REVISION No. : 03 − Feb 09/01 L7 

# A319/A320/A321

SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel: (33) 5 61 93 33 33 Telex: AIRBU 530526 F Fax : (33) 5 61 93 42 51 ATA SYSTEM : TITLE : 57 WINGS − INNER REAR SPAR − INTRODUCTION OF INTERFERENCE FIT FASTENERS MODIFICATION No. : 24591J1322 24591J1323 24591J1345 This page transmits Revision No. 03 of Service Bulletin No. A320−57−1089. ADDITIONAL WORK No additional work is required by this revision for aircraft modified by any previous issue. REASON The threshold figures indicated in the previous issue of this Service Bulletin have been defined on the basis of full scale fatigue tests. Since then, a survey, carried out on the A320 family fleet, has highlighted some differences between the mission parameters of in−service aircraft and those initially considered. The differences are mainly on the weight of fuel at landing and on the average flight time which are higher than those defined for the analysis of the the fatigue related tasks. This has led to an adjustment of the A320 family reference fatigue mission. Consequently, additional thresholds for the accomplishment of this Service Bulletin, expressed in flight hours, have been introduced. The opportunity has been taken to correct minor errors throughout the Service Bulletin. Format differences due to a change in specification to the Service Bulletin presentation are not identified. CHANGES SB Summary : − Para. MATERIAL INFORMATION; Reference changed due to format change. − Para. APPENDICES; Accomplishment Timescale Flow Charts Appendix 1 removed from content, Appendices 2 thru 6 re−numbered 1 thru 5. SB Planning Information : − Para. A.(2)(b); Validation statement added. − Para. E.(2) Accomplishment Timescales; A note has been added which refers to Service Bulletins A320−57−1004 and A320−57−1060. Flight Hour (FH) thresholds added and reference to Flow Charts changed. − Para. F.; New standard sentence added. − Para. G.; New standard sentence added. − Accomplishment Timescale Flow Charts inserted as Figure 1 with added Flight Hour (FH) thresholds. Sheets 2 and 3 timescales amended in

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 1 of 3REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN REVISION TRANSMITTAL SHEET accordance with ISB A320−57−1088. Also, the instructions that refer to Service Bulletins A320−57−1004 and A320−57−1060 have been deleted. SB Material Information : − Para. B.; ’Special Information’ from previous revision now included as ’Industry Support Information’, references changed accordingly. − Para. F.; Appendix reference changed. SB Accomplishment Instructions : − Para. A. and Para. B.; References to Appendices changed throughout. − Para. A.(1)(n); Mod. applicability to aircraft type added throughout. − Para. B.(1); Para. reference changed. − Para. B.(1)(a) and (c); NTM reference changed. − Para. B.(2)(a)3 and (b)3; NTM reference changed and NOTE added denoting the NTM technique applicability. − Para. B.(3)(a)3 and (b)3; NTM reference changed and NOTE added denoting the NTM technique applicability. − Para. B.(14); Table 14 Kit A05 Hole No. 12 fastener P/N amended. − Para. D.(5); Mod. applicability to aircraft type added throughout. − Figures renumbered due to insertion of Accomplishment Timescale Flow Charts in Planning Information. − Figure 4 Sheet 2; Mod. applicability to aircraft type added. − Figure 6 Sheet 1; A320−100 series wing shown. − Figure 7 Sheet 1; A320−200 series actuator cylinder anchorage shown. SB Appendices : − Content of original Appendix 1 moved to SB Planning Information. Remaining Appendices renumbered accordingly. − Appendix 1; Airbus Industrie address revised. − Appendix 3 and 4; Minor corrections made as necessary. − Appendix 4; Tooling set reference numbers deleted from tables. FILING 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 Revision No. 01 was issued to include accomplishment instructions which were not included at original issue due to a missing page caused by a formatting error. Service Bulletin Validation changes were also included and the requirement for removing the engines was deleted. Aircraft shoring procedures were included as an appendix. Revision No. 02 was issued because of a change in the policy for the holding

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 2REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN REVISION TRANSMITTAL SHEET and the procurement of the tooling for this Service Bulletin. Also there are no longer supplementary spares kits for 2nd option fasteners. These will be procured under the normal spares procurement process, individually as required. REVISION SEQUENCE ORIGINAL : Dec 22/96 REVISION No. : 01 − Apr 17/97 REVISION No. : 02 − Nov 06/98 REVISION No. : 03 − Feb 09/01

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 3EVALUATION TABLE COMPLIANCE Recommended CANCELS INSPECTION SB Yes POTENTIAL AD No A/C OPERATION AFFECTED No RELIABILITY AFFECTED Yes PAX COMFORT AFFECTED No COST SAVING Yes ETOPS AFFECTED No STRUCTURAL LIFE EXTN Yes VENDOR SB INVOLVED No KIT PRICE (USD) See SB

REVISION No. : 03 − Feb 09/01 L7 

# A319/A320/A321

SERVICE BULLETIN SUMMARY AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel: (33) 5 61 93 33 33 Telex: AIRBU 530526 F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft ATA SYSTEM : TITLE : 57 WINGS − INNER REAR SPAR − INTRODUCTION OF INTERFERENCE FIT FASTENERS MODIFICATION No. : 24591J1322 24591J1323 24591J1345 REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES In fatigue tests, cracks were found in the inner rear spar. These cracks started to appear between 64,120 and 82,607 simulated flight cycles (FC). The cracks propagated from holes for the attachment of gear rib 5, the forward pintle fitting and the actuating cylinder anchorage. Service Bulletins A320−57−1004 (Mod No. 20740J0335 J0575) and A320−57−1060 (Mod No. 23304J0989) and Modifications 20741J0336 and 20796J0348 introduced cold expansion of the holes in the inner rear spar to reduce the possibility of cracks occurring. However, in−service experience has shown that there is still a possibility that cracks may occur. This Service Bulletin introduces cold re−expansion of the holes in the inner rear spar for the attachment of gear rib 5, the forward pintle fitting and the actuating cylinder anchorage. The pintle fitting and gear rib 5 are also cold expanded. Interference fit fasteners are installed in the rear spar and gear rib 5, whilst a clearance fit is maintained in the actuating cylinder anchorage and pintle fitting. The accomplishment of this Service Bulletin will further reduce the possibility of cracks occurring, which will prevent the possibility of costly and time consuming repairs. It will also cancel the inspection requirements of Service Bulletin A320−57−1088. Service Bulletin A320−57−1089 supersedes Service Bulletins A320−57−1004 and A320−57−1060, if A320−57−1089 is carried out at the same threshold as A320−57−1004 and A320−57−1060.

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 1 of 4REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN SUMMARY EFFECTIVITY This Service Bulletin is applicable to this (these) operators(s): AAA ABB ACA ADR AEL AFR AIB AIH AJM ALK AMC AMM ANA AWE BAW CDN CMM CSC CTN CYP DLH FTI GFA IAC IBE IWD JMC KAC LAJ LRC LTU LXR MON MSR MXA NWA OYC RJA RYN SAA SHK SSV SWR TAP TAR TAS TLA TNA TRZ UAL VLE This modification is embodied before delivery on aircraft MSNs 0559, 0562, 0565, 0568 and subsequent. CONCURRENT REQUIREMENTS None REFERENCES/REPERCUSSIONS TFU : 572100005 OEB : None AOT : None SIL : None LIFE LIMIT : No LINE MAINTENANCE AFFECTED : No OTHER : None NATURE OF THE WORK AIRCRAFT : Yes. EQUIPMENT : No. HARD : No. SOFT : No. OBRM : No. MANPOWER Kit 571089A01 or Kit 571089A02 or Kit 571089A03 or Kit 571089A05 or Kit 571089A07 or Kit 571089A08 TOTAL MANHOURS 980.0 ELAPSED TIME (HOURS) 250.0 MATERIAL INFORMATION AIRCRAFT DATA Modification of one A/C requires one of the following Kits 571089A01, A02, A03, A05, A07 or A08. These Kits contain ’1st Option’ parts only. For the procurement of contingency parts and tooling above ’1st Option’ size, refer to the MATERIAL INFORMATION, Para. B of this Service Bulletin. APPENDICES APPENDIX 1 : Shoring Procedure. APPENDIX 2 : Modification Progress Sheets. APPENDIX 3 : Cold Expansion Planning Information.

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 2REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN SUMMARY APPENDIX 4 : Cold Expansion Tooling Lists. APPENDIX 5 : Cold Expansion Tooling and Process Information Sheets.

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 3REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN SUMMARY

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 4REVISION No. : 03 − Feb 09/01 L7 320−111 320−211 320−212 320−214 320−231 320−232 320−233 

# A319/A320/A321

SERVICE BULLETIN

AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel: (33) 5 61 93 33 33 Telex: AIRBU 530526 F Fax : (33) 5 61 93 42 51 ATA SYSTEM : TITLE : 57 WINGS − INNER REAR SPAR − INTRODUCTION OF INTERFERENCE FIT FASTENERS MODIFICATION No. : 24591J1322 24591J1323 24591J1345 This document contains Airbus Industrie PROPRIETARY INFORMATION and shall at all times remain the property of Airbus Industrie; no intellectual property right or licence is granted by Airbus Industrie 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 part to third parties and shall not be duplicated in any manner (except for the purpose of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without Airbus Industrie’s prior written consent. 1. PLANNING INFORMATION A. EFFECTIVITY (1) Models

(2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft MSN: 0002−0008 0010−0014 0016−0078 0080−0104 0106−0363 0365−0384 0386−0411 0413−0432 0435−0457 0459−0467 0469−0472 0475−0476 0478−0480 0482−0483 0485−0487 0489−0492 0496−0497 0499−0501 0503−0504 0506−0508 0510−0512 0523 0525 0527−0528 0530−0531 0533−0534 0537 0539−0540 0542−0543 0545 0547−0549 0551 0553−0554 0556 0558 0561 0566 (b) 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 Industrie. 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.

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 1 of 122REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

OPERATOR MSN AAA 0022 0023 0024 0025 0026 0027 0029 0030 0140 0142 0157 0229 0288 0331 0547 ABB 0348 0349 ACA 0059 0068 0073 0084 0122 0126 0127 0141 0149 0150 0154 0159 0183 0233 0242 0248 0253 0254 0255 0265 0277 0290 0310 0311 0324 0330 0333 0341 0342 0350 0359 0378 0384 0426 ADR 0043 0113 0114 AEL 0085 0131 0132 AFR 0002 0003 0004 0005 0007 0010 0012 0013 0014 0016 0019 0020 0021 0033 0036 0044 0061 0062 0063 0100 0101 0102 0108 0115 0128 0129 0130 0133 0144 0145 0155 0156 0184 0186 0187 0188 0203 0204 0211 0214 0215 0220 0226 0227 0228 0236 0237 0239 0244 0270 0278 0285 0286 0287 0337 0352 0377 0491 AIB 0344 AIH 0163 0164 0168 0169 0179 0193 0389 0424 0429 0449 AJM 0422 0528 ALK 0374 0406 AMC 0112 0293 AMM 0291 0292 0327 0336 ANA 0138 0139 0148 0151 0167 0170 0196 0212 0219 0245 0300 0328 0365 0383 0413 0482 0501 0507 0531 0534 0549 0554 AWE 0052 0053 0054 0055 0064 0065 0066 0067 0076 0077 0081 0082 0091 0092 0098 0099 0238 0271 0304 0315 0317 0448 0453 0455 0471 0527 0543 BAW 0006 0008 0011 0017 0018 0039 0042 0103 0109 0120 CDN 0174 0175 0210 0231 0232 0279 0283 0284 0302 0305 0309 0403 0404 CMM 0397 0409 0427 CSC 0540 0551 0556 CTN 0258 CYP 0028 0035 0037 0038 0180 0256 0295 0316 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 FTI 0230 0338 0437 0444 0476 GFA 0313 0325 0345 0375 0419 0421 0438 0445 0459 0466 0497 0537 IAC 0045 0046 0047 0048 0049 0050 0051 0056 0057 0058 0074 0075 0080 0089 0090 0095 0096 0097 0396 0398 0416 0423 0431 0432 0451 0469 0486 0490 0492 0499 IBE 0134 0136 0143 0146 0158 0173 0176 0177 0199 0207 0223 0224 0240 0241 0246 0264 0266 0274 0303 0312 0323 0356 IWD 0225 0308 0314 JMC 0354 0357 0411 0443 KAC 0181 0182 0195 LAJ 0376 0386 0480

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 2REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

OPERATOR MSN LRC 0425 0460 0461 0558 0561 LTU 0530 LXR 0395 MON 0379 0391 0392 0446 MSR 0165 0166 0178 0194 0198 0351 0366 MXA 0252 0259 0260 0261 0275 0276 0280 0296 0320 0321 0353 0361 0368 0369 0467 NWA 0031 0032 0034 0040 0041 0060 0106 0107 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 0400 0408 0410 0417 0418 OYC 0221 0222 0294 0299 0301 RJA 0087 0088 0289 0407 RYN 0362 0363 0393 0394 SAA 0243 0249 0250 0251 0334 0335 0440 SHK 0322 0326 0478 SSV 0496 0525 SWR 0533 0545 0548 0553 0566 TAP 0185 0191 0234 0235 TAR 0119 0123 0124 0205 0370 0390 0402 0511 TAS 0371 TLA 0247 0257 0405 0414 0415 0428 0430 TNA 0332 0441 TRZ 0347 0373 0447 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 VLE 0189 0190 0343 0420 0436 0542 This modification is embodied before delivery on aircraft MSNs 0559, 0562, 0565, 0568 and subsequent. This Service Bulletin has been validated on aircraft MSN 0006. (c) Effectivity by MSN and Kit/Configuration MSN 0002−0008 0010−0014 0016−0021 KIT No. QTY PER A/C CONFIGURATION 571089A01 1 None MSN 0022−0047 KIT No. QTY PER A/C CONFIGURATION 571089A02 1 None MSN 0048−0051

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 3REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION 571089A03 1 None MSN 0052−0078 0080−0104 0106−0315 KIT No. QTY PER A/C CONFIGURATION 571089A05 1 None MSN 0316−0363 0365−0381 KIT No. QTY PER A/C CONFIGURATION 571089A07 1 None MSN 0382−0384 0386−0411 0413−0432 0435−0457 0459−0467 0469−0472 0475−0476 0478−0480 0482−0483 0485−0487 0489−0492 0496−0497 0499−0501 0503−0504 0506−0508 0510−0512 0523 0525 0527−0528 0530−0531 0533−0534 0537 0539−0540 0542−0543 0545 0547−0549 0551 0553−0554 0556 0558 0561 0566 KIT No. QTY PER A/C CONFIGURATION 571089A08 1 None (3) Spares None B. CONCURRENT REQUIREMENTS None C. REASON (1) History In fatigue tests, cracks were found in the inner rear spar. These cracks started to appear between 64,120 and 82,607 simulated flight cycles (FC). The cracks propagated from holes for the attachment of gear rib 5, the forward pintle fitting and the actuating cylinder anchorage. Service Bulletins A320−57−1004 (Mod No. 20740J0335 J0575) and A320−57−1060 (Mod No. 23304J0989) and Modifications 20741J0336 and 20796J0348 introduced cold expansion of the holes in the inner rear spar to reduce the possibility of cracks occurring. However, in−service experience has shown that there is still a possibility that cracks may occur. (2) Objective/Action This Service Bulletin introduces cold re−expansion of the holes in the inner rear spar for the attachment of gear rib 5, the forward pintle fitting and the actuating cylinder anchorage. The pintle

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 41.D.(1)

1.D.(2)

1.D.(3)

1.D.(4)

1.D.(5)

1.D.(6)

1.D.(7)

1.D.(8)

1.D.(9)

1.D.(10)

1.D.(11)

1.D.(12)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN
fitting and gear rib 5 are also cold expanded. Interference fit fasteners are installed in the rear spar and gear rib 5, whilst a clearance fit is maintained in the actuating cylinder anchorage and pintle fitting. (3) Advantages The accomplishment of this Service Bulletin will further reduce the possibility of cracks occurring, which will prevent the possibility of costly and time consuming repairs. It will also cancel the inspection requirements of Service Bulletin A320−57−1088. The accomplishment of this Service Bulletin will also ensure that the inner rear spar will reach design life goal. Service Bulletin A320−57−1089 supersedes Service Bulletins A320−57−1004 and/or A320−57−1060, if A320−57−1089 is carried out at the same threshold as A320−57−1004 and/or A320−57−1060. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to: (1) Defuel the aircraft. (2) Lift the aircraft on jacks. (3) Remove the LH and RH MLG actuators and the LH and RH MLGs. (4) Gain access to the forward face of the inner rear spar and remove the fuel feed and gallery pipes, LH and RH. (5) Depressurize the Blue, Yellow and Green hydraulic systems and reservoirs. (6) Remove or loosen the hydraulic pipelines from the inner rear spar, between Ribs 2 and 9, LH and RH. (7) Remove the bolts and the actuating cylinder anchorage. (8) Cold expand the holes in the rear spar. Install the anchorage. NOTE : The fasteners are an interference fit in the rear spar and they are a clearance fit in the actuating cylinder anchorage and in the Rib 3 brackets. (9) Remove the bolts from the pintle fitting, in sequence, and cold expand the parallel holes. (10) Install oversize bolts and studs to secure the pintle fitting. NOTE : The fasteners are an interference fit in the rear spar and they are a clearance fit in the pintle fitting. (11) Remove the bolts from the gear support rib, in sequence, and cold expand the holes in the gear support rib and the inner rear spar. (12) Install oversize bolts and studs in the gear support rib.

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 51.D.(13)

1.D.(14)

1.D.(15)

1.D.(16)

1.D.(17)

1.D.(18)

1.D.(19)

1.D.(20)

1.D.(21)

1.E.(2)(a)

1.E.(2)(b)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN
NOTE : The fasteners are an interference fit in the inner rear spar and the gear support rib. (13) Install the hydraulic pipelines to the inner rear spar, between ribs 2 and 9, LH and RH. (14) Install the fuel feed and gallery pipes. (15) Install the LH and RH MLG actuators and the LH and RH MLGs. (16) Pressurize the Yellow, Blue and Green hydraulic reservoirs. (17) Do a functional test of the MLG and the flight controls. (18) Lower the aircraft to the ground and remove the jacks. (19) Refuel the aircraft. (20) Do a leak check for the fuel and hydraulic fluid. (21) Close up and complete the documentation. E. COMPLIANCE (1) Classification Recommended (2) Accomplishment Timescale NOTE : It is considered that both Service Bulletins A320−57−1004 and A320−57−1060 have been accomplished. (a) Kit No. 571089A01 It is recommended that this Service Bulletin be accomplished at or before 12,000 FC or 22,400 FH (whichever occurs first) from the accomplishment of Service Bulletins A320−57−1004 and A320−57−1060 (Refer to Figure 1, Sheet 1, Accomplishment Timescale Flow Chart). (b) Kits No. 571089A02 thru A08 It is recommended that this Service Bulletin be accomplished at or before 20,000 FC or 37,300 FH (whichever occurs first) from first flight (Refer to Figure 1, Sheets 2 and 3, Accomplishment Timescale Flow Charts). F. APPROVAL The technical content of this Service Bulletin has been approved under the authority of DGAC Design Organization Approval No. F.JA.02. 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 an adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labour cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 6REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN
upwards to suit operators’ 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. Aircraft Gain access 110 Modification 750 Close up 120 TOTAL MANHOURS 980.0 ELAPSED TIME (HOURS) 250.0 H. WEIGHT AND BALANCE Not changed I. ELECTRICAL LOAD DATA None J. REFERENCES Aircraft Maintenance Manual (AMM) : 06−41−53 06−41−57 07−11−00 12−11−28 20−21−11 20−21−12 20−23−11 20−28−00 27−14−51 27−50−00 27−64−52 28−00−00 28−10−00 28−11−00 28−25−00 29−10−00 29−14−00 29−11−47 29−11−52 29−13−47 29−13−52 32−11−11 32−31−46 32−42−00 32−43−00 53−22−11 57−27−11 71−13−00 78−36−00 Structural Repair Manual (SRM) : 51−21−11 51−42−00 51−42−11 51−44−11 51−48−00 51−75−12 51−76−11 51−76−12 Nondestructive Test Manual (NTM) : 51−10−01 Service Bulletin : A320−57−1004 Service Bulletin : A320−57−1060 Service Bulletin : A320−57−1088 FTI Tooling List : A320−57−1089−1 Repair Instruction : R57258266 K. PUBLICATIONS AFFECTED None L. INTERCHANGEABILITY/MIXABILITY Not applicable

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 7REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Figure 1 Sheet 1

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 8 Accomplishment Timescale Flow ChartREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Figure 1 Sheet 2

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 9 Accomplishment Timescale Flow ChartREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Figure 1 Sheet 3

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 10 Accomplishment Timescale Flow ChartREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

2. MATERIAL INFORMATION A. MATERIAL − PRICE AND AVAILABILITY (1) Material Customers with aircraft shown in the effectivity of this Service Bulletin should submit a purchase order to Airbus Industrie. Quote the number of this Service Bulletin. AIRBUS INDUSTRIE MATERIEL SUPPORT CENTER P.O. BOX 630262 22312 HAMBURG GERMANY (2) Price and Availability Kit 571089A01 Cost : 30595.00 US Dollars Availability : 120 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 571089A02 Cost : 32727.00 US Dollars Availability : 120 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 571089A03 Cost : 32727.00 US Dollars Availability : 120 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 571089A05 Cost : 27036.00 US Dollars Availability : 120 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 571089A07

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 112.B.(1)

2.B.(1)(a)

2.B.(1)(b)

2.B.(1)(c)

2.B.(2)

2.B.(2)(a)

2.B.(2)(b)

2.B.(2)(c)

2.B.(2)(d)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Cost : 27036.00 US Dollars Availability : 120 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 571089A08 Cost : 27036.00 US Dollars Availability : 120 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 (1) Parts (a) The Service Bulletin Kits contain ’1st Option’ parts only. Any requirements above ’1st Option’ are classified as contingency items. Contingency items include : − Service Bulletin ’2nd Option’ parts − Repair parts and tooling. (b) For the procurement of ’2nd Option’ parts send a spares purchase order quoting the Part No. of the item(s) required to the AIRBUS INDUSTRIE Materiel Support Center (MSC)(Refer to Para. A. (1)). (c) For repair information, contact the AIRBUS INDUSTRIE Structures Repair Engineering Dept. NOTE : A stock of contingency items is held by the MSC. (2) Cold Expansion Tooling (a) There are three catagories of tooling (Refer to Appendices 4 and 5) : − Capital Tooling (1 Kit is required per Customer, Kit available on hire if necessary) − Durable Tooling (1 Kit is to be procured per Customer) − Consumable Tooling (1 Kit is to be procured per Aircraft) (b) For Kits A01, A02 and A03 the procurement of tooling is through FTI as previously (Refer to Para. F.). (c) For Kits A05, A07 and A08 the procurement of tooling is now through the MSC (Refer to Para. F). (d) Reamers and Final Hole Gages for 2nd Option Fasteners are available as a separate Kit (2nd Option Tool Kit) from MSC, if

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 12Kit No. Hole No. Start Hole Dowel dia.ins(mm) Intermediate Dowel dia.ins(mm) Final Hole Dowel dia.ins(mm) A01, A02, A03 52−61 0.552−0.553 (14.02−14.04) 0.562−0.563 (14.27−14.30) 0.572−0.573 (14.53−14.55) 74−81 0.405−0.406 (10.29−10.31) 0.413−0.414 (10.49−10.51) 0.431−0.432 (10.95−10.97) A05, A07, A08 52−61 0.504−0.505 (12.80−12.82) 0.513−0.514 (13.03−13.05) 0.524−0.525 (13.31−13.33) 74−81 0.374−0.375 (9.50−9.52) 0.381−0.382 (9.68−9.70) 0.399−0.400 (10.15−10.17) 2.B.(3)

2.B.(4)

2.B.(5)

2.B.(6)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN
required (Refer to Para. F). (3) Due to the potential difficulty in removing fasteners, it is recommended that the standard tools that follow are used. The tools are used with a riveting gun : − Bolt Extractor Adaptor, Part Nos. CHS 510A−4, CHS 510A−7, CHS 510A−8, CHS 510A−9, CHS 510A−10. − Bolt Extractor Snap, Part Nos. CHS 510−2, CHS 510−3. NOTE : The tools are procurable from the MSC. (4) If there are K−Fastener (KAYNAR) Nuts Part No. NSA5475K installed on the Pintle Fitting, the following Standard Tools will be required : − Ring Spanners Part Nos. SRS 603−7 thru 603−10 − Socket Spanners Part Nos. EWS 603−7 thru 603−10 If necessary, refer to IPC for Vendor Code V15653. (5) A DESOUTER Type 90 degree angle windy drill, P/N D3141−S−750 with a 5/16 in. collet and an ATLAS COPCO Type 90 degree angle windy drill, P/N LBV33S005−1 with a 1/2 in. chuck will be required for some hole positions. (6) It is highly recommended that three sets of dowels are manufactured to locate the actuating cylinder anchorage in place as the holes are being drilled and reamed. Each set will contain four dowels. The four dowels will be of two sizes, two dowels diameter sized for bolt holes 52 to 61 and two dowels diameter sized for bolt holes 74 to 81. Each of the three sets will be for the start hole size diameter, the post cold expansion diameter (intermediate) and the final hole diameter. Refer to Accomplishment Instructions, Para. B.(4) FTI Tooling and the FTI Tool Kit A320−57−1089−1 for applicable Kit No. and hole diameter sizes. Refer to the table that follows for the applicable dowel sizes.

NOTE : All dowels should be approx. 1.5 in. (38 mm) in length with a lead in taper of 0.5 in (12.7 mm).

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 13REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

C. LIST OF COMPONENTS Kit 571089A01 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP D5725297723000 6 Stud D5725297723200 2 Stud D5725297723400 2 Stud D5725297723600 6 Stud D5725297723800 4 Stud D5725297724000 4 Stud D5725297727200 4 Stud D5725297727400 4 Stud D5725297727800 2 Stud D5725297738000 4 Stud D5725297728400 2 Stud D5725297738200 4 Stud D5725297732000 6 Stud D5725297732400 2 Stud D5725297732600 8 Stud D5725297732800 6 Stud D5725297820200 4 Stud D5725297826000 4 Stud D5725297820600 2 Stud D5725297826200 4 Stud D5725297821000 2 Stud D5725297822800 4 Stud D5725297921000 96 Washer D5725297921800 144 Washer D5725297922200 60 Washer D5725297923600 22 Washer D5725297924000 20 Washer D5725297924800 48 Washer D5725297925600 72 Washer D5725297926000 30 Washer D5725297928400 48 Washer D5725297929000 16 Washer D5725297929600 44 Washer D5725297930200 12 Washer D5725297930600 14 Washer D5725297931400 24 Washer D5725297932000 8 Washer D5725297932600 22 Washer AN960C716 24 Washer AN960C816 28 Washer AN960KD716 44 Washer AN960KD816 40 Washer NSA5057−9 52 Nut NSA5472−7K7 38 Nut NSA5472−8K7 38 Nut NSA5472−9K7 28 Nut NSA5472−10K7 142 Nut

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 14REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP NSA5479VHK7−12 30 Bolt NSA5479VHK7−13 4 Bolt NSA5479VHK8−12 4 Bolt NSA5479VHK8−13 16 Bolt NSA5479VHK8−14 6 Bolt NSA5479VHK8−15 4 Bolt NSA5479VHK8−18 4 Bolt NSA5479VHK9−14X 8 Bolt NSA5479VHK9−17X 4 Bolt NSA5479VHK9−18X 2 Bolt NSA5479VHK9−20X 2 Bolt NSA5479VHK9−26X 8 Bolt NSA5479VHK1020X 2 Bolt NSA5479VHK1023X 2 Bolt NSA5479VHK1030X 4 Bolt NSA935401−05 8 Tie NSA935401−08 2 Tie ASNA0080−508A 20 Rivet MS20470AD5−10 20 Rivet MS24665−304 10 Pin Kit 571089A02 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP D5725297723000 2 Stud D5725297723400 12 Stud D5725297723600 2 Stud D5725297724200 4 Stud D5725297724400 4 Stud D5725297727200 4 Stud D5725297727400 4 Stud D5725297727800 2 Stud D5725297738000 4 Stud D5725297728400 2 Stud D5725297738200 4 Stud D5725297732000 4 Stud D5725297732200 2 Stud D5725297732400 2 Stud D5725297732600 8 Stud D5725297732800 6 Stud D5725297820200 4 Stud D5725297826000 4 Stud D5725297820600 2 Stud D5725297826200 4 Stud D5725297821000 2 Stud D5725297822800 4 Stud D5725297921000 104 Washer D5725297921800 144 Washer D5725297922200 60 Washer D5725297924000 16 Washer D5725297924800 52 Washer

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 15REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP D5725297925600 72 Washer D5725297926000 30 Washer D5725297928400 48 Washer D5725297929000 16 Washer D5725297929600 44 Washer D5725297930200 12 Washer D5725297930600 14 Washer D5725297931400 24 Washer D5725297932000 8 Washer D5725297932600 22 Washer AN960C716 24 Washer AN960C816 28 Washer AN960KD716 44 Washer AN960KD816 32 Washer NSA5057−9 52 Nut NSA5472−7K7 38 Nut NSA5472−8K7 34 Nut NSA5472−9K7 32 Nut NSA5472−10K7 142 Nut NSA5479VHK7−12 30 Bolt NSA5479VHK7−13 4 Bolt NSA5479VHK8−13 8 Bolt NSA5479VHK8−14 6 Bolt NSA5479VHK8−15 12 Bolt NSA5479VHK8−18 4 Bolt NSA5479VHK9−15X 12 Bolt NSA5479VHK9−16X 2 Bolt NSA5479VHK9−17X 2 Bolt NSA5479VHK9−18X 2 Bolt NSA5479VHK9−21X 2 Bolt NSA5479VHK9−26X 8 Bolt NSA5479VHK1020X 2 Bolt NSA5479VHK1023X 2 Bolt NSA5479VHK1030X 4 Bolt NSA935401−05 8 Tie NSA935401−08 2 Tie ASNA0080−508A 20 Rivet MS20470AD5−10 20 Rivet MS24665−304 10 Pin Kit 571089A03 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP D5725297722600 4 Stud D5725297722800 4 Stud D5725297723000 2 Stud D5725297723400 12 Stud D5725297723600 2 Stud D5725297727200 4 Stud D5725297727400 4 Stud D5725297727800 2 Stud

