@A330

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: 57

TITLE: WINGS - CENTER FUSELAGE - MODIFY FASTENERS IN FR40

KEELBEAM/BOTTOM SKIN PANEL JUNCTION AREA.

MODIFICATION No.: 54459S18477

This page transmits Revision No.01 of Service Bulletin No.A330-57-3090

ADDITIONAL WORK

**CONF ALL

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision No. 01 issued to update the installation of the bolts and washers.

CHANGES

SUMMARY

MODIFICATIONS Minor editorial or document structure change N

REASON/DESCRIPTION/OPERATIONAL

CONSEQUENCES

Minor editorial or document structure change N

GENERAL EVALUATION Minor editorial or document structure change N

MATERIAL PRICE INFORMATION Minor editorial or document structure change N

EFFECTIVITY Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REFERENCES / REPERCUSSIONS Minor editorial or document structure change N

NATURE OF THE WORK Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

APPENDICES Minor editorial or document structure change N

Fig. A-FSAAA Minor editorial or document structure change N

Fig. A-FSAAA Sheet 01 Minor editorial or document structure change N

PLANNING INFORMATION

EFFECTIVITY Minor editorial or document structure change N

Configuration definition Minor editorial or document structure change N

CONF 001 Minor editorial or document structure change N

Material Effectivity Minor editorial or document structure change N

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 1

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REASON Minor editorial or document structure change N

History Minor editorial or document structure change N

Objective/Action Minor editorial or document structure change N

Advantages Minor editorial or document structure change N

Operational/Maintenance

Consequences

Minor editorial or document structure change N

DESCRIPTION Minor editorial or document structure change N

COMPLIANCE Minor editorial or document structure change N

Classification Minor editorial or document structure change N

Accomplishment Timescale Minor editorial or document structure change N

APPROVAL Minor editorial or document structure change N

Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

Minor editorial or document structure change N

WEIGHT AND BALANCE Minor editorial or document structure change N

Minor editorial or document structure change N

ELECTRICAL LOAD DATA Minor editorial or document structure change N

REFERENCES Minor editorial or document structure change N

Minor editorial or document structure change N

PUBLICATION AFFECTED Minor editorial or document structure change N

INTERCHANGEABILITY/MIXABILITY Minor editorial or document structure change N

SPARES Minor editorial or document structure change N

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY Minor editorial or document structure change N

Procurement Addresses Minor editorial or document structure change N

Price and Availability Minor editorial or document structure change N

INDUSTRY SUPPORT INFORMATION Minor editorial or document structure change N

LIST OF COMPONENTS Minor editorial or document structure change N

Kit 573090A01R02 Minor editorial or document structure change N

Supplementary Kit 573090A01S01 Minor editorial or document structure change N

LIST OF MATERIALS - OPERATOR

SUPPLIED

Minor editorial or document structure change N

Consumable Materials Minor editorial or document structure change N

Consumable CMLA01 Minor editorial or document structure change N

Components Minor editorial or document structure change N

Equipment Minor editorial or document structure change N

PARTS TO BE RE-IDENTIFIED BY

OPERATOR

Minor editorial or document structure change N

TOOLING Minor editorial or document structure change N

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 2

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Tooling - Price and Availability Minor editorial or document structure change N

Tools Minor editorial or document structure change N

Special Tools Minor editorial or document structure change N

ACCOMPLISHMENT INSTRUCTIONS

TASK 573090- 831-801-001-

MODIFICATION

Minor editorial or document structure change N

Task associated data - 001 Minor editorial or document structure change N

Subtask 573090-910-001-001 Minor editorial or document structure change N

Subtask 573090-839-001-001 Minor editorial or document structure change N

Subtask 573090-941-002-001 Minor editorial or document structure change N

Subtask 573090-020-001-001 Minor editorial or document structure change N

Subtask 573090-831-005-001 Minor editorial or document structure change N

Subtask 573090-831-006-001 Minor editorial or document structure change N

Subtask 573090-831-007-001 Minor editorial or document structure change N

Subtask 573090-420-001-001 Minor editorial or document structure change N

Subtask 573090-941-001-001 Minor editorial or document structure change N

Subtask 573090-700-001-001 Minor editorial or document structure change N

Subtask 573090-942-001-001 Minor editorial or document structure change N

Fig. A-FHAAA Minor editorial or document structure change N

Fig. A-FHAAA Sheet 01 Minor editorial or document structure change N

Fig. A-FHBAA Minor editorial or document structure change N

Fig. A-FHBAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBAAA Minor editorial or document structure change N

Fig. A-FBAAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBAAA Sheet 02 Minor editorial or document structure change N

Fig. A-FBAAA Sheet 03 Minor editorial or document structure change N

Fig. A-FBAAA Sheet 04 Minor editorial or document structure change N

Fig. A-FBAAA Sheet 05 Minor editorial or document structure change N

Fig. A-FBAAA Sheet 06 Minor editorial or document structure change N

Fig. A-FBBAA Minor editorial or document structure change N

Fig. A-FBBAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBBAA Sheet 02 Minor editorial or document structure change N

Fig. A-FBBAA Sheet 03 Minor editorial or document structure change N

Fig. A-FBEAA Minor editorial or document structure change N

Fig. A-FBEAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBEAA Sheet 02 Minor editorial or document structure change N

Fig. A-FBEAA Sheet 03 Minor editorial or document structure change N

Fig. A-FBHAA Minor editorial or document structure change N

Fig. A-FBHAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBHAA Sheet 02 Minor editorial or document structure change N

Fig. A-FBHAA Sheet 03 Minor editorial or document structure change N

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Fig. A-FGAAA Minor editorial or document structure change N

Fig. A-FGAAA Sheet 01 Minor editorial or document structure change N

Fig. A-FGAAA Sheet 02 Minor editorial or document structure change N

Fig. A-FGAAA Sheet 03 Minor editorial or document structure change N

FILLING INSTRUCTIONS

HISTORY OF PREVIOUS REVISIONS

No previous revision

REVISION SEQUENCE

ORIGINAL: Mar 27/06

REVISION No. : 01 - Jun 15/11

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 4

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SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is not approved for modification of the aircraft.

ATA SYSTEM: 57

TITLE: WINGS - CENTER FUSELAGE - MODIFY FASTENERS IN FR40

KEELBEAM/BOTTOM SKIN PANEL JUNCTION AREA.

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR 54459S18477

MINOR None

NOTE: 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.

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

On the A330 and A340 aircraft fatigue test specimen, cracks appeared on the right and left sides

between the crossing area of the keel beam fitting and the front spar of the Center Wing Box (CWB).

The damage was found at 31,717 simulated Flight Cycles (FC).

Modification Service Bulletin No. A330-57-3032 (Mod. No. 43577S12677 (FUSELAGE - CENTER

FUSELAGE - MODIFY LOWER KEEL FITTING AND FORWARD LOWER SHELL CONNECTION)) has

been issued to remove possible damage at the crossing area of the keel beam fitting and the front spar

of the CWB and to improve the fatigue strength of the area by means of 4 spotfacings on the lower keel

fitting and installation of the reinforcement fitting.

A cold working of the holes going through the reinforcement fitting, the lower angle and the FR40 is

also performed.

During accomplishment of the above mentioned modification Service Bulletin No. A330-57-3032 some

cracks findings outside Service Bulletin limits have been reported.

Service Bulletin No. A330-57-3081 (WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM

FASTENER HOLE AT FRAME 40 (UNREPAIRED AIRCRAFT)) requiring a special detailed inspection

on the horizontal flange of the keel beam in the area of first fastener hole aft of FR40.

This Service Bulletin consists in disconnecting one more fastener from the keel beam/bottom skin panel

junction by reaming a hole into the keel beam and oversizing the fastener.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 1

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@A330

SERVICE BULLETIN

SUMMARY

Then, the two adjacent fasteners are removed in order to perform cold working and to install

interference fit fasteners.

Accomplishment of this Service Bulletin will avoid initiation of cracks at the crossing area of the keel

beam fitting and the lower panel of the Center Wing Box (CWB).

Accomplishment of this Service Bulletin cancels the inspection requirements of Inspection Service

Bulletin No. A330-57-3081.

The ALI task 571162 is to be created to inspect the fastener holes of the forward lower panel.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB YES

POTENTIAL AD NO A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin recommended to be accomplished to prevent significant operational

disruptions.

MATERIAL PRICE INFORMATION

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 573090A01R02 2 2,860.00 Bushes, bolts, nuts and washers.

Supplementary kit

573090A01S01

2 1,130.00 Bolts, nuts and washers.

TOTAL 3,990.00

EFFECTIVITY

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

BEL CPA EIN HDA HFY HVN MAS OHY THA TSC VLK XAX

NOTE: This modification is applicable by Service Bulletin only.

