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

ADDITIONAL WORK

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 reserved
SERVICE 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 reserved
SERVICE 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.

FILING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

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 reserved
SERVICE 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.

REVISION SEQUENCE

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 reserved
SERVICE 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/OPERATIONAL CONSEQUENCES

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 AFFECTED Yes

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 reserved
SERVICE 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.

EFFECTIVITY

This Service Bulletin is applicable to these operator(s) :

62X 95V KNE LMJ

NOTE : This Service Bulletin is written for the operators listed above. The modification in this Service

Bulletin can be done by other operators. If other operators want to do this modification, use the

RFC/RMO procedure and write to :

AIRBUS

CUSTOMER SERVICES DIRECTORATE

SC Department

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

CONCURRENT REQUIREMENTS

None

REFERENCES/REPERCUSSIONS

TFU : None

OEB : None

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 reserved
SERVICE BULLETIN

SUMMARY

AOT : None

SIL : None

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : No

OTHERS : None

NATURE OF THE WORK

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

MATERIAL INFORMATION

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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 13

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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. PLANNING INFORMATION

A. EFFECTIVITY

(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

REVISION No. : 04 - Feb 01/10 Page : 1 of 678

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 2

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

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 reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 4

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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. CONCURRENT REQUIREMENTS

None

C. REASON

(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 reserved
SERVICE 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. DESCRIPTION

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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 22

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

(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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE BULLETIN

(bl) Install the AFT cargo compartment panels 151AW, 151BW and 152BW at FR47.

E. COMPLIANCE

(1) Classification

Optional

(2) Accomplishment Timescale

In accordance with operators’ maintenance schedule.

F. APPROVAL

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. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the

work. These estimates assume that the work will be done by experienced personnel, and may

need to be revised upwards to suit 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 reserved
SERVICE BULLETIN

H. WEIGHT AND BALANCE

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. ELECTRICAL LOAD DATA

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 reserved
SERVICE BULLETIN

J. REFERENCES

Aircraft Maintenance Manual (AMM) : 06-31-53 06-41-53 07-11-00 11-00-00

12-34-24 20-21-11 20-21-12 20-21-15

20-23-11 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

REVISION No. : 04 - Feb 01/10 Page : 31

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 32

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 33

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SERVICE 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

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

REVISION No. : 04 - Feb 01/10 Page : 34

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE BULLETIN

K. PUBLICATIONS AFFECTED

Aircraft Maintenance Manual (AMM) : 05-21-50 10-11-00 10-12-00 11-31-31

12-11-28 28-00-00 28-10-00 28-11-00

28-11-27 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 reserved
SERVICE 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. INTERCHANGEABILITY/MIXABILITY

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 reserved
SERVICE BULLETIN

2. MATERIAL INFORMATION

A. MATERIAL - PRICE AND AVAILABILITY

(1) Material

Customers with aircraft shown in the effectivity of this Service Bulletin should send a

purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is :

AIRBUS 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. INDUSTRY SUPPORT INFORMATION

Refer to Paragraph 2.A.(2) : Price and Availability.

C. LIST OF COMPONENTS

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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 107

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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. LIST OF MATERIALS - OPERATOR SUPPLIED

(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 reserved
SERVICE 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 reserved
SERVICE 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. PARTS TO BE RE-IDENTIFIED BY THE OPERATOR

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 reserved
SERVICE 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. TOOLING - PRICE AND AVAILABILITY

ITEM PART NUMBER QTY DESCRIPTION

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

REVISION No. : 04 - Feb 01/10 Page : 133

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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. SPECIAL TOOLS

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 reserved
SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL

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

REVISION No. : 04 - Feb 01/10 Page : 135

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

4 Open the avionics door 822, refer to AMM 52-41-00, Page block 201.

5 Open the passenger/crew door 841, refer to AMM 52-10-00, Page block 201.

6 Open the FWD/AFT cargo compartment doors, refer to AMM 52-30-00, Page

block 201.

NOTE : Make sure that the applicable safety equipment is installed at

the cargo compartment doors.

7 Open the 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.

10 Depressurize the Green, Blue and Yellow hydraulic reservoirs, refer to AMM

29-14-00, Page block 201.

11 Put the warning notices in position to tell persons not to pressurize the hydraulic

systems.

12 Open the accessory compartment door 312AR, refer to AMM 52-41-16, Page

block 401.

13 Open the maintenance door 314AR, refer to AMM 52-41-23, Page block 401.

14 Open the APU doors 315AL and 316AR, refer to AMM 52-41-00, Page block 201.

15 Remove 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

REVISION No. : 04 - Feb 01/10 Page : 136

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

- 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.

16 Remove and retain the aft galley unit to get access to the pressure seals

7105VP, 7106VP, 7107VP, 7108VP and 7110VP at FR70, refer to AMM

25-33-41, Page block 401.

17 Remove and retain the belly fairing panels 147FB, 148FB, 197BB, 197GB,

198BB and 198GB, refer to AMM 53-35-11, Page block 401.

18 In the cockpit, remove the lining panels 211HC, 212FC, 212KC, 212KW, 212JW

and 212HW, refer to AMM 06-41-53, Page block 1 and AMM 25-13-41, Page

block 401.

19 In 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.

20 Defuel the center tank, refer to AMM 28-25-00, Page block 301.

21 Obey the instructions for the fuel safety procedures, refer to AMM 28-00-00,

Page block 301 and AMM 28-10-00, Page block 301 and make sure that the

ventilation of the center tank is correct.

22 On the FUEL section of the HYD/FUEL Panel 40VU, make sure that all L

TK PUMPS and R TK PUMPS pushbutton switches are released (the OFF

legends are on).

23 Do the preparation procedure as specified in the removal/installation of the

indicator - fuel quantity, multi-tank (6QT), refer to AMM 28-42-22, Page block 401.

24 Make sure that there is(are) warning notice(s) on the external power receptacle

to tell persons not to connect an external power source.

25 Make sure that the EMER EXIT LT pushbutton switch on the 25VU is set to OFF.

26 In the cockpit, on the Overhead Panel 35VU, release the BAT pushbutton

switches.

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

REVISION No. : 04 - Feb 01/10 Page : 137

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

27 Put a warning notice in position in the cockpit to tell persons not to operate

the fuel system.

28 Put a warning notice in position on the Panel 35VU to tell persons not to

operate the batteries.

29 Put a warning notice in position on the Refuel/Defuel Panel 800VU to tell

persons not to operate the NORMAL BATTERY switch.

30 Put a warning notice in position in the cockpit to tell persons not to start the APU.

31 Put a warning notice in position in the cockpit to tell persons not to start the

ENG1, 2.

32 Disconnect the battery connectors

a For the job set-up, refer to the removal/installation of the batteries, refer to

AMM 24-38-51, Page block 401.

b Turn the knurled nut a quarter turn.

c Disconnect the connectors.

d Put blanking caps on the disconnected electrical connectors.

(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

REVISION No. : 04 - Feb 01/10 Page : 138

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SERVICE BULLETIN

(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

REVISION No. : 04 - Feb 01/10 Page : 139

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SERVICE BULLETIN

(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

REVISION No. : 04 - Feb 01/10 Page : 140

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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. MODIFICATION

(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

REVISION No. : 04 - Feb 01/10 Page : 141

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 142

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

d Transfer 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

b Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 143

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SERVICE BULLETIN

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

d Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 144

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SERVICE BULLETIN

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

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REVISION No. : 04 - Feb 01/10 Page : 145

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SERVICE BULLETIN

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

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REVISION No. : 04 - Feb 01/10 Page : 146

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SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 147

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SERVICE BULLETIN

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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SERVICE BULLETIN

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 :

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SERVICE BULLETIN

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.

d Adjust the release cable so that the dimension "B" is between 9.8 mm (0.386

in.) and 13.2 mm (0.519 in.) as shown in Detail Z10-10.

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SERVICE BULLETIN

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.

g Adjust the length of the adapter, Item 002, and connect the adapter with the

lever with these items as shown in Section B10-B10 :

1 pin MS20392-2C19 Item 036

3 washer NAS1149C0332R Item 070

1 pin MS24665-153 Item 080

h Secure the both rod ends and the adjustment nuts of the release cable

with lockwire (Mat. No. 19-010) as shown in Details V7-10 and Z7-9 and

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

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SERVICE BULLETIN

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 :

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SERVICE BULLETIN

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.

d Adjust the release cable so that the dimension "B" is between 9.8 mm (0.386

in.) and 13.2 mm (0.519 in.) as shown in Detail Z10-10.

e Install this item as shown in Details V7-10 and Z10-10 :

1 adapter L32A319-165-002 Item 002

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SERVICE BULLETIN

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.

g Adjust the length of the adapter, Item 002, and connect the adapter with the

lever with these items as shown in Section B10-B10 :

1 pin MS20392-2C19 Item 036

3 washer NAS1149C0332R Item 070

1 pin MS24665-153 Item 080

h Secure the both rod ends and the adjustment nuts of the release cable

with lockwire (Mat. No. 19-010) as shown in Details V7-10 and Z7-9 and

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

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SERVICE 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.

2 Transfer 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

b Transfer drill the holes and open the holes to final dimension.

