SERVICE BULLETIN REVISION TRANSMITTAL SHEET

**AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  **Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F**  **Fax : (33) 5 61 93 42 51 ATA SYSTEM : 28**  **TITLE : FUEL - TANKS - INSTALL PROVISIONS FOR TWO ACT ON A320 WITH BULK CONFIGURATION MODIFICATION No. :** 150855K13954, 25415P4179, 25696P4347, 25713J1492, 25713K4481, 26110J1523, 26110K4482, 26138K4772, 27115J1522, 27377K4984, 27378K4985, 27379K4999, 27380K5000, 27381K5002, 27446P5502, 27447P5503, 27448P5504, 27717K5539, 28068P5759, 28378J2056, 28661J2073, 28817J1973, 28900P8797, 30248P11386, 30356P6676, 30356P6683, 30373K6720, 31110K7004, 31143K7155, 31642K7282, 31700K7502, 31812K7403, 32120K7850, 32261J2241, 33198K8488, 33199K8489, 33373K8623, 33492J2482, 34751K9651, 34760K9660, 35068P9022, 35248K9948, 35282P9110, 37580K11542, 39156K12369 This page transmits Revision No. 04 of Service Bulletin No. A320-28-1132 ADDITIONALWORK No additional work is required by this revision for aircraft modified by any previous issue. REASON This Revision is issue to : - add Mod. No. 30248P11386, Mod. No. 35248K9948 and Mod. No. 39156K12369, - add aircraft MSN 1868 to the effectivity and update the operators, - add Config. 03, - update Kit A10 and add Kits A23 thru A27, - add Kits D48, D52 thru D54, D59, D60, G03 thru G05, G10 and G12, - introduce minor changes. CHANGES SUMMARY : - REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. MODIFICATION CLASSIFICATION, Mod No added. - EFFECTIVITY

. Operators updated. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 1 of 4 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN REVISION TRANSMITTAL SHEET

- MATERIAL INFORMATION

. Config. 03 and Kits added. PLANNING INFORMATION : - EFFECTIVITY

. 1.A. Aircraft MSN 1868 added. Operators updated and Config. 03 added. - DESCRIPTION

. 1.D.(6) Config. 03 added. . 1.D.(7) Config. 03 added. . 1.D.(8) Config. 03 added. - MANPOWER

. 1.G. Config. 03 added. - WEIGHT AND BALANCE

. 1.H. Config. 03 added. - REFERENCES

. 1.J. Drawings updated. - INTERCHANGEABILITY/MIXABILITY

. 1.L. Config. 03 added. MATERIAL INFORMATION : - MATERIAL - PRICE AND AVAILABILITY - Material

. 2.A.(1) Vendor address added. - LIST OF COMPONENTS

. 2.C. Kits A10 and D20 updated. Kits A23 thru A27, D48, D52 thru D54, D59, D60, G03 thru G05, G10 and G12 added. - LIST OF MATERIALS - OPERATOR SUPPLIED - Components

. 2.D.(2) Config. 03 added. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 2 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN REVISION TRANSMITTAL SHEET

ACCOMPLISHMENT INSTRUCTIONS : - GENERAL - Preparation

. 3.A.(1)(a) Config. 03 added - Standard Practices

. 3.A.(2)(aw) Drawing added. - MODIFICATION

. 3.B.(6) Config. 03 added. . 3.B.(7) Config. 03 added. . 3.B.(8) Config. 03 added. - TESTS

. 3.C.(1) Config. 03 added. - CLOSE-UP

. 3.D.(1) Config. 03 added. NOTE : Layout changes due to computerization of this revision are not identified. FILINGINSTRUCTIONS 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. HIST OR YOFPREVIOUSREVISIONS Revision 01 was issued to : - add Mod. No. 28900P8797 and remove Mod. No. 30139J2110, - include improvements further to embodiment of this Service Bulletin on aircraft MSN 2165 based on Statement of Approved Design Data (SADD) 913.0022/05, - change Kit D83R01 to D83R00 in the Summary, - update standard sentences, - update drawing references, - change/correct item numbers. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 3 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN REVISION TRANSMITTAL SHEET

- introduce minor changes. Revision 02 was issued to : - add aircraft MSNs 3379 and 3402 to the effectivity and update the operators, - add D11, D37, D38, D39, D43, D44, D45, D46, D55, D56, D57, D58, D64, D65, D69, D76, D77, D78, D96, D97, D98 and D99 for Config. 02, - add the Mod. No. 31642K7282, 34751K9651, 34760K9660, 35068P9022, 35282P9110 and 37580K11542, - change the Service Bulletin to the latest standard, - introduce minor changes. Revision 03 was issued to : - update the weight and balance data, - change the Service Bulletin to the latest standard, - add minor changes - add corrections further to accomplishment of this Service Bulletin on aircraft MSN 3379. REVISIONSEQUENCE ORIGINAL : Oct 13/04 REVISION No. : 01 - Oct 12/06 REVISION No. : 02 - Nov 12/08 REVISION No. : 03 - Oct 05/09 REVISION No. : 04 - Feb 01/10

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 4 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

**AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  **Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F**  **Fax : (33) 5 61 93 42 51**This summary is for information only and is not approved for modification of the aircraft **ATA SYSTEM : 28 TITLE : FUEL - TANKS - INSTALL PROVISIONS FOR TWO ACT ON A320 WITH BULK CONFIGURATION**  **MODIFICATION No. :**150855K13954, 25415P4179, 25696P4347, 25713J1492, 25713K4481, 26110J1523, 26110K4482, 26138K4772, 27115J1522, 27377K4984, 27378K4985, 27379K4999, 27380K5000, 27381K5002, 27446P5502, 27447P5503, 27448P5504, 27717K5539, 28068P5759, 28378J2056, 28661J2073, 28817J1973, 28900P8797, 30248P11386, 30356P6676, 30356P6683, 30373K6720, 31110K7004, 31143K7155, 31642K7282, 31700K7502, 31812K7403, 32120K7850, 32261J2241, 33198K8488, 33199K8489, 33373K8623, 33492J2482, 34751K9651, 34760K9660, 35068P9022, 35248K9948, 35282P9110, 37580K11542, 39156K12369 REASON/DESCRIPTION/OPERA TIONALCONSEQUENCES This Service Bulletin is issued in response to the request of a operator 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.

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

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 1 of 13 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

MODIFICATION CLASSIFICATION

MAJOR 26138K4772 28378J2056

MINOR 150855K13954 25415P4179 25696P4347 25713K4481 25713J1492 26110J1523 26110K4482 27115J1522 27377K4984 27378K4985 27379K4999 27380K5000 27381K5002 27446P5502 27447P5503 27448P5504 27717K5539 28068P5759 28661J2073 28817J1973 28900P8797 30248P11386 30356P6683 30356P6676 30373K6720 31110K7004 31143K7155 31642K7282 31700K7502 31812K7403 32120K7850 32261J2241 33198K8488 33199K8489 33373K8623 33431K8711 33492J2482 34159K9239 34751K9651 34760K9660 35068P9022 35248K9948 35282P9110 37580K11542 39156K12369 As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural strength, reliability, operational characteristics affecting the airworthiness of the product. All other changes are major changes. **E F** **F E** **C T** **I V** **I T** **Y** This Service Bulletin is applicable to these operator(s) : 62X 95V KNE LMJ NOTE : This Service Bulletin is written for the operators listed above. Themodification 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 CONCURRENTREQUIREMENTS None REFERENCES/REPERCUSSIONS TFU : None OEB : None DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 2 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

AOT : None SIL : None LIFE LIMIT : None LINE MAINTENANCE AFFECTED : No OTHERS : None NA TUREOFTHEWORK AIRCRAFT : YES EQUIPMENT : YES HARD : YES SOFT : YES OBRM : NO MANPOWER Config. 01

**TOTAL MANHOURS 2000 ELAPSED TIME (HOURS)**  **450** Config. 02

**TOTAL MANHOURS 2010**  **ELAPSED TIME (HOURS) 455**  Config. 03

**TOTAL MANHOURS 2010**  **ELAPSED TIME (HOURS) 455**  MA TERIALINFORMA TION AIRCRAFT DATA Config. 01 thru Config. 03 Kit 281132A01R01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 3 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Plate, rod, brackets doublers and related hardware. Kit 281132A02R02 Plate, rod, brackets and related hardware. Kit 281132A03R01 Canister, valves, pump, plate, insert, spring, pin, plug, bulkhead, door, fairing, fittings, leads, actuator, switch and related hardware. Kit 281132A04R01 Valves, sleeves, flange, elbows, strip, tees, leads, union, pipes, restructures and related hardware. Kit 281132A05R00 Elbows, plate, filter and related hardware. Kit 281132A06R01 Bundle, placards, switch, sleeves, connector, shunt circuit breakers, and related hardware. Kit 281132A07R00 Plate. Kit 281132A08R00 Plate. Kit 281132A09R00 Placards. Kit 281132A10R02 Brackets, bundles, modules, connectors, backshells, relay, base, stud, conduits, mounts, spacer, placards and related hardware. Kit 281132A11R01 Rack, modules, placards, plate, flange, base, retainer, relay, and related hardware. Kit 281132A13R00 Placards. Kit 281132A14R00 Placards. Kit 281132A15R01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 4 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Bundle, placards, switch, sleeves, connector, shunt circuit breakers, and related hardware. Kit 281132A16R00 Cover, rack, modules, placards, base, retainer, relay, and related hardware. Kit 281132A17R00 Unit. Kit 281132A18R00 Placards. Kit 281132A19R00 Brackets, bundles, modules, connectors, backshells, relay, base, mounts, spacer, placards and related hardware. Kit 281132A20R00 Plate, rod, brackets, doubler, fittings, supports, loft and related hardware. Kit 281132A21R01 Plate, rod, brackets, doubler, fittings, supports, angles and related hardware. Kit 281132A22R00 Brackets. Kit 281132A23R00 Valve, door, bulkhead, fairing and related hardware. Kit 281132A24R00 Flange, elbow, pipes, union, clamps, bracket and related hardware. Kit 281132A25R00 Bundle, base, relay, modules, connectors, backshells and related hardware. Kit 281132A26R00 Placard. Kit 281132A27R00 Brackets. Kit 281132B01R00 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 5 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Valves, filter, actuator and clamp. Kit 281132B02R00 Panel and relay Kit 281132B03R00 Panels Kit 281132B04R00 Bundle Kit 281132D01R00 Tube, leads and related hardware. Kit 281132D02R00 Tube, strap, elbow and related hardware. Kit 281132D03R00 Brackets and related hardware. Kit 281132D04R00 Panel, fairing, cover, section, brackets, angle and related hardware. Kit 281132D05R01 Connecting sections, angles, beam, struts, fittings, angles, plates, sections, shims, coupling and related hardware. Kit 281132D06R01 Fittings, plates, sections, angles, shims, support, webs, key, doublers, cover, tubes, plugs, straps, x-beams and related hardware. Kit 281132D07R00 Angles and related hardware. Kit 281132D08R00 pins and collars. Kit 281132D09R00 Profiles, sections, straps and related hardware. Kit 281132D10R00 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 6 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Insulation blankets and strips. Kit 281132D11R00 Insulation blankets and strips. Kit 281132D12R00 Bracket pin and ring. Kit 281132D13R00 Tubes, flanges, sleeves, brackets, spacer, clamps, springs, leads and related hardware. Kit 281132D14R00 Monitor, tubes, hose, fitting, bracket, elbow, tees, unions, placards and related hardware. Kit 281132D15R00 Monitor, tubes, hose, elbows, tee, straps, leads, placard and related hardware. Kit 281132D16R01 Tubes, inlet, filter couplings, placards, elbow, tees, leads, straps and related hardware. Kit 281132D17R00 Brackets, angles and related hardware. Kit 281132D18R00 Beam and related hardware. Kit 281132D19R00 Shield, shim and related hardware. Kit 281132D20R02 TDPs and related hardware. Kit 281132D22R00 Shims and related hardware. Kit 281132D24R01 Tracks, blocks, supports, shims, plates, doubler and related hardware. Kit 281132D26R01 Placards, strips and foils. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 7 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Kit 281132D27R01 Net and Stanchion. Kit 281132D28R01 TDPs and related hardware. Kit 281132D29R00 Covers and related hardware. Kit 281132D31R00 Panels and related hardware. Kit 281132D32R00 Cord and tape. Kit 281132D33R00 Panels, plates, spacer and related hardware. Kit 281132D34R00 Sections and cord. Kit 281132D35R00 Panels and related hardware. Kit 281132D36R02 Sections, brackets, supports, plates and related hardware. Kit 281132D37R00 Panels, plates, spacer and related hardware. Kit 281132D38R00 Panels and related hardware. Kit 281132D39R00 Sections and cord. Kit 281132D40R03 X-beams, plates, fittings, sections, straps, filler, angles, doublers, cover, tubes, plugs, shims, bushings, supports, rings and related hardware. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 8 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Kit 281132D41R00 Pins and collars. Kit 281132D42R00 Connecting sections, angles, beam, struts, fittings, angles, plates, sections, shims, coupling and related hardware. Kit 281132D43R00 Tube, strap, elbow and related hardware. Kit 281132D44R00 Brackets and related hardware. Kit 281132D45R00 Tubes, inlet, filter couplings, placards, elbow, tees, leads, straps and related hardware. Kit 281132D46R00 Brackets, angles and related hardware. Kit 281132D47R00 Tubes, tee and related hardware. Kit 281132D48R00 Tubes, tee and related hardware. Kit 281132D50R01and Kit 281132D51R01 Controls, adapter, angles, brackets, bridge and related hardware. Kit 281132D52R00 Panels, plates and related hardware. Kit 281132D53R00 Panels and related hardware. Kit 281132D54R00 Panels and related hardware. Kit 281132D55R00 Panels, strips, bumpers and related hardware. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 9 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Kit 281132D56R00 Panels. Kit 281132D57R00 Panels. Kit 281132D58R00 Panels and covers. Kit 281132D59R00 Panels, covers, bumpers and related hardware. Kit 281132D60R00 Sections, bracket, plate, support and related hardware. Kit 281132D61R00 Angles, plates, sheets, fittings, straps, wall, stiffeners, profiles and related hardware. Kit 281132D62R00and Kit 281132D63R00 Pins and collars. Kit 281132D64R00 Panels and related hardware. Kit 281132D65R00 Brackets, tee, unions, blocks, tubes, elbows and related hardware. Kit 281132D69R01 Cable harnesses, brackets, reservoirs, placards and related hardware. Kit 281132D70R00 cable harnesses, brackets, reservoirs, placards and related hardware. Kit 281132D71R00 Brackets, tubes, sections, leads, caps, pockets, placards plates, sheets and related hardware. Kit 281132D72R00 Boxes and related hardware. Kit 281132D73R00 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 10 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Placards. Kit 281132D74R00 Tubes and tee. Kit 281132D75R00 Brackets and related hardware. Kit 281132D76R00 Boxes and related hardware. Kit 281132D77R00 Placards. Kit 281132D78R00 Electrical equipment. Kit 281132D80R00 Panels, strips, bumpers and related hardware. Kit 281132D81R00 Panels. Kit 281132D82R00 Panels. Kit 281132D83R00 Panels and covers. Kit 281132D84R00 Brackets, tee, unions, blocks, tubes, elbows and related hardware. Kit 281132D85R01 thru Kit 281132D86R00 Electrical equipment. Kit 281132D87R01 thru Kit 281132D93R01 Brackets, angles, strip, mounts spacer, strap, guides, sections, clamps, fittings, receptacles, connectors, sleeves, and related hardware. Kit 281132D94R01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 11 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Cap, nuts. Kit 281132D95R00 Fittings, plates, sections, angles, shims, support, webs, key, doublers, cover, tubes, plugs, straps, x-beams and related hardware. Kit 281132D96R02 X-beams, plates, fittings, sections, straps, filler, angles, doublers, cover, tubes, plugs, shims, bushings, supports, rings and related hardware. Kit 281132D97R01 Electrical equipment. Kit 281132D98R02 Brackets, angles, strip, mounts spacer, strap, guides, sections, clamps, fittings, receptacles, connectors, sleeves, and related hardware. Kit 281132D99R00 Electrical equipment. Kit 281132G03R00 Brackets, angles and related hardware. Kit 281132G04R00 Fittings, spacer, supports, receptacles, mounts, placards, and related hardware. Kit 281132G05R00 Electrical equipments. Kit 281132G10R02 Sections, angles, shims and related hardware. Kit 281132G12R00 Nut and cap. Kit 281132T01R00 Stowage box.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 12 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

APPENDICES Refer to Appendix 1 - Leak test of the ACT shroud system and drain lines Refer to Appendix 2 - Instruction Manual for the Adjustment Device PN : 98D28108641000

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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This Page Intentionally Left Blank

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 14 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

**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 PROVISIONS FOR TWO ACT ON A320 WITH BULK CONFIGURATION MODIFICATION No. :** 150855K13954, 25415P4179, 25696P4347, 25713J1492, 25713K4481, 26110J1523, 26110K4482, 26138K4772, 27115J1522, 27377K4984, 27378K4985, 27379K4999, 27380K5000, 27381K5002, 27446P5502, 27447P5503, 27448P5504, 27717K5539, 28068P5759, 28378J2056, 28661J2073, 28817J1973, 28900P8797, 30248P11386, 30356P6676, 30356P6683, 30373K6720, 31110K7004, 31143K7155, 31642K7282, 31700K7502, 31812K7403, 32120K7850, 32261J2241, 33198K8488, 33199K8489, 33373K8623, 33492J2482, 34751K9651, 34760K9660, 35068P9022, 35248K9948, 35282P9110, 37580K11542, 39156K12369 This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that the said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS prior written consent. **1. P L** **A N** **N I** **N G** **I N** **F O** **R M** **A T** **I O** **N A. E** **F F** **E C** **T I** **V I** **T Y**  (1) Models 320-214 320-232 (2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft MSN : 1868 2165 3379 3402 (b) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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OPERATOR MSN 62X 3402 95V 3379 KNE 2165 LMJ 1868 (c) Effectivity by MSN and Kit/Configuration The Kits and configurations applicable to these MSNs are given at the end of this list 2165 KIT No. QTY PER A/C CONFIGURATION 281132A01R01 1 01 281132A02R02 1 01 281132A03R01 1 01 281132A04R01 1 01 281132A05R00 1 01 281132A06R01 1 01 281132A07R00 1 01 281132A08R00 1 01 281132A09R00 1 01 281132A10R02 1 01 281132A11R01 1 01 281132B01R00 1 01 281132B02R00 1 01 281132B03R00 1 01 281132B04R00 1 01

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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KIT No. QTY PER A/C CONFIGURATION 281132D01R00 1 01 281132D02R00 1 01 281132D03R00 1 01 281132D04R00 1 01 281132D05R01 1 01 281132D06R01 1 01 281132D07R00 1 01 281132D08R00 1 01 281132D09R00 1 01 281132D10R00 1 01 281132D12R00 1 01 281132D13R00 1 01 281132D14R00 1 01 281132D15R00 1 01 281132D16R01 1 01 281132D17R00 1 01 281132D18R00 1 01 281132D19R00 1 01 281132D20R02 1 01 281132D22R00 1 01 281132D24R01 1 01

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KIT No. QTY PER A/C CONFIGURATION 281132D26R01 1 01 281132D27R01 1 01 281132D28R01 1 01 281132D29R00 1 01 281132D31R00 1 01 281132D32R00 1 01 281132D33R00 1 01 281132D34R00 1 01 281132D35R00 1 01 281132D36R02 1 01 281132D40R03 1 01 281132D41R00 1 01 281132D50R01 1 01 281132D51R01 1 01 281132D61R00 1 01 281132D62R00 1 01 281132D63R00 1 01 281132D70R00 1 01 281132D71R00 1 01 281132D72R00 1 01 281132D73R00 1 01 281132D74R00 1 01 281132D75R00 1 01

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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KIT No. QTY PER A/C CONFIGURATION 281132D80R00 1 01 281132D81R00 1 01 281132D82R00 1 01 281132D83R00 1 01 281132D84R00 1 01 281132D85R01 1 01 281132D86R00 1 01 281132D87R01 1 01 281132D88R00 1 01 281132D89R00 1 01 281132D90R00 1 01 281132D91R01 1 01 281132D92R03 1 01 281132D93R01 1 01 281132D94R01 1 01 The Kits and configurations applicable to these MSNs are given at the end of this list 3379 3402 KIT No. QTY PER A/C CONFIGURATION 281132A03R01 1 02 281132A04R01 1 02 281132A05R00 1 02 281132A07R00 1 02

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 5 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION 281132A13R00 1 02 281132A14R00 1 02 281132A15R01 1 02 281132A16R00 1 02 281132A17R00 1 02 281132A18R00 1 02 281132A19R00 1 02 281132A20R00 1 02 281132A21R01 1 02 281132B01R00 1 02 281132B02R00 1 02 281132B03R00 1 02 281132B04R00 1 02 281132D01R00 1 02 281132D04R00 1 02 281132D07R00 1 02 281132D08R00 1 02 281132D09R00 1 02 281132D11R00 1 02 281132D12R00 1 02 281132D13R00 1 02 281132D14R00 1 02 281132D15R00 1 02

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 6 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION 281132D18R00 1 02 281132D19R00 1 02 281132D20R02 1 02 281132D22R00 0 02 281132D24R01 1 02 281132D26R01 1 02 281132D27R01 1 02 281132D28R01 1 02 281132D29R00 1 02 281132D32R00 1 02 281132D36R02 1 02 281132D37R00 1 02 281132D38R00 1 02 281132D39R00 1 02 281132D41R00 1 02 281132D42R00 1 02 281132D43R00 1 02 281132D44R00 1 02 281132D45R00 1 02 281132D46R00 1 02 281132D47R00 1 02 281132D50R01 1 02

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 7 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION 281132D51R01 1 02 281132D55R00 1 02 281132D56R00 1 02 281132D57R00 1 02 281132D58R00 1 02 281132D61R00 1 02 281132D62R00 1 02 281132D63R00 1 02 281132D64R00 1 02 281132D65R00 1 02 281132D69R01 1 02 281132D71R00 1 02 281132D75R00 1 02 281132D76R00 1 02 281132D77R00 1 02 281132D78R00 1 02 281132D84R00 1 02 281132D89R00 1 02 281132D90R00 1 02 281132D91R01 1 02 281132D92R03 1 02 281132D93R01 1 02 281132D94R01 1 02

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 8 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION 281132D95R00 1 02 281132D96R02 1 02 281132D97R01 1 02 281132D98R02 1 02 281132D99R00 1 02 The Kits and configurations applicable to these MSNs are given at the end of this list 1868 KIT No. QTY PER A/C CONFIGURATION 281132A05R00 1 03 281132A07R00 1 03 281132A11R01 1 03 281132A14R00 1 03 281132A15R01 1 03 281132A18R00 1 03 281132A20R00 1 03 281132A21R01 1 03 281132A23R00 1 03 281132A24R00 1 03 281132A25R00 1 03 281132A26R00 1 03 281132A27R00 1 03 281132B01R00 1 03 281132B02R00 1 03 281132B03R00 1 03 281132B04R00 1 03

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 9 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION 281132D01R00 1 03 281132D04R00 1 03 281132D05R01 1 03 281132D06R01 1 03 281132D07R00 1 03 281132D08R00 1 03 281132D09R00 1 03 281132D11R00 1 03 281132D12R00 1 03 281132D13R00 1 03 281132D14R00 1 03 281132D15R00 1 03 281132D16R01 1 03 281132D17R00 1 03 281132D18R00 1 03 281132D19R00 1 03 281132D20R02 1 03 281132D22R00 1 03 281132D24R01 1 03 281132D26R01 1 03 281132D27R01 1 03 281132D28R01 1 03 281132D29R00 1 03

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 10 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION 281132D32R00 1 03 281132D39R00 1 03 281132D40R03 1 03 281132D41R00 1 03 281132D43R00 1 03 281132D44R00 1 03 281132D48R00 1 03 281132D50R01 1 03 281132D51R01 1 03 281132D52R00 1 03 281132D53R00 1 03 281132D54R00 1 03 281132D56R00 1 03 281132D57R00 1 03 281132D58R00 1 03 281132D59R00 1 03 281132D60R00 1 03 281132D61R00 1 03 281132D62R00 1 03 281132D63R00 1 03

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 11 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION 281132D69R01 1 03 281132D71R00 1 03 281132D72R00 1 03 281132D73R00 1 03 281132D75R00 1 03 281132D84R00 1 03 281132D86R00 1 03 281132D87R01 1 03 281132D89R00 1 03 281132D90R00 1 03 281132D93R01 1 03 281132D98R02 1 03 281132G03R00 1 03 281132G04R00 1 03 281132G05R00 1 03 281132G10R02 1 03 281132G12R00 1 03 NOTE : Config. 01 concerns the embodiement of Mod. Nos. 25415P4197 25696P4347 25713J1492 25713K4481 26110J1523 26110K4482 26138K4772 27115J1522 27377K4984 27378K4985 27379K4999 27380K5000 27381K5002 27446P5502 27447P5503 27448P5504 27717K5539 28068P5759 28378J2056 28661J2073 28817J1973 28900P8797 30356P6676 30356P6683 30373K6720 31110K7004 31143K7155 31700K7502 31812K7403 32261J2241 33198K8488 33199K8489 33373K8623 33492J2482. NOTE : Config. 02 concerns the embodiement of Mod. Nos. 25415P4197 25696P4347 25713J1492 25713K4481 26110J1523 26110K4482 26138K4772 27115J1522 27377K4984 27378K4985 27379K4999 27380K5000 27381K5002 27446P5502 27447P5503 27448P5504 27717K5539 28068P5759 28378J2056 28661J2073 28817J1973 28900P8797 30356P6676 30356P6683 30373K6720 31110K7004 31143K7155 31642K7282 31700K7502 31812K7403 32261J2241 33198K8488 33199K8489 33373K8623 33431K8711 33492J2482 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 12 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

34751K9651 34760K9660 35068P9022 35248K9948 35282P9110 37580K11542 39156K12369. NOTE : Config. 03 concerns the embodiement of Mod. Nos. 25415P4197 25696P4347 25713J1492 25713K4481 26110J1523 26110K4482 26138K4772 27115J1522 27377K4984 27378K4985 27379K4999 27380K5000 27381K5002 27446P5502 27447P5503 27448P5504 27717K5539 28068P5759 28378J2056 28661J2073 28817J1973 28900P8797 30248P11386 30356P6676 30356P6683 30373K6720 31110K7004 31143K7155 31642K7282 31700K7502 31812K7403 32261J2241 33198K8488 33199K8489 33373K8623 33431K8711 33492J2482 34159K9239 34751K9651 34760K9660 35068P9022 35248K9948 35282P9110 37580K11542 39156K12369 150855K13954. (3) Spares Door assy D5713019400200 Front plate D9251092000000 Pipe assy D2821008001300 Computer SIC5059-11-0207 FQI 1407KID02-03 Placard D11311357A00 Placard D11311359A00 Placard D11311364A00 Placard 02048-23 Integrally lighted plate 002098-05 **B. C O** **N C** **U R** **R E** **N T** **R E** **Q U** **I R** **E M** **E N** **T S**  None **C. R E** **A S** **O N**  (1) History This Service Bulletin is issued in response to the request of a operator 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. (4) Operational/Maintenance Consequences The operational/maintenance consequences of this Service Bulletin are covered by the update of the affected publications detailed in PLANNING INFORMATION paragraph K. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 13 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

This Service Bulletin is based on the aircraft configuration as known by Airbus (first aircraft delivery configuration and modified by the reported incorporation of Airbus SBs). Prior to Service Bulletin embodiment, the operator is reminded to pay specific attention to structural damage which may exist and to repairs which were performed on the aircraft because they may be affected by the Service Bulletin. 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 additional or modified maintenance requirements, such as temporary limits or additional inspections, that apply with respect to the Service Bulletin configuration. Airbus disclaims any liability for the effect which the Service Bulletin may have on repairs performed on the aircraft before embodiment of the Service Bulletin. If the post Service Bulletin repair status is no more covered by the SRM and for repairs outside of the SRM covered by a RAS issued by Airbus, the operator should contact Airbus Customer Services Repair Engineering Support (SER1). Repair review will be done by Airbus at conditions of the Customer Services Catalogue. **D. D E** **S C** **R I** **P T** **I O** **N** To accomplish this Service Bulletin it is necessary to : (1) Config. 01 thru Config. 02 (a) Remove the nets from the AFT cargo compartment. (b) Remove the Tie Down Points (TDPs) from the AFT cargo compartment. (c) Remove the belly fairing panels 197AB and 198GB. (d) Modify the attachment structure of the belly fairing panels 197AB and 198GB. (e) Remove and not reuse the pressure reservoirs for the offwing escape slides, LH/RH. (f) Remove and discard the placards at the AFT cargo compartment lining panels between FR47 and FR48, LH/RH. (g) Modify the insulation blankets. (h) Relocate the release cable for the offwing slide, LH. (i) Relocate the release cable for the offwing slide, RH. (j) Install the pressure reservoir of the offwing escape slide LH/RH. (k) Install a bracket at the passenger compartment floor structure at FR53. (l) Install the additional angles at the webs of the keel beam structure between FR42 and FR46. (m) Replace the fasteners between FR42 and FR44, LH/RH. (n) Remove and discard the attachment structure of the partition panels 151AW, 151BW and 152BW between FR46 and FR47. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 14 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(o) Modify the structure. (p) Replace fasteners at FR48, FR49, FR50 and FR51 between STGR34LH and STGR36LH. (q) Replace fasteners at FR52, FR53 and FR54 between STGR34LH and STGR36LH. (r) Install Longitudinal profiles at the cargo compartment floor structure between FR53 an FR59. (s) Measure the level of the AFT cargo compartment floor structure. (t) Install the water drain connection and the cavity drain access cover between FR52 and FR53. (u) Install the shims on the floor framework of the AFT cargo compartment between FR47 and FR54. (v) Install the roller tracks between FR47 and FR54 in the AFT cargo compartment. (w) Install/Adjust the YZ-latches at FR47, FR48 and FR49 and adjust the XZ-latches. (x) Install/Adjust the YZ-latches at FR50, FR51 and FR52 and adjust the XZ-latches. (y) Install the shims on the frames of the AFT cargo compartment at FR47, FR48, FR49, FR50 and FR51. (z) Install the brackets for the fuel drain/vent systems between FR42 and FR43 (aa) Install the beam between FR46 and FR47. (ab) Install the fuel transfer line between FR41 and FR47. (ac) Install the vent line between FR37 and FR47. (ad) Install the cover between FR46 and FR47 at the fuel transfer line and vent line. (ae) Install the system between FR37 and FR48. (af) Install the cavity drain and monitoring system between FR46 and FR50. (ag) Install the cavity drain and monitoring system between FR50 and FR53. (ah) Install the attachment structure of the partition panels and floor panels. (ai) Remove and discard the attachment parts at FR42. (aj) Remove and discard the attachment parts at FR42. (ak) Remove and discard the attachment parts between FR46 and FR49. (al) Remove and discard the attachment parts at FR46 and FR54. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 15 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(am) Remove and discard the attachment parts at FR46 and FR54. (an) Remove the cable harnesses 4605VB, 4628VB, 4650VB, 4655VB, 4656VB, 4661VB, 4662VB, 4663VB, 4664VB, 4670VB, 4671VB, 4672VB, 4673VB, 4680VB, 4681VB, 4683VB, 4692VB, 4693VB 4694VB. (ao) Remove the cable harnesses 4213VB, 4214VB, 4216VB, 4218VB, 4220VB, 4221VB, 4222VB, 4223VB, 4224VB, 4225VB, 4226VB, 4227VB, 4232VB, 4233VB, 5214VB, 5220VB, 5224VB, 5233VB. (ap) Install the attachment parts at FR42. (aq) Install the attachment parts between FR46 and FR54. (ar) Install the attachment parts in the bilge area between FR46 and FR54. (as) Install the attachment parts at FR42. (at) Install the attachment parts between FR46 and FR49. (au) Replace the cap assembly of the AFT cargo-compartment smoke-detectors (3WH, 4WH) between FR52 and FR53. (av) Seal the gaps at the installed passenger compartment floor panels. (aw) Install these protection covers on the roller tracks between FR53 and FR54. (ax) Replace the placards at the side wall panels in the AFT cargo compartment. (ay) Install the belly fairing panels 197AB and 198GB. (az) Install the Tie Down Points (TDP’s) in the AFT cargo compartment. (ba) Replace Tie Down Point (TDP) and the stanchion bracket in the ceiling area of the AFT cargo compartment. (bb) Install the nets in the AFT cargo compartment. (bc) Install the brackets for the fuel drain/vent systems between FR46 and FR54. (bd) Install the ACT pressurization system between FR51 and FR53. (be) Install the ACT pressurization system between FR48 and FR54. (bf) Install the equipment for the ACT pressurization system between FR48 and FR54. (bg) Install the Relay box in the forward avionics compartment. (bh) Remove and discard the refuel/defuel panel mounting assembly in the belly fairing, zone 192. (2) Config. 01 AI-F Part DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 16 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(a) Install the doublers on the upper surface panels (b) Install the brackets on the upper surface panels (c) Install the rod on the upper surface panels (d) Install the bracket on FR42 (e) Install the bracket above FR42 (f) Install the brackets on the lower surface panels (g) Install the rod and the plate on the lower surface panels (h) Install the Additional Center Tank (ACT) door (i) Install the equipment on the ACT door (j) Replace the Fuel Quantity Indicator (FQI) 6QT (k) Modify the pipes in the center tank (l) Install the ACT pipes in the center tank (m) Install the transfert elbow (n) Install the air ventilation elbow (o) Apply the sealing protection to the center tank (p) Modify the equipment in the HYD/Fuel Panel 40VU (q) Modify the equipment and the wiring in the Rear C/B Panel 121VU (r) Install the routing of Relay Box 802VU, between FR4 and FR5, in the avionics compartment (s) Install the connectors 1975VC and 1982VC between FR33 and FR34 (t) Modify the equipment in the AFT Electronics Rack 80VU (u) Modify the equipment in the Relay Box 103VU (v) Modify the equipment in the Contactor Box 107VU (w) Modify the wiring in the aircraft (x) Modify the equipment in the FWD Electronics Rack 90VU (3) Config. 01 AI-GE Part (a) Remove and discard the overhead stowage compartments between FR43 and FR47. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 17 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(b) Remove and discard the placards at the overhead stowage compartments between FR43 and FR47. (c) Remove and discard the passenger compartment floor panels 241JF, 251AF 251BF, 251FF, 251GF and 252BF. (d) Modify the electrical equipment. (e) Install the overhead stowage compartment. (f) Install the placards on the overhead stowage compartment. (g) Remove the LH sidewall panels between FR46 and FR58. (h) Remove the RH sidewall panels between FR46 and 52A. (i) Remove and discard the aft cargo compartment panels 151AW, 151BW and 152BW at FR47. (j) Remove and discard the insulation blankets at FR46. (k) Remove the AFT cargo compartment ceiling panels between FR47 and FR59. (l) Remove and discard the floor panels from the AFT cargo compartment, between FR47 and FR59. (m) Remove and discard the sloped floor panels from the AFT cargo compartment, between FR47 and FR59. (n) Remove the wires of cable harness 4234VB (o) Remove the wires of cable harness 4209VB (p) Modify the structure. (q) Remove the corner profiles at STGR38LH/RH between FR48 and FR56. (r) Remove the shear plates at STGR38LH/RH between FR48 and FR59. (s) Remove the crossbeams at FR48, FR49, FR50 and FR51 in the AFT cargo compartment. (t) Remove the crossbeams at FR52, FR53 and FR54 in the AFT cargo compartment. (u) Modify the structure at FR48 between STGR34LH and STGR34RH. (v) Modify the structure at FR49 between STGR34LH and STGR34RH. (w) Modify the structure at FR50 between STGR34LH and STGR34RH. (x) Modify the structure at FR51 between STGR34LH and STGR34RH. (y) Modify the structure at FR52 between STGR34LH and STGR34RH. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 18 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(z) Modify the structure at FR52A between STGR38RH and STGR40RH. (aa) Modify the structure at FR53 between STGR34LH and STGR41RH. (ab) Modify the structure at FR53 between STGR36LH and STGR42LH. (ac) Modify the structure at FR54 between STGR34LH and STGR41RH. (ad) Install the shear plates between FR48 and FR51 at STGR43LH. (ae) Install the shear plates between FR51 and FR54 at STGR43LH. (af) Drill additional fastener holes between FR51 and FR54. (ag) Modify the structure between FR47 and FR48 at STGR38LH/RH and STGR43LH. (4) Config. 02 AI-F Part (a) Install the doublers on the upper surface panels (b) Install the brackets on the upper surface panels (c) Install the rod on the upper surface panels (d) Install the bracket on FR42 (e) Install the bracket above FR42 (f) Install the brackets on the lower surface panels (g) Install the rod and the plate on the lower surface panels (h) Install the Additional Center Tank (ACT) door (i) Install the equipment on the ACT door (j) Replace the Fuel Quantity Indicator (FQI) 6QT (k) Modify the pipes in the center tank (l) Install the ACT pipes in the center tank (m) Install the transfert elbow (n) Install the air ventilation elbow (o) Apply the sealing protection to the center tank (p) Modify the equipment in the HYD/Fuel Panel 40VU (q) Modify the equipment and the wiring in the Rear C/B Panel 121VU

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 19 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(r) Install the routing of Relay Box 802VU, between FR4 and FR5, in the avionics compartment (s) Install the connectors 1975VC and 1982VC between FR33 and FR34 (t) Modify the equipment in the AFT Electronics Rack 80VU (u) Modify the equipment in the Relay Box 103VU (v) Modify the equipment in the Contactor Box 107VU (w) Modify the wiring in the aircraft (x) Modify the equipment in the FWD Electronics Rack 90VU (y) Modify the marking on the belly fairing, between FR47 and FR53 (5) Config. 02 AI-GE Part (a) Remove and discard the overhead stowage compartments between FR43 and FR47. (b) Remove and discard the placards at the overhead stowage compartments between FR43 and FR47. (c) Modify the electrical equipment. (d) Install the overhead stowage compartment. (e) Install the placards on the overhead stowage compartment. (f) Remove and discard the passenger compartment floor panels 241JF, 251AF 251BF, 251FF, 251GF and 252BF. (g) Remove the LH sidewall panels between FR46 and FR58. (h) Remove the RH sidewall panels between FR46 and FR52A. (i) Remove and discard the insulation blankets at FR46. (j) Remove the AFT cargo compartment ceiling panels between FR47 and FR59. (k) Remove and discard the floor panels from the AFT cargo compartment, between FR47 and FR56. (l) Remove and discard the sloped floor panels from the AFT cargo compartment, between FR47 and FR59. (m) Remove the cable harness 4209VB. (n) Install the beam assy between FR46 and FR47 from -Y1292 to +Y1292. (o) Install the struts at the beam between FR46 and FR47. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 20 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(p) Replace fasteners between FR42 and FR46 at several places. (q) Drill the holes in FR46 between STGR42LH and STGR43LH. (r) Modify the structure of FR47 between STGR35LH to STGR35RH. (s) Modify the structure between FR47 and FR48 at STGR38LH/RH and STGR43LH. (t) Remove the corner profiles at STGR38LH/RH between FR48 and FR56. (u) Remove the shear plates at STGR38LH/RH between FR48 and FR59. (v) Remove the crossbeams at FR48, FR49, FR50 and FR51 in the AFT cargo compartment. (w) Remove the crossbeams at FR52, FR53 and FR54 in the AFT cargo compartment. (x) Modify the structure at FR48 between STGR34LH and STGR34RH. (y) Modify the structure at FR49 between STGR34LH and STGR34RH. (z) Modify the structure at FR50 between STGR34LH and STGR34RH. (aa) Modify the structure at FR51 between STGR34LH and STGR34RH. (ab) Modify the structure at FR52 between STGR34LH and STGR34RH. (ac) Modify the structure at FR52A between STGR38RH and STGR40RH. (ad) Modify the structure at FR53 between STGR34LH and STGR41RH. (ae) Modify the structure at FR53 between STGR36LH and STGR42LH. (af) Modify the structure at FR54 between STGR34LH and STGR41RH. (ag) Install the shear plates between FR48 and FR51 at STGR43LH. (ah) Install the shear plates between FR51 and FR54 at STGR43LH. (ai) Modify the structure between FR47 and FR48 at STGR38LH/RH and STGR43LH. (aj) Install the plates between FR48 and FR59 at STGR38LH and STGR38RH. (ak) Install the corner sections at STGR38LH/RH between FR48 and FR59. (al) Modify the crossbeams from FR48 thru FR52 for the roller track installation. (am) Install the water drain connection between FR47 and FR48. (an) Install the water drain connection and the cavity drain access cover between FR49 and FR50.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 21 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(ao) Drill three holes in the outer skin between FR47 and FR49 and between STGR43LH and STGR42RH. (ap) Install the water drain connection between FR50 and FR51. (aq) Modify the routing of the hydraulic tubes between FR46 and FR50. (ar) Install the brackets for the pressure system and cavity drain system between FR51 and FR53. (as) Replace the APU fuel tube in the keel beam area between FR42 and FR47. (at) Install the ACT pressurization system between FR51 and FR53. (au) Remove and discard the attachment parts of the cable harnesses in the AFT cargo compartment crossbeam area between FR49 and FR55. (av) Install the brackets at crossbeams at FR 42 and between FR50 and FR54. (aw) Install/modify the cable harness 4605VB, 4607VB. (ax) Install the wires of cable harness 4209VB. (ay) Install the attachment parts of the cable harnesses in the AFT cargo compartment crossbeam area between FR49 and FR55. (az) Attach the placards printed with the modification and the SB-number to the cable harnesses. (ba) Install the AFT cargo compartment floor panels between FR47 and FR59. (bb) Install the AFT cargo compartment floor panels between FR47 and FR59. (bc) Install the seal section in the gaps between the AFT cargo compartment floor panels between FR47 and FR59. (bd) Install the AFT cargo compartment ceiling panels between FR47 and FR59. (be) Install the passenger compartment floor panels 241JF, 251AF 251BF, 251FF, 251GF and 252BF. (bf) Install the insulation blankets at FR46. (bg) Install the LH sidewall panels between FR46 and FR58. (bh) Install the RH sidewall panels between FR46 and FR52A. (bi) Install the AFT cargo compartment panels 151AW, 151BW and 152BW at FR47. (6) Config. 03 AI-F Part (a) Install the doublers on the upper surface panels DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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(b) Install the brackets on the upper surface panels (c) Install the rod on the upper surface panels (d) Install the bracket on FR42 (e) Install the bracket above FR42 (f) Install the brackets on the lower surface panels (g) Install the rod and the plate on the lower surface panels (h) Install the Additional Center Tank (ACT) door (i) Install the equipment on the ACT door (j) Replace the Fuel Quantity Indicator (FQI) 6QT (k) Modify the pipes in the center tank (l) Install the ACT pipes in the center tank (m) Install the transfer elbow (n) Install the air ventilation elbow (o) Apply the sealing protection to the center tank (p) Modify the equipment in the HYD/Fuel Panel 40VU (q) Modify the equipment and the wiring in the Rear C/B Panel 121VU (r) Install the routing of the Relay Box 802VU, between FR4 and FR5, in the avionics compartment (s) Install the connectors 1975VC and 1982VC between FR33 and FR34 (t) Modify the equipment in the AFT Electronics Rack 80VU (u) Modify the equipment in the Relay Box 103VU (v) Modify the equipment in the Contactor Box 107VU (w) Modify the wiring in the aircraft (x) Modify the equipment in the FWD Electronics Rack 90VU (y) Modify the marking on the belly fairing, between FR47 and FR53 (7) Config. 03 AI-GE Part 1 (a) Remove the nets from the AFT cargo compartment. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 23 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(b) Remove the Tie Down Points (TDPs) from the AFT cargo compartment. (c) Remove the belly fairing panels 197AB and 198GB. (d) Modify the attachment structure of the belly fairing panels 197AB and 198GB. (e) Remove and not reuse the pressure reservoirs for the offwing escape slides, LH/RH. (f) Remove and discard the placards at the AFT cargo compartment lining panels between FR47 and FR48, LH/RH. (g) Modify the insulation blankets. (h) Relocate the release cable for the offwing slide, LH. (i) Relocate the release cable for the offwing slide, RH. (j) Install the pressure reservoir of the offwing escape slide LH/RH. (k) Install a bracket at the passenger compartment floor structure at FR53. (l) Install the additional angles at the webs of the keel beam structure between FR42 and FR46. (m) Replace the fasteners between FR42 and FR44, LH/RH. (n) Remove and discard the attachment structure of the partition panels 151AW, 151BW and 152BW between FR46 and FR47. (o) Modify the structure. (p) Replace fasteners at FR48, FR49, FR50 and FR51 between STGR34LH and STGR36LH. (q) Replace fasteners at FR52, FR53 and FR54 between STGR34LH and STGR36LH. (r) Install Longitudinal profiles at the cargo compartment floor structure between FR53 an FR59. (s) Measure the level of the AFT cargo compartment floor structure. (t) Install the water drain connection and the cavity drain access cover between FR52 and FR53. (u) Install the shims on the floor framework of the AFT cargo compartment between FR47 and FR54. (v) Install the roller tracks between FR47 and FR54 in the AFT cargo compartment. (w) Install/Adjust the YZ-latches at FR47, FR48 and FR49 and adjust the XZ-latches. (x) Install/Adjust the YZ-latches at FR50, FR51 and FR52 and adjust the XZ-latches. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 24 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(y) Install the shims on the frames of the AFT cargo compartment at FR47, FR48, FR49, FR50 and FR51. (z) Install the brackets for the fuel drain/vent systems between FR42 and FR43 (aa) Install the beam between FR46 and FR47. (ab) Install the fuel transfer line between FR41 and FR47. (ac) Install the vent line between FR37 and FR47. (ad) Install the cover between FR46 and FR47 at the fuel transfer line and vent line. (ae) Install the system between FR37 and FR48. (af) Install the cavity drain and monitoring system between FR46 and FR50. (ag) Install the cavity drain and monitoring system between FR50 and FR53. (ah) Install the attachment structure of the partition panels and floor panels. (ai) Remove and discard the attachment parts at FR42. (aj) Remove and discard the attachment parts at FR42. (ak) Remove and discard the attachment parts between FR46 and FR49. (al) Remove and discard the attachment parts at FR46 and FR54. (am) Remove and discard the attachment parts at FR46 and FR54. (an) Remove the cable harnesses , 4628VB, 4655VB, 4656VB, 4661VB, 4662VB, 4663VB, 4664VB, 4670VB, 4671VB, 4672VB, 4673VB, 4680VB, 4681VB, 4683VB, 4692VB, 4693VB 4694VB. (ao) Remove the cable harnesses 4213VB, 4214VB, 4216VB, 4218VB, 4220VB, 4221VB, 4222VB, 4223VB, 4224VB, 4225VB, 4226VB, 4227VB, 4232VB, 4233VB, 5214VB, 5220VB, 5224VB, 5233VB. (ap) Install the attachment parts at FR42. (aq) Install the attachment parts between FR46 and FR54. (ar) Install the attachment parts in the bilge area between FR46 and FR54. (as) Install the attachment parts at FR42. (at) Install the attachment parts between FR46 and FR49. (au) Replace the cap assembly of the AFT cargo-compartment smoke-detectors (3WH, 4WH) between FR52 and FR53. (av) Seal the gaps at the installed passenger compartment floor panels. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 25 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(aw) Install these protection covers on the roller tracks between FR53 and FR54. (ax) Replace the placards at the side wall panels in the AFT cargo compartment. (ay) Install the belly fairing panels 197AB and 198GB. (az) Install the Tie Down Points (TDP’s) in the AFT cargo compartment. (ba) Replace Tie Down Point (TDP) and the stanchion bracket in the ceiling area of the AFT cargo compartment. (bb) Install the nets in the AFT cargo compartment. (bc) Install the equipment for the ACT pressurization system between FR48 and FR54. (bd) Install the Relay box in the forward avionics compartment. (be) Remove and discard the refuel/defuel panel mounting assembly in the belly fairing, zone 192. (8) Config. 03 AI-GE, Part 2 (a) Remove and discard the overhead stowage compartments between FR43 and FR47. (b) Remove and discard the placards at the overhead stowage compartments between FR43 and FR47. (c) Modify the electrical equipment. (d) Install the overhead stowage compartment. (e) Install the placards on the overhead stowage compartment. (f) Remove and discard the passenger compartment floor panels 241JF, 251AF 251BF, 251FF, 251GF and 252BF. (g) Remove the LH sidewall panels between FR46 and FR58. (h) Remove the RH sidewall panels between FR46 and FR52A. (i) Remove and discard the insulation blankets at FR46. (j) Remove the AFT cargo compartment ceiling panels between FR47 and FR59. (k) Remove and discard the floor panels from the AFT cargo compartment, between FR47 and FR56. (l) Remove and discard the sloped floor panels from the AFT cargo compartment, between FR47 and FR59. (m) Remove the cable harness 4209VB. (n) Modify the structure. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 26 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(o) Install the struts at the beam between FR46 and FR47. (p) Replace fasteners between FR42 and FR46 at several places. (q) Drill the holes in FR46 between STGR42LH and STGR43LH. (r) Modify the structure of FR47 between STGR35LH to STGR35RH. (s) Modify the structure between FR47 and FR48 at STGR38LH/RH and STGR43LH. (t) Remove the corner profiles at STGR38LH/RH between FR48 and FR56. (u) Remove the shear plates at STGR38LH/RH between FR48 and FR59. (v) Remove the crossbeams at FR48, FR49, FR50 and FR51 in the AFT cargo compartment. (w) Remove the crossbeams at FR52, FR53 and FR54 in the AFT cargo compartment. (x) Modify the structure at FR48 between STGR34LH and STGR34RH. (y) Modify the structure at FR49 between STGR34LH and STGR34RH. (z) Modify the structure at FR50 between STGR34LH and STGR34RH. (aa) Modify the structure at FR51 between STGR34LH and STGR34RH. (ab) Modify the structure at FR52 between STGR34LH and STGR34RH. (ac) Modify the structure at FR52A between STGR38RH and STGR40RH. (ad) Modify the structure at FR53 between STGR34LH and STGR41RH. (ae) Modify the structure at FR53 between STGR36LH and STGR42LH. (af) Modify the structure at FR54 between STGR34LH and STGR41RH. (ag) Install the shear plates between FR48 and FR51 at STGR43LH. (ah) Install the shear plates between FR51 and FR54 at STGR43LH. (ai) Drill additional fastener holes between FR51 and FR54. (aj) Modify the structure between FR47 and FR48 at STGR38LH/RH and STGR43LH. (ak) Install the plates between FR48 and FR59 at STGR38LH and STGR38RH. (al) Install the corner sections at STGR38LH/RH between FR48 and FR59. (am) Modify the crossbeams from FR48 thru FR52 for the roller track installation. (an) Install the water drain connection between FR47 and FR48. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 27 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(ao) Install the water drain connection and the cavity drain access cover between FR49 and FR50. (ap) Drill three holes in the outer skin between FR47 and FR49 and between STGR43LH and STGR42RH. (aq) Install the water drain connection between FR50 and FR51. (ar) Modify the routing of the hydraulic tubes between FR46 and FR50. (as) Install the brackets for the fuel drain/vent systems between FR46 and FR54. (at) Install the brackets for the pressure system and cavity drain system between FR51 and FR53. (au) Replace the APU fuel tube in the keel beam area between FR42 and FR47. (av) Install the ACT pressurization system between FR51 and FR53. (aw) Install the ACT pressurization system between FR48 and FR54. (ax) Install the attachment parts of the cable harnesses in the AFT cargo compartment crossbeam area between FR49 and FR55. (ay) Install the brackets at crossbeams at FR42 and between FR50 and FR54. (az) Install/modify the cable harness 4606VB, 4607VB. (ba) Install the wires of cable harness 4209VB. (bb) Install the attachment parts of the cable harnesses in the AFT cargo compartment crossbeam area between FR49 and FR55. (bc) Attach the placards printed with the modification and the SB-number to the cable harnesses. (bd) Install the AFT cargo compartment floor panels between FR47 and FR59. (be) Install the AFT cargo compartment floor panels between FR47 and FR59. (bf) Install the seal section in the gaps between the AFT cargo compartment floor panels between FR47 and FR59. (bg) Install the AFT cargo compartment ceiling panels between FR47 and FR59. (bh) Install the passenger compartment floor panels 241JF, 251AF 251BF, 251FF, 251GF and 252BF. (bi) Install the insulation blankets at FR46. (bj) Install the LH sidewall panels between FR46 and FR58. (bk) Install the RH sidewall panels between FR46 and FR52A. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 28 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(bl) Install the AFT cargo compartment panels 151AW, 151BW and 152BW at FR47. **E. C O** **M P** **L I** **A N** **C E**  (1) Classification Optional (2) Accomplishment Timescale In accordance with operators’ maintenance schedule. **F. A P** **P R** **O V**  **A L**  Approved under EASA Design Organization Approval No. EASA 21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. **G. M A** **N P** **O W** **E R**  The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operators’ circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying time for paints, sealants, etc. and general administration work are also not included. Config. 01 Complete Modification on Aircraft 2000 **TOTAL MANHOURS 2000**  **ELAPSED TIME (HOURS) 450**  Config. 02 Complete Modification on Aircraft 2010 **TOTAL MANHOURS 2010**  **ELAPSED TIME (HOURS) 455**  Config. 03 Complete Modification on Aircraft 2010 **TOTAL MANHOURS 2010**  **ELAPSED TIME (HOURS) 455**  DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 29 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

**H. W E** **I G** **H T** **A N** **D B** **A L** **A N** **C E**  Config. 01 Manufacturers Empty Weight : +321.212 kg (+708.1439 lb) Effect on Balance : +7035.819 kgm (+50890.078 lb.ft) Config. 02 Manufacturers Empty Weight : +340.218 kg (+750.0446 lb) Effect on Balance : +7504.477 kgm (+54279.882 lb.ft) Config. 03 Manufacturers Empty Weight : +340.218 kg (+750.0446 lb) Effect on Balance : +7504.477 kgm (+54279.882 lb.ft) **I. E L** **E C** **T R** **I C** **A L** **L O** **A D** **D A** 

**T**

**A** Not changed

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 30 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

**J. R E** **F E** **R E** **N C** **E S**  Aircraft Maintenance Manual (AMM) : 06-31-53 06-41-53 07-11-00 11-00-00 12-34-24 20-21-11 20-21-12 20-21-15 20-23-11 20-28-00 21-26-00 21-31-00 21-43-00 21-43-34 21-52-41 21-55-00 21-61-51 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 25-33-41 25-54-12 25-55-00 25-55-11 25-62-42 25-62-43 25-62-46 25-80-00 26-12-00 26-13-00 26-16-15 26-17-00 26-17-34 26-21-00 26-22-00 27-24-00 27-34-00 27-51-00 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 28-23-51 28-24-00 28-25-00 28-25-51 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 29-00-00 29-10-00 29-11-00 29-11-41 29-12-00 29-13-00 29-13-14 29-14-00 29-22-00 29-23-00 29-24-00 29-31-00 29-32-00 29-33-11 29-34-00 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 36-11-00 36-12-00 49-61-34 49-62-00 52-10-00 52-30-00 52-35-00 52-41-00 52-41-16 52-41-23 53-22-12 53-22-14 53-32-12 53-35-11 53-42-12 53-42-14 73-25-34 74-00-00 78-31-00 Elec. Std. Practices Manual (ESPM) : 20-25-51 20-33-00 20-33-44 20-44-22 20-44-24 20-44-71 20-51-10 20-52-21 20-55-00 Structural Repair Manual (SRM) : 51-22-00 51-23-00 51-24-00 51-42-11 51-43-12 51-44-11 51-46-11 51-71-11 51-75-11 Consumable Material List (CML) Standards Manual (SM) DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Service Bulletin A320-28-1081 Appendix 1 Appendix 2 Top Drawing D00071141000, Sheet(s) 01, Issue C Top Drawing D00071141004, Sheet(s) 03, Issue C Top Drawing D00071141008, Sheet(s) 05, Issue E DESIGN DRAWINGS SHEET(S) 281132A00001 A00 Sheet(s) 01 281132A00001 A00 Sheet(s) 02 281132A00001 A00 Sheet(s) 03 281132A00001 A00 Sheet(s) 04 281132A00002 A00 Sheet(s) 01 281132A00002 A00 Sheet(s) 02 281132A00002 A00 Sheet(s) 03 281132A00002 A00 Sheet(s) 04 281132A00002 B00 Sheet(s) 05 281132A00003 A00 Sheet(s) 01 281132A00003 A00 Sheet(s) 02 281132A00003 A00 Sheet(s) 03 281132A00003 A00 Sheet(s) 04 281132A00003 A00 Sheet(s) 05 281132A01001 A00 Sheet(s) 01 281132A01001 A00 Sheet(s) 02 281132A01001 B00 Sheet(s) 03 281132A01002 A00 Sheet(s) 01 281132A01003 A00 Sheet(s) 01 281132A01003 A00 Sheet(s) 02 281132A01003 A00 Sheet(s) 03 281132A01003 B00 Sheet(s) 04 281132A01004 A00 Sheet(s) 01 281132A02001 A00 Sheet(s) 01 281132A02002 A00 Sheet(s) 01 281132A02002 A00 Sheet(s) 02 281132A02002 B00 Sheet(s) 03 281132A02003 A00 Sheet(s) 01 281132A02003 A00 Sheet(s) 02 281132A02003 B00 Sheet(s) 03 281132A02004 A00 Sheet(s) 01 281132A02004 A00 Sheet(s) 02 281132A03001 A00 Sheet(s) 01 281132A03002 A00 Sheet(s) 01 281132A03002 A00 Sheet(s) 02 281132A03003 A00 Sheet(s) 02 281132A03003 A00 Sheet(s) 03 281132A03003 A00 Sheet(s) 04 281132A03003 B00 Sheet(s) 01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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DESIGN DRAWINGS SHEET(S) 281132A03003 B00 Sheet(s) 05 281132A04001 A00 Sheet(s) 01 281132A04001 A00 Sheet(s) 02 281132A04001 A00 Sheet(s) 03 281132A04002 A00 Sheet(s) 01 281132A04002 A00 Sheet(s) 02 281132A04002 A00 Sheet(s) 03 281132A04002 A00 Sheet(s) 04 281132A04003 A00 Sheet(s) 01 281132A04003 A00 Sheet(s) 02 281132A04003 A00 Sheet(s) 03 281132A04003 A00 Sheet(s) 04 281132A04003 A00 Sheet(s) 05 281132A04003 B00 Sheet(s) 06 281132A04003 B00 Sheet(s) 07 281132A04004 A00 Sheet(s) 01 281132A04005 A00 Sheet(s) 01 281132A04006 A00 Sheet(s) 01 281132A04007 A00 Sheet(s) 01 281132A04008 A00 Sheet(s) 01 281132A04009 A00 Sheet(s) 01 281132A04010 A00 Sheet(s) 01 281132A04011 A00 Sheet(s) 01 281132A04011 A00 Sheet(s) 02 281132A04012 A00 Sheet(s) 01 281132A04013 B00 Sheet(s) 01 281132A05001 A00 Sheet(s) 01 281132A05002 A00 Sheet(s) 01 281132A05003 A00 Sheet(s) 01 281132A05003 A00 Sheet(s) 02 281132A06001 A00 Sheet(s) 01 281132A06002 A00 Sheet(s) 01 281132A06002 A00 Sheet(s) 02 281132A06003 A00 Sheet(s) 01 281132A06501 A00 Sheet(s) 01 281132A06501 A00 Sheet(s) 02 281132A06502 A00 Sheet(s) 01 281132A06502 A00 Sheet(s) 02 281132A06503 A00 Sheet(s) 01 281132A06503 A00 Sheet(s) 02 281132A06504 A00 Sheet(s) 01 281132A06504 A00 Sheet(s) 02 281132A06505 A00 Sheet(s) 01 281132A06505 A00 Sheet(s) 02 281132A06506 A00 Sheet(s) 01 281132A06506 A00 Sheet(s) 02 281132A06507 A00 Sheet(s) 01 281132A06507 A00 Sheet(s) 02 281132A06508 A00 Sheet(s) 01 281132A06508 A00 Sheet(s) 02 281132A06509 A00 Sheet(s) 01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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DESIGN DRAWINGS SHEET(S) 281132A06509 A00 Sheet(s) 02 281132A06510 A00 Sheet(s) 01 281132A06510 A00 Sheet(s) 02 281132A06511 A00 Sheet(s) 01 281132A06511 A00 Sheet(s) 02 281132A10001 A00 Sheet(s) 01 281132A10001 A00 Sheet(s) 02 281132A10002 A00 Sheet(s) 01 281132A10003 A00 Sheet(s) 01 281132A10003 A00 Sheet(s) 02 281132A10004 A00 Sheet(s) 01 281132A10004 A00 Sheet(s) 02 281132A10005 A00 Sheet(s) 01 281132A10005 A00 Sheet(s) 02 281132A10006 A00 Sheet(s) 01 281132A10006 A00 Sheet(s) 02 281132A10007 A00 Sheet(s) 01 281132A10007 A00 Sheet(s) 02 281132A10007 A00 Sheet(s) 03 281132A10008 A00 Sheet(s) 01 281132A10008 A00 Sheet(s) 02 281132A10501 A00 Sheet(s) 01 281132A10501 A00 Sheet(s) 02 281132A10502 A00 Sheet(s) 01 281132A10502 A00 Sheet(s) 02 281132A10502 A00 Sheet(s) 03 281132A10503 A00 Sheet(s) 01 281132A10503 A00 Sheet(s) 02 281132A10504 A00 Sheet(s) 01 281132A10504 A00 Sheet(s) 02 281132A10504 A00 Sheet(s) 03 281132A10505 A00 Sheet(s) 01 281132A10505 A00 Sheet(s) 02 281132A10505 A00 Sheet(s) 03 281132A10506 A00 Sheet(s) 01 281132A10506 A00 Sheet(s) 02 281132A10506 A00 Sheet(s) 03 281132A10507 A00 Sheet(s) 01 281132A10507 A00 Sheet(s) 02 281132A10508 A00 Sheet(s) 01 281132A10508 A00 Sheet(s) 02 281132A10509 A00 Sheet(s) 01 281132A10509 A00 Sheet(s) 02 281132A10510 A00 Sheet(s) 01 281132A10510 A00 Sheet(s) 02 281132A10510 A00 Sheet(s) 03 281132A10511 A00 Sheet(s) 01 281132A10511 B00 Sheet(s) 02 281132A10512 A00 Sheet(s) 01 281132A10512 A00 Sheet(s) 02 281132A10513 A00 Sheet(s) 01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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DESIGN DRAWINGS SHEET(S) 281132A10513 A00 Sheet(s) 02 281132A10514 A00 Sheet(s) 01 281132A10514 A00 Sheet(s) 02 281132A10515 A00 Sheet(s) 01 281132A10515 A00 Sheet(s) 02 281132A10516 A00 Sheet(s) 01 281132A10516 A00 Sheet(s) 02 281132A10517 A00 Sheet(s) 01 281132A10517 A00 Sheet(s) 02 281132A10518 A00 Sheet(s) 01 281132A10518 A00 Sheet(s) 02 281132A10519 A00 Sheet(s) 01 281132A10519 A00 Sheet(s) 02 281132A10520 A00 Sheet(s) 01 281132A10520 A00 Sheet(s) 02 281132A10521 A00 Sheet(s) 01 281132A10521 A00 Sheet(s) 02 281132A10522 A00 Sheet(s) 01 281132A10522 A00 Sheet(s) 02 281132A11001 A00 Sheet(s) 01 281132A11002 A00 Sheet(s) 01 281132A11002 B00 Sheet(s) 02 281132A11003 A00 Sheet(s) 01 281132A11003 A00 Sheet(s) 02 281132A14001 A00 Sheet(s) 01 281132A15001 A00 Sheet(s) 01 281132A15002 A00 Sheet(s) 01 281132A15002 A00 Sheet(s) 02 281132A15003 A00 Sheet(s) 01 281132A15501 A00 Sheet(s) 01 281132A15501 A00 Sheet(s) 02 281132A15502 A00 Sheet(s) 01 281132A15502 A00 Sheet(s) 02 281132A15503 A00 Sheet(s) 01 281132A15503 A00 Sheet(s) 02 281132A15504 A00 Sheet(s) 01 281132A15504 A00 Sheet(s) 02 281132A15505 A00 Sheet(s) 01 281132A15505 A00 Sheet(s) 02 281132A15506 A00 Sheet(s) 01 281132A15506 A00 Sheet(s) 02 281132A15507 A00 Sheet(s) 01 281132A15507 A00 Sheet(s) 02 281132A15508 A00 Sheet(s) 01 281132A15508 A00 Sheet(s) 02 281132A15509 A00 Sheet(s) 01 281132A15509 A00 Sheet(s) 02 281132A15510 A00 Sheet(s) 01 281132A15510 A00 Sheet(s) 02 281132A15511 A00 Sheet(s) 01 281132A15511 A00 Sheet(s) 02 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 35 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281132A16001 A00 Sheet(s) 01 281132A16002 A00 Sheet(s) 01 281132A16003 A00 Sheet(s) 01 281132A16004 A00 Sheet(s) 01 281132A16004 A00 Sheet(s) 02 281132A18001 A00 Sheet(s) 01 281132A18001 A00 Sheet(s) 02 281132A18001 A00 Sheet(s) 03 281132A18001 A00 Sheet(s) 04 281132A19001 A00 Sheet(s) 01 281132A19002 A00 Sheet(s) 01 281132A19002 A00 Sheet(s) 02 281132A19002 A00 Sheet(s) 03 281132A19003 A00 Sheet(s) 01 281132A19003 A00 Sheet(s) 02 281132A19004 A00 Sheet(s) 01 281132A19004 A00 Sheet(s) 02 281132A19004 A00 Sheet(s) 03 281132A19005 A00 Sheet(s) 01 281132A19005 A00 Sheet(s) 02 281132A19006 A00 Sheet(s) 01 281132A19501 A00 Sheet(s) 01 281132A19501 A00 Sheet(s) 02 281132A19502 A00 Sheet(s) 01 281132A19502 A00 Sheet(s) 02 281132A19502 A00 Sheet(s) 03 281132A19503 A00 Sheet(s) 01 281132A19503 A00 Sheet(s) 02 281132A19504 A00 Sheet(s) 01 281132A19504 A00 Sheet(s) 02 281132A19504 A00 Sheet(s) 03 281132A19505 A00 Sheet(s) 01 281132A19505 A00 Sheet(s) 02 281132A19505 A00 Sheet(s) 03 281132A19506 A00 Sheet(s) 01 281132A19506 A00 Sheet(s) 02 281132A19506 A00 Sheet(s) 03 281132A19507 A00 Sheet(s) 01 281132A19507 A00 Sheet(s) 02 281132A19508 A00 Sheet(s) 01 281132A19508 A00 Sheet(s) 02 281132A19509 A00 Sheet(s) 01 281132A19509 A00 Sheet(s) 02 281132A19510 A00 Sheet(s) 01 281132A19510 A00 Sheet(s) 02 281132A19510 A00 Sheet(s) 03 281132A19511 A00 Sheet(s) 01 281132A19511 B00 Sheet(s) 02 281132A19512 A00 Sheet(s) 01 281132A19512 A00 Sheet(s) 02 281132A19513 A00 Sheet(s) 01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 36 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281132A19513 A00 Sheet(s) 02 281132A19514 A00 Sheet(s) 01 281132A19514 A00 Sheet(s) 02 281132A19515 A00 Sheet(s) 01 281132A19515 A00 Sheet(s) 02 281132A19516 A00 Sheet(s) 01 281132A19516 A00 Sheet(s) 02 281132A19517 A00 Sheet(s) 01 281132A19517 A00 Sheet(s) 02 281132A19518 A00 Sheet(s) 01 281132A19518 A00 Sheet(s) 02 281132A19519 A00 Sheet(s) 01 281132A19519 A00 Sheet(s) 02 281132A19520 A00 Sheet(s) 01 281132A19520 A00 Sheet(s) 02 281132A19521 A00 Sheet(s) 01 281132A19521 A00 Sheet(s) 02 281132A19522 A00 Sheet(s) 01 281132A19522 A00 Sheet(s) 02 281132A20001 A00 Sheet(s) 01 281132A20001 A00 Sheet(s) 02 281132A20001 A00 Sheet(s) 03 281132A20002 A00 Sheet(s) 01 281132A20003 A00 Sheet(s) 01 281132A20003 A00 Sheet(s) 02 281132A20003 A00 Sheet(s) 03 281132A20003 A00 Sheet(s) 04 281132A20004 A00 Sheet(s) 01 281132A21001 A00 Sheet(s) 01 281132A21002 A00 Sheet(s) 01 281132A21002 A00 Sheet(s) 02 281132A21002 A00 Sheet(s) 03 281132A21003 A00 Sheet(s) 01 281132A21003 A00 Sheet(s) 03 281132A21003 A00 Sheet(s) 04 281132A21003 B00 Sheet(s) 02 281132A21004 A00 Sheet(s) 01 281132A21004 A00 Sheet(s) 02 281132A23001 A00 Sheet(s) 01 281132A23002 A00 Sheet(s) 01 281132A23002 A00 Sheet(s) 02 281132A23003 A00 Sheet(s) 01 281132A23003 A00 Sheet(s) 02 281132A23003 A00 Sheet(s) 03 281132A23003 A00 Sheet(s) 04 281132A23003 A00 Sheet(s) 05 281132A24001 A00 Sheet(s) 01 281132A24001 A00 Sheet(s) 02 281132A24001 A00 Sheet(s) 03 281132A24002 A00 Sheet(s) 01 281132A24002 A00 Sheet(s) 02 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 37 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281132A24002 A00 Sheet(s) 03 281132A24002 A00 Sheet(s) 04 281132A24003 A00 Sheet(s) 01 281132A24003 A00 Sheet(s) 02 281132A24003 A00 Sheet(s) 03 281132A24003 A00 Sheet(s) 04 281132A24003 A00 Sheet(s) 05 281132A24003 A00 Sheet(s) 06 281132A24004 A00 Sheet(s) 01 281132A24005 A00 Sheet(s) 01 281132A24006 A00 Sheet(s) 01 281132A24007 A00 Sheet(s) 01 281132A24008 A00 Sheet(s) 01 281132A24009 A00 Sheet(s) 01 281132A24010 A00 Sheet(s) 01 281132A24011 A00 Sheet(s) 01 281132A24011 A00 Sheet(s) 02 281132A24012 A00 Sheet(s) 01 281132A24013 A00 Sheet(s) 01 281132A25001 A00 Sheet(s) 01 281132A25001 A00 Sheet(s) 02 281132A25002 A00 Sheet(s) 01 281132A25003 A00 Sheet(s) 01 281132A25003 A00 Sheet(s) 02 281132A25004 A00 Sheet(s) 01 281132A25004 A00 Sheet(s) 02 281132A25005 A00 Sheet(s) 01 281132A25005 A00 Sheet(s) 02 281132A25006 A00 Sheet(s) 01 281132A25006 A00 Sheet(s) 02 281132A25007 A00 Sheet(s) 01 281132A25007 A00 Sheet(s) 02 281132A25007 A00 Sheet(s) 03 281132A25008 A00 Sheet(s) 01 281132A25008 A00 Sheet(s) 02 281132A25501 A00 Sheet(s) 01 281132A25501 A00 Sheet(s) 02 281132A25502 A00 Sheet(s) 01 281132A25502 A00 Sheet(s) 02 281132A25502 A00 Sheet(s) 03 281132A25503 A00 Sheet(s) 01 281132A25503 A00 Sheet(s) 02 281132A25504 A00 Sheet(s) 01 281132A25504 A00 Sheet(s) 02 281132A25504 A00 Sheet(s) 03 281132A25505 A00 Sheet(s) 01 281132A25505 A00 Sheet(s) 02 281132A25505 A00 Sheet(s) 03 281132A25506 A00 Sheet(s) 01 281132A25506 A00 Sheet(s) 02 281132A25506 A00 Sheet(s) 03 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 38 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281132A25507 A00 Sheet(s) 01 281132A25507 A00 Sheet(s) 02 281132A25508 A00 Sheet(s) 01 281132A25508 A00 Sheet(s) 02 281132A25509 A00 Sheet(s) 01 281132A25509 A00 Sheet(s) 02 281132A25510 A00 Sheet(s) 01 281132A25510 A00 Sheet(s) 02 281132A25510 A00 Sheet(s) 03 281132A25511 A00 Sheet(s) 01 281132A25511 A00 Sheet(s) 02 281132A25512 A00 Sheet(s) 01 281132A25512 A00 Sheet(s) 02 281132A25513 A00 Sheet(s) 01 281132A25513 A00 Sheet(s) 02 281132A25514 A00 Sheet(s) 01 281132A25514 A00 Sheet(s) 02 281132A25515 A00 Sheet(s) 01 281132A25515 A00 Sheet(s) 02 281132A25516 A00 Sheet(s) 01 281132A25516 A00 Sheet(s) 02 281132A25517 A00 Sheet(s) 01 281132A25517 A00 Sheet(s) 02 281132A25518 A00 Sheet(s) 01 281132A25518 A00 Sheet(s) 02 281132A25519 A00 Sheet(s) 01 281132A25519 A00 Sheet(s) 02 281132A25520 A00 Sheet(s) 01 281132A25520 A00 Sheet(s) 02 281132A25521 A00 Sheet(s) 01 281132A25521 A00 Sheet(s) 02 281132A25522 A00 Sheet(s) 01 281132A25522 A00 Sheet(s) 02 D23793324001 Sheet(s) 1 D25278404054 Sheet(s) 48 and 49 D25278439090 Sheet(s) 42 D25286364010 Sheet(s) 7 and 8 D25288767000 Sheet(s) 1 and 2 D25570049000 Sheet(s) 1 D25570049002 Sheet(s) 2 D25570049004 Sheet(s) 3 D25570049006 Sheet(s) 4 D25570049008 Sheet(s) 5 D25570049010 Sheet(s) 6 D25570049012 Sheet(s) 7 and 17 D25570049014 Sheet(s) 8 D25570049016 Sheet(s) 9 D25572624008 Sheet(s) 8, 11 and 15 D25572624000 Sheet(s) 1 thru 3 D25572624002 Sheet(s) 4 and 5 D25572624004 Sheet(s) 6 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 39 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) D25572624006 Sheet(s) 6 and 7 D25572624008 Sheet(s) 8 thru 16 D25572624010 Sheet(s) 17 and 18 D25572624012 Sheet(s) 19 D25572624026 Sheet(s) 35 D25572624028 Sheet(s) 36 D25573522000 Sheet(s) 1 D25573525000 Sheet(s) 1 thru 4. D25670762000 Sheet(s) 1 thru 7 D25671745000 Sheet(s) 1 thru 7 D25671746000 Sheet(s) 1 thru 4 D25690000004 Sheet(s) 7 thru 9 D25870003028 Sheet(s) 20 D25870003056 Sheet(s) 20 D26170100024 Sheet(s) 41 thru 42 D26170100028 Sheet(s) 41 thru 42 D28270515000 Sheet(s) 1 thru 4 D28270972002 Sheet(s) 6 thru 12 D28270973002 Sheet(s) 6 thru 10 D28270974002 Sheet(s) 4 thru 6 D28270975004 Sheet(s) 7 thru 15 D28270975006 Sheet(s) 8, 11 and 13 thru 16 D28270982002 Sheet(s) 19 and 25 D28270982004 Sheet(s) 12 thru 14, 17, 19, 20, 22 and 25 thru 27 D28270982006 Sheet(s) 12 thru 14 and 17 thru 28 D28270990002 Sheet(s) 2 and 4 D28270991000 Sheet(s) 1 thru 3 D28270991002 Sheet(s) 1 thru 3 D28270992002 Sheet(s) 1, 2, 3 and 5 D28270998002 Sheet(s) 2 D28270999004 Sheet(s) 3 D28271200002 Sheet(s) 3 thru 6 D32170220004 Sheet(s) 5 D32170220005 Sheet(s) 5 D53370297002 Sheet(s) 1 thru 12 D53370297003 Sheet(s) 1 thru 12 D53370780004 Sheet(s) 2 D53371046000 Sheet(s) 1 thru 5 D53371237000 Sheet(s) 1 D53371237001 Sheet(s) 1 D53372362004 Sheet(s) all D53372362008 Sheet(s) all D53470075002 Sheet(s) 1 thru 14 D53470075004 Sheet(s) 2 thru 4, 6, 7, 14 and 16 D53470075008 Sheet(s) 18 thru 31 D53470076002 Sheet(s) 18 and 21 D53470076004 Sheet(s) 1 thru 10 D53470076008 Sheet(s) 11, 12 thru 21 D53470095002 Sheet(s) 1 D53470096002 Sheet(s) 1 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 40 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) D53472833008 Sheet(s) 4 D53474078000 Sheet(s) 1 D53474078002 Sheet(s) 1 D53475024000 Sheet(s) 1 thru 6 D53672854000 Sheet(s) 1 D53672856000 Sheet(s) 1 D53675015000 Sheet(s) 1 D53675015004 Sheet(s) 7 thru 9 D53675015006 Sheet(s) 10 thru 12 D53675016000 Sheet(s) 1 and 2 D53675510010 Sheet(s) 16 D53675510010 Sheet(s) 16 thru 18 D53675510012 Sheet(s) 19, 20 and 21 D53675520008 Sheet(s) 13 thru 15 D53675520010 Sheet(s) 16 thru 18 D53675520012 Sheet(s) 19 and 20 D53675525002 Sheet(s) 4 thru 8 D53975018002 Sheet(s) 9 thru 12 D53975019000 Sheet(s) 1 thru 6 D53975019000 Sheet(s) 3 D92355000 Sheet(s) 1 D92450032 Sheet(s) 6 and 7 D92450115 Sheet(s) 1 and 2 D92491681000 Sheet(s) 52 view V-V52. D92491681002 Sheet(s) 7 and 8 D92491681002 Sheet(s) 7 and 9 D92491681004 Sheet(s) 10 thru 35, 56 and 57 D92491681006 Sheet(s) 34 thru 45 D92491681010 Sheet(s) 49 thru 52 D92491681012 Sheet(s) 13, 15, 17, 19, 21, 46, 55, 58 and 59 D92492244002 Sheet(s) 10 D92550025 Sheet(s) 1 D92550032 Sheet(s) 1 and 2 D92556025 Sheet(s) 1 and 3 D92891805000 Sheet(s) 2, 4 thru 9, and 11 thru 15 D92891805002 Sheet(s) 16 thru 19 D92891805004 Sheet(s) 17 thru 49 D92891805008 Sheet(s) 3 thru 7, 9, 13 thru 15 and 53 thru 59 D92891805010 Sheet(s) 22, 23, 24, 28, 33 thru 41, 45, 48, 49, 59, 61 thru 63, 66 and 67 D92894713020 Sheet(s) 1 D92894713026 Sheet(s) 1 D92894736004 Sheet(s) 14 thru 17 D92894738042 Sheet(s) 1 D92990627012 Sheet(s) 17, 18, B01 to B03, H01 to H09, W01 and W02, X01 and X02, V01 to V05 D92990627013 Sheet(s) 17 and 19 D92990634001 Sheet(s) 2 and B01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 41 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) D92990634002 Sheet(s) 3 D92990820000 Sheet(s) 1 and B01 D92990820001 Sheet(s) 2 D92990824002 Sheet(s) 3, B01, H01, W01 and V01 D92990824007 Sheet(s) 7 D92990833000 Sheet(s) 1, B01, H01, W01, X01 and V01 D92990833001 Sheet(s) 2 D92991405000 Sheet(s) 1 D92991405001 Sheet(s) 2 D92991428013 Sheet(s) 18 D92991428014 Sheet(s) 12 and 19, H01 to H18 and W01 and W02, X01 and X02 D92991450015 Sheet(s) 11, V01 and V02 D92991455006 Sheet(s) 7, B01 and B02 and V01 D92991455007 Sheet(s) 6, H01, H02, W01 and X01 D92991455009 Sheet(s) 6, H01, H02, W01 and X01 D92991456004 Sheet(s) 5, B01 and B02 D92991456005 Sheet(s) 4, H01, H02, W01 and X01 D92991456007 Sheet(s) 4, H01, H02, W01 and X01 D92991461009 Sheet(s) 11, B01 and B02, H01 to H06, W01, X01 and V01 to V02 D92991461011 Sheet(s) 11, B01 and B02, H01 to H06, W01, X01 and V01 to V02 D92991461019 Sheet(s) 26, B01 to B04, H01 to H21, V01 to V05, W01 and W02, X01 D92991461020 Sheet(s) 27, B01 to B04, H01 to H21, W01 and W02, X01 and V01 to V05 D92991461021 Sheet(s) 26, B01 to B04, H01 to H21, V01 to V05, W01 and W02, X01 D92991461022 Sheet(s) 27, B01 to B04, H01 to H21, W01 and W02, X01 and V01 to V05 D92991462008 Sheet(s) 10, B01 and B02, H01 to H06, W01, X01, V01 and V02 D92991462010 Sheet(s) 10, B01 and B02, H01 to H06, W01, X01, V01 and V02 D92991463003 Sheet(s) 8, B01, H01 to H09, W01 and W02, X01 D92991463004 Sheet(s) 10, B01 and B02, H01 to H09, W01 and W02, X01 and V01 to V04 D92991464002 Sheet(s) 4 and B01 D92991464003 Sheet(s) 5, B01, H01 to H06, W01, X01 and V01 and V02 D92991470007 Sheet(s) 8, B01 to B04, H01 to H06, W01, X01, V01 to V03 D92991470008 Sheet(s) 9, B01 to B04, H01 to H06, W01, X01 and V01 to V03 D92991471005 Sheet(s) 7, B01 to B05, H01 to H07, W01 and W02, X01, V01 to V03 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 42 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) D92991471006 Sheet(s) 8, B01 to B05, H01 to H07, W01 and W02, X01 and V01 to V03 D92991472013 Sheet(s) 14, B01 and B02, H01 to H04, W01, X01, V01 and V02 D92991472015 Sheet(s) 12, B01 and B02, H01 to H03, W01, X01, V01 and V02 D92991473003 Sheet(s) 4, B01 and B02, H01 to H04, W01, X01, V01 and V02 D92991473004 Sheet(s) 3, B01 and B02, H01 to H04, W01, X01, V01 and V02 D92991480012 Sheet(s) 13, B01 to B03, H01 to H05, W01, X01, V01 and V02 D92991480013 Sheet(s) 16, B01 to B03, H01 to H04 and V01 and V02 D92991480015 Sheet(s) 16, B01 to B03, H01 to H04 and V01 and V02 D92991481003 Sheet(s) 4, B01, H01, W01, V01 D92991481004 Sheet(s) 5, B01, H01, W01, V01 D92991483005 Sheet(s) 6, B01 and B02, H01 to H09, W01 and W02, X01 and X02, V01 to V04 D92991483006 Sheet(s) 7, B01 and B02, H01 to H09, W01 and W02, X01 and X02, V01 to V04 D92991483008 Sheet(s) 7, B01 and B02, H01 to H09, W01 and W02, X01 and X02, V01 to V04 D92991492005 Sheet(s) 6, B01, H01, W01, X01, V01 D92991492006 Sheet(s) 7, B01, H01, W01, X01, V01 D92991493003 Sheet(s) 4, B01 and B02, H01 to H03, W01, X01, V01 and V02 D92991493004 Sheet(s) 3, B01 and B02, H01 to H03, W01, X01, V01 and V02 D92991494003 Sheet(s) 4, B01 and B02, H01 to H03, W01, X01, V01 and V02 D92991494004 Sheet(s) 3, B01 and B02, H01 to H03, W01, X01, V01 and V02 D9299229900 Sheet(s) 1 thru 40 D92992299002 Sheet(s) 1 thru 4 D92992299004 Sheet(s) 5 and B01 D92992299006 Sheet(s) 6 and B01 D92992299008 Sheet(s) 7 thru 9 and B01 D92992299010 Sheet(s) 10 thru 15 and B01 D92992299012 Sheet(s) 16, 17 and B01 D92992299014 Sheet(s) 18 thru 21 and B01 D92992299016 Sheet(s) 22 and B01 D92992299018 Sheet(s) 23 thru 28 and B01 D92992299020 Sheet(s) 29, 30 and B01 D92992299022 Sheet(s) 31, 32 and B01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 43 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) D92992299024 Sheet(s) 33 thru 36 and B01 D92992299026 Sheet(s) 37 and 38 and B01 D92992299028 Sheet(s) 39 and B01 D92992299030 Sheet(s) 40 and B01 D92997026001 Sheet(s) 1 and 2 D92997026002 Sheet(s) 3 thru7 D92997028002 Sheet(s) 1 and 2 and B01 D92997028004 Sheet(s) 3 and 4 and B01 D92997028006 Sheet(s) 5 and 6 and B01 D92997028010 Sheet(s) 9 and 10, B01 D92997028030 Sheet(s) 1 thru 4, 9 thru 10 and 24 thru 37 D92997028031 Sheet(s) 3 and 4 and B01 D92997028032 Sheet(s) 26 to 29, B01 D92997028033 Sheet(s) 30 and 31, B01 D92997028034 Sheet(s) 32 and 33, B01 D92997028035 Sheet(s) 34 to 36, B01 D92997028036 Sheet(s) 37 and 38, B01 D92997028037 Sheet(s) 39 and 40, B01 D92997028040 Sheet(s) 1 thru 4, 9 thru 10 and 24 thru 37 D92999559004 Sheet(s) 2 D92999559006 Sheet(s) 3 D92999559012 Sheet(s) 7 and 8 D92999559014 Sheet(s) 9 thru 12 D92999559016 Sheet(s) 13 D92999559020 Sheet(s) 18 and 19 D92999559024 Sheet(s) 21 thru 24 D92999559026 Sheet(s) 25 and 26 D92999559028 Sheet(s) 27 D92999559030 Sheet(s) 28 D92999561000 Sheet(s) all D92999561004 Sheet(s) 5 thru 7 D92999561006 Sheet(s) 8 thru 12 D92999561008 Sheet(s) 14 thru 19 D92999561010 Sheet(s) 20 and 21 D93070515002 Sheet(s) 1, 6 thru 12 D93070516000 Sheet(s) 1 thru 6 D93070668000 Sheet(s) 1 thru 8

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 44 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

**K. P U** **B L** **I C** **A T** **I O** **N S** **A F** **F E** **C T** **E D**  Aircraft Maintenance Manual (AMM) : 05-21-50 10-11-00 10-12-00 11-31-31 12-11-28 28-00-00 28-10-00 28-11-00 28-11-27 28-11-47 28-11-49 28-12-00 28-12-41 28-12-44 28-12-55 28-12-56 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 28-28-00 28-28-11 28-28-31 28-28-33 28-28-34 28-28-35 28-28-36 28-28-37 28-28-38 28-28-39 28-28-41 28-28-42 28-28-43 28-28-44 28-28-45 28-28-46 28-28-47 28-28-48 28-28-51 28-28-53 28-28-54 28-28-55 28-28-56 28-28-57 28-40-00 28-42-00 28-42-15 28-42-16 28-42-21 28-42-22 28-42-24 28-42-25 28-43-00 28-46-00 28-46-18 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 Illustrated Parts Catalog (IPC) : 11-31-31 11-31-34 11-36-28 24-92-02 25-71-01 25-71-11 28-25-05 28-25-08 28-25-59 28-28-03 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 31-14-11 33-13-08 53-16-01 57-11-05 57-16-05 57-17-05 57-17-11 Flight Crew Operating Manual (FCOM) : VOL 1 thru VOL 4 Master Minimum Equipment List (MMEL) 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 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 45 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

revision prior to SB embodiment. For this purpose, please request the intermediate revision by fax, telex or mail to : SEDCC, 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 (SEDCC). **L. I N** **T E** **R C** **H A** **N G** **E A** **B I** **L I** **T Y**  **/ M** **I X** **A B** **I L** **I T** **Y** Config. 01 DESCRIPTION OLD PART No. NEW PART No. INT MIXABILITY FQI 1407KID02-03 1418KID01-03 03 Not applicable FQIC SIC5059-11-0207 SIC5059-12-0308 03 Not applicable NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. Config. 02 DESCRIPTION OLD PART No. NEW PART No. INT MIXABILITY FQI 1407KID02-03 1418KID01-03 03 Not applicable NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. Config. 03 DESCRIPTION OLD PART No. NEW PART No. INT MIXABILITY FQI 1407KID02-03 1419KID01-03 03 Not applicable FQIC SIC5059-11-0207 SIC5059-14-20 03 Not applicable NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common Support Data Dictionary (CSDD), Chapter 2.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 46 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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

**A I** **L A** **B I** **L I** **T Y**  (1) Material Customers with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is : AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 HAMBURG GERMANY For ordering by internet : http://spares.airbus.com For SB Kits by fax : +49 40 50 76 25 90 For Spares by fax : +49 40 50 76 40 12 Vendor parts are to be purchased from : SMITHS AEROSPACE ELECTRONIC SYSTEMS PO BOX 188 GL52 8SF CHELTENHAM UNITED KINGDOM EATON AEROSPACE LTD STATION ROAD 3DW SOUTH MOLTON NORTH DEVON EX 36 UNITED KINGDOM FR-HITEMP LTD ABBEY PARK PO14 QA TITCHFIELD FAREHAM HANTS UNITED KINGDOM LIEBHERR - AEROSPACE TOULOUSE SA 408 AVENUE DES ETATS UNIS 31016 TOULOUSE CEDEX FRANCE (2) Price and Availability Sales terms must be agreed between the Customer and AIRBUS in accordance with the RFC (or RFC/RMO) procedure. **B. I N** **D U** **S T** **R Y** **S U** **P P** **O R** **T I** **N F** **O R** **M A**  **T I** **O N**  Refer to Paragraph 2.A.(2) : Price and Availability. **C. L I** **S T** **O F** **C O** **M P** **O N** **E N** **T S**  Kit 281132A01R01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 47 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 A2823301800202 Plate 4 ASNA2050DCJ3215 Rivet 4 ASNA2397-10L Washer 2 ASNA2397-416L Washer 53 ASNA2528-3 NUT

1 D2821334100000 Rod 1 D2821334220000 Bracket 1 D5713031920000 Doubler 1 D5713032000095 Loft 1 D5713304820004 Doubler 1 D5791042020095 Fitting 1 D5791042120095 Fitting 1 D5791042220095 Support 1 D5791042320095 Support 1 D5791043020095 Fitting 1 D5791048200095 Fitting 1 D5791048300095 Fitting 1 D5791049400095 Support 1 D5791049500095 Support 1 D5791049820095 Fitting 1 D5791050020095 Fitting 1 D5791332300000 Bracket 1 D5791332400000 Bracket 19 EN6115V3-3 Bolt 15 EN6115V3-4 Bolt 17 EN6115V3-5 Bolt

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

4 NSA5357-3-8 Pin 4 NSA5357-3-10 Pin 20 NSA5357-4-7 Pin 13 NSA5357-4-8 Pin

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

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132A02R02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 48 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 A2823301800202 Plate 2 ASNA2050DCJ3215 Rivet 12 ASNA2397-10L Washer

2 ASNA2397-416L Washer 1 D2821040120000 Plate 1 D2821040220000 Bracket 1 D2821334100200 Rod 1 D5791040020095 Bracket 1 D5791040120095 Bracket 1 D5791040220095 Bracket 1 D5791040320095 Bracket 1 D5791040400095 Support 1 D5791040500095 Support 1 D5791040620095 Bracket 1 D5791040720095 Bracket 1 D5791040820095 Bracket 1 D5791040920095 Bracket 1 D5791041020095 Bracket 1 D5791041820095 Support 8 NAS6603-2 Bolt 8 NAS6603-4 Bolt 2 NAS6604-9 Bolt 8 NSA5050-3 Nut 2 NSA5050-4 Nut 33 NSA5330-8 COLLAR

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

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

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132A03R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 1158000-15 Canister 1 1158000-21 Valve 1 568-1-27170-002 Pump 1 568-1-27171-002 Plate 1 A2821064620000 Insert 1 A2821064720000 Spring 1 A2821064820040 Pin 1 A2823260500000 Valve 1 A2823260820000 Plug 8 A5713052120300 Washer DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 49 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 15 ABS0114V4-18 Bolt

4 ASNA2055-03 Washer 1 ASNA2397-10L Washer 6 ASNA2397-416 Washer 1 ASNA2397-416L Washer 2 ASNA2397-6L Washer 8 ASNA2397D10L Washer 6 ASNA2397D416L Washer 1 D2821067800000 Bulkhead 1 D5713323000000 Door 1 D5713334000000 Fairing 1 D5713334400000 Fitting 1 D5713334500000 Fitting 1 D5713334600000 Fitting 2 E0088-10-100 Lead 1 E0088-16-100 Lead 1 E0088-16-125 Lead 1 HTE190001-2 Actuator 1 HTE8002 Clamp 1 HTE690045 Switch 1 HTE900135 Valve 15 MS20002C4 Washer

1 M MS20995C32 Wire 1 MS21042-06 Nut 1 MS21042L06 Nut 6 NAS1153-4 Screw 4 NAS1154-10 Screw 8 NAS1726C4E Nut 2 NAS1801-06-6 Screw 1 NAS1801-3-6 Screw 4 NAS6603-1 Bolt 3 NAS6603-2 Bolt 1 NAS6603-3 Bolt 4 NAS6603-5 Bolt 6 NAS6604-3 Bolt 6 NAS6604-7 Bolt 1 NAS6604-20 Bolt 6 NSA5050-3 Nut 1 NSA5050-4 Nut 1 NSA5112-04 Washer 3 NSA8200-6 Packing 1 NSA8203-019 O-Ring 1 NSA8203-113 O-Ring 1 NSA8203-154 O-Ring 1 NSA8203-167 O-Ring 1 NSA8203-224 O-Ring 1 NSA8203-226 O-Ring 1 NSA8203-245 O-Ring

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 50 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132A04R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 365A02 Valve 1 9843144M Valve 1 A2821038600000 Sleeve 1 A2821079520000 Flange 1 A2821120120000 Elbow 4 ABS0107-150 Nut 4 ABS0107-200 Nut 1 ASNA0182-1DA Strip 18 ASNA2397-10L Washer 24 ASNA2397-416L Washer

2 ASNA2397-6L Washer 4 ASNA2397D10L Washer 1 D2821331020000 Tee 1 D2821331320000 Tee 1 D2821331620000 Tee 1 D2821331920000 Elbow 1 D2821332220000 Elbow 1 D2821332620000 Elbow 1 D2821332900000 Elbow 1 D2821333220000 Elbow 1 D2821333420000 Elbow 1 D2821333800000 Sleeve 1 D2821333900000 Pipe 1 D2821333900100 Pipe 1 D2821333900300 Pipe 1 D2821333900400 Pipe 1 D2821333900600 Pipe 1 D2821333900700 Pipe 1 D2821333900900 Pipe 1 D2821333901000 Pipe 1 D2821334800000 Pipe 1 D2821334900000 Pipe 1 D2821335000000 Pipe 1 D2821335621800 RSTRCTR 1 D2821335800000 Pipe 1 D2821336300000 Sleeve 1 D2821336500000 Sleeve 1 D2821336621240 RSTRCTR 1 D2821336720240 RSTRCTR 1 D2821338500000 Pipe 2 E0088-10-100 Lead 1 E0088-10-160 Lead 3 E0088-10-200 Lead 1 E0088-10-280 Lead DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 51 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 MS21042L06 Nut 1 MS21902D4 Union 4 NAS1726-3E Nut 24 NAS1726-4E Nut

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

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

4 NAS6604-12 Bolt 20 NSA5050-3 Nut

6 NSA5050-4 Nut 1 NSA5516A04NF Clamp 1 NSA8200-4 Packing 1 NSA8200-5 Packing 1 NSA8203-215 O-Ring 18 NSA8203-222 O-Ring 13 NSA8203-226 O-Ring

4 NSA840003-150 Ring 4 NSA840003-200 Ring

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132A05R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 ASNA2397-10L Washer 12 ASNA2397-416L Washer

5 ASNA2397JD10L Washer 1 D2821330700000 Elbow 1 D2821334600000 Nutplate 1 D2821334700000 Nutplate 1 D2821337120000 Plate 1 D2821337500000 Nutplate 1 D2821337600000 Nutplate 1 D2821337700041 Elbow 1 D2821337800000 Filter 5 NAS6603-2 Bolt 2 NAS6603-5 Bolt 6 NAS6604-8 Bolt DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 52 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 6 NAS6604-9 Bolt 2 NSA5050-3 Nut 1 NSA8203-148 O-Ring 1 NSA8203-152 O-Ring

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132A06R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

20 ASNA2553-0401 Washer

1 D1131043320100 Placard 1 D1131043320200 Placard 1 D9000095128395 Bundle 1 D9100095114295 PLCRDSET 1 E0415C3LM078E Switch 1 E0416-02 Sleeve 1 E0417C01S CNCTR 20 E0736N08-01 Screw

2 NAS1102-04-6 Screw 8 NSA931305-01 Clamp 3 NSA931320-030 C/B 4 NSA931320-050 C/B 1 NSA931322-100 C/B 150 NSA935401-03 Tie 150 NSA935401-06 Tie 2 NSA939526-02 Shunt

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 281132A07R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D33110194A00 Plate

Kit 281132A08R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9251314920000 Plate

Kit 281132A09R00 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 53 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D00410468A00 Placard 1 D11311361A00 PLACARD

Kit 281132A10R02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 ASNA2050DCJ3215 Rivet 2 ASNA2051DCJ3215 Rivet 8 ASNA2397-10L Washer 1 ASNA2397-3L Washer 4 ASNA2397-4L Washer 1 D5391047900001 Bracket 1 D9000095128495 Bundle 1 D9000095128595 Bundle 1 D9000095131295 Bundle 1 D9100095114395 PLCRDSET 1 D9241244120000 Bracket 1 E0052R14B19SNF CNCTR 1 E0052R20B41SNF CNCTR 1 E0080-01-14C BACKSHLL 1 E0080-01-20C BACKSHLL 1 E0218UXU120A Relay 1 E0219ASUXU Base 1 E0245-28A0 RELAY 1 E0247A0S BASE 1 E0250A0S BASE 2 E0420-04 Stud 1 E0427-01A RETAINER 10 M E0432A14 Conduit

2 E0661-22 Mount 1 E0666D28A0 RELAY 4 EN3545-007SCD BACKSHLL 1 EN3545D01FXB22A CNCTR (01) 1 EN3545D03FXA22A CNCTR (02) 1 EN3545D03MXB22A CNCTR (03) 1 EN3545E03FXB24A CNCTR (04) 11 MS21042L04 Nut

1 NAS1100-04-6 Screw 3 NAS1100-04-7 Screw 6 NAS1726-3E Nut 3 NAS1801-3-8 Screw 5 NAS1801-3-9 Screw 1 NAS1801-3-20 Screw 1 NSA5527-03-01 Spacer 1 NSA932843AA01 Relay 1 NSA932844AA Base 100 NSA935401-03 Tie 200 NSA935401-04 Tie 200 NSA935401-05 Tie 800 NSA935401-06 Tie DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 54 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1500 NSA935401-08 Tie 4 NSA935504-01 Mount 1 NSA935504-03 Mount 1 NSA937901E0 IDENT 1 NSA937901E1 IDENT 2 NSA937901E2 IDENT 1 NSA937901E6 IDENT 1 NSA937901E8 IDENT 1 NSA937901MA2008 Module 1 NSA937901MA2204 Module 1 NSA937901MA2206 Module

NOTE(01) PN supplied with reference EN3545D01FXB00A. NOTE(01) PN supplied with reference EN3545D03FXA00A. NOTE(02) PN supplied with reference EN3545D03MXB00A. NOTE(03) PN supplied with reference EN3545E03FXB00A. NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132A11R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 3 ASNA2397-10L Washer 1 ASNA2397-3L Washer 5 ASNA2397-4L Washer 2 ASNA2397-6L Washer 1 D0003006100000 Rack 1 D9100095112895 PLCRDSET 1 D9251116900000 Plate 2 D9251127600000 Flange 1 E0161D01A12X CNCTR 1 E0247A0S BASE 1 E0425A2001 Module 1 E0427-01A RETAINER 1 E0666D28A0 RELAY 3 MS21042L04 Nut 1 NAS1100-04-6 Screw 4 NAS1100-04-7 Screw 4 NAS1100-06-12 Screw 3 NAS1102-3-10 Screw 6 NAS1726-3E Nut 3 NAS1801-3-8 Screw 1 NSA937901E1 IDENT DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 55 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 3 NSA937901E2 IDENT 1 NSA937901MA2011 Module 1 NSA937901MA2204 Module 5 NSA939511-03 Cover

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132A13R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D11311361A00 PLACARD 1 D11311658A00 PLACARD

Kit 281132A14R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2821336920000 PLACARD 1 D2821336920200 PLACARD 1 D2821336920400 PLACARD 1 D2821336920600 PLACARD 1 D2821336920800 PLACARD

Kit 281132A15R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 8 ABS0772A02A CLIP 1 ABS0951C3LM078 SWITCH 5 ASNA2083BG2-10 SCREW 1 ASNA2397-8L WASHER 1 D1131043320100 Placard 1 D1131043320200 Placard 1 D9000095128395 Bundle 1 D9100095114296 PLCRDSET 1 D9251314900000 PLATE 1 E0416-02 Sleeve 1 E0417C01S CNCTR 1 MS21042-08 NUT 28 NAS1102-04-5 SCREW

2 NAS1102-06-5 SCREW 4 NAS1102-06-7 SCREW 1 NAS1102-08-7 SCREW 3 NSA931320-030 C/B 4 NSA931320-050 C/B 1 NSA931322-100 C/B DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 56 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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

150 NSA935401-03 Tie 150 NSA935401-06 Tie 2 NSA939526-02 Shunt

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 281132A16R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 3 ASNA2397-10L Washer 1 ASNA2397-3L Washer 5 ASNA2397-4L Washer 2 ASNA2397-6L Washer 1 D0003006100000 Rack 1 D9100095112895 PLCRDSET 1 D9251116900000 Plate 2 D9251127600000 Flange 1 E0161D01A12X CNCTR 1 E0247A0S BASE 1 E0425A2001 Module 1 E0427-01A RETAINER 1 E0666D28A0 RELAY 3 MS21042L04 Nut 1 NAS1100-04-6 Screw 4 NAS1100-04-7 Screw 4 NAS1100-06-12 Screw 3 NAS1102-3-10 Screw 6 NAS1726-3E Nut 3 NAS1801-3-8 Screw 1 NSA937901E1 IDENT 3 NSA937901E2 IDENT 1 NSA937901MA2011 Module 1 NSA937901MA2204 Module 5 NSA939511-03 Cover

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132A17R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 30042-0000-0501 CTL UNIT

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 57 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Kit 281132A18R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D0041109120000 PLACARD 4 D1121004620000 PLACARD 2 D1121009120000 PLACARD

Kit 281132A19R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 5 ASNA2397-10L Washer 1 ASNA2397-3L Washer 4 ASNA2397-4L Washer 1 D9000095128495 Bundle 1 D9000095128595 Bundle 1 D9000095131295 Bundle 1 D9000095150195 BUNDLE 1 D9100095116795 PLCRDSET 1 E0080-01-14C BACKSHLL 1 E0080-01-20C BACKSHLL 1 E0245-28A0 RELAY 1 E0247A0S BASE 1 E0250A0S BASE 1 E0427-01A RETAINER 1 E0666D28A0 RELAY 4 EN3545-007SCD BACKSHLL 1 EN3545D03FXA22A CNCTR (01) 1 EN3545D03MXB22A CNCTR (02) 1 EN3545E01FXB22A CNCTR (03) 1 EN3545E03FXB24A CNCTR (04) 1 EN3646A61419BN CNCTR 1 EN3646A62041BN CNCTR 8 MS21042L04 Nut 1 NAS1101-04-6 SCREW 3 NAS1101-04-7 SCREW 5 NAS1801-3-8 Screw 1 NSA932843AA01 Relay 1 NSA932844AA Base 110 NSA935401-03 Tie 200 NSA935401-04 Tie 200 NSA935401-05 Tie 800 NSA935401-06 Tie 1500 NSA935401-08 Tie 1 NSA937901E0 IDENT 1 NSA937901E1 IDENT 1 NSA937901E2 IDENT 1 NSA937901E8 IDENT 1 NSA937901MA2008 Module 1 NSA937901MA2206 Module

NOTE(01) PN supplied with reference EN3545D03FXA00A. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 58 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

NOTE(02) PN supplied with reference EN3545D03MXB00A. NOTE(03) PN supplied with reference EN3545E01FXB00A. NOTE(04) PN supplied with reference EN3545E03FXB00A. NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132A20R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 A2823301800202 Plate 4 ASNA2050DCJ3215 Rivet 4 ASNA2397-10L Washer 2 ASNA2397-416L Washer 53 ASNA2528-3 NUT

1 D2821334100300 ROD 1 D2821334220000 Bracket 1 D5713031920000 Doubler 1 D5713032000095 Loft 1 D5713304820004 Doubler 1 D5791042020095 Fitting 1 D5791042120095 Fitting 1 D5791042220095 Support 1 D5791042320095 Support 1 D5791043020095 Fitting 1 D5791048200095 Fitting 1 D5791048300095 Fitting 1 D5791049400095 Support 1 D5791049500095 Support 1 D5791049820095 Fitting 1 D5791050020095 Fitting 1 D5791332300000 Bracket 1 D5791332400000 Bracket 19 EN6115V3-3 Bolt 15 EN6115V3-4 Bolt 17 EN6115V3-5 Bolt

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

4 NSA5357-3-8 Pin 4 NSA5357-3-10 Pin DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 59 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 12 NSA5357-4-7 Pin 13 NSA5357-4-8 Pin

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

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132A21R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 12 ASNA2397-10L Washer

2 ASNA2397-416L Washer 2 ASNA2536-3 NUT 2 ASNA2536-4 NUT 2 ASNA2536-5 NUT 1 D2821040120000 Plate 1 D2821040220000 Bracket 1 D2821334100400 ROD 1 D5791040020095 Bracket 1 D5791040320095 Bracket 1 D5791040400095 Support 1 D5791040500095 Support 1 D5791040620095 Bracket 1 D5791040720095 Bracket 1 D5791040820095 Bracket 1 D5791040920095 Bracket 1 D5791041020095 Bracket 1 D5791041820095 Support 1 D5791317500002 ANGLE 2 EN6115V3-6 BOLT 2 EN6115V4X-11 BOLT 2 EN6115V5X-13 BOLT 8 NAS6603-2 Bolt 8 NAS6603-4 Bolt 2 NAS6604-9 Bolt 8 NSA5050-3 Nut 2 NSA5050-4 Nut 31 NSA5330-8 COLLAR

1 NSA5330-10 Collar 8 NSA5357-4-9 Pin 5 NSA5357-4-10 Pin 17 NSA5357-4-11 Pin

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

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 60 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132A22R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5791050820001 BRACKET 1 D5791050920001 BRACKET

Kit 281132A23R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 A2821064620000 Insert 1 A2821064720000 Spring 1 A2821064820040 Pin 1 A2823260500000 Valve 1 A2823260820000 Plug 8 A5713052120300 Washer 15 ABS0114V4-18 Bolt

4 ASNA2055-03 Washer 1 ASNA2397-10L Washer 6 ASNA2397-416 Washer 1 ASNA2397-416L Washer 2 ASNA2397-6L Washer 8 ASNA2397D10L Washer 6 ASNA2397D416L Washer 1 D2821067800000 Bulkhead 1 D5713323000000 Door 1 D5713334000000 Fairing 1 D5713334400000 Fitting 1 D5713334500000 Fitting 1 D5713334600000 Fitting 2 E0088-10-100 Lead 1 E0088-16-100 Lead 1 E0088-16-125 Lead 15 MS20002C4 Washer

1 M MS20995C32 Wire 1 MS21042-06 Nut 1 MS21042L06 Nut 6 NAS1153-4 Screw 4 NAS1154-10 Screw 8 NAS1726C4E Nut 2 NAS1801-06-6 Screw 1 NAS1801-3-6 Screw 4 NAS6603-1 Bolt 3 NAS6603-2 Bolt 1 NAS6603-3 Bolt 4 NAS6603-5 Bolt 6 NAS6604-3 Bolt DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 61 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 6 NAS6604-7 Bolt 1 NAS6604-20 Bolt 6 NSA5050-3 Nut 1 NSA5050-4 Nut 1 NSA5112-04 Washer 3 NSA8200-6 Packing 1 NSA8203-019 O-Ring 1 NSA8203-113 O-Ring 1 NSA8203-154 O-Ring 1 NSA8203-167 O-Ring 1 NSA8203-224 O-Ring 1 NSA8203-226 O-Ring 1 NSA8203-245 O-Ring

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132A24R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 A2821038600000 Sleeve 1 A2821079520000 Flange 1 A2821120120000 Elbow 4 ABS0107-150 Nut 4 ABS0107-200 Nut 1 ASNA0182-1DA Strip 18 ASNA2397-10L Washer 24 ASNA2397-416L Washer

2 ASNA2397-6L Washer 4 ASNA2397D10L Washer 1 D2821331020000 Tee 1 D2821331320000 Tee 1 D2821331620000 Tee 1 D2821331920000 Elbow 1 D2821332220000 Elbow 1 D2821332620000 Elbow 1 D2821332900000 Elbow 1 D2821333220000 Elbow 1 D2821333420000 Elbow 1 D2821333800000 Sleeve 1 D2821333900000 Pipe 1 D2821333900100 Pipe 1 D2821333900300 Pipe 1 D2821333900400 Pipe 1 D2821333900600 Pipe 1 D2821333900700 Pipe 1 D2821333900900 Pipe DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 62 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2821333901000 Pipe 1 D2821334800000 Pipe 1 D2821334900000 Pipe 1 D2821335000000 Pipe 1 D2821335621800 RSTRCTR 1 D2821335800000 Pipe 1 D2821336300000 Sleeve 1 D2821336500000 Sleeve 1 D2821336621240 RSTRCTR 1 D2821336720240 RSTRCTR 1 D2821338500000 Pipe 2 E0088-10-100 Lead 1 E0088-10-160 Lead 3 E0088-10-200 Lead 1 E0088-10-280 Lead 2 MS21042L06 Nut 1 MS21902D4 Union 4 NAS1726-3E Nut 24 NAS1726-4E Nut

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

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

4 NAS6604-12 Bolt 20 NSA5050-3 Nut

6 NSA5050-4 Nut 1 NSA5516A04NF Clamp 1 NSA8200-4 Packing 1 NSA8200-5 Packing 1 NSA8203-215 O-Ring 18 NSA8203-222 O-Ring 13 NSA8203-226 O-Ring

4 NSA840003-150 Ring 4 NSA840003-200 Ring

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132A25R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 63 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 ASNA2050DCJ3215 Rivet 2 ASNA2051DCJ3215 Rivet 8 ASNA2397-10L Washer 1 ASNA2397-3L Washer 4 ASNA2397-4L Washer 1 D5391047900001 Bracket 1 D9000095128495 Bundle 1 D9000095128595 Bundle 1 D9000095131295 Bundle 1 D9000095150195 BUNDLE 1 D9000095400195 Bundle 1 D9100095116795 PLCRDSET 1 D9241244120000 Bracket 1 E0080-01-14C BACKSHLL 1 E0080-01-20C BACKSHLL 1 E0245-28A0 RELAY 1 E0247A0S BASE 1 E0250A0S BASE 2 E0420-04 Stud 1 E0427-01A RETAINER 10 M E0432A14 Conduit

2 E0661-22 Mount 1 E0666D28A0 RELAY 4 EN3545-007SCD BACKSHLL 1 EN3545D03FXA22A CNCTR (01) 1 EN3545D03MXB22A CNCTR (02) 1 EN3545E01FXB22A CNCTR (03) 1 EN3545E03FXB24A CNCTR (04) 1 EN3646A61419BN CNCTR 1 EN3646A62041BN CNCTR 8 MS21042L04 Nut 1 NAS1100-04-6 Screw 3 NAS1100-04-7 Screw 6 NAS1726-3E Nut 3 NAS1801-3-8 Screw 5 NAS1801-3-9 Screw 1 NAS1801-3-20 Screw 1 NSA5527-03-01 Spacer 1 NSA932843AA01 Relay 1 NSA932844AA Base 100 NSA935401-03 Tie 200 NSA935401-04 Tie 200 NSA935401-05 Tie 800 NSA935401-06 Tie 1500 NSA935401-08 Tie 4 NSA935504-01 Mount 1 NSA935504-03 Mount 1 NSA937901E0 IDENT 1 NSA937901E1 IDENT 2 NSA937901E2 IDENT 1 NSA937901E6 IDENT DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 64 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 NSA937901E8 IDENT 1 NSA937901MA2008 Module 1 NSA937901MA2204 Module 1 NSA937901MA2206 Module

NOTE(01) PN supplied with reference EN3545D03FXA00A. NOTE(02) PN supplied with reference EN3545D03MXB00A. NOTE(03) PN supplied with reference EN3545E01FXB00A. NOTE(04) PN supplied with reference EN3545E03FXB00A. Kit 281132A26R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D00410468A00 Placard 1 D11311361A00 PLACARD

Kit 281132A27R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5791040120095 BRACKET 1 D5791040220095 BRACKET

Kit 281132B01R00 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 41 QB0566 1 Filter 42 HTE490005 1 Valve 43 HTE200002-1 1 Actuator 44 HTE920007-001 1 Valve 45 HTE8002 1 Clamp 46 PAS148-133A 1 Valve 47 HTE490005 1 Valve Kit 281132B02R00 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP D9255002500200 1 Panel D9255602500400 1 Relay Kit 281132B03R00 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 65 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

D9255003200400 1 Panel D9245011500600 1 Panel Kit 281132B04R00 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP D92400000647 1 Bundle Kit 281132D01R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 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 1 D2827097702200 TUBE D28279990002 0006

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D02R00 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

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 281132D03R00 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 66 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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 LN9198-4010CF RIVET D28270992000 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 281132D04R00 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 RECEPTCLD53475024000 0028

5 NAS1791A3-1 NUT D53475024000 0030 2 D5347521320000 WASHER D53475024000 0032 32 DIN65399-2406BF RIVET D53475024000 0125 57 LN9198-4009CF RIVET D53475024000 0240 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 281132D05R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5337217000800 BEAM D53372362004 0000 2 D5337218500000 STRUT D53372362004 0002 4 D5337218600000 STRUT D53372362004 0004 1 D5337219220000 FITTING D53372362004 0008 1 D5337219220100 FITTING D53372362004 0009 1 D5337219120200 FITTING D53372362004 0010 1 D5337219120300 FITTING D53372362004 0011 1 D5337219020200 FITTING D53372362004 0012 1 D5337215920000 ANGLE D53372362004 0014 8 D5337215920200 ANGLE D53372362004 0016 1 D5337215920400 ANGLE D53372362004 0018 1 D5337215920500 ANGLE D53372362004 0019 1 D5337215920600 ANGLE D53372362004 0020 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 67 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5337217320000 PLATE D53372362004 0022 1 D5337217400000 PLATE D53372362004 0024 1 D5337217400100 PLATE D53372362004 0025 1 D5337216020000 SECTION D53372362004 0026 1 D5347449520800 SECTION D53372362004 0028 1 D5347449520900 SECTION D53372362004 0029 1 D5337601520600 SHIM D53372362004 0030 1 D5337601520800 SHIM D53372362004 0032 1 D5337601521000 SHIM D53372362004 0034 1 D5337601521200 SHIM D53372362004 0036 1 D5337601521400 SHIM D53372362004 0038 1 D5347100720600 COUPLING D53372362004 0040 3 D5337602020000 SECTION D53372362004 0044 3 D5337602020100 SECTION D53372362004 0045 4 D5337236220400 SHIM D53372362004 0052 2 D5347007421800 ANGLE D53372362004 0152 2 D5347007421900 ANGLE D53372362004 0153 1 D5347007420800 ANGLE D53372362004 0156 1 D5347007420900 ANGLE D53372362004 0157 4 NAS1791A3-1 NUT D53372362004 0216 12 ASNA0082A302 BOLT D53372362004 0435

2 ASNA0082A303 BOLT D53372362004 0436 4 ASNA0082A304 BOLT D53372362004 0438 15 ASNA0082A305 BOLT D53372362004 0440

1 ASNA0082A306 BOLT D53372362004 0442 2 MS21250-09024 BOLT D53372362004 0464 2 NAS1726-9E NUT D53372362004 0466 2 MS20002C9 WASHER D53372362004 0468 4 MS21250-06018 BOLT D53372362004 0470 4 NAS1726-6E NUT D53372362004 0472 4 MS20002C6 WASHER D53372362004 0474 8 DAN7-6-6X PIN D53372362004 0566 12 DAN5-6-4X PIN D53372362004 0764

8 DAN5-6-5X PIN D53372362004 0765 16 DAN5-6-6X PIN D53372362004 0766 24 DAN5-6-7X PIN D53372362004 0767 82 DAN5-6-8X PIN D53372362004 0768 17 DAN5-6-9X PIN D53372362004 0769

4 DAN5-6-10X PIN D53372362004 0770 12 DAN5-6-11X PIN D53372362004 0771 12 DAN5-6-12X PIN D53372362004 0772 68 NSA5075-5 COLLAR D53372362004 0804 170 NSA5075-6 COLLAR D53372362004 0806 187 DAN11-6X COLLAR D53372362004 0807

48 DAN11-8X COLLAR D53372362004 0810 210 NSA5076-6 COLLAR D53372362004 0816 8 DAN12-6X COLLAR D53372362004 0817 20 DAN6-6-5 PIN D53372362004 0865

4 DAN5-8-7X PIN D53372362004 0887 9 DAN5-8-8X PIN D53372362004 0888 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 68 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 10 DAN5-8-9X PIN D53372362004 0889 10 DAN5-8-10X PIN D53372362004 0890

7 DAN5-8-11X PIN D53372362004 0891 8 DAN5-8-12X PIN D53372362004 0892 36 DAN5-5-4 PIN D53372362004 0944 16 DAN5-5-5 PIN D53372362004 0945

4 DAN5-5-9 PIN D53372362004 0949 3 DAN7-5-5 PIN D53372362004 0955 9 DAN7-5-6 PIN D53372362004 0956 12 DAN5-6-3 PIN D53372362004 0963 12 DAN5-6-4 PIN D53372362004 0964 216 DAN5-6-5 PIN D53372362004 0965

80 DAN5-6-6 PIN D53372362004 0966 10 DAN5-6-7 PIN D53372362004 0967 18 DAN5-6-8 PIN D53372362004 0968

4 DAN5-6-9 PIN D53372362004 0969 1 D5337036520200 ANGLE D53372362004 0150 1 D5337036520300 ANGLE D53372362004 0151 4 D5347100920090 SUPPORT D53372362004 0048 4 D5347100920190 SUPPORT D53372362004 0049 1 D5347101620490 CONNECTND53372362004 0042 1 D5347101620590 CONNECTND53372362004 0043 1 D5347104120090 ANGLE D53372362004 0050 1 D5347104120190 ANGLE D53372362004 0051 8 DAN6-6-6 PIN D53372362004 0866 208 LN9198-4010CF RIVET D53372362004 0032

61 LN9198-4810CF RIVET D53372362004 0648

4 LN9198-5610CF RIVET D53372362004 0656 12 NAS1097AD3-10 RIVET D53372362004 0524 12 NAS1097AD4-10 RIVET D53372362004 0532 102 NAS1097AD5-10 RIVET D53372362004 0540 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 281132D06R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5347449320000 FITTING D53470076004 0010 1 D5337217620000 SHEET 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 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 69 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 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 1 D5337217621000 SHEET D53470076004 0056 2 D5347470024200 ANGLE D53470076004 0058 2 D5337217621200 SHEET 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 SHEET 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 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 70 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 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 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 D5347449820400 FITTING D53470076004 0244 8 NAS1791A3-1 NUT D53470076004 0260 2 MS16625-4212 RING D53470076004 0500 10 NAS1153E7 SCREW D53470076004 0502

