sb_57_1154_04

@A318/A319/A320/A321SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUSCUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNAC CEDEXFRANCETel : (33) 5 61 93 33 33Telex : AIRBU 530526FFax : (33) 5 61 93 42 51

ATA SYSTEM: 57

TITLE: WINGS - INSPECTION OF WING TOP SKIN PANEL 2 OVERHANGBETWEEN RIB 22 AND RIB 27 TO INSPECT FOR CORROSION

MODIFICATION No.: None

This page transmits Revision No.04 of Service Bulletin No.A320-57-1154

ADDITIONAL WORK

**CONF ALL

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

REASON

Revision 04 issued:

- To remove COMPB01 from Para. 2.A.(2) ’Price and Availability’

- To update the Gantt chart to colour

- To update the effectivity

- To Provide both bolting options (ASNA2001 OR ASNA2026) for the Fixed Panel Assembly, Item (3)for Config. 003 only.

CHANGES

FRONT MATTERWINGS - INSPECTION OF WING TOPSKIN PANEL 2 OVERHANG BETWEENRIB 22 AND RIB 27 TO INSPECT FORCORROSION

CONFIGURATION UPDATED R

SUMMARYMATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE

UPDATEDR

EFFECTIVITY OPERATOR LIST UPDATED RPLANNING INFORMATIONEFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATEDR

Configuration definition

DATE: Mar 06/09 SERVICE BULLETIN No.: A320-57-1154

REVISION No.: 04 - Jan 26/12 Page: 1

7

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



CONF 002 CONFIGURATION DEFINITION UPDATED RCONF 003 CONFIGURATION DEFINITION UPDATED R

MATERIAL INFORMATIONMATERIAL - PRICE AND AVAILABILITY

Price and Availability PRICE AND AVAILABILITY UPDATEDMATERIAL AVAILABILITY UPDATEDMATERIAL PRICE UPDATEDMATERIAL SET UPDATED

R

ACCOMPLISHMENT INSTRUCTIONSTASK 571154- 832-895-001-INSPECTION

Subtask 571154-220-401-005 SUBTASK SOLUTION UPDATEDCONFIGURATION UPDATEDFIGURE REFERENCE UPDATED

R


R


R

Subtask 571154-220-402-005 SUBTASK SOLUTION UPDATEDNOTE UPDATEDQUANTITY UPDATEDITEM NUMBER UPDATEDPART NUMBER UPDATEDPART NUMBER DESCRIPTION UPDATED

R

Fig. A-UDAAE

Fig. A-UDAAE Sheet 01 SHEET UPDATED R

APPENDIX 3 - ELAPSED TIME ASSUMPTIONFig. A-UVAAA

Fig. A-UVAAA Sheet 01 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

This Revision is issued:

To inform operators that the Kits have been updated

To inform operators that the accomplishment instructions have been amended to clarify the inspectionareas.

Revision 02 is issued:

To incorporate validation comments.



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Revision 03 issued:

To extend the effectivity of this Service Bulletin to include aircraft up to and including MSN 4099

To inform operators that this Service Bulletin is now an Airbus Monitored Retrofit Campaign

To add OIT SE 999.0026/11 to the OTHER references in the REFERENCES / REPERCUSSIONS table

To include a reporting sheet to identify level of Service Bulletin accomplishment

To include a Gantt Chart for the elapsed time assumptions.

Operators are advised that due to some aircraft being deleted from the effectivity of this ServiceBulletin, the configuration numbering may have changed.

REVISION SEQUENCE

ORIGINAL: Mar 06/09

REVISION No. : 01 - Oct 16/09

REVISION No. : 02 - Sep 10/10

REVISION No. : 03 - Sep 09/11

REVISION No. : 04 - Jan 26/12



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This Page Intentionally Left Blank



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SUMMARY


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

ATA SYSTEM: 57


**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Several instances of exfoliation corrosion of the wing top skin panel 2 have been reported. Thecorrosion was found aft of the rear spar and the false rear spar, in front of the aileron and haddeveloped from the lower surface of the panel 2.

Two possible causes have been identified as potential contributing factors for the corrosion:

- the panel is made from aluminum alloy 7150T651, its resistance against corrosion is increased byChromic Acid Anodizing and paint coating, however, a sample inspection has revealed, in someinstances, degrading of the paint system

- in-service aircraft may be affected by degraded sealing at the interface of the wing top skin panel 2and aft panels.

If left untreated, the corrosion could become exfoliation corrosion; caused when moisture comes intocontact with the exposed edges of the aluminum alloy panel.

This Service Bulletin details instructions to perform a (repeat) special detailed ultrasonic inspectionor alternatively (as a terminating action) a detailed visual inspection (x10 magnification) at fastenerlocations at the wing top skin panel 2 overhang upper and lower surface and at the wing top skin panel2 overhang edge (vertical skin edge and chamfer) to detect any exfoliation corrosion.

Accomplishment of this Service Bulletin will establish if there are signs of corrosion of the wing top skinpanel 2 overhang and if necessary, provide details of repair instructions to rectify any corroded areas.

Also, the re-application of the corrosion protection scheme and the restoration of the sealant will reducepossible corrosion occurrences in the area.

This Service Bulletin has been validated on A320 aircraft MSN 1023.



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SUMMARY

This Service Bulletin has been accomplished at Revision No. 01 on aircraft MSN 1023 to validate itscontent.

A booklet including photographs taken during the validation of this Service Bulletin is available onAirbusWorld - Maintenance and Engineering - Service Bulletin Information.

Accomplishment of this Service Bulletin will significantly reduce the likelihood of major repairs andexcessive aircraft downtime.

If there is previous experience of exfoliation corrosion in this area, or if the aircraft is being operated inan aggressive corrosive environment, AIRBUS recommends that the inspections are performed at theearliest opportunity.

GENERAL EVALUATION

EVALUATION TABLECOMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB NO

POTENTIAL AD NO A/C OPERATION AFFECTED NORELIABILITY AFFECTED NO PAX COMFORT AFFECTED NOCOST SAVING NO ETOPS AFFECTED NOSTRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin recommended to be accomplished to prevent significant operationaldisruptions.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLEMATERIAL SET QTY PER

A/CPRICE PERA/C (USD)

MAIN PARTS

Kit 571154B01R01 2 1,984.00 Bolt-Csk Head, Rivet-Solid Csk, Nuts

Kit 571154B04R01 2 2,980.00 Rivet-Blind Csk, Rivet-Solid Csk, Nuts

Kit 571154B07R03 2 3,680.00 Bolt-Csk Head, Rivet-Blind Csk, Rivet-Solid Csk, Nuts

TOTAL 8,644.00

**CONF 002



MAIN PARTS




TOTAL 8,504.00



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SUMMARY

**CONF 003



MAIN PARTS




TOTAL 7,216.00

Component COMPB01 2 See SB Bolt-Csk Head, Nut

EFFECTIVITY

**CONF ALL

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

01Z 03X 15T 16T 17W 27V 31V 31X 35U 36V 46U 47Y 52T53U 53Z 59U 59Z 61T 62X 69X 73W 74T 78X 79W 80X 82V85T 86W 86Z 89T 91X 93V 95V 95W 96W 98W AAF AAN AARAAW ABL ABQ ABY ACA ACI ADH ADR AEE AFL AFR AGC AHYAIJ AJM ALK AMC AMU ANA ANZ ART AUA AUH AVA AXM AZAB2V BAB BAL BAW BEC BEL BER BGF BGH BHP BIE BJN BKPBMA BON BRS BTV C9G CCA CCM CEB CEF CES CHH CIB CQHCQN CSA CSC CSN CSZ CTN CYP D2F DAL DCS DKH DLH DRKEAA EDW EIN ETD EZD EZY F2I FFT FHE FHY FIN FPY FRNG2X G4I G8E GAF GAP GFA GIA GIR GLG GMI GOW GSW GWIGWY HAY HCC HDA HRM HVN I2L IAC IBE IGO IRA IRM ISSIWD IZM JAV JBU JET JKK JSA JST JZR KAC KFR KGL KHOKIL KKK KMF KNE KZR LAN LBT LBY LFO LFX LIT LJB LLMLLP LMJ LMU LZB M2I MAC MAU MDL MEA MHS MJN MLD MLMMLR MMA MON MSC MSR MXA NIA NKS NLY NMA NMB NVD NVRNWS OAI OHY ONE ORF OZW PAL PIC PTR PVJ QAF QTR R1TRAM RBA RBG RFJ RJA RKM RNV ROT RYW RZO SAA SAS SBISBN SDM SFJ SFW SGG SHJ SHY SKU SLK SND SNX SOL STUSUD SVA SVR SVW SWM SWR SYR TAE TAI TAK TAM TAP TARTBJ TCW TCX TGW THY TNA TOM TWJ UAL UDC UEA UKN UNAUSA VIM VJC VKG VKH VLE VLG VLK VNV VOI VRD WAU WGTWHT WRC WTJ WZZ XLF YAP

CONCURRENT REQUIREMENTS

This Service Bulletin can be done at the same time as the following Service Bulletin(s):

- Service Bulletin No. A320-57-1155.

REFERENCES / REPERCUSSIONS

TFU 57.21.00.007OEB NoneAOT None



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SUMMARY

SIL 57-10557-110

LINE MAINTENANCE AFFECTED NoLIFE LIMIT NoneOTHER OIT SE 999.0030/09, OIT SE 999.0026/11, SBIT

SEMB/914.0413/09, SBIT SEMB/914.0635/09

NATURE OF THE WORK

AIRCRAFT YESEQUIPMENT NO

HARD NOSOFT NOOBRM NO

MANPOWER

**CONF 001

Task 571154-832-895-001: INSPECTIONTOTAL MANHOURS 52.00ELAPSED TIME (HOURS) 29.50

**CONF 002


**CONF 003


APPENDICES

**CONF ALL

APPENDIX 1 - SPECIAL TOOLING

APPENDIX 2 - SERVICE BULLETIN REPORTING SHEET

APPENDIX 3 - ELAPSED TIME ASSUMPTION



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SUMMARY

**CONF ALL

LH SHOWNRH SIMILAR

A

RIB22

RIB24

FIXED PANELASSEMBLY

RIB27

A

575AT(675AT)

TRAILING EDGEFALSEWORK

N_SB_571154_7_SAAA_01_03

Figure A-USAAA - Sheet 01



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SUMMARY




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ATA SYSTEM: 57



This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain theproperty of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection withany information contained in it. It is delivered on the express condition that said document and theinformation contained in it shall be treated as confidential, shall not be used for any purpose other thanthat for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shallnot be duplicated in any manner (except for the purposes of performing the tasks described hereunderand provided that any recipient of such document shall comply with the conditions herein), withoutAIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

(1) Models

318-111 318-112 318-121 318-122 319-111 319-112 319-113 319-114319-115 319-131 319-132 319-133 320-211 320-212 320-214 320-216320-231 320-232 320-233 321-111 321-112 321-131 321-211 321-212321-213 321-231 321-232

(2) Effectivity by MSN

0029 0039 0042-0047 0049-0057 0059 0061 0063-0078 0080-0088 0090 0093-00960099 0102-0104 0109-0127 0135-0155 0157-0162 0164-0176 0178-0179 0181-01830185-0187 0189-0192 0194-0218 0220-0224 0227-0237 0239-0242 0244-02450248-0250 0252-0256 0258-0270 0272-0279 0281-0287 0289-0303 0306-0312 03140316-0325 0328-0335 0337 0339-0343 0345-0362 0364-0373 0375-0396 0398-04100412-0432 0434-0436 0438-0466 0468-0477 0479-0480 0482-0535 0537-05460548-0601 0603-0614 0616-0631 0633-0707 0709-0752 0754-0788 0790-09550957-1043 1045-1185 1187-1217 1219-1277 1279-1373 1375-1463 1465-18121814-1821 1823-1829 1831-1918 1920-1929 1931-1984 1986-1991 1993-20242026-2110 2112-2423 2425-2499 2501-2721 2723-3037 3039-3091 3093-31093111-3162 3164-4099



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(3) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the timeof issue in accordance with the information available to AIRBUS. Any future changesresulting from transfer of an aircraft from one operator to another will not be reflected inthis list unless the Service Bulletin is revised for another reason.

OPERATOR MSN01Z 158903X 242115T 0764 1494 2910 316416T 402417W 304627V 382631V 0164 0332 036831X 219235U 008836V 013646U 2906 2952 2982 3275 3296 3332 3674 3734 3986 405347Y 039452T 159953U 3316 3748 3812 3895 3905 395053Z 146859U 2706 307359Z 155661T 040762X 340269X 058873W 008774T 216578X 073979W 375180X 274882V 325585T 023486W 038486Z 0169 1706 175089T 335691X 283793V 393295V 337995W 294996W 4044 406798W 0039 0042 0103 0120AAF 0244 0639 0808 0823 1006 1451 1846 2870 3852AAN 0430 0527



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OPERATOR MSNAAR 0802 1174 1227 1356 1511 1636 1670 1734 2041 2045 2110 2226

2247 2290 2397 2459 2808 2840 2943 3244 3297 3437 3483 34963641 3873

AAW 3224 3236 3615 3657 4004ABL 1970ABQ 3364 3385 3388 3403 3974ABY 2278 2349 2712 2930 2964 3044 3218 3246 3444 3476 3626 3802

3840 3925 4061ACA 0059 0068 0073 0084 0122 0126 0127 0141 0149 0150 0154 0159

0174 0175 0183 0210 0231 0232 0233 0242 0248 0253 0254 02550265 0277 0284 0290 0309 0324 0330 0341 0378 0403 0404 05460572 0634 0656 0670 0672 0682 0688 0691 0693 0695 0697 07110719 0721 0728 0732 0736 0740 0742 0752 0757 0769 0773 07790785 0800 0813 0817 0829 0831 0840 0845 1562 1577 1602 16111623 1630 1632 1638 1673 1719 1726 1742 1748 1772 1783 18051811 1853 1864 1874 1940 2018 2145

ACI 2152ADH 3138 3161 3328 3343 3502 3515 3532ADR 0043 0191 0444AEE 1727 1880 2468 3033 3066 3074 3162 3365 3392 3423 3439 3462

3478 3526 3527 3709 3714 3745 3753 3773 3785 3820 3829 38503878 3990 4065 4094

AFL 2052 2069 2072 2091 2093 2106 2116 2133 2144 2151 2163 21792222 2233 2243 2330 2337 2342 2875 2903 2912 2920 2947 29572965 3052 3063 3157 3191 3267 3281 3298 3334 3336 3373 34103511 3545 3574 3627 3631 3640 3644 3699 3711 3778 3786 37893794 3823 3835 3838 3923 3942 3954 3998 4058 4074 4099

AFR 0044 0061 0063 0102 0115 0144 0145 0155 0186 0187 0214 02270228 0236 0237 0239 0270 0278 0285 0286 0287 0337 0352 03770491 0498 0509 0521 0529 0544 0598 0600 0608 0618 0625 06370777 0796 0938 0985 0998 1000 1020 1025 1036 1133 1151 11691176 1190 1201 1216 1267 1271 1299 1344 1404 1415 1444 14491471 1476 1502 1505 1524 1616 1622 1640 1645 1658 1677 16911699 1733 1859 1873 1879 1885 1894 1900 1924 1938 1949 20352059 2071 2081 2100 2109 2140 2213 2228 2317 2344 2350 24562582 2601 2686 2705 2716 2721 2750 2918 2938 2951 2961 29672972 3008 3009 3051 3065 3098 3372 3399 3401 3419 3420 34413470 3777 3795 3814 3825 3859 3884 3930 4063 4084

AGC 0190 0279 0395AHY 0331 2487 2516 2588 2685 2788 2846 2853 2865 2991 3006AIJ 0707 1132 1162 1179 1244 1259 1308 1322 1747 1780 2048 2189

2227 2539 3021 3123 3149 3160 3286 3304 3312 3374 3508 35143667 3690

AJM 0624 0626 0628ALK 2345 2564 2584 2908AMC 2113 2122 2142 2186 2291 2332 2382 2665 2768 3056 3068AMU 0557 0597 0620 0631 0805 0908 0928 1758 1790 1850 1893 1912

1926 1962



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OPERATOR MSNANA 0139 0151 0167 0170 0196 0212 0245 0300 0328 0365 0383 0413