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SERVICE 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’.

a Transfer 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.

b Open the holes to final dimension.

c Install these items :

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SERVICE BULLETIN

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.

b Open 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

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SERVICE BULLETIN

1 plate D5397483921200 Item (204) Discard

1 section D5347047400200 Item (230) Discard

1 section D5347047400300 Item (231) Discard

3 Close 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

REVISION No. : 04 - Feb 01/10 Page : 158

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 159

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

b Transfer drill the holes to the plate, Item 009, and open the holes to final

dimension.

c Install this item as shown in drawing D53371046000, Sheet 5, Sections

F1-F5 and C5-C5 :

1 plate D5337107420200 Item 009

with :

2 pin DAN6-6-4 Item 021

4 pin DAN5-6-4 Item 022

6 collar NSA5075-6 Item 025

8 rivet LN9198-4012CF Item 035

10 pin DAN5-5-7 Item 036

8 pin DAN5-5-6 Item 037

12 collar NSA5075-5 Item 038

6 collar NSA5076-5 Item 039

d Put these items in position as shown in drawing D53371046000, Sheet 5,

Sections F1-F5, B5-B5 and Detail A5-5 :

1 wall D5337311520200 Item 010

1 plate D5337311920200 Item 011

2 angle D5337309820000 Item 012

2 stiffener D5337307220100 Item 013

1 stiffener D5337307220000 Item 014

1 profile D5337312120400 Item 015

1 profile D5337312120600 Item 016

1 profile D5337312120700 Item 017

1 profile D5337312120200 Item 018

e Transfer drill the holes, drill the additional holes, open all holes to final

dimension and install with these items as shown in drawing D53371046000,

Sheet 5, Sections F1-F5, B5-B5 and A5-A5 and Detail A5-5 :

15 rivet LN9198-4009CF Item 031

3 rivet LN9198-4010CF Item 032

10 rivet LN9198-4011CF Item 033

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

REVISION No. : 04 - Feb 01/10 Page : 160

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SERVICE BULLETIN

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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining 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

REVISION No. : 04 - Feb 01/10 Page : 161

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

NOTE : Do not remove all fasteners at the same time. Replace the

fasteners step by step.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining 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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining 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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

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

REVISION No. : 04 - Feb 01/10 Page : 162

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining fasteners, Item 865 and 806, will be installed

during the installation of the reinforcing straps at 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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining fasteners, Item 865 and 806, will be installed

during the installation of the reinforcing straps at 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

REVISION No. : 04 - Feb 01/10 Page : 163

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SERVICE BULLETIN

NOTE : Do not remove all fasteners at the same time. Replace the

fasteners step by step.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining fasteners, Item 865 and 806, will be installed

during the installation of the reinforcing straps at 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

2 Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 164

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

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SERVICE BULLETIN

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

b Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 166

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 167

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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) :

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SERVICE BULLETIN

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.

b Transfer 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

e Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 169

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SERVICE BULLETIN

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.

b Transfer 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

e Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 170

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SERVICE BULLETIN

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.

b Transfer 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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SERVICE BULLETIN

8 pin DAN7-5-5 Item 041

4 pin DAN7-5-6 Item 042

12 collar DAN12-5 Item 043

e Transfer 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

b Adjust the support, Item 80.

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

REVISION No. : 04 - Feb 01/10 Page : 172

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 173

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

3 Temporarily 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

4 Temporarily 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.

6 Adjust the X-gaps with the adjustment screws at FR47 as shown in drawing

D25572624008, Sheet 12 :

a Adjust 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).

7 Adjust 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.

8 Adjust 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

REVISION No. : 04 - Feb 01/10 Page : 174

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

9 Adjust 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.

b Temporarily 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

10 Remove 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.

2 Temporarily 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

REVISION No. : 04 - Feb 01/10 Page : 175

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

3 Temporarily 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.

4 Temporarily 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.

6 Adjust 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.

7 Adjust 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.

8 Adjust 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.

9 Adjust 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

REVISION No. : 04 - Feb 01/10 Page : 176

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SERVICE BULLETIN

b Adjust 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

10 Remove 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

REVISION No. : 04 - Feb 01/10 Page : 177

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

3 Transfer drill the holes from aircraft structure to the beam and open the holes

to final dimension.

4 Install this item :

1 beam D2827099720000 Item 000

with :

8 bolt NSA5031-3-10 Item 770

8 nut NAS1726C3P Item 807

8 washer NAS1149C0332R Item 808

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

REVISION No. : 04 - Feb 01/10 Page : 178

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

(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

REVISION No. : 04 - Feb 01/10 Page : 179

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 180

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 181

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SERVICE BULLETIN

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

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REVISION No. : 04 - Feb 01/10 Page : 182

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SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 183

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SERVICE BULLETIN

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.

g Attach the tube, Item 032, at the bracket, Item 033, between FR40 and FR41

with these items as shown in Detail W9-11 :

1 clamp D28270935002 Item 035

1 clamp D28270935004 Item 037

2 washer NAS1149C0332R Item 083

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

REVISION No. : 04 - Feb 01/10 Page : 184

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SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 185

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

with :

4 washer NAS1149C0432R Item 082

2 nut NAS1726-4E Item 085

1 bolt NAS1304-8 Item 089

1 bolt NAS1304-10 Item 091

d Push the flange, Item 040, over the inner tube, Item 034, and install the

nut, Item 066.

e Assemble these items as shown in Detail Q9-11 :

2 spacer A2827090120400 Item 031

1 tube D2827092800000 Item 044

1 tube D2827092900000 Item 046

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

REVISION No. : 04 - Feb 01/10 Page : 186

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

m Install 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

REVISION No. : 04 - Feb 01/10 Page : 187

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 188

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 189

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

2 Transfer drill the two holes in the upper beam and open them to final dimension.

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

REVISION No. : 04 - Feb 01/10 Page : 190

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

3 Connect this item at the vent shroud line as shown in drawing D28270973002,

Sheet 6 :

1 tube D2827093603400 Item 100

and install these items as shown in Details Y6-8 and X6-8 and 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

REVISION No. : 04 - Feb 01/10 Page : 191

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 192

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

with :

6 washer NAS1149C0332R Item 007

6 screw NAS1096-3-8 Item 009

6 clamp MS21919WDE11 Item 015

10 Install these items at FR46 as shown in Detail S6-9 :

1 tee NAS1763D080808 Item 033

1 fitting D2827094320000 Item 204

with :

2 nut NAS1726-3E Item 010

2 screw NAS1096-3-10 Item 012

11 Install 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

12 Install these items between FR47 and FR48 as shown in Detail Q6-10 :

1 nut AN924-8D Item 003

1 washer NAS1149D1290K Item 004

1 tee MS21912D8 Item 013

1 washer NAS1149D1216H Item 023

13 Install 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 reserved
SERVICE 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

14 Install these items as shown in Details P10-10 and S6-9 :

4 washer NAS1149C0332R Item 007

4 screw NAS1096-3-8 Item 009

2 strap E0090-10-125NN Item 025

4 clamp NSA5519-11 Item 035

4 nut NAS1291C3M Item 036

15 Install these items with sealant (Mat. No. 09-016) at the belly fairing as shown in

Detail Q6-10 :

1 reducer MS21916D8-6 Item 017

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

16 Install this item with adhesive (Mat. No. 08-010) as shown in Detail Q6-10 :

1 placard D2827094421400 Item 214

17 Install 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

REVISION No. : 04 - Feb 01/10 Page : 194

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 195

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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

5 At 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

b Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 197

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 198

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

m Install this item as shown in Detail V4-4 :

3 plate D5397492700000 Item 054

with :

9 screw NAS1102E3-7 Item 400

9 washer DAN125-4 Item 402

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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

10 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

11 Remove the cable harness 4650VB/1R

Refer to Drawing(s) :

D92991450014 Sheet(s) 12, V01 and V02

12 Remove the cable harness 4672VB/2M

Refer to Drawing(s) :

D92991472013 Sheet(s) 14, B01 and B02, H01 to H04, W01, X01, V01 and V02

13 Remove the cable harness 4673VB/1S

Refer to Drawing(s) :

D92991473003 Sheet(s) 4, B01 and B02, H01 to H04, W01, X01, V01 and V02

14 Remove the cable harness 4680VB/1MB

Refer to Drawing(s) :

D92991480012 Sheet(s) 13, B01 to B03, H01 to H05, W01, X01, V01 and V02

15 Remove the cable harness 4681VB/7M

Refer to Drawing(s) :

D92991481003 Sheet(s) 4, B01, H01, W01, V01

16 Cable 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 reserved
SERVICE BULLETIN

Refer to Drawing(s) :

D92991483005 Sheet(s) 6, B01 and B02, H01 to H09, W01 and W02,

X01 and X02, V01 to V04

17 Remove the cable harness 4692VB/2M

Refer to Drawing(s) :

D92991492005 Sheet(s) 6, B01, H01, W01, X01, V01

18 Remove the cable harness 4693VB/1S

Refer to Drawing(s) :

D92991493003 Sheet(s) 4, B01 and B02, H01 to H03, W01, X01, V01 and V02

19 Remove 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 reserved
SERVICE 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

10 Remove the wires of cable harness 4225VB

Refer to Drawing(s) :

D92999561010 Sheet(s) 20, lines 1 and 2

D92999561010 Sheet(s) 21, BEFORE MOD.

11 Remove the wires of cable harness 4226VB

Refer to Drawing(s) :

D92999559024 Sheet(s) 21 and 22,

12 Remove 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

13 Remove the wires of cable harness 4232VB

Refer to Drawing(s) :

D92999559026 Sheet(s) 25

14 Remove the wires of cable harness 4233VB

Refer to Drawing(s) :

D92999559028 Sheet(s) 27, lines 1 to 4

15 Remove the wires of cable harness 5214VB

Refer to Drawing(s) :

D92999559030 Sheet(s) 28, line 1

16 Remove the wires of cable harness 5220VB

Refer to Drawing(s) :

D92990820000 Sheet(s) 1 and B01

17 Remove 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 reserved
SERVICE BULLETIN

Refer to Drawing(s) :

D92990824002 Sheet(s) 3, B01, H01, W01 and V01

18 Remove 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 :

a Clean 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 reserved
SERVICE 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 reserved
SERVICE 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

2 At FR53, remove as shown in drawing D255762400, Sheet 6.

1 TDP DAN152-1 Item (502) Discard

2 screw NAS1102-3-18 Item (501) Discard

3 At FR52A, install as shown in drawing D2557624004, Sheet 6.

1 TDP DAN152-1 Item 502

with :

2 screw NAS1102-3-18 Item 501

4 At 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

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SERVICE 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

10 Install 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 reserved
SERVICE 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

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SERVICE 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

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SERVICE 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

10 Install 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

11 Install 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

12 Install 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

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SERVICE BULLETIN

1 filter A2163302000000 Item 027

1 inlet A2151034520000 Item 028

1 nut AN924-4D Item 092

13 Install 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.

14 Install 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.

15 Install this item with adhesive (Mat. No. 08-010) as shown in Section C13-C10 :

1 placard D2827094421000 Item 210

16 Install 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

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SERVICE 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

17 Install 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 reserved
SERVICE 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).

d Temporarily 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.

b Cut 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 reserved
SERVICE 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

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SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 226

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SERVICE BULLETIN

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 reserved
SERVICE 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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 229

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 235

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 237

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

1 Washer ASNA2397-416L

Item 39

4 Washer ASNA2397D10L

Item 40

1 Nut NSA5050-4

Item 42

2 Nut NSA5050-3

Item 48

Wire-Lock MS20995C32

3 Install the refuel valve 41QU and the canister 164QM :

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 reserved
SERVICE 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 reserved
SERVICE BULLETIN

1 Washer ASNA2397-6L

Item 16

4 Nut NAS1726C4E

Item 18

1 Nut MS21042L06

Item 22

1 Lead-Bonding E0088-16-100

Item 24

Wire-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 reserved
SERVICE 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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 242

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 244

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 246

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

10 Install :

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

11 Install :

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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 255

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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

5 Attach 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

REVISION No. : 04 - Feb 01/10 Page : 257

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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 reserved
SERVICE 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

a On the mounting rail of the terminal block 1853VT, install :

1 Module NSA937901MA2206

in position 28

1 Module NSA937901MA2204

in position 62

2 Module Identification NSA937901E2

1 Module Identification NSA937901E6

1 Module Identification NSA937901E8

(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

REVISION No. : 04 - Feb 01/10 Page : 260

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 262

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 263

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

NOTE : You must install these computers again after the modification

of the wiring.

b Disconnect the bonding braid.

c Remove the attachment hardware from the Shelf 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

REVISION No. : 04 - Feb 01/10 Page : 264

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

6 Attach the wires with :

100 Tie-Cable NSA935401-03

200 Tie-Cable NSA935401-04

200 Tie-Cable NSA935401-05

800 Tie-Cable NSA935401-06

1500 Tie-Cable NSA935401-08

7 Install the Shelf 92VU

a Install the Shelf 92VU on aircraft.

