# @ A318/A319/A320/A321 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

5 DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : 1 of 4 Printed in FRANCE © AIRBUS, 2006 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 

# MANDATORY MANDATORY MANDATORY
ATA SYSTEM : 57 TITLE : WINGS - CENTER WING - INSPECTION OF CENTER WING BOX LOWER PANEL BORE HOLES. MODIFICATION No. : None This page transmits Revision No. 01 of Service Bulletin No. A320-57-1120. ADDITIONAL WORK No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 01 issued to inform the operators that this Service Bulletin is rendered Mandatory and issued to add Config. 02 with the new repair procedure to be used when the Service Bulletin is accomplished between 12,000 Flight Cycle (FC) and 24,000 FC or between 20,000 Flight Hours (FH) and 40,000 FH. CHANGES SUMMARY : — REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES . Sentence updated. In the EVALUATION TABLE Recommended becomes Mandatory, DE-FUELLING/VENTILATING and NORMAL JACKING added. KIT PRICE added. — MANPOWER . Config. 02 added. — APPENDICES . Appendix 2 concerning the Inspection report added. PLANNING INFORMATION : — EFFECTIVITY . Para. 1.A. NOTES and Config. 02 added.

# @ A318/A319/A320/A321 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved — REASON . Para. 1.C. Sentence updated. — DESCRIPTION . Para. 1.D. Config. 02 added. — 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 added. Reference to ESPM 20-55-00 added. Refer to NTM 51-10-01 added. Reference to SRM 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 nut item 97, NSA5479BK6-14 becomes NSA5479VHK6-14 for the item 157, NSA5479BK6-15 becomes NSA5479VHK6-15 for the item 159, NSA5479BK6-17 becomes 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

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# @ A318/A319/A320/A321 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved . Para. 3.A. CAUTION added. Paragraphs concerning the degas and ventilate the center tank added. — Standard Practices . Para. 3.A.(2) Paragraphs concerning the drill and deburr the holes added. Paragraphs concerning the oversize the holes added. — INSPECTION . Para. 3.B. (1)(a)8 concerning the removal of the rib pad added. Para. 3.B(1)(e) concerning the close-up for the inspection modified. Para. 3.B.(1)7a Item 132 NSA5479BV5-13X becomes Item 139 and NOTE modified, para. 3.B.(1)7c NOTE modified. Para. 3.B.(2) added for the Config. 02. — REPAIR . Para. 3.C. (1) updated and para. 3(C)(2) added for the Config. 02. — ILLUSTRATIONS . Figure 8, Sheet 5 item 132 becomes 139. . Figure 9, Sheet 9 NSA5479BK6-14 becomes NSA5479VHK6-14 for the screw item 157. Figure 9, Sheet 10 NSA5479BK6-15 becomes NSA5479VHK6-15 for the screw item 159 and NSA5479BK6-17 becomes NSA5479VHK6-17 for the screw item 164. Figure 9, Sheet 11 NSA5479BK6-15 becomes NSA5479VHK6-15 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 revision are not identified. FILING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS No previous revisions.

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# @ A318/A319/A320/A321 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved REVISION SEQUENCE ORIGINAL : Sep 04/03 REVISION No. : 01 — Nov 15/06

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# @ A318/A319/A320/A321 SERVICE BULLETIN SUMMARY

5 DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : 1 of 5 Printed in FRANCE © AIRBUS, 2006 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft 

# MANDATORY MANDATORY MANDATORY
ATA SYSTEM : 57 TITLE : WINGS - CENTER WING - INSPECTION OF CENTER WING BOX LOWER PANEL BORE HOLES. MODIFICATION No. : None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During removal of one Center Wing Box (CWB) lower aft panel on a build up section, it was noted : — Excessive PR sealant in between the lower panel and the rib pads, — Small metal chips between the panel and rib pads. The investigations revealed that the installation of rib pads on the panel had not been correctly ensured due to poor clamping during drilling (use of a new slave pin). The deviation has been identified on both FWD and aft lower panels at Y +- 254, Y +- 765 and Y +- 1292. After fatigue analysis only A321 would require a further action after delivery. — If accomplished before 12,000 Flight Cycle (FC) or 20,000 Flight Hours (FH) 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 nominal fasteners; If fastener holes are damaged : oversize to R1 and install R1 fasteners. . to reinstall the rib pads. — If accomplished Between 12,000 FC and 24,000 FC or 20,000 FH and 40,000 FH which occurs first, this Service Bulletin requests :

# @ A318/A319/A320/A321 SERVICE BULLETIN SUMMARY

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved . to remove the rib pads one by one; . to perform a special detailed visual inspection of the holes area and contact AIRBUS if crack is detected. Accomplishment of this Service Bulletin will allow detecting damages and correcting all the deviations. Accomplishment of Service Bulletin No. A320-57-1120 at revision No. 00 cancels 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 SB No POTENTIAL AD Yes A/C OPERATION AFFECTED No RELIABILITY AFFECTED No PAX COMFORT AFFECTED No COST SAVING No ETOPS AFFECTED No STRUCTURAL LIFE EXTN Yes VENDOR SB INVOLVED No DE-FUELLING/VENTILLATIN G Yes NORMAL JACKING Yes KIT PRICE (USD) A01R05 92,530 KIT PRICE (USD) A02R01 139,21 0

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# @ A318/A319/A320/A321 SERVICE BULLETIN SUMMARY

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved SOFT : NO OBRM : NO MANPOWER Config. 01 thru Config. 02 , inspection

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 TOTAL MANHOURS 163.0 ELAPSED TIME (HOURS) 90.0

TOTAL MANHOURS 90.0 ELAPSED TIME (HOURS) 45.0

TOTAL MANHOURS 120.0 ELAPSED TIME (HOURS) 60.0

TOTAL MANHOURS 144.0 ELAPSED TIME (HOURS) 72.0

TOTAL MANHOURS 24.0 ELAPSED TIME (HOURS) 12.0

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# @ A318/A319/A320/A321 SERVICE BULLETIN SUMMARY

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Appendix 03 : Jacking procedure for the inspection of the rib pads in the center wing box between FR36 and FR42.

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# @ A318/A319/A320/A321 SERVICE BULLETIN SUMMARY

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 5

# @ A318/A319/A320/A321 SERVICE BULLETIN

5 DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : 1 of 164 Printed in FRANCE © AIRBUS, 2006 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 

# MANDATORY MANDATORY MANDATORY
ATA SYSTEM : 57 TITLE : WINGS - CENTER WING - INSPECTION OF CENTER WING BOX LOWER PANEL BORE HOLES. MODIFICATION No. : None This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS' prior written consent. 1. PLANNING INFORMATION 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 MSN : 1293 1299 1307 1333 1356 1366 (b) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason.

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 MSNs are given at the end of this list: 1293 1299 1307 1333 1356 1366

NOTE : Config. 01 concerns the aircraft before 12,000 FC or 20,000 FH whichever occurs first. NOTE : Config. 02 concerns the aircraft between 12,000 FC and 24,000 FC or between 20,000 FH and 40,000FH whichever occurs first. (3) Spares None B. CONCURRENT REQUIREMENTS None C. REASON (1) History During removal of one Center Wing Box (CWB) lower aft panel on a build up section, it was noted : — Excessive PR sealant in between the lower panel and the rib pads, — Small metal chips between the panel and rib pads. The investigations revealed that the installation of rib pads on the panel had not been correctly ensured due to poor clamping during drilling (use of a new slave pin). OPERATOR MSN AAR 1356 AFR 1299 CSC 1293 JKK 1333 1366 TAP 1307

KIT No. QTY PER A/C CONFIGURATION 571120A01R05 1 01 571120A02R01 1 02

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved The deviation has been identified on both FWD and aft lower panels at Y +- 254, Y +- 765 and Y +- 1292. After fatigue analysis only A321 would require a further action after delivery. (2) Objective/Action — If accomplished before 12,000 Flight Cycle (FC) or 20,000 Flight Hours (FH) 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 nominal fasteners; If fastener holes are damaged : oversize to R1 and install R1 fasteners. . to reinstall the rib pads. — If accomplished Between 12,000 FC and 24,000 FC or 20,000 FH and 40,000 FH which occurs first, this Service Bulletin requests : . to remove the rib pads one by one; . to perform a special detailed visual inspection of the holes area and contact AIRBUS if crack is detected. (3) Advantages Accomplishment of this Service Bulletin will allow detecting damages and correcting all the deviations. Accomplishment of Service Bulletin No. A320-57-1120 at revision No. 00 cancels the inspection requirements of this Service Bulletin. (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

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (b) Repair 1 Replace the installation of the rib pads with oversize fasteners. (2) Config. 02 (a) Inspection 1 Do a special detailed visual inspection Refer to Figure 15 (b) Repair 1 Replace the installation of the rib pads with next nominal fasteners and oversize fasteners. E. COMPLIANCE (1) Classification Mandatory (2) Accomplishment Timescale Accomplishment of this Inspection Service Bulletin must be performed before 24,000 FC or 40,000 FH since the first flight of the aircraft, whichever occurs first. Accomplishment of this Service Bulletin is expected to be rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). It is anticipated that the AD will confirm the (thresholds and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. F. APPROVAL Approved under EASA Design Organisation Approval No. EASA 21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator's circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved procurement of parts and tools, drying times for paints, sealants, etc, and general administration work are also not included. Config. 01 thru Config. 02 , inspection

Config. 01 , repair with nominal fasteners Get access 30.0 Removal the ACT (if necessary) 10.0 Removal of the pipes, support diffuser 2.0 Removal the LH, RH jet pumps FR41, FR42 5.0 Removal the strut, support FR41 and FR42 1.5 Removal 22QJ, 17QT and 18QT 2.0 Removal air conditioning FR34 and FR36 2.0 Removal fittings vapor seal 2.0 Visual inspection holes of rib pads 24.0 Installation fittings vapor seal 3.5 Installation air between FR34 and FR36 3.0 Installation 22QJ, 17QT and 18QT 3.0 Installation strut/support FR41 and FR42 2.5 Installation RH, RH jet pumps FR41, FR42 7.0 Installation pipes and support diffuser 4.0 Installation ACT (if removed) 13.0 Test 6.5 Close-up 42.0 TOTAL MANHOURS 163.0 ELAPSED TIME (HOURS) 90.0
Replacement rib pads nominal fasteners 90.0

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Config. 01 , replacement rib pads oversize fasteners

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 90.0 ELAPSED TIME (HOURS) 45.0

Installation oversize fasteners 120.0 TOTAL MANHOURS 120.0 ELAPSED TIME (HOURS) 60.0

Installation next nominal fasteners 144.0 TOTAL MANHOURS 144.0 ELAPSED TIME (HOURS) 72.0

Installation oversize fasteners 24.0 TOTAL MANHOURS 24.0 ELAPSED TIME (HOURS) 12.0

Aircraft Maintenance Manual (AMM) : 07-11-00 12-34-24 20-21-11 20-21-15 20-28-00 21-21-41 21-21-42 21-21-43 21-21-51 21-51-11 21-52-42 21-61-13 21-61-15 21-61-16 21-61-51 21-63-15 21-63-16 25-55-11 27-84-45 27-84-53 28-00-00 28-10-00 28-11-00 28-12-00 28-13-42 28-25-00 28-25-42 28-25-52 28-26-41 28-26-43 28-28-00 28-28-31 28-28-33 28-42-15 28-42-44 28-42-47 28-46-15 29-12-21 29-12-42 29-12-51 29-24-51 32-12-00 33-48-12 52-10-00 52-30-00 53-35-11 53-35-13 57-17-11

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) : 20-55-00 Non destructive Testing Manual (NTM) : 51-10-01 Structural Repair Manual (SRM) : 51-24-00 51-42-11 51-43-00 51-43-12 51-44-11 51-51-00

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved

This Page Intentionally Left Blank

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 2. MATERIAL INFORMATION A. MATERIAL — PRICE AND AVAILABILITY (1) Material Customers with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is : AIRBUS 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 order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. Kit 571120A02R01 Cost : 139,210.00US Dollars Availability : 120 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. B. INDUSTRY SUPPORT INFORMATION For those aircraft with findings further to inspection as per this Service Bulletin, AIRBUS will provide the kits at no charge, and will credit the manhours for the correction at the operator's agreed in-house warranty labor rate upon receipt of a warranty claim. AIRBUS will credit the manhours indicated in this Service Bulletin for inspections that are performed on aircraft in warranty at the time of such inspection. Credit will be at the Operator's agreed in-house warranty labor rate upon receipt of a warranty claim.

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved C. LIST OF COMPONENTS Kit 571120A01R05 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 5 NSA5050-4 6 Nut 8 NSA5050-3 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

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 571120A02R01 160 NSA5479BV5-17 12 Screw 161 NSA5479BV4-14 12 Screw 162 NSA5479BV6-22 16 Screw 163 NSA5479BV5-19 4 Screw 164 NSA5479VHK6-17 8 Screw

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 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 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. 130 NSA5050-6 8 Nut 131 NSA5330-5 16 Nut 139 NSA5479BV5-13X 1 Screw 140 NSA5479BV4-12X 2 Screw 147 NSA5479BV5-14X 3 Screw 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 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved D. LIST OF MATERIALS — OPERATOR SUPPLIED (1) Consumable Materials

(2) Components Config. 01 DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C INST DISP None As required 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. INT INST DISP 5 NSA5050-4 42 Nut (01) 128 NSA5330-4 268 Nut (01) 129 NSA5050-5 158 Nut (01) 130 NSA5050-6 60 Nut (01) 131 NSA5330-5 82 Nut (01) 132 NSA5479BV4-11X 22 Screw (01) 133 NSA5479BV4-7X 76 Screw (01) 134 NSA5479BV5-12X 46 Screw (01) 135 NSA5479BV4-8X 82 Screw (01) 136 NSA5479BV4-9X 80 Screw (01) 137 NSA5479VHK6-14X 16 Screw (01) 138 NSA5479BV5-9X 80 Screw (01) 139 NSA5479BV5-13X 35 Screw (01) 140 NSA5479BV4-12X 4 Screw (01)

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 use the tools listed in AMM 07-11-00 Page block 1, SRM 51-51-00 and NTM 51-10-01 procedure A, Part 6. G. SPECIAL TOOLS None 141 NSA5479BV5-15X 20 Screw (01) 142 NSA5479VHK6-17X 8 Screw (01) 143 NSA5479VHK6-15X 20 Screw (01) 144 NSA5479BV5-18X 6 Screw (01) 145 NSA5479BV4-10X 33 Screw (01) 146 NSA5479BV4-13X 4 Screw (01) 147 NSA5479BV5-14X 34 Screw (01) 148 NSA5479BV5-17X 12 Screw (01) 149 NSA5479BV4-14X 12 Screw (01) 150 NSA5479BV6-22X 16 Screw (01) 151 NSA5479BV5-19X 4 Screw (01) ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL (1) Preparation WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE, TO DO THIS : — PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. — REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00. (a) Config. 01 thru Config. 02 1 Electrically ground the aircraft (Refer to AMM 12-34-24 Page block 401). 2 Put the access platforms in position. 3 Open the passenger/crew door 831, (Refer to AMM 52-10-00 Page block 201). 4 Open the Main Landing Gear doors (Refer to AMM 32-12-00 Page block 201). 5 Open the Cargo door 825 (Refer to AMM 52-30-00 Page block 201). 6 Open, safety and tag circuit breakers (Refer to AMM 28-42-47 Page block 401), (Refer to AMM 28-42-44 Page block 401), (Refer to AMM 28-42-15 Page block 401), (Refer to AMM 33-48-12 Page block 401), (Refer to AMM 27-84-45 Page block 401), (Refer to AMM 27-84-53 Page block 401), (Refer to AMM 21-61-51 Page block 401), (Refer to AMM 21-51-11 Page block 401), (Refer to AMM 21-61-16 Page block 401), (Refer to AMM 29-24-51 Page block 401) and (Refer to AMM 28-28-00 Page block 401), 7 Defuel the fuel the center tank (Refer to AMM 28-25-00 Page block 301).

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 8 Degas and ventilate the center tank (Refer to AMM 28-00-00 Page block 301 and AMM 28-10-00 Page block 301). 9 Open the access covers FIN 147AZ and FIN 148AZ (Refer to AMM 57-17-11 Page block 401). 10 De-active the venting system (Refer to AMM 28-12-00 Page block 401). 11 Remove the refuel diffuser assembly of the center tank (Refer to AMM 28-25-42 Page block 401). 12 Remove the vapor seal (Refer to AMM 28-13-42 Page block 401). 13 Remove the center tank fuel lever sensor FIN 22QJ only (Refer to AMM 28-46-15 Page block 401). 14 Remove the center tank probes FIN 37QT and FIN 38QT (Refer to AMM 28-42-15 Page block 401). 15 Remove the Jet Pump Fuel Control Valves FIN 153QM and FIN 154QM (Refer to AMM 28-26-43 Page block 401). 16 Remove the Jet Pumps center tank FIN 157QM and FIN 158QM (Refer to AMM 28-26-41 Page block 401). 17 Remove the cabin recirculation fans FIN 14HG and FIN 15HG (Refer to AMM 21-21-51 Page block 401). 18 Remove the check valves FIN 4020HM and FIN 4021HM (Refer to AMM 21-21-42 Page block 401). 19 Remove the water injectors FIN 20HM and FIN 21HM (Refer to AMM 21-52-42 Page block 401). 20 Remove the mixer unit tempeature sensors FIN 24HK and FIN 25HK (Refer to AMM 21-63-16 Page block 401). 21 Remove the mixer unit (Refer to AMM 21-21-43 Page block 401). 22 Remove the duct temperature sensors FIN 15HK, FIN 16HK and FIN 17HK (Refer to AMM 21-63-15 Page block 401). 23 Remove the recirculation filters FIN 4012HM and FIN 4013HM (Refer to AMM 21-21-41 Page block 401). 24 Remove the BLUE electric pump FIN 2075GJ (Refer to AMM 29-12-51 Page block 401). 25 Remove the BLUE power accumulator FIN 2070GM (Refer to AMM 29-12-42 Page block 401).

