SERVICE BULLETIN REVISION TRANSMITTAL SHEET

**AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  **Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F**  **Fax : (33) 5 61 93 42 51 ATA SYSTEM : 28**  **TITLE : FUEL - TANKS - INSTALL ONE ACT PROVISION ON A320 WITH CLS MODIFICATION No. :**  25415P4179, 25696P4347, 25713J1492, 25713K4481, 26138K4772, 27115J1522, 27446P5502, 27447P5503, 28068P5759, 28404K6135, 28507K6195, 28521K6229, 28661J2073, 28817J1973, 30139J2110, 30356P6683, 30373K6720, 31110K7004, 31143K7155, 31642K7282, 31700K7502, 32244K7774, 32261J2241, 33110K8396, 33198K8488, 33492J2482, 33670K6096, 33671K6098, 33672K4980, 34240K9240 This page transmits Revision No. 03 of Service Bulletin No. A320-28-1118. AD D I T I O NAL WO R K Additional work is required by this revision for Config 02 aircraft, modified by revision 02. NOTE : ADDITIONAL WORK 1 is required by this revision for aircraft MSN 1137 modified by issue 00 thru Revision 02. - installation of new placards. NOTE : ADDITIONAL WORK 2 is required by this revision for aircraft modified by Revision 02. - installation of new plates. R EASO N Revision No. 03 has been issued to incorporate minor improvements further to accomplishment of this Service Bulletin on a Config 02 aircraft. Also, for Config 02 aircraft, in the revision 02 issue of this Service Bulletin, the placards installed on the belly fairing were incorrect. This revision is issued to install the correct placards on the belly fairing. To update Kits D05 and D39 thru D42 and D96. C HAN G E S SUMMARY : - REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. Mods have been updated. - MANPOWER

. Config. 01, introduced by revision 02 has been added. Config. 02, introduced by revision 02 has been added. Additional work has been added. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 1 of 6 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN REVISION TRANSMITTAL SHEET

- MATERIAL INFORMATION

. Kit A16 has been amended to Kit A18. Kit D05, D39, D40, D41, D42, D46 and D85 have been raised in issue. Kit D96 has been added. PLANNING INFORMATION : - EFFECTIVITY

. 1.A. Kit A18R00 added for Config. 02. Kit D05, D39, D40, D41 and D42 have been raised in issue. Kit D96 has been added. Notes for additional work have been added. - DESCRIPTION

. 1.D.(3) Workstep added. . 1.D.(5) Description revised. . 1.D.(6) Description revised. . 1.D.(7) Description revised. . 1.D.(9) Introduced by revision 02 has been added. . 1.D.(10) Additional work has been added. . 1.D.(11) Additional work has been added. . 1.D.(12) Additional work has been added. - MANPOWER

. 1.G. Config. 01, introduced by revision 02 has been added. Config. 02 additional work has been added. - WEIGHT AND BALANCE

. 1.H. Kits D05, D39, D40, D41, D42, D46 and D96 have been raised in issue. Additional work has been added. - REFERENCES

. 1.J. Drawing numbers have been updated. MATERIAL INFORMATION : - Material

. 2.A.(1) Address updated. - LIST OF COMPONENTS

. 2.C. Kit A17 has been added. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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. 2.C. Kit A18 has been added. . 2.C. Kit D05 has been raised in issue. . 2.C. Kit D39 has been raised in issue. . 2.C. Kit D40 has been raised in issue. . 2.C. Kit D41 has been raised in issue. . 2.C. Kit D42 has been raised in issue. . 2.C. Kit D46 has been raised in issue. . 2.C. Kit D85 has been raised in issue. . 2.C. Kit D96 has been raised in issue. - TOOLING - PRICE AND AVAILABILITY

. 2.F. Tooling part number has been updated. ACCOMPLISHMENT INSTRUCTIONS : - MODIFICATION

. 3.B.(1)(p) Drawing number has been amended. . 3.B.(1)(p)2 Part numbers have been amended. . 3.B.(2) Drawing numbers updated. . 3.B.(2)(p) Updated. . 3.B.(5)(e) Workstep has been amended. . 3.B.(5)(ac) Remove reference of Sheet 13 and delete para 2. . 3.B.(5)(af) Kit D05 has been raised in issue. . 3.B.(5)(ag)1 Kit D05 has been raised in issue. . 3.B.(5)(ak) Kit D05 has been raised in issue. . 3.B.(5)(al) Kit D05 has been raised in issue. . 3.B.(5)(am) Kit D05 has been raised in issue. . 3.B.(5)(an) Kit D05 has been raised in issue. . 3.B.(5)(ao) Kit D05 has been raised in issue. . 3.B.(5)(ap) Kit D05 has been raised in issue. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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. 3.B.(5)(aq) Kit D05 has been raised in issue. . 3.B.(5)(aq)4 Kit D05 has been raised in issue. . 3.B.(5)(bi)10 Drawing reference corrected. . 3.B.(5)(bj) Sheet ref has been amended. . 3.B.(6)(a) Workstep changed from Config. 01 and 02 to Config. 01. . 3.B.(6)(b) Workstep changed from Config. 01 and 02 to Config. 01. . 3.B.(6)(c) Workstep added. . 3.B.(6)(p) Kit D85 has been raised in issue. . 3.B.(6)(x) Workstep changed from Config. 02 to Config. 01. . 3.B.(6)(z)2 Kit D05 has been raised in issue. . 3.B.(6)(z)2e Kit D05 has been raised in issue. . 3.B.(6)(z)3e Kit D05 has been raised in issue. . 3.B.(6)(au)1 Partnumber changed from D5367161701800 to D5367161702200. . 3.B.(7)(c) Reference of Sheet 16 deleted. . 3.B.(7)(d) Kit D85 has been raised in issue. . 3.B.(7)(e) Kit D85 has been raised in issue. . 3.B.(7)(f) Kit D85 has been raised in issue. . 3.B.(7)(g) Kit D85 has been raised in issue. . 3.B.(7)(g)4g Partnumber changed from D5347470420400 to D5347470420200. . 3.B.(7)(g)5a Quantity and PN corrected. . 3.B.(7)(h) Kit D85 has been raised in issue. . 3.B.(7)(h)2 Section changed from F15-F7 to C1-C4. Delete reference of Sheet 16. . 3.B.(7)(i) Kit D85 has been raised in issue. . 3.B.(7)(j) Kit D85 has been raised in issue. . 3.B.(7)(k) Kit D85 has been raised in issue. . 3.B.(7)(k)2 Items 136, 0202, 0206, 0210, 0212 and 220 added. . 3.B.(7)(l) Kit D85 has been raised in issue. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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. 3.B.(7)(m) Kit D85 has been raised in issue. . 3.B.(7)(n) Kit D85 has been raised in issue. . 3.B.(7)(n)2 Kit D05 has been raised in issue. . 3.B.(7)(n)2e Kit D05 has been raised in issue. . 3.B.(7)(n)3e Kit D05 has been raised in issue. . 3.B.(7)(o) Kit D85 has been raised in issue. . 3.B.(7)(p) Kit D85 has been raised in issue. . 3.B.(7)(q)3 Drawing corrected. . 3.B.(7)(t) Drawing number changed. . 3.B.(7)(x) Kit D40 has been raised in issue. . 3.B.(7)(z) Kit D39 has been raised in issue. . 3.B.(7)(z)1 Part number changed from D5367161701800 to D5367161702200. . 3.B.(7)(ab) Sheet reference corrected. . 3.B.(7)(ag) Workstep added. . 3.B.(7)(ah) Kit D41 has been raised in issue. . 3.B.(7)(ai) Kit D42 has been raised in issue. . 3.B.(7)(ai)1 Item 83 thru 86 added. . 3.B.(7)(am) Placard part numbers changed. . 3.B.(7)(ap)1b Kit D98 has been amended to Kit D69. . 3.B.(7)(as) Kit D96 has been raised in issue. . 3.B.(10) ADDITIONAL WORK added for Config. 02. . 3.B.(11) Workstep for ADDITIONAL WORK 1 added. . 3.B.(12) Workstep for ADDITIONAL WORK 2 added. - TESTS

. 3.C. Job set-up and preliminary test procedure updated. . 3.C.(1)(bc) Note has been added. - Figure 31 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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. Sheet 1, Hookup Chart revised. - Figure 36

. Sheet 1 and 2, Hookup Charts revised. - Figure 37

. Sheet 1, Hookup Chart revised. - Figure 46

. Sheet 1, Hookup Chart revised. F I L I N G I N ST RU CT I O N S 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. H I STO RY O F P R E V I O U S R E V I S I O N S Revision 01 was issued to: - incorporate Defect Reports following the accomplishment of this Service Bulletin on aircraft MSN 0870 - update Kits B02R01, D05R05, D06R03, D13R01, D15R01, D16R02, D21R00, D33R02, D36R03, D50R02, D67R02, D68R01, D69R01, D70R01 and D71R01, - correct the fool proofing of connector 47QJ-A - update drawing references - update Standard Sentences - amend the complete text for SB harmonization. Revision No. 02 was issued to add aircraft MSN 1137 and 1150 for operator AUA. For aircraft MSN 0870 in the initial issue, the fuel quantity indicator part number was incorrect and the placards on the ACT door were not installed, this revision also addressed these anomalies by additional work. R E V I S I O N S E Q U E N C E ORIGINAL : Jun 18/04 REVISION No. : 01 - Oct 24/06 REVISION No. : 02 - Jul 25/08 REVISION No. : 03 - May 12/09

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 6 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

**AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  **Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F**  **Fax : (33) 5 61 93 42 51** This summary is for information only and is not approved for modification of the aircraft **ATA SYSTEM : 28 TITLE : FUEL - TANKS - INSTALL ONE ACT PROVISION ON A320 WITH CLS**  **MODIFICATION No. :** 25415P4179, 25696P4347, 25713J1492, 25713K4481, 26138K4772, 27115J1522, 27446P5502, 27447P5503, 28068P5759, 28404K6135, 28507K6195, 28521K6229, 28661J2073, 28817J1973, 30139J2110, 30356P6683, 30373K6720, 31110K7004, 31143K7155, 31642K7282, 31700K7502, 32244K7774, 32261J2241, 33110K8396, 33198K8488, 33492J2482, 33670K6096, 33671K6098, 33672K4980, 34240K9240 R EASO N/D E S C R I PT I O N/O P E RA T I O NAL CO N S E Q U E N C E S This Service Bulletin is issued in response to the request of a customer to install the systems and structural provisions in the aft cargo compartment for an Additional Center Tank (ACT). This Service Bulletin describes the steps required to install the systems and the structural provisions for an ACT to be installed. The provision to install one ACT will give the aircraft an increased operational range due to the additional fuel capacity. Removal of the ACT provides an increased bulk loading capacity.

EVALUATION TABLE COMPLIANCE Optional CANCELS INSPECTION SB No POTENTIAL AD No A/C OPERATION AFFECTED Yes RELIABILITY AFFECTED No PAX COMFORT AFFECTED No COST SAVING No ETOPS AFFECTED No STRUCTURAL LIFE EXTN No VENDOR SB INVOLVED No KIT PRICE (USD) See SB

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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MODIFICATION CLASSIFICATION MAJOR 26138K4772 34456J2596

MINOR 25415P4179 25696P4347 25713J1492 25713K4481 27115J1522 27446P5502 27447P5503 28068P5759 28404K6135 28507K6195 28521K6229 28661J2073 28817J1973 30139J2110 30356P6683 30373K6720 31110K7004 31143K7155 31642K7282 31700K7502 32244K7774 32261J2241 33110K8396 33198K8488 33492J2482 33670K6096 33671K6098 33672K4980 34240K9240 34307J2597 34556J2616 34759K9659 35068P9022 37148K10948 38810K12322 As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural strength, reliability, operational characteristics affecting the airworthiness of the product. All other changes are major changes. **E F**  **F E** **C T** **I V** **I T** **Y** This Service Bulletin is applicable to these operators: AUA TAP NOTE : This Service Bulletin is written for the operator listed above. The modification in this Service Bulletin can be done by other operators. If other operators want to do this modification, use the RFC/RMO procedure and write to: AIRBUS CUSTOMER SERVICES DIRECTORATE AI/SC Department 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE CO N C U R R E NT R E Q U I R E M E NTS None R E F E R E N C E S/R E P E RC U S S I O N S TFU : None OEB : None AOT : None SIL : None LIFE LIMIT : None LINE MAINTENANCE AFFECTED : No OTHERS : None

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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NA T U R E O F TH E WO R K AIRCRAFT : Yes EQUIPMENT : Yes HARD : Yes SOFT : Yes OBRM : No MAN POW E R Config. 01 thru Config. 02 Complete Modification on Aircraft

**TOTAL MANHOURS 1600.00 ELAPSED TIME (HOURS) 350.00**  Config. 01 ADDITIONAL WORK (introduced at revision 01)

**TOTAL MANHOURS 2.0 ELAPSED TIME (HOURS) 2.0**  Config. 01 ADDITIONAL WORK (introduced at revision 02)

**TOTAL MANHOURS 2.5 ELAPSED TIME (HOURS) 2.5**  Config. 02 ADDITIONAL WORK

**TOTAL MANHOURS 1.5 ELAPSED TIME (HOURS) 1.5**  MA T E R I A L I N FO R MA T I O N AIRCRAFT DATA Config. 01 thru Config. 02 Kit 281118A01R03 thru Kit 281118A13R00 Harnesses, brackets, spacers, placards and associated hardware. Kit 281118A14R00 thru Kit 281118A18R00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 3 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Placards. Kit 281118B01R00 Actuator, filter, valves and a clamp. Kit 281118B02R01 Panel 801VU and Relay Box 802VU. Kit 281118B03R00 Panel mounting assembly. Kit 281118B04R02 and Kit 281118B05R00 Panel 800VU and wiring bundle. Kit 281118D01R00 Harnesses, brackets, spacers, placards and associated hardware. Kit 281118D02R00 Reservoirs, tubes, hoses, brackets, sections, clamps, placards and associated hardware. Kit 281118D03R00 Overhead stowage compartments and associated hardware. Kit 281118D04R00 Placards. Kit 281118D05R06 Beam, struts, fittings, angles, plates, sections, supports, connections, coupling, shims and associated hardware. Kit 281118D07R00 Angles, sheets and associated hardware. Kit 281118D09R00 Fittings and associated hardware. Kit 281118D11R01 Brackets and associated hardware. Kit 281118D13R01 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 4 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Tubes, flanges, sleeves, brackets, spacer, clamps, springs and associated hardware. Kit 281118D14R00 Monitor, tubes, hose, fitting, bracket, elbow, unions, placards and associated hardware. Kit 281118D15R01 Monitor, tubes, hose, elbows and associated hardware. Kit 281118D18R00 Beam and associated hardware. Kit 281118D19R00 Shield, shim and associated hardware. Kit 281118D36R03 Sections, plates and associated hardware. Kit 281118D50R02 and Kit 281118D51R01 Controls, adapters, angles, brackets, profiles, holders, bridge and associated hardware. Kit 281118D60R00 Panel, brackets, shims and associated hardware. Kit 281118D61R00 Angles, plates, straps, wall, stiffeners, profiles and associated hardware. Kit 281118D62R00 and Kit 281118D63R00 Pins and collars. Kit 281118D67R02 Clamps, spacers, placards, strips and associated hardware. Kit 281118D69R01 Guides, spacers, supports, mounts and associated hardware. Kit 281118D70R01 Brackets, angles and associated hardware. Kit 281118D72R00 Brackets, mount, spacer and associated hardware. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Cable harnesses and electrical equipment. Kit 281118D78R00 Panels. Kit 281118D79R00 Kit 281118D80R00 Panels. Kit 281118D81R00 Panels and a cover. Kit 281118D82R01 Tubes, brackets, clamps and associated hardware. Kit 281118D83R01 Tubes and a tee. Kit 281118D84R00 Electrical equipment. Config. 01 Kit 281118D06R03 Beams, plates, fittings, doubler, section straps, sections, angles, webs, filler, shims, cover, tube, plugs, bushing and associated hardware. Kit 281118D08R00 Pins and collar. Kit 281118D10R00 Insulation blankets and associated hardware. Kit 281118D12R00 Bracket and associated hardware. Kit 281118D16R02 Monitor, tubes, inlet, couplings, placards, elbow and associated hardware. Kit 281118D17R00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Brackets, angles and associated hardware. Kit 281118D21R00 and Kit 281118D22R00 Shims and associated hardware. Kit 281118D23R01 YZ-latches and associated hardware. Kit 281118D24R00 Tracks, blocks, plate, doubler and associated hardware. Kit 281118D25R00 Tracks, latches and associated hardware. Kit 281118D26R00 Placards. Kit 281118D31R00 Panels and associated hardware. Kit 281118D32R00 Cord and tape. Kit 281118D33R02 Panels, plates, spacers and associated hardware. Kit 281118D34R00 Sections and cord. Kit 281118D35R01 Panels and associated hardware. Kit 281118D68R01 Brackets, mounts, supports, spacers, covers, sheets, straps and associated hardware. Kit 281118D71R01 Brackets, plates, sheets and associated hardware. Kit 281118D73R00 Mount, deflector, guide, spacer, strap and associated hardware. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 7 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Kit 281118D74R00 Config. 02 Kit 281118D27R00 Blankets. Kit 281118D29R00 Cord and tape. Kit 281118D30R00 Sections and Cord. Kit 281118D37R00 Floor panels and associated hardware. Kit 281118D38R00 Sections, brackets and associated hardware. Kit 281118D39R01 Panels and associated hardware. Kit 281118D40R02 Shims. Kit 281118D41R01 Roller tracks, roller, fitting, TDPs, doubler, plates, funnel, filter and associated hardware. Kit 281118D42R01 YZ-latches, roller and associated hardware. Kit 281118D43R00 Ball mats and associated hardware. Kit 281118D44R00 Tie down point and associated hardware. Kit 281118D45R00 Pin. Kit 281118D46R01 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 8 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Placards. Kit 281118D55R00 Bracket, ring and pin. Kit 281118D56R00 Bracket, clamp and associated hardware. Kit 281118D85R02 Beams, plates, fittings, doubler, sections straps, sections, angles, webs, filler, shims, cover, tube, plugs, bushing and associated hardware. Kit 281118D86R00 Pins and collars. Kit 281118D87R00 Electrical equipment. Kit 281118D91R01 Tubes, inlet, filter, couplings, placards, elbow and associated hardware. Kit 281118D92R00 Brackets, angles and associated hardware. Kit 281118D93R00 Brackets, mounts, supports, spacers, covers, sheets, straps and associated hardware. Kit 281118D94R00 Brackets, angles and associated hardware. Kit 281118D96R01 Harness, Equipment and Placards. Kit 281118T01R00 Stowage box. AP P E N D I C E S Refer to Appendix 1- Leak test of the ACT shroud system and drain lines

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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This Page Intentionally Left Blank

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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**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 ATA SYSTEM : 28**  **TITLE : FUEL - TANKS - INSTALL ONE ACT PROVISION ON A320 WITH CLS MODIFICATION No. :**  25415P4179, 25696P4347, 25713J1492, 25713K4481, 26138K4772, 27115J1522, 27446P5502, 27447P5503, 28068P5759, 28404K6135, 28507K6195, 28521K6229, 28661J2073, 28817J1973, 30139J2110, 30356P6683, 30373K6720, 31110K7004, 31143K7155, 31642K7282, 31700K7502, 32244K7774, 32261J2241, 33110K8396, 33198K8488, 33492J2482, 33670K6096, 33671K6098, 33672K4980, 34240K9240 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 the 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. P L** **A N**  **N I**  **N G**  **I N**  **F O**  **R M** **A T** **I O**  **N A. E**  **F F**  **E C** **T I** **V I** **T Y**  (1) Models 320-214 (2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft MSN: 0870 1137 1150 (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.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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OPERATOR MSN AUA 1137 1150 TAP 0870 (c) Effectivity by MSN and Kit/Configuration The Kits and configurations applicable to these MSNs are given at the end of this list 0870 KIT No. QTY PER A/C CONFIGURATION 281118A01R03 1 01 281118A02R03 1 01 281118A03R01 1 01 281118A04R05 1 01 281118A05R01 1 01 281118A06R01 1 01 281118A07R00 1 01 281118A08R01 1 01 281118A09R01 1 01 281118A10R02 1 01 281118A11R03 1 01 281118A12R00 1 01 281118A13R00 1 01 281118A15R00 1 01 281118A16R00 1 01 281118B01R00 1 01

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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KIT No. QTY PER A/C CONFIGURATION 281118B02R01 1 01 281118B03R00 1 01 281118B04R02 1 01 281118B05R00 1 01 281118D01R00 1 01 281118D02R00 1 01 281118D03R00 1 01 281118D04R00 1 01 281118D05R06 1 01 281118D06R03 1 01 281118D07R00 1 01 281118D08R00 1 01 281118D09R00 1 01 281118D10R00 1 01 281118D11R01 1 01 281118D12R00 1 01 281118D13R01 1 01 281118D14R00 1 01 281118D15R01 1 01 281118D16R02 1 01 281118D17R00 1 01 281118D18R00 1 01 281118D19R00 1 01 281118D21R00 1 01

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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KIT No. QTY PER A/C CONFIGURATION 281118D22R00 1 01 281118D23R01 1 01 281118D24R00 1 01 281118D25R00 1 01 281118D26R00 1 01 281118D31R00 1 01 281118D32R00 1 01 281118D33R02 1 01 281118D34R00 1 01 281118D35R01 1 01 281118D36R03 1 01 281118D50R02 1 01 281118D51R01 1 01 281118D60R00 1 01 281118D61R00 1 01 281118D62R00 1 01 281118D63R00 1 01 281118D67R02 1 01 281118D68R01 1 01 281118D69R01 1 01 281118D70R01 1 01 281118D71R01 1 01 281118D72R00 1 01 281118D73R00 1 01

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 4 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION 281118D74R00 1 01 281118D78R00 1 01 281118D79R00 1 01 281118D80R01 1 01 281118D81R00 1 01 281118D82R01 1 01 281118D83R01 1 01 281118D84R00 1 01 The Kits and configurations applicable to these MSNs are given at the end of this list 1137 1150 KIT No. QTY PER A/C CONFIGURATION 281118A01R03 1 02 281118A02R03 1 02 281118A03R01 1 02 281118A04R05 1 02 281118A05R01 1 02 281118A06R01 1 02 281118A07R00 1 02 281118A08R01 1 02 281118A10R02 1 02 281118A11R03 1 02 281118A12R00 1 02 281118A13R00 1 02

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 5 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION 281118A14R00 1 02 281118A15R00 1 02 281118A16R00 1 02 281118A18R00 1 02 281118B01R00 1 02 281118B02R01 1 02 281118B03R00 1 02 281118B04R02 1 02 281118B05R00 1 02 281118D01R00 1 02 281118D02R00 1 02 281118D03R00 1 02 281118D04R00 1 02 281118D05R06 1 02 281118D07R00 1 02 281118D09R00 1 02 281118D11R01 1 02 281118D13R01 1 02 281118D14R00 1 02 281118D15R01 1 02 281118D18R00 1 02 281118D19R00 1 02 281118D27R00 1 02 281118D29R00 1 02 281118D30R00 1 02

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 6 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION 281118D37R00 1 02 281118D38R00 1 02 281118D39R01 1 02 281118D40R02 1 02 281118D41R01 1 02 281118D42R01 1 02 281118D43R00 1 02 281118D44R00 1 02 281118D45R00 1 02 281118D46R01 1 02 281118D50R02 1 02 281118D51R01 1 02 281118D55R00 1 02 281118D56R00 1 02 281118D60R00 1 02 281118D61R00 1 02 281118D62R00 1 02 281118D63R00 1 02 281118D67R02 1 02 281118D69R01 1 02 281118D70R01 1 02 281118D72R00 1 02 281118D78R00 1 02 281118D79R00 1 02

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 7 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION 281118D80R01 1 02 281118D81R00 1 02 281118D82R01 1 02 281118D83R01 1 02 281118D84R00 1 02 281118D85R02 1 02 281118D86R00 1 02 281118D87R00 1 02 281118D91R01 1 02 281118D92R00 1 02 281118D93R00 1 02 281118D94R00 1 02 281118D95R00 1 02 281118D96R01 1 02 281118T01R00 1 02 NOTE : ADDITIONAL WORK 1 applicable for Configuration 02 is required for aircraft MSNs 1137 that have been modified by accomplishment of this Service Bulletin from the original to revision 02. NOTE : ADDITIONAL WORK 2 applicable for Configuration 02 is required for aircraft that has been modified by accomplishment of this Service Bulletin by revision 02. NOTE : Config. 01 is valid for aircraft MSN 0870 as a standard configuration. NOTE : Config. 02 is valid for aircraft MSN 1137 and 1150 as a standard configuration.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 8 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(3) Spares Config. 01 Door assy D5713019400200 Pipe assy D2821008001300 Computer 3QT SIC5059-11-0207 Fuel Quantity Indicator 6QT 1407KID02-03 Placard 32LM D11310817B00 Placard 33LM 002051-09 Placard 34LM D11310779A00 Placard 35LM D11310814A00 Placard 36LM 02048-23 Plate-Integrally Lighted 14LF 002098-05 Plate-Front 40VU D9251092000000 Config. 02 Door assy D5713019400200 Pipe assy D2821008001300 Computer 3QT SIC5059-11-0207 Fuel Quantity Indicator 6QT 1407KID02-03 Placard 32LM D11310817B00 Placard 33LM D11311191A00 Placard 34LM D11310779A00 Placard 35LM D11310814A00 Placard 36LM D11311157A00 Plate-Integrally Lighted 14LF 002098-05 Plate-Front 40VU D9251092000000 **B. C O**  **N C**  **U R**  **R E**  **N T**  **R E** **Q U**  **I R**  **E M**  **E N** **T S**  None **C. R E** **A S** **O N**  (1) History This Service Bulletin is issued in response to the request of a customer to install the systems and structural provisions in the aft cargo compartment for an Additional Center Tank (ACT). (2) Objective/Action This Service Bulletin describes the steps required to install the systems and the structural provisions for an ACT to be installed. (3) Advantages Installation of one Additional Center Tank (ACT) gives the aircraft an increased operational range due to the additional fuel capacity. Removal of the ACT provides an increased bulk loading capacity. (4) Operational/Maintenance Consequences The operational/maintenance consequences of this Service Bulletin are covered by the update of the affected publications detailed in PLANNING INFORMATION paragraph K. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 9 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

**D. D E** **S C**  **R I**  **P T** **I O**  **N** To accomplish this Service Bulletin it is necessary to: (1) Config. 01 (a) Install the doublers on the upper surface panels (b) Install the brackets on the upper surface panels (c) Install the rod on the upper surface panels (d) Install the bracket on FR42 (e) Install the bracket above FR42 (f) Install the brackets on the lower surface panels (g) Install the rod and the plate on the lower surface panels (h) Install the ACT door (i) Install the equipment on the ACT door (j) Replace the fuel quantity indicator 6QT (k) Modify the pipes in the center tank (l) Install the ACT pipes in the center tank (m) Install the transfert elbow (n) Install the air ventilation elbow (o) Apply the sealing protection to the center tank (p) Install the marking on the Belly Fairing (q) Modify the equipment in the Panel 40VU (r) Modify the equipment in the Panel 121VU (s) Modify the wiring in the Panel 121VU (t) Install the routing of Relay Box 802VU, between FR4 and FR5, in the avionics compartment (u) Install the connector 1982VC between FR33 and FR34 (v) Modify the equipment in the AFT Electronics Rack 80VU (w) Modify the equipment in the Relay Box 103VU DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 10 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(x) Modify the equipment in the Contactor Box 107VU (y) Modify the wiring in the aircraft (z) Modify the equipment in the FWD Electronics Rack 90VU (aa) Modify the Refuel Panel 51VU (ab) Modify the wiring in the aircraft (2) Config. 02 (a) Install the doublers on the upper surface panels (b) Install the brackets on the upper surface panels (c) Install the rod on the upper surface panels (d) Install the bracket on FR42 (e) Install the bracket above FR42 (f) Install the brackets on the lower surface panels (g) Install the rod and the plate on the lower surface panels (h) Install the ACT door (i) Install the equipment on the ACT door (j) Replace the fuel quantity indicator 6QT (k) Modify the pipes in the center tank (l) Install the ACT pipes in the center tank (m) Install the transfert elbow (n) Install the air ventilation elbow (o) Apply the sealing protection to the center tank (p) Install the marking on the Belly Fairing (q) Modify the equipment in the Panel 40VU (r) Modify the equipment in the Panel 121VU (s) Modify the wiring in the Panel 121VU (t) Install the routing of Relay Box 802VU, between FR4 and FR5, in the avionics compartment DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 11 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(u) Install the connector 1982VC between FR33 and FR34 (v) Modify the equipment in the AFT Electronics Rack 80VU (w) Modify the equipment in the Relay Box 103VU (x) Modify the equipment in the Contactor Box 107VU (y) Modify the wiring in the aircraft (z) Modify the equipment in the FWD Electronics Rack 90VU (aa) Modify the Refuel Panel 51VU (ab) Modify the wiring in the aircraft (3) Config. 01 thru Config. 02 Kit 281118B02R01 (a) Install the relay box in the forward avionics compartment. (4) Config. 01 thru Config. 02 Kit 281118B02R01, Kit 281118B03R00, Kit 281118B04R02 and Kit 281118B05R00 (a) Remove the refuel/defuel mounting assembly and the associated refuel-panel equipment in the belly fairing, Zone 192. (b) Install additional wiring between zones 192 and 132. (c) Install the new refuel/defuel mounting assembly and the associated refuel-panel equipment in the belly fairing, Zone 192. (5) Config. 01 thru Config. 02 Top Drawing D0007113700/002 (a) Remove and discard the belly fairing panel 197AB. (b) Modify the attachment structure of the belly fairing panel 197AB. (c) Remove and not reuse the pressure reservoirs for the offwing escape slides LH/RH. (d) Remove and discard the placards at the AFT cargo compartment lining panels between FR47 and FR48 LH/RH. (e) Remove and discard the overhead stowage compartments between FR43 and FR47. (f) Remove and discard the placards at the overhead stowage compartments between FR43 and FR47. (g) Remove and retain the insulation blankets in the affected areas. (h) Install the brackets for relocation of the pressure reservoirs of the offwing escape slides LH/RH. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 12 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(i) Modify and re-identify the insulation blankets after the bracket installation. (j) Install the retained insulation blankets in the affected areas. (k) Install the support and the tubes for the pressure reservoir of the offwing escape slide LH. (l) Install the support and the tubes for the pressure reservoir of the offwing escape slide RH. (m) Relocate the release cable for the offwing slide LH. (n) Relocate the release cable for the offwing slide RH. (o) Installation of the cable harness 5339VB from the terminal block 7223VT to the receptacle 7555VC. (p) Installation of the cable harness 5340VB from the terminal block 7224VT to the receptacle 7556VC. (q) Install the overhead stowage compartment between FR43 and FR47 LH/RH. (r) Install the placards at the overhead stowage compartment between FR43 and FR47 LH/RH (s) Install the pressure reservoir of the offwing escape slide LH between FR45 and FR47. (t) Install the pressure reservoir of the offwing escape slide RH between FR45 and FR47. (u) Install the additional angles at the webs of the keel beam structure between FR42 and FR46. (v) Replace the fasteners between FR42 and FR44, LH (w) Replace the fasteners between FR42 and FR44, RH. (x) Remove and discard the AFT cargo compartment partition panels 151AW, 151BW and 152BW at FR47. (y) Remove these placards. (z) Remove the sidewall panels 151EW and 151HW. (aa) Remove the sidewall panel 152DW. (ab) Remove the AFT cargo compartment ceiling panels between FR47 and FR59. (ac) Remove and discard the track between FR47 and FR52 and the YZ-latches at FR47, FR48, FR49, FR50 and FR51. (ad) Remove the screwed brackets for the old wire routing between FR46 and FR50. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 13 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(ae) Remove the brackets for the old wire routing between FR46 and FR50. (af) Install the corner fittings between FR46 and FR47 at -Y1292 and +Y1292. (ag) Replace fasteners between FR42 and FR46 at several places. (ah) Install the bonding brackets between FR42 and FR43 and between +Y254 and +Y765. (ai) Drill the hole between FR42 and FR43 for fuel/vent shroud drain system. (aj) Install the girder plates for the fuel/vent lines between FR42 and FR46 between +Y254 and -Y254. (ak) Drill the holes into FR46 between STGR42 LH and STGR43 LH. (al) Modify the structure of FR47 between STGR35 LH to STGR35 RH. (am) Modify the structure between FR47 and FR48 at STGR38 LH/RH and STGR43 LH. (an) Modify the structure at FR43 and FR44 between STGR21 LH/RH and STGR23 LH/RH. (ao) Install reinforcing angles between FR47 and FR49 at STGR1 LH/RH and STGR2 LH/RH and at FR48 between STGR8 LH/RH and STGR13 LH/RH. (ap) Install the struts at the beam between FR46 and FR47. (aq) Install the brackets at FR46 between +Y254 to +Y765 and -Y254 to -Y765. (ar) Modify the laying of the hydraulic tubes between FR46 and FR50. (as) Remove and retain the green hydraulic reservoir. (at) Install the brackets for the fuel drain/vent systems between FR42 and FR43. (au) Install the green hydraulic reservoir. (av) Install the beam between FR46 and FR47. (aw) Install the fuel transfer line between FR41 and FR47. (ax) Install the vent line between FR37 and FR47. (ay) Install the cover between FR46 and FR47 at the fuel transfer line and vent line. (az) Install the shroud drain system between FR37 and FR48. (ba) Install the cavity drain and monitoring system between FR46 and FR50. (bb) Replace the APU fuel shroud drain tube in the keel beam area between FR42 and FR47. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 14 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(bc) Remove and discard the attachment parts of the cable harness in the AFT cargo compartment bilge area between FR46 and FR50. (bd) Remove the cable harnesses 4605VB, 4655VB, 4656VB, 4661VB, 4662VB, 4663VB, 4664VB, 4671VB, 4672VB, 4673VB, 4680VB, 4681VB, 4683VB, 4692VB, 4693VB, 4694VB and 4696VB. (be) Install the brackets for the wiring between FR46 and FR50. (bf) Install the screwed brackets for the wiring between FR46 and FR49. (bg) Attach the cable harnesses in the AFT cargo compartment bilge area between FR46 and FR50. (bh) Attach the cable harnesses at FR42. (bi) Modify the wiring of the cable harnesses 4209VB, 4213VB, 4214VB, 4215VB, 4216VB, 4220VB, 4221VB, 4222VB, 4223VB, 4224VB, 4225VB, 4226VB, 4232VB, 4233VB and 5214VB. (bj) Remove the cable harnesses 4227VB, 4234VB, 5220VB, 5224VB and 5233VB. (bk) Install the cable harnesses 4227VB, 4234VB, 5220VB, 5224VB and 5233VB. (bl) Install the sidewall panels 151EW and 151HW. (bm) Install the sidewall panel 152DW. (bn) Install the AFT cargo compartment ceiling panels between FR47 and FR59. (bo) Install the AFT cargo compartment partition panels 151AW, 151BW and 152BW at FR47. (bp) Install the belly fairing panel 197AB. (6) Config. 01 Top Drawing D0007113700 (a) Remove and discard the attachment parts of the cable harness in the cabin floor crossbeam area at FR42 and between FR49 and FR55. (b) Remove and retain the attachment parts of the cable harness at FR42. (c) Modify the AFT-cargo-compartment sidewall-panel 152DW for access to the ACT pressurization system connection between FR49 and FR50. (d) Remove the wires from the cable harnesses 4619VB and 4620VB. (e) Remove and discard the passenger compartment floor panels 241JF, 251BF and 252BF. (f) Install a bracket at the passenger compartment floor structure at FR53. (g) Remove and discard the insulation blankets at FR46. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 15 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(h) Remove and discard the AFT cargo compartment floor panel between FR47 and FR52A and between FR56 and FR59. (i) Remove and discard the AFT cargo compartment floor panel between FR47 and FR59. (j) Replace the screwed brackets for the wire routing between FR41 and FR42. (k) Remove and discard the attachment structure of the partition panels 151AW, 151BW and 152BW. (l) Replace fasteners at FR48, FR49, FR50 and FR51 between STGR3 LH and STGR36 LH. (m) Remove the corner profiles at STGR38 LH/RH between FR48 and FR56. (n) Remove the shear plates at STGR38 LH/RH between FR48 and FR59. (o) Remove the crossbeams at FR48, FR49, FR50 and FR51 in the AFT cargo compartment. (p) Modify the structure at FR48 between STGR34 LH and STGR34 RH. (q) Modify the structure at FR49 between STGR34 LH and STGR34 RH. (r) Modify the structure at FR50 between STGR34 LH and STGR34 RH. (s) Modify the structure at FR51 between STGR34 LH and STGR34 RH. (t) Modify the structure at FR53 between STGR36 LH and STGR42 LH. (u) Install the shear plates between FR48 and FR51 at STGR43 LH. (v) Install the plates between FR48 and FR59 at STGR38 LH and STGR38 RH. (w) Install the corner sections at STGR38 LH/RH between FR48 and FR59. (x) Install a bracket at the passenger compartment floor structure at FR53. (y) Modify the crossbeams from FR48 thru FR52 for the roller track installation. (z) Install the water drain connection between FR47 and FR48. (aa) Install the water drain connection and the cavity drain access cover between FR49 and FR50. (ab) Drill three holes in the outer skin between FR47 and FR49 and between STGR43 LH and STGR42 RH. (ac) Measure the level of the AFT cargo compartment floor structure. (ad) Install the shims on the floor framework of the AFT cargo compartment between FR47 and FR51. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 16 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(ae) Install the roller tracks between FR47 and FR52 in the AFT cargo compartment. (af) Adjust the YZ-latches at FR47, FR48 and FR49. (ag) Adjust the YZ-latches at FR50, FR51 and FR52. (ah) Install the shims on the frames of the AFT cargo compartment at FR47, FR48, FR49, FR50 and FR51. (ai) Install the YZ-latches in the AFT cargo compartment at FR47, FR48, FR49, FR50 and FR51. (aj) Install the shims under the track and the YZ-latches between FR52 and FR59. (ak) Install the brackets for the fuel drain/vent systems between FR46 and FR54. (al) Install the ACT pressurization system between FR48 and FR54. (am) Install the attachment structure of the partition panels 151AW, 151BW and 152BW between FR46 and FR47. (an) Install the brackets for the wiring in cabin floor crossbeams between FR41 and 55. (ao) Install the cable harnesses 4605VB, 4655VB, 4656VB, 4661VB, 4662VB, 4663VB, 4664VB, 4671VB, 4672VB, 4673VB, 4680VB, 4681VB, 4683VB, 4692VB, 4693VB, 4694VB and 4696VB. (ap) Attach the cable harnesses in the cabin floor crossbeam area at FR42 and between FR49 and FR55. (aq) Modify the wiring of the cable harnesses 4606VB, 4607VB, 4628VB, 4640VB, 4644VB, 4648VB, 4650VB, 4670VB, 4675VB, 5609VB, 5662VB, 5663VB, 5664VB, 5670VB and 5675VB. (ar) Install the AFT cargo compartment floor panels between FR47 and FR52A and between FR56 and FR59. (as) Install the AFT cargo compartment floor panels between FR47 and FR59. (at) Install the seal sections in the gaps between the cargo compartment floor panels between FR47 and FR59. (au) Install the passenger compartment floor panels 241JF, 251BF and 252BF. (av) Seal the gaps at the installed passenger compartment floor panels 241JF, 251BF and 252BF. (aw) Modify the carpet to get access to the access panels in the passenger compartment floor panels 241JF, 251BF and 252BF. (ax) Install the AFT cargo compartment panels 151AW, 151BW and 152BW at FR47. (ay) Replace the placards at the side wall panels in the AFT cargo compartment. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 17 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(7) Config. 02 Top Drawing D00071137002 (a) Remove the corner profiles at STGR38 LH/RH between FR48 and FR56. (b) Remove the shear plates at STGR38 LH/RH between FR48 and FR59. (c) Remove the crossbeams at FR48, FR49, FR50 and FR51 in the AFT cargo compartment. (d) Modify the structure at FR48 between STGR34 LH and STGR34 RH. (e) Modify the structure at FR49 between STGR34 LH and STGR34 RH. (f) Modify the structure at FR50 between STGR34 LH and STGR34 RH. (g) Modify the structure at FR51 between STGR34 LH and STGR34 RH. (h) Install the shear plates between FR48 and FR51 at STGR43 LH. (i) Modify the structure at FR53 between STGR36 LH and STGR42 LH. (j) Install the shear plates between FR48 and FR51 at STGR43 LH. (k) Install the plates between FR48 and FR59 at STGR38 LH and STGR38 RH. (l) Install the corner sections at STGR38 LH/RH between FR48 and FR59. (m) Modify the crossbeams from FR48 thru FR52 for the roller track installation. (n) Install the water drain connection between FR47 and FR48. (o) Install the water drain connection and the cavity drain access cover between FR49 and FR50. (p) Drill three holes in the outer skin between FR47 and FR49 and between STGR43 LH and STGR42 RH. (q) Install the brackets for the fuel drain/vent systems between FR46 and FR54. (r) Replace fasteners at FR48, FR49, FR50 and FR51 between STGR3 LH and STGR36 LH. (s) Remove and discard the insulation blankets at FR46. (t) Install the insulation blankets at FR46. (u) Install a bracket at the passenger compartment floor structure at FR53. (v) Replace the bracket between FR46 and FR47. (w) Install the ACT pressurization system between FR48 and FR54. (x) Install the shims under the track and the YZ-latches between FR52 and FR59. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 18 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(y) Remove and discard the passenger compartment floor panels 231LF, 231MF, 241JF and 231QF. (z) Install the passenger compartment floor panels 231LF, 231MF and 241JF. (aa) Seal the gaps at the installed passenger compartment floor panels 231LF, 231MF and 241JF (ab) Remove and discard the AFT cargo compartment floor panel between FR47 and FR52A and between FR56 and FR59. (ac) Install the AFT cargo compartment floor panels between FR47 and FR52A and between FR56 and FR59. (ad) Install the seal sections in the gaps between the cargo compartment floor panels between FR47 and FR59. (ae) Remove and discard the attachment structure of the partition panels 151AW, 151BW and 152BW. (af) Install the attachment structure of the partition panels 151AW, 151BW and 152BW between FR46 and FR47. (ag) Install the attachment structure of the cargo compartment floor panels at FR49 and FR51. (ah) Install the roller tracks between FR47 and FR59. (ai) Install the YZ-Latches between FR47 and FR58. (aj) Install the ball mats between FR52A and FR56. (ak) Install the tie down point (TDP) and plugs. (al) Install the pins on the YZ-Guides. (am) Install the placards. (an) Replace the cable harness. (ao) Remove and discard the attachment parts of the cable harness in the cabin floor crossbeam area at FR42 and between FR49 and FR55. (ap) Attach the cable harnesses in the cabin floor crossbeam area at FR42 and between FR49 and FR55. (aq) Install the brackets for the wiring in cabin floor crossbeams at FR42, FR50 and FR54. (ar) Replace the screwed brackets for the wire routing between FR41 and FR42. (as) Replace the cable harnesses 4605VB, 4655VB, 4656VB, 4661VB, 4662VB, 4663VB, 4664VB, 4670VB, 4671VB, 4672VB, 4673VB, 4680VB, 4681VB, 4683VB, 4692VB, 4693VB, 4694VB and 4696VB. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 19 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(8) Config. 01 ADDITIONAL WORK (introduced by revision 01) NOTE : If this Service Bulletin has been accomplished before revision 01, it is necessary to do the additional work as described in this paragraph. Aircraft modified per revision 01 or later revisions are not affected by the additional work described in this paragraph. (a) Modify the fool proofing of the connector 47QJ-A (9) Config. 01 ADDITIONAL WORK (introduced by revision 02) NOTE : If this Service Bulletin has been accomplished before revision 02, it is necessary to do the additional work as described in this paragraph. Aircraft modified per revision 02 or later revisions are not affected by the additional work described in this paragraph. (a) Install the placards on the ACT door (b) Replace the fuel quantity indicator 6QT (10) Config. 02 , ADDITIONAL WORK ADDITIONAL WORK is required by this revision for aircraft modified at Revision 02. (a) Install the markings on the belly fairing. (11) Config. 02 ADDITIONAL WORK 1 (a) Preparation (b) Modification (c) Test (d) Close up (12) Config. 02 ADDITIONAL WORK 2 (a) Preparation (b) Modification (c) Test (d) Close up **E. C O**  **M P**  **L I** **A N**  **C E**  (1) Classification Optional (2) Accomplishment Timescale DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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In accordance with operators’ maintenance schedule. **F. A P**  **P R** **O V**  **A L**  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. M A** **N P** **O W** **E R**  The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc, and general administration work are also not included. Config. 01 thru Config. 02 Complete Modification on Aircraft Get Access 50.0 Modification 1350.0 Test 150.0 Close-up 50.0 **TOTAL MANHOURS 1600.0 ELAPSED TIME (HOURS) 350.0**  Config. 01 , ADDITIONAL WORK (introduced by revision 01) Get access 0.5 Modify the fool proofing FIN 47QJ-A 0.5 Test 0.5 Close up 0.5 **TOTAL MANHOURS 2.0 ELAPSED TIME (HOURS) 2.0**  Config. 01 , ADDITIONAL WORK (introduced by revision 02) Get access 0.5 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 21 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Install the placards on the ACT door 0.5 Replace the indicator 6QT 0.5 Test 0.5 Close-up 0.5 **TOTAL MANHOURS 2.5 ELAPSED TIME (HOURS) 2.5**  Config. 02 , ADDITIONAL WORK Get access 0.5 Install the markings on belly fairing 0.5 Close-up 0.5 **TOTAL MANHOURS 1.5 ELAPSED TIME (HOURS) 1.5**  **H. W E**  **I G**  **H T**  **A N**  **D B** **A L** **A N**  **C E**  Config. 01 thru Config. 02 Kit 281118A01R03 thru Kit 281118A016R00 Manufacturers Empty Weight : +17.608 kg (+38.8185 lb) Effect on Balance : +292.56 kgm (+2116.086 lb.ft) Config. 01 thru Config. 02 Kit 281118B01R00 Manufacturers Empty Weight : +2.26 kg (+4.9823 lb) Effect on Balance : +53.92 kgm (+390.003 lb.ft) Config. 01 thru Config. 02 Kit 281118D01R00 Manufacturers Empty Weight : +0.28 kg (+0.6172 lb) Effect on Balance : +5.16 kgm (+37.322 lb.ft) Config. 01 thru Config. 02 Kit 281118D02R00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 22 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Manufacturers Empty Weight : +20.32 kg (+44.7974 lb) Effect on Balance : +417.86 kgm (+3022.381 lb.ft) Config. 01 thru Config. 02 Kit 281118D03R00 Manufacturers Empty Weight : +0.67 kg (+1.4770 lb) Effect on Balance : +13.60 kgm (+98.368 lb.ft) Config. 01 thru Config. 02 Kit 281118D04R00 Not changed Config. 01 thru Config. 02 Kit 281118D05R06 Manufacturers Empty Weight : +15.26 kg (+33.6421 lb) Effect on Balance : +314.26 kgm (+2273.042 lb.ft) Config. 01 Kit 281118D06R03 Manufacturers Empty Weight : +16.48 kg (+36.3318 lb) Effect on Balance : +422.22 kgm (+3053.917 lb.ft) Config. 01 thru Config. 02 Kit 281118D07R00 Manufacturers Empty Weight : +0.12 kg (+0.2645 lb) Effect on Balance : +2,14 kgm (+15.478 lb.ft) Config. 01 Kit 281118D08R00 Manufacturers Empty Weight : +0.23 kg (+0.5070 lb) Effect on Balance : +5.24 kgm (+37.900 lb.ft) Config. 01 thru Config. 02 Kit 281118D09R00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 23 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Manufacturers Empty Weight : +0.38 kg (+0.8377 lb) Effect on Balance : +7.82 kgm (+56.562 lb.ft) Config. 01 Kit 281118D10R00 Manufacturers Empty Weight : +0.17 kg (+0.3747 lb) Effect on Balance : +3.54 kgm (+25.604 lb.ft) Config. 01 thru Config. 02 Kit 281118D11R01 Not changed Config. 01 thru Config. 02 Kit 281118D12R00 Manufacturers Empty Weight : +0.06 kg (+0.1322 lb) Effect on Balance : +1.59 kgm (+11.500 lb.ft) Config. 01 thru Config. 02 Kit 281118D13R01 Manufacturers Empty Weight : +23.30 kg (+51.3671 lb) Effect on Balance : +440.37 kgm (+3185.196 lb.ft) Config. 01 thru Config. 02 Kit 281118D14R00 Manufacturers Empty Weight : +2.07 kg (+4.5635 lb) Effect on Balance : +40.37 kgm (+291.996 lb.ft) Config. 01 thru Config. 02 Kit 281118D15R01 Manufacturers Empty Weight : +1.16 kg (+2.5573 lb) Effect on Balance : +25.40 kgm (+183.718 lb.ft) Config. 01 Kit 281118D16R02 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 24 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Manufacturers Empty Weight : +5.29 kg (+11.6623 lb) Effect on Balance : +127.86 kgm (+924.811 lb.ft) Config. 01 Kit 281118D17R00 Manufacturers Empty Weight : +1.35 kg (+2.9762 lb) Effect on Balance : +28.49 kgm (+206.068 lb.ft) Config. 01 thru Config. 02 Kit 281118D18R00 Manufacturers Empty Weight : +0.49 kg (+1.0802 lb) Effect on Balance : +10.24 kgm (+74.065 lb.ft) Config. 01 thru Config. 02 Kit 281118D19R00 Manufacturers Empty Weight : +1.01 kg (+2.2266 lb) Effect on Balance : +21.11 kgm (+152.688 lb.ft) Config. 01 Kit 281118D21R00 Manufacturers Empty Weight : +1.60 kg (+3.5273 lb) Effect on Balance : +41.44 kgm (+299.735 lb.ft) Config. 01 Kit 281118D22R00 Manufacturers Empty Weight : +3.93 kg (+8.6640 lb) Effect on Balance : +88.1 kgm (+637.227 lb.ft) Config. 01 Kit 281118D23R01 Manufacturers Empty Weight : +4.53 kg (+9.9868 lb) Effect on Balance : +110.08 kgm (+796.208 lb.ft) Config. 01 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 25 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Kit 281118D24R00 Manufacturers Empty Weight : +59.20 kg (+130.5123 lb) Effect on Balance : +1326.08 kgm (+9591.536 lb.ft) Config. 01 Kit 281118D25R00 Manufacturers Empty Weight : +10.469 kg (+23.0799 lb) Effect on Balance : +262.503 kgm (+1898.684 lb.ft) Config. 01 Kit 281118D26R00 Not changed Config. 02 Kit 281118D27R00 Manufacturers Empty Weight : +0.17 kg (+0.3747 lb) Effect on Balance : +3.54 kgm (+25.604 lb.ft) Config. 02 Kit 281118D29R00 Manufacturers Empty Weight : +0.52 kg (+1.1463 lb) Effect on Balance : +11.65 kgm (+84.264 lb.ft) Config. 02 Kit 281118D30R00 Manufacturers Empty Weight : +1.34 kg (+2.9541 lb) Effect on Balance : +32.16 kgm (+232.613 lb.ft) Config. 01 Kit 281118D31R00 Manufacturers Empty Weight : +2.35 kg (+5.1808 lb) Effect on Balance : +50.29 kgm (+363.747 lb.ft) Config. 01 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 26 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Kit 281118D32R00 Manufacturers Empty Weight : +0.52 kg (+1.1463 lb) Effect on Balance : +11.65 kgm (+84.264 lb.ft) Config. 01 Kit 281118D33R02 Manufacturers Empty Weight : +3.76 kg (+8.2892 lb) Effect on Balance : +88.55 kgm (+640.482 lb.ft) Config. 01 Kit 281118D34R00 Manufacturers Empty Weight : +1.34 kg (+2.9541 lb) Effect on Balance : +32.16 kgm (+232.613 lb.ft) Config. 01 Kit 281118D35R01 Manufacturers Empty Weight : +9.43 kg (+20.7893 lb) Effect on Balance : +229.15 kgm (+1657.441 lb.ft) Config. 01 Kit 281118D36R03 Manufacturers Empty Weight : +4.07 kg (+8.9727 lb) Effect on Balance : +91.17 kgm (+659.432 lb.ft) Config. 02 Kit 281118D37R00 Manufacturers Empty Weight : +3.76 kg (+8.2892 lb) Effect on Balance : +88.55 kgm (+640.482 lb.ft) Config. 02 Kit 281118D38R00 Manufacturers Empty Weight : +4.07 kg (+8.9727 lb) Effect on Balance : +91.17 kgm (+659.432 lb.ft) DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 27 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Config. 02 Kit 281118D39R01 Manufacturers Empty Weight : +2.35 kg (+5.1808 lb) Effect on Balance : +50.29 kgm (+363.747 lb.ft) Config. 02 Kit 281118D40R02 Manufacturers Empty Weight : +3.760 kg (+8.2892 lb) Effect on Balance : +87.150 kgm (+630.355 lb.ft) Config. 02 Kit 281118D41R01 Manufacturers Empty Weight : +64.618 kg (+142.4568 lb) Effect on Balance : +1456.466 kgm (+10534.618 lb.ft) Config. 02 Kit 281118D42R01 Manufacturers Empty Weight : +12.150 kg (+26.7858 lb) Effect on Balance : +293.936 kgm (+2126.039 lb.ft) Config. 02 Kit 281118D43R00 Manufacturers Empty Weight : +26.105 kg (+57.5510 lb) Effect on Balance : +658.823 kgm (+4765.266 lb.ft) Config. 02 Kit 281118D44R00 Manufacturers Empty Weight : +0.299 kg (+0.6591 lb) Effect on Balance : +5.622 kgm (+40.663 lb.ft) Config. 02 Kit 281118D45R00 Manufacturers Empty Weight : +0.002 kg (+0.0044 lb) DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 28 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Effect on Balance : +0.063 kgm (+0.455 lb.ft) Config. 02 Kit 281118D46R01 Not changed Config. 01 thru Config. 02 Kit 281118D50R02 Manufacturers Empty Weight : -0.42 kg (-0.9260 lb) Effect on Balance : -7.98 kgm (-57.720 lb.ft) Config. 01 thru Config. 02 Kit 281118D51R01 Manufacturers Empty Weight : -0.41 kg (-0.9039 lb) Effect on Balance : -7.79 kgm (-56.346 lb.ft) Config. 02 Kit 281118D55R00 Manufacturers Empty Weight : +0.06 kg (+0.1322 lb) Effect on Balance : +1.59 kgm (+11.500 lb.ft) Config. 02 Kit 281118D56R00 Not changed Config. 01 thru Config. 02 Kit 281118D60R00 Manufacturers Empty Weight : +0.10 kg (+0.2204 lb) Effect on Balance : +2.22 kgm (+16.057 lb.ft) Config. 01 thru Config. 02 Kit 281118D61R00 Manufacturers Empty Weight : +3.32 kg (+7.3192 lb) Effect on Balance : +63.74 kgm (+461.031 lb.ft) DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 29 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Config. 01 thru Config. 02 Kit 281118D62R00 Manufacturers Empty Weight : +0.30 kg (+0.6613 lb) Effect on Balance : +5.73 kgm (+41.445 lb.ft) Config. 01 thru Config. 02 Kit 281118D63R00 Manufacturers Empty Weight : +0.30 kg (+0.6613 lb) Effect on Balance : +5.73 kgm (+41.445 lb.ft) Config. 01 thru Config. 02 Kit 281118D67R02 Manufacturers Empty Weight : +1.86 kg (+4.1005 lb) Effect on Balance : +34.78 kgm (+251.563 lb.ft) Config. 01 Kit 281118D68R01 Manufacturers Empty Weight : +6.35 kg (+13.9992 lb) Effect on Balance : +134.62 kgm (+973.706 lb.ft) Config. 01 thru Config. 02 Kit 281118D69R01 Manufacturers Empty Weight : +1.73 kg (+3.8139 lb) Effect on Balance : +37.80 kgm (+273.407 lb.ft) Config. 01 thru Config. 02 Kit 281118D70R01 Manufacturers Empty Weight : +1.04 kg (+2.2927 lb) Effect on Balance : +23.09 kgm (+167.009 lb.ft) Config. 01 Kit 281118D71R01 Manufacturers Empty Weight : +0.17 kg (+0.3747 lb) DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 30 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Effect on Balance : +3.98 kgm (+28.787 lb.ft) Config. 01 thru Config. 02 Kit 281118D72R00 Manufacturers Empty Weight : +0.35 kg (+0.7716 lb) Effect on Balance : +7.52 kgm (+54.392 lb.ft) Config. 01 Kit 281118D73R00 Manufacturers Empty Weight : +0.27 kg (+0.5952 lb) Effect on Balance : +4.96 kgm (+35.875 lb.ft) Config. 01 Kit 281118D74R00 Manufacturers Empty Weight : +7.30 kg (+16.0935 lb) Effect on Balance : +158.41 kgm (+1145.779 lb.ft) Config. 02 Kit 281118D78R00 Manufacturers Empty Weight : +7.207 kg (+15.8885 lb) Effect on Balance : +182.960 kgm (+1323.349 lb.ft) Config. 02 Kit 281118D79R00 Manufacturers Empty Weight : +0.755 kg (+1.6644 lb) Effect on Balance : +17.636 kgm (+127.561 lb.ft) Config. 02 Kit 281118D80R01 Manufacturers Empty Weight : +1.75 kg (+3.8580 lb) Effect on Balance : +42.05 kgm (+304.147 lb.ft) Config. 01 thru Config. 02 Kit 281118D81R00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 31 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Manufacturers Empty Weight : +1.72 kg (+3.7919 lb) Effect on Balance : +36.73 kgm (+265.668 lb.ft) Config. 01 thru Config. 02 Kit 281118D82R01 Not changed Config. 01 thru Config. 02 Kit 281118D83R01 Manufacturers Empty Weight : +0.19 kg (+0.4188 lb) Effect on Balance : +3.66 kgm (+26.472 lb.ft) Config. 01 thru Config. 02 Kit 281118D84R00 Manufacturers Empty Weight : +11.40 kg (+25.1324 lb) Effect on Balance : +243.96 kgm (+1764.562 lb.ft) Config. 02 Kit 281118D85R02 Manufacturers Empty Weight : +16.48 kg (+36.3318 lb) Effect on Balance : +422.22 kgm (+3053.917 lb.ft) Config. 01 Kit 281118D86R00 Manufacturers Empty Weight : +0.234 kg (+0.5158 lb) Effect on Balance : +5.132 kgm (+37.119 lb.ft) Config. 02 Kit 281118D87R00 Manufacturers Empty Weight : +16.48 kg (+36.3318 lb) Effect on Balance : +422.22 kgm (+3053.917 lb.ft) Config. 02 Kit 281118D91R01 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 32 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Manufacturers Empty Weight : +5.29 kg (+11.6623 lb) Effect on Balance : +127.86 kgm (+924.811 lb.ft) Config. 02 Kit 281118D92R00 Manufacturers Empty Weight : +1.35 kg (+2.9762 lb) Effect on Balance : +28.49 kgm (+206.068 lb.ft) Config. 02 Kit 281118D93R00 Manufacturers Empty Weight : +6.35 kg (+13.9992 lb) Effect on Balance : +134.62 kgm (+973.706 lb.ft) Config. 02 Kit 281118D94R00 Manufacturers Empty Weight : +0.17 kg (+0.3747 lb) Effect on Balance : +3.98 kgm (+28.787 lb.ft) Config. 02 Kit 281118D95R00 Manufacturers Empty Weight : +0.27 kg (+0.5952 lb) Effect on Balance : +4.96 kgm (+35.875 lb.ft) Config. 02 Kit 281118D96R01 Manufacturers Empty Weight : +7.30 kg (+16.0935 lb) Effect on Balance : +158.41 kgm (+1145.779 lb.ft) Kit D46R01 ADDITIONAL WORK 1 Not changed Kit D41R01 ADDITIONAL WORK 2 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 33 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Not changed **I. E L**  **E C** **T R**  **I C** **A L**  **L O** **A D**  **D A**  **T**

**A** Not changed

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 34 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

**J. R E**  **F E**  **R E**  **N C**  **E S**  Aircraft Maintenance Manual (AMM) : 06-31-53 06-41-53 07-11-00 11-00-00 12-34-24 20-21-11 20-21-12 20-21-15 20-23-11 20-28-00 21-21-00 21-26-00 21-31-00 21-51-00 21-55-00 21-61-00 21-63-00 22-61-00 22-63-00 22-66-34 22-83-34 22-96-00 22-97-00 23-11-00 23-12-00 23-13-00 23-44-00 23-51-00 23-71-00 23-73-00 24-22-33 24-22-55 24-23-17 24-23-34 24-23-51 24-23-55 24-24-00 24-24-51 24-32-00 24-38-51 24-41-00 24-62-55 25-13-41 25-23-41 25-23-43 25-23-44 25-23-48 25-21-41 25-23-41 25-23-43 25-23-44 25-23-48 25-24-41 25-28-41 25-33-41 25-52-21 25-52-22 25-52-44 25-52-69 25-54-12 25-55-11 25-62-43 25-62-46 25-80-00 26-12-00 26-12-12 26-13-00 26-15-00 26-17-00 26-21-00 26-22-00 27-22-00 27-24-00 27-34-00 27-51-00 27-54-00 27-55-11 27-81-00 27-84-00 27-92-15 27-92-16 27-92-41 27-93-00 27-94-00 27-96-00 28-00-00 28-10-00 28-11-00 28-15-00 28-21-00 28-22-00 28-23-00 28-23-51 28-24-00 28-25-00 28-25-51 28-25-55 28-25-58 28-28-00 28-29-00 28-42-00 28-42-01 28-42-22 28-42-34 28-46-00 29-00-00 29-10-00 29-11-00 29-11-41 29-12-00 29-13-00 29-13-14 29-14-00 29-19-51 29-22-00 29-23-00 29-24-00 29-31-00 29-32-00 29-33-11 29-34-00 30-11-00 30-31-00 30-42-00 31-32-00 31-33-00 31-35-00 31-36-00 31-50-00 31-55-34 31-60-00 32-12-00 32-31-00 32-33-00 32-33-17 32-42-00 32-43-00 32-44-00 32-45-00 32-45-52 32-46-00 32-47-00 32-48-00 32-51-00 32-69-00 33-13-00 33-14-00 33-31-00 33-37-00 33-41-00 33-42-00 33-48-00 33-51-00 34-10-00 34-12-34 34-13-00 34-14-00 34-42-00 34-48-00 34-51-00 34-55-00 34-58-31 35-13-14 35-23-00 36-11-00 36-12-00 38-31-34 49-61-34 49-62-00 52-10-00 52-30-00 52-35-00 52-40-00 52-41-00 52-41-16 52-41-23 53-22-12 53-22-14 53-35-11 53-42-12 53-42-14 73-25-34 74-00-00 77-32-34 78-31-00 Structural Repair Manual (SRM) : 51-22-00 51-23-00 51-24-00 51-42-11 51-43-12 51-44-11 51-46-00 51-46-11 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 35 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Consumable Material List (CML) Electrical Standard Practices Manual (ESPM) : 20-25-51 20-33-00 20-33-44 20-44-22 20-44-24 20-44-71 20-51-10 20-52-21 20-55-00 Top Drawing : D0007113700000 Aircraft Wiring List (AWL) Process and Material Specification Manual (PMS) Standards Manual (SM) Appendix 1 Top Drawing D0007113700000, Sheet(s) 01 Issue A00 Top Drawing D0007113700200, Sheet(s) 02 Issue B00 DESIGN DRAWINGS SHEET(S) 281118A00001 Sheet(s) 01 A00 281118A00001 Sheet(s) 02 A00 281118A00001 Sheet(s) 03 A00 281118A00001 Sheet(s) 04 A00 281118A00001 Sheet(s) 05 A00 281118A00002 Sheet(s) 01 A00 281118A00002 Sheet(s) 02 A00 281118A00002 Sheet(s) 03 A00 281118A00002 Sheet(s) 04 A00 281118A00002 Sheet(s) 05 B00 281118A01001 Sheet(s) 01 A00 281118A01001 Sheet(s) 02 A00 281118A01001 Sheet(s) 03 B00 281118A01002 Sheet(s) 01 A00 281118A01003 Sheet(s) 01 A00 281118A01003 Sheet(s) 02 A00 281118A01003 Sheet(s) 03 A00 281118A01003 Sheet(s) 04 B00 281118A01004 Sheet(s) 01 A00 281118A02001 Sheet(s) 01 A00 281118A02002 Sheet(s) 01 A00 281118A02002 Sheet(s) 02 A00 281118A02002 Sheet(s) 03 B00 281118A02003 Sheet(s) 01 A00 281118A02003 Sheet(s) 02 A00 281118A02003 Sheet(s) 03 B00 281118A02004 Sheet(s) 01 A00 281118A02004 Sheet(s) 02 A00 281118A03000 Sheet(s) 01 A00 281118A03001 Sheet(s) 01 B00 281118A03002 Sheet(s) 01 A00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 36 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281118A03002 Sheet(s) 02 A00 281118A03003 Sheet(s) 01 A00 281118A03003 Sheet(s) 02 A00 281118A03003 Sheet(s) 03 B00 281118A03003 Sheet(s) 04 A00 281118A03003 Sheet(s) 05 A00 281118A04000 Sheet(s) 01 A00 281118A04001 Sheet(s) 01 A00 281118A04001 Sheet(s) 02 A00 281118A04001 Sheet(s) 03 A00 281118A04002 Sheet(s) 01 A00 281118A04002 Sheet(s) 02 A00 281118A04002 Sheet(s) 03 A00 281118A04002 Sheet(s) 04 A00 281118A04003 Sheet(s) 01 A00 281118A04003 Sheet(s) 02 A00 281118A04003 Sheet(s) 03 A00 281118A04003 Sheet(s) 04 A00 281118A04003 Sheet(s) 05 A00 281118A04003 Sheet(s) 06 B00 281118A04003 Sheet(s) 07 B00 281118A04004 Sheet(s) 01 A00 281118A04005 Sheet(s) 01 A00 281118A04006 Sheet(s) 01 A00 281118A04007 Sheet(s) 01 A00 281118A04008 Sheet(s) 01 A00 281118A04009 Sheet(s) 01 A00 281118A04010 Sheet(s) 01 A00 281118A04011 Sheet(s) 01 A00 281118A04011 Sheet(s) 02 A00 281118A04012 Sheet(s) 01 A00 281118A04013 Sheet(s) 01 B00 281118A05001 Sheet(s) 01 A00 281118A05002 Sheet(s) 01 A00 281118A05003 Sheet(s) 01 A00 281118A05003 Sheet(s) 02 A00 281118A06000 Sheet(s) 01 A00 281118A06001 Sheet(s) 01 A00 281118A06002 Sheet(s) 01 B00 281118A06002 Sheet(s) 02 A00 281118A06003 Sheet(s) 01 B00 281118A06501 Sheet(s) 01 A00 281118A06501 Sheet(s) 02 A00 281118A06502 Sheet(s) 01 A00 281118A06502 Sheet(s) 02 A00 281118A06503 Sheet(s) 01 A00 281118A06503 Sheet(s) 02 A00 281118A06504 Sheet(s) 01 A00 281118A06504 Sheet(s) 02 A00 281118A06505 Sheet(s) 01 A00 281118A06505 Sheet(s) 02 A00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 37 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281118A06506 Sheet(s) 01 A00 281118A06506 Sheet(s) 02 A00 281118A06507 Sheet(s) 01 A00 281118A06507 Sheet(s) 02 A00 281118A06508 Sheet(s) 01 A00 281118A06508 Sheet(s) 02 A00 281118A06509 Sheet(s) 01 A00 281118A06509 Sheet(s) 02 A00 281118A06510 Sheet(s) 01 A00 281118A06510 Sheet(s) 02 A00 281118A06511 Sheet(s) 01 A00 281118A06511 Sheet(s) 02 A00 281118A09000 Sheet(s) 01 A00 281118A09001 Sheet(s) 01 A00 281118A10001 Sheet(s) 01 A00 281118A10001 Sheet(s) 02 A00 281118A10002 Sheet(s) 01 A00 281118A10003 Sheet(s) 01 B00 281118A10003 Sheet(s) 02 B00 281118A10004 Sheet(s) 01 A00 281118A10004 Sheet(s) 02 A00 281118A10005 Sheet(s) 01 A00 281118A10005 Sheet(s) 02 A00 281118A10006 Sheet(s) 01 A00 281118A10007 Sheet(s) 01 A00 281118A10007 Sheet(s) 02 A00 281118A10008 Sheet(s) 01 A00 281118A10008 Sheet(s) 02 A00 281118A10501 Sheet(s) 01 A00 281118A10501 Sheet(s) 02 A00 281118A10502 Sheet(s) 01 A00 281118A10502 Sheet(s) 02 A00 281118A10502 Sheet(s) 03 A00 281118A10503 Sheet(s) 01 A00 281118A10503 Sheet(s) 02 A00 281118A10504 Sheet(s) 01 A00 281118A10504 Sheet(s) 02 A00 281118A10505 Sheet(s) 01 B00 281118A10505 Sheet(s) 02 B00 281118A10506 Sheet(s) 01 A00 281118A10506 Sheet(s) 02 A00 281118A10507 Sheet(s) 01 A00 281118A10507 Sheet(s) 02 A00 281118A10507 Sheet(s) 03 A00 281118A10508 Sheet(s) 01 A00 281118A10508 Sheet(s) 02 A00 281118A10509 Sheet(s) 01 B00 281118A10509 Sheet(s) 02 A00 281118A10510 Sheet(s) 01 B00 281118A10510 Sheet(s) 02 B00 281118A10511 Sheet(s) 01 A00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 38 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281118A10511 Sheet(s) 02 B00 281118A10512 Sheet(s) 01 A00 281118A10512 Sheet(s) 02 A00 281118A10513 Sheet(s) 01 A00 281118A10513 Sheet(s) 02 A00 281118A10514 Sheet(s) 01 A00 281118A10514 Sheet(s) 02 A00 281118A10515 Sheet(s) 01 A00 281118A10515 Sheet(s) 02 A00 281118A10516 Sheet(s) 01 A00 281118A10516 Sheet(s) 02 A00 281118A10517 Sheet(s) 01 A00 281118A10517 Sheet(s) 02 A00 281118A10518 Sheet(s) 01 A00 281118A10518 Sheet(s) 02 A00 281118A10519 Sheet(s) 01 A00 281118A10519 Sheet(s) 02 A00 281118A10520 Sheet(s) 01 A00 281118A10520 Sheet(s) 02 A00 281118A10521 Sheet(s) 01 B00 281118A10521 Sheet(s) 02 A00 281118A11000 Sheet(s) 01 A00 281118A11001 Sheet(s) 01 A00 281118A11002 Sheet(s) 01 B00 281118A11002 Sheet(s) 02 B00 281118A11003 Sheet(s) 01 A00 281118A11003 Sheet(s) 02 A00 281118A12001 Sheet(s) 01 A00 281118A12002 Sheet(s) 01 A00 281118A12501 Sheet(s) 01 A00 281118A12501 Sheet(s) 02 A00 281118A12502 Sheet(s) 01 A00 281118A12502 Sheet(s) 02 A00 281118A12503 Sheet(s) 01 A00 281118A14000 Sheet(s) 01 A00 281118A14001 Sheet(s) 01 A00 281118A15001 Sheet(s) 01 A00 281118A16001 Sheet(s) 01 A00 281118A16001 Sheet(s) 02 A00 281118A16001 Sheet(s) 03 A00 281118A18001 Sheet(s) 01 A00 281118A18001 Sheet(s) 02 A00 D25286364010 Sheet(s) 7 and 8 D25288767000 Sheet(s) 1 and 2 D25570048000 Sheet(s) 1 D25570048002 Sheet(s) 2 D25570048004 Sheet(s) 3 D25570048006 Sheet(s) 4 D25571787004 Sheet(s) 1 and 3 D25572631000 Sheet(s) 1 thru 3 D25572631002 Sheet(s) 5 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 39 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) D25572631004 Sheet(s) 6 D25572631006 Sheet(s) 7 D25572631006 Sheet(s) 7 and 8 D25572631008 Sheet(s) 10 and 13 D25572631008 Sheet(s) 10 thru 12 D25572631008 Sheet(s) 11 and 13 D25572631008 Sheet(s) 12 and 13 D25572631012 Sheet(s) 1, 16 and 17 D25572631022 Sheet(s) 22 D25572631024 Sheet(s) 23 thru 29 D25572631026 Sheet(s) 30 thru 33 D25572631028 Sheet(s) 34 and 35 D25572631030 Sheet(s) 36 D25572631032 Sheet(s) 37 D25572631034 Sheet(s) 38 D25572631036 Sheet(s) 41 D25573522000 Sheet(s) 1 D25573524000 Sheet(s) 1 thru 4 D25670762000 Sheet(s) 1 thru 7 D25671745000 Sheet(s) 1 thru 7 D25671746000 Sheet(s) 1 thru 4 D25690000004 Sheet(s) 7 thru 9 D25870003028 Sheet(s) 20 D25870003054 Sheet(s) 20 D26270107000 Sheet(s) 1 thru 3 D28270972002 Sheet(s) 7 thru 12 D28270972002 Sheet(s) 8 D28270972002 Sheet(s) 8 and 10 D28270972002 Sheet(s) 9 thru 12 D28270973002 Sheet(s) 6 thru 10 D28270974002 Sheet(s) 4 thru 6 D28270975002 Sheet(s) 7 thru 12 D28270975006 Sheet(s) 8, 11 and 13 thru 16 D28270982002 Sheet(s) 12 D28270982002 Sheet(s) 13 D28270982002 Sheet(s) 14 D28270982002 Sheet(s) 17 D28270982002 Sheet(s) 17 and 18 D28270982002 Sheet(s) 17 and 20 D28270982002 Sheet(s) 18 and 19 D28270982002 Sheet(s) 20 D28270982002 Sheet(s) 21 and 22 D28270982002 Sheet(s) 23 and 22 D28270982006 Sheet(s) 12 D28270982006 Sheet(s) 13 D28270982006 Sheet(s) 14 D28270982006 Sheet(s) 19 D28270982006 Sheet(s) 20 and 24 D28270982006 Sheet(s) 23 and 26 D28270982006 Sheet(s) 23 and 27 D28270982006 Sheet(s) 24 and 25 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 40 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) D28270982006 Sheet(s) 24 and 28 D28270998002 Sheet(s) 2 D28270999004 Sheet(s) 3 D28271200000 Sheet(s) 1 and 2 D32170220004 Sheet(s) 5 D32170220005 Sheet(s) 5 D53370297000 Sheet(s) 1 thru 3 D53370297000 Sheet(s) 4 thru 6 D53370297000 Sheet(s) 7 thru 10 and 12 D53370297001 Sheet(s) 1 thru 3 D53370297001 Sheet(s) 4 thru 6 D53370297001 Sheet(s) 7 thru 9, 11, 12 D53370780000 Sheet(s) 1 D53371046000 Sheet(s) 1 D53371046000 Sheet(s) 2 D53371046000 Sheet(s) 3 D53371046000 Sheet(s) 4 D53371046000 Sheet(s) 5 D53371237000 Sheet(s) 1 D53371237001 Sheet(s) 1 D53372362000 D53372362000 Sheet(s) 1 and 3 D53372362000 Sheet(s) 1, 2 and 3 D53372362000 Sheet(s) 2 and 3 D53372362000 Sheet(s) 3 D53372362000 Sheet(s) 4 D53372362000 Sheet(s) 5, 7, 8 and 9 D53372362000 Sheet(s) 5, 8 and 9 D53372362000 Sheet(s) 6 D53372362000 Sheet(s) 7 D53372362000 Sheet(s) 8 D53372362000 Sheet(s) 9 D53372362000 Sheet(s) 9 and 10 D53372366000 Sheet(s) 1 D53470075002 Sheet(s) 2, 3 and 4 D53470075002 Sheet(s) 1, 2, 3, 4, 6, 10 and 11 D53470075002 Sheet(s) 10 D53470075002 Sheet(s) 12 D53470075002 Sheet(s) 13 D53470075002 Sheet(s) 14 D53470075002 Sheet(s) 2 D53470075002 Sheet(s) 3 D53470075002 Sheet(s) 3 and 7 D53470075002 Sheet(s) 4 D53470075002 Sheet(s) 4 and 7 D53470075002 Sheet(s) 5 D53470075002 Sheet(s) 6 D53470075002 Sheet(s) 8 and 11 D53470075002 Sheet(s) 9 and 10 D53470075004 Sheet(s) 10 D53470075004 Sheet(s) 12 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 41 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) D53470075004 Sheet(s) 13 D53470075004 Sheet(s) 14 D53470075004 Sheet(s) 16 D53470075004 Sheet(s) 17 D53470075004 Sheet(s) 2 D53470075004 Sheet(s) 2, 3, 4 and 16 D53470075004 Sheet(s) 2, 3, 4, 6, 10, 11, 16 and 17 D53470075004 Sheet(s) 3 D53470075004 Sheet(s) 3 and 7 D53470075004 Sheet(s) 4 D53470075004 Sheet(s) 4, 7 and 16 D53470075004 Sheet(s) 6 D53470075004 Sheet(s) 8 and 11 D53470075004 Sheet(s) 8, 11 and 17 D53470075004 Sheet(s) 9 and 10 D53470095000 Sheet(s) 1 D53470095002 Sheet(s) 1 D53472833002 Sheet(s) 2 D53472833008 Sheet(s) 4 D53475023000 Sheet(s) 1 D53475023000 Sheet(s) 1 thru 4 D53672848000 Sheet(s) 1 D53672848000 Sheet(s) 2 and 3 D53672848002 Sheet(s) 1 D53672848002 Sheet(s) 5 and 6 D53672849000 Sheet(s) 1 thru 3 D53672849002 Sheet(s) 4 thru 6 D53672850000 Sheet(s) 1 D53672850000 Sheet(s) 2 and 3 D53675013000 Sheet(s) 1 D53675013000 Sheet(s) 2 and 3 D53675013010 Sheet(s) 12 D53675013010 Sheet(s) 12 thru 14 D53675014000 Sheet(s) 1 and 2 D53675014002 Sheet(s) 3 and 4 D53675511002 Sheet(s) 4 thru 6 D53975018000 Sheet(s) 1 thru 3 D53975018000 Sheet(s) 3 D53975018000 Sheet(s) 4 thru 6 D53975018002 Sheet(s) 10 thru 12 D53975018002 Sheet(s) 7 thru 9 D92492243000 Sheet(s) 1 thru 13 and 21 D92492243002 Sheet(s) 14 thru 20 D92492243004 Sheet(s) 22 thru 25 D92492244000 Sheet(s) 1 thru 9 D92492244000 Sheet(s) 1, 2, 4, 6 and 8 D92492244002 Sheet(s) 10 D92891803000 Sheet(s) 1 thru 16 D92891803000 Sheet(s) 1, 2, 4, 6, 8, 10, 11 and 13 D92891803002 Sheet(s) 18, 20, 22, 24, 25, 26, 27, 28, 30 and 31 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 42 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) D92891803002 Sheet(s) 19, 21, 23, 25, 26, 27, 28, 29 and 31 D92891803004 Sheet(s) 32 thru 38 D92891803006 Sheet(s) 40 thru 54 D92894713020 Sheet(s) 1 D92894736004 Sheet(s) 14 thru 17 D92895832002 Sheet(s) 2 thru 19 D92990609001 Sheet(s) 1 D92990609002 Sheet(s) 2 D92990613012 Sheet(s) 13 D92990613014 Sheet(s) 14 D92990614128 Sheet(s) 71 D92990614130 Sheet(s) 73 D92990615007 Sheet(s) 10 D92990615008 Sheet(s) 11 D92990616003 Sheet(s) 2 D92990616004 Sheet(s) 3 D92990620042 Sheet(s) 3 D92990620044 Sheet(s) 4 D92990621002 Sheet(s) 3 D92990621003 Sheet(s) 6 D92990622003 Sheet(s) 3 D92990622004 Sheet(s) 5 D92990623010 Sheet(s) 12 and 13 D92990623011 Sheet(s) 14 and 16 D92990624048 Sheet(s) 7 D92990624053 Sheet(s) 8 D92990625010 Sheet(s) 14 and 15 D92990625011 Sheet(s) 15 and 16 D92990626008 Sheet(s) 13 and 14 D92990626009 Sheet(s) 13 and 15 D92990627010 Sheet(s) 14 and 15 D92990627011 Sheet(s) 15 and 16 D92990632007 Sheet(s) 7 and 8 D92990632009 Sheet(s) 8 and 9 D92990633042 Sheet(s) 1 D92990633044 Sheet(s) 3 D92990634001 Sheet(s) 2 D92990634002 Sheet(s) 3 D92990814015 Sheet(s) 22 and 25 D92990814020 Sheet(s) 22 and 30 D92990820000 Sheet(s) 1 D92990820001 Sheet(s) 2 D92990824002 Sheet(s) 3 D92990824007 Sheet(s) 7 D92990833000 Sheet(s) 1 D92990833001 Sheet(s) 2 D92991405000 Sheet(s) 1 D92991405001 Sheet(s) 2 D92991455004 Sheet(s) 5 D92991455005 Sheet(s) 6 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 43 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) D92991456002 Sheet(s) 3 D92991456003 Sheet(s) 4 D92991461010 Sheet(s) 15 D92991461011 Sheet(s) 16 D92991461013 Sheet(s) 18 D92991461015 Sheet(s) 20 D92991462006 Sheet(s) 7 D92991462007 Sheet(s) 8 D92991463003 Sheet(s) 8 D92991463004 Sheet(s) 10 D92991464002 Sheet(s) 4 D92991464003 Sheet(s) 5 D92991470006 Sheet(s) 7 D92991470008 Sheet(s) 9 D92991471002 Sheet(s) 4 D92991471003 Sheet(s) 5 D92991471004 Sheet(s) 6 D92991471006 Sheet(s) 8 D92991472007 Sheet(s) 8 D92991472008 Sheet(s) 9 D92991472010 Sheet(s) 11 D92991472015 Sheet(s) 12 D92991473001 Sheet(s) 2 D92991473002 Sheet(s) 3 D92991480008 Sheet(s) 9 D92991480010 Sheet(s) 11 D92991481001 Sheet(s) 2 D92991481002 Sheet(s) 3 D92991481010 Sheet(s) 11 D92991483003 Sheet(s) 4 D92991483004 Sheet(s) 5 D92991492001 Sheet(s) 2 D92991492002 Sheet(s) 3 D92991492003 Sheet(s) 4 D92991492006 Sheet(s) 7 D92991493001 Sheet(s) 2 D92991493002 Sheet(s) 3 D92991494001 Sheet(s) 2 D92991494002 Sheet(s) 3 D92991496002 Sheet(s) 3 D92991496003 Sheet(s) 3 D92991496003 Sheet(s) 4 D92992294044 Sheet(s) 23 and 24 D92997026001 Sheet(s) 1 and 2 D92997026001 Sheet(s) 2 D92997026002 Sheet(s) 3 thru 8 D92997026002 Sheet(s) 4, 6 and 8 D92997026004 Sheet(s) 10, 12, 14, 16 and 18 D92997026004 Sheet(s) 9 thru 18 D92997026005 Sheet(s) 19 and 20 D92997026005 Sheet(s) 20 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 44 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) D92997026006 Sheet(s) 21 and 22 D92997026006 Sheet(s) 22 D92997026007 Sheet(s) 23 and 24 D92997026007 Sheet(s) 24 D92997026008 Sheet(s) 25 and 26 D92997026008 Sheet(s) 26 D92997026015 Sheet(s) 28 and 30 D92997026019 Sheet(s) 31 and 32 D92997026019 Sheet(s) 32 D92997026027 Sheet(s) 33 and 34 D92997026027 Sheet(s) 34 D92997026028 Sheet(s) 35 and 36 D92997026028 Sheet(s) 36 D92997026029 Sheet(s) 37 and 38 D92997026029 Sheet(s) 38 D92997026030 Sheet(s) 39 and 40 D92997026030 Sheet(s) 40 D92997026031 Sheet(s) 41 and 42 D92997026031 Sheet(s) 42 D92997026032 Sheet(s) 43 and 44 D92997026032 Sheet(s) 44 D92997056000 Sheet(s) all D92999559020 Sheet(s) 20 D93070515000 Sheet(s) 1 thru 8 D93070668000 Sheet(s) 1 thru 8 **K. P U**  **B L** **I C** **A T** **I O**  **N S**  **A F**  **F E** **C T** **E D**  Aircraft Maintenance Manual (AMM) : 05-21-50 10-11-00 10-12-00 11-31-31 12-11-28 28-00-00 28-10-00 28-11-00 28-12-00 28-12-41 28-12-44 28-20-00 28-21-00 28-21-52 28-21-53 28-23-00 28-24-00 28-25-00 28-25-42 28-25-51 28-25-52 28-25-58 28-28-11 28-28-31 28-28-33 28-28-46 28-28-51 28-28-53 28-40-00 28-42-00 28-42-15 28-42-16 28-42-21 28-42-22 28-43-00 28-46-00 28-46-34 32-62-00 57-10-00 57-17-11 Aircraft Schematic Manual (ASM) : 27-81-10 28-00-00 28-20-00 28-21-00 28-25-00 28-28-00 28-42-00 28-46-00 32-62-00 33-14-00 Aircraft Wiring Lists (AWL)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 45 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Aircraft Wiring Manual (AWM) : 24-58-06 24-68-01 24-68-02 24-68-04 24-68-05 24-68-15 27-81-25 28-21-07 28-21-08 28-25-04 28-25-08 28-28-01 28-28-02 28-28-03 28-28-04 28-42-15 28-42-16 28-42-19 28-42-21 28-46-01 28-46-03 28-46-14 28-46-15 31-54-81 33-14-08 93-01-03 93-01-07 93-01-21 Structural Repair Manual (SRM) : 53-31-14 53-31-17 53-31-29 53-41-14 53-45-12 57-11-11 57-11-29 57-17-00 57-19-00 Trouble Shooting Manual (TSM) : 28-25-00 28-28-00 28-42-00 28-46-00 32-31-00 Illustrated Parts Catalog (IPC) : 11-31-31 11-31-34 11-32-25 11-35-53 11-36-25 11-36-28 24-92-02 24-92-04 25-43-46 25-52-04 25-52-41 25-52-44 25-55-04 25-55-11 25-62-04 25-62-43 25-71-01 25-71-11 25-81-04 27-24-04 28-11-04 28-12-04 28-25-04 28-25-05 28-25-08 28-25-59 28-28-03 28-28-04 28-28-05 28-28-08 28-28-11 28-28-31 28-28-33 28-28-36 28-28-39 28-28-42 28-28-43 28-28-44 28-28-51 28-28-52 28-28-53 28-28-56 28-42-08 28-42-34 28-46-08 29-16-04 31-14-11 32-42-04 33-13-08 53-16-01 53-32-04 53-36-03 53-42-04 53-46-04 Structural Repair Manual (SRM) : 53-31-14 53-31-17 53-31-29 53-41-14 53-45-12 57-11-05 57-16-05 57-17-05 57-17-11 Flight Crew Operating Manual (FCOM) : Vol 1, 2, 3 and 4 Flight Manual (FM) Master Minimum Equipment List (MMEL) Weight and Balance Manual (WBM) This Service Bulletin has an operational impact. Please inform AIRBUS, at least four weeks in advance, in case you need of your operational documentation to be amended by an intermediate revision prior to SB embodiment. For this purpose, please request the intermediate revision by fax, telex or mail to: SDC3, AIRBUS Customer Services Directorate Fax No. (33) 5 61 93 28 06 Sita No. TLSBP7X E-mail sb.reporting@airbus.fr DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 46 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