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 16REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP D5725297738000 4 Stud D5725297728400 2 Stud D5725297738200 4 Stud D5725297732000 4 Stud D5725297732200 2 Stud D5725297732400 2 Stud D5725297732600 8 Stud D5725297732800 6 Stud D5725297820200 4 Stud D5725297826000 4 Stud D5725297820600 2 Stud D5725297826200 4 Stud D5725297821000 2 Stud D5725297823200 4 Stud D5725297920600 56 Washer D5725297921000 48 Washer D5725297921800 160 Washer D5725297922200 44 Washer D5725297924000 16 Washer D5725297924400 28 Washer D5725297924800 24 Washer D5725297925600 80 Washer D5725297926000 22 Washer D5725297928400 48 Washer D5725297929000 16 Washer D5725297929600 44 Washer D5725297930200 12 Washer D5725297930600 14 Washer D5725297931400 24 Washer D5725297932000 8 Washer D5725297932600 22 Washer AN960C716 24 Washer AN960C816 28 Washer AN960KD716 44 Washer AN960KD816 32 Washer NSA5057−8 20 Nut NSA5057−9 36 Nut NSA5472−7K7 38 Nut NSA5472−8K7 46 Nut NSA5472−9K7 20 Nut NSA5472−10K7 142 Nut NSA5479VHK7−12 30 Bolt NSA5479VHK7−13 4 Bolt NSA5479VHK8−13 8 Bolt NSA5479VHK8−14 6 Bolt NSA5479VHK8−15 12 Bolt NSA5479VHK8−18 4 Bolt NSA5479VHK8−15Y 12 Bolt NSA5479VHK9−16X 2 Bolt NSA5479VHK9−17X 2 Bolt

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 17REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP NSA5479VHK9−18X 2 Bolt NSA5479VHK9−21X 2 Bolt NSA5479VHK9−26X 8 Bolt NSA5479VHK1020X 2 Bolt NSA5479VHK1023X 2 Bolt NSA5479VHK1030X 4 Bolt NSA935401−05 8 Tie NSA935401−08 2 Tie ASNA0080−508A 20 Rivet MS20470AD5−10 20 Rivet MS24665−304 10 Pin Kit 571089A05 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP D5725297720000 2 Stud D5725297720200 12 Stud D5725297720400 2 Stud D5725297722600 4 Stud D5725297722800 4 Stud D5725297727200 4 Stud D5725297727400 4 Stud D5725297727800 2 Stud D5725297738000 4 Stud D5725297728400 2 Stud D5725297738200 4 Stud D5725297820200 4 Stud D5725297826000 4 Stud D5725297820600 2 Stud D5725297826200 4 Stud D5725297821000 2 Stud D5725297823200 4 Stud D5725297920000 44 Washer D5725297920200 32 Washer D5725297920600 96 Washer D5725297921800 160 Washer D5725297923400 22 Washer D5725297923800 16 Washer D5725297924400 52 Washer D5725297925600 80 Washer D5725297927400 24 Washer D5725297927600 28 Washer D5725297928000 48 Washer D5725297928600 16 Washer D5725297929200 44 Washer D5725297930000 12 Washer D5725297930400 14 Washer D5725297931000 24 Washer D5725297931600 8 Washer D5725297932200 22 Washer NSA5057−8 52 Nut

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 18REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP NSA5472−6K7 34 Nut NSA5472−7K7 34 Nut NSA5472−8K7 32 Nut NSA5472−9K7 10 Nut NSA5472−10K7 112 Nut NSA5479VHK6−12Y 30 Bolt NSA5479VHK6−13Y 4 Bolt NSA5479VHK7−13Y 8 Bolt NSA5479VHK7−14Y 6 Bolt NSA5479VHK7−15Y 12 Bolt NSA5479VHK7−18Y 4 Bolt NSA5479VHK8−15Y 12 Bolt NSA5479VHK8−16Y 2 Bolt NSA5479VHK8−17Y 2 Bolt NSA5479VHK8−18Y 2 Bolt NSA5479VHK8−21Y 2 Bolt NSA5479VHK8−26Y 8 Bolt NSA5479VHK9−20Y 2 Bolt NSA5479VHK9−23Y 2 Bolt NSA5479VHK9−30Y 4 Bolt NSA5479VHK1024Y 4 Bolt NSA5479VHK1026Y 2 Bolt NSA5479VHK1030Y 2 Bolt NSA5479VHK1031Y 8 Bolt NSA5479VHK1032Y 6 Bolt NSA935401−05 8 Tie NSA935401−08 2 Tie ANSA0080−508A 20 Rivet MS20470AD5−10 20 Rivet MS24665−304 10 Tie Kit 571089A07 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP D5725297720000 2 Stud D5725297720200 12 Stud D5725297720400 2 Stud D5725297722600 4 Stud D5725297722800 4 Stud D5725297727200 4 Stud D5725297727600 2 Stud D5725297727800 4 Stud D5725297738000 4 Stud D5725297729000 2 Stud D5725297729200 4 Stud D5725297820000 4 Stud D5725297820400 2 Stud D5725297826000 4 Stud D5725297820800 2 Stud D5725297826200 4 Stud D5725297823200 4 Stud

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 19REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP D5725297920000 44 Washer D5725297920200 32 Washer D5725297920600 96 Washer D5725297921800 160 Washer D5725297923400 22 Washer D5725297923800 16 Washer D5725297924400 52 Washer D5725297925600 80 Washer D5725297927400 24 Washer D5725297927600 28 Washer D5725297928000 48 Washer D5725297928600 16 Washer D5725297929200 44 Washer D5725297930000 12 Washer D5725297930400 14 Washer D5725297931000 24 Washer D5725297931600 8 Washer D5725297932200 22 Washer NSA5057−8 52 Nut NSA5472−6K7 38 Nut NSA5472−7K7 34 Nut NSA5472−8K7 32 Nut NSA5472−9K7 10 Nut NSA5472−10K7 112 Nut NSA5479VHK6−12Y 30 Bolt NSA5479VHK6−13Y 4 Bolt NSA5479VHK7−13Y 8 Bolt NSA5479VHK7−14Y 6 Bolt NSA5479VHK7−15Y 12 Bolt NSA5479VHK7−18Y 4 Bolt NSA5479VHK8−15Y 12 Bolt NSA5479VHK8−16Y 2 Bolt NSA5479VHK8−17Y 2 Bolt NSA5479VHK8−18Y 2 Bolt NSA5479VHK8−21Y 2 Bolt NSA5479VHK8−26Y 8 Bolt NSA5479VHK9−20Y 2 Bolt NSA5479VHK9−23Y 2 Bolt NSA5479VHK9−30Y 4 Bolt NSA5479VHK1024Y 4 Bolt NSA5479VHK1026Y 2 Bolt NSA5479VHK1030Y 2 Bolt NSA5479VHK1031Y 8 Bolt NSA5479VHK1032Y 6 Bolt NSA935401−05 8 Tie NSA935401−08 2 Tie ASNA0800−508A 20 Rivet MS20470AD5−10 20 Rivet MS24665−304 10 Pin Kit 571089A08

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 20REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP D5725297720000 2 Stud D5725297720200 12 Stud D5725297720400 2 Stud D5725297722600 4 Stud D5725297722800 4 Stud D5725297727200 4 Stud D5725297727600 2 Stud D5725297727800 4 Stud D5725297738000 4 Stud D5725297729000 2 Stud D5725297729200 4 Stud D5725297820000 4 Stud D5725297820400 2 Stud D5725297826000 4 Stud D5725297820800 2 Stud D5725297826200 4 Stud D5725297823200 4 Stud D5725297920000 44 Washer D5725297920200 32 Washer D5725297920600 96 Washer D5725297921800 160 Washer D5725297923400 22 Washer D5725297923800 16 Washer D5725297924400 52 Washer D5725297925600 80 Washer D5725297927400 24 Washer D5725297927600 28 Washer D5725297928000 48 Washer D5725297928600 16 Washer D5725297929200 44 Washer D5725297930000 12 Washer D5725297930400 14 Washer D5725297931000 24 Washer D5725297931600 8 Washer D5725297932200 22 Washer NSA5057−8 52 Nut NSA5472−6K7 38 Nut NSA5472−7K7 34 Nut NSA5472−8K7 32 Nut NSA5472−9K7 10 Nut NSA5472−10K7 112 Nut NSA5479VHK6−12Y 30 Bolt NSA5479VHK6−13Y 4 Bolt NSA5479VHK7−13Y 8 Bolt NSA5479VHK7−14Y 6 Bolt NSA5479VHK7−15Y 12 Bolt NSA5479VHK7−18Y 4 Bolt NSA5479VHK8−15Y 8 Bolt NSA5479VHK8−16Y 2 Bolt NSA5479VHK8−17Y 2 Bolt NSA5479VHK8−18Y 6 Bolt

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 21REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP NSA5479VHK8−21Y 2 Bolt NSA5479VHK8−26Y 8 Bolt NSA5479VHK9−20Y 2 Bolt NSA5479VHK9−23Y 2 Bolt NSA5479VHK9−30Y 4 Bolt NSA5479VHK1024Y 4 Bolt NSA5479VHK1026Y 2 Bolt NSA5479VHK1030Y 2 Bolt NSA5479VHK1031Y 8 Bolt NSA5479VHK1032Y 6 Bolt NSA935401−05 8 Tie NSA935401−08 2 Tie ASNA0800−508A 20 Rivet MS20470AD5−10 20 Rivet MS24665−304 10 Pin D. LIST OF MATERIALS − OPERATOR SUPPLIED DESCRIPTION REFERENCE TO CML QTY PER A/C INST DISP MAT. No. Sealant 09−001 As required Sealant 09−002 As required LOTOXANE Solvent 11−026 As required Epoxide Primer 16−006 As required Flexible Polyurethane 16−021 As required BOELUBE 70305 None As required * NOTE : * BOELUBE 70305 can be procured from : A.T.A. ENGINEERING BOUNDARY WAY, HEMEL HEMPSTEAD, HERTS, HP2 7SS Tel. 01442 264411/2 FAX 01442 231383 E. PARTS TO BE RE IDENTIFIED BY THE OPERATOR None F. TOOLING − PRICE AND AVAILABILITY For Kits A01, A02 and A03 : Tooling is procured as FTI Tool List A320−57−1089−1 from : FATIGUE TECHNOLOGY INC 100 ANDOVER PARK WEST SEATTLE WA USA 98 188−2868 For Kits A05, A07 and A08 : The tooling listed in APPENDIX 4 is procured by use of the eight digit Part No. from :

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 22REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

AIRBUS INDUSTRIE MATERIEL SUPPORT CENTER P.O. BOX 630262 22312 HAMBURG GERMANY G. SPECIAL TOOLS None

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 23REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 24 This Page Intentionally Left Blank3.A.(1)(a)

3.A.(1)(b)

3.A.(1)(c)

3.A.(1)(d)

3.A.(1)(e)

3.A.(1)(f)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : MAKE SURE THAT THE GROUND SAFETY−LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : PUT THE SAFETY DEVICES AND WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: − THE FLIGHT CONTROLS − THE FLIGHT CONTROL SURFACES − LANDING GEAR AND RELATED DOORS − COMPONENTS THAT MOVE. WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY IN AN AREA WITH A GOOD SUPPLY OF AIR. DO NOT GET THEM IN YOUR MOUTH PUT ON PROTECTIVE CLOTHING OBEY THE MANUFACTURER’S INSTRUCTIONS DO NOT SMOKE DO NOT BREATHE THE GAS THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANTS GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. WARNING : OBEY ALL THE FUEL SAFETY PROCEDURES. WARNING : OBEY ALL THE SAFETY PROCEDURES WHEN YOU DO WORK IN A FUEL TANK. NOTE : This Service Bulletin can be accomplished with the engines installed or removed. (1) Preparation (a) Defuel the aircraft (Refer to AMM 28−25−00 Page block 301). (b) Fully extend the flaps (Refer to AMM 27−50−00 Page block 201). (c) Open, safety and tag these circuit breakers : PANEL DESIGNATION FIN LOCATION 49VU FLIGHT CONT/FLP/CONT AND MONG/SYS1 6CV B06 49VU FLIGHT CONT/FLP/CONT AND MONG/SYS2 8CV B07 121VU FLIGHT CONT/WTB/FLP/SYS1 10CV Q21 121VU FLIGHT CONT/WTB/FLP/SYS2 12CV P20 (d) If the aircraft engines are to stay installed, refer to Appendix 1 , Para.(4)(a). Lift the aircraft on main jacks (Refer to AMM 07−11−00 Page block 201). (e) Remove the MLG actuating cylinder, LH and RH (Refer to AMM 32−31−46 Page block 401). (f) Remove the MLG LH and RH (Refer to AMM 32−11−11

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 253.A.(1)(g)

3.A.(1)(h)

3.A.(1)(i)

3.A.(1)(j)

3.A.(1)(k)

3.A.(1)(l)

3.A.(1)(m)

3.A.(1)(n)

3.A.(1)(n) 1

3.A.(1)(n) 2

3.A.(1)(n) 3

3.A.(1)(n) 4

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN
Page block 401). (g) Remove the belly fairing panels 147CB, 148DB and 191/192LB (Refer to AMM 53−25−11 Page block 401 ). CAUTION : THE AIRCRAFT MUST BE SUPPORTED ON JACKS AND SHORED IN ACCORDANCE WITH APPENDIX 1. (h) Refer to Appendix 1 , to shore the aircraft at Frame 42, LH and RH and if the engines are installed, at the engine cradles LH and RH. (i) Remove the access panels 540AB and 640AB (Refer to AMM 57−27−11 Page block 401). (j) Remove the access panels 574AB and 674AB (Refer to AMM 06−41−57 ). (k) Open the fuel tanks to a clean supply of air (Refer to AMM 28−10−00 Page block 301). CAUTION : THERE MUST BE NO MOVEMENT OF THE AIRCRAFT SUPPORT JACKS DURING AND AFTER THE REMOVAL OF THE RIB 5 BUILD DOOR. MOVEMENT OF THE JACKS COULD CAUSE THE RIB 5 TO DISTORT AND PREVENT INSTALLATION OF THE BUILD DOOR. (l) This procedure is optional. Removal of the Build Door will improve access. Remove and keep the 30 nuts and bolts that attach the Build Door in Rib 5. Remove and keep the Build Door. (m) Remove and keep the fuel feed and gallery pipes, Items (1) thru (7) (Refer to Figure 2 and refer to AMM 28−00−00 Page block 401). (n) Removal of Hydraulic Pipes, Clamps and Brackets and Hydraulic Components Refer to Figure 3 and Figure 4 1 Depressurize the Blue, Green and Yellow hydraulic systems (Refer to AMM 29−14−00 Page block 201). 2 Put the applicable access platforms in position. 3 Make a temporary mark on the hydraulic pipelines where the clamp block assemblies are installed. NOTE : The temporary marks will help you position the clamp block assemblies when the hydraulic pipelines are installed. 4 Remove and keep the clamp block assemblies for the hydraulic pipelines, Items (18), (20), (21), (22), (23), (24), (25), (27), (28), (29), (30), (31) and (34). Keep the parts that attach the clamp block assemblies with the applicable clamp block assembly. Remove and keep the clamp block plate Item (43) and the distance tube (44).

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 263.A.(1)(n) 5

3.A.(1)(n) 6

3.A.(1)(n)6 a

3.A.(1)(n)6 b

3.A.(1)(n)6 c

3.A.(1)(n) 7

3.A.(1)(n)7 a

3.A.(1)(n)7 b

3.A.(1)(n)7 c

3.A.(1)(n) 8

3.A.(1)(n) 9

3.A.(1)(n) 10

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN
NOTE : To help with the installation of the clamp block assemblies, identify them and their attaching parts with the position from which they were removed. 5 Disconnect the hydraulic pipelines Items (46) and (47), at the fuselage (Refer to Figure 4 Sheet 1 ). 6 PRE−MOD 21023(applicable to A320−100 Series A/C only).
a Make a temporary mark where the tube spacers are installed. Remove and discard the cable ties and remove and keep the tube spacer Item (49). NOTE : The cable ties and tube spacers are first installed as necessary. Thus the quantity and positions cannot be shown accurately. The temporary marks will help you to install them in the correct positions. b Remove and keep the clamp block assembly Item (50), together with the parts which attach it.
c Remove and keep the nuts Item (52), the washers Item (54) and the bolts Item (53). Remove and keep the support bracket Item (51) and the location block Item (56) (LH) and (55) (RH) (complete with the hydraulic pipelines Items (46) and (47) and the flexible hydraulic pipelines). 7 POST−MOD 21023(applicable to all A320−200 series A/C)
a Remove and keep the nuts Item (58), the bolts Item (61), the loop clamps Item (60) and the angles Item (62) (Detail A). b Remove and keep the nuts Item (58), the bolts Item (57) and the angle Item (59) (Detail A).
c Remove and keep the nuts Item (52), the washers Item (54) and the bolts Item (53). Remove and keep the support bracket Item (51) and the location block Item (56) (LH) and (55) (RH) (complete with the hydraulic pipelines Items (46) and (47) and the flexible hydraulic pipelines). 8 Remove and keep the hydraulic pipelines Items (48) and (73). 9 Remove and keep the nuts Item (65), the bolts Items (63) and (64) and remove and keep the bracket assembly Item (66) (LH) and (67) (RH). 10 Make a temporary mark where the tube spacers are installed. Remove and discard the cable ties and remove and keep the tube spacers Items (17), (19), (32) and (33).

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 273.A.(1)(n) 11

3.A.(1)(n) 12

3.A.(1)(n) 13

3.A.(1)(n) 14

3.A.(1)(n) 15

3.A.(1)(n) 16

3.A.(1)(n) 17

3.A.(1)(o)

3.A.(1)(o) 1

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN
NOTE : The cable ties and tube spacers are first installed as necessary. Thus the quantity and positions cannot be shown accurately. The temporary marks will help you to install them in the correct positions. 11 Remove and keep the guide assembly Item (82) and the channel assembly Item (83). 12 Disconnect the hydraulic pipelines Items (74) thru (81) at the inboard end. 13 Before removal of the hydraulic pipeline, Item (77), measure and record the clearance between the pipe and the ends of the fasteners at hole positions 17, 18, 24 and 25 (Refer to Figure 6 , Sheet 2 ). NOTE : At these positions it may be necessary to cut the new fasteners before installation to keep the minimum pipe clearances within limits. Use this data for reference if it is necessary to cut fasteners. 14 Remove and keep : − the hydraulic pipelines Item (77) − the compensated slide 1010GM (Refer to AMM 29−11−47 Page block 401) − the compensated slide 3010GM (Refer to AMM 29−13−47 Page block 401) − the fire shutoff valve 1046GK (Refer to AMM 29−11−52 Page block 401) − the fire shutoff valve 3046GD (Refer to AMM 29−13−52 Page block 401). 15 Drill out the rivets and remove the brackets Item (35). 16 Loosen the clamps and pipe assemblies outboard of Rib 5, for better access. NOTE : If access is still not easy, it may be necessary to cut through the pipelines, Items (76), (78), (79) and (80) on the outboard side of panels 574/674AB. 17 If necessary, at panel 574AB and 674AB disconnect the conduit (electrical) assemblies from the bracket and remove the bracket. (o) Remove the Strut Assemblies Refer to Figure 5 1 Remove and discard the cotter pins Item (150). Remove and keep the nuts Item (151), the washers Item (152) and the bolts (154). Remove the lockwire, loosen the nuts Items (155) and fully shorten the strut assemblies. Remove and keep the slide bushes Item (153) and the strut assemblies.

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 283.A.(2)(a)

3.A.(2)(b)

3.A.(2)(c)

3.A.(2)(d)

3.A.(2)(e)

3.A.(2)(f)

3.A.(2)(g)

3.A.(2)(h)

3.A.(2)(i)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

(2) Standard Practices (a) Use these torque values for nuts Part No. NSA5057 : − 1/2 in. nut, torque load 66−71 Nm (49−52 lbf ft) − 9/16 in. nut, torque load 90−97 Nm (67−71 lbf ft) and these torque values for nuts Part No. NSA5472 : − 3/8 in. nut, torque load 22−26 Nm (16−19 lbf ft) − 7/16 in. nut, torque load 32−38 Nm (24−28 lbf ft) − 1/2 in. nut, torque load 48−55 Nm (36−40 lbf ft) − 9/16 in. nut, torque load 68−78 Nm (51−57 lbf ft) − 5/8 in. nut, torque load 85−101 Nm (63−74 lbf ft). (b) Torque values for fuel, hydraulic and air data unions (Refer to AMM 20−21−12 Page block 201). (c) Sealing of fasteners (Refer to SRM 51−76−11 ). (d) Sealing of fasteners in the fuel tank (Refer to SRM 51−76−12 ). (e) Fasteners − hole and drill data (Refer to SRM 51−44−11 ). (f) Removal/installation of fasteners (Refer to SRM 51−42−11 ). This reference includes the lubrication of fasteners. For fasteners that are not supplied pre−lubricated with Cetyl Alcohol, it is recommended that Boelube 70305 is used as the preferred lubricant. The Boelube lubrication will make the installation of the interference fit fasteners easier. Boelube 70305 is a paste compound and should be applied to the full length of the bore before the fastener is installed. Boelube 70305 is water soluble, excess may be removed with a mild detergent or solvent wipe. Refer to MATERIAL INFORMATION Para. D. (g) Repair of protective finishes (Refer to SRM 51−21−11 ). (h) Where it is necessary to cut square drives and pintails from studs, deburr, clean and apply the following treatment. For Zinc coated studs : − Brush coat with sealant (Mat. No. 09−001) . For Cadmium plated studs : − Cadmium plate by the ’DALIC’ process (Refer to SRM 51−21−11 ), apply Epoxy Primer (Mat. No. 16−006) and Flexible Polyurethane (Mat. No. 16−021) . (i) Repair of hydraulic pipelines (Refer to AMM 20−23−11 Page block 201).

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 293.B.(1)

3.B.(1)(a)

3.B.(1)(b)

3.B.(1)(c)

3.B.(1)(d)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

B. MODIFICATION NOTE : The fastener removal and hole inspection sequence has been revised following in service experience. This will make sure all defects are identified before any rework has begun so that the necessary applicable repair can be carried out satisfactorily. For this reason it is necessary to follow the sequence given. NOTE : The actuating cylinder anchorage, the forward pintle fitting and the gear rib may all be worked on at the same time. (1) ACTUATING CYLINDER ANCHORAGE, LH and RH If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE for the 2nd option fastener and washers, quote this Service Bulletin (Refer to Table 1 and Tables 6 (Kit No A01) or 9 (Kit No A02) or 12 (Kit No A03) or 15 (Kit No A05) or 18 (Kit No A07) or 21 (Kit No A08)). The new fasteners are an interference fit in the rear spar and a clearance fit in the actuating cylinder anchorage. It is recommended that manufactured dowels are used to keep the actuating cylinder anchorage in position while you are reaming (Refer to 2.B.(6) ). Refer to Figure 6 , Sheet 1 or Figure 7 , Sheet 1 (a) Remove the bolts or studs from the position 52, 53, 56 thru 77, 80 and 81 from the actuating cylinder anchorage. As you remove each bolt : Measure the grip length required in each hole and make sure it is the same grip length of the oversize replacement bolt. Keep the removed bolts from holes 52, 53, 80, and 81 to use to temporarily hold the anchorage. Discard the remaining bolts. Do a test for cracks in each hole with the Eddy Current Technique (Refer to NTM 51−10−01 Part 6, Procedure A). NOTE : Any cracks, damage or assembly differences must be reported to : AIRBUS INDUSTRIE, Structures Repair Engineering Department, Fax : (33) 561 93 47 47 (b) Temporarily install the bolts in hole positions 52, 53, 80 and 81 with their nuts and washers. (c) Remove the bolts or studs from positions 54, 55, 78 and 79. As you remove each bolt : Measure the grip length required in each hole and make sure it is the same grip length of the oversize replacement bolt. Do a test for cracks in each hole with the Eddy Current Technique (Refer to NTM 51−10−01 Part 6, Procedure A). NOTE : Any cracks, damage or assembly differences must be reported to : AIRBUS INDUSTRIE, Structures Repair Engineering Departmen, Fax : (33) 561 93 47 47 (d) Use the applicable start reamer to open out the holes 54 thru 79 in the rear spar; the actuating cylinder anchorage and the Rib 3 brackets to the start−hole diameter for cold expansion (Refer to Table 4 and to SRM 51−48−00 and to Appendix 3 , Cold

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 303.B.(1)(e)

3.B.(1)(f)

3.B.(1)(g)

3.B.(1)(h)

3.B.(1)(i)

3.B.(1)(j)

3.B.(1)(k)

3.B.(1)(k)1

3.B.(1)(k)2

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN
Expansion Planning Information ). NOTE : In some positions it will be necessary to use the extra long reamer. NOTE : For Kit No. 571089A01 it is assumed that Service Bulletins A320−57−1004 and A320−57−1060 have been accomplished to the final−hole diameter for the 2nd option. For Kits No. 571089A02 and A03 it has been assumed that Service Bulletin A320−57−1060 has been accomplished to the final−hole diameter for the 2nd option. However if the service Bulletins A320−57−1004 and A320−57−1060 have not been accomplished, for Kits No. 571089A01 thru A03 it will be necessary to open up the holes to post Service Bulletins A320−57−1004 and A320−57−1060 2nd option final−hole diameter. (e) Install the applicable dowels for the start−hole diameter in holes 54 and 55 and in holes 78 and 79 and use the old bolts to clamp the anchorage. (f) Remove the bolts or studs from hole positions 52, 53, 80 and 81 and repeat the procedures at step [*]for holes 52, 53, 80 and 81. (g) Remove and keep the nuts, washers, bolts and the brackets that attach the actuating cylinder anchorage to the web of the side stay fitting at Rib 2. (h) Remove dowels and old bolts and remove the actuating cylinder anchorage and visually inspect it. (i) Remove and keep the nuts, bolts and the brackets from the forward face of the rear spar at Rib 3, in front of holes 52 thru 55. For applicable aircraft, where throat washers are installed on the forward face of the rear spar at holes 61 and 63, remove them. (j) Use a plastic tool, fine scotch brite and LOTOXANE Solvent (Mat. No. 11−026) to clean the actuating cylinder anchorage; the Rib 3 brackets, the throat washers and the rear spar (front and rear faces). (k) At each hole in the positions 52 thru 81 : 1 Cold expand the hole in the inner rear spar only (Refer to Table 4 and to SRM 51−48−00 and to Appendix Appendix 3 , Cold Expansion Planning Information). NOTE : The instruction in SRM 51−48−00, paragraph 2.A.(13) does not apply without consultation with AIRBUS INDUSTRIE. 2 Use the applicable intermediate reamers to open out the holes 52 thru 81 on the actuating cylinder anchorage,the Rib 3 brackets and the throat washers to the same diameter as the post−cold expansion hole diameter on the rear spar (Refer to Appendix Appendix 3 , Cold Expansion Planning

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 313.B.(1)(k)3

3.B.(1)(k)4

3.B.(1)(k)5

3.B.(1)(k)6

3.B.(1)(k)6 a

3.B.(1)(k)6 b

3.B.(1)(k)6 c

3.B.(1)(k)7

3.B.(1)(k)8

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Information). 3 Temporarily install the actuating cylinder anchorage and the Rib 3 brackets using the intermediate size dowels and the old bolts. 4 Use the applicable finish−reamer to ream the holes in the rear spar, the actuating cylinder anchorage and the Rib 3 brackets to the final−hole diameter (Refer to Table 4 and to SRM 51−48−00 and to Appendix Appendix 3 , Cold Expansion Planning Information). Make sure that each hole is reamed for an interference fit of the fastener in the rear spar. NOTE : It will be necessary to replace the intermediate size dowels with the final hole diameter dowels as the holes are reamed. 5 Do a 1st option final−gage check on the holes 52 thru 81 in the rear spar (Refer to Table 4 and to SRM 51−48−00 and to Appendix Appendix 3 , Cold Expansion Planning Information). NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE for the 2nd option fastener and washers, quote this Service Bulletin (Refer to Table 1 and Tables 6 (Kit No A01) or 9 (Kit No A02) or 12 (Kit No A03) or 15 (Kit No A05) or 18 (Kit No A07) or 21 (Kit No A08)). 6 2nd Option
a Any fastener hole that fails the 1st option final−gage check must be opened out to the next final−hole diameter using the 2nd option finish reamer (Refer to Table 4 and to SRM 51−48−00 and to Appendix Appendix 3 , Cold Expansion Planning Information). b Record the Hole No. of any hole that is required to be opened out to the 2nd option final−hole diameter. Make sure that the holes in the actuating cylinder anchorage and the Rib 3 brackets are opened out to the clearance fit for the correct option (Refer to paragraph 3.B.(1)(i) ).
c If necessary, do a 2nd option final−gage check on holes 52 thru 81 in the rear spar (Refer to Table 4 and to SRM 51−48−00 and to Appendix Appendix 3 , Cold Expansion Planning Information). NOTE : If the 2nd option final hole diameter is not within the limits, contact AIRBUS INDUSTRIE, Structures Repair Engineering Department, for instructions. 7 Remove the actuating cylinder anchorage and Rib 3 brackets. 8 Use the applicable finish−reamer to ream the holes in the throat washers.

