5 DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

MANDATORY MANDATORY MAND

ATA SYSTEM : 57

TITLE : WINGS - CENTER WING - INSPECTION OF CENTER WING BOX LOWER 

HOLES.

MODIFICATION No. : None

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

ADDITIONAL WORK

No additional work is required by this revision for aircraft m

previous issue.

REASON

Revision No. 01 issued to inform the operators that this Servi

rendered Mandatory and issued to add Config. 02 with the new 

procedure to be used when the Service Bulletin is accomplishe

12,000 Flight Cycle (FC) and 24,000 FC or between 20,000 Flig

and 40,000 FH.

CHANGES

SUMMARY :

— REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. Sentence updated. In the EVALUATION TABLE Recommended beco

DE-FUELLING/VENTILATING and NORMAL JACKING added. KIT PRIC

— MANPOWER

. Config. 02 added.

— APPENDICES

. Appendix 2 concerning the Inspection report added.

PLANNING INFORMATION :

— EFFECTIVITY

. Para. 1.A. NOTES and Config. 02 added.
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— COMPLIANCE

. Para. 1.E.(1) Recommended becomes Mandatory.

— Accomplishment Timescale

. Para. 1.E.(2) Sentence updated.

— APPROVAL

. Para. 1.F. Sentence updated.

— MANPOWER

. Para. 1.G. Config. 02 added.

— REFERENCES

. Para. 1.J. Reference to AMM 28-00-00 and AMM 28-10-00 add

to ESPM 20-55-00 added. Refer to NTM 51-10-01 added. Refe

51-43-00 added. Appendix 2 added.

MATERIAL INFORMATION :

— MATERIAL - PRICE AND AVAILABILITY

. Para. 2.A. Sentence updated.

— INDUSTRIAL SUPPORT

. Para. 2.B. Sentence updated.

— LIST OF COMPONENTS

. Para. 2.C. Kit 571120A01R05 : Quantity becomes 60 for the 

NSA5479BK6-14 becomes NSA5479VHK6-14 for the item 157, NSA

becomes NSA5479VHK6-15 for the item 159, NSA5479BK6-17 be

NSA5479VHK6-17 for the item 164. Kit 571120A02R01 added.

— TOOLING - PRICE AND AVAILABILITY

. Para. 2.F. Reference to NTM 51-10-01 added.

ACCOMPLISHMENT INSTRUCTIONS :

— GENERAL

2
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— INSPECTION

. Para. 3.B. (1)(a)8 concerning the removal of the rib pad 

3.B(1)(e) concerning the close-up for the inspection modi

3.B.(1)7a Item 132 NSA5479BV5-13X becomes Item 139 and NOT

para. 3.B.(1)7c NOTE modified. Para. 3.B.(2) added for th

— REPAIR

. Para. 3.C. (1) updated and para. 3(C)(2) added for the Co

— ILLUSTRATIONS

. Figure 8, Sheet 5 item 132 becomes 139.

. Figure 9, Sheet 9 NSA5479BK6-14 becomes NSA5479VHK6-14 fo

item 157. Figure 9, Sheet 10 NSA5479BK6-15 becomes NSA547

the screw item 159 and NSA5479BK6-17 becomes NSA5479VHK6-

screw item 164. Figure 9, Sheet 11 NSA5479BK6-15 becomes 

for the screw item 159.

. Figure 11, Sheet 1 modified.

. Figure 12, Sheets 1 thru 5 added.

. Figure 13, Sheets 1 thru 12 added.

. Figure 14, Sheet 1 added.

APPENDIX 2 :

— Appendix 2 added for the Config. 02.

NOTE : Lay-out changes due to computerization of this revisio

identified.

FILING INSTRUCTIONS

This Service Bulletin has been generated electronically and is 

complete document. Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service B

HISTORY OF PREVIOUS REVISIONS

No previous revisions.

3
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

4
5 DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

This summary is for information only

and is not approved for modification of the aircraf

MANDATORY MANDATORY MAND

ATA SYSTEM : 57

TITLE : WINGS - CENTER WING - INSPECTION OF CENTER WING BOX LOWER 

HOLES.

MODIFICATION No. : None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During removal of one Center Wing Box (CWB) lower aft panel on a 

section, it was noted :

— Excessive PR sealant in between the lower panel and the rib pad

— Small metal chips between the panel and rib pads.

The investigations revealed that the installation of rib pads on 

not been correctly ensured due to poor clamping during drilling 

slave pin).

The deviation has been identified on both FWD and aft lower panel

Y +- 765 and Y +- 1292.

After fatigue analysis only A321 would require a further action a

— If accomplished before 12,000 Flight Cycle (FC) or 20,000 Fligh

which occurs first, this Service Bulletin requests :

. to remove the rib pads one by one;

. to perform a detailed visual inspection of the holes area :

If fastener holes are not damaged : reinstall with new nomina

If fastener holes are damaged : oversize to R1 and install R1 

. to reinstall the rib pads.

— If accomplished Between 12,000 FC and 24,000 FC or 20,000 FH an

which occurs first, this Service Bulletin requests :
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Accomplishment of Service Bulletin No. A320-57-1120 at revision N

the inspection requirements of this Service Bulletin.

EFFECTIVITY

This Service Bulletin is applicable to these operators :

AAR AFR CSC JKK TAP

CONCURRENT REQUIREMENTS

None

REFERENCES/REPERCUSSIONS

TFU : None

OEB : None

AOT : None

SIL : None

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : No

OTHERS : None

NATURE OF THE WORK

AIRCRAFT : YES

EQUIPMENT : NO

HARD : NO

EVALUATION TABLE

COMPLIANCE Mandatory CANCELS INSPECTION 

POTENTIAL AD Yes A/C OPERATION AFFEC

RELIABILITY AFFECTED No PAX COMFORT AFFECTE

COST SAVING No ETOPS AFFECTED 

STRUCTURAL LIFE EXTN Yes VENDOR SB INVOLVED 

DE-FUELLING/VENTILLATIN

G

Yes NORMAL JACKING 

KIT PRICE (USD) A01R05 92,530 KIT PRICE (USD) A02

2
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Config. 01 , repair with nominal fasteners

Config. 01 , replacement rib pads oversize fasteners

Config. 02 , repair with next nominal fasteners

Config. 02 , replacement rib pads oversize fasteners

MATERIAL INFORMATION

AIRCRAFT DATA

None

APPENDICES

Config. 01

Appendix 01 : Inspection report.

Config. 02

Appendix 02 : Inspection report.

Config. 01 thru Config. 02

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 1

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 1

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

3
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

4
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

5
5 DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

MANDATORY MANDATORY MAND

ATA SYSTEM : 57

TITLE : WINGS - CENTER WING - INSPECTION OF CENTER WING BOX LOWER 

HOLES.

MODIFICATION No. : None

This document contains AIRBUS PROPRIETARY INFORMATION and shall a

remain the property of AIRBUS; no intellectual property right or 

granted by AIRBUS in connection with any information contained in 

delivered on the express condition that said document and the inf

contained in it shall be treated as confidential, shall not be us

purpose other than that for which it is hereby delivered. It shal

disclosed in whole or in part to third parties and shall not be d

any manner (except for the purposes of performing the tasks descr

and provided that any recipient of such document shall comply wit

conditions herein), without AIRBUS' prior written consent.

1. PLANNING INFORMATION

A. EFFECTIVITY

(1) Models

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

(2) Aircraft

(a) Effectivity by MSN

This Service Bulletin is applicable to aircraft 

1293 1299 1307 1333 1356 1366

(b) Effectivity by Operator

The Operator/MSN relationship is provided for in

and is correct at the time of issue in accordan

information available to AIRBUS. Any future cha

from transfer of an aircraft from one operator t

not be reflected in this list unless the Service 

revised for another reason.
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(c) Effectivity by MSN and Kit/Configuration

The kits and configurations applicable to these 

at the end of this list:

1293 1299 1307 1333 1356 1366

NOTE : Config. 01 concerns the aircraft before 1

20,000 FH whichever occurs first.

NOTE : Config. 02 concerns the aircraft between 

24,000 FC or between 20,000 FH and 40,000

occurs first.

(3) Spares

None

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During removal of one Center Wing Box (CWB) lower aft 

build up section, it was noted :

— Excessive PR sealant in between the lower panel and 

— Small metal chips between the panel and rib pads.

The investigations revealed that the installation o

the panel had not been correctly ensured due to poo

during drilling (use of a new slave pin).

JKK 1333 1366

TAP 1307

KIT No. QTY PER A/C CONFIGURATION

571120A01R05 1 01

571120A02R01 1 02

2
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— If accomplished before 12,000 Flight Cycle (FC) or 

Hours (FH) which occurs first, this Service Bullet

. to remove the rib pads one by one;

. to perform a detailed visual inspection of the ho

If fastener holes are not damaged : reinstall wit

fasteners;

If fastener holes are damaged : oversize to R1 a

fasteners.

. to reinstall the rib pads.

— If accomplished Between 12,000 FC and 24,000 FC or 

40,000 FH which occurs first, this Service Bulleti

. to remove the rib pads one by one;

. to perform a special detailed visual inspection o

area and contact AIRBUS if crack is detected.

(3) Advantages

Accomplishment of this Service Bulletin will allow d

damages and correcting all the deviations.

Accomplishment of Service Bulletin No. A320-57-1120 a

00 cancels the inspection requirements of this Servi

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

(1) Config. 01

(a) Inspection

1 Do a visual inspection

Refer to Figure 11

3
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

1 Do a special detailed visual inspection

Refer to Figure 15

(b) Repair

1 Replace the installation of the rib pads wit

fasteners and oversize fasteners.

E. COMPLIANCE

(1) Classification

Mandatory

(2) Accomplishment Timescale

Accomplishment of this Inspection Service Bulletin m

performed before 24,000 FC or 40,000 FH since the fi

the aircraft, whichever occurs first.

Accomplishment of this Service Bulletin is expected t

mandatory by the issue of an Airworthiness Directive 

by the European Aviation Safety Agency (EASA). It is 

that the AD will confirm the (thresholds and/or inte

date) given above but reference should be made to th

confirmation of the mandated accomplishment timescal

F. APPROVAL

Approved under EASA Design Organisation Approval No. EASA 

If an aircraft listed in the effectivity has a modificatio

embodied that is not of AIRBUS origin, and which affects 

this Service Bulletin, the operator is responsible for ob

approval by its airworthiness authority for any adaptatio

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are 

direct labor cost to do the work. These estimates assume 

will be done by experienced personnel, and may need to be 

upwards to suit operator's circumstances. The estimates do 

the time to prepare, plan or inspect the work. Manufactur

4
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Config. 01 , repair with nominal fasteners

necessary)

Removal of the pipes,

support diffuser

Removal the LH, RH jet

pumps FR41, FR42

Removal the strut, support

FR41 and FR42

Removal 22QJ, 17QT and

18QT

Removal air conditioning

FR34 and FR36

Removal fittings vapor

seal

Visual inspection holes of

rib pads

Installation fittings

vapor seal

Installation air between

FR34 and FR36

Installation 22QJ, 17QT

and 18QT

Installation strut/support

FR41 and FR42

Installation RH, RH jet

pumps FR41, FR42

Installation pipes and

support diffuser

Installation ACT (if

removed)

Test 

Close-up 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Replacement rib pads

nominal fasteners

5
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Config. 02 , repair with next nominal fasteners

Config. 02 , replacement rib pads oversize fasteners

H. WEIGHT AND BALANCE

Not changed

I. ELECTRICAL LOAD DATA

Not changed

J. REFERENCES

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Installation next nominal

fasteners

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Installation oversize

fasteners

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Aircraft Maintenance Manual (AMM) : 07-11-00 12-34-24 

20-21-15 20-28-00 

21-21-42 21-21-43 

21-51-11 21-52-42 

21-61-15 21-61-16 

21-63-15 21-63-16 

27-84-45 27-84-53 

28-10-00 28-11-00 

28-13-42 28-25-00 

28-25-52 28-26-41 

28-28-00 28-28-31 

28-42-15 28-42-44 

28-46-15 29-12-21 

29-12-51 29-24-51 

33-48-12 52-10-00 

53-35-11 53-35-13 

6
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Appendix 1

Appendix 2

Appendix 3

Standards Manual (SM)

K. PUBLICATIONS AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not applicable

7
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

This Page Intentionally Left Blank

8
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

of this Service Bulletin. The address is :

AIRBUS Spares Support and Services

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

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

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

(2) Price and Availability

Kit 571120A01R05

Cost : 92,530.00US Dollars

Availability : 120 calendar days from receipt of orde

The Kit availability given above is the standard lead 

date of your purchase order. If you require the Kit(

time, please include a retrofit planning schedule wit

so that we can try to comply with your requirements.

Kit 571120A02R01

Cost : 139,210.00US Dollars

Availability : 120 calendar days from receipt of orde

The Kit availability given above is the standard lead 

date of your purchase order. If you require the Kit(

time, please include a retrofit planning schedule wit

so that we can try to comply with your requirements.

B. INDUSTRY SUPPORT INFORMATION

For those aircraft with findings further to inspection as 

Service Bulletin, AIRBUS will provide the kits at no char

credit the manhours for the correction at the operator's a

warranty labor rate upon receipt of a warranty claim.

AIRBUS will credit the manhours indicated in this Service 

inspections that are performed on aircraft in warranty at 

such inspection. Credit will be at the Operator's agreed 

warranty labor rate upon receipt of a warranty claim.

9
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

8 NSA50503 48 Nut

12 NAS1726-4E 12 Nut

39 NAS1726-3E 3 Nut

41 NSA5479BV5-15 20 Screw

47 MS21073L3 2 Nut

53 NSA5479BV5-14 37 Screw

54 NSA5479BV5-18 6 Screw

55 ASNA2536-5 171 Nut

65 MS21043-06 2 Nut

66 MS21043-08 2 Nut

67 NSA5474-3K7 1 Nut

83 MS24665-153 76 Pin

84 NSA5060-5 64 Nut

85 NSA5060-6 12 Nut

94 MS21042-3 4 Nut

96 NSA5479BV4-11 32 Screw

97 ASNA2536-4 60 Nut

99 NSA5479BV4-10 41 Screw

101 NSA5479BV4-12 6 Screw

105 NSA5479BV5-13 36 Screw

108 ASNA2536-7 6 Nut

109 NSA5479BV7-30 2 Screw

110 ASNA2536-6 72 Nut

111 NSA5479BV6-25 4 Screw

112 NSA5479BV5-21 2 Screw

113 NSA5479BV7-29 4 Screw

114 NSA5479BV6-23 8 Screw

115 NSA5479BV5-20 4 Screw

116 ASNA2528-4 268 Nut

123 ASNA2528-5 82 Nut

152 NSA5479BV4-7 76 Screw

153 NSA5479BV5-12 46 Screw

154 NSA5479BV4-13 4 Screw

155 NSA5479BV4-8 82 Screw

156 NSA5479BV4-9 80 Screw

157 NSA5479VHK6-14 16 Screw

158 NSA5479BV5-9 80 Screw

159 NSA5479VHK6-15 20 Screw

10
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 571120A02R01

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. 