These amendments will be confirmed by the next normal revision of operational documentation, once your Service Bulletin accomplishment report has been sent, as usual, to our Customer Services Directorate (SDC3). **L. I N** **T E**  **R C**  **H A** **N G**  **E A**  **B I**  **L I** **T Y**  **/ M**  **I X** **A B**  **I L** **I T** **Y** DESCRIPTION OLD PART No. NEW PART No. INT MIXABILITY Fuel Quantity Indicator 1407KID02-03 1422KID02-03 03 Not applicable FQIC SIC5059-11-0207 SIC5059-12-0308 03 Not applicable NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common Support Data Dictionary (CSDD), Chapter 2.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 47 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 48 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

**2. M A**  **T E**  **R I** **A L**  **I N**  **F O**  **R M** **A T** **I O**  **N A. M** **A T** **E R**  **I A** **L -**  **P R**  **I C**  **E A** **N D**  **A V** 

**A I**  **L A**  **B I**  **L I** **T Y**  (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, Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 HAMBURG GERMANY For ordering by internet:http://spares.airbus.com For SB Kits by fax: +49 40 50 76 25 90 For Spares by fax: +49 40 50 76 40 12 (2) Price and Availability Sales terms must be agreed between the Customers and AIRBUS in accordance with the RFC (or RFC/RMO) procedure. **B. I N**  **D U**  **S T** **R Y**  **S U**  **P P** **O R** **T I**  **N F** **O R**  **M A**  **T I**  **O N**  Refer to Paragraph 2.A.(2): Price and Availability. **C. L I**  **S T**  **O F**  **C O**  **M P** **O N**  **E N** **T S**  Kit 281118A01R03 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 A2823301800202 Plate 4 ASNA2050DCJ3215 Rivet 4 ASNA2397-10L Washer 2 ASNA2397-416L Washer 53 ASNA2528-3 Nut

1 D2821334100000 Rod 1 D2821334220000 Bracket 1 D5713031920000 Doubler 1 D5713032000095 Loft 1 D5713304820004 Doubler 1 D5791042020095 Fitting 1 D5791042120095 Fitting 1 D5791042220095 Support 1 D5791042320095 Support 1 D5791043020095 Fitting 1 D5791048200095 Fitting 1 D5791048300095 Fitting 1 D5791049400095 Support 1 D5791049500095 Support 1 D5791049820095 Fitting DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 49 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5791050020095 Fitting 1 D5791332300000 Bracket 1 D5791332400000 Bracket 19 EN6115V3-3 Bolt 15 EN6115V3-4 Bolt 17 EN6115V3-5 Bolt

2 EN6115V3-7 Bolt 4 NAS6603-4 Bolt 2 NAS6604-9 Bolt 4 NSA5050-3 Nut 2 NSA5050-4 Nut 79 NSA5330-6 Nut 31 NSA5330-8 Nut 22 NSA5357-3-5 Pin 29 NSA5357-3-6 Pin 20 NSA5357-3-7 Pin

4 NSA5357-3-8 Pin 4 NSA5357-3-10 Pin 12 NSA5357-4-7 Pin 13 NSA5357-4-8 Pin

2 NSA5357-4-9 Pin 4 NSA5357-4-10 Pin

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 281118A02R02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 A2823301800202 Plate 2 ASNA2050DCJ3215 Rivet 12 ASNA2397-10L Washer

2 ASNA2397-416L Washer 1 D2821040120000 Plate 1 D2821040220000 Bracket 1 D2821334100200 Rod 1 D5791040020095 Bracket 1 D5791040120095 Bracket 1 D5791040220095 Bracket 1 D5791040320095 Bracket 1 D5791040400095 Support 1 D5791040500095 Support 1 D5791040620095 Bracket 1 D5791040720095 Bracket 1 D5791040820095 Bracket 1 D5791040920095 Bracket 1 D5791041020095 Bracket 1 D5791041820095 Bracket DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 50 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 8 NAS6603-2 Bolt 8 NAS6603-4 Bolt 2 NAS6604-9 Bolt 8 NSA5050-3 Nut 2 NSA5050-4 Nut 33 NSA5330-8 Nut

3 NSA5330-10 Collar 8 NSA5357-4-9 Pin 5 NSA5357-4-10 Pin 19 NSA5357-4-11 Pin

1 NSA5357-4-12 Pin 3 NSA5357-5-13 Pin

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 281118A03R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 1158000-15 Canister 1 1158000-21 Valve 1 568-1-27170-002 Pump 1 568-1-27171-002 Plate 1 A2821064620000 Insert 1 A2821064720000 Spring 1 A2821064820040 Pin 1 A2823260500000 Valve 1 A2823260820000 Plug 8 A5713052120300 Washer 15 ABS0114V4-18 Bolt

4 ASNA2055-03 Washer 1 ASNA2397-10L Washer 6 ASNA2397-416 Washer 1 ASNA2397-416L Washer 1 ASNA2397-6L Washer 8 ASNA2397D10L Washer 6 ASNA2397D416L Washer 1 D2821067800000 Bulkhead 1 D5713323000000 Door 1 D5713334000000 Fairing 1 D5713334400000 Fitting 1 D5713334500000 Fitting 1 D5713334600000 Fitting 3 E0088-10-100 Lead 1 E0088-16-125 Lead 1 HTE190001-2 Actuator 1 HTE8002 Clamp DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 51 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 HTE690045 Switch 1 HTE900135 Valve 15 MS20002C4 Washer

1 M MS20995C32 Wire 1 MS21042-06 Nut 6 NAS1153-4 Screw 4 NAS1154-10 Screw 8 NAS1726C4E Nut 1 NAS1801-06-8 Screw 1 NAS1801-3-6 Screw 5 NAS6603-1 Bolt 3 NAS6603-2 Bolt 1 NAS6603-3 Bolt 4 NAS6603-5 Bolt 6 NAS6604-3 Bolt 6 NAS6604-7 Bolt 1 NAS6604-20 Bolt 7 NSA5050-3 Nut 1 NSA5050-4 Nut 1 NSA5112-04 Washer 3 NSA8200-6 Packing 1 NSA8203-019 O-Ring 1 NSA8203-113 O-Ring 1 NSA8203-154 O-Ring 1 NSA8203-167 O-Ring 1 NSA8203-224 O-Ring 1 NSA8203-226 O-Ring 1 NSA8203-245 O-Ring

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 281118A04R04 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 365A02 Valve 1 9843144M Valve 1 A2821038600000 Sleeve 1 A2821079520000 Flange 1 A2821120120000 Elbow 4 ABS0107-150 Nut 4 ABS0107-200 Nut 18 ASNA2397-10L Washer 24 ASNA2397-416L Washer

2 ASNA2397-6L Washer 4 ASNA2397D10L Washer 1 D2821331020000 Tee 1 D2821331320000 Tee DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 52 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2821331620000 Tee 1 D2821331920000 Elbow 1 D2821332220000 Elbow 1 D2821332620000 Elbow 1 D2821332900000 Elbow 1 D2821333220000 Elbow 1 D2821333420000 Elbow 1 D2821333800000 Sleeve 1 D2821333900000 Pipe 1 D2821333900100 Pipe 1 D2821333900300 Pipe 1 D2821333900400 Pipe 1 D2821333900600 Pipe 1 D2821333900700 Pipe 1 D2821333900900 Pipe 1 D2821333901000 Pipe 1 D2821334800000 Pipe 1 D2821334900000 Pipe 1 D2821335000000 Pipe 1 D2821335100000 Pipe 1 D2821335621800 RSTRCTR 1 D2821335800000 Pipe 1 D2821336300000 Sleeve 1 D2821336500000 Sleeve 1 D2821336621240 RSTRCTR 1 D2821336720240 RSTRCTR 2 E0088-10-100 Lead 1 E0088-10-160 Lead 3 E0088-10-200 Lead 1 E0088-10-280 Lead 2 MS21042L06 Nut 1 MS21902D4 Union 4 NAS1726-3E Nut 24 NAS1726-4E Nut

2 NAS1801-06-10 Screw 1 NAS6603-1 Bolt 19 NAS6603-2 Bolt

8 NAS6603-3 Bolt 8 NAS6603-4 Bolt 4 NAS6603-5 Bolt 8 NAS6603-7 Bolt 2 NAS6604-2 Bolt 4 NAS6604-3 Bolt 4 NAS6604-4 Bolt 16 NAS6604-5 Bolt

4 NAS6604-12 Bolt 20 NSA5050-3 Nut

6 NSA5050-4 Nut 1 NSA5516-04ND Clamp 1 NSA8200-4 Packing DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 53 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 NSA8200-5 Packing 1 NSA8203-215 O-Ring 18 NSA8203-222 O-Ring 13 NSA8203-226 O-Ring

4 NSA840003-150 Ring 4 NSA840003-200 Ring

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 281118A05R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 ASNA2397-10L Washer 12 ASNA2397-416L Washer

5 ASNA2397JD10L Washer 1 D2821330700000 Elbow 1 D2821334600000 Nutplate 1 D2821334700000 Nutplate 1 D2821337120000 Plate 1 D2821337500000 Nutplate 1 D2821337600000 Nutplate 1 D2821337700041 Elbow 1 D2821337800000 Filter 5 NAS6603-2 Bolt 2 NAS6603-5 Bolt 6 NAS6604-8 Bolt 6 NAS6604-9 Bolt 2 NSA5050-3 Nut 1 NSA8203-148 O-Ring 1 NSA8203-152 O-Ring

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 281118A06R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 16 ASNA2553-0401 Washer

1 D1131043320100 Placard 1 D1131043320200 Placard 1 D9000095128395 Bundle 1 D9100095112695 PLCRDSET 1 E0415C3LM078E Switch 1 E0416-02 Sleeve DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 54 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 E0417C01S CNCTR 16 E0736N08-01 Screw

2 NAS1102-04-6 Screw 6 NSA931305-01 Clamp 3 NSA931320-030 C/B NOTE (01) 2 NSA931320-050 C/B NOTE (02) 1 NSA931322-100 C/B NOTE (03) 150 NSA935401-03 Tie 150 NSA935401-06 Tie NOTE(01) PN supplied with reference NSA931320-030A NOTE(02) PN supplied with reference NSA931320-050A NOTE(03) PN supplied with reference NSA931322-100A 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 281118A07R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D33110194A00 Plate

Kit 281118A08R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9251314920000 Plate

Kit 281118A09R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D00410426A00 Placard 1 D00410428A00 Placard 1 D00410444A00 Placard 1 D11311000A00 Placard 1 D11311010A00 Placard

Kit 281118A10R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 ASNA2051DCJ3215 Rivet 8 ASNA2397-10L Washer 3 ASNA2397-4L Washer DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 55 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9000095128495 Bundle 1 D9000095128595 Bundle 1 D9100095112795 PLCRDSET 1 D9241244120000 Bracket 1 E0052R14B19SNF CNCTR 1 E0052R20B41SNF CNCTR 1 E0080-01-14C BCKSHELL 1 E0080-01-20C BCKSHELL 1 E0245-28A0 Relay 1 E0250A0S Base 2 E0420-04 Stud 10 M E0432A12 Conduit

2 E0661-22 Mount 1 EN3545D03FXA22A CNCTR NOTE (01) 1 EN3545D03MXB22A CNCTR NOTE (02) 1 EN3545E03FXB24A CNCTR NOTE (03) 3 EN3545SCD BCKSHELL 5 MS21042L04 Nut 3 NAS1100-04-7 Screw 6 NAS1726-3E Nut 3 NAS1801-3-8 Screw 5 NAS1801-3-9 Screw 1 NAS1801-3-20 Screw 1 NSA5527-03-01 Spacer 1 NSA932843AA01 Relay 1 NSA932844AA Base 100 NSA935401-03 Tie 200 NSA935401-04 Tie 200 NSA935401-05 Tie 800 NSA935401-06 Tie 1500 NSA935401-08 Tie 4 NSA935504-01 Mount 1 NSA935504-03 Mount 1 NSA937901E0 IDENT 1 NSA937901E1 IDENT 2 NSA937901E2 IDENT 1 NSA937901E6 IDENT 1 NSA937901E8 IDENT 1 NSA937901MA2008 Module 1 NSA937901MA2204 Module 1 NSA937901MA2206 Module

NOTE(01) PN supplied with reference EN3545D03FXA00A. NOTE(02) PN supplied with reference EN3545D03MXB00A. NOTE(03) PN supplied with reference EN3545E03FXB00A. 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 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 56 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281118A11R03 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 30042-0000-0501 CTLUNIT 2 ASNA2397-3L Washer 5 ASNA2397-4L Washer 2 ASNA2397-6L Washer 3 ASNA2397-10L Washer 1 D0003006100000 Rack 1 D9100095112895 PLCRDSET 1 D9251116900000 Plate 2 D9251127600000 Flange 1 E0161D01A12X CNCTR 1 E0247A0S Base 1 E0425A2001 Module 1 E0427-01 Retainer 1 E0666D28A0 Relay 3 MS21042L04 Nut 1 NAS1100-04-6 Screw 4 NAS1100-04-7 Screw 4 NAS1100-06-12 Screw 3 NAS1102-3-10 Screw 6 NAS1726-3E Nut 4 NAS1801-3-8 Screw 1 NSA937901E1 IDENT 3 NSA937901E2 IDENT 1 NSA937901MA2011 Module 1 NSA937901MA2204 Module 5 NSA939511-03 Cover

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 281118A12R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9000095131595 Bundle 1 D9251122800600 Plate 1 D9550005100395 Panel 50 NSA935401-03 Tie 50 NSA935401-04 Tie 100 NSA935401-06 Tie 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 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 57 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281118A13R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D33110251A00 Plate

Kit 281118A14R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D00410426A00 PLACARD 1 D00410444A00 PLACARD 1 D00411041A00 PLACARD 1 D11311000A00 PLACARD 1 D11311133A00 PLACARD

NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. Kit 281118A15R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2821336920000 PLACARD 1 D2821336920200 PLACARD 1 D2821336920400 PLACARD 1 D2821336920600 PLACARD 1 D2821336920800 PLACARD

Kit 281118A16R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D1121080900000 MARKING

Kit 281118A17R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 E0088-10-280 LEAD 1 EN3646A61419BW CNCTR 4 NAS6603-3 BOLT 1 NSA5357-4-11 PIN

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 281118A18R00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 58 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D0041109120000 PLACARD 2 D1121004620000 PLACARD 2 D1121009120000 PLACARD

Kit 281118B01R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 EA QB0566 Filter D28270975002 41 1 EA HTE490005 Valve D28270975002 42 1 EA HTE200002-1 Actuator D28270975002 43 1 EA HTE920007-001 Valve D28270975002 44 1 EA HTE8002 Clamp D28270975002 45 1 EA PAS148-133A Valve D28270975002 46 1 EA HTE490005 Valve D28270975002 47

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 281118B02R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9255002500000 Panel D92550025 1 D9255602500800 Relay D92355000

Kit 281118B03R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9245011500600 Panel D92450115

Kit 281118B04R02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9255003200400 Panel D92550032

Kit 281118B05R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9240000064695 Bundle

Kit 281118D01R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

40 D9239310902800 PLCRDSETD92894713020 0000 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 59 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 80 NSA935401-03 TIE D92894713020 0080

4 NAS1096-2-12 SCREW D92894736004 0007 2 NAS1096-3-9 SCREW D92894736004 0030 1 D9299043900000 HARNESS D92894736004 0039 1 D9299044000000 HARNESS D92894736004 0040 1 D9239386503200 PLCRDSETD92894736004 0050 4 NAS1100-04-5 SCREW D92894736004 0051 4 NAS1149CN616R WASHER D92894736004 0150 3 NAS1149CN816R WASHER D92894736004 0152 2 NAS1149C0332R WASHER D92894736004 0153 4 MS21042-04 NUT D92894736004 0200 3 NSA5066-08-1 NUT D92894736004 0230 2 E0343-01 MOUNT D92894736004 0250 1 NSA935504-01 MOUNT D92894736004 0251 1 NSA935504-03 MOUNT D92894736004 0253 1 NSA935513-07 MOUNT D92894736004 0259 2 ABS0355-01 BRACKET D92894736004 0262 2 ABS0355-02 BRACKET D92894736004 0263 2 NSA935514-03 WASHER D92894736004 0264 4 NSA5527-03-03 SPACER D92894736004 0304 15 NSA935401-03 TIE D92894736004 0793 30 NSA935401-04 TIE D92894736004 0794 15 NSA935401-05 TIE D92894736004 0795 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 281118D02R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D2567072701000 BRACKET D25670762000 0000 6 D2567072700200 BRACKET D25670762000 0002 2 D2567072700400 BRACKET D25670762000 0004 2 D2567072700500 BRACKET D25670762000 0005 2 D2567072701200 BRACKET D25670762000 0006 3 D2567072700800 BRACKET D25670762000 0008 3 D2567072700900 BRACKET D25670762000 0009 66 LN9198-4008CF RIVET D25670762000 9001

1 D2567070100000 TUBE D25671745000 0000 1 D2567070100100 TUBE D25671745000 0001 1 D2567070100200 TUBE D25671745000 0002 1 D2567070100300 TUBE D25671745000 0003 1 D2567070600000 SECTION D25671745000 0010 1 D2567070600200 SECTION D25671745000 0012 4 E0088-10-80NN LEAD D25671745000 0050 4 ABS0396C08JA CLAMP D25671745000 0060 10 NSA5515-8 CLAMP D25671745000 0062 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 60 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 4 NSA5519-11 CLAMP D25671745000 0064 1 NSA5515-12 CLAMP D25671745000 0066 2 NAS817-10 CAP D25671745000 0070 28 NAS1096-3-10 SCREW D25671745000 0080

5 NAS1096-2-9 SCREW D25671745000 0082 4 NAS1096-2-7 SCREW D25671745000 0084 2 NAS1096-3-12 SCREW D25671745000 0103 30 NAS1149D0363K WASHER D25671745000 0110 13 NAS1149DN832K WASHER D25671745000 0112

1 64079-3 HOSE D25671745000 0595 2 64079-5 HOSE D25671745000 0597 2 D2567043200000 POCKET D25671746000 0050 2 ASNA0033-172 CLAMP D25671746000 0060 1 73228620 SECTION D25671746000 0070 NOTE (01) 4 NAS1096-3-7 SCREW D25671746000 0080 4 NAS1149D0363K WASHER D25671746000 0090 1 D9239310903000 PLCRDSETD25671746000 0100 2 MS20392-2C15 PIN D25671746000 0110 6 NAS1149C0332R WASHER D25671746000 0120 2 MS24665-1013 PIN D25671746000 0130 1 D2567074100600 PLACARD D25671746000 0140

NOTE(01) PN 73228620 is the same as PN LN29837A1 given in the drawing. 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 281118D03R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 16 NAS1102-4-16 SCREW D25286364010 0002 16 NAS1149F0432P WASHER D25286364010 0004 16 NAS1169C416L WASHER D25286364010 0006 16 MS21042-4 NUT D25286364010 0008 16 NAS1102-08-16 SCREW D25286364010 0010 16 NAS1149FN816P WASHER D25286364010 0012 16 NAS1169C8L WASHER D25286364010 0014 16 MS21042-08 NUT D25286364010 0016

1 D2527305811800 BOX D25286364010 0020 1 D2527305811900 BOX D25286364010 0021 4 MS20392-3C23 PIN D25286364010 0030 2 MS20392-3C27 PIN D25286364010 0031 6 NAS1149F0463P WASHER D25286364010 0032 6 AA55487-5 PIN D25286364010 0033 4 MS20392-4C67 PIN D25286364010 0042 2 MS20392-4C45 PIN D25286364010 0043 4 NAS1149C0532R WASHER D25286364010 0046 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 61 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 6 DAN191-20 RING D25286364010 0047 2 NSA5528-045 CLAMP D25286364010 0065

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 281118D04R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D2527719940600 PLACARD D25288767000 0206 2 D2527700844200 PLACARD D25288767000 0242 2 A2528131544600 PLACARD D25288767000 0246

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 281118D05R06 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5337217000200 BEAM D53372362000 0000 2 D5337218500000 STRUT D53372362000 0002 4 D5337218600000 STRUT D53372362000 0004 2 D5337217220000 FITTING D53372362000 0006 2 D5337217220100 FITTING D53372362000 0007 1 D5337219220000 FITTING D53372362000 0008 1 D5337219220100 FITTING D53372362000 0009 1 D5337219120200 FITTING D53372362000 0010 1 D5337219120300 FITTING D53372362000 0011 1 D5337219020200 FITTING D53372362000 0012 1 D5337215920000 ANGLE D53372362000 0014 8 D5337215920200 ANGLE D53372362000 0016 1 D5337215920400 ANGLE D53372362000 0018 1 D5337215920500 ANGLE D53372362000 0019 1 D5337215920600 ANGLE D53372362000 0020 1 D5337217320200 WEB D53372362000 0022 NOTE (01) 1 D5337217400000 PLATE D53372362000 0024 1 D5337217400100 PLATE D53372362000 0025 1 D5337216020000 SECTION D53372362000 0026 1 D5347449520800 SECTION D53372362000 0028 1 D5347449520900 SECTION D53372362000 0029 2 D5337601520600 SHIM D53372362000 0030 2 D5337601520800 SHIM D53372362000 0032 2 D5337601521000 SHIM D53372362000 0034 2 D5337601521200 SHIM D53372362000 0036 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 62 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D5337601521400 SHIM D53372362000 0038 1 D5347100720600 COUPLING D53372362000 0040 1 D5347101620490 CONNECTN D53372362000 0042 NOTE (01) 1 D5347101620590 CONNECTN D53372362000 0043 NOTE (02) 3 D5337602020000 SECTION D53372362000 0044 3 D5337602020100 SECTION D53372362000 0045 4 NAS1791A3-1 NUT D53372362000 0046 4 D5347100920090 SUPPORT D53372362000 0048 NOTE (03) 4 D5347100920190 SUPPORT D53372362000 0049 NOTE (04) 1 D5347104120090 ANGLE D53372362000 0050 NOTE (05) 1 D5347104120190 ANGLE D53372362000 0051 NOTE (06) 4 D5337236220400 SHIM D53372362000 0052 1 D5337036521400 ANGLE D53372362000 0150 1 D5337036521500 ANGLE D53372362000 0151 2 D5347007421800 ANGLE D53372362000 0152 2 D5347007421900 ANGLE D53372362000 0153 1 D5347007420800 ANGLE D53372362000 0156 1 D5347007420900 ANGLE D53372362000 0157 12 ASNA0082A302 BOLT D53372362000 0435

2 ASNA0082A303 BOLT D53372362000 0436 4 ASNA0082A304 BOLT D53372362000 0438 15 ASNA0082A305 BOLT D53372362000 0440

1 ASNA0082A306 BOLT D53372362000 0442 2 NAS1149D0363K WASHER D53372362000 0458 2 NSA5031-3-14 BOLT D53372362000 0460 2 NAS1726-3E NUT D53372362000 0462 2 MS21250-09024 BOLT D53372362000 0464 2 NAS1726-9E NUT D53372362000 0466 2 MS20002C9 WASHER D53372362000 0468 4 MS21250-06018 BOLT D53372362000 0470 4 NAS1726-6E NUT D53372362000 0472 4 MS20002C6 WASHER D53372362000 0474 8 DAN7-6-6X PIN D53372362000 0566 12 DAN5-6-4X PIN D53372362000 0764

8 DAN5-6-5X PIN D53372362000 0765 16 DAN5-6-6X PIN D53372362000 0766 24 DAN5-6-7X PIN D53372362000 0767 68 DAN5-6-8X PIN D53372362000 0768 24 DAN5-6-9X PIN D53372362000 0769 13 DAN5-6-10X PIN D53372362000 0770 12 DAN5-6-11X PIN D53372362000 0771 12 DAN5-6-12X PIN D53372362000 0772 76 NSA5075-5 COLLAR D53372362000 0804 259 NSA5075-6 COLLAR D53372362000 0806 188 DAN11-6X COLLAR D53372362000 0807

41 DAN11-8X COLLAR D53372362000 0810 210 NSA5076-6 COLLAR D53372362000 0816

75 DAN12-6X COLLAR D53372362000 0817 20 DAN6-6-5 PIN D53372362000 0865

8 DAN6-6-6 PIN D53372362000 0866 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 63 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 4 DAN5-8-7X PIN D53372362000 0887 5 DAN5-8-8X PIN D53372362000 0888 7 DAN5-8-9X PIN D53372362000 0889 14 DAN5-8-10X PIN D53372362000 0890

7 DAN5-8-11X PIN D53372362000 0891 8 DAN5-8-12X PIN D53372362000 0892 36 DAN5-5-4 PIN D53372362000 0944 NOTE (08) 24 DAN5-5-5 PIN D53372362000 0945

4 DAN5-5-7 PIN D53372362000 0947 4 DAN5-5-11 PIN D53372362000 0951 3 DAN7-5-5 PIN D53372362000 0955 9 DAN7-5-6 PIN D53372362000 0956 12 DAN5-6-3 PIN D53372362000 0963 36 DAN5-6-4 PIN D53372362000 0964 212 DAN5-6-5 PIN D53372362000 0965

80 DAN5-6-6 PIN D53372362000 0966 46 DAN5-6-7 PIN D53372362000 0967 42 DAN5-6-8 PIN D53372362000 0968 10 DAN5-6-9 PIN D53372362000 0969

6 DAN5-6-11 PIN D53372362000 0971 6 DAN5-6-13 PIN D53372362000 0973 12 NAS1097AD3-10 RIVET D53372362000 0524 12 NAS1097AD4-10 RIVET D53372362000 0532 102 NAS1097AD5-12 RIVET D53372362000 0540 248 LN9198-4014CF RIVET D53372362000 0640

61 LN9198-4814CF RIVET D53372362000 0648

4 LN9198-5614CF RIVET D53372362000 0656

NOTE( 01) D5347101620490 is the same part as D5347101620400, but manufacture without pilot holes. NOTE( 02) D5347101620590 is the same part as D5347101620500, but manufacture without pilot holes. NOTE( 03) Modified connection. (old PN D5347100920000) NOTE( 04) Modified connection. (old PN D5347100920100) NOTE( 05) Modified angle. (old PN D5347104120000) NOTE( 06) Modified angle. (old PN D5347104120100) NOTE( 07) Alternative PN D5337217320000 NOTE( 08) Alternative to Item 0640, LN9198-4014CF. 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. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 64 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Kit 281118D06R03 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D5347035000600 XBEAM D53470075004 0010 4 D5337217620000 SHEET D53470075004 0012 3 D5337217620100 SHEET D53470075004 0014 4 D5347449420600 FITTING D53470075004 0016 4 D5347449420700 FITTING D53470075004 0018 1 D5347449521800 SECTION D53470075004 0020 5 D5347448420200 STRAP D53470075004 0022 4 D5347448420300 STRAP D53470075004 0024 8 D5337217620800 FILLER D53470075004 0026 4 D5347449520300 SECTION D53470075004 0028 3 D5347449520200 SECTION D53470075004 0030 7 D5347449520500 SECTION D53470075004 0032 6 D5347449520400 SECTION D53470075004 0034 1 D5347470020000 ANGLE D53470075004 0036 1 D5347470020100 ANGLE D53470075004 0038 3 D5347470020400 ANGLE D53470075004 0044 2 D5347470020500 ANGLE D53470075004 0046 6 D5347470020200 ANGLE D53470075004 0048 4 D5347470020300 ANGLE D53470075004 0050 1 D5347026000600 XBEAM D53470075004 0052 2 D5347470520000 ANGLE D53470075004 0054 2 D5347470520100 ANGLE D53470075004 0056 1 D5347449523400 SECTION D53470075004 0058 1 D5347449523600 SECTION D53470075004 0060 2 D5347449522000 SECTION D53470075004 0062 2 D5347449523200 SECTION D53470075004 0064 1 D5347470320000 WEB D53470075004 0066 1 D5347470020800 ANGLE D53470075004 0068 1 D5347470021000 ANGLE D53470075004 0070 1 D5347470020600 ANGLE D53470075004 0072 1 D5347470021200 ANGLE D53470075004 0074 1 D5347035300600 XBEAM D53470075004 0076 1 D5337217620700 SHEET D53470075004 0078 1 D5347470420400 WEB D53470075004 0080 1 D5347470021600 ANGLE D53470075004 0082 1 D5347470021800 ANGLE D53470075004 0084 1 D5347470043800 ANGLE D53470075004 0088 2 D5347470021400 ANGLE D53470075004 0090 1 D5347470022200 ANGLE D53470075004 0092 1 D5347449520200 SECTION D53470075004 0094 1 D5347449520400 SECTION D53470075004 0096 1 D5347470020500 ANGLE D53470075004 0098 2 D5347470020300 ANGLE D53470075004 0100 2 D5347471320800 PLATE D53470075004 0100 1 D5347658420000 ANGLE D53470075004 0102 1 D5347471321200 PLATE D53470075004 0104 2 D5347471500200 PLATE D53470075004 0108 1 D5347471500000 PLATE D53470075004 0110 1 D5347471500600 PLATE D53470075004 0112 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 65 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5347471500800 PLATE D53470075004 0114 1 D5347471501000 PLATE D53470075004 0116 2 D5347471500300 PLATE D53470075004 0118 1 D5347471500100 PLATE D53470075004 0120 1 D5347471501400 PLATE D53470075004 0122 1 D5347471502600 PLATE D53470075004 0124 1 D5347659100000 ANGLE D53470075004 0126 6 D5347470120000 ANGLE D53470075004 0128 7 D5347470120200 ANGLE D53470075004 0130 4 D5347470120100 ANGLE D53470075004 0132 5 D5347470120300 ANGLE D53470075004 0134 1 D5347048100600 SECTION D53470075004 0152 1 D5347047500800 SECTION D53470075004 0154 1 D5347047600800 SECTION D53470075004 0156 1 D5347646320200 DOUBLER D53470075004 0160 1 D5347646320000 DOUBLER D53470075004 0162 1 D5347470920200 COVER D53470075004 0164 2 D5347669200000 PLATE D53470075004 0166 2 D5347669000000 TUBE D53470075004 0172 2 D5347669100000 PLUG D53470075004 0174 4 D5347472120000 SHIM D53470075004 0176 4 D5347470220000 SHIM D53470075004 0178 4 D5347658620000 BUSHING D53470075004 0204 1 D5347065020400 SECTION D53470075004 0208 1 D5347048800400 PLATE D53470075004 0214 1 D5347048900400 PLATE D53470075004 0216 1 D5347049200400 PLATE D53470075004 0218 1 D5347046824300 ANGLE D53470075004 0222 1 D5347046824600 ANGLE D53470075004 0224 2 D5347046824000 ANGLE D53470075004 0228 1 D5347046823800 ANGLE D53470075004 0230 1 D5347046823600 ANGLE D53470075004 0232 1 D5347046824200 ANGLE D53470075004 0234 1 D5347046824400 ANGLE D53470075004 0236 2 MS16625-4212 RING D53470075004 0500 10 NAS1153E7 SCREW D53470075004 0502

8 ABS0337-01A RECEPTCLD53470075004 0504 2 NAS1096-3-10 SCREW D53470075004 0506 4 NAS1791A3-1 NUT D53470075004 0508 10 NAS1474A3 NUT D53470075004 0510 28 MBBN4477-4014 RIVET D53470075004 0540 NOTE (01) 347 MBBN4477-4814 RIVET D53470075004 0548 NOTE (01) 969 LN9198-4014CF RIVET D53470075004 0640 548 LN9198-4814CF RIVET D53470075004 0648 4 DAN6-6-5X PIN D53470075004 0665 3 DAN6-6-6X PIN D53470075004 0666 11 DAN6-6-7X PIN D53470075004 0667 10 DAN6-6-9X PIN D53470075004 0669 16 DAN6-6-8Y PIN D53470075004 0678 44 DIN65399-2408CF RIVET D53470075004 0724 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 66 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

135 DIN65399-3208CF RIVET D53470075004 0732

10 DAN5-6-4X PIN D53470075004 0764 24 DAN5-6-5X PIN D53470075004 0765

8 DAN5-6-6X PIN D53470075004 0766 16 DAN5-6-8X PIN D53470075004 0768

8 DAN5-6-8Y PIN D53470075004 0778 24 NSA5330-6 COLLAR D53470075004 0803

3 NSA5075-5 COLLAR D53470075004 0804 775 NSA5075-6 COLLAR D53470075004 0806 104 DAN11-6X COLLAR D53470075004 0807

40 NSA5075-8 COLLAR D53470075004 0808 16 DAN6-6-3 PIN D53470075004 0863

8 DAN6-6-4 PIN D53470075004 0864 4 DAN6-6-6 PIN D53470075004 0866 10 DAN6-6-7 PIN D53470075004 0867

3 DAN5-5-5 PIN D53470075004 0945 70 DAN5-6-3 PIN D53470075004 0963 183 DAN5-6-4 PIN D53470075004 0964 187 DAN5-6-5 PIN D53470075004 0965 128 DAN5-6-6 PIN D53470075004 0966

40 DAN5-6-7 PIN D53470075004 0967 81 DAN5-6-8 PIN D53470075004 0968 20 DAN5-6-10 PIN D53470075004 0970 24 DAN5-8-5 PIN D53470075004 0985

8 DAN5-8-6 PIN D53470075004 0986 9 DAN5-8-7 PIN D53470075004 0987

NOTE(01) Rivet MBBN4477-4014 is used alternative for NAS1097KE5-14. NOTE(02) Rivet MBBN4477-4814 is used alternative for NAS1097KE6-14. 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 281118D07R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5337270100000 ANGLE D53370780000 0000 1 D5337070100000 ANGLE D53370780000 0002 1 D5337270100400 ANGLE D53370780000 0004 1 D5337070100200 ANGLE D53370780000 0006 1 D5337270100800 ANGLE D53370780000 0008 1 D5337070100400 ANGLE D53370780000 0010 2 D5337070220000 SHEET D53370780000 0020 8 ASNA0082-303 BOLT D53370780000 0363 4 ASNA0082-304 BOLT D53370780000 0364

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 67 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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 281118D08R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

136 NSA5075-6 COLLAR D53470095002 0806

16 DAN6-6-3 PIN D53470095002 0863 16 DAN6-6-5 PIN D53470095002 0865 72 DAN5-6-3 PIN D53470095002 0963 32 DAN5-6-4 PIN D53470095002 0964 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 281118D09R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D5337142320000 FITTING D53372366000 0001 26 DAN5-5-3 PIN D53372366000 0002 26 NSA5075-5 COLLAR D53372366000 0003 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 281118D10R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2587085105400 BLANKET D25870003028 0001 1 D2587085205000 BLANKET D25870003028 0002 1 D2587085305400 BLANKET D25870003028 0003 1 D2587085405000 BLANKET D25870003028 0004 1 D2587085505200 BLANKET D25870003028 0005 1 D2587085705000 BLANKET D25870003028 0007 1 D2587085805000 BLANKET D25870003028 0008 1 D2587085905000 BLANKET D25870003028 0009 1 D2587086005000 BLANKET D25870003028 0010 1 D2587086105000 BLANKET D25870003028 0011 1 D2587085002000 BLANKET D25870003028 0020 1 D2587085602000 BLANKET D25870003028 0026 1 D2587086202000 BLANKET D25870003028 0032 1 D2587086302200 BLANKET D25870003028 0033 1 D2587086502000 BLANKET D25870003028 0034 1 D2587087102000 BLANKET D25870003028 0035 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 68 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2587087302000 BLANKET D25870003028 0036 80 F2587003300000 STRIP D25870003028 0100 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 281118D11R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9357040100200 BRACKET D93070668000 0112 1 D9357040100300 BRACKET D93070668000 0113 4 DAN257-3264 RIVET D93070668000 0125

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 281118D12R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5347212920400 BRACKET D53472833002 0000 10 NAS1252-10L WASHER D53472833002 0400

4 NSA5182-3 NUT D53472833002 0401 2 NSA5031-3-4 BOLT D53472833002 0413 2 NSA5031-3-5 BOLT D53472833002 0414

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 281118D13R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827093320400 FLANGE D28270972002 0000 1 D2827093100200 TUBE D28270972002 0002 1 D2827093000200 TUBE D28270972002 0004 1 D2827093321400 SLEEVE D28270972002 0006 1 D2827093100000 TUBE D28270972002 0008 1 D2827093000000 TUBE D28270972002 0010 1 D2827093221200 SPACER D28270972002 0012 2 D2827093222200 FLANGE D28270972002 0014 1 D2827093322400 SLEEVE D28270972002 0016 2 D2827092700000 TUBE D28270972002 0018 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 69 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D2827093222600 FLANGE D28270972002 0020 2 D2827093222800 FLANGE D28270972002 0028 1 D2827093320600 FLANGE D28270972002 0030 2 A2827090120400 SPACER D28270972002 0031 1 D2827092900600 TUBE D28270972002 0032 1 D2827093500000 BRACKET D28270972002 0033 1 D2827092800400 TUBE D28270972002 0034 1 D2827093500200 CLAMP D28270972002 0035 2 D2827093321200 SLEEVE D28270972002 0036 1 D2827093500400 CLAMP D28270972002 0037 2 D2827093320800 FLANGE D28270972002 0038 1 D2827093322200 SLEEVE D28270972002 0039 2 D2827093221600 FLANGE D28270972002 0040 2 D2827093321000 SLEEVE D28270972002 0042 1 D2827092800000 TUBE D28270972002 0044 1 D2827092900000 TUBE D28270972002 0046 1 D2827092900200 TUBE D28270972002 0048 1 D2827092900400 TUBE D28270972002 0050 1 D2827094800000 BRACKET D28270972002 0051 1 D2827092800200 TUBE D28270972002 0052 4 NSA8203-151 ORING D28270972002 0053 9 NSA8203-152 ORING D28270972002 0054 1 NSA8203-154 ORING D28270972002 0055 1 NSA8203-156 ORING D28270972002 0056 3 NSA8203-222 ORING D28270972002 0057 9 NSA8203-226 ORING D28270972002 0058 3 NSA8203-230 ORING D28270972002 0059 10 NSA8203-234 ORING D28270972002 0060

4 NSA5519-25 CLAMP D28270972002 0061 4 NSA5519-30 CLAMP D28270972002 0062 2 ABS0107-150 NUT D28270972002 0064 3 NSA840003-150 RING D28270972002 0065 12 ABS0107-200 NUT D28270972002 0066

7 NSA840003-200 RING D28270972002 0067 2 AN814-4DL PLXBLDR D28270972002 0071 2 NSA8200-4 PACKING D28270972002 0072 3 A2827090220200 SPRING D28270972002 0074 6 A2827051720200 SPRING D28270972002 0075 63 NAS1149C0432R WASHER D28270972002 0082 52 NAS1149C0332R WASHER D28270972002 0083 29 NAS1291C3M NUT D28270972002 0084 58 NAS1726-4E NUT D28270972002 0085

8 NAS1304-4 BOLT D28270972002 0086 7 NAS1304-5 BOLT D28270972002 0087 1 NAS1304-6 BOLT D28270972002 0088 6 NAS1304-8 BOLT D28270972002 0089 4 NAS1304-9 BOLT D28270972002 0090 11 NAS1304-10 BOLT D28270972002 0091

9 NAS1304-11 BOLT D28270972002 0092 4 NAS1304-12 BOLT D28270972002 0093 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 70 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 8 NAS1304-14 BOLT D28270972002 0094 2 NAS1303-2 BOLT D28270972002 0095 21 NAS1303-3 BOLT D28270972002 0096

8 NAS1304-2 BOLT D28270972002 0098 4 NAS1304-3 BOLT D28270972002 0100 4 E0089-10-125NN LEAD D28270972002 0102 1 E0089-10-160NN LEAD D28270972002 0103 2 E0089-10-200NN LEAD D28270972002 0104 4 E0089-41-100NN LEAD D28270972002 0105 2 E0089-41-200NN LEAD D28270972002 0106 2 E0089-41-250NN LEAD D28270972002 0107 3 E0088-10-125 LEAD D28270972002 0108 2 E0088-10-200 LEAD D28270972002 0109 0.345 NSA937210MB0300 TUBING D28270972002 0110

0.38 NSA937210MB0300 TUBING D28270972002 0111 2 E0089-10-250NN LEAD D28270972002 0112

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 281118D14R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 MS21902D8 UNION D28270973002 0000 2 NSA8200-8 PACKING D28270973002 0001 1 MS21907D8 ELBOW D28270973002 0002 2 AN924-8D NUT D28270973002 0003 2 NAS1149D1290K WASHER D28270973002 0004 2 MS21905D8 TEE D28270973002 0005 1 NSA5527-03-16 SPACER D28270973002 0006 28 NAS1149C0332R WASHER D28270973002 0007

1 NAS1096-3-15 SCREW D28270973002 0008 21 NAS1096-3-8 SCREW D28270973002 0009 10 NAS1726-3E NUT D28270973002 0010

3 NAS1096-3-7 SCREW D28270973002 0011 2 NAS1096-3-10 SCREW D28270973002 0012 1 MS21912D8 TEE D28270973002 0013 9 MS21919WDE8 CLAMP D28270973002 0014 6 MS21919WDE11 CLAMP D28270973002 0015 1 MS21919WDE48 CLAMP D28270973002 0016 1 MS21916D8-6 REDUCER D28270973002 0017 3 NAS1149C0432R WASHER D28270973002 0018 3 NAS1304-4 BOLT D28270973002 0019 1 NSA8200-6 PACKING D28270973002 0022 2 NAS1149D1216H WASHER D28270973002 0023 3 NAS1096-3-9 SCREW D28270973002 0024 6 E0090-10-125NN LEAD D28270973002 0025 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 71 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 NAS1149D0316H WASHER D28270973002 0026 1 NAS1303-2 BOLT D28270973002 0027 1 NSA5575-7 CLAMP D28270973002 0028 4 NAS1304-2 BOLT D28270973002 0030 4 NAS1726-4E NUT D28270973002 0032 1 NAS1763D080808 TEE D28270973002 0033 12 NSA5519-11 CLAMP D28270973002 0035 12 NAS1291C3M NUT D28270973002 0036

1 E0090-10-200NN LEAD D28270973002 0037 2 E0091-10-280NN LEAD D28270973002 0038 1 D56KAN002 HOSE D28270973002 0039 2 ASNA0033-016 CLAMP D28270973002 0040 1 D2827093603400 TUBE D28270973002 0100 1 D2827093600200 TUBE D28270973002 0102 1 D2827093603200 TUBE D28270973002 0108 1 D2827093601600 TUBE D28270973002 0116 1 D2827093602000 TUBE D28270973002 0120 1 D2827093602400 TUBE D28270973002 0124 1 D2827093602600 TUBE D28270973002 0126 1 D2827093603000 TUBE D28270973002 0130 1 D2827097600200 TUBE D28270973002 0134 1 D2827093603600 TUBE D28270973002 0136 1 D2827097600400 TUBE D28270973002 0138 1 51263408-0840 HOSE D28270973002 0202 1 D2827094320000 FITTING D28270973002 0204 1 L83A13-617 VALVE D28270973002 0206 1 513535E0107-090 HOSE D28270973002 0208 1 D2827094720000 BRACKET D28270973002 0210 1 D2827094421400 PLACARD D28270973002 0214 1 D2827098322800 BRACKET D28270973002 0216

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 281118D15R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 5 MS21919WDE8 CLAMP D28270974002 0014 15 NAS1096-3-8 SCREW D28270974002 0016 17 NAS1149C0332R WASHER D28270974002 0017

2 MS21905D8 TEE D28270974002 0021 1 NSA855120-8D ELBOW D28270974002 0022 1 NAS1762D0808 ELBOW D28270974002 0023 1 MS21916D8-6 REDUCER D28270974002 0025 1 NSA8200-6 PACKING D28270974002 0026 3 NAS1149C0432R WASHER D28270974002 0027 3 NAS1304-4 BOLT D28270974002 0028 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 72 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 MS21914-8D CAP D28270974002 0033 1 AN924-8D NUT D28270974002 0034 1 NAS1149D1290K WASHER D28270974002 0035 1 MS21912D8 TEE D28270974002 0036 1 NAS1149D1216H WASHER D28270974002 0037 10 NAS1291C3M NUT D28270974002 0049

9 NSA5519-11 CLAMP D28270974002 0051 2 ASNA0033-016 CLAMP D28270974002 0056 1 D56KAN002 HOSE D28270974002 0057 1 E0090-10-125NN LEAD D28270974002 0060 5 E0090-10-160NN LEAD D28270974002 0061 1 D2827097700200 TUBE D28270974002 0122 1 D2827097700400 TUBE D28270974002 0124 1 D2827093701800 TUBE D28270974002 0130 1 D2827097701000 TUBE D28270974002 0132 1 D2827097701200 TUBE D28270974002 0134 1 L83A13-617 VALVE D28270974002 0202 1 513535E0107-090 HOSE D28270974002 0204 1 D2827094421600 PLACARD D28270974002 0216

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 281118D16R02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827098000800 TUBE D28270975002 0005 1 D2827098001000 TUBE D28270975002 0007 1 D2827098001200 TUBE D28270975002 0009 1 D2827098001400 TUBE D28270975002 0011 1 D2827097901200 TUBE D28270975002 0013 1 D2827097901400 TUBE D28270975002 0015 1 D2827097901000 TUBE D28270975002 0016 1 D2827097901600 TUBE D28270975002 0017 1 D2827097901800 TUBE D28270975002 0019 1 D2827097902000 TUBE D28270975002 0021 1 D2827097902200 TUBE D28270975002 0023 1 D2827097902400 TUBE D28270975002 0025 1 A2163302000000 FILTER D28270975002 0027 1 A2151034520000 INLET D28270975002 0028 1 MS21902D10 UNION D28270975002 0030 1 NAS1612-10 PACKING D28270975002 0031 1 83694912 HOSE D28270975002 0040 NOTE (01) 2 A2827092300000 COUPLING D28270975002 0050 29 NAS1726C3E NUT D28270975002 0070 20 NAS1096-3-8 SCREW D28270975002 0071 29 NAS1149C0332R WASHER D28270975002 0073 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 73 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 AN924-10J NUT D28270975002 0074 2 MS21909J10 TEE D28270975002 0075 2 NAS1149F1432P WASHER D28270975002 0076 1 TSTMNR503-0 CONDUIT D28270975002 0077 4 NSA935401-03 TIE D28270975002 0078 10 MS21919WDE10 CLAMP D28270975002 0079 13 MS21919WDE4 CLAMP D28270975002 0080

8 NSA5575-8A CLAMP D28270975002 0081 4 NSA5575-2 CLAMP D28270975002 0082 7 E0090-10-125NN LEAD D28270975002 0083 4 E0090-18-100NN LEAD D28270975002 0084 4 NAS1096-1-8 SCREW D28270975002 0085 4 NAS1149DN616H WASHER D28270975002 0086 4 MS21042-06 NUT D28270975002 0087 8 NAS1303-2 BOLT D28270975002 0088 8 NAS1726-3E NUT D28270975002 0089 8 NAS1149D0316H WASHER D28270975002 0090 1 MS21908J10 ELBOW D28270975002 0091 1 AN924-4D NUT D28270975002 0092 4 NAS1726C4E NUT D28270975002 0093 2 MS21914-10D CAP D28270975002 0094 1 AN924-10J NUT D28270975002 0095 1 NAS1149C1432R WASHER D28270975002 0096 7 NAS1096-3-9 SCREW D28270975002 0097 2 NAS1096-3-12 SCREW D28270975002 0098 1 MS21905J10 TEE D28270975002 0099 1 MS21919WCH15 CLAMP D28270975002 0101 1 E0090-10-160NN LEAD D28270975002 0102 1 D2827094420000 PLACARD D28270975002 0200 1 D2827094420200 PLACARD D28270975002 0202 1 D2827094420400 PLACARD D28270975002 0204 1 D2827094420600 PLACARD D28270975002 0206 1 D2827094420800 PLACARD D28270975002 0208 1 D2827094421000 PLACARD D28270975002 0210 1 D2827094421200 PLACARD D28270975002 0212

NOTE(01) PN 83694912 is the same as PN 1451515F0150-180 given in the drawing. 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 281118D17R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 6 NAS1096-3-8 SCREW D28270982002 0004 6 NAS1149C0332R WASHER D28270982002 0005 6 NAS1726C3E NUT D28270982002 0006 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 74 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 10 LN9198-3212BF RIVET D28270982002 0032 90 LN9198-4012BF RIVET D28270982002 0040

8 DAN7-6-8Y PIN D28270982002 0041 8 DAN12-6Y COLLAR D28270982002 0042 3 F5397461900600 BRACKET D28270982002 0100 2 D2827094222800 ANGLE D28270982002 0102 1 D2827098300000 BRACKET D28270982002 0104 1 D2827098300200 BRACKET D28270982002 0106 4 D2827094221400 ANGLE D28270982002 0112 2 D2827094220400 ANGLE D28270982002 0113 2 D2827094221800 ANGLE D28270982002 0115 2 D2827094222200 ANGLE D28270982002 0116 2 D2827098320800 BRACKET D28270982002 0117 2 D2827098321000 BRACKET D28270982002 0118 1 D2827098321200 ANGLE D28270982002 0119 2 D2827098321400 ANGLE D28270982002 0120 2 D2827098321600 ANGLE D28270982002 0121 2 D2827094200400 BRACKET D28270982002 0124 1 D2827098325200 BRACKET D28270982002 0125 1 D2827098300800 BRACKET D28270982002 0126 2 D2827098323200 BRACKET D28270982002 0127 2 D2827098323000 BRACKET D28270982002 0128 1 D2827098323400 BRACKET D28270982002 0129 1 D2827098323800 BRACKET D28270982002 0130 1 D2827093521000 BRACKET D28270982002 0131 1 D2827098324200 BRACKET D28270982002 0132 1 D2827098324400 BRACKET D28270982002 0133 1 D2827098324000 BRACKET D28270982002 0134

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 281118D18R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827099720000 BEAM D28270998002 0000 8 NSA5031-3-10 BOLT D28270998002 0770 8 NAS1726C3P NUT D28270998002 0807 8 NAS1149C0332R WASHER D28270998002 0808

Kit 281118D19R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827098322400 SHIM D28270999004 0004 8 NAS1303-5 BOLT D28270999004 0006 2 NAS1303-8 BOLT D28270999004 0010 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 75 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 10 NAS1149D0332K WASHER D28270999004 0014

1 D2827099600400 SHIELD D28270999004 0022

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 281118D21R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 8 D2557214637400 SHIM D25572631002 0000 8 D2557214637200 SHIM D25572631002 0001 6 D2557214635000 SHIM D25572631002 0002 6 D2557214635100 SHIM D25572631002 0003 6 D2557214635200 SHIM D25572631002 0004 3 D2557214636800 SHIM D25572631002 0005 3 D2557214637000 SHIM D25572631002 0006 1 D2557214653400 SHIM D25572631002 0007 1 D2557214653500 SHIM D25572631002 0008 1 D2557214653600 SHIM D25572631002 0009 1 D2557214653800 SHIM D25572631002 0010 1 D2557214653900 SHIM D25572631002 0011 1 D2557214654000 SHIM D25572631002 0012 25 NAS1102-3-10 SCREW D25572631002 0013 42 NAS1726-3E NUT D25572631002 0014 25 NAS1102-3-9 SCREW D25572631002 0015

2 NAS1100-3-7 SCREW D25572631002 0016 20 NAS1102-3-11 SCREW D25572631002 0017 NOTE (01) 20 NAS1102-3-14 SCREW D25572631002 0018 NOTE (01) 20 NAS1102-3-12 SCREW D25572631002 0019 NOTE (01) NOTE(01) Alternative bolt depending on shim thickness). 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 281118D22R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 16 D2557214635000 SHIM D25572631004 0000 16 D2557214635100 SHIM D25572631004 0001 16 D2557214635200 SHIM D25572631004 0002

1 D2557214633400 SHIM D25572631004 0003 1 D2557214633500 SHIM D25572631004 0004 1 D2557214633600 SHIM D25572631004 0005 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 76 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D2557214637600 SHIM D25572631004 0006 2 D2557214637700 SHIM D25572631004 0007 2 D2557214637800 SHIM D25572631004 0008 1 D2557214635400 SHIM D25572631004 0009 1 D2557214635500 SHIM D25572631004 0010 1 D2557214635600 SHIM D25572631004 0011 1 D2557214638400 SHIM D25572631004 0012 1 D2557214638500 SHIM D25572631004 0013 1 D2557214638600 SHIM D25572631004 0014 1 D2557214638800 SHIM D25572631004 0015 1 D2557214638900 SHIM D25572631004 0016 3 D2557214638100 SHIM D25572631004 0019 3 D2557214638200 SHIM D25572631004 0020 10 D2557214632000 SHIM D25572631004 0021 10 D2557214631800 SHIM D25572631004 0022

4 D2557214640000 SHIM D25572631004 0023 4 D2557214640200 SHIM D25572631004 0024 2 D2557214639600 SHIM D25572631004 0025 2 D2557214639700 SHIM D25572631004 0026 2 D2557214639800 SHIM D25572631004 0027 8 D2557214653200 SHIM D25572631004 0030 2 D2557214653000 SHIM D25572631004 0031 1 D2557214649200 SHIM D25572631004 0032 1 D2557214649300 SHIM D25572631004 0033 1 D2557214649400 SHIM D25572631004 0034 1 D2557214645200 SHIM D25572631004 0035 1 D2557214645300 SHIM D25572631004 0036 1 D2557214645400 SHIM D25572631004 0037 1 D2557214652000 SHIM D25572631004 0038 1 D2557214652100 SHIM D25572631004 0039 1 D2557214652200 SHIM D25572631004 0040 2 D2557214644800 SHIM D25572631004 0041 2 D2557214644900 SHIM D25572631004 0042 2 D2557214645000 SHIM D25572631004 0043 1 D2557214644000 SHIM D25572631004 0044 1 D2557214644100 SHIM D25572631004 0045 1 D2557214644200 SHIM D25572631004 0046 2 D2557206229800 PLUG D25572631004 0047 4 NAS1102-3-10 SCREW D25572631004 0048

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 281118D23R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 6 D2557238000400 LATCH D25572631006 0001 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 77 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 4 D2557238000000 LATCH D25572631006 0002 60 MS21250-03008 BOLT D25572631006 0003 120 MS21250-03006 BOLT D25572631006 0004 120 NAS1726-3E NUT D25572631006 0005

12 NAS1096-3-7 SCREW D25572631006 0006 12 NAS1096-3-8 SCREW D25572631006 0007 12 NAS1096-3-9 SCREW D25572631006 0008 60 MS21250-03010 BOLT D25572631006 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 281118D24R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 77 NAS1100-3-14 SCREW D25572631008 0006 38 NAS1102-3-10 SCREW D25572631008 0007 318 NAS1726-3E NUT D25572631008 0008

64 NAS1102-3-9 SCREW D25572631008 0039

1 D2557268028600 PLATE D25572631008 0049 1 D2557268121000 DOUBLER D25572631008 0050 6 D2557268030600 SHIM D25572631008 0051 6 D2557226520400 SUPPORT D25572631008 0052 6 D2557226120200 BLOCK D25572631008 0053 6 NSA5042C05-180 BOLT D25572631008 0054 6 NSA5060-4 NUT D25572631008 0055 6 NAS1149C0432R WASHER D25572631008 0056 6 NAS1149C0532R WASHER D25572631008 0057 6 MS24665-153 PIN D25572631008 0058 36 DAN7-5-5 PIN D25572631008 0061 36 DAN7-5-6 PIN D25572631008 0062 36 DAN12-5 COLLAR D25572631008 0063 51 NAS1100-3-10 SCREW D25572631008 0070 13 NAS1102-3-11 SCREW D25572631008 0080 14 NAS1102-3-14 SCREW D25572631008 0082 45 NAS1100-3-9 SCREW D25572631008 0083 54 NAS1100-3-11 SCREW D25572631008 0084 80 NAS1100-3-7 SCREW D25572631008 0087

1 D2557221301400 TRACK D25572631008 0088 1 D2557221300600 TRACK D25572631008 0089 2 D2557235621000 PLATE D25572631008 0091 1 D2557221301200 TRACK D25572631008 0092 15 LN9198-3216CF RIVET D25572631008 0094 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

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 78 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281118D25R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 134100-5 LATCH D25572631010 0141 2 D2557237422800 TRACK D25572631010 0142 1 D2557237423000 TRACK D25572631010 0143 4 MS21250-05028 BOLT D25572631010 0144 5 MS21250-05022 BOLT D25572631010 0145 9 MS21042-5 NUT D25572631010 0146 1 D2557238721000 SPACER D25572631010 0147 12 D2557231520400 SPACER D25572631010 0148 NOTE : The content of Kit 281118D25R00 is necessary for the accomplishment of the SB A320-28-1119. Tag the parts and put them into suitable boxes into storage. 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 281118D26R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557295526200 PLACARD D25572631012 0150 1 A2557144422000 PLACARD D25572631012 0151 1 D2557295122400 PLACARD D25572631012 0152

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 281118D27R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2587085002200 BLANKET D25870003054 0000 1 D2587085105600 BLANKET D25870003054 0001 1 D2587085205200 BLANKET D25870003054 0002 1 D2587085305600 BLANKET D25870003054 0003 1 D2587085405200 BLANKET D25870003054 0004 1 D2587085505400 BLANKET D25870003054 0005 1 D2587085602200 BLANKET D25870003054 0006 1 D2587085705200 BLANKET D25870003054 0007 1 D2587085805200 BLANKET D25870003054 0008 1 D2587085905200 BLANKET D25870003054 0009 1 D2587086005400 BLANKET D25870003054 0010 1 D2587086105200 BLANKET D25870003054 0011 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 79 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2587086202200 BLANKET D25870003054 0012 1 D2587086302400 BLANKET D25870003054 0013 1 D2587086502200 BLANKET D25870003054 0014 1 D2587087102200 BLANKET D25870003054 0015 1 D2587087302200 BLANKET D25870003054 0016 80 F2587003400000 STRIP D25870003054 0100 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 281118D29R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

25 DAN107-1 CORD D53675014002 0385 25 ABS5093AT25 TAPE D53675014002 0387 Kit 281118D30R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

1.5 ABS0305LC SECTION D53675511002 0001 7.2 ABS0399A SECTION D53675511002 0004 25 DAN107-1 CORD D53675511002 0005 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 281118D31R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367161701800 PANEL D53675013000 0016 2 D5367160001200 PANEL D53675013000 0028 56 ABS0376-3-25 SCREW D53675013000 0400 56 ABS0365-3-1B NUT D53675013000 0405 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 281118D32R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 80 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

25 DAN107-1 CORD D53675014000 0385 20 ABS5093AT25 TAPE D53675014000 0387 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 281118D33R02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367326000000 PANEL D53672848000 0028 1 D5367326100200 PANEL D53672848000 0030 1 D5367326200200 PANEL D53672848000 0032 1 D5367326300000 PANEL D53672848000 0034 1 D5367321800000 PANEL D53672848000 0072 1 D5367321900000 PANEL D53672848000 0074 1 D5367322100000 PANEL D53672848000 0076 1 D5367322000000 PANEL D53672848000 0078 1 D5367327000000 PANEL D53672848000 0080 1 D5367327100000 PANEL D53672848000 0082 1 D5397484220000 PLATE D53672848000 0110 1 D5397484220100 PLATE D53672848000 0111 2 D5397489520000 SPACER D53672848000 0118 2 D5397489520100 SPACER D53672848000 0119 139 ABS0376-3-30 SCREW D53672848000 0402 108 ABS0376-3-40 SCREW D53672848000 0404

20 NAS1102-3-8 SCREW D53672848000 0408 76 ABS0365-3-1B NUT D53672848000 0410 1.6 ABS5006-4D TAPE D53672848000 0441 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 281118D34R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 8 ABS0305LC SECTION D53672849000 0001 20 ABS0305LB SECTION D53672849000 0002 20 ABS0398A02 SECTION D53672849000 0003 20 ABS0399A SECTION D53672849000 0004 80 DAN107-1 CORD D53672849000 0005 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. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 81 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Kit 281118D35R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367301800000 PANEL D53672850000 0000 1 D5367301800100 PANEL D53672850000 0001 1 D5367302000000 PANEL D53672850000 0002 1 D5367302400000 PANEL D53672850000 0004 1 D5367302600000 PANEL D53672850000 0006 1 D5367303400000 PANEL D53672850000 0008 1 D5367303400100 PANEL D53672850000 0009 1 D5367302200000 PANEL D53672850000 0010 1 D5367302700000 PANEL D53672850000 0012 1 D5367306200000 PANEL D53672850000 0028 1 D5367306200100 PANEL D53672850000 0029 1 D5367305500000 PANEL D53672850000 0030 1 D5367305300000 PANEL D53672850000 0032 1 D5367305400000 PANEL D53672850000 0034 1 D5367305200000 PANEL D53672850000 0038 1 D5367305600000 PANEL D53672850000 0040 1 D5367316000000 PANEL D53672850000 0042 1 D5367316000100 PANEL D53672850000 0043 320 ABS0376-3-25 SCREW D53672850000 0400

64 ABS0376-3-30 SCREW D53672850000 0402 320 ABS0365-3-1B NUT D53672850000 0410 6 NAS1169C10L WASHER D53672850000 0414

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 281118D36R03 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D5397489200000 SECTION D53975018000 0000 2 D5397489200100 SECTION D53975018000 0001 44 NAS6703-2 BOLT D53975018000 0025 44 NAS1149D0332K WASHER D53975018000 0026

1 D5347047400200 SECTION D53975018000 0030 1 D5347047400300 SECTION D53975018000 0031 1 D5397467800800 SECTION D53975018000 0040 1 D5397467800900 SECTION D53975018000 0041 1 D5397492600000 SECTION D53975018000 0042 1 D5397468800200 SECTION D53975018000 0044 1 D5397468800300 SECTION D53975018000 0045 1 D5397468000400 SECTION D53975018000 0046 1 D5397468000500 SECTION D53975018000 0047 1 D5397492500090 SECTION D53975018000 0048 1 D5397492500290 SECTION D53975018000 0050 1 D5397467400500 SECTION D53975018000 0052 1 D5397467400400 SECTION D53975018000 0053 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 3 D5397492700000 PLATE D53975018000 0054 9 NAS1102E3-7 SCREW D53975018000 0400 9 DAN125-4 WASHER D53975018000 0402 250 NAS1097AD4-10 RIVET D53975018000 0532 4 NSA5075-6 COLLAR D53975018000 0806 4 DAN5-6-2 PIN D53975018000 0962

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 281118D37R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367520801400 PANEL D53672848002 0036 1 D5367520801800 PANEL D53672848002 0038 1 D5367520805000 PANEL D53672848002 0040 1 D5367520805200 PANEL D53672848002 0042 1 D5367521102600 PANEL D53672848002 0084 1 D5367521102800 PANEL D53672848002 0086 1 D5367521103000 PANEL D53672848002 0088 1 D5367521103200 PANEL D53672848002 0090 1 D5367521103400 PANEL D53672848002 0092 1 D5367521103600 PANEL D53672848002 0094 1 D5397484220000 PLATE D53672848002 0110 1 D5397484220100 PLATE D53672848002 0111 2 D5397489520000 SPACER D53672848002 0118 2 D5397489520100 SPACER D53672848002 0119 62 ABS0376-3-30 SCREW D53672848002 0402 93 ABS0376-3-40 SCREW D53672848002 0404 12 NAS1102-3-8 SCREW D53672848002 0408 55 ABS0365-3-1B NUT D53672848002 0410 1.6 ABS5006-4D TAPE D53672848002 0441 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 281118D38R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D5397489200000 SECTION D53975018002 0000 2 D5397489200100 SECTION D53975018002 0001 1 D5397469000000 BRACKET D53975018002 0016 1 D5397469000100 BRACKET D53975018002 0017 1 D5397469200000 BRACKET D53975018002 0018 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 83 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5397469200100 BRACKET D53975018002 0019 1 D5397469300000 BRACKET D53975018002 0020 1 D5397469300100 BRACKET D53975018002 0021 44 NAS6703-2 BOLT D53975018002 0025 44 NAS1149D0332K WASHER D53975018002 0026 22 D5397469700000 SUPPORT D53975018002 0028

1 D5347047400200 SECTION D53975018002 0030 1 D5347047400300 SECTION D53975018002 0031 1 D5397467800800 SECTION D53975018002 0040 1 D5397467800900 SECTION D53975018002 0041 1 D5397492600000 SECTION D53975018002 0042 1 D5397468800200 SECTION D53975018002 0044 1 D5397468800300 SECTION D53975018002 0045 1 D5397468000400 SECTION D53975018002 0046 1 D5397468000500 SECTION D53975018002 0047 1 D5397492500090 SECTION D53975018002 0048 1 D5397492500290 SECTION D53975018002 0050 1 D5397467400500 SECTION D53975018002 0052 1 D5397467400400 SECTION D53975018002 0053 3 D5397492700000 PLATE D53975018002 0054 9 NAS1102E3-7 SCREW D53975018002 0400 9 DAN125-4 WASHER D53975018002 0402 49 NAS1097AD4-10 RIVET D53975018002 0532 49 EN6081D6-12 RIVET D53975018002 0648

4 NSA5075-6 COLLAR D53975018002 0806 4 DAN5-6-2 PIN D53975018002 0962

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 281118D39R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367161702200 PANEL D53675013010 0018 2 D5367160001600 PANEL D53675013010 0029 1 D5367150100200 PANEL D53675013010 0030 74 ABS0376-3-25 SCREW D53675013010 0400 74 ABS0365-3-1B NUT D53675013010 0405 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 281118D40R02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 84 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

12 D2557214631800 SHIM D25572631022 0014 12 D2557214632000 SHIM D25572631022 0015

4 D2557214633400 SHIM D25572631022 0034 4 D2557214633500 SHIM D25572631022 0035 4 D2557214633600 SHIM D25572631022 0036 36 D2557214635000 SHIM D25572631022 0050 36 D2557214635100 SHIM D25572631022 0051 36 D2557214635200 SHIM D25572631022 0052

2 D2557214635400 SHIM D25572631022 0054 2 D2557214635500 SHIM D25572631022 0055 2 D2557214635600 SHIM D25572631022 0056 2 D2557214653400 SHIM D25572631022 0058 2 D2557214653500 SHIM D25572631022 0059 2 D2557214653600 SHIM D25572631022 0060 14 D2557214636800 SHIM D25572631022 0066 14 D2557214637000 SHIM D25572631022 0068 16 D2557214637200 SHIM D25572631022 0070 16 D2557214637400 SHIM D25572631022 0072

4 D2557214637600 SHIM D25572631022 0076 4 D2557214637700 SHIM D25572631022 0077 4 D2557214637800 SHIM D25572631022 0078 12 D2557214638000 SHIM D25572631022 0080 12 D2557214638100 SHIM D25572631022 0081 12 D2557214638200 SHIM D25572631022 0082

2 D2557214638400 SHIM D25572631022 0084 2 D2557214638500 SHIM D25572631022 0085 2 D2557214638600 SHIM D25572631022 0086 6 D2557214638800 SHIM D25572631022 0088 6 D2557214638900 SHIM D25572631022 0089 6 D2557214639000 SHIM D25572631022 0090 4 D2557214639600 SHIM D25572631022 0096 4 D2557214639700 SHIM D25572631022 0097 4 D2557214639800 SHIM D25572631022 0098 2 D2557206229800 PLUG D25572631022 0104 4 NAS1102-3-10 SCREW D25572631022 0134 4 D2557214653000 SHIM D25572631022 0229 2 D2557214653800 SHIM D25572631022 0233 2 D2557214653900 SHIM D25572631022 0234 2 D2557214654000 SHIM D25572631022 0235 16 D2557214653200 SHIM D25572631022 0236 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 281118D41R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557221501800 TRACK D25572631024 0001 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 85 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 4 NAS1102-3-7 SCREW D25572631024 0006 142 NAS1102-3-10 SCREW D25572631024 0007 303 NAS1726-3E NUT D25572631024 0008 144 NAS1102-3-11 SCREW D25572631024 0009 144 NAS1102-3-12 SCREW D25572631024 0010 101 NAS1102-3-14 SCREW D25572631024 0011 6 NAS1102-3-16 SCREW D25572631024 0012 4 NAS1100-3-5 SCREW D25572631024 0018 1 D2557265000000 SPACER D25572631024 0019 1 D2557243320000 FUNNEL D25572631024 0022 1 A2577238700400 STOP D25572631024 0023 2 D2557263120400 PLATE D25572631024 0024 8 NAS1102-3-8 SCREW D25572631024 0026 1 A2577238320000 ROLLER D25572631024 0027 1 D2557268000000 FITTING D25572631024 0029 1 D2557221501600 TRACK D25572631024 0030 4 NAS1801-3-8 SCREW D25572631024 0032 2 NAS1149C0463R WASHER D25572631024 0036 2 NAS1304-5 BOLT D25572631024 0037 16 NAS1096-3-11 SCREW D25572631024 0038 43 NAS1102-3-9 SCREW D25572631024 0039

2 NAS1303-6 BOLT D25572631024 0040 2 NAS1100-3-6 SCREW D25572631024 0041 28 MS21042-3 NUT D25572631024 0042 28 NAS1153-3 SCREW D25572631024 0043

2 A2577238420400 PIN D25572631024 0044 2 NAS1149C0563R WASHER D25572631024 0045 2 NSA5059-5 NUT D25572631024 0046 8 MS24665-153 PIN D25572631024 0047 6 NAS1306-5 BOLT D25572631024 0049 6 NAS1726-6E NUT D25572631024 0050 6 NAS1801-3-8 SCREW D25572631024 0053 3 NSA5066-3-1 NUT D25572631024 0054 2 DAN152-1 TDP D25572631024 0056 1 D2557243220000 BRACKET D25572631024 0058 1 D2557243520000 FILTER D25572631024 0059 140 NAS1100-3-10 SCREW D25572631024 0070 138 NAS1100-3-9 SCREW D25572631024 0083 146 NAS1100-3-11 SCREW D25572631024 0084

42 NAS1100-3-12 SCREW D25572631024 0085

8 NAS1100-3-14 SCREW D25572631024 0086 104 NAS1100-3-7 SCREW D25572631024 0087 1 D2557221301400 TRACK D25572631024 0088 6 NAS1100-3-16 SCREW D25572631024 0089 2 D2557235621000 PLATE D25572631024 0091 1 D2557221301200 TRACK D25572631024 0092 49 DIN65399-3210CF RIVET D25572631024 0094

2 ABS0202-3-10 SCREW D25572631024 0101 1 D2557295123200 PLACARD D25572631024 0102 2 D2557214652800 SHIM D25572631024 0103 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 86 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D2557214652700 SHIM D25572631024 0104 11 1460T100-3 ROLLER D25572631024 0122

1 109100-1 LATCH D25572631024 0126 1 D2557268028600 PLATE D25572631024 0149 1 D2557268121000 DOUBLER D25572631024 0150 6 D2557268030600 SHIM D25572631024 0151 6 D2557226520400 SUPPORT D25572631024 0152 6 D2557226120200 BLOCK D25572631024 0153 6 NSA5042C05-180 BOLT D25572631024 0154 6 NSA5060-4 NUT D25572631024 0155 6 NAS1149C0432R WASHER D25572631024 0156 6 NAS1149C0532R WASHER D25572631024 0157 36 DAN7-5-5 PIN D25572631024 0161 36 DAN7-5-6 PIN D25572631024 0162 36 DAN12-5 COLLAR D25572631024 0163 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 281118D42R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 7 D2557238001000 LATCH D25572631026 0004 8 D2557235000800 LATCH D25572631026 0005 8 2847T100-1 ROLLER D25572631026 0009 66 MS21250-03006 BOLT D25572631026 0024 86 MS21250-03008 BOLT D25572631026 0025 92 MS21250-03010 BOLT D25572631026 0026 92 MS21250-03012 BOLT D25572631026 0027 26 MS21250-03014 BOLT D25572631026 0028 122 NAS1726-3E NUT D25572631026 0045 6 D2557238000400 LATCH D25572631026 0076 12 NAS1096-3-7 SCREW D25572631026 0079 12 NAS1096-3-8 SCREW D25572631026 0080 12 NAS1096-3-10 SCREW D25572631026 0081 12 NAS1096-3-12 SCREW D25572631026 0082 30 NAS1102-3-12 SCREW D25572631026 0083 30 NAS1102-3-14 SCREW D25572631026 0084 30 NAS1102-3-18 SCREW D25572631026 0085 30 NAS1102-3-22 SCREW D25572631026 0086 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 281118D43R00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 87 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 4 NAS1102-3-10 SCREW D25572631028 0033 16 NSA5030-3-5 SCREW D25572631028 0034

4 NAS1726-3E NUT D25572631028 0035 1 D2557215902400 MAT D25572631028 0070 1 D2557215702400 MAT D25572631028 0071 1 D2557216001400 MAT D25572631028 0072 18 EN6131C3C4 NUT D25572631028 0086 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 281118D44R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 DAN152-1 TDP D25572631030 0000 2 D2557206220200 TDP D25572631030 0002 2 NAS1726-3E NUT D25572631030 0003 2 NAS1102-3-10 SCREW D25572631030 0004 2 D2557215020200 SPACER D25572631030 0008 2 NAS1153-23 SCREW D25572631030 0010 2 NAS1153-25 SCREW D25572631030 0014

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 281118D46R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 A2557144422000 PLACARD D25572631036 0011 1 D2557294923000 PLACARD D25572631036 0030 1 D2557295138400 PLACARD D25572631036 0184 1 D2557295122600 PLACARD D25572631036 0026 1 D2557294923800 PLACARD D25572631036 0038

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 281118D50R02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 L32A319-160-002 CONTROL D53370297000 0000 1 L32A319-165-002 ADAPTER D53370297000 0002 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D5337025020000 ANGLE D53370297000 0006 2 D5337025620200 SECTION D53370297000 0008 1 D5337025620600 SECTION D53370297000 0010 1 D5337025920000 ANGLE D53370297000 0012 1 D5337645020000 BRIDGE D53370297000 0014 1 D5337645300200 BRACKET D53370297000 0016 1 D5337645420000 BRACKET D53370297000 0018 10 MS21919WCH6 CLAMP D53370297000 0030 0.06 DAN79-07 HOSE D53370297000 0032 2 NSA935401-03 TIE D53370297000 0034 1 MS20392-2C19 PIN D53370297000 0036 7 NSA5031-3-5 BOLT D53370297000 0040 3 NSA5031-3-4 BOLT D53370297000 0042 1 NAS1726C4P NUT D53370297000 0060 1 NAS509-4C NUT D53370297000 0062 10 NAS1726C3P NUT D53370297000 0064 16 NAS1149C0332R WASHER D53370297000 0070

2 MS24665-153 PIN D53370297000 0080 32 LN9198-3212BF RIVET D53370297000 0632

2 DIN65399-3208BF RIVET D53370297000 0652

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 281118D51R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 L32A319-160-002 CONTROL D53370297001 0000 1 L32A319-165-001 ADAPTER D53370297001 0004 2 D5337025020100 ANGLE D53370297001 0007 2 D5337025620200 SECTION D53370297001 0008 1 D5337025620700 SECTION D53370297001 0011 1 D5337025920000 ANGLE D53370297001 0012 1 D5337645020100 BRIDGE D53370297001 0015 1 D5337645300300 BRACKET D53370297001 0017 1 D5337645420000 BRACKET D53370297001 0018 10 MS21919WCH6 CLAMP D53370297001 0030 0.06 DAN79-07 HOSE D53370297001 0032 2 NSA935401-03 TIE D53370297001 0034 1 MS20392-2C19 PIN D53370297001 0036 7 NSA5031-3-5 BOLT D53370297001 0040 3 NSA5031-3-4 BOLT D53370297001 0042 1 NAS1726C4P NUT D53370297001 0060 1 NAS509-4C NUT D53370297001 0062 10 NAS1726C3P NUT D53370297001 0064 16 NAS1149C0332R WASHER D53370297001 0070

2 MS24665-153 PIN D53370297001 0080 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 89 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 32 LN9198-3212BF RIVET D53370297001 0632 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 281118D55R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5347212320000 BRACKET D53472833008 0000 1 D5347212420000 PIN D53472833008 0002 1 D5347212420200 RING D53472833008 0004

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 281118D56R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 NSA5516A18NJ CLAMP D26270107000 0002 3 NAS1726-3E NUT D26270107000 0003 1 NAS1303-2 BOLT D26270107000 0004 1 ASNA0182-3DA STRIP D26270107000 0005 1 D2627004020800 BRACKET D26270107000 0100 2 NSA5031-3-14 BOLT D26270107000 0123

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 281118D60R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5347503400200 PANEL D53475023000 0000 1 D5347542400000 BRACKET D53475023000 0020 2 D5347542720000 BRACKET D53475023000 0022 1 D5347542400200 BRACKET D53475023000 0024 2 NAS1791A3-1 NUT D53475023000 0026 3 ABS0368-01 RECEPTCLD53475023000 0028 2 D5347521320000 WASHER D53475023000 0032 15 DIN65399-2412BF RIVET D53475023000 0125 40 LN9198-4012CF RIVET D53475023000 0240

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 90 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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 281118D61R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 A9249175120000 ANGLE D53371046000 0001 1 D5337312600000 PLATE D53371046000 0002 1 D5337312000000 PLATE D53371046000 0003 4 D5337312420000 STRAP D53371046000 0004 8 NAS6703U7 BOLT D53371046000 0005 8 NAS6703U5 BOLT D53371046000 0006 16 NAS1726C3P NUT D53371046000 0007 16 NAS1149C0332R WASHER D53371046000 0008

1 D5337107420200 PLATE D53371046000 0009 1 D5337311520200 WALL D53371046000 0010 1 D5337311920200 PLATE D53371046000 0011 2 D5337309820000 SHEET D53371046000 0012 2 D5337307220100 STIFFENR D53371046000 0013 1 D5337307220000 STIFFENR D53371046000 0014 1 D5337312120400 SECTION D53371046000 0015 1 D5337312120600 SECTION D53371046000 0016 1 D5337312120700 SECTION D53371046000 0017 1 D5337312120200 SECTION D53371046000 0018 1 D5337313420000 SECTION D53371046000 0019 3 DAN7-5A5 PIN D53371046000 0020 2 DAN6-6-4 PIN D53371046000 0021 4 DAN5-6-4 PIN D53371046000 0022 20 DAN5-6-6 PIN D53371046000 0023

4 DAN5-6-7 PIN D53371046000 0024 6 NSA5075-6 COLLAR D53371046000 0025 3 ABS0258-5C COLLAR D53371046000 0026 24 NSA5076-6 COLLAR D53371046000 0027 12 LN9198-3208BF RIVET D53371046000 0028 196 LN9198-4812CF RIVET D53371046000 0029 8 LN9198-4814CF RIVET D53371046000 0030 15 LN9198-4009CF RIVET D53371046000 0031

3 LN9198-4010CF RIVET D53371046000 0032 11 LN9198-4011CF RIVET D53371046000 0033

8 LN9198-4012CF RIVET D53371046000 0035 10 DAN5-5-7 PIN D53371046000 0036

8 DAN5-5-6 PIN D53371046000 0037 12 NSA5075-5 COLLAR D53371046000 0038

6 NSA5076-5 COLLAR D53371046000 0039

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. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 91 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Kit 281118D62R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

20 DAN7-6-8X PIN D53371237000 0001 32 DAN7-8-8X PIN D53371237000 0002 12 DAN7-8-10X PIN D53371237000 0003

1 DAN8-8-8X PIN D53371237000 0004 20 DAN12-6X COLLAR D53371237000 0005 45 DAN12-8X COLLAR D53371237000 0006 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 281118D63R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

20 DAN7-6-8X PIN D53371237001 0001 32 DAN7-8-8X PIN D53371237001 0002 12 DAN7-8-10X PIN D53371237001 0003

1 DAN8-8-8X PIN D53371237001 0004 20 DAN12-6X COLLAR D53371237001 0005 45 DAN12-8X COLLAR D53371237001 0006 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 281118D67R02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 8 NAS1096-2-7 SCREW D92891803004 0004 8 NAS1096-2-18 SCREW D92891803004 0005 23 NAS1096-2-10 SCREW D92891803004 0006

4 NAS1096-2-12 SCREW D92891803004 0007 2 NAS1096-2-14 SCREW D92891803004 0009 20 NAS1096-2-19 SCREW D92891803004 0012

2 NAS1096-2-25 SCREW D92891803004 0016 10 NSA935808C01 WASHER D92891803004 0020 22 NAS1096-2-43 SCREW D92891803004 0022

2 NAS1096-3-6 SCREW D92891803004 0026 4 NAS1096-3-8 SCREW D92891803004 0028 12 NSA5066-08-2 NUT D92891803004 0032

6 MS21919WCH4 CLAMP D92891803004 0041 16 NSA935807-06 CLAMP D92891803004 0042

6 NSA935807-09 CLAMP D92891803004 0045 4 NSA5527-03-01 SPACER D92891803004 0050 6 NAS1100-04-5 SCREW D92891803004 0051 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 92 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 NSA5527-03-02 SPACER D92891803004 0052 6 NSA5527-03-06 SPACER D92891803004 0055 38 NAS1149CN816R WASHER D92891803004 0152

2 NAS1149C0332R WASHER D92891803004 0153 18 NSA935808C01 WASHER D92891803004 0171

2 MS21042L3 NUT D92891803004 0210 38 NSA5066-08-2 NUT D92891803004 0231

6 NSA5527-03-02 SPACER D92891803004 0302 19 NSA5527-03-04 SPACER D92891803004 0306 18 NSA5527-03-06 SPACER D92891803004 0310

8 MS21919WCH4 CLAMP D92891803004 0350 10 MS21919WCH2 CLAMP D92891803004 0364 22 NSA935807-06 CLAMP D92891803004 0376 22 NSA935807-09 CLAMP D92891803004 0377 100 NSA935401-05 TIE D92891803004 0780 100 NSA935401-03 TIE D92891803004 0793 150 NSA935401-04 TIE D92891803004 0794 1 D9249171020200 SECTION D92891803004 0800 0.675 NSA939510AN STRIP D92891803004 0894 1 NSA939510DN STRIP D92891803004 0896 2 E0484KMJ0900 TUBING D92891803004 1190

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 281118D68R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

22 NAS1096-2-7 SCREW D92891803002 0001 23 NAS1096-2-9 SCREW D92891803002 0005

7 NAS1096-2-12 SCREW D92891803002 0007 2 NAS1096-2-16 SCREW D92891803002 0010 5 NAS1096-2-19 SCREW D92891803002 0012 2 NAS1096-2-22 SCREW D92891803002 0014 1 NAS1096-2-36 SCREW D92891803002 0020 92 NAS1096-3-9 SCREW D92891803002 0030 24 NAS1100-04-5 SCREW D92891803002 0051 12 NAS1102-08-8 SCREW D92891803002 0058 32 NAS1102-3-9 SCREW D92891803002 0099 24 NAS1149CN416R WASHER D92891803002 0150 50 NAS1149CN816R WASHER D92891803002 0152 136 NAS1149C0332R WASHER D92891803002 0153

28 NAS1149D0363K WASHER D92891803002 0161

4 ASNA0113-40ADL WASHER D92891803002 0163 10 NSA935808C01 WASHER D92891803002 0171

2 D9249102520000 WASHER D92891803002 0190 24 MS21042-04 NUT D92891803002 0200 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 93 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 4 MS21042-3 NUT D92891803002 0203 28 MS21042L3 NUT D92891803002 0210 27 NAS1291C3M NUT D92891803002 0218

1 NSA5110-08-1 NUT D92891803002 0225 3 NSA5066-08-1 NUT D92891803002 0230 18 NSA5067-08-1 NUT D92891803002 0236

6 E0343-01 MOUNT D92891803002 0250 12 NSA935504-01 MOUNT D92891803002 0251

8 NSA935504-02 MOUNT D92891803002 0252 2 NSA935513-01 MOUNT D92891803002 0256 10 NSA935513-05 MOUNT D92891803002 0257

1 NSA935513-07 MOUNT D92891803002 0259 8 ABS0355-01 BRACKET D92891803002 0262 11 ABS0355-02 BRACKET D92891803002 0263 12 NSA935514-03 WASHER D92891803002 0264

2 E0660-01 MOUNT D92891803002 0266 20 ABS0731A01 SUPPORT D92891803002 0267

1 NSA5527-03-02 SPACER D92891803002 0302 2 NSA5527-03-03 SPACER D92891803002 0304 4 NSA5527-03-04 SPACER D92891803002 0306 1 NSA5527-03-06 SPACER D92891803002 0310 5 NSA5527-03-08 SPACER D92891803002 0314 1 NSA5527-03-11 SPACER D92891803002 0320 1 MS21919WCH6 CLAMP D92891803002 0352 6 NSA935807-09 CLAMP D92891803002 0377 4 NSA935807-16 CLAMP D92891803002 0381 8 D9249101020000 FRLDHALF D92891803002 0668 8 D9249101020200 FRLDHALF D92891803002 0669 2 D9249104800000 SHEET D92891803002 0727 1 D9249104800400 SHEET D92891803002 0729 3 D2557016200000 COVER D92891803002 0734 2.72 TSTMNR502-0 CONDUIT D92891803002 0763 4 NSA934710T13 FITTING D92891803002 0773 16 NSA934710T14 FITTING D92891803002 0774 45 NSA935510-02 BOBBIN D92891803002 0777 15 NSA934710E20 SPRING D92891803002 0783

