.

9 If repairs in the booster areas larger than 55000 mm2 (85.25 sq.in.) have been

detected which are not manufacturing rework, do the UT inspection around the

repairs in accordance with the Subtask 551041-832-205-001 of this Service

Bulletin.

10 If repairs have been detected during the pulse thermography inspection which

are not manufacturing rework and not in the booster areas, do the ELCH

and/or UT inspection around the repairs in accordance with the Subtask

551041-832-205-001 of this Service Bulletin.

11 After the inspection, restore the paint coating in accordance with the SRM

51-75-12.

NOTE: Refer to OIT 999.0130/06 ’paint system - best practises’.

(4) Subtask 551041-832-204-001 - Do the corrective actions in case of fluid ingress

detected

Manpower Resources

Manhours 0

Minimum number of person 1

Subtask elapsed time 0

Skills NON DESTRUCTIVE

TESTING

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 55

6

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SERVICE BULLETIN

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Adhesive Film Tape--

Aluminium Foil

05RAB9 As required

Pressure Sensitive Tape 05RFB1

Self-Adhes. Disks 05TNB1 As required

Methyl-Ethyl-Ketone 08BBF1 As required

Trichloroethane Legacy 08BBU9 As required

Laminating Resin-Epoxy

Srm Type 2

13EBC1 As required

References

Non Destructive Test Manual (NTM) 51-10-25

Task 55-40-50-290-801

Fig. A-GFAAA

Flow Chart

Sheet 01 - Flow Chart 1

Sheet 02 - Flow Chart 2

Sheet 03 - Flow Chart 3

Sheet 04 - Flow Chart 4

Sheet 05 - Flow Chart 5

Sheet 06

Fig. A-GBHAA

Report sheet and sketches

Sheet 01 - Pulse thermography report sheet

Sheet 02 - Repair records report sheet

Sheet 03

Sheet 04

Fig. A-GBFAA

Core ventilation procedure

Sheet 01

Sheet 02

Sheet 03

Fig. A-GAAAA

Closing of ventilation holes

Sheet 01

Sheet 02

(a) If fluid ingress has been detected, continue with the subsequent work steps in

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

1 Around the identified fluid ingress, do the ELCH and/or UT inspection in

accordance with the Subtask 551041-832-205-001 of this Service Bulletin.

2 If a damage has been detected during the ELCH and/or UT inspection, contact

AIRBUS and follow their instructions. Use the report sheet Fig. A-GBHAA

Sheet 01.

3 If local single spots up to 1500 mm2 (2.33 sq.in.) with fluid ingress have been

detected, report the findings to AIRBUS. Use the report sheet Fig. A-GBHAA

Sheet 01 and the rudder related sketches, refer to Fig. A-GBHAA Sheet 03

and Fig. A-GBHAA Sheet 04.

No further actions on these local single spots of fluid ingress in accordance

with this Service Bulletin.

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 56

6

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SERVICE BULLETIN

4 If a maximum of 5 local single spots per side shell larger than 1500 mm2 (2.33

sq.in.) and up to 5000 mm2 (7.75 sq.in.) have been detected, do the ventilation

of the rudder core:

a

CAUTION: TO DRILL THE HOLES APPLY MODERATE

PRESSURE TO PREVENT DAMAGE TO THE SKIN, AT

THE END OF THE DRILLING OPERATION. DO NOT

DRILL THE OPPOSITE SHELL.

Drill the holes to a DIA of 3.0 mm (0.12 in.) through the outer and inner

skin in accordance with the dimensions shown on Fig. A-GBFAA Sheet

02 and Fig. A-GBFAA Sheet 03.

NOTE: Spots of fluid ingress behind the trailing edge screw line

must not be vented.

b Temporary restoration of the drain holes option 1:

<1> Close the drain holes with:

Adhesive Film

Tape-- Aluminium

Foil

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

<2> Do repetitive detailed inspections of the restored area for loose or

lost adhesive disks or tape until the repair of the affected area has

been done.

<3> In case of loose or lost tape or disks, close the holes again with:

or

Adhesive Film

Tape-- Aluminium

Foil

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 57

6

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SERVICE BULLETIN

c Temporary restoration of the drain holes option 2:

<1> Close the drain holes in accordance with the instructions given in

the Figure Fig. A-GAAAA Sheet 01 and Fig. A-GAAAA Sheet 02.

<a> Consumable Material necessary to close the drain holes:

Pressure Sensitive

Tape

05RFB1 As required

Laminating ResinEpoxy Srm Type 2

13EBC1 As required

Methyl-Ethyl-Ketone 08BBF1 As required

Trichloroethane

Legacy

08BBU9 As required

5 Do repetitive thermography inspections until the repair of the affected area

has been done (Refer to NTM 51-10-25 (preferred)) or (Refer to NTM Task

55-40-50-290-801).

NOTE: In case of any findings during the pulse thermography

inspection, save the images and send it together with the

report sheet to AIRBUS.

6 Do the repair in accordance with the SRM.

Due to the pending availability of the SRM improved repair, contact AIRBUS

for detailed repair instructions.

7 Report the repair to AIRBUS. Use the report sheet Fig. A-GBHAA Sheet 02.

8 If more than 5 local single spots per side shell larger than 1500 mm2 (2.33

sq.in.) and up to 5000 mm2 (7.75 sq.in.) have been detected, report to

AIRBUS and follow their instructions. Use the report sheet Fig. A-GBHAA

Sheet 01.

9 If local single spots larger than 5000 mm2 (7.75 sq.in.) with fluid ingress have

been detected, report the findings to AIRBUS and follow their instructions. Use

the report sheet Fig. A-GBHAA Sheet 01.

(5) Subtask 551041-832-205-001 - Do the ELCH and/or UT inspection around identified

repairs

Manpower Resources

Manhours 0

Minimum number of person 1

Subtask elapsed time 0

Skills NON DESTRUCTIVE

TESTING

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 58

6

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

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

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

51-10-26

55-40-09

Fig. A-GBEAA

Typical pulse thermography and

ELCH/UT inspection

Sheet 01

Sheet 02 - Repair size assessment

Sheet 03 - Repair size assessment

Sheet 04 - Boundary and grid of ELCH/UT

inspections

Sheet 05 - ELCH inspection grid

Fig. A-GBGAA

Rudder skin thickness identification

Sheet 01

Sheet 02

Sheet 03

Fig. A-GBHAA

Report sheet and sketches

Sheet 01 - Pulse thermography report sheet

Sheet 02 - Repair records report sheet

Sheet 03

Sheet 04

(a) If necessary, clean the areas to be inspected with:

Non Aqueous

Cleaner-General

08BAA9 As required

and

Textile-Lint Free

Cotton

14SBA1 As required

(b) Identify the skin thickness of the areas to be inspected, refer to Fig. A-GBGAA

Sheet 02 and Fig. A-GBGAA Sheet 03.

(c) If the skin thickness of the affected areas does not exceed 1.5 mm (0.06 in.), do an

ELCH inspection around the marked repair areas (Refer to NTM 51-10-26).

1 For the ELCH inspection, use a grid of 75 mm x 75 mm from the boundary of

the largest repair ply up to 200 mm around the largest repair ply, refer to Fig.

A-GBEAA Sheet 04.

a For the adjustment of the ELCH, refer to NTM 51-10-26.

b For the assessment criteria (yellow and red values) for the ELCH

inspection, refer to NTM 55-40-09, Para 2.C.

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 59

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SERVICE BULLETIN

(d) If the skin of the affected areas is thicker than 1.5 mm (0.06 in.), do an UT

inspection around the marked repair areas (Refer to NTM 51-10-24).

1 Do the UT inspection in an area between the boundary of the largest repair

ply up to 75 mm around the largest repair ply, refer to Fig. A-GBEAA Sheet

04.

(e) If a damage has been detected during the ELCH/UT inspection, provide detailed

information of the identified repair, report to AIRBUS and follow their instructions.

Use the report sheet Fig. A-GBHAA Sheet 02 and the rudder related sketches,

refer to Fig. A-GBHAA Sheet 03 and Fig. A-GBHAA Sheet 04.

(f) If no damage has been detected during the ELCH/UT inspection, continue with the

steps given in the Subtask 551041-832-206-001 of this Service Bulletin.

(6) Subtask 551041-832-206-001 - Do terminating actions in case of no damage

detected

Manpower Resources

Manhours 0

Minimum number of person 1

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

Adhesive Film Tape--

Aluminium Foil

05RAB9 As required

Pressure Sensitive Tape 05RFB1 As required

Self-Adhes. Disks 05TNB1 As required

Methyl-Ethyl-Ketone 08BBF1 As required

Trichloroethane Legacy 08BBU9 As required

Laminating Resin-Epoxy

Srm Type 2

13EBC1 As required

References

Fig. A-GBFAA

Core ventilation procedure

Sheet 01

Sheet 02

Sheet 03

Fig. A-GBHAA

Report sheet and sketches

Sheet 01 - Pulse thermography report sheet

Sheet 02 - Repair records report sheet

Sheet 03

Sheet 04

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 60

6

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SERVICE BULLETIN

References

Fig. A-GFAAA

Flow Chart

Sheet 01 - Flow Chart 1

Sheet 02 - Flow Chart 2

Sheet 03 - Flow Chart 3

Sheet 04 - Flow Chart 4

Sheet 05 - Flow Chart 5

Sheet 06

Fig. A-GAAAA

Closing of ventilation holes

Sheet 01

Sheet 02

(a) If no damage has been detected, continue with the subsequent work steps in

accordance with the Flow Chart Fig. A-GFAAA Sheet 02:

1 If a repair up to 10000 mm2 (15.50 sq.in.) has been detected, provide detailed

information about the repair and report to AIRBUS. Use the report sheet Fig.

A-GBHAA Sheet 02 and the rudder related sketches, refer to Fig. A-GBHAA

Sheet 03 and Fig. A-GBHAA Sheet 04.

2 If a repair larger than 10000 mm2 (15.50 sq.in.) and up to 20000 mm2 (31.00

sq.in.) has been detected, do the ventilation of the core:

NOTE: Instead of the core ventilation procedure, you can do repetitive

ELCH and/or UT inspections around the repair areas until the

repair has been done, refer to Subtask 551041-832-205-001.

a

CAUTION: TO DRILL THE HOLES APPLY MODERATE

PRESSURE TO PREVENT DAMAGE TO THE SKIN, AT

THE END OF THE DRILLING OPERATION. DO NOT

DRILL THE OPPOSITE SHELL.

