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 - INSTALLATION OF PROVISIONS FOR ONE ACT IN A319 AFT CARGO COMPARTMENT WITH BULK CONFIGURATION**  **MODIFICATION No. :** 25415P4179, 25696P4347, 25711J1492, 25711K4487, 26138K4772, 27115J1522, 27446P5502, 27447P5503, 27717K5539, 28068P5759, 28661J2073, 28817J1973, 30139J2110, 30356P6676, 30356P7357, 30373K6720, 31110K7004, 31143K7155, 31700K7502, 32261J2241, 33628K8825, 34240K9240, 34245K9245, 34417K9434, 34550K9440, 35442K9945, 35567K9967, 37122K5304, 37137K5305, 37226J2826 This page transmits Revision No. 01 of Service Bulletin No. A320-28-1154.
A D D I T I O N A L WO R K Additional work is required by this revision for aircraft modified by any previous issue.
R E A S O N Revision 01 is issued to include improvements according to DR 28-1154/1479/001 thru 28-1154/1479/034, 28-1154/1479/500, 28-1154/1479/505 and 28-1154/1479/506 further to accomplishment of this Service Bulletin on aircraft MSN 1479. C H A N G E S SUMMARY : - MANPOWER

. Manpower for ADDITIONAL WORK added. - MATERIAL INFORMATION

. Kit A13 added. PLANNING INFORMATION : - EFFECTIVITY

. 1.A. Kit A13 added. NOTE added. - DESCRIPTION

. 1.D.(1)(ai) Paragraph added.

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 1 of 4
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN REVISION TRANSMITTAL SHEET

. 1.D.(1)(bt) Work step added. . 1.D.(2) ADDITIONAL WORK added. - MANPOWER

. 1.G. Config. 01 added. Manpower for Kit D17 updated. ADDITIONAL WORK added. - WEIGHT AND BALANCE

. 1.H. Config. 01 added. - REFERENCES

. 1.J. References updated. MATERIAL INFORMATION : - LIST OF COMPONENTS

. 2.C. Kit A13 added. Kits D05, D06, D16, D17, D44, D77, D78 and D82 updated. ACCOMPLISHMENT INSTRUCTIONS : - GENERAL - Preparation

. 3.A.(1)(a)8 Removal of belly fairing access panels added. . 3.A.(1)(a)9 Removal of air inlets added. . 3.A.(1)(a)10 Removal of welding group on air condition packs added. . 3.A.(1)(a)11 Removal of distribution ducts added. . 3.A.(1)(a)12 Removal of torque tube assemblies added. . 3.A.(1)(a)13 Removal of hydraulic pipes added. . 3.A.(1)(a)17 Removal of offwing escape slides added. . 3.A.(1)(a)21 Paragraph amended to cover the removal of the SFCC. . 3.A.(1)(a)30 Removal of VHF 2 antenna added. . 3.A.(1)(a)31 Removal of SDAC (1WV1), (1WV2) added. . 3.A.(1)(a)32 Removal of GCU added. - Standard Practices

. 3.A.(2)(ag) ESPM 20-52-21 added. DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 2
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN REVISION TRANSMITTAL SHEET

- MODIFICATION

. 3.B. NOTE for Top Drawing added. . 3.B.(1)(j) Drawings updated. . 3.B.(1)(k) Drawings updated. . 3.B.(1)(q) Drawings updated. . 3.B.(1)(s) Kit A13R00 added. NOTE deleted. Drawing updated. . 3.B.(1)(t) Drawings updated. . 3.B.(1)(ac) Drawing D92992293, Sheets 42 and 43 added. . 3.B.(1)(af)1 Drawing D53370297002, Sheets 8 thru 12 added. Drawing D53375751004, Sheet 7 added. . 3.B.(1)(af)2 Drawing D53370297003, Sheets 8 thru 12 added. . 3.B.(1)(ai) Paragraph added. . 3.B.(1)(br) Drawing D92997046008, Sheet 31 deleted. . 3.B.(1)(bt) Work step added. . 3.B.(2) ADDITIONAL WORK added. - TESTS

. 3.C.(1)(c)4a paragraph added. . 3.C.(1)(c)4b Paragraph added. . 3.C.(1)(c)4c Paragraph added. . 3.C.(1)(c)4d Paragraph added. . 3.C.(1)(c)4f Test of emergency lighting system added. . 3.C.(1)(c)4h Tests of SFCC (21CV), (22CV) added. . 3.C.(1)(c)4i Installation and test of the GCU added. . 3.C.(1)(m) Paragraph amended. . 3.C.(1)(cj) Paragraph added. - CLOSE-UP

. 3.D.(1)(d) Installation of air inlets added.

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 3
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN REVISION TRANSMITTAL SHEET

. 3.D.(1)(e) Installation of welding group added. . 3.D.(1)(f) Installation of distribution ducts added. . 3.D.(1)(g) Installation of torque tube assemblies added. . 3.D.(1)(h) Installation of hydraulic pipes added. . 3.D.(1)(j) Paragraph amended to cover the installation of the SDAC. . 3.D.(1)(k) Paragraph amended to cover the installation of the SFCC. . 3.D.(1)(l) Installation of VHF 2 antenna added. . 3.D.(1)(m) Paragraph added. . 3.D.(1)(q) Paragraph added. . 3.D.(1)(w) Installation of belly fairing access panels added. NOTE : Layout changes due to computerization of this revision are not identified.
F I L I N G I N S T R U CT I O N S This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin.
H I S T O R Y O F P R E V I O U S R E V I S I O N S No previous revisions.
R E V I S I O N S E Q U E N C E ORIGINAL : Feb 07/07 REVISION No. : 01 - Apr 07/08

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 4
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

**AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  **Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F**  **Fax : (33) 5 61 93 42 51** This summary is for information only and is not approved for modification of the aircraft **ATA SYSTEM : 28 TITLE : FUEL - TANKS - INSTALLATION OF PROVISIONS FOR ONE ACT IN A319 AFT CARGO**  **COMPARTMENT WITH BULK CONFIGURATION MODIFICATION No. :**  25415P4179, 25696P4347, 25711J1492, 25711K4487, 26138K4772, 27115J1522, 27446P5502, 27447P5503, 27717K5539, 28068P5759, 28661J2073, 28817J1973, 30139J2110, 30356P6676, 30356P7357, 30373K6720, 31110K7004, 31143K7155, 31700K7502, 32261J2241, 33628K8825, 34240K9240, 34245K9245, 34417K9434, 34550K9440, 35442K9945, 35567K9967, 37122K5304, 37137K5305, 37226J2826
R E A S O N/D E S C R I PT I O N/O P E RA T I O N A L C O N S E Q U E N C E S This Service Bulletin is issued in response to the request from an operator to install the system and structural provisions for a single Additional Center Tank (ACT) in the AFT cargo compartment. This Service Bulletin describes the work necessary to install the system and structural provisions for a single ACT in the AFT cargo compartment with bulk configuration. The accomplishment of this Service Bulletin and the future installation of the ACT gives the aircraft an increased operational range due to the additional 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

NORMAL JACKING Yes VENDOR SB INVOLVED No

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 1 of 10
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

EVALUATION TABLE

STRUCTURAL LIFE EXTN No DE-FUELLING/VENTILATION Yes
KIT PRICE (USD) See SB

MODIFICATION CLASSIFICATION

MAJOR 26138K4772 37226J2826

MINOR 25415P4179 25696P4347 25711J1492 25711K4487 27115J1522 27446P5502 27447P5503 27717K5539 28068P5759 28661J2073 28817J1973 30139J2110 30356P6676 30356P7357 30373K6720 31110K7004 31143K7155 31700K7502 32261J2241 33628K8825 34240K9240 34245K9245 34417K9434 34550K9440 35442K9945 35567K9967 37122K5304 37137K5305 As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural strength, reliability, operational characteristics affecting the airworthiness of the product. All other changes are major changes.
**E F**  **F E**  **C T**  **I V**  **I T** **Y** This Service Bulletin is applicable to this (these) operator(s) :
TAR NOTE : This Service Bulletin is written for the operators listed ab ove. 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 C O N C U R R E N T R E Q U I R E M E N T S Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the following Service Bulletin(s) or the equivalent production modification(s):

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 2
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Service Bulletin No. A320-25-1427 Mod. No. 28353K5964 Mod. No. 28354K5965 Mod. No. 31833K7629 Mod. No. 34403K9438 Mod. No. 34407K9448 Mod. No. 34462K9432 Mod. No. 35101K9701 Service Bulletin No. A320-22-1102 Mod. No. 30439P6703 Mod. No. 31040P6954 Mod. No. 33299P8256 Service Bulletin No. A320-22-1084 Mod. No. 31365P6987 Service Bulletin No. A320-31-1257 Mod. No. 28479P5706 Mod. No. 28916P6437 Mod. No. 30644P6792 Mod. No. 30660P6801 Mod. No. 30797P6866 Mod. No. 31283P7125 Mod. No. 33374P8274 Mod. No. 34005P8911 Mod. No. 37128P10100
R E F E R E N C E S/R E P E R C U S S I O N S TFU : None OEB : None AOT : None SIL : None LIFE LIMIT : None LINE MAINTENANCE AFFECTED : No OTHERS : None
N A T U R E O F T H E WO R K AIRCRAFT : Yes EQUIPMENT : Yes HARD : Yes SOFT : Yes OBRM : No
M A N POW E R Config. 01

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 3
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

**TOTAL MANHOURS 2136.75 ELAPSED TIME (HOURS) 525.00**  Config. 01, ADDITIONAL WORK

**TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00** 
M A T E R I A L I N FO R M A T I O N AIRCRAFT DATA Config. 01

Kit 281154A01R00 Supports, brackets, fittings, doubler and related hardware.

Kit 281154A02R00 Supports, brackets, plate and related hardware.

Kit 281154A03R01 Fairings, fittings, valve, plug, placards and related hardware.

Kit 281154A04R00 Pipes, sleeves, elbows and related hardware.

Kit 281154A05R00 Elbows, filter, plate and related hardware.

Kit 281154A06R02 Switch, circuit breakers, sleeves, plate and related hardware.

Kit 281154A07R00 Plate.
DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 4
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Kit 281154A08R00 Switch, pump, valve, actuator, canister, plate and clamp.

Kit 281154A09R00 Valve.

Kit 281154A10R01 Bracket, relay, bundles, mount, stud and related hardware.

Kit 281154A11R01 Flange, rack, plate and related hardware.

Kit 281154A12R00 Control unit.

Kit 281154A13R00 Bundle.

Kit 281154B01R00 Valves, filter, actuator and clamp.

Kit 281154B02R00 Relay.

Kit 281154B03R00 Panels.

Kit 281154B04R00 Wire Bundle.

Kit 281154D01R00
DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 5
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Placards.

Kit 281154D02R00 Electrical harnesses, electrical equipment and placards.

Kit 281154D04R01 Brackets, panel and related hardware.

Kit 281154D05R02 Connecting sections, angles, beam, struts, fittings, supports and related hardware.

Kit 281154D06R04 Fittings, cross-beams, sections, angles, coupling, shims, shear plates, web, doublers, cover, tubes, plugs, straps and related hardware.

Kit 281154D07R00 Angles and related hardware.

Kit 281154D10R00 Insulation blankets and strips.

Kit 281154D11R01 Overhead Stowage Compartments and related hardware.

Kit 281154D12R00 Placards.

Kit 281154D13R00 Inflation reservoirs, hoses, brackets, tubes, sections, bonding leads, placards and related hardware.

Kit 281154D14R01 Placard set and cable ties
DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 6
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Kit 281154D15R00 Brackets, electrical harnesses, placard set and related hardware.

Kit 281154D16R02 Flexible control assemblies, adaptors, sections, angles, bridges, brackets and related hardware.

Kit 281154D17R02 Harnesses

Kit 281154D21R00 Brackets and related hardware.

Kit 281154D30R00 Ceiling panels.

Kit 281154D31R01 Sidewall panels.

Kit 281154D32R00 Sidewall panels.

Kit 281154D33R00 Partition panels.

Kit 281154D41R00 Flanges, tubes, sleeves, spacers, brackets, springs bonding leads and related hardware.

Kit 281154D42R00 Monitor, tubes, hose, elbow, fitting, bracket, reducers, unions, tee pieces, bonding leads and related hardware.

Kit 281154D43R00 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 7
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Monitor, tubes, hose, reducer, elbows, tee pieces, bonding leads and related hardware.

Kit 281154D44R01 Tubes, inlet, filter, hose, couplings, elbows, conduit, Tee-pieces, placards, bonding leads and related hardware.

Kit 281154D45R00 Angles, brackets and related hardware.

Kit 281154D46R00 Beam and related hardware.

Kit 281154D47R00 Shield, shim and related hardware.

Kit 281154D48R00 Tubes and tee piece.

Kit 281154D50R00 Tubes, block, unions, brackets, elbows, cord and related hardware.

Kit 281154D61R00 Angles, plates, straps, stiffeners, sections, and related hardware.

Kit 281154D62R00 Pins and collars.

Kit 281154D63R00 Pins and collars.

Kit 281154D71R00 Floor panels, tape and related hardware.
DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 8
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Kit 281154D72R00 Cord and tape.

Kit 281154D73R00 Panels, plates, spacers, tape and related hardware.

Kit 281154D74R01 Sections and cord.

Kit 281154D75R00 Panels and related hardware.

Kit 281154D76R00 Plates, brackets, sections and related hardware.

Kit 281154D77R02 Brackets, cable guides, fittings, bobbins, mounts, connectors, covers, spacers, labels and related hardware.

Kit 281154D78R02 Brackets, angles, sheets and related hardware.

Kit 281154D79R00 Brackets, guides, deflector, section, strap and related hardware.

Kit 281154D80R00 Roller tracks, plates, doublers, shims, supports, sliding blocks, latches and related hardware.

Kit 281154D81R01 Shims, plugs and screws.

Kit 281154D82R01 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 9
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN SUMMARY

Tie down points and related hardware.

Kit 281154D83R00 Placards.

Kit 281154D84R00 Covers, tie-down point, placard and related hardware.
A P P E N D I C E S None

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 10
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

**AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  **Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F**  **Fax : (33) 5 61 93 42 51 ATA SYSTEM : 28**  **TITLE : FUEL - TANKS - INSTALLATION OF PROVISIONS FOR ONE ACT IN A319 AFT CARGO COMPARTMENT WITH BULK CONFIGURATION**  **MODIFICATION No. :** 25415P4179, 25696P4347, 25711J1492, 25711K4487, 26138K4772, 27115J1522, 27446P5502, 27447P5503, 27717K5539, 28068P5759, 28661J2073, 28817J1973, 30139J2110, 30356P6676, 30356P7357, 30373K6720, 31110K7004, 31143K7155, 31700K7502, 32261J2241, 33628K8825, 34240K9240, 34245K9245, 34417K9434, 34550K9440, 35442K9945, 35567K9967, 37122K5304, 37137K5305, 37226J2826 This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS’ prior written consent.
**1. P L** **A N**  **N I**  **N G**  **I N**  **F O**  **R M**  **A T**  **I O**  **N**
**A. E F**  **F E**  **C T**  **I V**  **I T** **Y** (1) Models
319-114 (2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft MSN :
1479 (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 : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 1 of 140
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

OPERATOR MSN TAR 1479 (c) Effectivity by MSN and Kit/Configuration The Kits and configurations applicable to these MSNs are given at the end of this list
1479 KIT No. QTY PER A/C CONFIGURATION 281154A01R00 1 01 281154A02R00 1 01 281154A03R01 1 01 281154A04R00 1 01 281154A05R00 1 01 281154A06R02 1 01 281154A07R00 1 01 281154A08R00 1 01 281154A09R00 1 01 281154A10R01 1 01 281154A11R01 1 01 281154A12R00 1 01 281154A13R00 1 01 281154B01R00 1 01 281154B02R00 1 01 281154B03R00 1 01 281154B04R00 1 01

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 2
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION 281154D01R00 1 01 281154D02R00 1 01 281154D04R01 1 01 281154D05R02 1 01 281154D06R04 1 01 281154D07R00 1 01 281154D10R00 1 01 281154D11R01 1 01 281154D12R00 1 01 281154D13R00 1 01 281154D14R01 1 01 281154D15R00 1 01 281154D16R02 1 01 281154D17R02 1 01 281154D21R00 1 01 281154D30R00 1 01 281154D31R01 1 01 281154D32R00 1 01 281154D33R00 1 01 281154D41R00 1 01 281154D42R00 1 01 281154D43R00 1 01 281154D44R01 1 01

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 3
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION 281154D45R00 1 01 281154D46R00 1 01 281154D47R00 1 01 281154D48R00 1 01 281154D50R00 1 01 281154D61R00 1 01 281154D62R00 1 01 281154D63R00 1 01 281154D71R00 1 01 281154D72R00 1 01 281154D73R00 1 01 281154D74R01 1 01 281154D75R00 1 01 281154D76R00 1 01 281154D77R02 1 01 281154D78R02 1 01 281154D79R00 1 01 281154D80R00 1 01 281154D81R01 1 01 281154D82R01 1 01 281154D83R00 1 01 281154D84R00 1 01 NOTE : Config. 01 is valid for all the aircraft given in the effectivity of this Service Bulletin as a standard configuration. NOTE : ADDITIONAL WORK with Kit A13 is required for aircraft which are modified by the original issue of this Service Bulletin.

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 4
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(3) Spares Config. 01 Door assy D5713019400200 Pipe assy D2821008001300 FQI 1407KID02-03 FQIC SIC5059-11-0207 Integrally lighted plate 002098-05 Front plate D9251092000000 Plate D9251102000000 Plate D9251116900000 **B. C O**  **N C**  **U R**  **R E**  **N T**  **R E**  **Q U**  **I R**  **E M**  **E N**  **T S**  Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the following Service Bulletin(s) or the equivalent production modification(s): Service Bulletin No. A320-22-1084 Mod. No. 31365P6987 Service Bulletin No. A320-22-1102 Mod. No. 30439P6703 Mod. No. 31040P6954 Mod. No. 33299P8256 Service Bulletin No. A320-25-1427 Mod. No. 28353K5964 Mod. No. 28354K5965 Mod. No. 31833K7629 Mod. No. 34403K9438 Mod. No. 34407K9448 Mod. No. 34462K9432 Mod. No. 35101K9701 Service Bulletin No. A320-31-1257 Mod. No. 28479P5706 Mod. No. 28916P6437 Mod. No. 30644P6792 Mod. No. 30660P6801 Mod. No. 30797P6866 Mod. No. 31283P7125 Mod. No. 33374P8274 Mod. No. 34005P8911 Mod. No. 37128P10100 **C. R E** **A S**  **O N**  (1) History This Service Bulletin is issued in response to the request from an operator to install the system and structural provisions for a single Additional Center Tank (ACT) in the AFT cargo compartment. (2) Objective/Action This Service Bulletin describes the work necessary to install the system and structural provisions for a single ACT in the AFT cargo compartment with bulk configuration. (3) Advantages

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 5
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

The accomplishment of this Service Bulletin and the future installation of the ACT gives the aircraft an increased operational range due to the additional 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 the PLANNING INFORMATION, paragraph K. This Service Bulletin is based on the aircraft configuration as known by Airbus (first aircraft delivery configuration and modified by the reported incorporation of Airbus SBs). Prior to Service Bulletin embodiment, the operator is reminded to pay specific attention to structural damage which may exist and to repairs which were performed on the aircraft because they may be affected by the Service Bulletin. Operators must verify that all allowable damage limits and repairs performed (both in accordance with the SRM and outside of the SRM) are still applicable and effective to the new Service Bulletin configuration. There may be additional or modified maintenance requirements, such as temporary limits or additional inspections, that apply with respect to the Service Bulletin configuration. Airbus disclaims any liability for the effect which the Service Bulletin may have on repairs performed on the aircraft before embodiment of the Service Bulletin. If the post Service Bulletin repair status is no more covered by the SRM and for repairs outside of the SRM covered by a RAS issued by Airbus, the operator should contact Airbus Customer Services Repair Engineering Support (SER1). Repair review will be done by Airbus at conditions of the Customer Services Catalogue.
**D. D E**  **S C**  **R I**  **P T**  **I O**  **N** To accomplish this Service Bulletin it is necessary to : (1) Config. 01 (a) Install the doublers on the extrados, in the center tank (b) Install the brackets on the extrados, in the center tank (c) Install the bracket on the rear spar assy, in the center tank (d) Install the brackets on the intrados, in the center tank (e) Install the Additional Center Tank (ACT) door assy on the center tank (f) Replace the Fuel Quantity Indicator (FQI) 6QT (g) Modify the transfer line in the center tank (h) Install the transfer elbow and the air ventilation elbow on the center tank (i) Apply the sealing protection to the center tank (j) Modify the equipment and the wiring in the HYD/Fuel Panel 40VU

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 6
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(k) Modify the equipment and the wiring in the Rear C/B Panel 121VU and the Rear Panel 120VU (l) Modify the routing in the avionics compartment (m) Modify the equipment in the FWD cargo compartment (n) Modify the equipment and the wiring in the Relay Box 103VU (o) Modify the equipment and the wiring in the Contactor Box 107VU (p) Modify the equipment and the wiring in the AFT Electronics Rack 80VU (q) Modify the equipment and the wiring in the FWD Electronics Rack 90VU (r) Modify the wiring between the avionics compartment and the cockpit (s) Modify the wiring on the connectors 4065VC-A and 4066VC-A (t) Modify the wiring in the avionics compartment and in the FWD cargo compartment (u) Install the equipment for ACT pressurization system between FR46 and FR58. (v) In the FWD avionics compartment, install the relay logic box. (w) Replace the refuel/defuel panel. (x) Remove the inflation reservoirs 7506MM and 7507MM, for the LH and RH offwing escape slides. (y) Remove and retain the cargo nets from the AFT cargo compartment. (z) In the AFT cargo compartment, remove the placards from the sidewall panels. (aa) In the AFT cargo compartment, remove the placards for the inflation reservoir access. (ab) Install the MOD/SB placards on the new and modified wires. (ac) In the passenger compartment between FR41 and FR46, LH and RH, modify the harnesses 5339VB and 5340VB. (ad) Between FR45 and FR47/51 (LH and RH), install the reservoirs and the associated pressure tubes for the offwing escape slides. (ae) Replace the Overhead Stowage Compartments (OHSC) between FR43 and FR47/51. (af) Relocate the release cables for the LH and RH offwing escape slides. (ag) Install the ACT structural provisions in the center fuselage. (ah) Install the angles on the webs of the keel beam, between FR42 and FR46.

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 7
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(ai) Remove the center beams between FR52 to FR55 from the AFT cargo compartment. (aj) Install the ACT structural provisions in the AFT cargo compartment, between FR52 and FR63. (ak) Replace the fasteners between FR42 and FR44 (LH). (al) Replace the fasteners between FR42 and FR44 (RH). (am) Replace the belly fairing panel 197AB and do the modification to the attachment structure. (an) Install the placards on the belly fairing panel 197AB. (ao) Install the roller tracks and do the adjustment of the YZ and the XZ latches. (ap) Install the shim plates, as required, after the results of the roller track levelling. (aq) Apply the corrosion preventative to the roller tracks. (ar) Install the covers on the roller tracks and the YZ latches. (as) In the AFT cargo compartment at FR54, install the tie-down points. (at) In the AFT cargo compartment, replace the plates on the floor crossbeams at FR54 and FR55 and the attachment structure for the FR47 partition panels. (au) In the AFT cargo compartment, replace the floor panels 151PE, 151VG, 151ZG and 151CE. (av) In the AFT cargo compartment, replace the floor panels 151TG, 151AE, 151DE, 151GE, 152TG and 152WG. (aw) Replace the insulation blankets on the AFT face of the bulkhead at FR46 (ax) In the AFT cargo compartment, replace the ceiling panels 151EC, 151FC and 151GC. (ay) In the AFT cargo compartment, replace the LH sidewall panels 151SW, 151TW, 151UW and 151VW. (az) In the AFT cargo compartment, replace the RH sidewall panels 152CW and 152DW. (ba) Install the placards on the sidewall panels in the AFT cargo compartment. (bb) In the AFT cargo compartment, replace the FR47/51 partition panels 151BW, 151AW and 152BW. (bc) In the passenger compartment, replace the floor panels 241JF, 251GF, 251FF, 252GF and 252HF. (bd) Seal the gaps between the passenger compartment floor-panels 241JF, 251GF, 251FF, 252GF and 252HF. DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 8
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(be) Install the fuel transfer and fuel vent lines. (bf) Install the shroud drain system between FR37 and FR52. (bg) Install the ACT pressurization and the cavity drain and monitoring systems. (bh) Install the protective shield for the fuel transfer and fuel vent lines. (bi) Replace the fuel drain line between FR42 and FR47/51. (bj) Install the support brackets and do the modification to the floor structure at FR42, FR53, FR54 and FR58. (bk) Replace the cable guides between FR41 and FR42. (bl) Replace the support bracket at FR42. (bm) Do the modification to the bracket installation between FR46 and FR56. (bn) Do the modification to the bracket installation between FR46 and FR52 and at FR54. (bo) Do the modification to the attachment parts for the cable harnesses between FR46 thru FR55. (bp) Do the modification to the attachment parts for the cable harnesses at FR42 and in the AFT cargo compartment at FR52 thru FR54, FR56, FR58 and FR59. (bq) Do the modification to the attachment parts for the cable harnesses at FR42. (br) Install/modify the cable harnesses and install the MOD/SB placards. (bs) Replace the harnesses 4225VB, 4226VB and 4227VB. (bt) Reroute the harness 4232VB. (bu) Do the modification to the routing of the hydraulic lines between FR46 and FR55. (bv) Do the levelling of the cargo roller tracks. (bw) Install the cargo nets in the AFT cargo compartment. (2) Config. 01 , ADDITIONAL WORK **E. C O**  **M P**  **L I**  **A N**  **C E**  (1) Classification Optional (2) Accomplishment Timescale In accordance with operators’ maintenance schedule.
DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 9
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

**F. A P**  **P R** **O V**  **A L**  Approved under EASA Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. **G. M A**  **N P**  **O W**  **E R**  The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc, and general administration work are also not included. Config. 01 Get access 120.00 Install the doublers on the extrados 8.00 Install the brackets on the extrados 16.00 Install the brackets on the rear spar 1.50 Install the brackets on the intrados 16.00 Install the ACT door assy 16.00 Replace the FQI 1.00 Modify the transfer line 32.00 Install the transfer elbow 4.00 Install the air ventilation elbow 4.00 Apply the sealing protection 12.00 Modify the 40VU 4.00 Modify the 121VU and 120VU 8.00 Modify the routing 8.00 Install the connector 1982VC 1.00 Modify the 103VU 4.00 Modify the 107VU 4.00

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 10
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Modify the 80VU 6.00 Modify the 90VU 16.00 Modify wiring in AVNCS COMPT and cockpit 18.00 Modify wiring on 4065VC-A and 4066VC-A 12.00 Modify wiring in AVNCS and cargo COMPT 14.00 Modification, Kit B01 thru B04 5.50 Removal of components 35.00 Modification, Kit D01 1.00 Modification, Kit D02 325.00 Modification, Kit D04 10.00 Modification, Kit D05 145.00 Modification, Kit D06 558.00 Modification, Kit D07 2.00 Modification, Kit D10 5.00 Modification, Kit D11 3.00 Modification, Kit D12 1.00 Modification, Kit D13 18.00 Modification, Kit D14 1.00 Modification, Kit D15 6.00 Modification, Kit D16 12.00 Modification, Kit D17 88.00 Modification, Kit D21 1.00 Modification, Kit D30 3.00 Modification, Kit D31 3.00 Modification, Kit D32 1.50 Modification, Kit D33 2.00 Modification, Kit D41 12.00 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 11
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Modification, Kit D42 7.00 Modification, Kit D43 4.00 Modification, Kit D44 3.50 Modification, Kit D45 21.00 Modification, Kit D46 2.00 Modification, Kit D47 0.50 Modification, Kit D48 3.00 Modification, Kit D50 9.00 Modification, Kit D61 30.00 Modification, Kit D62 9.00 Modification, Kit D63 9.00 Modification, Kit D71 20.00 Modification, Kit D72 2.00 Modification, Kit D73 12.00 Modification, Kit D74 2.00 Modification, Kit D75 8.00 Modification, Kit D76 20.00 Modification, Kit D77 215.00 Modification, Kit D78 75.00 Modification, Kit D79 5.50 Modification, Kit D80 45.00 Modification, Kit D81 7.00 Modification, Kit D82 0.25 Modification, Kit D83 0.50 Modification, Kit D84 4.00 Test 19.00 Close up 58.00 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 12
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

**TOTAL MANHOURS 2136.75 ELAPSED TIME (HOURS) 525.00**  Config. 01 , ADDITIONAL WORK Get access 2.00 Replace the wire 2828-0036 3.00 Close-up 2.00 **TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00** 
**H. W E**  **I G**  **H T**  **A N**  **D B** **A L** **A N**  **C E**  Config. 01 Kit 281154A01R00 thru Kit 281154A12R00 Manufacturers Empty Weight : +68.88 kg (+151.8528 lb) Effect on Balance : +1282.72 kgm (+9277.913 lb.ft) Kit 281154B01R00 thru Kit 281154B04R00 Manufacturers Empty Weight : +3.50 kg (+7.7161 lb) Effect on Balance : +77.87 kgm (+563.233 lb.ft) Kit 281154D01R00 Not changed Kit 281154D02R00 Manufacturers Empty Weight : +6.24 kg (+13.7567 lb) Effect on Balance : +124.80 kgm (+902.678 lb.ft) Kit 281154D04R01 Manufacturers Empty Weight : +0.90 kg (+1.9841 lb) Effect on Balance : +18.50 kgm (+133.810 lb.ft) Kit 281154D05R02 Manufacturers Empty Weight : +12.34 kg (+27.2047 lb)