1 NSA934710E23 SPRING D92891803002 0784 1 NSA934710E24 SPRING D92891803002 0786 200 NSA935401-03 TIE D92891803002 0793 400 NSA935401-04 TIE D92891803002 0794 200 NSA935401-05 TIE D92891803002 0795 2 D9249107300400 STRAP D92891803002 0812 1 D9249107100600 STRAP D92891803002 0834 2 DAN328H25 TAPE D92891803002 0877 2 EN2997KE3C12 CAP D92891803002 0930 1 EN2997KE3C16 CAP D92891803002 0932 2 EN2997KE512 CONNECTR D92891803002 0933 1 EN2997KE516 CONNECTR D92891803002 0935 2 D9249104900600 BRACKET D92891803002 1110

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 94 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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 281118D69R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9289180320000 PLACARD D92891803000 NOTE (01) 1 D9289180320200 PLACARD D92891803000 NOTE (01) 28 NAS1096-2-8 SCREW D92891803000 0001 116 NAS1096-2-18 SCREW D92891803000 0002 3 NAS1096-2-28 SCREW D92891803000 0003 77 NAS1096-3-8 SCREW D92891803000 0004 144 NSA5066-08-2 NUT D92891803000 0005 1 NSA5527-03-08 SPACER D92891803000 0006 101 MS21042L3 NUT D92891803000 0007 160 NAS1149DN816K WASHER D92891803000 0009

33 NAS1149D0332K WASHER D92891803000 0010 11 MS21919WCH5 CLAMP D92891803000 0013

4 NSA5527-03-02 SPACER D92891803000 0016 2 NSA935808-01 WASHER D92891803000 0017 1 ABS0731A01 SUPPORT D92891803000 0018 76 NAS1149C0332R WASHER D92891803000 0019 110 NSA5527-03-01 SPACER D92891803000 0020

12 NSA934710T11 FITTING D92891803000 0021 22 NSA934710T14 FITTING D92891803000 0022

1 E0660-01 MOUNT D92891803000 0023 9 NSA935513-01 MOUNT D92891803000 0027 64 NAS1149D0363K WASHER D92891803000 0030 123 NSA935504-01 MOUNT D92891803000 0031

23 NSA5527-03-03 SPACER D92891803000 0035 1002 NSA935401-04 TIE D92891803000 0036 1 MS21042L08 NUT D92891803000 0037 1 D9249181406400 GUIDE D92891803000 0038 1 D9249181406600 GUIDE D92891803000 0039 10 NSA934710E20 SPRING D92891803000 0040

2 NSA934710E23 SPRING D92891803000 0041 2 D9249173320000 FRLDHALF D92891803000 0042 2 D9249173320200 FRLDHALF D92891803000 0043 1 D9249173320400 FRLDHALF D92891803000 0044 1 D9249173320600 FRLDHALF D92891803000 0045 7 NSA5527-03-04 SPACER D92891803000 0048 8 NAS1096-2-10 SCREW D92891803000 0049 1 NAS1096-2-43 SCREW D92891803000 0055 1 NSA935504-02 MOUNT D92891803000 0056 4 NAS1096-2-24 SCREW D92891803000 0058 1 NSA5527-03-06 SPACER D92891803000 0059 8 E0343-01 MOUNT D92891803000 0063 32 NAS1096-3-10 SCREW D92891803000 0064 0.1 NSA939510BN STRIP D92891803000 0080 12 D9249102520000 WASHER D92891803000 0086 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 95 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 ABS0355-01 BRACKET D92891803000 0096 1 ABS0355-02 BRACKET D92891803000 0097 1 NSA935514-03 WASHER D92891803000 0098 2 NSA935510-02 BOBBIN D92891803000 0099

NOTE(01) Use the placards for the drawings D92891803000, D92891803002 and D92891803004. 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 281118D70R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

42 A9249635720200 BRACKET D92492243000 0001 55 D9249179320000 BRACKET D92492243000 0002

6 D9249178000600 BRACKET D92492243000 0007 3 D9249177520000 ANGLE D92492243000 0012 4 D9249172321200 BRACKET D92492243000 0016 1 D9249184620400 BRACKET D92492243000 0021 1 D9249177100000 BRACKET D92492243000 0023 1 D9249180922600 BRACKET D92492243000 0026 1 MS21060L3 NUT D92492243000 0027 1 D9249178001200 BRACKET D92492243000 0030 6 DIN65399-3208BF RIVET D92492243000 0621 310 LN9198-3208BF RIVET D92492243000 0632

16 LN9198-4814CF RIVET D92492243000 0648

6 DIN65399-2408BF RIVET D92492243000 0724

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 281118D71R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 4 NSA5066-08-1 NUT D92492243002 0230 1 D5347849120400 BRACKET D92492243002 0402 1 D5347849120500 BRACKET D92492243002 0403 1 D5347849021400 BRACKET D92492243002 0404 1 D5347849021500 BRACKET D92492243002 0405 2 A9249199820000 PLATE D92492243002 0406 2 A9249187820200 SHEET D92492243002 0565 1 D9249103700200 PLATE D92492243002 0629 50 LN9198-3208BF RIVET D92492243002 0632 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 96 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 4 D9249104920000 BRACKET D92492243002 0735 3 D9249104920400 BRACKET D92492243002 0737

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 281118D72R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 8 NAS1096-3-8 SCREW D92492244000 0001 40 NAS1096-2-8 SCREW D92492244000 0003

1 NAS1096-2-18 SCREW D92492244000 0004 9 NAS1149D0332K WASHER D92492244000 0005 40 NAS1149DN816K WASHER D92492244000 0006

8 MS21042L3 NUT D92492244000 0009 16 MS21042L08 NUT D92492244000 0010

4 DAN364-02 PIN D92492244000 0011 3 ABS0355-01 BRACKET D92492244000 0012 3 ABS0355-02 BRACKET D92492244000 0013 3 NSA935514-03 WASHER D92492244000 0014 1 E0343-01 MOUNT D92492244000 0015 1 NSA5527-03-06D SPACER D92492244000 0017 6 D9249177920000 BRACKET D92492244000 0018 1 D9249180800200 BRACKET D92492244000 0024 1 D9249180800400 BRACKET D92492244000 0025 1 D9249180900000 BRACKET D92492244000 0026 1 D9249180922400 BRACKET D92492244000 0027 2 D9249177820200 BRACKET D92492244000 0030

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 281118D73R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 7 NAS1096-2-12 SCREW D92492244002 0007 1 NAS1096-2-14 SCREW D92492244002 0009 10 ASNA0113-40ADL WASHER D92492244002 0163

2 D9249102520000 WASHER D92492244002 0190 4 E0660-01 MOUNT D92492244002 0266 1 NSA5527-03-04 SPACER D92492244002 0306 1 NSA5527-03-07 SPACER D92492244002 0312 2 D9249104720000 GUIDE D92492244002 0724 1 D9249102620600 DEFLECTR D92492244002 0730 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 97 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9249107302800 CONNECTN D92492244002 0824 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 281118D74R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9299140500100 HARNESS D92997026000 0002 1 D9299702600100 EQUIPMNT D92997026000 0004 1 D9299702600200 EQUIPMNT D92997026000 0006 1 D9299702600400 EQUIPMNT D92997026000 0008 1 D9299702600500 EQUIPMNT D92997026000 0010 1 D9299702600700 EQUIPMNT D92997026000 0013 1 D9299702600800 EQUIPMNT D92997026000 0015 1 D9299145500500 HARNESS D92997026000 0017 1 D9299145600300 HARNESS D92997026000 0019 1 D9299146101100 HARNESS D92997026000 0021 1 D9299146200700 HARNESS D92997026000 0023 1 D9299146300400 HARNESS D92997026000 0025 1 D9299146400300 HARNESS D92997026000 0027 1 D9299702601500 EQUIPMNT D92997026000 0029 1 D9299147100300 HARNESS D92997026000 0031 1 D9299147200800 HARNESS D92997026000 0033 1 D9299147300200 HARNESS D92997026000 0035 1 D9299702601900 EQUIPMNT D92997026000 0037 1 D9299148001000 HARNESS D92997026000 0039 1 D9299148100200 HARNESS D92997026000 0041 1 D9299148300400 HARNESS D92997026000 0043 1 D9299149200200 HARNESS D92997026000 0045 1 D9299149300200 HARNESS D92997026000 0047 1 D9299149400200 HARNESS D92997026000 0049 1 D9299149600300 HARNESS D92997026000 0051 1 D9299702602700 EQUIPMNT D92997026000 0052 1 D9299702602800 EQUIPMNT D92997026000 0053 1 D9299702602900 EQUIPMNT D92997026000 0054 1 D9299702603000 EQUIPMNT D92997026000 0055 1 D9299702603100 EQUIPMNT D92997026000 0056 1 D9299702603200 EQUIPMNT D92997026000 0057 1 D9299702603300 EQUIPMNT D92997026000 0059 1 D9299702603400 EQUIPMNT D92997026000 0061 1 D9289471302200 PLCRDSETD92997026000 0062 1 D9299702600600 EQUIPMNT D92997026000 0063

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

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 98 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281118D78R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557176800200 PANEL D25570048004 0012 1 D2557176201000 PANEL D25570048004 0014

Kit 281118D79R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557035200800 PANEL D25570048006 0016

Kit 281118D80R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557062000800 PANEL D25570048000 0000 1 D2557031000400 PANEL D25570048000 0002

Kit 281118D81R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557166000400 PANEL D25570048002 0003 1 D2557166000500 PANEL D25570048002 0004 1 D2557166200200 PANEL D25570048002 0005 2 D2557017000200 COVER D25570048002 0010

Kit 281118D82R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 ASNA3752D120812 UNION D93070515000 0011 2 NSA855006D4 UNION D93070515000 0013 2 NSA855006-6 UNION D93070515000 0014 2 NSA855006-8 UNION D93070515000 0015 4 NSA935401-05 TIE D93070515000 0033 4 MS21042-3 NUT D93070515000 0034 2 NAS679C06 NUT D93070515000 0036 1 D3247090101000 TUBE D93070515000 0044 1 D3247091100600 TUBE D93070515000 0046 1 D2917090100400 TUBE D93070515000 0056 17 NSA5066-3-1 NUT D93070515000 0085

3 NSA935401-06 TIE D93070515000 0086 3 NSA935401-04 TIE D93070515000 0087 1 D9357072520300 BRACKET D93070515000 0108 1 NSA855006D8 UNION D93070515000 0116 2 NAS1149D0363K WASHER D93070515000 0124 4 NAS1149D0332K WASHER D93070515000 0125 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 99 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 NAS1096-3-7 SCREW D93070515000 0128 1 NSA5586D BLOCK D93070515000 0131 1 D2917091100000 TUBE D93070515000 0139 1 D3247091600200 TUBE D93070515000 0142 1 D3247090600400 TUBE D93070515000 0143 1 D3247091600000 TUBE D93070515000 0145 1 D2707023100000 TUBE D93070515000 0152 1 D2917091100200 TUBE D93070515000 0155 1 D2777000102600 TUBE D93070515000 0157 1 D2777001102400 TUBE D93070515000 0158 1 D3247090600000 TUBE D93070515000 0183 1 D3247090600600 TUBE D93070515000 0184 2 NSA855020-8 ELBOW D93070515000 0188 2 A9348225520000 BLOCK D93070515000 0190 1 D9357070820000 BRACKET D93070515000 0191 1 D9357045500000 BRACKET D93070515000 0192 1 NSA5516A06NJ CLAMP D93070515000 0194 1 NSA5516A14NJ CLAMP D93070515000 0195 3 LN9198-3210CF RIVET D93070515000 0198 6 LN9198-3210BF RIVET D93070515000 0199

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 281118D83R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827050501600 TUBE D28271200000 0002 1 D2827050501400 TUBE D28271200000 0012 1 NSA855113-11C TEE D28271200000 0021

Kit 281118D84R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9299955900200 EQUIPMNT D92999559000 0001 1 D9299955900400 EQUIPMNT D92999559000 0002 1 D9299955900600 EQUIPMNT D92999559000 0003 1 D9299955900800 EQUIPMNT D92999559000 0004 1 D9299955901000 EQUIPMNT D92999559000 0005 1 D9299955901200 EQUIPMNT D92999559000 0006 1 D9299955901400 EQUIPMNT D92999559000 0007 1 D9299955901600 EQUIPMNT D92999559000 0008 1 D9299955901800 EQUIPMNT D92999559000 0009 1 D9299955902000 EQUIPMNT D92999559000 0010 1 D9299955902200 EQUIPMNT D92999559000 0011 1 D9299955902400 EQUIPMNT D92999559000 0012 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 100 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9299062701100 HARNESS D92999559000 0014 1 D9299955902600 EQUIPMNT D92999559000 0015 1 D9299955902800 EQUIPMNT D92999559000 0016 1 D9299063400200 HARNESS D92999559000 0018 1 D9299955903000 EQUIPMNT D92999559000 0019 1 D9299082000100 HARNESS D92999559000 0021 1 D9299082400700 HARNESS D92999559000 0023 1 D9299083300100 HARNESS D92999559000 0025 1 D9289471302200 PLCRDSETD92999559000 0026

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 281118D85R02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D5347035000600 XBEAM D53470075002 0010 4 D5337217620000 SHEET D53470075002 0012 3 D5337217620100 SHEET D53470075002 0014 4 D5347449420600 FITTING D53470075002 0016 4 D5347449420700 FITTING D53470075002 0018 1 D5347449521800 SECTION D53470075002 0020 5 D5347448420200 STRAP D53470075002 0022 4 D5347448420300 STRAP D53470075002 0024 8 D5337217620800 FILLER D53470075002 0026 4 D5347449520300 SECTION D53470075002 0028 3 D5347449520200 SECTION D53470075002 0030 7 D5347449520500 SECTION D53470075002 0032 6 D5347449520400 SECTION D53470075002 0034 1 D5347470020000 ANGLE D53470075002 0036 1 D5347470020100 ANGLE D53470075002 0038 3 D5347470020400 ANGLE D53470075002 0044 2 D5347470020500 ANGLE D53470075002 0046 6 D5347470020200 ANGLE D53470075002 0048 4 D5347470020300 ANGLE D53470075002 0050 1 D5347026000600 XBEAM D53470075002 0052 2 D5347470520000 ANGLE D53470075002 0054 2 D5347470520100 ANGLE D53470075002 0056 1 D5347449523400 SECTION D53470075002 0058 1 D5347449523600 SECTION D53470075002 0060 2 D5347449522000 SECTION D53470075002 0062 2 D5347449523200 SECTION D53470075002 0064 1 D5347470320000 WEB D53470075002 0066 1 D5347470020800 ANGLE D53470075002 0068 1 D5347470021000 ANGLE D53470075002 0070 1 D5347470020600 ANGLE D53470075002 0072 1 D5347470021200 ANGLE D53470075002 0074 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 101 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5347035300600 XBEAM D53470075002 0076 1 D5337217620700 SHEET D53470075002 0078 1 D5347470420200 WEB D53470075002 0080 1 D5347470021600 ANGLE D53470075002 0082 1 D5347470021800 ANGLE D53470075002 0084 1 D5347470024800 ANGLE D53470075002 0086 1 D5347470022000 ANGLE D53470075002 0088 1 D5347470021400 ANGLE D53470075002 0090 1 D5347470022200 ANGLE D53470075002 0092 1 D5347470022400 ANGLE D53470075002 0094 1 D5347470023000 ANGLE D53470075002 0096 2 D5347470022800 ANGLE D53470075002 0098 1 D5347470022600 ANGLE D53470075002 0100 1 D5347658420000 ANGLE D53470075002 0102 1 D5347471321200 PLATE D53470075002 0104 2 D5347471500200 PLATE D53470075002 0108 1 D5347471500000 PLATE D53470075002 0110 1 D5347471500600 PLATE D53470075002 0112 1 D5347471500800 PLATE D53470075002 0114 1 D5347471501000 PLATE D53470075002 0116 2 D5347471500300 PLATE D53470075002 0118 1 D5347471500100 PLATE D53470075002 0120 1 D5347471501400 PLATE D53470075002 0122 1 D5347471501200 PLATE D53470075002 0124 1 D5347659100000 ANGLE D53470075002 0126 6 D5347470120000 ANGLE D53470075002 0128 7 D5347470120200 ANGLE D53470075002 0130 4 D5347470120100 ANGLE D53470075002 0132 5 D5347470120300 ANGLE D53470075002 0134 1 D5347066920600 SECTION D53470075002 0136 1 D5347471322400 PLATE D53470075002 0138 1 D5347471322600 PLATE D53470075002 0140 1 D5347048100600 SECTION D53470075002 0152 1 D5347047500800 SECTION D53470075002 0154 1 D5347047600800 SECTION D53470075002 0156 1 D5347646320200 DOUBLER D53470075002 0160 1 D5347646320000 DOUBLER D53470075002 0162 1 D5347470920200 COVER D53470075002 0164 2 D5347669200200 PLATE D53470075002 0166 2 D5347669000000 TUBE D53470075002 0172 2 D5347669100000 PLUG D53470075002 0174 4 D5347472120000 SHIM D53470075002 0176 4 D5347470220000 SHIM D53470075002 0178 1 D5337236320200 SHIM D53470075002 0202 4 D5347658620000 BUSHING D53470075002 0204 1 D5347063721600 SECTION D53470075002 0206 1 D5347065020400 SECTION D53470075002 0208 1 D5347048700200 PLATE D53470075002 0210 1 D5347048500400 PLATE D53470075002 0212 1 D5347048800400 PLATE D53470075002 0214 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 102 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5347048900400 PLATE D53470075002 0216 1 D5347049200400 PLATE D53470075002 0218 1 D5347046824500 ANGLE D53470075002 0220 1 D5347046824300 ANGLE D53470075002 0222 1 D5347046824600 ANGLE D53470075002 0224 2 D5347046824000 ANGLE D53470075002 0228 1 D5347046823800 ANGLE D53470075002 0230 1 D5347046823600 ANGLE D53470075002 0232 1 D5347046824200 ANGLE D53470075002 0234 1 D5347046824400 ANGLE D53470075002 0236 2 MS16625-4212 RING D53470075002 0500 10 NAS1153E7 SCREW D53470075002 0502

8 ABS0337-01A RECEPTCLD53470075002 0504 2 NAS1096-3-10 SCREW D53470075002 0506 4 NAS1791A3-1 NUT D53470075002 0508 10 NAS1474A3 NUT D53470075002 0510 28 MBBN4477-4014 RIVET D53470075002 0514 347 MBBN4477-4814 RIVET D53470075002 0549 969 LN9198-4014CF RIVET D53470075002 0614 548 LN9198-4814CF RIVET D53470075002 0648 4 DAN6-6-5X PIN D53470075002 0665 5 DAN6-6-6X PIN D53470075002 0666 13 DAN6-6-7X PIN D53470075002 0667

8 DAN6-6-8X PIN D53470075002 0668 10 DAN6-6-9X PIN D53470075002 0669

8 DAN6-6-8Y PIN D53470075002 0678 36 DIN65399-2408CF RIVET D53470075002 0724 84 DIN65399-3208CF RIVET D53470075002 0732

7 DAN5-6-4X PIN D53470075002 0764 24 DAN5-6-5X PIN D53470075002 0765 14 DAN5-6-6X PIN D53470075002 0766

9 DAN5-6-8X PIN D53470075002 0768 8 DAN5-6-8Y PIN D53470075002 0778 16 NSA5330-6 COLLAR D53470075002 0803

3 NSA5075-5 COLLAR D53470075002 0804 762 NSA5075-6 COLLAR D53470075002 0806

94 DAN11-6X COLLAR D53470075002 0807 40 NSA5075-8 COLLAR D53470075002 0808 16 DAN6-6-3 PIN D53470075002 0863 10 DAN6-6-4 PIN D53470075002 0864 45 DAN6-6-5 PIN D53470075002 0865

4 DAN6-6-6 PIN D53470075002 0866 10 DAN6-6-7 PIN D53470075002 0867 20 DAN6-6-10 PIN D53470075002 0870 NOTE (01)

3 DAN5-5-5 PIN D53470075002 0945 70 DAN5-6-3 PIN D53470075002 0963 163 DAN5-6-4 PIN D53470075002 0964 187 DAN5-6-5 PIN D53470075002 0965 126 DAN5-6-6 PIN D53470075002 0966

40 DAN5-6-7 PIN D53470075002 0967 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 103 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 71 DAN5-6-8 PIN D53470075002 0968 20 DAN5-6-10 PIN D53470075002 0970 NOTE (02) 24 DAN5-8-5 PIN D53470075002 0985

8 DAN5-8-6 PIN D53470075002 0986 8 DAN5-8-7 PIN D53470075002 0987

NOTE( 01) Alternative part to Pin DAN6-5-10, Item 970. NOTE( 02) Alternative part is Pin DAN6-6-10, Item 870. 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 281118D86R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

136 NSA5075-6 COLLAR D53470095000 0806

16 DAN6-6-3 PIN D53470095000 0863 16 DAN6-6-5 PIN D53470095000 0865 72 DAN5-6-3 PIN D53470095000 0963 32 DAN5-6-4 PIN D53470095000 0964 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 281118D87R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9299229404400 EQUIPMNT D92895832002 0010

Kit 281118D91R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827098000800 TUBE D28270975006 0005 1 D2827098001400 TUBE D28270975006 0011 1 D2827097901200 TUBE D28270975006 0013 1 D2827097901400 TUBE D28270975006 0015 1 D2827097901000 TUBE D28270975006 0016 1 D2827097901600 TUBE D28270975006 0017 1 D2827097901800 TUBE D28270975006 0019 1 D2827097902000 TUBE D28270975006 0021 1 D2827097902400 TUBE D28270975006 0025 1 D2827097904000 TUBE D28270975006 0026 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 104 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 A2163302000000 FILTER D28270975006 0027 1 A2151034520000 INLET D28270975006 0028 1 MS21902D10 UNION D28270975006 0030 1 NAS1612-10 PACKING D28270975006 0031 1 83694912 HOSE D28270975006 0040 2 A2827092300000 COUPLING D28270975006 0050 25 NAS1726C3E NUT D28270975006 0070 18 NAS1096-3-8 SCREW D28270975006 0071 27 NAS1149C0332R WASHER D28270975006 0073

2 AN924-10J NUT D28270975006 0074 2 MS21909J10 TEE D28270975006 0075 2 NAS1149F1432P WASHER D28270975006 0076 1 TSTMNR503-0 CONDUIT D28270975006 0077 4 NSA935401-03 TIE D28270975006 0078 10 MS21919WDE10 CLAMP D28270975006 0079 11 MS21919WDE4 CLAMP D28270975006 0080

8 NSA5575-8A CLAMP D28270975006 0081 4 NSA5575-2 CLAMP D28270975006 0082 7 E0090-10-125NN LEAD D28270975006 0083 4 E0090-18-100NN LEAD D28270975006 0084 4 NAS1096-1-8 SCREW D28270975006 0085 4 MS21042-06 NUT D28270975006 0087 8 NAS1303-2 BOLT D28270975006 0088 8 NAS1726-3E NUT D28270975006 0089 1 MS21908J10 ELBOW D28270975006 0091 1 AN924-4D NUT D28270975006 0092 4 NAS1726C4E NUT D28270975006 0093 2 MS21914-10D CAP D28270975006 0094 1 AN924-10J NUT D28270975006 0095 1 NAS1149C1432R WASHER D28270975006 0096 7 NAS1096-3-9 SCREW D28270975006 0097 2 NAS1096-3-12 SCREW D28270975006 0098 1 MS21905J10 TEE D28270975006 0099 1 MS21919WCH15 CLAMP D28270975006 0101 1 E0090-10-160NN LEAD D28270975006 0102 16 NAS1149F0332P WASHER D28270975006 0103

8 NAS1149FN616P WASHER D28270975006 0104 1 D2827094420000 PLACARD D28270975006 0200 1 D2827094420200 PLACARD D28270975006 0202 1 D2827094420400 PLACARD D28270975006 0204 1 D2827094420600 PLACARD D28270975006 0206 1 D2827094420800 PLACARD D28270975006 0208 1 D2827094421000 PLACARD D28270975006 0210 1 D2827094421200 PLACARD D28270975006 0212 1 D2827098002400 TUBE D28270975006 0220 1 D2827098002600 TUBE D28270975006 0222

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

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 105 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281118D92R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 6 NAS1096-3-8 SCREW D28270982006 0004 6 NAS1149C0332R WASHER D28270982006 0005 6 NAS1726C3E NUT D28270982006 0006 49 LN9198-3212BF RIVET D28270982006 0032 49 LN9198-4013BF RIVET D28270982006 0040

8 DAN7-6-8Y PIN D28270982006 0041 8 DAN12-6Y COLLAR D28270982006 0042 3 F5397461900600 BRACKET D28270982006 0100 2 D2827094222800 ANGLE D28270982006 0102 1 D2827098300000 BRACKET D28270982006 0104 1 D2827098300200 BRACKET D28270982006 0106 3 D2827094221400 ANGLE D28270982006 0112 2 D2827094220400 ANGLE D28270982006 0113 2 D2827094222200 ANGLE D28270982006 0116 2 D2827098320800 BRACKET D28270982006 0117 2 D2827098321000 BRACKET D28270982006 0118 1 D2827098321200 ANGLE D28270982006 0119 2 D2827094200400 BRACKET D28270982006 0124 1 D2827098325200 BRACKET D28270982006 0125 1 D2827098300800 BRACKET D28270982006 0126 2 D2827098323200 BRACKET D28270982006 0127 1 D2827098323000 BRACKET D28270982006 0128 1 D2827098323800 BRACKET D28270982006 0130 1 D2827093521000 BRACKET D28270982006 0131 1 D2827098324200 BRACKET D28270982006 0132 1 D2827098324400 BRACKET D28270982006 0133 1 D2827098324000 BRACKET D28270982006 0134 1 D2827098326000 BRACKET D28270982006 0135 1 D2827098326200 BRACKET D28270982006 0136 2 D2827098327600 ANGLE D28270982006 0137 1 D2827098327800 ANGLE D28270982006 0138 1 D2827098328000 ANGLE D28270982006 0139 1 D2827098328200 ANGLE D28270982006 0140

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 281118D93R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 14 NAS1096-2-7 SCREW D92891803006 0004 10 NAS1096-2-9 SCREW D92891803006 0005

5 NAS1096-2-12 SCREW D92891803006 0007 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 106 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 5 NAS1096-2-19 SCREW D92891803006 0012 2 NAS1096-2-22 SCREW D92891803006 0014 1 NAS1096-2-36 SCREW D92891803006 0020 92 NAS1096-3-9 SCREW D92891803006 0030 16 NAS1100-04-5 SCREW D92891803006 0051 12 NAS1102-08-8 SCREW D92891803006 0058 32 NAS1102-3-9 SCREW D92891803006 0099 16 NAS1149CN416R WASHER D92891803006 0150 38 NAS1149CN816R WASHER D92891803006 0152 136 NAS1149C0332R WASHER D92891803006 0153

28 NAS1149D0363K WASHER D92891803006 0161

4 ASNA0113-40ADL WASHER D92891803006 0163 8 NSA935808C01 WASHER D92891803006 0171 2 D9249102520000 WASHER D92891803006 0190 16 MS21042-04 NUT D92891803006 0200

4 MS21042-3 NUT D92891803006 0203 28 MS21042L3 NUT D92891803006 0210 27 NAS1291C3M NUT D92891803006 0218

1 NSA5110-08-1 NUT D92891803006 0225 3 NSA5066-08-1 NUT D92891803006 0230 18 NSA5067-08-1 NUT D92891803006 0236

4 E0343-01 MOUNT D92891803006 0250 7 NSA935504-01 MOUNT D92891803006 0251 1 NSA935504-02 MOUNT D92891803006 0252 2 NSA935513-01 MOUNT D92891803006 0256 10 NSA935513-05 MOUNT D92891803006 0257

1 NSA935513-07 MOUNT D92891803006 0259 7 ABS0355-01 BRACKET D92891803006 0262 11 ABS0355-02 BRACKET D92891803006 0263 11 NSA935514-03 WASHER D92891803006 0264

1 E0660-01 MOUNT D92891803006 0266 20 ABS0731A01 SUPPORT D92891803006 0267

7 ABS0774A01A BRACKET D92891803006 0268 1 NSA5527-03-02 SPACER D92891803006 0302 4 NSA5527-03-04 SPACER D92891803006 0306 1 NSA5527-03-06 SPACER D92891803006 0310 5 NSA5527-03-08 SPACER D92891803006 0314 1 NSA5527-03-11 SPACER D92891803006 0320 1 MS21919WCH6 CLAMP D92891803006 0352 6 NSA935807-09 CLAMP D92891803006 0377 2 NSA935807-16 CLAMP D92891803006 0381 1 D9249101020000 FRLDHALF D92891803006 0668 1 D9249101020200 FRLDHALF D92891803006 0669 2 D9249104800000 SHEET D92891803006 0727 1 D9249104800400 SHEET D92891803006 0729 3 D2557016200000 COVER D92891803006 0734 2.72 TSTMNR502-0 CONDUIT D92891803006 0763

16 NSA934710T14 FITTING D92891803006 0774 45 NSA935510-02 BOBBIN D92891803006 0777 15 NSA934710E20 SPRING D92891803006 0783 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 107 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 NSA934710E23 SPRING D92891803006 0784 1 NSA934710E24 SPRING D92891803006 0786 200 NSA935401-03 TIE D92891803006 0793 400 NSA935401-04 TIE D92891803006 0794 200 NSA935401-05 TIE D92891803006 0795 1 D9249107100600 STRAP D92891803006 0834 2 D9249107303000 CONNECTN D92891803006 0846 2 DAN328H25 TAPE D92891803006 0877 2 EN2997KE3C12 CAP D92891803006 0930 1 EN2997KE3C16 CAP D92891803006 0932 2 EN2997KE512 CONNECTR D92891803006 0933 1 EN2997KE516 CONNECTR D92891803006 0935 2 D9249104900600 BRACKET D92891803006 1110

Kit 281118D94R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 4 NSA5066-08-1 NUT D92492243004 0230 2 A9249199820000 PLATE D92492243004 0406 2 A9249187820200 SHEET D92492243004 0565 14 LN9198-3208BF RIVET D92492243004 0632

3 D9249104920400 BRACKET D92492243004 0737

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 281118D95R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 7 NAS1096-2-12 SCREW D92492244002 0007 1 NAS1096-2-14 SCREW D92492244002 0009 10 ASNA0113-40ADL WASHER D92492244002 0163

2 D9249102520000 WASHER D92492244002 0180 4 E0660-01 MOUNT D92492244002 0266 1 NSA5527-03-04 SPACER D92492244002 0306 1 NSA5527-03-07 SPACER D92492244002 0312 2 D9249104720000 GUIDE D92492244002 0724 1 D9249102620600 DEFLECTR D92492244002 0730 1 D9249107302800 CONNECTN D92492244002 0824 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 281118D96R01 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 108 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9299140500100 HARNESS D92997056000 0002 1 D9299702600100 EQUIPMNT D92997056000 0004 1 D9299702600200 EQUIPMNT D92997056000 0006 1 D9299702600400 EQUIPMNT D92997056000 0010 1 D9299702600500 EQUIPMNT D92997056000 0012 1 D9299702600600 EQUIPMNT D92997056000 0014 1 D9299702600700 EQUIPMNT D92997056000 0016 1 D9299702600800 EQUIPMNT D92997056000 0018 1 D9299145500500 HARNESS D92997056000 0020 1 D9299145600300 HARNESS D92997056000 0022 1 D9299705600100 EQUIPMNT D92997056000 0024 1 D9299146200700 HARNESS D92997056000 0026 1 D9299146300400 HARNESS D92997056000 0028 1 D9299146400300 HARNESS D92997056000 0030 1 D9299147000800 HARNESS D92997056000 0032 1 D9299147100600 HARNESS D92997056000 0034 1 D9299147201500 HARNESS D92997056000 0036 1 D9299147300200 HARNESS D92997056000 0038 1 D9299702601900 EQUIPMNT D92997056000 0040 1 D9299148001000 HARNESS D92997056000 0042 1 D9299148100200 HARNESS D92997056000 0044 1 D9299148300400 HARNESS D92997056000 0046 1 D9299149200600 HARNESS D92997056000 0048 1 D9299149300200 HARNESS D92997056000 0050 1 D9299149400200 HARNESS D92997056000 0052 1 D9299149600300 HARNESS D92997056000 0054 1 D9299702602700 EQUIPMNT D92997056000 0056 1 D9299702602800 EQUIPMNT D92997056000 0058 1 D9299702602900 EQUIPMNT D92997056000 0060 1 D9299702603000 EQUIPMNT D92997056000 0062 1 D9299702603100 EQUIPMNT D92997056000 0064 1 D9299702603200 EQUIPMNT D92997056000 0066 1 D9289471302200 PLCRDSETD92997056000

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. **D. L I**  **S T**  **O F**  **M A**  **T E**  **R I** **A L** **S -**  **O P**  **E R** **A T** **O R**  **S U**  **P P**  **L I**  **E D**  (1) Consumable Materials DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP MAT No. Common grease Mat. No. 04-004 As required Grease Mat. No. 04-012 As required Zinc chromate Mat. No. 05-002 As required Coating Mat. No. 07-001 As required Sealing coat Mat. No. 07-011 As required DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 109 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP MAT No. Sealant Mat. No. 08-007 As required Adhesive Mat. No. 08-010 As required Adhesive Mat. No. 08-010A As required Adhesive Mat. No. 08-048 As required Adhesive Mat. No. 08-051 As required Adhesive Mat. No. 08-053 As required Sealant, Anaerobic Mat. No. 08-623 As required Fuel Tank Sealant Polysulfide Mat. No. 09-001 As required Fuel Tank Sealant Polysulfide Mat. No. 09-002 As required Sealant Mat. No. 09-005 As required Sealant Mat. No. 09-013 As required Sealant Mat. No. 09-016 As required Sealant Mat. No. 09-018 As required Protective Coating For Fuel Vapor Mat. No. 09-032 As required Dry Cleaning Solvent Mat. No. 11-002 As required Cleaning agent Mat. No. 11-026 As required Chemical Conversion Coating Yellow Aluminum Mat. No. 13.002 As required Anti-Corrosion Primer (Polyurethane) Mat. No. 16-001 As required Anti corrosion primer Mat. No. 16-006 As required Fuel Tank Coating Mat. No. 16-015 As required Polyurethane top coat Mat. No. 16-018 As required Wash primer Mat. No. 16-020 As required Cotton cloth Mat. No. 19-003 As required Lockwire Mat. No. 19-009 As required Lockwire Mat. No. 19-010 As required Lockwire Mat. No. 19-018 As required NOTE : To accomplish this Service Bulletin it is necessary to use the expendable parts listed in the AMM 29-11-41, Page block 401. (2) Components QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 1422KID02-03 IND (01) 1 SIC5059-12-0308 Computer NOTE (01) NOTE(01) The operator must get this equipment from: SMITHS AEROSPACE ELECTRONIC SYSTEMS PO BOX 188 GL52 8SF CHELTENHAM UNITED KINGDOM **E. P A**  **R T** **S T** **O B**  **E R**  **E -** **I D**  **E N** **T I**  **F I**  **E D**  **B Y**  **T H**  **E O**  **P E**  **R A**  **T O**  **R** ITEM NEW PART No. KEYWORD ITEM OLD PART No. INT DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 110 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

D2587011905200 BLANKET D2587011903200 03 D2587012105200 BLANKET D2587012103200 03 D2587012305200 BLANKET D2587012303200 03 D2587041405000 BLANKET D2587041403000 03 D2587041605000 BLANKET D2587041603000 03 D2587041705000 BLANKET D2587041703000 03 D2587041905000 BLANKET D2587041903000 03 D2587042005000 BLANKET D2587042003000 03 D2587042105000 BLANKET D2587042103000 03 D2587042305000 BLANKET D2587042303000 03 D2587051405000 BLANKET D2587051402400 03 D2587051605000 BLANKET D2587051602200 03 D2587051705000 BLANKET D2587051702200 03 D2587051905000 BLANKET D2587051902200 03 D2587052005200 BLANKET D2587052002200 03 D2587052105200 BLANKET D2587052102200 03 D2587052305000 BLANKET D2587052302200 03 D2587041405000 BLANKET D2587041403000 03 D2587041605000 BLANKET D2587041603000 03 D2587041705000 BLANKET D2587041703000 03 D2587041905000 BLANKET D2587041903000 03 D2587042005200 BLANKET D2587042003000 03 D2587042105200 BLANKET D2587042103000 03 D2587042305000 BLANKET D2587042303000 03 D2587060105200 BLANKET D2587060102000 03 D2587060305200 BLANKET D2587060302200 03 D2587065605000 BLANKET D2587065602000 03 D2587070105200 BLANKET D2587070102000 03 D2587070305200 BLANKET D2587070302000 03 D2587071005400 BLANKET D2587071002000 03 D2587075205000 BLANKET D2587075202200 03 D2557178700400 PANEL D2557178700200 03 NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. **F. T O** **O L** **I N**  **G -**  **P R**  **I C**  **E A** **N D**  **A V** 

**A I**  **L A**  **B I**  **L I** **T Y**  ITEM PART NUMBER QTY DESCRIPTION D255-72711-004W 1 Tool for YZ-latch adjustment (ACT) NOTE : The complete tool number is D255-72711-004W6400-01. The tool can be borrowed from the Airbus assembly line. Please contact e-mail : upgrade.services@airbus.com Kit 281118T01R00 ITEM PART NUMBER QTY DESCRIPTION D28108298001 1 Stowage DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 111 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Procurement to be negotiated directly with AIRBUS. NOTE : The content of Kit 281118T01R00is necessary for the accomplishment of the SB A320-28-1119. Tag the part and put it into storage. **G. S P**  **E C**  **I A**  **L T** **O O**  **L S**  PERMASWAGE repair kit DLT series or D12000 series tools (vendor code F6087). This tool is used for the hydraulic tube installation (Kit D82). Locally manufacture or equivalent, test tools 1, 2 and test box (Refer to Figures 3, 4 and 5).

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 112 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

**3. A C** **C O**  **M P**  **L I**  **S H**  **M E**  **N T**  **I N**  **S T** **R U**  **C T** **I O**  **N S**  **A. G E**  **N E**  **R A**  **L** WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE ASSOCIATED DOORS - OR ANY COMPONENT THAT MOVES. MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS. WARNING : IF YOU GET THE HYDRAULIC FLUID ON YOUR SKIN OR IN YOUR EYES: - FLUSH IT AWAY WITH CLEAN WATER - GET MEDICAL AID. 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, CLEANING. (1) Preparation (a) Config. 01 thru Config. 02 1 Jacking the aircraft, refer to AMM 07-11-00, Page block 201. 2 Make sure that the aircraft is electrically grounded, refer to AMM 12-34-24, Page block 201. 3 Energize the aircraft electrical circuits, refer to AMM 24-41-00, Page block 201. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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4 Put the access platform(s) in position. 5 Open the passenger/crew door, refer to AMM 52-10-00, Page block 001. 6 Open the FWD/AFT cargo compartment doors, refer to AMM 52-30-00, Page block 201. NOTE : Make sure that the applicable safety equipment is installed at the cargo compartment doors. 7 Open the avionics door 822, refer to AMM 52-41-00, Page block 201. 8 Open the main landing gear doors, refer to AMM 32-12-00, Page block 201. NOTE : Make sure that the applicable safety equipment is installed at the main landing gear doors. 9 In the cockpit, remove the lining panels 211HC, 212FC, 212KC, 212KW, 212JW and 212HW, refer to AMM 06-41-53, Page block 1 and AMM 25-13-41, Page block 401. 1 0 In the forward cargo compartment, remove the panels 131AC, 131AW, 131BW, 131CW, 131DW, 132AW, 131HC, 131LC, 131MC, 131BC and 131CC, refer to AMM 06-41-53, Page block 1. 1 1 Defuel the center tank, refer to AMM 28-25-00, Page block 301. 1 2 Obey the instructions for the fuel safety procedures, refer to AMM 28-00-00, Page block 301 and AMM 28-10-00, Page block 301 and make sure of the correct ventilation of the center tank. 1 3 On the FUEL section of the HYD/FUEL Panel 40VU, make sure that all L TK PUMPS and R TK PUMPS pushbutton switches are released (the OFF legends are on). 1 4 Do the preparation procedure as specified in the removal/installation of the indicator - fuel quantity, multi tank 6QT, refer to AMM 28-42-22, Page block 401. 1 5 Remove the outlet PN D2821302620000 (Refer to IPC 28-12-05). 1 6 Do the preparation procedure as specified in the removal/installation of the galley unit (6475MM) (Refer to AMM 25-31-41, Page block 401). 1 7 Make sure that the external connector(s) is(are) not connected to the aircraft receptacle(s) EXT PW. 1 8 Make sure that there is(are) warning notice(s) on the external power receptacle to tell persons not to connect an external power source. 1 9 Make sure that the EMER EXIT LT pushbutton switch on the 25VU is set to OFF. 20 In the cockpit, on the Overhead Panel 35VU, release the BAT pushbutton switches. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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2 1 Put a warning notice in position on the Panel 35VU to tell persons not to operate the batteries. 22 Put a warning notice in position on the Refuel/Defuel Panel 800VU to tell persons not to operate the NORMAL BATTERY switch. 23 Put a warning notice in position in the cockpit to tell persons not to start the APU. 24 Put a warning notice in position in the cockpit to tell persons not to operate the fuel system. 25 Put a warning notice in position in the cockpit to tell persons not to start the ENG1, 2. 26 Depressurize the Green, Blue and Yellow hydraulic system, refer to AMM 29-10-00, Page block 201. 27 Depressurize the Green, Blue and Yellow hydraulic reservoirs, refer to AMM 29-14-00, Page block 201. 28 Put the warning notices in position to tell persons not to pressurize the hydraulic systems. 29 De-energize the aircraft electrical circuits, refer to AMM 24-41-00, Page block 201. 30 Disconnect the connectors from the batteries (2PB1, 2PB2):

a For the job set-up refer to the removal/installation of the batteries, refer to AMM 24-38-51, Page block 401. b Turn the knurled nut a quarter turn.

c Disconnect the connectors. d Put blanking caps on the disconnected electrical connectors. 3 1 Open the accessory compartment door 312AR, refer to AMM 52-41-16, Page block 201. 32 Open the maintenance door 314AR, refer to AMM 52-41-23, Page block 201. 33 Open the APU doors 315AL and 316AR, refer to AMM 52-41-00, Page block 201. 34 Remove and retain as required: - the passenger compartment seats, refer to AMM 25-21-41, Page block 401. - the passenger compartment floor covering, refer to AMM 25-28-41, Page block 401. - the passenger compartment floor panels, refer to AMM 53-22-12, Page block 401 and AMM 53-42-12, Page block 401. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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- the upper cabin sidewall panels, refer to AMM 25-23-43, Page block 401. - the lower cabin sidewall panels, refer to AMM 25-23-44, Page block 401. - the cabin ceiling panels, refer to AMM 25-23-41, Page block 401. - the cabin cove light panels, refer to AMM 25-23-48, Page block 401. - the overhead stowage compartments in the cabin, refer to AMM 25-24-41, Page block 401. - the insulation blankets, refer to AMM 25-80-00, Page block 201. - the FWD cargo compartment ceiling panel, refer to AMM 25-54-12, Page block 401. - the FWD cargo compartment sidewall panel, refer to AMM 25-54-12, Page block 401. - the FWD cargo compartment floor panel, refer to AMM 53-22-14, Page block 401. - the AFT cargo compartment sidewall panel, refer to AMM 25-55-11, Page block 401. 35 Remove and retain the aft galley unit to get access to the pressure seals 7105VP, 7106VP, 7107VP, 7108VP and 7110VP at FR70, refer to AMM 25-33-41, Page block 401. 36 Remove and retain the belly fairing panels 147FB, 148FB, 197BB, 197GB, 197LB, 198BB and 198GB, refer to AMM 53-35-11, Page block 401. (2) Standard Practices (a) Refer to the AIRBUS Standards Manual (SM) if you find part numbers for the hardware components in the related kit(s) which you can not identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. (b) If you find process and material specifications in the affected design drawings which you do not know, refer to the cross reference list in the Process and Material Specification Manual (PMS). (c) For material specifications (Mat. No.) given in this Service Bulletin, refer to the Consumable Material List (CML). (d) Tag the parts which you must remove and retain, to make the subsequent installation easier. (e) For the frame (FR) identification, refer to AMM 06-31-53, Page block 001. (f) Obey the hydraulic safety procedures, refer to AMM 29-00-00, Page block 201). DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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(g) Put blanking plugs on all disconnected line ends. (h) For installation align the tube connections and hand tighten them. Torque the tube connections to the nominal torque value when the work is finished. (i) For torque values of pipe unions, refer to AMM 20-21-12, Page block 201. (j) For connecting of hydraulic tubes with PERMASWAGE fittings, refer to AMM 20-23-11, Page block 201. (k) Torque the fasteners of the electrical components, refer to AMM 20-21-15, Page block 201. (l) Do the electrical bonding, refer to AMM 20-28-00, Page block 301 with Pure Mineral Vaseline (Mat. No. 04-012) and Electrical Bonding Coating (Blue Color) (Mat. No. 07-001). (m) For location of the access panels and partition panels, refer to AMM 06-41-53, Page block 001. (n) If necessary, clean the work area with solvent (Mat. No. 11-026) and a cloth (Mat. No. 19-003). (o) For the cleaning of the stripping area, use Solvent General Purpose (Mat. No. 11-026). (p) Remove the old sealant with a plastic spatula and clean the surface with solvent (Mat. No. 11-026). (q) Before installation of structural items apply sealant (Mat. No. 09-013) on all mating surfaces. (r) Wet install fasteners with sealant (Mat. No. 09-013). (s) When you remove fasteners you must be careful that you do not damage the holes in the structure. (t) Make sure that you have the correct edge clearance before you drill the fastener holes. (u) Transfer drill the existing holes with a pilot drill and a drill bush. (v) Drill the additional holes with a pilot drill of 2.5 mm (0.098 in.) diameter. Increase the hole diameter to the correct size for the fastener which you must install. (w) For fastener hole and drill data, refer to SRM 51-44-11. (x) For countersink of holes, refer to SRM 51-46-11, Page block 001. (y) General removal/installation procedures for fasteners, refer to SRM 51-42-11. (z) For alternative and substitute fasteners, refer to SRM 51-43-12. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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(aa) Countersink the holes (Refer to SRM 51-46-00). (ab) Cut the rivets to the necessary length. (ac) Torque standard threaded fasteners, refer to AMM 20-21-11, Page block 201. (ad) For corrosion prevention, refer to SRM 51-22-00. (ae) For coatings application, refer to SRM 51-23-00. (af) For sealing, refer to SRM 51-24-00. (ag) After drilling/re-working apply wash primer (Mat. No. 16-020), polyurethane primer (Mat. No. 16-001) and polyurethane top coat (Mat. No. 16-002) on affected areas. (ah) General removal/installation procedures for fuel pipes, refer to AMM 28-00-00, Page block 401. (ai) Before installation lubricate all O-rings with vaseline (Mat. No. 04-012). (aj) For electrical bonding of electrical connectors, refer to AMM 20-28-00, Page block 201. (ak) For electrical bonding of pipes, refer to AMM 20-28-00, Page block 201. (al) Clean the surfaces at the location of the placards with Dry Cleaning Solvent (Mat. No. 11-002). (am) For installation of placards, refer to AMM 11-00-00, Page block 201. (an) Removal/Installation of the insulation blankets, refer to AMM 25-80-00, Page block 201. (ao) Removal/Installation of the overhead stowage compartment, refer to AMM 25-24-41, Page block 401. (ap) To install new wires, cut the wires to the necessary length, crimp the terminals and connect them. (aq) Route the new wires with the wires that are in the aircraft. (ar) Put blanking caps on the disconnected electrical connectors. (as) When you install electrical connectors do a visual check of each connector which was disconnected to make sure that: - the electrical connectors are serviceable before you connect them again - the label of the connector is the same as the label on the receptacle - the connector is correctly locked with lockwire (Mat. No. 19-009), where locking facilities exists. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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(at) After installation or modification of electrical wires, do a continuity test, refer to ESPM 20-52-21. (au) Torque the fasteners of the electrical components, refer to AMM 20-21-15, Page block 201. (av) Obey the instructions for the general wiring installation, refer to ESPM 20-33-00. (aw) For the cable tie application and tooling, refer to ESPM 20-33-44 and ESPM 20-25-51. (ax) To accomplish this Service Bulletin refer also to the following: Top Drawing D0007113700000, Sheet(s) 01 Issue A00 Top Drawing D0007113700200, Sheet(s) 02 Issue B00 (ay) The drawings/kits listed in Para. 1.J. and Para. 2.C. are not in the sequence of the worksteps. The sequence can be changed by the operator as required. (az) Install grounding modules, refer to ESPM 20-44-71. (ba) Install connectors, refer to ESPM 20-44-22 and ESPM 20-44-24. **B. M O**  **D I**  **F I**  **C A**  **T I**  **O N**  (1) Config. 01 281118A00001 Sheet(s) 01 A00 281118A00001 Sheet(s) 02 A00 281118A00001 Sheet(s) 03 A00 281118A00001 Sheet(s) 04 A00 281118A00001 Sheet(s) 05 A00 281118A03000 Sheet(s) 01 A00 281118A04000 Sheet(s) 01 A00 281118A06000 Sheet(s) 01 A00 281118A09000 Sheet(s) 01 A00 281118A11000 Sheet(s) 01 A00 (a) Install the doublers on the upper surface panels Refer to Kit 281118A01R03 281118A01001 Sheet(s) 01 A00 281118A01001 Sheet(s) 02 A00 NOTE : Remove the finch paint and the paint protection from the extrados panel between Y=+254 and Y=-254 and between FR36 and FR42. Do not use a metallic tool. Do not cause damage to the head of the rivet, (Refer to SRM 51-75-11, Paragraph 3). Stop the removal when you can see the primary protection (green color). Only remove rivets at location of the doubler.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 119 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Drill one hole to a diameter of 64 mm (2.519 in.) and one hole to a diameter of 74 mm (2.913 in.), (Refer to drawing 281118A01001, Sheets 01 and 02). 1 Loft D5713032000095 2 Install : 281118A01001 Sheet(s) 03 B00 Item 0 1 Doubler D5713304820004

Item 1 1 Doubler D5713031920000

with : Fuel Tank Sealant Polysulfide (Mat. No. 09-002) Attach with : Item 10 19 Bolt EN6115V3-3 Item 11 15 Bolt EN6115V3-4 Item 12 15 Bolt EN6115V3-5 Item 13 29 Pin-Hi Lok NSA5357-3-6 Item 14 12 Pin-Hi Lok NSA5357-3-7 Item 15 16 Pin-Hi Lok NSA5357-3-5 Item 22 8 Pin-Hi Lok NSA5357-4-7

Item 23 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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5 Pin-Hi Lok NSA5357-4-8

Item 30 57 Collar NSA5330-6 Item 35 49 Nut ASNA2528-3 Item 40 13 Collar NSA5330-8 3 Install : 281118A01002 Sheet(s) 01 A00 Item 0 1 Bracket Assy D5791332400000

Item 1 1 Bracket Assy D5791332300000

Attach with : Item 10 2 Bolt EN6115V3-5

Item 11 4 Nut ASNA2528-3

Item 12 2 Bolt EN6115V3-7 (b) Install the brackets on the upper surface panels Refer to Kit 281118A01R03 281118A01003 Sheet(s) 01 A00 281118A01003 Sheet(s) 02 A00 281118A01003 Sheet(s) 03 A00 281118A01003 Sheet(s) 04 B00 NOTE : To install the brackets, put them in position and counter-drill with the existing holes on aircraft. Item 1 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 Support Assy D5791049500095 Item 2 1 Support Assy D5791049400095 Item 3 1 Fitting D5791048300095 Item 4 1 Fitting D5791048200095 Item 5 1 Fitting D5791042020095 Item 6 1 Fitting D5791042120095 Item 9 1 Fitting D5791043020095 Item 10 1 Fitting D5791049820095 Item 11 1 Fitting D5791050020095 Item 12 1 Support D5791042320095 Item 13 1 Support D5791042220095 Item 21

2 Corner Plate A2823301800202 Attach with : Item 20 Fuel Tank Sealant Polysulfide (Mat. No. 09-002) Item 22 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 122 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

4 Rivet ASNA2050DCJ3215 Item 100

6 Pin-Hi Lok NSA5357-3-5 Item 102

8 Pin-Hi Lok NSA5357-3-7 Item 103

4 Pin-Hi Lok NSA5357-3-8 Item 104

4 Pin-Hi Lok NSA5357-3-10 Item 107

4 Pin-Hi Lok NSA5357-4-7 Item 108

8 Pin-Hi Lok NSA5357-4-8 Item 109

2 Pin-Hi Lok NSA5357-4-9 Item 110

4 Pin-Hi Lok NSA5357-4-10 Item 120

22 Collar NSA5330-6 Item 130

18 Collar NSA5330-8 (c) Install the rod on the upper surface panels Refer to Kit 281118A01R03 281118A01004 Sheet(s) 01 A00 Item 0 1 Rod D2821334100000 Item 4 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 123 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Bracket D2821334220000 Attach with : Item 12

4 Bolt NAS6603-4 Item 14

2 Bolt NAS6604-9 Item 20

4 Nut NSA5050-3 Item 22

2 Nut NSA5050-4 Item 24

4 Washer ASNA2397-10L Item 26

2 Washer ASNA2397-416L (d) Install the bracket on FR42 Refer to Kit 281118A02R03 281118A02001 Sheet(s) 01 A00 NOTE : Remove the finch paint and the paint protection in the center tank. Do not use a metallic tool. Do not cause damage to the head of the rivet, (Refer to SRM 51-75-11, Paragraph 3). Stop the removal when you can see the primary protection (green color). Only remove rivets at location of the doubler. Item 12 1 Corner Plate A2823301800202 Attach with : Item 32

2 Rivet ASNA2050DCJ3215 (e) Install the bracket above FR42 Refer to Kit 281118A02R03 281118A02002 Sheet(s) 01 A00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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DESIGN DRAWINGS SHEET(S) 281118A02002 Sheet(s) 02 A00 281118A02002 Sheet(s) 03 B00 Item 0 1 Machined Bracket D5791041820095 Attach with : Item 10 Fuel Tank Sealant Polysulfide (Mat. No. 09-002) Item 60

2 Pin-Hi Lok NSA5357-4-11 Item 65

2 Pin-Hi Lok NSA5357-5-13 Item 75

2 Collar NSA5330-8 Item 80

2 Collar NSA5330-10 (f) Install the brackets on the lower surface panels Refer to Kit 281118A02R03 281118A02003 Sheet(s) 01 A00 281118A02003 Sheet(s) 02 A00 281118A02003 Sheet(s) 03 B00 NOTE : To install the brackets, put them in position and counter-drill with the existing holes on aircraft. Item 1 1 Machined Bracket D5791040320095 Item 2 1 Support Assy D5791040500095 Item 3 1 Support Assy D5791040400095 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Item 4 1 Machined Bracket D5791040120095 Item 5 1 Machined Bracket D5791040020095 Item 6 1 Machined Bracket D5791040220095 Item 7 1 Machined Bracket D5791040820095 Item 8 1 Machined Bracket D5791040920095 Item 9 1 Machined Bracket D5791040620095 Item 10 1 Machined Bracket D5791040720095 Item 11 1 Machined Bracket D5791041020096 Attach with : Item 20 Fuel Tank Sealant Polysulfide (Mat. No. 09-002) Item 44

4 Bolt NAS6603-4 Item 62

4 Nut NSA5050-3 Item 157

8 Pin-Hi Lok NSA5357-4-9 Item 158

5 Pin-Hi Lok NSA5357-4-10 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Item 159

17 Pin-Hi Lok NSA5357-4-11 Item 160 1 Pin-Hi Lok NSA5357-4-12 Item 162 1 Pin-Hi Lok NSA5357-5-13 Item 165

31 Collar NSA5330-8 Item 170 1 Collar NSA5330-10 (g) Install the rod and the plate on the lower surface panels Refer to Kit 281118A02R03 281118A02004 Sheet(s) 01 A00 281118A02004 Sheet(s) 02 A00 Item 2 1 Rod D2821334100200 Item 6 1 Bracket D2821040220000 Item 8 1 Bracket D2821040120000 Attach with : Item 10

8 Bolt NAS6603-2 Item 12

4 Bolt NAS6603-4 Item 14

2 Bolt NAS6604-9 Item 20 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 127 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

4 Nut NSA5050-3 Item 22

2 Nut NSA5050-4 Item 24

12 Washer ASNA2397-10L Item 26

2 Washer ASNA2397-416L (h) Install the Additional Center Tank (ACT) door Refer to Kit 281118A03R01 1 Remove : 281118A03001 Sheet(s) 01 B00 Item (1) 1 Door Assy D5713019400200

Item (4) 1 Screw Discard

Item (8) 1 Washer Discard

Item (5) 15 Washer Discard Item (6) 15 Screw Discard Item (7) 15 Washer Discard 2 Install : 281118A03002 Sheet(s) 01 A00 281118A03002 Sheet(s) 02 A00 1 Door Assy D5713323000000

Item 0 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 128 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Fairing D5713334000000

Item 1 1 Intrados Fitting D5713334600000

Item 2 1 Fitting D5713334500000

Item 3 1 Fitting D5713334400000

Attach with : Item 6 8 Washer A5713052120300

Item 10 3 Bolt NAS6603-2

Item 11 15 Bolt ABS0114V4-18 Items 15 and 36 4 Washer ASNA2397D10L

Item 16 15 Washer MS20002C4 Item 20 1 Bolt NAS6603-3

Item 22 6 Bolt NAS6604-3

Item 40 6 Washer ASNA2397D416L (i) Install the equipment on the ACT door Refer to Kit 281118A03R01 and Kit 281118A15R00 281118A03003 Sheet(s) 01 A00 281118A03003 Sheet(s) 02 A00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 129 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281118A03003 Sheet(s) 03 B00 281118A03003 Sheet(s) 04 A00 281118A03003 Sheet(s) 05 A00 1 Install the pressure switch 2QH : 281118A03003 Sheet(s) 02 A00 Item 0 1 Pressure Switch HTE690045

Attach with : Item 30 Zinc Chromate General Purpose (Mat. No. 05-002) Item 8 1 Bulkhead D2821067800000

Item 10 1 Plug A2823260820000

Item 12 1 Safety Valve A2823260500000

Item 18 3 Packing NSA8200-6

Item 20 1 O-Ring NSA8203-019

Item 22 4 Bolt NAS6603-5

Item 24 4 Washer ASNA2055-03

Item 26 4 Nut NSA5050-3

Item 28 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 130 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 M Lockwire MS20995C32 2 Install the fuel pump 1QH and the mounting plate 163QM : 281118A03003 Sheet(s) 03 B00 Item 0 1 Fuel Pump 568-1-27170-002

Item 2 1 Mounting Plate 568-1-27171-002

Attach with : Item 50 Grease High Pressure (Mat. No. 04-004) Item 10 1 Pin A2821064820040

Item 12 1 Insert A2821064620000

Item 14 1 Spring A2821064720000

Item 18 1 O-Ring NSA8203-113

Item 22 1 O-Ring NSA8203-167

Item 24 1 O-Ring NSA8203-224

Item 26 1 O-Ring NSA8203-226

Item 28 2 Bonding Lead E0088-10-100

Item 29 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 131 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

4 Bolt NAS6603-1

Item 30 6 Bolt NAS6604-7

Item 32 1 Bolt NAS6604-20

Item 34 1 Seal Washer NSA5112-04

Item 36 6 Washer ASNA2397-416

Item 38 1 Washer ASNA2397-416L

Item 39 4 Washer ASNA2397D10L

Item 40 1 Nut NSA5050-4

Item 42 2 Nut NSA5050-3

Item 48 Wire-Lock MS20995C32 3 Install the refuel valve 41QU and the canister 164QM : 281118A03003 Sheet(s) 04 A00 Item 0 1 Canister-Valve,Refuel 1158000-15

Item 2 1 Refuel Valve 1158000-21

Attach with : Item 20 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 132 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Zinc Chromate General Purpose (Mat. No. 05-002) Item 6 1 O-Ring NSA8203-245

Item 8 4 Screw NAS1154-10

Item 10 1 Screw NAS1801-06-8

Item 11 1 Screw NAS1801-3-6

Item 12 1 Washer ASNA2397-6L

Item 13 1 Washer ASNA2397-10L

Item 14 1 Nut MS21042-06

Item 16 4 Nut NAS1726C4E

Item 22 1 Bonding Lead E0088-16-125 4 Install the actuator 6QH and the valve 165QM : 281118A03003 Sheet(s) 05 A00 Item 0 1 Valve HTE900135

Item 2 1 Actuator HTE190001-2

Attach with : Item 20 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 133 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Zinc Chromate General Purpose (Mat. No. 05-002) Item 4 1 Clamp-V HTE8002

Item 6 1 O-Ring NSA8203-154

Item 8 6 Screw NAS1153-4

Item 13 1 Bolt NAS6603-1

Item 16 4 Nut NAS1726C4E

Item 18 1 Nut NSA5050-3

Item 22 1 Bonding Lead E0088-10-100

Item 24 Wire-Lock MS20995C32 5 Install the placards on the ACT door 281118A15001 Sheet(s) 01 A00 Item 0 1 Placard D2821336920000

Item 2 1 Placard D2821336920200

Item 4 1 Placard D2821336920400

Item 6 1 Placard D2821336920600 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 134 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 8 1 Placard D2821336920800

NOTE : Use Zinc Chromate General Purpose (Mat. No. 05-002), Anti-Corrosion Primer (Polyurethane) (Mat. No. 16-001) and Grease High Pressure (Mat. No. 04-004). (j) Replace the fuel quantity indicator 6QT (Refer to AMM 28-42-22, Page block 401) Refer to Kit 281118A03R01 1 Remove : 1 Fuel Quantity Indicator 1407KID02-03 2 Install : 1 Indicator-Fuel,Quantity 1422KID02-03 (k) Modify the pipes in the center tank Refer to Kit 281118A04R05 1 Remove : 281118A04001 Sheet(s) 01 A00 281118A04001 Sheet(s) 02 A00 281118A04001 Sheet(s) 03 A00 Item (2) 1 Pipe Assy D2821008001300

with : Item (5) 2 O-Ring Discard

Items (4) and (9) 2 Screw Retain

Items (8) and (10) 2 Washer Retain 2 Install : 281118A04002 Sheet(s) 01 A00 281118A04002 Sheet(s) 02 A00 281118A04002 Sheet(s) 03 A00 281118A04002 Sheet(s) 04 A00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 135 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 6 1 Pipe Assy D2821333900000

Item 120 1 Machined Tee D2821331020000

Item 12 1 Pipe Assy D2821333900100

Item 5 4 O-Ring NSA8203-226

Attach with : Item 16 2 Bolt NAS6603-2

Item 18 2 Nut NAS1726-3E

Item 110 4 Bolt NAS6604-5

Item 112 4 Washer ASNA2397-416L

Item 114 4 Nut NAS1726-4E

Items (4) and (9) 2 Screw

Items (8) and (10) 2 Washer (l) Install the ACT pipes in the center tank Refer to Kit 281118A04R05 1 Install : 281118A04003 Sheet(s) 01 A00 281118A04003 Sheet(s) 02 A00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 136 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281118A04003 Sheet(s) 03 A00 281118A04003 Sheet(s) 04 A00 281118A04003 Sheet(s) 05 A00 281118A04003 Sheet(s) 06 B00 281118A04003 Sheet(s) 07 B00 Item 20 1 Pipe Assy D2821333900900

Item 22 1 Pipe Assy D2821333900300

Item 24 1 Pipe Assy D2821333900400

Item 28 1 Pipe Assy D2821333900600

Item 30 1 Pipe Assy D2821333900700

Item 32 1 Pipe Assy D2821333901000

Item 34 1 Sleeve A2821038600000

Item 36 1 Sleeve D2821333800000

Item 38 1 Pipe D2821334800000

Item 40 1 Pipe D2821334900000

Item 42 1 Pipe Assy D2821335000000

Item 44 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 137 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Pipe Assy D2821335100000

NOTE : If you install the pipe assy D2821338500000 as an alternative to the pipe assy D2821335100000, apply Chemical Conversion Coating Yellow Aluminum (Mat. No. 13-002). Item 46 1 Pipe D2821335800200

Item 50 1 Restrictor D2821336720240

Attach with : Item 51 1 Clamp NSA5516-04ND

Item 52 1 Union MS21902D4

Item 55 2 Nut ABS0107-150

Item 56 3 Nut ABS0107-200

Item 57 2 Ring-Retaining NSA840003-150

Item 58 3 Ring-Retaining NSA840003-200

Item 60 1 Packing NSA8200-4

Item 62 1 O-Ring NSA8203-215

Item 64 12 O-Ring NSA8203-222 Item 66 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 138 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

5 O-Ring NSA8203-226

Item 68 2 Screw NAS1801-06-10

Item 70 14 Bolt NAS6603-2 Item 72 4 Bolt NAS6603-4

Item 73 4 Bolt NAS6603-5

Item 74 4 Bolt NAS6603-7

Item 76 2 Bolt NAS6604-2

Item 77 4 Bolt NAS6604-3

Item 78 2 Nut MS21042L06

Item 80 18 Nut NSA5050-3 Item 82 6 Nut NSA5050-4

Item 83 2 Washer ASNA2397-6L

Item 84 8 Washer ASNA2397-10L

Item 90 1 Bonding Lead E0088-10-160 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 139 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 92 2 Bonding Lead E0088-10-200

Item 93 1 Bonding Lead E0088-10-280 2 Install : 281118A04004 Sheet(s) 01 A00 Item 0 1 Machined Tee D2821331620000

Attach with : Item 10 6 Bolt NAS6604-5

Item 12 6 Washer ASNA2397-416L

Item 14 6 Nut NAS1726-4E 3 Install : 281118A04005 Sheet(s) 01 A00 Item 0 1 Machined Elbow D2821332220000

Attach with : Item 10 2 Bolt NAS6604-4

Item 12 2 Washer ASNA2397-416L

Item 14 2 Nut NAS1726-4E

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 140 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

4 Install : 281118A04006 Sheet(s) 01 A00 Item 0 1 Elbow Moulded A2821120120000

Attach with : Item 10 2 Bolt NAS6604-4

Item 12 2 Washer ASNA2397-416L

Item 14 2 Nut NAS1726-4E 5 Install : 281118A04007 Sheet(s) 01 A00 Item 0 1 Machined Elbow D2821338720000

Attach with : Item 10 2 Bolt NAS6604-5

Item 12 2 Washer ASNA2397-416L

Item 14 2 Nut NAS1726-4E 6 Install : 281118A04008 Sheet(s) 01 A00 Item 0 1 Elbow Assy D2821339020095

Attach with : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 141 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 8 1 O-Ring NSA8203-226

Item 10 4 Bolt NAS6603-4

Item 12 4 Washer ASNA2397D10L 7 Install : 281118A04009 Sheet(s) 01 A00 Item 0 1 Machined Elbow D2821333220000

Item 2 1 Machined Elbow D2821333420000

Item 4 1 Restrictor D2821336621240

Attach with : Item 8 2 O-Ring NSA8203-222

Item 10 8 Bolt NAS6603-3

Item 12 8 Washer ASNA2397-10L 8 Install : 281118A04010 Sheet(s) 01 A00 Item 0 1 Valve 9843144M

Item 1 1 Flange A2821079520000 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 142 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 2 1 Restrictor D2821335621800

Attach with : Item 20 Fuel Tank Sealant Polysulfide (Mat. No. 09-002) Item 3 1 Nut ABS0107-200

Item 4 1 Ring-Retaining NSA840003-200

Item 5 3 O-Ring NSA8203-226

Item 8 4 Bolt NAS6604-12

Item 9 4 Nut NAS1726-4E

Item 11 2 Bonding Lead E0088-10-100

Item 12 2 Nut NAS1726-3E

Item 13 1 Bolt NAS6603-2

Item 14 1 Bolt NAS6603-1

Item 17 1 Bonding Lead E0088-10-200

Item 19 2 Washer ASNA2397-10L DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 143 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

9 Install : 281118A04011 Sheet(s) 01 A00 281118A04011 Sheet(s) 02 A00 Item 54 1 Valve 365A02

Item 35 1 Sleeve Assy D2821336300000

Attach with : Item 55 2 Nut ABS0107-150

Item 57 2 Ring-Retaining NSA840003-150

Item 61 1 Packing NSA8200-5

Item 64 2 O-Ring NSA8203-222

Item 70 2 Bolt NAS6603-2

Item 80 2 Nut NSA5050-3 1 0 Install : 281118A04012 Sheet(s) 01 A00 Item 0 1 Tee D2821331320000

Attach with : Item 10 4 Bolt NAS6604-5 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 144 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 12 4 Washer ASNA2397-416L

Item 14 4 Nut NAS1726-4E 1 1 Install : 281118A04013 Sheet(s) 01 B00 Item 0 1 Machined Elbow D2821331920000

Item 2 1 Sleeve D2821336500000

Attach with : Item 8 2 O-Ring NSA8203-222

Item 10 4 Bolt NAS6603-7

Item 12 4 Washer ASNA2397-416L (m) Install the transfert elbow Refer to Kit 281118A05R01 281118A05001 Sheet(s) 01 A00 Item 0 1 Transfert Elbow Assy D2821330700000 Item 2 1 Nutplate Assy D2821334700000 Item 4 1 Nutplate Assy D2821337500000 Item 8 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 145 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 O-Ring NSA8203-148 Attach with : Item 10

6 Bolt NAS6604-9 Item 12

6 Washer ASNA2397-416L Item 14 1 Bolt NAS6603-2 Item 16 1 Washer ASNA2397-10L (n) Install the air ventilation elbow Refer to Kit 281118A05R01 281118A05002 Sheet(s) 01 A00 Item 0 1 Elbow Assy D2821337700041 Item 2 1 Nutplate Assy D2821334600000 Item 4 1 Nutplate Assy D2821337600000 Item 14 1 Filter D2821337800000 Item 16 1 Plate D2821337120000 Item 8 1 O-Ring NSA8203-152 Attach with : Item 10 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 146 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

6 Bolt NAS6604-8 Item 12

6 Washer ASNA2397-416L Item 18

4 Bolt NAS6603-2 Item 20

2 Bolt NAS6603-5 Item 22

5 Washer ASNA2397JD10L Item 24

2 Nut NSA5050-3 Item 26 1 Washer ASNA2397-10L (o) Apply the sealing protection to the center tank Refer to Kit 281118A05R01 281118A05003 Sheet(s) 01 A00 281118A05003 Sheet(s) 02 A00 1 After the installation of the doublers and attachments, apply the sealing protection between FR36 and FR42, on the upper and lower surface panels, with : - Fuel Tank Sealant Polysulfide (Mat. No. 09-001) - Fuel Tank Sealant Polysulfide (Mat. No. 09-002) - Protective Coating For Fuel Vapor (Mat. No. 09-032) - Anti-Corrosion Primer (Polyurethane) (Mat. No. 16-001) - Fuel Tank Coating (Mat. No. 16-015). (p) Install the marking on the belly fairing Refer to Kit 281118A16R00 281118A16002 Sheet(s) 01 A00 1 Clean the surfaces of the placards to which you will apply the adhesive with Solvent General Purpose (Mat. No. 11-026) and Lint-Free Cotton Cloth (Mat. No. 19-003). DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 147 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 Install : 2 placards D1121004600000 Item 0 2 placards D1121009100000 Item 1 1 placard D0041109120000 Item 2 (q) Modify the equipment in the HYD/Fuel Panel 40VU Refer to Kit 281118A06R01, Kit 281118A07R00, Kit 281118A08R01 and Kit 281118A09R01 1 Remove : 281118A06002 Sheet(s) 01 B00 Item (35) FIN 14LF 1 Plate-Integrally Lighted 002098-05

Item (0) 1 Plate-Front D9251092000000 2 Install : 281118A06001 Sheet(s) 01 A00 281118A06002 Sheet(s) 02 A00 FIN 24QH 1 Switch-Pushbutton E0415C3LM078E

with : 1 Sleeve E0416-02 2 Screw NAS1102-04-6 1 Connector E0417C01S

Item 0 1 Plate Front D9251314900000

FIN 14LF 1 Plate-Integrally Lighted D33110194A00

Item 4 1 Placard D1131043320100

Item 6 1 Placard D1131043320200 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 148 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

NOTE : On the new front plate, near the new item of equipment and the items that you installed again, bond the placards, supplied in : Placard Set D9100095112695 NOTE : Safety the screws with Sealant, Anaerobic (Mat. No. 08-623) NOTE : For the modification of the wiring, refer to paragraph ACCOMPLISHMENT INSTRUCTIONS B. (1) (y). (r) Modify the equipment in the Rear C/B Panel 121VU Refer to Kit 281118A06R01 and Kit 281118A09R01 1 Remove : 281118A09001 Sheet(s) 01 A00 FIN 32LM 1 Placard D11310817B00

FIN 33LM 1 Placard 002051-09

FIN 34LM 1 Placard D11310779A00

FIN 35LM 1 Placard D11310814A00

FIN 36LM 1 Placard 002048-23 2 Install : 281118A06003 Sheet(s) 01 B00 281118A09001 Sheet(s) 01 A00 FIN 9QH 1 Circuit Breaker NSA931320-050

in position P29 FIN 25QH 1 Circuit Breaker NSA931322-100

in position Q29 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 149 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

FIN 30QH 1 Circuit Breaker NSA931320-030

in position N29 FIN 33QU 1 Circuit Breaker NSA931320-050

in position L29 FIN 51QJ 1 Circuit Breaker NSA931320-030

in position M29 FIN 52QJ 1 Circuit Breaker NSA931320-030

in position M28 with 16 Screw E0736N08-01 16 Washer-Locking ASNA2553-0401

6 Clamp-Locking NSA931305-01

FIN 32LM 1 Placard D00410444A00

FIN 33LM 1 Placard D00410428A00

FIN 34LM 1 Placard D11311000A00

FIN 35LM 1 Placard D00410426A00

FIN 36LM 1 Placard D11311010A00

NOTE : Near the new circuit breaker, bond the placards, supplied in : Placard Set D9100095112695 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 150 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(s) Modify the wiring in the Rear C/B Panel 121VU Refer to Kit 281118A06R01 281118A06501 Sheet(s) 01 A00 281118A06501 Sheet(s) 02 A00 281118A06502 Sheet(s) 01 A00 281118A06502 Sheet(s) 02 A00 281118A06503 Sheet(s) 01 A00 281118A06503 Sheet(s) 02 A00 281118A06504 Sheet(s) 01 A00 281118A06504 Sheet(s) 02 A00 281118A06505 Sheet(s) 01 A00 281118A06505 Sheet(s) 02 A00 281118A06506 Sheet(s) 01 A00 281118A06506 Sheet(s) 02 A00 281118A06507 Sheet(s) 01 A00 281118A06507 Sheet(s) 02 A00 281118A06508 Sheet(s) 01 A00 281118A06508 Sheet(s) 02 A00 281118A06509 Sheet(s) 01 A00 281118A06509 Sheet(s) 02 A00 281118A06510 Sheet(s) 01 A00 281118A06510 Sheet(s) 02 A00 281118A06511 Sheet(s) 01 A00 281118A06511 Sheet(s) 02 A00 1 Remove the wires : 281118A06501 Sheet(s) 02 A00 281118A06503 Sheet(s) 02 A00 281118A06505 Sheet(s) 02 A00 281118A06508 Sheet(s) 02 A00 281118A06510 Sheet(s) 02 A00 2 Install the wires : 281118A06502 Sheet(s) 02 A00 281118A06504 Sheet(s) 02 A00 281118A06506 Sheet(s) 02 A00 281118A06507 Sheet(s) 02 A00 281118A06509 Sheet(s) 02 A00 281118A06511 Sheet(s) 02 A00, supplied in : Bundle D9000095128395 3 Attach the wires with : 150 Tie-Cable NSA935401-03 150 Tie-Cable NSA935401-06 (t) Install the routing of the Relay Box 802VU between FR4 and FR5, in the avionics compartment Refer to Kit 281118A10R02

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 151 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Remove : 281118A10001 Sheet(s) 01 A00 Item (0) 2 Pin Discard 2 Install : 281118A10001 Sheet(s) 02 A00 Item 1 2 Mount E0661-22

Item 2 2 Stud E0420-04 3 Install : 281118A10002 Sheet(s) 01 A00 Item 1 1 Bracket D9241244120000

Item 4 2 Mount NSA935504-01

Attach with : Item 18 2 Rivet ASNA2051DCJ3215

Item 2 1 Spacer NSA5527-03-01

Item 3 1 Screw NAS1801-3-20

Item 5 1 Nut NAS1726-3E 4 Install : 281118A10003 Sheet(s) 01 B00 281118A10003 Sheet(s) 02 B00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 152 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

5 Install : 281118A10004 Sheet(s) 01 A00 281118A10004 Sheet(s) 02 A00 Item 0 1 Mount NSA935504-03

Item 2 2 Mount NSA935504-01

Attach with : Item 4 3 Screw NAS1801-3-8

Item 6 3 Washer ASNA2397-10L Placard Set D9100095112795 6 Install : 281118A10005 Sheet(s) 01 A00 281118A10005 Sheet(s) 02 A00 Item 10 5 Screw NAS1801-3-9

Item 11 5 Washer ASNA2397-10L

Item 14 5 Nut NAS1726-3E

FIN 4065VC-A 1 Connector E0052R20B41SNF 1 Backshell E0080-01-20C

FIN 4066VC-A 1 Connector E0052R14B19SNF 1 Backshell E0080-01-14C Placard Set D9100095112795 10 M Conduit E0432A12 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 153 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(u) Install the connector 1982VC between FR33 and FR34 Refer to Kit 281118A10R02 281118A10006 Sheet(s) 01 A00 1 Connector EN3545E03FXB24A 1 Backshell EN3545-007SCD Placard Set D9100095112795 (v) Modify the equipment in the AFT Electronics Rack 80VU Refer to Kit 281118A10R02 1 On the Shelf 85VU

a On the mounting rail of the terminal block 1853VT, install : 1 Module NSA937901MA2206 in position 28 1 Module NSA937901MA2204 in position 62 2 Module Identification NSA937901E2 1 Module Identification NSA937901E6 1 Module Identification NSA937901E8 (w) Modify the equipment in the Relay Box 103VU Refer to Kit 281118A10R02 281118A10007 Sheet(s) 01 A00 281118A10007 Sheet(s) 02 A00 1 Install : FIN 50QJ 1 Relay E0245-28A0 1 Base E0250A0S

Item 6 2 Nut MS21042L04

in position A77 Placard Set D9100095112795 (x) Modify the equipment in the Contactor Box 107VU Refer to Kit 281118A10R02

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 154 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Install : 281118A10008 Sheet(s) 01 A00 281118A10008 Sheet(s) 02 A00 FIN 26QH 1 Relay NSA932843AA01 1 Base NSA932844AA

Item 8 3 Screw NAS1100-04-7

Item 4 3 Washer ASNA2397-4L

Item 6 3 Nut MS21042L04

in position B7 FIN 1274VC 1 Connector EN3545D03MXB22A

FIN 1274VC-A 1 Connector EN3545D03FXA22A 2 Backshell EN3545-007SCD Placard Set D9100095112795 2 On the mounting rail of terminal block 1176VT, install : 1 Module NSA937901MA2008 1 Module Identification NSA937901E0 1 Module Identification NSA937901E1

in position 10. (y) Modify the wiring in the aircraft Refer to Kit 281118A10R02 281118A10501 Sheet(s) 01 A00 281118A10501 Sheet(s) 02 A00 281118A10502 Sheet(s) 01 A00 281118A10502 Sheet(s) 02 A00 281118A10502 Sheet(s) 03 A00 281118A10503 Sheet(s) 01 A00 281118A10503 Sheet(s) 02 A00 281118A10504 Sheet(s) 01 A00 281118A10504 Sheet(s) 02 A00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 155 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281118A10505 Sheet(s) 01 B00 281118A10505 Sheet(s) 02 B00 281118A10506 Sheet(s) 01 A00 281118A10506 Sheet(s) 02 A00 281118A10507 Sheet(s) 01 A00 281118A10507 Sheet(s) 02 A00 281118A10507 Sheet(s) 03 A00 281118A10508 Sheet(s) 01 A00 281118A10508 Sheet(s) 02 A00 281118A10509 Sheet(s) 01 B00 281118A10509 Sheet(s) 02 A00 281118A10510 Sheet(s) 01 B00 281118A10510 Sheet(s) 02 B00 281118A10511 Sheet(s) 01 A00 281118A10511 Sheet(s) 02 B00 281118A10512 Sheet(s) 01 A00 281118A10512 Sheet(s) 02 A00 281118A10513 Sheet(s) 01 A00 281118A10513 Sheet(s) 02 A00 281118A10514 Sheet(s) 01 A00 281118A10514 Sheet(s) 02 A00 281118A10515 Sheet(s) 01 A00 281118A10515 Sheet(s) 02 A00 281118A10516 Sheet(s) 01 A00 281118A10516 Sheet(s) 02 A00 281118A10517 Sheet(s) 01 A00 281118A10517 Sheet(s) 02 A00 281118A10518 Sheet(s) 01 A00 281118A10518 Sheet(s) 02 A00 281118A10519 Sheet(s) 01 A00 281118A10519 Sheet(s) 02 A00 281118A10520 Sheet(s) 01 A00 281118A10520 Sheet(s) 02 A00 281118A10521 Sheet(s) 01 B00 281118A10521 Sheet(s) 02 A00 1 Remove the Shelf 92VU

a From the Shelf 92VU, remove for access the computers 7QJ, 9QJ, 3QT and 1XG : (Refer to AMM 24-41-34, Page block 401) (Refer to AMM 28-42-34, Page block 401) (Refer to AMM 28-46-34, Page block 401) 1 FLSCU1 Retain 1 FLSCU2 Retain 1 FQIC Retain 1 GPCU Retain NOTE : You must install these computers again after the modification of the wiring. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 156 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

b Disconnect the bonding braid.

c Remove the attachment hardware from the Shelf 92VU. NOTE : Retain the hardware. d Remove the Shelf 92VU and install it on bench. 2 Remove the Shelf 93VU

a From the Shelf 93VU, remove for access the computers 1CE3, 5GA1 and 8HK : (Refer to AMM 21-63-34, Page block 401) (Refer to AMM 27-94-34, Page block 401) (Refer to AMM 32-31-71, Page block 401) 1 SEC3 Retain 1 LGCIU1 Retain 1 ZONE CONT Retain NOTE : You must install these computers again after the modification of the wiring. b Disconnect the bonding braid.

c Remove the attachment hardware from the Shelf 93VU. NOTE : Retain the hardware. d Remove the Shelf 93VU and install it on bench. 3 Remove the Shelf 94VU

a From the Shelf 94VU, remove for access the computers 5GA2, 10GG and 10WQ : (Refer to AMM 26-17-34, Page block 401) (Refer to AMM 32-31-71, Page block 401) (Refer to AMM 32-42-34, Page block 401) 1 LGCIU2 Retain 1 BSCU Retain 1 SDCU Retain NOTE : You must install these computers again after the modification of the wiring. b Disconnect the bonding braid.

c Remove the attachment hardware from the Shelf 94U. NOTE : Retain the hardware. d Remove the Shelf 94VU and install it on bench. 4 Remove the wires : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 157 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

281118A10508 Sheet(s) 02 A00 281118A10511 Sheet(s) 02 B00 281118A10513 Sheet(s) 02 A00 281118A10516 Sheet(s) 02 A00 281118A10518 Sheet(s) 02 A00 281118A10520 Sheet(s) 02 A00 5 Install the wires : 281118A10501 Sheet(s) 02 A00 281118A10502 Sheet(s) 02 A00 281118A10502 Sheet(s) 03 A00 281118A10503 Sheet(s) 02 A00 281118A10504 Sheet(s) 02 A00 281118A10505 Sheet(s) 02 B00 281118A10506 Sheet(s) 02 A00 281118A10507 Sheet(s) 03 A00 281118A10509 Sheet(s) 02 A00 281118A10510 Sheet(s) 02 B00 281118A10512 Sheet(s) 02 A00 281118A10514 Sheet(s) 02 A00 281118A10515 Sheet(s) 02 A00 281118A10517 Sheet(s) 02 A00 281118A10519 Sheet(s) 02 A00 281118A10521 Sheet(s) 02 A00, supplied in : Bundle D9000095128495 Bundle D9000095128595 6 Attach the wires with : 100 Tie-Cable NSA935401-03 200 Tie-Cable NSA935401-04 200 Tie-Cable NSA935401-05 800 Tie-Cable NSA935401-06 1500 Tie-Cable NSA935401-08

7 Install the Shelf 92VU

a Install the Shelf 92VU on aircraft. b Do the electrical bonding on the shelf attachment.

c Attach the Shelf 92VU and connect the bonding braid with the hardware retained at removal. NOTE : Retain the hardware. d On the Shelf 92VU, install the computers 7QJ, 9QJ, 3QT and 1XG : (Refer to AMM 24-41-34, Page block 401) (Refer to AMM 28-42-34, Page block 401) (Refer to AMM 28-46-34, Page block 401) 1 FLSCU1 1 FLSCU2 1 FQIC DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 158 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 GPCU NOTE : These computers were retained at removal. 8 Install the Shelf 93VU

a Install the Shelf 93VU on aircraft. b Do the electrical bonding on the shelf attachment.

c Attach the Shelf 93VU and connect the bonding braid with the hardware retained at removal. NOTE : Retain the hardware. d On the Shelf 93VU, install the computers 1CE3, 5GA1 and 8HK : (Refer to AMM 21-63-34, Page block 401) (Refer to AMM 27-94-34, Page block 401) (Refer to AMM 32-31-71, Page block 401) 1 SEC3 1 LGCIU1 1 ZONE CONT NOTE : These computers were retained at removal. 9 Install the Shelf 94VU

a Install the Shelf 94VU on aircraft. b Do the electrical bonding on the shelf attachment.