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 26 Remove the air accumulator pressure gage FIN 2072GM (Refer to AMM 29-12-21 Page block 401). 27 Remove the water extractor temperature sensors FIN 11HH and FIN 31HH (Refer to AMM 21-61-13 Page block 401). 28 Remove the ACT (Additional Center Tank) fuel transfer pump mounting plate FIN 163QM (Refer to AMM 28-28-31 Page block 401), (if installed). 29 Remove the refuel valve canister FIN 164QM (Refer to AMM 28-25-52 Page block 401), (if installed). 30 Remove the ACT transfer valve FIN 165QM (Refer to AMM 28-28-33 Page block 401), (if installed). 31 Remove the partitions FIN 151BW, FIN 151AW and FIN 152AW from the aft cargo compartment at FR47 (Refer to AMM 25-55-11 Page block 401). 32 Remove the panels FIN 191EB, FIN 191LB, FIN 147CB, FIN 191JB, FIN 191GB, FIN 147BB, FIN 147AB, FIN 195CB, FIN 191CB, FIN 191DB, FIN 191HB, FIN 191MB, FIN 192EB, FIN 192LB, FIN 148DB, FIN 192EB, FIN 192FB, FIN 196AB, FIN 195AB and FIN 195BB (Refer to AMM 53-35-11 Page block 401) 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 numbers (Mat. No.), refer to the CML. b Put all the retained hardware in identified plastic bags and attach the bags to the related units. c Use a non-metallic spatula to remove the sealant and clean the areas with Solvent (Mat No. 11-026) . d Clean the surfaces to be sealed with Solvent (Mat No. 11-026) . e Remove and install the fasteners (Refer to SRM 51-42-11). f Drill and deburr the holes (Refer to SRM 51-44-11). g Oversize the holes (Refer to SRM 51-43-00). h Protect the cut out areas or the parts with Chemical Conversion Coating Yellow Aluminum (Mat No. 13-002) ,

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Polyurethane Primer (Mat No. 16-001C) and Sealant Polysulfide (Mat No. 09-002C) . i Do the electrical bonding (Refer to AMM 20-28-00 Page block 201) with Pure Mineral Vaseline and Petrolatum (Mat No. 04-012) and Electrical Bonding Coating (Blue Color) (Mat No. 07-001) . j Torque the standard threaded fasteners (Refer to AMM 20-21-11 Page block 201). k Torque the electrical component fasteners (Refer to AMM 20-21-15 Page block 201). l Apply the sealant (Refer to SRM 51-24-00). m For alternative and substitute fasteners, (Refer to SRM 51-43-12). n Apply the Corrosion Inhibiting fillet Consistency (Mat No. 09-016B) to the interfaces of the structure and all the parts. o Protect the areas to prevent damage to the equipment and structure not removed. 2 For repair only : a Apply the Adhesion Promoter For Polysulfide Sealant (Mat No. 09-028A) to the interfaces of the structure and all parts. b Apply the Corrosion Inhibiting fillet Consistency (Mat No. 09-016) on all fasteners. c Apply the Corrosion Inhibiting fillet Consistency (Mat No. 09-016B) to the interfaces of the structure and all 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 at FR42 (if installed). Refer to Figure 1 a Remove : Refer to Figure 1 , Sheets 1 and 2

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 4 Screw Item (1) Retain 5 Washer Item (2) Retain 3 Screw Item (3) Retain 2 Screw Item (4) Retain 2 Nut Item (5) Discard 2 Circlip Item (6) Retain 2 Nut Item (7) Retain 2 Nut Item (8) Discard 6 Screw Item (9) Retain 6 Washer Item (10) Retain 1 Sleeve Item (11) Retain 6 Nut Item (12) Discard 1 Pipe assy Item (13) Retain 1 Machined tee Item (14) Retain

1 non return valve 176QM Item (15) Retain

2 Screw Item (17) Retain 2 Nut Item (8) Discard 2 Bolt Item (16) Retain 2 Washer Item (10) Retain 2 Nut Item (12) Discard 1 Elbow Item (18) Retain 1 Pipe Item (19) Retain

2 Screw Item (3) Retain 3 Nut Item (8) Discard 2 Screw Item (16) Retain 4 Washer Item (10) Retain 4 Nut Item (12) Discard 2 Screw Item (9) Retain 1 Screw Item (17) Retain 1 Pipe Item (20) Retain 1 Elbow Item (21) Retain 1 Sleeve Item (22) Retain 1 Nut Item (24) Retain 1 Circlip Item (23) Retain 1 Pipe Item (25) Retain 1 Elbow Item (26) Retain 1 Pipe Item (27) Retain

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved d Remove : Refer to Figure 1 , Sheets 1 thru 5

e Remove : Refer to Figure 1 , Sheets 1 thru 6

with :

attached with :

2 Remove the pipes and support of the diffuser in the RH center wing box at FR42. Refer to Figure 2 a Remove :

attached with :

b Remove :

attached with : 3 Screw Item (17) Retain 3 Nut Item (8) Discard 1 Pipe Item (29) Retain 1 Pipe Item (30) Retain

1 Pipe Item (31) Retain
1 Elbow Item (32) Retain 1 Pipe Item (33) Retain
2 Screw Item (4) Retain 2 Nut Item (5) Discard 1 Screw Item (3) Retain 1 Washer Item (2) Retain 4 Screw Item (28) Retain 4 Nut Item (8) Discard

1 Elbow Item (34) Retain 1 Pipe assy Item (35) Retain
4 Screw Item (36) Retain 4 Washer Item (37) Retain 1 Screw Item (38) Retain 1 Nut Item (39) Discard
1 Support Item (40) Retain
2 Screw Item (41) Retain

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 3 Remove the LH and RH jet pump circuits between FR41 and FR42. Refer to Figure 3 a Remove the LH jet pump circuit between FR41 and FR42. Refer to Figure 3 — Remove : Refer to Figure 3

attached with :

b Remove the RH jet pump circuit between FR41 and FR42. Refer to Figure 3 — Remove : Refer to Figure 3

attached with :

4 Remove the oblique strut and its support between FR41 and FR42. Refer to Figure 4 a Remove : Refer to Figure 4 1 Pipe assy Item (42) Retain 1 LH Elbow Item (43) Retain 1 Pipe assy Item (45) Retain 1 Adaptor assy Item (46) Retain
2 Screw Item (38) Retain 1 Nut Item (39) Discard 1 Nut Item (47) Discard

1 Pipe assy Item (42) Retain 1 RH Elbow Item (44) Retain 1 Pipe assy Item (45) Retain 1 Adaptor assy Item (46) Retain
2 Screw Item (38) Retain 1 Nut Item (39) Discard 1 Nut Item (47) Discard

1 oblique strut Item (48) Retain

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved attached with :

b Remove : Refer to Figure 4

attached with :

5 Remove the sensor FIN 22QJ, the harness FIN 18QT from the sensor FIN 22QJ and the harnesses FIN 17QT and FIN 18QT 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 sensor FIN 22QJ : Refer to Figure 5 , Sheets 1 thru 3

attached with :

c Attach the cable FIN 18QT on the box upper. 2 Screw Item (49) Retain 2 Washer Item (10) Retain 2 Nut Item (5) Discard

1 Support Item (50) Retain 1 Support Item (51) Retain 1 Support Item (52) Retain
2 Screw Item (53) Retain 1 Screw Item (54) Retain 3 Nut Item (55) Discard

1 Sensor 22QJ Item (56) Retain
2 Screw Item (57) Retain 2 Nut Item (8) Discard

1 Harness 18QT Item (58) Retain
2 Screw Item (59) Retain 2 Washer Item (2) Retain 5 Collar Item (60) Retain 4 Screw Item (17) Retain 4 Nut Item (8) Discard 1 Collar Item (61) Retain 4 Collar Item (62) Retain

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved d Remove the harnesses FIN 17QT and FIN 18QT from the ultracomp. FIN 50QT. Refer to Figure 5 — Remove : Refer to Figure 5 , Sheet 4

attached with :

6 Remove the air conditioning system between FR34 and FR36 in the cargo compartment. Refer to Figure 7 a Remove :

b Remove :

attached with :

7 Remove the fittings of the vapor seal between FR36 and FR40. Refer to Figure 8 a Make a mark on the fitting of the vapor seal before its removal to show the location. 1 Harness 17QT Item (64) Retain 1 Harness 18QT Item (58) Retain
2 Nut Item (65) Discard 2 Nut Item (66) Discard 1 Nut Item (67) Discard 2 Washer Item (70) Retain 2 Washer Item (69) Retain 1 Washer Item (68) Retain 4 Screw Item (63) Retain 4 Nut Item (8) Discard 3 Collar Item (60) Retain 1 Collar Item (61) Retain 4 Collar Item (62) Retain

1 Duct assy Item (88) Retain 1 Duct assy Item (89) Retain
1 Duct assy Item (90) Retain 1 Duct assy Item (91) Retain
4 Bolt Item (92) Retain 4 Washer Item (93) Retain 4 Nut Item (94) Discard

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved b Remove : NOTE : During the removal of the Screws of the fitting of vapor seal, make sure that there are not interferences with another part.

attached with :

c Remove : NOTE : During the removal of the Screws of the fitting of vapor seal, make sure that there are not interferences with another part.

attached with :

d Remove : NOTE : During the removal of the screws of the fitting of vapor seal, make sure that there are no interferences with another part.

attached with :

e Remove : NOTE : During the removal of the screws of the fitting of vapor seal, make sure that there are no interferences with another part.

attached with : 1 Fitting Item (95) Retain
3 Screw Item (96) Discard 1 Screw Item (53) Discard 3 Nut Item (97) Discard 1 Nut Item (55) Discard

1 Fitting Item (98) Retain
4 Screw Item (99) Discard 4 Nut Item (97) Discard

1 Fitting Item (100) Retain
2 Screw Item (99) Discard 2 Screw Item (101) Discard 4 Nut Item (97) Discard

1 Fitting Item (102) Retain
2 Screw Item (96) Discard 2 Screw Item (53) Discard

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved f Remove : NOTE : During the removal of the screws of the fitting of vapor seal, make sure that there are no interferences with another part.

attached with :

g Remove : NOTE : During the removal of the screws of the fitting of vapor seal, make sure that there are no 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 center wing box, every rib pad should be removed and installed before the removal of another one. You must remove/install the rib pads and the associated struts in this sequence : Y - 1292 Y + 254 Y - 765 Y + 765 Y - 254 2 Nut Item (97) Discard 2 Nut Item (55) Discard

1 Fitting Item (103) Retain
4 Screw Item (96) Discard 4 Nut Item (97) Discard

1 Fitting Item (104) Retain
1 Screw Item (105) Discard 1 Screw Item (96) Discard 2 Screw Item (99) Discard 3 Nut Item (97) Discard 1 Nut Item (55) Discard

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Y + 1292 NOTE (02) You can remove a rib pad and start to remove another one if you do not remove all the fasteners of the second rib pad. a Remove the struts and the rib pad at Y - 1292. Refer to Figure 6 Refer to Figure 9 , Sheets 1 thru 3 and 9 thru 11 — Remove the struts : Refer to Figure 6

attached with :

NOTE : Remove the strut Item (79) only if necessary. attached with :

— Remove the rib pad : Refer to Figure 9 , Sheets 1 thru 3 and 9 thru 11

attached with : 1 Bonding Lead Item (71) Retain 1 Bonding Lead Item (72) Retain 1 Bonding Lead Item (73) Retain
3 Nut Item (8) Discard 3 Screw Item (57) Retain 1 Strut Item (74) Retain 1 Strut Item (75) Retain 1 Strut Item (76) Retain 1 Strut Item (77) Retain 1 Strut Item (78) Retain 1 Strut Item (79) Retain

12 Cotter Pin Item (83) Discard 12 Nut Item (84) Discard 12 Washer Item (86) Retain

4 Axle Item (117) Retain 6 Axle Item (118) Retain 2 Axle Item (122) Retain

1 rib pad Item (106) Retain
17 Nut Item (55) Discard

6 Nut Item (97) Discard 1 Nut Item (108) Discard 10 Nut Item (110) Discard

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved and with the screws (Discard) as per Figure 9 , Sheets 1 thru 3 and 9 thru 11 . b Remove the struts and the rib pad at Y + 254. Refer to Figure 6 Refer to Figure 9 , Sheets 1 , 2 , 6 and 9 thru 11 — Remove the struts : Refer to Figure 6

attached with :

NOTE : Remove the strut Item (82) only if necessary. attached with :

— Remove the rib pad : Refer to Figure 9 , Sheets 1 , 2 , 6 and 9 thru 11 46 Nut Item (116) Discard 20 Nut Item (123) Discard

1 Screw Item (113) Discard 2 Screw Item (114) Discard 1 Screw Item (115) Discard

3 Bonding Lead Item (71) Retain 1 Bonding Lead Item (72) Retain
4 Nut Item (8) Discard 4 Screw Item (57) Retain 1 Strut Item (74) Retain 1 Strut Item (75) Retain 1 Strut Item (76) Retain 1 Strut Item (77) Retain 1 Strut Item (80) Retain 1 Strut Item (81) Retain 1 Strut Item (82) Retain

14 Cotter Pin Item (83) Discard

8 Nut Item (84) Discard 6 Nut Item (85) Discard 8 Washer Item (86) Retain 6 Washer Item (87) Retain 4 Axle Item (117) Retain 4 Axle Item (118) Retain 2 Axle Item (119) Retain 2 Axle Item (120) Retain 2 Axle Item (121) Retain

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved attached with :

and with the screws (Discard) as per Figure 9 , Sheets 1 , 2 , 6 and 9 thru 11 . c Remove the struts and the rib pad at Y - 765. Refer to Figure 6 Refer to Figure 9 , Sheets 1 , 2 , 4 and 9 thru 11 — Remove the struts : Refer to Figure 6

attached with :

NOTE : Remove the strut Item (79) only if necessary. attached with : 1 Rib Pad Item (125) Retain
45 Nut Item (55) Discard 10 Nut Item (97) Discard

1 Nut Item (108) Discard 16 Nut Item (110) Discard 42 Nut Item (116) Discard

1 Screw Item (109) Discard 2 Screw Item (111) Discard 1 Screw Item (112) Discard

1 Bonding Lead Item (71) Retain 1 Bonding Lead Item (72) Retain 1 Bonding Lead Item (73) Retain
3 Nut Item (8) Discard 3 Screw Item (57) Retain 1 Strut Item (74) Retain 1 Strut Item (75) Retain 1 Strut Item (76) Retain 1 Strut Item (77) Retain 1 Strut Item (78) Retain 1 Strut Item (79) Retain

12 Cotter Pin Item (83) Discard 12 Nut Item (84) Discard 12 Washer Item (86) Retain

4 Axle Item (117) Retain 6 Axle Item (118) Retain 2 Axle Item (122) Retain

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 , 4 and 9 thru 11

attached with :

and with the screws (Discard) as per Figure 9 , Sheets 1 , 2 , 4 and 9 thru 11 . d Remove the struts and the rib pad at Y + 765. Refer to Figure 6 Refer to Figure 9 , Sheets 1 , 2 , 7 and 9 thru 11 — Remove the struts : Refer to Figure 6

attached with :

NOTE : Remove the strut Item (79) only if necessary. attached with : 1 Rib Pad Item (106) Retain
15 Nut Item (55) Discard

6 Nut Item (97) Discard 1 Nut Item (108) Discard 10 Nut Item (110) Discard 46 Nut Item (116) Discard 22 Nut Item (123) Discard

1 Screw Item (113) Discard 2 Screw Item (114) Discard 1 Screw Item (115) Discard 1 Plate Item (124) Retain

1 Bonding Lead Item (71) Retain 1 Bonding Lead Item (72) Retain 1 Bonding Lead Item (73) Retain
3 Nut Item (8) Discard 3 Screw Item (57) Retain 1 Strut Item (74) Retain 1 Strut Item (75) Retain 1 Strut Item (76) Retain 1 Strut Item (77) Retain 1 Strut Item (78) Retain 1 Strut Item (79) Retain

12 Cotter Pin Item (83) Discard 12 Nut Item (84) Discard

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 , 7 and 9 thru 11

attached with :

and with the screws (Discard) as per Figure 9 , Sheets 1 , 2 , 7 and 9 thru 11 . e Remove the struts and the rib pad at Y - 254. Refer to Figure 6 Refer to Figure 9 , Sheets 1 , 2 , 5 and 9 thru 11 — Remove the struts : Refer to Figure 6

attached with :