5 NSA5050-4 18 Nut

8 NSA5050-3 46 Nut

12 NAS1726-4E 12 Nut

39 NAS1726-3E 3 Nut

47 MS21073L3 2 Nut

53 NSA5479BV5-14 3 Screw

55 ASNA2536-5 45 Nut

65 MS21043-06 2 Nut

66 MS21043-08 2 Nut

67 NSA5474-3K7 1 Nut

83 MS24665-153 76 Pin

84 NSA5060-5 64 Nut

85 NSA5060-6 12 Nut

94 MS21042-3 4 Nut

96 NSA5479BV4-11 10 Screw

97 ASNA2536-4 18 Nut

99 NSA5479BV4-10 8 Screw

101 NSA5479BV4-12 2 Screw

105 NSA5479BV5-13 5 Screw

108 ASNA2536-7 58 Nut

109 NSA5479BV7-30 2 Screw

110 ASNA2536-6 114 Nut

111 NSA5479BV6-25 4 Screw

112 NSA5479BV5-21 2 Screw

113 NSA5479BV7-29 5 Screw

114 NSA5479BV6-23 10 Screw

115 NSA5479BV5-20 5 Screw

123 ASNA2528-5 268 Nut

129 NSA5050-5 54 Nut

11
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

153 NSA5479BV5-12 6 Screw

158 NSA5479BV5-9 80 Screw

165 NSA5479BV6-14 14 Screw

166 NSA5479BV6-13 17 Screw

167 NSA5479BV5-7 76 Screw

168 NSA5479BV6-12 46 Screw

169 NSA5479BV5-8 82 Screw

170 NSA5479BK7-14 16 Screw

171 NSA5479BV6-9 64 Screw

172 NSA5479BV6-15 20 Screw

173 NSA5479BK7-17 8 Screw

174 NSA5479BK7-15 20 Screw

175 NSA5479BV6-18 2 Screw

176 NSA5479BV7-22 8 Screw

177 NSA5479BV6-19 4 Screw

178 NSA5479BV5-10 30 Screw

179 NSA5479BV5-11 22 Screw

180 ASNA2528-6 66 Nut

181 NSA5479BV5-9Y 16 Screw

182 NSA5479BV5-17Y 12 Screw

183 NSA5479BV5-14Y 12 Screw

184 NSA5479BV4-14Y 12 Screw

185 NSA5479BV5-13Y 20 Screw

186 NSA5479BV5-18Y 4 Screw

187 NSA5479BV6-22Y 8 Screw

188 NSA5368-516D 48 Washer

189 NSA5368-416D 12 Washer

190 NSA5368-616D 8 Washer

12
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(2) Components

Config. 01

q

Pure Mineral Vaseline and

Petrolatum

04-012 As required

Synthe. Hydrocarbon Grease

High Pressure

04-022 As required

Electrical Bonding Coating

(Blue Color)

07-001 As required

Fuel Tank Sealant

Polysulfide

09-002 As required

Sealant Polysulfide 09-002C As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Corrosion Inhibiting fillet

Consistency

09-016B As required

Adhesion Promoter For

Polysulfide Sealant

09-028A As required

Solvent 11-026 As required

Chemical Conversion Coating

Yellow Aluminum

13-002 As required

Polyurethane Primer 16-001C As required

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. 

5 NSA5050-4 42 Nut 

128 NSA5330-4 268 Nut 

129 NSA5050-5 158 Nut 

130 NSA5050-6 60 Nut 

131 NSA5330-5 82 Nut 

132 NSA5479BV4-11X 22 Screw 

133 NSA5479BV4-7X 76 Screw 

134 NSA5479BV5-12X 46 Screw 

135 NSA5479BV4-8X 82 Screw 

136 NSA5479BV4-9X 80 Screw 

137 NSA5479VHK6-14X 16 Screw 

138 NSA5479BV5-9X 80 Screw 

139 NSA5479BV5-13X 35 Screw 

140 NSA5479BV4-12X 4 Screw 

13
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE (01) The operator must get it from :

HONEYWELL HARDWARE PRODUCT GROUP

LADEMANNBOGEN 128

HAMBOURG D22339

GERMANY

E. PARTS TO BE RE—IDENTIFIED BY THE OPERATOR

None

F. TOOLING — PRICE AND AVAILABILITY

To accomplish this Service Bulletin it is necessary to us

listed in AMM 07-11-00 Page block 1, SRM 51-51-00 and NTM 

procedure A, Part 6.

G. SPECIAL TOOLS

None

146 NSA5479BV4-13X 4 Screw 

147 NSA5479BV5-14X 34 Screw 

148 NSA5479BV5-17X 12 Screw 

149 NSA5479BV4-14X 12 Screw 

150 NSA5479BV6-22X 16 Screw 

151 NSA5479BV5-19X 4 Screw 

14
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO 

ELECTRICAL WIRING IN A SATISFACTORY CONDITI

(ELECTRICALLY AND MECHANICALLY SERVICEABLE)

MAINTENANCE WORK, REPAIRS OR MODIFICATIONS

ELECTRICAL WIRING, COMPONENTS AND THE WORK 

AS POSSIBLE, TO DO THIS :

— PUT PROTECTION, SUCH AS PLASTIC SHEETING

AS NECESSARY ON WIRING AND COMPONENTS.

— REGULARLY REMOVE ALL SHAVINGS, UNWANTED M

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF 

AND DAMAGE TO THE ELECTRICAL WIRING INSTAL

IF THERE IS CONTAMINATION REFER TO ESPM 20

(a) Config. 01 thru Config. 02

1 Electrically ground the aircraft (Refer to AM

Page block 401).

2 Put the access platforms in position.

3 Open the passenger/crew door 831, (Refer to A

Page block 201).

4 Open the Main Landing Gear doors (Refer to AM

Page block 201).

5 Open the Cargo door 825 (Refer to AMM 52-30-0

201).

6 Open, safety and tag circuit breakers (Refer 

28-42-47 Page block 401), (Refer to AMM 28-42

401), (Refer to AMM 28-42-15 Page block 401), 

33-48-12 Page block 401), (Refer to AMM 27-84

401), (Refer to AMM 27-84-53 Page block 401), 

21-61-51 Page block 401), (Refer to AMM 21-51

401), (Refer to AMM 21-61-16 Page block 401), 

29-24-51 Page block 401) and (Refer to AMM 28

block 401),

7 Defuel the fuel the center tank (Refer to AMM 

block 301).

15
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

11 Remove the refuel diffuser assembly of the ce

(Refer to AMM 28-25-42 Page block 401).

12 Remove the vapor seal (Refer to AMM 28-13-42 

401).

13 Remove the center tank fuel lever sensor FIN 

(Refer to AMM 28-46-15 Page block 401).

14 Remove the center tank probes FIN 37QT and F

to AMM 28-42-15 Page block 401).

15 Remove the Jet Pump Fuel Control Valves FIN 

154QM (Refer to AMM 28-26-43 Page block 401)

16 Remove the Jet Pumps center tank FIN 157QM a

(Refer to AMM 28-26-41 Page block 401).

17 Remove the cabin recirculation fans FIN 14HG 

(Refer to AMM 21-21-51 Page block 401).

18 Remove the check valves FIN 4020HM and FIN 40

AMM 21-21-42 Page block 401).

19 Remove the water injectors FIN 20HM and FIN 2

AMM 21-52-42 Page block 401).

20 Remove the mixer unit tempeature sensors FIN 

25HK (Refer to AMM 21-63-16 Page block 401).

21 Remove the mixer unit (Refer to AMM 21-21-43 

401).

22 Remove the duct temperature sensors FIN 15HK

FIN 17HK (Refer to AMM 21-63-15 Page block 40

23 Remove the recirculation filters FIN 4012HM a

(Refer to AMM 21-21-41 Page block 401).

24 Remove the BLUE electric pump FIN 2075GJ (Ref

29-12-51 Page block 401).

25 Remove the BLUE power accumulator FIN 2070GM 

29-12-42 Page block 401).

16
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

401), (if installed).

29 Remove the refuel valve canister FIN 164QM (

28-25-52 Page block 401), (if installed).

30 Remove the ACT transfer valve FIN 165QM (Refe

28-28-33 Page block 401), (if installed).

31 Remove the partitions FIN 151BW, FIN 151AW a

from the aft cargo compartment at FR47 (Refe

25-55-11 Page block 401).

32 Remove the panels FIN 191EB, FIN 191LB, FIN 

191JB, FIN 191GB, FIN 147BB, FIN 147AB, FIN 

191CB, FIN 191DB, FIN 191HB, FIN 191MB, FIN 

192LB, FIN 148DB, FIN 192EB, FIN 192FB, FIN 

195AB and FIN 195BB (Refer to AMM 53-35-11 Pa

and (Refer to AMM 53-35-13 Page block 401).

(2) Standard Practices

(a) Config. 01 thru Config. 02

1 For inspection and repair :

a For the specification of the material numb

No.), refer to the CML.

b Put all the retained hardware in identifie

and attach the bags to the related units.

c Use a non-metallic spatula to remove the 

clean the areas with Solvent (Mat No. 11-0

d Clean the surfaces to be sealed with Solve

11-026) .

e Remove and install the fasteners (Refer to 

51-42-11).

f Drill and deburr the holes (Refer to SRM 

g Oversize the holes (Refer to SRM 51-43-00)

h Protect the cut out areas or the parts wit

Conversion Coating Yellow Aluminum (Mat No

17
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

j Torque the standard threaded fasteners (Re

20-21-11 Page block 201).

k Torque the electrical component fasteners 

20-21-15 Page block 201).

l Apply the sealant (Refer to SRM 51-24-00)

m For alternative and substitute fasteners, 

51-43-12).

n Apply the Corrosion Inhibiting fillet Con

No. 09-016B) to the interfaces of the str

the parts.

o Protect the areas to prevent damage to the 

structure not removed.

2 For repair only :

a Apply the Adhesion Promoter For Polysulfid

No. 09-028A) to the interfaces of the str

parts.

b Apply the Corrosion Inhibiting fillet Con

No. 09-016) on all fasteners.

c Apply the Corrosion Inhibiting fillet Con

No. 09-016B) to the interfaces of the str

the parts.

B. INSPECTION

(1) Config. 01

(a) Access for the inspection.

Refer to Figure 1 thru 9

1 Remove the installation of the ACT transfer a

installed).

Refer to Figure 1

a Remove :

Refer to Figure 1 , Sheets 1 and 2

18
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

with :

b Remove :

Refer to Figure 1 , Sheets 1 thru 3

c Remove :

Refer to Figure 1 , Sheets 1 thru 4

2 Nut Item (7

2 Nut Item (8

6 Screw Item (9

6 Washer Item (1

1 Sleeve Item (1

6 Nut Item (1

1 Pipe assy Item (1

1 Machined tee Item (1

1 non return valve

176QM

Item (1

2 Screw Item (1

2 Nut Item (8

2 Bolt Item (1

2 Washer Item (1

2 Nut Item (1

1 Elbow Item (1

1 Pipe Item (1

2 Screw Item (3

3 Nut Item (8

2 Screw Item (1

4 Washer Item (1

4 Nut Item (1

2 Screw Item (9

1 Screw Item (1

1 Pipe Item (2

1 Elbow Item (2

1 Sleeve Item (2

1 Nut Item (2

1 Circlip Item (2

1 Pipe Item (2

1 Elbow Item (2

1 Pipe Item (2

19
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

e Remove :

Refer to Figure 1 , Sheets 1 thru 6

with :

attached with :

2 Remove the pipes and support of the diffuser 

center wing box at FR42.

Refer to Figure 2

a Remove :

attached with :

b Remove :

attached with :

p

1 Pipe Item (3

1 Elbow Item (3

1 Pipe Item (3

2 Screw Item (4

2 Nut Item (5

1 Screw Item (3

1 Washer Item (2

4 Screw Item (2

4 Nut Item (8

1 Elbow Item (3

1 Pipe assy Item (3

4 Screw Item (3

4 Washer Item (3

1 Screw Item (3

1 Nut Item (3

1 Support Item (4

2 Screw Item (4

20
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— Remove :

Refer to Figure 3

attached with :

b Remove the RH jet pump circuit between FR4

Refer to Figure 3

— Remove :

Refer to Figure 3

attached with :

4 Remove the oblique strut and its support betw

FR42.

Refer to Figure 4

a Remove :

Refer to Figure 4

1 Pipe assy Item (4

1 LH Elbow Item (4

1 Pipe assy Item (4

1 Adaptor assy Item (4

2 Screw Item (3

1 Nut Item (3

1 Nut Item (4

1 Pipe assy Item (4

1 RH Elbow Item (4

1 Pipe assy Item (4

1 Adaptor assy Item (4

2 Screw Item (3

1 Nut Item (3

1 Nut Item (4

1 oblique strut Item (4

21
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Refer to Figure 4

attached with :

5 Remove the sensor FIN 22QJ, the harness FIN 

sensor FIN 22QJ and the harnesses FIN 17QT a

from the ultracomp. FIN 50QT.

Refer to Figure 5

a Remove the sensor FIN 22QJ :

Refer to Figure 5 , Sheets 1 thru 3

attached with :

b Remove the harness FIN 18QT from the senso

Refer to Figure 5 , Sheets 1 thru 3

attached with :

c Attach the cable FIN 18QT on the box uppe

1 Support Item (5

1 Support Item (5

1 Support Item (5

2 Screw Item (5

1 Screw Item (5

3 Nut Item (5

1 Sensor 22QJ Item (5

2 Screw Item (5

2 Nut Item (8

1 Harness 18QT Item (5

2 Screw Item (5

2 Washer Item (2

5 Collar Item (6

4 Screw Item (1

4 Nut Item (8

1 Collar Item (6

4 Collar Item (6

22
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

attached with :

6 Remove the air conditioning system between FR

the cargo compartment.

Refer to Figure 7

a Remove :

b Remove :

attached with :

7 Remove the fittings of the vapor seal betwee

FR40.

Refer to Figure 8

a Make a mark on the fitting of the vapor se

removal to show the location.

