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

6 DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : 1 of 3 Printed in FRANCE © AIRBUS, 2007 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 ATA SYSTEM : 28 TITLE : FUEL - TANKS - INSTALL TWO ACT PROVISIONS WITH CLS CONFIGURATION MODIFICATION No. : 25415P4179 25696P4347 25713J1492 25713K4481 26110J1523 26110K4482 26138K4772 27446P5502 27447P5503 27448P5504 27717K5539 28068P5759 28661J2073 28817J1973 30356P6676 30356P7357 30373K6720 31110K7004 31143K7155 31700K7502 31812K7403 32261J2241 33198K8488 33199K8489 33373K8623 33492J2482 34742K9642 34758K9658 36348K10556 36349K10557 36350K10558 36399K6099 This page transmits Revision No. 01 of Service Bulletin No. A320-28-1145. ADDITIONAL WORK No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 01 is issued to add improvements following Defect Reports on aircraft MSN 2403. CHANGES SUMMARY : — MANPOWER . Updated — MATERIAL INFORMATION . Kits A13R00 and D80R00 added. PLANNING INFORMATION : — EFFECTIVITY . 1.A. Kits A13R00 and D80R00 added. — DESCRIPTION . 1.D. Installation of 2928VU added. — MANPOWER

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

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved . 1.G. Updated. — WEIGHT AND BALANCE . 1.H. Kit A13 and D80 added. — REFERENCES . 1.J. Updated. MATERIAL INFORMATION : — Material . 2.A.(1) Sentence and address updated. — LIST OF COMPONENTS . 2.C. Kits A04R02, A06R02, A10R01, D42R03, D47R01, D49R01 and D85R03 updated. Kits A13R00 and D80R00 added. Kit D83R01, Item 266 deleted. — Consumable Materials . 2.D.(1) Mat. No. 08-007B added. ACCOMPLISHMENT INSTRUCTIONS : — MODIFICATION . 3.B.(1) Drawings 281145A00001 Sheet 01 thru Sheet 03 added. . 3.B.(1)(e) Kit A13R00 and related drawing added. Drawings updated. . 3.B.(1)(j) Placard set D9100095114295 becomes D9100095114296. Mat. No. 08-007B added. Drawings updated. . 3.B.(1)(n) Bundle PN D9000095137995 becomes D9000095137996. Drawings updated. . 3.B.(1)(s)6 Drawings updated. . 3.B.(5)(i) NOTE added. . 3.B.(5)(bc) Work step added. . 3.B.(5)(bk) Drawing D92891120000, Sheets 9 and 33 added. . 3.B.(5)(bm)15 NOTE added. — TESTS . 3.C.(1)(d) Test for switching panel 2028VU added. . 3.C.(1)(e) Test of CLS added.

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

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Layout changes due to computerization of this revision are not identified. FILING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS No previous revisions. REVISION SEQUENCE ORIGINAL : Feb 28/06 REVISION No. : 01 — Apr 27/07

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

6 DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : 1 of 8 Printed in FRANCE © AIRBUS, 2007 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft ATA SYSTEM : 28 TITLE : FUEL - TANKS - INSTALL TWO ACT PROVISIONS WITH CLS CONFIGURATION MODIFICATION No. : 25415P4179 25696P4347 25713J1492 25713K4481 26110J1523 26110K4482 26138K4772 27446P5502 27447P5503 27448P5504 27717K5539 28068P5759 28661J2073 28817J1973 30356P6676 30356P7357 30373K6720 31110K7004 31143K7155 31700K7502 31812K7403 32261J2241 33198K8488 33199K8489 33373K8623 33492J2482 34742K9642 34758K9658 36348K10556 36349K10557 36350K10558 36399K6099 REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES 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 two Additional Center Tanks (ACT). This Service Bulletin details the procedures to install systems and the structural provisions for two ACTs to be installed. The accomplishment of this Service Bulletin and the installation of one or two ACTs will give the aircraft an increased operational range due to the increased fuel capacity. The operational/maintenance consequences of this Service Bulletin are covered by the update of the affected publications.

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 NORMAL JACKING Yes VENDOR SB INVOLVED No STRUCTURAL LIFE EXTN No DE-FUELING/VENTILATION Yes KIT PRICE (USD) See SB

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

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 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. EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) : 62X NOTE : This Service Bulletin is written for the operators 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 SC Department 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE CONCURRENT REQUIREMENTS None REFERENCES/REPERCUSSIONS TFU : None OEB : None AOT : None SIL : None LIFE LIMIT : None LINE MAINTENANCE AFFECTED : No OTHERS : None NATURE OF THE WORK AIRCRAFT : Yes MODIFICATION CLASSIFICATION MAJOR 26138K4772 MINOR 25415P4179 25696P4347 25713J1492 25713K4481 26110J1523 26110K4482 27446P5502 27447P5503 27448P5504 27717K5539 28068P5759 28661J2073 28817J1973 30356P6676 30356P7357 30373K6720 31110K7004 31143K7155 31700K7502 31812K7403 32261J2241 33198K8488 33199K8489 33373K8623 33492J2482 34742K9642 34758K9658 36348K10556 36349K10557 36350K10558 36399K6099

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

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved EQUIPMENT : Yes HARD : Yes SOFT : Yes OBRM : No MANPOWER Config. 01 , Kit 281145A01R01 thru Kit 281145A13R00

Config. 01 , Kit 281145B01R00 thru Kit 281145B04R00

Config. 01 , Kit 281145D01R00 thru Kit 281145D86R00

MATERIAL INFORMATION AIRCRAFT DATA Config. 01 Kit 281145A01R01 Plate, brackets, doublers, supports, fittings, loft drawing and related hardware. Kit 281145A02R02 Plates, brackets, rod, supports and related hardware. Kit 281145A03R00 Canister, valves, pump, plate, insert, spring, pin, plug, bulkhead, door, fairing, fittings, leads, actuator, switch and related hardware. Kit 281145A04R02 Valve, sleeves, flange, elbows, strip, tee pieces, leads, union, pipes, restrictors and related hardware. Kit 281145A05R00 Elbows, plate, filter and related hardware. TOTAL MANHOURS 281.50 ELAPSED TIME (HOURS) 161.50

TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 3.00

TOTAL MANHOURS 1978.00 ELAPSED TIME (HOURS) 390.00

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

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Kit 281145A06R02 Bundle, placards, switch, sleeve, connector, shunt, circuit breakers and related hardware. Kit 281145A07R00 and Kit 281145A08R00 Plate. Kit 281145A09R00 Placards. Kit 281145A10R01 Brackets, bundles, modules, connectors, backshells, relays, bases, stud, conduits, mounts, spacer, placards and related hardware. Kit 281145A11R03 Rack, modules, placards, connector, flange, base, retainer, relay and related hardware. Kit 281145A12R00 Control unit. Kit 281145A13R00 Placards. Kit 281145B01R00 Valves, filter, actuator and clamp. Kit 281145B02R00 Panel and relay Kit 281145B03R00 Panels Kit 281145B04R00 Bundle Kit 281145D01R00 Tube, leads and related hardware. Kit 281145D02R00 Tube, strap, elbow and related hardware.

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

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Kit 281145D03R00 Brackets and related hardware. Kit 281145D04R00 Panel, fairing, cover, section, brackets, angle and related hardware. Kit 281145D05R00 Beam, struts, sections, angles, fittings, angles, plates, shims, supports, connections, coupling and related hardware. Kit 281145D06R00 Fittings, plates, sections, angles, shims, support, webs, key, doublers, cover, tubes, plugs, straps, x-beams and related hardware. Kit 281145D07R00 Angles and related hardware. Kit 281145D08R00 Pins and collars. Kit 281145D10R00 Insulation blankets and strips. Kit 281145D11R00 Brackets and related hardware. Kit 281145D13R01 Tubes, flanges, sleeves, brackets, spacer, clamps, springs, leads and related hardware. Kit 281145D14R00 Monitor, tubes, hose, fitting, bracket, elbow, tee pieces, reducer, unions, placards and related hardware. Kit 281145D15R00 Monitor, tubes, hose, elbows, tee pieces, leads, placard and related hardware. Kit 281145D16R01 Tubes, inlet, filter, couplings, hoses, union, placards, elbow, tees, leads, straps and related hardware. Kit 281145D17R00

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

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Brackets, angles and related hardware. Kit 281145D18R00 Beam and related hardware. Kit 281145D19R00 Shield, shim and related hardware. Kit 281145D20R00 Drain tubes and tee piece. Kit 281145D25R00 thru Kit 281145D27R00 Panels. Kit 281145D28R00 Panels and cover. Kit 281145D31R00 Panels and related hardware. Kit 281145D32R00 Cord and tape. Kit 281145D33R00 Panels, plates, spacer and related hardware. Kit 281145D34R00 Sections and cord. Kit 281145D36R00 Sections, brackets, supports, plates and related hardware. Kit 281145D40R01 X-beams, plates, fittings, sections, straps, filler, angles, doublers, cover, tubes, plugs, shims, bushings, rings and related hardware. Kit 281145D41R00 Pins and collars. Kit 281145D42R03 Tracks, doubler, plates, shims, supports, blocks, latches and related hardware.

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

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Kit 281145D43R00 Hardware. Kit 281145D44R01 Shims, plugs and related hardware. Kit 281145D46R00 TDPs and related hardware. Kit 281145D47R01 Sheets, mats, strips, band, tape and related hardware. Kit 281145D48R00 Cable ties. Kit 281145D49R01 Latch, tracks and related hardware. Kit 281145D50R00 Latches. Kit 281145D51R00 Placards strip and foil. Kit 281145D52R00 Nets and stantion. Kit 281145D61R00 Angles, plates, sheets, straps, wall, stiffeners, sections and related hardware. Kit 281145D62R00 and Kit 281145D63R00 Pins and collars. Kit 281145D70R00 Placards and cable ties. Kit 281145D72R00 Placards. Kit 281145D73R00

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

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Harnesses, mounts, placards and related hardware. Kit 281145D74R00 Brackets, tubes, sections, hoses, leads, reservoirs, placards and related hardware. Kit 281145D75R00 Overhead stowage compartments and related hardware. Kit 281145D76R00 Flexible control assemblies, adaptors, sections, angles, bridges, brackets and related hardware. Kit 281145D80R00 Panel, brackets and related hardware. Kit 281145D82R01 Unions, tubes, bracket and related hardware. Kit 281145D83R01 Brackets, sections, deflector, plate, sheet, angle and related hardware. Kit 281145D84R00 Brackets, mounts and related hardware. Kit 281145D85R03 Brackets, mounts, sheets, conduit, connectors, supports, bobbins, guides, receptacles, placards, strap and related hardware. Kit 281145D86R00 Harnesses and electrical equipment APPENDICES Appendix 1 - Leak test of the ACT shroud system and drain lines

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# @ A318/A319/A320/A321
SERVICE BULLETIN

6 DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : 1 of 148 Printed in FRANCE © AIRBUS, 2007 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 ATA SYSTEM : 28 TITLE : FUEL - TANKS - INSTALL TWO ACT PROVISIONS WITH CLS CONFIGURATION MODIFICATION No. : 25415P4179 25696P4347 25713J1492 25713K4481 26110J1523 26110K4482 26138K4772 27446P5502 27447P5503 27448P5504 27717K5539 28068P5759 28661J2073 28817J1973 30356P6676 30356P7357 30373K6720 31110K7004 31143K7155 31700K7502 31812K7403 32261J2241 33198K8488 33199K8489 33373K8623 33492J2482 34742K9642 34758K9658 36348K10556 36349K10557 36350K10558 36399K6099 This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS' prior written consent. 1. PLANNING INFORMATION A. EFFECTIVITY (1) Models 320-232 (2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft MSN : 2403 (b) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason.

# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (c) Effectivity by MSN and Kit/Configuration The kits and configurations applicable to these MSNs are given at the end of this list: 2403 OPERATOR MSN
62X 2403

KIT No. QTY PER A/C CONFIGURATION 281145A01R01 1 01 281145A02R02 1 01 281145A03R00 1 01 281145A04R02 1 01 281145A05R00 1 01 281145A06R02 1 01 281145A07R00 1 01 281145A08R00 1 01 281145A09R00 1 01 281145A10R01 1 01 281145A11R03 1 01 281145A12R00 1 01 281145A13R00 1 01 281145B01R00 1 01 281145B02R00 1 01 281145B03R00 1 01 281145B04R00 1 01 281145D01R00 1 01 281145D02R00 1 01 281145D03R00 1 01 281145D04R00 1 01 281145D05R00 1 01 281145D06R00 1 01 281145D07R00 1 01 281145D08R00 1 01 281145D10R00 1 01 281145D11R00 1 01 281145D13R01 1 01 281145D14R00 1 01

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved

281145D15R00 1 01 281145D16R01 1 01 281145D17R00 1 01 281145D18R00 1 01 281145D19R00 1 01 281145D20R00 1 01 281145D25R00 1 01 281145D26R00 1 01 281145D27R00 1 01 281145D28R00 1 01 281145D31R00 1 01 281145D32R00 1 01 281145D33R00 1 01 281145D34R00 1 01 281145D36R00 1 01 281145D40R01 1 01 281145D41R00 1 01 281145D42R03 1 01 281145D43R00 1 01 281145D44R01 1 01 281145D46R00 1 01 281145D47R01 1 01 281145D48R00 1 01 281145D49R01 1 01 281145D50R00 1 01 281145D51R00 1 01 281145D52R00 1 01 281145D61R00 1 01 281145D62R00 1 01 281145D63R00 1 01 281145D70R00 1 01 281145D72R00 1 01 281145D73R00 1 01 281145D74R00 1 01 281145D75R00 1 01 281145D76R00 1 01 281145D80R00 1 01 KIT No. QTY PER A/C CONFIGURATION

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Config. 01 is valid for all the aircraft given in this Service Bulletin as a standard configuration. (3) Spares Config. 01 Door assy D5713019400200 Pipe assy D2821008001300 Computer SIC5059-11-0207 FQI 1407KID02-03 Fuel Quantity Indicator 1422KID-02-03 Placard D11311364A00 Placard D11311359A00 Integrally lighted plate 002098-05 Front plate D9251092000000 Plate D9251102000000 B. CONCURRENT REQUIREMENTS None C. REASON (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 two Additional Center Tanks (ACT). (2) Objective/Action This Service Bulletin details the procedures to install systems and the structural provisions for two ACTs to be installed. (3) Advantages The accomplishment of this Service Bulletin and the installation of one or two ACTs will give the aircraft an increased operational range due to the increased fuel capacity. 281145D82R01 1 01 281145D83R01 1 01 281145D84R00 1 01 281145D85R03 1 01 281145D86R00 1 01 KIT No. QTY PER A/C CONFIGURATION

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (4) Operational/Maintenance Consequences — This Service Bulletin has an operational impact. Refer to paragraph K, PUBLICATION AFFECTED. — Prior to Service Bulletin embodiment, specific attention has to be paid to existing aircraft structural damage and/or repairs as they may be affected by the Service Bulletin embodiment. Operators must verify that all allowable damage limits and repairs performed (both in accordance with the SRM and outside of the SRM) are still applicable and effective to the new Service Bulletin configuration. There may be a change or additional maintenance requirements, such as temporary limits or additional inspections, that apply in function of the Service Bulletin configuration. — If the post Service Bulletin status is not covered by the SRM and for repairs outside of the SRM, the operator should contact AIRBUS Customer Services Repair Engineering Support (SER1). Repair review will be done by AIRBUS in accordance with the Customer Services Catalogue. D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : (1) Config. 01 (a) Install the doublers on the extrados, in the center tank (b) Install the brackets on the extrados, in the center tank (c) Install the bracket on the rear spar assy, in the center tank (d) Install the brackets on the intrados, in the center tank (e) Install the Additional Center Tank (ACT) door assy on the center tank (f) Replace the Fuel Quantity Indicator (FQI) 6QT (g) Modify the transfer line in the center tank (h) Install the transfer elbow and the air ventilation elbow on the center tank (i) Apply the sealing protection to the center tank (j) Modify the equipment and the wiring in the HYD/Fuel Panel 40VU (k) Modify the equipment and the wiring in the Rear C/B Panel 121VU and the Rear Panel 120VU (l) Modify the routing in the avionics compartment

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (m) Modify the equipment in the FWD cargo compartment (n) Modify the wiring in the avionics compartment and in the FWD cargo compartment (o) Modify the wiring between the avionics compartment and the cockpit (p) Modify the equipment and the wiring in the Relay Box 103VU (q) Modify the equipment and the wiring in the Contactor Box 107VU (r) Modify the equipment and the wiring in the AFT Electronics Rack 80VU (s) Modify the equipment and the wiring in the FWD Electronics Rack 90VU (2) Config. 01 , Kit 281145B01R00 (a) Install the equipment for the ACT pressurization system between FR48 and FR54. (3) Config. 01 , Kit 281145B02R00 (a) Install the relay box in the forward avionics compartment. (4) Config. 01 , Kit 281145B02R00 , Kit 281145B03R00 and Kit 281145B04R00 (a) Remove and discard the refuel/defuel panel mounting assembly in the belly fairing, zone 192. (b) Install additional wiring between zone 192 and 132 (c) Install the new refuel/defuel panel mounting assembly in the belly fairing, zone 192. (5) Config. 01 (a) Remove the inflation reservoirs 7506MM and 7507MM, for the LH and RH offwing escape slides. (b) In the AFT cargo compartment, remove the placards for the inflation reservoir access. (c) Install the MOD/SB placards. (d) In the passenger compartment between FR41 and FR47, install the harnesses 5339VB and 5340VB (e) Between FR45 and FR48 (LH and RH), install the off-wing escape slide reservoirs and associated pressure tubes.

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (f) Replace the Overhead Stowage Compartments (OHSC) between FR43 and FR47 (LH and RH). (g) Relocate the release cables for the LH and RH off-wing escape slides. (h) Do the structural modification for the ACT 1 and ACT 2 provisions in the center fuselage. (i) Do the structural modification for the ACT 1 provisions in the AFT cargo compartment between FR48 and FR53. (j) Do the structural modification for the ACT 2 provisions in the AFT cargo compartment between FR52 and FR54. (k) Install the angles on the webs of the keel beam, between FR42 and FR46 (l) Replace the fasteners at FR48, FR49, FR50 and FR51, between STGR33 and STGR36 (LH). (m) Replace the fasteners at FR52, FR53 and FR54, between STGR33 and STGR36 (LH). (n) Replace the belly fairing panels 197AB and 198GB and do the modification to the attachment structure. (o) Do the modification to the passenger compartment floor structure between FR42 and FR46. (p) Replace the fasteners between FR42 and FR44 (LH). (q) Replace the fasteners between FR42 and FR44 (RH). (r) In the AFT cargo compartment remove the ball mats, the ball strips, the power drive units, the cargo nets and the XZ latch 32. (s) Remove the roller tracks. (t) Remove the servo mechanism and actuator. (u) Remove the entrance guides, the YZ latch assemblies and guide rail. (v) Install the roller tracks and YZ latch assemblies. (w) Install the servo mechanism and actuator. (x) Install the shim plates on the floor framework between FR47 and FR59. (y) Protect the roller tracks for corrosion.

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (z) Attach the cable harnesses to the structure between FR54 and FR54A. (aa) Remove the Tie Down Points for the cargo nets at FR52A, FR53, FR56 and on the roller track at FR50, FR53, FR56 and FR59. (ab) Install the Tie Down Points for the cargo nets at FR52A, FR53, FR56 and on the roller track at FR50, FR53, FR56 and FR59. (ac) Install the ball mats and ball strips between FR52A and FR56. (ad) Install the X-latch, latch rail, guide rails and support rail between FR53 and FR58. (ae) Install the cargo nets in the AFT cargo compartment. (af) Remove the placards on the sidewall panels in the AFT cargo compartment. (ag) Install the placards on the sidewall panels in the AFT cargo compartment. (ah) After the adjustment of the roller tracks remove and retain the XZ latches at FR50 and FR53. (ai) Install the XZ latch 32ACT in the center roller track at FR50 and FR53. (aj) Do the modification to the attachment structure for the AFT cargo-compartment sidewall and partition panels. (ak) In the AFT cargo compartment replace the floor panels 151SF, 152SF, 151TF, 152TF, 151AG, 152AG, 151BG and 152BG. (al) Seal the gaps between the cargo compartment floor-panels 151SF, 152SF, 151TF, 152TF, 151AG, 152AG, 151BG and 152BG. (am) Replace the insulation blankets between FR46 and FR47. (an) In the AFT cargo compartment, replace the ceiling panels 151AC, 151BC and 151GC. (ao) In the AFT cargo compartment, replace the sidewall panels 151CW, 151EW and 151HW. (ap) In the AFT cargo compartment, replace the sidewall panels 152CW and 152DW. (aq) In the AFT cargo compartment at FR47, replace the partition panels 151BW, 151AW and 152BW. (ar) In the passenger compartment, replace the floor panels 241JF, 251BF, 252BF, 252CF, 251GF, 251FF, 252GF and 252HF.

8

# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (as) Seal the gaps between the passenger compartment floor-panels 241JF, 251BF, 252BF, 252CF, 251GF, 251FF, 252GF and 252HF. (at) Install the fuel vent line between FR37 and FR47 and the fuel transfer line between FR41 and FR47. (au) Install the shroud drain system between FR37 and FR48. (av) Install the ACT 1 cavity drain and monitoring system between FR46 and FR50. (aw) Install the ACT 1 pressurization system between FR48 and FR54. (ax) Install the brackets for the fuel drain/vent systems between FR46 and FR54 (ay) Install the ACT 2 cavity drain and monitoring system between FR50 and FR53. (az) Install the ACT 2 pressurization system between FR51 and FR53. (ba) Install the support brackets for the pressurization and cavity drain systems between FR51 and FR53 (bb) Install the beam between FR46 and FR47 (bc) Install the switching panel 2028VU. (bd) Install the cover between FR46 and FR47 at the fuel transfer and vent lines. (be) Replace the fuel drain line between FR42 and FR47. (bf) Do the modification to the support brackets on floor structure in the passenger compartment, between FR41 and FR42 and between FR49 and FR55. (bg) Replace the support bracket at FR42. (bh) Do the modification to the support bracket installation in the AFT cargo compartment between FR47 and FR55 (bi) Do the modification to the support bracket installation between FR46 and FR52 and FR54. (bj) Do the modification to the attachment parts for the cable harnesses at FR42 and in the AFT cargo compartment between FR49 and FR55. (bk) Do the modification to the attachment parts for the cable harnesses at FR42. (bl) Do the modification to the attachment parts for the cable harnesses between FR46 and FR55.