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 13
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Effect on Balance : +236.31 kgm (+1709.230 lb.ft) Kit 281154D06R04 Manufacturers Empty Weight : +19.70 kg (+43.4306 lb) Effect on Balance : +498.41 kgm (+3604.999 lb.ft) Kit 281154D07R00 Manufacturers Empty Weight : +0.11 kg (+0.2425 lb) Effect on Balance : +2.21 kgm (+15.984 lb.ft) Kit 281154D10R00 Manufacturers Empty Weight : -0.07 kg (-0.1544 lb) Effect on Balance : -1.41 kgm (-10.199 lb.ft) Kit 281154D11R01 Manufacturers Empty Weight : +0.46 kg (+1.0141 lb) Effect on Balance : +8.72 kgm (+63.071 lb.ft) Kit 281154D12R00 Not changed Kit 281154D13R00 Manufacturers Empty Weight : +6.80 kg (+14.9912 lb) Effect on Balance : +14.28 kgm (+103.287 lb.ft) Kit 281154D14R01 Not changed Kit 281154D15R00 Manufacturers Empty Weight : +0.22 kg (+0.4850 lb) Effect on Balance : +3.76 kgm (+27.196 lb.ft) Kit 281154D16R02 Manufacturers Empty Weight : -0.99 kg (-2.1826 lb) Effect on Balance : -17.32 kgm (-125.276 lb.ft) Kit 281154D17R02 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 14
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Manufacturers Empty Weight : +3.00 kg (+6.6138 lb) Effect on Balance : +59.40 kgm (+429.640 lb.ft) Kit 281154D21R00 Not changed Kit 281154D30R00 Manufacturers Empty Weight : +11.85 kg (+26.1245 lb) Effect on Balance : +259.51 kgm (+1877.035 lb.ft) Kit 281154D31R01 Manufacturers Empty Weight : +10.40 kg (+22.9278 lb) Effect on Balance : +225.68 kgm (+1632.343 lb.ft) Kit 281154D32R00 Manufacturers Empty Weight : -0.50 kg (-1.1023 lb) Effect on Balance : -10.40 kgm (-75.224 lb.ft) Kit 281154D33R00 Manufacturers Empty Weight : +10.75 kg (+23.6994 lb) Effect on Balance : +211.77 kgm (+1531.732 lb.ft) Kit 281154D41R00 Manufacturers Empty Weight : +23.30 kg (+51.3671 lb) Effect on Balance : +398.43 kgm (+2881.844 lb.ft) Kit 281154D42R00 Manufacturers Empty Weight : +10.80 kg (+23.8096 lb) Effect on Balance : +193.32 kgm (+1398.283 lb.ft) Kit 281154D43R00 Manufacturers Empty Weight : +0.95 kg (+2.0943 lb) Effect on Balance : +19.19 kgm (+138.801 lb.ft) Kit 281154D44R01 Manufacturers Empty Weight : +8.00 kg (+17.6368 lb) DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 15
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Effect on Balance : +177.20 kgm (+1281.687 lb.ft) Kit 281154D45R00 Manufacturers Empty Weight : +1.30 kg (+2.8659 lb) Effect on Balance : +28.47 kgm (+205.923 lb.ft) Kit 281154D46R00 Manufacturers Empty Weight : +0.49 kg (+1.0802 lb) Effect on Balance : +8.94 kgm (+64.663 lb.ft) Kit 281154D47R00 Manufacturers Empty Weight : +1.01 kg (+2.2266 lb) Effect on Balance : +19.54 kgm (+141.332 lb.ft) Kit 281154D48R00 Manufacturers Empty Weight : +0.19 kg (+0.4188 lb) Effect on Balance : +3.36 kgm (+24.302 lb.ft) Kit 281154D50R00 Manufacturers Empty Weight : +0.10 kg (+0.2204 lb) Effect on Balance : +2.03 kgm (+14.682 lb.ft) Kit 281154D61R00 Manufacturers Empty Weight : +3.40 kg (+7.4956 lb) Effect on Balance : +60.52 kgm (+437.741 lb.ft) Kit 281154D62R00 Manufacturers Empty Weight : +0.37 kg (+0.8157 lb) Effect on Balance : +6.53 kgm (+47.231 lb.ft) Kit 281154D63R00 Manufacturers Empty Weight : +0.37 kg (+0.8157 lb) Effect on Balance : +6.53 kgm (+47.231 lb.ft) Kit 281154D71R00 Manufacturers Empty Weight : +5.02 kg (+11.0670 lb) DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 16
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Effect on Balance : +104.42 kgm (+755.269 lb.ft) Kit 281154D72R00 Manufacturers Empty Weight : +0.11 kg (+0.2425 lb) Effect on Balance : +2.26 kgm (+16.346 lb.ft) Kit 281154D73R00 Manufacturers Empty Weight : -2.70 kg (-5.9525 lb) Effect on Balance : -59.40 kgm (-429.641 lb.ft) Kit 281154D74R01 Manufacturers Empty Weight : +2.00 kg (+4.4092 lb) Effect on Balance : +44.00 kgm (+318.252 lb.ft) Kit 281154D75R00 Manufacturers Empty Weight : +0.73 kg (+1.6093 lb) Effect on Balance : +15.18 kgm (+109.796 lb.ft) Kit 281154D76R00 Manufacturers Empty Weight : +3.20 kg (+7.0547 lb) Effect on Balance : +69.92 kgm (+505.731 lb.ft) Kit 281154D77R02 Manufacturers Empty Weight : +7.90 kg (+17.4163 lb) Effect on Balance : +162.74 kgm (+1177.098 lb.ft) Kit 281154D78R02 Manufacturers Empty Weight : +0.85 kg (+1.8739 lb) Effect on Balance : 18.10 kgm (+130.917 lb.ft) Kit 281154D79R00 Manufacturers Empty Weight : +1.30 kg (+2.8659 lb) Effect on Balance : +26.52 kgm (+191.819 lb.ft) Kit 281154D80R00 Manufacturers Empty Weight : +62.06 kg (+136.8174 lb) DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 17
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Effect on Balance : +1272.23 kgm (+9202.039 lb.ft) Kit 281154D81R01 Manufacturers Empty Weight : +6.10 kg (+13.4480 lb) Effect on Balance : +126.88 kgm (+917.723 lb.ft) Kit 281154D82R01 Manufacturers Empty Weight : +0.06 kg (+0.1322 lb) Effect on Balance : +1.28 kgm (+9.258 lb.ft) Kit 281154D83R00 Manufacturers Empty Weight : +0.10 kg (+0.2204 lb) Effect on Balance : +2.30 kgm (+16.635 lb.ft) Kit 281154D84R00 Manufacturers Empty Weight : +9.70 kg (+21.3846 lb) Effect on Balance : +223.10 kgm (+1613.682 lb.ft)
**I. E L**  **E C** **T R**  **I C** **A L**  **L O** **A D**  **D A** 

**T**

**A** Not changed

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 18
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

**J. R E**  **F E**  **R E**  **N C**  **E S**  Aircraft Maintenance Manual (AMM) : 06-31-53 06-41-53 07-11-00 11-00-00 12-33-21 12-34-24 20-21-11 20-21-12 20-21-15 20-23-11 20-28-00 21-20-00 21-26-00 21-31-00 21-61-00 21-61-51 21-63-00 21-63-34 22-66-34 22-96-00 22-97-00 23-12-00 23-12-11 23-44-00 23-71-00 24-22-34 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 25-54-11 25-54-12 25-55-00 25-55-11 25-62-00 25-62-42 25-62-43 25-62-46 25-80-00 26-12-00 26-13-00 26-17-34 26-21-00 26-22-00 27-24-00 27-34-00 27-51-00 27-51-34 27-54-00 27-81-00 27-84-00 27-92-15 27-92-16 27-92-41 27-93-00 27-94-00 27-94-34 27-96-00 28-00-00 28-10-00 28-15-00 28-21-00 28-22-00 28-23-00 28-24-00 28-25-00 28-25-55 28-29-00 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 29-23-00 29-24-00 29-31-00 29-32-00 29-33-11 29-34-00 31-10-00 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 32-47-00 32-48-00 32-51-00 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 36-11-00 36-12-00 49-61-34 49-62-00 52-10-00 52-30-00 52-35-00 52-41-00 53-22-14 53-32-12 53-35-11 53-35-13 53-42-12 53-42-14 57-17-11 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 20-52-10 20-52-21 20-55-00 Illustrated Parts Catalog (IPC) : 21-21-03 28-12-05 29-11-03 29-13-03 Structural Repair Manual (SRM) : 51-22-00 51-23-00 51-24-00 51-42-11 51-44-11 51-46-11 51-46-12 51-75-11 51-76-12 Consumable Material List (CML) Process and Material Specification (PMS) DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 19
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Standards Manual (SM) Service Bulletin No. A320-22-1084 Service Bulletin No. A320-22-1102 Service Bulletin No. A320-25-1427 Service Bulletin No. A320-31-1257 Top Drawing D00071141002. DESIGN DRAWINGS SHEET(S) 281154A00001 Sheet(s) 01 A00 281154A00001 Sheet(s) 02 A00 281154A00001 Sheet(s) 03 A00 281154A01001 Sheet(s) 01 A00 281154A01001 Sheet(s) 02 A00 281154A01001 Sheet(s) 03 A00 281154A01002 Sheet(s) 01 A00 281154A01003 Sheet(s) 01 A00 281154A01003 Sheet(s) 02 A00 281154A01003 Sheet(s) 03 A00 281154A01003 Sheet(s) 04 A00 281154A01004 Sheet(s) 01 A00 281154A01004 Sheet(s) 02 A00 281154A01004 Sheet(s) 03 A00 281154A01005 Sheet(s) 01 A00 281154A02001 Sheet(s) 01 A00 281154A02002 Sheet(s) 01 A00 281154A02002 Sheet(s) 02 A00 281154A02002 Sheet(s) 03 A00 281154A02003 Sheet(s) 01 A00 281154A02003 Sheet(s) 02 A00 281154A03000 Sheet(s) 01 A00 281154A03001 Sheet(s) 01 A00 281154A03002 Sheet(s) 01 A00 281154A03002 Sheet(s) 02 A00 281154A03003 Sheet(s) 01 A00 281154A03004 Sheet(s) 01 A00 281154A03005 Sheet(s) 01 A00 281154A03006 Sheet(s) 01 A00 281154A03007 Sheet(s) 01 A00 281154A03008 Sheet(s) 01 A00 281154A04000 Sheet(s) 01 A00 281154A04001 Sheet(s) 01 A00 281154A04001 Sheet(s) 02 A00 281154A04001 Sheet(s) 03 A00 281154A04002 Sheet(s) 01 A00 281154A04002 Sheet(s) 02 A00 281154A04002 Sheet(s) 03 A00 281154A04002 Sheet(s) 04 A00 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 20
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281154A04003 Sheet(s) 01 A00 281154A04003 Sheet(s) 02 A00 281154A04003 Sheet(s) 03 A00 281154A04003 Sheet(s) 04 A00 281154A04003 Sheet(s) 05 A00 281154A04004 Sheet(s) 01 A00 281154A04005 Sheet(s) 01 A00 281154A04006 Sheet(s) 01 A00 281154A04007 Sheet(s) 01 A00 281154A04008 Sheet(s) 01 A00 281154A04009 Sheet(s) 01 A00 281154A04010 Sheet(s) 01 A00 281154A04011 Sheet(s) 01 A00 281154A04011 Sheet(s) 02 A00 281154A04012 Sheet(s) 01 A00 281154A04013 Sheet(s) 01 A00 281154A05001 Sheet(s) 01 A00 281154A05002 Sheet(s) 01 A00 281154A05003 Sheet(s) 01 A00 281154A05003 Sheet(s) 02 A00 281154A06000 Sheet(s) 01 A00 281154A06001 Sheet(s) 01 A00 281154A06002 Sheet(s) 01 A00 281154A06003 Sheet(s) 01 A00 281154A06004 Sheet(s) 01 A00 281154A06005 Sheet(s) 01 A00 281154A06501 Sheet(s) 01 A00 281154A06501 Sheet(s) 02 A00 281154A06502 Sheet(s) 01 A00 281154A06502 Sheet(s) 02 A00 281154A06503 Sheet(s) 01 A00 281154A06503 Sheet(s) 02 A00 281154A06504 Sheet(s) 01 A00 281154A06504 Sheet(s) 02 A00 281154A06505 Sheet(s) 01 A00 281154A06505 Sheet(s) 02 A00 281154A06506 Sheet(s) 01 A00 281154A06506 Sheet(s) 02 A00 281154A06507 Sheet(s) 01 A00 281154A06507 Sheet(s) 02 A00 281154A06508 Sheet(s) 01 A00 281154A06508 Sheet(s) 02 A00 281154A06509 Sheet(s) 01 A00 281154A06509 Sheet(s) 02 A00 281154A06510 Sheet(s) 01 A00 281154A06510 Sheet(s) 02 A00 281154A06511 Sheet(s) 01 A00 281154A06511 Sheet(s) 02 A00 281154A10001 Sheet(s) 01 A00 281154A10001 Sheet(s) 02 A00 281154A10002 Sheet(s) 01 A00 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 21
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281154A10002 Sheet(s) 02 A00 281154A10003 Sheet(s) 01 A00 281154A10004 Sheet(s) 01 A00 281154A10004 Sheet(s) 02 A00 281154A10005 Sheet(s) 01 A00 281154A10005 Sheet(s) 02 A00 281154A10006 Sheet(s) 01 A00 281154A10006 Sheet(s) 02 A00 281154A10007 Sheet(s) 01 A00 281154A10007 Sheet(s) 02 A00 281154A10008 Sheet(s) 01 A00 281154A10008 Sheet(s) 02 A00 281154A10009 Sheet(s) 01 A00 281154A10009 Sheet(s) 02 A00 281154A10010 Sheet(s) 01 A00 281154A10501 Sheet(s) 01 A00 281154A10501 Sheet(s) 02 A00 281154A10501 Sheet(s) 03 A00 281154A10501 Sheet(s) 04 A00 281154A10501 Sheet(s) 05 A00 281154A10501 Sheet(s) 06 A00 281154A10501 Sheet(s) 07 A00 281154A10501 Sheet(s) 08 A00 281154A10501 Sheet(s) 09 A00 281154A10502 Sheet(s) 01 A00 281154A10502 Sheet(s) 02 A00 281154A10502 Sheet(s) 03 A00 281154A10502 Sheet(s) 04 A00 281154A10502 Sheet(s) 05 A00 281154A10503 Sheet(s) 01 B00 281154A10503 Sheet(s) 02 A00 281154A10503 Sheet(s) 03 A00 281154A10503 Sheet(s) 04 A00 281154A10503 Sheet(s) 05 A00 281154A10503 Sheet(s) 06 A00 281154A10503 Sheet(s) 07 A00 281154A10504 Sheet(s) 01 A00 281154A10504 Sheet(s) 02 A00 281154A10504 Sheet(s) 03 A00 281154A10504 Sheet(s) 04 B00 281154A10505 Sheet(s) 01 A00 281154A10505 Sheet(s) 02 A00 281154A10505 Sheet(s) 03 A00 281154A10505 Sheet(s) 04 A00 281154A10505 Sheet(s) 05 A00 281154A10506 Sheet(s) 01 A00 281154A10506 Sheet(s) 02 A00 281154A10506 Sheet(s) 03 A00 281154A10507 Sheet(s) 01 B00 281154A10507 Sheet(s) 02 A00 281154A10507 Sheet(s) 03 A00 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 22
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281154A10507 Sheet(s) 04 A00 281154A10507 Sheet(s) 05 A00 281154A10508 Sheet(s) 01 A00 281154A10508 Sheet(s) 02 A00 281154A10508 Sheet(s) 03 A00 281154A10509 Sheet(s) 01 A00 281154A10509 Sheet(s) 02 A00 281154A10509 Sheet(s) 03 A00 281154A10510 Sheet(s) 01 A00 281154A10510 Sheet(s) 02 A00 281154A10511 Sheet(s) 01 A00 281154A10511 Sheet(s) 02 A00 281154A10512 Sheet(s) 01 A00 281154A10512 Sheet(s) 02 A00 281154A10513 Sheet(s) 01 A00 281154A10513 Sheet(s) 02 A00 281154A10514 Sheet(s) 01 A00 281154A10514 Sheet(s) 02 A00 281154A10515 Sheet(s) 01 A00 281154A10515 Sheet(s) 02 A00 281154A10516 Sheet(s) 01 A00 281154A10516 Sheet(s) 02 A00 281154A10517 Sheet(s) 01 A00 281154A10517 Sheet(s) 02 A00 281154A10518 Sheet(s) 01 B00 281154A10518 Sheet(s) 02 A00 281154A10518 Sheet(s) 03 A00 281154A10518 Sheet(s) 04 A00 281154A10518 Sheet(s) 05 A00 281154A10519 Sheet(s) 01 A00 281154A10519 Sheet(s) 02 A00 281154A10520 Sheet(s) 01 A00 281154A10520 Sheet(s) 02 A00 281154A10521 Sheet(s) 01 A00 281154A10521 Sheet(s) 02 A00 281154A11000 Sheet(s) 01 A00 281154A11001 Sheet(s) 01 A00 281154A11002 Sheet(s) 01 A00 281154A11002 Sheet(s) 02 A00 281154A11003 Sheet(s) 01 A00 281154A11004 Sheet(s) 01 A00 281154A11004 Sheet(s) 02 A00 D11277100197 Sheet(s) 67 D25286364014 Sheet(s) 7 and 8 D25288767000 Sheet(s) 1 and 2 D25571077000 Sheet(s) 1 D25571077002 Sheet(s) 2 D25571077004 Sheet(s) 3 D25571077006 Sheet(s) 4 D25572207000 Sheet(s) 1 thru 7 D25572592000 Sheet(s) 1 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 23
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) D25572592004 Sheet(s) 3 D25572592006 Sheet(s) 4 D25572592010 Sheet(s) 6 D25572592012 Sheet(s) 7 D25572592014 Sheet(s) 8 D25572672032 Sheet(s) 17 D25572676034 Sheet(s) 18 D25573522000 Sheet(s) 1 D25573525008 Sheet(s) 17 thru 20 D25670762000 Sheet(s) 1 thru 7 D25671745000 Sheet(s) 1 thru 7 D25671746000 Sheet(s) 1 thru 4 D25690000004 Sheet(s) 7 thru 9 D25870003050 Sheet(s) 28 D28270515000 Sheet(s) 1 thru 4 D28270998002 Sheet(s) 2 D28270999004 Sheet(s) 3 D28271012000 Sheet(s) 1 thru 6 D28271013000 Sheet(s) 5 D28271014000 Sheet(s) 1 thru 3 D28271015 Sheet(s) 1, 5, 6 and 8 D28271015000 Sheet(s) 1 thru 8 D28271016002 Sheet(s) 1 thru 5, 7 thru 12 D53370297002 Sheet(s) 1 thru 4 and 6 thru 12 D53370297003 Sheet(s) 1 thru 12 D53370780004 Sheet(s) 2 D53371072000 Sheet(s) 1 thru 6 D53371236000 Sheet(s) 1 D53371236001 Sheet(s) 1 D53372385000 Sheet(s) 1 thru 7 D53375751004 Sheet(s) 7 D53475023000 Sheet(s) 1 thru 4 D53476032000 Sheet(s) 1 thru 27 D53672231058 Sheet(s) 23 thru 25 D53672231108 Sheet(s) 26 D53675023000 Sheet(s) 1 thru 2 D53675024000 Sheet(s) 1 thru 3 D53675516002 Sheet(s) 4 thru 6 D53675526002 Sheet(s) 4 thru 6 D53975027000 Sheet(s) 1 thru 6 D92355000 Sheet(s) 1 D92450115 Sheet(s) 1 and 2 D92450341 Sheet(s) 1, 4 and 6 D92492871000 Sheet(s) 1 thru 5 D92492871002 Sheet(s) 6 D92492871004 Sheet(s) 7 thru 9 D92492872000 Sheet(s) 1 thru 13 D92492872002 Sheet(s) 14 thru 17 D92550025 Sheet(s) 1 D92550032 Sheet(s) 1 and 2 D92556025 Sheet(s) 1 and 5 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 24
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) D92891821016 Sheet(s) 17 D92891825000 Sheet(s) 1 thru 28 D92891825002 Sheet(s) 29 thru 43 D92891825004 Sheet(s) 44 thru 49 D92894713084 Sheet(s) 1 D92894748008 Sheet(s) 32 thru 36 D92894721006 Sheet(s) 10 thru 16 D92894736004 Sheet(s) 14 thru 17 D92992293014 Sheet(s) 16 D92992293016 Sheet(s) 17 D92992293038 Sheet(s) 42 D92992293040 Sheet(s) 43 D92995625002 Sheet(s) 4 and H002 D92995625008 Sheet(s) 9 and H008 D92995626002 Sheet(s) 5 and H002 D92995626006 Sheet(s) 10 and H006 D92995627002 Sheet(s) 4 and H002 D92995627006 Sheet(s) 7 and H006 D92996405000 Sheet(s) 1 D92996405001 Sheet(s) 2 and H001 D92996455000 Sheet(s) 1 and H000 D92996455001 Sheet(s) 2 and H001 D92996461008 Sheet(s) 9 and H008 D92996461009 Sheet(s) 10 and H009 D92996462000 Sheet(s) 1 and H000 D92996462001 Sheet(s) 2 and H001 D92996463000 Sheet(s) 1 and H000 D92996463001 Sheet(s) 2 and H001 D92996464000 Sheet(s) 1 and H000 D92996464001 Sheet(s) 2 and H001 D92996470002 Sheet(s) 3 and H002 D92996470003 Sheet(s) 4 and H003 D92996471002 Sheet(s) 3 and H002 D92996471004 Sheet(s) 5 and H004 D92996472006 Sheet(s) 7 and H006 D92996472007 Sheet(s) 8 and H007 D92996473000 Sheet(s) 1 and H000 D92996473001 Sheet(s) 2 and H001 D92996475001 Sheet(s) 2 and H001 D92996475003 Sheet(s) 4 and H003 D92996480003 Sheet(s) 4 and H003 D92996480004 Sheet(s) 5 and H004 D92996481000 Sheet(s) 1 and H000 D92996481001 Sheet(s) 2 and H001 D92996483000 Sheet(s) 1 and H000 D92996483001 Sheet(s) 2 and H001 D92996492002 Sheet(s) 3 and H002 D92996492003 Sheet(s) 4 and H003 D92996493000 Sheet(s) 1 and H000 D92996493001 Sheet(s) 2 and H001 D92996494000 Sheet(s) 1 and H000 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 25
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) D92996494001 Sheet(s) 2 and H001 D92996496000 Sheet(s) 1 and H000 D92996496001 Sheet(s) 2 and H001 D92997046001 Sheet(s) 1 and 2 D92997046002 Sheet(s) 3 thru 5 D92997046003 Sheet(s) 6 thru 9 D92997046004 Sheet(s) 10 thru 20 D92997046005 Sheet(s) 21 and 22 D92997046006 Sheet(s) 23 and 24 D92997046007 Sheet(s) 25 and 26 D92997046008 Sheet(s) 27 thru 30 and 32 D92997046009 Sheet(s) 33 and 34 D92997046010 Sheet(s) 35 thru 37 D92997046011 Sheet(s) 38 thru 40 D92997046012 Sheet(s) 41 and 42 D92997046013 Sheet(s) 43 and 44 D92999571004 Sheet(s) 3 and 4 D93070668000 Sheet(s) 1 thru 8 D93470502000 Sheet(s) 1 thru 6
**K. P U**  **B L**  **I C** **A T**  **I O**  **N S**  **A F**  **F E**  **C T**  **E D**  Aircraft Maintenance Manual (AMM) : 05-21-50 10-11-00 10-12-00 11-31-31 12-11-28 28-00-00 28-10-00 28-11-00 28-12-00 28-12-41 28-12-44 28-20-00 28-21-00 28-21-52 28-21-53 28-23-00 28-24-00 28-25-00 28-25-42 28-25-51 28-25-52 28-25-58 28-28-11 28-28-31 28-28-33 28-28-46 28-28-51 28-28-53 28-40-00 28-42-00 28-42-15 28-42-16 28-42-21 28-42-22 28-43-00 28-46-00 28-46-34 32-62-00 57-10-00 57-17-11 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 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

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 26
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Aircraft Wiring Manual (AWM) : 24-58-06 24-68-01 24-68-02 24-68-04 24-68-05 24-68-15 27-81-25 28-21-07 28-21-08 28-25-04 28-25-08 28-28-01 28-28-02 28-28-03 28-28-04 28-42-15 28-42-16 28-42-19 28-42-21 28-46-01 28-46-03 28-46-14 28-46-15 31-54-81 33-14-08 93-01-03 93-01-07 93-01-21 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 List (AWL) Master Minimum Equipment List (MMEL) Flight Manual (FM) Flight Crew Operating Manual : Vol. 1 Vol. 2 Vol. 3 This Service Bulletin has an operational impact. Please inform AIRBUS, at least four weeks in advance, in case you need your operational documentation to be amended by an intermediate revision prior to SB embodiment. For this purpose, please request the intermediate revision by fax, telex or mail to : SDC3, AIRBUS - Customer Services Directorate Fax No. (33) 5 61 93 28 06 Sita No. TLSBP7X E-mail sb.reporting@airbus.com These amendments will be confirmed by the next normal revision of operational documentation, once your Service Bulletin accomplishment report has been sent, as usual, to our Customer Services Directorate (SDC3).
**L. I N**  **T E**  **R C**  **H A**  **N G**  **E A**  **B I**  **L I**  **T Y**  **/ M**  **I X** **A B**  **I L**  **I T** **Y** DESCRIPTION OLD PART No. NEW PART No. INT MIXABILITY FQI 1407KID02-03 1422KID02-03 03 Not applicable FQIC SIC5059-11-0207 SIC5059-12-0308 03 Not applicable NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. NOTE(01) You can install Fuel Quantity Indication Computer (FQIC) PN SIC5059-13-10 as an alternative to PN SIC5059-12-0308.

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 27
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 28
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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

**A I**  **L A**  **B I**  **L I** **T Y**  (1) Material The material kit is included in the commercial offer of the Letter Agreement, and as such will be supplied by Airbus Upgrade Services. To facilitate the material kit reception, Airline Customers are requested to send a Customer Purchase Order to : Airbus Upgrade Services Attn : FCO Manager Vendor parts are to be purchased from :

AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE (2) Price and Availability Sales terms must be agreed between the Customers and AIRBUS in accordance with the RFC (or RFC/RMO) procedure.
**B. I N**  **D U**  **S T**  **R Y**  **S U**  **P P** **O R** **T I**  **N F** **O R**  **M A**  **T I**  **O N**  Refer to paragraph 2.A.(2): Price and Availability. **C. L I**  **S T**  **O F**  **C O**  **M P** **O N**  **E N**  **T S**  Kit 281154A01R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5713304820004 Doubler 281154A01001 0 1 D5713031920000 Doubler 281154A01001 1 19 EN6115V3-3 Bolt 281154A01001 10 15 EN6115V3-4 Bolt 281154A01001 11 15 EN6115V3-5 Bolt 281154A01001 12 29 NSA5357-3-6 Pin 281154A01001 13 12 NSA5357-3-7 Pin 281154A01001 14 16 NSA5357-3-5 Pin 281154A01001 15

8 NSA5357-4-7 Pin 281154A01001 22 5 NSA5357-4-8 Pin 281154A01001 23 57 NSA5330-6 Nut 281154A01001 30 49 ASNA2528-3 Nut 281154A01001 35 13 NSA5330-8 Nut 281154A01001 40 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 29
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
1 D5791332400000 Bracket 281154A01002 0 1 D5791332300000 Bracket 281154A01002 1 2 EN6115V3-5 Bolt 281154A01002 10 4 ASNA2528-3 Nut 281154A01002 11 2 EN6115V3-7 Bolt 281154A01002 12 1 D5791049500095 Support 281154A01003 1 1 D5791049400095 Support 281154A01003 2 1 D5791048300095 Fitting 281154A01003 3 1 D5791048200095 Fitting 281154A01003 4 1 D5791042020095 Fitting 281154A01003 5 1 D5791042120095 Fitting 281154A01003 6 1 D5791043020095 Fitting 281154A01003 9 1 D5791049820095 Fitting 281154A01003 10 1 D5791050020095 Fitting 281154A01003 11 1 D5791042320095 Support 281154A01003 12 1 D5791042220095 Support 281154A01003 13 2 A2823301800202 Plate 281154A01003 21 4 ASNA2050DCJ3215 Rivet 281154A01003 22 6 NSA5357-3-5 Pin 281154A01003 100 8 NSA5357-3-7 Pin 281154A01003 102 4 NSA5357-3-8 Pin 281154A01003 103 4 NSA5357-3-10 Pin 281154A01003 104 4 NSA5357-4-7 Pin 281154A01003 107 8 NSA5357-4-8 Pin 281154A01003 108 2 NSA5357-4-9 Pin 281154A01003 109 4 NSA5357-4-10 Pin 281154A01003 110 22 NSA5330-6 Nut 281154A01003 120 18 NSA5330-8 Nut 281154A01003 130

1 D5791041820095 Support 281154A01004 0 2 NSA5357-4-11 Pin 281154A01004 60 2 NSA5357-5-13 Pin 281154A01004 65 2 NSA5330-8 Nut 281154A01004 75 2 NSA5330-10 Nut 281154A01004 80 1 D2821334100300 Rod 281154A01005 0 1 D2821334220000 Bracket 281154A01005 4 4 NAS6603-4 Bolt 281154A01005 12 2 NAS6604-9 Bolt 281154A01005 14 4 NSA5050-3 Nut 281154A01005 20 2 NSA5050-4 Nut 281154A01005 22 4 ASNA2397-10L Washer 281154A01005 24 2 ASNA2397-416L Washer 281154A01005 26 1 D5713032000095 Loft

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154A02R00

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 30
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 A2823301800202 Plate 281154A02001 12 2 ASNA2050DCJ3215 Rivet 281154A02001 32 1 D5791040320095 Bracket 281154A02002 1 1 D5791040500095 Support 281154A02002 2 1 D5791040400095 Support 281154A02002 3 1 D5791040120095 Bracket 281154A02002 4 1 D5791040020295 Bracket 281154A02002 5 1 D5791040220095 Bracket 281154A02002 6 1 D5791040820095 Bracket 281154A02002 7 1 D5791040920095 Bracket 281154A02002 8 1 D5791040620095 Bracket 281154A02002 9 1 D5791040720095 Bracket 281154A02002 10 1 D5791041020095 Bracket 281154A02002 11 4 NAS6603-4 Bolt 281154A02002 44 4 NSA5050-3 Nut 281154A02002 62 8 NSA5357-4-9 Pin 281154A02002 157 5 NSA5357-4-10 Pin 281154A02002 158 17 NSA5357-4-11 Pin 281154A02002 159

1 NSA5357-4-12 Pin 281154A02002 160 1 NSA5357-5-13 Pin 281154A02002 162 31 NSA5330-8 Nut 281154A02002 165

1 NSA5330-10 Nut 281154A02002 170 1 D2821334100400 Rod 281154A02003 2 1 D2821040220000 Bracket 281154A02003 6 1 D2821040120000 Plate 281154A02003 8 8 NAS6603-2 Bolt 281154A02003 10 4 NAS6603-4 Bolt 281154A02003 12 2 NAS6604-9 Bolt 281154A02003 14 4 NSA5050-3 Nut 281154A02003 20 2 NSA5050-4 Nut 281154A02003 22 12 ASNA2397-10L Washer 281154A02003 24

2 ASNA2397-416L Washer 281154A02003 26

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154A03R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5713334000000 Fairing 281154A03002 0 1 D5713334600000 Fitting 281154A03002 1 1 D5713334500000 Fitting 281154A03002 2 1 D5713334400000 Fitting 281154A03002 3 1 D5713323000000 Door 281154A03002 4 8 A5713052120300 Washer 281154A03002 6 3 NAS6603-2 Bolt 281154A03002 10 15 ABS0114V4-18 Bolt 281154A03002 11

4 ASNA2397D10L Washer 281154A03002 15 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 31
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
15 MS20002C4 Washer 281154A03002 16

1 NAS6603-3 Bolt 281154A03002 20 6 NAS6604-3 Bolt 281154A03002 22 6 ASNA2397D416L Washer 281154A03002 40 1 D2821067800000 Bulkhead 281154A03004 8 1 A2823260820000 Plug 281154A03004 10 1 A2823260500000 Valve 281154A03004 12 3 NSA8200-6 O-Ring 281154A03004 18 1 NSA8203-019 O-Ring 281154A03004 20 4 NAS6603-5 Bolt 281154A03004 22 4 ASNA2055-03 Washer 281154A03004 24 4 NSA5050-3 Nut 281154A03004 26 0.3 m MS20995C32 Wire 281154A03004 28

