@A318/A319/A320/A321

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - MAIN STRUCTURE - GEAR RIB 5 - CHANGE TO GEAR RIB

BUSHES

MODIFICATION No.: 32025J2211

This page transmits Revision No.05 of Service Bulletin No.A320-57-1118

ADDITIONAL WORK

**CONF ALL

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

REASON

Revision No. 05 issued to introduce a dye penetrant inspection, introduce a new Repair Instruction

R572-48341 and add a caution referring to the application of sealant at the bush/lug interface of Gear

Rib 5. The opportunity has been taken to issue the SB in the latest format.

CHANGES

Layout changes due to computerization of this revision are not identified.

SUMMARY

MODIFICATIONS Minor editorial or document structure change N

REASON/DESCRIPTION/OPERATIONAL

CONSEQUENCES

Minor editorial or document structure change N

GENERAL EVALUATION Minor editorial or document structure change N

MATERIAL PRICE INFORMATION Minor editorial or document structure change N

Minor editorial or document structure change N

EFFECTIVITY Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REFERENCES / REPERCUSSIONS Minor editorial or document structure change N

NATURE OF THE WORK Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

Minor editorial or document structure change N

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 1

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REVISION TRANSMITTAL SHEET

APPENDICES Minor editorial or document structure change N

Fig. A-USAAA Minor editorial or document structure change N

Fig. A-USAAA Sheet 01 Minor editorial or document structure change N

PLANNING INFORMATION

EFFECTIVITY Minor editorial or document structure change N

Configuration definition Minor editorial or document structure change N

CONF 001 Minor editorial or document structure change N

CONF 002 Minor editorial or document structure change N

Material Effectivity Minor editorial or document structure change N

Minor editorial or document structure change N

Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REASON Minor editorial or document structure change N

History Minor editorial or document structure change N

Objective/Action Minor editorial or document structure change N

Advantages Minor editorial or document structure change N

Operational/Maintenance

Consequences

Minor editorial or document structure change N

DESCRIPTION Minor editorial or document structure change N

COMPLIANCE Minor editorial or document structure change N

Classification Minor editorial or document structure change N

Accomplishment Timescale Minor editorial or document structure change N

APPROVAL Minor editorial or document structure change N

Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

Minor editorial or document structure change N

Minor editorial or document structure change N

WEIGHT AND BALANCE Minor editorial or document structure change N

ELECTRICAL LOAD DATA Minor editorial or document structure change N

REFERENCES Minor editorial or document structure change N

Minor editorial or document structure change N

Minor editorial or document structure change N

PUBLICATION AFFECTED Minor editorial or document structure change N

Minor editorial or document structure change N

INTERCHANGEABILITY/MIXABILITY Minor editorial or document structure change N

SPARES Minor editorial or document structure change N

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY Minor editorial or document structure change N

Procurement Addresses Minor editorial or document structure change N

Price and Availability Minor editorial or document structure change N

INDUSTRY SUPPORT INFORMATION Minor editorial or document structure change N

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 2

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REVISION TRANSMITTAL SHEET

LIST OF COMPONENTS Minor editorial or document structure change N

Kit 571118B01R01 Minor editorial or document structure change N

Kit 571118B02R00 Minor editorial or document structure change N

LIST OF MATERIALS - OPERATOR

SUPPLIED

Minor editorial or document structure change N

Consumable Materials Minor editorial or document structure change N

Consumable CMLB01 Minor editorial or document structure change N

Components Minor editorial or document structure change N

Equipment Minor editorial or document structure change N

PARTS TO BE RE-IDENTIFIED BY

OPERATOR

Minor editorial or document structure change N

Reidentified part set REIDB01 Minor editorial or document structure change N

Reidentified part set REIDB02 Minor editorial or document structure change N

TOOLING Minor editorial or document structure change N

Tooling - Price and Availability Minor editorial or document structure change N

Tools Minor editorial or document structure change N

Standard tool TOOLB01 Minor editorial or document structure change N

Standard tool TOOLB02 Minor editorial or document structure change N

Special Tools Minor editorial or document structure change N

ACCOMPLISHMENT INSTRUCTIONS

TASK 571118- 831-895-001-

MODIFICATION

Minor editorial or document structure change N

Task associated data - 001 Minor editorial or document structure change N

Task associated data - 002 Minor editorial or document structure change N

Subtask 571118-910-401-001 Additional references added N

Subtask 571118-839-401-001 Minor editorial or document structure change N

Subtask 571118-910-401-001 Additional references added N

Subtask 571118-839-401-001 Minor editorial or document structure change N

Subtask 571118-941-401-001 Minor editorial or document structure change N

Subtask 571118-941-401-001 Minor editorial or document structure change N

Subtask 571118-020-401-002 Minor editorial or document structure change N

Subtask 571118-210-401-001 Visual and NDT inspections added N

Subtask 571118-420-401-002 CAUTION has been added N

Subtask 571118-930-402-001 Minor editorial or document structure change N

Subtask 571118-020-401-003 Minor editorial or document structure change N

Subtask 571118-210-401-002 Visual and NDT inspections added N

Subtask 571118-420-401-003 CAUTION has been added N

Subtask 571118-930-402-002 Minor editorial or document structure change N

Subtask 571118-710-401-001 Minor editorial or document structure change N

Subtask 571118-710-401-002 Minor editorial or document structure change N

Subtask 571118-942-401-001 Minor editorial or document structure change N

Subtask 571118-942-401-001 Minor editorial or document structure change N

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 3

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REVISION TRANSMITTAL SHEET

Fig. A-UBAAA Minor editorial or document structure change N

Fig. A-UBAAA Sheet 01 Minor editorial or document structure change N

Fig. A-UBAAA Sheet 02 Minor editorial or document structure change N

Fig. A-UBAAA Sheet 03 Minor editorial or document structure change N

Fig. A-UBAAA Sheet 04 Minor editorial or document structure change N

Fig. A-UBCAA Minor editorial or document structure change N

Fig. A-UBCAA Sheet 01 Minor editorial or document structure change N

Fig. A-UBCAA Sheet 02 Minor editorial or document structure change N

Fig. A-UBEAA Minor editorial or document structure change N

Fig. A-UBEAA Sheet 01 Minor editorial or document structure change N

FILLING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

NOTE: This is only applicable for Revision No. 05 and subsequent. If information is required for

Revisions issued previous to this, please check your copies of Revision Transmittal

Sheets or contact AIRBUS.

REVISION SEQUENCE

ORIGINAL: Sep 05/02

REVISION No. : 05 - Jul 23/12

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 4

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SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - MAIN STRUCTURE - GEAR RIB 5 - CHANGE TO GEAR RIB

BUSHES

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 32025J2211

NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the

mass, balance, structural strength, reliability, operational characteristics affecting the

airworthiness of the product. All other changes are major changes.

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During accomplishment of Service Bulletin A320-57-1100 (Mod. No. 26010J1558, Inner Rear Spar -

Introduction of Interference Fit Fasteners) some operators have experienced difficulties removing and

installing the MLG rear pintle-pin at gear rib 5 on A321 aircraft. The difficulties experienced have been

due to the misalignment of the bushes in the gear rib 5 lugs which has caused interference with the

pintle-pin. Corrosion has been found in the lugs of the gear rib 5 after removal of the bushes on several

aircraft. There have also been occurrences of misalignment of the bushes and corrosion found by

operators of A320 aircraft during accomplishment of SB A320-57-1089.

Some cracks initiating from pitting corrosion and developing under fatigue loads have been identified on

the gear rib 5 fitting. In some cases, detected cracks have exceeded repairable limits leading to the

replacement of the gear rib 5 fitting.

The installation of new bushes with an increased interference level between bush and lug addresses

the movement of bushes in the lugs and the potential subsequent corrosion which may cause a crack

to develop. It has been identified that the cause of the misalignment was due to the movement of the

bushes during operation.

This Service Bulletin introduces the installation of the new bushes and the application of a sealant of a

different type.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 1

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SERVICE BULLETIN

SUMMARY

The requirements of this Service Bulletin do not apply to a MLG support rib 5 fitting that has been

repaired either:

- in accordance with A319 SRM 57-26-13 para 5C.

or

- in accordance with A320/A321 SRM 57-26-13 para 5D.

or

- in accordance with the Repair Instruction R572-58376, "Removal of corrosion/damage from Gear

Rib lugs and installation of oversize repair bushes" (A319/A320/A321) at issue C or any later issue.

or

- in accordance with the Repair Instruction R572-48341, "Removal of corrosion/damage from Gear

Rib lugs and installation of oversize repair bushes" (A319/A320/A321) at issue A or any later issue.

or

- in accordance with Repair Instruction R572-58507 "Gear Rib 5 replacement" (A319/A320) and

associated Repair Instruction R572-58209.

or

- in accordance with Repair Instruction R572-45020 "Gear Rib 5 replacement" (A321) and associated

Repair Instruction R572-45019.

Accomplishment of this Service Bulletin will significantly reduce the possibility of both bush

misalignment and corrosion in the gear rib 5 that can cause a crack to initiate and develop leading to

potential extensive repair.

Accomplishment of this Service Bulletin cancels the inspection requirements of Service Bulletin

A320-57-1138.

Aircraft that are post Service Bulletin A320-57-1118 must be inspected as per Service Bulletin

A320-57-1166.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB YES

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NORMAL JACKING YES

NOTE (1): Service Bulletin must be accomplished.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 2

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SERVICE BULLETIN

SUMMARY

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 571118B01R01 1 5,440.00 Bush

Standard tool TOOLB01 1 See SB

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 571118B02R00 1 9,290.00 Bush

Standard tool TOOLB02 1 See SB

EFFECTIVITY

**CONF ALL

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

14S 15S 15T 31V 35U 36V 47Y 53Z 56W 59Z 61T 66X 69X

73W 78T 85T 86W 86Z 98W 99W AAF AAR ABL ACA ADR AEE

AFR AGC AHY AIJ AJM AMU ANA ART AUA AVA AZA AZI B2V

BAW BEL BER BGH BIE BMA BTV C9G CCA CCM CES CIB CIT

CQH CQN CSA CSC CSN CTN CTT CYP D2F DAL DCS DLH DNV

EAA EDW EIN ETD EZD F2I FFT FHE FHY FIN FPY FRN G2X

G4I G8E GIA GIR GSW GWI HAY HDA HRM HVN I2L I2T IAC

IBE IBS IRA IRM ISS JAV JBU JET JST KAC KCA KGL KHO

KKK KMF KZR LAN LBT LBY LFO LLM LLP LMU MAU MHS MLD

MLR MMA MML MON MSR MXA NMA NVD NWS O2X OHY OZW PAL

PIC PTR QAF QTR RFJ RNV RYW RZO SAS SBI SBN SDM SFW

SGG SGX SHJ SHY SKU SLK SNX SOL STU SVR SWM SWR SYR

TAE TAI TAM TAP TAR TBJ TCW TCX THY TNA TOM UAL UDC

USA VLE VLG VLK VOI WGT WHT WTJ XLF YAP

This modification is embodied before delivery on A320 aircraft MSN 1823 and subsequent, on A321

aircraft MSN 1783 and subsequent, on A319 aircraft MSN 1774, MSN 1781 and subsequent and on

A318 aircraft MSN 1939 and subsequent.

