@A330

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: 53

TITLE: FUSELAGE - GENERAL - IMPROVE RIVETING IN REAR FUSELAGE

AREA AT SECTION 17 FROM FR59 TO FR66

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 203702D50758

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

Prior to delivery of an A330-200F aircraft, fasteners were found missing at some locations in the

forward fuselage area at Section 17, from Frame (FR)59 to FR66.

The fastener installation and condition at the affected locations are inspected by Inspection Service

Bulletin No. A330-53-3213. In the event of findings at that inspection, this Modification Service Bulletin

details the procedure to install the correct fasteners at the identified locations.

Accomplishment of this Service Bulletin will make sure that the aircraft is restored to the original

approved design integrity.

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 YES VENDOR SB INVOLVED NO

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

disruptions.

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

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SERVICE BULLETIN

SUMMARY

MATERIAL PRICE INFORMATION

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 533218D01R01 1 60.00 Fasteners

EFFECTIVITY

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

CRK ETD MAS MNB QTR THY TPA YZR

CONCURRENT REQUIREMENTS

Service Bulletin(s) to be accomplished previously or simultaneously:

Service Bulletin No. A330-53-3213

NOTE: - A330-53-3213 FUSELAGE - FORWARD FUSELAGE - INSPECTION FOR

SUSPECTED MISSING/NON-CONFORMING FASTENERS AT SECTION 17

FROM FR59 TO FR66

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 533218-831-848-001: Modification

TOTAL MANHOURS 9.75

ELAPSED TIME (HOURS) 9.75

APPENDICES

None

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SERVICE BULLETIN

SUMMARY

**CONF ALL

Z150

NOTE:

FR60

FR61

A

FR59

STGR15LH

STGR14LH

MODIFICATION AREAS

FR58

FR59

FR60

FR61

FR62

FR63

FR66

STGR22ARH

STGR24RH

STGR25RH

STGR27RH

STGR38RH

STGR45RH

FR60A

STGR43RH

STGR47RH FR59

FR60

FR65

FR66

STGR37RH

FR64

FR65

STGR26RH

B

B

Z260

A

G_SB_533218_6_SAAA_01_00

Figure A-GSAAA - Sheet 01

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SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

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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: 53

TITLE: FUSELAGE - GENERAL - IMPROVE RIVETING IN REAR FUSELAGE

AREA AT SECTION 17 FROM FR59 TO FR66

MODIFICATION No.: 203702D50758

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: The intent of this modification is achieved in production on A330 aircraft

with Manufacturer Serial Number (MSN) 1442 and subsequent through

Modification Number 202674D50581.

(1) Models

330-223F 330-243F

(2) Effectivity by MSN

1004 1032 1051 1062 1070 1092 1115 1136 1148 1164 1175 1180 1320 1332 1344

1350 1368 1380 1386 1406 1414 1418 1428

(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: May 06/14 SERVICE BULLETIN No.: A330-53-3218

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@A330

SERVICE BULLETIN

OPERATOR MSN

CRK 1051 1062 1115 1320

ETD 1032 1070 1414

MAS 1136 1148 1164 1180

MNB 1332

QTR 1350 1386 1406

THY 1004 1092 1344 1418

TPA 1368 1380 1428

YZR 1175

(4) Configuration by MSN

MSN CONFIGURATION

1004 1032 1051 1062 1070 1092 1115 1136 1148 1164 1175

1180 1320 1332 1344 1350 1368 1380 1386 1406 1414 1418

1428

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 533218D01R01 1

Consumable CMLD01 As required

B. CONCURRENT REQUIREMENTS

Service Bulletin(s) to be accomplished previously or simultaneously:

Service Bulletin No. A330-53-3213

NOTE: - A330-53-3213 FUSELAGE - FORWARD FUSELAGE - INSPECTION

FOR SUSPECTED MISSING/NON-CONFORMING FASTENERS AT

SECTION 17 FROM FR59 TO FR66

C. REASON

(1) History

Prior to delivery of an A330-200F aircraft, fasteners were found missing at some

locations in the forward fuselage area at Section 17, from Frame (FR)59 to FR66.

(2) Objective/Action

The fastener installation and condition at the affected locations are inspected by

Inspection Service Bulletin No. A330-53-3213. In the event of findings at that inspection,

this Modification Service Bulletin details the procedure to install the correct fasteners at

the identified locations.