Drill the holes to a DIA of 3.0 mm (0.12 in.) through the outer and inner

skin in accordance with the dimensions shown on Fig. A-GBFAA Sheet

02 and Fig. A-GBFAA Sheet 03.

NOTE: Repairs behind the trailing edge screw line must not be

vented.

b Temporary restoration of the drain holes option 1:

<1> Close the drain holes with:

Adhesive Film

Tape-- Aluminium

Foil

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

<2> Do repetitive detailed inspections of the restored area for loose or

lost adhesive disks or tape until the repair of the affected area has

been done.

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 61

6

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SERVICE BULLETIN

<3> In case of loose or lost tape or disks, close the holes again with:

Adhesive Film

Tape-- Aluminium

Foil

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

c Temporary restoration of the drain holes option 2:

<1> Close the drain holes in accordance with the instructions given in

the Figure Fig. A-GAAAA Sheet 01 and Fig. A-GAAAA Sheet 02.

<a> Consumable Material necessary to close the drain holes:

Pressure Sensitive

Tape

05RFB1 As required

Laminating ResinEpoxy Srm Type 2

13EBC1 As required

Methyl-Ethyl-Ketone 08BBF1 As required

Trichloroethane

Legacy

08BBU9 As required

d Report the results and the planned terminating action to AIRBUS. Use

the report sheet Fig. A-GBHAA Sheet 02.

e Do the terminating action in accordance with the SRM.

Due to the pending availability of the SRM improved repair, contact

AIRBUS for detailed repair instructions.

NOTE: The new repair cutout is the size equal to the largest

outer skin repair ply.

3 If a repair larger than 20000 mm2 (31.00 sq.in.) and up to 80000 mm2 (124

sq.in.) has been detected, do the ventilation of the core:

a

CAUTION: TO DRILL THE HOLES APPLY MODERATE

PRESSURE TO PREVENT DAMAGE TO THE SKIN, AT

THE END OF THE DRILLING OPERATION. DO NOT

DRILL THE OPPOSITE SHELL.

Drill the holes to a DIA of 3.0 mm (0.12 in.) through the outer and inner

skin in accordance with the dimensions shown on Fig. A-GBFAA Sheet

02 and Fig. A-GBFAA Sheet 03.

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 62

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b Temporary restoration of the drain holes option 1:

<1> Close the drain holes with:

Adhesive Film

Tape-- Aluminium

Foil

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

<2> Do repetitive detailed inspections of the restored area for loose or

lost adhesive disks or tape until the repair of the affected area has

been done.

<3> In case of loose or lost tape or disks, close the holes again with:

Adhesive Film

Tape-- Aluminium

Foil

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

c Temporary restoration of the drain holes option 2:

<1> Close the drain holes in accordance with the instructions given in

the Figure Fig. A-GAAAA Sheet 01 and Fig. A-GAAAA Sheet 02.

<a> Consumable Material necessary to close the drain holes:

Pressure Sensitive

Tape

05RFB1 As required

Laminating ResinEpoxy Srm Type 2

13EBC1 As required

Methyl-Ethyl-Ketone 08BBF1 As required

Trichloroethane

Legacy

08BBU9 As required

d Report the results and the planned terminating action to AIRBUS. Use

the report sheet Fig. A-GBHAA Sheet 02.

e Do the terminating action in accordance with the SRM.

NOTE: The new repair cutout is equal to the largest outer skin

repair ply.

NOTE: If the repair is larger than 30000 mm2 (46.50 sq.in.),

contact AIRBUS for additional instructions.

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 63

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4 If a repair larger than 80000 mm2 (124 sq.in.) has been detected, do the

ventilation of the core:

a

CAUTION: TO DRILL THE HOLES APPLY MODERATE

PRESSURE TO PREVENT DAMAGE TO THE SKIN, AT

THE END OF THE DRILLING OPERATION. DO NOT

DRILL THE OPPOSITE SHELL.

Drill the holes to a DIA of 3.0 mm (0.12 in.) through the outer and inner

skin in accordance with the dimensions shown on Fig. A-GBFAA Sheet

02 and Fig. A-GBFAA Sheet 03.

b Temporary restoration of the drain holes option 1:

<1> Close the drain holes with:

Adhesive Film

Tape-- Aluminium

Foil

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

<2> Do repetitive detailed inspections of the restored area for loose or

lost adhesive disks or tape until the repair of the affected area has

been done.

<3> In case of loose or lost tape or disks, close the holes again with:

Adhesive Film

Tape-- Aluminium

Foil

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

c Temporary restoration of the drain holes option 2:

<1> Close the drain holes in accordance with the instructions given in

the Figure Fig. A-GAAAA Sheet 01 and Fig. A-GAAAA Sheet 02.

<a> Consumable Material necessary to close the drain holes:

Pressure Sensitive

Tape

05RFB1 As required

Laminating ResinEpoxy Srm Type 2

13EBC1 As required

Methyl-Ethyl-Ketone 08BBF1 As required

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 64

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Trichloroethane

Legacy

08BBU9 As required

d Report the results and the planned terminating action to AIRBUS. Use

the report sheet Fig. A-GBHAA Sheet 02.

e Do the terminating action:

Replace the affected rudder shell

or

replace the rudder in accordance with the grace period given in the

accomplishment timescale table.

No further action is necessary in accordance with this Service Bulletin.

NOTE: The rudder shell replacement can be done only at the

AIRBUS Stade facility.

(7) Subtask 551041-832-207-001 - Inspect the rudder side shell upper GFRP areas

Manpower Resources

Manhours 0

Minimum number of person 1

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

Non Aqueous CleanerGeneral08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

References

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

Task 51-10-19-280-801

Task 55-40-50-290-801

Structural Repair Manual (SRM) 51-75-11

51-75-12

Fig. A-GBBAA

Repair type identification

Sheet 01

Sheet 02

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 65

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References

Fig. A-GFAAA

Flow Chart

Sheet 01 - Flow Chart 1

Sheet 02 - Flow Chart 2

Sheet 03 - Flow Chart 3

Sheet 04 - Flow Chart 4

Sheet 05 - Flow Chart 5

Sheet 06

Fig. A-GBEAA

Typical pulse thermography and

ELCH/UT inspection

Sheet 01

Sheet 02 - Repair size assessment

Sheet 03 - Repair size assessment

Sheet 04 - Boundary and grid of ELCH/UT

inspections

Sheet 05 - ELCH inspection grid

Fig. A-GABAA

Paint borer instructions

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

(a) If repairs in the rudder side shell upper GFRP area are recorded, do the

subsequent inspections in accordance with the Flow Chart Fig. A-GFAAA Sheet 04:

1 Make sure that the paint thickness in the areas to be inspected by pulse

thermography does not exceed:

- 400 microns.

- 400 microns below the decal foil if a decal foil is installed.

NOTE: It is the responsibility of the operator to ensure that the paint

thickness in all areas to be inspected is below or equal to the

limit of 400 microns.

a If the paint coating and/or logo application is too thick, abrade the paint in

accordance with the SRM 51-75-11 to a thickness below or equal to the

limit of 400 microns.

NOTE: Chemical paint stripping is not allowed.

b In case of doubts about the paint thickness, measure the thickness using

a Paint Borer Kit, refer to the Figure Fig. A-GABAA Sheet 01 thru Fig. AGABAA Sheet 08.

<1>

CAUTION: DO NOT DRILL DEEPLY INTO THE BASE

MATERIAL (CFRP OR GFRP). DRILLING TOO

DEEP LEADS TO DAMAGE IN THE OUTER SKIN

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 66

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If you damage the outer skin with the paint borer, refer to the

Subtask 551041-833-201-001 for repair instructions.

2 Clean the areas to be inspected with:

Non Aqueous

Cleaner-General

08BAA9 As required

and

Textile-Lint Free

Cotton

14SBA1 As required

3 Do a pulse thermography inspection to get the precise location and size of the

repair (Refer to NTM Task 55-40-50-290-801).

NOTE: The pulse thermography inspection indicates the outer skin

repair ply geometry. The largest repair ply defines the

boundary of the repair area.

NOTE: Make sure that you use the pulse thermography inspection

parameters for GFRP (Refer to NTM Task 55-40-50-290-801).

4 Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02 and

Fig. A-GBEAA Sheet 03.

5 If a repair type A-A (refer to Fig. A-GBBAA Sheet 02) has been identified, do a

Tap test inspection on the repair (Refer to NTM Task 51-10-03-280-801 or

NTM Task 51-10-19-280-801) to identify a skin to core disbonding.

6 For all other repair types, do the ELCH and/or UT inspection around the

repair, refer to the Subtask 551041-832-205-001 of this Service Bulletin.

7 If fluid ingress has been detected, refer to Subtask 551041-832-204-001 of

this Service Bulletin.

8 For further actions continue with the instructions given in the Subtask

551041-832-206-001 and the actions in the Flow Chart Fig. A-GFAAA Sheet

02 of this Service Bulletin.

9 After the inspection, restore the paint coating in accordance with the SRM

51-75-12.

NOTE: Refer to OIT 999.0130/06 ’paint system - best practises’.

(b) If there is no information about repairs in the rudder side shell upper GFRP area,

do the subsequent inspections in accordance with the Flow Chart Fig. A-GFAAA

Sheet 04:

1 Make sure that the paint thickness in the areas to be inspected by pulse

thermography does not exceed:

- 400 microns.

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 67

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- 400 microns below the decal foil if a decal foil is installed.

NOTE: It is the responsibility of the operator to ensure that the paint

thickness in all areas to be inspected is below or equal to the

limit of 400 microns.

a If the paint coating and/or logo application is too thick, abrade the paint in

accordance with the SRM 51-75-11 to a thickness below or equal to the

limit of 400 microns.

NOTE: Chemical paint stripping is not allowed.

b In case of doubts about the paint thickness, measure the thickness using

a Paint Borer Kit, refer to the Figure Fig. A-GABAA Sheet 01 thru Fig. AGABAA Sheet 08.

<1>

CAUTION: DO NOT DRILL DEEPLY INTO THE BASE

MATERIAL (CFRP OR GFRP). DRILLING TOO

DEEP LEADS TO DAMAGE IN THE OUTER SKIN

If you damage the outer skin with the paint borer, refer to the

Subtask 551041-833-201-001 for repair instructions.

2 Clean the areas to be inspected with:

Non Aqueous

Cleaner-General

08BAA9 As required

and

Textile-Lint Free

Cotton

14SBA1 As required

3 Do a pulse thermography inspection on the complete GFRP area to identify

repairs (Refer to NTM Task 55-40-50-290-801).