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU 57.26.13.001

57.26.13.002

OEB None

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 3

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SERVICE BULLETIN

SUMMARY

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHERS OIT SE 999.0073/05

OTHERS OIT SE 999.0036/06

OTHERS OIT SE 999.0110/06

OTHERS OIT SE 999.0014/10

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 571118-831-895-001: MODIFICATION

TOTAL MANHOURS 73.00

ELAPSED TIME (HOURS) 40.00

**CONF 002

Task 571118-831-895-001: MODIFICATION

TOTAL MANHOURS 73.00

ELAPSED TIME (HOURS) 40.00

APPENDICES

**CONF ALL

None

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 4

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SERVICE BULLETIN

SUMMARY

**CONF ALL

N_SB_571118_7_SAAA_01_01

INNER REAR SPAR

GEAR RIB 5

A

A

Figure A-USAAA - Sheet 01

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 5

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SUMMARY

This Page Intentionally Left Blank

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 6

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SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - MAIN STRUCTURE - GEAR RIB 5 - CHANGE TO GEAR RIB

BUSHES

MODIFICATION No.: 32025J2211

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

(1) Models

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

320-211 320-212 320-214 320-231 320-232 320-233 321-111 321-112

321-131 321-211 321-212 321-231 321-232

(2) Effectivity by MSN

0029 0039 0042-0059 0061 0063-0078 0080-0090 0093-0097 0099 0102-0104

0109-0127 0135-0155 0157-0162 0164-0176 0178-0179 0181-0183 0185-0187

0189-0192 0194-0195 0197-0224 0227 0229-0237 0239-0270 0272-0279 0281-0285

0287 0289-0303 0306-0312 0314 0316-0337 0339-0343 0345-0362 0364-0373

0375-0396 0398-0432 0434-0436 0438-0452 0454-0466 0468-0480 0482-0535

0537-0546 0548-0601 0603-0627 0629-0631 0633-0707 0709-0752 0754-0788

0790-0955 0957-1043 1045-1185 1187-1217 1219-1277 1279-1373 1375-1598

1600-1659 1661-1773 1775-1780 1782 1784-1785 1787 1789 1792-1793 1797 1799

1802 1804 1806 1809 1812 1814 1816 1818 1821

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 1

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(3) Effectivity by Operator

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

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

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

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

OPERATOR MSN

14S 0283

15S 1589

15T 0764 1494

31V 0164 0332 0368 0395

35U 0088

36V 0136

47Y 0394

53Z 1468

56W 0247 0257 0327 0336

59Z 1556

61T 0407

66X 1068

69X 0219 0357 0588

73W 0087

78T 1306 1564 1725

85T 0234

86W 0384

86Z 1429

98W 0039 0042 0103 0109 0120

99W 1333

AAF 0244 0639 0808 0823 1006 1451

AAR 0802 1174 1356 1511 1636 1670 1734

ABL 1227

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

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

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

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

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

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

1623 1632 1638 1673 1719 1726 1742 1748 1772

ADR 0043 0191 0444

AEE 1727

AFR 0044 0061 0063 0102 0115 0144 0145 0155 0186 0187 0214 0227

0236 0237 0239 0270 0278 0285 0287 0337 0352 0377 0491 0498

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

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

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

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

AGC 0190

AHY 0331

AIJ 0169 0707 1132 1162 1179 1244 1259 1308 1322 1747 1780

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 2

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SERVICE BULLETIN

OPERATOR MSN

AJM 0624 0626

AMU 0557 0597 0620 0631 0805 0908 0928 1758

ANA 0139 0151 0167 0170 0212 0245 0300 0328 0365 0383 0413 0482

0501 0507 0531 0534 0549 0554 0658 0669 0685

ART 0142 0279 0310 0311 0333 0359 0426 0724

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

1387 1458 1478

AVA 1612 1618 1634

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

0576 0583 0586 0593 0599 0765 0819 0848 0940 0951 0959 0999

1138 1168 1217 1220 1448 1457 1473 1480 1489 1722 1740 1745

1770 1779

AZI 0527

B2V 0185

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

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

1513 1529 1537 1558 1574 1590 1594 1604 1606 1661 1665 1687

1689 1696 1708 1754 1760 1782 1814

BEL 0644 1086 1102 1160 1336 1388 1441 1493 1797

BER 1504 1553 1629

BGH 0221 0294 0349 1087

BIE 0519 0827 0891

BMA 1014 1177 1418 1424 1690 1711

BTV 0168 0441 0449 0460 0461 1017

C9G 0246 0772

CCA 0876 0921 1296 1753

CCM 1145

CES 0665 0754 0828 0838 0854 0883 0897 0909 0914 0925 0939 0967

0984 0986 1005 1028 1030 1041 1070 1072 1093 1108 1285 1303

1312 1316 1330 1345 1357 1361 1377 1386 1532 1541 1542 1551

1601 1603 1639 1778

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

CIT 0710

CQH 0978 1286 1372 1686 1769

CQN 0696 0698 0704 0705

CSA 0674 0684 1439 1450

CSC 0540 0550 0551 0556 0573 0582 0591 0878 0902 0912 0915 0919

1007 1013 1060 1293 1500

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

1035 1039 1057 1596 1614 1776

CTN 0258 0767 0833 1009 1029 1237 1252

CTT 1676

CYP 0256 1729 1768

D2F 0243 0251 0326 0411 0478

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 3

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SERVICE BULLETIN

OPERATOR MSN

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

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

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

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

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

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

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

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

1752 1766 1789 1812

DCS 1053

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

0116 0117 0135 0137 0147 0161 0162 0172 0200 0201 0202 0209

0216 0217 0218 0267 0268 0269 0346 0382 0401 0412 0458 0468

0473 0474 0484 0493 0502 0505 0518 0560 0563 0564 0567 0595

0609 0610 0616 0623 0627 0636 0641 0646 0651 0652 0654 0679

0689 0692 0694 0699 0700 0717 0723 0729 0738 0744 0794 0853

0860 0875 0887 0901 1016 1080 1161 1172 1188 1214 1260 1273

1337 1365 1367

DNV 1630

EAA 0386 0445

EDW 0942 0947 1026

EIN 0926 1023 1094 1242 1394 1443 1467

ETD 0350

EZD 0667 0743 0872 0874 1074

F2I 0391 0615

FFT 1515 1579 1583 1615 1684 1759 1806

FHE 0888 0936 1171 1210

FHY 0580 0771 0855

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

1544 1588 1712

FPY 0112 0189 0342 0438

FRN 0409 0466 0497

G2X 0347 1678 1735

G4I 1157

G8E 0222 0348 0369 0373 1464

GIA 0839 0892 1635

GIR 0630

GSW 0376

GWI 1077 1084 1089 1136 1147 1155 1170 1209 1277

HAY 0716 0949

HDA 0633 0756 0784 0812 0930 0993 1024 1253 1695 1721

HRM 0293 0517 0535 0642

HVN 0590 0594 0601 0605 0607 0611 0617 0619 0648 0650

I2L 0443 1407 1497

I2T 1631 1682

IAC 0045 0046 0047 0048 0049 0050 0051 0056 0057 0058 0074 0075

0080 0089 0090 0095 0096 0097 0308 0314 0396 0398 0416 0423

0431 0432 0451 0469 0486 0490 0492 0499 1668 1718

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 4

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SERVICE BULLETIN

OPERATOR MSN

IBE 0223 0274 1021 1027 1047 1059 1067 1099 1119 1154 1180 1208

1229 1247 1255 1262 1288 1292 1318 1347 1362 1530 1540 1554

1572 1655 1674 1681 1694 1716 1736 1793 1809

IBS 0158 0173 0176 0207 0224 0266 0323 0356 1101 1516

IRA 0303 0312 0345 0530 0575 0857

IRM 1202

ISS 0737 0749 1048 1125 1198 1283 1305 1715 1723

JAV 0029

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

1452 1506 1528 1546 1557 1610 1650 1705 1739 1784 1785

JET 0204 0215 0371 0421 0542 0647 0660 0816 0877

JST 1195 1408

KAC 0181 0182 0195

KCA 0393 0414

KGL 0663 0668 0787 0954

KHO 0354 0361 0362 0405

KKK 0604 0614 0675 0761 0968 0974 1124 1438 1503 1730

KMF 0480

KZR 1042 1204

LAN 1304 1332 1351 1355 1491 1512 1526 1548 1568 1626

LBT 0301 0400 0793 0937 0970 0995 1121 1175 1597 1744

LBY 0558 0561 1098

LFO 0659

LLM 1054

LLP 0739 1411

LMU 0666 0932 0943 1366

MAU 1592

MHS 1300 1353

MLD 0249 0622 0741

MLR 0977

MMA 0113 0114 0295 0316

MML 1706 1750

MON 0379 0389 0392 0864 0983 1015 1045 1081 1153 1207 1370 1428

1433 1571 1637 1707 1763

MSR 0165 0166 0178 0194 0198 0322 0351 0366 0680 0687 0715 0725

MXA 0252 0259 0260 0261 0275 0276 0296 0320 0321 0353

NMA 1697 1732

NVD 0211 0299 0375 0415 0419 0528 1263

NWS 1219 1233 1276

O2X 0291 0292 1183 1383

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

0835 0916 0963 1004 1008 1421 1482 1509

OZW 0429

PAL 0706 0745

PIC 0990

PTR 0459 0537

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SERVICE BULLETIN

OPERATOR MSN

QAF 0927 1335

QTR 1487 1566 1648 1656 1773

RFJ 0814

RNV 0229 0913

RYW 0569

RZO 0795

SAS 1587 1619 1642 1675

SBI 1071 1078 1090 1091 1126 1129 1131 1149 1164 1167

SBN 0325 0428

SDM 0427 0525 0649 1130 1488 1560 1578 1654 1657 1679 1743 1761

1767

SFW 0671 0994

SGG 0799 0879 1390

SGX 1605

SHJ 0910

SHY 0138 0148 0811 1194

SKU 0179 0406 0447 1400 1523

SLK 0899 0969 1228 1422 1561 1698

SNX 0289

SOL 0302

STU 0420 0436 0446

SVR 0140 0157 0203 0220 0735 0775 0815 0841 0991 1012 1063 1152

1199 1484 1720 1751 1777

SWM 0430 0476

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

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

0734 0782 0987 1018 1144 1762

SYR 0886 0918 1032 1076 1085 1117

TAE 0657 0934 0946

TAI 1066 1113 1334 1598 1624 1625

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

1158 1215 1246 1251 1339 1368 1376 1459 1486 1518 1575 1580

1591 1593 1595 1608 1613 1628 1652 1663 1672 1692 1703 1717

1757 1771 1775 1802 1804 1818

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

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

1307 1399 1667 1713 1756 1765 1799 1816

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

1187 1479 1700

TBJ 1485

TCW 0425 0653 1787

TCX 0424 0677 1238 1250

THY 1002

TNA 0538 0555 0606 0731 0746 0791 0822

TOM 0781 0852 1320

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SERVICE BULLETIN

OPERATOR MSN

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

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

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

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

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

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

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

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

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

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

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

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

1741 1755 1821

UDC 0085 0230 0235 0579 0645 0662 0733 0747 0760

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