0482 0501 0507 0531 0534 0549 0554 0658 0669 0685 2061 29983099 3147 3148 3189

ANZ 2085 2090 2112 2130 2148 2153 2173 2257 2297 2533 2594 2663ART 0142 0310 0311 0333 0359 0426 0724AUA 0552 0570 0581 0768 0776 0797 0920 0935 1137 1150 1189 1385

1387 1458 1478 2131 2174 2262 2416 2494 2547 2652AUH 2403AVA 1612 1618 1634 2066 2328 2333 2358 2367 2377 2394 2523 2544

2552 2575 2662 3408 3467 3518 3647 3664 3691 3961 3980 39883992 4001 4011 4026 4046 4051

AXM 2612 2633 2656 2683 2699 2760 2816 2826 2842 2881 2885 29262944 2956 2989 3000 3018 3064 3117 3140 3154 3173 3182 31943201 3223 3232 3261 3277 3291 3299 3327 3338 3353 3370 33943404 3427 3448 3477 3486 3489 3505 3521 3536 3549 3568 35763582 3610 3628 3648 3679 3701 3715 3729 3765 3776 3813 38753963 3997 4019 4035 4070 4079 4088 4098

AZA 0434 0477 0488 0494 0495 0513 0514 0515 0516 0524 0526 05320576 0583 0586 0593 0599 0765 0819 0848 0940 0951 0959 09991138 1168 1217 1220 1448 1457 1473 1480 1489 1722 1740 17451770 1779 2033 2057 2074 2083 2086 2101 2127 2869 2932 29953076 3079 3080 3115 3178 3213 3295 3362 3412 3464 3482 35633598 3609 3643 3666 3695 3732 3815 3831 3846 3885 3906 39213956 3976 3978 4075

B2V 0185BAB 2700 2763 3861 4055BAL 2335 3492BAW 0109 1082 1115 1118 1142 1193 1197 1222 1225 1232 1236 1239

1258 1261 1279 1295 1329 1338 1380 1384 1423 1440 1445 14661510 1513 1529 1537 1558 1574 1590 1594 1604 1606 1661 16651687 1689 1696 1708 1754 1760 1782 1814 1829 1871 1883 18991907 1910 1958 2038 2040 2305 2320 2323 2324 2351 2363 25363081 3235 3254 3290 3301 3314 3351 3468 3499 3550 3607 36493697 3703 3721 3726 3912 4007 4039

BEC 3199BEL 0644 1086 1102 1160 1336 1388 1441 1493 2196 2230 3790BER 1504 1553 1607 1629 1797 1838 1931 1966 1988 1994 2005 2009

2619 3093 3121 3242 3245 3289 3415 3447 3516 3661 3689 37003704 3708 3728 3749 3853 3865 3872 3945 3995 4013

BGF 3188BGH 0221 0294 0349 1087 3139BHP 2968 3055 3202 3422 3604 4033BIE 0293 0517 0519 0642 0827 0891 2707BJN 3617BKP 2254 2310 2509 3421 3424 3454 3694 3759 3911BMA 1014 1177 1418 1424 1690 1711 1922 1987 2098 2188 2190 2194

2389 2429 2441 2466 2653 2694 2697 2720 2799 2981 3049 35123926

BON 3142



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OPERATOR MSNBRS 2263BTV 0168 0441 0449 0460 0461 0710 1676C9G 0772 2277 2362CCA 0876 0921 1296 1654 1679 1753 2000 2007 2015 2172 2202 2205

2237 2269 2285 2293 2298 2454 2499 2508 2525 2532 2545 25512559 2614 2643 2805 2819 2839 2847 2890 3195 3200 3215 32213226 3250 3307 3329 3337 3461 3506 3523 3601 3623 3653 36553665 3678 3722 3725 3766 3806 3940 3973 4022 4031 4062 4091

CCM 1068 1145 3882 3952CEB 2419 2439 2556 2586 2625 2638 2786 2790 2821 2831 2852 2876

2994 3048 3272 3433 3472 3487 3646 3762 3767CEF 2801 3085CES 0665 0754 0828 0838 0854 0883 0897 0909 0914 0925 0939 0967

0984 0986 1005 1028 1030 1041 1070 1072 1093 1108 1285 13031312 1316 1330 1345 1357 1361 1377 1386 1532 1541 1542 15511601 1603 1639 1778 1786 1906 1911 1964 1981 2022 2034 20362049 2056 2068 2155 2171 2182 2199 2212 2219 2221 2235 22392244 2274 2309 2315 2437 2451 2478 2493 2498 2543 2549 25622591 2606 2627 2693 2757 2825 2882 2895 3168 3170 3186 31973233 3247 3249 3262 3471 3481 3559 3593 3611 3612 3613 36393650 3677 3682 3692 3716 3775 3793 3797 3870 3904 3929 39373965 3969 4027 4037 4043 4045

CHH 2557 2561 2581 2611 2617 2644 2733 2746 2849 2891 2985 32853520 3548 3561 3578 3580 3638 3768 3842 3849 3851 3914 39583982 4042

CIB 0774 0809 0884 0894 0905 0957 0971 1381 1402 1416 1437 1968CQH 0978 1286 1372 1686 1769 1852 1920 2939 3014 3023 3747 3819

4072 4093CQN 0696 0698 0704 0705 3836 3876 3901CSA 0674 0684 1439 1450 2719 2758 2789 3031 3043 3060 3094 3097

3406 3436 3452 3660 3892CSC 0540 0550 0551 0556 0573 0582 0591 0874 0878 0902 0912 0915

0919 1007 1013 1060 1293 1500 2313 2348 2396 2431 2510 25342597 2639 3114 3116 3124 3158 3167 3196 3210 3386 3449 35833591 3680 3730 3893 3962 3996 4018 4068

CSN 0709 0712 0718 0720 0722 0849 0859 0881 0895 0900 0950 09661035 1039 1057 1596 1614 1776 1788 1971 1974 1986 1995 20042008 2067 2080 2200 2203 2232 2273 2354 2361 2371 2408 24262435 2484 2505 2506 2511 2519 2521 2530 2541 2546 2554 25552558 2574 2579 2637 2667 2680 2689 2701 2708 2713 2714 27412743 2759 2767 2770 2772 2796 2809 2815 2824 2834 2855 28612877 2899 2901 2915 2936 2940 2948 2950 2960 2969 2971 29863020 3067 3075 3112 3144 3217 3241 3251 3258 3269 3311 33423459 3493 3507 3552 3566 3587 3645 3681 3764 3784 3828 38473860 3867 3890 3903 3910 3920 3934 3938 3941 3951 3959 39813983 3999 4003 4017 4036 4038 4071

CSZ 2672 2684 2841 2905 2909 2935 2973 2980 3131 3132 3153 32063366 3383 3435 3440 3456 3528 3599 3696 3698 3756 3848 38553887 3898 3935 3971 4010 4028



7



OPERATOR MSNCTN 0258 0767 0833 1009 1029 1237 1252CYP 0256 1729 1768 2108 2275 2334 2343 2359 2383 2718D2F 0211 1008 1963 2648 2660DAL 0118 0121 0125 0152 0153 0160 0171 0192 0197 0206 0208 0213

0262 0263 0272 0273 0281 0282 0297 0298 0306 0307 0318 03190329 0339 0340 0355 0358 0360 0367 0372 0380 0381 0387 03880399 0408 0410 0417 0418 0766 0778 0786 0801 0807 0818 08300832 0846 0903 0907 0911 0923 0962 0964 0981 0988 0996 10111037 1058 1062 1191 1230 1249 1324 1325 1346 1392 1414 14341453 1456 1483 1498 1501 1520 1535 1543 1549 1567 1570 15821633 1641 1646 1659 1662 1683 1685 1693 1709 1714 1738 17461752 1766 1774 1789 1796 1800 1810 1812 1815 1820 1824 18281833 1839 1875 1897 1923 1959 1976 1982 1990 2002 2013 20262039 2047 2082 2087 2092 2095

DCS 1053 3243 3513 3632DKH 2879 2913 2975 3027 3234 3268 3368 3485 3596 3605 3967 3984

4064DLH 0069 0070 0071 0072 0078 0083 0086 0093 0094 0104 0110 0111

0116 0117 0135 0137 0147 0161 0162 0172 0200 0201 0202 02090216 0217 0218 0267 0268 0269 0346 0382 0401 0412 0458 04680473 0474 0484 0493 0502 0505 0518 0560 0563 0564 0567 05950609 0610 0616 0623 0627 0652 0679 0689 0692 0694 0699 07000717 0723 0729 0738 0744 0853 0860 0875 0887 0901 1080 11611188 1214 1260 1273 1337 1365 1367 3265 3339 3360 3387 34343592 3625 3864 3936 3987 4005 4016 4047 4054 4073 4085 4097

DRK 2306 2346EAA 0325 0386 0445EDW 0942 0947 1026EIN 0926 1023 1094 1242 1394 1443 1467 2191 2206 2217 2250 2256

2272 2294 2364 2374 2399 2409 2411 2432 2486 2542 2583 26352810 3129 3136 3318 3345 3501 3755 3781 3857

ETD 0350 1944 1945 1947 1955 2167 3004 3050 3676 3693 3713 39024066 4077

EZD 0667 0743 0872 1074 2137 2141 2147 3621EZY 2037 2043 2050 2053 2062 2119 2120 2129 2170 2176 2181 2184

2245 2251 2265 2271 2283 2289 2300 2319 2353 2360 2370 23782380 2385 2387 2398 2402 2412 2420 2427 2436 2442 2446 24502460 2463 2471 2477 2481 2492 2495 2503 2512 2514 2527 25282538 2548 2565 2578 2605 2636 2646 2677 2681 2691 2702 27092715 2727 2729 2735 2742 2744 2754 2765 2769 2777 2779 27822795 2803 2812 2818 2827 2829 2854 2860 2866 2873 2884 29232946 2959 3003 3036 3041 3053 3059 3061 3082 3084 3088 30903118 3122 3134 3137 3176 3184 3411 3413 3426 3432 3442 34663537 3544 3555 3569 3571 3608 3634 3675 3683 3702 3720 37353742 3746 3754 3763 3774 3788 3799 3805 3808 3810 3824 38433844 3845 3854 3871 3888 3909 3913 3922 3946 3953 3975 39793991 4006 4012 4014 4034 4040 4048 4056 4069 4076 4080 4087

F2I 0283



7



OPERATOR MSNFFT 1515 1579 1583 1615 1660 1684 1759 1781 1803 1806 1841 1939

1943 1980 1991 1997 2010 2012 2017 2019 2030 2051 2103 21982209 2218 2236 2240 2241 2253 2258 2260 2276 2287 2318 23252392 2400 2406 2448 2465 2483 2497 2518 2751 2806 2836 28573389 3431

FHE 0888 0936 1171 1210FHY 0580 0771 0855 2524FIN 0941 0961 1073 1107 1184 1185 1241 1309 1352 1364 1405 1470

1544 1588 1678 1712 1735 1791 1808 1913 1916 1978 1989 20652124 2146 2154 2208 2266

FPY 0112 0342 0438FRN 0409 0466 0497G2X 0189G4I 1157 1795 2507G8E 0222 0348GAF 3897 4060GAP 2162 2183GFA 1884 1901 3706 4030 4059 4083GIA 0839 0892 1635 2598GIR 0630 1973GLG 1866 1872 1882 1925 2078 2126GMI 3019 3407GOW 3256 3306 3597 3616 3798 3827 3900 3915 3933GSW 0376GWI 1077 1084 1089 1136 1147 1155 1170 1209 1277 2607 2628 2632

2813 2833 2976 3011 3128 3172 3193 3352 3358 3375 3500 35343839 3841

GWY 1564 1725 1860 1867HAY 2745 3533 3560HCC 2180HDA 0633 0756 0784 0812 0930 0993 1024 1253 1695 1721 1984 2021

2229 2238 2428 4023HRM 0535HVN 0590 0594 0601 0605 0607 0611 0617 0619 0648 0650 2255 2261

2267 2303 2480 2974 3005 3013 3022 3198 3315 3355 3600 37373862 3964 3966

I2L 0415 0443IAC 0045 0046 0047 0049 0050 0051 0056 0057 0074 0075 0080 0090

0095 0096 0308 0314 0396 0398 0416 0423 0431 0432 0451 04690486 0490 0492 0499 1668 1718 2593 2624 2629 2907 3130 31463212 3271 3288 3300 3305 3326 3340 3344 3367 3498 3551 35573573 3619 3620 3687 3752 3792 3822 3874 3918 3955 3970 40024009 4020 4029 4052 4078 4089 4096



7



OPERATOR MSNIBE 0173 0176 0207 0223 0266 0274 0323 1021 1027 1047 1059 1067

1099 1101 1119 1154 1180 1208 1229 1247 1255 1262 1288 12921318 1347 1362 1516 1530 1540 1554 1572 1655 1674 1681 16941716 1736 1793 1809 1836 2115 2220 2225 2242 2248 2264 22702311 2347 2357 2365 2381 2391 2472 2488 2563 2599 2736 27562776 2807 2843 2897 2996 3054 3078 3102 3169 3179 3209 33203377 3380 3443 3651 3744

IGO 2844 2863 2883 2911 2958 2990 3086 3159 3192 3227 3335 33573414 3453 3457 3497 3541 3618 3782 3863 3943 4008

IRA 0303 0312 0345 0530 0575 0857 2054IRM 1202ISS 0737 0749 1048 1125 1198 1283 1305 1715 1723 1823 1896 1937

1983 2001 2102IWD 2011 3758 3868 3889IZM 1730 2118 2404 2414 2452JAV 0029JBU 1123 1156 1173 1235 1240 1257 1270 1280 1302 1327 1398 1446

1452 1506 1528 1546 1557 1610 1650 1705 1739 1784 1785 18491861 1898 1904 1915 1917 1927 1948 2006 2020 2031 2042 20632075 2099 2125 2132 2136 2149 2150 2159 2160 2177 2201 22152231 2246 2259 2280 2284 2286 2307 2314 2336 2352 2368 23842386 2415 2447 2449 2461 2489 2491 2504 2520 2535 2577 25802640 2647 2671 2710 2725 2755 2781 2802 2814 2832 2848 28712880 2900 2945 2970 2977 2992 3029 3039 3072 3091 3119 31503190 3228 3263 3287 3348 3381 3416 3451 3479 3488 3517 35543572 3622 3659 3707 3724 3760 3800 3811

JET 0204 0215 0371 0421 0542 0647 0660 0816 0877 2698 2723 2797JKK 1183 1276 1333 1349 1366 1383 1407 1497 1631 1682 1749 1843

1862 1914 1933 1946 1979 1998 2027 2168 2210 2223 2479 2589JSA 2156 2164 2316 2356 2395 2401 2423 2453 2457 2604JST 1195 1408 2169 2185 2197 2292 2299 2322 2329 2338 2455 2475

2515 2526 2537 2573 2587 2600 2608 2642 2651 2703 2717 27662787 3474 3495 3547 3668 3717 3743 3783 3899 3916 3917 3948

JZR 2569 2792 2822 3919 3939KAC 0181 0182 0195 2046 3957KFR 2366 2376 2413 2443 2496 2502 2522 2531 2576 2621 2634 2645

2650 2664 2670 2676 2731 2747 2753 2817 2856 2874 2916 29192922 2927 2933 3012 3034 3089 3105 3120 3270 3302 3322

KGL 0668 0787 2029 2077KHO 0354 0361 0362 0405KIL 2214 2224 2249KKK 0604 0614 0675 0761 0968 0974 1124 1438 1503 1878 1950 1953KMF 0480KNE 1886 2123 3238 3361 3396 3425 3475 3530 3787 3817 3894KZR 1042 1204 2016 2128 2828 2987 3141 3484 3519 3614



7



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

1877 1903 2089 2096 2295 2304 2321 2572 2585 2845 2858 28642872 2886 2887 2892 2894 3264 3280 3319 3330 3371 3390 34383469 3509 3535 3556 3585 3602 3606 3635 3642 3663 3671 37703772 3779

LBT 0301 0400 0793 0937 0970 0995 1121 1175 1597 1744 3480LBY 0558 0561 1098LFO 0659LFX 3589 3818LIT 0636 0641 0646 0651 0654 0794 1016 1172LJB 3985LLM 1054LLP 1411LMJ 1868LMU 0666 0932 0943LZB 2540 2596 3028 3309 3564 3780M2I 1017MAC 2166 3809 3833MAU 1592 1936MDL 0391MEA 1956 1967 1977 2055 3736 3804 3837MHS 1300 1353MJN 3723MLD 0249 0622 0741MLM 2592 3363MLR 0977 3106MMA 0113 0114 0295 0316MON 0379 0389 0392 0864 0983 1015 1045 1081 1153 1207 1370 1428