NOTE: The pulse thermography inspection indicates the outer skin

repair ply geometry. The largest repair ply defines the

boundary of the repair area.

NOTE: Make sure that you use the pulse thermography inspection

parameters for GFRP (Refer to NTM Task 55-40-50-290-801).

4 If repairs which are not manufacturing rework have been identified, mark the

boundary of the repair area, refer to Fig. A-GBEAA Sheet 02 and Fig. AGBEAA Sheet 03.

5 Do a Tap test inspection (Refer to NTM Task 51-10-03-280-801 or NTM Task

51-10-19-280-801) on the complete GFRP area to identify a skin to core

disbonding.

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 68

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6 Do the ELCH and/or UT inspection around the repair, refer to the Subtask

551041-832-205-001 of this Service Bulletin.

7 If fluid ingress has been detected, refer to Subtask 551041-832-204-001 of

this Service Bulletin.

8 For further actions continue with the instructions given in the Subtask

551041-832-206-001 and the actions in the Flow Chart Fig. A-GFAAA Sheet

02 of this Service Bulletin.

9 After the inspection, restore the paint coating in accordance with the SRM

51-75-12.

NOTE: Refer to OIT 999.0130/06 ’paint system - best practises’.

(8) Subtask 551041-833-201-001 - Close the holes in case of a drilling thru the outer

skin during paint thickness measurement

Manpower Resources

Manhours 0

Minimum number of person 1

Subtask elapsed time 0

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Adhesive Film Tape--

Aluminium Foil

05RAB9 As required

Self-Adhes. Disks 05TNB1 As required

Non Aqueous CleanerGeneral08BAA9 As required

Laminating Resin-Epoxy

Srm Type 2

13EBC1 As required

Textile-Lint Free Cotton 14SBA1 As required

References

Structural Repair Manual (SRM) 51-75-12

51-77-10 Para 5

51-77-11 Para 4.M.(2)

51-77-11 Para 4.A.(3)

51-77-11 Para 4.E

51-77-11 Para 5.D

51-77-11 Figure 14

(a) Hole closing procedure option 1:

1

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 69

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WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN

YOU USE CLEANING AGENTS, ADHESIVES, SEALANTS

AND PAINTS: THESE MATERIALS ARE DANGEROUS.

WARNING: WEAR THE CORRECT PROTECTIVE GLOVES, GOGGLES

AND FILTER MASKS WHEN YOU USE CLEANING AGENTS,

ADHESIVES, SEALANTS AND PAINTS: THESE MATERIALS

ARE DANGEROUS.

Prepare and dry the restoration area in accordance with the SRM 51-77-11

Para 4.M.(2).

2 Prepare in accordance with the SRM 51-77-11 Para 4.A.(3):

Laminating ResinEpoxy Srm Type 213EBC1 As required

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.

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

4 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 hole.

5 Close the filled holes with

Adhesive Film

Tape-- Aluminium

Foil

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

6 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 in accordance with the SRM 51-77-11 Para

5.D, and control the temperature by means of thermocouples in accordance

with the SRM 51-77-11 Figure 14.

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 70

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7 Do the final surface restoration in accordance with the compliance time given

in Para 1.E.(2), table 5:

a Remove the self adhesive tape from the restoration areas.

b Inspect the restoration in accordance with the SRM 51-77-10 Para 5.

c Remove any surplus resin from the border area of the restoration. Use

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

d Clean the restoration areas in accordance with the SRM 51-77-11 Para

4.E. Use:

Non Aqueous

Cleaner-General

08BAA9 As required

and

Textile-Lint Free

Cotton

14SBA1 As required

e Restore the surface protection in accordance with the SRM 51-75-12.

(b) Hole closing procedure option 2:

1

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 in accordance with the SRM 51-77-11

Para 4.M.(2).

2 Prepare in accordance with the SRM 51-77-11 Para 4.A.(3):

Laminating ResinEpoxy Srm Type 213EBC1 As required

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.

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

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 71

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4 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 hole.

5 Close the filled holes with

Adhesive Film

Tape-- Aluminium

Foil

05RAB9 As required

or

Self-Adhes. Disks 05TNB1 As required

6 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:

a Remove the self adhesive tape from the restoration areas.

b Inspect the restoration in accordance with the SRM 51-77-10 Para 5.

c Remove any surplus resin from the border area of the restoration. Use

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

d Clean the restoration areas in accordance with the SRM 51-77-11 Para

4.E. Use:

Non Aqueous

Cleaner-General

08BAA9 As required

and

Textile-Lint Free

Cotton

14SBA1 As required

e Restore the surface protection in accordance with the SRM 51-75-12.

(9) Subtask 551041-832-208-001 - Identify the repair size by local sanding

Manpower Resources

Manhours 0

Minimum number of person 1

Subtask elapsed time 0

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 55-40-50

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 72

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References

Structural Repair Manual (SRM) 51-23-11

51-75-11 Para 3.D

51-75-12

51-77-10

51-77-11 Para 4.D

51-77-11 Para 4.E

51-77-11 Para 4.G

Fig. A-GFAAA

Flow Chart

Sheet 01 - Flow Chart 1

Sheet 02 - Flow Chart 2

Sheet 03 - Flow Chart 3

Sheet 04 - Flow Chart 4

Sheet 05 - Flow Chart 5

Sheet 06

Fig. A-GBDAA

Booster area definition

Sheet 01

Sheet 02

Fig. A-GBHAA

Report sheet and sketches

Sheet 01 - Pulse thermography report sheet

Sheet 02 - Repair records report sheet

Sheet 03

Sheet 04

Fig. A-GBEAA

Typical pulse thermography and

ELCH/UT inspection

Sheet 01

Sheet 02 - Repair size assessment

Sheet 03 - Repair size assessment

Sheet 04 - Boundary and grid of ELCH/UT

inspections

Sheet 05 - ELCH inspection grid

CAUTION: IT IS THE OPERATOR’S RESPONSIBILITY TO ENSURE THAT

STRUCTURAL SIDE SHELL OUTER SKIN PLY (CFRP OR GFRP) IN

ACCORDANCE WITH THE DESIGN DRAWING IS NOT DAMAGED

DURING THE LOCAL SANDING PROCESS.

REMARK: IN MOST OF THE RUDDER SURFACE THE OUTER

SKIN CONSISTS ONLY OF ONE CFRP OR GFRP PLY. IN

CASE OF SANDING DAMAGE IMMEDIATE REPAIR BEFORE NEXT

FLIGHT IS REQUIRED. AN AREA DAMAGED BY THE LOCAL

SANDING COMBINED WITH AN EXISTING REPAIR CAN LEAD

TO A NON-REPAIRABLE SIZE AND SUBSEQUENT SIDE SHELL

REPLACEMENT.

NOTE: The local sanding procedure is only valid for fully documented repairs.

(a) Do the subsequent work steps in accordance with the Flow Chart Fig. A-GFAAA

Sheet 01, beginning with the box ’LOCAL PAINT THICKNESS IDENTIFICATION’.

1 Identify the paint thickness and the initial basic primer on top of the repair and

beside the repair location.

NOTE: It is recommended to use a Paint Borer Kit Model 518, 518S

or 518MC.

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 73

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2 Clean the previous repair area in accordance with the SRM 51-77-11 Para

4.E.

3 Do a local mechanical sanding on top and around the repair in accordance

with the SRM 51-75-11 Para 3.D on a step-by-step basis up to the initial basic

primer layer.

NOTE: The allowed maximum repair size is 1m2 (10.76sq.ft.) per local

repair.

4 If the largest repair ply is visible:

a Remove the dust and dry the area in accordance with the SRM 51-77-11

Para 4.G.

b Use a magnifying lens to inspect the sanded area for damage.

<1> In case of findings, do the damage assessment in accordance with

the SRM 51-77-10.

c Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02

and Fig. A-GBEAA Sheet 03.

d Identify the booster areas in accordance with Fig. A-GBDAA Sheet 02.

e If repairs in the booster areas up to 55000 mm2 (85.25 sq.in.) have

been detected, report the findings to AIRBUS. Use the report sheet Fig.

A-GBHAA Sheet 02 and the rudder related sketches, refer to Fig. AGBHAA Sheet 03 and Fig. A-GBHAA Sheet 04.

<1> Restore the surface protection in accordance with the SRM

51-23-11.

No further actions on these repairs in accordance with this Service

Bulletin.

f If repairs in the booster areas larger than 55000 mm2 (85.25 sq.in.) have

been detected, do the UT inspection around the repair in accordance with

Subtask 551041-832-205-001 of this Service Bulletin.

g If repairs not in the booster area have been detected, do the ELCH

and/or UT inspection in accordance with Subtask 551041-832-205-001 of

this Service Bulletin.

h If fluid ingress has been detected during the pulse thermography

inspection, refer to Subtask 551041-832-204-001 of this Service Bulletin.

i After the inspection, restore the paint coating in accordance with SRM

51-75-12 and SRM 51-23-11.

NOTE: Refer to OIT 999.0130/06 ’paint system - best practises’.

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 74

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5 If the largest repair ply is not visible, continue the local mechanical sanding on

top and around the repair in accordance with the SRM 51-77-11 Para 4.D

on a step-by-step basis up to the pore filler or adhesive with a radius of

approximately 50.0mm (1.97in.) beyond the initial detected repair patch.

6 If the largest repair ply is visible now:

a Remove the dust and dry the area in accordance with the SRM 51-77-11

Para 4.G.

b Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02

and Fig. A-GBEAA Sheet 03.

c Use a magnifying lens to inspect the sanded area for damage.

d In case of findings, do the damage assessment in accordance with the

SRM 51-77-10.

e Identify the booster areas in accordance with Fig. A-GBDAA Sheet 02.

f If repairs in the booster areas up to 55000 mm2 (85.25 sq.in.) have

been detected, report the findings to AIRBUS. Use the report sheet Fig.

A-GBHAA Sheet 02 and the rudder related sketches, refer to Fig. AGBHAA Sheet 03 and Fig. A-GBHAA Sheet 04.

<1> Restore the surface protection in accordance with the SRM

51-23-11.

No further actions on these repairs in accordance with this Service

Bulletin.

g If repairs in the booster areas larger than 55000 mm2 (85.25 sq.in.) have

been detected, do the UT inspection around the repair in accordance with

Subtask 551041-832-205-001 of this Service Bulletin.

h If repairs not in the booster area have been detected, do the ELCH

and/or UT inspection in accordance with Subtask 551041-832-205-001 of

this Service Bulletin.

i If fluid ingress has been detected during the pulse thermography

inspection, refer to Subtask 551041-832-204-001 of this Service Bulletin.

j After the inspection, restore the paint coating in accordance with the

SRM 51-75-12 and SRM 51-23-11.