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

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

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

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

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

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

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

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

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

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

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

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

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

1710 1724 1764 1792

VLE 1226

VLG 0143 0146 0199 0240 0241 0264 0992 1221 1349 1396 1413 1430

1461 1550 1749

VLK 0422 0714 0730 1200 1213 1379

VOI 1140 1159

WGT 1212

WHT 0726 1256

WTJ 0548

XLF 0343

YAP 0533 0566 0973 1454

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

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SERVICE BULLETIN

(4) Configuration by MSN

MSN CONFIGURATION

0029 0039 0042 0043 0044 0045 0046 0047 0048 0049 0050

0051 0052 0053 0054 0055 0056 0057 0058 0059 0061 0063

0064 0065 0066 0067 0068 0069 0070 0071 0072 0073 0074

0075 0076 0077 0078 0080 0081 0082 0083 0084 0085 0086

0087 0088 0089 0090 0093 0094 0095 0096 0097 0099 0102

0103 0104 0109 0110 0111 0112 0113 0114 0115 0116 0117

0118 0119 0120 0121 0122 0123 0124 0125 0126 0127 0135

0136 0137 0138 0139 0140 0141 0142 0143 0144 0145 0146

0147 0148 0149 0150 0151 0152 0153 0154 0155 0157 0158

0159 0160 0161 0162 0164 0165 0166 0167 0168 0169 0170

0171 0172 0173 0174 0175 0176 0178 0179 0181 0182 0183

0185 0186 0187 0189 0190 0191 0192 0194 0195 0197 0198

0199 0200 0201 0202 0203 0204 0205 0206 0207 0208 0209

0210 0211 0212 0213 0214 0215 0216 0217 0218 0219 0220

0221 0222 0223 0224 0227 0229 0230 0231 0232 0233 0234

0235 0236 0237 0239 0240 0241 0242 0243 0244 0245 0246

0247 0248 0249 0250 0251 0252 0253 0254 0255 0256 0257

0258 0259 0260 0261 0262 0263 0264 0265 0266 0267 0268

0269 0270 0272 0273 0274 0275 0276 0277 0278 0279 0281

0282 0283 0284 0285 0287 0289 0290 0291 0292 0293 0294

0295 0296 0297 0298 0299 0300 0301 0302 0303 0306 0307

0308 0309 0310 0311 0312 0314 0316 0317 0318 0319 0320

0321 0322 0323 0324 0325 0326 0327 0328 0329 0330 0331

0332 0333 0334 0335 0336 0337 0339 0340 0341 0342 0343

0345 0346 0347 0348 0349 0350 0351 0352 0353 0354 0355

0356 0357 0358 0359 0360 0361 0362 0365 0366 0367 0368

0369 0370 0371 0372 0373 0375 0376 0377 0378 0379 0380

0381 0382 0383 0384 0386 0387 0388 0389 0390 0391 0392

0393 0394 0395 0396 0398 0399 0400 0401 0402 0403 0404

0405 0406 0407 0408 0409 0410 0411 0413 0414 0415 0416

0417 0418 0419 0420 0421 0422 0423 0424 0425 0426 0427

0428 0429 0430 0431 0432 0435 0436 0438 0439 0440 0441

0442 0443 0444 0445 0446 0447 0448 0449 0450 0451 0452

0454 0455 0456 0457 0459 0460 0461 0462 0463 0464 0465

0466 0469 0470 0471 0472 0475 0476 0478 0479 0480 0482

0483 0485 0486 0487 0489 0490 0491 0492 0496 0497 0499

0500 0501 0503 0504 0506 0507 0508 0510 0511 0512 0523

0525 0527 0528 0530 0531 0533 0534 0537 0539 0540 0542

0543 0545 0546 0548 0549 0551 0553 0554 0556 0558 0559

0561 0562 0565 0566 0568 0569 0571 0572 0573 0574 0575

0577 0578 0579 0580 0582 0584 0585 0587 0588 0589 0590

0592 0594 0596 0598 0600 0601 0603 0605 0607 0608 0609

0610 0611 0612 0613 0615 0616 0617 0618 0619 0621 0622

0623 0624 0625 0626 0627 0629 0630 0634 0635 0636 0637

0638 0639 0640 0641 0643 0644 0645 0646 0647 0648 0649

0650 0651 0653 0654 0655 0656 0657 0658 0659 0660 0661

0662 0665 0667 0669 0670 0671 0672 0673 0676 0678 0679

0681 0682 0683 0685 0686 0688 0689 0690 0691 0693 0694

0695 0696 0697 0698 0700 0701 0702 0703 0704 0705 0706

001

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 8

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SERVICE BULLETIN

MSN CONFIGURATION

0707 0709 0710 0711 0712 0713 0714 0716 0717 0718 0719

0720 0721 0722 0723 0724 0726 0727 0728 0729 0730 0732

0733 0734 0735 0736 0737 0738 0739 0740 0741 0742 0743

0744 0745 0747 0748 0749 0750 0751 0752 0754 0755 0756

0757 0758 0759 0760 0762 0763 0764 0766 0767 0768 0769

0770 0772 0773 0774 0776 0778 0779 0780 0782 0783 0784

0785 0786 0788 0790 0791 0793 0794 0795 0797 0798 0799

0800 0801 0803 0804 0805 0807 0809 0812 0813 0814 0816

0817 0818 0820 0821 0822 0824 0825 0826 0828 0829 0830

0831 0832 0833 0834 0836 0837 0838 0839 0840 0842 0843

0844 0845 0846 0847 0849 0850 0851 0853 0854 0856 0857

0858 0859 0860 0861 0862 0863 0865 0866 0867 0868 0869

0870 0871 0872 0873 0874 0875 0876 0877 0879 0880 0881

0882 0883 0884 0885 0886 0888 0889 0890 0892 0893 0894

0895 0896 0897 0898 0899 0900 0902 0903 0904 0905 0906

0907 0909 0910 0911 0912 0913 0914 0916 0917 0918 0919

0921 0922 0923 0924 0925 0927 0928 0929 0930 0931 0932

0933 0934 0936 0937 0938 0939 0942 0943 0944 0945 0946

0947 0948 0949 0950 0951 0952 0953 0955 0957 0958 0960

0962 0964 0965 0966 0967 0969 0971 0972 0973 0975 0976

0977 0978 0979 0980 0981 0982 0984 0985 0986 0988 0989

0990 0992 0994 0996 0997 0998 0999 1000 1001 1002 1003

1005 1007 1009 1010 1011 1013 1014 1016 1018 1019 1020

1022 1025 1026 1028 1029 1030 1031 1032 1033 1034 1035

1036 1037 1038 1039 1040 1041 1043 1046 1047 1048 1049

1050 1051 1052 1053 1054 1055 1056 1057 1058 1059 1061

1062 1063 1064 1065 1066 1067 1068 1069 1070 1071 1072

1073 1074 1075 1076 1077 1078 1079 1081 1082 1083 1084

1085 1086 1087 1088 1089 1090 1091 1092 1093 1095 1096

1097 1098 1099 1100 1101 1102 1103 1104 1105 1106 1107

1108 1109 1110 1111 1112 1113 1114 1115 1116 1117 1118

1119 1120 1121 1122 1123 1124 1125 1126 1127 1128 1129

1130 1131 1132 1134 1135 1136 1137 1138 1139 1140 1141

1142 1143 1145 1146 1147 1148 1149 1150 1151 1152 1154

1155 1156 1157 1158 1159 1160 1162 1163 1164 1165 1166

1167 1168 1169 1170 1171 1172 1173 1175 1176 1177 1178

1179 1180 1181 1182 1183 1184 1187 1189 1190 1191 1192

1193 1194 1196 1197 1198 1200 1201 1203 1205 1206 1208

1209 1210 1211 1212 1213 1215 1216 1217 1221 1222 1223

1224 1225 1226 1228 1229 1230 1231 1232 1234 1235 1236

1237 1239 1240 1242 1243 1244 1245 1246 1247 1248 1249

1251 1252 1253 1254 1255 1256 1257 1258 1259 1261 1262

1263 1264 1265 1266 1267 1268 1269 1270 1271 1272 1274

1275 1277 1279 1280 1281 1282 1283 1284 1285 1286 1287

1288 1289 1290 1291 1292 1294 1295 1296 1297 1298 1300

1301 1302 1303 1304 1305 1306 1308 1309 1310 1311 1312

1313 1314 1315 1316 1317 1318 1319 1320 1321 1322 1323

1324 1325 1326 1327 1328 1329 1330 1331 1332 1334 1335

1336 1337 1338 1339 1340 1341 1342 1343 1344 1345 1346

1347 1348 1349 1350 1351 1352 1353 1354 1355 1357 1358

1359 1360 1361 1362 1363 1364 1365 1367 1368 1369 1370

001

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 9

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SERVICE BULLETIN

MSN CONFIGURATION

1371 1372 1373 1375 1376 1377 1378 1379 1380 1381 1382

1383 1384 1385 1386 1387 1388 1389 1390 1391 1392 1393

1394 1395 1396 1397 1398 1400 1401 1402 1404 1405 1406

1407 1409 1410 1411 1413 1414 1415 1416 1418 1419 1420

1422 1423 1424 1426 1427 1429 1430 1432 1434 1435 1437

1439 1440 1441 1443 1444 1445 1446 1448 1449 1450 1452

1453 1454 1456 1457 1459 1460 1461 1463 1464 1466 1467

1468 1469 1470 1471 1473 1474 1475 1477 1478 1479 1480

1482 1483 1484 1485 1486 1488 1489 1490 1491 1493 1494

1495 1497 1498 1500 1501 1502 1504 1505 1506 1507 1508

1509 1510 1512 1513 1514 1515 1516 1518 1520 1522 1523

1524 1526 1527 1528 1529 1530 1532 1533 1534 1535 1537

1538 1540 1541 1542 1543 1544 1545 1546 1547 1548 1549

1550 1551 1552 1553 1555 1556 1557 1558 1559 1560 1561

1562 1563 1564 1565 1566 1567 1568 1569 1570 1571 1573

1574 1575 1576 1577 1578 1579 1580 1581 1582 1583 1584

1585 1586 1588 1589 1590 1591 1592 1593 1594 1595 1597

1598 1600 1601 1603 1604 1605 1606 1608 1609 1610 1612

1613 1615 1616 1617 1618 1620 1621 1622 1624 1625 1626

1627 1628 1630 1631 1633 1634 1635 1637 1639 1640 1641

1643 1644 1645 1646 1647 1648 1649 1650 1652 1653 1654

1655 1656 1657 1659 1661 1662 1663 1664 1665 1667 1668

1669 1671 1672 1673 1674 1676 1677 1678 1679 1680 1682

1683 1684 1685 1686 1687 1688 1689 1692 1693 1694 1696

1697 1698 1699 1700 1702 1703 1705 1706 1708 1709 1710

1712 1714 1715 1717 1718 1719 1721 1722 1723 1725 1727

1728 1729 1730 1731 1732 1733 1735 1736 1737 1738 1739

1740 1741 1742 1743 1744 1745 1746 1747 1749 1750 1751

1752 1753 1754 1755 1756 1757 1758 1759 1760 1761 1762

1764 1765 1766 1767 1768 1769 1770 1771 1773 1775 1777

1778 1779 1780 1782 1784 1785 1787 1789 1792 1793 1797

1799 1802 1804 1806 1809 1812 1814 1816 1818 1821

001

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 10

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MSN CONFIGURATION

0364 0385 0412 0434 0458 0468 0473 0474 0477 0484 0488

0493 0494 0495 0498 0502 0505 0509 0513 0514 0515 0516

0517 0518 0519 0520 0521 0522 0524 0526 0529 0532 0535

0538 0541 0544 0550 0552 0555 0557 0560 0563 0564 0567

0570 0576 0581 0583 0586 0591 0593 0595 0597 0599 0604

0606 0614 0620 0631 0633 0642 0652 0663 0664 0666 0668

0674 0675 0677 0680 0684 0687 0692 0699 0715 0725 0731

0746 0761 0765 0771 0775 0777 0781 0787 0792 0796 0802

0806 0808 0810 0811 0815 0819 0823 0827 0835 0841 0848

0852 0855 0864 0878 0887 0891 0901 0908 0915 0920 0926

0935 0940 0941 0954 0959 0961 0963 0968 0970 0974 0983

0987 0991 0993 0995 1004 1006 1008 1012 1015 1017 1021

1023 1024 1027 1042 1045 1060 1080 1094 1133 1144 1153

1161 1174 1185 1188 1195 1199 1202 1204 1207 1214 1219

1220 1227 1233 1238 1241 1250 1260 1273 1276 1293 1299

1307 1333 1356 1366 1399 1403 1408 1412 1417 1421 1425

1428 1431 1433 1436 1438 1442 1447 1451 1455 1458 1462

1465 1472 1476 1481 1487 1492 1496 1499 1503 1511 1517

1519 1521 1525 1531 1536 1539 1554 1572 1587 1596 1602

1607 1611 1614 1619 1623 1629 1632 1636 1638 1642 1651

1658 1666 1670 1675 1681 1690 1691 1695 1701 1704 1707

1711 1713 1716 1720 1724 1726 1734 1748 1763 1772 1776

002

(5) Configuration definition

**CONF 001

Config 001 is valid for A320-200 and A319 aircraft that have not had oversized

interference fit bushes installed by Repair Instruction.

**CONF 002

Config 002 is valid for A321 aircraft that have not had oversized interference fit bushes

installed by Repair Instruction.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 571118B01R01 1

Consumable CMLB01 As required

Standard tool TOOLB01 1

Reidentified part set REIDB01 1

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 571118B02R00 1

Consumable CMLB01 As required

Standard tool TOOLB02 1

Reidentified part set REIDB02 1

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

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**CONF ALL

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During accomplishment of Service Bulletin A320-57-1100 (Mod. No. 26010J1558, Inner

Rear Spar - Introduction of Interference Fit Fasteners) some operators have experienced

difficulties removing and installing the MLG rear pintle-pin at gear rib 5 on A321 aircraft.