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (bm) Install/modify the cable harnesses between FR33 and FR55. (bn) Do the modification to the routing of the hydraulic tubes between FR46 and FR51. (bo) Do the levelling of the cargo roller tracks. E. COMPLIANCE (1) Classification Optional (2) Accomplishment Timescale In accordance with operators' maintenance schedule. F. APPROVAL Approved under EASA Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator's circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc, and general administration work are also not included. Config. 01 , Kit 281145A01R01 thru Kit 281145A13R00 Get access 72.0 Install the doublers on the extrados 8.0
Install the brackets on the extrados 16.0
Install the brackets on the rear spar 1.5
Install the brackets on the intrados 16.0 Install the ACT door assy 16.0 Replace the FQI 1.0 Modify the transfer line 32.0

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Config. 01 , Kit 281145B01R00 thru Kit 281145B04R00

Config. 01 , Kit 281145D01R00 thru Kit 281145D86R00 Install the transfer elbow 4.0 Install the air ventilation elbow 4.0 Apply the sealing protection 12.0 Modify the 40VU 4.0 Modify the 121VU and 120VU 8.0 Modify the routing 8.0 Install the connectors 1975VC and 1982VC 1.0 Modify wiring in AVNCS and cargo COMPT 16.0 Modify wiring in AVNCS and cockpit 20.0 Modify the 103VU 4.0 Modify the 107VU 4.0 Modify the 80VU 6.0 Modify the 90VU 16.0 Test 5.0 Close-up 7.0 TOTAL MANHOURS 281.5 ELAPSED TIME (HOURS) 161.5

Get access 1.00 Modification 5.50 Close access 1.00 TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 3.00

Get access (including jacking) 55.00 Removal of components 35.00 Modification, Kit D01 4.00 Modification, Kit D02 3.50 Modification, Kit D03 3.50 Modification, Kit D04 15.00 Modification, Kit D05 175.00 Modification, Kit D06 220.00

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Modification, Kit D07 2.00 Modification, Kit D08 17.00 Modification, Kit D10 5.00 Modification, Kit D11 1.00 Modification, Kit D13 12.00 Modification, Kit D14 7.00 Modification, Kit D15 4.00 Modification, Kit D16 3.50 Modification, Kit D17 21.00 Modification, Kit D18 2.00 Modification, Kit D19 0.50 Modification, Kit D20 3.00 Modification, Kit D25 3.00 Modification, Kit D26 2.50 Modification, Kit D27 1.50 Modification, Kit D28 2.00 Modification, Kit D31 18.00 Modification, Kit D32 2.50 Modification, Kit D33 15.00 Modification, Kit D34 2.00 Modification, Kit D36 20.00 Modification, Kit D40 450.00 Modification, Kit D41 19.00 Modification, Kit D42 70.00 Modification, Kit D43 1.50 Modification, Kit D44 10.50 Modification, Kit D46 2.00 Modification, Kit D47 5.00 Modification, Kit D48 0.50 Modification, Kit D49 4.00 Modification, Kit D50 1.00 Modification, Kit D51 8.50 Modification, Kit D52 0.50 Modification, Kit D61 22.00 Modification, Kit D62 8.50 Modification, Kit D63 8.50 Modification, Kit D70 1.50 Modification, Kit D72 1.00

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved H. WEIGHT AND BALANCE Config. 01 , Kit 281145A01R01 thru Kit 281145A13R00 Manufacturers Empty Weight : +18.34 kg (+40.4323 lb) Effect on Balance : +285.64 kgm (+2066.034 lb.ft) Kit 281145B01R00 thru Kit 281145B04R00 Not changed Kit 281145D01R00 Manufacturers Empty Weight : +0.24 kg (+0.5291 lb) Effect on Balance : +5.59 kgm (+40.432 lb.ft) Kit 281145D02R00 Manufacturers Empty Weight : +0.49 kg (+1.0802 lb) Effect on Balance : +11.83 kgm (+85.566 lb.ft) Kit 281145D03R00 Manufacturers Empty Weight : +0.22 kg (+0.4850 lb) Effect on Balance : +5.28 kgm (+38.190 lb.ft) Kit 281145D04R00 Manufacturers Empty Weight : +16.05 kg (+35.3838 lb) Modification, Kit D73 6.00 Modification, Kit D74 18.00 Modification, Kit D75 3.00 Modification, Kit D76 12.00 Modification, Kit D80 2.50 Modification, Kit D82 3.50 Modification, Kit D83 54.00 Modification, Kit D84 5.00 Modification, Kit D85 215.00 Modification, Kit D86 325.00 Test 14.50 Close up 50.00 TOTAL MANHOURS 1978.00 ELAPSED TIME (HOURS) 390.00

13

# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Effect on Balance : +363.53 kgm (+2629.412 lb.ft) Kit 281145D05R00 Manufacturers Empty Weight : +15.20 kg (+33.5099 lb) Effect on Balance : +309.47 kgm (+2238.396 lb.ft) Kit 281145D06R00 Manufacturers Empty Weight : +11.36 kg (+25.0442 lb) Effect on Balance : +281.73 kgm (+2037.753 lb.ft) Kit 281145D07R00 Manufacturers Empty Weight : +0.17 kg (+0.3747 lb) Effect on Balance : +3.04 kgm (+21.988 lb.ft) Kit 281145D08R00 Manufacturers Empty Weight : +0.17 kg (+0.3747 lb) Effect on Balance : +4.19 kgm (+30.306 lb.ft) Kit 281145D10R00 Manufacturers Empty Weight : -0.43 kg (-0.9480 lb) Effect on Balance : -9.33 kgm (-67.484 lb.ft) Kit 281145D11R00 Manufacturers Empty Weight : +0.03 kg (+0.0661 lb) Effect on Balance : +0.47 kgm (+3.399 lb.ft) Kit 281145D13R01 Manufacturers Empty Weight : +23.30 kg (+51.3671 lb) Effect on Balance : +454.35 kgm (+3286.313 lb.ft) Kit 281145D14R00 Manufacturers Empty Weight : +2.00 kg (+4.4092 lb) Effect on Balance : +39.16 kgm (+283.244 lb.ft) Kit 281145D15R00 Manufacturers Empty Weight : +1.15 kg (+2.5352 lb) Effect on Balance : +25.27 kgm (+182.777 lb.ft)

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Kit 281145D16R01 Manufacturers Empty Weight : +7.72 kg (+17.0195 lb) Effect on Balance : +185.74 kgm (+1343.457 lb.ft) Kit 281145D17R00 Manufacturers Empty Weight : +1.21 kg (+2.6675 lb) Effect on Balance : +26.50 kgm (+191.674 lb.ft) Kit 281145D18R00 Manufacturers Empty Weight : +0.49 kg (+1.0802 lb) Effect on Balance : +10.73 kgm (+77.610 lb.ft) Kit 281145D19R00 Manufacturers Empty Weight : +1.02 kg (+2.2486 lb) Effect on Balance : +21.52 kgm (+155.654 lb.ft) Kit 281145D20R00 Manufacturers Empty Weight : +0.28 kg (+0.6172 lb) Effect on Balance : +5.43 kgm (+39.275 lb.ft) Kit 281145D25R00 Manufacturers Empty Weight : +19.10 kg (+42.1078 lb) Effect on Balance : +461.26 kgm (+3336.293 lb.ft) Kit 281145D26R00 Manufacturers Empty Weight : +3.80 kg (+8.3774 lb) Effect on Balance : +92.24 kgm (+667.171 lb.ft) Kit 281145D27R00 Manufacturers Empty Weight : -0.40 kg (-0.8819 lb) Effect on Balance : -9.08 kgm (-65.676 lb.ft) Kit 281145D28R00 Manufacturers Empty Weight : +1.70 kg (+3.7478 lb) Effect on Balance : +36.31 kgm (+262.630 lb.ft) Kit 281145D31R00

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Manufacturers Empty Weight : +9.90 kg (+21.8255 lb) Effect on Balance : +223.74 kgm (+1618.311 lb.ft) Kit 281145D32R00 Manufacturers Empty Weight : +0.16 kg (+0.3527 lb) Effect on Balance : +3.71 kgm (+26.834 lb.ft) Kit 281145D33R00 Manufacturers Empty Weight : +1.50 kg (+3.3069 lb) Effect on Balance : +35.70 kgm (+258.218 lb.ft) Kit 281145D34R00 Manufacturers Empty Weight : +1.70 kg (+3.7478 lb) Effect on Balance : +41.31 kgm (+298.795 lb.ft) Kit 281145D36R00 Manufacturers Empty Weight : +5.40 kg (+11.9048 lb) Effect on Balance : +114.91 kgm (+831.144 lb.ft) Kit 281145D40R01 Manufacturers Empty Weight : +16.75 kg (+36.9270 lb) Effect on Balance : +448.23 kgm (+3242.047 lb.ft) Kit 281145D41R00 Manufacturers Empty Weight : +0.23 kg (+0.5070 lb) Effect on Balance : +5.04 kgm (+36.454 lb.ft) Kit 281145D42R03 Manufacturers Empty Weight : +124.70 kg (+274.9136 lb) Effect on Balance : +2903.02 kgm (+20997.543 lb.ft) Kit 281145D43R00 Manufacturers Empty Weight : +0.03 kg (+0.0661 lb) Effect on Balance : +0.75 kgm (+5.424 lb.ft) Kit 281145D44R01 Manufacturers Empty Weight : +11.70 kg (+25.7938 lb)

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Effect on Balance : +274.25 kgm (+1983.650 lb.ft) Kit 281145D46R00 Manufacturers Empty Weight : +0.29 kg (+0.6393 lb) Effect on Balance : +6.79 kgm (+49.112 lb.ft) Kit 281145D47R01 Manufacturers Empty Weight : +27.14 kg (+59.8328 lb) Effect on Balance : +693.70 kgm (+5017.532 lb.ft) Kit 281145D48R00 Not changed Kit 281145D49R01 Manufacturers Empty Weight : +6.62 kg (+14.5944 lb) Effect on Balance : +176.09 kgm (+1273.658 lb.ft) Kit 281145D50R00 Manufacturers Empty Weight : +9.60 kg (+21.1641 lb) Effect on Balance : +226.94 kgm (+1641.457 lb.ft) Kit 281145D51R00 Manufacturers Empty Weight : +0.47 kg (+1.0361 lb) Effect on Balance : +11.11 kgm (+80.358 lb.ft) Kit 281145D52R00 Manufacturers Empty Weight : +9.80 kg (+21.6050 lb) Effect on Balance : +239.61 kgm (+1733.099 lb.ft) Kit 281145D61R00 Manufacturers Empty Weight : +3.30 kg (+7.2751 lb) Effect on Balance : +62.57 kgm (+452.568 lb.ft) Kit 281145D62R00 Manufacturers Empty Weight : +0.34 kg (+0.7495 lb) Effect on Balance : +6.46 kgm (+46.725 lb.ft) Kit 281145D63R00

17

# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Manufacturers Empty Weight : +0.29 kg (+0.6393 lb) Effect on Balance : +5.49 kgm (+39.709 lb.ft) Kit 281145D70R00 Manufacturers Empty Weight : +0.08 kg (+0.1763 lb) Effect on Balance : +1.85 kgm (+13.381 lb.ft) Kit 281145D72R00 Not changed Kit 281145D73R00 Manufacturers Empty Weight : +0.22 kg (+0.4850 lb) Effect on Balance : +4.20 kgm (+30.378 lb.ft) Kit 281145D74R00 Manufacturers Empty Weight : +20.38 kg (+44.9297 lb) Effect on Balance : +424.51 kgm (+3070.480 lb.ft) Kit 281145D75R00 Manufacturers Empty Weight : +1.20 kg (+2.6455 lb) Effect on Balance : +11.40 kgm (+82.456 lb.ft) Kit 281145D76R00 Manufacturers Empty Weight : -0.51 kg (-1.1244 lb) Effect on Balance : -10.35 kgm (-74.862 lb.ft) Kit 281145D80R00 Manufacturers Empty Weight : +0.850 kg (+1.8739 lb) Effect on Balance : +26.095 kgm (+188.745 lb.ft) Kit 281145D82R01 Manufacturers Empty Weight : +0.27 kg (+0.5952 lb) Effect on Balance : +5.93 kgm (+42.891 lb.ft) Kit 281145D83R01 Manufacturers Empty Weight : +1.00 kg (+2.2046 lb) Effect on Balance : +29.90 kgm (+216.266 lb.ft)

18

# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Kit 281145D84R00 Manufacturers Empty Weight : +0.52 kg (+1.1463 lb) Effect on Balance : +12.22 kgm (+88.387 lb.ft) Kit 281145D85R03 Manufacturers Empty Weight : +0.45 kg (+0.9920 lb) Effect on Balance : +9.67 kgm (+69.943 lb.ft) Kit 281145D86R00 Manufacturers Empty Weight : +5.70 kg (+12.5662 lb) Effect on Balance : +113.43 kgm (+820.439 lb.ft) I. ELECTRICAL LOAD DATA Not changed

19

# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved J. REFERENCES 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 20-28-00 21-26-00 21-31-00 21-43-34 21-51-00 21-63-00 21-63-34 22-66-34 22-96-00 22-97-00 23-12-00 23-44-00 23-71-00 24-23-17 24-23-34 24-23-51 24-23-55 24-24-00 24-38-51 24-41-00 24-41-34 25-13-41 25-21-41 25-23-41 25-23-43 25-23-44 25-23-48 25-24-41 25-28-41 25-52-00 25-52-21 25-52-22 25-52-26 25-52-34 25-52-44 25-52-48 25-52-51 25-52-69 25-54-12 25-54-41 25-55-11 25-55-41 25-62-43 25-62-46 25-80-00 26-12-00 26-13-00 26-17-00 26-17-34 26-21-00 26-22-00 27-24-00 27-34-00 27-51-00 27-51-34 27-54-00 27-81-00 27-84-00 27-92-15 27-92-16 27-92-41 27-93-00 27-94-00 27-94-34 27-96-00 28-00-00 28-10-00 28-15-00 28-21-00 28-22-00 28-23-00 28-24-00 28-25-00 28-25-55 28-28-00 28-29-00 28-42-00 28-42-21 28-42-22 28-42-34 28-46-00 28-46-34 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 31-30-00 31-32-00 31-33-00 31-50-00 31-55-34 31-60-00 32-12-00 32-31-00 32-31-71 32-33-00 32-33-17 32-42-00 32-42-34 32-43-00 32-44-00 32-45-00 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 34-13-00 34-48-00 35-23-00 36-11-00 36-12-00 49-61-34 49-62-00 52-30-00 52-35-00 52-41-00 53-22-14 53-32-12 53-35-13 53-42-12 53-42-14 57-17-11 73-25-34 74-00-00 78-31-00 Consumable Material List (CML)

20

# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Process and Material Specification (PMS) Standards Manual (SM) Common Support Data Dictionary (CSDD) Chapter 2 Top Drawing, Issue C, Sheet 2 D00071141002 Appendix 1 Elec. Std. Practices Manual (ESPM) : 20-25-51 20-33-00 20-33-44 20-44-22 20-44-24 20-44-71 20-52-10 20-52-21 20-55-00 Illustrated Parts Catalog (IPC) : 28-12-05 Structural Repair Manual (SRM) : 51-42-11 51-44-11 51-46-00 51-75-11 51-76-12

DESIGN DRAWINGS SHEET(S) 281145A00001 01 A00 281145A00001 02 A00 281145A00001 03 B00 281145A01001 01 A00 281145A01001 02 A00 281145A01001 03 A00 281145A01002 01 A00 281145A01003 01 A00 281145A01003 02 A00 281145A01003 03 A00 281145A01003 04 A00 281145A01004 01 A00 281145A01004 02 A00 281145A01004 03 A00 281145A01005 01 A00 281145A02001 01 A00 281145A02002 01 A00 281145A02002 02 A00 281145A02002 03 A00 281145A02003 01 A00 281145A02003 02 A00 281145A03000 01 A00 281145A03001 01 A00 281145A03002 01 A00 281145A03002 02 A00 281145A03003 01 B00 281145A03004 01 A00 281145A03005 01 A00

21

# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 281145A03006 01 A00 281145A03007 01 A00 281145A04000 01 A00 281145A04001 01 A00 281145A04001 02 A00 281145A04001 03 A00 281145A04002 01 A00 281145A04002 02 A00 281145A04002 03 A00 281145A04002 04 A00 281145A04003 01 A00 281145A04003 02 A00 281145A04003 03 A00 281145A04003 04 A00 281145A04003 05 A00 281145A04004 01 A00 281145A04005 01 A00 281145A04006 01 A00 281145A04007 01 A00 281145A04008 01 A00 281145A04009 01 A00 281145A04010 01 A00 281145A04011 01 A00 281145A04011 02 A00 281145A04012 01 A00 281145A04013 01 A00 281145A05001 01 A00 281145A05002 01 A00 281145A05003 01 A00 281145A05003 02 A00 281145A06000 01 A00 281145A06001 01 A00 281145A06002 01 A00 281145A06003 01 B00 281145A06004 01 A00 281145A06005 01 A00 281145A06501 01 A00 281145A06501 02 A00 281145A06502 01 A00 281145A06502 02 A00 281145A06503 01 A00 281145A06503 02 A00 281145A06504 01 A00 DESIGN DRAWINGS SHEET(S)

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 281145A06504 02 A00 281145A06505 01 A00 281145A06505 02 A00 281145A06506 01 A00 281145A06506 02 A00 281145A06507 01 A00 281145A06507 02 A00 281145A06508 01 A00 281145A06508 02 A00 281145A06509 01 A00 281145A06509 02 A00 281145A06510 01 A00 281145A06510 02 A00 281145A06511 01 A00 281145A06511 02 A00 281145A10001 01 A00 281145A10001 02 A00 281145A10002 01 A00 281145A10002 02 A00 281145A10003 01 A00 281145A10004 01 A00 281145A10004 02 A00 281145A10005 01 A00 281145A10005 02 A00 281145A10006 01 A00 281145A10006 02 A00 281145A10007 01 A00 281145A10007 02 A00 281145A10008 01 A00 281145A10008 02 A00 281145A10008 03 A00 281145A10009 01 A00 281145A10009 02 A00 281145A10010 01 A00 281145A10501 01 A00 281145A10501 02 A00 281145A10501 03 A00 281145A10501 04 A00 281145A10501 05 A00 281145A10501 06 A00 281145A10501 07 B00 281145A10501 08 A00 281145A10502 01 A00 DESIGN DRAWINGS SHEET(S)

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 281145A10502 02 A00 281145A10502 03 A00 281145A10502 04 A00 281145A10502 05 A00 281145A10502 06 A00 281145A10502 07 B00 281145A10503 01 A00 281145A10503 02 A00 281145A10503 03 A00 281145A10503 04 A00 281145A10503 05 B00 281145A10503 06 A00 281145A10504 01 A00 281145A10504 02 A00 281145A10504 03 A00 281145A10504 04 A00 281145A10504 05 B00 281145A10504 06 A00 281145A10505 01 A00 281145A10505 02 A00 281145A10505 03 A00 281145A10505 04 B00 281145A10505 05 A00 281145A10506 01 A00 281145A10506 02 A00 281145A10506 03 A00 281145A10506 04 A00 281145A10506 05 B00 281145A10506 06 A00 281145A10507 01 A00 281145A10507 02 A00 281145A10507 03 A00 281145A10507 04 B00 281145A10507 05 A00 281145A10508 01 B00 281145A10508 02 A00 281145A10508 03 B00 281145A10509 01 A00 281145A10509 02 A00 281145A10509 03 B00 281145A10510 01 A00 281145A10510 02 A00 281145A10510 03 B00 DESIGN DRAWINGS SHEET(S)

24

# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 281145A10511 01 A00 281145A10511 02 A00 281145A10512 01 A00 281145A10512 02 A00 281145A10513 01 A00 281145A10513 02 A00 281145A10514 01 A00 281145A10514 02 A00 281145A10515 01 A00 281145A10515 02 A00 281145A10516 01 A00 281145A10516 02 A00 281145A10517 01 A00 281145A10517 02 A00 281145A10518 01 A00 281145A10518 02 A00 281145A10519 01 A00 281145A10519 02 A00 281145A10519 03 A00 281145A10519 04 B00 281145A10520 01 A00 281145A10520 02 A00 281145A10521 01 A00 281145A10521 02 A00 281145A10522 01 A00 281145A10522 02 A00 281145A11000 01 B00 281145A11001 01 A00 281145A11002 01 B00 281145A11003 01 A00 281145A11004 01 A00 281145A11004 02 A00 281145A13001 01 A00 D25286364014 7 and 8 D25288767000 1 and 2 D25571073000 1 D25571073002 2 D25571073004 3 D25571073006 4 D25572585000 1, 2, 7 and 23 D25572585002 3 - 5 D25572585004 6 D25572585006 8 - 10 DESIGN DRAWINGS SHEET(S)

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved D25572585012 13 - 22 D25572585014 24 and 25 D25572585016 26 D25572585018 27 D25572585020 30 D25572585022 31 D25572585024 32 and 33 D25572585026 28 and 29 D25572585028 34 and 35 D25572585030 40 D25572585032 38 D25572585034 36 D25572585036 37 D25572585038 39 D25573522000 1 D25573525006 13 - 16 D25670762000 1 - 7 D25671745000 1 - 7 D25671746000 1 - 4 D25690000004 7 - 9 D25870003048 20 D28270515000 1 - 4 D28270972002 7 - 12 D28270973002 6 - 10 D28270974002 4 - 6 D28270975 7 thru 12 D28270975004 8, 10, 11, 13 - 15 D28270982004 12 - 14, 17, 19, 20, 24 - 26 D28270990002 2 and 4 D28270991000 1 - 3 D28270992000 1 - 4 D28270998002 2 D28270999004 3 D53370297002 1 - 7 D53370297003 1 - 7 D53370780004 2 D53371046000 1 - 5 D53371237000 1 D53371237001 1 D53372362006 1, 4 - 9 and 12 - 14 D53470075004 1 - 4, 6 - 17 D53470076004 1 - 10 DESIGN DRAWINGS SHEET(S)

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved D53470095002 1 D53470096002 1 D53475024000 1 - 6 D53675015002 3 and 4 D53675016002 3 and 4 D53675510000 1 - 3 D53675511000 1 - 3 D53975019000 1 - 6 D92355000 1 D92393242000 1 D92450032 6 and 7 D92450115 1 and 2 D92491681000 1 - 6 D92491681002 7 - 9 D92491681006 34 - 45 D92491681008 10, 12 - 24, 26, 27, 46 - 48 D92492261000 1 D92550025 1 D92550032 1 and 2 D92556025 1 and 3 D92891120000 9 and 33 D92891805000 1 - 15 D92891805002 16 - 19 D92891805006 20, 22 - 31, 39 - 43, 45 - 48, 50 - 52 D92894713062 1 D92894736004 14 - 17 D92991405000 1 D92991405001 2 D92991419005 6, H005 D92991419006 5, H006 D92991420005 6, H005 D92991420006 5, H006 D92991428013 18, H013 D92991428014 19, H014 D92991456004 5, H004 D92991456005 4, H005 D92991461021 26, H021 D92991461022 27, H022 D92991462010 10, H010 D92991462011 10, H004 D92991462011 11, H011 DESIGN DRAWINGS SHEET(S)

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved D92991463003 8, H003 D92991464002 4, H002 D92991464003 5, H003 D92991470007 8, H007 D92991470008 9, H008 D92991471005 7, H005 D92991471006 8, H006 D92991472014 15, H014 D92991472016 16, H016 D92991473003 4, H003 D92991473004 3, H004 D92991475006 7, H006 D92991475007 8, H007 D92991480014 15, H014 D92991480015 16, H015 D92991481003 4, H003 D92991481004 5, H004 D92991483007 6, H007 D92991483008 7, H008 D92991492005 6, H005 D92991492006 7, H006 D92991493003 4, H003 D92991493004 3, H004 D92991494003 4, H003 D92991494004 3, H004 D92992293014 16 D92992293016 17 D92997026001 1 and 2 D92997026002 3 - 8 D92997028002 1 and 2 D92997028004 3 and 4 D92997028006 5 and 6 D92997028008 7 and 8 D92997043001 1 - 4 D92997043002 5 and 6 D92997043003 7 and 8 D92997043004 9 - 11 D92997043005 12 and 13 D92997043006 14 and 15 D92997043007 16 - 23 D93070516000 1 - 6 D93070668000 1 - 8 DESIGN DRAWINGS SHEET(S)

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved K. PUBLICATIONS AFFECTED 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) 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) : 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

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 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.com 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. INTERCHANGEABILITY/MIXABILITY

NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. Illustrated Parts Catalog (IPC) : 11-31-31 11-31-34 11-32-25 11-36-25 11-36-28 11-36-53 24-24-03 24-92-02 24-92-03 24-92-04 25-24-09 25-52-04 25-55-04 25-62-04 25-71-01 25-71-11 25-81-04 27-54-03 27-84-03 27-92-03 28-11-04 28-12-03 28-12-04 28-21-03 28-22-03 28-25-03 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 28-28-51 28-28-52 28-28-53 28-42-08 28-42-34 28-46-08 29-12-03 29-12-04 29-22-03 29-22-04 29-23-03 29-32-03 31-14-11 32-31-03 32-43-03 33-13-08 33-37-03 33-51-04 53-16-01 53-35-03 53-36-03 53-42-04 53-46-04 53-49-04 57-11-05 57-16-05 57-17-05 57-17-11 Master Minimum Equipment List (MMEL) Flight Crew Operating Manual (FCOM) : Vol. 1

DESCRIPTION OLD PART No. NEW PART No. INT MIXABILITY FQI 1407KID02-03 1418KID01-03 03 Not applicable

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 2. MATERIAL INFORMATION A. MATERIAL — PRICE AND AVAILABILITY (1) Material The Material Kit is included in the commercial offer of the Letter Agreement, and such as will be supplied by AIRBUS Upgrade Services. To facilitate the Material Kit reception, Airline Customers are requested to send a Customer Purchase Order to : AIRBUS UPGRADE SERVICES Attn FCO manager Vendor parts are to be purchased from : SMITHS AEROSPACE ELECTRONIC SYSTEMS PO BOX 188 GL52 8SF CHELTENHAM UNITED KINGDOM (2) Price and Availability Sales terms must be agreed between the Customers and AIRBUS in accordance with the RFC (or RFC/RMO) procedure. B. INDUSTRY SUPPORT INFORMATION Refer to paragraph 2.A.(2): Price and Availability. C. LIST OF COMPONENTS Kit 281145A01R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5713304820004 Doubler 281145A01001 0 1 D5713031920000 Doubler 281145A01001 1 19 EN6115V3-3 Bolt 281145A01001 10 15 EN6115V3-4 Bolt 281145A01001 11 15 EN6115V3-5 Bolt 281145A01001 12 29 NSA5357-3-6 Pin 281145A01001 13 12 NSA5357-3-7 Pin 281145A01001 14 16 NSA5357-3-5 Pin 281145A01001 15

8 NSA5357-4-7 Pin 281145A01001 22 5 NSA5357-4-8 Pin 281145A01001 23 57 NSA5330-6 Nut 281145A01001 30 49 ASNA2528-3 Nut 281145A01001 35 13 NSA5330-8 Nut 281145A01001 40

1 D5791332400000 Bracket 281145A01002 0 1 D5791332300000 Bracket 281145A01002 1

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service 2 EN6115V3-5 Bolt 281145A01002 10 4 ASNA2528-3 Nut 281145A01002 11 2 EN6115V3-7 Bolt 281145A01002 12 1 D5791049500095 Support 281145A01003 1 1 D5791049400095 Support 281145A01003 2 1 D5791048300095 Fitting 281145A01003 3 1 D5791048200095 Fitting 281145A01003 4 1 D5791042020095 Fitting 281145A01003 5 1 D5791042120095 Fitting 281145A01003 6 1 D5791043020095 Fitting 281145A01003 9 1 D5791049820095 Fitting 281145A01003 10 1 D5791050020095 Fitting 281145A01003 11 1 D5791042320095 Support 281145A01003 12 1 D5791042220095 Support 281145A01003 13 2 A2823301800202 Plate 281145A01003 21 4 ASNA2050DCJ3215 Rivet 281145A01003 22 6 NSA5357-3-5 Pin 281145A01003 100 8 NSA5357-3-7 Pin 281145A01003 102 4 NSA5357-3-8 Pin 281145A01003 103 4 NSA5357-3-10 Pin 281145A01003 104 4 NSA5357-4-7 Pin 281145A01003 107 8 NSA5357-4-8 Pin 281145A01003 108 2 NSA5357-4-9 Pin 281145A01003 109 4 NSA5357-4-10 Pin 281145A01003 110 22 NSA5330-6 Nut 281145A01003 120 18 NSA5330-8 Nut 281145A01003 130

1 D5791041820095 Support 281145A01004 0 2 NSA5357-4-11 Pin 281145A01004 60 2 NSA5357-5-13 Pin 281145A01004 65 2 NSA5330-8 Nut 281145A01004 75 2 NSA5330-10 Nut 281145A01004 80 1 D2821334100300 Rod 281145A01005 0 1 D2821334220000 Bracket 281145A01005 4 4 NAS6603-4 Bolt 281145A01005 12 2 NAS6604-9 Bolt 281145A01005 14 4 NSA5050-3 Nut 281145A01005 20 2 NSA5050-4 Nut 281145A01005 22 4 ASNA2397-10L Washer 281145A01005 24 2 ASNA2397-416L Washer 281145A01005 26 1 D5713032000095 Loft QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145A02R02

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 281145A03R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 A2823301800202 Plate 281145A02001 12 2 ASNA2050DCJ3215 Rivet 281145A02001 32 1 D5791040320095 Bracket 281145A02002 1 1 D5791040500095 Support 281145A02002 2 1 D5791040400095 Support 281145A02002 3 1 D5791040120095 Bracket 281145A02002 4 1 D5791040020295 Bracket 281145A02002 5 1 D5791040220095 Bracket 281145A02002 6 1 D5791040820095 Bracket 281145A02002 7 1 D5791040920095 Bracket 281145A02002 8 1 D5791040620095 Bracket 281145A02002 9 1 D5791040720095 Bracket 281145A02002 10 1 D5791041020095 Bracket 281145A02002 11 4 NAS6603-4 Bolt 281145A02002 44 4 NSA5050-3 Nut 281145A02002 62 8 NSA5357-4-9 Pin 281145A02002 157 5 NSA5357-4-10 Pin 281145A02002 158 17 NSA5357-4-11 Pin 281145A02002 159