1433 1707 1763 1794 1941 2105 2234 3546 3575MSC 2937 2966 3282 3323MSR 0165 0166 0178 0194 0198 0322 0351 0366 0680 0687 0715 0725

2070 2073 2079 2088 2094MXA 0252 0259 0260 0261 0275 0276 0291 0292 0296 0320 0321 0347

0353 0357 0369 0373 0447 1429NIA 3183 3219NKS 2433 2470 2473 2476 2485 2490 2560 2567 2590 2603 2622 2673

2679 2704 2711 2893 2898 2929 2942 2963 2978 2983 3007 30173026 3165 3393 3395

NLY 2529 2668 2749 2867 2902 3504 3830NMA 1697 1732NMB 3346 3586NVD 0299 0375 0419NVR 2211 2216 2410NWS 1219OAI 1454OHY 0364 0385 0455 0471 0496 0640 0663 0676 0792 0835 0916 0954

0963 1004 1421 1482 1509 2571 2688



7



OPERATOR MSNONE 3001 3030 3062 3214 3216ORF 2566OZW 0429PAL 0706 0745 2878 2925 2954 3087 3107 3108 3187 3205 3273 3310

3455 3553 3579 3652 3731PIC 0990PTR 0459 0537PVJ 3542QAF 0927 1335 3994QTR 1487 1566 1648 1656 1773 1895 1928 1957 2097 2107 2121 2138

2161 2288 2341 3071 3274 3369 3397 3636 3669R1T 1908RAM 2064 2076 2726 3070RBA 2023 2032 2135 2139RBG 2764 3152RFJ 0814RJA 2649 2692 2730 2793 2953 3428 3458 3522 3685 3803 3832RKM 2158 3907RNV 0229 0913 3834ROT 2931 2955 3220 3225RYW 0569RZO 0795 2390 2425 3891SAA 2268 2281 2308 2326 2355 2375 2379 2418 2438 2469 2501SAS 1587 1619 1642 1675 1798 1807 1817 1848 2850 2888 3231 3292SBI 1071 1078 1090 1091 1126 1129 1131 1149 1164 1167 1819 1870

2028 2279 2369 2373 2464 2474 2618 2623 2641 3446 3473 34903494 3866 3880 4032

SBN 0428SDM 0427 0525 0649 1130 1488 1560 1578 1657 1743 1761 1767 1851

1863 1876 1890SFJ 2620 2658 2695 3025SFW 0671 0994SGG 0799 0879 1390SHJ 0910SHY 0138 0148 0811 1194SKU 0179 0406 1400 1523SLK 0899 0969 1228 1422 1561 1698 2058 2252 2517 2568 2775 3104

3570 3821SND 1999SNX 0289SOL 0302STU 0420 0436 0446SUD 3040SVA 4015 4057 4081 4090 4092SVR 0140 0157 0203 0220 0735 0775 0815 0841 0991 1012 1063 1152

1199 1484 1720 1751 1777 1905 2117 2175 2187 2327



7



OPERATOR MSNSVW 2921 3100 3133 3856SWM 0476SWR 0520 0522 0541 0545 0553 0559 0562 0574 0577 0578 0585 0596

0603 0612 0621 0635 0643 0664 0673 0681 0701 0703 0713 07270734 0782 0987 1018 1144 1762 1951 2024 2134

SYR 0886 0918 1032 1076 1085 1117TAE 0657 0934 2084 2659TAI 1066 1113 1334 1598 1624 1625 1934 1952 2282 2301 2339 2434

2444 2553 2610 2687 2791 2862 2917 3042 3057 3103 3113 32483276 3378 3418 3510 3538 3577 3581 3869

TAK 3171 3331TAM 0250 0334 0335 0440 0758 0976 1010 1092 1096 1103 1139 1143

1158 1215 1246 1251 1339 1368 1376 1459 1486 1518 1575 15801591 1593 1595 1608 1613 1628 1652 1663 1672 1692 1703 17171757 1771 1775 1801 1802 1804 1818 1825 1826 1827 1831 18321835 1837 1855 1857 1888 1891 2014 2044 2372 2393 2417 24452467 2513 2602 2661 2734 2737 2783 2784 2838 2859 2896 29042924 3002 3032 3035 3047 3058 3111 3156 3180 3211 3222 32293240 3266 3278 3284 3294 3313 3325 3391 3540 3565 3588 35943595 3630 3658 3662 3710 3727 3733 3750 3761 3816 3908 39724000

TAP 0629 0750 0755 0763 0790 0821 0837 0870 0906 0917 0933 09450960 0979 0982 1034 1100 1106 1120 1127 1165 1181 1206 12311307 1399 1667 1713 1756 1765 1799 1816 2178 3769 3883 40214095

TAR 0119 0123 0124 0205 0370 0390 0402 0511 0869 0880 0958 09751187 1479 1700 3096

TBJ 1485TCW 0425 0453 0653 1306 1787 1929 1975TCX 0424 0677 0716 1238 1250 1942 1961 1965 2003 2060 2114TGW 2195 2331 2340 2724 2728 3757 3801THY 0806 0810 1002 1233 1856 1909 1996 2609 2626 2631 2655 2738

2739 2823 2868 2928 2934 2941 2984 2999 3010 3015 3126 31853207 3208 3239 3257 3259 3283 3303 3308 3341 3350 3382 34053429 3525 3539 3558 3567 3603 3637 3654 3673 3688 3718 37193738 3896 3931 3949

TNA 0538 0555 0606 0731 0746 0791 0822 2914TOM 0781 0852 1320 1571 1605 1637TWJ 2550



7



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

0470 0472 0475 0479 0483 0485 0487 0489 0500 0503 0504 05060508 0510 0512 0523 0539 0568 0571 0587 0589 0592 0613 06380655 0678 0683 0686 0690 0702 0748 0751 0759 0780 0783 07880798 0804 0820 0824 0825 0826 0834 0836 0842 0843 0847 08500851 0858 0862 0865 0867 0871 0873 0882 0893 0898 0944 09480952 0955 0965 0980 0989 1001 1022 1031 1104 1105 1128 11461163 1192 1211 1243 1248 1266 1272 1282 1290 1291 1321 13411343 1359 1363 1401 1409 1420 1426 1427 1432 1435 1460 14691474 1475 1477 1495 1507 1508 1514 1522 1533 1538 1545 15551559 1569 1573 1581 1584 1585 1586 1600 1609 1617 1620 16271647 1649 1653 1664 1669 1671 1680 1688 1702 1728 1731 17371741 1755 1821 1840 1842 1845 1847 1865

UDC 0085 0230 0235 0579 0645 0662 0733 0747 0760 1869UEA 0946 0949 1263 2654 2696 2762 2774 2820 2835 3024UKN 3260UNA 3333 3886USA 0052 0053 0054 0055 0064 0065 0066 0067 0076 0077 0081 0082

0099 0317 0448 0565 0584 0762 0770 0803 0844 0856 0861 08630866 0868 0885 0889 0890 0896 0904 0922 0924 0929 0931 09530972 0997 1003 1019 1033 1038 1040 1043 1046 1049 1050 10511052 1055 1056 1061 1064 1065 1069 1075 1079 1083 1088 10951097 1109 1110 1111 1112 1114 1116 1122 1134 1135 1141 11481166 1178 1182 1196 1203 1205 1223 1224 1234 1245 1254 12641265 1268 1269 1274 1275 1281 1284 1287 1289 1294 1297 12981301 1310 1311 1313 1314 1315 1317 1319 1323 1326 1328 13311340 1342 1348 1350 1354 1358 1360 1369 1371 1373 1375 13781382 1389 1391 1393 1395 1397 1403 1406 1410 1412 1417 14191425 1431 1436 1442 1447 1455 1462 1463 1465 1472 1481 14901492 1496 1499 1517 1519 1521 1525 1527 1531 1534 1536 15391547 1552 1563 1565 1576 1621 1643 1644 1651 1666 1701 17041710 1724 1764 1792 1844 1935 2193 2302 2312 2405 2422 24302458 2482 2570 2595 2613 2615 2630 2669 2690 3584 3629 36333712 3740 3796 3858 3879 3881 3924 3928 3944 3960 3977 39893993 4025 4041 4050 4082 4086

VIM 2732 2804 3125VJC 3739 3791 4049VKG 1881 1887 1889 1921 1932 1954 1960 1972VKH 0393 0414VLE 1226VLG 0143 0146 0158 0199 0224 0240 0241 0264 0356 0992 1221 1396

1413 1430 1461 1550 2104 2143 2207 2388 2407 2678 2761 27852794 2798 2889 2962 2988 3083 3095 3109 3145 3151 3174 32033237 3293 3321 3376 3400 3529

VLK 0422 0528 0714 0730 1200 1213 1379VNV 0543 0661 1918 1969 1993 2157VOI 1140 1159 2204 2296 2657 2666 2771 2780 2979 2997 3045 3069

3077 3175 3252 3253 3279 3317 3450 3463 3491 3524 3543 35903624 3672 3705



7



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

3101 3135 3155 3181 3204 3230 3324 3347 3349 3359 3398 34173445 3460 3465 3503 3656 3670 3684 3686

WAU 3531 3741WGT 1212WHT 0726 1256 2440 2675WRC 2462 2682WTJ 0548WZZ 1834 1892 1902 2752 3127 3143 3166 3177 3354 3384 3409 3430

3562 3771 3807 3877 3927 3947 3968XLF 0343YAP 0533 0566 0973



7



(4) Configuration by MSN

MSN CONFIGURATION0029 0043 0044 0045 0046 0047 0049 0050 0051 0056 00570059 0061 0063 0068 0070 0071 0072 0073 0074 0075 00780080 0083 0084 0086 0090 0093 0094 0095 0096 0102 01040110 0111 0113 0114 0115 0116 0117 0122 0126 0127 01350137 0138 0139 0140 0141 0142 0144 0145 0147 0148 01490150 0151 0154 0155 0157 0159 0161 0162 0164 0165 01660167 0168 0169 0170 0172 0174 0175 0178 0179 0181 01820183 0185 0186 0187 0189 0190 0191 0194 0195 0196 01980200 0201 0202 0203 0204 0209 0210 0211 0212 0214 02150216 0217 0218 0220 0221 0222 0227 0228 0229 0231 02320233 0234 0235 0236 0237 0239 0242 0244 0245 0248 02490250 0253 0254 0255 0256 0265 0267 0268 0269 0270 02770278 0279 0283 0284 0285 0286 0287 0289 0290 0294 02950299 0300 0301 0309 0310 0311 0316 0317 0324 0325 03280330 0331 0333 0334 0335 0337 0341 0342 0343 0345 03460348 0350 0351 0352 0354 0359 0362 0364 0365 0366 03750377 0378 0379 0382 0383 0384 0385 0386 0389 0391 03920393 0394 0395 0396 0398 0401 0403 0404 0406 0409 04120413 0415 0416 0419 0421 0423 0427 0429 0431 0432 04340438 0440 0443 0445 0446 0449 0451 0455 0458 0459 04660468 0469 0471 0473 0474 0476 0477 0482 0484 0486 04880490 0491 0492 0493 0494 0495 0497 0498 0499 0501 05020503 0504 0505 0506 0507 0508 0509 0510 0511 0512 05130514 0515 0516 0517 0518 0519 0520 0521 0522 0523 05240525 0526 0527 0528 0529 0530 0531 0532 0533 0534 05350537 0538 0539 0540 0541 0542 0543 0544 0545 0546 05480549 0550 0551 0552 0553 0554 0555 0556 0557 0558 05590560 0561 0562 0563 0564 0565 0566 0567 0568 0569 05700571 0572 0573 0574 0575 0576 0577 0578 0579 0580 05810582 0583 0584 0585 0586 0587 0588 0589 0590 0591 05920593 0594 0595 0596 0597 0598 0599 0600 0601 0603 06040605 0606 0607 0608 0609 0610 0611 0612 0613 0614 06160617 0618 0619 0620 0621 0622 0623 0624 0625 0626 06270628 0629 0630 0631 0633 0634 0635 0636 0637 0638 06390640 0641 0642 0643 0644 0645 0646 0647 0648 0649 06500651 0652 0653 0654 0655 0656 0657 0658 0659 0660 06610662 0663 0664 0665 0666 0667 0668 0669 0670 0671 06720673 0674 0675 0676 0677 0678 0679 0680 0681 0682 06830684 0685 0686 0687 0688 0689 0690 0691 0692 0693 06940695 0696 0697 0698 0699 0700 0701 0702 0703 0704 07050706 0707 0709 0710 0711 0712 0713 0714 0715 0716 07170718 0719 0720 0721 0722 0723 0724 0725 0726 0727 07280729 0730 0731 0732 0733 0734 0735 0736 0737 0738 07390740 0741 0742 0743 0744 0745 0746 0747 0748 0749 07500751 0752 0754 0755 0756 0757 0758 0759 0760 0761 07620763 0764 0765 0766 0767 0768 0769 0770 0771 0772 07730774 0775 0776 0777 0778 0779 0780 0781 0782 0783 07840785 0786 0787 0788 0790 0791 0792 0793 0794 0795 07960797 0798 0799 0800 0801 0802 0803 0804 0805 0806 0807

003



7



MSN CONFIGURATION0808 0809 0810 0811 0812 0813 0814 0815 0816 0817 08180819 0820 0821 0822 0823 0824 0825 0826 0827 0828 08290830 0831 0832 0833 0834 0835 0836 0837 0838 0839 08400841 0842 0843 0844 0845 0846 0847 0848 0849 0850 08510852 0853 0854 0855 0856 0857 0858 0859 0860 0861 08620863 0864 0865 0866 0867 0868 0869 0870 0871 0872 08730874 0875 0876 0877 0878 0879 0880 0881 0882 0883 08840885 0886 0887 0888 0889 0890 0891 0892 0893 0894 08950896 0897 0898 0899 0900 0901 0902 0903 0904 0905 09060907 0908 0909 0910 0911 0912 0913 0914 0915 0916 09170918 0919 0920 0921 0922 0923 0924 0925 0926 0927 09280929 0930 0931 0932 0933 0934 0935 0936 0937 0938 09390940 0941 0942 0943 0944 0945 0946 0947 0948 0949 09500951 0952 0953 0954 0955 0957 0958 0959 0960 0961 09620963 0964 0965 0966 0967 0968 0969 0970 0971 0972 09730974 0975 0976 0977 0978 0979 0980 0981 0982 0983 09840985 0986 0987 0988 0989 0990 0991 0992 0993 0994 09950996 0997 0998 0999 1000 1001 1002 1003 1004 1005 10061007 1008 1009 1010 1011 1012 1013 1014 1015 1016 10171018 1019 1020 1021 1022 1023 1024 1025 1026 1027 10281029 1030 1031 1032 1033 1034 1035 1036 1037 1038 10391040 1041 1042 1043 1045 1046 1047 1048 1049 1050 10511052 1053 1054 1055 1056 1057 1058 1059 1060 1061 10621063 1064 1065 1066 1067 1068 1069 1070 1071 1072 10731074 1075 1076 1077 1078 1079 1080 1081 1082 1083 10841085 1086 1087 1088 1089 1090 1091 1092 1093 1094 10951096 1097 1098 1099 1100 1101 1102 1103 1104 1105 11061107 1108 1109 1110 1111 1112 1113 1114 1115 1116 11171118 1119 1120 1121 1122 1123 1124 1125 1126 1127 11281129 1130 1131 1132 1133 1134 1135 1136 1137 1138 11391140 1141 1142 1143 1144 1145 1146 1147 1148 1149 11501151 1152 1153 1154 1155 1156 1157 1158 1159 1160 11611162 1163 1164 1165 1166 1167 1168 1169 1170 1171 11721173 1174 1175 1176 1177 1178 1179 1180 1181 1182 11831184 1185 1187 1188 1189 1190 1191 1192 1193 1194 11951196 1197 1198 1199 1200 1201 1202 1203 1204 1205 12061207 1208 1209 1210 1211 1212 1213 1214 1215 1216 12171219 1220 1221 1222 1223 1224 1225 1226 1227 1228 12291230 1231 1232 1233 1234 1235 1236 1237 1238 1239 12401241 1242 1243 1244 1245 1246 1247 1248 1249 1250 12511252 1253 1254 1255 1256 1257 1258 1259 1260 1261 12621263 1264 1265 1266 1267 1268 1269 1270 1271 1272 12731274 1275 1276 1277 1279 1280 1281 1282 1283 1284 12851286 1287 1288 1289 1290 1291 1292 1293 1294 1295 12961297 1298 1299 1300 1301 1302 1303 1304 1305 1306 13071308 1309 1310 1311 1312 1313 1314 1315 1316 1317 13181319 1320 1321 1322 1323 1324 1325 1326 1327 1328 13291330 1331 1332 1333 1334 1335 1336 1337 1338 1339 13401341 1342 1343 1344 1345 1346 1347 1348 1349 1350 13511352 1353 1354 1355 1356 1357 1358 1359 1360 1361 13621363 1364 1365 1366 1367 1368 1369 1370 1371 1372 1373