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 32HOLE No. FIRST OPTION HOLE DIAMETER in (mm) SECOND OPTION HOLE DIAMETER in (mm)
74,75,76,77,78,79,80,81 0.4375−0.4395 (11.112−11−163) − 64,65,66,67,68,69,70,71 72,73 0.5000−0.5020 (12.700−12.751) 0.5156−0.5176 (13.096−13.147) 52,53,54,55,56,57,58 59 60,61 62,63 0.5781−0.5801 (14.684−14.734) 0.5937−0.5957 (15.080−15.131)
74,75,76,77,78,79,80,81 0.4375−0.4395 (11.112−11−163) − 66,67,68,69,70,71,72,73 0.5000−0.5020 (12.700−12.751) 0.5156−0.5176 (13.096−13.147) 52,53,54,55,56,57,58,59 60,61 62,63,64,65 0.5781−0.5801 (14.684−14.734) 0.5937−0.5957 (15.080−15.131)
74,75,76,77,78,79,80,81 0.4375−0.4395 (11.112−11−163) − 66,67,68,69,70,71,72,73 0.5000−0.5020 (12.700−12.751) 0.5156−0.5176 (13.096−13.147) 3.B.(1)(k)9

3.B.(1)(l)

3.B.(1)(l)1

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

9 If a bolt is to be installed, radius the edge of the hole (to clear the underhead radius of the bolt) on the forward face of the rear spar (Refer to SRM 51−44−11 ). NOTE : Bolts are installed from the forward face of the rear spar (inside the fuel tank), studs may be installed from the rear face or the forward face of the rear spar. CAUTION : MAKE SURE THAT THE HOLES IN THE ACTUATING CYLINDER AND THE RIB 3 BRACKETS ARE OPENED OUT TO THE APPLICABLE OPTION FOR EACH HOLE POSITION. THE HOLES THAT ARE 2nd OPTION WERE RECORDED IN PARAGRAPH 3.B.(1)(k)6 b . (l) Actuating Cylinder Anchorage, Rib 3 Brackets and the Throat Washers 1 Ream the holes in the actuating cylinder anchorage and the throat washers at holes 61 and 63 and also the holes 52 thru 55 in the Rib 3 bracket, to a clearance fit (Refer to Table 1 and SRM 51−44−11 ).

TABLE 1 Actuating Cylinder Anchorage

Kit No. 571089A01 :

Kit No. 571089A02 :

Kit No. 571089A03 :

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 33HOLE No. FIRST OPTION HOLE DIAMETER in (mm) SECOND OPTION HOLE DIAMETER in (mm) 52,53,54,55,56,57,58,59 60,61 0.5312−0.5332 (13.492−13.543) 0.5470−0.5490 (13.894−13.945) 62,63,64,65 0.5781−0.5801 (14.684−14.734) 0.5937−0.5957 (15.080−15.131)
74,75,76,77,78,79,80,81 0.4062−0.4082 (10.317−10.368) − 66,67,68,69,70,71,72,73 0.4687−0.4707 (11.905−11.956) − 52,53,54,55,56,57,58,59 60,61 62,63,64,65 0.5312−0.5332 (13.492−13.543) 0.5470−0.5490 (13.894−13.945)

3.B.(1)(l)2

3.B.(1)(l)3

3.B.(1)(l)4

3.B.(1)(l)5

3.B.(1)(l)6

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Kit No. 571089A05, A07 and A08 :

2 Apply protective treatment to the worked or damaged surfaces (Refer to SRM 51−21−11 ). 3 Apply sealant (Mat. No. 09−001) to the mating surfaces of the actuating cylinder anchorage, Rib 3 brackets, Rib 3 and the rear spar. 4 Use the fasteners removed in paragraph 3.B.(1)(i) (that attach the Rib 3 brackets to Rib 3) to loosely install the brackets at Rib 3. 5 Use the fasteners listed in the table for the applicable kit, to install the actuating cylinder anchorage and the Rib 3 brackets on the rear spar (Refer to SRM 51−42−11 ). NOTE : The fasteners are an interference fit in the rear spar and a clearance fit in the actuating cylinder anchorage and the Rib 3 brackets. NOTE : The studs have a lead at the opposite end to the square drive. Make sure that the studs are installed by the lead end first from the tank side. NOTE : The square drives of the studs must be cut off after installation if there is a possibility of them fouling hydraulic pipes etc. 6 Install the nuts and the 3.2 mm washers Refer to SRM 51−42−11 , SRM 51−76−12 and the applicable Table for the Kit No.). If necessary, additional 1.6 mm washers may be added, to a maximum of two. If these washers are installed on the studs, they must have an equal number at each end. Also, on studs, the threads must protrude the same at each end after the nuts have been torqued (Refer to paragraph 3.A.(2)(a) ).

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 343.B.(1)(l)7

3.B.(1)(l)8

3.B.(1)(l)9

3.B.(1)(m)

3.B.(2)

3.B.(2)(a)

3.B.(2)(a)1

3.B.(2)(a)2

3.B.(2)(a)3

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN
NOTE : If the washers do not fit correctly into the spotfaces, remove material from the washer (Refer to Figure 8 ). 7 Torque the fasteners loosely installed in paragraph 3.B.(1)(l)4 (Refer to SRM 51−42−11 and SRM 51−76−12 ). 8 Apply sealant (Mat. No. 09−001) to the mating surfaces of the brackets, removed in paragraph 3.B.(1)(g) , the actuating cylinder anchorage and the web of the sidestay fitting at Rib 2. 9 Use the nuts, the bolts and the washers removed in paragraph 3.B.(1)(g) to install the brackets to the actuating cylinder anchorage and the web of the side stay fitting. (m) Restore the fuel tank sealing (Refer to SRM 51−76−12 ). CAUTION : DO NOT REMOVE THE TAPER−LOK BOLTS FROM POSITIONS 1 THRU 4 AND 32 THRU 35 ON THE FORWARD PINTLE FITTING. (2) FORWARD PINTLE FITTING, LH and RH If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE for the 2nd option fastener and washers, quote this Service Bulletin (Refer to Table 2 and Tables 5 (Kit No A01) or 8 (Kit No A02) or 11 (Kit No A03) or 14 (Kit No A05) or 17 (Kit No A07) or 20 (Kit No A08)). The new fasteners introduced by this Service Bulletin are an interference fit in the rear spar and a clearance fit in the pintle fitting. Refer to Figure 6 , Sheets 1 and 2 or Figure 7 , Sheets 1 and 2 (a) At hole positions 6, 8, 10, 12, 14, 16, 18, 20, 22, 24, 26, 29, 31, 37, 39, 42, 44, 46, 48, 50 and 51 : 1 Remove and keep the nut, the washer and the bolt. Record the position where each bolt was removed from. NOTE : Where ‘blue’ nuts NSA 5475K are installed, splined sockets EWS 603−7 thru −10 will be required for their removal. 2 Measure the grip length required in each hole and make sure it is the same grip length of the oversize replacement fastener. 3 Visually inspect the pintle fitting and do a test for cracks in each fastener hole in the rear spar with the Eddy Current Technique (Refer to NTM 51−10−01 Part 6, Procedure A). NOTE : The NTM technique referenced above is only applicable to the fastener hole bores in the rear spar. It is not applicable to the fastener hole bores in the pintle fitting or the fastener hole bores in the joint strap at holes 8, 10 and 14. This is because the pintle fitting and joint strap are

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 353.B.(2)(a)4

3.B.(2)(b)

3.B.(2)(b)1

3.B.(2)(b)2

3.B.(2)(b)3

3.B.(2)(c)

3.B.(2)(c)1

3.B.(2)(c)1 a

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN
made from titanium alloy material. The NTM techniquie is applicable to alumuinium alloy material only. NOTE : Any cracks, damage or assembly differences must be reported to AIRBUS INDUSTRIE, Structures Repair Engineering Department. 4 Temporarily install the bolts kept at Step 1 in their original positions with their nuts and washers. Make sure they are fully tightened. (b) At hole positions 5, 7, 9, 11, 13, 15, 17, 19, 21, 23, 25, 27, 28, 30, 36, 38, 40, 41, 43, 45, 47 and 49 : 1 Remove the nut, the washer and the bolt. Record the position where each bolt was removed from. NOTE : Where ‘blue’ nuts NSA 5475K are installed, splined sockets EWS 603−7 thru −10 will be required for their removal. 2 Measure the grip length required in each hole and make sure it is the same grip length of the oversize replacement fastener. 3 Visually inspect the pintle fitting and do a test for cracks in each fastener hole in the rear spar with the Eddy Current Technique (Refer to NTM 51−10−01 Part 6, Procedure A). NOTE : The NTM technique referenced above is only applicable to the fastener hole bores in the rear spar. It is not applicable to the fastener hole bores in the pintle fitting or the fastener hole bores in the joint strap at holes 7, 11 and 13. This is because the pintle fitting and joint strap are made from titanium alloy material. The NTM techniquie is applicable to alumuinium alloy material only. NOTE : Any cracks, damage or assembly differences must be reported to AIRBUS INDUSTRIE, Structures Repair Engineering Department. CAUTION : COLD EXPAND THE HOLES IN THE SEQUENCE DETAILED IN THE PARAGRAPHS 3.B.(2)(c) AND 3.B.(2)(d) THAT FOLLOW. (c) At hole positions 5, 7, 9, 11, 13, 15, 17, 19, 21, 23, 25, 27, 28, 30, 36, 38, 40, 41, 43, 45, 47 and 49 : 1 At each Hole : The bracket(s) can stay on the pintle fitting while cold expansion is done.
a Use a plastic tool, fine scotch brite and LOTOXANE Solvent (Mat. No. 11−026) to clean the pintle fitting and the forward face of the rear spar.

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 363.B.(2)(c)1 b

3.B.(2)(c)1 c

3.B.(2)(c)1 d

3.B.(2)(c)1 e

3.B.(2)(c)1 f

3.B.(2)(c)1 g

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

b Use the applicable start reamer to open out the holes to the start−hole diameter for cold expansion (Refer to Table 4 and to SRM 51−48−00 and to Appendix 3 , Cold Expansion Planning Information). NOTE : For Kit No. 571089A01 thru A03 it is assumed that Service Bulletin A320−57−1060 has been accomplished to the final−hole diameter for the 2nd option. However, if the Service Bulletin A320−57−1060 has not been accomplished, for Kits Nos. 571089A01 thru A03, it will be necessary to open the holes to Post A320−57−1060 2nd option final−hole diameter.
c Cold expand the hole (Refer to Table 4 and to SRM 51−48−00 and to Appendix 3 , Cold Expansion Planning Information). NOTE : The instruction in SRM 51−48−00 paragraph 2.A.(13) does not apply without consultation with AIRBUS INDUSTRIE. d Use the applicable finish−reamer to ream the holes in the rear spar and the pintle fitting to the 1st option final−hole diameter (Refer to Table 4 and to SRM 51−48−00 and to Appendix 3 , Cold Expansion Planning Information). Make sure that the hole is reamed for an interference fit of the fastener.
e Do a first option final−gage check on the hole in the rear spar (Refer to Table 4 and to SRM 51−48−00 and to Appendix 3 , Cold Expansion Planning Information). NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE for the 2nd option fastener and washers, quote this Service Bulletin (Refer to Table 2 and Tables 5 (Kit No A01) or 8 (Kit No A02) or 11 (Kit No A03) or 14 (Kit No A05) or 17 (Kit No A07) or 20 (Kit No A08)). f Any fastener hole that fails the 1st option final−gage check must be opened out to the next final−hole diameter using the 2nd option finish−reamer (Refer to Table 4 and to SRM 51−48−00 and to Appendix 3 , Cold Expansion Planning Information). Record the position No. of any hole required to be opened out to the 2nd option final−hole diameter. Make sure that any hole in the pintle fitting is opened out to the clearance fit for the correct option. g If necessary, do a 2nd option final−gage check on the hole in the rear spar (Refer to Table 4 and to SRM 51−48−00 and to Appendix 3 , Cold Expansion Planning Information).

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 37HOLE No. FIRST OPTION HOLE DIA. ins. (mm) SECOND OPTION HOLE DIA. ins. (mm) Kit No. 571089A01 thru A03 :

Kit No. 571089A05, A07 and A08 : 3.B.(2)(c)1 h

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN
NOTE : If the 2nd option final hole diameter is not within the limits, contact AIRBUS INDUSTRIE, Structures Repair Engineering Department, for instructions. h Counterbore the holes in the pintle fitting, to a clearance fit (Refer to Table 2 and SRM 51−44−11 and Figure 6 or Figure 7 , Sheet 2 , Section D−D). Make sure that the counterbore goes into the rear spar between 0.0 and 1.0 mm (0.0 and 0.04 in) (Refer to Table 3). NOTE : Use a suitable lock collar as a reamer stop to control the counterbore depth. TABLE 2 Pintle Fitting

39,40,43,44,45,48,49 50,51 0.4375−0.4395 (11.112−11.163 − 36,37,38,41,42,46,47 0.5000−0.5020 (12.700−12.751) 0.5156−0.5176 (13.096−13.147) 5,17,18,23,24,25,26,27 28,29,30,31 0.5781−0.5801 (14.684−14.735) 0.5937−0.5957 (15.080−15.131)
13,14,16,19 0.6406−0.6426 (16.271−16.322) 0.6562−0.6582 (16.667−16.718) 6,7,8,9,10,11,12,15,20 21,22 0.7030−0.7050 (17.856−17.907) 0.7190−0.7210 (18.263−18.313)

39,40,43,44,45,48,49 50,51 0.4062−0.4082 (10.317−10.368) − 36,37,38,41,42,46,47 0.4687−0.4707 (11.905−11.956) − 5,17,18,23,24,25,26,27 28,29 30,31 0.5312−0.5332 (13.492−13.543) 0.5470−0.5490 (13.894−13.944)
13,14,16,19 0.5937−0.5957 (15.080−15.131) 0.6090−0.6110 (15.469−15.519) 6,7,8,9,10,11,12,15,20 21,22 0.6562−0.6582 (16.667−16.718) 0.6720−0.6740 (17.069−17.120)

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 38HOLE No. NOMINAL THICKNESS OF PINTLE FITTING mm (in.) REAMER STOP SETTING mm (in.)

6,7*,8*,9,10*,11* 22.5 (0.866) 22.8 to 23.3
12 (0.898 to 0.917) 13*,14*,15 20.5 (0.807) 20.8 to 21.3
(0.819 to 0.838) 16,17 10.0 (0.394) 10.3 to 10.8
(0.406 to 0.425) 18,19 9.0 (0.354) 9.3 to 9.8 (0.366 to 0.385) 5,20,21,22 15.0 (0.590) 15.3 to 15.8
(0.603 to 0.622) 23,24,25,26,27 7.0 (0.275) 7.3 to 7.8 (0.288 to 0.307) 28,46,47 10.0 (0.394) 10.3 to 10.8
(0.406 to 0.425) 48,49,50 6.0 (0.236) 6.3 to 6.8 (0.248 to 0.267) 29,30,31 15.0 (0.590) 15.3 to 15.8
(0.603 to 0.622) 37,38,41,42 10.0 (0.394) 10.3 to 10.8
(0.406 to 0.425) 39,40,43,44,45, 6.0 (0.236) 6.3 to 6.8 51,36 (0.248 to 0.267)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

TABLE 3 Reamer Stop/Counterbore Depths

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 39* Holes where the counterbore extends through the reinforcing strap, which is included within the pintle fitting thickness.

3.B.(2)(c)1 i

3.B.(2)(c)1 j

3.B.(2)(c)2

3.B.(2)(c)3

3.B.(2)(c)4

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

i Radius the edge of the holes, where bolts are installed, on the forward face of the rear spar except for the holes in positions 40, 45 and 51 where the underhead radius is on the rear face of the pintle fitting (Refer to SRM 51−44−11 ). j Restore the protective finish as necessary (Refer to SRM 51−21−11 ). 2 Install the bolts except those in positions 40, 45 and 51 with the head on the forward face of the rear spar (from inside the fuel tank)(Refer to SRM 51−42−11 and SRM 51−76−12 ). NOTE : The fasteners are an interference fit in the rear spar and a clearance fit in the pintle fitting. 3 Install the nuts and the 3.2 mm washers (Refer to SRM 51−42−11 , SRM 51−76−12 and the applicable Table for the Kit No.). If necessary, additional 1.6 mm washers may be installed to a maximum of two. NOTE : If the washers do not fit correctly into the spotfaces, remove material from the washer (Refer to Figure 8 ). 4 Install the studs, the nuts and the 3.2 mm washers (Refer to SRM 51−42−11 , SRM 51−76−12 and the applicable Table for the Kit No.). Make sure that the corrosion resistant washers marked * are installed adjacent to the pintle fitting. If necessary, additional 1.6 mm washers may be installed to a maximum of two. The number of washers under the nuts must be the same at each end. Make sure that the thread extends from each nut equally, after the nuts have been torqued. NOTE : Because they may foul the hydraulic pipe, Item (77) the studs for hole positions 17, 18, 24 and 25 may need to be cut before installation (Refer to Para. 3.D.(5)(n) . The data recorded at Para. 3.A.(1)(n) 13 should be used for reference. NOTE : The fasteners are an interference fit in the rear spar and a clearance fit in the pintle fitting.

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 403.B.(2)(d)

3.B.(2)(e)

3.B.(3)

3.B.(3)(a)

3.B.(3)(a)1

3.B.(3)(a)2

3.B.(3)(a)3

3.B.(3)(a)4

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN
NOTE : The studs have a lead at the opposite end to the square drive. Make sure that the studs are installed by the lead end first. They may be installed from the front or the rear of the rear spar. NOTE : The square drives of the studs must be cut off after installation if there is a possibility of them fouling hydraulic pipes etc. (d) Remove the nut, the washer and the bolt at hole positions 6, 8, 10, 12, 14, 16, 18, 20, 22, 24, 26, 29, 31, 37, 39, 42, 44, 46, 48, 50 and 51 do paragraphs 3.B.(2)(c)1 thru 3.B.(2)(c)4

. (e) Repair the fuel tank sealing (Refer to SRM 51−76−12 ). (3) GEAR RIB, LH and RH If the 1st option final hole diameter is not within the limits,send a purchase order to MSC, AIRBUS INDUSTRIE for the 2nd option fastener and washers, quote this Service Bulletin (Refer to Table 7 (Kit No A01) or 10 (Kit No A02) or 13 (Kit No A03) or 16 (Kit No A05) or 19 (Kit No A07) or 22 (Kit No A08)). The new fasteners introduced by this Service Bulletin are an interference fit in the rear spar and the gear rib. Refer to Figure 6 , Sheet 1 and 3 or Figure 7 , Sheet 1 and 3 (a) At hole positions 83, 85, 87, 89, 91, 93, 95, 97, 99 and 101: 1 Remove and keep the nut, the washer and the bolt. Record the position where each bolt was removed from. 2 Measure the grip length required in each hole and make sure it is the same grip length of the oversize replacement fastener. 3 Visually inspect the gear rib and do a test for cracks in each hole with the Eddy Current Technique (Refer to NTM 51−10−01 Part 6, Procedure A). NOTE : The NTM technique referenced above is only applicable to the fastener hole bores in the rear spar and gear rib. It is not applicable to the fastener hole bores in the joint strap at holes 85, 91, 95 and 101. This is because the joint strap is made from titanium alloy material. The NTM techniquie is applicable to alumuinium alloy material only. NOTE : Any cracks, damage or assembly differences must be reported to AIRBUS INDUSTRIE, Structure Repair Engineering Department. CAUTION : BECAUSE OF THE LIMITED ACCESS EXTREME CARE MUST BE TAKEN WHEN DRILLING AND REAMING TO MAKE SURE TOLERANCES ARE NOT EXCEEDED. 4 Temporarily install the bolts kept at Step 1 in their original positions with their nuts and washers. Make sure they are fully tightened.

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 413.B.(3)(b)

3.B.(3)(b)1

3.B.(3)(b)2

3.B.(3)(b)3

3.B.(3)(c)

3.B.(3)(c)1

3.B.(3)(c)1 a

3.B.(3)(c)1 b

3.B.(3)(c)1 c

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN
(b) At hole positions 82, 84, 86, 88, 90, 92, 94, 96, 98 and 100: 1 Remove the nut, the washer and the bolt. Record the position where each bolt was removed from. 2 Measure the grip length required in each hole and make sure it is the same grip length of the oversize replacement fastener. 3 Visually inspect the gear rib and do a test for cracks in each hole with the Eddy Current Technique (Refer to NTM 51−10−01 Part 6, Procedure A). NOTE : The NTM technique referenced above is only applicable to the fastener hole bores in the rear spar and gear rib. It is not applicable to the fastener hole bores in the joint strap at holes 86, 90, 96 and 100. This is because the joint strap is made from titanium alloy material. The NTM techniquie is applicable to alumuinium alloy material only. NOTE : Any cracks, damage or assembly differences must be reported to AIRBUS INDUSTRIE, Structure Repair Engineering Department. CAUTION : BECAUSE OF THE LIMITED ACCESS EXTREME CARE MUST BE TAKEN WHEN DRILLING AND REAMING TO MAKE SURE TOLERANCES ARE NOT EXCEEDED. CAUTION : COLD EXPAND THE HOLES IN THE SEQUENCE DETAILED IN THE PARAGRAPHS 3.B.(3)(c) AND 3.B.(3)(d) THAT FOLLOW. (c) At hole positions 82, 84, 86, 88, 90, 92, 94, 96, 98 and 100: 1 At Each Hole :
a Use a plastic tool, fine scotch brite and LOTOXANE Solvent (Mat. No. 11−026) to clean the gear rib and the forward face of the rear spar. b Use the applicable start reamer to open out the holes to the start−hole diameter for cold expansion (Refer to Table 4 and to SRM 51−48−00 and to Appendix 3 , Cold Expansion Planning Information). NOTE : For Kit No. 571089A01 it is assumed that Service Bulletin A320−57−1004 has been accomplished to the final−hole diameter for holes 82 and 83. However, if the Service Bulletin A320−57−1004 has not been accomplished, for Kits No. 571089A01, it will be necessary to open the holes 82 and 83 to Post A320−57−1004 final−hole diameter.
c Cold expand the hole (Refer to Table 4 and to SRM 51−48−00 and to Appendix 3 , Cold Expansion Planning Information).

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 423.B.(3)(c)1 d

3.B.(3)(c)1 e

3.B.(3)(c)1 f

3.B.(3)(c)1 g

3.B.(3)(c)1 h

3.B.(3)(c)2

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN
NOTE : The instruction in SRM 51−48−00 paragraph 2.A.(13) does not apply without consultation with AIRBUS INDUSTRIE. d Use the applicable finish−reamer to ream the holes in the rear spar and the gear rib to the 1st option final−hole diameter (Refer to Table 4 and to SRM 51−48−00 and to Appendix 3 , Cold Expansion Planning Information). Make sure that the hole is reamed for an interference fit of the fastener.
e Do a 1st option final−gage check on the hole in the rear spar and the gear rib (Refer to Table 4 and to SRM 51−48−00 and to Appendix 3 , Cold Expansion Planning Information). NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE for the 2nd option fastener and washers, quote this Service Bulletin (Refer to Table 7 (Kit No A01) or 10 (Kit No A02) or 13 (Kit No A03) or 16 (Kit No A05) or 19 (Kit No A07) or 22 (Kit No A08)). f Any fastener hole that fails the 1st option final−gage check must be opened out to the next final−hole diameter using the 2nd option finish−reamer (Refer to Table 4 and to SRM 51−48−00 and to Appendix 3 , Cold Expansion Planning Information). Record the position No. of any hole required to be opened out to the 2nd option final−hole diameter. g If necessary, do a 2nd option final−gage check on the hole in the rear spar and gear rib (Refer to Table 4 and to SRM 51−48−00 and to Appendix 3 , Cold Expansion Planning Information). NOTE : If the 2nd option final hole diameter is not within the limits,contact AIRBUS INDUSTRIE, Structures Repair Engineering Department, for instructions. h Restore the protective finish as necessary (Refer to SRM 51−21−11 ). 2 Install the studs, the nuts and the 3.2 mm washers (Refer to SRM 51−42−11 , SRM 51−76−12 and the applicable Table for the Kit No.). If necessary, additional 1.6 mm washers may be installed to a maximum of two. The number of washers under the nuts must be the same at each end. Make sure that the thread extends from each nut equally, after the nuts have been torqued. NOTE : If the washers do not fit correctly into the spotfaces, remove material from the washer (Refer to Figure 8 ).

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 433.B.(3)(c)3

3.B.(3)(c)3 a

3.B.(3)(c)3 b

3.B.(3)(c)3 c

3.B.(3)(c)3 d

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : The fasteners are an interference fit in the rear spar and in the gear rib. NOTE : At hole positions 82 thru 91 the pintail studs are installed with the square drive on the forward face of the rear spar (from inside the fuel tank). NOTE : At hole positions 92 thru 101 the studs may be installed from the front or the rear of the rear spar. NOTE : The studs have a lead at the opposite end to the square drive. Make sure that the studs are installed by the lead end first. NOTE : The square drives of the studs must be cut off after installation if there is a possibility of them fouling hydraulic pipes etc. NOTE : Holes 85, 86, 90, 91, 95, 96, 100 and 101 have a titanium reinforcing plate between the gear rib and the rear spar. Because of this the studs for these holes are zinc plated. 3 The Installation of studs in Holes 82 thru 91 is as follows (Refer to Figure 6 or Figure 7 , Sheet 3 , Section F−F):
a Install the stud from inside the tank until the pintail protrudes through the gear rib. CAUTION : MAKE SURE THAT THE STUD DOES NOT TURN WHEN THE STUD IS PULLED THROUGH THE HOLE. IF THE STUD TURNS THE INTERFERENCE FIT OF THE STUD WILL BE DEGRADED. b Install a suitable thrust bearing on the pintail to give a flat bearing surface. Install suitable packers (washers) and a 9/16 UNC nut on the pintail. Use a suitable lubricant on the threads of the pintail and the 9/16 UNC nut. Make sure that the stud does not turn and tighten the nut to pull the stud through the hole. CAUTION : DO NOT PULL THE PINTAIL THROUGH TOO FAR BEFORE THE ADDITION OF EXTRA PACKERS. BECAUSE THERE IS LIMITED SPACE, IF THE PACKERS ARE NOT FREQUENTLY ADDED THERE WILL BE A POINT WHEN IT WILL BE IMPOSSIBLE TO REMOVE THE NUT TO ADD THE PACKERS.
c When the thread protrudes sufficiently through the nut, release the tension on the thread. Remove the nut and put on additional packers. Tighten the nut and continue to pull the stud through the hole. Repeat this operation until the stud is in its correct position (Refer to Figure 6 or Figure 7 , Sheet 3 , Section F−F). d With the stud in the correct position, release the tension on the stud. Turn the nut counter clockwise and clear the undercut of the pintail of packers and the

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 44HOLE No. COLD EXPANSION START HOLE DIA. in ins.(mm) FTI TOOL (STDN) FIRST OPTION FINAL HOLE DIA.in ins.(mm) SECOND OPTION FINAL HOLE DIA.in ins.(mm) KIT No. 571089A01 39,40,43,44,45 48,49,50,51,74 75,76,77,78,79 80,81 0.4060−0.4090 (10.312−10.388) 12−3−N 0.4320−0.4340 (10.973−11.024) −

36,37,38,41,42 46,47,64,65,66 67,68,69,70,71 72,73 0.4740−0.4770 (12.040−12.116) 16−0−N 0.4945−0.4965 (12.560−12.611) 0.5101−0.5121 (12.957−13.007)

5,17,18,23,24 25,26,27,28,29 30,31,52,53,54 55,56,57,58,59 60,61,62,63 0.5530−0.5560 (14.046−14.122) 18−1−N 0.5731−0.5751 (14.557−14.608) 0.5887−0.5907 (14.953−15.004)

13,14,16,19 0.6130−0.6160 (15.570−15.646) 20−1−N 0.6356−0.6376 (16.144−16.195) 0.6512−0.6532 (16.540−16.591) 3.B.(3)(c)3 e

3.B.(3)(c)3 f

3.B.(3)(c)3 g

3.B.(3)(d)

3.B.(3)(e)

3.B.(3)(f)

3.B.(4)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN
thrust bearing. CAUTION : MAKE SURE THAT YOU TAKE GREAT CARE WHEN CUTTING TO PROTECT THE ADJACENT STRUCTURE. PARTICULARLY THE REAR SPAR AND THE GEAR RIB.
e Cut through the undercut and remove the pintail. Remove the packers the thrust bearing and the nut. f Apply protective treatment as applicable to the cut ends of the studs (Refer to Standard Practices Para. 3.A.(2)(h) ). g Install the washers and nuts as detailed in paragraph 3.B.(3)(c)2 . (d) Remove the nut, the washer and the bolt at hole positions 83, 85, 87, 89, 91, 93, 95, 97, 99 and 101 and do paragraphs 3.B.(3)(c)1 thru [*]. (e) Restore the fuel tank sealing (Refer to SRM 51−76−12 ). (f) Restore the surface finish (Refer to SRM 51−75−12 ). (4) Cold Expansion Tooling Kits A01, A02 and A03 : Refer to FTI for Tooling List A320−57−1089−1. Kits A05, A07 and A08 : Refer to Appendix 4
TABLE 4 − COLD EXPANSION TOOLING

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 45HOLE No. COLD EXPANSION START HOLE DIA. in ins.(mm) FTI TOOL (STDN) FIRST OPTION FINAL HOLE DIA.in ins.(mm) SECOND OPTION FINAL HOLE DIA.in ins.(mm) 84,85,86,87,88 89,90,91,92,93 94,95,96,97,98 99,100,101 0.6310−0.6340 (16.027−16.104) 20−2−N 0.6512−0.6532 (16.540−16.591) 0.6670−0.6690 (16.942−16.993)

6,7,8,9,10,11,1 2 15,20,21,22,82 83 0.6750−0.6780 (17.145−17.221) 22−1−N 0.6980−0.7000 (17.729−17.780) 0.7137−0.7157 (18.128−18.179)

KIT No. 571089A02 39,40,43,44,45 48,49,50,51,74 75,76,77,78,79 80,81 0.4060−0.4090 (10.312−10.388) 12−3−N 0.4320−0.4340 (10.973−11.024) −

36,37,38,41,42 0.4740−0.4770 16−0−N 0.4945−0.4965 0.5101−0.5121 46,47,66,67,68 (12.040−12.116) (12.560−12.611) (12.957−13.007) 69,70,71,72,73 5,17,18,23,24, 18−1−N 0.5887−0.5907 25,26,27,28,29, (14.953−1 5.004) 30,31,52,53,54, 55,56,57,58,59, 60,61,62,63, 64,65 13,14,16,19 0.6130−0.6160 20−1−N 0.6356−0.6376 0.6512−0.6532 (15.570−15.646) (16.144−16.195) (16.540−16.591)
84,85,86,87,88 0.6310−0.6340 20−2−N 0.6512−0.6532 0.6670−0.6690 89,90,91,92,93 (16.027−16.104) (16.540−16.591) (16.942−16.993) 94,95,96,97,98 99,100,101 6,7,8,9,10,11 0.6750−0.6780 22−1−N 0.6980−0.7000 0.7137−0.7157 12,15,20,21,22 (17.145−17.221) (17.729−17.780) (18.128−18.179) 82,83