c Attach the Shelf 94VU and connect the bonding braid with the hardware retained at removal. NOTE : Retain the hardware. d On the Shelf 94VU, install the computers 5GA2, 10GG and 10WQ : (Refer to AMM 26-17-34, Page block 401) (Refer to AMM 32-31-71, Page block 401) (Refer to AMM 32-42-34, Page block 401) 1 LGCIU2 1 BSCU 1 SDCU NOTE : These computers were retained at removal. (z) Modify the equipment in the FWD Electronics Rack 90VU Refer to Kit 281118A11R03 1 On the Shelf 92VU

a Remove : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 159 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(Refer to AMM 28-42-34, Page block 401) 281118A11001 Sheet(s) 01 A00 FIN 3QT 1 Computer-FQI With OBRM SIC5059-11-0207 Item (3) 1 Plate Assy D9251102000000 Item (4) 2 Screw Discard Item (112) 2 Screw Discard Item (28) 2 Washer Discard Item (16) 4 Nut Discard

b On the mounting rail of the terminal block 202VT, install : 281118A11002 Sheet(s) 01 B00 1 Module NSA937901MA2011 in position 21 1 Module NSA937901MA2204 in position 22 3 Module Identification NSA937901E2 1 Module Identification NSA937901E1

c Modify the fool proofing on the connector 3QT-A (Refer to ESPM 20-44-22) 281118A11002 Sheet(s) 02 B00 d Install : (Refer to AMM 28-42-34, Page block 401) 281118A11002 Sheet(s) 01 B00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 160 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281118A11002 Sheet(s) 02 B00 FIN 2MCU 1 Rack D0003006100000 Item 15 5 Cover NSA939511-03 Item 5 1 Plate Assy D9251116900000 Attach with : Item 112 3 Screw NAS1801-3-8 Item 4 3 Screw NAS1102-3-10 Item 28 3 Washer ASNA2397-10L Item 16 6 Nut NAS1726-3E FIN 47QJ 1 Level Sensing Control Unit 30042-0000-0501
FIN 47QJ-A 1 Connector E0161D01A12X Attach with : Item 0 2 Flange Assy D9251127600000 Item 6 4 Screw NAS1100-06-12 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 161 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 9 4 Screw NAS1100-04-7 Item 14 4 Washer ASNA2397-4L Item 12 2 Washer ASNA2397-6L FIN 3QT 1 FQIC SIC5059-12-0308 FIN 624VG 1 Module-Grounding E0425A2001 Placard Set D9100095112895 2 On the Shelf 94VU, install : 281118A11003 Sheet(s) 01 A00 281118A11003 Sheet(s) 02 A00 FIN 56QJ 1 Relay E0666D28A0 1 Base E0247A0S

Item 1 1 Retainer Assy E0427-01

Item 2 1 Screw NAS1100-04-6

Item 4 1 Washer ASNA2397-4L

Item 5 2 Washer ASNA2397-3L

Item 6 3 Nut MS21042L04

in position B15 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 162 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Placard Set D9100095112895 (aa) Modify the Refuel Panel 51VU Refer to Kit 281118A12R00 and Kit 281118A13R00 1 Remove : 281118A12001 Sheet(s) 01 A00 Item 14 1 Plate Discard

Item 11 1 Plate Retain

Item 15 1 Air Outlet Front Face Retain

Item 46 1 Preselector 10QT Retain

Item 39 1 Refuel Panel 51VU Discard 2 Install : 281118A12002 Sheet(s) 01 A00 281118A12503 Sheet(s) 01 A00 Item 14 1 Plate Assy D9251122800600

Item 11 1 Plate

Item 15 1 Air Outlet Front Face

Item 46 1 Preselector 10QT

Item 39 1 Refuel Panel 51VU D9550005100395 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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FIN 39LF 1 Plate Integrally Lighted D33110251A00 (ab) Modify the wiring in the aircraft Refer to Kit 281118A12R00 1 Modify the wiring 281118A12501 Sheet(s) 01 A00 281118A12501 Sheet(s) 02 A00 281118A12502 Sheet(s) 01 A00 281118A12502 Sheet(s) 02 A00

a Install the wires : 281118A12501 Sheet(s) 02 A00 281118A12502 Sheet(s) 02 A00, supplied in : Bundle D9000095131595 b Attach the wires with : 50 Tie-Cable NSA935401-04 50 Tie-Cable NSA935401-03 100 Tie-Cable NSA935401-06 (2) Config. 02 281118A00002 Sheet(s) 01 B00 281118A00002 Sheet(s) 02 B00 281118A00002 Sheet(s) 03 A00 281118A00002 Sheet(s) 04 A00 281118A00002 Sheet(s) 05 B00 281118A03000 Sheet(s) 01 A00 281118A04000 Sheet(s) 01 A00 281118A06000 Sheet(s) 01 A00 281118A11000 Sheet(s) 01 A00 281118A14000 Sheet(s) 01 A00 (a) Install the doublers on the upper surface panels Refer to Kit 281118A01R03 281118A01001 Sheet(s) 01 A00 281118A01001 Sheet(s) 02 A00 NOTE : Remove the finch paint and the paint protection from the extrados panel between Y=+254 and Y=-254 and between FR36 and FR42. Do not use a metallic tool. Do not cause damage to the head of the rivet, (Refer to SRM 51-75-11, Paragraph 3). Stop the removal when you can see the primary protection (green color). Only remove rivets at location of the doubler. 1 Drill one hole to a diameter of 64 mm (2.519 in.) and one hole to a diameter of 74 mm (2.913 in.), (Refer to drawing 281118A01001, Sheets 01 and 02). DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 164 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Loft D5713032000095 2 Install : 281118A01001 Sheet(s) 03 B00 Item 0 1 Doubler D5713304820004

Item 1 1 Doubler D5713031920000

with : Fuel Tank Sealant Polysulfide (Mat. No. 09-002) Attach with : Item 10 19 Bolt EN6115V3-3 Item 11 15 Bolt EN6115V3-4 Item 12 15 Bolt EN6115V3-5 Item 13 29 Pin-Hi Lok NSA5357-3-6 Item 14 12 Pin-Hi Lok NSA5357-3-7 Item 15 16 Pin-Hi Lok NSA5357-3-5 Item 22 8 Pin-Hi Lok NSA5357-4-7

Item 23 5 Pin-Hi Lok NSA5357-4-8

Item 30 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 165 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

57 Collar NSA5330-6 Item 35 49 Nut ASNA2528-3 Item 40 13 Collar NSA5330-8 3 Install : 281118A01002 Sheet(s) 01 A00 Item 0 1 Bracket Assy D5791332400000

Item 1 1 Bracket Assy D5791332300000

Attach with : Item 10 2 Bolt EN6115V3-5

Item 11 4 Nut ASNA2528-3

Item 12 2 Bolt EN6115V3-7 (b) Install the brackets on the upper surface panels Refer to Kit 281118A01R03 and Kit 281118A17R00 281118A01005 Sheet(s) 01 A00 281118A01005 Sheet(s) 02 A00 281118A01005 Sheet(s) 03 A00 281118A01005 Sheet(s) 04 A00 NOTE : To install the brackets, put them in position and counter-drill with the existing holes on aircraft. Item 1 1 Support Assy D5791049500095 Item 2 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 166 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Support Assy D5791049400095 Item 3 1 Fitting D5791048300095 Item 4 1 Fitting D5791048200095 Item 5 1 Fitting D5791042020095 Item 6 1 Fitting D5791042120095 Item 9 1 Fitting D5791043020095 Item 10 1 Fitting D5791049820095 Item 11 1 Fitting D5791050020095 Item 12 1 Support D5791042320095 Item 13 1 Support D5791042220095 Item 21

2 Corner Plate A2823301800202 Attach with : Item 20 Fuel Tank Sealant Polysulfide (Mat. No. 09-002) Item 22

4 Rivet ASNA2050DCJ3215 Item 100 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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6 Pin-Hi Lok NSA5357-3-5 Item 102

8 Pin-Hi Lok NSA5357-3-7 Item 103

4 Pin-Hi Lok NSA5357-3-8 Item 104

4 Pin-Hi Lok NSA5357-3-10 Item 107

4 Pin-Hi Lok NSA5357-4-7 Item 108

7 Pin-Hi Lok NSA5357-4-8 Item 109

2 Pin-Hi Lok NSA5357-4-9 Item 110

4 Pin-Hi Lok NSA5357-4-10 Item 140 1 Pin-Hi Lok NSA5357-4-11 Item 120

22 Collar NSA5330-6 Item 130

18 Collar NSA5330-8 NOTE : Item 140 is supplied in Kit 281118A17R00. (c) Install the rod on the upper surface panels Refer to Kit 281118A01R03 281118A01004 Sheet(s) 01 A00 Item 0 1 Rod D2821334100000 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 168 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 4 1 Bracket D2821334220000 Attach with : Item 12

4 Bolt NAS6603-4 Item 14

2 Bolt NAS6604-9 Item 20

4 Nut NSA5050-3 Item 22

2 Nut NSA5050-4 Item 24

4 Washer ASNA2397-10L Item 26

2 Washer ASNA2397-416L (d) Install the bracket on FR42 Refer to Kit 281118A02R03 281118A02001 Sheet(s) 01 A00 NOTE : Remove the finch paint and the paint protection in the center tank. Do not use a metallic tool. Do not cause damage to the head of the rivet, (Refer to SRM 51-75-11, Paragraph 3). Stop the removal when you can see the primary protection (green color). Only remove rivets at location of the doubler. Item 12 1 Corner Plate A2823301800202 Attach with : Item 32

2 Rivet ASNA2050DCJ3215 (e) Install the bracket above FR42 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 169 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Kit 281118A02R03 281118A02002 Sheet(s) 01 A00 281118A02002 Sheet(s) 02 A00 281118A02002 Sheet(s) 03 B00 Item 0 1 Machined Bracket D5791041820095 Attach with : Item 10 Fuel Tank Sealant Polysulfide (Mat. No. 09-002) Item 60

2 Pin-Hi Lok NSA5357-4-11 Item 65

2 Pin-Hi Lok NSA5357-5-13 Item 75

2 Collar NSA5330-8 Item 80

2 Collar NSA5330-10 (f) Install the brackets on the lower surface panels Refer to Kit 281118A02R03 281118A02003 Sheet(s) 01 A00 281118A02003 Sheet(s) 02 A00 281118A02003 Sheet(s) 03 B00 NOTE : To install the brackets, put them in position and counter-drill with the existing holes on aircraft. Item 1 1 Machined Bracket D5791040320095 Item 2 1 Support Assy D5791040500095 Item 3 1 Support Assy D5791040400095 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 170 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 4 1 Machined Bracket D5791040120095 Item 5 1 Machined Bracket D5791040020095 Item 6 1 Machined Bracket D5791040220095 Item 7 1 Machined Bracket D5791040820095 Item 8 1 Machined Bracket D5791040920095 Item 9 1 Machined Bracket D5791040620095 Item 10 1 Machined Bracket D5791040720095 Item 11 1 Machined Bracket D5791041020096 Attach with : Item 20 Fuel Tank Sealant Polysulfide (Mat. No. 09-002) Item 44

4 Bolt NAS6603-4 Item 62

4 Nut NSA5050-3 Item 157

8 Pin-Hi Lok NSA5357-4-9 Item 158

5 Pin-Hi Lok NSA5357-4-10 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 171 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 159

17 Pin-Hi Lok NSA5357-4-11 Item 160 1 Pin-Hi Lok NSA5357-4-12 Item 162 1 Pin-Hi Lok NSA5357-5-13 Item 165

31 Collar NSA5330-8 Item 170 1 Collar NSA5330-10 (g) Install the rod and the plate on the lower surface panels Refer to Kit 281118A02R03 281118A02004 Sheet(s) 01 A00 281118A02004 Sheet(s) 02 A00 Item 2 1 Rod D2821334100200 Item 6 1 Bracket D2821040220000 Item 8 1 Bracket D2821040120000 Attach with : Item 10

8 Bolt NAS6603-2 Item 12

4 Bolt NAS6603-4 Item 14

2 Bolt NAS6604-9 Item 20 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 172 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

4 Nut NSA5050-3 Item 22

2 Nut NSA5050-4 Item 24

12 Washer ASNA2397-10L Item 26

2 Washer ASNA2397-416L (h) Install the Additional Center Tank (ACT) door Refer to Kit 281118A03R01 1 Remove : 281118A03001 Sheet(s) 01 B00 Item (1) 1 Door Assy D5713019400200

Item (4) 1 Screw Discard

Item (8) 1 Washer Discard

Item (5) 15 Washer Discard Item (6) 15 Screw Discard Item (7) 15 Washer Discard 2 Install : 281118A03002 Sheet(s) 01 A00 281118A03002 Sheet(s) 02 A00 1 Door Assy D5713323000000

Item 0 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 173 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Fairing D5713334000000

Item 1 1 Intrados Fitting D5713334600000

Item 2 1 Fitting D5713334500000

Item 3 1 Fitting D5713334400000

Attach with : Item 6 8 Washer A5713052120300

Item 10 3 Bolt NAS6603-2

Item 11 15 Bolt ABS0114V4-18 Items 15 and 36 4 Washer ASNA2397D10L

Item 16 15 Washer MS20002C4 Item 20 1 Bolt NAS6603-3

Item 22 6 Bolt NAS6604-3

Item 40 6 Washer ASNA2397D416L (i) Install the equipment on the ACT door Refer to Kit 281118A03R01 and Kit 281118A15R00 281118A03003 Sheet(s) 01 A00 281118A03003 Sheet(s) 02 A00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 174 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281118A03003 Sheet(s) 03 B00 281118A03003 Sheet(s) 04 A00 281118A03003 Sheet(s) 05 A00 281118A15001 Sheet(s) 01 A00 1 Install the pressure switch 2QH : 281118A03003 Sheet(s) 02 A00 Item 0 1 Pressure Switch HTE690045

Attach with : Item 30 Zinc Chromate General Purpose (Mat. No. 05-002) Item 8 1 Bulkhead D2821067800000

Item 10 1 Plug A2823260820000

Item 12 1 Safety Valve A2823260500000

Item 18 3 Packing NSA8200-6

Item 20 1 O-Ring NSA8203-019

Item 22 4 Bolt NAS6603-5

Item 24 4 Washer ASNA2055-03

Item 26 4 Nut NSA5050-3 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Item 28 1 M Lockwire MS20995C32 2 Install the fuel pump 1QH and the mounting plate 163QM : 281118A03003 Sheet(s) 03 B00 Item 0 1 Fuel Pump 568-1-27170-002

Item 2 1 Mounting Plate 568-1-27171-002

Attach with : Item 50 Grease High Pressure (Mat. No. 04-004) Item 10 1 Pin A2821064820040

Item 12 1 Insert A2821064620000

Item 14 1 Spring A2821064720000

Item 18 1 O-Ring NSA8203-113

Item 22 1 O-Ring NSA8203-167

Item 24 1 O-Ring NSA8203-224

Item 26 1 O-Ring NSA8203-226

Item 28 2 Bonding Lead E0088-10-100 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 176 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 29 4 Bolt NAS6603-1

Item 30 6 Bolt NAS6604-7

Item 32 1 Bolt NAS6604-20

Item 34 1 Seal Washer NSA5112-04

Item 36 6 Washer ASNA2397-416

Item 38 1 Washer ASNA2397-416L

Item 39 4 Washer ASNA2397D10L

Item 40 1 Nut NSA5050-4

Item 42 2 Nut NSA5050-3

Item 48 Wire-Lock MS20995C32 3 Install the refuel valve 41QU and the canister 164QM : 281118A03003 Sheet(s) 04 A00 Item 0 1 Canister-Valve,Refuel 1158000-15

Item 2 1 Refuel Valve 1158000-21

Attach with : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Item 20 Zinc Chromate General Purpose (Mat. No. 05-002) Item 6 1 O-Ring NSA8203-245

Item 8 4 Screw NAS1154-10

Item 10 1 Screw NAS1801-06-8

Item 11 1 Screw NAS1801-3-6

Item 12 1 Washer ASNA2397-6L

Item 13 1 Washer ASNA2397-10L

Item 14 1 Nut MS21042-06

Item 16 4 Nut NAS1726C4E

Item 22 1 Bonding Lead E0088-16-125 4 Install the actuator 6QH and the valve 165QM : 281118A03003 Sheet(s) 05 A00 Item 0 1 Valve HTE900135

Item 2 1 Actuator HTE190001-2

Attach with : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 178 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 20 Zinc Chromate General Purpose (Mat. No. 05-002) Item 4 1 Clamp-V HTE8002

Item 6 1 O-Ring NSA8203-154

Item 8 6 Screw NAS1153-4

Item 13 1 Bolt NAS6603-1

Item 16 4 Nut NAS1726C4E

Item 18 1 Nut NSA5050-3

Item 22 1 Bonding Lead E0088-10-100

Item 24 Wire-Lock MS20995C32 5 Install the placards on the ACT door 281118A15001 Sheet(s) 01 A00 Item 0 1 Placard D2821336920000

Item 2 1 Placard D2821336920200

Item 4 1 Placard D2821336920400

Item 6 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 179 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Placard D2821336920600

Item 8 1 Placard D2821336920800

NOTE : Use Zinc Chromate General Purpose (Mat. No. 05-002), Anti-Corrosion Primer (Polyurethane) (Mat. No. 16-001) and Grease High Pressure (Mat. No. 04-004). (j) Replace the fuel quantity indicator 6QT (Refer to AMM 28-42-22, Page block 401) Refer to Kit 281118A03R01 1 Remove : 1 Fuel Quantity Indicator 1407KID02-03 2 Install : 1 Indicator-Fuel,Quantity 1422KID02-03 (k) Modify the pipes in the center tank Refer to Kit 281118A04R05 1 Remove : 281118A04001 Sheet(s) 01 A00 281118A04001 Sheet(s) 02 A00 281118A04001 Sheet(s) 03 A00 Item (2) 1 Pipe Assy D2821008001300

with : Item (5) 2 O-ring Discard

Items (4) and (9) 2 Screw Retain

Items (8) and (10) 2 Washer Retain 2 Install : 281118A04002 Sheet(s) 01 A00 281118A04002 Sheet(s) 02 A00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 180 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281118A04002 Sheet(s) 03 A00 281118A04002 Sheet(s) 04 A00 Item 6 1 Pipe Assy D2821333900000

Item 120 1 Machined Tee D2821331020000

Item 12 1 Pipe Assy D2821333900100

Item 5 4 O-Ring NSA8203-226

Attach with : Item 16 2 Bolt NAS6603-2

Item 18 2 Nut NAS1726-3E

Item 110 4 Bolt NAS6604-5

Item 112 4 Washer ASNA2397-416L

Item 114 4 Nut NAS1726-4E

Items (4) and (9) 2 Screw

Items (8) and (10) 2 Washer (l) Install the ACT pipes in the center tank Refer to Kit 281118A04R05 and Kit 281118A17R00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 181 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Install : 281118A04015 Sheet(s) 01 A00 281118A04015 Sheet(s) 02 A00 281118A04015 Sheet(s) 03 A00 281118A04015 Sheet(s) 04 A00 281118A04015 Sheet(s) 05 A00 281118A04015 Sheet(s) 06 A00 Item 20 1 Pipe Assy D2821333900900

Item 22 1 Pipe Assy D2821333900300

Item 24 1 Pipe Assy D2821333900400

Item 28 1 Pipe Assy D2821333900600

Item 30 1 Pipe Assy D2821333900700

Item 32 1 Pipe Assy D2821333901000

Item 34 1 Sleeve A2821038600000

Item 36 1 Sleeve D2821333800000

Item 38 1 Pipe D2821334800000

Item 40 1 Pipe D2821334900000

Item 42 1 Pipe Assy D2821335000000 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 182 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 44 1 Pipe Assy D2821335100000

NOTE : If you install the pipe assy D2821338500000 as an alternative to the pipe assy D2821335100000, apply Chemical Conversion Coating Yellow Aluminum (Mat. No. 13-002). Item 46 1 Pipe D2821335800200

Item 50 1 Restrictor D2821336720240

Attach with : Item 51 1 Clamp NSA5516-04ND

Item 52 1 Union MS21902D4

Item 55 2 Nut ABS0107-150

Item 56 3 Nut ABS0107-200

Item 57 2 Ring-Retaining NSA840003-150

Item 58 3 Ring-Retaining NSA840003-200

Item 60 1 Packing NSA8200-4

Item 62 1 O-Ring NSA8203-215

Item 64 12 O-Ring NSA8203-222 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Item 66 5 O-Ring NSA8203-226

Item 68 2 Screw NAS1801-06-10

Item 70 14 Bolt NAS6603-2 Item 72 4 Bolt NAS6603-4

Item 73 4 Bolt NAS6603-5

Item 74 4 Bolt NAS6603-3

Item 76 2 Bolt NAS6604-2

Item 77 4 Bolt NAS6604-3

Item 78 2 Nut MS21042L06

Item 80 18 Nut NSA5050-3 Item 82 6 Nut NSA5050-4

Item 83 2 Washer ASNA2397-6L

Item 84 8 Washer ASNA2397-10L

Item 90 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 Bonding Lead E0088-10-160

Item 92 2 Bonding Lead E0088-10-200

Item 93 1 Bonding Lead E0088-10-280

NOTE : Item 74 is supplied in Kit 281118A17R00. 2 Install : 281118A04004 Sheet(s) 01 A00 Item 0 1 Machined Tee D2821331620000

Attach with : Item 10 6 Bolt NAS6604-5

Item 12 6 Washer ASNA2397-416L

Item 14 6 Nut NAS1726-4E 3 Install : 281118A04005 Sheet(s) 01 A00 Item 0 1 Machined Elbow D2821332220000

Attach with : Item 10 2 Bolt NAS6604-4

Item 12 2 Washer ASNA2397-416L

Item 14 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 185 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 Nut NAS1726-4E 4 Install : 281118A04006 Sheet(s) 01 A00 Item 0 1 Elbow Moulded A2821120120000

Attach with : Item 10 2 Bolt NAS6604-4

Item 12 2 Washer ASNA2397-416L

Item 14 2 Nut NAS1726-4E 5 Install : 281118A04007 Sheet(s) 01 A00 Item 0 1 Machined Elbow D2821338720000

Attach with : Item 10 2 Bolt NAS6604-5

Item 12 2 Washer ASNA2397-416L

Item 14 2 Nut NAS1726-4E 6 Install : 281118A04008 Sheet(s) 01 A00 Item 0 1 Elbow Assy D2821339020095 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 186 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Attach with : Item 8 1 O-Ring NSA8203-226

Item 10 4 Bolt NAS6603-4

Item 12 4 Washer ASNA2397D10L 7 Install : 281118A04009 Sheet(s) 01 A00 Item 0 1 Machined Elbow D2821333220000

Item 2 1 Machined Elbow D2821333420000

Item 4 1 Restrictor D2821336621240

Attach with : Item 8 2 O-Ring NSA8203-222

Item 10 8 Bolt NAS6603-3

Item 12 8 Washer ASNA2397-10L 8 Install : 281118A04014 Sheet(s) 01 A00 Item 0 1 Valve 9843144M

Item 1 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 Flange A2821079520000

Item 2 1 Restrictor D2821335621800

Attach with : Item 20 Fuel Tank Sealant Polysulfide (Mat. No. 09-002) Item 3 1 Nut ABS0107-200

Item 4 1 Ring-Retaining NSA840003-200

Item 5 3 O-Ring NSA8203-226

Item 8 4 Bolt NAS6604-12

Item 9 4 Nut NAS1726-4E

Item 11 2 Bonding Lead E0088-10-100

Item 12 2 Nut NAS1726-3E

Item 13 1 Bolt NAS6603-2

Item 14 1 Bolt NAS6603-1

Item 17 1 Bonding Lead E0088-10-280

Item 19 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 188 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 Washer ASNA2397-10L

NOTE : Item 17 is supplied in Kit 281118A17R00. 9 Install : 281118A04011 Sheet(s) 01 A00 281118A04011 Sheet(s) 02 A00 Item 54 1 Valve 365A02

Item 35 1 Sleeve Assy D2821336300000

Attach with : Item 55 2 Nut ABS0107-150

Item 57 2 Ring-Retaining NSA840003-150

Item 61 1 Packing NSA8200-5

Item 64 2 O-Ring NSA8203-222

Item 70 2 Bolt NAS6603-2

Item 80 2 Nut NSA5050-3 1 0 Install : 281118A04012 Sheet(s) 01 A00 Item 0 1 Tee D2821331320000

Attach with : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 189 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 10 4 Bolt NAS6604-5

Item 12 4 Washer ASNA2397-416L

Item 14 4 Nut NAS1726-4E 1 1 Install : 281118A04013 Sheet(s) 01 B00 Item 0 1 Machined Elbow D2821331920000

Item 2 1 Sleeve D2821336500000

Attach with : Item 8 2 O-Ring NSA8203-222

Item 10 4 Bolt NAS6603-7

Item 12 4 Washer ASNA2397-416L (m) Install the transfert elbow Refer to Kit 281118A05R01 281118A05001 Sheet(s) 01 A00 Item 0 1 Transfert Elbow Assy D2821330700000 Item 2 1 Nutplate Assy D2821334700000 Item 4 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 190 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Nutplate Assy D2821337500000 Item 8 1 O-Ring NSA8203-148 Attach with : Item 10

6 Bolt NAS6604-9 Item 12

6 Washer ASNA2397-416L Item 14 1 Bolt NAS6603-2 Item 16 1 Washer ASNA2397-10L (n) Install the air ventilation elbow Refer to Kit 281118A05R01 281118A05002 Sheet(s) 01 A00 Item 0 1 Elbow Assy D2821337700041 Item 2 1 Nutplate Assy D2821334600000 Item 4 1 Nutplate Assy D2821337600000 Item 14 1 Filter D2821337800000 Item 16 1 Plate D2821337120000 Item 8 1 O-Ring NSA8203-152 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Attach with : Item 10

6 Bolt NAS6604-8 Item 12

6 Washer ASNA2397-416L Item 18

4 Bolt NAS6603-2 Item 20

2 Bolt NAS6603-5 Item 22

5 Washer ASNA2397JD10L Item 24

2 Nut NSA5050-3 Item 26 1 Washer ASNA2397-10L (o) Apply the sealing protection to the center tank Refer to Kit 281118A05R01 281118A05003 Sheet(s) 01 A00 281118A05003 Sheet(s) 02 A00 1 After the installation of the doublers and attachments, apply the sealing protection between FR36 and FR42, on the upper and lower surface panels, with : - Fuel Tank Sealant Polysulfide (Mat. No. 09-001) - Fuel Tank Sealant Polysulfide (Mat. No. 09-002) - Protective Coating For Fuel Vapor (Mat. No. 09-032) - Anti-Corrosion Primer (Polyurethane) (Mat. No. 16-001) - Fuel Tank Coating (Mat. No. 16-015). (p) Install the markings on the belly fairing Refer to Kit 281118A18R00 281118A18001 Sheet(s) 01 A00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 192 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281118A18001 Sheet(s) 02 A00 1 Clean the surfaces of the placards to which you will apply the adhesive with Solvent General Purpose (Mat. No. 11-026) and Lint-Free Cotton Cloth (Mat. No. 19-003). 2 Install : Item 0 2 Placard D1121004620000

Item 1 2 Placard D1121009120000

Item 2 1 Placard D0041109120000 (q) Modify the equipment in the HYD/Fuel Panel 40VU Refer to Kit 281118A06R01, Kit 281118A07R00, Kit 281118A08R01 and Kit 281118A09R01 1 Remove : 281118A06002 Sheet(s) 01 B00 Item (35) FIN 14LF 1 Plate-Integrally Lighted 002098-05

Item (0) 1 Plate-Front D9251092000000 2 Install : 281118A06001 Sheet(s) 01 A00 281118A06002 Sheet(s) 02 A00 FIN 24QH 1 Switch-Pushbutton E0415C3LM078E

with : 1 Sleeve E0416-02 2 Screw NAS1102-04-6 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 193 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Connector E0417C01S

Item 0 1 Plate Front D9251314900000

FIN 14LF 1 Plate-Integrally Lighted D33110194A00

Item 4 1 Placard D1131043320100

Item 6 1 Placard D1131043320200

NOTE : On the new front plate, near the new item of equipment and the items that you installed again, bond the placards, supplied in : Placard Set D9100095112695 NOTE : Safety the screws with Sealant, Anaerobic (Mat. No. 08-623) NOTE : For the modification of the wiring, refer to paragraph ACCOMPLISHMENT INSTRUCTIONS B. (2) (y). (r) Modify the equipment in the Rear C/B Panel 121VU Refer to Kit 281118A06R01 and Kit 281118A14R00 1 Remove : 281118A14001 Sheet(s) 01 A00 FIN 32LM 1 Placard D11310817B00

FIN 33LM 1 Placard D11311191A00

FIN 34LM 1 Placard D11310779A00

FIN 35LM 1 Placard D11310814A00

FIN 36LM DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 194 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Placard D11311157A00 2 Install : 281118A14001 Sheet(s) 01 A00 FIN 9QH 1 Circuit Breaker NSA931320-050

in position P29 FIN 25QH 1 Circuit Breaker NSA931322-100

in position Q29 FIN 30QH 1 Circuit Breaker NSA931320-030

in position N29 FIN 33QU 1 Circuit Breaker NSA931320-050

in position L29 FIN 51QJ 1 Circuit Breaker NSA931320-030

in position M29 FIN 52QJ 1 Circuit Breaker NSA931320-030

in position M28 with : 16 Screw E0736N08-01 16 Washer-Locking ASNA2553-0401

6 Clamp-Locking NSA931305-01

FIN 32LM 1 Placard D00410444A00

FIN 33LM DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 195 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Placard D00411041A00

FIN 34LM 1 Placard D11311000A00

FIN 35LM 1 Placard D00410426A00

FIN 36LM 1 Placard D11311133A00

NOTE : Near the new circuit breaker, bond the placards, supplied in : Placard Set D9100095112695 (s) Modify the wiring in the Rear C/B Panel 121VU Refer to Kit 281118A06R01 281118A06501 Sheet(s) 01 A00 281118A06501 Sheet(s) 02 A00 281118A06502 Sheet(s) 01 A00 281118A06502 Sheet(s) 02 A00 281118A06503 Sheet(s) 01 A00 281118A06503 Sheet(s) 02 A00 281118A06504 Sheet(s) 01 A00 281118A06504 Sheet(s) 02 A00 281118A06505 Sheet(s) 01 A00 281118A06505 Sheet(s) 02 A00 281118A06506 Sheet(s) 01 A00 281118A06506 Sheet(s) 02 A00 281118A06507 Sheet(s) 01 A00 281118A06507 Sheet(s) 02 A00 281118A06508 Sheet(s) 01 A00 281118A06508 Sheet(s) 02 A00 281118A06509 Sheet(s) 01 A00 281118A06509 Sheet(s) 02 A00 281118A06510 Sheet(s) 01 A00 281118A06510 Sheet(s) 02 A00 281118A06511 Sheet(s) 01 A00 281118A06511 Sheet(s) 02 A00 1 Remove the wires : 281118A06501 Sheet(s) 02 A00 281118A06503 Sheet(s) 02 A00 281118A06505 Sheet(s) 02 A00 281118A06508 Sheet(s) 02 A00 281118A06510 Sheet(s) 02 A00 2 Install the wires : 281118A06502 Sheet(s) 02 A00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 196 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

281118A06504 Sheet(s) 02 A00 281118A06506 Sheet(s) 02 A00 281118A06507 Sheet(s) 02 A00 281118A06509 Sheet(s) 02 A00 281118A06511 Sheet(s) 02 A00, supplied in : Bundle D9000095128395 3 Attach the wires with : 150 Tie-Cable NSA935401-03 150 Tie-Cable NSA935401-06 (t) Install the routing of the Relay Box 802VU between FR4 and FR5, in the avionics compartment Refer to Kit 281118A10R02 1 Remove : 281118A10001 Sheet(s) 01 A00 Item (0) 2 Pin Discard 2 Install : 281118A10001 Sheet(s) 02 A00 Item 1 2 Mount E0661-22

Item 2 2 Stud E0420-04 3 Install : 281118A10002 Sheet(s) 01 A00 Item 1 1 Bracket D9241244120000

Item 4 2 Mount NSA935504-01

Attach with : Item 18 2 Rivet ASNA2051DCJ3215 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 197 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 2 1 Spacer NSA5527-03-01

Item 3 1 Screw NAS1801-3-20

Item 5 1 Nut NAS1726-3E 4 Install : 281118A10003 Sheet(s) 01 B00 281118A10003 Sheet(s) 02 B00 5 Install : 281118A10004 Sheet(s) 01 A00 281118A10004 Sheet(s) 02 A00 Item 0 1 Mount NSA935504-03

Item 2 2 Mount NSA935504-01

Attach with : Item 4 3 Screw NAS1801-3-8

Item 6 3 Washer ASNA2397-10L Placard Set D9100095112795 6 Install : 281118A10005 Sheet(s) 01 A00 281118A10005 Sheet(s) 02 A00 Item 10 5 Screw NAS1801-3-9

Item 11 5 Washer ASNA2397-10L DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 198 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 14 5 Nut NAS1726-3E

FIN 4065VC-A 1 Connector E0052R20B41SNF 1 Backshell E0080-01-20C

FIN 4066VC-A 1 Connector E0052R14B19SNF 1 Backshell E0080-01-14C Placard Set D9100095112795 10 M Conduit E0432A12 (u) Install the connector 1982VC between FR33 and FR34 Refer to Kit 281118A10R02 281118A10006 Sheet(s) 01 A00 1 Connector EN3545E03FXB24A 1 Backshell EN3545-007SCD Placard Set D9100095112795 (v) Modify the equipment in the AFT Electronics Rack 80VU Refer to Kit 281118A10R02 1 On the Shelf 85VU

a On the mounting rail of the terminal block 1853VT, install : 1 Module NSA937901MA2206 in position 28 1 Module NSA937901MA2204 in position 62 2 Module Identification NSA937901E2 1 Module Identification NSA937901E6 1 Module Identification NSA937901E8 (w) Modify the equipment in the Relay Box 103VU Refer to Kit 281118A10R02 281118A10007 Sheet(s) 01 A00 281118A10007 Sheet(s) 02 A00 1 Install : FIN 50QJ DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 199 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Relay E0245-28A0 1 Base E0250A0S

Item 6 2 Nut MS21042L04

in position A77 Placard Set D9100095112795 (x) Modify the equipment in the Contactor Box 107VU Refer to Kit 281118A10R02 1 Install : 281118A10008 Sheet(s) 01 A00 281118A10008 Sheet(s) 02 A00 FIN 26QH 1 Relay NSA932843AA01 1 Base NSA932844AA

Item 8 3 Screw NAS1100-04-7

Item 4 3 Washer ASNA2397-4L

Item 6 3 Nut MS21042L04

in position B7 FIN 1274VC 1 Connector EN3545D03MXB22A

FIN 1274VC-A 1 Connector EN3545D03FXA22A 2 Backshell EN3545-007SCD Placard Set D9100095112795 2 On the mounting rail of terminal block 1176VT, install : 1 Module NSA937901MA2008 1 Module Identification NSA937901E0 1 Module Identification NSA937901E1 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 200 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

in position 10. (y) Modify the wiring in the aircraft Refer to Kit 281118A10R02 281118A10501 Sheet(s) 01 A00 281118A10501 Sheet(s) 02 A00 281118A10502 Sheet(s) 01 A00 281118A10502 Sheet(s) 02 A00 281118A10502 Sheet(s) 03 A00 281118A10503 Sheet(s) 01 A00 281118A10503 Sheet(s) 02 A00 281118A10504 Sheet(s) 01 A00 281118A10504 Sheet(s) 02 A00 281118A10505 Sheet(s) 01 B00 281118A10505 Sheet(s) 02 B00 281118A10506 Sheet(s) 01 A00 281118A10506 Sheet(s) 02 A00 281118A10507 Sheet(s) 01 A00 281118A10507 Sheet(s) 02 A00 281118A10507 Sheet(s) 03 A00 281118A10508 Sheet(s) 01 A00 281118A10508 Sheet(s) 02 A00 281118A10509 Sheet(s) 01 B00 281118A10509 Sheet(s) 02 A00 281118A10510 Sheet(s) 01 B00 281118A10510 Sheet(s) 02 B00 281118A10511 Sheet(s) 01 A00 281118A10511 Sheet(s) 02 B00 281118A10512 Sheet(s) 01 A00 281118A10512 Sheet(s) 02 A00 281118A10513 Sheet(s) 01 A00 281118A10513 Sheet(s) 02 A00 281118A10514 Sheet(s) 01 A00 281118A10514 Sheet(s) 02 A00 281118A10515 Sheet(s) 01 A00 281118A10515 Sheet(s) 02 A00 281118A10516 Sheet(s) 01 A00 281118A10516 Sheet(s) 02 A00 281118A10517 Sheet(s) 01 A00 281118A10517 Sheet(s) 02 A00 281118A10518 Sheet(s) 01 A00 281118A10518 Sheet(s) 02 A00 281118A10519 Sheet(s) 01 A00 281118A10519 Sheet(s) 02 A00 281118A10520 Sheet(s) 01 A00 281118A10520 Sheet(s) 02 A00 281118A10521 Sheet(s) 01 B00 281118A10521 Sheet(s) 02 A00 1 Remove the Shelf 92VU

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 201 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a From the Shelf 92VU, remove for access the computers 7QJ, 9QJ, 3QT and 1XG : (Refer to AMM 24-41-34, Page block 401) (Refer to AMM 28-42-34, Page block 401) (Refer to AMM 28-46-34, Page block 401) 1 FLSCU1 Retain 1 FLSCU2 Retain 1 FQIC Retain 1 GPCU Retain NOTE : You must install these computers again after the modification of the wiring. b Disconnect the bonding braid.

c Remove the attachment hardware from the Shelf 92VU. NOTE : Retain the hardware. d Remove the Shelf 92VU and install it on bench. 2 Remove the Shelf 93VU

a From the Shelf 93VU, remove for access the computers 1CE3, 5GA1 and 8HK : (Refer to AMM 21-63-34, Page block 401) (Refer to AMM 27-94-34, Page block 401) (Refer to AMM 32-31-71, Page block 401) 1 SEC3 Retain 1 LGCIU1 Retain 1 ZONE CONT Retain NOTE : You must install these computers again after the modification of the wiring. b Disconnect the bonding braid.

c Remove the attachment hardware from the Shelf 93VU. NOTE : Retain the hardware. d Remove the Shelf 93VU and install it on bench. 3 Remove the Shelf 94VU

a From the Shelf 94VU, remove for access the computers 5GA2, 10GG and 10WQ : (Refer to AMM 26-17-34, Page block 401) (Refer to AMM 32-31-71, Page block 401) (Refer to AMM 32-42-34, Page block 401) 1 LGCIU2 Retain 1 BSCU Retain 1 SDCU Retain DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 202 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

NOTE : You must install these computers again after the modification of the wiring. b Disconnect the bonding braid.

c Remove the attachment hardware from the Shelf 94U. NOTE : Retain the hardware. d Remove the Shelf 94VU and install it on bench. 4 Remove the wires : 281118A10508 Sheet(s) 02 A00 281118A10511 Sheet(s) 02 B00 281118A10513 Sheet(s) 02 A00 281118A10516 Sheet(s) 02 A00 281118A10518 Sheet(s) 02 A00 281118A10520 Sheet(s) 02 A00 5 Install the wires : 281118A10501 Sheet(s) 02 A00 281118A10502 Sheet(s) 02 A00 281118A10502 Sheet(s) 03 A00 281118A10503 Sheet(s) 02 A00 281118A10504 Sheet(s) 02 A00 281118A10505 Sheet(s) 02 B00 281118A10506 Sheet(s) 02 A00 281118A10507 Sheet(s) 03 A00 281118A10509 Sheet(s) 02 A00 281118A10510 Sheet(s) 02 B00 281118A10512 Sheet(s) 02 A00 281118A10514 Sheet(s) 02 A00 281118A10515 Sheet(s) 02 A00 281118A10517 Sheet(s) 02 A00 281118A10519 Sheet(s) 02 A00 281118A10521 Sheet(s) 02 A00, supplied in : Bundle D9000095128495 Bundle D9000095128595 6 Attach the wires with : 100 Tie-Cable NSA935401-03 200 Tie-Cable NSA935401-04 200 Tie-Cable NSA935401-05 800 Tie-Cable NSA935401-06 1500 Tie-Cable NSA935401-08

7 Install the Shelf 92VU

a Install the Shelf 92VU on aircraft. b Do the electrical bonding on the shelf attachment. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 203 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

c Attach the Shelf 92VU and connect the bonding braid with the hardware retained at removal. NOTE : Retain the hardware. d On the Shelf 92VU, install the computers 7QJ, 9QJ, 3QT and 1XG : (Refer to AMM 24-41-34, Page block 401) (Refer to AMM 28-42-34, Page block 401) (Refer to AMM 28-46-34, Page block 401) 1 FLSCU1 1 FLSCU2 1 FQIC 1 GPCU NOTE : These computers were retained at removal. 8 Install the Shelf 93VU

a Install the Shelf 93VU on aircraft. b Do the electrical bonding on the shelf attachment.

c Attach the Shelf 93VU and connect the bonding braid with the hardware retained at removal. NOTE : Retain the hardware. d On the Shelf 93VU, install the computers 1CE3, 5GA1 and 8HK : (Refer to AMM 21-63-34, Page block 401) (Refer to AMM 27-94-34, Page block 401) (Refer to AMM 32-31-71, Page block 401) 1 SEC3 1 LGCIU1 1 ZONE CONT NOTE : These computers were retained at removal. 9 Install the Shelf 94VU

a Install the Shelf 94VU on aircraft. b Do the electrical bonding on the shelf attachment.

c Attach the Shelf 94VU and connect the bonding braid with the hardware retained at removal. NOTE : Retain the hardware. d On the Shelf 94VU, install the computers 5GA2, 10GG and 10WQ : (Refer to AMM 26-17-34, Page block 401) (Refer to AMM 32-31-71, Page block 401) (Refer to AMM 32-42-34, Page block 401) 1 LGCIU2 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 BSCU 1 SDCU NOTE : These computers were retained at removal. (z) Modify the equipment in the FWD Electronics Rack 90VU Refer to Kit 281118A11R03 1 On the Shelf 92VU

a Remove : (Refer to AMM 28-42-34, Page block 401) 281118A11001 Sheet(s) 01 A00 FIN 3QT 1 Computer-FQI With OBRM SIC5059-11-0207 Item (3) 1 Plate Assy D9251102000000 Item (4) 2 Screw Discard Item (112) 2 Screw Discard Item (28) 2 Washer Discard Item (16) 4 Nut Discard

b On the mounting rail of the terminal block 202VT, install : 281118A11002 Sheet(s) 01 B00 1 Module NSA937901MA2011 in position 21 1 Module NSA937901MA2204 in position 22 3 Module Identification NSA937901E2 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 Module Identification NSA937901E1

c Modify the fool proofing on the connector 3QT-A (Refer to ESPM 20-44-22) 281118A11002 Sheet(s) 02 B00 d Install : (Refer to AMM 28-42-34, Page block 401) 281118A11002 Sheet(s) 01 B00 281118A11002 Sheet(s) 02 B00 FIN 2MCU 1 Rack D0003006100000 Item 15 5 Cover NSA939511-03 Item 5 1 Plate Assy D9251116900000 Attach with : Item 112 3 Screw NAS1801-3-8 Item 4 3 Screw NAS1102-3-10 Item 28 3 Washer ASNA2397-10L Item 16 6 Nut NAS1726-3E FIN 47QJ 1 Level Sensing Control Unit 30042-0000-0501
FIN 47QJ-A 1 Connector E0161D01A12X Attach with : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Item 0 2 Flange Assy D9251127600000 Item 6 4 Screw NAS1100-06-12 Item 9 4 Screw NAS1100-04-7 Item 14 4 Washer ASNA2397-4L Item 12 2 Washer ASNA2397-6L FIN 3QT 1 FQIC SIC5059-12-0308 FIN 624VG 1 Module-Grounding E0425A2001 Placard Set D9100095112895 2 On the Shelf 94VU, install : 281118A11003 Sheet(s) 01 A00 281118A11003 Sheet(s) 02 A00 FIN 56QJ 1 Relay E0666D28A0 1 Base E0247A0S

Item 1 1 Retainer Assy E0427-01

Item 2 1 Screw NAS1100-04-6

Item 4 1 Washer ASNA2397-4L

Item 5 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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2 Washer ASNA2397-3L

Item 6 3 Nut MS21042L04

in position B15 Placard Set D9100095112895 (aa) Modify the Refuel Panel 51VU Refer to Kit 281118A12R00, Kit 281118A13R00 and Kit 281118A17R00 1 Remove : 281118A12001 Sheet(s) 01 A00 Item 14 1 Plate Discard

Item 11 1 Plate Retain

Item 15 1 Air Outlet Front Face Retain

Item 46 1 Preselector 10QT Retain

Item 39 1 Refuel Panel 51VU Discard

FIN 2465VC-A 1 Connector-Plug E0052R14B19SNF Discard 2 Install : 281118A12002 Sheet(s) 01 A00 281118A12503 Sheet(s) 01 A00 Item 14 1 Plate Assy D9251122800600

Item 11 1 Plate DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Item 15 1 Air Outlet Front Face

Item 46 1 Preselector 10QT

Item 39 1 Refuel Panel 51VU D9550005100395

FIN 39LF 1 Plate Integrally Lighted D33110251A00

FIN 2465VC-A 1 Connector-Plug EN3646A61419BW

NOTE : Connector 2465VC-A is supplied in Kit 281118A17R00. (ab) Modify the wiring in the aircraft Refer to Kit 281118A12R00 1 Modify the wiring 281118A12501 Sheet(s) 01 A00 281118A12501 Sheet(s) 02 A00 281118A12502 Sheet(s) 01 A00 281118A12502 Sheet(s) 02 A00

a Install the wires : 281118A12501 Sheet(s) 02 A00 281118A12502 Sheet(s) 02 A00, supplied in : Bundle D9000095131595 b Attach the wires with : 50 Tie-Cable NSA935401-04 50 Tie-Cable NSA935401-03 100 Tie-Cable NSA935401-06 (3) Config. 01 thru Config. 02 Kit 281118B02R01 Refer to drawings: D92355000 Sheet(s) 1 D92556025 Sheet(s) 1 and 3 (a) Install this item in the forward avionics compartment: 1 Relay Box D9255602500800 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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(4) Config. 01 thru Config. 02 Kit 281118B02R01, Kit 281118B03R00, Kit 281118B04R02 and Kit 281118B05R00 Refer to drawings: D92450032 Sheet(s) 6 and 7 D92450115 Sheet(s) 1 and 2 D92550025 Sheet(s) 1 D92550032 Sheet(s) 1 and 2 (a) Remove and discard the refuel/defuel panel mounting assembly in the belly fairing, zone 192. 1 Remove the pre-select unit 5QT (Refer to AMM 28-42-21, Page block 401). 2 Remove the refuel/defuel control panel 800VU (Refer to AMM 28-25-55, Page block 401). 3 Remove the fuel quantity indicator unit 6QT (Refer to AMM 28-42-22, Page block 401). 4 Temporarily remove all attachments and associated fittings from the panel mounting-assembly. 5 Remove the panel mounting-assembly, retain the attachment bolts for installation of the new panel mounting-assembly in the same position. (b) Install additional wiring between zone 192 and 132. 1 Remove the wire shown on line 3, refer to figure 49 Sheet 1 (Hook-up Chart). 2 Install the wires shown on lines 1 thru 11 (Refer to Figure 49 Sheet 1 (Hook-up Chart). supplied in: 1 Bundle D9240000064695

and route them with the wires that are in the aircraft. 3 Cut the wires to the necessary length, crimp the terminals and connect them. 4 Do a intrinsically safe continuity test of the new wires. 5 Attach the wires with tie-wraps as necessary. (c) Install the new refuel/defuel panel mounting assembly in the belly fairing, zone 192. 1 Use a non-metallic spatula to remove the sealant and clean the areas with Solvent (Mat. No. 11-026). 2 Use sealant (Mat. No. 09-001) to wet assemble the refuel panel mounting-assembly and position it in the belly fairing. Use the attachment bolts retained from removal and install: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 Panel Assy-Mounting D9245011500600 3 Install all the attachment and associated fittings removed from the panel mounting-assembly. 4 Install the pre-select unit 5QT (Refer to AMM 28-42-21, Page block 401). 5 Install the refuel/defuel control panel 800VU (Refer to AMM 28-25-55, Page block 401). 1 Panel Assy-Refuel, 800 VU D9255003200400 Item 51

6 Install the fuel quantity indicator unit 6QT (Refer to AMM 28-42-22, Page block 401).

a Install: 1 Indicator-Fuel, Quantity 1418KID01-03 NOTE : Locally manufacture an "INOP" (inoperative) label to the dimensions of the ACT 2 window and install in the ACT 2 window of the fuel quantity indicator unit 6QT. 7 Install the refuel panel assembly 801VU Refer to drawing D92550025 and install this item: 1 Panel Assy-Refuel, 801VU D9255002500000 (5) Config. 01 thru Config. 02 Top Drawing D0007113700/002 (a) Remove and discard the belly fairing panel 197AB. Refer to AMM 53-35-11, Page block 401 1 Remove these items : Refer to Drawing(s) : D53475023000 Sheet(s) 1 thru 4 1 panel D5347503000000 Item (002) discard 46 screw NSA5030-3-3 Item A 16 screw NSA5030-3-4 Item B 59 screw NSA5030-3-6 Item C NOTE : Remove and retain the Items A, B and C. (b) Modify the attachment structure of the belly fairing panel 197AB. Refer to Kit 281118D60R00 Refer to Drawing(s) : D53475023000 Sheet(s) 1 thru 4 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 Install the brackets as shown in Detail Z1-3, Sections C3-C4 and D3-D4 :

a Put these items in position : 1 bracket D5347542400000 Item 020 2 angle D5347542720000 Item 022 1 bracket D5347542400200 Item 024

b Drill the holes and open the holes to final dimension.

c Install these items : 1 bracket D5347542400000 Item 020 2 angle D5347542720000 Item 022 1 bracket D5347542400200 Item 024 with : 34 rivet LN9198-4012CF Item 240 2 Drill the holes as shown in View C1-2 and View B3-2 :

a Mark the position of the holes at the rib. b Drill the holes with 30.0 mm (1.181 in.) diameter.

c Deburr the holes. 3 Replace nut plates as shown in Section E1-E3 :

a Remove and discard this item : 5 nut NAS1791A3-1 Item (026) discard

b Install these items : 3 recepcle ABS0368-01 Item 028 2 nut NAS1791A3-1 Item 030 2 shim D5347521320000 Item 032 with : 10 rivet DIN65399-2412BF Item 125 (c) Remove and not reuse the pressure reservoirs for the offwing escape slides LH/RH. Refer to Drawing(s) : D25690000004 Sheet(s) 7 thru 9 1 Remove and not reuse these items as shown in Sections B7-B8 and A7-A9 : 1 reservoir 60592-101 Item (008) not reuse 1 reservoir 60592-101 Item (009) not reuse DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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2 screw NAS1096-2-16 Item (010) discard 10 washer ASNA0113-40ADL Item (012) discard

2 spacer NSA5527-03-01 Item (014) discard 2 clamp NAS5516-18NJ Item (018) discard 8 screw NAS1096-2-10 Item (020) discard 1 bracket D2567043300000 Item (042) discard 1 bracket D2567043300100 Item (043) discard 1 tie NSA935402-51 Item (050) discard 1 tie NSA935402-51 Item (051) discard (d) Remove and discard the placards at the AFT cargo compartment lining panels between FR47 and FR48 LH/RH. Refer to Drawing(s) : D25573522000 Sheet(s) 1 1 Remove and discard this item :

2 placard A2557146821600 Item (518) discard (e) Modify the AFT cargo compartment side wall-panel 152DW for access to the ACT pressurization system connection between FR49 and FR50. Refer to drawing(s): D25286364010 Sheet(s) 7 and 8 1 Remove and discard these items : 1 box (LH) D2527305509400 Item (514) discard 1 box (RH) D2527305509500 Item (515) discard (f) Remove and discard the placards at the overhead stowage compartments between FR43 and FR47. Refer to Drawing(s) : D25288767000 Sheet(s) 1 and 2 1 Remove and discard this item :

4 placard D2527700844200 Item (1242) discard (g) Remove and retain the insulation blankets in the affected areas. Refer to AMM 25-80-00, Page block 201 Refer to Drawing(s) : D25671745000 Sheet(s) 1 thru 7 D25670762000 Sheet(s) 1 thru 7 (h) Install the brackets for relocation of the pressure reservoirs of the offwing escape slides LH/RH. Refer to Kit 281118D02R00

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Refer to Drawing(s) : D25670762000 Sheet(s) 1 thru 7 1 Put these items in position, drill the holes and install the brackets as shown in Details Y2-3 and Y5-6 : 2 bracket D2567072701200 Item 006

with : 8 rivet LN9198-4008CF Item 100 2 Put these items in position, drill the holes and install the brackets as shown in Details X2-3 and W2-3 : 2 bracket D2567072700400 Item 004

with : 4 rivet LN9198-4008CF Item 100 3 Put these items in position, drill the holes and install the brackets as shown in Details X5-6 and W5-6 : 2 bracket D2567072700500 Item 005

with : 4 rivet LN9198-4008CF Item 100 4 Put these items in position, drill the holes and install the brackets as shown in Details V2-3, V5-6, U2-3, U5-6, T2-3, T5-6 : 6 bracket D2567072700200 Item 002

with : 12 rivet LN9198-4008CF Item 100 5 Put these items in position, drill the holes and install the brackets as shown in Details S2-3 and S5-6 : 2 bracket D2567072701000 Item 000

with : 8 rivet LN9198-4008CF Item 100 6 Put these items in position, drill the holes and install the brackets as shown in Details A4-4, B4-4 and C4-4 : 3 bracket D2567072700800 Item 008 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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with : 15 rivet LN9198-4008CF Item 100 7 Put these items in position, drill the holes and install the brackets as shown in Details A7-7, B7-7 and C7-7 : 3 bracket D2567072700900 Item 009

with : 15 rivet LN9198-4008CF Item 100 (i) Modify and re-identify the insulation blankets after the bracket installation.

(j) Install the retained insulation blankets in the affected areas. Refer to AMM 25-80-00, Page block 201

(k) Install the support and the tubes for the pressure reservoir of the offwing escape slide LH. Refer to Kit 281118D02R00 Refer to Drawing(s) : D25671745000 Sheet(s) 1 thru 7 1 Install the support between FR45 and FR47 as shown in Detail Z2-6 : 1 section D2567070600000 Item 010

with : 6 screw NAS1096-3-10 Item 080 6 washer NAS1149D0363K Item 110 2 Install the tubes as shown in Details Y2-2, X2-2 and Z2-2 : 1 tube D2567070100000 Item 000 1 tube D2567070100200 Item 002 1 cap NAS817-10 Item 070 1 tube 64079-3 Item 595 1 tube 64079-5 Item 597

with : 2 clamp ABS0396C08JA Item 060 1 clamp NSA5515-12 Item 066 5 clamp NAS5515-8 Item 062 9 screw NAS1096-3-10 Item 080 1 screw NAS1096-2-9 Item 082 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 nut MS21042-08 Item 092 9 washer NAS1149D0363K Item 110 1 washer NAS1149DN832K Item 112 3 Install the bonding straps as shown in Detail E2-2 and D2-2 : 2 lead E0088-10-80NN Item 050

with : 2 clamp NSA5519-11 Item 064 2 screw NAS1096-2-9 Item 082 2 screw NAS1096-2-7 Item 084 2 nut MS21042-08 Item 092 6 washer NAS1149DN832K Item 112 (l) Install the support and the tubes for the pressure reservoir of the offwing escape slide RH. Refer to Kit 281118D02R00 Refer to Drawing(s) : D25671745000 Sheet(s) 1 thru 7 1 Install the support between FR45 and FR47 as shown in Detail Z4-7 : 1 section D2567070600200 Item 012

with : 4 screw NAS1096-3-10 Item 080 2 screw NAS1096-3-12 Item 103 6 washer NAS1149D0363K Item 110 2 Install the tubes as shown in Details A4-4 and Z4-4 : 1 tube D2567070100100 Item 001 1 tube D2567070100300 Item 003 1 cap NAS817-10 Item 070 1 tube 64079-1 Item 596 1 tube 64079-5 Item 597

with : 2 clamp ABS0396C08JA Item 060 5 clamp NAS5515-8 Item 062 9 screw NAS1096-3-10 Item 080 9 washer NAS1149D0363K Item 110 3 After installation of the tubes, do the pressure test of the hose/pipe routing :

a Disconnect the pipe from the slide. b Blanc the rigid pipe with cap MS21914-10J. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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c Put pressure on the pipe and stabilize a pressure of 35.0 bar. Hold this pressure for 15 minutes. Admissible pressure drop : up to and including 2 bar. 4 Install the bonding straps as shown in Details E4-4 and D5-5: 2 lead E0088-10-80NN Item 050

with : 2 clamp NSA5519-11 Item 064 2 screw NAS1096-2-9 Item 082 2 screw NAS1096-2-7 Item 084 2 nut MS21042-08 Item 092 6 washer NAS1149DN832K Item 112 (m) Relocate the release cable for the offwing slide LH. Refer to Kit 281118D50R02 1 Remove the old release cable for the offwing slide LH between FR40 and FR47 : Refer to Drawing(s) : D53370297000 Sheet(s) 1 thru 3

a Remove these items as shown in Detail Y2-2 : 1 nut NAS1726C4P Item (814) discard 1 nut NAS509-4C Item (816) discard 1 flange D5337025520000 Item A 1 bolt NSA5031H4-4 Item C 1 bolt NSA5031-4-4 Item D 1 washer NSA1149C0463R Item E NOTE : Remove and retain the Items A, C, D and E. b Remove these items as shown in Section G2-G3 : 2 washer NAS1149C0332R Item (818) discard 1 pin MS24665-153 Item (822) discard 1 bolt D5337048420200 Item B NOTE : Remove and retain the Item B.

c Remove and discard these items as shown in Detail A1-2 : 1 cable 1606290-001 Item (800) discard 12 clamp MS21919WCH6 Item (802) discard

2 tie NSA935401-03 Item (804) discard 6 bolt NSA5031-3-5 Item (806) discard 6 bolt NSA5031-3-4 Item (810) discard 8 nut NAS1726C3P Item (812) discard DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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9 washer NAS1149C0332R Item (818) discard 1 washer NAS1149C0463R Item (820) discard

d Remove these items as shown in Detail B2-3: 1 clamp MS21919WCH6 Item (802) discard 1 bolt NSA5031-3-4 Item (810) discard 1 washer NAS1149C0332R Item (818) discard 1 bracket D5337025200 Item (830)

e Close the remaining two rivet holes with these items as shown in Detail A4-6: 2 rivet DIN65399-3208BF Item 652 2 Install the brackets for the release cable attachment between FR41 and FR46 : Refer to Drawing(s) : D53370297000 Sheet(s) 4 thru 6

a Put the item in position, drill the holes for the rivets and install this item as shown in Detail A5-5 : 1 angle D5337025920000 Item 012 with : 2 rivet LN9198-3212BF Item 632

b Put the items in position, drill the holes for the rivets and install these items as shown in Details B5-5 and C5-5 : 2 profile D5337025620200 Item 008 1 profile D5337025620600 Item 010 with : 4 rivet LN9198-3212BF Item 632

c Put the items in position, drill the holes for the rivets and install these items as shown in Section D4-D5 and in Details E5-5 and F5-5 : 2 angle D5337025020000 Item 006 1 bridge D5337645020000 Item 014 with : 8 rivet LN9198-3212BF Item 632

d Put the item in position, drill the holes for the rivets and install this item as shown in Detail A6-6 : 1 bracket D5337645300200 Item 016 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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with : 4 rivet LN9198-3212BF Item 632

e Put the item in position, drill the holes for the rivets and install this item as shown in Section F4-F6 : 1 holder D5337645420000 Item 018 with : 4 rivet LN9198-3212BF Item 632 3 Install the release cable for the offwing slide LH between FR40 and FR46 : Refer to Drawing(s) : D53370297000 Sheet(s) 7 thru 10 and 12

a Install this item as shown in Detail C1-7 : 1 control L32A319-160-002 Item 000 with : 10 clamp MS21919WCH6 Item 030

1 hose DAN79-07 Item 032 2 tie NSA935401-03 Item 034 7 bolt NSA5031-3-5 Item 040 3 bolt NSA5031-3-4 Item 042 10 nut NAS1726C3P Item 064 10 washer NAS1149C0332R Item 070 b Install these items and secure with lockwire (Mat. No. 19-010) as shown in Detail Z7-9 : 1 nut NAS1726C4P Item 060 1 nut NAS509-4C Item 062 1 flange D5337025520000 Item A 1 bolt NSA5031H4-4 Item C 1 bolt NSA50314-4 Item D 1 washer NSA1149C0463R Item E NOTE : The Items A, C, D and E are retained parts.

c Install these items as shown in Section J7-J9 : 3 washer NAS1149C0332R Item 070 1 pin MS24665-153 Item 080 1 bolt D5337048420200 Item B NOTE : The Item B is a retained part.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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d Adjust the release cable so that the dimension "B" is between 9.8 mm (0.386 in.) and 13.2 mm (0.519 in.) as shown in Detail Z10-10.

e Install this item as shown in Details V7-10 and Z10-10 : 1 adapter L32A319-165-002 Item 002

f Install a rigging pin with 5.0 mm (0.197 in.) diameter at the lever as shown in drawing D53370297000, Sheet 10, Detail V7-10. g Adjust the length of the adapter, Item 002, and connect the adapter with the lever with these items as shown in Section B10-B10 : 1 pin MS20392-2C19 Item 036 3 washer NAS1149C0332R Item 070 1 pin MS24665-153 Item 080

h Secure the both rod ends and the adjustment nuts of the release cable with lockwire (Mat. No. 19-010) as shown in Details V7-10 and Z7-9 and in Section B10-B10. i Remove the rigging pin from the lever. (n) Relocate the release cable for the offwing slide RH. Refer to Kit 281118D51R01 1 Remove the old release cable for the offwing slide RH between FR40 and FR47 : Refer to Drawing(s) : D53370297001 Sheet(s) 1 thru 3

a Remove these items as shown in Detail Y2-2 : 1 nut NAS1726C4P Item (814) discard 1 nut NAS509-4C Item (816) discard 1 flange D5337025520000 Item A 1 bolt NSA5031H4-4 Item C 1 bolt NSA5031-4-4 Item D 1 washer NSA1149C0463R Item E NOTE : Remove and retain the Items A, C, D and E. b Remove these items as shown in Section G2-G3 : 2 washer NAS1149C0332R Item (818) discard 1 pin MS24665-153 Item (822) discard 1 bolt D5337048420200 Item B NOTE : Remove and retain the Item B.

c Remove and discard these items as shown in Detail A1-2 : 1 cable 1606290-001 Item (800) discard DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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12 clamp MS21919WCH6 Item (802) discard

2 tie NSA935401-03 Item (804) discard 6 bolt NSA5031-3-5 Item (806) discard 6 bolt NSA5031-3-4 Item (810) discard 8 nut NAS1726C3P Item (812) discard 9 washer NAS1149C0332R Item (818) discard 1 washer NAS1149C0463R Item (820) discard 2 Install the brackets for the release cable attachment between FR41 and FR46 : Refer to Drawing(s) : D53370297001 Sheet(s) 4 thru 6

a Put the item in position, drill the holes for the rivets and install this item as shown in Detail A5-5 : 1 angle D5337025920000 Item 012 with : 2 rivet LN9198-3212BF Item 632

b Put the items in position, drill the holes for the rivets and install these items as shown in Details B5-5 and C5-5 : 2 profile D5337025620200 Item 008 1 profile D5337025620700 Item 011 with : 4 rivet LN9198-3212BF Item 632

c Put the items in position, drill the holes for the rivets and install these items as shown in Section D4-D5 and in Details E5-5 and F5-5 : 2 angle D5337025020100 Item 007 1 bridge D5337645020100 Item 015 with : 8 rivet LN9198-3212BF Item 632

d Put the item in position, drill the holes for the rivets and install this item as shown in Detail A6-6 : 1 bracket D5337645300300 Item 017 with : 4 rivet LN9198-3212BF Item 632

e Put the item in position, drill the holes for the rivets and install this item as shown in Section F4-F6 : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 holder D5337645420000 Item 018 with : 4 rivet LN9198-3212BF Item 632 3 Install the release cable for the offwing slide RH between FR40 and FR46 : Refer to Drawing(s) : D53370297001 Sheet(s) 7 thru 9, 11, 12

a Install this item as shown in Detail C1-7 : 1 control L32A319-160-002 Item 000 with : 10 clamp MS21919WCH6 Item 030

1 hose DAN79-07 Item 032 2 tie NSA935401-03 Item 034 7 bolt NSA5031-3-5 Item 040 3 bolt NSA5031-3-4 Item 042 10 nut NAS1726C3P Item 064 10 washer NAS1149C0332R Item 070 b Install these items and secure with lockwire (Mat. No. 19-010) as shown in Detail Z7-9 : 1 nut NAS1726C4P Item 060 1 nut NAS509-4C Item 062 1 flange D5337025520000 Item A 1 bolt NSA5031H4-4 Item C 1 bolt NSA50314-4 Item D 1 washer NSA1149C0463R Item E NOTE : The Items A, C, D and E are retained parts.

c Install these items as shown in Section J7-J9 : 3 washer NAS1149C0332R Item 070 1 pin MS24665-153 Item 080 1 bolt D5337048420200 Item B NOTE : The Item B is a retained part. d Adjust the release cable so that the dimension "B" is between 9.8 mm (0.386 in.) and 13.2 mm (0.519 in.) as shown in Detail Z11-11.

e Install this item as shown in Details W7-11 and Z11-11 : 1 adapter L32A319-165-001 Item 004

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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f Install a rigging pin with 5.0 mm (0.197 in.) diameter at the lever as shown in drawing D53370297001, Sheet 11, Detail W7-11. g Adjust the length of the adapter, item 004, and connect the adapter with the lever with these items as shown in Section B11-B11 : 1 pin MS20392-2C19 Item 036 3 washer NAS1149C0332R Item 070 1 pin MS24665-153 Item 080

h Secure the both rod ends and the adjustment nuts of the release cable with lockwire (Mat. No. 19-010) as shown in Details W7-11 and Z7-9 and in Section B11-B11. i Remove the rigging pin from the lever. (o) Installation of the cable harness 5339VB from the terminal block 7223VT to the receptacle 7555VC. Refer to Kit 281118D01R00 Refer to Figure 1 (Hookup Chart 1) Refer to Drawing(s) : D92894736004 Sheet(s) 14 thru 17 D92894713020 Sheet(s) 1 1 Installation of the brackets.

a Remove this item as shown in drawing D92894736004, Sheet 16, Detail A : 1 screw NAS1096-2-9 Item (005) discard and install these parts : 1 screw NAS1096-2-12 Item 007 1 bracket E0343-01 Item 250 1 bracket NSA935504-03 Item 253 1 spacer NSA5527-03-03 Item 304

b Remove this item as shown in drawing D92894736004, Sheet 16, Section A-A : 2 pin DAN364-02 Item (291) discard and install these items : 2 bracket ABS0355-01 Item 262 2 bracket ABS0355-02 Item 263 2 washer NSA935514-03 Item 264

c Install this item as shown in drawing D92894736004, Sheet 16, Detail B : 1 bracket NSA935513-07 Item 259 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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2 Installation of the wiring.

a Route the wires with the existing wire, as shown in Hookup Chart 1, lines 1 and 2 and the drawing D92894736004, supplied with : 1 harness D9299043900000 Item 039 and connect with : tie NSA935401-03 Item 793 tie NSA935401-04 Item 794 tie NSA935401-05 Item 795 b Connect 7555VC with these items as shown in drawing D92894736004, Sheet 16, Detail B : 2 screw NAS1100-04-5 Item 051 2 washer NAS1149CN616R Item 150 2 nut MS21042-04 Item 200

c Connect 7499VN with these items as shown in drawing D92894736004, Sheet 16, Detail B : 1 screw NAS1096-3-9 Item 030 1 washer NAS1149C0332R Item 153

d Install the placards as shown in drawing D92894736004, Sheet 16, Details A and B : 2 placard D9239386503200 Item 050

e Install the "MOD/SB" placards on the harness 5339VB, Item 039, as shown in drawing D92894713020, Sheet 1 : 20 placard D9239310902800 Item 000 40 tie NSA935401-03 Item 080 (p) Installation of the cable harness 5340VB from the terminal block 7224VT to the receptacle 7556VC. Refer to Kit 281118D01R00 Refer to Figure 2 (Hookup Chart 2) Refer to Drawing(s) : D92894736004 Sheet(s) 14 thru 17 D92894713020 Sheet(s) 1 1 Installation of the brackets.

a Install these items as shown in drawing D92894736004, Sheet 16, Detail C : 3 screw NAS1096-2-12 Item 007 3 washer NAS1149CN816R Item 152 3 nut NSA5066-08-1 Item 230 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 bracket E0343-01 Item 250 1 bracket NSA935504-01 Item 251 3 spacer NSA5527-03-03 Item 304 2 Installation of the wiring.

a Route the wires with the existing wire, as shown in Hookup chart 2, lines 1 and 2 and the drawing D92894736004, supplied with : 1 harness D9299044000000 Item 040 and connect with : tie NSA935401-03 Item 793 tie NSA935401-04 Item 794 tie NSA935401-05 Item 795 b Connect 7556VC with these items as shown in drawing D92894736004, Sheet 16, Detail C : 2 screw NAS1100-04-5 Item 051 2 washer NAS1149CN616R Item 150 2 nut MS21042-04 Item 200

c Connect 7100VN with these items as shown in drawing D92894736004, Sheet 16, Detail D : 1 screw NAS1096-3-9 Item 030 1 washer NAS1149C0332R Item 153

d Install the placards as shown in drawing D92894736004, Sheet 16, Details C and D : 2 placard D9239386503200 Item 050

e Install the "MOD/SB" placards on the harness 5340VB, Item 040, as shown in drawing D92894713020, Sheet 1 : 20 placard D9239310902800 Item 000 40 tie NSA935401-03 Item 080 (q) Install the overhead stowage compartment between FR43 and FR47 LH/RH. Refer to Kit 281118D03R00 1 Install : Refer to Drawing(s) : D25286364010 Sheet(s) 7 and 8

a Install the boxes, Items 020 and 021, as shown in Sections A7-8 and D7-8 : 1 box (LH) D2527305811800 Item 020 1 box (RH) D2527305811900 Item 021 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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with : 16 screw NAS1102-4-16 Item 002 16 washer NAS1149F0432P Item 004 16 washer NAS1169C416L Item 006 16 nut MS21042-4 Item 008 16 screw NAS1102-08-16 Item 010 16 washer NAS1149FN816P Item 012 16 washer NAS1169C8L Item 014 16 nut MS21042-08 Item 016

4 pin MS20392-3C23 Item 030 2 pin MS20392-3C27 Item 031 6 washer NAS1149F0463P Item 032 6 pin AA55487-5 Item 033 4 pin MS20392-4C67 Item 042 2 pin MS20392-4C45 Item 043 4 washer NAS1149C0532R Item 046 6 split-Ring DAN191-20 Item 047 2 clamp NSA5528-045 Item 065 (r) Install the placards at the overhead stowage compartment between FR43 and FR47 LH/RH Refer to Kit 281118D04R00 1 Install : Refer to Drawing(s) : D25288767000 Sheet(s) 1 and 2

a Install these items : 2 placard D2527719940600 Item 206 2 placard D2527700844200 Item 242 2 placard A2528131544600 Item 246 (s) Install the pressure reservoir of the offwing escape slide LH between FR45 and FR47. Refer to Kit 281118D02R00 Refer to Drawing(s) : D25671746000 Sheet(s) 1 thru 4 1 Install : 1 reservoir 60592-103 Item 594

with : 1 pocket D2567043200000 Item 050 1 clamp ASNA0033-172 Item 060 1 section LN29837A1 Item 070 2 screw NAS1096-3-7 Item 080 2 washer NAS1149D0363K Item 090 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 placard D9239310903000 Item 100 1 pin MS20392-2C15 Item 110 3 washer NAS1149C0332R Item 120 1 cotter pin MS24665-1013 Item 130 1 placard D2567074100600 Item 140

NOTE : PN 73228620 is the same as PN LN29837A1 given in the drawing. Cut the section, Item 070, in two pieces. One part for the left hand side and the other part for the right hand side. (t) Install the pressure reservoir of the offwing escape slide RH between FR45 and FR47. Refer to Kit 281118D02R00 Refer to Drawing(s) : D25671746000 Sheet(s) 1 thru 4 1 Install : 1 reservoir 60592-103 Item 0598

with : 1 pocket D2567043200000 Item 050 1 clamp ASNA0033-172 Item 060 1 Section LN29837A1 Item 070 2 screw NAS1096-3-7 Item 080 2 washer NAS1149D0363K Item 090 1 placard D9239310903000 Item 100 1 pin MS20392-2C15 Item 110 3 washer NAS1149C0332R Item 120 1 cotter pin MS24665-1013 Item 130 1 placard D2567074100600 Item 140

NOTE : PN 73228620 is the same as PN LN29837A1 given in the drawing. (u) Install the additional angles at the webs of the keel beam structure between FR42 and FR46. Refer to Kit 281118D07R00 Refer to Drawing(s) : D53370780000 Sheet(s) 1 1 Install angles at webs of keel beam structure as shown in Section A1-A1 and E1-E1 ’AFTER MODIFICATION’.

a Put these items in position : 1 angle D5337270100000 Item 000 1 angle D5337270100800 Item 008 2 shim D5337070220000 Item 020

b Drill the holes and open the holes to final dimension. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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c Install these items : 1 angle D5337270100000 Item 000 1 angle D5337270100800 Item 008 2 shim D5337070220000 Item 020 with : 4 bolt ASNA0082-304 Item 364 2 Install the angles at the webs of keel beam structure as shown in Sections B1-B1, C1-C1, D1-D1 and F1-F1 ’AFTER MODIFICATION’.

a Remove existing rivets as shown in Sections B1-B1, D1-D1 and F1-F1. b Put these items in position : 1 angle D5337070100000 Item 002 1 angle D5337270100400 Item 004 1 angle D5337070100200 Item 006 1 angle D5337070100400 Item 010

c Drill the holes and open the holes to final dimension. d Install these items : 1 angle D5337070100000 Item 002 1 angle D5337270100400 Item 004 1 angle D5337070100200 Item 006 1 angle D5337070100400 Item 010 with : 8 bolt ASNA0082-303 Item 363 (v) Replace the fasteners between FR42 and FR44, LH Refer to Kit 281118D62R00 Refer to Drawing(s) : D53371237000 Sheet(s) 1 1 Remove the affected fasteners as shown in Detail Z1-1. 2 Open the holes to final dimension. 3 Install these items :

20 pin DAN7-6-8X Item 001 32 pin DAN7-8-8X Item 002 12 pin DAN7-8-10X Item 003

1 pin DAN8-8-8X Item 004 20 collar DAN12-6X Item 005 45 collar DAN12-8X Item 006 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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(w) Replace the fasteners between FR42 and FR44, RH. Refer to Kit 281118D63R00 Refer to Drawing(s) : D53371237001 Sheet(s) 1 1 Remove the affected fasteners as shown in Detail Z1-1. 2 Open the holes to final dimension. 3 Install these items :

20 pin DAN7-6-8X Item 001 32 pin DAN7-8-8X Item 002 12 pin DAN7-8-10X Item 003

1 pin DAN8-8-8X Item 004 20 collar DAN12-6X Item 005 45 collar DAN12-8X Item 006 (x) Remove and discard the AFT cargo compartment partition panels 151AW, 151BW and 152BW at FR47. Refer to AMM 25-55-11, Page block 401 Refer to Drawing(s) : D25570048002 Sheet(s) 2 1 Remove and discard these items : 1 panel D2557166000000 Item (100) discard 1 panel D2557166000100 Item (102) discard 1 panel D2557166200000 Item (104) discard (y) Remove these placards. Refer to Drawing(s) : D25572631034 Sheet(s) 38 1 Remove : 1 placard A25571468216 Item (18) discard 1 placard D25572951222 Item (29) discard 1 placard D25572951226 Item (30) discard 1 placard D25572952300 Item (40) discard (z) Remove the sidewall panels 151EW and 151HW. Refer to AMM 25-55-11, Page block 401 Refer to Drawing(s) : D25570048004 Sheet(s) 3 1 Remove : 1 sidewall panel D2557033600000 Item (112) discard DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 sidewall panel D2557033600600 Item (114) discard (aa) Remove the sidewall panel 152DW. Refer to AMM 25-55-12, Page block 401 Refer to Drawing(s) : D25570048006 Sheet(s) 4 1 Remove : 1 sidewall panel D2557035200000 Item (116) discard (ab) Remove the AFT cargo compartment ceiling panels between FR47 and FR59. Refer to AMM 25-55-11, Page block 401 Refer to Drawing(s) : D25570048000 Sheet(s) 1 1 Remove and retain these items as shown in drawing D25570048000, Sheet 1 : 1 bumper D2557165020000 Item A 2 bumper D2557165620000 Item B 2 bumper D2557165720200 Item C 2 rail D2558501900000 Item D 1 rail D2558503100000 item E

NOTE : Retain the Items A thru E. 2 Remove and retain the AFT cargo compartment ceiling panels 151BC and 151DC Refer to AMM 25-55-11, Page block 401 3 Remove and discard these items as shown in drawing D25570048000, Sheet 1 : 1 panel D2557030000000 Item (100) discard 1 panel D2557031000000 Item (102) discard (ac) Remove and discard the track between FR47 and FR52 and the YZ-latches at FR47, FR48, FR49, FR50 and FR51. Refer to Drawing(s) : D25572631000 Sheet(s) 1 thru 3 1 Remove and discard these items as shown in drawing D25572631000, Sheet 1, ’PRE MOD’, Details X1-2 and Y1-3 : 1 track D2557221400800 Item (001) discard 12 roller 2847T100-1 Item (002) discard 60 bolt MS21250-03006 Item (003) discard 12 bolt MS21250-03008 Item (004) discard 72 nut NAS1726-3E Item (005) discard 10 YZ-latch D2557235000400 Item (006) discard DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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28 screw NAS1102-3-10 Item (007) discard 28 nut NAS1726-3E Item (008) discard

2 bolt NSA5042C05-165 Item (010) discard 2 nut NAS1726-4E Item (011) discard 2 bearing D2557226520000 Item (013) discard 4 washer D2557226420000 Item (014) discard 2 block D2557226120000 Item (016) discard 2 strap D2557225320600 Item (021) discard 2 strap D2557225320700 Item (022) discard 4 bolt MS21250-04004 Item (027) discard 4 nut MS21042-4 Item (028) discard 4 washer NAS1149C0463R Item (029) discard 2 washer NAS1149F0563P Item (034) discard (ad) Remove the screwed brackets for the old wire routing between FR46 and FR50. Refer to Drawing(s) : D92492244000 Sheet(s) 1, 2, 4, 6 and 8 1 Remove these items between FR46 and FR47 as shown in drawing D92492244000, Sheet 2, Section A-A2.

a Remove and discard these items : 6 bracket D9249177920000 Item (018) discard 3 bracket D9249177720400 Item (019) discard 1 bracket D9249177820000 Item (020) discard 1 bracket D9249177820100 Item (021) discard 2 bracket D9249180800000 Item (022) discard 2 Remove this item at FR47 as shown in drawing D92492244000, Sheet 4, Section C-C4.

a Remove and discard this item : 1 bracket D9249180921000 Item (023) discard 3 Remove these items at FR48 as shown in drawing D92492244000, Sheet 6, Section E-E6.

a Remove and discard these items : 1 bracket D9249180921400 Item (029) discard 1 bracket D9249180921200 Item (031) discard 7 bracket ABS0355-01 Item (040) discard 7 bracket ABS0355-02 Item (041) discard 7 washer NSA935514-03 Item (042) discard 4 Remove these items at FR49 as shown in drawing D92492244000, Sheet 8, Section G-G8.

a Remove and discard these items : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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6 bracket ABS0355-01 Item (040) discard 6 bracket ABS0355-02 Item (041) discard 6 washer NSA935514-03 Item (042) discard 3 pin DAN364-02 Item (043) discard (ae) Remove the brackets for the old wire routing between FR46 and FR50. Refer to Kit 281118D70R01 Refer to Drawing(s) : D92492243000 Sheet(s) 1 thru 13 and 21 1 Remove this item between FR46 and FR47 as shown in drawing D92492243000, Sheet 2, Section A-A2.

a Remove and discard this item : 6 bracket D9249178000000 Item (003) discard NOTE : Closing of the rivet holes is not necessary because the attachment structure of the partition panels is replaced by the drawing D53975018000. 2 Remove this item between FR46 and FR47 as shown in drawing D92492243000, Sheet 2, Detail W.

a Remove and discard this item : 2 bracket D9249179320000 Item (004) discard and close the holes with this item : 4 rivet LN9198-3208BF Item 632 3 Remove these items at FR47 as shown in drawing D92492243000, Sheet 4, Detail Z.

a Remove and discard this item : 1 bracket D9249172120000 Item (005) discard 1 bracket D9249181820200 Item (006) discard 1 bracket D9249171620400 Item (008) discard 1 bracket D9249178000400 Item (009) discard and close the holes, except the holes of the Item (009), with this item : 2 rivet DIN65399-3208BF Item 621 13 rivet LN9198-3208BF Item 632 4 Remove this item at FR48 as shown in drawing D92492243000, Sheet 6, Section E-E6.

a Remove and discard this item : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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2 bracket A9249635720200 Item (010) discard NOTE : Closing of the rivet holes is not necessary because the crossbeam is replaced by the drawing D53470075004. 5 Remove this item at FR48 as shown in drawing D92492243000, Sheet 6, Sections C-C, D-D, Q-Q and Detail X.

a Remove and discard this item : 7 bracket A9249635720200 Item (010) discard and close the holes with this item : 14 rivet LN9198-3208BF Item 632 6 Remove this item at FR49 as shown in drawing D92492243000, Sheet 8, Section G-G08, Detail Z

a Remove and discard this item : 3 bracket A9249635720200 Item (010) discard NOTE : Closing of the rivet holes is not necessary because the crossbeam is replaced by the drawing D53470075004. 7 Remove this item at FR49 as shown in drawing D92492243000, Sheet 8, Sections B-B, C-C and D-D.

a Remove and discard this item : 6 bracket A9249635720200 Item (010) discard and close the holes with this item : 12 rivet LN9198-3208BF Item 632 8 Remove this item at FR50 as shown in drawing D92492243000, Sheet 10, Section J-J10.

a Remove and discard this item : 1 bracket D9249177520000 Item (012) discard NOTE : Closing of the rivet holes is not necessary because the crossbeam is replaced by the drawing D53470075004. 9 Remove this item at FR52 as shown in drawing D92492243000, Sheet 21, Section L-L21.

a Remove and discard this item : 1 bracket A9249635720200 Item (010) discard DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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(af) Install the corner fittings between FR46 and FR47 at -Y1292 and +Y1292. Refer to Kit 281118D05R06 Refer to Drawing(s) : D53372362000 Sheet(s) 1 and 3 1 Install the fittings between FR46 and FR47 at +Y1292 as shown in Detail Z1-3.

a Put these items in position : 1 fitting D5337217220000 Item 006 1 fitting D5337217220100 Item 007

b Drill the holes and open the holes to final dimension.

c Install these items : 1 fitting D5337217220000 Item 006 1 fitting D5337217220100 Item 007 with : 2 collar NSA5075-5 Item 804 20 collar NSA5075-6 Item 806

2 pin DAN5-5-7 Item 947 2 pin DAN5-6-6 Item 966 8 pin DAN5-6-7 Item 967 3 pin DAN5-6-9 Item 969 3 pin DAN5-6-11 Item 971 4 pin DAN5-6-13 Item 973 2 Install the fittings between FR46 and FR47 at -Y1292 as shown in Detail Z1-3.

a Put these items in position : 1 fitting D5337217220000 Item 006 1 fitting D5337217220100 Item 007

b Drill the holes and open the holes to final dimension.

c Install these items : 1 fitting D5337217220000 Item 006 1 fitting D5337217220100 Item 007 with : 2 washer NAS1149D0363K Item 458 2 bolt NSA5031-3-14 Item 460 2 nut NAS1726-3E Item 462 2 collar NSA5075-5 Item 804 18 collar NSA5075-6 Item 806

2 pin DAN5-5-7 Item 947 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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2 pin DAN5-6-6 Item 966 8 pin DAN5-6-7 Item 967 3 pin DAN5-6-9 Item 969 3 pin DAN5-6-11 Item 971 2 pin DAN5-6-13 Item 973 (ag) Replace fasteners between FR42 and FR46 at several places. 1 Replace the fasteners between FR44 and FR46 between +Y1292 to +Y1650 and -Y1292 to -Y1650. Refer to Kit 281118D05R06 Refer to Drawing(s) : D53372362000 Sheet(s) 4

a Remove the existing rivets, drill the holes to final dimension and install these items as shown in Detail Y4-4 : 210 collar NSA5076-6 Item 816 4 pin DAN6-6-5 Item 865 166 pin DAN5-6-5 Item 965

40 pin DAN5-6-6 Item 966 2 Replace the fasteners between FR44 and FR46 between +Y765 to +Y1292 and -Y765 to -Y1292. Refer to Drawing(s) : D53371046000 Sheet(s) 1

a Remove the existing rivets, drill the holes to final dimension and install these items as shown in drawing D53371046000, Sheet 1 : 20 pin DAN5-6-6 Item 023