8 ABS0337-01A RECEPTCLD53470076004 0504 2 NAS1096-3-10 SCREW D53470076004 0506 10 NAS1474A3 NUT D53470076004 0510

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 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 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 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 71 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 12 DAN5-8-6 PIN D53470076004 0986 12 DAN5-8-7 PIN D53470076004 0987

1 D5347065620400 SECTION D53470076004 0242 46 DIN65399-2415CF RIVET D53470076004 0724 20 MBBN4477-4010 RIVET D53470076004 0514 320 MBBN4477-4810 RIVET D53470076004 0549 220 LN9198-4014CF RIVET D53470076004 0640 310 LN9198-4816CF RIVET D53470076004 0648

12 LN9198-6412CF RIVET D53470076004 0664 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 281132D07R00 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

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 281132D08R00 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 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 281132D09R00

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 72 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5347456000000 SECTION D53474078002 0000 1 D5347456100000 SECTION D53474078002 0002 3 D5347034000800 SECTION D53474078002 0004 1 D5347034000600 SECTION D53474078002 0006 2 D5347448620200 STRAP D53474078002 0008 20 NSA5031-3-3 BOLT D53474078002 0530 20 NAS1726C3P NUT D53474078002 0532

4 NSA5031-4-5 BOLT D53474078002 0534 4 NAS1726C4P NUT D53474078002 0536 12 NSA5075-6 COLLAR D53474078002 0806

8 DAN5-6-3 PIN D53474078002 0963 4 DAN5-6-5 PIN D53474078002 0965

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 281132D10R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2587085105400 BLANKET D25870003028 0001 1 D2587085205000 BLANKET D25870003028 0002 1 D2587085305400 BLANKET D25870003028 0003 1 D2587085405000 BLANKET D25870003028 0004 1 D2587085505200 BLANKET D25870003028 0005 1 D2587085705000 BLANKET D25870003028 0007 1 D2587085805000 BLANKET D25870003028 0008 1 D2587085905000 BLANKET D25870003028 0009 1 D2587086005000 BLANKET D25870003028 0010 1 D2587086105000 BLANKET D25870003028 0011 1 D2587085002000 BLANKET D25870003028 0020 1 D2587085602000 BLANKET D25870003028 0026 1 D2587086202000 BLANKET D25870003028 0032 1 D2587086302200 BLANKET D25870003028 0033 1 D2587086502000 BLANKET D25870003028 0034 1 D2587087102000 BLANKET D25870003028 0035 1 D2587087302000 BLANKET D25870003028 0036 80 F2587003300000 STRIP D25870003028 0100 Kit 281132D11R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2587085002200 BLANKET D25870003056 0000 1 D2587085105600 BLANKET D25870003056 0001 1 D2587085205200 BLANKET D25870003056 0002 1 D2587085305600 BLANKET D25870003056 0003 1 D2587085405200 BLANKET D25870003056 0004 1 D2587085505400 BLANKET D25870003056 0005 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 73 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2587085602200 BLANKET D25870003056 0006 1 D2587085705200 BLANKET D25870003056 0007 1 D2587085805200 BLANKET D25870003056 0008 1 D2587085905200 BLANKET D25870003056 0009 1 D2587086005400 BLANKET D25870003056 0010 1 D2587086105200 BLANKET D25870003056 0011 1 D2587086202200 BLANKET D25870003056 0012 1 D2587086302400 BLANKET D25870003056 0013 1 D2587086502200 BLANKET D25870003056 0014 1 D2587087102200 BLANKET D25870003056 0015 1 D2587087302200 BLANKET D25870003056 0016 80 F2587003400000 STRIP D25870003056 0100 Kit 281132D12R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5347212320000 BRACKET D53472833008 0000 1 D5347212420000 PIN D53472833008 0002 1 D5347212420200 RING D53472833008 0004

Kit 281132D13R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827093320400 FLANGE D28270972002 0000 1 D2827093100200 TUBE D28270972002 0002 1 D2827093000200 TUBE D28270972002 0004 1 D2827093321400 SLEEVE D28270972002 0006 1 D2827093100000 TUBE D28270972002 0008 1 D2827093000000 TUBE D28270972002 0010 1 D2827093221200 SPACER D28270972002 0012 2 D2827093222200 FLANGE D28270972002 0014 1 D2827093322400 SLEEVE D28270972002 0016 2 D2827092700000 TUBE D28270972002 0018 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 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 74 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 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 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 3 E0088-10-125 LEAD D28270972002 0108 2 E0088-10-200 LEAD D28270972002 0109 0.345 NSA937210MB0300 TUBING D28270972002 0110

0.38 NSA937210MB0300 TUBING D28270972002 0111 2 E0089-10-250NN LEAD D28270972002 0112 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 75 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 E0089-41-250NN LEAD D28270972002 0107

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 281132D14R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 MS21902D8 UNION D28270973002 0000 2 NSA8200-8 PACKING D28270973002 0001 1 MS21907D8 ELBOW D28270973002 0002 2 AN924-8D NUT D28270973002 0003 2 NAS1149D1290K WASHER D28270973002 0004 2 MS21905D8 TEE D28270973002 0005 1 NSA5527-03-16 SPACER D28270973002 0006 28 NAS1149C0332R WASHER D28270973002 0007

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

3 NAS1096-3-7 SCREW D28270973002 0011 2 NAS1096-3-10 SCREW D28270973002 0012 1 MS21912D8 TEE D28270973002 0013 9 MS21919WDE8 CLAMP D28270973002 0014 6 MS21919WDE11 CLAMP D28270973002 0015 1 MS21919WDE48 CLAMP D28270973002 0016 1 MS21916D8-6 REDUCER D28270973002 0017 3 NAS1149C0432R WASHER D28270973002 0018 3 NAS1304-4 BOLT D28270973002 0019 1 NSA8200-6 PACKING D28270973002 0022 2 NAS1149D1216H WASHER D28270973002 0023 3 NAS1096-3-9 SCREW D28270973002 0024 6 E0090-10-125NN LEAD D28270973002 0025 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 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 76 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 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 513535E0107-090 HOSE D28270973002 0208 1 D2827094720000 BRACKET D28270973002 0210 1 D2827094421400 PLACARD D28270973002 0214 1 D2827098322800 BRACKET D28270973002 0216 1 L83A13-617 VALVE D28270973002 0206

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 281132D15R00 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 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 77 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827097701200 TUBE D28270974002 0134 1 513535E0107-090 HOSE D28270974002 0204 1 D2827094421600 PLACARD D28270974002 0216 1 L83A13-617 VALVE D28270974002 0202

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 281132D16R01 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 2 A2827092300000 COUPLING D28270975004 0050 27 NAS1726C3E NUT D28270975004 0070 18 NAS1096-3-8 SCREW D28270975004 0071 27 NAS1149C0332R WASHER D28270975004 0073

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 4 NAS1726C4E NUT D28270975004 0093 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 78 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 MS21914-10D CAP D28270975004 0094 2 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

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 281132D17R00 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 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 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 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 79 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 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 10 LN9198-3212BF RIVET D28270982004 0032 90 LN9198-4012BF RIVET D28270982004 0040 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 281132D18R00 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

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 281132D19R00 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

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 281132D20R02

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 80 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 12 NAS1102-3-10 SCREW D25572624000 0010 28 NAS1102-3-12 SCREW D25572624000 0011 46 NAS1726-3E NUT D25572624000 0013

1 D2557206226000 TDP D25572624000 0017 3 DAN152-1 TDP D25572624000 0509 36 NAS1102-3-14 SCREW D25572624000 0512 15 NAS1102-3-16 SCREW D25572624000 0514

5 NAS1102-3-18 SCREW D25572624000 05145 9 D2557206228600 TDP D25572624000 0530 1 D2557206229600 TDP D25572624000 0531

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 281132D22R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 36 D2557214631800 SHIM D25572624006 0014 12 D2557214632000 SHIM D25572624006 0015

9 D2557214633400 SHIM D25572624006 0034 6 D2557214633600 SHIM D25572624006 0036 45 D2557214635000 SHIM D25572624006 0050

7 D2557214635200 SHIM D25572624006 0052 3 D2557214635800 SHIM D25572624006 0058 1 D2557214636000 SHIM D25572624006 0060 6 D2557214637600 SHIM D25572624006 0076 2 D2557214637800 SHIM D25572624006 0078 18 D2557214638000 SHIM D25572624006 0080

6 D2557214638200 SHIM D25572624006 0082 3 D2557214638400 SHIM D25572624006 0084 1 D2557214638600 SHIM D25572624006 0086 18 D2557214638800 SHIM D25572624006 0088

3 D2557214639000 SHIM D25572624006 0090 1 D2557214639200 SHIM D25572624006 0092 1 D2557214639400 SHIM D25572624006 0094 9 D2557214639600 SHIM D25572624006 0096 3 D2557214639800 SHIM D25572624006 0098 18 D2557214640000 SHIM D25572624006 0100

4 D2557214640200 SHIM D25572624006 0102 3 D2557206229800 PLUG D25572624006 0104 3 D2557214642000 SHIM D25572624006 0106 1 D2557214642200 SHIM D25572624006 0108 3 D2557214642400 SHIM D25572624006 0110 1 D2557214642600 SHIM D25572624006 0112 3 D2557214642800 SHIM D25572624006 0114 1 D2557214643000 SHIM D25572624006 0116 3 D2557214641200 SHIM D25572624006 0118 1 D2557214641400 SHIM D25572624006 0120 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 81 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 3 D2557214646000 SHIM D25572624006 0122 1 D2557214646200 SHIM D25572624006 0124 5 D2557214643600 SHIM D25572624006 0126 2 D2557214643800 SHIM D25572624006 0128 3 D2557214644400 SHIM D25572624006 0130 1 D2557214644500 SHIM D25572624006 0132 6 NAS1102-3-10 SCREW D25572624006 0134 1 D2557214644600 SHIM D25572624006 0136

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 281132D24R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557224600200 TRACK D25572624008 0000 1 D2557224600400 TRACK D25572624008 0001 1 D2557224600000 TRACK D25572624008 0002 2 D2557268121200 BRACKET D25572624008 0003 2 D2557214640800 SHIM D25572624008 0004 1 D2557214640400 SHIM D25572624008 0005 1 D2557268122800 BRACKET D25572624008 0006 1 D2557214641000 SHIM D25572624008 0008 1 D2557268121000 DOUBLER D25572624008 0009 1 D2557268028600 PLATE D25572624008 0010 2 D2557237320600 BOLT D25572624008 0013 2 NAS1149C0563R WASHER D25572624008 0014 2 MS24665-300 PIN D25572624008 0015 56 NAS1102-3-7 SCREW D25572624008 0026 56 NAS1102-3-10 SCREW D25572624008 0027 448 NAS1726-3E NUT D25572624008 0028

50 NAS1100-3-12 SCREW D25572624008 0029 31 NAS1100-3-14 SCREW D25572624008 0030

2 MS21250-03008 BOLT D25572624008 0031 153 NAS1102-3-9 SCREW D25572624008 0032 108 MS21250-03010 BOLT D25572624008 0034 4 MS21250-03012 BOLT D25572624008 0035 6 NSA5042C05-180 BOLT D25572624008 0036 6 NSA5060-4 NUT D25572624008 0037 6 NAS1149C0432R WASHER D25572624008 0038 6 NAS1149C0532R WASHER D25572624008 0039 6 MS24665-153 PIN D25572624008 0040 36 DAN7-5-5 PIN D25572624008 0041 36 DAN7-5-6 PIN D25572624008 0042 36 DAN12-5 COLLAR D25572624008 0043 42 NAS1102-3-8 SCREW D25572624008 0044 49 NAS1100-3-10 SCREW D25572624008 0045 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 82 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 6 NAS1100-3-8 SCREW D25572624008 0046 2 NSA5059-5 NUT D25572624008 0047 52 NAS1096-3-7 SCREW D25572624008 0048 160 MS21250-03006 BOLT D25572624008 0049

57 NAS1102-3-11 SCREW D25572624008 0050 74 NAS1102-3-12 SCREW D25572624008 0051 32 NAS1102-3-14 SCREW D25572624008 0052 155 NAS1100-3-9 SCREW D25572624008 0053 6 NAS1100-3-11 SCREW D25572624008 0054 1 NAS1100-3-6 SCREW D25572624008 0055 1 NAS1149C0332R WASHER D25572624008 0056 170 NAS1100-3-7 SCREW D25572624008 0057 8 NAS1102-3-8 SCREW D25572624008 0058 6 D2557268030600 SHIM D25572624008 0069 6 D2557226520400 SUPPORT D25572624008 0070 6 D2557226120200 BLOCK D25572624008 0071 1 NAS1149C0563R WASHER D25572624008 0076 12 D2557238000400 LATCH D25572624008 0078

1 D2557240102000 SUPPORT D25572624008 0080 5 D2557268122200 PLATE D25572624008 0081 1 D2557268122400 PLATE D25572624008 0082 2 MS21250-04012 BOLT D25572624008 0083 3 MS21250-04024 BOLT D25572624008 0084 6 MS21250-04026 BOLT D25572624008 0085 3 MS21250-04030 BOLT D25572624008 0086 12 NAS1726-4E NUT D25572624008 0087

9 NAS1149F0432P WASHER D25572624008 0088 1 MS21250-04028 BOLT D25572624008 0089 2 NAS1102-08-10 SCREW D25572624008 0091 2 NAS1726-05E NUT D25572624008 0092 1 D2557240021400 STOP D25572624008 0094 3 MS21250-06018 BOLT D25572624008 0095 3 NSA5379-6C WASHER D25572624008 0096 1 NAS1304-10 BOLT D25572624008 0097 1 NAS1149F0432P WASHER D25572624008 0098 5 D2557268123000 PLATE D25572624008 0099 5 D2557268123200 PLATE D25572624008 0100 5 D2557268123400 PLATE D25572624008 0101 5 D2557268123600 PLATE D25572624008 0102 5 D2557268123800 PLATE D25572624008 0103 5 D2557268124000 PLATE D25572624008 0104 5 D2557268124200 PLATE D25572624008 0105 5 D2557268124400 PLATE D25572624008 0106 5 D2557268124600 PLATE D25572624008 0107 5 D2557268124800 PLATE D25572624008 0108 5 D2557268125000 PLATE D25572624008 0109 1 NAS1149C0432R WASHER D25572624008 0110 12 NAS1801-3-11 SCREW D25572624008 0111 100 MS21042-3 NUT D25572624008 0112

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 83 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D26R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557295021300 PLACARD D25572624028 0001 1 D2557295021400 PLACARD D25572624028 0002 1 D2557295028000 PLACARD D25572624028 0005 1 D2557295028100 PLACARD D25572624028 0006 4 D2557295024000 STRIP D25572624028 0008 11 D2557295024300 STRIP D25572624028 0022

1 A2557146821200 PLACARD D25572624028 0024 2 D2557295122600 PLACARD D25572624028 0030 1 D2557295123600 PLACARD D25572624028 0034 1 D2557295123800 PLACARD D25572624028 0035 1 D2557295229400 PLACARD D25572624028 0036 2 A2557144422600 PLACARD D25572624028 0038 7 D2557295030600 FOIL D25572624028 0040 1 A2557332320000 PLACARD D25572624028 0041 1 A2557332420000 PLACARD D25572624028 0042

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 281132D27R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 AC40-0253621 NET D25572624002 0520 1 HA70-0214006 STANCHIN D25572624002 0521 1 AC40-0209900 NET D25572624002 0522

Kit 281132D28R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557205820000 FITTING D25572624004 0500 4 NAS1102-3-18 SCREW D25572624004 0501 1 DAN152-1 TDP D25572624004 0502

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 281132D29R00 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 84 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D2557264402800 COVER D25572624010 0001 4 NSA5030-3-5 SCREW D25572624010 0020 4 NSA5030-3-11 SCREW D25572624010 0021

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 281132D31R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367161701800 PANEL D53675015000 0016 2 D5367160001600 PANEL D53675015000 0030 1 D5367160100800 PANEL D53675015000 0032 2 D5367162300800 PANEL D53675015000 0034 1 D5367162400800 PANEL D53675015000 0036 132 ABS0376-3-25 SCREW D53675015000 0400 132 ABS0365-3-1B NUT D53675015000 0405 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D32R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 25.251 DAN107-1 CORD D53675016000 0385 0 ABS5093AT25 TAPE

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 281132D33R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367326000000 PANEL D53672854000 0028 1 D5367326100200 PANEL D53672854000 0030 1 D5367326200200 PANEL D53672854000 0032 1 D5367326300400 PANEL D53672854000 0038 1 D5367326500200 PANEL D53672854000 0040 1 D5367326600000 PANEL D53672854000 0042 1 D5367326700000 PANEL D53672854000 0044 1 D5367326800000 PANEL D53672854000 0046 1 D5367326900000 PANEL D53672854000 0048 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 85 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367205900200 PLATE D53672854000 0050 1 D5397484220000 PLATE D53672854000 0110 1 D5397484220100 PLATE D53672854000 0111 2 D5397489520000 SPACER D53672854000 0112 2 D5397489520100 SPACER D53672854000 0113 1 D5397489420000 SPACER D53672854000 0114 1 D5397489420200 SPACER D53672854000 0116 1 D5367320700000 PANEL D53672854000 0218 1 D5367320900000 PANEL D53672854000 0220 139 ABS0376-3-30 SCREW D53672854000 0402 108 ABS0376-3-40 SCREW D53672854000 0404

12 NAS1102-3-8 SCREW D53672854000 0408 55 ABS0365-3-1B NUT D53672854000 0410 14 NAS1149C0332R WASHER D53672854000 0420 14 MS21042L3 NUT D53672854000 0430 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 281132D34R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 3 ABS0305LC SECTION D53672855000 0001 11.5 ABS0305LB SECTION D53672855000 0002 11.5 ABS0399A SECTION D53672855000 0004 22.556 DAN107-1 CORD D53672855000 0005 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D35R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367306200000 PANEL D53672856000 0028 1 D5367306200100 PANEL D53672856000 0029 1 D5367305500000 PANEL D53672856000 0030 1 D5367305300000 PANEL D53672856000 0032 1 D5367305400000 PANEL D53672856000 0034 1 D5367306100200 PANEL D53672856000 0036 1 D5367306100300 PANEL D53672856000 0037 1 D5367305200000 PANEL D53672856000 0038 1 D5367305600000 PANEL D53672856000 0040 1 D5367301800000 PANEL D53672856000 0200 1 D5367301800100 PANEL D53672856000 0201 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 86 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367302000000 PANEL D53672856000 0202 1 D5367302400000 PANEL D53672856000 0204 1 D5367302600000 PANEL D53672856000 0206 1 D5367303400000 PANEL D53672856000 0208 1 D5367303400100 PANEL D53672856000 0209 1 D5367302200000 PANEL D53672856000 0210 1 D5367302700000 PANEL D53672856000 0212 297 ABS0376-3-25 SCREW D53672856000 0400

62 ABS0376-3-30 SCREW D53672856000 0402 168 ABS0365-3-1B NUT D53672856000 0410 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 281132D36R02 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 219 NAS1097AD4-12 RIVET D53975019000 0532 110 LN9198-4816CF RIVET D53975019000 0648 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 87 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D37R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367520801400 PANEL D53675510010 0028 1 D5367520801800 PANEL D53675510010 0030 1 D5367520805000 PANEL D53675510010 0032 1 D5367520802600 PANEL D53675510010 0038 1 D5367521101600 PANEL D53675510010 0040 1 D5367521101800 PANEL D53675510010 0042 1 D5367521105200 PANEL D53675510010 0044 1 D5367521105400 PANEL D53675510010 0046 1 D5367521105600 PANEL D53675510010 0048 1 D5367205900200 PLATE D53675510010 0050 1 D5397484220000 PLATE D53675510010 0110 1 D5397484220100 PLATE D53675510010 0111 2 D5397489520000 SPACER D53675510010 0112 2 D5397489520100 SPACER D53675510010 0113 1 D5397489420000 SPACER D53675510010 0114 1 D5397489420200 SPACER D53675510010 0116 33 ABS0376-3-30 SCREW D53675510010 0402 130 ABS0376-3-40 SCREW D53675510010 0404

23 NAS1102-3-8 SCREW D53675510010 0408 85 EN6131C3C4 NUT D53675510010 0411 11 NAS1149C0332R WASHER D53675510010 0420 11 MS21042L3 NUT D53675510010 0430 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 281132D38R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367406200000 PANEL D53675520008 0028 1 D5367406200100 PANEL D53675520008 0029 1 D5367405500000 PANEL D53675520008 0030 1 D5367405300000 PANEL D53675520008 0032 1 D5367405400000 PANEL D53675520008 0034 1 D5367405200000 PANEL D53675520008 0038 1 D5367405600000 PANEL D53675520008 0040 1 D5367416000200 PANEL D53675520008 0084 1 D5367416000300 PANEL D53675520008 0085 221 ABS0376-3-30 SCREW D53675520008 0402 0.44 ABS5006-4D TAPE D53675520008 0408 192 EN6131C3C4 NUT D53675520008 0411 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 88 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 6 ABS0376-3-35 SCREW D53675520008 0412

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 281132D39R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 22.556 DAN107-1 CORD D53675525002 0001

11.5 ABS0399A SECTION D53675525002 0003 11.5 ABS0398A01 SECTION D53675525002 0004 3 ABS0305LC SECTION D53675525002 0005 11.5 ABS0305LB SECTION D53675525002 0006 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D40R03 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D5347035000600 XBEAM D53470075004 0010 4 D5337217620000 SHEET D53470075004 0012 3 D5337217620100 SHEET D53470075004 0014 4 D5347449420600 FITTING D53470075004 0016 4 D5347449420700 FITTING D53470075004 0018 1 D5347449521800 SECTION D53470075004 0020 5 D5347448420200 STRAP D53470075004 0022 4 D5347448420300 STRAP D53470075004 0024 8 D5337217620800 FILLER D53470075004 0026 4 D5347449520300 SECTION D53470075004 0028 3 D5347449520200 SECTION D53470075004 0030 7 D5347449520500 SECTION D53470075004 0032 6 D5347449520400 SECTION D53470075004 0034 1 D5347470020000 ANGLE D53470075004 0036 1 D5347470020100 ANGLE D53470075004 0038 3 D5347470020400 ANGLE D53470075004 0044 2 D5347470020500 ANGLE D53470075004 0046 6 D5347470020200 ANGLE D53470075004 0048 4 D5347470020300 ANGLE D53470075004 0050 1 D5347026000600 XBEAM D53470075004 0052 2 D5347470520000 ANGLE D53470075004 0054 2 D5347470520100 ANGLE D53470075004 0056 1 D5347449523400 SECTION D53470075004 0058 1 D5347449523600 SECTION D53470075004 0060 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 89 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D5347449522000 SECTION D53470075004 0062 2 D5347449523200 SECTION D53470075004 0064 1 D5347470320000 WEB D53470075004 0066 1 D5347470020800 ANGLE D53470075004 0068 1 D5347470021000 ANGLE D53470075004 0070 1 D5347470020600 ANGLE D53470075004 0072 1 D5347470021200 ANGLE D53470075004 0074 1 D5347035300600 XBEAM D53470075004 0076 1 D5337217620700 SHEET D53470075004 0078 1 D5347470420400 WEB D53470075004 0080 1 D5347470021600 ANGLE D53470075004 0082 1 D5347470021800 ANGLE D53470075004 0084 1 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 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 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 90 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 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 RECEPTCLD53470075004 0504 2 NAS1096-3-10 SCREW D53470075004 0506 4 NAS1791A3-1 NUT D53470075004 0508 10 NAS1474A3 NUT D53470075004 0510

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

8 DAN5-6-6X PIN D53470075004 0766 9 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 44 MBBN4477-4012 RIVET D53470075004 0541 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 91 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1000 LN9198-4012CF RIVET D53470075004 0640

600 LN9198-4812CF RIVET D53470075004 0648

40 DIN65399-2410CF RIVET D53470075004 0724 100 DIN65399-3210CF RIVET D53470075004 0732 400 MBBN4477-4812 RIVET D53470075004 0549 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 281132D41R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

136 NSA5075-6 COLLAR D53470095002 0806

16 DAN6-6-3 PIN D53470095002 0863 16 DAN6-6-5 PIN D53470095002 0865 72 DAN5-6-3 PIN D53470095002 0963 32 DAN5-6-4 PIN D53470095002 0964 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D42R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5337217000800 BEAM D53372362008 0000 2 D5337218500000 STRUT D53372362008 0002 4 D5337218600000 STRUT D53372362008 0004 1 D5337219220000 FITTING D53372362008 0008 1 D5337219220100 FITTING D53372362008 0009 1 D5337219120200 FITTING D53372362008 0010 1 D5337219120300 FITTING D53372362008 0011 1 D5337219020200 FITTING D53372362008 0012 1 D5337215920000 ANGLE D53372362008 0014 8 D5337215920200 ANGLE D53372362008 0016 1 D5337215920400 ANGLE D53372362008 0018 1 D5337215920500 ANGLE D53372362008 0019 1 D5337215920600 ANGLE D53372362008 0020 1 D5337217320200 WEB D53372362008 0022 1 D5337217400000 PLATE D53372362008 0024 1 D5337217400100 PLATE D53372362008 0025 1 D5337216020000 SECTION D53372362008 0026 1 D5347449520800 SECTION D53372362008 0028 1 D5347449520900 SECTION D53372362008 0029 1 D5337601520600 SHIM D53372362008 0030 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 92 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5337601520800 SHIM D53372362008 0032 1 D5337601521000 SHIM D53372362008 0034 1 D5337601521200 SHIM D53372362008 0036 1 D5337601521400 SHIM D53372362008 0038 1 D5347100720600 COUPLING D53372362008 0040 3 D5337602020000 SECTION D53372362008 0044 3 D5337602020100 SECTION D53372362008 0045 4 NAS1791A3-1 NUT D53372362008 0046 4 D5337236220400 SHIM D53372362008 0052 1 D5337036522600 ANGLE D53372362008 0150 1 D5337036522700 ANGLE D53372362008 0151 2 D5347007422000 ANGLE D53372362008 0152 2 D5347007422100 ANGLE D53372362008 0153 2 D5347007422200 ANGLE D53372362008 0156 12 ASNA0082A302 BOLT D53372362008 0435

2 ASNA0082A303 BOLT D53372362008 0436 4 ASNA0082A304 BOLT D53372362008 0438 15 ASNA0082A305 BOLT D53372362008 0440

1 ASNA0082A306 BOLT D53372362008 0442 2 MS21250-09024 BOLT D53372362008 0464 2 NAS1726-9E NUT D53372362008 0466 2 MS20002C9 WASHER D53372362008 0468 4 MS21250-06018 BOLT D53372362008 0470 4 NAS1726-6E NUT D53372362008 0472 4 MS20002C6 WASHER D53372362008 0474 8 DAN7-6-6X PIN D53372362008 0566 12 DAN5-6-4X PIN D53372362008 0764

8 DAN5-6-5X PIN D53372362008 0765 16 DAN5-6-6X PIN D53372362008 0766 24 DAN5-6-7X PIN D53372362008 0767 86 DAN5-6-8X PIN D53372362008 0768 20 DAN5-6-9X PIN D53372362008 0769

4 DAN5-6-10X PIN D53372362008 0770 12 DAN5-6-11X PIN D53372362008 0771 12 DAN5-6-12X PIN D53372362008 0772 68 NSA5075-5 COLLAR D53372362008 0804 170 NSA5075-6 COLLAR D53372362008 0806 194 DAN11-6X COLLAR D53372362008 0807

41 DAN11-8X COLLAR D53372362008 0810 210 NSA5076-6 COLLAR D53372362008 0816 8 DAN12-6X COLLAR D53372362008 0817 20 DAN6-6-5 PIN D53372362008 0865

8 DAN6-6-6 PIN D53372362008 0866 4 DAN5-8-7X PIN D53372362008 0887 5 DAN5-8-8X PIN D53372362008 0888 7 DAN5-8-9X PIN D53372362008 0889 10 DAN5-8-10X PIN D53372362008 0890

7 DAN5-8-11X PIN D53372362008 0891 8 DAN5-8-12X PIN D53372362008 0892 36 DAN5-5-4 PIN D53372362008 0944 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 93 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 16 DAN5-5-5 PIN D53372362008 0945

4 DAN5-5-9 PIN D53372362008 0949 3 DAN7-5-5 PIN D53372362008 0955 9 DAN7-5-6 PIN D53372362008 0956 12 DAN5-6-3 PIN D53372362008 0963 12 DAN5-6-4 PIN D53372362008 0964 216 DAN5-6-5 PIN D53372362008 0965

80 DAN5-6-6 PIN D53372362008 0966 10 DAN5-6-7 PIN D53372362008 0967 18 DAN5-6-8 PIN D53372362008 0968

4 DAN5-6-9 PIN D53372362008 0969 1 D5347101620490 CONNECTND53372362008 0042 1 D5347101620590 CONNECTND53372362008 0043 4 D5347100920090 SUPPORT D53372362008 0048 4 D5347100920190 SUPPORT D53372362008 0190 1 D5347104120090 ANGLE D53372362008 0050 1 D5347104120190 ANGLE D53372362008 0051 12 NAS1097AD3-10 RIVET D53372362008 0524 12 NAS1097AD4-10 RIVET D53372362008 0532 98 NAS1097AD5-10 RIVET D53372362008 0540 200 LN9198-4010CF RIVET D53372362008 0032

61 LN9198-4810CF RIVET D53372362008 0648

4 LN9198-5610CF RIVET D53372362008 0656

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 281132D43R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827097905200 TUBE D28270991002 0002 1 AN924-10J NUT D28270991002 0034 1 NAS1149C1432R WASHER D28270991002 0035 1 NAS1726C3E NUT D28270991002 0070 1 NAS1149C0332R WASHER D28270991002 0073 1 MS21919WDE10 CLAMP D28270991002 0079 1 NSA5575-8A CLAMP D28270991002 0081 1 E0090-10-125NN LEAD D28270991002 0083 1 NAS1303-2 BOLT D28270991002 0088 1 NAS1726-3E NUT D28270991002 0089 1 NAS1149D0316H WASHER D28270991002 0090 1 MS21908J10 ELBOW D28270991002 0091 1 NAS1801-3-9 SCREW D28270991002 0097 1 DAN107-2 CORD D28270991002 0102

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 94 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D44R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827098324800 BRACKET D28270992002 0002 1 D2827098325200 BRACKET D28270992002 0006 2 D2827098329200 BRACKET D28270992002 0008 49 EN6081D5-09 RIVET D28270992002 0040 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 281132D45R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827098000800 TUBE D28270975006 0005 1 D2827098001400 TUBE D28270975006 0011 1 D2827097901200 TUBE D28270975006 0013 1 D2827097901400 TUBE D28270975006 0015 1 D2827097901000 TUBE D28270975006 0016 1 D2827097901600 TUBE D28270975006 0017 1 D2827097901800 TUBE D28270975006 0019 1 D2827097902000 TUBE D28270975006 0021 1 D2827097902400 TUBE D28270975006 0025 1 D2827097904000 TUBE D28270975006 0026 1 A2163302000000 FILTER D28270975006 0027 1 A2151034520000 INLET D28270975006 0028 1 MS21902D10 UNION D28270975006 0030 1 NAS1612-10 PACKING D28270975006 0031 1 83694912 HOSE D28270975006 0040 2 A2827092300000 COUPLING D28270975006 0050 25 NAS1726C3E NUT D28270975006 0070 18 NAS1096-3-8 SCREW D28270975006 0071 27 NAS1149C0332R WASHER D28270975006 0073

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

8 NSA5575-8A CLAMP D28270975006 0081 4 NSA5575-2 CLAMP D28270975006 0082 7 E0090-10-125NN LEAD D28270975006 0083 4 E0090-18-100NN LEAD D28270975006 0084 4 NAS1096-1-8 SCREW D28270975006 0085 4 MS21042-06 NUT D28270975006 0087 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 95 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 8 NAS1303-2 BOLT D28270975006 0088 8 NAS1726-3E NUT D28270975006 0089 1 MS21908J10 ELBOW D28270975006 0091 1 AN924-4D NUT D28270975006 0092 4 NAS1726C4E NUT D28270975006 0093 2 MS21914-10D CAP D28270975006 0094 1 AN924-10J NUT D28270975006 0095 1 NAS1149C1432R WASHER D28270975006 0096 7 NAS1096-3-9 SCREW D28270975006 0097 2 NAS1096-3-12 SCREW D28270975006 0098 1 MS21905J10 TEE D28270975006 0099 1 MS21919WCH15 CLAMP D28270975006 0101 1 E0090-10-160NN LEAD D28270975006 0102 16 NAS1149F0332P WASHER D28270975006 0103

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

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D46R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 6 NAS1096-3-8 SCREW D28270982006 0004 6 NAS1149C0332R WASHER D28270982006 0005 6 NAS1726C3E NUT D28270982006 0006 8 DAN7-6-8Y PIN D28270982006 0041 8 DAN12-6Y COLLAR D28270982006 0042 3 F5397461900600 BRACKET D28270982006 0100 2 D2827094222800 ANGLE D28270982006 0102 1 D2827098300000 BRACKET D28270982006 0104 1 D2827098300200 BRACKET D28270982006 0106 3 D2827094221400 ANGLE D28270982006 0112 2 D2827094220400 ANGLE D28270982006 0113 2 D2827094222200 ANGLE D28270982006 0116 2 D2827098320800 BRACKET D28270982006 0117 2 D2827098321000 BRACKET D28270982006 0118 1 D2827098321200 ANGLE D28270982006 0119 2 D2827094200400 BRACKET D28270982006 0124 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 96 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827098325200 BRACKET D28270982006 0125 1 D2827098300800 BRACKET D28270982006 0126 2 D2827098323200 BRACKET D28270982006 0127 1 D2827098323000 BRACKET D28270982006 0128 1 D2827098323800 BRACKET D28270982006 0130 1 D2827093521000 BRACKET D28270982006 0131 1 D2827098324200 BRACKET D28270982006 0132 1 D2827098324400 BRACKET D28270982006 0133 1 D2827098324000 BRACKET D28270982006 0134 1 D2827098326000 BRACKET D28270982006 0135 1 D2827098326200 BRACKET D28270982006 0136 2 D2827098327600 ANGLE D28270982006 0137 1 D2827098327800 ANGLE D28270982006 0138 1 D2827098328000 ANGLE D28270982006 0139 1 D2827098328200 ANGLE D28270982006 0140 49 LN9198-3212BF RIVET D28270982006 0032 49 LN9198-4012BF RIVET D28270982006 0040 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 281132D47R00 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

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 281132D48R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827050501600 TUBE D2827120000200 0004 1 D2827050501400 TUBE D2827120000200 0014 1 NSA855113-11C TEE D2827120000200 0022 25 NAS1149C0332R WASHER D2827120000200 0025 14 NAS1291C3M NUT D2827120000200 0026

4 NSA5575-4A CLAMP D2827120000200 0062 4 ABS1510D100NN STRAP D2827120000200 0064 1 ABS1510D160NN STRAP D2827120000200 0068 1 ABS1510D140NN STRAP D2827120000200 0070 1 E0090-10-160NN LEAD D2827120000200 0072 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 97 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 11 NAS1303-2 BOLT D2827120000200 0074

3 NAS1303-3 BOLT D2827120000200 0076

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 281132D50R01 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 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 18 LN9198-3208BF RIVET D53370297002 0632

8 LN9198-3210BF RIVET D53370297002 0632 6 LN9198-3212BF RIVET D53370297002 0632 2 DIN65399-3208BF RIVET D53370297002 0632

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D51R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 L32A319-160-002 CONTROL D53370297003 0000 1 L32A319-165-001 ADAPTER D53370297003 0004 2 D5337025020100 ANGLE D53370297003 0007 2 D5337025620200 SECTION D53370297003 0008 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 98 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 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 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 18 LN9198-3208BF RIVET D53370297003 0632

8 LN9198-3210BF RIVET D53370297003 0632 6 LN9198-3212BF RIVET D53370297003 0632 2 DIN65399-3208BF RIVET D53370297003 0632

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D52R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367520801400 PANEL D53675510012 0028 1 D5367520801800 PANEL D53675510012 0030 1 D5367520805000 PANEL D53675510012 0032 1 D5367520802600 PANEL D53675510012 0038 1 D5367521101600 PANEL D53675510012 0040 1 D5367521101800 PANEL D53675510012 0042 1 D5367521105200 PANEL D53675510012 0044 1 D5367521105400 PANEL D53675510012 0046 1 D5367521105600 PANEL D53675510012 0048 1 D5367205900200 PLATE D53675510012 0050 1 D5367521100600 PANEL D53675510012 0052 1 D5367521100800 PANEL D53675510012 0054 1 D5397484220000 PLATE D53675510012 0110 1 D5397484220100 PLATE D53675510012 0111 2 D5397489520000 SPACER D53675510012 0112 2 D5397489520100 SPACER D53675510012 0113 1 D5397489420200 SPACER D53675510012 0116 80 ABS0376-3-30 SCREW D53675510012 0402 125 ABS0376-3-40 SCREW D53675510012 0404

21 NAS1102-3-8 SCREW D53675510012 0408 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 99 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 87 EN6131C3C4 NUT D53675510012 0411 10 NAS1149C0332R WASHER D53675510012 0420 10 MS21042L3 NUT D53675510012 0430 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 281132D53R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367401800000 PANEL D53675520010 0000 1 D5367401800100 PANEL D53675520010 0001 1 D5367402000000 PANEL D53675520010 0002 1 D5367402400000 PANEL D53675520010 0004 1 D5367402600000 PANEL D53675520010 0006 1 D5367403400000 PANEL D53675520010 0008 1 D5367403400100 PANEL D53675520010 0009 1 D5367402200000 PANEL D53675520010 0010 1 D5367402700000 PANEL D53675520010 0012 1 D5367406200000 PANEL D53675520010 0028 1 D5367406200100 PANEL D53675520010 0029 1 D5367405500000 PANEL D53675520010 0030 1 D5367405300000 PANEL D53675520010 0032 1 D5367405400000 PANEL D53675520010 0034 1 D5367405200000 PANEL D53675520010 0038 1 D5367405600000 PANEL D53675520010 0040 1 D5367416000200 PANEL D53675520010 0084 1 D5367416000300 PANEL D53675520010 0085 380 ABS0376-3-30 SCREW D53675520010 0402 0.44 ABS5006-4D TAPE D53675520010 0408 320 EN6131C3C4 NUT D53675520010 0411 6 ABS0376-3-35 SCREW D53675520010 0412

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 281132D54R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 E5367161701800 PANEL D53675015006 0016 2 E5367160001600 PANEL D53675015006 0028 1 E5367160100800 PANEL D53675015006 0032 1 E5367162400800 PANEL D53675015006 0036 2 E5367162301400 PANEL D53675015006 0042 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 100 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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

122 ABS0376-3-25 SCREW D53675015006 0400 122 EN6131-3C1 NUT D53675015006 0405 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D55R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 3 D2558503820200 STRIP D25570049008 0010 1 D2557165620000 BUMPER D25570049008 0012 1 D2557165720000 BUMPER D25570049008 0014 1 D2557131000200 PANEL D25570049008 0050 1 D2557131400600 PANEL D25570049008 0052 1 D2557131600800 PANEL D25570049008 0054 1 D2557134200000 PANEL D25570049008 0056 1 D2557122000000 PANEL D25570049008 0058 9 NAS1102-3-10 SCREW D25570049008 0070 14 NAS1100-3-18 SCREW D25570049008 0071

6 ABS0208-01 WASHER D25570049008 0072 14 NAS1149D0332K WASHER D25570049008 0073

6 NAS1102-08-12 SCREW D25570049008 0074 0.045 ABS5006-6J TAPE D25570049008 0080 Kit 281132D56R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557132600200 PANEL D25570049010 0060 1 D2557132400800 PANEL D25570049010 0062 1 D2557132200800 PANEL D25570049010 0064

Kit 281132D57R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557133000200 PANEL D25570049012 0066 1 D2557133400600 PANEL D25570049012 0068

Kit 281132D58R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D2557017000200 COVER D25570049014 0044 1 D2557123600400 PANEL D25570049014 0090 1 D2557123600500 PANEL D25570049014 0091 1 D2557123800200 PANEL D25570049014 0092 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 101 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Kit 281132D59R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 3 D2558503820200 STRIP D25570049016 0010 1 D2557165620000 BUMPER D25570049016 0012 1 D2557165720000 BUMPER D25570049016 0014 1 D2558521803400 COVER D25570049016 0016 1 D2558521803600 COVER D25570049016 0018 1 D2557131002600 PANEL D25570049016 0051 1 D2557131402000 PANEL D25570049016 0053 1 D2557131602000 PANEL D25570049016 0055 1 D2557134200000 PANEL D25570049016 0056 1 D2557061000200 PANEL D25570049016 0057 1 D2557122000400 PANEL D25570049016 0059 9 NAS1102-3-10 SCREW D25570049016 0070 14 NAS1100-3-18 SCREW D25570049016 0071

6 ABS0208-01 WASHER D25570049016 0072 14 NAS1149D0332K WASHER D25570049016 0073

3 NAS1102-08-12 SCREW D25570049016 0074 3 NAS1102-08-14 SCREW D25570049016 0075 0.045 ABS5006-6J TAPE D25570049016 0080 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 281132D60R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

219 NAS1097AD4-12 RIVET D53975018002 0532 110 EN6081D6-10 RIVET D53975018002 0648 2 D5397489200000 SECTION D53975018002 0000 2 D5397489200100 SECTION D53975018002 0001 1 D5397469000000 BRACKET D53975018002 0016 1 D5397469000100 BRACKET D53975018002 0017 1 D5397469200000 BRACKET D53975018002 0018 1 D5397469200100 BRACKET D53975018002 0019 1 D5397469300000 BRACKET D53975018002 0020 1 D5397469300100 BRACKET D53975018002 0021 44 NAS6703-2 BOLT D53975018002 0025 44 NAS1149D0332K WASHER D53975018002 0026 22 D5397469700000 SUPPORT D53975018002 0028

1 D5347047400200 SECTION D53975018002 0030 1 D5347047400300 SECTION D53975018002 0031 1 D5397467800800 SECTION D53975018002 0040 1 D5397467800900 SECTION D53975018002 0041 1 D5397492600000 SECTION D53975018002 0042 1 D5397468800200 SECTION D53975018002 0044 1 D5397468800300 SECTION D53975018002 0045 1 D5397468000400 SECTION D53975018002 0046 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 102 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5397468000500 SECTION D53975018002 0047 1 D5397492500090 SECTION D53975018002 0048 1 D5397492500290 SECTION D53975018002 0050 1 D5397467400500 SECTION D53975018002 0052 1 D5397467400400 SECTION D53975018002 0053 3 D5397492700000 PLATE D53975018002 0054 9 NAS1102E3-7 SCREW D53975018002 0400 9 DAN125-4 WASHER D53975018002 0402 4 NSA5075-6 COLLAR D53975018002 0806 4 DAN5-6-2 PIN D53975018002 0962

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D61R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 A9249175120000 ANGLE D53371046000 0001 1 D5337312600000 PLATE D53371046000 0002 1 D5337312000000 PLATE D53371046000 0003 4 D5337312420000 STRAP D53371046000 0004 8 NAS6703U7 BOLT D53371046000 0005 8 NAS6703U5 BOLT D53371046000 0006 16 NAS1726C3P NUT D53371046000 0007 16 NAS1149C0332R WASHER D53371046000 0008

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

4 DAN5-6-7 PIN D53371046000 0024 6 NSA5075-6 COLLAR D53371046000 0025 3 ABS0258-5C COLLAR D53371046000 0026 24 NSA5076-6 COLLAR D53371046000 0027 12 LN9198-3208BF RIVET D53371046000 0028 196 LN9198-4812CF RIVET D53371046000 0029 8 LN9198-4814CF RIVET D53371046000 0030 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 103 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 15 LN9198-4009CF RIVET D53371046000 0031

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

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

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

6 NSA5076-5 COLLAR D53371046000 0039

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D62R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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

1 DAN8-8-8X PIN D53371237000 0004 20 DAN12-6X COLLAR D53371237000 0005 45 DAN12-8X COLLAR D53371237000 0006 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D63R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

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

1 DAN8-8-8X PIN D53371237001 0004 20 DAN12-6X COLLAR D53371237001 0005 45 DAN12-8X COLLAR D53371237001 0006 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D64R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 104 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 D5367161701800 PANEL D53675015004 0016 2 D5367160001600 PANEL D53675015004 0030 1 D5367160100800 PANEL D53675015004 0032 2 D5367162300800 PANEL D53675015004 0034 1 D5367162400800 PANEL D53675015004 0036 26 ABS0376-3-23 SCREW D53675015004 0398 96 ABS0376-3-25 SCREW D53675015004 0400 122 EN6131-3C1 NUT D53675015004 0505 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 281132D65R00 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

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 281132D69R01 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 PLCRDSETD92894736004 0050 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 105 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 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 200 D9239240905800 PLACARD D92894738042 0000 400 NSA935401-03 TIE D92894738042 0080 400 D9239240905800 PLACARD 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 281132D70R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

40 D9239310902800 PLACARD D92894713020 0000 80 NSA935401-03 TIE D92894713020 0080

4 NAS1096-2-12 SCREW D92894736004 0007 2 NAS1096-3-9 SCREW D92894736004 0030 1 D9299043900000 HARNESS D92894736004 0039 1 D9299044000000 HARNESS D92894736004 0040 1 D9239386503200 PLCRDSETD92894736004 0050 4 NAS1100-04-5 SCREW D92894736004 0051 4 NAS1149CN616R WASHER D92894736004 0150 3 NAS1149CN816R WASHER D92894736004 0152 2 NAS1149C0332R WASHER D92894736004 0153 4 MS21042-04 NUT D92894736004 0200 3 NSA5066-08-1 NUT D92894736004 0230 2 E0343-01 MOUNT D92894736004 0250 1 NSA935504-01 MOUNT D92894736004 0251 1 NSA935504-03 MOUNT D92894736004 0253 1 NSA935513-07 MOUNT D92894736004 0259 2 ABS0355-01 BRACKET D92894736004 0262 2 ABS0355-02 BRACKET D92894736004 0263 2 NSA935514-03 WASHER D92894736004 0264 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 106 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 4 NSA5527-03-03 SPACER D92894736004 0304 30 NSA935401-04 TIE D92894736004 0794 15 NSA935401-05 TIE D92894736004 0795 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D71R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D2567072701000 BRACKET D25670762000 0000 6 D2567072700200 BRACKET D25670762000 0002 2 D2567072700400 BRACKET D25670762000 0004 2 D2567072700500 BRACKET D25670762000 0005 2 D2567072701200 BRACKET D25670762000 0006 3 D2567072700800 BRACKET D25670762000 0008 3 D2567072700900 BRACKET D25670762000 0009 66 LN9198-4008CF RIVET D25670762000 9001

1 D2567070100000 TUBE D25671745000 0000 1 D2567070100100 TUBE D25671745000 0001 1 D2567070100200 TUBE D25671745000 0002 1 D2567070100300 TUBE D25671745000 0003 1 D2567070600000 SECTION D25671745000 0010 1 D2567070600200 SECTION D25671745000 0012 4 E0088-10-80NN LEAD D25671745000 0050 4 ABS0396C08JA CLAMP D25671745000 0060 10 NSA5515-8 CLAMP D25671745000 0062

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 73228620 SECTION D25671746000 0070 4 NAS1096-3-7 SCREW D25671746000 0080 4 NAS1149D0363K WASHER D25671746000 0090 1 D9239310903000 PLCRDSETD25671746000 0100 2 MS20392-2C15 PIN D25671746000 0110 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 6 NAS1149C0332R WASHER D25671746000 0120 2 MS24665-1013 PIN D25671746000 0130 1 D2567074100600 PLACARD D25671746000 0140 1 60592-103 RESERVORD25671746000 0594 1 60592-103 RESERVORD25671746000 0598

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 281132D72R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 16 NAS1102-4-16 SCREW D25286364010 0002 16 NAS1149F0432P WASHER D25286364010 0004 16 NAS1169C416L WASHER D25286364010 0006 16 MS21042-4 NUT D25286364010 0008 16 NAS1102-08-16 SCREW D25286364010 0010 16 NAS1149FN816P WASHER D25286364010 0012 16 NAS1169C8L WASHER D25286364010 0014 16 MS21042-08 NUT D25286364010 0016

1 D2527305811800 BOX D25286364010 0020 1 D2527305811900 BOX D25286364010 0021 4 MS20392-3C23 PIN D25286364010 0030 2 MS20392-3C27 PIN D25286364010 0031 6 NAS1149F0463P WASHER D25286364010 0032 6 AA55487-5 PIN D25286364010 0033 4 MS20392-4C67 PIN D25286364010 0042 2 MS20392-4C45 PIN D25286364010 0043 4 NAS1149C0532R WASHER D25286364010 0046 6 DAN191-20 RING D25286364010 0047 2 NSA5528-045 CLAMP D25286364010 0065

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D73R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D2527719940600 PLACARD D25288767000 0206 2 A2528131544600 PLACARD D25288767000 0246 2 D2527700844200 PLACARD D25288767000 1242

Kit 281132D74R00

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 108 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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

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 281132D75R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9357040100200 BRACKET D93070668000 0112 1 D9357040100300 BRACKET D93070668000 0113 4 DAN257-3264 RIVET D93070668000 0125

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. 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 281132D76R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2529421402600 CMPRTMNTD25278439090 0014 1 D2529421502600 CMPRTMNTD25278439090 0015 2 NAS1801-06-6 SCREW D25278439090 0122 4 NAS1149F0432P WASHER D25278439090 0161 2 NAS1149CN832R WASHER D25278439090 0164 2 MS21042-06 NUT D25278439090 0180 2 MS20392-3C27 PIN D25278439090 0205 2 MS20392-3C31 PIN D25278439090 0206 4 AA55487-4 PIN D25278439090 0250 2 ABS0901-045 CLAMP D25278439090 0290

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 281132D77R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 109 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 D2527719940600 PLACARD D25278404054 0206 2 D2528842244100 PLACARD D25278404054 0241 2 D2528842244200 PLACARD D25278404054 0242

Kit 281132D78R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9299229900200 ELTEQUIP D92992299000 0001 1 D9299229900400 ELTEQUIP D92992299000 0002 1 D9299229900600 ELTEQUIP D92992299000 0003 1 D9299229900800 ELTEQUIP D92992299000 0004 1 D9299229901000 ELTEQUIP D92992299000 0005 1 D9299229901200 ELTEQUIP D92992299000 0006 1 D9299229901400 ELTEQUIP D92992299000 0007 1 D9299229901600 ELTEQUIP D92992299000 0008 1 D9299229901800 ELTEQUIP D92992299000 0009 1 D9299229902000 ELTEQUIP D92992299000 0010 1 D9299229902200 ELTEQUIP D92992299000 0011 1 D9299229902400 ELTEQUIP D92992299000 0012 1 D9299062701300 HARNESS D92992299000 0014 1 D9299229902600 ELTEQUIP D92992299000 0015 1 D9299229902800 ELTEQUIP D92992299000 0016 1 D9299229903000 ELTEQUIP D92992299000 0019 1 D9299082000100 HARNESS D92992299000 0021 1 D9299082400700 HARNESS D92992299000 0023 1 D9299083300100 HARNESS D92992299000 0025

Kit 281132D80R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557173004000 PANEL D25570049000 0000 1 D2557174209600 PANEL D25570049000 0002 1 D2557174404600 PANEL D25570049000 0004 1 D2557175000000 PANEL D25570049000 0006 1 D2557164600000 PANEL D25570049000 0008 3 D2558503820200 STRIP D25570049000 0010 1 D2557165620000 BUMPER D25570049000 0012 1 D2557165720000 BUMPER D25570049000 0014 9 NAS1102-3-10 SCREW D25570049000 0070 14 NAS1100-3-18 SCREW D25570049000 0071

6 ABS0208-01 WASHER D25570049000 0072 14 NAS1149D0332K WASHER D25570049000 0073

6 NAS1102-08-12 SCREW D25570049000 0074 0.045 ABS5006-6J TAPE D25570049000 0080 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 110 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Kit 281132D81R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557176800200 PANEL D25570049002 0020 1 D2557176200800 PANEL D25570049002 0022 1 D2557176000600 PANEL D25570049002 0024

Kit 281132D82R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557178000200 PANEL D25570049004 0030 1 D2557178600600 PANEL D25570049004 0032

Kit 281132D83R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557166000400 PANEL D25570049006 0040 1 D2557166000500 PANEL D25570049006 0041 1 D2557166200200 PANEL D25570049006 0042 2 D2557017000200 COVER D25570049006 0044

Kit 281132D84R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9357072520300 BRACKET D93070515002 0108 1 ASNA3752D120812 UNION D93070515002 0111 2 NSA855006D4 UNION D93070515002 0113 2 NSA855006-6 UNION D93070515002 0114 2 NSA855006-8 UNION D93070515002 0115 1 NSA855006D8 UNION D93070515002 0116 4 NAS1096-3-7 SCREW D93070515002 0128 1 NSA5586B BLOCK D93070515002 0132 3 NSA935401-05 TIE D93070515002 0133 2 NAS679C06 NUT D93070515002 0136 1 D2917091100000 TUBE D93070515002 0139 1 D3247091600200 TUBE D93070515002 0142 1 D3247090600400 TUBE D93070515002 0143 1 D3247090101000 TUBE D93070515002 0144 1 D3247091600000 TUBE D93070515002 0145 1 D3247091100600 TUBE D93070515002 0146 1 D2707023100000 TUBE D93070515002 0152 1 D2917091100200 TUBE D93070515002 0155 1 D2917090100400 TUBE D93070515002 0156 1 D2777000102600 TUBE D93070515002 0157 1 D2777001102400 TUBE D93070515002 0158 1 D3247090600000 TUBE D93070515002 0183 1 D3247090600600 TUBE D93070515002 0184 23 NSA5066-3-1 NUT D93070515002 0185

3 NSA935401-06 TIE D93070515002 0186 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 111 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 3 NSA935401-04 TIE D93070515002 0187 2 NSA855020-8 ELBOW D93070515002 0188 2 A9348225520000 BLOCK D93070515002 0190 1 D9357070820000 BRACKET D93070515002 0191 1 D9357045500000 BRACKET D93070515002 0192 1 NSA5516CA06NJ CLAMP D93070515002 0193 3 LN9198-3210CF RIVET D93070515002 0198 6 LN9198-3210BF RIVET D93070515002 0199 1 D9357045500000 BRACKET

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 281132D85R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9299140500100 HARNESS D92997028000 0002 1 D9299702600100 EQUIPMNTD92997028000 0004 1 D9299702600200 EQUIPMNTD92997028000 0006 1 D9299142801400 HARNESS D92997028000 0008 1 D9299702800200 EQUIPMNTD92997028000 0010 1 D9299702800400 EQUIPMNTD92997028000 0012 1 D9299702800600 EQUIPMNTD92997028000 0014 1 D9299702800800 EQUIPMNTD92997028000 0016 1 D9299145500700 HARNESS D92997028000 0018 1 D9299145600500 HARNESS D92997028000 0020 1 D9299146102000 HARNESS D92997028000 0022 1 D9299146200900 HARNESS D92997028000 0024 1 D9299146300400 HARNESS D92997028000 0026 1 D9299146400300 HARNESS D92997028000 0028 1 D9299147000800 HARNESS D92997028000 0030 1 D9299147100600 HARNESS D92997028000 0032 1 D9299147201500 HARNESS D92997028000 0034 1 D9299147300400 HARNESS D92997028000 0036 1 D9299702801000 EQUIPMNTD92997028000 0038 1 D9299148001300 HARNESS D92997028000 0040 1 D9299148100400 HARNESS D92997028000 0042 1 D9299148300600 HARNESS D92997028000 0044 1 D9299149200600 HARNESS D92997028000 0046 1 D9299149300400 HARNESS D92997028000 0048 1 D9299149400400 HARNESS D92997028000 0050 1 D9299702801200 EQUIPMNTD92997028000 0054 1 D9299702602800 EQUIPMNTD92997028000 0056 1 D9299702801400 EQUIPMNTD92997028000 0058 1 D9299702801600 EQUIPMNTD92997028000 0060 1 D9299702801800 EQUIPMNTD92997028000 0062 1 D9299702802000 EQUIPMNTD92997028000 0064 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 112 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9289471302600 PLCRDSETD92997028000 0065

Kit 281132D86R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9299956100200 EQUIPMNTD92999561000 0001 1 D9299955900400 EQUIPMNTD92999561000 0002 1 D9299955900600 EQUIPMNTD92999561000 0003 1 D9299956100400 EQUIPMNTD92999561000 0004 1 D9299956100600 EQUIPMNTD92999561000 0005 1 D9299955901200 EQUIPMNTD92999561000 0006 1 D9299955901400 EQUIPMNTD92999561000 0007 1 D9299955901600 EQUIPMNTD92999561000 0008 1 D9299956100800 EQUIPMNTD92999561000 0009 1 D9299955902000 EQUIPMNTD92999561000 0010 1 D9299956101000 EQUIPMNTD92999561000 0011 1 D9299955902400 EQUIPMNTD92999561000 0012 1 D9299062701300 HARNESS D92999561000 0014 1 D9299955902600 EQUIPMNTD92999561000 0015 1 D9299955902800 EQUIPMNTD92999561000 0016 1 D9299063400200 HARNESS D92999561000 0018 1 D9299955903000 EQUIPMNTD92999561000 0019 1 D9299082000100 HARNESS D92999561000 0021 1 D9299082400700 HARNESS D92999561000 0023 1 D9299083300100 HARNESS D92999561000 0025 1 D9289471302600 PLCRDSETD92999561000 0026

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D87R01 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 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 113 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 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 BRACKET 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 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 CONNECTRD92891805000 0933 2 EN2997KE516 CONNECTRD92891805000 0935 3 D2557016200200 COVER D92891805000 1099 4 D9249104900600 BRACKET D92891805000 1110 3 D2557016200000 COVER D92891805000 9001

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 114 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Kit 281132D88R00 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

4 MS21042-08 NUT D92491681000 0202 4 NSA5066-08-1 NUT D92491681000 0230 4 E0660-01 MOUNT D92491681000 0266 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 D9249102520000 WASHER D92491681000 0680 2 D9249104720000 GUIDE D92491681000 0724 1 D9249102620600 DEFLECTRD92491681000 0730 6 D9249104920400 BRACKET D92491681000 0737 1 D9249107302800 CONNECTND92491681000 0824

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D89R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 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

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 281132D90R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 8 NAS1801-08-10 SCREW D92891805002 0006 5 NAS1801-08-19 SCREW D92891805002 0012 1 NAS1801-08-25 SCREW D92891805002 0016 9 NSA935808C01 WASHER D92891805002 0151 12 NAS1149CN816R WASHER D92891805002 0152 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 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 115 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 5 MS21919WCH2 CLAMP D92891805002 0364 6 NSA935807-06 CLAMP D92891805002 0376 6 NSA935807-09 CLAMP D92891805002 0377

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 281132D91R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 61 NAS1801-08-8 SCREW D92891805004 0001 127 NAS1801-08-19 SCREW D92891805004 0002

15 NAS1801-08-29 SCREW D92891805004 0003 45 NAS1801-3-8 SCREW D92891805004 0004 266 NSA5066-08-2 NUT D92891805004 0005 5 NSA5527-03-08 SPACER D92891805004 0006 61 MS21042L3 NUT D92891805004 0007 24 MS21042L04 NUT D92891805004 0008 196 NAS1149DN816K WASHER D92891805004 0009

46 NAS1149D0332K WASHER D92891805004 0010 24 NAS1149DN416K WASHER D92891805004 0011

3 NSA935510-02 BOBBIN D92891805004 0012 14 MS21919WCH5 CLAMP D92891805004 0013 11 NSA5527-03-02 SPACER D92891805004 0016

1 NSA935808-01 WASHER D92891805004 0017 10 ABS0731A01 SUPPORT D92891805004 0018 20 NAS1149C0332R WASHER D92891805004 0019 154 NSA5527-03-01 SPACER D92891805004 0020 5 NSA934710T11 FITTING D92891805004 0021 2 NSA934710T14 FITTING D92891805004 0022 1 E0660-01 MOUNT D92891805004 0023 24 NAS1100-04-8 SCREW D92891805004 0025 17 NSA935513-01 MOUNT D92891805004 0027

1 NSA935504-03 MOUNT D92891805004 0030 176 NSA935504-01 MOUNT D92891805004 0031 1 ASNA0032H052 CLAMP D92891805004 0033 5 NSA935513-07 MOUNT D92891805004 0034 41 NSA5527-03-03 SPACER D92891805004 0035 1000 NSA935401-04 TIE D92891805004 0036 17 MS21042L08 NUT D92891805004 0037

1 D9249181406400 GUIDE D92891805004 0038 1 D9249181406600 GUIDE D92891805004 0039 1 NAS1801-3-18 SCREW D92891805004 0040 8 NAS1801-08-14 SCREW D92891805004 0041 1 D9249181404800 GUIDE D92891805004 0042 1 NSA935808C01 WASHER D92891805004 0043 1 D9249181401800 GUIDE D92891805004 0047 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 116 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 4 EN3646A508 RECEPTCLD92891805004 0048 2 ABS0355-03 BRACKET D92891805004 0049 20 NSA5527-03-04 SPACER D92891805004 0052 16 NAS1801-08-10 SCREW D92891805004 0053

1 NAS1096-2-43 SCREW D92891805004 0055 1 NSA5527-03-06 SPACER D92891805004 0057 1 NAS1096-2-24 SCREW D92891805004 0058 1 NSA5527-03-06 SPACER D92891805004 0059 16 NAS1149D0363K WASHER D92891805004 0060

5 E0343-01 MOUNT D92891805004 0063 12 NAS1096-3-10 SCREW D92891805004 0064

3 EN3646A510 RECEPTCLD92891805004 0065 3 EN3646A516 RECEPTCLD92891805004 0066 2 EN3646A3C10 CAP D92891805004 0067 1 EN3646A520 RECEPTCLD92891805004 0068 1 EN3646A522 RECEPTCLD92891805004 0069 200 NSA5539S SLEEVE D92891805004 0070 1 NAS1801-3-44 SCREW D92891805004 0072 200 NSA935401-03 TIE D92891805004 0073 1 NSA5527-03-03 SPACER D92891805004 0075 1 NAS1801-3-28 SCREW D92891805004 0076 1 A9249429720200 BRACKET D92891805004 0078 1 A9249429620400 SEALING D92891805004 0079 1 NSA939510BN STRIP D92891805004 0080 1 A9249436120000 BRACKET D92891805004 0083 1 NAS1801-3-13 SCREW D92891805004 0084 23 D9249102520000 WASHER D92891805004 0190

1 D9249181401600 GUIDE D92891805004 0671

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 281132D92R03 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 34 A9249635720200 BRACKET D92491681004 0001 17 D9249179320000 BRACKET D92491681004 0002

6 D9249178000600 BRACKET D92491681004 0007 1 D9249177124400 BRACKET D92491681004 0009 5 D9249177520000 ANGLE D92491681004 0013 4 D9249172321200 BRACKET D92491681004 0016 1 D9249177520200 ANGLE D92491681004 0019 1 D9249184620400 BRACKET D92491681004 0021 1 D9249177100000 BRACKET D92491681004 0023 1 D9249180922600 BRACKET D92491681004 0026 1 MS21060L3 NUT D92491681004 0027 1 D9249178001200 BRACKET D92491681004 0032 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 117 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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

228 LN9198-3215BF RIVET D92491681004 0632

12 LN9198-4828CF RIVET D92491681004 0648

2 DIN65399-2412BF RIVET D92491681004 0724

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D93R01 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 1 D9249180900000 BRACKET D92491681006 0026 1 D9249180922400 BRACKET D92491681006 0027 6 D9249177920000 BRACKET D92491681006 0028 2 D9249177820200 BRACKET D92491681006 0030

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D94R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 8 MS21043-3 NUT D26170100028 0014 1 D2617013302800 CAP D26170100028 0131

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 281132D95R00

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 118 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5347449320000 FITTING D53470076008 0010 1 D5337217620000 SHEET D53470076008 0012 1 D5347449521600 SECTION D53470076008 0014 1 D5347658920000 FITTING D53470076008 0016 1 D5347659220000 SHIM D53470076008 0018 1 D5347659020000 FITTING D53470076008 0020 6 D5347470020200 ANGLE D53470076008 0022 1 D5347470020300 ANGLE D53470076008 0023 3 D5347470020400 ANGLE D53470076008 0024 1 D5347449520400 SECTION D53470076008 0026 3 D5347449520500 SECTION D53470076008 0027 3 D5347449520300 SECTION D53470076008 0028 1 D5347470021400 ANGLE D53470076008 0030 1 D5337217620800 FILLER D53470076008 0032 1 D5347470023200 ANGLE D53470076008 0034 1 D5347470023400 ANGLE D53470076008 0036 2 D5337217620400 SHIM D53470076008 0038 1 D5347470520000 ANGLE D53470076008 0040 1 D5347470520100 ANGLE D53470076008 0041 1 D5347470021000 ANGLE D53470076008 0042 1 D5347470021200 ANGLE D53470076008 0044 1 D5347470024000 ANGLE D53470076008 0046 1 D5347658220200 SHIM D53470076008 0048 1 D5347470023800 ANGLE D53470076008 0050 1 D5347470023600 ANGLE D53470076008 0052 1 D5347659320000 FITTING D53470076008 0054 1 D5337217621000 SHEET D53470076008 0056 2 D5347470024200 ANGLE D53470076008 0058 2 D5337217621200 SHEET D53470076008 0060 1 D5347470046200 ANGLE D53470076008 0062 2 D5347470046400 ANGLE D53470076008 0064 1 D5347470520300 SUPPORT D53470076008 0066 1 D5347658820000 WEB D53470076008 0070 1 D5347470025000 ANGLE D53470076008 0072 1 D5347470025200 ANGLE D53470076008 0074 1 D5347657920200 WEB D53470076008 0076 1 D5347449522600 SECTION D53470076008 0078 1 D5347449522800 SECTION D53470076008 0080 1 D5347550021000 KEY D53470076008 0082 2 D5347471320800 PLATE D53470076008 0084 2 D5347449522000 SECTION D53470076008 0088 1 D5347449522200 SECTION D53470076008 0090 1 D5347449523400 SECTION D53470076008 0096 2 D5347449524000 SECTION D53470076008 0098 1 D5347449524200 SECTION D53470076008 0100 1 D5347471321800 PLATE D53470076008 0102 1 D5337217625800 SHEET D53470076008 0110 1 D5347075321400 CLIP D53470076008 0114 1 D5347646320400 DOUBLER D53470076008 0160 1 D5347646321000 DOUBLER D53470076008 0162 1 D5347470920200 COVER D53470076008 0164 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 119 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D5347669200200 PLATE D53470076008 0166 2 D5347669000000 TUBE D53470076008 0172 2 D5347669100000 PLUG D53470076008 0174 2 D5347472120200 SHIM D53470076008 0176 4 D5347470220000 SHIM D53470076008 0178 2 D5347472120400 SHIM D53470076008 0180 1 D5347660220200 SHIM D53470076008 0182 3 D5347449420600 FITTING D53470076008 0200 1 D5347449421100 FITTING D53470076008 0201 2 D5347448420200 STRAP D53470076008 0202 1 D5347448420300 STRAP D53470076008 0203 1 D5347037820400 SUPPORT D53470076008 0204 1 D5347449920200 FITTING D53470076008 0206 1 D5347657720000 WEB D53470076008 0208 1 D5347026100600 XBEAM D53470076008 0218 1 D5347035601400 XBEAM D53470076008 0230 1 D5347449820400 FITTING D53470076008 0244 2 MS16625-4212 RING D53470076008 0500 10 NAS1153E7 SCREW D53470076008 0502

8 ABS0337-01A RECEPTCLD53470076008 0504 2 NAS1096-3-10 SCREW D53470076008 0506 10 NAS1474A3 NUT D53470076008 0510

2 NAS1067C3M NUT D53470076008 0512 2 DAN6-6-5X PIN D53470076008 0665 5 DAN6-6-6X PIN D53470076008 0666 6 DAN6-6-7X PIN D53470076008 0667 6 DAN6-6-8X PIN D53470076008 0668 8 DAN6-6-7Y PIN D53470076008 0677 8 DAN6-6-8Y PIN D53470076008 0678 12 DAN5-6-5X PIN D53470076008 0765

1 DAN5-6-7X PIN D53470076008 0767 1 DAN5-6-8X PIN D53470076008 0768 16 NSA5330-6 COLLAR D53470076008 0803 540 NSA5075-6 COLLAR D53470076008 0806

33 DAN11-6X COLLAR D53470076008 0807 33 NSA5075-8 COLLAR D53470076008 0808 68 DAN6-6-3 PIN D53470076008 0863

8 DAN6-6-4 PIN D53470076008 0864 62 DAN6-6-5 PIN D53470076008 0865 73 DAN6-6-6 PIN D53470076008 0866 22 DAN6-6-7 PIN D53470076008 0867 54 DAN6-6-8 PIN D53470076008 0868 28 DAN6-6-10 PIN D53470076008 0870 30 DAN5-6-3 PIN D53470076008 0963 71 DAN5-6-4 PIN D53470076008 0964 81 DAN5-6-5 PIN D53470076008 0965 28 DAN5-6-6 PIN D53470076008 0966 10 DAN5-6-7 PIN D53470076008 0967

6 DAN5-6-8 PIN D53470076008 0968 3 DAN5-6-9 PIN D53470076008 0969 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 120 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 9 DAN5-8-5 PIN D53470076008 0985 15 DAN5-8-6 PIN D53470076008 0986

9 DAN5-8-7 PIN D53470076008 0987 20 MBBN4477-4010 RIVET D53470076008 0541 300 MBBN4477-4810 RIVET D53470076008 0549 110 LN9198-4014CF RIVET D53470076008 0640 300 LN9198-4816CF RIVET D53470076008 0648

10 LN9198-6412CF RIVET D53470076008 0664 45 DIN65399-2415CF RIVET D53470076008 0724 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D96R02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D5347035000600 XBEAM D53470075008 0010 4 D5337217620000 SHEET D53470075008 0012 3 D5337217620100 SHEET D53470075008 0014 4 D5347449420600 FITTING D53470075008 0016 4 D5347449420700 FITTING D53470075008 0018 1 D5347449521800 SECTION D53470075008 0020 5 D5347448420200 STRAP D53470075008 0022 4 D5347448420300 STRAP D53470075008 0024 8 D5337217620800 FILLER D53470075008 0026 4 D5347449520300 SECTION D53470075008 0028 3 D5347449520200 SECTION D53470075008 0030 7 D5347449520500 SECTION D53470075008 0032 6 D5347449520400 SECTION D53470075008 0034 1 D5347470020000 ANGLE D53470075008 0036 1 D5347470020100 ANGLE D53470075008 0038 3 D5347470020400 ANGLE D53470075008 0044 2 D5347470020500 ANGLE D53470075008 0046 6 D5347470020200 ANGLE D53470075008 0048 4 D5347470020300 ANGLE D53470075008 0050 1 D5347026000600 XBEAM D53470075008 0052 2 D5347470520000 ANGLE D53470075008 0054 2 D5347470520100 ANGLE D53470075008 0056 1 D5347449523400 SECTION D53470075008 0058 1 D5347449523600 SECTION D53470075008 0060 2 D5347449522000 SECTION D53470075008 0062 2 D5347449523200 SECTION D53470075008 0064 1 D5347470320000 WEB D53470075008 0066 1 D5347470020800 ANGLE D53470075008 0068 1 D5347470021000 ANGLE D53470075008 0070 1 D5347470020600 ANGLE D53470075008 0072 1 D5347470021200 ANGLE D53470075008 0074 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 121 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5347035300600 XBEAM D53470075008 0076 1 D5337217620700 SHEET D53470075008 0078 1 D5347470420400 WEB D53470075008 0080 1 D5347470021600 ANGLE D53470075008 0082 1 D5347470021800 ANGLE D53470075008 0084 1 D5347470024800 ANGLE D53470075008 0086 1 D5347470043800 ANGLE D53470075008 0088 1 D5347470021400 ANGLE D53470075008 0090 1 D5347470022200 ANGLE D53470075008 0092 1 D5347449520200 SECTION D53470075008 0094 1 D5347449520400 SECTION D53470075008 0096 1 D5347470020500 ANGLE D53470075008 0098 2 D5347470020300 ANGLE D53470075008 0100 1 D5347658420000 ANGLE D53470075008 0102 1 D5347471321200 PLATE D53470075008 0104 2 D5347471500200 PLATE D53470075008 0108 1 D5347471500000 PLATE D53470075008 0110 1 D5347471502800 PLATE D53470075008 0112 1 D5347471501000 PLATE D53470075008 0116 2 D5347471500300 PLATE D53470075008 0118 1 D5347471500100 PLATE D53470075008 0120 1 D5347471503200 PLATE D53470075008 0122 1 D5347471502600 PLATE D53470075008 0124 1 D5347659100000 ANGLE D53470075008 0126 6 D5347470120000 ANGLE D53470075008 0128 6 D5347470120200 ANGLE D53470075008 0130 4 D5347470120100 ANGLE D53470075008 0132 5 D5347470120300 ANGLE D53470075008 0134 1 D5347471322400 PLATE D53470075008 0138 1 D5347471322600 PLATE D53470075008 0140 1 D5347048100600 SECTION D53470075008 0152 1 D5347047500800 SECTION D53470075008 0154 1 D5347047600800 SECTION D53470075008 0156 1 D5347646320200 DOUBLER D53470075008 0160 1 D5347646320000 DOUBLER D53470075008 0162 1 D5347470920200 COVER D53470075008 0164 2 D5347669200200 PLATE D53470075008 0166 2 D5347669000000 TUBE D53470075008 0172 2 D5347669100000 PLUG D53470075008 0174 4 D5347472120000 SHIM D53470075008 0176 4 D5347470220000 SHIM D53470075008 0178 4 D5347658620000 BUSHING D53470075008 0204 1 D5347048800400 PLATE D53470075008 0214 1 D5347048900400 PLATE D53470075008 0216 1 D5347049200400 PLATE D53470075008 0218 1 D5347046824300 ANGLE D53470075008 0222 1 D5347046824600 ANGLE D53470075008 0224 2 D5347046824000 ANGLE D53470075008 0228 1 D5347046823800 ANGLE D53470075008 0230 1 D5347046823600 ANGLE D53470075008 0232 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 122 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5347046824200 ANGLE D53470075008 0234 1 D5347046824400 ANGLE D53470075008 0236 2 MS16625-4212 RING D53470075008 0500 10 NAS1153E7 SCREW D53470075008 0502

8 ABS0337-01A RECEPTCLD53470075008 0504 2 NAS1096-3-10 SCREW D53470075008 0506 12 NAS1791A3-1 NUT D53470075008 0508 10 NAS1474A3 NUT D53470075008 0510

8 DAN6-6-7X PIN D53470075008 0667 10 DAN6-6-9X PIN D53470075008 0669

1 DAN6-6-8Y PIN D53470075008 0678 7 DAN5-6-4X PIN D53470075008 0764 24 DAN5-6-5X PIN D53470075008 0765 10 DAN5-6-8X PIN D53470075008 0768

8 DAN5-6-8Y PIN D53470075008 0778 8 NSA5330-6 COLLAR D53470075008 0803 3 NSA5075-5 COLLAR D53470075008 0804 781 NSA5075-6 COLLAR D53470075008 0806

63 DAN11-6X COLLAR D53470075008 0807 40 NSA5075-8 COLLAR D53470075008 0808 16 DAN6-6-3 PIN D53470075008 0863

8 DAN6-6-4 PIN D53470075008 0864 34 DAN6-6-5 PIN D53470075008 0865

4 DAN6-6-6 PIN D53470075008 0866 10 DAN6-6-7 PIN D53470075008 0867

1 DAN6-6-8 PIN D53470075008 0868 1 DAN6-6-10 PIN D53470075008 0870 3 DAN5-5-5 PIN D53470075008 0945 70 DAN5-6-3 PIN D53470075008 0963 183 DAN5-6-4 PIN D53470075008 0964 187 DAN5-6-5 PIN D53470075008 0965 126 DAN5-6-6 PIN D53470075008 0966

40 DAN5-6-7 PIN D53470075008 0967 83 DAN5-6-8 PIN D53470075008 0968 20 DAN5-6-10 PIN D53470075008 0970 24 DAN5-8-5 PIN D53470075008 0985

8 DAN5-8-6 PIN D53470075008 0986 8 DAN5-8-7 PIN D53470075008 0987 40 DIN65399-2410CF RIVET D53470075008 0724 90 DIN65399-3210CF RIVET D53470075008 0732 30 MBBN4477-4012 RIVET D53470075008 0541 350 MBBN4477-4812 RIVET D53470075008 0549 970 LN9198-4012CF RIVET D53470075008 0640 550 LN9198-4812CF RIVET D53470075008 0648 4 D5347472120200 SHIM D53470075008 0176 1 D5347471500800 PLATE D53470075008 0176

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 123 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132D97R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 8 NAS1801-08-6 SCREW D92891805008 0004 22 NAS1801-08-9 SCREW D92891805008 0005

4 NAS1801-08-12 SCREW D92891805008 0007 2 NAS1801-08-17 SCREW D92891805008 0010 4 NAS1801-08-19 SCREW D92891805008 0012 2 NAS1801-08-23 SCREW D92891805008 0014 1 NAS1801-08-39 SCREW D92891805008 0020 49 NAS1801-3-9 SCREW D92891805008 0030 48 NAS1100-04-5 SCREW D92891805008 0051 24 NAS1102-08-8 SCREW D92891805008 0058 48 NAS1149CN416R WASHER D92891805008 0150 23 NAS1149CN816R WASHER D92891805008 0152 61 NAS1149C0332R WASHER D92891805008 0153

4 ASNA0113-40ADL WASHER D92891805008 0163 16 NSA935808C01 WASHER D92891805008 0171

2 D9249102520000 WASHER D92891805008 0190 48 MS21042-04 NUT D92891805008 0200

3 MS21042-08 NUT D92891805008 0202 8 MS21042-3 NUT D92891805008 0203 32 NAS1291C3M NUT D92891805008 0218

1 NSA5110-08-1 NUT D92891805008 0225 6 NSA5066-08-1 NUT D92891805008 0230 36 NSA5067-08-1 NUT D92891805008 0236

5 E0343-01 MOUNT D92891805008 0250 11 NSA935504-01 MOUNT D92891805008 0251

1 NSA935504-02 BRACKET D92891805008 0252 4 NSA935513-01 MOUNT D92891805008 0256 11 NSA935513-05 MOUNT D92891805008 0257

1 NSA935513-07 MOUNT D92891805008 0259 6 ABS0355-01 BRACKET D92891805008 0262 10 ABS0355-02 BRACKET D92891805008 0263 10 NSA935514-03 WASHER D92891805008 0264

1 E0660-01 MOUNT D92891805008 0266 20 ABS0731A01 SUPPORT D92891805008 0267

9 ABS0774A01A BRACKET D92891805008 0268 2 NSA5527-03-03 SPACER D92891805008 0304 4 NSA5527-03-04 SPACER D92891805008 0306 1 NSA5527-03-06 SPACER D92891805008 0310 4 NSA5527-03-08 SPACER D92891805008 0314 1 NSA5527-03-11 SPACER D92891805008 0320 1 MS21919WCH6 CLAMP D92891805008 0352 12 NSA935807-09 CLAMP D92891805008 0377

4 NSA935807-16 CLAMP D92891805008 0381 4 D9249104800000 SHEET D92891805008 0727 2 D9249104800400 SHEET D92891805008 0729 3 TSTMNR502-0 CONDUIT D92891805008 0763 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 124 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 NSA934710T13 FITTING D92891805008 0773 30 NSA935510-02 BOBBIN D92891805008 0777 100 NSA935401-03 TIE D92891805008 0793 200 NSA935401-04 TIE D92891805008 0794 100 NSA935401-05 TIE D92891805008 0795 1 D9249107100600 STRAP D92891805008 0834 2 D9249107303000 CONNECTND92891805008 0846 2 DAN328H25 TAPE D92891805008 0877 4 EN2997KE3C12 CAP D92891805008 0930 2 EN2997KE3C16 CAP D92891805008 0932 4 EN2997KE512 CONNECTRD92891805008 0933 2 EN2997KE516 CONNECTRD92891805008 0935 10 EN6049-006-08-5 SLEEVE D92891805008 1032 1.3 EN6049-006-13-5 SLEEVE D92891805008 1033 1.3 EN6049-006-19-5 SLEEVE D92891805008 1034

6 D2557016200200 COVER D92891805008 1099 3 D9249104900600 BRACKET D92891805008 1110 1 D9249104901800 BRACKET D92891805008 1137 1 D9289180520200 PLACARD D92891805008 0002

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 281132D98R02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 4 NSA5066-08-1 NUT D92491681010 0230 2 A9249187820200 SHEET D92491681010 0565 2 A9249199820000 PLATE D92491681010 0632 6 D9249104920400 BRACKET D92491681010 0737 20 EN6081D4-10 RIVET D92491681010 9001

7 NAS1096-2-12 SCREW D92492244002 0007 1 NAS1096-2-14 SCREW D92492244002 0009 10 ASNA0113-40ADL WASHER D92492244002 0163

2 D9249102520000 WASHER D92492244002 0180 4 MS21042-08 NUT D92492244002 0202 4 E0660-01 MOUNT D92492244002 0266 1 NSA5527-03-04 SPACER D92492244002 0306 1 NSA5527-03-07 SPACER D92492244002 0312 2 D9249104720000 GUIDE D92492244002 0724 1 D9249102620600 DEFLECTRD92492244002 0730 1 D9249107302800 CONNECTND92492244002 0824

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 125 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Kit 281132D99R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9299140500100 HARNESS D92997028030 0002 1 D9299702600100 EQUIPMNTD92997028030 0004 1 D9299702600200 EQUIPMNTD92997028030 0006 1 D9299142801400 HARNESS D92997028030 0008 1 D9299702800200 EQUIPMNTD92997028030 0010 1 D9299702800400 EQUIPMNTD92997028030 0012 1 D9299702803100 EQUIPMNTD92997028030 0014 1 D9299145001500 HARNESS D92997028030 0016 1 D9299145500900 HARNESS D92997028030 0018 1 D9299145600700 HARNESS D92997028030 0020 1 D9299146102200 HARNESS D92997028030 0022 1 D9299146201100 HARNESS D92997028030 0024 1 D9299146300400 HARNESS D92997028030 0026 1 D9299146400300 HARNESS D92997028030 0028 1 D9299147000800 HARNESS D92997028030 0030 1 D9299147100800 HARNESS D92997028030 0032 1 D9299147201500 HARNESS D92997028030 0034 1 D9299147300400 HARNESS D92997028030 0036 1 D9299702801000 EQUIPMNTD92997028030 0038 1 D9299148001500 HARNESS D92997028030 0040 1 D9299148100400 HARNESS D92997028030 0042 1 D9299148300800 HARNESS D92997028030 0044 1 D9299149200600 HARNESS D92997028030 0046 1 D9299149300400 HARNESS D92997028030 0048 1 D9299149400400 HARNESS D92997028030 0050 1 D9299702803200 EQUIPMNTD92997028030 0054 1 D9299702803300 EQUIPMNTD92997028030 0056 1 D9299702803400 EQUIPMNTD92997028030 0058 1 D9299702803500 EQUIPMNTD92997028030 0060 1 D9299702803600 EQUIPMNTD92997028030 0062 1 D9299702803700 EQUIPMNTD92997028030 0064 1 D9289471302600 PLCRDSETD92997028030 0065

Kit 281132G03R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

43 A9249635720200 BRACKET D92491681012 0001 65 D9249179320000 BRACKET D92491681012 0002

6 D9249178000600 BRACKET D92491681012 0007 1 D9249177124400 BRACKET D92491681012 0009 6 D9249177520000 ANGLE D92491681012 0013 4 D9249172321200 BRACKET D92491681012 0016 2 D9249177520200 ANGLE D92491681012 0019 1 D9249184620400 BRACKET D92491681012 0021 1 D9249177100000 BRACKET D92491681012 0023 1 D9249180922600 BRACKET D92491681012 0026 1 MS21060L3 NUT D92491681012 0027 1 D9249178001200 BRACKET D92491681012 0032 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 126 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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

335 EN6081AD4-10 RIVET D92491681012 0632

12 EN6081D6-18 RIVET D92491681012 0648

2 EN6101AD3-08 RIVET D92491681012 0724

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281132G04R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 70 NAS1801-08-8 SCREW D92891805010 0001 115 NAS1801-08-19 SCREW D92891805010 0002

15 NAS1801-08-29 SCREW D92891805010 0003 67 NAS1801-3-8 SCREW D92891805010 0004 193 NSA5066-08-2 NUT D92891805010 0005 1 NSA5527-03-08 SPACER D92891805010 0006 94 MS21042L3 NUT D92891805010 0007 28 MS21042L04 NUT D92891805010 0008 218 NAS1149DN816K WASHER D92891805010 0009

48 NAS1149D0332K WASHER D92891805010 0010 28 NAS1149DN416K WASHER D92891805010 0011

6 NSA935510-02 BOBBIN D92891805010 0012 15 MS21919WCH5 CLAMP D92891805010 0013

4 NSA5527-03-02 SPACER D92891805010 0016 1 NSA935808-01 WASHER D92891805010 0017 10 ABS0731A01 SUPPORT D92891805010 0018 44 NAS1149C0332R WASHER D92891805010 0019 143 NSA5527-03-01 SPACER D92891805010 0020 7 NSA934710T11 FITTING D92891805010 0021 3 NSA934710T14 FITTING D92891805010 0022 1 E0660-01 MOUNT D92891805010 0023 9 NAS1801-08-39 SCREW D92891805010 0024 28 NAS1100-04-8 SCREW D92891805010 0025

8 NSA935513-01 MOUNT D92891805010 0027 1 NSA935513-05 MOUNT D92891805010 0028 2 NSA935504-03 MOUNT D92891805010 0030 172 NSA935504-01 MOUNT D92891805010 0031 1 ASNA0032H052 CLAMP D92891805010 0033 41 NSA5527-03-03 SPACER D92891805010 0035 1000 NSA935401-04 TIE D92891805010 0036 16 MS21042L08 NUT D92891805010 0037

1 D9249181406400 GUIDE D92891805010 0038 1 D9249181406600 GUIDE D92891805010 0039 2 NAS1801-3-18 SCREW D92891805010 0040 16 NAS1801-08-14 SCREW D92891805010 0041

1 D9249181404800 GUIDE D92891805010 0042 1 D9249181401800 GUIDE D92891805010 0047 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 127 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 EN3646A508 RECEPTCLD92891805010 0048 2 ABS0355-03 BRACKET D92891805010 0049 18 NSA5527-03-04 SPACER D92891805010 0052 16 NAS1801-08-10 SCREW D92891805010 0053

1 NAS1801-08-43 SCREW D92891805010 0055 1 NSA935504-02 BRACKET D92891805010 0056 34 NAS1149D0363K WASHER D92891805010 0060

7 E0343-01 MOUNT D92891805010 0063 20 NAS1801-3-10 SCREW D92891805010 0064

5 EN3646A510 RECEPTCLD92891805010 0065 4 EN3646A516 RECEPTCLD92891805010 0066 4 EN3646A3C10 CAP D92891805010 0067 1 EN3646A520 RECEPTCLD92891805010 0068 1 EN3646A522 RECEPTCLD92891805010 0069 1 NAS1801-3-28 SCREW D92891805010 0076 2 A9249429720200 BRACKET D92891805010 0078 2 A9249429620400 SEALING D92891805010 0079 1 A9249436120000 BRACKET D92891805010 0083 1 NAS1801-3-13 SCREW D92891805010 0084 1 NAS1149CN832R WASHER D92891805010 0112 1 NSA935514-05A MOUNT D92891805010 0113 22 D9249102520000 WASHER D92891805010 0190

1 D9289180520200 PLACARD D92891805010

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 281132G05R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9299702600100 EQUIPMNTD92997028040 0004 1 D9299702600200 EQUIPMNTD92997028040 0006 1 D9299142801400 HARNESS D92997028040 0008 1 D9299702800200 EQUIPMNTD92997028040 0010 1 D9299702800400 EQUIPMNTD92997028040 0012 1 D9299702803100 EQUIPMNTD92997028040 0014 1 D9299702800800 EQUIPMNTD92997028040 0016 1 D9299145500900 HARNESS D92997028040 0018 1 D9299145600700 HARNESS D92997028040 0020 1 D9299146102000 HARNESS D92997028040 0022 1 D9299146200900 HARNESS D92997028040 0024 1 D9299146300400 HARNESS D92997028040 0026 1 D9299146400300 HARNESS D92997028040 0028 1 D9299147000800 HARNESS D92997028040 0030 1 D9299147100600 HARNESS D92997028040 0032 1 D9299147201500 HARNESS D92997028040 0034 1 D9299147300400 HARNESS D92997028040 0036 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 128 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9299702801000 EQUIPMNTD92997028040 0038 1 D9299148001300 HARNESS D92997028040 0040 1 D9299148100400 HARNESS D92997028040 0042 1 D9299148300600 HARNESS D92997028040 0044 1 D9299149200600 HARNESS D92997028040 0046 1 D9299149300400 HARNESS D92997028040 0048 1 D9299149400400 HARNESS D92997028040 0050 1 D9299702803200 EQUIPMNTD92997028040 0054 1 D9299702803300 EQUIPMNTD92997028040 0056 1 D9299702803400 EQUIPMNTD92997028040 0058 1 D9299702803500 EQUIPMNTD92997028040 0060 1 D9299702803600 EQUIPMNTD92997028040 0062 1 D9299702803700 EQUIPMNTD92997028040 0064 1 D9289471302600 PLCRDSETD92997028040 0065

Kit 281132G10R02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5347470420200 WEB D53470075002 080 1 D5347470022000 ANGLE D53470075002 0088 1 D5347470022400 ANGLE D53470075002 0094 1 D5347470023000 ANGLE D53470075002 096 2 D5347470022800 ANGLE D53470075002 0098 1 D5347470022600 ANGLE D53470075002 0100 1 D5347471501200 PLATE D53470075002 0124 1 D5347066920600 SECTION D53470075002 0136 1 D5337236320200 SHIM D53470075002 0202 1 D5347063721600 SECTION D53470075002 0206 1 D5347048700200 PLATE D53470075002 210 1 D5347048500400 PLATE D53470075002 0212 2 DAN6-6-6X PIN D53470075002 666 2 DAN6-6-7X PIN D53470075002 667 8 DAN6-6-8X PIN D53470075002 668 6 DAN5-6-6X PIN D53470075002 766 13 NSA5075-6 COLLAR D53470075002 806 25 DAN11-6X COLLAR D53470075002 807

2 DAN6-6-4 PIN D53470075002 864 11 DAN6-6-5 PIN D53470075002 865 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 281132G12R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 10 MS21043-3 NUT D26170100024 0014 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 129 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2617013300600 CAP D26170100024 0031

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. **D. L I** **S T** **O F** **M A**  **T E** **R I** **A L** **S -** **O P** **E R** **A T** **O R** **S U** **P P** **L I** **E D**  (1) Consumable Materials DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP MAT No. Grease High Pressure Mat. No. 04-004 As required Pure Mineral Vaseline Mat. No. 04-012 As required Zinc Chromate General Purpose Mat. No. 05-002 As required Electrical Bonding Coating (Blue Color) Mat. No. 07-001 As required Sealing coat Mat. No. 07-011 As required Sealant Mat. No. 08-007 As required Sealant High Temperature Mat. No. 08-007B As required Adhesive Mat. No. 08-010 As required Adhesive Mat. No. 08-010A As required Adhesive Mat. No. 08-048 As required Adhesive Mat. No. 08-051 As required Adhesive Mat. No. 08-053 As required Sealant High Temperature Mat. No. 08-573 As required Sealant, Anaerobic Mat. No. 08-623 As required Fuel Tank Sealant Polysulfide Mat. No. 09-001 As required Fuel Tank Sealant Polysulfide Mat. No. 09-002 As required Sealant Mat. No. 09-005 As required Sealant Mat. No. 09-013 As required Corrosion Inhibiting Fillet Consistency Mat. No. 09-016 As required Sealant Mat. No. 09-018 As required Protective Coating For Fuel Vapor Mat. No. 09-032 As required Polyurethane top coat, grey Mat. No. 16-002 As required Dry Cleaning Solvent Mat. No. 11-002 As required Solvent General Purpose Mat. No. 11-026 As required Anti-Corrosion Primer (Polyurethane) Mat. No. 16-001 As required Anti corrosion primer Mat. No. 16-006 As required Fuel Tank Coating Mat. No. 16-015 As required Polyurethane top coat Mat. No. 16-018 As required Wash primer Mat. No. 16-020 As required Cotton cloth Mat. No. 19-003 As required Lockwire Mat. No. 19-009 As required Lockwire Mat. No. 19-010 As required Lockwire Mat. No. 19-018 As required DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 130 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP MAT No. NOTE : To accomplish this Service Bulletin it is necessary to use the expendable parts listed in the AMM 29-11-41, Page block 401. (2) Components Config. 01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 1418KID01-03 IND (01) 1 SIC5059-12-0308 Computer (01) NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. NOTE(01) The operator must get this equipment from : SMITHS AEROSPACE ELECTRONIC SYSTEMS PO BOX 188 GL52 8SF CHELTENHAM UNITED KINGDOM Config. 02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 1418KID01-03 IND (01) NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. NOTE(01) The operator must get this equipment from : SMITHS AEROSPACE ELECTRONIC SYSTEMS PO BOX 188 GL52 8SF CHELTENHAM UNITED KINGDOM Config. 03 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 1158000-15 Canister (02) 1 1158000-21 Valve (02) 1 1419KID01-03 IND (01) 1 365A02 Valve (04) 1 568-1-27170-002 Pump (03) 1 568-1-27171-002 Plate (03) 1 HTE190001-2 Actuator (02) 1 HTE8002 Clamp (02) DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 131 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 HTE690045 Switch (02) 1 HTE900135 Valve (02) 1 SIC5059-12-0308 Computer (01) 1 9843144M Valve (01) 1 30042-0000-0501 CTL Unit (01) NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. NOTE(01) The operator must get this equipment from : SMITHS AEROSPACE ELECTRONIC SYSTEMS PO BOX 188 GL52 8SF CHELTENHAM UNITED KINGDOM NOTE(02) The operator must get this equipment from : EATON AEROSPACE LTD STATION ROAD 3DW SOUTH MOLTON NORTH DEVON EX 36 UNITED KINGDOM NOTE(03) The operator must get this equipment from : FR-HITEMP LTD ABBEY PARK PO14 QA TITCHFIELD FAREHAM HANTS UNITED KINGDOM NOTE(04) The operator must get this equipment from : LIEBHERR - AEROSPACE TOULOUSE SA 408 AVENUE DES ETATS UNIS 31016 TOULOUSE CEDEX FRANCE **E. P A** **R T** **S T** **O B** **E R** **E -** **I D** **E N** **T I** **F I** **E D** **B Y** **T H** **E O** **P E** **R A**  **T O** **R** ITEM NEW PART No. KEYWORD ITEM OLD PART No. INT D2587011905200 BLANKET D2587011903200 03 NOTE 01 D2587011905400 BLANKET D2587011903400 03 NOTE 01 D2587012105200 BLANKET D2587012103200 03 NOTE 01 D2587012105400 BLANKET D2587012103400 03 NOTE 01 D2587012305200 BLANKET D2587012303200 03 NOTE 01 D2587012305400 BLANKET D2587012303400 03 NOTE 01 D2587041405000 BLANKET D2587041403000 03 NOTE 01 D2587041406600 BLANKET D2587041403200 03 NOTE 01 D2587041605000 BLANKET D2587041603000 03 NOTE 01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 132 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

ITEM NEW PART No. KEYWORD ITEM OLD PART No. INT D2587041605600 BLANKET D2587041603200 03 NOTE 01 D2587041705000 BLANKET D2587041703000 03 NOTE 01 D2587041705200 BLANKET D2587041703200 03 NOTE 01 D2587041905000 BLANKET D2587041903000 03 NOTE 01 D2587041905200 BLANKET D2587041903200 03 NOTE 01 D2587042005200 BLANKET D2587042003000 03 NOTE 01 D2587042005400 BLANKET D2587042003200 03 NOTE 01 D2587042105200 BLANKET D2587042103000 03 NOTE 01 D2587042105400 BLANKET D2587042103200 03 NOTE 01 D2587042305000 BLANKET D2587042303000 03 NOTE 01 D2587042305200 BLANKET D2587042303200 03 NOTE 01 D2587051405000 BLANKET D2587051402400 03 NOTE 01 D2587051406400 BLANKET D2587051402600 03 NOTE 01 D2587051605000 BLANKET D2587051602200 03 NOTE 01 D2587051605200 BLANKET D2587051602400 03 NOTE 01 D2587051705000 BLANKET D2587051702200 03 NOTE 01 D2587051705600 BLANKET D2587051702400 03 NOTE 01 D2587051905000 BLANKET D2587051902200 03 NOTE 01 D2587051905200 BLANKET D2587051902400 03 NOTE 01 D2587052005200 BLANKET D2587052002200 03 NOTE 01 D2587052005400 BLANKET D2587052002400 03 NOTE 01 D2587052105200 BLANKET D2587052102200 03 NOTE 01 D2587052105400 BLANKET D2587052102400 03 NOTE 01 D2587052305000 BLANKET D2587052302200 03 NOTE 01 D2587052305200 BLANKET D2587052302400 03 NOTE 01 D2587060105200 BLANKET D2587060102000 03 NOTE 02 D2587060105400 BLANKET D2587060102200 03 NOTE 02 D2587060305200 BLANKET D2587060302200 03 NOTE 02 D2587060305400 BLANKET D2587060302400 03 NOTE 02 D2587065605000 BLANKET D2587065602000 03 NOTE 02 D2587065605200 BLANKET D2587065602400 03 NOTE 02 D2587070105200 BLANKET D2587070102000 03 NOTE 02 D2587070105400 BLANKET D2587070102200 03 NOTE 02 D2587070305200 BLANKET D2587070302000 03 NOTE 02 D2587070305400 BLANKET D2587070302200 03 NOTE 02 D2587071005400 BLANKET D2587071002000 03 NOTE 02 D2587071005600 BLANKET D2587071002200 03 NOTE 02 D2587075205000 BLANKET D2587075202200 03 NOTE 02 D2587075205200 BLANKET D2587075202400 03 NOTE 02 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. T O** **O L** **I N** **G -** **P R** **I C** **E A** **N D** **A V** 

**A I** **L A** **B I** **L I** **T Y**  ITEM PART NUMBER QTY DESCRIPTION DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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98D28108641000 1 Tool for YZ-latch adjustment (ACT) Kit 281132T01R00 ITEM PART NUMBER QTY DESCRIPTION D28108298001 1 Stowage box Procurement to be negotiated directly with AIRBUS. NOTE : The content of Kit 281132T01R00is necessary for the accomplishment of the Service Bulletin A320-28-1081 (INSTALLATION OF ONE OR TWO ADDITIONAL CENTER TANKS). Tag the part and put it into storage. **G. S P** **E C** **I A** **L T** **O O** **L S**  PERMASWAGE repair kit DLT series or D12000 series tools (vendor code F6087). This tool is used for the hydraulic tube installation (Kit D84 and D65).

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 134 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

**3. A C** **C O** **M P** **L I** **S H** **M E** **N T** **I N** **S T** **R U** **C T** **I O** **N S**  **A. G E** **N E** **R A** **L** WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR : - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE RELATED DOORS - OR ANY COMPONENT THAT MOVES. MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS. WARNING : IF YOU GET THE HYDRAULIC FLUID ON YOUR SKIN OR IN YOUR EYES: - FLUSH IT AWAY WITH CLEAN WATER - GET MEDICAL AID. CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS : - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON ELECTRICAL 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 thru Config. 03 1 Jack the aircraft, refer to AMM 07-11-00, Page block 201. 2 Make sure that the aircraft is electrically grounded, refer to AMM 12-34-24, Page block 201. 3 Put the access platform(s) in position. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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4Open the avionics door 822, refer to AMM 52-41-00, Page block 201. 5Open the passenger/crew door 841, refer to AMM 52-10-00, Page block 201. 6Open the FWD/AFT cargo compartment doors, refer to AMM 52-30-00, Page block 201. NOTE : Make sure that the applicable safety equipment is installed at the cargo compartment doors. 7Open the MLG doors, refer to AMM 32-12-00, Page block 201. NOTE : Make sure that the applicable safety equipment is installed at the main landing gear doors. 8 Remove the offwing escape slides 7504MM and 7505MM for access, refer to AMM 25-62-42, Page block 401. 9 Depressurize the Green, Blue and Yellow hydraulic system, refer to AMM 29-10-00, Page block 201. 10Depressurize the Green, Blue and Yellow hydraulic reservoirs, refer to AMM 29-14-00, Page block 201. 11Put the warning notices in position to tell persons not to pressurize the hydraulic systems. 12Open the accessory compartment door 312AR, refer to AMM 52-41-16, Page block 401. 13Open the maintenance door 314AR, refer to AMM 52-41-23, Page block 401. 14Open the APU doors 315AL and 316AR, refer to AMM 52-41-00, Page block 201. 15Remove and retain as necessary: - the passenger compartment seats, refer to AMM 25-21-41, Page block 401. - the passenger compartment floor covering, refer to AMM 25-28-41, Page block 401. - the passenger compartment floor panels, refer to AMM 53-22-12, Page block 401 and AMM 53-42-12, Page block 401. - the upper cabin sidewall panels, refer to AMM 25-23-43, Page block 401. - the lower cabin sidewall panels, refer to AMM 25-23-44, Page block 401. - the cabin ceiling panels, refer to AMM 25-23-41, Page block 401. - the cabin cove light panels, refer to AMM 25-23-48, Page block 401.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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- the overhead stowage compartments in the cabin, refer to AMM 25-24-41, Page block 401. - the insulation blankets, refer to AMM 25-80-00, Page block 201. - the FWD cargo compartment ceiling panel, refer to AMM 25-54-12, Page block 401. - the FWD cargo compartment sidewall panel, refer to AMM 25-54-12, Page block 401. - the FWD cargo compartment floor panel, refer to AMM 53-22-14, Page block 401. - the AFT cargo compartment sidewall panel, refer to AMM 25-55-11, Page block 401. 16Remove and retain the aft galley unit to get access to the pressure seals 7105VP, 7106VP, 7107VP, 7108VP and 7110VP at FR70, refer to AMM 25-33-41, Page block 401. 17Remove and retain the belly fairing panels 147FB, 148FB, 197BB, 197GB, 198BB and 198GB, refer to AMM 53-35-11, Page block 401. 18In the cockpit, remove the lining panels 211HC, 212FC, 212KC, 212KW, 212JW and 212HW, refer to AMM 06-41-53, Page block 1 and AMM 25-13-41, Page block 401. 19In the FWD cargo compartment, remove the panels 131AC, 131AW, 131BW, 131CW, 131DW, 132BW, 131HC, 131KC, 131LC, 131BC and 131CC, refer to AMM 06-41-53, Page block 1. 20Defuel the center tank, refer to AMM 28-25-00, Page block 301. 21Obey 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. 22On 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). 23Do 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. 24Make sure that there is(are) warning notice(s) on the external power receptacle to tell persons not to connect an external power source. 25Make sure that the EMER EXIT LT pushbutton switch on the 25VU is set to OFF. 26In the cockpit, on the Overhead Panel 35VU, release the BAT pushbutton switches. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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27Put a warning notice in position in the cockpit to tell persons not to operate the fuel system. 28Put a warning notice in position on the Panel 35VU to tell persons not to operate the batteries. 29Put a warning notice in position on the Refuel/Defuel Panel 800VU to tell persons not to operate the NORMAL BATTERY switch. 30Put a warning notice in position in the cockpit to tell persons not to start the APU. 31Put a warning notice in position in the cockpit to tell persons not to start the ENG1, 2. 32Disconnect 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. bTurn the knurled nut a quarter turn.

c Disconnect the connectors. d Put blanking caps on the disconnected electrical connectors. (2) Standard Practices (a) Refer to the AIRBUS Standards Manual (SM) if you find part numbers for the hardware components in the related kit(s) which you can not identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. (b) If you find process and material specifications in the affected design drawings which you do not know, refer to the cross reference list in the Process and Material Specification Manual (PMS). (c) For material specifications (Mat. No.) given in this Service Bulletin, refer to the Consumable Material List (CML) . (d) Tag the parts which you must remove and retain, to make the subsequent installation easier. (e) For the frame (FR) identification, refer to AMM 06-31-53, Page block 001. (f) For the cleaning of the stripping area, use Solvent General Purpose (Mat. No. 11-026). (g) Obey the hydraulic safety procedures, refer to AMM 29-00-00, Page block 201. (h) Put blanking plugs on all disconnected line ends. (i) For installation align the tube connections and hand tighten them. Torque the tube connections to the nominal torque value when the work is finished. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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(j) Torque the pipe unions, refer to AMM 20-21-12, Page block 201. (k) For connecting of hydraulic tubes with PERMASWAGE fittings, refer to AMM 20-23-11, Page block 201. (l) For location of the access panels and partition panels, refer to AMM 06-41-53, Page block 001. (m) If necessary, clean the work area with solvent (Mat. No. 11-026) and a cloth (Mat. No. 19-003). (n) Remove the old sealant with a plastic spatula and clean the surface with solvent (Mat. No. 11-026). (o) Before installation of structural items apply sealant (Mat. No. 09-013) on all mating surfaces. (p) Wet install fasteners with sealant (Mat. No. 09-013). (q) When you remove fasteners you must be careful that you do not damage the holes in the structure. (r) Make sure that you have the correct edge distance before you drill the fastener holes. (s) Transfer drill the existing holes with a pilot drill and a drill bush. (t) Drill the additional holes with a pilot drill of 2.5 mm (0.098 in.) diameter. Increase the hole diameter to the correct size for the fastener which you must install. (u) For fastener hole and drill data, refer to SRM 51-44-11. (v) For countersink of holes, refer to SRM 51-46-11, Page block 001. (w) General removal/installation procedures for fasteners, refer to SRM 51-42-11. (x) For alternative and substitute fasteners, refer to SRM 51-43-12. (y) Cut the rivets to the necessary length. (z) Torque the standard threaded fasteners, refer to AMM 20-21-11, Page block 201. (aa) For corrosion prevention, refer to SRM 51-22-00. (ab) For coatings application, refer to SRM 51-23-00. (ac) For sealing, refer to SRM 51-24-00. (ad) After drilling/re-working apply wash primer (Mat. No. 16-020), polyurethane primer (Mat. No. 16-001) and polyurethane top coat (Mat. No. 16-002) on affected areas. (ae) General removal/installation procedures for fuel pipes, refer to AMM 28-00-00, Page block 201. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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(af) Before installation, lubricate all O-rings with vaseline (Mat. No. 04-012). (ag) 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. 07-001D). (ah) For electrical bonding of pipes, refer to AMM 20-28-00, Page block 201. (ai) Clean the surfaces at the location of the placards with Dry Cleaning Solvent (Mat. No. 11-002). (aj) For installation of placards, refer to AMM 11-00-00, Page block 201. (ak) Removal/Installation of the insulation blankets, refer to AMM 25-80-00, Page block 201. (al) Removal/Installation of the overhead stowage compartment, refer to AMM 25-24-41, Page block 401. (am) To install new wires, cut them to the necessary length, crimp the terminals and connect them. (an) Route the new wires with the wires that are in the aircraft. (ao) Put blanking caps on the disconnected electrical connectors. (ap) When you will install electrical connectors do a visual check of each connector which was disconnected to make sure that : - the all electrical connectors are serviceable before you connect them again - the label of the connector is the same as the label on the receptacle - the connector is correctly locked with lockwire (Mat. No. 19-009), where locking facilities exists. (aq) After installation or modification of electrical wires do a continuity test, refer to ESPM 20-52-21. (ar) Torque the fasteners of the electrical components, refer to AMM 20-21-15, Page block 201. (as) Obey the instructions for the general wiring installation, refer to ESPM 20-33-00. (at) Install the grounding modules, refer to ESPM 20-44-71. (au) For the cable tie application and tooling, refer to ESPM 20-33-44 and ESPM 20-25-51. (av) Install the connectors, refer to ESPM 20-44-22 and ESPM 20-44-24. (aw) To accomplish this Service Bulletin refer also to the following : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Top Drawing D00071141000, Sheet(s) 01, Issue C Top Drawing D00071141004, Sheet(s) 03, Issue C Top Drawing D00071141008, Sheet(s) 05, Issue E (ax) The drawings/kits listed in Para. 1.J. and Para. 2.C. are not in the sequence of the worksteps. The sequence can be changed by the operator as required. **B. M O** **D I** **F I** **C A**  **T I** **O N**  (1) Config. 01 thru Config. 02 (a) Remove the nets from the AFT cargo compartment. Refer to AMM 25-55-00, Page block 401 Refer to Drawing(s) : D25572624002 Sheet(s) 4 1 Remove these items : 1 net AC40-0217100 Item (000) Discard 1 net AC40-0209500 Item (002) Discard 1 net AC40-0217000 Item W1 1 net AC40-0217500 Item W2 1 net AC40-0209900 Item W3

NOTE : Retain Items W1, W2 and W3. (b) Remove the Tie Down Points (TDPs) from the AFT cargo compartment. Refer to Drawing(s) : D25572624000 Sheet(s) 1 thru 3 1 Remove these items as shown in drawing D25572624000, Sheet 1 Details A thru F : 26 TDP D2557206221800 Item (000) Discard 26 TDP D2557206222000 Item (002) Discard

7 TDP D2557206230000 Item (005) Discard 54 screw NAS1102-3-10 Item (010) Discard 19 screw NAS1102-3-12 Item (011) Discard 73 nut NAS1726-3E Item (013) Discard

1 TDP D2557206226000 Item (017) Discard 1 shim plate D2557214428800 Item (040) Discard 1 shim plate D2557214429000 Item (041) Discard 1 TDP D2557206232400 Item (047) Discard 1 TDP D2557206230200 Item (048) Discard (c) Remove the belly fairing panels 197AB and 198GB. Refer to AMM 53-35-11, Page block 401

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Refer to Drawing(s) : D53475024000 Sheet(s) 1 1 Remove these items : 1 panel 197AB D5347503000000 Item (100) Discard 1 panel 198GB D5347503000000 Item (102) Discard

NOTE : Retain Items A, B and C. (d) Modify the attachment structure of the belly fairing panels 197AB and 198GB. Refer to Kit 281132D04R00 Refer to Drawing(s) : D53475024000 Sheet(s) 1 thru 6 1 Install the brackets as shown in Detail Z1-3, Sections C3-C4 and D3-D4 :

a Put these items in position : 1 bracket D5347542400000 Item 008 2 angle D5347542720000 Item 010 1 bracket D5347542400200 Item 012

b Drill the holes and open the holes to final dimension.

c Install these items : 1 bracket D5347542400000 Item 008 2 angle D5347542720000 Item 010 1 bracket D5347542400200 Item 012 with : 34 rivet LN9198-4009CF Item 240 2 Drill the holes as shown in Details C1-2 and B3-2 :

a Mark the position of the holes at the rib. b Drill the holes with 30.0 mm (1.181 in.) diameter.

c Deburr the holes. 3 Replace nut plates as shown in Section E1-E3 :

a Remove and discard this item : 5 nut NAS1791A3-1 Item (106) Discard

b Install these items : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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3 receptacle ABS0368-01 Item 028 2 nut NAS1791A3-1 Item 030 2 shim D5347521320000 Item 032 with : 10 rivet DIN65399-2400BF Item 125 4 Remove the zed-member as shown in Detail Y1-5

a Remove the fasteners and remove : 1 zed-member D5347518920000 Item (104) Discard 5 Install the receptacles as shown in Details Y1-5, A5-5 and Z5-5

a Mark the positions of the holes. b Drill the five 8.0 mm (0.315 in.) holes.

c Put in position : 5 receptacle ABS0368-01 Item 028

dTransfer drill the rivet holes.

e Install the receptacles, Item 28, with : 10 rivet DIN65399-2400BF Item 125 6 Install the bracket and T-section as shown in Y1-5, And Details D5-5, E5-5 and B5-6

a Put in position 1 T-section D5347521520000 Item 006 1 angle D5347521920000 Item 016

bTransfer drill the rivet holes.

c Install : 1 T-section D5347521520000 Item 006 1 angle D5347521920000 Item 016 with : 19 rivet LN9198-4009CF Item 240 7 Install receptacles and nut plates as shown in Details Y1-5 and B5-6

a Mark the positions of the six holes on the T-section, Item 006. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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b Drill the three 8.0 mm (0.315 in.) and three 6.5 mm (0.256 in.) holes.

c Put in position : 3 receptacle ABS0368-01 Item 028 2 nut NAS1791A3-1 Item 030

dTransfer drill the rivet holes.

e Install the receptacles, Item 28, and the nut plates, Item 30, with : 121 rivet DIN65399-2400BF Item 125 8 Install the bracket as shown in Detail A1-1 and Section F1-F1 on the web at FR50.

a Remove the two affected rivets. b Put in position : 1 bracket D5347521120000 Item 014

c Transfer drill the rivet holes. d Install : 1 bracket D5347521120000 Item 014 with : 2 rivet LN9198-4009CF Item 240 (e) Remove and not reuse the pressure reservoirs for the offwing escape slides, LH/RH. Refer to Drawing(s) : D25690000004 Sheet(s) 7 thru 9 1 Remove and not reuse these items as shown in Sections B7-B8 and A7-A9 : 1 reservoir 60592-101 Item (008) not reuse 1 reservoir 60592-101 Item (009) not reuse 2 screw NAS1096-2-16 Item (010) Discard 10 washer ASNA0113-40ADL Item (012) Discard

2 spacer NSA5527-03-01 Item (014) Discard 2 clamp NAS5516-18NJ Item (018) Discard 8 screw NAS1096-2-10 Item (020) Discard 1 bracket D2567043300000 Item (042) Discard 1 bracket D2567043300100 Item (043) Discard 1 tie NSA935402-51 Item (050) Discard 1 tie NSA935402-51 Item (051) Discard (f) Remove and discard the placards at the AFT cargo compartment lining panels between FR47 and FR48, LH/RH. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Refer to Drawing(s) : D25573522000 Sheet(s) 1 1 Remove and discard this item :

2 placard A2557146821600 Item (518) Discard (g) Modify the insulation blankets. Refer to Kit 281132D71R00 Refer to AMM 25-80-00 Refer to Drawing(s) : D25670762000 Sheet(s) 1 thru 7 D25671745000 Sheet(s) 1 thru 7 1 Remove and retain the insulation blankets in the affected areas. Refer to AMM 25-80-00, Page block 201 2 Install the brackets for relocation of the pressure reservoirs of the offwing escape slides, LH/RH. Refer to Drawing(s) : D25670762000 Sheet(s) 1 thru 7

a Put these items in position, drill the holes and install the brackets as shown in Details Y2-3 and Y5-6 : 2 bracket D2567072701200 Item 006 with : 8 rivet LN9198-4008CF Item 100

b Put these items in position, drill the holes and install the brackets as shown in Details X2-3 and W2-3 : 2 bracket D2567072700400 Item 004 with : 4 rivet LN9198-4008CF Item 100

c Put these items in position, drill the holes and install the brackets as shown in Details X5-6 and W5-6 : 2 bracket D2567072700500 Item 005 with : 4 rivet LN9198-4008CF Item 100 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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d Put these items in position, drill the holes and install the brackets as shown in Details V2-3, V5-6, U2-3, U5-6, T2-3, T5-6 : 6 bracket D2567072700200 Item 002 with : 12 rivet LN9198-4008CF Item 100

e Put these items in position, drill the holes and install the brackets as shown in Details S2-3 and S5-6 : 2 bracket D2567072701000 Item 000 with : 8 rivet LN9198-4008CF Item 100

f Put these items in position, drill the holes and install the brackets as shown in Details A4-4, B4-4 and C4-4 : 3 bracket D2567072700800 Item 008 with : 15 rivet LN9198-4008CF Item 100 g Put these items in position, drill the holes and install the brackets as shown in Details A7-7, B7-7 and C7-7 : 3 bracket D2567072700900 Item 009 with : 15 rivet LN9198-4008CF Item 100 3 Modify and re-identify the insulation blankets after the bracket installation. For re-identification, refer to para. 2.E. 4 Install the retained insulation blankets in the affected areas. Refer to AMM 25-80-00 5 Install the support and the tubes for the pressure reservoir of the offwing escape slide, LH. Refer to Drawing(s) : D25671745000 Sheet(s) 1 thru 7

a Install the support between FR45 and FR47 as shown in Detail Z2-6 : 1 section D2567070600000 Item 010 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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with : 6 screw NAS1096-3-10 Item 080 6 washer NAS1149D0363K Item 110

b Install the tubes as shown in Details Y2-2, X2-2 and Z2-2 : 1 tube D2567070100000 Item 000 1 tube D2567070100200 Item 002 1 cap NAS817-10 Item 070 1 tube 64079-3 Item 595 1 tube 64079-5 Item 597 with : 2 clamp ABS0396C08JA Item 060 1 clamp NSA5515-12 Item 066 5 clamp NAS5515-8 Item 062 9 screw NAS1096-3-10 Item 080 1 screw NAS1096-2-9 Item 082 1 nut MS21042-08 Item 092 9 washer NAS1149D0363K Item 110 1 washer NAS1149DN832K Item 112

c Install the bonding straps as shown in Detail E2-2 and D2-2 : 2 lead E0088-10-80NN Item 050 with : 2 clamp NSA5519-11 Item 064 2 screw NAS1096-2-9 Item 082 2 screw NAS1096-2-7 Item 084 2 nut MS21042-08 Item 092 6 washer NAS1149DN832K Item 112 6 Install the support and the tubes for the pressure reservoir of the offwing escape slide, RH. D25671745000 Sheet(s) 2 thru 7

a Install the support between FR45 and FR47 as shown in Detail Z4-7 : 1 section D2567070600200 Item 012 with : 4 screw NAS1096-3-10 Item 080 2 screw NAS1096-3-12 Item 103 6 washer NAS1149D0363K Item 110

b Install the tubes as shown in Details A4-4 and Z4-4 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 tube D2567070100100 Item 001 1 tube D2567070100300 Item 003 1 cap NAS817-10 Item 070 1 tube 64079-1 Item 596 1 tube 64079-5 Item 597 with : 2 clamp ABS0396C08JA Item 060 5 clamp NAS5515-8 Item 062 9 screw NAS1096-3-10 Item 080 9 washer NAS1149D0363K Item 110

c Install the bonding straps as shown in Details E4-4 and D5-5: 2 lead E0088-10-80NN Item 050 with : 2 clamp NSA5519-11 Item 064 2 screw NAS1096-2-9 Item 082 2 screw NAS1096-2-7 Item 084 2 nut MS21042-08 Item 092 6 washer NAS1149DN832K Item 112 (h) Relocate the release cable for the offwing slide, LH. Refer to Kit 281132D50R01 Refer to Drawing(s) : D53370297002 Sheet(s) 1 thru 12 1 Remove the old release cable for the offwing slide LH between FR40 and FR47 : Refer to Drawing(s) : D53370297002 Sheet(s) 1 thru 12

a Remove these items as shown in Detail Y2-2 : 1 nut NAS1726C4P Item (814) Discard 1 nut NAS509-4C Item (816) Discard 1 flange D5337025520000 Item A 1 bolt NSA5031H4-4 Item C 1 bolt NSA5031-4-4 Item D 1 washer NSA1149C0463R Item E NOTE : Remove and retain the Items A, C, D and E. b Remove these items as shown in Section G2-G3 : 2 washer NAS1149C0332R Item (818) Discard 1 pin MS24665-153 Item (822) Discard 1 bolt D5337048420200 Item B DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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NOTE : Remove and retain the Item B.