003



7




003



7



MSN CONFIGURATION3636 3637 3638 3639 3640 3641 3642 3643 3644 3645 36463647 3648 3649 3650 3651 3652 3653 3654 3655 3656 36573658 3659 3660 3661 3662 3663 3664 3665 3666 3667 36683669 3670 3671 3672 3673 3674 3675 3676 3677 3678 36793680 3681 3682 3683 3684 3685 3686 3687 3688 3689 36903691 3692 3693 3694 3695 3696 3697 3698 3699 3700 37013702 3703 3704 3705 3706 3707 3708 3709 3710 3711 37123713 3714 3715 3716 3717 3718 3719 3720 3721 3722 37233724 3725 3726 3727 3728 3729 3730 3731 3732 3733 37343735 3736 3737 3738 3739 3740 3741 3742 3743 3744 37453746 3747 3748 3749 3750 3751 3752 3753 3754 3755 37563757 3758 3759 3760 3761 3762 3763 3764 3765 3766 37673768 3769 3770 3771 3772 3773 3774 3775 3776 3777 37783779 3780 3781 3782 3783 3784 3785 3786 3787 3788 37893790 3791 3792 3793 3794 3795 3796 3797 3798 3799 38003801 3802 3803 3804 3805 3806 3807 3808 3809 3810 38113812 3813 3814 3815 3816 3817 3818 3819 3820 3821 38223823 3824 3825 3826 3827 3828 3829 3830 3831 3832 38333834 3835 3836 3837 3838 3839 3840 3841 3842 3843 38443845 3846 3847 3848 3849 3850 3851 3852 3853 3854 38553856 3857 3858 3859 3860 3861 3862 3863 3864 3865 38663867 3868 3869 3870 3871 3872 3873 3874 3875 3876 38773878 3879 3880 3881 3882 3883 3884 3885 3886 3887 38883889 3890 3891 3892 3893 3894 3895 3896 3897 3898 38993900 3901 3902 3903 3904 3905 3906 3907 3908 3909 39103911 3912 3913 3914 3915 3916 3917 3918 3919 3920 39213922 3923 3924 3925 3926 3927 3928 3929 3930 3931 39323933 3934 3935 3936 3937 3938 3939 3940 3941 3942 39433944 3945 3946 3947 3948 3949 3950 3951 3952 3953 39543955 3956 3957 3958 3959 3960 3961 3962 3963 3964 39653966 3967 3968 3969 3970 3971 3972 3973 3974 3975 39763977 3978 3979 3980 3981 3982 3983 3984 3985 3986 39873988 3989 3990 3991 3992 3993 3994 3995 3996 3997 39983999 4000 4001 4002 4003 4004 4005 4006 4007 4008 40094010 4011 4012 4013 4014 4015 4016 4017 4018 4019 40204021 4022 4023 4024 4025 4026 4027 4028 4029 4030 40314032 4033 4034 4035 4036 4037 4038 4039 4040 4041 40424043 4044 4045 4046 4047 4048 4049 4050 4051 4052 40534054 4055 4056 4057 4058 4059 4060 4061 4062 4063 40644065 4066 4067 4068 4069 4070 4071 4072 4073 4074 40754076 4077 4078 4079 4080 4081 4082 4083 4084 4085 40864087 4088 4089 4090 4091 4092 4093 4094 4095 4096 40974098 4099

003

0039 0042 0052 0053 0054 0055 0064 0065 0066 0067 00690076 0077 0081 0082 0099 0103 0109 0112 0120 0230 02520259 0260 0261 0275 0276 0293 0296 0308 0314 0320 03210322 0332 0347 0353 0357 0361 0369 0371 0373 0405

001 002 003



7



MSN CONFIGURATION0085 0087 0088 0118 0119 0121 0123 0124 0125 0136 01430146 0152 0153 0158 0160 0171 0173 0176 0192 0197 01990205 0206 0207 0208 0213 0223 0224 0240 0241 0258 02620263 0264 0266 0272 0273 0274 0281 0282 0291 0292 02970298 0302 0303 0306 0307 0312 0318 0319 0323 0329 03390340 0349 0355 0356 0358 0360 0367 0368 0370 0372 03760380 0381 0387 0388 0390 0399 0400 0402 0407 0408 04100414 0417 0418 0420 0422 0424 0425 0426 0428 0430 04350436 0439 0441 0442 0444 0447 0448 0450 0452 0453 04540456 0457 0460 0461 0462 0463 0464 0465 0470 0472 04750479 0480 0483 0485 0487 0489 0496 0500

002 003

(5) Configuration definition

**CONF 001Config. 001 is valid for all aircraft A320-200 series that are Pre SB A320 57-1050 or PreModification 23012J0856 or 21999P2000 and Pre SB A320 57-1079 or Pre Modification24418J1277.NOTE: Aircraft that have embodied SB A320 57-1050 are to be considered as Config.002.NOTE: Aircraft that have embodied SB A320 57-1079 are to be considered as Config.003.

**CONF 002Config. 02 is valid for all aircraft A320-200 series that are Post SB A320 57-1050 or PostModification 23012J0856 or 21999P2000 and Pre SB A320 57-1079 or Pre Modification24418J1277.NOTE: Aircraft that have embodied SB A320 57-1079 are to be considered as Config.003.

**CONF 003Config. 003 is valid for all aircraft A320-200 series and A321-100 and A321-200 seriesthat are Post SB A320 57-1079 or Post Modification 24418J1277 and for all A318 andA319 aircraft.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTESConsumable CMLB00 As required

Kit 571154B01R01 2Kit 571154B04R01 2Kit 571154B07R03 2

**CONF 002


Kit 571154B01R01 2



7



MATERIAL QTY PER A/C SEE NOTESKit 571154B05R00 2Kit 571154B07R03 2

**CONF 003


Kit 571154B01R01 2Kit 571154B06R00 2Kit 571154B07R03 2Component COMPB01 2 (1)

NOTE (1): COMPB01 is only applicable to CONF 003 aircraft that are Pre Mod. No.38026J2845.

**CONF ALL

B. CONCURRENT REQUIREMENTS

This Service Bulletin can be done at the same time as the following Service Bulletin(s):

- Service Bulletin No. A320-57-1155.

C. REASON

(1) History

Several instances of exfoliation corrosion of the wing top skin panel 2 have beenreported. The corrosion was found aft of the rear spar and the false rear spar, in front ofthe aileron and had developed from the lower surface of the panel 2.

Two possible causes have been identified as potential contributing factors for thecorrosion:

- the panel is made from aluminum alloy 7150T651, its resistance against corrosionis increased by Chromic Acid Anodizing and paint coating, however, a sampleinspection has revealed, in some instances, degrading of the paint system

- in-service aircraft may be affected by degraded sealing at the interface of the wingtop skin panel 2 and aft panels.

If left untreated, the corrosion could become exfoliation corrosion; caused when moisturecomes into contact with the exposed edges of the aluminum alloy panel.

(2) Objective/Action

This Service Bulletin details instructions to perform a (repeat) special detailed ultrasonicinspection or alternatively (as a terminating action) a detailed visual inspection (x10magnification) at fastener locations at the wing top skin panel 2 overhang upper andlower surface and at the wing top skin panel 2 overhang edge (vertical skin edge andchamfer) to detect any exfoliation corrosion.



7



(3) Advantages

Accomplishment of this Service Bulletin will establish if there are signs of corrosion ofthe wing top skin panel 2 overhang and if necessary, provide details of repairinstructions to rectify any corroded areas.

Also, the re-application of the corrosion protection scheme and the restoration of thesealant will reduce possible corrosion occurrences in the area.

This Service Bulletin has been validated on A320 aircraft MSN 1023.

This Service Bulletin has been accomplished at Revision No. 01 on aircraft MSN 1023 tovalidate its content.

A booklet including photographs taken during the validation of this Service Bulletin isavailable on AirbusWorld - Maintenance and Engineering - Service Bulletin Information.

(4) Operational/Maintenance Consequences

Accomplishment of this Service Bulletin will significantly reduce the likelihood of majorrepairs and excessive aircraft downtime.

If there is previous experience of exfoliation corrosion in this area, or if the aircraft isbeing operated in an aggressive corrosive environment, AIRBUS recommends that theinspections are performed at the earliest opportunity.

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 571154-832-895-001: INSPECTION

(1) SPECIAL DETAILED ULTRASONIC INSPECTION OF THE WING TOP SKINPANEL 2 OVERHANG BETWEEN RIB 22 AND RIB 27

(2) DETAILED VISUAL INSPECTION OF THE WING TOP SKIN PANEL 2 EDGE ANDUPPER AND LOWER SURFACE AT RIB 22 - TRAILING EDGE FALSEWORK

(3) DETAILED VISUAL INSPECTION OF THE WING TOP SKIN PANEL 2 EDGE ANDCHAMFER AND UPPER AND LOWER SURFACE BETWEEN RIB 22 AND RIB 24


(5) REPAIR/REPLACEMENT OF SEALANT

**CONF 002





7







**CONF 003







**CONF ALL

E. COMPLIANCE

(1) Classification

RECOMMENDED: Service Bulletin recommended to be accomplished to preventsignificant operational disruptions.

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin is recommended within 40 months from releaseof this Service Bulletin or within 40 months from entry into service, whatever comeslater.

A repetitive inspection is recommended within 40 months of initial ultrasonic inspection ifthe terminating inspection has not been performed.

F. APPROVAL

The technical content of this document is approved under the authority of DesignOrganization Approval No. EASA.21J.031.



7



If an aircraft listed in the effectivity has a modification or repair embodied that is not ofAIRBUS origin, and which affects the content of this Service Bulletin, the operator isresponsible for obtaining approval by its airworthiness authority for any adaptation necessarybefore incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost todo 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 notinclude the time to prepare, plan or inspect the work. Manufacture and procurement of partsand tools, drying times for paints, sealants, etc., and general administration work are also notincluded.

**CONF 001

Task 571154-832-895-001: INSPECTIONGet Access 2.00On Aircraft

SPECIAL DETAILED ULTRASONIC INSPECTION OFTHE WING TOP SKIN PANEL 2 OVERHANGBETWEEN RIB 22 AND RIB 27

2.00

DETAILED VISUAL INSPECTION OF THE WING TOPSKIN PANEL 2 EDGE AND UPPER AND LOWERSURFACE AT RIB 22 - TRAILING EDGEFALSEWORK

12.00

DETAILED VISUAL INSPECTION OF THE WING TOPSKIN PANEL 2 EDGE AND CHAMFER AND UPPERAND LOWER SURFACE BETWEEN RIB 22 AND RIB24

8.00


23.00

REPAIR/REPLACEMENT OF SEALANT 1.00Tests 2.00Close-Up 2.00

TOTAL MANHOURS 52.00ELAPSED TIME (HOURS) 29.50

NOTE: These manhours are per wing.

**CONF 002



2.00



7



Task 571154-832-895-001: INSPECTIONDETAILED VISUAL INSPECTION OF THE WING TOPSKIN PANEL 2 EDGE AND UPPER AND LOWERSURFACE AT RIB 22 - TRAILING EDGEFALSEWORK

12.00


8.00


23.00




**CONF 003



2.00

DETAILED VISUAL INSPECTION OF THE WING TOPSKIN PANEL 2 EDGE AND UPPER AND LOWERSURFACE AT RIB 22 - TRAILING EDGEFALSEWORK

12.00


8.00


23.00






7



**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 20-23-11 27-14-00 27-14-5127-50-00 29-00-00 51-76-0057-51-37

Consumable Material List (CML)Drawing R572-58616Elec. Std. Practices Manual (ESPM) 20-55-00Non Destructive Test Manual (NTM) 51-90-00 57-29-07Process and Material Specification (PMS) Process and Material Specification

(PMS) 01-02-42Process and Material Specification(PMS) 01-05-70

Standards Manual (SM)Structural Repair Manual (SRM) 51-21-00 51-21-11 51-22-00

51-23-11 51-23-12 51-24-0051-42-11 51-42-21 51-43-0051-44-00 51-44-11 51-74-0051-75-11 51-75-12 51-76-0057-21-11

**CONF 002






7




51-23-11 51-23-12 51-24-0051-42-11 51-42-21 51-43-0051-44-00 51-44-11 51-74-0051-75-11 51-75-12 51-76-0057-21-11

**CONF 003





51-23-11 51-23-12 51-24-0051-42-11 51-42-21 51-43-0051-44-00 51-44-11 51-74-0051-75-11 51-75-12 51-76-0051-76-11 57-21-11

**CONF ALL

K. PUBLICATION AFFECTED

Impact on scheduled maintenance : refer to Maintenance Planning Document (MPD) No.572125-01-1

Non Destructive Test Manual (NTM) 57-29-07

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None



7



2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

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

Kit 571154B01R01Kit 571154B04R01Kit 571154B05R00Kit 571154B06R00Kit 571154B07R03Component COMPB01

Customers with aircraft shown in theeffectivity of this Service Bulletin should senda purchase order to AIRBUS. Quote thenumber of this Service Bulletin. The addressis:

AIRBUS Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 Hamburg

Germany

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

For ordering by E-mail: [email protected]

For ordering by fax: +49 40 50 76 25 90 forSB kit orders

(2) Price and Availability

Kit 571154B01R01Cost 992.00 USDAvailability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchaseorder. If you require Kits before this time, please include a retrofit planning schedule withyour order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditionsat the issue date of the Service Bulletin.

Kit 571154B04R01Cost 1,490.00 USD

Availability 90 calendar days from receipt of order




7




Kit 571154B05R00Cost 1,420.00 USD




Kit 571154B06R00Cost 776.00 USDAvailability 90 calendar days from receipt of order



Kit 571154B07R03Cost 1,840.00 USD




B. INDUSTRY SUPPORT INFORMATION

AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

C. LIST OF COMPONENTS

Kit 571154B01R01

ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEENOTES

20 EN6114K3X-5 7 Bolt (20) ASNA2026HK3-5

22 NSA5414-48-18 1 Rivet (22) NSA5414-48-18

23 MS20426AD5-12 25 Rivet (23) MS20426AD5-12

24 NSA5474-3K7 8 Nut (24) NSA5474-3K7



7



NOTE: If you find part numbers of hardware components in the related kit(s) whichyou cannot identify in the LIST OF COMPONENTS of this Service Bulletin,refer to Standards Manual (SM). The SM will give you the correct part numberto part number relationship.

Kit 571154B04R01


23 MS20426AD5-12 20 Rivet (23) MS20426AD5-12

24 NSA5474-3K7 2 Nut (24) NSA5474-3K7

35 ASNA0077D505 93 Rivet (35) ASNA0077D505








Kit 571154B05R00


23 MS20426AD5-12 20 Rivet (23) MS20426AD5-12

24 NSA5474-3K7 14 Nut (24) NSA5474-3K7









Kit 571154B06R00


23 MS20426AD5-12 20 Rivet (23) MS20426AD5-12



7




24 NSA5474-3K7 123 Nut (24) NSA5474-3K7





Kit 571154B07R03


20 EN6114K3X-5 6 Bolt (30) ASNA2026VBV3-5

21 EN6114K3X-6 7 Bolt (21) ASNA2026VBV3-6

23 MS20426AD5-12 4 Rivet (23) MS20426AD5-12

24 NSA5474-3K7 16 Nut (24) NSA5474-3K7

50 ASNA0079-512ALC 69 Rivet (50) ASNA0079-512A

52 MS20426AD6-12 2 Rivet (52) MS20426AD6-12



56 MS20426AD4-12 25 Rivet (56) MS20426AD4-12


D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLB00

ITEM DESCRIPTION REFERENCE TO CMLMAT. No.