The difficulties experienced have been due to the misalignment of the bushes in the

gear rib 5 lugs which has caused interference with the pintle-pin. Corrosion has been

found in the lugs of the gear rib 5 after removal of the bushes on several aircraft. There

have also been occurrences of misalignment of the bushes and corrosion found by

operators of A320 aircraft during accomplishment of SB A320-57-1089.

Some cracks initiating from pitting corrosion and developing under fatigue loads have

been identified on the gear rib 5 fitting. In some cases, detected cracks have exceeded

repairable limits leading to the replacement of the gear rib 5 fitting.

(2) Objective/Action

The installation of new bushes with an increased interference level between bush and

lug addresses the movement of bushes in the lugs and the potential subsequent

corrosion which may cause a crack to develop. It has been identified that the cause of

the misalignment was due to the movement of the bushes during operation.

This Service Bulletin introduces the installation of the new bushes and the application of

a sealant of a different type.

The requirements of this Service Bulletin do not apply to a MLG support rib 5 fitting that

has been repaired either:

- in accordance with A319 SRM 57-26-13 para 5C.

or

- in accordance with A320/A321 SRM 57-26-13 para 5D.

or

- in accordance with the Repair Instruction R572-58376, "Removal of

corrosion/damage from Gear Rib lugs and installation of oversize repair bushes"

(A319/A320/A321) at issue C or any later issue.

or

- in accordance with the Repair Instruction R572-48341, "Removal of

corrosion/damage from Gear Rib lugs and installation of oversize repair bushes"

(A319/A320/A321) at issue A or any later issue.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 12

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or

- in accordance with Repair Instruction R572-58507 "Gear Rib 5 replacement"

(A319/A320) and associated Repair Instruction R572-58209.

or

- in accordance with Repair Instruction R572-45020 "Gear Rib 5 replacement" (A321)

and associated Repair Instruction R572-45019.

(3) Advantages

Accomplishment of this Service Bulletin will significantly reduce the possibility of both

bush misalignment and corrosion in the gear rib 5 that can cause a crack to initiate and

develop leading to potential extensive repair.

Accomplishment of this Service Bulletin cancels the inspection requirements of Service

Bulletin A320-57-1138.

Aircraft that are post Service Bulletin A320-57-1118 must be inspected as per Service

Bulletin A320-57-1166.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 571118-831-895-001: MODIFICATION

(1) Removal of Bushes

(2) Inspection of Gear Rib 5

(3) Bush Installation

(4) Re-identify the Gear Rib 5

**CONF 002

Task 571118-831-895-001: MODIFICATION

(1) Removal of Bushes

(2) Inspection of Gear Rib 5

(3) Bush Installation

(4) Re-identify the Gear Rib 5

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

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**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

The accomplishment of this Service Bulletin is required within 5 years following the

effective date of the Airworthiness Directive (AD);

Accomplishment of this Service Bulletin has been rendered mandatory by the issue of an

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

The AD must be used as the reference document for the mandatory accomplishment

timescale.

F. APPROVAL

The technical content of this document is approved under the authority of Design

Organisation Approval No. EASA 21J.031.

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

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

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

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

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

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

included.

**CONF 001

Task 571118-831-895-001: MODIFICATION

Get Access 1.50

On Aircraft

Removal of Bushes 18.00

Inspection of Gear Rib 5 32.00

Bush Installation 17.50

Re-identify the Gear Rib 5 0.50

Tests 2.00

Close-Up 1.50

TOTAL MANHOURS 73.00

ELAPSED TIME (HOURS) 40.00

NOTE: If the repair procedure given in Repair Instruction R572-48341, "Removal of

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 14

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corrosion/damage from the Gear Rib Lugs and Installation of Oversize Repair

Bushes" is necessary, then approximately 56.0 manhours for each wing will

need to be added for Modification.

**CONF 002

Task 571118-831-895-001: MODIFICATION

Get Access 1.50

On Aircraft

Removal of Bushes 18.00

Inspection of Gear Rib 5 32.00

Bush Installation 17.50

Re-identify the Gear Rib 5 0.50

Tests 2.00

Close-Up 1.50

TOTAL MANHOURS 73.00

ELAPSED TIME (HOURS) 40.00

NOTE: If the repair procedure given in Repair Instruction R572-48341, "Removal of

corrosion/damage from the Gear Rib Lugs and Installation of Oversize Repair

Bushes" is necessary, then approximately 56.0 manhours for each wing will

need to be added for Modification.

**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 07-11-00 27-54-00 27-54-45

32-11-11

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

Non Destructive Test Manual (NTM) 51-10-02 51-80-00

Process and Material Specification (PMS) Process and Material Specification

(PMS) 01-06-12

Structural Repair Manual (SRM) 51-21-11 51-24-00 51-72-12

**CONF 002

Aircraft Maintenance Manual (AMM) 07-11-00 27-54-00 27-54-45

32-11-11

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

Non Destructive Test Manual (NTM) 51-10-02 51-81-00

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 15

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Process and Material Specification (PMS) Process and Material Specification

(PMS) 01-06-12

Structural Repair Manual (SRM) 51-21-11 51-24-00 51-72-12

**CONF ALL

K. PUBLICATION AFFECTED

Illustrated Parts Catalog (IPC) 57-26-05

Maintenance Planning Document (MPD) 575150-01

Structural Repair Manual (SRM) 57-26-13

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 16

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2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Kit 571118B01R01

Kit 571118B02R00

Customers with aircraft shown in the

effectivity of this Service Bulletin should send

a purchase order to AIRBUS. Quote the

number of this Service Bulletin. The address

is:

AIRBUS Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 Hamburg

Germany

For ordering by internet:

http://spares.airbus.com

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

For ordering by E-mail: airbus.kit@airbus.com

(2) Price and Availability

Kit 571118B01R01

Cost 5,440.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require the Kit(s) before this time, please include a retrofit planning

schedule with your order so that we can try to comply with your requirements.

Kit 571118B02R00

Cost 9,290.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require the Kit(s) before this time, please include a retrofit planning

schedule with your order so that we can try to comply with your requirements.

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will provide the material at no charge for orders placed before 31 Dec 2012. AIRBUS

will also credit the manhours indicated in this Service Bulletin at the operator’s agreed inhouse warranty labor rate upon receipt of a warranty claim.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 17

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C. LIST OF COMPONENTS

Kit 571118B01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

2 D5725102300800 2 Bush (2) D5725102300000

(2) D5725102300200 (1)

(2) D5725102300400 (1)

(2) D5725102300600 (1)

3 D5725102200200 2 Bush (3) D5725102200000

4 D5725102100200 2 Bush (4) D5725102100000

NOTE (1): Alternative bushes D5725102300400 and D5725102300600, Item (2) may be

installed on A320-200 and A319 aircraft.

Kit 571118B02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

2 D5725926600200 2 Bush (2) D5725926600000

3 D5725926700200 2 Bush (3) D5725926700000

4 D5725926800200 2 Bush (4) D5725926800000

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Anaerobic 08-003 As required

Fuel Tank Sealant Polysulfide 09-002 As required

Low Adhesion Polysulfide Sealant 09-019C As required

Adhesion Promoter For Polysulfide

Sealant

09-028 As required

Solvent General Purpose 11-026 As required

Chemical Conversion Coating

Yellow Aluminum

13-002 As required

Anti-Corrosion Primer 16-006 As required

External Top Coat 16-018 As required

Polyurethane Gloss Finish (Clear

Basecoat)

16-021B As required (1)

Lint-Free Cotton Cloth 19-003 As required

Marker Pen 8404 As required (2)

NOTE (1): Mat. No. 07-018 is an alternative lacquer to Mat. No. 16-021B when

used to protect written part numbers.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 18

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NOTE (2): The Marker Pen 8404 can be procured from:

Edding (UK) Ltd.

Merlin Centre

Acrewood Way

St Albans

Herts.

England

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

Reidentify Gear Rib by marking the SB Number "SB A320-57-1118" adjacent to the old part

number.

Reidentified part set REIDB01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

D5725101700000 Gear Rib D5725101700000

D5725101700100 Gear Rib D5725101700100

D5725101700200 Gear Rib D5725101700200

D5725101700300 Gear Rib D5725101700300

D5725218100000 Gear Rib D5725218100000

D5725218100100 Gear Rib D5725218100100

D5725218100200 Gear Rib D5725218100200

D5725218100300 Gear Rib D5725218100300

D5725218100400 Gear Rib D5725218100400

D5725218100500 Gear Rib D5725218100500

D5725218100600 Gear Rib D5725218100600

D5725218100700 Gear Rib D5725218100700

Reidentified part set REIDB02

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

D5725551100000 Gear Rib D5725551100000

D5725551100100 Gear Rib D5725551100100

D5725918100000 Gear Rib D5725918100000

D5725918100100 Gear Rib D5725918100100

D5725918100200 Gear Rib D5725918100200

D5725918100300 Gear Rib D5725918100300

D5725918100400 Gear Rib D5725918100400

D5725918100500 Gear Rib D5725918100500

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 19

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F. TOOLING

(1) Tooling - Price and Availability

If the repair procedure given in Repair Instruction R572-48341, "Removal of

corrosion/damage from Gear Rib lugs and installation of oversize repair bushes" is

necessary, then the tool kit 7K800256D044 which contains the In-line Boring Fixture

Tool will be necessary.

It is acceptable to use the tool kit 7K800256D044 in place of the tool kits

98D57004025000 or 98D57004025001.

(2) Tools

NOTE: Each kit includes:

- In-line Honing Tool

- Facing Tool

- Alignment Tool

- Removal/Installation Tool

The In-line Honing Tool comprises (Refer to Drawing 98D57004025):

- 1 Alignment Hone MT58133/170 (item 65)

- 2 Finishing Stones N2F6C (item 68)

- 2 Roughing Stones N2F3C (item 67)

- 4 Plastic Guides N2 (item 66)

The Finishing and Roughing Stones are supplied as a set complete with

two aluminium guides.

The Facing Tool comprises (Refer to Drawing 98D57004025):

- Spacing Bush 98D57004025-230 (item 28)

- Hollow Location Shaft D57004025-214 (item 20)

- Clamp Fork 98D57004025-222 (item 24)

- Nylon Washer 98D57004025-224 (item 25)

- Clamp Collar 98D57004025-218 (item 22)

- Clamp Stud 98D57004025-228 (item 27)

- Cutter Shaft 98D57004025-216 (item 21)

- Bearing 51204 (item 42)

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 20

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- Collar Nut 404-207 (item 41)

- Lathe Tool 98D57004025-248 (item 44)

- Spacer Clamp 98D57004025-226 (item 26)

- Packer 98D57004025-232 (item 45)

- Depth Stop 98D57004025-220 (item 23)

- Grub screw (item 43)

- Hex bolt (item 46)

- Socket Hd cap screw (item 47)

The Alignment Tool is the Truing Sleeve MT19003 (item 64)

The Removal/Installation Tool comprises (Refer to Drawing

98D57004000):

- Reaction Block 98D57004000-200 (item 0)

- Bolt 98D57004000-208 (item 1)

- Nut 98D57004000-210 (item 2)

- Washer 98D57004000-212 (item 3)

- Location Block 98D57004000-202 (item 4)

- Split Location Ring 98D57004000-204 (item 5)

- Socket Hd cap screw (item 6)

- Installation Block 98D57004000-206 (item 7)

- Sleeve 98D57004000-214 (item 8)

- Nut (item 9)

- Block R/I D57004000-216 (item 10)

The kit is a tool kit designed for the repair of the pintle bushes in the

gear rib 5. It will be required to:

- remove and install the bushes,

- line-hone the bushes to the finished internal diameter after

installation,

- machine the flange of the bush, Item 2.

You can get the kit(s) from AIRBUS.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 21

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If Repair Instruction R572-48341 Issue A, is necessary, then the tool kit

7K800256D044 which contains the In-line Boring Fixture Tool will be

necessary.

It is acceptable to use the tool kit 7K800256D044 in place of the tool kits

98D57004025000 or 98D57004025001.