c Remove and discard these items as shown in Detail A1-2 : 1 cable L32A319-160-001 Item (800) Discard 12 clamp MS21919WCH6 Item (802) Discard

2 tie NSA935401-03 Item (804) Discard 6 bolt NSA5031-3-5 Item (806) Discard 6 bolt NSA5031-3-4 Item (810) Discard 8 nut NAS1726C3P Item (812) Discard 9 washer NAS1149C0332R Item (818) Discard 1 washer NAS1149C0463R Item (820) Discard 2 Install the brackets for the release cable attachment between FR41 and FR46 : Refer to Drawing(s) : D53370297002 Sheet(s) 1 thru 12

a Put the item in position, drill the rivet holes and install this item as shown in Detail A5-5 : 1 angle D5337025920000 Item 012 with : 2 rivet LN9198-3208BF Item 632

b Put the items in position, drill the rivet holes and install these items as shown in Details B5-5 and C5-5 : 2 profile D5337025620200 Item 008 1 profile D5337025620600 Item 010 with : 4 rivet LN9198-3212BF Item 632

c Put the items in position, drill the rivet holes and install these items as shown in Section D4-D5 and Details E5-5 and F5-5 : 2 angle D5337025020000 Item 006 1 bridge D5337645020000 Item 014 with : 8 rivet LN9198-3210BF Item 632

d Put the item in position, drill the rivet holes and install this item as shown in Detail A6-6 : 1 bracket D5337645300200 Item 016 with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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4 rivet LN9198-3208BF Item 632

e Put the item in position, drill the rivet holes and install this item as shown in Section F4-F6 : 1 holder D5337645420000 Item 018 with : 4 rivet LN9198-3208BF Item 632 3 Install the release cable for the offwing slide LH between FR40 and FR46 : Refer to Drawing(s) : D53370297002 Sheet(s) 1 thru 12

a Install this item as shown in Detail C1-7 : 1 control L32A319-160-002 Item 000 with : 10 clamp MS21919WCH6 Item 030

1 hose DAN79-07 Item 032 2 tie NSA935401-03 Item 034 7 bolt NSA5031-3-5 Item 040 3 bolt NSA5031-3-4 Item 042 10 nut NAS1726C3P Item 064 10 washer NAS1149C0332R Item 070 b Install these items and secure with lockwire (Mat. No. 19-010) as shown in Detail Z7-9 : 1 nut NAS1726C4P Item 060 1 nut NAS509-4C Item 062 1 flange D5337025520000 Item A 1 bolt NSA5031H4-4 Item C 1 bolt NSA50314-4 Item D 1 washer NSA1149C0463R Item E NOTE : The Items A, C, D and E are retained parts.

c Install these items as shown in Section J7-J9 : 3 washer NAS1149C0332R Item 070 1 pin MS24665-153 Item 080 1 bolt D5337048420200 Item B NOTE : The Item B is a retained part. dAdjust the release cable so that the dimension "B" is between 9.8 mm (0.386 in.) and 13.2 mm (0.519 in.) as shown in Detail Z10-10. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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e Install this item as shown in Details V7-10 and Z10-10 : 1 adapter L32A319-165-002 Item 002

f Install a rigging pin with 5.0 mm (0.197 in.) diameter at the lever as shown in drawing D53370297002, Sheet 10, Detail V7-10. gAdjust the length of the adapter, Item 002, and connect the adapter with the lever with these items as shown in Section B10-B10 : 1 pin MS20392-2C19 Item 036 3 washer NAS1149C0332R Item 070 1 pin MS24665-153 Item 080

h Secure the both rod ends and the adjustment nuts of the release cable with lockwire (Mat. No. 19-010) as shown in Details V7-10 and Z7-9 and Section B10-B10. i Remove the rigging pin from the lever. (i) Relocate the release cable for the offwing slide, RH. Refer to Kit 281132D51R01 Refer to Drawing(s) : D53370297003 Sheet(s) 1 thru 12 1 Remove the old release cable for the offwing slide LH between FR40 and FR47 : Refer to Drawing(s) : D53370297003 Sheet(s) 1 thru 12

a Remove these items as shown in Detail Y2-2 : 1 nut NAS1726C4P Item (814) Discard 1 nut NAS509-4C Item (816) Discard 1 flange D5337025520000 Item A 1 bolt NSA5031H4-4 Item C 1 bolt NSA5031-4-4 Item D 1 washer NSA1149C0463R Item E NOTE : Remove and retain the Items A, C, D and E. b Remove these items as shown in Section G2-G3 : 2 washer NAS1149C0332R Item (818) Discard 1 pin MS24665-153 Item (822) Discard 1 bolt D5337048420200 Item B NOTE : Remove and retain the Item B.

c Remove and discard these items as shown in Detail A1-2 : 1 cable L32A319-160-001 Item (800) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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12 clamp MS21919WCH6 Item (802) Discard

2 tie NSA935401-03 Item (804) Discard 6 bolt NSA5031-3-5 Item (806) Discard 6 bolt NSA5031-3-4 Item (810) Discard 8 nut NAS1726C3P Item (812) Discard 9 washer NAS1149C0332R Item (818) Discard 1 washer NAS1149C0463R Item (820) Discard 2 Install the brackets for the release cable attachment between FR41 and FR46 : Refer to Drawing(s) : D53370297002 Sheet(s) 1 thru 12

a Put the item in position, drill the rivet holes and install this item as shown in Detail A5-5 : 1 angle D5337025920000 Item 012 with : 2 rivet LN9198-3208BF Item 632

b Put the items in position, drill the rivet holes and install these items as shown in Details B5-5 and C5-5 : 2 profile D5337025620200 Item 008 1 profile D5337025620600 Item 010 with : 4 rivet LN9198-3212BF Item 632

c Put the items in position, drill the rivet holes and install these items as shown in Section D4-D5 and Details E5-5 and F5-5 : 2 angle D5337025020000 Item 006 1 bridge D5337645020000 Item 014 with : 8 rivet LN9198-3210BF Item 632

d Put the item in position, drill the rivet holes and install this item as shown in Detail A6-6 : 1 bracket D5337645300200 Item 016 with : 4 rivet LN9198-3208BF Item 632

e Put the item in position, drill the rivet holes and install this item as shown in Section F4-F6 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 holder D5337645420000 Item 018 with : 4 rivet LN9198-3208BF Item 632 3 Install the release cable for the offwing slide LH between FR40 and FR46 : Refer to Drawing(s) : D53370297002 Sheet(s) 1 thru 12

a Install this item as shown in Detail C1-7 : 1 control L32A319-160-002 Item 000 with : 10 clamp MS21919WCH6 Item 030

1 hose DAN79-07 Item 032 2 tie NSA935401-03 Item 034 7 bolt NSA5031-3-5 Item 040 3 bolt NSA5031-3-4 Item 042 10 nut NAS1726C3P Item 064 10 washer NAS1149C0332R Item 070 b Install these items and secure with lockwire (Mat. No. 19-010) as shown in Detail Z7-9 : 1 nut NAS1726C4P Item 060 1 nut NAS509-4C Item 062 1 flange D5337025520000 Item A 1 bolt NSA5031H4-4 Item C 1 bolt NSA50314-4 Item D 1 washer NSA1149C0463R Item E NOTE : The Items A, C, D and E are retained parts.

c Install these items as shown in Section J7-J9 : 3 washer NAS1149C0332R Item 070 1 pin MS24665-153 Item 080 1 bolt D5337048420200 Item B NOTE : The Item B is a retained part. dAdjust the release cable so that the dimension "B" is between 9.8 mm (0.386 in.) and 13.2 mm (0.519 in.) as shown in Detail Z10-10.

e Install this item as shown in Details V7-10 and Z10-10 : 1 adapter L32A319-165-002 Item 002

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f Install a rigging pin with 5.0 mm (0.197 in.) diameter at the lever as shown in drawing D53370297002, Sheet 10, Detail V7-10. gAdjust the length of the adapter, Item 002, and connect the adapter with the lever with these items as shown in Section B10-B10 : 1 pin MS20392-2C19 Item 036 3 washer NAS1149C0332R Item 070 1 pin MS24665-153 Item 080

h Secure the both rod ends and the adjustment nuts of the release cable with lockwire (Mat. No. 19-010) as shown in Details V7-10 and Z7-9 and Section B10-B10. i Remove the rigging pin from the lever. (j) Install the pressure reservoir of the offwing escape slide LH/RH. Refer to Kit 281132D71R00 Refer to Drawing(s) : D25671746000 Sheet(s) 1 thru 4 1 Install the pressure reservoir of the offwing escape slide, LH between FR45 and FR47. Refer to Drawing(s) : D25671746000 Sheet(s) 1 thru 4

a Install : 1 reservoir 60592-103 Item 594 with : 1 pocket D2567043200000 Item 050 1 clamp ASNA0033-172 Item 060 1 section LN29837A1 Item 070 2 screw NAS1096-3-7 Item 080 2 washer NAS1149D0363K Item 090 1 placard D9239310903000 Item 100 1 pin MS20392-2C15 Item 110 3 washer NAS1149C0332R Item 120 1 cotter pin MS24665-1013 Item 130 1 placard D2567074100600 Item 140 NOTE : Cut the section, Item 070, in two pieces. One part for the left hand side and the other part for the right hand side. 2 Install the pressure reservoir of the offwing escape slide, RH between FR45 and FR47. Refer to Drawing(s) : D25671746000 Sheet(s) 1, 2 and 4 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 154 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Install : 1 reservoir 60592-103 Item 0598 with : 1 pocket D2567043200000 Item 050 1 clamp ASNA0033-172 Item 060 1 section LN29837A1 Item 070 2 screw NAS1096-3-7 Item 080 2 washer NAS1149D0363K Item 090 1 placard D9239310903000 Item 100 1 pin MS20392-2C15 Item 110 3 washer NAS1149C0332R Item 120 1 cotter pin MS24665-1013 Item 130 1 placard D2567074100600 Item 140 (k) Install a bracket at the passenger compartment floor structure at FR53. Refer to Kit 281132D12R00 Refer to Drawing(s) : D53472833008 Sheet(s) 4 1 Put the bracket, Item 000, in position as shown in Detail Z4-4. 2Transfer drill the hole and open it to final dimension. 3 Install this item : 1 bracket D5347212320000 Item 000

with : 1 retaining pin D5347212420000 Item 002 4 retaining ring D5347212420200 Item 004 (l) Install the additional angles at the webs of the keel beam structure between FR42 and FR46. Refer to Kit 281132D07R00 Refer to Drawing(s) : D53370780004 Sheet(s) 2 1 Install angles at webs of keel beam structure as shown in Section A2-A2 and Detail E2-2 ’AFTER MODIFICATION’.

a Put these items in position : 1 angle D5337270100000 Item 030 1 angle D5337270100800 Item 038

bTransfer drill the holes and open the holes to final dimension. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 155 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

c Install these items : 1 angle D5337270100000 Item 030 1 angle D5337270100800 Item 038 with : 4 bolt ASNA0082-204 Item 264 2 Install the angles at the webs of keel beam structure as shown in Section B2-B2 and Detail Y2-2 ’AFTER MODIFICATION’.

aTransfer drill the holes and open the holes to final dimension. b Put these items in position : 1 angle D5337070100200 Item 032 1 angle D5337270100400 Item 034 1 angle D5337070100600 Item 036 1 angle D5337070101000 Item 040

c Drill the holes and open the holes to final dimension. d Install these items : 1 angle D5337070100200 Item 032 1 angle D5337270100400 Item 034 1 angle D5337070100600 Item 036 1 angle D5337070101000 Item 040 with : 8 bolt ASNA0082-203 Item 263 (m) Replace the fasteners between FR42 and FR44, LH/RH. Refer to Kit 281132D62R00 Refer to Kit 281132D63R00 Refer to Drawing(s) : D53371237000 Sheet(s) 1 D53371237001 Sheet(s) 1 1 Replace the fasteners between FR42 and FR44, LH. Refer to Kit 281132D62R00 Refer to Drawing(s) : D53371237000 Sheet(s) 1

a Remove the affected fasteners as shown in Detail Z1-1. bOpen the holes to final dimension.

c Install these items : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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20 pin DAN7-6-8X Item 001 32 pin DAN7-8-8X Item 002 12 pin DAN7-8-10X Item 003

1 pin DAN8-8-8X Item 004 20 collar DAN12-6X Item 005 45 collar DAN12-8X Item 006 2 Replace the fasteners between FR42 and FR44, RH. Refer to Kit 281132D63R00 Refer to Drawing(s) : D53371237001 Sheet(s) 1

a Remove the affected fasteners as shown in Detail Z1-1. bOpen the holes to final dimension.

c Install these items : 20 pin DAN7-6-8X Item 001 32 pin DAN7-8-8X Item 002 12 pin DAN7-8-10X Item 003

1 pin DAN8-8-8X Item 004 20 collar DAN12-6X Item 005 45 collar DAN12-8X Item 006 (n) Remove and discard the attachment structure of the partition panels 151AW, 151BW and 152BW between FR46 and FR47. Refer to Kit 281132D36R02 Refer to Drawing(s) : D53975019000 Sheet(s) 1 thru 3 1 Remove and discard these items as shown in Section B1-B2 : 1 section D5397468100000 Item (201) Discard 1 section D5397467400200 Item (202) Discard 1 section D5397467400300 Item (203) Discard 2 section D5397468900400 Item (208) Discard 1 section D5397467900600 Item (220) Discard 1 section D5397467900400 Item (222) Discard 1 section D5397474700000 Item (233) Discard 1 section D5397474900000 Item (334) Discard 1 section D5397467800600 Item (238) Discard 1 section D5397467800700 Item (239) Discard 14 bracket D5397489820000 Item (270) Discard

2 bracket D5397489820200 Item (272) Discard 4 bracket D5397489820400 Item (274) Discard 2 bracket D5397489820600 Item (276) Discard 2 Remove and discard these items as shown in drawing D53975019000, Sheet 1 : 1 plate D5397480620000 Item (200) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 plate D5397483921200 Item (204) Discard 1 section D5347047400200 Item (230) Discard 1 section D5347047400300 Item (231) Discard 3Close the two existing holes at AD/FR47 with these items as shown in D53975019000, Sheet 1: 2 rivet NAS1097AD4-10 Item 532 (o) Modify the structure. Refer to Kit 281132D61R00 Refer to Drawing(s) : D53371046000 Sheet(s) 1 thru 5 1 Replace the fasteners between FR44 and FR46 between +Y765 to +Y1292 and -Y765 to -Y1292. Refer to Drawing(s) : D53371046000 Sheet(s) 1 thru 5

a Remove the existing rivets, drill the holes to final dimension and install these items as shown in drawing D53371046000, Sheet 1 : 20 pin DAN5-6-6 Item 023

4 pin DAN5-6-7 Item 024 24 collar NSA5076-6 Item 027 196 rivet LN9198-4812CF Item 029 8 rivet LN9198-4814CF Item 030 2 Install the bonding brackets between FR42 and FR43 and between +Y254 and +Y765.

a Put this item in position as shown in drawing D53371046000, Sheet 1, Section K1-K1 : 2 angle A9249175120000 Item 001

b Drill the additional holes, open the holes to final dimension and install this item : 2 angle A9249175120000 Item 001 with : 12 rivet LN9198-3208BF Item 028 3 Drill the hole between FR42 and FR43 for fuel/vent system.

a Drill one hole with 19.1 mm to 19.3 mm (0.752 in. to 0.759 in.) diameter as shown in drawing D53371046000, Sheet 1, Section H1-H1. b Deburr the hole. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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4 Install the girder plate at FR42. Refer to Drawing(s) : D53371046000 Sheet(s) 1 thru 5

a Put this item in position as shown in Section B1-B2 : 1 plate D5337312600000 Item 002

b Mark and drill the holes for the bolts.

c Install this item : 1 plate D5337312600000 Item 002 with : 2 strap D5337312420000 Item 004 4 bolt NAS6703U7 Item 005 4 bolt NAS6703U5 Item 006 8 nut NAS1726C3P Item 007 8 washer NAS1149C0332R Item 008 5 Install the girder plate at FR43. Refer to Drawing(s) : D53371046000 Sheet(s) 1 thru 5

a Put this item in position as shown in Section D1-D3 : 1 plate D5337312000000 Item 003

b Mark and drill the holes for the bolts.

c Install this item : 1 plate D5337312000000 Item 003 with : 2 strap D5337312420000 Item 004 4 bolt NAS6703U7 Item 005 4 bolt NAS6703U5 Item 006 8 nut NAS1726C3P Item 007 8 washer NAS1149C0332R Item 008 6 Remove the shear plate at FR46 between +Y254 and -Y254. Refer to Drawing(s) : D53371046000 Sheet(s) 1 thru 5

a Remove and discard this item as shown in Section E1-E4 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 shear plate D5337105820000 Item (034) Discard 7 Install the girder plate at FR46. Refer to drawings : D53371046000 Sheet(s) 1 thru 5 D53372362004 Sheet(s) 6

a Put this item in position as shown in drawing D53371046000, Sheet 5, Section F1-F5 : 1 plate D5337107420200 Item 009

bTransfer drill the holes to the plate, Item 009, and open the holes to final dimension.

c Install this item as shown in drawing D53371046000, Sheet 5, Sections F1-F5 and C5-C5 : 1 plate D5337107420200 Item 009 with : 2 pin DAN6-6-4 Item 021 4 pin DAN5-6-4 Item 022 6 collar NSA5075-6 Item 025 8 rivet LN9198-4012CF Item 035 10 pin DAN5-5-7 Item 036

8 pin DAN5-5-6 Item 037 12 collar NSA5075-5 Item 038

6 collar NSA5076-5 Item 039

d Put these items in position as shown in drawing D53371046000, Sheet 5, Sections F1-F5, B5-B5 and Detail A5-5 : 1 wall D5337311520200 Item 010 1 plate D5337311920200 Item 011 2 angle D5337309820000 Item 012 2 stiffener D5337307220100 Item 013 1 stiffener D5337307220000 Item 014 1 profile D5337312120400 Item 015 1 profile D5337312120600 Item 016 1 profile D5337312120700 Item 017 1 profile D5337312120200 Item 018

eTransfer drill the holes, drill the additional holes, open all holes to final dimension and install with these items as shown in drawing D53371046000, Sheet 5, Sections F1-F5, B5-B5 and A5-A5 and Detail A5-5 : 15 rivet LN9198-4009CF Item 031

3 rivet LN9198-4010CF Item 032 10 rivet LN9198-4011CF Item 033 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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and with these items as shown in drawing D53372362004, Sheet 6, Details C1-6 and A6-6 : 12 bolt ASNA0082A302 Item 435

2 bolt ASNA0082A303 Item 436 4 bolt ASNA0082A304 Item 438 15 bolt ASNA0082A305 Item 440

1 bolt ASNA0082A306 Item 442 12 collar NSA5075-5 Item 804

3 pin DAN7-5-5 Item 955 9 pin DAN7-5-6 Item 956

f Put this item at the wall, Item 010, in position as shown in drawing D53371046000, Sheet 5, Sections F1-F5 : 1 profile D5337313420000 Item 019

g Drill the holes, open the holes to final dimension and install with these items : 3 pin DAN7-5A5 Item 020 3 collar ABS0258-5C Item 026 (p) Replace fasteners at FR48, FR49, FR50 and FR51 between STGR34LH and STGR36LH. Refer to Kit 281132D41R00 Refer to Drawing(s) : D53470095002 Sheet(s) 1 1 Replace the fasteners at FR48 between STGR34LH and STGR36LH as shown in Section A1-A1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining pins, Item 865 and collars, Item 806, will be installed during the installation of the reinforcing straps at FR48. 2 Replace the fasteners at FR49 between STGR34LH and STGR36LH as shown in Section A1-A1.

a Remove the existing fasteners in the affected area. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining pins, Item 865 and collars, Item 806, will be installed during the installation of the reinforcing straps at FR49. 3 Replace the fasteners at FR50 between STGR34LH and STGR36LH as shown in Section A1-A1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining pins, Item 865 and collars, Item 806, will be installed during the installation of the reinforcing straps at FR50. 4 Replace the fasteners at FR51 between STGR34LH and STGR36LH as shown in Section A1-A1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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NOTE : The remaining pins, Item 865 and collars, Item 806, will be installed during the installation of the reinforcing straps at FR51. (q) Replace fasteners at FR52, FR53 and FR54 between STGR34LH and STGR36LH. Refer to Drawing(s) : Refer to Kit 281132D08R00 D53470096002 Sheet(s) 1 1 Replace the fasteners at FR52 between STGR34LH and STGR36LH as shown in Section A1-A1 and Detail A1-1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR52. 2 Replace the fasteners at FR53 between STGR34LH and STGR36LH as shown in Section A1-A1 and Detail A1-1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR53. 3 Replace the fasteners at FR54 between STGR34LH and STGR36LH as shown in Section A1-A1 and Detail A1-1.

a Remove the existing fasteners in the affected area. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR54. (r) Install Longitudinal profiles at the cargo compartment floor structure between FR53 an FR59. Refer to Kit 281132D09R00 Refer to Drawing(s) : D53474078000 Sheet(s) 1 D53474078002 Sheet(s) 1 1 Put in position as shown in Detail A1-1 and Sections A1-A1, B1-B1 and C1-C1 : 1 profile D5347456000000 Item 000 1 profile D5347456100000 Item 002 3 profile D5347434000800 Item 004 1 profile D5347434000600 Item 006 2 strap D5347448620200 Item 008 2Transfer drill the fastener holes and open to final dimension. 3 Install as shown in Detail A1-1 and Sections A1-A1, B1-B1 and C1-C1 : 1 profile D5347456000000 Item 000 1 profile D5347456100000 Item 002 3 profile D5347434000800 Item 004 1 profile D5347434000600 Item 006 2 strap D5347448620200 Item 008

with : 20 bolt NSA5031-3-3 Item 530 20 nut NAS1726C3P Item 532

4 bolt NSA5031-4-5 Item 534 4 nut NAS1726C4P Item 536 12 collar NSA5075-6 Item 806

8 pin DAN5-6-3 Item 963 4 pin DAN5-6-5 Item 965 (s) Measure the level of the AFT cargo compartment floor structure. Refer to Kit 281132D24R01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Refer to Drawing(s) : D25572624008 Sheet(s) 8 thru 16 D25573525000 Sheet(s) 1 thru 4 1 Temporarily install the roller tracks between FR47 and FR54 : NOTE : Attach the roller tracks only at the frames. 1 track D2557224600200 Item 000 1 track D2557224600400 Item 001 1 track D2557224600000 Item 002

with : 56 screw NAS1102-3-7 Item 026 56 screw NAS1102-3-10 Item 027 448 nut NAS1726-3E Item 028

63 screw NAS1102-3-9 Item 032

7 screw NAS1102-3-11 Item 050 35 screw NAS1100-3-9 Item 053

6 screw NAS1100-3-11 Item 054 1 screw NAS1100-3-6 Item 055 1 washer NAS1149C0332R Item 056 170 screw NAS1100-3-7 Item 057 2 Do the leveling of the roller tracks between FR47 and FR54 to get the necessary shim thicknesses, refer to drawing D25573525000 Sheet(s) 1 thru 4. 3 Remove and retain the roller tracks and fastening parts between FR47 and FR54. (t) Install the water drain connection and the cavity drain access cover between FR52 and FR53. Refer to Drawing(s) : D53470076004 Sheet(s) 8 and 10 D53470076008 Sheet(s) 18 and 20 1 Make a cutout between 63.7 mm (2.508 in.) and 64.3 mm (2.531 in.) diameter in the skin panel between FR52 and FR53 and between STGR42LH and STGR43LH as shown in Details B10-10 and Y10-10. 2 Install the doubler at the outer skin as shown in Section B8-B10 and Detail B10-10 : CAUTION : REMOVE THE EXISTING RIVETS CAREFULLY. THE HEADS OF THE RIVETS WILL BE USED DURING THE DOUBLER INSTALLATION FOR THE EXISTING COUNTERSINKS IN THE SKIN PANEL.

a Remove the existing fasteners in the affected area. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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b Put this item in position as shown in Section B8-B10 : 1 doubler D5347646321000 Item 162

c Transfer drill the holes. d Drill the additional holes as shown in Detail B10-10 and open all holes to final dimension.

e Install this item : 1 doubler D5347646321000 Item 162 with : 50 rivet MBBN4477-4810 Item 549

8 pin DAN6-6-7Y Item 677 8 collar NSA5330-6 Item 803 156 collar NSA5075-6 Item 806

25 pin DAN6-6-5 Item 865 58 pin DAN6-6-6 Item 866 14 pin DAN6-6-7 Item 867 59 pin DAN6-6-8 Item 868 3 Install the tube as shown in Section B8-B10 and Details B10-10 and Y10-10 :

a Put these items in position : 1 tube D5347669000000 Item 172 2 shim D5347472120400 Item 180 1 shim D5347660220200 Item 182

bTransfer drill the holes, drill the additional holes and open the holes to final dimension as shown in Detail Y10-10.

c Install these items : 1 tube D5347669000000 Item 172 2 shim D5347472120400 Item 180 1 shim D5347660220200 Item 182 with : 16 collar NSA5075-6 Item 806

2 pin DAN6-6-7 Item 867 14 pin DAN6-6-10 Item 870 d Drill the four holes for the receptacles, Item 504, with 5.6 mm (0.220 in.) diameter as shown in Detail Y10-10 and install this item : 4 receptacle ABS0337-01A Item 504 with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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8 rivet DIN65399-2400CF Item 724

e Install these items at the tube, Item 172, as shown in Section B8-B10 : 1 plate D5347669200000 Item 166 1 plug D5347669100000 Item 174 1 ring MS16625-4212 Item 500 1 screw NAS1096-3-10 Item 506 4 Make a cutout in the skin panel between FR52 and FR53 and between STGR40LH and STGR41LH as shown in Detail B10-10. 5 Install the nuts, Item 510, around the cutout as shown in Detail Z10-10 :

a Remove the six rivets in the stringer and open the holes to 5.6 mm (0.220 in.) diameter. b Drill the four holes with 5.6 mm (0.220 in.) diameter in the skin.

c Install these items : 4 shim D5347470220000 Item 178 10 nut NAS1474A3 Item 510 with : 20 rivet DIN65399-2400CF Item 724 d Install this item as shown in Section B8-B10 : 1 cover D5347470920200 Item 164 with : 10 screw NAS1153E7 Item 502 (u) Install the shims on the floor framework of the AFT cargo compartment between FR47 and FR54. Refer to Kit 281132D22R00 Refer to Drawing(s) : D25572624006 Sheet(s) 7 1 Put these items in position as required as shown in drawing D25572624006, Sheet 7 : NOTE : The quantity of the shims at each position is dependent on the roller track measurement between FR47 and FR54. 36 shim D2557214631800 Item 014 12 shim D2557214632000 Item 015

9 shim D2557214633400 Item 034 6 shim D2557214633600 Item 036 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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45 shim D2557214635000 Item 050

7 shim D2557214635200 Item 052 3 shim D2557214635800 Item 058 1 shim D2557214636000 Item 060 6 shim D2557214637600 Item 076 2 shim D2557214637800 Item 078 18 shim D2557214638000 Item 080

6 shim D2557214638200 Item 082 3 shim D2557214638400 Item 084 1 shim D2557214638600 Item 086 18 shim D2557214638800 Item 088

3 shim D2557214639000 Item 090 1 shim D2557214639200 Item 092 1 shim D2557214639400 Item 094 9 shim D2557214639600 Item 096 3 shim D2557214639800 Item 098 18 shim D2557214640000 Item 100

4 shim D2557214640200 Item 102 3 TDP D2557214629800 Item 104 3 shim D2557214642000 Item 106 1 shim D2557214642200 Item 108 3 shim D2557214642400 Item 110 1 shim D2557214642600 Item 112 3 shim D2557214642800 Item 114 1 shim D2557214643000 Item 116 3 shim D2557214641200 Item 118 1 shim D2557214641400 Item 120 3 shim D2557214646000 Item 122 1 shim D2557214646200 Item 124 5 shim D2557214643600 Item 126 3 shim D2557214643800 Item 128 1 shim D2557214644400 Item 130 1 shim D2557214644500 Item 132 6 screw NAS1102-3-10 Item 134 1 shim D2557214644600 Item 136 (v) Install the roller tracks between FR47 and FR54 in the AFT cargo compartment. Refer to Kit 281132D20R02 Refer to Kit 281132D24R01 1 Remove the bearing supports and close the holes. Refer to Drawing(s) : D25572624000 Sheet(s) 1

a Remove the two bearing supports as shown in drawing D25572624000, Sheet 1, View Y and View Z : 2 bearing support D2557226520000 Item (57) 4 rivet EN6080AD5-08 Item 060 2 Protect the attachment elements of the roller tracks between FR47 and FR54. Refer to Drawing(s) : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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D25572624012 Sheet(s) 19 3 Install the track between FR47 and FR54 at the Aircraft Datum (AD). Refer to Drawing(s) : D25572624008 Sheet(s) 8 thru 16

a Put these items in position as shown in drawing D25572624008, Sheet 8, Sheet 9 Detail Z8-9 and Sheet 15, Detail L8-15 and Detail X : 1 track D2557224600200 Item 000 2 shim D2557268030600 Item 069 2 bearing support D2557226520400 Item 070 2 block D2557226120200 Item 071 NOTE : For the alignment connect the bearing supports, Item 070, and the track, Item 000, with rigging pins temporarily. bTransfer drill the holes to the brackets, Item 070.

c Drill the additional holes. d Install these items as shown in View L8-15 : 2 shim D2557268030600 Item 069 2 bearing support D2557226520400 Item 070 with : 8 pin DAN7-5-5 Item 041 4 pin DAN7-5-6 Item 042 12 collar DAN12-5 Item 043

eTransfer drill the holes from the track, Item 000. f Install this item with sealant (Mat. No. 09-005) as shown in Detail Z8-9 : 1 track D2557224600200 Item 000 1 bracket D2557268121200 Item 003 1 shim D2557214640800 Item 004 1 shim D2557214640400 Item 005 1 bracket D2557268122800 Item 006 1 doubler D2557268121000 Item 009 1 plate D2557268028600 Item 010 with : 69 screw NAS1102-3-7 Item 026 16 screw NAS1102-3-10 Item 027 162 nut NAS1726-3E Item 028

51 screw NAS1102-3-9 Item 032 12 screw NAS1100-3-9 Item 053

4 screw NAS1100-3-11 Item 054 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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10 screw NAS1100-3-7 Item 057 NOTE : Dependent on the thickness of the shims it could be necessary to install alternative bolts as shown in the table, refer to drawing D25572624008, Sheet 9. g Remove the rigging pins and connect the bearing supports, Item 070, and the track, Item 000, with these items as shown in drawing D25572624008, Sheet 15, Detail X : 2 bolt NSA5042C05-180 Item 036 2 nut NSA5060-4 Item 037 2 washer NAS1149C0432R Item 038 2 washer NAS1149C0532R Item 039 2 pin MS24665-153 Item 040 4 Install the track between FR47 and FR54 at +Y623. Refer to Drawing(s) : D25572624008 Sheet(s) 8, 11 and 15

a Put these items in position as shown in drawing D25572624008, Sheet 8, Sheet 11, Detail Y9-11 and Sheet 15, Detail L8-15 and Detail X : 1 track D2557224600000 Item 002 2 shim D2557268030600 Item 069 2 bearing support D2557226520400 Item 070 2 block D2557226120200 Item 071 NOTE : For the alignment connect the bearing supports, Item 070, and the track, Item 002, with rigging pins temporarily. bTransfer drill the holes to the bearing supports, Item 070.

c Drill the additional holes. d Install these items as shown in View L8-15 : 2 shim D2557268030600 Item 069 2 bearing support D2557226520400 Item 070 with : 8 pin DAN7-5-5 Item 041 4 pin DAN7-5-6 Item 042 12 collar DAN12-5 Item 043

eTransfer drill the holes from the track, Item 002. f Install this item with sealant (Mat. No. 09-005) as shown in Detail -Y8-11 : 1 track D2557224600000 Item 002 1 bracket D2557268121200 Item 003 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 bracket D2557214641000 Item 008 with : 12 screw NAS1102-3-10 Item 027 149 nut NAS1726-3E Item 028

18 screw NAS1102-3-9 Item 032

5 screw NAS1102-3-11 Item 050 20 screw NAS1100-3-9 Item 053

4 screw NAS1100-3-11 Item 054 90 screw NAS1100-3-7 Item 057 NOTE : Dependent on the thickness of the shims it could be necessary to install alternative bolts as shown in the table, refer to drawing D25572624008, Sheet 11. g Remove the rigging pins and connect the bearing supports, Item 070, and the track, Item 002, with these items as shown in drawing D25572624008, Sheet 15, Detail X : 2 bolt NSA5042C05-180 Item 036 2 nut NSA5060-4 Item 037 2 washer NAS1149C0432R Item 038 2 washer NAS1149C0532R Item 039 2 pin MS24665-153 Item 040 5 Install the track between FR47 and FR52A at -Y623. Refer to Drawing(s) : D25572624008 Sheet(s) 10 and 13

a Put these items in position as shown in drawing D25572624008, Sheet 8, Sheet 10, Detail X8-10 and Sheet 15, Detail L8-15 and Detail X : 1 track D2557224600400 Item 001 2 shim D2557268030600 Item 069 2 bearing support D2557226520400 Item 070 2 block D2557226120200 Item 071 NOTE : For the alignment connect the bearing supports, Item 070, and the track, Item 001, with rigging pins temporarily. bTransfer drill the holes to the bearing supports, Item 070.

c Drill the additional holes. d Install these items as shown in View L8-15 : 2 shim D2557268030600 Item 069 2 bearing support D2557226520400 Item 070 with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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8 pin DAN7-5-5 Item 041 4 pin DAN7-5-6 Item 042 12 collar DAN12-5 Item 043

eTransfer drill the holes from the track, Item 001. f Install this item with sealant (Mat. No. 09-005) as shown in Detail X8-10 : 1 track D2557224600400 Item 001 with : 10 screw NAS1102-3-10 Item 027 104 nut NAS1726-3E Item 028 6 screw NAS1102-3-9 Item 032 3 screw NAS1102-3-11 Item 050 15 screw NAS1100-3-9 Item 053

1 screw NAS1100-3-6 Item 055 1 washer NAS1149C0332R Item 056 2 screw NAS1100-3-11 Item 054 68 screw NAS1100-3-7 Item 057 NOTE : Dependent on the thickness of the shims it could be necessary to install alternative bolts as shown in the table, refer to drawing D25572631008, Sheet 10. g Remove the rigging pins and connect the bearing supports, Item 070, and the track, Item 001, with these items as shown in drawing D25572624008, Sheet 15, Detail X : 2 bolt NSA5042C05-180 Item 036 2 nut NSA5060-4 Item 037 2 washer NAS1149C0432R Item 038 2 washer NAS1149C0532R Item 039 2 pin MS24665-153 Item 040 6 Install the support for the XZ-latch between FR52A and FR53 at -Y623. Refer to Drawing(s) : D25572624008 Sheet(s) 16

a Put these items in position as shown in drawing D25572624008, Sheet 16 : 1 support D2557240102000 Item 080 with : 2 bolt MS21250-04030 Item 086 2 nut NAS1726-4E Item 087 2 washer NAS1149F0432P Item 088

bAdjust the support, Item 80. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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c Transfer drill eight holes an open to final diameter of 7.0 mm (0.276 in.). d Drill two holes to a final diameter between 7.900 mm (0.3110 in.) and 7.922 mm (0.3119 in.).

e Before final installation of the support, Item 80, install : 2 screw NAS1102-08-10 Item 091 2 nut NAS1726-05E Item 092 and smooth mounting surface with sealant (Mat. No. 09-013). f Install as shown in drawing D25572624008, Sheet 16 : 1 support D2557240102000 Item 080 with : 2 bolt D2557237320600 Item 013 2 washer NAS1149C0563R Item 014 2 pin MS24665-300 Item 015 2 screw NAS1100-3-12 Item 029 2 screw NAS1100-3-12 Item 046 5 plate D2557268122200 Item 081 NOTE 01 1 plate D2557268122400 Item 082 2 bolt MS21250-04012 Item 083 1 bolt MS21250-04024 Item 084 3 bolt MS21250-04026 Item 085 3 bolt MS21250-04030 Item 086 9 nut NAS1726-4E Item 087 9 washer NAS1149F0432P Item 088 1 bolt MS21250-04028 Item 089 1 nut MS21250-04028 Item 090 1 end stop D2557240021400 Item 094 NOTE 02 3 bolt MS21250-06018 Item 095 NOTE 02 3 washer NSA5379-6C Item 096 NOTE 02 1 bolt NAS1304-10 Item 097 NOTE 02 1 washer NAS1149F0432P Item 098 NOTE 02 NOTE(01) QTY as required. See adjustment of the XZ-latch. NOTE(02) Final installation after installation of ACTs. NOTE : For installation of adapter plates and adjustment of the XZ-latch. (w) Install/Adjust the YZ-latches at FR47, FR48 and FR49 and adjust the XZ-latches. Refer to Kit 281132D24R01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Refer to Drawing(s) : D25572624008 Sheet(s) 8 thru 16 1 Remove and retain the XZ-latch pawls at FR50 and FR53 and retain the nine fastening bolts. NOTE : Tag the XZ-latches with their installation position. 2 Put the tool 98D28108641000 in position between FR47 and FR50 as shown in drawing D25572624008, Sheet 12 and 14. 3Temporarily put these items in position at FR47, FR48 and FR49 as shown in drawing D25572624008, Sheet 14, Detail T8-14 and Sections A-A and D8-D14 : 6 YZ-latch D2557238000400 Item 078

with : 36 nut NAS1726-3E Item 028 12 bolt MS21250-03006 Item 048 36 bolt MS21250-03006 Item 049 4Temporarily install the retained XZ-latch pawls with the retained nine fastening bolts at FR50. NOTE : Install the XZ-latch pawls in the tagged installation position. 5 Ensure that the tool 98D28108641000 has full contact with the rollers of the roller tracks. 6Adjust the X-gaps with the adjustment screws at FR47 as shown in drawing D25572624008, Sheet 12 :

aAdjust the X-gaps with the adjustment screws between 0.65 mm (0.026 in.) and 1.65 mm (0.065 in.) at three places. b Secure the adjustment screws with lockwire (Mat. No. 19-010). 7Adjust the Z-gaps between the tool 98D28108641000 and the YZ-latches at FR47, FR48 and FR49LH/RH as shown in drawing D25572624008, Sheet 14 :

a Measure the Z-gap at FR47, FR48 and FR49 . b If the gaps are not between 2 mm (0.078 in.) and 4 mm (0.157 in.), install shims under the affected YZ-latches.

c If are the gaps correct, finally install the YZ-latches. 8Adjust the Y-gaps between the tool 98D28108641000 and the YZ-latches at FR47, FR48 and FR49 as shown in drawing D25572624008, Sheet 14 :

a Measure the Y-gap at FR47, FR48 and FR49. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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b If the gaps are not between 0.5 mm (0.019 in.) and 1.5 mm (0.059 in.), remove the plate at the affected YZ-latches and adjust the Y-gap with the eccentric bolt as shown in drawing D25572624008, Sheet 14. 9Adjust the X-gaps at FR50 as shown in drawing D25572624008, Sheet 13 :

a Move the tool 98D28108641000 in FWD direction until the tool has contact with the three adjustment screws of the XZ-latches at FR47. bTemporarily install the retained XZ-latch pawls at FR50 with the retained fastening parts. NOTE : Install the YZ-latches in the tagged installation position.

c Adjust the X-gaps between the tool 98D28108641000 and the XZ-latches at FR50 to between 1.3 mm (0.051 in.) and 3.3 mm (0.130 in.) at three places. - Install two adapter plates at each of the XZ-latches at FR50 as necessary to reach the required x-gaps. adapter plate D2557268123000 Item 099 adapter plate D2557268123200 Item 100 adapter plate D2557268123400 Item 101 adapter plate D2557268123600 Item 102 adapter plate D2557268123800 Item 103 adapter plate D2557268124000 Item 104 adapter plate D2557268124200 Item 105 adapter plate D2557268124400 Item 106 adapter plate D2557268124600 Item 107 adapter plate D2557268124800 Item 108 adapter plate D2557268125000 Item 109 with : 4 screw NAS1102-3-8 Item 58 10Remove and retain the XZ-latches at FR50 and retain the fastening parts. NOTE : Tag the YZ-latches with their installation position. NOTE : The adapter plates must be remain in their installation position . (x) Install/Adjust the YZ-latches at FR50, FR51 and FR52 and adjust the XZ-latches. Refer to Drawing(s) : D25572624008 Sheet(s) 12 thru 14 1 Put the tool 98D28108641000 in position between FR50 and FR53 as shown in drawing D25572624008, Sheet 12 and 14. 2Temporarily put these items in position at FR50, FR51 and FR52 as shown in drawing D25572624008, Sheet 14, Detail T8-14 and Sections A-A and D8-D14 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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6 YZ-latch D2557238000400 Item 078

with : 36 nut NAS1726-3E Item 028 12 bolt MS21250-03006 Item 048 36 bolt MS21250-03006 Item 049 3Temporarily install the retained XZ-latch pawls with the retained nine fastening bolts at FR50. NOTE : Install the YZ-latche pawls in the tagged installation position. 4Temporarily install the retained XZ-latch pawls with the retained ten fastening bolts at FR53. NOTE : Install the YZ-latche pawls in the tagged installation position. 5 Ensure that the tool 98D28108641000 has full contact with the rollers of the roller tracks. 6Adjust the Z-gaps between the tool 98D28108641000 and the YZ-latches at FR50, FR51 and FR52, LH/RH as shown in drawing D25572624008, Sheet 14 :

a Measure the Z-gap at FR50, FR51 and FR52. b If the gaps are not between 2 mm (0.078 in.) and 4 mm (0.157 in.), install shims under the affected YZ-latches.

c If are the gaps correct, finally install the YZ-latches. 7Adjust the Z-gap between the tool 98D28108641000 and the XZ-latch at FR53, RH (door area) as shown in drawing D25572624008, Sheet 13 :

a Measure the Z-gap at the XZ-latch pawl at FR53, RH (door area). b If the gap is not between 0.5 mm (0.20 in.) and 2.5 mm (0.098 in.), install shims under the affected XZ-latch. 8Adjust the Y-gaps between the tool 98D28108641000 and the YZ-latches at FR50, FR51 and FR52 as shown in drawing D25572624008, Sheet 14 :

a Measure the Y-gap at FR50, FR51 and FR52. b If the gaps are not between 0.5 mm (0.019 in.) and 1.5 mm (0.059 in.), remove the plate at the affected YZ-latches and adjust the Y-gap with the eccentric bolt as shown in drawing D25572624008, Sheet 14. 9Adjust the X-gaps at FR53 as shown in drawing D25572624008, Sheet 13 :

a Move the tool 98D28108641000 in FWD direction until the tool has contact with the three XZ-latch pawls at FR50. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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bAdjust the X-gaps between the tool 98D28108641000 and the XZ-latches at FR53 to between 1.3 mm (0.051 in.) and 3.3 mm (0.130 in.) at three places. - Install two adapter plates at each of the XZ-latches at FR53 at AD and +Y623 and one adaptor plate in the door area -Y623 as necessary to reach the required x-gaps. NOTE : Rework the stopper plate of the X-latch at FR53 at -Y623 for clearance in X-direction, adapter plate D2557268123000 Item 099 adapter plate D2557268123200 Item 100 adapter plate D2557268123400 Item 101 adapter plate D2557268123600 Item 102 adapter plate D2557268123800 Item 103 adapter plate D2557268124000 Item 104 adapter plate D2557268124200 Item 105 adapter plate D2557268124400 Item 106 adapter plate D2557268124600 Item 107 adapter plate D2557268124800 Item 108 adapter plate D2557268125000 Item 109 with : 4 screw NAS1102-3-8 Item 58 10Remove the XZ-latches at FR50 and FR53 and the fastening parts and retain all the parts in the stowage box PN D28108298001 until installation of ACTs. NOTE : Tag the YZ-latches with their installation position. NOTE : The adapter plates must be remain in their installation position. (y) Install the shims on the frames of the AFT cargo compartment at FR47, FR48, FR49, FR50 and FR51. Refer to Kit 281132D22R00 Refer to Drawing(s) : D25572624006 Sheet(s) 6 1 Put these items with sealant (Mat. No. 09-005) in position as required as shown in drawing D25572624006, Sheet 6, Detail U1-6 : NOTE : The quantity of the shims at each position is dependent on the measurement of gaps between the tool 98D28108641000 and the YZ-latches at FR47, FR48 and FR49. 10 shim D2557214632000 Item 021 10 shim D2557214631800 Item 022 (z) Install the brackets for the fuel drain/vent systems between FR42 and FR43 Refer to Kit 281132D75R00 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Refer to Drawing(s) : D93070668000 Sheet(s) 1 thru 8 1 Remove and retain the green hydraulic reservoir, refer to AMM 29-11-41, Page block 401. 2 Install the brackets for the fuel drain/vent systems between FR42 and FR43.

a Put these items in position as shown in Details A7 and A8 : 1 bracket D9357040100200 Item 112 1 bracket D9357040100300 Item 113

b Drill the rivet holes.

c Install these items : 1 bracket D9357040100200 Item 112 1 bracket D9357040100300 Item 113 with : 4 rivet DAN257-3264 Item 125 3 Install the green hydraulic reservoir, refer to AMM 29-11-41, Page block 401. (aa) Install the beam between FR46 and FR47. Refer to Kit 281132D18R00 Refer to Drawing(s) : D28270998002 Sheet(s) 2 1 Remove the existing fasteners in the affected area. 2 Put this item in position as shown in Detail A2-2 : 1 beam D2827099720000 Item 000

NOTE : Ensure that the reference holes are in line. 3Transfer drill the holes from aircraft structure to the beam and open the holes to final dimension. 4 Install this item : 1 beam D2827099720000 Item 000

with : 8 bolt NSA5031-3-10 Item 770 8 nut NAS1726C3P Item 807 8 washer NAS1149C0332R Item 808 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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(ab) Install the fuel transfer line between FR41 and FR47. Refer to Kit 281132D13R00 Refer to Drawing(s) : D28270972002 Sheet(s) 7 thru 12 1 Install the fuel transfer line between FR41 and FR43. Refer to Drawing(s) : D28270972002 Sheet(s) 8 and 12

a Install at the inner tube (which is installed at the top of the center tank at FR41) these items as shown in Detail Z8-8 : 1 O-ring NSA8203-222 Item 057 1 nut ABS0107-150 Item 064 1 ring NSA840003-150 Item 065

b Put at the outer tube, Item 002, these items in position as shown in Details Y8-8 and Z8-8 : 1 O-ring NSA8203-152 Item 054 1 O-ring NSA8203-230 Item 059

c Install these items at the inner tube, Item 004, as shown in Details Y8-8 and Z8-8 : 2 washer NAS1149C0332R Item 083 2 nut NAS1291C3M Item 084 2 lead E0088-10-125NN Item 108 2 tubing NSA937210MB0300 Item 110 NOTE : Cut the tubing, Item 110, in three pieces. d Insert this item : 1 tube D2827093000200 Item 004 in : 1 tube D2827093100200 Item 002 and put them between FR41 and FR43 with these items temporarily in position : 1 flange D2827093320400 Item 000 1 O-ring NSA8203-154 Item 055

e Push the inner tube, Item 004, over the inner tube (which is installed at the top of the center tank at FR41) and connect the both tubes with the nut, Item 064, as shown in Detail Z8-8.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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f Connect the strap, Item 108, at the flange with these items as shown in Detail Z8-8 : 1 washer NAS1149C0332R Item 083 1 bolt NAS1303-2 Item 095

g Push the flange, Item 000, and the O-ring, Item 055, in position and install these items as shown in Detail A8-8 : 10 washer NAS1149C0432R Item 082

6 nut NAS1726-4E Item 085 4 bolt NAS1304-4 Item 086 2 bolt NAS1304-3 Item 100

h Install this item and secure with lockwire (Mat. No. 19-018) as shown in Section B8-B8 : 1 spring D2827090220200 Item 074

i Install these items as shown in Detail Z8-8 : 1 clamp NSA5519-25 Item 061 6 washer NAS1149C0332R Item 083 3 nut NAS1291C3M Item 084 3 bolt NAS1303-3 Item 096 1 lead E0089-10-125NN Item 102 1 lead E0089-10-250NN Item 112 2 Install the fuel transfer line between FR43 and FR46. Refer to Drawing(s) : D28270972002 Sheet(s) 6 thru 12

a Insert this item as shown in Detail Y8-8 : 1 tube D2827093000000 Item 010 in : 1 tube D2827093100000 Item 008

b Install at the inner tube, Item 010, these items as shown in Detail Y8-8 : 1 O-ring NSA8203-222 Item 057 1 nut ABS0107-150 Item 064 1 ring NSA840003-150 Item 065

c Put at the outer tube, Item 008, this item in position as shown in Details Y8-8 and X8-8 : 2 O-ring NSA8203-230 Item 059

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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d Push over the outer tube, Item 008, these items temporarily as shown in Detail Y8-8 : 1 sleeve D2827093321400 Item 006 1 O-ring NSA8203-152 Item 054

e Put the tubes, Item 008 and 010, between FR43 and FR46 in position and connect the inner tube, Item 010, at the inner tube, Item 004, with the nut, Item 064, and install these items as shown in Detail Y8-8 and Section D8-D8 : 2 washer NAS1149C0432R Item 082 2 nut NAS1726-4E Item 085 2 bolt NAS1304-9 Item 090

f Connect the strap, Item 108, at the tube, Item 010, with these items as shown in Detail Y8-8 : 1 washer NAS1149C0332R Item 083 1 nut NAS1291C3M Item 084

g Push the sleeve,Item 006, and the O-ring, Item 054, in position and install these items as shown in Section D8-D8 : 2 washer NAS1149C0432R Item 082 4 nut NAS1726-4E Item 085 2 bolt NAS1304-11 Item 092 2 bolt NAS1304-12 Item 093

h Install this item and secure with lockwire (Mat. No. 19-018) as shown in Section C8-C8 : 1 spring D2827090220200 Item 074

i Install these items as shown in Details Y8-8 and C8-C8 : 2 clamp NSA5519-25 Item 061 6 washer NAS1149C0332R Item 083 3 nut NAS1291C3M Item 084 3 bolt NAS1303-3 Item 096 1 lead E0089-10-125NN Item 102 1 lead E0089-41-100NN Item 105 3 Install the fuel transfer line between FR46 and FR47. Refer to Drawing(s) : D28270972002 Sheet(s) 6 thru 12

a Install between FR46 and FR47, Y254 and -Y254, this item as shown in Section A10-A10 : 1 bracket D2827094800000 Item 051 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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with : 4 washer NAS1149C0432R Item 082 4 bolt NAS1304-2 Item 098

b Push over the outer tube, Item 008, this item temporarily as shown in Detail X8-8 : 1 sleeve D2827093322400 Item 016

c Put at the inner tube, Item 010, these items in position as shown in Detail X8-8 : 1 spacer D2827093221200 Item 012 1 O-ring NSA8203-222 Item 057 1 O-ring NSA8203-226 Item 058 1 ring NSA840003-150 Item 065 1 nut ABS0107-200 Item 066 1 ring NSA840003-200 Item 067

d Install these items at the girder plate at FR46 as shown in Details X8-8 and F8-F8 : 1 flange D2827093222200 Item 014 1 tube D2827092700000 Item 018 1 O-ring NSA8203-152 Item 054 1 O-ring NSA8203-234 Item 060 2 washer NAS1149C0432R Item 082 2 nut NAS1726-4E Item 085 2 bolt NAS1304-9 Item 090

e Push the inner pipe of the tube, Item 018, over the spacer, Item 012, and install the nut, Item 066. f Connect the strap of the tube, Item 018, at the inner tube, Item 010, with these items as shown in Detail X8-8: 1 washer NAS1149C0332R Item 083 1 nut NAS1291C3M Item 084

g Push the sleeve,Item 016, at FR46 in position and install these items as shown in Details X8-X8 and F8-F8: 2 washer NAS1149C0432R Item 082 4 nut NAS1726-4E Item 085 2 bolt NAS1304-11 Item 092 2 bolt NAS1304-12 Item 093

h Install this item and secure with lockwire (Mat. No. 19-018) as shown in Section E8-E8 : 1 spring D2827090220200 Item 074 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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i Install these items as shown in Detail X8-8 and Section E8-E8 : 1 clamp NSA5519-25 Item 061 4 washer NAS1149C0332R Item 083 2 nut NAS1291C3M Item 084 2 bolt NAS1303-3 Item 096 1 lead E0089-10-125NN Item 102

j Install at the tube, Item 018, these items as shown in Detail V8-10 and Section A10-A10 : 1 flange D2827093222600 Item 020 1 O-ring NSA8203-151 Item 053 1 O-ring NSA8203-226 Item 058 with : 2 washer NAS1149C0432R Item 082 1 nut NAS1726-4E Item 085 1 bolt NAS1304-5 Item 087 2 bolt NAS1304-10 Item 091

k Install at the flange, Item 020, these items and secure with lockwire (Mat. No. 19-018) as shown in Detail V8-10: 1 plug AN814-4DL Item 071 1 packing NSA8200-4 Item 072

l Install these items as shown in Detail V8-10 and Section A10-A10 : 1 flange D2827093222800 Item 028 1 O-ring NSA8203-151 Item 053 with : 2 nut NAS1726-4E Item 085 2 bolt NAS1304-8 Item 089 2 bolt NAS1304-10 Item 091 (ac) Install the vent line between FR37 and FR47. Refer to Kit 281132D13R00 Refer to Drawing(s) : D28270972002 Sheet(s) 6 thru 12 1 Install the vent line between FR37 and FR42. Refer to Drawing(s) : D28270972002 Sheet(s) 6 thru 12

a Install between FR40 and FR41 this item as shown in Detail W9-11 : 1 bracket D2827093500000 Item 033 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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with : 4 nut NAS1726-4E Item 085 4 bolt NAS1304-2 Item 098

b Install at the inner tube (which is installed at the top of the center tank between FR37 and FR38) these items as shown in Detail U9-9 : 1 O-ring NSA8203-226 Item 058 1 nut ABS0107-200 Item 066 1 ring NSA840003-200 Item 067

c Put at the outer tube, Item 032, this item in position as shown in Details U9-9 and S9-10 : 2 O-ring NSA8203-234 Item 060

d Install these items at the inner tube, Item 034, as shown in Details U9-9 and S9-10 : 2 washer NAS1149C0332R Item 083 2 nut NAS1291C3M Item 084 1 lead E0088-10-125NN Item 108 1 lead E0088-10-200NN Item 109 1 tubing NSA937210MB0300 Item 110 1 tubing NSA937210MB0300 Item 111 NOTE : Cut the tubing, Item 111, in two pieces.

e Insert this item : 1 tube D2827092800400 Item 034 in : 1 tube D2827092900600 Item 032 and put them between FR37 and FR42 with these items temporarily in position : 1 flange D2827093320600 Item 030 1 O-ring NSA8203-156 Item 056

f Push the inner tube, Item 034, over the inner tube (which is installed at the top of the center tank between FR37 and FR38) and connect the both tubes with the nut, Item 066, as shown in Detail U9-9. gAttach the tube, Item 032, at the bracket, Item 033, between FR40 and FR41 with these items as shown in Detail W9-11 : 1 clamp D28270935002 Item 035 1 clamp D28270935004 Item 037 2 washer NAS1149C0332R Item 083 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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2 bolt NAS1303-3 Item 096

h Connect the strap, Item 108, at the flange with these items as shown in Detail U9-9 : 1 washer NAS1149C0332R Item 083 1 bolt NAS1303-2 Item 095

i Push the flange, Item 030, and the O-ring, Item 056, in position and install these items as shown in Detail A9-9: 10 washer NAS1149C0432R Item 082

6 nut NAS1726-4E Item 085 4 bolt NAS1304-4 Item 086 2 bolt NAS1304-3 Item 100

j Install this item and secure with lockwire (Mat. No. 19-018) as shown in Section B9-B9 : 1 spring D2827090220200 Item 075

k Install these items as shown in Detail U9-9 : 1 clamp NSA5519-30 Item 062 6 washer NAS1149C0332R Item 083 3 nut NAS1291C3M Item 084 3 bolt NAS1303-3 Item 096 1 lead E0089-10-125NN Item 102 1 lead E0089-10-250NN Item 112 2 Install the vent line between FR42 and FR43. Refer to Drawing(s) : D28270972002 Sheet(s) 6 thru 12

a Install at the inner tube, Item 034, these items as shown in Detail S9-10 : 1 O-ring NSA8203-226 Item 058 1 nut ABS0107-200 Item 066 1 retaining ring NSA840003-200 Item 067

b Push over the outer tube, Item 032, this item temporarily as shown in Detail S9-10 : 1 sleeve D2827093321200 Item 036

c Install at the girder plate at FR42 these items as shown in Detail S9-10 and Section J10-J9 : 1 flange D2827093320800 Item 038 1 flange D2827093221600 Item 040 1 O-ring NSA8203-152 Item 054 1 O-ring NSA8203-234 Item 060 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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with : 4 washer NAS1149C0432R Item 082 2 nut NAS1726-4E Item 085 1 bolt NAS1304-8 Item 089 1 bolt NAS1304-10 Item 091

d Push the flange, Item 040, over the inner tube, Item 034, and install the nut, Item 066.

eAssemble these items as shown in Detail Q9-11 : 2 spacer A2827090120400 Item 031 1 tube D2827092800000 Item 044 1 tube D2827092900000 Item 046 1 tube D2827092900200 Item 048 1 O-ring NSA8203-152 Item 054 2 lead E0089-41-250NN Item 107 with : 2 washer NAS1149C0432R Item 082 6 nut NAS1726-4E Item 085 5 bolt NAS1304-5 Item 087 1 bolt NAS1304-6 Item 088

f Install at the tube, Item 044, these items as shown in Details S9-10 and T9-9 : 2 O-ring NSA8203-226 Item 058 2 nut ABS0107-200 Item 066 2 ring NSA840003-200 Item 067

g Install at the outer tubes, Items 046 and 048, this item as shown in Details S9-10 and T9-9 : 2 O-ring NSA8203-234 Item 060

h Push over the outer tube, Item 046, these items temporarily as shown in Detail S9-10 : 1 sleeve D2827093321000 Item 042 1 O-ring NSA8203-152 Item 054

i Push the inner tube, Item 044, in the flange, Item 040, and connect the nut, Item 066, as shown in Detail S9-10. j Connect the strap, Item 109, at the inner tube, Item 044, with these items as shown in Detail S9-10 : 1 washer NAS1149C0332R Item 083 1 nut NAS1291C3M Item 084

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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k Push the sleeves, Item 036 and 042, at the girder plate at FR42 in position and install these items as shown in Detail S9-10 and Section F10-F9 : 4 washer NAS1149C0432R Item 082 4 nut NAS1726-4E Item 085 4 bolt NAS1304-14 Item 093

l Install these items and secure with lockwire (Mat. No. 19-018) as shown in Sections C10-C9 and D10-D9 : 2 spring D2827090220200 Item 075

mInstall these items as shown in Details S9-10 and U9-10 and Section E10-E9 : 1 clamp NSA5519-30 Item 062 6 washer NAS1149C0332R Item 083 3 nut NAS1291C3M Item 084 3 bolt NAS1303-3 Item 096 1 lead E0089-10-200NN Item 104 1 lead E0089-41-100NN Item 105 1 lead E0089-41-200NN Item 106

n Install at the inner tube, Item 044, these items as shown in Detail T9-9 : 1 washer NAS1149C0332R Item 083 1 nut NAS1291C3M Item 084 1 lead E0088-10-200NN Item 109 1 tubing NSA937210MB0300 Item 111

o Push over the outer tube, Item 048, this item temporarily as shown in Detail T9-9 : 1 sleeve D2827093321200 Item 036

p Install at the bracket at FR43 these items as shown in Detail T9-9 and Section J9-J9 : 1 flange D2827093320800 Item 038 1 flange D2827093221600 Item 040 1 O-ring NSA8203-152 Item 054 1 O-ring NSA8203-234 Item 060 with : 4 washer NAS1149C0432R Item 082 2 nut NAS1726-4E Item 085 1 bolt NAS1304-8 Item 089 1 bolt NAS1304-10 Item 091

q Push the flange, Item 040, over the inner tube, Item 044, and install the nut, Item 066. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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3 Install the vent line between FR43 and FR46. Refer to Drawing(s) : D28270972002 Sheet(s) 6 thru 12

a Insert this item : 1 tube D2827092800200 Item 052 in : 1 tube D2827092900400 Item 050

b Put at the outer tube, Item 050, this item in position as shown in Details T9-9 and R9-11 : 2 O-ring NSA8203-234 Item 060

c Install at the inner tube, Item 052, these items as shown in Details T9-9 and R9-11 : 2 O-ring NSA8203-226 Item 058 2 nut ABS0107-200 Item 066 2 ring NSA840003-200 Item 067

d Push over the outer tube, Item 050, these items temporarily as shown in Detail T9-9 : 1 sleeve D2827093321000 Item 042 1 ring NSA8203-152 Item 054

e Put the tubes, Item 050 and 052, between FR43 and FR46, in position. f Push the inner tube, Item 052, in the flange, Item 040, at FR43 and install the nut, Item 066, as shown in Detail T9-9. g Connect the strap, Item 109, at the inner tube, Item 052, with these items as shown in Detail T9-9 : 1 washer NAS1149C0332R Item 083 1 nut NAS1291C3M Item 084

h Push the sleeves, Item 036 and 042, at the girder plate at FR43 in position and install these items as shown in Detail T9-9 and Section F9-F9 : 4 washer NAS1149C0432R Item 082 4 nut NAS1726-4E Item 085 4 bolt NAS1304-14 Item 093

i Install these items and secure with lockwire (Mat. No. 19-018) as shown in Sections C10-C9 and D10-D9 : 2 spring D2827090220200 Item 075 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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j Install these items as shown in Details T9-9 and U9-10 and Section E9-E9 : 1 clamp NSA5519-30 Item 062 6 washer NAS1149C0332R Item 083 3 nut NAS1291C3M Item 084 3 bolt NAS1303-3 Item 096 1 lead E0089-10-200NN Item 104 1 lead E0089-41-100NN Item 105 1 lead E0089-41-200NN Item 106 4 Install the vent line between FR46 and FR47. Refer to Drawing(s) : D28270972002 Sheet(s) 9 and 12

a Push over the outer tube, Item 050, this item temporarily as shown in Detail R9-11 : 1 sleeve D2827093322200 Item 039

b Install these items at the girder plate at FR46 as shown in Detail R9-11 and Section N11-N11 : 1 flange D2827093222200 Item 014 1 tube D2827092700000 Item 018 1 O-ring NSA8203-152 Item 054 1 O-ring NSA8203-234 Item 060 4 washer NAS1149C0432R Item 082 2 nut NAS1726-4E Item 085 1 bolt NAS1304-10 Item 091 1 bolt NAS1304-11 Item 092

c Push the inner pipe of the tube, Item 018, over the inner tube, Item 052, and install the nut, Item 066. d Connect the strap of the tube, Item 018, at the inner tube, Item 052, with these items as shown in Detail R9-11 : 1 washer NAS1149C0332R Item 083 1 nut NAS1291C3M Item 084

e Push the sleeve,Item 039, at FR46 in position and install these items as shown in Detail R9-11 and Section N11-N11 : 4 washer NAS1149C0432R Item 082 4 nut NAS1726-4E Item 085 4 bolt NAS1304-11 Item 092

f Install this item and secure with lockwire (Mat. No. 19-018) as shown in Section K11-K9 : 1 spring D2827051720200 Item 075 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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g Install these items as shown in Detail R9-11 and P11-11 and Section L11-L11 : 1 clamp NSA5519-30 Item 062 4 washer NAS1149C0332R Item 083 2 nut NAS1291C3M Item 084 2 bolt NAS1303-3 Item 096 1 lead E0089-10-160NN Item 103 1 lead E0089-41-100NN Item 105

h Install at the tube, Item 018, these items as shown in Detail V9-10 and Section A10-A10 : 1 flange D2827093222600 Item 020 1 O-ring NSA8203-151 Item 053 1 O-ring NSA8203-226 Item 058 with : 2 washer NAS1149C0432R Item 082 1 nut NAS1726-4E Item 085 1 bolt NAS1304-5 Item 087 2 bolt NAS1304-10 Item 091

i Install at the flange, Item 020, these items and secure with lockwire (Mat. No. 19-018) as shown in Detail V9-10: 1 plug AN814-4DL Item 071 1 packing NSA8200-4 Item 072

j Install these items as shown in Detail V9-10 and Section A10-A10 : 1 flange D2827093222800 Item 028 1 O-ring NSA8203-151 Item 053 with : 2 nut NAS1726-4E Item 085 2 bolt NAS1304-8 Item 089 2 bolt NAS1304-10 Item 091 (ad) Install the cover between FR46 and FR47 at the fuel transfer line and vent line. Refer to Kit 281132D19R00 Refer to Drawing(s) : D28270999004 Sheet(s) 3 1 Put this item in position as shown in Detail Z3-3 : 1 shield D2827099600400 Item 022 2Transfer drill the two holes in the upper beam and open them to final dimension. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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3 Install these items as shown in Detail A3-3 : 1 shim D2827098322400 Item 004 1 shield D2827099600400 Item 022

with : 8 bolt NAS1303-5 Item 006 2 bolt NAS1303-8 Item 010 10 washer NAS1149D0332K Item 014 (ae) Install the system between FR37 and FR48. Refer to Kit 281132D14R00 Refer to Drawing(s) : D28270973002 Sheet(s) 6 thru 10 1 Install this item between FR38 and FR39 as shown in Detail Y6-8 : 1 bracket D2827094720000 Item 210

with : 2 bolt NAS1304-2 Item 030 2 nut NAS1726-4E Item 032 2 Install these items as shown in Details W6-8 and Z6-8 : 2 union MS21902D8 Item 000 2 packing NSA8200-8 Item 001 3Connect this item at the vent shroud line as shown in drawing D28270973002, Sheet 6 : 1 tube D2827093603400 Item 100

and install these items as shown in Details Y6-8 and X6-8 and Section B6-B8 : 4 washer NAS1149C0332R Item 007 1 screw NAS1096-3-8 Item 009 4 nut NAS1726-3E Item 010 2 screw NAS1096-3-7 Item 011 3 clamp MS21919WDE8 Item 014 1 clamp MS21919WDE48 Item 016 1 screw NAS1096-3-9 Item 024 1 bracket D2827098322800 Item 216 4 Install at the tube, Item 100, these items as shown in drawing D28270973002, Sheet 6 : 1 washer NAS1149C0332R Item 007 1 screw NAS1096-3-8 Item 009 1 clamp NSA5519-11 Item 035 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 nut NAS1291C3M Item 036 1 lead E0091-10-280NN Item 038 5 Connect this item at the fuel shroud line as shown in drawing D28270973002, Sheet 6 : 1 tube D2827093600200 Item 102

and connect the tube, Item 100, and the tube, Item 102, with this item : 1 tee MS21905D8 Item 005 6 Install these items between FR42 and FR43 as shown in Detail V6-8 : 1 elbow MS21907D8 Item 002 1 nut AN924-8D Item 003 1 washer NAS1149D1290K Item 004 1 washer NAS1149D1216H Item 023

and install this item as shown in drawing D28270973002, Sheet 6 : 1 tube D2827093602400 Item 124 7 Install these items as shown in Detail R6-8 : 3 washer NAS1149C0332R Item 007 2 screw NAS1096-3-8 Item 009 1 screw NAS1096-3-9 Item 024 2 strap E0090-10-125NN Item 025 1 clamp NSA5519-11 Item 035 1 nut NAS1291C3M Item 036 8 Install these items between FR42 and FR43 as shown in Details A6-7 and C6-9 : 1 tube D2827093603200 Item 108 1 tube D2827093602600 Item 126

with : 1 spacer NSA5527-03-16 Item 006 4 washer NAS1149C0332R Item 007 1 screw NAS1096-3-15 Item 008 3 screw NAS1096-3-8 Item 009 1 nut NAS1726-3E Item 010 2 clamp MS21919WDE8 Item 014 1 strap E0090-10-125NN Item 025 2 clamp NSA5519-11 Item 035 2 nut NAS1291C3M Item 036 9 Install this item in the keel beam as shown in drawing D28270973002, Sheet 6 : 1 hose 51263408-0840 Item 202 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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with : 6 washer NAS1149C0332R Item 007 6 screw NAS1096-3-8 Item 009 6 clamp MS21919WDE11 Item 015 10Install these items at FR46 as shown in Detail S6-9 : 1 tee NAS1763D080808 Item 033 1 fitting D2827094320000 Item 204

with : 2 nut NAS1726-3E Item 010 2 screw NAS1096-3-10 Item 012 11Install these items at FR46 as shown in Details B6-7, T6-8 and U6-8 : 1 tee MS21905D8 Item 005 1 tube D2827093601600 Item 116 1 tube D2827093602000 Item 120 1 tube D2827093603000 Item 130

with : 4 washer NAS1149C0332R Item 007 3 screw NAS1096-3-8 Item 009 3 nut NAS1726-3E Item 010 2 clamp MS21919WDE8 Item 014 1 screw NAS1096-3-9 Item 024 1 strap E0090-10-125NN Item 025 1 washer NAS1149D0316H Item 026 1 bolt NAS1303-2 Item 027 1 clamp NSA5575-7 Item 028 2 clamp NSA5519-11 Item 035 2 nut NAS1291C3M Item 036 1 strap E0090-10-200NN Item 037 1 lead E0091-10-280NN Item 038 12Install these items between FR47 and FR48 as shown in Detail Q6-10 : 1 nut AN924-8D Item 003 1 washer NAS1149D1290K Item 004 1 tee MS21912D8 Item 013 1 washer NAS1149D1216H Item 023 13Install these items between FR46 and FR48 as shown in Details Q6-10 and P10-10 : 1 tube D2827093603600 Item 136 1 tube D2827097600400 Item 138

with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 193 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 washer NAS1149C0332R Item 007 1 screw NAS1096-3-7 Item 011 1 clamp MS21919WDE8 Item 014 1 hose D56KAN002 Item 039 2 clamp ASNA0033-016 Item 040 14Install these items as shown in Details P10-10 and S6-9 :

4 washer NAS1149C0332R Item 007 4 screw NAS1096-3-8 Item 009 2 strap E0090-10-125NN Item 025 4 clamp NSA5519-11 Item 035 4 nut NAS1291C3M Item 036 15Install these items with sealant (Mat. No. 09-016) at the belly fairing as shown in Detail Q6-10 : 1 reducer MS21916D8-6 Item 017 1 packing NSA8200-6 Item 022 1 monitor L83A13-617 Item 206

with : 3 washer NAS1149C0432R Item 018 3 bolt NAS1304-4 Item 019

and install this item : 1 hose 513535E0107-090 Item 208 16Install this item with adhesive (Mat. No. 08-010) as shown in Detail Q6-10 : 1 placard D2827094421400 Item 214 17Install this item as shown in Detail Q6-10 : 1 tube D2827097600200 Item 134 (af) Install the cavity drain and monitoring system between FR46 and FR50. Refer to Kit 281132D15R00 Refer to Drawing(s) : D28270974002 Sheet(s) 4 thru 6 1 Install these items between FR48 and FR49 as shown in Section C4-C5 : 1 nut AN924-8D Item 034 1 washer NAS1149D1290K Item 035 1 tee MS21912D8 Item 036 1 washer NAS1149D1216H Item 037 2 Install these items between FR48 and FR50 as shown in drawing D28270974002, Sheet 4 and in Details C4-C5 and D4-6: DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 tee MS21905D8 Item 021 1 elbow NAS1762D0808 Item 023 2 cap MS21914-8D Item 033 1 tube D2827097700400 Item 124 1 tube D2827097701200 Item 134

with : 3 clamp MS21919WDE8 Item 014 3 screw NAS1096-3-8 Item 016 4 washer NAS1149C0332R Item 017 1 nut NAS1291C3M Item 049 3 Install these items between FR49 and FR50 as shown in drawing D28270974002, Sheet 4 : 3 screw NAS1096-3-8 Item 016 3 washer NAS1149C0332R Item 017 3 nut NAS1291C3M Item 049 3 clamp NSA5519-11 Item 051 2 lead E0090-10-160NN Item 061 4 Install this item as shown in drawing D28270974002, Sheet 4 and Section B4-B6 : 1 tube D2827097700200 Item 122

with : 3 clamp MS21919WDE8 Item 014 3 screw NAS1096-3-8 Item 016 4 washer NAS1149C0332R Item 017 5 Install these items between FR46 and FR47 as shown in drawing D28270974002, Sheet 4, Section A4-A6 and Detail Z4-4 : 1 tee MS21905D8 Item 021 1 elbow NSA855120-8D Item 022 1 tube D2827093701800 Item 130 1 tube D2827097701000 Item 132

with : 1 clamp MS21919WDE8 Item 014 3 screw NAS1096-3-8 Item 016 3 washer NAS1149C0332R Item 017 3 nut NAS1291C3M Item 049 3 clamp NSA5519-11 Item 051 2 clamp ASNA0033-016 Item 056 1 hose D56KAN002 Item 057 1 strap E0090-10-125NN Item 060 1 lead E0090-10-160NN Item 061 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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NOTE : The connection to the and monitoring system will be installed in para (7)(ae)(7). 6 Install these items between FR47 and FR48 as shown in drawing D28270974002, Sheet 4 : 3 screw NAS1096-3-8 Item 016 3 washer NAS1149C0332R Item 017 3 nut NAS1291C3M Item 049 3 clamp NSA5519-11 Item 051 2 lead E0090-10-160NN Item 061 7 Install this item with sealant (Mat. No. 09-016) at the belly fairing as shown in Detail A5-5 and Section C4-C5: 1 reducer MS21916D8-6 Item 025 1 packing NSA8200-6 Item 026 1 valve L83A13-617 Item 202

with : 3 washer NAS1149C0432R Item 027 3 bolt NAS1304-4 Item 028

and install this item : 1 hose 513535E0107-090 Item 204 8 Install this item with adhesive (Mat. No. 08-010) as shown in Detail A5-5 : 1 placard D2827094421600 Item 216 (ag) Install the cavity drain and monitoring system between FR50 and FR53. Refer to Kit 281132D01R00 Refer to Drawing(s) : D28270990002 Sheet(s) 2 and 4 1 From the tee at FR50 shown in Sheet 4, remove : 1 cap MS21914-8D Item (033) Retain

NOTE : The cap was installed with Kit 281132D15R00, drawing D28270974002, Item 033. 2 Install these items between FR50 and FR53 as shown in sheet 4: 1 tube D28270977022 Item 006

with : 1 screw MS21919WDE8 Item 016 1 washer NAS1149C0332R Item 017 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 196 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 nut NAS1291C3M Item 049 1 clamp NSA5519-11 Item 051 1 bonding lead E0090-10-160NN Item 061 3 Install these items between FR51 and FR52 as shown in sheet 2 and Sections B1-B2 and C1-C2: 2 clamp MS21919WDE8 Item 014 2 screw MS21919WDE8 Item 016 2 washer NAS1149C0332R Item 017 2 nut NAS1291C3M Item 049 4 Install these items between FR52A and FR53 as shown in sheet 2 and Detail Y2-2: 1 clamp MS21919WDE8 Item 014 1 screw NAS1096-3-9 Item 015 1 screw MS21919WDE8 Item 016 2 washer NAS1149C0332R Item 017 2 nut NAS1291C3M Item 049 1 clamp NSA5519-11 Item 051 1 bonding lead E0090-10-160NN Item 061 5At FR52A, on tube, Item 004, install as shown in sheet 2 and Detail A1-2 : 1 cap MS21914-8D Item (033) Retained (ah) Install the attachment structure of the partition panels and floor panels. Refer to Kit 281132D36R02 Refer to Drawing(s) : D53975019000 Sheet(s) 3 thru 6 1 Install the attachment structure of the partition panels 151AW, 151BW and 152BW between FR46 and FR47.

a Put these items in position as shown in Section B3-B4, Details X4-5, Z4-5, Y6-6 and Sections A5-A5, B5-B5 and A6-A6: 22 bracket D5397469700000 Item 028 bTransfer drill the rivet holes and open them to final dimension.

c Install as shown in Section F3-F3, A5-A5, B5-B5 and A6-A6 : 22 bracket D5397469700000 Item 028 with : 88 rivet LN9198-4816CF Item 648 d Install these items as shown in Section B3-B4 and Details X4-5 and Z4-5 and Sections A5-A5 and B5-B5 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 T-section D5397468800200 Item 044 1 T-section D5397468800300 Item 045 1 T-section D5397468000400 Item 046 1 T-section D5397468000500 Item 047 with : 32 bolt NAS6703-2 Item 025 32 washer NAS1149D0332K Item 026

e Put these items in position as shown in Section B3-B4 and Detail Y4-6 and Section A6-A6 : 1 section D5397467400400 Item 052 1 section D5397467400500 Item 053 1 bracket D5397469000000 Item 016 1 bracket D5397469000100 Item 017 1 bracket D5397469200000 Item 018 1 bracket D5397469200100 Item 019 1 bracket D5397469300000 Item 020 1 bracket D5397469300100 Item 021

f Drill and countersink the rivet holes and open them to final dimension. g Put these items in position as shown in Section B3-B4 and Detail Y4-6 and Section A6-A6 : 1 section D5397467400400 Item 052 1 section D5397467400500 Item 053 1 bracket D5397469000000 Item 016 1 bracket D5397469000100 Item 017 1 bracket D5397469200000 Item 018 1 bracket D5397469200100 Item 019 1 bracket D5397469300000 Item 020 1 bracket D5397469300100 Item 021 Transfer drill the rivet holes and install the sections with : 12 bolt NAS6703-2 Item 025 12 washer NAS1149D0332K Item 026 18 rivet NAS1097AD-10 Item 532 h Put these items in position as shown in Section B3-B4 : 1 section D5397492500000 Item 048 1 section D5397492500200 Item 050

i Drill and countersink the holes and open them to final dimension. j Install these items : 1 T-section D5397492500000 Item 048 1 T-section D5397492500200 Item 050 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 T-section D5397467400400 Item 052 1 T-section D5397467400500 Item 053 with 94 rivet NAS1097AD4-12 Item 532 k Drill and countersink the holes and open them to final dimension. l Install these items : 1 section D5397467800800 Item 040 1 section D5397467800900 Item 041 1 section D5397492600000 Item 042 with : 50 rivet NAS1097AD4-12 Item 532

mInstall this item as shown in Detail V4-4 : 3 plate D5397492700000 Item 054 with : 9 screw NAS1102E3-7 Item 400 9 washer DAN125-4 Item 402

n Seal the gaps with sealant (Mat. No. 09-013) as shown in Section A4-A4 and Detail V4-4.

o Put these items in position as shown in Section B6-B6 : 1 section D5347047400200 Item 030 1 section D5347047400300 Item 031

p Drill and countersink the holes and open them to final dimension. q Install these items : 1 section D5347047400200 Item 030 1 section D5347047400300 Item 031 with : 32 rivet NAS1097AD4-12 Item 532 2 Install the attachment structure of the cargo compartment floor panels at FR49, FR51 and FR54. Refer to Drawing(s) : D53975019000 Sheet(s) 3 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 199 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Put these items at FR49, FR51 and 54 in position : 3 section D5397489200000 Item 000 2 section D5397489200100 Item 001 1 section D5397489300000 Item 002

b Drill and countersink the holes and open them to final dimension.

c Install these items : 3 section D5397489200000 Item 000 2 section D5397489200100 Item 001 1 section D5397489300000 Item 002 with : 25 rivet NAS1097AD4-12 Item 532 (ai) Remove and discard the attachment parts at FR42. Refer to Drawing(s) : D92491681002 Sheet(s) 7 and 8 1 Remove and discard the attachment as shown in drawing D92491681002, Sheets 7, 8 and B01.

a Remove discard these parts : 1 bracket D9249170620000 Item (503) Discard 2 screw NAS1096-2-7 Item (522) Discard 2 washer NAS1149CN832R Item (531) Discard 2 nut MS21042-08 Item (541) Discard (aj) Remove and discard the attachment parts at FR42. Refer to Drawing(s) : D92891805002 Sheet(s) 17 and 18 1 Remove and discard the attachment as shown in drawing D92891805002, Sheets 17 and 18 and B01.

a Remove discard these parts : 9 screw NAS1096-2-10 Item (506) Discard 9 washer NAS1149CN816R Item (652) Discard 9 washer NSA935808C01 Item (671) Discard 9 clip-nut NSA5066-08-2 Item (731) Discard 9 spacer NSA5527-03-04 Item (806) Discard 2 clamp MS21919WCH4 Item (850) Discard 3 clamp NSA935807-06 Item (876) Discard 6 clamp NSA935807 Item (877) Discard (ak) Remove and discard the attachment parts between FR46 and FR49. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 200 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s) : D92891805004 Sheet(s) 22, 24, 28, 30, 32, 34, 38, 41, 43, 45 and 47 1 Remove and discard the attachment as shown in drawing D92891805004, Sheets 22, 24, 28, 30, 32, 34, 38, 41, 43, 45 and 47.

a Remove discard these parts : 17 screw NAS1096-2-8 Item (501) Discard 18 screw NAS1096-2-18 Item (502) Discard 13 screw NAS1096-2-28 Item (503) Discard 50 screw NAS1096-3-8 Item (504) Discard 39 clip-nut NSA5066-08-2 Item (505) Discard

1 spacer NSA5527-03-08 Item (506) Discard 71 nut MS21042L3 Item (507) Discard 28 nut MS21042L04 Item (508) Discard 69 washer NAS1149DN816K Item (509) Discard 31 washer NAS1149DO332K Item (510) Discard 28 washer NAS1149DN416K Item (511) Discard

2 sleeve NSA935510-02 Item (512) Discard 15 clamp MS21919WCH5 Item (513) Discard

2 clamp NSA935807-12 Item (514) Discard 10 spacer NSA5527-03-02 Item (516) Discard

3 washer NSA935808-01 Item (517) Discard 36 washer NAS1149C0332R Item (519) Discard 30 spacer NSA5527-03-01 Item (520) Discard

3 bulkhead NSA934710T14 Item (521) Discard 28 screw NAS1096-2-14 Item (525) Discard

8 bracket NSA935513-01 Item (527) Discard 1 bracket NSA935513-05 Item (528) Discard 1 bracket ABS0354-01 Item (529) Discard 1 bracket NSA935504-03 Item (530) Discard 32 bracket NSA935504-01 Item (531) Discard

1 clamp ASNA0032H052 Item (533) Discard 1 tie NSA935401-04 Item (536) Discard 13 nut MS21042L08 Item (537) Discard

1 cable guide D9249184105600 Item (538) Discard 1 cable guide D9249184105800 Item (539) Discard 1 cable guide D9249184104800 Item (542) Discard 1 strap D9249107300400 Item (546) Discard 1 cable guide D9249181401800 Item (547) Discard 2 socket NSA938004-08 Item (548) Discard 2 cover NSA938005-08 Item (549) Discard 4 spacer NSA5527-03-04 Item (552) Discard 8 screw NAS1096-2-10 Item (553) Discard 2 bracket ABS0355-03 Item (554) Discard 1 screw NAS1096-2-43 Item (555) Discard 16 screw NAS1096-3-10 Item (559) Discard 26 washer NAS1149D0363K Item (560) Discard

2 spacer NSA5527-03-08 Item (561) Discard 5 bracket E0343-01 Item (563) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 201 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 screw NAS1096-2-32 Item (564) Discard 3 socket NSA938004-10 Item (565) Discard 3 socket NSA938004-16 Item (566) Discard 2 cover NSA938005-10 Item (567) Discard 1 socket NSA938004-20 Item (568) Discard 1 socket NSA938004-22 Item (569) Discard 1 bushing NSA5539S Item (570) Discard 1 spacer NSA5527-03-03 Item (572) Discard 1 tie NSA935401-03 Item (573) Discard 3 bracket NSA935504-01 Item (575) Discard 2 screw NAS1096-3-28 Item (576) Discard 1 screw NAS1096-3-39 Item (577) Discard 1 sealing A9249429620400 Item (579) Discard 3 bracket A9249429720200 Item (580) Discard 1 angle A9249436120000 Item (581) Discard 1 screw NAS1096-3-13 Item (582) Discard 1 washer NAS1149CN832R Item (612) Discard 1 bracket NSA935514-04A Item (613) Discard 1 tube TSTMNR502-0 Item (631) Discard 1 cable guide D9249181401600 Item (671) Discard 20 washer D9249102520000 Item (690) Discard

6 spacer NSA5527-03-15 Item (828) Discard (al) Remove and discard the attachment parts at FR46 and FR54. Refer to Drawing(s) : D92491681004 Sheet(s) 12, 14, 15, 16, 18, 20, 22, 24 and 26, 30 and 34. 1 Remove and discard the attachment as shown in drawing D92491681004, Sheets 12, 14, 15, 16, 18, 20, 22, 24 and 26, 30 and 34.

a Remove discard these parts : 20 bracket A9249635720200 Item (501) Discard

3 bracket D9249179320000 Item (502) Discard 1 bracket D9249172120000 Item (504) Discard 1 plate D9249175620400 Item (505) Discard 6 bracket D9249178000000 Item (507) Discard 1 bracket D9249177020000 Item (511) Discard 3 bracket D9249177520000 Item (513) Discard 1 console D9249181820200 Item (523) Discard 1 bracket D9249171620400 Item (524) Discard 1 bracket D9249178000400 Item (530) Discard 1 support D9249185020400 Item (550) Discard (am) Remove and discard the attachment parts at FR46 and FR54. Refer to Drawing(s) : D92491681006 Sheet(s) 36, 38, 39, 42 and 44. 1 Remove and discard the attachment as shown in drawing D92491681006, Sheets 36, 38, 39, 42 and 44. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 202 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Remove discard these parts : 6 bracket D9249177920000 Item (511) Discard 3 bracket D9249177720400 Item (512) Discard 1 bracket D9249177820000 Item (513) Discard 1 bracket D9249177820100 Item (514) Discard 8 bracket D9249177121200 Item (517) Discard 1 bracket D9249180500000 Item (518) Discard 2 bracket D9249180800000 Item (524) Discard 1 bracket D9249180921000 Item (525) Discard 1 bracket D9249180921200 Item (526) Discard 1 bracket D9249180921400 Item (527) Discard (an) Remove the cable harnesses 4605VB, 4628VB, 4650VB, 4655VB, 4656VB, 4661VB, 4662VB, 4663VB, 4664VB, 4670VB, 4671VB, 4672VB, 4673VB, 4680VB, 4681VB, 4683VB, 4692VB, 4693VB 4694VB. 1 Remove the cable harness 4605VB Refer to Drawing(s) : D92991405000 Sheet(s) 1

a Disconnect the plugs 1997VC-A and 4RC2-A. b Discard the harness 4605VB. 2 Remove the cable harness 4628VB/1M Refer to Drawing(s) : D92991428013 Sheet(s) 18 3 Remove the cable harness 4655VB/6S Refer to Drawing(s) : D92991455006 Sheet(s) 7, B01 and B02 and V01 4 Remove the cable harness 4656VB/6E and 6G Refer to Drawing(s) : D92991456004 Sheet(s) 5, B01 and B02 5 Remove the cable harness 4661VB/1M Refer to Drawing(s) : D92991461021 Sheet(s) 26, B01 to B04, H01 to H21, V01 to V05, W01 and W02, X01 6 Remove the cable harness 4662VB/2M Refer to Drawing(s) : D92991462010 Sheet(s) 10, B01 and B02, H01 to H06, W01, X01, V01 and V02 7 Remove the cable harness 4663CVB/1S DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 203 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s) : D92991463003 Sheet(s) 8, B01, H01 to H09, W01 and W02, X01 8 Remove the cable harness 4664VB/2S Refer to Drawing(s) : D92991464002 Sheet(s) 4 and B01 9 Remove the cable harness 4670VB/1M Refer to Drawing(s) : D92991470007 Sheet(s) 8, B01 to B04, H01 to H06, W01, X01, V01 to V03 10Remove the cable harness 4671VB/1M Refer to Drawing(s) : D92991471005 Sheet(s) 7, B01 to B05, H01 to H07, W01 and W02, X01, V01 to V03 11Remove the cable harness 4650VB/1R Refer to Drawing(s) : D92991450014 Sheet(s) 12, V01 and V02 12Remove the cable harness 4672VB/2M Refer to Drawing(s) : D92991472013 Sheet(s) 14, B01 and B02, H01 to H04, W01, X01, V01 and V02 13Remove the cable harness 4673VB/1S Refer to Drawing(s) : D92991473003 Sheet(s) 4, B01 and B02, H01 to H04, W01, X01, V01 and V02 14Remove the cable harness 4680VB/1MB Refer to Drawing(s) : D92991480012 Sheet(s) 13, B01 to B03, H01 to H05, W01, X01, V01 and V02 15Remove the cable harness 4681VB/7M Refer to Drawing(s) : D92991481003 Sheet(s) 4, B01, H01, W01, V01 16Cable harness 4683VB/8M

a Remove the air inlet plenum for access, refer to AMM 21-61-51, Page block 401. b Remove the welding group (Item 127) for access, refer to AMM 21-52-41, Page block 401.

c Remove the cable harness 4683VB/8M DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 204 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s) : D92991483005 Sheet(s) 6, B01 and B02, H01 to H09, W01 and W02, X01 and X02, V01 to V04 17Remove the cable harness 4692VB/2M Refer to Drawing(s) : D92991492005 Sheet(s) 6, B01, H01, W01, X01, V01 18Remove the cable harness 4693VB/1S Refer to Drawing(s) : D92991493003 Sheet(s) 4, B01 and B02, H01 to H03, W01, X01, V01 and V02 19Remove the cable harness 4694VB/2S Refer to Drawing(s) : D92991494003 Sheet(s) 4, B01 and B02, H01 to H03, W01, X01, V01 and V02 (ao) Remove the cable harnesses 4213VB, 4214VB, 4216VB, 4218VB, 4220VB, 4221VB, 4222VB, 4223VB, 4224VB, 4225VB, 4226VB, 4227VB, 4232VB, 4233VB, 5214VB, 5220VB, 5224VB, 5233VB. 1 Remove the wires of cable harness 4213VB Refer to Drawing(s) : D92999559004 Sheet(s) 2, lines 1 to 3 2 Remove the wires of cable harness 4214VB Refer to Drawing(s) : D92999559006 Sheet(s) 3, lines 1 to 8 3 Remove the wires of cable harness 4216VB Refer to Drawing(s) : D92999561004 Sheet(s) 5, lines 1 to 7 D92999561004 Sheet(s) 6 4 Remove the wires of cable harness 4218VB Refer to Drawing(s) : D92999561006 Sheet(s) 8 and 9, 12 5 Remove the wires of cable harness 4220VB Refer to Drawing(s) : D92999559012 Sheet(s) 7 6 Remove the wires of cable harness 4221VB Refer to Drawing(s) : D92999559014 Sheet(s) 9 and 10 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 205 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

7 Remove the wires of cable harness 4222VB Refer to Drawing(s) : D92999559016 Sheet(s) 13, lines 1 to 7 8 Remove the wires of cable harness 4223VB Refer to Drawing(s) : D92999561008 Sheet(s) 14, 15 and 18 9 Remove the wires of cable harness 4224VB Refer to Drawing(s) : D92999559020 Sheet(s) 18 10Remove the wires of cable harness 4225VB Refer to Drawing(s) : D92999561010 Sheet(s) 20, lines 1 and 2 D92999561010 Sheet(s) 21, BEFORE MOD. 11Remove the wires of cable harness 4226VB Refer to Drawing(s) : D92999559024 Sheet(s) 21 and 22, 12Remove the wires of cable harness 4227VB Refer to Drawing(s) : D92990627012 Sheet(s) 17, 18, B01 to B03, H01 to H09, W01 and W02, X01 and X02, V01 to V05 13Remove the wires of cable harness 4232VB Refer to Drawing(s) : D92999559026 Sheet(s) 25 14Remove the wires of cable harness 4233VB Refer to Drawing(s) : D92999559028 Sheet(s) 27, lines 1 to 4 15Remove the wires of cable harness 5214VB Refer to Drawing(s) : D92999559030 Sheet(s) 28, line 1 16Remove the wires of cable harness 5220VB Refer to Drawing(s) : D92990820000 Sheet(s) 1 and B01 17Remove the wires of cable harness 5224VB DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 206 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s) : D92990824002 Sheet(s) 3, B01, H01, W01 and V01 18Remove the wires of cable harness 5233VB Refer to Drawing(s) : D92990833000 Sheet(s) 1, B01, H01, W01, X01 and V01 (ap) Install the attachment parts at FR42. Refer to Kit 281132D89R00 Refer to Drawing(s) : D92491681002 Sheet(s) 7 and 9 1 Install the attachment as shown in drawing D92491681002, Sheets 7, 9 and B01.

a Install these parts : 2 L-profile D9249171020200 Item 012 2 screw NAS1096-2-7 Item 022 2 screw NAS1801-08-7 Item 031 2 nut MS21042-08 Item 041 (aq) Install the attachment parts between FR46 and FR54. Refer to Kit 281132D92R03 Refer to Drawing(s) : D92491681004 Sheet(s) 10 thru 35 1 Install the attachment as shown in drawing D92891681004, Sheets 11, 13, 15, 17, 19, 21, 23, 25 and 27, 30 thru 33 and 35.

a Install these parts : 34 bracket A9249635720200 Item 001 17 bracket D9249179320000 Item 002

5 angle D9249177520000 Item 003 6 bracket D9249178000600 Item 007 1 bracket D9249177124400 Item 009 4 bracket D9249172321200 Item 016 1 angle D9249177520200 Item 019 1 bracket D9249184620400 Item 021 1 bracket D9249177100000 Item 023 1 bracket D9249180922600 Item 026 1 nut MS21060L3 Item 027 1 bracket D9249178000800 Item 030 1 bracket D9249178001200 Item 032 228 rivet LN9198-3215BF Item 632

20 rivet LN9198-4828CF Item 648 10 rivet DIN65399-2412BF Item 725 (ar) Install the attachment parts in the bilge area between FR46 and FR54. Refer to Kit 281132D93R01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 207 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s) : D92491681006 Sheet(s) 34 thru 45 1 Install the attachment as shown in drawing D92891681006, Sheets 36 thru 45.

a Install these parts : 22 screw NAS1801-3-8 Item 001 40 screw NAS1801-08-8 Item 003

1 screw NAS1801-08-19 Item 004 23 washer NAS1149D0332K Item 005 40 washer NAS1149DN816K Item 006 22 nut MS21042L3 Item 009 16 nut MS21042L08 Item 010

1 mount E0343-01 Item 015 4 bracket D9249177121200 Item 016 1 spacer NSA5527-03-06D Item 017 1 bracket D9249177124200 Item 018 1 plate D9249175020000 Item 020 1 bracket D9249180800200 Item 024 1 bracket D9249180800400 Item 025 1 bracket D9249180900000 Item 026 1 bracket D9249180922400 Item 027 6 bracket D9249177920000 Item 028 2 bracket D9249177820200 Item 030 (as) Install the attachment parts at FR42. Refer to Kit 281132D90R00 Refer to Drawing(s) : D92891805002 Sheet(s) 16 and 19 1 Install the attachment as shown in drawing D92891805002, Sheets 17 thru 19 and B01.

a Install these parts : 8 screw NAS1801-08-10 Item 006 5 screw NAS1801-08-19 Item 012 1 screw NAS1801-08-25 Item 016 9 washer NSA935808C01 Item 151 12 washer NAS1149CN816R Item 152 12 clip-nut NSA5066-08-2 Item 231

3 spacer NSA5527-03-02 Item 302 11 spacer NSA5527-03-04 Item 306

4 spacer NSA5527-03-06 Item 310 11 clamp MS21919WCH4 Item 350

5 clamp MS21919WCH2 Item 364 6 clamp NSA935807-06 Item 376 6 clamp NSA935807-09 Item 377 (at) Install the attachment parts between FR46 and FR49. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 208 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Kit 281132D91R01 Refer to Drawing(s) : D92891805004 Sheet(s) 17 thru 49 1 Install the attachment as shown in drawing D92891805004, Sheets 17, 21, 23, 25, 27, 29, 31, 35, 36, 37, 38, 40, 42, 44, 48 and 49.

a Install these parts : 61 screw NAS1801-08-8 Item 001 127 screw NAS1801-08-19 Item 002

15 screw NAS1801-08-19 Item 003 45 screw NAS1801-3-8 Item 004 266 nut NSA5066-08-2 Item 005 5 spacer NSA5527-03-0 Item 006 61 nut MS21042L3 Item 007 24 nut MS21042L04 Item 008 196 washer NAS1149DN816K Item 009

46 washer NAS1149D0332K Item 010 24 washer NAS1149DN416K Item 011

3 bobbin NSA935510-02 Item 012 14 clamp MS21919WCH5 Item 013 11 spacer NSA5527-03-02 Item 016

1 washer NSA935808-01 Item 017 10 support ABS0731A01 Item 018 20 washer NAS1149C0332R Item 019 154 spacer NSA5527-03-01 Item 020 5 fitting NSA934710T11 Item 021 2 fitting NSA934710T14 Item 022 1 mount E0660-01 Item 023 24 screw NAS1100-04-8 Item 025 17 mount NSA935513-01 Item 027

1 mount NSA935504-03 Item 030 176 mount NSA935504-01 Item 031 1 clamp ASNA0032H052 Item 033 5 mount NSA935513-07 Item 034 41 spacer NSA5527-03-03 Item 035 1000 tie NSA935401-04 Item 036 17 nut MS21042L08 Item 037

1 guide D9249181406400 Item 038 1 guide D9249181406600 Item 039 1 screw NAS1801-3-18 Item 040 8 screw NAS1801-08-14 Item 041 1 guide Item 042 1 washer NSA935808C01 Item 043 1 guide D9249181401800 Item 047 4 receptacle NSA938004-08 Item 048 2 bracket ABS0355-03 Item 0049 20 spacer NSA5527-03-04 Item 052 16 screw NAS1801-08-10 Item 053

1 screw NAS1096-2-43 Item 055 1 screw NAS1096-2-24 Item 058 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 209 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 spacer NSA5527-03-06 Item 059 16 washer NAS1149D0363K Item 060

5 mount E0343-01 Item 063 12 screw NAS1096-3-10 Item 064

3 receptacle NSA938004-10 Item 065 3 receptacle NSA938004-16 Item 066 2 cap NSA938005-10 Item 067 1 receptacle NSA938004-20 Item 068 1 receptacle NSA938004-22 Item 069 200 sleeve NSA5539S Item 070 1 screw NAS1801-3-44 Item 072 200 tie NSA935401-03 Item 073 1 spacer NSA5527-03-03 Item 075 1 screw NAS1801-3-28 Item 076 1 bracket A9249429720200 Item 078 1 sealing A9249429620400 Item 079 1 strip NSA939510BN Item 080 1 bracket A9249436120000 Item 083 1 screw NAS1801-3-13 Item 084 23 washer D9249102520000 Item 0190 (au) Replace the cap assembly of the AFT cargo-compartment smoke-detectors (3WH, 4WH) between FR52 and FR53. Refer to Kit 281132D94R01 Refer to Drawing(s) : Refer to AMM 26-16-15 D26170100028 Sheet(s) 41 thru 42 1 Remove the existing cap assembly. Refer to AMM 26-16-15, Page block 401 2 Install : 8 nut MS21043-3 Item 014 1 cap assy D2617013302800 Item 131 (av) Seal the gaps at the installed passenger compartment floor panels. Refer to Kit 281132D32R00 Refer to Drawing(s) : D53675016000 Sheet(s) 1 and 2 1 Install this item : 1 cord DAN107-1 Item 385

and seal all gaps with sealant (Mat. No. 09-016). 2 Install after sealing this item : 1 tape ABS5093AT25 Item 387 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 210 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

3 Modify the affected carpet to get access the access panels in the passenger compartment floor panels 241JF, 251AF 251BF, 251FF, 251GF and 252BF. (aw) Install these protection covers on the roller tracks between FR53 and FR54. Refer to Kit 281132D29R00 Refer to Drawing(s) : D25572624010 Sheet(s) 17 and 18 1 Install these items :

2 cover D2557264403000 Item 001 4 screw D2557264403000 Item 020 4 screw D2557264403000 Item 021 (ax) Replace the placards at the side wall panels in the AFT cargo compartment. Refer to Kit 281132D26R01 Refer to Drawing(s) : D25572624026 Sheet(s) 35 D25572624028 Sheet(s) 36 1 Remove these items as shown in drawing D25572624026, Sheet 35, Details B, C, D and E : 1 placard D2557295021300 Item (001) Discard 1 placard D2557295021400 Item (002) Discard 1 placard D2557295028000 Item (003) Discard 1 placard D2557295028100 Item (004) Discard 4 placard D2557295024000 Item (008) Discard 1 placard D2557295022000 Item (015) Discard 2 placard A2557146821600 Item (018) Discard 11 placard D2557295024300 Item (024) Discard

8 placard D2557295030600 Item (040) Discard 1 placard D2557295228600 Item (041) Discard 2 Install these items as shown in drawing D25572624028, Sheet 36, Details B, C, D and G :

aClean the affected areas with cleaning agent (Mat. No. 11-026). b Install these items : 1 placard D2557295021300 Item 001 1 placard D2557295021400 Item 002 1 placard D2557295028000 Item 005 1 placard D2557295028100 Item 006 4 placard D2557295024000 Item 008 11 placard D2557295024300 Item 022

1 placard A2557146821200 Item 024 2 placard D2557295122600 Item 030 1 placard D2557295123600 Item 034 1 placard D2557295123800 Item 035 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 211 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 placard A2557295229400 Item 036 2 placard A2557144422600 Item 038 7 placard D2557295030600 Item 040 1 placard A2557332320000 Item 041 1 placard A2557332420000 Item 042 (ay) Install the belly fairing panels 197AB and 198GB. Refer to AMM 53-35-11 Refer to Kit 281132D04R00 Refer to Drawing(s) : D53475024000 Sheet(s) 1 1 Install this item as shown in Detail A1-1 : Refer to AMM 53-35-11, Page block 401 1 panel D5347503400200 Item 000 1 panel D5347505400200 Item 002 1 panel D5347505600400 Item 004

NOTE : Insert the key ring of the panel, Item 004, in the bracket, Item 014 installed on the web at FR50. with : 73 screw NSA5030-3-3 Item A 23 screw NSA5030-3-4 Item B 77 screw NSA5030-3-6 Item C NOTE : Items A, B and C are retained parts. (az) Install the Tie Down Points (TDP’s) in the AFT cargo compartment. Refer to Kit 281132D20R02 Refer to Drawings : D25572624000 Sheet(s) 1 thru 3 1 Install these items as shown in drawing D2557624000, Sheet 2, Section 2-2 and Sheet 3 Sections C3-C3, H3-H3 and M3-M3 : 3 TDP DAN152-1 Item 509 1 TDP D2557206226000 Item 517 9 TDP D2557206286000 Item 530 1 TDP D2557206296000 Item 531

with : 12 screw NAS1102-3-10 Item 510 18 screw NAS1102-3-12 Item 511 18 screw NAS1102-3-14 Item 512 46 nut NAS1726-3E Item 513 15 screw NAS1102-3-16 Item 514 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 212 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

5 screw NAS1102-3-18 Item 515 (ba) Replace Tie Down Point (TDP) and the stanchion bracket in the ceiling area of the AFT cargo compartment. Refer to Kit 281132D28R01 Refer to Drawings : D25572624004 Sheet(s) 6 1 At FR52A, remove as shown in drawing D25572624004, Sheet 6, Section C8-C8. 1 bracket D2557205820000 Item (500) Discard 2 screw NAS1102-3-18 Item (501) Discard 2At FR53, remove as shown in drawing D255762400, Sheet 6. 1 TDP DAN152-1 Item (502) Discard 2 screw NAS1102-3-18 Item (501) Discard 3At FR52A, install as shown in drawing D2557624004, Sheet 6. 1 TDP DAN152-1 Item 502

with : 2 screw NAS1102-3-18 Item 501 4At FR53, install as shown in drawing D255762400, Sheet 6, Section C8-C8. 1 bracket D2557205820000 Item 500

with : 2 screw NAS1102-3-18 Item 501 (bb) Install the nets in the AFT cargo compartment. Refer to AMM 25-55-00 Refer to Kit 281132D27R01 Refer to Drawings : D25572624002 Sheet(s) 4 and 5 1 Install these items : Refer to AMM 25-55-00, Page block 401 1 net AC40-0253621 Item 520 1 stanchion HA70-0214006 Item 521 1 net AC40-0217000 Item W1 1 net AC40-0217500 Item W2 1 net AC40-0209900 Item W3

NOTE : Items W1, W2 and W3 are retained parts. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 213 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(bc) Install the brackets for the fuel drain/vent systems between FR46 and FR54. Refer to Kit 281132D17R00 Refer to drawing : D28270982004 Sheet(s) 12 1 Install the brackets between FR46 and FR47 as shown in Details A12-12, Y12-12 and Z12-12 :

a Remove the existing fasteners from the affected areas. b Put these items in position : 2 angle D2827094222800 Item 102 2 bracket D2827094200400 Item 124

c Transfer drill the holes, drill the additional holes and open them to final dimension. d Install these items : 2 angle D2827094222800 Item 102 2 bracket D2827094200400 Item 124 with : 6 rivet LN9198-3212BF Item 032 8 pin DAN7-6-8Y Item 041 8 collar DAN12-6Y Item 042 2 Install the brackets at FR47 and FR48 as shown in Details A12-13, B12-13 and C12-13 : Refer to drawing : D28270982004 Sheet(s) 13

a Put this item in position : 3 bracket F5397461900600 Item 100

b Drill the rivet holes.

c Install this item : 3 bracket F5397461900600 Item 100 with : 6 rivet LN9198-4012BF Item 040 3 Install the brackets at FR48 and FR49 as shown in Details X14-14, Y14-14 and Z14-14 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 214 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to drawing : D28270982004 Sheet(s) 14

a Put these items in position : 1 bracket D2827098300000 Item 104 1 bracket D2827098300200 Item 106 1 bracket D2827098325200 Item 125

b Drill the rivet holes.

c Install these items : 1 bracket D2827098300000 Item 104 1 bracket D2827098300200 Item 106 1 bracket D2827098325200 Item 125 with : 6 rivet LN9198-4012BF Item 040 4 Install the brackets at FR49 as shown in Details B26-26, D26-26 and B22-22 : Refer to drawing : D28270982004 Sheet(s) 22 and 26

a Put these items in position : 2 bracket D2827098320800 Item 117 2 bracket D2827098321000 Item 118 1 angle D2827098321200 Item 119

b Drill the rivet holes.

c Install these items : 2 bracket D2827098320800 Item 117 2 bracket D2827098321000 Item 118 1 angle D2827098321200 Item 119 with : 14 rivet LN9198-4012BF Item 040 5 Install the angles at FR50, FR51, FR52 and FR53 as shown in Details W23-27, X23-27, Y23-27 and Z23-27 : Refer to drawing : D28270982004 Sheet(s) 27

a Put these items in position : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 215 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 angle D2827098327600 Item 137 1 angle D2827098327800 Item 138 1 angle D2827098328000 Item 139 1 angle D2827098328200 Item 140

b Drill the rivet holes.

c Install these items : 2 angle D2827098327600 Item 137 1 angle D2827098327800 Item 138 1 angle D2827098328000 Item 139 1 angle D2827098328200 Item 140 with : 8 rivet LN9198-4012BF Item 040 6 Install the angles at FR50 and FR51 as shown in Sections G24-G20 and F24-F17 : Refer to drawing : D28270982004 Sheet(s) 17 and 20

a Put this item at FR51 in position : 2 angle D2827094220400 Item 113

b Put this item at FR50 ad FR51 in position : 2 angle D2827094222200 Item 116

c Drill the rivet holes. d Install these items : 2 angle D2827094220400 Item 113 2 angle D2827094222200 Item 116 with : 12 rivet LN9198-4012BF Item 040 7 Install the brackets at FR52 and FR53 as shown in Sections A17-A17, C17-C17 and B25-B25 : Refer to drawing : D28270982004 Sheet(s) 17 and 25

a Put this item at FR52 in position : 2 angle D2827094221800 Item 115 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 216 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

b Put this item at FR52 and FR53 in position : 2 bracket D2827098323200 Item 127

c Drill the rivet holes. d Install these items : 2 angle D2827094221800 Item 115 2 bracket D2827098323200 Item 127 with : 8 rivet LN9198-4012BF Item 040 8 Install the bracket between FR51 and FR52 as shown in Section B17-B17 : Refer to drawing : D28270982004 Sheet(s) 17

a Put this item in position : 1 bracket D2827098300800 Item 126

b Drill the rivet holes.

c Install this item : 1 bracket D2827098300800 Item 126 with : 6 rivet LN9198-4012BF Item 040 9 Install the brackets at FR53 and FR54 as shown in Sections A25-A25, C25-C25, A19-A19 and D19-D19 : Refer to drawing : D28270982002 Sheet(s) 19 and 25

a Put this item at FR53 in position : 3 angle D2827094221400 Item 112

b Put this item at FR54 in position : 1 bracket D2827098326000 Item 135

c Put this item at FR53 and FR54 in position : 1 bracket D2827098326200 Item 136

d Drill the rivet holes. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 217 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

e Install these items : 3 angle D2827094221400 Item 112 1 bracket D2827098326000 Item 135 1 bracket D2827098326200 Item 136 with : 10 rivet LN9198-4012BF Item 040 10Install the brackets between FR53 and FR54 as shown in Section D24-D20 : Refer to drawing : D28270982004 Sheet(s) 20

a Put these items at FR53 and FR54 in position : 1 bracket D2827098324200 Item 132 1 bracket D2827098324400 Item 133

b Drill the rivet holes.

c Install these items : 1 bracket D2827098324200 Item 132 1 bracket D2827098324400 Item 133 with : 4 rivet LN9198-4012BF Item 040

d Put these items between FR53 and FR54 in position : 1 bracket D2827098323800 Item 130 1 bracket D2827093521000 Item 131 1 bracket D2827098324000 Item 134

e Drill the rivet holes. f Install these items : 1 bracket D2827098323800 Item 130 1 bracket D2827093521000 Item 131 1 bracket D2827098324000 Item 134 with : 6 screw NAS1096-3-8 Item 004 6 washer NAS1149C0332R Item 005 6 nut NAS1726C3E Item 006 2 rivet LN9198-4012BF Item 040 (bd) Install the ACT pressurization system between FR51 and FR53. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 218 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Kit 281132D02R00 Refer to Drawing(s) : D28270991000 Sheet(s) 1 thru 3 1 From the tee at FR51 shown in Sheet 1, remove : 1 cap MS21914-10D Item (094) Retain

NOTE : The cap was installed with Kit 281132D16R01, drawing D28270975004, Item 094. 2 Install these items between FR50 and FR53 as shown in Sheet 1 : 1 tube D2827097902600 Item 000

with : 1 elbow MS21908J10 Item 091 1 nut AN924-10J Item 034 1 washer NAS1149C1432R Item 035 3 Install these items as shown in Sheet 1 and Section I1-3: 1 nut NAS1726C3E Item 070 1 washer NAS1149C0332R Item 073 1 clamp MS21919 WDE10 Item 079 1 clamp NSA5575-8A Item 081 1 bonding lead E0090-10-125NN Item 083 1 bolt NAS1303-2 Item 088 1 nut NAS1726-3E Item 089 1 washer NAS1149D0332H Item 090 1 screw NAS1096-3-9 Item 097 4 Between FR52 and FR53, on tube, Item 000, install as shown in Detail II1-3 : 1 cap MS21914-10D Item (094) Retained (be) Install the ACT pressurization system between FR48 and FR54. Refer to Kit 281132D16R01 Refer to Kit 281132B01R00 Refer to Drawing(s) : D28270975004 Sheet(s) 8, 10, 11, 13 thru 15 1 Install these items at the crossbeam at FR54 as shown in Section D8-D8 : 1 coupling A2827092300000 Item 050 1 nut AN924-10J Item 074 1 tee MS21909J10 Item 075 1 washer NAS1149F1432P Item 076

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 219 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 Install these items at the crossbeam at FR54 as shown in drawing D28270975004, Sheet 13 and Sections A13-A8 and C8-C8 : 1 tube D2827097902000 Item 021 1 valve HTE490005 Item 042 1 actuator HTE200002-1 Item 043 1 valve HTE920007-001 Item 044 1 clamp HTE8002 Item 045

NOTE : The Items 042, 043, 044 and 045 are contained in Kit 281132B01R00. 3 Install these items as shown in Sections A13-A8, B8-B8 and C8-C8 : 1 nut NAS1726C3E Item 070 1 screw NAS1096-3-8 Item 071 1 washer NAS1149C0332R Item 073 1 clamp NSA5575-8A Item 081 1 strap E0090-10-125NN Item 083 1 bolt NAS1303-2 Item 088 1 nut NAS1726-3E Item 089 2 washer NAS1149F0332P Item 103 4 Install these items with adhesive (Mat. No. 08-010)as shown in Section A13-A8 : 1 placard D2827094420000 Item 200 1 placard D2827094420200 Item 202 1 placard D2827094420400 Item 204 1 placard D2827094421200 Item 212 5 Install these items at the crossbeam at FR53 as shown in Section B14-B14 : 1 coupling A2827092300000 Item 050 1 nut AN924-10J Item 074 1 tee MS21909J10 Item 075 1 washer NAS1149F1432P Item 076 6 Install these items at the crossbeam at FR53 as shown in drawing D28270975004, Sheet 13 and Section B13-B14 : 1 tube D2827097901800 Item 019 1 valve HTE490005 Item 047

NOTE : The Item 047 is contained in Kit 281132B01R00. 7 Install this item between FR53 and FR54 as shown in Section E13-E11 : 1 valve PAS148-133A Item 046

with : 2 nut NAS1726C3E Item 070 2 washer NAS1149C0332R Item 073 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 220 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 screw NAS1096-3-12 Item 098

NOTE : The Item 046 is contained in Kit 281132B01R00. 8 Install these items as shown in Section B13-B14 : 1 clamp NSA5575-8A Item 081 1 strap E0090-10-125NN Item 083 1 bolt NAS1303-2 Item 088 1 nut NAS1726-3E Item 089 2 washer NAS1149F0332P Item 103 9 Install these items with adhesive (Mat. No. 08-010)as shown in Section B13-B14 : 1 placard D2827094420600 Item 206 1 placard D2827094420800 Item 208 10Install this item between FR53 and FR54 as shown in drawing D28270975004, Sheet 13 and Section E13-E11 : 1 hose 1451515F0150-18 Item 040

with : 1 nut NAS1726C3E Item 070 1 screw NAS1096-3-8 Item 071 1 washer NAS1149C0332R Item 073 1 clamp MS21919WCH15 Item 101 11Install these items as shown in drawing D28270975002, Sheet 13 and Sections B13-B14, E13-E11, G13-G15, H13-H15, K13-K15 and L13-L15 : 1 tube D2827098000800 Item 005 1 tube D2827098001400 Item 011 1 tube D2827098002400 Item 220 1 tube D2827098002600 Item 222

with : 13 nut NAS1726C3E Item 070 10 screw NAS1096-3-8 Item 071 13 washer NAS1149C0332R Item 073 11 clamp MS21919WDE4 Item 080

4 clamp NSA5575-2 Item 082 4 lead E0090-18-100NN Item 084 4 screw NAS1096-1-8 Item 085 4 nut MS21042-06 Item 087 3 screw NAS1096-3-9 Item 097 8 washer NAS1149FN616P Item 104 12Install these items between FR48 and FR49 as shown in Section G13-G15 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 221 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 filter A2163302000000 Item 027 1 inlet A2151034520000 Item 028 1 nut AN924-4D Item 092 13Install these items as shown in drawing D28270975004, Sheet 13, Detail I14-14 and Sections C13-C10 and D13-D11 : 1 tube D2827097901000 Item 016 1 tube D2827097901600 Item 017 1 tube D2827097904000 Item 026 1 tube D2827097902400 Item 025

with : 6 nut NAS1726C3E Item 070 3 screw NAS1096-3-8 Item 071 6 washer NAS1149C0332R Item 073 1 conduit TSTMNR503-0 Item 077 2 tie NSA935401-03 Item 078 6 clamp MS21919WDE10 Item 079 4 clamp NSA5575-8A Item 081 4 strap E0090-10-125NN Item 083 4 bolt NAS1303-2 Item 088 4 nut NAS1726-3E Item 089 3 screw NAS1096-3-9 Item 097 8 washer NAS1149F0332P Item 103

NOTE : Cut the conduit, Item 077, in two pieces. 14Install this item between FR51 and FR52 as shown in drawing D28270975004, Sheet 13 and Section C13-C10 : 1 filter QB0566 Item 041

with : 1 union MS21902D10 Item 030 1 packing NAS1612-10 Item 031 4 nut NAS1726C4E Item 093

NOTE : The Item 041 is contained in Kit 281132B01R00. 15Install this item with adhesive (Mat. No. 08-010) as shown in Section C13-C10 : 1 placard D2827094421000 Item 210 16Install this item as shown in drawing D28270975004, Sheet 7 and Sections D13-D11 and F13-F11 : 1 tube D2827097901400 Item 015

with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 222 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 nut NAS1726C3E Item 070 2 screw NAS1096-3-8 Item 071 2 washer NAS1149C0332R Item 073 1 conduit TSTMNR503-0 Item 077 2 tie NSA935401-03 Item 078 2 clamp MS21919WDE10 Item 079 17Install these items as shown in drawing D28270975004, Sheet 7 and Details X13-11, Y13-11 and Z13-11 : 1 tube D2827097901200 Item 013 1 elbow MS21908J10 Item 091 1 tee MS21905J10 Item 099

with : 2 nut NAS1726C3E Item 070 1 screw NAS1096-3-8 Item 071 2 washer NAS1149C0332R Item 073 2 clamp MS21919WDE10 Item 079 2 clamp NSA5575-8A Item 081 1 strap E0090-10-125NN Item 083 2 bolt NAS1303-2 Item 088 2 nut NAS1726-3E Item 089 2 cap MS21914-10D Item 094 1 nut AN924-10J Item 095 1 washer NAS1149C1432R Item 096 1 screw NAS1096-3-9 Item 097 1 strap E0090-10-160NN Item 102 4 washer NAS1149F0332P Item 103 (bf) Install the equipment for the ACT pressurization system between FR48 and FR54. Refer to Kit 281132B01R00 Refer to drawings : D28270975004 Sheet(s) 7 thru 12 1 Install the equipment for the ACT pressurization system between FR48 and FR54.

a Install these items at the crossbeam at FR54 as shown in drawing D28270975004, sheet 7 and Sections A7-A8 and C8-C8 : 1 Filter-Air. Assembly QB0566 Item 41 1 Valve-Non-Return HTE490005 Item 42 1 Actuator-Valve, Single Motor HTE200002-1 Item 43 1 Valve-Air Shut Off HTE920007-001 Item 44 1 Clamp-V Band HTE8002 Item 45 1 Valve-Pressure, Reducing PAS148-133A Item 46 1 Valve-Non-Return HTE490005 Item 47 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 223 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(bg) Install the Relay box in the forward avionics compartment. Refer to Kit 281132B02R00 Refer to drawings : D92355000 Sheet(s) 1 D92556025 Sheet(s) 1 and 3 1 Install this item in the forward avionics compartment : 1 Relay box D9255602500400 (bh) Remove and discard the refuel/defuel panel mounting assembly in the belly fairing, zone 192. Refer to Kit 281132B02R00, Kit 281132B03R00 and Kit 281132B04R00 Refer to drawings : D92450032 Sheet(s) 6 and 7 D92450115 Sheet(s) 1 and 2 D92550025 Sheet(s) 1 D92550032 Sheet(s) 1 and 2 1 Remove and discard the refuel/defuel panel mounting assembly in the belly fairing, zone 192.