4 pin DAN5-6-7 Item 024 24 collar NSA5076-6 Item 027 196 rivet LN9198-4812CF Item 029 8 rivet LN9198-4814CF Item 030 NOTE : Items 023, 024, 027, 029 and 030 are contained in Kit Kit 281118D61R00 3 Replace the fasteners between FR42 and FR43 at +Y1650 and -Y1650. Refer to Drawing(s) : D53372362000 Sheet(s) 4 D32170220004 Sheet(s) 5 D32170220005 Sheet(s) 5

a If necessary, remove the MLG torque tube assembly (Refer to AMM 32-33-17, Page block 401) and the shafts for access. Refer to Drawing(s) : D32170220004 Sheet(s) 5 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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D32170220005 Sheet(s) 5 b Remove the existing rivets, drill the holes to final dimension and install these items as shown in Detail X4-4 : 12 pin DAN5-6-4X Item 764

8 pin DAN5-6-5X Item 765 8 pin DAN5-6-6X Item 766 2 pin DAN5-6-7X Item 767 2 collar NSA5075-6 Item 806 30 collar DAN11-6X Item 807

2 pin DAN5-6-8 Item 968

c If removed, install the MLG torque tube assembly (Refer to AMM 32-33-17, Page block 401. and the shafts. Refer to Drawing(s) : D32170220004 Sheet(s) 5 D32170220005 Sheet(s) 5 4 Replace the fasteners at FR43, STGR28 LH/RH. Refer to Drawing(s) : D53372362000 Sheet(s) 3

a Remove the existing rivets, drill the holes to final dimension and install these items as shown in Detail T1-3 : 6 collar DAN11-6X Item 807 6 pin DAN5-6-6X Item 766 (ah) Install the bonding brackets between FR42 and FR43 and between +Y254 and +Y765. Refer to Kit 281118D61R00 Refer to Drawing(s) : D53371046000 Sheet(s) 1 1 Put this item in position as shown in drawing D53371046000, Sheet 1, Section K1-K1 : 2 angle A9249175120000 Item 001 2 Drill the additional holes, open the holes to final dimension and install this item : 2 angle A9249175120000 Item 001

with : 12 rivet LN9198-3208BF Item 028 (ai) Drill the hole between FR42 and FR43 for fuel/vent shroud drain system. Refer to Kit 281118D61R00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Refer to Drawing(s) : D53371046000 Sheet(s) 1 1 Drill one hole with 19.1 mm to 19.3 mm (0.752 in. to 0.759 in.) diameter as shown in drawing D53371046000, Sheet 1, Section H1-H1. 2 Deburr the hole. (aj) Install the girder plates for the fuel/vent lines between FR42 and FR46 between +Y254 and -Y254. Refer to Kit 281118D61R00 Refer to Drawing(s) : D53371046000 Sheet(s) 2 1 Install the girder plate at FR42.

a Put this item in position as shown in Section B1-B2 : 1 plate D5337312600000 Item 002

b Mark and drill the holes for the bolts.

c Install this item : 1 plate D5337312600000 Item 002 with : 2 strap D5337312420000 Item 004 4 bolt NAS6703U7 Item 005 4 bolt NAS6703U5 Item 006 8 nut NAS1726C3P Item 007 8 washer NAS1149C0332R Item 008 2 Install the girder plate at FR43. Refer to Drawing(s) : D53371046000 Sheet(s) 3

a Put this item in position as shown in Section D1-D3 : 1 plate D5337312000000 Item 003

b Mark and drill the holes for the bolts.

c Install this item : 1 plate D5337312000000 Item 003 with : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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2 strap D5337312420000 Item 004 4 bolt NAS6703U7 Item 005 4 bolt NAS6703U5 Item 006 8 nut NAS1726C3P Item 007 8 washer NAS1149C0332R Item 008 3 Remove the shear plate at FR46 between +Y254 and -Y254. Refer to Drawing(s) : D53371046000 Sheet(s) 4

a Remove and discard this item as shown in Section E1-E4 : 1 shear plate D5337105820000 Item (034) discard 4 Install the girder plate at FR46. Refer to drawings : D53371046000 Sheet(s) 5 D53372362000 Sheet(s) 6

a Put this item in position as shown in drawing D53371046000, Sheet 5, Section F1-F5 : 1 plate D5337107420200 Item 009

b Transfer drill the holes to the plate, Item 009, and open the holes to final dimension.

c Install this item as shown in drawing D53371046000, Sheet 5, Sections F1-F5 and C5-C5 : 1 plate D5337107420200 Item 009 with : 2 pin DAN6-6-4 Item 021 4 pin DAN5-6-4 Item 022 6 collar NSA5075-6 Item 025 8 rivet LN9198-4012CF Item 035 10 pin DAN5-5-7 Item 036

8 pin DAN5-5-6 Item 037 12 collar NSA5075-5 Item 038

6 collar NSA5076-5 Item 039

d Put these items in position as shown in drawing D53371046000, Sheet 5, Sections F1-F5, B5-B5 and Detail A5-5 : 1 wall D5337311520200 Item 010 1 plate D5337311920200 Item 011 2 angle D5337309820000 Item 012 2 stiffener D5337307220100 Item 013 1 stiffener D5337307220000 Item 014 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 profile D5337312120400 Item 015 1 profile D5337312120600 Item 016 1 profile D5337312120700 Item 017 1 profile D5337312120200 Item 018

e Transfer drill the holes, drill the additional holes, open all holes to final dimension and install with these items as shown in drawing D53371046000, Sheet 5, Sections F1-F5, B5-B5 and A5-A5 and Detail A5-5 : 15 rivet LN9198-4009CF Item 031

3 rivet LN9198-4010CF Item 032 10 rivet LN9198-4011CF Item 033 and with these items as shown in drawing D53372362000, Sheet 6, Details C1-6 and A6-6 : 12 bolt ASNA0082A302 Item 435

2 bolt ASNA0082A303 Item 436 4 bolt ASNA0082A304 Item 438 15 bolt ASNA0082A305 Item 440

1 bolt ASNA0082A306 Item 442 12 collar NSA5075-5 Item 804

3 pin DAN7-5-5 Item 955 9 pin DAN7-5-6 Item 956

f Put this item at the wall, Item 010, in position as shown in drawing D53371046000, Sheet 5, Sections F1-F5 : 1 profile D5337313420000 Item 019

g Drill the holes, open the holes to final dimension and install with these items : 3 pin DAN7-5A5 Item 020 3 collar ABS0258-5C Item 026 (ak) Drill the holes into FR46 between STGR42 LH and STGR43 LH. Refer to Kit 281118D05R06 Refer to Drawing(s) : D53372362000 Sheet(s) 6 1 Drill one hole with 22.0 mm (0.866 in.) diameter and two holes with 5.6 mm (0.22 in.) diameter as shown in Detail A7-6. 2 Deburr the holes. (al) Modify the structure of FR47 between STGR35 LH to STGR35 RH. Refer to Kit 281118D05R06 Refer to Drawing(s) : D53372362000 Sheet(s) 5, 7, 8 and 9 1 Replace the fitting at FR47 at STGR44 as shown in Detail A1-A5. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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a Remove and discard the fitting : 1 fitting D5347008120200 Item (202) discard

b Put this item in position : 1 fitting D5337219020200 Item 012

c Transfer drill the holes and open the holes to final dimension. d Install this item : 1 fitting D5337219020200 Item 012 with : 5 rivet LN9198-4814CF Item 648 10 collar NSA5075-6 Item 806 10 pin DAN5-6-5 Item 965 2 Replace the supports at FR47 at STGR35 LH/RH, STGR36L LH/RH, STGR39 LH/RH and STGR40 LH/RH as shown in Detail A1-A5.

a Remove and discard the supports : 4 support (LH) D5347100920000 Item (206) discard 4 support (RH) D5347100920100 Item (207) discard

b Put these items in position : 4 support (LH) D5347100920090 Item 048 4 support (RH) D5347100920190 Item 049

c Transfer drill the holes, open all holes and all countersinks to the final dimension. d Install these items : 4 support (LH) D5347100920090 Item 048 4 support (RH) D5347100920190 Item 049 with : 32 rivet LN9198-4014CF Item 640 3 Install the angles at FR47 between STGR36 LH/RH and STGR40 LH/RH as shown in Section A1-A5 and in Details Y1-8 and U1-9.

a Remove the existing fasteners between the affected stringers. b Put this item between the affected stringers in position : 8 angle D5337215920200 Item 016 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 240 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

c Transfer drill the holes from the skin panel to the angles. d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install this item : 8 angle D5337215920200 Item 016 with : 24 rivet LN9198-4814CF Item 648 34 collar DAN11-6X Item 807

2 pin DAN5-6-7X Item 767 28 pin DAN5-6-8X Item 768

2 pin DAN5-6-10X Item 770 2 pin DAN5-6-12X Item 772 4 Install the angles at FR47 between STGR35 LH/RH and STGR36 LH/RH as shown in Section A1-A5 and in Detail Y1-8.

a Remove the existing fasteners between the affected stringers. b Put these items between the affected stringers in position : 1 angle (LH) D5337215920400 Item 018 1 angle (RH) D5337215920500 Item 019

c Transfer drill the holes from the skin panel to the angle. d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install these items : 1 angle (LH) D5337215920400 Item 018 1 angle (RH) D5337215920500 Item 019 with : 6 rivet LN9198-4814CF Item 648 8 collar DAN11-6X Item 807 6 pin DAN5-6-8X Item 768 2 pin DAN5-6-10X Item 770 5 Install the angle at FR47 between STGR40 LH and STGR41 LH as shown in Section A1-A5 and in Detail Y1-8.

a Remove the existing fasteners between the affected stringers. b Put this item between the affected stringers in position : 1 angle D5337215920000 Item 014 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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c Transfer drill the holes from the skin panel to the angle. d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install this item : 1 angle D5337215920000 Item 014 with : 3 rivet LN9198-4814CF Item 648 4 collar DAN11-8X Item 810 4 pin DAN5-8-8X Item 888 6 Install the angle at FR47 between STGR40 RH and STGR41 RH as shown in Details Y5-5 and U1-9.

a Remove the existing fasteners between the affected stringers. b Put this item between the affected stringers in position : 1 angle D5337215920600 Item 020

c Transfer drill the holes from the skin panel to the angle. d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install this item : 1 angle D5337215920600 Item 020 with : 3 rivet LN9198-4814CF Item 648 3 collar DAN11-8X Item 810 3 pin DAN5-8-9X Item 889 7 Remove the angles at FR47 at STGR37 LH/RH and STGR38 LH/RH as shown in Section A1-A5.

a Remove and discard these items : 2 angle (LH) D5347104120000 Item (212) discard 2 angle (RH) D5347104120100 Item (213) discard 8 Replace the fittings at FR47 between STGR37 LH/RH and STGR38 LH/RH as shown in Section A1-A5.

a Remove and discard these items : 1 fitting (LH) D5337219220200 Item (204) discard DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 fitting (RH) D5337219220300 Item (205) discard

b Put these items in position : 1 fitting (LH) D5337219220000 Item 008 1 fitting (RH) D5337219220100 Item 009

c Put these items at STGR37 LH/RH in position : 1 angle (LH) D5347104120090 Item 050 1 angle (RH) D5347104120190 Item 051

d Transfer drill the holes and open the holes to final dimension.

e Install these items : 1 fitting (LH) D5337219220000 Item 008 1 fitting (RH) D5337219220100 Item 009 1 angle (LH) D5347104120090 Item 050 1 angle (RH) D5347104120190 Item 051 with : 8 pin DAN7-6-6X Item 566 4 rivet LN9198-4014CF Item 640 8 rivet LN9198-4814CF Item 648 4 rivet LN9198-5614CF Item 656 22 collar NSA5075-6 Item 806

8 collar DAN12-6X Item 817 16 pin DAN5-6-5 Item 965

2 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 9 Install the fittings at FR47 between STGR38 LH/RH and STGR39 LH/RH as shown in Section A1-A5.

a Put these items at FR47 in position : 1 fitting (LH) D5337219120200 Item 010 1 fitting (RH) D5337219120300 Item 011

b Drill the holes and open the holes to final dimension.

c Install these items : 1 fitting (LH) D5337219120200 Item 010 1 fitting (RH) D5337219120300 Item 011 with : 12 rivet LN9198-4814CF Item 648 16 collar NSA5075-5 Item 804 16 pin DAN5-5-5 Item 945 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 0 Install the nuts at FR47 as shown in Section A1-A5.

a Drill the four holes 5.6 mm (0.220 in.) diameter for the nuts. b Put the nuts, Item 046, in position.

c Drill the holes and countersink the holes for the rivets. d Install these items : 4 nut NAS1791A3-1 Item 046 with : 8 rivet NAS1097AD3-10 Item 524 1 1 Remove the support at FR47 at STGR43 LH as shown in Section A1-A5.

a Remove and discard this item : 1 support D5347465720300 Item (200) discard 1 2 Remove the nuts at FR47 as shown in Detail C5-5.

a Remove and discard these items : 2 nut NAS1068C3 Item (214) discard

b Close the holes with : 4 rivet NAS1097AD3-10 Item 524 1 3 Drill twelve holes with 5.6 mm (0.220 in.) diameter as shown in Details A5-5 and B5-5. (am) Modify the structure between FR47 and FR48 at STGR38 LH/RH and STGR43 LH. Refer to Kit 281118D05R06 Refer to drawing : D53372362000 Sheet(s) 7 1 Remove the nuts at STGR38 LH and STGR38 RH as shown in Detail W1-7.

a Remove and discard this item : 6 nut NAS1791A3-1 Item (216) discard 2 Remove the connections at STGR38 LH and STGR38 RH as shown in Detail W1-7.

a Remove and discard these items : 1 connection (LH) D5347101620400 Item (210) discard DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 244 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 connection (RH) D5347101620500 Item (211) discard 3 Install the plates, the sections and the connections at STGR38 LH and STGR38 RH as shown in Detail W1-7. Refer to drawing : D53372362000 Sheet(s) 7

a At STGR38 LH : Put these items in position : 1 plate D5337217400000 Item 024 1 section D5347449520800 Item 028 1 shim D5337601520600 Item 030 1 shim D5337601520800 Item 032 1 shim D5337601521000 Item 034 1 shim D5337601521200 Item 036 1 shim D5337601521400 Item 038 1 connection D5347101620490 Item 042 NOTE : Install the shims, Item 030, 032, 034, 036 and 038, as required. NOTE : Install the section, Item 028, together with the angle, Item 130. b At STGR38 RH : Put these items in position : 1 plate D5337217400100 Item 025 1 section D5347449520900 Item 029 1 shim D5337601520600 Item 030 1 shim D5337601520800 Item 032 1 shim D5337601521000 Item 034 1 shim D5337601521200 Item 036 1 shim D5337601521400 Item 038 1 connection D5347101620590 Item 043 NOTE : Install the shims, Item 030, 032, 034, 036 and 038, as required. NOTE : Install the section, Item 029, together with the angle, Item 134, at FR48.

c Transfer drill the holes from the skin panel and the stringer to the connections. d Drill the additional holes into the plates, sections and connections and open all holes and all countersinks to final dimension.

e Install these items at STGR38 LH : 1 plate D5337217400000 Item 024 1 section D5347449520800 Item 028 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 245 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 shim D5337601520600 Item 030 1 shim D5337601520800 Item 032 1 shim D5337601521000 Item 034 1 shim D5337601521200 Item 036 1 shim D5337601521400 Item 038 1 connection D5347101620490 Item 042 with : 6 rivet NAS1097AD4-10 Item 532 21 rivet LN9198-4014CF Item 640

1 pin DAN5-6-6X Item 766 4 pin DAN5-6-7X Item 767 13 pin DAN5-6-8X Item 768

1 pin DAN5-6-9X Item 769 6 collar NSA5075-6 Item 806 19 collar DAN11-6X Item 807

4 pin DAN5-6-5 Item 965 2 pin DAN5-6-9 Item 969

f Install these items at STGR38 RH : 1 plate D5337217400100 Item 025 1 section D5347449520900 Item 029 1 shim D5337601520600 Item 030 1 shim D5337601520800 Item 032 1 shim D5337601521000 Item 034 1 shim D5337601521200 Item 036 1 shim D5337601521400 Item 038 1 connection D5347101620590 Item 043 with : 6 rivet NAS1097AD-10 Item 532 21 rivet LN9198-4014CF Item 640

1 pin DAN5-6-6X Item 766 4 pin DAN5-6-7X Item 767 13 pin DAN5-6-8X Item 768

1 pin DAN5-6-9X Item 769 6 collar NSA5075-6 Item 806 19 collar DAN11-6X Item 807

4 pin DAN5-6-5 Item 965 2 pin DAN5-6-9 Item 969 4 Remove the connection at STGR43 LH as shown in Detail V1-7. Refer to drawing : D53372362000

a Remove and discard this item : 1 connection D5347100720400 Item (208) discard DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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5 Install the plate, the section and the coupling at STGR43 LH as shown in Detail V1-7. Refer to drawing : D53372362000

a Put these items at STGR43 LH in position : 1 plate D5337217320200 Item 022 NOTE 1 section D5337216020000 Item 026 1 coupling D5347100720600 Item 040 NOTE : Alternative PN D5337217320000 b Transfer drill the holes from STGR43 to the plate and the connection.

c Drill all additional holes in the plate and the section and open all holes and all countersinks to final dimension. d Install these items : 1 plate D5337217320200 Item 022 NOTE 1 section D5337216020000 Item 026 1 coupling D5347100720600 Item 040 with : 34 rivet LN9198-4014CF Item 640

4 pin DAN5-6-7X Item 767 4 pin DAN5-6-8X Item 768 2 collar NSA5075-6 Item 806 8 collar DAN11-6X Item 807 16 collar DAN11-8X Item 810

1 pin DAN5-8-8X Item 888 4 pin DAN5-8-9X Item 889 10 pin DAN5-8-10X Item 890

1 pin DAN5-8-11X Item 891 2 pin DAN5-6-7 Item 967 NOTE : Alternative PN D5337217320000 (an) Modify the structure at FR43 and FR44 between STGR21 LH/RH and STGR23 LH/RH. Refer to Kit 281118D05R06 Refer to Drawing(s) : D53372362000 Sheet(s) 8 1 Install the sections at FR43 and FR44 between STGR21 LH and STGR23 LH as shown in Detail X1-8.

a Put this item in position : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 247 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

3 section D5337602020000 Item 044

b Drill the holes and open the holes to final dimension.

c Countersink all additional holes in the skin panel. d Install these items : 3 section D5337602020000 Item 044 with : 21 collar NSA5075-6 Item 806

8 pin DAN6-6-5 Item 865 4 pin DAN6-6-6 Item 866 3 pin DAN5-6-4 Item 964 6 pin DAN5-6-5 Item 965 2 Install the sections at FR43 and FR44 between STGR21 RH and STGR23 RH as shown in Detail X1-8.

a Put this item in position : 3 section D5337602020100 Item 045

b Drill the holes and open the holes to final dimension.

c Countersink all additional holes in the skin panel. d Install these items : 3 section D5337602020100 Item 045 with : 21 collar NSA5075-6 Item 806

8 pin DAN6-6-5 Item 865 4 pin DAN6-6-6 Item 866 3 pin DAN5-6-4 Item 964 6 pin DAN5-6-5 Item 965 (ao) Install reinforcing angles between FR47 and FR49 at STGR1 LH/RH and STGR2 LH/RH and at FR48 between STGR8 LH/RH and STGR13 LH/RH. Refer to Kit 281118D05R06 Refer to Drawing(s) : D53372362000 Sheet(s) 9 and 10 1 Install the reinforcing angles between FR47 and FR48 at STGR1 LH/RH and STGR2 LH/RH as shown in Section D1-D10.

a Remove the fasteners in the affected areas. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 248 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

b Put these items in position : 4 shim D5337236220400 Item 052 2 angle (LH) D5347007421800 Item 152 2 angle (RH) D5347007421900 Item 153

c Drill the holes into the stringer and the skin panel. d Transfer drill the holes from the stringer to the angles and open all holes and to final dimension.

e Countersink all additional holes in the skin panel. f Install these items : 4 shim D5337236220400 Item 052 2 angle (LH) D5347007421800 Item 152 2 angle (RH) D5347007421900 Item 153 with : 64 rivet NAS1097AD5-12 Item 540 48 rivet LN9198-4014CF Item 640 12 collar NSA5075-6 Item 806 12 pin DAN5-6-3 Item 963 2 Install the reinforcing angles between FR48 and FR49 at STGR2 LH/RH as shown in Section D1-D10.

a Put these items in position : 1 angle (LH) D5347007420800 Item 156 1 angle (RH) D5347007420900 Item 157

b Drill the holes into the stringer and the skin panel and open the holes to final dimension.

c Countersink all additional holes in the skin panel. d Install these items : 1 angle (LH) D5347007420800 Item 156 1 angle (RH) D5347007420900 Item 157 with : 38 rivet NAS1097AD5-12 Item 540 36 rivet LN9198-4014CF Item 640 3 Install the reinforcing angles at FR48 between STGR8 LH/RH and STGR13 LH/RH as shown in Section C1-C9.

a Put these items in position : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 249 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 angle (LH) D5337036521400 Item 150 1 angle (RH) D5337036521500 Item 151

b Drill the holes and open the holes to final dimension.

c Install these items : 1 angle (LH) D5337036521400 Item 150 1 angle (RH) D5337036521500 Item 151 with : 52 rivet LN9198-4014CF Item 640 (ap) Install the struts at the beam between FR46 and FR47. Refer to Kit 281118D05R06 Refer to Drawing(s) : D53372362000 Sheet(s) 2 and 3 1 Install these items as shown in Details A1-2 and Z1-3 :

2 strut D5337218500000 Item 002 4 strut D5337218600000 Item 004

with : 2 bolt MS21250-09024 Item 464 2 nut NAS1726-9E Item 466 2 washer MS20002C9 Item 468 4 bolt MS21250-06018 Item 470 4 nut NAS1726-6E Item 472 4 washer MS20002C6 Item 474

NOTE : Tighten the nuts temporarily. The final attachment of the struts is possible after the installation of the attachment structure of the partition panels. (aq) Install the brackets at FR46 between +Y254 to +Y765 and -Y254 to -Y765. Refer to Kit 281118D05R06 Refer to Kit 281118D09R00 Refer to drawings : D53372362000 Sheet(s) 4 D53372366000 Sheet(s) 1 1 Remove the existing fasteners in the affected areas. 2 Put this item in position as shown in the drawing D53372366000, Sheet 1, Details Z1-1 and Y1-1 : 2 bracket D5337142320000 Item 001 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 250 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

3 Transfer drill the holes, drill the additional holes and open all holes to final dimension as shown in the drawings D53372362000, Sheet 4, Detail W4-4 and D53372366000, Sheet 1, Details Z1-1 and Y1-1. 4 Install this item : 2 bracket D5337142320000 Item 001

with : 26 pin DAN5-5-3 Item 002 26 collar NSA5075-5 Item 003 46 collar NSA5075-6 Item 806 34 pin DAN5-6-6 Item 966 12 pin DAN5-6-8 Item 968 NOTE : Items 806, 966 and 968 are contained in Kit 281118D05R06. (ar) Modify the laying of the hydraulic tubes between FR46 and FR50. Refer to Kit 281118D82R01 For connecting of hydraulic tubes with PERMASWAGE fittings (Refer to AMM 20-23-11, Page block 201). Refer to Drawing(s) : D93070515000 Sheet(s) 1 thru 8 1 Remove the attachment parts and the hydraulic tubes between FR46 and FR49 as shown in drawing D93070515000, Sheets 2, 3 and 8 :

a Remove and retain these items as shown in the table in drawing D93070515000, Sheet 8 : 3 spacer NSA5586-A Item A 10 bolt NAS67703U18 Item B 13 washer NAS1149D0363K Item C

4 washer NAS1149C0332R Item D 2 clamp A93480340206 Item E 4 clamp D93470284224 Item F 4 clamp D93470286226 Item G 2 clamp NSA5516-11NJ Item H 3 clamp NSA5516-14NJ Item J 2 clamp NSA5516-22NJ Item K 1 clamp NSA5519-4 Item L 1 clamp NSA5519-6 Item M 4 sleeve D93470249200 Item N 1 lead E0089-16-100 Item P 1 lead E0089-06-100NN Item Q 4 bolt A102-1/2D Item R 2 screw NAS1100-06-5 Item S 3 screw NAS1096-3-7 Item T 4 cover D9347075620400 Item U 2 cover D9347075621200 Item V DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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NOTE : Retain the Items A thru V. b Remove and discard these items : 1 tee ASNA37520120812 Item (011) discard 2 sleeve D93470249200 Item (012) discard 2 union NSA855006D4 Item (013) discard 1 union NSA855006-6 Item (014) discard 2 union NSA855006-8 Item (015) discard 2 clamp D93470286226 Item (023) discard 4 washer NAS1149D0316K Item (025) discard 2 spacer NSA5586-A Item (032) discard 5 tie NSA935401-05 Item (033) discard 4 nut MS21042-3 Item (034) discard 2 nut NAS679C06 Item (036) discard 1 tube D29170901006 Item (039) discard 1 tube D32470911002 Item (042) discard 1 tube D32470901002 Item (043) discard 1 tube D32470901010 Item (044) discard 1 tube D32470911004 Item (045) discard 1 tube D32470911006 Item (046) discard 1 tube D27770001022 Item (052) discard 1 tube D27770011018 Item (055) discard 1 tube D29170901004 Item (056) discard 1 tube D32470901028 Item (083) discard 1 tube D32470901032 Item (084) discard 17 nut NSA5066-3-1 Item (085) discard

3 cable tie NSA935401-06 Item (086) discard 3 cable tie NSA935401-04 Item (087) discard

c Remove and discard these items as shown in drawing D93070515000, Sheet 2, View A2-2 : 1 bracket D93570727202 Item (005) discard 3 rivet LN9198-3210BF Item (099) discard and close the holes at FR46 with this item : 3 rivet LN9198-3210CF Item 198 2 Install the brackets at FR46 as shown in drawing D93070515000, Sheet 4, View A4-4 :

a Put these items in position : 1 bracket D9357070820000 Item 191 1 bracket D9357045500000 Item 192 drill the additional holes and install with this item : 4 rivet LN9198-3210BF Item 199

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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3 Install the bracket between FR47 and FR48 at STGR39 LH as shown in drawing D93070515000, Sheet 7, Section A5-A7 :

a Put this item in position : 1 bracket D9357072520300 Item 108 drill the additional holes and install with this item : 2 rivet LN9198-3210BF Item 199 4 Shorten the length of the hydraulic tubes between FR49 and FR50 as shown in drawing D93070515000, Sheet 5. 5 Install the hydraulic tubes between FR46 and FR50 as shown in drawing D93070515000, Sheets 4 thru 8 :

a Put these items in position : 1 tee ASNA3752D120812 Item 111 2 union NSA855006D4 Item 113 2 union NSA855006-6 Item 114 2 union NSA855006-8 Item 115 1 union NSA855006D8 Item 116 1 tube D2917091100000 Item 139 1 tube D3247091600200 Item 142 1 tube D3247090600400 Item 143 1 tube D3247090101000 Item 144 1 tube D3247091600000 Item 145 1 tube D3247091100600 Item 146 1 tube D2707023100000 Item 152 1 tube D2917091100200 Item 155 1 tube D2917090100400 Item 156 1 tube D2777000102600 Item 157 1 tube D2777001102400 Item 158 1 tube D3247090600000 Item 183 1 tube D3247090600600 Item 184 2 elbow NSA855020-8 Item 188 NOTE : Shorten the tubes, Item 157 and 158, to the correct length. b Connect the hydraulic tubes (Refer to AMM 20-23-11, Page block 201).

c Tighten all connections of the hydraulic tubes. d Attach the hydraulic tubes with these items : 2 washer NAS1149D0363K Item 124 4 washer NAS1149C0332R Item 125 2 screw NAS1096-3-7 Item 128 1 spacer NSA5586-D Item 131 4 tie NSA935401-05 Item 133 4 nut MS21042-3 Item 134 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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2 nut NAS679C06 Item 136 17 nut NSA5066-3-1 Item 185

3 cable tie NSA935401-06 Item 186 3 cable tie NSA935401-04 Item 187 2 clamp A9348225520000 Item 190 1 clamp NSA5516A06NJ Item 194 1 clamp NSA5516A14NJ Item 195 and with these items : 3 spacer NSA5586-A Item A 10 bolt NAS67703U18 Item B 13 washer NAS1149D0363K Item C

4 washer NAS1149C0332R Item D 2 clamp A93480340206 Item E 4 clamp D93470284224 Item F 4 clamp D93470286226 Item G 2 clamp NSA5516-11NJ Item H 3 clamp NSA5516-14NJ Item J 2 clamp NSA5516-22NJ Item K 1 clamp NSA5519-4 Item L 1 clamp NSA5519-6 Item M 4 sleeve D93470249200 Item N 1 lead E0089-16-100 Item P 1 lead E0089-06-100NN Item Q 4 bolt A102-1/2D Item R 2 screw NAS1100-06-5 Item S 3 screw NAS1096-3-7 Item T 4 cover D9347075620400 Item U 2 cover D9347075621200 Item V NOTE : Items A thru V are retained parts. 6 Mark all positions of the spacers with polyurethane top coat (Mat. No. 16-018) as shown in drawing D93070515000, Sheet 4, Detail Y4-4. (as) Remove and retain the green hydraulic reservoir. Refer to AMM 29-11-41, Page block 401 Refer to Drawing(s) : D93070668000 Sheet(s) 1 thru 8 (at) Install the brackets for the fuel drain/vent systems between FR42 and FR43. Refer to Kit 281118D11R01 Refer to Drawing(s) : D93070668000 Sheet(s) 1 thru 8 1 Put these items in position as shown in Views A7 and A8 : 1 bracket D9357040100200 Item 112 1 bracket D9357040100300 Item 113 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 254 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 Drill the holes for the rivets. 3 Install these items : 1 bracket D9357040100200 Item 112 1 bracket D9357040100300 Item 113

with : 4 rivet DAN257-3264 Item 125 (au) Install the green hydraulic reservoir. Refer to AMM 29-11-41, Page block 401 (av) Install the beam between FR46 and FR47. Refer to Kit 281118D18R00 Refer to Drawing(s) : D28270998002 Sheet(s) 2 1 Remove the existing fasteners in the affected area. 2 Put this item in position as shown in Detail A2-2 : 1 beam D2827099720000 Item 000

NOTE : Ensure that the reference holes are in line. 3 Transfer drill the holes from aircraft structure to the beam and open the holes to final dimension. 4 Install this item : 1 beam D2827099720000 Item 000

with : 8 bolt NSA5031-3-10 Item 770 8 nut NAS1726C3P Item 807 8 washer NAS1149C Item 808 (aw) Install the fuel transfer line between FR41 and FR47. Refer to Kit 281118D13R01 Refer to Drawing(s) : D28270972002 Sheet(s) 7 thru 12 1 Install the fuel transfer line between FR41 and FR43.

a Install at the inner tube (which is installed at the top of the center tank at FR41) these items as shown in Detail Z8-8 : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 255 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 O-ring NSA8203-222 Item 057 1 nut ABS0107-150 Item 064 1 ring NSA840003-150 Item 065

b Put at the outer tube, Item 002, these items in position as shown in Details Y8-8 and Z8-8 : 1 O-ring NSA8203-152 Item 054 1 O-ring NSA8203-230 Item 059

c Install these items at the inner tube, Item 004, as shown in Details Y8-8 and Z8-8 : 2 washer NAS1149C0332R Item 083 2 nut NAS1291C3M Item 084 2 lead E0088-10-125NN Item 108 2 tubing NSA937210MB0300 Item 110 NOTE : Cut the tubing, Item 110, in three pieces. d Insert this item : 1 tube D2827093000200 Item 004 into : 1 tube D2827093100200 Item 002 and put them between FR41 and FR43 with these items temporarily in position : 1 flange D2827093320400 Item 000 1 O-ring NSA8203-154 Item 055

e Push the inner tube, Item 004, over the inner tube (which is installed at the top of the center tank at FR41) and connect the both tubes with the nut, Item 064, as shown in Detail Z8-8. f Connect the strap, Item 108, at the flange with these items as shown in Detail Z8-8 : 1 washer NAS1149C0332R Item 083 1 bolt NAS1303-2 Item 095

g Push the flange, Item 000, and the o-ring, Item 055, in position and install these items as shown in Detail A8-8 : 10 washer NAS1149C0432R Item 082

6 nut NAS1726-4E Item 085 4 bolt NAS1304-4 Item 086 2 bolt NAS1304-3 Item 100

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 256 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

h Install this item and secure with lockwire (Mat. No. 19-018) as shown in Section B8-B8 : 1 spring A2827090220200 Item 074

i Install these items as shown in Detail Z8-8 : 1 clamp NSA5519-25 Item 061 6 washer NAS1149C0332R Item 083 3 nut NAS1291C3M Item 084 3 bolt NAS1303-3 Item 096 1 lead E0089-10-125NN Item 102 1 lead E0089-10-250NN Item 112 2 Install the fuel transfer line between FR43 and FR46. Refer to Drawing(s) : D28270972002 Sheet(s) 8

a Insert this item as shown in Detail Y8-8 : 1 tube D2827093000000 Item 010 into : 1 tube D2827093100000 Item 008

b Install at the inner tube, Item 010, these items as shown in Detail Y8-8 : 1 O-ring NSA8203-222 Item 057 1 nut ABS0107-150 Item 064 1 ring NSA840003-150 Item 065

c Put at the outer tube, Item 008, this item in position as shown in Details Y8-8 and X8-8 : 2 O-ring NSA8203-230 Item 059

d Push over the outer tube, Item 008, these items temporarily as shown in Detail Y8-8 : 1 sleeve D2827093321400 Item 006 1 O-ring NSA8203-152 Item 054

e Put the tubes, Item 008 and 010, between FR43 and FR46 in position and connect the inner tube, Item 010, at the inner tube, Item 004, with the nut, Item 064, and install these items as shown in Detail Y8-8 and in Section D8-D8 : 2 washer NAS1149C0432R Item 082 2 nut NAS1726-4E Item 085 2 bolt NAS1304-9 Item 090 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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f Connect the strap, Item 108, at the tube, Item 010, with these items as shown in Detail Y8-8 : 1 washer NAS1149C0332R Item 083 1 nut NAS1291C3M Item 084

g Push the sleeve, Item 006, and the o-ring, Item 054, in position and install these items as shown in Section D8-D8 : 2 washer NAS1149C0432R Item 082 4 nut NAS1726-4E Item 085 2 bolt NAS1304-11 Item 092 2 bolt NAS1304-12 Item 093

h Install this item and secure with lockwire (Mat. No. 19-018) as shown in Section C8-C8 : 1 spring A2827090220200 Item 074

i Install these items as shown in Details Y8-8 and C8-C8 : 2 clamp NSA5519-25 Item 061 6 washer NAS1149C0332R Item 083 3 nut NAS1291C3M Item 084 3 bolt NAS1303-3 Item 096 1 lead E0089-10-125NN Item 102 1 lead E0089-41-100NN Item 105 3 Install the fuel transfer line between FR46 and FR47. Refer to Drawing(s) : D28270972002 Sheet(s) 8 and 10

a Install between FR46 and FR47, +Y254 and -Y254, this item as shown in Section A10-A10 : 1 bracket D2827094800000 Item 051 with : 4 washer NAS1149C0432R Item 082 4 bolt NAS1304-2 Item 098

b Push over the outer tube, Item 008, this item temporarily as shown in Detail X8-8 : 1 sleeve D2827093322400 Item 016

c Put at the inner tube, Item 010, these items in position as shown in Detail X8-8 : 1 spacer D2827093221200 Item 012 1 O-ring NSA8203-222 Item 057 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 258 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 O-ring NSA8203-226 Item 058 1 ring NSA840003-150 Item 065 1 nut ABS0107-200 Item 066 1 ring NSA840003-200 Item 067

d Install these items at the girder plate at FR46 as shown in Details X8-8 and F8-F8 : 1 flange D2827093222200 Item 014 1 tube D2827092700000 Item 018 1 O-ring NSA8203-152 Item 054 1 O-ring NSA8203-234 Item 060 2 washer NAS1149C0432R Item 082 2 nut NAS1726-4E Item 085 2 bolt NAS1304-9 Item 090

e Push the inner pipe of the tube, Item 018, over the spacer, Item 012, and install the nut, Item 066. f Connect the strap of the tube, Item 018, at the inner tube, Item 010, with these items as shown in Detail X8-8: 1 washer NAS1149C0332R Item 083 1 nut NAS1291C3M Item 084

g Push the sleeve, Item 016, at FR46 in position and install these items as shown in Details F8-F8 and F8-F8: 2 washer NAS1149C0432R Item 082 4 nut NAS1726-4E Item 085 2 bolt NAS1304-11 Item 092 2 bolt NAS1304-12 Item 093

h Install this item and secure with lockwire (Mat. No. 19-018) as shown in Section E8-E8 : 1 spring A2827090220200 Item 074

i Install these items as shown in Detail X8-8 and in Section E8-E8 : 1 clamp NSA5519-25 Item 061 4 washer NAS1149C0332R Item 083 2 nut NAS1291C3M Item 084 2 bolt NAS1303-3 Item 096 1 lead E0089-10-125NN Item 102

j Install at the tube, Item 018, these items as shown in Detail V8-10 and in Section A10-A10 : 1 flange D2827093222600 Item 020 1 O-ring NSA8203-151 Item 053 1 O-ring NSA8203-226 Item 058 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 259 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

with : 2 washer NAS1149C0432R Item 082 1 nut NAS1726-4E Item 085 1 bolt NAS1304-5 Item 087 2 bolt NAS1304-10 Item 091

k Install at the flange, Item 020, these items and secure with lockwire (Mat. No. 19-018) as shown in Detail V8-10: 1 PLXBLDR AN814-4DL Item 071 1 packing NSA8200-4 Item 072

l Install these items as shown in Detail V8-10 and in Section A10-A10 : 1 flange D2827093222800 Item 028 1 O-ring NSA8203-151 Item 053 with : 2 nut NAS1726-4E Item 085 2 bolt NAS1304-8 Item 089 2 bolt NAS1304-10 Item 091 (ax) Install the vent line between FR37 and FR47. Refer to Kit 281118D13R01 Refer to Drawing(s) : D28270972002 Sheet(s) 9 thru 12 1 Install the vent line between FR37 and FR42.

a Install between FR40 and FR41 this item as shown in Detail W9-11 : 1 bracket D2827093500000 Item 033 with : 4 nut NAS1726-4E Item 085 4 bolt NAS1304-2 Item 098

b Install at the inner tube (which is installed at the top of the center tank between FR37 and FR38) these items as shown in Detail U9-9 : 1 O-ring NSA8203-226 Item 058 1 nut ABS0107-200 Item 066 1 ring NSA840003-200 Item 067

c Put at the outer tube, Item 032, this item in position as shown in Details U9-9 and S9-10 : 2 O-ring NSA8203-234 Item 060 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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d Install these items at the inner tube, Item 034, as shown in Details U9-9 and S9-10 : 2 washer NAS1149C0332R Item 083 2 nut NAS1291C3M Item 084 1 lead E0088-10-125NN Item 108 1 lead E0088-10-200NN Item 109 1 tubing NSA937210MB0300 Item 110 1 tubing NSA937210MB0300 Item 111 NOTE : Cut the tubing, Item 111, in two pieces.

e Insert this item : 1 tube D2827092800400 Item 034 into : 1 tube D2827092900600 Item 032 and put them between FR37 and FR42 with these items temporarily in position : 1 flange D2827093320600 Item 030 1 O-ring NSA8203-156 Item 056

f Push the inner tube, Item 034, over the inner tube (which is installed at the top of the center tank between FR37 and FR38) and connect the both tubes with the nut, Item 066, as shown in Detail U9-9. g Attach the tube, Item 032, at the bracket, Item 033, between FR40 and FR41 with these items as shown in Detail W9-11 : 1 clamp D28270935002 Item 035 1 clamp D28270935004 Item 037 2 washer NAS1149C0332R Item 083 2 bolt NAS1303-3 Item 096

h Connect the strap, Item 108, at the flange with these items as shown in Detail U9-9 : 1 washer NAS1149C0332R Item 083 1 bolt NAS1303-2 Item 095

i Push the flange, Item 030, and the O-ring, Item 056, in position and install these items as shown in Detail A9-9: 10 washer NAS1149C0432R Item 082

6 nut NAS1726-4E Item 085 4 bolt NAS1304-4 Item 086 2 bolt NAS1304-3 Item 100

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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j Install this item and secure with lockwire (Mat. No. 19-018) as shown in Section B9-B9 : 1 spring A2827051700200 Item 075

k Install these items as shown in Detail U9-9 : 1 clamp NSA5519-30 Item 062 6 washer NAS1149C0332R Item 083 3 nut NAS1291C3M Item 084 3 bolt NAS1303-3 Item 096 1 lead E0089-10-125NN Item 102 1 lead E0089-10-250NN Item 112 2 Install the vent line between FR42 and FR43. Refer to Drawing(s) : D28270972002 Sheet(s) 9 thru 12

a Install at the inner tube, item 034, these Items as shown in Detail S9-10 : 1 O-ring NSA8203-226 Item 058 1 nut ABS0107-200 Item 066 1 retaining ring NSA840003-200 Item 067

b Push over the outer tube, item 032, this Item temporarily as shown in Detail S9-10 : 1 sleeve D2827093321200 Item 036

c Install at the girder plate at FR42 these items as shown in Detail S9-10 and in Section J10-J9 : 1 flange D2827093320800 Item 038 1 flange D2827093221600 Item 040 1 O-ring NSA8203-152 Item 054 1 O-ring NSA8203-234 Item 060 with : 4 washer NAS1149C0432R Item 082 2 nut NAS1726-4E Item 085 1 bolt NAS1304-8 Item 089 1 bolt NAS1304-10 Item 091

d Push the flange, Item 040, over the inner tube, Item 034, and install the nut, Item 066.

e Assemble these items as shown in Detail Q9-11 : 2 spacer A2827090120400 Item 031 1 tube D2827092800000 Item 044 1 tube D2827092900000 Item 046 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 tube D2827092900200 Item 048 1 O-ring NSA8203-152 Item 054 2 lead E0089-41-250NN Item 107 with : 2 washer NAS1149C0432R Item 082 6 nut NAS1726-4E Item 085 5 bolt NAS1304-5 Item 087 1 bolt NAS1304-6 Item 088

f Install at the tube, Item 044, these items as shown in Details S9-10 and T9-9 : 2 O-ring NSA8203-226 Item 058 2 nut ABS0107-200 Item 066 2 ring NSA840003-200 Item 067

g Install at the outer tubes, Items 046 and 048, this item as shown in Details S9-10 and T9-9 : 2 O-ring NSA8203-234 Item 060

h Push over the outer tube, Item 046, these items temporarily as shown in Detail S9-10 : 1 sleeve D2827093321000 Item 042 1 O-ring NSA8203-152 Item 054

i Push the inner tube, Item 044, into the flange, Item 040, and connect the nut, Item 066, as shown in Detail S9-10. j Connect the strap, Item 109, at the inner tube, Item 044, with these items as shown in Detail S9-10 : 1 washer NAS1149C0332R Item 083 1 nut NAS1291C3M Item 084

k Push the sleeves, 036 and 042, at the girder plate at FR42 in position and install these items as shown in Detail S9-10 and in Section F10-F9 : 4 washer NAS1149C0432R Item 082 4 nut NAS1726-4E Item 085 4 bolt NAS1304-14 Item 094

l Install these items and secure with lockwire (Mat. No. 19-018) as shown in Sections C10-C9 and D10-D9 : 2 spring A2827051700200 Item 075

m Install these items as shown in Details S9-10 and U9-10 and Section E10-E9 : 1 clamp NSA5519-30 Item 062 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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6 washer NAS1149C0332R Item 083 3 nut NAS1291C3M Item 084 3 bolt NAS1303-3 Item 096 1 lead E0089-10-200NN Item 104 1 lead E0089-41-100NN Item 105 1 lead E0089-41-200NN Item 106

n Install at the inner tube, 044, these items as shown in Detail T9-9 : 1 washer NAS1149C0332R Item 083 1 nut NAS1291C3M Item 084 1 lead E0088-10-200 Item 109 1 tubing NSA937210MB0300 Item 111

o Push over the outer tube, 048, this item temporarily as shown in Detail T9-9 : 1 sleeve D2827093321200 Item 036

p Install at the bracket at FR43 these items as shown in Detail T9-9 and in Section J9-J9 : 1 flange D2827093320800 Item 038 1 flange D2827093221600 Item 040 1 O-ring NSA8203-152 Item 054 1 O-ring NSA8203-234 Item 060 with : 4 washer NAS1149C0432R Item 082 2 nut NAS1726-4E Item 085 1 bolt NAS1304-8 Item 089 1 bolt NAS1304-10 Item 091

q Push the flange, 040, over the inner tube, item 044, and install the nut, 066. 3 Install the vent line between FR43 and FR46. Refer to Drawing(s) : D28270972002 Sheet(s) 9 thru 12

a Insert this item : 1 tube D2827092800200 Item 052 into : 1 tube D2827092900400 Item 050

b Put at the outer tube, Item 050, this item in position as shown in Details T9-9 and R9-11 : 2 O-ring NSA8203-234 Item 060 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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c Install at the inner tube, Item 052, these items as shown in Details T9-9 and R9-11 : 2 O-ring NSA8203-226 Item 058 2 nut ABS0107-200 Item 066 2 ring NSA840003-200 Item 067

d Push over the outer tube, Item 050, these items temporarily as shown in Detail T9-9 : 1 sleeve D2827093321000 Item 042 1 ring NSA8203-152 Item 054

e Put the tubes, Item 050 and 052, between FR43 and FR46, in position. f Push the inner tube, Item 052, into the flange, Item 040, at FR43 and install the nut, Item 066, as shown in Detail T9-9. g Connect the lead, Item 109, at the inner tube, Item 052, with these items as shown in Detail T9-9 : 1 washer NAS1149C0332R Item 083 1 nut NAS1291C3M Item 084

h Push the sleeves, Item 036 and 042, at the girder plate at FR43 in position and install these items as shown in Details T9-9 and F9-F9 : 4 washer NAS1149C0432R Item 082 4 nut NAS1726-4E Item 085 4 bolt NAS1304-14 Item 093

i Install these items and secure with lockwire (Mat. No. 19-018) as shown in Sections C10-C9 and D10-D9 : 2 spring A2827051700200 Item 075

j Install these items as shown in Details T9-9 and U9-10 and Section E9-E9 : 1 clamp NSA5519-30 Item 062 6 washer NAS1149C0332R Item 083 3 nut NAS1291C3M Item 084 3 bolt NAS1303-3 Item 096 1 lead E0089-10-200NN Item 104 1 lead E0089-41-100NN Item 105 1 lead E0089-41-200NN Item 106 4 Install the vent line between FR46 and FR47. Refer to Drawing(s) : D28270972002 Sheet(s) 9 thru 12

a Push over the outer tube, Item 050, this item temporarily as shown in Detail R9-11 : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 sleeve D2827093322200 Item 039

b Install these items at the girder plate at FR46 as shown in Detail R9-11 and in Section N11-N11 : 1 flange D2827093222200 Item 014 1 tube D2827092700000 Item 018 1 O-ring NSA8203-152 Item 054 1 O-ring NSA8203-234 Item 060 4 washer NAS1149C0432R Item 082 2 nut NAS1726-4E Item 085 1 bolt NAS1304-10 Item 091 1 bolt NAS1304-11 Item 092

c Push the inner pipe of the tube, Item 018, over the inner tube, Item 052, and install the nut, Item 066. d Connect the strap of the tube, Item 018, at the inner tube, Item 052, with these items as shown in Detail R9-11 : 1 washer NAS1149C0332R Item 083 1 nut NAS1291C3M Item 084

e Push the sleeve, Item 039, at FR46 in position and install these items as shown in Detail R9-11 and in Section N11-N11 : 4 washer NAS1149C0432R Item 082 4 nut NAS1726-4E Item 085 4 bolt NAS1304-11 Item 092

f Install this item and secure with lockwire (Mat. No. 19-018) as shown in Section K11-K9 : 1 spring A2827051700200 Item 075

g Install these items as shown in Detail R9-11 and P11-11 and in Section L11-L11 : 1 clamp NSA5519-30 Item 062 4 washer NAS1149C0332R Item 083 2 nut NAS1291C3M Item 084 2 bolt NAS1303-3 Item 096 1 lead E0089-10-160NN Item 103 1 lead E0089-41-100NN Item 105

h Install at the tube, Item 018, these items as shown in Detail V9-10 and in Section A10-A10 : 1 flange D2827093222600 Item 020 1 O-ring NSA8203-151 Item 053 1 O-ring NSA8203-226 Item 058 with : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 266 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 washer NAS1149C0432R Item 082 1 nut NAS1726-4E Item 085 1 bolt NAS1304-5 Item 087 2 bolt NAS1304-10 Item 091

i Install at the flange, Item 020, these items and secure with lockwire (Mat. No. 19-018) as shown in Detail V9-10: 1 PLXBLDR AN814-4DL Item 071 1 packing NSA8200-4 Item 072

j Install these items as shown in Detail V9-10 and in Section A10-A10 : 1 flange D2827093222800 Item 028 1 O-ring NSA8203-151 Item 053 with : 2 nut NAS1726-4E Item 085 2 bolt NAS1304-8 Item 089 2 bolt NAS1304-10 Item 091 (ay) Install the cover between FR46 and FR47 at the fuel transfer line and vent line. Refer to Kit 281118D19R00 Refer to Drawing(s) : D28270999004 Sheet(s) 3 1 Put this item in position as shown in Detail Z3-3 : 1 shield D2827099600400 Item 022 2 Transfer drill the two holes into the upper beam and open them to final dimension. 3 Install these items as shown in Detail A3-3 : 1 shim D2827098322400 Item 004 1 shield D2827099600400 Item 022

with : 8 bolt NAS1303-5 Item 006 2 bolt NAS1303-8 Item 010 10 washer NAS1149D0332K Item 014 (az) Install the shroud drain system between FR37 and FR48. Refer to Kit 281118D14R00 Refer to Drawing(s) : D28270973002 Sheet(s) 6 thru 10 1 Install this item between FR38 and FR39 as shown in Detail Y6-8 : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 bracket D2827094720000 Item 210

with : 4 bolt NAS1304-2 Item 030 4 nut NAS1726-4E Item 032 2 Install these items as shown in Details W6-8 and Z6-8 : 2 union MS21902D8 Item 000 2 packing NSA8200-8 Item 001 3 Connect this item at the vent shroud line as shown in drawing D28270973002, Sheet 6 : 1 tube D2827093603400 Item 100

and install these items as shown in Details Y6-8 and X6-8 and in Section B6-B8 : 4 washer NAS1149C0332R Item 007 1 screw NAS1096-3-8 Item 009 4 nut NAS1726-3E Item 010 2 screw NAS1096-3-7 Item 011 3 clamp MS21919WDE8 Item 014 1 clamp MS21919WDE48 Item 016 1 screw NAS1096-3-9 Item 024 1 bracket D2827098322800 Item 216 4 Install at the tube, Item 100, these items as shown in drawing D28270973002, Sheet 6 : 1 washer NAS1149C0332R Item 007 1 screw NAS1096-3-8 Item 009 1 clamp NSA5519-11 Item 035 1 nut NAS1291C3M Item 036 1 lead E0091-10-280NN Item 038 5 Connect this item at the fuel shroud line as shown in drawing D28270973002, Sheet 6 : 1 tube D2827093600200 Item 102

and connect the tube, Item 100, and the tube, Item 102, with this item : 1 tee MS21905D8 Item 005 6 Install these items between FR42 and FR43 as shown in Detail V6-8 : 1 elbow MS21907D8 Item 002 1 nut AN924-8D Item 003 1 washer NAS1149D1290K Item 004 1 washer NAS1149D1216H Item 023 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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and install this item as shown in drawing D28270973002, Sheet 6 : 1 tube D2827093602400 Item 124 7 Install these items as shown in Detail R6-8 : 3 washer NAS1149C0332R Item 007 2 screw NAS1096-3-8 Item 009 1 screw NAS1096-3-9 Item 024 2 strap E0090-10-125NN Item 025 1 clamp NSA5519-11 Item 035 1 nut NAS1291C3M Item 036 8 Install these items between FR42 and FR43 as shown in Details A6-7 and C6-9 : 1 tube D2827093603200 Item 108 1 tube D2827093602600 Item 126

with : 1 spacer NSA5527-03-16 Item 006 4 washer NAS1149C0332R Item 007 1 screw NAS1096-3-15 Item 008 3 screw NAS1096-3-8 Item 009 1 nut NAS1726-3E Item 010 2 clamp MS21919WDE8 Item 014 1 strap E0090-10-125NN Item 025 2 clamp NSA5519-11 Item 035 2 nut NAS1291C3M Item 036 9 Install this item in the keel beam as shown in drawing D28270973002, Sheet 6 : 1 hose 51263408-0840 Item 202

with : 6 washer NAS1149C0332R Item 007 6 screw NAS1096-3-8 Item 009 6 clamp MS21919WDE11 Item 015 1 0 Install these items at FR46 as shown in Detail S6-9 : 1 tee NAS1763D080808 Item 033 1 fitting D2827094320000 Item 204

with : 2 nut NAS1726-3E Item 010 2 screw NAS1096-3-10 Item 012 1 1 Install these items at FR46 as shown in Details B6-7, T6-8 and U6-8 : 1 tee MS21905D8 Item 005 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 tube D2827093601600 Item 116 1 tube D2827093602000 Item 120 1 tube D2827093603000 Item 130

with : 4 washer NAS1149C0332R Item 007 3 screw NAS1096-3-8 Item 009 3 nut NAS1726-3E Item 010 2 clamp MS21919WDE8 Item 014 1 screw NAS1096-3-9 Item 024 1 strap E0090-10-125NN Item 025 1 washer NAS1149D0316H Item 026 1 bolt NAS1303-2 Item 027 1 clamp NSA5575-7 Item 028 2 clamp NSA5519-11 Item 035 2 nut NAS1291C3M Item 036 1 strap E0090-10-200NN Item 037 1 lead E0091-10-280NN Item 038 1 2 Install these items between FR47 and FR48 as shown in Detail Q6-10 : 1 nut AN924-8D Item 003 1 washer NAS1149D1290K Item 004 1 tee MS21912D8 Item 013 1 washer NAS1149D1216H Item 023 1 3 Install these items between FR46 and FR48 as shown in Details Q6-10 and P10-10 : 1 tube D2827093603600 Item 136 1 tube D2827093600400 Item 138

with : 1 washer NAS1149C0332R Item 007 1 screw NAS1096-3-7 Item 011 1 clamp MS21919WDE8 Item 014 1 hose D56KAN002 Item 039 2 clamp ASNA0033-016 Item 040 1 4 Install these items as shown in Details P10-10 and S6-9 :

4 washer NAS1149C0332R Item 007 4 screw NAS1096-3-8 Item 009 2 strap E0090-10-125NN Item 025 4 clamp NSA5519-11 Item 035 4 nut NAS1291C3M Item 036 1 5 Install these items with sealant (Mat. No. 09-016) at the belly fairing as shown in Detail Q6-10 : 1 reducer MS21916D8-6 Item 017 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 packing NSA8200-6 Item 022 1 monitor L83A13-617 Item 206

with : 3 washer NAS1149C0432R Item 018 3 bolt NAS1304-4 Item 019

and install this item : 1 hose 513535E0107-090 Item 208 1 6 Install this item with adhesive (Mat. No. 08-010)as shown in Detail Q6-10 : 1 placard D2827094421400 Item 214 1 7 Install this item as shown in Detail Q6-10 : 1 tube D2827097600200 Item 134

NOTE : The connection to the cavity drain and monitoring system will be installed in para (5) (ba) 5

. (ba) Install the cavity drain and monitoring system between FR46 and FR50. Refer to Kit 281118D15R01 Refer to Drawing(s) : D28270974002 Sheet(s) 4 thru 6 1 Install these items between FR48 and FR49 as shown in Section C4-C5 : 1 nut AN924-8D Item 034 1 washer NAS1149D1290K Item 035 1 tee MS21912D8 Item 036 1 washer NAS1149D1216H Item 037 2 Install these items between FR48 and FR50 as shown in drawing D28270974002, Sheet 4 and in Details C4-C5 and D4-6: 1 tee MS21905D8 Item 021 1 elbow NAS1762D0808 Item 023 2 cap MS21914-8D Item 033 1 tube D2827097700400 Item 124 1 tube D2827097701200 Item 134

with : 3 clamp MS21919WDE8 Item 014 3 screw NAS1096-3-8 Item 016 4 washer NAS1149C0332R Item 017 1 nut NAS1291C3M Item 049

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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3 Install these items between FR49 and FR50 as shown in drawing D28270974002, Sheet 4 : 3 screw NAS1096-3-8 Item 016 3 washer NAS1149C0332R Item 017 3 nut NAS1291C3M Item 049 3 clamp NSA5519-11 Item 051 2 lead E0090-10-160NN Item 061 4 Install this item as shown in drawing D28270974002, Sheet 4 and Section B4-B6 : 1 tube D2827097700200 Item 122

with : 3 clamp MS21919WDE8 Item 014 3 screw NAS1096-3-8 Item 016 4 washer NAS1149C0332R Item 017 5 Install these items between FR46 and FR47 as shown in drawing D28270974002, Sheet 4, Section A4-A6 and in Detail Z4-4 : 1 tee MS21905D8 Item 021 1 elbow NSA855120-8D Item 022 1 tube D2827093701800 Item 130 1 tube D2827097701000 Item 132

with : 1 clamp MS21919WDE8 Item 014 3 screw NAS1096-3-8 Item 016 3 washer NAS1149C0332R Item 017 3 nut NAS1291C3M Item 049 3 clamp NSA5519-11 Item 051 2 clamp ASNA0033-016 Item 056 1 hose D56KAN002 Item 057 1 strap 0090-10-125NN Item 060 1 lead E0090-10-160NN Item 061

NOTE : The connection to the shroud drain and monitoring system will be installed in para (5) (az) 1 7

. NOTE : The connection to the APU fuel shroud system will be installed in para (5) (bb) 2 b

. 6 Install these items between FR47 and FR48 as shown in drawing D28270974002, Sheet 4 : 3 screw NAS1096-3-8 Item 016 3 washer NAS1149C0332R Item 017 3 nut NAS1291C3M Item 049 3 clamp NSA5519-11 Item 051 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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2 lead E0090-10-160NN Item 061 7 Install this item with sealant (Mat. No. 09-016) at the belly fairing as shown in Detail A5-5 and in Section C4-C5: 1 reducer MS21916D8-6 Item 025 1 packing NSA8200-6 Item 026 1 monitor L83A13-617 Item 202

with : 3 washer NAS1149C0432R Item 027 3 bolt NAS1304-4 Item 028

and install this item : 1 hose 513535E0107-090 Item 204 8 Install this item with adhesive (Mat. No. 08-010)as shown in Detail A5-5 : 1 placard D2827094421600 Item 216 (bb) Replace the APU fuel shroud drain tube in the keel beam area between FR42 and FR47. Refer to Kit 281118D83R01 Refer to Drawing(s) : D28271200000 Sheet(s) 1 and 2 1 Remove the APU fuel shroud drain tube in the keel beam area between FR42 and FR47 as shown in drawing D28271200000 ’BEFORE’, View B1-2 and Detail Z :

a Remove and retain this item : 7 clamp NSA5516-10NJ Item A NOTE : Retain the Item A. b Remove and discard this item : 1 tube D28270505006 Item (506) discard 2 Install the APU fuel shroud drain tubes in the keel beam area between FR42 and FR47 as shown in drawing D28271200000 ’AFTER’, View C1-2 and Detail Y :

a Install these items : 1 tube D2827050501600 Item 002 1 tube D2827050501400 Item 012 1 tee NSA855113-11C Item 021 with : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 273 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

7 clamp NSA5516-10NJ Item A NOTE : Item A are retained parts. b Connect the APU fuel shroud drain system with the cavity drain and monitoring system. (bc) Remove and discard the attachment parts of the cable harness in the AFT cargo compartment bilge area between FR46 and FR50. Refer to Drawing(s) : D92891803000 Sheet(s) 1, 2, 4, 6, 8, 10, 11 and 13 1 Remove and discard the attachment parts of the cable harness between FR46 and FR50.

a Remove and discard these parts : 5 spacer NSA5527-03-08 Item (008) discard 16 nut MS21042L3 Item (011) discard 12 screw NAS1096-3-8 Item (012) discard 77 nut NSA5066-08-2 Item (014) discard 81 washer NAS1149DN816K Item (015) discard 51 screw NAS1096-2-18 Item (024) discard 10 clamp MS21919WCH5 Item (025) discard 53 spacer NSA5527-03-01 Item (026) discard 13 washer NAS1149C0332R Item (028) discard

8 bulkhead NSA934710T11 Item (029) discard 14 washer NAS1149D0363K Item (030) discard

5 washer NAS1149D0332K Item (034) discard 6 bulkhead NSA934710T14 Item (046) discard 60 bracket NSA935504-01 Item (047) discard

4 spacer NSA5527-03-04 Item (048) discard 8 screw NAS1096-2-10 Item (049) discard 12 screw NAS1096-2-8 Item (050) discard

1 screw NAS1096-2-14 Item (051) discard 1 spacer NSA5527-03-03 Item (054) discard 5 bracket E0343-01 Item (066) discard 7 screw NAS1096-2-28 Item (067) discard 4 nut MS21042L08 Item (068) discard 1 clamp NSA935807-06 Item (069) discard 1 bracket NSA935513-07 Item (070) discard 3 bracket ABS0354-01 Item (071) discard 2 clamp NSA935807-12 Item (072) discard 2 washer NSA935808-01 Item (073) discard 3 nut MS21042L04 Item (074) discard 3 washer NAS1149DN416K Item (075) discard 3 screw NAS1100-04-8 Item (076) discard 5 socket NSA938004-08 Item (077) discard 5 cover NSA938005-08 Item (078) discard 3 bracket NSA935513-01 Item (079) discard 8 spacer NSA5527-03-02 Item (083) discard 1 guide D92491814056 Item (084) discard DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 guide D92491814058 Item (085) discard 12 washer D92491025200 Item (086) discard

1 screw NAS1096-2-43 Item (087) discard 1 strap D92491073004 Item (088) discard 2 spacer NSA5527-03-08 Item (089) discard 2 screw NAS1096-2-32 Item (090) discard 2 circle D92491733200 Item (091) discard 2 circle D92491733202 Item (092) discard 2 screw NAS1102-3-8 Item (093) discard 2 screw NAS1096-2-24 Item (094) discard 1 bracket E0660-01 Item (095) discard (bd) Remove the cable harnesses 4605VB, 4655VB, 4656VB, 4661VB, 4662VB, 4663VB, 4664VB, 4671VB, 4672VB, 4673VB, 4680VB, 4681VB, 4683VB, 4692VB, 4693VB, 4694VB and 4696VB. 1 Remove the cable harness 4605VB. Refer to Drawing(s) : D92991405000 Sheet(s) 1

a Disconnect the plugs 1997VC-A and 4RC2-A (VHF-antenna). b Loosen/remove and tag all attachment parts of the cable harness 4605VB to make later installation easier.

c Remove and discard the cable harness : 1 harness 4605VB D9299140500000 Item (001) discard 2 Remove the cable harness 4655VB. Refer to Drawing(s) : D92991455004 Sheet(s) 5

a Disconnect the plug from the receptacle and remove the receptacle 2975VC from the structure. b Disconnect the plugs (8XE2,8XE3,8XE4) from the constant speed motor(8XE).

c Disconnect the bonding point 6555VN. d Loosen/remove and tag all attachment parts of the cable harness 4655VB to make later installation easier.

e Remove and discard the cable harness : 1 harness 4655VB D9299145500400 Item (016) discard 3 Remove the cable harness 4656VB.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 275 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s) : D92991456002 Sheet(s) 3

a Disconnect the plug from the receptacle and remove the receptacle 2952VC from the structure. b Disconnect the plug from the receptacle and remove the receptacle 2954VC from the structure.

c Disconnect the plugs (8XE1,8XE2) from the constant speed motor(8XE). d Disconnect the bonding point 6554VN.

e Loosen/remove and tag all attachment parts of the cable harness 4656VB to make later installation easier. f Remove and discard the cable harness : 1 harness 4656VB D9299145600200 Item (018) discard 4 Remove the cable harness 4661VB. Refer to Drawing(s) : D92991461010 Sheet(s) 15

a Disconnect the plugs from the receptacles and remove the receptacles 2985VC, 2987VC,2989VC, 2993VC, 2975VC, 7600VC, 7611VC and 7612VC from the structure. b Disconnect the plugs 1939VC-A, 1941VC-A, 1943VC-A, 1945VC-A, 1947VC-A, 2815GE-A, 3068GN-A and 72GG-B.

c Disconnect the wires of the cable harness 4661VB from the terminals 7223VT, 7224VT, 7502VT, 7505VT and 7528VT. d Disconnect the bonding points 6593VN, 6594VN, 6794VN, 6795VN and 6796VN.

e Loosen/remove and tag all attachment parts of the cable harness 4661VB to make later installation easier. f Remove and discard the cable harness : 1 harness 4661VB D9299146101000 Item (020) discard 5 Remove the cable harness 4662VB. Refer to Drawing(s) : D92991462006 Sheet(s) 7

a Disconnect the plugs 1978VC-A, 1994VC-A, 1996VC-A, 7601VC-A and 72GG-A. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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b Disconnect the wires of the cable harness 4662VB from the terminals 7512VT and 7616VT.

c Disconnect the bonding points 6765VN, 6766VN and 6801VN. d Loosen/remove and tag all attachment parts of the cable harness 4662VB to make later installation easier.

e Remove and discard the cable harness : 1 harness 4662VB D9299146200600 Item (022) discard 6 Remove the cable harness 4663VB. Refer to Drawing(s) : D92991463003 Sheet(s) 8

a Disconnect the plugs from the receptacles and remove the receptacles 2991VC, 2999VC and 7610VC. b Disconnect the plugs 1969VC-A and 7602VC-A.

c Disconnect the wires of the cable harness 4663VB from the terminal 7110VT. d Loosen/remove and tag all attachment parts of the cable harness 4663VB to make later installation easier.

e Remove and discard the cable harness : 1 harness 4663VB D9299146300300 Item (024) discard 7 Remove the cable harness 4664VB. Refer to Drawing(s) : D92991464002 Sheet(s) 4

a Disconnect the plug from the receptacle and remove the receptacle 7605VC. b Disconnect the plugs 1966VC-A and 1968VC-A.

c Disconnect the wires of the cable harness 4664VB from the terminal 7110VT. d Loosen/remove and tag all attachment parts of the cable harness 4664VB to make later installation easier.

e Remove and discard the cable harness : 1 harness 4664VB D9299146400200 Item (026) discard 8 Remove the cable harness 4671VB. Refer to Drawing(s) : D92991471002 Sheet(s) 4 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 277 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Disconnect the plugs from the receptacles and remove the receptacles 2811GE and 2812GE. b Disconnect the plugs 2455GE-A, 2027GE-A, 2065GN-A, 37QA-A, 2151GN-A, 2454GN-A, 2454GE-C, 2074GJ-A, 2075GJ-A, 4CN-A, 25CV-A, 7611VC-A and 7612VC-A.

c Disconnect the bonding points 6741VN, 6743VN, 6671VN, 6552VN, 6568VN, 6954VN, 6955VN, 6956VN and 6957VN. d Loosen/remove and tag all attachment parts of the cable harness 4671VB to make later installation easier.

e Remove and discard the cable harness : 1 harness 4671VB D9299147100200 Item (030) discard 9 Remove the cable harness 4672VB. Refer to Drawing(s) : D92991472007 Sheet(s) 8

a Disconnect the plug from the receptacle and remove the receptacle 7601VC. b Disconnect the plugs 11GA-A, 29GA-A, 24CV-A, 3CN-B, 1012GL-A and 3012GL-A.

c Disconnect the bonding points 6561VN, 6564VN, 6738VN, 6958VN, 6961VN and 6816VN. d Loosen/remove and tag all attachment parts of the cable harness 4672VB to make later installation easier.

e Remove and discard the cable harness : 1 harness 4672VB D9299147200700 Item (032) discard 1 0 Remove the cable harness 4673VB. Refer to Drawing(s) : D92991473001 Sheet(s) 2

a Disconnect the plugs 4CN-A, 25CV-A, 28CV-A and 7610VC-A. b Disconnect the bonding point 6559VN.

c Loosen/remove and tag all attachment parts of the cable harness 4673VB to make later installation easier. d Remove and discard the cable harness : 1 harness 4673VB D9299147300100 Item (034) discard DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 1 Remove the cable harness 4680VB. Refer to Drawing(s) : D92991480008 Sheet(s) 9

a Disconnect the plugs 8GA-A, 26GA-A, 62GG-A, 63GG-A, 23CV-A, 3CN-A, 23GG-A, 7532VC-A, 7600VC-A and 7531VC-A. b Disconnect the bonding points 6776VN, 6797VN, 6566VN, 6963VN, 6990VN, 6960VN and 6991VN.

c Loosen/remove and tag all attachment parts of the cable harness 4680VB to make later installation easier. d Remove and discard the cable harness : 1 harness 4680VB D9299148000800 Item (038) discard 1 2 Remove the cable harness 4681VB. Refer to Drawing(s) : D92991481001 Sheet(s) 2

a Disconnect the plug 2151GN-A. b Disconnect the bonding point 6957VN.

c Disconnect the wires of the cable harness 4681VB from the terminal 7613VT. d Loosen/remove and tag all attachment parts of the cable harness 4681VB to make later installation easier.

e Remove and discard the cable harness : 1 harness 4681VB D9299148100100 Item (040) discard 1 3 Remove the cable harness 4683VB. Refer to Drawing(s) : D92991483003 Sheet(s) 4

a Disconnect the plugs 1848VC-A, 1850VC-A, 3151GN-A, 10CE-1A, 7614VC-A and 7615VC-A. b Disconnect the bonding points 6763VN and 6598VN.

c Loosen/remove and tag all attachment parts of the cable harness 4683VB to make later installation easier. d Remove and discard the cable harness : 1 harness 4683VB D9299148300300 Item (042) discard DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 279 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 4 Remove the cable harness 4692VB. Refer to Drawing(s) : D92991492001 Sheet(s) 2

a Disconnect the plug 2150GP-A. b Disconnect the bonding point 6739VN.

c Disconnect the wires of the cable harness 4692VB from the terminal 7616VT. d Loosen/remove and tag all attachment parts of the cable harness 4692VB to make later installation easier.

e Remove and discard the cable harness : 1 harness 4692VB D9299149200100 Item (044) discard 1 5 Remove the cable harness 4693VB. Refer to Drawing(s) : D92991493001 Sheet(s) 2

a Disconnect the plug from the receptacle and remove the receptacle 7602VC. b Disconnect the plugs 23CV-A, 3CN-A and 27CV-A.

c Disconnect the bonding point 6563VN. d Loosen/remove and tag all attachment parts of the cable harness 4693VB to make later installation easier.

e Remove and discard the cable harness : 1 harness 4693VB D9299149300100 Item (046) discard 1 6 Remove the cable harness 4694VB. Refer to Drawing(s) : D92991494001 Sheet(s) 2

a Disconnect the plugs 27CV-B, 24CV-A, 7605VC-A and 3CN-B. b Disconnect the bonding point 6561VN.

c Loosen/remove and tag all attachment parts of the cable harness 4694VB to make later installation easier. d Remove and discard the cable harness : 1 harness 4694VB D9299149400100 Item (048) discard 1 7 Remove the cable harness 4696VB. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Refer to Drawing(s) : D92991496002 Sheet(s) 3

a Disconnect the plugs 1852VC-A and 7604VC-A. b Loosen/remove and tag all attachment parts of the cable harness 4696VB to make later installation easier.

c Remove and discard the cable harness : 1 harness 4696VB D9299149600200 Item (050) discard (be) Install the brackets for the wiring between FR46 and FR50. Refer to Kit 281118D70R01 Refer to drawing(s) : D92492243000 Sheet(s) 1 thru 13 and 21 1 Install these items at FR46 as shown in drawing D92492243000, Sheet 3, Section B-B3 and Sheet 12, Details F3-12 and G3-12.

a Put these items in position, drill the holes for the rivets and install : 20 bracket D9249179320000 Item 002

1 bracket D9249184620400 Item 021 with : 44 rivet LN9198-3208BF Item 632 2 Install this item between FR46 and FR47 as shown in drawing D92492243000, Sheet 3, Section B-B3 and Section A-A.

a Put this item in position, drill the holes for the rivets and install : 6 bracket D9249178000600 Item 007 with : 24 rivet LN9198-3208BF Item 632 3 Install this item between FR46 and FR47 as shown in drawing D92492243000, Sheet 3, Section B-B3 and Sheet 13, Sections F3-F13, B3-B13, C3-C13 and D3-D13.

a Put this item in position, drill the holes for the rivets and install : 12 bracket D9249179320000 Item 002 with : 22 rivet LN9198-3208BF Item 632 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 281 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

4 Install this item between FR46 and FR47 as shown in drawing D92492243000, Sheet 3, Section B-B3 and Sheet 13, Details H, J, L and K.

a Remove the existing rivets in the affected areas. b Put this item in position, transfer drill the holes for the rivets, open the holes to final dimension and install : 4 bracket D9249172321200 Item 016 with : 12 rivet LN9198-4814CF Item 648 5 Install these items at FR47 as shown in drawing D92492243000, Sheet 5, Detail Z.

a Put these items in position, transfer drill the holes, drill the additional holes, open the holes to final dimension and install : 1 bracket A9249635720200 Item 001 3 bracket D9249179320000 Item 002 1 bracket D9249178001200 Item 030 with : 16 rivet LN9198-3208BF Item 632 6 Install these items between FR47 and FR48 as shown in drawing D92492243000, Sheet 5, Section H-H.

a Put these items in position, drill the holes for the rivets and install : 2 bracket D9249179320000 Item 002 2 angle D9249177520000 Item 013 1 bracket D9249177100000 Item 023 with : 22 rivet LN9198-3208BF Item 632 b Drill the hole for the nut plate with 5.1 mm (0.201 in.) diameter.

c Put this item in position, drill the holes for the rivets and install : 1 nut MS21060L3 Item 027 with : 2 rivet DIN65399-2408BF Item 724 7 Install this item between FR47 and FR48 as shown in drawing D92492243000, Sheet 5, Sections K-K and M-M. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 282 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Put this item in position, drill the holes for the rivets and install : 2 bracket A9249635720200 Item 001 with : 4 rivet LN9198-3208BF Item 632 8 Install this item at FR48 as shown in drawing D92492243000, Sheet 7, Sections B-B, D-D, S-S and T-T.

a Put this item in position, drill the holes for the rivets and install : 7 bracket A9249635720200 Item 001 with : 14 rivet LN9198-3208BF Item 632 9 Install these items between FR48 and FR49 as shown in drawing D92492243000, Sheet 7, View Q.

a Put this item in position, drill the holes for the rivets and install : 2 bracket A9249635720200 Item 001 5 bracket D9249179320000 Item 002 with : 14 rivet LN9198-3208BF Item 632 1 0 Drill the holes at FR48 as shown in drawing D92492243000, Sheet 7, Section F-F7.

a Drill the five additional holes with 5.1 mm (0.201 in.) diameter. b Open one hole to 6.1 mm (0.240 in.) diameter in the FR48. 1 1 Install these items at FR49 as shown in drawing D92492243000, Sheet 9, Sections D-D, K-K, H-H, F-F, L-L, C-C and B-B.

a Put this item in position, drill the holes for the rivets and install : 19 bracket A9249635720200 Item 001 with : 38 rivet LN9198-3208BF Item 632 1 2 Install these items at FR49 as shown in drawing D92492243000, Sheet 9, Detail Z.

a Put these items in position, drill the holes for the rivets and install : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 283 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 bracket A9249635720200 Item 001 1 bracket D9249179320000 Item 002 1 bracket D9249180922600 Item 026 with : 6 rivet LN9198-3208BF Item 632 1 3 Install these items at FR50 as shown in drawing D92492243000, Sheet 11, Detail X.

a Put these items in position, drill the holes for the rivets and install : 1 bracket A9249635720200 Item 001 1 angle D9249177520000 Item 013 with : 8 rivet LN9198-3208BF Item 632 1 4 Install these items between FR49 and FR51 as shown in drawing D92492243000, Sheet 11, Section A-A.

a Put these items in position, drill the holes for the rivets and install : 2 bracket A9249635720200 Item 001 7 bracket D9249179320000 Item 002 with : 18 rivet LN9198-3208BF Item 632 1 5 Install these items between FR51 and FR52 as shown in drawing D92492243000, Sheet 21, Sections M-M21 and S-S21.

a Put these items in position, drill the holes for the rivets and install : 2 bracket A9249635720200 Item 001 with : 4 rivet LN9198-3208BF Item 632 (bf) Install the screwed brackets for the wiring between FR46 and FR49. Refer to Kit 281118D72R00 Refer to Drawing(s) : D92492244000 Sheet(s) 1 thru 9 1 Install these items between FR46 and FR47 as shown in drawing D92492243000, Sheet 3, Section B-B3.

a Install these items : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 bracket D9249180800200 Item 024 1 bracket D9249180800400 Item 025 6 bracket D9249177920000 Item 028 2 bracket D9249177820200 Item 030 with : 40 screw NAS1096-2-8 Item 003 40 washer NAS1149DN816K Item 006 16 nut MS21042L08 Item 010 2 Install these items at FR48 as shown in drawing D92492243000, Sheet 7, Section F-F7, Detail C.

a Install these items : 1 bracket D9249180900000 Item 026 1 bracket D9249180922400 Item 027 with : 6 screw NAS1096-3-8 Item 001 1 screw NAS1096-2-18 Item 004 7 washer NAS1149D0332K Item 005 6 nut MS21042L3 Item 009 1 mount E0343-01 Item 015 1 spacer NSA5527-03-06D Item 017 3 Install this item at FR48 as shown in drawing D92492243000, Sheet 7, Section B-B :

a Install this item : 3 pin DAN364-02 Item 011 4 Install these items at FR49 as shown in drawing D92492243000, Sheet 9, Section H-H9:

a Install these items : 3 bracket ABS0355-01 Item 012 3 bracket ABS0355-02 Item 013 3 washer NSA935514-03 Item 014 (bg) Attach the cable harnesses in the AFT cargo compartment bilge area between FR46 and FR50. Refer to Kit 281118D69R01 Refer to Drawing(s) : D92891803000 Sheet(s) 1 thru 16 1 Attach the cable harnesses between FR46 and FR50 as shown in drawing D92891803000, Sheets 1, 3, 5, 7, 9, 10, 12, 14, 15 and 16. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 285 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Attach with these items : 28 screw NAS1096-2-8 Item 001 116 screw NAS1096-2-18 Item 002 3 screw NAS1096-2-28 Item 003 77 screw NAS1096-2-8 Item 004 144 nut NSA5066-08-2 Item 005 1 spacer NSA5527-03-08 Item 006 101 nut MS21042L3 Item 007 159 washer NAS1149DN816K Item 009

33 washer NAS1149D0332K Item 010 11 clamp MS21919WCH5 Item 013

4 spacer NSA5527-03-02 Item 016 2 washer NSA935808-01 Item 017 1 support ABS0731A01 Item 018 76 washer NAS1149C0332R Item 019 110 spacer NSA5527-03-01 Item 020

12 fitting NSA934710T11 Item 021 22 fitting NSA934710T14 Item 022

1 mount E0660-01 Item 023 7 mount NSA935513-01 Item 027 123 mount NSA935504-01 Item 031

23 spacer NSA5527-03-03 Item 035 1002 tie NSA935401-04 Item 036 1 nut MS21042L08 Item 037 1 guide D9249181406400 Item 038 1 guide D9249181406600 Item 039 10 spring NSA934710E20 Item 040

2 spring NSA934710E23 Item 041 2 circle D9249173320000 Item 042 2 circle D9249173320200 Item 043 2 circle D9249173320400 Item 044 2 circle D9249173320600 Item 045 7 spacer NSA5527-03-04 Item 052 8 screw NAS1096-2-10 Item 053 1 screw NAS1096-2-43 Item 055 1 mount NSA935504-02 Item 056 4 screw NAS1096-2-24 Item 058 1 spacer NSA5527-03-06 Item 059 64 washer NAS1149D0363K Item 060

8 mount E0343-01 Item 063 32 screw NAS1096-3-10 Item 064 0.1 ME strip NSA939510BN Item 080

1 bracket ABS0355-01 Item 096 1 bracket ABS0355-02 Item 097 1 washer NSA935514-03 Item 098 2 bobbin NSA935510-02 Item 099 12 washer D9249102520000 Item 190 b Install the placards as shown in drawing D92891803000 ’POST’, supplied in : 1 placards D9289180320200 1 placards D9289180320000 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 286 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(bh) Attach the cable harnesses at FR42. Refer to Kit 281118D67R02 Refer to Drawing(s) : D92891803004 Sheet(s) 32 thru 38 1 On FR42 install as shown in drawing D92891803004, Sheet 36, Section K-K36 these items : 1 L-Section D9249171020200 Item 800

with : 2 screw NAS1096-3-6 Item 026 2 washer NAS1149C0332R Item 153 2 nut MS21042L3 Item 210 2 Attach the cable harnesses at FR42 as shown in drawing D92891803004, Sheets 32 thru 38.

a Attach with these items : 8 screw NAS1096-2-7 Item 004 8 screw NAS1096-2-18 Item 005 23 screw NAS1096-2-10 Item 006

4 screw NAS1096-2-12 Item 007 2 screw NAS1096-2-14 Item 009 20 screw NAS1096-2-19 Item 012

2 screw NAS1096-2-25 Item 016 10 washer NSA935808C01 Item 020 22 screw NAS1096-2-43 Item 022

4 screw NAS1096-3-8 Item 028 12 nut NSA5066-08-2 Item 032

6 clamp MS21919WCH4 Item 041 16 clamp NSA935807-06 Item 042

6 clamp NSA935807-09 Item 045 4 spacer NSA5527-03-01 Item 050 6 screw NAS1100-04-5 Item 051 2 spacer NSA5527-03-02 Item 052 6 spacer NSA5527-03-06 Item 055 38 washer NAS1149CN816R Item 152 18 washer NSA935808C01 Item 171 38 nut NSA5066-08-2 Item 231

6 spacer NSA5527-03-02 Item 302 19 spacer NSA5527-03-04 Item 306 18 spacer NSA5527-03-06 Item 310

8 clamp MS21919WCH4 Item 350 10 clamp MS21919WCH2 Item 364 22 clamp NSA935807-06 Item 376 22 clamp NSA935807-09 Item 377 100 tie NSA935401-05 Item 780 100 tie NSA935401-03 Item 793 150 tie NSA935401-04 Item 794 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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0.67 ME strip NSA939510AN Item 894 1 ME strip NSA939510DN Item 896 2 ME tubing E0484KMJ0900 Item 1190

b Install the placards as shown in drawing D92891803004 ’POST’, supplied in : 1 placards D9289180320200 1 placards D9289180320000 NOTE : The placard sets are contained in Kit 281118D69R01. (bi) Modify the wiring of the cable harnesses 4209VB, 4213VB, 4214VB, 4215VB, 4216VB, 4220VB, 4221VB, 4222VB, 4223VB, 4224VB, 4225VB, 4226VB, 4232VB, 4233VB and 5214VB. Refer to Kit 281118D84R00 Refer to Drawing(s) : D92990609001 Sheet(s) 1 D92990609002 Sheet(s) 2 D92990613012 Sheet(s) 13 D92990613014 Sheet(s) 14 D92990614128 Sheet(s) 71 D92990614130 Sheet(s) 73 D92990615007 Sheet(s) 10 D92990615008 Sheet(s) 11 D92990616003 Sheet(s) 2 D92990616004 Sheet(s) 3 D92990620042 Sheet(s) 3 D92990620044 Sheet(s) 4 D92990621002 Sheet(s) 3 D92990621003 Sheet(s) 6 D92990622003 Sheet(s) 3 D92990622004 Sheet(s) 5 D92990623010 Sheet(s) 12 and 13 D92990623011 Sheet(s) 14 and 16 D92990624048 Sheet(s) 7 D92990624053 Sheet(s) 8 D92999559020 Sheet(s) 20 D92990625010 Sheet(s) 14 and 15 D92990625011 Sheet(s) 15 and 16 D92990626008 Sheet(s) 13 and 14 D92990626009 Sheet(s) 13 and 15 D92990632007 Sheet(s) 7 and 8 D92990632009 Sheet(s) 8 and 9 D92990633042 Sheet(s) 1 D92990633044 Sheet(s) 3 D92990814015 Sheet(s) 22 and 25 D92990814020 Sheet(s) 22 and 30 1 Modify the wiring of the cable harness 4209VB. Refer to drawing D92990609001, Sheet 1 Refer to drawing D92990609002, Sheet 2 Refer to Figure 27 (Hookup Chart) DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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a Remove the wires as shown on the lines 1 thru 9 (Refer to drawing D92990609001 and refer to Figure 27). b Install the wires as shown on the lines 11 thru 19 (Refer to drawing D92990609002 and refer to Figure 27), supplied in : elect. equipment D9299955900200 Item 001

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : placard D9289471302200 Item 026 2 Modify the wiring of the cable harness 4213VB. Refer to drawing D92990613012, Sheet 13 Refer to drawing D92990613014, Sheet 14 Refer to Figure 28 (Hookup Chart)

a Remove the wires as shown on the lines 1 thru 3 (Refer to drawing D92990613012 and refer to Figure 28). b Install the wires as shown on the lines 5 thru 7 (Refer to drawing D92990613014 and refer to Figure 28), supplied in : elect. equipment D9299955900400 Item 002

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : placard D9289471302200 Item 026 3 Modify the wiring of the cable harness 4214VB. Refer to drawing D92990614128, Sheet 71 Refer to drawing D92990614130, Sheet 73 Refer to Figure 29 (Hookup Chart)

a Remove the wires as shown on the lines 1 thru 8 (Refer to drawing D92990614128 and refer to Figure 29). b Install the wires as shown on the lines 10 thru 17 (Refer to drawing D92990614130 and refer to Figure 29), supplied in : elect. equipment D9299955900600 Item 003 NOTE : To do the modification of cable harness 4214VB, you must open 7106VP. Do not close 7106VP at this time. Close 7106VP after the modification of cable harness 4227VB, Refer to paragraph (5) (bk) 1 e . c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : placard D9289471302200 Item 026 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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4 Modify the wiring of the cable harness 4215VB. Refer to drawing D92990615007, Sheet 10 Refer to drawing D92990615008, Sheet 11 Refer to Figure 30 (Hookup Chart) Refer to Figure 31 (Hookup Chart)

a Remove the wires as shown on the lines 1 thru 15 (Refer to drawing D92990615007 and refer to Figure 30). b Install the wires as shown on the lines 1 thru 15 (Refer to drawing D92990615008 and refer to Figure 31), supplied in : elect. equipment D9299955900800 Item 004

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : placard D9289471302200 Item 026 5 Modify the wiring of the cable harness 4216VB. Refer to drawing D92990616003, Sheet 2 Refer to drawing D92990616004, Sheet 3 Refer to Figure 32 (Hookup Chart)

a Remove the wires as shown on the lines 1 thru 7 (Refer to drawing D92990616003 and refer to Figure 32). b Install the wires as shown on the lines 9 thru 15 (Refer to drawing D92990616004 and refer to Figure 32), supplied in : elect. equipment D9299955901000 Item 005

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : placard D9289471302200 Item 026 6 Modify the wiring of the cable harness 4220VB. Refer to drawing D92990620042, Sheet 3 Refer to drawing D92990620044, Sheet 4 Refer to Figure 33 (Hookup Chart) Refer to Figure 34 (Hookup Chart)

a Remove the wires as shown on the lines 1 thru 21 (Refer to drawing D92990620042 and refer to Figure 33). b Install the wires as shown on the lines 1 thru 21 (Refer to drawing D92990620044 and refer to Figure 34), supplied in : elect. equipment D9299955901200 Item 006

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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placard D9289471302200 Item 026 7 Modify the wiring of the cable harness 4221VB. Refer to drawing D92990621002, Sheet 3 Refer to drawing D92990621003, Sheet 6 Refer to Figure 35 (Hookup Chart) Refer to Figure 36 (Hookup Chart)

a Remove the wires as shown on the lines 1 thru 24 (Refer to drawing D92990621002 and refer to Figure 35, Sheet 1) and on the lines 1 thru 12 (Refer to drawing D92990621002 and refer to Figure 35, Sheet 2). b Install the wires as shown on the lines 1 thru 24 (Refer to drawing D92990621003 and refer to Figure 36, Sheet 1) and on the lines 1 thru 12 (Refer to drawing D92990621003 and refer to Figure 36, Sheet 2), supplied in : elect. equipment D9299955901400 Item 007

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : placard D9289471302200 Item 026 8 Modify the wiring of the cable harness 4222VB. Refer to drawing D92990622003, Sheet 3 Refer to drawing D92990622004, Sheet 5 Refer to Figure 37 (Hookup Chart)

a Remove the wires as shown on the lines 1 thru 7 (Refer to drawing D92990622003 and refer to Figure 37). b Install the wires as shown on the lines 9 thru 15 (Refer to drawing D92990622004 and refer to Figure 37), supplied in : elect. equipment D9299955901600 Item 008

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : placard D9289471302200 Item 026 9 Modify the wiring of the cable harness 4223VB. Refer to drawing D92990623010, Sheet 12 and 13 Refer to drawing D92990623011, Sheet 14 and 16 Refer to Figure 38 (Hookup Chart) Refer to Figure 39 (Hookup Chart)

a Remove the wires as shown on the lines 1 thru 24 (Refer to drawing D92990623010 and refer to Figure 38, Sheet 1) and on the lines 1 thru 4 (Refer to drawing D92990623010 and refer to Figure 38, Sheet 2).