NOTE: Refer to OIT 999.0130/06 ’paint system - best practises’.

7 If the largest repair ply is still not visible:

a Remove the dust and dry the area in accordance with the SRM 51-77-11

Para 4.G.

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 75

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b Do a pulse thermography inspection to get the precise location and the

size of the repair (Refer to NTM 55-40-50).

NOTE: The pulse thermography inspection indicates the outer

skin repair ply geometry. The largest repair ply defines

the boundary of the repair area.

NOTE: In case of any findings (repair, damage, fluid ingress)

during the pulse thermography inspection, save the

images and send it together with the report sheet to

AIRBUS.

c Mark the boundary of the repair area, refer to Fig. A-GBEAA Sheet 02

and Fig. A-GBEAA Sheet 03.

d If fluid ingress has been detected during the pulse thermography

inspection, refer to Subtask 551041-832-204-001 of this Service Bulletin.

e Identify the booster areas in accordance with Fig. A-GBDAA Sheet 02.

f If repairs in the booster areas up to 55000 mm2 (85.25 sq.in.) have

been detected, report the findings to AIRBUS. Use the report sheet Fig.

A-GBHAA Sheet 02 and the rudder related sketches, refer to Fig. AGBHAA Sheet 03 and Fig. A-GBHAA Sheet 04.

<1> Restore the surface protection in accordance with the SRM

51-23-11.

No further actions on these repairs in accordance with this Service

Bulletin.

g If repairs in the booster areas larger than 55000 mm2 (85.25 sq.in.) have

been detected, do the UT inspection around the repair in accordance with

Subtask 551041-832-205-001 of this Service Bulletin.

h If repairs not in the booster area have been detected, do the ELCH

and/or UT inspection in accordance with Subtask 551041-832-205-001 of

this Service Bulletin.

i After the inspection, restore the paint coating in accordance with SRM

51-75-12 and SRM 51-23-11.

NOTE: Refer to OIT 999.0130/06 ’paint system - best practises’.

D. TEST

None

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 76

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SERVICE BULLETIN

E. CLOSE-UP

(1) Subtask 551041-942-201-001 - 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

55-40-00, Page Block 601

(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 inspection/check Close-up procedure

(Refer to AMM 55-40-00, Page Block 601).

(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: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 77

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**CONF ALL

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

POSITION OF

RUDDER S/N PLACARD

AT MSN:

0001 − 0528,

0530 − 0531,

0533 − 0536

MFR

DESCR.

SER. N °

CA CODE

MFG DATE

A/C

PN

NSA9117−63D

D5547100XXXXX

TS−XXXX

A

Z326

N_SB_551041_6_BAAA_01_00

A

Figure A-GBAAA - Sheet 01

Rudder SN identification

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 78

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SERVICE BULLETIN

**CONF ALL

A

Z326

A

N_SB_551041_6_BBAA_01_00

A

A

F

F

E

E

D

D

C

C

B

B

LH SHOWN

RH SIMILAR

Figure A-GBBAA - Sheet 01

Repair type identification

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 79

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SERVICE BULLETIN

**CONF ALL

A A

B B

C C

D D

E E

F F

OUTER SKIN WITH AND WITHOUT CORE CLOSING

OUTER SKIN AND CORE REPAIR

WITHOUT CORE CLOSING

OUTER SKIN AND CORE REPAIR

WITH CORE CLOSING

BOTH SKIN AND CORE REPAIR

WITH AND WITHOUT CORE CLOSING /

REPAIR WITH ACCESS FROM ONE SIDE ONLY

DELAMINATION AND CORE DAMAGE WITH

CORE CLOSING (SRM 55−41−00 PAGE BLOCK 201 FIG.204/218) 

(SRM 55−41−00 PAGE BLOCK 201 FIG.206/217)

(SRM 55−41−00 PAGE BLOCK 201 FIG.207/

(SRM 55−41−00 PAGE BLOCK 201 FIG.207/210/220)

(SRM 55−41−00 PAGE BLOCK 201 FIG.207/210/220)

BOTH SKIN AND CORE REPAIR WITH AND WITHOUT 

CORE CLOSING / REPAIR WITH ACCESS FROM BOTH SIDE

(SRM 55−41−00 PAGE BLOCK 201 FIG. 201/202/

207/208/211/215/216/220)

209/210/220)

N_SB_551041_6_BBAA_02_02

Figure A-GBBAA - Sheet 02

Repair type identification

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 80

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SERVICE BULLETIN

**CONF ALL

REPAIR PROCEDURE

203

9.E.

55−41−00

REPAIR OF DELAMINATION AT RUDDER SPAR

55−41−00 9.N.

55−41−00 9.C.

55−41−00 205

55−41−00 9.M. 213

214

9.S. 219

REPAIR OF ABRASIONS AND SCRATCHES IN ZONE ’F’

REPAIR OF IMPACT DELAMINATION AT RUDDER SPAR STIFFENER

55−41−00 REPAIR OF ABRASIONS AND SCRATCHES IN ZONE ’L’

PARA. FIG.

9.L. 212

CHAPTER

SA SRM ISSUE: 01. NOV 2009

NOTE:

INSPECTION OF IDENTIFIED REPAIRS, IN ACCORDANCE WITH THE ISB, IS REQUIRED, IF

THE SRM REFERENCE OF THE REPAIR IS NOT LISTED IN THE TABLE ABOVE.

REPAIR OF IMPACT DELAMINATION, CRACKS, HOLES AND 

ABRASIONS IN ZONE ’B’

REPAIR OF IMPACT DELAMINATION, CRACKS, HOLES AND 

ABRASIONS IN ZONE ’J’

55−41−13 TEMPORARY REPAIR OF LARGE DAMAGED AREA IN 5.A. 201

ZONES ’F’, ’H’ AND ’L’

55−41−13 REPAIR FOR DEBONDING WITHOUT CRACKS AND HOLES 5.B. 202

IN ZONES ’F’ AND ’L’

N_SB_551041_6_BCAA_01_01

Figure A-GBCAA - Sheet 01

Repair type identification - SRM list

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 81

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**CONF ALL

FAM A/C TYP MSN AIRLINE RUDDER S/N DAMAGE

REPORT DATE

RAS REFERENCE ISB INSPECTION

REQUIRED

SA A320 25 P2C TS − 1025 20. JAN. 2003 RAS/DAHAM/4016405/2003 YesSA A320 61 AFR TS − 1061 7. JUL. 2006 RAS/DAHAM/4021015/2006 YesSA A320 128 AFR TS − 1130 17. NOV.1992 RAS/DAHAM/0750/92 YesSA A320 196 ANA TS − 1198 16. APR. 1999 RAS/DAHAM/2218/98 YesSA A320 277 CDN NOT REPORTED (TS − 1280) 2. MAR. 1998 RAS/DAHAM/2010/98 YesSA A320 630 AJM NOT REPORTED (TS − 1632) 27 MAY 1998 RAS/DAHAM/2071/98 YesSA A319 660 AFR TS − 2026 1. FEB. 2007 RAS/DAHAM/4021794/2007 YesSA A320 1835 TAM TS − 3180 7. DEC. 2007 RAS/DAHAM/4023510/2007 YesSA A319 2691 EZY TS − 4071 30 JAN. 2008 RAS/DAHAM/4024241/2008 Yes

NOTE:

MSN AND AIRLINE INFORMATION

AT THE DATE OF THE RAS ISSUANCE.

N_SB_551041_6_BCAA_02_01

Figure A-GBCAA - Sheet 02

Repair type identification - RAS list

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 82

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SERVICE BULLETIN

**CONF ALL

A

Z326

A

B

B

N_SB_551041_6_BDAA_01_01

Figure A-GBDAA - Sheet 01

Booster area definition

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 83

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SERVICE BULLETIN

**CONF ALL

990.00 mm

(38.98 in)

1700.00mm

(66.93 in)

785.00mm

(30.91 in)

DEFINITION OF

BOOSTER AREA

VALID FOR RUDDER

LH SHOWN

D55471000

32

30

25

20

15

10

5

1

BR7

BR6

BR5

BR4

BR3

BR2

BR1

B RH SYMMETRICAL

D55471001

D55471002

D55471003

D55471004

N_SB_551041_6_BDAA_02_03

Figure A-GBDAA - Sheet 02

Booster area definition

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 84

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SERVICE BULLETIN

**CONF ALL

A

Z326

A

B E

B E

N_SB_551041_6_BEAA_01_00

Figure A-GBEAA - Sheet 01

Typical pulse thermography and ELCH/UT inspection

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 85

6

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SERVICE BULLETIN

**CONF ALL

TYPICAL 

PULSE THERMOGRAPHY

INSPECTION

LH SHOWN

RH SYMETRICAL

32

30

25

20

15

10

5

1

BR7

BR6

BR5

BR4

BR3

BR2

BR1

B

C

D

N_SB_551041_6_BEAA_02_01

Figure A-GBEAA - Sheet 02

Typical pulse thermography and ELCH/UT inspection - Repair size assessment

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 86

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SERVICE BULLETIN

**CONF ALL

REPAIR SIZE = D2 x /4

100.0mm x 100.0mm

(3.93 in x 3.93 in)

(15.50 sq.in)

DAMAGE IN THE 

OUTER SKIN AND CORE

MAX. REPAIR PLY

REPAIR PLY

D

 (110.0mm)2 x /4

= (4.33 in2 x /4)

 ca. 10 000 mm2 =

DAMAGE IN THE 

OUTER SKIN AND CORE

MAX. REPAIR PLY

REPAIR PLIES

REPAIR SIZE = A x B

=

50.0mm x 200.0mm

(1.97 in x 7.87 in) =

OR

(15.50 sq.in)

10 000 mm2 =

B

A

EXAMPLE:

EXAMPLE:

D = 110.0mm DIA

C

D

02 THE NEW CUTOUT SIZE FOR THE REPAIR IS THE

SIZE OF THE FORMER OUTER SKIN REPAIR PLY.