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU 57.11.00.005

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

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SERVICE BULLETIN

SUMMARY

LIFE LIMIT None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 573090-831-801-001: MODIFICATION

TOTAL MANHOURS 76.00

ELAPSED TIME (HOURS) 41.50

APPENDICES

None

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 3

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SERVICE BULLETIN

SUMMARY

**CONF ALL

STGR1

A

Z141−142

A

FR40

FR47

B

B

FR40 DATUM

STGR1

Y−1959

C

B

RH SIDE SHOWN

LH SIDE SYMMETRICAL

VIEW INSIDE CENTER TANK AT FR40

VIEW INSIDE CENTER TANK AT FR40

C

FR40 DATUM

Y−1959

FASTENERS REPLACED

G_SB_573090_5_SAAA_01_00

Figure A-FSAAA - Sheet 01

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 4

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

ATA SYSTEM: 57

TITLE: WINGS - CENTER FUSELAGE - MODIFY FASTENERS IN FR40

KEELBEAM/BOTTOM SKIN PANEL JUNCTION AREA.

MODIFICATION No.: 54459S18477

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

NOTE: This modification is applicable by Service Bulletin only.

NOTE: This Service Bulletin is only applicable on aircraft on which Mod.

No. 41652S11819 (FUSELAGE - STRUCTURE - INTRODUCE A340

COMMONALITY ITEMS) is not embodied.

(1) Models

330-301 330-321 330-322 330-342

(2) Effectivity by MSN

0012 0017 0030 0037 0045 0050 0054-0055 0059-0060 0062 0064-0067 0069-0073

0077 0082-0083 0086-0087 0095-0096 0098-0100 0102 0106-0107 0109-0112

(3) 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: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

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@A330

SERVICE BULLETIN

OPERATOR MSN

BEL 0030 0037 0045 0082 0095

CPA 0012 0017 0071 0102

EIN 0059

HDA 0083 0099 0106 0109

HFY 0096

HVN 0087

MAS 0067 0069 0073 0077 0100 0107 0110

OHY 0072 0098

THA 0050 0060 0062 0064 0065 0066 0112

TSC 0111

VLK 0055 0070 0086

XAX 0054

(4) Configuration by MSN

MSN CONFIGURATION

0012 0017 0030 0037 0045 0050 0054 0055 0059 0060 0062

0064 0065 0066 0067 0069 0070 0071 0072 0073 0077 0082

0083 0086 0087 0095 0096 0098 0099 0100 0102 0106 0107

0109 0110 0111 0112

001

(5) Configuration definition

**CONF 001

Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a

standard configuration.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Kit 573090A01R02 2

Supplementary kit 573090A01S01 2

Consumable CMLA01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

On the A330 and A340 aircraft fatigue test specimen, cracks appeared on the right and

left sides between the crossing area of the keel beam fitting and the front spar of the

Center Wing Box (CWB).

The damage was found at 31,717 simulated Flight Cycles (FC).

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 2

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SERVICE BULLETIN

Modification Service Bulletin No. A330-57-3032 (Mod. No. 43577S12677 (FUSELAGE -

CENTER FUSELAGE - MODIFY LOWER KEEL FITTING AND FORWARD LOWER

SHELL CONNECTION)) has been issued to remove possible damage at the crossing

area of the keel beam fitting and the front spar of the CWB and to improve the fatigue

strength of the area by means of 4 spotfacings on the lower keel fitting and installation

of the reinforcement fitting.

A cold working of the holes going through the reinforcement fitting, the lower angle and

the FR40 is also performed.

During accomplishment of the above mentioned modification Service Bulletin No.

A330-57-3032 some cracks findings outside Service Bulletin limits have been reported.

Service Bulletin No. A330-57-3081 (WINGS - CENTER WING BOX - INSPECTION OF

KEEL BEAM FASTENER HOLE AT FRAME 40 (UNREPAIRED AIRCRAFT)) requiring a

special detailed inspection on the horizontal flange of the keel beam in the area of first

fastener hole aft of FR40.

(2) Objective/Action

This Service Bulletin consists in disconnecting one more fastener from the keel

beam/bottom skin panel junction by reaming a hole into the keel beam and oversizing

the fastener.

Then, the two adjacent fasteners are removed in order to perform cold working and to

install interference fit fasteners.

(3) Advantages

Accomplishment of this Service Bulletin will avoid initiation of cracks at the crossing area

of the keel beam fitting and the lower panel of the Center Wing Box (CWB).

Accomplishment of this Service Bulletin cancels the inspection requirements of

Inspection Service Bulletin No. A330-57-3081.

The ALI task 571162 is to be created to inspect the fastener holes of the forward lower

panel.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 573090-831-801-001: MODIFICATION

(1) On the LH and RH sides, Remove Only if Necessary the Ducts between FR39.1

AND FR40 for Access.

(2) On the LH and RH sides of the center tank at FR40, replace the keel beam fasteners

(for aircraft without bushes).

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

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SERVICE BULLETIN

(3) On the LH and RH sides of the center tank at FR40, replace the keel beam fasteners

(for aircraft repaired with bushes).

(4) On the LH and RH sides of the center tank at FR40, replace the fasteners of the

FWD lower panel.

(5) On the LH and RH sides, Install (if removed) the Ducts between FR39.1 and Fr40.

E. COMPLIANCE

(1) Classification

RECOMMENDED: Service Bulletin recommended to be accomplished to prevent

significant operational disruptions.

(2) Accomplishment Timescale

AIRBUS strongly recommends not to perform modification before the FC/FH values

given in the table below. In case of early embodiment, additional inspection of CWB

lower panel might be required before DSG or ISG.

Aircraft A330-300 pre Mod. No. 41652S11819

Recommended NOT before FC or FH whichever

occurs later

Proposed Compliance

20,050 FC / 61,140 FH

F. APPROVAL

Approved under EASA Design Organisation Approval No. EASA.21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, and which affects the content of this Service Bulletin, the operator is

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

G. MANPOWER

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

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

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

include the time to prepare, plan or inspect the work. Manufacture and procurement of parts

and tools, drying times for paints, sealants, etc., and general administration work are also not

included.

Task 573090-831-801-001: MODIFICATION

Get Access 9.00

On Aircraft

On the LH and RH sides, Remove Only if Necessary

the Ducts between FR39.1 AND FR40 for Access.

3.00

On the LH and RH sides of the center tank at FR40,

replace the keel beam fasteners (for aircraft without

bushes).

16.00

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

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SERVICE BULLETIN

Task 573090-831-801-001: MODIFICATION

On the LH and RH sides of the center tank at FR40,

replace the keel beam fasteners (for aircraft repaired

with bushes).

16.00

On the LH and RH sides of the center tank at FR40,

replace the fasteners of the FWD lower panel.

14.00

On the LH and RH sides, Install (if removed) the Ducts

between FR39.1 and Fr40.

3.00

Tests 3.00

Close-Up 12.00

TOTAL MANHOURS 76.00

ELAPSED TIME (HOURS) 41.50

NOTE: The total manhours for one aircraft modified is 60.00 hours.

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-41-53 12-34-24 20-21-11

20-28-00 21-20-00 21-53-18

23-53-18 28-11-00 32-12-00

36-12-41 53-35-13 57-17-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01 51-10-18

Process and Material Specification (PMS) Process and Material Specification

(PMS) 01-05-05

Service Bulletin (SB) A330-57-3032

A330-57-3081

Service Information Letter (SIL) SIL 51-012

Standards Manual (SM)

Structural Repair Manual (SRM) 51-42-11 51-44-11 51-48-00

51-76-12

K. PUBLICATION AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

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SERVICE BULLETIN

This Page Intentionally Left Blank

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Kit 573090A01R02

Supplementary kit 573090A01S01

Customers with aircraft shown in the

effectivity of this Service Bulletin should send

a purchase order to AIRBUS. Quote the

number of this Service Bulletin. The address

is:

AIRBUS Material, Logistics and Suppliers

Weg beim Jeager 150

D-22335 Hamburg

Germany

For ordering by internet :

http://spares.airbus.com

For ordering modification kits by fax : +49 40

50 76 25 90

For ordering of single spares by fax : +49 40

50 76 40 13

(2) Price and Availability

NOTE: Operator that has already received Kit 573090A01 at previous revision

must complete it as per table below :

Kit held by

operator

Supplementary

kit required

latest status of

kit

INST/DISP

573090A01R01 573090A01S01 573090A01R02

573090A01R02 NONE 573090A01R02

Kit 573090A01R02 does not require an Kit 573090A01S01 because Kit

573090A01S01 is included in 573090A01R02.

Kit 573090A01R02

Cost 1,430.00 USD

Availability 180 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require the Kit(s) before this time, please include a retrofit planning

schedule with your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Supplementary kit 573090A01S01

Cost 565.00 USD

Availability 180 calendar days from receipt of order

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

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SERVICE BULLETIN

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require the Kit(s) before this time, please include a retrofit planning

schedule with your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

B. INDUSTRY SUPPORT INFORMATION

This Service bulletin is subject to the Fatigue Test Integration Program. Refer to the FTIP

policy.