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

0.5530−0.5560 (14.046−14.122) 0.5731−0.5751 (14.557−14.608)

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 46HOLE No. COLD EXPANSION START HOLE DIA. in ins.(mm) FTI TOOL (STDN) FIRST OPTION FINAL HOLE DIA.in ins.(mm) SECOND OPTION FINAL HOLE DIA.in ins.(mm) KIT No. 571089A03 39,40,43,44,45 0.4060−0.4090 12−3−N 0.4320−0.4340 − 48,49,50,51,74 (10.312−10.388) (10.973−11.024) 75,76,77.78,79 80,81 36,37,38,41,42 0.4740−0.4770 16−0−N 0.4945−0.4965 0.5101−0.5121 46,47,66,67,68 (12.040−12.116) (12.560−12.611) (12.957−13.007) 69,70,71,72,73 52,53,54,55,56 0.5050−0.5080 16−2−N 0.5257−0.5277 0.5410−0.5430 57,58,59,60,61, (12.827−12.903) (13.353−13.404) (13.741−13.792) 5,17,18,23,24 0.5530−0.5560 18−1−N 0.5731−0.5751 0.5887−0.5907 25,26,27,28,29 (14.046−14.122) (14.557−14.608) (14.953−15.004) 30,31,62,63,64 65 13,14,16,19 0.6130−0.6160 20−1−N 0.6356−0.6376 0.6512−0.6532 (15.570−15.646) (16.144−16.195) (16.540−16.591) 82,83,84,85,86 0.6310−0.6340 20−2−N 0.6512−0.6532 0.6670−0.6690 87,88,89,90,91 (16.027−16.104) (16.540−16.591) (16.942−16.993) 92,93,94,95,96 97,98,99,100 101 6,7,8,9,10,11 0.6750−0.6780 22−1−N 0.6980−0.7000 0.7137−0.7157 12,15,20,21,22 (17.145−17.221) (17.729−17.780) (18.128−18.179) KIT No. 571089A05, A07 AND A08 39,40,43,44,45 0.3750−0.3780 12−1−N 0.4007−0.4027 − 48,49,50,51,74 (9.525−9.601) (10.178−10.228) 75,76,77.78,79 80,81 36,37,38,41,42 0.4370−0.4400 14−1− 0.4632−0.4652 −

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 47HOLE No. COLD EXPANSION START HOLE DIA. in ins.(mm) FTI TOOL (STDN) FIRST OPTION FINAL HOLE DIA.in ins.(mm) SECOND OPTION FINAL HOLE DIA.in ins.(mm) 46,47,66,67,68 (11.100−11.176) (11.765−11.816) 69,70,71,72,73 5,17,18,23,24 0.5050−0.5080 16−2−N 0.5257−0.5277 0.5410−0.5430 25,26,27,28,29 (12.827−12.903) (13.353−13.404) (13.741−13.792) 30,31,52,53,54 55,56,57,58,59 60,61,62,63,64 65 13,14,16,19 0.5680−0.5710 18−2−N 0.5887−0.5907 0.6040−0.6060 (14.427−14.503) (14.953−15.004) (15.342−15.392) 6,7,8,9,10,11 0.6310−0.6340 20−2−N 0.6512−0.6532 0.6670−0.6690 12,15,20,21,22 (16.027−16.104) (16.540−16.591) (16.942−16.993) 82,83,84,85,86 87,88,89,90,91 92,93,94,95,96 97,98,99,100 101

KIT A01 Hole No. 1st Option Fasteners 2nd Option Fasteners FASTENERS FOR THE PINTLE FITTING : 5 BOLT NSA5479VHK9−26X BOLT NSA5479VHK9−26Y NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297931400 WASHER D5725297931600 WASHER D5725297928400 WASHER D5725297928600 3.B.(5)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

(5) Kit No. 571089A01 PINTLE FITTING 1ST AND 2ND OPTION FASTENERS IN HOLE NUMBER SEQUENCE NOTE : In the table that follows the washers marked * are corrosion resistant and must be installed adjacent to the pintle fitting.
TABLE 5

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 48KIT A01 Hole No. 1st Option Fasteners 2nd Option Fasteners 6 STUD D5725297732800 STUD D5725297733800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 7,8 STUD D5725297732600 STUD D5725297733600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 9 STUD D5725297732800 STUD D5725297733800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 10,11 STUD D5725297732600 STUD D5725297733600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 12 STUD D5725297732800 STUD D5725297733800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 13,14 BOLT NSA5479VHK10−30X BOLT NSA5479VHK10−30Y

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 49KIT A01 Hole No. 1st Option Fasteners 2nd Option Fasteners NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297932000 WASHER D5725297932200 WASHER D5725297929000 WASHER D5725297929200 15 STUD D5725297732400 STUD D5725297733400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 16 BOLT NSA5479VHK10−23X BOLT NSA5479VHK10−23Y NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297932000 WASHER D5725297932200 WASHER D5725297929000 WASHER D5725297929200 17 STUD D5725297723600 STUD D5725297725200 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297931400* WASHER D5725297931600* WASHER D5725297921000 WASHER D5725297921200 WASHER D5725297928400* WASHER D5725297928600* 18 STUD D5725297723400 STUD D5725297725000 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297931400* WASHER D5725297931600* WASHER D5725297921000 WASHER D5725297921200 WASHER D5725297928400* WASHER D5725297928600* 19 BOLT NSA5479VHK10−20X BOLT NSA5479VHK10−20Y NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297932000 WASHER D5725297932200 WASHER D5725297929000 WASHER D5725297929200 20,21,22 STUD D5725297732000 STUD D5725297733000 NUT NSA5472−10K7 NUT NSA5472−10K7

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 50KIT A01 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 23 BOLT NSA5479VHK9−20X BOLT NSA5479VHK9−20Y NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297931400 WASHER D5725297931600 WASHER D5725297928400 WASHER D5725297928600 24 STUD D5725297723200 STUD D5725297724800 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297931400* WASHER D5725297931600* WASHER D5725297921000 WASHER D5725297921200 WASHER D5725297928400* WASHER D5725297928600* 25 STUD D5725297723000 STUD D5725297724600 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297931400* WASHER D5725297931600* WASHER D5725297921000 WASHER D5725297921200 WASHER D5725297928400* WASHER D5725297928600* 26,27 BOLT NSA5479VHK9−17X BOLT NSA5479VHK9−17Y NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER−D5725297931400 WASHER−D5725297931600 WASHER D5725297928400 WASHER D5725297928600 28 BOLT NSA5479VHK9−18X BOLT NSA5479VHK9−18Y NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297931400 WASHER D5725297931600 WASHER D5725297928400 WASHER D5725297928600 29,30,31 BOLT NSA5479VHK9−26X BOLT NSA5479VHK9−26Y NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297931400 WASHER D5725297931600

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 51KIT A01 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297928400 WASHER D5725297928600 36 BOLT NSA5479VHK8−15 BOLT NSA5479VHK8−15X NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297930600 WASHER D5725297930800 WASHER AN960C816 WASHER D5725297927800 37 BOLT NSA5479VHK8−18 BOLT NSA5479VHK8−18X NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297930600 WASHER D5725297930800 WASHER AN960C816 WASHER D5725297927800 38 BOLT NSA5479VHK8−14 BOLT NSA5479VHK8−14X NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297930600 WASHER D5725297930800 WASHER AN960C816 WASHER D5725297927800 39 BOLT NSA5479VHK7−12 − NUT NSA5472−7K7 WASHER−D5725297930200 WASHER AN960C716 40 BOLT NSA5479VHK7−12 − NUT NSA5472−7K7 WASHER D5725297923600 WASHER AN960KD716 41 BOLT NSA5479VHK8−18 BOLT NSA5479VHK8−18X NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297930600 WASHER D5725297930800 WASHER AN960C816 WASHER D5725297927800 42 BOLT NSA5479VHK8−15 BOLT NSA5479VHK8−15X NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297930600 WASHER D5725297930800 WASHER AN960C816 WASHER D5725297927800 43,44 BOLT NSA5479VHK7−13 − NUT NSA5472−7K7

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 52KIT A01 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297930200 WASHER AN960C716 45 BOLT NSA5479VHK7−12 − NUT NSA5472−7K7 WASHER−D5725297923600 WASHER AN960KD716 46,47 BOLT NSA5479VHK8−14 BOLT NSA5479VHK8−14X NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297930600 WASHER D5725297930800 WASHER AN960C816 WASHER D5725297927800 48,49,50 BOLT NSA5479VHK7−12 − NUT NSA5472−7K7 WASHER−D5725297930200 WASHER AN960C716 51 BOLT NSA5479VHK7−12 − NUT NSA5472−7K7 WASHER D5725297923600 WASHER AN960KD716

3.B.(6)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE, quoting this Service Bulletin for the 2nd option fastener and washers. NOTE : Where 2nd option fasteners are not listed, refer to AIRBUS INDUSTRIE, Structure Repair Engineering Department for further advice. (6) Kit No. 571089A01 ACTUATING CYLINDER ANCHORAGE 1ST AND 2ND OPTION FASTENERS IN HOLE NUMBER SEQUENCE

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 53Kit A01 Hole No. 1st Option Fasteners 2nd Option Fasteners FASTENERS FOR THE ACTUATING CYLINDER ANCHORAGE : 52,53 STUD D5725297723800 STUD D5725297725400 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297921000 WASHER D5725297921200 54,55 STUD D5725297724000 STUD D5725297725600 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297921000 WASHER D5725297921200 56,57,58 BOLT NSA5479VHK9−14X BOLT NSA5479VHK9−14Y 59 NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297921000 WASHER D5725297921200 60,62 STUD D5725297723000 STUD D5725297724600 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297921000 WASHER D5725297921200 61,63 STUD D5725297723600 STUD D5725297725200 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297921000 WASHER D5725297921200 64,65,66 BOLT NSA5479VHK8−13 BOLT NSA5479VHK8−13X 67,68,69 NUT NSA5472−8K7 NUT NSA5472−8K7 70,71 WASHER D5725297924000 WASHER D5725297924200 WASHER AN960KD816 WASHER D5725297920400 72,73 BOLT NSA5479VHK8−12 BOLT NSA5479VHK8−12X

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

TABLE 6

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 54Kit A01 Hole No. 1st Option Fasteners 2nd Option Fasteners NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297924000 WASHER D5725297924200 WASHER AN960KD816 WASHER D5725297920400 74,75,76 BOLT NSA5479VHK7−12 − 77,78,79 NUT NSA5472−7K7 80,81 WASHER D5725297923600 WASHER AN960KD716

Kit A01 Hole No. 1st Option Fasteners 2nd Option Fasteners FASTENERS FOR THE GEAR RIB 5: 82,83 STUD D5725297822800 STUD D5725297823000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297922200 WASHER D5725297922400 84 STUD D5725297820600 STUD D5725297821800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 85,86 STUD D5725297826000 STUD D5725297826400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 87,88 STUD D5725297820200 STUD D5725297821400 3.B.(7)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE, quoting this Service Bulletin for the 2nd option fastener and washers. (7) Kit No. 571089A01 GEAR RIB 1ST AND 2ND OPTION FASTENERS IN HOLE NUMBER SEQUENCE
TABLE 7

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 55Kit A01 Hole No. 1st Option Fasteners 2nd Option Fasteners NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 89 STUD D5725297821000 STUD D5725297822200 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 90,91 STUD D5725297826200 STUD D5725297826600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 92,93 STUD D5725297727400 STUD D5725297729600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 94 STUD D5725297728400 STUD D5725297730600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 95,96 STUD D5725297738200 STUD D5725297738600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 97,98 STUD D5725297727200 STUD D5725297729400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 99 STUD D5725297727800 STUD D5725297730000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 56Kit A01 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297921800 WASHER D5725297922000 100,101 STUD D5725297738000 STUD D5725297738400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000

Kit A02 Hole No. 1st Option Fasteners 2nd Option Fasteners FASTENERS FOR THE PINTLE FITTING : 5 BOLT NSA5479VHK9−26X BOLT NSA5479VHK9−26Y NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297931400 WASHER D5725297931600 WASHER D5725297928400 WASHER D5725297928600 6 STUD D5725297732800 STUD D5725297733800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 7,8 STUD D5725297732600 STUD D5725297733600 3.B.(8)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE, quoting this Service Bulletin for the 2nd option fastener and washers. NOTE : Where 2nd option fasteners are not listed, refer to AIRBUS INDUSTRIE, Structure Repair Engineering Department for further advice. (8) Kit No. 571089A02 PINTLE FITTING 1ST AND 2ND OPTION FASTENERS IN HOLE NUMBER SEQUENCE NOTE : In the table that follows the washers marked * are corrosion resistant and must be installed adjacent to the pintle fitting.
TABLE 8

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 57Kit A02 Hole No. 1st Option Fasteners 2nd Option Fasteners NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 9 STUD D5725297732800 STUD D5725297733800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 10,11 STUD D5725297732600 STUD D5725297733600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 12 STUD D5725297732800 STUD D5725297733800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 13,14 BOLT NSA5479VHK10−30X BOLT NSA5479VHK10−30Y NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297932000 WASHER D5725297932200 WASHER D5725297929000 WASHER D5725297929200 15 STUD D5725297732400 STUD D5725297733400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800*

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 58Kit A02 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 16 BOLT NSA5479VHK10−23X BOLT NSA5479VHK10−23Y NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297932000 WASHER D5725297932200 WASHER D5725297929000 WASHER D5725297929200 17 STUD D5725297723600 STUD D5725297725200 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297931400* WASHER D5725297931600* WASHER D5725297921000 WASHER D5725297921200 WASHER D5725297928400* WASHER D5725297928600* 18 STUD D5725297723400 STUD D5725297725000 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297931400* WASHER D5725297931600* WASHER D5725297921000 WASHER D5725297921200 WASHER D5725297928400* WASHER D5725297928600* 19 BOLT NSA5479VHK10−20X BOLT NSA5479VHK10−20Y NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297932000 WASHER D5725297932200 WASHER D5725297929000 WASHER D5725297929200 20,21 STUD D5725297732000 STUD D5725297733000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 22 STUD D5725297732200 STUD D5725297733200 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 59Kit A02 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 23 BOLT NSA5479VHK9−21X BOLT NSA5479VHK9−21Y NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297931400 WASHER D5725297931600 WASHER D5725297928400 WASHER D5725297928600 24 STUD D5725297723400 STUD D5725297725000 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297931400* WASHER D5725297931600* WASHER D5725297921000 WASHER D5725297921200 WASHER D5725297928400* WASHER D5725297928600* 25 STUD D5725297723000 STUD D5725297724600 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297931400* WASHER D5725297931600* WASHER D5725297921000 WASHER D5725297921200 WASHER D5725297928400* WASHER D5725297928600* 26 BOLT NSA5479VHK9−17X BOLT NSA5479VHK9−17Y NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297931400 WASHER D5725297931600 WASHER D5725297928400 WASHER D5725297928600 27 BOLT NSA5479VHK9−16X BOLT NSA5479VHK9−16Y NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297931400 WASHER D5725297931600 WASHER D5725297928400 WASHER D5725297928600 28 BOLT NSA5479VHK9−18X BOLT NSA5479VHK9−18Y NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297931400 WASHER D5725297931600 WASHER D5725297928400 WASHER D5725297928600

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 60Kit A02 Hole No. 1st Option Fasteners 2nd Option Fasteners 29,30,31 BOLT NSA5479VHK9−26X BOLT NSA5479VHK9−26Y NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297931400 WASHER D5725297931600 WASHER D5725297928400 WASHER D5725297928600 36 BOLT NSA5479VHK8−15 BOLT NSA5479VHK8−15X NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297930600 WASHER D5725297930800 WASHER AN960C816 WASHER D5725297927800 37 BOLT NSA5479VHK8−18 BOLT NSA5479VHK8−18X NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297930600 WASHER D5725297930800 WASHER AN960C816 WASHER D5725297927800 38 BOLT NSA5479VHK8−14 BOLT NSA5479VHK8−14X NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297930600 WASHER D5725297930800 WASHER AN960C816 WASHER D5725297927800 39 BOLT NSA5479VHK7−12 − NUT NSA5472−7K7 WASHER D5725297930200 WASHER AN960C716 40 BOLT NSA5479VHK7−12 − NUT NSA5472−7K7 WASHER D5725297923600 WASHER AN960KD716 41 BOLT NSA5479VHK8−18 WASHER D5725297927800 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297930600 WASHER D5725297930800 WASHER AN960C816 BOLT NSA5479VHK8−18X 42 BOLT NSA5479VHK8−15 BOLT NSA5479VHK8−15X NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297930600 WASHER D5725297930800

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 61Kit A02 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER AN960C816 WASHER D5725297927800 43,44 BOLT NSA5479VHK7−13 − NUT NSA5472−7K7 WASHER D5725297930200 WASHER AN960C716 45 BOLT NSA5479VHK7−12 − NUT NSA5472−7K7 WASHER D5725297923600 WASHER AN960KD716 46,47 BOLT NSA5479VHK8−14 BOLT NSA5479VHK8−14X NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297930600 WASHER D5725297930800 WASHER AN960C816 WASHER D5725297927800 48,49,50 BOLT NSA5479VHK7−12 − NUT NSA5472−7K7 WASHER D5725297930200 WASHER AN960C716 51 BOLT NSA5479VHK7−12 − NUT NSA5472−7K7 WASHER D5725297923600 WASHER AN960KD716

3.B.(9)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE, quoting this Service Bulletin for the 2nd option fastener and washers. NOTE : Where 2nd option fasteners are not listed, refer to AIRBUS INDUSTRIE, Structure Repair Engineering Department for further advice. (9) Kit No. 571089A02 ACTUATING CYLINDER ANCHORAGE 1ST AND 2ND OPTION FASTENERS IN HOLE NUMBER SEQUENCE

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 62Kit A02 Hole No. 1st Option Fasteners 2nd Option Fasteners FASTENERS FOR THE ACTUATING CYLINDER ANCHORAGE : 52,53 STUD D5725297724200 STUD D5725297725800 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297921000 WASHER D5725297921200 54,55 STUD D5725297724400 STUD D5725297726000 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297921000 WASHER D5725297921200 56,57,58 BOLT NSA5479VHK9−15X BOLT NSA5479VHK9−15Y 59,60,61 NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297921000 WASHER D5725297921200 62,63,64 STUD D5725297723400 STUD D5725297725000 65 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297921000 WASHER D5725297921200 66,67,68 BOLT NSA5479VHK8−15 BOLT NSA5479VHK8−15X 69 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297924000 WASHER D5725297924200 WASHER AN960KD816 WASHER D5725297920400 70,71,72 BOLT NSA5479VHK8−13 BOLT NSA5479VHK8−13X 73 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297924000 WASHER D5725297924200

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

TABLE 9

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 63Kit A02 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER AN960KD816 WASHER D5725297920400 74,75,76 BOLT NSA5479VHK7−1 − 77,78,79 NUT NSA5472−7K7 80,81 WASHER D5725297923600 WASHER AN960KD716

Kit A02 Hole No. 1st Option Fasteners 2nd Option Fasteners FASTENERS FOR THE GEAR RIB 5: 82,83 STUD D5725297822800 STUD D5725297823000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297922200 WASHER D5725297922400 84 STUD D5725297820600 STUD D5725297821800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 85,86 STUD D5725297826000 STUD D5725297826400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 87,88 STUD D5725297820200 STUD D5725297821400 3.B.(10)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE, quoting this Service Bulletin for the 2nd option fastener and washers. NOTE : Where 2nd option fasteners are not listed, refer to AIRBUS INDUSTRIE, Structure Repair Engineering Department for further advice. (10) Kit No. 571089A02 GEAR RIB 1ST AND 2ND OPTION FASTENERS IN HOLE NUMBER SEQUENCE
TABLE 10

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 64Kit A02 Hole No. 1st Option Fasteners 2nd Option Fasteners NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 89 STUD D5725297821000 STUD D5725297822200 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 90,91 STUD D5725297826200 STUD D5725297826600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 92,93 STUD D5725297727400 STUD D5725297729600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 94 STUD D5725297728400 STUD D5725297730600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 95,96 STUD D5725297738200 STUD D5725297738600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 97,98 STUD D5725297727200 STUD D5725297729400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 99 STUD D5725297727800 STUD D5725297730000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 65Kit A02 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297921800 WASHER D5725297922000 100,101 STUD D5725297738000 STUD D5725297738400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000

Kit A03 Hole No. 1st Option Fasteners 2nd Option Fasteners FASTENERS FOR THE PINTLE FITTING : 5 BOLT NSA5479VHK9−26X BOLT NSA5479VHK9−26Y NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297931400 WASHER D5725297931600 WASHER D5725297928400 WASHER D5725297928600 6 STUD D5725297732800 STUD D5725297733800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 7,8 STUD D5725297732600 STUD D5725297733600 3.B.(11)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE, quoting this Service Bulletin for the 2nd option fastener and washers. NOTE : Where 2nd option fasteners are not listed, refer to AIRBUS INDUSTRIE, Structure Repair Engineering Department for further advice. (11) Kit No. 571089A03 PINTLE FITTING 1ST AND 2ND OPTION FASTENERS IN HOLE NUMBER SEQUENCE NOTE : In the table that follows the washers marked * are corrosion resistant and must be installed adjacent to the pintle fitting.
TABLE 11

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 66Kit A03 Hole No. 1st Option Fasteners 2nd Option Fasteners NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 9 STUD D5725297732800 STUD D5725297733800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 10,11 STUD D5725297732600 STUD D5725297733600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 12 STUD D5725297732800 STUD D5725297733800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 13,14 BOLT NSA5479VHK10−30X BOLT NSA5479VHK10−30Y NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297932000 WASHER D5725297932200 WASHER D5725297929000 WASHER D5725297929200 15 STUD D5725297732400 STUD D5725297733400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800*

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 67Kit A03 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 16 BOLT NSA5479VHK10−23 BOLT NSA5479VHK10−23Y NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297932000 WASHER D5725297932200 WASHER D5725297929000 WASHER D5725297929200 17 STUD D5725297723600 STUD D5725297725200 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297931400* WASHER D5725297931600* WASHER D5725297921000 WASHER D5725297921200 WASHER D5725297928400* WASHER D5725297928600* 18 STUD D5725297723400 STUD D5725297725000 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297931400* WASHER D5725297931600* WASHER D5725297921000 WASHER D5725297921200 WASHER D5725297928400* WASHER D5725297928600* 19 BOLT NSA5479VHK10−20Y BOLT NSA5479VHK10−20Y NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297932000 WASHER D5725297932200 WASHER D5725297929000 WASHER D5725297929200 20,21 STUD D5725297732000 STUD D5725297733000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200 WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 22 STUD D5725297732200 STUD D5725297733200 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297926000 WASHER D5725297926200

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 68Kit A03 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297932600* WASHER D5725297932800* WASHER D5725297922200 WASHER D5725297922400 WASHER D5725297929600* WASHER D5725297929800* 23 BOLT NSA5479VHK9−21X BOLT NSA5479VHK9−21Y NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297931400 WASHER D5725297931600 WASHER D5725297928400 WASHER D5725297928600 24 STUD D5725297723400 STUD D5725297725000 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297931400* WASHER D5725297931600* WASHER D5725297921000 WASHER D5725297921200 WASHER D5725297928400* WASHER D5725297928600* 25 STUD D5725297723000 STUD D5725297724600 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297931400* WASHER D5725297931600* WASHER D5725297921000 WASHER D5725297921200 WASHER D5725297928400* WASHER D5725297928600* 26 BOLT NSA5479VHK9−17X BOLT NSA5479VHK9−17Y NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297931400 WASHER D5725297931600 WASHER D5725297928400 WASHER D5725297928600 27 BOLT NSA5479VHK9−16X BOLT NSA5479VHK9−16Y NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297931400 WASHER D5725297931600 WASHER D5725297928400 WASHER D5725297928600 28 BOLT NSA5479VHK9−18X BOLT NSA5479VHK9−18Y NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297931400 WASHER D5725297931600 WASHER D5725297928400 WASHER D5725297928600

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 69Kit A03 Hole No. 1st Option Fasteners 2nd Option Fasteners 29,30,31 BOLT NSA5479VHK9−26X BOLT NSA5479VHK9−26Y NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297931400 WASHER D5725297931600 WASHER D5725297928400 WASHER D5725297928600 36 BOLT NSA5479VHK8−15 BOLT NSA5479VHK8−15X NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297930600 WASHER D5725297930800 WASHER AN960C816 WASHER D5725297927800 37 BOLT NSA5479VHK8−18 BOLT NSA5479VHK8−18X NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297930600 WASHER D5725297930800 WASHER AN960C816 WASHER D5725297927800 38 BOLT NSA5479VHK8−14 BOLT NSA5479VHK8−14X NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297930600 WASHER D5725297930800 WASHER AN960C816 WASHER D5725297927800 39 BOLT NSA5479VHK7−12 − NUT NSA5472−7K7 WASHER D5725297930200 WASHER AN960C716 40 BOLT NSA5479VHK7−12 − NUT NSA5472−7K7 WASHER D5725297923600 WASHER AN960KD716 41 BOLT NSA5479VHK8−18 BOLT NSA5479VHK8−18X NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297930600 WASHER D5725297930800 WASHER AN960C816 WASHER D5725297927800 42 BOLT NSA5479VHK8−15 BOLT NSA5479VHK8−15X NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297930600 WASHER D5725297930800

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 70Kit A03 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER AN960C816 WASHER D5725297927800 43,44 BOLT NSA5479VHK7−13 − NUT NSA5472−7K7 WASHER D5725297930200 WASHER AN960C716 45 BOLT NSA5479VHK7−12 − NUT NSA5472−7K7 WASHER D5725297923600 WASHER AN960KD716 46,47 BOLT NSA5479VHK8−14 BOLT NSA5479VHK8−14X NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297930600 WASHER D5725297930800 WASHER AN960C816 WASHER D5725297927800 48,49,50 BOLT NSA5479VHK7−12 − NUT NSA5472−7K7 WASHER D5725297930200 WASHER AN960C716 51 BOLT NSA5479VHK7−12 − NUT NSA5472−7K7 WASHER D5725297923600 WASHER AN960KD716

3.B.(12)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE, quoting this Service Bulletin for the 2nd option fastener and washers. NOTE : Where 2nd option fasteners are not listed, refer to AIRBUS INDUSTRIE, Structure Repair Engineering Department for further advice. (12) Kit 571089A03 ACTUATING CYLINDER ANCHORAGE 1ST AND 2ND OPTION FASTENERS IN HOLE NUMBER SEQUENCE

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 71Kit A03 Hole No. 1st Option Fasteners 2nd Option Fasteners FASTENERS FOR THE ACTUATING CYLINDER ANCHORAGE : 52,53 STUD D5725297722600 STUD D5725297722200 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297924400 WASHER D5725297924600 WASHER D5725297920600 WASHER D5725297920800 54,55 STUD D5725297722800 STUD D5725297722400 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297924400 WASHER D5725297924600 WASHER D5725297920600 WASHER D5725297920800 56,57,58 BOLT NSA5479VHK8−15Y BOLT D5725297720600 59,60,61 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297924600 WASHER D5725297924600 WASHER D5725297920600 WASHER D5725297920800 62,63,64 STUD D5725297723400 STUD D5725297725000 65 NUT NSA5057−9 NUT NSA5057−9 WASHER D5725297924800 WASHER D5725297925000 WASHER D5725297921000 WASHER D5725297921200 66,67,68 BOLT NSA5479VHK8−15 BOLT NSA5479VHK8−15X 69 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297924000 WASHER D5725297924200 WASHER AN960KD816 WASHER D5725297920400 70,71,72 BOLT NSA5479VHK8−13 BOLT NSA5479VHK8−13X 73 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297924000 WASHER D5725297924200

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

TABLE 12

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 72Kit A03 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER AN960KD816 WASHER D5725297920400 74,75,76 BOLT NSA5479VHK7−12 − 77,78,79 NUT NSA5472−7K7 80,81 WASHER D5725297923600 WASHER AN960KD716

Kit A03 Hole No. 1st Option Fasteners 2nd Option Fasteners FASTENERS FOR THE GEAR RIB 5: 82,83 STUD D5725297823200 STUD D5725297823400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 84 STUD D5725297820600 STUD D5725297821800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 85,86 STUD D5725297826000 STUD D5725297826400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 87,88 STUD D5725297820200 STUD D5725297821400 3.B.(13)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE, quoting this Service Bulletin for the 2nd option fastener and washers. NOTE : Where 2nd option fasteners are not listed, refer to AIRBUS INDUSTRIE, Structure Repair Engineering Department for further advice. (13) Kit No. 571089A03 GEAR RIB 1ST AND 2ND OPTION FASTENERS IN HOLE NUMBER SEQUENCE
TABLE 13

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 73Kit A03 Hole No. 1st Option Fasteners 2nd Option Fasteners NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 89 STUD D5725297821000 STUD D5725297822200 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 90,91 STUD D5725297826200 STUD D5725297826600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 92,93 STUD D5725297727400 STUD D5725297729600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 94 STUD D5725297728400 STUD D5725297730600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 95,96 STUD D5725297738200 STUD D5725297738600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 97,98 STUD D5725297727200 STUD D5725297729400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000 99 STUD D5725297727800 STUD D5725297730000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 74Kit A03 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297921800 WASHER D5725297922000 100,101 STUD D5725297738000 STUD D5725297738400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297925600 WASHER D5725297925800 WASHER D5725297921800 WASHER D5725297922000

Kit A05 Hole No. 1st Option Fasteners 2nd Option Fasteners FASTENERS FOR THE PINTLE FITTING : 5 BOLT NSA5479VHK8−26Y STUD D5725297722000 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297928000 WASHER D5725297928200* WASHER D5725297931000 WASHER D5725297931200* WASHER D5725297920800 WASHER D5725297924600 6 BOLT NSA5479VHK10−32Y STUD D5725297731000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 3.B.(14)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE, quoting this Service Bulletin for the 2nd option fastener and washers. NOTE : Where 2nd option fasteners are not listed, refer to AIRBUS INDUSTRIE, Structure Repair Engineering Department for further advice. (14) Kit No. 571089A05 PINTLE FITTING 1ST AND 2ND OPTION FASTENERS IN HOLE NUMBER SEQUENCE NOTE : In the table that follows the washers marked * are corrosion resistant and must be installed adjacent to the pintle fitting.
TABLE 14