1 Harness 17QT Item (6

1 Harness 18QT Item (5

2 Nut Item (6

2 Nut Item (6

1 Nut Item (6

2 Washer Item (7

2 Washer Item (6

1 Washer Item (6

4 Screw Item (6

4 Nut Item (8

3 Collar Item (6

1 Collar Item (6

4 Collar Item (6

1 Duct assy Item (8

1 Duct assy Item (8

1 Duct assy Item (9

1 Duct assy Item (9

4 Bolt Item (9

4 Washer Item (9

4 Nut Item (9

23
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

attached with :

c Remove :

NOTE : During the removal of the Screws of 

of vapor seal, make sure that there 

interferences with another part.

attached with :

d Remove :

NOTE : During the removal of the screws of 

of vapor seal, make sure that there 

interferences with another part.

attached with :

e Remove :

NOTE : During the removal of the screws of 

of vapor seal, make sure that there 

interferences with another part.

attached with :

3 Screw Item (9

1 Screw Item (5

3 Nut Item (9

1 Nut Item (5

1 Fitting Item (9

4 Screw Item (9

4 Nut Item (9

1 Fitting Item (1

2 Screw Item (9

2 Screw Item (1

4 Nut Item (9

1 Fitting Item (1

2 Screw Item (9

2 Screw Item (5

24
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

attached with :

g Remove :

NOTE : During the removal of the screws of 

of vapor seal, make sure that there 

interferences with another part.

attached with :

8 Remove the struts and the rib pads.

Refer to Figure 6

Refer to Figure 9

NOTE (01) To have sufficient stiffness of the 

box, every rib pad should be remove

installed before the removal of ano

You must remove/install the rib pad

associated struts in this sequence 

Y - 1292

Y + 254

Y - 765

Y + 765

Y - 254

1 Fitting Item (1

4 Screw Item (9

4 Nut Item (9

1 Fitting Item (1

1 Screw Item (1

1 Screw Item (9

2 Screw Item (9

3 Nut Item (9

1 Nut Item (5

25
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Refer to Figure 6

Refer to Figure 9 , Sheets 1 thru 3 and 

— Remove the struts :

Refer to Figure 6

attached with :

NOTE : Remove the strut Item (79) only i

attached with :

— Remove the rib pad :

Refer to Figure 9 , Sheets 1 thru 3 an

attached with :

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

3 Nut Item (8

3 Screw Item (5

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

12 Cotter Pin Item (8

12 Nut Item (8

12 Washer Item (8

4 Axle Item (1

6 Axle Item (1

2 Axle Item (1

1 rib pad Item (1

17 Nut Item (5

6 Nut Item (9

1 Nut Item (1

10 Nut Item (1

26
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

tu 3 ad 9 tu 

b Remove the struts and the rib pad at Y + 2

Refer to Figure 6

Refer to Figure 9 , Sheets 1 , 2 , 6 and 

— Remove the struts :

Refer to Figure 6

attached with :

NOTE : Remove the strut Item (82) only i

attached with :

— Remove the rib pad :

Refer to Figure 9 , Sheets 1 , 2 , 6 an

3 Bonding Lead Item (7

1 Bonding Lead Item (7

4 Nut Item (8

4 Screw Item (5

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (8

1 Strut Item (8

1 Strut Item (8

14 Cotter Pin Item (8

8 Nut Item (8

6 Nut Item (8

8 Washer Item (8

6 Washer Item (8

4 Axle Item (1

4 Axle Item (1

2 Axle Item (1

2 Axle Item (1

2 Axle Item (1

27
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

and with the screws (Discard) as per Fig

1 , 2 , 6 and 9 thru 11 .

c Remove the struts and the rib pad at Y - 

Refer to Figure 6

Refer to Figure 9 , Sheets 1 , 2 , 4 and 

— Remove the struts :

Refer to Figure 6

attached with :

NOTE : Remove the strut Item (79) only i

attached with :

16 Nut Item (1

42 Nut Item (1

1 Screw Item (1

2 Screw Item (1

1 Screw Item (1

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

3 Nut Item (8

3 Screw Item (5

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

12 Cotter Pin Item (8

12 Nut Item (8

12 Washer Item (8

4 Axle Item (1

6 Axle Item (1

2 Axle Item (1

28
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

and with the screws (Discard) as per Fig

1 , 2 , 4 and 9 thru 11 .

d Remove the struts and the rib pad at Y + 

Refer to Figure 6

Refer to Figure 9 , Sheets 1 , 2 , 7 and 

— Remove the struts :

Refer to Figure 6

attached with :

NOTE : Remove the strut Item (79) only i

attached with :

15 Nut Item (5

6 Nut Item (9

1 Nut Item (1

10 Nut Item (1

46 Nut Item (1

22 Nut Item (1

1 Screw Item (1

2 Screw Item (1

1 Screw Item (1

1 Plate Item (1

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

3 Nut Item (8

3 Screw Item (5

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

12 Cotter Pin Item (8

12 Nut Item (8

29
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

g, , , 

attached with :

and with the screws (Discard) as per Fig

1 , 2 , 7 and 9 thru 11 .

e Remove the struts and the rib pad at Y - 2

Refer to Figure 6

Refer to Figure 9 , Sheets 1 , 2 , 5 and 

— Remove the struts :

Refer to Figure 6

attached with :

NOTE : Remove the strut Item (82) only i

1 Rib Pad Item (1

15 Nut Item (5

6 Nut Item (9

1 Nut Item (1

10 Nut Item (1

46 Nut Item (1

22 Nut Item (1

1 Screw Item (1

2 Screw Item (1

1 Screw Item (1

3 Bonding Lead Item (7

1 Bonding Lead Item (7

4 Nut Item (8

4 Screw Item (5

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (8

1 Strut Item (8

1 Strut Item (8

30
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— Remove the rib pad :

Refer to Figure 9 , Sheets 1 , 2 , 5 an

attached with :

and with the screws (Discard) as per Fig

1 , 2 , 5 and 9 thru 11 .

f Remove the struts and the rib pad at Y + 

Refer to Figure 6

Refer to Figure 9 , Sheets 1 , 2 and 8 t

— Remove the struts :

Refer to Figure 6

attached with :

(

4 Axle Item (1

2 Axle Item (1

2 Axle Item (1

2 Axle Item (1

1 Rib Pad Item (1

45 Nut Item (5

10 Nut Item (9

1 Nut Item (1

16 Nut Item (1

42 Nut Item (1

1 Screw Item (1

2 Screw Item (1

1 Screw Item (1

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

3 Nut Item (8

3 Screw Item (5

1 Strut Item (7

1 Strut Item (7

31
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— Remove the rib pad :

Refer to Figure 9 , Sheets1,2,8 th

attached with :

and with the screws (Discard) as per Fig

1,2,8 thru 11 .

(b) For the inspection area, refer to Figure 10 .

(c) Do a visual inspection, refer to Figure 11 .

(d) For the inspection report, refer to Appendix 01 

(e) Close-up for the inspection with nominal fastene

Refer to Figure 1 thru 8

NOTE (01) To have sufficient stiffness of the ce

every rib pad should be removed and in

the removal of another one.

You must remove/install the rib pads a

associated struts in this sequence :

12 Cotter Pin Item (8

12 Nut Item (8

12 Washer Item (8

4 Axle Item (1

6 Axle Item (1

2 Axle Item (1

1 Rib Pad Item (1

19 Nut Item (5

6 Nut Item (9

1 Nut Item (1

10 Nut Item (1

46 Nut Item (1

18 Nut Item (1

1 Screw Item (1

2 Screw Item (1

1 Screw Item (1

32
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Y - 254

Y + 1292

NOTE (02) For the replacement of the nominal fas

installation of the rib pads, refer to 

571120A01R05 .

1 Install the rib pad and the struts at Y - 129

Refer to Figure 6

refer to Figure 9 , Sheets 1 thru 3 and 9 

a Install the rib pad :

refer to Figure 9 , Sheets 1 thru 3 and 

attach with :

NOTE : Item (106) was retained at removal

1 Rib Pad Item (1

19 Nut ASNA2536-5 Item 55

6 Nut ASNA2536-4 Item 97

1 Nut ASNA2536-7 Item 10

10 Nut ASNA2536-6 Item 11

46 Nut ASNA2528-4 Item 11

20 Nut ASNA2528-5 Item 12

4 Screw NSA5479BV4-11 Item 96

14 Screw NSA5479BV4-7 Item 15

8 Screw NSA5479BV5-12 Item 15

12 Screw NSA5479BV4-8 Item 15

14 Screw NSA5479BV4-9 Item 15

4 Screw NSA5479VHK6-14 Item 15

20 Screw NSA5479BV5-9 Item 15

2 Screw NSA5479BV5-13 Item 10

4 Screw NSA5479VHK6-15 Item 15

6 Screw NSA5479BV4-10 Item 99

6 Screw NSA5479BV5-14 Item 53

2 Screw NSA5479BV5-17 Item 16

2 Screw NSA5479BV4-14 Item 16

1 Screw NSA5479BV7-29 Item 11

2 Screw NSA5479BV6-23 Item 11

1 Screw NSA5479BV5-20 Item 11

33
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Install the Strut Item (79) only if 

attach with :

NOTE (01) Install axles Items (117), (118) 

with Synthe. Hydrocarbon Grease 

(Mat No. 04-022) .

NOTE (02) Wet assembly under all the heads 

with Fuel Tank Sealant Polysulfi

09-001) .

NOTE (03) The end of cotter pin Item 83 mu

carrefully folded against Items 

NOTE (04) Protect the head of axles Items 

and (122) with Polyurethane Prim

16-001C) .

NOTE : Items (74), (75), (76), (77), (78)

(117), (118) and (122) were retaine

attach with :

NOTE : Items (57), (71), (72) and (73) we

removal.

2 Install the rib pad and the struts at Y + 254

(

4 Axle Item (1

6 Axle Item (1

2 Axle Item (1

12 Cotter Pin MS24665-153 Item 83

12 Nut NSA5060-5 Item 84

12 Washer Item (8

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

3 Nut NSA5050-3 Item 8

3 Screw Item (5

34
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

attach with :

NOTE : Item (125) was retained at removal

b Install the struts :

Refer to Figure 6

1 Rib Pad Item (1

47 Nut ASNA2536-5 Item 55

10 Nut ASNA2536-4 Item 97

1 Nut ASNA2536-7 Item 10

16 Nut ASNA2536-6 Item 11

42 Nut ASNA2528-4 Item 11

4 Screw NSA5479BV4-11 Item 96

12 Screw NSA5479BV4-7 Item 15

8 Screw NSA5479BV5-12 Item 15

14 Screw NSA5479BV4-8 Item 15

13 Screw NSA5479BV4-9 Item 15

16 Screw NSA5479BV5-13 Item 10

2 Screw NSA5479BV4-12 Item 10

10 Screw NSA5479BV5-15 Item 41

4 Screw NSA5479VHK6-17 Item 16

2 Screw NSA5479VHK6-15 Item 15

2 Screw NSA5479BV5-18 Item 54

3 Screw NSA5479BV4-10 Item 99

2 Screw NSA5479BV4-13 Item 15

6 Screw NSA5479BV5-14 Item 53

2 Screw NSA5479BV5-17 Item 16

2 Screw NSA5479BV4-14 Item 16

8 Screw NSA5479BV6-22 Item 16

2 Screw NSA5479BV5-19 Item 16

1 Screw NSA5479BV7-30 Item 10

2 Screw NSA5479BV6-25 Item 11

1 Screw NSA5479BV5-21 Item 11

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (8

1 Strut Item (8

1 Strut Item (8

35
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE (01) Install axles Items (117), (118)

and (121) with Synthe. Hydrocarb

Pressure (Mat No. 04-022) .

NOTE (02) Wet assembly under all the heads 

with Fuel Tank Sealant Polysulfi

09-001) .

NOTE (03) The end of cotter pin Item 83 mu

carrefully folded against Items 

or 85.

NOTE (04) Protect the head of axles Items 

(119), (120) and (121) with Poly

Primer (Mat No. 16-001C) .

NOTE : Items (74), (75), (76), (77), (80)

(86), (87), (117), (118), (119), (1

were retained at removal.

attach with :

NOTE : Items (57), (71) and (72) were reta

removal.

3 Install the rib pad and the struts at Y - 76

Refer to Figure 6

Refer to Figure 9 , Sheets 1 , 2 , 4 and 9 

2 Axle Item (1

14 Cotter Pin MS24665-153 Item 83

8 Nut NSA5060-5 Item 84

6 Nut NSA5060-6 Item 85

8 Washer Item (8

6 Washer Item (8

3 Bonding Lead Item (7

1 Bonding Lead Item (7

4 Nut NSA5050-3 Item 8

4 Screw Item (5

36
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Items (106) and (124) were retained 

b Install the struts :

Refer to Figure 6

NOTE : Install the strut Item (79) only if 

attach with :

1 Plate Item (1

16 Nut ASNA2536-5 Item 55

6 Nut ASNA2536-4 Item 97

1 Nut ASNA2536-7 Item 10

10 Nut ASNA2536-6 Item 11

22 Nut ASNA2528-5 Item 12

46 Nut ASNA2528-4 Item 11

4 Screw NSA5479BV4-11 Item 96

13 Screw NSA5479BV4-7 Item 15

9 Screw NSA5479BV5-12 Item 15

14 Screw NSA5479BV4-8 Item 15

13 Screw NSA5479BV4-9 Item 15

4 Screw NSA5479VHK6-14 Item 15

20 Screw NSA5479BV5-9 Item 15

4 Screw NSA5479VHK6-15 Item 15

6 Screw NSA5479BV4-10 Item 99

6 Screw NSA5479BV5-14 Item 53

2 Screw NSA5479BV5-17 Item 16

2 Screw NSA5479BV4-14 Item 16

1 Screw NSA5479BV7-29 Item 11

2 Screw NSA5479BV6-23 Item 11

1 Screw NSA5479BV5-20 Item 11

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

4 Axle Item (1

6 Axle Item (1

2 Axle Item (1

37
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

yy

(Mat No. 04-022) .

NOTE (02) Wet assembly under all the heads 

with Fuel Tank Sealant Polysulfi

09-001) .

NOTE (03) The end of cotter pin Item 83 mu

carrefully folded against Items 

NOTE (04) Protect the head of axles Items 

and (122) with Polyurethane Prim

16-001C) .

NOTE : Items (74), (75), (76), (77), (78)

(117), (118) and (122) were retaine

attach with :

NOTE : Items (57), (71), (72) and (73) we

removal.

4 Install the rib pad and the struts at Y + 76

Refer to Figure 6

Refer to Figure 9 , Sheets 1 , 2 , 7 and 9 

a Install the rib pad :

Refer to Figure 9 , Sheets 1 , 2 , 7 and 

attach with :

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

3 Nut NSA5050-3 Item 8

3 Screw Item (5

1 Rib Pad Item (1

16 Nut ASNA2536-5 Item 55

6 Nut ASNA2536-4 Item 97

1 Nut ASNA2536-7 Item 10

38
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Item (106) was retained at removal

b Install the struts :

Refer to Figure 6

NOTE : Install the Strut Item (79) only if 

attach with :

NOTE (01) Install axles Items (117), (118) 

with Synthe. Hydrocarbon Grease 

(Mat No. 04-022) .

NOTE (02) Wet assembly under all the heads 

with Fuel Tank Sealant Polysulfi

09-001) .

13 Screw NSA5479BV49 Item 15

4 Screw NSA5479VHK6-14 Item 15

22 Screw NSA5479BV5-9 Item 15

4 Screw NSA5479VHK6-15 Item 15

6 Screw NSA5479BV4-10 Item 99

6 Screw NSA5479BV5-14 Item 53

2 Screw NSA5479BV5-17 Item 16

2 Screw NSA5479BV4-14 Item 16

1 Screw NSA5479BV7-29 Item 11

2 Screw NSA5479BV6-23 Item 11

1 Screw NSA5479BV5-20 Item 11

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

4 Axle Item (1

6 Axle Item (1

2 Axle Item (1

12 Cotter Pin MS24665-153 Item 83

12 Nut NSA5060-5 Item 84

12 Washer Item (8

39
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(117), (118) and (122) were retaine

attach with :

NOTE : Items (57), (71), (72) and (73) we

removal.