C. LIST OF COMPONENTS

Kit 573090A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

7 EN6115V6Y11 1 Bolt

8 ASNA2528-6 1 Nut

9 NSA5368PD616A 1 Washer

10 EN6115V5Y12 1 Bolt

11 ASNA2528-5 1 Nut

12 NSA5368PD516A 1 Washer

13 F5332433320000 1 Bush

14 F5332433320200 1 Bush

17 F5332433320400 1 Bush

18 EN6115V5X12 1 Bolt

19 EN6115V6X13 1 Bolt

20 NSA5368-616A 1 Washer

21 NSA5368-516A 1 Washer

22 ASNA2531-6 1 Nut

23 ASNA2531-5 1 Nut

39 NSA5368PD616B 1 Washer

40 NSA5368-616B 1 Washer

41 NSA5368-516B 1 Washer

42 NSA5368PD516B 1 Washer

48 EN6115V5X13 1 Bolt

49 EN6115V6X14 1 Bolt

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Supplementary kit 573090A01S01

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

7 EN6115V6Y11 1 Bolt

9 NSA5368PD616A 1 Washer

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

10 EN6115V5Y12 1 Bolt

12 NSA5368PD516A 1 Washer

18 EN6115V5X12 1 Bolt

19 EN6115V6X13 1 Bolt

20 NSA5368-616A 1 Washer

21 NSA5368-516A 1 Washer

22 ASNA2531-6 1 Nut

23 ASNA2531-5 1 Nut

39 NSA5368PD616B 1 Washer

40 NSA5368-616B 1 Washer

41 NSA5368-516B 1 Washer

42 NSA5368PD516B 1 Washer

48 EN6115V5X13 1 Bolt

49 EN6115V6X14 1 Bolt

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Low Density Fuel Tank Sealant 09-002D As required

Corrosion Inhibiting Brush

Consistency

09-013B As required

Solvent General Purpose 11-026 As required

Chemical Conversion Coating

Yellow Aluminum

13-002 As required

Polyurethane Primer 16-001C As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

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F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

(a) To accomplish this Service Bulletin, it is necessary to use the following tools and

equipment.

- Equipment and materials for the check of the holes as per NTM 51-10-01 Part 6.

- Tools necessary to do the check by ROTOTEST :

1. Instrument

Rototest B588 and rotor standard.

Supplier :

ROHMANN GMBH

Rudolf Diesel Str.13

D - 67227 FRANKENTHAL

Tel. : 49.(0)6233/3789 - 0

Fax. : 49.(0)6233/3789 - 77

GERMANY

2. Probe RS50-7-9 (0.311 in.).

Supplier :

ROHMANN GMBH

Rudolf Diesel Str.13

D - 67227 FRANKENTHAL

Tel. : 49.(0)6233/3789 - 0

Fax. : 49.(0)6233/3789 - 77

GERMANY

3. Calibration standard :

99A53003001101.

AIRBUS

WEG BEIM JAEGER 150

D - 22453 HAMBURG

Tel. : 49.(0)40/5076 - 0

Fax. : 49.(0)40/503168

GERMANY

- Equipment and materials for the check of the holes as per NTM 51-10-18 Part 6.

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(b) Fatigue Technology Incorporated (FTI) has allocated the following tool kit numbers

for cold working :

NOTE : For definition of capital, durable and expendable tools, refer to SIL 51-012.

- Capital tooling : ref. FTI-A330-57-3090-1

This tool reference include all capital, durable and expendable tooling kits

regardless of effectivity but capital tooling is normally already and previously bought

by the operator as a long term investment or loaned from FTI.

- Durable tooling : ref. DK-A330-57-3090-1

NOTE : In this durable tool, there is the minimum quantity necessary to accomplish

this Service Bulletin on one aircraft. In case of accomplishment of this Service

Bulletin on more than one aircraft, operator can define the quantity of durable tool to

be ordered by reference to SIL 51-012

- Expendable tooling : ref. EK-A330-57-3090-1

NOTE : In this expendable tool, there is the minimum quantiy necessary to

accomplish this Service Bulletin on one aircraft. One expendable tool has to be

ordered for each aircraft where this Service Bulletin is accomplished.

Operators interested in obtaining the FTI tool kit should contact :

Fatigue Technology Inc.

401 Andover Park West

SEATTLE, WA 98188-7605

USA

E.Mail : sales@fatiguetech.com

E.Mail : aog@fatiguetech.com

Phone : (1) 206 2462010

Fax : (1) 206 2449886

(3) Special Tools

None

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This Page Intentionally Left Blank

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 573090-831-801-001 - MODIFICATION

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: MAKE SURE THAT THE WHEEL CHOCKS ARE IN POSITION.

MOVEMENTS OF THE AIRCRAFT CAN BE DANGEROUS.

WARNING: MAKE SURE THAT THE AREA AROUND THE AIRCRAFT IS SAFE BEFORE

YOU START A REFUEL/DEFUEL PROCEDURE. IN THIS SAFE AREA, DO NOT

LET PERSONS :

- SMOKE

- MAKE SPARKS OR FIRE

- USE ANY EQUIPMENT WHICH IS NOT APPROVED FOR THE TASK.

AIRCRAFT FUEL IS FLAMMABLE.

WARNING: DO NOT SPILL FUEL ON THE ENGINES OR THE BRAKES. IF YOU SPILL FUEL

ON ENGINES OR BRAKES THAT ARE HOT, IT CAN CAUSE FIRES.

WARNING: MAKE SURE THAT YOU HAVE THE CORRECT FIRE FIGHTING EQUIPMENT

AVAILABLE.

WARNING: DO NOT GET AIRCRAFT FUEL :

- IN YOUR MOUTH

- IN YOUR EYES

- ON YOUR SKIN FOR A LONG TIME.

WARNING: MAKE SURE THAT GROUND SAFETY - LOCKS ARE CORRECTLY INSTALLED

ON THE LANDING GEAR.

THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR.

WARNING: OBEY THE SAFETY PROCEDURES WHEN YOU DO WORK IN A FUEL TANK.

THIS WILL PREVENT INJURY OR DAMAGE.

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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.

Task Associated Data

Manpower

TOTAL MANHOURS 76.00

ELAPSED TIME (HOURS) 41.50

A. GENERAL

(1) Subtask 573090-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Low Density Fuel Tank

Sealant

09-002D

Corrosion Inhibiting Brush

Consistency

09-013B

Solvent General Purpose 11-026 As required

Chemical Conversion

Coating Yellow Aluminum

13-002

Polyurethane Primer 16-001C

References

Aircraft Maintenance Manual (AMM) 20-21-11, Page Block 201

Consumable Material List (CML)

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-05-05

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SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-42-11

51-44-11

51-48-00

51-76-12

(a) For the specification of the material numbers (Mat. No.) refer to the CML.

(b) Clean the surfaces to be sealed with

Solvent General

Purpose

11-026 As required

.

(c) Use a non-metallic spatula to remove the sealant and clean the areas with

Solvent General

Purpose

11-026 As required

.

(d) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(e) Drill and deburr the holes (Refer to SRM 51-44-11).

(f) Remove and install the fasteners (Refer to SRM 51-42-11).

(g) Torque the standard threaded fasteners (Refer to AMM 20-21-11 Page Block 201).

(h) Do the cold expansion of the holes (Refer to SRM 51-48-00).

(i) Apply the sealant (Refer to SRM 51-76-12).

(j) Apply the

Corrosion Inhibiting

Brush Consistency

09-013B As required

on all the fasteners to be installed (wet assembly).

(k) Apply the

Low Density Fuel

Tank Sealant

09-002D As required

on the fasteners inside center tank at FR40.

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(l) Protect the spotfacing areas with

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

and

Polyurethane

Primer

16-001C As required

.

(m) Install the bushes with liquid nitrogen (Refer to PMS 01-05-05).

(2) Subtask 573090-839-001-001 - Administrative

Write in the applicable aircraft records that you have done all the work given in the

Service Bulletin.

B. PREPARATION

(1) Subtask 573090-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53

12-34-24, Page Block 201

21-20-00, Page Block 201

21-53-18, Page Block 401

32-12-00, Page Block 201

36-12-41, Page Block 401

53-35-13, Page Block 401

57-17-11, Page Block 401

(a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201).

(b) Put the access platform(s) in position.

(c) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block

201).

(d) Do the preparation procedure as specified in removal/installation of the airconditioning distribution ducts (Refer to AMM 21-20-00 Page Block 201).

(e) Do the preparation procedure as specified in removal/installation of the pack

discharge temperature-sensor (541HH and 542HH) (Refer to AMM 21-53-18 Page

Block 401).

(f) Do the preparation procedure as specified in removal/installation of the APU bleedair ducts (Refer to AMM 36-12-41 Page Block 401).

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(g) Remove the access panels 191FB for the LH side and 192GB for the RH side

(Refer to AMM 53-35-13 Page Block 401 and AMM 06-41-53).

(h) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block

401).

C. PROCEDURE

(1) Subtask 573090-020-001-001 - On the LH and RH sides, Remove Only if Necessary

the Ducts between FR39.1 AND FR40 for Access.

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 21-53-18, Page Block 401

36-12-41, Page Block 401

Fig. A-FHAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40, for access.

Sheet 01

Fig. A-FHBAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40, for

access.

Sheet 01

NOTE: On the LH and RH sides, remove only if necessary the ducts between

FR39.1 and FR40, for access.

(a) On RH side, remove the air conditioning duct.