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 75Kit A05 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297925800 7,8 BOLT NSA5479VHK10−31Y STUD D5725297730800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 9 BOLT NSA5479VHK10−32Y STUD D5725297731000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 10,11 BOLT NSA5479VHK10−31Y STUD D5725297730800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 12 BOLT NSA5479VHK10−32Y STUD D5725297731000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 13,14 BOLT NSA5479VHK9−30Y STUD D5725297726600 NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297928600 WASHER D5725297928800 WASHER D5725297931600 WASHER D5725297931800 WASHER D5725297921400 WASHER D5725297925200

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 76Kit A05 Hole No. 1st Option Fasteners 2nd Option Fasteners 15 BOLT NSA5479VHK10−30Y STUD D5725297734600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 16 BOLT NSA5479VHK9−23Y STUD D5725297726400 NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297928600 WASHER D5725297928800* WASHER D5725297931600 WASHER D5725297931800* WASHER D5725297921400 WASHER D5725297925200 17 STUD D5725297720400 STUD D5725297721800 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297928000* WASHER D5725297928200* WASHER D5725297931000* WASHER D5725297931200* WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 18 STUD D5725297720200 STUD D5725297721400 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297928000* WASHER D5725297928200* WASHER D5725297931000* WASHER D5725297931200* WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 19 BOLT NSA5479VHK9−20Y STUD D5725297726200 NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297928600 WASHER D5725297928800* WASHER D5725297931600 WASHER D5725297931800* WASHER D5725297921400 WASHER D5725297925200 20,21 BOLT NSA5479VHK10−24Y STUD D5725297734400

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 77Kit A05 Hole No. 1st Option Fasteners 2nd Option Fasteners NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 22 BOLT NSA5479VHK10−26Y STUD D5725297730200 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 23 BOLT NSA5479VHK8−21Y STUD D5725297721600 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297928000 WASHER D5725297928200* WASHER D5725297931000 WASHER D5725297931200* WASHER D5725297920800 WASHER D5725297924600 24 STUD D5725297720200 STUD D5725297721400 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297928000* WASHER D5725297928200* WASHER D5725297931000* WASHER D5725297931200* WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 25 STUD D5725297720000 STUD D5725297721000 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297928000* WASHER D5725297928200* WASHER D5725297931000* WASHER D5725297931200* WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 26 BOLT NSA5479VHK8−17Y STUD D5725297734200 NUT NSA5472−8K7 NUT NSA5472−8K7

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 78Kit A05 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297928000 WASHER D5725297928200* WASHER D5725297931000 WASHER D5725297931200* WASHER D5725297920800 WASHER D5725297924600 27 BOLT NSA5479VHK8−16Y STUD D5725297720800 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297928000 WASHER D5725297928200* WASHER D5725297931000 WASHER D5725297931200* WASHER D5725297920800 WASHER D5725297924600 28 BOLT NSA5479VHK8−18Y STUD D5725297721200 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297928000 WASHER D5725297928200* WASHER D5725297931000 WASHER D5725297931200* WASHER D5725297920800 WASHER D5725297924600 29,30,31 BOLT NSA5479VHK8−26Y STUD D5725297722000 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297928000 WASHER D5725297928200* WASHER D5725297931000 WASHER D5725297931200* WASHER D5725297920800 WASHER D5725297924600 36 BOLT NSA5479VHK7−15Y − NUT NSA5472−7K7 WASHER D5725297927600 WASHER D5725297930400 37 BOLT NSA5479VHK7−18Y − NUT NSA5472−7K7 WASHER D5725297927600 WASHER D5725297930400 38 BOLT NSA5479VHK7−14Y −

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 79Kit A05 Hole No. 1st Option Fasteners 2nd Option Fasteners NUT NSA5472−7K7 WASHER D5725297927600 WASHER D5725297930400 39 BOLT NSA5479VHK6−12Y − NUT NSA5472−6K7 WASHER D5725297927400 WASHER D5725297930000 40 BOLT NSA5479VHK6−12Y − NUT NSA5472−6K7 WASHER D5725297923400 WASHER D5725297920000 41 BOLT NSA5479VHK7−18Y − NUT NSA5472−7K7 WASHER D5725297927600 WASHER D5725297930400 42 BOLT NSA5479VHK7−15Y − NUT NSA5472−7K7 WASHER D5725297927600 WASHER D5725297930400 43,44 BOLT NSA5479VHK6−13Y − NUT NSA5472−6K7 WASHER D5725297927400 WASHER D5725297930000 45 BOLT NSA5479VHK6−12Y − NUT NSA5472−6K7 WASHER D5725297923400 WASHER D5725297920000 46,47 BOLT NSA5479VHK7−14Y − NUT NSA5472−7K7 WASHER D5725297927600 WASHER D5725297930400

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 80Kit A05 Hole No. 1st Option Fasteners 2nd Option Fasteners 48,49,50 BOLT NSA5479VHK6−12Y − NUT NSA5472−6K7 WASHERS D5725297927400 WASHER D5725297930000 51 BOLT NSA5479VHK6−12Y − NUT NSA5472−6K7 WASHER D5725297923400 WASHER D5725297920000

Kit A05 Hole No. 1st Option Fasteners 2nd Option Fasteners FASTENERS FOR THE ACTUATING CYLINDER ANCHORAGE : 52,53 STUD D5725297722600 STUD D5725297722200 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 54,55 STUD D5725297722800 STUD D5725297722400 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 56,57,58 BOLT NSA5479VHK8−15Y STUD D5725297720600 3.B.(15)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE, quoting this Service Bulletin for the 2nd option fastener and washers. NOTE : Where 2nd option fasteners are not listed, refer to AIRBUS INDUSTRIE, Structure Repair Engineering Department for further advice. (15) Kit No. 571089A05 ACTUATING CYLINDER ANCHORAGE 1ST AND 2ND OPTION FASTENERS IN HOLE NUMBER SEQUENCE
TABLE 15

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 81Kit A05 Hole No. 1st Option Fasteners 2nd Option Fasteners 59,60,61 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 62,63,64 STUD D5725297720200 STUD D5725297721400 65 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 66,67,68 BOLT NSA5479VHK7−15Y − 69 NUT NSA5472−7K7 WASHER D5725297923800 WASHER D5725297920200 70,71,72 BOLT NSA5479VHK7−13Y − 73 NUT NSA5472−7K7 WASHER D5725297923800 WASHER D5725297920200 74,75,76 BOLT NSA5479VHK6−12Y − 77,78,79 NUT NSA5472−6K7 80,81 WASHER D5725297923400 WASHER D5725297920000

3.B.(16)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE, quoting this Service Bulletin for the 2nd option fastener and washers. NOTE : Where 2nd option fasteners are not listed, refer to AIRBUS INDUSTRIE, Structure Repair Engineering Department for further advice. (16) Kit No. 571089A05 GEAR RIB 1ST AND 2ND OPTION FASTENERS IN HOLE NUMBER SEQUENCE

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 82Kit A05 Hole No. 1st Option Fasteners 2nd Option Fasteners FASTENERS FOR THE GEAR RIB 5: 82,83 STUD D5725297823200 STUD D5725297823400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 84 STUD D5725297820600 STUD D5725297821800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 85,86 STUD D5725297826000 STUD D5725297826400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 87,88 STUD D5725297820200 STUD D5725297821400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 89 STUD D5725297821000 STUD D5725297822200 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 90,91 STUD D5725297826200 STUD D5725297826600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 92,93 STUD D5725297727400 STUD D5725297729600 NUT NSA5472−10K7 NUT NSA5472−10K7

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

TABLE 16

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 83Kit A05 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 94 STUD D5725297728400 STUD D5725297730600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 95,96 STUD D5725297738200 STUD D5725297738600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 97,98 STUD D5725297727200 STUD D5725297729400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 99 STUD D5725297727800 STUD D5725297730000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 100,101 STUD D5725297738000 STUD D5725297738400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800

3.B.(17)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE, quoting this Service Bulletin for the 2nd option fastener and washers. NOTE : Where 2nd option fasteners are not listed, refer to AIRBUS INDUSTRIE, Structure Repair Engineering Department for further advice. (17) Kit No. 571089A07 PINTLE FITTING 1ST AND 2ND OPTION FASTENERS IN HOLE NUMBER SEQUENCE NOTE : In the table that follows the washers marked * are corrosion resistant and must be installed adjacent to the pintle fitting.

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 84Kit A07 Hole No. 1st Option Fasteners 2nd Option Fasteners FASTENERS FOR THE PINTLE FITTING : 5 BOLT NSA5479VHK8−26Y STUD D5725297722000 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297928000 WASHER D5725297928200* WASHER D5725297931000 WASHER D5725297931200* WASHER D5725297920800 WASHER D5725297924600 6 BOLT NSA5479VHK10−32Y STUD D5725297731000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 7,8 BOLT NSA5479VHK10−31Y STUD D5725297730800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 9 BOLT NSA5479VHK10−32Y STUD D5725297731000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 10,11 BOLT NSA5479VHK10−31Y STUD D5725297730800 NUT NSA5472−10K7 NUT NSA5472−10K7K

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

TABLE 17

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 85Kit A07 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 12 BOLT NSA5479VHK10−32Y STUD D5725297731000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 13,14 BOLT NSA5479VHK9−30Y STUD D5725297726600 NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297928600 WASHER D5725297928800* WASHER D5725297931600 WASHER D5725297931800* WASHER D5725297921400 WASHER D5725297925200 15 BOLT NSA5479VHK10−30Y STUD D5725297734600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 16 BOLT NSA5479VHK9−23Y STUD D5725297726400 NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297928600 WASHER D5725297928800* WASHER D5725297931600 WASHER D5725297931800* WASHER D5725297921400 WASHER D5725297925200 17 STUD D5725297720400 STUD D5725297721800 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297928000* WASHER D5725297928200*

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 86Kit A07 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297931000* WASHER D5725297931200* WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 18 STUD D5725297720200 STUD D5725297721400 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297928000* WASHER D5725297928200* WASHER D5725297931000* WASHER D5725297931200* WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 19 BOLT NSA5479VHK9−20Y STUD D5725297726200 NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297928600 WASHER D5725297928800* WASHER D5725297931600 WASHER D5725297931800* WASHER D5725297921400 WASHER D5725297925200 20,21 BOLT NSA5479VHK10−24Y STUD D5725297734400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 22 BOLT NSA5479VHK10−26Y STUD D5725297730200 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 23 BOLT NSA5479VHK8−21Y STUD D5725297721600 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297928000 WASHER D5725297928200* WASHER D5725297931000 WASHER D5725297931200*

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 87Kit A07 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297920800 WASHER D5725297924600 24 STUD D5725297720200 STUD D5725297721400 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297928000* WASHER D5725297928200* WASHER D5725297931000* WASHER D5725297931200* WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 25 STUD D5725297720000 STUD D5725297721000 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297928000* WASHER D5725297928200* WASHER D5725297931000* WASHER D5725297931200* WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 26 BOLT NSA5479VHK8−17Y STUD D5725297734200 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297928000 WASHER D5725297928200* WASHER D5725297931000 WASHER D5725297931200* WASHER D5725297920800 WASHER D5725297924600 27 BOLT NSA5479VHK8−16Y STUD D5725297720800 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297928000 WASHER D5725297928200* WASHER D5725297931000 WASHER D5725297931200* WASHER D5725297920800 WASHER D5725297924600 28 BOLT NSA5479VHK8−18Y STUD D5725297721200 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297928000 WASHER D5725297928200* WASHER D5725297931000 WASHER D5725297931200* WASHER D5725297920800

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 88Kit A07 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297924600 29,30,31 BOLT NSA5479VHK8−26Y STUD D5725297722000 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297928000 WASHER D5725297928200* WASHER D5725297931000 WASHER D5725297931200* WASHER D5725297920800 WASHER D5725297924600 36 BOLT NSA5479VHK7−15Y − NUT NSA5472−7K7 WASHER D5725297927600 WASHER D5725297930400 37 BOLT NSA5479VHK7−18Y − NUT NSA5472−7K7 WASHER D5725297927600 WASHER D5725297930400 38 BOLT NSA5479VHK7−14Y − NUT NSA5472−7K7 WASHER D5725297927600 WASHER D5725297930400 39 BOLT NSA5479VHK6−12Y − NUT NSA5472−6K7 WASHER D5725297927400 WASHER D5725297930000 40 BOLT NSA5479VHK6−12Y − NUT NSA5472−6K7 WASHER D5725297923400 WASHER D5725297920000 41 BOLT NSA5479VHK7−18Y − NUT NSA5472−7K7 WASHER D5725297927600 WASHER D5725297930400

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 89Kit A07 Hole No. 1st Option Fasteners 2nd Option Fasteners 42 BOLT NSA5479VHK7−15Y − NUT NSA5472−7K7 WASHER D5725297927600 WASHER D5725297930400 43,44 BOLT NSA5479VHK6−13Y − NUT NSA5472−6K7 WASHER D5725297927400 WASHER D5725297930000 45 BOLT NSA5479VHK6−12Y − NUT NSA5472−6K7 WASHER D5725297923400 WASHER D5725297920000 46,47 BOLT NSA5479VHK7−14Y − NUT NSA5472−7K7 WASHER D5725297927600 WASHER D5725297930400 48,49,50 BOLT NSA5479VHK6−12Y − NUT NSA5472−6K7 WASHER D5725297927400 WASHER D5725297930000 51 BOLT NSA5479VHK6−12Y − NUT NSA5472−6K7 WASHER D5725297923400 WASHER D5725297920000

3.B.(18)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE, quoting this Service Bulletin for the 2nd option fastener and washers. NOTE : Where 2nd option fasteners are not listed, refer to AIRBUS INDUSTRIE, Structure Repair Engineering Department for further advice. (18) Kit No. 571089A07 ACTUATING CYLINDER ANCHORAGE 1ST AND 2ND OPTION FASTENERS IN HOLE NUMBER SEQUENCE

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 90Kit A07 Hole No. 1st Option Fasteners 2nd Option Fasteners FASTENERS FOR THE ACTUATING CYLINDER ANCHORAGE : 52,53 STUD D5725297722600 STUD D5725297722200 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 54,55 STUD D5725297722800 STUD D5725297722400 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 56,57,58 BOLT NSA5479VHK8−15Y STUD D5725297720600 59,60,61 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 62,63,64 STUD D5725297720200 STUD D5725297721400 65 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 66,67,68 BOLT NSA5479VHK7−15Y − 69 NUT NSA5472−7K7 WASHER D5725297923800 WASHER D5725297920200 70,71,72 BOLT NSA5479VHK7−13Y − 73 NUT NSA5472−7K7 WASHER D5725297923800

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

TABLE 18

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 91Kit A07 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297920200 74,75,76 BOLT NSA5479VHK6−12Y − 77,78,79 NUT NSA5472−6K7 80,81 WASHER D5725297923400 WASHER D5725297920000

Kit A07 Hole No. 1st Option Fasteners 2nd Option Fasteners FASTENERS FOR THE GEAR RIB 5: 82,83 STUD D5725297823200 STUD D5725297823400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 84, STUD D5725297820400 STUD D5725297821600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 85,86 STUD D5725297826000 STUD D5725297826400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 87,88 STUD D5725297820000 STUD D5725297821200 3.B.(19)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE, quoting this Service Bulletin for the 2nd option fastener and washers. NOTE : Where 2nd option fasteners are not listed, refer to AIRBUS INDUSTRIE, Structure Repair Engineering Department for further advice. (19) Kit No. 571089A07 GEAR RIB 1ST AND 2ND OPTION FASTENERS IN HOLE NUMBER SEQUENCE
TABLE 19

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 92Kit A07 Hole No. 1st Option Fasteners 2nd Option Fasteners NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 89 STUD D5725297820800 STUD D5725297822000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 90,91 STUD D5725297826200 STUD D5725297826600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 92,93 STUD D5725297727800 STUD D5725297730000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 94 STUD D5725297729000 STUD D5725297731200 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 95,96 STUD D5725297729200 STUD D5725297731400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 97,98 STUD D5725297727200 STUD D5725297729400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 99 STUD D5725297727600 STUD D5725297729800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 93Kit A07 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297925600 WASHER D5725297925800 100,101 STUD D5725297738000 STUD D5725297738400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800

Kit A08 Hole No. 1st Option Fasteners 2nd Option Fasteners FASTENERS FOR THE PINTLE FITTING : 5 BOLT NSA5479VHK8−26Y STUD D5725297722000 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297928000 WASHER D5725297928200* WASHER D5725297931000 WASHER D5725297931200* WASHER D5725297920800 WASHER D5725297924600 6 BOLT NSA5479VHK10−32Y STUD D5725297731000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 3.B.(20)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE, quoting this Service Bulletin for the 2nd option fastener and washers. NOTE : Where 2nd option fasteners are not listed, refer to AIRBUS INDUSTRIE, Structure Repair Engineering Department for further advice. (20) Kit No. 571089A08 PINTLE FITTING 1ST AND 2ND OPTION FASTENERS IN HOLE NUMBER SEQUENCE NOTE : In the table that follows the washers marked * are corrosion resistant and must be installed adjacent to the pintle fitting.
TABLE 20

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 94Kit A08 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297925800 7,8 BOLT NSA5479VHK10−31Y STUD D5725297730800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 9 BOLT NSA5479VHK10−32Y STUD D5725297731000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 10,11 BOLT NSA5479VHK10−31Y STUD D5725297730800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 12 BOLT NSA5479VHK10−32Y STUD D5725297731000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 13,14 BOLT NSA5479VHK9−30Y STUD D5725297726600 NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297928600 WASHER D5725297928800* WASHER D5725297931600 WASHER D5725297931800* WASHER D5725297921400 WASHER D5725297925200

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 95Kit A08 Hole No. 1st Option Fasteners 2nd Option Fasteners 15 BOLT NSA5479VHK10−30Y STUD D5725297734600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 16 BOLT NSA5479VHK9−23Y STUD D5725297726400 NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297928600 WASHER D5725297928800* WASHER D5725297931600 WASHER D5725297931800* WASHER D5725297921400 WASHER D5725297925200 17 STUD D5725297720400 STUD D5725297721800 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297928000* WASHER D5725297928200* WASHER D5725297931000* WASHER D5725297931200* WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 18 STUD D5725297720200 STUD D5725297721400 NUT NSA5057−8 NUT NSA5057−8 WASHERS D5725297928000* WASHER D5725297928200* WASHER D5725297931000* WASHER D5725297931200* WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 19 BOLT NSA5479VHK9−20Y STUD D5725297726200 NUT NSA5472−9K7 NUT NSA5472−9K7 WASHER D5725297928600 WASHER D5725297928800* WASHER D5725297931600 WASHER D5725297931800 WASHER D5725297921400 WASHER D5725297925200 20,21 BOLT NSA5479VHK10−24Y STUD D5725297734400

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 96Kit A08 Hole No. 1st Option Fasteners 2nd Option Fasteners NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 22 BOLT NSA5479VHK10−26Y STUD D5725297730200 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297929200 WASHER D5725297929400* WASHER D5725297932200 WASHER D5725297932400* WASHER D5725297922000 WASHER D5725297925800 23 BOLT NSA5479VHK8−21Y STUD D5725297721600 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297928000 WASHER D5725297928200* WASHER D5725297931000 WASHER D5725297931200* WASHER D5725297920800 WASHER D5725297924600 24 STUD D5725297720200 STUD D5725297721400 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297928000* WASHER D5725297928200* WASHER D5725297931000* WASHER D5725297931200* WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 25 STUD D5725297720000 STUD D5725297721000 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297928000* WASHER D5725297928200* WASHER D5725297931000* WASHER D5725297931200* WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 26 BOLT NSA5479VHK8−17Y STUD D5725297734200 NUT NSA5472−8K7 NUT NSA5472−8K7

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 97Kit A08 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297928000 WASHER D5725297928200* WASHER D5725297931000 WASHER D5725297931200* WASHER D5725297920800 WASHER D5725297924600 27 BOLT NSA5479VHK8−16Y STUD D5725297720800 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297928000 WASHER D5725297928200* WASHER D5725297931000 WASHER D5725297931200* WASHER D5725297920800 WASHER D5725297924600 28 BOLT NSA5479VHK8−18Y STUD D5725297721200 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297928000 WASHER D5725297928200* WASHER D5725297931000 WASHER D5725297931200* WASHER D5725297920800 WASHER D5725297924600 29,30,31 BOLT NSA5479VHK8−26Y STUD D5725297722000 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297928000 WASHER D5725297928200* WASHER D5725297931000 WASHER D5725297931200* WASHER D5725297920800 WASHER D5725297924600 36 BOLT NSA5479VHK7−15Y − NUT NSA5472−7K7 WASHER D5725297927600 WASHER D5725297930400 37 BOLT NSA5479VHK7−18Y − NUT NSA5472−7K7 WASHER D5725297927600 WASHER D5725297930400 38 BOLT NSA5479VHK7−14Y −

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 98Kit A08 Hole No. 1st Option Fasteners 2nd Option Fasteners NUT NSA5472−7K7 WASHER D5725297927600 WASHER D5725297930400 39 BOLT NSA5479VHK6−12Y − NUT NSA5472−6K7 WASHER D5725297927400 WASHER D5725297930000 40 BOLT NSA5479VHK6−12Y − NUT NSA5472−6K7 WASHER D5725297923400 WASHER D5725297920000 41 BOLT NSA5479VHK7−18Y − NUT NSA5472−7K7 WASHER D5725297927600 WASHER D5725297930400 42 BOLT NSA5479VHK7−15Y − NUT NSA5472−7K7 WASHER D5725297927600 WASHER D5725297930400 43,44 BOLT NSA5479VHK6−13Y − NUT NSA5472−6K7 WASHER D5725297927400 WASHER D5725297930000 45 BOLT NSA5479VHK6−12Y − NUT NSA5472−6K7 WASHER D5725297923400 WASHER D5725297920000 46,47 BOLT NSA5479VHK7−14Y − NUT NSA5472−7K7 WASHER D5725297927600 WASHER D5725297930400

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 99Kit A08 Hole No. 1st Option Fasteners 2nd Option Fasteners 48,49,50 BOLT NSA5479VHK6−12Y − NUT NSA5472−6K7 WASHER D5725297927400 WASHER D5725297930000 51 BOLT NSA5479VHK6−12Y − NUT NSA5472−6K7 WASHER D5725297923400 WASHER D5725297920000

Kit A08 Hole No. 1st Option Fasteners 2nd Option Fasteners FASTENERS FOR THE ACTUATING CYLINDER ANCHORAGE : 52,53 STUD D5725297722600 STUD D5725297722200 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 54,55 STUD D5725297722800 STUD D5725297722400 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 56,57 BOLT NSA5479VHK8−18Y STUD D5725297721200 3.B.(21)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE, quoting this Service Bulletin for the 2nd option fastener and washers. NOTE : Where 2nd option fasteners are not listed, refer to AIRBUS INDUSTRIE, Structure Repair Engineering Department for further advice. (21) Kit No. 571089A08 ACTUATING CYLINDER ANCHORAGE 1ST AND 2ND OPTION FASTENERS IN HOLE NUMBER SEQUENCE
TABLE 21

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 100Kit A08 Hole No. 1st Option Fasteners 2nd Option Fasteners NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 58,59,60 BOLT NSA5479VHK8−15Y STUD D5725297720600 61 NUT NSA5472−8K7 NUT NSA5472−8K7 WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 62,63,64 STUD D5725297720200 STUD D5725297721400 65 NUT NSA5057−8 NUT NSA5057−8 WASHER D5725297920600 WASHER D5725297920800 WASHER D5725297924400 WASHER D5725297924600 66,67,68 BOLT NSA5479VHK7−15Y − 69 NUT NSA5472−7K7 WASHER D5725297923800 WASHER D5725297920200 70,71,72 BOLT NSA5479VHK7−13Y − 73 NUT NSA5472−7K7 WASHER D5725297923800 WASHER D5725297920200 74,75,76 BOLT NSA5479VHK6−12Y − 77,78,79 NUT NSA5472−6K7 80,81 WASHER D5725297923400 WASHER D5725297920000

3.B.(22)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE, quoting this Service Bulletin for the 2nd option fastener and washers. NOTE : Where 2nd option fasteners are not listed, refer to AIRBUS INDUSTRIE, Structure Repair Engineering Department for further advice. (22) Kit No. 571089A08 GEAR RIB 1ST AND 2ND OPTION FASTENERS IN HOLE NUMBER SEQUENCE

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 101Kit A08 Hole No. 1st Option Fasteners 2nd Option Fasteners FASTENERS FOR THE GEAR RIB 5: 82,83 STUD D5725297823200 STUD D5725297823400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 84, STUD D5725297820400 STUD D5725297821600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 85,86 STUD D5725297826000 STUD D5725297826400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 87,88 STUD D5725297820000 STUD D5725297821200 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 89 STUD D5725297820800 STUD D5725297822000 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 90,91 STUD D5725297826200 STUD D5725297826600 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 92,93 STUD D5725297727800 STUD D5725297730000 NUT NSA5472−10K7 NUT NSA5472−10K7

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

TABLE 22

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 102Kit A08 Hole No. 1st Option Fasteners 2nd Option Fasteners WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 94 STUD D5725297729000 STUD D5725297731200 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 95,96 STUD D5725297729200 STUD D5725297731400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 97,98 STUD D5725297727200 STUD D5725297729400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 99 STUD D5725297727600 STUD D5725297729800 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800 100,101 STUD D5725297738000 STUD D5725297738400 NUT NSA5472−10K7 NUT NSA5472−10K7 WASHER D5725297921800 WASHER D5725297922000 WASHER D5725297925600 WASHER D5725297925800

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

NOTE : If the 1st option final hole diameter is not within the limits, send a purchase order to MSC, AIRBUS INDUSTRIE, quoting this Service Bulletin for the 2nd option fastener and washers. NOTE : Where 2nd option fasteners are not listed, refer to AIRBUS INDUSTRIE, Structure Repair Engineering Department for further advice. C. TEST None

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 103MATERIAL PIPE DIAMETER (in) DISTANCE FROM CLAMP TO CLAMP/UNION OR UNION TO UNION (in) RADIAL DISPLACEMENT (in) Titanium 0.25 to 0.50 5 to 10 0.15 Titanium 0.25 to 0.50 Above 10 0.30 Titanium 0.625 to 1.500 5 to 10 0.05 Titanium 0.625 to 1.500 Above 10 0.15 Stainless Steel 0.25 to 0.50 5 to 10 0.10

Stainless Steel 0.25 to 0.50 Above 10 0.15

Stainless Steel 0.625 to 1.500 5 to 10 0.05

Stainless Steel 0.625 to 1.500 Above 10 0.05 3.D.(1)

3.D.(2)

3.D.(3)

3.D.(4)

3.D.(4)(a)

3.D.(5)

3.D.(5)(a)

3.D.(5)(b)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

D. CLOSE UP (1) Make sure that the work areas are clean and clear of tools and other items of equipment. (2) Install any pipeline assemblies and clamps loosened or removed in paragraph 3.A.(1)(n) 16 . NOTE : If the pipelines, Items (76), (78), (79) and (80) had to be cut to gain access, refer to para. 3.A.(2)(i) . NOTE : If the hydraulic pipelines do not align at the clamp block assemblies or at the unions, they can be corrected by radial displacement as follows :

(3) Install the bracket and connect the conduit assemblies referred to in paragraph 3.A.(1)(n) 17 . (4) Install the Strut Assemblies Refer to Figure 5 (a) Install the strut assemblies and the slide bushes Item (153). Install the bolts Item (154), the washers Item (152), the nuts Item (157) and the cotter pins MS24665−304 Item 150. (5) Install the Brackets, Clamps, Hydraulic Components and Hydraulic Pipes Refer to Figure 3 and Figure 4 (a) Use the rivets ASNA0080−508A to install the brackets Item (35). (b) Apply sealant (Mat. No. 09−002) to the mating surfaces of : − the location block Item (56) (LH)

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 1043.D.(5)(c)

3.D.(5)(d)

3.D.(5)(e)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

− the location block Item (55) (RH) − the bracket assembly Item (66) (LH) − the bracket assembly Item (67) (RH) PRE−MOD 21023 (applicable to A320−100 series A/C only) − the support brackets Item (51) POST−MOD 21023 (applicable to all A320−200 series A/C) − the angles Item (59). (c) Use : − the bolts Items (63) − the bolts Items (64) − the nuts Items (65) to install : − the bracket assembly Item (66) (LH) − the bracket assembly Item (67) (RH). (d) Use : − the bolts Items (53) − the washers Items (54) − the nuts Items (52) to install: PRE−MOD 21023 (applicable to A320−100 series A/C only) − the location block Item (56) (LH) − the location block Item (55) (RH) − the support brackets Item (51) − complete with the hydraulic pipelines Items (46) and (47) and the flexible hydraulic pipelines. Connect the hydraulic pipelines Items (46) and (47) (Refer to AMM 20−21−12 Page block 201 ). POST−MOD 21023 (applicable to all A320−200 series A/C) − the location block Item (56) (LH) − the location block Item (55) (RH) − complete with the hydraulic pipelines Items (46) and (47) and the flexible hydraulic pipelines. Connect the hydraulic pipelines Items (46) and (47) (Refer to AMM 20−21−12 Page block 201). (e) Use : POST−MOD 21023(applicable to all A320−200 series A/C) − the bolts Items (57) − the nuts Item (58)

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 1053.D.(5)(f)

3.D.(5)(g)

3.D.(5)(h)

3.D.(5)(i)

3.D.(5)(j)

3.D.(5)(k)

3.D.(5)(l)

3.D.(5)(m)

3.D.(5)(n)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

to install : − the angles Item (59). (f) Install : − the hydraulic pipelines Item 77 − the compensated slide 1010GM (Refer to AMM 29−11−47 Page block 401) − the compensated slide 3010GM (Refer to AMM 29−13−47 Page block 401) − the fire shutoff valve 1046GK (Refer to AMM 29−11−52 Page block 401) − the fire shutoff valve 3046GD (Refer to AMM 29−13−52 Page block 401). (g) Install the guide assembly Item (82) and the channel assembly Item (83). (h) Connect the hydraulic pipelines Items (74) thru (81). (i) Install the hydraulic pipelines Items (48) and (73) (Refer to AMM 20−21−12 Page block 201). (j) Use : PRE−MOD 21023 (applicable to A320−100 series A/C only) − the cable tie NSA935401−05 to install : − the tube spacer pads Item (49) and install the clamp block assembly Item (50). (k) Use : POST−MOD 21023 (applicable to all A320−200 series A/C) − the bolts Item (61) − the nuts Item (58) to install : − the loop clamps Item (60) − the angles Item (62). (l) Install the clamp block assemblies for the hydraulic pipelines, Items (18), (20), (21), (22), (23), (24), (25), (27), (28), (29), (30), (31) and (34). Install the tube spacer, Item (44) and clamp block plate, Item (43). (m) Use the cable ties NSA935401−05 and NSA935041−08 to install the tube spacer pads Items (17), (19), (32) and (33). (n) Make sure that there is a minimum gap of 5 mm between hydraulic pipelines. Make sure that there is a minimum gap of 5 mm between each hydraulic pipeline and the adjacent structure and any electrical cables.