1 NSA5357-4-12 Pin 281145A02002 160 1 NSA5357-5-13 Pin 281145A02002 162 31 NSA5330-8 Nut 281145A02002 165

1 NSA5330-10 Nut 281145A02002 170 1 D2821334100400 Rod 281145A02003 2 1 D2821040220000 Bracket 281145A02003 6 1 D2821040120000 Plate 281145A02003 8 8 NAS6603-2 Bolt 281145A02003 10 4 NAS6603-4 Bolt 281145A02003 12 2 NAS6604-9 Bolt 281145A02003 14 4 NSA5050-3 Nut 281145A02003 20 2 NSA5050-4 Nut 281145A02003 22 12 ASNA2397-10L Washer 281145A02003 24

2 ASNA2397-416L Washer 281145A02003 26

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5713334000000 Fairing 281145A03002 0 1 D5713334600000 Fitting 281145A03002 1 1 D5713334500000 Fitting 281145A03002 2 1 D5713334400000 Fitting 281145A03002 3 1 D5713323000000 Door 281145A03002 4 8 A5713052120300 Washer 281145A03002 6 3 NAS6603-2 Bolt 281145A03002 10 15 ABS0114V4-18 Bolt 281145A03002 11

4 ASNA2397D10L Washer 281145A03002 15 15 MS20002C4 Washer 281145A03002 16

1 NAS6603-3 Bolt 281145A03002 20 6 NAS6604-3 Bolt 281145A03002 22 6 ASNA2397D416L Washer 281145A03002 40 1 HTE690045 Switch 281145A03004 0 1 D2821067800000 Bulkhead 281145A03004 8 1 A2823260820000 Plug 281145A03004 10 1 A2823260500000 Valve 281145A03004 12 3 NSA8200-6 O-Ring 281145A03004 18 1 NSA8203-019 O-Ring 281145A03004 20 4 NAS6603-5 Bolt 281145A03004 22 4 ASNA2055-03 Washer 281145A03004 24 4 NSA5050-3 Nut 281145A03004 26 30 cm MS20995C32 Wire 281145A03004 28

1 568-1-27170-002 Pump 281145A03005 0 1 568-1-27171-002 Plate 281145A03005 2 1 A2821064820040 Pin 281145A03005 10 1 A2821064620000 Insert 281145A03005 12 1 A2821064720000 Spring 281145A03005 14 1 NSA8203-113 O-Ring 281145A03005 18 1 NSA8203-167 O-Ring 281145A03005 22 1 NSA8203-224 O-Ring 281145A03005 24 1 NSA8203-226 O-Ring 281145A03005 26 2 E0088-10-100 Lead 281145A03005 28 4 NAS6603-1 Bolt 281145A03005 29 6 NAS6604-7 Bolt 281145A03005 30 1 NAS6604-20 Bolt 281145A03005 32 1 NSA5112-04 Washer 281145A03005 34 6 ASNA2397-416 Washer 281145A03005 36 1 ASNA2397-416L Washer 281145A03005 38 4 ASNA2397D10L Washer 281145A03005 39 1 NSA5050-4 Nut 281145A03005 40 2 NSA5050-3 Nut 281145A03005 42

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. 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 281145A04R02 30 cm MS20995C32 Wire 281145A03005 48

1 1158000-15 Canister 281145A03006 0 1 1158000-21 Valve 281145A03006 2 1 NSA8203-245 O-Ring 281145A03006 6 4 NAS1154-10 Screw 281145A03006 8 1 NAS1801-06-6 Screw 281145A03006 10 1 NAS1801-3-6 Screw 281145A03006 11 1 ASNA2397-6L Washer 281145A03006 12 1 ASNA2397-10L Washer 281145A03006 13 1 MS21042-06 Nut 281145A03006 14 4 NAS1726C4E Nut 281145A03006 16 1 E0088-16-125 Lead 281145A03006 22 1 HTE900135 Valve 281145A03007 0 1 HTE190001-2 Actuator 281145A03007 2 1 HTE8002 Clamp 281145A03007 4 1 NSA8203-154 O-Ring 281145A03007 6 6 NAS1153-4 Screw 281145A03007 8 1 NAS1801-06-6 Screw 281145A03007 13 4 NAS1726C4E Nut 281145A03007 16 1 ASNA2397-6L Washer 281145A03007 17 1 MS21042L06 Nut 281145A03007 18 1 E0088-16-100 Lead 281145A03007 22 40 cm MS20995C32 Wire 281145A03007 24

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 4 NSA8203-226 O-Ring 281145A04002 5 1 D2821333900000 Pipe 281145A04002 6 1 NAS6603-3 Bolt 281145A04002 9 1 ASNA2397JD10L Washer 281145A04002 10 1 ASNA2397-10L Washer 281145A04002 11 1 D2821333900100 Pipe 281145A04002 12 3 NAS6603-2 Bolt 281145A04002 16 2 NAS1726-3E Nut 281145A04002 18 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 4 NAS6604-5 Bolt 281145A04002 110 4 ASNA2397-416L Washer 281145A04002 112 4 NAS1726-4E Nut 281145A04002 114 1 D2821331020000 Tee 281145A04002 120 1 D2821333900900 Pipe 281145A04003 20 1 D2821333900300 Pipe 281145A04003 22 1 D2821333900400 Pipe 281145A04003 24 1 D2821333900600 Pipe 281145A04003 28 1 D2821333900700 Pipe 281145A04003 30 1 D2821333901000 Pipe 281145A04003 32 1 A2821038600000 Sleeve 281145A04003 34 1 D2821333800000 Sleeve 281145A04003 36 1 D2821334800200 Pipe 281145A04003 38 1 D2821334900200 Pipe 281145A04003 40 1 D2821335000200 Pipe 281145A04003 42 1 D2821338500000 Pipe 281145A04003 44 1 D2821335800200 Pipe 281145A04003 46 1 D2821336720240 RSTRCTR 281145A04003 50 1 NSA5516A04NF Clamp 281145A04003 51 1 MS21902D4 Union 281145A04003 52 1 ASNA0182-1DA Strip 281145A04003 53 2 ABS0107-150 Nut 281145A04003 55 2 ABS0107-200 Nut 281145A04003 56 2 NSA840003-150 Ring 281145A04003 57 2 NSA840003-200 Ring 281145A04003 58 1 NSA8200-4 O-Ring 281145A04003 60 1 NSA8203-215 O-Ring 281145A04003 62 12 NSA8203-222 O-Ring 281145A04003 64

4 NSA8203-226 O-Ring 281145A04003 66 2 NAS1801-06-10 Screw 281145A04003 68 14 NAS6603-2 Bolt 281145A04003 70

4 NAS6603-4 Bolt 281145A04003 72 4 NAS6603-5 Bolt 281145A04003 73 4 NAS6603-3 Bolt 281145A04003 74 2 NAS6604-2 Bolt 281145A04003 76 4 NAS6604-3 Bolt 281145A04003 77 2 MS21042L06 Nut 281145A04003 78 19 NSA5050-3 Nut 281145A04003 80

6 NSA5050-4 Nut 281145A04003 82 2 ASNA2397-6L Washer 281145A04003 83 7 ASNA2397-10L Washer 281145A04003 84 2 E0088-10-160 Lead 281145A04003 90 1 E0088-10-200 Lead 281145A04003 92 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 1 E0088-10-280 Lead 281145A04003 93 1 D2821331620000 Tee 281145A04004 0 6 NAS6604-5 Bolt 281145A04004 10 6 ASNA2397-416L Washer 281145A04004 12 6 NAS1726-4E Nut 281145A04004 14 1 D2821332220000 Elbow 281145A04005 0 2 NAS6604-4 Bolt 281145A04005 10 2 ASNA2397-416L Washer 281145A04005 12 2 NAS1726-4E Nut 281145A04005 14 1 A2821120120000 Elbow 281145A04006 0 2 NAS6604-4 Bolt 281145A04006 10 2 ASNA2397-416L Washer 281145A04006 12 2 NAS1726-4E Nut 281145A04006 14 1 D2821332620000 Elbow 281145A04007 0 2 NAS6604-5 Bolt 281145A04007 10 2 ASNA2397-416L Washer 281145A04007 12 2 NAS1726-4E Nut 281145A04007 14 1 D2821339020000 Elbow 281145A04008 0 1 NSA8203-226 O-Ring 281145A04008 8 4 NAS6603-4 Bolt 281145A04008 10 4 ASNA2397D10L Washer 281145A04008 12 1 D2821333220000 Elbow 281145A04009 0 1 D2821333420000 Elbow 281145A04009 2 1 D2821336621240 RSTRCTR 281145A04009 4 2 NSA8203-222 O-Ring 281145A04009 8 8 NAS6603-3 Bolt 281145A04009 10 8 ASNA2397-10L Washer 281145A04009 12 1 9843144M Valve 281145A04010 0 1 A2821079520000 Flange 281145A04010 1 1 D2821335621800 RSTRCTR 281145A04010 2 1 ABS0107-200 Nut 281145A04010 3 1 NSA840003-200 Ring 281145A04010 4 3 NSA8203-226 O-Ring 281145A04010 5 4 NAS6604-12 Bolt 281145A04010 8 4 NAS1726-4E Nut 281145A04010 9 2 E0088-10-100 Lead 281145A04010 11 2 NAS1726-3E Nut 281145A04010 12 1 NAS6603-2 Bolt 281145A04010 13 1 NAS6603-1 Bolt 281145A04010 14 2 ASNA2397-10L Washer 281145A04010 19 1 D2821336300000 Sleeve 281145A04011 35 1 365A02 Valve 281145A04011 54 2 ABS0107-150 Nut 281145A04011 55 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. 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 281145A05R00 2 NSA840003-150 Ring 281145A04011 57 1 NSA8200-5 O-Ring 281145A04011 61 2 NSA8203-222 O-Ring 281145A04011 64 2 NAS6603-2 Bolt 281145A04011 70 2 NSA5050-3 Nut 281145A04011 80 1 D2821331320000 Tee 281145A04012 0 4 NAS6604-5 Bolt 281145A04012 10 4 ASNA2397-416L Washer 281145A04012 12 4 NAS1726-4E Nut 281145A04012 14 1 D2821331920000 Elbow 281145A04013 0 1 D2821336500000 Sleeve 281145A04013 2 2 NSA8203-222 O-Ring 281145A04013 8 4 NAS6603-7 Bolt 281145A04013 10 4 ASNA2397-416L Washer 281145A04013 12

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2821330700000 Elbow 281145A05001 0 1 D2821334700000 Nutplate 281145A05001 2 1 D2821337500000 Nutplate 281145A05001 4 1 NSA8203-148 O-Ring 281145A05001 8 6 NAS6604-9 Bolt 281145A05001 10 6 ASNA2397-416L Washer 281145A05001 12 1 NAS6603-2 Bolt 281145A05001 14 1 ASNA2397-10L Washer 281145A05001 16 1 D2821337700041 Elbow 281145A05002 0 1 D2821334600000 Nutplate 281145A05002 2 1 D2821337600000 Nutplate 281145A05002 4 1 NSA8203-152 O-Ring 281145A05002 8 6 NAS6604-8 Bolt 281145A05002 10 6 ASNA2397-416L Washer 281145A05002 12 1 D2821337800000 Filter 281145A05002 14 1 D2821337120000 Plate 281145A05002 16 4 NAS6603-2 Bolt 281145A05002 18 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145A06R02

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. 2 NAS6603-5 Bolt 281145A05002 20 5 ASNA2397JD10L Washer 281145A05002 22 2 NSA5050-3 Nut 281145A05002 24 1 ASNA2397-10L Washer 281145A05002 26

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 4 NAS1102-06-7 Screw 281145A06003 14 1 NAS1102-08-7 Screw 281145A06003 15 2 NAS1102-06-5 Screw 281145A06003 16 5 ASNA2083BG2-10 Screw 281145A06003 17 28 NAS1102-04-6 Screw 281145A06003 18

1 MS21042-08 Nut 281145A06003 21 1 ASNA2397-8L Washer 281145A06003 24 1 E0417C01S CNCTR 281145A06003 31 1 E0416-02 Sleeve 281145A06003 32 1 E0415C3LM078E Switch 281145A06003 33 1 D1131043320100 Placard 281145A06004 4 1 D1131043320200 Placard 281145A06004 6 3 NSA931320-030 C/B 281145A06005 1 4 NSA931320-050 C/B 281145A06005 2 1 NSA931322-100 C/B 281145A06005 3 20 E0736N08-01 Screw 281145A06005 4 20 ASNA2553-0401 Washer 281145A06005 5

8 ABS0772A02A Clamp 281145A06005 6 10 ASNA2080G04 Button 281145A06005 9

1 D9000095128395 Bundle 1 D9100095114296 PLCRDSET 150 NSA935401-03 Tie 150 NSA935401-06 Tie 2 NSA939526-02 Shunt QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Kit 281145A07R00

NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. Kit 281145A08R00

Kit 281145A09R00

Kit 281145A10R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D33110194A00 Plate 281145A06003 35

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9251314900000 Plate 281145A06003 0

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D11311658A00 Placard 281145A06005 7 1 D11311361A00 Placard 281145A06005 8

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 E0661-21 Mount 281145A10002 1 4 E0420-04 Stud 281145A10002 2 1 ABS0355-02 Bracket 281145A10002 3 2 E0661-22 Mount 281145A10002 5 1 D9241244120000 Bracket 281145A10003 1 1 NSA5527-03-01 Spacer 281145A10003 2 1 NAS1801-3-20 Screw 281145A10003 3 2 NSA935504-01 Mount 281145A10003 4 1 NAS1726-3E Nut 281145A10003 5 2 ASNA2051DCJ3215 Rivet 281145A10003 18 1 D5391047900001 Bracket 281145A10004 0 2 ASNA2050DCJ3215 Rivet 281145A10004 6 1 NSA935504-03 Mount 281145A10005 0 2 NSA935504-01 Mount 281145A10005 2 3 NAS1801-3-8 Screw 281145A10005 4 3 ASNA2397-10L Washer 281145A10005 6 5 NAS1801-3-9 Screw 281145A10006 10 5 ASNA2397-10L Washer 281145A10006 11 5 NAS1726-3E Nut 281145A10006 14 1 EN3646A62041BN CNCTR 281145A10006 20 1 EN3646A61419BN CNCTR 281145A10006 21 1 E0080-01-20C BACKSHLL 281145A10006 22

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 1 E0080-01-14C BACKSHLL 281145A10006 23 10 M E0432A14 Conduit 281145A10006

1 EN3545E03FXB24A CNCTR 281145A10007 20 (01) 1 EN3545E01FXB22A CNCTR 281145A10007 21 (02) 2 EN3545-007SCD BACKSHLL 281145A10007 22 1 E0427-01A Retainer 281145A10008 1 1 NAS1100-04-6 Screw 281145A10008 2 1 ASNA2397-4L Washer 281145A10008 4 1 ASNA2397-3L Washer 281145A10008 5 5 MS21042L04 Nut 281145A10008 6 1 E0245-28A0 Relay 281145A10008 40 1 E0250A0S Base 281145A10008 41 1 E0666D28A0 Relay 281145A10008 50 1 E0247A0S Base 281145A10008 51 3 ASNA2397-4L Washer 281145A10009 4 3 MS21042L04 Nut 281145A10009 6 3 NAS1100-04-7 Screw 281145A10009 8 1 EN3545D03FXA22A CNCTR 281145A10009 50 (03) 1 EN3545D03MXB22A CNCTR 281145A10009 51 (04) 2 EN3545-007SCD BACKSHLL 281145A10009 52 1 NSA937901MA2008 Module 281145A10009 60 1 NSA937901E1 IDENT 281145A10009 61 1 NSA937901E0 IDENT 281145A10009 62 1 NSA932843AA01 Relay 281145A10009 70 1 NSA932844AA Base 281145A10009 71 1 NSA937901MA2206 Module 281145A10010 0 2 NSA937901E2 IDENT 281145A10010 1 1 NSA937901E8 IDENT 281145A10010 2 1 NSA937901MA2204 Module 281145A10010 3 1 NSA937901E6 IDENT 281145A10010 4 1 D9000095137395 Bundle 1 D9000095137495 Bundle 1 D9000095137595 Bundle 1 D9000095137695 Bundle 1 D9000095137795 Bundle 1 D9000095137895 Bundle 1 D9000095137996 BUNDLE 1 D9000095138095 Bundle 1 D9100095116795 PLCRDSET 100 NSA935401-03 Tie 360 NSA935401-04 Tie 300 NSA935401-05 Tie QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE (01) PN supplied with reference EN3545E03FXB00A. NOTE (02) PN supplied with reference EN3545E01FXB00A. NOTE (03) PN supplied with reference EN3545D03FXA00A. NOTE (04) PN supplied with reference EN3545D03MXB00A. 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 281145A11R03 480 NSA935401-06 Tie 960 NSA935401-08 Tie

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 3 NAS1102-3-10 Screw 281145A11002 4 1 D9251116900000 Plate 281145A11002 7 3 NAS1801-3-8 Screw 281145A11002 12 5 NSA939511-03 Cover 281145A11002 15 6 NSA5050-3 Nut 281145A11002 16 3 ASNA2397-10L Washer 281145A11002 28 1 NSA937901MA2204 Module 281145A11002 50 1 NSA937901MA2011 Module 281145A11002 51 3 NSA937901E2 IDENT 281145A11002 52 1 NSA937901E1 IDENT 281145A11002 53 1 E0425A2001 Module 281145A11002 55 2 D9251127600000 Flange 281145A11003 0 1 D0003006100000 Rack 281145A11003 1 1 E0161D01A12X CNCTR 281145A11003 3 (01) 4 NAS1100-06-12 Screw 281145A11003 6 4 NAS1100-04-7 Screw 281145A11003 9 2 ASNA2397-6L Washer 281145A11003 12 4 ASNA2397-4L Washer 281145A11003 14 1 E0427-01A Retainer 281145A11004 1 1 NAS1100-04-6 Screw 281145A11004 2 1 ASNA2397-4L Washer 281145A11004 4 1 ASNA2397-3L Washer 281145A11004 5 3 MS21042L04 Nut 281145A11004 6 1 E0247A0S Base 281145A11004 40 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE (01) PN supplied with reference E0161D01A01X. 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 281145A12R00

NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. Kit 281145A13R00

Kit 281145B01R00

Kit 281145B02R00

Kit 281145B03R00 1 E0666D28A0 Relay 281145A11004 41 1 D9100095116895 PLCRDSET

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 30042-0000-0501 CTL UNIT 281145A11002

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2821336920000 PLACARD 281145A13001 0 1 D2821336920200 PLACARD 281145A13001 2 1 D2821336920400 PLACARD 281145A13001 4 1 D2821336920600 PLACARD 281145A13001 6 1 D2821336920800 PLACARD 281145A13001 8

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 41 QB0566 1 Filter 42 HTE490005 2 Valve 43 HTE200002-1 1 Actuator 44 HTE920007-001 1 Valve 45 HTE8002 1 Clamp 46 PAS148-133A 1 Valve

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP D9255002500200 1 Panel D9255602500400 1 Relay QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Kit 281145B04R00

Kit 281145D01R00

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 281145D02R00 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP D9245011500600 1 Panel D9255003200400 1 Panel

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP D92400000647 1 Bundle

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827097702200 TUBE D28279990002 0006 3 MS21919WDE8 CLAMP D28270990002 0014 1 NAS1096-3-9 SCREW D28270990002 0015 4 NAS1096-3-8 SCREW D28270990002 0016 5 NAS1149C0332R WASHER D28270990002 0017 5 NAS1291C3M NUT D28270990002 0049 2 NSA5519-11 CLAMP D28270990002 0051 2 E0090-10-160NN LEAD D28270990002 0061

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827097902600 TUBE D28270991000 0000 1 AN924-10J NUT D28270991000 0034 1 NAS1149C1432R WASHER D28270991000 0035 1 NAS1726C3E NUT D28270991000 0070 1 NAS1149C0332R WASHER D28270991000 0073 1 MS21919WDE10 CLAMP D28270991000 0079 1 NSA5575-8A CLAMP D28270991000 0081 1 E0090-10-125NN LEAD D28270991000 0083 1 NAS1303-2 BOLT D28270991000 0088 1 NAS1726-3E NUT D28270991000 0089 1 NAS1149D0316H WASHER D28270991000 0090 1 MS21908J10 ELBOW D28270991000 0091 1 NAS1096-3-9 SCREW D28270991000 0097

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D03R00

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 281145D04R00

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 281145D05R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827098324800 BRACKET D28270992000 0002 2 D2827098325000 BRACKET D28270992000 0004 1 D2827098325200 BRACKET D28270992000 0006 10 LN9198-4012CF RIVET D28270992000 0040

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5347503400200 PANEL D53475024000 0000 1 D5347505400200 FAIRING D53475024000 0002 1 D5347505600400 COVER D53475024000 0004 1 D5347521520000 SECTION D53475024000 0006 1 D5347542400000 BRACKET D53475024000 0008 2 D5347542720000 BRACKET D53475024000 0010 1 D5347542400200 BRACKET D53475024000 0012 1 D5347521120000 BRACKET D53475024000 0014 1 D5347521920000 ANGLE D53475024000 0016 11 ABS0368-01 RECEPTCL D53475024000 0028

5 NAS1791A3-1 NUT D53475024000 0030 2 D5347521320000 WASHER D53475024000 0032 32 DIN65399-2406BF RIVET D53475024000 0125 57 LN9198-4009CF RIVET D53475024000 0240

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5337217000800 BEAM D53372362006 0000 2 D5337218500000 STRUT D53372362006 0002 4 D5337218600000 STRUT D53372362006 0004 1 D5337219220000 FITTING D53372362006 0008 1 D5337219220100 FITTING D53372362006 0009 1 D5337219120200 FITTING D53372362006 0010 1 D5337219120300 FITTING D53372362006 0011 1 D5337219020200 FITTING D53372362006 0012 1 D5337215920000 ANGLE D53372362006 0014 8 D5337215920200 ANGLE D53372362006 0016 1 D5337215920400 ANGLE D53372362006 0018 1 D5337215920500 ANGLE D53372362006 0019 1 D5337215920600 ANGLE D53372362006 0020 1 D5337217320000 PLATE D53372362006 0022 1 D5337217400000 PLATE D53372362006 0024 1 D5337217400100 PLATE D53372362006 0025 1 D5337216020090 SECTION D53372362006 0026 1 D5347449520800 SECTION D53372362006 0028 1 D5347449520900 SECTION D53372362006 0029 1 D5337601520600 SHIM D53372362006 0030 1 D5337601520800 SHIM D53372362006 0032 1 D5337601521000 SHIM D53372362006 0034 1 D5337601521200 SHIM D53372362006 0036 1 D5337601521400 SHIM D53372362006 0038 1 D5347100720600 COUPLING D53372362006 0040 1 D5347101620490 CONNECTN D53372362006 0042 1 D5347101620590 CONNECTN D53372362006 0043 3 D5337602020000 SECTION D53372362006 0044 3 D5337602020100 SECTION D53372362006 0045 4 NAS1791A3-1 NUT D53372362006 0046 1 D5347100920090 SUPPORT D53372362006 0048 1 D5347100920190 SUPPORT D53372362006 0049 1 D5347104120090 ANGLE D53372362006 0050 1 D5347104120190 ANGLE D53372362006 0051 4 D5337236220400 SHIM D53372362006 0052 1 D5337036520200 ANGLE D53372362006 0150 1 D5337036520300 ANGLE D53372362006 0151 2 D5347007422000 ANGLE D53372362006 0152 2 D5347007422100 ANGLE D53372362006 0153 2 D5347007422200 ANGLE D53372362006 0156 12 ASNA0082A302 BOLT D53372362006 0435

2 ASNA0082A303 BOLT D53372362006 0436

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 4 ASNA0082A304 BOLT D53372362006 0438 15 ASNA0082A305 BOLT D53372362006 0440

1 ASNA0082A306 BOLT D53372362006 0442 2 MS21250-09024 BOLT D53372362006 0464 2 NAS1726-9E NUT D53372362006 0466 2 MS20002C9 WASHER D53372362006 0468 4 MS21250-06018 BOLT D53372362006 0470 4 NAS1726-6E NUT D53372362006 0472 4 MS20002C6 WASHER D53372362006 0474 12 NAS1097AD3-10 RIVET D53372362006 0524 12 NAS1097AD4-10 RIVET D53372362006 0532 98 NAS1097AD5-10 RIVET D53372362006 0540

8 DAN7-6-6X PIN D53372362006 0566 200 LN9198-4010CF RIVET D53372362006 0640

61 LN9198-4810CF RIVET D53372362006 0648

4 LN9198-5610CF RIVET D53372362006 0656 12 DAN5-6-4X PIN D53372362006 0764

8 DAN5-6-5X PIN D53372362006 0765 16 DAN5-6-6X PIN D53372362006 0766 24 DAN5-6-7X PIN D53372362006 0767 86 DAN5-6-8X PIN D53372362006 0768 20 DAN5-6-9X PIN D53372362006 0769

4 DAN5-6-10X PIN D53372362006 0770 12 DAN5-6-11X PIN D53372362006 0771 12 DAN5-6-12X PIN D53372362006 0772 68 NSA5075-5 COLLAR D53372362006 0804 170 NSA5075-6 COLLAR D53372362006 0806 194 DAN11-6X COLLAR D53372362006 0807

41 DAN11-8X COLLAR D53372362006 0810 210 NSA5076-6 COLLAR D53372362006 0816 8 DAN12-6X COLLAR D53372362006 0817 20 DAN6-6-5 PIN D53372362006 0865

8 DAN6-6-6 PIN D53372362006 0866 4 DAN5-8-7X PIN D53372362006 0887 5 DAN5-8-8X PIN D53372362006 0888 7 DAN5-8-9X PIN D53372362006 0889 10 DAN5-8-10X PIN D53372362006 0890

7 DAN5-8-11X PIN D53372362006 0891 8 DAN5-8-12X PIN D53372362006 0892 36 DAN5-5-4 PIN D53372362006 0944 16 DAN5-5-5 PIN D53372362006 0945