Refer to Fig. A-FHAAA

1 Remove :

1 Duct Item (26) Retain

1 Insulation Item (25) Retain

1 Nut Item (28) Retain

1 Bolt Item (29) Retain

1 Washer Item (30) Retain

2 Screw Item (31) Retain

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2 Washer Item (32) Retain

2 Nut Item (33) Retain

1 Clamp Item (34) Retain

1 Clamp Item (27) Retain

NOTE (01): Disconnect and move the rod Items (35) and (36) without

removal.

NOTE (02): Remove the Insulation Item (35) with associated clamp Item

(27) from the duct Item (26) only if necessary.

NOTE (03): For the removal of the sensor 542HH (Refer to AMM 21-53-18

Page Block 401).

(b) On RH side, remove the air ventilation duct.

Refer to Fig. A-FHBAA

1 Remove :

1 Duct Item (36) Retain

8 Clamp Item (33) Retain

4 Clamp Item (32) Retain

2 Sleeve Item (34) Retain

1 Sleeve Item (35) Retain

(c) On LH side, remove the necessary APU bleed air system ducts between FR39.1

and FR40 (Refer to AMM 36-12-41 Page Block 401).

(d) Put the blanking plugs on the disconnected line ends.

(2) Subtask 573090-831-005-001 - On the LH and RH sides of the center tank at FR40,

replace the keel beam fasteners (for aircraft without bushes).

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

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Material necessary to do the job

Kit 573090A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

7 EN6115V6Y11 1 Bolt

8 ASNA2528-6 1 Nut

9 NSA5368PD616A 1 Washer

10 EN6115V5Y12 1 Bolt

11 ASNA2528-5 1 Nut

12 NSA5368PD516A 1 Washer

13 F5332433320000 1 Bush

14 F5332433320200 1 Bush

39 NSA5368PD616B 1 Washer

42 NSA5368PD516B 1 Washer

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Low Density Fuel Tank

Sealant

09-002D As required

Corrosion Inhibiting Brush

Consistency

09-013B As required

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Polyurethane Primer 16-001C As required

References

Non Destructive Test Manual (NTM) 51-10-01

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-05-05

Structural Repair Manual (SRM) 51-42-11 Paragraph 7.C.(g).Table 14

Fig. A-FBAAA

Replacement of the Fasteners of the

Keel Beam (holes without bushes), LH

and RH sides.

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

NOTE (01): Firstly, the stack up assembly must be checked to determine the actual

length of the bolt to be used.

After measurement, if the shank protusion above the stack up assembly

is lower than 0.8mm (0.031in.), then a washer with a thickness of 0.8mm

(0.031in.) shall be used.

Otherwise if the shank protusion is between 0.8mm (0.031in.) and

1.6mm (0.063in.), then a washer with a thickness of 1.6mm (0.063 in.)

shall be used.

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NOTE (02): The installed fasteners shall be checked in accordance with the

requirement of SRM 51-42-11 Paragraph 7.C.(g).Table 14 to ensure that

an adequate thread protusion is maintained after installation.

Remark : SRM 51-42-11 Paragraph 7.C.(g).Table 14 is applicable for all Hi-Lite / HiTigue (Bull Nose or Lead-in radius) and nut combinations.

NOTE: Description below is given for one side of the aircraft, two Kit

573090A01R02 are necessary to modify one aircraft.

(a) Inspect the hole.

Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02

1 Remove :

1 Screw Item (7) Discard

1 Nut Item (8) Discard

2 Remove the sealant and clean the hole.

3 Do a rotating inspection of the hole (Refer to NTM 51-10-01).

a If no crack is detected, do the operations given in paragraph 3.C.(2).(b),

b If crack is detected in the keel beam only, do the operations given in

paragraph 3.C.(2).(c),

c If crack is detected in the CWB lower panel only or in CWB lower panel

and the keel beam, do the operations given in paragraph . 3.C.(2).(d).

(b) No crack, oversize the hole in the keel beam.

Refer to Fig. A-FBAAA Sheet 01 thru Fig. A-FBAAA Sheet 03

1 Ream the hole at the level of the keel beam only to a diameter comprised

between 21mm (0.827in.) and 21.2mm (0.835in.) with a radius of 2mm

(0.079in.). Admissible reaming depth in the CWB lower panel is comprised

between 1mm (0.039in.) and 1.2mm (0.047in.).

2 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 21mm

(0.827in.).

3 Oversize the hole in the CWB lower panel, shim and gusset to a diameter

comprised between 10.177mm (0.4in.) and 10.219 mm (0.402in.).

4 Do a chamfer of 0.8mm*0.8mm (0.031in.*0.031in.) on the hole dia. 10.177mm

(0.4in.).

5 Clean the drilled area.

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6 Install :

1 Bolt EN6115V6Y11 Item 7

1 Nut ASNA2528-6 Item 8

1 Washer NSA5368PD616A Item 9

or

1 Washer NSA5368PD616B Item 39

NOTE (01): Before installation of the fasteners (wet assembly), apply :

Corrosion Inhibiting

Brush Consistency

09-013B As required

NOTE (02): Apply on the parts :

Polyurethane

Primer

16-001C As required

and

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

NOTE (03): Apply on the fasteners inside center tank :

Low Density Fuel

Tank Sealant

09-002D As required

(c) Crack detected in the keel beam only.

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA Sheet

04

1 Ream the hole at the level of the keel beam only to a diameter comprised

between 19mm(0.748in.) and 19.2mm(0.756in.). Admissible reaming depth in

the CWB lower panel is comprised between 0.5mm (0.02in.) and 0.7mm

(0.028in.).

2 Do a rotating inspection of the hole in the keel beam (Refer to NTM 51-10-01).

a Crack finding, contact AIRBUS.

b No crack finding, oversize the hole in the keel beam to a diameter

comprised between 21mm (0.827in.) and 21.2mm (0.835in.) with a radius

of 2mm (0.079in.). Admissible reaming depth in the CWB lower panel is

comprised between 1mm (0.039in.) and 1.2mm (0.047in.).

c Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 21mm

(0.827in.).

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d Oversize the hole in the CWB lower panel, shim and gusset to

a diameter comprised between 10.177mm (0.4in.) and 10.219 mm

(0.402in.).

e Do a chamfer of 0.8mm*0.8mm (0.031in.*0.031in.) on the hole dia.

10.177mm (0.4in.).

f Install :

1 Bolt EN6115V6Y11 Item 7

1 Nut ASNA2528-6 Item 8

1 Washer NSA5368PD616A Item 9

or

1 Washer NSA5368PD616B Item 39

NOTE (01): Before installation of the fasteners (wet assembly), apply :

Corrosion Inhibiting

Brush Consistency

09-013B As required

NOTE (02): Apply on the parts :

Polyurethane

Primer

16-001C As required

and

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

NOTE (03): Apply on the fasteners inside center tank :

Low Density Fuel

Tank Sealant

09-002D As required

(d) Crack detected in the CWB lower panel only and/or in the CWB lower panel and

the keel beam.

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02, Fig. A-FBAAA Sheet 05

and Fig. A-FBAAA Sheet 06

1 Ream the hole in the keel beam and the CWB lower panel to diameter

comprised between 11.1mm (0.437in.) and 11.3mm (0.445in.). Admissible

reaming depth in the shim is comprised between 0.5mm (0.02in.) and 0.7mm.

(0.028in.).

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2 Do a rotating inspection of the hole in the keel beam and the CWB lower

panel (Refer to NTM 51-10-01).

a If no crack is detected in the CWB lower panel, do the operations given

in paragraph 3.C.(2)(d)3,

b If crack is detected in the CWB lower panel, do the operations given in

paragraph 3.C.(2)(d)4.

3 No crack finding in the CWB lower panel.

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA

Sheet 05

a Ream the hole in the keel beam and the CWB lower panel to

diameter comprised between 13.1mm (0.516in.) and 13.12mm (0.517in.).

Admissible reaming depth in the shim is comprised between 1mm

(0.039in.) and 1.2mm (0.047in.).

b Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 13.1mm

(0.516in.).

c Ream the hole at the level of the keel beam only to a diameter

comprised between 19mm(0.748in.) and 19.2mm(0.756in.). Admissible

reaming depth in the CWB lower panel is comprised between 0.5mm

(0.02in.) and 0.7mm. (0.028in.).

d Do a rotating inspection of the hole in the keel beam (Refer to NTM

51-10-01).

<1> Crack finding, contact AIRBUS.

<2> No crack finding, oversize the hole in the keel beam to a diameter

comprised between 21mm (0.827in.) and 21.2mm (0.835in.) with a

radius of 2mm (0.079in.). Admissible reaming depth in the CWB

lower panel is comprised between 1mm (0.039in.) and 1.2mm

(0.047in.).

e Oversize the hole in the shim and the gusset to a diameter comprised

between 8.692mm (0.342in.) and 8.732mm (0.344in.).

f Install a stepped bush in the bottom skin panel :

1 Bush F5332433320000 Item 13

1 Bolt EN6115V5Y12 Item 10

1 Nut ASNA2528-5 Item 11

1 Washer NSA5368PD516A Item 12

or

1 Washer NSA5368PD516B Item 42

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NOTE (01): Before installation of the fasteners (wet assembly), apply :

Corrosion Inhibiting

Brush Consistency

09-013B As required

NOTE (02): Apply on the parts :

Polyurethane

Primer

16-001C As required

and

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

NOTE (03): Apply on the fasteners inside center tank :

Low Density Fuel

Tank Sealant

09-002D As required

NOTE (04): Install the bush Item 13 with liquid nitrogen (Refer to

Process and Material Specification (PMS) 01-05-05).