1 A2821064820040 Pin 281154A03005 10 1 A2821064620000 Insert 281154A03005 12 1 A2821064720000 Spring 281154A03005 14 1 NSA8203-113 O-Ring 281154A03005 18 1 NSA8203-167 O-Ring 281154A03005 22 1 NSA8203-224 O-Ring 281154A03005 24 1 NSA8203-226 O-Ring 281154A03005 26 2 E0088-10-100 Lead 281154A03005 28 4 NAS6603-1 Bolt 281154A03005 29 6 NAS6604-7 Bolt 281154A03005 30 1 NAS6604-20 Bolt 281154A03005 32 1 NSA5112-04 Washer 281154A03005 34 6 ASNA2397-416 Washer 281154A03005 36 1 ASNA2397-416L Washer 281154A03005 38 4 ASNA2397D10L Washer 281154A03005 39 1 NSA5050-4 Nut 281154A03005 40 2 NSA5050-3 Nut 281154A03005 42 0.3 m MS20995C32 Wire 281154A03005 48

1 NSA8203-245 O-Ring 281154A03006 6 4 NAS1154-10 Screw 281154A03006 8 1 NAS1801-06-6 Screw 281154A03006 10 1 NAS1801-3-6 Screw 281154A03006 11 1 ASNA2397-6L Washer 281154A03006 12 1 ASNA2397-10L Washer 281154A03006 13 1 MS21042-06 Nut 281154A03006 14 4 NAS1726C4E Nut 281154A03006 16 1 E0088-16-125 Lead 281154A03006 22 1 NSA8203-154 O-Ring 281154A03007 6 6 NAS1153-4 Screw 281154A03007 8 1 NAS1801-06-6 Screw 281154A03007 13 4 NAS1726C4E Nut 281154A03007 16 1 ASNA2397-6L Washer 281154A03007 17 1 MS21042L06 Nut 281154A03007 18 1 E0088-16-100 Lead 281154A03007 22 0.4 m MS20995C32 Wire 281154A03007 24

1 D2821336920000 PLACARD 281154A03008 0 1 D2821336920200 PLACARD 281154A03008 2 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 32
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
1 D2821336920400 PLACARD 281154A03008 4 1 D2821336920600 PLACARD 281154A03008 6 1 D2821336920800 PLACARD 281154A03008 8

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154A04R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 4 NSA8203-226 O-Ring 281154A04002 5 1 D2821333900000 Pipe 281154A04002 6 1 NAS6603-3 Bolt 281154A04002 9 1 ASNA2397JD10L Washer 281154A04002 10 1 ASNA2397-10L Washer 281154A04002 11 1 D2821333900100 Pipe 281154A04002 12 3 NAS6603-2 Bolt 281154A04002 16 2 NAS1726-3E Nut 281154A04002 18 4 NAS6604-5 Bolt 281154A04002 110 4 ASNA2397-416L Washer 281154A04002 112 4 NAS1726-4E Nut 281154A04002 114 1 D2821331020000 Tee 281154A04002 120 1 D2821333900900 Pipe 281154A04003 20 1 D2821333900300 Pipe 281154A04003 22 1 D2821333900400 Pipe 281154A04003 24 1 D2821333900600 Pipe 281154A04003 28 1 D2821333900700 Pipe 281154A04003 30 1 D2821333901000 Pipe 281154A04003 32 1 A2821038600000 Sleeve 281154A04003 34 1 D2821333800000 Sleeve 281154A04003 36 1 D2821334800200 Pipe 281154A04003 38 1 D2821334900200 Pipe 281154A04003 40 1 D2821335000200 Pipe 281154A04003 42 1 D2821338500000 Pipe 281154A04003 44 1 D2821335800200 Pipe 281154A04003 46 1 D2821336720240 RSTRCTR 281154A04003 50 1 NSA5516A04NF Clamp 281154A04003 51 1 MS21902D4 Union 281154A04003 52 1 ASNA0182-1DA Strip 281154A04003 53 2 ABS0107-150 Nut 281154A04003 55 2 ABS0107-200 Nut 281154A04003 56 2 NSA840003-150 Ring 281154A04003 57 2 NSA840003-200 Ring 281154A04003 58 1 NSA8200-4 O-Ring 281154A04003 60 1 NSA8203-215 O-Ring 281154A04003 62 12 NSA8203-222 O-Ring 281154A04003 64

4 NSA8203-226 O-Ring 281154A04003 66 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 33
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
2 NAS1801-06-10 Screw 281154A04003 68 14 NAS6603-2 Bolt 281154A04003 70

4 NAS6603-4 Bolt 281154A04003 72 4 NAS6603-5 Bolt 281154A04003 73 4 NAS6603-7 Bolt 281154A04003 74 2 NAS6604-2 Bolt 281154A04003 76 4 NAS6604-3 Bolt 281154A04003 77 2 MS21042L06 Nut 281154A04003 78 19 NSA5050-3 Nut 281154A04003 80

6 NSA5050-4 Nut 281154A04003 82 2 ASNA2397-6L Washer 281154A04003 83 7 ASNA2397-10L Washer 281154A04003 84 2 E0088-10-160 Lead 281154A04003 90 1 E0088-10-200 Lead 281154A04003 92 1 E0088-10-280 Lead 281154A04003 93 1 D2821331620000 Tee 281154A04004 0 6 NAS6604-5 Bolt 281154A04004 10 6 ASNA2397-416L Washer 281154A04004 12 6 NAS1726-4E Nut 281154A04004 14 1 D2821332220000 Elbow 281154A04005 0 2 NAS6604-4 Bolt 281154A04005 10 2 ASNA2397-416L Washer 281154A04005 12 2 NAS1726-4E Nut 281154A04005 14 1 A2821120120000 Elbow 281154A04006 0 2 NAS6604-4 Bolt 281154A04006 10 2 ASNA2397-416L Washer 281154A04006 12 2 NAS1726-4E Nut 281154A04006 14 1 D2821332620000 Elbow 281154A04007 0 2 NAS6604-5 Bolt 281154A04007 10 2 ASNA2397-416L Washer 281154A04007 12 2 NAS1726-4E Nut 281154A04007 14 1 D2821339020000 Elbow 281154A04008 0 1 NSA8203-226 O-Ring 281154A04008 8 4 NAS6603-4 Bolt 281154A04008 10 4 ASNA2397D10L Washer 281154A04008 12 1 D2821333220000 Elbow 281154A04009 0 1 D2821333420000 Elbow 281154A04009 2 1 D2821336621240 RSTRCTR 281154A04009 4 2 NSA8203-222 O-Ring 281154A04009 8 8 NAS6603-3 Bolt 281154A04009 10 8 ASNA2397-10L Washer 281154A04009 12 1 A2821079520000 Flange 281154A04010 1 1 D2821335621800 RSTRCTR 281154A04010 2 1 ABS0107-200 Nut 281154A04010 3 1 NSA840003-200 Ring 281154A04010 4 3 NSA8203-226 O-Ring 281154A04010 5 4 NAS6604-12 Bolt 281154A04010 8 4 NAS1726-4E Nut 281154A04010 9 2 E0088-10-100 Lead 281154A04010 11 2 NAS1726-3E Nut 281154A04010 12 1 NAS6603-2 Bolt 281154A04010 13 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 34
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
1 NAS6603-1 Bolt 281154A04010 14 2 ASNA2397-10L Washer 281154A04010 19 1 D2821336300000 Sleeve 281154A04011 35 2 ABS0107-150 Nut 281154A04011 55 2 NSA840003-150 Ring 281154A04011 57 1 NSA8200-5 O-Ring 281154A04011 61 2 NSA8203-222 O-Ring 281154A04011 64 2 NAS6603-2 Bolt 281154A04011 70 2 NSA5050-3 Nut 281154A04011 80 1 D2821331320000 Tee 281154A04012 0 4 NAS6604-5 Bolt 281154A04012 10 4 ASNA2397-416L Washer 281154A04012 12 4 NAS1726-4E Nut 281154A04012 14 1 D2821331920000 Elbow 281154A04013 0 1 D2821336500000 Sleeve 281154A04013 2 2 NSA8203-222 O-Ring 281154A04013 8 4 NAS6603-7 Bolt 281154A04013 10 4 ASNA2397-416L Washer 281154A04013 12

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154A05R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2821330700000 Elbow 281154A05001 0 1 D2821334700000 Nutplate 281154A05001 2 1 D2821337500000 Nutplate 281154A05001 4 1 NSA8203-148 O-Ring 281154A05001 8 6 NAS6604-9 Bolt 281154A05001 10 6 ASNA2397-416L Washer 281154A05001 12 1 NAS6603-2 Bolt 281154A05001 14 1 ASNA2397-10L Washer 281154A05001 16 1 D2821337700041 Elbow 281154A05002 0 1 D2821334600000 Nutplate 281154A05002 2 1 D2821337600000 Nutplate 281154A05002 4 1 NSA8203-152 O-Ring 281154A05002 8 6 NAS6604-8 Bolt 281154A05002 10 6 ASNA2397-416L Washer 281154A05002 12 1 D2821337800000 Filter 281154A05002 14 1 D2821337120000 Plate 281154A05002 16 4 NAS6603-2 Bolt 281154A05002 18 2 NAS6603-5 Bolt 281154A05002 20 5 ASNA2397JD10L Washer 281154A05002 22 2 NSA5050-3 Nut 281154A05002 24 1 ASNA2397-10L Washer 281154A05002 26

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 35
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154A06R02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9251314900000 Plate 281154A06003 0 4 NAS1102-06-7 Screw 281154A06003 14 1 NAS1102-08-7 Screw 281154A06003 15 2 NAS1102-06-5 Screw 281154A06003 16 5 ASNA2083BG2-10 Screw 281154A06003 17 28 NAS1102-04-6 Screw 281154A06003 18

1 MS21042-08 Nut 281154A06003 21 1 ASNA2397-8L Washer 281154A06003 24 1 E0417C01S CNCTR 281154A06003 31 1 E0416-02 Sleeve 281154A06003 32 1 E0415C3LM078E Switch 281154A06003 33 1 D1131043320100 Placard 281154A06004 4 1 D1131043320200 Placard 281154A06004 6 3 NSA931320-030 C/B 281154A06005 1 2 NSA931320-050 C/B 281154A06005 2 1 NSA931322-100 C/B 281154A06005 3 6 ABS0772A02A Clamp 281154A06005 6 1 D9000095128395 Bundle 1 D9100095114295 PLCRDSET 150 NSA935401-03 Tie 150 NSA935401-06 Tie NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154A07R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D33110194A00 Plate 281154A06003 35

Kit 281154A08R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 HTE690045 Switch 281154A03004 0 1 568-1-27170-002 Pump 281154A03005 0 1 568-1-27171-002 Plate 281154A03005 2 1 1158000-15 Canister 281154A03006 0 1 1158000-21 Valve 281154A03006 2 1 HTE900135 Valve 281154A03007 0 1 HTE190001-2 Actuator 281154A03007 2 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 36
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 HTE8002 Clamp 281154A03007 4

NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. Kit 281154A09R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 9843144M Valve 281154A04010 0 1 365A02 Valve 281154A04011 54

Kit 281154A10R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 E0661-21 Mount 281154A10002 1 4 E0420-04 Stud 281154A10002 2 1 ABS0355-02 Bracket 281154A10002 3 2 E0661-22 Mount 281154A10002 5 1 D9241244120000 Bracket 281154A10003 1 1 NSA5527-03-01 Spacer 281154A10003 2 1 NAS1801-3-20 Screw 281154A10003 3 2 NSA935504-01 Mount 281154A10003 4 1 NAS1726-3E Nut 281154A10003 5 2 ASNA2051DCJ3215 Rivet 281154A10003 18 1 D5391047900001 Bracket 281154A10004 0 2 ASNA2050DCJ3215 Rivet 281154A10004 6 1 NSA935504-03 Mount 281154A10005 0 2 NSA935504-01 Mount 281154A10005 2 3 NAS1801-3-8 Screw 281154A10005 4 3 ASNA2397-10L Washer 281154A10005 6 5 NAS1801-3-9 Screw 281154A10006 10 5 ASNA2397-10L Washer 281154A10006 11 5 NAS1726-3E Nut 281154A10006 14 1 EN3646A62041BN CNCTR 281154A10006 20 1 EN3646A61419BN CNCTR 281154A10006 21 1 E0080-01-20C BACKSHLL 281154A10006 22 1 E0080-01-14C BACKSHLL 281154A10006 23 10 m E0432A14 Conduit 281154A10006

1 EN3545D03FXB24A CNCTR 281154A10007 20 (01) 1 EN3545-007SCD BACKSHLL 281154A10007 22 2 MS21042L04 Nut 281154A10008 6 1 E0245-28A0 Relay 281154A10008 40 1 E0250A0S Base 281154A10008 41 3 ASNA2397-4L Washer 281154A10009 4 3 MS21042L04 Nut 281154A10009 6 3 NAS1100-04-7 Screw 281154A10009 8 1 EN3545D03FXA22A CNCTR 281154A10009 50 (02) 1 EN3545D03MXB22A CNCTR 281154A10009 51 (03) DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 37
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
2 EN3545-007SCD BACKSHLL 281154A10009 52 1 NSA937901MA2008 Module 281154A10009 60 1 NSA937901E1 IDENT. 281154A10009 61 1 NSA937901E0 IDENT. 281154A10009 62 1 NSA932843AA01 Relay 281154A10009 70 1 NSA932844AA Base 281154A10009 71 1 NSA937901MA2206 Module 281154A10010 0 2 NSA937901E2 IDENT. 281154A10010 1 1 NSA937901E8 IDENT. 281154A10010 2 1 NSA937901MA2204 Module 281154A10010 3 1 NSA937901E6 IDENT. 281154A10010 4 1 D9000095140995 BUNDLE 1 D9000095141095 BUNDLE 1 D9000095141195 BUNDLE 1 D9000095141295 BUNDLE 1 D9000095141395 BUNDLE 1 D9000095141495 BUNDLE 1 D9000095141595 BUNDLE 1 D9000095141695 BUNDLE 1 D9000095141795 BUNDLE 1 D9100095117895 PLCRDSET 100 NSA935401-03 Tie 360 NSA935401-04 Tie 300 NSA935401-05 Tie 480 NSA935401-06 Tie 960 NSA935401-08 Tie NOTE(01) PN supplied with reference EN3545D03FXB00A. NOTE(02) PN supplied with reference EN3545D03FXA00A. NOTE(03) PN supplied with reference EN3545D03MXB00A. NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154A11R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 NAS1102-3-10 Screw 281154A11002 4 1 D9251101900000 PLATE 281154A11002 5 6 NAS1801-3-8 Screw 281154A11002 12 5 NSA939511-03 Cover 281154A11002 15 8 NSA5050-3 Nut 281154A11002 16 6 ASNA2397-10L Washer 281154A11002 28 1 NSA937901MA2204 Module 281154A11002 50 1 NSA937901MA2011 Module 281154A11002 51 3 NSA937901E2 IDENT. 281154A11002 52 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 38
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
1 NSA937901E1 IDENT. 281154A11002 53 1 E0425A2001 Module 281154A11002 55 2 D9251127600000 Flange 281154A11003 0 1 D0003006100000 Rack 281154A11003 1 1 E0161D01A12X CNCTR 281154A11003 3 (01) 4 NAS1100-06-12 Screw 281154A11003 6 4 NAS1100-04-7 Screw 281154A11003 9 2 ASNA2397-6L Washer 281154A11003 12 4 ASNA2397-4L Washer 281154A11003 14 1 E0427-01A Retainer 281154A11004 1 1 NAS1100-04-6 Screw 281154A11004 2 1 ASNA2397-4L Washer 281154A11004 4 1 ASNA2397-3L Washer 281154A11004 5 3 MS21042L04 Nut 281154A11004 6 1 E0247A0S Base 281154A11004 40 1 E0666D28A0 Relay 281154A11004 41 1 D9100095116895 PLCRDSET

NOTE(01) PN supplied with reference E0161D01A01X. NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154A12R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 30042-0000-0501 CTL UNIT 281154A11002

Kit 281154A13R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9000095147795 Bundle 50 NSA935401-06 Tie NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154B01R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 QB0566 Filter D28271015 41 2 HTE490005 Valve D28271015 42 1 HTE200002-1 Actuator D28271015 43 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 39
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
1 HTE920007-001 Valve D28271015 44 1 HTE8002 Clamp D28271015 45 1 PAS148-133A Valve D28271015 46

Kit 281154B02R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9255602500800 Relay D92355000 158

Kit 281154B03R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9245011500600 Panel D92450341 154 1 D9255003200400 Panel D92450341 168 1 D9255002500000 Panel D92450341 174

Kit 281154B04R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9240000065595 Bundle D92400000

Kit 281154D01R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D1121004620000 PLACARD D11277100197 0071 2 D1121009120000 PLACARD D11277100197 0099 1 D1127700034100 PLACARD D11277100197 0141

Kit 281154D02R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9289182101600 PLACARD D92891821016 1 D9299640500100 HARNESS D92997046000 0002 1 D9299704600100 ELTEQUIP D92997046000 0004 1 D9299704600200 ELTEQUIP D92997046000 0006 1 D9299704600300 ELTEQUIP D92997046000 0008 1 D9299704600400 ELTEQUIP D92997046000 0010 1 D9299704600500 ELTEQUIP D92997046000 0012 1 D9299704600600 ELTEQUIP D92997046000 0014 1 D9299704600700 ELTEQUIP D92997046000 0018 1 D9299645500100 HARNESS D92997046000 0020 1 D9299646100900 HARNESS D92997046000 0024 1 D9299646200100 HARNESS D92997046000 0026 1 D9299646300100 HARNESS D92997046000 0028 1 D9299646400100 HARNESS D92997046000 0030 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 40
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
1 D9299647000300 HARNESS D92997046000 0032 1 D9299647100400 HARNESS D92997046000 0034 1 D9299647200700 HARNESS D92997046000 0036 1 D9299647300100 HARNESS D92997046000 0038 1 D9299647500300 HARNESS D92997046000 0040 1 D9299648000400 HARNESS D92997046000 0042 1 D9299648100100 HARNESS D92997046000 0044 1 D9299648300100 HARNESS D92997046000 0046 1 D9299649200300 HARNESS D92997046000 0048 1 D9299649300100 HARNESS D92997046000 0050 1 D9299649400100 HARNESS D92997046000 0052 1 D9299649600100 HARNESS D92997046000 0054 1 D9299704600800 ELTEQUIP D92997046000 0060 1 D9299704600900 ELTEQUIP D92997046000 0065 1 D9299704601000 ELTEQUIP D92997046000 0070 1 D9299704601100 ELTEQUIP D92997046000 0075 1 D9299704601200 ELTEQUIP D92997046000 0080 1 D9299704601300 ELTEQUIP D92997046000 0085

Kit 281154D04R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5347503400200 PANEL D53475024000 0000 1 D5347542400000 BRACKET D53475024000 0008 2 D5347542720000 BRACKET D53475024000 0010 1 D5347542400200 BRACKET D53475024000 0012 3 ABS0368-01 RECEPTCLD53475024000 0028 2 NAS1791A3-1 NUT D53475024000 0030 2 D5347521320000 WASHER D53475024000 0032 49 DIN65399-2406BF RIVET D53475024000 0125 49 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 281154D05R02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5337217000200 BEAM D53372385000 0001 4 MS21250-06018 BOLT D53372385000 0002 4 NAS1726-6E NUT D53372385000 0003 4 MS20002C6 WASHER D53372385000 0004 2 MS21250-09024 BOLT D53372385000 0005 2 NAS1726-9E NUT D53372385000 0006 2 MS20002C9 WASHER D53372385000 0007 2 D5337217220000 FITTING D53372385000 0010 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 41
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
2 D5337217220100 FITTING D53372385000 0011 4 D5347100920090 SUPPORT D53372385000 0012 1 D5337219220000 FITTING D53372385000 0013 1 D5337219120200 FITTING D53372385000 0014 4 NAS1791A3-1 NUT D53372385000 0015 1 D5337219020200 FITTING D53372385000 0016 1 D5337215920000 ANGLE D53372385000 0017 8 D5337215920200 ANGLE D53372385000 0018 1 D5347104120090 ANGLE D53372385000 0019 1 D5337215920400 ANGLE D53372385000 0020 1 D5337215920600 ANGLE D53372385000 0021 4 D5347100920190 SUPPORT D53372385000 0022 13 DAN5-6-4X PIN D53372385000 0023

4 DAN5-6-7X PIN D53372385000 0024 8 DAN5-6-5X PIN D53372385000 0025 2 DAN5-6-12X PIN D53372385000 0026 4 DAN5-6-10X PIN D53372385000 0027 1 D5337219120300 FITTING D53372385000 0028 80 DAN5-6-6 PIN D53372385000 0029 12 DAN5-6-7 PIN D53372385000 0030

6 DAN5-6-11 PIN D53372385000 0031 6 DAN5-6-13 PIN D53372385000 0032 12 DAN5-6-9X PIN D53372385000 0033 14 DAN5-6-9 PIN D53372385000 0034 19 LN9198-4014CF RIVET D53372385000 0035

1 D5337219220100 FITTING D53372385000 0036 60 LN9198-4812CF RIVET D53372385000 0037 16 LN9198-4012CF RIVET D53372385000 0038

8 DAN7-6-6X PIN D53372385000 0039 210 NSA5076-6 COLLAR D53372385000 0040 196 DAN5-6-5 PIN D53372385000 0041

12 NAS1097AD3-5 RIVET D53372385000 0045

6 DAN11-8X COLLAR D53372385000 0046 1 D5347104120190 ANGLE D53372385000 0047 8 DAN12-6X COLLAR D53372385000 0048 14 DAN5-6-8 PIN D53372385000 0049 32 DAN5-6-8X PIN D53372385000 0050 42 NSA5075-5 COLLAR D53372385000 0051 83 DAN11-6X COLLAR D53372385000 0052

3 DAN5-8-9X PIN D53372385000 0053 26 DAN5-5-3 PIN D53372385000 0054

2 D5337218500000 STRUT D53372385000 0055 4 D5337218600000 STRUT D53372385000 0056 1 D5337215920500 ANGLE D53372385000 0057 2 DIN65399-3210CF RIVET D53372385000 0058 16 DAN5-5-5 PIN D53372385000 0059

3 DAN5-8-8X PIN D53372385000 0060 2 D5337142320000 FITTING D53372385000 0061 8 DAN5-6-6X PIN D53372385000 0062 128 NSA5075-6 COLLAR D53372385000 0063 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 42
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
2 DAN5-6-14 PIN D53372385000 0073 4 NSA5075-6 COLLAR D53372385000 0074 8 EN6081KE6 RIVET D53372385000 0075 4 DAN7-6-6 PIN D53372385000 0076 4 DAN7-6-11 PIN D53372385000 0077 8 DAN12-6 COLLAR D53372385000 0078

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D06R04 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 4 D5347449420600 FITTING D53476032000 0001 4 D5337217620000 SHEET D53476032000 0002 2 D5347035000600 XBEAM D53476032000 0003 7 D5347449520500 SECTION D53476032000 0004 1 D5347470020000 ANGLE D53476032000 0005 4 D5347449520300 SECTION D53476032000 0006 6 D5337217620800 FILLER D53476032000 0007 4 D5347448420200 STRAP D53476032000 0008 4 D5347448420300 STRAP D53476032000 0009 3 D5337217620100 SHEET D53476032000 0010 3 D5347449420700 FITTING D53476032000 0011 7 D5347470020300 ANGLE D53476032000 0012 3 D5347449520400 SECTION D53476032000 0013 2 D5347470020500 ANGLE D53476032000 0014 4 D5347658620000 BUSHING D53476032000 0015 3 D5347470020400 ANGLE D53476032000 0016 6 D5347470020200 ANGLE D53476032000 0017 1 D5347470020600 ANGLE D53476032000 0018 1 D5347470020800 ANGLE D53476032000 0019 1 D5347470021800 ANGLE D53476032000 0020 1 D5347470046600 ANGLE D53476032000 0021 1 D5347470047400 ANGLE D53476032000 0022 1 D5347470046800 ANGLE D53476032000 0023 1 D5347470047000 ANGLE D53476032000 0024 1 D5347470047200 ANGLE D53476032000 0025 1 D5347470047600 ANGLE D53476032000 0026 1 D5347470044400 ANGLE D53476032000 0027 1 D5337217622200 SHIM D53476032000 0028 2 D5347449522000 SECTION D53476032000 0029 2 D5347470520100 ANGLE D53476032000 0030 1 D5347470320000 WEB D53476032000 0031 1 D5347470021400 ANGLE D53476032000 0032 1 D5347470024800 ANGLE D53476032000 0033 1 D5347470023400 ANGLE D53476032000 0034 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 43
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
1 D5347653600000 XBEAM D53476032000 0035 2 D5347470520000 ANGLE D53476032000 0036 1 D5347470320200 WEB D53476032000 0037 1 D5347470027800 ANGLE D53476032000 0038 1 D5347470028000 ANGLE D53476032000 0039 1 D5347470028200 ANGLE D53476032000 0040 1 D5347470028400 ANGLE D53476032000 0041 2 D5347449520000 SECTION D53476032000 0042 1 D5347658220400 SHIM D53476032000 0043 1 D5347660020000 FITTING D53476032000 0044 1 D5347660120000 FITTING D53476032000 0045 1 D5347449421100 FITTING D53476032000 0046 1 D5347448420400 STRAP D53476032000 0047 1 D5347646000200 SECTION D53476032000 0048 1 D5347047500800 SECTION D53476032000 0049 1 D5347047701000 SECTION D53476032000 0050 2 D5347449523200 SECTION D53476032000 0051 1 D5347449523400 SECTION D53476032000 0052 1 D5347449523600 SECTION D53476032000 0053 1 D5347711620800 ANGLE D53476032000 0054 1 D5337601520600 SHIM D53476032000 0055 1 D5337601520800 SHIM D53476032000 0056 1 D5337601521000 SHIM D53476032000 0057 1 D5337601521200 SHIM D53476032000 0058 1 D5337601521400 SHIM D53476032000 0059 1 D5347101620400 CONNECTN D53476032000 0060 1 D5337217400000 PLATE D53476032000 0061 1 D5347449520800 SECTION D53476032000 0062 2 D5347471501800 PLATE D53476032000 0063 1 D5347471501600 PLATE D53476032000 0064 6 D5347470120200 ANGLE D53476032000 0065 5 D5347470120000 ANGLE D53476032000 0066 1 D5347046826800 ANGLE D53476032000 0067 1 D5347046824200 ANGLE D53476032000 0068 1 D5347046825400 ANGLE D53476032000 0069 1 D5347471500600 PLATE D53476032000 0070 1 D5347048900600 PLATE D53476032000 0071 1 D5347659600000 PLATE D53476032000 0072 1 D5347656700200 PLATE D53476032000 0073 1 D5347471502200 PLATE D53476032000 0074 1 D5347471502000 PLATE D53476032000 0075 1 D5347471501700 PLATE D53476032000 0076 1 D5347471501900 PLATE D53476032000 0077 4 D5347470120300 ANGLE D53476032000 0078 3 D5347470120100 ANGLE D53476032000 0079 1 D5347659100200 ANGLE D53476032000 0080 1 D5347100720600 COUPLING D53476032000 0081 1 D5337216020000 SECTION D53476032000 0082 1 D5337217320200 WEB D53476032000 0083 1 D5347471322000 PLATE D53476032000 0084 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 44
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
1 D5347471322400 PLATE D53476032000 0085 1 D5347471322600 PLATE D53476032000 0086 1 D5347646100000 SECTION D53476032000 0087 1 D5347047900400 SECTION D53476032000 0088 1 D5347046825600 ANGLE D53476032000 0089 1 D5347046825800 ANGLE D53476032000 0090 1 D5347656800200 PLATE D53476032000 0091 1 D5347046826000 ANGLE D53476032000 0092 1 D5347046826200 ANGLE D53476032000 0093 1 D5347049400200 PLATE D53476032000 0094 1 D5347046825900 ANGLE D53476032000 0095 1 D5347046825700 ANGLE D53476032000 0096 1 D5347046826600 ANGLE D53476032000 0097 1 D5347656800300 PLATE D53476032000 0098 1 D5347656900800 PLATE D53476032000 0099 1 D5347046826300 ANGLE D53476032000 0100 1 D5347046826100 ANGLE D53476032000 0101 1 D5347049400300 PLATE D53476032000 0102 2 D5347669200000 PLATE D53476032000 0103 1 D5347646320200 DOUBLER D53476032000 0104 2 D5347607520000 SHIM D53476032000 0105 2 D5347669000000 TUBE D53476032000 0106 2 D5347669100000 PLUG D53476032000 0107 4 D5347472120000 SHIM D53476032000 0108 1 D5347470920200 COVER D53476032000 0109 1 D5347646320000 DOUBLER D53476032000 0110 4 D5347470220000 SHIM D53476032000 0111 1 D5347449521800 SECTION D53476032000 0112 1 D5347026000800 XBEAM D53476032000 0113 1 D5337217400100 PLATE D53476032000 0114 1 D5347449520900 SECTION D53476032000 0115 1 D5347101620500 CONNECTN D53476032000 0116 2 MS16625-4212 RING D53476032000 0117 2 NAS1801-3-10 SCREW D53476032000 0118 10 NAS1153E7 SCREW D53476032000 0119

4 NAS1791A3-1 NUT D53476032000 0120 8 ABS0337-01A RECEPTCLD53476032000 0121 10 NAS1474A3 NUT D53476032000 0122 30 DAN5-6-5X PIN D53476032000 0123 21 DAN5-6-4X PIN D53476032000 0124 376 EN6081D6-08 RIVET D53476032000 0125

34 DAN5-6-7 PIN D53476032000 0126 120 DAN5-6-6 PIN D53476032000 0127 185 DAN5-6-5 PIN D53476032000 0128 116 DAN5-6-4 PIN D53476032000 0129 149 DAN5-6-3 PIN D53476032000 0130

52 DAN6-6-5 PIN D53476032000 0131

4 DAN6-6-4 PIN D53476032000 0132 32 DAN6-6-3 PIN D53476032000 0133 21 DAN5-8-5 PIN D53476032000 0134 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 45
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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

199 DAN11-6X COLLAR D53476032000 0135 807 NSA5075-6 COLLAR D53476032000 0136

37 NSA5075-8 COLLAR D53476032000 0137 16 EN6069KE6-11 RIVET D53476032000 0138 21 EN6069KE4-10 RIVET D53476032000 0139 46 DAN5-6-8X PIN D53476032000 0140 12 DAN6-6-7 PIN D53476032000 0141

5 DAN6-6-9X PIN D53476032000 0142 2 DAN6-6-9 PIN D53476032000 0143 4 DAN6-6-7X PIN D53476032000 0144 14 DAN5-8-6 PIN D53476032000 0145

2 DAN5-8-7 PIN D53476032000 0146 70 DAN5-6-8 PIN D53476032000 0147 10 DAN6-6-6 PIN D53476032000 0148 90 EN6101D4-04 RIVET D53476032000 0149 36 DAN5-5-4 PIN D53476032000 0150 39 NSA5075-5 COLLAR D53476032000 0151

