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 3
REVISION 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 : 2
REVISION 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 : 3
EVALUATION 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 4
REVISION 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 : 2
REVISION 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 : 3
REVISION 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 : 4
REVISION 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 122
REVISION 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 : 2
REVISION 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 : 3
REVISION 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 : 4
 1.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 : 5
 1.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 : 6
REVISION 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 : 7
REVISION 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 Chart 
REVISION 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 Chart 
REVISION 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 Chart 
REVISION 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 : 11
 2.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 : 12
 

Kit 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 : 13
REVISION 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 : 14
REVISION 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 : 15
REVISION 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 : 16
REVISION 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 : 17
REVISION 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 : 18
REVISION 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 : 19
REVISION 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 : 20
REVISION 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 : 21
REVISION 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 : 22
REVISION 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 : 23
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 : 24

This Page Intentionally Left Blank
 3.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 : 25
 3.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 : 26
 3.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 : 27
 3.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 : 28
 3.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 : 29
 3.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 : 30
 3.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 : 31
 3.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 : 32
 

HOLE 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 : 33
HOLE 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 : 34
 3.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 : 35
 3.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 : 36
 3.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 : 37
 

HOLE 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 : 38
 HOLE 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 : 40
 3.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 : 41
 3.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 : 42
 3.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 : 43
 3.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 : 44
 

HOLE 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 : 45
HOLE 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 : 46
HOLE 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 : 47
 

HOLE 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 : 48
KIT 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 : 49
KIT 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 : 50
KIT 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 : 51
KIT 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 : 52
KIT 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 : 53
Kit 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 : 54
 

Kit 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 : 55
Kit 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 : 56
 

Kit 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 : 57
Kit 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 : 58
Kit 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 : 59
Kit 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 : 60
Kit 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 : 61
Kit 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 : 62
Kit 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 : 63
 

Kit 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 : 64
Kit 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 : 65
 

Kit 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 : 66
Kit 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 : 67
Kit 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 : 68
Kit 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 : 69
Kit 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 : 70
Kit 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 : 71
Kit 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 : 72
 

Kit 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 : 73
Kit 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 : 74
 

Kit 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 : 75
Kit 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 : 76
Kit 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 : 77
Kit 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 : 78
Kit 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 : 79
Kit 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 : 80
 

Kit 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 : 81
Kit 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 : 82
Kit 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 : 83
Kit 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 : 84
Kit 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 : 85
Kit 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 : 86
Kit 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 : 87
Kit 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 : 88
Kit 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 : 89
Kit 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 : 90
Kit 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 : 91
 

Kit 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 : 92
Kit 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 : 93
 

Kit 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 : 94
Kit 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 : 95
Kit 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 : 96
Kit 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 : 97
Kit 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 : 98
Kit 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 : 99
 

Kit 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 : 100
Kit 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 : 101
Kit 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 : 102
Kit 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 : 103
 

MATERIAL

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 : 104
 3.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 : 105
 3.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 : 106
 3.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 : 107
 3.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 : 108
REVISION 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 pipes
REVISION 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 Pipes
REVISION 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 Pipes
REVISION 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 Pipes
REVISION 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 Pipes
REVISION 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 Pipes
REVISION 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 Assembly
REVISION 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 Series
REVISION 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 Series
REVISION 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 Series
REVISION 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 Series
REVISION 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 Series
REVISION 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 Series
REVISION 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 Spotfaces
 1. 

 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 8
 3.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 : 2
 4.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 : 3
 6. 

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 : 4
REVISION 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 Form
REVISION 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 Form
REVISION 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 RH
REVISION 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 RH
 MECH 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 10
 MECH 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 : 2
 MECH 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 : 3
 MECH 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 : 4
 MECH 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 : 5
 

MECH 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 : 6
 

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)

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 : 7
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)

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 : 8
 

 

MECH 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 : 9
 

 

MECH 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 : 10
 

 

PLANNING 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 33
 

PLANNING 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 : 2
 

PLANNING 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 : 3
 

PLANNING 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 : 4
 

 

PLANNING 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 : 5
 

PLANNING 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 : 6
 

PLANNING 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 : 7
 

PLANNING 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 : 8
 

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

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 : 9
 

 

PLANNING 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 : 10
 

PLANNING 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 : 11
 

PLANNING 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 : 12
 

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

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 : 13
 

 

PLANNING 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 : 14
 

PLANNING 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 : 15
 

PLANNING 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 : 16
 

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

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 : 17
 

PLANNING 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 : 18
 

 

PLANNING 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 : 19
 

PLANNING 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 : 20
 

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

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 : 21
 

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

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 : 22
 

 

PLANNING 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 : 23
 

PLANNING 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 : 24
 

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

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 : 25
 

PLANNING 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 : 26
 

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

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 : 27
 

PLANNING 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 : 28
 

 

PLANNING 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 : 29
 

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

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 : 30
 

PLANNING 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 : 31
 

PLANNING 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 : 32
PLANNING 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 : 33
 

 

For 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 6
 

 

 

Part 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 : 2
 

 

 

Part 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 : 3
 

 

 

Where 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 : 4
 

 

Where 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 : 5
 

Where 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 : 6
 1. 

 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 6
 2.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 : 2
REVISION 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 : 3
REVISION 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 Procedure
REVISION 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 Puller
REVISION 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 Puller
REVISION 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 1
REVISION 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