a Remove the pre-select unit 5QT (Refer to AMM 28-42-21, Page block 401). b Remove the refuel/defuel control panel 800VU (Refer to AMM 28-25-55, Page block 401).

c Remove the fuel quantity indicator unit 6QT (Refer to AMM 28-42-22, Page block 401). dTemporarily remove all attachments and associated fittings from the panel mounting-assembly.

e Remove the panel mounting-assembly, retain the attachment bolts for installation of the new panel mounting-assembly in the same position. 2 Install additional wiring between zone 192 and 132

a Install the wires shown on lines 1 thru 14 (Refer to Figure 2 Sheet 1). supplied in : 1 Bundle D92400000647 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. bCut the wires to the necessary length, crimp the terminals and connect them. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 224 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

c Attach the wires with tie-wraps as necessary. d Do an intrinsically safe continuity test of the new wires. 3 Install the new refuel/defuel panel mounting assembly in the belly fairing, zone 192.

a Use a non-metallic spatula to remove the sealant and clean the areas with Solvent (Mat. No. 11-026). b Use sealant (Mat. No. 09-001) to wet assemble the refuel panel mounting-assembly and position it in the belly fairing. Use the attachment bolts retained from removal and install : 1 Panel Assy-Mounting D9245011500600

c Install all the attachment and associated fittings removed from the panel mounting-assembly. d Install the pre-select unit 5QT (Refer to AMM 28-42-21, Page block 401).

e Install the refuel/defuel control panel 800VU (Refer to AMM 28-25-55, Page block 401). 1 Panel Assy-Refuel D9255003200400

f Install the fuel quantity indicator unit 6QT (Refer to AMM 28-42-22, Page block 401). g Install the refuel panel assembly 801VU Refer to drawing D92550025 and install this item : 1 Panel Assy-Refuel D9255002500200 (2) Config. 01 AI-F Part 281132A00001 A00 Sheet(s) 01 281132A00001 A00 Sheet(s) 02 281132A00001 A00 Sheet(s) 03 281132A00001 A00 Sheet(s) 04 (a) Install the doublers on the upper surface panels Refer to Kit 281132A01R01 281132A01001 A00 Sheet(s) 01 281132A01001 A00 Sheet(s) 02 281132A01001 B00 Sheet(s) 03 281132A01002 A00 Sheet(s) 01 NOTE : Remove the finch paint and the paint protection from the extrados panel between Y=+254 and Y=-254 and between FR36 and FR42. Do not use a metallic tool. Do not cause damage to the head of the rivets, (Refer DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 225 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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. 1 Drill one hole to a diameter of 64 mm (2.519 in.) and one hole to a diameter of 74 mm (2.913 in.), (Refer to drawing 281132A01001, Sheets 1 and 2). 1 Loft D5713032000095 2 Install : 281132A01001 B00 Sheet(s) 03 Item 0 1 Doubler D5713304820004

Item 1 1 Doubler D5713031920000

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

Item 23 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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5 Pin-Hi Lok NSA5357-4-8

Item 30 57 Collar NSA5330-6 Item 35 49 Nut ASNA2528-3 Item 40 13 Collar NSA5330-8 3 Install : 281132A01002 A00 Sheet(s) 01 Item 0 1 Bracket Assy D5791332400000

Item 1 1 Bracket Assy D5791332300000

Attach with : Item 10 2 Bolt EN6115V3-5

Item 11 4 Nut ASNA2528-3

Item 12 2 Bolt EN6115V3-7 (b) Install the brackets on the upper surface panels Refer to Kit 281132A01R01 281132A01003 A00 Sheet(s) 01 281132A01003 A00 Sheet(s) 02 281132A01003 A00 Sheet(s) 03 281132A01003 B00 Sheet(s) 04 Item 1 1 Support Assy D5791049500095 Item 2 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 227 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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

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

4 Rivet ASNA2050DCJ3215 Item 100 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 228 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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

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

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

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

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

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

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

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

22 Collar NSA5330-6 Item 130

18 Collar NSA5330-8 (c) Install the rod on the upper surface panels Refer to Kit 281132A01R01 281132A01004 A00 Sheet(s) 01 Item 0 1 Rod D2821334100000 Item 4 1 Bracket D2821334220000 Attach with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Item 12

4 Bolt NAS6603-4 Item 14

2 Bolt NAS6604-9 Item 20

4 Nut NSA5050-3 Item 22

2 Nut NSA5050-4 Item 24

4 Washer ASNA2397-10L Item 26

2 Washer ASNA2397-416L (d) Install the bracket on FR42 Refer to Kit 281132A02R02 281132A02001 A00 Sheet(s) 01 NOTE : Remove the finch paint and the paint protection in the center tank. Do not use a metallic tool. Do not cause damage to the head of the 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. Item 12 1 Corner Plate A2823301800202 Attach with : Item 32

2 Rivet ASNA2050DCJ3215 (e) Install the bracket above FR42 Refer to Kit 281132A02R02 281132A02002 A00 Sheet(s) 01 281132A02002 A00 Sheet(s) 02 281132A02002 B00 Sheet(s) 03 Item 0 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 230 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Support D5791041820095 Attach with : Item 10 Fuel Tank Sealant Polysulfid (Mat. No. 09-002) Item 60

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

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

2 Collar NSA5330-8 Item 80

2 Collar NSA5330-10 (f) Install the brackets on the lower surface panels Refer to Kit 281132A02R02 281132A02003 A00 Sheet(s) 01 281132A02003 A00 Sheet(s) 02 281132A02003 B00 Sheet(s) 03 Item 1 1 Machined Bracket D5791040320095 Item 2 1 Support Assy D5791040500095 Item 3 1 Support Assy D5791040400095 Item 4 1 Machined Bracket D5791040120095 Item 5 1 Machined Bracket D5791040020095 Item 6 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 231 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Machined Bracket D5791040220095 Item 7 1 Machined Bracket D5791040820095 Item 8 1 Machined Bracket D5791040920095 Item 9 1 Machined Bracket D5791040620095 Item 10 1 Machined Bracket D5791040720095 Item 11 1 Machined Bracket D5791041020095 Attach with : Item 20 Fuel Tank Sealant Polysulfid (Mat. No. 09-002) Item 44

4 Bolt NAS6603-4 Item 62

4 Nut NSA5050-3 Item 157

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

5 Pin-Hi Lok NSA5357-4-10 Item 159

17 Pin-Hi Lok NSA5357-4-11 Item 160 1 Pin-Hi Lok NSA5357-4-12 Item 162 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 232 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Pin-Hi Lok NSA5357-5-13 Item 165

31 Collar NSA5330-8 Item 170 1 Collar NSA5330-10 (g) Install the rod and the plate on the lower surface panels Refer to Kit 281132A02R02 281132A02004 A00 Sheet(s) 01 281132A02004 A00 Sheet(s) 02 Item 2 1 Rod D2821334100200 Item 6 1 Bracket D2821040220000 Item 8 1 Plate D2821040120000 Attach with : Item 10

8 Bolt NAS6603-2 Item 12

4 Bolt NAS6603-4 Item 14

2 Bolt NAS6604-9 Item 20

4 Nut NSA5050-3 Item 22

2 Nut NSA5050-4 Item 24

12 Washer ASNA2397-10L DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 233 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 26

2 Washer ASNA2397-416L (h) Install the Additional Center Tank (ACT) door Refer to Kit 281132A03R01 281132A03001 A00 Sheet(s) 01 281132A03002 A00 Sheet(s) 01 281132A03002 A00 Sheet(s) 02 1 Remove : 281132A03001 A00 Sheet(s) 01 1 Door Assy D5713019400200 1 Screw Item (4) Discard 1 Washer Item (8) Discard 15 Washer Item (5) Discard 15 Screw Item (6) Discard 15 Washer Item (7) Discard 2 Install : 281132A03002 A00 Sheet(s) 01 281132A03002 A00 Sheet(s) 02 1 Door Assy D5713323000000

Item 0 1 Fairing D5713334000000

Item 1 1 Intrados Fitting D5713334600000

Item 2 1 Fitting D5713334500000

Item 3 1 Fitting D5713334400000

Attach with : Item 30 Fuel Tank Sealant Polysulfid (Mat. No. 09-002) Item 6 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 234 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

8 Washer A5713052120300

Item 10 3 Bolt NAS6603-2

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

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

Item 22 6 Bolt NAS6604-3

Item 40 6 Washer ASNA2397D416L (i) Install the equipment on the ACT door Refer to Kit 281132A03R01 281132A03003 B00 Sheet(s) 01 281132A03003 A00 Sheet(s) 02 281132A03003 A00 Sheet(s) 03 281132A03003 A00 Sheet(s) 04 281132A03003 B00 Sheet(s) 05 1 Install the pressure switch 2QH : 281132A03003 A00 Sheet(s) 02 Item 0 1 Pressure Switch HTE690045

Attach with : Item 30 Zinc Chromate General Purpose (Mat. No. 05-002) DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Item 8 1 Bulkhead D2821067800000

Item 10 1 Plug A2823260820000

Item 12 1 Safety Valve A2823260500000

Item 18 3 Packing NSA8200-6

Item 20 1 O-Ring NSA8203-019

Item 22 4 Bolt NAS6603-5

Item 24 4 Washer-Sealing ASNA2055-03

Item 26 4 Nut NSA5050-3

Item 28 1 M Wire-Lock MS20995C32 2 Install the fuel pump 1QH and the mounting plate 163QM : 281132A03003 A00 Sheet(s) 03 Item 0 1 Fuel Pump 568-1-27170-002

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

Attach with : Item 50 Grease High Pressure (Mat. No. 04-004) DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 236 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 10 1 Pin A2821064820040

Item 12 1 Insert A2821064620000

Item 14 1 Spring A2821064720000

Item 18 1 O-Ring NSA8203-113

Item 22 1 O-Ring NSA8203-167

Item 24 1 O-Ring NSA8203-224

Item 26 1 O-Ring NSA8203-226

Item 28 2 Bonding Lead E0088-10-100

Item 29 4 Bolt NAS6603-1

Item 30 6 Bolt NAS6604-7

Item 32 1 Bolt NAS6604-20

Item 34 1 Seal Washer NSA5112-04

Item 36 6 Washer ASNA2397-416

Item 38 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 Washer ASNA2397-416L

Item 39 4 Washer ASNA2397D10L

Item 40 1 Nut NSA5050-4

Item 42 2 Nut NSA5050-3

Item 48Wire-Lock MS20995C32 3 Install the refuel valve 41QU and the canister 164QM : 281132A03003 A00 Sheet(s) 04 Item 0 1 Canister 1158000-15

Item 2 1 Refuel Valve 1158000-21

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

Item 8 4 Screw NAS1154-10

Item 10 1 Screw NAS1801-06-6

Item 11 1 Screw NAS1801-3-6

Item 12 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 238 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Washer ASNA2397-6L

Item 13 1 Washer ASNA2397-10L

Item 14 1 Nut MS21042-06

Item 16 4 Nut NAS1726C4E

Item 22 1 Bonding Lead E0088-16-125 4 Install the actuator 6QH and the valve 165QM : 281132A03003 B00 Sheet(s) 05 Item 0 1 Valve HTE900135

Item 2 1 Actuator HTE190001-2

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

Item 6 1 O-Ring NSA8203-154

Item 8 6 Screw NAS1153-4

Item 13 1 Screw NAS1801-06-6

Item 17 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 239 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Washer ASNA2397-6L

Item 16 4 Nut NAS1726C4E

Item 18 1 Nut MS21042L06

Item 22 1 Lead-Bonding E0088-16-100

Item 24Wire-Lock MS20995C32 (j) Replace the Fuel Quantity Indicator (FQI) 6QT (Refer to AMM 28-42-22, Page block 401) 1 Remove : 1 Fuel Quantity Indicator 1407KID02-03 2 Install : 1 Fuel Quantity Indicator 1418KID01-03 (k) Modify the pipes in the center tank Refer to Kit 281132A04R01 281132A04001 A00 Sheet(s) 01 281132A04001 A00 Sheet(s) 02 281132A04001 A00 Sheet(s) 03 281132A04002 A00 Sheet(s) 01 281132A04002 A00 Sheet(s) 02 281132A04002 A00 Sheet(s) 03 281132A04002 A00 Sheet(s) 04 1 Remove : 281132A04001 A00 Sheet(s) 01 281132A04001 A00 Sheet(s) 02 281132A04001 A00 Sheet(s) 03 Item (2) 1 Pipe Assy D2821008001300

with : Item (5) DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 240 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 O-ring Discard

Items (4) and (9) 2 Screw Retain

Items (8) and (10) 2 Washer Retain 2 Install : 281132A04002 A00 Sheet(s) 01 281132A04002 A00 Sheet(s) 02 281132A04002 A00 Sheet(s) 03 281132A04002 A00 Sheet(s) 04 Item 6 1 Pipe Assy D2821333900000

Item 120 1 Machined Tee D2821331020000

Item 12 1 Pipe Assy D2821333900100

Item 5 4 O-Ring NSA8203-226

Attach with : Item 16 2 Bolt NAS6603-2

Item 18 2 Nut NAS1726-3E

Item 110 4 Bolt NAS6604-5

Item 112 4 Washer ASNA2397-416L

Item 114 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 241 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

4 Nut NAS1726-4E

Items (4) and (9) 2 Screw

Items (8) and (10) 2 Washer

NOTE : Items (4), (9), (8) and (10) were retained at removal. (l) Install the ACT pipes in the center tank Refer to Kit 281132A04R01 281132A04003 A00 Sheet(s) 01 281132A04003 A00 Sheet(s) 02 281132A04003 A00 Sheet(s) 03 281132A04003 A00 Sheet(s) 04 281132A04003 A00 Sheet(s) 05 281132A04003 B00 Sheet(s) 06 281132A04003 B00 Sheet(s) 07 281132A04004 A00 Sheet(s) 01 281132A04005 A00 Sheet(s) 01 281132A04006 A00 Sheet(s) 01 281132A04007 A00 Sheet(s) 01 281132A04008 A00 Sheet(s) 01 281132A04009 A00 Sheet(s) 01 281132A04010 A00 Sheet(s) 01 281132A04011 A00 Sheet(s) 01 281132A04011 A00 Sheet(s) 02 281132A04012 A00 Sheet(s) 01 281132A04013 B00 Sheet(s) 01 1 Install : 281132A04003 A00 Sheet(s) 01 281132A04003 A00 Sheet(s) 02 281132A04003 A00 Sheet(s) 03 281132A04003 A00 Sheet(s) 04 281132A04003 A00 Sheet(s) 05 281132A04003 B00 Sheet(s) 06 281132A04003 B00 Sheet(s) 07 Item 20 1 Pipe Assy D2821333900900

Item 22 1 Pipe Assy D2821333900300

Item 24 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 Pipe Assy D2821333900400

Item 28 1 Pipe Assy D2821333900600

Item 30 1 Pipe Assy D2821333900700

Item 32 1 Pipe Assy D2821333901000

Item 34 1 Sleeve A2821038600000

Item 36 1 Sleeve D2821333800000

Item 38 1 Pipe Assy D2821334800000

Item 40 1 Pipe Assy D2821334900000

Item 42 1 Pipe Assy D2821335000000

Item 44 1 Pipe Assy D2821338500000

Item 46 1 Pipe Assy D2821335800000

Item 50 1 Restrictor D2821336720240

Attach with : Item 51 1 Clamp NSA5516A04NF

Item 52 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 243 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Union MS21902D4

Item 53 1 Strip-Bonding ASNA0182-1DA

Item 55 2 Nut ABS0107-150

Item 56 3 Nut ABS0107-200

Item 57 2 Ring-Retaining NSA840003-150

Item 58 3 Ring-Retaining NSA840003-200

Item 60 1 Packing NSA8200-4

Item 62 1 O-Ring NSA8203-215

Item 64 12 O-Ring NSA8203-222 Item 66 5 O-Ring NSA8203-226

Item 68 2 Screw NAS1801-06-10

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

Item 73 4 Bolt NAS6603-5 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Item 74 4 Bolt NAS6603-7

Item 76 2 Bolt NAS6604-2

Item 77 4 Bolt NAS6604-3

Item 78 2 Nut MS21042L06

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

Item 83 2 Washer ASNA2397-6L

Item 84 8 Washer ASNA2397-10L

Item 90 1 Bonding Lead E0088-10-160

Item 92 2 Bonding Lead E0088-10-200

Item 93 1 Bonding Lead E0088-10-280 2 Install : 281132A04004 A00 Sheet(s) 01 Item 0 1 Machined Tee D2821331620000

Attach with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 245 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 10 6 Bolt NAS6604-5

Item 12 6 Washer ASNA2397-416L

Item 14 6 Nut NAS1726-4E 3 Install : 281132A04005 A00 Sheet(s) 01 Item 0 1 Machined Elbow D2821332220000

Attach with : Item 10 2 Bolt NAS6604-4

Item 12 2 Washer ASNA2397-416L

Item 14 2 Nut NAS1726-4E 4 Install : 281132A04006 A00 Sheet(s) 01 Item 0 1 Elbow-Moulded A2821120120000

Attach with : Item 10 2 Bolt NAS6604-4

Item 12 2 Washer ASNA2397-416L

Item 14 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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2 Nut NAS1726-4E 5 Install : 281132A04007 A00 Sheet(s) 01 Item 0 1 Machined Elbow D2821332620000

Attach with : Item 10 2 Bolt NAS6604-5

Item 12 2 Washer ASNA2397-416L

Item 14 2 Nut NAS1726-4E 6 Install : 281132A04008 A00 Sheet(s) 01 Item 0 1 Elbow Assy D2821332900000

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

Item 10 4 Bolt NAS6603-4

Item 12 4 Washer ASNA2397D10L 7 Install : 281132A04009 A00 Sheet(s) 01 Item 0 1 Machined Elbow D2821333220000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 247 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 2 1 Machined Elbow D2821333420000

Item 4 1 Restrictor D2821336621240

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

Item 10 8 Bolt NAS6603-3

Item 12 8 Washer ASNA2397-10L 8 Install : 281132A04010 A00 Sheet(s) 01 Item 0 1 Valve-Non Return 9843144M

Item 1 1 Flange A2821079520000

Item 2 1 Restrictor D2821335621800

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

Item 4 1 Ring-Retaining NSA840003-200

Item 5 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 248 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

3 O-Ring NSA8203-226

Item 8 4 Bolt NAS6604-12

Item 9 4 Nut NAS1726-4E

Item 11 2 Bonding Lead E0088-10-100

Item 12 2 Nut NAS1726-3E

Item 13 1 Bolt NAS6603-2

Item 14 1 Bolt NAS6603-1

Item 17 1 Bonding Lead E0088-10-200

Item 19 2 Washer ASNA2397-10L 9 Install : 281132A04011 A00 Sheet(s) 01 281132A04011 A00 Sheet(s) 02 Item 54 1 Valve 365A02

Item 35 1 Sleeve Assy D2821336300000

Attach with : Item 55 2 Nut ABS0107-150 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 249 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 57 2 Ring-Retaining NSA840003-150

Item 61 1 Packing NSA8200-5

Item 64 2 O-Ring NSA8203-222

Item 70 2 Bolt NAS6603-2

Item 80 2 Nut NSA5050-3 10Install : 281132A04012 A00 Sheet(s) 01 Item 0 1 Tee D2821331320000

Attach with : Item 10 4 Bolt NAS6604-5

Item 12 4 Washer ASNA2397-416L

Item 14 4 Nut NAS1726-4E 11Install : 281132A04013 B00 Sheet(s) 01 Item 0 1 Machined Elbow D2821331920000

Item 2 1 Sleeve D2821336500000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 250 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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

Item 10 4 Bolt NAS6603-7

Item 12 4 Washer ASNA2397-416L (m) Install the transfert elbow Refer to Kit 281132A05R00 281132A05001 A00 Sheet(s) 01 Item 0 1 Transfert Elbow Assy D2821330700000 Item 2 1 Nutplate Assy D2821334700000 Item 4 1 Nutplate Assy D2821337500000 Item 8 1 O-Ring NSA8203-148 Attach with : Item 10

6 Bolt NAS6604-9 Item 12

6 Washer ASNA2397-416L Item 14 1 Bolt NAS6603-2 Item 16 1 Washer ASNA2397-10L DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 251 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(n) Install the air ventilation elbow Refer to Kit 281132A05R00 281132A05002 A00 Sheet(s) 01 Item 0 1 Elbow Assy D2821337700041 Item 2 1 Nutplate Assy D2821334600000 Item 4 1 Nutplate Assy D2821337600000 Item 14 1 Filter D2821337800000 Item 16 1 Plate D2821337120000 Item 8 1 O-Ring NSA8203-152 Attach with : Item 10

6 Bolt NAS6604-8 Item 12

6 Washer ASNA2397-416L Item 18

4 Bolt NAS6603-2 Item 20

2 Bolt NAS6603-5 Item 22

5 Washer ASNA2397JD10L Item 24 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 252 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 Nut NSA5050-3 Item 26 1 Washer ASNA2397-10L (o) Apply the sealing protection to the center tank Refer to Kit 281132A05R00 281132A05003 A00 Sheet(s) 01 281132A05003 A00 Sheet(s) 02 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 (Polyurethane) (Mat. No. 16-001) - Fuel Tank Coating (Mat. No. 16-015). (p) Modify the equipment in the HYD/Fuel Panel 40VU Refer to Kit 281132A06R01, Kit 281132A07R00 and Kit 281132A08R00 281132A06001 A00 Sheet(s) 01 281132A06002 A00 Sheet(s) 01 281132A06002 A00 Sheet(s) 02 1 Remove : 281132A06002 A00 Sheet(s) 01 FIN 14LF 1 Plate-Integrally Lighted 002098-05

Item (0) 1 Plate-Front D9251092000000 2 Install : 281132A06001 A00 Sheet(s) 01 281132A06002 A00 Sheet(s) 02 FIN 24QH 1 Switch-Pushbutton E0415C3LM078E DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 253 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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

Item 0 1 Plate-Front D9251314920000

FIN 14LF 1 Plate-Integrally Lighted D33110194A00

Item 4 1 Placard D1131043320100

Item 6 1 Placard D1131043320200

NOTE : On the new front plate, near the new equipment and the items that you installed again, bond the placards, supplied in : Placard Set D9100095114295 NOTE : Safety the screws with Sealant, Anaerobic (Mat. No. 08-623). NOTE : For the modification to the wiring, Refer to ACCOMPLISHMENT INSTRUCTIONS paragraph B.(2) (w). (q) Modify the equipment and the wiring in the Rear C/B Panel 121VU Refer to Kit 281132A06R01 and Kit 281132A09R00 281132A06003 A00 Sheet(s) 01 281132A06501 A00 Sheet(s) 01 281132A06501 A00 Sheet(s) 02 281132A06502 A00 Sheet(s) 01 281132A06502 A00 Sheet(s) 02 281132A06503 A00 Sheet(s) 01 281132A06503 A00 Sheet(s) 02 281132A06504 A00 Sheet(s) 01 281132A06504 A00 Sheet(s) 02 281132A06505 A00 Sheet(s) 01 281132A06505 A00 Sheet(s) 02 281132A06506 A00 Sheet(s) 01 281132A06506 A00 Sheet(s) 02 281132A06507 A00 Sheet(s) 01 281132A06507 A00 Sheet(s) 02 281132A06508 A00 Sheet(s) 01 281132A06508 A00 Sheet(s) 02 281132A06509 A00 Sheet(s) 01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 254 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281132A06509 A00 Sheet(s) 02 281132A06510 A00 Sheet(s) 01 281132A06510 A00 Sheet(s) 02 281132A06511 A00 Sheet(s) 01 281132A06511 A00 Sheet(s) 02 1 Remove : 281132A06003 A00 Sheet(s) 01 FIN 33LM 1 Placard D11311357A00

FIN 36LM 1 Placard D11311359A00 2 Install : 281132A06003 A00 Sheet(s) 01 FIN 10QH 1 Circuit Breaker NSA931320-050

in position P28 FIN 9QH 1 Circuit Breaker NSA931320-050

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

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

in position N29 FIN 34QU 1 Circuit Breaker NSA931320-050

in position L28 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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FIN 33QU 1 Circuit Breaker NSA931320-050

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

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

in position M28 with : 20 Screw E0736N08-01 20 Washer-Locking ASNA2553-0401

8 Clamp-Locking NSA931305-01

FIN 33LM 1 Placard D00410468A00

FIN 36LM 1 Placard D11311361A00

NOTE : Near the new circuit breaker, bond the placards, supplied in : Placard Set D9100095114295 3 Remove the wires : 281132A06501 A00 Sheet(s) 02 281132A06503 A00 Sheet(s) 02 281132A06505 A00 Sheet(s) 02 281132A06508 A00 Sheet(s) 02 281132A06510 A00 Sheet(s) 02 4 Install the wires : 281132A06502 A00 Sheet(s) 02 281132A06504 A00 Sheet(s) 02 281132A06506 A00 Sheet(s) 02 281132A06507 A00 Sheet(s) 02 281132A06509 A00 Sheet(s) 02 281132A06511 A00 Sheet(s) 02 supplied in : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 256 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Bundle D9000095128395 Then, install : FIN 1114PP 1 Shunt NSA939526-02

between circuit breakers 9QH and 10QH FIN 1115PP 1 Shunt NSA939526-02

between circuit breakers 33QU and 34QU 5Attach the wires with : 150 Tie-Cable NSA935401-03 150 Tie-Cable NSA935401-06 (r) Install the routing of Relay Box 802VU, between FR4 and FR5, in the avionics compartment Refer to Kit 281132A10R02 281132A10001 A00 Sheet(s) 01 281132A10001 A00 Sheet(s) 02 281132A10002 A00 Sheet(s) 01 281132A10003 A00 Sheet(s) 01 281132A10003 A00 Sheet(s) 02 281132A10004 A00 Sheet(s) 01 281132A10004 A00 Sheet(s) 02 281132A10005 A00 Sheet(s) 01 281132A10005 A00 Sheet(s) 02 1 Remove : 281132A10001 A00 Sheet(s) 01 Item (0) 2 Pin Discard 2 Install : 281132A10001 A00 Sheet(s) 02 Item 1 2 Mount E0661-22

Item 2 2 Stud E0420-04 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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3 Install : 281132A10002 A00 Sheet(s) 01 Item 1 1 Bracket D9241244120000

Item 4 2 Mount NSA935504-01

Attach with : Item 18 2 Rivet ASNA2051DCJ3215

Item 2 1 Spacer NSA5527-03-01

Item 3 1 Screw NAS1801-3-20

Item 5 1 Nut NAS1726-3E 4 Install : 281132A10003 A00 Sheet(s) 01 281132A10003 A00 Sheet(s) 02 Item 0 1 Bracket D5391047900001

Attach with : Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016) Item 6 2 Rivet ASNA2050DCJ3215 5 Install : 281132A10004 A00 Sheet(s) 01 281132A10004 A00 Sheet(s) 02 Item 0 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 258 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Mount NSA935504-03

Item 2 2 Mount NSA935504-01

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

Item 6 3 Washer ASNA2397-10L

NOTE : Bond the related placards, supplied in : Placard Set D9100095114395 6 Install : 281132A10005 A00 Sheet(s) 01 281132A10005 A00 Sheet(s) 02 Item 10 5 Screw NAS1801-3-9

Item 11 5 Washer ASNA2397-10L

Item 14 5 Nut NAS1726-3E

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

FIN 4066VC-A 1 Connector E0052R14B19SNF 1 Backshell E0080-01-14C 10 M Conduit E0432A14 NOTE : Bond the related placards, supplied in : Placard Set D9100095114395 (s) Install the connectors 1975VC and 1982VC between FR33 and FR34 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 259 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Kit 281132A10R02 281132A10006 A00 Sheet(s) 01 281132A10006 A00 Sheet(s) 02 FIN 1975VC 1 Connector EN3545D01FXB22A 1 Backshell EN3545-007SCD FIN 1982VC 1 Connector EN3545E03FXB24A 1 Backshell EN3545-007SCD NOTE : Bond the related placards, supplied in : Placard Set D9100095114395 (t) Modify the equipment in the AFT Electronics Rack 80VU Refer to Kit 281132A10R02 1 On the Shelf 85VU

aOn the mounting rail of the terminal block 1853VT, install : 1 Module NSA937901MA2206 in position 28 1 Module NSA937901MA2204 in position 62 2 Module Identification NSA937901E2 1 Module Identification NSA937901E6 1 Module Identification NSA937901E8 (u) Modify the equipment in the Relay Box 103VU Refer to Kit 281132A10R02 281132A10007 A00 Sheet(s) 01 281132A10007 A00 Sheet(s) 02 281132A10007 A00 Sheet(s) 03 1 Install : FIN 50QJ 1 Relay E0245-28A0 1 Base E0250A0S

Item 6 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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2 Nut MS21042L04

in position A77 FIN 53QH 1 Relay E0218UXU120A 1 Base E0219ASUXU

Item 6 3 Nut MS21042L04

in position J03 FIN 57QJ 1 Relay E0666D28A0 1 Base E0247A0S

Item 1 1 Retainer-Assy E0427-01A

Item 2 1 Screw NAS1100-04-6

Item 4 1 Washer ASNA2397-4L

Item 5 1 Washer ASNA2397-3L

Item 6 3 Nut MS21042L04

in position J09 NOTE : Bond the related placards, supplied in : Placard Set D9100095114395 (v) Modify the equipment in the Contactor Box 107VU Refer to Kit 281132A10R02 281132A10008 A00 Sheet(s) 01 281132A10008 A00 Sheet(s) 02 1 Install : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 261 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

FIN 26QH 1 Relay NSA932843AA01 1 Base NSA932844AA

Item 8 3 Screw NAS1100-04-7

Item 4 3 Washer ASNA2397-4L

Item 6 3 Nut MS21042L04

in position B7 FIN 1274VC 1 Connector EN3545D03MXB22A

FIN 1274VC-A 1 Connector EN3545D03FXA22A 2 Backshell EN3545-007SCD

NOTE : Bond the related placards, supplied in : Placard Set D9100095114395 2 On the mounting rail of terminal block 1176VT, install : 1 Module NSA937901MA2008 1 Module Identification NSA937901E0 1 Module Identification NSA937901E1

in position 10 (w) Modify the wiring in the aircraft Refer to Kit 281132A10R02 281132A10501 A00 Sheet(s) 01 281132A10501 A00 Sheet(s) 02 281132A10502 A00 Sheet(s) 01 281132A10502 A00 Sheet(s) 02 281132A10502 A00 Sheet(s) 03 281132A10503 A00 Sheet(s) 01 281132A10503 A00 Sheet(s) 02 281132A10504 A00 Sheet(s) 01 281132A10504 A00 Sheet(s) 02 281132A10504 A00 Sheet(s) 03 281132A10505 A00 Sheet(s) 01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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DESIGN DRAWINGS SHEET(S) 281132A10505 A00 Sheet(s) 02 281132A10505 A00 Sheet(s) 03 281132A10506 A00 Sheet(s) 01 281132A10506 A00 Sheet(s) 02 281132A10506 A00 Sheet(s) 03 281132A10507 A00 Sheet(s) 01 281132A10507 A00 Sheet(s) 02 281132A10508 A00 Sheet(s) 01 281132A10508 A00 Sheet(s) 02 281132A10509 A00 Sheet(s) 01 281132A10509 A00 Sheet(s) 02 281132A10510 A00 Sheet(s) 01 281132A10510 A00 Sheet(s) 02 281132A10510 A00 Sheet(s) 03 281132A10511 A00 Sheet(s) 01 281132A10511 B00 Sheet(s) 02 281132A10512 A00 Sheet(s) 01 281132A10512 A00 Sheet(s) 02 281132A10513 A00 Sheet(s) 01 281132A10513 A00 Sheet(s) 02 281132A10514 A00 Sheet(s) 01 281132A10514 A00 Sheet(s) 02 281132A10515 A00 Sheet(s) 01 281132A10515 A00 Sheet(s) 02 281132A10516 A00 Sheet(s) 01 281132A10516 A00 Sheet(s) 02 281132A10517 A00 Sheet(s) 01 281132A10517 A00 Sheet(s) 02 281132A10518 A00 Sheet(s) 01 281132A10518 A00 Sheet(s) 02 281132A10519 A00 Sheet(s) 01 281132A10519 A00 Sheet(s) 02 281132A10520 A00 Sheet(s) 01 281132A10520 A00 Sheet(s) 02 281132A10521 A00 Sheet(s) 01 281132A10521 A00 Sheet(s) 02 281132A10522 A00 Sheet(s) 01 281132A10522 A00 Sheet(s) 02 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) 1 FLSCU1 Retain 1 FLSCU2 Retain 1 FQIC Retain 1 GAPCU Retain DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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NOTE : You must install these computers again after the modification of the wiring. b Disconnect the bonding braid.

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

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

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

a From the Shelf 94VU, remove for access the computers 5GA2, 10GG, 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 LGCIU2 Retain 1 BSCU Retain 1 HEAT CONT Retain 1 SDCU Retain NOTE : You must install these computers again after the modification of the wiring. b Disconnect the bonding braid.

c Remove the attachment hardware from the Shelf 94U. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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NOTE : Retain the hardware. d Remove the Shelf 94VU and install it on bench. 4 Remove the wires : 281132A10508 A00 Sheet(s) 02 281132A10511 B00 Sheet(s) 02 281132A10513 A00 Sheet(s) 02 281132A10516 A00 Sheet(s) 02 281132A10518 A00 Sheet(s) 02 281132A10520 A00 Sheet(s) 02 5 Install the wires : 281132A10501 A00 Sheet(s) 02 281132A10502 A00 Sheet(s) 02 281132A10502 A00 Sheet(s) 03 281132A10503 A00 Sheet(s) 02 281132A10504 A00 Sheet(s) 02 281132A10504 A00 Sheet(s) 03 281132A10505 A00 Sheet(s) 02 281132A10505 A00 Sheet(s) 03 281132A10506 A00 Sheet(s) 02 281132A10506 A00 Sheet(s) 03 281132A10507 A00 Sheet(s) 02 281132A10509 A00 Sheet(s) 02 281132A10510 A00 Sheet(s) 02 281132A10510 A00 Sheet(s) 03 281132A10512 A00 Sheet(s) 02 281132A10514 A00 Sheet(s) 02 281132A10515 A00 Sheet(s) 02 281132A10517 A00 Sheet(s) 02 281132A10519 A00 Sheet(s) 02 281132A10521 A00 Sheet(s) 02 281132A10522 A00 Sheet(s) 02 supplied in : Bundle D9000095128495 Bundle D9000095128595 Bundle D9000095131295 6Attach the wires with : 100 Tie-Cable NSA935401-03 200 Tie-Cable NSA935401-04 200 Tie-Cable NSA935401-05 800 Tie-Cable NSA935401-06 1500 Tie-Cable NSA935401-08

7 Install the Shelf 92VU

a Install the Shelf 92VU on aircraft. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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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) 1 FLSCU1 1 FLSCU2 1 FQIC 1 GAPCU NOTE : These computers were retained at removal. 8 Install the Shelf 93VU

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

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

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

c Attach the Shelf 94VU and connect the bonding braid with the hardware retained at removal. NOTE : Retain the hardware. d On the Shelf 94VU, install the computers 5GA2, 10GG, 10HC and 10WQ : (Refer to AMM 21-43-34, Page block 401) (Refer to AMM 26-17-34, Page block 401) DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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(Refer to AMM 32-31-71, Page block 401) (Refer to AMM 32-42-34, Page block 401) 1 LGCIU2 1 BSCU 1 HEAT CONT 1 SDCU NOTE : These computers were retained at removal. (x) Modify the equipment in the FWD Electronics Rack 90VU Refer to Kit 281132A11R01 281132A11001 A00 Sheet(s) 01 281132A11002 A00 Sheet(s) 01 281132A11002 B00 Sheet(s) 02 281132A11003 A00 Sheet(s) 01 281132A11003 A00 Sheet(s) 02 1 On the Shelf 92VU

a Remove : (Refer to AMM 28-42-34, Page block 401) 281132A11001 A00 Sheet(s) 01 FIN 3QT 1 Computer-FQI With OBRM SIC5059-11-0207 Item (3) 1 Plate Assy D9251102000000 Item (4) 2 Screw Discard Item (112) 2 Screw Discard Item (28) 2 Washer Discard Item (16) 4 Nut Discard

bOn the mounting rail of the terminal block 202VT, install : 281132A11002 A00 Sheet(s) 01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 Module NSA937901MA2011 in position 21 1 Module NSA937901MA2204 in position 22 3 Module Identification NSA937901E2 1 Module Identification NSA937901E1

c Modify the foolproofing on the connector 3QT-A (Refer to ESPM 20-44-22) 281132A11002 B00 Sheet(s) 02 d Install : (Refer to AMM 28-42-34, Page block 401) 281132A11002 A00 Sheet(s) 01 281132A11002 B00 Sheet(s) 02 FIN 2MCU 1 Rack D0003006100000 Item 15 5 Cover NSA939511-03 Item 5 1 Plate Assy D9251116900000 Attach with : Item 112 3 Screw NAS1801-3-8 Item 4 3 Screw NAS1102-3-10 Item 28 3 Washer ASNA2397-10L Item 16 6 Nut NAS1726-3E FIN 47QJ DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 Level Sensing Control Unit 30042-0000-0501
FIN 47QJ-A 1 Connector E0161D01A12X Attach with : Item 0 2 Flange Assy D9251127600000 Item 6 4 Screw NAS1100-06-12 Item 9 4 Screw NAS1100-04-7 Item 14 4 Washer ASNA2397-4L Item 12 2 Washer ASNA2397-6L FIN 3QT 1 FQIC SIC5059-12-0308 FIN 624VG 1 Module-Grounding E0425A2001 NOTE : Bond the related placards, supplied in : Placard Set D9100095112895 2 On the Shelf 94VU, install : 281132A11003 A00 Sheet(s) 01 281132A11003 A00 Sheet(s) 02 FIN 56QJ 1 Relay E0666D28A0 1 Base E0247A0S

Item 1 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 Retainer-Assy E0427-01A

Item 2 1 Screw NAS1100-04-6

Item 4 1 Washer ASNA2397-4L

Item 5 1 Washer ASNA2397-3L

Item 6 3 Nut MS21042L04

in position B15 NOTE : Bond the related placards, supplied in : Placard Set D9100095112895 (3) Config. 01 AI-GE Part (a) Remove and discard the overhead stowage compartments between FR43 and FR47. Refer to Drawing(s) : Refer to AMM 25-24-41, Page block 401 D25286364010 Sheet(s) 7 and 8 1 Remove and discard these items : 1 box (LH) D2527305509400 Item (514) Discard 1 box (RH) D2527305509500 Item (515) Discard (b) Remove and discard the placards at the overhead stowage compartments between FR43 and FR47. Refer to Drawing(s) : D25288767000 Sheet(s) 2 1 Remove and discard this item :

4 placard D2527700844200 Item (1242) Discard (c) Remove and discard the passenger compartment floor panels 241JF, 251AF 251BF, 251FF, 251GF and 252BF. Refer to AMM 53-32-12, Page block 401 and AMM 53-42-12, Page block 401 Refer to drawing(s) : D53675015000 Sheet(s) 1 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 Remove and discard these items :

2 panel D5367160000000 Item (204) Discard 1 panel D5367160100000 Item (206) Discard 2 panel D5367166300000 Item (214) Discard 1 panel D5367166400000 Item (216) Discard 1 connecting plate D5367009920400 Item (302) Discard 1 panel D5367161700000 Item (304) Discard

and discard the removed fastening parts. (d) Modify the electrical equipment. Refer to Kit 281132D70R00 Refer to drawings : D92894736004 Sheet(s) 14 thru 17 D92894713020 Sheet(s) 1 D23793324001 Sheet(s) 1 1 Remove the cable harnesses 1780, 1782, 1783 and 1785. Refer to drawing D23793324001 (Sheet 1) 2 Replace the cable harness 5339VB from the terminal block 7223VT to the receptacle 7555VC. Refer to drawing D92894736004 (Sheets 14 thru 17) Refer to drawing D92894713020 (Sheet 1) Refer to Figure 1 (Hookup Chart 1)

a Install these items as shown in drawing D92894736004, Sheet 16, Detail C : 3 screw NAS1096-2-12 Item 007 3 washer NAS1149CN816R Item 152 3 nut NSA5066-08-1 Item 230 1 bracket E0343-01 Item 250 1 bracket NSA935504-01 Item 251 3 spacer NSA5527-03-03 Item 304

b Remove this item as shown in drawing D92894736004, Sheet 16, Detail A : 1 screw NAS1096-2-9 Item (005) Discard and install these parts : 1 screw NAS1096-2-12 Item 007 1 bracket E0343-01 Item 250 1 bracket NSA935504-03 Item 253 1 spacer NSA5527-03-03 Item 304

c Remove this item as shown in drawing D92894736004, Sheet 16, Section A-A : 2 pin DAN364-02 Item (291) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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and install these items : 2 bracket ABS0355-01 Item 262 2 bracket ABS0355-02 Item 263 2 washer NSA935514-03 Item 264

d Install this item as shown in drawing D92894736004, Sheet 16, Detail B : 1 bracket NSA935513-07 Item 259

e Route the wires with the existing wire, as shown in Hookup Chart 1, lines 1 and 2 and the drawing D92894736004, supplied with : 1 harness D9299043900000 Item 039 and connect with : AR tie NSA935401-03 Item 793 AR tie NSA935401-04 Item 794 AR tie NSA935401-05 Item 795 f Connect 7555VC with these items as shown in drawing D92894736004, Sheet 16, Detail B : 2 screw NAS1100-04-5 Item 051 2 washer NAS1149CN616R Item 150 2 nut MS21042-04 Item 200

g Connect 7499VN with these items as shown in drawing D92894736004, Sheet 16, Detail B : 1 screw NAS1096-3-9 Item 030 1 washer NAS1149C0332R Item 153

h Install the placards as shown in drawing D92894736004, Sheet 16, Details A and B : 2 placard D9239386503200 Item 050

i Install the "MOD/SB" placards on the harness 5339VB, Item 039, as shown in drawing D92894713020, Sheet 1 : 20 placard D9239310902800 Item 000 40 tie NSA935401-03 Item 080 3 Replace the cable harness 5340VB from the terminal block 7224VT to the receptacle 7556VC. Refer to drawing D92894736004 (Sheet 14 thru 17) Refer to drawing D92894713020 (Sheet 1) Refer to Figure (Hookup Chart 2)

a Route the wires with the existing wire, as shown in Hookup chart 2, lines 1 and 2 and the drawing D92894736004, supplied with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 harness D9299044000000 Item 040 and connect with : AR tie NSA935401-03 Item 793 AR tie NSA935401-04 Item 794 AR tie NSA935401-05 Item 795 bConnect 7556VC with these items as shown in drawing D92894736004, Sheet 16, Detail C : 2 screw NAS1100-04-5 Item 051 2 washer NAS1149CN616R Item 150 2 nut MS21042-04 Item 200

c Connect 7100VN with these items as shown in drawing D92894736004, Sheet 16, Detail D : 1 screw NAS1096-3-9 Item 030 1 washer NAS1149C0332R Item 153

d Install the placards as shown in drawing D92894736004, Sheet 16, Details C and D : 2 placard D9239386503200 Item 050

e Install the "MOD/SB" placards on the harness 5340VB, Item 040, as shown in drawing D92894713020, Sheet 1 : 20 placard D9239310902800 Item 000 40 tie NSA935401-03 Item 080 (e) Install the overhead stowage compartment. Refer to Kit 281132D72R00 Refer to Drawings : D25286364010 Sheet(s) 7 and 8 1 Install the overhead stowage compartment between FR43 and FR47, LH/RH. 2 Install the boxes, Items 020 and 021, as shown in Sections A7-8 and D7-8 : 1 box (LH) D2527305811800 Item 020 1 box (RH) D2527305811900 Item 021

with : 16 screw NAS1102-4-16 Item 002 16 washer NAS1149F0432P Item 004 16 washer NAS1169C416L Item 006 16 nut MS21042-4 Item 008 16 screw NAS1102-08-16 Item 010 16 washer NAS1149FN816P Item 012 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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16 washer NAS1169C8L Item 014 16 nut MS21042-08 Item 016

4 pin MS20392-3C23 Item 030 2 pin MS20392-3C27 Item 031 6 washer NAS1149F0463P Item 032 6 pin AA55487-5 Item 033 4 pin MS20392-4C67 Item 042 2 pin MS20392-4C45 Item 043 4 washer NAS1149C0532R Item 046 6 split-ring DAN191-20 Item 047 2 clamp NSA5528-045 Item 065 (f) Install the placards on the overhead stowage compartment. Refer to Kit 281132D73R00 Refer to Drawing(s) : D25288767000 Sheet(s) 1 and 2 1 Install the placards on the overhead stowage compartment between FR43 and FR47, LH/RH.

a Install these items : 2 placard D2527719940600 Item 206 2 placard D2527700844200 Item 242 2 placard A2528131544600 Item 246 (g) Remove the LH sidewall panels between FR46 and FR58. Refer to refer to AMM 25-55-11 Refer to Drawing(s) : D25570049002 Sheet(s) 2 1 Remove and discard these items : Refer to refer to AMM 25-55-11, Page block 401 1 panel D2557176800000 Item (120) Discard 1 panel D2557176200600 Item (122) Discard 1 panel D2557176000200 Item (144) Discard (h) Remove the RH sidewall panels between FR46 and 52A. Refer to AMM 25-55-11 Refer to Drawing(s) : D25570049004 Sheet(s) 3 1 Remove and discard these items : Refer to AMM 25-55-11, Page block 401 1 panel D2557177800000 Item (130) Discard 1 panel D2557178600000 Item (132) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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(i) Remove and discard the aft cargo compartment panels 151AW, 151BW and 152BW at FR47. Refer to AMM 25-55-11 Refer to Drawing(s) : D25570049006 Sheet(s) 4 1 Remove and discard these items : Refer to AMM 25-55-11, Page block 401 1 panel D2557166000000 Item (140) Discard 1 panel D2557166000100 Item (141) Discard 1 panel D2557166200000 Item (142) Discard (j) Remove and discard the insulation blankets at FR46. Refer to AMM 25-80-00 Refer to Drawing(s) : D25870003028 Sheet(s) 20 1 Remove and discard these items : Refer to AMM 25-80-00, Page block 201 1 blanket D2587085002000 Item (020) Discard 1 blanket D2587085102200 Item (021) Discard 1 blanket D2587085202000 Item (022) Discard 1 blanket D2587085302200 Item (023) Discard 1 blanket D2587085402000 Item (024) Discard 1 blanket D2587085502200 Item (025) Discard 1 blanket D2587085602000 Item (026) Discard 1 blanket D2587085702000 Item (027) Discard 1 blanket D2587085802000 Item (028) Discard 1 blanket D2587085902000 Item (029) Discard 1 blanket D2587086002000 Item (030) Discard 1 blanket D2587086102000 Item (031) Discard 1 blanket D2587086202000 Item (032) Discard 1 blanket D2587086302200 Item (033) Discard 1 blanket D2587086502000 Item (034) Discard 1 blanket D2587087102000 Item (035) Discard 1 blanket D2587087302000 Item (036) Discard (k) Remove the AFT cargo compartment ceiling panels between FR47 and FR59. Refer to AMM 25-55-11 Refer to Drawing(s) : D25570049000 Sheet(s) 1 1 Remove and retain these items as shown in drawing D25570049000, Sheet 1 : Refer to AMM 25-55-11, Page block 401 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 rail D2558503100000 Item A 2 rail D2558501900000 Item B

NOTE : Retain the Items A and B. 2 Remove and retain the AFT cargo compartment ceiling panel 151DC, refer to AMM 25-55-11, Page block 401. 3 Remove and discard these items as shown in drawing D25570049000, Sheet 1 : 1 panel D2557173003600 Item (100) Discard 1 panel D2557174208200 Item (102) Discard 1 panel D2557174404200 Item (100) Discard 1 panel D2557173600000 Item (102) Discard 1 panel D2557164400000 Item (100) Discard (l) Remove and discard the floor panels from the AFT cargo compartment, between FR47 and FR59. Refer to AMM 53-42-14 Refer to Drawing(s) : D53672854000 Sheet(s) 1 1 Remove and discard these items as shown in Detail A1-1 : Refer to AMM 53-42-14, Page block 401 1 panel D5367320400000 Item (212) Discard 1 panel D5367320500000 Item (214) Discard 1 panel D5367320600000 Item (216) Discard 1 panel D5367320700000 Item (218) Discard 1 panel D5367320900000 Item (220) Discard 1 panel D5367305900000 Item (222) Discard Discard the fastening items. (m) Remove and discard the sloped floor panels from the AFT cargo compartment, between FR47 and FR59. Refer to AMM 53-42-14 Refer to Drawing(s) : D53672856000 Sheet(s) 1 1 Remove and discard these items as shown in Details A1-1 and B1-1 : Refer to AMM 53-42-14, Page block 401 1 panel D5367301800000 Item (200) Discard 1 panel D5367301800100 Item (201) Discard 1 panel D5367302000000 Item (202) Discard 1 panel D5367302400000 Item (204) Discard 1 panel D5367302600000 Item (206) Discard 1 panel D5367303400000 Item (208) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 panel D5367303400100 Item (209) Discard 1 panel D5367302200000 Item (210) Discard 1 panel D5367302700000 Item (212) Discard 1 panel D5367301900000 Item (214) Discard 1 panel D5367301900100 Item (215) Discard 1 panel D5367302100000 Item (216) Discard 1 panel D5367302500000 Item (218) Discard 1 panel D5367302800000 Item (220) Discard 1 panel D5367303500000 Item (222) Discard 1 panel D5367303500100 Item (223) Discard 1 panel D5367302300000 Item (224) Discard 1 panel D5367302900000 Item (226) Discard

Discard the fastening items. (n) Remove the wires of cable harness 4234VB Refer to Drawing(s) : D92990634001 Sheet(s) 2 and B01 (o) Remove the wires of cable harness 4209VB Refer to Drawing(s) : D92992299002 Sheet(s) 1 and 3 (p) Modify the structure. Refer to Kit 281132D05R01 Refer to Drawing(s) : D53372362004 Sheet(s) 2 thru 13 1 Install the beam assy between FR46 and FR47 from -Y1292 to +Y1292. D53372362004 Sheet(s) 12

a Remove the existing rivets in the affected areas. 1 beam D5337217000200 Item 000

b Put this item in position as shown in Detail A1-12 :

c Transfer drill the holes, drill the additional holes and open all holes to final dimension. d Install this items : 1 T-beam D5337217000200 Item 000 with : 8 pin DAN5-6-7X Item 767 4 pin DAN5-6-8X Item 768 4 collar NSA5075-5 Item 804 8 collar NSA5075-6 Item 806 12 collar DAN11-6X Item 807 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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4 pin DAN5-6-7 Item 967 4 pin DAN5-6-8 Item 968 4 pin DAN5-5-9 Item 949 2 Install the struts at the beam between FR46 and FR47.

a Install these items as shown in Details A1-12 and Z1-13 : 2 strut D5337218500000 Item 002 4 strut D5337218600000 Item 004 with : 2 bolt MS21250-09024 Item 464 2 nut NAS1726-9E Item 466 2 washer MS20002C9 Item 468 4 bolt MS21250-06018 Item 470 4 nut NAS1726-6E Item 472 4 washer MS20002C6 Item 474 NOTE : Tighten the nuts temporarily. The final attachment of the struts is possible after the installation of the attachment structure of the partition panels. 3 Replace fasteners between FR42 and FR46 between +Y1292 to +Y1650 and -Y1292 to -Y1650.

a Remove the existing rivets, drill the holes to final dimension and install these items as shown in Detail Y4-4 : 210 collar NSA5076-6 Item 816 4 pin DAN6-6-5 Item 865 166 pin DAN5-6-5 Item 965

40 pin DAN5-6-6 Item 966 b If necessary remove the MLG torque tube assembly, refer to AMM 32-33-17, Page block 401, and the shafts. Refer to drawing D53372362004, Sheet 4 Refer to drawing D32170220004, Sheet 5 Refer to drawing D32170220005, Sheet 5 12 pin DAN5-6-4X Item 764

8 pin DAN5-6-5X Item 765 8 pin DAN5-6-6X Item 766 2 pin DAN5-6-7X Item 767 2 collar NSA5075-6 Item 806 30 collar DAN11-6X Item 807

2 pin DAN5-6-8 Item 968

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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4 Replace the fasteners at FR43, STGR28LH/RH. D53372362004 Sheet(s) 3

a Remove the existing rivets, drill the holes to final dimension and install these items as shown in Detail T1-13 : 6 pin DAN5-6-6X Item 766 6 collar DAN11-6X Item 807 5 Drill the holes in FR46 between STGR42LH and STGR43LH. Refer to Drawing(s) : D53372362004 Sheet(s) 6

a Drill one hole with 22.0 mm (0.866 in.) diameter and two holes with 5.6 mm (0.22 in.) diameter as shown in Detail A7-6. b Deburr the holes. 6 Replace the fitting at FR47 at STGR43 to STGR44 as shown in Detail A1-A5. Refer to Drawing(s) : D53372362004 Sheet(s) 5, 8 and 9

a Remove : 1 support D5347465720300 Item (200) Discard 1 fitting D5347008120200 Item (202) Discard 1 profile D5347034400000 Item (220) Discard

b Put this item in position : 1 fitting D5337219020200 Item 012

c Transfer drill the holes and open the holes to final dimension. d Install this item : 1 fitting D5337219020200 Item 012 with : 5 rivet LN9198-4810CF Item 648 10 collar NSA5075-6 Item 806 10 pin DAN5-6-5 Item 965 7 Replace the supports at FR47 at STGR35LH/RH, STGR36LH/RH, STGR39LH/RH and STGR40LH/RH as shown in Detail A1-A5.

a Remove and discard the supports : 4 support (LH) D5347100920000 Item (206) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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4 support (RH) D5347100920100 Item (207) Discard

b Put these items in position : 4 support (LH) D5347100920090 Item 048 4 support (RH) D5347100920190 Item 049

c Transfer drill the holes, open all holes and all countersinks to the final dimension. d Install these items : 4 support (LH) D5347100920090 Item 048 4 support (RH) D5347100920190 Item 049 with : 32 rivet LN9198-4010CF Item 640 8 Install the angles at FR47 between STGR36LH/RH and STGR40LH/RH as shown in Section A1-A5 and in Details Y1-8 and U1-9.

a Remove the existing fasteners between the affected stringers. b Put this item between the affected stringers in position : 8 angle D5337215920200 Item 016

c Transfer drill the holes from the skin panel to the angles. d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install this item : 8 angle D5337215920200 Item 016 with : 24 rivet LN9198-4810CF Item 648 32 collar DAN11-6X Item 807

2 pin DAN5-6-7X Item 767 26 pin DAN5-6-8X Item 768

2 pin DAN5-6-10X Item 770 2 pin DAN5-6-12X Item 772 9 Install the angles at FR47 between STGR35LH/RH and STGR36LH/RH as shown in Section A1-A5 and in Detail Y1-8.

a Remove the existing fasteners between the affected stringers. b Put these items between the affected stringers in position : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 angle (LH) D5337215920400 Item 018 1 angle (RH) D5337215920500 Item 019

cTransfer drill the holes from the skin panel to the angle. d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install these items : 1 angle (LH) D5337215920400 Item 018 1 angle (RH) D5337215920500 Item 019 with : 6 rivet LN9198-4810CF Item 648 8 collar DAN11-6X Item 807 6 pin DAN5-6-8X Item 768 2 pin DAN5-6-10X Item 770 10Install the angle at FR47 between STGR40LH and STGR41LH as shown in Section A1-A5 and in Detail Y1-8.

a Remove the existing fasteners between the affected stringers. b Put this item between the affected stringers in position : 1 angle D5337215920000 Item 014

c Transfer drill the holes from the skin panel to the angle. d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install this item : 1 angle D5337215920000 Item 014 with : 3 rivet LN9198-4810CF Item 648 4 collar DAN11-6X Item 807 4 pin DAN5-6-8X Item 768 11Install the angle at FR47 between STGR40RH and STGR41RH as shown in Details Y5-5 and U1-9.

a Remove the existing fasteners between the affected stringers. b Put this item between the affected stringers in position : 1 angle D5337215920600 Item 020 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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c Transfer drill the holes from the skin panel to the angle. d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install this item : 1 angle D5337215920600 Item 020 with : 3 rivet LN9198-4810CF Item 648 3 collar DAN11-6X Item 807 3 pin DAN5-6-9X Item 769 12Remove the angles at FR47 at STGR37LH/RH and STGR38LH/RH as shown in Section A1-A5.

a Remove and discard these items : 2 angle (LH) D5347104120000 Item (212) Discard 2 angle (RH) D5347104120100 Item (213) Discard 13Replace the fittings at FR47 between STGR37LH/RH and STGR38LH/RH as shown in Section A1-A5.

a Remove and discard these items : 1 fitting (LH) D5337219220200 Item (204) Discard 1 fitting (RH) D5337219220300 Item (205) Discard

b Put these items in position : 1 fitting (LH) D5337219220000 Item 008 1 fitting (RH) D5337219220100 Item 009

c Put these items at STGR37LH/RH in position : 1 angle (LH) D5347104120090 Item 050 1 angle (RH) D5347104120190 Item 051

dTransfer drill the holes and open the holes to final dimension.

e Install these items : 1 fitting (LH) D5337219220000 Item 008 1 fitting (RH) D5337219220100 Item 009 1 angle (LH) D5347104120090 Item 050 1 angle (RH) D5347104120190 Item 051 with : 8 pin DAN7-6-6X Item 566 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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4 rivet LN9198-4010CF Item 640 8 rivet LN9198-4810CF Item 648 4 rivet LN9198-5610CF Item 656 22 collar NSA5075-6 Item 806

8 collar DAN12-6X Item 817 16 pin DAN5-6-5 Item 965

2 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 14Install the fittings at FR47 between STGR38LH/RH and STGR39LH/RH as shown in Section A1-A5.

a Put these items at FR47 in position : 1 fitting (LH) D5337219120200 Item 010 1 fitting (RH) D5337219120300 Item 011

b Drill the holes and open the holes to final dimension.

c Install these items : 1 fitting (LH) D5337219120200 Item 010 1 fitting (RH) D5337219120300 Item 011 with : 12 rivet LN9198-4810CF Item 648 16 collar NSA5075-5 Item 804 16 pin DAN5-5-5 Item 945 15Install the nuts at FR47 as shown in Section A1-A5.

a Drill the four holes 5.6 mm (0.220 in.) diameter for the nuts. b Put the nuts, Item 046, in position.

c Drill the holes and countersink the rivet holes. d Install these items : 4 nut NAS1791A3-1 Item 046 with : 8 rivet NAS1097AD3-10 Item 524 16Remove the support at FR47 at STGR43LH as shown in Section A1-A5.

a Remove and discard this item : 1 support D5347465720300 Item (200) Discard 17Remove the nuts at FR47 as shown in Detail C5-5. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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a Remove and discard these items : 2 nut NAS1068C3 Item (214) Discard

bClose the holes with : 4 rivet NAS1097AD3-10 Item 524 18Drill twelve holes with 5.6 mm (0.220 in.) diameter as shown in Details A5-5 and B5-5. 19Install the sections at FR43 and FR44 between STGR21LH and STGR23LH as shown in Detail X1-8. Refer to Drawing(s) : D53372362004 Sheet(s) 8

a Put this item in position : 3 section D5337602020000 Item 044

b Drill the holes and open the holes to final dimension.

c Countersink all additional holes in the skin panel. d Install these items : 3 section D5337602020000 Item 044 with : 21 collar NSA5075-6 Item 806

8 pin DAN6-6-5 Item 865 3 pin DAN5-6-4 Item 964 4 pin DAN6-6-6 Item 866 6 pin DAN5-6-5 Item 965 20Install the sections at FR43 and FR44 between STGR21RH and STGR23RH as shown in Detail X1-8. Refer to Drawing(s) : D53372362004 Sheet(s) 8

a Put this item in position : 3 section D5337602020100 Item 045

b Drill the holes and open the holes to final dimension.

c Countersink all additional holes in the skin panel. d Install these items : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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3 section D5337602020100 Item 045 with : 21 collar NSA5075-6 Item 806

8 pin DAN6-6-5 Item 865 3 pin DAN5-6-4 Item 964 4 pin DAN6-6-6 Item 866 6 pin DAN5-6-5 Item 965 21Install the reinforcing angles between FR47 and FR48 at STGR1LH/RH and STGR2LH/RH as shown in Section D1-D10. Refer to Drawing(s) : D53372362004 Sheet(s) 9 and 10

a Remove the fasteners in the affected areas. b Put these items in position : 4 shim D5337236220400 Item 052 2 angle (LH) D5347007421800 Item 152 2 angle (RH) D5347007421900 Item 153

c Drill the holes in the stringer and the skin panel. dTransfer drill the holes from the stringer to the angles and open all holes and to final dimension.

e Countersink all additional holes in the skin panel. f Install these items : 4 shim D5337236220400 Item 052 2 angle (LH) D5347007421800 Item 152 2 angle (RH) D5347007421900 Item 153 with : 64 rivet NAS1097AD5-12 Item 540 48 rivet LN9198-4010CF Item 640 12 collar NSA5075-6 Item 806 12 pin DAN5-6-3 Item 963 22Install the reinforcing angles between FR48 and FR49 at STGR2LH/RH as shown in Section D1-D10. Refer to Drawing(s) : D53372362004 Sheet(s) 9 and 10

a Put these items in position : 1 angle (LH) D5347007420800 Item 156 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 angle (RH) D5347007420900 Item 157

b Drill the holes in the stringer and the skin panel and open the holes to final dimension.

c Countersink all additional holes in the skin panel. d Install these items : 1 angle (LH) D5347007420800 Item 156 1 angle (RH) D5347007420900 Item 157 with : 38 rivet NAS1097AD5-12 Item 540 36 rivet LN9198-4010CF Item 640 23Install the reinforcing angles at FR48 between STGR8LH/RH and STGR13LH/RH as shown in Section C1-C9. Refer to Drawing(s) : D53372362004 Sheet(s) 9 and 10

a Put these items in position : 1 angle (LH) D5337036520200 Item 150 1 angle (RH) D5337036520300 Item 151

b Drill the holes and open the holes to final dimension.

c Install these items : 1 angle (LH) D5337036520200 Item 150 1 angle (RH) D5337036520300 Item 151 with : 52 rivet LN9198-4010CF Item 640 (q) Remove the corner profiles at STGR38LH/RH between FR48 and FR56. Refer to Drawing(s) : D53470075002 Sheet(s) 10 1 Remove and discard these items as shown in Details Z9-10 and X9-10 : 1 corner profile D5347048100400 Item (452) Discard 1 corner profile D5347047500400 Item (454) Discard 1 corner profile D5347047600600 Item (456) Discard (r) Remove the shear plates at STGR38LH/RH between FR48 and FR59.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Refer to Drawing(s) : D53470075002 Sheet(s) 8 and 11 1 Remove and discard these items at STGR38LH as shown in Sections H1-H8 and K1-K11 : 1 shear plate D5347048800000 Item (374) Discard 1 shear plate D5347048900000 Item (376) Discard 1 shear plate D5347049200200 Item (378) Discard 2 angle D5347046820600 Item (386) Discard 1 angle D5347046820200 Item (390) Discard 1 angle D5347046820800 Item (392) Discard 1 angle D5347046821000 Item (394) Discard 1 connection D5347065020200 Item (398) Discard 3 angle D5347046820000 Item (460) Discard 2 angle D5347046820200 Item (462) Discard 1 angle D5347046820400 Item (464) Discard 2 shear plate D5347049000000 Item (474) Discard 1 shear plate D5347049100000 Item (476) Discard 2 Remove and discard these items at STGR38RH as shown in Sections G1-G17 and J1-J17 : 1 shear plate D5347048700000 Item (370) Discard 1 shear plate D5347048500200 Item (372) Discard 1 shear plate D5347046821100 Item (380) Discard 1 angle D5347046820900 Item (382) Discard 1 angle D5347046822000 Item (384) Discard 1 shear plate D5347063720600 Item (396) Discard 2 angle D5347046820100 Item (468) Discard 3 angle D5347046820300 Item (470) Discard 1 angle D5347046822400 Item (472) Discard 1 shear plate D5347049000100 Item (478) Discard 1 shear plate D5347049000300 Item (480) Discard 1 shear plate D5347048600400 Item (482) Discard (s) Remove the crossbeams at FR48, FR49, FR50 and FR51 in the AFT cargo compartment. Refer to Drawing(s) : D53470075002 Sheet(s) 2 thru 4 NOTE : For minor crossbeam modification, two frames can only be reworks at one time with standard jacking. 1 Remove these items at FR48 as shown in drawing D53470075002, Sheet 2, Section A1-A2 ’BEFORE’.

a Remove and discard these items : 1 crossbeam D5347035000400 Item (400) Discard 1 shim D5347061120200 Item (402) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 fitting D5347061220000 Item (404) Discard 1 shim D5347061120300 Item (406) Discard 1 fitting D5347061220100 Item (408) Discard 1 support D5347069920800 Item (412) Discard

bClose the eight holes as shown in Details B2-2 and C2-2 : 8 rivet MBBN4477-4012 Item 541

c Close the two holes at FR48 at STGR43LH/RH as shown in Section A1-A2 : 2 rivet MBBN4477-4012 Item 541 2 Remove these items at FR49 as shown in drawing D53470075004, Sheet 3, Section B15-B3 ’BEFORE’.

a Remove and discard these items : 1 crossbeam D5347035000400 Item (400) Discard 1 shim D5347061120200 Item (402) Discard 1 fitting D5347061220000 Item (404) Discard 1 shim D5347061120300 Item (406) Discard 1 fitting D5347061220100 Item (408) Discard 1 support D5347069920800 Item (412) Discard

bClose the eight holes as shown in Details B3-3 and C3-3 : 8 rivet MBBN4477-4012 Item 541

c Close the two holes at FR49 at STGR43LH/RH as shown in Section B15-B3 ’AFTER’ : 2 rivet MBBN4477-4012 Item 541 3 Remove these items at FR50 as shown in drawing D53470075004, Sheet 4, Section C15-C4 ’BEFORE’.

a Remove and discard these items : 1 crossbeam D5347026000400 Item (410) Discard 1 shim D5347061120200 Item (402) Discard 1 fitting D5347061220000 Item (404) Discard 1 shim D5347061120300 Item (406) Discard 1 fitting D5347061220100 Item (408) Discard 1 clip D5347073720400 Item (430) Discard 1 clip D5347073920200 Item (432) Discard 1 clip D5347074020000 Item (434) Discard 1 clip D5347073720500 Item (436) Discard

bClose the eight holes as shown in Details B4-4 and C4-4 : 8 rivet MBBN4477-4012 Item 541 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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c Close the four holes at FR50 at STGR43LH/RH as shown in Section C15-C4 ’AFTER’ : 4 rivet MBBN4477-4012 Item 541 4 Remove these items at FR51 as shown in drawing D53470075004, Sheet 16, Section D15-D16 ’BEFORE’.

a Remove and discard these items : 1 crossbeam D5347035300400 Item (420) Discard 1 shim D5347061120200 Item (402) Discard 1 fitting D5347061220000 Item (404) Discard 1 shim D5347061120300 Item (406) Discard 1 fitting D5347061220100 Item (408) Discard 1 clip D5347074420400 Item (440) Discard 1 clip D5347074620200 Item (442) Discard 1 clip D5347074720000 Item (444) Discard 1 clip D5347074420500 Item (446) Discard 1 connection D5347557525400 Item (448) Discard

bClose the eight holes as shown in Details B16-16 and C16-16 : 8 rivet MBBN4477-4012 Item 541

c Close the four holes at FR51 at STGR43LH/RH as shown in Section D15-D16 ’AFTER’ : 4 rivet MBBN4477-4012 Item 541 (t) Remove the crossbeams at FR52, FR53 and FR54 in the AFT cargo compartment. Refer to Drawing(s) : D53470076004 Sheet(s) 1, 2, 4 and 5 1 Remove these items from FR52 as shown in drawing D53470076004, Sheet 2, Section A1-A2 ’BEFORE’.

a Remove and discard these items : 1 fitting D5347061220000 Item (400) Discard 1 fitting D5347061220100 Item (401) Discard 1 shim D5347061120200 Item (402) Discard 1 shim D5347061120300 Item (403) Discard 1 support D5347037820200 Item (404) Discard 1 fitting D5347448720000 Item (406) Discard 1 clip D5347074320600 Item (408) Discard 1 clip D5347075120200 Item (410) Discard 1 clip D5347075220000 Item (412) Discard 1 clip D5347074320700 Item (414) Discard 1 angle D5347557520600 Item (416) Discard 1 support D5347038420200 Item (444) Discard 1 fitting D5347449920200 Item A DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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NOTE : Discard the Item A. b Close the eight holes as shown in Details A2-2 and B2-2 : 8 rivet MBBN4477-4010 Item 541

c Close the four holes at FR52 at STGR43LH/RH as shown in Section A1-A2 : 4 rivet MBBN4477-4010 Item 541 2 Remove these items at FR53 as shown in drawing D53470076004, Sheet 4, Section C1-C4 ’BEFORE’.

a Remove and discard these items : 1 fitting D5347061220000 Item (400) Discard 1 crossbeam D5347026100400 Item (418) Discard 1 clip D5347075320400 Item (420) Discard 1 support D5347068120200 Item (422) Discard 1 clip D5347074520000 Item (424) Discard 1 clip D5347075420000 Item (426) Discard 1 clip D5347075520200 Item (428) Discard

bClose the four holes as shown in Detail A4-4 : 8 rivet MBBN4477-4010 Item 541

c Close the four holes at FR53 at STGR43LH/RH as shown in Section C1-C4 ’AFTER’ : 4 rivet MBBN4477-4010 Item 541 3 Remove these items at FR54 as shown in drawing D53470076004, Sheet 5, Section D1-D5 ’BEFORE’.

a Remove and discard these items : 1 fitting D5347061220000 Item (400) Discard 1 shim D5347061120200 Item (402) Discard 1 crossbeam D5347035601000 Item (430) Discard 1 clip D5347098020000 Item (432) Discard 1 support D5347068120300 Item (434) Discard 1 clip D5347075820200 Item (436) Discard 1 clip D5347075920000 Item (438) Discard 1 clip D5347076020200 Item (440) Discard

bClose the four holes as shown in Detail A5-5 : 8 rivet MBBN4477-4010 Item 541

c Close the four holes at FR54 at STGR43LH/RH as shown in Section D1-D5 ’AFTER’ : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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4 rivet MBBN4477-4010 Item 541 (u) Modify the structure at FR48 between STGR34LH and STGR34RH. Refer to Kit 281132D40R03 Refer to Drawing(s) : D53470075004 Sheet(s) 2 1 Replace the fasteners at FR48 between STGR34RH and STGR36RH as shown in Section A15-A2 ’AFTER’.

a Remove the existing fasteners in the affected area as shown in Section A15-A2 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR48. 2 Install the reinforcing straps at FR48 between STGR35LH/RH and STGR42LH/RH as shown in Section A15-A2 ’AFTER’ :

a Put these items at FR48 in position : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes to final dimension. d Install these items : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with : 58 rivet LN9198-4012CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit 281132D41R00. 3 Install the fittings at FR48 at STGR37LH/RH as shown in Section A15-A2 ’AFTER’ :

a Put these items at FR48 in position : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

bTransfer drill the holes from the frame to the fittings and open all holes to final dimension.

c Install these items : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with : 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR48 as shown in Section A15-A2 ’AFTER’ :

a Put these items at FR48 temporarily in position : 1 crossbeam D5347035000600 Item 010 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 010, IS IN LINE WITH THE CROSSBEAMS AT FR47 AND FR55. b Mark the fastener holes as shown in Detail Y2-3 and Z2-3.

c Drill the marked holes with 3.3 mm (0.130 in.) diameter. dTransfer drill all other holes from the frame to the crossbeam.

e Drill all additional holes and open all holes to final dimension. f Remove the crossbeam. g Mark and drill the holes in FR48 as shown in Detail C3-3. h Put the crossbeam in position and install these items : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 crossbeam D5347035000600 Item 010 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026 with : 32 rivet LN9198-4816CF Item 648

6 pin DAN5-6-5X Item 765 60 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 6 collar NSA5075-8 Item 808 16 pin DAN5-6-4 Item 964 34 pin DAN5-6-5 Item 965 10 pin DAN5-6-6 Item 966

2 pin DAN5-6-7 Item 967 6 pin DAN5-8-5 Item 985

i Put this item at FR48 in position as shown in Detail C3-3 : 2 bushing D5347658620000 Item 204

j Transfer drill the holes from the frame to the bushings and open the holes to final dimension. k Install these items as shown in Detail C3-3 : 2 bushing D5347658620000 Item 204 with : 2 collar NSA5075-6 Item 806 2 pin DAN5-6-7 Item 967 5 Replace the fasteners at FR48 between STGR42LH and STGR42RH :

a Remove the fasteners as shown in Section A15-A2 ’BEFORE’. bOpen the holes to final dimension.

c Install these items as shown in Section A15-A2 ’AFTER’ : 17 rivet LN9198-4816CF Item 648 6 Install the sections and the angles at FR48 between STGR34LH/RH and STGR39LH/RH as shown in Section A15-A2 ’AFTER’ :

a Put these items in position : 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 3 section D5347449520500 Item 032 3 section D5347449520400 Item 034 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 angle D5347470020000 Item 036 1 angle D5347470020100 Item 038

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items : 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 3 section D5347449520500 Item 032 3 section D5347449520400 Item 034 1 angle D5347470020000 Item 036 1 angle D5347470020100 Item 038 with : 32 rivet MBBN4477-4812 Item 549 40 rivet LN9198-4816CF Item 648

8 collar NSA5075-6 Item 806 8 pin DAN6-6-4 Item 864 (v) Modify the structure at FR49 between STGR34LH and STGR34RH. Refer to Kit 281132D40R03 Refer to Drawing(s) : D53470075004 Sheet(s) 3 1 Replace the fasteners at FR49 between STGR34RH and STGR36RH as shown in Section B15-B3 ’AFTER’ :

a Remove the existing fasteners in the affected area as shown in Section B15-B3 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR49. 2 Install the reinforcing straps at FR49 between STGR35LH/RH and STGR42LH/RH as shown in Section B15-B3 ’AFTER’ : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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a Put these items at FR49 in position : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes to final dimension. d Install these items : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with : 58 rivet LN9198-4012CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit 281132D41R00. 3 Install the fittings at FR49 at STGR37LH/RH as shown in Section B15-B3 ’AFTER’ :

a Put these items at FR49 in position : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

bTransfer drill the holes from the frame to the fittings and open all holes to final dimension.

c Install these items : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with : 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR49 as shown in Section B15-B3 ’AFTER’ :

a Put these items at FR49 temporarily in position : 1 crossbeam D5347035000600 Item 010 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 010, IS IN LINE WITH THE CROSSBEAMS AND FR47 AND FR55. b Mark the fastener holes as shown in Detail Y3-3 and Z3-3.

c Drill the marked holes with 3.3 mm (0.130 in.) diameter. dTransfer drill all other holes from the frame to the crossbeam.

e Drill all additional holes and open all holes to final dimension. f Remove the crossbeam. g Mark and drill the holes in FR49 as shown in Detail C3-3. h Put the crossbeam in position and install these items : 1 crossbeam D5347035000600 Item 010 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026 with : 32 rivet LN9198-4816CF Item 648

6 pin DAN5-6-5X Item 765 60 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 6 collar NSA5075-8 Item 808 16 pin DAN5-6-4 Item 964 36 pin DAN5-6-5 Item 965

8 pin DAN5-6-6 Item 966 2 pin DAN5-6-7 Item 967 6 pin DAN5-8-5 Item 985

i Put this items at FR49 in position as shown in Detail C3-3 : 2 bushing D5347658620000 Item 204

j Transfer drill the holes from the frame to the bushings and open the holes to final dimension. k Install these items as shown in Detail C3-3 : 2 bushing D5347658620000 Item 204 with : 2 collar NSA5075-6 Item 806 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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2 pin DAN5-6-7 Item 967 5 Install the sections and the angles at FR49 between STGR34LH/RH an and STGR39LH/RH as shown in Section B15-B3 ’AFTER’ :

a Put these items in position : 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 1 section D5347449520500 Item 032 1 section D5347449520400 Item 034 1 angle D5347470020400 Item 044 1 angle D5347470020500 Item 046 2 angle D5347470020200 Item 048 2 angle D5347470020300 Item 050

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items : 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 1 section D5347449520500 Item 032 1 section D5347449520400 Item 034 1 angle D5347470020400 Item 044 1 angle D5347470020500 Item 046 2 angle D5347470020200 Item 048 2 angle D5347470020300 Item 050 with : 46 rivet MBBN4477-4812 Item 549 40 rivet LN9198-4816CF Item 648 6 Replace the riveting between clip and skin panel at FR49 between STGR34LH/RH and STGR37LH/RH as shown in Section B15-B3 :

a Remove the existing rivets. bOpen the holes and the countersinks to final dimension.

c Install this item : 24 rivet MBBN4477-4812 Item 549 (w) Modify the structure at FR50 between STGR34LH and STGR34RH. Refer to Kit 281132D40R03 Refer to Drawing(s) : D53470075004 Sheet(s) 4 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 Replace the fasteners at FR50 between STGR34RH and STGR36RH as shown in Section C15-C4 ’AFTER’ :

a Remove the existing fasteners in the affected area as shown in Section C15-C4 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR50. 2 Install the reinforcing straps at FR50 between STGR35LH/RH and STGR42LH/RH as shown in Section C15-C4 ’AFTER’ :

a Put these items at FR50 in position : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes to final dimension. d Install these items : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with : 58 rivet LN9198-4012CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit 281132D41R00. 3 Install the fittings at FR50 at STGR37LH/RH as shown in Section C15-C4 ’AFTER’ :

a Put these items at FR50 in position : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

bTransfer drill the holes from the frame to the fittings and open all holes to final dimension.

c Install these items : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with : 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR50 as shown in Section C15-C4 ’AFTER’ :

a Put these items at FR50 in position : 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026 1 crossbeam D5347026000600 Item 052

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 052, IS IN LINE WITH THE CROSSBEAMS AND FR47 AND FR55. bTransfer drill all holes from the frame to the crossbeam.

c Put these items at FR50 between STGR42LH and STGR42RH in position : 1 angle D5347470520000 Item 054 1 angle D5347470520100 Item 056 1 web D5347470320000 Item 066

dTransfer drill the holes from the frame and skin panel to the shear web and the supports.

e Drill all additional holes and open all holes and all countersinks to final dimension. f Install these items : 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026 1 crossbeam D5347026000600 Item 052 1 angle D5347470520000 Item 054 1 angle D5347470520100 Item 056 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 web D5347470320000 Item 066 with : 12 rivet MBBN4477-4812 Item 549

4 rivet LN9198-4014CF Item 640 51 rivet LN9198-4816CF Item 648

6 pin DAN5-6-5X Item 765 56 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 12 collar NSA5075-8 Item 808 20 pin DAN5-6-4 Item 964 32 pin DAN5-6-5 Item 965

4 pin DAN5-6-6 Item 966 6 pin DAN5-8-5 Item 985 4 pin DAN5-8-6 Item 986 2 pin DAN5-8-7 Item 987 5 Install the sections and the angles at FR50 between STGR34LH and STGR34RH as shown in Section C15-C4 ’AFTER’:

a Put these items in position : 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 2 section D5347449520500 Item 032 2 section D5347449520400 Item 034 1 angle D5347470020400 Item 044 1 angle D5347470020500 Item 046 2 angle D5347470020200 Item 048 2 angle D5347470020300 Item 050 1 section D5347449523400 Item 058 1 section D5347449523600 Item 060 2 section D5347449523200 Item 064 1 angle D5347470020800 Item 068 1 angle D5347470021000 Item 070 1 angle D5347470020600 Item 072 1 angle D5347470021200 Item 074

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel and the two holes in the angles, Item 064, and install with these items : 82 rivet MBBN4477-4812 Item 549 69 rivet LN9198-4816CF Item 648

4 collar NSA5075-6 Item 806 4 pin DAN5-6-4 Item 964 6 Replace the riveting between clip and skin panel at FR50 between STGR34LH/RH and STGR37LH/RH as shown in Section C15-C4 ’AFTER’ :

a Remove the existing rivets. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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bOpen the holes and the countersinks to final dimension.

c Install this item : 24 rivet MBBN4477-4812 Item 548 (x) Modify the structure at FR51 between STGR34LH and STGR34RH. Refer to Kit 281132D40R03 Refer to Drawing(s) : D53470075004 Sheet(s) 16 1 Replace the fasteners at FR51 between STGR34RH and STGR36RH as shown in Section D15-D16 ’AFTER’ :

a Remove the existing fasteners in the affected area as shown in Section D15-D16 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 34 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 16 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 6 pin DAN5-6-5 Item 965 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR51. 2 Install the reinforcing straps at FR51 between STGR35LH/RH and STGR42LH/RH as shown in Section D15-D16 ’AFTER’ :

a Put these at FR51 in position : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes and all countersinks to final dimension. d Install these items : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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58 rivet LN9198-4012CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit 281132D41R00. 3 Install the fittings at FR51 at STGR37LH/RH as shown in Section D15-D16 ’AFTER’ :

a Put these items at FR51 in position : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

bTransfer drill the holes from the frame to the fittings and open all holes to final dimension.

c Install these items : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with : 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR51 as shown in Section D15-D16 ’AFTER’ :

a Put these items at FR51 in position : 1 plate D5337217620000 Item 012 2 filler D5337217620800 Item 026 1 crossbeam D5347035300600 Item 076 1 plate D5337217620700 Item 078

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 076, IS IN LINE WITH THE CROSSBEAMS AND FR47 AND FR55. bTransfer drill all holes from the frame to the crossbeam.

c Put this item at FR51 in position as shown in Section B16-B16 : 1 support angle D5347658420000 Item 102

d Put these items at FR51 between STGR42LH and STGR42RH in position : 1 angle D5347470520000 Item 054 1 angle D5347470520100 Item 056 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 web D5347470420400 Item 080

eTransfer drill the holes from the frame and skin panel to the shear web and the supports. f Drill all additional holes and open all holes and all countersinks to final dimension. g Install these items : 1 plate D5337217620000 Item 012 2 filler D5337217620800 Item 026 1 angle D5347470520000 Item 054 1 angle D5347470520100 Item 056 1 crossbeam D5347035300600 Item 076 1 plate D5337217620700 Item 078 1 web D5347470420400 Item 080 1 support angle D5347658420000 Item 102 with : 12 rivet MBBN4477-4812 Item 549 16 rivet LN9198-4014CF Item 640 57 rivet LN9198-4816CF Item 648

6 pin DAN5-6-5X Item 765 44 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 12 collar NSA5075-8 Item 808 19 pin DAN5-6-4 Item 964 21 pin DAN5-6-5 Item 965

2 pin DAN5-6-6 Item 966 2 pin DAN5-6-8 Item 968 6 pin DAN5-8-5 Item 985 3 pin DAN5-8-6 Item 986 3 pin DAN5-8-7 Item 987 5 Install the sections and the angles at FR51 between STGR34LH/RH and STGR42LH/RH as shown in Section D15-D16 ’AFTER’:

a Put these items in position : 1 section D5347449520300 Item 028 1 section D5347449520500 Item 032 1 angle D5347470020400 Item 044 2 angle D5347470020200 Item 048 1 angle D5347470021600 Item 082 1 angle D5347470021800 Item 084 1 angle D5347470024800 Item 086 1 angle D5347470043800 Item 088 1 angle D5347470021400 Item 090 1 angle D5347470022200 Item 092 1 section D5347449520200 Item 094 1 section D5347449520400 Item 096 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 angle D5347470020500 Item 098 2 angle D5347470020300 Item 100

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel and install with these items : 34 rivet MBBN4477-4812 Item 549 62 rivet LN9198-4816CF Item 648

4 pin DAN6-6-7X Item 667 4 pin DAN6-6-9X Item 669 27 collar NSA5075-6 Item 806

8 collar DAN11-6X Item 807 17 pin DAN6-6-5 Item 865 10 pin DAN6-6-7 Item 867 6 Replace the riveting between clip and skin panel at FR51 between STGR40LH/RH and STGR42LH/RH as shown in Section D15-D16 ’AFTER’ :

a Remove the existing rivets. bOpen the holes and the countersinks to final dimension.

c Install these items : 8 rivet MBBN4477-4812 Item 549 4 pin DAN6-6-7X Item 667 4 pin DAN6-6-9X Item 669 8 pin DAN6-6-8Y Item 678 8 collar NSA5330-6 Item 803 8 collar DAN11-6X Item 807 7 Replace the riveting between stringer and skin panel at FR51 at STGR41RH as shown in Detail A16-A16 :

a Remove the existing rivets. bOpen the holes and the countersinks to final dimension.

c Install these items : 8 pin DAN6-6-8Y Item 678 8 collar NSA5330-6 Item 803 (y) Modify the structure at FR52 between STGR34LH and STGR34RH. Refer to Kit 281132D06R01 Refer to Drawing(s) : D53470076004 Sheet(s) 2, 6 and 7 1 Replace the fasteners at FR52 between STGR34RH and STGR36RH as shown in Section A1-A2 ’AFTER’ : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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a Remove the affected fasteners between STGR34RH and STGR36RH as shown in Section A1-A2 ’AFTER’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 24 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 15 pin DAN5-6-3 Item 963

5 pin DAN5-6-4 Item 964 NOTE : The collars, Item 806, and the fasteners, Item 865, will be installed during the installation of the reinforcing straps at FR52. 2 Install the reinforcing straps at FR52 between STGR35LH/RH and STGR42LH/RH as shown in Section A1-A2 ’AFTER’ :

a Put these items at FR52 in position : 1 strap (LH) D5347448420200 Item 202 1 strap (RH) D5347448420300 Item 203

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes to final dimension. d Install these items : 1 strap (LH) D5347448420200 Item 202 1 strap (RH) D5347448420300 Item 203 with : 58 rivet LN9198-4012CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : The collars and the fasteners, Item 806 and Item 865, are supplied in Kit 281132D08R00. 3 Install the fittings at FR52 at STGR37LH/RH as shown in Section A1-A2 ’AFTER’ :

a Put these items at FR52 in position : 1 fitting (LH) D5347449420600 Item 200 1 fitting (RH) D5347449421100 Item 201 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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bTransfer drill the holes from the frame to the fittings and open all holes to final dimension.

c Install these items : 1 fitting (LH) D5347449420600 Item 200 1 fitting (RH) D5347449421100 Item 201 with : 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Reinforce the crossbeam attachment at FR52 as shown in Section A1-A2 ’AFTER’ :

a Remove the crossbeam from FR52 temporarily. b Put these items with the removed crossbeam at FR52 in position : 1 fitting D5347449320000 Item 010 1 reinforcing sheet D5337217620000 Item 012 1 L-profile D5347449521600 Item 014 1 fitting D5347658920000 Item 016 1 shim D5347659220000 Item 018 1 fitting D5347659020000 Item 020 1 shim D5337217620800 Item 032 2 shim D5337217620400 Item 038 1 shim D5347658220200 Item 048 1 support D5347037820400 Item 204 1 fitting D5347449920200 Item 206 1 fitting D5347449820400 Item 244

CAUTION : ENSURE THAT THE CROSSBEAM IS IN LINE WITH THE CROSSBEAMS AT FR47 AND FR55.

c Transfer drill all holes from the frame. d Put these items at FR52 between STGR42LH and STGR42RH in position : 1 support D5347470520000 Item 040 1 support D5347470520100 Item 041 1 web D5347657720000 Item 208

eTransfer drill the holes from the frame and skin panel to the shear web and the supports. f Drill all additional holes and open all holes to final dimension.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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g Install the crossbeam with these items at FR52 as shown in Section A1-A2 ’AFTER’ : 1 fitting D5347449320000 Item 010 1 reinforcing sheet D5337217620000 Item 012 1 L-profile D5347449521600 Item 014 1 fitting D5347658920000 Item 016 1 shim D5347659220000 Item 018 1 fitting D5347659020000 Item 020 1 shim D5337217620800 Item 032 2 shim D5337217620400 Item 038 1 support D5347470520000 Item 040 1 support D5347470520100 Item 041 1 shim D5347658220200 Item 048 1 support D5347037820400 Item 204 1 fitting D5347449920200 Item 206 1 web D5347657720000 Item 208 1 fitting D5347449820400 Item 244 with : 12 rivet MBBN4477-4810 Item 549

6 rivet LN9198-4014CF Item 640 39 rivet LN9198-4816CF Item 648

6 rivet LN9198-6412CF Item 664 6 pin DAN5-6-5X Item 765 65 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 9 collar NSA5075-8 Item 808 10 pin DAN5-6-3 Item 963 15 pin DAN5-6-4 Item 964 37 pin DAN5-6-5 Item 965

1 pin DAN5-6-6 Item 966 2 pin DAN5-6-7 Item 967 3 pin DAN5-8-5 Item 985 4 pin DAN5-8-6 Item 986 2 pin DAN5-8-7 Item 987 5 Install this item at the crossbeam at FR52 as shown in drawing D53470076004, Sheet 7, Detail X1-7 :

a Drill the two holes and open the holes to final dimension. b Install this item : 2 rivet LN9198-4014CF Item 640 6 Replace the fasteners at FR52 between STGR41LH/RH and STGR42LH/RH :

a Remove the fasteners as shown in Section A1-A2 ’BEFORE’. bOpen the holes to final dimension. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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c Install these items as shown in Section A1-A2 ’AFTER’ : 10 rivet LN9198-4816CF Item 648 7 Install the L-profiles and the angles at FR52 between STGR34LH/RH and STGR42LH/RH as shown in Section A1-A2 ’AFTER’ :

a Put these items in position : 2 angle D5347470020200 Item 022 1 angle D5347470020300 Item 023 1 angle D5347470020400 Item 024 1 L-profile D5347449520400 Item 026 1 L-profile D5347449520500 Item 027 1 L-profile D5347449520300 Item 028 1 angle D5347470021400 Item 030 1 angle D5347470023200 Item 034 1 angle D5347470023400 Item 036 1 angle D5347470021000 Item 042 1 angle D5347470021200 Item 044 1 angle D5347470024000 Item 046 1 angle D5347470023800 Item 050 1 angle D5347470023600 Item 052 1 key D5347550021000 Item 082

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items : 2 angle D5347470020200 Item 022 1 angle D5347470020300 Item 023 1 angle D5347470020400 Item 024 1 L-profile D5347449520400 Item 026 1 L-profile D5347449520500 Item 027 1 L-profile D5347449520300 Item 028 1 angle D5347470021400 Item 030 1 angle D5347470023200 Item 034 1 angle D5347470023400 Item 036 1 angle D5347470021000 Item 042 1 angle D5347470021200 Item 044 1 angle D5347470024000 Item 046 1 angle D5347470023800 Item 050 1 angle D5347470023600 Item 052 1 key D5347550021000 Item 082 with : 43 rivet MBBN4477-4810 Item 549 59 rivet LN9198-4816CF Item 648 23 collar NSA5075-6 Item 806

8 pin DAN6-6-3 Item 863 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 pin DAN6-6-5 Item 865 10 pin DAN6-6-6 Item 866

3 pin DAN6-6-7 Item 867 1 pin DAN6-6-8 Item 868 8 Replace the riveting between clip and skin panel at FR52 between STGR35LH/RH and STGR42LH/RH as shown in Section A1-A2 ’AFTER’ :

a Remove the existing rivets. bOpen the holes and the countersinks to final dimension.

c Install these items : 25 rivet MBBN4477-4810 Item 549 27 collar NSA5075-6 Item 806

8 pin DAN6-6-3 Item 863 4 pin DAN6-6-4 Item 864 1 pin DAN6-6-5 Item 865 10 pin DAN6-6-6 Item 866

3 pin DAN6-6-7 Item 867 1 pin DAN6-6-8 Item 868 (z) Modify the structure at FR52A between STGR38RH and STGR40RH. Refer to Kit 281132D06R01 Refer to Drawing(s) : D53470076004 Sheet(s) 3 1 Remove these items from FR52A as shown in drawing D53470076004, Sheet 3, Detail A3-3 and Section B1-B3 ’BEFORE’.

a Remove and discard these items : 1 nut NAS1791A3-1 Item (460) Discard 1 nut NAS1068C3 Item (462) Discard

bClose the existing rivet holes with this item : 4 rivet DIN65399-2400CF Item 724 2 Close the existing rivet holes at FR52A as shown in drawing D53470076004, Sheet 3, Detail B3-3 ’AFTER’.

a Install these items : 2 pin DAN6-6-5X Item 665 2 collar DAN11-6X Item 807 3 Install the fitting at FR52A as shown in drawing D53470076004, Sheet 3, Section B1-B3 ’AFTER’.

a Put this item at FR52A in position : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 fitting D5347659320000 Item 054

b Drill all additional holes and open all holes to final dimension.

c Install this item at FR52A : 1 fitting D5347659320000 Item 054 with these items : 11 collar NSA5075-6 Item 806

5 pin DAN5-6-4 Item 964 3 pin DAN5-6-6 Item 966 3 pin DAN5-6-9 Item 969 (aa) Modify the structure at FR53 between STGR34LH and STGR41RH. Refer to Kit 281132D06R01 Refer to Drawing(s) : D53470076004 Sheet(s) 4 1 Install the fitting at FR53 at STGR37LH as shown in Section C1-C4 ’AFTER’ :

a Put this item at FR53 in position : 1 fitting (LH) D5347449420600 Item 200

bTransfer drill the holes from the frame to the fitting and open all holes to final dimension.

c Install this item : 1 fitting (LH) D5347449420600 Item 200 with : 17 collar NSA5075-6 Item 806

7 pin DAN5-6-4 Item 964 4 pin DAN5-6-5 Item 965 4 pin DAN5-6-6 Item 966 2 pin DAN5-6-7 Item 967 2 Install the crossbeam at FR53 as shown in Section C1-C4 ’AFTER’ :

a Put these items at FR53 in position : 1 plate D5337217621000 Item 056 1 shim D5337217621200 Item 060 1 crossbeam D5347026100600 Item 218

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 218, IS IN LINE WITH THE CROSSBEAMS AND FR47 AND FR55. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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bTransfer drill all holes from the frame.

c Put these items at FR53 between STGR42LH and STGR42RH in position : 1 support D5347470520300 Item 066 1 web D5347657820000 Item 068 1 web D5347658820000 Item 070 1 support D5347470520500 Item 104

dTransfer drill the holes from the frame and skin panel to the shear web and the supports.

e Drill all additional holes and open all holes to final dimension. f Install these item : 1 plate D5337217621000 Item 056 1 shim D5337217621200 Item 060 1 support D5347470520300 Item 066 1 web D5347657820000 Item 068 1 web D5347658820000 Item 070 1 support D5347470520500 Item 104 1 crossbeam D5347026100600 Item 218 with : 4 rivet MBBN4477-4010 Item 541 13 rivet MBBN4477-4810 Item 549

4 rivet LN9198-4014CF Item 640 42 rivet LN9198-4816CF Item 648

3 pin DAN5-6-5X Item 765 30 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 6 collar NSA5075-8 Item 808 3 pin DAN5-6-3 Item 963 11 pin DAN5-6-4 Item 964 12 pin DAN5-6-5 Item 965

2 pin DAN5-6-6 Item 966 3 pin DAN5-8-5 Item 985 4 pin DAN5-8-6 Item 986 2 pin DAN5-8-7 Item 987 3 Replace the fasteners at FR53 between STGR41LH and STGR42LH :

a Remove the fasteners as shown in Section C1-C4 ’BEFORE’. bOpen the holes to final dimension.

c Install this item as shown in Section C1-C4 ’AFTER’ : 5 rivet LN9198-4816CF Item 648

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 311 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

4 Install the L-profiles and the angles at FR53 between STGR34LH and STGR41RH as shown in Section C1-C4 ’AFTER’ :

a Put these items in position : 2 angle D5347470020200 Item 022 1 angle D5347470020400 Item 024 1 L-profile D5347449520500 Item 027 1 L-profile D5347449520300 Item 028 1 angle D5347470024200 Item 058 1 angle D5347470024400 Item 062 1 angle D5347470024600 Item 064 1 L-profile D5347449523800 Item 094 1 L-profile D5347449523400 Item 096 2 L-profile D5347449524000 Item 098 1 L-profile D5347449524200 Item 100 1 shim D5347044922600 Item 106 3 shim D5347044922800 Item 108

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items : 2 angle D5347470020200 Item 022 1 angle D5347470020400 Item 024 1 L-profile D5347449520500 Item 027 1 L-profile D5347449520300 Item 028 1 angle D5347470024200 Item 058 1 angle D5347470024400 Item 062 1 angle D5347470024600 Item 064 1 L-profile D5347449523800 Item 094 1 L-profile D5347449523400 Item 096 2 L-profile D5347449524000 Item 098 1 L-profile D5347449524200 Item 100 1 shim D5347044922600 Item 106 3 shim D5347044922800 Item 108 with : 41 rivet MBBN4477-4810 Item 549 40 rivet LN9198-4816CF Item 648 16 collar NSA5075-6 Item 806 12 pin DAN6-6-3 Item 863

4 pin DAN5-6-3 Item 963 5 Replace the riveting between clip and skin panel at FR53 between STGR34LH and STGR42LH and between STGR41RH and STGR42RH as shown in Section C1-C4 :

a Remove the existing rivets. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 312 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

bOpen the holes and the countersinks to final dimension.

c Install these items : 28 rivet MBBN4477-4810 Item 549 12 collar NSA5075-6 Item 806 12 pin DAN6-6-3 Item 863 (ab) Modify the structure at FR53 between STGR36LH and STGR42LH. Refer to Kit 281132D40R03 Refer to Drawing(s) : D53470075004 Sheet(s) 6 1 Remove this item at FR53 as shown in Section E15-E6 ’BEFORE’ :

a Remove and discard this item : 1 shim D5347061120200 Item (402) Discard 2 Install the reinforcing strap at FR53 between STGR35LH and STGR42LH as shown in Section E15-E6 ’AFTER’ :

a Put this item at FR53 in position : 1 strap D5347448420200 Item 022

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes and all countersinks to final dimension. d Install these items : 1 strap D5347448420200 Item 022 with : 29 rivet LN9198-4014CF Item 640

4 collar NSA5075-6 Item 806 4 pin DAN6-6-5 Item 865 NOTE : The collars and the fasteners, Item 806 and Item 865, are supplied in Kit 281132D08R00. (ac) Modify the structure at FR54 between STGR34LH and STGR41RH. Refer to Kit 281132D06R01 Refer to Drawing(s) : D53470076004 Sheet(s) 5 1 Install the reinforcing strap at FR54 between STGR35LH and STGR42LH as shown in Section D1-D5 ’AFTER’ : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 313 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Put this item at FR54 in position : 1 strap (LH) D5347448420200 Item 202

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing strap to the frame and open all holes to final dimension. d Install this item : 1 strap (LH) D5347448420200 Item 202 with : 29 rivet LN9198-4014CF Item 640

4 collar NSA5075-6 Item 806 4 pin DAN6-6-5 Item 865 NOTE : The collars and the fasteners, Item 806 and Item 865, are supplied in Kit 281132D08R00. 2 Install the fitting at FR54 at STGR37LH as shown in Section D1-D5 ’AFTER’ :

a Put this item at FR54 in position : 1 fitting (LH) D5347449420600 Item 200

bTransfer drill the holes from the frame to the fitting and open all holes to final dimension.

c Install this item : 1 fitting (LH) D5347449420600 Item 200 with : 17 collar NSA5075-6 Item 806

7 pin DAN5-6-4 Item 964 4 pin DAN5-6-5 Item 965 4 pin DAN5-6-6 Item 966 2 pin DAN5-6-7 Item 967 3 Install the crossbeam at FR54 as shown in Section D1-D5 ’AFTER’ :

a Put these items at FR54 in position : 1 shim D5337217621200 Item 060 1 plate D5337217625800 Item 110 1 crossbeam D5347035601400 Item 230

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 230, IS IN LINE WITH THE CROSSBEAMS AT FR47 AND FR55. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 314 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

bTransfer drill all holes from the frame.

c Put these items at FR54 between STGR42LH and STGR42RH in position : 1 web D5347657920000 Item 076 1 L-profile D5347449522600 Item 078 1 L-profile D5347449522800 Item 080

dTransfer drill the holes from the frame and skin panel to the shear web and the L-profile.

e Drill all additional holes and open all holes and all countersinks to final dimension. f Install these items : 1 shim D5337217621200 Item 060 1 web D5347657920000 Item 076 1 L-profile D5347449522600 Item 078 1 L-profile D5347449522800 Item 080 1 plate D5337217625800 Item 110 1 crossbeam D5347035601400 Item 230 with : 4 rivet MBBN4477-4010 Item 541 16 rivet MBBN4477-4810 Item 549

8 rivet LN9198-4014CF Item 640 42 rivet LN9198-4816CF Item 648

3 pin DAN5-6-5X Item 765 28 collar NSA5075-6 Item 806

3 collar DAN11-6X Item 807 9 collar NSA5075-8 Item 808 10 pin DAN5-6-4 Item 964 16 pin DAN5-6-5 Item 965

2 pin DAN5-6-6 Item 966 3 pin DAN5-8-5 Item 985 4 pin DAN5-8-6 Item 986 2 pin DAN5-8-7 Item 987 4 Replace the fasteners at FR54 between STGR41LH and STGR42LH :

a Remove the fasteners as shown in Section D1-D5 ’BEFORE’. bOpen the holes to final dimension.

c Install this item as shown in Section D1-D5 ’AFTER’ : 6 rivet LN9198-4816CF Item 648 5 Install the L-profile and the angles at FR54 between STGR34LH and STGR42LH as shown in Section D1-D5 ’AFTER’: DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 315 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Put these items in position : 2 angle D5347470020200 Item 022 1 angle D5347470020400 Item 024 1 L-profile D5347449520500 Item 027 1 L-profile D5347449520300 Item 028 1 angle D5347470024200 Item 058 1 angle D5347470025000 Item 072 1 angle D5347470025200 Item 074

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items : 2 angle D5347470020200 Item 022 1 angle D5347470020400 Item 024 1 L-profile D5347449520500 Item 027 1 L-profile D5347449520300 Item 028 1 angle D5347470024200 Item 058 1 angle D5347470025000 Item 072 1 angle D5347470025200 Item 074 with : 23 rivet MBBN4477-4810 Item 549 29 rivet LN9198-4816CF Item 648 12 collar NSA5075-6 Item 806 12 pin DAN6-6-3 Item 863 6 Replace the riveting between clip and skin panel at FR54 between STGR34LH and STGR42LH as shown in Section D1-D5 ’AFTER’ :

a Remove the existing rivets. bOpen the holes and the countersinks to final dimension.

c Install these items : 23 rivet MBBN4477-4810 Item 549 12 collar NSA5075-6 Item 806 12 pin DAN6-6-3 Item 863 (ad) Install the shear plates between FR48 and FR51 at STGR43LH. 1 Install the shear plate between FR48 and FR49 at STGR43LH as shown in Section F15-F7 : Refer to Kit 281132D40R03 Refer to Drawing(s) : D53470075004 Sheet(s) 3 and 7 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 316 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Put this item in position : 1 plate D5347471321200 Item 104

b Put this item in position as shown in Sheet 3, Section B15-B3 : 1 section D5347449521800 Item 020

c Transfer drill the holes to the section, Item 020. d Drill the additional holes from the shear plate to the stringer and crossbeams and open all holes to final dimension.

e Install these items : 1 section D5347449521800 Item 020 1 plate D5347471321200 Item 104 with : 34 rivet LN9198-4014CF Item 640

2 rivet LN9198-4816CF Item 648 2 collar NSA5075-6 Item 806 2 pin DAN5-6-7 Item 967 2 Install the shear plates between FR49 and FR51 at STGR43LH as shown in Section F15-F7 : Refer to Drawing(s) : D53470075004 Sheet(s) 4, 7 and 16

a Put this item in position : 1 angle D5347471322400 Item 138 1 angle D5347471322600 Item 140

b Put this item in position as shown in Sheet 4, Section C15-C4 and Sheet 16, Section D15-D16. 2 section D5347449522000 Item 062

c Transfer drill the holes to the sections, Item 062. d Drill the additional holes from the shear plate to the stringer and crossbeams and open all holes to final dimension.

e Install these items : 2 section D5347449522000 Item 062 1 angle D5347471322400 Item 138 1 angle D5347471322600 Item 140 with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 317 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

59 rivet LN9198-4014CF Item 640

4 rivet LN9198-4816CF Item 648 4 collar NSA5075-8 Item 808 4 pin DAN5-8-7 Item 987 (ae) Install the shear plates between FR51 and FR54 at STGR43LH. Refer to Kit 281132D06R01 Refer to Drawing(s) : D53470076004 Sheet(s) 2, 4, 5 and 6 1 Install the shear plate between FR51 and FR52 at STGR43LH as shown in drawing D53470076004, Sheet 6, Section E1-E6 and Sheet 2, Section A1-A2 ’AFTER’ :

a Put these items in position : 1 shear plate D5347471320800 Item 084 1 L-profile D5347449522000 Item 088

bTransfer drill the holes to the L-profile, Item 088.

c Drill the additional holes from the shear plate to the stringer and crossbeams and open all holes to final dimension. d Install these items : 1 shear plate D5347471320800 Item 084 1 L-profile D5347449522000 Item 088 with : 29 rivet LN9198-4014CF Item 640

7 rivet LN9198-4816CF Item 648 2 collar NSA5075-8 Item 808 2 pin DAN5-8-7 Item 987 2 Install the shear plate between FR52 and FR53 at STGR43LH as shown in drawing D53470076004, Sheet 6, Section E1-E6 and Sheet 4, Section C1-C4 ’AFTER’ :

a Put these items in position : 1 L-profile D5347449522200 Item 090 1 shear plate D5347471321800 Item 102

bTransfer drill the holes to the L-profile, Item 090.

c Drill the additional holes from the shear plate to the stringer and crossbeams and open all holes to final dimension. d Install these items : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 318 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 L-profile D5347449522200 Item 090 1 shear plate D5347471321800 Item 102 with : 29 rivet LN9198-4014CF Item 640

7 rivet LN9198-4816CF Item 648 2 collar NSA5075-8 Item 808 2 pin DAN5-8-7 Item 987 3 Install the shear plate between FR53 and FR54 at STGR43LH as shown in drawing D53470076004, Sheet 6, Section E1-E6 and Sheet 5, Section D1-D5 ’AFTER’ :

a Remove and discard this item at STGR43LH as shown in drawing D53470076004, Sheet 6, Section E1-E6 and Detail A6-6 : 1 section D5347065620200 Item (442) Discard

b Put these items in position as shown in drawing D53470076004, Sheet 6, Section E1-E6 and Detail A6-6 and Sheet 5, Section D1-D5 : 1 shear plate D5347471321000 Item 086 1 L-profile D5347449522400 Item 092 1 shim D5347044924200 Item 150 NOTE 1 section D5347065620400 Item 242 NOTE : And/or PN D5347044920000, as required.

c Transfer drill the holes, drill the additional holes and open all holes to final dimension. d Install these items : 1 shear plate D5347471321000 Item 086 1 L-profile D5347449522400 Item 092 1 shim D5347044924200 Item 150 1 section D5347065620400 Item 242 with : 26 rivet LN9198-4014CF Item 640

7 rivet LN9198-4816CF Item 648 2 pin DAN6-6-5X Item 665 4 pin DAN6-6-6X Item 666 6 pin DAN6-6-7X Item 667 8 pin DAN5-6-7X Item 767 20 collar DAN11-6X Item 807

2 collar NSA5075-8 Item 808 2 pin DAN5-8-7 Item 987

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 319 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(af) Drill additional fastener holes between FR51 and FR54. D53470076004 Sheet(s) 7 1 Drill additional fastener holes between FR51 and FR54, refer to drawing D53470076004, Sheet 7, Detail X1-7. (ag) Modify the structure between FR47 and FR48 at STGR38LH/RH and STGR43LH. Refer to Kit 281132D05R01 Refer to Drawing(s) : D53372362004 Sheet(s) 7 1 Remove the nuts at STGR38LH and STGR38RH as shown in Detail W1-7.

a Remove and discard this item : 6 nut NAS1791A3-1 Item (216) Discard 2 Remove the connections at STGR38LH and STGR38RH as shown in Detail W1-7.

a Remove and discard these items : 1 connection (LH) D5347101620400 Item (210) Discard 1 connection (RH) D5347101620500 Item (211) Discard 3 Install the plates, the sections and the connections at STGR38LH and STGR38RH as shown in Detail W1-7. Refer to Drawing(s) : D53372362004

aAt STGR38LH : Put these items in position : 1 plate D5337217400000 Item 024 1 section D5347449520800 Item 028 1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620400 Item 042 NOTE : Install the fillers, Item 030, 032, 034, 036 and 038, as required. NOTE : Install the section, Item 028, together with the angle, Item 130. bAt STGR38RH : Put these items in position : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 320 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 plate D5337217400100 Item 025 1 section D5347449520900 Item 029 1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620500 Item 043 NOTE : Install the fillers, Item 030, 032, 034, 036 and 038, as required. NOTE : Install the section, Item 029, together with the angle, Item 134, at FR48.

cTransfer drill the holes from the skin panel and the stringer to the connections. d Drill the additional holes in the plates, sections and connections and open all holes and all countersinks to final dimension.

e Install these items at STGR38LH : 1 plate D5337217400000 Item 024 1 section D5347449520800 Item 028 1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620490 Item 042 with : 6 rivet NAS1097AD4-10 Item 532 21 rivet LN9198-4014CF Item 640

1 pin DAN5-6-6X Item 766 4 pin DAN5-6-7X Item 767 13 pin DAN5-6-8X Item 768

1 pin DAN5-6-9X Item 769 6 collar NSA5075-6 Item 806 19 collar DAN11-6X Item 807

4 pin DAN5-6-5 Item 965 2 pin DAN5-6-9 Item 969

f Install these items at STGR38RH : 1 plate D5337217400100 Item 025 1 section D5347449520900 Item 029 1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 321 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(4) Config. 02 AI-F Part 281132A00002 A00 Sheet(s) 01 281132A00002 A00 Sheet(s) 02 281132A00002 A00 Sheet(s) 03 281132A00002 A00 Sheet(s) 04 281132A00002 B00 Sheet(s) 05 (a) Install the doublers on the upper surface panels Refer to Kit 281132A20R00 281132A20001 A00 Sheet(s) 01 281132A20001 A00 Sheet(s) 02 281132A20001 A00 Sheet(s) 03 281132A20002 A00 Sheet(s) 01 NOTE : Remove the finch paint and the paint protection from the extrados panel between Y=+254 and Y=-254 and between FR36 and FR42. Do not use a metallic tool. Do not cause damage to the head of the 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. 1 Drill one hole to a diameter of 64 mm (2.519 in.) and one hole to a diameter of 74 mm (2.913 in.), (Refer to drawing 281132A20001, Sheets 1 and 2). 1 Loft D5713032000095 2 Install : 281132A20001 A00 Sheet(s) 03 Item 0 1 Doubler D5713304820004

Item 1 1 Doubler D5713031920000

Attach with : Fuel Tank Sealant Polysulfid (Mat. No. 09-002) Item 10 19 Bolt EN6115V3-3 Item 11 15 Bolt EN6115V3-4 Item 12 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 322 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

15 Bolt EN6115V3-5 Item 13 29 Pin-Hi Lok NSA5357-3-6 Item 14 12 Pin-Hi Lok NSA5357-3-7 Item 15 16 Pin-Hi Lok NSA5357-3-5 Item 22 8 Pin-Hi Lok NSA5357-4-7

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

Item 30 57 Collar NSA5330-6 Item 35 49 Nut ASNA2528-3 Item 40 13 Collar NSA5330-8 3 Install : 281132A20002 A00 Sheet(s) 01 Item 0 1 Bracket Assy D5791332400000

Item 1 1 Bracket Assy D5791332300000

Attach with : Item 10 2 Bolt EN6115V3-5

Item 11 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 323 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

4 Nut ASNA2528-3

Item 12 2 Bolt EN6115V3-7 (b) Install the brackets on the upper surface panels Refer to Kit 281132A20R00 281132A20003 A00 Sheet(s) 01 281132A20003 A00 Sheet(s) 02 281132A20003 A00 Sheet(s) 03 281132A20003 A00 Sheet(s) 04 Item 1 1 Support Assy D5791049500095 Item 2 1 Support Assy D5791049400095 Item 3 1 Fitting D5791048300095 Item 4 1 Fitting D5791048200095 Item 5 1 Fitting D5791042020095 Item 6 1 Fitting D5791042120095 Item 9 1 Fitting D5791043020095 Item 10 1 Fitting D5791049820095 Item 11 1 Fitting D5791050020095 Item 12 1 Support D5791042320095 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 324 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 13 1 Support D5791042220095 Item 21

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

4 Rivet ASNA2050DCJ3215 Item 100

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

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

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

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

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

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

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

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

22 Collar NSA5330-6 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 325 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 130

18 Collar NSA5330-8 (c) Install the rod on the upper surface panels Refer to Kit 281132A20R00 281132A20004 A00 Sheet(s) 01 Item 0 1 Rod D2821334100300 Item 4 1 Bracket D2821334220000 Attach with : Item 12

4 Bolt NAS6603-4 Item 14

2 Bolt NAS6604-9 Item 20

4 Nut NSA5050-3 Item 22

2 Nut NSA5050-4 Item 24

4 Washer ASNA2397-10L Item 26

2 Washer ASNA2397-416L (d) Install the bracket on FR42 Refer to Kit 281132A21R01 281132A21001 A00 Sheet(s) 01 NOTE : Remove the finch paint and the paint protection in the center tank. Do not use a metallic tool. Do not cause damage to the head of the 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. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 326 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 12 1 Angle D5791317500002 Attach with : Item 51

2 Bolt EN6115V3-6 Item 52

2 Nut ASNA2536-3 (e) Install the bracket above FR42 Refer to Kit 281132A20R00 281132A21002 A00 Sheet(s) 01 281132A21002 A00 Sheet(s) 02 281132A21002 A00 Sheet(s) 03 Item 0 1 Support D5791041820095 Attach with : Item 10 Fuel Tank Sealant Polysulfid (Mat. No. 09-002) Item 60

2 Bolt EN6115V4X-11 Item 65

2 Bolt EN6115V5X-13 Item 75

2 Nut ASNA2536-4 Item 80

2 Nut ASNA2536-5 (f) Install the brackets on the lower surface panels Refer to Kit 281132A21R01 and Kit 281132A22R00 281132A21003 A00 Sheet(s) 01 281132A21003 B00 Sheet(s) 02 281132A21003 A00 Sheet(s) 03 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 327 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 1 1 Machined Bracket D5791040320095 Item 2 1 Support Assy D5791040500095 Item 3 1 Support Assy D5791040400095 Item 4 1 Machined Bracket D5791050820001 Item 5 1 Machined Bracket D5791040020095 Item 6 1 Machined Bracket D5791050920001 Item 7 1 Machined Bracket D5791040820095 Item 8 1 Machined Bracket D5791040920095 Item 9 1 Machined Bracket D5791040620095 Item 10 1 Machined Bracket D5791040720095 Item 11 1 Machined Bracket D5791041020095 Attach with : Item 20 Fuel Tank Sealant Polysulfid (Mat. No. 09-002) Item 44

4 Bolt NAS6603-4 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 328 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 62

4 Nut NSA5050-3 Item 157

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

5 Pin-Hi Lok NSA5357-4-10 Item 159

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

31 Collar NSA5330-8 Item 170 1 Collar NSA5330-10 (g) Install the rod and the plate on the lower surface panels Refer to Kit 281132A21R01 281132A21004 A00 Sheet(s) 01 281132A21004 A00 Sheet(s) 02 Item 2 1 Rod D2821334100400 Item 6 1 Bracket D2821040220000 Item 8 1 Plate D2821040120000 Attach with : Item 10 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 329 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

8 Bolt NAS6603-2 Item 12

4 Bolt NAS6603-4 Item 14

2 Bolt NAS6604-9 Item 20

4 Nut NSA5050-3 Item 22

2 Nut NSA5050-4 Item 24

12 Washer ASNA2397-10L Item 26

2 Washer ASNA2397-416L (h) Install the Additional Center Tank (ACT) door Refer to Kit 281132A03R01 281132A03001 A00 Sheet(s) 01 281132A03002 A00 Sheet(s) 01 281132A03002 A00 Sheet(s) 02 1 Remove : 281132A03001 A00 Sheet(s) 01 1 Door Assy D5713019400200 1 Screw Item (4) Discard 1 Washer Item (8) Discard 15 Washer Item (5) Discard 15 Screw Item (6) Discard 15 Washer Item (7) Discard 2 Install : 281132A03002 A00 Sheet(s) 01 281132A03002 A00 Sheet(s) 02 1 Door Assy D5713323000000

Item 0 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 330 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Fairing D5713334000000

Item 1 1 Intrados Fitting D5713334600000

Item 2 1 Fitting D5713334500000

Item 3 1 Fitting D5713334400000

Attach with : Item 30 Fuel Tank Sealant Polysulfid (Mat. No. 09-002) Item 6 8 Washer A5713052120300

Item 10 3 Bolt NAS6603-2

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

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

Item 22 6 Bolt NAS6604-3

Item 40 6 Washer ASNA2397D416L (i) Install the equipment on the ACT door DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 331 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Kit 281132A03R01 and Kit 281132A14R00 281132A03003 B00 Sheet(s) 01 281132A03003 A00 Sheet(s) 02 281132A03003 A00 Sheet(s) 03 281132A03003 A00 Sheet(s) 04 281132A03003 B00 Sheet(s) 05 281132A14001 A00 Sheet(s) 01 1 Install the pressure switch 2QH : 281132A03003 A00 Sheet(s) 02 Item 0 1 Pressure Switch HTE690045

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

Item 10 1 Plug A2823260820000

Item 12 1 Safety Valve A2823260500000

Item 18 3 Packing NSA8200-6

Item 20 1 O-Ring NSA8203-019

Item 22 4 Bolt NAS6603-5

Item 24 4 Washer-Sealing ASNA2055-03

Item 26 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 332 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

4 Nut NSA5050-3

Item 28 1 M Wire-Lock MS20995C32 2 Install the fuel pump 1QH and the mounting plate 163QM : 281132A03003 A00 Sheet(s) 03 Item 0 1 Fuel Pump 568-1-27170-002

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

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

Item 12 1 Insert A2821064620000

Item 14 1 Spring A2821064720000

Item 18 1 O-Ring NSA8203-113

Item 22 1 O-Ring NSA8203-167

Item 24 1 O-Ring NSA8203-224

Item 26 1 O-Ring NSA8203-226

Item 28 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 333 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 Bonding Lead E0088-10-100

Item 29 4 Bolt NAS6603-1

Item 30 6 Bolt NAS6604-7

Item 32 1 Bolt NAS6604-20

Item 34 1 Seal Washer NSA5112-04

Item 36 6 Washer ASNA2397-416

Item 38 1 Washer ASNA2397-416L

Item 39 4 Washer ASNA2397D10L

Item 40 1 Nut NSA5050-4

Item 42 2 Nut NSA5050-3

Item 48Wire-Lock MS20995C32 3 Install the refuel valve 41QU and the canister 164QM : 281132A03003 A00 Sheet(s) 04 Item 0 1 Canister 1158000-15

Item 2 1 Refuel Valve 1158000-21 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 334 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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