7 DAN5-6-9 PIN D53476032000 0152 22 DAN5-6-9X PIN D53476032000 0153

4 EN6069AD4-05 RIVET D53476032000 0154 1 DAN5-8-8X PIN D53476032000 0155 34 DAN11-8X COLLAR D53476032000 0156

4 DAN5-8-9X PIN D53476032000 0157 10 DAN5-8-10X PIN D53476032000 0158

7 DAN5-8-11X PIN D53476032000 0159 8 EN6101D3-04 RIVET D53476032000 0160 5 DAN6-6-4X PIN D53476032000 0161 8 DAN6-6-5X PIN D53476032000 0162 4 DAN5-8-7X PIN D53476032000 0163 10 DAN5-6-12X PIN D53476032000 0164 36 DAN5-6-11X PIN D53476032000 0165

8 DAN5-8-12X PIN D53476032000 0166 20 DAN5-6-10 PIN D53476032000 0167

8 DAN5-6-8Y PIN D53476032000 0168 16 NSA5330-6 COLLAR D53476032000 0169

3 DAN5-5-5 PIN D53476032000 0170 8 DAN6-6-8Y PIN D53476032000 0171 224 LN9198-4014CF RIVET D53476032000 0172

23 DAN5-6-7X PIN D53476032000 0173 14 DAN5-6-6X PIN D53476032000 0174 37 EN6081D5-06 RIVET D53476032000 0175 258 EN6081D5-07 RIVET D53476032000 0176

16 LN9198-4012CF RIVET D53476032000 0177 266 LN9198-4016CF RIVET D53476032000 0178 162 EN6081D6-09 RIVET D53476032000 0179 4 EN6081D6-10 RIVET D53476032000 0180 6 EN6081D6-12 RIVET D53476032000 0181 146 EN6069KE6-07 RIVET D53476032000 0182

60 EN6069KE6-08 RIVET D53476032000 0183 50 EN6069KE6-09 RIVET D53476032000 0184 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 46
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
8 EN6069KE6-10 RIVET D53476032000 0185 24 DIN65399-2412CF RIVET D53476032000 0186 12 DIN65399-2414CF RIVET D53476032000 0187 46 EN6101D4-06 RIVET D53476032000 0188 20 DAN6-6-10 PIN D53476032000 0189 57 DAN6-6-8 PIN D53476032000 0190

4 EN6080D6-09 RIVET D53476032000 0257 20 LN9198-4018CF RIVET D53476032000 0258

1 D5347006621200 SHEET D53476032000 0259 1 D5347006621000 SHEET D53476032000 0260 1 D5347044926200 SHIM D53476032000 0261 1 D5347044926000 SHIM D53476032000 0262

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D07R00 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 281154D10R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2587385000200 BLANKET D25870003050 0000 1 D2587385105400 BLANKET D25870003050 0001 1 D2587385205200 BLANKET D25870003050 0002 1 D2587385305400 BLANKET D25870003050 0003 1 D2587385405200 BLANKET D25870003050 0004 1 D2587385505400 BLANKET D25870003050 0005 1 D2587385600200 BLANKET D25870003050 0006 1 D2587385705400 BLANKET D25870003050 0007 1 D2587385805200 BLANKET D25870003050 0008 1 D2587385905400 BLANKET D25870003050 0009 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 47
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
1 D2587386005600 BLANKET D25870003050 0010 1 D2587386105400 BLANKET D25870003050 0011 1 D2587386200200 BLANKET D25870003050 0012 1 D2587386300200 BLANKET D25870003050 0013 1 D2587386500200 BLANKET D25870003050 0014 1 D2587386700200 BLANKET D25870003050 0015 1 D2587386900200 BLANKET D25870003050 0016 80 F2587003400000 STRIP D25870003050 0100 Kit 281154D11R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 16 NAS1102-4-16 SCREW D25286364014 0002 16 NAS1149F0432P WASHER D25286364014 0004 16 NAS1169C416L WASHER D25286364014 0006 16 MS21042-4 NUT D25286364014 0008 16 NAS1102-08-16 SCREW D25286364014 0010 16 NAS1149FN816P WASHER D25286364014 0012 16 NAS1169C8L WASHER D25286364014 0014 16 MS21042-08 NUT D25286364014 0016

1 FACC79120418 CMPRTMNT D25286364014 0020 1 FACC79120419 CMPRTMNT D25286364014 0021 4 MS20392-3C23 PIN D25286364014 0030 2 MS20392-3C27 PIN D25286364014 0031 6 NAS1149F0463P WASHER D25286364014 0032 6 AA55487-5 PIN D25286364014 0033 4 MS20392-4C67 PIN D25286364014 0042 2 MS20392-4C45 PIN D25286364014 0043 4 NAS1149C0532R WASHER D25286364014 0046 6 DAN191-20 RING D25286364014 0047 2 NSA5528-045 CLAMP D25286364014 0065

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D12R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D2527719940600 PLACARD D25288767000 0206 2 D2527700844200 PLACARD D25288767000 0242 2 A2528131544600 PLACARD D25288767000 0246

Kit 281154D13R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 48
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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 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 LN29837A1 SECTION D25671746000 0070 4 NAS1096-3-7 SCREW D25671746000 0080 4 NAS1149D0363K WASHER D25671746000 0090 1 D9239310903000 PLCRDSETD25671746000 0100 75 LN9198-4012CF RIVET D25671746000 0100

2 MS20392-2C15 PIN D25671746000 0110 6 NAS1149C0332R WASHER D25671746000 0120 2 MS24665-1013 PIN D25671746000 0130 1 D2567074100600 PLACARD D25671746000 0140 1 60592-103 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 281154D14R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 49
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

12 D9239310906200 PLCRDSETD92894713084 0000 24 NSA935401-03 TIE D92894713084 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 281154D15R00 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 4 NAS1100-04-5 SCREW D92894736004 0051 4 NAS1149CN616R WASHER D92894736004 0150 3 NAS1149CN816R WASHER D92894736004 0152 2 NAS1149C0332R WASHER D92894736004 0153 4 MS21042-04 NUT D92894736004 0200 3 NSA5066-08-1 NUT D92894736004 0230 2 E0343-01 MOUNT D92894736004 0250 1 NSA935504-01 MOUNT D92894736004 0251 1 NSA935504-03 MOUNT D92894736004 0253 1 NSA935513-07 MOUNT D92894736004 0259 2 ABS0355-01 BRACKET D92894736004 0262 2 ABS0355-02 BRACKET D92894736004 0263 2 NSA935514-03 WASHER D92894736004 0264 4 NSA5527-03-03 SPACER D92894736004 0304 15 NSA935401-03 TIE D92894736004 0793 30 NSA935401-04 TIE D92894736004 0794 15 NSA935401-05 TIE D92894736004 0795 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D16R02 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 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 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 50
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
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 2 DIN65399-3210BF RIVET D53370297002 9002 32 LN9198-3216BF RIVET D53370297002 9004

1 L32A319-160-002 CONTROL D53370297003 0000 1 L32A319-165-001 ADAPTER D53370297003 0004 2 D5337025020100 ANGLE D53370297003 0007 2 D5337025620200 SECTION D53370297003 0008 1 D5337025620700 SECTION D53370297003 0011 1 D5337025920000 ANGLE D53370297003 0012 1 D5337645020100 BRIDGE D53370297003 0015 1 D5337645300300 BRACKET D53370297003 0017 1 D5337645420000 BRACKET D53370297003 0018 10 MS21919WCH6 CLAMP D53370297003 0030 0.06 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 2 DIN65399-3210BF RIVET D53370297003 0652 32 LN9198-3216BF RIVET D53370297003 0632

2 D5337025020000 ANGLE D53375751004 0006 2 D5337025620200 SECTION D53375751004 0008 1 D5337025620600 SECTION D53375751004 0010 1 D5337025920000 ANGLE D53375751004 0012 1 D5337645020000 BRIDGE D53375751004 0014 16 LN9198-3210BF RIVET D53375751004 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 281154D17R02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9299562500800 HARNESS D92894721006 0010 1 D9299562600600 HARNESS D92894721006 0020 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 51
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
1 D9299562700600 HARNESS D92894721006 0030 150 NSA935401-03 TIE D92894721006 0130 300 NSA935401-04 TIE D92894721006 0131 150 NSA935401-05 TIE D92894721006 0132 1 D9299957100400 EQUIPMNTD92894748008 0000 4 NAS1801-08-9 SCREW D92894748008 0005 2 NAS1801-08-12 SCREW D92894748008 0007 2 NAS1149CN816R WASHER D92894748008 0152 4 NSA935808C01 WASHER D92894748008 0171 4 D9249102520000 WASHER D92894748008 0190 2 ABS0355-01 BRACKET D92894748008 0262 4 ABS0355-02 BRACKET D92894748008 0263 4 NSA935514-03 WASHER D92894748008 0264 3 ABS0774A01A BRACKET D92894748008 0268 2 NSA5527-03-03 SPACER D92894748008 0304 4 NSA935807-09 CLAMP D92894748008 0377 3.2 TSTMNR502-0 CONDUIT D92894748008 0763 80 NSA935401-03 TIE D92894748008 0793 150 NSA935401-04 TIE D92894748008 0794

80 NSA935401-05 TIE D92894748008 0795

2 D9249107303000 CONNECTN D92894748008 0846 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D21R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D9357040100200 BRACKET D93070668000 0112 1 D9357040100300 BRACKET D93070668000 0113 4 NAS1919B04-02 RIVET D93070668000 0125

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D30R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557131000400 PANEL D25571077000 0000 1 D2557196200800 PANEL D25571077000 0002

Kit 281154D31R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 52
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 D2557132200800 PANEL D25571077002 0010 1 D2557132400000 PANEL D25571077002 0012 1 D2557196801000 PANEL D25571077002 0014 1 D2557132800800 PANEL D25571077002 0016

Kit 281154D32R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557133000200 PANEL D25571077004 0020 1 D2557197000200 PANEL D25571077004 0022

Kit 281154D33R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557123600400 PANEL D25571077006 0030 1 D2557123600500 PANEL D25571077006 0031 1 D2557123800200 PANEL D25571077006 0032 2 D2557017000200 COVER D25571077006 0040

Kit 281154D41R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827093320400 FLANGE D28271012000 0000 1 D2827093100200 TUBE D28271012000 0002 1 D2827093000200 TUBE D28271012000 0004 1 D2827093321400 SLEEVE D28271012000 0006 1 D2827093100000 TUBE D28271012000 0008 1 D2827093000000 TUBE D28271012000 0010 1 D2827093221200 SPACER D28271012000 0012 2 D2827093222200 FLANGE D28271012000 0014 1 D2827093322400 SLEEVE D28271012000 0016 2 D2827092700000 TUBE D28271012000 0018 2 D2827093222600 FLANGE D28271012000 0020 2 D2827093222800 FLANGE D28271012000 0028 1 D2827093320600 FLANGE D28271012000 0030 2 A2827090120400 SPACER D28271012000 0031 1 D2827092900600 TUBE D28271012000 0032 1 D2827093500000 BRACKET D28271012000 0033 1 D2827092800400 TUBE D28271012000 0034 1 D2827093500200 CLAMP D28271012000 0035 2 D2827093321200 SLEEVE D28271012000 0036 1 D2827093500400 CLAMP D28271012000 0037 2 D2827093320800 FLANGE D28271012000 0038 1 D2827093322200 SLEEVE D28271012000 0039 2 D2827093221600 FLANGE D28271012000 0040 2 D2827093321000 SLEEVE D28271012000 0042 1 D2827092800000 TUBE D28271012000 0044 1 D2827092900000 TUBE D28271012000 0046 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 53
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
1 D2827092900200 TUBE D28271012000 0048 1 D2827092900400 TUBE D28271012000 0050 1 D2827094800000 BRACKET D28271012000 0051 1 D2827092800200 TUBE D28271012000 0052 4 NSA8203-151 ORING D28271012000 0053 9 NSA8203-152 ORING D28271012000 0054 1 NSA8203-154 ORING D28271012000 0055 1 NSA8203-156 ORING D28271012000 0056 3 NSA8203-222 ORING D28271012000 0057 9 NSA8203-226 ORING D28271012000 0058 3 NSA8203-230 ORING D28271012000 0059 10 NSA8203-234 ORING D28271012000 0060

4 NSA5519-25 CLAMP D28271012000 0061 4 NSA5519-30 CLAMP D28271012000 0062 2 ABS0107-150 NUT D28271012000 0064 3 NSA840003-150 RING D28271012000 0065 7 ABS0107-200 NUT D28271012000 0066 7 NSA840003-200 RING D28271012000 0067 2 AN814-4DL PLXBLDR D28271012000 0071 2 NSA8200-4 PACKING D28271012000 0072 3 A2827090220200 SPRING D28271012000 0074 6 A2827051720200 SPRING D28271012000 0075 63 NAS1149C0432R WASHER D28271012000 0082 52 NAS1149C0332R WASHER D28271012000 0083 29 NAS1291C3M NUT D28271012000 0084 58 NAS1726-4E NUT D28271012000 0085

8 NAS1304-4 BOLT D28271012000 0086 7 NAS1304-5 BOLT D28271012000 0087 1 NAS1304-6 BOLT D28271012000 0088 6 NAS1304-8 BOLT D28271012000 0089 4 NAS1304-9 BOLT D28271012000 0090 11 NAS1304-10 BOLT D28271012000 0091

9 NAS1304-11 BOLT D28271012000 0092 4 NAS1304-12 BOLT D28271012000 0093 8 NAS1304-14 BOLT D28271012000 0094 2 NAS1303-2 BOLT D28271012000 0095 21 NAS1303-3 BOLT D28271012000 0096

8 NAS1304-2 BOLT D28271012000 0098 4 NAS1304-3 BOLT D28271012000 0100 4 E0089-10-125NN LEAD D28271012000 0102 1 E0089-10-160NN LEAD D28271012000 0103 2 E0089-10-200NN LEAD D28271012000 0104 4 E0089-41-100NN LEAD D28271012000 0105 2 E0089-41-200NN LEAD D28271012000 0106 2 E0089-41-250NN LEAD D28271012000 0107 3 E0088-10-125 LEAD D28271012000 0108 2 E0088-10-200 LEAD D28271012000 0109 0.345 NSA937210MB0300 TUBING D28271012000 0110

0.38 NSA937210MB0300 TUBING D28271012000 0111 2 E0089-10-250NN LEAD D28271012000 0112 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 54
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D42R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 MS21902D8 UNION D28271013000 0000 2 NSA8200-8 PACKING D28271013000 0001 1 MS21907D8 ELBOW D28271013000 0002 2 AN924-8D NUT D28271013000 0003 2 NAS1149D1290K WASHER D28271013000 0004 2 MS21905D8 TEE D28271013000 0005 1 NSA5527-03-16 SPACER D28271013000 0006 27 NAS1149C0332R WASHER D28271013000 0007

1 NAS1096-3-15 SCREW D28271013000 0008 20 NAS1096-3-8 SCREW D28271013000 0009 10 NAS1726-3E NUT D28271013000 0010

3 NAS1096-3-7 SCREW D28271013000 0011 2 NAS1096-3-10 SCREW D28271013000 0012 1 MS21912D8 TEE D28271013000 0013 8 MS21919WDE8 CLAMP D28271013000 0014 6 MS21919WDE11 CLAMP D28271013000 0015 1 MS21919WDE48 CLAMP D28271013000 0016 1 MS21916D8-6 REDUCER D28271013000 0017 3 NAS1149C0432R WASHER D28271013000 0018 3 NAS1304-4 BOLT D28271013000 0019 1 NSA8200-6 PACKING D28271013000 0022 2 NAS1149D1216H WASHER D28271013000 0023 3 NAS1096-3-9 SCREW D28271013000 0024 7 E0090-10-125NN LEAD D28271013000 0025 1 NAS1149D0316H WASHER D28271013000 0026 1 NAS1303-2 BOLT D28271013000 0027 1 NSA5575-7 CLAMP D28271013000 0028 4 NAS1304-2 BOLT D28271013000 0030 4 NAS1726-4E NUT D28271013000 0032 1 NAS1763D080808 TEE D28271013000 0033 11 NSA5519-11 CLAMP D28271013000 0035 11 NAS1291C3M NUT D28271013000 0036

1 E0091-10-250NN STRAP D28271013000 0037 2 E0091-10-280NN LEAD D28271013000 0038 1 D56KAN002 HOSE D28271013000 0039 2 ASNA0033-016 CLAMP D28271013000 0040 1 E0090-10-100NN LEAD D28271013000 0041 1 D2827093603400 TUBE D28271013000 0100 1 D2827093600200 TUBE D28271013000 0102 1 D2827093603200 TUBE D28271013000 0108 1 D2827093601600 TUBE D28271013000 0116 1 D2827093602000 TUBE D28271013000 0120 1 D2827093602400 TUBE D28271013000 0124 1 D2827093604000 TUBE D28271013000 0126 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 55
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
1 D2827093603000 TUBE D28271013000 0130 1 D2827097600200 TUBE D28271013000 0134 1 D2827093603600 TUBE D28271013000 0136 1 D2827097600400 TUBE D28271013000 0138 1 51263408-0840 HOSE D28271013000 0202 1 D2827094320000 FITTING D28271013000 0204 1 L83A13-617 MONITOR D28271013000 0206 1 513535E0107-090 HOSE D28271013000 0208 1 D2827094720000 BRACKET D28271013000 0210 1 D2827094421400 PLACARD D28271013000 0214 1 D2827098322800 BRACKET D28271013000 0216

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D43R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 5 MS21919WDE8 CLAMP D28271014000 0014 14 NAS1096-3-8 SCREW D28271014000 0016 15 NAS1149C0332R WASHER D28271014000 0017

2 MS21905D8 TEE D28271014000 0021 1 NSA855120-8D ELBOW D28271014000 0022 1 NAS1762D0808 ELBOW D28271014000 0023 1 MS21916D8-6 REDUCER D28271014000 0025 1 NSA8200-6 PACKING D28271014000 0026 3 NAS1149C0432R WASHER D28271014000 0027 3 NAS1304-4 BOLT D28271014000 0028 2 MS21914-8D CAP D28271014000 0033 1 AN924-8D NUT D28271014000 0034 1 NAS1149D1290K WASHER D28271014000 0035 1 MS21912D8 TEE D28271014000 0036 1 NAS1149D1216H WASHER D28271014000 0037 10 NAS1291C3M NUT D28271014000 0049

9 NSA5519-11 CLAMP D28271014000 0051 2 ASNA0033-016 CLAMP D28271014000 0056 1 D56KAN002 HOSE D28271014000 0057 1 E0090-10-125NN LEAD D28271014000 0060 5 E0090-10-160NN LEAD D28271014000 0061 1 D2827097700200 TUBE D28271014000 0122 1 D2827097700400 TUBE D28271014000 0124 1 D2827093701800 TUBE D28271014000 0130 1 D2827097701000 TUBE D28271014000 0132 1 D2827097701200 TUBE D28271014000 0134 1 L83A13-617 MONITOR D28271014000 0202 1 513535E0107-090 HOSE D28271014000 0204 1 D2827094421600 PLACARD D28271014000 0216 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 56
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D44R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827098001800 TUBE D28271015000 0002 1 D2827098002000 TUBE D28271015000 0004 1 D2827098002200 TUBE D28271015000 0005 1 D2827098002800 TUBE D28271015000 0007 1 D2827097903200 TUBE D28271015000 0008 1 D2827097903495 TUBE D28271015000 0009 1 D2827097903800 TUBE D28271015000 0010 1 D2827097903000 TUBE D28271015000 0012 1 D2827097903600 TUBE D28271015000 0014 1 D2827097901800 TUBE D28271015000 0019 1 D2827097902000 TUBE D28271015000 0021 1 D2827097902400 TUBE D28271015000 0025 1 A2163302000000 FILTER D28271015000 0027 1 A2151034520000 INLET D28271015000 0028 1 MS21902D10 UNION D28271015000 0030 2 NAS1612-10 PACKING D28271015000 0031 1 83694912 HOSE D28271015000 0040 (01) 2 A2827092300000 COUPLING D28271015000 0050 30 NAS1726C3E NUT D28271015000 0070 20 NAS1096-3-8 SCREW D28271015000 0071 30 NAS1149C0332R WASHER D28271015000 0073

2 AN924-10J NUT D28271015000 0074 2 MS21909J10 TEE D28271015000 0075 2 NAS1149F1432P WASHER D28271015000 0076 2 TSTMNR503-0 CONDUIT D28271015000 0077 4 NSA935401-03 TIE D28271015000 0078 12 MS21919WDE10 CLAMP D28271015000 0079 13 MS21919WDE4 CLAMP D28271015000 0080 10 NSA5575-8A CLAMP D28271015000 0081

4 NSA5575-2 CLAMP D28271015000 0082 8 E0090-10-125NN LEAD D28271015000 0083 4 E0090-18-100NN LEAD D28271015000 0084 4 NAS1096-1-8 SCREW D28271015000 0085 4 NAS1149DN616H WASHER D28271015000 0086 4 MS21042-06 NUT D28271015000 0087 10 NAS1303-2 BOLT D28271015000 0088 10 NAS1726-3E NUT D28271015000 0089 10 NAS1149D0316H WASHER D28271015000 0090

1 MS21908J10 ELBOW D28271015000 0091 1 AN924-4D NUT D28271015000 0092 4 NAS1726C4E NUT D28271015000 0093 2 MS21914-10D CAP D28271015000 0094 1 AN924-10J NUT D28271015000 0095 1 NAS1149C1432R WASHER D28271015000 0096 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 57
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
9 NAS1096-3-9 SCREW D28271015000 0097 2 NAS1096-3-12 SCREW D28271015000 0098 1 MS21905J10 TEE D28271015000 0099 1 MS21919WCH15 CLAMP D28271015000 0101 1 E0090-10-160NN LEAD D28271015000 0102 1 D2827094420000 PLACARD D28271015000 0200 1 D2827094420200 PLACARD D28271015000 0202 1 D2827094420400 PLACARD D28271015000 0204 1 D2827094420600 PLACARD D28271015000 0206 1 D2827094420800 PLACARD D28271015000 0208 1 D2827094421000 PLACARD D28271015000 0210 1 D2827094421200 PLACARD D28271015000 0212 1 D2827097903495 TUBE D28271015000 9001

NOTE(01) Part number supplied, 1451515F0150-180. NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D45R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 6 NAS1096-3-8 SCREW D28271016002 0004 6 NAS1149C0332R WASHER D28271016002 0005 6 NAS1726C3E NUT D28271016002 0006 10 LN9198-3210BF RIVET D28271016002 0032 65 LN9198-4010BF RIVET D28271016002 0040

8 DAN7-6-8Y PIN D28271016002 0041 8 DAN12-6Y COLLAR D28271016002 0042 3 F5397461900600 BRACKET D28271016002 0100 2 D2827094222800 ANGLE D28271016002 0102 1 D2827098300000 BRACKET D28271016002 0104 1 D2827098300200 BRACKET D28271016002 0106 4 D2827094221400 ANGLE D28271016002 0112 1 D2827094220400 ANGLE D28271016002 0113 1 D2827094221800 ANGLE D28271016002 0115 2 D2827094222200 ANGLE D28271016002 0116 1 D2827094225000 ANGLE D28271016002 0117 2 D2827098321000 BRACKET D28271016002 0118 1 D2827098321200 ANGLE D28271016002 0119 2 D2827098321400 ANGLE D28271016002 0120 2 D2827098326600 ANGLE D28271016002 0121 2 D2827094200400 BRACKET D28271016002 0124 1 D2827098325200 BRACKET D28271016002 0125 3 D2827098323200 BRACKET D28271016002 0127 1 D2827098323000 BRACKET D28271016002 0128 1 D2827098323800 BRACKET D28271016002 0130 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 58
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
1 D2827093521000 BRACKET D28271016002 0131 1 D2827098324200 BRACKET D28271016002 0132 1 D2827098324400 BRACKET D28271016002 0133 1 D2827098324000 BRACKET D28271016002 0134 1 D2827098325400 BRACKET D28271016002 0154 1 D2827098301200 BRACKET D28271016002 0157 1 D2827098326000 BRACKET D28271016002 0158 2 D2827098327200 BRACKET D28271016002 0159 1 D2827098326200 BRACKET D28271016002 0160

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D46R00 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 281154D47R00 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 281154D48R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2827050501600 TUBE D28270515000 0002 1 NSA855113-11C TEE D28270515000 0021 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 59
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
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 281154D50R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2917090100400 TUBE D93470502000 0011 1 D3247091100600 TUBE D93470502000 0026 1 D3247090101000 TUBE D93470502000 0029 2 A9348225520000 BLOCK D93470502000 0046 2 NSA5516A06NJ CLAMP D93470502000 0049 1 ASNA3752D120812 UNION D93470502000 0050 2 NSA855006-6 UNION D93470502000 0053 2 NSA855006D4 UNION D93470502000 0070 2 NSA855006-8 UNION D93470502000 0071 4 NAS1801-3-7 SCREW D93470502000 0080 19 NSA5066-3-1 NUT D93470502000 0090

2 NSA935401-05 TIE D93470502000 0098 0.066 DAN107-2 CORD D93470502000 0102 1 D9357072520300 BRACKET D93470502000 0108 1 D2917091100200 TUBE D93470502000 0110 1 D2777050600000 TUBE D93470502000 0112 1 D2707023100000 TUBE D93470502000 0117 1 D2777050100000 TUBE D93470502000 0118 1 D2917091100000 TUBE D93470502000 0124 1 D3247091600000 TUBE D93470502000 0125 1 D3247091600200 TUBE D93470502000 0127 1 D3247090600000 TUBE D93470502000 0128 1 D3247090600400 TUBE D93470502000 0130 1 D3247090600600 TUBE D93470502000 0131 1 NSA5516A06NJ CLAMP D93470502000 0149 1 NSA5516A14NJ CLAMP D93470502000 0151 1 D9357045500000 BRACKET D93470502000 0152 1 NSA855006D8 UNION D93470502000 0154 1 D9357070820000 BRACKET D93470502000 0155 2 NSA855020-8 ELBOW D93470502000 0175 2 NAS679C06M NUT D93470502000 0191 3 NAS1149D0363K WASHER D93470502000 0194 6 LN9198-3210BF RIVET D93470502000 0199

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

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 60
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Kit 281154D61R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 A9249175120000 ANGLE D53371072000 0001 1 D5337312600000 PLATE D53371072000 0002 1 D5337312000000 PLATE D53371072000 0003 4 D5337312420000 STRAP D53371072000 0004 8 NAS6703U7 BOLT D53371072000 0005 8 NAS6703U5 BOLT D53371072000 0006 16 NAS1726C3P NUT D53371072000 0007 16 NAS1149C0332R WASHER D53371072000 0008

1 D5337107420200 PLATE D53371072000 0009 1 D5337311520200 WALL D53371072000 0010 1 D5337311920200 PLATE D53371072000 0011 2 D5337309820000 SHEET D53371072000 0012 2 D5337307220100 STIFFENR D53371072000 0013 1 D5337307220000 STIFFENR D53371072000 0014 1 D5337312120400 SECTION D53371072000 0015 1 D5337312120600 SECTION D53371072000 0016 1 D5337312120700 SECTION D53371072000 0017 1 D5337312120200 SECTION D53371072000 0018 1 D5337313420000 SECTION D53371072000 0019 3 DAN7-5A5 PIN D53371072000 0020 2 DAN6-6-4 PIN D53371072000 0021 4 DAN5-6-4 PIN D53371072000 0022 20 DAN5-6-6 PIN D53371072000 0023

4 DAN5-6-7 PIN D53371072000 0024 6 NSA5075-6 COLLAR D53371072000 0025 3 ABS0258-5C COLLAR D53371072000 0026 24 NSA5076-6 COLLAR D53371072000 0027 12 LN9198-3208BF RIVET D53371072000 0028 196 LN9198-4812CF RIVET D53371072000 0029 8 LN9198-4814CF RIVET D53371072000 0030 15 LN9198-4009CF RIVET D53371072000 0031

3 LN9198-4010CF RIVET D53371072000 0032 11 LN9198-4011CF RIVET D53371072000 0033

8 LN9198-4012CF RIVET D53371072000 0034 17 DAN5-5-6 PIN D53371072000 0035 24 NSA5075-5 COLLAR D53371072000 0036 10 DAN5-5-7 PIN D53371072000 0037

6 NSA5076-5 COLLAR D53371072000 0038 3 DAN5-5-5 PIN D53371072000 0039 12 ASNA0082A302 BOLT D53371072000 0040

2 ASNA0082A303 BOLT D53371072000 0041 4 ASNA0082A304 BOLT D53371072000 0042 15 ASNA0082A305 BOLT D53371072000 0043

1 ASNA0082A306 BOLT D53371072000 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. DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 61
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Kit 281154D62R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

20 DAN7-6-8X PIN D53371236000 0001 32 DAN7-8-8X PIN D53371236000 0002 12 DAN7-8-10X PIN D53371236000 0003

1 DAN8-8-8X PIN D53371236000 0004 20 DAN12-6X COLLAR D53371236000 0005 45 DAN12-8X COLLAR D53371236000 0006

3 DAN5-6-6X PIN D53371236000 0007 3 DAN11-6X COLLAR D53371236000 0008

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D63R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

20 DAN7-6-8X PIN D53371236001 0001 32 DAN7-8-8X PIN D53371236001 0002 12 DAN7-8-10X PIN D53371236001 0003

1 DAN8-8-8X PIN D53371236001 0004 20 DAN12-6X COLLAR D53371236001 0005 45 DAN12-8X COLLAR D53371236001 0006

3 DAN5-6-6X PIN D53371236001 0007 3 DAN11-6X COLLAR D53371236001 0008

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D71R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367161701800 PANEL D53675024000 0026 1 D5367162400400 PANEL D53675024000 0028 1 D5367150500600 PANEL D53675024000 0042 2 D5367162301200 PANEL D53675024000 0126 1.5 ABS5006-2G TAPE D53675024000 0375 0.9 ABS5006-4G TAPE D53675024000 0376 82 ABS0376-3-25 SCREW D53675024000 0400 82 ABS0365-3-1B NUT D53675024000 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. DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 62
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Kit 281154D72R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 29.5 DAN107-1 CORD D53675023000 0385

22 ABS5093AT25 TAPE D53675023000 0387 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D73R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367520800400 PANEL D53675516002 0024 1 D5367520801800 PANEL D53675516002 0056 1 D5367520801400 PANEL D53675516002 0058 1 D5367520805000 PANEL D53675516002 0060 1 D5367520805200 PANEL D53675516002 0062 1 D5367520805400 PANEL D53675516002 0064 1 D5397484220000 PLATE D53675516002 0110 1 D5397484220100 PLATE D53675516002 0111 1 D5397489520100 SPACER D53675516002 0125 1 D5397489520000 SPACER D53675516002 0126 1 D5397489520400 SPACER D53675516002 0127 1 D5397489520200 SPACER D53675516002 0128 1 D5367520800600 PANEL D53675516002 0136 38 ABS0376-3-30 SCREW D53675516002 0402 107 ABS0376-3-40 SCREW D53675516002 0404

12 NAS1102-3-8 SCREW D53675516002 0408 42 EN6131-3C1 NUT D53675516002 0410 20 NAS1291C4M NUT D53675516002 0413 17 NSA5030-4-16 SCREW D53675516002 0416

1 NSA5030-4-23 SCREW D53675516002 0417 1 NSA5030-4-27 SCREW D53675516002 0418 1 NSA5030-4-34 SCREW D53675516002 0419 4 NSA5031-3-4 BOLT D53675516002 0420 4 NAS1149C0332R WASHER D53675516002 0421 2 NSA5030-3-16 SCREW D53675516002 0422 3.65 ABS5006-4C TAPE D53675516002 0430