4 DAN5-5-9 PIN D53372362006 0949 3 DAN7-5-5 PIN D53372362006 0955 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

47

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D06R00 9 DAN7-5-6 PIN D53372362006 0956 12 DAN5-6-3 PIN D53372362006 0963 12 DAN5-6-4 PIN D53372362006 0964 216 DAN5-6-5 PIN D53372362006 0965

80 DAN5-6-6 PIN D53372362006 0966 10 DAN5-6-7 PIN D53372362006 0967 18 DAN5-6-8 PIN D53372362006 0968

4 DAN5-6-9 PIN D53372362006 0969

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5347449320000 FITTING D53470076004 0010 1 D5337217620000 PLATE D53470076004 0012 1 D5347449521600 SECTION D53470076004 0014 1 D5347658920000 FITTING D53470076004 0016 1 D5347659220000 SHIM D53470076004 0018 1 D5347659020000 FITTING D53470076004 0020 6 D5347470020200 ANGLE D53470076004 0022 1 D5347470020300 ANGLE D53470076004 0023 3 D5347470020400 ANGLE D53470076004 0024 1 D5347449520400 SECTION D53470076004 0026 3 D5347449520500 SECTION D53470076004 0027 3 D5347449520300 SECTION D53470076004 0028 1 D5347470021400 ANGLE D53470076004 0030 1 D5337217620800 FILLER D53470076004 0032 1 D5347470023200 ANGLE D53470076004 0034 1 D5347470023400 ANGLE D53470076004 0036 2 D5337217620400 SHIM D53470076004 0038 1 D5347470520000 ANGLE D53470076004 0040 1 D5347470520100 ANGLE D53470076004 0041 1 D5347470021000 ANGLE D53470076004 0042 1 D5347470021200 ANGLE D53470076004 0044 1 D5347470024000 ANGLE D53470076004 0046 1 D5347658220200 SHIM D53470076004 0048 1 D5347470023800 ANGLE D53470076004 0050 1 D5347470023600 ANGLE D53470076004 0052 1 D5347659320000 FITTING D53470076004 0054 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 1 D5337217621000 PLATE D53470076004 0056 2 D5347470024200 ANGLE D53470076004 0058 2 D5337217621200 PLATE D53470076004 0060 1 D5347470024400 ANGLE D53470076004 0062 1 D5347470024600 ANGLE D53470076004 0064 1 D5347470520300 SUPPORT D53470076004 0066 1 D5347657820000 WEB D53470076004 0068 1 D5347658820000 WEB D53470076004 0070 1 D5347470025000 ANGLE D53470076004 0072 1 D5347470025200 ANGLE D53470076004 0074 1 D5347657920000 WEB D53470076004 0076 1 D5347449522600 SECTION D53470076004 0078 1 D5347449522800 SECTION D53470076004 0080 1 D5347550021000 KEY D53470076004 0082 1 D5347471320800 PLATE D53470076004 0084 1 D5347471321000 PLATE D53470076004 0086 1 D5347449522000 SECTION D53470076004 0088 1 D5347449522200 SECTION D53470076004 0090 1 D5347449522400 SECTION D53470076004 0092 1 D5347449523800 SECTION D53470076004 0094 1 D5347449523400 SECTION D53470076004 0096 2 D5347449524000 SECTION D53470076004 0098 1 D5347449524200 SECTION D53470076004 0100 1 D5347471321800 PLATE D53470076004 0102 1 D5347470520500 SUPPORT D53470076004 0104 1 D5347044922600 SHIM D53470076004 0106 3 D5347044922800 SHIM D53470076004 0108 1 D5337217625800 PLATE D53470076004 0110 1 D5347044924200 SHIM D53470076004 0150 1 D5347646320400 DOUBLER D53470076004 0160 1 D5347646321000 DOUBLER D53470076004 0162 1 D5347470920200 COVER D53470076004 0164 2 D5347669200000 PLATE D53470076004 0166 2 D5347669000000 TUBE D53470076004 0172 2 D5347669100000 PLUG D53470076004 0174 2 D5347472120200 SHIM D53470076004 0176 4 D5347470220000 SHIM D53470076004 0178 2 D5347472120400 SHIM D53470076004 0180 1 D5347660220200 SHIM D53470076004 0182 3 D5347449420600 FITTING D53470076004 0200 1 D5347449421100 FITTING D53470076004 0201 2 D5347448420200 STRAP D53470076004 0202 1 D5347448420300 STRAP D53470076004 0203 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 1 D5347037820400 SUPPORT D53470076004 0204 1 D5347449920200 FITTING D53470076004 0206 1 D5347657720000 WEB D53470076004 0208 1 D5347026100600 XBEAM D53470076004 0218 1 D5347035601400 XBEAM D53470076004 0230 1 D5347065620400 SECTION D53470076004 0242 1 D5347449820400 FITTING D53470076004 0244 8 NAS1791A3-1 NUT D53470076004 0260 2 MS16625-4212 RING D53470076004 0500 10 NAS1153E7 SCREW D53470076004 0502

8 ABS0337-01A RECEPTCL D53470076004 0504 2 NAS1096-3-10 SCREW D53470076004 0506 10 NAS1474A3 NUT D53470076004 0510 16 MBBN4477-4010 RIVET D53470076004 0541 294 MBBN4477-4810 RIVET D53470076004 0549 106 LN9198-4010CF RIVET D53470076004 0640 290 LN9198-4810CF RIVET D53470076004 0648 6 LN9198-6410CF RIVET D53470076004 0664 4 DAN6-6-5X PIN D53470076004 0665 7 DAN6-6-6X PIN D53470076004 0666 25 DAN6-6-7X PIN D53470076004 0667 18 DAN6-6-8X PIN D53470076004 0668

8 DAN6-6-7Y PIN D53470076004 0677 8 DAN6-6-8Y PIN D53470076004 0678 44 DIN65399-2410CF RIVET D53470076004 0724 12 DAN5-6-5X PIN D53470076004 0765 18 DAN5-6-7X PIN D53470076004 0767

3 DAN5-6-8X PIN D53470076004 0768 16 NSA5330-6 COLLAR D53470076004 0803 565 NSA5075-6 COLLAR D53470076004 0806

87 DAN11-6X COLLAR D53470076004 0807 33 NSA5075-8 COLLAR D53470076004 0808 68 DAN6-6-3 PIN D53470076004 0863

8 DAN6-6-4 PIN D53470076004 0864 62 DAN6-6-5 PIN D53470076004 0865 73 DAN6-6-6 PIN D53470076004 0866 22 DAN6-6-7 PIN D53470076004 0867 54 DAN6-6-8 PIN D53470076004 0868 28 DAN6-6-10 PIN D53470076004 0870 30 DAN5-6-3 PIN D53470076004 0963 71 DAN5-6-4 PIN D53470076004 0964 81 DAN5-6-5 PIN D53470076004 0965 28 DAN5-6-6 PIN D53470076004 0966 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D07R00

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 281145D08R00

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. 10 DAN5-6-7 PIN D53470076004 0967 27 DAN5-6-8 PIN D53470076004 0968

3 DAN5-6-9 PIN D53470076004 0969 9 DAN5-8-5 PIN D53470076004 0985 12 DAN5-8-6 PIN D53470076004 0986 12 DAN5-8-7 PIN D53470076004 0987

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5337270100000 ANGLE D53370780004 0030 1 D5337270100200 ANGLE D53370780004 0032 1 D5337270100400 ANGLE D53370780004 0034 1 D5337270100600 ANGLE D53370780004 0036 1 D5337270100800 ANGLE D53370780004 0038 1 D5337270101000 ANGLE D53370780004 0040 8 ASNA0082-203 BOLT D53370780004 0263 4 ASNA0082-204 BOLT D53370780004 0264

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 102 NSA5075-6 COLLAR D53470096002 0806

12 DAN6-6-3 PIN D53470096002 0863 12 DAN6-6-5 PIN D53470096002 0865 54 DAN5-6-3 PIN D53470096002 0963 24 DAN5-6-4 PIN D53470096002 0964 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Kit 281145D10R00

Kit 281145D11R00

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 281145D13R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2587085002200 BLANKET D25870003048 0000 1 D2587085105600 BLANKET D25870003048 0001 1 D2587085205200 BLANKET D25870003048 0002 1 D2587085305600 BLANKET D25870003048 0003 1 D2587085405200 BLANKET D25870003048 0004 1 D2587085505400 BLANKET D25870003048 0005 1 D2587085602200 BLANKET D25870003048 0006 1 D2587085705200 BLANKET D25870003048 0007 1 D2587085805200 BLANKET D25870003048 0008 1 D2587085905200 BLANKET D25870003048 0009 1 D2587086005400 BLANKET D25870003048 0010 1 D2587086105200 BLANKET D25870003048 0011 1 D2587086202200 BLANKET D25870003048 0012 1 D2587086302400 BLANKET D25870003048 0013 1 D2587086502200 BLANKET D25870003048 0014 1 D2587087102200 BLANKET D25870003048 0015 1 D2587087302200 BLANKET D25870003048 0016 80 F2587003400000 STRIP D25870003048 0100

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9357040100200 BRACKET D93070668000 0112 1 D9357040100300 BRACKET D93070668000 0113 4 NAS1919B04-02 RIVET D93070668000 0125

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

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 2 D2827093222200 FLANGE D28270972002 0014 1 D2827093322400 SLEEVE D28270972002 0016 2 D2827092700000 TUBE D28270972002 0018 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 7 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 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D14R00 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 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 E0089-41-280NN LEAD D28270972002 0107 3 E0088-10-125 LEAD D28270972002 0108 2 E0088-10-200 LEAD D28270972002 0109 0.34 5 ME NSA937210MB0300 TUBING D28270972002 0110
0.38 ME NSA937210MB0300 TUBING D28270972002 0111 2 E0089-10-250NN LEAD D28270972002 0112

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

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 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 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 MONITOR D28270973002 0206 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D15R00 1 513535E0107-090 HOSE D28270973002 0208 1 D2827094720000 BRACKET D28270973002 0210 1 D2827094421400 PLACARD D28270973002 0214 1 D2827098322800 BRACKET D28270973002 0216

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 5 MS21919WDE8 CLAMP D28270974002 0014 15 NAS1096-3-8 SCREW D28270974002 0016 16 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 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 MONITOR D28270974002 0202 1 513535E0107-090 HOSE D28270974002 0204 1 D2827094421600 PLACARD D28270974002 0216 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D16R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827098000800 TUBE D28270975004 0005 1 D2827098001400 TUBE D28270975004 0011 1 D2827097901200 TUBE D28270975004 0013 1 D2827097901400 TUBE D28270975004 0015 1 D2827097901000 TUBE D28270975004 0016 1 D2827097901600 TUBE D28270975004 0017 1 D2827097901800 TUBE D28270975004 0019 1 D2827097902000 TUBE D28270975004 0021 1 D2827097902400 TUBE D28270975004 0025 1 D2827097904000 TUBE D28270975004 0026 1 A2163302000000 FILTER D28270975004 0027 1 A2151034520000 INLET D28270975004 0028 1 MS21902D10 UNION D28270975004 0030 1 NAS1612-10 PACKING D28270975004 0031 1 83694912 HOSE D28270975004 0040 (01) 2 A2827092300000 COUPLING D28270975004 0050 27 NAS1726C3E NUT D28270975004 0070 18 NAS1096-3-8 SCREW D28270975004 0071 27 NAS1149C0332R WASHER D28270975004 0073

2 AN924-10J NUT D28270975004 0074 2 MS21909J10 TEE D28270975004 0075 2 NAS1149F1432P WASHER D28270975004 0076 1 TSTMNR503-0 CONDUIT D28270975004 0077 4 NSA935401-03 TIE D28270975004 0078 10 MS21919WDE10 CLAMP D28270975004 0079 11 MS21919WDE4 CLAMP D28270975004 0080

8 NSA5575-8A CLAMP D28270975004 0081 3 NSA5575-2 CLAMP D28270975004 0082 7 E0090-10-125NN LEAD D28270975004 0083 4 E0090-18-100NN LEAD D28270975004 0084 4 NAS1096-1-8 SCREW D28270975004 0085 4 MS21042-06 NUT D28270975004 0087 8 NAS1303-2 BOLT D28270975004 0088 8 NAS1726-3E NUT D28270975004 0089 1 MS21908J10 ELBOW D28270975004 0091 1 AN924-4D NUT D28270975004 0092

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE (01) Part number supplied, 1451515F0150-180. 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 281145D17R00 4 NAS1726C4E NUT D28270975004 0093 2 MS21914-10D CAP D28270975004 0094 1 AN924-10J NUT D28270975004 0095 1 NAS1149C1432R WASHER D28270975004 0096 7 NAS1096-3-9 SCREW D28270975004 0097 2 NAS1096-3-12 SCREW D28270975004 0098 1 MS21905J10 TEE D28270975004 0099 1 MS21919WCH15 CLAMP D28270975004 0101 1 E0090-10-160NN LEAD D28270975004 0102 16 NAS1149F0332P WASHER D28270975004 0103

8 NAS1149FN616P WASHER D28270975004 0104 1 D2827094420000 PLACARD D28270975004 0200 1 D2827094420200 PLACARD D28270975004 0202 1 D2827094420400 PLACARD D28270975004 0204 1 D2827094420600 PLACARD D28270975004 0206 1 D2827094420800 PLACARD D28270975004 0208 1 D2827094421000 PLACARD D28270975004 0210 1 D2827094421200 PLACARD D28270975004 0212 1 D2827098002400 TUBE D28270975004 0220 1 D2827098002600 TUBE D28270975004 0222

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 6 NAS1096-3-8 SCREW D28270982004 0004 6 NAS1149C0332R WASHER D28270982004 0005 6 NAS1726C3E NUT D28270982004 0006 69 LN9198-3212BF RIVET D28270982004 0032 69 LN9198-4012BF RIVET D28270982004 0040

8 DAN7-6-8Y PIN D28270982004 0041 8 DAN12-6Y COLLAR D28270982004 0042 3 F5397461900600 BRACKET D28270982004 0100 2 D2827094222800 ANGLE D28270982004 0102 1 D2827098300000 BRACKET D28270982004 0104 1 D2827098300200 BRACKET D28270982004 0106 3 D2827094221400 ANGLE D28270982004 0112 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D18R00

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 281145D19R00 2 D2827094220400 ANGLE D28270982004 0113 2 D2827094221800 ANGLE D28270982004 0115 2 D2827094222200 ANGLE D28270982004 0116 2 D2827098320800 BRACKET D28270982004 0117 2 D2827098321000 BRACKET D28270982004 0118 1 D2827098321200 ANGLE D28270982004 0119 2 D2827094200400 BRACKET D28270982004 0124 1 D2827098325200 BRACKET D28270982004 0125 1 D2827098300800 BRACKET D28270982004 0126 2 D2827098323200 BRACKET D28270982004 0127 1 D2827098323000 BRACKET D28270982004 0128 1 D2827098323800 BRACKET D28270982004 0130 1 D2827093521000 BRACKET D28270982004 0131 1 D2827098324200 BRACKET D28270982004 0132 1 D2827098324400 BRACKET D28270982004 0133 1 D2827098324000 BRACKET D28270982004 0134 1 D2827098326000 BRACKET D28270982004 0135 1 D2827098326200 BRACKET D28270982004 0136 2 D2827098327600 ANGLE D28270982004 0137 1 D2827098327800 ANGLE D28270982004 0138 1 D2827098328000 ANGLE D28270982004 0139 1 D2827098328200 ANGLE D28270982004 0140

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

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D20R00

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 281145D25R00

Kit 281145D26R00

Kit 281145D27R00 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 10 NAS1149D0332K WASHER D28270999004 0014

1 D2827099600400 SHIELD D28270999004 0022

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827050501600 TUBE D28270515000 0002 1 NSA855113-11C TEE D28270515000 0021 1 D2827050502600 TUBE D28270515000 0044

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557131000200 PANEL D25571073000 0000 1 D2557131400600 PANEL D25571073000 0002 1 D2557131600800 PANEL D25571073000 0004

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557132600200 PANEL D25571073002 0010 1 D2557132401000 PANEL D25571073002 0012 1 D2557132200600 PANEL D25571073002 0014

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Kit 281145D28R00

Kit 281145D31R00

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 281145D32R00

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. QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557133000200 PANEL D25571073004 0020 1 D2557133400600 PANEL D25571073004 0022

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557123600400 PANEL D25571073006 0030 1 D2557123600500 PANEL D25571073006 0031 1 D2557123800200 PANEL D25571073006 0032 2 D2557017000200 COVER D25571073006 0040

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367161701800 PANEL D53675015002 0016 2 D5367160001600 PANEL D53675015002 0030 1 D5367160100800 PANEL D53675015002 0032 1 D5367162400800 PANEL D53675015002 0036 1 D5367150100200 PANEL D53675015002 0040 2 D5367162301400 PANEL D53675015002 0042 1 D5367150500800 PANEL D53675015002 0044 36 ABS0376-3-23 SCREW D53675015002 0398 130 ABS0376-3-25 SCREW D53675015002 0400 166 EN6131-3C1 NUT D53675015002 0505

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 38.5 41 ME DAN107-1 CORD D53675016002 0385
38.5 41 ME ABS5093AT25 TAPE D53675016002 0387

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Kit 281145D33R00

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 281145D34R00

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 281145D36R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367520801400 PANEL D53675510000 0028 1 D5367520801800 PANEL D53675510000 0030 1 D5367520805000 PANEL D53675510000 0032 1 D5367520802600 PANEL D53675510000 0038 1 D5367521104000 PANEL D53675510000 0084 1 D5367521104200 PANEL D53675510000 0086 1 D5367521104400 PANEL D53675510000 0088 1 D5367521104600 PANEL D53675510000 0090 1 D5367521104800 PANEL D53675510000 0092 1 D5367521105000 PANEL D53675510000 0094 1 D5397484220000 PLATE D53675510000 0110 1 D5397484220100 PLATE D53675510000 0111 2 D5397489520000 SPACER D53675510000 0118 2 D5397489520100 SPACER D53675510000 0119 61 ABS0376-3-30 SCREW D53675510000 0402 95 ABS0376-3-40 SCREW D53675510000 0404 12 NAS1102-3-8 SCREW D53675510000 0408

1 NAS1102-3-24 SCREW D53675510000 0409 80 EN6131-3C1 NUT D53675510000 0410

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2.25 ME ABS0305LC SECTION D53675511000 0001 12.1 ME ABS0399A SECTION D53675511000 0004 21.0 62 ME DAN107-1 CORD D53675511000 0005

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D40R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 3 D5397489200000 SECTION D53975019000 0000 2 D5397489200100 SECTION D53975019000 0001 1 D5397489300000 SECTION D53975019000 0002 1 D5397469000000 BRACKET D53975019000 0016 1 D5397469000100 BRACKET D53975019000 0017 1 D5397469200000 BRACKET D53975019000 0018 1 D5397469200100 BRACKET D53975019000 0019 1 D5397469300000 BRACKET D53975019000 0020 1 D5397469300100 BRACKET D53975019000 0021 44 NAS6703-2 BOLT D53975019000 0025 44 NAS1149D0332K WASHER D53975019000 0026 22 D5397469700000 SUPPORT D53975019000 0028

1 D5347047400200 SECTION D53975019000 0030 1 D5347047400300 SECTION D53975019000 0031 1 D5397467800800 SECTION D53975019000 0040 1 D5397467800900 SECTION D53975019000 0041 1 D5397492600000 SECTION D53975019000 0042 1 D5397468800200 SECTION D53975019000 0044 1 D5397468800300 SECTION D53975019000 0045 1 D5397468000400 SECTION D53975019000 0046 1 D5397468000500 SECTION D53975019000 0047 1 D5397492500000 SECTION D53975019000 0048 1 D5397492500200 SECTION D53975019000 0050 1 D5397467400500 SECTION D53975019000 0052 1 D5397467400400 SECTION D53975019000 0053 3 D5397492700000 PLATE D53975019000 0054 9 NAS1102E3-7 SCREW D53975019000 0400 9 DAN125-4 WASHER D53975019000 0402 190 NAS1097AD4-12 RIVET D53975019000 0532 8 LN9198-4816CF RIVET D53975019000 0648

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D5347035000600 XBEAM D53470075004 0010 4 D5337217620000 PLATE D53470075004 0012 3 D5337217620100 PLATE D53470075004 0014

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 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 PLATE D53470075004 0078 1 D5347470420400 WEB D53470075004 0080 1 D5347470021600 ANGLE D53470075004 0082 1 D5347470021800 ANGLE D53470075004 0084 1 D5347470024800 ANGLE D53470075004 0086 1 D5347470043800 ANGLE D53470075004 0088 1 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 1 D5347658420000 ANGLE D53470075004 0102 1 D5347471321200 PLATE D53470075004 0104 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

64

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 2 D5347471500200 PLATE D53470075004 0108 1 D5347471500000 PLATE D53470075004 0110 1 D5347471500600 PLATE D53470075004 0112 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 D5347471322400 PLATE D53470075004 0138 1 D5347471322600 PLATE D53470075004 0140 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 D5347046824500 ANGLE D53470075004 0220 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 RECEPTCL D53470075004 0504 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

65

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service 2 NAS1096-3-10 SCREW D53470075004 0506 4 NAS1791A3-1 NUT D53470075004 0508 10 NAS1474A3 NUT D53470075004 0510 28 MBBN4477-4010 RIVET D53470075004 0541 347 MBBN4477-4812 RIVET D53470075004 0549 969 LN9198-4010CF RIVET D53470075004 0640 548 LN9198-4810CF 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

8 DAN6-6-8Y PIN D53470075004 0678 36 DIN65399-2410CF RIVET D53470075004 0724 84 DIN65399-3210CF RIVET D53470075004 0732 10 DAN5-6-4X PIN D53470075004 0764 24 DAN5-6-5X PIN D53470075004 0765

8 DAN5-6-6X PIN D53470075004 0766 14 DAN5-6-8X PIN D53470075004 0768

8 DAN5-6-8Y PIN D53470075004 0778 16 NSA5330-6 COLLAR D53470075004 0803

3 NSA5075-5 COLLAR D53470075004 0804 749 NSA5075-6 COLLAR D53470075004 0806

69 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 34 DAN6-6-5 PIN D53470075004 0865

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 126 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 8 DAN5-8-7 PIN D53470075004 0987 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

66

# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D41R00

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 281145D42R03 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

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557258500800 TRACK D25572585012 0007 1 D2557268121000 DOUBLER D25572585012 0009 1 D2557268028600 PLATE D25572585012 0010 1 D2557258501000 TRACK D25572585012 0011 1 D2557265025800 PLATE D25572585012 0012 2 D2557237320600 BOLT D25572585012 0013 3 NAS1149C0563R WASHER D25572585012 0014 2 MS24665-300 PIN D25572585012 0015 14 MS21042-3 NUT D25572585012 0016 14 NAS1153-3 SCREW D25572585012 0017

1 D2557224601000 TRACK D25572585012 0018 1 D2557224600600 TRACK D25572585012 0019 56 NAS1102-3-7 SCREW D25572585012 0026 166 NAS1102-3-10 SCREW D25572585012 0027 436 NAS1726-3E NUT D25572585012 0028

38 NAS1100-3-12 SCREW D25572585012 0029 19 NAS1100-3-14 SCREW D25572585012 0030 25 MS21250-03008 BOLT D25572585012 0031 52 NAS1102-3-9 SCREW D25572585012 0032 16 NAS1133E5 SCREW D25572585012 0033 NOTE 01 108 MS21250-03010 BOLT D25572585012 0034 4 MS21250-03012 BOLT D25572585012 0035 6 NSA5042C05-180 BOLT D25572585012 0036 6 NSA5060-4 NUT D25572585012 0037

67

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 6 NAS1149C0432R WASHER D25572585012 0038 39 NAS1149C0532R WASHER D25572585012 0039

6 MS24665-153 PIN D25572585012 0040 36 DAN7-5-5 PIN D25572585012 0041 36 DAN7-5-6 PIN D25572585012 0042 36 DAN12-5 COLLAR D25572585012 0043 42 NAS1102-3-8 SCREW D25572585012 0044 34 NAS1100-3-10 SCREW D25572585012 0045 10 NAS1100-3-8 SCREW D25572585012 0046

2 NSA5059-5 NUT D25572585012 0047 52 NAS1133E3 SCREW D25572585012 0048 160 MS21250-03006 BOLT D25572585012 0049

68 NAS1102-3-11 SCREW D25572585012 0050 74 NAS1102-3-12 SCREW D25572585012 0051 32 NAS1102-3-14 SCREW D25572585012 0052 35 NAS1100-3-9 SCREW D25572585012 0053 135 NAS1100-3-11 SCREW D25572585012 0054 5 NAS1100-3-6 SCREW D25572585012 0055 5 NAS1149C0332R WASHER D25572585012 0056 170 NAS1100-3-7 SCREW D25572585012 0057

18 NAS1303-7 BOLT D25572585012 0058

2 NAS1303-9 BOLT D25572585012 0059 6 D2557268030600 SHIM D25572585012 0069 6 D2557226520400 SUPPORT D25572585012 0070 6 D2557226120200 BLOCK D25572585012 0071 48 MS21250-03014 BOLT D25572585012 0072 12 D2557238000400 LATCH D25572585012 0078 18 NAS1153-13 SCREW D25572585012 0079

1 D2557240102200 SUPPORT D25572585012 0080 5 D2557268122200 PLATE D25572585012 0081 1 D2557268122400 PLATE D25572585012 0082 2 MS21250-04012 BOLT D25572585012 0083 2 MS21250-04024 BOLT D25572585012 0084 3 MS21250-04026 BOLT D25572585012 0085 4 MS21250-04030 BOLT D25572585012 0086 10 NAS1726-4E NUT D25572585012 0087 11 NAS1149F0432P WASHER D25572585012 0088

2 NAS1102-08-10 SCREW D25572585012 0091 2 NAS1726-05E NUT D25572585012 0092 1 D2557240021400 STOP D25572585012 0094 3 MS21250-06018 BOLT D25572585012 0095 3 NSA5379-6C WASHER D25572585012 0096 1 NAS1304-18 BOLT D25572585012 0097 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

68

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE (01) Alternative for Item 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 281145D43R00