5 Install the rib pad and the struts at Y - 254

Refer to Figure 6

Refer to Figure 9 , Sheets 1 , 2 , 5 and 9 

a Install the rib pad :

Refer to Figure 9 , Sheets 1 , 2 , 5 and 

attach with :

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

3 Nut NSA5050-3 Item 8

3 Screw Item (5

1 Rib Pad Item (1

47 Nut ASNA2536-5 Item 55

8 Nut ASNA2536-4 Item 97

1 Nut ASNA2536-7 Item 10

16 Nut ASNA2536-6 Item 11

42 Nut ASNA2528-4 Item 11

2 Screw NSA5479BV4-11 Item 96

12 Screw NSA5479BV4-7 Item 15

8 Screw NSA5479BV5-12 Item 15

14 Screw NSA5479BV4-8 Item 15

13 Screw NSA5479BV4-9 Item 15

15 Screw NSA5479BV5-13 Item 10

2 Screw NSA5479BV4-12 Item 10

10 Screw NSA5479BV5-15 Item 41

4 Screw NSA5479VHK6-17 Item 16

2 Screw NSA5479VHK6-15 Item 15

2 Screw NSA5479BV5-18 Item 54

6 Screw NSA5479BV4-10 Item 99

40
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Item (125) was retained at removal

b Install the struts :

Refer to Figure 6

NOTE : Install the strut Item (82) only if 

attach with :

NOTE (01) Install axles Items (117), (118)

and (121) with Synthe. Hydrocarb

Pressure (Mat No. 04-022) .

NOTE (02) Wet assembly under all the heads 

with Fuel Tank Sealant Polysulfi

09-001) .

NOTE (03) The end of cotter pin Item 83 mu

carrefully folded against Items 

or 85.

2 Screw NSA5479BV625 Item 11

1 Screw NSA5479BV5-21 Item 11

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (8

1 Strut Item (8

1 Strut Item (8

4 Axle Item (1

4 Axle Item (1

2 Axle Item (1

2 Axle Item (1

2 Axle Item (1

14 Cotter Pin MS24665-153 Item 83

8 Nut NSA5060-5 Item 84

6 Nut NSA5060-6 Item 85

8 Washer Item (8

6 Washer Item (8

41
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

attach with :

NOTE : Items (57), (71) and (72) were reta

removal.

6 Install the rib pad and the struts at Y + 129

Refer to Figure 6

Refer to Figure 9 , Sheets1,2,8 thru 1

a Install the rib pad :

attach with :

3 Bonding Lead Item (7

1 Bonding Lead Item (7

4 Nut NSA5050-3 Item 8

4 Screw Item (5

1 Rib Pad Item (1

19 Nut ASNA2536-5 Item 55

6 Nut ASNA2536-4 Item 97

1 Nut ASNA2536-7 Item 10

10 Nut ASNA2536-6 Item 11

46 Nut ASNA2528-4 Item 11

18 Nut ASNA2528-5 Item 12

4 Screw NSA5479BV4-11 Item 96

12 Screw NSA5479BV4-7 Item 15

6 Screw NSA5479BV5-12 Item 15

14 Screw NSA5479BV4-8 Item 15

14 Screw NSA5479BV4-9 Item 15

4 Screw NSA5479VHK6-14 Item 15

18 Screw NSA5479BV5-9 Item 15

2 Screw NSA5479BV5-13 Item 10

4 Screw NSA5479VHK6-15 Item 15

2 Screw NSA5479BV5-18 Item 54

6 Screw NSA5479BV4-10 Item 99

6 Screw NSA5479BV5-14 Item 53

2 Screw NSA5479BV5-17 Item 16

2 Screw NSA5479BV4-14 Item 16

1 Screw NSA5479BV7-29 Item 11

42
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Install the strut Item (79) only if 

attach with :

NOTE (01) Install axles Items (117), (118) 

with Synthe. Hydrocarbon Grease 

(Mat No. 04-022) .

NOTE (02) Wet assembly under all the heads 

with Fuel Tank Sealant Polysulfi

09-001) .

NOTE (03) The end of cotter pin Item 83 mu

carrefully folded against Items 

NOTE (04) Protect the head of axles Items 

and (122) with Polyurethane Prim

16-001C) .

NOTE : Items (74), (75), (76), (77), (78)

(117), (118) and (122) were retaine

attach with :

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

12 Cotter Pin MS24665-153 Item 83

12 Nut NSA5060-5 Item 84

12 Washer Item (8

4 Axle Item (1

6 Axle Item (1

2 Axle Item (1

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

3 Nut NSA5050-3 Item 8

43
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Refer to Figure 8

NOTE : Install the fittings of vapor seal onl

removal/installation of the rib pads a

associated struts (refer to ACCOMPLISH

INSTRUCTIONS paragraph. C (1)).

a Install :

attach with :

or if oversize :

or if oversize :

NOTE : Item (104) was retained at removal

b Install :

attach with :

NOTE : Item (103) was retained at removal

c Install :

attach with :

1 Fitting Item (1

1 Screw NSA5479BV5-13 Item 10

1 screw NSA5479BV5-13X Item 13

1 Screw NSA5479BV4-11 Item 96

2 Screw NSA5479BV4-10 Item 99

3 Nut ASNA2536-4 Item 97

1 Nut ASNA2536-5 Item 55

1 Nut NSA5050-5 Item 12

1 Fitting Item (1

4 Screw NSA5479BV4-11 Item 96

4 Nut ASNA2536-4 Item 97

1 Fitting Item (1

44
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

or if oversize :

NOTE : Item (102) was retained at removal

d Install :

attach with :

or if oversize :

or if oversize :

NOTE : Item (100) was retained at removal

e Install :

attach with :

NOTE : Item (98) was retained at removal.

f Install :

attach with :

2 Nut ASNA2536-5 Item 55

2 Nut NSA5050-5 Item 12

1 Fitting Item (1

2 Screw NSA5479BV4-10 Item 99

2 Screw NSA5479BV4-12 Item 10

2 Screw NSA5479BV4-12X Item 14

2 Nut ASNA2536-4 Item 97

2 Nut NSA5050-4 Item 5

1 Fitting Item (9

4 Screw NSA5479BV4-10 Item 99

4 Nut ASNA2536-4 Item 97

1 Fitting Item (9

45
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

or if oversize :

NOTE : Item (95) was retained at removal.

8 Install the air conditioning system between 

in the cargo compartment.

Refer to Figure 7

a Install :

attach with :

NOTE : Items (90), (91), (92) and (93) we

removal.

b Install :

NOTE : Items (88) and (89) were retainer a

9 Install the sensor FIN 22QJ, the harness FIN 

sensor FIN 22QJ and the harnesses FIN 17QT a

the ultracomp. FIN 50QT.

Refer to Figure 5

a Install the harnesses FIN 17QT and FIN 18Q

ultracomp. FIN 50QT.

Refer to Figure 5

1 Nut ASNA2536-5 Item 55

1 Nut NSA5050-5 Item 12

1 Duct assy Item (9

1 Duct assy Item (9

4 Bolt Item (9

4 Washer Item (9

4 Nut MS21042-3 Item 94

1 Duct assy Item (8

1 Duct assy Item (8

46
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Items (58), (60), (61), (62), (63

(69) and (70) were retained at re

b Install the sensor FIN 22QJ and the harne

the sensor FIN 22QJ.

— Install :

attach with :

NOTE : Items (2), (17), (58), (59), (60)

(62) were retained at removal.

— Install :

attach with :

2 Washer Item (6

1 Washer Item (6

2 Nut MS21043-06 Item 65

2 Nut MS21043-08 Item 66

1 Nut NSA5474-3K7 Item 67

4 Nut NSA5050-3 Item 8

3 Collar Item (6

1 Collar Item (6

4 Collar Item (6

4 Screw Item (6

1 Harness 18QT Item (5

5 Collar Item (6

1 Collar Item (6

4 Collar Item (6

2 Washer Item (2

2 Screw Item (5

4 Screw Item (1

4 Nut NSA5050-3 Item 8

1 Sensor 22QJ Item (5

2 Screw Item (5

47
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Refer to Figure 4

a Install :

Attach with :

NOTE : Install the supports Item (50), wit

and (52) with Fuel Tank Sealant Pol

No. 09-002) .

NOTE : Items (50), (51), (52), (53) and (

retained at removal.

b Install :

attach with :

NOTE : Items (10), (48) and (49) were reta

removal.

11 Install the LH and RH jet pumps circuit betwe

FR42.

Refer to Figure 3

a Install the RH jet pump circuit between F

Refer to Figure 3

Install :

1 Support Item (5

1 Support Item (5

1 Support Item (5

2 Screw Item (5

1 Screw Item (5

3 Nut ASNA2536-5 Item 55

1 Strut Oblique Item (4

2 Screw Item (4

2 Washer Item (1

2 Nut NSA5050-4 Item 5

48
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Items (38), (42), (44), (45) and (4

retained at removal.

b Install the LH jet pump circuit between F

Refer to Figure 3

Install :

attach with :

NOTE : Items (38), (42), (43), (45) and (4

retained at removal.

12 Install the pipes and support of the diffuse

center wing box at FR42.

Refer to Figure 2

a Install :

attach with :

NOTE : Items (40) and (41) were retained a

b Install on the diffuser

2 Screw Item (3

1 Nut NAS1726-3E Item 39

1 Nut MS21073L3 Item 47

1 Pipe assy Item (4

1 RH Elbow Item (4

1 Pipe assy Item (4

1 Adaptor assy Item (4

2 Screw Item (3

1 Nut NAS1726-3E Item 39

1 Nut MS21073L3 Item 47

1 Support Item (4

2 Screw Item (4

49
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Items (34), (35), (36), (37) and (

retained at removal.

13 Install the ACT transfer at FR42 (if removed)

Refer to Figure 1

a Install :

Refer to Figure 1

with :

attach with :

NOTE : Items (2), (3), (4), (28), (31), (

were retained at removal.

b Install :

Refer to Figure 1 , Sheets 1 thru 5

1 Screw Item (3

1 Nut NAS1726-3E Item 39

1 Pipe Item (3

1 Elbow Item (3

1 Pipe Item (3

2 Screw Item (4

2 Nut NSA5050-4 Item 5

1 Screw Item (3

1 Washer Item (2

4 Screw Item (2

8 Nut NSA5050-3 Item 8

1 Pipe Item (2

1 Pipe Item (3

3 Screw Item (1

3 Nut NSA5050-3 Item 8

50
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Items (3), (9), (10), (16), (17), 

(22), (23), (24), (25), (26) and (2

retained at removal.

d Install :

Refer to Figure 1 , Sheets 1 thru 3

NOTE : Items (10), (16), (17), (18) and (1

retained at removal.

e Install :

Refer to Figure 1 , Sheets 1 thru 2

1 Elbow Item (2

1 Pipe Item (2

1 Sleeve Item (2

1 Circlip Item (2

1 Nut Item (2

1 Elbow Item (2

1 Pipe Item (2

2 Screw Item (9

4 Washer Item (1

4 Nut NAS1726-4E Item 12

2 Screw Item (1

1 Screw Item (1

3 Nut NSA5050-3 Item 8

3 Screw Item (3

1 Elbow Item (1

1 Pipe Item (1

2 Bolt Item (1

2 Washer Item (1

2 Nut NAS1726-4E Item 12

2 Screw Item (1

2 Nut NSA5050-3 Item 8

51
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Items (1), (2), (3), (4), (6), (7)

(11), (13), (14) and (15) were reta

removal.

(2) Config. 02

(a) Access for the inspection.

Refer to Figure 1 thru 7 , 12 and 13

1 Remove the installation of the ACT transfer a

installed).

Refer to Figure 1

a Remove :

Refer to Figure 1 , Sheets 1 and 2

1 Valve non return

176QM

Item (1

6 Screw Item (9

6 Washer Item (1

6 Nut NAS1726-4E Item 12

2 Nut NSA5050-3 Item 8

1 Pipe assy Item (1

4 Screw Item (1

5 Washer Item (2

3 Screw Item (3

2 Screw Item (4

2 Nut NSA5050-4 Item 5

4 Screw Item (1

5 Washer Item (2

3 Screw Item (3

2 Screw Item (4

2 Nut Item (5

2 Circlip Item (6

2 Nut Item (7

2 Nut Item (8

6 Screw Item (9

6 Washer Item (1

52
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

b Remove :

Refer to Figure 1 , Sheets 1 thru 3

c Remove :

Refer to Figure 1 , Sheets 1 thru 4

d Remove :

Refer to Figure 1 , Sheets 1 thru 5

e Remove :

176QM

(

2 Screw Item (1

2 Nut Item (8

2 Bolt Item (1

2 Washer Item (1

2 Nut Item (1

1 Elbow Item (1

1 Pipe Item (1

2 Screw Item (3

3 Nut Item (8

2 Screw Item (1

4 Washer Item (1

4 Nut Item (1

2 Screw Item (9

1 Screw Item (1

1 Pipe Item (2

1 Elbow Item (2

1 Sleeve Item (2

1 Nut Item (2

1 Circlip Item (2

1 Pipe Item (2

1 Elbow Item (2

1 Pipe Item (2

3 Screw Item (1

3 Nut Item (8

1 Pipe Item (2

1 Pipe Item (3

53
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

attached with :

2 Remove the pipes and support of the diffuser 

center wing box at FR42.

Refer to Figure 2

a Remove :

attached with :

b Remove :

attached with :

3 Remove the LH and RH jet pump circuits betwee

FR42.

Refer to Figure 3

a Remove the LH jet pump circuit between FR4

Refer to Figure 3

— Remove :

2 Screw Item (4

2 Nut Item (5

1 Screw Item (3

1 Washer Item (2

4 Screw Item (2

4 Nut Item (8

1 Elbow Item (3

1 Pipe assy Item (3

4 Screw Item (3

4 Washer Item (3

1 Screw Item (3

1 Nut Item (3

1 Support Item (4

2 Screw Item (4

54
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

b Remove the RH jet pump circuit between FR4

Refer to Figure 3

— Remove :

Refer to Figure 3

attached with :

4 Remove the strut oblique and its support betw

FR42.

Refer to Figure 4

a Remove :

Refer to Figure 4

attached with :

b Remove :

Refer to Figure 4

2 Screw Item (3

1 Nut Item (3

1 Nut Item (4

1 Pipe assy Item (4

1 RH Elbow Item (4

1 Pipe assy Item (4

1 Adaptor assy Item (4

2 Screw Item (3

1 Nut Item (3

1 Nut Item (4

1 Strut Oblique Item (4

2 Screw Item (4

2 Washer Item (1

2 Nut Item (5

55
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

5 Remove the sensor FIN 22QJ, the harness FIN 

sensor FIN 22QJ and the harnesses FIN 17QT a

from the ultracomp. FIN 50QT.

Refer to Figure 5

a Remove the sensor FIN 22QJ :

Refer to Figure 5 , Sheets 1 thru 3

attached with :

b Remove the harness FIN 18QT from the senso

Refer to Figure 5 , Sheets 1 thru 3

attached with :

c Attach the cable FIN 18QT on the box uppe

d Remove the harnesses FIN 17QT and FIN 18QT 

ultracomp. FIN 50QT.

Refer to Figure 5

— Remove :

Refer to Figure 5 , Sheet 4

1 Screw Item (5

3 Nut Item (5

1 Sensor 22QJ Item (5

2 Screw Item (5

2 Nut Item (8

1 Harness 18QT Item (5

2 Screw Item (5

2 Washer Item (2

5 Collar Item (6

4 Screw Item (1

4 Nut Item (8

1 Collar Item (6

4 Collar Item (6

56
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

6 Remove the air conditioning system between FR

the cargo compartment.

Refer to Figure 7

a Remove :

b Remove :

attached with :

7 Remove the fittings of the vapor seal betwee

FR40.

Refer to Figure 12

a Make a mark on the fitting of the vapor se

removal to show the location.

b Remove :

NOTE : During the removal of the screws of 

of vapor seal, make sure that there 

interferences with another part.