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 1063.D.(6)

3.D.(7)

3.D.(8)

3.D.(9)

3.D.(10)

3.D.(11)

3.D.(12)

3.D.(13)

3.D.(14)

3.D.(15)

3.D.(16)

3.D.(17)

3.D.(18)

3.D.(19)

3.D.(20)

3.D.(21)

3.D.(22)

3.D.(23)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN
NOTE : There is a possibility that a foul will exist between hydraulic pipes and the studs at hole positions 17, 18, 24 and 25 on the Pintle Fitting. If this condition is apparent, refer to Repair Instruction R57258266. (6) Install the fuel and refuel gallery pipes Items (1) thru (7), LH and RH (Refer to Figure 2 and AMM 28−00−00 Page block 401). (7) Make sure that the work area is clean and clear of tools and other items of equipment. (8) If necessary, install the Rib 5 Build Door with the 30 nuts and bolts. Torque tighten the nuts from between 10.7 and 12.4 Nm (7.9 and 9.1 lbf ft). (9) If the engines are installed, release the loads equally on the jacks at the engine cradles LH and RH (Refer to Appendix 1 ). Release the loads equally at Frame 42 LH and RH (Refer to Appendix 1 ). Move the support jacks clear of the aircraft. (10) Install the MLG actuating cylinder, LH and RH (Refer to AMM 32−31−46 Page block 401). (11) Install the MLG (LH and RH) (Refer to AMM 32−11−11 Page block 401). (12) Install the access panels 540AB and 640AB (Refer to AMM 57−27−11 Page block 401). (13) Pressurize the Green, Blue and Yellow hydraulic systems (Refer to AMM 29−10−00 Page block 201). (14) Make sure that there are no leaks from the installed hydraulic pipelines. Do a check on the hydraulic pipelines when you do paragraphs 3.D.(15) thru 3.D.(21) . (15) Bleed the MLG actuating cylinder (Refer to AMM 32−31−46 Page block 401). (16) Bleed the normal wheel brake system (Refer to AMM 32−42−00 Page block 301). (17) Fill and bleed the alternate brake system (Refer to AMM 32−43−00 Page block 301). (18) Do ten full travel operations of the ailerons to bleed the aileron servo−controls (Refer to AMM 27−14−51 Page block 401). (19) Do five full travel operations of the spoilers 1 to 5 to bleed the spoiler servo−controls (Refer to AMM 27−64−52 Page block 401). (20) Remove the access platforms. (21) Do the tests of the MLG (LH and RH)(Refer to AMM 32−11−11 Page block 401). (22) Lower the aircraft to the ground (Refer to AMM 07−11−00 Page block 201). (23) If the engines are installed, remove the LH and RH engine cradles (Refer to Appendix 1 ), close the engine fan cowls (Refer to AMM 71−13−00 Page block 201) and the thrust reverser cowls (Refer to

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 1073.D.(24)

3.D.(25)

3.D.(26)

3.D.(27)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN
AMM 78−36−00 Page block 201). (24) Refuel the aircraft (Refer to AMM 12−11−28 Page block 301). Check for leaks particularly on the rear spar in the area of the forward pintle fitting, the actuating cylinder anchorage and the gear support rib (Refer to AMM 28−11−00 Page block 501). (25) Install the panels 574AB and 674AB. (26) Install the belly fairing panels 147CB, 148DB and 191/192 LB (Refer to AMM 53−25−11 Page block 401). (27) Retract the flaps (Refer to AMM 27−50−00 Page block 201). E. DOCUMENTATION Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 108REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Figure 2 Sheet 1

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 109 Removal/Installation Fuel pipesREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Figure 3 Sheet 1

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 110 Removal/Installation Hydraulic PipesREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Figure 4 Sheet 1

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 111 Removal/Installation Hydraulic PipesREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Figure 4 Sheet 2

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 112 Removal/Installation Hydraulic PipesREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Figure 4 Sheet 3

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 113 Removal/Installation Hydraulic PipesREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Figure 4 Sheet 4

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 114 Removal/Installation Hydraulic PipesREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Figure 5 Sheet 1

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 115 Removal/Installation of the Strut AssemblyREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Figure 6 Sheet 1

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 116 Hole Positions Inner Rear Spar 100 SeriesREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Figure 6 Sheet 2

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 117 Hole Positions Inner Rear Spar 100 SeriesREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Figure 6 Sheet 3

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 118 Hole Positions Inner Rear Spar 100 SeriesREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Figure 7 Sheet 1

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 119 Hole Positions Inner Rear Spar 200 SeriesREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Figure 7 Sheet 2

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 120 Hole Positions Inner Rear Spar 200 SeriesREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Figure 7 Sheet 3

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 121 Hole Positions Inner Rear Spar 200 SeriesREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

Figure 8 Sheet 1

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 122 Adjustment of Washers at Spotfaces1.

1.A.

1.B.

1.C.

1.D.

2.

3.

3.A.

3.B.

3.B.(1)

3.B.(2)

3.B.(3)

3.B.(4)

3.B.(5)

REVISION No. : 03 − Feb 09/01 L7 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 01 1. AIRCRAFT SHORING PROCEDURE FOR SERVICE BULLETIN A320−57−1089. The aircraft configuration must be as follows : A. A/C on front and main jacks (for A/C with engines installed refer to Para. 4.A.). B. Main landing gear removed. C. Vertical and horizontal stabilizers installed. D. Fuel tanks empty. NOTE : After the A/C is shored, a limitation of the staff working on the A/C and a limitation of the removal/installation of equipment is required : − The number of personnel on the A/C at the same time is limited to make sure that the STEP 4 + or − 10% load margin conditions given in the text that follows are not exceeded. − Removal/Installation of equipments on the A/C is limited to ensure that the STEP 4 + or − 10% load margin conditions given in the text that follows are not exceeded. 2. If there is any deviation from the above configuration complete the Aircraft Configuration Form (Refer to Figure 1 Sheet 1 and 2) and send it to :
AIRBUS INDUSTRIE (AI/SE−A32) CUSTOMER SUPPORT DIRECTORATE 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE Fax No. : (33) 561 93 36 14 3. For Aircraft with Engines Removed (Refer to Figure 2) A. Measure the front and main jacks reactions. The front jack reaction must be higher than 500 daN and less than 3000 daN. B. If the main jack reaction is higher than 12000 daN : (1) Install a ballast of 2000 daN (2039 kgf) inside the forward fuselage at FR25 in the cargo compartment. (2) Install the FITTINGS P/N 98D07203002100, Item 1 at FR42/RIB1 LH and RH. (3) Put the JACKS P/N TMHAS09, Item 2 in position at FR42/RIB1 LH and RH. (4) Install the ADAPTORS P/N 98A07003907200, Item 3 and LOAD CELLS P/N 343.100kN, Item 4 between the JACKS and FITTINGS at FR42/RIB1 LH and RH. (5) Apply the following loads to each side to the jacks at FR42/RIB1 in steps : CAUTION : AT STEP 4, MAKE SURE THAT THE LOAD APPLIED IS NOT MORE THAN THE MAXIMUM PERMISSIBLE LOAD AT THE FR42/RIB1 JACK (REFER TO PARA.5.).

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 1 of 83.C.

3.C.(1)

3.C.(2)

3.D.

4.

4.A.

4.A.(1)

4.A.(2)

4.A.(3)

4.B.

4.B.(1)

4.B.(2)

4.B.(2)(a)

4.B.(2)(b)

4.B.(2)(c)

4.B.(2)(d)

4.B.(2)(e)

4.B.(2)(f)

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 01 − STEP 1 2900 daN − STEP 2 5800 daN − STEP 3 8700 daN − STEP 4 Continue applying load to the FR42/RIB1 jacks until the main jack reactions reach 5450 daN + or − 10%. C. If the main jack reaction is lower than 12000 daN : (1) Repeat paras B. (1) thru (4). (2) Apply the following loads to each side to the jacks at FR42/RIB1 in steps : − STEP 1 2100 daN − STEP 2 4200 daN − STEP 3 6300 daN − STEP 4 8400 daN + or − 10%. D. Install the safety stay at FR73/74 to prevent any rotation of the A/C (Refer to AMM 07−11−00 ). 4. For Aircraft with Engines Installed (Refer to Figure 2 and Figure 3) A. Before the Aircraft is lifted on jacks and MLG removed (1) Open the engine fan cowls (Refer to AMM 71−13−00 Page block 201). (2) Open the thrust reverser cowls (Refer to AMM 78−36−00 Page block 201). (3) Install the CRADLES (complete with stabilization rods) P/N 98D07203004000, Item 5 (CFM Engines) or P/N 98D07203005000, Item 6 (IAE Engines)(Refer to Figure 3). B. After the Aircraft is lifted on jacks and the MLG removed (1) Measure the front and main jacks reactions. The front jack reaction must be higher than 2400 daN. (2) If the main jack reaction is higher than 14300 daN : (a) Install a ballast of 2000 daN (2039 kgf) inside the forward fuselage at FR25 in the cargo compartment. (b) Install the FITTINGS P/N 98D07203002100, Item 1 at FR42/RIB1 LH and RH. (c) Put the JACKS P/N TMHAS09, Item 2 in position at FR42/RIB1 LH and RH. (d) Install the ADAPTORS P/N 98A07003907200, Item 3 and LOAD CELLS P/N 343.100kN, Item 4 between the JACKS and FITTINGS at FR42/RIB1 LH and RH. (e) Put standard wheel jacks, Item 7 in position under the CRADLES. (f) Install the LOAD CELLS P/N 343.63kN, Item 8 between the wheel

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 24.B.(2)(g)

4.B.(3)

4.B.(3)(a)

4.B.(3)(b)

4.B.(4)

5.

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 01 jacks and CRADLES. (g) Apply the following loads simultaneously at each side to the jacks at FR42/RIB1 and to each engine CRADLE. FR42/RIB1 in steps : CAUTION : AT STEP 4, MAKE SURE THAT THE LOAD APPLIED IS NOT MORE THAN THE MAXIMUM PERMISSIBLE LOAD AT THE FR42/RIB1 JACK (REFER TO PARA.5.). − STEP 1 2900 daN − STEP 2 5800 daN − STEP 3 8700 daN − STEP 4 Continue applying load to the FR42/RIB1 jacks until the main jack reactions reach 5450 daN + or − 10%. Engine CRADLE in steps : CAUTION : AT STEP 4, MAKE SURE THAT THE LOAD APPLIED IS NOT MORE THAN THE MAXIMUM PERMISSIBLE LOAD AT THE ENGINE CRADLE JACK (REFER TO PARA.5.). − STEP 1 800 daN − STEP 2 1600 daN − STEP 3 2400 daN − STEP 4 3200 daN + or − 10%. (3) If the main jack reaction is lower than 14300 daN : (a) Repeat paras (2) (a) thru (f). (b) Apply the following loads simultaneously at each side to the jacks at FR42/RIB1 and to each engine CRADLE. FR42/RIB1 in steps : − STEP 1 2100 daN − STEP 2 4200 daN − STEP 3 6300 daN − STEP 4 8400 daN + or − 10%. Engine CRADLE in steps : − STEP 1 800 daN − STEP 2 1600 daN − STEP 3 2400 daN − STEP 4 3200 daN + or − 10%. (4) Install the safety stay at FR73/74 to prevent any rotation of the A/C (Refer to AMM 07−11−00 ). 5. Maximum Permissible Loads (during accomplishment of this Service Bulletin) − Main Jacks : 6000 daN − FR42/RIB1 Jack : 11500 daN

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 36.

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 01
− Front Jack : 6800 daN − Safety Stay FR73/74 : 2000 daN − Engine Cradles (when installed) : 3450 daN. 6. Aircraft Configuration Form (Refer to Figure 1 Sheets 1 and 2).

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 4REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 01

Figure 1 Sheet 1

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 5 Aircraft Configuration FormREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 01

Figure 1 Sheet 2

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 6 Aircraft Configuration FormREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 01

Figure 2 Sheet 1

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 7 Shoring at FR42/RIB1 LH and RHREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 01

Figure 3 Sheet 1

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 8 Shoring at Engine Cradles LH and RHMECH INSP MECH

HOLE No. Remove fastener, measure & clean hole Eddy Current Inspect Hole Start Ream & check hole dia. Cold Expand & check hole dia. Final Ream & check hole dia. 6 8 10 12 14 16 18 20 22 24 26 29 31 37 39 42 44 46 48 50 51

REVISION No. : 03 − Feb 09/01 L7 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 02 SB A320−57−1089 MODIFICATION PROGRESS SHEETS These progress sheets are produced as a guide for planning purposes only. It is the choice of the Customer to use them or not to use them. It is intended that they be copied (and enlarged if required) and used to chart the progress of the modification.

PINTLE FITTING COLD EXPANSION

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 1 of 10MECH INSP MECH INSP MECH

HOLE No. Clearance Ream Fitting to Counter−bore Depth Radius hole (as applicable ) OK to install fastener Install fastener & torque OK to seal Seal fastener (SRM 51−76−00) 6 8 10 12 14 16 18 20 22 24 26 29 31 37 39 42 44 46 48 50 51

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 02

PINTLE FITTING COUNTERBORING & FASTENER INSTALLATION

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 2MECH INSP MECH

HOLE No. Remove fastener, measure & clean hole Eddy Current Inspect Hole Start Ream & check hole dia. Cold Expand & check hole dia. Final Ream & check hole dia. 5 7 9 11 13 15 17 19 21 23 25 27 28 30 36 38 40 41 43 45 47 49

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 02

PINTLE FITTING COLD EXPANSION

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 3MECH INSP MECH INSP MECH

HOLE No. Clearance Ream Fitting to Counter−bore Depth Radius hole (as applicable ) OK to install fastener Install fastener & torque OK to seal Seal fastener (SRM 51−76−00) 5 7 9 11 13 15 17 19 21 23 25 27 28 30 36 38 40 41 43 45 47 49

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 02

PINTLE FITTING COUNTERBORING & FASTENER INSTALLATION

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 4MECH INSP MECH MECH/INSP MECH

HOLE No. Remove fastener, measure & clean hole Eddy Current Inspect Hole Start Ream & check hole dia. Remove Actuating Cylinder Anchorage & Inspect Clean Rib 3 Brackets, Fitting & Spar 52 53 54 55 65 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 02

ACTUATING CYLINDER ANCHORAGE AND REAR SPAR

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 5MECH INSP MECH MECH/INSP MECH

HOLE No. Remove fastener, measure & clean hole Eddy Current Inspect Hole Start Ream & check hole dia. Remove Actuating Cylinder Anchorage & Inspect Clean Rib 3 Brackets, Fitting & Spar 77 78 79 80 81

MECH

HOLE No. Cold Expand

Spar Holes &

Check dia. Intermediate Ream Holes in Fitting, Rib

3 Brkts To Spar Post Cold Exp. Dia. Temporarily Install Fitting & Rib 3 Brkts Ream Holes in

Spar & Fitting to Final Hole Dia. for Spar. Check Dia. Remove Fitting & Rib 3 Brkts. Radius Holes in Spar (as applicable) 52 53 54 55 56 57 58 59 60 61 62 63 64 65

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 02

ACTUATING CYLINDER ANCHORAGE AND REAR SPAR

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 6MECH

HOLE No. Cold Expand

Spar Holes &

Check dia. Intermediate Ream Holes in Fitting, Rib

3 Brkts To Spar Post Cold Exp. Dia. Temporarily Install Fitting & Rib 3 Brkts Ream Holes in

Spar & Fitting to Final Hole Dia. for Spar. Check Dia. Remove Fitting & Rib 3 Brkts. Radius Holes in Spar (as applicable) 66 67 68 69 70 71 72 73 74 75 76 77 78 79 80 81

MECH INSP MECH INSP MECH

HOLE No. Clearance Ream Fitting & Rib 3 Brkts Apply Sealant to Mating Surfaces OK to Install Fitting & Rib 3 Brkts Install Fasteners & Torque OK to seal Seal Fasteners (SRM 51−76−00) 52 53 54

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 02

ACTUATING CYLINDER ANCHORAGE AND REAR SPAR

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 7MECH INSP MECH INSP MECH

HOLE No. Clearance Ream Fitting & Rib 3 Brkts Apply Sealant to Mating Surfaces OK to Install Fitting & Rib 3 Brkts Install Fasteners & Torque OK to seal Seal Fasteners (SRM 51−76−00) 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 79 80 81

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 02

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 8MECH INSP MECH HOLE No. Remove fastener, measure & clean hole Eddy Current Inspect Hole Start Ream & check hole dia. Cold Expand & check hole dia. Final Ream & check hole dia.
83 85 87 89 91 93 95 97 99 101

INSP MECH INSP MECH

HOLE No. OK to Install Fastener Install Fastener & torque OK to Seal Seal fastener (SRM 51−76−00) 83 85 87 89 91 93 95 97 99 101

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 02

GEAR RIB (First Pass)

GEAR RIB (First Pass) (Continued)

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 9MECH INSP MECH HOLE No. Remove fastener, measure & clean hole Eddy Current Inspect Hole Start Ream & check hole dia. Cold Expand & check hole dia. Final Ream & check hole dia.
82 84 86 88 90 92 94 96 98 100

INSP MECH INSP MECH

HOLE No. OK to Install Fastener Install Fastener & torque OK to Seal Seal fastener (SRM 51−76−00) 82 84 86 88 90 92 94 96 98 100

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 02

GEAR RIB (Second Pass)

GEAR RIB (Second Pass) (Continued)

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 10PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A01

Hole Nos. 5 6,7,10 Puller Unit MBHO−20 MBHO−20 Preliminary Core Drills KD−181N−.5380−R KD−221N−.6600−R Preliminary Start Reamers Start Reamers SR−181N−RC SR−221N−RC Mid Start Reamers Combination Gage CBG−18−1−N−1 CBG−22−1−N−1 Mandrel Check Fixture CBMG−18−1−N CBMG−22−1−N Mandrel CBM−18−1−N−2OA−65−V2 CBM−22−1−N−2OA−65−V2 Flared Split Sleeves CBS−18−1−N−36F CBS−22−1−N−36F Nosecap Assembly CBCE−99D−18−1−NF−RA CBCE−99E−22−1−NF−RA Intermediate Reamer Final Reamer 1st Option FR1−181N−.5731−RC FR1−221N−.6980−RC Clearance Reamer 1st Option CR1−181N−.5781−RC CR1−221N−.7031−RC Final Hole Gage 1st Option CBFG−18−1−N−1−.5731/.5 751 CBFG−22−1−N−1−.6980/.7000
Final Reamer 2nd Option FR2−181N−.5887−RC FR2−221N−.7137−RC Clearance Reamer 2nd Option CR2−181N−.5937−RC CR2−221N−.7188−RC Final Hole Gage 2nd Option CBFG−18−1−N−1−.5887/.5 907 CBFG−22−1−N−1−.7137/.7157

PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A01

Hole Nos. 8,9,11,12,15,20 21,22 13,16,19 Puller Unit MB−30 MBHO−20 Preliminary Core Drills KD−221N−.6600−R KD−201N−.5980−R Preliminary Start Reamers Start Reamers SR−221N−RC SR−201N−RC Mid Start Reamers

REVISION No. : 03 − Feb 09/01 L7 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03 COLD EXPANSION PLANNING INFORMATION

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 1 of 33PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A01

Hole Nos. 8,9,11,12,15,20 21,22 13,16,19 Combination Gage CBG−22−1−N−1 CBG−20−1−N−1 Mandrel Check Fixture CBMG−22−1−N CBMG−20−1−N Mandrel CBM−22−1−N−2−55−V2 CBM−20−1−N−2OA−50−V2 Flared Split Sleeves CBS−22−1−N−36F CBS−20−1−N−36F Nosecap Assembly MEN−26C−2201F CBCE−96D−20−1−NF−RA Intermediate Reamer Final Reamer 1st Option FR1−221N−.6980−RC FR1−201N−.6356−RC Clearance Reamer 1st Option CR1−221N−.7031−RC CR1−201N−.6406−RC Final Hole Gage 1st Option CBFG−22−1−N−1−.6980/.7 000 CBFG−20−1−N−1−.6356/.637 6 Final Reamer 2nd Option FR2−221N−.7137−RC FR2−201N−.6512−RC Clearance Reamer 2nd Option CR2−221N−.7188−RC CR2−201N−.6562−RC Final Hole Gage 2nd Option CBFG−22−1−N−1−.7137/.7 157 CBFG−20−1−N−1−.6512/.653 2

PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A01

Hole Nos. 14 17,18,24,25 Puller Unit MB−30 MHPE−20−18−1−N−5205 Preliminary Core Drills KD−201N−.5980−R KD−181N−.5380−S Preliminary Start Reamers Start Reamers SR−201N−RC SR−181N−SC Mid Start Reamers Combination Gage CBG−20−1−N−1 CBG−18−1−N−1 Mandrel Check Fixture CBMG−20−1−N CBMG−18−1−N Mandrel CBM−20−1−N−2−55−V2 INCLUDED WITH PULLER UNIT Flared Split Sleeves CBS−20−1−N−36F CBS−18−1−N−23F Nosecap Assembly MEN−26B−2001F INCLUDED WITH PULLER UNIT

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 2PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A01

Hole Nos. 14 17,18,24,25 Intermediate Reamer Final Reamer 1st Option FR1−201N−.6356−RC FR1−181N−.5731−SC Clearance Reamer 1st Option CR1−201N−.6406−RC CR1−181N−.5781−SC Final Hole Gage 1st Option CBFG−20−1−N−1−.6356/.6 376 CBFG−18−1−N−1−.5731/.575 1 Final Reamer 2nd Option FR2−201N−.6512−RC FR2−181N−.5887−SC Clearance Reamer 2nd Option CR2−201N−.6562−RC CR2−181N−.5937−SC Final Hole Gage 2nd Option CBFG−20−1−N−1−.6512/.6 532 CBFG−18−1−N−1−.5887/.590 7

PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A01

Hole Nos. 23,26,27 28,29,30,31 Puller Unit MBH0−20 MB−30 Preliminary Core Drills KD−181N−.5380−R KD−181N−.5380−R Preliminary Start Reamers Start Reamers SR−181N−RC SR−181N−RC Mid Start Reamers Combination Gage CBG−18−1−N−1 CBG−18−1−N−1 Mandrel Check Fixture CBMG−18−1−N CBMG−18−1−N Mandrel CBM−18−1−N−2OA−50−V2 CBM−18−1−N−2−55−V2 Flared Split Sleeves CBS−18−1−N−36F CBS−18−1−N−36F Nosecap Assembly CBCE−96D−18−1−NF−RA MEN−26B−1801F Intermediate Reamer Final Reamer 1st Option FR1−181N−.5731−RC FR1−181N−.5731−RC Clearance Reamer 1st Option CR1−181N−.5781−RC CR1−181N−.5781−RC

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 3PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A01

Hole Nos. 23,26,27 28,29,30,31 Final Hole Gage 1st Option CBFG−18−1−N−1−.5731/.5 751 CBFG−18−1−N−1−.5731/.575 1 Final Reamer 2nd Option FR2−181N−.5887−RC FR2−181N−.5887−RC Clearance Reamer 2nd Option CR2−181N−.5937−RC CR2−181N−.5937−RC Final Hole Gage 2nd Option CBFG−18−1−N−1−.5887/.5 907 CBFG−18−1−N−1−.5887/.590 7

PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A01

Hole Nos. 36,37,38,41,42,46,47 39,40,43,44,45,48,49 50,51 Puller Unit MB−30 MB−30 Preliminary Core Drills Preliminary Start Reamers PSR−160N−.4590−RC PSR−123N−.3906−RC Start Reamers SR−160N−RC SR−123N−RC Mid Start Reamers Combination Gage CBG−16−0−N−1 CBG−12−3−N−1 Mandrel Check Fixture CBMG−16−0−N CBMG−12−3−N Mandrel CBM−16−0−N−2−55−V2 CBM−12−3−N−2−55−V2 Flared Split Sleeves CBS−16−0−N−23F CBS−12−3−N−23F Nosecap Assembly MEN−26B−1601F MEN−26B−1223F Intermediate Reamer Final Reamer 1st Option FR1−160N−.4945−RC FR1−123N−.4320−RC Clearance Reamer 1st Option CR1−160N−.5000−RC CR1−123N−.4375−RC Final Hole Gage 1st Option CBFG−16−0−N−1−.4945/.4 965 CBFG−12−3−N−1−.4320/.434 0 Final Reamer 2nd Option FR2−160N−.5101−RC Clearance Reamer 2nd Option CR2−160N−.5156−RC Final Hole Gage 2nd Option CBFG−16−0−N−1−.5101/.5 121

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 4PLANNING INFORMATION FOR ACTUATING CYLINDER ANCHORAGE EFFECTIVE TO KIT No. A01
Hole No. 52,53,54,55,56,57,58,5 9 60,61,62,63 64,6566,67,68,69,70,71 72,73 Puller Unit MB−30 MB−30 Preliminary Core Drills KD181N−.5380−L Preliminary Start Reamers PSR−160N−.4590−LC Start Reamers SR−181N−LC SR−160N−LC Mid Start Reamers Combination Gage CBG−18−1−N−1 CBG−16−0−N−1 Mandrel Check Fixture CBMG−18−1−N CBMG−16−0−N Mandrel CBM−18−1−N−2−55−V2 CBM−16−0−N−2−55−V2 Flared Split Sleeves CBS−18−1−N−36F CBS−16−0−N−23F Nosecap Assembly MEN−26B−1801F MEN−26B−1601F Intermediate Reamer IR−181N−.5630−RC IR−160N−.4840−RC Final Reamer 1st Option FR1−181N−.5731−LC FR1−160N−.4945−LC Clearance Reamer 1st Option CR1−181N−.5781−RC CR1−160N−.5000−RC Final Hole Gage 1st Option CBFG−18−1−N−1−.5731/.5 751 CBFG−16−0−N−1−.4945/.496 5 Final Reamer 2nd Option FR2−181N−.5887−LC FR2−160N−.5101−LC Clearance Reamer 2nd Option CR2−181N−.5937−RC CR2−160N−.5156−RC Final Hole Gage 2nd Option CBFG−18−1−N−1−.5887/.5 907 CBFG−16−0−N−1−.5101/.512 1

PLANNING INFORMATION FOR ACTUATING CYLINDER ANCHORAGE EFFECTIVE TO KIT No. A01 Hole Nos. 74,75,76,77,78,79 80,81 Puller Unit MB−30 Preliminary Core Drills Preliminary Start Reamers PSR−123N−.3906−LC Start Reamers SR−123N−LC Mid Start Reamers Combination Gage CBG−12−3−N−1

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 5PLANNING INFORMATION FOR ACTUATING CYLINDER ANCHORAGE EFFECTIVE TO KIT No. A01 Hole Nos. 74,75,76,77,78,79 80,81 Mandrel Check Fixture CBMG−12−3−N Mandrel CBM−12−3−N−2−55−V2 Flared Split Sleeves CBS−12−3−N−23F Nosecap Assembly MEN−26B−1223F Intermediate Reamer IR−123N−.4140−RC Final Reamer 1st Option FR1−123N−.4320−LC Clearance Reamer 1st Option CR1−123N−.4375−RC Final Hole Gage 1st Option CBFG−12−3−N−1−.4320/.43 40 Final Reamer 2nd Option Clearance Reamer 2nd Option Final Hole Gage 2nd Option

PLANNING INFORMATION FOR ACTUATING CYLINDER ANCHORAGE EFFECTIVE TO KIT No. A01 Hole Nos. 82,83 84,85,86 Puller Unit MBHO−20 MBHO−20 Preliminary Core Drills KD−221N−.6600−S* Preliminary Start Reamers Start Reamers SR−221N−SC or SR−221N−P67−SC* Mid Start Reamers SRM−202N−.6320−SC Combination Gage CBG−22−1−N−1 CBG−20−2−N−1 Mandrel Check Fixture CBMG−22−1−N CBMG−20−2−N Mandrel CBM−22−1−N−2OA−25−V2 CBM−20−2−N−2OA−40−V2 Flared Split Sleeves CBS−22−1−N−32F CBS−20−2−N−36F Nosecap Assembly CBCE−91S−2201F−RA CBCE−94S−2023F−RA Intermediate Reamer Final Reamer 1st Option FR1−221N−.6990−SC FR1−202N−.6522−SC Clearance Reamer 1st Option

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 6PLANNING INFORMATION FOR ACTUATING CYLINDER ANCHORAGE EFFECTIVE TO KIT No. A01 Hole Nos. 82,83 84,85,86 Final Hole Gage 1st Option CBFG−22−1−N−1−.6980/.7 000 CBFG−20−2−N−1−.6512/.653 2 Final Reamer 2nd Option FR2−221N−.7147−SC FR2−202N−.6680−SC Clearance Reamer 2nd Option Final Hole Gage 2nd Option CBFG−22−1−N−1−.7137/.7 157 CBFG−20−2−N−1−.6670/.669 0 * As the A320−57−1004 Service Bulletin may have been accomplished on the aircraft,and if the EHD is .6719/.6738, it will not be necessary to use KD−221N−.6600−S, rather select and use start reamer SR−221N−P67−SC

PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT No. A01 Hole Nos. 87 Puller Unit MHP−20−2−N−32/36 Preliminary Core Drills Preliminary Start Reamers Start Reamers Mid Start Reamers SRM−202N−.6320−SC Combination Gage CBG−20−2−N−1 Mandrel Check Fixture CBMG−20−2−N Mandrel USE SHORT MANDREL MARKED 20−2−N−32 ONLY ON THIS HOLE(INCLUDED WITH PULLER UNIT) Flared Split Sleeves CBS−20−2−N−32F Nosecap Assembly INCLUDED WITH PULLER UNIT

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 7PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT No. A01 Hole Nos. 87 Intermediate Reamer Final Reamer 1st Option FR1−202N−.6522−SC Clearance Reamer 1st Option Final Hole Gage 1st Option CBFG−20−2−N−1−.6512/.6532 Final Reamer 2nd Option FR2−202N−.6680−SC Clearance Reamer 2nd Option Final Hole Gage 2nd Option CBFG−20−2−N−1−.6670/.6690

PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT No. A01 Hole Nos. 88,89,90,91 92,93,94,95,96,97,98 99,100,101 Puller Unit MHP−20−2−N−32/36 MB−30 Preliminary Core Drills Preliminary Start Reamers Start Reamers SR−202N−RC Mid Start Reamers SRM−202N−.6320−SC Combination Gage CBG−20−2−N−1 CBG−20−2−N−1 Mandrel Check Fixture CBMG−20−2−N CBMG−20−2−N Mandrel INCLUDED WITH PULLER UNIT CBM−20−2−N−2−55−V2
Flared Split Sleeves CBS−20−2−N−36F CBS−20−2−N−36F Nosecap Assembly USE LONG MANDREL MARKED 20−2−N−36 ONLY (INCLUDED WITH PULLER UNIT) MEN−26C−2023F

Intermediate Reamer Final Reamer 1st Option FR1−202N−.6522−SC FR1−202N−.6522−RC Clearance Reamer 1st Option

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 8PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT No. A01 Hole Nos. 88,89,90,91 92,93,94,95,96,97,98 99,100,101 Final Hole Gage 1st Option CBFG−20−2−N−1−.6512/.6 532 CBFG−20−2−N−1−.6512/.653 2 Final Reamer 2nd Option FR2−202N−.6680−SC FR2−202N−.6680−RC Clearance Reamer 2nd Option Final Hole Gage 2nd Option CBFG−20−2−N−1−.6670/.6 690 CBFG−20−2−N−.6670/.6690

PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A02

Hole Nos. 5 6,7,10 Puller Unit MBHO−20 MBHO−20 Preliminary Core Drills KD−181N−.5380−R KD−221N−.6600−R Preliminary Start Reamers Start Reamers SR−181N−RC SR−221N−RC Mid Start Reamers Combination Gage CBG−18−1−N−1 CBG−22−1−N−1 Mandrel Check Fixture CBMG−18−1−N CBMG−22−1−N Mandrel CBM−18−1−N−2OA−65−V2 CBM−22−1−N−2OA−65−V2 Flared Split Sleeves CBS−18−1−N−36F CBS−22−1−N−36F Nosecap Assembly CBCE−99D−18−1−NF−RA CBCE−99E−22−1−NF−RA Intermediate Reamer Final Reamer 1st Option FR1−181N−.5731−RC FR1−221N−.6980−RC Clearance Reamer 1st Option CR1−181N−.5781−RC CR1−221N−.7031−RC Final Hole Gage 1st Option CBFG−18−1−N−1−.5731/.5 751 CBFG−22−1−N−1−.6980/.7000
Final Reamer 2nd Option FR2−181N−.5887−RC FR2−221N−.7137−RC Clearance Reamer 2nd Option CR2−181N−.5937−RC CR2−221N−.7188−RC Final Hole Gage 2nd Option CBFG−18−1−N−1−.5887/.5 907 CBFG−22−1−N−1−.7137/.7157

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 9PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A02

Hole Nos. 8,9,11,12,15,20 21,22 13,16,19 Puller Unit MB−30 MBHO−20 Preliminary Core Drills KD−221N−.6600−R KD−201N−.5980−R Preliminary Start Reamers Start Reamers SR−221N−RC SR−201N−RC Mid Start Reamers Combination Gage CBG−22−1−N−1 CBG−20−1−N−1 Mandrel Check Fixture CBMG−22−1−N CBMG−20−1−N Mandrel CBM−22−1−N−2−55−V2 CBM−20−1−N−2OA−50−V2 Flared Split Sleeves CBS−22−1−N−36F CBS−20−1−N−36F Nosecap Assembly MEN−26C−2201F CBCE−96D−20−1−NF−RA Intermediate Reamer Final Reamer 1st Option FR1−221N−.6980−RC FR1−201N−.6356−RC Clearance Reamer 1st Option CR1−221N−.7031−RC CR1−201N−.6406−RC Final Hole Gage 1st Option CBFG−22−1−N−1−.6980/.7 000 CBFG−20−1−N−1−.6356/.637 6 Final Reamer 2nd Option FR2−221N−.7137−RC FR2−201N−.6512−RC Clearance Reamer 2nd Option CR2−221N−.7188−RC CR2−201N−.6562−RC Final Hole Gage 2nd Option CBFG−22−1−N−1−.7137/.7 157 CBFG−20−1−N−1−.6512/.653 2

PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A02

Hole Nos. 14 17,18,24,25 Puller Unit MB−30 MHPE−20−18−1−N−5205 Preliminary Core Drills KD−201N−.5980−R KD−181N−.5380−S Preliminary Start Reamers Start Reamers SR−201N−RC SR−181N−SC Mid Start Reamers Combination Gage CBG−20−1−N−1 CBG−18−1−N−1

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 10PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A02

Hole Nos. 14 17,18,24,25 Mandrel Check Fixture CBMG−20−1−N CBMG−18−1−N Mandrel CBM−20−1−N−2−55−V2 INCLUDED WITH PULLER UNIT Flared Split Sleeves CBS−20−1−N−36F CBS−18−1−N−23F Nosecap Assembly MEN−26B−2001F INCLUDED WITH PULLER UNIT Intermediate Reamer Final Reamer 1st Option FR1−201N−.6356−RC FR1−181N−.5731−SC Clearance Reamer 1st Option CR1−201N−.6406−RC CR1−181N−.5781−SC Final Hole Gage 1st Option CBFG−20−1−N−1−.6356/.6 376 CBFG−18−1−N−1−.5731/.575 1 Final Reamer 2nd Option FR2−201N−.6512−RC FR2−181N−.5887−SC Clearance Reamer 2nd Option CR2−201N−.6562−RC CR2−181N−.5937−SC Final Hole Gage 2nd Option CBFG−20−1−N−1−.6512/.6 532 CBFG−18−1−N−1−.5887/.590 7

PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A02

Hole Nos. 23,26,27 28,29,30,31 Puller Unit MBHO−20 MB−30 Preliminary Core Drills KD−181N−.5380−R KD−181N−.5380−R Preliminary Start Reamers Start Reamers SR−181N−RC SR−181N−RC Mid Start Reamers Combination Gage CBG−18−1−N−1 CBG−18−1−N−1 Mandrel Check Fixture CBMG−18−1−N CBMG−18−1−N Mandrel CBM−18−1−N−2OA−50−V2 CBM−18−1−N−2−55−V2 Flared Split Sleeves CBS−18−1−N−36F CBS−18−1−N−36F Nosecap Assembly CBCE−96D−18−1−NF−RA MEN−26B−1801F Intermediate Reamer

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 11PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A02

Hole Nos. 23,26,27 28,29,30,31 Final Reamer 1st Option FR1−181N−.5731−RC FR1−181N−.5731−RC Clearance Reamer 1st Option CR1−181N−.5781−RC CR1−181N−.5781−RC Final Hole Gage 1st Option CBFG−18−1−N−1−.5731/.5 751 CBFG−18−1−N−1−.5731/.575 1 Final Reamer 2nd Option FR2−181N−.5887−RC FR2−181N−.5887−RC Clearance Reamer 2nd Option CR2−181N−.5937−RC CR2−181N−.5937−RC Final Hole Gage 2nd Option CBFG−18−1−N−1−.5887/.5 907 CBFG−18−1−N−1−.5887/.590 7

PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A02

Hole Nos. 36,37,38,41,42,46,47 39,40,43,44,45,48,49 50,51 Puller Unit MB−30 MB−30 Preliminary Core Drills Preliminary Start Reamers PSR−160N−.4590−RC PSR−123N−.3906−RC Start Reamers SR−160N−RC SR−123N−RC Mid Start Reamers Combination Gage CBG−16−0−N−1 CBG−12−3−N−1 Mandrel Check Fixture CBMG−16−0−N CBMG−12−3−N Mandrel CBM−16−0−N−2−55−V2 CBM−12−3−N−2−55−V2 Flared Split Sleeves CBS−16−0−N−23F CBS−12−3−N−23F Nosecap Assembly MEN−26B−1601F MEN−26B−1223F Intermediate Reamer Final Reamer 1st Option FR1−160N−.4945−RC FR1−123N−.4320−RC Clearance Reamer 1st Option CR1−160N−.5000−RC CR1−123N−.4375−RC

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 12PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A02

Hole Nos. 36,37,38,41,42,46,47 39,40,43,44,45,48,49 50,51 Final Hole Gage 1st Option CBFG−16−0−N−1−.4945/.4 965 CBFG−12−3−N−1−.4320/.434 0 Final Reamer 2nd Option FR2−160N−.5101−RC Clearance Reamer 2nd Option CR2−160N−.5156−RC Final Hole Gage 2nd Option CBFG−16−0−N−1−.5101/.5 121

PLANNING INFORMATION FOR ACTUATING CYLINDER ANCHORAGE EFFECTIVE TO KIT No. A02
Hole Nos. 52,53,54,55,56,57,58,5 9 60,61,62,63,64,65 66,67,68,69,70,71,72,73 Puller Unit MB−30 MB−30 Preliminary Core Drills KD181N−.5380−L Preliminary Start Reamers PSR−160N−.4590−LC Start Reamers SR−181N−LC SR−160N−LC Mid Start Reamers Combination Gage CBG−18−1−N−1 CBG−16−0−N−1 Mandrel Check Fixture CBMG−18−1−N CBMG−16−0−N Mandrel CBM−18−1−N−2−55−V2 CBM−16−0−N−2−55−V2 Flared Split Sleeves CBS−18−1−N−36F CBS−16−0−N−23F Nosecap Assembly MEN−26B−1801F MEN−26B−1601F Intermediate Reamer IR−181N−.5630−RC IR−160N−.4840−RC Final Reamer 1st Option FR1−181N−.5731−LC FR1−160N−.4945−LC Clearance Reamer 1st Option CR1−181N−.5781−RC CR1−160N−.5000−RC Final Hole Gage 1st Option CBFG−18−1−N−1−.5731/.5 751 CBFG−16−0−N−1−.4945/.496 5 Final Reamer 2nd Option FR2−181N−.5887−LC FR2−160N−.5101−LC Clearance Reamer 2nd Option CR2−181N−.5937−RC CR2−160N−.5156−RC Final Hole Gage 2nd Option CBFG−18−1−N−1−.5887/.5 907 CBFG−16−0−N−1−.5101/.512 1

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 13PLANNING INFORMATION FOR ACTUATING CYLINDER ANCHORAGE EFFECTIVE TO KIT No. A02 Hole Nos. 74,75,76,77,78,79 80,81 Puller Unit MB−30 Preliminary Core Drills Preliminary Start Reamers PSR−123N−.3906−LC Start Reamers SR−123N−LC Mid Start Reamers Combination Gage CBG−12−3−N−1 Mandrel Check Fixture CBMG−12−3−N Mandrel CBM−12−3−N−2−55−V2 Flared Split Sleeves CBS−12−3−N−23F Nosecap Assembly MEN−26B−1223F Intermediate Reamer IR−123N−.4140−RC Final Reamer 1st Option FR1−123N−.4320−LC Clearance Reamer 1st Option CR1−123N−.4375−RC Final Hole Gage 1st Option CBFG−12−3−N−1−.4320/.43 40 Final Reamer 2nd Option Clearance Reamer 2nd Option Final Hole Gage 2nd Option

PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT No. A02 Hole Nos. 82,83 84,85,86 Puller Unit MBHO−20 MBHO−20 Preliminary Core Drills KD−221N−.6600−S* Preliminary Start Reamers Start Reamers SR−221N−SC or SR−221N−P67−SC* Mid Start Reamers SRM−202N−.6320−SC Combination Gage CBG−22−1−N−1 CBG−20−2−N−1 Mandrel Check Fixture CBMG−22−1−N CBMG−20−2−N

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 14PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT No. A02 Hole Nos. 82,83 84,85,86 Mandrel CBM−22−1−N−2OA−25−V2 CBM−20−2−N−2OA−40−V2 Flared Split Sleeves CBS−22−1−N−32F CBS−20−2−N−36F Nosecap Assembly CBCE−91S−2201F−RA CBCE−94S−2023F−RA Intermediate Reamer Final Reamer 1st Option FR1−221N−.6990−SC FR1−202N−.6522−SC Clearance Reamer 1st Option Final Hole Gage 1st Option CBFG−22−1−N−1−.6980/.7 000 CBFG−20−2−N−1−.6512/.653 2 Final Reamer 2nd Option FR2−221N−.7147−SC FR2−202N−.6680−SC Clearance Reamer 2nd Option Final Hole Gage 2nd Option CBFG−22−1−N−1−.7137/.7 157 CBFG−20−2−N−1−.6670/.669 0 * As the A320−57−1004 Service Bulletin may have been accomplished on the aircraft, and if the EHD is .6719/.6738, it will not be necessary to use KD−221N−.6600−S, rather select and use start reamer SR−221N−P67−SC

PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT No. A02 Hole Nos. 87 Puller Unit MHP−20−2−N−32/36 Preliminary Core Drills Preliminary Start Reamers Start Reamers Mid Start Reamers SRM−202N−.6320−SC Combination Gage CBG−20−2−N−1 Mandrel Check Fixture CBMG−20−2−N

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 15PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT No. A02 Hole Nos. 87 Mandrel USE SHORT MANDREL MARKED 20−2−N−32 ONLY ON THIS HOLE(INCLUDED WITH PULLER UNIT) Flared Split Sleeves CBS−20−2−N−32F Nosecap Assembly INCLUDED WITH PULLER UNIT Intermediate Reamer Final Reamer 1st Option FR1−202N−.6522−SC Clearance Reamer 1st Option Final Hole Gage 1st Option CBFG−20−2−N−1−.6512/.6532 Final Reamer 2nd Option FR2−202N−.6680−SC Clearance Reamer 2nd Option Final Hole Gage 2nd Option CBFG−20−2−N−1−.6670/.6690

PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT No. A02 Hole Nos. 88,89,90,91 92,93,94,95,96,97,98,99 100,101 Puller Unit MHP−20−2−N−32/36 MB−30 Preliminary Core Drills Preliminary Start Reamers Start Reamers SR−202N−RC Mid Start Reamers SRM−202N−.6320−SC Combination Gage CBG−20−2−N−1 CBG−20−2−N−1 Mandrel Check Fixture CBMG−20−2−N CBMG−20−2−N Mandrel USE LONG MANDREL MARKED 20−2−N−36 ONLY (INCLUDED WITH PULLER UNIT) CBM−20−2−N−2−55−V2

Flared Split Sleeves CBS−20−2−N−36F CBS−20−2−N−36F Nosecap Assembly INCLUDED WITH PULLER UNIT MEN−26C−2023F

Intermediate Reamer

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 16PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT No. A02 Hole Nos. 88,89,90,91 92,93,94,95,96,97,98,99 100,101 Final Reamer 1st Option FR1−202N−.6522−SC FR1−202N−.6522−RC Clearance Reamer 1st Option Final Hole Gage 1st Option CBFG−20−2−N−1−.6512/.6 532 CBFG−20−2−N−1−.6512/.653 2 Final Reamer 2nd Option FR2−202N−.6680−SC FR2−202N−.6680−RC Clearance Reamer 2nd Option Final Hole Gage 2nd Option CBFG−20−2−N−1−.6670/.6 690 CBFG−20−2−N−.6670/.6690

PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A03

Hole Nos. 5 6,7,10 Puller Unit MBHO−20 MBHO−20 Preliminary Core Drills KD−181N−.5380−R KD−221N−.6600−R Preliminary Start Reamers Start Reamers SR−181N−RC SR−221N−RC Mid Start Reamers Combination Gage CBG−18−1−N−1 CBG−22−1−N−1 Mandrel Check Fixture CBMG−18−1−N CBMG−22−1−N Mandrel CBM−18−1−N−2OA−65−V2 CBM−22−1−N−2OA−65−V2 Flared Split Sleeves CBS−18−1−N−36F CBS−22−1−N−36F Nosecap Assembly CBCE−99D−18−1−NF−RA CBCE−99E−22−1−NF−RA Intermediate Reamer Final Reamer 1st Option FR1−181N−.5731−RC FR1−221N−.6980−RC Clearance Reamer 1st Option CR1−181N−.5781−RC CR1−221N−.7031−RC

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 17PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A03

Hole Nos. 5 6,7,10 Final Hole Gage 1st Option CBFG−18−1−N−1−.5731/.5 751 CBFG−22−1−N−1−.6980/.7000
Final Reamer 2nd Option FR2−181N−.5887−RC FR2−221N−.7137−RC Clearance Reamer 2nd Option CR2−181N−.5937−RC CR2−221N−.7188−RC Final Hole Gage 2nd Option CBFG−18−1−N−1−.5887/.5 907 CBFG−22−1−N−1−.7137/.7157

PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A03

Hole Nos. 8,9,11,12,15,20 21,22 13,16,19 Puller Unit MB−30 MBHO−20 Preliminary Core Drills KD−221N−.6600−R KD−201N−.5980−R Preliminary Start Reamers Start Reamers SR−221N−RC SR−201N−RC Mid Start Reamers Combination Gage CBG−22−1−N−1 CBG−20−1−N−1 Mandrel Check Fixture CBMG−22−1−N CBMG−20−1−N Mandrel CBM−22−1−N−2−55−V2 CBM−20−1−N−2OA−50−V2 Flared Split Sleeves CBS−22−1−N−36F CBS−20−1−N−36F Nosecap Assembly MEN−26C−2201F CBCE−96D−20−1−NF−RA Intermediate Reamer Final Reamer 1st Option FR1−221N−.6980−RC FR1−201N−.6356−RC Clearance Reamer 1st Option CR1−221N−.7031−RC CR1−201N−.6406−RC Final Hole Gage 1st Option CBFG−22−1−N−1−.6980/.7 000 CBFG−20−1−N−1−.6356/.637 6 Final Reamer 2nd Option FR2−221N−.7137−RC FR2−201N−.6512−RC Clearance Reamer 2nd Option CR2−221N−.7188−RC CR2−201N−.6562−RC Final Hole Gage 2nd Option CBFG−22−1−N−1−.7137/.7 157 CBFG−20−1−N−1−.6512/.653 2

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 18PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A03

Hole Nos. 14 17,18,24,25 Puller Unit MB−30 MHPE−20−18−1−N−5205 Preliminary Core Drills KD−201N−.5980−R KD−181N−.5380−S Preliminary Start Reamers Start Reamers SR−201N−RC SR−181N−SC Mid Start Reamers Combination Gage CBG−20−1−N−1 CBG−18−1−N−1 Mandrel Check Fixture CBMG−20−1−N CBMG−18−1−N Mandrel CBM−20−1−N−2−55−V2 INCLUDED WITH PULLER UNIT Flared Split Sleeves CBS−20−1−N−36F CBS−18−1−N−23F Nosecap Assembly MEN−26B−2001F INCLUDED WITH PULLER UNIT Intermediate Reamer Final Reamer 1st Option FR1−201N−.6356−RC FR1−181N−.5731−SC Clearance Reamer 1st Option CR1−201N−.6406−RC CR1−181N−.5781−SC Final Hole Gage 1st Option CBFG−20−1−N−1−.6356/.6 376 CBFG−18−1−N−1−.5731/.575 1 Final Reamer 2nd Option FR2−201N−.6512−RC FR2−181N−.5887−SC Clearance Reamer 2nd Option CR2−201N−.6562−RC CR2−181N−.5937−SC Final Hole Gage 2nd Option CBFG−20−1−N−1−.6512/.6 532 CBFG−18−1−N−1−.5887/.590 7

PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A03

Hole Nos. 23,26,27 28,29,30,31 Puller Unit MBHO−20 MB−30 Preliminary Core Drills KD−181N−.5380−R KD−181N−.5380−R Preliminary Start Reamers Start Reamers SR−181N−RC SR−181N−RC Mid Start Reamers

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 19PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A03

Hole Nos. 23,26,27 28,29,30,31 Combination Gage CBG−18−1−N−1 CBG−18−1−N−1 Mandrel Check Fixture CBMG−18−1−N CBMG−18−1−N Mandrel CBM−18−1−N−2OA−50−V2 CBM−18−1−N−2−55−V2 Flared Split Sleeves CBS−18−1−N−36F CBS−18−1−N−36F Nosecap Assembly CBCE−96D−18−1−NF−RA MEN−26B−1801F Intermediate Reamer Final Reamer 1st Option FR1−181N−.5731−RC FR1−181N−.5731−RC Clearance Reamer 1st Option CR1−181N−.5781−RC CR1−181N−.5781−RC Final Hole Gage 1st Option CBFG−18−1−N−1−.5731/.5 751 CBFG−18−1−N−1−.5731/.575 1 Final Reamer 2nd Option FR2−181N−.5887−RC FR2−181N−.5887−RC Clearance Reamer 2nd Option CR2−181N−.5937−RC CR2−181N−.5937−RC Final Hole Gage 2nd Option CBFG−18−1−N−1−.5887/.5 907 CBFG−18−1−N−1−.5887/.590 7

PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A03

Hole Nos. 36,37,38,41,42 46,47 39,40,43,44,45,48 49,50,51 Puller Unit MB−30 MB−30 Preliminary Core Drills Preliminary Start Reamers PSR−160N−.4590−RC PSR−123N−.3906−RC Start Reamers SR−160N−RC SR−123N−RC Mid Start Reamers Combination Gage CBG−16−0−N−1 CBG−12−3−N−1 Mandrel Check Fixture CBMG−16−0−N CBMG−12−3−N Mandrel CBM−16−0−N−2−55−V2 CBM−12−3−N−2−55−V2 Flared Split Sleeves CBS−16−0−N−23F CBS−12−3−N−23F Nosecap Assembly MEN−26B−1601F MEN−26B−1223F Intermediate Reamer

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 20PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT No. A03

Hole Nos. 36,37,38,41,42 46,47 39,40,43,44,45,48 49,50,51 Final Reamer 1st Option FR1−160N−.4945−RC FR1−123N−.4320−RC Clearance Reamer 1st Option CR1−160N−.5000−RC CR1−123N−.4375−RC Final Hole Gage 1st Option CBFG−16−0−N−1−.4945/.4 965 CBFG−12−3−N−1−.4320/.434 0 Final Reamer 2nd Option FR2−160N−.5101−RC Clearance Reamer 2nd Option CR2−160N−.5156−RC Final Hole Gage 2nd Option CBFG−16−0−N−1−.5101/.5 121

PLANNING INFORMATION FOR ACTUATING CYLINDER ANCHORAGE EFFECTIVE TO KIT No. A03
Hole Nos. 52,53,54,55,56,57 58,59,60,61 62,63,64,65 Puller Unit MB−30 MB−30 Preliminary Core Drills KD181N−.5380−L Preliminary Start Reamers Start Reamers SR−162N−LC SR−181N−LC Mid Start Reamers Combination Gage CBG−16−2−N−1 CBG−18−1−N−1 Mandrel Check Fixture CBMG−16−2−N CBMG−18−1−N Mandrel CBM−16−2−N−2−55−V2 CBM−18−1−N−2−55−V2 Flared Split Sleeves CBS−16−2−N−36F CBS−18−1−N−36F Nosecap Assembly MEN−26B−1623F MEN−26B−1801F Intermediate Reamer IR−162N−.5140−RC IR−181N−.5630−RC Final Reamer 1st Option FR1−162N−.5257−LC FR1−181N−.5731−LC Clearance Reamer 1st Option CR1−162N−.5312−RC

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 21PLANNING INFORMATION FOR ACTUATING CYLINDER ANCHORAGE EFFECTIVE TO KIT No. A03
Hole Nos. 52,53,54,55,56,57 58,59,60,61 62,63,64,65 Final Hole Gage 1st Option CBFG−16−2−N−1−.5257/.5 277 CBFG−18−1−N−1−.5731/.575 1 Final Reamer 2nd Option FR2−162N−.5410−LC FR2−181N−.5887−LC Clearance Reamer 2nd Option CR2−162N−.5470−RC Final Hole Gage 2nd Option CBFG−16−2−N−1−.5410/.5 430 CBFG−18−1−N−1−.5887/.590 7

PLANNING INFORMATION FOR ACTUATING CYLINDER ANCHORAGE EFFECTIVE TO KIT No. A03
Hole Nos. 66,67,68,69,70,71 72,73 74,75,76,77,78,79 80,81 Puller Unit MB−30 MB−30 Preliminary Core Drills Preliminary Start Reamers PSR−160N−.4590−LC PSR−123N−.3906−LC Start Reamers SR−160N−LC SR−123N−LC Mid Start Reamers Combination Gage CBG−16−0−N−1 CBG−12−3−N−1 Mandrel Check Fixture CBMG−16−0−N CBMG−12−3−N Mandrel CBM−16−0−N−2−55−V2 CBM−12−3−N−2−55−V2 Flared Split Sleeves CBS−16−0−N−23F CBS−12−3−N−23F Nosecap Assembly MEN−26B−1601F MEN−26B−1223F Intermediate Reamer IR−160N−.4840−RC IR−123N−.4140−RC Final Reamer 1st Option FR1−160N−.4945−LC FR1−123N−.4320−LC Clearance Reamer 1st Option CR1−160N−.5000−RC CR1−123N−.4375−RC Final Hole Gage 1st Option CBFG−16−0−N−1−.4945/.4 965 CBFG−12−3−N−1−.4320/.434 0 Final Reamer 2nd Option FR2−160N−.5101−LC Clearance Reamer 2nd Option Final Hole Gage 2nd Option CBFG−16−0−N−1−.5101/.5 121

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 22PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT No. A03 Hole Nos. 82,83 84,85,86 Puller Unit MBHO−20 MBHO−20 Preliminary Core Drills Preliminary Start Reamers Start Reamers Mid Start Reamers SRM−202N−.6320−SC SRM−202N−.6320−SC Combination Gage CBG−20−2−N−1 CBG−20−2−N−1 Mandrel Check Fixture CBMG−20−2−N CBMG−20−2−N Mandrel CBM−20−2−N−2OA−25−V2 CBM−20−2−N−2OA−40−V2 Flared Split Sleeves CBS−20−2−N−36F CBS−20−2−N−36F Nosecap Assembly CBCE−91S−2023F−RA CBCE−94S−2023F−RA Intermediate Reamer Final Reamer 1st Option FR1−202N−.6522−SC FR1−202N−.6522−SC Clearance Reamer 1st Option Final Hole Gage 1st Option CBFG−20−2−N−1−.6512/.6 532 CBFG−20−2−N−1−.6512/.653 2 Final Reamer 2nd Option FR2−202N−.6680−SC FR2−202N−.6680−SC Clearance Reamer 2nd Option Final Hole Gage 2nd Option CBFG−20−2−N−1−.6670/.6 690 CBFG−20−2−N−1−.6670/.669 0

PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT No. A03 Hole Nos. 87 Puller Unit MHP−20−2−N−32/36 Preliminary Core Drills Preliminary Start Reamers Start Reamers Mid Start Reamers SRM−202N−.6320−SC Combination Gage CBG−20−2−N−1 Mandrel Check Fixture CBMG−20−2−N

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 23PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT No. A03 Hole Nos. 87 Mandrel USE SHORT MANDREL MARKED 20−2−N−32 ONLY ON THIS HOLE(INCLUDED WITH PULLER UNIT) Flared Split Sleeves CBS−20−2−N−32F Nosecap Assembly INCLUDED WITH PULLER UNIT Intermediate Reamer Final Reamer 1st Option FR1−202N−.6522−SC Clearance Reamer 1st Option Final Hole Gage 1st Option CBFG−20−2−N−1−.6512/.6532 Final Reamer 2nd Option FR2−202N−.6680−SC Clearance Reamer 2nd Option Final Hole Gage 2nd Option CBFG−20−2−N−1−.6670/.6690

PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT No. A03 Hole Nos. 88,89,90,91 92,93,94,95,96,97,98 99,100,101 Puller Unit MHP−20−2−N−32/36 MB−30 Preliminary Core Drills Preliminary Start Reamers Start Reamers SR−202N−RC Mid Start Reamers SRM−202N−.6320−SC Combination Gage CBG−20−2−N−1 CBG−20−2−N−1 Mandrel Check Fixture CBMG−20−2−N CBMG−20−2−N Mandrel USE LONG MANDREL MARKED 20−2−N−36 ONLY (INCLUDED WITH PULLER UNIT) CBM−20−2−N−2−55−V2

Flared Split Sleeves CBS−20−2−N−36F CBS−20−2−N−36F Nosecap Assembly INCLUDED WITH PULLER UNIT MEN−26C−2023F Intermediate Reamer

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 24PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT No. A03 Hole Nos. 88,89,90,91 92,93,94,95,96,97,98 99,100,101 Final Reamer 1st Option FR1−202N−.6522−SC FR1−202N−.6522−RC Clearance Reamer 1st Option Final Hole Gage 1st Option CBFG−20−2−N−1−.6512/.6 532 CBFG−20−2−N−1−.6512/.653 2 Final Reamer 2nd Option FR2−202N−.6680−SC FR2−202N−.6680−RC Clearance Reamer 2nd Option Final Hole Gage 2nd Option CBFG−20−2−N−1−.6670/.6 690 CBFG−20−2−N−.6670/.6690

PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT Nos. A05/A07/A08 Hole Nos. 5 6,7,10 Puller Unit MBHO−20 MBHO−20 Preliminary Core Drills Preliminary Start Reamers Start Reamers SR−162N−RC SR−202N−RC Mid Start Reamers Combination Gage CBG−16−2−N−1 CBG−20−2−N−1 Mandrel Check Fixture CBMG−16−2−N CBMG−20−2−N Mandrel CBM−16−2−N−20A−65−V2 CBM−20−2−N−20A−65−V2 Flared Split Sleeves CBS−16−2−N−36F CBS−20−2−N−36F Nosecap Assembly CBCE−99D−16−2−NF−RA CBCE−99E−20−2−NF−RA Intermediate Reamer Final Reamer 1st Option FR1−162N−.5257−RC FR1−202N−.6512−RC Clearance Reamer 1st Option CR1−162N−.5312−RC CR1−202N−.6562−RC