QTY PER A/C SEENOTES

Grease 04-015 As required

Anti-static Paint (Low Resistivity) 07-005 As required

Masking Tape 08-074 As required

Corrosion Inhibiting Sealant - FilletConsistency

09-016 As required

Adhesion Promoter ForPolysulphide Sealant

09-028 As required

Solvent General Purpose 11-026 As required



7



ITEM DESCRIPTION REFERENCE TO CMLMAT. No.


Chlorinated Phenol Stripper (WashPrimer System)

12-010 As required

Chemical Conversion CoatingYellow Aluminum

13-002 As required

Anti-Corrosion Primer(Polyurethane)

16-001 As required

Polyurethane Top Coat Gray (forInternal Applic.)

16-002 As required

Wash Primer 16-020 As required

Lint-Free Cotton Cloth 19-003 As required

Lockwire Stainless Steel Annealed0.8mm Dia

19-010 As required

Scotch Brite Pads 19-011 As required

(2) Components

NOTE: COMPB01 is only applicable to CONF 003 aircraft that are Pre Mod. No.38026J2845.

Component COMPB01


20 EN6114K3X-5 1 Bolt (20) ASNA2026HK3-5

24 NSA5474-3K7 1 Nut (24) NSA5474-3K7

NOTE: If you find part numbers of hardware components in the related kit(s)which you cannot identify in the LIST OF COMPONENTS of this ServiceBulletin, refer to Standards Manual (SM). The SM will give you thecorrect part number to part number relationship.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

None



7



(3) Special Tools

Refer to NTM 57-29-07 for the NDT equipment.

For Special Tool refer to APPENDIX 1 - SPECIAL TOOLING for local manufacture.



7



3. ACCOMPLISHMENT INSTRUCTIONS

Task 571154-832-895-001 - INSPECTION

Task Associated Data

**CONF 001

Zone575 675

Modified FIN33CE1 33CE2 33CE3 33CE4

AccessPanel 575AT 575HB 575JB 575KB 575LB 575MB 675AT 675HB

675JB 675KB 675LB 675MBManpower


**CONF 002

Zone575 675





**CONF 003

Zone575 675







7



**CONF ALL

A. GENERAL

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THECAUTIONS INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEPELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLYAND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCEWORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICALWIRING, COMPONENTS AND THE WORK AREA AS CLEAN ASPOSSIBLE. TO DO THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC;AS NECESSARY ON WIRING AND COMPONENTS

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL ANDOTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OFCONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRINGINSTALLATION.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.

**CONF 001

(1) Subtask 571154-839-401-001 - ADMINISTRATIVE

Manpower Resources

Skills UTILITY

(a) Write in the applicable aircraft records that you have done all the work given in thisService Bulletin.

**CONF 002


Manpower Resources

Skills UTILITY


**CONF 003


Manpower Resources

Skills UTILITY



7




**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 571154-910-401-001 - STANDARD PRACTICES

Manpower Resources

Skills AIRFRAME

Material necessary to do the job

Consumable CMLB00ITEM DESCRIPTION REFERENCE TO

CML MAT. No.QTY PER A/C SEE

NOTESAnti-static Paint (LowResistivity)

07-005 As required



ReferencesAircraft Maintenance Manual (AMM) Task 20-23-11-911-001

Task 29-00-00-910-004Consumable Material List (CML)

Drawing R572-58616

Process and Material Specification(PMS)

Process and Material Specification (PMS)01-02-42Process and Material Specification (PMS)01-05-70

Structural Repair Manual (SRM) 51-21-0051-22-0051-23-1151-23-1251-42-1151-42-2151-43-0051-44-1151-74-0051-76-0057-21-11

(a) For the specification of the material numbers (Mat. No.) (Refer to ConsumableMaterial List (CML)).

(b) Remove/install the fasteners in metallic structure (Refer to SRM 51-42-11).

(c) Remove/install the fasteners in composite structure (Refer to SRM 51-42-21).



7



(d) When a fastener hole is damaged and outside the tolerances for the originalfastener nominal diameter, an oversize fastener must be installed (Refer to SRM51-44-11).

(e) For installation of close tolerance (interference fit) bolts (Refer to Process andMaterial Specification (PMS) 01-05-70).

(f) For installation of hydraulic tubes (Refer to AMM Task 20-23-11-911-001).

(g) For the removal and installation procedures for hydraulic systems (Refer to AMMTask 29-00-00-910-004).

(h) For repair limits (Refer to SRM 57-21-11).

(i) For types of corrosion (Refer to SRM 51-22-00).

(j) For initial rework/repair procedures and damage reporting of corrosion findings(Refer to Drawing R572-58616).

(k) For repair of corroded areas (Refer to SRM 51-74-00).

(l) For paint coatings (Refer to SRM 51-23-11).

(m) For sealing (Refer to SRM 51-76-00).

(n) For protective treatment (Refer to SRM 51-21-00).

(o) For fastener oversize and alternatives (Refer to SRM 51-43-00).

(p) Where dimpled washers are installed on glasscloth panels they are retained inplace by anti-static paint in a wet condition.

If the washers come loose on panel removal, use

Lint-Free CottonCloth

19-003 As required

made moist with

Solvent GeneralPurpose

11-026 As required

to clean the area and re-apply

Anti-static Paint(Low Resistivity)

07-005 As required

(Refer to SRM 51-23-12 and Process and Material Specification (PMS) 01-02-42).

(2) Subtask 571154-941-401-001 - JOB SET-UP

Work Zones and Access PanelsZone Access/Work location

575



7



675

Manpower Resources

Skills AIRFRAME


WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES INPOSITION BEFORE YOU START A TASK ON OR NEAR:

- THE FLIGHT CONTROLS

- THE FLIGHT CONTROL SURFACES

- THE LANDING GEAR AND THE RELATED DOORS

- COMPONENTS THAT MOVE.

(a) Put the safety barrier(s) in position.

(b) Fully extend the flaps (Refer to AMM Task 27-50-00-866-008).

(c) Make sure that the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER98D27803500001 is installed on the flap/slat control lever.

(d) Put a WARNING NOTICE in the cockpit to tell persons not to operate the flaps orslats.

(e) Put an ACCESS PLATFORM 4M (13 FT) in position.

**CONF 002


Manpower Resources

Skills AIRFRAME





07-005 As required




Task 29-00-00-910-004



7



ReferencesConsumable Material List (CML)

Drawing R572-58616




















7







19-003 As required

made moist with


11-026 As required



07-005 As required




575675

Manpower Resources

Skills AIRFRAME












7





**CONF 003


Manpower Resources

Skills AIRFRAME





07-005 As required




Task 29-00-00-910-004Consumable Material List (CML)

Drawing R572-58616









7


















19-003 As required

made moist with


11-026 As required



07-005 As required




575



7



675

Manpower Resources

Skills AIRFRAME












**CONF ALL

C. PROCEDURE

NOTE: Operators have two options to satisfy the inspection requirements of thisService Bulletin:

Option 1 - to perform a special detailed ultrasonic inspection (REPEATinspection) do

**CONF 001 SUBTASK 571154-270-401 001 SPECIAL DETAILEDULTRASONIC INSPECTION OF THE WING TOP SKIN PANEL 2OVERHANG BETWEEN RIB 22 AND RIB 27

**CONF 002 SUBTASK 571154-270-401 001 SPECIAL DETAILEDULTRASONIC INSPECTION OF THE WING TOP SKIN PANEL 2OVERHANG BETWEEN RIB 22 AND RIB 27

**CONF 003 SUBTASK 571154-270-401 001 SPECIAL DETAILEDULTRASONIC INSPECTION OF THE WING TOP SKIN PANEL 2



7



OVERHANG BETWEEN RIB 22 AND RIB 27

Option 2 - to perform detailed visual inspections (x10 magnification)(TERMINATING inspection) do:

**CONF 001 SUBTASK 571154-220-403 001 DETAILED VISUALINSPECTION OF THE WING TOP SKIN PANEL 2 EDGE AND UPPER ANDLOWER SURFACE AT RIB 22 - TRAILING EDGE FALSEWORK



and

**CONF 001 SUBTASK 571154-220-401 005 DETAILED VISUALINSPECTION OF THE WING TOP SKIN PANEL 2 EDGE AND CHAMFERAND UPPER AND LOWER SURFACE BETWEEN RIB 22 AND RIB 24



and




NOTE: Operators also have an option to do a Special Detailed Inspection (as perNTM 57-29-07 and Figure A-UAAAA - Sheet 01) to provide an advanced



7



notification of significant hidden corrosion areas.

**CONF 001

(1) Subtask 571154-270-401-001 - SPECIAL DETAILED ULTRASONIC INSPECTION OFTHE WING TOP SKIN PANEL 2 OVERHANG BETWEEN RIB 22 AND RIB 27


575675

Manpower Resources

Manhours 2.00Minimum number of person 2

Subtask elapsed time 1.00

Skills NON DESTRUCTIVETESTING

ReferencesNon Destructive Test Manual (NTM) 57-29-07

Fig. A-UAAAAINSPECTION FLOW CHART

Sheet 01

Fig. A-UBAAASEALANT AND CORROSIONINSPECTION AREAS - RIB 22-27

Sheet 01Sheet 02

Fig. A-UFAAASEALANT AND CORROSIONINSPECTION AREA - TRAILING EDGEFALSEWORK - RIB 22

Sheet 01Sheet 02

NOTE: The worksteps that follow are to be accomplished on the LH and RHwing.

(a) Do a special detailed ultrasonic inspection (Refer to Fig. A-UAAAA Sheet 01, Fig.A-UBAAA Sheet 01, Fig. A-UBAAA Sheet 02, Fig. A-UFAAA Sheet 01 and Fig. A-UFAAA Sheet 02) on the wing top skin overhang between Rib 22 and Rib 27 in thearea of the trailing edge falsework, panels 575AT(675AT), Item (1) and the FixedPanel Assembly, Item (3) (Refer to NTM 57-29-07).

(b) If there are no indications of corrosion, do a visual inspection of the sealant at thewing top skin panel 2 overhang between Rib 22 and Rib 27 and the trailing edgefalsework, the panels 575AT(675AT), Item (1) and the Fixed Panel Assembly, Item(3):

1 Make sure that the sealant surface is smooth and not damaged.

2 If the sealant is found to be damaged or missing, the area must berepaired (Refer to SUBTASK 571154-833-401 001 REPAIR/REPLACEMENTOF SEALANT ).



7



(c) Re-inspect the wing top skin panel 2 overhang between Rib 22 and Rib 27 within40 months (Refer to Fig. A-UAAAA Sheet 01).

(d) If there are indications of corrosion, do detailed visual inspections (x10magnification) (TERMINATING inspection) at the wing top skin panel 2 edge andupper and lower surface at the applicable area:

- to inspect at Rib 22 (trailing edge falsework) refer to SUBTASK571154-220-403 001 DETAILED VISUAL INSPECTION OF THE WING TOPSKIN PANEL 2 EDGE AND UPPER AND LOWER SURFACE AT RIB 22 -TRAILING EDGE FALSEWORK

- to inspect between Rib 22 and Rib 24 refer to SUBTASK 571154-220-401 005DETAILED VISUAL INSPECTION OF THE WING TOP SKIN PANEL 2 EDGEAND CHAMFER AND UPPER AND LOWER SURFACE BETWEEN RIB 22AND RIB 24


(2) Subtask 571154-220-403-001 - DETAILED VISUAL INSPECTION OF THE WING TOPSKIN PANEL 2 EDGE AND UPPER AND LOWER SURFACE AT RIB 22 - TRAILINGEDGE FALSEWORK


575 Access Panel 575HB, Panel 575JB675 Access Panel 675HB, Panel 675JB

Manpower Resources



Skills AIRFRAMENON DESTRUCTIVETESTING


Kit 571154B07R03ITEM NEW PART N˚ QTY (UM) KEYWORD SEE

NOTES20 EN6114K3X-5 6 Bolt21 EN6114K3X-6 7 Bolt23 MS20426AD5-12 4 Rivet24 NSA5474-3K7 16 Nut50 ASNA0079-512ALC 69 Rivet52 MS20426AD6-12 2 Rivet



7



ITEM NEW PART N˚ QTY (UM) KEYWORD SEENOTES

54 ASNA0079-518ALC 3 Rivet55 ASNA0079-613ALC 1 Rivet56 MS20426AD4-12 25 Rivet




07-005 As required

Corrosion Inhibiting Sealant- Fillet Consistency

09-016 As required


Chlorinated Phenol Stripper(Wash Primer System)

12-010 As required

Chemical ConversionCoating Yellow Aluminum

13-002 As required


16-001 As required

Polyurethane Top CoatGray (for Internal Applic.)

16-002 As required





Task 57-51-37-000-006Task 57-51-37-400-004Task 57-51-37-400-006


Structural Repair Manual (SRM) 51-23-1251-24-0051-44-0051-44-1151-74-0051-75-1151-75-1257-21-11


Sheet 01Sheet 02

Fig. A-UHAAAPAINT REMOVAL LIMITS - WING TOPSKIN PANEL 2

Sheet 01



7



CAUTION: YOU MUST BE CAREFUL WHEN YOU REMOVE FASTENERS TOPREVENT DAMAGE TO THE FASTENER HOLE.


(a) Remove the panels 575HB(675HB) (Refer to AMM Task 57-51-37-000-004) and575JB(675JB) (Refer to AMM Task 57-51-37-000-006).

(b) Remove the items that follow to remove the Skin Panel, Item (57) (Refer to Fig. A-UFAAA Sheet 01 and Fig. A-UFAAA Sheet 02):

3 Nut NSA5474-3K7 Item (24) Discard

2 Bolt-Csk Head ASNA2026VBV3-5 Item (30) Retain


3 Washer-Dimpled NAS1169C-10L Item (44) Retain

69 Rivet-Blind Csk ASNA0079-512A Item (50) Discard

2 Rivet-Solid Csk MS20426AD6-12 Item (52) Discard





1 Inspect the sealant on the Skin Panel, Item (57) for corrosion contamination. Ifthere are signs of corrosion particles on the sealant, AIRBUS recommend thatthe related location on the wing top skin panel 2 lower surface be marked toidentify the source of the corrosion.

(c) Remove the items that follow to remove the Splice Plate, Item (58) (Refer to Fig. A-UFAAA Sheet 01 and Fig. A-UFAAA Sheet 02):


7 Bolt-Csk Head ASNA2026VBV3-6 Item (21) Discard

1 Inspect the sealant on the Splice Plate, Item (58) for corrosion contamination.If there are signs of corrosion particles on the sealant, AIRBUS recommendthat the related location on the wing top skin panel 2 lower surface be markedto identify the source of the corrosion.



7



(d) Remove the items that follow to remove the Splice Plate, Item (59) (Refer to Fig. A-UFAAA Sheet 01 and Fig. A-UFAAA Sheet 02):




(e) Use a non-metallic scraper to carefully remove the sealant from along the wing topskin panel 2 vertical skin edge between the trailing edge falsework (Refer to Fig. A-UFAAA Sheet 01 and Fig. A-UFAAA Sheet 02).

(f) Use

Chlorinated PhenolStripper (WashPrimer System)

12-010 As required

(Refer to SRM 51-75-11) and non-metallic scrapers and remove the paint system atthe wing top skin panel 2 vertical skin edge and chamfer between the trailing edgefalsework at Rib 22 (Refer to Fig. A-UFAAA Sheet 01 and Fig. A-UFAAA Sheet 02).

NOTE: It is not possible to remove all the primer with chemical stripper.Some signs of primer can stay.

NOTE: The paint system must not be removed mechanically.

NOTE: Do not remove paint from the skin edge in the area of the fittings(Refer to Fig. A-UHAAA Sheet 01) or from the upper and lowersurface of the wing top skin panel 2.

(g) Do a detailed visual inspection (x10 magnification) at fastener locations at the wingtop skin panel 2 upper and lower surface (Refer to Fig. A-UFAAA Sheet 01, Fig. A-UFAAA Sheet 02 and NTM 51-90-00).

(h) Do a detailed visual inspection (x10 magnification) of the wing top skin panel 2vertical skin edge and chamfer (Refer to Fig. A-UFAAA Sheet 01, Fig. A-UFAAASheet 02 and NTM 51-90-00).