02

02

N_SB_551041_6_BEAA_03_01

Figure A-GBEAA - Sheet 03

Typical pulse thermography and ELCH/UT inspection - Repair size assessment

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 87

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**CONF ALL

TYPICAL 

ELCH/UT

INSPECTION

LH SHOWN

RH SYMETRICAL

INSPECTION AREA

ELCH/UT

SKIN THICKNESS 1.5mm (0.23 in):

A=200.0mm (7.87 in) 

AROUND THE MAX. REPAIR PLY 

ELCH METHOD

GRID = 75.0mm x75.0mm (2.95 in x 2.95 in)

SKIN THICKNESS 1.5mm (0.23 in):

A=75.0mm (2.95 in) 

AROUND THE MAX. REPAIR PLY 

UT−METHOD

32

30

25

20

15

10

5

1

BR7

BR6

BR5

BR4

BR3

BR2

BR1

MAX. REPAIR PLY

A

E

F

N_SB_551041_6_BEAA_04_01

Figure A-GBEAA - Sheet 04

Typical pulse thermography and ELCH/UT inspection - Boundary and grid of ELCH/UT inspections

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 88

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SERVICE BULLETIN

**CONF ALL

TYPICAL TRAILING EDGE

ELCH INSPECTION

NOTE:

DISTANCE FROM EDGE 

F

75.0 mm

(2.95 in)

75.0 mm

(2.95 in)

EXISTING SCREW

75.0 mm

(2.95 in)

75.0 mm

(2.95 in)

75.0 mm

(2.95 in)

01

01

INSPECTION POINT

ELCH TOOL

TYPICAL TRAILING EDGE

ELCH INSPECTION

AROUND REPAIR AREA

75.0 mm

(2.95 in) 75.0 mm

(2.95 in)

MAX. REPAIR PLY

02

02

02 SCREWS AND ELCH TOOL ARE NOT DRAWN TO SCALE N_SB_551041_6_BEAA_05_04

Figure A-GBEAA - Sheet 05

Typical pulse thermography and ELCH/UT inspection - ELCH inspection grid

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 89

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SERVICE BULLETIN

**CONF ALL

A

Z326

A

B

B

N_SB_551041_6_BFAA_01_00

Figure A-GBFAA - Sheet 01

Core ventilation procedure

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 90

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SERVICE BULLETIN

**CONF ALL

MAX. RECTANGULAR REPAIR SIZE 100.0mm (3.94 in):

DRILL HOLES THRU INNER AND OUTER SKIN.

CAUTION: DO NOT DRILL THE OPPOSITE SHELL.

NOTE:

03

01

MIN. 90.0 mm

(3.54 in)

100.0 mm

(3.94 in)

02 REPAIR SIZE DETECTED BY THERMOGRAPHY

MAX.

02

B

APPLICABLE TO MAX. 6 HOLES

IN A ROW

TYPICAL 

CORE VENTING

IF REPAIR SIZE IS LARGER THAN 105 000mm2 (162.75 sq.in.),

CONTACT AIRBUS FOR FURTHER INSTRUCTIONS

MAX. 100.0 mm

(3.94 in)

03

C

DRILL 1 ROW IN THE MID OF THE REPAIR.

IF THE RECTANGULAR REPAIR SIZE IS LARGER THAN

100.0mm (3.94 in), DRILL 2 ROWS 

AS SHOWN IN FIG. A−GBFAA, SHEET 03.

05 CONFIRM BY AN ADDITIONAL INSPECTION THAT THE DRILL

HOLE HAS PENETRATED THE INNER SKIN.

(E.G. BY INSERTING A SUITABLE PIN DEEPER THAN NOMINAL

PANEL THICKNESS, OR BY ILLUMINATION OF THE RUDDER

FROM INSIDE THROUGH A HOLE IN THE SPAR AND VISUAL

INSPECTION THROUGH THE DRILL HOLE.)

A A

01

3.0 mm DIA

(0.12 in)

01

OUTER SKIN

INNER SKIN

OPPOSITE SHELL

MAX. REPAIR PLY

02

C D

A 05

A

30.0 mm

(1.18 in)

TE−SCREW

REPAIR PLY

N_SB_551041_6_BFAA_02_03

Figure A-GBFAA - Sheet 02

Core ventilation procedure

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 91

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**CONF ALL

IF THE RECTANGULAR REPAIR SIZE IS LARGER THAN

100.0 mm

(3.94 in)

NOTE:

04

MIN. 90.0 mm

(3.54 in) MIN. 90.0 mm (3.54 in)

100.0 mm

(3.94 in)

02 REPAIR SIZE DETECTED BY THERMOGRAPHY

MAX. REPAIR PLY

02

04

D

APPLICABLE TO MAX. 6 HOLES

IN A SQUARE GRID

IF REPAIR SIZE IS LARGER THAN 105 000mm2 (162.75 sq.in.),

CONTACT AIRBUS FOR FURTHER INSTRUCTIONS

> 100.0 mm

(3.94 in)

100.0 mm (3.94 in), DRILL 2 ROWS.

N_SB_551041_6_BFAA_03_00

Figure A-GBFAA - Sheet 03

Core ventilation procedure

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 92

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SERVICE BULLETIN

**CONF ALL

A

Z326

A

C

B

N_SB_551041_6_BGAA_01_00

Figure A-GBGAA - Sheet 01

Rudder skin thickness identification

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 93

6

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SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in)

LH SHOWN

SKIN THICKNESS 

> 1.5mm (0.059 in)

SKIN THICKNESS 

NO INSPECTION

B

32

30

25

20

15

10

5

1

BR7

BR6

BR5

BR4

BR3

BR2

BR1

238.0mm

(9.37 in)

202.0mm

(7.95 in)

(2.00 in)

51.0mm

333.0mm

(13.11 in)

1698.0mm

(66.85 in)

326.0mm

(12.83 in)

230.0mm

(9.06 in)

N_SB_551041_6_BGAA_02_00

Figure A-GBGAA - Sheet 02

Rudder skin thickness identification

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 94

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SERVICE BULLETIN

**CONF ALL

< 1.5mm (0.059 in)

RH SHOWN

SKIN THICKNESS 

> 1.5mm (0.059 in)

SKIN THICKNESS 

NO INSPECTION

32

30

25

20

15

10

5

1

BR7

BR6

BR5

BR4

BR3

BR2

BR1

238.0mm

(9.37 in)

202.0mm

(7.95 in)

52.0mm

(2.05 in)

94.0mm

(3.70 in)

1698.0mm

(66.85 in)

(12.83 in)

326.0mm

10.0mm

C (0.39 in)

N_SB_551041_6_BGAA_03_00

Figure A-GBGAA - Sheet 03

Rudder skin thickness identification

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 95

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**CONF ALL

REPAIR DETECTED WITH NIL DAMAGE

NO REPAIR DETECTED

PLEASE SEND REPORTING SHEET TO:

AIRBUS

CUSTOMER SERVICE STRUCTRE ENGINEERING

DEPARTMENT SEES1

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

Structure.sbinspectionresult@airbus.com

REPAIR DETECTED WITH DAMAGE

PLEASE SEND REPORTING SHEET TO:

DEPARTMENT SEER1/2/3

NOTE: ATTACH ALSO THE INITIAL PUSLE THERMOGRAPHY PHOTOS.

PREVIOUS REPORTS PER SB55−1041REV00 FIGURE A−GBHAA − SHEET 01/02/03 ARE VALID

AIRCRAFT

MSN

RUDDER S/N

INSPECTION DATE

FLIGHT CYCLES FC

FLIGHT HOURS FH

DATA

PULSE THERMOGRAPHY

COMPLETE INSPECTION LH AND RH SIDE

YES/NO

INSPECTION RESULT

REPAIR DETECTED

LH

RH

LIQUID INGRESS DETECTION

DAMAGE CHECK UT − ELCH INDICATION

SUMMARY

RUDDER SIDE SHELLS SANDWICH REPAIR PULSE THERMOGRAPHY REPORT

N_SB_551041_6_BHAA_01_03

Figure A-GBHAA - Sheet 01

Report sheet and sketches - Pulse thermography report sheet

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 96

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**CONF ALL

PLEASE SEND REPORTING SHEET TO:

AIRBUS

CUSTOMER SERVICE STRUCTRE ENGINEERING

DEPARTMENT SEES1

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

Structure.sbinspectionresult@airbus.com

FIGURE A−GBHAA − SHEET 01 / REPORT SHEET AND SKETCHES − REPORT SHEET

PREVIOUS REPORTS PER SB55−1041REV00 FIGURE A−GBHAA − SHEET 01 ARE VALID

AIRCRAFT

MSN

RUDDER S/N

RECORDS REVIEW DATE

DATA

RECORDS STATUS

REPAIR RECORDS COMPLETE SINCE ORIGINAL

YES/NO

REPAIR SCHEME

RUDDER FLIGHT CYCLES / FLIGHT HOURS

REPAIR DATE

LH OR RH SIDE SHELL

SRM FIGURE 2XX (SRM 55−41−00 AND/OR 55−41−13 PB201)

DAMAGE SIZE (CIRCULAR) DIAMETER IN mm

SUMMARY

RUDDER SIDE SHELLS SANDWICH REPAIR RECORDS

SRM (STRUCTURAL REPAIR MANUAL) REPAIR PERFORMED

REPAIR APPROVED BY LOCAL AIRWORTHINESS

DAMAGE SIZE (RECTANGULAR SHAPE) LENGTH AND WIDTH IN mm

DAMAGE SIZE (mm2)

REPAIR OUTER PLY SIZE (mm2) IF KNOWN FROM RECORDS

LOCATION AS PER SRM 55−41−00 PB101 FIGURE 103 ZONE CODE.

SERVICE BULLETIN NO.: A320−55−1041 REVXX

IN CASE OF MORE THAN 1 REPAIR, DUPLICATE THIS REPORTING SHEET

(0 FLIGHT CYCLES) EIS ENTRY INTO SERVICE

AUTHORITIES (NO AIRBUS APPROVAL)

N_SB_551041_6_BHAA_02_04

Figure A-GBHAA - Sheet 02

Report sheet and sketches - Repair records report sheet

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 97

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**CONF ALL

Rudder Side Shell 

(Show damage location, size and type.)

Sandwich Repair Inspection

Damage 

location

Damage 

description / type

Damage 

size mm2 / sq.in.

NOTE:

01 FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER.

01

32

30

25

20

15

10

5

1

BR7

BR6

BR5

BR4

BR3

BR2

BR1

Valid for rudder:

D55471000

D55471001

D55471002

D55471003

D55471004

LH

N_SB_551041_6_BHAA_03_02

Figure A-GBHAA - Sheet 03

Report sheet and sketches

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 98

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**CONF ALL

Damage 

location

Damage 

description / type

Damage 

size mm2 / sq.in.