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SERVICE BULLETIN

(3) Advantages

Accomplishment of this Service Bulletin will make sure that the aircraft is restored to the

original approved design integrity.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 533218-831-848-001: Modification

(1) Install the Fasteners at FR59, STGR15 LH

(2) Install the Fastener at FR59A, STGR45 to STGR47 RH

(3) Install the Fasteners at FR60A, STGR26 RH

(4) Install the Fasteners at FR61, STGR14 to STGR15 LH

(5) Install the Fasteners at FR64, STGR24 RH

(6) Install the Fasteners at FR65, STGR22A, STGR23 and STGR25 RH

(7) Install the Fasteners at FR65 to FR66, STGR37 RH

(8) Install the Fastener at FR65 to FR66, STGR45 to STGR46 RH

(9) Install the Fastener at FR66, STGR27 RH

E. COMPLIANCE

(1) Classification

RECOMMENDED: Service Bulletin recommended to be accomplished to prevent

significant operational disruptions.

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin is to be performed, when applicable,

immediately after Inspection Service Bulletin No. A330-53-3213.

Accomplishment of this Service Bulletin is recommended at the earliest opportunity

where manpower and facilities are available.

F. APPROVAL

The technical content of this document is approved under the authority of Design

Organisation Approval No. EASA.21J.031.

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@A330

SERVICE BULLETIN

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 533218-831-848-001: Modification

Get Access 3.50

On Aircraft

Install the Fasteners at FR59, STGR15 LH 0.25

Install the Fastener at FR59A, STGR45 to STGR47 RH 0.25

Install the Fasteners at FR60A, STGR26 RH 0.25

Install the Fasteners at FR61, STGR14 to STGR15 LH 0.50

Install the Fasteners at FR64, STGR24 RH 0.25

Install the Fasteners at FR65, STGR22A, STGR23 and

STGR25 RH

0.50

Install the Fasteners at FR65 to FR66, STGR37 RH 0.25

Install the Fastener at FR65 to FR66, STGR45 to

STGR46 RH

0.25

Install the Fastener at FR66, STGR27 RH 0.25

Close-Up 3.50

TOTAL MANHOURS 9.75

ELAPSED TIME (HOURS) 9.75

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53

12-34-24 20-21-11 25-53-00

25-54-00 25-55-22 25-80-00

52-10-00 52-30-00 53-00-00

Consumable Material List (CML)

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

Service Bulletin (SB) A330-53-3213

Standards Manual (SM)

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@A330

SERVICE BULLETIN

Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00

51-44-11 51-46-11 51-47-00

51-75-12

K. PUBLICATION AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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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

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:

Kit 533218D01R01 AIRBUS Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 2590

For ordering by E-mail; airbus.kit@airbus.com

(2) Price and Availability

Kit 533218D01R01

Cost 60.00 USD

Availability 30 calendar days from receipt of order

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

order. If items are required 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.

The latest valid price and lead time for ordering purposes shall be obtained through the

AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.

B. INDUSTRY SUPPORT INFORMATION

For aircraft under warranty at Jun 01/11, AIRBUS will credit the manhours indicated in this

Service Bulletin at the agreed in-house warranty labor rate for claims received not later than

90 days after completion of the last affected aircraft of your fleet.

For aircraft under warranty at Jun 01/11, AIRBUS will share the costs of accomplishment of

this Service Bulletin by providing the kits at no charge for orders placed before Dec 31/16.

C. LIST OF COMPONENTS

Kit 533218D01R01

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

NOTES

1 DAN6-6-7 1 PIN

2 DAN6-6-8 1 PIN

3 EN6081D5-14 26 RIVET

4 NAS1919C05S03U 1 RIVET

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SERVICE BULLETIN

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

NOTES

5 NSA5075-6 2 COLLAR

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 CMLD01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant - General

Purpose Brushable

06AAA1 As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 533218-831-848-001 - Modification

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

INCLUDED IN THE REFERENCED PROCEDURES.

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.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words ’refer to’ are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words ’in accordance with’ are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

Task Associated Data

Zone

150 160 260

Access

Door 822 823 831

Panel 151KC 152WK 162BF 162EW 261DX 261EX 261FX 261JX

261XW 261YW 261ZW 262JX 262QX 262RX 262UX 262WX

Manpower

TOTAL MANHOURS 9.75

ELAPSED TIME (HOURS) 9.75

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SERVICE BULLETIN

A. GENERAL

(1) Subtask 533218-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-20-00, Page Block 001

06-31-53, Page Block 001

06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-801

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-11

51-46-11

51-47-00

51-75-12

(a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

Consumable Materials List (CML).