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

REVISION No. : 04 - Feb 01/10 Page : 265

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 266

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

(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

b On the mounting rail of the terminal block 202VT, install :

281132A11002 A00 Sheet(s) 01

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

REVISION No. : 04 - Feb 01/10 Page : 267

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 268

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 269

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 270

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 271

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 272

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

b Connect 7556VC with these items as shown in drawing D92894736004,

Sheet 16, Detail C :

2 screw NAS1100-04-5 Item 051

2 washer NAS1149CN616R Item 150

2 nut MS21042-04 Item 200

c Connect 7100VN with these items as shown in drawing D92894736004,

Sheet 16, Detail D :

1 screw NAS1096-3-9 Item 030

1 washer NAS1149C0332R Item 153

d Install the placards as shown in drawing D92894736004, Sheet 16, Details

C and D :

2 placard D9239386503200 Item 050

e Install the "MOD/SB" placards on the harness 5340VB, Item 040, as shown

in drawing D92894713020, Sheet 1 :

20 placard D9239310902800 Item 000

40 tie NSA935401-03 Item 080

(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

REVISION No. : 04 - Feb 01/10 Page : 273

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 274

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

(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

REVISION No. : 04 - Feb 01/10 Page : 275

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 276

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 277

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 278

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 279

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 280

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

10 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

11 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

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

REVISION No. : 04 - Feb 01/10 Page : 281

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SERVICE BULLETIN

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

12 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

13 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

d Transfer drill the holes and open the holes to final dimension.

e Install these items :

1 fitting (LH) D5337219220000 Item 008

1 fitting (RH) D5337219220100 Item 009

1 angle (LH) D5347104120090 Item 050

1 angle (RH) D5347104120190 Item 051

with :

8 pin DAN7-6-6X Item 566

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

REVISION No. : 04 - Feb 01/10 Page : 282

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

14 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

15 Install the nuts at FR47 as shown in Section A1-A5.

a Drill the four holes 5.6 mm (0.220 in.) diameter for the nuts.

b Put the nuts, Item 046, in position.

c Drill the holes and countersink the rivet holes.

d Install these items :

4 nut NAS1791A3-1 Item 046

with :

8 rivet NAS1097AD3-10 Item 524

16 Remove the support at FR47 at STGR43LH as shown in Section A1-A5.

a Remove and discard this item :

1 support D5347465720300 Item (200) Discard

17 Remove the nuts at FR47 as shown in Detail C5-5.

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

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SERVICE BULLETIN

a Remove and discard these items :

2 nut NAS1068C3 Item (214) Discard

b Close the holes with :

4 rivet NAS1097AD3-10 Item 524

18 Drill twelve holes with 5.6 mm (0.220 in.) diameter as shown in Details A5-5

and B5-5.

19 Install 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

20 Install 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

REVISION No. : 04 - Feb 01/10 Page : 284

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SERVICE BULLETIN

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

21 Install 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.

d Transfer drill the holes from the stringer to the angles and open all holes and

to final dimension.

e Countersink all additional holes in the skin panel.

f Install these items :

4 shim D5337236220400 Item 052

2 angle (LH) D5347007421800 Item 152

2 angle (RH) D5347007421900 Item 153

with :

64 rivet NAS1097AD5-12 Item 540

48 rivet LN9198-4010CF Item 640

12 collar NSA5075-6 Item 806

12 pin DAN5-6-3 Item 963

22 Install 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

REVISION No. : 04 - Feb 01/10 Page : 285

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SERVICE BULLETIN

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

23 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 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

REVISION No. : 04 - Feb 01/10 Page : 286

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 287

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

1 fitting D5347061220000 Item (404) Discard

1 shim D5347061120300 Item (406) Discard

1 fitting D5347061220100 Item (408) Discard

1 support D5347069920800 Item (412) Discard

b Close the eight holes as shown in Details B2-2 and C2-2 :

8 rivet MBBN4477-4012 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

b Close 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

b Close 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

REVISION No. : 04 - Feb 01/10 Page : 288

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

b Close 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

REVISION No. : 04 - Feb 01/10 Page : 289

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

b Close 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

b Close 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

REVISION No. : 04 - Feb 01/10 Page : 290

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining fasteners, Item 865 and 806, will be installed

during the installation of the reinforcing straps at FR48.

2 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

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all

holes 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

REVISION No. : 04 - Feb 01/10 Page : 291

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

b Transfer drill the holes from the frame to the fittings and open all holes

to final dimension.

c Install these items :

1 fitting (LH) D5347449420600 Item 016

1 fitting (RH) D5347449420700 Item 018

with :

34 collar NSA5075-6 Item 806

14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965

8 pin DAN5-6-6 Item 966

4 pin DAN5-6-7 Item 967

4 Install the crossbeam at 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.

d Transfer drill all other holes from the frame to the crossbeam.

e Drill all additional holes and open all holes to final dimension.

f Remove the crossbeam.

g Mark and drill the holes 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

REVISION No. : 04 - Feb 01/10 Page : 292

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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’.

b Open 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

REVISION No. : 04 - Feb 01/10 Page : 293

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining fasteners, Item 865 and 806, will be installed

during the installation of the reinforcing straps at FR49.

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

REVISION No. : 04 - Feb 01/10 Page : 294

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

a Put these items at FR49 in position :

1 strap (LH) D5347448420200 Item 022

1 strap (RH) D5347448420300 Item 024

b Transfer drill the holes 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

b Transfer drill the holes from the frame to the fittings and open all holes

to final dimension.

c Install these items :

1 fitting (LH) D5347449420600 Item 016

1 fitting (RH) D5347449420700 Item 018

with :

34 collar NSA5075-6 Item 806

14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965

8 pin DAN5-6-6 Item 966

4 pin DAN5-6-7 Item 967

4 Install the crossbeam at 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

REVISION No. : 04 - Feb 01/10 Page : 295

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

d Transfer drill all other holes from the frame to the crossbeam.

e Drill all additional holes and open all holes to final dimension.

f Remove the crossbeam.

g Mark and drill the holes 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

REVISION No. : 04 - Feb 01/10 Page : 296

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

b Open 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

REVISION No. : 04 - Feb 01/10 Page : 297

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining fasteners, Item 865 and 806, will be installed

during the installation of the reinforcing straps at FR50.

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

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all

holes 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

REVISION No. : 04 - Feb 01/10 Page : 298

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

1 fitting (LH) D5347449420600 Item 016

1 fitting (RH) D5347449420700 Item 018

b Transfer drill the holes from the frame to the fittings and open all holes

to final dimension.

c Install these items :

1 fitting (LH) D5347449420600 Item 016

1 fitting (RH) D5347449420700 Item 018

with :

34 collar NSA5075-6 Item 806

14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965

8 pin DAN5-6-6 Item 966

4 pin DAN5-6-7 Item 967

4 Install the crossbeam at 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.

b Transfer 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

d Transfer drill the holes from the frame and skin panel to the shear web

and the supports.

e Drill all additional holes and open all holes and all countersinks to final

dimension.

f Install these items :

1 plate D5337217620000 Item 012

1 plate D5337217620100 Item 014

2 filler D5337217620800 Item 026

1 crossbeam D5347026000600 Item 052

1 angle D5347470520000 Item 054

1 angle D5347470520100 Item 056

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

REVISION No. : 04 - Feb 01/10 Page : 299

Printed in France © AIRBUS 2008 All rights reserved
SERVICE 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 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

REVISION No. : 04 - Feb 01/10 Page : 300

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SERVICE BULLETIN

b Open 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.

b Open the affected holes to final dimension.

c Install these items :

34 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

16 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

6 pin DAN5-6-5 Item 965

NOTE : The remaining fasteners, 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

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open

all holes and all countersinks to final dimension.

d Install these items :

1 strap (LH) D5347448420200 Item 022

1 strap (RH) D5347448420300 Item 024

with :

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

REVISION No. : 04 - Feb 01/10 Page : 301

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

b Transfer drill the holes from the frame to the fittings and open all holes

to final dimension.

c Install these items :

1 fitting (LH) D5347449420600 Item 016

1 fitting (RH) D5347449420700 Item 018

with :

34 collar NSA5075-6 Item 806

14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965

8 pin DAN5-6-6 Item 966

4 pin DAN5-6-7 Item 967

4 Install the crossbeam at FR51 as shown in Section D15-D16 ’AFTER’ :

a Put these items at FR51 in position :

1 plate D5337217620000 Item 012

2 filler D5337217620800 Item 026

1 crossbeam D5347035300600 Item 076

1 plate D5337217620700 Item 078

CAUTION : ENSURE THAT THE NEW CROSSBEAM, ITEM 076, IS IN LINE

WITH THE CROSSBEAMS AND FR47 AND FR55.

b Transfer drill all holes from the frame to the crossbeam.

c Put this item at FR51 in position as shown in Section B16-B16 :

1 support angle D5347658420000 Item 102

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

REVISION No. : 04 - Feb 01/10 Page : 302

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SERVICE BULLETIN

1 web D5347470420400 Item 080

e Transfer drill the holes from the frame and skin panel to the shear web

and the supports.

f Drill all additional holes and open all holes and all countersinks to final

dimension.

g Install these items :

1 plate D5337217620000 Item 012

2 filler D5337217620800 Item 026

1 angle D5347470520000 Item 054

1 angle D5347470520100 Item 056

1 crossbeam D5347035300600 Item 076

1 plate D5337217620700 Item 078

1 web D5347470420400 Item 080

1 support angle D5347658420000 Item 102

with :

12 rivet MBBN4477-4812 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

REVISION No. : 04 - Feb 01/10 Page : 303

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SERVICE BULLETIN

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.

b Open 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.

b Open the holes and the countersinks to final dimension.

c Install these items :

8 pin DAN6-6-8Y Item 678

8 collar NSA5330-6 Item 803

(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

REVISION No. : 04 - Feb 01/10 Page : 304

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SERVICE BULLETIN

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.

b Open 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

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all

holes 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

REVISION No. : 04 - Feb 01/10 Page : 305

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SERVICE BULLETIN

b Transfer drill the holes from the frame to the fittings and open all holes

to final dimension.

c Install these items :

1 fitting (LH) D5347449420600 Item 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

e Transfer drill the holes from the frame and skin panel to the shear web

and the supports.

f Drill all additional holes and open all holes to final dimension.