NOTE : Remove the strut Item (82) only if necessary. 12 Washer Item (86) Retain

4 Axle Item (117) Retain 6 Axle Item (118) Retain 2 Axle Item (122) Retain

1 Rib Pad Item (106) Retain
15 Nut Item (55) Discard

6 Nut Item (97) Discard 1 Nut Item (108) Discard 10 Nut Item (110) Discard 46 Nut Item (116) Discard 22 Nut Item (123) Discard

1 Screw Item (113) Discard 2 Screw Item (114) Discard 1 Screw Item (115) Discard

3 Bonding Lead Item (71) Retain 1 Bonding Lead Item (72) Retain
4 Nut Item (8) Discard 4 Screw Item (57) Retain 1 Strut Item (74) Retain 1 Strut Item (75) Retain 1 Strut Item (76) Retain 1 Strut Item (77) Retain 1 Strut Item (80) Retain 1 Strut Item (81) Retain 1 Strut Item (82) Retain

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved attached with :

— Remove the rib pad : Refer to Figure 9 , Sheets 1 , 2 , 5 and 9 thru 11

attached with :

and with the screws (Discard) as per Figure 9 , Sheets 1 , 2 , 5 and 9 thru 11 . f Remove the struts and the rib pad at Y + 1292. Refer to Figure 6 Refer to Figure 9 , Sheets 1 , 2 and 8 thru 11 — Remove the struts : Refer to Figure 6

attached with : 14 Cotter Pin Item (83) Discard

8 Nut Item (84) Discard 6 Nut Item (85) Discard 8 Washer Item (86) Retain 6 Washer Item (87) Retain 4 Axle Item (117) Retain 4 Axle Item (118) Retain 2 Axle Item (119) Retain 2 Axle Item (120) Retain 2 Axle Item (121) Retain

1 Rib Pad Item (125) Retain
45 Nut Item (55) Discard 10 Nut Item (97) Discard

1 Nut Item (108) Discard 16 Nut Item (110) Discard 42 Nut Item (116) Discard

1 Screw Item (109) Discard 2 Screw Item (111) Discard 1 Screw Item (112) Discard

1 Bonding Lead Item (71) Retain 1 Bonding Lead Item (72) Retain 1 Bonding Lead Item (73) Retain
3 Nut Item (8) Discard 3 Screw Item (57) Retain 1 Strut Item (74) Retain 1 Strut Item (75) Retain

31

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : Remove the strut Item (79) only if necessary. attached with :

— Remove the rib pad : Refer to Figure 9 , Sheets1,2,8 thru 11

attached with :

and with the screws (Discard) as per Figure 9 , Sheets 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 fasteners. Refer to Figure 1 thru 8 NOTE (01) To have sufficient stiffness of the center wing box, every rib pad should be removed and installed before the removal of another one. You must remove/install the rib pads and the associated struts in this sequence : 1 Strut Item (76) Retain 1 Strut Item (77) Retain 1 Strut Item (78) Retain 1 Strut Item (79) Retain

12 Cotter Pin Item (83) Discard 12 Nut Item (84) Discard 12 Washer Item (86) Retain

4 Axle Item (117) Retain 6 Axle Item (118) Retain 2 Axle Item (122) Retain

1 Rib Pad Item (106) Retain
19 Nut Item (55) Discard

6 Nut Item (97) Discard 1 Nut Item (108) Discard 10 Nut Item (110) Discard 46 Nut Item (116) Discard 18 Nut Item (123) Discard

1 Screw Item (113) Discard 2 Screw Item (114) Discard 1 Screw Item (115) Discard

32

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Y - 1292 Y + 254 Y - 765 Y + 765 Y - 254 Y + 1292 NOTE (02) For the replacement of the nominal fasteners for the installation of the rib pads, refer to the Kit 571120A01R05 . 1 Install the rib pad and the struts at Y - 1292. Refer to Figure 6 refer to Figure 9 , Sheets 1 thru 3 and 9 thru 11 a Install the rib pad : refer to Figure 9 , Sheets 1 thru 3 and 9 thru 11

attach with :

NOTE : Item (106) was retained at removal. 1 Rib Pad Item (106)

19 Nut ASNA2536-5 Item 55

6 Nut ASNA2536-4 Item 97 1 Nut ASNA2536-7 Item 108 10 Nut ASNA2536-6 Item 110 46 Nut ASNA2528-4 Item 116 20 Nut ASNA2528-5 Item 123

4 Screw NSA5479BV4-11 Item 96 14 Screw NSA5479BV4-7 Item 152

8 Screw NSA5479BV5-12 Item 153 12 Screw NSA5479BV4-8 Item 155 14 Screw NSA5479BV4-9 Item 156

4 Screw NSA5479VHK6-14 Item 157 20 Screw NSA5479BV5-9 Item 158

2 Screw NSA5479BV5-13 Item 105 4 Screw NSA5479VHK6-15 Item 159 6 Screw NSA5479BV4-10 Item 99 6 Screw NSA5479BV5-14 Item 53 2 Screw NSA5479BV5-17 Item 160 2 Screw NSA5479BV4-14 Item 161 1 Screw NSA5479BV7-29 Item 113 2 Screw NSA5479BV6-23 Item 114 1 Screw NSA5479BV5-20 Item 115

33

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved b Install the struts :

NOTE : Install the Strut Item (79) only if removed. attach with :

NOTE (01) Install axles Items (117), (118) and (122) with Synthe. Hydrocarbon Grease High Pressure (Mat No. 04-022) . NOTE (02) Wet assembly under all the heads of screws with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . NOTE (03) The end of cotter pin Item 83 must be carrefully folded against Items nuts Item 84. NOTE (04) Protect the head of axles Items (117), (118) and (122) with Polyurethane Primer (Mat No. 16-001C) . NOTE : Items (74), (75), (76), (77), (78), (79), (86), (117), (118) and (122) were retained at removal.

attach with :

NOTE : Items (57), (71), (72) and (73) were retained at removal. 2 Install the rib pad and the struts at Y + 254.

1 Strut Item (74) 1 Strut Item (75) 1 Strut Item (76) 1 Strut Item (77) 1 Strut Item (78) 1 Strut Item (79)

4 Axle Item (117) 6 Axle Item (118) 2 Axle Item (122) 12 Cotter Pin MS24665-153 Item 83 12 Nut NSA5060-5 Item 84 12 Washer Item (86)

1 Bonding Lead Item (71) 1 Bonding Lead Item (72) 1 Bonding Lead Item (73)

3 Nut NSA5050-3 Item 8 3 Screw Item (57)

34

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 , 2 , 6 and 9 thru 11 a Install the rib pad : Refer to Figure 9 , Sheets 1 , 2 , 6 and 9 thru 11

attach with :

NOTE : Item (125) was retained at removal. b Install the struts : Refer to Figure 6 1 Rib Pad Item (125)

47 Nut ASNA2536-5 Item 55 10 Nut ASNA2536-4 Item 97

1 Nut ASNA2536-7 Item 108 16 Nut ASNA2536-6 Item 110 42 Nut ASNA2528-4 Item 116

4 Screw NSA5479BV4-11 Item 96 12 Screw NSA5479BV4-7 Item 152

8 Screw NSA5479BV5-12 Item 153 14 Screw NSA5479BV4-8 Item 155 13 Screw NSA5479BV4-9 Item 156 16 Screw NSA5479BV5-13 Item 105

2 Screw NSA5479BV4-12 Item 101 10 Screw NSA5479BV5-15 Item 41

4 Screw NSA5479VHK6-17 Item 164 2 Screw NSA5479VHK6-15 Item 159 2 Screw NSA5479BV5-18 Item 54 3 Screw NSA5479BV4-10 Item 99 2 Screw NSA5479BV4-13 Item 154 6 Screw NSA5479BV5-14 Item 53 2 Screw NSA5479BV5-17 Item 160 2 Screw NSA5479BV4-14 Item 161 8 Screw NSA5479BV6-22 Item 162 2 Screw NSA5479BV5-19 Item 163 1 Screw NSA5479BV7-30 Item 109 2 Screw NSA5479BV6-25 Item 111 1 Screw NSA5479BV5-21 Item 112

1 Strut Item (74) 1 Strut Item (75) 1 Strut Item (76) 1 Strut Item (77) 1 Strut Item (80) 1 Strut Item (81) 1 Strut Item (82)

35

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : Install the Strut Item (82) only if removed. attach with :

NOTE (01) Install axles Items (117), (118), (119), (120) and (121) with Synthe. Hydrocarbon Grease High Pressure (Mat No. 04-022) . NOTE (02) Wet assembly under all the heads of screws with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . NOTE (03) The end of cotter pin Item 83 must be carrefully folded against Items nuts Item 84 or 85. NOTE (04) Protect the head of axles Items (117), (118), (119), (120) and (121) with Polyurethane Primer (Mat No. 16-001C) . NOTE : Items (74), (75), (76), (77), (80), (81), (82), (86), (87), (117), (118), (119), (120) and (121) were retained at removal.

attach with :

NOTE : Items (57), (71) and (72) were retained at removal. 3 Install the rib pad and the struts at Y - 765. Refer to Figure 6 Refer to Figure 9 , Sheets 1 , 2 , 4 and 9 thru 11 4 Axle Item (117) 4 Axle Item (118) 2 Axle Item (119) 2 Axle Item (120) 2 Axle Item (121) 14 Cotter Pin MS24665-153 Item 83

8 Nut NSA5060-5 Item 84 6 Nut NSA5060-6 Item 85 8 Washer Item (86) 6 Washer Item (87)

3 Bonding Lead Item (71) 1 Bonding Lead Item (72)

4 Nut NSA5050-3 Item 8 4 Screw Item (57)

36

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved a Install the rib pad : Refer to Figure 9 , Sheets 1 , 2 , 4 and 9 thru 11

attach with :

NOTE : Items (106) and (124) were retained at removal. b Install the struts : Refer to Figure 6

NOTE : Install the strut Item (79) only if removed. attach with : 1 Rib Pad Item (106)
1 Plate Item (124) 16 Nut ASNA2536-5 Item 55

6 Nut ASNA2536-4 Item 97 1 Nut ASNA2536-7 Item 108 10 Nut ASNA2536-6 Item 110 22 Nut ASNA2528-5 Item 123 46 Nut ASNA2528-4 Item 116

4 Screw NSA5479BV4-11 Item 96 13 Screw NSA5479BV4-7 Item 152

9 Screw NSA5479BV5-12 Item 153 14 Screw NSA5479BV4-8 Item 155 13 Screw NSA5479BV4-9 Item 156

4 Screw NSA5479VHK6-14 Item 157 20 Screw NSA5479BV5-9 Item 158

4 Screw NSA5479VHK6-15 Item 159 6 Screw NSA5479BV4-10 Item 99 6 Screw NSA5479BV5-14 Item 53 2 Screw NSA5479BV5-17 Item 160 2 Screw NSA5479BV4-14 Item 161 1 Screw NSA5479BV7-29 Item 113 2 Screw NSA5479BV6-23 Item 114 1 Screw NSA5479BV5-20 Item 115

1 Strut Item (74) 1 Strut Item (75) 1 Strut Item (76) 1 Strut Item (77) 1 Strut Item (78) 1 Strut Item (79)

4 Axle Item (117) 6 Axle Item (118) 2 Axle Item (122)

37

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE (01) Install axles Items (117), (118) and (122) with Synthe. Hydrocarbon Grease High Pressure (Mat No. 04-022) . NOTE (02) Wet assembly under all the heads of screws with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . NOTE (03) The end of cotter pin Item 83 must be carrefully folded against Items nuts Item 84. NOTE (04) Protect the head of axles Items (117), (118) and (122) with Polyurethane Primer (Mat No. 16-001C) . NOTE : Items (74), (75), (76), (77), (78), (79), (86), (117), (118) and (122) were retained at removal.

attach with :

NOTE : Items (57), (71), (72) and (73) were retained at removal. 4 Install the rib pad and the struts at Y + 765. Refer to Figure 6 Refer to Figure 9 , Sheets 1 , 2 , 7 and 9 thru 11 a Install the rib pad : Refer to Figure 9 , Sheets 1 , 2 , 7 and 9 thru 11

attach with : 12 Cotter Pin MS24665-153 Item 83 12 Nut NSA5060-5 Item 84 12 Washer Item (86)

1 Bonding Lead Item (71) 1 Bonding Lead Item (72) 1 Bonding Lead Item (73)

3 Nut NSA5050-3 Item 8 3 Screw Item (57)

1 Rib Pad Item (106)

16 Nut ASNA2536-5 Item 55

6 Nut ASNA2536-4 Item 97 1 Nut ASNA2536-7 Item 108

38

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 removed. attach with :

NOTE (01) Install axles Items (117), (118) and (122) with Synthe. Hydrocarbon Grease High Pressure (Mat No. 04-022) . NOTE (02) Wet assembly under all the heads of screws with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . 10 Nut ASNA2536-6 Item 110 46 Nut ASNA2528-4 Item 116 22 Nut ASNA2528-5 Item 123

4 Screw NSA5479BV4-11 Item 96 13 Screw NSA5479BV4-7 Item 152

7 Screw NSA5479BV5-12 Item 153 14 Screw NSA5479BV4-8 Item 155 13 Screw NSA5479BV4-9 Item 156

4 Screw NSA5479VHK6-14 Item 157 22 Screw NSA5479BV5-9 Item 158

4 Screw NSA5479VHK6-15 Item 159 6 Screw NSA5479BV4-10 Item 99 6 Screw NSA5479BV5-14 Item 53 2 Screw NSA5479BV5-17 Item 160 2 Screw NSA5479BV4-14 Item 161 1 Screw NSA5479BV7-29 Item 113 2 Screw NSA5479BV6-23 Item 114 1 Screw NSA5479BV5-20 Item 115

1 Strut Item (74) 1 Strut Item (75) 1 Strut Item (76) 1 Strut Item (77) 1 Strut Item (78) 1 Strut Item (79)

4 Axle Item (117) 6 Axle Item (118) 2 Axle Item (122) 12 Cotter Pin MS24665-153 Item 83 12 Nut NSA5060-5 Item 84 12 Washer Item (86)

39

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE (03) The end of cotter pin Item 83 must be carrefully folded against Items nuts Item 84. NOTE (04) Protect the head of axles Items (117), (118) and (122) with Polyurethane Primer (Mat No. 16-001C) . NOTE : Items (74), (75), (76), (77), (78), (79), (86), (117), (118) and (122) were retained at removal.

attach with :

NOTE : Items (57), (71), (72) and (73) were retained at 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 thru 11 a Install the rib pad : Refer to Figure 9 , Sheets 1 , 2 , 5 and 9 thru 11

attach with : 1 Bonding Lead Item (71) 1 Bonding Lead Item (72) 1 Bonding Lead Item (73)

3 Nut NSA5050-3 Item 8 3 Screw Item (57)

1 Rib Pad Item (125)

47 Nut ASNA2536-5 Item 55

8 Nut ASNA2536-4 Item 97 1 Nut ASNA2536-7 Item 108 16 Nut ASNA2536-6 Item 110 42 Nut ASNA2528-4 Item 116

2 Screw NSA5479BV4-11 Item 96 12 Screw NSA5479BV4-7 Item 152

8 Screw NSA5479BV5-12 Item 153 14 Screw NSA5479BV4-8 Item 155 13 Screw NSA5479BV4-9 Item 156 15 Screw NSA5479BV5-13 Item 105

2 Screw NSA5479BV4-12 Item 101 10 Screw NSA5479BV5-15 Item 41

4 Screw NSA5479VHK6-17 Item 164 2 Screw NSA5479VHK6-15 Item 159 2 Screw NSA5479BV5-18 Item 54 6 Screw NSA5479BV4-10 Item 99

40

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 removed. attach with :

NOTE (01) Install axles Items (117), (118), (119), (120) and (121) with Synthe. Hydrocarbon Grease High Pressure (Mat No. 04-022) . NOTE (02) Wet assembly under all the heads of screws with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . NOTE (03) The end of cotter pin Item 83 must be carrefully folded against Items nuts Item 84 or 85. 2 Screw NSA5479BV4-13 Item 154 4 Screw NSA5479BV5-14 Item 53 2 Screw NSA5479BV5-17 Item 160 2 Screw NSA5479BV4-14 Item 161 8 Screw NSA5479BV6-22 Item 162 2 Screw NSA5479BV5-19 Item 163 1 Screw NSA5479BV7-30 Item 109 2 Screw NSA5479BV6-25 Item 111 1 Screw NSA5479BV5-21 Item 112

1 Strut Item (74) 1 Strut Item (75) 1 Strut Item (76) 1 Strut Item (77) 1 Strut Item (80) 1 Strut Item (81) 1 Strut Item (82)

4 Axle Item (117) 4 Axle Item (118) 2 Axle Item (119) 2 Axle Item (120) 2 Axle Item (121) 14 Cotter Pin MS24665-153 Item 83

8 Nut NSA5060-5 Item 84 6 Nut NSA5060-6 Item 85 8 Washer Item (86) 6 Washer Item (87)

41

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE (04) Protect the head of axles Items (117), (118), (119), (120) and (121) with Polyurethane Primer (Mat No. 16-001C) . NOTE : Items (74), (75), (76), (77), (80), (81), (82), (86), (87), (117), (118), (119), (120) and (121) were retained at removal.

attach with :

NOTE : Items (57), (71) and (72) were retained at removal. 6 Install the rib pad and the struts at Y + 1292. Refer to Figure 6 Refer to Figure 9 , Sheets1,2,8 thru 11 a Install the rib pad :

attach with : 3 Bonding Lead Item (71) 1 Bonding Lead Item (72)