20 NAS1149C0432R WASHER D53675516002 0432 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D74R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 63
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2.91 ABS0305LC SECTION D53672231058 0001 6.96 ABS0305LB SECTION D53672231058 0002

17 DAN107-1 CORD D53672231058 0005 6.96 ABS0398A01 SECTION D53672231108 0003 2.36 ABS0399A SECTION D53672231108 0004 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D75R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5367406200000 PANEL D53675526002 0022 1 D5367405500000 PANEL D53675526002 0024 1 D5367405400000 PANEL D53675526002 0026 1 D5367414100000 PANEL D53675526002 0028 1 D5367414200000 PANEL D53675526002 0030 1 D5367414300000 PANEL D53675526002 0032 148 ABS0376-3-30 SCREW D53675526002 0402 198 EN6131-3C1 NUT D53675526002 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 281154D76R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D5397483921800 PLATE D53975027000 0000 1 D5397497600000 PLATE D53975027000 0002 1 D5397468200000 SECTION D53975027000 0010 1 D5397468200100 SECTION D53975027000 0011 1 D5397469000000 BRACKET D53975027000 0016 1 D5397469000100 BRACKET D53975027000 0017 1 D5397469200000 BRACKET D53975027000 0018 1 D5397469200100 BRACKET D53975027000 0019 1 D5397469300000 BRACKET D53975027000 0020 1 D5397469300100 BRACKET D53975027000 0021 44 NSA5031-3-4 BOLT D53975027000 0025 44 NAS1149D0332K WASHER D53975027000 0026 22 D5397469700000 SUPPORT D53975027000 0028

1 D5347047400200 SECTION D53975027000 0030 1 D5347047400300 SECTION D53975027000 0031 1 D5397467800800 SECTION D53975027000 0040 1 D5397467800900 SECTION D53975027000 0041 1 D5397492600000 SECTION D53975027000 0042 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 64
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
1 D5397468800200 SECTION D53975027000 0044 1 D5397468800300 SECTION D53975027000 0045 1 D5397468000400 SECTION D53975027000 0046 1 D5397468000500 SECTION D53975027000 0047 1 D5397492500000 SECTION D53975027000 0048 1 D5397492500200 SECTION D53975027000 0050 1 D5397467400400 SECTION D53975027000 0052 1 D5397467400500 SECTION D53975027000 0053 3 D5397492700000 PLATE D53975027000 0100 2 D5397479500800 PLATE D53975027000 0110 9 NAS1102E3-7 SCREW D53975027000 0400 9 DAN125-4 WASHER D53975027000 0402 69 EN6069AD4-10 RIVET D53975027000 0532 69 EN6081D6-10 RIVET D53975027000 0648 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D77R02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

40 NAS1801-08-8 SCREW D92891825000 0001 106 NAS1801-08-18 SCREW D92891825000 0002 8 NAS1801-08-28 SCREW D92891825000 0003 74 NAS1801-3-8 SCREW D92891825000 0004 163 NSA5066-08-2 NUT D92891825000 0005 1 ABS0355-03 BRACKET D92891825000 0006 85 MS21042L3 NUT D92891825000 0007

4 MS21042L04 NUT D92891825000 0008 168 NAS1149DN816K WASHER D92891825000 0009

25 NAS1149D0332K WASHER D92891825000 0010

4 NAS1149DN416K WASHER D92891825000 0011 5 NSA935510-02 BOBBIN D92891825000 0012 12 MS21919WCH5 CLAMP D92891825000 0013

6 NSA5527-03-02 SPACER D92891825000 0016 2 NSA935807C16 CLAMP D92891825000 0017 2 ABS0731A01 SUPPORT D92891825000 0018 60 NAS1149C0332R WASHER D92891825000 0019 172 NSA5527-03-01 SPACER D92891825000 0020 7 NSA934710T11 FITTING D92891825000 0021 7 NSA934710T14 FITTING D92891825000 0022 1 NSA5527-03-05 SPACER D92891825000 0023 8 NAS1102-3-9 SCREW D92891825000 0024 4 NAS1100-04-8 SCREW D92891825000 0025 10 NSA935513-01 MOUNT D92891825000 0027 136 NSA935504-01 MOUNT D92891825000 0031 3 NSA935513-07 MOUNT D92891825000 0034 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 65
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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

26 NSA5527-03-03 SPACER D92891825000 0035 250 NSA935401-04 TIE D92891825000 0036 6 MS21042L08 NUT D92891825000 0037 2 D9249173320000 FRLDHALF D92891825000 0040 2 D9249173320200 FRLDHALF D92891825000 0041 1 D9249181406400 GUIDE D92891825000 0042 1 D9249181406600 GUIDE D92891825000 0043 10 NSA5527-03-04 SPACER D92891825000 0052 12 NAS1801-08-10 SCREW D92891825000 0053

1 NAS1801-08-43 SCREW D92891825000 0055 2 NSA5527-03-08 SPACER D92891825000 0056 1 NAS1801-08-25 SCREW D92891825000 0058 19 NAS1801-3-10 SCREW D92891825000 0059 50 NAS1149D0363K WASHER D92891825000 0060

7 E0343-01 MOUNT D92891825000 0063 1 NSA939510BN STRIP D92891825000 0080 21 D9249102520000 WASHER D92891825000 0190

1 D9289182520000 PLACARD D92891825000 0200 1 D9289182520200 PLACARD D92891825000 0202 1 EN6049-005-15-5 SLEEVE D92891825000 1035 26 NAS1801-08-7 SCREW D92891825002 0004 19 NAS1801-08-9 SCREW D92891825002 0005

2 NAS1801-08-12 SCREW D92891825002 0007 3 NAS1801-08-19 SCREW D92891825002 0012 1 NAS1801-08-36 SCREW D92891825002 0020 2 NAS1801-3-3 SCREW D92891825002 0029 69 NAS1801-3-9 SCREW D92891825002 0030 24 NAS1100-04-4 SCREW D92891825002 0050 12 NAS1102-08-8 SCREW D92891825002 0058 24 NAS1149CN416R WASHER D92891825002 0150 50 NAS1149CN816R WASHER D92891825002 0152 77 NAS1149C0332R WASHER D92891825002 0153

2 NAS1149D0332K WASHER D92891825002 0157 4 ASNA0113-40ADL WASHER D92891825002 0163 10 NSA935808C01 WASHER D92891825002 0171

2 D9249102520000 WASHER D92891825002 0190 24 MS21042-04 NUT D92891825002 0200

2 MS21042-08 NUT D92891825002 0202 5 MS21042-3 NUT D92891825002 0203 34 NAS1291C3M NUT D92891825002 0218

1 NSA5110-08-1 NUT D92891825002 0225 7 NSA5066-08-1 NUT D92891825002 0230 19 NSA5067-08-1 NUT D92891825002 0236

9 E0343-01 MOUNT D92891825002 0250 4 NSA935504-01 MOUNT D92891825002 0251 2 NSA935504-02 MOUNT D92891825002 0252 2 E0343-01 MOUNT D92891825002 0257 1 NSA935513-07 MOUNT D92891825002 0259 11 ABS0355-01 BRACKET D92891825002 0262 13 ABS0355-02 BRACKET D92891825002 0263 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 66
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
13 NSA935514-03 WASHER D92891825002 0264

1 E0660-01 MOUNT D92891825002 0266 6 ABS0774A01A BRACKET D92891825002 0268 2 NSA5527-03-03 SPACER D92891825002 0304 4 NSA5527-03-04 SPACER D92891825002 0306 1 NSA5527-03-06 SPACER D92891825002 0310 2 NSA5527-03-08 SPACER D92891825002 0314 10 NSA935807-09 CLAMP D92891825002 0377

2 D9249104800000 SHEET D92891825002 0727 1 D9249104800400 SHEET D92891825002 0729 3.2 TSTMNR502-0 CONDUIT D92891825002 0763

2 NSA935510-03 BOBBIN D92891825002 0782 81 NSA935401-03 TIE D92891825002 0793 150 NSA935401-04 TIE D92891825002 0794

80 NSA935401-05 TIE D92891825002 0795

1 D9249107100600 STRAP D92891825002 0834 2 D9249107303000 CONNECTN D92891825002 0846 1 D9289182520000 PLACARD D92891825002 0850 8 DAN328H25 TAPE D92891825002 0877 2 EN2997KE3C12 CAP D92891825002 0930 1 EN2997KE3C16 CAP D92891825002 0932 2 EN2997KE512 CONNECTR D92891825002 0933 1 EN2997KE516 CONNECTR D92891825002 0935 4 EN6049-006-13-5 SLEEVE D92891825002 1033 3 D2557016200200 COVER D92891825002 1099 2 D9249104900600 BRACKET D92891825002 1110 9 NAS1801-08-10 SCREW D92891825004 0006 7 NAS1801-08-19 SCREW D92891825004 0012 1 NAS1801-08-25 SCREW D92891825004 0016 1 NAS1801-3-3 SCREW D92891825004 0025 3 NAS1801-3-8 SCREW D92891825004 0028 14 NAS1149CN816R WASHER D92891825004 0152

4 NAS1149C0332R WASHER D92891825004 0153 13 NSA935808C01 WASHER D92891825004 0171

2 MS21042-08 NUT D92891825004 0202 4 MS21042L3 NUT D92891825004 0210 14 NSA5066-08-1 NUT D92891825004 0231

3 NSA5527-03-02 SPACER D92891825004 0302 14 NSA5527-03-04 SPACER D92891825004 0306

6 NSA5527-03-06 SPACER D92891825004 0310 3 MS21919WCH4 CLAMP D92891825004 0350 5 MS21919WCH2 CLAMP D92891825004 0364 8 NSA935807-06 CLAMP D92891825004 0376 8 NSA935807-09 CLAMP D92891825004 0377 40 NSA935401-03 TIE D92891825004 0793 40 NSA935401-04 TIE D92891825004 0794

1 D9289182520000 PLACARD D92891825004 0850

NOTE : Refer to the AIRBUS 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 : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 67
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D78R02 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

44 A9249635720200 BRACKET D92492872000 0001 51 D9249179320000 BRACKET D92492872000 0002

6 D9249178000600 BRACKET D92492872000 0007 3 D9249177520000 ANGLE D92492872000 0012 4 D9249172321200 BRACKET D92492872000 0016 1 D9249184620400 BRACKET D92492872000 0021 1 D9249177100000 BRACKET D92492872000 0023 1 D9249180922600 BRACKET D92492872000 0026 1 MS21060L3 NUT D92492872000 0027 1 D9249178001200 BRACKET D92492872000 0030 2 EN6101AD4-10 RIVET D92492872000 0621 286 LN9198-3214BF RIVET D92492872000 0632

12 EN6081D6-12 RIVET D92492872000 0648

2 EN6101AD3-14 RIVET D92492872000 0724 2 NSA5066-08-1 NUT D92492872002 0230 2 A9249187820200 SHEET D92492872002 0565 1 D9249103700200 PLATE D92492872002 0629 3 D9249104920400 BRACKET D92492872002 0737 2 D9249104922600 BRACKET D92492872002 1131 2 D9249104922700 BRACKET D92492872002 1132 2 D9249104922800 BRACKET D92492872002 1133 2 D9249104922900 BRACKET D92492872002 1134 35 LN9198-3210BF RIVET D92492872002 9005 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D79R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 8 NAS1801-3-8 SCREW D92492871000 0001 7 NAS1149D0332K WASHER D92492871000 0002 6 MS21042L3 NUT D92492871000 0003 1 NAS1801-08-18 SCREW D92492871000 0007 36 NAS1801-08-8 SCREW D92492871000 0008 36 NAS1149DN816K WASHER D92492871000 0009

8 MS21042L08 NUT D92492871000 0010 1 E0343-01 MOUNT D92492871000 0015 1 NSA5527-03-06D SPACER D92492871000 0017 2 D9249177820200 BRACKET D92492871000 0030 1 D9249177124200 BRACKET D92492871000 0032 1 D9249180800200 BRACKET D92492871000 0033 1 D9249180800400 BRACKET D92492871000 0034 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 68
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
1 D9249180900000 BRACKET D92492871000 0035 1 D9249180922400 BRACKET D92492871000 0036 7 NAS1801-08-12 SCREW D92492871002 0007 1 NAS1801-08-14 SCREW D92492871002 0009 10 ASNA0113-40ADL WASHER D92492871002 0163

2 D9249102520000 WASHER D92492871002 0190 4 MS21042-08 NUT D92492871002 0202 4 E0660-01 MOUNT D92492871002 0266 1 NSA5527-03-04 SPACER D92492871002 0306 1 NSA5527-03-07 SPACER D92492871002 0312 2 D9249104720000 GUIDE D92492871002 0724 1 D9249102620600 DEFLECTRD92492871002 0730 1 D9249107302800 STRAP D92492871002 0824 2 NAS1801-08-7 SCREW D92492871004 0004 2 NAS1149CN832R WASHER D92492871004 0158 2 MS21042-08 NUT D92492871004 0202 1 D9249171020200 SECTION D92492871004 0501

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 281154D80R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP

288 NAS1102-3-10 SCREW D25572207000 0007 306 NAS1726-3E NUT D25572207000 0008

42 NAS1100-3-12 SCREW D25572207000 0035 14 NAS1100-3-14 SCREW D25572207000 0036 36 MS21250-03008 BOLT D25572207000 0038 20 NAS1102-3-9 SCREW D25572207000 0039 16 NAS1096-3-8 SCREW D25572207000 0040 36 MS21250-03010 BOLT D25572207000 0041 36 MS21250-03012 BOLT D25572207000 0042

1 D2557221401800 TRACK D25572207000 0043 1 D2557221402000 TRACK D25572207000 0044 1 D2557221402200 TRACK D25572207000 0045 36 MS21250-03014 BOLT D25572207000 0046

1 D2557268028600 PLATE D25572207000 0049 1 D2557268121000 DOUBLER D25572207000 0050 12 D2557268030600 SHIM D25572207000 0051

6 D2557226520400 SUPPORT D25572207000 0052 6 D2557226120200 BLOCK D25572207000 0053 6 NSA5042C05-180 BOLT D25572207000 0054 6 NSA5060-4 NUT D25572207000 0055 6 NAS1149C0432R WASHER D25572207000 0056 6 NAS1149C0532R WASHER D25572207000 0057 6 MS24665-153 PIN D25572207000 0058 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 69
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP
36 DAN7-5-5 PIN D25572207000 0061 36 DAN7-5-6 PIN D25572207000 0062 36 DAN12-5 COLLAR D25572207000 0063 32 NAS1102-3-8 SCREW D25572207000 0066 148 NAS1100-3-10 SCREW D25572207000 0070

20 NAS1100-3-8 SCREW D25572207000 0071 16 NAS1096-3-12 SCREW D25572207000 0077

6 D2557238000400 LATCH D25572207000 0078 50 MS21250-03006 BOLT D25572207000 0079 77 NAS1102-3-11 SCREW D25572207000 0080 77 NAS1102-3-12 SCREW D25572207000 0081 32 NAS1102-3-14 SCREW D25572207000 0082 20 NAS1100-3-9 SCREW D25572207000 0083 46 NAS1100-3-11 SCREW D25572207000 0084

5 D2557268123000 PLATE D25572207000 0099 5 D2557268123200 PLATE D25572207000 0100 5 D2557268123400 PLATE D25572207000 0101 5 D2557268123600 PLATE D25572207000 0102 5 D2557268123800 PLATE D25572207000 0103 5 D2557268124000 PLATE D25572207000 0104 5 D2557268124200 PLATE D25572207000 0105 5 D2557268124400 PLATE D25572207000 0106 5 D2557268124600 PLATE D25572207000 0107 5 D2557268124800 PLATE D25572207000 0108 5 D2557268125000 PLATE D25572207000 0109 5 D2557268127600 PLATE D25572207000 0110 5 D2557268127800 PLATE D25572207000 0111 5 D2557268128000 PLATE D25572207000 0112 5 D2557268128200 PLATE D25572207000 0113 5 D2557268128400 PLATE D25572207000 0114 5 D2557268128600 PLATE D25572207000 0115 5 D2557268128800 PLATE D25572207000 0116 5 D2557268129000 PLATE D25572207000 0117 5 D2557268129200 PLATE D25572207000 0118 5 D2557268129400 PLATE D25572207000 0119 5 D2557268129600 PLATE D25572207000 0120 5 D2557268129800 PLATE D25572207000 0121 5 D2557268130000 PLATE D25572207000 0122 5 D2557268130200 PLATE D25572207000 0123 5 D2557268127400 PLATE D25572207000 0124 5 D2557268130400 PLATE D25572207000 0125 5 D2557268130600 PLATE D25572207000 0126 5 D2557268130800 PLATE D25572207000 0127 5 D2557268131000 PLATE D25572207000 0128 5 D2557268131200 PLATE D25572207000 0129

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you 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 : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 70
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Kit 281154D81R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 D2557214633400 SHIM D25572676034 0034 2 D2557214633500 SHIM D25572676034 0035 2 D2557214633600 SHIM D25572676034 0036 20 D2557214635000 SHIM D25572676034 0050 20 D2557214635100 SHIM D25572676034 0051 20 D2557214635200 SHIM D25572676034 0052

4 D2557214655600 SHIM D25572676034 0054 4 D2557214655700 SHIM D25572676034 0055 4 D2557214655800 SHIM D25572676034 0056 6 D2557214638000 SHIM D25572676034 0080 6 D2557214638100 SHIM D25572676034 0081 6 D2557214638200 SHIM D25572676034 0082 6 D2557214638400 SHIM D25572676034 0084 6 D2557214638500 SHIM D25572676034 0085 6 D2557214638600 SHIM D25572676034 0086 2 D2557214639200 SHIM D25572676034 0092 2 D2557214639300 SHIM D25572676034 0093 2 D2557214639400 SHIM D25572676034 0094 4 D2557214639600 SHIM D25572676034 0096 4 D2557214639700 SHIM D25572676034 0097 4 D2557214639800 SHIM D25572676034 0098 2 D2557206229800 PLUG D25572676034 0104 4 NAS1102-3-10 SCREW D25572676034 0134 6 D2557214644000 SHIM D25572676034 0140 6 D2557214644100 SHIM D25572676034 0141 6 D2557214644200 SHIM D25572676034 0142 2 D2557214652000 SHIM D25572676034 0220 2 D2557214652100 SHIM D25572676034 0221 2 D2557214652200 SHIM D25572676034 0222 12 D2557214632000 SHIM D25572676034 0227 12 D2557214631800 SHIM D25572676034 0228

2 D2557214655900 SHIM D25572676034 0259 2 D2557214656000 SHIM D25572676034 0260 2 D2557214656100 SHIM D25572676034 0261 2 D2557214656800 SHIM D25572676034 0268 2 D2557214656900 SHIM D25572676034 0269 2 D2557214657000 SHIM D25572676034 0270 2 D2557214657200 SHIM D25572676034 0272 2 D2557214657300 SHIM D25572676034 0273 2 D2557214657400 SHIM D25572676034 0274 2 D2557214657600 SHIM D25572676034 0276 2 D2557214657700 SHIM D25572676034 0277 2 D2557214657800 SHIM D25572676034 0278

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you 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 : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 71
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Kit 281154D82R01 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 2 DAN152-1 TDP D25572592006 0001 4 NAS1102-3-10 SCREW D25572592006 0010 14 NAS1102-3-12 SCREW D25572592006 0011 14 NAS1102-3-14 SCREW D25572592006 0012 28 NAS1726-3E NUT D25572592006 0013

7 D2557206228600 TDP D25572592006 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 281154D83R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 1 D2557295822000 PLACARD D25572592010 0035 1 D2557295722600 PLACARD D25572592010 0036 1 A2557144422000 PLACARD D25572592010 0037

Kit 281154D84R00 QTY UM NEW PART No. KEYWORD DRAWING No. ITEM INST DISP 6 D2557264401400 COVER D25572592012 0010 4 NAS1100-3-8 SCREW D25572592012 0011 4 NAS1149D0316K WASHER D25572592012 0012 3 D2557264405200 COVER D25572592012 0018 6 NAS1102-3-6 SCREW D25572592012 0020 20 NSA5030-3-3 SCREW D25572592012 0021

2 ABS0202-3-10 SCREW D25572592012 0023 6 NSA5039-3-2 SCREW D25572592012 0024 12 NSA5110-3-1 NUT D25572592012 0029 12 ABS0208-01 WASHER D25572592012 0030

6 NAS1149C0332R WASHER D25572592012 0031 1 D2557295123200 PLACARD D25572592012 0032 1 DAN152-1 TDP D25572592012 0035 3 D2557264405000 COVER D25572592012 0050 3 D2557264401800 COVER D25572592012 0052 22 NSA5030-3-5 SCREW D25572592012 0053 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. **D. L I**  **S T**  **O F**  **M A**  **T E**  **R I**  **A L** **S -**  **O P**  **E R** **A T** **O R**  **S U**  **P P**  **L I**  **E D**  (1) Consumable Materials DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 72
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP MAT No. Synth. Ester Based Grease, High Pressure Mat. No. 04-004 As required Pure Mineral Vaseline Mat. No. 04-012 As required Putty, Zinc Chromate General Purpose Mat. No. 05-002 As required Conductive Film Mat. No. 05-099 As required Electrical Bonding Coating (Blue Color) Mat. No. 07-001 As required Internal Polyurethane Varnish Mat. No. 07-017 As required Transparent Protective Coating Mat. No. 07-023 As required General Purpose Dimethacrylate Green Mat. No. 08-002 As required Adhesive Sealant Mat. No. 08-004 As required Sealant, High Temp. Mat. No. 08-007B As required Two Component Epoxy Adhesive Mat. No. 08-010 As required Two Component Polyurethane Adhesive Mat. No. 08-025 As required Adhesive Mat. No. 08-048 As required Sealant, High Temp. Mat. No. 08-573 As required Fuel Tank Sealant Polysulfide Mat. No. 09-001 As required Fuel Tank Sealant Polysulfide Mat. No. 09-002 As required Corrosion Inhibitive Interfay Sealant Mat. No. 09-005 As required Corrosion Inhibiting Brush Consistency Mat. No. 09-013 As required Corrosion Inhibiting Fillet Consistency Mat. No. 09-016 As required Corrosion Inhibiting Low Adhesion Sealant Mat. No. 09-018 As required Low Adhesion Corrosion Inhibiting Sealant Mat. No. 09-019 As required Protective Coating For Fuel Vapor Mat. No. 09-032 As required Dry Cleaning Solvent Mat. No. 11-002 As required Solvent General Purpose Mat. No. 11-026 As required Corrosion Preventive Temporary Protective Compound Mat. No. 15-008 As required Corrosion Preventive Temporary Protective Compound Mat. No. 15-009 As required Anti-Corrosion Primer (Polyurethane) Mat. No. 16-001 As required Polyurethane Top Coat Grey Mat. No. 16-002 As required Anti-Corrosion Primer Mat. No. 16-006F As required Fuel Tank Coating Mat. No. 16-015 As required External Top Coat (Polyurethane) Mat. No. 16-018 As required Wash Primer Mat. No. 16-020 As required Wash Primer Mat. No. 16-020A As required Flexible Polyurethane Mat. No. 16-021 As required Lint-Free Cotton Cloth Mat. No. 19-003 As required Lockwire, 0.5 mm Dia. Mat. No. 19-009 As required Lockwire, 0.6 mm Dia. Mat. No. 19-018 As required Lockwire LN9424A100 None As required (01) DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 73
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP MAT No. Low Adhesion Sealant MC216A None As required (01) Varnish, RAL3000 WL570510 None As required (01) NOTE(01) This material can be obtained from : INTERTURBINE LOGISTIK GMBH Kisdorfer Weg 36 - 38 24568 Kaltenkirchen Germany Phone : +49 4191 809 300 Fax : +49 4191 809 333 AOG : +49 4191 809 444 (2) Components ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 1422KID02-03 1 FQI 1407KID02-03 01 SIC5059-12-0308 1 FQIC SIC5059-11-0207 01 02 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) You can install Fuel Quantity Indication Computer (FQIC) PN SIC5059-13-10 as an alternative to PN SIC5059-12-0308.
**E. P A**  **R T** **S T** **O B**  **E R**  **E -**  **I D**  **E N**  **T I**  **F I**  **E D**  **B Y**  **T H**  **E O**  **P E**  **R A**  **T O**  **R** ITEM NEW PART No. KEYWORD ITEM OLD PART No. INT 0 D9241244300000 PLATE (0) D9241134400100 03 D2587311905400 BLANKET D2587311900000 03 (01) D2587312105400 BLANKET D2587312100000 03 (01) D2587312305400 BLANKET D2587312300000 03 (01) D2587341406600 BLANKET D2587341400000 03 (01) D2587341605800 BLANKET D2587341600000 03 (01) D2587341905200 BLANKET D2587341900000 03 (01) D2587342005400 BLANKET D2587342000000 03 (01) D2587342105200 BLANKET D2587342100000 03 (01) D2587342305400 BLANKET D2587342300000 03 (01) D2587351405800 BLANKET D2587351400000 03 (01) D2587351605800 BLANKET D2587351600000 03 (01) DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 74
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

ITEM NEW PART No. KEYWORD ITEM OLD PART No. INT D2587351905200 BLANKET D2587351900000 03 (01) D2587352005200 BLANKET D2587352000000 03 (01) D2587352105200 BLANKET D2587352100000 03 (01) D2587352305200 BLANKET D2587352300000 03 (01) D2587360105200 BLANKET D2587360100000 03 (02) D2587360305200 BLANKET D2587360300000 03 (02) D2587364605200 BLANKET D2587364600000 03 (02) D2587370105200 BLANKET D2587370100000 03 (02) D2587370305400 BLANKET D2587370300000 03 (02) D2587370806000 BLANKET D2587370800000 03 (02) D2587371905200 BLANKET D2587371900000 03 (02) D2587372405200 BLANKET D2587372400000 03 (02) D2587374205200 BLANKET D2587374200000 03 (02) D2587374605200 BLANKET D2587374600000 03 (02) D2587374805200 BLANKET D2587374800000 03 (02) D2587375805200 BLANKET D2587375800000 03 (02) D2587376005200 BLANKET D2587376000000 03 (02) NOTE(01) Insulation Blanket in the passenger compartment. NOTE(02) Insulation Blanket in the AFT cargo compartment. NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common Support Data Dictionary (CSDD), Chapter 2.
**F. T O**  **O L**  **I N**  **G -**  **P R**  **I C**  **E A** **N D**  **A V** 

**A I**  **L A**  **B I**  **L I** **T Y**  To accomplish this Service Bulletin it is necessary to use the tooling listed in : - AMM 07-11-00, Page block 201 - AMM 20-23-11, Page block 201 - AMM 29-14-00, Page block 201 - AMM 32-12-00, Page block 201 - AMM 52-30-00, Page block 201. **G. S P**  **E C**  **I A**  **L T** **O O**  **L S**  To accomplish this Service Bulletin it is necessary to use the latch adjustment tool PN 98D28108641000.