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

REVISION No. : 04 - Feb 01/10 Page : 306

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SERVICE BULLETIN

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’.

b Open the holes to final dimension.

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

REVISION No. : 04 - Feb 01/10 Page : 307

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SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 308

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SERVICE BULLETIN

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.

b Open 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

b Close 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

REVISION No. : 04 - Feb 01/10 Page : 309

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

b Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 310

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

b Transfer 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

d Transfer drill the holes from the frame and skin panel to the shear web

and the supports.

e Drill all additional holes and open all holes 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’.

b Open 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

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SERVICE 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

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SERVICE BULLETIN

b Open 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

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open

all holes and all countersinks to final dimension.

d Install these items :

1 strap D5347448420200 Item 022

with :

29 rivet LN9198-4014CF Item 640

4 collar NSA5075-6 Item 806

4 pin DAN6-6-5 Item 865

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

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Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

a Put this item at FR54 in position :

1 strap (LH) D5347448420200 Item 202

b Transfer 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

b Transfer 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 reserved
SERVICE BULLETIN

b Transfer 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

d Transfer 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’.

b Open 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 reserved
SERVICE 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.

b Open 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 reserved
SERVICE 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 reserved
SERVICE 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

b Transfer 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

b Transfer 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 reserved
SERVICE 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 reserved
SERVICE 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

a At 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.

b At 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 reserved
SERVICE 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.

c Transfer 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 48

Wire-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 reserved
SERVICE 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 reserved
SERVICE 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 24

Wire-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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

10 Install :

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

11 Install :

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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

5 Attach 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 reserved
SERVICE 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 reserved
SERVICE BULLETIN

Refer to Kit 281132A19R00

281132A19006 A00 Sheet(s) 01

1 On the Shelf 85VU

a On 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

6 Attach the wires with :

100 Tie-Cable NSA935401-03

200 Tie-Cable NSA935401-04

200 Tie-Cable NSA935401-05

800 Tie-Cable NSA935401-06

1500 Tie-Cable NSA935401-08

7 Install the Shelf 92VU

a Install the Shelf 92VU on aircraft.

b Do the electrical bonding on the shelf attachment.

c Attach the Shelf 92VU and connect the bonding braid with the hardware

retained at removal.

NOTE : Retain the hardware.

d On the Shelf 92VU, install the computers 7QJ, 9QJ, 3QT and 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 reserved
SERVICE 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 reserved
SERVICE BULLETIN

Item (3)

1 Plate Assy D9251102000000

Item (12)

2 Screw Discard

Item (28)

2 Washer Discard

Item (16)

4 Nut Discard

b On 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 368

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

3 Transfer 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 376

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

d Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 377

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 378

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

d Transfer drill the holes and open the holes to final dimension.

e Install these items :

1 fitting (LH) D5337219220000 Item 008

1 fitting (RH) D5337219220100 Item 009

1 angle (LH) D5347104120090 Item 050

1 angle (RH) D5347104120190 Item 051

with :

8 pin DAN7-6-6X Item 566

4 rivet LN9198-4010CF 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

REVISION No. : 04 - Feb 01/10 Page : 379

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

10 Install the nuts at FR47 as shown in Section A1-A5.

a Drill the four holes 5.6 mm (0.220 in.) diameter for the nuts.

b Put the nuts, Item 046, in position.

c Drill the holes and countersink the rivet holes.

d Install these items :

4 nut NAS1791A3-1 Item 046

with :

8 rivet NAS1097AD3-10 Item 524

11 Remove the support at FR47 at STGR43LH as shown in Section A1-A5.

a Remove and discard this item :

1 support D5347465720300 Item (200) Discard

12 Remove the nuts at FR47 as shown in Detail C5-5.

a Remove and discard these items :

2 nut NAS1068C3 Item (214) Discard

b Close the holes with :

4 rivet NAS1097AD3-10 Item 524

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

REVISION No. : 04 - Feb 01/10 Page : 380

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

13 Drill 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

a At 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.

b At 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

REVISION No. : 04 - Feb 01/10 Page : 381

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

c Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 382

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

b Transfer drill the holes from STGR43 to the plate and the connection.

c Drill all additional holes in the plate and the section and open all holes and

all countersinks to final dimension.

d Install these items :

1 plate 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

REVISION No. : 04 - Feb 01/10 Page : 383

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SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 384

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

b Close 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

REVISION No. : 04 - Feb 01/10 Page : 385

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

b Close 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

b Close 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

REVISION No. : 04 - Feb 01/10 Page : 386

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

b Close 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

b Close 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

b Close the four holes as shown in Detail A5-5 :

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

REVISION No. : 04 - Feb 01/10 Page : 387

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining fasteners, Item 865 and 806, will be installed

during the installation of the reinforcing straps at FR48.

2 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

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all

holes 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

REVISION No. : 04 - Feb 01/10 Page : 388

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

b Transfer drill the holes from the frame to the fittings and open all holes

to final dimension.

c Install these items :

1 fitting (LH) D5347449420600 Item 016

1 fitting (RH) D5347449420700 Item 018

with :

34 collar NSA5075-6 Item 806

14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965

8 pin DAN5-6-6 Item 966

4 pin DAN5-6-7 Item 967

4 Install the crossbeam at 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.

d Transfer drill all other holes from the frame to the crossbeam.

e Drill all additional holes and open all holes to final dimension.

f Remove the crossbeam.

g Mark and drill the holes 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

REVISION No. : 04 - Feb 01/10 Page : 389

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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’.

b Open 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

REVISION No. : 04 - Feb 01/10 Page : 390

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining fasteners, Item 865 and 806, will be installed

during the installation of the reinforcing straps at FR49.

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 reserved
SERVICE BULLETIN

a Put these items at FR49 in position :

1 strap (LH) D5347448420200 Item 022

1 strap (RH) D5347448420300 Item 024

b Transfer drill the holes 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

b Transfer drill the holes from the frame to the fittings and open all holes

to final dimension.

c Install these items :

1 fitting (LH) D5347449420600 Item 016

1 fitting (RH) D5347449420700 Item 018

with :

34 collar NSA5075-6 Item 806

14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965

8 pin DAN5-6-6 Item 966

4 pin DAN5-6-7 Item 967

4 Install the crossbeam at 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

REVISION No. : 04 - Feb 01/10 Page : 392

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

d Transfer drill all other holes from the frame to the crossbeam.

e Drill all additional holes and open all holes to final dimension.

f Remove the crossbeam.

g Mark and drill the holes 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

REVISION No. : 04 - Feb 01/10 Page : 393

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

b Open 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 reserved
SERVICE 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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining fasteners, Item 865 and 806, will be installed

during the installation of the reinforcing straps at FR50.

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

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all

holes 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 reserved
SERVICE 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

b Transfer drill the holes from the frame to the fittings and open all holes

to final dimension.

c Install these items :

1 fitting (LH) D5347449420600 Item 016

1 fitting (RH) D5347449420700 Item 018

with :

34 collar NSA5075-6 Item 806

14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965

8 pin DAN5-6-6 Item 966

4 pin DAN5-6-7 Item 967

4 Install the crossbeam at 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.

b Transfer 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

d Transfer drill the holes from the frame and skin panel to the shear web

and the supports.

e Drill all additional holes and open all holes and all countersinks to final

dimension.

f Install these items :

1 plate D5337217620000 Item 012

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

REVISION No. : 04 - Feb 01/10 Page : 396

Printed in France © AIRBUS 2008 All rights reserved
SERVICE 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 reserved
SERVICE 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.

b Open 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.

b Open the affected holes to final dimension.

c Install these items :

34 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

16 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

6 pin DAN5-6-5 Item 965

NOTE : The remaining fasteners, 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

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open

all holes and all countersinks to final dimension.