Item 8 4 Screw NAS1154-10

Item 10 1 Screw NAS1801-06-6

Item 11 1 Screw NAS1801-3-6

Item 12 1 Washer ASNA2397-6L

Item 13 1 Washer ASNA2397-10L

Item 14 1 Nut MS21042-06

Item 16 4 Nut NAS1726C4E

Item 22 1 Bonding Lead E0088-16-125 4 Install the actuator 6QH and the valve 165QM : 281132A03003 B00 Sheet(s) 05 Item 0 1 Valve HTE900135

Item 2 1 Actuator HTE190001-2 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 335 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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

Item 6 1 O-Ring NSA8203-154

Item 8 6 Screw NAS1153-4

Item 13 1 Screw NAS1801-06-6

Item 17 1 Washer ASNA2397-6L

Item 16 4 Nut NAS1726C4E

Item 18 1 Nut MS21042L06

Item 22 1 Lead-Bonding E0088-16-100

Item 24Wire-Lock MS20995C32 5 Identify the equipment on the ACT door 281132A14001 A00 Sheet(s) 01

a Bond the placards : Item 0 1 Placard D2821336920000 Item 2 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 336 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Placard D2821336920200 Item 4 1 Placard D2821336920400 Item 6 1 Placard D2821336920600 Item 8 1 Placard D2821336920800 (j) Replace the Fuel Quantity Indicator (FQI) 6QT (Refer to AMM 28-42-22, Page block 401) 1 Remove : 1 Fuel Quantity Indicator 1407KID02-03 2 Install : 1 Fuel Quantity Indicator 1418KID01-03 (k) Modify the pipes in the center tank Refer to Kit 281132A04R01 281132A04001 A00 Sheet(s) 01 281132A04001 A00 Sheet(s) 02 281132A04001 A00 Sheet(s) 03 281132A04002 A00 Sheet(s) 01 281132A04002 A00 Sheet(s) 02 281132A04002 A00 Sheet(s) 03 281132A04002 A00 Sheet(s) 04 1 Remove : 281132A04001 A00 Sheet(s) 01 281132A04001 A00 Sheet(s) 02 281132A04001 A00 Sheet(s) 03 Item (2) 1 Pipe Assy D2821008001300

with : Item (5) 2 O-ring Discard

Items (4) and (9) DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 337 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 Screw Retain

Items (8) and (10) 2 Washer Retain 2 Install : 281132A04002 A00 Sheet(s) 01 281132A04002 A00 Sheet(s) 02 281132A04002 A00 Sheet(s) 03 281132A04002 A00 Sheet(s) 04 Item 6 1 Pipe Assy D2821333900000

Item 120 1 Machined Tee D2821331020000

Item 12 1 Pipe Assy D2821333900100

Item 5 4 O-Ring NSA8203-226

Attach with : Item 16 2 Bolt NAS6603-2

Item 18 2 Nut NAS1726-3E

Item 110 4 Bolt NAS6604-5

Item 112 4 Washer ASNA2397-416L

Item 114 4 Nut NAS1726-4E

Items (4) and (9) DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 338 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 Screw

Items (8) and (10) 2 Washer

NOTE : Items (4), (9), (8) and (10) were retained at removal. (l) Install the ACT pipes in the center tank Refer to Kit 281132A04R01 281132A04003 A00 Sheet(s) 01 281132A04003 A00 Sheet(s) 02 281132A04003 A00 Sheet(s) 03 281132A04003 A00 Sheet(s) 04 281132A04003 A00 Sheet(s) 05 281132A04003 B00 Sheet(s) 06 281132A04003 B00 Sheet(s) 07 281132A04004 A00 Sheet(s) 01 281132A04005 A00 Sheet(s) 01 281132A04006 A00 Sheet(s) 01 281132A04007 A00 Sheet(s) 01 281132A04008 A00 Sheet(s) 01 281132A04009 A00 Sheet(s) 01 281132A04010 A00 Sheet(s) 01 281132A04011 A00 Sheet(s) 01 281132A04011 A00 Sheet(s) 02 281132A04012 A00 Sheet(s) 01 281132A04013 B00 Sheet(s) 01 1 Install : 281132A04003 A00 Sheet(s) 01 281132A04003 A00 Sheet(s) 02 281132A04003 A00 Sheet(s) 03 281132A04003 A00 Sheet(s) 04 281132A04003 A00 Sheet(s) 05 281132A04003 B00 Sheet(s) 06 281132A04003 B00 Sheet(s) 07 Item 20 1 Pipe Assy D2821333900900

Item 22 1 Pipe Assy D2821333900300

Item 24 1 Pipe Assy D2821333900400

Item 28 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 339 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Pipe Assy D2821333900600

Item 30 1 Pipe Assy D2821333900700

Item 32 1 Pipe Assy D2821333901000

Item 34 1 Sleeve A2821038600000

Item 36 1 Sleeve D2821333800000

Item 38 1 Pipe Assy D2821334800000

Item 40 1 Pipe Assy D2821334900000

Item 42 1 Pipe Assy D2821335000000

Item 44 1 Pipe Assy D2821338500000

Item 46 1 Pipe Assy D2821335800000

Item 50 1 Restrictor D2821336720240

Attach with : Item 51 1 Clamp NSA5516A04NF

Item 52 1 Union MS21902D4

Item 53 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 340 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Strip-Bonding ASNA0182-1DA

Item 55 2 Nut ABS0107-150

Item 56 3 Nut ABS0107-200

Item 57 2 Ring-Retaining NSA840003-150

Item 58 3 Ring-Retaining NSA840003-200

Item 60 1 Packing NSA8200-4

Item 62 1 O-Ring NSA8203-215

Item 64 12 O-Ring NSA8203-222 Item 66 5 O-Ring NSA8203-226

Item 68 2 Screw NAS1801-06-10

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

Item 73 4 Bolt NAS6603-5

Item 74 4 Bolt NAS6603-7 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 341 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 76 2 Bolt NAS6604-2

Item 77 4 Bolt NAS6604-3

Item 78 2 Nut MS21042L06

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

Item 83 2 Washer ASNA2397-6L

Item 84 8 Washer ASNA2397-10L

Item 90 1 Bonding Lead E0088-10-160

Item 92 2 Bonding Lead E0088-10-200

Item 93 1 Bonding Lead E0088-10-280 2 Install : 281132A04004 A00 Sheet(s) 01 Item 0 1 Machined Tee D2821331620000

Attach with : Item 10 6 Bolt NAS6604-5 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 342 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 12 6 Washer ASNA2397-416L

Item 14 6 Nut NAS1726-4E 3 Install : 281132A04005 A00 Sheet(s) 01 Item 0 1 Machined Elbow D2821332220000

Attach with : Item 10 2 Bolt NAS6604-4

Item 12 2 Washer ASNA2397-416L

Item 14 2 Nut NAS1726-4E 4 Install : 281132A04006 A00 Sheet(s) 01 Item 0 1 Elbow-Moulded A2821120120000

Attach with : Item 10 2 Bolt NAS6604-4

Item 12 2 Washer ASNA2397-416L

Item 14 2 Nut NAS1726-4E

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 343 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

5 Install : 281132A04007 A00 Sheet(s) 01 Item 0 1 Machined Elbow D2821332620000

Attach with : Item 10 2 Bolt NAS6604-5

Item 12 2 Washer ASNA2397-416L

Item 14 2 Nut NAS1726-4E 6 Install : 281132A04008 A00 Sheet(s) 01 Item 0 1 Elbow Assy D2821332900000

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

Item 10 4 Bolt NAS6603-4

Item 12 4 Washer ASNA2397D10L 7 Install : 281132A04009 A00 Sheet(s) 01 Item 0 1 Machined Elbow D2821333220000

Item 2 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 344 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Machined Elbow D2821333420000

Item 4 1 Restrictor D2821336621240

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

Item 10 8 Bolt NAS6603-3

Item 12 8 Washer ASNA2397-10L 8 Install : 281132A04010 A00 Sheet(s) 01 Item 0 1 Valve-Non Return 9843144M

Item 1 1 Flange A2821079520000

Item 2 1 Restrictor D2821335621800

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

Item 4 1 Ring-Retaining NSA840003-200

Item 5 3 O-Ring NSA8203-226 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 345 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 8 4 Bolt NAS6604-12

Item 9 4 Nut NAS1726-4E

Item 11 2 Bonding Lead E0088-10-100

Item 12 2 Nut NAS1726-3E

Item 13 1 Bolt NAS6603-2

Item 14 1 Bolt NAS6603-1

Item 17 1 Bonding Lead E0088-10-200

Item 19 2 Washer ASNA2397-10L 9 Install : 281132A04011 A00 Sheet(s) 01 281132A04011 A00 Sheet(s) 02 Item 54 1 Valve 365A02

Item 35 1 Sleeve Assy D2821336300000

Attach with : Item 55 2 Nut ABS0107-150

Item 57 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 346 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 Ring-Retaining NSA840003-150

Item 61 1 Packing NSA8200-5

Item 64 2 O-Ring NSA8203-222

Item 70 2 Bolt NAS6603-2

Item 80 2 Nut NSA5050-3 10Install : 281132A04012 A00 Sheet(s) 01 Item 0 1 Tee D2821331320000

Attach with : Item 10 4 Bolt NAS6604-5

Item 12 4 Washer ASNA2397-416L

Item 14 4 Nut NAS1726-4E 11Install : 281132A04013 B00 Sheet(s) 01 Item 0 1 Machined Elbow D2821331920000

Item 2 1 Sleeve D2821336500000

Attach with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 347 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 8 2 O-Ring NSA8203-222

Item 10 4 Bolt NAS6603-7

Item 12 4 Washer ASNA2397-416L (m) Install the transfert elbow Refer to Kit 281132A05R00 281132A05001 A00 Sheet(s) 01 Item 0 1 Transfert Elbow Assy D2821330700000 Item 2 1 Nutplate Assy D2821334700000 Item 4 1 Nutplate Assy D2821337500000 Item 8 1 O-Ring NSA8203-148 Attach with : Item 10

6 Bolt NAS6604-9 Item 12

6 Washer ASNA2397-416L Item 14 1 Bolt NAS6603-2 Item 16 1 Washer ASNA2397-10L (n) Install the air ventilation elbow DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 348 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Kit 281132A05R00 281132A05002 A00 Sheet(s) 01 Item 0 1 Elbow Assy D2821337700041 Item 2 1 Nutplate Assy D2821334600000 Item 4 1 Nutplate Assy D2821337600000 Item 14 1 Filter D2821337800000 Item 16 1 Plate D2821337120000 Item 8 1 O-Ring NSA8203-152 Attach with : Item 10

6 Bolt NAS6604-8 Item 12

6 Washer ASNA2397-416L Item 18

4 Bolt NAS6603-2 Item 20

2 Bolt NAS6603-5 Item 22

5 Washer ASNA2397JD10L Item 24

2 Nut NSA5050-3 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 349 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 26 1 Washer ASNA2397-10L (o) Apply the sealing protection to the center tank Refer to Kit 281132A05R00 281132A05003 A00 Sheet(s) 01 281132A05003 A00 Sheet(s) 02 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 (Polyurethane) (Mat. No. 16-001) - Fuel Tank Coating (Mat. No. 16-015). (p) Modify the equipment in the HYD/Fuel Panel 40VU Refer to Kit 281132A07R00 and Kit 281132A15R01 281132A15001 A00 Sheet(s) 01 281132A15002 A00 Sheet(s) 01 281132A15002 A00 Sheet(s) 02 1 Remove : 281132A15001 A00 Sheet(s) 01 281132A15002 A00 Sheet(s) 01 FIN 14LF 1 Plate-Integrally Lighted 002098-05

Item (0) 1 Plate-Front D9251092000000

Item (14) 4 Screw

Item (15) 1 Screw

Item (21) DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 350 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Nut

Item (24) 1 Washer

Item (16) 2 Screw

Item (17) 5 Screw

Item (18) 26 Screw 2 Install : 281132A15001 A00 Sheet(s) 01 281132A15002 A00 Sheet(s) 02 FIN 24QH 1 Switch-Pushbutton ABS0951C3LM078

with : 1 Sleeve E0416-02 1 Connector E0417C01S

Item 0 1 Plate D9251314900000

FIN 14LF 1 Plate-Integrally Lighted D33110194A00

Item 4 1 Placard D1131043320100

Item 6 1 Placard D1131043320200

Item 14 4 Screw NAS1102-06-7

Item 15 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 351 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Screw NAS1102-08-7

Item 21 1 Nut MS21042-08

Item 24 1 Washer ASNA2397-8L

Item 16 2 Screw NAS1102-06-5

Item 17 5 Screw ASNA2083BG2-10

Item 18 28 Screw NAS1102-04-5 NOTE : On the new front plate, near the new equipment and the items that you installed again, bond the placards, supplied in : Placard Set D9100095114296 NOTE : Safety the screws with Sealant High Temperature (Mat. No. 08-007B) or Sealant High Temperature (Mat. No. 08-573). NOTE : For the modification to the wiring, Refer to ACCOMPLISHMENT INSTRUCTIONS paragraph B.(4) (w). (q) Modify the equipment and the wiring in the Rear C/B Panel 121VU Refer to Kit 281132A13R00 and Kit 281132A15R01 281132A15003 A00 Sheet(s) 01 281132A15501 A00 Sheet(s) 01 281132A15501 A00 Sheet(s) 02 281132A15502 A00 Sheet(s) 01 281132A15502 A00 Sheet(s) 02 281132A15503 A00 Sheet(s) 01 281132A15503 A00 Sheet(s) 02 281132A15504 A00 Sheet(s) 01 281132A15504 A00 Sheet(s) 02 281132A15505 A00 Sheet(s) 01 281132A15505 A00 Sheet(s) 02 281132A15506 A00 Sheet(s) 01 281132A15506 A00 Sheet(s) 02 281132A15507 A00 Sheet(s) 01 281132A15507 A00 Sheet(s) 02 281132A15508 A00 Sheet(s) 01 281132A15508 A00 Sheet(s) 02 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 352 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281132A15509 A00 Sheet(s) 01 281132A15509 A00 Sheet(s) 02 281132A15510 A00 Sheet(s) 01 281132A15510 A00 Sheet(s) 02 281132A15511 A00 Sheet(s) 01 281132A15511 A00 Sheet(s) 02 1 Remove : 281132A15003 A00 Sheet(s) 01 FIN 33LM 1 Placard D11311364A00

FIN 36LM 1 Placard D11311359A00 2 Install : 281132A15003 A00 Sheet(s) 01 FIN 10QH 1 Circuit Breaker NSA931320-050

in position P28 FIN 9QH 1 Circuit Breaker NSA931320-050

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

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

in position N29 FIN 34QU 1 Circuit Breaker NSA931320-050 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 353 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

in position L28 FIN 33QU 1 Circuit Breaker NSA931320-050

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

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

in position M28 with : 8 Clip-Locking ABS0772A02A

FIN 33LM 1 Placard D11311658A00

FIN 36LM 1 Placard D11311361A00

NOTE : Near the new circuit breaker, bond the placards, supplied in : Placard Set D9100095114296 3 Remove the wires : 281132A15501 A00 Sheet(s) 02 281132A15503 A00 Sheet(s) 02 281132A15505 A00 Sheet(s) 02 281132A15508 A00 Sheet(s) 02 281132A15510 A00 Sheet(s) 02 4 Install the wires : 281132A15502 A00 Sheet(s) 02 281132A15504 A00 Sheet(s) 02 281132A15506 A00 Sheet(s) 02 281132A15507 A00 Sheet(s) 02 281132A15509 A00 Sheet(s) 02 281132A15511 A00 Sheet(s) 02 supplied in : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 354 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Bundle D9000095128395 Then, install : FIN 1114PP 1 Shunt NSA939526-02

between circuit breakers 9QH and 10QH FIN 1115PP 1 Shunt NSA939526-02

between circuit breakers 33QU and 34QU 5Attach the wires with : 150 Tie-Cable NSA935401-03 150 Tie-Cable NSA935401-06 (r) Install the routing of Relay Box 802VU, between FR4 and FR5, in the avionics compartment Refer to Kit 281132A19R00 281132A19001 A00 Sheet(s) 01 281132A19002 A00 Sheet(s) 01 281132A19002 A00 Sheet(s) 02 281132A19002 A00 Sheet(s) 03 1 On the plate assy, between FR4 and FR5, bond the placard supplied in : 281132A19001 A00 Sheet(s) 01 Placard Set D9100095116795 2 Modify the routing, between FR4 and FR5, in the avionics compartment 281132A19002 A00 Sheet(s) 01 281132A19002 A00 Sheet(s) 02 281132A19002 A00 Sheet(s) 03

a Remove : Item (8) 9 Tie-Cable Discard

b Install : Item 8 10 Tie-Cable NSA935401-03 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 355 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 9 5 Screw NAS1801-3-8 Item 11 5 Washer ASNA2397-10L FIN 4065VC-A Item 20 1 Connector-Plug EN3646A62041BN Item 22 1 Backshell E0080-01-20C FIN 4066VC-A Item 21 1 Connector-Plug EN3646A61419BN Item 23 1 Backshell E0080-01-14C NOTE : For the modification to the wiring, Refer to ACCOMPLISHMENT INSTRUCTIONS paragraph B.(4) (w). (s) Install the connectors 1975VC and 1982VC between FR33 and FR34 Refer to Kit 281132A19R00 281132A19003 A00 Sheet(s) 01 281132A19003 A00 Sheet(s) 02 FIN 1975VC 1 Connector EN3545E01FXB22A 1 Backshell EN3545-007SCD FIN 1982VC 1 Connector EN3545E03FXB24A 1 Backshell EN3545-007SCD NOTE : Bond the related placards, supplied in : Placard Set D9100095116795 (t) Modify the equipment in the AFT Electronics Rack 80VU DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 356 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Kit 281132A19R00 281132A19006 A00 Sheet(s) 01 1 On the Shelf 85VU

aOn the mounting rail of the terminal block 1853VT, install : 1 Module NSA937901MA2206 in position 28 1 Module Identification NSA937901E2 1 Module Identification NSA937901E8 (u) Modify the equipment in the Relay Box 103VU Refer to Kit 281132A10R02 281132A19004 A00 Sheet(s) 01 281132A19004 A00 Sheet(s) 02 281132A19004 A00 Sheet(s) 03 1 Install : FIN 50QJ Item 40 1 Relay E0245-28A0

Item 41 1 Base E0250A0S

Item 6 2 Nut MS21042L04

in position E49 FIN 57QJ Item 50 1 Relay E0666D28A0

Item 51 1 Base E0247A0S

Item 1 1 Retainer-Assy E0427-01A DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 357 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 2 1 Screw NAS1101-04-6

Item 4 1 Washer ASNA2397-4L

Item 5 1 Washer ASNA2397-3L

Item 6 3 Nut MS21042L04

in position P01 NOTE : Bond the related placards, supplied in : Placard Set D9100095116795 (v) Modify the equipment in the Contactor Box 107VU Refer to Kit 281132A10R02 281132A19005 A00 Sheet(s) 01 281132A19005 A00 Sheet(s) 02 1 Install : FIN 26QH Item 70 1 Relay NSA932843AA01

Item 71 1 Base NSA932844AA

Item 8 3 Screw NAS1101-04-7

Item 4 3 Washer ASNA2397-4L

Item 6 3 Nut MS21042L04

in position B07 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 358 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

FIN 1274VC Item 50 1 Connector EN3545D03MXB22A

FIN 1274VC-A Item 51 1 Connector EN3545D03FXA22A

Item 52 2 Backshell EN3545-007SCD

NOTE : Bond the related placards, supplied in : Placard Set D9100095116795 2 On the mounting rail of terminal block 1176VT, install : 1 Module NSA937901MA2008 1 Module Identification NSA937901E0 1 Module Identification NSA937901E1

in position 10 (w) Modify the wiring in the aircraft Refer to Kit 281132A19R00 281132A19501 A00 Sheet(s) 01 281132A19501 A00 Sheet(s) 02 281132A19502 A00 Sheet(s) 01 281132A19502 A00 Sheet(s) 02 281132A19502 A00 Sheet(s) 03 281132A19503 A00 Sheet(s) 01 281132A19503 A00 Sheet(s) 02 281132A19504 A00 Sheet(s) 01 281132A19504 A00 Sheet(s) 02 281132A19504 A00 Sheet(s) 03 281132A19505 A00 Sheet(s) 01 281132A19505 A00 Sheet(s) 02 281132A19505 A00 Sheet(s) 03 281132A19506 A00 Sheet(s) 01 281132A19506 A00 Sheet(s) 02 281132A19506 A00 Sheet(s) 03 281132A19507 A00 Sheet(s) 01 281132A19507 A00 Sheet(s) 02 281132A19508 A00 Sheet(s) 01 281132A19508 A00 Sheet(s) 02 281132A19509 A00 Sheet(s) 01 281132A19509 A00 Sheet(s) 02 281132A19510 A00 Sheet(s) 01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 359 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281132A19510 A00 Sheet(s) 02 281132A19510 A00 Sheet(s) 03 281132A19511 A00 Sheet(s) 01 281132A19511 B00 Sheet(s) 02 281132A19512 A00 Sheet(s) 01 281132A19512 A00 Sheet(s) 02 281132A19513 A00 Sheet(s) 01 281132A19513 A00 Sheet(s) 02 281132A19514 A00 Sheet(s) 01 281132A19514 A00 Sheet(s) 02 281132A19515 A00 Sheet(s) 01 281132A19515 A00 Sheet(s) 02 281132A19516 A00 Sheet(s) 01 281132A19516 A00 Sheet(s) 02 281132A19517 A00 Sheet(s) 01 281132A19517 A00 Sheet(s) 02 281132A19518 A00 Sheet(s) 01 281132A19518 A00 Sheet(s) 02 281132A19519 A00 Sheet(s) 01 281132A19519 A00 Sheet(s) 02 281132A19520 A00 Sheet(s) 01 281132A19520 A00 Sheet(s) 02 281132A19521 A00 Sheet(s) 01 281132A19521 A00 Sheet(s) 02 281132A19522 A00 Sheet(s) 01 281132A19522 A00 Sheet(s) 02 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) 1 FLSCU1 Retain 1 FLSCU2 Retain 1 FQIC Retain 1 GAPCU Retain NOTE : You must install these computers again after the modification of the wiring. b Disconnect the bonding braid.

c Remove the attachment hardware from the Shelf 92VU. NOTE : Retain the hardware. d Remove the Shelf 92VU and install it on bench. 2 Remove the Shelf 93VU DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 360 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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

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

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

c Remove the attachment hardware from the Shelf 94U. NOTE : Retain the hardware. d Remove the Shelf 94VU and install it on bench. 4 Remove the wires : 281132A19508 A00 Sheet(s) 02 281132A19511 B00 Sheet(s) 02 281132A19513 A00 Sheet(s) 02 281132A19516 A00 Sheet(s) 02 281132A19518 A00 Sheet(s) 02 281132A19520 A00 Sheet(s) 02 5 Install the wires : 281132A19501 A00 Sheet(s) 02 281132A19502 A00 Sheet(s) 02 281132A19502 A00 Sheet(s) 03 281132A19503 A00 Sheet(s) 02 281132A19504 A00 Sheet(s) 02 281132A19504 A00 Sheet(s) 03 281132A19505 A00 Sheet(s) 02 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 361 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281132A19505 A00 Sheet(s) 03 281132A19506 A00 Sheet(s) 02 281132A19506 A00 Sheet(s) 03 281132A19507 A00 Sheet(s) 02 281132A19509 A00 Sheet(s) 02 281132A19510 A00 Sheet(s) 02 281132A19510 A00 Sheet(s) 03 281132A19512 A00 Sheet(s) 02 281132A19514 A00 Sheet(s) 02 281132A19515 A00 Sheet(s) 02 281132A19517 A00 Sheet(s) 02 281132A19519 A00 Sheet(s) 02 281132A19521 A00 Sheet(s) 02 281132A19522 A00 Sheet(s) 02 supplied in : Bundle D9000095128495 Bundle D9000095128595 Bundle D9000095131295 Bundle D9000095150195 6Attach the wires with : 100 Tie-Cable NSA935401-03 200 Tie-Cable NSA935401-04 200 Tie-Cable NSA935401-05 800 Tie-Cable NSA935401-06 1500 Tie-Cable NSA935401-08

7 Install the Shelf 92VU

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

c Attach the Shelf 92VU and connect the bonding braid with the hardware retained at removal. NOTE : Retain the hardware. d On the Shelf 92VU, install the computers 7QJ, 9QJ, 3QT and 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) 1 FLSCU1 1 FLSCU2 1 FQIC 1 GAPCU NOTE : These computers were retained at removal. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 362 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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 and 5GA1 : (Refer to AMM 27-94-34, Page block 401) (Refer to AMM 32-31-71, Page block 401) 1 SEC3 1 LGCIU1 NOTE : These computers were retained at removal. 9 Install the Shelf 94VU

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

c Attach the Shelf 94VU and connect the bonding braid with the hardware retained at removal. NOTE : Retain the hardware. d On the Shelf 94VU, install the computers 5GA2 and 10GG : (Refer to AMM 32-31-71, Page block 401) (Refer to AMM 32-42-34, Page block 401) 1 LGCIU2 1 BSCU NOTE : These computers were retained at removal. (x) Modify the equipment in the FWD Electronics Rack 90VU Refer to Kit 281132A16R00 and Kit 281132A17R00 281132A16001 A00 Sheet(s) 01 281132A16002 A00 Sheet(s) 01 281132A16003 A00 Sheet(s) 01 281132A16004 A00 Sheet(s) 01 281132A16004 A00 Sheet(s) 02 1 On the Shelf 92VU

a Remove : 281132A16001 A00 Sheet(s) 01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 363 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item (3) 1 Plate Assy D9251102000000 Item (12) 2 Screw Discard Item (28) 2 Washer Discard Item (16) 4 Nut Discard

bOn the mounting rail of the terminal block 202VT, install : 281132A16002 A00 Sheet(s) 01 1 Module NSA937901MA2011 in position 21 1 Module NSA937901MA2204 in position 22 3 Module Identification NSA937901E2 1 Module Identification NSA937901E1

c Install : 281132A16002 A00 Sheet(s) 01 281132A16003 A00 Sheet(s) 01 Item 1 1 Rack D0003006100000 Item 15 5 Cover NSA939511-03 Item 7 1 Plate Assy D9251116900000 Attach with : Item 12 3 Screw NAS1801-3-8 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 364 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 4 3 Screw NAS1102-3-10 Item 28 3 Washer ASNA2397-10L Item 16 6 Nut NAS1726-3E FIN 624VG 1 Module-Grounding E0425A2001 FIN 47QJ 1 Level Sensing Control Unit 30042-0000-0501
FIN 47QJ-A 1 Connector E0161D01A12X Attach with : Item 0 2 Flange Assy D9251127600000 Item 6 4 Screw NAS1100-06-12 Item 9 4 Screw NAS1100-04-7 Item 14 4 Washer ASNA2397-4L Item 30 2 Washer ASNA2397-6L NOTE : Bond the related placards, supplied in : Placard Set D9100095112895

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 365 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 On the Shelf 94VU, install : 281132A16004 A00 Sheet(s) 01 281132A16004 A00 Sheet(s) 02 Item 40 1 Relay E0666D28A0

Item 41 1 Base E0247A0S

Item 1 1 Retainer-Assy E0427-01A

Item 2 1 Screw NAS1100-04-6

Item 4 1 Washer ASNA2397-4L

Item 5 1 Washer ASNA2397-3L

Item 6 3 Nut MS21042L04

in position B15 NOTE : Bond the related placards, supplied in : Placard Set D9100095112895 (y) Modify the marking on the belly fairing, between FR47 and FR53 Refer to Kit 281132A18R00 281132A18001 A00 Sheet(s) 01 281132A18001 A00 Sheet(s) 02 281132A18001 A00 Sheet(s) 03 281132A18001 A00 Sheet(s) 04 1 Between FR47 and FR50, bond the placards : Item 0 2 Placard D1121004620000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 366 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 1 2 Placard D1121009120000

Item 2 1 Placard D0041109120000 2 Between FR50 and FR53, bond the placards : Item 0 2 Placard D1121004620000

Item 2 1 Placard D0041109120000 (5) Config. 02 AI-GE Part (a) Remove and discard the overhead stowage compartments between FR43 and FR47. Refer to Drawing(s) : Refer to AMM 25-24-41 D25278439090 Sheet(s) 42 1 Remove and discard these items : Refer to AMM 25-24-41, Page block 401 1 box (LH) D2529421400000 Item (1014) Discard 1 box (RH) D2529421500000 Item (1015) Discard (b) Remove and discard the placards at the overhead stowage compartments between FR43 and FR47. Refer to Drawing(s) : D25278404054 Sheet(s) 48 and 49 1 Remove and discard this item :

4 placard D2528842244200 Item (1242) Discard (c) Modify the electrical equipment. Refer to Kit 281132D69R01 Refer to drawings : D92894736004 Sheet(s) 14 thru 17 D92894738042 Sheet(s) 1 1 Install the cable harness 5339VB from the terminal block 7223VT to the receptacle 7555VC. Refer to drawing D92894736004 (Sheets 14 thru 17) DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 367 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to drawing D92894738042 (Sheet 1) Refer to Figure 1 (Hookup Chart 1)

a Remove this item as shown in drawing D92894736004, Sheet 16, Detail A : 1 screw NAS1096-2-9 Item (005) Discard and install these parts : 1 screw NAS1096-2-12 Item 007 1 bracket E0343-01 Item 250 1 bracket NSA935504-03 Item 253 1 spacer NSA5527-03-03 Item 304

b Remove this item as shown in drawing D92894736004, Sheet 16, Section A-A : 2 pin DAN364-02 Item (291) Discard and install these items : 2 bracket ABS0355-01 Item 262 2 bracket ABS0355-02 Item 263 2 washer NSA935514-03 Item 264

c Install this item as shown in drawing D92894736004, Sheet 16, Detail B : 1 bracket NSA935513-07 Item 259

d Route the wires with the existing wire, as shown in Hookup Chart 1, lines 1 and 2 and the drawing D92894736004, supplied with : 1 harness D9299043900000 Item 039 and connect with : AR tie NSA935401-03 Item 793 AR tie NSA935401-04 Item 794 AR tie NSA935401-05 Item 795

e Connect 7555VC with these items as shown in drawing D92894736004, Sheet 16, Detail B : 2 screw NAS1100-04-5 Item 051 2 washer NAS1149CN616R Item 150 2 nut MS21042-04 Item 200

f Connect 7499VN with these items as shown in drawing D92894736004, Sheet 16, Detail B : 1 screw NAS1096-3-9 Item 030 1 washer NAS1149C0332R Item 153 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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g Install the placards as shown in drawing D92894736004, Sheet 16, Details A and B : 2 placard D9239386503200 Item 050

h Install the "MOD/SB" placards on the harness 5339VB, Item 039, as shown in drawing D92894713020, Sheet 1 : 100 placard D9239240905800 Item 000 200 tie NSA935401-03 Item 080 2 Install the cable harness 5340VB from the terminal block 7224VT to the receptacle 7556VC. Refer to drawing D92894736004 (Sheet 14 thru 17) Refer to drawing D92894738042 (Sheet 1) Refer to Figure (Hookup Chart 2)

a Install these items as shown in drawing D92894736004, Sheet 16, Detail C : 3 screw NAS1096-2-12 Item 007 3 washer NAS1149CN816R Item 152 3 nut NSA5066-08-1 Item 230 1 bracket E0343-01 Item 250 1 bracket NSA935504-01 Item 251 3 spacer NSA5527-03-03 Item 304

b Route the wires with the existing wire, as shown in Hookup chart 2, lines 1 and 2 and the drawing D92894736004, supplied with : 1 harness D9299044000000 Item 040 and connect with : AR tie NSA935401-03 Item 793 AR tie NSA935401-04 Item 794 AR tie NSA935401-05 Item 795

c Connect 7556VC with these items as shown in drawing D92894736004, Sheet 16, Detail C : 2 screw NAS1100-04-5 Item 051 2 washer NAS1149CN616R Item 150 2 nut MS21042-04 Item 200

d Connect 7100VN with these items as shown in drawing D92894736004, Sheet 16, Detail D : 1 screw NAS1096-3-9 Item 030 1 washer NAS1149C0332R Item 153

e Install the placards as shown in drawing D92894736004, Sheet 16, Details C and D : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 369 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 placard D9239386503200 Item 050

f Install the "MOD/SB" placards on the harness 5340VB, Item 040, as shown in drawing D92894713020, Sheet 1 : 100 placard D9239240905800 Item 000 200 tie NSA935401-03 Item 080 (d) Install the overhead stowage compartment. Refer to Kit 281132D76R00 Refer to AMM 25-24-41 Refer to Drawing(s) : D25278439090 Sheet(s) 42 1 Install the overhead stowage compartment between FR43 and FR47, LH/RH. Refer to AMM 25-24-41, Page block 401 Refer to Drawing(s) : D25278439090 Sheet(s) 42 2 Install the boxes : 1 box (LH) D2529421402600 Item 014 1 box (RH) D2529421502600 Item 015

with : 2 screw NAS1801-06-6 Item 122 4 washer NAS1149F0432P Item 161 2 washer NAS1149CN832R Item 164 2 nut MS21042-06 Item 180 2 pin MS20392-3C27 Item 205 2 pin MS20392-3C31 Item 206 4 pin AA55487-4 Item 250 2 clamp ABS0901-045 Item 290 (e) Install the placards on the overhead stowage compartment. Refer to Kit 281132D77R00 Refer to Drawing(s) : D25278404054 Sheet(s) 48 and 49 1 Install the placards on the overhead stowage compartment between FR43 and FR47, LH/RH.

a Install these items : 2 placard D2527719940600 Item 206 2 placard D2528842244100 Item 241 2 placard D2528842244200 Item 242 (f) Remove and discard the passenger compartment floor panels 241JF, 251AF 251BF, 251FF, 251GF and 252BF. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 370 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to AMM 53-32-12, Page block 401 and AMM 53-42-12, Page block 401 Refer to Drawing(s) : D53675015004 Sheet(s) 7 1 Remove and discard these items :

2 panel D5367160000000 Item (204) Discard 1 panel D5367160100000 Item (206) Discard 2 panel D5367162300000 Item (214) Discard 1 panel D5367162400000 Item (216) Discard 1 connecting plate D5367009920400 Item (302) Discard 1 panel D5367161700000 Item (304) Discard

and discard the removed fastening parts. (g) Remove the LH sidewall panels between FR46 and FR58. Refer to refer to AMM 25-55-11, Page block 401 Refer to Drawing(s) : D25570049010 Sheet(s) 6 1 Remove and discard these items : 1 panel D2557132600000 Item (160) Discard 1 panel D25571324004000 Item (162) Discard 1 panel D2557132200200 Item (164) Discard (h) Remove the RH sidewall panels between FR46 and FR52A. Refer to refer to AMM 25-55-11, Page block 401 Refer to Drawing(s) : D25570049012 Sheet(s) 17 1 Remove and discard these items : 1 panel D2557133000000 Item (166) Discard 1 panel D2557133400000 Item (168) Discard (i) Remove and discard the insulation blankets at FR46. Refer to AMM 25-80-00, Page block 201 Refer to Drawing(s) : D25870003056 Sheet(s) 20 1 Remove and discard these items : 1 blanket D2587085002200 Item (020) Discard 1 blanket D2587085102400 Item (021) Discard 1 blanket D2587085202200 Item (022) Discard 1 blanket D2587085302400 Item (023) Discard 1 blanket D2587085402200 Item (024) Discard 1 blanket D2587085504200 Item (025) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 371 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 blanket D2587085602200 Item (026) Discard 1 blanket D2587085702200 Item (027) Discard 1 blanket D2587085802200 Item (028) Discard 1 blanket D2587085902200 Item (029) Discard 1 blanket D2587086002200 Item (030) Discard 1 blanket D2587086102200 Item (031) Discard 1 blanket D2587086202200 Item (032) Discard 1 blanket D2587086302400 Item (033) Discard 1 blanket D2587086502200 Item (034) Discard 1 blanket D2587087102200 Item (035) Discard 1 blanket D2587087302200 Item (036) Discard (j) Remove the AFT cargo compartment ceiling panels between FR47 and FR59. Refer to AMM 25-55-11, Page block 401 Refer to Drawing(s) : D25570049008 Sheet(s) 5 1 Remove and retain these items as shown in drawing D25570049008, Sheet 5 :

2 rail D2557043000000 Item C 1 rail D2557043000200 Item D

NOTE : Retain the Items C and D. 2 Remove and retain the AFT cargo compartment ceiling panel 151DC, refer to AMM 25-55-11, Page block 401. 3 Remove and discard these items as shown in drawing D25570049008, Sheet 5: 1 panel D2557131000000 Item (150) Discard 1 panel D2557131400000 Item (152) Discard 1 panel D2557131600000 Item (154) Discard 1 panel D2557132000000 Item (156) Discard 1 panel D2557121800000 Item (158) Discard (k) Remove and discard the floor panels from the AFT cargo compartment, between FR47 and FR56. Refer to AMM 53-42-14, Page block 401 Refer to drawing(s) : D53675510010 Sheet(s) 16 1 Remove and discard these items as shown in Detail A16-16 : 1 panel D5367521100000 Item (202) Discard 1 panel D5367521100200 Item (204) Discard 1 panel D5367521100400 Item (206) Discard 1 panel D5367205900000 Item (222) Discard Discard the fastening items.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 372 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(l) Remove and discard the sloped floor panels from the AFT cargo compartment, between FR47 and FR59. Refer to AMM 53-42-14, Page block 401 Refer to Drawing(s) : D53675520008 Sheet(s) 13 1 Remove and discard these items as shown in Detail A13-13 : 1 panel D5367401900000 Item (228) Discard 1 panel D5367401900100 Item (229) Discard 1 panel D5367402100000 Item (230) Discard 1 panel D5367402500000 Item (232) Discard 1 panel D5367402800000 Item (234) Discard 1 panel D5367403500000 Item (236) Discard 1 panel D5367403500100 Item (237) Discard 1 panel D5367402300000 Item (238) Discard 1 panel D5367402900000 Item (240) Discard

Discard the fastening items. (m) Remove the cable harness 4209VB. 1 Remove the wires of cable harness 4209VB Refer to Drawing(s) : D92992299002 Sheet(s) 1 and 3 (n) Install the beam assy between FR46 and FR47 from -Y1292 to +Y1292. Refer to Kit 281132D42R00 Refer to Drawing(s) : D53372362008 Sheet(s) 1,4 thru 9 and 12 thru 14 1 Remove the existing rivets in the affected areas. 2 Put this item in position as shown in Detail A1-12 : 1 T-beam D5337217000800 Item 000 3Transfer drill the holes, drill the additional holes and open all holes to final dimension. 4 Install this item : 1 T-beam D5337217000800 Item 000

with : 8 pin DAN5-6-7X Item 767 4 pin DAN5-6-8X Item 768 4 collar NSA5075-5 Item 804 8 collar NSA5075-6 Item 806 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 373 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

12 collar DAN11-6X Item 807

4 pin DAN5-6-7 Item 967 4 pin DAN5-6-8 Item 968 4 pin DAN5-5-9 Item 949 (o) Install the struts at the beam between FR46 and FR47. Refer to Kit 281132D42R00 Refer to Drawing(s) : D53372362008 Sheet(s) 12 and 13 1 Install these items as shown in Details A1-12 and Z1-13 :

2 strut D5337218500000 Item 002 4 strut D5337218600000 Item 004

with : 2 bolt MS21250-09024 Item 464 2 nut NAS1726-9E Item 466 2 washer MS20002C9 Item 468 4 bolt MS21250-06018 Item 470 4 nut NAS1726-6E Item 472 4 washer MS20002C6 Item 474

NOTE : Tighten the nuts temporarily. The final attachment of the struts is possible after the installation of the attachment structure of the partition panels. (p) Replace fasteners between FR42 and FR46 at several places. Refer to Kit 281132D42R00 Refer to Drawing(s): D53372362008 Sheet(s) all D53371046000 Sheet(s) 1 thru 5 1 Replace the fasteners between FR44 and FR46 between +Y1292 to +Y1650 and -Y1292 to -Y1650. Refer to Drawing(s) : D53372362008 Sheet(s) 4

a Remove the existing rivets, drill the holes to final dimension and install these items as shown in Detail Y4-4 : 210 collar NSA5076-6 Item 816 4 pin DAN6-6-5 Item 865 166 pin DAN5-6-5 Item 965

40 pin DAN5-6-6 Item 966 2 Replace the fasteners between FR42 and FR43 at +Y1650 and -Y1650.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 374 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s) : D53372362008 Sheet(s) 4 D32170220004 Sheet(s) 5 D32170220005 Sheet(s) 5

a If necessary remove the MLG torque tube assembly, refer to AMM 32-33-17, Page block 401, and the shafts. Refer to Drawing(s) : D32170220004 Sheet(s) 5 D32170220005 Sheet(s) 5 b Remove the existing rivets, drill the holes to final dimension and install these items as shown in Detail X4-4 : 12 pin DAN5-6-4X Item 764

8 pin DAN5-6-5X Item 765 8 pin DAN5-6-6X Item 766 2 pin DAN5-6-7X Item 767 2 collar NSA5075-6 Item 806 30 collar DAN11-6X Item 807

2 pin DAN5-6-8 Item 968

c If removed, install the MLG torque tube assembly, refer to AMM 32-33-17, Page block 401, and the shafts. Refer to Drawing(s) : D32170220004 Sheet(s) 5 D32170220005 Sheet(s) 5 3 Replace the fasteners at FR43, STGR28LH/RH. Refer to Drawing(s) : D53372362008 Sheet(s) 13

a Remove the existing rivets, drill the holes to final dimension and install these items as shown in Detail T1-13 : 6 pin DAN5-6-6X Item 766 6 collar DAN11-6X Item 807 (q) Drill the holes in FR46 between STGR42LH and STGR43LH. Refer to Drawing(s) : D53372362008 Sheet(s) 6 1 Drill one hole with 22.0 mm (0.866 in.) diameter and two holes with 5.6 mm (0.22 in.) diameter as shown in Detail A7-6. 2 Deburr the holes. (r) Modify the structure of FR47 between STGR35LH to STGR35RH. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 375 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Kit 281132D42R00 Refer to Drawing(s) : D53372362008 Sheet(s) 5, 8 and 9 1 Replace the fitting at FR47 at STGR43 to STGR44 as shown in Detail A1-A5.

a Remove : 1 support D5347465720300 Item (200) Discard 1 fitting D5347008120200 Item (202) Discard

b Put this item in position : 1 fitting D5337219020200 Item 012

c Transfer drill the holes and open the holes to final dimension. d Install this item : 1 fitting D5337219020200 Item 012 with : 5 rivet LN9198-4810CF Item 648 10 collar NSA5075-6 Item 806 10 pin DAN5-6-5 Item 965 2 Replace the supports at FR47 at STGR35LH/RH, STGR36LH/RH, STGR39LH/RH and STGR40LH/RH as shown in Detail A1-A5.

a Remove the supports for modification : 4 support (LH) D5347100920000 Item (206) Retain 4 support (RH) D5347100920100 Item (207) Retain

b Modify the supports as shown on Sheet 5, Detail A1-A5 : 4 support (LH) D5347100920000 Item (206) Retain 4 support (RH) D5347100920100 Item (207) Retain NOTE : Re-identify the supports : - Support PN D5347100920000, Item (206), becomes PN D5347100920000, Item (048) - Support PN D5347100920100, Item (207), becomes PN D5347100920100, Item (049)

c Put modified supports in position : 4 support (LH) D5347100920000 Item (048) Retained 4 support (RH) D5347100920100 Item (049) Retained

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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dTransfer drill the holes, open all holes and all countersinks to the final dimension.

e Install these items : 4 support (LH) D5347100920000 Item (048) Retained 4 support (RH) D5347100920100 Item (049) Retained with : 32 rivet LN9198-4010CF Item 640 3 Install the angles at FR47 between STGR36LH/RH and STGR40LH/RH as shown in Section A1-A5 and in Details Y1-8 and U1-9.

a Remove the existing fasteners between the affected stringers. b Put this item between the affected stringers in position : 8 angle D5337215920200 Item 016

c Transfer drill the holes from the skin panel to the angles. d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install this item : 8 angle D5337215920200 Item 016 with : 24 rivet LN9198-4810CF Item 648

2 pin DAN5-6-7X Item 767 26 pin DAN5-6-8X Item 768

2 pin DAN5-6-10X Item 770 2 pin DAN5-6-12X Item 772 32 collar DAN11-6X Item 807 4 Install the angles at FR47 between STGR35LH/RH and STGR36LH/RH as shown in Section A1-A5 and in Detail Y1-8.

a Remove the existing fasteners between the affected stringers. b Put these items between the affected stringers in position : 1 angle (LH) D5337215920400 Item 018 1 angle (RH) D5337215920500 Item 019

c Transfer drill the holes from the skin panel to the angle. d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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e Install these items : 1 angle (LH) D5337215920400 Item 018 1 angle (RH) D5337215920500 Item 019 with : 6 rivet LN9198-4810CF Item 648 8 collar DAN11-6X Item 807 6 pin DAN5-6-8X Item 768 2 pin DAN5-6-10X Item 770 5 Install the angle at FR47 between STGR40LH and STGR41LH as shown in Section A1-A5 and in Detail Y1-8.

a Remove the existing fasteners between the affected stringers. b Put this item between the affected stringers in position : 1 angle D5337215920000 Item 014

c Transfer drill the holes from the skin panel to the angle. d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install this item : 1 angle D5337215920000 Item 014 with : 3 rivet LN9198-4810CF Item 648 4 collar DAN11-6X Item 807 4 pin DAN5-6-8X Item 768 6 Install the angle at FR47 between STGR40RH and STGR41RH as shown in Details Y5-5 and U1-9.

a Remove the existing fasteners between the affected stringers. b Put this item between the affected stringers in position : 1 angle D5337215920600 Item 020

c Transfer drill the holes from the skin panel to the angle. d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install this item : 1 angle D5337215920600 Item 020 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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with : 3 rivet LN9198-4810CF Item 648 3 collar DAN11-6X Item 807 3 pin DAN5-6-9X Item 769 7 Remove the angles at FR47 at STGR37LH/RH and STGR38LH/RH as shown in Section A1-A5.

a Remove and discard these items : 2 angle (LH) D5347104120000 Item (212) Discard 2 angle (RH) D5347104120100 Item (213) Discard 8 Replace the fittings at FR47 between STGR37LH/RH and STGR38LH/RH as shown in Section A1-A5.

a Remove and discard these items : 1 fitting (LH) D5337219220200 Item (204) Discard 1 fitting (RH) D5337219220300 Item (205) Discard

b Put these items in position : 1 fitting (LH) D5337219220000 Item 008 1 fitting (RH) D5337219220100 Item 009

c Put these items at STGR37LH/RH in position : 1 angle (LH) D5347104120090 Item 050 1 angle (RH) D5347104120190 Item 051

dTransfer drill the holes and open the holes to final dimension.

e Install these items : 1 fitting (LH) D5337219220000 Item 008 1 fitting (RH) D5337219220100 Item 009 1 angle (LH) D5347104120090 Item 050 1 angle (RH) D5347104120190 Item 051 with : 8 pin DAN7-6-6X Item 566 4 rivet LN9198-4010CF Item 640 8 rivet LN9198-4810CF Item 648 4 rivet LN9198-5610CF Item 656 22 collar NSA5075-6 Item 806

8 collar DAN12-6X Item 817 16 pin DAN5-6-5 Item 965

2 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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9 Install the fittings at FR47 between STGR38LH/RH and STGR39LH/RH as shown in Section A1-A5.

a Put these items at FR47 in position : 1 fitting (LH) D5337219120200 Item 010 1 fitting (RH) D5337219120300 Item 011

b Drill the holes and open the holes to final dimension.

c Install these items : 1 fitting (LH) D5337219120200 Item 010 1 fitting (RH) D5337219120300 Item 011 with : 12 rivet LN9198-4810CF Item 648 16 collar NSA5075-5 Item 804 16 pin DAN5-5-5 Item 945 10Install the nuts at FR47 as shown in Section A1-A5.

a Drill the four holes 5.6 mm (0.220 in.) diameter for the nuts. b Put the nuts, Item 046, in position.

c Drill the holes and countersink the rivet holes. d Install these items : 4 nut NAS1791A3-1 Item 046 with : 8 rivet NAS1097AD3-10 Item 524 11Remove the support at FR47 at STGR43LH as shown in Section A1-A5.

a Remove and discard this item : 1 support D5347465720300 Item (200) Discard 12Remove the nuts at FR47 as shown in Detail C5-5.

a Remove and discard these items : 2 nut NAS1068C3 Item (214) Discard

bClose the holes with : 4 rivet NAS1097AD3-10 Item 524 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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13Drill twelve holes with 5.6 mm (0.220 in.) diameter as shown in Details A5-5 and B5-5. (s) Modify the structure between FR47 and FR48 at STGR38LH/RH and STGR43LH. Refer to Kit 281132D42R00 Refer to Drawing(s) : D53372362008 Sheet(s) 7 1 Remove the nuts at STGR38LH and STGR38RH as shown in Detail W1-7.

a Remove and discard this item : 6 nut NAS1791A3-1 Item (216) Discard 2 Remove the connections at STGR38LH and STGR38RH as shown in Detail W1-7.

a Remove and discard these items : 1 connection (LH) D5347101620400 Item (210) Discard 1 connection (RH) D5347101620500 Item (211) Discard 3 Install the plates, the sections and the connections at STGR38LH and STGR38RH as shown in Detail W1-7. Refer to Drawing(s) : D53372362008

aAt STGR38LH : Put these items in position : 1 plate D5337217400000 Item 024 1 section D5347449520800 Item 028 1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620490 Item 042 NOTE : Install the fillers, Item 030, 032, 034, 036 and 038, as required. NOTE : Install the section, Item 028, together with the angle, Item 130. bAt STGR38RH : Put these items in position : 1 plate D5337217400100 Item 025 1 section D5347449520900 Item 029 1 filler D5337601520600 Item 030 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620590 Item 043 NOTE : Install the fillers, Item 030, 032, 034, 036 and 038, as required. NOTE : Install the section, Item 029, together with the angle, Item 134, at FR48.

cTransfer drill the holes from the skin panel and the stringer to the connections. d Drill the additional holes in the plates, sections and connections and open all holes and all countersinks to final dimension.

e Install these items at STGR38LH : 1 plate D5337217400000 Item 024 1 section D5347449520800 Item 028 1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620490 Item 042 with : 6 rivet NAS1097AD4-10 Item 532 21 rivet LN9198-4014CF Item 640

1 pin DAN5-6-6X Item 766 4 pin DAN5-6-7X Item 767 13 pin DAN5-6-8X Item 768

1 pin DAN5-6-9X Item 769 6 collar NSA5075-6 Item 806 19 collar DAN11-6X Item 807

4 pin DAN5-6-5 Item 965 2 pin DAN5-6-9 Item 969

f Install these items at STGR38RH : 1 plate D5337217400100 Item 025 1 section D5347449520900 Item 029 1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620590 Item 043 with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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6 rivet NAS1097AD4-10 Item 532 21 rivet LN9198-4014CF Item 640

1 pin DAN5-6-6X Item 766 4 pin DAN5-6-7X Item 767 13 pin DAN5-6-8X Item 768

1 pin DAN5-6-9X Item 769 6 collar NSA5075-6 Item 806 19 collar DAN11-6X Item 807

4 pin DAN5-6-5 Item 965 2 pin DAN5-6-9 Item 969 4 Remove the connection at STGR43LH as shown in Detail V1-7. Refer to Drawing(s) : D53372362004 Sheet(s) all

a Remove and discard this item : 1 connection D5347100720400 Item (208) Discard 5 Install the plate, the section and the coupling at STGR43LH as shown in Detail V1-7. Refer to Drawing(s) : D53372362008 Sheet(s) all

a Put these items at STGR43LH in position : 1 plate D5337217320000 Item 022 1 section D5337216020000 Item 026 1 coupling D5347100720600 Item 040

bTransfer drill the holes from STGR43 to the plate and the connection.

c Drill all additional holes in the plate and the section and open all holes and all countersinks to final dimension. d Install these items : 1 plate D5337217320000 Item 022 1 section D5337216020000 Item 026 1 coupling D5347100720600 Item 040 with : 34 rivet LN9198-4014CF Item 640

4 pin DAN5-6-7X Item 767 4 pin DAN5-6-8X Item 768 2 collar NSA5075-6 Item 806 8 collar DAN11-6X Item 807 16 collar DAN11-8X Item 810

1 pin DAN5-8-8X Item 888 4 pin DAN5-8-9X Item 889 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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10 pin DAN5-8-10X Item 890

1 pin DAN5-8-11X Item 891 2 pin DAN5-6-7 Item 967 6 Install the reinforcing angles at FR48 between STGR8LH/RH and STGR13LH/RH as shown in Section C1-C9. Refer to Drawing(s) : D53372362008 Sheet(s) 9

a Put these items in position : 1 angle (LH) D5337036522600 Item 150 1 angle (RH) D5337036522700 Item 151

b Drill the holes and open the holes to final dimension.

c Install these items : 1 angle (LH) D5337036522600 Item 150 1 angle (RH) D5337036522700 Item 151 with : 52 rivet LN9198-4010CF Item 640 (t) Remove the corner profiles at STGR38LH/RH between FR48 and FR56. Refer to Drawing(s) : D53470075008 Sheet(s) 27 1 Remove and discard these items as shown in Details Z26-27 and X26-27 : 1 corner profile D5347048100400 Item (452) Discard 1 corner profile D5347047500400 Item (454) Discard 1 corner profile D5347047600600 Item (456) Discard (u) Remove the shear plates at STGR38LH/RH between FR48 and FR59. Refer to Drawing(s) : D53470075008 Sheet(s) 18, 25 and 28 1 Remove and discard these items at STGR38LH as shown in Sections J18-J28 and H18-H25 : 1 shear plate D5347048800000 Item (374) Discard 1 shear plate D5347048900000 Item (376) Discard 1 shear plate D5347049200200 Item (378) Discard 2 angle D5347046820600 Item (386) Discard 1 angle D5347046820200 Item (390) Discard 1 angle D5347046820800 Item (392) Discard 1 angle D5347046821000 Item (394) Discard 3 angle D5347046820000 Item (460) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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2 angle D5347046820200 Item (462) Discard 2 angle D5347046820400 Item (464) Discard 2 shear plate D5347049000000 Item (474) Discard 1 shear plate D5347049100000 Item (476) Discard 2 Remove and discard these items at STGR38RH as shown in Sections J18-J28 and H18-H25: 1 angle D5347046820900 Item (382) Discard 1 angle D5347046822000 Item (384) Discard 2 angle D5347046820100 Item (468) Discard 3 angle D5347046820300 Item (470) Discard 1 angle D5347046822400 Item (472) Discard 1 shear plate D5347049000100 Item (478) Discard 1 shear plate D5347049000300 Item (480) Discard 1 shear plate D5347048600400 Item (482) Discard (v) Remove the crossbeams at FR48, FR49, FR50 and FR51 in the AFT cargo compartment. Refer to Drawing(s) : D53470075008 Sheet(s) 18 thru 22 NOTE : For minor crossbeam modification, two frames can only be reworks at one time with standard jacking. 1 Remove these items at FR48 as shown in drawing D53470075008, Sheet 19, Section A18-A19 ’BEFORE’.

a Remove and discard these items : 1 crossbeam D5347035000400 Item (400) Discard 1 shim D5347061120200 Item (402) Discard 1 fitting D5347061220000 Item (404) Discard 1 shim D5347061120300 Item (406) Discard 1 fitting D5347061220100 Item (408) Discard 1 support D5347069920800 Item (412) Discard

bClose the eight holes as shown in Details B19-19 and C19-19 : 8 rivet NAS1097-5 2 Remove these items at FR49 as shown in drawing D53470075008, Sheet 20, Section B18-B20 ’BEFORE’.

a Remove and discard these items : 1 crossbeam D5347035000400 Item (400) Discard 1 shim D5347061120200 Item (402) Discard 1 fitting D5347061220000 Item (404) Discard 1 shim D5347061120300 Item (406) Discard 1 fitting D5347061220100 Item (408) Discard 1 support D5347069920800 Item (412) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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b Close the eight holes as shown in Details B20-20 and C20-20 : 8 rivet NAS1097-5 3 Remove these items at FR50 as shown in drawing D53470075008, Sheet 21, Section C18-C21 ’BEFORE’.

a Remove and discard these items : 1 crossbeam D5347026000400 Item (410) Discard 1 shim D5347061120200 Item (402) Discard 1 fitting D5347061220000 Item (404) Discard 1 shim D5347061120300 Item (406) Discard 1 fitting D5347061220100 Item (408) Discard 1 clip D5347073720400 Item (430) Discard 1 clip D5347073920200 Item (432) Discard 1 clip D5347074020000 Item (434) Discard 1 clip D5347073720500 Item (436) Discard

bClose the eight holes as shown in Details B21-21 and C21-21 : 8 rivet NAS1097-5 4 Remove these items at FR51 as shown in drawing D53470075008, Sheet 22 Section D18-D22 ’BEFORE’.

a Remove and discard these items : 1 crossbeam D5347035300400 Item (420) Discard 1 shim D5347061120200 Item (402) Discard 1 fitting D5347061220000 Item (404) Discard 1 shim D5347061120300 Item (406) Discard 1 fitting D5347061220100 Item (408) Discard 1 clip D5347074420400 Item (440) Discard 1 clip D5347074620200 Item (442) Discard 1 clip D5347074720000 Item (444) Discard 1 clip D5347074420500 Item (446) Discard

bClose the eight holes as shown in Details B22-22 and C22-22 : 8 rivet NAS1097-5 (w) Remove the crossbeams at FR52, FR53 and FR54 in the AFT cargo compartment. D53470076008 Sheet(s) 11 and 12 1 Remove these items from FR52 as shown in drawing D53470076008, Sheet 12, Section A11-A12 ’BEFORE’.

a Remove and discard these items : 1 fitting D5347061220000 Item (400) Discard 1 fitting D5347061220100 Item (401) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 shim D5347061120200 Item (402) Discard 1 shim D5347061120300 Item (403) Discard 1 support D5347037820200 Item (404) Discard 1 fitting D5347448720000 Item (406) Discard 1 clip D5347074320600 Item (408) Discard 1 clip D5347075120200 Item (410) Discard 1 clip D5347075220000 Item (412) Discard 1 clip D5347074320700 Item (414) Discard 1 angle D5347557520600 Item (416) Discard 1 support D5347038420200 Item (444) Discard 1 fitting D5347449920200 Item A NOTE : Discard the Item A. bClose the eight holes as shown in Details A12-12 and B12-12 : 8 rivet NAS1097-5 2 Remove these items as shown in drawing D53470076008, Sheet 13, Section B11-13 and A13-13 : 1 nut-plate NAS1791A3-1 Item (460) Discard 1 nut-plate NAS1068C3 Item (462) Discard 3 Remove these items at FR53 as shown in drawing D53470076008, Sheet 14, Section C11-C14 ’BEFORE’.

a Remove and discard these items : 1 fitting D5347061220000 Item (400) Discard 1 crossbeam D5347026100400 Item (418) Discard 1 clip D5347075420000 Item (426) Discard 1 clip D5347075520200 Item (428) Discard 1 clip D5347075320800 Item (464) Discard

bClose the four holes as shown in Detail A4-4 : 8 rivet NAS1097-5 4 Remove these items at FR54 as shown in drawing D53470076008, Sheet 15, Section D11-D15 ’BEFORE’.

a Remove and discard these items : 1 fitting D5347061220000 Item (400) Discard 1 shim D5347061120200 Item (402) Discard 1 crossbeam D5347035601000 Item (430) Discard 1 clip D5347098020000 Item (432) Discard 1 clip D5347075820200 Item (436) Discard 1 clip D5347075920000 Item (438) Discard 1 clip D5347076020200 Item (440) Discard

bClose the four holes as shown in Detail A5-5 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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8 rivet NAS1097-5 (x) Modify the structure at FR48 between STGR34LH and STGR34RH. Refer to Kit 281132D96R02 Refer to Drawing(s) : D53470075008 Sheet(s) 18 and 19 1 Replace the fasteners at FR48 between STGR34RH and STGR36RH as shown in Section A18-A19 ’AFTER’.

a Remove the existing fasteners in the affected area as shown in Section A18-A19 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR48. 2 Install the reinforcing straps at FR48 between STGR35LH/RH and STGR42LH/RH as shown in Section A18-A19 ’AFTER’ :

a Put these items at FR48 in position : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes to final dimension. d Install these items : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with : 58 rivet LN9198-4012CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit 281132D41R00. 3 Install the fittings at FR48 at STGR37LH/RH as shown in Section A18-A19 ’AFTER’ :

a Put these items at FR48 in position : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

bTransfer drill the holes from the frame to the fittings and open all holes to final dimension.

c Install these items : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with : 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR48 as shown in Section A18-A19 ’AFTER’ :

a Put these items at FR48 temporarily in position : 1 crossbeam D5347035000600 Item 010 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 010, IS IN LINE WITH THE CROSSBEAMS AT FR47 AND FR55. b Mark the fastener holes as shown in Detail B19-20 and C19-20.

c Drill the marked holes with 3.3 mm (0.130 in.) diameter. dTransfer drill all other holes from the frame to the crossbeam.

e Drill all additional holes and open all holes to final dimension. f Remove the crossbeam. g Mark and drill the holes in FR48 as shown in Detail C. h Put the crossbeam in position and install these items : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 crossbeam D5347035000600 Item 010 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026 with : 32 rivet LN9198-4816CF Item 648

6 pin DAN5-6-5X Item 765 60 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 6 collar NSA5075-8 Item 808 16 pin DAN5-6-4 Item 964 34 pin DAN5-6-5 Item 965 10 pin DAN5-6-6 Item 966

2 pin DAN5-6-7 Item 967 6 pin DAN5-8-5 Item 985

i Put this item at FR48 in position as shown in Details Z19-20, Y19-20 and C20-20 : 2 bushing D5347658620000 Item 204

j Transfer drill the holes from the frame to the bushings and open the holes to final dimension. k Install these items as shown in Detail C20-20 : 2 bushing D5347658620000 Item 204 with : 2 collar NSA5075-6 Item 806 2 pin DAN5-6-7 Item 967 5 Replace the fasteners at FR48 between STGR42LH and STGR42RH :

a Remove the fasteners as shown in Section A18-19 ’BEFORE’. bOpen the holes to final dimension.

c Install these items as shown in Section A18-A19 ’AFTER’ : 17 rivet LN9198-4816CF Item 648 6 Install the sections and the angles at FR48 between STGR34LH/RH and STGR39LH/RH as shown in Section A18-A19 ’AFTER’ :

a Put these items in position : 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 3 section D5347449520500 Item 032 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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3 section D5347449520400 Item 034 1 angle D5347470020000 Item 036 1 angle D5347470020100 Item 038

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items : 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 3 section D5347449520500 Item 032 3 section D5347449520400 Item 034 1 angle D5347470020000 Item 036 1 angle D5347470020100 Item 038 with : 32 rivet MBBN4477-4812 Item 549 40 rivet LN9198-4816CF Item 648

8 collar NSA5075-6 Item 806 8 pin DAN6-6-4 Item 864 (y) Modify the structure at FR49 between STGR34LH and STGR34RH. Refer to Kit 281132D95R00 Refer to Drawing(s) : D53470076008 Sheet(s) 18 and 20 1 Replace the fasteners at FR49 between STGR34RH and STGR36RH as shown in Section B18-B20 ’AFTER’ :

a Remove the existing fasteners in the affected area as shown in Section B18-B20 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR49. 2 Install the reinforcing straps at FR49 between STGR35LH/RH and STGR42LH/RH as shown in Section B18-B20 ’AFTER’ : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 391 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Put these items at FR49 in position : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes to final dimension. d Install these items : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with : 58 rivet LN9198-4012CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit 281132D41R00. 3 Install the fittings at FR49 at STGR37LH/RH as shown in Section B18-B20 ’AFTER’ :

a Put these items at FR49 in position : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

bTransfer drill the holes from the frame to the fittings and open all holes to final dimension.

c Install these items : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with : 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR49 as shown in Section B18-B20 ’AFTER’ :

a Put these items at FR49 temporarily in position : 1 crossbeam D5347035000600 Item 010 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 010, IS IN LINE WITH THE CROSSBEAMS AND FR47 AND FR55. b Mark the fastener holes as shown in Detail Y20-20 and Z20-20.

c Drill the marked holes with 3.3 mm (0.130 in.) diameter. dTransfer drill all other holes from the frame to the crossbeam.

e Drill all additional holes and open all holes to final dimension. f Remove the crossbeam. g Mark and drill the holes in FR49 as shown in Detail C20-20. h Put the crossbeam in position and install these items : 1 crossbeam D5347035000600 Item 010 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026 with : 32 rivet LN9198-4816CF Item 648

6 pin DAN5-6-5X Item 765 60 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 6 collar NSA5075-8 Item 808 16 pin DAN5-6-4 Item 964 36 pin DAN5-6-5 Item 965

8 pin DAN5-6-6 Item 966 2 pin DAN5-6-7 Item 967 6 pin DAN5-8-5 Item 985

i Put this items at FR49 in position as shown in Detail C20-20 : 2 bushing D5347658620000 Item 204

j Transfer drill the holes from the frame to the bushings and open the holes to final dimension. k Install these items as shown in Detail C20-20 : 2 bushing D5347658620000 Item 204 with : 2 collar NSA5075-6 Item 806 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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2 pin DAN5-6-7 Item 967 5 Install the sections and the angles at FR49 between STGR34LH/RH an and STGR39LH/RH as shown in Section B18-B20 ’AFTER’ :

a Put these items in position : 1 L-profile D5347449521800 Item 020 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 1 section D5347449520500 Item 032 1 section D5347449520400 Item 034 1 angle D5347470020400 Item 044 1 angle D5347470020500 Item 046 2 angle D5347470020200 Item 048 2 angle D5347470020300 Item 050

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items : 1 L-profile D5347449521800 Item 020 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 1 section D5347449520500 Item 032 1 section D5347449520400 Item 034 1 angle D5347470020400 Item 044 1 angle D5347470020500 Item 046 2 angle D5347470020200 Item 048 2 angle D5347470020300 Item 050 with : 46 rivet MBBN4477-4812 Item 549 40 rivet LN9198-4816CF Item 648 6 Replace the riveting between clip and skin panel at FR49 between STGR34LH/RH and STGR37LH/RH as shown in Section B18-B20 :

a Remove the existing rivets. bOpen the holes and the countersinks to final dimension.

c Install this item : 24 rivet MBBN4477-4812 Item 549 (z) Modify the structure at FR50 between STGR34LH and STGR34RH. Refer to Kit 281132D95R00

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 394 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s) : D53470076008 Sheet(s) 18 and 21 1 Replace the fasteners at FR50 between STGR34RH and STGR36RH as shown in Section C18-C21 ’AFTER’ :

a Remove the existing fasteners in the affected area as shown in Section C18-C2184 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR50. 2 Install the reinforcing straps at FR50 between STGR35LH/RH and STGR42LH/RH as shown in Section C18-C21 ’AFTER’ :

a Put these items at FR50 in position : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes to final dimension. d Install these items : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with : 58 rivet LN9198-4012CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit 281132D41R00.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 395 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

3 Install the fittings at FR50 at STGR37LH/RH as shown in Section C18-C21 ’AFTER’ :

a Put these items at FR50 in position : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

bTransfer drill the holes from the frame to the fittings and open all holes to final dimension.

c Install these items : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with : 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR50 as shown in Section C18-C21 ’AFTER’ :

a Put these items at FR50 in position : 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026 1 crossbeam D5347026000600 Item 052

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 052, IS IN LINE WITH THE CROSSBEAMS AND FR47 AND FR55. bTransfer drill all holes from the frame to the crossbeam.

c Put these items at FR50 between STGR42LH and STGR42RH in position : 1 angle D5347470520000 Item 054 1 angle D5347470520100 Item 056 1 web D5347470320000 Item 066

dTransfer drill the holes from the frame and skin panel to the shear web and the supports.

e Drill all additional holes and open all holes and all countersinks to final dimension. f Install these items : 1 plate D5337217620000 Item 012 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 396 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026 1 crossbeam D5347026000600 Item 052 1 angle D5347470520000 Item 054 1 angle D5347470520100 Item 056 1 web D5347470320000 Item 066 with : 12 rivet MBBN4477-4812 Item 549

4 rivet LN9198-4014CF Item 640 51 rivet LN9198-4816CF Item 648

6 pin DAN5-6-5X Item 765 56 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 12 collar NSA5075-8 Item 808 20 pin DAN5-6-4 Item 964 32 pin DAN5-6-5 Item 965

4 pin DAN5-6-6 Item 966 6 pin DAN5-8-5 Item 985 4 pin DAN5-8-6 Item 986 2 pin DAN5-8-7 Item 987 5 Install the sections and the angles at FR50 between STGR34LH and STGR34RH as shown in Section C15-C4 ’AFTER’:

a Put these items in position : 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 2 section D5347449520500 Item 032 2 section D5347449520400 Item 034 1 angle D5347470020400 Item 044 1 angle D5347470020500 Item 046 2 angle D5347470020200 Item 048 2 angle D5347470020300 Item 050 1 section D5347449523400 Item 058 1 section D5347449523600 Item 060 1 section D5347449522000 Item 062 2 section D5347449523200 Item 064 1 angle D5347470020800 Item 068 1 angle D5347470021000 Item 070 1 angle D5347470020600 Item 072 1 angle D5347470021200 Item 074

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel and the two holes in the angles, Item 064, and install with these items : 82 rivet MBBN4477-4812 Item 549 69 rivet LN9198-4816CF Item 648

4 collar NSA5075-6 Item 806 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 397 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

4 pin DAN5-6-4 Item 964 6 Replace the riveting between clip and skin panel at FR50 between STGR34LH/RH and STGR37LH/RH as shown in Section C18-C21 ’AFTER’ :

a Remove the existing rivets. bOpen the holes and the countersinks to final dimension.

c Install this item : 24 rivet NAS1097KE6-00 Item 548 (aa) Modify the structure at FR51 between STGR34LH and STGR34RH. Refer to Kit 281132D96R02 Refer to Drawing(s) : D53470075008 Sheet(s) 18 and 22 1 Replace the fasteners at FR51 between STGR34RH and STGR36RH as shown in Section D18-D22 ’AFTER’ :

a Remove the existing fasteners in the affected area as shown in Section D18-D22 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 34 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 16 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 6 pin DAN5-6-5 Item 965 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR51. 2 Install the reinforcing straps at FR51 between STGR35LH/RH and STGR42LH/RH as shown in Section D18-D22 ’AFTER’ :

a Put these at FR51 in position : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes and all countersinks to final dimension. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 398 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

d Install these items : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with : 58 rivet LN9198-4012CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit 281132D41R00. 3 Install the fittings at FR51 at STGR37LH/RH as shown in Section D18-D22 ’AFTER’ :

a Put these items at FR51 in position : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

bTransfer drill the holes from the frame to the fittings and open all holes to final dimension.

c Install these items : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with : 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR51 as shown in Section D18-D22’AFTER’ :

a Put these items at FR51 in position : 1 plate D5337217620000 Item 012 2 filler D5337217620800 Item 026 1 crossbeam D5347035300600 Item 076 1 plate D5337217620700 Item 078

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 076, IS IN LINE WITH THE CROSSBEAMS AND FR47 AND FR55. bTransfer drill all holes from the frame to the crossbeam.

c Put this item at FR51 in position as shown in Section B18-B22 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 399 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 support angle D5347658420000 Item 102

d Put these items at FR51 between STGR42LH and STGR42RH in position : 1 angle D5347470520000 Item 054 1 angle D5347470520100 Item 056 1 web D5347470420400 Item 080

eTransfer drill the holes from the frame and skin panel to the shear web and the supports. f Drill all additional holes and open all holes and all countersinks to final dimension. g Install these items : 1 plate D5337217620000 Item 012 2 filler D5337217620800 Item 026 1 angle D5347470520000 Item 054 1 angle D5347470520100 Item 056 1 crossbeam D5347035300600 Item 076 1 plate D5337217620700 Item 078 1 web D5347470420400 Item 080 1 support angle D5347658420000 Item 102 with : 12 rivet MBBN4477-4812 Item 549 16 rivet LN9198-4014CF Item 640 57 rivet LN9198-4816CF Item 648

6 pin DAN5-6-5X Item 765 44 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 12 collar NSA5075-8 Item 808 19 pin DAN5-6-4 Item 964 21 pin DAN5-6-5 Item 965

2 pin DAN5-6-6 Item 966 2 pin DAN5-6-8 Item 968 6 pin DAN5-8-5 Item 985 3 pin DAN5-8-6 Item 986 3 pin DAN5-8-7 Item 987 5 Install the sections and the angles at FR51 between STGR34LH/RH and STGR42LH/RH as shown in Section D18-D22 ’AFTER’:

a Put these items in position : 1 section D5347449520300 Item 028 1 section D5347449520500 Item 032 1 angle D5347470020400 Item 044 2 angle D5347470020200 Item 048 2 angle D5347449522000 Item 062 1 angle D5347470021600 Item 082 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 400 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 angle D5347470021800 Item 084 1 angle D5347470024800 Item 086 1 angle D5347470043800 Item 088 1 angle D5347470021400 Item 090 1 angle D5347470022200 Item 092 1 section D5347449520200 Item 094 1 section D5347449520400 Item 096 1 angle D5347470020500 Item 098 2 angle D5347470020300 Item 100

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel and install with these items : 34 rivet MBBN4477-4812 Item 549 62 rivet LN9198-4816CF Item 648

4 pin DAN6-6-7X Item 667 4 pin DAN6-6-9X Item 669 27 collar NSA5075-6 Item 806

8 collar DAN11-6X Item 807 17 pin DAN6-6-5 Item 865 10 pin DAN6-6-7 Item 867 6 Replace the riveting between clip and skin panel at FR51 between STGR40LH/RH and STGR42LH/RH as shown in Section D18-D22 ’AFTER’ :

a Remove the existing rivets. bOpen the holes and the countersinks to final dimension.

c Install these items : 8 rivet MBBN4477-4812 Item 549 4 pin DAN6-6-7X Item 667 4 pin DAN6-6-9X Item 669 8 pin DAN6-6-8Y Item 678 8 collar NSA5330-6 Item 803 8 collar DAN11-6X Item 807 7 Replace the riveting between stringer and skin panel at FR51 at STGR41RH as shown in Detail D18-D22 :

a Remove the existing rivets. bOpen the holes and the countersinks to final dimension.

c Install these items : 8 pin DAN6-6-8Y Item 678 8 collar NSA5330-6 Item 803 (ab) Modify the structure at FR52 between STGR34LH and STGR34RH. Refer to Kit 281132D95R00 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 401 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s) : D53470076008 Sheet(s) 11 and 12 1 Replace the fasteners at FR52 between STGR34RH and STGR36RH as shown in Section A11-A12 ’AFTER’ :

a Remove the affected fasteners between STGR34RH and STGR36RH as shown in Section A11-A12 ’AFTER’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 24 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 15 pin DAN5-6-3 Item 963

5 pin DAN5-6-4 Item 964 NOTE : The collars, Item 806, and the fasteners, Item 865, will be installed during the installation of the reinforcing straps at FR52. 2 Install the reinforcing straps at FR52 between STGR35LH/RH and STGR42LH/RH as shown in Section A11-A12 ’AFTER’ :

a Put these items at FR52 in position : 1 strap (LH) D5347448420200 Item 202 1 strap (RH) D5347448420300 Item 203

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes to final dimension. d Install these items : 1 strap (LH) D5347448420200 Item 202 1 strap (RH) D5347448420300 Item 203 with : 58 rivet LN9198-4012CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : The collars and the fasteners, Item 806 and Item 865, are supplied in Kit 281132D08R00.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 402 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

3 Install the fittings at FR52 at STGR37LH/RH as shown in Section A1-A2 ’AFTER’ :

a Put these items at FR52 in position : 1 fitting (LH) D5347449420600 Item 200 1 fitting (RH) D5347449421100 Item 201

bTransfer drill the holes from the frame to the fittings and open all holes to final dimension.

c Install these items : 1 fitting (LH) D5347449420600 Item 200 1 fitting (RH) D5347449421100 Item 201 with : 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Reinforce the crossbeam attachment at FR52 as shown in Section A11-A12 ’AFTER’ :

a Remove the crossbeam from FR52 temporarily. b Put these items with the removed crossbeam at FR52 in position : 1 fitting D5347449320000 Item 010 1 reinforcing sheet D5337217620000 Item 012 1 L-profile D5347449521600 Item 014 1 fitting D5347658920000 Item 016 1 shim D5347659220000 Item 018 1 fitting D5347659020000 Item 020 1 shim D5337217620800 Item 032 2 shim D5337217620400 Item 038 1 shim D5347658220200 Item 048 1 support D5347037820400 Item 204 1 fitting D5347449920200 Item 206 1 fitting D5347449820400 Item 244

CAUTION : ENSURE THAT THE CROSSBEAM IS IN LINE WITH THE CROSSBEAMS AT FR47 AND FR55.

c Transfer drill all holes from the frame. d Put these items at FR52 between STGR42LH and STGR42RH in position : 1 support D5347470520000 Item 040 1 support D5347470520100 Item 041 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 403 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 web D5347657720000 Item 208

eTransfer drill the holes from the frame and skin panel to the shear web and the supports. f Drill all additional holes and open all holes to final dimension. g Install the crossbeam with these items at FR52 as shown in Section A11-A12 ’AFTER’ : 1 fitting D5347449320000 Item 010 1 reinforcing sheet D5337217620000 Item 012 1 L-profile D5347449521600 Item 014 1 fitting D5347658920000 Item 016 1 shim D5347659220000 Item 018 1 fitting D5347659020000 Item 020 1 shim D5337217620800 Item 032 2 shim D5337217620400 Item 038 1 support D5347470520000 Item 040 1 support D5347470520100 Item 041 1 shim D5347658220200 Item 048 1 support D5347037820400 Item 204 1 fitting D5347449920200 Item 206 1 web D5347657720000 Item 208 1 fitting D5347449820400 Item 244 with : 12 rivet MBBN4477-4810 Item 549

6 rivet LN9198-4014CF Item 640 39 rivet LN9198-4816CF Item 648

6 rivet LN9198-6412CF Item 664 6 pin DAN5-6-5X Item 765 65 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 9 collar NSA5075-8 Item 808 10 pin DAN5-6-3 Item 963 15 pin DAN5-6-4 Item 964 37 pin DAN5-6-5 Item 965

1 pin DAN5-6-6 Item 966 2 pin DAN5-6-7 Item 967 3 pin DAN5-8-5 Item 985 4 pin DAN5-8-6 Item 986 2 pin DAN5-8-7 Item 987 5 Install this item at the crossbeam at FR52 as shown in drawing D53470076008, Sheet 17, Detail X11-17 :

a Drill the two holes and open the holes to final dimension. b Install this item : 2 rivet LN9198-4014CF Item 640 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 404 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

6 Replace the fasteners at FR52 between STGR41LH/RH and STGR42LH/RH :

a Remove the fasteners as shown in Section A11-A12 ’BEFORE’. bOpen the holes to final dimension.

c Install these items as shown in Section A11-A12 ’AFTER’ : 10 rivet LN9198-4816CF Item 648 7 Install the L-profiles and the angles at FR52 between STGR34LH/RH and STGR42LH/RH as shown in Section A11-A12 ’AFTER’ :

a Put these items in position : 2 angle D5347470020200 Item 022 1 angle D5347470020300 Item 023 1 angle D5347470020400 Item 024 1 L-profile D5347449520400 Item 026 1 L-profile D5347449520500 Item 027 1 L-profile D5347449520300 Item 028 1 angle D5347470021400 Item 030 1 angle D5347470023200 Item 034 1 angle D5347470023400 Item 036 1 angle D5347470021000 Item 042 1 angle D5347470021200 Item 044 1 angle D5347470024000 Item 046 1 angle D5347470023800 Item 050 1 angle D5347470023600 Item 052 1 key D5347550021000 Item 082

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items : 2 angle D5347470020200 Item 022 1 angle D5347470020300 Item 023 1 angle D5347470020400 Item 024 1 L-profile D5347449520400 Item 026 1 L-profile D5347449520500 Item 027 1 L-profile D5347449520300 Item 028 1 angle D5347470021400 Item 030 1 angle D5347470023200 Item 034 1 angle D5347470023400 Item 036 1 angle D5347470021000 Item 042 1 angle D5347470021200 Item 044 1 angle D5347470024000 Item 046 1 angle D5347470023800 Item 050 1 angle D5347470023600 Item 052 1 key D5347550021000 Item 082 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 405 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

with : 43 rivet MBBN4477-4810 Item 549 59 rivet LN9198-4816CF Item 648 23 collar NSA5075-6 Item 806

8 pin DAN6-6-3 Item 863 1 pin DAN6-6-5 Item 865 10 pin DAN6-6-6 Item 866

3 pin DAN6-6-7 Item 867 1 pin DAN6-6-8 Item 868 8 Replace the riveting between clip and skin panel at FR52 between STGR35LH/RH and STGR42LH/RH as shown in Section A11-A12 ’AFTER’ :

a Remove the existing rivets. bOpen the holes and the countersinks to final dimension.

c Install these items : 25 rivet MBBN4477-4810 Item 549 27 collar NSA5075-6 Item 806

8 pin DAN6-6-3 Item 863 4 pin DAN6-6-4 Item 864 1 pin DAN6-6-5 Item 865 10 pin DAN6-6-6 Item 866

3 pin DAN6-6-7 Item 867 1 pin DAN6-6-8 Item 868 (ac) Modify the structure at FR52A between STGR38RH and STGR40RH. Refer to Kit 281132D95R00 Refer to Drawing(s) : D53470076008 Sheet(s) 13 1 Remove these items from FR52A as shown in drawing D53470076008, Sheet 13, Detail A13-A13 and Section B11-B13 ’BEFORE’.

a Remove and discard these items : 1 nut NAS1791A3-1 Item (460) Discard 1 nut NAS1068C3 Item (462) Discard

bClose the existing rivet holes with this item : 4 rivet DIN65399-2400CF Item 724 2 Close the existing rivet holes at FR52A as shown in drawing D53470076008, Sheet 13, Detail B13-B13 ’AFTER’.

a Install these items : 2 pin DAN6-6-5X Item 665 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 406 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 collar DAN11-6X Item 807 3 Install the fitting at FR52A as shown in drawing D53470076008, Sheet 13, Section B11-B13 ’AFTER’.

a Put this item at FR52A in position : 1 fitting D5347659320000 Item 054

b Drill all additional holes and open all holes to final dimension.

c Install this item at FR52A : 1 fitting D5347659320000 Item 054 with these items : 11 collar NSA5075-6 Item 806

5 pin DAN5-6-4 Item 964 3 pin DAN5-6-6 Item 966 3 pin DAN5-6-9 Item 969 (ad) Modify the structure at FR53 between STGR34LH and STGR41RH. Refer to Kit 281132D95R00 Refer to Drawing(s) : D53470076008 Sheet(s) 14 1 Install the fitting at FR53 at STGR37LH as shown in Section C11-C14 ’AFTER’ :

a Put this item at FR53 in position : 1 fitting (LH) D5347449420600 Item 200

bTransfer drill the holes from the frame to the fitting and open all holes to final dimension.

c Install this item : 1 fitting (LH) D5347449420600 Item 200 with : 17 collar NSA5075-6 Item 806

7 pin DAN5-6-4 Item 964 4 pin DAN5-6-5 Item 965 4 pin DAN5-6-6 Item 966 2 pin DAN5-6-7 Item 967 2 Install the crossbeam at FR53 as shown in Section C11-C14 ’AFTER’ :

a Put these items at FR53 in position : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 plate D5337217621000 Item 056 1 shim D5337217621200 Item 060 1 crossbeam D5347026100600 Item 218

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 218, IS IN LINE WITH THE CROSSBEAMS AND FR47 AND FR55. bTransfer drill all holes from the frame.

c Put these items at FR53 between STGR42LH and STGR42RH in position : 1 support D5347470520300 Item 066 1 web D5347658820000 Item 070

dTransfer drill the holes from the frame and skin panel to the shear web and the supports.

e Drill all additional holes and open all holes to final dimension. f Install these item : 1 plate D5337217621000 Item 056 1 shim D5337217621200 Item 060 1 support D5347470520300 Item 066 1 web D5347658820000 Item 070 1 crossbeam D5347026100600 Item 218 with : 4 rivet MBBN4477-4010 Item 541 13 rivet MBBN4477-4810 Item 549

4 rivet LN9198-4014CF Item 640 42 rivet LN9198-4816CF Item 648

3 pin DAN5-6-5X Item 765 30 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 6 collar NSA5075-8 Item 808 3 pin DAN5-6-3 Item 963 11 pin DAN5-6-4 Item 964 12 pin DAN5-6-5 Item 965

2 pin DAN5-6-6 Item 966 3 pin DAN5-8-5 Item 985 4 pin DAN5-8-6 Item 986 2 pin DAN5-8-7 Item 987 3 Replace the fasteners at FR53 between STGR41LH and STGR42LH :

a Remove the fasteners as shown in Section C11-C14 ’BEFORE’. bOpen the holes to final dimension.

c Install this item as shown in Section C11-C14 ’AFTER’ : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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5 rivet LN9198-4816CF Item 648 4 Install the L-profiles and the angles at FR53 between STGR34LH and STGR41RH as shown in Section C11-C14 ’AFTER’ :

a Put these items in position : 2 angle D5347470020200 Item 022 1 angle D5347470020400 Item 024 1 L-profile D5347449520500 Item 027 1 L-profile D5347449520300 Item 028 1 angle D5347470024200 Item 058 1 angle D5347470046200 Item 062 1 angle D5347470046400 Item 064 1 L-profile D5347449523400 Item 096 2 L-profile D5347449524000 Item 098 1 L-profile D5347449524200 Item 100 1 clip D5347075321400 Item 114 Refer to Drawing(s) : b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items : 2 angle D5347470020200 Item 022 1 angle D5347470020400 Item 024 1 L-profile D5347449520500 Item 027 1 L-profile D5347449520300 Item 028 1 angle D5347470024200 Item 058 1 angle D5347470024400 Item 062 1 angle D5347470024600 Item 064 1 L-profile D5347449523400 Item 096 2 L-profile D5347449524000 Item 098 1 L-profile D5347449524200 Item 100 1 clip D5347075321400 Item 114 with : 41 rivet MBBN4477-4810 Item 549 40 rivet LN9198-4816CF Item 648 16 collar NSA5075-6 Item 806 12 pin DAN6-6-3 Item 863

4 pin DAN5-6-3 Item 963 5 Replace the riveting between clip and skin panel at FR53 between STGR34LH and STGR42LH and between STGR41RH and STGR42RH as shown in Section C11-C14 :

a Remove the existing rivets. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 409 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

bOpen the holes and the countersinks to final dimension.

c Install these items : 28 rivet MBBN4477-4810 Item 549 12 collar NSA5075-6 Item 806 12 pin DAN6-6-3 Item 863 (ae) Modify the structure at FR53 between STGR36LH and STGR42LH. Refer to Kit 281132D96R02 Refer to Drawing(s) : D53470075008 Sheet(s) 23 1 Remove this item at FR53 as shown in Section E18-E23 ’BEFORE’ :

a Remove and discard this item : 1 shim D5347061120200 Item (402) Discard 2 Install the reinforcing strap at FR53 between STGR35LH and STGR42LH as shown in Section E18-E23 ’AFTER’ :

a Put this item at FR53 in position : 1 strap D5347448420200 Item 022

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes and all countersinks to final dimension. d Install these items : 1 strap D5347448420200 Item 022 with : 29 rivet LN9198-4014CF Item 640

4 collar NSA5075-6 Item 806 4 pin DAN6-6-5 Item 865 NOTE : The collars and the fasteners, Item 806 and Item 865, are supplied in Kit 281132D08R00. (af) Modify the structure at FR54 between STGR34LH and STGR41RH. Refer to Kit 281132D95R00 Refer to Drawing(s) : D53470076008 Sheet(s) 11 and 15 1 Install the reinforcing strap at FR54 between STGR35LH and STGR42LH as shown in Section D11-D15 ’AFTER’ : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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a Put this item at FR54 in position : 1 strap (LH) D5347448420200 Item 202

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing strap to the frame and open all holes to final dimension. d Install this item : 1 strap (LH) D5347448420200 Item 202 with : 29 rivet LN9198-4014CF Item 640

4 collar NSA5075-6 Item 806 4 pin DAN6-6-5 Item 865 NOTE : The collars and the fasteners, Item 806 and Item 865, are supplied in Kit 281132D08R00. 2 Install the fitting at FR54 at STGR37LH as shown in Section D11-D15 ’AFTER’ :

a Put this item at FR54 in position : 1 fitting (LH) D5347449420600 Item 200

bTransfer drill the holes from the frame to the fitting and open all holes to final dimension.

c Install this item : 1 fitting (LH) D5347449420600 Item 200 with : 17 collar NSA5075-6 Item 806

7 pin DAN5-6-4 Item 964 4 pin DAN5-6-5 Item 965 4 pin DAN5-6-6 Item 966 2 pin DAN5-6-7 Item 967 3 Install the crossbeam at FR54 as shown in Section D11-D15 ’AFTER’ :

a Put these items at FR54 in position : 1 shim D5337217621200 Item 060 1 plate D5337217625800 Item 110 1 crossbeam D5347035601400 Item 230

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 230, IS IN LINE WITH THE CROSSBEAMS AT FR47 AND FR55. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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bTransfer drill all holes from the frame.

c Put these items at FR54 between STGR42LH and STGR42RH in position : 1 web D5347657920200 Item 076 1 L-profile D5347449522600 Item 078 1 L-profile D5347449522800 Item 080

dTransfer drill the holes from the frame and skin panel to the shear web and the L-profile.

e Drill all additional holes and open all holes and all countersinks to final dimension. f Install these items : 1 shim D5337217621200 Item 060 1 web D5347657920200 Item 076 1 L-profile D5347449522600 Item 078 1 L-profile D5347449522800 Item 080 1 plate D5337217625800 Item 110 1 crossbeam D5347035601400 Item 230 with : 4 rivet MBBN4477-4010 Item 541 16 rivet MBBN4477-4810 Item 549

8 rivet LN9198-4014CF Item 640 42 rivet LN9198-4816CF Item 648

3 pin DAN5-6-5X Item 765 28 collar NSA5075-6 Item 806

3 collar DAN11-6X Item 807 9 collar NSA5075-8 Item 808 10 pin DAN5-6-4 Item 964 16 pin DAN5-6-5 Item 965

2 pin DAN5-6-6 Item 966 3 pin DAN5-8-5 Item 985 4 pin DAN5-8-6 Item 986 2 pin DAN5-8-7 Item 987 4 Replace the fasteners at FR54 between STGR41LH and STGR42LH :

a Remove the fasteners as shown in Section D11-D15 ’BEFORE’. bOpen the holes to final dimension.

c Install this item as shown in Section D11-D15 ’AFTER’ : 6 rivet LN9198-4816CF Item 648 5 Install the L-profile and the angles at FR54 between STGR34LH and STGR42LH as shown in Section D11-D15 ’AFTER’: DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 412 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Put these items in position : 2 angle D5347470020200 Item 022 1 angle D5347470020400 Item 024 1 L-profile D5347449520500 Item 027 1 L-profile D5347449520300 Item 028 1 angle D5347470024200 Item 058 1 angle D5347470025000 Item 072 1 angle D5347470025200 Item 074

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items : 2 angle D5347470020200 Item 022 1 angle D5347470020400 Item 024 1 L-profile D5347449520500 Item 027 1 L-profile D5347449520300 Item 028 1 angle D5347470024200 Item 058 1 angle D5347470025000 Item 072 1 angle D5347470025200 Item 074 with : 23 rivet MBBN4477-4810 Item 549 29 rivet LN9198-4816CF Item 648 12 collar NSA5075-6 Item 806 12 pin DAN6-6-3 Item 863 6 Replace the riveting between clip and skin panel at FR54 between STGR34LH and STGR42LH as shown in Section D11-D15 ’AFTER’ :

a Remove the existing rivets. bOpen the holes and the countersinks to final dimension.

c Install these items : 23 rivet MBBN4477-4810 Item 549 12 collar NSA5075-6 Item 806 12 pin DAN6-6-3 Item 863 (ag) Install the shear plates between FR48 and FR51 at STGR43LH. Refer to Kit 281132D96R02 Refer to Drawing(s) : D53470075008 Sheet(s) 18 and 24 1 Install the shear plate between FR48 and FR49 at STGR43LH as shown in Section F18-F24 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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a Put this item in position : 1 plate D5347471321200 Item 104

b Put this item in position as shown in Sheet 20, Section B18-B20 : 1 section D5347449521800 Item 020

c Transfer drill the holes to the section, Item 020. d Drill the additional holes from the shear plate to the stringer and crossbeams and open all holes to final dimension.

e Install these items : 1 section D5347449521800 Item 020 1 plate D5347471321200 Item 104 with : 34 rivet LN9198-4014CF Item 640

2 rivet LN9198-4816CF Item 648 2 collar NSA5075-6 Item 806 2 pin DAN5-6-7 Item 967 2 Install the shear plates between FR49 and FR51 at STGR43LH as shown in Section F18-F24 : Refer to Drawing(s) : D53470075008 Sheet(s) 20 and 24

a Put this item in position : 1 angle D5347471322400 Item 138 1 angle D5347471322600 Item 140

b Put this item in position as shown in Sheet 21, Section C18-C21 and Sheet 22, Section D18-D22. 2 section D5347449522000 Item 062

c Transfer drill the holes to the sections, Item 062. d Drill the additional holes from the shear plate to the stringer and crossbeams and open all holes to final dimension.

e Install these items : 2 section D5347449522000 Item 062 1 angle D5347471322400 Item 138 1 angle D5347471322600 Item 140 with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 414 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

59 rivet LN9198-4014CF Item 640

4 rivet LN9198-4816CF Item 648 4 collar NSA5075-8 Item 808 4 pin DAN5-8-7 Item 987 (ah) Install the shear plates between FR51 and FR54 at STGR43LH. Refer to Kit 281132D95R00 Refer to Drawing(s) : D53470076008 Sheet(s) 11, 12 and 14 thru 17 1 Install the shear plate between FR51 and FR52 at STGR43LH as shown in drawing D53470076008, Sheet 11, Section E11-E16 ’AFTER’ and Sheet 12, Section A11-A12 ’AFTER’ :

a Put these items in position : 1 shear plate D5347471320800 Item 084 1 L-profile D5347449522000 Item 088

bTransfer drill the holes to the L-profile, Item 088.

c Drill the additional holes from the shear plate to the stringer and crossbeams and open all holes to final dimension. d Install these items : 1 shear plate D5347471320800 Item 084 1 L-profile D5347449522000 Item 088 with : 29 rivet LN9198-4014CF Item 640

7 rivet LN9198-4816CF Item 648 2 collar NSA5075-8 Item 808 2 pin DAN5-8-7 Item 987 2 Install the shear plate between FR52 and FR53 at STGR43LH as shown in drawing D53470076008, Sheet 16, Section E11-E16 and Section C11-C14, Sheet 14 ’AFTER’ :

a Put these items in position : 1 L-profile D5347449522200 Item 090 1 shear plate D5347471321800 Item 102

bTransfer drill the holes to the L-profile, Item 090.

c Drill the additional holes from the shear plate to the stringer and crossbeams and open all holes to final dimension. d Install these items : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 415 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 L-profile D5347449522200 Item 090 1 shear plate D5347471321800 Item 102 with : 29 rivet LN9198-4014CF Item 640

7 rivet LN9198-4816CF Item 648 2 collar NSA5075-8 Item 808 2 pin DAN5-8-7 Item 987 3 Install the shear plate between FR53 and FR54 at STGR43LH as shown in drawing D53470076008, Sheet 16, Section E11-E16 and Sheet 15 Section D11-D15 ’AFTER’ :

a Put these items in position as shown in drawing D53470076008, Sheet 16, Section E11-E16 : 1 shear plate D5347471320800 Item 084 1 L-profile D5347449522000 Item 088

bTransfer drill the holes, drill the additional holes and open all holes to final dimension.

c Install these items : 1 shear plate D5347471320800 Item 084 1 L-profile D5347449522000 Item 088 with : 29 rivet LN9198-4014CF Item 640

7 rivet LN9198-4816CF Item 648 2 collar NSA5075-8 Item 808 2 pin DAN5-8-7 Item 986 4 Drill additional fastener holes between FR51 and FR54, refer to drawing D53470076008, Sheet 17, Detail X11-17. (ai) Modify the structure between FR47 and FR48 at STGR38LH/RH and STGR43LH. Refer to Kit 281132D42R00 Refer to Drawing(s) : D53372362008 Sheet(s) 7 1 Remove the nuts at STGR38LH and STGR38RH as shown in Detail W1-7.

a Remove and discard this item : 6 nut NAS1791A3-1 Item (216) Discard 2 Remove the connections at STGR38LH and STGR38RH as shown in Detail W1-7. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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a Remove and discard these items : 1 connection (LH) D5347101620400 Item (210) Discard 1 connection (RH) D5347101620500 Item (211) Discard 3 Install the plates, the sections and the connections at STGR38LH and STGR38RH as shown in Detail W1-7.

aAt STGR38LH : Put these items in position : 1 plate D5337217400000 Item 024 1 section D5347449520800 Item 028 1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620490 Item 042 NOTE : Install the fillers, Item 030, 032, 034, 036 and 038, as required. NOTE : Install the section, Item 028, together with the angle, Item 130. bAt STGR38RH : Put these items in position : 1 plate D5337217400100 Item 025 1 section D5347449520900 Item 029 1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620590 Item 043 NOTE : Install the fillers, Item 030, 032, 034, 036 and 038, as required. NOTE : Install the section, Item 029, together with the angle, Item 134, at FR48.

cTransfer drill the holes from the skin panel and the stringer to the connections. d Drill the additional holes in the plates, sections and connections and open all holes and all countersinks to final dimension.

e Install these items at STGR38LH : 1 plate D5337217400000 Item 024 1 section D5347449520800 Item 028 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620490 Item 042 with : 6 rivet NAS1097AD4-10 Item 532 21 rivet LN9198-4014CF Item 640

1 pin DAN5-6-6X Item 766 4 pin DAN5-6-7X Item 767 13 pin DAN5-6-8X Item 768

1 pin DAN5-6-9X Item 769 6 collar NSA5075-6 Item 806 19 collar DAN11-6X Item 807

4 pin DAN5-6-5 Item 965 2 pin DAN5-6-9 Item 969

f Install these items at STGR38RH : 1 plate D5337217400100 Item 025 1 section D5347449520900 Item 029 1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620590 Item 043 with : 6 rivet NAS1097AD4-10 Item 532 21 rivet LN9198-4014CF Item 640

1 pin DAN5-6-6X Item 766 4 pin DAN5-6-7X Item 767 13 pin DAN5-6-8X Item 768

1 pin DAN5-6-9X Item 769 6 collar NSA5075-6 Item 806 19 collar DAN11-6X Item 807

4 pin DAN5-6-5 Item 965 2 pin DAN5-6-9 Item 969 4 Remove the connection at STGR43LH as shown in Detail V1-7.

a Remove and discard this item : 1 connection D5347100720400 Item (208) Discard 5 Install the plate, the section and the coupling at STGR43LH as shown in Detail V1-7. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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a Put these items at STGR43LH in position : 1 plate D5337217320000 Item 022 1 section D5337216020000 Item 026 1 coupling D5347100720600 Item 040

bTransfer drill the holes from STGR43 to the plate and the connection.

c Drill all additional holes in the plate and the section and open all holes and all countersinks to final dimension. d Install these items : 1 plate D5337217320000 Item 022 1 section D5337216020000 Item 026 1 coupling D5347100720600 Item 040 with : 34 rivet LN9198-4014CF Item 640

4 pin DAN5-6-7X Item 767 4 pin DAN5-6-8X Item 768 2 collar NSA5075-6 Item 806 8 collar DAN11-6X Item 807 16 collar DAN11-8X Item 810

1 pin DAN5-8-8X Item 888 4 pin DAN5-8-9X Item 889 10 pin DAN5-8-10X Item 890

1 pin DAN5-8-11X Item 891 2 pin DAN5-6-7 Item 967 (aj) Install the plates between FR48 and FR59 at STGR38LH and STGR38RH. Refer to Kit 281132D96R02 Refer to Drawing(s) : D53470075008 Sheet(s) 18 thru 31 1 Install the plates and the angles between FR48 and FR59 at STGR38LH as shown in Sections H18-H25 and K28-K28 : Refer to Drawing(s) : D53470075008 Sheet(s) 25

a Put these items in position : 2 plate D5347471500200 Item 108 1 plate D5347471500000 Item 110 1 plate D5347471502800 Item 112 1 plate D5347471500800 Item 114 1 plate D5347471501000 Item 116 6 angle D5347470120000 Item 128 6 angle D5347470120200 Item 130 1 plate D5347048800400 Item 214 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 plate D5347048900400 Item 216 1 plate D5347049200400 Item 218 2 angle D5347046824000 Item 228 1 angle D5347046823800 Item 230 1 angle D5347046823600 Item 232 1 angle D5347046824200 Item 234 1 angle D5347046824400 Item 236 NOTE : Install the angle, Item 130, together with the section, Item 028. bTransfer drill the holes from the stringer and frames to the plates and the angles.

c Transfer drill the holes from the skin panel to the section at FR52. d Drill the additional holes and open all holes to final dimension.

e Install the listed items as shown in Sections H18-H25 and X28-28 with : 227 rivet LN9198-4014CF Item 640 4 pin DAN6-6-5X Item 665 3 pin DAN6-6-6X Item 666 3 pin DAN6-6-7X Item 667 5 pin DAN5-6-4X Item 764 8 pin DAN5-6-6X Item 766 3 pin DAN5-6-8X Item 768 16 collar NSA5075-6 Item 806 26 collar DAN11-6X Item 807 10 pin DAN5-6-4 Item 964

6 pin DAN5-6-8 Item 968 2 Install the plates and angles between FR48 and FR59 at STGR38RH as shown in Sections G18-G25 and B25-B25 : Refer to Drawing(s) : D53470075008 Sheet(s) 25

a Put these items in position : 2 plate D5347471500300 Item 118 1 plate D5347471500100 Item 120 1 plate D5347471503200 Item 122 1 plate D5347471502600 Item 124 1 angle D5347659100000 Item 126 4 angle D5347470120100 Item 132 5 angle D5347470120300 Item 134 1 angle D5347046824300 Item 222 1 angle D5347046824600 Item 224 NOTE : Install the angle, Item 134, together with the section, Item 029, at FR48.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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bTransfer drill the holes from the stringer and frames to the plates and the angles and open all holes to final dimension.

c Install the listed items as shown in Sections G18-G25 and B25-B25 with : 106 rivet LN9198-4014CF Item 640 2 pin DAN5-6-4X Item 764 1 pin DAN5-6-8X Item 768 3 collar NSA5075-5 Item 804 6 collar NSA5075-6 Item 806 3 collar DAN11-6X Item 807 3 pin DAN5-5-5 Item 945 4 pin DAN5-6-4 Item 964 2 pin DAN5-6-8 Item 968 (ak) Install the corner sections at STGR38LH/RH between FR48 and FR59. Refer to Kit 281132D96R02 Refer to Drawing(s) : D53470075008 Sheet(s) 18, 26, 27 and 28 1 Install the corner sections at STGR38LH between FR48 and FR59 as shown in Details X26-27 :

a Put these items between FR48 and FR56 in position : 1 section D5347047500800 Item 154 1 section D5347047600800 Item 156

bTransfer drill the holes from the fittings to the corner sections as shown in Details A18-A19, B18-B20 and C18-C21.

c Drill the holes from the corner sections to the plates between FR48 and FR59 as shown in Details X26-27, T27-27 and U27-27 . d Open the holes to final dimension and countersink the holes.

e Install these items : 1 section D5347047500800 Item 154 1 section D5347047600800 Item 156 with : 16 rivet MBBN4477-4012 Item 541 12 rivet MBBN4477-4812 Item 549 87 rivet DIN65399-3200CF Item 732 f The holes with 5.6 mm (0.220 in.) diameter between FR48 and FR51 as shown in Detail X26-27 will transfer from the roller tracks. 2 Install the corner section at STGR38RH between FR48 and FR59 as shown in Details Z26-27 and Z18-28 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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a Put this item between FR48 and FR52A in position : 1 section D5347048100600 Item 152

bTransfer drill the holes from the fittings to the corner section as shown in Details A18-A19, B18-B20, C18-C21 and D18-D22.

c Drill the holes from the corner section to the plates between FR48 and FR59 as shown in Details Z26-27 and Z18-28. d Open the holes to final dimension and countersink the holes.

e Install these items : 1 section D5347048100600 Item 152 with : 8 rivet MBBN4477-4012 Item 541 12 rivet MBBN4477-4812 Item 549 48 rivet DIN65399-3200CF Item 732 f The holes with 5.6 mm (0.220 in.) diameter between FR48 and FR51 as shown in Detail Z26-27 will transfer from the roller tracks. (al) Modify the crossbeams from FR48 thru FR52 for the roller track installation. Refer to Kit 281132D96R02 Refer to drawings : D53470075008 Sheet(s) 18, 26 and 27 1 Drill the holes in the crossbeams at FR48, FR49, FR50 and FR51 as shown in Details U26-26 and W26-26 :

a Mark and drill the holes with 5.6 mm (0.220 in.). 2 Install the nuts, Item 508, at the crossbeam at FR52 as shown in Details A27-A27, V27-27 and W18-27 :

a Mark and drill the holes with 5.2 mm (0.205 in.). b Put the nuts in position, drill the rivet holes and install this item : 4 nut NAS1791A3-1 Item 508 with : 8 rivet DIN65399-2400CF Item 724 (am) Install the water drain connection between FR47 and FR48. Refer to Kit 281132D96R02

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 422 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to drawings : D53372362008 Sheet(s) 9 D53470075008 Sheet(s) 29 1 Make a cutout between 63.7 mm (2.508 in.) and 64.3 mm (2.531 in.) diameter in the skin panel between FR47 and FR48 and between STGR42RH and STGR43RH as shown in drawing D53470075008, Sheet 29, Sections C18-29 and A30-30. 2 Install the doubler at the outer skin as shown in the drawing D53470075008, Sheet 30, Section A29-A30 and Z30-30 and the drawing D53372362008, Sheet 9, Detail U1-9. NOTE : Drawing D53372362008 shows the position of the doubler and fasteners for the attachment. The fasteners are contained in Kit 281132D42R00.

a Remove the existing fasteners in the affected area. b Put this item in position as shown in drawing D53470075008, Sheet 30, Section A29-A30 and drawing D53372362008, Sheet 9, Detail U1-9 : 1 doubler D5347646320200 Item 160

c Transfer drill the holes. d Drill the additional holes and open all holes to final dimension as shown in drawing D53470075008, Sheet 30, Detail A29-30.

e Install this item : 1 doubler D5347646320200 Item 160 with : 33 rivet LN9198-4816CF Item 648 12 pin DAN5-6-8X Item 768 18 pin DAN5-6-9X Item 769

4 pin DAN5-6-11X Item 771 10 pin DAN5-6-12X Item 772 14 collar NSA5075-6 Item 806 44 collar DAN11-6X Item 807 18 collar DAN11-8X Item 810

4 pin DAN5-8-7X Item 887 6 pin DAN5-8-11X Item 891 8 pin DAN5-8-12X Item 892 14 pin DAN5-6-6 Item 966 NOTE : The Items 768, 769, 771, 772, 807, 810, 887, 891 and 892 are contained in Kit 281132D42R00.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 423 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

3 Install the tube as shown in drawing D53470075008, Sheet 30, Section C18-29 and in Detail A30-30 :

a Put these items in position : 1 tube D5347669000000 Item 172 2 shim D5347472120000 Item 176

or 2 Shim D5347472120200 Item 176

bTransfer drill the eight holes as shown in drawing D53372362008, Sheet 30, Detail Z30-30.

c Drill the eight holes as shown in drawing D53470075008, Sheet 30, Detail Z30-30. d Open all holes to final dimension.

e Install these items : 1 tube D5347669000000 Item 172 2 shim D5347472120000 Item 176

or 2 Shim D5347472120200 Item 176 with : 8 pin DAN5-6-11X Item 771 8 collar NSA5075-6 Item 806 8 collar DAN11-6X Item 807 2 pin DAN6-6-6 Item 866 6 pin DAN6-6-10 Item 870 NOTE : The Items 771 and 807 are contained in Kit 281132D05R01, refer to drawing D53372362004, Sheet 9. f Drill the four holes for the receptacles, Item 504, with 5.6 mm (0.220 in.) diameter as shown in drawing D53470075008, Sheet 30, Detail Z30-30 and install this item : 4 receptacle ABS0337-01A Item 504 with : 8 rivet DIN65399-2400CF Item 724

g Install at the tube, Item 172, as shown in drawing D53470075008, Sheet 30, Section A29-A30 these items : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 424 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 plate D5347669200000 Item 166 1 plug D5347669100000 Item 174 1 ring MS16625-4212 Item 500 1 screw NAS1096-3-10 Item 506 (an) Install the water drain connection and the cavity drain access cover between FR49 and FR50. Refer to Kit 281132D96R02 Refer to Drawing(s) : D53470075008 Sheet(s) 31 1 Make a cutout between 63.7 mm (2.508 in.) and 64.3 mm (2.531 in.) diameter in the skin panel between FR49 and FR50 and between STGR42LH and STGR43LH as shown in Sections B29-B31 and Detail A31-31. 2 Install the doubler at the outer skin as shown in Section B29-B31 : CAUTION : REMOVE THE EXISTING RIVETS CAREFULLY. THE HEADS OF THE RIVETS WILL BE USED DURING THE DOUBLER INSTALLATION FOR THE EXISTING COUNTERSINKS IN THE SKIN PANEL.

a Remove the existing fasteners in the affected area. b Put this item in position as shown in Detail A31-31 : 1 doubler D5347646320000 Item 162

c Transfer drill the holes. d Drill the additional holes as shown in Detail A31-31 and open all holes to final dimension.

e Install this item : 1 doubler D5347646320000 Item 162 with : 48 rivet LN9198-4816CF Item 648

8 pin DAN5-6-8Y Item 778 8 collar NSA5330-6 Item 803 154 collar NSA5075-6 Item 806

25 pin DAN5-6-5 Item 965 58 pin DAN5-6-6 Item 966 14 pin DAN5-6-7 Item 967 57 pin DAN5-6-8 Item 968 3 Install the tube as shown in Section B29-B31 and Detail A31-31 :

a Put these items in position : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 425 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 tube D5347669000000 Item 172 2 shim D5347472120000 Item 176

or 2 Shim D5347472120200 Item 176

bTransfer drill the eight holes from the stringers to the tube as shown in Detail Y31-31.

c Drill the eight holes as shown in Detail Y34-31. d Open all holes to final dimension.

e Install these items : 1 tube D5347669000000 Item 172 2 shim D5347472120000 Item 176

or 2 Shim D5347472120200 Item 176 with : 16 collar NSA5075-6 Item 806

2 pin DAN6-6-6 Item 866 6 pin DAN6-6-10 Item 870 8 pin DAN5-6-10 Item 970

f Drill the four holes for the receptacles, Item 504, with 5.6 mm (0.220 in.) diameter as shown in Detail Y31-31 and install this item : 4 receptacle ABS0337-01A Item 504 with : 8 rivet DIN65399-2400CF Item 724

g Install these items at the tube, Item 172, as shown in Section B29-B31 : 1 plate D5347669200000 Item 166 1 plug D5347669100000 Item 174 1 ring MS16625-4212 Item 500 1 screw NAS1096-3-10 Item 506 4 Make a cutout in the skin panel between FR49 and FR50 and between STGR40LH and STGR41LH as shown in Detail A31-31. 5 Install the nuts, Item 510, around the cutout as shown in Detail Z31-31 :

a Remove the six rivets in the stringer and open the holes to 5.6 mm (0.220 in.) diameter. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 426 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

b Drill the four holes with 5.6 mm (0.220 in.) diameter in the skin.

c Install these items : 4 shim D5347470220000 Item 178 10 nut NAS1474A3 Item 510 with : 20 rivet DIN65399-2400CF Item 724 d Install this item as shown in Section B29-B31 : 1 cover D5347470920200 Item 164 with : 10 screw NAS1153E7 Item 502 (ao) Drill three holes in the outer skin between FR47 and FR49 and between STGR43LH and STGR42RH. Refer to Drawing(s) : D53470075008 Sheet(s) 29 1 Drill two holes with 20.0 mm (0.787 in.) diameter and one hole with 14.5 mm (0.578 in.) diameter as shown in Detail C18-29. (ap) Install the water drain connection between FR50 and FR51. Refer to Kit 281132D95R00 Refer to Drawing(s) : D53470076008 Sheet(s) 18 and 19 1 Make a cutout between 63.7 mm (2.508 in.) and 64.3 mm (2.531 in.) diameter in the skin panel between FR50 and FR51 and between STGR42RH and STGR43RH as shown in drawing D53470076008, Sheet 19, Sections A18-A19 and Detail A19-19. 2 Install the doubler at the outer skin as shown in the drawing D53470076008, Sheet 19, Section A18-A19. CAUTION : REMOVE THE EXISTING RIVETS CAREFULLY. THE HEADS OF THE RIVETS WILL BE USED DURING THE DOUBLER INSTALLATION FOR THE EXISTING COUNTERSINKS IN THE SKIN PANEL.

a Remove the existing fasteners in the affected area. b Put this item in position as shown in drawing D53470076008, Sheet 19, Section A18-A19 and Detail A19-19 : 1 doubler D5347646320400 Item 160 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 427 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

c Transfer drill the holes. d Drill the additional holes and open all holes to final dimension as shown in drawing D53470076008, Sheet 19, Detail A19-19.

e Install this item : 1 doubler D5347646320400 Item 160 with : 24 rivet MBBN4477-4810 Item 549

7 pin DAN6-6-6X Item 666 19 pin DAN6-6-7X Item 667 18 pin DAN6-6-8X Item 668

8 pin DAN Item 678 8 collar NSA5330-6 Item 803 23 collar NSA5075-6 Item 806 44 collar DAN11-6X Item 807 18 pin DAN6-6-5 Item 865

5 pin DAN6-6-6 Item 866 3 Install the tube as shown in drawing D53470076008, Sheet 19, Section A18-A19 and in Detail A19-19 :

a Put these items in position : 1 tube D5347669000000 Item 172 2 shim D5347472120200 Item 176

bTransfer drill the holes, drill the additional holes and open all holes to final dimension as shown in drawing D53470076008, Sheet 19, Detail Z19-19.

c Install these items : 1 tube D5347669000000 Item 172 2 shim D5347472120200 Item 176 with : 8 collar NSA5075-6 Item 806 2 pin DAN6-6-6 Item 866 14 pin DAN6-6-10 Item 870 d Drill the holes for the receptacles, Item 504, with 5.6 mm (0.220 in.) diameter as shown in drawing D53470076008, Sheet 19, Detail Z19-19 and install this item : 4 receptacle ABS0337-01A Item 504 with : 8 rivet DIN65399-2400CF Item 724 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 428 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

e Install at the tube, Item 172, as shown in drawing D53470076004, Sheet 9, Section A8-A9 these items : 1 plate D5347669200000 Item 166 1 plug D5347669100000 Item 174 1 ring MS16625-4212 Item 500 1 screw NAS1096-3-10 Item 506 (aq) Modify the routing of the hydraulic tubes between FR46 and FR50. Refer to Kit 281132D65R00 For connection of hydraulic tubes with PERMASWAGE fittings, refer to AMM 20-23-11, Page block 201. Refer to Drawing(s) : D93070516000 Sheet(s) 1 thru 6 1 Remove the attachment parts and the hydraulic tubes between FR46 and FR50 as shown in drawing D93070516000, Sheets 1 thru 6 :

a Remove and retain these items as shown in the table in drawing D93070516000, Sheet 2 : 4 washer NAS1149D016K Item A 4 bolt NAS1096-3-7 Item B 4 clamp NSA16CA06NJ Item C 2 clamp NSA5516-11NJ Item D 4 bolt A102-1/2D Item E 4 washer NAS1149D0332K Item F 2 clamp NSA5516-22NJ Item G 4 bolt NAS6703U16 Item H 4 clamp D93470740204 Item J 4 washer NAS1149C0332R Item K 1 clamp NSA5519-4 Item L 2 screw NAS1100-06-5 Item M 1 clamp NSA5519-6 Item N 1 lead E0089-06-100N Item O 1 lead E0089-16-100 Item P 1 cover D93470756204 Item Q NOTE : Retain the Items A thru Q. b Remove and discard these items : CAUTION : CUT THE TWO EXISTING TUBES AT FR49. THE REMAINING TUBES BETWEEN FR49 AN FR50 MUST BE REUSED AT INSTALLATION. CUT THE TUBES TO FINAL LENGTH DURING INSTALLATION. 1 spacer NSA5527-03-16 Item (005) Discard 1 bolt NAS6703U3 Item (006) Discard 1 nut MS21042-3 Item (007) Discard 1 washer NAS1149D0332K Item (008) Discard 1 clamp NSA5516A11NJ Item (010) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 429 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 clamp NSA5516A22NJ Item (011) Discard 1 union NSA855006-6 Item (015) Discard 1 tee ASNA3752D120812 Item (016) Discard 1 tube D29170911008 Item (020) Discard 1 tube D27070231014 Item (021) Discard 1 tube D29170901004 Item (022) Discard 12 nut NSA5066-3-1 Item (060) Discard

2 nut NAS679C06 Item (065) Discard 1 tie NSA935401-06 Item (086) Discard 1 tie NSA935401-04 Item (087) Discard

c Remove and discard these items as shown in drawing D93070516000, Sheet 3, Detail A1-3 : 1 bracket D93570727202 Item (045) Discard 3 rivet LN9198-3210BF Item (099) Discard and close the holes at FR46 with this item : 3 rivet LN9198-3210CF Item 198 2 Install the brackets at FR46 as shown in drawing D93070516000, Sheet 4, Detail A4-4 :

a Put these items in position : 1 bracket D9357045500000 Item 145 drill the additional holes and install with this item : 2 rivet LN9198-3210BF Item 199 3 Shorten the length of the hydraulic tubes between FR49 and FR50 as shown in drawing D93070516000, Sheet 6. 4 Install the hydraulic tubes between FR46 and FR50 as shown in drawing D93070516000, Sheet 6 :

a Put these items in position : 2 union NSA855006-6 Item 115 1 tee ASNA3752D120812 Item 116 1 tube D2917091100002 Item 120 1 tube D2707023100000 Item 121 1 tube D2917090100400 Item 122 1 union NSA855006D8 Item 130 1 tube D2777000102600 Item 135 NOTE 1 tube D2777001102400 Item 136 NOTE 1 tube D3247091100400 Item 139 NOTE : Shorten the tubes, Item 135 and 136, to the correct length. b Connect the hydraulic tubes, refer to AMM 20-23-11, Page block 201. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 430 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

c Tighten all connections of the hydraulic tubes. dAttach the hydraulic tubes with these items : 1 spacer NSA5586-B Item 150 1 tie NSA935401-05 Item 151 11 nut NSA5066-3-1 Item 160