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 281145D44R01 5 D2557268123000 PLATE D25572585012 0099 5 D2557268123200 PLATE D25572585012 0100 5 D2557268123400 PLATE D25572585012 0101 5 D2557268123600 PLATE D25572585012 0102 5 D2557268123800 PLATE D25572585012 0103 5 D2557268124000 PLATE D25572585012 0104 5 D2557268124200 PLATE D25572585012 0105 5 D2557268124400 PLATE D25572585012 0106 5 D2557268124600 PLATE D25572585012 0107 5 D2557268124800 PLATE D25572585012 0108 5 D2557268125000 PLATE D25572585012 0109 1 D2557224601400 TRACK D25572585012 0114 18 NAS1153-11 SCREW D25572585012 0162 18 NAS1153-15 SCREW D25572585012 0164 24 NAS1133E10 SCREW D25572585012 0165 NOTE 01

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 NAS1149C0332R WASHER D25572585014 0031 11 NAS1726C3P NUT D25572585014 0036

1 NSA5039-3-1 SCREW D25572585014 0042 4 NSA5030-3-2 SCREW D25572585014 0044 2 NSA5039-3-3 SCREW D25572585014 0045 2 NSA5039-3-7 SCREW D25572585014 0046 2 NSA5030-3-9 SCREW D25572585014 0047 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

69

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

24 D2557214631800 SHIM D25572585016 0014 24 D2557214632000 SHIM D25572585016 0015

6 D2557214633400 SHIM D25572585016 0034 6 D2557214633500 SHIM D25572585016 0035 6 D2557214633600 SHIM D25572585016 0036 40 D2557214635000 SHIM D25572585016 0050 40 D2557214635100 SHIM D25572585016 0051 40 D2557214635200 SHIM D25572585016 0052

2 D2557214635400 SHIM D25572585016 0054 2 D2557214635500 SHIM D25572585016 0055 2 D2557214635600 SHIM D25572585016 0056 2 D2557214635800 SHIM D25572585016 0058 6 D2557214636000 SHIM D25572585016 0060 6 D2557214636800 SHIM D25572585016 0066 6 D2557214637000 SHIM D25572585016 0068 12 D2557214637200 SHIM D25572585016 0070 12 D2557214637400 SHIM D25572585016 0072

4 D2557214637600 SHIM D25572585016 0076 4 D2557214637700 SHIM D25572585016 0077 4 D2557214637800 SHIM D25572585016 0078 12 D2557214638000 SHIM D25572585016 0080 12 D2557214638100 SHIM D25572585016 0081 12 D2557214638200 SHIM D25572585016 0082

2 D2557214638400 SHIM D25572585016 0084 2 D2557214638500 SHIM D25572585016 0085 2 D2557214638600 SHIM D25572585016 0086 12 D2557214638800 SHIM D25572585016 0088 12 D2557214638900 SHIM D25572585016 0089 12 D2557214639000 SHIM D25572585016 0090

6 D2557214639600 SHIM D25572585016 0096 6 D2557214639700 SHIM D25572585016 0097 6 D2557214639800 SHIM D25572585016 0098 12 D2557214640000 SHIM D25572585016 0100 12 D2557214640200 SHIM D25572585016 0102

3 D2557206229800 PLUG D25572585016 0104 2 D2557214642000 SHIM D25572585016 0106 2 D2557214642100 SHIM D25572585016 0107 2 D2557214642200 SHIM D25572585016 0108 2 D2557214642400 SHIM D25572585016 0110 2 D2557214642600 SHIM D25572585016 0112 2 D2557214642800 SHIM D25572585016 0114 2 D2557214643000 SHIM D25572585016 0116

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Kit 281145D46R00

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 281145D47R01 2 D2557214641200 SHIM D25572585016 0118 2 D2557214641400 SHIM D25572585016 0120 2 D2557214641600 SHIM D25572585016 0122 2 D2557214641800 SHIM D25572585016 0124 2 D2557214643600 SHIM D25572585016 0126 2 D2557214643800 SHIM D25572585016 0128 6 NAS1102-3-10 SCREW D25572585016 0134 4 D2557214653000 SHIM D25572585016 0229 2 D2557214653800 SHIM D25572585016 0233 2 D2557214653900 SHIM D25572585016 0234 2 D2557214654000 SHIM D25572585016 0235 20 D2557214653200 SHIM D25572585016 0236

3 D2557214633800 SHIM D25572585016 0238 2 D2557214634000 SHIM D25572585016 0240

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 DAN152-1 TDP D25572585022 0009 6 NAS1102-3-10 SCREW D25572585022 0010 3 NAS1102-3-14 SCREW D25572585022 0011 9 NAS1726-3E NUT D25572585022 0013 1 D2557206230400 FITTING D25572585022 0029 1 D2557206230600 FITTING D25572585022 0031

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557213623800 SHEET D25572585024 0007 2 NAS1153-27 SCREW D25572585024 0010 2 NAS1153-25 SCREW D25572585024 0014 4 NSA5039-3-6 SCREW D25572585024 0031 4 NSA5039-3-8 SCREW D25572585024 0032 11 NSA5030-3-5 SCREW D25572585024 0034

8 NAS1726-3E NUT D25572585024 0035 23 ABS0365-3-2B NUT D25572585024 0037

1 D2557214429600 SHEET D25572585024 0066 1 D2557215901800 MAT D25572585024 0070 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D48R00

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 281145D49R01

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 281145D50R00 1 D2557215702000 MAT D25572585024 0071 1 D2557216001000 MAT D25572585024 0072 1 D2557210500200 STRIP D25572585024 0074 1 D2557210600400 STRIP D25572585024 0075 0.2 ME ABS5006-6D TAPE D25572585024 0076 1.3 ME ABS5006-4B TAPE D25572585024 0077

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 NSA935401-04 TIE D25572585026 0003

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 134100-5 LATCH D25572585028 0141 1 D2557237422800 TRACK D25572585028 0142 3 D2557237423000 TRACK D25572585028 0143 4 MS21250-05028 BOLT D25572585028 0144 2 MS21250-05022 BOLT D25572585028 0145 6 MS21042-5 NUT D25572585028 0146 6 D2557238721000 SPACER D25572585028 0147 12 D2557231520400 SPACER D25572585028 0148

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 109100-1 LATCH D25572585030 0100 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Kit 281145D51R00

Kit 281145D52R00

Kit 281145D61R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557295021300 PLACARD D25572585032 0001 1 D2557295021400 PLACARD D25572585032 0002 1 D2557295028000 PLACARD D25572585032 0005 1 D2557295028100 PLACARD D25572585032 0006 4 D2557295024000 STRIP D25572585032 0008 11 D2557295024300 STRIP D25572585032 0022

1 A2557146821200 PLACARD D25572585032 0024 2 D2557295122600 PLACARD D25572585032 0030 1 D2557295123600 PLACARD D25572585032 0034 1 D2557295123800 PLACARD D25572585032 0035 2 D2557295236800 PLACARD D25572585032 0036 2 A2557144422600 PLACARD D25572585032 0038 7 D2557295030600 FOIL D25572585032 0040 1 A2557332320000 PLACARD D25572585032 0041 1 A2557332420000 PLACARD D25572585032 0042

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 AC40-0209900 NET D25572585034 0005 1 AC40-0253615 NET D25572585034 0008 1 AC40-0253610 NET D25572585034 0009 1 HA70-0214005 STANCHIN D25572585034 0011 1 AC40-0253620 NET D25572585034 0012

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

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D62R00

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 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

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

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D63R00

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 281145D70R00

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 281145D72R00

Kit 281145D73R00 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

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

50 D9239310904800 PLACARD D92894713062 0000 100 NSA935401-03 TIE D92894713062 0080

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

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 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 PLCRDSET D92894736004 0050

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D74R00 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

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 LN9198-4010CF RIVET D25670762000 0100

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

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D75R00 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 5 MS21042-08 NUT D25671745000 0092 2 NAS1096-3-12 SCREW D25671745000 0103 30 NAS1149D0363K WASHER D25671745000 0110 13 NAS1149DN832K WASHER D25671745000 0112

1 64079-3 HOSE D25671745000 0595 1 64079-1 HOSE D25671745000 0596 2 64079-5 HOSE D25671745000 0597 2 D2567043200000 POCKET D25671746000 0050 2 ASNA0033-172 CLAMP D25671746000 0060 1 LN29837A1 SECTION D25671746000 0070 4 NAS1096-3-7 SCREW D25671746000 0080 4 NAS1149D0363K WASHER D25671746000 0090 1 D9239310903000 PLCRDSET D25671746000 0100 2 MS20392-2C15 PIN D25671746000 0110 6 NAS1149C0332R WASHER D25671746000 0120 2 MS24665-1013 PIN D25671746000 0130 1 D2567074100600 PLACARD D25671746000 0140 1 60592-103 RESERVOR D25671746000 0594 1 60592-103 RESERVOR D25671746000 0598

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

16 NAS1102-4-16 SCREW D25286364014 0002 16 NAS1149F0432P WASHER D25286364014 0004 16 NAS1169C416L WASHER D25286364014 0006 16 MS21042-4 NUT D25286364014 0008 16 NAS1102-08-16 SCREW D25286364014 0010 16 NAS1149FN816P WASHER D25286364014 0012 16 NAS1169C8L WASHER D25286364014 0014 16 MS21042-08 NUT D25286364014 0016

1 FACC79120418 CMPRTMNT D25286364014 0020 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D76R00 1 FACC79120419 CMPRTMNT D25286364014 0021 4 MS20392-3C23 PIN D25286364014 0030 2 MS20392-3C27 PIN D25286364014 0031 6 NAS1149F0463P WASHER D25286364014 0032 6 AA55487-5 PIN D25286364014 0033 4 MS20392-4C67 PIN D25286364014 0042 2 MS20392-4C45 PIN D25286364014 0043 4 NAS1149C0532R WASHER D25286364014 0046 6 DAN191-20 RING D25286364014 0047 2 NSA5528-045 CLAMP D25286364014 0065

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 L32A319-160-002 CONTROL D53370297002 0000 1 L32A319-165-002 ADAPTER D53370297002 0002 2 D5337025020000 ANGLE D53370297002 0006 2 D5337025620200 SECTION D53370297002 0008 1 D5337025620600 SECTION D53370297002 0010 1 D5337025920000 ANGLE D53370297002 0012 1 D5337645020000 BRIDGE D53370297002 0014 1 D5337645300200 BRACKET D53370297002 0016 1 D5337645420000 BRACKET D53370297002 0018 10 MS21919WCH6 CLAMP D53370297002 0030 0.06 ME DAN79-07 HOSE D53370297002 0032 2 NSA935401-03 TIE D53370297002 0034 1 MS20392-2C19 PIN D53370297002 0036 7 NSA5031-3-5 BOLT D53370297002 0040 3 NSA5031-3-4 BOLT D53370297002 0042 1 NAS1726C4P NUT D53370297002 0060 1 NAS509-4C NUT D53370297002 0062 10 NAS1726C3P NUT D53370297002 0064 13 NAS1149C0332R WASHER D53370297002 0070

2 MS24665-153 PIN D53370297002 0080 32 LN9198-3212BF RIVET D53370297002 0632

2 DIN65399-3208BF RIVET D53370297002 0652 1 L32A319-160-002 CONTROL D53370297003 0000 1 L32A319-165-001 ADAPTER D53370297003 0004 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

78

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D80R00

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. 2 D5337025020100 ANGLE D53370297003 0007 2 D5337025620200 SECTION D53370297003 0008 1 D5337025620700 SECTION D53370297003 0011 1 D5337025920000 ANGLE D53370297003 0012 1 D5337645020100 BRIDGE D53370297003 0015 1 D5337645300300 BRACKET D53370297003 0017 1 D5337645420000 BRACKET D53370297003 0018 10 MS21919WCH6 CLAMP D53370297003 0030 0.06 ME DAN79-07 HOSE D53370297003 0032 2 NSA935401-03 TIE D53370297003 0034 1 MS20392-2C19 PIN D53370297003 0036 7 NSA5031-3-5 BOLT D53370297003 0040 3 NSA5031-3-4 BOLT D53370297003 0042 1 NAS1726C4P NUT D53370297003 0060 1 NAS509-4C NUT D53370297003 0062 10 NAS1726C3P NUT D53370297003 0064 13 NAS1149C0332R WASHER D53370297003 0070

2 MS24665-153 PIN D53370297003 0080 32 LN9198-3212BF RIVET D53370297003 0632

2 DIN65399-3208BF RIVET D53370297003 0652

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9259014000000 PANEL D92393242000 0000 4 NAS1096-3-8 SCREW D92393242000 0001 4 NAS1149CN616R WASHER D92393242000 0002 1 NSA931025-03C PLACARD D92393242000 0003 1 D9249226220200 BRACKET D92492261000 0001 1 D9249226200000 BRACKET D92492261000 0002 8 LN9198-4010CF RIVET D92492261000 0640 7 DIN65399-4010CF RIVET D92492261000 0740 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

79

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Kit 281145D82R01

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 281145D83R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 NSA855006-6 UNION D93070516000 0015 1 ASNA3752D120812 UNION D93070516000 0016 1 D2917090100400 TUBE D93070516000 0022 11 NSA5066-3-1 NUT D93070516000 0060

1 NSA935401-06 TIE D93070516000 0086 1 NSA935401-04 TIE D93070516000 0087 2 LN9198-3210BF RIVET D93070516000 0099 1 D2917091100200 TUBE D93070516000 0120 1 D2707023100000 TUBE D93070516000 0121 1 NSA855006D8 UNION D93070516000 0130 1 D2777000102600 TUBE D93070516000 0135 1 D2777001102400 TUBE D93070516000 0136 1 D2917091100400 TUBE D93070516000 0139 1 D9357045500000 BRACKET D93070516000 0145 1 NSA5586B BLOCK D93070516000 0150 1 NSA935401-05 TIE D93070516000 0151 2 NAS679C06M NUT D93070516000 0165 2 LN9198-3210CF RIVET D93070516000 0198

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 7 NAS1096-2-12 SCREW D92491681000 0007 1 NAS1096-2-14 SCREW D92491681000 0009 10 ASNA0113-40ADL WASHER D92491681000 0163

2 D9249102520000 WASHER D92491681000 0190 4 MS21042-08 NUT D92491681000 0202 4 NSA5066-08-1 NUT D92491681000 0230 1 NSA5527-03-04 SPACER D92491681000 0306 1 NSA5527-03-07 SPACER D92491681000 0312 2 A9249187820200 SHEET D92491681000 0565 2 A9249199820000 PLATE D92491681000 0632 2 D9249104720000 GUIDE D92491681000 0724 1 D9249102620600 DEFLECTR D92491681000 0730 6 D9249104920400 BRACKET D92491681000 0737 1 D9249107302800 CONNECTN D92491681000 0824

80

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D84R00 2 D9249171020200 SECTION D92491681002 0012 2 NAS1096-2-7 SCREW D92491681002 0022 2 NAS1801-08-7 SCREW D92491681002 0031 2 MS21042-08 NUT D92491681002 0041 36 A9249635720200 BRACKET D92491681008 0001 17 D9249179320000 BRACKET D92491681008 0002

1 A9249175120000 ANGLE D92491681008 0003 6 D9249178000600 BRACKET D92491681008 0007 1 D9249177124400 BRACKET D92491681008 0009 5 D9249177520000 ANGLE D92491681008 0013 4 D9249172321200 BRACKET D92491681008 0016 1 D9249172722800 BRACKET D92491681008 0018 1 D9249177520200 ANGLE D92491681008 0019 1 D9249184620400 BRACKET D92491681008 0021 1 D9249177100000 BRACKET D92491681008 0023 1 D9249180922600 BRACKET D92491681008 0026 1 MS21060L3 NUT D92491681008 0027 1 D9249178001200 BRACKET D92491681008 0032 200 LN9198-3215BF RIVET D92491681008 0632

20 LN9198-4828CF RIVET D92491681008 0648 10 DIN65399-2412BF RIVET D92491681008 0724

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

18 NAS1801-3-8 SCREW D92491681006 0001 40 NAS1801-08-8 SCREW D92491681006 0003

1 NAS1801-08-19 SCREW D92491681006 0004 19 NAS1149D0332K WASHER D92491681006 0005 40 NAS1149DN816K WASHER D92491681006 0006 18 MS21042L3 NUT D92491681006 0009 16 MS21042L08 NUT D92491681006 0010

1 E0343-01 MOUNT D92491681006 0015 4 D9249177121200 BRACKET D92491681006 0016 1 NSA5527-03-06D SPACER D92491681006 0017 1 D9249177124200 BRACKET D92491681006 0018 1 D9249180800200 BRACKET D92491681006 0024 1 D9249180800400 BRACKET D92491681006 0025 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D85R03 1 D9249180900000 BRACKET D92491681006 0026 1 D9249180922400 BRACKET D92491681006 0027 6 D9249177920000 BRACKET D92491681006 0028 2 D9249177820200 BRACKET D92491681006 0030

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

20 NAS1801-08-6 SCREW D92891805000 0004 21 NAS1801-08-9 SCREW D92891805000 0005

4 NAS1801-08-12 SCREW D92891805000 0007 2 NAS1801-08-17 SCREW D92891805000 0010 2 NAS1801-08-19 SCREW D92891805000 0012 2 NAS1801-08-23 SCREW D92891805000 0014 1 NAS1801-08-39 SCREW D92891805000 0020 97 NAS1801-3-9 SCREW D92891805000 0030

8 NAS1100-04-5 SCREW D92891805000 0051 24 NAS1102-08-8 SCREW D92891805000 0058

8 NAS1149CN416R WASHER D92891805000 0150 34 NAS1149CN816R WASHER D92891805000 0152 108 NAS1149C0332R WASHER D92891805000 0153 3 ASNA0113-40ADL WASHER D92891805000 0163 16 NSA935808C01 WASHER D92891805000 0171

1 D9249102520000 WASHER D92891805000 0190 24 MS21042-04 NUT D92891805000 0200

3 MS21042-08 NUT D92891805000 0202 8 MS21042-3 NUT D92891805000 0203 32 NAS1291C3M NUT D92891805000 0218

1 NSA5110-08-1 NUT D92891805000 0225 6 NSA5066-08-1 NUT D92891805000 0230 36 NSA5067-08-1 NUT D92891805000 0236

5 E0343-01 MOUNT D92891805000 0250 10 NSA935504-01 MOUNT D92891805000 0251

1 NSA935504-02 MOUNT D92891805000 0252 3 NSA935513-01 MOUNT D92891805000 0256 6 NSA935513-05 MOUNT D92891805000 0257 1 NSA935513-07 MOUNT D92891805000 0259 6 ABS0355-01 BRACKET D92891805000 0262 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 10 ABS0355-02 BRACKET D92891805000 0263 10 NSA935514-03 WASHER D92891805000 0264

1 E0660-01 MOUNT D92891805000 0266 20 ABS0731A01 SUPPORT D92891805000 0267 11 ABS0774A01A BRACKET D92891805000 0268

2 NSA5527-03-03 SPACER D92891805000 0304 2 NSA5527-03-04 SPACER D92891805000 0306 4 NSA5527-03-08 SPACER D92891805000 0314 1 NSA5527-03-11 SPACER D92891805000 0320 1 MS21919WCH6 CLAMP D92891805000 0352 12 NSA935807-09 CLAMP D92891805000 0377

4 NSA935807-16 CLAMP D92891805000 0381 4 D9249104800000 SHEET D92891805000 0727 2 D9249104800400 SHEET D92891805000 0729 3 TSTMNR502-0 CONDUIT D92891805000 0763 30 NSA935510-02 BOBBIN D92891805000 0777 100 NSA935401-03 TIE D92891805000 0793 200 NSA935401-04 TIE D92891805000 0794 100 NSA935401-05 TIE D92891805000 0795 1 D9249107100600 STRAP D92891805000 0834 2 DAN328H25 TAPE D92891805000 0877 4 EN2997KE3C12 CAP D92891805000 0930 2 EN2997KE3C16 CAP D92891805000 0932 4 EN2997KE512 CONNECTR D92891805000 0933 2 EN2997KE516 CONNECTR D92891805000 0935 6 D2557016200200 COVER D92891805000 1099 4 D9249104900600 BRACKET D92891805000 1110 2 D9249107303000 CONNECTN D92891805000 0846 8 NAS1801-08-10 SCREW D92891805002 0006 5 NAS1801-08-19 SCREW D92891805002 0012 1 NAS1801-08-25 SCREW D92891805002 0016 1 NAS1096-3-8 SCREW D92891805002 0028 9 NSA935808C01 WASHER D92891805002 0151 12 NAS1149CN816R WASHER D92891805002 0152

1 NAS1149C0332R WASHER D92891805002 0153 1 MS21042L3 NUT D92891805002 0210 12 NSA5066-08-2 NUT D92891805002 0231

3 NSA5527-03-02 SPACER D92891805002 0302 11 NSA5527-03-04 SPACER D92891805002 0306

4 NSA5527-03-06 SPACER D92891805002 0310 11 MS21919WCH4 CLAMP D92891805002 0350

5 MS21919WCH2 CLAMP D92891805002 0364 6 NSA935807-06 CLAMP D92891805002 0376 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

83

# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 6 NSA935807-09 CLAMP D92891805002 0377 61 NAS1801-08-8 SCREW D92891805006 0001 127 NAS1801-08-19 SCREW D92891805006 0002

15 NAS1801-08-29 SCREW D92891805006 0003 47 NAS1801-3-8 SCREW D92891805006 0004 266 NSA5066-08-2 NUT D92891805006 0005 5 NSA5527-03-08 SPACER D92891805006 0006 63 MS21042L3 NUT D92891805006 0007 26 MS21042L04 NUT D92891805006 0008 196 NAS1149DN816K WASHER D92891805006 0009

48 NAS1149D0332K WASHER D92891805006 0010 28 NAS1149DN416K WASHER D92891805006 0011

3 NSA935510-02 BOBBIN D92891805006 0012 14 MS21919WCH5 CLAMP D92891805006 0013 11 NSA5527-03-02 SPACER D92891805006 0016

1 NSA935808-01 WASHER D92891805006 0017 10 ABS0731A01 SUPPORT D92891805006 0018 20 NAS1149C0332R WASHER D92891805006 0019 154 NSA5527-03-01 SPACER D92891805006 0020 5 NSA934710T11 FITTING D92891805006 0021 2 NSA934710T14 FITTING D92891805006 0022 1 E0660-01 MOUNT D92891805006 0023 26 NAS1100-04-8 SCREW D92891805006 0025 17 NSA935513-01 MOUNT D92891805006 0027

2 NSA935513-05 MOUNT D92891805006 0028 1 NSA935504-03 MOUNT D92891805006 0030 176 NSA935504-01 MOUNT D92891805006 0031 1 ASNA0032H052 CLAMP D92891805006 0033 5 NSA935513-07 MOUNT D92891805006 0034 41 NSA5527-03-03 SPACER D92891805006 0035 1000 NSA935401-04 TIE D92891805006 0036 17 MS21042L08 NUT D92891805006 0037

1 D9249181406400 GUIDE D92891805006 0038 1 D9249181406600 GUIDE D92891805006 0039 1 NAS1801-3-18 SCREW D92891805006 0040 8 NAS1801-08-14 SCREW D92891805006 0041 1 D9249181404800 GUIDE D92891805006 0042 1 NSA935808C01 WASHER D92891805006 0043 1 D9249181401800 GUIDE D92891805006 0047 4 EN3646A508 RECEPTCL D92891805006 0048 2 ABS0355-03 BRACKET D92891805006 0049 20 NSA5527-03-04 SPACER D92891805006 0052 16 NAS1801-08-10 SCREW D92891805006 0053 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281145D86R00 1 NAS1096-2-43 SCREW D92891805006 0055 2 NSA935504-02 MOUNT D92891805006 0056 1 NSA5527-03-06 SPACER D92891805006 0057 1 NAS1096-2-24 SCREW D92891805006 0058 1 NSA5527-03-06 SPACER D92891805006 0059 16 NAS1149D0363K WASHER D92891805006 0060

2 NSA5527-03-15 SPACER D92891805006 0061 1 EN3646A514 RECEPTCL D92891805006 0062 5 E0343-01 MOUNT D92891805006 0063 12 NAS1096-3-10 SCREW D92891805006 0064

3 EN3646A510 RECEPTCL D92891805006 0065 3 EN3646A516 RECEPTCL D92891805006 0066 2 EN3646A3C10 CAP D92891805006 0067 1 EN3646A520 RECEPTCL D92891805006 0068 1 EN3646A522 RECEPTCL D92891805006 0069 200 NSA5539S SLEEVE D92891805006 0070 1 NAS1801-3-44 SCREW D92891805006 0072 200 NSA935401-03 TIE D92891805006 0073 1 NSA5527-03-03 SPACER D92891805006 0075 1 NAS1801-3-28 SCREW D92891805006 0076 1 A9249429720200 BRACKET D92891805006 0078 1 A9249429620400 SEALING D92891805006 0079 0.1 ME NSA939510BN STRIP D92891805006 0080 1 A9249436120000 BRACKET D92891805006 0083 1 NAS1801-3-13 SCREW D92891805006 0084 23 D9249102520000 WASHER D92891805006 0190

1 D9289180520000 PLACARD D92891805006 0200 1 D9289182100800 PLACARD D92891805006 1 D9289182100900 PLACARD D92891805006

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9299140500100 HARNESS D92997043000 0002 1 D9299702600100 EQUIPMNT D92997043000 0004 1 D9299702600200 EQUIPMNT D92997043000 0006 1 D9299142801400 HARNESS D92997043000 0008 1 D9299702800200 EQUIPMNT D92997043000 0010 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved D. LIST OF MATERIALS — OPERATOR SUPPLIED (1) Consumable Materials 1 D9299702800400 EQUIPMNT D92997043000 0012 1 D9299702800600 EQUIPMNT D92997043000 0014 1 D9299702800800 EQUIPMNT D92997043000 0016 1 D9299145600500 HARNESS D92997043000 0020 1 D9299146102200 HARNESS D92997043000 0022 1 D9299146201100 HARNESS D92997043000 0024 1 D9299146300400 HARNESS D92997043000 0026 1 D9299146400300 HARNESS D92997043000 0028 1 D9299147000800 HARNESS D92997043000 0030 1 D9299147100600 HARNESS D92997043000 0032 1 D9299147201600 HARNESS D92997043000 0034 1 D9299147300400 HARNESS D92997043000 0036 1 D9299147500700 HARNESS D92997043000 0038 1 D9299148001500 HARNESS D92997043000 0040 1 D9299148100400 HARNESS D92997043000 0042 1 D9299148300800 HARNESS D92997043000 0044 1 D9299149200600 HARNESS D92997043000 0046 1 D9299149300400 HARNESS D92997043000 0048 1 D9299149400400 HARNESS D92997043000 0050 1 D9299704300100 EQUIPMNT D92997043000 0054 1 D9299704300200 EQUIPMNT D92997043000 0056 1 D9299704300300 EQUIPMNT D92997043000 0058 1 D9299704300400 EQUIPMNT D92997043000 0060 1 D9299704300500 EQUIPMNT D92997043000 0062 1 D9299704300600 EQUIPMNT D92997043000 0064 1 D9299704300700 EQUIPMNT D92997043000 0066 1 D9299141900600 HARNESS D92997043000 0072 1 D9299142000600 HARNESS D92997043000 0074

DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C INST DISP
Synth. Ester Based Grease High Pressure 04-004 As required Pure Mineral Vaseline 04-012 As required Putty, Zinc Chromate General Purpose 05-002 As required Conductive Film 05-099 As required Electrical Bonding Coating (Blue Color) 07-001 As required Sealant High Temperature 08-007B As required

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

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (2) Components None Transparent Protective Coating 07-023 As required Two Component Epoxy Adhesive 08-010 As required Sealant, Anaerobic 08-013 As required Two Component Polyurethane Adhesive 08-025 As required Adhesive 08-048 As required Epoxy Resin 08-051 As required Fuel Tank Sealant Polysulfide 09-001 As required Fuel Tank Sealant Polysulfide 09-002 As required Corrosion Inhibitive Interfay Sealant 09-005 As required Corrosion Inhibiting Brush Consistency 09-013 As required Corrosion Inhibiting Fillet Consistency 09-016 As required Protective Coating For Fuel Vapor 09-032 As required Dry Cleaning Solvent 11-002 As required Solvent General Purpose 11-026 As required Corrosion Preventive Temporary Protective Compound 15-005 As required

Corrosion Preventive Temporary Protective Compound 15-008 As required

Anti-Corrosion Primer (Polyurethane) 16-001 As required Polyurethane Top Coat Grey 16-002 As required Fuel Tank Coating 16-015 As required External Top Coat (Polyurethane) 16-018 As required Lockwire 0.5 mm 19-009 As required Lockwire 0.6 mm 19-018 As required Lockwire LN9424A100 None As required DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C INST DISP

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved E. PARTS TO BE RE—IDENTIFIED BY THE OPERATOR

NOTE (01) Passenger Compartment NOTE (02) AFT Cargo Compartment NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. F. TOOLING — PRICE AND AVAILABILITY None G. SPECIAL TOOLS None ITEM NEW PART No. KEYWORD ITEM OLD PART No. INT D2587011905200 BLANKET D2587011903200 03 (01) D2587012105200 BLANKET D2587012103200 03 (01) D2587012305200 BLANKET D2587012303200 03 (01) D2587041405000 BLANKET D2587041403000 03 (01) D2587041605000 BLANKET D2587041603000 03 (01) D2587041705000 BLANKET D2587041703000 03 (01) D2587041905000 BLANKET D2587041903000 03 (01) D2587042005200 BLANKET D2587042003000 03 (01) D2587042105200 BLANKET D2587042103000 03 (01) D2587042305000 BLANKET D2587042303000 03 (01) D2587051405000 BLANKET D2587051402400 03 (01) D2587051605000 BLANKET D2587051602200 03 (01) D2587051705000 BLANKET D2587051702200 03 (01) D2587051905000 BLANKET D2587051902200 03 (01) D2587052005200 BLANKET D2587052002200 03 (01) D2587052105200 BLANKET D2587052102200 03 (01) D2587052305000 BLANKET D2587052302200 03 (01) D2587060105200 BLANKET D2587060102000 03 (02) D2587060305200 BLANKET D2587060302200 03 (02) D2587065605000 BLANKET D2587065602000 03 (02) D2587070105200 BLANKET D2587070102000 03 (02) D2587070305200 BLANKET D2587070302000 03 (02) D2587071005400 BLANKET D2587071002000 03 (02) D2587075205000 BLANKET D2587075202200 03 (02)

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE 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 RELATED DOORS — COMPONENTS THAT MOVE. 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. (1) Preparation (a) Config. 01 1 Lift the aircraft on jacks, (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 Put the access platform(s) in position. 4 Open the avionics door 822, (Refer to AMM 52-41-00 Page block 201). 5 Open the FWD and AFT cargo compartment doors, (Refer to AMM 52-30-00 Page block 201).

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Make sure that the applicable safety equipment is installed on the FWD and AFT cargo compartment doors. 6 Open the MLG doors, (Refer to AMM 32-12-00 Page block 201). NOTE : Make sure that the applicable safety equipment is installed on the MLG doors. 7 Depressurize the Green, Blue and Yellow hydraulic systems, (Refer to AMM 29-10-00 Page block 201). 8 Depressurize the reservoirs of the Green, Blue and Yellow hydraulic systems, (Refer to AMM 29-14-00 Page block 201). 9 Put warning notices in position to tell persons not to pressurize the hydraulic systems. 10 Remove the Green hydraulic reservoir, (Refer to AMM 29-11-41 Page block 401). 11 If necessary, remove the MLG torque tube assembly, (Refer to AMM 32-33-17 Page block 401). NOTE : It may be necessary to remove the MLG torque tube assembly to get access for the replacement of fasteners in the ceiling of the MLG bay between FR42 and FR43. 12 In the passenger compartment, remove as necessary : — the passenger seats, (Refer to AMM 25-21-41 Page block 401). — the textile floor-covering, (Refer to AMM 25-28-41 Page block 401). — the floor panels, (Refer to AMM 53-32-12 Page block 401 and AMM 53-42-12 Page block 401). — the ceiling panels, (Refer to AMM 25-23-41 Page block 401) — the cove light panels, (Refer to AMM 25-23-48 Page block 401) — the upper sidewall panels, (Refer to AMM 25-23-43 Page block 401) — the lower sidewall (dado) panels, (Refer to AMM 25-23-44 Page block 401) — the overhead stowage compartments, (Refer to AMM 25-24-41 Page block 401)

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved — the insulation blankets, (Refer to AMM 25-80-00 Page block 201). 13 In the FWD cargo compartment, remove as necessary : — the floor panels, (Refer to AMM 53-22-14 Page block 401) — the sidewall panels, (Refer to AMM 25-54-12 Page block 401) — the ceiling panels, (Refer to AMM 25-54-12 Page block 401) 14 In the AFT cargo compartment, remove as necessary : — the ceiling panels, (Refer to AMM 25-55-11 Page block 401) — the sidewall panels, (Refer to AMM 25-55-11 Page block 401) — the floor panels, (Refer to AMM 53-42-14 Page block 401). 15 Remove the belly fairing panels 147FB, 148FB, 197AB, 197BB, 197GB, 198BB and 198GB, (Refer to AMM 53-35-13 Page block 401). NOTE : The belly fairing panels 197AB and 198GB are replaced in the modification. 16 In the cockpit, remove the lining panels 211HC, 212FC, 212KC, 212KW, 212JW and 212HW, (Refer to AMM 06-41-53 Page block 001 and AMM 25-13-41 Page block 401). 17 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 001). 18 Defuel the center tank, (Refer to AMM 28-25-00 Page block 301). 19 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 that the ventilation of the center tank is correct. 20 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). 21 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).

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 22 Remove the cover 148AZ, (Refer to AMM 57-17-11 Page block 401). 23 Remove the outlet PN D2821302620000, (Refer to IPC 28-12-05). 24 Make sure that the external connector(s) is (are) not connected to the aircraft receptacle(s) EXT PW. 25 Make sure that there is (are) warning notice(s) on the external power receptacle to tell persons not to connect an external power source. 26 Make sure that the EMER EXIT LT pushbutton switch on the 25VU is set to OFF. 27 In the cockpit, on the ELEC Panel 35VU, release the BAT pushbutton switches. 28 Put a warning notice in position on the ELEC Panel 35VU to tell persons not to operate the batteries. 29 Put a warning notice in position on the Refuel/Defuel Panel 800VU to tell persons not to operate the NORMAL BATTERY switch. 30 Put a warning notice in position in the cockpit to tell persons not to start the APU. 31 Put a warning notice in position in the cockpit to tell persons not to operate the fuel system. 32 Put a warning notice in position in the cockpit to tell persons not to start the ENG1, 2. 33 Disconnect 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). b Turn the knurled nut a quarter turn. c Disconnect the connectors. d Put blanking caps on the disconnected electrical connectors. 34 To route the wires into the Overhead Panel 20VU, remove VUs and items of equipment as necessary, but do not disconnect them. NOTE : Disconnection of the connectors in the Overhead Panel 20VU will include a high increase in manhours for the test.

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (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 design drawings which you do not know, refer to the cross reference list in the Process and Material Specification (PMS) (c) Refer to the Consumable Material List (CML) for the specification of the materials (Mat. No.) you must use in this Service Bulletin. (d) For definitions of interchangeability codes in column INT. refer to the ATA Common Support Data Dictionary (CSDD) Chapter 2 . (e) For the identification of access panels, (Refer to AMM 06-41-53 Page block 001). (f) For the frame (FR) identification, (Refer to AMM 06-31-53 Page block 001). (g) Remove the old sealant with a plastic spatula and clean the surface with Solvent General Purpose (Mat No. 11-026) . (h) For the cleaning of the stripping area, use Solvent General Purpose (Mat No. 11-026) . (i) Remove and install the fasteners, (Refer to SRM 51-42-11). (j) Torque the standard threaded fasteners, (Refer to AMM 20-21-11 Page block 201). (k) Wet install fasteners with Corrosion Inhibiting Brush Consistency (Mat No. 09-013) . (l) Drill and deburr the holes, (Refer to SRM 51-44-11). (m) Countersink the holes, (Refer to SRM 51-46-00). (n) Cut the rivets to the necessary length. (o) Clean the surfaces at the location of the placards with Dry Cleaning Solvent (Mat No. 11-002) . (p) Bond the placards, (Refer to AMM 11-00-00 Page block 201). (q) Do the sealing and the protection in the center tank, (Refer to SRM 51-76-12).

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (r) Torque the standard threaded fasteners, (Refer to AMM 20-21-11 Page block 201). (s) Torque the pipe unions, (Refer to AMM 20-21-12 Page block 201). (t) The cargo floor panels have a protective foil to cover the anti-slip surface. Remove the protection foil before panel installation on aircraft. Make sure that the protection foil is fully removed. (u) Torque the fasteners of the electrical components, (Refer to AMM 20-21-15 Page block 201). (v) Do the electrical bonding (Refer to AMM 20-28-00 Page block 201) with Pure Mineral Vaseline (Mat No. 04-012) and Electrical Bonding Coating (Blue Color) (Mat No. 07-001) . (w) Put blanking caps on the disconnected electrical connectors. (x) Obey the instructions for the general wiring installation, (Refer to ESPM 20-33-00). (y) To install new wires, cut them to the necessary length, crimp the terminals and connect them. (z) Route the new wires with the wires that are in the aircraft. (aa) Do a continuity test of the new and of the modified wires, (Refer to ESPM 20-52-21). (ab) For the cable tie application and tooling, (Refer to ESPM 20-25-51 and ESPM 20-33-44). (ac) Install the grounding modules, (Refer to ESPM 20-44-71). (ad) Install the connectors, (Refer to ESPM 20-44-22 and ESPM 20-44-24). (ae) 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 0.5 mm (Mat No. 19-009) , where locking facilities exists.

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved B. MODIFICATION NOTE : The order of the worksteps are in the sequence on the top drawing and are not a sequence of worksteps. The sequence can be changed by the operator as required. NOTE : To accomplish this Service Bulletin, refer to Top Drawing, Issue C, Sheet 2 D00071141002 . (1) Config. 01

NOTE : Remove the finch paint and the paint protection from the extrado panels between Y=+254 and Y=-254 and between FR36 and FR42 and in the center tank. Do not use a metallic tool. Do not cause damage to the head of the rivets, (Refer to SRM 51-75-11, paragraph 3). Stop the removal when you can see the primary protection (green color). Only remove the rivets at the location of the doubler. (a) Install the doublers on the extrados, in the center tank Refer to Kit 281145A01R01

NOTE : Use a loft to drill the extrado panels :

NOTE : Use Fuel Tank Sealant Polysulfid (Mat No. 09-002) . (b) Install the brackets on the extrados, in the center tank Refer to Kit 281145A01R01

NOTE : Use Fuel Tank Sealant Polysulfid (Mat No. 09-002) , Anti-Corrosion Primer (Mat No. 16-001) , Corrosion Inhibiting Brush Consistency (Mat No. 09-013) and 281145A00001 Sheet(s) 01 A00 281145A00001 Sheet(s) 02 A00 281145A00001 Sheet(s) 03 B00

281145A01001 Sheet(s) 01 A00 281145A01001 Sheet(s) 02 A00 281145A01001 Sheet(s) 03 A00 281145A01002 Sheet(s) 01 A00

1 Loft D5713032000095

281145A01003 Sheet(s) 01 A00 281145A01003 Sheet(s) 02 A00 281145A01003 Sheet(s) 03 A00 281145A01003 Sheet(s) 04 A00 281145A01004 Sheet(s) 01 A00 281145A01004 Sheet(s) 02 A00 281145A01004 Sheet(s) 03 A00 281145A01005 Sheet(s) 01 A00

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Corrosion Preventive temporary Protective compound (Mat No. 15-008) . (c) Install the bracket on the rear spar assy, in the center tank Refer to Kit 281145A02R02

NOTE : Use Anti-Corrosion Primer (Mat No. 16-001) . (d) Install the brackets on the intrados, in the center tank Refer to Kit 281145A02R02

NOTE : Use Fuel Tank Sealant Polysulfid (Mat No. 09-002) , Corrosion Preventive temporary Protective compound (Mat No. 15-008) and Anti-Corrosion Primer (Mat No. 16-001)

. (e) Install the Additional Center Tank (ACT) door assy on the center tank Refer to Kit 281145A03R00 and Kit 281145A13R00

1 Remove :

2 Install : 281145A02001 Sheet(s) 01 A00

281145A02002 Sheet(s) 01 A00 281145A02002 Sheet(s) 02 A00 281145A02002 Sheet(s) 03 A00 281145A02003 Sheet(s) 01 A00 281145A02003 Sheet(s) 02 A00

281145A03000 Sheet(s) 01 A00 281145A03001 Sheet(s) 01 A00 281145A03002 Sheet(s) 01 A00 281145A03002 Sheet(s) 02 A00 281145A03003 Sheet(s) 01 B00 281145A03004 Sheet(s) 01 A00 281145A03005 Sheet(s) 01 A00 281145A03006 Sheet(s) 01 A00 281145A03007 Sheet(s) 01 A00 281145A13001 Sheet(s) 01 A00

281145A03000 Sheet(s) 01 A00 281145A03001 Sheet(s) 01 A00

281145A03002 Sheet(s) 01 A00 281145A03002 Sheet(s) 02 A00 281145A03003 Sheet(s) 01 B00 281145A03004 Sheet(s) 01 A00 281145A03005 Sheet(s) 01 A00

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Use Zinc Chromate General Purpose (Mat No. 05-002) , Anti-Corrosion Primer (Mat No. 16-001) and Grease High Pressure (Mat No. 04-004) . (f) Replace the Fuel Quantity Indicator (FQI) 6QT (Refer to AMM 28-42-22 Page block 401) 1 Remove :

2 Install :

(g) Modify the transfer line in the center tank Refer to Kit 281145A04R02

1 Remove : 281145A03006 Sheet(s) 01 A00 281145A03007 Sheet(s) 01 A00 281145A13001 Sheet(s) 01 A00

1 Fuel Quantity Indicator 1407KID02-03

1 Fuel Quantity Indicator 1418KID01-03

281145A04000 Sheet(s) 01 A00 281145A04001 Sheet(s) 01 A00 281145A04001 Sheet(s) 02 A00 281145A04001 Sheet(s) 03 A00 281145A04002 Sheet(s) 01 A00 281145A04002 Sheet(s) 02 A00 281145A04002 Sheet(s) 03 A00 281145A04002 Sheet(s) 04 A00 281145A04003 Sheet(s) 01 A00 281145A04003 Sheet(s) 02 A00 281145A04003 Sheet(s) 03 A00 281145A04003 Sheet(s) 04 A00 281145A04003 Sheet(s) 05 A00 281145A04004 Sheet(s) 01 A00 281145A04005 Sheet(s) 01 A00 281145A04006 Sheet(s) 01 A00 281145A04007 Sheet(s) 01 A00 281145A04008 Sheet(s) 01 A00 281145A04009 Sheet(s) 01 A00 281145A04010 Sheet(s) 01 A00 281145A04011 Sheet(s) 01 A00 281145A04011 Sheet(s) 02 A00 281145A04012 Sheet(s) 01 A00 281145A04013 Sheet(s) 01 A00

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# @ A318/A319/A320/A321
SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 2 Install :

NOTE : Use Anti-Corrosion Primer (Mat No. 16-001) and Fuel Tank Sealant Polysulfid (Mat No. 09-002) . (h) Install the transfer elbow and the air ventilation elbow on the center tank Refer to Kit 281145A05R00

NOTE : Use Anti-Corrosion Primer (Mat No. 16-001) , Protective Coating For Fuel Vapor (Mat No. 09-032) , Fuel Tank Sealant Polysulfid (Mat No. 09-002) , Fuel Tank Sealant Polysulfide (Mat No. 09-001) and Fuel Tank Coating (Mat No. 16-015) . (i) Apply the sealing protection to the center tank 281145A04000 Sheet(s) 01 A00 281145A04001 Sheet(s) 01 A00 281145A04001 Sheet(s) 02 A00 281145A04001 Sheet(s) 03 A00

281145A04002 Sheet(s) 01 A00 281145A04002 Sheet(s) 02 A00 281145A04002 Sheet(s) 03 A00 281145A04002 Sheet(s) 04 A00 281145A04003 Sheet(s) 01 A00 281145A04003 Sheet(s) 02 A00 281145A04003 Sheet(s) 03 A00 281145A04003 Sheet(s) 04 A00 281145A04003 Sheet(s) 05 A00 281145A04004 Sheet(s) 01 A00 281145A04005 Sheet(s) 01 A00 281145A04006 Sheet(s) 01 A00 281145A04007 Sheet(s) 01 A00 281145A04008 Sheet(s) 01 A00 281145A04009 Sheet(s) 01 A00 281145A04010 Sheet(s) 01 A00 281145A04011 Sheet(s) 01 A00 281145A04011 Sheet(s) 02 A00 281145A04012 Sheet(s) 01 A00 281145A04013 Sheet(s) 01 A00

281145A05001 Sheet(s) 01 A00 281145A05002 Sheet(s) 01 A00 281145A05003 Sheet(s) 01 A00 281145A05003 Sheet(s) 02 A00

281145A05003 Sheet(s) 01 A00 281145A05003 Sheet(s) 02 A00

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 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 Polysulfid (Mat No. 09-002) — Protective Coating For Fuel Vapor (Mat No. 09-032) — Anti-Corrosion Primer (Mat No. 16-001) — Fuel Tank Coating (Mat No. 16-015) . (j) Modify the equipment and the wiring in the HYD/Fuel Panel 40VU Refer to Kit 281145A06R02 , Kit 281145A07R00 , Kit 281145A08R00 and Kit 281145A10R01

1 Remove :

2 Install :

NOTE : Secure the screws with Sealant, High Temperature (Mat No. 08-573) or Sealant, High Temperature (Mat No. 08-007B) . NOTE : The placards are supplied in :

3 Modify the wires 281145A06000 Sheet(s) 01 A00 281145A06001 Sheet(s) 01 A00 281145A06002 Sheet(s) 01 A00 281145A06003 Sheet(s) 01 B00 281145A06004 Sheet(s) 01 A00

281145A06000 Sheet(s) 01 A00 281145A06001 Sheet(s) 01 A00 281145A06002 Sheet(s) 01 A00

281145A06001 Sheet(s) 01 A00 281145A06003 Sheet(s) 01 B00 281145A06004 Sheet(s) 01 A00

Placard Set D9100095114296

281145A10501 Sheet(s) 01 A00 281145A10501 Sheet(s) 03 A00 281145A10502 Sheet(s) 01 A00 281145A10502 Sheet(s) 02 A00 281145A10503 Sheet(s) 01 A00 281145A10503 Sheet(s) 03 A00

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved a Install the wires :

supplied in

NOTE : The bundle is supplied in Kit 281145A10R01 . b Attach the wires with :

(k) Modify the equipment and the wiring in the Rear C/B Panel 121VU and the Rear Panel 120VU Refer to Kit 281145A06R02 , Kit 281145A09R00 and Kit 281145A10R01 1 Install :

NOTE : The placards are supplied in :

2 Modify the wiring in the Rear Circuit Breaker Panel 121VU 281145A10501 Sheet(s) 03 A00 281145A10502 Sheet(s) 02 A00 281145A10503 Sheet(s) 03 A00

Bundle D9000095137495

150 Tie-Cable NSA935401-03 150 Tie-Cable NSA935401-06

281145A06005 Sheet(s) 01 A00

Placard Set D9100095114295

281145A06501 Sheet(s) 01 A00 281145A06501 Sheet(s) 02 A00 281145A06502 Sheet(s) 01 A00 281145A06502 Sheet(s) 02 A00 281145A06503 Sheet(s) 01 A00 281145A06503 Sheet(s) 02 A00 281145A06504 Sheet(s) 01 A00 281145A06504 Sheet(s) 02 A00 281145A06505 Sheet(s) 01 A00 281145A06505 Sheet(s) 02 A00 281145A06506 Sheet(s) 01 A00 281145A06506 Sheet(s) 02 A00 281145A06507 Sheet(s) 01 A00 281145A06507 Sheet(s) 02 A00 281145A06508 Sheet(s) 01 A00 281145A06508 Sheet(s) 02 A00 281145A06509 Sheet(s) 01 A00 281145A06509 Sheet(s) 02 A00 281145A06510 Sheet(s) 01 A00 281145A06510 Sheet(s) 02 A00

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved a Remove the wires :

b Install the wires :

supplied in :

Install : FIN 1114PP

between circuit breakers 9QH and 10QH FIN 1115PP

between circuit breakers 33QU and 34QU c Attach the wires with :

3 Modify the wiring in the Rear Panel 120VU 281145A06511 Sheet(s) 01 A00 281145A06511 Sheet(s) 02 A00

281145A06501 Sheet(s) 02 A00 281145A06503 Sheet(s) 02 A00 281145A06505 Sheet(s) 02 A00 281145A06507 Sheet(s) 02 A00 281145A06510 Sheet(s) 02 A00

281145A06502 Sheet(s) 02 A00 281145A06504 Sheet(s) 02 A00 281145A06506 Sheet(s) 02 A00 281145A06508 Sheet(s) 02 A00 281145A06509 Sheet(s) 02 A00 281145A06511 Sheet(s) 02 A00

Bundle D9000095128395

1 Shunt NSA939526-02

1 Shunt NSA939526-02

50 Tie-Cable NSA935401-03 60 Tie-Cable NSA935401-04 40 Tie-Cable NSA935401-05

281145A10501 Sheet(s) 01 A00 281145A10501 Sheet(s) 02 A00 281145A10503 Sheet(s) 01 A00 281145A10503 Sheet(s) 02 A00 281145A10504 Sheet(s) 01 A00 281145A10504 Sheet(s) 02 A00 281145A10505 Sheet(s) 01 A00

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved a Install the wires :

supplied in :

b Attach the wires with :

(l) Modify the routing in the avionics compartment Refer to Kit 281145A10R01

1 Remove :

2 Install : 281145A10505 Sheet(s) 02 A00 281145A10506 Sheet(s) 01 A00 281145A10506 Sheet(s) 02 A00 281145A10507 Sheet(s) 01 A00 281145A10507 Sheet(s) 02 A00

281145A10501 Sheet(s) 02 A00 281145A10503 Sheet(s) 02 A00 281145A10504 Sheet(s) 02 A00 281145A10505 Sheet(s) 02 A00 281145A10506 Sheet(s) 02 A00 281145A10507 Sheet(s) 02 A00

Bundle D9000095137395

50 Tie-Cable NSA935401-03 60 Tie-Cable NSA935401-04 20 Tie-Cable NSA935401-05

281145A10001 Sheet(s) 01 A00 281145A10001 Sheet(s) 02 A00 281145A10002 Sheet(s) 01 A00 281145A10002 Sheet(s) 02 A00 281145A10003 Sheet(s) 01 A00 281145A10004 Sheet(s) 01 A00 281145A10004 Sheet(s) 02 A00 281145A10005 Sheet(s) 01 A00 281145A10005 Sheet(s) 02 A00 281145A10006 Sheet(s) 01 A00 281145A10006 Sheet(s) 02 A00

281145A10001 Sheet(s) 01 A00 281145A10001 Sheet(s) 02 A00

281145A10002 Sheet(s) 01 A00 281145A10002 Sheet(s) 02 A00 281145A10003 Sheet(s) 01 A00 281145A10004 Sheet(s) 01 A00 281145A10004 Sheet(s) 02 A00

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : The placards are supplied in :

NOTE : Use Anti-Corrosion Primer (Mat No. 16-001) , Polyurethane Top Coat Grey (Mat No. 16-002) and Corrosion Inhibiting Fillet Consistency (Mat No. 09-016) . (m) Modify the equipment in the FWD cargo compartment Refer to Kit 281145A10R01 1 Install :

NOTE : The placards are supplied in :

(n) Modify the wiring in the avionics compartment and in the FWD cargo compartment Refer to Kit 281145A10R01 281145A10005 Sheet(s) 01 A00 281145A10005 Sheet(s) 02 A00 281145A10006 Sheet(s) 01 A00 281145A10006 Sheet(s) 02 A00