4 Nut NSA5050-3 Item 8 4 Screw Item (57)

1 Rib Pad Item (106)

19 Nut ASNA2536-5 Item 55

6 Nut ASNA2536-4 Item 97 1 Nut ASNA2536-7 Item 108 10 Nut ASNA2536-6 Item 110 46 Nut ASNA2528-4 Item 116 18 Nut ASNA2528-5 Item 123

4 Screw NSA5479BV4-11 Item 96 12 Screw NSA5479BV4-7 Item 152

6 Screw NSA5479BV5-12 Item 153 14 Screw NSA5479BV4-8 Item 155 14 Screw NSA5479BV4-9 Item 156

4 Screw NSA5479VHK6-14 Item 157 18 Screw NSA5479BV5-9 Item 158

2 Screw NSA5479BV5-13 Item 105 4 Screw NSA5479VHK6-15 Item 159 2 Screw NSA5479BV5-18 Item 54 6 Screw NSA5479BV4-10 Item 99 6 Screw NSA5479BV5-14 Item 53 2 Screw NSA5479BV5-17 Item 160 2 Screw NSA5479BV4-14 Item 161 1 Screw NSA5479BV7-29 Item 113

42

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 removed. attach with :

NOTE (01) Install axles Items (117), (118) and (122) with Synthe. Hydrocarbon Grease High Pressure (Mat No. 04-022) . NOTE (02) Wet assembly under all the heads of screws with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . NOTE (03) The end of cotter pin Item 83 must be carrefully folded against Items nuts Item 84. NOTE (04) Protect the head of axles Items (117), (118) and (122) with Polyurethane Primer (Mat No. 16-001C) . NOTE : Items (74), (75), (76), (77), (78), (79), (86), (117), (118) and (122) were retained at removal.

attach with : 2 Screw NSA5479BV6-23 Item 114 1 Screw NSA5479BV5-20 Item 115

1 Strut Item (74) 1 Strut Item (75) 1 Strut Item (76) 1 Strut Item (77) 1 Strut Item (78) 1 Strut Item (79)

12 Cotter Pin MS24665-153 Item 83 12 Nut NSA5060-5 Item 84 12 Washer Item (86)

4 Axle Item (117) 6 Axle Item (118) 2 Axle Item (122)

1 Bonding Lead Item (71) 1 Bonding Lead Item (72) 1 Bonding Lead Item (73)

3 Nut NSA5050-3 Item 8

43

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : Items (57), (71), (72) and (73) were retained at removal. 7 Install the fittings of vapor seal between FR36 and FR40. Refer to Figure 8 NOTE : Install the fittings of vapor seal only after removal/installation of the rib pads and the associated struts (refer to ACCOMPLISHMENT 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 : 3 Screw Item (57)

1 Fitting Item (104)

1 Screw NSA5479BV5-13 Item 105

1 screw NSA5479BV5-13X Item 139 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 129

1 Fitting Item (103)

4 Screw NSA5479BV4-11 Item 96 4 Nut ASNA2536-4 Item 97

1 Fitting Item (102)

44

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved or if oversize :

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 Screw NSA5479BV4-11 Item 96 2 Screw NSA5479BV5-14 Item 53

2 Screw NSA5479BV5-14X Item 147 2 Nut ASNA2536-4 Item 97 2 Nut ASNA2536-5 Item 55

2 Nut NSA5050-5 Item 129

1 Fitting Item (100)

2 Screw NSA5479BV4-10 Item 99 2 Screw NSA5479BV4-12 Item 101

2 Screw NSA5479BV4-12X Item 140 2 Nut ASNA2536-4 Item 97

2 Nut NSA5050-4 Item 5

1 Fitting Item (98)

4 Screw NSA5479BV4-10 Item 99 4 Nut ASNA2536-4 Item 97

1 Fitting Item (95)

45

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved or if oversize :

or if oversize :
NOTE : Item (95) was retained at removal. 8 Install the air conditioning system between FR34 and FR36 in the cargo compartment. Refer to Figure 7 a Install :

attach with :

NOTE : Items (90), (91), (92) and (93) were retainer at removal. b Install :

NOTE : Items (88) and (89) were retainer at removal. 9 Install the sensor FIN 22QJ, the harness FIN 18QT on the sensor FIN 22QJ and the harnesses FIN 17QT and FIN 18QT on the ultracomp. FIN 50QT. Refer to Figure 5 a Install the harnesses FIN 17QT and FIN 18QT on the ultracomp. FIN 50QT. Refer to Figure 5 3 Screw NSA5479BV4-11 Item 96 1 Screw NSA5479BV5-14 Item 53

1 Screw NSA5479BV5-14X Item 147 3 Nut ASNA2536-4 Item 97 1 Nut ASNA2536-5 Item 55

1 Nut NSA5050-5 Item 129

1 Duct assy Item (90) 1 Duct assy Item (91)
4 Bolt Item (92) 4 Washer Item (93) 4 Nut MS21042-3 Item 94

1 Duct assy Item (88) 1 Duct assy Item (89)

46

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved — Install :

attach with :

NOTE : Items (58), (60), (61), (62), (63), (64), (68), (69) and (70) were retained at removal. b Install the sensor FIN 22QJ and the harness FIN 18QT on the sensor FIN 22QJ. — Install :

attach with :

NOTE : Items (2), (17), (58), (59), (60), (61) and (62) were retained at removal. — Install :

attach with : 1 Harness 17QT Item (64) 1 Harness 18QT Item (58)
2 Washer Item (70) 2 Washer Item (69) 1 Washer Item (68) 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 (60) 1 Collar Item (61) 4 Collar Item (62) 4 Screw Item (63)

1 Harness 18QT Item (58)
5 Collar Item (60) 1 Collar Item (61) 4 Collar Item (62) 2 Washer Item (2) 2 Screw Item (59) 4 Screw Item (17) 4 Nut NSA5050-3 Item 8

1 Sensor 22QJ Item (56)
2 Screw Item (57)

47

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : Items (56) and (57) were retained at removal. 10 Install the oblique struts and its support between FR41 and FR42. Refer to Figure 4 a Install :

Attach with :

NOTE : Install the supports Item (50), with Items (51) and (52) with Fuel Tank Sealant Polysulfide (Mat No. 09-002) . NOTE : Items (50), (51), (52), (53) and (54) were retained at removal. b Install :

attach with :

NOTE : Items (10), (48) and (49) were retained at removal. 11 Install the LH and RH jet pumps circuit between FR41 and FR42. Refer to Figure 3 a Install the RH jet pump circuit between FR41 and FR42. Refer to Figure 3 Install : 2 Nut NSA5050-3 Item 8

1 Support Item (50) 1 Support Item (51) 1 Support Item (52)
2 Screw Item (53) 1 Screw Item (54) 3 Nut ASNA2536-5 Item 55

1 Strut Oblique Item (48)
2 Screw Item (49) 2 Washer Item (10) 2 Nut NSA5050-4 Item 5

48

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved attach with :

NOTE : Items (38), (42), (44), (45) and (46) were retained at removal. b Install the LH jet pump circuit between FR41 and FR42. Refer to Figure 3 Install :

attach with :

NOTE : Items (38), (42), (43), (45) and (46) were retained at removal. 12 Install the pipes and support of the diffuser in the RH center wing box at FR42. Refer to Figure 2 a Install :

attach with :
NOTE : Items (40) and (41) were retained at removal. b Install on the diffuser 1 Pipe assy Item (42) 1 RH Elbow Item (44) 1 Pipe assy Item (45) 1 Adaptor assy Item (46)
2 Screw Item (38) 1 Nut NAS1726-3E Item 39 1 Nut MS21073L3 Item 47

1 Pipe assy Item (42) 1 RH Elbow Item (43) 1 Pipe assy Item (45) 1 Adaptor assy Item (46)
2 Screw Item (38) 1 Nut NAS1726-3E Item 39 1 Nut MS21073L3 Item 47

1 Support Item (40)
2 Screw Item (41)

49

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved attach with :

NOTE : Items (34), (35), (36), (37) and (38) were 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), (32) and (33) were retained at removal. b Install : Refer to Figure 1 , Sheets 1 thru 5 1 Pipe assy Item (35) 1 Elbow Item (34)
4 Screw Item (36) 4 Washer Item (37) 1 Screw Item (38) 1 Nut NAS1726-3E Item 39

1 Pipe Item (31)
1 Elbow Item (32) 1 Pipe Item (33)
2 Screw Item (4) 2 Nut NSA5050-4 Item 5 1 Screw Item (3) 1 Washer Item (2) 4 Screw Item (28) 8 Nut NSA5050-3 Item 8

1 Pipe Item (29) 1 Pipe Item (30) 3 Screw Item (17) 3 Nut NSA5050-3 Item 8

50

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : Items (17), (29) and (30) were retained at removal. c Install : Refer to Figure 1 , Sheets 1 thru 4

NOTE : Items (3), (9), (10), (16), (17), (20), (21), (22), (23), (24), (25), (26) and (27) were retained at removal. d Install : Refer to Figure 1 , Sheets 1 thru 3

NOTE : Items (10), (16), (17), (18) and (19) were retained at removal. e Install : Refer to Figure 1 , Sheets 1 thru 2 1 Pipe Item (27) 1 Elbow Item (26) 1 Pipe Item (25) 1 Sleeve Item (22) 1 Circlip Item (23) 1 Nut Item (24) 1 Elbow Item (21) 1 Pipe Item (20) 2 Screw Item (9) 4 Washer Item (10) 4 Nut NAS1726-4E Item 12 2 Screw Item (16) 1 Screw Item (17) 3 Nut NSA5050-3 Item 8 3 Screw Item (3)

1 Elbow Item (18) 1 Pipe Item (19) 2 Bolt Item (16) 2 Washer Item (10) 2 Nut NAS1726-4E Item 12 2 Screw Item (17) 2 Nut NSA5050-3 Item 8

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved with :

NOTE : Items (1), (2), (3), (4), (6), (7), (9), (10), (11), (13), (14) and (15) were retained at 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 at FR42 (if installed). Refer to Figure 1 a Remove : Refer to Figure 1 , Sheets 1 and 2 1 Sleeve Item (11) 2 Circlip Item (6) 2 Nut Item (7) 1 Machined tee Item (14)

1 Valve non return 176QM Item (15) 6 Screw Item (9) 6 Washer Item (10) 6 Nut NAS1726-4E Item 12 2 Nut NSA5050-3 Item 8 1 Pipe assy Item (13) 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) Retain 5 Washer Item (2) Retain 3 Screw Item (3) Retain 2 Screw Item (4) Retain 2 Nut Item (5) Discard 2 Circlip Item (6) Retain 2 Nut Item (7) Retain 2 Nut Item (8) Discard 6 Screw Item (9) Retain 6 Washer Item (10) Retain

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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

d Remove : Refer to Figure 1 , Sheets 1 thru 5

e Remove : 1 Sleeve Item (11) Retain 6 Nut Item (12) Discard 1 Pipe assy Item (13) Retain 1 Machined tee Item (14) Retain

1 non return valve 176QM Item (15) Retain

2 Screw Item (17) Retain 2 Nut Item (8) Discard 2 Bolt Item (16) Retain 2 Washer Item (10) Retain 2 Nut Item (12) Discard 1 Elbow Item (18) Retain 1 Pipe Item (19) Retain

2 Screw Item (3) Retain 3 Nut Item (8) Discard 2 Screw Item (16) Retain 4 Washer Item (10) Retain 4 Nut Item (12) Discard 2 Screw Item (9) Retain 1 Screw Item (17) Retain 1 Pipe Item (20) Retain 1 Elbow Item (21) Retain 1 Sleeve Item (22) Retain 1 Nut Item (24) Retain 1 Circlip Item (23) Retain 1 Pipe Item (25) Retain 1 Elbow Item (26) Retain 1 Pipe Item (27) Retain

3 Screw Item (17) Retain 3 Nut Item (8) Discard 1 Pipe Item (29) Retain 1 Pipe Item (30) Retain

53

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Refer to Figure 1 , Sheets 1 thru 6

with :

attached with :

2 Remove the pipes and support of the diffuser in the RH 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 between FR41 and FR42. Refer to Figure 3 a Remove the LH jet pump circuit between FR41 and FR42. Refer to Figure 3 — Remove : 1 Pipe Item (31) Retain
1 Elbow Item (32) Retain 1 Pipe Item (33) Retain
2 Screw Item (4) Retain 2 Nut Item (5) Discard 1 Screw Item (3) Retain 1 Washer Item (2) Retain 4 Screw Item (28) Retain 4 Nut Item (8) Discard

1 Elbow Item (34) Retain 1 Pipe assy Item (35) Retain
4 Screw Item (36) Retain 4 Washer Item (37) Retain 1 Screw Item (38) Retain 1 Nut Item (39) Discard
1 Support Item (40) Retain
2 Screw Item (41) Retain

54

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Refer to Figure 3

attached with :

b Remove the RH jet pump circuit between FR41 and FR42. Refer to Figure 3 — Remove : Refer to Figure 3

attached with :

4 Remove the strut oblique and its support between FR41 and FR42. Refer to Figure 4 a Remove : Refer to Figure 4

attached with :

b Remove : Refer to Figure 4 1 Pipe assy Item (42) Retain 1 LH Elbow Item (43) Retain 1 Pipe assy Item (45) Retain 1 Adaptor assy Item (46) Retain
2 Screw Item (38) Retain 1 Nut Item (39) Discard 1 Nut Item (47) Discard

1 Pipe assy Item (42) Retain 1 RH Elbow Item (44) Retain 1 Pipe assy Item (45) Retain 1 Adaptor assy Item (46) Retain
2 Screw Item (38) Retain 1 Nut Item (39) Discard 1 Nut Item (47) Discard

1 Strut Oblique Item (48) Retain
2 Screw Item (49) Retain 2 Washer Item (10) Retain 2 Nut Item (5) Discard

55

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved attached with :

5 Remove the sensor FIN 22QJ, the harness FIN 18QT from the sensor FIN 22QJ and the harnesses FIN 17QT and FIN 18QT 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 sensor FIN 22QJ : Refer to Figure 5 , Sheets 1 thru 3

attached with :

c Attach the cable FIN 18QT on the box upper. d Remove the harnesses FIN 17QT and FIN 18QT from the ultracomp. FIN 50QT. Refer to Figure 5 — Remove : Refer to Figure 5 , Sheet 4 1 Support Item (50) Retain 1 Support Item (51) Retain 1 Support Item (52) Retain
2 Screw Item (53) Retain 1 Screw Item (54) Retain 3 Nut Item (55) Discard

1 Sensor 22QJ Item (56) Retain
2 Screw Item (57) Retain 2 Nut Item (8) Discard

1 Harness 18QT Item (58) Retain
2 Screw Item (59) Retain 2 Washer Item (2) Retain 5 Collar Item (60) Retain 4 Screw Item (17) Retain 4 Nut Item (8) Discard 1 Collar Item (61) Retain 4 Collar Item (62) Retain

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved attached with :

6 Remove the air conditioning system between FR34 and FR36 in the cargo compartment. Refer to Figure 7 a Remove :

b Remove :

attached with :

7 Remove the fittings of the vapor seal between FR36 and FR40. Refer to Figure 12 a Make a mark on the fitting of the vapor seal before its removal to show the location. b Remove : NOTE : During the removal of the screws of the fitting of vapor seal, make sure that there are not interferences with another part. 1 Harness 17QT Item (64) Retain 1 Harness 18QT Item (58) Retain
2 Nut Item (65) Discard 2 Nut Item (66) Discard 1 Nut Item (67) Discard 2 Washer Item (70) Retain 2 Washer Item (69) Retain 1 Washer Item (68) Retain 4 Screw Item (63) Retain 4 Nut Item (8) Discard 3 Collar Item (60) Retain 1 Collar Item (61) Retain 4 Collar Item (62) Retain

1 Duct assy Item (88) Retain 1 Duct assy Item (89) Retain
1 Duct assy Item (90) Retain 1 Duct assy Item (91) Retain
4 Bolt Item (92) Retain 4 Washer Item (93) Retain 4 Nut Item (94) Discard

1 Fitting Item (95) Retain

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 the fitting of vapor seal, make sure that there are not interferences with another part.

attached with :

d Remove : NOTE : During the removal of the screws of the fitting of vapor seal, make sure that there are no interferences with another part.

attached with :

e Remove : NOTE : During the removal of the screws of the fitting of vapor seal, make sure that there are no interferences with another part.

attached with :

f Remove : NOTE : During the removal of the screws of the fitting of vapor seal, make sure that there are no interferences with another part. 3 Screw Item (96) Discard 1 Screw Item (53) Discard 3 Nut Item (97) Discard 1 Nut Item (55) Discard

1 Fitting Item (98) Retain
4 Screw Item (99) Discard 4 Nut Item (97) Discard

1 Fitting Item (100) Retain
2 Screw Item (99) Discard 2 Screw Item (101) Discard 4 Nut Item (97) Discard

1 Fitting Item (102) Retain
2 Screw Item (96) Discard 2 Screw Item (53) Discard 2 Nut Item (97) Discard 2 Nut Item (55) Discard

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 the fitting of vapor seal, make sure that there are no 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 center wing box, every rib pad should be removed and installed before the removal of another one. You must remove/install the rib pads and the 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 to remove another one if you do not remove all the fasteners of the second rib pad. a Remove the struts and the rib pad at Y - 1292. 1 Fitting Item (103) Retain
4 Screw Item (96) Discard 4 Nut Item (97) Discard