Standard tool TOOLB01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

98D57004025000 Kit, Rem.-Inst. - Pintle Bushes 1

NOTE: Each kit includes:

- In-line Honing Tool

- Facing Tool

- Alignment Tool

- Removal/Installation Tool

The In-line Honing Tool comprises (Refer to Drawing 98D57004025):

- 1 Alignment Hone MT58133/170 (item 65)

- 2 Finishing Stones N2F6C (item 68)

- 2 Roughing Stones N2F3C (item 67)

- 4 Plastic Guides N2 (item 66)

The Finishing and Roughing Stones are supplied as a set complete with

two aluminium guides.

The Facing Tool comprises (Refer to Drawing 98D57004025):

- Spacing Bush 98D57004025-230 (item 28)

- Hollow Location Shaft D57004025-214 (item 20)

- Clamp Fork 98D57004025-222 (item 24)

- Nylon Washer 98D57004025-224 (item 25)

- Clamp Collar 98D57004025-218 (item 22)

- Clamp Stud 98D57004025-228 (item 27)

- Cutter Shaft 98D57004025-216 (item 21)

- Bearing 51204 (item 42)

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 22

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- Collar Nut 404-207 (item 41)

- Lathe Tool 98D57004025-248 (item 44)

- Spacer Clamp 98D57004025-226 (item 26)

- Packer 98D57004025-232 (item 45)

- Depth Stop 98D57004025-220 (item 23)

- Grub screw (item 43)

- Hex bolt (item 46)

- Socket Hd cap screw (item 47)

The Alignment Tool is the Truing Sleeve MT19003 (item 64)

The Removal/Installation Tool comprises (Refer to Drawing

98D57004000)

- Reaction Block 98D57004000-200 (item 0)

- Bolt 98D57004000-208 (item 1)

- Nut 98D57004000-210 (item 2)

- Washer 98D57004000-212 (item 3)

- Location Block 98D57004000-202 (item 4)

- Split Location Ring 98D57004000-204 (item 5)

- Socket Hd cap screw (item 6)

- Installation Block 98D57004000-206 (item 7)

- Sleeve 98D57004000-214 (item 8)

- Nut (item 9)

- Block R/I D57004000-216 (item 10)

The kit is a tool kit designed for the repair of the pintle bushes in the

gear rib 5. It will be required to:

- remove and install the bushes,

- line-hone the bushes to the finished internal diameter after

installation,

- machine the flange of the bush, Item 2.

You can get the kit(s) from AIRBUS.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 23

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If the repair procedure given in Repair Instruction R572-48341 Issue B

"Removal of corrosion/damage from Gear Rib lugs and installation of

oversize repair bushes" is necessary, then the tool kit 7K800256D044

which contains the In-line Boring Fixture Tool will be necessary.

It is acceptable to use the tool kit 7K800256D044 in place of the tool kits

98D57004025000 or 98D57004025001.

Standard tool TOOLB02

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

98D57004025001 Kit, Rem.-Inst. - Pintle Bushes 1

NOTE: Each kit includes:

- In-line Honing Tool

- Facing Tool

- Alignment Tool

- Removal/Installation Tool

The In-line Honing Tool comprises (Refer to Drawing 98D57004025):

- 1 Alignment Hone MT58133/170 (item 65)

- 2 Finishing Stones N2F6C (item 68)

- 2 Roughing Stones N2F3C (item 67)

- 4 Plastic Guides N2 (item 66)

The Finishing and Roughing Stones are supplied as a set complete with

two aluminium guides.

The Facing Tool comprises (Refer to Drawing 98D57004025):

- Spacing Bush 98D57004025-242 (item 63)

- Hollow Location Shaft 98D57004025-236 (item 60)

- Clamp Fork 98D57004025-222 (item 24)

- Nylon Washer 98D57004025-240 (item 62)

- Clamp Collar 98D57004025-238 (item 61)

- Clamp Stud 98D57004025-228 (item 27)

- Cutter Shaft 98D57004025-216 (item 21)

- Bearing 51204 (item 42)

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 24

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- Collar Nut 404-207 (item 41)

- Lathe Tool 98D57004025-248 (item 44)

- Spacer Clamp 98D57004025-226 (item 26)

- Packer 98D57004025-232 (item 45)

- Depth Stop 98D57004025-220 (item 23)

The Alignment Tool is the Truing Sleeve MT19003 (item 64)

The Removal/Installation Tool comprises (Refer to Drawing

98D57004080):

- Split Location Ring 98D57004080-200 (item 0)

- Reaction Block 98D57004080-202 (item 1)

- Installation Block 98D57004080-204 (item 2)

- Block R/I 98D57004080-206 (item 3)

- Bolt 98D57004080-208 (item 4)

- Washer 98D57004080-210 (item 5)

- Nut 98D57004080-212 (item 6)

- Location Block 98D57004080-214 (item 7)

- Sleeve 98D57004080-216 (item 8)

- Socket Hd cap screw (item 9)

- Nut (item 10)

The kit is a tool kit designed for the repair of the pintle bushes in the

gear rib 5. It will be required to:

- remove and install the bushes,

- line-hone the bushes to the finished internal diameter after

installation,

- machine the flange of the bush, Item 2.

You can get the kit(s) from AIRBUS.

If the repair procedure given in Repair Instruction R572-48341, "Removal

of corrosion/damage from Gear Rib lugs and installation of oversize

repair bushes is necessary, then the tool kit 7K800256D044 which

contains the In-line Boring Fixture Tool will be necessary.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 25

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It is acceptable to use the tool kit 7K800256D044 in place of the tool kits

98D57004025000 or 98D57004025001.

(3) Special Tools

None

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 26

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 571118-831-895-001 - MODIFICATION

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC. AS

NECESSARY ON WIRING AND COMPONENTS

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

Task Associated Data

**CONF 001

Zone

730 740

Manpower

TOTAL MANHOURS 73.00

ELAPSED TIME (HOURS) 40.00

**CONF 002

Zone

730 740

Manpower

TOTAL MANHOURS 73.00

ELAPSED TIME (HOURS) 40.00

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 27

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**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 571118-910-401-001 - STANDARD PRACTICES

Manpower Resources

Skills AIRFRAME

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Marker Pen 8404 As required (1)

NOTE (1): The Marker Pen 8404 can be procured from:

Edding (UK) Ltd.

Merlin Centre

Acrewood Way

St Albans

Herts.

England

References

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-06-12

Structural Repair Manual (SRM) 51-21-11

51-24-00

51-72-12

(a) For part marking use:

Marker Pen 8404 As required

and refer to Process and Material Specification (PMS) 01-06-12 and Para. 2.D. and

2.E.

(b) Application of protective treatments (Refer to SRM 51-21-11).

(c) Application of sealants (Refer to SRM 51-24-00).

(d) Replacement of bushes (Refer to SRM 51-72-12).

(2) Subtask 571118-839-401-001 - ADMINISTRATIVE

Manpower Resources

Skills AIRFRAME

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

Service Bulletin.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 28

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**CONF 002

(1) Subtask 571118-910-401-001 - STANDARD PRACTICES

Manpower Resources

Skills AIRFRAME

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Marker Pen 8404 As required (1)

NOTE (1): The Marker Pen 8404 can be procured from:

Edding (UK) Ltd.

Merlin Centre

Acrewood Way

St Albans

Herts.

England

References

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-06-12

Structural Repair Manual (SRM) 51-21-11

51-24-00

51-72-12

(a) For part marking use:

Marker Pen 8404 As required

and refer to Process and Material Specification (PMS) 01-06-12 and Para. 2.D. and

2.E.

(b) Application of protective treatments (Refer to SRM 51-21-11).

(c) Application of sealants (Refer to SRM 51-24-00).

(d) Replacement of bushes (Refer to SRM 51-72-12).

(2) Subtask 571118-839-401-001 - ADMINISTRATIVE

Manpower Resources

Skills AIRFRAME

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

Service Bulletin.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 29

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**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 571118-941-401-001 - JOB SET-UP

Work Zones and Access Panels

Zone Access/Work location

730

740

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 07-11-00, Page Block 201

27-54-45, Page Block 401

32-11-11, Page Block 401

(a) Lift the aircraft on jacks (Refer to AMM 07-11-00 Page Block 201).

NOTE: It is recommended that the jacks used to lift the aircraft have a

function to control the load. This will be necessary to prevent new

jacking, if it is found that the gear rib fitting has to be replaced.

(b) Remove the LH and RH MLG legs (Refer to AMM 32-11-11 Page Block 401).

(c) Put access platforms in Zones 730/740.

(d) Remove the torque shaft 6208CM (6258CM) (Refer to AMM 27-54-45 Page Block

401).

NOTE: Removal of the torque shaft is recommended to allow for removal /

installation of the bushes and for clearance when the honing tool is

used.

**CONF 002

(1) Subtask 571118-941-401-001 - JOB SET-UP

Work Zones and Access Panels

Zone Access/Work location

730

740

Manpower Resources

Skills AIRFRAME

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 30

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References

Aircraft Maintenance Manual (AMM) 07-11-00, Page Block 201

27-54-45, Page Block 401

32-11-11, Page Block 401

(a) Lift the aircraft on jacks (Refer to AMM 07-11-00 Page Block 201).

NOTE: It is recommended that the jacks used to lift the aircraft have a

function to control the load. This will be necessary to prevent new

jacking, if it is found that the gear rib fitting has to be replaced.

(b) Remove the LH and RH MLG legs (Refer to AMM 32-11-11 Page Block 401).

(c) Put access platforms in Zones 730/740.

(d) Remove the torque shaft 6208CM (6258CM) (Refer to AMM 27-54-45 Page Block

401).

NOTE: Removal of the torque shaft is recommended to allow for removal /

installation of the bushes and for clearance when the honing tool is

used.

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 571118-020-401-002 - Removal of Bushes

Manpower Resources

Manhours 18.00

Minimum number of person 2

Subtask elapsed time 9.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

Standard tool TOOLB01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

98D57004025000 Kit, Rem.-Inst. - Pintle

Bushes

1

NOTE: Each kit includes:

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 31

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SERVICE BULLETIN

- In-line Honing Tool

- Facing Tool

- Alignment Tool

- Removal/Installation Tool

The In-line Honing Tool comprises (Refer to Drawing 98D57004025):

- 1 Alignment Hone MT58133/170 (item 65)

- 2 Finishing Stones N2F6C (item 68)

- 2 Roughing Stones N2F3C (item 67)

- 4 Plastic Guides N2 (item 66)

The Finishing and Roughing Stones are supplied as a set complete with

two aluminium guides.

The Facing Tool comprises (Refer to Drawing 98D57004025):

- Spacing Bush 98D57004025-230 (item 28)

- Hollow Location Shaft D57004025-214 (item 20)

- Clamp Fork 98D57004025-222 (item 24)

- Nylon Washer 98D57004025-224 (item 25)

- Clamp Collar 98D57004025-218 (item 22)

- Clamp Stud 98D57004025-228 (item 27)

- Cutter Shaft 98D57004025-216 (item 21)

- Bearing 51204 (item 42)

- Collar Nut 404-207 (item 41)

- Lathe Tool 98D57004025-248 (item 44)

- Spacer Clamp 98D57004025-226 (item 26)

- Packer 98D57004025-232 (item 45)

- Depth Stop 98D57004025-220 (item 23)

- Grub screw (item 43)

- Hex bolt (item 46)

- Socket Hd cap screw (item 47)

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 32

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The Alignment Tool is the Truing Sleeve MT19003 (item 64)

The Removal/Installation Tool comprises (Refer to Drawing

98D57004000)

- Reaction Block 98D57004000-200 (item 0)

- Bolt 98D57004000-208 (item 1)

- Nut 98D57004000-210 (item 2)

- Washer 98D57004000-212 (item 3)

- Location Block 98D57004000-202 (item 4)

- Split Location Ring 98D57004000-204 (item 5)

- Socket Hd cap screw (item 6)

- Installation Block 98D57004000-206 (item 7)

- Sleeve 98D57004000-214 (item 8)

- Nut (item 9)

- Block R/I D57004000-216 (item 10)

The kit is a tool kit designed for the repair of the pintle bushes in the

gear rib 5. It will be required to:

- remove and install the bushes,

- line-hone the bushes to the finished internal diameter after

installation,

- machine the flange of the bush, Item 2.