2 nut NAS679C06M Item 165 1 tie NSA935401-06 Item 186 1 tie NSA935401-04 Item 187 and with these items : 4 washer NAS1149D016K Item A 4 bolt NAS1096-3-7 Item B 4 clamp NSA16CA06NJ Item C 2 clamp NSA5516-11NJ Item D 4 bolt A102-1/2D Item E 4 washer NAS1149D0332K Item F 2 clamp NSA5516-22NJ Item G 4 bolt NAS6703U16 Item H 4 clamp D93470740204 Item J 4 washer NAS1149C0332R Item K 1 clamp NSA5519-4 Item L 2 screw NAS1100-06-5 Item M 1 clamp NSA5519-6 Item N 1 lead E0089-06-100N Item O 1 lead E0089-16-100 Item P 1 cover D93470756204 Item Q NOTE : Items A thru Q are retained parts. 5 Mark all positions of the spacers with polyurethane top coat, RAL9001 (Mat. No. 16-018) as shown in drawing D93070515002, Sheet 12, Detail Z12-12. (ar) Install the brackets for the pressure system and cavity drain system between FR51 and FR53. Refer to Kit 281132D44R00 Refer to Drawing(s) : D28270992002 Sheet(s) 1, 2, 3 and 5 1 Put these items in position as shown in Details B2-2 and F5-5 and Sections C3-C5, D3-D5 : 1 bracket D2827098324800 Item 002 1 bracket D2827098325200 Item 006 2 bracket D2827098329200 Item 008 2 Drill the rivet holes. 3 Install these items : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 431 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 bracket D28270983-248 Item 002 1 bracket D28270983-252 Item 006 2 bracket D2827098329200 Item 008

with : 10 rivet EN6081D5 Item 040 (as) Replace the APU fuel tube in the keel beam area between FR42 and FR47. Refer to Kit 281132D47R00 Refer to Drawing(s) : D28270515000 Sheet(s) 1 thru 4 1 Remove the APU fuel tube in the keel beam area between FR42 and FR47 as shown in drawing D28270515000 ’BEFORE’, Detail C1-2 and Detail Z2-2 :

a Remove and retain this item : 7 clamp NSA5516-10NJ Item A NOTE : Retain the Items A. b Remove and discard this item : 1 tube D28270505006 Item (6) Discard 2 Install the APU fuel tubes in the keel beam area between FR42 and FR47 as shown in drawing D28270515000 ’AFTER’, Detail B3-3, C3-4 and Detail Z4-4 :

a Install these items : 1 tube D2827050501600 Item 002 1 tee NSA855113-11C Item 021 1 tube D2827050502600 Item 044 with : 7 clamp NSA5516-10NJ Item A NOTE : Items A are retained parts. b Connect the APU fuel system with the cavity drain and monitoring system. (at) Install the ACT pressurization system between FR51 and FR53. Refer to Kit 281132D43R00 Refer to Drawing(s) : D28270991002 Sheet(s) 1 thru 3 1 From the tee at FR51 shown in Sheet 3, Detail X1-3 remove : 1 cap MS21914-10D Item (094) Retain DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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NOTE : The cap was installed with Kit 281132D45R00, drawing D28270975006, Item 094. 2 Install these items between FR50 and FR53 as shown in Sheet 3, Detail X1-3 : 1 tube D2827097905200 Item 002

with : 1 elbow MS21908J10 Item 091 1 nut AN924-10J Item 034 1 washer NAS1149C1432R Item 035 3 Install these items as shown in Sheet 3 and Section Z1-3: 1 nut NAS1726C3E Item 070 1 washer NAS1149C0332R Item 073 1 clamp MS21919 WDE10 Item 079 1 clamp NSA5575-8A Item 081 1 bonding lead E0090-10-125NN Item 083 1 bolt NAS1303-2 Item 088 1 nut NAS1726-3E Item 089 1 washer NAS1149D0316H Item 090 1 screw NAS1801-3-9 Item 097 4 Between FR52 and FR53, on tube, Item 002, install as shown in Detail X1-3 : 1 cap MS21914-10D Item (094) Retained (au) Remove and discard the attachment parts of the cable harnesses in the AFT cargo compartment crossbeam area between FR49 and FR55. Refer to Kit 281132D97R01 Refer to Drawing(s) : D92891805008 Sheet(s) 3 thru 7, 9, 13 thru 15 and 53 thru 58 1 Remove and discard the attachment parts of the cable harnesses between FR49 and FR55 as shown in drawings D92891805000 and D92891805008, Sheets 3, 4, 7, 9, 13, 14, 15, 56 and 57.

a Remove discard these parts : 20 screw NAS1096-2-8 Item (504) Discard

1 screw NAS1096-2-12 Item (507) Discard 2 screw NAS1096-2-16 Item (510) Discard 1 screw NAS1096-2-22 Item (514) Discard 1 screw NAS1096-2-27 Item (517) Discard 1 bracket ABS0335-02 Item (563) Discard 18 washer NAS1149CN616R Item (652) Discard

4 washer ASNA0113-40ADL Item (663) Discard 1 nut MS21042-08 Item (702) Discard 2 bracket E0343-01 Item (750) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 bracket NSA935504-01 Item (751) Discard 2 bracket NSA935504-03 Item (753) Discard 1 bracket NSA935513-01 Item (756) Discard 2 bracket NSA935513-05 Item (757) Discard 2 bracket ABS0355-01 Item (762) Discard 3 washer NSA935514-03 Item (764) Discard 5 bracket ABS0774A01A Item (768) Discard 3 spacer NSA5527-03-02 Item (802) Discard 2 spacer NSA5527-03-04 Item (806) Discard 2 spacer NSA5527-03-06 Item (810) Discard 1 strap D9249107100000 Item (1335) Discard (av) Install the brackets at crossbeams at FR 42 and between FR50 and FR54. Refer to Kit 281132D98R02 Refer to Drawing(s) : D92491681010 Sheet(s) 49 thru 52 and D92492244002 Sheet(s) 10 1 Install the items as shown in drawing D92491681010, Sections A50, Details B-B and C-C and Y-Y51, V-V52, W-W52.

a Install these parts : 4 nut NSA5066-08-1 Item 230 2 sheet A9249187820200 Item 565 2 plate A9249199820000 Item 632 6 bracket D9249104920400 Item 737 2 Install the items as shown in drawing D92492244002, Section B and Detail B-B.

a Install these parts : 4 mount E0660-01 Item 266 2 guide D92491047200 Item 724 1 connector D92491073028 Item 824 1 deflector D92491026206 Item 730 1 spacer NSA5527-03-07 Item 312 1 spacer NSA5527-03-04 Item 306 with 7 screw NAS1096-2-12 Item 7 1 screw NAS1096-2-14 Item 9 10 washer ASNA0113-40ADL Item 163

2 washer D92491025200 Item 190 4 nut MS21042-08 Item 202 (aw) Install/modify the cable harness 4605VB, 4607VB. Refer to Kit 281132D99R00 Refer to Drawing(s) :

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 434 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) D92997028030 Sheet(s) 1 thru 4, 9 thru 10 and 24 thru 37 1 Install the cable harness 4605VB Refer to Drawing(s) : D92991405001 Sheet(s) 2 2 Modify the cable harness 4606VB Refer to Drawing(s) : D92997026001 Sheet(s) 1 and 2 3 Modify the cable harness 4607VB Refer to Drawing(s) : D92997026002 Sheet(s) 3 to 7 4 Modify the cable harness 4628VB/1M Refer to Drawing(s) : D92991428014 Sheet(s) 19, H01 to H18 and W01 and W02, X01 and X02 5 Modify the cable harness 4640VB Refer to Drawing(s) : D92997028002 Sheet(s) 1 and 2 and B01 6 Modify the cable harness 4644VB Refer to Drawing(s) : D92997028004 Sheet(s) 3 and 4 and B01 7 Modify the cable harness 4648VB Refer to Drawing(s) : D92997028006 Sheet(s) 5 and 6 and B01 8 Modify the cable harness 4650VB Refer to Drawing(s) : D92991450015 Sheet(s) 11, V01 and V02 9 Install the cable harness 4655VB/6S Refer to Drawing(s) : D92991455007 Sheet(s) 6, H01, H02, W01 and X01 10Install the cable harness 4656VB/6E and 6G Refer to Drawing(s) : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 435 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

D92991456005 Sheet(s) 4, H01, H02, W01 and X01 11Install the cable harness 4661VB/1M Refer to Drawing(s) : D92991461022 Sheet(s) 27, B01 to B04, H01 to H21, W01 and W02, X01 and V01 to V05 12Install the cable harness 4662VB/2M Refer to Drawing(s) : D92991461011 Sheet(s) 11, B01 and B02, H01 to H06, W01, X01 and V01 to V02 13Install the cable harness 4663VB/1S Refer to Drawing(s) : D92991463004 Sheet(s) 10, B01 and B02, H01 to H09, W01 and W02, X01 and V01 to V04 14Install the cable harness 4664VB/2S Refer to Drawing(s) : D92991464003 Sheet(s) 5, B01, H01 to H06, W01, X01 and V01 and V02 15Install the cable harness 4670VB/1M Refer to Drawing(s) : D92991470008 Sheet(s) 9, B01 to B04, H01 to H06, W01, X01 and V01 to V03 16Install the cable harness 4671VB/1M Refer to Drawing(s) : D92991471006 Sheet(s) 8, B01 to B05, H01 to H07, W01 and W02, X01 and V01 to V03 17Install the cable harness 4672VB/2M Refer to Drawing(s) : D92991472015 Sheet(s) 12, B01 and B02, H01 to H03, W01, X01, V01 and V02 18Install the cable harness 4673VB/1S Refer to Drawing(s) : D92991473004 Sheet(s) 3, B01 and B02, H01 to H04, W01, X01, V01 and V02 19Install the cable harness 4675VB/2M Refer to Drawing(s) : D92997028010 Sheet(s) 9 and 10, B01 20Install the cable harness 4680VB/1MB DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Refer to Drawing(s) : D92991480015 Sheet(s) 16, B01 to B03, H01 to H04 and V01 and V02 21Install the cable harness 4681VB/7M Refer to Drawing(s) : D92991481004 Sheet(s) 5, B01, H01, W01, V01 22Cable harness 4683VB/8M

a Install the cable harness 4683VB/8M Refer to Drawing(s) : D92991483008 Sheet(s) 7, B01 and B02, H01 to H09, W01 and W02, X01 and X02, V01 to V04 b Install the air inlet plenum, refer to AMM 21-61-51, Page block 401.

c Install the welding group (Item 127), refer to AMM 21-52-41, Page block 401. 23Install the cable harness 4692VB/2M Refer to Drawing(s) : D92991492006 Sheet(s) 7, B01, H01, W01, X01, V01 24Install the cable harness 4693VB/1S Refer to Drawing(s) : D92991493004 Sheet(s) 3, B01 and B02, H01 to H03, W01, X01, V01 and V02 25Install the cable harness 4694VB/2S Refer to Drawing(s) : D92991494004 Sheet(s) 3, B01 and B02, H01 to H03, W01, X01, V01 and V02 26Install the cable harness 5609VB/1M Refer to Drawing(s) : D92997028032 Sheet(s) 26 to 29, B01 27Install the cable harness 5662VB/2M Refer to Drawing(s) : D92997028033 Sheet(s) 30 and 31, B01 28Install the cable harness 5633VB/5S Refer to Drawing(s) : D92997028034 Sheet(s) 32 and 33, B01 29Install the cable harness 5664VB/4S Refer to Drawing(s) : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 437 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

D92997028035 Sheet(s) 34 to 36, B01 30Install the cable harness 5670VB/1M Refer to Drawing(s) : D92997028036 Sheet(s) 37 and 38, B01 31Install the cable harness 5675VB/2M Refer to Drawing(s) : D92997028037 Sheet(s) 39 and 40, B01 (ax) Install the wires of cable harness 4209VB. Refer to Kit 281132D78R00 Refer to Drawing(s) : D92992299 Sheet(s) 1 thru 40 1 Install : Refer to Drawing(s) : D92992299002 Sheet(s) 2 and 4, B01 2 Install : Refer to Drawing(s) : D92992299004 Sheet(s) 5 and B01 3 Install : Refer to Drawing(s) : D92992299006 Sheet(s) 6 and B01 4 Install : Refer to Drawing(s) : D92992299008 Sheet(s) 7 thru 9 and B01 5 Install : Refer to Drawing(s) : D92992299010 Sheet(s) 10 thru 15 and B01 6 Install : Refer to Drawing(s) : D92992299012 Sheet(s) 16, 17 and B01 7 Install : Refer to Drawing(s) : D92992299014 Sheet(s) 18 thru 21 and B01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 438 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

8 Install : Refer to Drawing(s) : D92992299016 Sheet(s) 22 and B01 9 Install : Refer to Drawing(s) : D92992299018 Sheet(s) 23 thru 28 and B01 10Install : Refer to Drawing(s) : D92992299020 Sheet(s) 29, 30 and B01 11Install : Refer to Drawing(s) : D92992299022 Sheet(s) 31, 32 and B01 12Install : Refer to Drawing(s) : D92992299024 Sheet(s) 33 thru 36 and B01 13Install the wires of cable harness 4227VB Refer to Drawing(s) : D92990627013 Sheet(s) 17 and 19, B01 to B03, H01 to H09, W01 and W02, X01 and X02, V01 to V05 14Install : Refer to Drawing(s) : D92992299026 Sheet(s) 37 and 38 and B01 15Install : Refer to Drawing(s) : D92992299028 Sheet(s) 39 and B01 16Install : Refer to Drawing(s) : D92992299030 Sheet(s) 40 and B01 17Install the wires of cable harness 5220VB Refer to Drawing(s) : D92990820001 Sheet(s) 2, B01, H01, W01, X01 and V01 18Install the wires of cable harness 5224VB DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 439 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s) : D92990824007 Sheet(s) 7, B01, H01, W01 and V01 19Install the wires of cable harness 5233VB Refer to Drawing(s) : D92990833001 Sheet(s) 2, B01, H01, W01 X01 and V01 (ay) Install the attachment parts of the cable harnesses in the AFT cargo compartment crossbeam area between FR49 and FR55. Refer to Kit 281132D97R01 Refer to Drawing(s) : D92891805008 Sheet(s) 3 thru 7, 9, 13 thru 15 and 53 thru 58 1 Install the attachment parts of the cable harnesses in the crossbeam area between FR49 and FR55 as shown in drawing D92891805000 and D92891805008, Sheets 4, 6, 9, 13, 14, 15, 55, 56, 57, 58 and 59.

a Install these parts : 8 screw NAS1801-08-6 Item 004 22 screw NAS1801-08-9 Item 005

4 screw NAS1801-08-12 Item 007 2 screw NAS1801-08-17 Item 010 4 screw NAS1801-08-19 Item 012 2 screw NAS1801-08-23 Item 014 1 screw NAS1801-08-39 Item 020 49 screw NAS1801-3-9 Item 030 48 screw NAS1100-04-5 Item 051 24 screw NAS1102-08-8 Item 058 48 washer NAS1149CN416R Item 150 23 washer NAS1149CN816R Item 152 61 washer NAS1149C0332R Item 153

4 washer ASNA0113-40ADL Item 163 16 washer NSA935808C01 Item 171

2 washer D9249102520000 Item 190 48 nut MS21042-04 Item 200

3 nut MS21042-08 Item 202 8 nut MS21042-3 Item 203 32 nut NAS1291C3M Item 218

1 clip-nut NSA5110-08-1 Item 225 6 clip-nut NSA5066-08-1 Item 230 36 clip-nut NSA5067-08-1 Item 236

5 bracket E0343-01 Item 250 11 bracket NSA935504-01 Item 251

1 bracket NSA935504-02 Item 252 4 bracket NSA935513-01 Item 256 11 bracket NSA935513-05 Item 257

1 bracket NSA935513-07 Item 259 6 bracket ABS0355-01 Item 262 10 bracket ABS0355-02 Item 263 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 440 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

10 washer NSA935514-03 Item 264

1 bracket E0660-01 Item 266 20 support ABS0731A01 Item 267

9 bracket ABS0774A01A Item 268 2 spacer NSA5527-03-03 Item 304 4 spacer NSA5527-03-04 Item 306 1 spacer NSA5527-03-06 Item 310 4 spacer NSA5527-03-08 Item 314 1 spacer NSA5527-03-11 Item 320 1 clamp MS21919WCH6 Item 352 12 clamp NSA935807-09 Item 377

4 clamp NSA935807-16 Item 381 4 sheet D9249104800000 Item 727 2 sheet D9249104800400 Item 729 1 tube TSTMNR502-0 Item 763 1 bulkhead NSA934710T13 Item 773 30 bobbin NSA935510-02 Item 777 100 tie NSA935401-03 Item 793 200 tie NSA935401-04 Item 794 100 tie NSA935401-05 Item 795 1 strap D9249107100600 Item 834 2 strap D9249107103000 Item 846 4 cover EN2997KE3C12 Item 930 2 cover EN2997KE3C16 Item 932 4 dummy receptacle EN2997KE512 Item 933 2 dummy receptacle EN2997KE516 Item 935 2 sleeve EN6049-006-08-5 Item 1032 2 sleeve EN6449-006-13-5 Item 1033 2 sleeve EN6049-006-19-5 Item 1034 6 cover D2557016200200 Item 1099 3 bracket D9249104900600 Item 1110 1 bracket D9249104901800 Item 1137 If there is no hole in the centerline AD of the crossbeam of FR54 drill the hole : Refer to Drawing(s) : D92491681000 Sheet(s) 52 view V-V52. NOTE : This drawing is provided with Kit D98. b Install the placard as shown in drawing D92891805008 Sheet(s) 59 1 placard D92891805202 Item 0002 (az) Attach the placards printed with the modification and the SB-number to the cable harnesses. Refer to Kit 281132D78R00 Refer to Kit 281132D99R00 Refer to Drawing(s) : D92894713026 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 441 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

360 placard E0248A2-4H9R Item 000 720 tie NSA935401-03 Item 080 (ba) Install the AFT cargo compartment floor panels between FR47 and FR59. Refer to Kit 281132D37R00 Refer to Drawing(s) : D53675510010 Sheet(s) 16 thru 18 1 Install the AFT cargo compartment floor panels between FR47 and FR59 as shown in Sections A17-17 : Refer to Drawing(s) : D53675510010 Sheet(s) 17 and 18 2 Install : Refer to AMM 53-42-14, Page block 401 and refer to drawing D53675510010, Sheets 17 and 18.

a Install these items as shown in Detail A17-17 : 1 panel D5367520801400 Item 028 1 panel D5367520801800 Item 030 1 panel D5367520805000 Item 032 1 panel D5367520802600 Item 038 1 panel D5367521101600 Item 040 1 panel D5367521101800 Item 042 1 panel D5367521105200 Item 044 1 panel D5367521105400 Item 046 1 panel D5367521105600 Item 048 1 doorsill D5367205900200 Item 050 1 shim D5367284220000 Item 110 1 shim D5367484220100 Item 111 2 shim D5367489520000 Item 112 2 shim D5367489520100 Item 113 1 shim D5367489420000 Item 114 1 shim D5367489420200 Item 116 with : 33 screw ABS0376-3-30 Item 402 130 screw ABS0376-3-40 Item 404

23 screw NAS1102-3-8 Item 408 85 nut EN6131C3C4 Item 411 11 washer NAS1149C0332R Item 420 11 nut MS21042L3 Item 430 (bb) Install the AFT cargo compartment floor panels between FR47 and FR59. Refer toKit 281132D38R00 Refer to Drawing(s) : D53675520008 Sheet(s) 13 thru 15 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 442 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Install : Refer to AMM 53-42-14, Page block 401 and refer to drawing D53675520008, Sheets 14 and 15.

a Install these items as shown in Details A14-14 and B14-14 and Sheet 15: 1 panel D5367406200000 Item 028 1 panel D5367406200100 Item 029 1 panel D5367405500000 Item 030 1 panel D5367405300000 Item 032 1 panel D5367405400000 Item 034 1 panel D5367405200000 Item 038 1 panel D5367405600000 Item 040 1 panel D5367416000200 Item 084 1 panel D5367416000300 Item 085 with : 221 screw ABS0376-3-30 Item 402 1 tape ABS5006-4D Item 408 92 nut EN6131C3C4 Item 411

6 screw ABS0376-3-35 Item 412 (bc) Install the seal section in the gaps between the AFT cargo compartment floor panels between FR47 and FR59. Refer toKit 281132D39R00 Refer to Drawing(s) : D53675525002 Sheet(s) 4 thru 6 1 Install these items as shown in drawing D53675525000, Sheet 4 thru 6 : 1 section ABS0399A Item 003 1 section ABS0398A01 Item 004 1 section ABS0305LC Item 005 1 section ABS0305LB Item 006 2 Install this item in the gaps as in drawing D53675525000, Sheet 4 thru 6 : 1 cord DAN107-1 Item 001

and seal all gaps with sealant (Mat. No. 09-016) as shown in drawing D53675525000, Sheet 4 thru 6. (bd) Install the AFT cargo compartment ceiling panels between FR47 and FR59. Refer toKit 281132D55R00 Refer to AMM 25-55-11, Page block 401. Refer to Drawing(s) : D25570049008 Sheet(s) 5 1 Install these items as shown in drawing D25570049000, Sheet 1 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 443 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 panel D2557131000200 Item 050 1 panel D2557131400600 Item 052 1 panel D2557131600800 Item 054 1 panel D2557134200000 Item 056 1 panel D2557122000000 Item 058 3 abrasion prot. D2558503820200 Item 010 1 bumper D2557165620000 Item 012 1 bumper D2557165720000 Item 014 9 screw NAS1102-3-10 Item 070 14 screw NAS1100-3-18 Item 071

6 washer ABS0208-01 Item 072 14 washer NAS1149D0332K Item 073

6 screw NAS1102-08-12 Item 074 1 tape ABS5006-6J Item 080 2 Install the AFT cargo compartment ceiling panel 151DC, refer to AMM 25-55-11, Page block 401. 3 Install these items as shown in drawing D25570049008, Sheet 5 : 2 rail D2557043000000 Item C 1 rail D2557043000200 Item D (be) Install the passenger compartment floor panels 241JF, 251AF 251BF, 251FF, 251GF and 252BF. Refer toKit 281132D64R00 Refer to Drawing(s) : D53675015004 Sheet(s) 7 thru 9 1 Install these items : 1 panel D5367161701800 Item 016 2 panel D5367160001600 Item 030 1 panel D5367160100800 Item 032 2 panel D5367162300800 Item 034 1 panel D5367162400800 Item 036

with : 26 screw ABS0376-3-23 Item 398 96 screw ABS0376-3-25 Item 400 122 clip nut EN6131-3C1 Item 505 (bf) Install the insulation blankets at FR46. Refer toKit 281132D11R00 Refer to AMM 25-80-00, Page block 201 Refer to Drawing(s) : D25870003056 Sheet(s) 20 1 Install these items : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 444 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 blanket D2587085002200 Item 000 1 blanket D2587085105600 Item 001 1 blanket D2587085205200 Item 002 1 blanket D2587085305600 Item 003 1 blanket D2587085405200 Item 004 1 blanket D2587085505400 Item 005 1 blanket D2587085602200 Item 006 1 blanket D2587085705200 Item 007 1 blanket D2587085805200 Item 008 1 blanket D2587085905200 Item 009 1 blanket D2587086005400 Item 010 1 blanket D2587086105200 Item 011 1 blanket D2587086202200 Item 012 1 blanket D2587086302400 Item 013 1 blanket D2587086502200 Item 014 1 blanket D2587087102200 Item 015 1 blanket D2587087302200 Item 016

with : 80 strip F2587003400000 Item 100 2 Modify and re-identify the insulation blankets after the bracket installation. For re-identification, refer to para. 2.E. Refer to AMM 25-80-00, Page block 201 (bg) Install the LH sidewall panels between FR46 and FR58. Refer toKit 281132D56R00 Refer to AMM 25-55-11, Page block 401 Refer to Drawing(s) : D25570049010 Sheet(s) 6 1 Install these items : 1 panel D2557132600200 Item 060 1 panel D2557132400800 Item 062 1 panel D2557132200800 Item 064 (bh) Install the RH sidewall panels between FR46 and FR52A. Refer toKit 281132D57R00 Refer to AMM 25-55-11, Page block 401 Refer to Drawing(s) : D25570049012 Sheet(s) 7 1 Install these items : 1 panel D2557133000200 Item 066 1 panel D2557133400600 Item 068 (bi) Install the AFT cargo compartment panels 151AW, 151BW and 152BW at FR47. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 445 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer toKit 281132D58R00 Refer to AMM 25-55-11, Page block 401 Refer to Drawing(s) : D25570049014 Sheet(s) 8 1 Install these items :

2 cover D2557017000200 Item 044 1 panel D2557123600400 Item 090 1 panel D2557123600500 Item 091 1 panel D2557123800200 Item 092 (6) Config. 03 AI-F Part 281132A00003 A00 Sheet(s) 01 281132A00003 A00 Sheet(s) 02 281132A00003 A00 Sheet(s) 03 281132A00003 A00 Sheet(s) 04 281132A00003 A00 Sheet(s) 05 (a) Install the doublers on the upper surface panels Refer to Kit 281132A20R00 281132A20001 A00 Sheet(s) 01 281132A20001 A00 Sheet(s) 02 281132A20001 A00 Sheet(s) 03 281132A20002 A00 Sheet(s) 01 NOTE : Remove the finch paint and the paint protection from the extrados panel between Y=+254 and Y=-254 and between FR36 and FR42. Do not use a metallic tool. Do not cause damage to the head of the rivets, ((Refer to SRM 51-71-11 paragraph 3). Stop the removal when you can see the primary protection (green color). Only remove the rivets at the location of the doubler. 1 Drill one hole to a diameter of 64 mm (2.519 in.) and one hole to a diameter of 74 mm (2.913 in.) Refer to drawing 281132A20001, Sheets 1 and 2 Use: 1 Loft D5713032000095 2 Install : 281132A20001 A00 Sheet(s) 03 Item 0 1 Doubler D5713304820004 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 446 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 1 1 Doubler D5713031920000

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

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

Item 30 57 Collar NSA5330-6 Item 35 49 Nut ASNA2528-3 Item 40 13 Collar NSA5330-8

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 447 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

3 Install : 281132A20002 A00 Sheet(s) 01 Item 0 1 Bracket Assy D5791332400000

Item 1 1 Bracket Assy D5791332300000

Attach with : Item 10 2 Bolt EN6115V3-5

Item 11 4 Nut ASNA2528-3

Item 12 2 Bolt EN6115V3-7 (b) Install the brackets on the upper surface panels Refer to Kit 281132A20R00 281132A20003 A00 Sheet(s) 01 281132A20003 A00 Sheet(s) 02 281132A20003 A00 Sheet(s) 03 281132A20003 A00 Sheet(s) 04 Item 1 1 Support Assy D5791049500095 Item 2 1 Support Assy D5791049400095 Item 3 1 Fitting D5791048300095 Item 4 1 Fitting D5791048200095 Item 5 1 Fitting D5791042020095 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 448 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 6 1 Fitting D5791042120095 Item 9 1 Fitting D5791043020095 Item 10 1 Fitting D5791049820095 Item 11 1 Fitting D5791050020095 Item 12 1 Support D5791042320095 Item 13 1 Support D5791042220095 Item 21

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

4 Rivet ASNA2050DCJ3215 Item 100

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

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

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

4 Pin-Hi Lok NSA5357-3-10 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 449 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 107

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

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

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

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

22 Collar NSA5330-6 Item 130

18 Collar NSA5330-8 (c) Install the rod on the upper surface panels Refer to Kit 281132A20R00 281132A20004 A00 Sheet(s) 01 Item 0 1 Rod D2821334100300 Item 4 1 Bracket D2821334220000 Attach with : Item 12

4 Bolt NAS6603-4 Item 14

2 Bolt NAS6604-9 Item 20

4 Nut NSA5050-3 Item 22 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 450 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 Nut NSA5050-4 Item 24

4 Washer ASNA2397-10L Item 26

2 Washer ASNA2397-416L (d) Install the bracket on FR42 Refer to Kit 281132A21R01 281132A21001 A00 Sheet(s) 01 NOTE : Remove the finch paint and the paint protection in the center tank. Do not use a metallic tool. Do not cause damage to the head of the 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. Item 12 1 Angle D5791317500002 Attach with : Item 51

2 Bolt EN6115V3-6 Item 52

2 Nut ASNA2536-3 (e) Install the bracket above FR42 Refer to Kit 281132A21R01 281132A21002 A00 Sheet(s) 01 281132A21002 A00 Sheet(s) 02 281132A21002 A00 Sheet(s) 03 Item 0 1 Support D5791041820095 Attach with : Item 10 Fuel Tank Sealant Polysulfid (Mat. No. 09-002) Item 60 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 451 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 Bolt EN6115V4X-11 Item 65

2 Bolt EN6115V5X-13 Item 75

2 Nut ASNA2536-4 Item 80

2 Nut ASNA2536-5 (f) Install the brackets on the lower surface panels Refer to Kit 281132A21R01 and Kit 281132A27R00 281132A21003 A00 Sheet(s) 01 281132A21003 A00 Sheet(s) 03 281132A21003 A00 Sheet(s) 04 Item 1 1 Machined Bracket D5791040320095 Item 2 1 Support Assy D5791040500095 Item 3 1 Support Assy D5791040400095 Item 4 1 Machined Bracket D5791040120095 Item 5 1 Machined Bracket D5791040020095 Item 6 1 Machined Bracket D5791040220095 Item 7 1 Machined Bracket D5791040820095 Item 8 1 Machined Bracket D5791040920095 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 452 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 9 1 Machined Bracket D5791040620095 Item 10 1 Machined Bracket D5791040720095 Item 11 1 Machined Bracket D5791041020095 Attach with : Item 20 Fuel Tank Sealant Polysulfid (Mat. No. 09-002) Item 44

4 Bolt NAS6603-4 Item 62

4 Nut NSA5050-3 Item 157

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

5 Pin-Hi Lok NSA5357-4-10 Item 159

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

31 Collar NSA5330-8 Item 170 1 Collar NSA5330-10 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 453 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(g) Install the rod and the plate on the lower surface panels Refer to Kit 281132A21R01 281132A21004 A00 Sheet(s) 01 281132A21004 A00 Sheet(s) 02 Item 2 1 Rod D2821334100400 Item 6 1 Bracket D2821040220000 Item 8 1 Plate D2821040120000 Attach with : Item 10

8 Bolt NAS6603-2 Item 12

4 Bolt NAS6603-4 Item 14

2 Bolt NAS6604-9 Item 20

4 Nut NSA5050-3 Item 22

2 Nut NSA5050-4 Item 24

12 Washer ASNA2397-10L Item 26

2 Washer ASNA2397-416L (h) Install the Additional Center Tank (ACT) door Refer to Kit 281132A23R00 281132A23001 A00 Sheet(s) 01 281132A23002 A00 Sheet(s) 01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 454 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281132A23002 A00 Sheet(s) 02 1 Remove : 281132A23001 A00 Sheet(s) 01 1 Door Assy D5713019400200 1 Screw Item (4) Discard 1 Washer Item (8) Discard 15 Washer Item (5) Discard 15 Screw Item (6) Discard 15 Washer Item (7) Discard 2 Install : 281132A23002 A00 Sheet(s) 01 281132A23002 A00 Sheet(s) 02 1 Door Assy D5713323000000

Item 0 1 Fairing D5713334000000

Item 1 1 Intrados Fitting D5713334600000

Item 2 1 Fitting D5713334500000

Item 3 1 Fitting D5713334400000

Attach with : Item 30 Fuel Tank Sealant Polysulfid (Mat. No. 09-002) Item 6 8 Washer A5713052120300

Item 10 3 Bolt NAS6603-2

Item 11 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 455 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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

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

Item 22 6 Bolt NAS6604-3

Item 40 6 Washer ASNA2397D416L (i) Install the equipment on the ACT door Refer to Kit 281132A14R00 and Kit 281132A23R00 281132A23003 A00 Sheet(s) 01 281132A23003 A00 Sheet(s) 02 281132A23003 A00 Sheet(s) 03 281132A23003 A00 Sheet(s) 04 281132A23003 A00 Sheet(s) 05 281132A14001 A00 Sheet(s) 01 1 Install the pressure switch 2QH : 281132A23003 A00 Sheet(s) 02 Item 0 1 Pressure Switch HTE690045

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

Item 10 1 Plug A2823260820000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 456 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 12 1 Safety Valve A2823260500000

Item 18 3 Packing NSA8200-6

Item 20 1 O-Ring NSA8203-019

Item 22 4 Bolt NAS6603-5

Item 24 4 Washer-Sealing ASNA2055-03

Item 26 4 Nut NSA5050-3

Item 28 1 M Wire-Lock MS20995C32 2 Install the fuel pump 1QH and the mounting plate 163QM : 281132A23003 A00 Sheet(s) 03 Item 0 1 Fuel Pump 568-1-27170-002

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

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

Item 12 1 Insert A2821064620000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 457 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 14 1 Spring A2821064720000

Item 18 1 O-Ring NSA8203-113

Item 22 1 O-Ring NSA8203-167

Item 24 1 O-Ring NSA8203-224

Item 26 1 O-Ring NSA8203-226

Item 28 2 Bonding Lead E0088-10-100

Item 29 4 Bolt NAS6603-1

Item 30 6 Bolt NAS6604-7

Item 32 1 Bolt NAS6604-20

Item 34 1 Seal Washer NSA5112-04

Item 36 6 Washer ASNA2397-416

Item 38 1 Washer ASNA2397-416L

Item 39 4 Washer ASNA2397D10L

Item 40 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 458 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Nut NSA5050-4

Item 42 2 Nut NSA5050-3

Item 48Wire-Lock MS20995C32 3 Install the refuel valve 41QU and the canister 164QM : 281132A23003 A00 Sheet(s) 04 Item 0 1 Canister 1158000-15

Item 2 1 Refuel Valve 1158000-21

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

Item 8 4 Screw NAS1154-10

Item 10 1 Screw NAS1801-06-6

Item 11 1 Screw NAS1801-3-6

Item 12 1 Washer ASNA2397-6L

Item 13 1 Washer ASNA2397-10L

Item 14 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 459 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Nut MS21042-06

Item 16 4 Nut NAS1726C4E

Item 22 1 Bonding Lead E0088-16-125 4 Install the actuator 6QH and the valve 165QM : 281132A23003 A00 Sheet(s) 05 Item 0 1 Valve HTE900135

Item 2 1 Actuator HTE190001-2

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

Item 6 1 O-Ring NSA8203-154

Item 8 6 Screw NAS1153-4

Item 13 1 Screw NAS1801-06-6

Item 17 1 Washer ASNA2397-6L

Item 16 4 Nut NAS1726C4E

Item 18 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 460 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Nut MS21042L06

Item 22 1 Lead-Bonding E0088-16-100

Item 24Wire-Lock MS20995C32 5 Identify the equipment on the ACT door 281132A14001 A00 Sheet(s) 01

a Bond the placards : Item 0 1 Placard D2821336920000 Item 2 1 Placard D2821336920200 Item 4 1 Placard D2821336920400 Item 6 1 Placard D2821336920600 Item 8 1 Placard D2821336920800 (j) Replace the Fuel Quantity Indicator (FQI) 6QT (Refer to AMM 28-42-22, Page block 401) 1 Remove : 1 Fuel Quantity Indicator 1407KID02-03 2 Install : 1 Fuel Quantity Indicator 1419KID01-03 (k) Modify the pipes in the center tank Refer to Kit 281132A24R00 281132A24001 A00 Sheet(s) 01 281132A24001 A00 Sheet(s) 02 281132A24001 A00 Sheet(s) 03 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 461 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281132A24002 A00 Sheet(s) 01 281132A24002 A00 Sheet(s) 02 281132A24002 A00 Sheet(s) 03 281132A24002 A00 Sheet(s) 04 1 Remove : 281132A24001 A00 Sheet(s) 01 281132A24001 A00 Sheet(s) 02 281132A24001 A00 Sheet(s) 03 Item (2) 1 Pipe Assy D2821008001300

with : Item (5) 2 O-ring Discard

Items (4) and (9) 2 Screw Retain

Items (8) and (10) 2 Washer Retain 2 Install : 281132A24002 A00 Sheet(s) 01 281132A24002 A00 Sheet(s) 02 281132A24002 A00 Sheet(s) 03 281132A24002 A00 Sheet(s) 04 Item 6 1 Pipe Assy D2821333900000

Item 120 1 Machined Tee D2821331020000

Item 12 1 Pipe Assy D2821333900100

Item 5 4 O-Ring NSA8203-226 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 462 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Attach with : Item 16 2 Bolt NAS6603-2

Item 18 2 Nut NAS1726-3E

Item 110 4 Bolt NAS6604-5

Item 112 4 Washer ASNA2397-416L

Item 114 4 Nut NAS1726-4E

Items (4) and (9) 2 Screw

Items (8) and (10) 2 Washer

NOTE : Items (4), (9), (8) and (10) were retained at removal. (l) Install the ACT pipes in the center tank Refer to Kit 281132A24R00 281132A24003 A00 Sheet(s) 01 281132A24003 A00 Sheet(s) 02 281132A24003 A00 Sheet(s) 03 281132A24003 A00 Sheet(s) 04 281132A24003 A00 Sheet(s) 05 281132A24003 A00 Sheet(s) 06 281132A24004 A00 Sheet(s) 01 281132A24005 A00 Sheet(s) 01 281132A24006 A00 Sheet(s) 01 281132A24007 A00 Sheet(s) 01 281132A24008 A00 Sheet(s) 01 281132A24009 A00 Sheet(s) 01 281132A24010 A00 Sheet(s) 01 281132A24011 A00 Sheet(s) 01 281132A24011 A00 Sheet(s) 02 281132A24012 A00 Sheet(s) 01 281132A24013 A00 Sheet(s) 01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 463 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Install : 281132A24003 A00 Sheet(s) 01 281132A24003 A00 Sheet(s) 02 281132A24003 A00 Sheet(s) 03 281132A24003 A00 Sheet(s) 04 281132A24003 A00 Sheet(s) 05 281132A24003 A00 Sheet(s) 06 Item 20 1 Pipe Assy D2821333900900

Item 22 1 Pipe Assy D2821333900300

Item 24 1 Pipe Assy D2821333900400

Item 28 1 Pipe Assy D2821333900600

Item 30 1 Pipe Assy D2821333900700

Item 32 1 Pipe Assy D2821333901000

Item 34 1 Sleeve A2821038600000

Item 36 1 Sleeve D2821333800000

Item 38 1 Pipe Assy D2821334800000

Item 40 1 Pipe Assy D2821334900000

Item 42 1 Pipe Assy D2821335000000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 464 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 44 1 Pipe Assy D2821338500000

Item 46 1 Pipe Assy D2821335800000

Item 50 1 Restrictor D2821336720240

Attach with : Item 51 1 Clamp NSA5516A04NF

Item 52 1 Union MS21902D4

Item 53 1 Strip-Bonding ASNA0182-1DA

Item 55 2 Nut ABS0107-150

Item 56 3 Nut ABS0107-200

Item 57 2 Ring-Retaining NSA840003-150

Item 58 3 Ring-Retaining NSA840003-200

Item 60 1 Packing NSA8200-4

Item 62 1 O-Ring NSA8203-215

Item 64 12 O-Ring NSA8203-222 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 465 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 66 5 O-Ring NSA8203-226

Item 68 2 Screw NAS1801-06-10

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

Item 73 4 Bolt NAS6603-5

Item 74 4 Bolt NAS6603-7

Item 76 2 Bolt NAS6604-2

Item 77 4 Bolt NAS6604-3

Item 78 2 Nut MS21042L06

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

Item 83 2 Washer ASNA2397-6L

Item 84 8 Washer ASNA2397-10L

Item 90 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 466 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Bonding Lead E0088-10-160

Item 92 2 Bonding Lead E0088-10-200

Item 93 1 Bonding Lead E0088-10-280 2 Install : 281132A24004 A00 Sheet(s) 01 Item 0 1 Machined Tee D2821331620000

Attach with : Item 10 6 Bolt NAS6604-5

Item 12 6 Washer ASNA2397-416L

Item 14 6 Nut NAS1726-4E 3 Install : 281132A24005 A00 Sheet(s) 01 Item 0 1 Machined Elbow D2821332220000

Attach with : Item 10 2 Bolt NAS6604-4

Item 12 2 Washer ASNA2397-416L

Item 14 2 Nut NAS1726-4E DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 467 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

4 Install : 281132A24006 A00 Sheet(s) 01 Item 0 1 Elbow-Moulded A2821120120000

Attach with : Item 10 2 Bolt NAS6604-4

Item 12 2 Washer ASNA2397-416L

Item 14 2 Nut NAS1726-4E 5 Install : 281132A24007 A00 Sheet(s) 01 Item 0 1 Machined Elbow D2821332620000

Attach with : Item 10 2 Bolt NAS6604-5

Item 12 2 Washer ASNA2397-416L

Item 14 2 Nut NAS1726-4E 6 Install : 281132A24008 A00 Sheet(s) 01 Item 0 1 Elbow Assy D2821332900000

Attach with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 468 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 8 1 O-Ring NSA8203-226

Item 10 4 Bolt NAS6603-4

Item 12 4 Washer ASNA2397D10L 7 Install : 281132A24009 A00 Sheet(s) 01 Item 0 1 Machined Elbow D2821333220000

Item 2 1 Machined Elbow D2821333420000

Item 4 1 Restrictor D2821336621240

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

Item 10 8 Bolt NAS6603-3

Item 12 8 Washer ASNA2397-10L 8 Install : 281132A24010 A00 Sheet(s) 01 Item 0 1 Valve-Non Return 9843144M BFE Part Item 1 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 469 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Flange A2821079520000

Item 2 1 Restrictor D2821335621800

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

Item 4 1 Ring-Retaining NSA840003-200

Item 5 3 O-Ring NSA8203-226

Item 8 4 Bolt NAS6604-12

Item 9 4 Nut NAS1726-4E

Item 11 2 Bonding Lead E0088-10-100

Item 12 2 Nut NAS1726-3E

Item 13 1 Bolt NAS6603-2

Item 14 1 Bolt NAS6603-1

Item 17 1 Bonding Lead E0088-10-200

Item 19 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 470 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 Washer ASNA2397-10L 9 Install : 281132A24011 A00 Sheet(s) 01 281132A24011 A00 Sheet(s) 02 Item 54 1 Valve 365A02

Item 35 1 Sleeve Assy D2821336300000

Attach with : Item 55 2 Nut ABS0107-150

Item 57 2 Ring-Retaining NSA840003-150

Item 61 1 Packing NSA8200-5

Item 64 2 O-Ring NSA8203-222

Item 70 2 Bolt NAS6603-2

Item 80 2 Nut NSA5050-3 10Install : 281132A24012 A00 Sheet(s) 01 Item 0 1 Tee D2821331320000

Attach with : Item 10 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 471 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

4 Bolt NAS6604-5

Item 12 4 Washer ASNA2397-416L

Item 14 4 Nut NAS1726-4E 11Install : 281132A24013 A00 Sheet(s) 01 Item 0 1 Machined Elbow D2821331920000

Item 2 1 Sleeve D2821336500000

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

Item 10 4 Bolt NAS6603-7

Item 12 4 Washer ASNA2397-416L (m) Install the transfer elbow Refer to Kit 281132A05R00 281132A05001 A00 Sheet(s) 01 Item 0 1 Transfert Elbow Assy D2821330700000 Item 2 1 Nutplate Assy D2821334700000 Item 4 1 Nutplate Assy D2821337500000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 472 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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

6 Bolt NAS6604-9 Item 12

6 Washer ASNA2397-416L Item 14 1 Bolt NAS6603-2 Item 16 1 Washer ASNA2397-10L (n) Install the air ventilation elbow Refer to Kit 281132A05R00 281132A05002 A00 Sheet(s) 01 Item 0 1 Elbow Assy D2821337700041 Item 2 1 Nutplate Assy D2821334600000 Item 4 1 Nutplate Assy D2821337600000 Item 14 1 Filter D2821337800000 Item 16 1 Plate D2821337120000 Item 8 1 O-Ring NSA8203-152 Attach with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 473 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Item 10

6 Bolt NAS6604-8 Item 12

6 Washer ASNA2397-416L Item 18

4 Bolt NAS6603-2 Item 20

2 Bolt NAS6603-5 Item 22

5 Washer ASNA2397JD10L Item 24

2 Nut NSA5050-3 Item 26 1 Washer ASNA2397-10L (o) Apply the sealing protection to the center tank Refer to Kit 281132A05R00 281132A05003 A00 Sheet(s) 01 281132A05003 A00 Sheet(s) 02 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 (Polyurethane) (Mat. No. 16-001) - Fuel Tank Coating (Mat. No. 16-015). (p) Modify the equipment in the HYD/Fuel Panel 40VU Refer to Kit 281132A07R00 and Kit 281132A15R01 281132A15001 A00 Sheet(s) 01 281132A15002 A00 Sheet(s) 01 281132A15002 A00 Sheet(s) 02 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 474 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Remove : 281132A15001 A00 Sheet(s) 01 281132A15002 A00 Sheet(s) 01 FIN 14LF 1 Plate-Integrally Lighted 002098-05

Item (0) 1 Plate-Front D9251092000000

Item (14) 4 Screw

Item (15) 1 Screw

Item (21) 1 Nut

Item (24) 1 Washer

Item (16) 2 Screw

Item (17) 5 Screw

Item (18) 26 Screw 2 Install : 281132A15001 A00 Sheet(s) 01 281132A15002 A00 Sheet(s) 02 FIN 24QH 1 Switch-Pushbutton ABS0951C3LM078

with : 1 Sleeve E0416-02 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 475 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Connector E0417C01S

Item 0 1 Plate D9251314900000

FIN 14LF 1 Plate-Integrally Lighted D33110194A00

Item 4 1 Placard D1131043320100

Item 6 1 Placard D1131043320200

Item 14 4 Screw NAS1102-06-7

Item 15 1 Screw NAS1102-08-7

Item 21 1 Nut MS21042-08

Item 24 1 Washer ASNA2397-8L

Item 16 2 Screw NAS1102-06-5

Item 17 5 Screw ASNA2083BG2-10

Item 18 28 Screw NAS1102-04-5 NOTE : On the new front plate, near the new equipment and the items that you installed again, bond the placards, supplied in : Placard Set D9100095114296 NOTE : Safety the screws with Sealant High Temperature (Mat. No. 08-007B) or Sealant High Temperature (Mat. No. 08-573). DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 476 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

NOTE : For the modification of the wiring, refer to ACCOMPLISHMENT INSTRUCTIONS paragraph B.(6) (w). (q) Modify the equipment and the wiring in the Rear C/B Panel 121VU Refer to Kit 281132A26R00 and Kit 281132A15R01 281132A15003 A00 Sheet(s) 01 281132A15501 A00 Sheet(s) 01 281132A15501 A00 Sheet(s) 02 281132A15502 A00 Sheet(s) 01 281132A15502 A00 Sheet(s) 02 281132A15503 A00 Sheet(s) 01 281132A15503 A00 Sheet(s) 02 281132A15504 A00 Sheet(s) 01 281132A15504 A00 Sheet(s) 02 281132A15505 A00 Sheet(s) 01 281132A15505 A00 Sheet(s) 02 281132A15506 A00 Sheet(s) 01 281132A15506 A00 Sheet(s) 02 281132A15507 A00 Sheet(s) 01 281132A15507 A00 Sheet(s) 02 281132A15508 A00 Sheet(s) 01 281132A15508 A00 Sheet(s) 02 281132A15509 A00 Sheet(s) 01 281132A15509 A00 Sheet(s) 02 281132A15510 A00 Sheet(s) 01 281132A15510 A00 Sheet(s) 02 281132A15511 A00 Sheet(s) 01 281132A15511 A00 Sheet(s) 02 1 Remove : 281132A15003 A00 Sheet(s) 01 FIN 33LM 1 Placard D11311357A00

FIN 36LM 1 Placard D11311359A00 2 Install : 281132A15003 A00 Sheet(s) 01 FIN 10QH 1 Circuit Breaker NSA931320-050

in position P28 FIN 9QH DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 477 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Circuit Breaker NSA931320-050

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

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

in position N29 FIN 34QU 1 Circuit Breaker NSA931320-050

in position L28 FIN 33QU 1 Circuit Breaker NSA931320-050

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

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

in position M28 with : 8 Clip-Locking ABS0772A02A

FIN 33LM 1 Placard D00410468A00

FIN 36LM 1 Placard D11311361A00

NOTE : Near the new circuit breakers, bond the placards, supplied in : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 478 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Placard Set D9100095114296 3 Remove the wires : 281132A15501 A00 Sheet(s) 02 281132A15503 A00 Sheet(s) 02 281132A15505 A00 Sheet(s) 02 281132A15508 A00 Sheet(s) 02 281132A15510 A00 Sheet(s) 02 4 Install the wires : 281132A15502 A00 Sheet(s) 02 281132A15504 A00 Sheet(s) 02 281132A15506 A00 Sheet(s) 02 281132A15507 A00 Sheet(s) 02 281132A15509 A00 Sheet(s) 02 281132A15511 A00 Sheet(s) 02 supplied in : Bundle D9000095128395 Then, install : FIN 1114PP 1 Shunt NSA939526-02

between circuit breakers 9QH and 10QH FIN 1115PP 1 Shunt NSA939526-02

between circuit breakers 33QU and 34QU 5Attach the wires with : 150 Tie-Cable NSA935401-03 150 Tie-Cable NSA935401-06 (r) Install the routing of the Relay Box 802VU, between FR4 and FR5, in the avionics compartment Refer to Kit 281132A25R00 281132A25001 A00 Sheet(s) 01 281132A25001 A00 Sheet(s) 02 281132A25002 A00 Sheet(s) 01 281132A25003 A00 Sheet(s) 01 281132A25003 A00 Sheet(s) 02 281132A25004 A00 Sheet(s) 01 281132A25004 A00 Sheet(s) 02 281132A25005 A00 Sheet(s) 01 281132A25005 A00 Sheet(s) 02 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 479 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Remove : 281132A25001 A00 Sheet(s) 01 Item (0) 2 Pin Discard 2 Install : 281132A25001 A00 Sheet(s) 02 Item 1 2 Mount E0661-22

Item 2 2 Stud E0420-04 3 Install : 281132A25002 A00 Sheet(s) 01 Item 1 1 Bracket D9241244120000

Item 4 2 Mount NSA935504-01

Attach with : Item 18 2 Rivet ASNA2051DCJ3215

Item 2 1 Spacer NSA5527-03-01

Item 3 1 Screw NAS1801-3-20

Item 5 1 Nut NAS1726-3E 4 Install : 281132A25003 A00 Sheet(s) 01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 480 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281132A25003 A00 Sheet(s) 02 Item 0 1 Bracket D5391047900001

Attach with : Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016) Item 6 2 Rivet ASNA2050DCJ3215 5 Install : 281132A25004 A00 Sheet(s) 01 281132A25004 A00 Sheet(s) 02 Item 0 1 Mount NSA935504-03

Item 2 2 Mount NSA935504-01

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

Item 6 3 Washer ASNA2397-10L

NOTE : Bond the related placards, supplied in : Placard Set D9100095116795 6 Install : 281132A25005 A00 Sheet(s) 01 281132A25005 A00 Sheet(s) 02 Item 10 5 Screw NAS1801-3-9

Item 11 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 481 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

5 Washer ASNA2397-10L

Item 14 5 Nut NAS1726-3E

FIN 4065VC-A 1 Connector-Plug EN3646A62041BN 1 Backshell E0080-01-20C

FIN 4066VC-A 1 Connector-Plug EN3646A61419BN 1 Backshell E0080-01-14C 10 M Conduit E0432A14 (s) Install the connectors 1975VC and 1982VC between FR33 and FR34 Refer to Kit 281132A25R00 281132A25006 A00 Sheet(s) 01 281132A25006 A00 Sheet(s) 02 FIN 1975VC 1 Connector EN3545E01FXB22A 1 Backshell EN3545-007SCD FIN 1982VC 1 Connector EN3545E03FXB24A 1 Backshell EN3545-007SCD NOTE : Bond the related placards, supplied in : Placard Set D9100095116795 (t) Modify the equipment in the AFT Electronics Rack 80VU Refer to Kit 281132A25R00 1 On the Shelf 85VU

aOn the mounting rail of the terminal block 1853VT, install : 1 Module NSA937901MA2206 in position 28 1 Module NSA937901MA2204 in position 62 2 Module Identification NSA937901E2 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 482 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Module Identification NSA937901E6 1 Module Identification NSA937901E8 (u) Modify the equipment in the Relay Box 103VU Refer to Kit 281132A25R00 281132A25007 A00 Sheet(s) 01 281132A25007 A00 Sheet(s) 02 281132A25007 A00 Sheet(s) 03 1 Install : FIN 50QJ 1 Relay E0245-28A0 1 Base E0250A0S

Item 6 2 Nut MS21042L04

in position A77 FIN 57QJ 1 Relay E0666D28A0 1 Base E0247A0S

Item 1 1 Retainer-Assy E0427-01A

Item 2 1 Screw NAS1100-04-6

Item 4 1 Washer ASNA2397-4L

Item 5 1 Washer ASNA2397-3L

Item 6 3 Nut MS21042L04

in position J09 NOTE : Bond the related placards, supplied in : Placard Set D9100095116795 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 483 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(v) Modify the equipment in the Contactor Box 107VU Refer to Kit 281132A25R00 281132A25008 A00 Sheet(s) 01 281132A25008 A00 Sheet(s) 02 1 Install : FIN 26QH Item 70 1 Relay NSA932843AA01

Item 71 1 Base NSA932844AA

Item 8 3 Screw NAS1100-04-7

Item 4 3 Washer ASNA2397-4L

Item 6 3 Nut MS21042L04

in position B7 FIN 1274VC Item 50 1 Connector EN3545D03MXB22A

FIN 1274VC-A Item 51 1 Connector EN3545D03FXA22A

Item 52 2 Backshell EN3545-007SCD

NOTE : Bond the related placards, supplied in : Placard Set D9100095116795 2 On the mounting rail of terminal block 1176VT, install : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 484 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Module NSA937901MA2008 1 Module Identification NSA937901E0 1 Module Identification NSA937901E1

in position 10 (w) Modify the wiring in the aircraft Refer to Kit 281132A25R00 281132A25501 A00 Sheet(s) 01 281132A25501 A00 Sheet(s) 02 281132A25502 A00 Sheet(s) 01 281132A25502 A00 Sheet(s) 02 281132A25502 A00 Sheet(s) 03 281132A25503 A00 Sheet(s) 01 281132A25503 A00 Sheet(s) 02 281132A25504 A00 Sheet(s) 01 281132A25504 A00 Sheet(s) 02 281132A25504 A00 Sheet(s) 03 281132A25505 A00 Sheet(s) 01 281132A25505 A00 Sheet(s) 02 281132A25505 A00 Sheet(s) 03 281132A25506 A00 Sheet(s) 01 281132A25506 A00 Sheet(s) 02 281132A25506 A00 Sheet(s) 03 281132A25507 A00 Sheet(s) 01 281132A25507 A00 Sheet(s) 02 281132A25508 A00 Sheet(s) 01 281132A25508 A00 Sheet(s) 02 281132A25509 A00 Sheet(s) 01 281132A25509 A00 Sheet(s) 02 281132A25510 A00 Sheet(s) 01 281132A25510 A00 Sheet(s) 02 281132A25510 A00 Sheet(s) 03 281132A25511 A00 Sheet(s) 01 281132A25511 A00 Sheet(s) 02 281132A25512 A00 Sheet(s) 01 281132A25512 A00 Sheet(s) 02 281132A25513 A00 Sheet(s) 01 281132A25513 A00 Sheet(s) 02 281132A25514 A00 Sheet(s) 01 281132A25514 A00 Sheet(s) 02 281132A25515 A00 Sheet(s) 01 281132A25515 A00 Sheet(s) 02 281132A25516 A00 Sheet(s) 01 281132A25516 A00 Sheet(s) 02 281132A25517 A00 Sheet(s) 01 281132A25517 A00 Sheet(s) 02 281132A25518 A00 Sheet(s) 01 281132A25518 A00 Sheet(s) 02 281132A25519 A00 Sheet(s) 01 281132A25519 A00 Sheet(s) 02 281132A25520 A00 Sheet(s) 01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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DESIGN DRAWINGS SHEET(S) 281132A25520 A00 Sheet(s) 02 281132A25521 A00 Sheet(s) 01 281132A25521 A00 Sheet(s) 02 281132A25522 A00 Sheet(s) 01 281132A25522 A00 Sheet(s) 02 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) 1 FLSCU1 Retain 1 FLSCU2 Retain 1 FQIC Retain 1 GAPCU Retain NOTE : You must install these computers again after the modification of the wiring. b Disconnect the bonding braid.

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

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

c Remove the attachment hardware from the Shelf 93VU. NOTE : Retain the hardware. d Remove the Shelf 93VU and install it on bench. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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3 Remove the Shelf 94VU

a From the Shelf 94VU, remove for access the computers 5GA2, 10GG, 10HC and 10WQ : (Refer to AMM 32-31-71, Page block 401) (Refer to AMM 32-42-34, Page block 401) (Refer to AMM 21-43-34, Page block 401) (Refer to AMM 26-17-34, Page block 401) 1 LGCIU2 Retain 1 BSCU Retain 1 HEAT CONT Retain 1 SDCU Retain NOTE : You must install these computers again after the modification of the wiring. b Disconnect the bonding braid.

c Remove the attachment hardware from the Shelf 94VU. NOTE : Retain the hardware. d Remove the Shelf 94VU and install it on bench. 4 Remove the wires : 281132A25508 A00 Sheet(s) 02 281132A25511 A00 Sheet(s) 02 281132A25513 A00 Sheet(s) 02 281132A25516 A00 Sheet(s) 02 281132A25518 A00 Sheet(s) 02 281132A25520 A00 Sheet(s) 02 5 Install the wires : 281132A25501 A00 Sheet(s) 02 281132A25502 A00 Sheet(s) 02 281132A25502 A00 Sheet(s) 03 281132A25503 A00 Sheet(s) 02 281132A25504 A00 Sheet(s) 02 281132A25504 A00 Sheet(s) 03 281132A25505 A00 Sheet(s) 02 281132A25505 A00 Sheet(s) 03 281132A25506 A00 Sheet(s) 02 281132A25506 A00 Sheet(s) 03 281132A25507 A00 Sheet(s) 02 281132A25509 A00 Sheet(s) 02 281132A25510 A00 Sheet(s) 02 281132A25510 A00 Sheet(s) 03 281132A25512 A00 Sheet(s) 02 281132A25514 A00 Sheet(s) 02 281132A25515 A00 Sheet(s) 02 281132A25517 A00 Sheet(s) 02 281132A25519 A00 Sheet(s) 02 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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DESIGN DRAWINGS SHEET(S) 281132A25521 A00 Sheet(s) 02 281132A25522 A00 Sheet(s) 02 supplied in : Bundle D9000095128495 Bundle D9000095128595 Bundle D9000095131295 Bundle D9000095150195 Bundle D9000095400195 6Attach the wires with : 100 Tie-Cable NSA935401-03 200 Tie-Cable NSA935401-04 200 Tie-Cable NSA935401-05 800 Tie-Cable NSA935401-06 1500 Tie-Cable NSA935401-08

7 Install the Shelf 92VU

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

c Attach the Shelf 92VU and connect the bonding braid with the hardware retained at removal. NOTE : Retain the hardware. d On the Shelf 92VU, install the computers 7QJ, 9QJ, 3QT and 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) 1 FLSCU1 1 FLSCU2 1 FQIC 1 GAPCU 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. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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

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

c Attach the Shelf 94VU and connect the bonding braid with the hardware retained at removal. NOTE : Retain the hardware. d On the Shelf 94VU, install the computers 5GA2, 10GG, 10HQ and 10WQ : (Refer to AMM 32-31-71, Page block 401) (Refer to AMM 32-42-34, Page block 401) (Refer to AMM 21-43-34, Page block 401) (Refer to AMM 26-17-34, Page block 401) 1 LGCIU2 1 BSCU 1 HEAT CONT 1 SDCU NOTE : These computers were retained at removal. (x) Modify the equipment in the FWD Electronics Rack 90VU Refer to Kit 281132A11R01 281132A11001 A00 Sheet(s) 01 281132A11002 A00 Sheet(s) 01 281132A11002 B00 Sheet(s) 02 281132A11003 A00 Sheet(s) 01 281132A11003 A00 Sheet(s) 02 1 On the Shelf 92VU

a Remove : (Refer to AMM 28-42-34, Page block 401) 281132A11001 A00 Sheet(s) 01 FIN 3QT 1 Computer-FQI With OBRM SIC5059-11-0207 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Item (3) 1 Plate Assy D9251102000000 Item (4) 2 Screw Discard Item (112) 2 Screw Discard Item (28) 2 Washer Discard Item (16) 4 Nut Discard

bOn the mounting rail of the terminal block 202VT, install : 281132A11002 A00 Sheet(s) 01 1 Module NSA937901MA2011 in position 21 1 Module NSA937901MA2204 in position 22 3 Module Identification NSA937901E2 1 Module Identification NSA937901E1

c Modify the fool proofing on the connector 3QT-A (Refer to ESPM 20-44-22) 281132A11002 B00 Sheet(s) 02 d Install : (Refer to AMM 28-42-34, Page block 401) 281132A11002 A00 Sheet(s) 01 281132A11002 B00 Sheet(s) 02 FIN 2MCU 1 Rack D0003006100000 Item 15 5 Cover NSA939511-03 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Item 5 1 Plate Assy D9251116900000 Attach with : Item 112 3 Screw NAS1801-3-8 Item 4 3 Screw NAS1102-3-10 Item 28 3 Washer ASNA2397-10L Item 16 6 Nut NAS1726-3E FIN 47QJ 1 Level Sensing Control Unit 30042-0000-0501 BFE Part FIN 47QJ-A 1 Connector E0161D01A12X Attach with : Item 0 2 Flange Assy D9251127600000 Item 6 4 Screw NAS1100-06-12 Item 9 4 Screw NAS1100-04-7 Item 14 4 Washer ASNA2397-4L Item 12 2 Washer ASNA2397-6L DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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FIN 3QT 1 FQIC SIC5059-14-20 FIN 624VG 1 Module-Grounding E0425A2001 NOTE : Bond the related placards, supplied in : Placard Set D9100095112895 2 On the Shelf 94VU, install : 281132A11003 A00 Sheet(s) 01 281132A11003 A00 Sheet(s) 02 FIN 56QJ 1 Relay E0666D28A0 1 Base E0247A0S

Item 1 1 Retainer-Assy E0427-01A

Item 2 1 Screw NAS1100-04-6

Item 4 1 Washer ASNA2397-4L

Item 5 1 Washer ASNA2397-3L

Item 6 3 Nut MS21042L04

in position B15 NOTE : Bond the related placards, supplied in : Placard Set D9100095112895 (y) Modify the marking on the belly fairing, between FR47 and FR53 Refer to Kit 281132A18R00 281132A18001 A00 Sheet(s) 01 281132A18001 A00 Sheet(s) 02 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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DESIGN DRAWINGS SHEET(S) 281132A18001 A00 Sheet(s) 03 281132A18001 A00 Sheet(s) 04 1 Between FR47 and FR50, bond the placards : Item 0 2 Placard D1121004620000

Item 1 2 Placard D1121009120000

Item 2 1 Placard D0041109120000 2 Between FR50 and FR53, bond the placards : Item 0 2 Placard D1121004620000

Item 2 1 Placard D0041109120000 (7) Config. 03 AI-GE Part 1 (a) Remove the nets from the AFT cargo compartment. Refer to AMM 25-55-00, Page block 401 Refer to Drawing(s) : D25572624002 Sheet(s) 4 1 Remove these items : 1 net AC40-0217100 Item (000) Discard 1 net AC40-0209500 Item (002) Discard 1 net AC40-0217000 Item W1 1 net AC40-0217500 Item W2 1 net AC40-0209900 Item W3

NOTE : Retain Items W1, W2 and W3. (b) Remove the Tie Down Points (TDPs) from the AFT cargo compartment. Refer to Drawing(s) : D25572624000 Sheet(s) 1 thru 3

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 Remove these items as shown in drawing D25572624000, Sheet 1 Details A thru F : 26 TDP D2557206221800 Item (000) Discard 26 TDP D2557206222000 Item (002) Discard

7 TDP D2557206230000 Item (005) Discard 54 screw NAS1102-3-10 Item (010) Discard 19 screw NAS1102-3-12 Item (011) Discard 73 nut NAS1726-3E Item (013) Discard

1 TDP D2557206226000 Item (017) Discard 1 shim plate D2557214428800 Item (040) Discard 1 shim plate D2557214429000 Item (041) Discard 1 TDP D2557206232400 Item (047) Discard 1 TDP D2557206230200 Item (048) Discard (c) Remove the belly fairing panels 197AB and 198GB. Refer to AMM 53-35-11, Page block 401 Refer to drawings : D53475024000 Sheet(s) 1 1 Remove these items : 1 panel 197AB D5347503000000 Item (100) Discard 1 panel 198GB D5347503000000 Item (102) Discard

NOTE : Retain Items A, B and C. (d) Modify the attachment structure of the belly fairing panels 197AB and 198GB. Refer to Kit 281132D04R00 Refer to Drawing(s) : D53475024000 Sheet(s) 1 thru 6 1 Install the brackets as shown in Detail Z1-3, Sections C3-C4 and D3-D4 :

a Put these items in position : 1 bracket D5347542400000 Item 008 2 angle D5347542720000 Item 010 1 bracket D5347542400200 Item 012

b Drill the holes and open the holes to final dimension.

c Install these items : 1 bracket D5347542400000 Item 008 2 angle D5347542720000 Item 010 1 bracket D5347542400200 Item 012 with : 34 rivet LN9198-4009CF Item 240 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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2 Drill the holes as shown in Details C1-2 and B3-2 :

a Mark the position of the holes at the rib. b Drill the holes with 30.0 mm (1.181 in.) diameter.

c Deburr the holes. 3 Replace nut plates as shown in Section E1-E3 :

a Remove and discard this item : 5 nut NAS1791A3-1 Item (106) Discard

b Install these items : 3 receptacle ABS0368-01 Item 028 2 nut NAS1791A3-1 Item 030 2 shim D5347521320000 Item 032 with : 10 rivet DIN65399-2400BF Item 125 4 Remove the zed-member as shown in Detail Y1-5

a Remove the fasteners and remove : 1 zed-member D5347518920000 Item (104) Discard 5 Install the receptacles as shown in Details Y1-5, A5-5 and Z5-5

a Mark the positions of the holes. b Drill the five 8.0 mm (0.315 in.) holes.

c Put in position : 5 receptacle ABS0368-01 Item 028

dTransfer drill the rivet holes.

e Install the receptacles, Item 28, with : 10 rivet DIN65399-2400BF Item 125 6 Install the bracket and T-section as shown in Y1-5, And Details D5-5, E5-5 and B5-6

a Put in position 1 T-section D5347521520000 Item 006 1 angle D5347521920000 Item 016 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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bTransfer drill the rivet holes.

c Install : 1 T-section D5347521520000 Item 006 1 angle D5347521920000 Item 016 with : 19 rivet LN9198-4009CF Item 240 7 Install receptacles and nut plates as shown in Details Y1-5 and B5-6

a Mark the positions of the six holes on the T-section, Item 006. b Drill the three 8.0 mm (0.315 in.) and three 6.5 mm (0.256 in.) holes.

c Put in position : 3 receptacle ABS0368-01 Item 028 2 nut NAS1791A3-1 Item 030

dTransfer drill the rivet holes.

e Install the receptacles, Item 28, and the nut plates, Item 30, with : 121 rivet DIN65399-2400BF Item 125 8 Install the bracket as shown in Detail A1-1 and Section F1-F1 on the web at FR50.

a Remove the two affected rivets. b Put in position : 1 bracket D5347521120000 Item 014

c Transfer drill the rivet holes. d Install : 1 bracket D5347521120000 Item 014 with : 2 rivet LN9198-4009CF Item 240 (e) Remove and not reuse the pressure reservoirs for the offwing escape slides, LH/RH. Refer to Drawing(s) : D25690000004 Sheet(s) 7 thru 9 1 Remove and not reuse these items as shown in Sections B7-B8 and A7-A9 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 reservoir 60592-101 Item (008) not reuse 1 reservoir 60592-101 Item (009) not reuse 2 screw NAS1096-2-16 Item (010) Discard 10 washer ASNA0113-40ADL Item (012) Discard

2 spacer NSA5527-03-01 Item (014) Discard 2 clamp NAS5516-18NJ Item (018) Discard 8 screw NAS1096-2-10 Item (020) Discard 1 bracket D2567043300000 Item (042) Discard 1 bracket D2567043300100 Item (043) Discard 1 tie NSA935402-51 Item (050) Discard 1 tie NSA935402-51 Item (051) Discard (f) Remove and discard the placards at the AFT cargo compartment lining panels between FR47 and FR48, LH/RH. Refer to Drawing(s) : D25573522000 Sheet(s) 1 1 Remove and discard this item :

2 placard A2557146821600 Item (518) Discard (g) Modify the insulation blankets. Refer to Kit 281132D71R00 Refer to AMM 25-80-00 Refer to Drawing(s) : D25670762000 Sheet(s) 1 thru 7 D25671745000 Sheet(s) 1 thru 7 1 Remove and retain the insulation blankets in the affected areas. Refer to AMM 25-80-00, Page block 201 2 Install the brackets for relocation of the pressure reservoirs of the offwing escape slides, LH/RH. Refer to Drawing(s) : D25670762000 Sheet(s) 1 thru 7

a Put these items in position, drill the holes and install the brackets as shown in Details Y2-3 and Y5-6 : 2 bracket D2567072701200 Item 006 with : 8 rivet LN9198-4008CF Item 100

b Put these items in position, drill the holes and install the brackets as shown in Details X2-3 and W2-3 : 2 bracket D2567072700400 Item 004 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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with : 4 rivet LN9198-4008CF Item 100

c Put these items in position, drill the holes and install the brackets as shown in Details X5-6 and W5-6 : 2 bracket D2567072700500 Item 005 with : 4 rivet LN9198-4008CF Item 100

d Put these items in position, drill the holes and install the brackets as shown in Details V2-3, V5-6, U2-3, U5-6, T2-3, T5-6 : 6 bracket D2567072700200 Item 002 with : 12 rivet LN9198-4008CF Item 100

e Put these items in position, drill the holes and install the brackets as shown in Details S2-3 and S5-6 : 2 bracket D2567072701000 Item 000 with : 8 rivet LN9198-4008CF Item 100

f Put these items in position, drill the holes and install the brackets as shown in Details A4-4, B4-4 and C4-4 : 3 bracket D2567072700800 Item 008 with : 15 rivet LN9198-4008CF Item 100 g Put these items in position, drill the holes and install the brackets as shown in Details A7-7, B7-7 and C7-7 : 3 bracket D2567072700900 Item 009 with : 15 rivet LN9198-4008CF Item 100 3 Modify and re-identify the insulation blankets after the bracket installation. For re-identification, refer to para. 2.E. 4 Install the retained insulation blankets in the affected areas. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Refer to AMM 25-80-00 5 Install the support and the tubes for the pressure reservoir of the offwing escape slide, LH. Refer to Drawing(s) : D25671745000 Sheet(s) 1 thru 7

a Install the support between FR45 and FR47 as shown in Detail Z2-6 : 1 section D2567070600000 Item 010 with : 6 screw NAS1096-3-10 Item 080 6 washer NAS1149D0363K Item 110

b Install the tubes as shown in Details Y2-2, X2-2 and Z2-2 : 1 tube D2567070100000 Item 000 1 tube D2567070100200 Item 002 1 cap NAS817-10 Item 070 1 tube 64079-3 Item 595 1 tube 64079-5 Item 597 with : 2 clamp ABS0396C08JA Item 060 1 clamp NSA5515-12 Item 066 5 clamp NAS5515-8 Item 062 9 screw NAS1096-3-10 Item 080 1 screw NAS1096-2-9 Item 082 1 nut MS21042-08 Item 092 9 washer NAS1149D0363K Item 110 1 washer NAS1149DN832K Item 112

c Install the bonding straps as shown in Detail E2-2 and D2-2 : 2 lead E0088-10-80NN Item 050 with : 2 clamp NSA5519-11 Item 064 2 screw NAS1096-2-9 Item 082 2 screw NAS1096-2-7 Item 084 2 nut MS21042-08 Item 092 6 washer NAS1149DN832K Item 112 6 Install the support and the tubes for the pressure reservoir of the offwing escape slide, RH. D25671745000 Sheet(s) 2 thru 7 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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a Install the support between FR45 and FR47 as shown in Detail Z4-7 : 1 section D2567070600200 Item 012 with : 4 screw NAS1096-3-10 Item 080 2 screw NAS1096-3-12 Item 103 6 washer NAS1149D0363K Item 110

b Install the tubes as shown in Details A4-4 and Z4-4 : 1 tube D2567070100100 Item 001 1 tube D2567070100300 Item 003 1 cap NAS817-10 Item 070 1 tube 64079-1 Item 596 1 tube 64079-5 Item 597 with : 2 clamp ABS0396C08JA Item 060 5 clamp NAS5515-8 Item 062 9 screw NAS1096-3-10 Item 080 9 washer NAS1149D0363K Item 110

c Install the bonding straps as shown in Details E4-4 and D5-5: 2 lead E0088-10-80NN Item 050 with : 2 clamp NSA5519-11 Item 064 2 screw NAS1096-2-9 Item 082 2 screw NAS1096-2-7 Item 084 2 nut MS21042-08 Item 092 6 washer NAS1149DN832K Item 112 (h) Relocate the release cable for the offwing slide, LH. Refer to Kit 281132D50R01 Refer to Drawing(s) : D53370297002 Sheet(s) 1 thru 12 1 Remove the old release cable for the offwing slide LH between FR40 and FR47 : Refer to Drawing(s) : D53370297002 Sheet(s) 1 thru 12

a Remove these items as shown in Detail Y2-2 : 1 nut NAS1726C4P Item (814) Discard 1 nut NAS509-4C Item (816) Discard 1 flange D5337025520000 Item A DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 bolt NSA5031H4-4 Item C 1 bolt NSA5031-4-4 Item D 1 washer NSA1149C0463R Item E NOTE : Remove and retain the Items A, C, D and E. b Remove these items as shown in Section G2-G3 : 2 washer NAS1149C0332R Item (818) Discard 1 pin MS24665-153 Item (822) Discard 1 bolt D5337048420200 Item B NOTE : Remove and retain the Item B.

c Remove and discard these items as shown in Detail A1-2 : 1 cable L32A319-160-001 Item (800) Discard 12 clamp MS21919WCH6 Item (802) Discard

2 tie NSA935401-03 Item (804) Discard 6 bolt NSA5031-3-5 Item (806) Discard 6 bolt NSA5031-3-4 Item (810) Discard 8 nut NAS1726C3P Item (812) Discard 9 washer NAS1149C0332R Item (818) Discard 1 washer NAS1149C0463R Item (820) Discard 2 Install the brackets for the release cable attachment between FR41 and FR46 : Refer to Drawing(s) : D53370297002 Sheet(s) 1 thru 12

a Put the item in position, drill the rivet holes and install this item as shown in Detail A5-5 : 1 angle D5337025920000 Item 012 with : 2 rivet LN9198-3208BF Item 632

b Put the items in position, drill the rivet holes and install these items as shown in Details B5-5 and C5-5 : 2 profile D5337025620200 Item 008 1 profile D5337025620600 Item 010 with : 4 rivet LN9198-3212BF Item 632

c Put the items in position, drill the rivet holes and install these items as shown in Section D4-D5 and Details E5-5 and F5-5 : 2 angle D5337025020000 Item 006 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 bridge D5337645020000 Item 014 with : 8 rivet LN9198-3210BF Item 632

d Put the item in position, drill the rivet holes and install this item as shown in Detail A6-6 : 1 bracket D5337645300200 Item 016 with : 4 rivet LN9198-3208BF Item 632

e Put the item in position, drill the rivet holes and install this item as shown in Section F4-F6 : 1 holder D5337645420000 Item 018 with : 4 rivet LN9198-3208BF Item 632 3 Install the release cable for the offwing slide LH between FR40 and FR46 : Refer to Drawing(s) : D53370297002 Sheet(s) 1 thru 12

a Install this item as shown in Detail C1-7 : 1 control L32A319-160-002 Item 000 with : 10 clamp MS21919WCH6 Item 030

1 hose DAN79-07 Item 032 2 tie NSA935401-03 Item 034 7 bolt NSA5031-3-5 Item 040 3 bolt NSA5031-3-4 Item 042 10 nut NAS1726C3P Item 064 10 washer NAS1149C0332R Item 070 b Install these items and secure with lockwire (Mat. No. 19-010) as shown in Detail Z7-9 : 1 nut NAS1726C4P Item 060 1 nut NAS509-4C Item 062 1 flange D5337025520000 Item A 1 bolt NSA5031H4-4 Item C 1 bolt NSA50314-4 Item D 1 washer NSA1149C0463R Item E DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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NOTE : The Items A, C, D and E are retained parts.

c Install these items as shown in Section J7-J9 : 3 washer NAS1149C0332R Item 070 1 pin MS24665-153 Item 080 1 bolt D5337048420200 Item B NOTE : The Item B is a retained part. dAdjust the release cable so that the dimension "B" is between 9.8 mm (0.386 in.) and 13.2 mm (0.519 in.) as shown in Detail Z10-10.

e Install this item as shown in Details V7-10 and Z10-10 : 1 adapter L32A319-165-002 Item 002

f Install a rigging pin with 5.0 mm (0.197 in.) diameter at the lever as shown in drawing D53370297002, Sheet 10, Detail V7-10. gAdjust the length of the adapter, Item 002, and connect the adapter with the lever with these items as shown in Section B10-B10 : 1 pin MS20392-2C19 Item 036 3 washer NAS1149C0332R Item 070 1 pin MS24665-153 Item 080

h Secure the both rod ends and the adjustment nuts of the release cable with lockwire (Mat. No. 19-010) as shown in Details V7-10 and Z7-9 and Section B10-B10. i Remove the rigging pin from the lever. (i) Relocate the release cable for the offwing slide, RH. Refer to Kit 281132D51R01 Refer to Drawing(s) : D53370297003 Sheet(s) 1 thru 12 1 Remove the old release cable for the offwing slide LH between FR40 and FR47 : Refer to Drawing(s) : D53370297003 Sheet(s) 1 thru 12

a Remove these items as shown in Detail Y2-2 : 1 nut NAS1726C4P Item (814) Discard 1 nut NAS509-4C Item (816) Discard 1 flange D5337025520000 Item A 1 bolt NSA5031H4-4 Item C 1 bolt NSA5031-4-4 Item D 1 washer NSA1149C0463R Item E DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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NOTE : Remove and retain the Items A, C, D and E. b Remove these items as shown in Section G2-G3 : 2 washer NAS1149C0332R Item (818) Discard 1 pin MS24665-153 Item (822) Discard 1 bolt D5337048420200 Item B NOTE : Remove and retain the Item B.

c Remove and discard these items as shown in Detail A1-2 : 1 cable L32A319-160-001 Item (800) Discard 12 clamp MS21919WCH6 Item (802) Discard

2 tie NSA935401-03 Item (804) Discard 6 bolt NSA5031-3-5 Item (806) Discard 6 bolt NSA5031-3-4 Item (810) Discard 8 nut NAS1726C3P Item (812) Discard 9 washer NAS1149C0332R Item (818) Discard 1 washer NAS1149C0463R Item (820) Discard 2 Install the brackets for the release cable attachment between FR41 and FR46 : Refer to Drawing(s) : D53370297002 Sheet(s) 1 thru 12

a Put the item in position, drill the rivet holes and install this item as shown in Detail A5-5 : 1 angle D5337025920000 Item 012 with : 2 rivet LN9198-3208BF Item 632

b Put the items in position, drill the rivet holes and install these items as shown in Details B5-5 and C5-5 : 2 profile D5337025620200 Item 008 1 profile D5337025620600 Item 010 with : 4 rivet LN9198-3212BF Item 632

c Put the items in position, drill the rivet holes and install these items as shown in Section D4-D5 and Details E5-5 and F5-5 : 2 angle D5337025020000 Item 006 1 bridge D5337645020000 Item 014 with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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8 rivet LN9198-3210BF Item 632

d Put the item in position, drill the rivet holes and install this item as shown in Detail A6-6 : 1 bracket D5337645300200 Item 016 with : 4 rivet LN9198-3208BF Item 632

e Put the item in position, drill the rivet holes and install this item as shown in Section F4-F6 : 1 holder D5337645420000 Item 018 with : 4 rivet LN9198-3208BF Item 632 3 Install the release cable for the offwing slide LH between FR40 and FR46 : Refer to Drawing(s) : D53370297002 Sheet(s) 1 thru 12

a Install this item as shown in Detail C1-7 : 1 control L32A319-160-002 Item 000 with : 10 clamp MS21919WCH6 Item 030

1 hose DAN79-07 Item 032 2 tie NSA935401-03 Item 034 7 bolt NSA5031-3-5 Item 040 3 bolt NSA5031-3-4 Item 042 10 nut NAS1726C3P Item 064 10 washer NAS1149C0332R Item 070 b Install these items and secure with lockwire (Mat. No. 19-010) as shown in Detail Z7-9 : 1 nut NAS1726C4P Item 060 1 nut NAS509-4C Item 062 1 flange D5337025520000 Item A 1 bolt NSA5031H4-4 Item C 1 bolt NSA50314-4 Item D 1 washer NSA1149C0463R Item E NOTE : The Items A, C, D and E are retained parts.

c Install these items as shown in Section J7-J9 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 505 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

3 washer NAS1149C0332R Item 070 1 pin MS24665-153 Item 080 1 bolt D5337048420200 Item B NOTE : The Item B is a retained part. dAdjust the release cable so that the dimension "B" is between 9.8 mm (0.386 in.) and 13.2 mm (0.519 in.) as shown in Detail Z10-10.

e Install this item as shown in Details V7-10 and Z10-10 : 1 adapter L32A319-165-002 Item 002

f Install a rigging pin with 5.0 mm (0.197 in.) diameter at the lever as shown in drawing D53370297002, Sheet 10, Detail V7-10. gAdjust the length of the adapter, Item 002, and connect the adapter with the lever with these items as shown in Section B10-B10 : 1 pin MS20392-2C19 Item 036 3 washer NAS1149C0332R Item 070 1 pin MS24665-153 Item 080

h Secure the both rod ends and the adjustment nuts of the release cable with lockwire (Mat. No. 19-010) as shown in Details V7-10 and Z7-9 and Section B10-B10. i Remove the rigging pin from the lever. (j) Install the pressure reservoir of the offwing escape slide LH/RH. Refer to Kit 281132D71R00 Refer to Drawing(s) : D25671746000 Sheet(s) 1 thru 4 1 Install the pressure reservoir of the offwing escape slide, LH between FR45 and FR47. Refer to Drawing(s) : D25671746000 Sheet(s) 1 thru 4

a Install : 1 reservoir 60592-103 Item 594 with : 1 pocket D2567043200000 Item 050 1 clamp ASNA0033-172 Item 060 1 section LN29837A1 Item 070 2 screw NAS1096-3-7 Item 080 2 washer NAS1149D0363K Item 090 1 placard D9239310903000 Item 100 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 pin MS20392-2C15 Item 110 3 washer NAS1149C0332R Item 120 1 cotter pin MS24665-1013 Item 130 1 placard D2567074100600 Item 140 NOTE : Cut the section, Item 070, in two pieces. One part for the left hand side and the other part for the right hand side. 2 Install the pressure reservoir of the offwing escape slide, RH between FR45 and FR47. Refer to Drawing(s) : D25671746000 Sheet(s) 1, 2 and 4

a Install : 1 reservoir 60592-103 Item 0598 with : 1 pocket D2567043200000 Item 050 1 clamp ASNA0033-172 Item 060 1 section LN29837A1 Item 070 2 screw NAS1096-3-7 Item 080 2 washer NAS1149D0363K Item 090 1 placard D9239310903000 Item 100 1 pin MS20392-2C15 Item 110 3 washer NAS1149C0332R Item 120 1 cotter pin MS24665-1013 Item 130 1 placard D2567074100600 Item 140 (k) Install a bracket at the passenger compartment floor structure at FR53. Refer to Kit 281132D12R00 Refer to Drawing(s) : D53472833008 Sheet(s) 4 1 Put the bracket, Item 000, in position as shown in Detail Z4-4. 2Transfer drill the hole and open it to final dimension. 3 Install this item : 1 bracket D5347212320000 Item 000

with : 1 retaining pin D5347212420000 Item 002 4 retaining ring D5347212420200 Item 004 (l) Install the additional angles at the webs of the keel beam structure between FR42 and FR46. Refer to Kit 281132D07R00 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Refer to Drawing(s) : D53370780004 Sheet(s) 2 1 Install angles at webs of keel beam structure as shown in Section A2-A2 and Detail E2-2 ’AFTER MODIFICATION’.

a Put these items in position : 1 angle D5337270100000 Item 030 1 angle D5337270100800 Item 038

bTransfer drill the holes and open the holes to final dimension.

c Install these items : 1 angle D5337270100000 Item 030 1 angle D5337270100800 Item 038 with : 4 bolt ASNA0082-204 Item 264 2 Install the angles at the webs of keel beam structure as shown in Section B2-B2 and Detail Y2-2 ’AFTER MODIFICATION’.

aTransfer drill the holes and open the holes to final dimension. b Put these items in position : 1 angle D5337070100200 Item 032 1 angle D5337270100400 Item 034 1 angle D5337070100600 Item 036 1 angle D5337070101000 Item 040

c Drill the holes and open the holes to final dimension. d Install these items : 1 angle D5337070100200 Item 032 1 angle D5337270100400 Item 034 1 angle D5337070100600 Item 036 1 angle D5337070101000 Item 040 with : 8 bolt ASNA0082-203 Item 263 (m) Replace the fasteners between FR42 and FR44, LH/RH. Refer to Kit 281132D62R00 Refer to Kit 281132D63R00

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Refer to Drawing(s) : D53371237000 Sheet(s) 1 D53371237001 Sheet(s) 1 1 Replace the fasteners between FR42 and FR44, LH. Refer to Kit 281132D62R00 Refer to Drawing(s) : D53371237000 Sheet(s) 1

a Remove the affected fasteners as shown in Detail Z1-1. bOpen the holes to final dimension.

c Install these items : 20 pin DAN7-6-8X Item 001 32 pin DAN7-8-8X Item 002 12 pin DAN7-8-10X Item 003

1 pin DAN8-8-8X Item 004 20 collar DAN12-6X Item 005 45 collar DAN12-8X Item 006 2 Replace the fasteners between FR42 and FR44, RH. Refer to Kit 281132D63R00 Refer to Drawing(s) : D53371237001 Sheet(s) 1

a Remove the affected fasteners as shown in Detail Z1-1. bOpen the holes to final dimension.

c Install these items : 20 pin DAN7-6-8X Item 001 32 pin DAN7-8-8X Item 002 12 pin DAN7-8-10X Item 003

1 pin DAN8-8-8X Item 004 20 collar DAN12-6X Item 005 45 collar DAN12-8X Item 006 (n) Remove and discard the attachment structure of the partition panels 151AW, 151BW and 152BW between FR46 and FR47. Refer to Kit 281132D60R00 Refer to Drawing(s) : D53975018002 Sheet(s) 7 and 8 1 Remove and discard these items as shown in Section B7-B8 : 1 section D5397468100000 Item (201) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 section D5397467400200 Item (202) Discard 1 section D5397467400300 Item (203) Discard 2 section D5397467400300 Item (210) Discard 1 section D5397467900600 Item (224) Discard 1 section D5397467900400 Item (226) Discard 1 section D5397474700000 Item (233) Discard 1 section D5397474900000 Item (234) Discard 1 section D5397467800600 Item (238) Discard 1 section D5397467800700 Item (239) Discard 14 bracket D5397489820000 Item (270) Discard

2 bracket D5397489820200 Item (272) Discard 4 bracket D5397489820400 Item (274) Discard 2 bracket D5397489820600 Item (276) Discard 2 bracket D5397474900000 Item (334) Discard 2 Remove and discard these items as shown in drawing D53975018002, Sheet 8: 1 plate D5397483921200 Item (204) Discard 1 section D5347047400200 Item (230) Discard 1 section D5347047400300 Item (231) Discard 3Close the two existing holes at AD/FR47 with these items as shown in D53975018002, Sheet 8: 2 rivet NAS1097AD4-10 Item 532 (o) Modify the structure. Refer to Kit 281132D61R00 Refer to Drawing(s) : D53371046000 Sheet(s) 1 thru 5 1 Replace the fasteners between FR44 and FR46 between +Y765 to +Y1292 and -Y765 to -Y1292. Refer to Drawing(s) : D53371046000 Sheet(s) 1 thru 5

a Remove the existing rivets, drill the holes to final dimension and install these items as shown in drawing D53371046000, Sheet 1 : 20 pin DAN5-6-6 Item 023

4 pin DAN5-6-7 Item 024 24 collar NSA5076-6 Item 027 196 rivet LN9198-4812CF Item 029 8 rivet LN9198-4814CF Item 030 2 Install the bonding brackets between FR42 and FR43 and between +Y254 and +Y765.

a Put this item in position as shown in drawing D53371046000, Sheet 1, Section K1-K1 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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2 angle A9249175120000 Item 001

b Drill the additional holes, open the holes to final dimension and install this item : 2 angle A9249175120000 Item 001 with : 12 rivet LN9198-3208BF Item 028 3 Drill the hole between FR42 and FR43 for fuel/vent system.

a Drill one hole with 19.1 mm to 19.3 mm (0.752 in. to 0.759 in.) diameter as shown in drawing D53371046000, Sheet 1, Section H1-H1. b Deburr the hole. 4 Install the girder plate at FR42. Refer to Drawing(s) : D53371046000 Sheet(s) 1 thru 5

a Put this item in position as shown in Section B1-B2 : 1 plate D5337312600000 Item 002

b Mark and drill the holes for the bolts.

c Install this item : 1 plate D5337312600000 Item 002 with : 2 strap D5337312420000 Item 004 4 bolt NAS6703U7 Item 005 4 bolt NAS6703U5 Item 006 8 nut NAS1726C3P Item 007 8 washer NAS1149C0332R Item 008 5 Install the girder plate at FR43. Refer to Drawing(s) : D53371046000 Sheet(s) 1 thru 5

a Put this item in position as shown in Section D1-D3 : 1 plate D5337312000000 Item 003

b Mark and drill the holes for the bolts.

c Install this item : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 plate D5337312000000 Item 003 with : 2 strap D5337312420000 Item 004 4 bolt NAS6703U7 Item 005 4 bolt NAS6703U5 Item 006 8 nut NAS1726C3P Item 007 8 washer NAS1149C0332R Item 008 6 Remove the shear plate at FR46 between +Y254 and -Y254. Refer to Drawing(s) : D53371046000 Sheet(s) 1 thru 5

a Remove and discard this item as shown in Section E1-E4 : 1 shear plate D5337105820000 Item (034) Discard 7 Install the girder plate at FR46. Refer to Drawing(s) : D53371046000 Sheet(s) 1 thru 5 D53372362004 Sheet(s) 6

a Put this item in position as shown in drawing D53371046000, Sheet 5, Section F1-F5 : 1 plate D5337107420200 Item 009

bTransfer drill the holes to the plate, Item 009, and open the holes to final dimension.

c Install this item as shown in drawing D53371046000, Sheet 5, Sections F1-F5 and C5-C5 : 1 plate D5337107420200 Item 009 with : 2 pin DAN6-6-4 Item 021 4 pin DAN5-6-4 Item 022 6 collar NSA5075-6 Item 025 8 rivet LN9198-4012CF Item 035 10 pin DAN5-5-7 Item 036

8 pin DAN5-5-6 Item 037 12 collar NSA5075-5 Item 038

6 collar NSA5076-5 Item 039

d Put these items in position as shown in drawing D53371046000, Sheet 5, Sections F1-F5, B5-B5 and Detail A5-5 : 1 wall D5337311520200 Item 010 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 plate D5337311920200 Item 011 2 angle D5337309820000 Item 012 2 stiffener D5337307220100 Item 013 1 stiffener D5337307220000 Item 014 1 profile D5337312120400 Item 015 1 profile D5337312120600 Item 016 1 profile D5337312120700 Item 017 1 profile D5337312120200 Item 018

eTransfer drill the holes, drill the additional holes, open all holes to final dimension and install with these items as shown in drawing D53371046000, Sheet 5, Sections F1-F5, B5-B5 and A5-A5 and Detail A5-5 : 15 rivet LN9198-4009CF Item 031

3 rivet LN9198-4010CF Item 032 10 rivet LN9198-4011CF Item 033 and with these items as shown in drawing D53372362004, Sheet 6, Details C1-6 and A6-6 : 12 bolt ASNA0082A302 Item 435

2 bolt ASNA0082A303 Item 436 4 bolt ASNA0082A304 Item 438 15 bolt ASNA0082A305 Item 440

1 bolt ASNA0082A306 Item 442 12 collar NSA5075-5 Item 804

3 pin DAN7-5-5 Item 955 9 pin DAN7-5-6 Item 956

f Put this item at the wall, Item 010, in position as shown in drawing D53371046000, Sheet 5, Sections F1-F5 : 1 profile D5337313420000 Item 019

g Drill the holes, open the holes to final dimension and install with these items : 3 pin DAN7-5A5 Item 020 3 collar ABS0258-5C Item 026 (p) Replace fasteners at FR48, FR49, FR50 and FR51 between STGR34LH and STGR36LH. Refer to Kit 281132D41R00 Refer to Drawing(s) : D53470095002 Sheet(s) 1 1 Replace the fasteners at FR48 between STGR34LH and STGR36LH as shown in Section A1-A1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining pins, Item 865 and collars, Item 806, will be installed during the installation of the reinforcing straps at FR48. 2 Replace the fasteners at FR49 between STGR34LH and STGR36LH as shown in Section A1-A1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining pins, Item 865 and collars, Item 806, will be installed during the installation of the reinforcing straps at FR49. 3 Replace the fasteners at FR50 between STGR34LH and STGR36LH as shown in Section A1-A1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining pins, Item 865 and collars, Item 806, will be installed during the installation of the reinforcing straps at FR50.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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4 Replace the fasteners at FR51 between STGR34LH and STGR36LH as shown in Section A1-A1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining pins, Item 865 and collars, Item 806, will be installed during the installation of the reinforcing straps at FR51. (q) Replace fasteners at FR52, FR53 and FR54 between STGR34LH and STGR36LH. Refer to Kit 281132D08R00 Refer to Drawing(s) : D53470096002 Sheet(s) 1 1 Replace the fasteners at FR52 between STGR34LH and STGR36LH as shown in Section A1-A1 and Detail A1-1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR52. 2 Replace the fasteners at FR53 between STGR34LH and STGR36LH as shown in Section A1-A1 and Detail A1-1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 515 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR53. 3 Replace the fasteners at FR54 between STGR34LH and STGR36LH as shown in Section A1-A1 and Detail A1-1.

a Remove the existing fasteners in the affected area. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR54. (r) Install Longitudinal profiles at the cargo compartment floor structure between FR53 an FR59. Refer to Kit 281132D09R00 Refer to Drawing(s) : D53474078000 Sheet(s) 1 D53474078002 Sheet(s) 1 1 Put in position as shown in Detail A1-1 and Sections A1-A1, B1-B1 and C1-C1 : 1 profile D5347456000000 Item 000 1 profile D5347456100000 Item 002 3 profile D5347434000800 Item 004 1 profile D5347434000600 Item 006 2 strap D5347448620200 Item 008 2Transfer drill the fastener holes and open to final dimension. 3 Install as shown in Detail A1-1 and Sections A1-A1, B1-B1 and C1-C1 : 1 profile D5347456000000 Item 000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 profile D5347456100000 Item 002 3 profile D5347434000800 Item 004 1 profile D5347434000600 Item 006 2 strap D5347448620200 Item 008

with : 20 bolt NSA5031-3-3 Item 530 20 nut NAS1726C3P Item 532

4 bolt NSA5031-4-5 Item 534 4 nut NAS1726C4P Item 536 12 collar NSA5075-6 Item 806

8 pin DAN5-6-3 Item 963 4 pin DAN5-6-5 Item 965 (s) Measure the level of the AFT cargo compartment floor structure. Refer to Kit 281132D24R01 Refer to Drawing(s) : D25572624008 Sheet(s) 8 thru 16 D25573525000 Sheet(s) 1 thru 4 1 Temporarily install the roller tracks between FR47 and FR54 : NOTE : Attach the roller tracks only at the frames. 1 track D2557224600200 Item 000 1 track D2557224600400 Item 001 1 track D2557224600000 Item 002

with : 56 screw NAS1102-3-7 Item 026 56 screw NAS1102-3-10 Item 027 448 nut NAS1726-3E Item 028

63 screw NAS1102-3-9 Item 032

7 screw NAS1102-3-11 Item 050 35 screw NAS1100-3-9 Item 053

6 screw NAS1100-3-11 Item 054 1 screw NAS1100-3-6 Item 055 1 washer NAS1149C0332R Item 056 170 screw NAS1100-3-7 Item 057 2 Do the leveling of the roller tracks between FR47 and FR54 to get the necessary shim thicknesses, refer to drawing D25573525000 Sheet(s) 1 thru 4. 3 Remove and retain the roller tracks and fastening parts between FR47 and FR54. (t) Install the water drain connection and the cavity drain access cover between FR52 and FR53. Refer to Kit 281132D06R01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Refer to Drawing(s) : D53470076004 Sheet(s) 8 and 10 1 Make a cutout between 63.7 mm (2.508 in.) and 64.3 mm (2.531 in.) diameter in the skin panel between FR52 and FR53 and between STGR42LH and STGR43LH as shown in Details B10-10 and Y10-10. 2 Install the doubler at the outer skin as shown in Section B8-B10 and Detail B10-10 : CAUTION : REMOVE THE EXISTING RIVETS CAREFULLY. THE HEADS OF THE RIVETS WILL BE USED DURING THE DOUBLER INSTALLATION FOR THE EXISTING COUNTERSINKS IN THE SKIN PANEL.

a Remove the existing fasteners in the affected area. b Put this item in position as shown in Section B8-B10 : 1 doubler D5347646321000 Item 162

c Transfer drill the holes. d Drill the additional holes as shown in Detail B10-10 and open all holes to final dimension.

e Install this item : 1 doubler D5347646321000 Item 162 with : 50 rivet MBBN4477-4810 Item 549

8 pin DAN6-6-7Y Item 677 8 collar NSA5330-6 Item 803 156 collar NSA5075-6 Item 806

25 pin DAN6-6-5 Item 865 58 pin DAN6-6-6 Item 866 14 pin DAN6-6-7 Item 867 59 pin DAN6-6-8 Item 868 3 Install the tube as shown in Section B8-B10 and Details B10-10 and Y10-10 :

a Put these items in position : 1 tube D5347669000000 Item 172 2 shim D5347472120400 Item 180 1 shim D5347660220200 Item 182

bTransfer drill the holes, drill the additional holes and open the holes to final dimension as shown in Detail Y10-10. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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c Install these items : 1 tube D5347669000000 Item 172 2 shim D5347472120400 Item 180 1 shim D5347660220200 Item 182 with : 16 collar NSA5075-6 Item 806

2 pin DAN6-6-7 Item 867 14 pin DAN6-6-10 Item 870 d Drill the four holes for the receptacles, Item 504, with 5.6 mm (0.220 in.) diameter as shown in Detail Y10-10 and install this item : 4 receptacle ABS0337-01A Item 504 with : 8 rivet DIN65399-2400CF Item 724

e Install these items at the tube, Item 172, as shown in Section B8-B10 : 1 plate D5347669200000 Item 166 1 plug D5347669100000 Item 174 1 ring MS16625-4212 Item 500 1 screw NAS1096-3-10 Item 506 4 Make a cutout in the skin panel between FR52 and FR53 and between STGR40LH and STGR41LH as shown in Detail B10-10. 5 Install the nuts, Item 510, around the cutout as shown in Detail Z10-10 :

a Remove the six rivets in the stringer and open the holes to 5.6 mm (0.220 in.) diameter. b Drill the four holes with 5.6 mm (0.220 in.) diameter in the skin.

c Install these items : 4 shim D5347470220000 Item 178 10 nut NAS1474A3 Item 510 with : 20 rivet DIN65399-2400CF Item 724 d Install this item as shown in Section B8-B10 : 1 cover D5347470920200 Item 164 with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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10 screw NAS1153E7 Item 502 (u) Install the shims on the floor framework of the AFT cargo compartment between FR47 and FR54. Refer to Kit 281132D22R00 Refer to Drawing(s) : D25572624006 Sheet(s) 7 1 Put these items in position as required as shown in drawing D25572624006, Sheet 7 : NOTE : The quantity of the shims at each position is dependent on the roller track measurement between FR47 and FR54. 36 shim D2557214631800 Item 014 12 shim D2557214632000 Item 015

9 shim D2557214633400 Item 034 6 shim D2557214633600 Item 036 45 shim D2557214635000 Item 050

7 shim D2557214635200 Item 052 3 shim D2557214635800 Item 058 1 shim D2557214636000 Item 060 6 shim D2557214637600 Item 076 2 shim D2557214637800 Item 078 18 shim D2557214638000 Item 080

6 shim D2557214638200 Item 082 3 shim D2557214638400 Item 084 1 shim D2557214638600 Item 086 18 shim D2557214638800 Item 088

3 shim D2557214639000 Item 090 1 shim D2557214639200 Item 092 1 shim D2557214639400 Item 094 9 shim D2557214639600 Item 096 3 shim D2557214639800 Item 098 18 shim D2557214640000 Item 100

4 shim D2557214640200 Item 102 3 TDP D2557214629800 Item 104 3 shim D2557214642000 Item 106 1 shim D2557214642200 Item 108 3 shim D2557214642400 Item 110 1 shim D2557214642600 Item 112 3 shim D2557214642800 Item 114 1 shim D2557214643000 Item 116 3 shim D2557214641200 Item 118 1 shim D2557214641400 Item 120 3 shim D2557214646000 Item 122 1 shim D2557214646200 Item 124 5 shim D2557214643600 Item 126 3 shim D2557214643800 Item 128 1 shim D2557214644400 Item 130 1 shim D2557214644500 Item 132 6 screw NAS1102-3-10 Item 134 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 shim D2557214644600 Item 136 (v) Install the roller tracks between FR47 and FR54 in the AFT cargo compartment. Refer to Kit 281132D20R02 Refer to Kit 281132D24R01 1 Remove the bearing supports and close the holes. Refer to Drawing(s) : D25572624000 Sheet(s) 1

a Remove the two bearing supports as shown in drawing D25572624000, Sheet 1, View Y and View Z : 2 bearing support D2557226520000 Item (57) 4 rivet EN6080AD5-08 Item 060 2 Protect the attachment elements of the roller tracks between FR47 and FR54. Refer to Drawing(s) : D25572624012 Sheet(s) 19 3 Install the track between FR47 and FR54 at the Aircraft Datum (AD). Refer to Drawing(s) : D25572624008 Sheet(s) 8 thru 16

a Put these items in position as shown in drawing D25572624008, Sheet 8, Sheet 9 Detail Z8-9 and Sheet 15, Detail L8-15 and Detail X : 1 track D2557224600200 Item 000 2 shim D2557268030600 Item 069 2 bearing support D2557226520400 Item 070 2 block D2557226120200 Item 071 NOTE : For the alignment connect the bearing supports, Item 070, and the track, Item 000, with rigging pins temporarily. bTransfer drill the holes to the brackets, Item 070.

c Drill the additional holes. d Install these items as shown in View L8-15 : 2 shim D2557268030600 Item 069 2 bearing support D2557226520400 Item 070 with : 8 pin DAN7-5-5 Item 041 4 pin DAN7-5-6 Item 042 12 collar DAN12-5 Item 043

eTransfer drill the holes from the track, Item 000. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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f Install this item with sealant (Mat. No. 09-005) as shown in Detail Z8-9 : 1 track D2557224600200 Item 000 1 bracket D2557268121200 Item 003 1 shim D2557214640800 Item 004 1 shim D2557214640400 Item 005 1 bracket D2557268122800 Item 006 1 doubler D2557268121000 Item 009 1 plate D2557268028600 Item 010 with : 69 screw NAS1102-3-7 Item 026 16 screw NAS1102-3-10 Item 027 162 nut NAS1726-3E Item 028

51 screw NAS1102-3-9 Item 032 12 screw NAS1100-3-9 Item 053

4 screw NAS1100-3-11 Item 054 10 screw NAS1100-3-7 Item 057 NOTE : Dependent on the thickness of the shims it could be necessary to install alternative bolts as shown in the table, refer to drawing D25572624008, Sheet 9. g Remove the rigging pins and connect the bearing supports, Item 070, and the track, Item 000, with these items as shown in drawing D25572624008, Sheet 15, Detail X : 2 bolt NSA5042C05-180 Item 036 2 nut NSA5060-4 Item 037 2 washer NAS1149C0432R Item 038 2 washer NAS1149C0532R Item 039 2 pin MS24665-153 Item 040 4 Install the track between FR47 and FR54 at +Y623. Refer to Drawing(s) : D255722624008 Sheet(s) 8, 11 and 15

a Put these items in position as shown in drawing D25572624008, Sheet 8, Sheet 11, Detail Y9-11 and Sheet 15, Detail L8-15 and Detail X : 1 track D2557224600000 Item 002 2 shim D2557268030600 Item 069 2 bearing support D2557226520400 Item 070 2 block D2557226120200 Item 071 NOTE : For the alignment connect the bearing supports, Item 070, and the track, Item 002, with rigging pins temporarily. bTransfer drill the holes to the bearing supports, Item 070.

c Drill the additional holes. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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d Install these items as shown in View L8-15 : 2 shim D2557268030600 Item 069 2 bearing support D2557226520400 Item 070 with : 8 pin DAN7-5-5 Item 041 4 pin DAN7-5-6 Item 042 12 collar DAN12-5 Item 043

eTransfer drill the holes from the track, Item 002. f Install this item with sealant (Mat. No. 09-005) as shown in Detail -Y8-11 : 1 track D2557224600000 Item 002 1 bracket D2557268121200 Item 003 1 bracket D2557214641000 Item 008 with : 12 screw NAS1102-3-10 Item 027 149 nut NAS1726-3E Item 028

18 screw NAS1102-3-9 Item 032

5 screw NAS1102-3-11 Item 050 20 screw NAS1100-3-9 Item 053

4 screw NAS1100-3-11 Item 054 90 screw NAS1100-3-7 Item 057 NOTE : Dependent on the thickness of the shims it could be necessary to install alternative bolts as shown in the table, refer to drawing D25572624008, Sheet 11. g Remove the rigging pins and connect the bearing supports, Item 070, and the track, Item 002, with these items as shown in drawing D25572624008, Sheet 15, Detail X : 2 bolt NSA5042C05-180 Item 036 2 nut NSA5060-4 Item 037 2 washer NAS1149C0432R Item 038 2 washer NAS1149C0532R Item 039 2 pin MS24665-153 Item 040 5 Install the track between FR47 and FR52A at -Y623. Refer to Drawing(s) : D25572624008 Sheet(s) 10 and 13

a Put these items in position as shown in drawing D25572624008, Sheet 8, Sheet 10, Detail X8-10 and Sheet 15, Detail L8-15 and Detail X : 1 track D2557224600400 Item 001 2 shim D2557268030600 Item 069 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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2 bearing support D2557226520400 Item 070 2 block D2557226120200 Item 071 NOTE : For the alignment connect the bearing supports, Item 070, and the track, Item 001, with rigging pins temporarily. bTransfer drill the holes to the bearing supports, Item 070.

c Drill the additional holes. d Install these items as shown in View L8-15 : 2 shim D2557268030600 Item 069 2 bearing support D2557226520400 Item 070 with : 8 pin DAN7-5-5 Item 041 4 pin DAN7-5-6 Item 042 12 collar DAN12-5 Item 043

eTransfer drill the holes from the track, Item 001. f Install this item with sealant (Mat. No. 09-005) as shown in Detail X8-10 : 1 track D2557224600400 Item 001 with : 10 screw NAS1102-3-10 Item 027 104 nut NAS1726-3E Item 028 6 screw NAS1102-3-9 Item 032 3 screw NAS1102-3-11 Item 050 15 screw NAS1100-3-9 Item 053

1 screw NAS1100-3-6 Item 055 1 washer NAS1149C0332R Item 056 2 screw NAS1100-3-11 Item 054 68 screw NAS1100-3-7 Item 057 NOTE : Dependent on the thickness of the shims it could be necessary to install alternative bolts as shown in the table, refer to drawing D25572631008, Sheet 10. g Remove the rigging pins and connect the bearing supports, Item 070, and the track, Item 001, with these items as shown in drawing D25572624008, Sheet 15, Detail X : 2 bolt NSA5042C05-180 Item 036 2 nut NSA5060-4 Item 037 2 washer NAS1149C0432R Item 038 2 washer NAS1149C0532R Item 039 2 pin MS24665-153 Item 040 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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6 Install the support for the XZ-latch between FR52A and FR53 at -Y623. Refer to Drawing(s) : D25572624008 Sheet(s) 16

a Put these items in position as shown in drawing D25572624008, Sheet 16 : 1 support D2557240102000 Item 080 with : 2 bolt MS21250-04030 Item 086 2 nut NAS1726-4E Item 087 2 washer NAS1149F0432P Item 088

bAdjust the support, Item 80.

c Transfer drill eight holes an open to final diameter of 7.0 mm (0.276 in.). d Drill two holes to a final diameter between 7.900 mm (0.3110 in.) and 7.922 mm (0.3119 in.).

e Before final installation of the support, Item 80, install : 2 screw NAS1102-08-10 Item 091 2 nut NAS1726-05E Item 092 and smooth mounting surface with sealant (Mat. No. 09-013). f Install as shown in drawing D25572624008, Sheet 16 : 1 support D2557240102000 Item 080 with : 2 bolt D2557237320600 Item 013 2 washer NAS1149C0563R Item 014 2 pin MS24665-300 Item 015 2 screw NAS1100-3-12 Item 029 2 screw NAS1100-3-12 Item 046 5 plate D2557268122200 Item 081 NOTE 01 1 plate D2557268122400 Item 082 2 bolt MS21250-04012 Item 083 1 bolt MS21250-04024 Item 084 3 bolt MS21250-04026 Item 085 3 bolt MS21250-04030 Item 086 9 nut NAS1726-4E Item 087 9 washer NAS1149F0432P Item 088 1 bolt MS21250-04028 Item 089 1 nut MS21250-04028 Item 090 1 end stop D2557240021400 Item 094 NOTE 02 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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3 bolt MS21250-06018 Item 095 NOTE 02 3 washer NSA5379-6C Item 096 NOTE 02 1 bolt NAS1304-10 Item 097 NOTE 02 1 washer NAS1149F0432P Item 098 NOTE 02 NOTE(01) QTY as required. See adjustment of the XZ-latch. NOTE(02) Final installation after installation of ACTs. NOTE : For installation of adapter plates and adjustment of the XZ-latch. (w) Install/Adjust the YZ-latches at FR47, FR48 and FR49 and adjust the XZ-latches. Refer to Kit 281132D24R01 Refer to Drawing(s) : D25572624008 Sheet(s) 8 thru 16 1 Remove and retain the XZ-latch pawls at FR50 and FR53 and retain the nine fastening bolts. NOTE : Tag the XZ-latches with their installation position. 2 Put the tool 98D28108641000 in position between FR47 and FR50 as shown in drawing D25572624008, Sheet 12 and 14. 3Temporarily put these items in position at FR47, FR48 and FR49 as shown in drawing D25572624008, Sheet 14, Detail T8-14 and Sections A-A and D8-D14 : 6 YZ-latch D2557238000400 Item 078

with : 36 nut NAS1726-3E Item 028 12 bolt MS21250-03006 Item 048 36 bolt MS21250-03006 Item 049 4Temporarily install the retained XZ-latch pawls with the retained nine fastening bolts at FR50. NOTE : Install the XZ-latch pawls in the tagged installation position. 5 Ensure that the tool 98D28108641000 has full contact with the rollers of the roller tracks. 6Adjust the X-gaps with the adjustment screws at FR47 as shown in drawing D25572624008, Sheet 12 :

aAdjust the X-gaps with the adjustment screws between 0.65 mm (0.026 in.) and 1.65 mm (0.065 in.) at three places. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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b Secure the adjustment screws with lockwire (Mat. No. 19-010). 7Adjust the Z-gaps between the tool 98D28108641000 and the YZ-latches at FR47, FR48 and FR49LH/RH as shown in drawing D25572624008, Sheet 14 :

a Measure the Z-gap at FR47, FR48 and FR49 . b If the gaps are not between 2 mm (0.078 in.) and 4 mm (0.157 in.), install shims under the affected YZ-latches.

c If are the gaps correct, finally install the YZ-latches. 8Adjust the Y-gaps between the tool 98D28108641000 and the YZ-latches at FR47, FR48 and FR49 as shown in drawing D25572624008, Sheet 14 :

a Measure the Y-gap at FR47, FR48 and FR49. b If the gaps are not between 0.5 mm (0.019 in.) and 1.5 mm (0.059 in.), remove the plate at the affected YZ-latches and adjust the Y-gap with the eccentric bolt as shown in drawing D25572624008, Sheet 14. 9Adjust the X-gaps at FR50 as shown in drawing D25572624008, Sheet 13 :

a Move the tool 98D28108641000 in FWD direction until the tool has contact with the three adjustment screws of the XZ-latches at FR47. bTemporarily install the retained XZ-latch pawls at FR50 with the retained fastening parts. NOTE : Install the YZ-latches in the tagged installation position.

c Adjust the X-gaps between the tool 98D28108641000 and the XZ-latches at FR50 to between 1.3 mm (0.051 in.) and 3.3 mm (0.130 in.) at three places. - Install two adapter plates at each of the XZ-latches at FR50 as necessary to reach the required x-gaps. adapter plate D2557268123000 Item 099 adapter plate D2557268123200 Item 100 adapter plate D2557268123400 Item 101 adapter plate D2557268123600 Item 102 adapter plate D2557268123800 Item 103 adapter plate D2557268124000 Item 104 adapter plate D2557268124200 Item 105 adapter plate D2557268124400 Item 106 adapter plate D2557268124600 Item 107 adapter plate D2557268124800 Item 108 adapter plate D2557268125000 Item 109 with : 4 screw NAS1102-3-8 Item 58 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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10Remove and retain the XZ-latches at FR50 and retain the fastening parts. NOTE : Tag the YZ-latches with their installation position. NOTE : The adapter plates must be remain in their installation position . (x) Install/Adjust the YZ-latches at FR50, FR51 and FR52 and adjust the XZ-latches. Refer to Drawing(s) : D25572624008 Sheet(s) 12 thru 14 1 Put the tool 98D28108641000 in position between FR50 and FR53 as shown in drawing D25572624008, Sheet 12 and 14. 2Temporarily put these items in position at FR50, FR51 and FR52 as shown in drawing D25572624008, Sheet 14, Detail T8-14 and Sections A-A and D8-D14 : 6 YZ-latch D2557238000400 Item 078

with : 36 nut NAS1726-3E Item 028 12 bolt MS21250-03006 Item 048 36 bolt MS21250-03006 Item 049 3Temporarily install the retained XZ-latch pawls with the retained nine fastening bolts at FR50. NOTE : Install the YZ-latche pawls in the tagged installation position. 4Temporarily install the retained XZ-latch pawls with the retained ten fastening bolts at FR53. NOTE : Install the YZ-latche pawls in the tagged installation position. 5 Ensure that the tool 98D28108641000 has full contact with the rollers of the roller tracks. 6Adjust the Z-gaps between the tool 98D28108641000 and the YZ-latches at FR50, FR51 and FR52, LH/RH as shown in drawing D25572624008, Sheet 14 :

a Measure the Z-gap at FR50, FR51 and FR52. b If the gaps are not between 2 mm (0.078 in.) and 4 mm (0.157 in.), install shims under the affected YZ-latches.

c If are the gaps correct, finally install the YZ-latches. 7Adjust the Z-gap between the tool 98D28108641000 and the XZ-latch at FR53, RH (door area) as shown in drawing D25572624008, Sheet 13 :

a Measure the Z-gap at the XZ-latch pawl at FR53, RH (door area). DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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b If the gap is not between 0.5 mm (0.20 in.) and 2.5 mm (0.098 in.), install shims under the affected XZ-latch. 8Adjust the Y-gaps between the tool 98D28108641000 and the YZ-latches at FR50, FR51 and FR52 as shown in drawing D25572624008, Sheet 14 :

a Measure the Y-gap at FR50, FR51 and FR52. b If the gaps are not between 0.5 mm (0.019 in.) and 1.5 mm (0.059 in.), remove the plate at the affected YZ-latches and adjust the Y-gap with the eccentric bolt as shown in drawing D25572624008, Sheet 14. 9Adjust the X-gaps at FR53 as shown in drawing D25572624008, Sheet 13 :

a Move the tool 98D28108641000 in FWD direction until the tool has contact with the three XZ-latch pawls at FR50. bAdjust the X-gaps between the tool 98D28108641000 and the XZ-latches at FR53 to between 1.3 mm (0.051 in.) and 3.3 mm (0.130 in.) at three places. - Install two adapter plates at each of the XZ-latches at FR53 at AD and +Y623 and one adaptor plate in the door area -Y623 as necessary to reach the required x-gaps. NOTE : Rework the stopper plate of the X-latch at FR53 at -Y623 for clearance in X-direction, adapter plate D2557268123000 Item 099 adapter plate D2557268123200 Item 100 adapter plate D2557268123400 Item 101 adapter plate D2557268123600 Item 102 adapter plate D2557268123800 Item 103 adapter plate D2557268124000 Item 104 adapter plate D2557268124200 Item 105 adapter plate D2557268124400 Item 106 adapter plate D2557268124600 Item 107 adapter plate D2557268124800 Item 108 adapter plate D2557268125000 Item 109 with : 4 screw NAS1102-3-8 Item 58 10Remove the XZ-latches at FR50 and FR53 and the fastening parts and retain all the parts in the stowage box PN D28108298001 until installation of ACTs. NOTE : Tag the YZ-latches with their installation position. NOTE : The adapter plates must be remain in their installation position. (y) Install the shims on the frames of the AFT cargo compartment at FR47, FR48, FR49, FR50 and FR51. Refer to Kit 281132D22R00 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Refer to Drawing(s) : D25572624006 Sheet(s) 7 1 Put these items with sealant (Mat. No. 09-005) in position as required as shown in drawing D25572624006, Sheet 7, Detail U1-6 : NOTE : The quantity of the shims at each position is dependent on the measurement of gaps between the tool 98D28108641000 and the YZ-latches at FR47, FR48 and FR49. 10 shim D2557214632000 Item 015 10 shim D2557214631800 Item 014 (z) Install the brackets for the fuel drain/vent systems between FR42 and FR43 Refer to Kit 281132D75R00 Refer to Drawing(s) : D93070668000 Sheet(s) 1 thru 8 1 Remove and retain the green hydraulic reservoir, refer to AMM 29-11-41, Page block 401. 2 Install the brackets for the fuel drain/vent systems between FR42 and FR43.

a Put these items in position as shown in Details A7 and A8 : 1 bracket D9357040100200 Item 112 1 bracket D9357040100300 Item 113

b Drill the rivet holes.

c Install these items : 1 bracket D9357040100200 Item 112 1 bracket D9357040100300 Item 113 with : 4 rivet DAN257-3264 Item 125 3 Install the green hydraulic reservoir, refer to AMM 29-11-41, Page block 401. (aa) Install the beam between FR46 and FR47. Refer to Kit 281132D18R00 Refer to Drawing(s) : D28270998002 Sheet(s) 2 1 Remove the existing fasteners in the affected area. 2 Put this item in position as shown in Detail A2-2 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 beam D2827099720000 Item 000