4 Crack finding in the CWB lower panel.

Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA

Sheet 06

a Ream the hole in the keel beam and the CWB lower panel to

diameter comprised between 13.1mm (0.516in.) and 13.3mm (0.524in.).

Admissible reaming depth in the shim is comprised between 0.5mm

(0.02in.) and 0.7mm. (0.028in.).

b Do a rotating inspection of the hole in the CWB lower panel and the keel

beam (Refer to NTM 51-10-01).

<1> Crack finding, contact AIRBUS.

<2> No crack finding, oversize the hole in the keel beam and the CWB

lower panel to a diameter comprised between 15mm (0.591 in.)

and 15.02mm (0.592in.) with a radius of 2mm (0.079in.). Admissible

reaming depth in the shim is comprised between 1mm (0.039in.)

and 1.2mm (0.047in.).

<3> Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia.

15mm (0.591 in.).

<4> Oversize the hole in the keel beam only to a diameter comprised

between 21mm (0.827in.) and 21.2mm (0.835in.) with a radius of

2mm (0.079in.). Admissible reaming depth in the CWB lower panel

is comprised between 0.5mm (0.02in.) and 0.7mm. (0.028in.).

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

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SERVICE BULLETIN

<5> Do a rotating inspection of the hole in the keel beam (Refer to NTM

51-10-01).

<6> Crack finding, contact AIRBUS.

<7> No crack finding, oversize the hole in the keel beam to a diameter

comprised between 23mm (0.906in.) and 23.2mm (0.913in.) with a

radius of 2mm (0.079in.). Admissible reaming depth in the CWB

lower panel is comprised between 1mm (0.039in.) and 1.2mm

(0.047in.).

<8> Oversize the hole in the shim and the gusset to a diameter

comprised between 8.692mm (0.342in.) and 8.732mm (0.344in.).

<9> Install a stepped bush in the bottom skin panel :

1 Bush F5332433320200 Item 14

1 Bolt EN6115V5Y12 Item 10

1 Nut ASNA2528-5 Item 11

1 Washer NSA5368PD516A Item 12

or

1 Washer NSA5368PD516B Item 42

NOTE (01): Before installation of the fasteners (wet assembly),

apply :

Corrosion Inhibiting

Brush Consistency

09-013B As required

NOTE (02): Apply on the parts :

Polyurethane

Primer

16-001C As required

and

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

NOTE (03): Apply on the fasteners inside center tank :

Low Density Fuel

Tank Sealant

09-002D As required

NOTE (04): Install the bush Item 14 with liquid nitrogen (Refer to

Process and Material Specification (PMS) 01-05-05).

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

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SERVICE BULLETIN

(3) Subtask 573090-831-006-001 - On the LH and RH sides of the center tank at FR40,

replace the keel beam fasteners (for aircraft repaired with bushes).

Manpower Resources

Manhours 16.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Kit 573090A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

7 EN6115V6Y11 1 Bolt

8 ASNA2528-6 1 Nut

9 NSA5368PD616A 1 Washer

10 EN6115V5Y12 1 Bolt

11 ASNA2528-5 1 Nut

12 NSA5368PD516A 1 Washer

17 F5332433320400 1 Bush

39 NSA5368PD616B 1 Washer

42 NSA5368PD516B 1 Washer

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Low Density Fuel Tank

Sealant

09-002D As required

Corrosion Inhibiting Brush

Consistency

09-013B As required

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Polyurethane Primer 16-001C As required

References

Non Destructive Test Manual (NTM) 51-10-01

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-05-05

Structural Repair Manual (SRM) 51-42-11 Paragraph 7.C.(g).Table 14

Fig. A-FBBAA

Replacement of the Fasteners of the

Keel Beam (holes with bushes dia. < or

= 19mm (0.748in.)), LH and RH sides.

Sheet 01

Sheet 02

Sheet 03

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

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SERVICE BULLETIN

References

Fig. A-FBEAA

Replacement of the Fasteners of the

Keel Beam (holes with bushes dia. >

19mm (0.748 in.) and < or = 21mm

(0.827in.)), LH and RH sides.

Sheet 01

Sheet 02

Sheet 03

Fig. A-FBHAA

Replacement of the Fasteners of the

Keel Beam (holes with bushes < or =

15mm (0.591in.)), LH and RH sides.

Sheet 01

Sheet 02

Sheet 03

NOTE (01): Firstly, the stack up assembly must be checked to determine the actual

length of the bolt to be used.

After measurement, if the shank protusion above the stack up assembly

is lower than 0.8mm (0.031in.), then a washer with a thickness of 0.8mm

(0.031in.) shall be used.

Otherwise if the shank protusion is between 0.8mm (0.031in.) and

1.6mm (0.063in.), then a washer with a thickness of 1.6mm (0.063 in.)

shall be used.

NOTE (02): The installed fasteners shall be checked in accordance with the

requirement of SRM 51-42-11 Paragraph 7.C.(g).Table 14 to ensure that

an adequate thread protusion is maintained after installation.

Remark : SRM 51-42-11 Paragraph 7.C.(g).Table 14 is applicable for all Hi-Lite / HiTigue (Bull Nose or Lead-in radius) and nut combinations.

NOTE: Description below is given for one side of the aircraft, two Kit

573090A01R02 are necessary to modify one aircraft.

(a) Inspect the hole.

Refer to Fig. A-FBBAA, Fig. A-FBEAA and Fig. A-FBHAA

1 Remove :

1 Screw Item (7) Discard

1 Nut Item (8) Discard

1 Bush Item (15) Discard

or

1 Screw Item (10) Discard

1 Nut Item (11) Discard

1 Bush Item (17) Discard

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

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SERVICE BULLETIN

2 Remove the sealant and clean the hole.

3 Do a rotating inspection of the hole (Refer to NTM 51-10-01).

a If case of crack finding : contact AIRBUS,

b If the bush with a diameter upper than 15mm (0.591in.) is installed in the

keel beam and the CWB lower panel, contact AIRBUS,

c If the bush with a diameter upper than 21mm (0.827in.) is installed in the

keel beam only contact AIRBUS,

d If no crack is detected and if the bush with a diameter lower or equal

than 19mm (0.748in.) is installed in the keel beam only, do the operations

given in paragraph 3.C.(3)(b),

e If no crack is detected and if the bush with a diameter upper than 19mm

(0.748in.) and lower or egal than 21mm (0.827in.) is installed in the keel

beam only, do the operations given in paragraph 3.C.(3)(c),

f If no crack is detected and if the bush with a diameter lower than 15mm

(0.591in.) is installed in the keel beam and the CWB lower panel, do the

operations given in paragraph 3.C.(3)(d).

(b) No crack (bush dia. < or = 19mm (0.748in.), oversize the hole in the keel beam.

Refer to Fig. A-FBBAA Sheet 01 thru Fig. A-FBBAA Sheet 03

1 Oversize the hole in the keel beam only to a diameter comprised between

21mm (0.827in.) and 21.2mm (0.835in.) with a radius of 2mm (0.079in.).

Admissible reaming depth in the CWB lower panel is comprised between 1mm

(0.039in.) and 1.2mm (0.047in.).

2 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 21mm

(0.827in.).

3 Oversize the hole in the CWB lower panel, the shim and the gusset to a

diameter comprised between 10.177mm (0.4in.) and 10.219mm (0.402in.).

4 Do a chamfer of 0.8mm*0.8mm (0.031in.*0.031in.) on the hole dia. 10.177mm

(0.4in.).

5 Install :

1 Bolt EN6115V6Y11 Item 7

1 Nut ASNA2528-6 Item 8

1 Washer NSA5368PD616A Item 9

or

1 Washer NSA5368PD616B Item 39

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 28

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SERVICE BULLETIN

NOTE (01): Before installation of the fasteners (wet assembly), apply :

Corrosion Inhibiting

Brush Consistency

09-013B As required

NOTE (02): Apply on the parts :

Polyurethane

Primer

16-001C As required

and

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

NOTE (03): Apply on the fasteners inside center tank :

Low Density Fuel

Tank Sealant

09-002D As required

(c) No crack (19mm (0.748in.) < bush dia. < or = 21mm (0.827in.)), oversize the hole

in the keel beam.

Refer to figure Fig. A-FBEAA Sheet 01 thru Fig. A-FBEAA Sheet 03

1 Oversize the hole in the keel beam only to a diameter comprised between

23mm (0.906in.) and 23.2mm (0.913in.) with a radius of 2mm (0.079in.).

Admissible reaming depth in the CWB lower panel is comprised between 1mm

(0.039in.) and 1.2mm (0.047in.).

2 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 23mm

(0.906in.).