(b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(c) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001.

(e) Remove and install fasteners in accordance with SRM 51-42-00.

(f) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00.

(g) If alternative and substitute fasteners have to be used, you must make sure that the

associated nut/collar are compatible in accordance with SRM 51-40-00 ’Mating Part’

column.

(h) Obtain fastener hole diameters and drill and de-burr data in accordance with SRM

51-44-11.

(i) Obtain fastener spacing and margin data in accordance with SRM 51-47-00.

(j) For the drilling of rivet holes:

- Use a soft lead pencil and make marks to show the position of the rivet holes.

- Make sure that you have the correct edge clearance before you drill the

fastener holes.

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SERVICE BULLETIN

- If not shown otherwise the tolerance for the rivet hole diameter is +0.1 mm

(+0.004 in.).

- If not shown otherwise the tolerance for the rivet hole position is +/-0.2 mm

(+/-0.007 in.).

- Transfer-drill the existing holes with a pilot drill and a drill bush.

- Drill new fastener holes with a pilot drill of 2.5 mm (0.0984 in.) diameter.

Increase the hole diameter to the correct size for the fastener which you must

install.

- Deburr the holes.

(k) Cut the rivets to the necessary length.

(l) Countersink the fastener holes in accordance with SRM 51-46-11.

(m) Apply sealant in accordance with SRM 51-24-00.

(n) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-801.

(o) Renew the protective finish in accordance with SRM 51-75-12.

(p) 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.

(2) Subtask 533218-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

B. PREPARATION

(1) Subtask 533218-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

150 Access Door 822

Panel 152WK, Panel 151KC

260 Access Door 831

Panel 261DX, Panel 261EX, Panel 261FX, Panel

261XW, Panel 261YW, Panel 262QX, Panel

262RX, Panel 262UX, Panel 262WX, Panel

261ZW, Panel 262JX

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SERVICE BULLETIN

160 Access Door 823

Panel 162BF, Panel 162EW

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-53-00-000-801

Task 25-54-00-000-001

Task 25-55-22-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Task 52-30-00-010-803

Task 53-00-00-000-803

Task 53-00-00-000-804

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Put access platform(s) in position below the AFT cargo-compartment door 822 and

the bulk cargo-compartment door 823.

(d) Open the AFT cargo-compartment door 822, refer to AMM Task 52-30-00-010-801.

(e) Open the bulk cargo-compartment door 823, refer to AMM Task 52-30-00-010-803.

(f) In the Main-Deck Cargo Compartment (MDCC), remove the lining panels 261XW,

261YW, 261ZW, 261DX, 261EX, 261FX, 262JX, 262QX, 262RX, 262UX and

262WX, refer to AMM Task 25-55-22-000-801.

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SERVICE BULLETIN

(g) In the AFT cargo-compartment, remove the floor panel 152WK, refer to AMM Task

53-00-00-000-803.

(h) In the AFT cargo-compartment, remove the ceiling panel 151KC, refer to AMM

Task 25-53-00-000-801.

(i) In the bulk cargo-compartment, remove the floor panel 162BF, refer to AMM Task

53-00-00-000-804.

(j) In the bulk cargo-compartment, remove the sidewall panel 162EW, refer to AMM

Task 25-54-00-000-001.

(k) remove the insulation blankets as necessary to get access to the work areas, refer

to AMM Task 25-80-00-000-801.

C. PROCEDURE

(1) Subtask 533218-831-201-001 - Install the Fasteners at FR59, STGR15 LH

Work Zones and Access Panels

Zone Access/Work location

260 Access Door 831

Panel 261XW, Panel 261YW, Panel 261ZW

Work location Frame 59

Stringer 15LH

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 533218D01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 EN6081D5-14 2 RIVET

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

References

Structural Repair Manual (SRM) 51-75-12

Fig. A-GBAAA

Installation of the fasteners at FR59,

STGR15 LH

Sheet 01

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SERVICE BULLETIN

(a) Install the fasteners at FR58, STGR15 LH.

Refer to

1 As shown in Fig. A-GBAAA Sheet 01:

a Mark the fastener hole positions and pilot drill the holes to 2.5 mm

(0.0984 in.) diameter in the structure.

b Open the fastener holes to between 4.06 mm and 4.17 mm (0.160 in. to

0.164 in.) diameter.