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 75
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 76
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

**3. A C**  **C O**  **M P**  **L I**  **S H**  **M E**  **N T**  **I N**  **S T**  **R U**  **C T**  **I O**  **N S**  **A. G E**  **N E**  **R A**  **L** WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR : - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE RELATED DOORS - COMPONENTS THAT MOVE. CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS : - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00. (1) Preparation (a) Config. 01
1 Lift the aircraft on jacks (Refer to AMM 07-11-00, Page block 201).
2 Make sure that the aircraft is electrically grounded (Refer to AMM 12-34-24, Page block 201).
3 Put the access platform(s) in position.
4 Open the passenger/crew door 841 (Refer to AMM 52-10-00, Page block 201).
5 Open the avionics door 822 (Refer to AMM 52-41-00, Page block 201).
6 Open the FWD and AFT cargo compartment doors (Refer to AMM 52-30-00, Page block 201). NOTE : Make sure that the applicable safety equipment is installed on the FWD and AFT cargo compartment doors.
DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 77
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

7 Open the MLG doors (Refer to AMM 32-12-00, Page block 201). NOTE : Make sure that the applicable safety equipment is installed on the MLG doors.
8 Remove the belly fairing access panels : - 192LB (Refer to AMM 53-35-11, Page block 401). - 147AB, 147EB, 147FB, 191BB, 191KB, 197BB and 197GB, 192EB, 192FB, 192KB, 198BB and 198MB (Refer to AMM 53-35-13, Page block 401).
9 Remove the air inlets LH/RH (Refer to AMM 21-61-51, Page block 401).
1 0 Remove only the welding group (Item 127) from the air condition packs 10HM and 11HM (Refer to AMM 21-61-51, Page block 401).
1 1 Remove the air cooling distribution duct below the cabin floor between FR42 and FR47 (Refer to AMM 21-20-00, Page block 201 and IPC 21-21-03-05, Items 20 and 40).
1 2 Remove he MLG torque tube assemblies, LH/RH (Refer to AMM 32-33-17, Page block 401).
1 3 Remove hydraulic pipes (Refer to AMM 20-23-11, Page block 201 and IPC 29-13-03-16, Item 10, IPC 29-11-0303B, Items 10 and 90).
1 4 In the cockpit, remove the lining panels 211HC, 212FC, 212KC, 212KW, 212JW and 212HW (Refer to AMM 06-41-53, Page block 1 and AMM 25-13-41, Page block 401).
1 5 In the forward cargo compartment, remove the panels 131AC, 131AW, 131BW, 131CW, 131DW, 132AW, 131HC, 131LC, 131MC, 131BC and 131CC (Refer to AMM 06-41-53, Page block 1 and AMM 25-54-11, Page block 401).
1 6 Do the special precautions before work on the offwing Escape Slide systems (Refer to AMM 25-62-00, Page block 201).
1 7 Remove the offwing escape-slides LH and RH (Refer to AMM 25-62-42, Page block 401).
1 8 Defuel the center tank (Refer to AMM 28-25-00, Page block 301).
1 9 Obey the instructions for the fuel safety procedures and make sure that the ventilation of the center tank is correct (Refer to AMM 28-00-00, Page block 301) and (AMM 28-10-00, Page block 301).
2 0 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).
2 1 Remove the Slat and Flap Control Computer (SFCC) (21CV), (22CV), (Refer to AMM 27-51-34, Page block 401). DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 78
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 2 Do the preparation procedure as specified in the removal/installation of the multi-tank fuel quantity indicator (6QT) (Refer to AMM 28-42-22, Page block 401).
2 3 Remove the cover 148AZ (Refer to AMM 57-17-11, Page block 401).
2 4 Put a warning notice in position in the cockpit to tell persons not to operate the fuel system.
2 5 Remove the outlet PN D2821003520000 (Refer to IPC 28-12-05).
2 6 Depressurize the Green, Blue and Yellow hydraulic systems (Refer to AMM 29-10-00, Page block 201).
2 7 Depressurize the reservoirs of the Green, Blue and Yellow hydraulic systems (Refer to AMM 29-14-00, Page block 201).
2 8 Put warning notices in position to tell persons not to pressurize the hydraulic systems.
2 9 Remove the Green hydraulic reservoir (Refer to AMM 29-11-41, Page block 401).
3 0 Remove the VHF 2 antenna (Refer to AMM 23-12-11, Page block 401).
3 1 Remove the System Data Acquisition Concentrator (SDAC) (1WV1), (1WV2) (Refer to AMM 31-55-34, Page block 401).
32 Remove the Ground Power Control Unit (GCU)-1(2) (1XU1, 1XU2) (Refer to AMM 24-22-34, Page block 401).
33 In the passenger compartment, remove as necessary : - the passenger seats (Refer to AMM 25-21-41, Page block 401) - the textile floor covering (Refer to AMM 25-28-41, Page block 401) - the floor panels (Refer to AMM 53-32-12, Page block 401 and AMM 53-42-12, Page block 401) - the ceiling panels (Refer to AMM 25-23-41, Page block 401 - the cove light panels (Refer to AMM 25-23-48, Page block 401) - the upper sidewall panels (Refer to AMM 25-23-43, Page block 401) - the lower sidewall (dado) panels (Refer to AMM 25-23-44, Page block 401) - the overhead stowage compartments (Refer to AMM 25-24-41, Page block 401) - the insulation blankets (Refer to AMM 25-80-00, Page block 201).
34 In the FWD cargo compartment, remove as necessary :
DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 79
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

- the floor panels (Refer to AMM 53-22-14, Page block 401) - the sidewall panels (Refer to AMM 25-54-12, Page block 401) - the ceiling panels (Refer to AMM 25-54-12, Page block 401).
35 In the AFT cargo compartment, remove as necessary : - the floor panels (Refer to AMM 53-42-14, Page block 401) - the sidewall panels (Refer to AMM 25-55-11, Page block 401) - the ceiling panels (Refer to AMM 25-55-11, Page block 401).
3 6 Make sure that the external connector(s) is(are) not connected to the aircraft receptacle(s) EXT PW.
3 7 Make sure that there is(are) warning notice(s) on the external power receptacle to tell persons not to connect an external power source.
3 8 Make sure that the EMER EXIT LT pushbutton switch on the 25VU is set to OFF.
3 9 In the cockpit, on the ELEC Panel 35VU, release the BAT pushbutton switches.
4 0 Put a warning notice in position on the ELEC Panel 35VU to tell persons not to operate the batteries.
4 1 Put a warning notice in position on the Refuel/Defuel Panel 800VU to tell persons not to operate the NORMAL BATTERY switch.
42 Put a warning notice in position in the cockpit to tell persons not to start the APU.
43 Put a warning notice in position in the cockpit to tell persons not to start the ENG1, 2.
44 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.
45 To route the wires into the Overhead Panel 20VU, remove the VUs and items of equipment as necessary, but do not disconnect them. NOTE : Disconnection of the connectors in the Overhead Panel 20VU will include a high increase in manhours for the test. (2) Standard Practices DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 80
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(a) Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. (b) Refer to the cross reference list in the Process and Material Specification (PMS) if you find process and material specifications in the affected design drawings which you do not know. (c) Refer to the Consumable Material List (CML) for the specification of materials (Mat. No.) that you must use to accomplish this Service Bulletin. (d) For the frame (FR) identification (Refer to AMM 06-31-53, Page block 001). (e) For the identification of access panels (Refer to AMM 06-41-53, Page block 001). (f) Clean the work areas with Solvent General Purpose (Mat. No. 11-026) and a Lint-Free Cotton Cloth (Mat. No. 19-003). (g) Obey the hydraulic safety procedures (Refer to AMM 29-00-00, Page block 201). (h) For information for the installation of permaswage fittings on the hydraulic lines (Refer to AMM 20-23-11, Page block 201). (i) Remove the old sealant with a nonmetallic scraper. Clean the surface with Solvent General Purpose (Mat. No. 11-026). (j) To drill and deburr the holes, refer to SRM 51-44-11. (k) For the countersinking of holes (Refer to SRM 51-46-11). (l) For information on spot facing (Refer to SRM 51-46-12). (m) For corrosion prevention (Refer to SRM 51-22-00). (n) For the application of protective coatings (Refer to SRM 51-23-00). (o) After drilling/reworking of the structure, apply : - Wash Primer (Mat. No. 16-020) - Anti-Corrosion Primer (Polyurethane) (Mat. No. 16-001) - External Top Coat (Polyurethane) (Mat. No. 16-018). (p) Cut the rivets to the necessary length. (q) Apply the sealing and the protection in the center tank, (Refer to SRM 51-76-12). (r) To remove and install the fasteners, refer to SRM 51-42-11. (s) To torque tighten the standard threaded fasteners, refer to AMM 20-21-11, Page block 201. DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 81
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(t) Torque the pipe unions, (Refer to AMM 20-21-12, Page block 201). (u) Before installation of structural items, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013). (v) Wet install the fasteners with Corrosion Inhibiting Brush Consistency (Mat. No. 09-013). (w) For the application of sealants (Refer to SRM 51-24-00). (x) For the removal/installation of fuel pipes (Refer to AMM 28-00-00, Page block 401). (y) To torque tighten the electrical component fasteners, refer to AMM 20-21-15, Page block 201. (z) Do the electrical bonding, (Refer to AMM 20-28-00, Page block 201) with Pure Mineral Vaseline (Mat. No. 04-012) and Electrical Bonding Coating (Blue Color) (Mat. No. 07-001). (aa) Clean the surfaces at the location of the placards with Dry Cleaning Solvent (Mat. No. 11-002). (ab) Bond the placards, (Refer to AMM 11-00-00, Page block 201). (ac) Obey the instructions for the general wiring installation, refer to ESPM 20-33-00. (ad) Put blanking caps on the disconnected electrical connectors. (ae) Make sure that the electrical connectors are serviceable before you connect them again. (af) Route the new wires with the wires that are in the aircraft. (ag) Do a continuity test of the new and of the modified wires, (Refer to ESPM 20-52-21). (ah) To install new wires, cut them to the necessary length, crimp the terminals and connect them. (ai) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21). (aj) When you install electrical connectors do a visual check of each connector which is disconnected to make sure that : - the electrical connectors are serviceable before you connect them again - the label of the connector is the same as the label on the receptacle - the connector is correctly locked with Lockwire, 0.5 mm Dia. (Mat. No. 19-009), where locking facilities exist. (ak) When you install cable ties on electrical cable installations, refer to ESPM 20-33-44 and ESPM 20-25-51 for the cable tie application and tooling.

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 82
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(al) Install the grounding modules, (Refer to ESPM 20-44-71). (am) Install the connectors (Refer to ESPM 20-44-22 and ESPM 20-44-24). (an) When you install the Service Bulletin identification placards on new or modified wires : - install one placard at each end of the wire - install the other placards approximately every 1500 mm along the length of the wire.
**B. M O**  **D I**  **F I**  **C A**  **T I**  **O N**  NOTE : To accomplish this Service Bulletin, refer to Top Drawing D00071141002.. NOTE : The order of the worksteps are in the sequence given on the top drawing and are not a sequence of worksteps. The sequence can be changed by the operator as required. NOTE : There is a list of all new components in the MATERIAL INFORMATION (para. 2.C and D) which are necessary to accomplish this Service Bulletin. We refer to the related installation drawings of all the new components in the MATERIAL INFORMATION. (1) Config. 01 D00071141002 281154A00001 Sheet(s) 01 A00 281154A00001 Sheet(s) 02 A00 281154A00001 Sheet(s) 03 A00 NOTE : Remove the finch paint and the paint protection from the extrados panels between Y=+254 and Y=-254, between FR36 and FR42 and in the center tank. Do not use a metallic tool. Do not cause damage to the head of the rivets, (Refer to SRM 51-75-11, paragraph 3). Stop the removal when you can see the primary protection (green color). Only remove the rivets at the location of the doubler. (a) Install the doublers on the extrados, in the center tank Refer to Kit 281154A01R00 281154A01001 Sheet(s) 01 A00 281154A01001 Sheet(s) 02 A00 281154A01001 Sheet(s) 03 A00 281154A01002 Sheet(s) 01 A00 NOTE : Use a loft to drill the extrados panels : 1 Loft D5713032000095 NOTE : Use Fuel Tank Sealant Polysulfide (Mat. No. 09-002). (b) Install the brackets on the extrados, in the center tank

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 83
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Kit 281154A01R00 281154A01003 Sheet(s) 01 A00 281154A01003 Sheet(s) 02 A00 281154A01003 Sheet(s) 03 A00 281154A01003 Sheet(s) 04 A00 281154A01004 Sheet(s) 01 A00 281154A01004 Sheet(s) 02 A00 281154A01004 Sheet(s) 03 A00 281154A01005 Sheet(s) 01 A00 NOTE : Use Fuel Tank Sealant Polysulfide (Mat. No. 09-002), Anti-Corrosion Primer (Mat. No. 16-001), Corrosion Inhibiting Brush Consistency (Mat. No. 09-013) and Corrosion Preventive Temporary Protective Compound (Mat. No. 15-008). (c) Install the bracket on the rear spar assy, in the center tank Refer to Kit 281154A02R00 281154A02001 Sheet(s) 01 A00 NOTE : Use Anti-Corrosion Primer (Mat. No. 16-001). (d) Install the brackets on the intrados, in the center tank Refer to Kit 281154A02R00 281154A02002 Sheet(s) 01 A00 281154A02002 Sheet(s) 02 A00 281154A02002 Sheet(s) 03 A00 281154A02003 Sheet(s) 01 A00 281154A02003 Sheet(s) 02 A00 NOTE : Use Fuel Tank Sealant Polysulfide (Mat. No. 09-002), Corrosion Preventive Temporary Protective Compound (Mat. No. 15-008) and Anti-Corrosion Primer (Mat. No. 16-001). (e) Install the Additional Center Tank (ACT) door assy on the center tank Refer to Kit 281154A03R01 and Kit 281154A08R00 281154A03000 Sheet(s) 01 A00 281154A03001 Sheet(s) 01 A00 281154A03002 Sheet(s) 01 A00 281154A03002 Sheet(s) 02 A00 281154A03003 Sheet(s) 01 A00 281154A03004 Sheet(s) 01 A00 281154A03005 Sheet(s) 01 A00 281154A03006 Sheet(s) 01 A00 281154A03007 Sheet(s) 01 A00 281154A03008 Sheet(s) 01 A00
1 Remove : 281154A03000 Sheet(s) 01 A00 281154A03001 Sheet(s) 01 A00 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 84
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 Install : 281154A03002 Sheet(s) 01 A00 281154A03002 Sheet(s) 02 A00 281154A03003 Sheet(s) 01 A00 281154A03004 Sheet(s) 01 A00 281154A03005 Sheet(s) 01 A00 281154A03006 Sheet(s) 01 A00 281154A03007 Sheet(s) 01 A00 281154A03008 Sheet(s) 01 A00 NOTE : Use Zinc Chromate General Purpose (Mat. No. 05-002), Anti-Corrosion Primer (Mat. No. 16-001) and Grease High Pressure (Mat. No. 04-004). (f) Replace the Fuel Quantity Indicator (FQI) 6QT (Refer to AMM 28-42-22, Page block 401)
1 Remove : 1 Fuel Quantity Indicator 1407KID02-03
2 Install : 1 Fuel Quantity Indicator 1418KID01-03 (g) Modify the transfer line in the center tank Refer to Kit 281154A04R00 and Kit 281154A09R00 281154A04000 Sheet(s) 01 A00 281154A04001 Sheet(s) 01 A00 281154A04001 Sheet(s) 02 A00 281154A04001 Sheet(s) 03 A00 281154A04002 Sheet(s) 01 A00 281154A04002 Sheet(s) 02 A00 281154A04002 Sheet(s) 03 A00 281154A04002 Sheet(s) 04 A00 281154A04003 Sheet(s) 01 A00 281154A04003 Sheet(s) 02 A00 281154A04003 Sheet(s) 03 A00 281154A04003 Sheet(s) 04 A00 281154A04003 Sheet(s) 05 A00 281154A04004 Sheet(s) 01 A00 281154A04005 Sheet(s) 01 A00 281154A04006 Sheet(s) 01 A00 281154A04007 Sheet(s) 01 A00 281154A04008 Sheet(s) 01 A00 281154A04009 Sheet(s) 01 A00 281154A04010 Sheet(s) 01 A00 281154A04011 Sheet(s) 01 A00 281154A04011 Sheet(s) 02 A00 281154A04012 Sheet(s) 01 A00 281154A04013 Sheet(s) 01 A00

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 85
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Remove : 281154A04000 Sheet(s) 01 A00 281154A04001 Sheet(s) 01 A00 281154A04001 Sheet(s) 02 A00 281154A04001 Sheet(s) 03 A00
2 Install : 281154A04002 Sheet(s) 01 A00 281154A04002 Sheet(s) 02 A00 281154A04002 Sheet(s) 03 A00 281154A04002 Sheet(s) 04 A00 281154A04003 Sheet(s) 01 A00 281154A04003 Sheet(s) 02 A00 281154A04003 Sheet(s) 03 A00 281154A04003 Sheet(s) 04 A00 281154A04003 Sheet(s) 05 A00 281154A04004 Sheet(s) 01 A00 281154A04005 Sheet(s) 01 A00 281154A04006 Sheet(s) 01 A00 281154A04007 Sheet(s) 01 A00 281154A04008 Sheet(s) 01 A00 281154A04009 Sheet(s) 01 A00 281154A04010 Sheet(s) 01 A00 281154A04011 Sheet(s) 01 A00 281154A04011 Sheet(s) 02 A00 281154A04012 Sheet(s) 01 A00 281154A04013 Sheet(s) 01 A00 NOTE : Use Anti-Corrosion Primer (Mat. No. 16-001) and Fuel Tank Sealant Polysulfide (Mat. No. 09-002). (h) Install the transfer elbow and the air ventilation elbow on the center tank Refer to Kit 281154A05R00 281154A05001 Sheet(s) 01 A00 281154A05002 Sheet(s) 01 A00 281154A05003 Sheet(s) 01 A00 281154A05003 Sheet(s) 02 A00 NOTE : Use Anti-Corrosion Primer (Mat. No. 16-001), Protective Coating For Fuel Vapor (Mat. No. 09-032), Fuel Tank Sealant Polysulfide (Mat. No. 09-002), Fuel Tank Sealant Polysulfide (Mat. No. 09-001) and Fuel Tank Coating (Mat. No. 16-015). (i) Apply the sealing protection to the center tank 281154A05003 Sheet(s) 01 A00 281154A05003 Sheet(s) 02 A00
1 After the installation of the doublers and attachments, apply the sealing protection between FR36 and FR42, on the upper and lower surface panels, with : - Fuel Tank Sealant Polysulfide (Mat. No. 09-001) DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 86
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

- Fuel Tank Sealant Polysulfide (Mat. No. 09-002) - Protective Coating For Fuel Vapor (Mat. No. 09-032) - Anti-Corrosion Primer (Mat. No. 16-001) - Fuel Tank Coating (Mat. No. 16-015). (j) Modify the equipment and the wiring in the HYD/Fuel Panel 40VU Refer to Kit 281154A06R02, Kit 281154A07R00 and Kit 281154A10R01 281154A06000 Sheet(s) 01 A00 281154A06001 Sheet(s) 01 A00 281154A06002 Sheet(s) 01 A00 281154A06003 Sheet(s) 01 A00 281154A06004 Sheet(s) 01 A00
1 Remove : 281154A06000 Sheet(s) 01 A00 281154A06001 Sheet(s) 01 A00 281154A06002 Sheet(s) 01 A00
2 Install : 281154A06001 Sheet(s) 01 A00 281154A06003 Sheet(s) 01 A00 281154A06004 Sheet(s) 01 A00 NOTE : Safety the screws with Sealant High Temperature (Mat. No. 08-573) or Sealant High Temperature (Mat. No. 08-007B). NOTE : The placards are supplied in : Placard Set D9100095114295
3 Modify the wires 281154A10501 Sheet(s) 01 A00 281154A10501 Sheet(s) 03 A00 281154A10503 Sheet(s) 01 B00 281154A10503 Sheet(s) 03 A00

a Install the wires : 281154A10501 Sheet(s) 03 A00 281154A10503 Sheet(s) 03 A00 supplied in : Bundle D9000095141095 b Attach the wires with : 150 Tie-Cable NSA935401-03 150 Tie-Cable NSA935401-06 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 87
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(k) Modify the equipment and the wiring in the Rear C/B Panel 121VU and the Rear Panel 120VU Refer to Kit 281154A06R02 and Kit 281154A10R01
1 Install : 281154A06005 Sheet(s) 01 A00 NOTE : The placards are supplied in : Placard Set D9100095114295
2 Modify the wiring in the Rear C/B Panel 121VU 281154A06501 Sheet(s) 01 A00 281154A06501 Sheet(s) 02 A00 281154A06502 Sheet(s) 01 A00 281154A06502 Sheet(s) 02 A00 281154A06503 Sheet(s) 01 A00 281154A06503 Sheet(s) 02 A00 281154A06504 Sheet(s) 01 A00 281154A06504 Sheet(s) 02 A00 281154A06505 Sheet(s) 01 A00 281154A06505 Sheet(s) 02 A00 281154A06506 Sheet(s) 01 A00 281154A06506 Sheet(s) 02 A00 281154A06507 Sheet(s) 01 A00 281154A06507 Sheet(s) 02 A00 281154A06508 Sheet(s) 01 A00 281154A06508 Sheet(s) 02 A00 281154A06509 Sheet(s) 01 A00 281154A06509 Sheet(s) 02 A00 281154A06510 Sheet(s) 01 A00 281154A06510 Sheet(s) 02 A00 281154A06511 Sheet(s) 01 A00 281154A06511 Sheet(s) 02 A00

a Remove the wires : 281154A06501 Sheet(s) 02 A00 281154A06503 Sheet(s) 02 A00 281154A06505 Sheet(s) 02 A00 281154A06507 Sheet(s) 02 A00 281154A06510 Sheet(s) 02 A00 b Install the wires : 281154A06502 Sheet(s) 02 A00 281154A06504 Sheet(s) 02 A00 281154A06506 Sheet(s) 02 A00 281154A06508 Sheet(s) 02 A00 281154A06509 Sheet(s) 02 A00 281154A06511 Sheet(s) 02 A00

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 88
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

supplied in : Bundle D9000095128395

c Attach the wires with : 50 Tie-Cable NSA935401-03 60 Tie-Cable NSA935401-04 40 Tie-Cable NSA935401-05
3 Modify the wiring in the Rear Panel 120VU 281154A10501 Sheet(s) 01 A00 281154A10501 Sheet(s) 02 A00 281154A10503 Sheet(s) 01 B00 281154A10503 Sheet(s) 02 A00 281154A10504 Sheet(s) 01 A00 281154A10504 Sheet(s) 02 A00 281154A10505 Sheet(s) 01 A00 281154A10505 Sheet(s) 02 A00 281154A10507 Sheet(s) 01 B00 281154A10507 Sheet(s) 02 A00

a Install the wires : 281154A10501 Sheet(s) 02 A00 281154A10503 Sheet(s) 02 A00 281154A10504 Sheet(s) 02 A00 281154A10505 Sheet(s) 02 A00 281154A10507 Sheet(s) 02 A00 supplied in : Bundle D9000095140995 b Attach the wires with : 50 Tie-Cable NSA935401-03 60 Tie-Cable NSA935401-04 20 Tie-Cable NSA935401-05 (l) Modify the routing in the avionics compartment Refer to Kit 281154A10R01 281154A10001 Sheet(s) 01 A00 281154A10001 Sheet(s) 02 A00 281154A10002 Sheet(s) 01 A00 281154A10002 Sheet(s) 02 A00 281154A10003 Sheet(s) 01 A00 281154A10004 Sheet(s) 01 A00 281154A10004 Sheet(s) 02 A00 281154A10005 Sheet(s) 01 A00 281154A10005 Sheet(s) 02 A00 281154A10006 Sheet(s) 01 A00 281154A10006 Sheet(s) 02 A00 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 89
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Remove : 281154A10001 Sheet(s) 01 A00 281154A10001 Sheet(s) 02 A00
2 Install : 281154A10002 Sheet(s) 01 A00 281154A10002 Sheet(s) 02 A00 281154A10003 Sheet(s) 01 A00 281154A10004 Sheet(s) 01 A00 281154A10004 Sheet(s) 02 A00 281154A10005 Sheet(s) 01 A00 281154A10005 Sheet(s) 02 A00 281154A10006 Sheet(s) 01 A00 281154A10006 Sheet(s) 02 A00 NOTE : The placards are supplied in : Placard Set D9100095117895 NOTE : Use Anti-Corrosion Primer (Mat. No. 16-001), Polyurethane Top Coat Grey (Mat. No. 16-002) and Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016).
3 Re-identify the plate assy Item 0 shown on drawing 281154A10003 Sheet 01 A00 1 Plate Assy D9241134400100 Item (0)

becomes 1 Plate Assy D9241244300000 Item 0 (m) Modify the equipment in the FWD cargo compartment Refer to Kit 281154A10R01
1 Install : 281154A10007 Sheet(s) 01 A00 281154A10007 Sheet(s) 02 A00 NOTE : The placards are supplied in : Placard Set D9100095117895 (n) Modify the equipment and the wiring in the Relay Box 103VU Refer to Kit 281154A10R01
1 Install : 281154A10008 Sheet(s) 01 A00 281154A10008 Sheet(s) 02 A00 NOTE : The placards are supplied in : Placard Set D9100095117895 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 90
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 Modify the wiring 281154A10518 Sheet(s) 01 B00 281154A10518 Sheet(s) 02 A00

a Install the wires : 281154A10518 Sheet(s) 02 A00 supplied in : Bundle D9000095141295 b Attach the wires with : 60 Tie-Cable NSA935401-04 60 Tie-Cable NSA935401-05 120 Tie-Cable NSA935401-06 240 Tie-Cable NSA935401-08 (o) Modify the equipment and the wiring in the Contactor Box 107VU Refer to Kit 281154A10R01
1 Install : 281154A10009 Sheet(s) 01 A00 281154A10009 Sheet(s) 02 A00 NOTE : The placards are supplied in : Placard Set D9100095117895
2 Modify the wiring 281154A10501 Sheet(s) 01 A00 281154A10501 Sheet(s) 04 A00 281154A10505 Sheet(s) 01 A00 281154A10505 Sheet(s) 03 A00

a Install the wires : 281154A10501 Sheet(s) 04 A00 281154A10505 Sheet(s) 03 A00 supplied in : Bundle D9000095141195 b Attach the wires with : 60 Tie-Cable NSA935401-04 60 Tie-Cable NSA935401-05 120 Tie-Cable NSA935401-06 240 Tie-Cable NSA935401-08

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 91
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(p) Modify the equipment and the wiring in the AFT Electronics Rack 80VU Refer to Kit 281154A10R01 281154A10010 Sheet(s) 01 A00
1 Install : 281154A10010 Sheet(s) 01 A00
2 Modify the wiring 281154A10501 Sheet(s) 01 A00 281154A10501 Sheet(s) 06 A00 281154A10502 Sheet(s) 01 A00 281154A10502 Sheet(s) 03 A00 281154A10509 Sheet(s) 01 A00 281154A10509 Sheet(s) 02 A00 281154A10510 Sheet(s) 01 A00 281154A10510 Sheet(s) 02 A00 281154A10511 Sheet(s) 01 A00 281154A10511 Sheet(s) 02 A00 281154A10512 Sheet(s) 01 A00 281154A10512 Sheet(s) 02 A00 281154A10513 Sheet(s) 01 A00 281154A10513 Sheet(s) 02 A00 281154A10514 Sheet(s) 01 A00 281154A10514 Sheet(s) 02 A00

a Remove the wires : 281154A10510 Sheet(s) 02 A00 281154A10512 Sheet(s) 02 A00 b Install the wires : 281154A10501 Sheet(s) 06 A00 281154A10502 Sheet(s) 03 A00 281154A10509 Sheet(s) 02 A00 281154A10511 Sheet(s) 02 A00 281154A10513 Sheet(s) 02 A00 281154A10514 Sheet(s) 02 A00 supplied in : Bundle D9000095141495

c Attach the wires with : 60 Tie-Cable NSA935401-04 60 Tie-Cable NSA935401-05 120 Tie-Cable NSA935401-06 240 Tie-Cable NSA935401-08 (q) Modify the equipment and the wiring in the FWD Electronics Rack 90VU Refer to Kit 281154A10R01, Kit 281154A11R01 and Kit 281154A12R00

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 92
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Remove the Shelf 92VU

a From the Shelf 92VU, remove for access the computers 7QJ, 9QJ, 3QT and 1XG : (Refer to AMM 24-41-34, Page block 401) (Refer to AMM 28-42-34, Page block 401) (Refer to AMM 28-46-34, Page block 401) 1 FLSCU1 Retain 1 FLSCU2 Retain 1 FQIC Retain 1 GAPCU Retain NOTE : You must install these computers again after the modification of the wiring. b Put blanking caps on the disconnected connectors.

c Disconnect the bonding braid. d Remove the attachment hardware from the Shelf. NOTE : Retain the hardware.

e 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 Put blanking caps on the disconnected connectors.

c Disconnect the bonding braid. d Remove the attachment hardware from the Shelf. NOTE : Retain the hardware.

e Remove the Shelf 93VU and install it on bench.
3 Remove the Shelf 94VU

a From the Shelf 94VU, remove for access the computers 5GA2, 10GG and 10WQ : DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 93
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(Refer to AMM 26-17-34, Page block 401) (Refer to AMM 32-31-71, Page block 401) (Refer to AMM 32-42-34, Page block 401) 1 LGCIU2 Retain 1 BSCU Retain 1 SDCU Retain NOTE : You must install these computers again after the modification of the wiring. b Put blanking caps on the disconnected connectors.

c Disconnect the bonding braid. d Remove the attachment hardware from the Shelf. NOTE : Retain the hardware.

e Remove the Shelf 94VU and install it on bench.
4 On the Shelf 92VU

a Remove : 281154A11000 Sheet(s) 01 A00 281154A11001 Sheet(s) 01 A00 b Install : 281154A11002 Sheet(s) 01 A00 281154A11002 Sheet(s) 02 A00 281154A11003 Sheet(s) 01 A00 NOTE : The placards are supplied in : Placard Set D9100095116895

c Replace the Fuel Quantity Indicator Computer (FQIC) 3QT - Remove : 1 FQIC SIC5059-11-0207 - Install : 1 FQIC SIC5059-12-0308
5 On the Shelf 94VU

a Install : 281154A11004 Sheet(s) 01 A00 281154A11004 Sheet(s) 02 A00 NOTE : The placards are supplied in : DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 94
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Placard Set D9100095116895
6 Modify the wiring 281154A10501 Sheet(s) 01 A00 281154A10501 Sheet(s) 05 A00 281154A10502 Sheet(s) 01 A00 281154A10502 Sheet(s) 02 A00 281154A10503 Sheet(s) 01 B00 281154A10503 Sheet(s) 04 A00 281154A10504 Sheet(s) 01 A00 281154A10504 Sheet(s) 03 A00 281154A10506 Sheet(s) 01 A00 281154A10506 Sheet(s) 02 A00 281154A10507 Sheet(s) 01 B00 281154A10507 Sheet(s) 03 A00 281154A10508 Sheet(s) 01 A00 281154A10508 Sheet(s) 02 A00 281154A10515 Sheet(s) 01 A00 281154A10515 Sheet(s) 02 A00 281154A10516 Sheet(s) 01 A00 281154A10516 Sheet(s) 02 A00 281154A10517 Sheet(s) 01 A00 281154A10517 Sheet(s) 02 A00 281154A10518 Sheet(s) 01 B00 281154A10518 Sheet(s) 03 A00 281154A10519 Sheet(s) 01 A00 281154A10519 Sheet(s) 02 A00 281154A10520 Sheet(s) 01 A00 281154A10520 Sheet(s) 02 A00 281154A10521 Sheet(s) 01 A00 281154A10521 Sheet(s) 02 A00

a Remove the wires : 281154A10515 Sheet(s) 02 A00 281154A10517 Sheet(s) 02 A00 281154A10519 Sheet(s) 02 A00 281154A10520 Sheet(s) 02 A00 b Install the wires : 281154A10501 Sheet(s) 05 A00 281154A10502 Sheet(s) 02 A00 281154A10503 Sheet(s) 04 A00 281154A10504 Sheet(s) 03 A00 281154A10506 Sheet(s) 02 A00 281154A10507 Sheet(s) 03 A00 281154A10508 Sheet(s) 02 A00 281154A10516 Sheet(s) 02 A00 281154A10518 Sheet(s) 03 A00 281154A10521 Sheet(s) 02 A00 supplied in : DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 95
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Bundle D9000095141395

c Attach the wires with : 60 Tie-Cable NSA935401-04 60 Tie-Cable NSA935401-05 120 Tie-Cable NSA935401-06 240 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. d On the Shelf 92VU, install the computer 47QJ : (Refer to AMM 28-46-34, Page block 401) Refer to Kit 281154A12R00 1 FLSCU3 30042-0000-0501

e On the Shelf 92VU, install the computers 7QJ, 9QJ, 3QT and 1XG : (Refer to AMM 24-41-34, Page block 401) (Refer to AMM 28-42-34, Page block 401) (Refer to AMM 28-46-34, Page block 401) 1 FLSCU1 1 FLSCU2 1 FQIC 1 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. 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 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 96
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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. d On the Shelf 94VU, install the computers 5GA2, 10GG and 10WQ : (Refer to AMM 26-17-34, Page block 401) (Refer to AMM 32-31-71, Page block 401) (Refer to AMM 32-42-34, Page block 401) 1 LGCIU2 1 BSCU 1 SDCU NOTE : These computers were retained at removal. (r) Modify the wiring between the avionics compartment and the cockpit Refer to Kit 281154A10R01 281154A10501 Sheet(s) 01 A00 281154A10501 Sheet(s) 08 A00 281154A10503 Sheet(s) 01 B00 281154A10503 Sheet(s) 06 A00 281154A10505 Sheet(s) 01 A00 281154A10505 Sheet(s) 04 A00 281154A10507 Sheet(s) 01 B00 281154A10507 Sheet(s) 04 A00
1 Install the wires : 281154A10501 Sheet(s) 08 A00 281154A10503 Sheet(s) 06 A00 281154A10505 Sheet(s) 04 A00 281154A10507 Sheet(s) 04 A00 supplied in : Bundle D9000095141695 (s) Modify the wiring on the connectors 4065VC-A and 4066VC-A Refer to Kit 281154A10R01 and Kit 281154A13R00 281154A10501 Sheet(s) 01 A00 281154A10501 Sheet(s) 07 A00 281154A10502 Sheet(s) 01 A00 281154A10502 Sheet(s) 04 A00 281154A10503 Sheet(s) 01 B00 281154A10503 Sheet(s) 05 A00 281154A10504 Sheet(s) 01 A00 281154A10504 Sheet(s) 04 C00 281154A10508 Sheet(s) 01 A00 281154A10508 Sheet(s) 03 A00 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 97
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281154A10518 Sheet(s) 01 B00 281154A10518 Sheet(s) 04 A00
1 Install the wires : 281154A10501 Sheet(s) 07 A00 281154A10502 Sheet(s) 04 A00 281154A10503 Sheet(s) 05 A00 281154A10504 Sheet(s) 04 C00 281154A10508 Sheet(s) 03 A00 281154A10518 Sheet(s) 04 A00 supplied in : Bundle D9000095141595 and: Bundle D9000095147795 Attach the wires with : 50 Tie-Cable NSA935401-06 (t) Modify the wiring in the avionics compartment and in the FWD cargo compartment Refer to Kit 281154A10R01 281154A10501 Sheet(s) 01 A00 281154A10501 Sheet(s) 09 A00 281154A10502 Sheet(s) 01 A00 281154A10502 Sheet(s) 05 A00 281154A10503 Sheet(s) 01 B00 281154A10503 Sheet(s) 07 A00 281154A10505 Sheet(s) 01 A00 281154A10505 Sheet(s) 05 A00 281154A10506 Sheet(s) 01 A00 281154A10506 Sheet(s) 03 A00 281154A10507 Sheet(s) 01 B00 281154A10507 Sheet(s) 05 A00 281154A10509 Sheet(s) 01 A00 281154A10509 Sheet(s) 03 A00 281154A10518 Sheet(s) 01 B00 281154A10518 Sheet(s) 05 A00
1 Install the wires : 281154A10501 Sheet(s) 09 A00 281154A10502 Sheet(s) 05 A00 281154A10503 Sheet(s) 07 A00 281154A10505 Sheet(s) 05 A00 281154A10506 Sheet(s) 03 A00 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 98
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