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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b Install the wires as shown on the lines 1 thru 24 (Refer to drawing D92990623011 and refer to Figure 39, Sheet 1) and on the lines 1 thru 4 (Refer to drawing D92990623011 and refer to Figure 39, Sheet 2), supplied in : elect. equipment D9299955901800 Item 009

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : placard D9289471302200 Item 026 1 0 Modify the wiring of the cable harness 4224VB. Refer to drawing D92990624048, Sheet 7 Refer to drawing D92990624053, Sheet 8 Refer to drawing D92894713022, Sheet 2 Refer to Figure 40 (Hookup Chart) Refer to Figure 41 (Hookup Chart)

a Remove the wires as shown on the lines 1 thru 15 (Refer to drawing D92990624048 and refer to Figure 40). b Install the wires as shown on the lines 1 thru 15 (Refer to drawing D92990624053 and refer to Figure 41), supplied in : elect. equipment D9299955902000 Item 010

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : placard D9289471302200 Item 026 1 1 Modify the wiring of the cable harness 4225VB. Refer to drawing D92990625010, Sheet 14 and 15 Refer to drawing D92990625011, Sheet 15 and 16 Refer to Figure 42 (Hookup Chart)

a Remove the wires as shown on the lines 1 and 2 (Refer to drawing D92990625010 and refer to Figure 42). b Install the wires as shown on the lines 4 and 5 (Refer to drawing D92990625011 and refer to Figure 42), supplied in : elect. equipment D9299955902200 Item 011

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : placard D9289471302200 Item 026 1 2 Modify the wiring of the cable harness 4226VB. Refer to drawing D92990626008, Sheet 13 and 14 Refer to drawing D92990626009, Sheet 13 and 15 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Refer to Figure 43 (Hookup Chart) Refer to Figure 44 (Hookup Chart)

a Remove the wires as shown on the lines 1 thru 24 (Refer to drawing D92990626008 and refer to Figure 43, Sheet 1) and on the lines 1 thru 8 (Refer to drawing D92990626008 and refer to Figure 43, Sheet 2). b Install the wires as shown on the lines 1 thru 24 (Refer to drawing D92990626009 and refer to Figure 44, Sheet 1) and on the lines 1 thru 8 (Refer to drawing D92990626009 and refer to Figure 44, Sheet 2), supplied in : elect. equipment D9299955902400 Item 012

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : placard D9289471302200 Item 026 1 3 Modify the wiring of the cable harness 4232VB. Refer to drawing D92990632007, Sheet 7 and 8 Refer to drawing D92990632009, Sheet 8 and 9 Refer to Figure 45 (Hookup Chart) Refer to Figure 46 (Hookup Chart)

a Remove the wires as shown on the lines 1 thru 17 (Refer to drawing D92990632007 and refer to Figure 45). b Install the wires as shown on the lines 1 thru 18 (Refer to drawing D92990632009 and refer to Figure 46), supplied in : elect. equipment D9299955902600 Item 015

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : placard D9289471302200 Item 026 1 4 Modify the wiring of the cable harness 4233VB. Refer to drawing D92990633042, Sheet 1 Refer to drawing D92990633044, Sheet 3 Refer to Figure 47 (Hookup Chart)

a Remove the wires as shown on the lines 1 thru 4 (Refer to drawing D92990633042 and refer to Figure 47). b Install the wires as shown on the lines 6 thru 9 (Refer to drawing D92990633044 and refer to Figure 47), supplied in : elect. equipment D9299955902800 Item 016

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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placard D9289471302200 Item 026 1 5 Modify the wiring of the cable harness 5214VB. Refer to drawing D92990814015, Sheet 22 and 25 Refer to drawing D92990814020, Sheet 22 and 30 Refer to Figure 48 (Hookup Chart)

a Remove the wire as shown on the lines 1 (Refer to drawing D92990814015 and refer to Figure 48). b Install the wire as shown on the lines 3 (Refer to drawing D92990814020 and refer to Figure 48), supplied in : elect. equipment D9299955903000 Item 019

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : placard D9289471302200 Item 026 (bj) Remove the cable harnesses 4227VB, 4234VB, 5220VB, 5224VB and 5233VB. Refer to Drawing(s) : D92990627010 Sheet(s) 14 and 15 D92990634001 Sheet(s) 2 D92990820000 Sheet(s) 1 D92990824002 Sheet(s) 3 D92990833000 Sheet(s) 1 1 Remove the cable harness 4227VB. Refer to drawing D92990627010, Sheet 14 and 15

a Disconnect the plugs 9CE-D and 9CE-H. b Disconnect the plugs from the receptacles and remove the receptacles 7614VC, 7615VC, 7114VC and 7137VC from the structure.

c Disconnect the wires of the cable harness 4227VB from the terminals 7581VT and 7105VT. d Disconnect the bonding points 6740VN, 6591VN and 6804VN.

e Loosen/remove and tag all attachment parts of the cable harness 4227VB to make later installation easier. f Remove and discard the cable harness : 1 harness 4227VB D9299062701000 Item (013) discard 2 Remove the cable harness 4234VB. Refer to drawing D92990634001, Sheet 2

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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a Disconnect the plugs from the receptacles and remove the receptacles 2996VC and 7145VC from the structure. b Loosen/remove and tag all attachment parts of the cable harness 4234VB to make later installation easier.

c Remove and discard the cable harness : 1 harness 4234VB D9299063400100 Item (017) discard 3 Remove the cable harness 5220VB. Refer to drawing D92990820000, Sheet 1

a Disconnect the plug 1972VC-A. b Disconnect the plug from the receptacle and remove the receptacle 7155VC from the structure.

c Loosen/remove and tag all attachment parts of the cable harness 5220VB to make later installation easier. d Remove and discard the cable harness : 1 harness 5220VB D9299082000000 Item (020) discard 4 Remove the cable harness 5224VB. Refer to drawing D92990824002, Sheet 3

a Disconnect the plug 1990VC-A. b Disconnect the plugs from the receptacles and remove the receptacles 7117VC and 7126VC from the structure.

c Disconnect the wires of the cable harness 5224VB from the terminal 7502VT. d Loosen/remove and tag all attachment parts of the cable harness 5224VB to make later installation easier.

e Remove and discard the cable harness : 1 harness 5224VB D9299082400200 Item (022) discard 5 Remove the cable harness 5233VB. Refer to drawing D92990833000, Sheet 1

a Disconnect the plug 1973VC-A. b Disconnect the plug from the receptacle and remove the receptacle 7132VC from the structure.

c Loosen/remove and tag all attachment parts of the cable harness 5233VB to make later installation easier. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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d Remove and discard the cable harness : 1 harness 5233VB D9299083300000 Item (024) discard (bk) Install the cable harnesses 4227VB, 4234VB, 5220VB, 5224VB and 5233VB. Refer to Kit 281118D84R00 Refer to Drawing(s) : D92990627011 Sheet(s) 15 and 16 D92990634002 Sheet(s) 3 D92990820001 Sheet(s) 2 D92990824007 Sheet(s) 7 D92990833001 Sheet(s) 2 1 Install the modified cable harness 4227VB. Refer to drawing D92990627011, Sheet 15 and 16

a Put this item with the old routing in position : 1 harness 4227VB D9299062701100 Item 014

b Attach the cable harness with the existing attachment parts.

c Connect the plugs 9CE-D and 9CE-H. d Install the receptacles 7614VC, 7615VC, 7114VC and 7137VC at the structure and connect the plugs.

e Connect the wires of the cable harness 4227VB at the terminals 7581VT and 7105VT (Refer to Aircraft Wiring List (AWL) . f Connect the bonding points 6740VN, 6591VN and 6804VN. g Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : placard D9289471302200 Item 026 2 Install the modified cable harness 4234VB. Refer to drawing D92990634002, Sheet 3

a Put this item with the old routing in position : 1 harness 4234VB D9299063400200 Item 018

b Attach the cable harness with the existing attachment parts.

c Install the receptacles 2996VC and 7145VC at the structure and connect the plugs. d Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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placard D9289471302200 Item 026 3 Install the modified cable harness 5220VB. Refer to drawing D92990820001, Sheet 2

a Put this item with the old routing in position : 1 harness 5220VB D9299082000100 Item 021

b Attach the cable harness with the existing attachment parts.

c Connect the plug 1972VC-A. d Install the receptacle 7155VC at the structure and connect the plug.

e Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : placard D9289471302200 Item 026 4 Install the modified cable harness 5224VB. Refer to drawing D92990824007, Sheet 7

a Put this item with the old routing in position : 1 harness 5224VB D9299082400700 Item 023

b Attach the cable harness with the existing attachment parts.

c Connect the plug 1990VC-A. d Install the receptacles 7117VC and 7126VC at the structure and connect the plugs.

e Connect the wires of the cable harness 5224VB at the terminal 7502VT (Refer to Aircraft Wiring List (AWL) . f Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : placard D9289471302200 Item 026 5 Install the modified cable harness 5233VB. Refer to drawing D92990833001, Sheet 2

a Put this item with the old routing in position : 1 harness 5233VB D9299083300100 Item 025

b Attach the cable harness with the existing attachment parts.

c Connect the plug 1973VC-A. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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d Install the receptacle 7132VC at the structure and connect the plug.

e Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness : placard D9289471302200 Item 026 (bl) Install the sidewall panels 151EW and 151HW. Refer to Kit 281118D78R00 Refer to AMM 25-55-11, Page block 401 Refer to Drawing(s) : D25570048004 Sheet(s) 3 1 Install : 1 sidewall panel D2557176800200 Item 12 1 sidewall panel D2557176201000 Item 14 (bm) Install the sidewall panel 152DW. Refer to Kit 281118D79R00 Refer to AMM 25-55-12, Page block 401 Refer to Drawing(s) : D25570048006 Sheet(s) 4 1 Install : 1 sidewall panel D2557035200800 Item 16 (bn) Install the AFT cargo compartment ceiling panels between FR47 and FR59. Refer to Kit 281118D80R01 Refer to AMM 25-55-11, Page block 401 and refer to drawing D25570048000, Sheet 1 Refer to Drawing(s) : D25570048000 Sheet(s) 1 1 Install these items as shown in drawing D25570048000, Sheet 1 : 1 panel D2557030000600 Item 000 1 panel D2557031000400 Item 002 2 Install the AFT cargo compartment ceiling panels 151BC and 151DC (Refer to AMM 25-55-11, Page block 401). 3 Install these items as shown in drawing D25570048000, Sheet 1 : 1 bumper D2557165020000 Item A 2 bumper D2557165620000 Item B 2 bumper D2557165720200 Item C 2 rail D2558501900000 Item D 1 rail D2558503100000 Item E DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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NOTE : Items A thru E are retained parts. (bo) Install the AFT cargo compartment partition panels 151AW, 151BW and 152BW at FR47. Refer to Kit 281118D81R00 Refer to AMM 25-55-11, Page block 401 Refer to Drawing(s) : D25570048002 Sheet(s) 2 1 Install these items : 1 panel D2557166000400 Item 003 1 panel D2557166000500 Item 004 1 panel D2557166200200 Item 005 2 cover D2557017000200 Item 010 (bp) Install the belly fairing panel 197AB. Refer to AMM 53-35-11, Page block 401 Refer to Kit 281118D60R00 Refer to Drawing(s) : D53475023000 Sheet(s) 1 1 Install this item as shown in View A1-1 : 1 panel D5347503400200 Item 000

with : 46 screw NSA5030-3-3 A 16 screw NSA5030-3-4 B 59 screw NSA5030-3-6 C NOTE : Items A, B and C are retained parts. (6) Config. 01 Top Drawing D0007113700 (a) Remove and discard the attachment parts of the cable harness in the cabin floor crossbeam area at FR42 and between FR49 and FR55. Refer to Drawing(s) : D92891803002 Sheet(s) 19, 21, 23, 25, 26, 27, 28, 29 and 31 1 Remove and discard the attachment parts of the cable harness at FR42 and between FR49 and FR55.

a Remove and discard these items : 14 screw NAS1096-2-7 Item (001) discard

1 screw NAS1096-2-9 Item (037) discard 3 screw NAS1096-2-12 Item (040) discard DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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3 screw NAS1096-2-16 Item (047) discard 1 screw NAS1096-2-22 Item (049) discard 1 screw NAS1096-2-27 Item (076) discard 28 screw NAS1096-3-8 Item (080) discard 56 screw NAS1096-3-9 Item (081) discard 21 washer NAS1149CN816R Item (177) discard 84 washer NAS1149C0332R Item (178) discard 28 washer NAS1149D0332K Item (179) discard

2 washer ASNA0113-40ADL Item (180) discard 1 nut MS21042-3 Item (222) discard 28 nut NAS1291C3M Item (228) discard

3 bracket E0343-01 Item (270) discard 4 bracket NSA935504-01 Item (271) discard 1 bracket NSA935504-02 Item (272) discard 4 bracket NSA935504-03 Item (275) discard 7 bracket NSA935513-01 Item (276) discard 7 bracket NSA935513-05 Item (277) discard 1 bracket ABS0355-02 Item (285) discard 1 lockwasher NSA935514-03 Item (286) discard 5 spacer NSA5527-03-02 Item (332) discard 3 spacer NSA5527-03-06 Item (333) discard 2 spacer NSA5527-03-04 Item (334) discard 1 clamp MS21919WCH6 Item (373) discard 7 circle D92491010200 Item (687) discard 7 circle D92491010202 Item (712) discard 4 bulkhead NSA934710T13 Item (787) discard 14 bulkhead NSA934710T14 Item (788) discard

1 strap D92491071000 Item (835) discard (b) Remove and retain the attachment parts of the cable harness at FR42. Refer to Kit 281118D67R02 Refer to Drawing(s) : D92891803004 Sheet(s) 32 thru 38 1 Remove and retain the attachment parts of the cable harness at FR42. 2 Remove and discard one bracket and its fastening parts of the cable harness at FR42 as shown in drawing D92891803004, Sheet 33 at location H9. (c) Modify the AFT-cargo-compartment sidewall-panel 152DW for access to the ACT pressurization system connection between FR49 and FR50. Refer to Drawing(s) : D25571787004 Sheet(s) 1 and 3 1 Remove the sidewall panel 152DW (Refer to AMM 25-55-11, Page block 401). 2 Modify the sidewall panel 152DW as shown in drawing D25571787004 Sheet(s) 1 and 3 3 Re-identify the sidewall panel 152DW DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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PN D25571787002 becomes D25571787004. (d) Remove the wires from the cable harnesses 4619VB and 4620VB. 1 Remove the wires from the cable harness 4619VB. Refer to drawing D92997026033, Sheet 46 Refer to Figure 25 (Hookup Chart)

a Remove the wires as shown on the lines 1 and 4 (Refer to drawing D92997026033, Sheet 46 and refer to Figure 25). b Install this item at the cable harness 4619VB: 1 elec. equipment D9299702603300 Item 059 2 Remove the wires from the cable harness 4620VB. Refer to drawing D92997026034, Sheet 48 Refer to Figure 26 (Hookup Chart)

a Remove the wires as shown on the lines 1 and 4 (Refer to drawing D92997026034, Sheet 48 and refer to Figure 26). b Install this item at the cable harness 4620VB: 1 elect. equipment D9299702603400 Item 061 (e) Remove and discard the passenger compartment floor panels 241JF, 251BF and 252BF. Refer to Kit 281118D31R00 Refer to AMM 53-42-12, Page block 401 Refer to Drawing(s): D53675013000 Sheet(s) 1 1 Remove and discard these items:

2 panel D5367160000000 Item (204) discard 1 panel D5367161700000 Item (304) discard (f) Install a bracket at the passenger compartment floor structure at FR53. Refer to Kit 281118D12R00 Refer to Drawing(s): D53472833002 Sheet(s) 2 1 Put the bracket, Item 000, in position as shown in Detail Z2-2. 2 Transfer drill the holes and open them to final dimension. 3 Install this item: 1 bracket D5347212920400 Item 000 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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with: 10 washer NAS1252-10L Item 400

4 nut NSA5182-3 Item 401 2 bolt NSA5031-3-4 Item 413 2 bolt NSA5031-3-5 Item 414 (g) Remove and discard the insulation blankets at FR46. Refer to AMM 25-80-00, Page block 201 Refer to Drawing(s): D25870003028 Sheet(s) 20 1 Remove and discard these items: 1 blanket D2587085002000 Item (020) discard 1 blanket D2587085102200 Item (021) discard 1 blanket D2587085202000 Item (022) discard 1 blanket D2587085302200 Item (023) discard 1 blanket D2587085402000 Item (024) discard 1 blanket D2587085502200 Item (025) discard 1 blanket D2587085602000 Item (026) discard 1 blanket D2587085702000 Item (027) discard 1 blanket D2587085802000 Item (028) discard 1 blanket D2587085902000 Item (029) discard 1 blanket D2587086002000 Item (030) discard 1 blanket D2587086102000 Item (031) discard 1 blanket D2587086202000 Item (032) discard 1 blanket D2587086302200 Item (033) discard 1 blanket D2587086502000 Item (034) discard 1 blanket D2587087102000 Item (035) discard 1 blanket D2587087302000 Item (036) discard (h) Remove and discard the AFT cargo compartment floor panel between FR47 and FR52A and between FR56 and FR59. Refer to AMM 53-42-14, Page block 401 Refer to Drawing(s): D53672848000 Sheet(s) 1 1 Remove and discard these items as shown in View A1-1: 1 panel D5367209500200 Item (218) discard 1 panel D5367209500300 Item (219) discard 1 panel D5367209600000 Item (220) discard 1 panel D5367209700000 Item (221) discard 1 panel D5367209800000 Item (222) discard 1 panel D5367209900000 Item (223) discard 1 panel D5367210200200 Item (224) discard 1 panel D5367210000200 Item (225) discard (i) Remove and discard the AFT cargo compartment floor panel between FR47 and FR59. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 302 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to AMM 53-42-14, Page block 401 Refer to Drawing(s): D53672850000 Sheet(s) 1 1 Remove and discard these items as shown in Detail A1-1: 1 panel D5367208100000 Item (200) discard 1 panel D5367208100100 Item (201) discard 1 panel D5367208200000 Item (202) discard 1 panel D5367208200100 Item (203) discard 1 panel D5367208300000 Item (204) discard 1 panel D5367208400000 Item (205) discard 1 panel D5367208500000 Item (206) discard 1 panel D5367208600000 Item (207) discard 1 panel D5367208700200 Item (208) discard 1 panel D5367208800000 Item (209) discard 1 panel D5367209100000 Item (210) discard 1 panel D5367209200000 Item (211) discard 1 panel D5367208900000 Item (212) discard 1 panel D5367209000000 Item (213) discard 1 panel D5367209300000 Item (214) discard 1 panel D5367209300100 Item (215) discard 1 panel D5367210100000 Item (216) discard 1 panel D5367210100100 Item (217) discard (j) Replace the screwed brackets for the wire routing between FR41 and FR42. Refer to Kit 281118D73R00 Refer to Drawing(s): D92492244002 Sheet(s) 10 1 Remove these items between FR41 and FR42 as shown in drawing D92492244002, Sheet 10, Section A-A.

a Remove and discard these items: 4 screw NAS1096-2-19 Item (012) discard 8 washer NAS1149D0332K Item (157) discard 4 washer NAS1149N816R Item (172) discard 8 washer D9249102520000 Item (180) discard 4 bracket NSA935504-03 Item (253) discard 1 bracket D9249107201200 Item (831) discard 2 Install these items between FR41 and FR42 as shown in drawing D92492244002, Sheet 10, Section B-B.

a Install these items: 7 screw NAS1096-2-12 Item 007 1 screw NAS1096-2-14 Item 009 10 washer ASNA0113-40ADL Item 163

2 washer D9249102520000 Item 190 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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4 nut MS21042-08 Item 202 4 mount E0660-01 Item 266 1 spacer NSA5527-03-04 Item 306 1 spacer NSA5527-03-07 Item 312 2 guide D9249104720000 Item 724 1 deflector D9249102620600 Item 730 1 strap D9249107302800 Item 824 (k) Remove and discard the attachment structure of the partition panels 151AW, 151BW and 152BW. Refer to Kit 281118D36R03 Refer to Drawing(s): D53975018000 Sheet(s) 1 thru 3 1 Remove and discard these items as shown in Section B1-B2: 1 section D5397468100000 Item (201) discard 1 section D5397467400200 Item (202) discard 1 section D5397467400300 Item (203) discard 1 section D5397468800000 Item (208) discard 1 section D5397468800100 Item (209) discard 1 section D5397468000200 Item (222) discard 1 section D5397468000300 Item (223) discard 2 bracket D5397469521200 Item (227) discard 1 section D5397474700000 Item (233) discard 1 section D5397467800600 Item (238) discard 1 section D5397467800700 Item (239) discard 1 section D5397474900000 Item (334) discard

NOTE : The attachment brackets of the sections, Item 202 and 203, remain in the aircraft. 2 Remove and discard these items as shown in drawing D53975018000, Sheet 1: 1 section D5347047400200 Item (230) discard 1 section D5347047400300 Item (231) discard 1 section D5347034400000 Item (234) discard 3 Close the existing holes with these items as shown in Sections C3-C3 and D3-D3: 2 rivet NAS1097AD4-10 Item 532 4 collar NSA5075-6 Item 806 4 pin DAN5-6-2 Item 962 (l) Replace fasteners at FR48, FR49, FR50 and FR51 between STGR3 LH and STGR36 LH. Refer to Kit 281118D08R00 Refer to Drawing(s): D53470095002 Sheet(s) 1 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 304 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Replace the fasteners at FR48 between STGR34 LH and STGR36 LH as shown in Section A1-A1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. b Open the affected holes to final dimension.

c Install these items: 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR48,. 2 Replace the fasteners at FR49 between STGR34 LH and STGR36 LH as shown in Section A1-A1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. b Open the affected holes to final dimension.

c Install these items: 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR49. 3 Replace the fasteners at FR50 between STGR34 LH and STGR36 LH as shown in Section A1-A1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. b Open the affected holes to final dimension.

c Install these items: 30 collar NSA5075-6 Item 806 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR50. 4 Replace the fasteners at FR51 between STGR34 LH and STGR36 LH as shown in Section A1-A1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. b Open the affected holes to final dimension.

c Install these items: 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR51. (m) Remove the corner profiles at STGR38 LH/RH between FR48 and FR56. Refer to Drawing(s): D53470075004 Sheet(s) 10 1 Remove and discard these items as shown in Details Z9-10 and X9-10: 1 corner profile D5347048100400 Item (452) discard 1 corner profile D5347047500400 Item (454) discard 1 corner profile D5347047600600 Item (456) discard (n) Remove the shear plates at STGR38 LH/RH between FR48 and FR59. Refer to Drawing(s): D53470075004 Sheet(s) 8, 11 and 17 1 Remove and discard these items at STGR38 LH as shown in Sections H15-H8 and K15-K11: 1 shear plate D5347048800000 Item (374) discard 1 shear plate D5347048900000 Item (376) discard 1 shear plate D5347049200200 Item (378) discard 2 angle D5347046820600 Item (386) discard 1 angle D5347046820200 Item (390) discard 1 angle D5347046820800 Item (392) discard 1 angle D5347046821000 Item (394) discard DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 connection D5347065020200 Item (398) discard 3 angle D5347046820000 Item (460) discard 2 angle D5347046820200 Item (462) discard 1 angle D5347046820400 Item (464) discard 2 shear plate D5347049000000 Item (474) discard 1 shear plate D5347049100000 Item (476) discard 2 Remove and discard these items at STGR38 RH as shown in Sections G15-G17 and J15-J17: 1 angle D5347046820900 Item (382) discard 1 angle D5347046822000 Item (384) discard 2 angle D5347046820100 Item (468) discard 3 angle D5347046820300 Item (470) discard 1 angle D5347046822400 Item (472) discard 1 shear plate D5347049000100 Item (478) discard 1 shear plate D5347049000300 Item (480) discard 1 shear plate D5347048600400 Item (482) discard (o) Remove the crossbeams at FR48, FR49, FR50 and FR51 in the AFT cargo compartment. D53470075004 Sheet(s) 2, 3, 4 and 16 1 Remove these items at FR48 as shown in drawing D53470075004, Sheet 2, Section A15-A2 ’BEFORE’.

a Remove and discard these items: 1 crossbeam D5347035000400 Item (400) discard 1 shim D5347061120200 Item (402) discard 1 fitting D5347061220000 Item (404) discard 1 shim D5347061120300 Item (406) discard 1 fitting D5347061220100 Item (408) discard 1 support D5347069920800 Item (412) discard

b Close the eight holes as shown in Details B2-2 and C2-2: 8 rivet MBBN4477-4014 Item 540

c Close the two holes at FR48 at STGR43 LH/RH as shown in Section A15-A2: 2 rivet MBBN4477-4014 Item 540 2 Remove these items at FR49 as shown in drawing D53470075004, Sheet 3, Section B15-B3 ’BEFORE’.

a Remove and discard these items: 1 crossbeam D5347035000400 Item (400) discard 1 shim D5347061120200 Item (402) discard 1 fitting D5347061220000 Item (404) discard 1 shim D5347061120300 Item (406) discard DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 fitting D5347061220100 Item (408) discard 1 support D5347069920800 Item (412) discard

b Close the eight holes as shown in Details B3-3 and C3-3: 8 rivet MBBN4477-4014 Item 540

c Close the two holes at FR49 at STGR43 LH/RH as shown in Section B15-B3 ’AFTER’: 2 rivet MBBN4477-4014 Item 540 3 Remove these items at FR50 as shown in drawing D53470075004, Sheet 4, Section C15-C4 ’BEFORE’.

a Remove and discard these items: 1 crossbeam D5347026000400 Item (410) discard 1 shim D5347061120200 Item (402) discard 1 fitting D5347061220000 Item (404) discard 1 shim D5347061120300 Item (406) discard 1 fitting D5347061220100 Item (408) discard 1 clip D5347073720400 Item (430) discard 1 clip D5347073920200 Item (432) discard 1 clip D5347074020000 Item (434) discard 1 clip D5347073720500 Item (436) discard

b Close the eight holes as shown in Details B4-4 and C4-4: 8 rivet MBBN4477-4014 Item 540

c Close the four holes at FR50 at STGR43 LH/RH as shown in Section C15-C4 ’AFTER’: 4 rivet MBBN4477-4014 Item 540 4 Remove these items at FR51 as shown in drawing D53470075004, Sheet 16, Section D15-D16 ’BEFORE’.

a Remove and discard these items: 1 crossbeam D5347035300400 Item (420) discard 1 shim D5347061120200 Item (402) discard 1 fitting D5347061220000 Item (404) discard 1 shim D5347061120300 Item (406) discard 1 fitting D5347061220100 Item (408) discard 1 clip D5347074420400 Item (440) discard 1 clip D5347074620200 Item (442) discard 1 clip D5347074720000 Item (444) discard 1 clip D5347074420500 Item (446) discard 1 connection D5347557525400 Item (448) discard

b Close the eight holes as shown in Details B16-16 and C16-16: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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8 rivet MBBN4477-4014 Item 540

c Close the four holes at FR51 at STGR43 LH/RH as shown in Section D15-D16 ’AFTER’: 4 rivet MBBN4477-4014 Item 540 (p) Modify the structure at FR48 between STGR34 LH and STGR34 RH. Refer to Kit 281118D85R02 Refer to Drawing(s): D53470075004 Sheet(s) 2 1 Replace the fasteners at FR48 between STGR34 RH and STGR36 RH as shown in Section A15-A2 ’AFTER’:

a Remove the existing fasteners in the affected area as shown in Section A15-A2 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. b Open the affected holes to final dimension.

c Install these items: 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Items 865 and 806, will be installed during the installation of the reinforcing straps at FR48. 2 Install the reinforcing straps at FR48 between STGR35 LH/RH and STGR42 LH/RH as shown in Section A15-A2 ’AFTER’:

a Put these items at FR48 in position: 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

b Transfer drill the holes form the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes to final dimension. d Install these items: 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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58 rivet LN9198-4014CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit 281118D08R00. 3 Install the fittings at FR48 at STGR37 LH/RH as shown in Section A15-A2 ’AFTER’:

a Put these items at FR48 in position: 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

b Transfer drill the holes form the frame to the fittings and open all holes to final dimension.

c Install these items: 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with: 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR48 as shown in Section A15-A2 ’AFTER’:

a Put these items at FR48 temporarily in position: 1 crossbeam D5347035000600 Item 010 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 010, IS IN LINE WITH THE CROSSBEAMS AT FR47 AND FR52. b Mark the fastener holes as shown in View Y2-3 and Z2-3.

c Drill the marked holes with 3.3 mm (0.130 in.) diameter. d Transfer drill all other holes from the frame to the crossbeam.

e Drill all additional holes and open all holes to final dimension. f Remove the crossbeam. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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g Mark and drill the holes into FR48 as shown in Detail C3-3. h Put the crossbeam in position and install these items: 1 crossbeam D5347035000600 Item 010 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026 with: 32 rivet LN9198-4814CF Item 648

6 pin DAN5-6-5X Item 765 60 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 6 collar NSA5075-8 Item 808 16 pin DAN5-6-4 Item 964 34 pin DAN5-6-5 Item 965 10 pin DAN5-6-6 Item 966

2 pin DAN5-6-7 Item 967 6 pin DAN5-8-5 Item 985

i Put this item at FR48 in position as shown in Detail C3-3: 2 bushing D5347658620000 Item 204

j Transfer drill the holes from the frame to the bushings and open the holes to final dimension. k Install these items as shown in Detail C3-3: 2 bushing D5347658620000 Item 204 with: 2 collar NSA5075-6 Item 806 2 pin DAN5-6-7 Item 967 5 Replace the fasteners at FR48 between STGR42 LH and STGR42 RH:

a Remove the fasteners as shown in Section A15-A2 ’BEFORE’. b Open the holes to final dimension.

c Install these items as shown in Section A15-A2 ’AFTER’: 17 rivet LN9198-4814CF Item 648 6 Install the sections and the angles at FR48 between STGR34 LH/RH and STGR39 LH/RH as shown in Section A15-A2 ’AFTER’:

a Put these items in position: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 3 section D5347449520500 Item 032 3 section D5347449520400 Item 034 1 angle D5347470020000 Item 036 1 angle D5347470020100 Item 038

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items: 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 3 section D5347449520500 Item 032 3 section D5347449520400 Item 034 1 angle D5347470020000 Item 036 1 angle D5347470020100 Item 038 with: 32 rivet MBBN4477-4814 Item 548 40 rivet LN9198-4814CF Item 648

8 collar NSA5075-6 Item 806 8 pin DAN6-6-4 Item 864 (q) Modify the structure at FR49 between STGR34 LH and STGR34 RH. Refer to Kit 281118D06R03 Refer to Drawing(s): D53470075004 Sheet(s) 3 1 Replace the fasteners at FR49 between STGR34 RH and STGR36 RH as shown in Section B15-B3 ’AFTER’:

a Remove the existing fasteners in the affected area as shown in Section B15-B3 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. b Open the affected holes to final dimension.

c Install these items: 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Items 865 and 806, will be installed during the installation of the reinforcing straps at FR49. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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2 Install the reinforcing straps at FR49 between STGR35 LH/RH and STGR42 LH/RH as shown in Section B15-B3 ’AFTER’:

a Put these items at FR49 in position: 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

b Transfer drill the holes form the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes to final dimension. d Install these items: 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with: 58 rivet LN9198-4014CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit 281118D08R00. 3 Install the fittings at FR49 at STGR37 LH/RH as shown in Section B15-B3 ’AFTER’:

a Put these items at FR49 in position: 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

b Transfer drill the holes form the frame to the fittings and open all holes to final dimension.

c Install these items: 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with: 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR49 as shown in Section B15-B3 ’AFTER’: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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a Put these items at FR49 temporarily in position: 1 crossbeam D5347035000600 Item 010 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 010, IS IN LINE WITH THE CROSSBEAMS AT FR47 AND FR52. b Mark the fastener holes as shown in View Y3-3 and Z3-3.

c Drill the marked holes with 3.3 mm (0.130 in.) diameter. d Transfer drill all other holes from the frame to the crossbeam.

e Drill all additional holes and open all holes to final dimension. f Remove the crossbeam. g Mark and drill the holes into FR49 as shown in Detail C3-3. h Put the crossbeam in position and install these items: 1 crossbeam D5347035000600 Item 010 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026 with: 32 rivet LN9198-4814CF Item 648

6 pin DAN5-6-5X Item 765 60 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 6 collar NSA5075-8 Item 808 16 pin DAN5-6-4 Item 964 36 pin DAN5-6-5 Item 965

8 pin DAN5-6-6 Item 966 2 pin DAN5-6-7 Item 967 6 pin DAN5-8-5 Item 985

i Put this items at FR49 in position as shown in Detail C3-3: 2 bushing D5347658620000 Item 204

j Transfer drill the holes from the frame to the bushings and open the holes to final dimension. k Install these items as shown in Detail C3-3: 2 bushing D5347658620000 Item 204 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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with: 2 collar NSA5075-6 Item 806 2 pin DAN5-6-7 Item 967 5 Install the sections and the angles at FR49 between STGR34 LH/RH and STGR39 LH/RH as shown in Section B15-B3 ’AFTER’:

a Put these items in position: 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 1 section D5347449520500 Item 032 1 section D5347449520400 Item 034 1 angle D5347470020400 Item 044 1 angle D5347470020500 Item 046 2 angle D5347470020200 Item 048 2 angle D5347470020300 Item 050

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items: 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 1 section D5347449520500 Item 032 1 section D5347449520400 Item 034 1 angle D5347470020400 Item 044 1 angle D5347470020500 Item 046 2 angle D5347470020200 Item 048 2 angle D5347470020300 Item 050 with: 46 rivet MBBN4477-4814 Item 548 40 rivet LN9198-4814CF Item 648 6 Replace the riveting between clip and skin panel at FR49 between STGR34 LH/RH and STGR37 LH/RH as shown in Section B15-B3:

a Remove the existing rivets. b Open the holes and the countersinks to final dimension.

c Install this item: 23 rivet MBBN4477-4814 Item 548 (r) Modify the structure at FR50 between STGR34 LH and STGR34 RH. Refer to Kit 281118D06R03 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 315 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s): D53470075004 Sheet(s) 4 1 Replace the fasteners at FR50 between STGR34 RH and STGR36 RH as shown in Section C15-C4 ’AFTER’:

a Remove the existing fasteners in the affected area as shown in Section C15-C4 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. b Open the affected holes to final dimension.

c Install these items: 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Items 865 and 806, will be installed during the installation of the reinforcing straps at FR50. 2 Install the reinforcing straps at FR50 between STGR35 LH/RH and STGR42 LH/RH as shown in Section C15-C4 ’AFTER’:

a Put these items at FR50 in position: 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

b Transfer drill the holes form the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes to final dimension. d Install these items: 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with: 58 rivet LN9198-4014CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit 281118D08R00.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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3 Install the fittings at FR50 at STGR37 LH/RH as shown in Section C15-C4 ’AFTER’:

a Put these items at FR50 in position: 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

b Transfer drill the holes form the frame to the fittings and open all holes to final dimension.

c Install these items: 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with: 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR50 as shown in Section C15-C4 ’AFTER’:

a Put these items at FR50 in position: 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026 1 crossbeam D5347026000600 Item 052

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 052, IS IN LINE WITH THE CROSSBEAMS AT FR47 AND FR52. b Transfer drill all holes from the frame to the crossbeam.

c Put these items at FR50 between STGR42 LH and STGR42 RH in position: 1 support D5347470520000 Item 054 1 support D5347470520100 Item 056 1 web D5347470320000 Item 066

d Transfer drill the holes from the frame and skin panel to the shear web and the supports.

e Drill all additional holes and open all holes and all countersinks to final dimension. f Install these items: 1 plate D5337217620000 Item 012 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026 1 crossbeam D5347026000600 Item 052 1 angle D5347470520000 Item 054 1 angle D5347470520100 Item 056 1 web D5347470320000 Item 066 with: 12 rivet MBBN4477-4814 Item 548

4 rivet LN9198-4014CF Item 640 51 rivet LN9198-4814CF Item 648

6 pin DAN5-6-5X Item 765 56 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 12 collar NSA5075-8 Item 808 20 pin DAN5-6-4 Item 964 32 pin DAN5-6-5 Item 965

4 pin DAN5-6-6 Item 966 6 pin DAN5-8-5 Item 985 4 pin DAN5-8-6 Item 986 2 pin DAN5-8-7 Item 987 5 Install the sections and the angles at FR50 between STGR34 LH and STGR34 RH as shown in Section C15-C4 ’AFTER’:

a Put these items in position: 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 2 section D5347449520500 Item 032 2 section D5347449520400 Item 034 1 angle D5347470020400 Item 044 1 angle D5347470020500 Item 046 2 angle D5347470020200 Item 048 2 angle D5347470020300 Item 050 1 profile D5347449523400 Item 058 1 profile D5347449523600 Item 060 2 profile D5347449523200 Item 064 1 angle D5347470020800 Item 068 1 angle D5347470021000 Item 070 1 angle D5347470020600 Item 072 1 angle D5347470021200 Item 074

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel and the two holes in the angles, Item 064, and install with these items: 82 rivet MBBN4477-4814 Item 548 69 rivet LN9198-4814CF Item 648

4 collar NSA5075-6 Item 806 4 pin DAN5-6-4 Item 964 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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6 Replace the riveting between clip and skin panel at FR50 between STGR34 LH/RH and STGR37 LH/RH as shown in Section C15-C4 ’AFTER’:

a Remove the existing rivets. b Open the holes and the countersinks to final dimension.

c Install this item: 23 rivet MBBN4477-4800 Item 548 (s) Modify the structure at FR51 between STGR34 LH and STGR34 RH. Refer to Kit 281118D06R03 Refer to Drawing(s): D53470075004 Sheet(s) 16 1 Replace the fasteners at FR51 between STGR34 RH and STGR36 RH as shown in Section D15-D16 ’AFTER’:

a Remove the existing fasteners in the affected area as shown in Section D15-D16 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. b Open the affected holes to final dimension.

c Install these items: 34 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 16 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 6 pin DAN5-6-5 Item 965 NOTE : The remaining fasteners, Items 865 and 806, will be installed during the installation of the reinforcing straps at FR51. 2 Install the reinforcing straps at FR51 between STGR35 LH/RH and STGR42 LH/RH as shown in Section D15-D16 ’AFTER’:

a Put these at FR51 in position: 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes and all countersinks to final dimension. d Install these items: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with: 58 rivet LN9198-4014CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit 281118D08R00. 3 Install the fittings at FR51 at STGR37 LH/RH as shown in Section D15-D16 ’AFTER’:

a Put these items at FR51 in position: 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

b Transfer drill the holes from the frame to the fittings and open all holes to final dimension.

c Install these items: 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with: 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR51 as shown in Section D15-D16 ’AFTER’:

a Put these items at FR51 in position: 1 plate D5337217620000 Item 012 2 filler D5337217620800 Item 026 1 crossbeam D5347035300600 Item 076 1 sheet D5337217620700 Item 078

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 076, IS IN LINE WITH THE CROSSBEAMS AT FR47 AND FR52. b Transfer drill all holes from the frame to the crossbeam.

c Put this item at FR51 in position as shown in Section B16-B16: 1 support angle D5347658420000 Item 102 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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d Put these items at FR51 between STGR42 LH and STGR42 RH in position: 1 support D5347470520000 Item 054 1 support D5347470520100 Item 056 1 plate D5347470420400 Item 080

e Transfer drill the holes from the frame and skin panel to the shear web and the supports. f Drill all additional holes and open all holes and all countersinks to final dimension. g Install these items: 1 plate D5337217620000 Item 012 2 filler D5337217620800 Item 026 1 angle D5347470520000 Item 054 1 angle D5347470520100 Item 056 1 crossbeam D5347035300600 Item 076 1 plate D5337217620700 Item 078 1 web D5347470420400 Item 080 1 support angle D5347658420000 Item 102 with: 12 rivet MBBN4477-4814 Item 548 16 rivet LN9198-4014CF Item 640 57 rivet LN9198-4814CF Item 648

6 pin DAN5-6-5X Item 765 44 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 12 collar NSA5075-8 Item 808 19 pin DAN5-6-4 Item 964 21 pin DAN5-6-5 Item 965

2 pin DAN5-6-6 Item 966 2 pin DAN5-6-8 Item 968 6 pin DAN5-8-5 Item 985 3 pin DAN5-8-6 Item 986 3 pin DAN5-8-7 Item 987 5 Install the sections and the angles at FR51 between STGR34 LH/RH and STGR42 LH/RH as shown in Section D15-D16 ’AFTER’:

a Put these items in position: 1 section D5347449520300 Item 028 1 section D5347449520500 Item 032 1 angle D5347470020400 Item 044 2 angle D5347470020200 Item 048 1 angle D5347470021600 Item 082 1 angle D5347470021800 Item 084 1 angle D5347470043800 Item 088 2 angle D5347470021400 Item 090 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 angle D5347470022200 Item 092 1 section D5347449520200 Item 094 1 section D5347449520400 Item 096 1 angle D5347470020500 Item 098 2 angle D5347470020300 Item 100

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel and install with these items: 34 rivet MBBN4477-4814 Item 548 62 rivet LN9198-4814CF Item 648

4 pin DAN6-6-7X Item 667 4 pin DAN6-6-9X Item 669 27 collar NSA5075-6 Item 806

8 collar DAN11-6X Item 807 17 pin DAN6-6-5 Item 865 10 pin DAN6-6-7 Item 867 6 Replace the riveting between clip and skin panel at FR51 between STGR40 LH/RH and STGR42 LH/RH as shown in Section D15-D16 ’AFTER’:

a Remove the existing rivets. b Open the holes and the countersinks to final dimension.

c Install these items: 8 rivet MBBN4477-4814 Item 548 4 pin DAN6-6-7X Item 667 4 pin DAN6-6-9X Item 669 8 pin DAN6-6-8Y Item 678 8 collar NSA5330-6 Item 803 8 collar DAN11-6X Item 807 7 Replace the riveting between stringer and skin panel at FR51 at STGR41 RH as shown in View A16-A16:

a Remove the existing rivets. b Open the holes and the countersinks to final dimension.

c Install these items: 8 pin DAN6-6-8Y Item 678 8 collar NSA5330-6 Item 803 (t) Modify the structure at FR53 between STGR36 LH and STGR42 LH. Refer to Kit 281118D06R03 Refer to Drawing(s): D53470075004 Sheet(s) 6 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 Remove this item at FR53 as shown in Section E15-E6 ’BEFORE’:

a Remove and discard this item: 1 shim D5347061120200 Item (402) discard 2 Install the reinforcing strap at FR53 between STGR35 LH and STGR42 LH as shown in Section E15-E6 ’AFTER’:

a Put this item at FR53 in position: 1 strap D5347448420200 Item 022

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes and all countersinks to final dimension. d Install these items: 1 strap D5347448420200 Item 022 with: 29 rivet LN9198-4014CF Item 640

4 collar NSA5075-6 Item 806 4 pin DAN6-6-5 Item 865 (u) Install the shear plates between FR48 and FR51 at STGR43 LH. Refer to Kit 281118D06R03 1 Install the shear plate between FR48 and FR49 at STGR43 LH as shown in Section F15-F7: Refer to Drawing(s): D53470075004 Sheet(s) 3 and 7

a Put this item in position: 1 plate D5347471321200 Item 104

b Put this item in position as shown in Sheet 3, Section B15-B3: 1 section D5347449521800 Item 020

c Transfer drill the holes to the section, Item 020. d Drill the additional holes from the shear plate to the stringer and crossbeams and open all holes to final dimension.

e Install these items: 1 section D5347449521800 Item 020 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 plate D5347471321200 Item 104 with: 34 rivet LN9198-4014CF Item 640

2 rivet LN9198-4814CF Item 648 2 collar NSA5075-6 Item 806 2 pin DAN5-6-7 Item 967 2 Install the shear plates between FR49 and FR51 at STGR43 LH as shown in Section F15-F7: Refer to Drawing(s): D53470075004 Sheet(s) 4, 7 and 16

a Put this item in position: 2 plate D5347471320800 Item 106

b Put this item in position as shown in Sheet 4, Section C15-C4 and Sheet 16, Section D15-D16. 2 section D5347449522000 Item 062

c Transfer drill the holes to the sections, Item 062. d Drill the additional holes from the shear plate to the stringer and crossbeams and open all holes to final dimension.

e Install these items: 2 section D5347449522000 Item 062 2 plate D5347471320800 Item 106 with: 68 rivet LN9198-4014CF Item 640

4 rivet LN9198-4814CF Item 648 4 collar NSA5075-8 Item 808 4 pin DAN5-8-7 Item 987 (v) Install the plates between FR48 and FR59 at STGR38 LH and STGR38 RH. Refer to Kit 281118D06R03 1 Install the plates and the angles between FR48 and FR59 at STGR38 LH as shown in Sections H15-H8 and K15-K11: Refer to Drawing(s): D53470075004 Sheet(s) 8 and 11

a Put these items in position: 2 plate D5347471500200 Item 108 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 plate D5347471500000 Item 110 1 plate D5347471500600 Item 112 1 plate D5347471500800 Item 114 1 plate D5347471501000 Item 116 6 angle D5347470120000 Item 128 6 angle D5347470120200 Item 130 1 section D5347065020400 Item 208 1 plate D5347048800400 Item 214 1 plate D5347048900400 Item 216 1 plate D5347049200400 Item 218 2 angle D5347046824000 Item 228 1 angle D5347046823800 Item 230 1 angle D5347046823600 Item 232 1 angle D5347046824200 Item 234 1 angle D5347046824400 Item 236 NOTE : Install the angle, Item 130, together with the section, Item 028. b Transfer drill the holes from the stringer and frames to the plates and the angles.

c Transfer drill the holes from the skin panel to the section at FR52. d Drill the additional holes and open all holes to final dimension.

e Install the listed items as shown in Sections H15-H8 and K15-K11 with: 230 rivet LN9198-4014CF Item 640 4 pin DAN6-6-5X Item 665 3 pin DAN6-6-6X Item 666 3 pin DAN6-6-7X Item 667 5 pin DAN5-6-4X Item 764 8 pin DAN5-6-6X Item 766 3 pin DAN5-6-8X Item 768 16 collar NSA5075-6 Item 806 26 collar DAN11-6X Item 807 10 pin DAN5-6-4 Item 964

6 pin DAN5-6-8 Item 968 2 Install the plates and angles between FR48 and FR59 at STGR38 RH as shown in Sections G15-G17 and J15-J17: Refer to Drawing(s): D53470075004 Sheet(s) 17

a Put these items in position: 2 plate D5347471500300 Item 118 1 plate D5347471500100 Item 120 1 plate D5347471501400 Item 122 1 plate D5347471502600 Item 124 1 angle D5347659100000 Item 126 4 angle D5347470120100 Item 132 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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5 angle D5347470120300 Item 134 1 angle D5347046824300 Item 222 1 angle D5347046824600 Item 224 NOTE : Install the angle, Item 134, together with the section, Item 029, at FR48. b Transfer drill the holes from the stringer and frames to the plates and the angles and open all holes to final dimension.

c Install the listed items as shown in Sections G15-G17 and J15-J17 with: 126 rivet LN9198-4014CF Item 640 2 pin DAN5-6-4X Item 764 1 pin DAN5-6-8X Item 768 3 collar NSA5075-5 Item 804 6 collar NSA5075-6 Item 806 3 collar DAN11-6X Item 807 3 pin DAN5-5-5 Item 945 4 pin DAN5-6-4 Item 964 2 pin DAN5-6-8 Item 968 (w) Install the corner sections at STGR38 LH/RH between FR48 and FR59. Refer to Kit 281118D06R03 Refer to Drawing(s): D53470075004 Sheet(s) 2, 3, 4, 6, 10, 11, 16 and 17 1 Install the corner sections at STGR38 LH between FR48 and FR59 as shown in Details X9-10 and Y15-11:

a Put these items between FR48 and FR56 in position: 1 profile D5347047500800 Item 154 1 profile D5347047600800 Item 156

b Transfer drill the holes from the fittings to the corner sections as shown in Details B2-2, B3-3, B4-4, B16-16 and A6-6.

c Drill the holes from the corner sections to the plates between FR48 and FR59 as shown in Details X9-10 and Y15-11. d Open the holes to final dimension and countersink the holes.

e Install these items: 1 profile D5347047500800 Item 154 1 profile D5347047600800 Item 156 with: 16 rivet MBBN4477-4014 Item 540 12 rivet MBBN4477-4814 Item 548 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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87 rivet DIN65399-3208CF Item 732 f The holes with 5.6 mm (0.220 in.) diameter between FR48 and FR51 as shown in Detail X9-10 will transfer from the roller tracks. 2 Install the corner section at STGR38 RH between FR48 and FR59 as shown in Details Z9-10 and Z15-11:

a Put this item between FR48 and FR52/A in position: 1 profile D5347048100600 Item 152

b Transfer drill the holes from the fittings to the corner section as shown in Details C2-2, C3-3, C4-4 and C16-16.

c Drill the holes from the corner section to the plates between FR48 and FR59 as shown in Details Z9-10 and Z15-11. d Open the holes to final dimension and countersink the holes.

e Install these items: 1 profile D5347048100600 Item 152 with: 8 rivet MBBN4477-4014 Item 540 12 rivet MBBN4477-4814 Item 548 48 rivet DIN65399-3208CF Item 732 f The holes with 5.6 mm (0.220 in.) diameter between FR48 and FR51 as shown in Detail Z9-10 will transfer from the roller tracks. (x) Install a bracket at the passenger compartment floor structure at FR53. Refer to Kit 281118D55R00 Refer to drawing(s) : D53472833002 Sheet(s) 2 1 Put the bracket, Item 000, in position as shown in Detail Z2-2. 2 Transfer drill the holes and open them to final dimension. 3 Install this item : 1 bracket D5347212920400 Item 000

with : 10 washer NAS1252-10L Item 400

4 nut NSA5182-3 Item 401 2 bolt NSA5031-3-4 Item 413 2 bolt NSA5031-3-5 Item 414 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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(y) Modify the crossbeams from FR48 thru FR52 for the roller track installation. Refer to Kit 281118D06R03 Refer to drawings: D53470075004 Sheet(s) 9 and 10 1 Drill the holes in the crossbeams at FR48, FR49, FR50 and FR51 as shown in Details U9-9 and W9-9:

a Mark and drill the holes with 5.6 mm (0.220 in.). 2 Install the nuts, Item 508, at the crossbeam at FR52 as shown in Detail W15-10:

a Mark and drill the holes with 5.2 mm (0.205 in.). b Put the nuts in position, drill the holes for the rivets and install this item: 4 nut NAS1791A3-1 Item 508 with: 8 rivet DIN65399-2408CF Item 724 (z) Install the water drain connection between FR47 and FR48. Refer to Kit 281118D06R03 Refer to drawings: D53372362000 Sheet(s) 9 D53470075004 Sheet(s) 13 1 Make a cutout between 63.7 mm (2.508 in.) and 64.3 mm (2.531 in.) diameter in the skin panel between FR47 and FR48 and between STGR42 RH and STGR43 RH as shown in drawing D53470075004, Sheet 13, Sections A12-A13 and A13-A13. 2 Install the doubler at the outer skin as shown in the drawing D53470075004, Sheet 13, Section A12-A13 and the drawing D53372362000, Sheet 9, Detail U1-9. NOTE : Drawing D53372362000 shows the position of the doubler and fasteners for the attachment. The fasteners are contained in Kit 281118D05R06. CAUTION : REMOVE THE EXISTING RIVETS CAREFULLY. THE HEADS OF THE RIVETS WILL BE USED DURING THE DOUBLER INSTALLATION FOR THE EXISTING COUNTERSINKS IN THE SKIN PANEL.

a Remove the existing fasteners in the affected area. b Put this item in position as shown in drawing D53470075004, Sheet 13, Section A12-A13 and drawing D53372362000, Sheet 9, Detail U1-9: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 doubler D5347646320200 Item 160

c Transfer drill the holes. d Drill the additional holes and open all holes to final dimension as shown in drawing D53470075004, Sheet 13, Detail A13-13.

e Install this item: 1 doubler D5347646320200 Item 160 with: 33 rivet LN9198-4814CF Item 648 12 pin DAN5-6-8X Item 768 18 pin DAN5-6-9X Item 769

4 pin DAN5-6-11X Item 771 10 pin DAN5-6-12X Item 772 14 collar NSA5075-6 Item 806 44 collar DAN11-6X Item 807 18 collar DAN11-8X Item 810

4 pin DAN5-8-7X Item 887 6 pin DAN5-8-11X Item 891 8 pin DAN5-8-12X Item 892 14 pin DAN5-6-6 Item 966 NOTE : The Items 768, 769, 771, 772, 807, 810, 887, 891 and 892 are contained in Kit 281118D05R06. 3 Install the tube as shown in drawing D53470075004, Sheet 13, Section A12-A13 and in Detail A13-13:

a Put these items in position: 1 tube D5347669000000 Item 172 2 shim D5347472120000 Item 176

b Transfer drill the eight holes as shown in drawing D53372362000, Sheet 9, Detail U1-9.

c Drill the eight holes as shown in drawing D53470075004, Sheet 13, Detail Z13-13. d Open all holes to final dimension.

e Install these items: 1 tube D5347669000000 Item 172 2 shim D5347472120000 Item 176 with: 8 pin DAN5-6-11X Item 771 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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8 collar NSA5075-6 Item 806 8 collar DAN11-6X Item 807 2 pin DAN6-6-6 Item 866 6 pin DAN5-6-10 Item 970 NOTE : The Items 771 and 807 are contained in Kit 281118D05R06, refer to drawing D53372362000, Sheet 9. f Drill the four holes for the receptacles, Item 504, with 5.6 mm (0.220 in.) diameter as shown in drawing D53470075004, Sheet 13, Detail Z13-13 and install this item: 4 receptacle ABS0337-01A Item 504 with: 8 rivet DIN65399-2408CF Item 724

g Install at the tube, Item 172, as shown in drawing D53470075004, Sheet 13, Section A12-A13 these items: 1 plate D5347669200000 Item 166 1 plug D5347669100000 Item 174 1 ring MS16625-4212 Item 500 1 screw NAS1096-3-10 Item 506 (aa) Install the water drain connection and the cavity drain access cover between FR49 and FR50. Refer to Kit 281118D06R03 Refer to Drawing(s): D53470075004 Sheet(s) 14 1 Make a cutout between 63.7 mm (2.508 in.) and 64.3 mm (2.531 in.) diameter in the skin panel between FR49 and FR50 and between STGR42 LH and STGR43 LH as shown in Sections B12-B14 and View A14-14. 2 Install the doubler at the outer skin as shown in Section B12-B14: CAUTION : REMOVE THE EXISTING RIVETS CAREFULLY. THE HEADS OF THE RIVETS WILL BE USED DURING THE DOUBLER INSTALLATION FOR THE EXISTING COUNTERSINKS IN THE SKIN PANEL.

a Remove the existing fasteners in the affected area. b Put this item in position as shown in View A14-14: 1 doubler D5347646320000 Item 162

c Transfer drill the holes.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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d Drill the additional holes as shown in View A14-14 and open all holes to final dimension.

e Install this item: 1 doubler D5347646320000 Item 162 with: 48 rivet LN9198-4814CF Item 648

8 pin DAN5-6-8Y Item 778 8 collar NSA5330-6 Item 803 154 collar NSA5075-6 Item 806

25 pin DAN5-6-5 Item 965 58 pin DAN5-6-6 Item 966 14 pin DAN5-6-7 Item 967 57 pin DAN5-6-8 Item 968 3 Install the tube as shown in Section B12-B14 and View A14-14:

a Put these items in position: 1 tube D5347669000000 Item 172 2 shim D5347472120000 Item 176

b Transfer drill the eight holes from the stringers to the tube as shown in Detail Y14-14.

c Drill the eight holes as shown in Detail Y14-14. d Open all holes to final dimension.

e Install these items: 1 tube D5347669000000 Item 172 2 shim D5347472120000 Item 176 with: 16 collar NSA5075-6 Item 806

2 pin DAN6-6-6 Item 866 14 pin DAN5-6-10 Item 970 f Drill the four holes for the receptacles, Item 504, with 5.6 mm (0.220 in.) diameter as shown in Detail Y14-14 and install this item: 4 receptacle ABS0337-01A Item 504 with: 8 rivet DIN65399-2408CF Item 724

g Install these items at the tube, Item 172, as shown in Section B12-B14: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 plate D5347669200000 Item 166 1 plug D5347669100000 Item 174 1 ring MS16625-4212 Item 500 1 screw NAS1096-3-10 Item 506 4 Make a cutout in the skin panel between FR49 and FR50 and between STGR40 LH and STGR41 LH as shown in View A14-14. 5 Install the nuts, Item 510, around the cutout as shown in Detail Z14-14:

a Remove the six rivets in the stringer and open the holes to 5.6 mm (0.220 in.) diameter. b Drill the four holes with 5.6 mm (0.220 in.) diameter in the skin.

c Install these items: 4 shim D5347470220000 Item 178 10 nut NAS1474A3 Item 510 with: 20 rivet DIN65399-2408CF Item 724 d Install this item as shown in Section B12-B14: 1 cover D5347470920200 Item 164 with: 10 screw NAS1153E7 Item 502 (ab) Drill three holes in the outer skin between FR47 and FR49 and between STGR43 LH and STGR42 RH. Refer to Kit 281118D06R03 Refer to Drawing(s): D53470075004 Sheet(s) 12 1 Drill two holes with 20.0 mm (0.787 in.) diameter and one hole with 14.5 mm (0.578 in.) diameter as shown in View C15-12. (ac) Measure the level of the AFT cargo compartment floor structure. Refer to Kit 281118D24R00 Refer to Drawing(s): D25572631008 Sheet(s) 10 thru 12 1 Install the roller tracks between FR46 and FR52 temporarily as shown in drawing: NOTE : Attach the roller tracks only at the frames. 1 track D2557221301400 Item 088 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 track D2557221300600 Item 089 1 track D2557221301200 Item 092

with: screw NAS1102-3-10 Item 007 nut NAS1726-3E Item 008 screw NAS1102-3-9 Item 039 screw NAS1100-3-10 Item 070 screw NAS1100-3-9 Item 083 screw NAS1100-3-11 Item 084 screw NAS1100-3-7 Item 087 2 Do the leveling of the roller tracks between FR46 and FR52 to get the necessary shim thicknesses, refer to drawing D25573524, Sheet 1 thru 4. 3 Remove the roller tracks between FR46 and FR52. (ad) Install the shims on the floor framework of the AFT cargo compartment between FR47 and FR51. Refer to Kit 281118D22R00 Refer to Drawing(s): D25572631004 Sheet(s) 6 1 Install these items as shown in drawing D25572631004, Sheet 6, Detail U1-6:

2 plug D2557206229800 Item 047 4 screw NAS1102-3-10 Item 048 2 Put these items in position as required as shown in drawing D25572631004, Sheet 6, Detail U1-6: NOTE : The quantity of the shims (maximum 3) at each position is dependent on the roller track measurement between FR47 and FR52. NOTE : Holes in the shims should be drilled in accordance with the roller tracks. Longitudinal holes are allowed in the shims. 16 shim D2557214635000 Item 000 16 shim D2557214635100 Item 001 16 shim D2557214635200 Item 002

1 shim D2557214633400 Item 003 1 shim D2557214633500 Item 004 1 shim D2557214633600 Item 005 2 shim D2557214637600 Item 006 2 shim D2557214637700 Item 007 2 shim D2557214637800 Item 008 1 shim D2557214635400 Item 009 1 shim D2557214635500 Item 010 1 shim D2557214635600 Item 011 1 shim D2557214638400 Item 012 1 shim D2557214638500 Item 013 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 333 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 shim D2557214638600 Item 014 1 shim D2557214638800 Item 015 1 shim D2557214638900 Item 016 3 shim D2557214638100 Item 019 3 shim D2557214638200 Item 020 4 shim D2557214640000 Item 023 4 shim D2557214640200 Item 024 2 shim D2557214639600 Item 025 2 shim D2557214639700 Item 026 2 shim D2557214639800 Item 027 8 shim D2557214653200 Item 030 2 shim D2557214653000 Item 031 1 shim D2557214649200 Item 032 1 shim D2557214649300 Item 033 1 shim D2557214649400 Item 034 1 shim D2557214645200 Item 035 1 shim D2557214645300 Item 036 1 shim D2557214645400 Item 037 1 shim D2557214652000 Item 038 1 shim D2557214652100 Item 039 1 shim D2557214652200 Item 040 2 shim D2557214644800 Item 041 2 shim D2557214644900 Item 042 2 shim D2557214645000 Item 043 1 shim D2557214644000 Item 044 1 shim D2557214644100 Item 045 1 shim D2557214644200 Item 046 (ae) Install the roller tracks between FR47 and FR52 in the AFT cargo compartment. Refer to Kit 281118D24R00 1 Install the track between FR47 and FR52 at the centering position. Refer to Drawing(s): D25572631008 Sheet(s) 11 and 13

a Put these items in position as shown in drawing D25572631008, Sheet 11, Detail T1-11 and Sheet 13, View L1-13 and Detail X: 2 shim D2557268030600 Item 051 2 bearing support D2557226520400 Item 052 2 block D2557226120200 Item 053 1 track D2557221300600 Item 089 NOTE : For the alignment connect the bearing supports, Item 052, and the track, Item 089, with rigging pins temporarily. b Transfer drill the holes to the bearing supports, Item 052.

c Drill the additional holes. d Install these items as shown in View L1-13: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 334 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 shim D2557268030600 Item 051 2 bearing support D2557226520400 Item 052 with: 8 pin DAN7-5-5 Item 061 4 pin DAN7-5-6 Item 062 12 collar DAN12-5 Item 063

e Transfer drill the holes from the track, Item 089. f Install this item with sealant (Mat. No. 09-005) as shown in Detail T1-11: 1 track D2557221300600 Item 089 with: 32 screw NAS1100-3-14 Item 006 10 screw NAS1102-3-10 Item 007 80 nut NAS1726-3E Item 008

5 screw NAS1102-3-9 Item 039 1 screw NAS1100-3-10 Item 070 6 screw NAS1102-3-11 Item 080 18 screw NAS1100-3-9 Item 083

2 screw NAS1100-3-11 Item 084 6 screw NAS1100-3-7 Item 087 NOTE : Dependent on the thickness of the shims it could be necessary to install alternative bolts as shown in the table, refer to drawing D25572631008, Sheet 11. g Remove the rigging pins and connect the bearing support, Item 052, and the track, Item 089, with these items as shown in drawing D25572631008, Sheet 13, Detail X: 2 bolt NSA5042C05-180 Item 054 2 nut NSA5060-4 Item 055 2 washer NAS1149C0432R Item 056 2 washer NAS1149C0532R Item 057 2 pin MS24665-153 Item 058

h Put these items at the track, Item 089, in position as shown in Detail T1-11: 1 plate D2557268028600 Item 049 1 doubler D2557268121000 Item 050 drill the additional holes and install with these items: 21 nut NAS1726-3E Item 008 21 screw NAS1102-3-9 Item 039 i Install this item with sealant (Mat. No. 09-005) as shown in Detail T1-11: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 335 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 plate D2557235621000 Item 091 with: 14 nut NAS1726-3E Item 008 14 screw NAS1102-3-14 Item 082 14 screw NAS1100-3-7 Item 087 2 Install the track between FR47 and FR51 at +Y623. Refer to Drawing(s): D25572631008 Sheet(s) 12 and 13

a Put these items in position as shown in drawing D25572631008, Sheet 12, Detail W1-12 and Sheet 13, View L1-13 and Detail X: 2 shim D2557268030600 Item 051 2 bearing support D2557226520400 Item 052 2 block D2557226120200 Item 053 1 track D2557221301200 Item 092 NOTE : For the alignment connect the bearing support, Item 052, and the track, Item 092, with rigging pins temporarily. b Transfer drill the holes to the bearing support, Item 052.

c Drill the additional holes. d Install these items as shown in View L1-13: 2 shim D2557268030600 Item 051 2 bearing support D2557226520400 Item 052 with: 8 pin DAN7-5-5 Item 061 4 pin DAN7-5-6 Item 062 12 collar DAN12-5 Item 063

e Transfer drill the holes from the track, Item 092. f Install this item with sealant (Mat. No. 09-005) as shown in Detail W1-12: 1 track D2557221301200 Item 092 with: 45 screw NAS1100-3-14 Item 006

8 screw NAS1102-3-10 Item 007 80 nut NAS1726-3E Item 008

5 screw NAS1102-3-9 Item 039 1 screw NAS1100-3-10 Item 070 2 screw NAS1102-3-11 Item 080 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 336 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

12 screw NAS1100-3-9 Item 083

2 screw NAS1100-3-11 Item 084 6 screw NAS1100-3-7 Item 087 NOTE : Dependent on the thickness of the shims it could be necessary to install alternative bolts as shown in the table, refer to drawing D25572631008, Sheet 12. g Remove the rigging pins and connect the bearing supports, Item 052, and the track, Item 092, with these items as shown in drawing D25572631008, Sheet 13, Detail X: 2 bolt NSA5042C05-180 Item 054 2 nut NSA5060-4 Item 055 2 washer NAS1149C0432R Item 056 2 washer NAS1149C0532R Item 057 2 pin MS24665-153 Item 058 3 Install the track between FR47 and FR51 at -Y623. Refer to Drawing(s): D25572631008 Sheet(s) 10 and 13

a Put these items in position as shown in drawing D25572631008, Sheet 10, Detail V1-10 and Sheet 13, View L1-13 and Detail X: 2 shim D2557268030600 Item 051 2 bearing support D2557226520400 Item 052 2 block D2557226120200 Item 053 1 track D2557221301400 Item 088 NOTE : For the alignment connect the bearing supports, Item 052, and the track, Item 088, with rigging pins temporarily. b Transfer drill the holes to the brackets, Item 052.

c Drill the additional holes. d Install these items as shown in View L1-13: 2 shim D2557268030600 Item 051 2 bearing supports D2557226520400 Item 052 with: 8 pin DAN7-5-5 Item 061 4 pin DAN7-5-6 Item 062 12 collar DAN12-5 Item 063

e Transfer drill the holes from the track, Item 088. f Install this item with sealant (Mat. No. 09-005) as shown in Detail V1-10: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 337 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 track D2557221301400 Item 088 with: 8 screw NAS1102-3-10 Item 007 80 nut NAS1726-3E Item 008

5 screw NAS1102-3-9 Item 039 1 screw NAS1100-3-10 Item 070 2 screw NAS1102-3-11 Item 080 12 screw NAS1100-3-9 Item 083

2 screw NAS1100-3-11 Item 084 50 screw NAS1100-3-7 Item 087 NOTE : Dependent on the thickness of the shims it could be necessary to install alternative bolts as shown in the table, refer to drawing D25572631008, Sheet 10. g Remove the rigging pins and connect the bearing supports, Item 052, and the track, Item 088, with these items as shown in drawing D25572631008, Sheet 13, Detail X: 2 bolt NSA5042C05-180 Item 054 2 nut NSA5060-4 Item 055 2 washer NAS1149C0432R Item 056 2 washer NAS1149C0532R Item 057 2 pin MS24665-153 Item 058 (af) Adjust the YZ-latches at FR47, FR48 and FR49. Refer to Kit 281118D23R01 Refer to Drawing(s): D25572631006 Sheet(s) 7 1 Put this item temporarily in position as shown in drawing, Details O7-7 and K7-8:

6 YZ-latch D2557238000400 Item 001

with: 24 bolt MS21250-03006 Item 004 24 nut NAS1726-3E Item 005 NOTE : The Items 001, 004 and 005 are contained in Kit 281118D23R01. 2 Put the tool D255-72711-004W6400-01 between FR47 and FR49 in position as shown in drawing D25572631008, Sheet 9 and 14. 3 Lock the three XZ-latches at FR50 at the roller tracks. 4 Ensure that the tool D255-72711-004W6400-01 has full contact with the rollers of the roller tracks.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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5 Adjust the X-gaps with the adjustment screws as shown in drawing D25572631008, Sheet 14:

a Adjust the X-gaps with the adjustment screws between 0.65 mm (0.026 in.) and 1.65 mm (0.065 in.) at all areas. b Secure the adjustment screws with lockwire (Mat. No. 19-010). 6 Adjust the Z-gaps between the tool D255-72711-004W6400-01 and the YZ-latches at FR47, FR48 and FR49 as shown in drawing D25572631006, Sheet 9:

a Measure the Z-gap at FR47, FR48 and FR49. b If are the gaps not between 2 mm (0.078 in.) and 4 mm (0.157 in.), install shims under the affected YZ-latches

c If are the gaps correct, install the YZ-latches. 7 Adjust the -Ygaps between the tool D255-72711-004W6400-01 and the YZ-latches at FR47, FR48 and FR49 as shown in drawing D25572631006, Sheet 9:

a Measure the -Ygap at FR47, FR48 and FR49. b If are the gaps not between 0.5 mm (0.019 in.) and 1.5 mm (0.059 in.), remove the plate at the affected YZ-latches and adjust the -Ygap with the eccentric bolt as shown in drawing D25572631006, Sheet 9. 8 Unlock the three XZ-latches at FR50 at the roller tracks and remove the tool D255-72711-004W6400-01. (ag) Adjust the YZ-latches at FR50, FR51 and FR52. Refer to Kit 281118D23R01 Refer to Drawing(s): D25572631006 Sheet(s) 7 1 Put these items temporarily in position as shown in drawing, Detail V7-7:

4 YZ-latch D2557238000000 Item 002

with: 16 bolt MS21250-03006 Item 004 16 nut NAS1726-3E Item 005 NOTE : The Items 002, 004 and 005 are contained in Kit 281118D23R01. 2 Put the tool D255-72711-004W6400-01 between FR50 and FR52 in position as shown in drawing D25572631008, Sheet 9 and 14. 3 Lock the XZ-latches at FR50 and FR53 at the roller tracks. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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4 Adjust the Z-gaps between the tool D255-72711-004W6400-01 and the YZ-latches at FR50, FR51 and FR52 as shown in drawing D25572631006, Sheet 9:

a Measure the Z-gap at FR50, FR51 and FR52. b At FR50 and FR51: - If are the gaps not between 2 mm (0.078 in.) and 4 mm (0.157 in.), install shims under the affected YZ-latches. - If are the gaps correct, install the YZ-latches.

c At FR52: - If are the gaps not between 2 mm (0.078 in.) and 4 mm (0.157 in.), install shims under the affected YZ-latches. - If are the gaps correct, install the YZ-latches. 5 Adjust the -Ygaps between the tool D255-72711-004W6400-01 and the YZ-latches at FR50 and FR51 as shown in drawing D25572631006, Sheet 9:

a Measure the -Ygap at FR50 and FR51. b If are the gaps not between 0.5 mm (0.019 in.) and 1.5 mm (0.059 in.), remove the plate at the affected YZ-latches and adjust the -Ygap with the eccentric bolt as shown in drawing D25572631006, Sheet 9. 6 Unlock the XZ-latches at FR50 and FR53 at the roller tracks and remove the tool D255-72711-004W6400-01. (ah) Install the shims on the frames of the AFT cargo compartment at FR47, FR48, FR49, FR50 and FR51. Refer to Kit 281118D22R00 Refer to Drawing(s): D25572631004 Sheet(s) 6 1 Put these items with sealant (Mat. No. 09-005) in position as required as shown in drawing D25572631004, Sheet 6, Detail U1-6: NOTE : The quantity of the shims at each position is dependent on the measurement of gaps between the tool D255-72711-004W6400-01 and the YZ-latches at FR47, FR48, FR49, FR50 and FR51. 10 shim D2557214632000 Item 021 10 shim D2557214631800 Item 022 (ai) Install the YZ-latches in the AFT cargo compartment at FR47, FR48, FR49, FR50 and FR51. Refer to Kit 281118D23R01 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 340 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s): D25572631006 Sheet(s) 7 and 8 1 Install this item with sealant (Mat. No. 09-005) at FR47 as shown in Detail O7-7:

2 latch D2557238000400 Item 001

with: 2 bolt MS21250-03008 Item 003 10 bolt MS21250-03006 Item 004 12 nut NAS1726-3E Item 005

4 screw NAS1096-3-7 Item 006

NOTE : Dependent on the thickness of the shims it could be necessary to install alternative bolts as shown in the table, refer to drawing D25572631006, Sheet 7. 2 Install this item with sealant (Mat. No. 09-005) at FR48 and FR49 as shown in Detail K7-8: 4 latch D2557238000400 Item 001

with: 4 bolt MS21250-03008 Item 003 20 bolt MS21250-03006 Item 004 24 nut NAS1726-3E Item 005

8 screw NAS1096-3-7 Item 006

NOTE : Dependent on the thickness of the shims it could be necessary to install alternative bolts as shown in the table, refer to drawing D25572631006, Sheet 8. 3 Install this item with sealant (Mat. No. 09-005) at FR50 and FR51 as shown in Detail V7-7: 4 latch D2557238000000 Item 002

with: 4 bolt MS21250-03008 Item 003 12 bolt MS21250-03006 Item 004 16 nut NAS1726-3E Item 005 NOTE : Dependent on the thickness of the shims it could be necessary to install alternative bolts as shown in the table, refer to drawing D25572631006, Sheet 7. (aj) Install the shims under the track and the YZ-latches between FR52 and FR59. Refer to Kit 281118D21R00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 341 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s): D25572631002 Sheet(s) 5 D25573524000 Sheet(s) 1 thru 4 NOTE : At a junction between new and existing roller tracks it is not allowed to shim only the new tracks. The same amount of shims must be placed below the new and the existing tracks. It may be necessary to shim the AFT roller tracks also. To get the necessary shim thicknesses, refer to drawing D25573524000, Sheet 1 thru 4. 1 Measure the difference in vertical direction at FR52 between both roller tracks in center line position. 2 Remove and retain the AFT cargo compartment ball mats between FR52A and FR56, refer to AMM 25-52-22, Page block 401. 3 Remove and retain this item as shown in drawing D25572631002, Sheet 5, Detail Z1-5 and refer to AMM 25-52-21, Page block 401: 1 track D25572213008 Item A

NOTE : Retain the Item A. NOTE : Discard the attachment parts. 4 Remove and retain the YZ-latches between FR52 and FR59 as shown in drawing D25572631006, Sheet 8, Details U8 and V8 and refer to AMM 25-52-44, Page block 401: 3 YZ-latch D2557238000000 Item A 8 YZ-latch D2557235000200 Item B

NOTE : Retain the Items A and B. NOTE : Discard the attachment parts. 5 Put these items in position as required as shown in drawing D25572631002, Sheet 4,: NOTE : The quantity of the shims at each position is depended on the measurement at FR52. 8 shim D2557214637400 Item 000 8 shim D2557214637200 Item 001 6 shim D2557214635000 Item 002 6 shim D2557214635100 Item 003 6 shim D2557214635200 Item 004 3 shim D2557214636800 Item 005 3 shim D2557214637000 Item 006 1 shim D2557214653400 Item 007 1 shim D2557214653500 Item 008 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 shim D2557214653600 Item 009 1 shim D2557214653800 Item 010 1 shim D2557214653900 Item 011 1 shim D2557214654000 Item 012 6 Install the YZ-latches between FR52 and FR59 with sealant (Mat. No. 09-005) as shown in drawing D25572631006, Sheet 8, Details U8 and V8 and refer to AMM 25-52-44, Page block 401: 3 YZ-latch D2557238000000 Item A 8 YZ-latch D2557235000200 Item B

with: 30 bolt MS21250-03008 Item 003 30 bolt MS21250-03006 Item 004 60 nut NAS1726-3E Item 005 NOTE : Items A and B are retained parts. NOTE : The Items 003, 004 and 005 are contained in the Kit 281118D23R01. 7 Install this item with sealant (Mat. No. 09-005) as shown in drawing D25572631002, Sheet 5, Detail Z1-5 and refer to AMM 25-52-21, Page block 401: 1 track D25572213008 Item A

with: 22 screw NAS1102-3-10 Item 013 36 nut NAS1726-3E Item 014 22 screw NAS1102-3-9 Item 015

2 screw NAS1100-3-7 Item 016

NOTE : Dependent on the thickness of the shims it could be necessary to install alternative bolts as shown in the table, refer to drawing D25572631002, Sheet 5. Alternative bolts, Item 017, Item 018 and Item 019, are supplied with the Kit. NOTE : Item A is a retained part. 8 Install the AFT cargo compartment ball mats between FR52A and FR56, (Refer to AMM 25-52-22, Page block 401). (ak) Install the brackets for the fuel drain/vent systems between FR46 and FR54. Refer to Kit 281118D17R00 1 Install the brackets between FR46 and FR47 as shown in Details A12-12, Y12-12 and Z12-12:

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 343 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s): D28270982002 Sheet(s) 12

a Remove the existing fasteners at the affected areas. b Put these items in position: 2 angle D2827094222800 Item 102 2 bracket D2827094200400 Item 124

c Transfer drill the holes, drill the additional holes and open them to final dimension. d Install these items: 2 angle D2827094222800 Item 102 2 bracket D2827094200400 Item 124 with: 6 rivet LN9198-3212BF Item 032 8 pin DAN7-6-8Y Item 041 8 collar DAN12-6Y Item 042 2 Install the brackets at FR47 and FR48 as shown in Details A12-13, B12-13 and C12-13: Refer to Drawing(s): D28270982002 Sheet(s) 13

a Put this item in position: 3 bracket F5397461900600 Item 100

b Drill the holes for the rivets.

c Install this item: 3 bracket F5397461900600 Item 100 with: 6 rivet LN9198-4012BF Item 040 3 Install the brackets at FR49 and FR50 as shown in Details X14-14, Y14-14 and Z14-14: Refer to Drawing(s): D28270982002 Sheet(s) 14

a Put these items in position: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 bracket D2827098300000 Item 104 1 bracket D2827098300200 Item 106 1 bracket D2827098325200 Item 125

b Drill the holes for the rivets.

c Install these items: 1 bracket D2827098300000 Item 104 1 bracket D2827098300200 Item 106 1 bracket D2827098325200 Item 125 with: 6 rivet LN9198-4012BF Item 040 4 Install the brackets at FR49 as shown in Details B21-21, D21-21 and B22-22: Refer to Drawing(s): D28270982002 Sheet(s) 21 and 22

a Put these items in position: 2 bracket D2827098320800 Item 117 2 bracket D2827098321000 Item 118 1 angle D2827098321200 Item 119

b Drill the holes for the rivets.

c Install these items: 2 bracket D2827098320800 Item 117 2 bracket D2827098321000 Item 118 1 angle D2827098321200 Item 119 with: 14 rivet LN9198-4012BF Item 040 5 Install the angles at FR50, FR51, FR52 and FR53 as shown in Details W15-20, X15-20, Y15-20 and Z15-20: Refer to Drawing(s): D28270982002 Sheet(s) 20

a Put these items in position: 2 angle D2827098321400 Item 120 2 angle D2827098321600 Item 121

b Drill the holes for the rivets.

c Install these items: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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2 angle D2827098321400 Item 120 2 angle D2827098321600 Item 121 with: 8 rivet LN9198-4012BF Item 040 6 Install the angles at FR50 and FR51 as shown in Details G16-G20 and F16-F17: Refer to Drawing(s): D28270982002 Sheet(s) 17 and 20

a Put this item at FR51 in position: 2 angle D2827094220400 Item 113

b Put this item at FR50 ad FR51 in position: 2 angle D2827094222200 Item 116

c Drill the holes for the rivets. d Install these items: 2 angle D2827094220400 Item 113 2 angle D2827094222200 Item 116 with: 12 rivet LN9198-4012BF Item 040 7 Install the brackets at FR52 and FR53 as shown in Details A17-A17, C17-C17 and B18-B18: Refer to Drawing(s): D28270982002 Sheet(s) 17 and 18

a Put this item at FR52 in position: 2 angle D2827094221800 Item 115

b Put this item at FR52 and FR53 in position: 2 bracket D2827098323200 Item 127

c Drill the holes for the rivets. d Install these items: 2 angle D2827094221800 Item 115 2 bracket D2827098323200 Item 127 with: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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8 rivet LN9198-4012BF Item 040 8 Install the bracket between FR51 and FR52 as shown in Section B17-B17: Refer to Drawing(s): D28270982002 Sheet(s) 17

a Put this item in position: 1 bracket D2827098300800 Item 126

b Drill the holes for the rivets.

c Install this item: 1 bracket D2827098300800 Item 126 with: 6 rivet LN9198-4012BF Item 040 9 Install the brackets at FR53 and FR54 as shown in Details A18-A18, C18-C18, A19-A19 and D19-D19: Refer to Drawing(s): D28270982002 Sheet(s) 18 and 19

a Put this item at FR53 in position: 4 angle D2827094221400 Item 112

b Put this item at FR53 and FR54 in position: 2 bracket D2827098323000 Item 128

c Put this item at FR54 in position: 2 bracket D2827098323400 Item 129

d Drill the holes for the rivets.

e Install these items: 4 angle D2827094221400 Item 112 2 bracket D2827098323000 Item 128 1 bracket D2827098323400 Item 129 with: 14 rivet LN9198-4012BF Item 040 1 0 Install the brackets between FR53 and FR54 as shown in Section D16-D20: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Refer to Drawing(s): D28270982002 Sheet(s) 20

a Put these items at FR53 and FR54 in position: 1 bracket D2827098324200 Item 132 1 bracket D2827098324400 Item 133

b Drill the holes for the rivets.

c Install these items: 1 bracket D2827098324200 Item 132 1 bracket D2827098324400 Item 133 with: 4 rivet LN9198-4012BF Item 040

d Put these items between FR53 and FR54 in position: 1 bracket D2827098323800 Item 130 1 bracket D2827093521000 Item 131 1 bracket D2827098324000 Item 134

e Drill the holes for the rivets. f Install these items: 1 bracket D2827098323800 Item 130 1 bracket D2827093521000 Item 131 1 bracket D2827098324000 Item 134 with: 6 screw NAS1096-3-8 Item 004 6 washer NAS1149C0332R Item 005 6 nut NAS1726C3E Item 006 2 rivet LN9198-4012BF Item 040 (al) Install the ACT pressurization system between FR48 and FR54. Refer to Kit 281118B01R02 Refer to Kit 281118D16R02 Refer to Drawing(s): D28270975002 Sheet(s) 7 thru 12 1 Install these items at the crossbeam at FR54 as shown in Section D8-D8: 1 coupling A2827092300000 Item 050 1 nut AN924-10J Item 074 1 tee MS21909J10 Item 075 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 348 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 washer NAS1149F1432P Item 076 2 Install these items at the crossbeam at FR54 as shown in drawing D28270975002, Sheet 7 and Sections A7-A8 and C8-C8: 1 tube D2827097902000 Item 021 1 valve HTE490005 Item 042 1 actuator HTE200002-1 Item 043 1 valve HTE920007-001 Item 044 1 clamp HTE8002 Item 045