1 Nut Item (6

2 Washer Item (7

2 Washer Item (6

1 Washer Item (6

4 Screw Item (6

4 Nut Item (8

3 Collar Item (6

1 Collar Item (6

4 Collar Item (6

1 Duct assy Item (8

1 Duct assy Item (8

1 Duct assy Item (9

1 Duct assy Item (9

4 Bolt Item (9

4 Washer Item (9

4 Nut Item (9

1 Fitting Item (9

57
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : During the removal of the screws of 

of vapor seal, make sure that there 

interferences with another part.

attached with :

d Remove :

NOTE : During the removal of the screws of 

of vapor seal, make sure that there 

interferences with another part.

attached with :

e Remove :

NOTE : During the removal of the screws of 

of vapor seal, make sure that there 

interferences with another part.

attached with :

f Remove :

NOTE : During the removal of the screws of 

of vapor seal, make sure that there 

interferences with another part.

1 Fitting Item (9

4 Screw Item (9

4 Nut Item (9

1 Fitting Item (1

2 Screw Item (9

2 Screw Item (1

4 Nut Item (9

1 Fitting Item (1

2 Screw Item (9

2 Screw Item (5

2 Nut Item (9

2 Nut Item (5

58
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

g Remove :

NOTE : During the removal of the screws of 

of vapor seal, make sure that there 

interferences with another part.

attached with :

8 Remove the struts and the rib pads.

Refer to Figure 6

Refer to Figure 13

NOTE (01) To have sufficient stiffness of the 

box, every rib pad should be remove

installed before the removal of ano

You must remove/install the rib pad

associated struts in this sequence 

Y - 1292

Y + 254

Y - 765

Y + 765

Y - 254

Y + 1292

NOTE (02) You can remove a rib pad and start 

another one if you do not remove al

fasteners of the second rib pad.

a Remove the struts and the rib pad at Y - 

1 Fitting Item (1

1 Screw Item (1

1 Screw Item (9

2 Screw Item (9

3 Nut Item (9

1 Nut Item (5

59
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

attached with :

NOTE : Remove the strut Item (79) only i

attached with :

— Remove the rib pad :

Refer to Figure 13 , Sheets 1 thru 3 , 

attached with :

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

3 Nut Item (8

3 Screw Item (5

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

12 Cotter Pin Item (8

12 Nut Item (8

12 Washer Item (8

4 Axle Item (1

6 Axle Item (1

2 Axle Item (1

1 Rib Pad Item (1

17 Nut Item (5

6 Nut Item (9

1 Nut Item (1

10 Nut Item (1

46 Nut Item (1

20 Nut Item (1

1 Screw Item (1

2 Screw Item (1

1 Screw Item (1

60
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— Remove the struts :

Refer to Figure 6

attached with :

NOTE : Remove the strut Item (82) only i

attached with :

— Remove the rib pad :

Refer to Figure 13 , Sheets 1 , 2 , 6 a

attached with :

3 Bonding Lead Item (7

1 Bonding Lead Item (7

4 Nut Item (8

4 Screw Item (5

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (8

1 Strut Item (8

1 Strut Item (8

14 Cotter Pin Item (8

8 Nut Item (8

6 Nut Item (8

8 Washer Item (8

6 Washer Item (8

4 Axle Item (1

4 Axle Item (1

2 Axle Item (1

2 Axle Item (1

2 Axle Item (1

1 Rib Pad Item (1

45 Nut Item (5

10 Nut Item (9

61
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

and with the screws (Discard) as per Fig

Sheets 1 , 2 , 6 and 9 thru 12 .

c Remove the struts and the rib pad at Y - 

Refer to Figure 6

Refer to Figure 13 , Sheets 1 , 2 , 4 , 9 

— Remove the struts :

Refer to Figure 6

attached with :

NOTE : Remove the strut Item (79) only i

attached with :

— Remove the rib pad :

Refer to Figure 13 , Sheets 1 , 2 , 4 , 

attached with :

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

3 Nut Item (8

3 Screw Item (5

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

12 Cotter Pin Item (8

12 Nut Item (8

12 Washer Item (8

4 Axle Item (1

6 Axle Item (1

2 Axle Item (1

1 Rib Pad Item (1

62
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

and with the screws (Discard) as per Fig

Sheets 1 , 2 , 4 , 9 11 and 12 .

d Remove the struts and the rib pad at Y + 

Refer to Figure 6

Refer to Figure 13 , Sheets 1 , 2 , 7 , 9 

— Remove the struts :

Refer to Figure 6

attached with :

NOTE : Remove the strut Item (79) only i

attached with :

— Remove the rib pad :

1 Screw Item (1

2 Screw Item (1

1 Screw Item (1

1 Plate Item (1

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

3 Nut Item (8

3 Screw Item (5

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

12 Cotter Pin Item (8

12 Nut Item (8

12 Washer Item (8

4 Axle Item (1

6 Axle Item (1

2 Axle Item (1

63
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

and with the screws (Discard) as per Fig

Sheets 1 , 2 , 7 , 9 , 11 and 12 .

e Remove the struts and the rib pad at Y - 2

Refer to Figure 6

Refer to Figure 13 , Sheets 1 , 2 , 5 and 

— Remove the struts :

Refer to Figure 6

attached with :

NOTE : Remove the strut Item (82) only i

attached with :

1 Nut Item (1

10 Nut Item (1

46 Nut Item (1

22 Nut Item (1

1 Screw Item (1

2 Screw Item (1

1 Screw Item (1

3 Bonding Lead Item (7

1 Bonding Lead Item (7

4 Nut Item (8

4 Screw Item (5

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (8

1 Strut Item (8

1 Strut Item (8

14 Cotter Pin Item (8

8 Nut Item (8

6 Nut Item (8

8 Washer Item (8

6 Washer Item (8

64
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Refer to Figure 13 , Sheets 1 , 2 , 5 a

attached with :

and with the screws (Discard) as per Fig

Sheets 1 , 2 , 5 and 9 thru 12 .

f Remove the struts and the rib pad at Y + 

Refer to Figure 6

Refer to Figure 13 , Sheets 1 , 2 and 8 

— Remove the struts :

Refer to Figure 6

attached with :

NOTE : Remove the strut Item (79) only i

1 Rib Pad Item (1

45 Nut Item (5

10 Nut Item (9

1 Nut Item (1

16 Nut Item (1

42 Nut Item (1

1 Screw Item (1

2 Screw Item (1

1 Screw Item (1

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

3 Nut Item (8

3 Screw Item (5

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

65
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— Remove the rib pad :

Refer to Figure 13 , Sheets 1 , 2 and 8 

attached with :

and with the screws (Discard) as per Ref

13 , Sheets 1 , 2 and 8 thru 12 .

(b) For the inspection area, refer to Figure 10 .

(c) Do a special detailed visual inspection, refer t

1 Do the rotating probe inspection :

Refer to NTM 51-10-01

a If no crack is detected :

— Oversize the holes, refer to ACCOMPLISHM

INSTRUCTIONS paragraph C.(2) and refer t

Sheet 1 thru 5 and Figure 13 , Sheet 1 

b If crack is detected :

— Contact AIRBUS.

(d) For the inspection report, refer to Appendix 02 

(e) Install the fittings of vapor seal between FR36 

Refer to Figure 12

(

1 Rib Pad Item (1

19 Nut Item (5

6 Nut Item (9

1 Nut Item (1

10 Nut Item (1

46 Nut Item (1

18 Nut Item (1

1 Screw Item (1

2 Screw Item (1

1 Screw Item (1

66
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

attach with :

or if oversize :

or if oversize :

NOTE : Item (104) was retained at removal.

2 Install :

attach with :

NOTE : Item (103) was retained at removal.

3 Install :

attach with :

or if oversize :

or if oversize :

1 Screw NSA5479BV5-13 Item 10

1 Screw NSA5479BV5-13X Item 13

1 Screw NSA5479BV4-11 Item 96

2 Screw NSA5479BV4-10 Item 99

3 Nut ASNA2536-4 Item 97

1 Nut ASNA2536-5 Item 55

1 Nut NSA5050-5 Item 12

1 Fitting Item (1

4 Screw NSA5479BV4-11 Item 96

4 Nut ASNA2536-4 Item 97

1 Fitting Item (1

2 Screw NSA5479BV4-11 Item 96

2 Screw NSA5479BV5-14 Item 53

2 Screw NSA5479BV5-14X Item 14

2 Nut ASNA2536-4 Item 97

2 Nut ASNA2536-5 Item 55

67
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

attach with :

or if oversize :

or if oversize :

NOTE : Item (100) was retained at removal.

5 Install :

attach with :

NOTE : Item (98) was retained at removal.

6 Install :

attach with :

or if oversize :

or if oversize :

2 Screw NSA5479BV4-10 Item 99

2 Screw NSA5479BV4-12 Item 10

2 Screw NSA5479BV4-12X Item 14

2 Nut ASNA2536-4 Item 97

2 Nut NSA5050-5 Item 12

1 Fitting Item (9

4 Screw NSA5479BV4-10 Item 99

4 Nut ASNA2536-4 Item 97

1 Fitting Item (9

3 Screw NSA5479BV4-11 Item 96

1 Screw NSA5479BV5-14 Item 53

1 Screw NSA5479BV5-14X Item 14

3 Nut ASNA2536-4 Item 97

1 Nut ASNA2536-5 Item 55

1 Nut NSA5050-5 Item 12

68
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

attach with :

NOTE : Items (90), (91), (92) and (93) were 

removal.

2 Install :

NOTE : Items (88) and (89) were retainer at 

(g) Install the sensor FIN 22QJ, the harness FIN 18Q

sensor FIN 22QJ and the harnesses FIN 17QT and F

ultracomp. FIN 50QT.

Refer to Figure 5

1 Install the harnesses FIN 17QT and FIN 18QT o

ultracomp. FIN 50QT.

Refer to Figure 5

a Install :

attach with :

1 Duct assy Item (9

1 Duct assy Item (9

4 Bolt Item (9

4 Washer Item (9

4 Nut MS21042-3 Item 94

1 Duct assy Item (8

1 Duct assy Item (8

1 Harness 17QT Item (6

1 Harness 18QT Item (5

2 Washer Item (7

2 Washer Item (6

1 Washer Item (6

2 Nut MS21043-06 Item 65

2 Nut MS21043-08 Item 66

69
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Items (58), (60), (61), (62), (63)

(69) and (70) were retained at remo

2 Install the sensor FIN 22QJ and the harness F

sensor FIN 22QJ.

a Install :

attach with :

NOTE : Items (2), (17), (58), (59), (60), 

were retained at removal.

b Install :

attach with :

NOTE : Items (56) and (57) were retained a

(h) Install the oblique struts and its support betwe

FR42.

Refer to Figure 4

1 Install :

1 Harness 18QT Item (5

5 Collar Item (6

1 Collar Item (6

4 Collar Item (6

2 Washer Item (2

2 Screw Item (5

4 Screw Item (1

4 Nut NSA5050-3 Item 8

1 Sensor 22QJ Item (5

2 Screw Item (5

2 Nut NSA5050-3 Item 8

1 Support Item (5

1 Support Item (5

1 Support Item (5

70
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

pp, 

(52) with Fuel Tank Sealant Polysulfid

09-002) .

NOTE : Items (50), (51), (52), (53) and (54) 

at removal.

2 Install :

attach with :

NOTE : Items (10), (48) and (49) were retaine

(i) Install the LH and RH jet pumps circuit between 

Refer to Figure 3

1 Install the RH jet pump circuit between FR41 

Refer to Figure 3

attach with :

NOTE : Items (38), (42), (44), (45) and (46) 

at removal.

2 Install the LH jet pump circuit between FR41 

Refer to Figure 3

1 Strut Oblique Item (4

2 Screw Item (4

2 Washer Item (1

2 Nut NSA5050-4 Item 5

1 Pipe assy Item (4

1 RH Elbow Item (4

1 Pipe assy Item (4

1 Adaptor assy Item (4

2 Screw Item (3

1 Nut NAS1726-3E Item 39

1 Nut MS21073L3 Item 47

71
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Items (38), (42), (43), (45) and (46) 

at removal.

(j) Install the pipes and support of the diffuser in 

wing box at FR42.

Refer to Figure 2

1 Install :

attach with :

NOTE : Items (40) and (41) were retained at 

2 Install on the diffuser

attach with :

NOTE : Items (34), (35), (36), (37) and (38) 

at removal.

(k) Install the ACT transfer at FR42 (if removed).

Refer to Figure 1

1 Install :

Refer to Figure 1

2 Screw Item (3

1 Nut NAS1726-3E Item 39

1 Nut MS21073L3 Item 47

1 Support Item (4

2 Screw Item (4

1 Pipe assy Item (3

1 Elbow Item (3

4 Screw Item (3

4 Washer Item (3

1 Screw Item (3

1 Nut NAS1726-3E Item 39

72
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

attach with :

NOTE : Items (2), (3), (4), (28), (31), (32) 

retained at removal.

2 Install :

Refer to Figure 1 , Sheets 1 thru 5

NOTE : Items (17), (29) and (30) were retaine

3 Install :

Refer to Figure 1 , Sheets 1 thru 4

2 Screw Item (4

2 Nut NSA5050-4 Item 5

1 Screw Item (3

1 Washer Item (2

4 Screw Item (2

8 Nut NSA5050-3 Item 8

1 Pipe Item (2

1 Pipe Item (3

3 Screw Item (1

3 Nut NSA5050-3 Item 8

1 Pipe Item (2

1 Elbow Item (2

1 Pipe Item (2

1 Sleeve Item (2

1 Circlip Item (2

1 Nut Item (2

1 Elbow Item (2

1 Pipe Item (2

2 Screw Item (9

4 Washer Item (1

4 Nut NAS1726-4E Item 12

73
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Items (3), (9), (10), (16), (17), (20)

(23), (24), (25), (26) and (27) were 

removal.

4 Install :

Refer to Figure 1 , Sheets 1 thru 3

NOTE : Items (10), (16), (17), (18) and (19) 

at removal.

5 Install :

Refer to Figure 1 , Sheets 1 thru 2

with :

1 Elbow Item (1

1 Pipe Item (1

2 Bolt Item (1

2 Washer Item (1

2 Nut NAS1726-4E Item 12

2 Screw Item (1

2 Nut NSA5050-3 Item 8

1 Sleeve Item (1

2 Circlip Item (6

2 Nut Item (7

1 Machined tee Item (1

1 Valve non return

176QM

Item (1

6 Screw Item (9

6 Washer Item (1

6 Nut NAS1726-4E Item 12

2 Nut NSA5050-3 Item 8

1 Pipe assy Item (1

4 Screw Item (1

5 Washer Item (2

74
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

C. REPAIR

(1) Config. 01

(a) Replace the installation of the rib pads with ov

fasteners.

Refer to Figure 6

Refer to Figure 9

NOTE : To have sufficient stiffness of the cente

every rib pad should be removed and insta

the removal of another one.