(i) If there are no signs of corrosion, re-apply corrosion protection


and with a roller

Anti-CorrosionPrimer(Polyurethane)

16-001 As required

and



7



Polyurethane TopCoat Gray (forInternal Applic.)

16-002 As required

as per SRM 51-75-12.

(j) If there are signs of corrosion that are within acceptable repair limits (Refer toSRM 57-21-11), repair the corroded areas (Refer to SRM 51-74-00) and re-applycorrosion protection


and with a roller


16-001 As required

and


16-002 As required


CAUTION: YOU MUST CONTACT AIRBUS FOR TECHNICAL INSTRUCTION IFTHE CORROSION EXTENDS BETWEEN THE TOP SKIN LOWERSURFACE AND THE REAR SPAR.

IF YOU SEPARATE THE WING TOP SKIN PANEL 2 FROM THEWING STRUCTURE WITHOUT TECHNICAL INSTRUCTION, AIRBUSWILL TAKE NO RESPONSIBILITY FOR ANY DAMAGE THAT MAY BECAUSED.

(k) If the corrosion extends between the top skin lower surface and the rear spar, youmust contact AIRBUS (before removing fasteners to lift the skin) to obtain a jackingprocedure before you do any more work.

(l) If there are signs of corrosion that are not within acceptable repair limits (Refer toSRM 57-21-11), contact AIRBUS for instruction.

(m) Use a


19-003 As required

made moist with


11-026 As required

to clean the mating faces of the splice plates and the wing surface.



7



(n) Drill and ream the fastener holes for the new Bolts, Items 20 and 21 in the wing topskin panel 2 and the Splice Plates, Items (58) and (59) to between 5.019 and 5.070mm (0.1976 and 0.1996 in.) (Refer to SRM 51-44-11).

(o) Deburr the holes that have been worked.

(p) Apply protective treatment

ChemicalConversion CoatingYellow Aluminum

13-002 As required

to the cut surfaces.

(q) Before wet assembly of components with Corrosion Inhibiting Sealant - FilletConsistency, any new primed or painted surfaces that are aged more than 72 hoursare to be prepared as follows:

1 Lightly abrade with


to give an even matt surface finish free from visible scratches.

2 Clean the abraded surfaces with


19-003 As required

made moist with


11-026 As required

NOTE: A high standard of surface cleanliness is necessary to makesure of subsequent and continued adhesion of the sealantthroughout the life of the aircraft.

Handling or contamination of cleaned surfaces is to beprevented.

(r) Use

Corrosion InhibitingSealant - FilletConsistency

09-016 As required

(Refer to SRM 51-24-00) to install the items that follow (Refer to Fig. A-UFAAASheet 01 and Fig. A-UFAAA Sheet 02):

NOTE: The sealant is to be applied to one faying surface only. Thethickness of sealant is to be constant to allow a continuous bead ofsealant that has flowed from between the assembled components.



7



NOTE: Make sure that the fastener holes are in the correct condition beforeyou re-install the items that were removed to get access for theinspection (Refer to SRM 51-44-00).

1 Install the items that follow to install the Splice Plate, Item (58):

7 Bolt-Csk Head EN6114K3X-6 Item 21

7 Nut NSA5474-3K7 Item 24




3 If any of the Dimpled Washers, Item (44) have come loose, do the steps thatfollow:

a Use a


19-003 As required

made moist with


11-026 As required

to clean the countersink of the applicable bolt holes in the Skin Panel,Item (57) and the Dimpled Washers, Item (44) (Refer to Fig. A-UFAAASheet 01).

b Apply


07-005 As required

(Refer to SRM 51-23-12) to the countersink of the applicable bolt holes inthe Skin Panel, Item (57) to re-attach the Dimpled Washers.

4 Install the items that follow to install the Skin Panel, Item (57):

3 Washer-Dimpled NAS1169C-10L Item (44) Retained atremoval

2 Bolt-Csk Head ASNA2026VBV3-5 Item (30) Retained atremoval





7



69 Rivet-Blind Csk ASNA0079-512ALC Item 50

2 Rivet-Solid Csk MS20426AD6-12 Item 52





(s) Install the panels 575HB(675HB) (Refer to AMM Task 57-51-37-400-004) and575JB(675JB) (Refer to AMM Task 57-51-37-400-006).

(t) Apply sealant between the wing top skin panel 2 overhang between the trailingedge falsework at Rib 22 and the wing top profile (Refer to SUBTASK571154-833-401 001 REPAIR/REPLACEMENT OF SEALANT ).

(3) Subtask 571154-220-401-005 - DETAILED VISUAL INSPECTION OF THE WING TOPSKIN PANEL 2 EDGE AND CHAMFER AND UPPER AND LOWER SURFACEBETWEEN RIB 22 AND RIB 24


575 Access Panel 575AT, Panel 575KB675 Access Panel 675AT, Panel 675KB

Manpower Resources






NOTES20 EN6114K3X-5 7 Bolt22 NSA5414-48-18 1 Rivet23 MS20426AD5-12 25 Rivet24 NSA5474-3K7 8 Nut



NOTESGrease 04-015 As required



7



ITEM DESCRIPTION REFERENCE TOCML MAT. No.



09-016 As required



12-010 As required


13-002 As required


16-001 As required


16-002 As required



Lockwire Stainless SteelAnnealed 0.8mm Dia

19-010 As required



Task 29-00-00-910-004Task 57-51-37-000-005Task 57-51-37-000-007Task 57-51-37-400-005Task 57-51-37-400-007




Sheet 01

Fig. A-UCAAAPANEL 575AT(675AT) AND SPLICEPLATE INSTALLATION - RIB 22-24

Sheet 01


Sheet 01Sheet 02


Sheet 01

Fig. A-UJAAAAILERON JACK No.1 - GREENSYSTEM HYDRAULIC PIPES

Sheet 01



7



ReferencesFig. A-UKAAAAILERON JACK No.2 - BLUE SYSTEMHYDRAULIC PIPES

Sheet 01



(a) Remove the panels 575KB(675KB) (Refer to AMM Task 57-51-37-000-005).

(b) Remove the panel 575AT(675AT), Item (1) (Refer to Fig. A-UCAAA Sheet 01 andAMM Task 57-51-37-000-007).

(c) Disconnect the Green system hydraulic pipes from the No.1 Aileron Jack33CE1(33CE2) (Refer to AMM Task 29-00-00-910-004 and Fig. A-UJAAA Sheet01):

WARNING: WEAR GOGGLES WHEN YOU REMOVE OR INSTALL THELOCKWIRE. CUT, REMOVE AND DISCARD THE LOCKWIRE ASYOU DO THE TASK. LOOSE LOCKWIRE CAN CUT OR BLINDYOU.

1 Remove and discard the lockwire from the Bolts, Item (124).

2 Remove the items that follow from the No.1 Aileron Jack, Item (120):

- 2 off Bolts, Item (124) - Retain

- 2 off Washers, Item (123) - Retain

- 2 off Clamp Blocks, Item (122) - Retain.

3 Remove the items that follow from the Support Bracket, Item (131):

- 2 off Nuts, Item (130) - Retain



- 2 off Distance Tubes, Item (133) - Retain


4 Disconnect the Nut, Item (121) from the No.1 Aileron Jack, Item (120).

5 Disconnect the Nut, Item (126) from the Green system hydraulic pipe. Removeand retain the Pipe, Item (125).




7




8 Put blanking caps:

- on the disconnected line ends

- on the ports of the No.1 Aileron Jack, Item (120)

- on the Green system hydraulic pipes, Items (125) and (128).

(d) Disconnect the Blue system hydraulic pipes from the No.2 Aileron Jack33CE3(33CE4) (Refer to AMM Task 29-00-00-910-004 and Fig. A-UKAAA Sheet01):













5 Disconnect the Nut, Item (106) from the Blue system hydraulic Union, Item(107). Remove and retain the Pipe, Item (105).







7




- on the Blue system hydraulic pipes, Items (105) and (110).

(e) Remove the items that follow to remove the Splice Plate Assembly, Item (2) (Referto Fig. A-UCAAA Sheet 01):


1 Rivet-Solid Csk NSA5414-48-18 Item (22) Discard


7 Bolt-Csk Head ASNA2026HK3-5 Item (20) Discard


NOTE: Make a note of all the items you remove and their positions.

1 Inspect the sealant on the Splice Plate, Item (2) for corrosion contamination. Ifthere are signs of corrosion particles on the sealant, AIRBUS recommend thatthe related location on the wing top skin panel 2 lower surface be marked toidentify the source of the corrosion.

(f) Remove the items that follow to remove the Splice Plate, Item (4) (Refer to Fig. A-UCAAA Sheet 01):




(g) Use a non-metallic scraper to carefully remove the sealant from along the wing topskin panel 2 vertical skin edge between Rib 22 and Rib 24 (Refer to Fig. A-UBAAASheet 01 and Fig. A-UBAAA Sheet 02).

(h) Use


12-010 As required

(Refer to SRM 51-75-11) and non-metallic scrapers and remove the paint system atthe wing top skin panel 2 vertical skin edge and chamfer between Rib 22 and Rib24 (Refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02).




7





(i) Do a detailed visual inspection (x10 magnification) at fastener locations at the wingtop skin panel 2 upper and lower surface (Refer to Fig. A-UBAAA Sheet 01, Fig. A-UBAAA Sheet 02 and NTM 51-90-00).

(j) Do a detailed visual inspection (x10 magnification) of the wing top skin panel 2vertical skin edge between Rib 22 and Rib 24 (Refer to Fig. A-UBAAA Sheet 01,Fig. A-UBAAA Sheet 02 and NTM 51-90-00).

(k) If there are no signs of corrosion, re-apply corrosion protection


and with a roller


16-001 As required

and


16-002 As required


(l) If there are signs of corrosion that are within acceptable repair limits (Refer toSRM 57-21-11), repair the corroded areas (Refer to SRM 51-74-00) and re-applycorrosion protection


and with a roller


16-001 As required

and


16-002 As required




7





(m) If the corrosion extends between the top skin lower surface and the rear spar, youmust contact AIRBUS (before removing fasteners to lift the skin) to obtain a jackingprocedure before you do any more work.

(n) If there are signs of corrosion that are not within acceptable repair limits (Refer toSRM 57-21-11), contact AIRBUS for instruction.

(o) Use a


19-003 As required

made moist with


11-026 As required


(p) Drill and ream the fastener holes for the new Bolts, Item 20 in the wing top skinpanel 2 and the Splice Plate Assembly, Item (2) to between 5.019 and 5.070 mm(0.1976 and 0.1996 in.) (Refer to SRM 51-44-11).

(q) Deburr the holes that have been worked.

(r) Apply protective treatment


13-002 As required


(s) Before wet assembly of components with Corrosion Inhibiting Sealant - FilletConsistency, any new primed or painted surfaces that are aged more than 72 hoursare to be prepared as follows:






7





19-003 As required

made moist with


11-026 As required



(t) Use


09-016 As required

(Refer to SRM 51-24-00 to install the items that follow that were removed for theinspection:



1 Install the Splice Plate Assembly, Item (2) with the items that follow (Refer toFig. A-UCAAA Sheet 01):


1 Rivet-Solid Csk NSA5414-48-18 Item 22




2 Install the Splice Plate, Item (4) with the items that follow (Refer to Fig. A-UCAAA Sheet 01):




7



(u) Connect the Green system hydraulic pipes to the No.1 Aileron Jack 33CE1(33CE2)(Refer to AMM Task 29-00-00-910-004 and Fig. A-UJAAA Sheet 01):

1 Remove the blanking caps from:

- the disconnected line ends

- the ports of the No.1 Aileron Jack, Item (120)

- the Green system hydraulic pipes, Items (125) and (128).

2 Apply


to the threads of the fittings of the Pipes, Items (125) and (128).

3 Connect the Nuts, Items (121) and (126) of the Pipe, Item (125) to the No.1Aileron Jack, Item (120) and the Green system hydraulic pipe.


5 Install the items that follow to the No.1 Aileron Jack, Item (120):

- 2 off Clamp Blocks, Item (122) - Retained at removal

- 2 off Washers, Item (123) - Retained at removal

- 2 off Bolts, Item (124) - Retained at removal.


6 Safety the Bolts, Item (124) with

Lockwire StainlessSteel Annealed0.8mm Dia

19-010 As required

7 Install the items that follow to the Support Bracket, Item (131):


- 2 off Distance Tubes, Item (133) - Retained at removal


- 2 off Bolts, Item (135) - Retained at removal

- 2 off Nuts, Item (130) - Retained at removal.



7



(v) Connect the Blue system hydraulic pipes to the No.2 Aileron Jack 33CE3(33CE4)(Refer to AMM Task 29-00-00-910-004 and Fig. A-UKAAA Sheet 01):




- the Blue system hydraulic pipes, Items (105) and (110).

2 Apply



3 Connect the Nuts, Items (101) and (106) of the Pipe, Item (105) to the No.2Aileron Jack, Item (100) and the Blue system hydraulic Union, Item (107).









19-010 As required






(w) Install the panels 575AT(675AT), Item (1) (Refer to AMM Task 57-51-37-400-007).



7



(x) Apply sealant between the wing top skin panel 2 overhang between Rib 22 and Rib24 and the panels 575AT(675AT), Item (1) and the Splice Plate Assembly, Item (2)(Refer to SUBTASK 571154-833-401 001 REPAIR/REPLACEMENT OF SEALANT).

(y) Install the panels 575KB(675KB) (Refer to AMM Task 57-51-37-400-005).



575 Access Panel 575LB, Panel 575MB675 Access Panel 675LB, Panel 675MB

Manpower Resources






NOTES23 MS20426AD5-12 20 Rivet24 NSA5474-3K7 2 Nut35 ASNA0077D505 93 Rivet36 ASNA0077D504 16 Rivet37 ASNA0077D506 5 Rivet38 ASNA0077D607 2 Rivet40 ASNA0077D605 24 Rivet41 ASNA0077D507 1 Rivet43 ASNA0077D606 2 Rivet



NOTESCorrosion Inhibiting Sealant- Fillet Consistency

09-016 As required



12-010 As required


16-001 As required



7






16-002 As required





Task 57-51-37-000-005Task 57-51-37-400-005


Structural Repair Manual (SRM) 51-24-0051-44-0051-74-0051-75-1151-75-1257-21-11


Sheet 01Sheet 02

Fig. A-UDAACFIXED PANEL INSTALLATION - RIB24-27

Sheet 01

Fig. A-UEAAASPLICE PLATE INSTALLATION - RIB24-27

Sheet 01


Sheet 01



(a) Remove the panels 575LB(675LB) and 575MB(675MB) (Refer to AMM Task57-51-37-000-005).

(b) Remove the items that follow to remove the Fixed Panel Assembly, Item (3) (Referto Fig. A-UDAAC Sheet 01) as follows:

61 Rivet-Blind Csk ASNA0077D505 Item (35) Discard





7






1 Inspect the sealant on the Fixed Panel Assembly, Item (3) for corrosioncontamination. If there are signs of corrosion particles on the sealant, AIRBUSrecommend that the related location on the wing top skin panel 2 lowersurface be marked to identify the source of the corrosion.

(c) Remove the items that follow to remove the Splice Plates (Refer to Fig. A-UEAAASheet 01):

1 For the Splice Plate, Item (60):






a Inspect the sealant on the Splice Plate, Item (60) for corrosioncontamination. If there are signs of corrosion particles on the sealant,AIRBUS recommend that the related location on the wing top skin panel2 lower surface be marked to identify the source of the corrosion.









7






(d) Use a non-metallic scraper to carefully remove the sealant from along the wing topskin panel 2 vertical skin edge between Rib 24 and Rib 27 (Refer to Fig. A-UBAAASheet 01 and Fig. A-UBAAA Sheet 02).

(e) Use


12-010 As required





(f) Do a detailed visual inspection (x10 magnification) at fastener locations at the wingtop skin panel 2 upper and lower surface (Refer to Fig. A-UBAAA Sheet 01, Fig. A-UBAAA Sheet 02 and NTM 51-90-00).

(g) Do a detailed visual inspection (x10 magnification) of the wing top skin panel 2vertical skin edge between Rib 24 and Rib 27 (Refer to Fig. A-UBAAA Sheet 01,Fig. A-UBAAA Sheet 02 and NTM 51-90-00).