NOTE : The Items 042, 043, 044 and 045 are contained in Kit 281118B01R00. 3 Install these items as shown in Sections A7-A8, B8-B8 and C8-C8: 1 nut NAS1726C3E Item 070 1 screw NAS1096-3-8 Item 071 1 washer NAS1149C0332R Item 073 1 clamp NSA5575-8A Item 081 1 strap E0090-10-125NN Item 083 1 bolt NAS1303-2 Item 088 1 nut NAS1726-3E Item 089 1 washer NAS1149D0316H Item 090 4 Install these items with adhesive (Mat. No. 08-010)as shown in Section A7-A8: 1 placard D2827094420000 Item 200 1 placard D2827094420200 Item 202 1 placard D2827094420400 Item 204 1 placard D2827094421200 Item 212 5 Install these items at the crossbeam at FR53 as shown in Section B9-B9: 1 coupling A2827092300000 Item 050 1 nut AN924-10J Item 074 1 tee MS21909J10 Item 075 1 washer NAS1149F1432P Item 076 6 Install these items at the crossbeam at FR53 as shown in drawing D28270975002, Sheet 7 and Section B7-B9: 1 tube D2827097901800 Item 019 1 valve HTE490005 Item 042

NOTE : The Item 047 is contained in Kit 281118B01R00. 7 Install this item between FR53 and FR54 as shown in Section E7-E11: 1 valve PAS148-133A Item 046

with: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 349 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 nut NAS1726C3E Item 070 2 washer NAS1149C0332R Item 073 2 screw NAS1096-3-12 Item 098

NOTE : The Item 046 is contained in Kit 281118B01R00. 8 Install these items as shown in Section B7-B9: 1 clamp NSA5575-8A Item 081 1 strap E0090-10-125NN Item 083 1 bolt NAS1303-2 Item 088 1 nut NAS1726-3E Item 089 1 washer NAS1149D0316H Item 090 9 Install these items with adhesive (Mat. No. 08-010)as shown in Section B7-B9: 1 placard D2827094420600 Item 206 1 placard D2827094420800 Item 208 1 0 Install this item between FR53 and FR54 as shown in drawing D28270975002, Sheet 7 and Section E7-E11: 1 hose 1451515F0150-18 Item 040

with: 1 nut NAS1726C3E Item 070 1 screw NAS1096-3-8 Item 071 1 washer NAS1149C0332R Item 073 1 clamp MS21919WCH15 Item 101 1 1 Install these items as shown in drawing D28270975002, Sheet 7 and Sections B7-B9, E7-E11 and G7-G12: 1 tube D2827098000800 Item 005 1 tube D2827098001000 Item 007 1 tube D2827098001200 Item 009 1 tube D2827098001400 Item 011

with: 15 nut NAS1726C3E Item 070 12 screw NAS1096-3-8 Item 071 15 washer NAS1149C0332R Item 073 13 clamp MS21919WDE4 Item 080

4 clamp NSA5575-2 Item 082 4 lead E0090-18-100NN Item 084 4 screw NAS1096-1-8 Item 085 4 washer NAS1149DN616H Item 086 4 nut MS21042-06 Item 087 3 screw NAS1096-3-9 Item 097 1 2 Install these items between FR48 and FR49 as shown in Section G7-G12: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 350 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 filter A2163302000000 Item 027 1 inlet A2151034520000 Item 028 1 nut AN924-4D Item 092 1 3 Install these items as shown in drawing D28270975002, Sheet 7, Detail I9-9 and Sections C7-C10 and D7-D11: 1 tube D2827097901000 Item 016 1 tube D2827097901600 Item 017 1 tube D2827097902200 Item 023 1 tube D2827097902400 Item 025

with: 6 nut NAS1726C3E Item 070 3 screw NAS1096-3-8 Item 071 6 washer NAS1149C0332R Item 073 1 conduit TSTMNR503-0 Item 077 2 tie NSA935401-03 Item 078 6 clamp MS21919WDE10 Item 079 4 clamp NSA5575-8A Item 081 4 strap E0090-10-125NN Item 083 4 bolt NAS1303-2 Item 088 4 nut NAS1726-3E Item 089 4 washer NAS1149D0316H Item 090 3 screw NAS1096-3-9 Item 097

NOTE : Cut the conduit, Item 077, into two pieces. 1 4 Install this item between FR51 and FR52 as shown in drawing D28270975002, Sheet 7 and Section C7-C10: 1 filter QB0566 Item 041

with: 1 union MS21902D10 Item 030 1 packing NAS1612-10 Item 031 4 nut NAS1726C4E Item 093

NOTE : The Item 041 is contained in Kit 281118B01R00. 1 5 Install this item with adhesive (Mat. No. 08-010)as shown in Section C7-C10: 1 placard D2827094421000 Item 210 1 6 Install this item as shown in drawing D28270975002, Sheet 7 and Sections D7-D11 and F7-F11: 1 tube D2827097901400 Item 015

with: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 351 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 nut NAS1726C3E Item 070 2 screw NAS1096-3-8 Item 071 2 washer NAS1149C0332R Item 073 1 conduit TSTMNR503-0 Item 077 2 tie NSA935401-03 Item 078 2 clamp MS21919WDE10 Item 079 1 7 Install these items as shown in drawing D28270975002, Sheet 7 and Details X7-11, Y7-11 and Z7-11: 1 tube D2827097901200 Item 013 1 elbow MS21908J10 Item 091 1 tee MS21905J10 Item 099

with: 2 nut NAS1726C3E Item 070 1 screw NAS1096-3-8 Item 071 2 washer NAS1149C0332R Item 073 2 clamp MS21919WDE10 Item 079 2 clamp NSA5575-8A Item 081 1 strap E0090-10-125NN Item 083 2 bolt NAS1303-2 Item 088 2 nut NAS1726-3E Item 089 2 washer NAS1149D0316H Item 090 2 cap MS21914-10D Item 094 1 nut AN924-10J Item 095 1 washer NAS1149C1432R Item 096 1 screw NAS1096-3-9 Item 097 1 strap E0090-10-160NN Item 102 (am) Install the attachment structure of the partition panels 151AW, 151BW and 152BW between FR46 and FR47. Refer to Kit 281118D36R03 Refer to Drawing(s): D53975018000 Sheet(s) 4 thru 6 1 Install these items as shown in Section B3-B4 and Details X4-5 and Z4-5: 1 section D5397468800200 Item 044 1 section D5397468800300 Item 045 1 section D5397468000400 Item 046 1 section D5397468000500 Item 047

with: 32 bolt NAS6703-2 Item 025 32 washer NAS1149D0332K Item 026 2 Put these items at the existing brackets in position as shown in Section B3-B4 and Detail Y4-6: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 section D5397467400500 Item 052 1 section D5397467400400 Item 053 3 Put these items in position as shown in Section B3-B4: 1 section D5397492500090 Item 048 1 section D5397492500290 Item 050 4 Drill and countersink the holes and open them to final dimension. 5 Install these items: 1 section D5397492500000 Item 048 1 section D5397492500200 Item 050 1 section D5397467400400 Item 052 1 section D5397467400500 Item 053

with: 100 rivet NAS1097AD4-10 Item 532 6 Put these items in position as shown in Section B3-B4: 1 section D5397467800800 Item 040 1 section D5397467800900 Item 041 1 section D5397492600000 Item 042 7 Drill and countersink the holes and open them to final dimension. 8 Install these items: 1 section D5397467800800 Item 040 1 section D5397467800900 Item 041 1 section D5397492600000 Item 042

with: 44 rivet NAS1097AD4-10 Item 532 9 Install this item as shown in Detail V4-4: 3 plate D5397492700000 Item 054

with: 9 screw NAS1102E3-7 Item 400 9 washer DAN125-4 Item 402 1 0 Seal the gaps with sealant (Mat. No. 09-013) as shown in Section A4-A4 and Detail V4-4. 1 1 Put these items in position as shown in Section B6-B6: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 353 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 section D5347047400200 Item 230 1 section D5347047400300 Item 231 1 2 Drill and countersink the holes and open them to final dimension. 1 3 Install these items: 1 section D5347047400200 Item 030 1 section D5347047400300 Item 031

with: 32 rivet NAS1097AD4-10 Item 532 (an) Install the brackets for the wiring in cabin floor crossbeams between FR41 and 55. Refer to Kit 281118D71R01 Refer to Drawing(s): D92492243002 Sheet(s) 14 thru 20 1 Install these items between FR41 and FR42 at -Y254 as shown in drawing D92492243002, Sheet 20, Detail F20.

a Put these items in position, drill the holes for the rivets and install: 2 nut NSA5066-08-1 Item 230 2 plate A9249199820000 Item 406 with: 4 rivet LN9198-3208BF Item 632

b Drill two holes with 5.1 mm (0.201 in.) diameter as shown in drawing D92492243002, Sheet 20, Section G-G. 2 Install this item at FR49 as shown in drawing D92492243002, Sheet 15, Section A-A15.

a Put this item in position, drill the holes for the rivets and install: 4 bracket D9249104920000 Item 735 with: 8 rivet LN9198-3208BF Item 632

b Drill one hole with 5.1 mm (0.201 in.) diameter in the cabin floor crossbeam at FR49.

c Drill one hole with 5.2 mm (0.205 in.) diameter in the cabin floor crossbeam at FR49.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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3 Install these items at FR50 as shown in drawing D92492243002, Sheet 16, Section B-B16.

a Put these items in position, drill the holes for the rivets and install: 1 bracket D5347849120400 Item 402 1 bracket D5347849120500 Item 403 1 bracket D5347849021400 Item 404 1 bracket D5347849021500 Item 405 3 bracket D9249104920400 Item 737 with: 32 rivet LN9198-3208BF Item 632 b Drill two holes with 5.1 mm (0.201 in.) diameter in the cabin floor crossbeam at FR50.

c Drill one hole with 5.2 mm (0.205 in.) diameter in the cabin floor crossbeam at FR50. 4 Drill one hole with 5.2 mm (0.205 in.) diameter in the cabin floor crossbeam at FR51, FR52 and FR53 as shown in drawing D92492243002, Sheet 17, Section C-C17. 5 Install these items at FR54 as shown in drawing D92492243002, Sheet 18, Section D-D18.

a Put these items in position, drill the holes for the rivets and install: 2 nut NSA5066-08-1 Item 230 2 Sheet A9249187820200 Item 565 1 plate D9249103700200 Item 629 with: 6 rivet LN9198-3208BF Item 632

b Drill ten holes with 5.1 mm (0.201 in.) diameter in the cabin floor crossbeam at FR54.

c Drill one hole with 5.2 mm (0.205 in.) diameter in the cabin floor crossbeam at FR54. 6 Drill two holes with 5.1 mm (0.201 in.) diameter and one hole with 5.2 mm (0.205 in.) diameter in the cabin floor crossbeam at FR55 as shown in drawing D92492243002, Sheet 19, Section E-E19. (ao) Install the cable harnesses 4605VB, 4655VB, 4656VB, 4661VB, 4662VB, 4663VB, 4664VB, 4671VB, 4672VB, 4673VB, 4680VB, 4681VB, 4683VB, 4692VB, 4693VB, 4694VB and 4696VB. Refer to Kit 281118D74R00 Refer to Drawing(s): DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 355 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Install the modified cable harness 4605VB. D92991405001 Sheet(s) 2

a Put this item with the old routing in position: 1 harness 4605VB D9299140500100 Item 002

b Attach the cable harness with the existing attachment parts.

c Connect the plugs 1997VC-A and 4RC2-A (VHF-antenna). d Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 2 Install the modified cable harness 4655VB. D92991455005 Sheet(s) 6

a Put this item with the old routing in position: 1 harness 4655VB D9299145500500 Item 017

b Attach the cable harness with the existing attachment parts.

c Connect the bonding point 6555VN. d Connect the plugs (8XE2,8XE3,8XE4) from the constant speed motor(8XE).

e Install the receptacle 2975VC at the structure and connect the plug. f Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 3 Install the modified cable harness 4656VB. D92991456003 Sheet(s) 4

a Put this item with the old routing in position: 1 harness 4656VB D9299145600300 Item 019

b Attach the cable harness with the existing attachment parts.

c Connect the bonding point 6554VN. d Connect the plugs (8XE1,8XE2) from the constant speed motor(8XE).

e Install the receptacle 2954VC at the structure and connect the plug. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 356 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

f Install the receptacle 2952VC at the structure and connect the plug. g Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 4 Install the modified cable harness 4661VB. D92991461011 Sheet(s) 16

a Put this item with the old routing in position: 1 harness 4661VB D9299146101100 Item 021

b Attach the cable harness with the existing attachment parts.

c Connect the bonding points 6593VN, 6594VN, 6794VN, 6795VN and 6796VN. d Connect the wires of the cable harness 4661VB at the terminals 7223VT, 7224VT, 7502VT, 7505VT and 7528VT.

e Connect the plugs 1939VC-A, 1941VC-A, 1943VC-A, 1945VC-A, 1947VC-A, 2815GE-A, 3068GN-A and 72GG-B. f Install the receptacles 2985VC, 2987VC,2989VC, 2993VC, 2975VC, 7600VC, 7611VC and 7612VC at the structure and connect the plugs. g Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 5 Install the modified cable harness 4662VB. D92991462007 Sheet(s) 8

a Put this item with the old routing in position: 1 harness 4662VB D9299146200700 Item 023

b Attach the cable harness with the existing attachment parts.

c Connect the bonding points 6765VN, 6766VN and 6801VN. d Connect the wires of the cable harness 4662VB at the terminals 7512VT and 7616VT (Refer to Aircraft Wiring List (AWL) .

e Connect the plugs 1978VC-A, 1994VC-A, 1996VC-A, 7601VC-A and 72GG-A.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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f Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 6 Install the modified cable harness 4663VB. D92991463004 Sheet(s) 10

a Put this item with the old routing in position: 1 harness 4663VB D9299146300400 Item 025

b Attach the cable harness with the existing attachment parts.

c Connect the wires of the cable harness 4663VB at the terminal 7110VT, (Refer to Aircraft Wiring List (AWL) . d Connect the plugs 1969VC-A and 7602VC-A.

e Install the receptacles 2991VC, 2999VC and 7610VC at the structure and connect the plugs. f Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 7 Install the modified cable harness 4664VB. D92991464003 Sheet(s) 5

a Put this item with the old routing in position: 1 harness 4664VB D9299146400300 Item 027

b Attach the cable harness with the existing attachment parts.

c Connect the wires of the cable harness 4664VB at the terminal 7110VT (Refer to Aircraft Wiring List (AWL) . d Connect the plugs 1966VC-A and 1968VC-A.

e Install the receptacle 7605VC at the structure and connect the plug. f Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 8 Install the modified cable harness 4671VB. D92991471003 Sheet(s) 5 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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a Put this item with the old routing in position: 1 harness 4671VB D9299147100300 Item 031

b Attach the cable harness with the existing attachment parts.

c Connect the bonding points 6741VN, 6743VN, 6671VN, 6552VN, 6568VN, 6954VN, 6955VN, 6956VN and 6957VN. d Connect the plugs 2455GE-A, 2027GE-A, 2065GN-A, 37QA-A, 2151GN-A, 2454GN-A, 2454GE-C, 2074GJ-A, 2075GJ-A, 4CN-A, 25CV-A, 7611VC-A and 7612VC-A.

e Install the receptacles 2811GE and 2812GE at the structure and connect the plugs. f Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 9 Install the modified cable harness 4672VB. D92991472008 Sheet(s) 9

a Put this item with the old routing in position: 1 harness 4672VB D9299147200800 Item 033

b Attach the cable harness with the existing attachment parts.

c Connect the bonding points 6561VN, 6564VN, 6738VN, 6958VN, 6961VN and 6816VN. d Connect the plugs 11GA-A, 29GA-A, 24CV-A, 3CN-B, 1012GL-A and 3012GL-A.

e Install the receptacle 7601VC at the structure and connect the plug. f Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 1 0 Install the modified cable harness 4673VB. D92991473002 Sheet(s) 3

a Put this item with the old routing in position: 1 harness 4673VB D9299147300200 Item 035

b Attach the cable harness with the existing attachment parts. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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c Connect the bonding point 6559VN. d Connect the plugs 4CN-A, 25CV-A, 28CV-A and 7610VC-A.

e Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 1 1 Install the modified cable harness 4680VB. D92991480010 Sheet(s) 11

a Put this item with the old routing in position: 1 harness 4680VB D9299148001000 Item 039

b Attach the cable harness with the existing attachment parts.

c Connect the bonding points 6776VN, 6797VN, 6566VN, 6963VN, 6990VN, 6960VN and 6991VN. d Connect the plugs 8GA-A, 26GA-A, 62GG-A, 63GG-A, 23CV-A, 3CN-A, 23GG-A, 7532VC-A, 7600VC-A and 7531VC-A.

e Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 1 2 Install the modified cable harness 4681VB. D92991481002 Sheet(s) 3

a Put this item with the old routing in position: 1 harness 4681VB D9299148100200 Item 041

b Attach the cable harness with the existing attachment parts.

c Connect the wires of the cable harness 4681VB at the terminal 7613VT (Refer to Aircraft Wiring List (AWL) . d Connect the bonding point 6957VN.

e Connect the plug 2151GN-A. f Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 360 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 3 Install the modified cable harness 4683VB. D92991483004 Sheet(s) 5

a Put this item with the old routing in position: 1 harness 4683VB D9299148300400 Item 043

b Attach the cable harness with the existing attachment parts.

c Connect the bonding points 6763VN and 6598VN. d Connect the plugs 1848VC-A, 1850VC-A, 3151GN-A, 10CE-1A, 7614VC-A and 7615VC-A.

e Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 1 4 Install the modified cable harness 4692VB. D92991492002 Sheet(s) 3

a Put this item with the old routing in position: 1 harness 4692VB D9299149200200 Item 045

b Attach the cable harness with the existing attachment parts.

c Connect the wires of the cable harness 4692VB at the terminal 7616VT (Refer to Aircraft Wiring List (AWL) . d Connect the bonding point 6739VN.

e Connect the plug 2150GP-A. f Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 1 5 Install the modified cable harness 4693VB. D92991493002 Sheet(s) 3

a Put this item with the old routing in position: 1 harness 4693VB D9299149300200 Item 047

b Attach the cable harness with the existing attachment parts.

c Connect the bonding point 6563VN. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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d Connect the plugs 23CV-A, 3CN-A and 27CV-A.

e Install the receptacle 7602VC at the structure and connect the plug. f Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 1 6 Install the modified cable harness 4694VB. D92991494002 Sheet(s) 3

a Put this item with the old routing in position: 1 harness 4694VB D9299149400200 Item 049

b Attach the cable harness with the existing attachment parts.

c Connect the bonding point 6561VN. d Connect the plugs 27CV-B, 24CV-A, 7605VC-A and 3CN-B.

e Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 1 7 Install the modified cable harness 4696VB. D92991496003 Sheet(s) 4

a Put this item with the old routing in position: 1 harness 4696VB D9299149600300 Item 051

b Attach the cable harness with the existing attachment parts.

c Connect the plugs 1852VC-A and 7604VC-A. d Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 (ap) Attach the cable harnesses in the cabin floor crossbeam area at FR42 and between FR49 and FR55. Refer to Kit 281118D68R01 Refer to Drawing(s): D92891803002 Sheet(s) 18, 20, 22, 24, 25, 26, 27, 28, 30 and 31 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 362 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Attach the cable harnesses at FR42 and between FR49 and FR55 as shown in drawing D92891803002, Sheets 18, 20, 22, 24, 25, 26, 27, 28, 30 and 31.

a Attach with these items: 22 screw NAS1096-2-7 Item 004 23 screw NAS1096-2-9 Item 005

7 screw NAS1096-2-12 Item 007 2 screw NAS1096-2-16 Item 010 5 screw NAS1096-2-19 Item 012 2 screw NAS1096-2-22 Item 014 1 screw NAS1096-2-36 Item 020 92 screw NAS1096-3-9 Item 030 24 screw NAS1100-04-5 Item 051 12 screw NAS1102-08-8 Item 058 32 screw NAS1102-3-9 Item 099 24 washer NAS1149CN416R Item 150 50 washer NAS1149CN816R Item 152 136 washer NAS1149C0332R Item 153

28 washer NAS1149D363K Item 161

4 washer ASNA0113-40ADL Item 163 10 washer NSA935808C01 Item 171

2 washer D9249102520000 Item 190 24 nut MS21042-04 Item 200 12 nut MS21042-08 Item 202

4 nut MS21042-3 Item 203 28 nut MS21042L3 Item 210 27 nut NAS1291C3M Item 218

1 nut NSA5110-08-1 Item 225 3 nut NSA5066-08-1 Item 230 18 nut NSA5567-08-1 Item 236

6 mount E0343-01 Item 250 12 mount NSA935504-01 Item 251

8 mount NSA935504-02 Item 252 2 mount NSA935513-01 Item 256 10 mount NSA935513-05 Item 257

1 mount NSA935513-07 Item 259 8 bracket ABS0355-01 Item 262 11 bracket ABS0355-02 Item 263 12 washer NSA935514-03 Item 264

2 mount E0660-01 Item 266 20 support ABS0731A01 Item 267

1 spacer NSA5527-03-02 Item 302 2 spacer NSA5527-03-03 Item 304 4 spacer NSA5527-03-04 Item 306 1 spacer NSA5527-03-06 Item 310 5 spacer NSA5527-03-08 Item 314 1 spacer NSA5527-03-11 Item 320 1 clamp MS21919WCH6 Item 352 6 clamp NSA935807-09 Item 377 4 clamp NSA935807-16 Item 381 8 circle D9249101020000 Item 668 8 circle D9249101020200 Item 669 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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2 sheet D9249104800000 Item 727 1 sheet D9249104800400 Item 729 3 cover D2557016200000 Item 734 2.72 ME conduit TSTMNR502-0 Item 763 4 fitting NSA934710T13 Item 773 16 fitting NSA934710T14 Item 774 45 bobbin NSA935510-02 Item 777 15 spring NSA934710E20 Item 783

1 spring NSA934710E23 Item 784 1 ME spring NSA934710E24 Item 786 200 tie NSA935401-03 Item 793 400 tie NSA935401-04 Item 794 200 tie NSA935401-05 Item 795 2 strap D9249107300400 Item 812 1 strap D9249107100600 Item 834 2 ME tape DAN328H25 Item 877 2 cap EN2997KE3C12 Item 930 1 cap EN2997KE3C16 Item 932 2 connector EN2997KE512 Item 933 1 connector EN2997KE516 Item 935 2 bracket D9249104900600 Item 1110 NOTE : Cut the conduit, Item 763, in sixteen pieces. b Install the placards as shown in drawing D92891803002 ’POST’, supplied in: 1 placards D9289180320200 1 placards D9289180320000 NOTE : The placard sets are contained in Kit 281118D69R01. (aq) Modify the wiring of the cable harnesses 4606VB, 4607VB, 4628VB, 4640VB, 4644VB, 4648VB, 4650VB, 4670VB, 4675VB, 5609VB, 5662VB, 5663VB, 5664VB, 5670VB and 5675VB. Refer to Kit 281118D74R00 Refer to Drawing(s): D92997026001 Sheet(s) 2 D92997026002 Sheet(s) 4, 6 and 8 D92997026004 Sheet(s) 10, 12, 14, 16 and 18 D92997026005 Sheet(s) 20 D92997026006 Sheet(s) 22 D92997026007 Sheet(s) 24 D92997026008 Sheet(s) 26 D92997026015 Sheet(s) 28 and 30 D92997026019 Sheet(s) 32 D92997026027 Sheet(s) 34 D92997026028 Sheet(s) 36 D92997026029 Sheet(s) 38 D92997026030 Sheet(s) 40 D92997026031 Sheet(s) 42 D92997026032 Sheet(s) 44 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 364 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Modify the wiring of the cable harness 4606VB. Refer to drawing D92997026001, Sheet 2 Refer to Figure 3 (Hookup Chart)

a Remove the end stops of the terminal block 7522VT. NOTE : Retain the end stops. b Add the module 2 to the terminal block 7522VT, supplied in: elect. equipment D9299702600100 Item 004

c Install the end stops of the terminal block 7522VT and secure the screws with lockwire (Mat. No. 19-010). d Modify the connection of the wires as shown on the lines 1 thru 8 (Refer to drawing D92997026001 and refer to Figure 3).

e Install the wire as shown on the line 9 (Refer to drawing D92997026001 and refer to Figure 3), supplied in: elect. equipment D9299702600100 Item 004 f Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 2 Modify the wiring of the cable harness 4607VB. Refer to drawing , Sheets 4, 6 and 8 Refer to Figure 4 (Hookup Chart) Refer to Figure 5 (Hookup Chart) Refer to Figure 6 (Hookup Chart)

a Remove the wires as shown on the lines 1, 3, 4, 7, 10, 12, 14, 16, 18, 20, 22 and 24 (Refer to drawing D92997026002, Sheet 4 and refer to Figure 4). b Remove the end stops of the terminal block 7517VT. NOTE : Retain the end stops.

c Remove the module 1 from the terminal block 7517VT. d Add the modules 2, 3 and 4 to the terminal block 7517VT, supplied in: elect. equipment D9299702600200 Item 006

e Install the end stops of the terminal block 7517VT and secure the screws with lockwire (Mat. No. 19-010). f Install the wires as shown on the lines 2, 5, 6, 8, 9, 11, 13, 15, 17, 19, 21, 23 and 25 (Refer to drawing D92997026002, Sheet 4 and refer to Figure 4), supplied in: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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elect. equipment D9299702600200 Item 006 g Remove the wires as shown on the lines 1, 3, 5, 7, 9, 10, 13, 14, 17, 18, 21 and 22 (Refer to drawing D92997026002, Sheet 6 and refer to Figure 5). h Install the wires as shown on the lines 2, 4, 6, 8, 11, 12, 15, 16, 19, 20, 23 and 24 (Refer to drawing D92997026002, Sheet 6 and refer to Figure 5), supplied in: elect. equipment D9299702600200 Item 006 i Remove the wires as shown on the lines 1, 2, 3, 7, 9, 10, 11, 15, 17, 18, 19 and 23 (Refer to drawing D92997026002, Sheet 8 and refer to Figure 6). j Install the wires as shown on the lines 4, 5, 6, 8, 12, 13, 14, 16, 20, 21, 22 and 24 (Refer to drawing D92997026002, Sheet 8 and refer to Figure 6), supplied in: elect. equipment D9299702600200 Item 006 k Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 3 Modify the wiring of the cable harness 4628VB. Refer to drawing D92997026004, Sheets 10, 12, 14, 16 and 18 Refer to Figure 7 (Hookup Chart) Refer to Figure 8 (Hookup Chart) Refer to Figure 9 (Hookup Chart) Refer to Figure 10 (Hookup Chart) Refer to Figure 11 (Hookup Chart)

a Remove the wires as shown on the lines 1 thru 25 (Refer to drawing D92997026004, Sheet 10 and refer to Figure 7). b Install the wires as shown on the lines 1 thru 25 (Refer to drawing D92997026004, Sheet 12 and refer to Figure 8), supplied in: elect. equipment D9299702600400 Item 008

c Remove the wires as shown on the lines 1 thru 17 (Refer to drawing D92997026004, Sheet 14 and refer to Figure 9). d Install the wires as shown on the lines 1 thru 17 (Refer to drawing D92997026004, Sheet 16 and refer to Figure 10), supplied in: elect. equipment D9299702600400 Item 008

e Remove the wires as shown on the lines 1, 2, 3, 7, 8, 9, 13, 14, 15, 19, 20 and 21 (Refer to drawing D92997026004, Sheet 18 and refer to Figure 11).

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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f Install the wires as shown on the lines 4, 5, 6, 10, 11, 12, 16, 17, 18, 22, 23 and 24 (Refer to drawing D92997026004, Sheet 18 and refer to Figure 11), supplied in: elect. equipment D9299702600400 Item 008 g Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 4 Modify the wiring of the cable harness 4640VB. Refer to drawing D92997026005, Sheet 20 Refer to Figure 12 (Hookup Chart)

a Remove the wires as shown on the lines 1 and 3 (Refer to drawing D92997026005, Sheet 20 and refer to Figure 12). b Install the wires as shown on the lines 2 and 4 (Refer to drawing D92997026005, Sheet 20 and refer to Figure 12), supplied in: elect. equipment D9299702600500 Item 010

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 5 Modify the wiring of the cable harness 4644VB. Refer to drawing D92997026006, Sheet 22 Refer to Figure 13 (Hookup Chart)

a Remove the wires as shown on the lines 1, 3, 5, 7, 9, 11, 13 and 15 (Refer to drawing D92997026006, Sheet 22 and refer to Figure 13). b Install the wires as shown on the lines 2, 4, 6, 8, 10, 12, 14 and 16 (Refer to drawing D92997026006, Sheet 22 and refer to Figure 13), supplied in: elect. equipment D9299702600600 Item 063

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 6 Modify the wiring of the cable harness 4648VB. Refer to drawing D92997026007, Sheet 24 Refer to Figure 14 (Hookup Chart)

a Remove the wires as shown on the lines 1, 3, 5 and 7 (Refer to drawing D92997026007, Sheet 24 and refer to Figure 14).

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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b Install the wires as shown on the lines 2, 4, 6 and 8 (Refer to drawing D92997026007, Sheet 24 and refer to Figure 14), supplied in: elect. equipment D9299702600700 Item 013

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 7 Modify the wiring of the cable harness 4650VB. Refer to drawing D92997026008, Sheet 26 Refer to Figure 15 (Hookup Chart)

a Remove the wires as shown on the lines 1 thru 8 (Refer to drawing D92997026008, Sheet 26 and refer to Figure 15). b Install the wires as shown on the lines 9 thru 16 (Refer to drawing D92997026008, Sheet 26 and refer to Figure 15), supplied in: elect. equipment D9299702600800 Item 015

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 8 Modify the wiring of the cable harness 4670VB. Refer to drawing D92997026015, Sheets 28 and 30 Refer to Figure 16 (Hookup Chart) Refer to Figure 17 (Hookup Chart)

a Remove the wires as shown on the lines 1 thru 14 (Refer to drawing D92997026015, Sheet 28 and refer to Figure 16). b Install the wires as shown on the lines 1 thru 14 (Refer to drawing D92997026015, Sheet 30 and refer to Figure 17), supplied in: elect. equipment D9299702601500 Item 029

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 9 Modify the wiring of the cable harness 4675VB. Refer to drawing D92997026019, Sheet 32 Refer to Figure 18 (Hookup Chart)

a Remove the wires as shown on the lines 1 and 3 (Refer to drawing D92997026019, Sheet 32 and refer to Figure 18).

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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b Install the wires as shown on the lines 2, 4 and 5 (Refer to drawing D92997026019, Sheet 32 and refer to Figure 18), supplied in: elect. equipment D9299702601900 Item 037

c Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 1 0 Modify the wiring of the cable harness 5609VB. Refer to drawing D92997026027, Sheet 34 Refer to Figure 19 (Hookup Chart)

a Install the wires as shown on the lines 1 thru 19 (Refer to drawing D92997026027, Sheet 34 and refer to Figure 19), supplied in: elect. equipment D9299702602700 Item 052 b Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 1 1 Modify the wiring of the cable harness 5662VB. Refer to drawing D92997026028, Sheet 36 Refer to Figure 20 (Hookup Chart)

a Install the wires as shown on the lines 1 thru 4 (Refer to drawing D92997026028, Sheet 36 and refer to Figure 20), supplied in: elect. equipment D9299702602800 Item 053 b Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 1 2 Modify the wiring of the cable harness 5663VB. Refer to drawing D92997026029, Sheet 38 Refer to Figure 21 (Hookup Chart)

a Install the wires as shown on the lines 1 thru 12 (Refer to drawing D92997026029, Sheet 38 and refer to Figure 21), supplied in: elect. equipment D9299702602900 Item 054 b Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 1 3 Modify the wiring of the cable harness 5664VB. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Refer to drawing D92997026030, Sheet 40 Refer to Figure 22 (Hookup Chart)

a Install the wires as shown on the lines 1 thru 11 (Refer to drawing D92997026030, Sheet 40 and refer to Figure 22), supplied in: elect. equipment D9299702603000 Item 055 b Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 1 4 Modify the wiring of the cable harness 5670VB. Refer to drawing D92997026031, Sheet 42 Refer to Figure 23 (Hookup Chart)

a Install the wires as shown on the lines 1 thru 9 (Refer to drawing D92997026031, Sheet 42 and refer to Figure 23), supplied in: elect. equipment D9299702603100 Item 056 b Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 1 5 Modify the wiring of the cable harness 5675VB. Refer to drawing D92997026032, Sheet 44 Refer to Figure 24 (Hookup Chart)

a Install the wires as shown on the lines 1 thru 7 (Refer to drawing D92997026032, Sheet 44 and refer to Figure 24), supplied in: elect. equipment D9299702603200 Item 057 b Install this item as shown in drawing D92894713022, Sheet 2 at the cable harness: placard D9289471302200 Item 062 (ar) Install the AFT cargo compartment floor panels between FR47 and FR52A and between FR56 and FR59. Refer to Kit 281118D33R02 Refer to AMM 53-42-14, Page block 401 Refer to Drawing(s): D53672848000 Sheet(s) 2 and 3 1 Install the AFT cargo compartment floor panels between FR47 and FR52A.

a Install these items at the cargo compartment crossbeams as shown in Detail A2-2: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 plate D5397484220000 Item 110 1 plate D5397484220100 Item 111 2 spacer D5397489520000 Item 118 2 spacer D5397489520100 Item 119 with: 20 screw NAS1102-3-8 Item 408 b Install this item as shown in Detail A2-2: 1,6 ME tape ABS5006-4D Item 441

c Install these items as shown in Detail A2-2: 1 panel D5367326000000 Item 028 1 panel D5367326100200 Item 030 1 panel D5367326200200 Item 032 1 panel D5367326300000 Item 034 1 panel D5367327000000 Item 080 1 panel D5367327100000 Item 082 with: 4 screw ABS0376-3-30 Item 402 91 screw ABS0376-3-40 Item 404 60 nut ABS0365-3-1B Item 410 2 Install the AFT cargo compartment floor panels between FR55 and FR59.

a Install these items as shown in Detail A2-2: 1 panel D5367321800000 Item 072 1 panel D5367321900000 Item 074 1 panel D5367322100000 Item 076 1 panel D5367322000000 Item 078 with: 41 screw ABS0376-3-30 Item 402 16 screw ABS0376-3-40 Item 404 16 nut ABS0365-3-1B Item 410 (as) Install the AFT cargo compartment floor panels between FR47 and FR59. Refer to Kit 281118D35R01 Refer to AMM 53-42-14, Page block 401 Refer to Drawing(s): D53672850000 Sheet(s) 2 and 3 1 Install these items between FR47 and FR59 LH as shown in Detail B2-2: 1 panel D5367301800000 Item 000 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 panel D5367302000000 Item 002 1 panel D5367302400000 Item 004 1 panel D5367302600000 Item 006 1 panel D5367303400000 Item 008 1 panel D5367306200000 Item 028 1 panel D5367305500000 Item 030 1 panel D5367305300000 Item 032 1 panel D5367305400000 Item 034 1 panel D5367316000000 Item 042

with: 185 screw ABS0376-3-25 Item 400

37 screw ABS0376-3-30 Item 402 185 nut ABS0365-3-1B Item 410 3 washer NAS1169C10L Item 414 2 Install these items between FR47 and FR52A RH and between FR56 and FR59 RH as shown in Detail A2-2: 1 panel D5367301800100 Item 001 1 panel D5367303400100 Item 009 1 panel D5367302200000 Item 010 1 panel D5367302700000 Item 012 1 panel D5367306200100 Item 029 1 panel D5367305200000 Item 038 1 panel D5367305600000 Item 040 1 panel D5367316000100 Item 043

with: 135 screw ABS0376-3-25 Item 400

27 screw ABS0376-3-30 Item 402 135 nut ABS0365-3-1B Item 410 3 washer NAS1169C10L Item 414 (at) Install the seal sections in the gaps between the cargo compartment floor panels between FR47 and FR59. Refer to Kit 281118D34R00 Refer to Drawing(s): D53672849000 Sheet(s) 1 thru 3 D53675511002 Sheet(s) 4 thru 6 1 Install these items as shown in drawing D53672849000, Sheet 1 thru 3: section ABS0305LC Item 001 section ABS0305LB Item 002 section ABS0398A02 Item 003 section ABS0399A Item 004 2 Install this item in the gaps as in drawing D53672849000, Sheet 1 thru 3: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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cord DAN107-1 Item 005 and seal all gaps with sealant (Mat. No. 09-016) as in drawing D53672849000, Sheet 1 thru 3. (au) Install the passenger compartment floor panels 241JF, 251BF and 252BF. Refer to Kit 281118D31R00 Refer to AMM 53-22-12, Page block 401 Refer to AMM 53-42-12, Page block 401 Refer to Drawing(s): D53675013000 Sheet(s) 2 and 3 1 Install these items: 1 panel D5367161702200 Item 018 2 panel D5367160001200 Item 028

with: 56 screw ABS0376-3-25 Item 400 56 nut ABS0365-3-1B Item 405 (av) Seal the gaps at the installed passenger compartment floor panels 241JF, 251BF and 252BF. Refer to Kit 281118D32R00 Refer to AMM 53-22-12, Page block 401 Refer to AMM 53-42-12, Page block 401 Refer to Drawing(s): D53675014000 Sheet(s) 1 and 2 1 Install this item: cord DAN107-1 Item 385 and seal all gaps with sealant (Mat. No. 09-016). 2 Install after sealing this item: tape ABS5093AT25 Item 387 (aw) Modify the carpet to get access to the access panels in the passenger compartment floor panels 241JF, 251BF and 252BF. Refer to Kit 281118D31R00 and Kit 281118D32R00 Refer to AMM 53-22-12, Page block 401 Refer to AMM 53-42-12, Page block 401 (ax) Install the AFT cargo compartment panels 151AW, 151BW and 152BW at FR47. Refer to Kit 281118D81R00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Refer to AMM 25-55-11, Page block 401 Refer to Drawing(s): D25570048002 Sheet(s) 2 1 Install these items: 1 panel D2557166000400 Item 003 1 panel D2557166000500 Item 004 1 panel D2557166200200 Item 005 2 cover D2557017000200 Item 010 (ay) Replace the placards at the side wall panels in the AFT cargo compartment. Refer to Kit 281118D26R00 Refer to Drawing(s): D25572631012 Sheet(s) 1, 16 and 17 1 Remove and discard these items as shown in drawing D25572631012, Sheet 16, Views C and G: 1 placard D2557295224400 Item (000) discard 1 placard D2557295122000 Item (025) discard 1 placard D2557295122600 Item (030) discard 2 Install these items as shown in drawing D25572631012, Sheet 17, Views C and G:

a Clean the affected areas with cleaning agent (Mat. No. 11-026). b Install these items: 1 placard D2557295526200 Item 150 1 placard A2557144422000 Item 151 1 placard D2557295122400 Item 152 (7) Config. 02 Top Drawing D00071137002 (a) Remove the corner profiles at STGR38 LH/RH between FR48 and FR56. Refer to Drawing(s): D53470075002 Sheet(s) 10 1 Remove and discard these items as shown in Details Z9-10 and X9-10: 1 corner profile D5347048100400 Item (452) discard 1 corner profile D5347047500400 Item (454) discard 1 corner profile D5347047600600 Item (456) discard (b) Remove the shear plates at STGR38 LH/RH between FR48 and FR59. Refer to Drawing(s): D53470075002 Sheet(s) 8 and 11 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 Remove and discard these items at STGR38 LH as shown in Sections H1-H8 and K1-K11: 1 shear plate D5347048700000 Item (370) Discard 1 shear plate D5347048500200 Item (372) Discard 1 shear plate D5347048800000 Item (374) discard 1 shear plate D5347048900000 Item (376) discard 1 shear plate D5347049200200 Item (378) discard 1 angle D5347046820900 Item (382) Discard 2 angle D5347046820600 Item (386) discard 1 angle D5347046820400 Item (388) Discard 1 connection D5347063720600 Item (396) Discard 1 angle D5347046820200 Item (390) discard 1 angle D5347046820800 Item (392) discard 1 angle D5347046821000 Item (394) discard 1 connection D5347063720600 Item (396) Discard 1 connection D5347065020200 Item (398) discard 3 angle D5347046820000 Item (460) discard 2 angle D5347046820200 Item (462) discard 1 angle D5347046820400 Item (464) discard 2 shear plate D5347049000000 Item (474) discard 1 shear plate D5347049100000 Item (476) discard 2 Remove and discard these items at STGR38 RH as shown in Sections G1-G8 and J1-J11: 1 angle D5347046820900 Item (382) discard 1 angle D5347046822000 Item (384) discard 2 angle D5347046820100 Item (468) discard 3 angle D5347046820300 Item (470) discard 1 angle D5347046822400 Item (472) discard 1 shear plate D5347049000100 Item (478) discard 1 shear plate D5347049000300 Item (480) discard 1 shear plate D5347048600400 Item (482) discard (c) Remove the crossbeams at FR48, FR49, FR50 and FR51 in the AFT cargo compartment. D53470075002 Sheet(s) 2, 3 and 4 1 Remove these items at FR48 as shown in drawing D53470075002, Sheet 2, Section A1-A2 ’BEFORE’.

a Remove and discard these items: 1 crossbeam D5347035000400 Item (400) discard 1 shim D5347061120200 Item (402) discard 1 fitting D5347061220000 Item (404) discard 1 shim D5347061120300 Item (406) discard 1 fitting D5347061220100 Item (408) discard 1 support D5347069920800 Item (412) discard

b Close the eight holes as shown in Details B2-2 and C2-2: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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8 rivet MBBN4477-4814 Item 548

c Close the two holes at FR48 at STGR43 LH/RH as shown in Section A1-A2: 2 rivet MBBN4477-4014 Item 540 2 Remove these items at FR49, Section B1-B3 ’BEFORE’. Refer to Drawing(s): D53470075002 Sheet(s) 3

a Remove and discard these items: 1 crossbeam D5347035000400 Item (400) discard 1 shim D5347061120200 Item (402) discard 1 fitting D5347061220000 Item (404) discard 1 shim D5347061120300 Item (406) discard 1 fitting D5347061220100 Item (408) discard 1 support D5347069920800 Item (412) discard

b Close the eight holes as shown in Details B3-3 and C3-3: 8 rivet MBBN4477-4814 Item 548

c Close the two holes at FR49 at STGR43 LH/RH as shown in Section B3-B3 ’AFTER’: 2 rivet MBBN4477-4014 Item 540 3 Remove these items at FR50, Section C1-C4 ’BEFORE’. Refer to Drawing(s): D53470075002 Sheet(s) 4

a Remove and discard these items: 1 crossbeam D5347026000400 Item (410) discard 1 shim D5347061120200 Item (402) discard 1 fitting D5347061220000 Item (404) discard 1 shim D5347061120300 Item (406) discard 1 fitting D5347061220100 Item (408) discard 1 clip D5347073720400 Item (430) discard 1 clip D5347073920200 Item (432) discard 1 clip D5347074020000 Item (434) discard 1 clip D5347073720500 Item (436) discard

b Close the eight holes as shown in Details B4-4 and C4-4: 8 rivet MBBN4477-4814 Item 548

c Close the four holes at FR50 at STGR43 LH/RH as shown in Section C4-4 ’AFTER’: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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4 rivet MBBN4477-4014 Item 540 4 Remove these items at FR51, Section D1-D5 ’BEFORE’. Refer to Drawing(s): D53470075002 Sheet(s) 5

a Remove and discard these items: 1 crossbeam D5347035300400 Item (420) discard 1 shim D5347061120200 Item (402) discard 1 fitting D5347061220000 Item (404) discard 1 shim D5347061120300 Item (406) discard 1 fitting D5347061220100 Item (408) discard 1 clip D5347074420400 Item (440) discard 1 clip D5347074620200 Item (442) discard 1 clip D5347074720000 Item (444) discard 1 clip D5347074420500 Item (446) discard 1 connection D5347557525400 Item (448) discard

b Close the eight holes as shown in Details B5-5 and C5-5: 8 rivet MBBN4477-4014 Item 540

c Close the four holes at FR51 at STGR43 LH/RH as shown in Section B5-5 ’AFTER’: 2 rivet MBBN4477-4014 Item 540 (d) Modify the structure at FR48 between STGR34 LH and STGR34 RH. Refer to Kit 281118D85R02 Refer to Drawing(s): D53470075002 Sheet(s) 2 1 Replace the fasteners at FR48 between STGR34 RH and STGR36 RH as shown in Section A1-A2 ’AFTER’:

a Remove the existing fasteners in the affected area as shown in Section A1-A2 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. b Open the affected holes to final dimension.

c Install these items: 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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NOTE : The remaining fasteners, Items 865 and 806, will be installed during the installation of the reinforcing straps at FR48. 2 Install the reinforcing straps at FR48 between STGR35 LH/RH and STGR42 LH/RH as shown in Section A1-A2 ’AFTER’:

a Put these items at FR48 in position: 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

b Transfer drill the holes form the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes to final dimension. d Install these items: 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with: 58 rivet LN9198-4014CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit 281118D08R00. 3 Install the fittings at FR48 at STGR37 LH/RH as shown in Section A15-A2 ’AFTER’:

a Put these items at FR48 in position: 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

b Transfer drill the holes form the frame to the fittings and open all holes to final dimension.

c Install these items: 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with: 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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4 Install the crossbeam at FR48 as shown in Section A15-A2 ’AFTER’:

a Put these items at FR48 temporarily in position: 1 crossbeam D5347035000600 Item 010 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 010, IS IN LINE WITH THE CROSSBEAMS AT FR47 AND FR52. b Mark the fastener holes as shown in View Z3-3 and Y3-3.

c Drill the marked holes with 3.3 mm (0.130 in.) diameter. d Transfer drill all other holes from the frame to the crossbeam.

e Drill all additional holes and open all holes to final dimension. f Remove the crossbeam. g Mark and drill the holes into FR48 as shown in Detail C3-3. h Put the crossbeam in position and install these items: 1 crossbeam D5347035000600 Item 010 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026 with: 32 rivet LN9198-4814CF Item 648

6 pin DAN5-6-5X Item 765 60 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 6 collar NSA5075-8 Item 808 16 pin DAN5-6-4 Item 964 34 pin DAN5-6-5 Item 965 10 pin DAN5-6-6 Item 966

2 pin DAN5-6-7 Item 967 6 pin DAN5-8-5 Item 985

i Put this item at FR48 in position as shown in Detail C3-3: 2 bushing D5347658620000 Item 204

j Transfer drill the holes from the frame to the bushings and open the holes to final dimension. k Install these items as shown in Detail C3-3: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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2 bushing D5347658620000 Item 204 with: 2 collar NSA5075-6 Item 806 2 pin DAN5-6-7 Item 967 5 Replace the fasteners at FR48 between STGR42 LH and STGR42 RH:

a Remove the fasteners as shown in Section A1-A2 ’BEFORE’. b Open the holes to final dimension.

c Install these items as shown in Section A1-A2 ’AFTER’: 17 rivet LN9198-4814CF Item 648 6 Install the sections and the angles at FR48 between STGR34 LH/RH and STGR39 LH/RH as shown in Section A1-A2 ’AFTER’:

a Put these items in position: 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 3 section D5347449520500 Item 032 3 section D5347449520400 Item 034 1 angle D5347470020000 Item 036 1 angle D5347470020100 Item 038

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items: 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 3 section D5347449520500 Item 032 3 section D5347449520400 Item 034 1 angle D5347470020000 Item 036 1 angle D5347470020100 Item 038 with: 32 rivet MBBN4477-4814 Item 548 40 rivet LN9198-4814CF Item 648

8 collar NSA5075-6 Item 806 8 pin DAN6-6-4 Item 864 (e) Modify the structure at FR49 between STGR34 LH and STGR34 RH. Refer to Kit 281118D85R02

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 380 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s): D53470075002 Sheet(s) 3 1 Replace the fasteners at FR49 between STGR34 RH and STGR36 RH as shown in Section B1-B3 ’AFTER’:

a Remove the existing fasteners in the affected area as shown in Section B1-B3 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. b Open the affected holes to final dimension.

c Install these items: 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Items 865 and 806, will be installed during the installation of the reinforcing straps at FR49. 2 Install the reinforcing straps at FR49 between STGR35 LH/RH and STGR42 LH/RH as shown in Section B1-B3 ’AFTER’:

a Put these items at FR49 in position: 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

b Transfer drill the holes form the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes to final dimension. d Install these items: 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with: 58 rivet LN9198-4014CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit 281118D08R00.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 381 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

3 Install the fittings at FR49 at STGR37 LH/RH as shown in Section B1-B3 ’AFTER’:

a Put these items at FR49 in position: 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

b Transfer drill the holes form the frame to the fittings and open all holes to final dimension.

c Install these items: 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with: 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR49 as shown in Section B1-B3 ’AFTER’:

a Put these items at FR49 temporarily in position: 1 crossbeam D5347035000600 Item 010 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 010, IS IN LINE WITH THE CROSSBEAMS AT FR47 AND FR52. b Mark the fastener holes as shown in View Y3-3 and Z3-3.

c Drill the marked holes with 3.3 mm (0.130 in.) diameter. d Transfer drill all other holes from the frame to the crossbeam.

e Drill all additional holes and open all holes to final dimension. f Remove the crossbeam. g Mark and drill the holes into FR49 as shown in Detail C3-3. h Put the crossbeam in position and install these items: 1 crossbeam D5347035000600 Item 010 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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2 filler D5337217620800 Item 026 with: 32 rivet LN9198-4814CF Item 648

6 pin DAN5-6-5X Item 765 60 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 6 collar NSA5075-8 Item 808 16 pin DAN5-6-4 Item 964 36 pin DAN5-6-5 Item 965

8 pin DAN5-6-6 Item 966 2 pin DAN5-6-7 Item 967 6 pin DAN5-8-5 Item 985

i Put this items at FR49 in position as shown in Detail C3-3: 2 bushing D5347658620000 Item 204

j Transfer drill the holes from the frame to the bushings and open the holes to final dimension. k Install these items as shown in Detail C3-3: 2 bushing D5347658620000 Item 204 with: 2 collar NSA5075-6 Item 806 2 pin DAN5-6-7 Item 967 5 Install the sections and the angles at FR49 between STGR34 LH/RH and STGR39 LH/RH as shown in Section B1-B3 ’AFTER’:

a Put these items in position: 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 1 section D5347449520500 Item 032 1 section D5347449520400 Item 034 1 angle D5347470020400 Item 044 1 angle D5347470020500 Item 046 2 angle D5347470020200 Item 048 2 angle D5347470020300 Item 050

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items: 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 section D5347449520500 Item 032 1 section D5347449520400 Item 034 1 angle D5347470020400 Item 044 1 angle D5347470020500 Item 046 2 angle D5347470020200 Item 048 2 angle D5347470020300 Item 050 with: 46 rivet MBBN4477-4814 Item 548 40 rivet LN9198-4814CF Item 648 6 Replace the riveting between clip and skin panel at FR49 between STGR34 LH/RH and STGR37 LH/RH as shown in Section B1-B3:

a Remove the existing rivets. b Open the holes and the countersinks to final dimension.

c Install this item: 23 rivet MBBN4477-4814 Item 548 (f) Modify the structure at FR50 between STGR34 LH and STGR34 RH. Refer to Kit 281118D85R02 Refer to Drawing(s): D53470075002 Sheet(s) 4 1 Replace the fasteners at FR50 between STGR34 RH and STGR36 RH as shown in Section C1-C4 ’AFTER’:

a Remove the existing fasteners in the affected area as shown in Section C1-C4 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. b Open the affected holes to final dimension.

c Install these items: 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Items 865 and 806, will be installed during the installation of the reinforcing straps at FR50. 2 Install the reinforcing straps at FR50 between STGR35 LH/RH and STGR42 LH/RH as shown in Section C1-C4 ’AFTER’: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 384 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Put these items at FR50 in position: 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

b Transfer drill the holes form the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes to final dimension. d Install these items: 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with: 58 rivet LN9198-4014CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit D08. 3 Install the fittings at FR50 at STGR37 LH/RH as shown in Section C1-C4 ’AFTER’:

a Put these items at FR50 in position: 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

b Transfer drill the holes form the frame to the fittings and open all holes to final dimension.

c Install these items: 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with: 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR50 as shown in Section C1-C4 ’AFTER’:

a Put these items at FR50 in position: 1 plate D5337217620000 Item 012 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026 1 crossbeam D5347026000600 Item 052

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 052, IS IN LINE WITH THE CROSSBEAMS AT FR47 AND FR52. b Transfer drill all holes from the frame to the crossbeam.

c Put these items at FR50 between STGR42 LH and STGR42 RH in position: 1 support D5347470520000 Item 054 1 support D5347470520100 Item 056 1 web D5347470320000 Item 066

d Transfer drill the holes from the frame and skin panel to the shear web and the supports.

e Drill all additional holes and open all holes and all countersinks to final dimension. f Install these items: 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026 1 crossbeam D5347026000600 Item 052 1 angle D5347470520000 Item 054 1 angle D5347470520100 Item 056 1 web D5347470320000 Item 066 with: 12 rivet MBBN4477-4814 Item 548

4 rivet LN9198-4014CF Item 640 51 rivet LN9198-4814CF Item 648

6 pin DAN5-6-5X Item 765 56 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 12 collar NSA5075-8 Item 808 20 pin DAN5-6-4 Item 964 32 pin DAN5-6-5 Item 965

4 pin DAN5-6-6 Item 966 6 pin DAN5-8-5 Item 985 4 pin DAN5-8-6 Item 986 2 pin DAN5-8-7 Item 987 5 Install the sections and the angles at FR50 between STGR34 LH and STGR34 RH as shown in Section C1-C4 ’AFTER’:

a Put these items in position: 1 section D5347449520300 Item 028 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 386 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 section D5347449520200 Item 030 2 section D5347449520500 Item 032 2 section D5347449520400 Item 034 1 angle D5347470020400 Item 044 1 angle D5347470020500 Item 046 2 angle D5347470020200 Item 048 2 angle D5347470020300 Item 050 1 profile D5347449523400 Item 058 1 profile D5347449523600 Item 060 2 profile D5347449523200 Item 064 1 angle D5347470020800 Item 068 1 angle D5347470021000 Item 070 1 angle D5347470020600 Item 072 1 angle D5347470021200 Item 074

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel and the two holes in the angles, Item 064, and install with these items: 82 rivet MBBN4477-4814 Item 548 69 rivet LN9198-4814CF Item 648

4 collar NSA5075-6 Item 806 4 pin DAN5-6-4 Item 964 6 Replace the riveting between clip and skin panel at FR50 between STGR34 LH/RH and STGR37 LH/RH as shown in Section C1-C4 ’AFTER’:

a Remove the existing rivets. b Open the holes and the countersinks to final dimension.

c Install this item: 23 rivet MBBN4477-4800 Item 548 (g) Modify the structure at FR51 between STGR34 LH and STGR34 RH. Refer to Kit 281118D85R02 Refer to Drawing(s): D53470075002 Sheet(s) 5 1 Replace the fasteners at FR51 between STGR34 RH and STGR36 RH as shown in Section D1-D5 ’AFTER’:

a Remove the existing fasteners in the affected area as shown in Section D1-D5 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. b Open the affected holes to final dimension. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 387 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

c Install these items: 34 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 16 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 6 pin DAN5-6-5 Item 965 NOTE : The remaining fasteners, Items 865 and 806, will be installed during the installation of the reinforcing straps at FR51. 2 Install the reinforcing straps at FR51 between STGR35 LH/RH and STGR42 LH/RH as shown in Section D1-D5 ’AFTER’:

a Put these at FR51 in position: 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes and all countersinks to final dimension. d Install these items: 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with: 58 rivet LN9198-4014CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit D08. 3 Install the fittings at FR51 at STGR37 LH/RH as shown in Section D1-D5 ’AFTER’:

a Put these items at FR51 in position: 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

b Transfer drill the holes from the frame to the fittings and open all holes to final dimension.

c Install these items: 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 388 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

with: 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR51 as shown in Section D1-D5 ’AFTER’:

a Put these items at FR51 in position: 1 plate D5337217620000 Item 012 2 filler D5337217620800 Item 026 1 crossbeam D5347035300600 Item 076 1 sheet D5337217620700 Item 078

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 076, IS IN LINE WITH THE CROSSBEAMS AT FR47 AND FR52. b Transfer drill all holes from the frame to the crossbeam.

c Put this item at FR51 in position as shown in Section B5-B5: 1 support angle D5347658420000 Item 102

d Put these items at FR51 between STGR42 LH and STGR42 RH in position: 1 support D5347470520000 Item 054 1 support D5347470520100 Item 056 1 plate D5347470420400 Item 080

e Transfer drill the holes from the frame and skin panel to the shear web and the supports. f Drill all additional holes and open all holes and all countersinks to final dimension. g Install these items: 1 plate D5337217620000 Item 012 2 filler D5337217620800 Item 026 1 angle D5347470520000 Item 054 1 angle D5347470520100 Item 056 1 crossbeam D5347035300600 Item 076 1 plate D5337217620700 Item 078 1 web D5347470420200 Item 080 1 support angle D5347658420000 Item 102 with: 12 rivet MBBN4477-4814 Item 548 16 rivet LN9198-4014CF Item 640 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 389 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

57 rivet LN9198-4814CF Item 648

6 pin DAN5-6-5X Item 765 44 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 12 collar NSA5075-8 Item 808 19 pin DAN5-6-4 Item 964 21 pin DAN5-6-5 Item 965

2 pin DAN5-6-6 Item 966 2 pin DAN5-6-8 Item 968 6 pin DAN5-8-5 Item 985 3 pin DAN5-8-6 Item 986 3 pin DAN5-8-7 Item 987 5 Install the sections and the angles at FR51 between STGR34 LH/RH and STGR42 LH/RH as shown in Section D1-D5 ’AFTER’:

a Put these items in position: 1 section D5347449520300 Item 028 1 section D5347449520500 Item 032 1 angle D5347470020400 Item 044 2 angle D5347470020200 Item 048 1 angle D5347470021600 Item 082 1 angle D5347470021800 Item 084 1 angle D5347470024800 Item 086 1 angle D5347470022000 Item 088 1 angle D5347470021400 Item 090 1 angle D5347470022200 Item 092 1 section D5347470022400 Item 094 1 section D5347470023000 Item 096 1 angle D5347470022800 Item 098 1 angle D5347470022600 Item 100

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel and install with these items: 34 rivet MBBN4477-4814 Item 548 62 rivet LN9198-4814CF Item 648

4 pin DAN6-6-7X Item 667 4 pin DAN6-6-9X Item 669 27 collar NSA5075-6 Item 806

8 collar DAN11-6X Item 807 17 pin DAN6-6-5 Item 865 10 pin DAN6-6-7 Item 867 6 Replace the riveting between clip and skin panel at FR51 between STGR40 LH/RH and STGR42 LH/RH as shown in Section D1-D5 ’AFTER’:

a Remove the existing rivets. b Open the holes and the countersinks to final dimension. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 390 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

c Install these items: 8 rivet MBBN4477-4814 Item 548 4 pin DAN6-6-7X Item 667 4 pin DAN6-6-9X Item 669 8 pin DAN6-6-8Y Item 678 8 collar NSA5330-6 Item 803 8 collar DAN11-6X Item 807 7 Replace the riveting between stringer and skin panel at FR51 at STGR41 RH as shown in View A5-A5:

a Remove the existing rivets. b Open the holes and the countersinks to final dimension.

c Install these items: 8 pin DAN6-6-8Y Item 678 8 collar NSA5330-6 Item 803 (h) Install the shear plates between FR48 and FR51 at STGR43 LH. Refer to Kit 281118D85R02 Refer to Drawing(s): D53470075002 Sheet(s) 3 and 7 1 Install the shear plate between FR48 and FR49 at STGR43 LH as shown in Section F1-F7:

a Put this item in position: 1 plate D5347471321200 Item 104

b Put this item in position as shown in Sheet 3, Section B15-B3: 1 section D5347449521800 Item 020

c Transfer drill the holes to the section, Item 020. d Drill the additional holes from the shear plate to the stringer and crossbeams and open all holes to final dimension.

e Install these items: 1 section D5347449521800 Item 020 1 plate D5347471321200 Item 104 with: 34 rivet LN9198-4014CF Item 640

2 rivet LN9198-4814CF Item 648 2 collar NSA5075-6 Item 806 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 391 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 pin DAN5-6-7 Item 967 2 Install the shear plates between FR49 and FR51 at STGR43 LH as shown in Section C1-C4: Refer to Drawing(s): D53470075002 Sheet(s) 4 and 7

a Put this item in position: 2 plate D5347471320800 Item 106

b Put this item in position as shown in Sheet 4. 2 section D5347449522000 Item 062

c Transfer drill the holes to the sections, Item 062. d Drill the additional holes from the shear plate to the stringer and crossbeams and open all holes to final dimension.

e Install these items: 2 section D5347449522000 Item 062 2 plate D5347471320800 Item 106 with: 68 rivet LN9198-4014CF Item 640

4 rivet LN9198-4814CF Item 648 4 collar NSA5075-8 Item 808 4 pin DAN5-8-7 Item 987 (i) Modify the structure at FR53 between STGR36 LH and STGR42 LH. Refer to Kit 281118D85R02 Refer to Drawing(s): D53470075002 Sheet(s) 6 1 Remove this item at FR53 as shown in Section E1-E6 ’BEFORE’:

a Remove and discard this item: 1 shim D5347061120200 Item (402) discard 2 Install the reinforcing strap at FR53 between STGR35 LH and STGR42 LH as shown in Section E1-E6 ’AFTER’:

a Put this item at FR53 in position: 1 strap D5347448420200 Item 022

b Transfer drill the holes from the frame to the straps. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 392 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

c Drill the additional holes from the reinforcing straps to the frame and open all holes and all countersinks to final dimension. d Install these items: 1 strap D5347448420200 Item 022 with: 29 rivet LN9198-4014CF Item 640

4 collar NSA5075-6 Item 806 4 pin DAN6-6-5 Item 865 (j) Install the shear plates between FR48 and FR51 at STGR43 LH. Refer to Kit 281118D85R02 Refer to Drawing(s): D53470075002 Sheet(s) 3 and 7 1 Install the shear plate between FR48 and FR49 at STGR43 LH as shown in Section F1-F7:

a Put this item in position: 1 plate D5347471321200 Item 104

b Put this item in position as shown in Sheet 3, Section B1-B3: 1 section D5347449521800 Item 020

c Transfer drill the holes to the section, Item 020. d Drill the additional holes from the shear plate to the stringer and crossbeams and open all holes to final dimension.

e Install these items: 1 section D5347449521800 Item 020 1 plate D5347471321200 Item 104 with: 34 rivet LN9198-4014CF Item 640

2 rivet LN9198-4814CF Item 648 2 collar NSA5075-6 Item 806 2 pin DAN5-6-7 Item 967 2 Install the shear plates between FR49 and FR51 at STGR43 LH as shown in Section F1-F7: Refer to Drawing(s): D53470075002 Sheet(s) 4 and 7 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 393 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Put this item in position: 1 plate D5347471322400 Item 138 1 plate D5347471322600 Item 140

b Put this item in position as shown in Sheet 4, Section C1-C4 and Sheet 5, Section D1-D5. 2 section D5347449522000 Item 062

c Transfer drill the holes to the sections, Item 062. d Drill the additional holes from the shear plate to the stringer and crossbeams and open all holes to final dimension.

e Install these items: 2 section D5347449522000 Item 062 1 plate D5347471322400 Item 138 1 plate D5347471322600 Item 140 with: 68 rivet LN9198-4014CF Item 640

4 rivet LN9198-4814CF Item 648 4 collar NSA5075-8 Item 808 4 pin DAN5-8-7 Item 987 (k) Install the plates between FR48 and FR59 at STGR38 LH and STGR38 RH. Refer to Kit 281118D85R02 Refer to Drawing(s): D53470075002 Sheet(s) 8 and 11 1 Install the plates and the angles between FR48 and FR59 at STGR38 LH as shown in Sections H1-H8 and K1-K11:

a Put these items in position: 2 plate D5347471500200 Item 108 1 plate D5347471500000 Item 110 1 plate D5347471500600 Item 112 1 plate D5347471500800 Item 114 1 plate D5347471501000 Item 116 6 angle D5347470120000 Item 128 6 angle D5347470120200 Item 130 1 section D5347065020400 Item 208 1 plate D5347048800400 Item 214 1 plate D5347048900400 Item 216 1 plate D5347049200400 Item 218 2 angle D5347046824000 Item 228 1 angle D5347046823800 Item 230 1 angle D5347046823600 Item 232 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 394 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 angle D5347046824200 Item 234 1 angle D5347046824400 Item 236 NOTE : Install the angle, Item 130, together with the section, Item 028. b Transfer drill the holes from the stringer and frames to the plates and the angles.

c Transfer drill the holes from the skin panel to the section at FR52. d Drill the additional holes and open all holes to final dimension.

e Install the listed items as shown in Sections H1-H8 and K1-K11 with: 230 rivet LN9198-4014CF Item 640 4 pin DAN6-6-5X Item 665 3 pin DAN6-6-6X Item 666 3 pin DAN6-6-7X Item 667 5 pin DAN5-6-4X Item 764 8 pin DAN5-6-6X Item 766 3 pin DAN5-6-8X Item 768 16 collar NSA5075-6 Item 806 26 collar DAN11-6X Item 807 10 pin DAN5-6-4 Item 964

6 pin DAN5-6-8 Item 968 2 Install the plates and angles between FR48 and FR59 at STGR38 RH as shown in Sections G1-G8 and J1-J11:

a Put these items in position: 2 plate D5347471500300 Item 118 1 plate D5347471500100 Item 120 1 plate D5347471501400 Item 122 1 plate D5347471502600 Item 124 1 angle D5347659100000 Item 126 4 angle D5347470120100 Item 132 5 angle D5347470120300 Item 134 1 section D5347066920600 Item 136 1 shim D5337236320200 Item 202 1 section D5347063721600 Item 206 1 shear plate D5347048700200 Item 210 1 shear plate D5347048500400 Item 212 1 angle D5347046824500 Item 220 1 angle D5347046824300 Item 222 1 angle D5347046824600 Item 224 NOTE : Install the angle, Item 134, together with the section, Item 029, at FR48. b Transfer drill the holes from the stringer and frames to the plates and the angles and open all holes to final dimension. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 395 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

c Install the listed items as shown in Sections G1-G8 and J1-J11 with: 126 rivet LN9198-4014CF Item 640 2 pin DAN5-6-4X Item 764 1 pin DAN5-6-8X Item 768 3 collar NSA5075-5 Item 804 6 collar NSA5075-6 Item 806 3 collar DAN11-6X Item 807 3 pin DAN5-5-5 Item 945 4 pin DAN5-6-4 Item 964 2 pin DAN5-6-8 Item 968 (l) Install the corner sections at STGR38 LH/RH between FR48 and FR59. Refer to Kit 281118D85R02 Refer to Drawing(s): D53470075002 Sheet(s) 1, 2, 3, 4, 6, 10 and 11 1 Install the corner sections at STGR38 LH between FR48 and FR59 as shown in Details X9-10 and Y1-11:

a Put these items between FR48 and FR56 in position: 1 profile D5347047500800 Item 154 1 profile D5347047600800 Item 156

b Transfer drill the holes from the fittings to the corner sections as shown in Details B2-2, B3-3, B4-4, B5-5 and A6-6.

c Drill the holes from the corner sections to the plates between FR48 and FR59 as shown in Details X9-10 and Y1-11. d Open the holes to final dimension and countersink the holes.

e Install these items: 1 profile D5347047500800 Item 154 1 profile D5347047600800 Item 156 with: 16 rivet MBBN4477-4014 Item 540 12 rivet MBBN4477-4814 Item 548 87 rivet DIN65399-3208CF Item 732 f The holes with 5.6 mm (0.220 in.) diameter between FR48 and FR51 as shown in Detail X9-10 will transfer from the roller tracks. 2 Install the corner section at STGR38 RH between FR48 and FR59 as shown in Details Z9-10 and Z1-11:

a Put this item between FR48 and FR52/A in position: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 396 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 profile D5347048100600 Item 152

b Transfer drill the holes from the fittings to the corner section as shown in Details C2-2, C3-3, C4-4 and C5-5.

c Drill the holes from the corner section to the plates between FR48 and FR59 as shown in Details Z9-10 and Z1-11. d Open the holes to final dimension and countersink the holes.

e Install these items: 1 profile D5347048100600 Item 152 with: 8 rivet MBBN4477-4014 Item 540 12 rivet MBBN4477-4814 Item 548 48 rivet DIN65399-3208CF Item 732 f The holes with 5.6 mm (0.220 in.) diameter between FR48 and FR51 as shown in Detail Z9-10 will transfer from the roller tracks. (m) Modify the crossbeams from FR48 thru FR52 for the roller track installation. Refer to Kit 281118D85R02 Refer to drawings: D53470075002 Sheet(s) 9 and 10 1 Drill the holes in the crossbeams at FR48, FR49, FR50 and FR51 as shown in Details U9-9 and W9-9:

a Mark and drill the holes with 5.6 mm (0.220 in.). 2 Install the nuts, Item 508, at the crossbeam at FR52 as shown in Detail W1-10:

a Mark and drill the holes with 5.2 mm (0.205 in.). b Put the nuts in position, drill the holes for the rivets and install this item: 4 nut NAS1791A3-1 Item 508 with: 8 rivet DIN65399-2408CF Item 724 (n) Install the water drain connection between FR47 and FR48. Refer to Kit 281118D85R02 Refer to drawings: D53372362000 Sheet(s) 9 D53470075002 Sheet(s) 13 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 397 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Make a cutout between 63.7 mm (2.508 in.) and 64.3 mm (2.531 in.) diameter in the skin panel between FR47 and FR48 and between STGR42 RH and STGR43 RH as shown in drawing D53470075002, Sheet 13, Sections A12-A13 and A13-A13. 2 Install the doubler at the outer skin as shown in the drawing D53470075002, Sheet 13, Section A12-A13 and the drawing D53372362000, Sheet 9, Detail U1-9. NOTE : Drawing D53372362000 shows the position of the doubler and fasteners for the attachment. The fasteners are contained in Kit 281118D05R06. CAUTION : REMOVE THE EXISTING RIVETS CAREFULLY. THE HEADS OF THE RIVETS WILL BE USED DURING THE DOUBLER INSTALLATION FOR THE EXISTING COUNTERSINKS IN THE SKIN PANEL.

a Remove the existing fasteners in the affected area. b Put this item in position as shown in drawing D53470075002, Sheet 13, Section A12-A13 and drawing D53372362000, Sheet 9, Detail U1-9: 1 doubler D5347646320200 Item 160

c Transfer drill the holes. d Drill the additional holes and open all holes to final dimension as shown in drawing D53470075002, Sheet 13, Detail A13-13.

e Install this item: 1 doubler D5347646320200 Item 160 with: 33 rivet LN9198-4814CF Item 648 12 pin DAN5-6-8X Item 768 18 pin DAN5-6-9X Item 769

4 pin DAN5-6-11X Item 771 10 pin DAN5-6-12X Item 772 14 collar NSA5075-6 Item 806 44 collar DAN11-6X Item 807 18 collar DAN11-8X Item 810

4 pin DAN5-8-7X Item 887 6 pin DAN5-8-11X Item 891 8 pin DAN5-8-12X Item 892 14 pin DAN5-6-6 Item 966 NOTE : The Items 768, 769, 771, 772, 807, 810, 887, 891 and 892 are contained in Kit 281118D05R06.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 398 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

3 Install the tube as shown in drawing D53470075002, Sheet 13, Section A12-A13 and in Detail A13-13:

a Put these items in position: 1 tube D5347669000000 Item 172 2 shim D5347472120000 Item 176

b Transfer drill the eight holes as shown in drawing D53372362000, Sheet 9, Detail U1-9.

c Drill the eight holes as shown in drawing D53470075002, Sheet 13, Detail Z13-13. d Open all holes to final dimension.

e Install these items: 1 tube D5347669000000 Item 172 2 shim D5347472120000 Item 176 with: 8 pin DAN5-6-11X Item 771 8 collar NSA5075-6 Item 806 8 collar DAN11-6X Item 807 2 pin DAN6-6-6 Item 866 6 pin DAN5-6-10 Item 970 see NOTE NOTE : Alternative part is pin DAN6-6-10, Item 870. NOTE : The Items 771 and 807 are contained in Kit 281118D05R06, refer to drawing D53372362000, Sheet 9. f Drill the four holes for the receptacles, Item 504, with 5.6 mm (0.220 in.) diameter as shown in drawing D53470075002, Sheet 13, Detail Z13-13 and install this item: 4 receptacle ABS0337-01A Item 504 with: 8 rivet DIN65399-2408CF Item 724

g Install at the tube, Item 172, as shown in drawing D53470075002, Sheet 13, Section A12-A13 these items: 1 plate D5347669200000 Item 166 1 plug D5347669100000 Item 174 1 ring MS16625-4212 Item 500 1 screw NAS1096-3-10 Item 506 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 399 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(o) Install the water drain connection and the cavity drain access cover between FR49 and FR50. Refer to Kit 281118D85R02 Refer to Drawing(s): D53470075002 Sheet(s) 14 1 Make a cutout between 63.7 mm (2.508 in.) and 64.3 mm (2.531 in.) diameter in the skin panel between FR49 and FR50 and between STGR42 LH and STGR43 LH as shown in Sections B12-B14 and View A14-14. 2 Install the doubler at the outer skin as shown in Section B12-B14: CAUTION : REMOVE THE EXISTING RIVETS CAREFULLY. THE HEADS OF THE RIVETS WILL BE USED DURING THE DOUBLER INSTALLATION FOR THE EXISTING COUNTERSINKS IN THE SKIN PANEL.

a Remove the existing fasteners in the affected area. b Put this item in position as shown in View A14-14: 1 doubler D5347646320000 Item 162

c Transfer drill the holes. d Drill the additional holes as shown in View A14-14 and open all holes to final dimension.

e Install this item: 1 doubler D5347646320000 Item 162 with: 48 rivet LN9198-4814CF Item 648

8 pin DAN5-6-8Y Item 778 8 collar NSA5330-6 Item 803 154 collar NSA5075-6 Item 806

25 pin DAN5-6-5 Item 965 58 pin DAN5-6-6 Item 966 14 pin DAN5-6-7 Item 967 57 pin DAN5-6-8 Item 968 3 Install the tube as shown in Section B12-B14 and View A14-14:

a Put these items in position: 1 tube D5347669000000 Item 172 2 shim D5347472120000 Item 176

b Transfer drill the eight holes from the stringers to the tube as shown in Detail Y14-14. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 400 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

c Drill the eight holes as shown in Detail Y14-14. d Open all holes to final dimension.

e Install these items: 1 tube D5347669000000 Item 172 2 shim D5347472120000 Item 176 with: 16 collar NSA5075-6 Item 806

2 pin DAN6-6-6 Item 866 14 pin DAN5-6-10 Item 970 see NOTE NOTE : Alternative part is pin DAN6-6-10, Item 870. f Drill the four holes for the receptacles, Item 504, with 5.6 mm (0.220 in.) diameter as shown in Detail Y14-14 and install this item: 4 receptacle ABS0337-01A Item 504 with: 8 rivet DIN65399-2408CF Item 724

g Install these items at the tube, Item 172, as shown in Section B12-B14: 1 plate D5347669200000 Item 166 1 plug D5347669100000 Item 174 1 ring MS16625-4212 Item 500 1 screw NAS1096-3-10 Item 506 4 Make a cutout in the skin panel between FR49 and FR50 and between STGR40 LH and STGR41 LH as shown in View A14-14. 5 Install the nuts, Item 510, around the cutout as shown in Detail Z14-14:

a Remove the six rivets in the stringer and open the holes to 5.6 mm (0.220 in.) diameter. b Drill the four holes with 5.6 mm (0.220 in.) diameter in the skin.

c Install these items: 4 shim D5347470220000 Item 178 10 nut NAS1474A3 Item 510 with: 20 rivet DIN65399-2408CF Item 724 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 401 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

d Install this item as shown in Section B12-B14: 1 cover D5347470920200 Item 164 with: 10 screw NAS1153E7 Item 502 (p) Drill three holes in the outer skin between FR47 and FR49 and between STGR43 LH and STGR42 RH. Refer to Kit 281118D85R02 Refer to Drawing(s): D53470075002 Sheet(s) 12 1 Drill two holes with 20.0 mm (0.787 in.) diameter and one hole with 14.5 mm (0.578 in.) diameter as shown in View C1-12. (q) Install the brackets for the fuel drain/vent systems between FR46 and FR54. Refer to Kit 281118D92R00 1 Install the brackets between FR46 and FR47 as shown in Details A12-12, Y12-12 and Z12-12: Refer to Drawing(s): D28270982006 Sheet(s) 12

a Remove the existing fasteners at the affected areas. b Put these items in position: 2 angle D2827094222800 Item 102 2 bracket D2827094200400 Item 124

c Transfer drill the holes, drill the additional holes and open them to final dimension. d Install these items: 2 angle D2827094222800 Item 102 2 bracket D2827094200400 Item 124 with: 6 rivet LN9198-3212BF Item 032 8 pin DAN7-6-8Y Item 041 8 collar DAN12-6Y Item 042 2 Install the brackets at FR47 and FR48 as shown in Details A12-13, B12-13 and C12-13: Refer to Drawing(s): D28270982006 Sheet(s) 13 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 402 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Put this item in position: 3 bracket F5397461900600 Item 100

b Drill the holes for the rivets.

c Install this item: 3 bracket F5397461900600 Item 100 with: 6 rivet LN9198-4012BF Item 040 3 Install the bracket at FR49 as shown in Sections A22-A22 and B22-B22: Refer to Drawing(s): D28270982006 Sheet(s) 23 and 22

a Put these items in position: 1 angle D2827098321200 Item 119

b Drill the holes for the rivets.

c Install these items: 1 angle D2827098321200 Item 119 with: 2 rivet LN9198-4012BF Item 040 4 Install the brackets at FR49 as shown in Details H23-H26, B26-B26 and D26-D26: Refer to Drawing(s): D28270982006 Sheet(s) 23 and 26

a Put these items in position: 2 bracket D2827098320800 Item 117 2 bracket D2827098321000 Item 118

b Drill the holes for the rivets.

c Install these items: 2 bracket D2827098320800 Item 117 2 bracket D2827098321000 Item 118 with: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 403 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

8 rivet LN9198-4012BF Item 040 5 Install the brackets at FR49 and FR50 as shown in Details X14-14, Y14-14 and Z14-14: Refer to Drawing(s): D28270982006 Sheet(s) 14

a Put these items in position: 1 bracket D2827098300000 Item 104 1 bracket D2827098300200 Item 106 1 bracket D2827098325200 Item 125

b Drill the holes for the rivets.

c Install these items: 1 bracket D2827098300000 Item 104 1 bracket D2827098300200 Item 106 1 bracket D2827098325200 Item 125 with: 6 rivet LN9198-4012BF Item 040 6 Install the brackets at FR54 as shown in Sections A19-A19 and D19-D19: Refer to Drawing(s): D28270982006 Sheet(s) 19

a Put these items at FR54 in position: 1 bracket D2827098326000 Item 135 1 bracket D2827098326200 Item 136

b Drill the holes for the rivets.

c Install these items: 1 bracket D2827098326000 Item 135 1 bracket D2827098326200 Item 136 with: 4 rivet LN9198-4012BF Item 040 7 Install the brackets at FR51 and between FR53 and FR54 as shown in Sections D24-D20 and G24-G20: Refer to Drawing(s): D28270982006 Sheet(s) 20 and 24 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 404 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Put this item at FR51 in position: 2 angle D2827094220400 Item 113

b Drill the holes for the rivets.

c Install these items: 2 angle D2827094220400 Item 113 with: 8 rivet LN9198-4012BF Item 040

d Put these items at FR53 and FR54 in position: 1 bracket D2827098324200 Item 132 1 bracket D2827098324400 Item 133

e Drill the holes for the rivets. f Install these items: 1 bracket D2827098324200 Item 132 1 bracket D2827098324400 Item 133 with: 4 rivet LN9198-4012BF Item 040

g Put these items between FR53 and FR54 in position: 1 bracket D2827098323800 Item 130 1 bracket D2827093521000 Item 131 1 bracket D2827098324000 Item 134

h Drill the holes for the rivets. i Install these items: 1 bracket D2827098323800 Item 130 1 bracket D2827093521000 Item 131 1 bracket D2827098324000 Item 134 with: 6 screw NAS1096-3-8 Item 004 6 washer NAS1149C0332R Item 005 6 nut NAS1726C3E Item 006 2 rivet LN9198-4012BF Item 040 8 Install the brackets at FR53 as shown in Details B24-B25, A25-A25, and C25-C25: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 405 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s): D28270982006 Sheet(s) 24 and 25

a Put this items in position: 3 angle D2827094221400 Item 112 2 bracket D2827098323200 Item 127 2 bracket D2827098323000 Item 128

b Drill the holes for the rivets.

c Install these items: 3 angle D2827094221400 Item 112 2 bracket D2827098323200 Item 127 2 bracket D2827098323000 Item 128 with: 10 rivet LN9198-4012BF Item 040 9 Install the brackets between FR50 and FR53 as shown in Details W23-27, X23-27 and Y23-27: Refer to Drawing(s): D28270982006 Sheet(s) 23 and 27

a Put this items in position: 2 angle D2827098227600 Item 137 1 bracket D2827098327800 Item 138 1 bracket D2827098328000 Item 139 1 bracket D2827098328200 Item 140

b Drill the holes for the rivets.

c Install these items: 2 angle D2827098227600 Item 137 1 bracket D2827098327800 Item 138 1 bracket D2827098328000 Item 139 1 bracket D2827098328200 Item 140 with: 10 rivet LN9198-4012BF Item 040 1 0 Install the brackets at FR52 as shown in Sections C24-C28, a28-A28, C28-C28 and D28-D28: Refer to Drawing(s): D28270982006 Sheet(s) 24 and 28 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 406 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Put this items at FR52 in position: 2 bracket D2827094222200 Item 116 2 bracket D2827098300800 Item 126 2 bracket D2827098323200 Item 127

b Drill the holes for the rivets.

c Install these items: 2 bracket D2827094222200 Item 116 2 bracket D2827098300800 Item 126 2 bracket D2827098323200 Item 127 with: 12 rivet LN9198-4012BF Item 040 (r) Replace fasteners at FR48, FR49, FR50 and FR51 between STGR3 LH and STGR36 LH. Refer to Kit 281118D86R00 Refer to Drawing(s): D53470095000 Sheet(s) 1 1 Replace the fasteners at FR48 between STGR34 LH and STGR36 LH as shown in Section A1-A1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. b Open the affected holes to final dimension.

c Install these items: 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR48. 2 Replace the fasteners at FR49 between STGR34 LH and STGR36 LH as shown in Section A1-A1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 407 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

b Open the affected holes to final dimension.

c Install these items: 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR49. 3 Replace the fasteners at FR50 between STGR34 LH and STGR36 LH as shown in Section A1-A1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. b Open the affected holes to final dimension.

c Install these items: 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR50. 4 Replace the fasteners at FR51 between STGR34 LH and STGR36 LH as shown in Section A1-A1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. b Open the affected holes to final dimension.

c Install these items: 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR51. (s) Remove and discard the insulation blankets at FR46. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 408 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to AMM 25-80-00, Page block 201 Refer to drawing(s): D25870003054 Sheet(s) 20 1 Remove and discard these items: 1 blanket D2587085002000 Item (020) discard 1 blanket D2587085102200 Item (021) discard 1 blanket D2587085202000 Item (022) discard 1 blanket D2587085302200 Item (023) discard 1 blanket D2587085402000 Item (024) discard 1 blanket D2587085502200 Item (025) discard 1 blanket D2587085602000 Item (026) discard 1 blanket D2587085702000 Item (027) discard 1 blanket D2587085802000 Item (028) discard 1 blanket D2587085902000 Item (029) discard 1 blanket D2587086002000 Item (030) discard 1 blanket D2587086102000 Item (031) discard 1 blanket D2587086202000 Item (032) discard 1 blanket D2587086302200 Item (033) discard 1 blanket D2587086502000 Item (034) discard 1 blanket D2587087102000 Item (035) discard 1 blanket D2587087302000 Item (036) discard (t) Install the insulation blankets at FR46. Refer to AMM 25-80-00, Page block 201 Refer to Kit 281118D27R00 Refer to Drawing(s): D25870003054 Sheet(s) 20 1 Install these items: 1 blanket D2587085002200 Item 000 1 blanket D2587085105600 Item 001 1 blanket D2587085205200 Item 002 1 blanket D2587085305600 Item 003 1 blanket D2587085405200 Item 004 1 blanket D2587085505000 Item 005 1 blanket D2587085602200 Item 006 1 blanket D2587085705200 Item 007 1 blanket D2587085805200 Item 008 1 blanket D2587085905200 Item 009 1 blanket D2587086005400 Item 010 1 blanket D2587086105200 Item 011 1 blanket D2587086202200 Item 012 1 blanket D2587086302400 Item 013 1 blanket D2587086502300 Item 014 1 blanket D2587087102300 Item 015 1 blanket D2587087303000 Item 016

with: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 409 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

80 strip F2587003400000 Item 100 (u) Install a bracket at the passenger compartment floor structure at FR53. Refer to Kit 281118D55R00 Refer to Drawing(s): D53472833008 Sheet(s) 4 1 Put the bracket, Item 000, in position as shown in Detail Z4-4. 2 Transfer drill the holes and open them to final dimension. 3 Install this item: 1 bracket D5347212320000 Item 000

with: 1 pin D5347212420000 Item 002 1 pin D5347212420200 Item 004 (v) Replace the bracket between FR46 and FR47. Refer to Kit 281118D56R00 Refer to Drawing(s): D26270107000 Sheet(s) 1 thru 3 1 Remove the bracket: 1 bracket D2627004020200 Item (001) discard 1 clamp Item (002) discard 3 nut Item (003) discard 3 screw Item (004) discard 1 bonding lead Item (005) discard 2 Install the bracket: Refer to Kit 281118D56R00

a Put the bracket, Item 100, in position and drill the two holes up to 13.0 mm (0.511 in.) dia. b Put in position and install this item: 1 bracket D2627004020800 Item 100 with: 1 clamp NSA5516A18NJ Item 075 3 nut NAS1726-3E Item 086 1 screw NAS1303-2 Item 090 1 bonding lead ASNA0182-3DA Item 098 2 screw NSA5031-3-14 Item 123 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 410 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(w) Install the ACT pressurization system between FR48 and FR54. Refer to Kit 281118D91R01 and Kit 281118B01R00 Refer to Drawing(s): D28270975006 Sheet(s) 8, 11 and 13 thru 16 1 Install these items at the crossbeam at FR54 as shown in Section D8-D8: 1 coupling A2827092300000 Item 050 1 nut AN924-10J Item 074 1 tee MS21909J10 Item 075 1 washer NAS1149F1432P Item 076 2 Install these items at the crossbeam at FR54 as shown in drawing D28270975006, Sheet 13, Sections E1-E13, Sheet 8, Section A7-A8 and C8-C8: 1 tube D2827097902000 Item 021 1 valve HTE490005 Item 042 1 actuator HTE200002-1 Item 043 1 valve HTE920007-001 Item 044 1 clamp HTE8002 Item 045