NOTE:

01 FOR THE DAMAGE LOCATION, MARK THE AREA AND IDENTIFY WITH A NUMBER.

01

Rudder Side Shell 

(Show damage location, size and type.)

Sandwich Repair Inspection

32

30

25

20

15

10

5

1

BR7

BR6

BR5

BR4

BR3

BR2

BR1

Valid for rudder:

D55471000

D55471001

D55471002

D55471003

D55471004

RH

N_SB_551041_6_BHAA_04_00

Figure A-GBHAA - Sheet 04

Report sheet and sketches

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 99

6

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SERVICE BULLETIN

**CONF ALL

A

Z326

A

B

B

N_SB_551041_6_BJAA_01_00

Figure A-GBJAA - Sheet 01

GFRP area location

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 100

6

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SERVICE BULLETIN

**CONF ALL

LH SHOWN B

32

30

25

20

15

10

5

1

BR7

BR6

BR5

BR4

BR3

BR2

BR1

575.0 mm

(22.64 in)

390.0 mm

(15.35 in)

GFRP AREA

CFRP AREA

RH SYMMETRICAL

N_SB_551041_6_BJAA_02_00

Figure A-GBJAA - Sheet 02

GFRP area location

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 101

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SERVICE BULLETIN

**CONF ALL

CHECK THE RUDDER RECORDS IF REPAIRS

(AIRBUS RAS , SRM AND OTHER ) 

NO YES

PERFORM PULSE THERMOGRAPHY

INSPECTION ON COMPLETE

FLUID REPAIR TYPE

INSPECTED IN ACCORDANCE WITH THE SB.

02 IDENTIFIED TO BE

REPORT THE INFORMATION TO AIRBUS.

01

PERFORMED

SINCE RUDDER EIS ?

REPAIR

DETECTED, WHICH

NO

YES

REPAIR 

YES NO

REPORT THE

INFORMATION TO AIRBUS.

PERFORM PULSE THERMOGRAPHY ON REPAIR 

LOCATION TO PRECISE LOCATION AND SIZE.

REPORT THE INFORMATION TO AIRBUS.

PERFORM ELCH AND/OR UT 

AROUND THE IDENTIFIED

NO FURTHER ACTION

REQUIRED IN ACCORDANCE

WITH THIS SB.

REFER TO FLOW CHART 2 FOR 

ACTIONS ON IDENTIFIED REPAIRS.

YES

NO

COMPLETE REPAIR

RECORDS AVAILABLE

SINCE RUDDER EIS ?

NO YES

NO FURTHER 

ACTIONS.

CONTINUE WITH

ACTIONS AS PER

FLOW CHART 3.

REPAIRS.

NO

YES

REPORT THE INFORMATION TO AIRBUS.

SIDE SHELLS TO IDENTIFY REPAIRS:

MARK THE REPAIRS.

MARK THE REPAIRS.

YES

REPAIRS IN THE BOOSTER

AREA

REPAIR SIZE 55000mm2

03 LARGER THAN

(85.25 sq.in.)

NO

 ARE RECORDED SINCE RUDDER EIS AND

04

05

06

OR NOT IN THE BOOSTER

AREA. 03

REPAIRS IN THE BOOSTER

AREA

REPAIR SIZE 55000mm2

03 LARGER THAN

(85.25 sq.in.) 06

OR NOT IN THE BOOSTER

AREA. 03

REPORT UNDOCUMENTED RUDDER 

S/N LIST TO AIRBUS SEES1 TO GET

RELATED RUDDER MANUFACTURING

REWORK DATA 07

IS NOT MANUFACTURING

REWORK ?

08

12

12

FOR PAINT THICKNESS IDENTIFICATION

REFER TO FLOW CHART 5

FOR PAINT THICKNESS IDENTIFICATION

REFER TO FLOW CHART 5

INGRESS

DETECTED

AND

PERFORM LOCAL SANDING ON TOP AND

REPAIR PLY

OF THE REPAIR

LARGEST 

VISIBLE?

YES

NO

AROUND THE PEPAIR UP TO PRIMER. 28

PERFORM LOCAL SANDING

ON TOP AROUND THE REPAIR

UP TO ADHESIVE. 24 25

REPAIR PLY

OF THE REPAIR

LARGEST 

VISIBLE?

YES

OR

NO

NOTE:

REFER TO FIGURE A−GFAAA, SHEET 06.

26

LOCAL PAINT THICKNESS IDENTIFICATION 27

MARK REPAIR SIZE ON SURFACE

22 23

25

N_SB_551041_6_FAAA_01_04

Figure A-GFAAA - Sheet 01

Flow Chart - Flow Chart 1

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 102

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SERVICE BULLETIN

**CONF ALL

ACTIONS ON IDENTIFIED

REPAIRS

DAMAGE

DETECTED YES NO

PROVIDE DETAILED 

DAMAGE REPORT AND

REPAIR SIZE 

10000mm2, (15.50 sq.in.) −

PROVIDE DETAILED

INFORMATION TO AIRBUS 

AVAILABLE.

PERFORM REPETITIVE 

ELCH AND/OR UT

INSPECTION AROUND THE

IDENTIFIED REPAIR.

PERFORM CORE VENTING

THROUGH INNER SKIN, IN

ACCORDANCE WITH VENTING

SCHEME.

PERFORM CORE VENTING

THROUGH INNER SKIN, IN

ACCORDANCE WITH VENTING

SCHEME.

OR

ON IDENTIFIED REPAIR

DETAILED INFORMATION ON IDENTIFIED REPAIR IF

REPORT TO AIRBUS

AND FOLLOW THEIR

INSTRUCTIONS.

FINDINGS

YES NO

REPORT THE RESULTS AND PLANNED

TERMINATING ACTION ON IDENTIFIED 

REPAIR IN ACCORDANCE WITH

SRM AT THE IDENTIFIED

REPAIR LOCATION.

REPAIR IN ACCORDANCE WITH

SRM AND WITH ADDITIONAL 

INSTRUCTIONS FROM AIRBUS.

REPLACE AFFECTED 

RUDDER SHELL 

OR REPLACE THE RUDDER.

09 REPAIR SIZE 09 REPAIR SIZE 09 REPAIR SIZE 09

10

10

11

TO AIRBUS SEER 1/2/3 OR

TERMINATING ACTION

10000mm2, (15.50 sq.in.). 20000mm2, (31.00 sq.in.). 20000mm2, (31.00 sq.in.) − 80000mm2, (124.00 sq.in.). 80000mm2, (124.00 sq.in.).

NO FURTHER ACTION

REQUIRED IN ACCORDANCE

WITH THIS SB.

AIRTAC AND FOLLOW

PERFORM CORE VENTING

THROUGH INNER SKIN, IN

ACCORDANCE WITH VENTING

SCHEME.

REPAIR TO AIRBUS SEOT 2, COPY SEES1

REPORT THE RESULTS AND PLANNED

TERMINATING ACTION ON IDENTIFIED 

REPORT THE RESULTS AND PLANNED

TERMINATING ACTION ON IDENTIFIED 

TERMINATING ACTION

REPAIR SIZE 30000mm2, (46.50 sq.in.).

REPAIR SIZE 30000mm2, (46.50 sq.in.).

NO FURTHER ACTION

REQUIRED IN ACCORDANCE

WITH THIS SB.

THEIR INSTRUCTIONS

REPAIR TO AIRBUS SEOT 2, COPY SEES1 REPAIR TO AIRBUS SEOT 2, COPY SEES1

19

19

NOTE:

REFER TO FIGURE A−GFAAA, SHEET 06.

N_SB_551041_6_FAAA_02_05

Figure A-GFAAA - Sheet 02

Flow Chart - Flow Chart 2

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 103

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SERVICE BULLETIN

**CONF ALL

ACTIONS ON DETECTED FLUID INGRESS.

LOCAL SINGLE SPOT FLUID INGRESS

1500 mm2, (2.33 sq.in.) AND 

5000 mm2, (7.75 sq.in.)

LOCAL SINGLE SPOT FLUID INGRESS

1500 mm2, (2.33 sq.in.)

LOCAL SPOT FLUID INGRESS

5000 mm2, (7.75 sq.in.)

DRAIN BY CORE VENTING.

REPORT TO AIRBUS SEER 1/2/3 OR AIRTAC

AND FOLLOW THEIR INSTRUCTIONS.

REPORT TO

AIRBUS.

NO FURTHER ACTION REQUIRED

IN ACCORDANCE WITH THIS ISB.

REPETITIVE THERMOGRAPHY

RE− INSPECTION.

DO THE REPAIR.

ACTIONS ON DETECTED FLUID INGRESS.

PERFORM ELCH AND/OR UT AROUND THE

IDENTIFIED FLUID INDICATION

DAMAGE

DETECTED YES

NO

THAN 5 SPOTS PER

NO REPORT TO AIRBUS SEER 1/2/3 OR AIRTAC

AND FOLLOW THEIR INSTRUCTIONS.

MORE

SIDE SHELL YES

NO

DETECTED

THAN 5 SPOTS PER

SIDE SHELL YES

MORE

DETECTED

NO

N_SB_551041_6_FAAA_03_05

Figure A-GFAAA - Sheet 03

Flow Chart - Flow Chart 3

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 104

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SERVICE BULLETIN

**CONF ALL

INSPECT THE RUDDER SIDE SHELL

YES KNOWN IN THE NO

PERFORM 

ON REPAIR LOCATION AND 

YES TYPE A−A NO

IN CASE OF FINDINGS,

TAP TEST INSPECTION

OR WOODPECKER

ALL OTHER REPAIR TYPES:

PERFORM ELCH

IDENTIFIED REPAIRS

CONTINUE WITH

ACTIONS IN FLOW CHART 2

UPPER GFRP AREA

GFRP AREA

REPAIRS

PULSE THERMOGRAPHY INSPECTION

MARK THE REPAIR

REPAIR

REPORTED

PERFORM

INSPECTION

AND/OR UT

AROUND THE

PERFORM 

ON THE COMPLETE

PULSE THERMOGRAPHY INSPECTION

GFRP AREA

TAP TEST INSPECTION OR

WOODPECKER INSPECTION

PERFORM

ON THE COMPLETE GFRP AREA

MARK THE REPAIRS

YES CORE DISBONDING

NO

SKIN TO

IDENTIFIED

ALL OTHER REPAIR TYPES:

PERFORM ELCH

IDENTIFIED REPAIRS

AND/OR UT

AROUND THE

18

WHICH ARE NOT

MANUFACTURING REWORKS

20

20

21

NOTE:

REFER TO FIGURE A−GFAAA, SHEET 06.