You can get the kit(s) from AIRBUS.

If the repair procedure given in Repair Instruction R572-48341 Issue B

"Removal of corrosion/damage from Gear Rib lugs and installation of

oversize repair bushes" is necessary, then the tool kit 7K800256D044

which contains the In-line Boring Fixture Tool will be necessary.

It is acceptable to use the tool kit 7K800256D044 in place of the tool kits

98D57004025000 or 98D57004025001.

References

Fig. A-UBAAA

Gear Rib 5 Bushes

Sheet 01

Sheet 02

Sheet 03

Sheet 04

NOTE: The worksteps that follow are done on the LH and the RH wings.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 33

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SERVICE BULLETIN

Refer to Fig. A-UBAAA Sheet 01 Fig. A-UBAAA Sheet 02 Fig. A-UBAAA Sheet 03 Fig.

A-UBAAA Sheet 04

(a) Remove and retain the anti-rotation washer, Item (1).

(b) Clean all unwanted material from the anti-rotation washer, Item (1) with a plastic

spatula and use:

Solvent General

Purpose

11-026 As required

(c) Use the Removal/Installation Tool from the Tool Kit:

98D57004025000 Kit, Rem.-Inst. -

Pintle Bushes

1

to remove these items:

1 Bush D5725102300000 Item (2) Discard

or

1 Bush D5725102300200 Item (2) Discard

or

2 Bush D5725102300400 Item (2) Discard

or

2 Bush D5725102300600 Item (2) Discard

1 Bush D5725102200000 Item (3) Discard

1 Bush D5725102100000 Item (4) Discard

NOTE: Remove the Bush, Item (4) before removal of the bushes, Items (2)

and (3).

(2) Subtask 571118-210-401-001 - Inspection of Gear Rib 5

Manpower Resources

Manhours 32.00

Minimum number of person 2

Subtask elapsed time 16.00

Skills AIRFRAME

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 34

7

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SERVICE BULLETIN

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Non Destructive Test Manual (NTM) 51-10-02

51-80-00

Fig. A-UBAAA

Gear Rib 5 Bushes

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Refer to Fig. A-UBAAA Sheet 01

(a) Visually inspect the gear rib forward lug bore to make sure that no liner bushes are

installed. If there are, report details to AIRBUS and await further instructions.

(b) Clean the bore, lug faces and chamfer of all unwanted material with a plastic

spatula and

Solvent General

Purpose

11-026 As required

(c) Do a visual inspection of the bores, spotfaces and chamfers of the lugs for the

pintle-pin bushes for corrosion/damage (Refer to NTM 51-10-02).

(d) Do a liquid penetrant inspection of the bores, spotfaces and chamfers of the lugs

for the pintle-pin bushes for corrosion/damage (Refer to NTM 51-80-00).

(e) Make sure that the dimension E (forward lug bore diameter) is between these

limits:

- 96.000 to 96.035 mm.

(f) Make sure that the dimension D (rear lug bore diameter) is between these limits:

- 106.000 to 106.035 mm.

(g) Make sure that the forward lug thickness across the existing spotfaces is between

these limits:

- 52.50 to 52.70 mm.

(h) If any dimensions are outside of limits, report details to AIRBUS and await further

instructions.

(i) If no damage is found do SUBTASK 571118-420-401 002 Bush Installation

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 35

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(j) If damage/corrosion is found, refer to the latest issue of Repair Instruction

R572-48341, "Removal of corrosion/damage from Gear Rib lugs and installation of

oversize repair bushes".

NOTE: The Repair Instruction reference includes the procedure for using

the In-line Boring Fixture Tool and for the installation of oversize

bushes.

(3) Subtask 571118-420-401-002 - Bush Installation

Manpower Resources

Manhours 17.50

Minimum number of person 2

Subtask elapsed time 8.75

Skills AIRFRAME

Material necessary to do the job

Kit 571118B01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 D5725102300800 2 Bush

3 D5725102200200 2 Bush

4 D5725102100200 2 Bush

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Anaerobic 08-003 As required

Fuel Tank Sealant

Polysulfide

09-002 As required

Low Adhesion Polysulfide

Sealant

09-019C As required

Adhesion Promoter For

Polysulfide Sealant

09-028 As required

Solvent General Purpose 11-026 As required

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Anti-Corrosion Primer 16-006 As required

External Top Coat 16-018 As required

Polyurethane Gloss Finish

(Clear Basecoat)

16-021B As required (1)

Lint-Free Cotton Cloth 19-003 As required

NOTE (1): Mat. No. 07-018 is an alternative lacquer to Mat. No. 16-021B when

used to protect written part numbers.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 36

7

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SERVICE BULLETIN

References

Fig. A-UBAAA

Gear Rib 5 Bushes

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-UBCAA

In-line Honing Tool

Sheet 01

Sheet 02

Fig. A-UBEAA

Facing Tool

Sheet 01

Refer to Fig. A-UBAAA Sheet 01 Fig. A-UBAAA Sheet 02 Fig. A-UBAAA Sheet 03 Fig.

A-UBAAA Sheet 04 and Fig. A-UBCAA Sheet 01 Fig. A-UBCAA Sheet 02 and Fig. AUBEAA Sheet 01

(a) Before installing the bushes check that the overall dimension G across the bushes,

items 2 and 3 is likely to be achieved. This can be done by measuring the

thickness of the lug and the thickness of the flange on the two bushes and adding

them together. This dimension should be between 68.50 and 68.60 mm. If this

dimension is outside the tolerance, report details to AIRBUS and await further

instructions.

(b) Re-protect surface finishes if there is visible damage to the surface protection or

the surface protection has been removed during inspection.

1 Apply:

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

to the chamfer, bore and the spotfaces of the lug.

2 Wash off excess Chemicals and make sure sufficient drying time is allowed.

3 Apply:

Anti-Corrosion

Primer

16-006 As required

to the chamfer and spotfaces of the lug and the mating surface for the seat of

the bush flange.

(c) Apply

Sealant, Anaerobic 08-003 As required

to the lug bore.

WARNING: LIQUID NITROGEN IS DANGEROUS. OBEY THE MANUFACTURERS

INSTRUCTIONS AND WEAR THE CORRECT PROTECTIVE

CLOTHING WHEN YOU USE LIQUID NITROGEN.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 37

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SERVICE BULLETIN

CAUTION: DO NOT PUT MORE THAN ONE BUSH AT A TIME INTO THE LIQUID

NITROGEN, USE CLEAN TONGS TO REMOVE THE BUSH FROM

THE LIQUID NITROGEN AND TO INSTALL IT IN THE BORE OF THE

LUG.

(d) Install:

2 Bush D5725102300800 Item 2

2 Bush D5725102200200 Item 3

2 Bush D5725102100200 Item 4

1 To make sure that the bush remains cold enough so that the risk of the bush

interfering with the bore on installation is minimized, the bush and mandrel

(assembled) must be immersed in liquid nitrogen for at least 30 minutes

immediately prior to installation.

2 Freeze each bush in sequence in liquid nitrogen for not less than 30 minutes.

3 Install each bush in sequence in the applicable end of the bore of the forward

lug of the aft gear-rib bearing. Make sure that the bushes are fully installed.

4 Clamp each bush firmly immediately after installation and then allow the

assembly to return to ambient temperature, allow the sealant to cure

fully to prevent any bush migration. Before the sealant cures, use the

removal/installation tool, Item 8 (from Tool Kit 98D57004025000) to make sure

that the bush is fully installed.

(e) Make sure that the overall dimension G across the bushes, items 2 and 3 is

between 68.50 and 68.60 mm. If this dimension is outside the tolerance, report

details to AIRBUS and await further instructions.

(f) Make sure the clearance dimension between the bushes, Item 2 and Item 3 is free

of sealant.

(g) Prior to honing it is recommended that the permanent four stage sealing procedure

is applied and the full cure time of the surface protection and sealants is allowed,

before proceeding further. However, it is acceptable to continue immediately with

the repair (honing the bushes) provided a temporary fillet seal is applied as follows:

1 Apply a temporary fillet seal around the bush heads. Use:

Low Adhesion

Polysulfide Sealant

09-019C As required

and leave until no longer tacky.

(h) Refer to Fig. A-UBCAA Sheet 01 Fig. A-UBCAA Sheet 02 and Fig. A-UBEAA Sheet

01

1 Assemble the in-line honing tool as shown.

2 Use the alignment tool to set up the in-line honing tool.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 38

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SERVICE BULLETIN

CAUTION: USE ONLY DELAPENA NO. 6 HONING FLUID (MAT. NO.

06-010).

3 Use the in-line honing tool to get the dimension C between these limits:

- 98.000 to 98.035 mm.

4 Use the in-line honing tool to get the dimension F between these limits:

- 88.000 to 88.035 mm.

NOTE: The dimensions C and F must be concentric with each other to

within a diameter of 0.02 mm.

5 If necessary, use the facing tool to machine the face of the bush, Item 2 to get

the dimension G between these limits:

- 68.50 to 68.60 mm.

NOTE: If you do not have the facing tool, as an alternative the face of

the bush Item 2 can be machined to the correct dimension

before installation.

NOTE: The machined face of the bush, item 2, must be perpendicular

to the final bore (dimension F ) within 0.05 mm.

(i) Use

Solvent General

Purpose

11-026 As required

to clean the area.

(j) Install the anti-rotation washer, Item (1) as follows:

1 Apply

Fuel Tank Sealant

Polysulfide

09-002 As required

to the contact surfaces of the anti-rotation washer, Item (1) and the mating

face of the gear rib.

2 Allow the sealant to cure and use:

Lint-Free Cotton

Cloth

19-003 As required

made moist with:

Solvent General

Purpose

11-026 As required

to remove any unwanted sealant.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 39

7

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SERVICE BULLETIN

CAUTION: THE PROCEDURE THAT FOLLOWS APPLIES A 3 STAGE PROCESS

TO MAKE SURE A ROBUST SEALING OF THE BUSH TO LUG.

DEVIATION FROM THIS PROCESS CAN ALLOW THE INTEGRITY

OF THE SEAL TO BE COMPROMISED.

(k) Apply:

Adhesion Promoter

For Polysulfide

Sealant

09-028 As required

around the flanges of the bushes, Items 3 and 4, and the lug face.

(l) Apply a continuous bead of sealant around the edges of the bushes, Items 3 and 4

to form a fillet seal, use:

Fuel Tank Sealant

Polysulfide

09-002 As required

leave until it is no longer tacky.

(m) Apply:

External Top Coat 16-018 As required

to the fillet seals to protect the sealant from hydraulic fluid.

(n) Apply:

Polyurethane Gloss

Finish (Clear

Basecoat)

16-021B As required

to the fillet seals to protect the sealant from hydraulic fluid.

NOTE: To prevent contamination/damage to the sealant and coatings, it is

required that the assembly is left to fully cure. Heaters (optional)

may be used to reduce the sealant cure time.

(4) Subtask 571118-930-402-001 - Re-identify the Gear Rib 5

Manpower Resources

Manhours 0.50

Minimum number of person 2

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 40

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Material necessary to do the job

Reidentified part set REIDB01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

D5725101700000 Gear Rib D5725101700000

D5725101700100 Gear Rib D5725101700100

D5725101700200 Gear Rib D5725101700200

D5725101700300 Gear Rib D5725101700300

D5725218100000 Gear Rib D5725218100000

D5725218100100 Gear Rib D5725218100100

D5725218100200 Gear Rib D5725218100200

D5725218100300 Gear Rib D5725218100300

D5725218100400 Gear Rib D5725218100400

D5725218100500 Gear Rib D5725218100500

D5725218100600 Gear Rib D5725218100600

D5725218100700 Gear Rib D5725218100700

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polyurethane Gloss Finish

(Clear Basecoat)

16-021B As required (1)

NOTE (1): Mat. No. 07-018 is an alternative lacquer to Mat. No. 16-021B when

used to protect written part numbers.