NOTE : The Items 042, 043, 044 and 045 are contained in Kit 281118B01R00. 3 Install these items as shown in Sections A7-A8, B8-B8 and C8-C8: 1 nut NAS1726C3E Item 070 1 screw NAS1096-3-8 Item 071 1 washer NAS1149C0332R Item 073 1 clamp NSA5575-8A Item 081 1 strap E0090-10-125NN Item 083 1 bolt NAS1303-2 Item 088 1 nut NAS1726-3E Item 089 1 washer NAS1149D0316H Item 090 4 Install these items with adhesive (Mat. No. 08-010)as shown in Section A7-A8: 1 placard D2827094420000 Item 200 1 placard D2827094420200 Item 202 1 placard D2827094420400 Item 204 1 placard D2827094421200 Item 212 5 Install these items at the crossbeam at FR53 as shown in Section B14-B14: 1 coupling A2827092300000 Item 050 1 nut AN924-10J Item 074 1 tee MS21909J10 Item 075 1 washer NAS1149F1432P Item 076 6 Install these items at the crossbeam at FR53 as shown in drawing D28270975006, Sheet, 13 and Section B13-B14: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 411 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 tube D2827097901800 Item 019 1 valve HTE490005 Item 047

NOTE : The Item 047 is contained in Kit 281118B01R00. 7 Install this item between FR53 and FR54 as shown in Section E7-E11: 1 valve PAS148-133A Item 046

with: 2 nut NAS1726C3E Item 070 2 washer NAS1149C0332R Item 073 2 screw NAS1096-3-12 Item 098

NOTE : The Item 046 is contained in Kit 281118B01R00. 8 Install these items as shown in Section I14-I14: 1 clamp NSA5575-8A Item 081 1 strap E0090-10-125NN Item 083 2 bolt NAS1303-2 Item 088 2 nut NAS1726-3E Item 089 4 washer NAS1149F0332P Item 103 9 Install these items with adhesive (Mat. No. 08-010) as shown in Section B13-B14: 1 placard D2827094420600 Item 206 1 placard D2827094420800 Item 208 1 0 Install this item between FR53 and FR54 as shown in drawing D28270975006, Sheet 13, and Section E3-E11: 1 hose 1451515F0150-18 Item 040

with: 1 nut NAS1726C3E Item 070 1 screw NAS1096-3-8 Item 071 1 washer NAS1149C0332R Item 073 1 clamp MS21919WCH15 Item 101 1 1 Install these items as shown in drawing D28270975006, Sheet 13, and Sections B13-B14, G13-G15, H13-H15, K13-K15 and L13-L15: 1 tube D2827098000800 Item 005 1 tube D2827098002400 Item 222 1 tube D2827098002600 Item 220 1 tube D2827098001400 Item 011

with: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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15 nut NAS1726C3E Item 070 12 screw NAS1096-3-8 Item 071 15 washer NAS1149C0332R Item 073 13 clamp MS21919WDE4 Item 080

4 clamp NSA5575-2 Item 082 4 lead E0090-18-100NN Item 084 4 screw NAS1096-1-8 Item 085 4 washer NAS1149DN616H Item 086 4 nut MS21042-06 Item 087 3 screw NAS1096-3-9 Item 097 1 2 Install these items between FR48 and FR49 as shown in Section G13-G15: 1 filter A2163302000000 Item 027 1 inlet A2151034520000 Item 028 1 nut AN924-4D Item 092 1 3 Install these items as shown in drawing D28270975006, Sheet 13, and Sections A13-A8, C13-C10 and D13-D11: 1 tube D2827097901000 Item 016 1 tube D2827097901600 Item 017 1 tube D2827097902400 Item 025 1 tube D2827097904000 Item 026

with: 6 nut NAS1726C3E Item 070 3 screw NAS1096-3-8 Item 071 6 washer NAS1149C0332R Item 073 1 conduit TSTMNR503-0 Item 077 2 tie NSA935401-03 Item 078 6 clamp MS21919WDE10 Item 079 4 clamp NSA5575-8A Item 081 4 strap E0090-10-125NN Item 083 4 bolt NAS1303-2 Item 088 4 nut NAS1726-3E Item 089 4 washer NAS1149D0316H Item 090 3 screw NAS1096-3-9 Item 097

NOTE : Cut the conduit, Item 077, into two pieces. 1 4 Install this item between FR51 and FR52 as shown in drawing D28270975006, Sheet 13, and Section C13-C10: 1 filter QB0566 Item 041

with: 1 union MS21902D10 Item 030 1 packing NAS1612-10 Item 031 4 nut NAS1726C4E Item 093 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 413 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

NOTE : The Item 041 is contained in Kit 281118B01R00. 1 5 Install this item with adhesive (Mat. No. 08-010)as shown in Section C13-C10: 1 placard D2827094421000 Item 210 1 6 Install this item as shown in drawing D28270975006 Sheet 13, and Section F13-F11: 1 tube D2827097901400 Item 015

with: 2 nut NAS1726C3E Item 070 2 screw NAS1096-3-8 Item 071 2 washer NAS1149C0332R Item 073 1 conduit TSTMNR503-0 Item 077 2 tie NSA935401-03 Item 078 2 clamp MS21919WDE10 Item 079 1 7 Install these items as shown in drawing D28270975006, Sheet 13, and Section F13-F11, Details X13-11, Y13-11 and Z13-11: 1 tube D2827097901200 Item 013 1 elbow MS21908J10 Item 091 1 tee MS21905J10 Item 099

with: 2 nut NAS1726C3E Item 070 1 screw NAS1096-3-8 Item 071 2 washer NAS1149C0332R Item 073 2 clamp MS21919WDE10 Item 079 2 clamp NSA5575-8A Item 081 1 strap E0090-10-125NN Item 083 2 bolt NAS1303-2 Item 088 2 nut NAS1726-3E Item 089 2 washer NAS1149D0316H Item 090 2 cap MS21914-10D Item 094 1 nut AN924-10J Item 095 1 washer NAS1149C1432R Item 096 1 screw NAS1096-3-9 Item 097 1 strap E0090-10-160NN Item 102 (x) Install the shims under the track and the YZ-latches between FR52 and FR59. Refer to Kit 281118D40R02 Refer to Drawing(s): D25572631022 Sheet(s) 22 NOTE : At a junction between new and existing roller tracks it is not allowed to shim only the new tracks. The same amount of shims must be DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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placed below the new and the existing tracks. It may be necessary to shim the AFT roller tracks also. 1 Measure the difference in vertical direction at FR52 between both roller tracks in center line position. 2 Remove and retain the AFT cargo compartment ball mats between FR52A and FR56, refer to AMM 25-52-22, Page block 401. 3 Remove and retain if necessary the roller tracks, as shown in drawing D25572631022, Sheet 22, and refer to AMM 25-52-21, Page block 401: 4 Remove and retain if necessary, the YZ-latches between FR52 and FR59 as shown in drawing D25572631022, Sheet 22, and refer to AMM 25-52-44, Page block 401: 5 Put these items in position as required as shown in drawing D25572631022, Sheet 4,: NOTE : The quantity of the shims at each position is depended on the measurement at FR52. YY 12 shim D2557214631800 Item 014 12 shim D2557214632000 Item 015

4 shim D2557214633400 Item 034 4 shim D2557214633500 Item 035 4 shim D2557214633600 Item 036 36 shim D2557214635000 Item 050 36 shim D2557214635100 Item 051 36 shim D2557214635200 Item 052

2 shim D2557214635400 Item 054 2 shim D2557214635500 Item 055 2 shim D2557214635600 Item 056 2 shim D2557214653400 Item 058 2 shim D2557214653500 Item 059 2 shim D2557214653600 Item 060 14 shim D2557214636800 Item 066 14 shim D2557214637000 Item 068 16 shim D2557214637200 Item 070 16 shim D2557214637400 Item 072

4 shim D2557214637600 Item 076 4 shim D2557214637700 Item 077 4 shim D2557214637800 Item 078 12 shim D2557214638000 Item 080 12 shim D2557214638100 Item 081 12 shim D2557214638200 Item 082

2 shim D2557214638400 Item 084 2 shim D2557214638500 Item 085 2 shim D2557214638600 Item 086 6 shim D2557214638800 Item 088 6 shim D2557214638900 Item 089 6 shim D2557214639000 Item 090 4 shim D2557214639600 Item 096 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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4 shim D2557214639700 Item 097 4 shim D2557214639800 Item 098 2 plug D2557206229800 Item 104 4 screw NAS1102-3-10 Item 134 4 shim D2557214653000 Item 229 2 shim D2557214653800 Item 233 2 shim D2557214653900 Item 234 2 shim D2557214654000 Item 235 16 shim D2557214653200 Item 236 6 If removed, install the YZ-latches between FR52 and FR59 with sealant (Mat. No. 09-005) as shown in drawing D25572631022, Sheet 22, and refer to AMM 25-52-44, Page block 401: 7 If removed, install the roller tracks with sealant (Mat. No. 09-005) as shown in drawing D25572631022, Sheet 22, and refer to AMM 25-52-21, Page block 401: 8 If removed, install in the ball mats between FR52A and FR56, (Refer to AMM 25-52-22, Page block 401). (y) Remove and discard the passenger compartment floor panels 231LF, 231MF, 241JF and 231QF. Refer to AMM 53-42-12, Page block 401 D53675013010 Sheet(s) 12 1 Remove and discard these items:

2 panel D5367160000000 Item (204) discard 1 panel D53671051000 Item (205) discard 1 panel D5367161700400 Item (305) discard 1 plate D5367009920400 Item (306) discard (z) Install the passenger compartment floor panels 231LF, 231MF and 241JF. Refer to Kit 281118D39R01 Refer to Drawing(s): D53675013010 Sheet(s) 12 thru 14 1 Install these items: 1 panel D5367161702200 Item 018 2 panel D5367160001600 Item 029 1 panel D5367150100200 Item 030

with: 74 screw ABS0376-3-25 Item 400 74 nut ABS0365-3-1B Item 405 (aa) Seal the gaps at the installed passenger compartment floor panels 231LF, 231MF and 241JF Refer to Kit 281118D29R00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Refer to Drawing(s): D53675014002 Sheet(s) 3 and 4 1 Install this item: cord DAN107-1 Item 385 and seal all gaps with sealant (Mat. No. 09-016). 2 Install after sealing this item: tape ABS5093AT25 Item 387 3 Modify the carpet to get access to the access panels in the passenger compartment floor panels 231LF, 231MF and 241JF. (ab) Remove and discard the AFT cargo compartment floor panel between FR47 and FR52A and between FR56 and FR59. Refer to AMM 53-42-14, Page block 401 Refer to Drawing(s): D53672848002 Sheet(s) 4 1 Remove and discard these items as shown in View A4-4: 1 panel D5367209500200 Item (218) discard 1 panel D5367209500300 Item (219) discard 1 panel D5367209600000 Item (220) discard 1 panel D5367209700000 Item (221) discard 1 panel D5367209800000 Item (222) discard 1 panel D5367209900000 Item (223) discard 1 panel D5367210200200 Item (224) discard 1 panel D5367210000200 Item (225) discard (ac) Install the AFT cargo compartment floor panels between FR47 and FR52A and between FR56 and FR59. Refer to Kit 281118D37R00 Refer to AMM 53-42-14, Page block 401 Refer to Drawing(s): D53672848002 Sheet(s) 5 and 6 1 Install the AFT cargo compartment floor panels between FR47 and FR52A.

a Install these items at the cargo compartment crossbeams as shown in Detail A5-5: 1 plate D5397484220000 Item 110 1 plate D5397484220100 Item 111 2 spacer D5397489520000 Item 118 2 spacer D5397489520100 Item 119 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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with: 20 screw NAS1102-3-8 Item 408 b Install this item as shown in Detail A5-52: 1,6 ME tape ABS5006-4D Item 441

c Install these items as shown in Detail A5-5: 1 panel D5367520801400 Item 036 1 panel D5367520801800 Item 038 1 panel D5367520805000 Item 040 1 panel D5367520805200 Item 042 1 panel D5367521103400 Item 092 1 panel D5367521103600 Item 094 with: 4 screw ABS0376-3-30 Item 402 91 screw ABS0376-3-40 Item 404 60 nut ABS0365-3-1B Item 410 2 Install the AFT cargo compartment floor panels between FR55 and FR59.

a Install these items as shown in Detail A5-5: 1 panel D5367521102600 Item 084 1 panel D5367521102800 Item 086 1 panel D5367521103000 Item 088 1 panel D5367521103200 Item 090 with: 41 screw ABS0376-3-30 Item 402 16 screw ABS0376-3-40 Item 404 16 nut ABS0365-3-1B Item 410 (ad) Install the seal sections in the gaps between the cargo compartment floor panels between FR47 and FR59. Refer to Kit 281118D30R00 Refer to Drawing(s): D53672849002 Sheet(s) 4 thru 6 1 Install these items: section ABS0305LC Item 001 section ABS0399A Item 004 2 Install this item in the gaps: cord DAN107-1 Item 005 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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and seal all gaps with sealant (Mat. No. 09-016). (ae) Remove and discard the attachment structure of the partition panels 151AW, 151BW and 152BW. Refer to Drawing(s): D53975018002 Sheet(s) 7 thru 9 1 Remove and discard these items as shown in Section B7-B8: 1 section D5397468100000 Item (201) discard 1 section D5397467400200 Item (202) discard 1 section D5397467400300 Item (203) discard 1 section D5397468900400 Item (210) discard 1 section D5397467900600 Item (224) discard 1 section D5397467900400 Item (226) discard 1 section D5397474700000 Item (233) discard 1 section D5397467800600 Item (238) discard 1 section D5397467800700 Item (239) discard 14 section D5397489820000 Item (270) discard

2 section D5397489820200 Item (272) discard 4 section D5397489820600 Item (274) discard 2 section D5397489820400 Item (276) discard 1 section D5397474900000 Item (334) discard

NOTE : The attachment brackets of the sections, Item 202 and 203, remain in the aircraft. 2 Remove and discard these items as shown in drawing D53975018002, Sheet 7: 1 section D5347047400200 Item (230) discard 1 section D5347047400300 Item (231) discard 1 section D5347034400000 Item (234) discard 3 Close the existing holes with these items as shown in Sections C9-C9 and D9-D9: 2 rivet NAS1097AD4-10 Item 532 4 collar NSA5075-6 Item 806 4 pin DAN5-6-2 Item 962 (af) Install the attachment structure of the partition panels 151AW, 151BW and 152BW between FR46 and FR47. Refer to Kit 281118D38R00 Refer to Drawing(s): D53975018002 Sheet(s) 10 thru 12 1 Install these items as shown in Section B9-B10 and Details X10-11 and Z10-11: 1 section D5397468800200 Item 044 1 section D5397468800300 Item 045 1 section D5397468000400 Item 046 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 section D5397468000500 Item 047

with: 32 bolt NAS6703-2 Item 025 32 washer NAS1149D0332K Item 026 2 Put these items at the existing brackets in position as shown in Section B9-B10 and Detail Y10-12: 1 section D5397467400500 Item 052 1 section D5397467400400 Item 053 3 Put these items in position as shown in Section B9-B10: 1 section D5397492500090 Item 048 1 section D5397492500290 Item 050 4 Drill and countersink the holes and open them to final dimension. 5 Install these items: 1 section D5397492500000 Item 048 1 section D5397492500200 Item 050 1 section D5397467400400 Item 052 1 section D5397467400500 Item 053

with: 100 rivet NAS1097AD4-10 Item 532 6 Put these items in position as shown in Section B9-B10: 1 section D5397467800800 Item 040 1 section D5397467800900 Item 041 1 section D5397492600000 Item 042 7 Drill and countersink the holes and open them to final dimension. 8 Install these items: 1 section D5397467800800 Item 040 1 section D5397467800900 Item 041 1 section D5397492600000 Item 042

with: 44 rivet NAS1097AD4-10 Item 532 9 Install this item as shown in Detail V10-10: 3 plate D5397492700000 Item 054 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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with: 9 screw NAS1102E3-7 Item 400 9 washer DAN125-4 Item 402 1 0 Seal the gaps with sealant (Mat. No. 09-013) as shown in Section A10-A10 and Detail V10-10. 1 1 Put these items in position as shown in Section B9-B10: 1 bracket D5397469000000 Item 016 1 bracket D5397469000001 Item 017 1 bracket D5397469200000 Item 018 1 bracket D5397469200100 Item 019 1 bracket D5397469300000 Item 020 1 bracket D5397469300100 Item 021 1 2 Drill and countersink the holes and open them to final dimension. 1 3 Install these items: 1 bracket D5397469000000 Item 016 1 bracket D5397469000100 Item 017 1 bracket D5397469200000 Item 018 1 bracket D5397469200100 Item 019 1 bracket D5397469300000 Item 020 1 bracket D5397469300100 Item 021

with: 14 rivet EN6081D6-12 Item 648 1 4 Put these items in position as shown in Section B6-B6: 1 section D5347047400200 Item 30 1 section D5347047400300 Item 31 1 5 Drill and countersink the holes and open them to final dimension. 1 6 Install these items: 1 section D5347047400200 Item 030 1 section D5347047400300 Item 031

with: 32 rivet NAS1097AD4-10 Item 532 (ag) Install the attachment structure of the cargo compartment floor panels at FR49 and FR51. Refer to Kit 281118D38R00

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Refer to Drawing(s) : D53975018000 Sheet(s) 9 1 Put these items at FR49 and FR51 in position :

2 section D5397489200000 Item 000 2 section D5397489200100 Item 001 2 Drill and countersink the holes and open them to final dimension. 3 Install these items : 2 section D5397489200000 Item 000 2 section D5397489200100 Item 001

with : 16 rivet NAS1097AD4-10 Item 532 (ah) Install the roller tracks between FR47 and FR59. Refer to Kit 281118D41R01 Refer to Drawing(s): D25572631024 Sheet(s) 23 thru 29 1 Install the roller track between FR47 and FR51, LH.

a Put these items in position as shown on Sheet 27, Detail W23-27: 1 track D2557221301200 Item 092 attach with: nut NAS1726-3E Item 008 b Alternative fastener parts as shown on Sheet 27, Detail W23-27: screw NAS1102-3-10 Item 007 screw NAS1102-3-11 Item 009 screw NAS1102-3-12 Item 010 screw NAS1100-3-14 Item 011 screw NAS1102-3-16 Item 012 screw NAS1102-3-9 Item 039 screw NAS1100-3-10 Item 070 screw NAS1100-3-9 Item 083 screw NAS1100-3-11 Item 084 screw NAS1100-3-15 Item 085 screw NAS1100-3-14 Item 086 screw NAS1100-3-7 Item 087 2 Install the roller track between FR47 and FR51, RH DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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a Put these items in position as shown on Sheet 26, Detail V23-26 1 track D2557221301400 Item 088 attach with: nut NAS1726-3E Item 008 b Alternative fastener parts as shown on Sheet 27, Detail V23-26: screw NAS1102-3-10 Item 007 screw NAS1102-3-11 Item 009 screw NAS1102-3-12 Item 010 screw NAS1100-3-14 Item 011 screw NAS1102-3-16 Item 012 screw NAS1102-3-9 Item 039 screw NAS1100-3-10 Item 070 screw NAS1100-3-9 Item 083 screw NAS1100-3-11 Item 084 screw NAS1100-3-15 Item 085 screw NAS1100-3-14 Item 086 screw NAS1100-3-7 Item 087 3 Install the roller track between FR47 and FR59

a Put these items in position as shown on Sheet 25, Details T23-25, View C25, and Sections A25-A25 and B25-B25: 1 track D2557221501600 Item 030 attach with: nut NAS1726-3E Item 008 b Alternative fastener parts as shown on Sheet 25, Detail T23-25: screw NAS1102-3-10 Item 007 screw NAS1102-3-11 Item 009 screw NAS1102-3-12 Item 010 screw NAS1100-3-14 Item 011 screw NAS1102-3-16 Item 012 screw NAS1102-3-9 Item 039 screw NAS1100-3-10 Item 070 screw NAS1100-3-9 Item 083 screw NAS1100-3-11 Item 084 screw NAS1100-3-15 Item 085 screw NAS1100-3-14 Item 086 screw NAS1100-3-7 Item 087

c Put in position and install on the roller track, Item 30, between FR47 and FR59, as shown on View C25: 11 roller 1460T100-3 Item 122 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 endstop A2577238700400 Item 23 1 switch 373FL01 Item D 2 PDU 2944T100-3 Item E 1 XZ-latch 109100-1 Item 126

d Put in position and install on the roller track, Item 30, between FR47 and FR48, as shown on Detail T23-25, Sections A25-A25 and B25-B25: 1 doupling D2557268028600 Item 149 attach with: screw NAS1102-3-7 Item 006 screw NAS1102-3-10 Item 007 1 roller A2577238320000 Item 027 2 pin A2577238420400 Item 044 2 washer NAS1149C0563R Item 045 2 nut NSA5059-5 Item 046 2 shim D2557214652800 Item 103 2 shim D2557214652700 Item 104

e Put in position and install on the roller track, Item 30, between FR49 and FR51, as shown on Detail T23-25: 1 doupling D2557268121000 Item 150 attach with: screw NAS1102-3-10 Item 007 nut NAS1726-3E Item 008 screw NAS1096-3-11 Item 038 2 screw NAS1096-3-11 Item 041 1 strengthening D2557268000000 Item 029 2 washer NAS1149C0436R Item 036 2 bolt NAS1304-5 Item 037 2 bolt NAS1303-6 Item 040 tie down point DAN152-1 Item 056 2 screw ABS0202-3-10 Item 101 1 placard D2557295123200 Item 102

f Put in position and install at FR52 on the roller track, Item 30, as shown on Detail T23-25: 1 plate D2557268121000 Item A attach with: screw NAS1102-3-10 Item 007 nut NAS1726-3E Item 008 2 plate D2557263120400 Item 024 28 nut MS21042-3 Item 042 28 screw NAS1153-3 Item 043

2 shim D2557235621000 Item 091 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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4 Install the roller track between FR47 and FR59

a Put these items in position as shown on Sheet 24, View Z23-24, Details M and X: 1 track D2557221501800 Item 001 attach with: nut NAS1726-3E Item 008 b Alternative fastener parts as shown on Sheet 24, View Z23-24: screw NAS1102-3-10 Item 007 screw NAS1102-3-11 Item 009 screw NAS1102-3-12 Item 010 screw NAS1100-3-14 Item 011

c Put in position and install on the roller track, Item 30, between FR47 and FR59, as shown on View C25: 11 roller 1460T100-3 Item 122

1 endstop A2577238700400 Item 23 1 switch 373FL01 Item D 2 PDU 2944T100-3 Item E 1 XZ-latch 109100-1 Item 126

d Put in position and install on the roller track, Item 30, between FR47 and FR48, as shown on Detail T23-25, Sections A25-A25 and B25-B25: 1 doupling D2557268028600 Item 149 attach with: screw NAS1102-3-7 Item 006 screw NAS1102-3-10 Item 007 1 roller A2577238320000 Item 027 2 pin A2577238420400 Item 044 2 washer NAS1149C0563R Item 045 2 nut NSA5059-5 Item 046 2 shim D2557214652800 Item 103 2 shim D2557214652700 Item 104

e Put in position and install on the roller track, Item 30, between FR49 and FR51, as shown on Detail T23-25: 1 doupling D2557268121000 Item 150 attach with: screw NAS1102-3-10 Item 007 nut NAS1726-3E Item 008 screw NAS1096-3-11 Item 038 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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2 screw NAS1096-3-11 Item 041 1 strengthening D2557268000000 Item 029 2 washer NAS1149C0436R Item 036 2 bolt NAS1304-5 Item 037 2 bolt NAS1303-6 Item 040 tie down point DAN152-1 Item 056 2 screw ABS0202-3-10 Item 101 1 placard D2557295123200 Item 102

f Put in position and install at FR52 on the roller track, Item 30, as shown on Detail T23-25: YY 1 plate D2557268121000 Item A attach with: screw NAS1102-3-10 Item 007 nut NAS1726-3E Item 008 2 plate D2557263120400 Item 024 28 nut MS21042-3 Item 042 28 screw NAS1153-3 Item 043 g Put in position and install on the roller track, Item 1, between FR52 and FR59, as shown on Detail V: 9 roller 141100-1 Item V

h Put in position and install on the roller track, Item 1, between FR52 and FR53, and FR55 and FR56: 2 XZ-latch 2842T100-3 Item C 2 switch 373FL01 Item D screw NAS1801-3-8 Item 032 i Put in position and install on the roller track, Item 1, these items as shown on Sheet 24, Sections Z23-24, Details Z and Y: 1 support D2557225800200 Item F 1 support D2557225800000 Item F 1 endstop D2557240020700 Item H 1 endstop D2557240020600 Item J attach with: 3 nut NAS1726-3E Item 008 4 screw NAS1100-3-5 Item 018 1 spacer D2557265000000 Item 019 1 drain funnel D2557243320000 Item 022 8 screw NAS1102-3-8 Item 026 6 bolt NAS1306-5 Item 049 6 nut NAS1726-6E Item 050 6 screw NAS1801-3-8 Item 053 3 nut NSA5066-3-1 Item 054 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 drain clamp D2557243220000 Item 058 1 filter D2557243520000 Item 059 6 screw NAS1100-3-16 Item 089 5 Install the support at FR47, as shown on Detail View L23-28.

a Drill the rivet holes for the rivets: rivet DIN65339-3210CF Item 094 b Put these items in position as shown on Sheet 28, View L23-28, and Detail X: 6 support D2557226520400 Item 152 attach with: 6 plate D2557268030600 Item 151 8 pin MS24665-153 Item 047 6 sliding block D2557226120200 Item 153 6 bolt NSA5042C05-180 Item 154 6 nut NSA5060-4 Item 155 6 washer NAS1149C0432R Item 156 6 washer NAS1149C0532R Item 157 36 pin DAN7-5-5 Item 161 36 pin DAN7-5-6 Item 162 36 collar DAN12-5 Item 163 (ai) Install the YZ-Latches between FR47 and FR58. Refer to Kit 281118D42R01 Refer to Drawing(s): D25572631026 Sheet(s) 30 thru 33 1 Put in position and install as shown on Sheets 31 and 32:

7 YZ-Latch D2557238001000 Item 004 8 YZ-Latch D2557238000800 Item 005 6 YZ-Latch D2557238000400 Item 006 8 roller 2847T100-1 Item 009

attach with: 66 bolt MS21250-03006 Item 024 86 bolt MS21250-03008 Item 025 92 bolt MS21250-03010 Item 026 92 nut NAS1726-3E Item 045 12 screw NAS1096-3-7 Item 079 30 screw NAS1102-3-12 Item 083 30 screw NAS1102-3-14 Item 084 30 screw NAS1102-3-18 Item 085 30 screw NAS1102-3-22 Item 086 2 Alternative fastener parts as shown on Sheets 31 and 32: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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92 bolt MS21250-03012 Item 027 26 bolt MS21250-03014 Item 028 12 screw NAS1096-3-8 Item 080 12 screw NAS1096-3-10 Item 081 12 screw NAS1096-3-12 Item 082 (aj) Install the ball mats between FR52A and FR56. Refer to Kit 281118D43R00 Refer to AMM 25-52-22, Page block 401 Refer to Drawing(s): D25572631028 Sheet(s) 34 and 35 1 Put in position and install: 1 ball mat D2557215902400 Item 070 1 ball mat D2557215702400 Item 071 1 ball mat D2557216001400 Item 072

attach with: 4 screw NAS1102-3-10 Item 033 16 screw NAS5030-3-5 Item 034

4 nut NAS1726-3E Item 035 18 clip nut EN6131C3C4 Item 086 (ak) Install the tie down point (TDP) and plugs. Refer to Kit 281118D44R00 Refer to Drawing(s): D25572631030 Sheet(s) 36 1 Put the TDP in position and install at FR56, as shown on Section E-E: 1 tie down point DAN152-1 Item 000

attach with: 2 nut NAS1726-3E Item 003 4 screw NAS1102-3-10 Item 004 2 Put the plug in position and install at FR53, as shown on Sections H-H and J-J: 2 plug D2557206220200 Item 002

attach with: 2 nut NAS1726-3E Item 003 2 spacer D2557215020200 Item 008 2 screw NAS1153-23 Item 010 2 screw NAS1153-25 Item 014 (al) Install the pins on the YZ-Guides. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 428 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Kit 281118D45R00 Refer to Drawing(s): D25572631032 Sheet(s) 37 1 Install as shown on Detail A-A:

8 pin MS24665-134 Item 010 (am) Install the placards. Refer to Kit 281118D46R01 Refer to Drawing(s) : D25572631036 Sheet(s) 41 1 Install as shown on Detail A-A : 1 placard A2557144422000 Item 011 1 placard D2557294923000 Item 030 1 placard D2557294923800 Item 038 1 placard D2557295122600 Item 026 1 placard D2557295134800 Item 184 (an) Replace the cable harness. Refer to Kit 281118D87R00 Refer to Drawing(s): D92895832002 Sheet(s) 2 thru 19 D92992294044 Sheet(s) 23 and 24 1 Install and connect the cable harness: Refer to Drawing(s): D92992294044 Sheet(s) 23 and 24 1 harness D9299229404400 Item 000 (ao) Remove and discard the attachment parts of the cable harness in the cabin floor crossbeam area at FR42 and between FR49 and FR55. Refer to Drawing(s): D92891803006 Sheet(s) 40 thru 54 1 Remove and discard the attachment parts of the cable harness at FR42 and between FR49 and FR55 2 Remove and discard this item, as shown on Sheet 42: 1 strap D9249107100000 Item (835) discard (ap) Attach the cable harnesses in the cabin floor crossbeam area at FR42 and between FR49 and FR55. Refer to Kit 281118D93R00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 429 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s): D92891803006 Sheet(s) 40 thru 54 1 Attach the cable harnesses at FR42 and between FR49 and FR55.

a Attach with these items: 14 screw NAS1096-2-7 Item 004 10 screw NAS1096-2-9 Item 005

5 screw NAS1096-2-12 Item 007 5 screw NAS1096-2-19 Item 012 2 screw NAS1096-2-22 Item 014 1 screw NAS1096-2-36 Item 020 92 screw NAS1096-3-9 Item 030 16 screw NAS1100-04-5 Item 051 12 screw NAS1102-08-8 Item 058 32 screw NAS1102-3-9 Item 099 16 washer NAS1149CN416R Item 150 38 washer NAS1149CN816R Item 152 136 washer NAS1149C0332R Item 153

28 washer NAS1149D363K Item 161

4 washer ASNA0113-40ADL Item 163 8 washer NSA935808C01 Item 171 2 washer D9249102520000 Item 190 16 nut MS21042-04 Item 200

2 nut MS21042-08 Item 202 4 nut MS21042-3 Item 203 28 nut MS21042L3 Item 210 27 nut NAS1291C3M Item 218

1 nut NSA5110-08-1 Item 225 3 nut NSA5066-08-1 Item 230 18 nut NSA5567-08-1 Item 236

4 mount E0343-01 Item 250 7 mount NSA935504-01 Item 251 1 mount NSA935504-02 Item 252 2 mount NSA935513-01 Item 256 10 mount NSA935513-05 Item 257

1 mount NSA935513-07 Item 259 7 bracket ABS0355-01 Item 262 11 bracket ABS0355-02 Item 263 11 washer NSA935514-03 Item 264

1 mount E0660-01 Item 266 20 support ABS0731A01 Item 267

7 bracket ABS0774A01A Item 268 1 spacer NSA5527-03-02 Item 302 4 spacer NSA5527-03-04 Item 306 1 spacer NSA5527-03-06 Item 310 5 spacer NSA5527-03-08 Item 314 1 spacer NSA5527-03-11 Item 320 1 clamp MS21919WCH6 Item 352 6 clamp NSA935807-09 Item 377 2 clamp NSA935807-16 Item 381 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 430 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 circle D9249101020000 Item 668 1 circle D9249101020200 Item 669 2 sheet D9249104800000 Item 727 1 sheet D9249104800400 Item 729 3 cover D2557016200000 Item 734 2.72 ME conduit TSTMNR502-0 Item 763

16 fitting NSA934710T14 Item 774 45 bobbin NSA935510-02 Item 777 15 spring NSA934710E20 Item 783

1 spring NSA934710E23 Item 784 1 ME spring NSA934710E24 Item 786 200 tie NSA935401-03 Item 793 400 tie NSA935401-04 Item 794 200 tie NSA935401-05 Item 795 1 strap D9249107100600 Item 834 2 ME tape DAN328H25 Item 877 2 cap EN2997KE3C12 Item 930 1 cap EN2997KE3C16 Item 932 2 connector EN2997KE512 Item 933 1 connector EN2997KE516 Item 935 2 bracket D9249104900600 Item 1110 NOTE : Cut the conduit, Item 763, in sixteen pieces. b Install the placards as shown in drawing D92891803006 ’POST’, supplied in: 1 placards D9289180320200 1 placards D9289180320000 NOTE : The placard sets are contained in Kit 281118D69R01. (aq) Install the brackets for the wiring in cabin floor crossbeams at FR42, FR50 and FR54. Refer to Kit 281118D94R00 Refer to Drawing(s): D92492243004 Sheet(s) 22 thru 25 1 Install these items at FR54, as shown Detail B-B24, Section A-A.

a Put these items in position, drill the holes for the rivets and install: 2 nut NSA5066-08-1 Item 230 2 mount A9249187820200 Item 565 with: 4 rivet LN9198-3208BF Item 632 2 Install this item at FR50 as shown in drawing D92492243004, Sheet 23, Detail A-A23, Sections B-B thru E-E.

a Put this item in position, drill the holes for the rivets and install: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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3 bracket D9249104920400 Item 737 with: 6 rivet LN9198-3208BF Item 632 3 Install these items at FR42 as shown in drawing D92492243004, Sheet 25, Detail C25, and Sections A-A and B-B.

a Put these items in position, drill the holes for the rivets and install: 2 nut NSA5066-08-1 Item 230 with: 4 rivet LN9198-3208BF Item 632

b Drill two holes with 5.1 mm (0.201 in.) diameter in the cabin floor crossbeam at FR42. (ar) Replace the screwed brackets for the wire routing between FR41 and FR42. Refer to Kit 281118D95R00 Refer to Drawing(s): D92492244002 Sheet(s) 10 1 Remove these items between FR41 and FR42 as shown in drawing D92492244002, Sheet 10, Section A-A.

a Remove and discard these items: 4 screw NAS1096-2-19 Item (012) discard 8 washer NAS1149D0332K Item (157) discard 4 washer NAS1149N816R Item (172) discard 8 washer D9249102520000 Item (180) discard 4 bracket NSA935504-03 Item (253) discard 1 bracket D9249107201200 Item (831) discard 2 Install these items between FR41 and FR42 as shown in drawing D92492244002, Sheet 10, Section B-B.

a Install these items: 7 screw NAS1096-2-12 Item 007 1 screw NAS1096-2-14 Item 009 10 washer ASNA0113-40ADL Item 163

2 washer D9249102520000 Item 190 4 nut MS21042-08 Item 202 4 mount E0660-01 Item 266 1 spacer NSA5527-03-04 Item 306 1 spacer NSA5527-03-07 Item 312 2 guide D9249104720000 Item 724 1 deflector D9249102620600 Item 730 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 432 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 strap D9249107302800 Item 824 (as) Replace the cable harnesses 4605VB, 4655VB, 4656VB, 4661VB, 4662VB, 4663VB, 4664VB, 4670VB, 4671VB, 4672VB, 4673VB, 4680VB, 4681VB, 4683VB, 4692VB, 4693VB, 4694VB and 4696VB. Refer to Kit 281118D96R01 Refer to Drawing(s): D92997056000 Sheet(s) all D92991405000 Sheet(s) 1 D92991455004 Sheet(s) 5 D92991456002 Sheet(s) 3 D92991461013 Sheet(s) 18 D92991462006 Sheet(s) 7 D92991463003 Sheet(s) 8 D92991464002 Sheet(s) 4 D92991470006 Sheet(s) 7 D92991471004 Sheet(s) 6 D92991472010 Sheet(s) 11 D92991473001 Sheet(s) 2 D92991480008 Sheet(s) 9 D92991481001 Sheet(s) 2 D92991483003 Sheet(s) 4 D92991492003 Sheet(s) 4 D92991493001 Sheet(s) 2 D92991494001 Sheet(s) 2 D92991496002 Sheet(s) 3 1 Disconnect and remove the cable harnesses: 1 harness 4605VB D9299140500000 Item (001) discard 1 harness 4655VB D9299145500400 Item (019) discard 1 harness 4656VB D9299145600200 Item (021) discard 1 harness 4661VB D9299146101300 Item (023) discard 1 harness 4662VB D9299146200600 Item (025) discard 1 harness 4663VB D9299146300300 Item (027) discard 1 harness 4664VB D9299146400200 Item (029) discard 1 harness 4670VB D9299147000600 Item (031) discard 1 harness 4671VB D9299147100400 Item (033) discard 1 harness 4672VB D9299147201000 Item (035) discard 1 harness 4673VB D9299147300100 Item (037) discard 1 harness 4680VB D9299148000800 Item (041) discard 1 harness 4681VB D9299148100100 Item (043) discard 1 harness 4683VB D9299148300300 Item (045) discard 1 harness 4692VB D9299149200300 Item (047) discard 1 harness 4693VB D9299149300100 Item (049) discard 1 harness 4694VB D9299149400100 Item (051) discard 1 harness 4696VB D9299149600200 Item (053) discard 2 Modify the cable harnesses.

a Modify the cable harness 4606VB: DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Refer to Drawing(s): D92997026001 Sheet(s) 1 and 2 b Modify the cable harness 4607VB: Refer to Drawing(s): D92997026002 Sheet(s) 3 thru 8

c Modify the cable harness 4628VB: Refer to Drawing(s): D92997026004 Sheet(s) 9 thru 18 d Modify the cable harness 4640VB: Refer to Drawing(s): D92997026005 Sheet(s) 19 and 20

e Modify the cable harness 4644VB: Refer to Drawing(s): D92997026006 Sheet(s) 21 and 22 f Modify the cable harness 4648VB: Refer to Drawing(s): D92997026007 Sheet(s) 23 and 24 g Modify the cable harness 4650VB: Refer to Drawing(s): D92997026008 Sheet(s) 25 and 26 h Modify the cable harness 4675VB: Refer to Drawing(s): D92997026019 Sheet(s) 31 and 32 i Modify the cable harness 5609VB: Refer to Drawing(s): D92997026027 Sheet(s) 33 and 34 j Modify the cable harness 5662VB: Refer to Drawing(s): D92997026028 Sheet(s) 35 and 36 k Modify the cable harness 5663VB: Refer to Drawing(s): D92997026029 Sheet(s) 37 and 38 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 434 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

l Modify the cable harness 5664VB: Refer to Drawing(s): D92997026030 Sheet(s) 39 and 40

m Modify the cable harness 5670VB: Refer to Drawing(s): D92997026031 Sheet(s) 41 and 42

n Modify the cable harness 5675VB: Refer to Drawing(s): D92997026032 Sheet(s) 43 and 44 3 Install and connect the cable harnesses: Refer to Drawing(s): D92991405001 Sheet(s) 2 D92991455005 Sheet(s) 6 D92991456003 Sheet(s) 4 D92997056001 Sheet(s) 1 D92991462007 Sheet(s) 8 D92991463004 Sheet(s) 10 D92991464003 Sheet(s) 5 D92991470008 Sheet(s) 9 D92991471006 Sheet(s) 8 D92991472015 Sheet(s) 12 D92991473002 Sheet(s) 3 D92991480008 Sheet(s) 9 D92991481010 Sheet(s) 11 D92991481002 Sheet(s) 3 D92991483004 Sheet(s) 5 D92991492006 Sheet(s) 7 D92991493002 Sheet(s) 3 D92991494002 Sheet(s) 3 D92991496003 Sheet(s) 3 1 harness 4605VB D9299140500100 Item 002 1 harness 4655VB D9299145500500 Item 020 1 harness 4656VB D9299145600300 Item 022 1 harness 4661VB D9299705600100 Item 024 1 harness 4662VB D9299146200700 Item 026 1 harness 4663VB D9299146300400 Item 028 1 harness 4664VB D9299146400300 Item 030 1 harness 4670VB D9299147000800 Item 032 1 harness 4671VB D9299147100600 Item 034 1 harness 4672VB D9299147201500 Item 036 1 harness 4673VB D9299147300200 Item 038 1 harness 4680VB D9299148001000 Item 042 1 harness 4681VB D9299148100200 Item 044 1 harness 4683VB D9299148300400 Item 046 1 harness 4692VB D9299149200600 Item 048 1 harness 4693VB D9299149300200 Item 050 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 435 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 harness 4694VB D9299149400200 Item 052 1 harness 4696VB D9299149600300 Item 054 (8) Config. 01 ADDITIONAL WORK (introduced by revision 01) If this Service Bulletin has been accomplished before revision 01, it is necessary to do the additional work as described in this paragraph. Aircraft modified per revision 01 or later revisions are not affected by the additional work described in this paragraph. (a) Make sure that the aircraft is electrically grounded, (Refer to AMM 12-34-24, Page block 201). (b) Put the access platform in position. (c) Open the avionics door 811, (Refer to AMM 52-41-00, Page block 201). (d) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION 121VU ACT/RFL/VALVE 33QU 29 L 121VU ACT/XFR VALVE/AUTO CTL 9QH 29 P 121VU ACT LOW LVL R 51QJ 29 M 121VU ACT LOW LVL L 52QJ 28 M 121VU ACT XFR VALVE MAN CTL 30QH 29 N 121VU ACT PUMP SUPPLY 25QH 29 Q (e) Modify the fool proofing of the connector 47QJ-A 281118A11002 Sheet(s) 02 B00 1 Remove : FIN 47QJ 1 Level Sensing Control Unit 30042-0000-0501 Retain

2 Modify the fool proofing : FIN 47QJ-A 1 Connector E0161D01A13X

becomes : FIN 47QJ-A 1 Connector E0161D01A12X 3 Install : FIN 47QJ DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 Level Sensing Control Unit 30042-0000-0501 NOTE : Modify the fool proofing of the equipment in relation to the connector. NOTE : The equipment was retained at removal. (f) Remove the safety clip(s) and tag(s) and close this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION 121VU ACT/RFL/VALVE 33QU 29 L 121VU ACT/XFR VALVE/AUTO CTL 9QH 29 P 121VU ACT LOW LVL R 51QJ 29 M 121VU ACT LOW LVL L 52QJ 28 M 121VU ACT XFR VALVE MAN CTL 30QH 29 N 121VU ACT PUMP SUPPLY 25QH 29 Q (g) Do the functional (BITE) test, (Refer to AMM 28-46-00, Page block 501). NOTE : If the AMM reference is not specified in the last AMM issue of the operator, do the test as written in ACCOMPLISHMENT INSTRUCTIONS paragraph C.(3)(c)3. (h) Make sure that the work areas are clean and clear of tools and other items of equipment. (i) De-energize the aircraft electrical circuits, (Refer to AMM 24-41-00, Page block 201). (j) Close the avionics door 811, (Refer to AMM 52-41-00, Page block 201). (k) Remove the access platform(s). (9) Config. 01 , ADDITIONAL WORK If this Service Bulletin has been accomplished before Revision No. 02, it is necessary to do the additional work as described in this paragraph. Aircraft modified per Revision No. 02 or later revisions are not affected by the additional work described in this paragraph. (a) Make sure that the aircraft is electrically grounded, (Refer to AMM 12-34-24, Page block 201). (b) Put the access platform(s) in position. (c) Do the preparation procedure as specified in the removal/installation of the fuel quantity indicator, multi-tank (6QT), (Refer to AMM 28-42-22, Page block 401). (d) Install the placards on the ACT door Refer to Kit 281118A15R00 281118A15001 Sheet(s) 01 A00 Item 0 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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1 Placard D2821336920000 Item 2 1 Placard D2821336920200 Item 4 1 Placard D2821336920400 Item 6 1 Placard D2821336920600 Item 8 1 Placard D2821336920800 NOTE : Use Zinc Chromate General Purpose (Mat. No. 05-002), Anti-Corrosion Primer (Polyurethane) (Mat. No. 16-001) and Grease High Pressure (Mat. No. 04-004). (e) Replace the fuel quantity indicator 6QT (Refer to AMM 28-42-22, Page block 401) 1 Remove : 1 Fuel Quantity Indicator 1418KID01-03 2 Install : 1 Indicator-Fuel,Quantity 1422KID02-03 3 Remove the access platform(s). 4 Do the close-up procedure as specified in the removal/installation of the fuel quantity indicator, multi-tank (6QT), (Refer to AMM 28-42-22, Page block 401). 5 Do the test after the removal/installation of the fuel quantity indicator, multi-tank (6QT), (Refer to AMM 28-42-22, Page block 401). (10) Config. 02 , ADDITIONAL WORK For aircraft MSN 1137 , if this Service Bulletin has been accomplished before Revision No. 03, it is necessary to do the additional work as described in this paragraph. Aircraft modified per Revision No. 03 or later revisions are not affected by the additional work described in this paragraph. (a) Make sure that the aircraft is electrically grounded, (Refer to AMM 12-34-24, Page block 201). (b) Install the markings on the belly fairing Refer to Kit 281118A18R00 281118A18001 Sheet(s) 01 A00 281118A18001 Sheet(s) 02 A00 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 438 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Clean the surfaces of the placards to which you will apply the adhesive with Solvent General Purpose (Mat. No. 11-026) and Lint-Free Cotton Cloth (Mat. No. 19-003). 2 Install : Item 0 2 Placard D1121004620000

Item 1 2 Placard D1121009120000

Item 2 1 Placard D0041109120000 (c) Make sure that the work areas are clean and clear of tools and other items of equipment. (d) Restore the systems and the aircraft to normal operating condition. (11) Config. 02 ADDITIONAL WORK 1 ADDITIONAL WORK 1 is required by this revision for aircraft modified by issue 00 thru Revision 02. (a) Preparation 1 Make sure that the aircraft is electrically grounded (Refer to AMM 12-34-24, Page block 201). 2 Energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page block 201). 3 Put the access platform(s) in position. 4 Open the AFT cargo compartment door (Refer to AMM 52-30-00, Page block 201). NOTE : Make sure that the applicable safety equipment is installed at the cargo compartment door. (b) Modification Refer to Kit 281118D46R01 Refer to Drawing(s) : D25572631036 Sheet(s) 41 1 Remove as shown on Detail A-A : 1 placard D2557295122400 Item 029 1 placard D2557144422000 Item 030 1 placard D2557295526200 Item 031 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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2 Install Refer to Kit 281118D46R01 1 placard D2557294923000 Item 030 1 placard D2557294923800 Item 038 1 placard D2557295122600 Item 026 1 placard D2557295134800 Item 184 1 placard A2557294928000 Item 011 (c) Test None (d) Close up 1 Make sure that the work areas are clean and clear of tools and other items of equipment. 2 Remove the safety equipment and close the AFT cargo compartment doors (Refer to AMM 52-30-00, Page block 201). 3 Close the AFT cargo compartment doors (Refer to AMM 52-30-00, Page block 201). 4 Remove the access platform(s). 5 De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page block 201). (12) Config. 02 ADDITIONAL WORK 2 ADDITIONAL WORK 2 is required by this revision for aircraft modified by issue 00 thru Revision 02. (a) Preparation 1 Make sure that the aircraft is electrically grounded (Refer to AMM 12-34-24, Page block 201). 2 Energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page block 201). 3 Put the access platform(s) in position. 4 Open the AFT cargo compartment door (Refer to AMM 52-30-00, Page block 201). NOTE : Make sure that the applicable safety equipment is installed at the cargo compartment door. (b) Modification Refer to Kit 281118D41R01

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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Refer to Drawing(s) : D25572631024 Sheet(s) 25 1 Remove these temporarily installed items :

2 plate Item (024) discard

and the attachments parts. 2 Put in position and install at FR52 on the roller track, Item 30, as shown on Detail T23-25 : Refer to Kit 281118D41R01 2 plate D2557263120400 Item 024

with : 28 nut MS21042-3 Item 042 28 screw NAS1153-3 Item 043 (c) Test None (d) Close up 1 Make sure that the work areas are clean and clear of tools and other items of equipment. 2 Remove the safety equipments and close the AFT cargo compartment door (Refer to AMM 52-30-00, Page block 201). 3 Close the AFT cargo compartment door (Refer to AMM 52-30-00, Page block 201). 4 Remove the access platform(s). 5 De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page block 201). **C. T E** **S T**  (1) Config. 01 thru Config. 02 (a) Job Set-up 1 Connect the battery connectors

a For the job set-up, refer to the removal/installation of the batteries (Refer to AMM 24-38-51, Page block 401). DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

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b Remove the blanking caps from the electrical connectors.

c Make sure that the electrical connectors are clean and in a correct condition. d Connect the connectors to the battery.

e Turn the knurled nut a quarter turn. 2 Remove all the warning notices. 3 Energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page block 201). (b) Preliminary tests NOTE : If the aircraft is operated is CAT3 conditions, you must also do the LAND CAT3 capability test (Refer to AMM 22-97-00, Page block 501). 1 On each connector that you disconnected, do the checks as specified in ESPM 20-52-10. NOTE : The functional and/or operational test(s) given in this ESPM procedure is (are) specified below. 2 Do the operational test of the instrument and panel integral lighting (Refer to AMM 33-13-00, Page block 501) 3 Do the operational test of the annunciator light test system in the cockpit (Refer to AMM 33-14-00, Page block 501). 4 Do the operational test of the avionics equipment ventilation system (Refer to AMM 21-26-00, Page block 501). 5 Do the operational test of the AFS (Refer to AMM 22-96-00, Page block 501). 6 Do the operational test of the EIS (Refer to AMM 31-60-00, Page block 501). 7 Do the operational test of the ECAM control panel (Refer to AMM 31-50-00, Page block 501). 8 Do the ground scanning of the central warning system (Refer to AMM 31-50-00, Page block 501). (c) Tests after the removal/installation of the items of equipment 1 Do the test after the removal/installation of the Fuel Quantity Indicating Computer (FQIC) (3QT) (Refer to AMM 28-42-22, Page block 401). 2 Do the BITE test of the landing gear (Refer to AMM 32-69-00, Page block 501). 3 Do the operational test of the circuit breaker monitoring system (Refer to AMM 31-30-00, Page block 501). (d) Tests DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 442 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Test after the disconnection/connection of the connectors 13VC, 43VC, 112VC, 219VC, 221VC, 222VC, 223VC, 224VC, 226VC, 227VC, 228VC, 230VC, 231VC, 232VC, 240VC, 278VC, 282VC, 283VC, 1945VC and 1990VC

a Do the BITE test of the landing gear (Refer to AMM 32-69-00, Page block 501). 2 Tests after the disconnection/connection of the connector 202VC

a Do the test after the removal/installation of the refuel valve 7QU (8QU) (Refer to AMM 28-25-51, Page block 401). b Do the test after the removal/installation of the refuel valve 10QU (Refer to AMM 28-25-51, Page block 401).

c Do the functional (BITE) test (Refer to AMM 28-46-00, Page block 501). NOTE : If AMM reference is not specified in the last AMM issue of the operator, do this test: - Job set-up

. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR:- THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE RELATED DOORS - COMPONENTS THAT MOVE. WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING : OBEY THE FUEL SAFETY PROCEDURES. . Put the safety barriers in position. . You must obey the fuel safety procedures when you do work on the fuel system (Refer to AMM 28-00-00, Page block 301). . If it is necessary to do a test of the high-level sensors 17QJ1 (17QJ2), 20QJ and the dummy load sensor 6QJ: . Open the access door 192MB to energize the refuel/defuel control panel. NOTE : Do not keep the door open longer than necessary because the battery can discharge.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 443 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

. If it is necessary to do a test of the center tank low-level sensors 21QJ and 22QJ, refuel the center tank to a minimum 650 kg (1440 lb) (Refer to AMM 12-11-28, Page block 301). - Procedure

. BITE test NOTE : The subsequent results are only available after two minutes from the time that you energized the Fuel Quantity Indication Computer (FQIC). ACTION RESULT 1. On the MCDU, get access to the FUEL page (Refer to AMM 31-32-00, Page Block 201). The MCDU shows the FUEL menu.
2. Push (in) the line key adjacent to the <COMMAND FLSS BITE indication. The MCDU first shows: FLSS BITE RESULTS AVAILABLE WITHIN 150s In 150 seconds or less, the MCDU shows: Refer to Table 1 for FLSS COMMAND BITE results. 3. Push (in) the line key adjacent to the <RETURN indication. The MCDU shows the FUEL menu. 4. Push (in) the <RETURN line key frequently until the CFDS menu page is shown.

CH1 FLSS STATUS FUEL LFT CTR R SURGE P - P HI LEVEL P P* P LO LEVEL 1 F P* F LO LEVEL 2 P* - P LOGIC P - P U/FULL A P* - P U/FULL B&C P - P * = PREVIOUS RESULTS Table 1 FLSS COMMAND BITE Results Displayed
DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 444 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

NOTE : The letter P shows that all sensors in that group are serviceable. NOTE : The letter F shows that one or more sensor(s) in that group are unserviceable. NOTE : Where an asterisk (*) is shown, the results from the last related BITE test are given. - Close-up

. Make sure that the work area is clean and clear of tool(s) and other items. . If necessary, close the access door 192MB. . Remove the safety barriers. 3 Test after the disconnection/connection of the connectors 204VC, 206VC, 216VC, 274VC, 296VC and 1142VC

a Do the operational check of the GAPCU via CFDS (Refer to AMM 24-41-00, Page block 501). 4 Test after the disconnection/connection of the connectors 208VC, 218VC, 220VC, 1918VC, 1972VC and 1973VC

a Do the functional (BITE) test (Refer to AMM 28-46-00, Page block 501) NOTE : If the AMM reference is not specified in the last AMM issue of the operator, do the test as written in ACCOMPLISHMENT INSTRUCTIONS paragraph C.(3)(c)3. 5 Test after the disconnection/connection of the connectors 210VC, 214VC, 235VC, 292VC, 294VC, 1970VC

a Do the status report (BITE) (Refer to AMM 28-42-00, Page block 501). 6 Test after the disconnection/connection of the connector 212VC

a Do the status report (BITE) (Refer to AMM 28-42-00, Page block 501). 7 Do the functional (BITE) test (Refer to AMM 28-46-00, Page block 501) NOTE : If the AMM reference is not specified in the last AMM issue of the operator, do the test as written in ACCOMPLISHMENT INSTRUCTIONS paragraph C.(3)(c)3. 8 Test after the disconnection/connection of the connectors 215VC, 217VC, 229VC, 239VC and 286VC

a Do the operational test of the Spoiler Elevator Computer 3 (SEC 3) (Refer to AMM 27-94-00, Page block 501). DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 445 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

9 Test after the disconnection/connection of the connector 225VC

a Do the operational test of the main fuel pump system to ensure both center tank pumps feed for 2 mn after engine start (Refer to AMM 28-21-00, Page block 501). 1 0 Test after the disconnection/connection of the connectors 234VC and 236VC

a Do the BITE test of the BSCU (Refer to AMM 32-46-00, Page block 501). 1 1 Test after the disconnection/connection of the connectors 237VC and 288VC

a Do the operational test of the Elevator and Aileron Computers (ELACs) (Refer to AMM 27-93-00, Page block 501). 1 2 Test after the disconnection/connection of the connectors 276VC, 1270VC and 1982VC

a No test. 1 3 Test after the disconnection/connection of the connector 280VC

a Do the operational test of the AFT cargo compartment heating system (Refer to AMM 21-43-00, Page block 501). 1 4 Test after the disconnection/connection of the connector 284VC

a Do the operational test of the lavatory smoke-detection system (Refer to AMM 26-17-00, Page block 501). 1 5 Test after the disconnection/connection of the connectors 1152VC, 1916VC, 2212VC and 2216VC

a Do the operational test of the engine fire and overheat detection (loop/squib) (Refer to AMM 26-12-00, Page block 501). 1 6 Test after the disconnection/connection of the connector 1266VC

a Do the operational test of the wing-tank fuel control (Refer to AMM 28-21-00, Page block 501). 1 7 Test after the disconnection/connection of the connector 1270VC

a Make sure that circuit breaker 1KT is closed, and do a voltage check at pin C of terminal block 7502VT, connector 2, to make sure that there is 115VAC voltage. 1 8 Test after the disconnection/connection of the connector 1947VC

a Do the operational test of the emergency ram-air inlet (Refer to AMM 21-55-00, Page block 501). 1 9 Test after the disconnection/connection of the connector 2200VC DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 446 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Do the operational test of the GPWS ground self-test function (Refer to AMM 34-48-00, Page block 501). 20 Test after the disconnection/connection of the connector 2450VC

a Do the test after the removal/installation of the crossfeed valve actuator 5QE (Refer to AMM 28-23-51, Page block 401). 2 1 Test after the disconnection/connection of the connector 2451VC

a Do the operational test of the electric pump of the Blue hydraulic system (Refer to AMM 29-12-00, Page block 501). 22 Test after the disconnection/connection of the connector 2452VC

a Do the operational test of the manual deployment and the retraction of the ram air turbine (Refer to AMM 29-22-00, Page block 501). (e) Make sure that the work areas are clean and clear of tools and other items of equipment. (f) Connect the connectors to the batteries (2PB1, 2PB2) (Refer to AMM 24-38-51, Page block 401). (g) Energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page block 201). (h) Do a leak test of the ACT shroud system and the drain lines (Refer to Appendix 1). (i) Do the tests of the cabin pressure control and monitoring system (Refer to AMM 21-31-00, Page block 501). (j) Do the tests of the cockpit and cabin temperature control system (Refer to AMM 21-63-00, Page block 501. (k) Do the tests after the removal/installation of the FAC (1CC1, 1CC2) (Refer to AMM 22-66-34, Page block 401). (l) Do the operational test of the VHF system (Refer to AMM 23-12-00, Page block 501. (m) Do the tests of the service interphone system (Refer to AMM 23-44-00, Page block 501). (n) Do the tests of the cockpit voice recorder (Refer to AMM 23-71-00, Page block 501). (o) Do the tests after the removal/installation of the AC current transformer (42XS) (Refer to AMM 24-23-17, Page block 401. (p) Do the tests after the removal/installation of the generator control unit (1XS) (Refer to AMM 24-23-34, Page block 401). (q) Do the tests after the removal/installation of the APU generator (8XS) (Refer to AMM 24-23-51, Page block 401). DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 447 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(r) Do the tests after the removal/installation of the AC auxiliary generator contactor (3XS) (Refer to AMM 24-23-55, Page block 401). (s) Do the tests of the emergency generation system (Refer to AMM 24-24-00, Page block 501). (t) Do the operational test after the removal/installation of the cargo loading control box (Refer to AMM 25-52-69, Page block 401). (u) Do the test after the removal/installation from the flexible control assembly of the offwing escape slides (Refer to AMM 25-62-43, Page block 401). (v) Do the test after the removal/installation of the offwing escape slides reservoirs (Refer to AMM 25-62-46, Page block 401). (w) Do the tests of the engine fire and overheat detection system (Refer to AMM 26-12-00, Page block 501). (x) Do the tests of the APU fire and overheat detection system (Refer to AMM 26-13-00, Page block 501). (y) Do the tests of the engine fire extinguishing system (Refer to AMM 26-21-00, Page block 501). (z) Do the tests of the APU fire extinguishing system (Refer to AMM 26-22-00, Page block 501). (aa) Do the tests of the rudder hydraulic actuation (Refer to AMM 27-24-00, Page block 501). (ab) Do the tests of the elevator hydraulic actuation (Refer to AMM 27-34-00, Page block 501). (ac) Do the tests of the flaps electrical control and monitoring system (Refer to AMM 27-51-00, Page block 501). (ad) Do the tests of the flap system (Refer to AMM 27-54-00, Page block 501). (ae) Do the tests of the slat electrical control and monitoring system (Refer to AMM 27-81-00, Page block 501). (af) Do the tests of the slat system (Refer to AMM 27-84-00, Page block 501). (ag) Do the test after the removal/installation of the pedal position transducer unit (Refer to AMM 27-92-15, Page block 401). (ah) Do the test after the removal/installation of the flight control accelerometer (Refer to AMM 27-92-16, Page block 401). (ai) Do the test of the side stick assembly (Refer to AMM 27-92-41, Page block 501). (aj) Do the test of the ELAC system (Refer to AMM 27-93-00, Page block 501). DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 448 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(ak) Do the test of the SEC system (Refer to AMM 27-94-00, Page block 501). (al) Do the test of the flight control pressure switches (10CE1,10CE2,10CE3) (Refer to AMM 27-96-00, Page block 501). (am) Do the test of the FCDC system (Refer to AMM 27-96-00, Page block 501). (an) Do the tests of the intercell transfer system (Refer to AMM 28-15-00, Page block 501). (ao) Do the tests of the main fuel pump system (Refer to AMM 28-21-00, Page block 501). (ap) Do the tests of the APU fuel pump system (Refer to AMM 28-22-00, Page block 501. (aq) Do the tests of the fuel crossfeed system (Refer to AMM 28-23-00, Page block 501). (ar) Do the tests of the engine LP fuel shut off system (Refer to AMM 28-24-00, Page block 501). (as) Do the tests of the fuel refuel/defuel system (Refer to AMM 28-25-00, Page block 501). (at) Do the tests of the additional center tank transfer system (Refer to AMM 28-28-00, Page block 501). (au) Do the tests of the APU LP fuel shut off system (Refer to AMM 28-29-00, Page block 501). (av) Do the tests of the fuel quantity indicating system (Refer to AMM 28-42-00, Page block 501). (aw) Do the tests of the fuel tank level sensing system (Refer to AMM 28-46-00, Page block 501). (ax) Do the tests of the green main hydraulic power system (Refer to AMM 29-11-00, Page block 501). (ay) Do the tests after the removal/installation of the green hydraulic reservoir (Refer to AMM 29-11-41, Page block 401). (az) Do the tests of the blue main hydraulic power system (Refer to AMM 29-12-00, Page block 501). (ba) Do the tests of the yellow main hydraulic power system (Refer to AMM 29-13-00, Page block 501). (bb) Do the tests after the removal/installation of the main HP-manifold (Refer to AMM 29-13-14, Page block 401). (bc) Do the tests after the removal/installation of the solenoid valves (if installed) (Refer to AMM 29-19-51, Page block 401). NOTE : Only necessary if the components are installed. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 449 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(bd) Do the tests of the blue auxiliary hydraulic power system (Refer to AMM 29-22-00, Page block 501). (be) Do the tests of the power transfer unit (PTU) (Refer to AMM 29-23-00, Page block 501). (bf) Do the tests of the yellow auxiliary hydraulic power system (Refer to AMM 29-24-00, Page block 501). (bg) Do the test of the hydraulic fluid quantity indicating system (Refer to AMM 29-31-00, Page block 501). (bh) Do the tests of the hydraulic fluid pressure indicating system (Refer to AMM 29-32-00, Page block 501. (bi) Do the tests after the removal/installation of the temperature transmitters (Refer to AMM 29-33-11, Page block 401). (bj) Do the tests of the hydraulic reservoir pressurization indicating system (Refer to AMM 29-34-00, Page block 501). (bk) Do the tests of the centralized fault display interface system (Refer to AMM 31-32-00, Page block 501). (bl) Do the tests of the digital flight data recording system (Refer to AMM 31-33-00, Page block 501). (bm) Do the tests of the central warning system (Refer to AMM 31-50-00, Page block 501. (bn) Do the tests after the removal/installation of the SDAC (Refer to AMM 31-55-34, Page block 401). (bo) Do the tests of the normal extension/retraction of the landing gear (Refer to AMM 32-31-00, Page block 501). (bp) After the removal/installation of the torque tube assembly and shaft of the MLG, do the functional tests of the free-fall extension system (Refer to AMM 32-33-00, Page block 501). (bq) Do the tests of the normal braking system (Refer to AMM 32-42-00, Page block 501). (br) Do the tests of the alternate braking system with anti-skid (Refer to AMM 32-43-00, Page block 501). (bs) Do the tests of the alternate braking system without anti-skid (Refer to AMM 32-44-00, Page block 501). (bt) Do the tests of the parking brake system (Refer to AMM 32-45-00, Page block 501). (bu) Do the tests of the brake temperature system (Refer to AMM 32-47-00, Page block 501). (bv) Do the tests of the brake cooling system (Refer to AMM 32-48-00, Page block 501). DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 450 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(bw) Do the tests of the nose wheel steering (Refer to AMM 32-51-00, Page block 501). (bx) Do the tests of the service area lighting (Refer to AMM 33-31-00, Page block 501). (by) Do the tests of the wheel well lighting (Refer to AMM 33-37-00, Page block 501). (bz) Do the test of the navigation lights (Refer to AMM 33-41-00, Page block 501). (ca) Do the tests of the landing lights (Refer to AMM 33-42-00, Page block 501). (cb) Do the tests of the anti-collision/strobe lighting (Refer to AMM 33-48-00, Page block 501). (cc) Do the tests of the cabin emergency lighting (Refer to AMM 33-51-00, Page block 501). (cd) Do the tests of the overspeed warnings in the slat/flap and landing gear extended configuration (Refer to AMM 34-13-00, Page block 501). (ce) Do the tests of the oxygen control and indicating system (Refer to AMM 35-23-00, Page block 501). (cf) Do the tests of the engine bleed air supply system (Refer to AMM 36-11-00, Page block 501). (cg) Do the tests of the APU bleed air supply and crossbleed system (Refer to AMM 36-12-00, Page block 501). (ch) Do the tests after the removal/installation of the APU electronic control box (59KD) (Refer to AMM 49-61-34, Page block 401). (ci) Do the tests of the APU emergency shutdown circuit (Refer to AMM 49-62-00, Page block 501). (cj) Do the tests of the cargo compartment door electrical control system (Refer to AMM 52-35-00, Page block 501). (ck) Do the tests of the engine interface unit (Refer to AMM 73-25-34, Page block 501). (cl) Do the tests of the engine ignition system (Refer to AMM 74-00-00, Page block 501). (cm) Do the tests of the thrust reverser control and indicating system (Refer to AMM 78-31-00, Page block 501). **D. C L** **O S**  **E U**  **P** (1) Config. 01 thru Config. 02 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) De-energize the aircraft electrical circuits, refer to AMM 24-41-00, Page block 201. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 451 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(c) Install the outlet PN D2821302620000 (Refer to IPC 28-12-05). (d) Do the close-up procedure as specified in the removal/installation of the galley unit (6475MM) (Refer to AMM 25-31-41, Page block 401). (e) Do the close-up procedure as specified in the removal/installation of the indicator - fuel quantity, multi tank 6QT (Refer to AMM 28-42-22, Page block 401). (f) In the forward cargo compartment, install the panels 131AC, 131AW, 131BW, 131CW, 131DW, 132AW, 131HC, 131LC, 131MC, 131BC and 131CC (Refer to AMM 06-41-53, Page block 1). (g) In the cockpit, install the lining panels 211HC, 212FC, 212KC, 212KW, 212JW and 212HW (Refer to AMM 06-41-53, Page block 1 and AMM 25-13-41, Page block 401). (h) Install the belly fairing panels 147FB, 148FB, 197BB, 197GB, 197LB, 198BB and 198GB, refer to AMM 53-35-11, Page block 401. (i) Install the aft galley unit, refer to AMM 25-33-41, Page block 401. (j) Install: - the passenger compartment floor panels, refer to AMM 53-22-12, Page block 401 and AMM 53-42-12, Page block 401. - the passenger compartment floor covering, refer to AMM 25-28-41, Page block 401. - the insulation blankets, refer to AMM 25-80-00, Page block 201. - the overhead stowage compartments in the cabin, refer to AMM 25-24-41, Page block 401. - the upper cabin sidewall panels, refer to AMM 25-23-43, Page block 401. - the lower cabin sidewall panels, refer to AMM 25-23-44, Page block 401. - the cabin ceiling panels, refer to AMM 25-23-41, Page block 401. - the cabin cove light panels, refer to AMM 25-23-48, Page block 401. - the passenger compartment seats between FR36 and FR54, refer to AMM 25-21-41, Page block 001. - the FWD cargo compartment ceiling panel, refer to AMM 25-54-12, Page block 401. - the FWD cargo compartment sidewall panel, refer to AMM 25-54-12, Page block 401. - the FWD cargo compartment floor panel, refer to AMM 53-22-14, Page block 401.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 452 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

- the AFT cargo compartment sidewall panels and the modified sidewall panel 152DW, refer to AMM 25-55-11, Page block 401. (k) Remove the safety equipment and close the main landing gear doors, refer to AMM 32-12-00, Page block 201. (l) Remove the safety equipments and close the FWD/ AFT cargo compartment doors, refer to AMM 52-30-00, Page block 201. (m) Depressurize the Green, Blue and Yellow hydraulic system, refer to AMM 29-10-00, Page block 201. (n) Close the accessory compartment door 312AR, refer to AMM 52-41-16, Page block 201. (o) Close the maintenance door 314AR, refer to AMM 52-41-23, Page block 201. (p) Close the APU doors 315AL and 316AR, refer to AMM 52-41-00, Page block 201. (q) Close the avionics door 822 (Refer to AMM 52-41-00, Page block 201). (r) Close the passenger/crew door 841, refer to AMM 52-10-00, Page block 001. (s) Remove the access platform(s). (t) Close the MLG doors (Refer to AMM 32-12-00, Page block 201). (u) Disconnect the aircraft electrical ground-connection (Refer to AMM 12-34-24, Page block 201). (v) Restore the systems and the aircraft to normal operating condition. **E. D O** **C U**  **M E**  **N T**  **A**

**T I**  **O N**  Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 453 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 1, Sheet 1 Config. 01 thru 02: Hookup Chart 1 (Kit D01) DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 454 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 2, Sheet 1 Config. 01 thru 02: Hookup Chart 2 (Kit D01) DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 455 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 3, Sheet 1 Config. 01: Hookup Chart 3 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 456 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 4, Sheet 1 Config. 01: Hookup Chart 4 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 457 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 5, Sheet 1 Config. 01: Hookup Chart 5 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 458 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 6, Sheet 1 Config. 01: Hookup Chart 6 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 459 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 7, Sheet 1 Config. 01: Hookup Chart 7 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 460 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 8, Sheet 1 Config. 01: Hookup Chart 8 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 461 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 9, Sheet 1 Config. 01: Hookup Chart 9 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 462 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 10, Sheet 1 Config. 01: Hookup Chart 10 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 463 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 11, Sheet 1 Config. 01: Hookup Chart 11 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 464 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 12, Sheet 1 Config. 01: Hookup Chart 12 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 465 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 13, Sheet 1 Config. 01: Hookup Chart 13 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 466 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 14, Sheet 1 Config. 01: Hookup Chart 14 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 467 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 15, Sheet 1 Config. 01: Hookup Chart 15 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 468 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 16, Sheet 1 Config. 01: Hookup Chart 16 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 469 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 17, Sheet 1 Config. 01: Hookup Chart 17 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 470 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 18, Sheet 1 Config. 01: Hookup Chart 18 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 471 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 19, Sheet 1 Config. 01: Hookup Chart 19 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 472 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 20, Sheet 1 Config. 01: Hookup Chart 20 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 473 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 21, Sheet 1 Config. 01: Hookup Chart 21 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 474 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 22, Sheet 1 Config. 01: Hookup Chart 22 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 475 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 23, Sheet 1 Config. 01: Hookup Chart 23 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 476 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 24, Sheet 1 Config. 01: Hookup Chart 24 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 477 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 25, Sheet 1 Config. 01: Hookup Chart 25 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 478 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 26, Sheet 1 Config. 01: Hookup Chart 26 (Kit D74)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 479 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 27, Sheet 1 Config. 01 thru 02: Hookup Chart 27 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 480 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 28, Sheet 1 Config. 01 thru 02: Hookup Chart 28 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 481 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 29, Sheet 1 Config. 01 thru 02: Hookup Chart 29 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 482 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 30, Sheet 1 Config. 01 thru 02: Hookup Chart 30 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 483 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 31, Sheet 1 Config. 01 thru 02: Hookup Chart 31 (Kit D84) DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 484 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 32, Sheet 1 Config. 01 thru 02: Hookup Chart 32 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 485 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 33, Sheet 1 Config. 01 thru 02: Hookup Chart 33 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 486 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 34, Sheet 1 Config. 01 thru 02: Hookup Chart 34 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 487 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 35, Sheet 1 Config. 01 thru 02: Hookup Chart 35 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 488 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 35, Sheet 2 Config. 01 thru 02: Hookup Chart 35 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 489 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 36, Sheet 1 Config. 01 thru 02: Hookup Chart 36 (Kit D84) DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 490 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 36, Sheet 2 Config. 01 thru 02: Hookup Chart 36 (Kit D84) DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 491 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 37, Sheet 1 Config. 01 thru 02: Hookup Chart 37 (Kit D84) DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 492 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 38, Sheet 1 Config. 01 thru 02: Hookup Chart 38 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 493 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 38, Sheet 2 Config. 01 thru 02: Hookup Chart 38 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 494 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 39, Sheet 1 Config. 01 thru 02: Hookup Chart 39 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 495 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 39, Sheet 2 Config. 01 thru 02: Hookup Chart 39 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 496 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 40, Sheet 1 Config. 01 thru 02: Hookup Chart 40 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 497 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 41, Sheet 1 Config. 01 thru 02: Hookup Chart 41 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 498 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 42, Sheet 1 Config. 01 thru 02: Hookup Chart 42 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 499 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 43, Sheet 1 Config. 01 thru 02: Hookup Chart 43 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 500 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 43, Sheet 2 Config. 01 thru 02: Hookup Chart 43 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 501 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 44, Sheet 1 Config. 01 thru 02: Hookup Chart 44 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 502 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 44, Sheet 2 Config. 01 thru 02: Hookup Chart 44 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 503 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 45, Sheet 1 Config. 01 thru 02: Hookup Chart 45 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 504 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 46, Sheet 1 Config. 01 thru 02: Hookup Chart 46 (Kit D84) DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 505 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 47, Sheet 1 Config. 01 thru 02: Hookup Chart 47 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 506 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 48, Sheet 1 Config. 01 thru 02: Hookup Chart 48 (Kit D84)

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 507 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 49, Sheet 1 Config. 01 thru 02: Hook-up Chart (Kit B05)
DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 508 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

**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 ATA SYSTEM : 28**  **TITLE : FUEL - TANKS - INSTALL ONE ACT PROVISION ON A320 WITH CLS MODIFICATION No. :**  25415P4179, 25696P4347, 25713J1492, 25713K4481, 26138K4772, 27115J1522, 27446P5502, 27447P5503, 28068P5759, 28404K6135, 28507K6195, 28521K6229, 28661J2073, 28817J1973, 30139J2110, 30356P6683, 30373K6720, 31110K7004, 31143K7155, 31642K7282, 31700K7502, 32244K7774, 32261J2241, 33110K8396, 33198K8488, 33492J2482, 33670K6096, 33671K6098, 33672K4980, 34240K9240 1. Leak test of the ACT shroud system and drain lines A. Leak test Refer to Figure 1 **(1) Test Preparation** (a) Obey the fuel safety procedure, refer to AMM 28-00-00, Page block 301. (b) Do the EIS start procedure (Upper ECAM DU and lower ECAM only), refer to AMM 31-60-00, Page block 201. (c) On the ECAM control panel push the FUEL pushbutton switch, on the lower ECAM DU the FUEL page comes into view. (d) Make certain that the indications are normal and show no ACT installed. (e) Remove the safety clip(s) and the tag(s) and close this (these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION 122VU LIGHTING/ANN LT SPLY/XFMR/BUS 1 26LP 04 X 49VU LIGHTING/XFMR/115.5V/ESS BUS 29LP 03 H 122VU LIGHTING/ANN LT SPLY/XFMR/STAT INV 28LP 03 X (f) Operational test of the annunciator light test system. 1 Do an operational test of the annunciator light test system in the cockpit, refer to AMM 33-14-00, Page block 501. NOTE : During the test, make sure that, on panel HYD/FUEL 40VU, the annunciator lights of the ACT indicator push-button switch stay off.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 1 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

(g) In the AFT area of the RH main landing gear bay, disconnect the elbow nut, item (1). Loosen the ACT cavity drain-line nut, item (2), turn the elbow to approximately 180 deg. and tighten the nut again. (h) Connect a Ground Pressure Generator (GPG) to the elbow of the ACT cavity drain-line. (i) Open the ACT transfer valve. 1 Open, safety and tag this circuit breaker: PANEL DESIGNATION FIN LOCATION 121VU ACT PUMP SPLY 25QH 29 Q 2 Open the ACT Transfer Valve 165QM by removing the actuator and move the valve by hand or electrically by closing these circuit breakers: PANEL DESIGNATION FIN LOCATION 121VU ACT XFR VALVE MAN CTL 30QH 29 N 121VU ACT XFR VALVE AUTO CTL 9QH 29 P and on 40VU, pushing the ACT P/B. P/B lights FAULT and FWD must come on. 3 In the LH MLG Bay on the rear side of the center tank, check at the mechanical indicator that the ACT XFR Valve is open. 4 Make sure that the ACT pump is not running. **(2) Leak Test of the ACT shroud system and drain lines.** (a) Test Procedure 1 On the GPG set the air supply maximum pressure to 1,4 bar (20 psi). 2 Introduce air from the GPG into the ACT system drain-line. Increase the pressure to 1,4 bar (20 psi) and retain at this pressure for 15 minutes. 3 The system must not leak. The pressure in the system must not decrease. If a leak is found, a repair must be made and the test procedure done again. (b) Close up 1 Release the pressure from the ACT system drain-line and disconnect the GPG from the ACT cavity drain-line. 2 Loosen the ACT cavity drain-line nut, item (2), turn the elbow to approximately 180 deg. and tighten the nut again. 3 Reconnect the elbow nut, item (1) to the ACT cavity drain-line. 2. Leak test of the ACT provision in the center tank. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 2 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

A. Leak Test NOTE : The test that follows should only be carried out if the aircraft does not have ACT(s) installed and will not have ACT(s) installed before flight. **(1) Test Preparation** (a) Make sure that a fuel bowser with sufficient capacity is available. (b) Connect the fuel bowser to the refuel coupling. **(2) Test Procedure** (a) Operate the leak monitors for the ACT shroud drain and the ACT interspace drain. (b) Operate the high level switch on 800VU, check that all the "high level" lamps illuminate. (c) With all refuel valves shut, put pressure on the refuel gallery via the bowser. The gallery will quickly prime with fuel. Any additional flow, due to system leakage, should not exceed 1 liter/min. (d) Press and hold the "Manual" button on the ACT refuel valve. The ACT refuel/transfer line will quickly prime with fuel. Any additional flow, due to system leakage, should not exceed 1 liter/min. (e) Release the "Manual" button on the ACT refuel valve. (f) On the panel 800VU, select the refuel valve for the center tank to "Open". (g) On the panel 800VU, select "Refuel" on the Mode select switch. (h) Refuel the center tank until it is stopped by the High Level sensors. (i) On the refuel panel 800VU, set all refuel valves to "Norm". (j) Examine the rear spar of the center tank and the top of the center tank for signs of fuel leakage. Pay particular attention to the connections for the ACT vent line, the ACT refuel/transfer line, and the equipment mounted on the LH manhole access door for the center tank. If a leak is found, carry out a repair and do the test procedure again. (k) Operate the leak monitors for the ACT shroud drain and the ACT interspace drain. If fuel comes out of the ACT shroud drain leak-monitor then there is a problem with the pipework of the ACT refuel/transfer line. Carry out a repair and do the test procedure again. **(3) After Test** (a) Retain the aircraft configuration for the next test. 3. Leak test of the ACT pressurization system. A. Leak Test DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 3 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

Refer to Figure 2 Sheet 1 Refer to Figure 3 Sheet 1 Refer to Figure 4 Sheet 1 Refer to Figure 5 Sheet 1 NOTE : The test that follows is to check that the ACT pressurization system does not leak and that the non-return valves in the system operate correctly. The test is to be done once on aircraft fitted with provisions for ACT(s) before the installation of the ACT. **(1) Test Preparation** (a) In the AFT cargo compartment, remove the ceiling access panel 151CC to get access to the test connectors T1 and T2 of the air pressurization system (Refer to AMM 25-55-11, Page block 401). (b) Connect the Test Tool 1 to the test port T1. (c) Connect the Test Tool 2 to the test port T2. (d) Remove the datum pipe guard in the belly fairing and install a blank. (e) Make sure that the connection(s) to the ACT(s) have blanks installed. (f) Close the air shut off valve. **(2) Test Procedure** (a) Introduce air from the GPG and raise the pressure to 1.4 bar (20.0 psi), retain at this pressure for 10 minutes. (b) Isolate the aircraft ACT pressurization system from the GPG. (c) Check that the pressure indicated at T1 remains the same over a ten minute period at 1.4 bar (20.0 psi). Make sure there is no leakage from the pipework between the upstream non-return valve and the air shut-off valve and no reverse leakage through the upstream non-return valve. (d) Check that the pressure indicated at T2 remains at zero. Make sure there is no leakage through the air shut-off valve. (e) Open the air shut-off valve. (f) Increase the pressure to 1.4 bar (20 psi) and check that this pressure is indicated at T1 and T2. (g) Isolate the aircraft ACT pressurization system from the GPG. (h) Check that the pressure indicated at T1 and T2 remains the same over a ten minute period at 1.4 bar (20 psi). Make sure there is no leakage downstream of the air shut-off valve and check the correct opening of the pressure reducing valve and the downstream non-return valve. DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 4 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

(i) Reduce the pressure on the GPG to zero and release any pressure retained in the system at T1. (j) Check that the pressure indicated at T2 remains at 1.4 bar (20 psi). This will show the correct operation of the downstream non-return valve and no reverse leakage through the valve. (k) Bleed air from T2 to reduce pressure to zero. **(3) Acceptable Results** (a) The system must not leak. The pressure in the system must not decrease. If a leak is found, a repair must be made and the test procedure done again. **(4) Close Up** (a) Release the pressure from the ACT pressurization system. (b) Carefully remove the blank from the datum pipe inlet in the belly fairing and replace the guard. (c) Disconnect the test tool 1 from T1. (d) Disconnect the test tool 2 from T2. (e) Close the air shut-off valve. (f) In the AFT cargo compartment, install the ceiling access panel 151CC AMM 25-55-11, Page block 401).

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 5 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

Figure 1, Sheet 1 Leak test of the ACT shroud system and drain lines

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 6 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

Figure 1, Sheet 2 Leak test of the ACT shroud system and drain lines

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 7 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

Figure 2, Sheet 1 Access to the Test Points T1 and T2

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 8 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

Figure 3, Sheet 1 ACT Test Arrangement - Test Tool 1 DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 9 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

Figure 4, Sheet 1 ACT Test Arrangement - Test Tool 2

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 10 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

Figure 5, Sheet 1

ACT Test Box DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 11 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

This Page Intentionally Left Blank

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 12 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN REPORTING SHEET

**TITLE : FUEL - TANKS - INSTALL ONE ACT PROVISION ON A320 WITH CLS MODIFICATION No. :**  25415P4179, 25696P4347, 25713J1492, 25713K4481, 26138K4772, 27115J1522, 27446P5502, 27447P5503, 28068P5759, 28404K6135, 28507K6195, 28521K6229, 28661J2073, 28817J1973, 30139J2110, 30356P6683, 30373K6720, 31110K7004, 31143K7155, 31642K7282, 31700K7502, 32244K7774, 32261J2241, 33110K8396, 33198K8488, 33492J2482, 33670K6096, 33671K6098, 33672K4980, 34240K9240 P l ease co m p l ete th e app rop ri ate ite m (A o r B) : A - SB W I LL B E embodied .................................................................. YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiement:

............................................................................................................................... ..............................................

............................................................................................................................... .............................................. B - SB HAS B E E N embodied on aircraft: ............................................................................................................

............................................................................................................................... ..............................................

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

..............................

............................................................................................................................... ..............................................

............................................................................................................................... .............................................. From Airline: ...................................................................................................................

..................................... Name/Title: ....................................................................................................................

...................................... Signature:..................... Date: ..................................................... I f ope rati o n a l docu m e ntati o n is affected (see Pa rag rap h 1

. K of th is S B) : If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either : Advance data................................................................................... YES/NO Or : Intermediate/Temporary revision ..................................................... YES/NO I m po rtant I nfo rm ati o n : 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. P l ease retu rn th is co m p l eted sh eet to : **AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  Attn: SEDCC1 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 e-mail: sb.reporting@airbus.com Or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 1 of 1 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN REPORTING QUALITY

**TITLE : FUEL - TANKS - INSTALL ONE ACT PROVISION ON A320 WITH CLS MODIFICATION No. :**  25415P4179, 25696P4347, 25713J1492, 25713K4481, 26138K4772, 27115J1522, 27446P5502, 27447P5503, 28068P5759, 28404K6135, 28507K6195, 28521K6229, 28661J2073, 28817J1973, 30139J2110, 30356P6683, 30373K6720, 31110K7004, 31143K7155, 31642K7282, 31700K7502, 32244K7774, 32261J2241, 33110K8396, 33198K8488, 33492J2482, 33670K6096, 33671K6098, 33672K4980, 34240K9240 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 futher 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 Co m m e nts :

Operator : Date: Name/Title : Please return this form to: **AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  Attn: SEMB Service Bulletins Management DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 1 of 1 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN REPORTING QUALITY

FAX: (+33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE : Jun 18/04 SERVICE BULLETIN No. : A320-28-1118

REVISION No. : 03 - May 12/09 Page : 1 of 1 Printed in France © AIRBUS 2008 All rights reserved