DESIGN DRAWINGS SHEET(S) 281154A10507 Sheet(s) 05 A00 281154A10509 Sheet(s) 03 A00 281154A10518 Sheet(s) 05 A00 supplied in : Bundle D9000095141795 (u) Install the equipment for ACT pressurization system between FR46 and FR58. Refer to Kit 281154B01R00
1 Install the equipment for ACT pressurization system between FR46 and FR58. Refer to Drawing : D28271015 Sheet(s) 1, 5, 6 and 8 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 (v) In the FWD avionics compartment, install the relay logic box. Refer to Kit 281154B02R00
1 Install this item in the forward avionics compartment : Refer to Drawing : D92355000 Sheet(s) 1 D92556025 Sheet(s) 1 and 5 1 Relay Logic Box D9255602500800 Item 158 (w) Replace the refuel/defuel panel. Refer to Kit 281154B03R00 thru Kit 281154B04R00 Refer to Drawings : D92450341 Sheet(s) 1, 4 and 6 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 :

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 : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 99
Printed in France © AIRBUS 2008 All rights reservedSERVICE 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 the additional wiring between zone 192 and 132 :

a Remove the wire shown on line 3 of the Hook-up Chart (Refer to Figure 5, Sheet 1). b Install the wires shown on lines 1 thru 11 of the Hook-up Chart (Refer to Figure 5, Sheet 1) supplied in : 1 Bundle D9240000065595 and route them with the wires that are in the aircraft.

c Cut the wires to the necessary length, crimp the terminals and connect them. d Do an intrinsically safe continuity test of the new wires.

e Attach the wires with tie-wraps as necessary.
3 Install the new refuel/defuel panel mounting assembly in the belly fairing, zone 192 :

a Use a non-metallic scraper to remove the sealant. Clean the areas with Solvent General Purpose (Mat. No. 11-026). b Use Corrosion Inhibiting Brush Consistency (Mat. No. 09-013) to wet assemble the refuel panel mounting-assembly and position it in the belly fairing. Use the attachment bolts retained from removal to 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 this refuel/defuel control panel 800VU (Refer to AMM 28-25-55, Page block 401) : 1 Panel Assy-Refuel D9255003200400

f Install this fuel quantity indicator unit 6QT (Refer to AMM 28-42-22, Page block 401) : 1 Indicator-Fuel 1422KID02-03 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 100
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

g Install this ACT refuel panel assembly 801VU : 1 Panel Assy-Refuel D9255002500000 (x) Remove the inflation reservoirs 7506MM and 7507MM, for the LH and RH offwing escape slides. Refer to AMM 25-62-46, Page block 401 Refer to drawing(s) : D25690000004 Sheet(s) 7 thru 9 (y) Remove and retain the cargo nets from the AFT cargo compartment. (Refer to AMM 25-55-00, Page block 001). Refer to drawing(s) : D25572592000 Sheet(s) 1 (z) In the AFT cargo compartment, remove the placards from the sidewall panels. Refer to drawing(s) : D25572592004 Sheet(s) 3 (aa) In the AFT cargo compartment, remove the placards for the inflation reservoir access. Refer to drawing(s) : D25573522000 Sheet(s) 1 (ab) Install the MOD/SB placards on the new and modified wires. Refer to Kit 281154D14R01 Refer to drawing(s) : D92894713084 Sheet(s) 1 (ac) In the passenger compartment between FR41 and FR46, LH and RH, modify the harnesses 5339VB and 5340VB. Refer to Kit 281154D15R00 Refer to drawing(s) : D92894736004 Sheet(s) 14 thru 17 D92992293014 Sheet(s) 16 D92992293016 Sheet(s) 17 D92992293038 Sheet(s) 42 D92992293040 Sheet(s) 43 (ad) Between FR45 and FR47/51 (LH and RH), install the reservoirs and the associated pressure tubes for the offwing escape slides. Refer to Kit 281154D13R00
1 When you accomplish this workstep, rem ove, modify and install the insulation blankets after the bracket installation. For the re-identification of the insulation blankets, refer to paragraph 2.E. DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 101
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

2 Install the support brackets for the reservoirs and associated pressure tubes for the offwing escape slide system. Refer to drawing(s) : D25670762000 Sheet(s) 1 thru 7 NOTE : Use the consumable materials that follow, for the corrosion protection : - Internal Polyurethane Varnish (Mat. No. 07-017) - Anti-Corrosion Primer (Mat. No. 16-006F) - Flexible Polyurethane (Mat. No. 16-021).
3 Install the pressure tubes between FR45 and FR47/51 (LH and RH). Refer to drawing(s) : D25671745000 Sheet(s) 1 thru 7 NOTE : This drawing contains the consumable material : - Putty, Zinc Chromate General Purpose (Mat. No. 05-002).
4 Install the inflation reservoirs 7784MM and 7788MM Refer to drawing(s) : D25671746000 Sheet(s) 1 thru 4 NOTE : This drawing contains the consumable material : - Synth. Ester Based Grease, High Pressure (Mat. No. 04-004). (ae) Replace the Overhead Stowage Compartments (OHSC) between FR43 and FR47/51. Refer to Kit 281154D11R01 Refer to Kit 281154D12R00
1 Replace the OHSCs. Refer to Kit 281154D11R01 (Refer to AMM 25-24-41, Page block 401). Refer to drawing(s) : D25286364014 Sheet(s) 7 and 8
2 Replace the placards on the doors of the OHSCs. Refer to Kit 281154D12R00 Refer to drawing(s) : D25288767000 Sheet(s) 1 and 2 (af) Relocate the release cables for the LH and RH offwing escape slides. Refer to Kit 281154D16R02 Refer to AMM 25-62-43, Page block 401

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 102
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Relocate and adjust the flexible control assembly for the LH offwing escape slide. Refer to drawing(s) : D53370297002 Sheet(s) 1 thru 4 and 6 thru 12 D53375751004 Sheet(s) 7 NOTE : This drawing contains these consumable materials : - Synth. Ester Based Grease, High Pressure (Mat. No. 04-004) - Conductive Film (Mat. No. 05-099) - Adhesive (Mat. No. 08-048) - Corrosion Inhibitive Interfay Sealant (Mat. No. 09-005) - Lockwire LN9424A100. NOTE : Use the consumable material that follows, for the corrosion protection : - Pure Mineral Vaseline (Mat. No. 04-012) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013).
2 Relocate and adjust the flexible control assembly for the RH offwing escape slide. Refer to drawing(s) : D53370297003 Sheet(s) 1 thru 12 NOTE : This drawing contains these consumable materials : - Synth. Ester Based Grease, High Pressure (Mat. No. 04-004) - Conductive Film (Mat. No. 05-099) - Adhesive (Mat. No. 08-048) - Corrosion Inhibitive Interfay Sealant (Mat. No. 09-005) - Lockwire LN9424A100. NOTE : Use the consumable material that follows, for the corrosion protection : - Pure Mineral Vaseline (Mat. No. 04-012) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013). (ag) Install the ACT structural provisions in the center fuselage. Refer to Kit 281154D05R02 Refer to drawing(s) : D53372385000 Sheet(s) 1 thru 7 NOTE : Use the consumable material that follows, for the corrosion protection : - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013). For access remove/install : (ah) Install the angles on the webs of the keel beam, between FR42 and FR46. Refer to Kit 281154D07R00 Refer to drawing(s) : D53370780004 Sheet(s) 2 NOTE : Use the consumable materials that follow, for the corrosion protection : - Internal Polyurethane Varnish (Mat. No. 07-017). DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 103
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

- Transparent Protective Coating (Mat. No. 07-023) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013) - Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016) - Anti-Corrosion Primer (Mat. No. 16-006F). (ai) Remove the center beams between FR52 to FR55 from the AFT cargo compartment. NOTE : The center beams (sections), PN D5347034000800, Item 91, were installed with Service Bulletin No. A320-25-1427. (aj) Install the ACT structural provisions in the AFT cargo compartment, between FR52 and FR63. Refer to Kit 281154D06R04 Refer to drawing(s) : D53476032000 Sheet(s) 1 thru 27 NOTE : Use the consumable materials that follow, for the corrosion protection : - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013) - Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016) - Transparent Protective Coating (Mat. No. 07-023) - Flexible Polyurethane (Mat. No. 16-021) - Anti-Corrosion Primer (Mat. No. 16-006F). (ak) Replace the fasteners between FR42 and FR44 (LH). Refer to Kit 281154D62R00 Refer to drawing(s) : D53371236000 Sheet(s) 1 NOTE : Install the rivets with : - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013). (al) Replace the fasteners between FR42 and FR44 (RH). Refer to Kit 281154D63R00 Refer to drawing(s) : D53371236001 Sheet(s) 1 NOTE : Wet install the rivets with Corrosion Inhibiting Brush Consistency (Mat. No. 09-013). (am) Replace the belly fairing panel 197AB and do the modification to the attachment structure. Refer to Kit 281154D04R01 Refer to drawing(s) : D53475023000 Sheet(s) 1 thru 4 NOTE : For the electrical bonding points, use the consumable materials that follow : - Electrical Bonding Coating (Blue Color) (Mat. No. 07-001) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013) DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 104
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

- Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016). NOTE : Use these consumable materials, for the installation of components: - Putty, Zinc Chromate General Purpose (Mat. No. 05-002) - Transparent Protective Coating (Mat. No. 07-023) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013) - Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016). NOTE : Use these consumable materials for the re-protection of the reworked frames : - Internal Polyurethane Varnish (Mat. No. 07-017) - Anti-Corrosion Primer (Mat. No. 16-006F) - Wash Primer (Mat. No. 16-020A). (an) Install the placards on the belly fairing panel 197AB. Refer to Kit 281154D01R00 Refer to drawing(s) : D11277100197 Sheet(s) 67 (ao) Install the roller tracks and do the adjustment of the YZ and the XZ latches. Refer to Kit 281154D80R00 Refer to drawing(s) : D25572207000 Sheet(s) 1 thru 7 NOTE : For the adjustment of the latches, use the latch adjustment tool 98D28108641000. NOTE : Refer to paragraph (1) (bv) and paragraph (1) (ap) for the roller track levelling. NOTE : After the adjustment of the XZ latches at FR54, tag the latch pawls to shown their installation location. Remove and retain the latch pawls and the attachment hardware for the future installation of the ACT. Do not remove the adaptor plates. NOTE : After drilling the roller tracks, re-protect with : - Internal Polyurethane Varnish (Mat. No. 07-017) - Anti-Corrosion Primer (Mat. No. 16-006F) - Wash Primer (Mat. No. 16-020). NOTE : Use the consumable materials that follow, for the corrosion protection : - Pure Mineral Vaseline (Mat. No. 04-012) - Putty, Zinc Chromate General Purpose (Mat. No. 05-002) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013) - Corrosion Preventive Temporary Protective Compound (Mat. No. 15-008) - Corrosion Preventive Temporary Protective Compound (Mat. No. 15-009). (ap) Install the shim plates, as required, after the results of the roller track levelling. Refer to Kit 281154D81R01 Refer to drawing(s) : DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 105
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

D25572676034 Sheet(s) 18 NOTE : The quantity of shims at each position is dependant on the results of the roller track levelling. Refer to paragraph (1) (bv). NOTE : Use the consumable materials that follow, for the corrosion protection : - Pure Mineral Vaseline (Mat. No. 04-012) - Putty, Zinc Chromate General Purpose (Mat. No. 05-002) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013). (aq) Apply the corrosion preventative to the roller tracks. Refer to drawing(s) : D25572672032 Sheet(s) 17 NOTE : Use the consumable materials that follow, for the corrosion protection : - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013) - Corrosion Inhibiting Low Adhesion Sealant (Mat. No. 09-018) - Corrosion Preventive Temporary Protective Compound (Mat. No. 15-009). (ar) Install the covers on the roller tracks and the YZ latches. Refer to Kit 281154D84R00 Refer to drawing(s) : D25572592012 Sheet(s) 7 NOTE : Install the fasteners with Putty, Zinc Chromate General Purpose (Mat. No. 05-002). NOTE : After installation, apply Corrosion Preventive Temporary Protective Compound (Mat. No. 15-009). (as) In the AFT cargo compartment at FR54, install the tie-down points. Refer to Kit 281154D82R01 Refer to drawing(s) : D25572592006 Sheet(s) 4 NOTE : Use the consumable materials that follow, for the corrosion protection : - Putty, Zinc Chromate General Purpose (Mat. No. 05-002) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013) - Low Adhesion Sealant MC216A. (at) In the AFT cargo compartment, replace the plates on the floor crossbeams at FR54 and FR55 and the attachment structure for the FR47 partition panels. Refer to Kit 281154D76R00 Refer to drawing(s) : D53975027000 Sheet(s) 1 thru 6 NOTE : Use the consumable materials that follow, for the corrosion protection : - Transparent Protective Coating (Mat. No. 07-023) - Corrosion Inhibitive Interfay Sealant (Mat. No. 09-005) DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 106
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

- Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016). (au) In the AFT cargo compartment, replace the floor panels 151PE, 151VG, 151ZG and 151CE. Refer to Kit 281154D73R00 Refer to Kit 281154D74R01 Refer to AMM 53-42-14, Page block 401.
1 Replace the floor panels in the AFT cargo compartment between FR47/51 and FR59. Refer to Kit 281154D73R00 Refer to drawing(s) : D53675516002 Sheet(s) 4 thru 6 NOTE : Install the fasteners with Putty, Zinc Chromate General Purpose (Mat. No. 05-002).
2 Seal the gaps between the floor panels. Refer to Kit 281154D74R01 Refer to drawing(s) : D53672231058 Sheet(s) 23 thru 25 D53672231108 Sheet(s) 26 NOTE : These drawings contain the consumable material : - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013). (av) In the AFT cargo compartment, replace the floor panels 151TG, 151AE, 151DE, 151GE, 152TG and 152WG. Refer to Kit 281154D75R00 Refer to AMM 53-42-14, Page block 401. Refer to drawing(s) : D53675526002 Sheet(s) 4 thru 6 NOTE : Install the fasteners with Putty, Zinc Chromate General Purpose (Mat. No. 05-002). (aw) Replace the insulation blankets on the AFT face of the bulkhead at FR46 Refer to Kit 281154D10R00 Refer to AMM 25-80-00, Page block 201. Refer to drawing(s) : D25870003050 Sheet(s) 28 (ax) In the AFT cargo compartment, replace the ceiling panels 151EC, 151FC and 151GC. Refer to Kit 281154D30R00

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 107
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to AMM 25-55-11, Page block 401. Refer to drawing(s) : D25571077000 Sheet(s) 1 (ay) In the AFT cargo compartment, replace the LH sidewall panels 151SW, 151TW, 151UW and 151VW. Refer to Kit 281154D31R01 Refer to AMM 25-55-11, Page block 401. Refer to drawing(s) : D25571077002 Sheet(s) 2 (az) In the AFT cargo compartment, replace the RH sidewall panels 152CW and 152DW. Refer to Kit 281154D32R00 Refer to AMM 25-55-11, Page block 401. Refer to drawing(s) : D25571077004 Sheet(s) 3 (ba) Install the placards on the sidewall panels in the AFT cargo compartment. Refer to Kit 281154D83R00 Refer to drawing(s) : D25572592010 Sheet(s) 6 (bb) In the AFT cargo compartment, replace the FR47/51 partition panels 151BW, 151AW and 152BW. Refer to Kit 281154D33R00 Refer to AMM 25-55-11, Page block 401. Refer to drawing(s) : D25571077006 Sheet(s) 4 (bc) In the passenger compartment, replace the floor panels 241JF, 251GF, 251FF, 252GF and 252HF. Refer to Kit 281154D71R00 Refer to AMM 53-32-12, Page block 401 Refer to AMM 53-42-12, Page block 401 Refer to drawing(s) : D53675024000 Sheet(s) 1 thru 3 NOTE : Install the fasteners with Putty, Zinc Chromate General Purpose (Mat. No. 05-002). (bd) Seal the gaps between the passenger compartment floor-panels 241JF, 251GF, 251FF, 252GF and 252HF. DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 108
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Refer to Kit 281154D72R00 Refer to drawing(s) : D53675023000 Sheet(s) 1 thru 2 NOTE : This drawing contains the consumable material : - Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016). (be) Install the fuel transfer and fuel vent lines. Refer to Kit 281154D41R00 Refer to Kit 281154D61R00
1 Do the modification to the passenger-compartment floor structure between FR42 and FR46. Refer to Kit 281154D61R00 Refer to drawing(s) : D53371072000 Sheet(s) 1 thru 6 NOTE : Use the consumable materials that follow, for the corrosion protection : - Putty, Zinc Chromate General Purpose (Mat. No. 05-002) - Electrical Bonding Coating (Blue Color) (Mat. No. 07-001) - Wash Primer (Mat. No. 16-020) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013) - Anti-Corrosion Primer (Polyurethane) (Mat. No. 16-001) - External Top Coat (Polyurethane) (Mat. No. 16-018).
2 Install the fuel vent line between FR37 and FR47/51 and the fuel transfer line between FR41 and FR47/51. Refer to Kit 281154D41R00 Refer to drawing(s) : D28271012000 Sheet(s) 1 thru 6 NOTE : This drawing contains the consumable material : - Lockwire, 0.6 mm Dia. (Mat. No. 19-018). (bf) Install the shroud drain system between FR37 and FR52. Refer to Kit 281154D21R00 Refer to Kit 281154D42R00
1 Install the support brackets for the shroud drain line on the support bracket for the Green hydraulic reservoir. Refer to Kit 281154D21R00 Refer to drawing(s) : D93070668000 Sheet(s) 1 thru 8 NOTE : Use the consumable materials that follow, for the corrosion protection : - Internal Polyurethane Varnish (Mat. No. 07-017) DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 109
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

- Transparent Protective Coating (Mat. No. 07-023) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013) - Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016) - Anti-Corrosion Primer (Mat. No. 16-006F).
2 Install the shroud drain lines between FR37 and FR52. Refer to Kit 281154D42R00 Refer to drawing(s) : D28271013000 Sheet(s) 5 NOTE : This drawing contains the consumable material : - Two Component Epoxy Adhesive (Mat. No. 08-010) - Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016). NOTE : Use the consumable materials that follow, for the corrosion protection : - Pure Mineral Vaseline (Mat. No. 04-012) - Transparent Protective Coating (Mat. No. 07-023) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013). (bg) Install the ACT pressurization and the cavity drain and monitoring systems. Refer to Kit 281154D43R00 Refer to Kit 281154D44R01 Refer to Kit 281154D45R00
1 Install the support brackets for the ACT pressurization system between FR54 and FR58. Refer to Kit 281154D45R00 Refer to drawing(s) : D28271016002 Sheet(s) 1 thru 5, 7 thru 12 NOTE : Wet install the non removable fasteners (except at the bonding points) with Corrosion Inhibiting Brush Consistency (Mat. No. 09-013). NOTE : Install the removable fasteners (except at the bonding points) with Putty, Zinc Chromate General Purpose (Mat. No. 05-002).
2 Install the cavity drain and monitoring system between FR46 and FR54. Refer to Kit 281154D43R00 Refer to drawing(s) : D28271014000 Sheet(s) 1 thru 3 NOTE : This drawing contains the consumable materials : - Two Component Epoxy Adhesive (Mat. No. 08-010) - Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016).

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 110
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

NOTE : Use the consumable materials that follow, for the corrosion protection : - Pure Mineral Vaseline (Mat. No. 04-012) - Transparent Protective Coating (Mat. No. 07-023) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013).
3 Install the ACT pressurization system between FR52 and FR58. Refer to Kit 281154D44R01 Refer to drawing(s) : D28271015000 Sheet(s) 1 thru 8 NOTE : The Items 0041 thru 0047 referenced on this drawing are supplied and installed with Kit 281154B01R00. Refer to paragraph (1) (u) 1

. NOTE : This drawing contains the consumable materials : - Two Component Epoxy Adhesive (Mat. No. 08-010). NOTE : Use the consumable materials that follow, for the corrosion protection : - Pure Mineral Vaseline (Mat. No. 04-012) - Putty, Zinc Chromate General Purpose (Mat. No. 05-002) - Transparent Protective Coating (Mat. No. 07-023) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013). (bh) Install the protective shield for the fuel transfer and fuel vent lines. Refer to Kit 281154D46R00 Refer to Kit 281154D47R00
1 Install the support beam between FR46 and FR47/51. Refer to Kit 281154D46R00 Refer to drawing(s) : D28270998002 Sheet(s) 2 NOTE : Use the consumable materials that follow, for the corrosion protection : - Transparent Protective Coating (Mat. No. 07-023) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013) - Anti-Corrosion Primer (Mat. No. 16-006F) - Flexible Polyurethane (Mat. No. 16-021)
2 Install the protective shield between FR46 and FR47/51 over the fuel transfer and fuel vent lines. Refer to Kit 281154D47R00 Refer to drawing(s) : D28270999004 Sheet(s) 3

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 111
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

NOTE : Install the fasteners with Putty, Zinc Chromate General Purpose (Mat. No. 05-002). (bi) Replace the fuel drain line between FR42 and FR47/51. Refer to Kit 281154D48R00 Refer to drawing(s) : D28270515000 Sheet(s) 1 thru 4 (bj) Install the support brackets and do the modification to the floor structure at FR42, FR53, FR54 and FR58. Refer to Kit 281154D78R02 Refer to drawing(s) : D92492872002 Sheet(s) 14 thru 17 NOTE : This drawing contains the consumable material : - Electrical Bonding Coating (Blue Color) (Mat. No. 07-001). NOTE : Use the consumable materials that follow, for the corrosion protection : - Internal Polyurethane Varnish (Mat. No. 07-017) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013) - Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016) - Anti-Corrosion Primer (Mat. No. 16-006F) - Flexible Polyurethane (Mat. No. 16-021). (bk) Replace the cable guides between FR41 and FR42. Refer to Kit 281154D79R00 Refer to drawing(s) : D92492871002 Sheet(s) 6 (bl) Replace the support bracket at FR42. Refer to Kit 281154D79R00 Refer to drawing(s) : D92492871004 Sheet(s) 7 thru 9 NOTE : This drawing contains the consumable materials : - Putty, Zinc Chromate General Purpose (Mat. No. 05-002) - Electrical Bonding Coating (Blue Color) (Mat. No. 07-001) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013). (bm) Do the modification to the bracket installation between FR46 and FR56. Refer to Kit 281154D78R02 Refer to drawing(s) : D92492872000 Sheet(s) 1 thru 13 NOTE : Use the consumable materials that follow, for the corrosion protection : - Electrical Bonding Coating (Blue Color) (Mat. No. 07-001)Internal Polyurethane Varnish (Mat. No. 07-017) - Transparent Protective Coating (Mat. No. 07-023) DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 112
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

- Corrosion Inhibiting Brush Consistency (Mat. No. 09-013) - Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016) - Anti-Corrosion Primer (Mat. No. 16-006F). (bn) Do the modification to the bracket installation between FR46 and FR52 and at FR54. Refer to Kit 281154D79R00 Refer to drawing(s) : D92492871000 Sheet(s) 1 thru 5 NOTE : This drawing contains the consumable materials : - Putty, Zinc Chromate General Purpose (Mat. No. 05-002) - Electrical Bonding Coating (Blue Color) (Mat. No. 07-001) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013). (bo) Do the modification to the attachment parts for the cable harnesses between FR46 thru FR55. Refer to Kit 281154D77R02 Refer to drawing(s) : D92891825000 Sheet(s) 1 thru 28 NOTE : This drawing contains the consumable materials : - Putty, Zinc Chromate General Purpose (Mat. No. 05-002) - Electrical Bonding Coating (Blue Color) (Mat. No. 07-001) - Transparent Protective Coating (Mat. No. 07-023) - Two Component Epoxy Adhesive (Mat. No. 08-010) - Two Component Polyurethane Adhesive (Mat. No. 08-025) - Adhesive (Mat. No. 08-048) - Corrosion Inhibiting Brush Consistency (Mat. No. 09-013) - Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016) - Varnish, RAL3000 WL570510. (bp) Do the modification to the attachment parts for the cable harnesses at FR42 and in the AFT cargo compartment at FR52 thru FR54, FR56, FR58 and FR59. Refer to Kit 281154D77R02 Refer to drawing(s) : D92891825002 Sheet(s) 29 thru 43 NOTE : This drawing contains the consumable materials : - Low Adhesion Corrosion Inhibiting Sealant (Mat. No. 09-019) - Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016) - General Purpose Dimethacrylate Green (Mat. No. 08-002). (bq) Do the modification to the attachment parts for the cable harnesses at FR42. Refer to Kit 281154D77R02 Refer to drawing(s) : D92891825004 Sheet(s) 44 thru 49 NOTE : This drawing contains the consumable materials : - Electrical Bonding Coating (Blue Color) (Mat. No. 07-001) DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 113
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

- Two Component Epoxy Adhesive (Mat. No. 08-010) - Adhesive (Mat. No. 08-048) - Lockwire, 0.5 mm Dia. (Mat. No. 19-009) - Varnish, RAL3000 WL570510. (br) Install/modify the cable harnesses and install the MOD/SB placards. Refer to Kit 281154D02R00
1 Replace the cable harness 4605VB. Refer to drawing(s) : D92996405000 Sheet(s) 1 D92996405001 Sheet(s) 2 and H001
2 Do the modification to the cable harness 4606VB. Refer to drawing(s) : D92997046001 Sheet(s) 1 and 2
3 Do the modification to the cable harness 4607VB. Refer to drawing(s) : D92997046002 Sheet(s) 3 thru 5
4 Do the modification to the cable harness 4609VB. Refer to drawing(s) : D92997046003 Sheet(s) 6 thru 9
5 Do the modification to the cable harness 4628VB. Refer to drawing(s) : D92997046004 Sheet(s) 10 thru 20
6 Do the modification to the cable harness 4640VB. Refer to drawing(s) : D92997046005 Sheet(s) 21 and 22
7 Do the modification to the cable harness 4644VB. Refer to drawing(s) : D92997046006 Sheet(s) 23 and 24
8 Do the modification to the cable harness 4650VB. Refer to drawing(s) : D92997046007 Sheet(s) 25 and 26
9 Do the modification to the cable harness 5609VB. Refer to drawing(s) : D92997046008 Sheet(s) 27 thru 30, 32 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 114
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 0 Do the modification to the cable harness 5662VB. Refer to drawing(s) : D92997046009 Sheet(s) 33 and 34
1 1 Do the modification to the cable harness 5663VB. Refer to drawing(s) : D92997046010 Sheet(s) 35 thru 37
1 2 Do the modification to the cable harness 5664VB. Refer to drawing(s) : D92997046011 Sheet(s) 38 thru 40
1 3 Do the modification to the cable harness 5670VB. Refer to drawing(s) : D92997046012 Sheet(s) 41 and 42
1 4 Do the modification to the cable harness 5675VB. Refer to drawing(s) : D92997046013 Sheet(s) 43 and 44
1 5 Replace the cable harness 4655VB. Refer to drawing(s) : D92996455000 Sheet(s) 1 and H000 D92996455001 Sheet(s) 2 and H001
1 6 Replace the cable harness 4661VB. Refer to drawing(s) : D92996461008 Sheet(s) 9 and H008 D92996461009 Sheet(s) 10 and H009
1 7 Replace the cable harness 4662VB. Refer to drawing(s) : D92996462000 Sheet(s) 1 and H000 D92996462001 Sheet(s) 2 and H001
1 8 Replace the cable harness 4663VB. Refer to drawing(s) : D92996463000 Sheet(s) 1 and H000 D92996463001 Sheet(s) 2 and H001
1 9 Replace the cable harness 4664VB. Refer to drawing(s) : D92996464000 Sheet(s) 1 and H000 DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 115
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

D92996464001 Sheet(s) 2 and H001
2 0 Replace the cable harness 4670VB. Refer to drawing(s) : D92996470002 Sheet(s) 3 and H002 D92996470003 Sheet(s) 4 and H003
2 1 Replace the cable harness 4671VB. Refer to drawing(s) : D92996471002 Sheet(s) 3 and H002 D92996471004 Sheet(s) 5 and H004
2 2 Replace the cable harness 4672VB. Refer to drawing(s) : D92996472006 Sheet(s) 7 and H006 D92996472007 Sheet(s) 8 and H007
2 3 Replace the cable harness 4673VB. Refer to drawing(s) : D92996473000 Sheet(s) 1 and H000 D92996473001 Sheet(s) 2 and H001
2 4 Replace the cable harness 4675VB. Refer to drawing(s) : D92996475001 Sheet(s) 2 and H001 D92996475003 Sheet(s) 4 and H003
2 5 Replace the cable harness 4680VB. Refer to drawing(s) : D92996480003 Sheet(s) 4 and H003 D92996480004 Sheet(s) 5 and H004
2 6 Replace the cable harness 4681VB. Refer to drawing(s) : D92996481000 Sheet(s) 1 and H000 D92996481001 Sheet(s) 2 and H001
2 7 Replace the cable harness 4683VB. Refer to drawing(s) : D92996483000 Sheet(s) 1 and H000 D92996483001 Sheet(s) 2 and H001
2 8 Replace the cable harness 4692VB. Refer to drawing(s) : DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 116
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

D92996492002 Sheet(s) 3 and H002 D92996492003 Sheet(s) 4 and H003
2 9 Replace the cable harness 4693VB. Refer to drawing(s) : D92996493000 Sheet(s) 1 and H000 D92996493001 Sheet(s) 2 and H001
3 0 Replace the cable harness 4694VB. Refer to drawing(s) : D92996494000 Sheet(s) 1 and H000 D92996494001 Sheet(s) 2 and H001
3 1 Replace the cable harness 4696VB. Refer to drawing(s) : D92996496000 Sheet(s) 1 and H000 D92996496001 Sheet(s) 2 and H001
32 Install the MOD/SB placards on the new and modified wires. Refer to drawing(s) : D92891821016 Sheet(s) 17 (bs) Replace the harnesses 4225VB, 4226VB and 4227VB. Refer to Kit 281154D17R02
1 Between FR37 and FR70, replace the harness 4225VB. Refer to drawing(s) : D92894721006 Sheet(s) 10 thru 16 D92995625002 Sheet(s) 4 and H002 D92995625008 Sheet(s) 9 and H008
2 Between FR52 and FR70, replace the harness 4226VB. Refer to drawing(s) : D92894721006 Sheet(s) 10 thru 16 D92995626002 Sheet(s) 5 and H002 D92995626006 Sheet(s) 10 and H006
3 Between FR41 and FR70, replace the harness 4227VB. Refer to drawing(s) : D92894721006 Sheet(s) 10 thru 16 D92995627002 Sheet(s) 4 and H002 D92995627006 Sheet(s) 7 and H006 (bt) Reroute the harness 4232VB. Refer to Kit 281154D17R02