NOTE : Ensure that the reference holes are in line. 3Transfer drill the holes from aircraft structure to the beam and open the holes to final dimension. 4 Install this item : 1 beam D2827099720000 Item 000

with : 8 bolt NSA5031-3-10 Item 770 8 nut NAS1726C3P Item 807 8 washer NAS1149C0332R Item 808 (ab) Install the fuel transfer line between FR41 and FR47. Refer to Kit 281132D13R00 Refer to Drawing(s) : D28270972002 Sheet(s) 7 thru 12 1 Install the fuel transfer line between FR41 and FR43. Refer to Drawing(s) : D28270972002 Sheet(s) 8 and 12

a Install at the inner tube (which is installed at the top of the center tank at FR41) these items as shown in Detail Z8-8 : 1 O-ring NSA8203-222 Item 057 1 nut ABS0107-150 Item 064 1 ring NSA840003-150 Item 065

b Put at the outer tube, Item 002, these items in position as shown in Details Y8-8 and Z8-8 : 1 O-ring NSA8203-152 Item 054 1 O-ring NSA8203-230 Item 059

c Install these items at the inner tube, Item 004, as shown in Details Y8-8 and Z8-8 : 2 washer NAS1149C0332R Item 083 2 nut NAS1291C3M Item 084 2 lead E0088-10-125NN Item 108 2 tubing NSA937210MB0300 Item 110 NOTE : Cut the tubing, Item 110, in three pieces. d Insert this item : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 tube D2827093000200 Item 004 in : 1 tube D2827093100200 Item 002 and put them between FR41 and FR43 with these items temporarily in position : 1 flange D2827093320400 Item 000 1 O-ring NSA8203-154 Item 055

e Push the inner tube, Item 004, over the inner tube (which is installed at the top of the center tank at FR41) and connect the both tubes with the nut, Item 064, as shown in Detail Z8-8. f Connect the strap, Item 108, at the flange with these items as shown in Detail Z8-8 : 1 washer NAS1149C0332R Item 083 1 bolt NAS1303-2 Item 095

g Push the flange, Item 000, and the O-ring, Item 055, in position and install these items as shown in Detail A8-8 : 10 washer NAS1149C0432R Item 082

6 nut NAS1726-4E Item 085 4 bolt NAS1304-4 Item 086 2 bolt NAS1304-3 Item 100

h Install this item and secure with lockwire (Mat. No. 19-018) as shown in Section B8-B8 : 1 spring D2827090220200 Item 074

i Install these items as shown in Detail Z8-8 : 1 clamp NSA5519-25 Item 061 6 washer NAS1149C0332R Item 083 3 nut NAS1291C3M Item 084 3 bolt NAS1303-3 Item 096 1 lead E0089-10-125NN Item 102 1 lead E0089-10-250NN Item 112 2 Install the fuel transfer line between FR43 and FR46. Refer to Drawing(s) : D28270972002 Sheet(s) 6 thru 12

a Insert this item as shown in Detail Y8-8 : 1 tube D2827093000000 Item 010 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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in : 1 tube D2827093100000 Item 008

b Install at the inner tube, Item 010, these items as shown in Detail Y8-8 : 1 O-ring NSA8203-222 Item 057 1 nut ABS0107-150 Item 064 1 ring NSA840003-150 Item 065

c Put at the outer tube, Item 008, this item in position as shown in Details Y8-8 and X8-8 : 2 O-ring NSA8203-230 Item 059

d Push over the outer tube, Item 008, these items temporarily as shown in Detail Y8-8 : 1 sleeve D2827093321400 Item 006 1 O-ring NSA8203-152 Item 054

e Put the tubes, Item 008 and 010, between FR43 and FR46 in position and connect the inner tube, Item 010, at the inner tube, Item 004, with the nut, Item 064, and install these items as shown in Detail Y8-8 and Section D8-D8 : 2 washer NAS1149C0432R Item 082 2 nut NAS1726-4E Item 085 2 bolt NAS1304-9 Item 090

f Connect the strap, Item 108, at the tube, Item 010, with these items as shown in Detail Y8-8 : 1 washer NAS1149C0332R Item 083 1 nut NAS1291C3M Item 084

g Push the sleeve,Item 006, and the O-ring, Item 054, in position and install these items as shown in Section D8-D8 : 2 washer NAS1149C0432R Item 082 4 nut NAS1726-4E Item 085 2 bolt NAS1304-11 Item 092 2 bolt NAS1304-12 Item 093

h Install this item and secure with lockwire (Mat. No. 19-018) as shown in Section C8-C8 : 1 spring D2827090220200 Item 074

i Install these items as shown in Details Y8-8 and C8-C8 : 2 clamp NSA5519-25 Item 061 6 washer NAS1149C0332R Item 083 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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3 nut NAS1291C3M Item 084 3 bolt NAS1303-3 Item 096 1 lead E0089-10-125NN Item 102 1 lead E0089-41-100NN Item 105 3 Install the fuel transfer line between FR46 and FR47. Refer to Drawing(s) : D28270972002 Sheet(s) 6 thru 12

a Install between FR46 and FR47, Y254 and -Y254, this item as shown in Section A10-A10 : 1 bracket D2827094800000 Item 051 with : 4 washer NAS1149C0432R Item 082 4 bolt NAS1304-2 Item 098

b Push over the outer tube, Item 008, this item temporarily as shown in Detail X8-8 : 1 sleeve D2827093322400 Item 016

c Put at the inner tube, Item 010, these items in position as shown in Detail X8-8 : 1 spacer D2827093221200 Item 012 1 O-ring NSA8203-222 Item 057 1 O-ring NSA8203-226 Item 058 1 ring NSA840003-150 Item 065 1 nut ABS0107-200 Item 066 1 ring NSA840003-200 Item 067

d Install these items at the girder plate at FR46 as shown in Details X8-8 and F8-F8 : 1 flange D2827093222200 Item 014 1 tube D2827092700000 Item 018 1 O-ring NSA8203-152 Item 054 1 O-ring NSA8203-234 Item 060 2 washer NAS1149C0432R Item 082 2 nut NAS1726-4E Item 085 2 bolt NAS1304-9 Item 090

e Push the inner pipe of the tube, Item 018, over the spacer, Item 012, and install the nut, Item 066. f Connect the strap of the tube, Item 018, at the inner tube, Item 010, with these items as shown in Detail X8-8: 1 washer NAS1149C0332R Item 083 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 nut NAS1291C3M Item 084

g Push the sleeve,Item 016, at FR46 in position and install these items as shown in Details X8-X8 and F8-F8: 2 washer NAS1149C0432R Item 082 4 nut NAS1726-4E Item 085 2 bolt NAS1304-11 Item 092 2 bolt NAS1304-12 Item 093

h Install this item and secure with lockwire (Mat. No. 19-018) as shown in Section E8-E8 : 1 spring D2827090220200 Item 074

i Install these items as shown in Detail X8-8 and Section E8-E8 : 1 clamp NSA5519-25 Item 061 4 washer NAS1149C0332R Item 083 2 nut NAS1291C3M Item 084 2 bolt NAS1303-3 Item 096 1 lead E0089-10-125NN Item 102

j Install at the tube, Item 018, these items as shown in Detail V8-10 and Section A10-A10 : 1 flange D2827093222600 Item 020 1 O-ring NSA8203-151 Item 053 1 O-ring NSA8203-226 Item 058 with : 2 washer NAS1149C0432R Item 082 1 nut NAS1726-4E Item 085 1 bolt NAS1304-5 Item 087 2 bolt NAS1304-10 Item 091

k Install at the flange, Item 020, these items and secure with lockwire (Mat. No. 19-018) as shown in Detail V8-10: 1 plug AN814-4DL Item 071 1 packing NSA8200-4 Item 072

l Install these items as shown in Detail V8-10 and Section A10-A10 : 1 flange D2827093222800 Item 028 1 O-ring NSA8203-151 Item 053 with : 2 nut NAS1726-4E Item 085 2 bolt NAS1304-8 Item 089 2 bolt NAS1304-10 Item 091 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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(ac) Install the vent line between FR37 and FR47. Refer to Kit 281132D13R00 Refer to Drawing(s) : D28270972002 Sheet(s) 6 thru 12 1 Install the vent line between FR37 and FR42. Refer to Drawing(s) : D28270972002 Sheet(s) 6 thru 12

a Install between FR40 and FR41 this item as shown in Detail W9-11 : 1 bracket D2827093500000 Item 033 with : 4 nut NAS1726-4E Item 085 4 bolt NAS1304-2 Item 098

b Install at the inner tube (which is installed at the top of the center tank between FR37 and FR38) these items as shown in Detail U9-9 : 1 O-ring NSA8203-226 Item 058 1 nut ABS0107-200 Item 066 1 ring NSA840003-200 Item 067

c Put at the outer tube, Item 032, this item in position as shown in Details U9-9 and S9-10 : 2 O-ring NSA8203-234 Item 060

d Install these items at the inner tube, Item 034, as shown in Details U9-9 and S9-10 : 2 washer NAS1149C0332R Item 083 2 nut NAS1291C3M Item 084 1 lead E0088-10-125NN Item 108 1 lead E0088-10-200NN Item 109 1 tubing NSA937210MB0300 Item 110 1 tubing NSA937210MB0300 Item 111 NOTE : Cut the tubing, Item 111, in two pieces.

e Insert this item : 1 tube D2827092800400 Item 034 in : 1 tube D2827092900600 Item 032

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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and put them between FR37 and FR42 with these items temporarily in position : 1 flange D2827093320600 Item 030 1 O-ring NSA8203-156 Item 056

f Push the inner tube, Item 034, over the inner tube (which is installed at the top of the center tank between FR37 and FR38) and connect the both tubes with the nut, Item 066, as shown in Detail U9-9. gAttach the tube, Item 032, at the bracket, Item 033, between FR40 and FR41 with these items as shown in Detail W9-11 : 1 clamp D28270935002 Item 035 1 clamp D28270935004 Item 037 2 washer NAS1149C0332R Item 083 2 bolt NAS1303-3 Item 096

h Connect the strap, Item 108, at the flange with these items as shown in Detail U9-9 : 1 washer NAS1149C0332R Item 083 1 bolt NAS1303-2 Item 095

i Push the flange, Item 030, and the O-ring, Item 056, in position and install these items as shown in Detail A9-9: 10 washer NAS1149C0432R Item 082

6 nut NAS1726-4E Item 085 4 bolt NAS1304-4 Item 086 2 bolt NAS1304-3 Item 100

j Install this item and secure with lockwire (Mat. No. 19-018) as shown in Section B9-B9 : 1 spring D2827090220200 Item 075

k Install these items as shown in Detail U9-9 : 1 clamp NSA5519-30 Item 062 6 washer NAS1149C0332R Item 083 3 nut NAS1291C3M Item 084 3 bolt NAS1303-3 Item 096 1 lead E0089-10-125NN Item 102 1 lead E0089-10-250NN Item 112 2 Install the vent line between FR42 and FR43. Refer to Drawing(s) : D28270972002 Sheet(s) 6 thru 12

a Install at the inner tube, Item 034, these items as shown in Detail S9-10 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 O-ring NSA8203-226 Item 058 1 nut ABS0107-200 Item 066 1 retaining ring NSA840003-200 Item 067

b Push over the outer tube, Item 032, this item temporarily as shown in Detail S9-10 : 1 sleeve D2827093321200 Item 036

c Install at the girder plate at FR42 these items as shown in Detail S9-10 and Section J10-J9 : 1 flange D2827093320800 Item 038 1 flange D2827093221600 Item 040 1 O-ring NSA8203-152 Item 054 1 O-ring NSA8203-234 Item 060 with : 4 washer NAS1149C0432R Item 082 2 nut NAS1726-4E Item 085 1 bolt NAS1304-8 Item 089 1 bolt NAS1304-10 Item 091

d Push the flange, Item 040, over the inner tube, Item 034, and install the nut, Item 066.

eAssemble these items as shown in Detail Q9-11 : 2 spacer A2827090120400 Item 031 1 tube D2827092800000 Item 044 1 tube D2827092900000 Item 046 1 tube D2827092900200 Item 048 1 O-ring NSA8203-152 Item 054 2 lead E0089-41-250NN Item 107 with : 2 washer NAS1149C0432R Item 082 6 nut NAS1726-4E Item 085 5 bolt NAS1304-5 Item 087 1 bolt NAS1304-6 Item 088

f Install at the tube, Item 044, these items as shown in Details S9-10 and T9-9 : 2 O-ring NSA8203-226 Item 058 2 nut ABS0107-200 Item 066 2 ring NSA840003-200 Item 067

g Install at the outer tubes, Items 046 and 048, this item as shown in Details S9-10 and T9-9 : 2 O-ring NSA8203-234 Item 060 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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h Push over the outer tube, Item 046, these items temporarily as shown in Detail S9-10 : 1 sleeve D2827093321000 Item 042 1 O-ring NSA8203-152 Item 054

i Push the inner tube, Item 044, in the flange, Item 040, and connect the nut, Item 066, as shown in Detail S9-10. j Connect the strap, Item 109, at the inner tube, Item 044, with these items as shown in Detail S9-10 : 1 washer NAS1149C0332R Item 083 1 nut NAS1291C3M Item 084

k Push the sleeves, Item 036 and 042, at the girder plate at FR42 in position and install these items as shown in Detail S9-10 and Section F10-F9 : 4 washer NAS1149C0432R Item 082 4 nut NAS1726-4E Item 085 4 bolt NAS1304-14 Item 093

l Install these items and secure with lockwire (Mat. No. 19-018) as shown in Sections C10-C9 and D10-D9 : 2 spring D2827090220200 Item 075

mInstall these items as shown in Details S9-10 and U9-10 and Section E10-E9 : 1 clamp NSA5519-30 Item 062 6 washer NAS1149C0332R Item 083 3 nut NAS1291C3M Item 084 3 bolt NAS1303-3 Item 096 1 lead E0089-10-200NN Item 104 1 lead E0089-41-100NN Item 105 1 lead E0089-41-200NN Item 106

n Install at the inner tube, Item 044, these items as shown in Detail T9-9 : 1 washer NAS1149C0332R Item 083 1 nut NAS1291C3M Item 084 1 lead E0088-10-200NN Item 109 1 tubing NSA937210MB0300 Item 111

o Push over the outer tube, Item 048, this item temporarily as shown in Detail T9-9 : 1 sleeve D2827093321200 Item 036

p Install at the bracket at FR43 these items as shown in Detail T9-9 and Section J9-J9 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 flange D2827093320800 Item 038 1 flange D2827093221600 Item 040 1 O-ring NSA8203-152 Item 054 1 O-ring NSA8203-234 Item 060 with : 4 washer NAS1149C0432R Item 082 2 nut NAS1726-4E Item 085 1 bolt NAS1304-8 Item 089 1 bolt NAS1304-10 Item 091

q Push the flange, Item 040, over the inner tube, Item 044, and install the nut, Item 066. 3 Install the vent line between FR43 and FR46. Refer to Drawing(s) : D28270972002 Sheet(s) 6 thru 12

a Insert this item : 1 tube D2827092800200 Item 052 in : 1 tube D2827092900400 Item 050

b Put at the outer tube, Item 050, this item in position as shown in Details T9-9 and R9-11 : 2 O-ring NSA8203-234 Item 060

c Install at the inner tube, Item 052, these items as shown in Details T9-9 and R9-11 : 2 O-ring NSA8203-226 Item 058 2 nut ABS0107-200 Item 066 2 ring NSA840003-200 Item 067

d Push over the outer tube, Item 050, these items temporarily as shown in Detail T9-9 : 1 sleeve D2827093321000 Item 042 1 ring NSA8203-152 Item 054

e Put the tubes, Item 050 and 052, between FR43 and FR46, in position. f Push the inner tube, Item 052, in the flange, Item 040, at FR43 and install the nut, Item 066, as shown in Detail T9-9. g Connect the strap, Item 109, at the inner tube, Item 052, with these items as shown in Detail T9-9 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 washer NAS1149C0332R Item 083 1 nut NAS1291C3M Item 084

h Push the sleeves, Item 036 and 042, at the girder plate at FR43 in position and install these items as shown in Detail T9-9 and Section F9-F9 : 4 washer NAS1149C0432R Item 082 4 nut NAS1726-4E Item 085 4 bolt NAS1304-14 Item 093

i Install these items and secure with lockwire (Mat. No. 19-018) as shown in Sections C10-C9 and D10-D9 : 2 spring D2827090220200 Item 075

j Install these items as shown in Details T9-9 and U9-10 and Section E9-E9 : 1 clamp NSA5519-30 Item 062 6 washer NAS1149C0332R Item 083 3 nut NAS1291C3M Item 084 3 bolt NAS1303-3 Item 096 1 lead E0089-10-200NN Item 104 1 lead E0089-41-100NN Item 105 1 lead E0089-41-200NN Item 106 4 Install the vent line between FR46 and FR47. Refer to Drawing(s) : D28270972002 Sheet(s) 9 and 12

a Push over the outer tube, Item 050, this item temporarily as shown in Detail R9-11 : 1 sleeve D2827093322200 Item 039

b Install these items at the girder plate at FR46 as shown in Detail R9-11 and Section N11-N11 : 1 flange D2827093222200 Item 014 1 tube D2827092700000 Item 018 1 O-ring NSA8203-152 Item 054 1 O-ring NSA8203-234 Item 060 4 washer NAS1149C0432R Item 082 2 nut NAS1726-4E Item 085 1 bolt NAS1304-10 Item 091 1 bolt NAS1304-11 Item 092

c Push the inner pipe of the tube, Item 018, over the inner tube, Item 052, and install the nut, Item 066. d Connect the strap of the tube, Item 018, at the inner tube, Item 052, with these items as shown in Detail R9-11 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 washer NAS1149C0332R Item 083 1 nut NAS1291C3M Item 084

e Push the sleeve,Item 039, at FR46 in position and install these items as shown in Detail R9-11 and Section N11-N11 : 4 washer NAS1149C0432R Item 082 4 nut NAS1726-4E Item 085 4 bolt NAS1304-11 Item 092

f Install this item and secure with lockwire (Mat. No. 19-018) as shown in Section K11-K9 : 1 spring D2827051720200 Item 075

g Install these items as shown in Detail R9-11 and P11-11 and Section L11-L11 : 1 clamp NSA5519-30 Item 062 4 washer NAS1149C0332R Item 083 2 nut NAS1291C3M Item 084 2 bolt NAS1303-3 Item 096 1 lead E0089-10-160NN Item 103 1 lead E0089-41-100NN Item 105

h Install at the tube, Item 018, these items as shown in Detail V9-10 and Section A10-A10 : 1 flange D2827093222600 Item 020 1 O-ring NSA8203-151 Item 053 1 O-ring NSA8203-226 Item 058 with : 2 washer NAS1149C0432R Item 082 1 nut NAS1726-4E Item 085 1 bolt NAS1304-5 Item 087 2 bolt NAS1304-10 Item 091

i Install at the flange, Item 020, these items and secure with lockwire (Mat. No. 19-018) as shown in Detail V9-10: 1 plug AN814-4DL Item 071 1 packing NSA8200-4 Item 072

j Install these items as shown in Detail V9-10 and Section A10-A10 : 1 flange D2827093222800 Item 028 1 O-ring NSA8203-151 Item 053 with : 2 nut NAS1726-4E Item 085 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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2 bolt NAS1304-8 Item 089 2 bolt NAS1304-10 Item 091 (ad) Install the cover between FR46 and FR47 at the fuel transfer line and vent line. Refer to Kit 281132D19R00 Refer to Drawing(s) : D28270999004 Sheet(s) 3 1 Put this item in position as shown in Detail Z3-3 : 1 shield D2827099600400 Item 022 2Transfer drill the two holes in the upper beam and open them to final dimension. 3 Install these items as shown in Detail A3-3 : 1 shim D2827098322400 Item 004 1 shield D2827099600400 Item 022

with : 8 bolt NAS1303-5 Item 006 2 bolt NAS1303-8 Item 010 10 washer NAS1149D0332K Item 014 (ae) Install the system between FR37 and FR48. Refer to Kit 281132D14R00 Refer to Drawing(s) : D28270973002 Sheet(s) 6 thru 10 1 Install this item between FR38 and FR39 as shown in Detail Y6-8 : 1 bracket D2827094720000 Item 210

with : 2 bolt NAS1304-2 Item 030 2 nut NAS1726-4E Item 032 2 Install these items as shown in Details W6-8 and Z6-8 : 2 union MS21902D8 Item 000 2 packing NSA8200-8 Item 001 3Connect this item at the vent shroud line as shown in drawing D28270973002, Sheet 6 : 1 tube D2827093603400 Item 100

and install these items as shown in Details Y6-8 and X6-8 and Section B6-B8 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 543 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

4 washer NAS1149C0332R Item 007 1 screw NAS1096-3-8 Item 009 4 nut NAS1726-3E Item 010 2 screw NAS1096-3-7 Item 011 3 clamp MS21919WDE8 Item 014 1 clamp MS21919WDE48 Item 016 1 screw NAS1096-3-9 Item 024 1 bracket D2827098322800 Item 216 4 Install at the tube, Item 100, these items as shown in drawing D28270973002, Sheet 6 : 1 washer NAS1149C0332R Item 007 1 screw NAS1096-3-8 Item 009 1 clamp NSA5519-11 Item 035 1 nut NAS1291C3M Item 036 1 lead E0091-10-280NN Item 038 5 Connect this item at the fuel shroud line as shown in drawing D28270973002, Sheet 6 : 1 tube D2827093600200 Item 102

and connect the tube, Item 100, and the tube, Item 102, with this item : 1 tee MS21905D8 Item 005 6 Install these items between FR42 and FR43 as shown in Detail V6-8 : 1 elbow MS21907D8 Item 002 1 nut AN924-8D Item 003 1 washer NAS1149D1290K Item 004 1 washer NAS1149D1216H Item 023

and install this item as shown in drawing D28270973002, Sheet 6 : 1 tube D2827093602400 Item 124 7 Install these items as shown in Detail R6-8 : 3 washer NAS1149C0332R Item 007 2 screw NAS1096-3-8 Item 009 1 screw NAS1096-3-9 Item 024 2 strap E0090-10-125NN Item 025 1 clamp NSA5519-11 Item 035 1 nut NAS1291C3M Item 036 8 Install these items between FR42 and FR43 as shown in Details A6-7 and C6-9 : 1 tube D2827093603200 Item 108 1 tube D2827093602600 Item 126

with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 spacer NSA5527-03-16 Item 006 4 washer NAS1149C0332R Item 007 1 screw NAS1096-3-15 Item 008 3 screw NAS1096-3-8 Item 009 1 nut NAS1726-3E Item 010 2 clamp MS21919WDE8 Item 014 1 strap E0090-10-125NN Item 025 2 clamp NSA5519-11 Item 035 2 nut NAS1291C3M Item 036 9 Install this item in the keel beam as shown in drawing D28270973002, Sheet 6 : 1 hose 51263408-0840 Item 202

with : 6 washer NAS1149C0332R Item 007 6 screw NAS1096-3-8 Item 009 6 clamp MS21919WDE11 Item 015 10Install these items at FR46 as shown in Detail S6-9 : 1 tee NAS1763D080808 Item 033 1 fitting D2827094320000 Item 204

with : 2 nut NAS1726-3E Item 010 2 screw NAS1096-3-10 Item 012 11Install these items at FR46 as shown in Details B6-7, T6-8 and U6-8 : 1 tee MS21905D8 Item 005 1 tube D2827093601600 Item 116 1 tube D2827093602000 Item 120 1 tube D2827093603000 Item 130

with : 4 washer NAS1149C0332R Item 007 3 screw NAS1096-3-8 Item 009 3 nut NAS1726-3E Item 010 2 clamp MS21919WDE8 Item 014 1 screw NAS1096-3-9 Item 024 1 strap E0090-10-125NN Item 025 1 washer NAS1149D0316H Item 026 1 bolt NAS1303-2 Item 027 1 clamp NSA5575-7 Item 028 2 clamp NSA5519-11 Item 035 2 nut NAS1291C3M Item 036 1 strap E0090-10-200NN Item 037 1 lead E0091-10-280NN Item 038 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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12Install these items between FR47 and FR48 as shown in Detail Q6-10 : 1 nut AN924-8D Item 003 1 washer NAS1149D1290K Item 004 1 tee MS21912D8 Item 013 1 washer NAS1149D1216H Item 023 13Install these items between FR46 and FR48 as shown in Details Q6-10 and P10-10 : 1 tube D2827093603600 Item 136 1 tube D2827097600400 Item 138

with : 1 washer NAS1149C0332R Item 007 1 screw NAS1096-3-7 Item 011 1 clamp MS21919WDE8 Item 014 1 hose D56KAN002 Item 039 2 clamp ASNA0033-016 Item 040 14Install these items as shown in Details P10-10 and S6-9 :

4 washer NAS1149C0332R Item 007 4 screw NAS1096-3-8 Item 009 2 strap E0090-10-125NN Item 025 4 clamp NSA5519-11 Item 035 4 nut NAS1291C3M Item 036 15Install these items with sealant (Mat. No. 09-016) at the belly fairing as shown in Detail Q6-10 : 1 reducer MS21916D8-6 Item 017 1 packing NSA8200-6 Item 022 1 monitor L83A13-617 Item 206

with : 3 washer NAS1149C0432R Item 018 3 bolt NAS1304-4 Item 019

and install this item : 1 hose 513535E0107-090 Item 208 16Install this item with adhesive (Mat. No. 08-010) as shown in Detail Q6-10 : 1 placard D2827094421400 Item 214 17Install this item as shown in Detail Q6-10 : 1 tube D2827097600200 Item 134 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 546 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(af) Install the cavity drain and monitoring system between FR46 and FR50. Refer to Kit 281132D15R00 Refer to Drawing(s) : D28270974002 Sheet(s) 4 thru 6 1 Install these items between FR48 and FR49 as shown in Section C4-C5 : 1 nut AN924-8D Item 034 1 washer NAS1149D1290K Item 035 1 tee MS21912D8 Item 036 1 washer NAS1149D1216H Item 037 2 Install these items between FR48 and FR50 as shown in drawing D28270974002, Sheet 4 and in Details C4-C5 and D4-6: 1 tee MS21905D8 Item 021 1 elbow NAS1762D0808 Item 023 2 cap MS21914-8D Item 033 1 tube D2827097700400 Item 124 1 tube D2827097701200 Item 134

with : 3 clamp MS21919WDE8 Item 014 3 screw NAS1096-3-8 Item 016 4 washer NAS1149C0332R Item 017 1 nut NAS1291C3M Item 049 3 Install these items between FR49 and FR50 as shown in drawing D28270974002, Sheet 4 : 3 screw NAS1096-3-8 Item 016 3 washer NAS1149C0332R Item 017 3 nut NAS1291C3M Item 049 3 clamp NSA5519-11 Item 051 2 lead E0090-10-160NN Item 061 4 Install this item as shown in drawing D28270974002, Sheet 4 and Section B4-B6 : 1 tube D2827097700200 Item 122

with : 3 clamp MS21919WDE8 Item 014 3 screw NAS1096-3-8 Item 016 4 washer NAS1149C0332R Item 017 5 Install these items between FR46 and FR47 as shown in drawing D28270974002, Sheet 4, Section A4-A6 and Detail Z4-4 : 1 tee MS21905D8 Item 021 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 elbow NSA855120-8D Item 022 1 tube D2827093701800 Item 130 1 tube D2827097701000 Item 132

with : 1 clamp MS21919WDE8 Item 014 3 screw NAS1096-3-8 Item 016 3 washer NAS1149C0332R Item 017 3 nut NAS1291C3M Item 049 3 clamp NSA5519-11 Item 051 2 clamp ASNA0033-016 Item 056 1 hose D56KAN002 Item 057 1 strap E0090-10-125NN Item 060 1 lead E0090-10-160NN Item 061

NOTE : The connection to the and monitoring system will be installed in para 2.(ae)(17). 6 Install these items between FR47 and FR48 as shown in drawing D28270974002, Sheet 4 : 3 screw NAS1096-3-8 Item 016 3 washer NAS1149C0332R Item 017 3 nut NAS1291C3M Item 049 3 clamp NSA5519-11 Item 051 2 lead E0090-10-160NN Item 061 7 Install this item with sealant (Mat. No. 09-016) at the belly fairing as shown in Detail A5-5 and Section C4-C5: 1 reducer MS21916D8-6 Item 025 1 packing NSA8200-6 Item 026 1 valve L83A13-617 Item 202

with : 3 washer NAS1149C0432R Item 027 3 bolt NAS1304-4 Item 028

and install this item : 1 hose 513535E0107-090 Item 204 8 Install this item with adhesive (Mat. No. 08-010) as shown in Detail A5-5 : 1 placard D2827094421600 Item 216 (ag) Install the cavity drain and monitoring system between FR50 and FR53. Refer to Kit 281132D01R00 Refer to Drawing(s) : D28270990002 Sheet(s) 2 and 4 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 548 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 From the tee at FR50 shown in Sheet 4, remove : 1 cap MS21914-8D Item (033) Retain

NOTE : The cap was installed with Kit 281132D15R00, drawing D28270974002, Item 033. 2 Install these items between FR50 and FR53 as shown in sheet 4: 1 tube D28270977022 Item 006

with : 1 screw MS21919WDE8 Item 016 1 washer NAS1149C0332R Item 017 1 nut NAS1291C3M Item 049 1 clamp NSA5519-11 Item 051 1 bonding lead E0090-10-160NN Item 061 3 Install these items between FR51 and FR52 as shown in sheet 2 and Sections B1-B2 and C1-C2: 2 clamp MS21919WDE8 Item 014 2 screw MS21919WDE8 Item 016 2 washer NAS1149C0332R Item 017 2 nut NAS1291C3M Item 049 4 Install these items between FR52A and FR53 as shown in sheet 2 and Detail Y2-2: 1 clamp MS21919WDE8 Item 014 1 screw NAS1096-3-9 Item 015 1 screw MS21919WDE8 Item 016 2 washer NAS1149C0332R Item 017 2 nut NAS1291C3M Item 049 1 clamp NSA5519-11 Item 051 1 bonding lead E0090-10-160NN Item 061 5At FR52A, on tube, Item 004, install as shown in sheet 2 and Detail A1-2 : 1 cap MS21914-8D Item (033) Retained (ah) Install the attachment structure of the partition panels and floor panels. Refer to Kit 281132D60R00 Refer to Drawing(s) : D53975018002 Sheet(s) 9 thru 12 1 Install the attachment structure of the partition panels 151AW, 151BW and 152BW between FR46 and FR47.

a Put these items in position as shown in Section B9-B10, Details X10-11, Z10-11, Y10-12 and Sections A11-A11, B11-11, D11-11 and X10-11 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 549 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

22 bracket D5397469700000 Item 028 bTransfer drill the rivet holes and open them to final dimension.

c Install as shown in Section A11-A11, B11-B11: 22 bracket D5397469700000 Item 028 with : 88 rivet EN6018D6 Item 648 d Install these items as shown in Section B9-B10 and Details X10-11 and Z10-11 and Sections A10-A10 and B10-B10 : 1 T-section D5397468800200 Item 044 1 T-section D5397468800300 Item 045 1 T-section D5397468000400 Item 046 1 T-section D5397468000500 Item 047 with : 32 bolt NAS6703-2 Item 025 32 washer NAS1149D0332K Item 026

e Put these items in position as shown in Section B9-B10 and Detail Y10-12 : 1 section D5397467400500 Item 052 1 section D5397467400400 Item 053 1 bracket D5397469000000 Item 016 1 bracket D5397469000100 Item 017 1 bracket D5397469200000 Item 018 1 bracket D5397469200100 Item 019 1 bracket D5397469300000 Item 020 1 bracket D5397469300100 Item 021

f Drill and countersink the rivet holes and open them to final dimension. g Put these items in position as shown in Section B9-B10 and Detail Y10-12 : 1 section D5397467400400 Item 052 1 section D5397467400500 Item 053 1 bracket D5397469000000 Item 016 1 bracket D5397469000100 Item 017 1 bracket D5397469200000 Item 018 1 bracket D5397469200100 Item 019 1 bracket D5397469300000 Item 020 1 bracket D5397469300100 Item 021 Transfer drill the rivet holes and install the sections with : 12 bolt NAS6703-2 Item 025 12 washer NAS1149D0332K Item 026 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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18 rivet NAS1097AD-10 Item 532 h Put these items in position as shown in Section B3-B4 : 1 section D5397492500000 Item 048 1 section D5397492500200 Item 050

i Drill and countersink the holes and open them to final dimension. j Install these items : 1 T-section D5397492500000 Item 048 1 T-section D5397492500200 Item 050 1 T-section D5397467400400 Item 052 1 T-section D5397467400500 Item 053 with 94 rivet NAS1097AD4-12 Item 532 k Drill and countersink the holes and open them to final dimension. l Install these items : 1 section D5397467800800 Item 040 1 section D5397467800900 Item 041 1 section D5397492600000 Item 042 with : 50 rivet NAS1097AD4-12 Item 532

mInstall this item as shown in Detail V10-10 : 3 plate D5397492700000 Item 054 with : 9 screw NAS1102E3-7 Item 400 9 washer DAN125-4 Item 402

n Seal the gaps with sealant (Mat. No. 09-013) as shown in Section A4-A4 and Detail V4-4.

o Put these items in position as shown in Section B12-B12 : 1 section D5347047400200 Item 030 1 section D5347047400300 Item 031

p Drill and countersink the holes and open them to final dimension. q Install these items : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 section D5347047400200 Item 030 1 section D5347047400300 Item 031 with : 32 rivet NAS1097AD4-12 Item 532 2 Install the attachment structure of the cargo compartment floor panels at FR49, FR51 and FR54. Refer to Drawing(s) : D53975018002 Sheet(s) 9

a Put these items at FR49, FR51 and 54 in position : 2 section D5397489200000 Item 000 2 section D5397489200100 Item 001

b Drill and countersink the holes and open them to final dimension.

c Install these items : 2 section D5397489200000 Item 000 2 section D5397489200100 Item 001 with : 25 rivet NAS1097AD4-12 Item 532 (ai) Remove and discard the attachment parts at FR42. Refer to Drawing(s) : D92491681002 Sheet(s) 7 and 8 1 Remove and discard the attachment as shown in drawing D92491681002, Sheets 7, 8 and B01.

a Remove discard these parts : 1 bracket D9249170620000 Item (503) Discard 2 screw NAS1096-2-7 Item (522) Discard 2 washer NAS1149CN832R Item (531) Discard 2 nut MS21042-08 Item (541) Discard (aj) Remove and discard the attachment parts at FR42. Refer to Drawing(s) : D92891805002 Sheet(s) 17 and 18 1 Remove and discard the attachment as shown in drawing D92891805002, Sheets 17 and 18 and B01.

a Remove discard these parts : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 552 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

9 screw NAS1096-2-10 Item (506) Discard 9 washer NAS1149CN816R Item (652) Discard 9 washer NSA935808C01 Item (671) Discard 9 clip-nut NSA5066-08-2 Item (731) Discard 9 spacer NSA5527-03-04 Item (806) Discard 2 clamp MS21919WCH4 Item (850) Discard 3 clamp NSA935807-06 Item (876) Discard 6 clamp NSA935807 Item (877) Discard (ak) Remove and discard the attachment parts between FR46 and FR49. Refer to Drawing(s) : D92891805010 Sheet(s) 22, 24, 28, 34, 39, 41, 45, 63 and 66 1 Remove and discard the attachment as shown in drawing D92891805010, Sheets 22, 24, 28, 34, 39, 41, 45, 63 and 66

a Remove discard these parts : 12 screw NAS1096-2-8 Item (501) Discard 18 screw NAS1096-2-18 Item (502) Discard 12 screw NAS1096-2-28 Item (503) Discard 41 screw NAS1096-3-8 Item (504) Discard 42 clip-nut NSA5066-08-2 Item (505) Discard

1 spacer NSA5527-03-08 Item (506) Discard 70 nut MS21042L3 Item (507) Discard 26 nut MS21042L04 Item (508) Discard 60 washer NAS1149DN816K Item (509) Discard 26 washer NAS1149DO332K Item (510) Discard 28 washer NAS1149DN416K Item (511) Discard

2 sleeve NSA935510-02 Item (512) Discard 10 clamp MS21919WCH5 Item (513) Discard

2 clamp NSA935807-12 Item (514) Discard 12 spacer NSA5527-03-02 Item (516) Discard

3 washer NSA935808-01 Item (517) Discard 40 washer NAS1149C0332R Item (519) Discard 30 spacer NSA5527-03-01 Item (520) Discard

3 bulkhead NSA934710T14 Item (521) Discard 1 bracket E0660-01 Item (523) Discard 26 screw NAS1096-2-14 Item (525) Discard

9 bracket NSA935513-01 Item (527) Discard 1 bracket NSA935513-05 Item (528) Discard 4 bracket ABS0354-01 Item (529) Discard 1 bracket NSA935504-03 Item (530) Discard 30 bracket NSA935504-01 Item (531) Discard

1 clamp ASNA0032H052 Item (533) Discard 1 tie NSA935513-07 Item (534) Discard 1 tie NSA935401-04 Item (536) Discard 12 nut MS21042L08 Item (537) Discard

1 cable guide D9249184105600 Item (538) Discard 1 cable guide D9249184105800 Item (539) Discard 1 cable guide D9249184104800 Item (542) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 strap D9249107300400 Item (546) Discard 1 cable guide D9249181401800 Item (547) Discard 4 socket NSA938004-08 Item (548) Discard 2 cover NSA938005-08 Item (549) Discard 13 spacer NSA5527-03-04 Item (552) Discard 17 screw NAS1096-2-10 Item (553) Discard

2 bracket ABS0355-03 Item (554) Discard 1 screw NAS1096-2-43 Item (555) Discard 2 spacer NSA5527-03-04 Item (558) Discard 24 screw NAS1096-3-10 Item (559) Discard 19 washer NAS1149D0363K Item (560) Discard

2 spacer NSA5527-03-08 Item (561) Discard 5 bracket E0343-01 Item (563) Discard 2 screw NAS1096-2-32 Item (564) Discard 3 socket NSA938004-10 Item (565) Discard 4 socket NSA938004-16 Item (566) Discard 2 cover NSA938005-10 Item (567) Discard 1 socket NSA938004-20 Item (568) Discard 1 socket NSA938004-22 Item (569) Discard 1 bushing NSA5539S Item (570) Discard 1 spacer NSA5527-03-03 Item (572) Discard 1 tie NSA935401-03 Item (573) Discard 3 bracket NSA935504-01 Item (575) Discard 2 screw NAS1096-3-28 Item (576) Discard 1 screw NAS1096-3-39 Item (577) Discard 1 sealing A9249429620400 Item (579) Discard 3 bracket A9249429720200 Item (580) Discard 1 angle A9249436120000 Item (581) Discard 1 screw NAS1096-3-13 Item (582) Discard 1 washer NAS1149CN832R Item (612) Discard 1 bracket NSA935514-04A Item (613) Discard 1 bracket ABS0354-01 Item (629) Discard 1 tube TSTMNR502-0 Item (631) Discard 1 cable tie NSA935401-05 Item (637) Discard 18 washer D9249102520000 Item (690) Discard (al) Remove and discard the attachment parts at FR46 and FR54. Refer to Drawing(s) : D92491681012 Sheet(s) 12, 20, 32 and 34 1 Remove and discard the attachment as shown in drawing D92491681012, Sheets 12, 20, 32 and 34

a Remove discard these parts : 25 bracket A9249635720200 Item (501) Discard

3 bracket D9249179320000 Item (502) Discard 1 bracket D9249172120000 Item (504) Discard 6 bracket D9249178000000 Item (507) Discard 1 bracket D9249177020000 Item (511) Discard 4 bracket D9249177520000 Item (513) Discard 1 console D9249181820200 Item (523) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 bracket D9249171620400 Item (524) Discard 1 bracket D9249178000400 Item (530) Discard 1 support D9249185020400 Item (550) Discard (am) Remove and discard the attachment parts at FR46 and FR54. Refer to Drawing(s) : D92491681006 Sheet(s) 36, 38, 39, 42 and 44. 1 Remove and discard the attachment as shown in drawing D92491681006, Sheets 36, 38, 39, 42 and 44.

a Remove discard these parts : 6 bracket D9249177920000 Item (511) Discard 3 bracket D9249177720400 Item (512) Discard 1 bracket D9249177820000 Item (513) Discard 1 bracket D9249177820100 Item (514) Discard 8 bracket D9249177121200 Item (517) Discard 1 bracket D9249180500000 Item (518) Discard 2 bracket D9249180800000 Item (524) Discard 1 bracket D9249180921000 Item (525) Discard 1 bracket D9249180921200 Item (526) Discard 1 bracket D9249180921400 Item (527) Discard (an) Remove the cable harnesses , 4628VB, 4655VB, 4656VB, 4661VB, 4662VB, 4663VB, 4664VB, 4670VB, 4671VB, 4672VB, 4673VB, 4680VB, 4681VB, 4683VB, 4692VB, 4693VB 4694VB. 1 Remove the cable harness 4628VB/1M Refer to Drawing(s) : D92991428013 Sheet(s) 18 2 Remove the cable harness 4655VB/6S Refer to Drawing(s) : D92991455006 Sheet(s) 7, B01 and B02 and V01 3 Remove the cable harness 4656VB/6E and 6G Refer to Drawing(s) : D92991456004 Sheet(s) 5, B01 and B02 4 Remove the cable harness 4661VB/1M Refer to Drawing(s) : D92991461019 Sheet(s) 26, B01 to B04, H01 to H21, V01 to V05, W01 and W02, X01 5 Remove the cable harness 4662VB/2M Refer to Drawing(s) : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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D92991462008 Sheet(s) 10, B01 and B02, H01 to H06, W01, X01, V01 and V02 6 Remove the cable harness 4663CVB/1S Refer to Drawing(s) : D92991463003 Sheet(s) 8, B01, H01 to H09, W01 and W02, X01 7 Remove the cable harness 4664VB/2S Refer to Drawing(s) : D92991464002 Sheet(s) 4 and B01 8 Remove the cable harness 4670VB/1M Refer to Drawing(s) : D92991470007 Sheet(s) 8, B01 to B04, H01 to H06, W01, X01, V01 to V03 9 Remove the cable harness 4671VB/1M Refer to Drawing(s) : D92991471005 Sheet(s) 7, B01 to B05, H01 to H07, W01 and W02, X01, V01 to V03 10Remove the cable harness 4672VB/2M Refer to Drawing(s) : D92991472013 Sheet(s) 14, B01 and B02, H01 to H04, W01, X01, V01 and V02 11Remove the cable harness 4673VB/1S Refer to Drawing(s) : D92991473003 Sheet(s) 4, B01 and B02, H01 to H04, W01, X01, V01 and V02 12Remove the cable harness 4680VB/1MB Refer to Drawing(s) : D92991480012 Sheet(s) 13, B01 to B03, H01 to H05, W01, X01, V01 and V02 13Remove the cable harness 4681VB/7M Refer to Drawing(s) : D92991481003 Sheet(s) 4, B01, H01, W01, V01 14Cable harness 4683VB/8M

a Remove the air inlet plenum for access, refer to AMM 21-61-51, Page block 401. b Remove the welding group (Item 127) for access, refer to AMM 21-52-41, Page block 401.

c Remove the cable harness 4683VB/8M DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Refer to Drawing(s) : D92991483005 Sheet(s) 6, B01 and B02, H01 to H09, W01 and W02, X01 and X02, V01 to V04 15Remove the cable harness 4692VB/2M Refer to Drawing(s) : D92991492005 Sheet(s) 6, B01, H01, W01, X01, V01 16Remove the cable harness 4693VB/1S Refer to Drawing(s) : D92991493003 Sheet(s) 4, B01 and B02, H01 to H03, W01, X01, V01 and V02 17Remove the cable harness 4694VB/2S Refer to Drawing(s) : D92991494003 Sheet(s) 4, B01 and B02, H01 to H03, W01, X01, V01 and V02 (ao) Remove the cable harnesses 4213VB, 4214VB, 4216VB, 4218VB, 4220VB, 4221VB, 4222VB, 4223VB, 4224VB, 4225VB, 4226VB, 4227VB, 4232VB, 4233VB, 5214VB, 5220VB, 5224VB, 5233VB. 1 Remove the wires of cable harness 4213VB Refer to Drawing(s) : D92999559004 Sheet(s) 2, lines 1 to 3 2 Remove the wires of cable harness 4214VB Refer to Drawing(s) : D92999559006 Sheet(s) 3, lines 1 to 8 3 Remove the wires of cable harness 4216VB Refer to Drawing(s) : D92999561004 Sheet(s) 5, lines 1 to 7 D92999561004 Sheet(s) 6 4 Remove the wires of cable harness 4218VB Refer to Drawing(s) : D92999561006 Sheet(s) 8 and 9, 12 5 Remove the wires of cable harness 4220VB Refer to Drawing(s) : D92999559012 Sheet(s) 7 6 Remove the wires of cable harness 4221VB Refer to Drawing(s) : D92999559014 Sheet(s) 9 and 10 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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7 Remove the wires of cable harness 4222VB Refer to Drawing(s) : D92999559016 Sheet(s) 13, lines 1 to 7 8 Remove the wires of cable harness 4223VB Refer to Drawing(s) : D92999561008 Sheet(s) 14, 15 and 18 9 Remove the wires of cable harness 4224VB Refer to Drawing(s) : D92999559020 Sheet(s) 18 10Remove the wires of cable harness 4225VB Refer to Drawing(s) : D92999561010 Sheet(s) 20, lines 1 and 2 D92999561010 Sheet(s) 21, BEFORE MOD. 11Remove the wires of cable harness 4226VB Refer to Drawing(s) : D92999559024 Sheet(s) 21 and 22, 12Remove the wires of cable harness 4227VB Refer to Drawing(s) : D92990627012 Sheet(s) 17, 18, B01 to B03, H01 to H09, W01 and W02, X01 and X02, V01 to V05 13Remove the wires of cable harness 4232VB Refer to Drawing(s) : D92999559026 Sheet(s) 25 14Remove the wires of cable harness 4233VB Refer to Drawing(s) : D92999559028 Sheet(s) 27, lines 1 to 4 15Remove the wires of cable harness 5214VB Refer to Drawing(s) : D92999559030 Sheet(s) 28, line 1 16Remove the wires of cable harness 5220VB Refer to Drawing(s) : D92990820000 Sheet(s) 1 and B01 17Remove the wires of cable harness 5224VB DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Refer to Drawing(s) : D92990824002 Sheet(s) 3, B01, H01, W01 and V01 18Remove the wires of cable harness 5233VB Refer to Drawing(s) : D92990833000 Sheet(s) 1, B01, H01, W01, X01 and V01 (ap) Install the attachment parts at FR42. Refer to Kit 281132D89R00 Refer to Drawing(s) : D92491681002 Sheet(s) 7 and 9 1 Install the attachment as shown in drawing D92491681002, Sheets 7, 9 and B01.

a Install these parts : 2 L-profile D9249171020200 Item 012 2 screw NAS1096-2-7 Item 022 2 screw NAS1801-08-7 Item 031 2 nut MS21042-08 Item 041 (aq) Install the attachment parts between FR46 and FR54. Refer to Kit 281132G03R00 Refer to Drawing(s) : D92491681012 Sheet(s) 13, 15, 17, 19, 21, 46, 55, 58 and 59 1 Install the attachment as shown in drawing D92891681012, Sheets 13, 15, 17, 19, 21, 46, 55, 58 and 59.

a Install these parts : 43 bracket A9249635720200 Item 001 65 bracket D9249179320000 Item 002

6 bracket D9249178000600 Item 007 1 bracket D9249177124400 Item 009 6 bracket D9249177520000 Item 013 4 bracket D9249172321200 Item 016 2 angle D9249177520200 Item 019 1 bracket D9249184620400 Item 021 1 bracket D9249177100000 Item 023 1 bracket D9249180922600 Item 026 1 nut MS21060L3 Item 027 1 bracket D9249178001200 Item 032 335 rivet EN6081AD4-10 Item 632

12 rivet EN6081D6-18 Item 648

2 rivet EN6081AD3-08 Item 725 (ar) Install the attachment parts in the bilge area between FR46 and FR54. Refer to Kit 281132D93R01 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 559 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s) : D92491681006 Sheet(s) 34 thru 45 1 Install the attachment as shown in drawing D92891681006, Sheets 36 thru 45.

a Install these parts : 22 screw NAS1801-3-8 Item 001 40 screw NAS1801-08-8 Item 003

1 screw NAS1801-08-19 Item 004 23 washer NAS1149D0332K Item 005 40 washer NAS1149DN816K Item 006 22 nut MS21042L3 Item 009 16 nut MS21042L08 Item 010

1 mount E0343-01 Item 015 4 bracket D9249177121200 Item 016 1 spacer NSA5527-03-06D Item 017 1 bracket D9249177124200 Item 018 1 plate D9249175020000 Item 020 1 bracket D9249180800200 Item 024 1 bracket D9249180800400 Item 025 1 bracket D9249180900000 Item 026 1 bracket D9249180922400 Item 027 6 bracket D9249177920000 Item 028 2 bracket D9249177820200 Item 030 (as) Install the attachment parts at FR42. Refer to Kit 281132D90R00 Refer to Drawing(s) : D92891805002 Sheet(s) 16 and 19 1 Install the attachment as shown in drawing D92891805002, Sheets 17 thru 19 and B01.

a Install these parts : 8 screw NAS1801-08-10 Item 006 5 screw NAS1801-08-19 Item 012 1 screw NAS1801-08-25 Item 016 9 washer NSA935808C01 Item 151 12 washer NAS1149CN816R Item 152 12 clip-nut NSA5066-08-2 Item 231

3 spacer NSA5527-03-02 Item 302 11 spacer NSA5527-03-04 Item 306

4 spacer NSA5527-03-06 Item 310 11 clamp MS21919WCH4 Item 350

5 clamp MS21919WCH2 Item 364 6 clamp NSA935807-06 Item 376 6 clamp NSA935807-09 Item 377 (at) Install the attachment parts between FR46 and FR49. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 560 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Kit 281132G04R00 Refer to Drawing(s) : D92891805010 Sheet(s) 23, 29, 33, 35 thru 40, 48, 49, 61, 62, 63 and 67 1 Install the attachment as shown in drawing D92891805010, Sheets 23, 29, 33, 35 thru 40, 48, 49, 61, 62, 63 and 67.

a Install these parts : 70 screw NAS1801-08-8 Item 001 115 screw NAS1801-08-19 Item 002

15 screw NAS1801-08-29 Item 003 67 screw NAS1801-3-8 Item 004 193 nut NSA5066-08-2 Item 005 1 spacer NSA5527-03-0 Item 006 94 nut MS21042L3 Item 007 28 nut MS21042L04 Item 008 218 washer NAS1149DN816K Item 009

48 washer NAS1149D0332K Item 010 28 washer NAS1149DN416K Item 011

6 bobbin NSA935510-02 Item 012 15 clamp MS21919WCH5 Item 013

4 spacer NSA5527-03-02 Item 016 1 washer NSA935808-01 Item 017 10 support ABS0731A01 Item 018 44 washer NAS1149C0332R Item 019 143 spacer NSA5527-03-01 Item 020 7 fitting NSA934710T11 Item 021 3 fitting NSA934710T14 Item 022 1 mount E0660-01 Item 023 9 screw NAS1096-2-39 Item 024 28 screw NAS1100-04-8 Item 025

8 mount NSA935513-01 Item 027 1 mount NSA935513-05 Item 028 172 mount NSA935504-01 Item 031 1 clamp ASNA0032H052 Item 033 41 spacer NSA5527-03-03 Item 035 1000 tie NSA935401-04 Item 036 16 nut MS21042L08 Item 037

1 guide D9249181406400 Item 038 1 guide D9249181406600 Item 039 2 screw NAS1801-3-18 Item 040 16 screw NAS1801-08-14 Item 041

1 guide D9249181404800 Item 042 1 washer NSA935808C01 Item 043 1 guide D9249181401800 Item 047 2 receptacle EN3646A508 Item 048 2 bracket ABS0355-03 Item 0049 18 spacer NSA5527-03-04 Item 052 16 screw NAS1801-08-10 Item 053

1 screw NAS1096-2-43 Item 055 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 bracket NSA935504-02 Item 056 34 washer NAS1149D0363K Item 060

7 mount E0343-01 Item 063 20 screw EN3646A510 Item 064

5 receptacle EN3646A510 Item 065 4 receptacle EN3646A516 Item 066 4 cap EN3646A3C10 Item 067 1 receptacle EN3646A520 Item 068 1 receptacle EN3646A522 Item 069 1 screw NAS1801-3-28 Item 076 1 bracket A9249429720200 Item 078 1 sealing A9249429620400 Item 079 1 strip NSA939510BN Item 080 1 bracket A9249436120000 Item 083 1 screw NAS1801-3-13 Item 084 1 washer NAS1149CN832R Item 112 1 bracket NSA935514-05A Item 113 22 washer D9249102520000 Item 0190 b Install the placard as shown in drawing D9289180501000 Sheet(s) 59 1 placard D92891805202 Item 0002 (au) Replace the cap assembly of the AFT cargo-compartment smoke-detectors (3WH, 4WH) between FR52 and FR53. Refer to Kit 281132G12R00 Refer to AMM 26-16-15 Refer to Drawing(s) : D26170100024 Sheet(s) 41 thru 42 1 Remove the existing cap assembly. Refer to AMM 26-16-15, Page block 401 2 Install : 8 nut MS21043-3 Item 014 1 cap assy D2617013300600 Item 031 (av) Seal the gaps at the installed passenger compartment floor panels. Refer to Kit 281132D32R00 Refer to Drawing(s) : D53675016000 Sheet(s) 1 and 2 1 Install this item : 1 cord DAN107-1 Item 385

and seal all gaps with sealant (Mat. No. 09-016). 2 Install after sealing this item : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 562 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 tape ABS5093AT25 Item 387 3 Modify the affected carpet to get access the access panels in the passenger compartment floor panels 241JF, 251AF 251BF, 251FF, 251GF and 252BF. (aw) Install these protection covers on the roller tracks between FR53 and FR54. Refer to Kit 281132D29R00 Refer to Drawing(s) : D25572624010 Sheet(s) 17 and 18 1 Install these items :

2 cover D2557264403000 Item 001 4 screw D2557264403000 Item 020 4 screw D2557264403000 Item 021 (ax) Replace the placards at the side wall panels in the AFT cargo compartment. Refer to Kit 281132D26R01 Refer to Drawing(s) : D25572624026 Sheet(s) 35 D25572624028 Sheet(s) 36 1 Remove these items as shown in drawing D25572624026, Sheet 35, Details B, C, D and E : 1 placard D2557295021300 Item (001) Discard 1 placard D2557295021400 Item (002) Discard 1 placard D2557295028000 Item (003) Discard 1 placard D2557295028100 Item (004) Discard 4 placard D2557295024000 Item (008) Discard 1 placard D2557295022000 Item (015) Discard 2 placard A2557146821600 Item (018) Discard 11 placard D2557295024300 Item (024) Discard

8 placard D2557295030600 Item (040) Discard 1 placard D2557295228600 Item (041) Discard 2 Install these items as shown in drawing D25572624028, Sheet 36, Details B, C, D and G :

aClean the affected areas with cleaning agent (Mat. No. 11-026). b Install these items : 1 placard D2557295021300 Item 001 1 placard D2557295021400 Item 002 1 placard D2557295028000 Item 005 1 placard D2557295028100 Item 006 4 placard D2557295024000 Item 008 11 placard D2557295024300 Item 022

1 placard A2557146821200 Item 024 2 placard D2557295122600 Item 030 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 placard D2557295123600 Item 034 1 placard D2557295123800 Item 035 1 placard A2557295229400 Item 036 2 placard A2557144422600 Item 038 7 placard D2557295030600 Item 040 1 placard A2557332320000 Item 041 1 placard A2557332420000 Item 042 (ay) Install the belly fairing panels 197AB and 198GB. Refer to AMM 53-35-11 Refer to Kit 281132D04R00 Refer to Drawing(s) : D53475024000 Sheet(s) 1 1 Install this item as shown in Detail A1-1 : Refer to AMM 53-35-11, Page block 401 1 panel D5347503400200 Item 000 1 panel D5347505400200 Item 002 1 panel D5347505600400 Item 004

NOTE : Insert the key ring of the panel, Item 004, in the bracket, Item 014 installed on the web at FR50. with : 73 screw NSA5030-3-3 Item A 23 screw NSA5030-3-4 Item B 77 screw NSA5030-3-6 Item C NOTE : Items A, B and C are retained parts. (az) Install the Tie Down Points (TDP’s) in the AFT cargo compartment. Refer to Kit 281132D20R02 Refer to Drawings : D25572624000 Sheet(s) 1 thru 3 1 Install these items as shown in drawing D2557624000, Sheet 2, Section 2-2 and Sheet 3 Sections C3-C3, H3-H3 and M3-M3 : 3 TDP DAN152-1 Item 509 1 TDP D2557206226000 Item 517 9 TDP D2557206286000 Item 530 1 TDP D2557206296000 Item 531

with : 12 screw NAS1102-3-10 Item 510 18 screw NAS1102-3-12 Item 511 18 screw NAS1102-3-14 Item 512 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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46 nut NAS1726-3E Item 513 15 screw NAS1102-3-16 Item 514

5 screw NAS1102-3-18 Item 515 (ba) Replace Tie Down Point (TDP) and the stanchion bracket in the ceiling area of the AFT cargo compartment. Refer to Kit 281132D28R01 Refer to Drawings : D25572624004 Sheet(s) 6 1 At FR52A, remove as shown in drawing D25572624004, Sheet 6, Section C8-C8. 1 bracket D2557205820000 Item (500) Discard 2 screw NAS1102-3-18 Item (501) Discard 2At FR53, remove as shown in drawing D255762400, Sheet 6. 1 TDP DAN152-1 Item (502) Discard 2 screw NAS1102-3-18 Item (501) Discard 3At FR52A, install as shown in drawing D2557624004, Sheet 6. 1 TDP DAN152-1 Item 502

with : 2 screw NAS1102-3-18 Item 501 4At FR53, install as shown in drawing D255762400, Sheet 6, Section C8-C8. 1 bracket D2557205820000 Item 500

with : 2 screw NAS1102-3-18 Item 501 (bb) Install the nets in the AFT cargo compartment. Refer to AMM 25-55-00 Refer to Kit 281132D27R01 Refer to Drawings : D25572624002 Sheet(s) 4 and 5 1 Install these items : Refer to AMM 25-55-00, Page block 401 1 net AC40-0253621 Item 520 1 stanchion HA70-0214006 Item 521 1 net AC40-0217000 Item W1 1 net AC40-0217500 Item W2 1 net AC40-0209900 Item W3 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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NOTE : Items W1, W2 and W3 are retained parts. (bc) Install the equipment for the ACT pressurization system between FR48 and FR54. Refer to Kit 281132B01R00 Refer to drawings : D28270975004 Sheet(s) 7 thru 12 1 Install the equipment for the ACT pressurization system between FR48 and FR54.

a Install these items at the crossbeam at FR54 as shown in drawing D28270975004, sheet 7 and Sections A7-A8 and C8-C8 : 1 Filter-Air. Assembly QB0566 Item 41 1 Valve-Non-Return HTE490005 Item 42 1 Actuator-Valve, Single Motor HTE200002-1 Item 43 1 Valve-Air Shut Off HTE920007-001 Item 44 1 Clamp-V Band HTE8002 Item 45 1 Valve-Pressure, Reducing PAS148-133A Item 46 1 Valve-Non-Return HTE490005 Item 47 (bd) Install the Relay box in the forward avionics compartment. Refer to Kit 281132B02R00 Refer to drawings : D92355000 Sheet(s) 1 D92556025 Sheet(s) 1 and 3 1 Install this item in the forward avionics compartment : 1 Relay box D9255602500400 (be) Remove and discard the refuel/defuel panel mounting assembly in the belly fairing, zone 192. Refer to Kit 281132B02R00, Kit 281132B03R00 and Kit 281132B04R00 Refer to Drawing(s) : D92450032 Sheet(s) 6 and 7 D92450115 Sheet(s) 1 and 2 D92550025 Sheet(s) 1 D92550032 Sheet(s) 1 and 2 1 Remove and discard the refuel/defuel panel mounting assembly in the belly fairing, zone 192.

a Remove the pre-select unit 5QT (Refer to AMM 28-42-21, Page block 401). b Remove the refuel/defuel control panel 800VU (Refer to AMM 28-25-55, Page block 401). DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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c Remove the fuel quantity indicator unit 6QT (Refer to AMM 28-42-22, Page block 401). dTemporarily remove all attachments and associated fittings from the panel mounting-assembly.

e Remove the panel mounting-assembly, retain the attachment bolts for installation of the new panel mounting-assembly in the same position. 2 Install additional wiring between zone 192 and 132

a Install the wires shown on lines 1 thru 14 (Refer to Figure 2 Sheet 1). supplied in : 1 Bundle D92400000647 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. bCut the wires to the necessary length, crimp the terminals and connect them.

c Attach the wires with tie-wraps as necessary. d Do an intrinsically safe continuity test of the new wires. 3 Install the new refuel/defuel panel mounting assembly in the belly fairing, zone 192.

a Use a non-metallic spatula to remove the sealant and clean the areas with Solvent (Mat. No. 11-026). b Use sealant (Mat. No. 09-001) to wet assemble the refuel panel mounting-assembly and position it in the belly fairing. Use the attachment bolts retained from removal and install : 1 Panel Assy-Mounting D9245011500600

c Install all the attachment and associated fittings removed from the panel mounting-assembly. d Install the pre-select unit 5QT (Refer to AMM 28-42-21, Page block 401).

e Install the refuel/defuel control panel 800VU (Refer to AMM 28-25-55, Page block 401). 1 Panel Assy-Refuel D9255003200400

f Install the fuel quantity indicator unit 6QT (Refer to AMM 28-42-22, Page block 401). DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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g Install the refuel panel assembly 801VU Refer to drawing D92550025 and install this item : 1 Panel Assy-Refuel D9255002500200 (8) Config. 03 AI-GE, Part 2 (a) Remove and discard the overhead stowage compartments between FR43 and FR47. Refer to AMM 25-24-41 Refer to Drawing(s) : D25278439090 Sheet(s) 42 1 Remove and discard these items : Refer to AMM 25-24-41, Page block 401 1 box (LH) D2529421400000 Item (1014) Discard 1 box (RH) D2529421500000 Item (1015) Discard (b) Remove and discard the placards at the overhead stowage compartments between FR43 and FR47. Refer to Drawing(s) : D25278404054 Sheet(s) 48 and 49 1 Remove and discard this item :

4 placard D2528842244200 Item (1242) Discard (c) Modify the electrical equipment. Refer to Kit 281132D69R01 Refer to Drawing(s) : D92894736004 Sheet(s) 14 thru 17 D92894738042 Sheet(s) 1 1 Install the cable harness 5339VB from the terminal block 7223VT to the receptacle 7555VC. Refer to drawing D92894736004 (Sheets 14 thru 17) Refer to drawing D92894738042 (Sheet 1) Refer to Figure 1 (Hookup Chart 1)

a Remove this item as shown in drawing D92894736004, Sheet 16, Detail A : 1 screw NAS1096-2-9 Item (005) Discard and install these parts : 1 screw NAS1096-2-12 Item 007 1 bracket E0343-01 Item 250 1 bracket NSA935504-03 Item 253 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 spacer NSA5527-03-03 Item 304

b Remove this item as shown in drawing D92894736004, Sheet 16, Section A-A : 2 pin DAN364-02 Item (291) Discard and install these items : 2 bracket ABS0355-01 Item 262 2 bracket ABS0355-02 Item 263 2 washer NSA935514-03 Item 264

c Install this item as shown in drawing D92894736004, Sheet 16, Detail B : 1 bracket NSA935513-07 Item 259

d Route the wires with the existing wire, as shown in Hookup Chart 1, lines 1 and 2 and the drawing D92894736004, supplied with : 1 harness D9299043900000 Item 039 and connect with : AR tie NSA935401-03 Item 793 AR tie NSA935401-04 Item 794 AR tie NSA935401-05 Item 795

e Connect 7555VC with these items as shown in drawing D92894736004, Sheet 16, Detail B : 2 screw NAS1100-04-5 Item 051 2 washer NAS1149CN616R Item 150 2 nut MS21042-04 Item 200

f Connect 7499VN with these items as shown in drawing D92894736004, Sheet 16, Detail B : 1 screw NAS1096-3-9 Item 030 1 washer NAS1149C0332R Item 153

g Install the placards as shown in drawing D92894736004, Sheet 16, Details A and B : 2 placard D9239386503200 Item 050

h Install the "MOD/SB" placards on the harness 5339VB, Item 039, as shown in drawing D92894713020, Sheet 1 : 100 placard D9239240905800 Item 000 200 tie NSA935401-03 Item 080

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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2 Install the cable harness 5340VB from the terminal block 7224VT to the receptacle 7556VC. Refer to drawing D92894736004 (Sheet 14 thru 17) Refer to drawing D92894738042 (Sheet 1) Refer to Figure (Hookup Chart 2)

a Install these items as shown in drawing D92894736004, Sheet 16, Detail C : 3 screw NAS1096-2-12 Item 007 3 washer NAS1149CN816R Item 152 3 nut NSA5066-08-1 Item 230 1 bracket E0343-01 Item 250 1 bracket NSA935504-01 Item 251 3 spacer NSA5527-03-03 Item 304

b Route the wires with the existing wire, as shown in Hookup chart 2, lines 1 and 2 and the drawing D92894736004, supplied with : 1 harness D9299044000000 Item 040 and connect with : AR tie NSA935401-03 Item 793 AR tie NSA935401-04 Item 794 AR tie NSA935401-05 Item 795

c Connect 7556VC with these items as shown in drawing D92894736004, Sheet 16, Detail C : 2 screw NAS1100-04-5 Item 051 2 washer NAS1149CN616R Item 150 2 nut MS21042-04 Item 200

d Connect 7100VN with these items as shown in drawing D92894736004, Sheet 16, Detail D : 1 screw NAS1096-3-9 Item 030 1 washer NAS1149C0332R Item 153

e Install the placards as shown in drawing D92894736004, Sheet 16, Details C and D : 2 placard D9239386503200 Item 050

f Install the "MOD/SB" placards on the harness 5340VB, Item 040, as shown in drawing D92894713020, Sheet 1 : 100 placard D9239240905800 Item 000 200 tie NSA935401-03 Item 080 (d) Install the overhead stowage compartment. Refer to Kit 281132D72R00 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Refer to Drawing(s) : D25286364010 Sheet(s) 7 and 8 1 Install the overhead stowage compartment between FR43 and FR47, LH/RH. 2 Install the boxes, Items 020 and 021, as shown in Sections A7-8 and D7-8 : 1 box (LH) D2527305811800 Item 020 1 box (RH) D2527305811900 Item 021

with : 16 screw NAS1102-4-16 Item 002 16 washer NAS1149F0432P Item 004 16 washer NAS1169C416L Item 006 16 nut MS21042-4 Item 008 16 screw NAS1102-08-16 Item 010 16 washer NAS1149FN816P Item 012 16 washer NAS1169C8L Item 014 16 nut MS21042-08 Item 016

4 pin MS20392-3C23 Item 030 2 pin MS20392-3C27 Item 031 6 washer NAS1149F0463P Item 032 6 pin AA55487-5 Item 033 4 pin MS20392-4C67 Item 042 2 pin MS20392-4C45 Item 043 4 washer NAS1149C0532R Item 046 6 split-ring DAN191-20 Item 047 2 clamp NSA5528-045 Item 065 (e) Install the placards on the overhead stowage compartment. Refer to Kit 281132D73R00 Refer to Drawing(s) : D25288767000 Sheet(s) 1 and 2 1 Install the placards on the overhead stowage compartment between FR43 and FR47, LH/RH.

a Install these items : 2 placard D2527719940600 Item 206 2 placard D2527700844200 Item 242 2 placard A2528131544600 Item 246 (f) Remove and discard the passenger compartment floor panels 241JF, 251AF 251BF, 251FF, 251GF and 252BF. Refer to AMM 53-32-12, Page block 401 Refer to AMM 53-42-12, Page block 401 Refer to Drawing(s) : D53675015006 Sheet(s) 10 thru 12 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 Remove and discard these items :

2 panel D5367160000000 Item (204) Discard 1 panel D5367160100000 Item (206) Discard 2 panel D5367162300000 Item (214) Discard 1 panel D5367162400000 Item (216) Discard 1 panel D5367161700000 Item (224) Discard 1 connecting plate D5367009920400 Item (302) Discard

and discard the removed fastening parts. (g) Remove the LH sidewall panels between FR46 and FR58. Refer to AMM 25-55-11, Page block 401 Refer to Drawing(s) : D25570049010 Sheet(s) 6 1 Remove and discard these items : 1 panel D2557132600000 Item (160) Discard 1 panel D25571324004000 Item (162) Discard 1 panel D2557132200200 Item (164) Discard (h) Remove the RH sidewall panels between FR46 and FR52A. Refer to AMM 25-55-11, Page block 401 Refer to Drawing(s) : D25570049012 Sheet(s) 17 1 Remove and discard these items : 1 panel D2557133000000 Item (166) Discard 1 panel D2557133400000 Item (168) Discard (i) Remove and discard the insulation blankets at FR46. Refer to AMM 25-80-00, Page block 201 Refer to Drawing(s) : D25870003056 Sheet(s) 20 1 Remove and discard these items : 1 blanket D2587085002200 Item (020) Discard 1 blanket D2587085102400 Item (021) Discard 1 blanket D2587085202200 Item (022) Discard 1 blanket D2587085302400 Item (023) Discard 1 blanket D2587085402200 Item (024) Discard 1 blanket D2587085504200 Item (025) Discard 1 blanket D2587085602200 Item (026) Discard 1 blanket D2587085702200 Item (027) Discard 1 blanket D2587085802200 Item (028) Discard 1 blanket D2587085902200 Item (029) Discard 1 blanket D2587086002200 Item (030) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 572 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 blanket D2587086102200 Item (031) Discard 1 blanket D2587086202200 Item (032) Discard 1 blanket D2587086302400 Item (033) Discard 1 blanket D2587086502200 Item (034) Discard 1 blanket D2587087102200 Item (035) Discard 1 blanket D2587087302200 Item (036) Discard (j) Remove the AFT cargo compartment ceiling panels between FR47 and FR59. Refer to AMM 25-55-11, Page block 401 Refer to Drawing(s) : D25570049016 Sheet(s) 9 1 Remove and retain these items : 1 rail D2557043000000 Item C 2 rail D2557043000200 Item D 2 Remove and discard these items : 1 panel D2557173003600 Item (170) Discard 1 panel D2557174208200 Item (172) Discard 1 panel D2557174404200 Item (174) Discard 1 panel D2557174601400 Item (176) Discard 1 panel D2557173600000 Item (178) Discard 1 panel D2557164400000 Item (180) Discard (k) Remove and discard the floor panels from the AFT cargo compartment, between FR47 and FR56. Refer to AMM 53-42-14, Page block 401 Refer to Drawing(s) : D53675510012 Sheet(s) 19 1 Remove and discard these items as shown in Detail A16-16 : 1 panel D5367521100000 Item (202) Discard 1 panel D5367521100200 Item (204) Discard 1 panel D5367521100400 Item (206) Discard 1 panel D5367205900000 Item (222) Discard Discard the fastening items. (l) Remove and discard the sloped floor panels from the AFT cargo compartment, between FR47 and FR59. Refer to AMM 53-42-14, Page block 401 Refer to Drawing(s) : D53675520012 Sheet(s) 19 and 20 1 Remove and discard these items as shown in Details A16-16 and B16-16 : 1 panel D5367301800000 Item (200) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 panel D5367301800100 Item (201) Discard 1 panel D5367302000000 Item (202) Discard 1 panel D5367302400000 Item (204) Discard 1 panel D5367302600000 Item (206) Discard 1 panel D5367303400000 Item (208) Discard 1 panel D5367303400100 Item (209) Discard 1 panel D5367302200000 Item (210) Discard 1 panel D5367302700000 Item (212) Discard 1 panel D5367301900000 Item (214) Discard 1 panel D5367301900100 Item (215) Discard 1 panel D5367302100000 Item (216) Discard 1 panel D5367302500000 Item (218) Discard 1 panel D5367302800000 Item (220) Discard 1 panel D5367303500000 Item (222) Discard 1 panel D5367303500100 Item (223) Discard 1 panel D5367302300000 Item (224) Discard 1 panel D5367302900000 Item (226) Discard

Discard the fastening items. (m) Remove the cable harness 4209VB. 1 Remove the wires of cable harness 4209VB Refer to Drawing(s) : D92992299002 Sheet(s) 1 and 3 (n) Modify the structure. Refer to Kit 281132D05R01 Refer to Drawing(s) : D53372362004 Sheet(s) 2 thru 13 1 Install the beam assy between FR46 and FR47 from -Y1292 to +Y1292. D53372362004 Sheet(s) 12

a Remove the existing rivets in the affected areas. 1 beam D5337217000200 Item 000

b Put this item in position as shown in Detail A1-12 :

c Transfer drill the holes, drill the additional holes and open all holes to final dimension. d Install this items : 1 T-beam D5337217000200 Item 000 with : 8 pin DAN5-6-7X Item 767 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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4 pin DAN5-6-8X Item 768 4 collar NSA5075-5 Item 804 8 collar NSA5075-6 Item 806 12 collar DAN11-6X Item 807

4 pin DAN5-6-7 Item 967 4 pin DAN5-6-8 Item 968 4 pin DAN5-5-9 Item 949 2 Install the struts at the beam between FR46 and FR47.

a Install these items as shown in Details A1-12 and Z1-13 : 2 strut D5337218500000 Item 002 4 strut D5337218600000 Item 004 with : 2 bolt MS21250-09024 Item 464 2 nut NAS1726-9E Item 466 2 washer MS20002C9 Item 468 4 bolt MS21250-06018 Item 470 4 nut NAS1726-6E Item 472 4 washer MS20002C6 Item 474 NOTE : Tighten the nuts temporarily. The final attachment of the struts is possible after the installation of the attachment structure of the partition panels. 3 Replace fasteners between FR42 and FR46 between +Y1292 to +Y1650 and -Y1292 to -Y1650.

a Remove the existing rivets, drill the holes to final dimension and install these items as shown in Detail Y4-4 : 210 collar NSA5076-6 Item 816 4 pin DAN6-6-5 Item 865 166 pin DAN5-6-5 Item 965

40 pin DAN5-6-6 Item 966 b If necessary remove the MLG torque tube assembly, refer to AMM 32-33-17, Page block 401, and the shafts. Refer to drawing D53372362004, Sheet 4 Refer to drawing D32170220004, Sheet 5 Refer to drawing D32170220005, Sheet 5 12 pin DAN5-6-4X Item 764

8 pin DAN5-6-5X Item 765 8 pin DAN5-6-6X Item 766 2 pin DAN5-6-7X Item 767 2 collar NSA5075-6 Item 806 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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30 collar DAN11-6X Item 807

2 pin DAN5-6-8 Item 968 4 Replace the fasteners at FR43, STGR28LH/RH. D53372362004 Sheet(s) 3

a Remove the existing rivets, drill the holes to final dimension and install these items as shown in Detail T1-13 : 6 pin DAN5-6-6X Item 766 6 collar DAN11-6X Item 807 5 Drill the holes in FR46 between STGR42LH and STGR43LH. Refer to Drawing(s) : D53372362004 Sheet(s) 6

a Drill one hole with 22.0 mm (0.866 in.) diameter and two holes with 5.6 mm (0.22 in.) diameter as shown in Detail A7-6. b Deburr the holes. 6 Replace the fitting at FR47 at STGR43 to STGR44 as shown in Detail A1-A5. Refer to Drawing(s) : D53372362004 Sheet(s) 5, 8 and 9

a Remove : 1 support D5347465720300 Item (200) Discard 1 fitting D5347008120200 Item (202) Discard 1 profile D5347034400000 Item (220) Discard

b Put this item in position : 1 fitting D5337219020200 Item 012

c Transfer drill the holes and open the holes to final dimension. d Install this item : 1 fitting D5337219020200 Item 012 with : 5 rivet LN9198-4810CF Item 648 10 collar NSA5075-6 Item 806 10 pin DAN5-6-5 Item 965 7 Replace the supports at FR47 at STGR35LH/RH, STGR36LH/RH, STGR39LH/RH and STGR40LH/RH as shown in Detail A1-A5. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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a Remove and discard the supports : 4 support (LH) D5347100920000 Item (206) Discard 4 support (RH) D5347100920100 Item (207) Discard

b Put these items in position : 4 support (LH) D5347100920090 Item 048 4 support (RH) D5347100920190 Item 049

c Transfer drill the holes, open all holes and all countersinks to the final dimension. d Install these items : 4 support (LH) D5347100920090 Item 048 4 support (RH) D5347100920190 Item 049 with : 32 rivet LN9198-4010CF Item 640 8 Install the angles at FR47 between STGR36LH/RH and STGR40LH/RH as shown in Section A1-A5 and in Details Y1-8 and U1-9.

a Remove the existing fasteners between the affected stringers. b Put this item between the affected stringers in position : 8 angle D5337215920200 Item 016

c Transfer drill the holes from the skin panel to the angles. d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install this item : 8 angle D5337215920200 Item 016 with : 24 rivet LN9198-4810CF Item 648 32 collar DAN11-6X Item 807

2 pin DAN5-6-7X Item 767 26 pin DAN5-6-8X Item 768

2 pin DAN5-6-10X Item 770 2 pin DAN5-6-12X Item 772 9 Install the angles at FR47 between STGR35LH/RH and STGR36LH/RH as shown in Section A1-A5 and in Detail Y1-8.

a Remove the existing fasteners between the affected stringers. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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b Put these items between the affected stringers in position : 1 angle (LH) D5337215920400 Item 018 1 angle (RH) D5337215920500 Item 019

c Transfer drill the holes from the skin panel to the angle. d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install these items : 1 angle (LH) D5337215920400 Item 018 1 angle (RH) D5337215920500 Item 019 with : 6 rivet LN9198-4810CF Item 648 8 collar DAN11-6X Item 807 6 pin DAN5-6-8X Item 768 2 pin DAN5-6-10X Item 770 10Install the angle at FR47 between STGR40LH and STGR41LH as shown in Section A1-A5 and in Detail Y1-8.

a Remove the existing fasteners between the affected stringers. b Put this item between the affected stringers in position : 1 angle D5337215920000 Item 014

c Transfer drill the holes from the skin panel to the angle. d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install this item : 1 angle D5337215920000 Item 014 with : 3 rivet LN9198-4810CF Item 648 4 collar DAN11-6X Item 807 4 pin DAN5-6-8X Item 768 11Install the angle at FR47 between STGR40RH and STGR41RH as shown in Details Y5-5 and U1-9.

a Remove the existing fasteners between the affected stringers. b Put this item between the affected stringers in position : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 angle D5337215920600 Item 020

cTransfer drill the holes from the skin panel to the angle. d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install this item : 1 angle D5337215920600 Item 020 with : 3 rivet LN9198-4810CF Item 648 3 collar DAN11-6X Item 807 3 pin DAN5-6-9X Item 769 12Remove the angles at FR47 at STGR37LH/RH and STGR38LH/RH as shown in Section A1-A5.

a Remove and discard these items : 2 angle (LH) D5347104120000 Item (212) Discard 2 angle (RH) D5347104120100 Item (213) Discard 13Replace the fittings at FR47 between STGR37LH/RH and STGR38LH/RH as shown in Section A1-A5.

a Remove and discard these items : 1 fitting (LH) D5337219220200 Item (204) Discard 1 fitting (RH) D5337219220300 Item (205) Discard

b Put these items in position : 1 fitting (LH) D5337219220000 Item 008 1 fitting (RH) D5337219220100 Item 009

c Put these items at STGR37LH/RH in position : 1 angle (LH) D5347104120090 Item 050 1 angle (RH) D5347104120190 Item 051

dTransfer drill the holes and open the holes to final dimension.

e Install these items : 1 fitting (LH) D5337219220000 Item 008 1 fitting (RH) D5337219220100 Item 009 1 angle (LH) D5347104120090 Item 050 1 angle (RH) D5347104120190 Item 051 with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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8 pin DAN7-6-6X Item 566 4 rivet LN9198-4010CF Item 640 8 rivet LN9198-4810CF Item 648 4 rivet LN9198-5610CF Item 656 22 collar NSA5075-6 Item 806

8 collar DAN12-6X Item 817 16 pin DAN5-6-5 Item 965

2 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 14Install the fittings at FR47 between STGR38LH/RH and STGR39LH/RH as shown in Section A1-A5.

a Put these items at FR47 in position : 1 fitting (LH) D5337219120200 Item 010 1 fitting (RH) D5337219120300 Item 011

b Drill the holes and open the holes to final dimension.

c Install these items : 1 fitting (LH) D5337219120200 Item 010 1 fitting (RH) D5337219120300 Item 011 with : 12 rivet LN9198-4810CF Item 648 16 collar NSA5075-5 Item 804 16 pin DAN5-5-5 Item 945 15Install the nuts at FR47 as shown in Section A1-A5.

a Drill the four holes 5.6 mm (0.220 in.) diameter for the nuts. b Put the nuts, Item 046, in position.

c Drill the holes and countersink the rivet holes. d Install these items : 4 nut NAS1791A3-1 Item 046 with : 8 rivet NAS1097AD3-10 Item 524 16Remove the support at FR47 at STGR43LH as shown in Section A1-A5.

a Remove and discard this item : 1 support D5347465720300 Item (200) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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17Remove the nuts at FR47 as shown in Detail C5-5.

a Remove and discard these items : 2 nut NAS1068C3 Item (214) Discard

bClose the holes with : 4 rivet NAS1097AD3-10 Item 524 18Drill twelve holes with 5.6 mm (0.220 in.) diameter as shown in Details A5-5 and B5-5. 19Install the sections at FR43 and FR44 between STGR21LH and STGR23LH as shown in Detail X1-8. Refer to Drawing(s) : D53372362004 Sheet(s) 8

a Put this item in position : 3 section D5337602020000 Item 044

b Drill the holes and open the holes to final dimension.

c Countersink all additional holes in the skin panel. d Install these items : 3 section D5337602020000 Item 044 with : 21 collar NSA5075-6 Item 806

8 pin DAN6-6-5 Item 865 3 pin DAN5-6-4 Item 964 4 pin DAN6-6-6 Item 866 6 pin DAN5-6-5 Item 965 20Install the sections at FR43 and FR44 between STGR21RH and STGR23RH as shown in Detail X1-8. Refer to Drawing(s) : D53372362004 Sheet(s) 8

a Put this item in position : 3 section D5337602020100 Item 045

b Drill the holes and open the holes to final dimension.

c Countersink all additional holes in the skin panel. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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d Install these items : 3 section D5337602020100 Item 045 with : 21 collar NSA5075-6 Item 806

8 pin DAN6-6-5 Item 865 3 pin DAN5-6-4 Item 964 4 pin DAN6-6-6 Item 866 6 pin DAN5-6-5 Item 965 21Install the reinforcing angles between FR47 and FR48 at STGR1LH/RH and STGR2LH/RH as shown in Section D1-D10. Refer to Drawing(s) : D53372362004 Sheet(s) 9 and 10

a Remove the fasteners in the affected areas. b Put these items in position : 4 shim D5337236220400 Item 052 2 angle (LH) D5347007421800 Item 152 2 angle (RH) D5347007421900 Item 153

c Drill the holes in the stringer and the skin panel. dTransfer drill the holes from the stringer to the angles and open all holes and to final dimension.

e Countersink all additional holes in the skin panel. f Install these items : 4 shim D5337236220400 Item 052 2 angle (LH) D5347007421800 Item 152 2 angle (RH) D5347007421900 Item 153 with : 64 rivet NAS1097AD5-12 Item 540 48 rivet LN9198-4010CF Item 640 12 collar NSA5075-6 Item 806 12 pin DAN5-6-3 Item 963 22Install the reinforcing angles between FR48 and FR49 at STGR2LH/RH as shown in Section D1-D10. Refer to Drawing(s) : D53372362004 Sheet(s) 9 and 10

a Put these items in position : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 angle (LH) D5347007420800 Item 156 1 angle (RH) D5347007420900 Item 157

b Drill the holes in the stringer and the skin panel and open the holes to final dimension.

c Countersink all additional holes in the skin panel. d Install these items : 1 angle (LH) D5347007420800 Item 156 1 angle (RH) D5347007420900 Item 157 with : 38 rivet NAS1097AD5-12 Item 540 36 rivet LN9198-4010CF Item 640 23Install the reinforcing angles at FR48 between STGR8LH/RH and STGR13LH/RH as shown in Section C1-C9. Refer to Drawing(s) : D53372362004 Sheet(s) 9 and 10

a Put these items in position : 1 angle (LH) D5337036520200 Item 150 1 angle (RH) D5337036520300 Item 151

b Drill the holes and open the holes to final dimension.

c Install these items : 1 angle (LH) D5337036520200 Item 150 1 angle (RH) D5337036520300 Item 151 with : 52 rivet LN9198-4010CF Item 640 (o) Install the struts at the beam between FR46 and FR47. Refer to Kit 281132D05R01 Refer to Drawing(s): D53372362004 Sheet(s) 12 and 13 1 Install these items as shown in Details A1-12 and Z1-13 :

2 strut D5337218500000 Item 002 4 strut D5337218600000 Item 004

with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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2 bolt MS21250-09024 Item 464 2 nut NAS1726-9E Item 466 2 washer MS20002C9 Item 468 4 bolt MS21250-06018 Item 470 4 nut NAS1726-6E Item 472 4 washer MS20002C6 Item 474

NOTE : Tighten the nuts temporarily. The final attachment of the struts is possible after the installation of the attachment structure of the partition panels. (p) Replace fasteners between FR42 and FR46 at several places. Refer to Kit 281132D05R01 Refer to Drawing(s): D53372362004 Sheet(s) all 1 Replace the fasteners between FR44 and FR46 between +Y1292 to +Y1650 and -Y1292 to -Y1650. Refer to Drawing(s): D53372362004 Sheet(s) 4

a Remove the existing rivets, drill the holes to final dimension and install these items as shown in Detail Y4-4 : 210 collar NSA5076-6 Item 816 4 pin DAN6-6-5 Item 865 166 pin DAN5-6-5 Item 965

40 pin DAN5-6-6 Item 966 2 Replace the fasteners between FR42 and FR43 at +Y1650 and -Y1650. Refer to Drawing(s): D53372362004 Sheet(s) 4 D32170220004 Sheet(s) 5 D32170220005 Sheet(s) 5

a If necessary remove the MLG torque tube assembly, refer to AMM 32-33-17, Page block 401, and the shafts. Refer to Drawing(s) : D32170220004 Sheet(s) 5 D32170220005 Sheet(s) 5 b Remove the existing rivets, drill the holes to final dimension and install these items as shown in Detail X4-4 : 12 pin DAN5-6-4X Item 764

8 pin DAN5-6-5X Item 765 8 pin DAN5-6-6X Item 766 2 pin DAN5-6-7X Item 767 2 collar NSA5075-6 Item 806 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 584 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

30 collar DAN11-6X Item 807

2 pin DAN5-6-8 Item 968

c If removed, install the MLG torque tube assembly, refer to AMM 32-33-17, Page block 401, and the shafts. Refer to Drawing(s) : D32170220004 Sheet(s) 5 D32170220005 Sheet(s) 5 3 Replace the fasteners at FR43, STGR28LH/RH. Refer to Drawing(s) : D53372362004 Sheet(s) 13

a Remove the existing rivets, drill the holes to final dimension and install these items as shown in Detail T1-13 : 6 pin DAN5-6-6X Item 766 6 collar DAN11-6X Item 807 (q) Drill the holes in FR46 between STGR42LH and STGR43LH. Refer to Drawing(s) : D53372362004 Sheet(s) 6 1 Drill one hole with 22.0 mm (0.866 in.) diameter and two holes with 5.6 mm (0.22 in.) diameter as shown in Detail A7-6. 2 Deburr the holes. (r) Modify the structure of FR47 between STGR35LH to STGR35RH. Refer to Kit 281132D05R01 Refer to Drawing(s) : D53372362004 Sheet(s) 5, 8 and 9 1 Replace the fitting at FR47 at STGR43 to STGR44 as shown in Detail A1-A5.

a Remove : 1 support D5347465720300 Item (200) Discard 1 fitting D5347008120200 Item (202) Discard

b Put this item in position : 1 fitting D5337219020200 Item 012

c Transfer drill the holes and open the holes to final dimension. d Install this item : 1 fitting D5337219020200 Item 012 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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with : 5 rivet LN9198-4810CF Item 648 10 collar NSA5075-6 Item 806 10 pin DAN5-6-5 Item 965 2 Replace the supports at FR47 at STGR35LH/RH, STGR36LH/RH, STGR39LH/RH and STGR40LH/RH as shown in Detail A1-A5.

a Remove the supports for modification : 4 support (LH) D5347100920000 Item (206) Retain 4 support (RH) D5347100920100 Item (207) Retain

b Modify the supports as shown on Sheet 5, Detail A1-A5 : 4 support (LH) D5347100920000 Item (206) Retain 4 support (RH) D5347100920100 Item (207) Retain NOTE : Re-identify the supports : - Support PN D5347100920000, Item (206), becomes PN D5347100920000, Item (048) - Support PN D5347100920100, Item (207), becomes PN D5347100920100, Item (049)

c Put modified supports in position : 4 support (LH) D5347100920000 Item (048) Retained 4 support (RH) D5347100920100 Item (049) Retained

dTransfer drill the holes, open all holes and all countersinks to the final dimension.

e Install these items : 4 support (LH) D5347100920000 Item (048) Retained 4 support (RH) D5347100920100 Item (049) Retained with : 32 rivet LN9198-4010CF Item 640 3 Install the angles at FR47 between STGR36LH/RH and STGR40LH/RH as shown in Section A1-A5 and in Details Y1-8 and U1-9.

a Remove the existing fasteners between the affected stringers. b Put this item between the affected stringers in position : 8 angle D5337215920200 Item 016

c Transfer drill the holes from the skin panel to the angles. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install this item : 8 angle D5337215920200 Item 016 with : 24 rivet LN9198-4810CF Item 648

2 pin DAN5-6-7X Item 767 26 pin DAN5-6-8X Item 768

2 pin DAN5-6-10X Item 770 2 pin DAN5-6-12X Item 772 32 collar DAN11-6X Item 807 4 Install the angles at FR47 between STGR35LH/RH and STGR36LH/RH as shown in Section A1-A5 and in Detail Y1-8.

a Remove the existing fasteners between the affected stringers. b Put these items between the affected stringers in position : 1 angle (LH) D5337215920400 Item 018 1 angle (RH) D5337215920500 Item 019

cTransfer drill the holes from the skin panel to the angle. d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install these items : 1 angle (LH) D5337215920400 Item 018 1 angle (RH) D5337215920500 Item 019 with : 6 rivet LN9198-4810CF Item 648 8 collar DAN11-6X Item 807 6 pin DAN5-6-8X Item 768 2 pin DAN5-6-10X Item 770 5 Install the angle at FR47 between STGR40LH and STGR41LH as shown in Section A1-A5 and in Detail Y1-8.

a Remove the existing fasteners between the affected stringers. b Put this item between the affected stringers in position : 1 angle D5337215920000 Item 014

c Transfer drill the holes from the skin panel to the angle. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 587 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install this item : 1 angle D5337215920000 Item 014 with : 3 rivet LN9198-4810CF Item 648 4 collar DAN11-6X Item 807 4 pin DAN5-6-8X Item 768 6 Install the angle at FR47 between STGR40RH and STGR41RH as shown in Details Y5-5 and U1-9.

a Remove the existing fasteners between the affected stringers. b Put this item between the affected stringers in position : 1 angle D5337215920600 Item 020

c Transfer drill the holes from the skin panel to the angle. d Drill the additional holes in the frame, open all holes and all countersinks to the final dimension.

e Install this item : 1 angle D5337215920600 Item 020 with : 3 rivet LN9198-4810CF Item 648 3 collar DAN11-6X Item 807 3 pin DAN5-6-9X Item 769 7 Remove the angles at FR47 at STGR37LH/RH and STGR38LH/RH as shown in Section A1-A5.

a Remove and discard these items : 2 angle (LH) D5347104120000 Item (212) Discard 2 angle (RH) D5347104120100 Item (213) Discard 8 Replace the fittings at FR47 between STGR37LH/RH and STGR38LH/RH as shown in Section A1-A5.

a Remove and discard these items : 1 fitting (LH) D5337219220200 Item (204) Discard 1 fitting (RH) D5337219220300 Item (205) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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b Put these items in position : 1 fitting (LH) D5337219220000 Item 008 1 fitting (RH) D5337219220100 Item 009

c Put these items at STGR37LH/RH in position : 1 angle (LH) D5347104120090 Item 050 1 angle (RH) D5347104120190 Item 051

dTransfer drill the holes and open the holes to final dimension.

e Install these items : 1 fitting (LH) D5337219220000 Item 008 1 fitting (RH) D5337219220100 Item 009 1 angle (LH) D5347104120090 Item 050 1 angle (RH) D5347104120190 Item 051 with : 8 pin DAN7-6-6X Item 566 4 rivet LN9198-4010CF Item 640 8 rivet LN9198-4810CF Item 648 4 rivet LN9198-5610CF Item 656 22 collar NSA5075-6 Item 806

8 collar DAN12-6X Item 817 16 pin DAN5-6-5 Item 965

2 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 9 Install the fittings at FR47 between STGR38LH/RH and STGR39LH/RH as shown in Section A1-A5.

a Put these items at FR47 in position : 1 fitting (LH) D5337219120200 Item 010 1 fitting (RH) D5337219120300 Item 011

b Drill the holes and open the holes to final dimension.

c Install these items : 1 fitting (LH) D5337219120200 Item 010 1 fitting (RH) D5337219120300 Item 011 with : 12 rivet LN9198-4810CF Item 648 16 collar NSA5075-5 Item 804 16 pin DAN5-5-5 Item 945 10Install the nuts at FR47 as shown in Section A1-A5. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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a Drill the four holes 5.6 mm (0.220 in.) diameter for the nuts. b Put the nuts, Item 046, in position.

c Drill the holes and countersink the rivet holes. d Install these items : 4 nut NAS1791A3-1 Item 046 with : 8 rivet NAS1097AD3-10 Item 524 11Remove the support at FR47 at STGR43LH as shown in Section A1-A5.

a Remove and discard this item : 1 support D5347465720300 Item (200) Discard 12Remove the nuts at FR47 as shown in Detail C5-5.

a Remove and discard these items : 2 nut NAS1068C3 Item (214) Discard

bClose the holes with : 4 rivet NAS1097AD3-10 Item 524 13Drill twelve holes with 5.6 mm (0.220 in.) diameter as shown in Details A5-5 and B5-5. (s) Modify the structure between FR47 and FR48 at STGR38LH/RH and STGR43LH. Refer to Kit 281132D05R01 Refer to Drawing(s) : D53372362004 Sheet(s) 7 1 Remove the nuts at STGR38LH and STGR38RH as shown in Detail W1-7.

a Remove and discard this item : 6 nut NAS1791A3-1 Item (216) Discard 2 Remove the connections at STGR38LH and STGR38RH as shown in Detail W1-7.

a Remove and discard these items : 1 connection (LH) D5347101620400 Item (210) Discard 1 connection (RH) D5347101620500 Item (211) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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3 Install the plates, the sections and the connections at STGR38LH and STGR38RH as shown in Detail W1-7. Refer to Drawing(s) : D53372362004

aAt STGR38LH : Put these items in position : 1 plate D5337217400000 Item 024 1 section D5347449520800 Item 028 1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620490 Item 042 NOTE : Install the fillers, Item 030, 032, 034, 036 and 038, as required. NOTE : Install the section, Item 028, together with the angle, Item 130. bAt STGR38RH : Put these items in position : 1 plate D5337217400100 Item 025 1 section D5347449520900 Item 029 1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620590 Item 043 NOTE : Install the fillers, Item 030, 032, 034, 036 and 038, as required. NOTE : Install the section, Item 029, together with the angle, Item 134, at FR48.

cTransfer drill the holes from the skin panel and the stringer to the connections. d Drill the additional holes in the plates, sections and connections and open all holes and all countersinks to final dimension.

e Install these items at STGR38LH : 1 plate D5337217400000 Item 024 1 section D5347449520800 Item 028 1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 591 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620490 Item 042 with : 6 rivet NAS1097AD4-10 Item 532 21 rivet LN9198-4014CF Item 640

1 pin DAN5-6-6X Item 766 4 pin DAN5-6-7X Item 767 13 pin DAN5-6-8X Item 768

1 pin DAN5-6-9X Item 769 6 collar NSA5075-6 Item 806 19 collar DAN11-6X Item 807

4 pin DAN5-6-5 Item 965 2 pin DAN5-6-9 Item 969

f Install these items at STGR38RH : 1 plate D5337217400100 Item 025 1 section D5347449520900 Item 029 1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620590 Item 043 with : 6 rivet NAS1097AD4-10 Item 532 21 rivet LN9198-4014CF Item 640

1 pin DAN5-6-6X Item 766 4 pin DAN5-6-7X Item 767 13 pin DAN5-6-8X Item 768

1 pin DAN5-6-9X Item 769 6 collar NSA5075-6 Item 806 19 collar DAN11-6X Item 807

4 pin DAN5-6-5 Item 965 2 pin DAN5-6-9 Item 969 4 Remove the connection at STGR43LH as shown in Detail V1-7. Refer to Drawing(s) : D53372362004 Sheet(s) all

a Remove and discard this item : 1 connection D5347100720400 Item (208) Discard 5 Install the plate, the section and the coupling at STGR43LH as shown in Detail V1-7. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Refer to Drawing(s) : D53372362004 Sheet(s) all

a Put these items at STGR43LH in position : 1 plate D5337217320000 Item 022 1 section D5337216020000 Item 026 1 coupling D5347100720600 Item 040

bTransfer drill the holes from STGR43 to the plate and the connection.

c Drill all additional holes in the plate and the section and open all holes and all countersinks to final dimension. d Install these items : 1 plate D5337217320000 Item 022 1 section D5337216020000 Item 026 1 coupling D5347100720600 Item 040 with : 34 rivet LN9198-4014CF Item 640

4 pin DAN5-6-7X Item 767 4 pin DAN5-6-8X Item 768 2 collar NSA5075-6 Item 806 8 collar DAN11-6X Item 807 16 collar DAN11-8X Item 810

1 pin DAN5-8-8X Item 888 4 pin DAN5-8-9X Item 889 10 pin DAN5-8-10X Item 890

1 pin DAN5-8-11X Item 891 2 pin DAN5-6-7 Item 967 6 Install the reinforcing angles at FR48 between STGR8LH/RH and STGR13LH/RH as shown in Section C1-C9. Refer to Drawing(s) : D53372362004 Sheet(s) 9

a Put these items in position : 1 angle (LH) D5337036522600 Item 150 1 angle (RH) D5337036522700 Item 151

b Drill the holes and open the holes to final dimension.

c Install these items : 1 angle (LH) D5337036522600 Item 150 1 angle (RH) D5337036522700 Item 151 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 593 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

with : 52 rivet LN9198-4010CF Item 640 (t) Remove the corner profiles at STGR38LH/RH between FR48 and FR56. Refer to Drawing(s) : D53470075002 Sheet(s) 10 1 Remove and discard these items as shown in Details Z9-10 and X9-10 : 1 corner profile D5347048100400 Item (452) Discard 1 corner profile D5347047500400 Item (454) Discard 1 corner profile D5347047600600 Item (456) Discard (u) Remove the shear plates at STGR38LH/RH between FR48 and FR59. Refer to Drawing(s) : D53470075002 Sheet(s) 1, 8 and 11 1 Remove and discard these items at STGR38LH as shown in Sections H1-8 and K1-11 : 1 shear plate D5347048800000 Item (374) Discard 1 shear plate D5347048900000 Item (376) Discard 1 shear plate D5347049200200 Item (378) Discard 2 angle D5347046820600 Item (386) Discard 1 angle D5347046820200 Item (390) Discard 1 angle D5347046820800 Item (392) Discard 1 angle D5347046821000 Item (394) Discard 3 angle D5347046820000 Item (460) Discard 2 angle D5347046820200 Item (462) Discard 2 angle D5347046820400 Item (464) Discard 2 shear plate D5347049000000 Item (474) Discard 1 shear plate D5347049100000 Item (476) Discard 2 Remove and discard these items at STGR38RH as shown in Sections G1-8 and J1-11 : 1 shear plate D5347048700000 Item (370) Discard 1 shear plate D5347048500200 Item (372) Discard 1 shear plate D5347046821100 Item (380) Discard 1 angle D5347046820900 Item (382) Discard 1 angle D5347046822000 Item (384) Discard 1 shear plate D5347063720600 Item (396) Discard 2 angle D5347046820100 Item (468) Discard 3 angle D5347046820300 Item (470) Discard 1 angle D5347046822400 Item (472) Discard 1 shear plate D5347049000100 Item (478) Discard 1 shear plate D5347049000300 Item (480) Discard 1 shear plate D5347048600400 Item (482) Discard

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 594 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(v) Remove the crossbeams at FR48, FR49, FR50 and FR51 in the AFT cargo compartment. Refer to Drawing(s) : D53470075002 Sheet(s) 1 thru 5 NOTE : Do not remove all the crossbeams at the same time. It is imperative that the following sequence is followed precisely due to stress reason : - Remove and change 1 crossbeam out of 2. Do the modification. - Remove and change the remaining crossbeams. Do the modification. 1 Remove these items at FR48 as shown in drawing D53470075002, Sheet 2, Section A1-A2 ’BEFORE’.

a Remove and discard these items : 1 crossbeam D5347035000200 Item (400) Discard 1 shim D5347061120200 Item (402) Discard 1 fitting D5347061220000 Item (404) Discard 1 shim D5347061120300 Item (406) Discard 1 fitting D5347061220100 Item (408) Discard 1 support D5347069920800 Item (412) Discard

bClose the eight holes as shown in Details B2-2 and C2-2 : 8 rivet NAS1097-5 2 Remove these items at FR49 as shown in drawing D53470075002, Sheet 3, Section B1-B3 ’BEFORE’.

a Remove and discard these items : 1 crossbeam D5347035000200 Item (400) Discard 1 shim D5347061120200 Item (402) Discard 1 fitting D5347061220000 Item (404) Discard 1 shim D5347061120300 Item (406) Discard 1 fitting D5347061220100 Item (408) Discard 1 support D5347069920800 Item (412) Discard

bClose the eight holes as shown in Details B3-3 and C3-3 : 8 rivet NAS1097-5 3 Remove these items at FR50 as shown in drawing D53470075002, Sheet 4, Section C1-C4 ’BEFORE’.

a Remove and discard these items : 1 crossbeam D5347026000200 Item (410) Discard 1 shim D5347061120200 Item (402) Discard 1 fitting D5347061220000 Item (404) Discard 1 shim D5347061120300 Item (406) Discard 1 fitting D5347061220100 Item (408) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 595 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 clip D5347073720400 Item (430) Discard 1 clip D5347073920200 Item (432) Discard 1 clip D5347074020000 Item (434) Discard 1 clip D5347073720500 Item (436) Discard

bClose the eight holes as shown in Details B21-21 and C21-21 : 8 rivet NAS1097-5 4 Remove these items at FR51 as shown in drawing D53470075002, Sheet 5, Section D1-D5 ’BEFORE’.

a Remove and discard these items : 1 crossbeam D5347035300200 Item (420) Discard 1 shim D5347061120200 Item (402) Discard 1 fitting D5347061220000 Item (404) Discard 1 shim D5347061120300 Item (406) Discard 1 fitting D5347061220100 Item (408) Discard 1 clip D5347074420400 Item (440) Discard 1 clip D5347074620200 Item (442) Discard 1 clip D5347074720000 Item (444) Discard 1 clip D5347074420500 Item (446) Discard 1 support D5347557525400 Item (448) Discard

bClose the eight holes as shown in Details B5-5 and C5-5 : 8 rivet NAS1097-5 (w) Remove the crossbeams at FR52, FR53 and FR54 in the AFT cargo compartment. Refer to Drawing(s) : D53470076004 Sheet(s) 1, 2, 4 and 5 NOTE : Do not remove all the crossbeams at the same time. It is imperative that the following sequence is followed precisely due to stress reason : - Remove and change 1 crossbeam out of 2. Do the modification. - Remove and change the remaining crossbeams. Do the modification. 1 Remove these items from FR52 as shown in drawing D53470076004, Sheet 2, Section A1-A2 ’BEFORE’.

a Remove and discard these items : 1 fitting D5347061220000 Item (400) Discard 1 fitting D5347061220100 Item (401) Discard 1 shim D5347061120200 Item (402) Discard 1 shim D5347061120300 Item (403) Discard 1 support D5347037820200 Item (404) Discard 1 fitting D5347448720000 Item (406) Discard 1 clip D5347074320600 Item (408) Discard 1 clip D5347075120200 Item (410) Discard 1 clip D5347075220000 Item (412) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 596 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 clip D5347074320700 Item (414) Discard 1 angle D5347557520600 Item (416) Discard 1 support D5347038420200 Item (444) Discard 1 fitting D5347449920200 Item A NOTE : Discard the Item A. bClose the eight holes as shown in the Detail A2-A2 and B2-B2 : 8 rivet NAS1097-5 2 Remove these items as shown in drawing D53470076004, Sheet 3, Section B1-B3 and A3-A3 ’BEFORE’: 1 nut-plate NAS1791A3-1 Item (460) Discard 1 nut-plate NAS1068C3 Item (462) Discard 3 Remove these items at FR53 as shown in drawing D53470076004, Sheet 4, Section C1-C4 ’BEFORE’.

a Remove and discard these items : 1 fitting D5347061220000 Item (400) Discard 1 crossbeam D5347026100400 Item (418) Discard 1 clip D5347075420000 Item (426) Discard 1 clip D5347075520200 Item (428) Discard 1 clip D5347075320800 Item (464) Discard

bClose the four holes as shown in Detail A4-4 : 8 rivet NAS1097-5 4 Remove these items at FR54 as shown in drawing D53470076004, Sheet 5, Section D1-D5 ’BEFORE’.

a Remove and discard these items : 1 fitting D5347061220000 Item (400) Discard 1 shim D5347061120200 Item (402) Discard 1 crossbeam D5347035601000 Item (430) Discard 1 clip D5347098020000 Item (432) Discard 1 clip D5347075820200 Item (436) Discard 1 clip D5347075920000 Item (438) Discard 1 clip D5347076020200 Item (440) Discard

bClose the four holes as shown in Detail A5-5 : 8 rivet NAS1097-5 (x) Modify the structure at FR48 between STGR34LH and STGR34RH. Refer to Kit 281132D40R03 Refer to Kit 281132G10R02 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 597 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s) : D53470075002 Sheet(s) 1 and 2 1 Replace the fasteners at FR48 between STGR34RH and STGR36RH as shown in Section A1-A2 ’AFTER’.

a Remove the existing fasteners in the affected area as shown in Section A1-A2 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR48. 2 Install the reinforcing straps at FR48 between STGR35LH/RH and STGR42LH/RH as shown in Section A1-A2 ’AFTER’ :

a Put these items at FR48 in position : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes to final dimension. d Install these items : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with : 58 rivet LN9198-4012CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit 281132D41R00

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 598 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

3 Install the fittings at FR48 at STGR37LH/RH as shown in Section A1-A2 ’AFTER’ :

a Put these items at FR48 in position : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

bTransfer drill the holes from the frame to the fittings and open all holes to final dimension.

c Install these items : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with : 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR48 as shown in Section A1-A2 ’AFTER’ :

a Put these items at FR48 temporarily in position : 1 crossbeam D5347035000600 Item 010 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 010, IS IN LINE WITH THE CROSSBEAMS AT FR47 AND FR55. b Mark the fastener holes as shown in Detail B2-2 and C2-2.

c Drill the marked holes with 3.3 mm (0.130 in.) diameter. dTransfer drill all other holes from the frame to the crossbeam.

e Drill all additional holes and open all holes to final dimension. f Remove the crossbeam. g Mark and drill the holes in FR48 as shown in Detail C. h Put the crossbeam in position and install these items : 1 crossbeam D5347035000600 Item 010 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 599 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 filler D5337217620800 Item 026 with : 32 rivet LN9198-4816CF Item 648

6 pin DAN5-6-5X Item 765 60 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 6 collar NSA5075-8 Item 808 16 pin DAN5-6-4 Item 964 34 pin DAN5-6-5 Item 965 10 pin DAN5-6-6 Item 966

2 pin DAN5-6-7 Item 967 6 pin DAN5-8-5 Item 985

i Put this item at FR48 in position as shown in Details C3-3, Z2-3, Z3-3, Y2-3 and Y3-3 : 2 bushing D5347658620000 Item 204

j Transfer drill the holes from the frame to the bushings and open the holes to final dimension. k Install these items as shown in Detail C3-3 : 2 bushing D5347658620000 Item 204 with : 2 collar NSA5075-6 Item 806 2 pin DAN5-6-7 Item 967 5 Replace the fasteners at FR48 between STGR42LH and STGR42RH :

a Remove the fasteners as shown in Section A1-A2 ’BEFORE’. bOpen the holes to final dimension.

c Install these items as shown in Section A1-A2 ’AFTER’ : 17 rivet LN9198-4816CF Item 648 6 Install the sections and the angles at FR48 between STGR34LH/RH and STGR39LH/RH as shown in Section A1-A2 ’AFTER’ :

a Put these items in position : 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 3 section D5347449520500 Item 032 3 section D5347449520400 Item 034 1 angle D5347470020000 Item 036 1 angle D5347470020100 Item 038 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 600 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items : 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 3 section D5347449520500 Item 032 3 section D5347449520400 Item 034 1 angle D5347470020000 Item 036 1 angle D5347470020100 Item 038 with : 32 rivet MBBN4477-4812 Item 549 40 rivet LN9198-4816CF Item 648

8 collar NSA5075-6 Item 806 8 pin DAN6-6-4 Item 864 (y) Modify the structure at FR49 between STGR34LH and STGR34RH. Refer to Kit 281132D40R03 Refer to Kit 281132G10R02 Refer to Drawing(s) : D53470075002 Sheet(s) 1 and 3 1 Replace the fasteners at FR49 between STGR34RH and STGR36RH as shown in Section B1-B3 ’AFTER’ :

a Remove the existing fasteners in the affected area as shown in Detail B3-3 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR49. 2 Install the reinforcing straps at FR49 between STGR35LH/RH and STGR42LH/RH as shown in Section B1-B3 ’AFTER’ :

a Put these items at FR49 in position : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 601 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes to final dimension. d Install these items : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with : 58 rivet LN9198-4012CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit 281132D41R00, refer to para. (7) (p) 2c. 3 Install the fittings at FR49 at STGR37LH/RH as shown in Section B1-B3 ’AFTER’ :

a Put these items at FR49 in position : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

bTransfer drill the holes from the frame to the fittings and open all holes to final dimension.

c Install these items : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with : 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR49 as shown in Section B1-B3 ’AFTER’ :

a Put these items at FR49 temporarily in position : 1 crossbeam D5347035000600 Item 010 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 602 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 filler D5337217620800 Item 026

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 010, IS IN LINE WITH THE CROSSBEAMS AND FR47 AND FR55. b Mark the fastener holes as shown in Detail Y3-3 and Z3-3.

c Drill the marked holes with 3.3 mm (0.130 in.) diameter. dTransfer drill all other holes from the frame to the crossbeam.

e Drill all additional holes and open all holes to final dimension. f Remove the crossbeam. g Mark and drill the holes in FR49 as shown in Detail C3-3. h Put the crossbeam in position and install these items : 1 crossbeam D5347035000600 Item 010 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026 with : 32 rivet LN9198-4816CF Item 648

6 pin DAN5-6-5X Item 765 60 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 6 collar NSA5075-8 Item 808 16 pin DAN5-6-4 Item 964 36 pin DAN5-6-5 Item 965

8 pin DAN5-6-6 Item 966 2 pin DAN5-6-7 Item 967 6 pin DAN5-8-5 Item 985

i Put this items at FR49 in position as shown in Detail C3-3 : 2 bushing D5347658620000 Item 204

j Transfer drill the holes from the frame to the bushings and open the holes to final dimension. k Install these items as shown in Detail C3-3 : 2 bushing D5347658620000 Item 204 with : 2 collar NSA5075-6 Item 806 2 pin DAN5-6-7 Item 967 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 603 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

5 Install the sections and the angles at FR49 between STGR34LH/RH an and STGR39LH/RH as shown in Section B1-B3 ’AFTER’ :

a Put these items in position : 1 L-profile D5347449521800 Item 020 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 1 section D5347449520500 Item 032 1 section D5347449520400 Item 034 1 angle D5347470020400 Item 044 1 angle D5347470020500 Item 046 2 angle D5347470020200 Item 048 2 angle D5347470020300 Item 050

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items : 1 L-profile D5347449521800 Item 020 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 1 section D5347449520500 Item 032 1 section D5347449520400 Item 034 1 angle D5347470020400 Item 044 1 angle D5347470020500 Item 046 2 angle D5347470020200 Item 048 2 angle D5347470020300 Item 050 with : 46 rivet MBBN4477-4812 Item 549 40 rivet LN9198-4816CF Item 648 6 Replace the riveting between clip and skin panel at FR49 between STGR34LH/RH and STGR37LH/RH as shown in Section B1-B3 :

a Remove the existing rivets. bOpen the holes and the countersinks to final dimension.

c Install this item : 24 rivet MBBN4477-4812 Item 549 (z) Modify the structure at FR50 between STGR34LH and STGR34RH. Refer to Kit 281132D40R03 Refer to Kit 281132G10R02 Refer to Drawing(s) : D53470075002 Sheet(s) 1 and 4 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 604 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Replace the fasteners at FR50 between STGR34RH and STGR36RH as shown in Section C1-C4 ’AFTER’ :

a Remove the existing fasteners in the affected area as shown in Section C1-C4 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR50. 2 Install the reinforcing straps at FR50 between STGR35LH/RH and STGR42LH/RH as shown in Section C1-C4 ’AFTER’ :

a Put these items at FR50 in position : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes to final dimension. d Install these items : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024 with : 58 rivet LN9198-4012CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit 281132D41R00, refer to para. (2)(p)3c(7) (p) 3c. 3 Install the fittings at FR50 at STGR37LH/RH as shown in Section C1-C4 ’AFTER’ :

a Put these items at FR50 in position : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 605 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

bTransfer drill the holes from the frame to the fittings and open all holes to final dimension.

c Install these items : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with : 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR50 as shown in Section C1-C4 ’AFTER’ :

a Put these items at FR50 in position : 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026 1 crossbeam D5347026000600 Item 052

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 052, IS IN LINE WITH THE CROSSBEAMS AND FR47 AND FR55. bTransfer drill all holes from the frame to the crossbeam.

c Put these items at FR50 between STGR42LH and STGR42RH in position : 1 angle D5347470520000 Item 054 1 angle D5347470520100 Item 056 1 web D5347470320000 Item 066

dTransfer drill the holes from the frame and skin panel to the shear web and the supports.

e Drill all additional holes and open all holes and all countersinks to final dimension. f Install these items : 1 plate D5337217620000 Item 012 1 plate D5337217620100 Item 014 2 filler D5337217620800 Item 026 1 crossbeam D5347026000600 Item 052 1 angle D5347470520000 Item 054 1 angle D5347470520100 Item 056 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 606 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 web D5347470320000 Item 066 with : 12 rivet MBBN4477-4812 Item 549

4 rivet LN9198-4014CF Item 640 51 rivet LN9198-4816CF Item 648

6 pin DAN5-6-5X Item 765 56 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 12 collar NSA5075-8 Item 808 20 pin DAN5-6-4 Item 964 32 pin DAN5-6-5 Item 965

4 pin DAN5-6-6 Item 966 6 pin DAN5-8-5 Item 985 4 pin DAN5-8-6 Item 986 2 pin DAN5-8-7 Item 987 5 Install the sections and the angles at FR50 between STGR34LH and STGR34RH as shown in Section C1-C4 ’AFTER’:

a Put these items in position : 1 section D5347449520300 Item 028 1 section D5347449520200 Item 030 2 section D5347449520500 Item 032 2 section D5347449520400 Item 034 1 angle D5347470020400 Item 044 1 angle D5347470020500 Item 046 2 angle D5347470020200 Item 048 2 angle D5347470020300 Item 050 1 section D5347449523400 Item 058 1 section D5347449523600 Item 060 1 section D5347449522000 Item 062 2 section D5347449523200 Item 064 1 angle D5347470020800 Item 068 1 angle D5347470021000 Item 070 1 angle D5347470020600 Item 072 1 angle D5347470021200 Item 074

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel and the two holes in the angles, Item 064, and install with these items : 82 rivet MBBN4477-4812 Item 549 69 rivet LN9198-4816CF Item 648

4 collar NSA5075-6 Item 806 4 pin DAN5-6-4 Item 964 6 Replace the riveting between clip and skin panel at FR50 between STGR34LH/RH and STGR37LH/RH as shown in Section C1-C4 ’AFTER’ : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 607 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Remove the existing rivets. bOpen the holes and the countersinks to final dimension.

c Install this item : 24 rivet NAS1097KE6-00 Item 548 (aa) Modify the structure at FR51 between STGR34LH and STGR34RH. Refer to Kit 281132D40R03 Refer to Kit 281132G10R02 Refer to Drawing(s) : D53470075002 Sheet(s) 5 1 Replace the fasteners at FR51 between STGR34RH and STGR36RH as shown in Section D1-D5 ’AFTER’ :

a Remove the existing fasteners in the affected area as shown in Section D1-D5 ’BEFORE’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 34 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 16 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964 6 pin DAN5-6-5 Item 965 NOTE : The remaining fasteners, Item 865 and 806, will be installed during the installation of the reinforcing straps at FR51. 2 Install the reinforcing straps at FR51 between STGR35LH/RH and STGR42LH/RH as shown in Section D1-D5 ’AFTER’ :

a Put these at FR51 in position : 1 strap (LH) D5347448420200 Item 022 1 strap (RH) D5347448420300 Item 024

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes and all countersinks to final dimension. d Install these items : 1 strap (LH) D5347448420200 Item 022 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 608 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 strap (RH) D5347448420300 Item 024 with : 58 rivet LN9198-4012CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : Four items of the fasteners, Item 806 and 865, are contained in Kit 281132D41R00, refer to para. (7) (p) 4c. 3 Install the fittings at FR51 at STGR37LH/RH as shown in Section D1-D5 ’AFTER’ :

a Put these items at FR51 in position : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018

bTransfer drill the holes from the frame to the fittings and open all holes to final dimension.

c Install these items : 1 fitting (LH) D5347449420600 Item 016 1 fitting (RH) D5347449420700 Item 018 with : 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Install the crossbeam at FR51 as shown in Section D1-D5’AFTER’ :

a Put these items at FR51 in position : 1 plate D5337217620000 Item 012 2 filler D5337217620800 Item 026 1 crossbeam D5347035300600 Item 076 1 plate D5337217620700 Item 078

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 076, IS IN LINE WITH THE CROSSBEAMS AND FR47 AND FR55. bTransfer drill all holes from the frame to the crossbeam.

c Put this item at FR51 in position as shown in Section B5-B5 : 1 support angle D5347658420000 Item 102 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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d Put these items at FR51 between STGR42LH and STGR42RH in position : 1 angle D5347470520000 Item 054 1 angle D5347470520100 Item 056 1 web D5347470420200 Item 080

eTransfer drill the holes from the frame and skin panel to the shear web and the supports. f Drill all additional holes and open all holes and all countersinks to final dimension. g Install these items : 1 plate D5337217620000 Item 012 2 filler D5337217620800 Item 026 1 angle D5347470520000 Item 054 1 angle D5347470520100 Item 056 1 crossbeam D5347035300600 Item 076 1 plate D5337217620700 Item 078 1 web D5347470420200 Item 080 1 support angle D5347658420000 Item 102 with : 12 rivet MBBN4477-4812 Item 549 16 rivet LN9198-4014CF Item 640 57 rivet LN9198-4816CF Item 648

6 pin DAN5-6-5X Item 765 44 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 12 collar NSA5075-8 Item 808 19 pin DAN5-6-4 Item 964 21 pin DAN5-6-5 Item 965