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 reserved
SERVICE 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

b Transfer drill the holes from the frame to the fittings and open all holes

to final dimension.

c Install these items :

1 fitting (LH) D5347449420600 Item 016

1 fitting (RH) D5347449420700 Item 018

with :

34 collar NSA5075-6 Item 806

14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965

8 pin DAN5-6-6 Item 966

4 pin DAN5-6-7 Item 967

4 Install the crossbeam at FR51 as shown in Section 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.

b Transfer 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 reserved
SERVICE 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

e Transfer drill the holes from the frame and skin panel to the shear web

and the supports.

f Drill all additional holes and open all holes and all countersinks to final

dimension.

g Install these items :

1 plate D5337217620000 Item 012

2 filler D5337217620800 Item 026

1 angle D5347470520000 Item 054

1 angle D5347470520100 Item 056

1 crossbeam D5347035300600 Item 076

1 plate D5337217620700 Item 078

1 web D5347470420400 Item 080

1 support angle D5347658420000 Item 102

with :

12 rivet MBBN4477-4812 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 reserved
SERVICE 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.

b Open 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.

b Open the holes and the countersinks to final dimension.

c Install these items :

8 pin DAN6-6-8Y Item 678

8 collar NSA5330-6 Item 803

(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 reserved
SERVICE 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.

b Open 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

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all

holes 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 reserved
SERVICE 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

b Transfer drill the holes from the frame to the fittings and open all holes

to final dimension.

c Install these items :

1 fitting (LH) D5347449420600 Item 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 reserved
SERVICE BULLETIN

1 web D5347657720000 Item 208

e Transfer drill the holes from the frame and skin panel to the shear web

and the supports.

f Drill all additional holes and open all holes 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 reserved
SERVICE BULLETIN

6 Replace the fasteners at FR52 between STGR41LH/RH and STGR42LH/RH :

a Remove the fasteners as shown in Section A11-A12 ’BEFORE’.

b Open 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 reserved
SERVICE 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.

b Open 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

b Close 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 reserved
SERVICE 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

b Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 407

Printed in France © AIRBUS 2008 All rights reserved
SERVICE 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.

b Transfer 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

d Transfer drill the holes from the frame and skin panel to the shear web

and the supports.

e Drill all additional holes and open all holes 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’.

b Open 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

REVISION No. : 04 - Feb 01/10 Page : 408

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE BULLETIN

b Open 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

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open

all holes and all countersinks to final dimension.

d Install these items :

1 strap D5347448420200 Item 022

with :

29 rivet LN9198-4014CF Item 640

4 collar NSA5075-6 Item 806

4 pin DAN6-6-5 Item 865

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

REVISION No. : 04 - Feb 01/10 Page : 410

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

a Put this item at FR54 in position :

1 strap (LH) D5347448420200 Item 202

b Transfer 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

b Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 411

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

b Transfer 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

d Transfer 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’.

b Open 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 reserved
SERVICE 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.

b Open 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

REVISION No. : 04 - Feb 01/10 Page : 413

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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

b Transfer 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

b Transfer 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 reserved
SERVICE 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

b Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 416

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

a At 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.

b At 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.

c Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 417

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 418

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

a Put these items at STGR43LH in position :

1 plate D5337217320000 Item 022

1 section D5337216020000 Item 026

1 coupling D5347100720600 Item 040

b Transfer drill the holes from STGR43 to the plate and the connection.

c Drill all additional holes in the plate and the section and open all holes and

all countersinks to final dimension.

d Install these items :

1 plate 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

REVISION No. : 04 - Feb 01/10 Page : 419

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

1 plate D5347048900400 Item 216

1 plate D5347049200400 Item 218

2 angle D5347046824000 Item 228

1 angle D5347046823800 Item 230

1 angle D5347046823600 Item 232

1 angle D5347046824200 Item 234

1 angle D5347046824400 Item 236

NOTE : Install the angle, Item 130, together with the section, Item 028.

b Transfer drill the holes from the stringer and frames to the plates and the

angles.

c Transfer drill the holes from the skin panel to the section at FR52.

d Drill the additional holes and open all holes to final dimension.

e Install the listed items as shown in Sections 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

REVISION No. : 04 - Feb 01/10 Page : 420

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

b Transfer drill the holes from the stringer and frames to the plates and the

angles and open all holes to final dimension.

c Install the listed items as shown in Sections 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

b Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 421

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

a Put this item between FR48 and FR52A in position :

1 section D5347048100600 Item 152

b Transfer 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 reserved
SERVICE 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 reserved
SERVICE 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

b Transfer 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 reserved
SERVICE 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 reserved
SERVICE BULLETIN

1 tube D5347669000000 Item 172

2 shim D5347472120000 Item 176

or

2 Shim D5347472120200 Item 176

b Transfer 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 reserved
SERVICE 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 reserved
SERVICE 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

b Transfer 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE BULLETIN

c Tighten all connections of the hydraulic tubes.

d Attach 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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 432

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 433

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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

10 Install 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 reserved
SERVICE BULLETIN

D92991456005 Sheet(s) 4, H01, H02, W01 and X01

11 Install 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

12 Install 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

13 Install 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

14 Install the cable harness 4664VB/2S

Refer to Drawing(s) :

D92991464003 Sheet(s) 5, B01, H01 to H06, W01, X01 and V01 and V02

15 Install 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

16 Install 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

17 Install the cable harness 4672VB/2M

Refer to Drawing(s) :

D92991472015 Sheet(s) 12, B01 and B02, H01 to H03, W01, X01, V01 and V02

18 Install the cable harness 4673VB/1S

Refer to Drawing(s) :

D92991473004 Sheet(s) 3, B01 and B02, H01 to H04, W01, X01, V01 and V02

19 Install the cable harness 4675VB/2M

Refer to Drawing(s) :

D92997028010 Sheet(s) 9 and 10, B01

20 Install the cable harness 4680VB/1MB

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

REVISION No. : 04 - Feb 01/10 Page : 436

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

Refer to Drawing(s) :

D92991480015 Sheet(s) 16, B01 to B03, H01 to H04 and V01 and V02

21 Install the cable harness 4681VB/7M

Refer to Drawing(s) :

D92991481004 Sheet(s) 5, B01, H01, W01, V01

22 Cable 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.

23 Install the cable harness 4692VB/2M

Refer to Drawing(s) :

D92991492006 Sheet(s) 7, B01, H01, W01, X01, V01

24 Install the cable harness 4693VB/1S

Refer to Drawing(s) :

D92991493004 Sheet(s) 3, B01 and B02, H01 to H03, W01, X01, V01 and V02

25 Install the cable harness 4694VB/2S

Refer to Drawing(s) :

D92991494004 Sheet(s) 3, B01 and B02, H01 to H03, W01, X01, V01 and V02

26 Install the cable harness 5609VB/1M

Refer to Drawing(s) :

D92997028032 Sheet(s) 26 to 29, B01

27 Install the cable harness 5662VB/2M

Refer to Drawing(s) :

D92997028033 Sheet(s) 30 and 31, B01

28 Install the cable harness 5633VB/5S

Refer to Drawing(s) :

D92997028034 Sheet(s) 32 and 33, B01

29 Install 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 reserved
SERVICE BULLETIN

D92997028035 Sheet(s) 34 to 36, B01

30 Install the cable harness 5670VB/1M

Refer to Drawing(s) :

D92997028036 Sheet(s) 37 and 38, B01

31 Install 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 reserved
SERVICE 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

10 Install :

Refer to Drawing(s) :

D92992299020 Sheet(s) 29, 30 and B01

11 Install :

Refer to Drawing(s) :

D92992299022 Sheet(s) 31, 32 and B01

12 Install :

Refer to Drawing(s) :

D92992299024 Sheet(s) 33 thru 36 and B01

13 Install 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

14 Install :

Refer to Drawing(s) :

D92992299026 Sheet(s) 37 and 38 and B01

15 Install :

Refer to Drawing(s) :

D92992299028 Sheet(s) 39 and B01

16 Install :

Refer to Drawing(s) :

D92992299030 Sheet(s) 40 and B01

17 Install the wires of cable harness 5220VB

Refer to Drawing(s) :

D92990820001 Sheet(s) 2, B01, H01, W01, X01 and V01

18 Install 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 reserved
SERVICE BULLETIN

Refer to Drawing(s) :

D92990824007 Sheet(s) 7, B01, H01, W01 and V01

19 Install 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE BULLETIN

1 Nut NSA5050-4

Item 42

2 Nut NSA5050-3

Item 48

Wire-Lock MS20995C32

3 Install the refuel valve 41QU and the canister 164QM :

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 reserved
SERVICE 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 reserved
SERVICE BULLETIN

1 Nut MS21042L06

Item 22

1 Lead-Bonding E0088-16-100

Item 24

Wire-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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

10 Install :

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 reserved
SERVICE BULLETIN

4 Bolt NAS6604-5

Item 12

4 Washer ASNA2397-416L

Item 14

4 Nut NAS1726-4E

11 Install :

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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

5 Attach 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

a On the mounting rail of the terminal block 1853VT, install :

1 Module NSA937901MA2206

in position 28

1 Module NSA937901MA2204

in position 62

2 Module Identification NSA937901E2

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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 485

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 486

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 487

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

6 Attach the wires with :

100 Tie-Cable NSA935401-03

200 Tie-Cable NSA935401-04

200 Tie-Cable NSA935401-05

800 Tie-Cable NSA935401-06

1500 Tie-Cable NSA935401-08

7 Install the Shelf 92VU

a Install the Shelf 92VU on aircraft.

b Do the electrical bonding on the shelf attachment.

c Attach the Shelf 92VU and connect the bonding braid with the hardware

retained at removal.

NOTE : Retain the hardware.

d On the Shelf 92VU, install the computers 7QJ, 9QJ, 3QT and 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

REVISION No. : 04 - Feb 01/10 Page : 488

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SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 489

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

Item (3)

1 Plate Assy D9251102000000

Item (4)

2 Screw Discard

Item (112)

2 Screw Discard

Item (28)

2 Washer Discard

Item (16)

4 Nut Discard

b On the mounting rail of the terminal block 202VT, install :

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

REVISION No. : 04 - Feb 01/10 Page : 490

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 491

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 492

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 493

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SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 494

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SERVICE BULLETIN

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

d Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 495

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SERVICE BULLETIN

b Transfer 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

d Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 496

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SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 497

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SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 498

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 499

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 500

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 501

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 502

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SERVICE BULLETIN

NOTE : The Items A, C, D and E are retained parts.

c Install these items as shown in Section J7-J9 :

3 washer NAS1149C0332R Item 070

1 pin MS24665-153 Item 080

1 bolt D5337048420200 Item B

NOTE : The Item B is a retained part.

d Adjust the release cable so that the dimension "B" is between 9.8 mm (0.386

in.) and 13.2 mm (0.519 in.) as shown in Detail 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.

g Adjust the length of the adapter, Item 002, and connect the adapter with the

lever with these items as shown in Section B10-B10 :

1 pin MS20392-2C19 Item 036

3 washer NAS1149C0332R Item 070

1 pin MS24665-153 Item 080

h Secure the both rod ends and the adjustment nuts of the release cable

with lockwire (Mat. No. 19-010) as shown in Details V7-10 and Z7-9 and

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

REVISION No. : 04 - Feb 01/10 Page : 503

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 504

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 :

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SERVICE 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.

d Adjust the release cable so that the dimension "B" is between 9.8 mm (0.386

in.) and 13.2 mm (0.519 in.) as shown in Detail Z10-10.

e Install this item as shown in Details V7-10 and Z10-10 :

1 adapter L32A319-165-002 Item 002

f Install a rigging pin with 5.0 mm (0.197 in.) diameter at the lever as shown in

drawing D53370297002, Sheet 10, Detail V7-10.

g Adjust the length of the adapter, Item 002, and connect the adapter with the

lever with these items as shown in Section B10-B10 :

1 pin MS20392-2C19 Item 036

3 washer NAS1149C0332R Item 070

1 pin MS24665-153 Item 080

h Secure the both rod ends and the adjustment nuts of the release cable

with lockwire (Mat. No. 19-010) as shown in Details V7-10 and Z7-9 and

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

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SERVICE BULLETIN

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.