1 Fitting Item (104) Retain
1 Screw Item (105) Discard 1 Screw Item (96) Discard 2 Screw Item (99) Discard 3 Nut Item (97) Discard 1 Nut Item (55) Discard

59

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Refer to Figure 6 Refer to Figure 13 , Sheets 1 thru 3 , 9 , 11 and 12 — Remove the struts : Refer to Figure 6

attached with :

NOTE : Remove the strut Item (79) only if necessary. attached with :

— Remove the rib pad : Refer to Figure 13 , Sheets 1 thru 3 , 9 , 11 and 12

attached with : 1 Bonding Lead Item (71) Retain 1 Bonding Lead Item (72) Retain 1 Bonding Lead Item (73) Retain
3 Nut Item (8) Discard 3 Screw Item (57) Retain 1 Strut Item (74) Retain 1 Strut Item (75) Retain 1 Strut Item (76) Retain 1 Strut Item (77) Retain 1 Strut Item (78) Retain 1 Strut Item (79) Retain

12 Cotter Pin Item (83) Discard 12 Nut Item (84) Discard 12 Washer Item (86) Retain

4 Axle Item (117) Retain 6 Axle Item (118) Retain 2 Axle Item (122) Retain

1 Rib Pad Item (106) Retain
17 Nut Item (55) Discard

6 Nut Item (97) Discard 1 Nut Item (108) Discard 10 Nut Item (110) Discard 46 Nut Item (116) Discard 20 Nut Item (123) Discard

1 Screw Item (113) Discard 2 Screw Item (114) Discard 1 Screw Item (115) Discard

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved and with the screws (Discard) as per Figure 13 , Sheets 1 thru 3 , 9 , 11 and 12 . b Remove the struts and the rib pad at Y + 254. Refer to Figure 6 Refer to Figure 13 , Sheet s 1 , 2 , 6 and 9 thru 12 — Remove the struts : Refer to Figure 6

attached with :

NOTE : Remove the strut Item (82) only if necessary. attached with :

— Remove the rib pad : Refer to Figure 13 , Sheets 1 , 2 , 6 and 9 thru 12

attached with : 3 Bonding Lead Item (71) Retain 1 Bonding Lead Item (72) Retain
4 Nut Item (8) Discard 4 Screw Item (57) Retain 1 Strut Item (74) Retain 1 Strut Item (75) Retain 1 Strut Item (76) Retain 1 Strut Item (77) Retain 1 Strut Item (80) Retain 1 Strut Item (81) Retain 1 Strut Item (82) Retain

14 Cotter Pin Item (83) Discard

8 Nut Item (84) Discard 6 Nut Item (85) Discard 8 Washer Item (86) Retain 6 Washer Item (87) Retain 4 Axle Item (117) Retain 4 Axle Item (118) Retain 2 Axle Item (119) Retain 2 Axle Item (120) Retain 2 Axle Item (121) Retain

1 Rib Pad Item (125) Retain
45 Nut Item (55) Discard 10 Nut Item (97) Discard

61

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved and with the screws (Discard) as per Figure 13 , Sheet s 1 , 2 , 6 and 9 thru 12 . c Remove the struts and the rib pad at Y - 765. Refer to Figure 6 Refer to Figure 13 , Sheet s 1 , 2 , 4 , 9 11 and 12 — Remove the struts : Refer to Figure 6

attached with :

NOTE : Remove the strut Item (79) only if necessary. attached with :

— Remove the rib pad : Refer to Figure 13 , Sheets 1 , 2 , 4 , 9 11 and 12

attached with : 1 Nut Item (108) Discard 16 Nut Item (110) Discard 42 Nut Item (116) Discard

1 Screw Item (109) Discard 2 Screw Item (111) Discard 1 Screw Item (112) Discard

1 Bonding Lead Item (71) Retain 1 Bonding Lead Item (72) Retain 1 Bonding Lead Item (73) Retain
3 Nut Item (8) Discard 3 Screw Item (57) Retain 1 Strut Item (74) Retain 1 Strut Item (75) Retain 1 Strut Item (76) Retain 1 Strut Item (77) Retain 1 Strut Item (78) Retain 1 Strut Item (79) Retain

12 Cotter Pin Item (83) Discard 12 Nut Item (84) Discard 12 Washer Item (86) Retain

4 Axle Item (117) Retain 6 Axle Item (118) Retain 2 Axle Item (122) Retain

1 Rib Pad Item (106) Retain

62

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved and with the screws (Discard) as per Figure 13 , Sheet s 1 , 2 , 4 , 9 11 and 12 . d Remove the struts and the rib pad at Y + 765. Refer to Figure 6 Refer to Figure 13 , Sheet s 1 , 2 , 7 , 9 , 11 and 12 — Remove the struts : Refer to Figure 6

attached with :

NOTE : Remove the strut Item (79) only if necessary. attached with :

— Remove the rib pad : 15 Nut Item (55) Discard

6 Nut Item (97) Discard 1 Nut Item (108) Discard 10 Nut Item (110) Discard 46 Nut Item (116) Discard 22 Nut Item (123) Discard

1 Screw Item (113) Discard 2 Screw Item (114) Discard 1 Screw Item (115) Discard 1 Plate Item (124) Retain

1 Bonding Lead Item (71) Retain 1 Bonding Lead Item (72) Retain 1 Bonding Lead Item (73) Retain
3 Nut Item (8) Discard 3 Screw Item (57) Retain 1 Strut Item (74) Retain 1 Strut Item (75) Retain 1 Strut Item (76) Retain 1 Strut Item (77) Retain 1 Strut Item (78) Retain 1 Strut Item (79) Retain

12 Cotter Pin Item (83) Discard 12 Nut Item (84) Discard 12 Washer Item (86) Retain

4 Axle Item (117) Retain 6 Axle Item (118) Retain 2 Axle Item (122) Retain

63

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Refer to Figure 13 , Sheets 1 , 2 , 7 , 9 , 11 and 12

attached with :

and with the screws (Discard) as per Figure 13 , Sheet s 1 , 2 , 7 , 9 , 11 and 12 . e Remove the struts and the rib pad at Y - 254. Refer to Figure 6 Refer to Figure 13 , Sheet s 1 , 2 , 5 and 9 thru 12 — Remove the struts : Refer to Figure 6

attached with :

NOTE : Remove the strut Item (82) only if necessary. attached with : 1 Rib Pad Item (106) Retain
15 Nut Item (55) Discard

6 Nut Item (97) Discard 1 Nut Item (108) Discard 10 Nut Item (110) Discard 46 Nut Item (116) Discard 22 Nut Item (123) Discard

1 Screw Item (113) Discard 2 Screw Item (114) Discard 1 Screw Item (115) Discard

3 Bonding Lead Item (71) Retain 1 Bonding Lead Item (72) Retain
4 Nut Item (8) Discard 4 Screw Item (57) Retain 1 Strut Item (74) Retain 1 Strut Item (75) Retain 1 Strut Item (76) Retain 1 Strut Item (77) Retain 1 Strut Item (80) Retain 1 Strut Item (81) Retain 1 Strut Item (82) Retain

14 Cotter Pin Item (83) Discard

8 Nut Item (84) Discard 6 Nut Item (85) Discard 8 Washer Item (86) Retain 6 Washer Item (87) Retain

64

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 , 5 and 9 thru 12

attached with :

and with the screws (Discard) as per Figure 13 , Sheet s 1 , 2 , 5 and 9 thru 12 . f Remove the struts and the rib pad at Y + 1292. Refer to Figure 6 Refer to Figure 13 , Sheet s 1 , 2 and 8 thru 12 — Remove the struts : Refer to Figure 6

attached with :

NOTE : Remove the strut Item (79) only if necessary. 4 Axle Item (117) Retain 4 Axle Item (118) Retain 2 Axle Item (119) Retain 2 Axle Item (120) Retain 2 Axle Item (121) Retain

1 Rib Pad Item (125) Retain
45 Nut Item (55) Discard 10 Nut Item (97) Discard

1 Nut Item (108) Discard 16 Nut Item (110) Discard 42 Nut Item (116) Discard

1 Screw Item (109) Discard 2 Screw Item (111) Discard 1 Screw Item (112) Discard

1 Bonding Lead Item (71) Retain 1 Bonding Lead Item (72) Retain 1 Bonding Lead Item (73) Retain
3 Nut Item (8) Discard 3 Screw Item (57) Retain 1 Strut Item (74) Retain 1 Strut Item (75) Retain 1 Strut Item (76) Retain 1 Strut Item (77) Retain 1 Strut Item (78) Retain 1 Strut Item (79) Retain

65

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved attached with :

— Remove the rib pad : Refer to Figure 13 , Sheets 1 , 2 and 8 thru 12

attached with :

and with the screws (Discard) as per Refer to Figure 13 , Sheet s 1 , 2 and 8 thru 12 . (b) For the inspection area, refer to Figure 10 . (c) Do a special detailed visual inspection, refer to Figure 14 . 1 Do the rotating probe inspection : Refer to NTM 51-10-01 a If no crack is detected : — Oversize the holes, refer to ACCOMPLISHMENT INSTRUCTIONS paragraph C.(2) and refer to Figure 12 , Sheet 1 thru 5 and Figure 13 , Sheet 1 thru 12 . 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 and FR40. Refer to Figure 12 12 Cotter Pin Item (83) Discard 12 Nut Item (84) Discard 12 Washer Item (86) Retain

4 Axle Item (117) Retain 6 Axle Item (118) Retain 2 Axle Item (122) Retain

1 Rib Pad Item (106) Retain
19 Nut Item (55) Discard

6 Nut Item (97) Discard 1 Nut Item (108) Discard 10 Nut Item (110) Discard 46 Nut Item (116) Discard 18 Nut Item (123) Discard

1 Screw Item (113) Discard 2 Screw Item (114) Discard 1 Screw Item (115) Discard

66

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : Install the fittings of vapor seal only after removal/installation of the rib pads and the associated struts (refer to ACCOMPLISHMENT INSTRUCTIONS paragraph. C (2)). 1 Install :

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 Fitting Item (104)

1 Screw NSA5479BV5-13 Item 105

1 Screw NSA5479BV5-13X Item 139 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 129

1 Fitting Item (103)

4 Screw NSA5479BV4-11 Item 96 4 Nut ASNA2536-4 Item 97

1 Fitting Item (102)

2 Screw NSA5479BV4-11 Item 96 2 Screw NSA5479BV5-14 Item 53

2 Screw NSA5479BV5-14X Item 147 2 Nut ASNA2536-4 Item 97 2 Nut ASNA2536-5 Item 55

67

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : Item (102) was retained at removal. 4 Install :

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 Nut NSA5050-5 Item 129

1 Fitting Item (100)

2 Screw NSA5479BV4-10 Item 99 2 Screw NSA5479BV4-12 Item 101

2 Screw NSA5479BV4-12X Item 140 2 Nut ASNA2536-4 Item 97

2 Nut NSA5050-5 Item 129

1 Fitting Item (98)

4 Screw NSA5479BV4-10 Item 99 4 Nut ASNA2536-4 Item 97

1 Fitting Item (95)

3 Screw NSA5479BV4-11 Item 96 1 Screw NSA5479BV5-14 Item 53

1 Screw NSA5479BV5-14X Item 147 3 Nut ASNA2536-4 Item 97 1 Nut ASNA2536-5 Item 55

1 Nut NSA5050-5 Item 129

68

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : Item (95) was retained at removal. (f) Install the air conditioning system between FR34 and FR36 in the cargo compartment. Refer to Figure 7 1 Install :

attach with :

NOTE : Items (90), (91), (92) and (93) were retainer at removal. 2 Install :

NOTE : Items (88) and (89) were retainer at removal. (g) Install the sensor FIN 22QJ, the harness FIN 18QT on the sensor FIN 22QJ and the harnesses FIN 17QT and FIN 18QT on the ultracomp. FIN 50QT. Refer to Figure 5 1 Install the harnesses FIN 17QT and FIN 18QT on the ultracomp. FIN 50QT. Refer to Figure 5 a Install :

attach with : 1 Duct assy Item (90) 1 Duct assy Item (91)
4 Bolt Item (92) 4 Washer Item (93) 4 Nut MS21042-3 Item 94

1 Duct assy Item (88) 1 Duct assy Item (89)

1 Harness 17QT Item (64) 1 Harness 18QT Item (58)
2 Washer Item (70) 2 Washer Item (69) 1 Washer Item (68) 2 Nut MS21043-06 Item 65 2 Nut MS21043-08 Item 66

69

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : Items (58), (60), (61), (62), (63), (64), (68), (69) and (70) were retained at removal. 2 Install the sensor FIN 22QJ and the harness FIN 18QT on the sensor FIN 22QJ. a Install :

attach with :

NOTE : Items (2), (17), (58), (59), (60), (61) and (62) were retained at removal. b Install :

attach with :

NOTE : Items (56) and (57) were retained at removal. (h) Install the oblique struts and its support between FR41 and FR42. Refer to Figure 4 1 Install :

1 Nut NSA5474-3K7 Item 67 4 Nut NSA5050-3 Item 8 3 Collar Item (60) 1 Collar Item (61) 4 Collar Item (62) 4 Screw Item (63)

1 Harness 18QT Item (58)
5 Collar Item (60) 1 Collar Item (61) 4 Collar Item (62) 2 Washer Item (2) 2 Screw Item (59) 4 Screw Item (17) 4 Nut NSA5050-3 Item 8

1 Sensor 22QJ Item (56)
2 Screw Item (57) 2 Nut NSA5050-3 Item 8

1 Support Item (50) 1 Support Item (51) 1 Support Item (52)

70

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Attach with :

NOTE : Install the supports Item (50), with Items (51) and (52) with Fuel Tank Sealant Polysulfide (Mat No. 09-002) . NOTE : Items (50), (51), (52), (53) and (54) were retained at removal. 2 Install :

attach with :

NOTE : Items (10), (48) and (49) were retained at removal. (i) Install the LH and RH jet pumps circuit between FR41 and FR42. Refer to Figure 3 1 Install the RH jet pump circuit between FR41 and FR42. Refer to Figure 3

attach with :

NOTE : Items (38), (42), (44), (45) and (46) were retained at removal. 2 Install the LH jet pump circuit between FR41 and FR42. Refer to Figure 3 2 Screw Item (53) 1 Screw Item (54) 3 Nut ASNA2536-5 Item 55

1 Strut Oblique Item (48)
2 Screw Item (49) 2 Washer Item (10) 2 Nut NSA5050-4 Item 5

1 Pipe assy Item (42) 1 RH Elbow Item (44) 1 Pipe assy Item (45) 1 Adaptor assy Item (46)
2 Screw Item (38) 1 Nut NAS1726-3E Item 39 1 Nut MS21073L3 Item 47

71

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved attach with :

NOTE : Items (38), (42), (43), (45) and (46) were retained at removal. (j) Install the pipes and support of the diffuser in the RH center wing box at FR42. Refer to Figure 2 1 Install :

attach with :
NOTE : Items (40) and (41) were retained at removal. 2 Install on the diffuser

attach with :

NOTE : Items (34), (35), (36), (37) and (38) were retained at removal. (k) Install the ACT transfer at FR42 (if removed). Refer to Figure 1 1 Install : Refer to Figure 1 1 Pipe assy Item (42) 1 RH Elbow Item (43) 1 Pipe assy Item (45) 1 Adaptor assy Item (46)
2 Screw Item (38) 1 Nut NAS1726-3E Item 39 1 Nut MS21073L3 Item 47

1 Support Item (40)
2 Screw Item (41)

1 Pipe assy Item (35) 1 Elbow Item (34)
4 Screw Item (36) 4 Washer Item (37) 1 Screw Item (38) 1 Nut NAS1726-3E Item 39

72

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DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved with :

attach with :

NOTE : Items (2), (3), (4), (28), (31), (32) and (33) were retained at removal. 2 Install : Refer to Figure 1 , Sheets 1 thru 5

NOTE : Items (17), (29) and (30) were retained at removal. 3 Install : Refer to Figure 1 , Sheets 1 thru 4 1 Pipe Item (31)
1 Elbow Item (32) 1 Pipe Item (33)
2 Screw Item (4) 2 Nut NSA5050-4 Item 5 1 Screw Item (3) 1 Washer Item (2) 4 Screw Item (28) 8 Nut NSA5050-3 Item 8

1 Pipe Item (29) 1 Pipe Item (30) 3 Screw Item (17) 3 Nut NSA5050-3 Item 8

1 Pipe Item (27) 1 Elbow Item (26) 1 Pipe Item (25) 1 Sleeve Item (22) 1 Circlip Item (23) 1 Nut Item (24) 1 Elbow Item (21) 1 Pipe Item (20) 2 Screw Item (9) 4 Washer Item (10) 4 Nut NAS1726-4E Item 12

73

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : Items (3), (9), (10), (16), (17), (20), (21), (22), (23), (24), (25), (26) and (27) were retained at removal. 4 Install : Refer to Figure 1 , Sheets 1 thru 3

NOTE : Items (10), (16), (17), (18) and (19) were retained at removal. 5 Install : Refer to Figure 1 , Sheets 1 thru 2

with : 2 Screw Item (16) 1 Screw Item (17) 3 Nut NSA5050-3 Item 8 3 Screw Item (3)