Placard Set D9100095116795

281145A10007 Sheet(s) 01 A00 281145A10007 Sheet(s) 02 A00

Placard Set D9100095116795

281145A10501 Sheet(s) 01 A00 281145A10501 Sheet(s) 07 B00 281145A10502 Sheet(s) 01 A00 281145A10502 Sheet(s) 07 B00 281145A10503 Sheet(s) 01 A00 281145A10503 Sheet(s) 05 B00 281145A10504 Sheet(s) 01 A00 281145A10504 Sheet(s) 05 B00 281145A10505 Sheet(s) 01 A00 281145A10505 Sheet(s) 04 B00 281145A10506 Sheet(s) 01 A00 281145A10506 Sheet(s) 05 B00 281145A10507 Sheet(s) 01 A00 281145A10507 Sheet(s) 04 B00 281145A10508 Sheet(s) 01 B00 281145A10508 Sheet(s) 03 B00 281145A10509 Sheet(s) 01 A00 281145A10509 Sheet(s) 03 B00 281145A10510 Sheet(s) 01 A00 281145A10510 Sheet(s) 03 B00

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 1 Install the wires :

supplied in :

(o) Modify the wiring between the avionics compartment and the cockpit Refer to Kit 281145A10R01

1 Install the wires :

supplied in : 281145A10519 Sheet(s) 01 A00 281145A10519 Sheet(s) 04 B00

281145A10501 Sheet(s) 07 B00 281145A10502 Sheet(s) 07 B00 281145A10503 Sheet(s) 05 B00 281145A10504 Sheet(s) 05 B00 281145A10505 Sheet(s) 04 B00 281145A10506 Sheet(s) 05 B00 281145A10507 Sheet(s) 04 B00 281145A10508 Sheet(s) 03 B00 281145A10509 Sheet(s) 03 B00 281145A10510 Sheet(s) 03 B00 281145A10519 Sheet(s) 04 B00

Bundle D9000095137996

281145A10501 Sheet(s) 01 A00 281145A10501 Sheet(s) 08 A00 281145A10502 Sheet(s) 01 A00 281145A10502 Sheet(s) 06 A00 281145A10503 Sheet(s) 01 A00 281145A10503 Sheet(s) 06 A00 281145A10504 Sheet(s) 01 A00 281145A10504 Sheet(s) 06 A00 281145A10505 Sheet(s) 01 A00 281145A10505 Sheet(s) 05 A00 281145A10506 Sheet(s) 01 A00 281145A10506 Sheet(s) 06 A00 281145A10507 Sheet(s) 01 A00 281145A10507 Sheet(s) 05 A00

281145A10501 Sheet(s) 08 A00 281145A10502 Sheet(s) 06 A00 281145A10503 Sheet(s) 06 A00 281145A10504 Sheet(s) 06 A00 281145A10505 Sheet(s) 05 A00 281145A10506 Sheet(s) 06 A00 281145A10507 Sheet(s) 05 A00

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (p) Modify the equipment and the wiring in the Relay Box 103VU Refer to Kit 281145A10R01 1 Install :

NOTE : The placards are supplied in :

2 Modify the wiring

a Install the wires :

supplied in :

b Attach the wires with :

(q) Modify the equipment and the wiring in the Contactor Box 107VU Refer to Kit 281145A10R01 1 Install :

NOTE : The placards are supplied in : Bundle D9000095138095

281145A10008 Sheet(s) 01 A00 281145A10008 Sheet(s) 02 A00 281145A10008 Sheet(s) 03 A00

Placard Set D9100095116795

281145A10502 Sheet(s) 01 A00 281145A10502 Sheet(s) 03 A00 281145A10506 Sheet(s) 01 A00 281145A10506 Sheet(s) 03 A00 281145A10519 Sheet(s) 01 A00 281145A10519 Sheet(s) 02 A00

281145A10502 Sheet(s) 03 A00 281145A10506 Sheet(s) 03 A00 281145A10519 Sheet(s) 02 A00

Bundle D9000095137695

60 Tie-Cable NSA935401-04 60 Tie-Cable NSA935401-05 120 Tie-Cable NSA935401-06 240 Tie-Cable NSA935401-08

281145A10009 Sheet(s) 01 A00 281145A10009 Sheet(s) 02 A00

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 2 Modify the wiring

a Install the wires :

supplied in :

b Attach the wires with :

(r) Modify the equipment and the wiring in the AFT Electronics Rack 80VU Refer to Kit 281145A10R01

1 Install :

2 Modify the wiring Placard Set D9100095116795

281145A10501 Sheet(s) 01 A00 281145A10501 Sheet(s) 04 A00 281145A10505 Sheet(s) 01 A00 281145A10505 Sheet(s) 03 A00

281145A10501 Sheet(s) 04 A00 281145A10505 Sheet(s) 03 A00

Bundle D9000095137595

60 Tie-Cable NSA935401-04 60 Tie-Cable NSA935401-05 120 Tie-Cable NSA935401-06 240 Tie-Cable NSA935401-08

281145A10010 Sheet(s) 01 A00

281145A10010 Sheet(s) 01 A00

281145A10501 Sheet(s) 01 A00 281145A10501 Sheet(s) 06 A00 281145A10502 Sheet(s) 01 A00 281145A10502 Sheet(s) 05 A00 281145A10504 Sheet(s) 01 A00 281145A10504 Sheet(s) 04 A00 281145A10510 Sheet(s) 01 A00 281145A10510 Sheet(s) 02 A00 281145A10511 Sheet(s) 01 A00 281145A10511 Sheet(s) 02 A00 281145A10512 Sheet(s) 01 A00 281145A10512 Sheet(s) 02 A00 281145A10513 Sheet(s) 01 A00 281145A10513 Sheet(s) 02 A00

106

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved a Remove the wires :

b Install the wires :

supplied in :

c Attach the wires with :

(s) Modify the equipment and the wiring in the FWD Electronics Rack 90VU Refer to Kit 281145A10R01 , Kit 281145A11R03 and Kit 281145A12R00 1 Remove the Shelf 92VU a From the Shelf 92VU, remove for access the computers 7QJ, 9QJ, 3QT and 24XG : (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) 281145A10514 Sheet(s) 01 A00 281145A10514 Sheet(s) 02 A00 281145A10515 Sheet(s) 01 A00 281145A10515 Sheet(s) 02 A00

281145A10511 Sheet(s) 02 A00 281145A10513 Sheet(s) 02 A00

281145A10501 Sheet(s) 06 A00 281145A10502 Sheet(s) 05 A00 281145A10504 Sheet(s) 04 A00 281145A10510 Sheet(s) 02 A00 281145A10512 Sheet(s) 02 A00 281145A10514 Sheet(s) 02 A00 281145A10515 Sheet(s) 02 A00

Bundle D9000095137895

60 Tie-Cable NSA935401-04 60 Tie-Cable NSA935401-05 120 Tie-Cable NSA935401-06 240 Tie-Cable NSA935401-08

1 FLSCU1 Retain 1 FLSCU2 Retain 1 FQIC Retain 1 GAPCU Retain

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 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)

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, 10HC and 10WQ : (Refer to AMM 21-43-34 Page block 401) (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 SEC3 Retain 1 LGCIU1 Retain 1 ZONE CONT Retain

1 LGCIU2 Retain 1 BSCU Retain 1 HEAT CONT Retain 1 SDCU Retain

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 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 On the Shelf 92VU a Remove :

b Install :

NOTE : The placards are supplied in :

5 On the Shelf 94VU a Install :

NOTE : The placards are supplied in :

6 Modify the wiring 281145A11000 Sheet(s) 01 B00 281145A11001 Sheet(s) 01 A00

281145A11002 Sheet(s) 01 B00 281145A11003 Sheet(s) 01 A00

Placard Set D9100095116895

281145A11004 Sheet(s) 01 A00 281145A11004 Sheet(s) 02 A00

Placard Set D9100095116895

281145A10501 Sheet(s) 01 A00 281145A10501 Sheet(s) 05 A00 281145A10502 Sheet(s) 01 A00 281145A10502 Sheet(s) 04 A00 281145A10503 Sheet(s) 01 A00 281145A10503 Sheet(s) 04 A00 281145A10504 Sheet(s) 01 A00 281145A10504 Sheet(s) 03 A00 281145A10506 Sheet(s) 01 A00 281145A10506 Sheet(s) 04 A00 281145A10507 Sheet(s) 01 A00 281145A10507 Sheet(s) 03 A00 281145A10508 Sheet(s) 01 B00 281145A10508 Sheet(s) 02 A00

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved a Remove the wires :

b Install the wires :

supplied in :

c Attach the wires with :

7 Install the Shelf 92VU a Install the Shelf 92VU on aircraft. 281145A10509 Sheet(s) 01 A00 281145A10509 Sheet(s) 02 A00 281145A10516 Sheet(s) 01 A00 281145A10516 Sheet(s) 02 A00 281145A10517 Sheet(s) 01 A00 281145A10517 Sheet(s) 02 A00 281145A10518 Sheet(s) 01 A00 281145A10518 Sheet(s) 02 A00 281145A10519 Sheet(s) 01 A00 281145A10519 Sheet(s) 03 A00 281145A10520 Sheet(s) 01 A00 281145A10520 Sheet(s) 02 A00 281145A10521 Sheet(s) 01 A00 281145A10521 Sheet(s) 02 A00 281145A10522 Sheet(s) 01 A00 281145A10522 Sheet(s) 02 A00

281145A10516 Sheet(s) 02 A00 281145A10518 Sheet(s) 02 A00 281145A10520 Sheet(s) 02 A00 281145A10521 Sheet(s) 02 A00

281145A10501 Sheet(s) 05 A00 281145A10502 Sheet(s) 04 A00 281145A10503 Sheet(s) 04 A00 281145A10504 Sheet(s) 03 A00 281145A10506 Sheet(s) 04 A00 281145A10507 Sheet(s) 03 A00 281145A10508 Sheet(s) 02 A00 281145A10509 Sheet(s) 02 A00 281145A10517 Sheet(s) 02 A00 281145A10519 Sheet(s) 03 A00 281145A10522 Sheet(s) 02 A00

Bundle D9000095137795

60 Tie-Cable NSA935401-04 60 Tie-Cable NSA935401-05 120 Tie-Cable NSA935401-06 240 Tie-Cable NSA935401-08

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 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 24XG : (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)

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)

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. 1 FLSCU1 1 FLSCU2 1 FQIC 1 GAPCU

1 SEC3 1 LGCIU1 1 ZONE CONT

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 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, 10HC and 10WQ : (Refer to AMM 21-43-34 Page block 401) (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)

NOTE : These computers were retained at removal. (2) Config. 01 , Kit 281145B01R00 Refer to drawings :

(a) Install the equipment for the ACT pressurization system between FR48 and FR54. 1 Install these items at the crossbeam at FR54 as shown in drawing D28270975, sheet 7 and Sections A7-A8 and C8-C8 :

(3) Config. 01 , Kit 281145B02R00 Refer to drawings :

(a) Install this item in the forward avionics compartment :

(4) Config. 01 , Kit 281145B02R00 , Kit 281145B03R00 and Kit 281145B04R00 1 LGCIU2 1 BSCU 1 HEAT CONT 1 SDCU

D28270975 Sheet(s) 7 thru 12

1 Filter QB0566 Item 41 1 Valve HTE490005 Item 42 1 Actuator HTE200002-1 Item 43 1 Valve HTE920007-001 Item 44 1 Clamp HTE8002 Item 45 1 Valve PAS148-133A Item 46 1 Valve HTE490005 Item 47

D92355000 Sheet(s) 1 D92556025 Sheet(s) 1 and 3

1 Relay box D9255602500400

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Refer to drawings :

(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 Install the wires shown on lines 1 thru 14 of the Hook-up Chart (Refer to Figure 1 Sheet 1 ). supplied in :

and route them with the wires that are in the aircraft. NOTE : The existing wire shown on line 3 can be reused if it is of sufficient length or it can be removed and the new wire installed. 2 Cut the wires to the necessary length, crimp the terminals and connect them. 3 Attach the wires with tie-wraps as necessary. 4 Do an intrinsically safe continuity test of the new wires. (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 General Purpose (Mat No. 11-026) . D92450032 Sheet(s) 6 and 7 D92450115 Sheet(s) 1 and 2 D92550025 Sheet(s) 1 D92550032 Sheet(s) 1 and 2

1 Bundle D92400000647

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 2 Use Fuel Tank Sealant Polysulfide (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 :

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).

6 Install the fuel quantity indicator unit 6QT (Refer to AMM 28-42-22 Page block 401). 7 Install the refuel panel assembly 801VU Refer to drawing D92550025 and install this item :

(5) Config. 01 Refer to Kit 281145D01R00 thru Kit 281145D86R00 (a) Remove the inflation reservoirs 7506MM and 7507MM, for the LH and RH offwing escape slides. (Refer to AMM 25-62-46 Page block 401). Refer to drawing(s) :

(b) In the AFT cargo compartment, remove the placards for the inflation reservoir access. (Refer to AMM 11-00-00 Page block 201). Refer to drawing(s) :

(c) Install the MOD/SB placards. Refer to Kit 281145D70R00

1 Panel Assy-Mounting D9245011500600

1 Panel Assy-Refuel, 800VU D9255003200400

1 Panel Assy-Refuel,801VU D9255002500200

D25690000004 Sheet(s) 7 - 9

D25573522000 Sheet(s) 1

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Refer to drawing(s) :

(d) In the passenger compartment between FR41 and FR47, install the harnesses 5339VB and 5340VB Refer to Kit 281145D73R00 Refer to drawing(s) :

(e) Between FR45 and FR48 (LH and RH), install the off-wing escape slide reservoirs and associated pressure tubes. Refer to Kit 281145D74R00 1 When you accomplish this workstep, remove, modify and install the insulation blankets after the bracket installation. For the re-identification of the insulation blankets, refer to paragraph 2.E. 2 Install the support brackets for the reservoirs and associated pressure tubes for the off-wing escape slide system. Refer to drawing(s) :

3 Install the pressure tubes between FR45 and FR48 (LH and RH). Refer to drawing(s) :

NOTE : This drawing contains the consumable material : — Putty, Zinc Chromate General Purpose (Mat No. 05-002) . 4 Install the inflation reservoirs 7784MM and 7788MM. Refer to drawing(s) :

NOTE : This drawing contains the consumable material : — Synth. Ester Based Grease High Pressure (Mat No. 04-004) . D92894713062 Sheet(s) 1

D92894736004 Sheet(s) 14 - 17 D92992293014 Sheet(s) 16 D92992293016 Sheet(s) 17

D25670762000 Sheet(s) 1 - 7

D25671745000 Sheet(s) 1 - 7

D25671746000 Sheet(s) 1 - 4

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (f) Replace the Overhead Stowage Compartments (OHSC) between FR43 and FR47 (LH and RH). Refer to Kit 281145D75R00 and Kit 281145D72R00 1 Replace the OHSCs (Refer to AMM 25-24-41 Page block 401). Refer to drawing(s) :

2 Install the placards on the doors of the OHSCs. Refer to drawing(s) :

(g) Relocate the release cables for the LH and RH off-wing escape slides. Refer to Kit 281145D76R00 . (Refer to AMM 25-62-43 Page block 401). 1 Relocate the flexible control assembly for the LH off-wing escape slide. Refer to drawing(s) :

NOTE : This drawing contains these consumable materials : — Lockwire LN9424A100 — Corrosion Inhibitive Interfay Sealant (Mat No. 09-005) — Synth. Ester Based Grease High Pressure (Mat No. 04-004) — Adhesive (Mat No. 08-048) — Conductive Film (Mat No. 05-099) 2 Relocate the flexible control assembly for the RH off-wing escape slide. Refer to drawing(s) :

NOTE : This drawing contains these consumable materials : D25286364014 Sheet(s) 7 and 8

D25288767000 Sheet(s) 1 and 2

D53370297002 Sheet(s) 1 - 7

D53370297003 Sheet(s) 1 - 7

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved — Lockwire LN9424A100 — Corrosion Inhibitive Interfay Sealant (Mat No. 09-005) — Synth. Ester Based Grease High Pressure (Mat No. 04-004) — Adhesive (Mat No. 08-048) — Conductive Film (Mat No. 05-099) (h) Do the structural modification for the ACT 1 and ACT 2 provisions in the center fuselage. Refer to Kit 281145D05R00 . Refer to drawing(s) :

NOTE : It is not necessary to modify and reuse Items 0206 and 0207. New components are supplied in the Kit 281145D05R00 . (i) Do the structural modification for the ACT 1 provisions in the AFT cargo compartment between FR48 and FR53. Refer to Kit 281145D40R01 . Refer to drawing(s) :

NOTE : For installation of the bracket, Item 102, alternate rivets ASNA0082B3 (quantity 12) can be used, refer to Sheet 16, Section B16-B16. (j) Do the structural modification for the ACT 2 provisions in the AFT cargo compartment between FR52 and FR54. Refer to Kit 281145D06R00 . Refer to drawing(s) :

(k) Install the angles on the webs of the keel beam, between FR42 and FR46 Refer to Kit 281145D07R00 Refer to drawing(s) : D53372362006 Sheet(s) 1, 4 - 9 and 12 - 14

D53470075004 Sheet(s) 1 - 4, 6 - 17

D53470076004 Sheet(s) 1 - 10

D53370780004 Sheet(s) 2

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (l) Replace the fasteners at FR48, FR49, FR50 and FR51, between STGR33 and STGR36 (LH). Refer to Kit 281145D41R00 Refer to drawing(s) :

(m) Replace the fasteners at FR52, FR53 and FR54, between STGR33 and STGR36 (LH). Refer to Kit 281145D08R00 Refer to drawing(s) :

(n) Replace the belly fairing panels 197AB and 198GB and do the modification to the attachment structure. Refer to Kit 281145D04R00 (Refer to AMM 53-35-13 Page block 401). Refer to drawing(s) :

(o) Do the modification to the passenger compartment floor structure between FR42 and FR46. Refer to Kit 281145D61R00 Refer to drawing(s) :

(p) Replace the fasteners between FR42 and FR44 (LH). Refer to Kit 281145D62R00 Refer to drawing(s) :

(q) Replace the fasteners between FR42 and FR44 (RH). Refer to Kit 281145D63R00 Refer to drawing(s) : D53470095002 Sheet(s) 1

D53470096002 Sheet(s) 1

D53475024000 Sheet(s) 1 - 6

D53371046000 Sheet(s) 1 - 5

D53371237000 Sheet(s) 1

D53371237001 Sheet(s) 1

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (r) In the AFT cargo compartment remove the ball mats, the ball strips, the power drive units, the cargo nets and the XZ latch 32. (Refer to AMM 25-52-22 Page block 401). (Refer to AMM 25-52-26 Page block 401). (Refer to AMM 25-52-34 Page block 401). (Refer to AMM 25-55-41 Page block 401). Refer to drawing(s) :

NOTE : Retain the power drive units, the XZ latch 32, the plugs, the spacers, the divider net and the door net. (s) Remove the roller tracks. (Refer to AMM 25-52-21 Page block 401). Refer to drawing(s) :

(t) Remove the servo mechanism and actuator. (Refer to AMM 25-52-51 Page block 401). Refer to drawing(s) :

NOTE : Retain the servo mechanism and actuator and associated components. Discard the attaching hardware. (u) Remove the entrance guides, the YZ latch assemblies and guide rail. (Refer to AMM 25-52-48 Page block 401). (Refer to AMM 25-52-44 Page block 401). Refer to drawing(s) :

(v) Install the roller tracks and YZ latch assemblies. Refer to Kit 281145D42R03 Refer to drawing(s) : D25572585000 Sheet(s) 1, 2, 7 and 23

D25572585002 Sheet(s) 3 - 5

D25572585004 Sheet(s) 6

D25572585006 Sheet(s) 8 - 10

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : This drawing contains this consumable material : — Corrosion Inhibiting Brush Consistency (Mat No. 09-013) . (w) Install the servo mechanism and actuator. Refer to Kit 281145D43R00 Refer to drawing(s) :

NOTE : This drawing contains this consumable material : — Synth. Ester Based Grease High Pressure (Mat No. 04-004) . (x) Install the shim plates on the floor framework between FR47 and FR59. Refer to Kit 281145D44R01 Refer to drawing(s) :

NOTE : The quantity of shims at each position is dependant on the results of the roller track levelling. Refer to paragraph 3.B.(5)(bo). (y) Apply corrosion preventative to the roller tracks. Refer to drawing(s) :

NOTE : Use Corrosion Preventive Temporary Protective Compound (Mat No. 15-005) . (z) Attach the cable harnesses to the structure between FR54 and FR54A. Refer to Kit 281145D48R00 Refer to drawing(s) :

(aa) Remove the Tie Down Points for the cargo nets at FR52A, FR53, FR56 and on the roller track at FR50, FR53, FR56 and FR59. D25572585012 Sheet(s) 13 - 22

D25572585014 Sheet(s) 24 and 25

D25572585016 Sheet(s) 26

D25572585018 Sheet(s) 27

D25572585026 Sheet(s) 28 and 29

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (Refer to AMM 25-54-41 Page block 401). Refer to drawing(s) :

(ab) Install the Tie Down Points for the cargo nets at FR52A, FR53, FR56 and on the roller track at FR50, FR53, FR56 and FR59. Refer to Kit 281145D46R00 Refer to drawing(s) :

(ac) Install the ball mats and ball strips between FR52A and FR56. Refer to Kit 281145D47R01 Refer to drawing(s) :

NOTE : This drawing contains the consumable material : — Corrosion Inhibiting Brush Consistency (Mat No. 09-013) . (ad) Install the X-latch, latch rail, guide rails and support rail between FR53 and FR58. Refer to Kit 281145D49R01 Refer to drawing(s) :

(ae) Install the cargo nets in the AFT cargo compartment. Refer to Kit 281145D52R00 Refer to drawing(s) :

(af) Remove the placards on the sidewall panels in the AFT cargo compartment. Refer to drawing(s) :

(ag) Install the placards on the sidewall panels in the AFT cargo compartment. D25572585020 Sheet(s) 30

D25572585022 Sheet(s) 31

D25572585024 Sheet(s) 32 and 33

D25572585028 Sheet(s) 34 and 35

D25572585034 Sheet(s) 36

D25572585036 Sheet(s) 37

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Refer to Kit 281145D51R00 (Refer to AMM 11-00-00 Page block 201). Refer to drawing(s) :

(ah) After the adjustment of the roller tracks remove and retain the XZ latches at FR50 and FR53. Refer to drawing(s) :

(ai) Install the XZ latch 32ACT in the center roller track at FR50 and FR53. Refer to Kit 281145D50R00 Refer to drawing(s) :

(aj) Do the modification to the attachment structure for the AFT cargo-compartment sidewall and partition panels. Refer to Kit 281145D36R00 Refer to drawing(s) :

NOTE : This drawing contains the consumable material : — Corrosion Inhibiting Fillet Consistency (Mat No. 09-016) . (ak) In the AFT cargo compartment replace the floor panels 151SF, 152SF, 151TF, 152TF, 151AG, 152AG, 151BG and 152BG. Refer to Kit 281145D33R00 (Refer to AMM 53-42-14 Page block 401). Refer to drawing(s) :

(al) Seal the gaps between the cargo compartment floor-panels 151SF, 152SF, 151TF, 152TF, 151AG, 152AG, 151BG and 152BG. Refer to Kit 281145D34R00 Refer to drawing(s) : D25572585032 Sheet(s) 38

D25572585038 Sheet(s) 39

D25572585030 Sheet(s) 40

D53975019000 Sheet(s) 1 - 6

D53675510000 Sheet(s) 1 - 3

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : This drawing contains the consumable material : — Corrosion Inhibiting Fillet Consistency (Mat No. 09-016) . (am) Replace the insulation blankets between FR46 and FR47. Refer to Kit 281145D10R00 (Refer to AMM 25-80-00 Page block 201). Refer to drawing(s) :

(an) In the AFT cargo compartment, replace the ceiling panels 151AC, 151BC and 151GC. Refer to Kit 281145D25R00 (Refer to AMM 25-55-11 Page block 401). Refer to drawing(s) :

(ao) In the AFT cargo compartment, replace the sidewall panels 151CW, 151EW and 151HW. Refer to Kit 281145D26R00 (Refer to AMM 25-55-11 Page block 401). Refer to drawing(s) :

(ap) In the AFT cargo compartment, replace the sidewall panels 152CW and 152DW. Refer to Kit 281145D27R00 (Refer to AMM 25-55-11 Page block 401). Refer to drawing(s) :

(aq) In the AFT cargo compartment at FR47, replace the partition panels 151BW, 151AW and 152BW. Refer to Kit 281145D28R00 D53675511000 Sheet(s) 1 - 3

D25870003048 Sheet(s) 20

D25571073000 Sheet(s) 1

D25571073002 Sheet(s) 2

D25571073004 Sheet(s) 3

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (Refer to AMM 25-55-11 Page block 401). Refer to drawing(s) :

(ar) In the passenger compartment, replace the floor panels 241JF, 251BF, 252BF, 252CF, 251GF, 251FF, 252GF and 252HF. Refer to Kit 281145D31R00 (Refer to AMM 53-32-12 Page block 401 and AMM 53-42-12 Page block 401). Refer to drawing(s) :

(as) Seal the gaps between the passenger compartment floor-panels 241JF, 251BF, 252BF, 252CF, 251GF, 251FF, 252GF and 252HF. Refer to Kit 281145D32R00 Refer to drawing(s) :

NOTE : This drawing contains the consumable material : — Corrosion Inhibiting Fillet Consistency (Mat No. 09-016) . (at) Install the fuel vent line between FR37 and FR47 and the fuel transfer line between FR41 and FR47. Refer to Kit 281145D13R01 Refer to drawing(s) :

NOTE : This drawing contains the consumable material : — Lockwire 0.6 mm (Mat No. 19-018) . (au) Install the shroud drain system between FR37 and FR48 Refer to Kit 281145D11R00 and Kit 281145D14R00 1 Install the support brackets on the Green hydraulic reservoir support. Refer to Kit 281145D11R00 Refer to drawing(s) : D25571073006 Sheet(s) 4

D53675015002 Sheet(s) 3 and 4

D53675016002 Sheet(s) 3 and 4

D28270972002 Sheet(s) 7 - 12

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DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 2 Install the shroud drain lines between FR37 and FR48 Refer to Kit 281145D48R00 Refer to drawing(s) :

NOTE : This drawing contains the consumable materials : — Corrosion Inhibiting Fillet Consistency (Mat No. 09-016) — Two Component Epoxy Adhesive (Mat No. 08-010) . (av) Install the ACT 1 cavity drain and monitoring system between FR46 and FR50. Refer to Kit 281145D15R00 Refer to drawing(s) :