You must remove/install the rib pads and 

struts in this sequence :

Y - 1292

Y + 254

Y - 765

Y + 765

Y - 254

Y + 1292

NOTE : For the replacement of the oversize faste

installation of the rib pads, parts are t

by :

HONEYWELL HARDWARE PRODUCT GROUP

LADEMANNBOGEN 128

HAMBOURG D22339

GERMANY

1 Install the rib pad and the struts at Y - 129

Refer to Figure 6

Refer to Figure 9 , Sheets 1 thru 3 and 12 

75
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Item (106) was retained at removal

b Install the struts :

Refer to Figure 6

NOTE : Install the strut Item (79) only if 

attach with :

1 Nut ASNA2536-5 Item 55

18 Nut NSA5050-5 Item 12

6 Nut NSA5050-4 Item 5

1 Nut ASNA2536-7 Item 10

2 Nut ASNA2536-6 Item 11

8 Nut NSA5050-6 Item 13

46 Nut NSA5330-4 Item 12

20 Nut NSA5330-5 Item 13

4 Screw NSA5479BV4-11X Item 13

14 Screw NSA5479BV4-7X Item 13

8 Screw NSA5479BV5-12X Item 13

12 Screw NSA5479BV4-8X Item 13

14 Screw NSA5479BV4-9X Item 13

4 Screw NSA5479VHK6-14X Item 13

20 Screw NSA5479BV5-9X Item 13

2 Screw NSA5479BV5-13X Item 13

4 Screw NSA5479VHK6-15X Item 14

6 Screw NSA5479BV4-10X Item 14

6 Screw NSA5479BV5-14X Item 14

2 Screw NSA5479BV5-17X Item 14

2 Screw NSA5479BV4-14X Item 14

1 Screw NSA5479BV7-29 Item 11

2 Screw NSA5479BV6-23 Item 11

1 Screw NSA5479BV5-20 Item 11

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

4 Axle Item (1

6 Axle Item (1

2 Axle Item (1

76
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

yy

(Mat No. 04-022) .

NOTE (02) Wet assembly under all the heads 

with Fuel Tank Sealant Polysulfi

09-001) .

NOTE (03) The end of cotter pin Item 83 mu

carrefully folded against Items 

NOTE (04) Protect the head of axles Items 

and (122) with Polyurethane Prim

16-001C) .

NOTE : Items (74), (75), (76), (77), (78)

(117), (118) and (122) were retaine

attach with :

NOTE : Items (57), (71), (72) and (73) we

removal.

2 Install the rib pad and the struts at Y + 254

Refer to Figure 6

Refer to Figure 9 , Sheets 1 , 2 , 6 and 12 

a Install the rib pad :

Refer to Figure 9 , Sheets 1 , 2 , 6 and 

attach with :

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Nut NSA5050-3 Item 8

3 Screw Item (5

1 Rib Pad Item (1

1 Nut ASNA2536-5 Item 55

46 Nut NSA5050-5 Item 12

10 Nut NSA5050-4 Item 5

77
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Item (125) was retained at removal

b Install the struts :

Refer to Figure 6

NOTE : Install the strut Item (82) only if 

attach with :

14 Screw NSA5479BV48X Item 13

13 Screw NSA5479BV4-9X Item 13

16 Screw NSA5479BV5-13X Item 13

2 Screw NSA5479BV4-12X Item 14

10 Screw NSA5479BV5-15X Item 14

4 Screw NSA5479VHK6-17X Item 14

2 Screw NSA5479VHK6-15X Item 14

2 Screw NSA5479BV5-18X Item 14

3 Screw NSA5479BV4-10X Item 14

2 Screw NSA5479BV4-13X Item 14

6 Screw NSA5479BV5-14X Item 14

2 Screw NSA5479BV5-17X Item 14

2 Screw NSA5479BV4-14X Item 14

8 Screw NSA5479BV6-22X Item 15

2 Screw NSA5479BV5-19X Item 15

1 Screw NSA5479BV7-30 Item 10

2 Screw NSA5479BV6-25 Item 11

1 Screw NSA5479BV5-21 Item 11

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (8

1 Strut Item (8

1 Strut Item (8

4 Axle Item (1

4 Axle Item (1

2 Axle Item (1

2 Axle Item (1

2 Axle Item (1

14 Cotter Pin MS24665-153 Item 83

78
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

() yy

Pressure (Mat No. 04-022) .

NOTE (02) Wet assembly under all the heads 

with Fuel Tank Sealant Polysulfi

09-001) .

NOTE (03) The end of cotter pin Item 83 mu

carrefully folded against Items 

or 85.

NOTE (04) Protect the head of axles Items 

(119), (120) and (121) with Poly

Primer (Mat No. 16-001C) .

NOTE : Items (74), (75), (76), (77), (80)

(86), (87), (117), (118), (119), (1

were retained at removal.

attach with :

NOTE : Items (57), (71), (72) and (73) we

removal.

3 Install the rib pad and the struts at Y - 76

Refer to Figure 6

Refer to Figure 9 , Sheets 1 , 2 , 4 and 12 

a Install the rib pad :

Refer to Figure 9 , Sheets 1 , 2 , 4 and 

attach with :

3 Bonding Lead Item (7

1 Bonding Lead Item (7

4 Nut NSA5050-3 Item 8

4 Screw Item (5

1 Rib Pad Item (1

1 Plate Item (1

79
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Items (106) and (124) were retained 

b Install the struts :

Refer to Figure 6

attach with :

NOTE : Items (57), (71), (72) and (73) we

removal.

4 Install the rib pad and the struts at Y + 76

Refer to Figure 6

Refer to Figure 9 , Sheets 1 , 2 , 7 and 12 

a Install the rib pad :

Refer to Figure 9 , Sheets 1 , 2 , 7 and 

46 Nut NSA53304 Item 12

22 Nut NSA5330-5 Item 13

4 Screw NSA5479BV4-11X Item 13

13 Screw NSA5479BV4-7X Item 13

9 Screw NSA5479BV5-12X Item 13

14 Screw NSA5479BV4-8X Item 13

13 Screw NSA5479BV4-9X Item 13

4 Screw NSA5479VHK6-14X Item 13

20 Screw NSA5479BV5-9X Item 13

4 Screw NSA5479VHK6-15X Item 14

6 Screw NSA5479BV4-10X Item 14

6 Screw NSA5479BV5-14X Item 14

2 Screw NSA5479BV5-17X Item 14

2 Screw NSA5479BV4-14X Item 14

1 Screw NSA5479BV7-29 Item 11

2 Screw NSA5479BV6-23 Item 11

1 Screw NSA5479BV5-20 Item 11

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

3 Nut NSA5050-3 Item 8

3 Screw Item (5

80
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Items (106) was retained at removal

b Install the struts :

Refer to Figure 6

NOTE : Install the strut Item (79) only if 

attach with :

1 Nut ASNA2536-7 Item 10

2 Nut ASNA2536-6 Item 11

8 Nut NSA5050-6 Item 13

46 Nut NSA5330-4 Item 12

22 Nut NSA5330-5 Item 13

4 Screw NSA5479BV4-11X Item 13

13 Screw NSA5479BV4-7X Item 13

7 Screw NSA5479BV5-12X Item 13

14 Screw NSA5479BV4-8X Item 13

13 Screw NSA5479BV4-9X Item 13

4 Screw NSA5479VHK6-14X Item 13

22 Screw NSA5479BV5-9X Item 13

4 Screw NSA5479VHK6-15X Item 14

6 Screw NSA5479BV4-10X Item 14

6 Screw NSA5479BV5-14X Item 14

2 Screw NSA5479BV5-17X Item 14

2 Screw NSA5479BV4-14X Item 14

1 Screw NSA5479BV7-29 Item 11

2 Screw NSA5479BV6-23 Item 11

1 Screw NSA5479BV5-20 Item 11

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

4 Axle Item (1

6 Axle Item (1

2 Axle Item (1

12 Cotter Pin MS24665-153 Item 83

12 Nut NSA5060-5 Item 84

81
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

with Fuel Tank Sealant Polysulfi

09-001) .

NOTE (03) The end of cotter pin Item 83 mu

carrefully folded against Items 

NOTE (04) Protect the head of axles Items 

and (122) with Polyurethane Prim

16-001C) .

NOTE : Items (74), (75), (76), (77), (78)

(117), (118) and (122) were retaine

attached with :

NOTE : Items (57), (71), (72) and (73) wer

removal.

5 Install the rib pad and the struts at Y - 254

Refer to Figure 6

Refer to Figure 9 , Sheets 1 , 2 , 5 and 12 

a Install the rib pad :

Refer to Figure 9 , Sheets 1 , 2 , 5 and 

attach with :

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

3 Nut Item (8

3 Screw Item (5

1 Rib Pad Item (1

1 Nut ASNA2536-5 Item 55

46 Nut NSA5050-5 Item 12

8 Nut NSA5050-4 Item 5

1 Nut ASNA2536-7 Item 10

2 Nut ASNA2536-6 Item 11

14 Nut NSA5050-6 Item 13

42 Nut NSA5330-4 Item 12

82
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Item (125) was retained at removal

b Install the struts :

Refer to Figure 6

NOTE : Install the strut Item (82) only if 

attach with :

10 Screw NSA5479BV515X Item 14

4 Screw NSA5479VHK6-17X Item 14

2 Screw NSA5479VHK6-15X Item 14

2 Screw NSA5479BV5-18X Item 14

6 Screw NSA5479BV4-10X Item 14

2 Screw NSA5479BV4-13X Item 14

4 Screw NSA5479BV5-14X Item 14

2 Screw NSA5479BV5-17X Item 14

2 Screw NSA5479BV4-14X Item 14

8 Screw NSA5479BV6-22X Item 15

2 Screw NSA5479BV5-19X Item 15

1 Screw NSA5479BV7-30 Item 10

2 Screw NSA5479BV6-25 Item 11

1 Screw NSA5479BV5-21 Item 11

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (8

1 Strut Item (8

1 Strut Item (8

4 Axle Item (1

4 Axle Item (1

2 Axle Item (1

2 Axle Item (1

2 Axle Item (1

14 Cotter Pin MS24665-153 Item 83

8 Nut NSA5060-5 Item 84

6 Nut NSA5060-6 Item 85

8 Washer Item (8

6 Washer Item (8

83
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE (03) The end of cotter pin Item 83 mu

carrefully folded against Items 

or 85.

NOTE (04) Protect the head of axles Items 

(119), (120) and (121) with Poly

Primer (Mat No. 16-001C) .

NOTE : Items (74), (75), (76), (77), (78)

(82), (86), (117), (118), (119), (1

were retained at removal.

attach with :

NOTE : Items (57), (71) and (72) were reta

removal.

6 Install the rib pad and the struts at Y + 129

Refer to Figure 6

Refer to Figure 9 , Sheets 1 , 2 , 8 and 12 

a Install the rib pad :

Refer to Figure 9 , Sheets 1 , 2 , 8 and 

attach with :

3 Bonding Lead Item (7

1 Bonding Lead Item (7

4 Nut NSA5050-3 Item 8

4 Screw Item (5

1 Rib Pad Item (1

1 Nut ASNA2536-5 Item 55

18 Nut NSA5050-5 Item 12

6 Nut NSA5050-4 Item 5

1 Nut ASNA2536-7 Item 10

2 Nut ASNA2536-6 Item 11

8 Nut NSA5050-6 Item 13

46 Nut NSA5330-4 Item 12

18 Nut NSA5030-5 Item 13

84
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Item (106) was retained at removal

b Install the strut :

Refer to Figure 6

NOTE : Install the strut Item (79) only if 

attach with :

NOTE (01) Install axles Items (117), (118) 

with Synthe. Hydrocarbon Grease 

(Mat No. 04-022) .

NOTE (02) Wet assembly under all the heads 

with Fuel Tank Sealant Polysulfi

09-001) .

2 Screw NSA5479BV513X Item 13

4 Screw NSA5479VHK6-15X Item 14

2 Screw NSA5479BV5-18X Item 14

6 Screw NSA5479BV4-10X Item 14

6 Screw NSA5479BV5-14X Item 14

2 Screw NSA5479BV5-17X Item 14

2 Screw NSA5479BV4-14X Item 14

1 Screw NSA5479BV7-29 Item 11

2 Screw NSA5479BV6-23 Item 11

1 Screw NSA5479BV5-20 Item 11

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

4 Axle Item (1

6 Axle Item (1

2 Axle Item (1

12 Cotter Pin MS24665-153 Item 83

12 Nut NSA5060-5 Item 84

12 Washer Item (8

85
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(117), (118) and (122) were retaine

attach with :

NOTE : Items (57), (71), (72) and (73) we

removal.

(2) Config. 02

(a) Replace the installation of the rib pads with ne

fasteners and oversize fasteners.

Refer to Figure 6

Refer to Figure 13

NOTE (01) To have sufficient stiffness of the ce

every rib pad should be removed and in

the removal of another one.

You must remove/install the rib pads a

associated struts in this sequence :

Y - 1292

Y + 254

Y - 765

Y + 765

Y - 254

Y + 1292

NOTE (02) For the replacement of the next nomina

and oversize fasteners for the install

rib pads, refer to the Kit 571120A02R0

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

3 Nut NSA5050-3 Item 8

3 Screw Item (5

86
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Refer to Figure 13 , Sheets 1 thru 3 , 9 

attach with :

NOTE : Item (106) was retained at removal

b Install the struts :

Refer to Figure 6

1 Rib Pad Item (1

1 Screw NSA5479BV7-29 Item 11

2 Screw NSA5479BV6-23 Item 11

1 Screw NSA5479BV5-20 Item 11

2 Screw NSA5479BV6-14 Item 16

14 Screw NSA5479BV5-7 Item 16

8 Screw NSA5479BV6-12 Item 16

12 Screw NSA5479BV5-8 Item 16

14 Screw NSA5479BV5-9 Item 15

4 Screw NSA5479BK7-14 Item 17

16 Screw NSA5479BV6-9 Item 17

2 Screw NSA5479BV6-13 Item 16

6 Screw NSA5479BV5-10 Item 17

4 Screw NSA5479BK7-15 Item 17

4 Screw NSA5479BV5-11 Item 17

4 Screw NSA5479BV5-9Y Item 18

2 Screw NSA5479BV5-17Y Item 18

2 Screw NSA5479BV5-14Y Item 18

2 Screw NSA5479BV4-14Y Item 18

2 Nut NSA5050-4 Item 5

5 Nut ASNA2536-5 Item 55

9 Nut ASNA2536-7 Item 10

14 Nut ASNA2536-6 Item 11

46 Nut ASNA2528-5 Item 12

4 Nut NSA5050-5 Item 12

4 Nut NSA5330-5 Item 13

16 Nut ASNA2528-6 Item 18

4 Washer NSA5368-516D Item 18

2 Washer NSA5368-416D Item 18

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

87
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE (01) Install axles Items (117), (118) 

with Synthe. Hydrocarbon Grease 

(Mat No. 04-022) .

NOTE (02) Wet assembly under all the heads 

with Fuel Tank Sealant Polysulfi

09-001) .

NOTE (03) The end of cotter pin Item 83 mu

carrefully folded against Items 

NOTE (04) Protect the head of axles Items 

and (122) with Polyurethane Prim

16-001C) .

NOTE : Items (74), (75), (76), (77), (78)

(117), (118) and (122) were retaine

attach with :

NOTE : Items (57), (71), (72) and (73) we

removal.