(h) If there are no signs of corrosion, re-apply corrosion protection


and with a roller


16-001 As required

and



7




16-002 As required


(i) If there are signs of corrosion that are within acceptable repair limits (Refer toSRM 57-21-11), repair the corroded areas (Refer to SRM 51-74-00) and re-applycorrosion protection


and with a roller


16-001 As required

and


16-002 As required




(j) If the corrosion extends between the top skin lower surface and the rear spar, youmust contact AIRBUS (before removing fasteners to lift the skin) to obtain a jackingprocedure before you do any more work.

(k) If there are signs of corrosion that are not within acceptable repair limits (Refer toSRM 57-21-11), contact AIRBUS for instruction.

(l) Use a


19-003 As required

made moist with


11-026 As required




7



(m) Before wet assembly of components with Corrosion Inhibiting Sealant - FilletConsistency, any new primed or painted surfaces that are aged more than 72 hoursare to be prepared as follows:






19-003 As required

made moist with


11-026 As required



(n) Use


09-016 As required

(Refer to SRM 51-24-00 to install the items that follow that were removed for theinspection (Refer to Fig. A-UDAAC Sheet 01 and Fig. A-UEAAA Sheet 01):



1 Install the Splice Plate, Item (60) with the items that follow:

13 Rivet-Blind Csk ASNA0077D505 Item 35






7










5 Install the Fixed Panel Assembly, Item (3) with the items that follow:







(o) Apply sealant between the wing top skin panel 2 overhang between Rib 24 and Rib27 and the Fixed Panel Assembly, Item (3) (Refer to SUBTASK 571154-833-401001 REPAIR/REPLACEMENT OF SEALANT ).

(p) Install the panels 575LB(675LB) and 575MB(675MB) (Refer to AMM Task57-51-37-400-005).

(5) Subtask 571154-833-401-001 - REPAIR/REPLACEMENT OF SEALANT


575675

Manpower Resources



Skills AIRFRAME



7






NOTESMasking Tape 08-074 As required


09-016 As required


09-028 As required



ReferencesAircraft Maintenance Manual (AMM) 51-76-00, Page Block 001

Structural Repair Manual (SRM) 51-24-00

(a) Repair or replace the sealant between the wing top skin panel 2 and the applicableaccess panel or wing panel (Refer to SRM 51-24-00, AMM 51-76-00, Page Block001 and to APPENDIX 1 - SPECIAL TOOLING ) as follows:

1 Use a


19-003 As required

made moist with


11-026 As required

to clean the gap between the wing top skin panel 2 and the applicable sealplate, access panel or wing panel.



2 Apply


to both sides of the gap to be filled.



7



3 Use


09-016 As required

to fillet seal the void between the wing top skin panel 2 and the applicableseal plate, access panel or wing panel (Refer to SRM 51-24-00 and AMM51-76-00, Page Block 001).

NOTE: Force the sealant into the gap removing air bubbles or voids.

4 Use the Special Tool (Refer to APPENDIX 1 - SPECIAL TOOLING ) and withthe applicable width tooth (that fits the gap between the wing top skin panel 2and the applicable seal plate, access panel or wing panel) remove 2.0 mm(0.078 in.) of sealant that has flowed from the gap between the wing top skinpanel 2 and the applicable seal plate, access panel or wing panel.

5 Use a


19-003 As required

made moist with


11-026 As required

to remove excess sealant and to clean the surface of the sealant.

6 When the sealant has cured, apply

Adhesion PromoterFor PolysulphideSealant

09-028 As required

over the new Corrosion Inhibiting Sealant - Fillet Consistency.

NOTE: Make sure that the new sealant is free from dirt and debris.

7 Use


09-016 As required

to aerodynamically fill the gap between the wing top skin panel 2 and theapplicable seal plate, access panel or wing panel.





7



8 Use a non-metallic scraper and remove any excess sealant to produce asmooth finish that is level with the wing top skin panel 2 and the applicableseal plate, access panel or wing panel.

9 Remove and discard the masking tape from both sides of the gap.

**CONF 002



575675

Manpower Resources






Sheet 01


Sheet 01Sheet 02


Sheet 01Sheet 02







7












Manpower Resources






NOTES20 EN6114K3X-5 6 Bolt21 EN6114K3X-6 7 Bolt23 MS20426AD5-12 4 Rivet



7




24 NSA5474-3K7 16 Nut50 ASNA0079-512ALC 69 Rivet52 MS20426AD6-12 2 Rivet54 ASNA0079-518ALC 3 Rivet55 ASNA0079-613ALC 1 Rivet56 MS20426AD4-12 25 Rivet




07-005 As required


09-016 As required



12-010 As required


13-002 As required


16-001 As required


16-002 As required





Task 57-51-37-000-006Task 57-51-37-400-004Task 57-51-37-400-006




Sheet 01Sheet 02



7



ReferencesFig. A-UHAAAPAINT REMOVAL LIMITS - WING TOPSKIN PANEL 2

Sheet 01





















7









(f) Use


12-010 As required









and with a roller



7




16-001 As required

and


16-002 As required




and with a roller


16-001 As required

and


16-002 As required






(m) Use a


19-003 As required

made moist with



7




11-026 As required






13-002 As required








19-003 As required

made moist with


11-026 As required



(r) Use


09-016 As required




7












a Use a


19-003 As required

made moist with


11-026 As required


b Apply


07-005 As required







7
















Manpower Resources









7







09-016 As required



12-010 As required


13-002 As required


16-001 As required


16-002 As required




19-010 As required



Task 29-00-00-910-004Task 57-51-37-000-005Task 57-51-37-000-007Task 57-51-37-400-005Task 57-51-37-400-007




Sheet 01

Fig. A-UCAAAPANEL 575AT(675AT) AND SPLICEPLATE INSTALLATION - RIB 22-24

Sheet 01


Sheet 01Sheet 02


Sheet 01



7



ReferencesFig. A-UJAAAAILERON JACK No.1 - GREENSYSTEM HYDRAULIC PIPES

Sheet 01

Fig. A-UKAAAAILERON JACK No.2 - BLUE SYSTEMHYDRAULIC PIPES

Sheet 01




(b) Remove the panel 575AT(675AT), Item (1) (Refer to Fig. A-UCAAA Sheet 01 andAMM Task 57-51-37-000-007).

















7




























7







(e) Remove the items that follow to remove the Splice Plate Assembly, Item (2) (Referto Fig. A-UCAAA Sheet 01):








(f) Remove the items that follow to remove the Splice Plate, Item (4) (Refer to Fig. A-UCAAA Sheet 01):





(h) Use


12-010 As required




7










and with a roller


16-001 As required

and


16-002 As required




and with a roller


16-001 As required

and


16-002 As required




7







(o) Use a


19-003 As required

made moist with


11-026 As required






13-002 As required








7





19-003 As required

made moist with


11-026 As required



(t) Use


09-016 As required




1 Install the Splice Plate Assembly, Item (2) with the items that follow (Refer toFig. A-UCAAA Sheet 01):






2 Install the Splice Plate, Item (4) with the items that follow (Refer to Fig. A-UCAAA Sheet 01):




7








2 Apply












19-010 As required









7








Manpower Resources






NOTES23 MS20426AD5-12 20 Rivet24 NSA5474-3K7 14 Nut35 ASNA0077D505 91 Rivet36 ASNA0077D504 8 Rivet37 ASNA0077D506 3 Rivet38 ASNA0077D607 2 Rivet40 ASNA0077D605 24 Rivet41 ASNA0077D507 1 Rivet43 ASNA0077D606 2 Rivet




09-016 As required



12-010 As required


16-001 As required



7






16-002 As required





Task 57-51-37-000-005Task 57-51-37-400-005




Sheet 01Sheet 02

Fig. A-UDAADFIXED PANEL INSTALLATION - RIB24-27

Sheet 01


Sheet 01


Sheet 01




(b) Remove the items that follow to remove the Fixed Panel Assembly, Item (3) (Referto Fig. A-UDAAD Sheet 01):






7







and the applicable fasteners

Asrequired

Bolt-Csk Head ASNA2026VBV3-6 Item (21) Retain

Asrequired


Asrequired


Asrequired

Bolt-Protruding Head ASNA2027VBV3-3 Item (32) Retain

Asrequired


Asrequired


and the











7
















(e) Use


12-010 As required





7









and with a roller


16-001 As required

and


16-002 As required




and with a roller


16-001 As required

and


16-002 As required




7







(l) Use a


19-003 As required

made moist with


11-026 As required








19-003 As required

made moist with


11-026 As required





7



(n) Use


09-016 As required

(Refer to SRM 51-24-00 to install the items that follow that were removed for theinspection (Refer to Fig. A-UDAAD Sheet 01 and Fig. A-UEAAA Sheet 01):















5 Install the Fixed Panel Assembly, Item (3) with the items that follow:








7





and the applicable fasteners

Asrequired

Bolt-Csk Head ASNA2026VBV3-6 Item (21) Retained atremoval

Asrequired


Asrequired


Asrequired

Bolt-Protruding Head ASNA2027VBV3-4 Item (45) Retained atremoval

Asrequired

Bolt-Protruding Head ASNA2027VBV3-5 Item (46) Retained atremoval

with the






575675

Manpower Resources



Skills AIRFRAME



7








09-016 As required


09-028 As required






1 Use a


19-003 As required

made moist with


11-026 As required




2 Apply





7



3 Use


09-016 As required




5 Use a


19-003 As required

made moist with


11-026 As required




09-028 As required



7 Use


09-016 As required






7





**CONF 003



575675

Manpower Resources






Sheet 01


Sheet 01Sheet 02


Sheet 01Sheet 02







7












Manpower Resources






NOTES20 EN6114K3X-5 6 Bolt21 EN6114K3X-6 7 Bolt23 MS20426AD5-12 4 Rivet



7




24 NSA5474-3K7 16 Nut50 ASNA0079-512ALC 69 Rivet52 MS20426AD6-12 2 Rivet54 ASNA0079-518ALC 3 Rivet55 ASNA0079-613ALC 1 Rivet56 MS20426AD4-12 25 Rivet




07-005 As required


09-016 As required



12-010 As required


13-002 As required


16-001 As required


16-002 As required





Task 57-51-37-000-006Task 57-51-37-400-004Task 57-51-37-400-006




Sheet 01Sheet 02



7



ReferencesFig. A-UHAAAPAINT REMOVAL LIMITS - WING TOPSKIN PANEL 2

Sheet 01





















7









(f) Use


12-010 As required









and with a roller



7




16-001 As required

and


16-002 As required




and with a roller


16-001 As required

and


16-002 As required






(m) Use a


19-003 As required

made moist with



7




11-026 As required






13-002 As required








19-003 As required

made moist with


11-026 As required



(r) Use


09-016 As required




7












a Use a


19-003 As required

made moist with


11-026 As required


b Apply


07-005 As required







7
















Manpower Resources









7



Component COMPB01


20 EN6114K3X-5 1 Bolt24 NSA5474-3K7 1 Nut





09-016 As required



12-010 As required


13-002 As required


16-001 As required


16-002 As required




19-010 As required



Task 29-00-00-910-00451-76-00, Page Block 001Task 57-51-37-000-005Task 57-51-37-000-007Task 57-51-37-400-005Task 57-51-37-400-007


Structural Repair Manual (SRM) 51-21-1151-24-0051-44-0051-44-1151-74-0051-75-1151-75-1251-76-1157-21-11


Sheet 01



7



ReferencesFig. A-UCAABPANEL 575AT(675AT) AND SPLICEPLATE INSTALLATION - RIB 22-24

Sheet 01


Sheet 01Sheet 02


Sheet 01

Fig. A-UJAAAAILERON JACK No.1 - GREENSYSTEM HYDRAULIC PIPES

Sheet 01

Fig. A-UKAAAAILERON JACK No.2 - BLUE SYSTEMHYDRAULIC PIPES

Sheet 01




(b) Remove the panel 575AT(675AT), Item (1) (Refer to Fig. A-UCAAB Sheet 01 andAMM Task 57-51-37-000-007).













7





























7










(e) Remove the items that follow to remove the Splice Plate Assembly, Item (2) (Referto Fig. A-UCAAB Sheet 01):






For aircraft Pre Mod. No. 38026J2845, you will also need to remove an additional:


and a




(f) Remove the items that follow to remove the Splice Plate, Item (4) (Refer to Fig. A-UCAAB Sheet 01):





7





(h) Use


12-010 As required









and with a roller


16-001 As required

and


16-002 As required




7





and with a roller


16-001 As required

and


16-002 As required






(o) Use a


19-003 As required

made moist with


11-026 As required






7





13-002 As required








19-003 As required

made moist with


11-026 As required



(t) Use


09-016 As required






7



1 Install the Splice Plate Assembly, Item (2) with the items that follow (Refer toFig. A-UCAAB Sheet 01):






For aircraft Pre Mod 38026J2845, you will also need to install an additional:


and a


2 Install the Splice Plate, Item (4) with the items that follow (Refer to Fig. A-UCAAB Sheet 01):







2 Apply









7








19-010 As required












2 Apply









7








19-010 As required














7



Manpower Resources






NOTES23 MS20426AD5-12 20 Rivet24 NSA5474-3K7 123 Nut35 ASNA0077D505 31 Rivet40 ASNA0077D605 13 Rivet43 ASNA0077D606 2 Rivet




09-016 As required



12-010 As required


16-001 As required


16-002 As required





Task 57-51-37-000-005Task 57-51-37-400-005





7



ReferencesFig. A-UBAAASEALANT AND CORROSIONINSPECTION AREAS - RIB 22-27

Sheet 01Sheet 02

Fig. A-UDAAEFIXED PANEL INSTALLATION - RIB24-27

Sheet 01


Sheet 01


Sheet 01




NOTE: Before removal of the Fixed Panel Assembly, Item (3), operators shouldnote that it is possible that fastener type ASNA2001 OR fastener typeASNA2026 may be installed.

(b) Remove as applicable the items that follow to remove the Fixed Panel Assembly,Item (3) (Refer to Fig. A-UDAAE Sheet 01):





37 Bolt-Csk Head ASNA2001VN3-5 Item (70) Retain








7
























7








(e) Use


12-010 As required









and with a roller



7




16-001 As required

and


16-002 As required




and with a roller


16-001 As required

and


16-002 As required






(l) Use a


19-003 As required

made moist with



7




11-026 As required








19-003 As required

made moist with


11-026 As required



(n) Use


09-016 As required

(Refer to SRM 51-24-00 to install the items that follow that were removed for theinspection (Refer to Fig. A-UDAAE Sheet 01 and Fig. A-UEAAA Sheet 01):








7












5 Install the Fixed Panel Assembly, Item (3) with the applicable items that follow:




37 Bolt-Csk Head ASNA2001VN3-5 Item (70) Retained atremoval









7











575675

Manpower Resources



Skills AIRFRAME






09-016 As required


09-028 As required







7




1 Use a


19-003 As required

made moist with


11-026 As required




2 Apply



3 Use


09-016 As required




5 Use a


19-003 As required

made moist with



7




11-026 As required




09-028 As required



7 Use


09-016 As required






**CONF ALL

D. TEST

NOTE: There is no requirement to do the system and operational tests if only therepeat ultrasonic inspection is performed.

**CONF 001

(1) Subtask 571154-790-401-001 - LEAK CHECK

Manpower Resources

Skills AIRFRAME


(a) Do a check for external leaks of the hydraulic components (Refer to AMM Task29-00-00-790-001).



7



(2) Subtask 571154-710-401-001 - OPERATIONAL

Manpower Resources

Skills AIRFRAME


(a) Do an operation test of the aileron and hydraulic action (Refer to AMM Task27-14-00-710-001).

**CONF 002


Manpower Resources

Skills AIRFRAME




Manpower Resources

Skills AIRFRAME



**CONF 003


Manpower Resources

Skills AIRFRAME




Manpower Resources

Skills AIRFRAME



7





**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 571154-942-401-001 - CLOSE-UP


575675

Manpower Resources

Skills UTILITY


Task 57-51-37-400-007

(a) Make sure that the work areas are clean and clear of tool(s) and other equipment.

(b) Fully retract the flaps (Refer to AMM Task 27-50-00-866-009).

(c) Do the Close-up procedure for the "Installation of the Access Panel 575AT(675AT)"(Refer to AMM Task 57-51-37-400-007).


Manpower Resources

Skills UTILITY

(a) Complete and return the Reporting Sheet (Refer to APPENDIX 2 - SERVICEBULLETIN REPORTING SHEET ) to:

AIRBUS

SEES2

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Fax No. +33561933614.