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 25PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT Nos. A05/A07/A08 Hole Nos. 5 6,7,10 Final Hole Gage 1st Option CBFG−16−2−N−1−.5257/.5 277 CBFG−20−2−N−1−.6512/.6532
Final Reamer 2nd Option FR2−162N−.5410−RC FR2−202N−.6670−RC Clearance Reamer 2nd Option CR2−162N−.5470−RC CR2−202N−.6720−RC Final Hole Gage 2nd Option CBFG−16−2−N−1−.5410/.5 430 CBFG−20−2−N−1−.6670/.6690

PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT Nos. A05/A07/A08 Hole Nos. 8,9,11,12,15,20 21,22 13,16,19 Puller Unit MB−30 MBHO−20 Preliminary Core Drills Preliminary Start Reamers Start Reamers SR−202N−RC SR−182N−RC Mid Start Reamers Combination Gage CBG−20−2−N−1 CBG−18−2−N−1 Mandrel Check Fixture CBMG−20−2−N CBMG−18−2−N Mandrel CBM−20−2−N−2−55−V2 CBM−18−2−N−20A−50−V2 Flared Split Sleeves CBS−20−2−N−36F CBS−18−2−N−36F Nosecap Assembly MEN−26C−2023F CBCE−96D−18−2−NF−RA Intermediate Reamer Final Reamer 1st Option FR1−202N−.6522−RC FR1−182N−.5887−RC
Clearance Reamer 1st Option CR1−202N−.6562−RC CR1−182N−.5937−RC

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 26PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT Nos. A05/A07/A08 Hole Nos. 8,9,11,12,15,20 21,22 13,16,19 Final Hole Gage 1st Option CBFG−20−2−N−1−.6512/.6 532 CBFG−18−2−N−1−.5887/.590 7 Final Reamer 2nd Option FR2−202N−.6670−RC FR2−182N−.6040−RC Clearance Reamer 2nd Option CR2−202N−.6720−RC CR2−182N−.6090−RC Final Hole Gage 2nd Option CBFG−20−2−N−1−.6670/.6 690 CBFG−18−2−N−1−.6040/.606 0

PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT Nos. A05/A07/A08 Hole Nos. 14 17,18,24,25 Puller Unit MB−30 MHPE−15−16−2−N−5205 Preliminary Core Drills Preliminary Start Reamers Start Reamers SR−182N−RC SR−162N−SC Mid Start Reamers Combination Gage CBG−18−2−N−1 CBG−16−2−N−1 Mandrel Check Fixture CBMG−18−2−N CBMG−16−2−N Mandrel CBM−18−2−N−2−55−V2 INCLUDED WITH PULLER UNIT Flared Split Sleeves CBS−18−2−N−36F CBS−16−2−N−23F Nosecap Assembly MEN−26B−1823F INCLUDED WITH PULLER UNIT Intermediate Reamer Final Reamer 1st Option FR1−182N−.5887−RC FR1−162N−.5257−SC Clearance Reamer 1st Option CR1−182N−.5937−RC CR1−162N−.5312−SC

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 27PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT Nos. A05/A07/A08 Hole Nos. 14 17,18,24,25 Final Hole Gage 1st Option CBFG−18−2−N−1−.5887/.5 907 CBFG−16−2−N−1−.5257/.527 7 Final Reamer 2nd Option FR2−182N−.6040−RC FR2−162N−.5410−SC Clearance Reamer 2nd Option CR2−182N−.6090−RC CR2−162N−.5470−SC Final Hole Gage 2nd Option CBFG−18−2−N−1−.6040/.6 060 CBFG−16−2−N−1−.5410/.543 0

PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT Nos. A05/A07/A08 Hole Nos. 23,26,27 28,29,30,31 Puller Unit MBHO−20 MB−30 Preliminary Core Drills Preliminary Start Reamers Start Reamers SR−162N−RC SR−162N−RC Mid Start Reamers Combination Gage CBG−16−2−N−1 CBG−16−2−N−1 Mandrel Check Fixture CBMG−16−2−N CBMG−16−2−N Mandrel CBM−16−2−N−20A−50−V2 CBM−16−2−N−2−55−V2 Flared Split Sleeves CBS−16−2−N−36F CBS−16−2−N−36F Nosecap Assembly CBCE−96D−16−2−NF−RA MEN−26B−1623F Intermediate Reamer Final Reamer 1st Option FR1−162N−.5257−RC FR1−162N−.5257−RC Clearance Reamer 1st Option CR1−162N−.5312−RC CR1−162N−.5312−RC Final Hole Gage 1st Option CBFG−16−2−N−1−.5257/.5 277 CBFG−16−2−N−1−.5257/.527 7 Final Reamer 2nd Option FR2−162−.5410−RC FR2−162−.5410−RC Clearance Reamer 2nd Option CR2−162N−.5470−RC CR2−162N−.5470−RC Final Hole Gage 2nd Option CBFG−16−2−N−1−.5410/.5 430 CBFG−16−2−N−1−.5410/.543 0

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 28PLANNING INFORMATION FOR PINTLE FITTING EFFECTIVE TO KIT Nos. A05/A07/A08 Hole Nos. 36,37,38,41,42,46,47 39,40,43,44,45,48 49,50,51 Puller Unit MB−30 MB−30 Preliminary Core Drills Preliminary Start Reamers Start Reamers SR−141N−RC SR−121N−RC Mid Start Reamers Combination Gage CBG−14−1−N−1 CBG−12−1−N−1 Mandrel Check Fixture CBMG−14−1−N CBMG−12−1−N Mandrel CBM−14−1−N−2−55−V2 CBM−12−1−N−2−55−V2 Flared Split Sleeves CBS−14−1−N−23F CBS−12−1−N−23F Nosecap Assembly MEN−26B−1401F MEN−26B−1201F Intermediate Reamer Final Reamer 1st Option FR1−141N−.4632−RC FR1−121N−.4007−RC Clearance Reamer 1st Option CR1−141N−.4687−RC CR1−121N−.4062−RC Final Hole Gage 1st Option CBFG−14−1−N−1−.4632/.4 652 CBFG−12−1−N−1−.4007/.402 7 Final Reamer 2nd Option Clearance Reamer 2nd Option Final Hole Gage 2nd Option

PLANNING INFORMATION FOR ACTUATING CYLINDER ANCHORAGE EFFECTIVE TO KIT Nos. A05/A07/A08

Hole Nos. 52,53,54,55,56,57,58,5 9 60,61,62,63,64,65 66,67,68,69,70,71,72,73 Puller Unit MB−30 MB−30 Preliminary Core Drills Preliminary Start Reamers Start Reamers SR−162N−LC SR−141N−LC

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 29PLANNING INFORMATION FOR ACTUATING CYLINDER ANCHORAGE EFFECTIVE TO KIT Nos. A05/A07/A08

Hole Nos. 52,53,54,55,56,57,58,5 9 60,61,62,63,64,65 66,67,68,69,70,71,72,73 Mid Start Reamers Combination Gage CBG−16−2−N−1 CBG−14−1−N−1 Mandrel Check Fixture CBMG−16−2−N CBMG−14−1−N Mandrel CBM−16−2−N−2−55−V2 CBM−14−1−N−2−55−V2 Flared Split Sleeves CBS−16−2−N−36F CBS−14−1−N−23F Nosecap Assembly MEN−26B−1623F MEN−26B−1401F Intermediate Reamer IR−162N−.5140−RC IR−141N−.4450−RC Final Reamer 1st Option FR1−162N−.5257−LC FR1−141N−.4632−LC Clearance Reamer 1st Option CR1−162N−.5312−RC CR1−141N−.4687−RC Final Hole Gage 1st Option CBFG−16−2−N−1−.5257/.5 277 CBFG−14−1−N−1−.4632/.465 2 Final Reamer 2nd Option FR2−162N−.5410−LC Clearance Reamer 2nd Option CR2−162N−.5470−RC Final Hole Gage 2nd Option CBFG−16−2−N−1−.5410/.5 430

PLANNING INFORMATION FOR ACTUATING CYLINDER ANCHORAGE EFFECTIVE TO KIT Nos. A05/A07/A08

Hole Nos. 74,75,76,77,78,79 80,81 Puller Unit MB−30 Preliminary Core Drills Preliminary Start Reamers Start Reamers SR−121N−LC Mid Start Reamers Combination Gage CBG−12−1−N−1 Mandrel Check Fixture CBMG−12−1−N Mandrel CBM−12−1−N−2−55−V2

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 30PLANNING INFORMATION FOR ACTUATING CYLINDER ANCHORAGE EFFECTIVE TO KIT Nos. A05/A07/A08

Hole Nos. 74,75,76,77,78,79 80,81 Flared Split Sleeves CBS−12−1−N−23F Nosecap Assembly MEN−26B−1201F Intermediate Reamer IR−121N−.3820−RC Final Reamer 1st Option FR1−121N−.4007−LC Clearance Reamer 1st Option CR1−121N−.4062−RC Final Hole Gage 1st Option CBFG−12−1−N−1−.4007/.4 027 Final Reamer 2nd Option Clearance Reamer 2nd Option Final Hole Gage 2nd Option

PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT Nos. A05/A07/A08

Hole Nos. 82,83 84,85,86 Puller Unit MBHO−20 MBHO−20 Preliminary Core Drills Preliminary Start Reamers Start Reamers Mid Start Reamers SRM−202N−.6320−SC SRM−202N−.6320−SC Combination Gage CBG−20−2−N−1 CBG−20−2−N−1 Mandrel Check Fixture CBMG−20−2−N CBMG−20−2−N Mandrel CBM−20−2−N−2OA−25−V2 CBM−20−2−N−2OA−40−V2 Flared Split Sleeves CBS−20−2−N−36F CBS−20−2−N−36F Nosecap Assembly CBCE−91S−2023F−RA CBCE−94S−2023F−RA Intermediate Reamer Final Reamer 1st Option FR1−202N−.6522−SC FR1−202N−.6522−SC Clearance Reamer 1st Option

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 31PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT Nos. A05/A07/A08

Hole Nos. 82,83 84,85,86 Final Hole Gage 1st Option CBFG−20−2−N−1−.6512/.6 532 CBFG−20−2−N−1−.6512/.653 2 Final Reamer 2nd Option FR2−202N−.6680−SC FR2−202N−.6680−SC Clearance Reamer 2nd Option Final Hole Gage 2nd Option CBFG−20−2−N−1−.6670/.6 690 CBFG−20−2−N−1−.6670/.669 0

PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT Nos. A05/A07/A08

Hole Nos. 87 Puller Unit MHP−20−2−N−32/36 Preliminary Core Drills Preliminary Start Reamers Start Reamers Mid Start Reamers SRM−202N−.6320−SC Combination Gage CBG−20−2−N−1 Mandrel Check Fixture CBMG−20−2−N Mandrel USE SHORT MANDREL MARKED 20−2−N−32 ONLY ON THIS HOLE(INCLUDED WITH PULLER UNIT) Flared Split Sleeves CBS−20−2−N−32F Nosecap Assembly INCLUDED WITH PULLER UNIT Intermediate Reamer Final Reamer 1st Option FR1−202N−.6522−SC Clearance Reamer 1st Option Final Hole Gage 1st Option CBFG−20−2−N−1−.6512/.6532 Final Reamer 2nd Option FR2−202N−.6680−SC Clearance Reamer 2nd Option Final Hole Gage 2nd Option CBFG−20−2−N−1−.6670/.6690

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 32PLANNING INFORMATION FOR GEAR RIB EFFECTIVE TO KIT Nos. A05/A07/A08

Hole Nos. 88,89,90,91 92,93,94,95,96,97,98 99,100,101 Puller Unit MHP−20−2−N−32/36 MB−30 Preliminary Core Drills Preliminary Start Reamers Start Reamers SR−202N−RC Mid Start Reamers SRM−202N−.6320−SC Combination Gage CBG−20−2−N−1 CBG−20−2−N−1 Mandrel Check Fixture CBMG−20−2−N CBMG−20−2−N Mandrel USE LONG MANDREL MARKED 20−2−N−36 ONLY (INCLUDED WITH PULLER UNIT) CBM−20−2−N−2−55−V2

Flared Split Sleeves CBS−20−2−N−36F CBS−20−2−N−36F Nosecap Assembly INCLUDED WITH PULLER UNIT MEN−26C−2023F

Intermediate Reamer Final Reamer 1st Option FR1−202N−.6522−SC FR1−202N−.6522−RC Clearance Reamer 1st Option Final Hole Gage 1st Option CBFG−20−2−N−1−.6512/.6 532 CBFG−20−2−N−1−.6512/.653 2 Final Reamer 2nd Option FR2−202N−.6680−SC FR2−202N−.6680−RC Clearance Reamer 2nd Option Final Hole Gage 2nd Option CBFG−20−2−N−1−.6670/.6 690 CBFG−20−2−N−1−.6670/.669 0

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 03

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 33For all tooling requirements for Kit Nos A01, A02 and A03 refer to FTI.

CAPITAL TOOLING Procurable from MSC by model number. Model No. Nomenclature KIT No. Applicability FT−200 PowerPak All Kits MBHO−20 Off−Set Puller All Kits MB−30 Medium Brute Puller All Kits

DURABLE TOOLING KIT For Kits A05,A07,A08 Procurable from MSC as PART NUMBER 8004−644 Nomenclature Qty MHPE−15−16−2−N−5205 Assy,Hand Puller 1 MHP−20−2−N−32/36 Assy, Mini Hand Puller * 1

Nomenclature Mandrel, threaded (long) Mandrel, threaded (short) 5376−008 1 Nut, Special Hardened 9/16−18UNF 5514−001 2

REVISION No. : 03 − Feb 09/01 L7 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 04 COLD EXPANSION TOOLING CAPITAL TOOLING, DURABLE TOOLING & CONSUMABLE TOOLING

* In addition the following is a list of sub components for the Mini Hand Puller Assy MHP−20−2−N−32/36 that are included in the durable kit.

LIST OF PARTS INCLUDED IN DURABLE TOOLING SETS FOR KITS A05,A07,A08

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 1 of 6Part No. Description Model Number Qty 2072−167 Combination Gage CBG−12−1−N−1 1 2020−057 Mandrel Check Fixture CBMG−12−1−N 1 2466−316 Mandrel CBM−12−1−N−2−55−V2 1 5157−025 Nosecap MEN−26B−1201F 1 2368−233 Final Hole Gage 1st Option CBFG−12−1−N−1−.4007/.4027 1 1045−261 Tooling Set Box FT−BX−C2 1

Part No. Description Model Number Qty 2072−195 Combination Gage CBG−14−1−N−1 1 2020−053 Mandrel Check Fixture CBMG−14−1−N 1 2466−320 Mandrel CBM−14−1−N−2−55−V2 1 5157−027 Nosecap MEN−26B−1401F 1 2368−304 Final Hole Gage 1st Option CBFG−14−1−N−1−.4632/.4652 1 1045−261 Tooling Set Box FT−BX−C2 1

Part No. Description Model Number Qty 2072−205 Combination Gage CBG−16−2−N−1 1 2020−048 Mandrel Check Fixture CBMG−16−2−N 1 2673−350 Mandrel CBM−16−2−N−20A−50−V2 1 2673−351 Mandrel CBM−16−2−N−20A−65−V2 1 2466−325 Mandrel CBM−16−2−N−2−55−V2 1 2946−026 Nosecap CBCE−96D−16−2−NF−RA 1 2946−028 Nosecap CBCE−99D−16−2−NF−RA 1 5157−030 Nosecap MEN−26B−1623F 1 2368−252 Final Hole Gage 1st Option CBFG−16−2−N−1−.5257/.5277 1 1045−424 Tooling Set Box FT−BX−MTB 1

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 04

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 2Part No. Description Model Number Qty 2072−213 Combination Gage CBG−18−2−N−1 1 2020−044 Mandrel Check Fixture CBMG−18−2−N 1 2673−313 Mandrel CBM−18−2−N−20A−50−V2 1 2466−329 Mandrel CBM−18−2−N−2−55−V2 1 2946−027 Nosecap CBCE−96D−18−2−NF−RA 1 5157−032 Nosecap MEN−26B−1823F 1 2368−301 Final Hole Gage 1st Option CBFG−18−2−N−1−.5887/.5907 1 1045−261 Tooling Set Box FT−BX−C2 1

Part No. Description Qty 2072−221 Combination Gage CBG−20−2−N−1 1 2020−040 Mandrel Check Fixture CBGM−20−2−N 1 2672−154 Mandrel CBM−20−2−N−20A−40−V2 1 2672−079 Mandrel CBM−20−2−N−20A−25−V2 1 2672−279 Mandrel CBM−20−2−N−20A−65−V2 1 2628−229 Mandrel CBM−20−2−N−2−55−V2 1 5157−034 Nosecap MEN−26C−2023F 1 2946−030 Nosecap CBCE−91S−2023F−RA 1 5119−001 Nosecap CBCE−94S−2023F−RA 1 2946−029 Nosecap CBCE−99E−20−2−NF−RA 1 2368−297 Final Hole Gage 1st Option CBFG−20−2−N−1−.6512/.6532 1 1045−424 Tooling Set Box FT−BX−MTB 1

CONSUMABLE TOOLING KIT For Kits A05,A07,A08 Consumable Tooling Set Procurable from MSC as PART NUMBER 8004−643

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 04

LIST OF PARTS INCLUDED IN CONSUMABLE TOOLING SET FOR KITS A05,A07,A08 This Tooling Kit Set contains a sufficient number of sleeves to work 1 aircraft. If you require additional sleeves or tooling, please contact Airbus Industrie.

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 3Where the consumable tooling is used : Part No. Description Model Number Qty 1126−144 Start Reamer SR−121N−RC 3 1126−145 Start Reamer SR−121N−LC 3 2515−184 Flared Split Sleeve CBS−12−1−N−23F 47 1143−112 Intermediate Reamer IR−121N−.3820−RC 2 1143−092 Final Reamer 1st Option FR1−121N−.4007−RC 3 1143−093 Final Reamer 1st Option FR1−121N−.4007−LC 3 1143−113 Clearance Reamer 1st Option CR1−121N−.4062−RC 2

Where the consumable tooling is used : Part No. Description Model Number Qty 1126−146 Start Reamer SR−141N−RC 3 1126−147 Start Reamer SR−141N−LC 3 2515−216 Flared Split Sleeve CBS−14−1−N−23F 42 1143−114 Intermediate Reamer IR−141N−.4450−RC 2
1143−094 Final Reamer 1st Option FR1−141N−.4632−RC 3 1143−095 Final Reamer 1st Option FR1−141N−.4632−LC 3 1143−115 Clearance Reamer 1st Option CR1−141N−.4687−RC 2

Where the consumable tooling is used : Part No. Description Model Number Qty 1126−149 Start Reamer SR−162N−SC 3 1126−150 Start Reamer SR−162N−RC 3

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 04

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 4Where the consumable tooling is used : Part No. Description Model Number Qty 1126−148 Start Reamer SR−162N−LC 3 2525−256 Flared Split Sleeve CBS−16−2−N−23F 55 2515−791 Flared Split Sleeve CBS−16−2−N−36F 55 1143−104 Intermediate Reamer IR−162N−.5140−RC 2 1143−090 Final Reamer 1st Option FR1−162N−.5257−SC 3 1143−089 Final Reamer 1st Option FR1−162N−.5257−RC 3 1143−091 Final Reamer 1st Option FR1−162N−.5257−LC 3 1143−109 Clearance Reamer 1st Option CR1−162N−.5312−SC 2 1143−108 Clearance Reamer 1st Option CR1−162N−.5312−RC 2

Where the consumable tooling is used : Part No. Description Model Number Qty 1126−142 Start Reamer SR−182N−RC 3 2515−794 Flared Split Sleeve CBS−18−2−N−36F 12 1143−087 Final Reamer 1st Option FR1−182N−.5887−RC 3 1143−135 Clearance Reamer 1st Option CR1−182N−.5937−RC 2

Where the consumable tooling is used : Part No. Description Model Number Qty 1126−153 Start Reamer SR−202N−RC 3 1126−130 Mid Start Reamer SRM−202N−.6320−SC 3

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 04

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 5Where the consumable tooling is used : Part No. Description Model Number Qty 2515−798 Flared Split Sleeve CBS−20−2−N−36F 62 2515−745 Flared Split Sleeve CBS−20−2−N−32F 3 1143−065 Final Reamer 1st Option FR1−202N−.6522−SC 3 1143−044 Final Reamer 1st Option FR1−202N−.6522−RC 3 1143−136 Clearance Reamer 1st Option CR1−202N−.6562−RC 2

Part No. Description Model Number Qty 1143−107 Final Reamer 2nd Option FR2−162−.5410−SC 2 1143−106 Final Reamer 2nd Option FR2−162−.5410−RC 2 1143−105 Final Reamer 2nd Option FR2−162−.5410−LC 2 1143−111 Clearance Reamer 2nd Option CR2−162−.5470−SC 2 1143−110 Clearance Reamer 2nd Option CR2−162−.5470−RC 2 2368−303 Final Hole Gage 2nd Option CBFG−16−2−N−1−.5410/.5430 1
1143−099 Final Reamer 2nd Option FR2−182−.6040−RC 2 1143−100 Clearance Reamer 2nd Option CR2−182−.6090−RC 2 2368−302 Final Hole Gage 2nd Option CBFG−18−2−N−1−.6040/.6060 1
1143−061 Final Reamer 2nd Option FR2−202−.6680−SC 2 1143−097 Final Reamer 2nd Option FR2−202−.6670−RC 2 1143−054 Final Reamer 2nd Option FR2−202−.6680−RC 2 1143−098 Clearance Reamer 2nd Option CR2−202−.6720−RC 2 2368−296 Final Hole Gage 2nd Option CBFG−20−2−N−1−.6670/.6690 1

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 04

2nd OPTION TOOL KIT (SUPPLEMENTARY KIT) Procurable from MSC as PART NUMBER 8004−645

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 61.

1.A.

1.B.

1.C.

1.D.

1.E.

1.F.

1.G.

1.H.

2.

2.A.

REVISION No. : 03 − Feb 09/01 L7 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 05 1. COLD EXPANSION TOOLING AND PROCESS INFORMATION SHEETS General Cold Expansion Process Refer to Figure 1 A. Select the cold expansion tooling from the Tool Listing. Drill the hole using the preliminary core drill (KD−XXXN−.XXXX−X), if required. B. Ream the hole to the appropriate starting hole diameter using the starting reamer (SR−XXXN−XC) or mid start reamer (SRM−XXXN−.XXXX−XC). In some locations it will be necessary to use a pre startreamer (PSR−XXXN−.XXXX−XC) prior to using a starting reamer. C. Verify the starting hole diameter using the starting hole go/no−go end of the combination gage (CBG−XX−X−N−1). If the hole is oversized, reject the hole and contact AIRBUS INDUSTRIE, Structures Repair Engineering Department for approval to rework to the next available hole size. D. Check the mandrel major diameter for wear by inserting the mandrel into the mandrel check fixture (CBMG−XX−X−N). If the mandrel is excessively worn and goes through the gage, discard the mandrel and select a new one. E. Split Sleeve Cold Expand the hole using the mandrel (CBM−XX−X−N−X−XX−V2), sleeves (CBS−XX−X−N−XXF), nosecap (MEN−XXX−XXXXF or CBCE−XXX−XXXXXX−XX), puller (MB−30, MBHO−20, MHPE−15−16−2−N−5205 or MHP−20−2−N−32/36), and PowerPak (FT−200, if required) specified in the Tooling List. F. Verify the cold expansion of the hole by using the Cx verification end of the combination gage (CBG−XX−X−N−1). If the gage does not go through the hole, the hole may not have been cold expanded. In some cases, the gage will not go through the holes in the pintle fitting because the titanium material does not expand at the same rate as the aluminum spar. Check the holes in the spar for pintle hole locations. Do Step C of this rework procedure again. G. Ream the holes to the appropriate final hole diameter using the gage finish reamer (FR1−XXXN−.XXXX−XC). Jack anchorage locations will require use of intermediate reamers (IR−XXXN−.XXXX−XC) to bring the anchorage to the post cold work size of the spar prior to finish reaming. Jack anchorage and pintle locations are reamed with clearance reamers (CR1−XXXN−.XXXX−XC) in the anchorage and pintle material only after reaming with finish reamers. H. Check finished reamed hole size with finished hole gage (CBFG−XX−X−N−1−.XXXX/.XXXX). If the hole is oversized, reject the hole and contact AIRBUS INDUSTRIE, Structures Repair Engineering Department for approval to rework to the next available hole size. 2. DEFINITIONS OF CAPITAL, DURABLE AND CONSUMABLE TOOLING. A. Capital Tooling − Includes tools such as Hydraulic Puller units (e.g. MB30 Medium Brute Puller Unit) and Power Packs (e.g. FT−200 Hydraulic PowerPak). This tooling enables use of Durable and Consumable tooling for Split Sleeve Cold Expansion in a wide variety of production and rework

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 1 of 62.B.

2.C.

3.

3.A.

3.B.

3.C.

REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 05 applications. For customers who do not already posess this tooling, it may be available on loan from MSC, AIRBUS INDUSTRIE. B. Durable Tooling − Includes tools which will not be consumed per aircraft but will wear over use. They should be inspected during and after each modification to make sure they have not worn below acceptable limits (e.g. the mandrel major diameter should be checked with the mandrel check fixture). Mandrels, combination gages, mandrel gages, Hand Pullers (e.g. MHP−20−2−N−32/36 Hand Puller), nosecap and final hole gages are examples of Durable Tooling. Tool Kits include a set of Durable Tooling required for the modification. Worn tooling replacement is the responsibility of the operator. C. Consumable Tools − Includes tools which are consumed during the Split Sleeve Cold Expansion process. Quantities defined in each Kit are sufficient to perform the modification of one aircraft. This is based upon in−service experience. The airline is responsible for any additional items they may need beyond those supplied in the Kit. Split sleeves, core drills, start reamers, final hole reamers and clearance reamers are all examples of consumable tools. 3. IN−SERVICE EXPERIENCE WITH TOOLING A. Capital Tooling − There has been no reported problems with capital tooling. B. Durable Tooling − Precautions must be taken to prevent threads on the MHP−20−2−N−32/36 from stripping. The liklihood of thread stripping can be reduced by applying a lubricant to the mandrel threads before use (Refer to Figure 2 ). A moly disulfide based lubricant or similar "anti−seize" type grease is recommended. The mandrel nut and threads should be inspected before each use. Replace if threads show signs of wear. Use only the 5514−001 special hardened nut if replacement is required. The life of the mandrel could be limited to one aircraft. − There have been reports that the MHP mandrel comes in contact with Rib 5 while processing hole 87 (Refer to Figure 3 ). This problem has been resolved by supplying a shorter mandrel with the MHP for processing hole 87. CAUTION : DO NOT USE THIS TOOLING ON ANY OTHER HOLE AS THE MANDREL MAY BECOME STUCK AND POTENTIALLY DAMAGE THE STRUCTURE. Use only mandrels stamped with 20−2−N−32 with split sleeve CBS−20−2−N−32F for hole 87. Mandrels marked 20−2−N−36 are to be used for holes 88, 89, 90 and 91. NOTE : There has been no reported problems with MHPE type puller unit. C. Consumable Tooling − Pilot end of finish reamers (e.g. FR1−XXXX−XXXX−LC or RC) in some cases will not fit into the post cold expanded holes in the Pintle

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 2REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 05 Fitting. It is recommended to either : . grind the diameter of the reamer pilot to 0.0010 in. less than the post cold expanded hole size, . or, manufacture a reamer to step ream the titanium material to a dimension of 0.002 ins. less than the pilot size of the final reamer. This condition has not been found on all aircraft. − There have been reports of breakage of the preliminary start reamers (e.g. PSR−XXXX−XXXX−LC or RC) during use. The cause of this is considered to be the tendency to apply a high bending moment on the reamer when using right angle drill motors. It is advised to only use right angle motors where access restrictions make it necessary. Also standard drill speed and feed requirements for the given hole size and material type should be observed.

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 3REVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 05

Figure 1 Sheet 1

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 4

Cold Expansion ProcedureREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 05

Figure 2 Sheet 1

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 5 MHP−20−2−N−32/36 Mini Hand PullerREVISION No. : 03 − Feb 09/01 

# A319/A320/A321

SERVICE BULLETIN

APPENDIX 05

Figure 3 Sheet 1

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 6 Processing at Hole 87 With Mini Hand PullerREVISION No. : 03 − Feb 09/01 L7 

# A319/A320/A321

SERVICE BULLETIN REPORTING SHEET TITLE : WINGS − INNER REAR SPAR − INTRODUCTION OF INTERFERENCE FIT FASTENERS MODIFICATION No. : 24591J1322 24591J1323 24591J1345 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: Advance data . . . . . . . . . . . . . . . . . . . . . . YES/NO Or : Intermediate/Temporary revision . . . . . . . . . . . . YES/NO Important Information: This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus Industrie 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 Industrie shall automatically include them in the manual revisions. Refer to SIL 00−037 for detailed information. Please return this completed sheet to: AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn: AI/SE−D32 Technical Data and Documentation Services Fax: (+33) 5 61 93 28 06 or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 1 of 1REVISION No. : 03 − Feb 09/01 L7 

# A319/A320/A321

SERVICE BULLETIN QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) − Quality rating of this SB 4 3 2 1 − Quality rating of the Accomplishment Instructions 4 3 2 1 − Quality rating of the Illustrations 4 3 2 1 − Is this SB easy to understand ? Y / N
If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit Content X Preparation X Reason X List of Materials X Mod/Inspection X Manpower Operator Supplied 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 INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX Attn : AI/SE−T1 Service Bulletins Management FAX : (33) 5 61 93 42 51 or via your Resident Customer Support Office.

DATE : Dec 22/96 SERVICE BULLETIN No. : A320−57−1089

Printed in France © Airbus Industrie 1996, All rights reserved Page : 1 of 1