2 Install the rib pad and the struts at Y + 254

Refer to Figure 6

Refer to Figure 13 , Sheets1,2,6,9 t

a Install the rib pad :

6 Axle Item (1

2 Axle Item (1

12 Cotter Pin MS24665-153 Item 83

12 Nut NSA5060-5 Item 84

12 Washer Item (8

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Nut NSA5050-3 Item 8

3 Screw Item (5

88
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Item (125) was retained at removal

b Install the struts :

Refer to Figure 6

1 Screw NSA5479BV5-21 Item 11

2 Screw NSA5479BV6-14 Item 16

12 Screw NSA5479BV5-7 Item 16

8 Screw NSA5479BV6-12 Item 16

14 Screw NSA5479BV5-8 Item 16

13 Screw NSA5479BV5-9 Item 15

6 Screw NSA5479BV6-13 Item 16

2 Screw NSA5479BV5-12 Item 15

10 Screw NSA5479BV6-15 Item 17

4 Screw NSA5479BK7-17 Item 17

2 Screw NSA5479BK7-15 Item 17

4 Screw NSA5479BV7-22 Item 17

2 Screw NSA5479BV6-19 Item 17

3 Screw NSA5479BV5-10 Item 17

2 Screw NSA5479BV5-13 Item 10

4 Screw NSA5479BV5-11 Item 17

2 Screw NSA5479BV5-17Y Item 18

2 Screw NSA5479BV5-14Y Item 18

2 Screw NSA5479BV4-14Y Item 18

10 Screw NSA5479BV5-13Y Item 18

2 Screw NSA5479BV5-18Y Item 18

4 Screw NSA5479BV6-22Y Item 18

42 Nut ASNA2528-5 Item 12

9 Nut ASNA2536-5 Item 55

11 Nut ASNA2536-7 Item 10

30 Nut ASNA2536-6 Item 11

16 Nut NSA5050-5 Item 12

4 Nut NSA5050-6 Item 13

2 Nut NSA5050-4 Item 5

16 Washer NSA5368-516D Item 18

2 Washer NSA5368-416D Item 18

4 Washer NSA5368-616D Item 19

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (8

89
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE (01) Install axles Items (117), (118)

and (121) with Synthe. Hydrocarb

Pressure (Mat No. 04-022) .

NOTE (02) Wet assembly under all the heads 

with Fuel Tank Sealant Polysulfi

09-001) .

NOTE (03) The end of cotter pin Item 83 mu

carrefully folded against Items 

or 85.

NOTE (04) Protect the head of axles Items 

(119), (120) and (121) with Poly

Primer (Mat No. 16-001C) .

NOTE : Items (74), (75), (76), (77), (80)

(86), (87), (117), (118), (119), (1

were retained at removal.

attach with :

NOTE : Items (57), (71), (72) and (73) we

removal.

3 Install the rib pad and the struts at Y - 76

4 Axle Item (1

2 Axle Item (1

2 Axle Item (1

2 Axle Item (1

14 Cotter Pin MS24665-153 Item 83

8 Nut NSA5060-5 Item 84

6 Nut NSA5060-6 Item 85

8 Washer Item (8

6 Washer Item (8

3 Bonding Lead Item (7

1 Bonding Lead Item (7

4 Nut NSA5050-3 Item 8

4 Screw Item (5

90
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

attach with :

NOTE : Items (106) and (124) were retained 

b Install the struts :

Refer to Figure 6

1 Rib Pad Item (1

1 Plate Item (1

1 Screw NSA5479BV7-29 Item 11

2 Screw NSA5479BV6-23 Item 11

1 Screw NSA5479BV5-20 Item 11

1 Screw NSA5479BV7-29 Item 11

2 Screw NSA5479BV6-23 Item 11

1 Screw NSA5479BV5-20 Item 11

3 Screw NSA5479BV6-14 Item 16

13 Screw NSA5479BV5-7 Item 16

9 Screw NSA5479BV6-12 Item 16

14 Screw NSA5479BV5-8 Item 16

13 Screw NSA5479BV5-9 Item 15

4 Screw NSA5479BK7-14 Item 17

16 Screw NSA5479BV6-9 Item 17

6 Screw NSA5479BV5-10 Item 17

4 Screw NSA5479BK7-15 Item 17

4 Screw NSA5479BV5-11 Item 17

4 Screw NSA5479BV5-9Y Item 18

2 Screw NSA5479BV5-17Y Item 18

2 Screw NSA5479BV5-14Y Item 18

2 Screw NSA5479BV4-14Y Item 18

5 Nut ASNA2536-5 Item 55

2 Nut NSA5050-4 Item 5

9 Nut ASNA2536-7 Item 10

12 Nut ASNA2536-6 Item 11

46 Nut ASNA2528-5 Item 12

4 Nut NSA5050-5 Item 12

4 Nut NSA5330-5 Item 13

18 Nut ASNA2528-6 Item 18

4 Washer NSA5368-516D Item 18

2 Washer NSA5368-416D Item 18

1 Strut Item (7

1 Strut Item (7

91
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE (01) Install axles Items (117), (118) 

with Synthe. Hydrocarbon Grease 

(Mat No. 04-022) .

NOTE (02) Wet assembly under all the heads 

with Fuel Tank Sealant Polysulfi

09-001) .

NOTE (03) The end of cotter pin Item 83 mu

carrefully folded against Items 

NOTE (04) Protect the head of axles Items 

and (122) with Polyurethane Prim

16-001C) .

NOTE : Items (74), (75), (76), (77), (78)

(117), (118) and (122) were retaine

attach with :

NOTE : Items (57), (71), (72) and (73) we

removal.

4 Install the rib pad and the struts at Y + 76

Refer to Figure 6

Refer to Figure 13 , Sheets 1 , 2 , 7 , 9 , 

4 Axle Item (1

6 Axle Item (1

2 Axle Item (1

12 Cotter Pin MS24665-153 Item 83

12 Nut NSA5060-5 Item 84

12 Washer Item (8

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

3 Nut NSA5050-3 Item 8

3 Screw Item (5

92
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Items (106) was retained at removal

b Install the struts :

Refer to Figure 6

NOTE : Install the strut Item (79) only if 

attach with :

1 Screw NSA5479BV7-29 Item 11

2 Screw NSA5479BV6-23 Item 11

1 Screw NSA5479BV5-20 Item 11

3 Screw NSA5479BV6-14 Item 16

1 Screw NSA5479BV6-13 Item 16

13 Screw NSA5479BV5-7 Item 16

7 Screw NSA5479BV6-12 Item 16

14 Screw NSA5479BV5-8 Item 16

13 Screw NSA5479BV5-9 Item 15

4 Screw NSA5479BK7-14 Item 17

18 Screw NSA5479BV6-9 Item 17

6 Screw NSA5479BV5-10 Item 17

4 Screw NSA5479BK7-15 Item 17

4 Screw NSA5479BV5-11 Item 17

4 Screw NSA5479BV5-9Y Item 18

2 Screw NSA5479BV5-17Y Item 18

2 Screw NSA5479BV5-14Y Item 18

2 Screw NSA5479BV4-14Y Item 18

5 Nut ASNA2536-5 Item 55

2 Nut NSA5050-4 Item 5

9 Nut ASNA2536-7 Item 10

12 Nut ASNA2536-6 Item 11

46 Nut ASNA2528-5 Item 12

4 Nut NSA5050-5 Item 12

4 Nut NSA5330-5 Item 13

18 Nut ASNA2528-6 Item 18

4 Washer NSA5368-516D Item 18

2 Washer NSA5368-416D Item 18

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

93
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE (01) Install axles Items (117), (118) 

with Synthe. Hydrocarbon Grease 

(Mat No. 04-022) .

NOTE (02) Wet assembly under all the heads 

with Fuel Tank Sealant Polysulfi

09-001) .

NOTE (03) The end of cotter pin Item 83 mu

carrefully folded against Items 

NOTE (04) Protect the head of axles Items 

and (122) with Polyurethane Prim

16-001C) .

NOTE : Items (74), (75), (76), (77), (78)

(117), (118) and (122) were retaine

attached with :

NOTE : Items (57), (71), (72) and (73) we

removal.

5 Install the rib pad and the struts at Y - 254

Refer to Figure 6

Refer to Figure 13 , Sheets1,2,5,9 t

a Install the rib pad :

Refer to Figure 13 , Sheets1,2,5,9 

attach with :

12 Washer Item (8

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Nut Item (7

3 Nut NSA5050-3 Item 8

3 Screw Item (5

1 Rib Pad Item (1

94
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Item (125) was retained at removal

b Install the struts :

Refer to Figure 6

NOTE : Install the strut Item (82) only if 

14 Screw NSA5479BV58 Item 16

13 Screw NSA5479BV5-9 Item 15

6 Screw NSA5479BV6-13 Item 16

4 Screw NSA5479BV5-12 Item 15

10 Screw NSA5479BV6-15 Item 17

4 Screw NSA5479BK7-17 Item 17

2 Screw NSA5479BK7-15 Item 17

4 Screw NSA5479BV7-22 Item 17

2 Screw NSA5479BV6-19 Item 17

3 Screw NSA5479BV5-10 Item 17

2 Screw NSA5479BV5-13 Item 10

2 Screw NSA5479BV5-11 Item 17

2 Screw NSA5479BV5-17Y Item 18

2 Screw NSA5479BV5-14Y Item 18

2 Screw NSA5479BV4-14Y Item 18

10 Screw NSA5479BV5-13Y Item 18

2 Screw NSA5479BV5-18Y Item 18

4 Screw NSA5479BV6-22Y Item 18

42 Nut ASNA2528-5 Item 12

9 Nut ASNA2536-5 Item 55

11 Nut ASNA2536-7 Item 10

30 Nut ASNA2536-6 Item 11

16 Nut NSA5050-5 Item 12

4 Nut NSA5050-6 Item 13

2 Nut NSA5050-4 Item 5

16 Washer NSA5368-516D Item 18

2 Washer NSA5368-416D Item 18

4 Washer NSA5368-616D Item 19

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (8

1 Strut Item (8

1 Strut Item (8

95
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE (01) Install axles Items (117), (118)

and (121) with Synthe. Hydrocarb

Pressure (Mat No. 04-022) .

NOTE (02) Wet assembly under all the heads 

with Fuel Tank Sealant Polysulfi

09-001) .

NOTE (03) The end of cotter pin Item 83 mu

carrefully folded against Items 

or 85.

NOTE (04) Protect the head of axles Items 

(119), (120) and (121) with Poly

Primer (Mat No. 16-001C) .

NOTE : Items (74), (75), (76), (77), (78)

(82), (86), (117), (118), (119), (1

were retained at removal.

attach with :

NOTE : Items (57), (71) and (72) were reta

removal.

6 Install the rib pad and the struts at Y + 129

Refer to Figure 6

Refer to Figure 13 , Sheets1,2,8 thru 

a Install the rib pad :

14 Cotter Pin MS24665-153 Item 83

8 Nut NSA5060-5 Item 84

6 Nut NSA5060-6 Item 85

8 Washer Item (8

6 Washer Item (8

3 Bonding Lead Item (7

1 Bonding Lead Item (7

4 Nut NSA5050-3 Item 8

4 screw Item (5

96
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : Item (106) was retained at removal

b Install the strut :

Refer to Figure 6

NOTE : Install the strut Item (79) only if 

attach with :

1 Screw NSA5479BV5-20 Item 11

2 Screw NSA5479BV6-14 Item 16

12 Screw NSA5479BV5-7 Item 16

6 Screw NSA5479BV6-12 Item 16

14 Screw NSA5479BV5-8 Item 16

14 Screw NSA5479BV5-9 Item 15

4 Screw NSA5479BK7-14 Item 17

14 Screw NSA5479BV6-9 Item 17

2 Screw NSA5479BV6-13 Item 16

6 Screw NSA5479BV5-10 Item 17

4 Screw NSA5479BK7-15 Item 17

2 Screw NSA5479BV6-18 Item 17

4 Screw NSA5479BV5-11 Item 17

4 Screw NSA5479BV5-9Y Item 18

2 Screw NSA5479BV5-17Y Item 18

2 Screw NSA5479BV5-14Y Item 18

2 Screw NSA5479BV4-14Y Item 18

2 Nut NSA5050-4 Item 5

5 Nut ASNA2536-5 Item 55

9 Nut ASNA2536-7 Item 10

16 Nut ASNA2536-6 Item 11

46 Nut ASNA2528-5 Item 12

4 Nut NSA5050-5 Item 12

4 Nut NSA5330-5 Item 13

14 Nut ASNA2528-6 Item 18

4 Washer NSA5368-516D Item 18

2 Washer NSA5368-416D Item 18

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

1 Strut Item (7

97
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE (01) Install axles Items (117), (118) 

with Synthe. Hydrocarbon Grease 

(Mat No. 04-022) .

NOTE (02) Wet assembly under all the heads 

with Fuel Tank Sealant Polysulfi

09-001) .

NOTE (03) The end of cotter pin Item 83 mu

carrefully folded against Items 

NOTE (04) Protect the head of axles Items 

and (122) with Polyurethane Prim

16-001C) .

NOTE : Items (74), (75), (76), (77), (78)

(117), (118) and (122) were retaine

attach with :

NOTE : Items (57), (71), (72) and (73) we

removal.

D. TEST

(1) Config. 01 thru Config. 02

(a) Install the ACT transfer valve FIN 165QM (Refer 

28-28-33 Page block 401), (if removed).

(b) Install the refuel valve canister FIN 164QM (Ref

28-25-52 Page block 401), (if removed).

(c) Install the ACT fuel transfer pump mounting plat

(Refer to AMM 28-28-31 Page block 401), (if remo

12 Washer Item (8

1 Bonding Lead Item (7

1 Bonding Lead Item (7

1 Bonding Lead Item (7

3 Nut NSA5050-3 Item 8

3 Screw Item (5

98
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(g) Install the BLUE electric pump FIN 2075GJ (Refe

29-12-51 Page block 401).

(h) Install the recirculation filters FIN 4012HM and 

(Refer to AMM 21-21-41 Page block 401).

(i) Install the duct temperature sensors FIN 15HK, 

FIN 17HK (Refer to AMM 21-63-15 Page block 401)

(j) Install the mixer unit (Refer to AMM 21-21-43 Pa

(k) Install the mixer unit tempeature sensors FIN 24

25HK (Refer to AMM 21-63-16 Page block 401).

(l) Install the water injectors FIN 20HM and FIN 21H

AMM 21-52-42 Page block 401).

(m) Install the check valves FIN 4020HM and FIN 402

AMM 21-21-42 Page block 401).

(n) Install the cabin recirculation fans FIN 14HG a

(Refer to AMM 21-21-51 Page block 401).

(o) Install the Jet Pumps center tank FIN 157QM and 

(Refer to AMM 28-26-41 Page block 401).

(p) Remove the Jet Pump Fuel Control Valves FIN 153Q

154QM (Refer to AMM 28-26-43 Page block 401).

(q) Install the center tank probes FIN 37QT and FIN 

AMM 28-42-15 Page block 401).

(r) Install the center tank fuel lever sensor FIN 2

AMM 28-46-15 Page block 401).

(s) Install the vapor seal (Refer to AMM 28-13-42 Pa

(t) Install the refuel diffuser assembly of the cent

to AMM 28-25-42 Page block 401).

(u) Remove the safety clips and tags and close these 

breakers (Refer to AMM 28-42-47 Page block 401), 

28-42-44 Page block 401), (Refer to AMM 28-42-1

401), (Refer to AMM 33-48-12 Page block 401), (

27-84-45 Page block 401), (Refer to AMM 27-84-5

401), (Refer to AMM 21-61-51 Page block 401), (

99
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(w) Do the test after the removal/installation of t

(Refer to AMM 28-13-42 Page block 401).