(a) Re-identify the gear rib 5 by part marking:

1 Gear Rib 5 D5725101700000

as

1 Gear Rib 5 D5725101700000

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

or

1 Gear Rib 5 D5725101700100

as

1 Gear Rib 5 D5725101700100

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

or

1 Gear Rib 5 D5725101700200

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 41

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as

1 Gear Rib 5 D5725101700200

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

1 Gear Rib 5 D5725101700300

as

1 Gear Rib 5 D5725101700300

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

or

1 Gear Rib 5 D5725218100000

as

1 Gear Rib 5 D5725218100000

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

or

1 Gear Rib 5 D5725218100100

as

1 Gear Rib 5 D5725218100100

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

or

1 Gear Rib 5 D5725218100200

as

1 Gear Rib 5 D5725218100200

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

or

1 Gear Rib 5 D5725218100300

as

1 Gear Rib 5 D5725218100300

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 42

7

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SERVICE BULLETIN

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

or

1 Gear Rib 5 D5725218100400

as

1 Gear Rib 5 D5725218100400

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

or

1 Gear Rib 5 D5725218100500

as

1 Gear Rib 5 D5725218100500

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

or

1 Gear Rib 5 D5725218100600

as

1 Gear Rib 5 D5725218100600

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

or

1 Gear Rib 5 D5725218100700

as

1 Gear Rib 5 D5725218100700

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

(b) Apply

Polyurethane Gloss

Finish (Clear

Basecoat)

16-021B As required

to protect the written part number from hydraulic fluid.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 43

7

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SERVICE BULLETIN

**CONF 002

(1) Subtask 571118-020-401-003 - Removal of Bushes

Manpower Resources

Manhours 18.00

Minimum number of person 2

Subtask elapsed time 9.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

Standard tool TOOLB02

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

98D57004025001 Kit, Rem.-Inst. - Pintle

Bushes

1

NOTE: Each kit includes:

- In-line Honing Tool

- Facing Tool

- Alignment Tool

- Removal/Installation Tool

The In-line Honing Tool comprises (Refer to Drawing 98D57004025):

- 1 Alignment Hone MT58133/170 (item 65)

- 2 Finishing Stones N2F6C (item 68)

- 2 Roughing Stones N2F3C (item 67)

- 4 Plastic Guides N2 (item 66)

The Finishing and Roughing Stones are supplied as a set complete with

two aluminium guides.

The Facing Tool comprises (Refer to Drawing 98D57004025):

- Spacing Bush 98D57004025-242 (item 63)

- Hollow Location Shaft 98D57004025-236 (item 60)

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 44

7

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- Clamp Fork 98D57004025-222 (item 24)

- Nylon Washer 98D57004025-240 (item 62)

- Clamp Collar 98D57004025-238 (item 61)

- Clamp Stud 98D57004025-228 (item 27)

- Cutter Shaft 98D57004025-216 (item 21)

- Bearing 51204 (item 42)

- Collar Nut 404-207 (item 41)

- Lathe Tool 98D57004025-248 (item 44)

- Spacer Clamp 98D57004025-226 (item 26)

- Packer 98D57004025-232 (item 45)

- Depth Stop 98D57004025-220 (item 23)

The Alignment Tool is the Truing Sleeve MT19003 (item 64)

The Removal/Installation Tool comprises (Refer to Drawing

98D57004080):

- Split Location Ring 98D57004080-200 (item 0)

- Reaction Block 98D57004080-202 (item 1)

- Installation Block 98D57004080-204 (item 2)

- Block R/I 98D57004080-206 (item 3)

- Bolt 98D57004080-208 (item 4)

- Washer 98D57004080-210 (item 5)

- Nut 98D57004080-212 (item 6)

- Location Block 98D57004080-214 (item 7)

- Sleeve 98D57004080-216 (item 8)

- Socket Hd cap screw (item 9)

- Nut (item 10)

The kit is a tool kit designed for the repair of the pintle bushes in the

gear rib 5. It will be required to:

- remove and install the bushes,

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 45

7

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SERVICE BULLETIN

- line-hone the bushes to the finished internal diameter after

installation,

- machine the flange of the bush, Item 2.

You can get the kit(s) from AIRBUS.

If the repair procedure given in Repair Instruction R572-48341, "Removal

of corrosion/damage from Gear Rib lugs and installation of oversize

repair bushes is necessary, then the tool kit 7K800256D044 which

contains the In-line Boring Fixture Tool will be necessary.

It is acceptable to use the tool kit 7K800256D044 in place of the tool kits

98D57004025000 or 98D57004025001.

References

Fig. A-UBAAA

Gear Rib 5 Bushes

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Refer to Fig. A-UBAAA Sheet 01 Fig. A-UBAAA Sheet 02 Fig. A-UBAAA Sheet 03 Fig.

A-UBAAA Sheet 04

(a) Remove and retain the anti-rotation washer, Item (1).

(b) Clean all unwanted material from the anti-rotation washer, Item (1) with a plastic

spatula and use:

Solvent General

Purpose

11-026 As required

(c) Use the Removal/Installation Tool from the Tool Kit

98D57004025001 Kit, Rem.-Inst. -

Pintle Bushes

1

to remove these items:

1 Bush D5725926600000 Item (2) Discard

1 Bush D5725926700000 Item (3) Discard

1 Bush D5725926800000 Item (4) Discard

NOTE (01): Remove the Bush, Item (4) before removal of the bushes, Items (2)

and (3).

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 46

7

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SERVICE BULLETIN

(2) Subtask 571118-210-401-002 - Inspection of Gear Rib 5

Manpower Resources

Manhours 32.00

Minimum number of person 2

Subtask elapsed time 16.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Non Destructive Test Manual (NTM) 51-10-02

51-81-00

Fig. A-UBAAA

Gear Rib 5 Bushes

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Refer to Fig. A-UBAAA Sheet 01

(a) Visually inspect the gear rib forward lug bore to make sure that no liner bushes are

installed. If there are, report details to AIRBUS and await further instructions.

(b) Clean the bore, lug faces and chamfer of all unwanted material with a plastic

spatula and

Solvent General

Purpose

11-026 As required

(c) Do a visual inspection of the bores, spotfaces and chamfers of the lugs for the

pintle-pin bushes for corrosion/damage (Refer to NTM 51-10-02).

(d) Do a liquid penetrant inspection of the bores, spotfaces and chamfers of the lugs

for the pintle-pin bushes for corrosion/damage (Refer to NTM 51-81-00).

(e) Make sure that the dimension E (forward lug bore diameter) is between these

limits:

- 102.000 to 102.035 mm.

(f) Make sure that the dimension D (rear lug bore diameter) is between these limits:

- 112.000 to 112.035 mm.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 47

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(g) Make sure that the forward lug thickness across the existing spotfaces is between

these limits:

- 52.50 to 52.70 mm.

(h) If any dimensions are outside of limits, report details to AIRBUS and await further

instructions.

(i) If no damage is found do SUBTASK 571118-420-401 003 Bush Installation

(j) If damage/corrosion is found, refer to Repair Instruction R572-48341, "Removal of

corrosion/damage from Gear Rib lugs and installation of oversize repair bushes".

NOTE: The Repair Instruction reference includes the procedure for using

the In-line Boring Fixture Tool and for the installation of oversize

bushes.

(3) Subtask 571118-420-401-003 - Bush Installation

Manpower Resources

Manhours 17.50

Minimum number of person 2

Subtask elapsed time 8.75

Skills AIRFRAME

Material necessary to do the job

Kit 571118B02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 D5725926600200 2 Bush

3 D5725926700200 2 Bush

4 D5725926800200 2 Bush

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Anaerobic 08-003 As required

Fuel Tank Sealant

Polysulfide

09-002 As required

Low Adhesion Polysulfide

Sealant

09-019C As required

Adhesion Promoter For

Polysulfide Sealant

09-028 As required

Solvent General Purpose 11-026 As required

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Anti-Corrosion Primer 16-006 As required

External Top Coat 16-018 As required

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 48

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ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polyurethane Gloss Finish

(Clear Basecoat)

16-021B As required (1)

Lint-Free Cotton Cloth 19-003 As required

NOTE (1): Mat. No. 07-018 is an alternative lacquer to Mat. No. 16-021B when

used to protect written part numbers.

References

Fig. A-UBAAA

Gear Rib 5 Bushes

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-UBCAA

In-line Honing Tool

Sheet 01

Sheet 02

Fig. A-UBEAA

Facing Tool

Sheet 01

Refer to Fig. A-UBAAA Sheet 01 Fig. A-UBAAA Sheet 02 Fig. A-UBAAA Sheet 03 Fig.

A-UBAAA Sheet 04 and Fig. A-UBCAA Sheet 01 Fig. A-UBCAA Sheet 02 and Fig. AUBEAA Sheet 01

(a) Before installing the bushes check that the overall dimension G across the bushes,

items 2 and 3 is likely to be achieved. This can be done by measuring the

thickness of the lug and the thickness of the flange on the two bushes and adding

them together. This dimension should be between 68.50 and 68.60 mm. If this

dimension is outside the tolerance, report details to AIRBUS and await further

instructions.

(b) Re-protect surface finishes if there is visible damage to the surface protection or

the surface protection has been removed during inspection.

1 Apply:

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

to the chamfer, bore and the spotfaces of the lug.

2 Wash off excess Chemicals and make sure sufficient drying time is allowed.

3 Apply:

Anti-Corrosion

Primer

16-006 As required

to the chamfer and spotfaces of the lug and the mating surface for the seat of

the bush flange.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 49

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(c) Apply

Sealant, Anaerobic 08-003 As required

to the lug bore.

WARNING: LIQUID NITROGEN IS DANGEROUS. OBEY THE MANUFACTURERS

INSTRUCTIONS AND WEAR THE CORRECT PROTECTIVE

CLOTHING WHEN YOU USE LIQUID NITROGEN.

CAUTION: DO NOT PUT MORE THAN ONE BUSH AT A TIME INTO THE LIQUID

NITROGEN, USE CLEAN TONGS TO REMOVE THE BUSH FROM

THE LIQUID NITROGEN AND TO INSTALL IT IN THE BORE OF THE

LUG.

(d) Install:

2 Bush D5725926600200 Item 2

2 Bush D5725926700200 Item 3

2 Bush D5725926800200 Item 4

1 To make sure that the bush remains cold enough so that the risk of the bush

interfering with the bore on installation is minimized, the bush and mandrel

(assembled) must be immersed in liquid nitrogen for at least 30 minutes

immediately prior to installation.

2 Freeze each bush in sequence in liquid nitrogen for not less than 30 minutes.

3 Install each bush in sequence in the applicable end of the bore of the forward

lug of the aft gear-rib bearing. Make sure that the bushes are fully installed.

4 Clamp each bush firmly immediately after installation and then allow the

assembly to return to ambient temperature, allow the sealant to cure

fully to prevent any bush migration. Before the sealant cures, use the

removal/installation tool, Item 8 (from Tool Kit 98D57004025000) to make sure

that the bush is fully installed.

(e) Make sure that the overall dimension G across the bushes, items 2 and 3 is

between 68.50 and 68.60 mm. If this dimension is outside the tolerance, report

details to AIRBUS and await further instructions.

(f) Make sure the clearance dimension between the bushes, Item 2 and Item 3 is free

of sealant.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 50

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(g) Prior to honing it is recommended that the permanent four stage sealing procedure

is applied and the full cure time of the surface protection and sealants is allowed,

before proceeding further. However, it is acceptable to continue immediately with

the repair (honing the bushes) provided a temporary fillet seal is applied as follows:

1 Apply a temporary fillet seal around the bush heads. Use:

Low Adhesion

Polysulfide Sealant

09-019C As required

and leave until no longer tacky.

(h) Refer to Fig. A-UBAAA Sheet 01 Fig. A-UBAAA Sheet 02 Fig. A-UBAAA Sheet 03

Fig. A-UBAAA Sheet 04 and Fig. A-UBCAA Sheet 01 Fig. A-UBCAA Sheet 02 and

Fig. A-UBEAA Sheet 01

1 Assemble the in-line honing tool as shown.

2 Use the alignment tool to set up the in-line honing tool.

CAUTION: USE ONLY DELAPENA NO. 6 HONING FLUID (MAT. NO.