2 Transfer 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

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REVISION No. : 04 - Feb 01/10 Page : 507

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

b Transfer 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’.

a Transfer 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

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Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

b Open 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.

b Open 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

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SERVICE BULLETIN

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

3 Close 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 :

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SERVICE BULLETIN

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 :

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SERVICE BULLETIN

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

b Transfer drill the holes to the plate, Item 009, and open the holes to final

dimension.

c Install this item as shown in drawing D53371046000, Sheet 5, Sections

F1-F5 and C5-C5 :

1 plate D5337107420200 Item 009

with :

2 pin DAN6-6-4 Item 021

4 pin DAN5-6-4 Item 022

6 collar NSA5075-6 Item 025

8 rivet LN9198-4012CF Item 035

10 pin DAN5-5-7 Item 036

8 pin DAN5-5-6 Item 037

12 collar NSA5075-5 Item 038

6 collar NSA5076-5 Item 039

d Put these items in position as shown in drawing D53371046000, Sheet 5,

Sections F1-F5, B5-B5 and Detail A5-5 :

1 wall D5337311520200 Item 010

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SERVICE BULLETIN

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

e Transfer drill the holes, drill the additional holes, open all holes to final

dimension and install with these items as shown in drawing D53371046000,

Sheet 5, Sections F1-F5, B5-B5 and A5-A5 and Detail A5-5 :

15 rivet LN9198-4009CF Item 031

3 rivet LN9198-4010CF Item 032

10 rivet LN9198-4011CF Item 033

and with these items as shown in drawing 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.

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SERVICE BULLETIN

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining 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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining 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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining pins, Item 865 and collars, Item 806, will be

installed during the installation of the reinforcing straps at FR50.

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SERVICE BULLETIN

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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining 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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining fasteners, Item 865 and 806, will be installed

during the installation of the reinforcing straps at 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.

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SERVICE BULLETIN

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining fasteners, Item 865 and 806, will be installed

during the installation of the reinforcing straps at 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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining fasteners, Item 865 and 806, will be installed

during the installation of the reinforcing straps at 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

2 Transfer 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

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SERVICE BULLETIN

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

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SERVICE BULLETIN

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

b Transfer drill the holes, drill the additional holes and open the holes to final

dimension as shown in Detail Y10-10.

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SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 519

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 520

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

b Transfer 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

e Transfer drill the holes from the track, Item 000.

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

REVISION No. : 04 - Feb 01/10 Page : 521

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SERVICE BULLETIN

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.

b Transfer drill the holes to the bearing supports, Item 070.

c Drill the additional holes.

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

REVISION No. : 04 - Feb 01/10 Page : 522

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SERVICE BULLETIN

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

e Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 523

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SERVICE BULLETIN

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.

b Transfer 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

e Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 524

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SERVICE BULLETIN

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

b Adjust 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

REVISION No. : 04 - Feb 01/10 Page : 525

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

3 Temporarily 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

4 Temporarily 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.

6 Adjust the X-gaps with the adjustment screws at FR47 as shown in drawing

D25572624008, Sheet 12 :

a Adjust 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

REVISION No. : 04 - Feb 01/10 Page : 526

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SERVICE BULLETIN

b Secure the adjustment screws with lockwire (Mat. No. 19-010).

7 Adjust 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.

8 Adjust 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.

9 Adjust 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.

b Temporarily 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

REVISION No. : 04 - Feb 01/10 Page : 527

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SERVICE BULLETIN

10 Remove 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.

2 Temporarily 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

3 Temporarily 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.

4 Temporarily 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.

6 Adjust 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.

7 Adjust 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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SERVICE BULLETIN

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.

8 Adjust 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.

9 Adjust 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.

b Adjust 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

10 Remove 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

REVISION No. : 04 - Feb 01/10 Page : 529

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 530

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

1 beam D2827099720000 Item 000

NOTE : Ensure that the reference holes are in line.

3 Transfer drill the holes from aircraft structure to the beam and open the holes

to final dimension.

4 Install this item :

1 beam D2827099720000 Item 000

with :

8 bolt NSA5031-3-10 Item 770

8 nut NAS1726C3P Item 807

8 washer 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

REVISION No. : 04 - Feb 01/10 Page : 531

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SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 532

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SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 533

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SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 534

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 535

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

(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

REVISION No. : 04 - Feb 01/10 Page : 536

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

and put them between FR37 and FR42 with these items temporarily in

position :

1 flange D2827093320600 Item 030

1 O-ring NSA8203-156 Item 056

f Push the inner tube, Item 034, over the inner tube (which is installed at the

top of the center tank between FR37 and FR38) and connect the both tubes

with the nut, Item 066, as shown in Detail U9-9.

g Attach the tube, Item 032, at the bracket, Item 033, between FR40 and FR41

with these items as shown in Detail W9-11 :

1 clamp D28270935002 Item 035

1 clamp D28270935004 Item 037

2 washer NAS1149C0332R Item 083

2 bolt NAS1303-3 Item 096

h Connect the strap, Item 108, at the flange with these items as shown in

Detail U9-9 :

1 washer NAS1149C0332R Item 083

1 bolt NAS1303-2 Item 095

i Push the flange, Item 030, and the O-ring, Item 056, in position and install

these items as shown in Detail A9-9:

10 washer NAS1149C0432R Item 082

6 nut NAS1726-4E Item 085

4 bolt NAS1304-4 Item 086

2 bolt NAS1304-3 Item 100

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

REVISION No. : 04 - Feb 01/10 Page : 537

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

e Assemble these items as shown in Detail Q9-11 :

2 spacer A2827090120400 Item 031

1 tube D2827092800000 Item 044

1 tube D2827092900000 Item 046

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

REVISION No. : 04 - Feb 01/10 Page : 538

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

m Install 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

REVISION No. : 04 - Feb 01/10 Page : 539

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 540

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 541

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 542

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SERVICE BULLETIN

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

2 Transfer 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

3 Connect this item at the vent shroud line as shown in drawing D28270973002,

Sheet 6 :

1 tube D2827093603400 Item 100

and install these items as shown in Details Y6-8 and X6-8 and Section B6-B8 :

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

REVISION No. : 04 - Feb 01/10 Page : 543

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SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 544

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

10 Install these items at FR46 as shown in Detail S6-9 :

1 tee NAS1763D080808 Item 033

1 fitting D2827094320000 Item 204

with :

2 nut NAS1726-3E Item 010

2 screw NAS1096-3-10 Item 012

11 Install 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

REVISION No. : 04 - Feb 01/10 Page : 545

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

12 Install these items between FR47 and FR48 as shown in Detail Q6-10 :

1 nut AN924-8D Item 003

1 washer NAS1149D1290K Item 004

1 tee MS21912D8 Item 013

1 washer NAS1149D1216H Item 023

13 Install 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

14 Install these items as shown in Details P10-10 and S6-9 :

4 washer NAS1149C0332R Item 007

4 screw NAS1096-3-8 Item 009

2 strap E0090-10-125NN Item 025

4 clamp NSA5519-11 Item 035

4 nut NAS1291C3M Item 036

15 Install these items with sealant (Mat. No. 09-016) at the belly fairing as shown in

Detail Q6-10 :

1 reducer MS21916D8-6 Item 017

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

16 Install this item with adhesive (Mat. No. 08-010) as shown in Detail Q6-10 :

1 placard D2827094421400 Item 214

17 Install 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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 547

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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

5 At 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 reserved
SERVICE BULLETIN

22 bracket D5397469700000 Item 028

b Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 550

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

m Install 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

REVISION No. : 04 - Feb 01/10 Page : 551

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 553

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 554

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 555

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

10 Remove the cable harness 4672VB/2M

Refer to Drawing(s) :

D92991472013 Sheet(s) 14, B01 and B02, H01 to H04, W01, X01, V01 and V02

11 Remove the cable harness 4673VB/1S

Refer to Drawing(s) :

D92991473003 Sheet(s) 4, B01 and B02, H01 to H04, W01, X01, V01 and V02

12 Remove the cable harness 4680VB/1MB

Refer to Drawing(s) :

D92991480012 Sheet(s) 13, B01 to B03, H01 to H05, W01, X01, V01 and V02

13 Remove the cable harness 4681VB/7M

Refer to Drawing(s) :

D92991481003 Sheet(s) 4, B01, H01, W01, V01

14 Cable 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 : 556

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

Refer to Drawing(s) :

D92991483005 Sheet(s) 6, B01 and B02, H01 to H09, W01 and W02,

X01 and X02, V01 to V04

15 Remove the cable harness 4692VB/2M

Refer to Drawing(s) :

D92991492005 Sheet(s) 6, B01, H01, W01, X01, V01

16 Remove the cable harness 4693VB/1S

Refer to Drawing(s) :

D92991493003 Sheet(s) 4, B01 and B02, H01 to H03, W01, X01, V01 and V02

17 Remove 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 : 557

Printed in France © AIRBUS 2008 All rights reserved
SERVICE 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

10 Remove the wires of cable harness 4225VB

Refer to Drawing(s) :

D92999561010 Sheet(s) 20, lines 1 and 2

D92999561010 Sheet(s) 21, BEFORE MOD.