N_SB_551041_6_FAAA_04_04

Figure A-GFAAA - Sheet 04

Flow Chart - Flow Chart 4

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 105

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SERVICE BULLETIN

**CONF ALL

PULSE THERMOGRAPHY PAINT

OPERATOR

IS SURE THAT THE 

NO

GFRP−AREA

400.00 microns

THICKNESS LIMITATION

RUDDER PAINT THICKNESS

IS BELOW THE GIVEN

LIMITS

YES

APPLY PAINT THICKNESS

MEASUREMENT TOOL

NO

LOCAL PAINT REMOVAL

RUDDER

PAINT THICKNESS

IS BELOW 

THE GIVEN

LIMITS

YES

CONTINUE WITH ACTIONS

DEFINED IN FLOW CHART 1 PAINT RESTORATION IS REQUIRED

AFTER PULSE THERMOGRAPHY

AND/OR ELCH/UT INSPECTION

13 14

16

15 17

PAINT RESTORATION

IS REQUIRED AFTER

PULSE THERMOGRAPHY

AND/OR ELCH/UT

INSPECTION

CFRP−AREA

800.00 microns

OR

400.00 microns

BELOW DECAL FOIL

NOTE:

REFER TO FIGURE A−GFAAA, SHEET 06.

N_SB_551041_6_FAAA_05_05

Figure A-GFAAA - Sheet 05

Flow Chart - Flow Chart 5

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 106

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SERVICE BULLETIN

**CONF ALL

SEE AIRBUS LIST WITH A/C MSN, RUDDER S/N

SEE AIRBUS DEFINITION OF REPAIR TYPES AFFECTED

BY THE ISB INSPECTION. REFER TO FIGURE A−GBBAA.

SEE AIRBUS BOOSTER DEFINITION. 

NOTE:

01

02

03

AND RAS NUMBER, REFER TO FIGURE A−GBCAA.

IF AN AIRCRAFT LISTED IN THE SB EFFECTIVITY HAS A

REPAIR EMBODIED THAT IS NOT OF AIRBUS ORIGIN, 

04

AND WHICH AFFECTS THE CONTENT OF THIS SB, THE

APPROVAL BY ITS AIRWORTHINESS AUTHORITY FOR

ANY ADAPTATION NECESSARY BEFORE 

THIS ACTION IS NOT NECESSARY, IF THE INFORMATION

HAS BEEN ALREADY SENT TO AIRBUS IN ACCORDANCE

05

NEXT STEP.

REFER TO FIGURE A−GBDAA.

OPERATOR IS RESPONSIBLE FOR OBTAINING THE

INCORPORATION OF THE SB.

WITH THE OIT SE 999.0060/10 CONTINUE WITH THE 

06 REPAIR SIZE DEFINED BY THE LARGEST REPAIR PLY.

ONLY MANUFACTURING HOT−CURING REWORKS ARE

DOCUMENTED IN AOT 55A1038 AND ISB 55−1035, −1036

07

MANUFACTURING REWORK COMPLETE DATA.

AND −1037. AIRBUS MUST BE CONTACTED FOR

08 BASED ON PROVIDED AIRBUS EVALUATION OF RUDDER

S/N MANUFACTURING REWORK DATA.

12 FOR GFRP−AREA INSPECTION REFER TO FLOW CHART 4

REPAIR SIZE DEFINED BY THE LARGEST REPAIR PLY.

PENDING AVAILABILITY OF SRM IMPROVED REPAIR, AIRBUS IS TO BE

CONTACTED FOR INSTRUCTIONS.

SIDE SHELL REPLACEMENT CAN BE DONE ONLY AT THE AIRBUS STADE FACILITY.

09

10

11

REFER TO FIGURE A−GBEAA.

19 THE NEW REPAIR CUTOUT IS EQUAL TO

THE LARGEST OUTER SKIN REPAIR PLY.

18 REFER TO FIGURE A−GBBAA

20 IN CASE OF FLUID INGRESS REFER TO

FLOW CHART 3 FOR FURTHER INSTRUCTIONS

21 FOR PAINT THICKNESS IDENTIFICATION REFER TO

FLOW CHART 5

13 PRIOR TO THE APPLICATION OF THE PULSE THERMOGRAPHY

METHOD NTM 55−40−50 THE OPERATOR HAS TO CHECK

THE SIDE SHELL PAINT THICKNESS. IT IS THE 

OPERATORS RESPONSIBILITY TO ENSURE THAT THE

RUDDER SIDE SHELL PAINT THICKNESS IS BELOW THE

GIVEN LIMITS.

PLEASE CONSIDER THE INFORMATION FOR PAINT

RESTORATION PROVIDED WITH THE OIT 999.0130/06

DATED 21 NOV 2006.

SRM 51−75−11 RECOMMENDS ABRADING COMPOSITE

SURFACE UP TO THE FIRST PRIMER COATING IN ORDER

TO AVOID SURFACE DAMAGE OF THE COMPOSITE.

IN CASE OF A SMOOTH AND EVEN PAINT THICKNESS

DISTRIBUTION FIG. A−GABAA PROVIDE GUIDANCE

MATERIAL ABOUT A FEASIBLE PAINT BORER LOCATION 

DISTRIBUTION OVER THE SIDE SHELL.

IN CASE PAINT REMOVAL LARGER THAN 2m2 IS REQUIRED

IT IS RECOMMENDED TO REMOVE THE RUDDER FROM

THE A/C.

14

15

16

17

22 CLEAN THE PREVIOUS REPAIR AREA.

REFER TO SRM 51−77−11 PARA 4.E.

PERFORM A LOCAL MECHANICAL SANDING

A STEP BY STEP BASIS UP TO INITIAL BASIC PRIMER LAYER.

AS PER SRM 51−75−11 PARA 3.D. ON 

23

ON TOP/AROUND THE REPAIR

NO VISIBLE REPAIR: 

USING ABRASIVE CLOTH GRADE 100, 220, 280, 400.

MECHANICAL SANDING ON A STEP BY STEP BASIS

24

CONTINUE LOCAL SANDING UP TO PORE FILLER/ADHESIVE.

REFER TO SRM 51−77−11 PARA 4.D.

25 ENSURE NO DAMAGE TO CFRP OR GFRP BASE MATERIAL.

IF THE LARGEST REPAIR PLY IS NOT VISIBLE,

BEYOUND THE INITIAL DETECTED REPAIR PATCH.

26

CONTINUE LOCAL SANDING ON AND AROUND THE REPAIR WITH A RADIUS APPROX. 50.0mm (1.97in)

27 USE PAINT BORER TO ASSESS LOCAL PAINT SCHEME, THICKNESS AND INITIAL BASIC PRIMER

PRIOR SANDING. USE ON TOP OF REPAIR AND BESIDE REPAIR LOCATION.

28 MAX. 1m2 (10.76 sq.ft.) SANDED AREA PER LOCAL REPAIR IS ALLOWED.

SRM 51−77−10 AND SEND A DETAILED REFERENCE REPORT TO SEER DEPARTMENT.

IN CASE OF DAMAGE, PERFORM ASSESSMENT AS PER

IT IS THE OPERATOR’S RESPONSIBILITY TO ENSURE THAT THE STRUCTURAL SIDE SHELL OUTER SKIN PLY

(CFRP OR GFRP) IN ACCORDANCE TO THE DESIGN DRAWING IS NOT DAMAGED DURING THE LOCAL 

SANDING PROCESS.

REMARK: IN MOST OF THE RUDDER SURFACE THE OUTER SKIN CONSISTS ONLY OF ONE CFRP OR GFRP PLY!

IN CASE OF SANDING DAMAGE IMMEDIATE REPAIR BEFORE NEXT FLIGHT IS REQUIRED. AN AREA DAMAGED

BY THE LOCAL SANDING COMBINED WITH AN EXISTING REPAIR CAN LEAD TO A NON−REPAIRABLE SIZE

AND SUBSEQUENT SIDE SHELL REPLACEMENT!

N_SB_551041_6_FAAA_06_01

Figure A-GFAAA - Sheet 06

Flow Chart

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 107

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SERVICE BULLETIN

**CONF ALL

Closing of ventilation holes in outer skin

Method 1 − Application of a bonded cover

NOTE: This repair needs to be re−inspected. Correct cover application has to be ensured by frequent

detailed visual inspection during the application period at intervals not exceeding 750 FC.

1. Apply high speed tape over the ventilation hole, refer to Chapter 51−77−12 Paragraph 2.

Method 2 − Application of laminated cover

NOTE: This repair needs no re−inspection.

2. Prepare the repair area, refer to Chapter 51−77−11 Paragraph 4.M.(2)., apply only step

1 to 2 and 10 to 17.

3. Protect the area adjacent to the repair area with flash tape (Material No. 05−138), refer to

Chapter 51−77−11, Paragraph 3.B.(2).

4. Prepare the laminating resin (Material No. 20−022), refer to Chapter 51−77−11, Paragraph 

6.B.(2) and 4.A.(3).

5. Prepare the repair plies (MIL−C−9084C TYPE VIIIA or B − style 7781 dry glass fabric), refer to

Chapter 51−77−11, Paragraph 4.H. For ply dimensions and orientation refer to Figure 1.

NOTE: Round all corners with radii 12mm (0.5 in.) minimum.

6. Prepare the laminating resin, refer to Chapter 51−77−11, Paragraph 6.B.(2) and 4.A.(3).

7. Apply repair plies to the repair area as shown in Figure 1, refer to Chapter 51−77−11, 

Paragraph 5.A.

8. If the repair cure shall be accelerated by heat:

− Install the vaccum bag, refer to Chapter 51−77−11, Paragraph 5.D.(1), respect modificatons

shown on Figure 2 and the heating equipment.

− Allow repair to cure under vacuum pressure, refer to Chapter 51−77−11, Paragraph 5.E.,

use 22 in. of hg (560 mm of hg or 75 Kpa) minimum. Let the resin gel for one hour at room

temperature, then cure for 4 hours at 60 C, refer to Chapter 51−77−11, Paragraph 5.E.

− Remove the vacuum bag and the heating equipment.

− Continue with step 10.

9. If the repair cure shall be performed at room temperature:

− Install the vacuum bag, refer to Chapter 51−77−11, Paragraph 5.D.(1) and respect modifications

shown on Figure 2.