3 Oversize the hole in the shim and the gusset to a diameter comprised

between 10.177mm (0.4in.) and 10.219mm (0.402in.).

4 Do a chamfer of 0.8mm*0.8mm (0.031in.*0.031in.) on the hole dia. 10.177mm

(0.4in.).

5 Install :

1 Bolt EN6115V6Y11 Item 7

1 Nut ASNA2528-6 Item 8

1 Washer NSA5368PD616A Item 9

or

1 Washer NSA5368PD616B Item 39

NOTE (01): Apply, before installation of the fasteners (wet assembly) :

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 29

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SERVICE BULLETIN

Corrosion Inhibiting

Brush Consistency

09-013B As required

NOTE (02): Apply on the parts :

Polyurethane

Primer

16-001C As required

and

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

NOTE (03): Apply the on the fasteners inside center tank :

Low Density Fuel

Tank Sealant

09-002D As required

(d) No crack (bush dia. < or = 15mm (0.591in.), oversize the hole in the keel beam.

Refer to Fig. A-FBHAA Sheet 01 thru Fig. A-FBHAA Sheet 03

1 Oversize the hole in the keel beam and the CWB lower panel to a diameter

comprised between 17mm (0.669in.) and 17.02mm (0.670in.) with a radius of

2mm (0.079in.). Admissible reaming depth in the shim is comprised between

1mm (0.039in.) and 1.2mm (0.047in.).

2 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm

(0.669in.).

3 Oversize the hole in the keel beam only to a diameter comprised between

26mm (1.024in.) and 26.2mm (1.031in.) with a radius of 2mm (0.079in.).

Admissible reaming depth in the CWB lower panel is comprised between 1mm

(0.039in.) and 1.2mm (0.047in.).

4 Oversize the hole in the shim and the gusset to a diameter comprised

between 8.692mm (0.342in.) and 8.732mm (0.344in.).

5 Install a stepped bush in the bottom skin panel :

1 Bush F5332433320400 Item 17

1 Bolt EN6115V5Y12 Item 10

1 Nut ASNA2528-5 Item 11

1 Washer NSA5368PD516A Item 12

or

1 Washer NSA5368PD516B Item 42

NOTE (01): Apply, before installation of the fasteners (wet assembly) :

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

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SERVICE BULLETIN

Corrosion Inhibiting

Brush Consistency

09-013B As required

NOTE (02): Apply on the parts :

Polyurethane

Primer

16-001C As required

and

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

NOTE (03): Apply on the fasteners inside center tank :

Low Density Fuel

Tank Sealant

09-002D As required

NOTE (04): Install the bush Item 17 with liquid nitrogen (Refer to PMS

01-05-05).

(4) Subtask 573090-831-007-001 - On the LH and RH sides of the center tank at FR40,

replace the fasteners of the FWD lower panel.

Manpower Resources

Manhours 14.00

Minimum number of person 2

Subtask elapsed time 7.00

Skills AIRFRAME

Material necessary to do the job

Kit 573090A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

18 EN6115V5X12 1 Bolt

19 EN6115V6X13 1 Bolt

20 NSA5368-616A 1 Washer

21 NSA5368-516A 1 Washer

22 ASNA2531-6 1 Nut

23 ASNA2531-5 1 Nut

40 NSA5368-616B 1 Washer

41 NSA5368-516B 1 Washer

48 EN6115V5X13 1 Bolt

49 EN6115V6X14 1 Bolt

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 31

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SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Low Density Fuel Tank

Sealant

09-002D As required

Corrosion Inhibiting Brush

Consistency

09-013B As required

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Polyurethane Primer 16-001C As required

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-42-11 Paragraph 7.C.(g).Table 14

51-48-00

Fig. A-FGAAA

Replacement of the Fasteners on the

FWD lower Panel, LH and RH sides.

Sheet 01

Sheet 02

Sheet 03

NOTE (01): Firstly, the stack up assembly must be checked to determine the actual

length of the bolt to be used.

After measurement, if the shank protusion above the stack up assembly

is lower than 0.8mm (0.031in.), then a washer with a thickness of 0.8mm

(0.031in.) shall be used.

Otherwise if the shank protusion is between 0.8mm (0.031in.) and

1.6mm (0.063in.), then a washer with a thickness of 1.6mm (0.063 in.)

shall be used.

NOTE (02): The installed fasteners shall be checked in accordance with the

requirement of SRM 51-42-11 Paragraph 7.C.(g).Table 14 to ensure that

an adequate thread protusion is maintained after installation.

Remark : SRM 51-42-11 Paragraph 7.C.(g).Table 14 is applicable for all Hi-Lite / HiTigue (Bull Nose or Lead-in radius) and nut combinations.

NOTE: Description below is given for one side of the aircraft, two Kit

573090A01R02 are necessary to modify one aircraft.

(a) Remove :

Refer to Fig. A-FGAAA Sheet 01 thru Fig. A-FGAAA Sheet 02

1 Screw Item (18) Discard

1 Screw Item (19) Discard

1 Nut Item (8) Discard

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

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SERVICE BULLETIN

1 Nut Item (11) Discard

(b) Remove the sealant and clean the holes.

(c) Do a rotating inspection, (Refer to NTM 51-10-01).

1 If a crack is detected, contact AIRBUS.

2 If no crack is detected, do the operations given in paragraph 3.C.(4)(d).

(d) Do the cold working of the holes.

Refer to Fig. A-FGAAA Sheet 01 and Fig. A-FGAAA Sheet 03

1 Ream the holes to the starting hole diameter of the cold working as shown on

Fig. A-FGAAA Sheet 03.

Use tool list No. DK-A330-57-3090-1.

2 Clean the drilles area.

3 Do the cold working of the holes (Refer to SRM 51-48-00).

Use FTI tool list No. FTI-A330-57-3090-1 and EK-A330-57-3090-1.

4 Ream the holes to the final hole diameter (Refer to Fig. A-FGAAA Sheet 01

and Fig. A-FGAAA Sheet 03).

Use FTI tool list No. DK-A330-57-3090-1.

5 Clean the drilled area.

6 Install :

1 Bolt EN6115V5X12 Item 18

or

1 Bolt EN6115V5X13 Item 48

1 Bolt EN6115V6X13 Item 19

or

1 Bolt EN6115V6X14 Item 49

1 Nut ASNA2531-5 Item 23

1 Nut ASNA2531-6 Item 22

1 Washer NSA5368-516A Item 21

or

1 Washer NSA5368-516B Item 41

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 33

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SERVICE BULLETIN

1 Washer NSA5368-616A Item 20

or

1 Washer NSA5368-616B Item 40

NOTE (01): Apply before installation of the fasteners (wet assembly) :

Corrosion Inhibiting

Brush Consistency

09-013B As required

NOTE (02): Apply on the parts :

Polyurethane

Primer

16-001C As required

and

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

NOTE (03): Apply the on the fasteners inside center tank :

Low Density Fuel

Tank Sealant

09-002D As required

(5) Subtask 573090-420-001-001 - On the LH and RH sides, Install (if removed) the

Ducts between FR39.1 and Fr40.

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 21-53-18, Page Block 401

36-12-41, Page Block 401

Fig. A-FHBAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40, for

access.

Sheet 01

Fig. A-FHAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40, for access.

Sheet 01

(a) Remove the blanking plugs on the disconnected line ends.

(b) On LH side, install (if removed) the APU bleed air system ducts between FR39.1

and FR40 (Refer to AMM 36-12-41 Page Block 401).

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

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SERVICE BULLETIN

(c) On RH side, install (if removed) the air ventilation duct.

Refer to Fig. A-FHBAA

1 Install :

1 Duct Item (36)

8 Clamp Item (33)

4 Clamp Item (32)

2 Sleeve Item (34)

1 Sleeve Item (35)

NOTE: items (32) thru (36) were retained at removal.

(d) On RH side, install (if removed) the air conditioning duct.

Refer to Fig. A-FHAAA

1 Install :

1 Duct Item (26)

1 Insulation Item (25)

1 Nut Item (28)

1 Bolt Item (29)

1 Washer Item (30)

2 Screw Item (31)

2 Washer Item (32)

2 Nut Item (33)

1 Clamp Item (34)

1 Clamp Item (27)

NOTE (01): Reconnect the rod Items (35) and (36).

NOTE (02): For the installation of the sensor 542HH (Refer to AMM

21-53-18 Page Block 401).

NOTE (03): Items (25) thru (34) were retained at removal.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

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SERVICE BULLETIN

D. TEST

(1) Subtask 573090-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 57-17-11, Page Block 401

(a) Close the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block

401).

(2) Subtask 573090-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 20-28-00, Page Block 501

21-20-00, Page Block 201

23-53-18, Page Block 401

28-11-00, Page Block 501

36-12-41, Page Block 401

53-35-13, Page Block 401

57-17-11, Page Block 401

(a) Do the test after removal/installation of the air conditioning distribution ducts (Refer

to AMM 21-20-00 Page Block 201) if removed.

(b) Do the test after removal/installation of the pack discharge temperature-sensor

(541HH and 542HH) (Refer to AMM 23-53-18 Page Block 401) if removed.