11 Remove the wires of cable harness 4226VB

Refer to Drawing(s) :

D92999559024 Sheet(s) 21 and 22,

12 Remove 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

13 Remove the wires of cable harness 4232VB

Refer to Drawing(s) :

D92999559026 Sheet(s) 25

14 Remove the wires of cable harness 4233VB

Refer to Drawing(s) :

D92999559028 Sheet(s) 27, lines 1 to 4

15 Remove the wires of cable harness 5214VB

Refer to Drawing(s) :

D92999559030 Sheet(s) 28, line 1

16 Remove the wires of cable harness 5220VB

Refer to Drawing(s) :

D92990820000 Sheet(s) 1 and B01

17 Remove the wires of cable harness 5224VB

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

REVISION No. : 04 - Feb 01/10 Page : 558

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

Refer to Drawing(s) :

D92990824002 Sheet(s) 3, B01, H01, W01 and V01

18 Remove 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 reserved
SERVICE 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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 561

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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 :

a Clean 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

REVISION No. : 04 - Feb 01/10 Page : 563

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 564

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

2 At FR53, remove as shown in drawing D255762400, Sheet 6.

1 TDP DAN152-1 Item (502) Discard

2 screw NAS1102-3-18 Item (501) Discard

3 At FR52A, install as shown in drawing D2557624004, Sheet 6.

1 TDP DAN152-1 Item 502

with :

2 screw NAS1102-3-18 Item 501

4 At 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

REVISION No. : 04 - Feb 01/10 Page : 565

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 566

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

c Remove the fuel quantity indicator unit 6QT (Refer to AMM 28-42-22,

Page block 401).

d Temporarily 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.

b Cut 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

REVISION No. : 04 - Feb 01/10 Page : 567

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 568

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 569

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 570

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 571

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 573

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 574

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 575

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 576

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 577

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

10 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

11 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 :

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

REVISION No. : 04 - Feb 01/10 Page : 578

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SERVICE BULLETIN

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

12 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

13 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

d Transfer drill the holes and open the holes to final dimension.

e Install these items :

1 fitting (LH) D5337219220000 Item 008

1 fitting (RH) D5337219220100 Item 009

1 angle (LH) D5347104120090 Item 050

1 angle (RH) D5347104120190 Item 051

with :

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

REVISION No. : 04 - Feb 01/10 Page : 579

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

14 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

15 Install the nuts at FR47 as shown in Section A1-A5.

a Drill the four holes 5.6 mm (0.220 in.) diameter for the nuts.

b Put the nuts, Item 046, in position.

c Drill the holes and countersink the rivet holes.

d Install these items :

4 nut NAS1791A3-1 Item 046

with :

8 rivet NAS1097AD3-10 Item 524

16 Remove 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

REVISION No. : 04 - Feb 01/10 Page : 580

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

17 Remove the nuts at FR47 as shown in Detail C5-5.

a Remove and discard these items :

2 nut NAS1068C3 Item (214) Discard

b Close the holes with :

4 rivet NAS1097AD3-10 Item 524

18 Drill twelve holes with 5.6 mm (0.220 in.) diameter as shown in Details A5-5

and B5-5.

19 Install 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

20 Install 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

REVISION No. : 04 - Feb 01/10 Page : 581

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

21 Install 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.

d Transfer drill the holes from the stringer to the angles and open all holes and

to final dimension.

e Countersink all additional holes in the skin panel.

f Install these items :

4 shim D5337236220400 Item 052

2 angle (LH) D5347007421800 Item 152

2 angle (RH) D5347007421900 Item 153

with :

64 rivet NAS1097AD5-12 Item 540

48 rivet LN9198-4010CF Item 640

12 collar NSA5075-6 Item 806

12 pin DAN5-6-3 Item 963

22 Install 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

REVISION No. : 04 - Feb 01/10 Page : 582

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

23 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 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

REVISION No. : 04 - Feb 01/10 Page : 583

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 585

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SERVICE BULLETIN

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

d Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 586

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 588

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

d Transfer drill the holes and open the holes to final dimension.

e Install these items :

1 fitting (LH) D5337219220000 Item 008

1 fitting (RH) D5337219220100 Item 009

1 angle (LH) D5347104120090 Item 050

1 angle (RH) D5347104120190 Item 051

with :

8 pin DAN7-6-6X Item 566

4 rivet LN9198-4010CF 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

10 Install the nuts at FR47 as shown in Section A1-A5.

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

REVISION No. : 04 - Feb 01/10 Page : 589

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

11 Remove the support at FR47 at STGR43LH as shown in Section A1-A5.

a Remove and discard this item :

1 support D5347465720300 Item (200) Discard

12 Remove the nuts at FR47 as shown in Detail C5-5.

a Remove and discard these items :

2 nut NAS1068C3 Item (214) Discard

b Close the holes with :

4 rivet NAS1097AD3-10 Item 524

13 Drill 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

REVISION No. : 04 - Feb 01/10 Page : 590

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SERVICE BULLETIN

3 Install the plates, the sections and the connections at STGR38LH and

STGR38RH as shown in Detail W1-7.

Refer to Drawing(s) :

D53372362004

a At 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.

b At 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.

c Transfer 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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 592

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

b Transfer drill the holes from STGR43 to the plate and the connection.

c Drill all additional holes in the plate and the section and open all holes and

all countersinks to final dimension.

d Install these items :

1 plate 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

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SERVICE 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 reserved
SERVICE 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

b Close 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

b Close 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 reserved
SERVICE 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

b Close 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

b Close 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 reserved
SERVICE 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.

b Close 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

b Close 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

b Close 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 reserved
SERVICE 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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining fasteners, Item 865 and 806, will be installed

during the installation of the reinforcing straps at FR48.

2 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

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all

holes 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 reserved
SERVICE 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

b Transfer drill the holes from the frame to the fittings and open all holes

to final dimension.

c Install these items :

1 fitting (LH) D5347449420600 Item 016

1 fitting (RH) D5347449420700 Item 018

with :

34 collar NSA5075-6 Item 806

14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965

8 pin DAN5-6-6 Item 966

4 pin DAN5-6-7 Item 967

4 Install the crossbeam at 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.

d Transfer drill all other holes from the frame to the crossbeam.

e Drill all additional holes and open all holes to final dimension.

f Remove the crossbeam.

g Mark and drill the holes 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

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SERVICE 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’.

b Open 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 reserved
SERVICE 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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining fasteners, Item 865 and 806, will be installed

during the installation of the reinforcing straps at FR49.

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 reserved
SERVICE BULLETIN

1 strap (LH) D5347448420200 Item 022

1 strap (RH) D5347448420300 Item 024

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all

holes 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) 2 c.

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

b Transfer drill the holes from the frame to the fittings and open all holes

to final dimension.

c Install these items :

1 fitting (LH) D5347449420600 Item 016

1 fitting (RH) D5347449420700 Item 018

with :

34 collar NSA5075-6 Item 806

14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965

8 pin DAN5-6-6 Item 966

4 pin DAN5-6-7 Item 967

4 Install the crossbeam at 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 reserved
SERVICE 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.

d Transfer drill all other holes from the frame to the crossbeam.

e Drill all additional holes and open all holes to final dimension.

f Remove the crossbeam.

g Mark and drill the holes 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 reserved
SERVICE 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.

b Open 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 reserved
SERVICE 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.

b Open the affected holes to final dimension.

c Install these items :

30 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

18 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

NOTE : The remaining fasteners, Item 865 and 806, will be installed

during the installation of the reinforcing straps at FR50.

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

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all

holes 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) 3 c.

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 reserved
SERVICE BULLETIN

1 fitting (LH) D5347449420600 Item 016

1 fitting (RH) D5347449420700 Item 018

b Transfer drill the holes from the frame to the fittings and open all holes

to final dimension.

c Install these items :

1 fitting (LH) D5347449420600 Item 016

1 fitting (RH) D5347449420700 Item 018

with :

34 collar NSA5075-6 Item 806

14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965

8 pin DAN5-6-6 Item 966

4 pin DAN5-6-7 Item 967

4 Install the crossbeam at 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.

b Transfer 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

d Transfer drill the holes from the frame and skin panel to the shear web

and the supports.

e Drill all additional holes and open all holes and all countersinks to final

dimension.

f Install these items :

1 plate D5337217620000 Item 012

1 plate D5337217620100 Item 014

2 filler D5337217620800 Item 026

1 crossbeam D5347026000600 Item 052

1 angle D5347470520000 Item 054

1 angle D5347470520100 Item 056

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 reserved
SERVICE 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 reserved
SERVICE BULLETIN

a Remove the existing rivets.

b Open 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.

b Open the affected holes to final dimension.

c Install these items :

34 collar NSA5075-6 Item 806

4 pin DAN6-6-3 Item 863

16 pin DAN5-6-3 Item 963

8 pin DAN5-6-4 Item 964

6 pin DAN5-6-5 Item 965

NOTE : The remaining fasteners, 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

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open

all holes and all countersinks to final dimension.

d Install these items :

1 strap (LH) D5347448420200 Item 022

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 reserved
SERVICE 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) 4 c.

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

b Transfer drill the holes from the frame to the fittings and open all holes

to final dimension.

c Install these items :

1 fitting (LH) D5347449420600 Item 016

1 fitting (RH) D5347449420700 Item 018

with :

34 collar NSA5075-6 Item 806

14 pin DAN5-6-4 Item 964

8 pin DAN5-6-5 Item 965

8 pin DAN5-6-6 Item 966

4 pin DAN5-6-7 Item 967

4 Install the crossbeam at FR51 as shown in Section 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.

b Transfer drill all holes from the frame to the crossbeam.

c Put this item at FR51 in position as shown in Section B5-B5 :

1 support angle D5347658420000 Item 102

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

REVISION No. : 04 - Feb 01/10 Page : 609

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

e Transfer drill the holes from the frame and skin panel to the shear web

and the supports.

f Drill all additional holes and open all holes and all countersinks to final

dimension.

g Install these items :

1 plate D5337217620000 Item 012

2 filler D5337217620800 Item 026

1 angle D5347470520000 Item 054

1 angle D5347470520100 Item 056

1 crossbeam D5347035300600 Item 076

1 plate D5337217620700 Item 078

1 web D5347470420200 Item 080

1 support angle D5347658420000 Item 102

with :

12 rivet MBBN4477-4812 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 reserved
SERVICE 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.

b Open 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.

b Open the holes and the countersinks to final dimension.

c Install these items :

8 pin DAN6-6-8Y Item 678

8 collar NSA5330-6 Item 803

(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 reserved
SERVICE 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.

b Open 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

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open all

holes 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 reserved
SERVICE 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

b Transfer drill the holes from the frame to the fittings and open all holes

to final dimension.

c Install these items :

1 fitting (LH) D5347449420600 Item 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 reserved
SERVICE BULLETIN

1 web D5347657720000 Item 208

e Transfer drill the holes from the frame and skin panel to the shear web

and the supports.

f Drill all additional holes and open all holes 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 reserved
SERVICE BULLETIN

6 Replace the fasteners at FR52 between STGR41LH/RH and STGR42LH/RH :

a Remove the fasteners as shown in Section A1-A2 ’BEFORE’.

b Open the holes to final dimension.

c Install these items as shown in Section A1-A2 ’AFTER’ :

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 reserved
SERVICE 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.

b Open 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

b Close 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 reserved
SERVICE 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

b Transfer 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 reserved
SERVICE 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.

b Transfer 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

d Transfer drill the holes from the frame and skin panel to the shear web

and the supports.