06-010).

3 Use the in-line honing tool to get the dimension C between these limits:

- 104.000 to 104.035 mm.

4 Use the in-line honing tool to get the dimension F between these limits:

- 94.000 to 94.035 mm.

NOTE: The dimensions C and F must be concentric with each other to

within a diameter of 0.02 mm.

5 If necessary, use the facing tool to machine the face of the bush, Item 2 to get

the dimension G between these limits:

- 68.50 to 68.60 mm.

NOTE: If you do not have the facing tool, as an alternative the face of

the bush, Item 2, can be machined to the correct dimension

before installation.

NOTE: The machined face of the bush, Item 2, must be perpendicular

to the bore (dimension F) within 0.05 mm.

(i) Use

Solvent General

Purpose

11-026 As required

to clean the area.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 51

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(j) Install the anti-rotation washer, Item (1) as follows:

1 Apply

Fuel Tank Sealant

Polysulfide

09-002 As required

to the contact surfaces of the anti-rotation washer, Item (1) and the mating

face of the gear rib.

2 Allow the sealant to cure and use:

Lint-Free Cotton

Cloth

19-003 As required

made moist with:

Solvent General

Purpose

11-026 As required

to remove any unwanted sealant.

CAUTION: THE PROCEDURE THAT FOLLOWS APPLIES A 3 STAGE PROCESS

TO MAKE SURE A ROBUST SEALING OF THE BUSH TO LUG.

DEVIATION FROM THIS PROCESS CAN ALLOW THE INTEGRITY

OF THE SEAL TO BE COMPROMISED.

(k) Apply:

Adhesion Promoter

For Polysulfide

Sealant

09-028 As required

around the flanges of the bushes, Items 3 and 4, and the lug face.

(l) Apply a continuous bead of sealant around the edges of the bushes, Items 3 and 4

to form a fillet seal, use:

Fuel Tank Sealant

Polysulfide

09-002 As required

leave until it is no longer tacky.

(m) Apply:

External Top Coat 16-018 As required

to the fillet seals to protect the sealant from hydraulic fluid.

(n) Apply:

Polyurethane Gloss

Finish (Clear

Basecoat)

16-021B As required

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 52

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to the fillet seals to protect the sealant from hydraulic fluid.

NOTE: To prevent contamination/damage to the sealant and coatings, it is

required that the assembly is left to fully cure. Heaters (optional)

may be used to reduce the sealant cure time.

(4) Subtask 571118-930-402-002 - Re-identify the Gear Rib 5

Manpower Resources

Manhours 0.50

Minimum number of person 2

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Reidentified part set REIDB02

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

D5725551100000 Gear Rib D5725551100000

D5725551100100 Gear Rib D5725551100100

D5725918100000 Gear Rib D5725918100000

D5725918100100 Gear Rib D5725918100100

D5725918100200 Gear Rib D5725918100200

D5725918100300 Gear Rib D5725918100300

D5725918100400 Gear Rib D5725918100400

D5725918100500 Gear Rib D5725918100500

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polyurethane Gloss Finish

(Clear Basecoat)

16-021B As required (1)

NOTE (1): Mat. No. 07-018 is an alternative lacquer to Mat. No. 16-021B when

used to protect written part numbers.

(a) Re-identify the gear rib 5 by part marking:

1 Gear Rib 5 D5725551100000

as

1 Gear Rib 5 D5725551100000

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

or

1 Gear Rib 5 D5725551100100

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 53

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as

1 Gear Rib 5 D5725551100100

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

or

1 Gear Rib 5 D5725918100000

as

1 Gear Rib 5 D5725918100000

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

or

1 Gear Rib 5 D5725918100100

as

1 Gear Rib 5 D5725918100100

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

or

1 Gear Rib 5 D5725918100200

as

1 Gear Rib 5 D5725918100200

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

or

1 Gear Rib 5 D5725918100300

as

1 Gear Rib 5 D5725918100300

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

or

1 Gear Rib 5 D5725918100400

as

1 Gear Rib 5 D5725918100400

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 54

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Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

or

1 Gear Rib 5 D5725918100500

as

1 Gear Rib 5 D5725918100500

Re-identify by marking the Service Bulletin number "SB 57-1118" adjacent to the

old P/N.

(b) Apply

Polyurethane Gloss

Finish (Clear

Basecoat)

16-021B As required

to protect the written part number from hydraulic fluid.

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 571118-710-401-001 - OPERATIONAL

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 27-54-00, Page Block 501

(a) After installation of the torque shaft 6208CM (6258CM) SUBTASK 571118-942-401

001 CLOSE-UP , do an operational test of the flap system (Refer to AMM 27-54-00

Page Block 501). Make sure that the operation of the torque shafts is satisfactory.

(b) The test procedures necessary for the MLG are included in the reference for

installation of the MLG legs SUBTASK 571118-942-401 001 CLOSE-UP .

**CONF 002

(1) Subtask 571118-710-401-002 - OPERATIONAL

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 27-54-00, Page Block 501

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 55

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(a) After installation of the torque shaft 6208CM (6258CM) SUBTASK 571118-942-401

001 CLOSE-UP , do an operational test of the flap system (Refer to AMM 27-54-00

Page Block 501). Make sure that the operation of the torque shafts is satisfactory.

(b) The test procedures necessary for the MLG are included in the reference for

installation of the MLG legs SUBTASK 571118-942-401 001 CLOSE-UP .

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 571118-942-401-001 - CLOSE-UP

Work Zones and Access Panels

Zone Access/Work location

730

740

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 07-11-00, Page Block 201

27-54-45, Page Block 401

32-11-11, Page Block 401

(a) Install the torque shaft 6208CM (6258CM) (Refer to AMM 27-54-45 Page Block

401).

(b) Install the LH and RH MLG legs (Refer to AMM 32-11-11 Page Block 401).

(c) Remove the access platforms from zones 730/740.

(d) Lower the aircraft off jacks (Refer to AMM 07-11-00 Page Block 201).

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

equipment.

**CONF 002

(1) Subtask 571118-942-401-001 - CLOSE-UP

Work Zones and Access Panels

Zone Access/Work location

730

740

Manpower Resources

Skills AIRFRAME

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 56

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References

Aircraft Maintenance Manual (AMM) 07-11-00, Page Block 201

27-54-45, Page Block 401

32-11-11, Page Block 401

(a) Install the torque shaft 6208CM (6258CM) (Refer to AMM 27-54-45 Page Block

401).

(b) Install the LH and RH MLG legs (Refer to AMM 32-11-11 Page Block 401).

(c) Remove the access platforms from zones 730/740.

(d) Lower the aircraft off jacks (Refer to AMM 07-11-00 Page Block 201).

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

equipment.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 57

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**CONF ALL

PINTLE AXIS

GENERAL ARRANGEMENT AND

DIMENSIONAL REQUIREMENTS

C D E

G

FORK DATUM

(REF)

FOR VIEWS C AND D SEE SHEET 2.

FOR VIEWS E AND F SEE SHEET 3.

FOR VIEWS G AND H SEE SHEET 4.

NOTE:

KEEP DISTANCE BETWEEN BUSHES FREE OF SEALANT.

APPLY A CONTINUOUS BEAD OF SEALANT AROUND EDGE OF BUSH.

IF NECESSARY, MACHINE THIS FACE ONLY TO GET DIMENSION G.

GEAR SUPPORT RIB

DATUM (REF)

A

G H

A

(1)

(2) 2 (4) 4

(3) 3

C D E F

B

B

N_SB_571118_7_BAAA_01_02

THE MACHINED FACE OF THE BUSH MUST BE PERPENDICULAR TO

THE FINAL BORE (DIMENSION F) WITHIN 0.05 mm.

04 THE DIMENSIONS C AND F MUST BE CONCENTRIC TO EACH OTHER

WITHIN A DIAMETER OF 0.02 mm.

04 F 04

Figure A-UBAAA - Sheet 01

Gear Rib 5 Bushes

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 58

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**CONF ALL

REMOVAL / INSTALLATION TOOL

REMOVAL / INSTALLATION TOOL

GEAR SUPPORT RIB

DATUM (REF)

C

D

BUSH (ITEM 4) REMOVAL

BUSH (ITEM 4) INSTALLATION

(4)

4

GEAR SUPPORT RIB

DATUM (REF)

N_SB_571118_7_BAAA_02_01

Figure A-UBAAA - Sheet 02

Gear Rib 5 Bushes

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 59

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**CONF ALL

REMOVAL / INSTALLATION TOOL

REMOVAL / INSTALLATION TOOL

GEAR SUPPORT RIB

DATUM (REF)

GEAR SUPPORT RIB

DATUM (REF)

BUSH (ITEM 3) REMOVAL

N_SB_571118_7_BAAA_03_01

(3)

BUSH (ITEM 3) INSTALLATION

3

E

F

Figure A-UBAAA - Sheet 03

Gear Rib 5 Bushes

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 60

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SERVICE BULLETIN

**CONF ALL

N_SB_571118_7_BAAA_04_01

REMOVAL / INSTALLATION TOOL

REMOVAL / INSTALLATION TOOL

BUSH (ITEM 2) REMOVAL

BUSH (ITEM 2) INSTALLATION

(2)

G

GEAR SUPPORT RIB

DATUM (REF)

GEAR SUPPORT RIB

DATUM (REF)

H

2

Figure A-UBAAA - Sheet 04

Gear Rib 5 Bushes

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 61

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**CONF ALL

STONE

ALIGNMENT HONE

BODY

DRIVE FORK CRADLE

SCREW

STONE

PIVOT DRIVE FORK THROUGH 90° AND WITHDRAW CENTER SPINDLE.INSERT STONE AND ALUMINIUM GUIDE SET INTO BODY AND REPLACE CENTER SPINDLE.LOOSEN SCREW AND PIVOT CRADLE THROUGH 90° AND WITHDRAW CENTER SPINDLE.INSERT NYLON GUIDE SET INTO BODY AND REPLACE CENTER SPINDLE.SWING CRADLE BACK INTO POSITION AND TIGHTEN SCREW.

ALUMINIUM

GUIDE

TO ASSEMBLE STONES AND GUIDES TO BODY: NOTE:

N_SB_571118_7_BCAA_01_01

CENTER

SPINDLE CENTER SPINDLE

NYLON

GUIDE SET

Figure A-UBCAA - Sheet 01

In-line Honing Tool

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 62

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**CONF ALL

N_SB_571118_7_BCAA_02_01

NOTE: USE OF ALIGNMENT TOOL TO ALIGN FACES OF THE

TWO STONES OF THE LINE − HONING TOOL.

ALIGNMENT

TOOL, ITEM 7

LINE − HONING

TOOL, ITEM 5

HAND HELD

 POWER TOOL

Figure A-UBCAA - Sheet 02

In-line Honing Tool

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 63

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**CONF ALL

GEAR SUPPORT RIB

DATUM

DEPTH STOP

LATHE TOOL

BOLT

BOLT

PACKER

SPACING

BUSH NYLON

WASHER

CLAMP

STUD

COLLAR

NUT

CLAMP

COLLAR

CLAMP FORK

GRUB

SCREW

SPACER CLAMP

HOLLOW LOCATION

SHAFT

CUTTER

SHAFT

N_SB_571118_7_BEAA_01_01

2

Figure A-UBEAA - Sheet 01

Facing Tool

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 64

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SERVICE BULLETIN

REPORTING SHEET

TITLE: WINGS - MAIN STRUCTURE - GEAR RIB 5 - CHANGE TO GEAR RIB

BUSHES

MODIFICATION No.: 32025J2211

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

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

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

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

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

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

Or : Intermediate revision YES/NO

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

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

the next feasible revision, this will result in

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

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

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

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

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

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

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 1

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SERVICE BULLETIN

QUALITY PERCEPTION FORM

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

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

improve the quality of our Service Bulletins.

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

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

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

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

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

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

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Sep 05/02 SERVICE BULLETIN No.: A320-57-1118

REVISION No.: 05 - Jul 23/12 Page: 1

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