(c) Do a leak check of the center tank (Refer to AMM 28-11-00 Page Block 501).

(d) Do the test after removal/installation of the APU bleed-air ducts (Refer to AMM

36-12-41 Page Block 401) if removed.

(e) Do the test after removal/installation of the belly fairing access panels (Refer to

AMM 53-35-13 Page Block 401).

(f) Do the test after removal/installation of the access covers 147AZ and 148AZ (Refer

to AMM 57-17-11 Page Block 401).

(g) Do a check of electrical bonding (Refer to AMM 20-28-00 Page Block 501).

NOTE: Refer to Table of the Maximum Permitted Resistance Values AMM

20-28-00 Page Block 501.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

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SERVICE BULLETIN

E. CLOSE-UP

(1) Subtask 573090-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53

21-20-00, Page Block 201

21-53-18, Page Block 401

32-12-00, Page Block 201

36-12-41, Page Block 401

53-35-13, Page Block 401

57-17-11, Page Block 401

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the access panels 191FB for the LH side and 192GB for the RH side (Refer

to AMM 53-35-13 Page Block 401 and AMM 06-41-53).

(c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201).

(d) Do the close-up procedure as specified in the removal / installation of the airconditioning distribution ducts (Refer to AMM 21-20-00 Page Block 201).

(e) Do the close-up procedure as specified in the removal / installation of the pack

discharge temperature-sensor (541HH and 542HH) (Refer to AMM 21-53-18 Page

Block 401).

(f) Do the close-up procedure as specified in the removal/installation of the APU

bleed-air ducts (Refer to AMM 36-12-41 Page Block 401).

(g) Remove the access platform(s).

(h) Do the close-up procedure as specified in the removal/installation of the access

cover 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401).

(i) Restore the systems and the aircraft to normal operating condition.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

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SERVICE BULLETIN

**CONF ALL

FR39.2

B

FR40.2

Z192

A

(25)

(27)

(33)

(31)

(32) (36)

(34)

(35)

(33)

(31)

(32)

542HH

(28)

(29)

(30)

(26)

A

B

G_SB_573090_5_HAAA_01_01

Figure A-FHAAA - Sheet 01

Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40, for access.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 38

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SERVICE BULLETIN

**CONF ALL

B C

D

Z191−Z192

FR40

FR47

A

B

A

(33)

(32) (32) (35)

(34) (33)

D

C

D

(36)

G_SB_573090_5_HBAA_01_01

Figure A-FHBAA - Sheet 01

Removal/Installation of the Ventilation Ducts between FR39.1 and FR40, for access.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 39

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SERVICE BULLETIN

**CONF ALL

A

Z141−142

A

FR40

FR47

B

B

FR40 DATUM

STGR1

Y−1959

C

B

RH SIDE SHOWN

LH SIDE SYMMETRICAL

VIEW INSIDE CENTER TANK AT FR40

G_SB_573090_5_BAAA_01_00

Figure A-FBAAA - Sheet 01

Replacement of the Fasteners of the Keel Beam (holes without bushes), LH and RH sides.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 40

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SERVICE BULLETIN

**CONF ALL

FR40 DATUM

Y−1959

C

VIEW INSIDE CENTER TANK AT FR40

F

D

D

(7) 7

(8) 8

9

STGR1

SECTION D−D

INSIDE CENTER TANK

OUTSIDE CENTER TANK

GUSSET

SHIM

CWB LOWER PANEL

KEEL BEAM

(8)

(7)

FASTENER NOT AFFECTED

F

HEAD ON HIDDEN SIDE

BEFORE

OR

10

11

12

13

OR

10

11

12

14

G_SB_573090_5_BAAA_02_00

OR 39 OR 42 OR 42

Figure A-FBAAA - Sheet 02

Replacement of the Fasteners of the Keel Beam (holes without bushes), LH and RH sides.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 41

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF ALL

SECTION D−D

SHIM

CWB LOWER PANEL

KEEL BEAM

GUSSET

AFTER

7

8 9

CWB LOWER PANEL

KEEL BEAM

CHAMFER 0.5mm x 0.5mm

(0.02in x 0.02in.)

1mm THRU 1.2mm MAX.

(0.039in. THRU 0.047in.) MAX.

1 APPLY MAT. No 09−002D

1

RADIUS 2mm

(0.079in.)

DIA 10.177mm THRU 10.219mm

(0.4in. THRU 0.402in.)

CHAMFER 0.8mm x 0.8mm

(0.031in x 0.031in.)

DIA 21mm THRU 21.2mm

(0.827in. THRU 0.835in.)

OR 39

G_SB_573090_5_BAAA_03_00

Figure A-FBAAA - Sheet 03

Replacement of the Fasteners of the Keel Beam (holes without bushes), LH and RH sides.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 42

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF ALL

SECTION D−D

SHIM

CWB LOWER PANEL

KEEL BEAM

GUSSET

AFTER

7

8 9

1 APPLY MAT. No 09−002D

1

RADIUS 2mm

(0.079in.)

STEP 1

SHIM

CWB LOWER PANEL

KEEL BEAM

1mm THRU 1.2mm

(0.039in. THRU 0.047in.)

0.5mm THRU 0.7mm

(0.02in. THRU 0.028in.)

DIA 10.177mm THRU 10.219mm

(0.4in. THRU 0.402in.)

CHAMFER 0.8mm x 0.8mm

(0.031in x 0.031in.)

CHAMFER 0.5mm x 0.5mm

(0.02in x 0.02in.)

DIA 19mm THRU 19.2mm

(0.748in. THRU 0.756in.)

STEP 2 DIA 21mm THRU 21.2mm

(0.827in. THRU 0.835in.)

G_SB_573090_5_BAAA_04_00

OR 39

Figure A-FBAAA - Sheet 04

Replacement of the Fasteners of the Keel Beam (holes without bushes), LH and RH sides.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 43

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF ALL

SECTION D−D

SHIM

CWB LOWER PANEL

KEEL BEAM

GUSSET

AFTER

1 APPLY MAT. No 09−002D

1

1mm THRU 1.2mm

(0.039in. THRU 0.047in.)

0.5mm THRU 0.7mm

(0.02in. THRU 0.028in.)

11 12

10

DIA 8.692mm THRU 8.732mm

(0.342in. THRU 0.344in.)

13

RADIUS 2mm

(0.079in.)

1mm THRU 1.2mm

(0.039in. THRU 0.047in.)

0.5mm THRU 0.7mm

(0.02in. THRU 0.028in.)

CHAMFER 0.5mm x 0.5mm

(0.02in x 0.02in.)

DIA 11.1mm THRU 11.3mm

(0.437in. THRU 0.445in.)

DIA 13.1mm THRU 13.12mm

(0.516in. THRU 0.517in.)

DIA 19mm THRU 19.2mm

(0.748in. THRU 0.756in.)

DIA 21mm THRU 21.2mm

(0.827in. THRU 0.835in.)

STEP 2

STEP 1

STEP 3

STEP 4

OR 42

G_SB_573090_5_BAAA_05_01

Figure A-FBAAA - Sheet 05

Replacement of the Fasteners of the Keel Beam (holes without bushes), LH and RH sides.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 44

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF ALL

SECTION D−D

SHIM

CWB LOWER PANEL

KEEL BEAM

GUSSET

AFTER

1 APPLY MAT. No 09−002D

1

1mm THRU 1.2mm

(0.039in. THRU 0.047in.)

0.5mm THRU 0.7mm

(0.02in. THRU 0.028in.)

11 12

10

1mm THRU 1.2mm

(0.039in. THRU 0.047in.)

0.5mm THRU 0.7mm

(0.02in. THRU 0.028in.)

14

RADIUS 2mm

(0.079in.)

DIA 8.692mm THRU 8.732mm

(0.342in. THRU 0.344in.)

CHAMFER 0.5mm x 0.5mm

(0.02in x 0.02in.)

DIA 11.1mm THRU 11.3mm

(0.437in. THRU 0.445in.)

DIA 13.1mm THRU 13.3mm

(0.516in. THRU 0.524in.)

DIA 21mm THRU 21.2mm

(0.827in. THRU 0.835in.)

DIA 15mm THRU 15.02mm

(0.591in. THRU 0.592in.)

DIA 23mm THRU 23.2mm

(0.906in. THRU 0.913in.)

STEP 2

STEP 1

STEP 3

STEP 4

STEP 5

OR 42

G_SB_573090_5_BAAA_06_01

Figure A-FBAAA - Sheet 06

Replacement of the Fasteners of the Keel Beam (holes without bushes), LH and RH sides.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 45

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF ALL

A

Z141−142

A

FR40

FR47

B

B

FR40 DATUM

STGR1

Y−1959

C

B

RH SIDE SHOWN

LH SIDE SYMMETRICAL

VIEW INSIDE CENTER TANK AT FR40

G_SB_573090_5_BBAA_01_01

Figure A-FBBAA - Sheet 01

Replacement of the Fasteners of the Keel Beam (holes with bushes dia. < or = 19mm (0.748in.)), LH

and RH sides.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 46

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF ALL

FR40 DATUM

Y−1959

C

VIEW INSIDE CENTER TANK AT FR40

F

D

D

STGR1

SECTION D−D

INSIDE CENTER TANK

OUTSIDE CENTER TANK

GUSSET

SHIM

CWB LOWER PANEL

KEEL BEAM

(8)

FASTENER NOT AFFECTED

F

HEAD ON HIDDEN SIDE

BEFORE

(7) 7

(8) 8

9

(15)

(15) (7)

DIA 19mm

(0.748in.)