7



**CONF 002

(1) Subtask 571154-942-401-001 - CLOSE-UP


575675

Manpower Resources

Skills UTILITY


Task 57-51-37-400-007





Manpower Resources

Skills UTILITY


AIRBUS

SEES2


31707 BLAGNAC CEDEX

FRANCE

Fax No. +33561933614.

**CONF 003

(1) Subtask 571154-942-401-001 - CLOSE-UP


575675



7



Manpower Resources

Skills UTILITY


Task 57-51-37-400-007





Manpower Resources

Skills UTILITY


AIRBUS

SEES2


31707 BLAGNAC CEDEX

FRANCE

Fax No. +33561933614.



7



**CONF ALL

CORROSIONDETECTED?

575HB/675HB, 575JB/675JB,

TERMINATING INSPECTION:REMOVE AILERON ACCESS

PANELS 575AT/675AT,

OR

WITHIN SB AREAVISUALLY INSPECT

SEALANT CONDITION ANDRESTORE IF NECESSARY

INSPECT THE WING TOP SKINOVERHANG BETWEEN RIB 22

AND RIB 27WITHIN 40 MONTHS

FOR EXPOSED VERTICALSKIN EDGE & CHAMFER:

UP TO 10.0 mm (0.393 in) FROMFITTING BRACKETS, CHEMICALSTRIP & SCRAPE PAINT SYSTEM

(NON−METALLIC TOOLS)

DETAILED VISUAL INSPECTION(x10 MAGNIFICATION)

AT FASTENER LOCATIONS(UPPER & LOWER SURFACE)

AS PER NTM 51−90−00

LAST OF EITHER;40 MONTHS FROM EIS OR

40 MONTHS FROM SB RELEASE

SPECIAL DETAILEDINSPECTION

AS PER NTM 57−29−07

AS PER SRM 51−75−11

OR

NTM 57−29−07

REPEAT INSPECTION:SPECIAL DETAILED

INSPECTION AS PER

CORROSIONDETECTED?

PROTECTION AS PERACCOMPLISHMENT

INSTRUCTIONS GIVEN INNO

RE−SEAL AS PERACCOMPLISHMENT

INSTRUCTIONS GIVEN INTHIS SERVICE BULLETIN

NO FURTHERACTION

YES

FINDINGSWITHIN SRM

57−21−11LIMITS?

REMOVECORROSION AS

PER SRM 51−74−00

CORROSIONFOUND UNDERFITTINGS OR

SPAR?

CONTACTAIRBUS

YES

NO

NOYES

YES NO

AND SPLICE PLATEFIXED PANEL ASSEMBLY

(NOTE: IT IS NOT POSSIBLE TOREMOVE ALL PRIMER − SEE

ILLUSTRATION A−UHAAA)

(SEE NOTE 1)

NOT REQUIRED IN AREA OF FITTING BRACKETSNOTE 2:(SEE ILLUSTRATION A−UHAAA).

TO PROVIDE ADVANCED NOTIFICATIONOF SIGNIFICANT HIDDEN CORROSION AREAS.

OPTIONALNOTE 1:

DETAILED VISUAL INSPECTION(x10 MAGNIFICATION) ATVERTICAL SKIN EDGE &

CHAMFER AS PER NTM 51−90−00(SEE NOTE 2)

N_SB_571154_7_AAAA_01_08

RE−APPLY SURFACE

THIS SERVICE BULLETIN

Figure A-UAAAA - Sheet 01INSPECTION FLOW CHART



7



**CONF ALL

AA

N_SB_571154_7_BAAA_01_01

LH SHOWNRH SIMILAR

A

RIB22

RIB24

FIXED PANELASSEMBLY

RIB27

B

B

AILERON

575AT(675AT)

Z575(Z675)

A

Figure A-UBAAA - Sheet 01SEALANT AND CORROSION INSPECTION AREAS - RIB 22-27



7



**CONF ALL

SEALANT

SPLICE PLATE ACCESS PANEL575AT (675AT)

SEALANT

REAR SPAR

FIXED PANELASSEMBLY

WING TOP SKINPANEL 2



SPLICE PLATE

REAR SPAR


CORROSION AFFECTED SURFACEPAINT REMOVAL NOT REQUIRED

ON UPPER/LOWER SURFACE

D B C

D B C


CORROSION AFFECTED SURFACEPAINT REMOVAL REQUIRED

CORROSION AFFECTED SURFACEPAINT REMOVAL REQUIRED

REAR SPAR

B B

A A

CB

DETAILED VISUAL INSPECTION(x10 MAGNIFICATION) AT FASTENER LOCATIONS

UPPER AND LOWER SURFACE

D



N_SB_571154_7_BAAA_02_07

Figure A-UBAAA - Sheet 02SEALANT AND CORROSION INSPECTION AREAS - RIB 22-27



7



**CONF 001 thru 002

Z575(Z675)

575AT

(675AT)

WING TOP SKIN(PANEL 2)

OUTERREAR SPAR

575KB

(675KB)

RIB22

RIB24

A

LH SHOWNRH SIMILAR

RIB23

RIB24

A

N_SB_571154_7_CAAA_01_06

Figure A-UCAAA - Sheet 01PANEL 575AT(675AT) AND SPLICE PLATE INSTALLATION - RIB 22-24



7



**CONF 003

Z575(Z675)

575AT

(675AT)


OUTERREAR SPAR

575KB

(675KB)

RIB22

RIB24

A

LH SHOWNRH SIMILAR

RIB23

RIB24

A

FOR POST MOD 38026J2845 NO FASTENERNOTE:INSTALLED AT THIS POSITION. N_SB_571154_7_CAAB_01_02

Figure A-UCAAB - Sheet 01PANEL 575AT(675AT) AND SPLICE PLATE INSTALLATION - RIB 22-24



7



**CONF 001

Z575(Z675)

RIB24

RIB27

LH SHOWNRH SIMILAR

VIEW ON BOTTOM OF FIXED PANEL ASSEMBLY

RIB27

HINGE NO.4

A

SYMBOL ITEM No.

35

36

37

38

40

41

N_SB_571154_7_DAAC_01_01

A

Figure A-UDAAC - Sheet 01FIXED PANEL INSTALLATION - RIB 24-27



7



**CONF 002

Z575(Z675)

RIB24

RIB27

LH SHOWNRH SIMILAR

VIEW ON BOTTOM OF FIXED PANEL ASSEMBLY

RIB27

HINGE NO.4

A

SYMBOL ITEM No.

35

36

37

38

40

41

N_SB_571154_7_DAAD_01_01

OR

OR

OR

OR

OR

OR

OR

OR

A

Figure A-UDAAD - Sheet 01FIXED PANEL INSTALLATION - RIB 24-27



7



**CONF 003

LH SHOWNRH SIMILAR

VIEW ON TOP OF FIXED PANEL ASSEMBLY

HINGE NO.4

RIB27

FIXED PANELASSEMBLY

A

SYMBOL ITEM No.

(71)OR(85), (44), (24)24

(21)OR(81), (44), (24)24

(30)OR(70), (31)OR(80), (82)OR(83), (44), (24)24

(30)OR(70), (31)OR(80), (44), (24)24

(21)OR(81), (42)OR(72), (71)OR(85), (84), (44), (24)24

(21)OR(81), (30)OR(70), (71)OR(85), (44), (24)24

RIB24

RIB27

Z575(Z675)

A

N_SB_571154_7_DAAE_01_03

Figure A-UDAAE - Sheet 01FIXED PANEL INSTALLATION - RIB 24-27



7



**CONF ALL

Z575(Z675)

RIB24

RIB27

A

LH SHOWNRH SIMILAR

OUTERREAR SPAR

RIB27

RIB26

RIB25


A

N_SB_571154_7_EAAA_01_01

Figure A-UEAAA - Sheet 01SPLICE PLATE INSTALLATION - RIB 24-27



7



**CONF ALL

RIB22

Z575(Z675)

A


OUTBOARDFLAP

575JB

(675JB)575HB

(675HB)

LH SHOWNRH SIMILAR

SKIN PANEL

A

FOR PRE MOD 26173J1636 NO FASTENERNOTE:INSTALLED AT THIS POSITION.

B

B

C

APPLY ANTI−STATIC PAINT UNDERTHE DIMPLED WASHER. N_SB_571154_7_FAAA_01_02

Figure A-UFAAA - Sheet 01SEALANT AND CORROSION INSPECTION AREA - TRAILING EDGE FALSEWORK - RIB 22



7



**CONF ALL

SEALANT

SPLICE PLATE


REAR SPAR


CORROSION AFFECTED SURFACEPAINT REMOVAL NOT REQUIRED

ON UPPER/LOWER SURFACE

REAR SPAR

CORROSIONAFFECTED SURFACE

PAINT REMOVALREQUIRED

SKIN PANEL


A A


C

D E

AA

E

TYPICAL INSTALLATIONDETAILED VISUAL INSPECTION

(x10 MAGNIFICATION) AT FASTENER LOCATIONSUPPER AND LOWER SURFACE

DDETAILED VISUAL INSPECTION

(x10 MAGNIFICATION)

N_SB_571154_7_FAAA_02_03

Figure A-UFAAA - Sheet 02SEALANT AND CORROSION INSPECTION AREA - TRAILING EDGE FALSEWORK - RIB 22



7



**CONF ALL

N_SB_571154_7_HAAA_01_02

REAR SPAR


CHEMICALLY STRIPAPPROXIMATELY UP TO10.0 mm (0.393 in) FROM

EDGES OF FITTING BRACKETS


TYPICAL FITTINGINSTALLATION

WINGLOWER SKIN


CHEMICALSTRIPPING

NOT REQUIRED

A




FITTINGBRACKET

(0.393 in)(TYPICAL)

10.0 mm(0.393 in)

(TYPICAL)

10.0 mm

A

AB

B



A A

B B A

Figure A-UHAAA - Sheet 01PAINT REMOVAL LIMITS - WING TOP SKIN PANEL 2



7



**CONF ALL

A

N_SB_571154_7_JAAA_01_00

Z575(Z675)

RIB23

REAR SPARJACK BRACKET

(REF ONLY)

AILERON JACKBRACKET

(REF ONLY)

33CE1

(33CE2)

TYPICAL

C

A

B

B

B

C

Figure A-UJAAA - Sheet 01AILERON JACK No.1 - GREEN SYSTEM HYDRAULIC PIPES



7



**CONF ALL

A

B

N_SB_571154_7_KAAA_01_00

RIB24

Z575(Z675)

AILERON JACKBRACKET

(REF ONLY)

REAR SPARJACK BRACKET

(REF ONLY)

TYPICAL

33CE3

(33CE4)

A

B

C

C

C

Figure A-UKAAA - Sheet 01AILERON JACK No.2 - BLUE SYSTEM HYDRAULIC PIPES



7






7




**CONF ALL

Refer to Figure A-UGAAA - Sheet 1 and Sheet 2 for the Special Tooling required for the application ofsealant.



7




**CONF ALL

PANEL 2WING TOP SKIN

PANEL

2.0 mm +/− 0.5 mm(0.078 in +/− 0.019 in)


PANEL

SEALANT

2.0 mm +/− 0.5 mm(0.078 in +/− 0.019 in)

SEALANT



A

A

B

B

C

C

EXAMPLE 1 EXAMPLE 2

EXAMPLE 1 EXAMPLE 2

EXAMPLE 1 EXAMPLE 2

A


PANEL 2WING TOP SKIN SEALANT

SEALANT

SEALANTSEALANT

SEALANTSEALANT

WHEN THE INITIAL LAYER OF SEALANT HAS CURED, APPLY ADHESIONNOTE:PROMOTER BEFORE YOU APPLY THE FINAL LAYER OF SEALANT. N_SB_571154_7_GAAA_01_02

A A

B B

C C

Figure A-UGAAA - Sheet 01SEALANT APPLICATION - INSTRUCTION AND TOOLING



7




**CONF ALL

REMOVE ALL NON CRITICAL SHARP EDGES.NOTE:

ETCH AS SHOWN THE TEETH SIZES ON BOTH FACES.

MATERIAL SPECIFICATION: NYLON 66 (PREFERED)PERSPEX (ALTERNATIVE).

6.0 mm

(0.236 in)

7.0

mm

(0.2

75 in

)

5.0 mm(0.196 in)

4.0

mm

(0.1

57 in

)

3.0 mm

(0.118in)

2.0 mm(0.078 in)

40.0 mm(1.574 in)

5.0 mm(0.196 in)

73.0

mm

(2.8

74 in

) R

EF

.

B

= 5 =

REVERSED FACECHAMFERED 1 SIDE

20.0 mm(0.787 in)

40.0 mm(1.574 in)

60

1 x

60

CH

AM

FE

R

5.0 mm(0.196 in)

2.0

mm

(0.0

78 in

)

TYPICAL TOOTH CHAMFERTYPICAL TOOTH POSITION

B

TYP.

69.0

mm

(2.7

16 in

)

AN_SB_571154_7_GAAA_02_01

Figure A-UGAAA - Sheet 02SEALANT APPLICATION - INSTRUCTION AND TOOLING



7







7




**CONF ALL

Refer to Figure A-UTAAA for the Service Bulletin reporting sheet.



7




**CONF ALL

MSNREV US DVI

NORAS

SB 57−1154 REPAIRS

YESSRM

FINDING

NOTE: ALL BOXES TO BE FILLED WITH A CROSS EXCEPT MSN AND SB REVISION COLUMNS.

EXAMPLE 0000 01 XX X

N_SB_571154_7_TAAA_01_00

Figure A-UTAAA - Sheet 01REPORTING SHEET



7




**CONF ALL

For details concerning the elapsed time assumptions, refer to the Gantt chart shown below:



7




**CONF ALL

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A320−57−1154

SB ELAPSED TIME(HOURS)

GET ACCESS

MH ET/S

TOTAL MANHOURSSB ELAPSED TIME

52.0029.50

STEPS

2.00 2.00

5 10 15 20 25 30 350

SPECIAL DETAILED ULTRASONIC INSPECTION 2.00 1.00

12.00 6.00

TESTS

CLOSE−UP 2.00 2.00

MH

ET/S:PER

MANHOURS

ELAPSED TIME PER STEPNUMBER OF PERSONS

THIS CHART IS ONLY A PROPOSAL.OPERATORS MAY DETERMINE THAT ANOTHER WAYTO DO THE WORK IS MORE SUITABLE FOR THEM.

NOTES:

PER

1

2

2

1

::

OF THE WING TOP SKIN PANEL 2 OVERHANGBETWEEN RIB 22 AND RIB 27

DETAILED VISUAL INSPECTION OF THE WINGTOP SKIN PANEL 2 EDGE AND UPPER ANDLOWER SURFACE AT RIB 22 − TRAILING EDGEFALSEWORK

8.00 4.002DETAILED VISUAL INSPECTION OF THE WINGTOP SKIN PANEL 2 EDGE AND CHAMFER ANDUPPER AND LOWER SURFACE BETWEENRIB 22 AND RIB 24

23.00 11.502DETAILED VISUAL INSPECTION OF THE WINGTOP SKIN PANEL 2 EDGE AND CHAMFER ANDUPPER AND LOWER SURFACE BETWEENRIB 24 AND RIB 27

REPAIR/REPLACEMENT OF SEALANT

2.00 2.001

1.00 1.001

N_SB_571154_7_VAAA_01_01IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURSARE NOT REFLECTED IN THIS GANTT CHART.

Figure A-UVAAA - Sheet 01ELAPSED TIME ASSUMPTION



7


@A318/A319/A320/A321SERVICE BULLETINREPORTING SHEET



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) ofembodiment:

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 tonext normal revision or prior to SB embodiment, please indicate required service(s):Either: Modification Operational Impact (MOI), if available YES/NOOr : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operationaldocumentation if this sheet is returned to Airbus and signed by a duly authorised representative. Withthe 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 automaticallyinclude them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUSCUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation ServicesFAX: (+33) 5 61 93 28 06e-mail: [email protected] via your Resident Customer Support Office.

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



7



QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported datathat you provide us will be used to analyse areas of difficulties and to take corrective action to furtherimprove the quality of our Service Bulletins.We thank you for the time you have taken in completing this form.

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

- Quality rating of this SB 4 3 2 1

- Quality rating of the Accomplishment Instructions 4 3 2 1

- Quality rating of the Illustrations 4 3 2 1

- Is this SB easy to understand ? Y / N

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

AIRBUSCUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins ManagementFAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.



7


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