− Allow repair to cure under vacuum pressure, refer to Chapter 51−77−11, Paragraph 5.E.,

use 22 in. of hg (560 mm of hg or 75 Kpa) minimum. Let the resin cure for six hours at room

temperature or perform resin gelation test outside the repair area, after resin gelation perform

cure for two hours (the latter approach must be applied if RT is below 18 C (65 F)).

− Remove the vacuum bag and continue with step 10 during the next stop.

10. Remove the flash tape. Ensure that the glass ply is correctly located and cured, refer to

Chapter 51−77−10, Paragraph 5.

11. Remove any resin remnants from the border area of the glass ply, use abrasive paper. Start with

280 grade and finish with 400 grade.

WARNING: CLEANING AGENT (MATERIAL NO. 11−003 or 11−004) IS DANGEROUS.

12. Clean the repair area with cleaning agent (Material No. 11−003 or 11−004), refer to Chapter 51−

77−10, Paragraph 4.E.(1)(a).

13. Restore the surface protection, refer to Chapter 51−75−12.

N_SB_551041_6_AAAA_01_03

Figure A-GAAAA - Sheet 01

Closing of ventilation holes

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 108

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SERVICE BULLETIN

**CONF ALL

Figure 1 − Ply lay−up

Ply 2 0/90 42 x 42mm

Ply 1 45 30 x 30mm

Ply 3 45 54 x 54mm

NON PERFORATING GLASS PLY FLASH TAPE

PARTING FILM

RUBBER CAUL

PLATE

BREATHER

DRY GLASS FABRIC

OR PEEL PLY

VACUUM GAGE VACUUM SOURCE

VACUUM BAG FILM

VACCUM BAG

SEALANT TAPE

NOTE:

01 RUBBER CAUL PLATE IS MANDATORY, 

01

REFER TO CHAPTER 51−77−11, PARAGRAPH 3.C.

Figure 2 − Bagging for curing process

N_SB_551041_6_AAAA_02_00

Figure A-GAAAA - Sheet 02

Closing of ventilation holes

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 109

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SERVICE BULLETIN

**CONF ALL

PAINT THICKNESS MEASUREMENT USING THE PAINT BORER ON THE RUDDER SIDE SHELL

THE PAINT THICKNESS MUST BE DETERMINED FOR A CORRECT SETTING OF THE

PULSE THERMOGRAPHY INSPECTION PARAMETERS. IF THE THICKNESS IS UNKNOWN

DETERMINE THE THICKNESS WITH THE PAINT BORER.

DESCRIPTION

1. GENERAL

A. THIS PROCEDURE CONTAINS THE INSPECTION PROCEDURE DESCRIBING

PAINT THICKNESS MEASUREMENT USING THE PAINT BORER ON

THE RUDDER SIDE SHELL.

PROCEDURE

1 TASK SUPPORTING DATA

A. AREA OF APPLICABILITY

ALL RUDDER INSPECTED WITH NTM 55−40−50

B. DESCRIPTION OF POSSIBLE DAMAGE

THE PAINT THICKNESS MUST BE DETERMINED FOR A CORRECT SETTING OF THE

PULSE THERMOGRAPHY INSPECTION PARAMETERS. IF THE THICKNESS IS UNKNOWN

DETERMINE THE THICKNESS WITH THE PAINT BORER.

C. JOB SETUP INFORMATION

(1) TOOLING

PREFERRED TOOL: PAINT BORER 518MC WITH THE DRILLS IN TABLE 1

ALTERNATIVE TOOL: PAINT BORER 518 OR PAINT BORER 518S WITH THE DRILLS

 IN TABLE 1

ADDITIONAL DOCUMENT: OPERATING MANUAL PAINT BORER

TABLE 1 : DRILLS

N_SB_551041_6_ABAA_01_05

Figure A-GABAA - Sheet 01

Paint borer instructions

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 110

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SERVICE BULLETIN

**CONF ALL

2 PROCEDURE:

1. PREPARE THE PAINT BORER ACCORDING TO THE OPERATING

1. PLACE THE PAINT BORER ON THE AREA, WHERE THE THICKNESS OF THE

 RUDDER PAINT HAS TO BE MEASURED, SEE FIG. A−GABAA SHEET 3+4

2. DO THE DRILLING AND THE PAINT THICKNESS MEASUREMENT ACCORDING 

 PAINT BORER OPERATING INSTRUCTIONS, REFER ALSO

 CAUTION: DO NOT DRILL DEEPLY INTO THE BASE MATERIAL (CFRP OR GFRP). ONLY A

TINY BASE MATERIAL SPOT IS ENOUGH TO MEASURE THE PAINT

THICKNESS, REFER TO FIG. A−GABAA SHEET 5+6

3. APPLY A CONTRAST MARK (WITH A NON PERMANENT MARKER PEN) ON THE

 THE SPOT OF MEASUREMENT. IF THE RUDDER PAINT IS LIGHT (E.G. YELLOW, 

 WHITE ...), USE A DARK (BLACK) PEN TO ENHANCE CONTRAST OF THE TOP

 COATING, IN CASE OF A DARK TOP COAT USE A LIGHT (WHITE) PEN. SEE

A. PREPARATION FOR INSPECTION

B. INSTRUMENT ADJUSTMENT

1. NO

C: INSPECTION PROCEDURE

 INSTRUCTIONS.

4. RECORD ALL THE MEASURED PAINT THICKNESS VALUES FOR THE

 PULSE THERMOGRAPHY INSPECTION.

5. AFTER MEASUREMENT SEAL THE SPOT WHERE DRILLED − REFER TO

 SRM 51−75−10.

 FIG. A−GABAA SHEET 7+8

 TO FIGURE A−GABAA SHEET 3−8

− IF THE LAYER THICKNESS IS NOT KNOWN,

INITIALLY USE A DRILL WITH 20−2000 m ( CUT ANGLE: 45°)

TO BRING THE FULL SECTION INTO VIEW;

CHANGE TO 10−1000 m (CUT ANGLE: 26.6°) IF THICKNESS

TURNS OUT TO BE 1000 m OR LESS

μ 

μ 

μ 

CAUTION: IT IS IMPORTANT TO HAVE THE ABOVE SPECIFIED DRILLS AVAILABLE.

CONTACT DRILL SUPPLIER IF THE CUTTING ANGLE AND DRILL NUMBERING

CAUTION: DO NOT USE ULTRASONIC OR EDDY CURRENT BASED PAINT THICKNESS

MEASUREMENT DEVICES, AS EDDY CURRENT ONLY WORKS ON METALLIC

AND FOR ULTRASONIC BASED DEVICES THE NUMBER OF POSSIBLE PAINT

LAYERS IS TOO HIGH TO GET RELIABLE RESULTS.

IS UNKNOWN.

N_SB_551041_6_ABAA_02_05

Figure A-GABAA - Sheet 02

Paint borer instructions

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 111

6

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF ALL

LH SHOWN

RH SIMILAR

A

Z326

A

CFRP

AREA

GFRP

AREA

B D E

C D E

N_SB_551041_6_ABAA_03_00

Figure A-GABAA - Sheet 03

Paint borer instructions

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 112

6

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF ALL

PAINT SYSTEM

DIFFERENT LAYERS

(E.G. FILLER, PRIMER,

TOP COAT, ...)

CFRP

HONEYCOMB

CORE

d

NOTE:

01 DRILL HOLE

01

d = PAINT SYSTEM

THICKNESS

SPOT DRILLING

DETERMINATION OF

PAINT THICKNESS

PAINT SYSTEM

DIFFERENT LAYERS

(E.G. FILLER, PRIMER,

TOP COAT, ...)

GFRP

HONEYCOMB

CORE

d 01

B

C

D E

F

G

N_SB_551041_6_ABAA_04_01

Figure A-GABAA - Sheet 04

Paint borer instructions

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 113

6

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

SERVICE BULLETIN

**CONF ALL

F

1) NOT DRILLED DEEP

ENOUGH

2) GOOD DRILLED DEPTH 

(TINY CFRP SPOT)

3) DRILLED TO DEEP

(BIG CFRP SPOT)

7) DRILLED TO DEEP

(DAMAGE OF THE HONEYCOMB

6) DRILLED TO DEEP

(BIG CFRP SPOT)

5) GOOD DRILLED

DEPTH (TINY

4) NOT DRILLED

DEEP ENOUGH

CFRP SPOT) CORE)

N_SB_551041_6_ABAA_05_00

Figure A-GABAA - Sheet 05

Paint borer instructions

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 114

6

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

SERVICE BULLETIN

**CONF ALL

8) NOT DRILLED DEEP

ENOUGH

9) NOT DRILLED DEEP

ENOUGH

10) GOOD DRILLED

DEPTH

11) DRILLED TOO DEEP

(BIG GFRP SPOT)

12) GOOD DRILLED DEPTH

(DAMAGE OF THE

13) DRILLED TOO DEEP

(TINY GFRP SPOT)

14) DRILLED TOO DEEP

(DAMAGE OF THE

(TINY GFRP SPOT)

HONEYCOMB CORE) HONEYCOMB CORE)

G

N_SB_551041_6_ABAA_06_00

Figure A-GABAA - Sheet 06

Paint borer instructions

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 115

6

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

SERVICE BULLETIN

**CONF ALL

N_SB_551041_6_ABAA_07_00

Figure A-GABAA - Sheet 07

Paint borer instructions

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 116

6

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

SERVICE BULLETIN

**CONF ALL

BR1

BR2

BR3

BR4

BR5

BR6

BR7

200.0mm (7.87in.) AFT OF BR7 RIVET CENTER

200.0mm (7.87in.) FWD OF HOIST POINT CENTER LINE

200.00mm (7.87in.) FROM

BR2 RIVET CENTER LINE

PROPOSAL:

1SPOT IN GFRP AREA

6SPOTS IN CFRP AREA

A

B

C

A

B

C

D

200.0mm (7.87in.) FWD OF HOIST POINT CENTER LINE

D

600.0mm (23.62in.)

600.0mm (23.62in.)

N_SB_551041_6_ABAA_08_02

Figure A-GABAA - Sheet 08

Paint borer instructions

DATE: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 117

6

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@A318/A319/A320/A321

SERVICE BULLETIN

REPORTING SHEET

TITLE: STABILIZERS - RUDDER SIDE SHELL SANDWICH REPAIR

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: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 1

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@A318/A319/A320/A321

SERVICE BULLETIN

QUALITY PERCEPTION FORM

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

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

improve the quality of our Service Bulletins.

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

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

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- 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: Nov 26/12 SERVICE BULLETIN No.: A320-55-1041

REVISION No.: 01 - Feb 24/14 Page: 1

6

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