G_SB_573090_5_BBAA_02_00

OR 39

Figure A-FBBAA - Sheet 02

Replacement of the Fasteners of the Keel Beam (holes with bushes dia. < or = 19mm (0.748in.)), LH

and RH sides.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 47

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF ALL

SECTION D−D

SHIM

CWB LOWER PANEL

KEEL BEAM

GUSSET

AFTER

7

8 9

CWB LOWER PANEL

KEEL BEAM

CHAMFER 0.5mm x 0.5mm

(0.02in x 0.02in.)

1mm THRU 1.2mm MAX.

(0.039in. THRU 0.047in.) MAX.

1 APPLY MAT. No 09−002D

1

RADIUS 2mm

(0.079in.)

DIA 10.177mm THRU 10.219mm

(0.4in. THRU 0.402in.)

CHAMFER 0.8mm x 0.8mm

(0.031in x 0.031in.)

DIA 21mm THRU 21.2mm

(0.827in. THRU 0.835in.)

G_SB_573090_5_BBAA_03_00

OR 39

Figure A-FBBAA - Sheet 03

Replacement of the Fasteners of the Keel Beam (holes with bushes dia. < or = 19mm (0.748in.)), LH

and RH sides.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 48

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF ALL

A

Z141−142

A

FR40

FR47

B

B

FR40 DATUM

STGR1

Y−1959

C

B

RH SIDE SHOWN

LH SIDE SYMMETRICAL

VIEW INSIDE CENTER TANK AT FR40

G_SB_573090_5_BEAA_01_01

Figure A-FBEAA - Sheet 01

Replacement of the Fasteners of the Keel Beam (holes with bushes dia. > 19mm (0.748 in.) and < or =

21mm (0.827in.)), LH and RH sides.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 49

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF ALL

FR40 DATUM

Y−1959

C

VIEW INSIDE CENTER TANK AT FR40

F

D

D

STGR1

SECTION D−D

INSIDE CENTER TANK

OUTSIDE CENTER TANK

GUSSET

SHIM

CWB LOWER PANEL

KEEL BEAM

(8)

FASTENER NOT AFFECTED

F

HEAD ON HIDDEN SIDE

BEFORE

(7) 7

(8) 8

9

(15)

(15) (7)

19mm DIA

(0.748in.)

 21mm

(0.827in.)

G_SB_573090_5_BEAA_02_00

OR 39

Figure A-FBEAA - Sheet 02

Replacement of the Fasteners of the Keel Beam (holes with bushes dia. > 19mm (0.748 in.) and < or =

21mm (0.827in.)), LH and RH sides.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 50

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF ALL

SECTION D−D

SHIM

CWB LOWER PANEL

KEEL BEAM

GUSSET

AFTER

7

8 9

CWB LOWER PANEL

KEEL BEAM

CHAMFER 0.5mm x 0.5mm

(0.02in x 0.02in.)

1mm THRU 1.2mm MAX.

(0.039in. THRU 0.047in.) MAX.

1 APPLY MAT. No 09−002D

1

RADIUS 2mm

(0.079in.)

DIA 10.177mm THRU 10.219mm

(0.4in. THRU 0.402in.)

CHAMFER 0.8mm x 0.8mm

(0.031in x 0.031in.)

DIA 23mm THRU 23.2mm

(0.906in. THRU 0.913in.)

G_SB_573090_5_BEAA_03_00

OR 39

Figure A-FBEAA - Sheet 03

Replacement of the Fasteners of the Keel Beam (holes with bushes dia. > 19mm (0.748 in.) and < or =

21mm (0.827in.)), LH and RH sides.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 51

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF ALL

A

Z141−142

A

FR40

FR47

B

B

FR40 DATUM

STGR1

Y−1959

C

B

RH SIDE SHOWN

LH SIDE SYMMETRICAL

VIEW INSIDE CENTER TANK AT FR40

G_SB_573090_5_BHAA_01_01

Figure A-FBHAA - Sheet 01

Replacement of the Fasteners of the Keel Beam (holes with bushes < or = 15mm (0.591in.)), LH and

RH sides.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 52

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF ALL

FR40 DATUM

Y−1959

C

VIEW INSIDE CENTER TANK AT FR40

F

D

D

STGR1

SECTION D−D

INSIDE CENTER TANK

OUTSIDE CENTER TANK

GUSSET

SHIM

CWB LOWER PANEL

KEEL BEAM

FASTENER NOT AFFECTED

F

HEAD ON HIDDEN SIDE

BEFORE

(11)

(17) (10)

DIA 15mm

(0.591in.)

(10)

(11)

(17)

10

11

12

17

G_SB_573090_5_BHAA_02_00

OR 42

Figure A-FBHAA - Sheet 02

Replacement of the Fasteners of the Keel Beam (holes with bushes < or = 15mm (0.591in.)), LH and

RH sides.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 53

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF ALL

SECTION D−D

SHIM

CWB LOWER PANEL

KEEL BEAM

GUSSET

AFTER

1 APPLY MAT. No 09−002D

1

1mm THRU 1.2mm

(0.039in. THRU 0.047in.)

11 12

10

1mm THRU 1.2mm

(0.039in. THRU 0.047in.)

RADIUS 2mm

(0.079in.)

17

DIA 8.692mm THRU 8.732mm

(0.342in. THRU 0.344in.)

DIA 26mm THRU 26.2mm

(1.024in. THRU 1.031in.)

DIA 17mm THRU 17.02mm

(0.669in. THRU 0.670in.)

G_SB_573090_5_BHAA_03_00

OR 42

Figure A-FBHAA - Sheet 03

Replacement of the Fasteners of the Keel Beam (holes with bushes < or = 15mm (0.591in.)), LH and

RH sides.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 54

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF ALL

A

Z141−142

A

FR40

FR47

B

B

FR40 DATUM

STGR1

Y−1959

C

B

RH SIDE SHOWN

LH SIDE SYMMETRICAL

VIEW INSIDE CENTER TANK AT FR40

G_SB_573090_5_GAAA_01_01

Figure A-FGAAA - Sheet 01

Replacement of the Fasteners on the FWD lower Panel, LH and RH sides.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 55

5

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@A330

SERVICE BULLETIN

**CONF ALL

Y−1959

BEFORE

C

HOLE OLD ITEM

STGR1

FR40

KEEL BEAM DAT.

FASTENER NOT AFFECTED

(19)

(18)

(8)

(11)

G_SB_573090_5_GAAA_02_00

Figure A-FGAAA - Sheet 02

Replacement of the Fasteners on the FWD lower Panel, LH and RH sides.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 56

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

**CONF ALL

C

AFTER

1

Y−1959

STGR1

FR40

KEEL BEAM DAT.

2

TABLE OF THE EXPANDED HOLES FOR THE NEW FASTENERS.

EXISTING HOLE

DIAMETER HOLE STDN

N°

9.12mm 9.19mm 12−0−N 9.823mm

(0.386in.)

9.782mm

(0.359in.) (0.361in.) (0.385in.)

7.55mm 7.62mm 8.245mm

(0.324in.)

8.211mm

(0.297in.) (0.3in.) (0.323in.) 10−0−N

NEW

ITEM

NEW

ITEM FASTENER NUT

1

2

HOLE

N°

FINAL HOLE

DIAMETER

STARTING HOLE

DIAMETER

= EXPANSION SLEEVE INSTALLATION

ORIENTATION SCHEMATIC DIAGRAM

FASTENER NOT AFFECTED

1 MAT. No. 09−002

1

MIN. MAX. MIN. MAX. MIN. MAX.

7.815mm

(0.307in.)

7.849mm

(0.309in.)

6.227mm

(0.245in.)

6.262mm

(0.246in.)

EN6115V6X13

ASNA2531−6

NEW

ITEM

22

NSA5368−616A

WASHER

19 20

1

2

OR

EN6115V6X14

OR

49

OR

NSA5368−616B

OR

40 1

EN6115V5X12 1

ASNA2531−5 23

18 NSA5368−516A 21

OR

EN6115V5X13

OR

48

OR

NSA5368−516B

OR

41 1

G_SB_573090_5_GAAA_03_01

Figure A-FGAAA - Sheet 03

Replacement of the Fasteners on the FWD lower Panel, LH and RH sides.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 57

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

REPORTING SHEET

TITLE: WINGS - CENTER FUSELAGE - MODIFY FASTENERS IN FR40

KEELBEAM/BOTTOM SKIN PANEL JUNCTION AREA.

MODIFICATION No.: 54459S18477

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

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

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

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

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

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

the next feasible revision, this will result in

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

- Updating of maintenance and operational documentation to show post SB data after embodiment.

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

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 1

5

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@A330

SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- 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 Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090

REVISION No.: 01 - Jun 15/11 Page: 1

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.