1 Elbow Item (18) 1 Pipe Item (19) 2 Bolt Item (16) 2 Washer Item (10) 2 Nut NAS1726-4E Item 12 2 Screw Item (17) 2 Nut NSA5050-3 Item 8

1 Sleeve Item (11) 2 Circlip Item (6) 2 Nut Item (7) 1 Machined tee Item (14)

1 Valve non return 176QM Item (15) 6 Screw Item (9) 6 Washer Item (10) 6 Nut NAS1726-4E Item 12 2 Nut NSA5050-3 Item 8 1 Pipe assy Item (13) 4 Screw Item (1) 5 Washer Item (2)

74

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : Items (1), (2), (3), (4), (6), (7), (9), (10), (11), (13), (14) and (15) were retained at removal. C. REPAIR (1) Config. 01 (a) Replace the installation of the rib pads with oversize fasteners. Refer to Figure 6 Refer to Figure 9 NOTE : To have sufficient stiffness of the center wing box, every rib pad should be removed and installed before the removal of another one. You must remove/install the rib pads and the associated struts in this sequence : Y - 1292 Y + 254 Y - 765 Y + 765 Y - 254 Y + 1292 NOTE : For the replacement of the oversize fasteners for the installation of the rib pads, parts are to be supplied by : HONEYWELL HARDWARE PRODUCT GROUP LADEMANNBOGEN 128 HAMBOURG D22339 GERMANY 1 Install the rib pad and the struts at Y - 1292. Refer to Figure 6 Refer to Figure 9 , Sheets 1 thru 3 and 12 thru 14 3 Screw Item (3) 2 Screw Item (4) 2 Nut NSA5050-4 Item 5

75

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved a Install the rib pad : Refer to Figure 9 , Sheets 1 thru 3 and 12 thru 14

attach with :

NOTE : Item (106) was retained at removal. b Install the struts : Refer to Figure 6

NOTE : Install the strut Item (79) only if removed. attach with : 1 rib pad Item (106)

1 Nut ASNA2536-5 Item 55 18 Nut NSA5050-5 Item 129

6 Nut NSA5050-4 Item 5 1 Nut ASNA2536-7 Item 108 2 Nut ASNA2536-6 Item 110 8 Nut NSA5050-6 Item 130 46 Nut NSA5330-4 Item 128 20 Nut NSA5330-5 Item 131

4 Screw NSA5479BV4-11X Item 132 14 Screw NSA5479BV4-7X Item 133

8 Screw NSA5479BV5-12X Item 134 12 Screw NSA5479BV4-8X Item 135 14 Screw NSA5479BV4-9X Item 136

4 Screw NSA5479VHK6-14X Item 137 20 Screw NSA5479BV5-9X Item 138

2 Screw NSA5479BV5-13X Item 139 4 Screw NSA5479VHK6-15X Item 143 6 Screw NSA5479BV4-10X Item 145 6 Screw NSA5479BV5-14X Item 147 2 Screw NSA5479BV5-17X Item 148 2 Screw NSA5479BV4-14X Item 149 1 Screw NSA5479BV7-29 Item 113 2 Screw NSA5479BV6-23 Item 114 1 Screw NSA5479BV5-20 Item 115

1 Strut Item (74) 1 Strut Item (75) 1 Strut Item (76) 1 Strut Item (77) 1 Strut Item (78) 1 Strut Item (79)

4 Axle Item (117) 6 Axle Item (118) 2 Axle Item (122)

76

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE (01) Install axles Items (117), (118) and (122) with Synthe. Hydrocarbon Grease High Pressure (Mat No. 04-022) . NOTE (02) Wet assembly under all the heads of screws with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . NOTE (03) The end of cotter pin Item 83 must be carrefully folded against Items nuts Item 84. NOTE (04) Protect the head of axles Items (117), (118) and (122) with Polyurethane Primer (Mat No. 16-001C) . NOTE : Items (74), (75), (76), (77), (78), (79), (86), (117), (118) and (122) were retained at removal.

attach with :

NOTE : Items (57), (71), (72) and (73) were retained at 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 thru 14 a Install the rib pad : Refer to Figure 9 , Sheets 1 , 2 , 6 and 12 thru 14

attach with : 12 Cotter Pin MS24665-153 Item 83 12 Nut NSA5060-5 Item 84 12 Washer Item (86)

1 Bonding Lead Item (71) 1 Bonding Lead Item (72) 1 Bonding Lead Item (73)

1 Nut NSA5050-3 Item 8 3 Screw Item (57)

1 Rib Pad Item (125)

1 Nut ASNA2536-5 Item 55 46 Nut NSA5050-5 Item 129 10 Nut NSA5050-4 Item 5

77

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 removed. attach with : 1 Nut ASNA2536-7 Item 108 2 Nut ASNA2536-6 Item 110 14 Nut NSA5050-6 Item 130 42 Nut NSA5330-4 Item 128

4 Screw NSA5479BV4-11X Item 132 12 Screw NSA5479BV4-7X Item 133

8 Screw NSA5479BV5-12X Item 134 14 Screw NSA5479BV4-8X Item 135 13 Screw NSA5479BV4-9X Item 136 16 Screw NSA5479BV5-13X Item 139

2 Screw NSA5479BV4-12X Item 140 10 Screw NSA5479BV5-15X Item 141

4 Screw NSA5479VHK6-17X Item 142 2 Screw NSA5479VHK6-15X Item 143 2 Screw NSA5479BV5-18X Item 144 3 Screw NSA5479BV4-10X Item 145 2 Screw NSA5479BV4-13X Item 146 6 Screw NSA5479BV5-14X Item 147 2 Screw NSA5479BV5-17X Item 148 2 Screw NSA5479BV4-14X Item 149 8 Screw NSA5479BV6-22X Item 150 2 Screw NSA5479BV5-19X Item 151 1 Screw NSA5479BV7-30 Item 109 2 Screw NSA5479BV6-25 Item 111 1 Screw NSA5479BV5-21 Item 112

1 Strut Item (74) 1 Strut Item (75) 1 Strut Item (76) 1 Strut Item (77) 1 Strut Item (80) 1 Strut Item (81) 1 Strut Item (82)

4 Axle Item (117) 4 Axle Item (118) 2 Axle Item (119) 2 Axle Item (120) 2 Axle Item (121) 14 Cotter Pin MS24665-153 Item 83

78

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE (01) Install axles Items (117), (118), (119), (120) and (121) with Synthe. Hydrocarbon Grease High Pressure (Mat No. 04-022) . NOTE (02) Wet assembly under all the heads of screws with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . NOTE (03) The end of cotter pin Item 83 must be carrefully folded against Items nuts Item 84 or 85. NOTE (04) Protect the head of axles Items (117), (118), (119), (120) and (121) with Polyurethane Primer (Mat No. 16-001C) . NOTE : Items (74), (75), (76), (77), (80), (81), (82), (86), (87), (117), (118), (119), (120) and (121) were retained at removal.

attach with :

NOTE : Items (57), (71), (72) and (73) were retained at removal. 3 Install the rib pad and the struts at Y - 765. Refer to Figure 6 Refer to Figure 9 , Sheets 1 , 2 , 4 and 12 thru 14 a Install the rib pad : Refer to Figure 9 , Sheets 1 , 2 , 4 and 12 thru 14

attach with : 8 Nut NSA5060-5 Item 84 6 Nut NSA5060-6 Item 85 8 Washer Item (86) 6 Washer Item (87)

3 Bonding Lead Item (71) 1 Bonding Lead Item (72)

4 Nut NSA5050-3 Item 8 4 Screw Item (57)

1 Rib Pad Item (106)
1 Plate Item (124)

79

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : Items (106) and (124) were retained at removal. b Install the struts : Refer to Figure 6

attach with :

NOTE : Items (57), (71), (72) and (73) were retained at removal. 4 Install the rib pad and the struts at Y + 765. Refer to Figure 6 Refer to Figure 9 , Sheets 1 , 2 , 7 and 12 thru 14 a Install the rib pad : Refer to Figure 9 , Sheets 1 , 2 , 7 and 12 thru 14 1 Nut ASNA2536-5 Item 55 15 Nut NSA5050-5 Item 129

6 Nut NSA5050-4 Item 5 1 Nut ASNA2536-7 Item 108 2 Nut ASNA2536-6 Item 110 8 Nut NSA5050-6 Item 130 46 Nut NSA5330-4 Item 128 22 Nut NSA5330-5 Item 131

4 Screw NSA5479BV4-11X Item 132 13 Screw NSA5479BV4-7X Item 133

9 Screw NSA5479BV5-12X Item 134 14 Screw NSA5479BV4-8X Item 135 13 Screw NSA5479BV4-9X Item 136

4 Screw NSA5479VHK6-14X Item 137 20 Screw NSA5479BV5-9X Item 138

4 Screw NSA5479VHK6-15X Item 143 6 Screw NSA5479BV4-10X Item 145 6 Screw NSA5479BV5-14X Item 147 2 Screw NSA5479BV5-17X Item 148 2 Screw NSA5479BV4-14X Item 149 1 Screw NSA5479BV7-29 Item 113 2 Screw NSA5479BV6-23 Item 114 1 Screw NSA5479BV5-20 Item 115

1 Bonding Lead Item (71) 1 Bonding Lead Item (72) 1 Bonding Lead Item (73)

3 Nut NSA5050-3 Item 8 3 Screw Item (57)

80

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved attach with :

NOTE : Items (106) was retained at removal. b Install the struts : Refer to Figure 6

NOTE : Install the strut Item (79) only if removed. attach with : 1 Rib Pad Item (106)

1 Nut ASNA2536-5 Item 55 15 Nut NSA5050-5 Item 129

6 Nut NSA5050-4 Item 5 1 Nut ASNA2536-7 Item 108 2 Nut ASNA2536-6 Item 110 8 Nut NSA5050-6 Item 130 46 Nut NSA5330-4 Item 128 22 Nut NSA5330-5 Item 131

4 Screw NSA5479BV4-11X Item 132 13 Screw NSA5479BV4-7X Item 133

7 Screw NSA5479BV5-12X Item 134 14 Screw NSA5479BV4-8X Item 135 13 Screw NSA5479BV4-9X Item 136

4 Screw NSA5479VHK6-14X Item 137 22 Screw NSA5479BV5-9X Item 138

4 Screw NSA5479VHK6-15X Item 143 6 Screw NSA5479BV4-10X Item 145 6 Screw NSA5479BV5-14X Item 147 2 Screw NSA5479BV5-17X Item 148 2 Screw NSA5479BV4-14X Item 149 1 Screw NSA5479BV7-29 Item 113 2 Screw NSA5479BV6-23 Item 114 1 Screw NSA5479BV5-20 Item 115

1 Strut Item (74) 1 Strut Item (75) 1 Strut Item (76) 1 Strut Item (77) 1 Strut Item (78) 1 Strut Item (79)

4 Axle Item (117) 6 Axle Item (118) 2 Axle Item (122) 12 Cotter Pin MS24665-153 Item 83 12 Nut NSA5060-5 Item 84

81

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE (01) Install axles Items (117), (118) and (122) with Synthe. Hydrocarbon Grease High Pressure (Mat No. 04-022) . NOTE (02) Wet assembly under all the heads of screws with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . NOTE (03) The end of cotter pin Item 83 must be carrefully folded against Items nuts Item 84. NOTE (04) Protect the head of axles Items (117), (118) and (122) with Polyurethane Primer (Mat No. 16-001C) . NOTE : Items (74), (75), (76), (77), (78), (79), (86), (117), (118) and (122) were retained at removal.

attached with :

NOTE : Items (57), (71), (72) and (73) were reatained at 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 thru 14 a Install the rib pad : Refer to Figure 9 , Sheets 1 , 2 , 5 and 12 thru 14

attach with : 12 Washer Item (86)

1 Bonding Lead Item (71) 1 Bonding Lead Item (72) 1 Bonding Lead Item (73)
3 Nut Item (8) Discard 3 Screw Item (57)

1 Rib Pad Item (125)

1 Nut ASNA2536-5 Item 55 46 Nut NSA5050-5 Item 129

8 Nut NSA5050-4 Item 5 1 Nut ASNA2536-7 Item 108 2 Nut ASNA2536-6 Item 110 14 Nut NSA5050-6 Item 130 42 Nut NSA5330-4 Item 128

82

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 removed. attach with : 2 Screw NSA5479BV4-11X Item 132 12 Screw NSA5479BV4-7X Item 133

8 Screw NSA5479BV5-12X Item 134 14 Screw NSA5479BV4-8X Item 135 13 Screw NSA5479BV4-9X Item 136 15 Screw NSA5479BV5-13X Item 139

2 Screw NSA5479BV4-12X Item 140 10 Screw NSA5479BV5-15X Item 141

4 Screw NSA5479VHK6-17X Item 142 2 Screw NSA5479VHK6-15X Item 143 2 Screw NSA5479BV5-18X Item 144 6 Screw NSA5479BV4-10X Item 145 2 Screw NSA5479BV4-13X Item 146 4 Screw NSA5479BV5-14X Item 147 2 Screw NSA5479BV5-17X Item 148 2 Screw NSA5479BV4-14X Item 149 8 Screw NSA5479BV6-22X Item 150 2 Screw NSA5479BV5-19X Item 151 1 Screw NSA5479BV7-30 Item 109 2 Screw NSA5479BV6-25 Item 111 1 Screw NSA5479BV5-21 Item 112

1 Strut Item (74) 1 Strut Item (75) 1 Strut Item (76) 1 Strut Item (77) 1 Strut Item (80) 1 Strut Item (81) 1 Strut Item (82)

4 Axle Item (117) 4 Axle Item (118) 2 Axle Item (119) 2 Axle Item (120) 2 Axle Item (121) 14 Cotter Pin MS24665-153 Item 83

8 Nut NSA5060-5 Item 84 6 Nut NSA5060-6 Item 85 8 Washer Item (86) 6 Washer Item (87)

83

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE (01) Install axles Items (117), (118), (119), (120) and (121) with Synthe. Hydrocarbon Grease High Pressure (Mat No. 04-022) . NOTE (02) Wet assembly under all the heads of screws with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . NOTE (03) The end of cotter pin Item 83 must be carrefully folded against Items nuts Item 84 or 85. NOTE (04) Protect the head of axles Items (117), (118), (119), (120) and (121) with Polyurethane Primer (Mat No. 16-001C) . NOTE : Items (74), (75), (76), (77), (78), (80), (81), (82), (86), (117), (118), (119), (120) and (121) were retained at removal.

attach with :

NOTE : Items (57), (71) and (72) were retained at removal. 6 Install the rib pad and the struts at Y + 1292. Refer to Figure 6 Refer to Figure 9 , Sheets 1 , 2 , 8 and 12 thru 14 a Install the rib pad : Refer to Figure 9 , Sheets 1 , 2 , 8 and 12 thru 14

attach with : 3 Bonding Lead Item (71) 1 Bonding Lead Item (72)

4 Nut NSA5050-3 Item 8 4 Screw Item (57)

1 Rib Pad Item (106)

1 Nut ASNA2536-5 Item 55 18 Nut NSA5050-5 Item 129

6 Nut NSA5050-4 Item 5 1 Nut ASNA2536-7 Item 108 2 Nut ASNA2536-6 Item 110 8 Nut NSA5050-6 Item 130 46 Nut NSA5330-4 Item 128 18 Nut NSA5030-5 Item 131

84

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 necessary. attach with :

NOTE (01) Install axles Items (117), (118) and (122) with Synthe. Hydrocarbon Grease High Pressure (Mat No. 04-022) . NOTE (02) Wet assembly under all the heads of screws with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . 4 Screw NSA5479BV4-11X Item 132 12 Screw NSA5479BV4-7X Item 133

6 Screw NSA5479BV5-12X Item 134 14 Screw NSA5479BV4-8X Item 135 14 Screw NSA5479BV4-9X Item 136

4 Screw NSA5479VHK6-14X Item 137 18 Screw NSA5479BV5-9X Item 138

2 Screw NSA5479BV5-13X Item 139 4 Screw NSA5479VHK6-15X Item 143 2 Screw NSA5479BV5-18X Item 144 6 Screw NSA5479BV4-10X Item 145 6 Screw NSA5479BV5-14X Item 147 2 Screw NSA5479BV5-17X Item 148 2 Screw NSA5479BV4-14X Item 149 1 Screw NSA5479BV7-29 Item 113 2 Screw NSA5479BV6-23 Item 114 1 Screw NSA5479BV5-20 Item 115

1 Strut Item (74) 1 Strut Item (75) 1 Strut Item (76) 1 Strut Item (77) 1 Strut Item (78) 1 Strut Item (79)

4 Axle Item (117) 6 Axle Item (118) 2 Axle Item (122) 12 Cotter Pin MS24665-153 Item 83 12 Nut NSA5060-5 Item 84 12 Washer Item (86)

85

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE (03) The end of cotter pin Item 83 must be carrefully folded against Items nuts Item 84. NOTE (04) Protect the head of axles Items (117), (118) and (122) with Polyurethane Primer (Mat No. 16-001C) . NOTE : Items (74), (75), (76), (77), (78), (79), (86), (117), (118) and (122) were retained at removal.

attach with :

NOTE : Items (57), (71), (72) and (73) were retained at removal. (2) Config. 02 (a) Replace the installation of the rib pads with next nominal fasteners and oversize fasteners. Refer to Figure 6 Refer to Figure 13 NOTE (01) To have sufficient stiffness of the center wing box, every rib pad should be removed and installed before the removal of another one. You must remove/install the rib pads and the 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 nominal fasteners and oversize fasteners for the installation of the rib pads, refer to the Kit 571120A02R01 . 1 Bonding Lead Item (71) 1 Bonding Lead Item (72) 1 Bonding Lead Item (73)