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 117
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 Between FR30 and FR71, reroute the harness 4232VB. Refer to drawing(s) : D92894748008 Sheet(s) 32 thru 36 D92999571004 Sheet(s) 3 and 4 and H004 (bu) Do the modification to the routing of the hydraulic lines between FR46 and FR55. Refer to Kit 281154D50R00 (Refer to AMM 20-23-11, Page block 201). Refer to drawing(s) : D93470502000 Sheet(s) 1 thru 6 NOTE : This drawing contains the consumable materials : - Adhesive Sealant (Mat. No. 08-004) - External Top Coat (Polyurethane) (Mat. No. 16-018). NOTE : Use the consumable materials that follow for the corrosion protection : - Putty, Zinc Chromate General Purpose (Mat. No. 05-002) - Electrical Bonding Coating (Blue Color) (Mat. No. 07-001) - Internal Polyurethane Varnish (Mat. No. 07-017) - Transparent Protective Coating (Mat. No. 07-023) - Corrosion Inhibitive Interfay Sealant (Mat. No. 09-005) - Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016) - Anti-Corrosion Primer (Mat. No. 16-006F). (bv) Do the levelling of the cargo roller tracks. Refer to drawing(s) : D25573525008 Sheet(s) 17 thru 20 (bw) Install the cargo nets in the AFT cargo compartment. (Refer to AMM 25-55-00, Page block 001). Refer to drawing(s) : D25572592014 Sheet(s) 8 NOTE : The cargo nets were retained at the removal procedure. (2) Config. 01 , ADDITIONAL WORK If this Service Bulletin has been accomplished before Revision No. 01, it is necessary to do the additional work as described in this paragraph. Aircraft modified per Revision No. 01 or later revisions are not affected by the additional work described in this paragraph. (a) Make sure that the aircraft is electrically grounded, (Refer to AMM 12-34-24, Page block 201). (b) Put the access platform(s) in position. (c) Open the avionics door 811, (Refer to AMM 52-41-00, Page block 201). (d) Open the cargo door 825, (Refer to AMM 52-30-00, Page block 201). DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 118
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(e) In the forward cargo compartment, remove the panels 131AC, 131AW, 131BW, 131CW, 131DW, 132AW, 131HC, 131LC, 131MC, 131BC and 131CC, (Refer to AMM 06-41-53, Page block 1 and AMM 25-54-11, Page block 401). (f) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION 121VU ACT1/XFR VALVE/AUTO CTL 9QH 29 P 121VU ACT1/REFUEL/VLV 33QU 29 L (g) Replace the wire 2828-0036 between the connectors 1945VC and 4065VC Refer to Kit 281154A13R00 281154A10504 Sheet(s) 04 C00
1 Install the wire 281154A10504 Sheet(s) 04 C00 supplied in: Bundle D9000095147795 (h) Attach the wires with : 50 Tie-Cable NSA935401-06 (i) Make sure that the work areas are clean and clear of tools and other items of equipment. (j) Remove the safety clip(s) and tag(s) and close this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION 121VU ACT1/XFR VALVE/AUTO CTL 9QH 29 P 121VU ACT1/REFUEL/VLV 33QU 29 L (k) In the forward cargo compartment, install the panels 131AC, 131AW, 131BW, 131CW, 131DW, 132AW, 131HC, 131LC, 131MC, 131BC and 131CC, (Refer to AMM 06-41-53, Page block 1 and AMM 25-54-11, Page block 401). (l) Close the avionics door 811, (Refer to AMM 52-41-00, Page block 201). (m) Close the cargo door 825, (Refer to AMM 52-30-00, Page block 201). (n) Remove the access platform(s). (o) Restore the systems and the aircraft to normal operating condition. **C. T E**  **S T**  (1) Config. 01

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 119
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(a) Job Set-up
1 Install the cover 148AZ (Refer to AMM 57-17-11, Page block 401).
2 On each connector that you disconnected, do a visual check to make sure that : (Refer to ESPM 20-52-10) - The label of the plug is the same as the label on the receptacle - The plug is correctly locked.
3 Connect the battery connectors

a For the job set-up, refer to the removal/installation of the batteries (Refer to AMM 24-38-51, Page block 401). b Remove the blanking caps from the electrical connectors.

c Make sure that the electrical connectors are clean and in a correct condition. d Connect the connectors to the battery.

e Turn the knurled nut a quarter turn.
4 Remove all the warning notices.
5 Energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page block 201). (b) Preliminary tests NOTE : If the aircraft is operated in CAT3 conditions, you must also do the LAND CAT3 capability test (Refer to AMM 22-97-00, Page block 501).
1 Do the operational test of the instrument and panel integral lighting (Refer to AMM 33-13-00, Page block 501).
2 Do the operational test of the annunciator light test system in the cockpit (Refer to AMM 33-14-00, Page block 501).
3 Do the operational test of the avionics equipment ventilation system (Refer to AMM 21-26-00, Page block 501).
4 Do the operational test of the AFS (Refer to AMM 22-96-00, Page block 501).
5 Do the operational test of the EIS (Refer to AMM 31-60-00, Page block 501).
6 Do the operational test of the ECAM control panel (Refer to AMM 31-50-00, Page block 501).
7 Do the ground scanning of the central warning system (Refer to AMM 31-50-00, Page block 501). (c) Tests DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 120
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

1 In the Rear C/B Panel 121VU, do a voltage check at pin 2 of each circuit breaker that follows, to make sure that there is 28VDC voltage : 2EN1, 9QH, 2GG, 2WZ, 52QJ, 1832GQ, 2RC2, 30QH, 8CV, 2QT, 51QJ, 3GS, 2QU and 33QU.
2 In the Rear C/B Panel 121VU, do a voltage check at pin 2 of each circuit breaker that follows, to make sure that there is 115VAC voltage : 11WT2, 3JH2 and 10WT2.
3 In the Rear C/B Panel 121VU, do a voltage check at pins A2, B2 and C2 of each circuit breaker that follows, to make sure that there is 115VAC voltage : 30QA and 25QH.
4 Tests after the removal/installation of the items of equipment

a Do a leak check on the affected hydraulic pipes after removal/installation, (Refer to AMM 29-00-00, Page block 601). b Do a leak check on the air conditioning distribution ducts after removal/installation (Refer to AMM 21-20-00, Page block 401and AMM 12-33-21, Page block 201).

c Do the bleeding of the normal braking at brake units after removal/installation of hydraulic pipes, (Refer to AMM 32-42-00, Page block 301). d Do the tension check of the free fall extension cables after removal/installation of the torque tube assemblies (Refer to AMM 32-33-00, Page block 601).

e Do the functional check of the free fall extension system after removal/installation of the torque tube assemblies (Refer to AMM 32-33-00, Page block 501). f After removal/installation of the offwing escape-slides, do the operational test of the emergency lighting system (Refer to AMM 33-51-00, Page block 501).
g After removal/installation do the test of the SDAC (1WV1), (1WV2) (Refer to AMM 31-50-00, Page block 501).
h After the removal/installation of the Slat and Flap Control Computer (SFCC) (21CV), (22CV), (Refer to AMM 27-51-34, Page block 401) : - Do the BITE test of the SFCC (flap system) (Refer to AMM 27-51-00, Page block 501). - Do the BITE test of the SFCC (slat system) (Refer to AMM 27-81-00, Page block 501). - Do the operational test of the flap and slat (Refer to AMM 27-54-00, Page block 501). DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 121
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

i After removal/installation of the (GCU)-1(2) (1XU1, 1XU2) : - Do the operational test of the GPCU (Refer to AMM 24-41-00, Page block 501).
5 Test after the disconnection/connection of the connectors 43VC, 112VC, 202VC, 208VC, 210VC, 212VC, 216VC, 218VC, 220VC, 226VC, 227VC, 230VC, 1152VC, 1266VC, 1916VC, 1918VC, 1947VC, 1970VC, 1972VC, 1973VC, 2200VC, 2206VC, 2212VC, 2216VC, 2452VC and 4065VC

a Included in the test after the removal/installation of the Shelves 92VU, 93VU and 94VU and of the HYD/Fuel Panel 40VU.
6 Test after the disconnection/connection of the connectors 13VC and 1945VC

a Included in the tests after the removal/installation of the items of equipment.
7 Test after the disconnection/connection of the connector 1270VC

a Make sure that the circuit breaker 1KT is closed, and do a voltage check at pin C of terminal block 7502VT, connector 2, to make sure that there is 115VAC voltage.
8 Test after the disconnection/connection of the connectors 2450VC, 2451VC and 2453VC Included in the preliminary tests.
9 Test after the disconnection/connection of the connector 1990VC

a Do the BITE test of the Centralized Fault Display Interface Unit (CFDIU) (Refer to AMM 31-32-00, Page block 501).
1 0 Test after the disconnection/connection of the connectors 1274VC, 1982VC and 4066VC No test.
1 1 Tests after the removal/installation of the Shelves 92VU, 93VU and 94VU and of the HYD/Fuel Panel 40VU

a Do the test after the removal/installation of the Fuel Quantity Indicating Computer (FQIC) (3QT) (Refer to AMM 28-42-34, Page block 401). b Do the test after the removal/installation of the Fuel-Level Sensing Control-Unit (FLSCU) (7QJ, 9QJ) (Refer to AMM 28-46-34, Page block 401).

c Do the test after the removal/installation of the Brake/Steering Control Unit (BSCU) (10GG) (Refer to AMM 32-42-34, Page block 401). d Do the test after the removal/installation of the Ground Power Control Unit (GPCU) (1XG) (Refer to AMM 24-41-34, Page block 401).

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 122
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

e Do the test after the removal/installation of the Landing Gear Control and Interface Unit (LGCIU) (5GA1, 5GA2) (Refer to AMM 32-31-71, Page block 401). f Do the test after the removal/installation of the Smoke-Detection Control Unit (SDCU) (10WQ) (Refer to AMM 26-17-34, Page block 401).
g Do the test after the removal/installation of the Spoiler Elevator Computer (SEC) (1CE1, 1CE2, 1CE3) (Refer to AMM 27-94-34, Page block 401).
h Do the test after the removal/installation of the zone controller (8HK) (Refer to AMM 21-63-34, Page block 401).
i Do the test program after the removal/installation of the Panel 40VU (Refer to AMM 31-10-00, Page block 201).
1 2 Test after the electrical bonding

a Do a check of the electrical bonding (Refer to AMM 20-28-00, Page block 501). NOTE : For the maximum permitted resistance values, refer to the table in AMM 20-28-00, Page block 501. (d) Do an operational test of the fuel quantity indicator lights (Refer to AMM 28-42-00, Page block 501). (e) Do a status report (BITE) of the fuel quantity indicator system (Refer to AMM 28-42-00, Page block 501). (f) Do an operational test of the refuel/defuel system (Refer to AMM 28-25-00, Page block 501). (g) Leak Test of the ACT Shroud System and Drain Lines Refer to Figure 1, Sheet 1 and 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

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 123
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

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 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 pushbutton switch stay off.
g In the aft area of the RH main landing gear bay, disconnect the elbow nut, Item (1). Loosen the ACT cavity drain-line nut, Item (2), turn the elbow to approximately 180 deg. and tighten the nut again. Make sure that the tank interspace drain connection(s) have blanks installed.
h Connect a Ground Pressure Generator (GPG) to the elbow of the ACT cavity drain-line.
i Open, safety and tag this circuit breaker : PANEL DESIGNATION FIN LOCATION 121VU ACT PUMP SPLY 25QH 29 Q j 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. k 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.
l Make sure that the ACT pump is not running.
2 Test Procedure

a On the GPG set the air supply maximum pressure to 1.4 bar (20 psi). b 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.

c 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.

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 124
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

3 Close up

a Release the pressure from the ACT system drain-line and disconnect the GPG from the ACT cavity drain-line. b Loosen the ACT cavity drain-line nut, Item (2), turn the elbow to approximately 180 deg. and tighten the nut again.

c Reconnect the elbow nut, Item (1) to the ACT cavity drain-line. (h) Leak Test of the ACT Provisions in the Center Tank NOTE : The test that follows should only be carried out if the aircraft does not have ACT(s) installed and will not have ACT(s) installed before flight.
1 Test Preparation

a Make sure that a fuel bowser with sufficient capacity is available. b Connect the fuel bowser to the refuel coupling.
2 Test Procedure

a Operate the leak monitors for the ACT shroud drain and the ACT interspace drain. b Operate the high level switch on 800VU, check that all the "high level" lamps illuminate.

c With all refuel valves shut, put pressure on the refuel gallery via the bowser. The gallery will quickly prime with fuel. Any additional flow, due to system leakage, should not exceed 1 liter/min. d Press and hold the "Manual" button on the ACT refuel valve. The ACT refuel/transfer line will quickly prime with fuel. Any additional flow, due to system leakage, should not exceed 1 liter/min.

e Release the "Manual" button on the ACT refuel valve. f On the panel 800VU, select the refuel valve for the center tank to "Open".
g On the panel 800VU, select "Refuel" on the Mode select switch.
h Refuel the center tank until it is stopped by the High Level sensors.
i On the refuel panel 800VU, set all refuel valves to "Norm". j Examine the rear spar of the center tank and the top of the center tank for signs of fuel leakage. Pay particular attention to the connections for the ACT vent line, the ACT refuel/transfer line, and the equipment mounted on the LH manhole access door for the center tank. If a leak is found, do a repair and do the test procedure again.
DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 125
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

k Operate the leak monitors for the ACT shroud drain and the ACT interspace drain. If fuel comes out of the ACT shroud drain leak-monitor then there is a problem with the pipework of the ACT refuel/transfer line. Do a repair and do the test procedure again.
l Retain the aircraft configuration for the next test. (i) Leak Test of the ACT Pressurization System Refer to Figure 2, 3 and 4 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. Make sure there is 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.

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 126
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

h Check that the pressure indicated at T1 and T2 remains the same over a ten minute period at 1.4 bar (20 psi). Make sure there is no leakage downstream of the air shut-off valve and check the correct opening of the pressure reducing valve and the downstream non-return valve.
i Reduce the pressure on the GPG to zero and release any pressure retained in the system at T1. j Check that the pressure indicated at T2 remains at 1.4 bar (20 psi). This will show the correct operation of the downstream non-return valve and no reverse leakage through the valve.
k Bleed air from T2 to reduce pressure to zero.
3 Acceptable Results

a The system must not leak. The pressure in the system must not decrease. If a leak is found, do a repair and do the test procedure 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 to AMM 25-55-11, Page block 401). (j) Do the tests of the cabin pressure control and monitoring system (Refer to AMM 21-31-00, Page block 501). (k) Do the tests of the cockpit and cabin temperature control system (Refer to AMM 21-63-00, Page block 501). (l) Do the tests after the removal/installation of the FAC(1CC1, 1CC2) (Refer to AMM 22-66-34, Page block 401). (m) Do the operational test of the VHF system after removal/installation (Refer to AMM 23-12-00, Page block 501). (n) Do the tests of the service interphone system (Refer to AMM 23-44-00, Page block 501). (o) Do the tests of the cockpit voice recorder (Refer to AMM 23-71-00, Page block 501).

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 127
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(p) Do the tests after the removal/installation of the AC current transformer (42XS) (Refer to AMM 24-23-17, Page block 401). (q) Do the tests after the removal/installation of the generator control unit (1XS) (Refer to AMM 24-23-34, Page block 401). (r) Do the tests after the removal/installation of the APU generator (8XS) (Refer to AMM 24-23-51, Page block 401). (s) Do the tests after the removal/installation of the AC auxiliary generator contactor (3XS) (Refer to AMM 24-23-55, Page block 401). (t) Do the tests of the emergency generation system (Refer to AMM 24-24-00, Page block 501). (u) Do the test after the removal/installation from the flexible control assembly of the offwing escape slides (Refer to AMM 25-62-43, Page block 401). (v) Do the test after the removal/installation of the offwing escape slides reservoirs (Refer to AMM 25-62-46, Page block 401). (w) Do the tests of the engine fire and overheat detection system (Refer to AMM 26-12-00, Page block 501). (x) Do the tests of the APU fire and overheat detection system (Refer to AMM 26-13-00, Page block 501). (y) Do the tests of the engine fire extinguishing system (Refer to AMM 26-21-00, Page block 501). (z) Do the tests of the APU fire extinguishing system (Refer to AMM 26-22-00, Page block 501). (aa) Do the tests of the rudder hydraulic actuation (Refer to AMM 27-24-00, Page block 501). (ab) Do the tests of the elevator hydraulic actuation (Refer to AMM 27-34-00, Page block 501). (ac) Do the tests of the flaps electrical control and monitoring system (Refer to AMM 27-51-00, Page block 501). (ad) Do the tests of the flap system (Refer to AMM 27-54-00, Page block 501). (ae) Do the tests of the slat electrical control and monitoring system (Refer to AMM 27-81-00, Page block 501). (af) Do the tests of the slat system (Refer to AMM 27-84-00, Page block 501). (ag) Do the test after the removal/installation of the pedal position transducer unit (Refer to AMM 27-92-15, Page block 401).

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 128
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(ah) Do the test after the removal/installation of the flight control accelerometer (Refer to AMM 27-92-16, Page block 401). (ai) Do the test of the side stick assembly (Refer to AMM 27-92-41, Page block 501). (aj) Do the test of the ELAC system (Refer to AMM 27-93-00, Page block 501). (ak) Do the test of the SEC system (Refer to AMM 27-94-00, Page block 501). (al) Do the test of the flight control pressure switches (10CE1, 10CE2, 10CE3) (Refer to AMM 27-96-00, Page block 501). (am) Do the test of the FCDC system (Refer to AMM 27-96-00, Page block 501). (an) Do the tests of the intercell transfer system (Refer to AMM 28-15-00, Page block 501). (ao) Do the tests of the main fuel pump system (Refer to AMM 28-21-00, Page block 501). (ap) Do the tests of the APU fuel pump system (Refer to AMM 28-22-00, Page block 501). (aq) Do the tests of the fuel crossfeed system (Refer to AMM 28-23-00, Page block 501). (ar) Do the tests of the engine LP fuel shut off system (Refer to AMM 28-24-00, Page block 501). (as) Do the tests of the fuel refuel/defuel system (Refer to AMM 28-25-00, Page block 501). (at) Do the tests of the APU LP fuel shut off system (Refer to AMM 28-29-00, Page block 501). (au) Do the tests of the fuel quantity indicating system (Refer to AMM 28-42-00, Page block 501). (av) Do the tests of the fuel tank level sensing system (Refer to AMM 28-46-00, Page block 501). (aw) Do the tests of the green main hydraulic power system (Refer to AMM 29-11-00, Page block 501). (ax) Do the tests after the removal/installation of the green hydraulic reservoir (Refer to AMM 29-11-41, Page block 401). (ay) Do the tests of the blue main hydraulic power system (Refer to AMM 29-12-00, Page block 501). (az) Do the tests of the yellow main hydraulic power system (Refer to AMM 29-13-00, Page block 501). (ba) Do the tests after the removal/installation of the main HP-manifold (Refer to AMM 29-13-14, Page block 401).

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 129
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(bb) Do the tests of the power transfer unit (PTU) (Refer to AMM 29-23-00, Page block 501). (bc) Do the tests of the yellow auxiliary hydraulic power system (Refer to AMM 29-24-00, Page block 501). (bd) Do the test of the hydraulic fluid quantity indicating system (Refer to AMM 29-31-00, Page block 501). (be) Do the tests of the hydraulic fluid pressure indicating system (Refer to AMM 29-32-00, Page block 501). (bf) Do the tests after the removal/installation of the temperature transmitters (Refer to AMM 29-33-11, Page block 401). (bg) Do the tests of the hydraulic reservoir pressurization indicating system (Refer to AMM 29-34-00, Page block 501). (bh) Do the tests of the centralized fault display interface system (Refer to AMM 31-32-00, Page block 501). (bi) Do the tests of the digital flight data recording system (Refer to AMM 31-33-00, Page block 501). (bj) Do the tests of the central warning system (Refer to AMM 31-50-00, Page block 501). (bk) Do the tests after the removal/installation of the SDAC (Refer to AMM 31-55-34, Page block 401). (bl) Do the tests of the normal extension/retraction of the landing gear (Refer to AMM 32-31-00, Page block 501). (bm) Do a functional test of the free-fall extension system (Refer to AMM 32-33-00, Page block 501). (bn) Do the tests of the normal braking system (Refer to AMM 32-42-00, Page block 501). (bo) Do the tests of the alternate braking system with anti-skid (Refer to AMM 32-43-00, Page block 501). (bp) Do the tests of the alternate braking system without anti-skid (Refer to AMM 32-44-00, Page block 501). (bq) Do the tests of the parking brake system (Refer to AMM 32-45-00, Page block 501). (br) Do the tests of the brake temperature system (Refer to AMM 32-47-00, Page block 501). (bs) Do the tests of the brake cooling system (Refer to AMM 32-48-00, Page block 501). (bt) Do the tests of the nose wheel steering (Refer to AMM 32-51-00, Page block 501). (bu) Do the tests of the service area lighting (Refer to AMM 33-31-00, Page block 501). DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 130
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(bv) Do the tests of the wheel well lighting (Refer to AMM 33-37-00, Page block 501). (bw) Do the test of the navigation lights (Refer to AMM 33-41-00, Page block 501). (bx) Do the tests of the landing lights (Refer to AMM 33-42-00, Page block 501). (by) Do the tests of the anti-collision/strobe lighting (Refer to AMM 33-48-00, Page block 501). (bz) Do the tests of the cabin emergency lighting (Refer to AMM 33-51-00, Page block 501). (ca) 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). (cb) Do the tests of the engine bleed air supply system (Refer to AMM 36-11-00, Page block 501). (cc) Do the tests of the APU bleed air supply and crossbleed system (Refer to AMM 36-12-00, Page block 501). (cd) Do the tests after the removal/installation of the APU electronic control box (59KD) (Refer to AMM 49-61-34, Page block 401). (ce) Do the tests of the APU emergency shutdown circuit (Refer to AMM 49-62-00, Page block 501). (cf) Do the tests of the cargo compartment door electrical control system (Refer to AMM 52-35-00, Page block 501). (cg) Do the tests of the engine interface unit (Refer to AMM 73-25-34, Page block 501). (ch) Do the tests of the engine ignition system (Refer to AMM 74-00-00, Page block 501). (ci) Do the tests of the thrust reverser control and indicating system (Refer to AMM 78-31-00, Page block 501). (cj) After installation of the air inlets LH/RH : - Do the adjustment of the ram air inlet flap (Refer to AMM 21-61-51, Page block 501). - Do the operational test of the pack temperature control system (Refer to AMM 21-61-00, Page block 501). **D. C L** **O S**  **E U**  **P** (1) Config. 01 (a) Make sure that the work areas are clean and clear of tools and other items of equipment.

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 131
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(b) In the Overhead Panel 20VU, install the VUs and items of equipment that you removed as necessary. (c) Install the outlet PN D2821003520000 (Refer to IPC 28-12-05). (d) Install the air inlets LH/RH (Refer to AMM 21-61-51, Page block 401). (e) Install the welding group (Item 127) on the air condition packs 10HM and 11HM (Refer to AMM 21-61-51, Page block 401). (f) Install the air cooling distribution duct below the cabin floor between FR42 and FR47 (Refer to AMM 21-20-00, Page block 201 and IPC 21-21-03-05, Items 20 and 40). (g) Install the MLG torque tube assemblies, LH/RH (Refer to AMM 32-33-17, Page block 401). (h) Install hydraulic pipes (Refer to AMM 20-23-11, Page block 201 and IPC 29-13-03-16, Item 10, IPC 29-11-0303B, Items 10 and 90). (i) Do the close-up procedure as specified in the removal/installation of the multi tank fuel quantity indicator (6QT) (Refer to AMM 28-42-22, Page block 401). (j) Install the System Data Acquisition Concentrator (SDAC) (1WV1), (1WV2) (Refer to AMM 31-55-34, Page block 401). (k) Install the Slat and Flap Control Computer (SFCC) (21CV), (22CV), (Refer to AMM 27-51-34, Page block 401). (l) Install the VHF 2 antenna (Refer to AMM 23-12-11, Page block 401). (m) Install the Ground Power Control Unit (GCU)-1(2) (1XU1, 1XU2) (Refer to AMM 24-22-34, Page block 401). (n) In the forward cargo compartment, install the panels 131AC, 131AW, 131BW, 131CW, 131DW, 132AW, 131HC, 131LC, 131MC, 131BC and 131CC (Refer to AMM 06-41-53, Page block 1 and AMM 25-54-11, Page block 401). (o) 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). (p) Refuel the center tank (Refer to AMM 28-25-00, Page block 301). (q) Install the offwing escape-slides LH and RH (Refer to AMM 25-62-42, Page block 401). (r) Do the special precautions after work of the offwing Escape Slide systems (Refer to AMM 25-62-00, Page block 201) (s) In the passenger compartment, install the components that were removed for access : - the insulation blankets (Refer to AMM 25-80-00, Page block 201)

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 132
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

- the floor panels (Refer to AMM 53-32-12, Page block 401 and AMM 53-42-12, Page block 401) - the textile floor covering (Refer to AMM 25-28-41, Page block 401) - the ceiling panels (Refer to AMM 25-23-41, Page block 401 - the cove light panels (Refer to AMM 25-23-48, Page block 401) - the upper sidewall panels (Refer to AMM 25-23-43, Page block 401) - the lower sidewall (dado) panels (Refer to AMM 25-23-44, Page block 401) - the overhead stowage compartments (Refer to AMM 25-24-41, Page block 401) - the passenger seats (Refer to AMM 25-21-41, Page block 401). (t) In the FWD cargo compartment, install the components that were removed for access : - the floor panels (Refer to AMM 53-22-14, Page block 401) - the sidewall panels (Refer to AMM 25-54-12, Page block 401) - the ceiling panels (Refer to AMM 25-54-12, Page block 401). (u) In the AFT cargo compartment, install the components that were removed for access : - the floor panels (Refer to AMM 53-42-14, Page block 401) - the sidewall panels (Refer to AMM 25-55-11, Page block 401) - the ceiling panels (Refer to AMM 25-55-11, Page block 401). (v) Do the close-up procedure after the installation of the fuel-quantity indicator, multi tank 6QT (Refer to AMM 28-42-22, Page block 401 ). (w) Install the belly fairing access panels : - 192LB (Refer to AMM 53-35-11, Page block 401). - 147AB, 147EB, 147FB, 191BB, 191KB, 197BB and 197GB, 192EB, 192FB, 192KB, 198BB and 198MB (Refer to AMM 53-35-11, Page block 401). (x) Remove the safety equipment and close the main landing gear doors (Refer to AMM 32-12-00, Page block 201). (y) Remove the safety equipment and close the FWD and AFT cargo compartment doors (Refer to AMM 52-30-00, Page block 201). (z) Close the avionics compartment door 822 (Refer to AMM 52-41-00, Page block 201).

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 133
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

(aa) Close the passenger/crew door 841, (Refer to AMM 52-10-00, Page block 201). (ab) Remove the access platform(s). (ac) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page block 201). (ad) Lower the aircraft to the ground (Refer to AMM 07-11-00, Page block 201). (ae) Restore the systems and the aircraft to normal operating conditions.
**E. D O**  **C U**  **M E**  **N T**  **A**

**T I**  **O N**  Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 134
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 1, Sheet 1 Config 01: Leak Test of ACT Shroud System and Drain Lines

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 135
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 1, Sheet 2 Config 01: Leak Test of ACT Shroud System and Drain Lines

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 136
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 2, Sheet 1 Config 01: Access to Test Points T1 and T2

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 137
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 3, Sheet 1 Config 01: ACT Test Arrangement - Test Tool 1

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 138
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 4, Sheet 1 Config 01: ACT Test Arrangement - Test Tool 2

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 139
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN

Figure 5, Sheet 1 Config 01: Hook-up Chart (Kit B04)

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 140
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN REPORTING SHEET

**TITLE : FUEL - TANKS - INSTALLATION OF PROVISIONS FOR ONE ACT IN A319 AFT CARGO COMPARTMENT WITH BULK CONFIGURATION**  **MODIFICATION No. :** 25415P4179, 25696P4347, 25711J1492, 25711K4487, 26138K4772, 27115J1522, 27446P5502, 27447P5503, 27717K5539, 28068P5759, 28661J2073, 28817J1973, 30139J2110, 30356P6676, 30356P7357, 30373K6720, 31110K7004, 31143K7155, 31700K7502, 32261J2241, 33628K8825, 34240K9240, 34245K9245, 34417K9434, 34550K9440, 35442K9945, 35567K9967, 37122K5304, 37137K5305, 37226J2826 P l e as e co m p l ete t h e a p p ro p r i ate i te m (A o r B ) : A - SB W I L L B E embodied .................................................................. YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiement:

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

............................................................................................................................... .............................................. B - SB H AS B E E N embodied on aircraft: ............................................................................................................

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

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

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

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

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

..................................... Name/Title: ....................................................................................................................

...................................... Signature:..................... Date: ..................................................... I f op e rat i o n a l d o c u m e n t at i o n i s affe cte d ( s e e Pa rag ra p h 1

. K of t h i s S B ) : If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either : Advance data................................................................................... YES/NO Or : Intermediate/Temporary revision ..................................................... YES/NO I m p o rt a n t I n fo r m at i o n : This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible revision, this will result in - updating of maintenance documentation to show pre and post SB data. - updating of maintenance and operational documentation to show post SB data after embodiment. If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include them in the manual revisions. Refer to SIL 00-037 for detailed information. P l e as e re t u r n t h i s co m p l ete d s h e et to : **AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  Attn: SEDCC1 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 e-mail: sb.reporting@airbus.com Or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.
DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 1 of 1
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN REPORTING QUALITY

**TITLE : FUEL - TANKS - INSTALLATION OF PROVISIONS FOR ONE ACT IN A319 AFT CARGO COMPARTMENT WITH BULK CONFIGURATION**  **MODIFICATION No. :** 25415P4179, 25696P4347, 25711J1492, 25711K4487, 26138K4772, 27115J1522, 27446P5502, 27447P5503, 27717K5539, 28068P5759, 28661J2073, 28817J1973, 30139J2110, 30356P6676, 30356P7357, 30373K6720, 31110K7004, 31143K7155, 31700K7502, 32261J2241, 33628K8825, 34240K9240, 34245K9245, 34417K9434, 34550K9440, 35442K9945, 35567K9967, 37122K5304, 37137K5305, 37226J2826 Use this form to tell us what is your perception of the quality of this Service Bulletin.The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to futher improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) -Quality rating of this SB 4 3 2 1 -Quality rating of the Accomplishment Instructions 4 3 2 1 -Quality rating of the Illustrations 4 3 2 1 -Is this SB easy to understand ? Y / N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue.

Planning Material Instructions X Effectivity X Kit Content X Preparation X Reason X List of Materials X Mod/Inspection X Manpower Operator Supplied X Test X References X Re-identification X Close-up X Publication X Tooling X Illustrations C o m m e n ts :

Operator : Date: Name/Title :
Please return this form to: **AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 1 of 1
Printed in France © AIRBUS 2008 All rights reservedSERVICE BULLETIN REPORTING QUALITY

Attn: SEMB Service Bulletins Management FAX: (+33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE : Feb 07/07 SERVICE BULLETIN No. : A320-28-1154

REVISION No. : 01 - Apr 07/08 Page : 1 of 1
Printed in France © AIRBUS 2008 All rights reserved