2 pin DAN5-6-6 Item 966 2 pin DAN5-6-8 Item 968 6 pin DAN5-8-5 Item 985 3 pin DAN5-8-6 Item 986 3 pin DAN5-8-7 Item 987 5 Install the sections and the angles at FR51 between STGR34LH/RH and STGR42LH/RH as shown in Section D1-D5 ’AFTER’:

a Put these items in position : 1 section D5347449520300 Item 028 1 section D5347449520500 Item 032 1 angle D5347470020400 Item 044 2 angle D5347470020200 Item 048 2 angle D5347449522000 Item 062 1 angle D5347470021600 Item 082 1 angle D5347470021800 Item 084 1 angle D5347470024800 Item 086 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 610 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 angle D5347470022000 Item 088 1 angle D5347470021400 Item 090 1 angle D5347470022200 Item 092 1 section D5347470022400 Item 094 1 section D5347470023000 Item 096 2 angle D5347470022800 Item 098 1 angle D5347470022600 Item 100

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel and install with these items : 34 rivet MBBN4477-4812 Item 549 62 rivet LN9198-4816CF Item 648

4 pin DAN6-6-7X Item 667 4 pin DAN6-6-9X Item 669 27 collar NSA5075-6 Item 806

8 collar DAN11-6X Item 807 17 pin DAN6-6-5 Item 865 10 pin DAN6-6-7 Item 867 6 Replace the riveting between clip and skin panel at FR51 between STGR40LH/RH and STGR42LH/RH as shown in Section D1-D5 ’AFTER’ :

a Remove the existing rivets. bOpen the holes and the countersinks to final dimension.

c Install these items : 8 rivet MBBN4477-4812 Item 549 4 pin DAN6-6-7X Item 667 4 pin DAN6-6-9X Item 669 8 pin DAN6-6-8Y Item 678 8 collar NSA5330-6 Item 803 8 collar DAN11-6X Item 807 7 Replace the riveting between stringer and skin panel at FR51 at STGR41RH as shown in Detail A5-A5 :

a Remove the existing rivets. bOpen the holes and the countersinks to final dimension.

c Install these items : 8 pin DAN6-6-8Y Item 678 8 collar NSA5330-6 Item 803 (ab) Modify the structure at FR52 between STGR34LH and STGR34RH. Refer to Kit 281132D06R01

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 611 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s) : D53470076004 Sheet(s) 2, 6 and 7 1 Replace the fasteners at FR52 between STGR34RH and STGR36RH as shown in Section A1-A2 ’AFTER’ :

a Remove the affected fasteners between STGR34RH and STGR36RH as shown in Section A1-A2 ’AFTER’. NOTE : Do not remove all fasteners at the same time. Replace the fasteners step by step. bOpen the affected holes to final dimension.

c Install these items : 24 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863 15 pin DAN5-6-3 Item 963

5 pin DAN5-6-4 Item 964 NOTE : The collars, Item 806, and the fasteners, Item 865, will be installed during the installation of the reinforcing straps at FR52. 2 Install the reinforcing straps at FR52 between STGR35LH/RH and STGR42LH/RH as shown in Section A1-A2 ’AFTER’ :

a Put these items at FR52 in position : 1 strap (LH) D5347448420200 Item 202 1 strap (RH) D5347448420300 Item 203

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes to final dimension. d Install these items : 1 strap (LH) D5347448420200 Item 202 1 strap (RH) D5347448420300 Item 203 with : 58 rivet LN9198-4012CF Item 640

8 collar NSA5075-6 Item 806 8 pin DAN6-6-5 Item 865 NOTE : The collars and the fasteners, Item 806 and Item 865, are supplied in Kit 281132D08R00.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 612 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

3 Install the fittings at FR52 at STGR37LH/RH as shown in Section A1-A2 ’AFTER’ :

a Put these items at FR52 in position : 1 fitting (LH) D5347449420600 Item 200 1 fitting (RH) D5347449421100 Item 201

bTransfer drill the holes from the frame to the fittings and open all holes to final dimension.

c Install these items : 1 fitting (LH) D5347449420600 Item 200 1 fitting (RH) D5347449421100 Item 201 with : 34 collar NSA5075-6 Item 806 14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965 8 pin DAN5-6-6 Item 966 4 pin DAN5-6-7 Item 967 4 Reinforce the crossbeam attachment at FR52 as shown in Section A1-A2 ’AFTER’ :

a Remove the crossbeam from FR52 temporarily. b Put these items with the removed crossbeam at FR52 in position : 1 fitting D5347449320000 Item 010 1 reinforcing sheet D5337217620000 Item 012 1 L-profile D5347449521600 Item 014 1 fitting D5347658920000 Item 016 1 shim D5347659220000 Item 018 1 fitting D5347659020000 Item 020 1 shim D5337217620800 Item 032 2 shim D5337217620400 Item 038 1 shim D5347658220200 Item 048 1 support D5347037820400 Item 204 1 fitting D5347449920200 Item 206 1 fitting D5347449820400 Item 244

CAUTION : ENSURE THAT THE CROSSBEAM IS IN LINE WITH THE CROSSBEAMS AT FR47 AND FR55.

c Transfer drill all holes from the frame. d Put these items at FR52 between STGR42LH and STGR42RH in position : 1 support D5347470520000 Item 040 1 support D5347470520100 Item 041 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 613 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 web D5347657720000 Item 208

eTransfer drill the holes from the frame and skin panel to the shear web and the supports. f Drill all additional holes and open all holes to final dimension. g Install the crossbeam with these items at FR52 as shown in Section A1-A2 ’AFTER’ : 1 fitting D5347449320000 Item 010 1 reinforcing sheet D5337217620000 Item 012 1 L-profile D5347449521600 Item 014 1 fitting D5347658920000 Item 016 1 shim D5347659220000 Item 018 1 fitting D5347659020000 Item 020 1 shim D5337217620800 Item 032 2 shim D5337217620400 Item 038 1 support D5347470520000 Item 040 1 support D5347470520100 Item 041 1 shim D5347658220200 Item 048 1 support D5347037820400 Item 204 1 fitting D5347449920200 Item 206 1 web D5347657720000 Item 208 1 fitting D5347449820400 Item 244 with : 12 rivet MBBN4477-4810 Item 549

6 rivet LN9198-4014CF Item 640 39 rivet LN9198-4816CF Item 648

6 rivet LN9198-6412CF Item 664 6 pin DAN5-6-5X Item 765 65 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 9 collar NSA5075-8 Item 808 10 pin DAN5-6-3 Item 963 15 pin DAN5-6-4 Item 964 37 pin DAN5-6-5 Item 965

1 pin DAN5-6-6 Item 966 2 pin DAN5-6-7 Item 967 3 pin DAN5-8-5 Item 985 4 pin DAN5-8-6 Item 986 2 pin DAN5-8-7 Item 987 5 Install this item at the crossbeam at FR52 as shown in drawing D53470076004, Sheet 7, Detail X1-7 :

a Drill the two holes and open the holes to final dimension. b Install this item : 2 rivet LN9198-4014CF Item 640 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 614 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

6 Replace the fasteners at FR52 between STGR41LH/RH and STGR42LH/RH :

a Remove the fasteners as shown in Section A1-A2 ’BEFORE’. bOpen the holes to final dimension.

c Install these items as shown in Section A1-A2 ’AFTER’ : 10 rivet LN9198-4816CF Item 648 7 Install the L-profiles and the angles at FR52 between STGR34LH/RH and STGR42LH/RH as shown in Section A1-A2 ’AFTER’ :

a Put these items in position : 2 angle D5347470020200 Item 022 1 angle D5347470020300 Item 023 1 angle D5347470020400 Item 024 1 L-profile D5347449520400 Item 026 1 L-profile D5347449520500 Item 027 1 L-profile D5347449520300 Item 028 1 angle D5347470021400 Item 030 1 angle D5347470023200 Item 034 1 angle D5347470023400 Item 036 1 angle D5347470021000 Item 042 1 angle D5347470021200 Item 044 1 angle D5347470024000 Item 046 1 angle D5347470023800 Item 050 1 angle D5347470023600 Item 052 1 key D5347550021000 Item 082

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items : 2 angle D5347470020200 Item 022 1 angle D5347470020300 Item 023 1 angle D5347470020400 Item 024 1 L-profile D5347449520400 Item 026 1 L-profile D5347449520500 Item 027 1 L-profile D5347449520300 Item 028 1 angle D5347470021400 Item 030 1 angle D5347470023200 Item 034 1 angle D5347470023400 Item 036 1 angle D5347470021000 Item 042 1 angle D5347470021200 Item 044 1 angle D5347470024000 Item 046 1 angle D5347470023800 Item 050 1 angle D5347470023600 Item 052 1 key D5347550021000 Item 082 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 615 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

with : 43 rivet MBBN4477-4810 Item 549 59 rivet LN9198-4816CF Item 648 23 collar NSA5075-6 Item 806

8 pin DAN6-6-3 Item 863 1 pin DAN6-6-5 Item 865 10 pin DAN6-6-6 Item 866

3 pin DAN6-6-7 Item 867 1 pin DAN6-6-8 Item 868 8 Replace the riveting between clip and skin panel at FR52 between STGR35LH/RH and STGR42LH/RH as shown in Section A1-A2 ’AFTER’ :

a Remove the existing rivets. bOpen the holes and the countersinks to final dimension.

c Install these items : 25 rivet MBBN4477-4810 Item 549 27 collar NSA5075-6 Item 806

8 pin DAN6-6-3 Item 863 4 pin DAN6-6-4 Item 864 1 pin DAN6-6-5 Item 865 10 pin DAN6-6-6 Item 866

3 pin DAN6-6-7 Item 867 1 pin DAN6-6-8 Item 868 (ac) Modify the structure at FR52A between STGR38RH and STGR40RH. Refer to Kit 281132D06R01 Refer to Drawing(s) : D53470076004 Sheet(s) 3 1 Remove these items from FR52A as shown in drawing D53470076004, Sheet 3, Detail A3-3 and Section B1-B3 ’BEFORE’.

a Remove and discard these items : 1 nut NAS1791A3-1 Item (460) Discard 1 nut NAS1068C3 Item (462) Discard

bClose the existing rivet holes with this item : 4 rivet DIN65399-2400CF Item 724 2 Close the existing rivet holes at FR52A as shown in drawing D53470076004, Sheet 3, Detail B3-3 ’AFTER’.

a Install these items : 2 pin DAN6-6-5X Item 665 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 616 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 collar DAN11-6X Item 807 3 Install the fitting at FR52A as shown in drawing D53470076004, Sheet 3, Section B1-B3 ’AFTER’.

a Put this item at FR52A in position : 1 fitting D5347659320000 Item 054

b Drill all additional holes and open all holes to final dimension.

c Install this item at FR52A : 1 fitting D5347659320000 Item 054 with these items : 11 collar NSA5075-6 Item 806

5 pin DAN5-6-4 Item 964 3 pin DAN5-6-6 Item 966 3 pin DAN5-6-9 Item 969 (ad) Modify the structure at FR53 between STGR34LH and STGR41RH. Refer to Kit 281132D06R01 Refer to Drawing(s) : D53470076004 Sheet(s) 4 1 Install the fitting at FR53 at STGR37LH as shown in Section C1-C4 ’AFTER’ :

a Put this item at FR53 in position : 1 fitting (LH) D5347449420600 Item 200

bTransfer drill the holes from the frame to the fitting and open all holes to final dimension.

c Install this item : 1 fitting (LH) D5347449420600 Item 200 with : 17 collar NSA5075-6 Item 806

7 pin DAN5-6-4 Item 964 4 pin DAN5-6-5 Item 965 4 pin DAN5-6-6 Item 966 2 pin DAN5-6-7 Item 967 2 Install the crossbeam at FR53 as shown in Section C1-C4 ’AFTER’ :

a Put these items at FR53 in position : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 617 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 plate D5337217621000 Item 056 1 shim D5337217621200 Item 060 1 crossbeam D5347026100600 Item 218

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 218, IS IN LINE WITH THE CROSSBEAMS AND FR47 AND FR55. bTransfer drill all holes from the frame.

c Put these items at FR53 between STGR42LH and STGR42RH in position : 1 support D5347470520300 Item 066 1 web D5347657820000 Item 068 1 web D5347658820000 Item 070 1 support D5347470520500 Item 104

dTransfer drill the holes from the frame and skin panel to the shear web and the supports.

e Drill all additional holes and open all holes to final dimension. f Install these item : 1 plate D5337217621000 Item 056 1 shim D5337217621200 Item 060 1 support D5347470520300 Item 066 1 web D5347657820000 Item 068 1 web D5347658820000 Item 070 1 support D5347470520500 Item 104 1 crossbeam D5347026100600 Item 218 with : 4 rivet MBBN4477-4010 Item 541 13 rivet MBBN4477-4810 Item 549

4 rivet LN9198-4014CF Item 640 42 rivet LN9198-4816CF Item 648

3 pin DAN5-6-5X Item 765 30 collar NSA5075-6 Item 806

6 collar DAN11-6X Item 807 6 collar NSA5075-8 Item 808 3 pin DAN5-6-3 Item 963 11 pin DAN5-6-4 Item 964 12 pin DAN5-6-5 Item 965

2 pin DAN5-6-6 Item 966 3 pin DAN5-8-5 Item 985 4 pin DAN5-8-6 Item 986 2 pin DAN5-8-7 Item 987 3 Replace the fasteners at FR53 between STGR41LH and STGR42LH :

a Remove the fasteners as shown in Section C1-C4 ’BEFORE’. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 618 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

bOpen the holes to final dimension.

c Install this item as shown in Section C1-C4 ’AFTER’ : 5 rivet LN9198-4816CF Item 648 4 Install the L-profiles and the angles at FR53 between STGR34LH and STGR41RH as shown in Section C1-C4 ’AFTER’ :

a Put these items in position : 2 angle D5347470020200 Item 022 1 angle D5347470020400 Item 024 1 L-profile D5347449520500 Item 027 1 L-profile D5347449520300 Item 028 1 angle D5347470024200 Item 058 1 angle D5347470024400 Item 062 1 angle D5347470024600 Item 064 1 L-profile D5347449523800 Item 094 1 L-profile D5347449523400 Item 096 2 L-profile D5347449524000 Item 098 1 L-profile D5347449524200 Item 100 1 shim D5347044922600 Item 106 3 shim D5347044922800 Item 108

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items : 2 angle D5347470020200 Item 022 1 angle D5347470020400 Item 024 1 L-profile D5347449520500 Item 027 1 L-profile D5347449520300 Item 028 1 angle D5347470024200 Item 058 1 angle D5347470024400 Item 062 1 angle D5347470024600 Item 064 1 L-profile D5347449523800 Item 094 1 L-profile D5347449523400 Item 096 2 L-profile D5347449524000 Item 098 1 L-profile D5347449524200 Item 100 1 shim D5347044922600 Item 106 3 shim D5347044922800 Item 108 with : 41 rivet MBBN4477-4810 Item 549 40 rivet LN9198-4816CF Item 648 16 collar NSA5075-6 Item 806 12 pin DAN6-6-3 Item 863

4 pin DAN5-6-3 Item 963 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 619 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

5 Replace the riveting between clip and skin panel at FR53 between STGR34LH and STGR42LH and between STGR41RH and STGR42RH as shown in Section C1-C4 :

a Remove the existing rivets. bOpen the holes and the countersinks to final dimension.

c Install these items : 28 rivet MBBN4477-4810 Item 549 12 collar NSA5075-6 Item 806 12 pin DAN6-6-3 Item 863 (ae) Modify the structure at FR53 between STGR36LH and STGR42LH. Refer to Kit 281132D40R03 Refer to Kit 281132G10R02 Refer to Drawing(s) : D53470075002 Sheet(s) 1 and 6 1 Remove this item at FR53 as shown in Section E1-E6 ’BEFORE’ :

a Remove and discard this item : 1 shim D5347061120200 Item (402) Discard 2 Install the reinforcing strap at FR53 between STGR35LH and STGR42LH as shown in Section E1-E6 ’AFTER’ :

a Put this item at FR53 in position : 1 strap D5347448420200 Item 022

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all holes and all countersinks to final dimension. d Install these items : 1 strap D5347448420200 Item 022 with : 29 rivet LN9198-4014CF Item 640

4 collar NSA5075-6 Item 806 4 pin DAN6-6-5 Item 865 NOTE : The collars and fasteners, Item 806 and 865, are supplied in Kit 281132D08R00. (af) Modify the structure at FR54 between STGR34LH and STGR41RH. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 620 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Kit 281132D06R01 Refer to Drawing(s) : D53470076004 Sheet(s) 1 and 5 1 Install the reinforcing strap at FR54 between STGR35LH and STGR42LH as shown in Section D1-D5 ’AFTER’ :

a Put this item at FR54 in position : 1 strap (LH) D5347448420200 Item 202

bTransfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing strap to the frame and open all holes to final dimension. d Install this item : 1 strap (LH) D5347448420200 Item 202 with : 29 rivet LN9198-4014CF Item 640

4 collar NSA5075-6 Item 806 4 pin DAN6-6-5 Item 865 NOTE : The collars and the fasteners, Item 806 and Item 865, are supplied in Kit 281132D08R00. 2 Install the fitting at FR54 at STGR37LH as shown in Section D1-D5 ’AFTER’ :

a Put this item at FR54 in position : 1 fitting (LH) D5347449420600 Item 200

bTransfer drill the holes from the frame to the fitting and open all holes to final dimension.

c Install this item : 1 fitting (LH) D5347449420600 Item 200 with : 17 collar NSA5075-6 Item 806

7 pin DAN5-6-4 Item 964 4 pin DAN5-6-5 Item 965 4 pin DAN5-6-6 Item 966 2 pin DAN5-6-7 Item 967 3 Install the crossbeam at FR54 as shown in Section D1-D5 ’AFTER’ : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 621 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

a Put these items at FR54 in position : 1 shim D5337217621200 Item 060 1 plate D5337217625800 Item 110 1 crossbeam D5347035601400 Item 230

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 230, IS IN LINE WITH THE CROSSBEAMS AT FR47 AND FR55. bTransfer drill all holes from the frame.

c Put these items at FR54 between STGR42LH and STGR42RH in position : 1 web D5347657920200 Item 076 1 L-profile D5347449522600 Item 078 1 L-profile D5347449522800 Item 080

dTransfer drill the holes from the frame and skin panel to the shear web and the L-profile.

e Drill all additional holes and open all holes and all countersinks to final dimension. f Install these items : 1 shim D5337217621200 Item 060 1 web D5347657920200 Item 076 1 L-profile D5347449522600 Item 078 1 L-profile D5347449522800 Item 080 1 plate D5337217625800 Item 110 1 crossbeam D5347035601400 Item 230 with : 4 rivet MBBN4477-4010 Item 541 16 rivet MBBN4477-4810 Item 549

8 rivet LN9198-4014CF Item 640 42 rivet LN9198-4816CF Item 648

3 pin DAN5-6-5X Item 765 28 collar NSA5075-6 Item 806

3 collar DAN11-6X Item 807 9 collar NSA5075-8 Item 808 10 pin DAN5-6-4 Item 964 16 pin DAN5-6-5 Item 965

2 pin DAN5-6-6 Item 966 3 pin DAN5-8-5 Item 985 4 pin DAN5-8-6 Item 986 2 pin DAN5-8-7 Item 987 4 Replace the fasteners at FR54 between STGR41LH and STGR42LH :

a Remove the fasteners as shown in Section D1-D5 ’BEFORE’. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 622 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

bOpen the holes to final dimension.

c Install this item as shown in Section D1-D5 ’AFTER’ : 6 rivet LN9198-4816CF Item 648 5 Install the L-profile and the angles at FR54 between STGR34LH and STGR42LH as shown in Section D1-D5 ’AFTER’:

a Put these items in position : 2 angle D5347470020200 Item 022 1 angle D5347470020400 Item 024 1 L-profile D5347449520500 Item 027 1 L-profile D5347449520300 Item 028 1 angle D5347470024200 Item 058 1 angle D5347470025000 Item 072 1 angle D5347470025200 Item 074

b Drill the additional holes and open the holes to final dimension.

c Countersink the holes in the skin panel. d Install these items : 2 angle D5347470020200 Item 022 1 angle D5347470020400 Item 024 1 L-profile D5347449520500 Item 027 1 L-profile D5347449520300 Item 028 1 angle D5347470024200 Item 058 1 angle D5347470025000 Item 072 1 angle D5347470025200 Item 074 with : 23 rivet MBBN4477-4810 Item 549 29 rivet LN9198-4816CF Item 648 12 collar NSA5075-6 Item 806 12 pin DAN6-6-3 Item 863 6 Replace the riveting between clip and skin panel at FR54 between STGR34LH and STGR42LH as shown in Section D1-D5 ’AFTER’ :

a Remove the existing rivets. bOpen the holes and the countersinks to final dimension.

c Install these items : 23 rivet MBBN4477-4810 Item 549 12 collar NSA5075-6 Item 806 12 pin DAN6-6-3 Item 863 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 623 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(ag) Install the shear plates between FR48 and FR51 at STGR43LH. Refer to Kit 281132D40R03 Refer to Kit 281132G10R02 Refer to Drawing(s) : D53470075002 Sheet(s) 1, 3 and 7 1 Install the shear plate between FR48 and FR49 at STGR43LH as shown in Section F1-F7 :

a Put this item in position : 1 plate D5347471321200 Item 104

b Put this item in position as shown in Sheet 3, Section B1-B3 : 1 section D5347449521800 Item 020

c Transfer drill the holes to the section, Item 020. d Drill the additional holes from the shear plate to the stringer and crossbeams and open all holes to final dimension.

e Install these items : 1 section D5347449521800 Item 020 1 plate D5347471321200 Item 104 with : 34 rivet LN9198-4014CF Item 640

2 rivet LN9198-4816CF Item 648 2 collar NSA5075-6 Item 806 2 pin DAN5-6-7 Item 967 2 Install the shear plates between FR49 and FR51 at STGR43LH as shown in Section F1-F7 : Refer to Drawing(s) : D53470075002 Sheet(s) 1, 4, 5 and 7

a Put this item in position : 1 angle D5347471322400 Item 138 1 angle D5347471322600 Item 140

b Put this item in position as shown in Sheet 4, Section C1-C4 and Sheet 5, Section D1-D5. 2 section D5347449522000 Item 062

c Transfer drill the holes to the sections, Item 062. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 624 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

d Drill the additional holes from the shear plate to the stringer and crossbeams and open all holes to final dimension.

e Install these items : 2 section D5347449522000 Item 062 1 angle D5347471322400 Item 138 1 angle D5347471322600 Item 140 with : 59 rivet LN9198-4014CF Item 640

4 rivet LN9198-4816CF Item 648 4 collar NSA5075-8 Item 808 4 pin DAN5-8-7 Item 987 (ah) Install the shear plates between FR51 and FR54 at STGR43LH. Refer to Kit 281132D06R01 Refer to Drawing(s) : D53470076004 Sheet(s) 1 thru 6 1 Install the shear plate between FR51 and FR52 at STGR43LH as shown in drawing D53470076004, Sheet 6, Section E1-E6 ’AFTER’, and Sheet 2, Section A1-A2 ’AFTER’:

a Put these items in position : 1 shear plate D5347471320800 Item 084 1 L-profile D5347449522000 Item 088

bTransfer drill the holes to the L-profile, Item 088.

c Drill the additional holes from the shear plate to the stringer and crossbeams and open all holes to final dimension. d Install these items : 1 shear plate D5347471320800 Item 084 1 L-profile D5347449522000 Item 088 with : 29 rivet LN9198-4014CF Item 640

7 rivet LN9198-4816CF Item 648 2 collar NSA5075-8 Item 808 2 pin DAN5-8-7 Item 987 2 Install the shear plate between FR52 and FR53 at STGR43LH as shown in drawing D53470076004, Sheet 6, Section E1-E6, and Sheet 4, Section C4-C4 ’AFTER’.

a Put these items in position : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 L-profile D5347449522200 Item 090 1 shear plate D5347471321800 Item 102

bTransfer drill the holes to the L-profile, Item 090.

c Drill the additional holes from the shear plate to the stringer and crossbeams and open all holes to final dimension. d Install these items : 1 L-profile D5347449522200 Item 090 1 shear plate D5347471321800 Item 102 with : 29 rivet LN9198-4014CF Item 640

7 rivet LN9198-4816CF Item 648 2 collar NSA5075-8 Item 808 2 pin DAN5-8-7 Item 987 3 Install the shear plate between FR53 and FR54 at STGR43LH as shown in drawing D53470076004, Sheet 6, Section E1-E6, and Sheet 5, Section D1-D5 ’AFTER’.

a Put these items in position as shown in drawing D53470076004, Sheet 6, Section E1-E6 : 1 shear plate D5347471320800 Item 084 1 L-profile D5347449522000 Item 088

bTransfer drill the holes, drill the additional holes and open all holes to final dimension.

c Install these items : 1 shear plate D5347471320800 Item 084 1 L-profile D5347449522000 Item 088 with : 29 rivet LN9198-4014CF Item 640

7 rivet LN9198-4816CF Item 648 2 collar NSA5075-8 Item 808 2 pin DAN5-8-7 Item 986 (ai) Drill additional fastener holes between FR51 and FR54. D53470076004 Sheet(s) 7 1 Drill additional fastener holes between FR51 and FR54, refer to drawing D53470076004, Sheet 7, Detail X1-7. (aj) Modify the structure between FR47 and FR48 at STGR38LH/RH and STGR43LH. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 626 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Kit 281132D05R01 Refer to Drawing(s) : D53372362004 Sheet(s) 7 1 Remove the nuts at STGR38LH and STGR38RH as shown in Detail W1-7.

a Remove and discard this item : 6 nut NAS1791A3-1 Item (216) Discard 2 Remove the connections at STGR38LH and STGR38RH as shown in Detail W1-7.

a Remove and discard these items : 1 connection (LH) D5347101620400 Item (210) Discard 1 connection (RH) D5347101620500 Item (211) Discard 3 Install the plates, the sections and the connections at STGR38LH and STGR38RH as shown in Detail W1-7.

aAt STGR38LH : Put these items in position : 1 plate D5337217400000 Item 024 1 section D5347449520800 Item 028 1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620490 Item 042 NOTE : Install the fillers, Item 030, 032, 034, 036 and 038, as required. NOTE : Install the section, Item 028, together with the angle, Item 130. bAt STGR38RH : Put these items in position : 1 plate D5337217400100 Item 025 1 section D5347449520900 Item 029 1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620590 Item 043 NOTE : Install the fillers, Item 030, 032, 034, 036 and 038, as required. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 627 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

NOTE : Install the section, Item 029, together with the angle, Item 134, at FR48.

cTransfer drill the holes from the skin panel and the stringer to the connections. d Drill the additional holes in the plates, sections and connections and open all holes and all countersinks to final dimension.

e Install these items at STGR38LH : 1 plate D5337217400000 Item 024 1 section D5347449520800 Item 028 1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620490 Item 042 with : 6 rivet NAS1097AD4-10 Item 532 21 rivet LN9198-4014CF Item 640

1 pin DAN5-6-6X Item 766 4 pin DAN5-6-7X Item 767 13 pin DAN5-6-8X Item 768

1 pin DAN5-6-9X Item 769 6 collar NSA5075-6 Item 806 19 collar DAN11-6X Item 807

4 pin DAN5-6-5 Item 965 2 pin DAN5-6-9 Item 969

f Install these items at STGR38RH : 1 plate D5337217400100 Item 025 1 section D5347449520900 Item 029 1 filler D5337601520600 Item 030 1 filler D5337601520800 Item 032 1 filler D5337601521000 Item 034 1 filler D5337601521200 Item 036 1 filler D5337601521400 Item 038 1 connection D5347101620590 Item 043 with : 6 rivet NAS1097AD4-10 Item 532 21 rivet LN9198-4014CF Item 640

1 pin DAN5-6-6X Item 766 4 pin DAN5-6-7X Item 767 13 pin DAN5-6-8X Item 768

1 pin DAN5-6-9X Item 769 6 collar NSA5075-6 Item 806 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 628 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

19 collar DAN11-6X Item 807

4 pin DAN5-6-5 Item 965 2 pin DAN5-6-9 Item 969 4 Remove the connection at STGR43LH as shown in Detail V1-7.

a Remove and discard this item : 1 connection D5347100720400 Item (208) Discard 5 Install the plate, the section and the coupling at STGR43LH as shown in Detail V1-7.

a Put these items at STGR43LH in position : 1 plate D5337217320000 Item 022 1 section D5337216020000 Item 026 1 coupling D5347100720600 Item 040

bTransfer drill the holes from STGR43 to the plate and the connection.

c Drill all additional holes in the plate and the section and open all holes and all countersinks to final dimension. d Install these items : 1 plate D5337217320000 Item 022 1 section D5337216020000 Item 026 1 coupling D5347100720600 Item 040 with : 34 rivet LN9198-4014CF Item 640

4 pin DAN5-6-7X Item 767 4 pin DAN5-6-8X Item 768 2 collar NSA5075-6 Item 806 8 collar DAN11-6X Item 807 16 collar DAN11-8X Item 810

1 pin DAN5-8-8X Item 888 4 pin DAN5-8-9X Item 889 10 pin DAN5-8-10X Item 890

1 pin DAN5-8-11X Item 891 2 pin DAN5-6-7 Item 967 (ak) Install the plates between FR48 and FR59 at STGR38LH and STGR38RH. Refer to Kit 281132D40R03 Refer to Kit 281132G10R02 Refer to Drawing(s) : D53470075002 Sheet(s) 1 thru 14 1 Install the plates and the angles between FR48 and FR59 at STGR38LH as shown in Sections H1-H8, J1-J11 and K1-K11 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 629 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s) : D53470075002 Sheet(s) 1, 8 and 11

a Put these items in position : 2 plate D5347471500200 Item 108 1 plate D5347471500000 Item 110 1 plate D5347471500600 Item 112 1 plate D5347471500800 Item 114 1 plate D5347471501000 Item 116 6 angle D5347470120000 Item 128 6 angle D5347470120200 Item 130

1 plate D5347063721600 Item 206 1 section D5347065020400 Item 208 1 plate D5347048700200 Item 210 1 plate D5347048500400 Item 212 1 plate D5347048800400 Item 214 1 plate D5347048900400 Item 216 1 plate D5347049200400 Item 218 2 angle D5347046824000 Item 228 1 angle D5347046823800 Item 230 1 angle D5347046823600 Item 232 1 angle D5347046824200 Item 234 1 angle D5347046824400 Item 236 NOTE : Install the angle, Item 130, together with the section, Item 028. bTransfer drill the holes from the stringer and frames to the plates and the angles.

c Transfer drill the holes from the skin panel to the section at FR52. d Drill the additional holes and open all holes to final dimension.

e Install the listed items as shown in Sections H1-H8 and K1-K11 with : 227 rivet LN9198-4014CF Item 640 4 pin DAN6-6-5X Item 665 3 pin DAN6-6-6X Item 666 3 pin DAN6-6-7X Item 667 5 pin DAN5-6-4X Item 764 8 pin DAN5-6-6X Item 766 3 pin DAN5-6-8X Item 768 16 collar NSA5075-6 Item 806 26 collar DAN11-6X Item 807 10 pin DAN5-6-4 Item 964

6 pin DAN5-6-8 Item 968

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 630 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 Install the plates and angles between FR48 and FR59 at STGR38RH as shown in Sections G1-G8 and J1-J11: Refer to Drawing(s) : D53470075002 Sheet(s) 8 and 11

a Put these items in position : 2 plate D5347471500300 Item 118 1 plate D5347471500100 Item 120 1 plate D5347471503200 Item 122 1 plate D5347471501200 Item 124 1 angle D5347659100000 Item 126 4 angle D5347470120100 Item 132 5 angle D5347470120300 Item 134 1 section D5347066920600 Item 136 1 shim D5347236320200 Item 202 1 section D5347063721600 Item 206 1 plate D5347048700200 Item 210 1 plate D5347048500400 Item 212 1 angle D5347046824500 Item 220 1 angle D5347046824300 Item 222 1 angle D5347046824600 Item 224 NOTE : Install the angle, Item 134, together with the section, Item 029, at FR48. bTransfer drill the holes from the stringer and frames to the plates and the angles and open all holes to final dimension.

c Install the listed items as shown in Sections G1-G8 and J1-J17 with : 106 rivet LN9198-4014CF Item 640 2 pin DAN6-6-6X Item 666 2 pin DAN6-6-7X Item 667 2 pin DAN6-6-8X Item 668 6 pin DAN5-6-6X Item 766 1 pin DAN5-6-8X Item 768 3 collar NSA5075-5 Item 804 19 collar NSA5075-6 Item 806 28 collar DAN11-6X Item 807

2 pin DAN6-6-4 Item 864 11 pin DAN6-6-5 Item 865

3 pin DAN5-5-5 Item 945 4 pin DAN5-6-4 Item 964 2 pin DAN5-6-8 Item 968 (al) Install the corner sections at STGR38LH/RH between FR48 and FR59. Refer to Kit 281132D40R03 Refer to Kit 281132G10R02 Refer to Drawing(s) : D53470075002 Sheet(s) 1, 9 and 10 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 631 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Install the corner sections at STGR38LH between FR48 and FR59 as shown in Details X9-10 :

a Put these items between FR48 and FR56 in position : 1 section D5347047500800 Item 154 1 section D5347047600800 Item 156

bTransfer drill the holes from the fittings to the corner sections as shown in Details A1-A2, B1-B3 and C1-C4.

c Drill the holes from the corner sections to the plates between FR48 and FR59 as shown in Details X9-10, T10-10 and U10-10 . d Open the holes to final dimension and countersink the holes.

e Install these items : 1 section D5347047500800 Item 154 1 section D5347047600800 Item 156 with : 16 rivet MBBN4477-4012 Item 541 12 rivet MBBN4477-4812 Item 549 87 rivet DIN65399-3200CF Item 732 f The holes with 5.6 mm (0.220 in.) diameter between FR48 and FR51 as shown in Detail X9-10 will transfer from the roller tracks. 2 Install the corner section at STGR38RH between FR48 and FR59 as shown in Details Z9-10 and Y9-10 :

a Put this item between FR48 and FR52A in position : 1 section D5347048100600 Item 152

bTransfer drill the holes from the fittings to the corner section as shown in Details A1-A2, B1-B3, C1-C4 and D1-D5

c Drill the holes from the corner section to the plates between FR48 and FR59 as shown in Details Z9-Z10 and Y9-10. d Open the holes to final dimension and countersink the holes.

e Install these items : 1 section D5347048100600 Item 152 with : 8 rivet MBBN4477-4012 Item 541 12 rivet MBBN4477-4812 Item 549 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 632 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

48 rivet DIN65399-3200CF Item 732 f The holes with 5.6 mm (0.220 in.) diameter between FR48 and FR51 as shown in Detail Z9-Z10 will transfer from the roller tracks. (am) Modify the crossbeams from FR48 thru FR52 for the roller track installation. Refer to Kit 281132D40R03 Refer to Kit 281132G10R02 Refer to drawings : D53470075002 Sheet(s) 9 and 10 1 Drill the holes in the crossbeams at FR48, FR49, FR50 and FR51 as shown in Details U9-9 and W9-9 :

a Mark and drill the holes with 5.6 mm (0.220 in.). 2 Install the nuts, Item 508, at the crossbeam at FR52 as shown in Details A10-A10, V10-10 and W1-10 :

a Mark and drill the holes with 5.2 mm (0.205 in.). b Put the nuts in position, drill the rivet holes and install this item : 4 nut NAS1791A3-1 Item 508 with : 8 rivet DIN65399-2400CF Item 724 (an) Install the water drain connection between FR47 and FR48. Refer to Kit 281132D40R03 Refer to Kit 281132G10R02 Refer to Drawing(s) : D53372362008 Sheet(s) 9 D53470075002 Sheet(s) 1, 12 and 13 1 Make a cutout between 63.7 mm (2.508 in.) and 64.3 mm (2.531 in.) diameter in the skin panel between FR47 and FR48 and between STGR42RH and STGR43RH as shown in drawing D53470075004, Sheet 12, Sections C1-12 and A13-13. 2 Install the doubler at the outer skin as shown in the drawing D53470075002, Sheet 13, Section A12-A13 and Z12-12 and the drawing D53372362008, Sheet 9, Detail U1-9. NOTE : Drawing D53372362008 shows the position of the doubler and fasteners for the attachment. The fasteners are contained in Kit 281132D42R00.

a Remove the existing fasteners in the affected area. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 633 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

b Put this item in position as shown in drawing D53470075002, Sheet 13, Section A13-A13 and drawing D53372362008, Sheet 9, Detail U1-9 : 1 doubler D5347646320200 Item 160

c Transfer drill the holes. d Drill the additional holes and open all holes to final dimension as shown in drawing D53470075004, Sheet 13, Detail A13-13.

e Install this item : 1 doubler D5347646320200 Item 160 with : 33 rivet LN9198-4816CF Item 648 12 pin DAN5-6-8X Item 768 18 pin DAN5-6-9X Item 769

4 pin DAN5-6-11X Item 771 10 pin DAN5-6-12X Item 772 14 collar NSA5075-6 Item 806 44 collar DAN11-6X Item 807 18 collar DAN11-8X Item 810

4 pin DAN5-8-7X Item 887 6 pin DAN5-8-11X Item 891 8 pin DAN5-8-12X Item 892 14 pin DAN5-6-6 Item 966 NOTE : The Items 768, 769, 771, 772, 807, 810, 887, 891 and 892 are contained in Kit 281132D42R00. 3 Install the tube as shown in drawing D53470075002, Sheet 13, Section C1-12 and in Detail A13-13 :

a Put these items in position : 1 tube D5347669000000 Item 172 2 shim D5347472120000 Item 176

or 2 Shim D5347472120200 Item 176

bTransfer drill the eight holes as shown in drawing D53372362008, Sheet 30, Detail Z30-30.

c Drill the eight holes as shown in drawing D53470075002, Sheet 13, Detail Z13-13. d Open all holes to final dimension.

e Install these items : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 634 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 tube D5347669000000 Item 172 2 shim D5347472120000 Item 176

or 2 Shim D5347472120200 Item 176 with : 8 pin DAN5-6-11X Item 771 8 collar NSA5075-6 Item 806 8 collar DAN11-6X Item 807 2 pin DAN6-6-6 Item 866 6 pin DAN6-6-10 Item 870 NOTE : The Items 771 and 807 are contained in Kit 281132D42R00, refer to drawing D53372362008, Sheet 9. f Drill the four holes for the receptacles, Item 504, with 5.6 mm (0.220 in.) diameter as shown in drawing D53470075002, Sheet 13, Detail Z13-13 and install this item : 4 receptacle ABS0337-01A Item 504 with : 8 rivet DIN65399-2400CF Item 724

g Install at the tube, Item 172, as shown in drawing D53470075002, Sheet 13, Section A13-13 these items : 1 plate D5347669200000 Item 166 1 plug D5347669100000 Item 174 1 ring MS16625-4212 Item 500 1 screw NAS1096-3-10 Item 506 (ao) Install the water drain connection and the cavity drain access cover between FR49 and FR50. Refer to Kit 281132D40R03 Refer to Kit 281132G10R02 Refer to Drawing(s) : D53470075002 Sheet(s) 14 1 Make a cutout between 63.7 mm (2.508 in.) and 64.3 mm (2.531 in.) diameter in the skin panel between FR49 and FR50 and between STGR42LH and STGR43LH as shown in Sections B12-B14 and Detail A14-14. 2 Install the doubler at the outer skin as shown in Section B12-B14 : CAUTION : REMOVE THE EXISTING RIVETS CAREFULLY. THE HEADS OF THE RIVETS WILL BE USED DURING THE DOUBLER DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 635 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

INSTALLATION FOR THE EXISTING COUNTERSINKS IN THE SKIN PANEL.

a Remove the existing fasteners in the affected area. b Put this item in position as shown in Detail A14-14 : 1 doubler D5347646320000 Item 162

c Transfer drill the holes. d Drill the additional holes as shown in Detail A14-14 and open all holes to final dimension.

e Install this item : 1 doubler D5347646320000 Item 162 with : 48 rivet LN9198-4816CF Item 648

8 pin DAN5-6-8Y Item 778 8 collar NSA5330-6 Item 803 154 collar NSA5075-6 Item 806

25 pin DAN5-6-5 Item 965 58 pin DAN5-6-6 Item 966 14 pin DAN5-6-7 Item 967 57 pin DAN5-6-8 Item 968 3 Install the tube as shown in Section B12-B14 and Detail A14-14 :

a Put these items in position : 1 tube D5347669000000 Item 172 2 shim D5347472120000 Item 176

or 2 Shim D5347472120200 Item 176

bTransfer drill the eight holes from the stringers to the tube as shown in Detail Y14-14.

c Drill the eight holes as shown in Detail Y14-14. d Open all holes to final dimension.

e Install these items : 1 tube D5347669000000 Item 172 2 shim D5347472120000 Item 176

or DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 636 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 Shim D5347472120200 Item 176 with : 16 collar NSA5075-6 Item 806

2 pin DAN6-6-6 Item 866 6 pin DAN6-6-10 Item 870 8 pin DAN5-6-10 Item 970

f Drill the four holes for the receptacles, Item 504, with 5.6 mm (0.220 in.) diameter as shown in Detail Y14-14 and install this item : 4 receptacle ABS0337-01A Item 504 with : 8 rivet DIN65399-2400CF Item 724

g Install these items at the tube, Item 172, as shown in Section B12-B14 : 1 plate D5347669200000 Item 166 1 plug D5347669100000 Item 174 1 ring MS16625-4212 Item 500 1 screw NAS1096-3-10 Item 506 4 Make a cutout in the skin panel between FR49 and FR50 and between STGR40LH and STGR41LH as shown in Detail A14-14. 5 Install the nuts, Item 510, around the cutout as shown in Detail Z14-14 :

a Remove the six rivets in the stringer and open the holes to 5.6 mm (0.220 in.) diameter. b Drill the four holes with 5.6 mm (0.220 in.) diameter in the skin.

c Install these items : 4 shim D5347470220000 Item 178 10 nut NAS1474A3 Item 510 with : 20 rivet DIN65399-2400CF Item 724 d Install this item as shown in Section B12-B14 : 1 cover D5347470920200 Item 164 with : 10 screw NAS1153E7 Item 502

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 637 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(ap) Drill three holes in the outer skin between FR47 and FR49 and between STGR43LH and STGR42RH. Refer to Drawing(s) : D53470075002 Sheet(s) 12 1 Drill two holes with 20.0 mm (0.787 in.) diameter and one hole with 14.5 mm (0.578 in.) diameter as shown in Detail C1-12. (aq) Install the water drain connection between FR50 and FR51. Refer to Kit 281132D06R01 Refer to Drawing(s) : D53470076004 Sheet(s) 8 and 9 1 Make a cutout between 63.7 mm (2.508 in.) and 64.3 mm (2.531 in.) diameter in the skin panel between FR50 and FR51 and between STGR42RH and STGR43RH as shown in drawing D53470076004, Sheet 9, Sections A8-A9 and Detail A9-9. 2 Install the doubler at the outer skin as shown in the drawing D53470076004, Sheet 9, Section A8-A9. CAUTION : REMOVE THE EXISTING RIVETS CAREFULLY. THE HEADS OF THE RIVETS WILL BE USED DURING THE DOUBLER INSTALLATION FOR THE EXISTING COUNTERSINKS IN THE SKIN PANEL.

a Remove the existing fasteners in the affected area. b Put this item in position as shown in drawing D53470076004, Sheet 9, Section A8-A9 and Detail A9-9 : 1 doubler D5347646320400 Item 160

c Transfer drill the holes. d Drill the additional holes and open all holes to final dimension as shown in drawing D53470076004, Sheet 9, Detail A9-9.

e Install this item : 1 doubler D5347646320400 Item 160 with : 24 rivet MBBN4477-4810 Item 549

7 pin DAN6-6-6X Item 666 19 pin DAN6-6-7X Item 667 18 pin DAN6-6-8X Item 668

8 pin DAN Item 678 8 collar NSA5330-6 Item 803 23 collar NSA5075-6 Item 806 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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44 collar DAN11-6X Item 807 18 pin DAN6-6-5 Item 865

5 pin DAN6-6-6 Item 866 3 Install the tube as shown in drawing D53470076004, Sheet 9, Section A8-A9 and in Detail A9-9 :

a Put these items in position : 1 tube D5347669000000 Item 172 2 shim D5347472120200 Item 176

bTransfer drill the holes, drill the additional holes and open all holes to final dimension as shown in drawing D53470076004, Sheet 9, Detail Z9-9.

c Install these items : 1 tube D5347669000000 Item 172 2 shim D5347472120200 Item 176 with : 8 collar NSA5075-6 Item 806 2 pin DAN6-6-6 Item 866 14 pin DAN6-6-10 Item 870 d Drill the holes for the receptacles, Item 504, with 5.6 mm (0.220 in.) diameter as shown in drawing D53470076004, Sheet 9, Detail Z9-9 and install this item : 4 receptacle ABS0337-01A Item 504 with : 8 rivet DIN65399-2400CF Item 724

e Install at the tube, Item 172, as shown in drawing D53470076004, Sheet 9, Section A8-A9 these items : 1 plate D5347669200000 Item 166 1 plug D5347669100000 Item 174 1 ring MS16625-4212 Item 500 1 screw NAS1096-3-10 Item 506 (ar) Modify the routing of the hydraulic tubes between FR46 and FR50. Refer to Kit 281132D84R00 For connection of hydraulic tubes with PERMASWAGE fittings, refer to AMM 20-23-11, Page block 201. Refer to Drawing(s) : D93070515002 Sheet(s) 1, 6 thru 12

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 639 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Remove the attachment parts and the hydraulic tubes between FR46 and FR50 as shown in drawing D93070515002, Sheets 1, and 6 thru 12 :

a Remove and retain these items as shown in the table in drawing D93070515002, Sheet 8 : 2 spacer NSA5586-A Item A 10 bolt NAS67703U18 Item B 17 washer NAS1149D0363K Item C

4 washer NAS1149C0332R Item D 4 clamp D93470284224 Item F 4 clamp D93470286226 Item G 2 clamp NSA5516-11NJ Item H 2 clamp NSA5516-22NJ Item K 1 clamp NSA5519-4 Item L 1 clamp NSA5519-6 Item M 4 sleeve D93470249200 Item N 1 lead E0089-16-100 Item P 1 lead E0089-06-100NN Item Q 4 bolt A102-1/2D Item R 2 screw NAS1100-06-5 Item S 3 screw NAS1096-3-7 Item T 4 cover D93470756204 Item U 2 cover D93470756212 Item V 2 clamp NSA5516CA06NJ Item W 4 clamp NSA5516CA14NJ Item Y 4 washer NAS1149D332K Item Z 4 clamp D93470740204 Item AA 4 bolt NAS6703U16 Item AB NOTE : Retain the Items A thru AB. b Remove and discard these items : CAUTION : CUT THE TWO EXISTING TUBES AT FR49. THE REMAINING TUBES BETWEEN FR49 AN FR50 MUST BE REUSED AT INSTALLATION. CUT THE TUBES TO FINAL LENGTH DURING INSTALLATION. 1 tee ASNA37520120812 Item (011) Discard 2 sleeve D93470249200 Item (012) Discard 2 union NSA855006D4 Item (013) Discard 1 union NSA855006-6 Item (014) Discard 2 union NSA855006-8 Item (015) Discard 1 clamp NSA5516CA22NJ Item (018) Discard 2 clamp NSA5516CA11NJ Item (019) Discard 2 clamp D93470286226 Item (023) Discard 2 screw NAS1196-3-13 Item (028) Discard 2 spacer NSA5527-03-06 Item (029) Discard 1 spacer NSA5527-03-16 Item (030) Discard 2 tie NSA935401-05 Item (033) Discard 2 nut MS21042-3 Item (034) Discard 2 nut NAS679C06 Item (036) Discard DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 640 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 bolt NAS670303 Item (037) Discard 1 bolt NAS6703011 Item (038) Discard 1 tube D29170901006 Item (039) Discard 1 tube D32470911002 Item (042) Discard 1 tube D32470901002 Item (043) Discard 1 tube D32470901010 Item (044) Discard 1 tube D32470911004 Item (045) Discard 1 tube D32470911006 Item (046) Discard 1 tube D27770001022 Item (052) Discard 1 tube D27770011018 Item (055) Discard 1 tube D29170901004 Item (056) Discard 1 tube D32470901028 Item (083) Discard 1 tube D32470901032 Item (084) Discard 23 nut NSA5066-3-1 Item (085) Discard

3 tie NSA935401-06 Item (086) Discard 3 tie NSA935401-04 Item (087) Discard

c Remove and discard these items as shown in drawing D93070515002, Sheet 9, Detail A9-9 : 1 bracket D93570727202 Item (005) Discard 3 rivet LN9198-3210BF Item (199) Discard and close the holes at FR46 with this item : 3 rivet LN9198-3210CF Item 198 2 Install the brackets at FR46 as shown in drawing D93070515002, Sheet 11, Detail A11-11 :

a Put these items in position : 1 bracket D9357070820000 Item 191 1 bracket D9357045500000 Item 192 drill the additional holes and install with this item : 4 rivet LN9198-3210BF Item 199 3 Install the bracket between FR47 and FR48 at STGR39LH as shown in drawing D93070515002, Sheet 7, Section A12-A7 :

a Put this item in position : 1 bracket D9357072520300 Item 108 drill the additional holes and install with this item : 2 rivet LN9198-3210BF Item 199 4Shorten the length of the hydraulic tubes between FR49 and FR50 as shown in drawing D93070515002, Sheet 12. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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5 Install the hydraulic tubes between FR46 and FR50 as shown in drawing D93070515002, Sheets 6 thru 12 :

a Put these items in position : 1 tee ASNA3752D120812 Item 111 2 union NSA855006D4 Item 113 2 union NSA855006-6 Item 114 2 union NSA855006-8 Item 115 1 union NSA855006D8 Item 116 1 tube D2917091100000 Item 139 1 tube D3247091600200 Item 142 1 tube D3247090600400 Item 143 1 tube D3247090101000 Item 144 1 tube D3247091600000 Item 145 1 tube D3247091100600 Item 146 1 tube D2707023100000 Item 152 1 tube D2917091100200 Item 155 1 tube D2917090100400 Item 156 1 tube D2777000102600 Item 157 NOTE 1 tube D2777001102400 Item 158 NOTE 1 tube D3247090600000 Item 183 1 tube D3247090600600 Item 184 2 elbow NSA855020-8 Item 188 NOTE : Shorten the tubes, Item 157 and 158, to the correct length. b Connect the hydraulic tubes, refer to AMM 20-23-11, Page block 201.

c Tighten all connections of the hydraulic tubes. dAttach the hydraulic tubes with these items : 4 screw NAS1096-3-7 Item 128 1 spacer NSA5586-A Item 132 3 tie NSA935401-05 Item 133 2 nut NAS679C06 Item 136 23 nut NSA5066-3-1 Item 185

3 tie NSA935401-06 Item 186 3 tie NSA935401-04 Item 187 1 clamp NSA5516CA06NJ Item 193 and with these items : 2 spacer NSA5586-A Item A 10 bolt NAS67703U18 Item B 15 washer NAS1149D0363K Item C

4 washer NAS1149C0332R Item D 4 clamp D93470284224 Item F 4 clamp D93470286226 Item G 2 clamp NSA5516-11NJ Item H 2 clamp NSA5516-22NJ Item K 1 clamp NSA5519-4 Item L DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 clamp NSA5519-6 Item M 4 sleeve D93470249200 Item N 1 lead E0089-16-100 Item P 1 lead E0089-06-100NN Item Q 4 bolt A102-1/2D Item R 2 screw NAS1100-06-5 Item S 3 screw NAS1096-3-7 Item T 4 cover D93470756204 Item U 2 cover D93470756212 Item V 2 clamp NSA5516CA06NJ Item W 4 clamp NSA5516CA14NJ Item Y 4 washer NAS1149D332K Item Z 4 clamp D93470740204 Item AA 4 bolt NAS6703U16 Item AB NOTE : Items A thru AB are retained parts. 6 Mark all positions of the spacers with polyurethane top coat, RAL9001 (Mat. No. 16-018) as shown in drawing D93070515002, Sheet 12, Detail Z12-12. (as) Install the brackets for the fuel drain/vent systems between FR46 and FR54. Refer to Kit 281132D17R00 Refer to Drawing(s) : D28270982004 Sheet(s) 12 thru 14, 19, 20, 22 and 25 thru 27 1 Install the brackets between FR46 and FR47 as shown in Details A12-12, Y12-12 and Z12-12 : Refer to Drawing(s) : D28270982004 Sheet(s) 12

a Remove the existing fasteners from the affected areas. b Put these items in position : 2 angle D2827094222800 Item 102 2 bracket D2827094200400 Item 124

cTransfer drill the holes, drill the additional holes and open them to final dimension. d Install these items : 2 angle D2827094222800 Item 102 2 bracket D2827094200400 Item 124 with : 6 rivet LN9198-3212BF Item 032 8 pin DAN7-6-8Y Item 041 8 collar DAN12-6Y Item 042 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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2 Install the brackets at FR47 and FR48 as shown in Details A12-13, B12-13 and C12-13 : Refer to Drawing(s) : D28270982004 Sheet(s) 12 thru 14

a Put this item in position : 3 bracket F5397461900600 Item 100

b Drill the rivet holes.

c Install this item : 3 bracket F5397461900600 Item 100 with : 6 rivet LN9198-4012BF Item 040 3 Install the brackets at FR48 and FR49 as shown in Details X14-14, Y14-14 and Z14-14 : Refer to Drawing(s) : D28270982004 Sheet(s) 12 thru 14

a Put these items in position : 1 bracket D2827098300000 Item 104 1 bracket D2827098300200 Item 106 1 bracket D2827098325200 Item 125

b Drill the rivet holes.

c Install these items : 1 bracket D2827098300000 Item 104 1 bracket D2827098300200 Item 106 1 bracket D2827098325200 Item 125 with : 6 rivet LN9198-4012BF Item 040 4 Install the brackets at FR49 as shown in Details B26-26, D26-26 and B22-22 : Refer to Drawing(s) : D28270982004 Sheet(s) 22 and 26

a Put these items in position : 2 bracket D2827098320800 Item 117 2 bracket D2827098321000 Item 118 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 644 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 angle D2827098321200 Item 119

b Drill the rivet holes.

c Install these items : 2 bracket D2827098320800 Item 117 2 bracket D2827098321000 Item 118 1 angle D2827098321200 Item 119 with : 14 rivet LN9198-4012BF Item 040 5 Install the angles at FR50, FR51, FR52 and FR53 as shown in Details W23-27, X23-27, Y23-27 and Z23-27 : Refer to Drawing(s) : D28270982004 Sheet(s) 23 thru 27

a Put these items in position : 2 angle D2827098327600 Item 137 1 angle D2827098327800 Item 138 1 angle D2827098328000 Item 139 1 angle D2827098328200 Item 140

b Drill the rivet holes.

c Install these items : 2 angle D2827098327600 Item 137 1 angle D2827098327800 Item 138 1 angle D2827098328000 Item 139 1 angle D2827098328200 Item 140 with : 8 rivet LN9198-4012BF Item 040 6 Install the angles at FR50 and FR51 as shown in Sections G24-G20 and F24-F17 : Refer to Drawing(s) : D28270982004 Sheet(s) 17, 22 thru 24

a Put this item at FR51 in position : 2 angle D2827094220400 Item 113

b Put this item at FR50 ad FR51 in position : 2 angle D2827094222200 Item 116 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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c Drill the rivet holes. d Install these items : 2 angle D2827094220400 Item 113 2 angle D2827094222200 Item 116 with : 12 rivet LN9198-4012BF Item 040 7 Install the brackets at FR52 and FR53 as shown in Sections C17-C17 and B25-B25 : Refer to Drawing(s) : D28270982004 Sheet(s) 17 thru 25

a Put this item at FR52 and FR53 in position : 2 bracket D2827098323200 Item 127

b Drill the rivet holes.

c Install these items : 2 bracket D2827098323200 Item 127 with : 4 rivet LN9198-4012BF Item 040 8 Install the bracket between FR51 and FR52 as shown in Section B17-B17 : Refer to Drawing(s) : D28270982004 Sheet(s) 13 and 17

a Put this item in position : 1 bracket D2827098300800 Item 126

b Drill the rivet holes.

c Install this item : 1 bracket D2827098300800 Item 126 with : 6 rivet LN9198-4012BF Item 040 9 Install the brackets at FR53 and FR54 as shown in Sections A25-A25, C25-C25, A19-A19 and D19-D19 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Refer to Drawing(s) : D28270982004 Sheet(s) 19 and 25

a Put this item at FR53 in position : 3 angle D2827094221400 Item 112

b Put this item at FR54 in position : 1 bracket D2827098326000 Item 135

c Put this item at FR53 and FR54 in position : 1 bracket D2827098326200 Item 136

d Drill the rivet holes.

e Install these items : 3 angle D2827094221400 Item 112 1 bracket D2827098326000 Item 135 1 bracket D2827098326200 Item 136 with : 10 rivet LN9198-4012BF Item 040 10Install the brackets between FR53 and FR54 as shown in Section A20-A20, B20-B20 and I20-20 : Refer to Drawing(s) : D28270982004 Sheet(s) 19 thru 20

a Put these items at FR53 and FR54 in position : 1 bracket D2827098324200 Item 132 1 bracket D2827098324400 Item 133

b Drill the rivet holes.

c Install these items : 1 bracket D2827098324200 Item 132 1 bracket D2827098324400 Item 133 with : 4 rivet LN9198-4012BF Item 040

d Put these items between FR53 and FR54 in position : 1 bracket D2827098323800 Item 130 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 bracket D2827093521000 Item 131 1 bracket D2827098324000 Item 134

e Drill the rivet holes. f Install these items : 1 bracket D2827098323800 Item 130 1 bracket D2827093521000 Item 131 1 bracket D2827098324000 Item 134 with : 6 screw NAS1096-3-8 Item 004 6 washer NAS1149C0332R Item 005 6 nut NAS1726C3E Item 006 2 rivet LN9198-4012BF Item 040 (at) Install the brackets for the pressure system and cavity drain system between FR51 and FR53. Refer to Kit 281132D44R00 Refer to Drawing(s) : D28270992002 Sheet(s) 1, 2, 3 and 5 1 Put these items in position as shown in Details B2-2 and F5-5 and Sections C3-C5, D3-D5 : 1 bracket D2827098324800 Item 002 1 bracket D2827098325200 Item 006 2 bracket D2827098329200 Item 008 2 Drill the rivet holes. 3 Install these items : 1 bracket D28270983-248 Item 002 1 bracket D28270983-252 Item 006 2 bracket D2827098329200 Item 008

with : 10 rivet EN6081D5 Item 040 (au) Replace the APU fuel tube in the keel beam area between FR42 and FR47. Refer to Kit 281132D48R00 Refer to Drawing(s) : D28271200002 Sheet(s) 3 thru 6 1 Remove the APU fuel tube in the keel beam area between FR42 and FR47:

a Remove and retain this item : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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7 clamp NSA5516-10NJ Item A NOTE : Retain the Items A. b Remove and discard this item : 1 tube D28270505006 Item (1000) Discard 2 Install the APU fuel tubes in the keel beam area between FR42 and FR47 as shown in drawing D28271200002 ’AFTER’, Detail B3-3, C3-4 and Detail W6-6 :

a Install these items : 1 tube D2827050501600 Item 004 1 tube D2827050501400 Item 014 1 tee NSA855113-11C Item 022 with : 7 clamp NSA5516-10NJ Item A NOTE : Items A are retained parts. b Install these items as shown in drawing D28271200002, Detail, X5-6, Y5-5, Z5-5 and W6-6 : 11 clamp NSA5575-4A Item 062

4 bonding-lead ABS1510D100NN Item 064 1 bonding-lead ABS1510D160NN Item 068 1 bonding-lead ABS1510D140NN Item 070 1 bonding-lead E0090-10-160NN Item 072 and secure with : 25 washer NAS1149C0322R Item 025 14 nut NAS1219C3M Item 026 11 bolt NAS1303-2 Item 074

3 bolt NAS1303-3 Item 076

c Connect the APU fuel system with the cavity drain and monitoring system. (av) Install the ACT pressurization system between FR51 and FR53. Refer to Kit 281132D43R00 Refer to Drawing(s) : D28270991002 Sheet(s) 1 thru 3 1 From the tee at FR51 shown in Sheet 3, Detail X1-3 remove : 1 cap MS21914-10D Item (094) Retain

NOTE : The cap was installed with Kit 281132D45R00, drawing D28270975006, Item 094. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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2 Install these items between FR50 and FR53 as shown in Sheet 3, Detail X1-3 : 1 tube D2827097905200 Item 002

with : 1 elbow MS21908J10 Item 091 1 nut AN924-10J Item 034 1 washer NAS1149C1432R Item 035 3 Install these items as shown in Sheet 3 and Section Z1-3: 1 nut NAS1726C3E Item 070 1 washer NAS1149C0332R Item 073 1 clamp MS21919 WDE10 Item 079 1 clamp NSA5575-8A Item 081 1 bonding lead E0090-10-125NN Item 083 1 bolt NAS1303-2 Item 088 1 nut NAS1726-3E Item 089 1 washer NAS1149D0316H Item 090 1 screw NAS1801-3-9 Item 097 4 Between FR52 and FR53, on tube, Item 002, install as shown in Detail X1-3 : 1 cap MS21914-10D Item (094) Retained (aw) Install the ACT pressurization system between FR48 and FR54. Refer to Kit 281132D16R01 Refer to Kit 281132B01R00 Refer to Drawing(s) : D28270975004 Sheet(s) 8, 10, 11 and 13 thru 15 1 Install these items at the crossbeam at FR54 as shown in Section D8-D8 : 1 coupling A2827092300000 Item 050 1 nut AN924-10J Item 074 1 tee MS21909J10 Item 075 1 washer NAS1149F1432P Item 076 2 Install these items at the crossbeam at FR54 as shown in drawing D28270975006, Sheet 13 and Sections A13-A8 and C8-C8 : 1 tube D2827097902000 Item 021 1 valve HTE490005 Item 042 1 actuator HTE200002-1 Item 043 1 valve HTE920007-001 Item 044 1 clamp HTE8002 Item 045

NOTE : The Items 042, 043, 044 and 045 are contained in Kit 281132B01R00. 3 Install these items as shown in Sections A13-A8, B8-B8 and C8-C8 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 nut NAS1726C3E Item 070 1 screw NAS1096-3-8 Item 071 1 washer NAS1149C0332R Item 073 1 clamp NSA5575-8A Item 081 1 strap E0090-10-125NN Item 083 1 bolt NAS1303-2 Item 088 1 nut NAS1726-3E Item 089 2 washer NAS1149F0332P Item 103 4 Install these items with adhesive (Mat. No. 08-010)as shown in Section A13-A8 : 1 placard D2827094420000 Item 200 1 placard D2827094420200 Item 202 1 placard D2827094420400 Item 204 1 placard D2827094421200 Item 212 5 Install these items at the crossbeam at FR53 as shown in Section B14-B14 : 1 coupling A2827092300000 Item 050 1 nut AN924-10J Item 074 1 tee MS21909J10 Item 075 1 washer NAS1149F1432P Item 076 6 Install these items at the crossbeam at FR53 as shown in drawing D28270975006, Sheet 13 and Section B13-B14 : 1 tube D2827097901800 Item 019 1 valve HTE490005 Item 047

NOTE : The Item 047 is contained in Kit 281132B01R00. 7 Install this item between FR53 and FR54 as shown in Section E13-E11 : 1 valve PAS148-133A Item 046

with : 2 nut NAS1726C3E Item 070 2 washer NAS1149C0332R Item 073 2 screw NAS1096-3-12 Item 098

NOTE : The Item 046 is contained in Kit 281132B01R00. 8 Install these items as shown in Section B13-B14 : 1 clamp NSA5575-8A Item 081 1 strap E0090-10-125NN Item 083 1 bolt NAS1303-2 Item 088 1 nut NAS1726-3E Item 089 2 washer NAS1149F0332P Item 103 9 Install these items with adhesive (Mat. No. 08-010)as shown in Section B13-B14 : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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1 placard D2827094420600 Item 206 1 placard D2827094420800 Item 208 10Install this item between FR53 and FR54 as shown in drawing D28270975006, Sheet 13 and Section E13-E11 : 1 hose 1451515F0150-180 Item 040

with : 1 nut NAS1726C3E Item 070 1 screw NAS1096-3-8 Item 071 1 washer NAS1149C0332R Item 073 1 clamp MS21919WCH15 Item 101 11Install these items as shown in drawing D28270975006, Sheet 13 and 15 and Sections B13-B14, E13-E11, G13-G15, H13-H15, K13-K15 and L13-L15 : 1 tube D2827098000800 Item 005 1 tube D2827098001400 Item 011 1 tube D2827098002400 Item 220 1 tube D2827098002600 Item 222

with : 13 nut NAS1726C3E Item 070 10 screw NAS1096-3-8 Item 071 13 washer NAS1149C0332R Item 073 11 clamp MS21919WDE4 Item 080

4 clamp NSA5575-2 Item 082 4 lead E0090-18-100NN Item 084 4 screw NAS1096-1-8 Item 085 4 nut MS21042-06 Item 087 3 screw NAS1096-3-9 Item 097 8 washer NAS1149FN616P Item 104 12Install these items between FR48 and FR49 as shown in Section G13-G15 : 1 filter A2163302000000 Item 027 1 inlet A2151034520000 Item 028 1 nut AN924-4D Item 092 13Install these items as shown in drawing D28270975006, Sheet 13 and 16 and Sections C13-C16 and D13-D11 : 1 tube D2827097901000 Item 016 1 tube D2827097901600 Item 017 1 tube D2827097904000 Item 026 1 tube D2827097902400 Item 025

with : 6 nut NAS1726C3E Item 070 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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3 screw NAS1096-3-8 Item 071 6 washer NAS1149C0332R Item 073 1 conduit TSTMNR503-0 Item 077 2 tie NSA935401-03 Item 078 6 clamp MS21919WDE10 Item 079 4 clamp NSA5575-8A Item 081 4 strap E0090-10-125NN Item 083 4 bolt NAS1303-2 Item 088 4 nut NAS1726-3E Item 089 3 screw NAS1096-3-9 Item 097 8 washer NAS1149F0332P Item 103

NOTE : Cut the conduit, Item 077, in two pieces. 14Install this item between FR51 and FR52 as shown in drawing D28270975006, Sheet 13 and 16 and Sections C13-C16 and A16-A16 : 1 filter QB0566 Item 041

with : 1 union MS21902D10 Item 030 1 packing NAS1612-10 Item 031 4 nut NAS1726C4E Item 093

NOTE : The Item 041 is contained in Kit 281132B01R00. 15Install this item with adhesive (Mat. No. 08-010) as shown in Section C13-C16 : 1 placard D2827094421000 Item 210 16Install this item as shown in drawing D28270975006, Sheet 13 and Sections D13-D11 and F13-F11 : 1 tube D2827097901400 Item 015

with : 2 nut NAS1726C3E Item 070 2 screw NAS1096-3-8 Item 071 2 washer NAS1149C0332R Item 073 1 conduit TSTMNR503-0 Item 077 2 tie NSA935401-03 Item 078 2 clamp MS21919WDE10 Item 079 17Install these items as shown in drawing D28270975006, Sheet 13 and Details F13-11, X13-11, Y13-11, Z13-11 and B11-B11 : 1 tube D2827097901200 Item 013 1 elbow MS21908J10 Item 091 1 tee MS21905J10 Item 099

with : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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2 nut NAS1726C3E Item 070 1 screw NAS1096-3-8 Item 071 2 washer NAS1149C0332R Item 073 2 clamp MS21919WDE10 Item 079 2 clamp NSA5575-8A Item 081 1 strap E0090-10-125NN Item 083 2 bolt NAS1303-2 Item 088 2 nut NAS1726-3E Item 089 2 cap MS21914-10D Item 094 1 nut AN924-10J Item 095 1 washer NAS1149C1432R Item 096 1 screw NAS1096-3-9 Item 097 1 strap E0090-10-160NN Item 102 4 washer NAS1149F0332P Item 103 (ax) Install the attachment parts of the cable harnesses in the AFT cargo compartment crossbeam area between FR49 and FR55. Refer to Kit 281132D87R01 Refer to Drawing(s) : D92891805000 Sheet(s) 2, 4, 6, 8, 9, 10, 12, 13, 14 and 15 1 Install the attachment parts of the cable harnesses in the crossbeam area between FR49 and FR55 as shown in drawing D92891805000, Sheets 2, 4, 6, 8, 9, 10, 12, 13, 14 and 15

a Install these parts : 20 screw NAS1801-08-6 Item 004 21 screw NAS1801-08-9 Item 005

4 screw NAS1801-08-12 Item 007 2 screw NAS1801-08-17 Item 010 2 screw NAS1801-08-19 Item 012 2 screw NAS1801-08-23 Item 014 1 screw NAS1801-08-39 Item 020 97 screw NAS1801-3-9 Item 030

8 screw NAS1100-04-5 Item 051 24 screw NAS1102-08-8 Item 058

8 washer NAS1149CN416R Item 150 34 washer NAS1149CN816R Item 152 108 washer NAS1149C0332R Item 153 3 washer ASNA0113-40ADL Item 163 16 washer NSA935808C01 Item 171

1 washer D9249102520000 Item 190 24 nut MS21042-04 Item 200

3 nut MS21042-08 Item 202 8 nut MS21042-3 Item 203 32 nut NAS1291C3M Item 218

1 clip-nut NSA5110-08-1 Item 225 6 clip-nut NSA5066-08-1 Item 230 36 clip-nut NSA5067-08-1 Item 236

5 bracket E0343-01 Item 250 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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10 bracket NSA935504-01 Item 251

1 bracket NSA935504-02 Item 252 3 bracket NSA935513-01 Item 256 6 bracket NSA935513-05 Item 257 1 bracket NSA935513-07 Item 259 6 bracket ABS0355-01 Item 262 10 bracket ABS0355-02 Item 263 10 washer NSA935514-03 Item 264

1 bracket E0660-01 Item 266 20 support ABS0731A01 Item 267 11 bracket ABS0774A01A Item 268

2 spacer NSA5527-03-03 Item 304 2 spacer NSA5527-03-04 Item 306 4 spacer NSA5527-03-08 Item 314 1 spacer NSA5527-03-11 Item 320 1 clamp MS21919WCH6 Item 352 12 clamp NSA935807-09 Item 377

4 clamp NSA935807-16 Item 381 4 sheet D9249104800000 Item 727 2 sheet D9249104800400 Item 729 1 tube TSTMNR502-0 Item 763 30 bobbin NSA935510-02 Item 777 100 tie NSA935401-03 Item 793 200 tie NSA935401-04 Item 794 100 tie NSA935401-05 Item 795 1 strap D9249107100600 Item 834 4 cover EN2997KE3C12 Item 930 2 cover EN2997KE3C16 Item 932 4 dummy receptacle EN2997KE512 Item 933 2 dummy receptacle EN2997KE516 Item 935 3 cover D2557016200200 Item 1099 4 bracket D9249104900600 Item 1110 (ay) Install the brackets at crossbeams at FR42 and between FR50 and FR54. Refer to Kit 281132D98R02 Refer to Drawing(s) : D92491681010 Sheet(s) 49 thru 52 and D92492244002 Sheet(s) 10 1 Install the items as shown in drawing D92491681010, Sections A50, Details B-B and C-C and Y-Y51, V-V52, W-W52.

a Install these parts : 4 nut NSA5066-08-1 Item 230 2 sheet A9249187820200 Item 565 2 plate A9249199820000 Item 632 6 bracket D9249104920400 Item 737 2 Install the items as shown in drawing D92492244002, Section B and Detail B-B.

a Install these parts : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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4 mount E0660-01 Item 266 2 guide D92491047200 Item 724 1 connectn D92491073028 Item 824 1 deflectr D92491026206 Item 730 1 spacer NSA5527-03-07 Item 312 1 spacer NSA5527-03-04 Item 306 with 7 screw NAS1096-2-12 Item 7 1 screw NAS1096-2-14 Item 9 10 washer ASNA0113-40ADL Item 163

2 washer D92491025200 Item 190 4 nut MS21042-08 Item 202 (az) Install/modify the cable harness 4606VB, 4607VB. Refer to Kit 281132G05R00 Refer to Drawing(s) : D92997028040 Sheet(s) 1 thru 4, 9 thru 10 and 24 thru 37 1 Modify the cable harness 4606VB Refer to Drawing(s) : D92997026001 Sheet(s) 1 and 2 2 Modify the cable harness 4607VB Refer to Drawing(s) : D92997026002 Sheet(s) 3 to 7 3 Modify the cable harness 4628VB/1M Refer to Drawing(s) : D92991428014 Sheet(s) 19, H01 to H18 and W01 and W02, X01 and X02 4 Modify the cable harness 4640VB Refer to Drawing(s) : D92997028002 Sheet(s) 1 and 2 and B01 5 Modify the cable harness 4644VB Refer to Drawing(s) : D92997028004 Sheet(s) 3 and 4 and B01 6 Modify the cable harness 4644VB Refer to Drawing(s) : D92997028031 Sheet(s) 3 and 4 and B01 7 Modify the cable harness 4648VB DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 656 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s) : D92997028006 Sheet(s) 5 and 6 and B01 8 Install the cable harness 4655VB/6S Refer to Drawing(s) : D92991455009 Sheet(s) 6, H01, H02, W01 and X01 9 Install the cable harness 4656VB/6E and 6G Refer to Drawing(s) : D92991456007 Sheet(s) 4, H01, H02, W01 and X01 10Install the cable harness 4661VB/1M Refer to Drawing(s) : D92991461020 Sheet(s) 27, B01 to B04, H01 to H21, W01 and W02, X01 and V01 to V05 11Install the cable harness 4662VB/2M Refer to Drawing(s) : D92991461009 Sheet(s) 11, B01 and B02, H01 to H06, W01, X01 and V01 to V02 12Install the cable harness 4663VB/1S Refer to Drawing(s) : D92991463004 Sheet(s) 10, B01 and B02, H01 to H09, W01 and W02, X01 and V01 to V04 13Install the cable harness 4664VB/2S Refer to Drawing(s) : D92991464003 Sheet(s) 5, B01, H01 to H06, W01, X01 and V01 and V02 14Install the cable harness 4670VB/1M Refer to Drawing(s) : D92991470008 Sheet(s) 9, B01 to B04, H01 to H06, W01, X01 and V01 to V03 15Install the cable harness 4671VB/1M Refer to Drawing(s) : D92991471006 Sheet(s) 8, B01 to B05, H01 to H07, W01 and W02, X01 and V01 to V03 16Install the cable harness 4672VB/2M Refer to Drawing(s) : D92991472015 Sheet(s) 12, B01 and B02, H01 to H03, W01, X01, V01 and V02 17Install the cable harness 4673VB/1S DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 657 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Drawing(s) : D92991473004 Sheet(s) 3, B01 and B02, H01 to H04, W01, X01, V01 and V02 18Install the cable harness 4675VB/2M Refer to Drawing(s) : D92997028010 Sheet(s) 9 and 10, B01 19Install the cable harness 4680VB/1MB Refer to Drawing(s) : D92991480013 Sheet(s) 16, B01 to B03, H01 to H04 and V01 and V02 20Install the cable harness 4681VB/7M Refer to Drawing(s) : D92991481004 Sheet(s) 5, B01, H01, W01, V01 21Cable harness 4683VB/8M

a Install the cable harness 4683VB/8M Refer to Drawing(s) : D92991483006 Sheet(s) 7, B01 and B02, H01 to H09, W01 and W02, X01 and X02, V01 to V04 b Install the air inlet plenum, refer to AMM 21-61-51, Page block 401.

c Install the welding group (Item 127), refer to AMM 21-52-41, Page block 401. 22Install the cable harness 4692VB/2M Refer to Drawing(s) : D92991492006 Sheet(s) 7, B01, H01, W01, X01, V01 23Install the cable harness 4693VB/1S Refer to Drawing(s) : D92991493004 Sheet(s) 3, B01 and B02, H01 to H03, W01, X01, V01 and V02 24Install the cable harness 4694VB/2S Refer to Drawing(s) : D92991494004 Sheet(s) 3, B01 and B02, H01 to H03, W01, X01, V01 and V02 25Install the cable harness 5609VB/1M Refer to Drawing(s) : D92997028032 Sheet(s) 26 to 29, B01 26Install the cable harness 5662VB/2M Refer to Drawing(s) : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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D92997028033 Sheet(s) 30 and 31, B01 27Install the cable harness 5633VB/5S Refer to Drawing(s) : D92997028034 Sheet(s) 32 and 33, B01 28Install the cable harness 5664VB/4S Refer to Drawing(s) : D92997028035 Sheet(s) 34 to 36, B01 29Install the cable harness 5670VB/1M Refer to Drawing(s) : D92997028036 Sheet(s) 37 and 38, B01 30Install the cable harness 5675VB/2M Refer to Drawing(s) : D92997028037 Sheet(s) 39 and 40, B01 (ba) Install the wires of cable harness 4209VB. Refer to Kit 281132D86R00 Refer to Drawing(s) : D92999561000 Sheet(s) all 1 Install : Refer to Drawing(s) : D92999561000 Sheet(s) 2 and 4 2 Install the wires of cable harness 4213VB Refer to Drawing(s) : D92999559004 Sheet(s) 2, lines 5 to 7 3 Install the wires of cable harness 4214VB Refer to Drawing(s) : D92999559006 Sheet(s) 3, lines 10 to 17 4 Install the wires of cable harness 4216VB Refer to Drawing(s) : D92999561004 Sheet(s) 5, lines 9 to 15 D92999561004 Sheet(s) 7 5 Install the wires of cable harness 4218VB Refer to Drawing(s) : D92999561006 Sheet(s) 10, lines 11 to 13 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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6 Install the wires of cable harness 4220VB Refer to Drawing(s) : D92999559012 Sheet(s) 8 7 Install the wires of cable harness 4221VB Refer to Drawing(s) : D92999559012 Sheet(s) 8 8 Install the wires of cable harness 4221VB Refer to Drawing(s) : D92999559014 Sheet(s) 11 and 12 9 Install the wires of cable harness 4222VB Refer to Drawing(s) : D92999559016 Sheet(s) 13, lines 9 to 19 10Install the wires of cable harness 4223VB Refer to Drawing(s) : D92999561008 Sheet(s) 16, 17 and 19 11Install the wires of cable harness 4224VB Refer to Drawing(s) : D92999559020 Sheet(s) 19 12Install the wires of cable harness 4225VB Refer to Drawing(s) : D92999561010 Sheet(s) 20, lines 4 and 5, D92999561010 Sheet(s) 21, AFTER MOD 13Install the wires of cable harness 4226VB Refer to Drawing(s) : D92999559024 Sheet(s) 23 and 24 14Install the wires of cable harness 4227VB Refer to Drawing(s) : D92990627013 Sheet(s) 17 and 19 15Install the wires of cable harness 4232VB Refer to Drawing(s) : D92999559026 Sheet(s) 26 16Install the wires of cable harness 4233VB DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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Refer to Drawing(s) : D92999559028 Sheet(s) 27, lines 6 to 9 17Install the wires of cable harness 4234VB Refer to Drawing(s) : D92990634002 Sheet(s) 3 18Install the wires of cable harness 5214VB Refer to Drawing(s) : D92999559030 Sheet(s) 28, line 3 19Install the wires of cable harness 5220VB Refer to Drawing(s) : D92990820001 Sheet(s) 2 20Install the wires of cable harness 5224VB Refer to Drawing(s) : D92990824007 Sheet(s) 7 21Install the wires of cable harness 5233VB Refer to Drawing(s) : D92990833001 Sheet(s) 2 (bb) Install the attachment parts of the cable harnesses in the AFT cargo compartment crossbeam area between FR49 and FR55. Refer to Kit 281132D87R01 Refer to Drawing(s) : D92891805000 Sheet(s) 2, 4 thru 9, and 11 thru 14 1 Install the attachment parts of the cable harnesses in the crossbeam area between FR49 and FR55.

a Install these Parts : 8 screw NAS1801-08-6 Item 004 22 screw NAS1801-08-9 Item 005

4 screw NAS1801-08-12 Item 007 2 screw NAS1801-08-17 Item 010 4 screw NAS1801-08-19 Item 012 2 screw NAS1801-08-23 Item 014 1 screw NAS1801-08-39 Item 020 49 screw NAS1801-3-9 Item 030 48 screw NAS1100-04-5 Item 051 24 screw NAS1102-08-8 Item 058 48 washer NAS1149CN416R Item 150 23 washer NAS1149CN816R Item 152 61 washer NAS1149C0332R Item 153 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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4 washer ASNA0113-40ADL Item 163 16 washer NSA935808C01 Item 171

2 washer D9249102520000 Item 190 48 nut MS21042-04 Item 200

3 nut MS21042-08 Item 202 8 nut MS21042-3 Item 203 32 nut NAS1291C3M Item 218

1 clip-nut NSA5110-08-1 Item 225 6 clip-nut NSA5066-08-1 Item 230 36 clip-nut NSA5067-08-1 Item 236

5 bracket E0343-01 Item 250 11 bracket NSA935504-01 Item 251

1 bracket NSA935504-02 Item 252 4 bracket NSA935513-01 Item 256 11 bracket NSA935513-05 Item 257

1 bracket NSA935513-07 Item 259 6 bracket ABS0355-01 Item 262 10 bracket ABS0355-02 Item 263 10 washer NSA935514-03 Item 264

1 bracket E0660-01 Item 266 20 support ABS0731A01 Item 267

9 bracket ABS0774A01A Item 268 2 spacer NSA5527-03-03 Item 304 4 spacer NSA5527-03-04 Item 306 1 spacer NSA5527-03-06 Item 310 4 spacer NSA5527-03-08 Item 314 1 spacer NSA5527-03-11 Item 320 1 clamp MS21919WCH6 Item 352 12 clamp NSA935807-09 Item 377

4 clamp NSA935807-16 Item 381 4 sheet D9249104800000 Item 727 2 sheet D9249104800400 Item 729 1 tube TSTMNR502-0 Item 763 30 bobbin NSA935510-02 Item 777 100 tie NSA935401-03 Item 793 200 tie NSA935401-04 Item 794 100 tie NSA935401-05 Item 795 1 strap D9249107100600 Item 834 2 strap D9249107103000 Item 846 4 cover EN2997KE3C12 Item 930 2 cover EN2997KE3C16 Item 932 4 dummy receptacle EN2997KE512 Item 933 2 dummy receptacle EN2997KE516 Item 935 6 cover D2557016200200 Item 1099 4 bracket D9249104900600 Item 1110 If there is no hole in the centerline AD of the crossbeam of FR54 drill the hole : Refer to Drawing(s) : D92491681000 Sheet(s) 52 view V-V52.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 662 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(bc) Attach the placards printed with the modification and the SB-number to the cable harnesses. Refer to Kit 281132D86R00 Refer to Kit 281132G05R00 Refer to Drawing(s) : D92894713026 Sheet(s) 1 360 placard E0248A2-4H9R Item 000 720 tie NSA935401-03 Item 080 (bd) Install the AFT cargo compartment floor panels between FR47 and FR59. Refer to Kit 281132D52R00 Refer to Drawing(s) : D53675510012 Sheet(s) 19, 20, 21 and 29 1 Install the AFT cargo compartment floor panels between FR47 and FR59 as shown in Sections A19-19 : Refer to Drawing(s) : D53675510012 Sheet(s) 19 and 20 2 Install : Refer to AMM 53-42-14, Page block 401 and refer to drawing D53675510012, Sheets 19 and 20.

a Install these items as shown in Detail A19-19 : 1 panel D5367520801400 Item 028 1 panel D5367520801800 Item 030 1 panel D5367520805000 Item 032 1 panel D5367520802600 Item 038 1 panel D5367521101600 Item 040 1 panel D5367521101800 Item 042 1 panel D5367521105200 Item 044 1 panel D5367521105400 Item 046 1 panel D5367521105600 Item 048 1 doorsill D5367205900200 Item 050 1 panel D5367521100600 Item 052 1 panel D5367521100800 Item 054 1 shim D5367284220000 Item 110 1 shim D5367484220100 Item 111 2 shim D5367489520000 Item 112 2 shim D5367489520100 Item 113 1 shim D5367489420000 Item 114 1 shim D5367489420200 Item 116 with : 33 screw ABS0376-3-30 Item 402 130 screw ABS0376-3-40 Item 404

23 screw NAS1102-3-8 Item 408 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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85 nut EN6131C3C4 Item 411 11 washer NAS1149C0332R Item 420 11 nut MS21042L3 Item 430 (be) Install the AFT cargo compartment floor panels between FR47 and FR59. Refer to Kit 281132D53R00 Refer to Drawing(s) : D53675520010 Sheet(s) 16 thru 18 1 Install : Refer to AMM 53-42-14, Page block 401 and refer to drawing D53675520010, Sheets 16 and 17.

a Install these items as shown in Details A16-16 and B16-16 and Sheet 17 : 1 panel D5367401800000 Item 000 1 panel D5367401800100 Item 001 1 panel D5367402000000 Item 002 1 panel D5367402400000 Item 004 1 panle D5367402600000 Item 006 1 panel D5367403400000 Item 008 1 panel D5367403400100 Item 009 1 panel D5367402200000 Item 010 1 panel D5367402700000 Item 012 1 panel D5367406200000 Item 028 1 panel D5367406200100 Item 029 1 panel D5367405500000 Item 030 1 panel D5367405300000 Item 032 1 panel D5367405400000 Item 034 1 panel D5367405200000 Item 038 1 panel D5367405600000 Item 040 1 panel D5367416000200 Item 084 1 panel D5367416000300 Item 085 with : 221 screw ABS0376-3-30 Item 402 1 tape ABS5006-4D Item 408 92 nut EN6131C3C4 Item 411

6 screw ABS0376-3-35 Item 412 (bf) Install the seal section in the gaps between the AFT cargo compartment floor panels between FR47 and FR59. Refer to Kit 281132D39R00 Refer to Drawing(s) : D53675525002 Sheet(s) 4 thru 6 1 Install these items as shown in drawing D53675525002, Sheet 4 thru 6 : 1 section ABS0399A Item 003 1 section ABS0398A01 Item 004 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 664 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 section ABS0305LC Item 005 1 section ABS0305LB Item 006 2 Install this item in the gaps as in drawing D53675525002, Sheet 4 thru 6 : 1 cord DAN107-1 Item 001

and seal all gaps with sealant (Mat. No. 09-016) as shown in drawing D53675525002, Sheet 4 thru 6. (bg) Install the AFT cargo compartment ceiling panels between FR47 and FR59. Refer to Kit 281132D59R00 Refer to AMM 25-55-11, Page block 401. Refer to Drawing(s) : D25570049016 Sheet(s) 9 1 Install these items as shown in drawing D25570049016, Sheet 9 : 1 prot. cover D2558521803400 Item 016 1 prot. cover D2558521803600 Item 018 1 panel D2557131002600 Item 051 1 panel D2557131402000 Item 053 1 panel D2557131600400 Item 055 1 panel D2557134200000 Item 056 1 panel D2557161000200 Item 057 1 panel D2557122000400 Item 059 3 abrasion prot. D2558503820200 Item 010 1 bumper D2557165620000 Item 012 1 bumper D2557165720000 Item 014 9 screw NAS1102-3-10 Item 070 14 screw NAS1100-3-18 Item 071

6 washer ABS0208-01 Item 072 14 washer NAS1149D0332K Item 073

6 screw NAS1102-08-12 Item 074 1 tape ABS5006-6J Item 080 2 Install the AFT cargo compartment ceiling panel 151DC, refer to AMM 25-55-11, Page block 401. 3 Install these items as shown in drawing D25570049016, Sheet 9 : 2 rail D2557043000000 Item C 1 rail D2557043000200 Item D (bh) Install the passenger compartment floor panels 241JF, 251AF 251BF, 251FF, 251GF and 252BF. Refer to Kit 281132D54R00 Refer to Drawing(s) : D53675015006 Sheet(s) 10 thru 12 1 Install these items : DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 665 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 panel D5367161701800 Item 016 2 panel D5367160001600 Item 028 1 panel D5367160100800 Item 032 1 panel D5367162400800 Item 036 2 panel D5367162301400 Item 042

with : 122 screw ABS0376-3-25 Item 400 122 clip nut EN6131-3C1 Item 505 (bi) Install the insulation blankets at FR46. Refer toKit 281132D11R00 Refer to AMM 25-80-00, Page block 201 Refer to Drawing(s) : D25870003056 Sheet(s) 20 1 Install these items : 1 blanket D2587085002200 Item 000 1 blanket D2587085105600 Item 001 1 blanket D2587085205200 Item 002 1 blanket D2587085305600 Item 003 1 blanket D2587085405200 Item 004 1 blanket D2587085505400 Item 005 1 blanket D2587085602200 Item 006 1 blanket D2587085705200 Item 007 1 blanket D2587085805200 Item 008 1 blanket D2587085905200 Item 009 1 blanket D2587086005400 Item 010 1 blanket D2587086105200 Item 011 1 blanket D2587086202200 Item 012 1 blanket D2587086302400 Item 013 1 blanket D2587086502200 Item 014 1 blanket D2587087102200 Item 015 1 blanket D2587087302200 Item 016

with : 80 strip F2587003400000 Item 100 2 Modify and re-identify the insulation blankets after the bracket installation. For re-identification, refer to para. 2.E. Refer to AMM 25-80-00, Page block 201 (bj) Install the LH sidewall panels between FR46 and FR58. Refer toKit 281132D56R00 Refer to AMM 25-55-11, Page block 401 Refer to Drawing(s) : D25570049010 Sheet(s) 6 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 666 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Install these items : 1 panel D2557132600200 Item 060 1 panel D2557132400800 Item 062 1 panel D2557132200800 Item 064 (bk) Install the RH sidewall panels between FR46 and FR52A. Refer to Kit 281132D57R00 Refer to AMM 25-55-11, Page block 401 Refer to Drawing(s) : D25570049012 Sheet(s) 7 1 Install these items : 1 panel D2557133000200 Item 066 1 panel D2557133400600 Item 068 (bl) Install the AFT cargo compartment panels 151AW, 151BW and 152BW at FR47. Refer to Kit 281132D58R00 Refer to AMM 25-55-11, Page block 401 Refer to Drawing(s) : D25570049014 Sheet(s) 8 1 Install these items :

2 cover D2557017000200 Item 044 1 panel D2557123600400 Item 090 1 panel D2557123600500 Item 091 1 panel D2557123800200 Item 092 **C. T E** **S T**  (1) Config. 01 thru Config. 03 Job Set-up (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Connect the battery connectors : 1 For the job set-up, refer to the removal/installation of the batteries, refer to AMM 24-38-51, Page block 401. 2 Remove the blanking caps from the electrical connectors. 3 Make sure that the electrical connectors are clean and in a correct condition. 4Connect the connectors to the battery. 5Turn the knurled nut a quarter turn. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 667 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(c) Remove all the warning notices. (d) On each connector that you disconnected, do a visual check to make sure that : Refer to ESPM 20-51-10 - The label of the plug is the same as the label on the receptacle. - The plug is correctly locked. Energize the aircraft electrical circuits, refer to AMM 24-41-00, Page block 201. (2) 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. (a) Do the operational test of the instrument and panel integral lighting, refer to AMM 33-13-00, Page block 501. (b) Do the operational test of the annunciator light test system in the cockpit, refer to AMM 33-14-00, Page block 501. (c) Do the operational check of system via MCDU, (Refer to AMM 21-26-00, Page block 501). (d) Do the operational test of the AFS, refer to AMM 22-96-00, Page block 501. (e) Do the operational test of the EIS, refer to AMM 31-60-00, Page block 501. (f) Do the operational test of the ECAM control panel, refer to AMM 31-50-00, Page block 501. (g) Do the ground scanning of the central warning system, refer to AMM 31-50-00, Page block 501. (3) Tests (a) Tests after the removal/installation of the items of equipment : 1 Do the test after the removal/installation of the Fuel Quantity Indicating Computer (FQIC) 3QT, refer to AMM 28-42-34, Page block 401. 2 Do the BITE test of the landing gear, refer to AMM 32-69-00, Page block 501. 3 Do the operational test of the circuit breaker monitoring system, refer to AMM 31-50-00, Page block 501. (b) Tests after the disconnection/connection of the connectors 13VC, 43VC, 112VC, 219VC, 221VC, 222VC, 223VC, 224VC, 226VC, 227VC, 228VC, 230VC, 231VC, 232VC, 240VC, 278VC, 282VC, 283VC, 1945VC, 1990VC and 2206VC : 1 Do the BITE test of the landing gear, refer to AMM 32-69-00, Page block 501. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 668 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2After the removal/installation of the offwing escape slides 7504MM and 7505MM, do the operational test of the emergency lighting system, refer to AMM 33-51-00, Page block 501. 3After the removal/installation torque tube assembly and shafts - MLG, do the functional test of the free-fall extension, refer to AMM 32-33-00, Page block 501. (c) Tests after the disconnection/connection of the connector 202VC : 1 Do the test after the removal/installation of the refuel valve 7QU (8QU), refer to AMM 28-25-51, Page block 401. 2 Do the test after the removal/installation of the refuel valve 10QU, refer to AMM 28-25-51, Page block 401. 3 Do the functional (BITE) test, refer to AMM 28-46-00, Page block 501. (d) Test after the disconnection/connection of the connectors 204VC, 206VC, 216VC, 274VC, 296VC and 1142VC : 1 Do the operational check of the GAPCU via CFDS, refer to AMM 24-41-00, Page block 501. (e) Test after the disconnection/connection of the connectors 208VC, 212VC, 218VC, 220VC, 1918VC, 1972VC and 1973VC : 1 Do the functional (BITE) test, refer to AMM 28-46-00, Page block 501. (f) Test after the disconnection/connection of the connectors 210VC, 214VC, 235VC, 292VC, 294VC, 1970VC : 1 Do the status report (BITE), refer to AMM 28-42-00, Page block 501. (g) Test after the disconnection/connection of the connectors 215VC, 217VC, 229VC, 239VC and 286VC : 1 Do the operational test of the Spoiler Elevator Computer 3 refer to AMM 27-94-00, Page block 501. (h) Test after the disconnection/connection of the connector 225VC : 1 Do the operational test of the main fuel pump system to ensure both center tank pumps feed for 2 mn after engine start, refer to AMM 28-21-00, Page block 501. (i) Test after the disconnection/connection of the connectors 234VC and 236VC : 1 Do the BITE test of the BSCU, refer to AMM 32-46-00, Page block 501. (j) Test after the disconnection/connection of the connectors 237VC and 288VC : 1 Do the operational test of the Elevator and Aileron Computer (ELACs), refer to AMM 27-93-00, Page block 501. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 669 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(k) Test after the disconnection/connection of the connectors 276VC and 1982VC : 1 No test. (l) Test after the disconnection/connection of the connector 280VC : 1 Do the operational test of the AFT cargo compartment heating system, refer to AMM 21-43-00, Page block 501. (m) Test after the disconnection/connection of the connector 284VC : 1 Do the operational test of the lavatory smoke-detection system, refer to AMM 26-17-00, Page block 501. (n) Test after the disconnection/connection of the connectors 290VC and 2453VC : 1 Done in preliminary tests. (o) Test after the disconnection/connection of the connectors 1152VC, 1916VC, 2212VC and 2216VC : 1 Do the operational test of the engine fire and overheat detection (loop/squib), refer to AMM 26-12-00, Page block 501. (p) Test after the disconnection/connection of the connector 1266VC : 1 Do the operational test of the wing-tank fuel control, refer to AMM 28-21-00, Page block 501. (q) Test after the disconnection/connection of the connector 1270VC : 1 Verify the ground at pin K of terminal block 1176VT, connector 3 and 6 in the contactor box 107VU. (r) Test after the disconnection/connection of the connector 1947VC : 1 Do the operational test of the emergency ram-air inlet, refer to AMM 21-55-00, Page block 501. (s) Test after the disconnection/connection of the connector 2200VC : 1 Do the operational test of the GPWS ground self-test function, refer to AMM 34-48-00, Page block 501). (t) Test after the disconnection/connection of the connector 2450VC : 1 Do the test after the removal/installation of the crossfeed valve actuator 5QE, refer to AMM 28-23-51, Page block 401. (u) Test after the disconnection/connection of the connector 2451VC : 1 Do the functional check of the electric pump of the Blue hydraulic system, (Refer to AMM 29-12-00, Page block 501). DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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(v) Test after the disconnection/connection of the connector 2452VC : 1 Do the operational test of the manual deployment and the retraction of the ram air turbine, refer to AMM 29-22-00, Page block 501. (4) Do a leak test of the ACT shroud system and the drain lines, Appendix 1. (5) Do the tests of the cabin pressure control and monitoring system, refer to AMM 21-31-00, Page block 501. (6) Do the tests of the cockpit and cabin temperature control system, refer to AMM 21-63-00, Page block 501. (7) Do the tests after the removal/installation of the FAC(1CC1, 1CC2), refer to AMM 22-66-34, Page block 401. (8) Do the operational test of the VHF system, refer to AMM 23-12-00, Page block 501. (9) Do the tests of the service interphone system, refer to AMM 23-44-00, Page block 501. (10) Do the tests of the cockpit voice recorder, refer to AMM 23-71-00, Page block 501. (11) Do the tests after the removal/installation of the AC current transformer(42XS), refer to AMM 24-23-17, Page block 401. (12) Do the tests after the removal/installation of the generator control unit (1XS), refer to AMM 24-23-34, Page block 401. (13) Do the tests after the removal/installation of the APU generator(8XS), refer to AMM 24-23-51, Page block 401. (14) Do the tests after the removal/installation of the AC auxiliary generator contactor(3XS), refer to AMM 24-23-55, Page block 401. (15) Do the tests of the emergency generation system , refer to AMM 24-24-00, Page block 501. (16) 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. (17) Do the test after the removal/installation of the offwing escape slides reservoirs, refer to AMM 25-62-46, Page block 401. (18) Do the tests of the engine fire and overheat detection system, refer to AMM 26-12-00, Page block 501. (19) Do the tests of the APU fire and overheat detection system, refer to AMM 26-13-00, Page block 501. (20) Do the tests of the engine fire extinguishing system, refer to AMM 26-21-00, Page block 501. (21) Do the tests of the APU fire extinguishing system, refer to AMM 26-22-00, Page block 501. (22) Do the tests of the rudder hydraulic actuation, refer to AMM 27-24-00, Page block 501. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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(23) Do the tests of the elevator hydraulic actuation, refer to AMM 27-34-00, Page block 501. (24) Do the tests of the flaps electrical control and monitoring system, refer to AMM 27-51-00, Page block 501. (25) Do the tests of the flap system, refer to AMM 27-54-00, Page block 501. (26) Do the tests of the slat electrical control and monitoring system, refer to AMM 27-81-00, Page block 501. (27) Do the tests of the slat system, refer to AMM 27-84-00, Page block 501. (28) Do the test after the removal/installation of the pedal position transducer unit, refer to AMM 27-92-15, Page block 401. (29) Do the test after the removal/installation of the flight control accelerometer, refer to AMM 27-92-16, Page block 401. (30) Do the test of the side stick assembly, refer to AMM 27-92-41, Page block 501. (31) Do the test of the ELAC system, refer to AMM 27-93-00, Page block 501. (32) Do the test of the SEC system, refer to AMM 27-94-00, Page block 501. (33) Do the test of the flight control pressure switches (10CE1,10CE2,10CE3), refer to AMM 27-96-00, Page block 501. (34) Do the test of the FCDC system, refer to AMM 27-96-00, Page block 501. (35) Do the tests of the intercell transfer system, refer to AMM 28-15-00, Page block 501. (36) Do the tests of the main fuel pump system, refer to AMM 28-21-00, Page block 501. (37) Do the tests of the APU fuel pump system, refer to AMM 28-22-00, Page block 501. (38) Do the tests of the fuel crossfeed system, refer to AMM 28-23-00, Page block 501. (39) Do the tests of the engine LP fuel shut off system, refer to AMM 28-24-00, Page block 501. (40) Do the tests of the fuel refuel/defuel system, refer to AMM 28-25-00, Page block 501. (41) Do the tests of the additional center tank transfer system, refer to AMM 28-28-00, Page block 501. (42) Do the tests of the APU LP fuel shut off system, refer to AMM 28-29-00, Page block 501. (43) Do the tests of the fuel quantity indicating system, refer to AMM 28-42-00, Page block 501. (44) Do the tests of the fuel tank level sensing system, refer to AMM 28-46-00, Page block 501. (45) Do the tests of the green main hydraulic power system, refer to AMM 29-11-00, Page block 501. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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(46) Do the tests after the removal/installation of the green hydraulic reservoir, refer to AMM 29-11-41, Page block 401. (47) Do the tests of the blue main hydraulic power system, refer to AMM 29-12-00, Page block 501. (48) Do the tests of the yellow main hydraulic power system, refer to AMM 29-13-00, Page block 501. (49) Do the tests after the removal/installation of the main HP-manifold, refer to AMM 29-13-14, Page block 401. (50) Do the tests of the power transfer unit (PTU), refer to AMM 29-23-00, Page block 501. (51) Do the tests of the yellow auxiliary hydraulic power system, refer to AMM 29-24-00, Page block 501. (52) Do the test of the hydraulic fluid quantity indicating system, refer to AMM 29-31-00, Page block 501. (53) Do the tests of the hydraulic fluid pressure indicating system, refer to AMM 29-32-00, Page block 501. (54) Do the tests after the removal/installation of the temperature transmitters, refer to AMM 29-33-11, Page block 401. (55) Do the tests of the hydraulic reservoir pressurization indicating system, refer to AMM 29-34-00, Page block 501. (56) Do the tests of the centralized fault display interface system, refer to AMM 31-32-00, Page block 501. (57) Do the tests of the digital flight data recording system, refer to AMM 31-33-00, Page block 501. (58) Do the tests of the central warning system, refer to AMM 31-50-00, Page block 501. (59) Do the tests after the removal/installation of the SDAC, refer to AMM 31-55-34, Page block 401. (60) Do the tests of the normal extension/retraction of the landing gear, refer to AMM 32-31-00, Page block 501. (61) Do a functional test of the free-fall extension system, refer to AMM 32-33-00, Page block 501. (62) Do the tests of the normal braking system, refer to AMM 32-42-00, Page block 501. (63) Do the tests of the alternate braking system with anti-skid, refer to AMM 32-43-00, Page block 501. (64) Do the tests of the alternate braking system without anti-skid, refer to AMM 32-44-00, Page block 501. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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(65) Do the tests of the parking brake system, refer to AMM 32-45-00, Page block 501. (66) Do the tests of the brake temperature system, refer to AMM 32-47-00, Page block 501. (67) Do the tests of the brake cooling system, refer to AMM 32-48-00, Page block 501. (68) Do the tests of the nose wheel steering, refer to AMM 32-51-00, Page block 501. (69) Do the tests of the service area lighting, refer to AMM 33-31-00, Page block 501. (70) Do the tests of the wheel well lighting, refer to AMM 33-37-00, Page block 501. (71) Do the test of the navigation lights, refer to AMM 33-41-00, Page block 501. (72) Do the tests of the landing lights, refer to AMM 33-42-00, Page block 501. (73) Do the tests of the anti-collision/strobe lighting, refer to AMM 33-48-00, Page block 501. (74) Do the tests of the cabin emergency lighting, refer to AMM 33-51-00, Page block 501. (75) 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. (76) Do the tests of the engine bleed air supply system, refer to AMM 36-11-00, Page block 501. (77) Do the tests of the APU bleed air supply and crossbleed system, refer to AMM 36-12-00, Page block 501. (78) Do the tests after the removal/installation of the APU electronic control box(59KD), refer to AMM 49-61-34, Page block 401. (79) Do the tests of the APU emergency shutdown circuit, refer to AMM 49-62-00, Page block 501. (80) Do the tests of the cargo compartment door electrical control system, refer to AMM 52-35-00, Page block 501. (81) Do the tests of the engine interface unit, refer to AMM 73-25-34, Page block 501. (82) Do the tests of the engine ignition system, refer to AMM 74-00-00, Page block 501. (83) Do the tests of the thrust reverser control and indicating system, refer to AMM 78-31-00, Page block 501. **D. C L** **O S** **E U** **P** (1) Config. 01 thru Config. 03 (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, 197BB, 197GB, 198BB and 198GB, refer to AMM 53-35-11, Page block 401. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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(c) Install the aft galley unit, refer to AMM 25-33-41, Page block 401. (d) Install the offwing escape slides 7504MM and 7505MM, refer to AMM 25-62-42, Page block 401. (e) Install : - the passenger compartment floor panels, refer to AMM 53-22-12, Page block 401 and AMM 53-42-12, Page block 401. - the passenger compartment floor covering, refer to AMM 25-28-41, Page block 401. - the insulation blankets, refer to AMM 25-80-00, Page block 201. - the overhead stowage compartments in the cabin, refer to AMM 25-24-41, Page block 401. - the upper cabin sidewall panels, refer to AMM 25-23-43, Page block 401. - the lower cabin sidewall panels, refer to AMM 25-23-44, Page block 401. - the cabin ceiling panels, refer to AMM 25-23-41, Page block 401. - the cabin cove light panels, refer to AMM 25-23-48, Page block 401. - the passenger compartment seats, refer to AMM 25-21-41, Page block 001. - the FWD cargo compartment ceiling panel, refer to AMM 25-54-12, Page block 401. - the FWD cargo compartment sidewall panel, refer to AMM 25-54-12, Page block 401. - the FWD cargo compartment floor panel, refer to AMM 53-22-14, Page block 401. - the AFT cargo compartment sidewall panel, 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) In the FWD cargo compartment, install the panels 131AC, 131AW, 131BW, 131CW, 131DW, 132BW, 131HC, 131KC, 131LC, 131BC and 131CC, refer to AMM 06-41-53, Page block 1. (h) 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. (i) Remove the safety equipment and close the main landing gear doors, refer to AMM 32-12-00, Page block 201.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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(j) Remove the safety equipment and close the FWD/AFT cargo compartment doors, refer to AMM 52-30-00, Page block 201. (k) Close the accessory compartment door 312AR, refer to AMM 52-41-16, Page block 201. (l) Close the maintenance door 314AR, refer to AMM 52-41-23, Page block 201. (m) Close the avionics door 822, refer to AMM 52-41-00, Page block 201. (n) Close the APU doors 315AL and 316AR, refer to AMM 52-41-00, Page block 201. (o) Close the passenger/crew door 841, refer to AMM 52-10-00, Page block 001. (p) Remove the access platform(s). (q) De-energize the aircraft electrical circuits, refer to AMM 24-41-00, Page block 201. (r) Lower the aircraft, refer to AMM 07-11-00, Page block 201. (s) Restore the systems and the aircraft to normal operating condition. **E. D O** **C U** **M E** **N T**  **A**

**T I** **O N**  Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 676 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 1, Sheet 1 Hookup Chart 1 (Kit D70)

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 677 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 2, Sheet 1 Config. 01: Hook-up Chart (Kit B04)
DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 678 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

**AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  **Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F**  **Fax : (33) 5 61 93 42 51 ATA SYSTEM : 28**  **TITLE : FUEL - TANKS - INSTALL PROVISIONS FOR TWO ACT ON A320 WITH BULK CONFIGURATION MODIFICATION No. :** 150855K13954, 25415P4179, 25696P4347, 25713J1492, 25713K4481, 26110J1523, 26110K4482, 26138K4772, 27115J1522, 27377K4984, 27378K4985, 27379K4999, 27380K5000, 27381K5002, 27446P5502, 27447P5503, 27448P5504, 27717K5539, 28068P5759, 28378J2056, 28661J2073, 28817J1973, 28900P8797, 30248P11386, 30356P6676, 30356P6683, 30373K6720, 31110K7004, 31143K7155, 31642K7282, 31700K7502, 31812K7403, 32120K7850, 32261J2241, 33198K8488, 33199K8489, 33373K8623, 33492J2482, 34751K9651, 34760K9660, 35068P9022, 35248K9948, 35282P9110, 37580K11542, 39156K12369 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) : PANEL DESIGNATION FIN LOCATION 122VU LIGHTING/ANN LT SPLY/XFMR/BUS 1 26LP 04 X 49VU LIGHTING/XFMR/115.5V/ESS BUS 29LP 03 H 122VU LIGHTING/ANN LT SPLY/XFMR/STAT INV 28LP 03 X (f) Operational test of the annunciator light test system. 1 Do an operational test of the annunciator light test system in the cockpit, refer to AMM 33-14-00, Page block 501. NOTE : During the test, make sure that, on panel HYD/FUEL 40VU, the annunciator lights of the ACT indicator push-button switch stay off. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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(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 121VU ACT PUMP SPLY 25QH 29 Q 2 Open the ACT Transfer Valve 165QM by removing the actuator and move the valve by hand or electrically by closing these circuit breakers : PANEL DESIGNATION FIN LOCATION 121VU ACT XFR VALVE MAN CTL 30QH 29 N 121VU ACT XFR VALVE AUTO CTL 9QH 29 P and on 40VU, pushing the ACT P/B. P/B lights FAULT and FWD must come on. 3 In the LH MLG Bay on the rear side of the center tank, check at the mechanical indicator that the ACT XFR Valve is open. 4 Make sure that the ACT pump is not running. **(2) Leak test of the ACT shroud system and drain lines.** (a) Test Procedure 1 On the GPG set the air supply maximum pressure to 1,4 bar (20 psi). 2 Introduce air from the GPG into the ACT system drain-line. Increase the pressure to 1,4 bar (20 psi) and retain at this pressure for 15 minutes. 3The 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. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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2. Leak test of the ACT provisions in the center tank. A. Leak Test NOTE : The test that follows should only be carried out if the aircraft does not have ACT(s) installed and will not have ACT(s) installed before flight. **(1) Test Preparation** (a) Make sure that a fuel bowser with sufficient capacity is available. (b) Connect the fuel bowser to the refuel coupling. **(2) Test Procedure** (a) Operate the leak monitors for the ACT 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 and the ACT interspace drain. If fuel comes out of the ACT leak-monitor then there is a problem with the pipework of the ACT refuel/transfer line. Carry out a repair and do the test procedure again. **(3) After Test** (a) Retain the aircraft configuration for the next test. 3. Leak test of the ACT pressurization system. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

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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 pressurization system does not leak and that the non-return valves in the system operate correctly. The test is to be done once on aircraft fitted with provisions for ACT(s) before the installation of the ACT. **(1) Test Preparation** (a) In the AFT cargo compartment, remove the ceiling access panel 151CC to get access to the test connectors T1 and T2 of the air pressurization system, refer to AMM 25-55-11, Page block 401. (b) Connect the Test Tool 1 to the test port T1. (c) Connect the Test Tool 2 to the test port T2. (d) Remove the datum pipe guard in the belly fairing and install a blank. (e) Make sure that the connection(s) to the ACT(s) have blanks installed. (f) Close the air shut off valve. **(2) Test Procedure** (a) Introduce air from the GPG and raise the pressure to 1.4 bar (20.0 psi), retain at this pressure for 10 minutes. (b) Isolate the aircraft ACT pressurization system from the GPG. (c) Check that the pressure indicated at T1 remains the same over a ten minute period at 1.4 bar (20.0 psi). Make sure there is no leakage from the pipework between the upstream non-return valve and the air shut-off valve and no reverse leakage through the upstream non-return valve. (d) Check that the pressure indicated at T2 remains at zero. Make sure there is no leakage through the air shut-off valve. (e) Open the air shut-off valve. (f) Increase the pressure to 1.4 bar (20 psi) and check that this pressure is indicated at T1 and T2. (g) Isolate the aircraft ACT pressurization system from the GPG. (h) Check that the pressure indicated at T1 and T2 remains the same over a ten minute period at 1.4 bar (20 psi). Make sure there is no leakage downstream of the air shut-off valve and check the correct opening of the pressure reducing valve and the downstream non-return valve.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 4 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

(i) Reduce the pressure on the GPG to zero and release any pressure retained in the system at T1. (j) Check that the pressure indicated at T2 remains at 1.4 bar (20 psi). This will show the correct operation of the downstream non-return valve and no reverse leakage through the valve. (k) Bleed air from T2 to reduce pressure to zero. **(3) Acceptable Results** (a) The system must not leak. The pressure in the system must not decrease. If a leak is found, a repair must be made and the test procedure done again. **(4) Close Up** (a) Release the pressure from the ACT pressurization system. (b) Carefully remove the blank from the datum pipe inlet in the belly fairing and replace the guard. (c) Disconnect the test tool 1 from T1. (d) Disconnect the test tool 1 from T2. (e) Close the air shut-off valve. (f) In the AFT cargo compartment, install the ceiling access panel 151CC, refer toAMM 25-55-11, Page block 401.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 5 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

Figure 1, Sheet 1 Leak Test of the ACT Shroud System and Drain Lines

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 6 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

Figure 1, Sheet 2 Leak Test of the ACT Shroud System and Drain Lines

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 7 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

Figure 2, Sheet 1 Access to the Test Points T1 and T2

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 8 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

Figure 3, Sheet 1 ACT Test Arrangement - Test Tool 1 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 9 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 1

Figure 4, Sheet 1 ACT Test Arrangement - Test Tool 2
DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 10 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

**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 PROVISIONS FOR TWO ACT ON A320 WITH BULK CONFIGURATION MODIFICATION No. :** 150855K13954, 25415P4179, 25696P4347, 25713J1492, 25713K4481, 26110J1523, 26110K4482, 26138K4772, 27115J1522, 27377K4984, 27378K4985, 27379K4999, 27380K5000, 27381K5002, 27446P5502, 27447P5503, 27448P5504, 27717K5539, 28068P5759, 28378J2056, 28661J2073, 28817J1973, 28900P8797, 30248P11386, 30356P6676, 30356P6683, 30373K6720, 31110K7004, 31143K7155, 31642K7282, 31700K7502, 31812K7403, 32120K7850, 32261J2241, 33198K8488, 33199K8489, 33373K8623, 33492J2482, 34751K9651, 34760K9660, 35068P9022, 35248K9948, 35282P9110, 37580K11542, 39156K12369 1. Instruction Manual for the Adjustment Device PN : 98D28108641000

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 1 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

Figure 1, Sheet 1 Instruction Manual for the Adjustment Device PN : 98D28108641000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 2 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

Figure 1, Sheet 2 Instruction Manual for the Adjustment Device PN : 98D28108641000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 3 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

Figure 1, Sheet 3 Instruction Manual for the Adjustment Device PN : 98D28108641000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 4 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

Figure 1, Sheet 4 Instruction Manual for the Adjustment Device PN : 98D28108641000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 5 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

Figure 1, Sheet 5 Instruction Manual for the Adjustment Device PN : 98D28108641000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 6 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

Figure 1, Sheet 6 Instruction Manual for the Adjustment Device PN : 98D28108641000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 7 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

Figure 1, Sheet 7 Instruction Manual for the Adjustment Device PN : 98D28108641000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 8 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

Figure 1, Sheet 8 Instruction Manual for the Adjustment Device PN : 98D28108641000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 9 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

Figure 1, Sheet 9 Instruction Manual for the Adjustment Device PN : 98D28108641000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 10 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

Figure 1, Sheet 10 Instruction Manual for the Adjustment Device PN : 98D28108641000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 11 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

Figure 1, Sheet 11 Instruction Manual for the Adjustment Device PN : 98D28108641000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 12 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

Figure 1, Sheet 12 Instruction Manual for the Adjustment Device PN : 98D28108641000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 13 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

Figure 1, Sheet 13 Instruction Manual for the Adjustment Device PN : 98D28108641000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 14 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

Figure 1, Sheet 14 Instruction Manual for the Adjustment Device PN : 98D28108641000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 15 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

Figure 1, Sheet 15 Instruction Manual for the Adjustment Device PN : 98D28108641000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 16 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

Figure 1, Sheet 16 Instruction Manual for the Adjustment Device PN : 98D28108641000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 17 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

Figure 1, Sheet 17 Instruction Manual for the Adjustment Device PN : 98D28108641000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 18 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

Figure 1, Sheet 18 Instruction Manual for the Adjustment Device PN : 98D28108641000 DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 19 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN APPENDIX 2

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DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 20 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN REPORTING SHEET

**TITLE : FUEL - TANKS - INSTALL PROVISIONS FOR TWO ACT ON A320 WITH BULK CONFIGURATION MODIFICATION No. :** 150855K13954, 25415P4179, 25696P4347, 25713J1492, 25713K4481, 26110J1523, 26110K4482, 26138K4772, 27115J1522, 27377K4984, 27378K4985, 27379K4999, 27380K5000, 27381K5002, 27446P5502, 27447P5503, 27448P5504, 27717K5539, 28068P5759, 28378J2056, 28661J2073, 28817J1973, 28900P8797, 30248P11386, 30356P6676, 30356P6683, 30373K6720, 31110K7004, 31143K7155, 31642K7282, 31700K7502, 31812K7403, 32120K7850, 32261J2241, 33198K8488, 33199K8489, 33373K8623, 33492J2482, 34751K9651, 34760K9660, 35068P9022, 35248K9948, 35282P9110, 37580K11542, 39156K12369 Pleasecompletetheappropriateitem(AorB): A - SB WILLBEembodied .................................................................. YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiement:

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............................................................................................................................................................................. B - SB HASBEENembodied on aircraft: ............................................................................................................

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

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

............................................................................................................................................................................. From Airline: ........................................................................................................................................................ Name/Title: .......................................................................................................................................................... Signature:..................... Date: ..................................................... Ifoperationaldocumentationisaffected(seeParagraph1

.KofthisSB):If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either : Advance data................................................................................... YES/NO Or : Intermediate/Temporary revision ..................................................... YES/NO 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. Pleasereturnthiscompletedsheetto: **AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  Attn: SEDCC1 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 e-mail: sb.reporting@airbus.com Or via your Resident Customer Support Office. DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 1 of 1 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN REPORTING SHEET

Alternatively, SB lists via letters or fax are also accepted.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 1 of 1 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN REPORTING QUALITY

**TITLE : FUEL - TANKS - INSTALL PROVISIONS FOR TWO ACT ON A320 WITH BULK CONFIGURATION MODIFICATION No. :** 150855K13954, 25415P4179, 25696P4347, 25713J1492, 25713K4481, 26110J1523, 26110K4482, 26138K4772, 27115J1522, 27377K4984, 27378K4985, 27379K4999, 27380K5000, 27381K5002, 27446P5502, 27447P5503, 27448P5504, 27717K5539, 28068P5759, 28378J2056, 28661J2073, 28817J1973, 28900P8797, 30248P11386, 30356P6676, 30356P6683, 30373K6720, 31110K7004, 31143K7155, 31642K7282, 31700K7502, 31812K7403, 32120K7850, 32261J2241, 33198K8488, 33199K8489, 33373K8623, 33492J2482, 34751K9651, 34760K9660, 35068P9022, 35248K9948, 35282P9110, 37580K11542, 39156K12369 Use this form to tell us what is your perception of the quality of this Service Bulletin.The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to futher improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) -Quality rating of this SB 4 3 2 1 -Quality rating of the Accomplishment Instructions 4 3 2 1 -Quality rating of the Illustrations 4 3 2 1 -Is this SB easy to understand ? Y / N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue.

Planning Material Instructions X Effectivity X Kit Content X Preparation X Reason X List of Materials X Mod/Inspection X Manpower Operator Supplied X Test X References X Re-identification X Close-up X Publication X Tooling X Illustrations Comments:

Operator : Date: Name/Title : Please return this form to: **AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte** DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 1 of 1 Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN REPORTING QUALITY

**31707 BLAGNAC CEDEX FRANCE** Attn: SEMB Service Bulletins Management FAX: (+33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE : Oct 13/04 SERVICE BULLETIN No. : A320-28-1132

REVISION No. : 04 - Feb 01/10 Page : 1 of 1 Printed in France © AIRBUS 2008 All rights reserved