3 Nut NSA5050-3 Item 8 3 Screw Item (57)

86

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 1 Install the rib pad and the struts at Y - 1292. Refer to Figure 6 Refer to Figure 13 , Sheets 1 thru 3 , 9 , 11 and 12 a Install the rib pad : Refer to Figure 13 , Sheets 1 thru 3 , 9 , 11 and 12

attach with :

NOTE : Item (106) was retained at removal. b Install the struts : Refer to Figure 6 1 Rib Pad Item (106)

1 Screw NSA5479BV7-29 Item 113 2 Screw NSA5479BV6-23 Item 114 1 Screw NSA5479BV5-20 Item 115 2 Screw NSA5479BV6-14 Item 165 14 Screw NSA5479BV5-7 Item 167

8 Screw NSA5479BV6-12 Item 168 12 Screw NSA5479BV5-8 Item 169 14 Screw NSA5479BV5-9 Item 158

4 Screw NSA5479BK7-14 Item 170 16 Screw NSA5479BV6-9 Item 171

2 Screw NSA5479BV6-13 Item 166 6 Screw NSA5479BV5-10 Item 178 4 Screw NSA5479BK7-15 Item 174 4 Screw NSA5479BV5-11 Item 179 4 Screw NSA5479BV5-9Y Item 181 2 Screw NSA5479BV5-17Y Item 182 2 Screw NSA5479BV5-14Y Item 183 2 Screw NSA5479BV4-14Y Item 184 2 Nut NSA5050-4 Item 5 5 Nut ASNA2536-5 Item 55 9 Nut ASNA2536-7 Item 108 14 Nut ASNA2536-6 Item 110 46 Nut ASNA2528-5 Item 123

4 Nut NSA5050-5 Item 129 4 Nut NSA5330-5 Item 131 16 Nut ASNA2528-6 Item 180

4 Washer NSA5368-516D Item 188 2 Washer NSA5368-416D Item 189

1 Strut Item (74) 1 Strut Item (75) 1 Strut Item (76) 1 Strut Item (77)

87

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : Install the strut Item (79) only if removed. attach with :

NOTE (01) Install axles Items (117), (118) and (122) with Synthe. Hydrocarbon Grease High Pressure (Mat No. 04-022) . NOTE (02) Wet assembly under all the heads of screws with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . NOTE (03) The end of cotter pin Item 83 must be carrefully folded against Items nuts Item 84. NOTE (04) Protect the head of axles Items (117), (118) and (122) with Polyurethane Primer (Mat No. 16-001C) . NOTE : Items (74), (75), (76), (77), (78), (79), (86), (117), (118) and (122) were retained at removal.

attach with :

NOTE : Items (57), (71), (72) and (73) were retained at removal. 2 Install the rib pad and the struts at Y + 254. Refer to Figure 6 Refer to Figure 13 , Sheet s1,2,6,9 thru 12 a Install the rib pad : 1 Strut Item (78) 1 Strut Item (79)

4 Axle Item (117) 6 Axle Item (118) 2 Axle Item (122) 12 Cotter Pin MS24665-153 Item 83 12 Nut NSA5060-5 Item 84 12 Washer Item (86)

1 Bonding Lead Item (71) 1 Bonding Lead Item (72) 1 Bonding Lead Item (73)

1 Nut NSA5050-3 Item 8 3 Screw Item (57)

88

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Refer to Figure 13 , Sheet s1,2,6,9 thru 12

attach with :

NOTE : Item (125) was retained at removal. b Install the struts : Refer to Figure 6 1 Rib Pad Item (125)

1 Screw NSA5479BV7-30 Item 109 2 Screw NSA5479BV6-25 Item 111 1 Screw NSA5479BV5-21 Item 112 2 Screw NSA5479BV6-14 Item 165 12 Screw NSA5479BV5-7 Item 167

8 Screw NSA5479BV6-12 Item 168 14 Screw NSA5479BV5-8 Item 169 13 Screw NSA5479BV5-9 Item 158

6 Screw NSA5479BV6-13 Item 166 2 Screw NSA5479BV5-12 Item 153 10 Screw NSA5479BV6-15 Item 172

4 Screw NSA5479BK7-17 Item 173 2 Screw NSA5479BK7-15 Item 174 4 Screw NSA5479BV7-22 Item 176 2 Screw NSA5479BV6-19 Item 177 3 Screw NSA5479BV5-10 Item 178 2 Screw NSA5479BV5-13 Item 105 4 Screw NSA5479BV5-11 Item 179 2 Screw NSA5479BV5-17Y Item 182 2 Screw NSA5479BV5-14Y Item 183 2 Screw NSA5479BV4-14Y Item 184 10 Screw NSA5479BV5-13Y Item 185

2 Screw NSA5479BV5-18Y Item 186 4 Screw NSA5479BV6-22Y Item 187 42 Nut ASNA2528-5 Item 123

9 Nut ASNA2536-5 Item 55 11 Nut ASNA2536-7 Item 108 30 Nut ASNA2536-6 Item 110 16 Nut NSA5050-5 Item 129

4 Nut NSA5050-6 Item 130 2 Nut NSA5050-4 Item 5 16 Washer NSA5368-516D Item 188

2 Washer NSA5368-416D Item 189 4 Washer NSA5368-616D Item 190

1 Strut Item (74) 1 Strut Item (75) 1 Strut Item (76) 1 Strut Item (77) 1 Strut Item (80)

89

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DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : Install the strut Item (82) only if removed. attach with :

NOTE (01) Install axles Items (117), (118), (119), (120) and (121) with Synthe. Hydrocarbon Grease High Pressure (Mat No. 04-022) . NOTE (02) Wet assembly under all the heads of screws with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . NOTE (03) The end of cotter pin Item 83 must be carrefully folded against Items nuts Item 84 or 85. NOTE (04) Protect the head of axles Items (117), (118), (119), (120) and (121) with Polyurethane Primer (Mat No. 16-001C) . NOTE : Items (74), (75), (76), (77), (80), (81), (82), (86), (87), (117), (118), (119), (120) and (121) were retained at removal.

attach with :

NOTE : Items (57), (71), (72) and (73) were retained at removal. 3 Install the rib pad and the struts at Y - 765.

1 Strut Item (81) 1 Strut Item (82)

4 Axle Item (117) 4 Axle Item (118) 2 Axle Item (119) 2 Axle Item (120) 2 Axle Item (121) 14 Cotter Pin MS24665-153 Item 83

8 Nut NSA5060-5 Item 84 6 Nut NSA5060-6 Item 85 8 Washer Item (86) 6 Washer Item (87)

3 Bonding Lead Item (71) 1 Bonding Lead Item (72)

4 Nut NSA5050-3 Item 8 4 Screw Item (57)

90

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DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Refer to Figure 6 Refer to Figure 13 , Sheet s 1 , 2 , 4 , 9 , 11 and 12 a Install the rib pad : Refer to Figure 13 , Sheet s 1 , 2 , 4 , 9 , 11 and 12

attach with :

NOTE : Items (106) and (124) were retained at removal. b Install the struts : Refer to Figure 6 1 Rib Pad Item (106)
1 Plate Item (124) 1 Screw NSA5479BV7-29 Item 113 2 Screw NSA5479BV6-23 Item 114 1 Screw NSA5479BV5-20 Item 115 1 Screw NSA5479BV7-29 Item 113 2 Screw NSA5479BV6-23 Item 114 1 Screw NSA5479BV5-20 Item 115 3 Screw NSA5479BV6-14 Item 165 13 Screw NSA5479BV5-7 Item 167

9 Screw NSA5479BV6-12 Item 168 14 Screw NSA5479BV5-8 Item 169 13 Screw NSA5479BV5-9 Item 158

4 Screw NSA5479BK7-14 Item 170 16 Screw NSA5479BV6-9 Item 171

6 Screw NSA5479BV5-10 Item 178 4 Screw NSA5479BK7-15 Item 174 4 Screw NSA5479BV5-11 Item 179 4 Screw NSA5479BV5-9Y Item 181 2 Screw NSA5479BV5-17Y Item 182 2 Screw NSA5479BV5-14Y Item 183 2 Screw NSA5479BV4-14Y Item 184 5 Nut ASNA2536-5 Item 55 2 Nut NSA5050-4 Item 5 9 Nut ASNA2536-7 Item 108 12 Nut ASNA2536-6 Item 110 46 Nut ASNA2528-5 Item 123

4 Nut NSA5050-5 Item 129 4 Nut NSA5330-5 Item 131 18 Nut ASNA2528-6 Item 180

4 Washer NSA5368-516D Item 188 2 Washer NSA5368-416D Item 189

1 Strut Item (74) 1 Strut Item (75)

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : Install the strut Item (79) only if removed. attach with :

NOTE (01) Install axles Items (117), (118) and (122) with Synthe. Hydrocarbon Grease High Pressure (Mat No. 04-022) . NOTE (02) Wet assembly under all the heads of screws with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . NOTE (03) The end of cotter pin Item 83 must be carrefully folded against Items nuts Item 84. NOTE (04) Protect the head of axles Items (117), (118) and (122) with Polyurethane Primer (Mat No. 16-001C) . NOTE : Items (74), (75), (76), (77), (78), (79), (86), (117), (118) and (122) were retained at removal.

attach with :

NOTE : Items (57), (71), (72) and (73) were retained at removal. 4 Install the rib pad and the struts at Y + 765. Refer to Figure 6 Refer to Figure 13 , Sheet s 1 , 2 , 7 , 9 , 11 and 12 1 Strut Item (76) 1 Strut Item (77) 1 Strut Item (78) 1 Strut Item (79)

4 Axle Item (117) 6 Axle Item (118) 2 Axle Item (122) 12 Cotter Pin MS24665-153 Item 83 12 Nut NSA5060-5 Item 84 12 Washer Item (86)

1 Bonding Lead Item (71) 1 Bonding Lead Item (72) 1 Bonding Lead Item (73)

3 Nut NSA5050-3 Item 8 3 Screw Item (57)

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved a Install the rib pad : Refer to Figure 13 , Sheet s 1 , 2 , 7 , 9 , 11 and 12

attach with :

NOTE : Items (106) was retained at removal. b Install the struts : Refer to Figure 6

NOTE : Install the strut Item (79) only if removed. attach with : 1 Rib Pad Item (106)

1 Screw NSA5479BV7-29 Item 113 2 Screw NSA5479BV6-23 Item 114 1 Screw NSA5479BV5-20 Item 115 3 Screw NSA5479BV6-14 Item 165 1 Screw NSA5479BV6-13 Item 166 13 Screw NSA5479BV5-7 Item 167

7 Screw NSA5479BV6-12 Item 168 14 Screw NSA5479BV5-8 Item 169 13 Screw NSA5479BV5-9 Item 158

4 Screw NSA5479BK7-14 Item 170 18 Screw NSA5479BV6-9 Item 171

6 Screw NSA5479BV5-10 Item 178 4 Screw NSA5479BK7-15 Item 174 4 Screw NSA5479BV5-11 Item 179 4 Screw NSA5479BV5-9Y Item 181 2 Screw NSA5479BV5-17Y Item 182 2 Screw NSA5479BV5-14Y Item 183 2 Screw NSA5479BV4-14Y Item 184 5 Nut ASNA2536-5 Item 55 2 Nut NSA5050-4 Item 5 9 Nut ASNA2536-7 Item 108 12 Nut ASNA2536-6 Item 110 46 Nut ASNA2528-5 Item 123

4 Nut NSA5050-5 Item 129 4 Nut NSA5330-5 Item 131 18 Nut ASNA2528-6 Item 180

4 Washer NSA5368-516D Item 188 2 Washer NSA5368-416D Item 189

1 Strut Item (74) 1 Strut Item (75) 1 Strut Item (76) 1 Strut Item (77) 1 Strut Item (78) 1 Strut Item (79)

93

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE (01) Install axles Items (117), (118) and (122) with Synthe. Hydrocarbon Grease High Pressure (Mat No. 04-022) . NOTE (02) Wet assembly under all the heads of screws with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . NOTE (03) The end of cotter pin Item 83 must be carrefully folded against Items nuts Item 84. NOTE (04) Protect the head of axles Items (117), (118) and (122) with Polyurethane Primer (Mat No. 16-001C) . NOTE : Items (74), (75), (76), (77), (78), (79), (86), (117), (118) and (122) were retained at removal.

attached with :

NOTE : Items (57), (71), (72) and (73) were retained at removal. 5 Install the rib pad and the struts at Y - 254. Refer to Figure 6 Refer to Figure 13 , Sheet s1,2,5,9 thru 12 a Install the rib pad : Refer to Figure 13 , Sheet s1,2,5,9 thru 12

attach with : 4 Axle Item (117) 6 Axle Item (118) 2 Axle Item (122) 12 Cotter Pin MS24665-153 Item 83 12 Nut NSA5060-5 Item 84 12 Washer Item (86)

1 Bonding Lead Item (71) 1 Bonding Lead Item (72) 1 Nut Item (73)

3 Nut NSA5050-3 Item 8 3 Screw Item (57)

1 Rib Pad Item (125)

94

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 removed. 1 Screw NSA5479BV7-30 Item 109 2 Screw NSA5479BV6-25 Item 111 1 Screw NSA5479BV5-21 Item 112 2 Screw NSA5479BV6-14 Item 165 12 Screw NSA5479BV5-7 Item 167

8 Screw NSA5479BV6-12 Item 168 14 Screw NSA5479BV5-8 Item 169 13 Screw NSA5479BV5-9 Item 158

6 Screw NSA5479BV6-13 Item 166 4 Screw NSA5479BV5-12 Item 153 10 Screw NSA5479BV6-15 Item 172

4 Screw NSA5479BK7-17 Item 173 2 Screw NSA5479BK7-15 Item 174 4 Screw NSA5479BV7-22 Item 176 2 Screw NSA5479BV6-19 Item 177 3 Screw NSA5479BV5-10 Item 178 2 Screw NSA5479BV5-13 Item 105 2 Screw NSA5479BV5-11 Item 179 2 Screw NSA5479BV5-17Y Item 182 2 Screw NSA5479BV5-14Y Item 183 2 Screw NSA5479BV4-14Y Item 184 10 Screw NSA5479BV5-13Y Item 185

2 Screw NSA5479BV5-18Y Item 186 4 Screw NSA5479BV6-22Y Item 187 42 Nut ASNA2528-5 Item 123

9 Nut ASNA2536-5 Item 55 11 Nut ASNA2536-7 Item 108 30 Nut ASNA2536-6 Item 110 16 Nut NSA5050-5 Item 129

4 Nut NSA5050-6 Item 130 2 Nut NSA5050-4 Item 5 16 Washer NSA5368-516D Item 188

2 Washer NSA5368-416D Item 189 4 Washer NSA5368-616D Item 190

1 Strut Item (74) 1 Strut Item (75) 1 Strut Item (76) 1 Strut Item (77) 1 Strut Item (80) 1 Strut Item (81) 1 Strut Item (82)

95

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved attach with :

NOTE (01) Install axles Items (117), (118), (119), (120) and (121) with Synthe. Hydrocarbon Grease High Pressure (Mat No. 04-022) . NOTE (02) Wet assembly under all the heads of screws with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . NOTE (03) The end of cotter pin Item 83 must be carrefully folded against Items nuts Item 84 or 85. NOTE (04) Protect the head of axles Items (117), (118), (119), (120) and (121) with Polyurethane Primer (Mat No. 16-001C) . NOTE : Items (74), (75), (76), (77), (78), (80), (81), (82), (86), (117), (118), (119), (120) and (121) were retained at removal.

attach with :

NOTE : Items (57), (71) and (72) were retained at removal. 6 Install the rib pad and the struts at Y + 1292. Refer to Figure 6 Refer to Figure 13 , Sheet s1,2,8 thru 12 a Install the rib pad : 4 Axle Item (117) 4 Axle Item (118) 2 Axle Item (119) 2 Axle Item (120) 2 Axle Item (121) 14 Cotter Pin MS24665-153 Item 83

8 Nut NSA5060-5 Item 84 6 Nut NSA5060-6 Item 85 8 Washer Item (86) 6 Washer Item (87)

3 Bonding Lead Item (71) 1 Bonding Lead Item (72)

4 Nut NSA5050-3 Item 8 4 screw Item (57)

96

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DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Refer to Figure 13 , Sheet s1,2,8 thru 12

attach with :

NOTE : Item (106) was retained at removal. b Install the strut : Refer to Figure 6

NOTE : Install the strut Item (79) only if necessary. attach with : 1 Rib Pad Item (106)

1 Screw NSA5479BV7-29 Item 113 2 Screw NSA5479BV6-23 Item 114 1 Screw NSA5479BV5-20 Item 115 2 Screw NSA5479BV6-14 Item 165 12 Screw NSA5479BV5-7 Item 167

6 Screw NSA5479BV6-12 Item 168 14 Screw NSA5479BV5-8 Item 169 14 Screw NSA5479BV5-9 Item 158

4 Screw NSA5479BK7-14 Item 170 14 Screw NSA5479BV6-9 Item 171

2 Screw NSA5479BV6-13 Item 166 6 Screw NSA5479BV5-10 Item 178 4 Screw NSA5479BK7-15 Item 174 2 Screw NSA5479BV6-18 Item 175 4 Screw NSA5479BV5-11 Item 179 4 Screw NSA5479BV5-9Y Item 181 2 Screw NSA5479BV5-17Y Item 182 2 Screw NSA5479BV5-14Y Item 183 2 Screw NSA5479BV4-14Y Item 184 2 Nut NSA5050-4 Item 5 5 Nut ASNA2536-5 Item 55 9 Nut ASNA2536-7 Item 108 16 Nut ASNA2536-6 Item 110 46 Nut ASNA2528-5 Item 123

4 Nut NSA5050-5 Item 129 4 Nut NSA5330-5 Item 131 14 Nut ASNA2528-6 Item 180

4 Washer NSA5368-516D Item 188 2 Washer NSA5368-416D Item 189

1 Strut Item (74) 1 Strut Item (75) 1 Strut Item (76) 1 Strut Item (77) 1 Strut Item (78) 1 Strut Item (79)

97

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE (01) Install axles Items (117), (118) and (122) with Synthe. Hydrocarbon Grease High Pressure (Mat No. 04-022) . NOTE (02) Wet assembly under all the heads of screws with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . NOTE (03) The end of cotter pin Item 83 must be carrefully folded against Items nuts Item 84. NOTE (04) Protect the head of axles Items (117), (118) and (122) with Polyurethane Primer (Mat No. 16-001C) . NOTE : Items (74), (75), (76), (77), (78), (79), (86), (117), (118) and (122) were retained at removal.

attach with :

NOTE : Items (57), (71), (72) and (73) were retained at removal. D. TEST (1) Config. 01 thru Config. 02 (a) Install the ACT transfer valve FIN 165QM (Refer to AMM 28-28-33 Page block 401), (if removed). (b) Install the refuel valve canister FIN 164QM (Refer to AMM 28-25-52 Page block 401), (if removed). (c) Install the ACT fuel transfer pump mounting plate FIN 163QM (Refer to AMM 28-28-31 Page block 401), (if removed).