NOTE : This drawing contains the consumable materials : — Corrosion Inhibiting Fillet Consistency (Mat No. 09-016) — Two Component Epoxy Adhesive (Mat No. 08-010) . NOTE : Do not tighten the cap, Item 0033 (installed between FR50 and FR51). This is removed when you install the ACT 2 cavity drain and monitoring system. (aw) Install the ACT 1 pressurization system between FR48 and FR54. Refer to Kit 281145D16R01 Refer to drawing(s) :

NOTE : The Items 0041 thru 0047 referenced on this drawing are supplied and installed with Kit 281145B01R00 , refer to paragraph 3.B.(2)(a). NOTE : Do not tighten the cap, Item 0094 (installed between FR51 and FR52). This is removed when you install the ACT 2 pressurization system. D93070668000 Sheet(s) 1 - 8

D28270973002 Sheet(s) 6 - 10

D28270974002 Sheet(s) 4 - 6

D28270975004 Sheet(s) 8, 10, 11, 13 - 15

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (ax) Install the brackets for the fuel drain/vent systems between FR46 and FR54 Refer to Kit 281145D17R00 Refer to drawing(s) :

(ay) Install the ACT 2 cavity drain and monitoring system between FR50 and FR53. Refer to Kit 281145D01R00 Refer to drawing(s) :

(az) Install the ACT 2 pressurization system between FR51 and FR53. Refer to Kit 281145D02R00 Refer to drawing(s) :

(ba) Install the support brackets for the pressurization and cavity drain systems between FR51 and FR53 Refer to Kit 281145D03R00 Refer to drawing(s) :

(bb) Install the beam between FR46 and FR47. Refer to Kit 281145D18R00 Refer to drawing(s) :

(bc) Install the switching panel 2028VU. Refer to Kit 281145D80R00 Refer to drawing(s) :

(bd) Install the cover between FR46 and FR47 at the fuel transfer and vent lines. D28270982004 Sheet(s) 12 - 14, 17, 19, 20, 24 - 26

D28270990002 Sheet(s) 2 and 4

D28270991000 Sheet(s) 1 - 3

D28270992000 Sheet(s) 1 - 4

D28270998002 Sheet(s) 2

D92393242000 Sheet(s) 1 D92492261000 Sheet(s) 1

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Refer to Kit 281145D19R00 Refer to drawing(s) :

(be) Replace the fuel drain line between FR42 and FR47. Refer to Kit 281145D20R00 Refer to drawing(s) :

(bf) Do the modification to the support brackets on floor structure in the passenger compartment, between FR41 and FR42 and between FR49 and FR55. Refer to Kit 281145D83R01 Refer to drawing(s) :

(bg) Replace the support bracket at FR42. Refer to Kit 281145D83R01 Refer to drawing(s) :

(bh) Do the modification to the support bracket installation in the AFT cargo compartment between FR47 and FR55 Refer to Kit 281145D84R00 Refer to drawing(s) :

(bi) Do the modification to the support bracket installation between FR46 and FR52 and FR54. Refer to Kit 281145D83R01 Refer to drawing(s) :

NOTE : This drawing contains the consumable material : — Corrosion Inhibiting Brush Consistency (Mat No. 09-013) . D28270999004 Sheet(s) 3

D28270515000 Sheet(s) 1 - 4

D92491681000 Sheet(s) 1 - 6

D92491681002 Sheet(s) 7 - 9

D92491681006 Sheet(s) 34 - 45

D92491681008 Sheet(s) 10, 12 - 24, 26, 27, 46 - 48

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (bj) Do the modification to the attachment parts for the cable harnesses at FR42 and in the AFT cargo compartment between FR49 and FR55. Refer to Kit 281145D85R03 Refer to drawing(s) :

NOTE : This drawing contains the consumable material : — Sealant, Anaerobic (Mat No. 08-013) . (bk) Do the modification to the attachment parts for the cable harnesses at FR42. Refer to Kit 281145D85R03 Refer to drawing(s) :

. For additional information concerning bonding points 6814VN DC2, 6989VN B1, 7309VN DC1, 7332VN B2 and 7334VN AC2 : Refer to drawing(s) :

(bl) Do the modification to the attachment parts for the cable harnesses between FR46 and FR55. Refer to Kit 281145D85R03 Refer to drawing(s) :

NOTE : This drawing contains the consumable materials : — Corrosion Inhibiting Fillet Consistency (Mat No. 09-016) — Adhesive (Mat No. 08-048) — Two Component Epoxy Adhesive (Mat No. 08-010) — Two Component Polyurethane Adhesive (Mat No. 08-025) — Transparent Protective Coating (Mat No. 07-023) D92891805000 Sheet(s) 1 - 15

D92891805002 Sheet(s) 16 - 19

D92891120000 Sheet(s) 9 and 33

D92891805006 Sheet(s) 20, 22 - 31, 39 - 43, 45 - 48, 50 - 52

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved — Epoxy Resin (Mat No. 08-051) — Electrical Bonding Coating (Blue Color) (Mat No. 07-001) . (bm) Install/modify the cable harnesses between FR33 and FR55. Refer to Kit 281145D86R00 1 Replace the cable harness 4605VB. Refer to drawing(s) :

2 Do the modification to the cable harness 4606VB. Refer to drawing(s) :

3 Do the modification to the cable harness 4607VB. Refer to drawing(s) :

4 Replace the cable harness 4628VB Refer to drawing(s) :

5 Do the modification to the cable harness 4640VB. Refer to drawing(s) :

6 Do the modification to the cable harness 4644VB. Refer to drawing(s) :

7 Do the modification to the cable harness 4648VB. Refer to drawing(s) :

8 Do the modification to the cable harness 4650VB. D92991405000 Sheet(s) 1 D92991405001 Sheet(s) 2

D92997026001 Sheet(s) 1 and 2

D92997026002 Sheet(s) 3 - 8

D92991428013 Sheet(s) 18, H013 D92991428014 Sheet(s) 19, H014

D92997028002 Sheet(s) 1 and 2

D92997028004 Sheet(s) 3 and 4

D92997028006 Sheet(s) 5 and 6

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Refer to drawing(s) :

9 Replace the cable harness 4656VB. Refer to drawing(s) :

10 Replace the cable harness 4661VB. Refer to drawing(s) :

11 Replace the cable harness 4662VB. Refer to drawing(s) :

12 Replace the cable harness 4663VB. Refer to drawing(s) :

13 Replace the cable harness 4664VB. Refer to drawing(s) :

14 Replace the cable harness 4670VB. Refer to drawing(s) :

15 Replace the cable harness 4671VB. Refer to drawing(s) : D92997028008 Sheet(s) 7 and 8

D92991456004 Sheet(s) 5, H004 D92991456005 Sheet(s) 4, H005

D92991461021 Sheet(s) 26, H021 D92991461022 Sheet(s) 27, H022

D92991462010 Sheet(s) 10, H010 D92991462011 Sheet(s) 11, H011

D92991463003 Sheet(s) 8, H003 D92991462011 Sheet(s) 10, H004

D92991464002 Sheet(s) 4, H002 D92991464003 Sheet(s) 5, H003

D92991470007 Sheet(s) 8, H007 D92991470008 Sheet(s) 9, H008

D92991471005 Sheet(s) 7, H005 D92991471006 Sheet(s) 8, H006

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : If necessary, to ease the installation, cut 7502VS on new harness and remake with NSA936809RG003 and NSA937201MR0500 . 16 Replace the cable harness 4672VB. Refer to drawing(s) :

17 Replace the cable harness 4673VB. Refer to drawing(s) :

18 Replace the cable harness 4675VB. Refer to drawing(s) :

19 Replace the cable harness 4680VB. Refer to drawing(s) :

20 Replace the cable harness 4681VB. Refer to drawing(s) :

21 Replace the cable harness 4683VB. Refer to drawing(s) :

22 Replace the cable harness 4692VB. Refer to drawing(s) :

23 Replace the cable harness 4693VB. D92991472014 Sheet(s) 15, H014 D92991472016 Sheet(s) 16, H016

D92991473003 Sheet(s) 4, H003 D92991473004 Sheet(s) 3, H004

D92991475006 Sheet(s) 7, H006 D92991475007 Sheet(s) 8, H007

D92991480014 Sheet(s) 15, H014 D92991480015 Sheet(s) 16, H015

D92991481003 Sheet(s) 4, H003 D92991481004 Sheet(s) 5, H004

D92991483007 Sheet(s) 6, H007 D92991483008 Sheet(s) 7, H008

D92991492005 Sheet(s) 6, H005 D92991492006 Sheet(s) 7, H006

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Refer to drawing(s) :

24 Replace the cable harness 4694VB. Refer to drawing(s) :

25 Install the cable harness 5609VB. Refer to drawing(s) :

26 Install the cable harness 5662VB. Refer to drawing(s) :

27 Install the cable harness 5633VB. Refer to drawing(s) :

28 Install the cable harness 5664VB. Refer to drawing(s) :

29 Install the cable harness 5670VB. Refer to drawing(s) :

30 Install the cable harness 5675VB. Refer to drawing(s) :

31 Install the cable harness 5660VB. Refer to drawing(s) : D92991493003 Sheet(s) 4, H003 D92991493004 Sheet(s) 3, H004

D92991494003 Sheet(s) 4, H003 D92991494004 Sheet(s) 3, H004

D92997043001 Sheet(s) 1 - 4

D92997043002 Sheet(s) 5 and 6

D92997043003 Sheet(s) 7 and 8

D92997043004 Sheet(s) 9 - 11

D92997043005 Sheet(s) 12 and 13

D92997043006 Sheet(s) 14 and 15

D92997043007 Sheet(s) 16 - 23

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 32 Replace the cable harness 4619VB. Refer to drawing(s) :

33 Replace the cable harness 4620VB. Refer to drawing(s) :

(bn) Do the modification to the routing of the hydraulic tubes between FR46 and FR51. Refer to Kit 281145D82R01 Refer to drawing(s) :

NOTE : This drawing contains the consumable material : — External Top Coat (Polyurethane) (Mat No. 16-018) . (bo) Do the levelling of the cargo roller tracks. Refer to drawing(s) :

C. TEST (1) Config. 01 (a) Job Set-up 1 Install the cover 148AZ, (Refer to AMM 57-17-11 Page block 401). 2 Install the Green hydraulic reservoir, (Refer to AMM 29-11-41 Page block 401). 3 If necessary, install the MLG torque tube assembly, (Refer to AMM 32-33-17 Page block 401). 4 On each connector that you disconnected, do a visual check to make sure that : (Refer to ESPM 20-52-10) — The label of the plug is the same as the label on the receptacle D92991419005 Sheet(s) 6, H005 D92991419006 Sheet(s) 5, H006

D92991420005 Sheet(s) 6, H005 D92991420006 Sheet(s) 5, H006

D93070516000 Sheet(s) 1 - 6

D25573525006 Sheet(s) 13 - 16

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved — The plug is correctly locked. 5 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). 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. 6 Remove all the warning notices. 7 Energize the aircraft electrical circuits, (Refer to AMM 24-41-00 Page block 201). (b) Preliminary tests NOTE : If the aircraft is operated in CAT3 conditions, you must also do the LAND CAT3 capability test, (Refer to AMM 22-97-00 Page block 501). 1 Do the operational test of the instrument and panel integral lighting, (Refer to AMM 33-13-00 Page block 501). 2 Do the operational test of the annunciator light test system in the cockpit, (Refer to AMM 33-14-00 Page block 501). 3 Do the operational test of the avionics equipment ventilation system, (Refer to AMM 21-26-00 Page block 501). 4 Do the operational test of the AFS, (Refer to AMM 22-96-00 Page block 501). 5 Do the operational test of the EIS, (Refer to AMM 31-60-00 Page block 501). 6 Do the operational test of the ECAM control panel, (Refer to AMM 31-50-00 Page block 501). 7 Do the ground scanning of the central warning system, (Refer to AMM 31-50-00 Page block 501). (c) Tests 1 Tests after the removal/installation of the items of equipment

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved a Do the BITE test of the landing gear, (Refer to AMM 32-69-00 Page block 501). b Do the operational test of the circuit breaker monitoring system, (Refer to AMM 31-30-00 Page block 501). c Do the test after the removal/installation of the System Data Acquisition Concentrator (SDAC) (1WV1, 1WV2), (Refer to AMM 31-55-34 Page block 401). d Do the test after the removal/installation of the Slat and Flap Control Computer (SFCC) (21CV, 22CV), (Refer to AMM 27-51-34 Page block 401). e Do the BITE test of the FLSCU, (Refer to AMM 28-46-00 Page block 501). 2 Test after the disconnection/connection of the connectors 13VC, 43VC, 112VC, 1990VC and 2206VC a Do the BITE test of the landing gear, (Refer to AMM 32-69-00 Page block 501). 3 Test after the disconnection/connection of the connectors 1918VC, 1972VC, 1973VC, 2450VC and 2451VC a Do the functional (BITE) test, (Refer to AMM 28-46-00 Page block 501). 4 Test after the disconnection/connection of the connectors 1970VC and 1916VC a Do the status report (BITE), (Refer to AMM 28-42-00 Page block 501). 5 Test after the disconnection/connection of the connector 2200VC a Do the BITE test of the BSCU, (Refer to AMM 32-46-00 Page block 501). 6 Test after the disconnection/connection of the connector 288VC a Do the operational test of the Elevator and Aileron Computers (ELACs), (Refer to AMM 27-93-00 Page block 501). 7 Test after the disconnection/connection of the connector 2453VC a Included in the preliminary tests.

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 8 Test after the disconnection/connection of the connectors 4065VC, 4066VC, 1975VC, 1274VC, 2212VC and 1982VC a No test. 9 Test after the disconnection/connection of the connector 1142VC a Do the operational test of the lavatory smoke detection system, (Refer to AMM 26-17-00 Page block 501). 10 Test after the disconnection/connection of the connectors 240VC, 281VC, 283VC and 1152VC a Do the operational test of the engine fire and overheat detection (loop/squib), (Refer to AMM 26-12-00 Page block 501). 11 Tests after the disconnection/connection of the connector 1945VC a Do the operational test of the cockpit and cabin temperature control with CFDS/MCDU, (Refer to AMM 21-63-00 Page block 501). b Do the BITE test of the landing gear, (Refer to AMM 32-69-00 Page block 501). 12 Test after the disconnection/connection of the connectors 1266VC and 2216VC a Do the operational test of the wing-tank fuel control, (Refer to AMM 28-21-00 Page block 501). 13 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. 14 Test after the disconnection/connection of the connector 1947VC a Do the operational test of the flow control and indicating system, (Refer to AMM 21-51-00 Page block 501). 15 Test after the disconnection/connection of the connectors 202VC, 206VC, 208VC, 210VC, 212VC, 214VC, 215VC, 216VC, 217VC, 218VC, 219VC, 220VC, 222VC, 224VC, 225VC, 226VC, 227VC, 228VC, 229VC, 230VC, 231VC, 232VC, 234VC, 235VC, 236VC, 237VC, 239VC, 276VC, 278VC, 280VC, 282VC, 286VC, 290VC, 292VC, 294VC and 296VC.

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved a Included in the test after the removal/installation of the Selves 92VU, 93VU and 94VU. 16 Test after the disconnection/connection of the connectors 204VC and 284VC a Included in the preliminary tests. 17 Tests after the disconnection/connection of the connector 221VC a Do the operational test of the APU fire and overheat detection system, (Refer to AMM 26-13-00 Page block 501). 18 Test after the disconnection/connection of the connector 223VC a Do the operational test of the Enhanced GPWS ground self test function, (Refer to AMM 34-48-00 Page block 501). 19 Tests after the removal/installation of the Shelves 92VU, 93VU and 94VU a Do the test after the removal/installation of the Fuel Quantity Indicating Computer (FQIC) (3QT), (Refer to AMM 28-42-34 Page block 401). b Do the test after the removal/installation of the Slat and Flap Control Computer (SFCC) (21CV, 22CV), (Refer to AMM 27-51-34 Page block 401). c Do the test after the removal/installation of the Fuel-Level Sensing Control-Unit (FLSCU) (7QJ, 9QJ), (Refer to AMM 28-46-34 Page block 401). d Do the test after the removal/installation of the Brake/Steering Control Unit (BSCU) (10GG), (Refer to AMM 32-42-34 Page block 401). e Do the test after the removal/installation of the Ground Auxiliary Power Control Unit (GAPCU) (24XG), (Refer to AMM 24-41-34 Page block 401). f Do the test after the removal/installation of the Landing gear Control and Interface Unit (LGCIU) (5GA1), (Refer to AMM 32-31-71 Page block 401). g Do the test after the removal/installation of the Smoke-Detection Control Unit (SDCU) (10WQ), (Refer to AMM 26-17-34 Page block 401). h Do the test after the removal/installation of the AFT cargo heat controller (10HC), (Refer to AMM 21-43-34 Page block 401).

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved i Do the test after the removal/installation of the Spoiler Elevator Computer (SEC) (1CE1, 1CE2, 1CE3), (Refer to AMM 27-94-34 Page block 401). j Do the test after the removal/installation of the zone controller (8HK), (Refer to AMM 21-63-34 Page block 401). 20 Do a voltage check at pin 2 of each circuit breaker that follows, in the Rear C/B Panel 121VU, to make sure that there is 28VDC voltage : 2EN1, 2WZ, 48WV, 14WV, 1EN1, 4EN1, 5CC2, 15CC, 9CA2, 3QP, 4QP, 1QE, 3QG, 4QG, 2QT, 3GS, 2RC2, 8CV, 20CE2, 21CE2, 21CE3, 19CE3, 2GG and 183GQ. 21 Do a voltage check at pin 2 of each circuit breaker that follows, in the Rear C/B Panel 121VU, to make sure that there is 115VDC voltage : 30QA, 11WT2, 12WT2, 3JH2, 10WT2, 2WW and 2WV. (d) Do the test of the ACT switching panel 2028VU. 1 Make sure that the electrical circuits are energized (Refer to AMM 24-41-00 Page block 201). 2 Remove the safety clip(s) and tag(s) and close this (these) circuit breaker(s) :

3 Set the power switch 5MY to ON. 4 Make sure that on the switching panel 2028VU all switches are in ON position. 5 Operate the CLS. a All PDUs must run in the commanded direction. 6 On the switching panel 2028VU, set the switch 150MY (ACT1) to OFF. 7 Operate the CLS. a The PDU 108MY, position 31 (below ACT1) must not run. All the other PDUs must run in the commanded direction. 8 On the switching panel 2028VU, set the switch 151MY (ACT2) to OFF. PANEL DESIGNATION FIN LOCATION 2001VU SEMI AUTO CLS-AFT 102MY D06 2001VU SEMI AUTO CLS-AFT 103MY D08

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 9 Operate the CLS. a The PDU 108MY, position 31 (below ACT1) and PDU 110MY, position 32 (below ACT2 must not run. All the other PDUs must run in the commanded direction. 10 On the switching panel 2028VU, set the switch 150MY (ACT1) and switch 151MY (ACT2) to ON. 11 Set the power switch 5MY to OFF. 12 Set the aircraft in normal operating position. (e) Do an operational test of the CLS (Refer to AMM 25-52-00 Page block 501). (f) Do an operational test of the fuel quantity indicator lights (Refer to AMM 28-42-00 Page block 501). (g) Do a status report (BITE) of the fuel quantity indicator system (Refer to AMM 28-42-00 Page block 501). (h) Do a leak test of the ACT shroud system and the drain lines, refer to Appendix 01 . (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. (r) Do the tests after the removal/installation of the AC auxiliary generator contactor(3XS), refer to AMM 24-23-55 Page block 401.

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (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.

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (aj) Do the test of the ELAC system, refer to AMM 27-93-00 Page block 501. (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 an operational test of the 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.

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (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, refer to AMM 29-19-51 Page block 401. (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) Do a functional test 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.

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (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. (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.

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (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. CLOSE UP (1) Config. 01 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the belly fairing panels 147FB, 148FB, 197AB, 197BB, 197GB, 198BB, 198GB and 198GB. (c) In the passenger compartment, install the components that were removed for access : — the insulation blankets, (Refer to AMM 25-80-00 Page block 201) — the floor panels, (Refer to AMM 53-32-12 Page block 401 and AMM 53-42-12 Page block 401) — the textile floor covering, (Refer to AMM 25-28-41 Page block 401) — the lower sidewall (dado) panels, (Refer to AMM 25-23-44 Page block 401) — the upper sidewall panels, (Refer to AMM 25-23-43 Page block 401) — the cove light panels, (Refer to AMM 25-23-48 Page block 401) — the ceiling panels, (Refer to AMM 25-23-41 Page block 401) — the overhead stowage compartments, (Refer to AMM 25-24-41 Page block 401) — the passenger seats, (Refer to AMM 25-21-41 Page block 401) (d) In the FWD cargo compartment, install the components that were removed for access : — the floor panels, (Refer to AMM 53-22-14 Page block 401) — the sidewall panels, (Refer to AMM 25-54-12 Page block 401) — the ceiling panels, (Refer to AMM 25-54-12 Page block 401). (e) In the AFT cargo compartment, install the components that were removed for access :

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved — the floor panels, (Refer to AMM 53-42-14 Page block 401) — the sidewall panels, (Refer to AMM 25-55-11 Page block 401) — the ceiling panels, (Refer to AMM 25-55-11 Page block 401). (f) 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). (g) Install the outlet PN D2821302620000, (Refer to IPC 28-12-05). (h) 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). (i) 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). (j) Refuel the center tank, (Refer to AMM 28-25-00 Page block 301). (k) Close the avionics door 822, (Refer to AMM 52-41-00 Page block 201). (l) Remove the safety equipment and close the FWD and AFT cargo compartment doors, (Refer to AMM 52-30-00 Page block 201). (m) Remove the safety equipment and close the MLG doors, (Refer to AMM 32-12-00 Page block 201). (n) Remove the access platform(s). (o) De-energize the aircraft electrical circuits, (Refer to AMM 24-41-00 Page block 201). (p) Lower the aircraft, (Refer to AMM 07-11-00 Page block 201). (q) Restore the systems and the aircraft to normal operating condition. E. DOCUMENTATION Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved

This Page Intentionally Left Blank

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SERVICE BULLETIN

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 1 Sheet 1 (Goto A3 section) Config. 01: Hook-up Chart (Kit B04)

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SERVICE BULLETIN APPENDIX 01

6 DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : 1 of 10 Printed in FRANCE © AIRBUS, 2007 All rights reserved 1. Leak test of the ACT shroud system and drain lines A. Leak test Refer to Figure 1 Sheet 1 and Sheet 2 . (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) :

(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. (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. Make sure that the tank interspace drain connection(s) have blanks installed. (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 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

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

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 2 Open the ACT Transfer Valve 165QM by removing the actuator and move the valve by hand or electrically by closing these circuit breakers :

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 Provisions in the Center Tank. A. Leak Test PANEL DESIGNATION FIN LOCATION 121VU ACT PUMP SPLY 25QH 29 Q

PANEL DESIGNATION FIN LOCATION 121VU ACT XFR VALVE MAN CTL 30QH 29 N 121VU ACT XFR VALVE AUTO CTL 9QH 29 P

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

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 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 litre/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 litre/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 problem with the pipework of the ACT refuel/transfer line. Carry out a repair and do the test procedure again. (3) After Test

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

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (a) Retain the aircraft configuration for the next test. 3. Leak Test of the ACT pressurisation system. A. Leak Test Refer to Figure 2 Sheet 1 Refer to Figure 3 Sheet 1 Refer to Figure 4 Sheet 1 NOTE : The test that follows is to check that the ACT pressurisation system does not leak and that the non-return valves in the system operate correctly. The test is to be done one time only 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 pressurisation 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.

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SERVICE BULLETIN APPENDIX 01

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (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 pressurisation 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. (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 pressurisation 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 1 from T2. (e) Close the air shut-off valve. (f) In the AFT cargo compartment, install the ceiling access panel 151CC (Refer to AMM 25-55-11 Page block 401).

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

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 1 Sheet 1 Leak Test of the ACT Shroud System and Drain Lines

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

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 1 Sheet 2 Leak Test of the ACT Shroud System and Drain Lines

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

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 2 Sheet 1 Access to the Test Points T1 and T2

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

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 3 Sheet 1 ACT Test Arrangement - Test Tool 1

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SERVICE BULLETIN APPENDIX 01

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 4 Sheet 1 ACT Arrangement - Test Tool 2

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SERVICE BULLETIN REPORTING SHEET

6 DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : 1 of 2 Printed in FRANCE © AIRBUS, 2007 All rights reserved TITLE : FUEL - TANKS - INSTALL TWO ACT PROVISIONS WITH CLS CONFIGURATION MODIFICATION No. : 25415P4179 25696P4347 25713J1492 25713K4481 26110J1523 26110K4482 26138K4772 27446P5502 27447P5503 27448P5504 27717K5539 28068P5759 28661J2073 28817J1973 30356P6676 30356P7357 30373K6720 31110K7004 31143K7155 31700K7502 31812K7403 32261J2241 33198K8488 33199K8489 33373K8623 33492J2482 34742K9642 34758K9658 36348K10556 36349K10557 36350K10558 36399K6099

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

DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Please complete the appropriate item (A or B): A - SB WILL BE embodied............. YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment:..........................

........................................

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

........................................

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

.......................................

....................................... From Airline:................................. Name/Title:.................................. Signature:.............. Date:............. If operational documentation is affected (see Paragraph 1.Kof this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service: Either: Modification Operational Impact (MOI), if available. . YES/NO Or : Intermediate revision.

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

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SERVICE BULLETIN QUALITY PERCEPTION FORM

6 DATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145 REVISION No. : 01 — Apr 27/07 Page : 1 of 1 Printed in FRANCE © AIRBUS, 2007 All rights reserved Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 4 3 2 1 - Quality rating of the Accomplishment Instructions 4 3 2 1 - Quality rating of the Illustrations 4 3 2 1 - Is this SB easy to understand ? Y / N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials X Mod/Inspection X Manpower Operator Supplied X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations Comments :

Operator : Date: Name/Title : Please return this form to : AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.@ A318/A319/A320/A321SERVICE BULLETINDATE : Feb 28/06 SERVICE BULLETIN No. : A320—28—1145REVISION No. : 01 — Apr 27/07 Page : 147/148Printed in FRANCE © AIRBUS, 2007 All rights reservedFigure 1 Sheet 1Config. 01: Hook-up Chart (Kit B04)