e Drill all additional holes and open all holes 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 reserved
SERVICE BULLETIN

b Open 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 reserved
SERVICE 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.

b Open 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

b Transfer drill the holes from the frame to the straps.

c Drill the additional holes from the reinforcing straps to the frame and open

all holes and all countersinks to final dimension.

d Install these items :

1 strap D5347448420200 Item 022

with :

29 rivet LN9198-4014CF Item 640

4 collar NSA5075-6 Item 806

4 pin DAN6-6-5 Item 865

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 reserved
SERVICE 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

b Transfer 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

b Transfer 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 reserved
SERVICE 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.

b Transfer 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

d Transfer 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 reserved
SERVICE BULLETIN

b Open 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.

b Open 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 reserved
SERVICE 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 reserved
SERVICE 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

b Transfer 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

REVISION No. : 04 - Feb 01/10 Page : 625

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

1 L-profile D5347449522200 Item 090

1 shear plate D5347471321800 Item 102

b Transfer 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

b Transfer 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 reserved
SERVICE 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.

a At 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.

b At 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 reserved
SERVICE BULLETIN

NOTE : Install the section, Item 029, together with the angle, Item

134, at FR48.

c Transfer drill the holes from the skin panel and the stringer to the

connections.

d Drill the additional holes 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 reserved
SERVICE 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

b Transfer drill the holes from STGR43 to the plate and the connection.

c Drill all additional holes in the plate and the section and open all holes and

all countersinks to final dimension.

d Install these items :

1 plate 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 reserved
SERVICE 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.

b Transfer drill the holes from the stringer and frames to the plates and the

angles.

c Transfer drill the holes from the skin panel to the section at FR52.

d Drill the additional holes and open all holes to final dimension.

e Install the listed items as shown in Sections H1-H8 and K1-K11 with :

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 reserved
SERVICE 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.

b Transfer drill the holes from the stringer and frames to the plates and the

angles and open all holes to final dimension.

c Install the listed items as shown in Sections 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 reserved
SERVICE 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

b Transfer 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

b Transfer 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 reserved
SERVICE 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 reserved
SERVICE 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

b Transfer 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 reserved
SERVICE 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 reserved
SERVICE 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

b Transfer drill the eight holes from the stringers to the tube as shown in

Detail Y14-14.

c Drill the eight holes as shown in Detail Y14-14.

d Open all holes to final dimension.

e Install these items :

1 tube D5347669000000 Item 172

2 shim D5347472120000 Item 176

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 reserved
SERVICE 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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 638

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

b Transfer 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 reserved
SERVICE 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 reserved
SERVICE 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

4 Shorten 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

REVISION No. : 04 - Feb 01/10 Page : 641

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

d Attach 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

REVISION No. : 04 - Feb 01/10 Page : 642

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

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

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

REVISION No. : 04 - Feb 01/10 Page : 643

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 645

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 646

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

10 Install 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

REVISION No. : 04 - Feb 01/10 Page : 647

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 648

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 649

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 650

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 651

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

1 placard D2827094420600 Item 206

1 placard D2827094420800 Item 208

10 Install 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

11 Install 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

12 Install these items between FR48 and FR49 as shown in Section G13-G15 :

1 filter A2163302000000 Item 027

1 inlet A2151034520000 Item 028

1 nut AN924-4D Item 092

13 Install 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

REVISION No. : 04 - Feb 01/10 Page : 652

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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.

14 Install 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.

15 Install this item with adhesive (Mat. No. 08-010) as shown in Section C13-C16 :

1 placard D2827094421000 Item 210

16 Install 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

17 Install 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

REVISION No. : 04 - Feb 01/10 Page : 653

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 654

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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

REVISION No. : 04 - Feb 01/10 Page : 655

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

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 reserved
SERVICE 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

10 Install 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

11 Install 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

12 Install 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

13 Install the cable harness 4664VB/2S

Refer to Drawing(s) :

D92991464003 Sheet(s) 5, B01, H01 to H06, W01, X01 and V01 and V02

14 Install 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

15 Install 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

16 Install the cable harness 4672VB/2M

Refer to Drawing(s) :

D92991472015 Sheet(s) 12, B01 and B02, H01 to H03, W01, X01, V01 and V02

17 Install 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 reserved
SERVICE BULLETIN

Refer to Drawing(s) :

D92991473004 Sheet(s) 3, B01 and B02, H01 to H04, W01, X01, V01 and V02

18 Install the cable harness 4675VB/2M

Refer to Drawing(s) :

D92997028010 Sheet(s) 9 and 10, B01

19 Install the cable harness 4680VB/1MB

Refer to Drawing(s) :

D92991480013 Sheet(s) 16, B01 to B03, H01 to H04 and V01 and V02

20 Install the cable harness 4681VB/7M

Refer to Drawing(s) :

D92991481004 Sheet(s) 5, B01, H01, W01, V01

21 Cable 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.

22 Install the cable harness 4692VB/2M

Refer to Drawing(s) :

D92991492006 Sheet(s) 7, B01, H01, W01, X01, V01

23 Install the cable harness 4693VB/1S

Refer to Drawing(s) :

D92991493004 Sheet(s) 3, B01 and B02, H01 to H03, W01, X01, V01 and V02

24 Install the cable harness 4694VB/2S

Refer to Drawing(s) :

D92991494004 Sheet(s) 3, B01 and B02, H01 to H03, W01, X01, V01 and V02

25 Install the cable harness 5609VB/1M

Refer to Drawing(s) :

D92997028032 Sheet(s) 26 to 29, B01

26 Install the cable harness 5662VB/2M

Refer to Drawing(s) :

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

REVISION No. : 04 - Feb 01/10 Page : 658

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SERVICE BULLETIN

D92997028033 Sheet(s) 30 and 31, B01

27 Install the cable harness 5633VB/5S

Refer to Drawing(s) :

D92997028034 Sheet(s) 32 and 33, B01

28 Install the cable harness 5664VB/4S

Refer to Drawing(s) :

D92997028035 Sheet(s) 34 to 36, B01

29 Install the cable harness 5670VB/1M

Refer to Drawing(s) :

D92997028036 Sheet(s) 37 and 38, B01

30 Install 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

REVISION No. : 04 - Feb 01/10 Page : 659

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SERVICE BULLETIN

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

10 Install the wires of cable harness 4223VB

Refer to Drawing(s) :

D92999561008 Sheet(s) 16, 17 and 19

11 Install the wires of cable harness 4224VB

Refer to Drawing(s) :

D92999559020 Sheet(s) 19

12 Install the wires of cable harness 4225VB

Refer to Drawing(s) :

D92999561010 Sheet(s) 20, lines 4 and 5,

D92999561010 Sheet(s) 21, AFTER MOD

13 Install the wires of cable harness 4226VB

Refer to Drawing(s) :

D92999559024 Sheet(s) 23 and 24

14 Install the wires of cable harness 4227VB

Refer to Drawing(s) :

D92990627013 Sheet(s) 17 and 19

15 Install the wires of cable harness 4232VB

Refer to Drawing(s) :

D92999559026 Sheet(s) 26

16 Install the wires of cable harness 4233VB

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

REVISION No. : 04 - Feb 01/10 Page : 660

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SERVICE BULLETIN

Refer to Drawing(s) :

D92999559028 Sheet(s) 27, lines 6 to 9

17 Install the wires of cable harness 4234VB

Refer to Drawing(s) :

D92990634002 Sheet(s) 3

18 Install the wires of cable harness 5214VB

Refer to Drawing(s) :

D92999559030 Sheet(s) 28, line 3

19 Install the wires of cable harness 5220VB

Refer to Drawing(s) :

D92990820001 Sheet(s) 2

20 Install the wires of cable harness 5224VB

Refer to Drawing(s) :

D92990824007 Sheet(s) 7

21 Install 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

REVISION No. : 04 - Feb 01/10 Page : 661

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SERVICE BULLETIN

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

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SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 663

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SERVICE BULLETIN

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

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REVISION No. : 04 - Feb 01/10 Page : 664

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SERVICE 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

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SERVICE 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

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SERVICE 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. TEST

(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.

4 Connect the connectors to the battery.

5 Turn the knurled nut a quarter turn.

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

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SERVICE 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

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SERVICE BULLETIN

2 After 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.

3 After 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

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SERVICE 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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SERVICE BULLETIN

(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

REVISION No. : 04 - Feb 01/10 Page : 671

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

(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

REVISION No. : 04 - Feb 01/10 Page : 672

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

(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

REVISION No. : 04 - Feb 01/10 Page : 673

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

(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. CLOSE UP

(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

REVISION No. : 04 - Feb 01/10 Page : 674

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

(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

REVISION No. : 04 - Feb 01/10 Page : 675

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

(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. DOCUMENTATION

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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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

REVISION No. : 04 - Feb 01/10 Page : 1

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

APPENDIX 1

(g) In the AFT area of the RH main landing gear bay, disconnect the elbow nut, Item

(1). Loosen the ACT cavity drain-line nut, Item (2), turn the elbow to approximately

180 deg. and tighten the nut again. 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.

3 The system must not leak. The pressure in the system must not decrease. If a

leak is found, a repair must be made and the test procedure done again.

(b) Close up

1 Release the pressure from the ACT system drain-line and disconnect the

GPG from the ACT cavity drain-line.

2 Loosen the ACT cavity drain-line nut, Item (2), turn the elbow to approximately

180 deg. and tighten the nut again.

3 Reconnect the elbow nut, Item (1) to the ACT cavity drain-line.

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 reserved
SERVICE BULLETIN

APPENDIX 1

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

REVISION No. : 04 - Feb 01/10 Page : 3

Printed in France © AIRBUS 2008 All rights reserved
SERVICE BULLETIN

APPENDIX 1

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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE 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 reserved
SERVICE BULLETIN

APPENDIX 2

This Page Intentionally Left Blank

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

REVISION No. : 04 - Feb 01/10 Page : 20

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SERVICE 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

Please complete the appropriate item (A or B):

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

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From Airline: ........................................................................................................................................................

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If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next

normal revision or prior to SB embodiment, please indicate required service(s):

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Important Information: This SB will only be incorporated in your maintenance and operational documentation

if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible

revision, this will result in

- updating of maintenance documentation to show pre and post SB data.

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If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include

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Please return this completed sheet to:

AIRBUS

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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

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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

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SERVICE 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

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If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short

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Planning Material Instructions

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X Publication X Tooling X Illustrations

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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

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SERVICE 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

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