4 Axle Item (117) 6 Axle Item (118) 2 Axle Item (122) 12 Cotter Pin MS24665-153 Item 83 12 Nut NSA5060-5 Item 84 12 Washer Item (86)

1 Bonding Lead Item (71) 1 Bonding Lead Item (72) 1 Bonding Lead Item (73)

3 Nut NSA5050-3 Item 8 3 Screw Item (57)

98

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (d) Install the water extractor temperature sensors FIN 11HH and FIN 31HH (Refer to AMM 21-61-13 Page block 401). (e) Install the air accumulator pressure gage FIN 2072GM (Refer to AMM 29-12-21 Page block 401). (f) Install the BLUE power accumulator FIN 2070GM (Refer to AMM 29-12-42 Page block 401). (g) Install the BLUE electric pump FIN 2075GJ (Refer to AMM 29-12-51 Page block 401). (h) Install the recirculation filters FIN 4012HM and FIN 4013HM (Refer to AMM 21-21-41 Page block 401). (i) Install the duct temperature sensors FIN 15HK, FIN 16HK and FIN 17HK (Refer to AMM 21-63-15 Page block 401). (j) Install the mixer unit (Refer to AMM 21-21-43 Page block 401). (k) Install the mixer unit tempeature sensors FIN 24HK and FIN 25HK (Refer to AMM 21-63-16 Page block 401). (l) Install the water injectors FIN 20HM and FIN 21HM (Refer to AMM 21-52-42 Page block 401). (m) Install the check valves FIN 4020HM and FIN 4021HM (Refer to AMM 21-21-42 Page block 401). (n) Install the cabin recirculation fans FIN 14HG and FIN 15HG (Refer to AMM 21-21-51 Page block 401). (o) Install the Jet Pumps center tank FIN 157QM and FIN 158QM (Refer to AMM 28-26-41 Page block 401). (p) Remove the Jet Pump Fuel Control Valves FIN 153QM and FIN 154QM (Refer to AMM 28-26-43 Page block 401). (q) Install the center tank probes FIN 37QT and FIN 38QT (Refer to AMM 28-42-15 Page block 401). (r) Install the center tank fuel lever sensor FIN 22QJ (Refer to AMM 28-46-15 Page block 401). (s) Install the vapor seal (Refer to AMM 28-13-42 Page block 401). (t) Install the refuel diffuser assembly of the center tank (Refer to AMM 28-25-42 Page block 401). (u) Remove the safety clips and tags and close these circuit breakers (Refer to AMM 28-42-47 Page block 401), (Refer to AMM 28-42-44 Page block 401), (Refer to AMM 28-42-15 Page block 401), (Refer to AMM 33-48-12 Page block 401), (Refer to AMM 27-84-45 Page block 401), (Refer to AMM 27-84-53 Page block 401), (Refer to AMM 21-61-51 Page block 401), (Refer to AMM

99

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 21-51-11 Page block 401), (Refer to AMM 21-61-16 Page block 401), (Refer to AMM 29-24-51 Page block 401), (Refer to AMM 28-28-00 Page block 401). (v) Do the test after the removal/installation of the refuel diffuser assembly of the center tank (Refer to AMM 28-25-42 Page block 401). (w) Do the test after the removal/installation of the vapor seal (Refer to AMM 28-13-42 Page block 401). (x) Do the test after the removal/installation of the center tank fuel lever sensor FIN 22QJ (Refer to AMM 28-46-15 Page block 401). (y) Do the test after the removal/installation of the ultracomp. FIN 50QT (Refer to AMM 28-42-47 Page block 401). (z) Do the test after the removal/installation of the center tank harnesses FIN 17QT and FIN 18QT (Refer to AMM 28-42-44 Page block 401). (aa) Do the test after the removal/installation of the center transfer tank fuel quantity probes FIN 35QT, FIN 36QT, FIN 37QT, FIN 38QT and FIN 51QT (Refer to AMM 28-42-15 Page block 401). (ab) Do the test after the removal/installation of the jet pump fuel control valves FIN 153QM and 154QM (Refer to AMM 28-26-43 Page block 401). (ac) Do the test after the removal/installation of the center tank jet pumps FIN 157QM and FIN 158QM (Refer to AMM 28-26-41 Page block 401). (ad) Do the test after the removal/installation of the cabin recirculation fans FIN 14HG and FIN 15HG (Refer to AMM 21-21-51 Page block 401). (ae) Do the test after the removal/installation of the mixer unit temperature sensors FIN 24HK and FIN 25HK (Refer to AMM 21-63-16 Page block 401). (af) Do the test after the removal/installation of the mixer unit (Refer to AMM 21-21-43 Page block 401). (ag) Do the test after the removal/installation of the duct temperature sensors FIN 15HK, FIN 16HK and FIN 17HK (Refer to AMM 21-63-15 Page block 401). (ah) Do the test after the removal/installation of the blue electric pump FIN 2075GJ (Refer to AMM 29-12-51 Page block 401).

100

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (ai) Do the test after the removal/installation of the blue power accumulator FIN 2070GM (Refer to AMM 29-12-42 Page block 401). (aj) Do the test after the removal/installation of the accumulator air pressure gage FIN 2072GM (Refer to AMM 29-12-21 Page block 401). (ak) Do the test after the removal/installation of the water extractor temperature sensors FIN 11HH and FIN 31HH (Refer to AMM 21-61-13 Page block 401). (al) Do the test after the removal/installation of the lower beacon/strobe light FIN 6LV from the fuselage outside (Refer to AMM 33-48-12 Page block 401). (am) Do the test after the removal/installation of the transmission torque shaft assy FIN 6004CM (Refer to AMM 27-84-45 Page block 401). (an) Do the test after the removal/installation of the valve blocks of the Power Control Unit (PCU) (slat) FIN 25CV and FIN 26CV (Refer to AMM 27-84-53 Page block 401). (ao) Do the test after the removal/installation of the air inlet flap actuators FIN 8HH and FIN 28HH (Refer to AMM 21-61-51 Page block 401). (ap) Do the test after the removal/installation of the pack outlet temperature sensor FIN 34HH (Refer to AMM 21-61-15 Page block 401). (aq) Do the test after the removal/installation of the pressure sensors FIN 9HB and FIN 10HB (Refer to AMM 21-51-11 Page block 401). (ar) Do the test after the removal/installation of the pack inlet pressure sensors FIN 16HH and FIN 36HH (Refer to AMM 21-61-16 Page block 401). (as) Do the test after the removal/installation of the electric pump FIN 3075GX (Refer to AMM 29-24-51 Page block 401). (at) Tests after the removal/installation of the ACT transfer at FR42 (if removed/installed): 1 Do the operational test of the ACT manual transfer (Refer to AMM 28-28-00 Page block 501). 2 Make sure that there are no leaks at the removed fuel pipe of the ACT transfer and at the interface of the refuel valve canister FIN 164QM with the structure. (au) Bonding tests :

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DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 1 Do the electrical bonding of the pipes (Refer to AMM 20-28-00 Page block 501). 2 Do the electrical bonding of the components with conductive bolts and screws in the tanks (Refer to AMM 20-28-00 Page block 501). (av) Do the leak test with fuel of the wing-tank outer-cell (Refer 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 147CB, FIN 191JB, FIN 191GB, FIN 147BB, FIN 147AB, FIN 195CB, FIN 191CB, FIN 191DB, FIN 191HB, FIN 191MB, FIN 192EB, FIN 192LB, FIN 148DB, FIN 192EB, FIN 192FB, FIN 196AB, FIN 195AB and FIN 195BB (Refer to AMM 53-35-11 Page block 401) and (Refer to AMM 53-35-13 Page block 401). (b) Install the partitions FIN 151BW, FIN 151AW and FIN 152AW from the aft cargo compartment at FR47 (Refer to AMM 25-55-11 Page block 401). (c) Close the acces doors 147AZ and 148AZ (Refer to AMM 57-17-11 Page block 401). (d) Reactive the venting system (Refer to AMM 28-12-00 Page block 401). (e) Refuel the center tank (Refer to AMM 28-25-00 Page block 301). (f) Close the Cargo door 825 (Refer to AMM 52-30-00 Page block 201). (g) Close the Main Landing Gear doors (Refer to AMM 32-12-00 Page block 201). (h) Close the passenger/crew door 831 (Refer to AMM 52-10-00 Page block 201). (i) Remove the access platforms. (j) Disconnect the aircraft electrical ground-connection (Refer to AMM 12-34-24 Page block 401). F. DOCUMENTATION Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

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# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 at FR42

103

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 at FR42

104

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 at FR42

105

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 at FR42

106

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 at FR42

107

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 at FR42

108

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 of the Diffuser in the RH Center Wing Box at FR42

109

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Pump Circuit Between FR41 and FR42

110

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Pump Circuit Between FR41 and FR42

111

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 and its Support Between FR41 and FR42

112

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 and its Support Between FR41 and FR42

113

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 and its Support Between FR41 and FR42

114

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Harness 18QT from the Sensor 22QJ and the Harnesses 17QT and 18QT from the Ultracomp 50QT

115

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Harness 18QT from the Sensor 22QJ and the Harnesses 17QT and 18QT from the Ultracomp 50QT

116

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Harness 18QT from the Sensor 22QJ and the Harnesses 17QT and 18QT from the Ultracomp 50QT

117

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Harness 18QT from the Sensor 22QJ and the Harnesses 17QT and 18QT from the Ultracomp 50QT

118

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Harness 18QT from the Sensor 22QJ and the Harnesses 17QT and 18QT from the Ultracomp 50QT

119

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Lower Panel of the Center Wing Box Between FR36 and FR42

120

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Lower Panel of the Center Wing Box Between FR36 and FR42

121

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Lower Panel of the Center Wing Box Between FR36 and FR42

122

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Lower Panel of the Center Wing Box Between FR36 and FR42

123

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Lower Panel of the Center Wing Box Between FR36 and FR42

124

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 System Between FR34 and FR36 in the Cargo compartment

125

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Between FR36 and FR40

126

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Between FR36 and FR40

127

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Between FR36 and FR40

128

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Between FR36 and FR40

129

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Between FR36 and FR40

130

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

131

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

132

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

133

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

134

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

135

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

136

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

137

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

138

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

139

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

140

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

141

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

142

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

143

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

144

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 11 Sheet 1 Config. 01 : Flow Chart

146

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Between FR36 and FR40

147

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Between FR36 and FR40

148

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Between FR36 and FR40

149

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Between FR36 and FR40

150

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Between FR36 and FR40

151

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

152

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

153

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

154

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

155

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

156

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

157

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

158

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

159

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

160

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

161

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

162

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Wing Box Between FR36 and FR42

163

# @ A318/A319/A320/A321 SERVICE BULLETIN

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 14 Sheet 1 Config. 02 : Flow Chart

164

# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 01

5 DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : 1 of 3 Printed in FRANCE © AIRBUS, 2006 All rights reserved Config. 01 The results of the inspection, including no findings, replacement or actions to be done, must be forwarded to AIRBUS Department (SEE92), on the attached inspection report Sheet.

# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 01

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 1 Sheet 1 Config. 01 : Inspection Report

2

# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 01

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 1 Sheet 2 Config. 01 : Inspection Report

3

# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 02

5 DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : 1 of 3 Printed in FRANCE © AIRBUS, 2006 All rights reserved Config. 02 The results of the inspection, including no findings, replacement or actions to be done, must be forwarded to AIRBUS Department (SEE92), on the attached inspection report Sheet.

# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 02

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 1 Sheet 1 Config. 02 : Inspection Report

2

# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 02

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 1 Sheet 2 Config. 02 : Inspection Report

3

# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 03

5 DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : 1 of 14 Printed in FRANCE © AIRBUS, 2006 All rights reserved 1. Config. 01 to 02 : Jacking procedure for the inspection of the rib pads in the center wing box between FR36 and FR42. A. FIXTURE, TOOLS, TEST AND SUPPORT EQUIPMENT

B. AIRCRAFT CONFIGURATION Refer to Figure 1 — This jacking procedure is valid only for the configuration below : 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 CFM 98D07203005000 2 Cradle for engine IAE 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

# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 03

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved — For the complete aircraft configuration : Refer to Figure 1 , Sheets 1 and 2 — Contact AI/FR if the aircraft configuration is not the same as the configuration given above. — If you do the other tasks at the same time, contact AI/FR. 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 cradles at points 3, 18, 19, 20, 23, 24, 25, 26, 27, 28 and under the LH and RH engines. Refer to Figure 1 , Sheets 3 , 4 , 5 and 6 NOTE : To do the jacking, you must apply the loads in 4 steps : — Step 1 : 25% — Step 2 : 50% — Step 3 : 75% — Step 4 : 100% Refer to Figure 1 , Sheet 9 (for aircraft without the ACT2) or Sheet 10 (for aircraft with the ACT2). CAUTION : MAKE SURE THAT THE LOADS DO NEVER EXCEED THE MAXIMUM PERMISSIBLE LOADS (REFER TO FIGURE 1 , SHEET 9 (FOR AIRCRAFT WITHOUT THE ACT2) OR SHEET 10 (FOR AIRCRAFT 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

# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 03

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Box Between FR36 and FR42.

3

# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 03

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Box Between FR36 and FR42.

4

# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 03

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Box Between FR36 and FR42.

5

# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 03

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Box Between FR36 and FR42.

6

# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 03

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Box Between FR36 and FR42.

7

# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 03

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Box Between FR36 and FR42.

8

# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 03

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Box Between FR36 and FR42.

9

# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 03

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Box Between FR36 and FR42.

10

# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 03

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Box Between FR36 and FR42.

11

# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 03

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Box Between FR36 and FR42.

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# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 03

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Box Between FR36 and FR42.

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# @ A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 03

DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 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 Box Between FR36 and FR42.

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# @ A318/A319/A320/A321 SERVICE BULLETIN REPORTING SHEET

5 DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : 1 of 1 Printed in FRANCE © AIRBUS, 2006 All rights reserved TITLE : WINGS - CENTER WING - INSPECTION OF CENTER WING BOX LOWER PANEL BORE HOLES. MODIFICATION No. : None
Please complete the appropriate item (A or B): A - SB WILL BE embodied............. YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment :..........................

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........................................ B - SB HAS BEEN embodied on aircraft :.....................

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........................................ Operator comments :..............................

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....................................... From Airline :................................. Name/Title :.................................. Signature :.............. Date :............. If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service: Either: Modification Operational Impact (MOI), if available. . YES/NO Or : Intermediate revision.
................ YES/NO Important Information: This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible revision, this will result in - updating of maintenance documentation to show pre and post SB data. - updating of maintenance and operational documentation to show post SB data after embodiment. If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include them in the manual revisions. Refer to SIL 00-037 for detailed information. Please return this completed sheet to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn: SDC32 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 e-mail: sb.reporting@airbus.com or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.

# @ A318/A319/A320/A321 SERVICE BULLETIN QUALITY PERCEPTION FORM

5 DATE : Sep 04/03 SERVICE BULLETIN No. : A320—57—1120 REVISION No. : 01 — Nov 15/06 Page : 1 of 1 Printed in FRANCE © AIRBUS, 2006 All rights reserved Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 4 3 2 1 - Quality rating of the Accomplishment Instructions 4 3 2 1 - Quality rating of the Illustrations 4 3 2 1 - Is this SB easy to understand ? Y / N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials X Mod/Inspection X Manpower Operator Supplied X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations Comments :

Operator : Date: Name/Title : Please return this form to : AIRBUS 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.