(x) Do the test after the removal/installation of t

fuel lever sensor FIN 22QJ (Refer to AMM 28-46-

401).

(y) Do the test after the removal/installation of t

FIN 50QT (Refer to AMM 28-42-47 Page block 401)

(z) Do the test after the removal/installation of t

harnesses FIN 17QT and FIN 18QT (Refer to AMM 2

block 401).

(aa) Do the test after the removal/installation of t

transfer tank fuel quantity probes FIN 35QT, FIN 

37QT, FIN 38QT and FIN 51QT (Refer to AMM 28-42

401).

(ab) Do the test after the removal/installation of t

fuel control valves FIN 153QM and 154QM (Refer t

Page block 401).

(ac) Do the test after the removal/installation of t

jet pumps FIN 157QM and FIN 158QM (Refer to AMM 

block 401).

(ad) Do the test after the removal/installation of t

recirculation fans FIN 14HG and FIN 15HG (Refer 

21-21-51 Page block 401).

(ae) Do the test after the removal/installation of t

temperature sensors FIN 24HK and FIN 25HK (Refe

21-63-16 Page block 401).

(af) Do the test after the removal/installation of t

(Refer to AMM 21-21-43 Page block 401).

(ag) Do the test after the removal/installation of t

temperature sensors FIN 15HK, FIN 16HK and FIN 

AMM 21-63-15 Page block 401).

(ah) Do the test after the removal/installation of t

electric pump FIN 2075GJ (Refer to AMM 29-12-51 

401).

100
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

extractor temperature sensors FIN 11HH and FIN 

AMM 21-61-13 Page block 401).

(al) Do the test after the removal/installation of t

beacon/strobe light FIN 6LV from the fuselage o

to AMM 33-48-12 Page block 401).

(am) Do the test after the removal/installation of th

torque shaft assy FIN 6004CM (Refer to AMM 27-84

401).

(an) Do the test after the removal/installation of th

of the Power Control Unit (PCU) (slat) FIN 25CV 

(Refer to AMM 27-84-53 Page block 401).

(ao) Do the test after the removal/installation of t

flap actuators FIN 8HH and FIN 28HH (Refer to AM

Page block 401).

(ap) Do the test after the removal/installation of t

temperature sensor FIN 34HH (Refer to AMM 21-61

401).

(aq) Do the test after the removal/installation of t

sensors FIN 9HB and FIN 10HB (Refer to AMM 21-51

401).

(ar) Do the test after the removal/installation of t

pressure sensors FIN 16HH and FIN 36HH (Refer to 

Page block 401).

(as) Do the test after the removal/installation of t

pump FIN 3075GX (Refer to AMM 29-24-51 Page blo

(at) Tests after the removal/installation of the ACT 

FR42 (if removed/installed):

1 Do the operational test of the ACT manual tra

to AMM 28-28-00 Page block 501).

2 Make sure that there are no leaks at the remo

of the ACT transfer and at the interface of t

valve canister FIN 164QM with the structure.

(au) Bonding tests :

101
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

to AMM 28-11-00 Page block 501).

E. CLOSE UP

(1) Config. 01 thru Config. 02

(a) Install the panels FIN 191EB, FIN 191LB, FIN 147

FIN 191GB, FIN 147BB, FIN 147AB, FIN 195CB, FIN 

191DB, FIN 191HB, FIN 191MB, FIN 192EB, FIN 192

FIN 192EB, FIN 192FB, FIN 196AB, FIN 195AB and 

(Refer to AMM 53-35-11 Page block 401) and (Refe

53-35-13 Page block 401).

(b) Install the partitions FIN 151BW, FIN 151AW and 

the aft cargo compartment at FR47 (Refer to AMM 

block 401).

(c) Close the acces doors 147AZ and 148AZ (Refer to 

Page block 401).

(d) Reactive the venting system (Refer to AMM 28-12

401).

(e) Refuel the center tank (Refer to AMM 28-25-00 Pa

(f) Close the Cargo door 825 (Refer to AMM 52-30-00 

201).

(g) Close the Main Landing Gear doors (Refer to AMM 

block 201).

(h) Close the passenger/crew door 831 (Refer to AMM 

block 201).

(i) Remove the access platforms.

(j) Disconnect the aircraft electrical ground-connec

AMM 12-34-24 Page block 401).

F. DOCUMENTATION

Write in the applicable aircraft records that you have don

given in the Service Bulletin.

102
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 1

Config. 01 to 02 : Removal/Installation of the ACT Transfer 

103
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 2

Config. 01 to 02 : Removal/Installation of the ACT Transfer 

104
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 3

Config. 01 to 02 : Removal/Installation of the ACT Transfer 

105
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 4

Config. 01 to 02 : Removal/Installation of the ACT Transfer 

106
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 5

Config. 01 to 02 : Removal/Installation of the ACT Transfer 

107
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 6

Config. 01 to 02 : Removal/Installation of the ACT Transfer 

108
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 2 Sheet 1

Config. 01 to 02 : Removal/Installation of the Pipes and Support o

in the RH Center Wing Box at FR42

109
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 1

Config. 01 to 02 : Removal/Installation of the LH and RH Jet P

Between FR41 and FR42

110
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 2

Config. 01 to 02 : Removal/Installation of the LH and RH Jet P

Between FR41 and FR42

111
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 4 Sheet 1

Config. 01 to 02 : Removal/Installation of the Oblique Strut an

Between FR41 and FR42

112
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 4 Sheet 2

Config. 01 to 02 : Removal/Installation of the Oblique Strut an

Between FR41 and FR42

113
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 4 Sheet 3

Config. 01 to 02 : Removal/Installation of the Oblique Strut an

Between FR41 and FR42

114
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 5 Sheet 1

Config. 01 to 02 : Removal/Installation of the Sensor 22QJ, the 

from the Sensor 22QJ and the Harnesses 17QT and 18QT from the U

115
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 5 Sheet 2

Config. 01 to 02 : Removal/Installation of the Sensor 22QJ, the 

from the Sensor 22QJ and the Harnesses 17QT and 18QT from the U

116
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 5 Sheet 3

Config. 01 to 02 : Removal/Installation of the Sensor 22QJ, the 

from the Sensor 22QJ and the Harnesses 17QT and 18QT from the U

117
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 5 Sheet 4

Config. 01 to 02 : Removal/Installation of the Sensor 22QJ, the 

from the Sensor 22QJ and the Harnesses 17QT and 18QT from the U

118
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 5 Sheet 5

Config. 01 to 02 : Removal/Installation of the Sensor 22QJ, the 

from the Sensor 22QJ and the Harnesses 17QT and 18QT from the U

119
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 6 Sheet 1

Config. 01 to 02 : Removal/Installation of the Struts and the Lowe

Center Wing Box Between FR36 and FR42

120
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 6 Sheet 2

Config. 01 to 02 : Removal/Installation of the Struts and the Lowe

Center Wing Box Between FR36 and FR42

121
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 6 Sheet 3

Config. 01 to 02 : Removal/Installation of the Struts and the Lowe

Center Wing Box Between FR36 and FR42

122
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 6 Sheet 4

Config. 01 to 02 : Removal/Installation of the Struts and the Lowe

Center Wing Box Between FR36 and FR42

123
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 6 Sheet 5

Config. 01 to 02 : Removal/Installation of the Struts and the Lowe

Center Wing Box Between FR36 and FR42

124
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 7 Sheet 1

Config. 01 to 02 : Removal/Installation of the Air Conditioning 

FR34 and FR36 in the Cargo compartment

125
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 8 Sheet 1

Config. 01 : Removal/Installation of the Fittings of Vapor Seal Be

FR40

126
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 8 Sheet 2

Config. 01 : Removal/Installation of the Fittings of Vapor Seal Be

FR40

127
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 8 Sheet 3

Config. 01 : Removal/Installation of the Fittings of Vapor Seal Be

FR40

128
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 8 Sheet 4

Config. 01 : Removal/Installation of the Fittings of Vapor Seal Be

FR40

129
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 8 Sheet 5

Config. 01 : Removal/Installation of the Fittings of Vapor Seal Be

FR40

130
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 1

Config. 01 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

131
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 2

Config. 01 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

132
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 3

Config. 01 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

133
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 4

Config. 01 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

134
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 5

Config. 01 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

135
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 6

Config. 01 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

136
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 7

Config. 01 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

137
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 8

Config. 01 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

138
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 9

Config. 01 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

139
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 10

Config. 01 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

140
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 11

Config. 01 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

141
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 12

Config. 01 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

142
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 13

Config. 01 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

143
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 9 Sheet 14

Config. 01 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

144
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 10 Sheet 1

Config. 01 to 02 : Area to Inspect

145
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 11 Sheet 1

Config. 01 : Flow Chart

146
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 12 Sheet 1

Config. 02 : Removal/Installation of the Fittings of Vapor Seal Be

FR40

147
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 12 Sheet 2

Config. 02 : Removal/Installation of the Fittings of Vapor Seal Be

FR40

148
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 12 Sheet 3

Config. 02 : Removal/Installation of the Fittings of Vapor Seal Be

FR40

149
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 12 Sheet 4

Config. 02 : Removal/Installation of the Fittings of Vapor Seal Be

FR40

150
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 12 Sheet 5

Config. 02 : Removal/Installation of the Fittings of Vapor Seal Be

FR40

151
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 13 Sheet 1

Config. 02 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

152
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 13 Sheet 2

Config. 02 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

153
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 13 Sheet 3

Config. 02 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

154
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 13 Sheet 4

Config. 02 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

155
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 13 Sheet 5

Config. 02 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

156
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 13 Sheet 6

Config. 02 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

157
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 13 Sheet 7

Config. 02 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

158
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 13 Sheet 8

Config. 02 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

159
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 13 Sheet 9

Config. 02 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

160
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 13 Sheet 10

Config. 02 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

161
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 13 Sheet 11

Config. 02 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

162
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 13 Sheet 12

Config. 02 : Removal/Installation of the Rib Pads in the Center Wi

FR36 and FR42

163
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 14 Sheet 1

Config. 02 : Flow Chart

164
5 DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 1

Config. 01 : Inspection Report

2
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 2

Config. 01 : Inspection Report

3
5 DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 1

Config. 02 : Inspection Report

2
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 2

Config. 02 : Inspection Report

3
5 DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

B. AIRCRAFT CONFIGURATION

Refer to Figure 1

— This jacking procedure is valid only for the configurat

The aircraft without :

. Fuel (with undrainable fuel)

. Belly fairing

. Air conditioning pack

PART NUMBER QTY DESCRIPTION

98D07203003040 1 Cradle

98D07203003042 1 Cradle

98D07203004000 2 Cradle for engine CF

98D07203005000 2 Cradle for engine IA

98D57004031043 2 Cradle

98D57004031040 2 Cradle

D01-207 or equivalent

TR87

1 Jack

98D07203002000 2 Jack

TR89 1 Jack

AS100000 2 Jack

D05-009 2 Jack

98D07203000048 1 Fitting

98D07203000049 1 Fitting

98D07103000000 1 Dynamometer

98A07003907200 5 Load cell

98A07003906200 5 Load cell

343A100KN2 2 Load cell

343A400KN2 3 Load cell

343A25KN2 4 Load cell
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

C. JACKING PROCEDURE

(Refer to SRM 51-51-00)

Refer to Figure 1

(1) Lift the aircraft on the jacks at points A, B1, B2.

(Refer to AMM 07-11-00 Page block 001).

(2) Install the additional jacks, the load cells and the 

points 3, 18, 19, 20, 23, 24, 25, 26, 27, 28 and und

RH engines.

Refer to Figure 1 , Sheets 3 , 4 , 5 and 6

NOTE : To do the jacking, you must apply the loads i

— Step 1 : 25%

— Step 2 : 50%

— Step 3 : 75%

— Step 4 : 100%

Refer to Figure 1 , Sheet 9 (for aircraft w

ACT2) or Sheet 10 (for aircraft with the AC

CAUTION : MAKE SURE THAT THE LOADS DO NEVER EXCEED TH

PERMISSIBLE LOADS (REFER TO FIGURE 1 , SHE

AIRCRAFT WITHOUT THE ACT2) OR SHEET 10 (FO

WITH THE ACT2).

(3) Install the safety jack at point C.

D. CLOSE-UP

(1) Refer to SRM 51-51-00.

Refer to (Refer to AMM 07-11-00 Page block 001).

2
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 1

Jacking for the Inspection of the Rib Pads in the Center Wing Bo

and FR42.

3
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 2

Jacking for the Inspection of the Rib Pads in the Center Wing Bo

and FR42.

4
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 3

Jacking for the Inspection of the Rib Pads in the Center Wing Bo

and FR42.

5
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 4

Jacking for the Inspection of the Rib Pads in the Center Wing Bo

and FR42.

6
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 5

Jacking for the Inspection of the Rib Pads in the Center Wing Bo

and FR42.

7
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 6

Jacking for the Inspection of the Rib Pads in the Center Wing Bo

and FR42.

8
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 7

Jacking for the Inspection of the Rib Pads in the Center Wing Bo

and FR42.

9
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 8

Jacking for the Inspection of the Rib Pads in the Center Wing Bo

and FR42.

10
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 9

Jacking for the Inspection of the Rib Pads in the Center Wing Bo

and FR42.

11
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 10

Jacking for the Inspection of the Rib Pads in the Center Wing Bo

and FR42.

12
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 11

Jacking for the Inspection of the Rib Pads in the Center Wing Bo

and FR42.

13
DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 12

Jacking for the Inspection of the Rib Pads in the Center Wing Bo

and FR42.

14
5 DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

A - SB WILL BE embodied............. YES/NO (if NO p

If YES, aircraft concerned (as per SB effectivity by default) and 

(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 th

information is needed prior to next normal revision or prior to S

please indicate required service:

Either: Modification Operational Impact (MOI), if available. . YE

Or : Intermediate revision. ................ YE

Important Information: This SB will only be incorporated in your m

operational documentation if this sheet is returned to Airbus and 

duly authorised representative. With the next feasible revision, 

result in

- updating of maintenance documentation to show pre and post S

- updating of maintenance and operational documentation to show 

after embodiment.

If this SB requires previous or simultaneous accomplishment of ot

Airbus shall automatically include them in the manual revisions. 

00-037 for detailed information.

Please return this completed sheet to:

 AIRBUS

 CUSTOMER SERVICES DIRECTORATE

 1 Rond Point Maurice Bellonte

 31707 BLAGNAC CEDEX FRANCE

 Attn: SDC32 Technical Data and Documentation Services

 FAX: (+33) 5 61 93 28 06

 e-mail: sb.reporting@airbus.com

 or via your Resident Customer Support Office.

 Alternatively, SB lists via letters or fax are also accepted.
5 DATE : Sep 04/03 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Nov 15/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

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

- Quality rating of this SB 

- Quality rating of the Accomplishment Instructions 

- Quality rating of the Illustrations 

- Is this SB easy to understand ? 

If you have had difficulties in the accomplishment of this SB plea

the area(s) and give a short description of the issue.

Planning Material Instruct

X Effectivity X Kit content X Preparat

X Reason X List of Materials X Mod/Insp

X Manpower Operator Supplied X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustra

Comments :

Operator : Date:

Name/Title :

Please return this form to :

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.