2 As shown in Fig. A-GBAAA Sheet 01, wet install:

2 Rivet EN6081D5-14 Item 3

with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in

accordance with SRM 51-75-12.

(2) Subtask 533218-831-202-001 - Install the Fastener at FR59A, STGR45 to STGR47

RH

Work Zones and Access Panels

Zone Access/Work location

150 Access Door 822

Panel 152WK

Work location Frame 59A

from Stringer 45RH to Stringer 47RH

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 533218D01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 NAS1919C05S03U 1 RIVET

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 14

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SERVICE BULLETIN

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

References

Structural Repair Manual (SRM) 51-75-12

Fig. A-GBBAA

Installation of the fasteners at FR59A,

STGR45 to STGR47 RH

Sheet 01

(a) Install the fastener at FR59A, STGR45 to STGR47 RH.

1 As shown in Fig. A-GBBAA Sheet 01:

a Transfer drill the pilot holes to 2.5 mm (0.0984 in.) diameter in the

structure.

b Open the fastener holes to between 4.06 mm and 4.17 mm (0.160 in. to

0.164 in.) diameter.

2 As shown in Fig. A-GBBAA Sheet 01, wet install:

1 Rivet NAS1919C05S03U Item 4

with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in

accordance with SRM 51-75-12.

(3) Subtask 533218-831-203-001 - Install the Fasteners at FR60A, STGR26 RH

Work Zones and Access Panels

Zone Access/Work location

150 Access Door 822

Panel 151KC

Work location Frame 60A

Stringer 26RH

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 15

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SERVICE BULLETIN

Material necessary to do the job

Kit 533218D01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 EN6081D5-14 3 RIVET

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

References

Structural Repair Manual (SRM) 51-75-12

Fig. A-GBCAA

Installation of the fasteners at FR60A,

STGR26 RH

Sheet 01

(a) Install the fasteners at FR60A, STGR26 RH.

1 As shown in Fig. A-GBCAA Sheet 01:

a Transfer drill the pilot holes to 2.5 mm (0.0984 in.) diameter in the

structure.

b Open the fastener holes to between 4.06 mm and 4.17 mm (0.160 in. to

0.164 in.) diameter.

2 As shown in Fig. A-GBCAA Sheet 01, wet install:

3 Rivet EN6081D5-14 Item 3

with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in

accordance with SRM 51-75-12.

(4) Subtask 533218-831-204-001 - Install the Fasteners at FR61, STGR14 to STGR15

LH

Work Zones and Access Panels

Zone Access/Work location

260 Access Door 831

Panel 261DX, Panel 261EX, Panel 261FX

Work location Frame 61

from Stringer 14LH to Stringer 15LH

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 16

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@A330

SERVICE BULLETIN

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Kit 533218D01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 EN6081D5-14 8 RIVET

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

References

Structural Repair Manual (SRM) 51-75-12

Fig. A-GBDAA

Installation of the fasteners at FR61,

STGR14 to STGR15 LH

Sheet 01

(a) Install the fasteners at FR61, STGR14 to STGR15 LH.

1 As shown in Fig. A-GBDAA Sheet 01:

a Mark the fastener hole positions and pilot drill the holes to 2.5 mm

(0.0984 in.) diameter in the structure.

b Open the fastener holes to between 4.06 mm and 4.17 mm (0.160 in. to

0.164 in.) diameter.

2 As shown in Fig. A-GBDAA Sheet 01, wet install:

8 Rivet EN6081D5-14 Item 3

with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in

accordance with SRM 51-75-12.

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 17

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@A330

SERVICE BULLETIN

(5) Subtask 533218-831-205-001 - Install the Fasteners at FR64, STGR24 RH

Work Zones and Access Panels

Zone Access/Work location

260 Access Door 831

Panel 262JX

Work location Frame 64

Stringer 24RH

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 533218D01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 EN6081D5-14 3 RIVET

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

References

Structural Repair Manual (SRM) 51-75-12

Fig. A-GBEAA

Installation of the fasteners at FR64,

STGR24 RH

Sheet 01

(a) Install the fasteners at FR64, STGR24 RH.

1 As shown in Fig. A-GBEAA Sheet 01:

a Transfer drill the pilot holes to 2.5 mm (0.0984 in.) diameter in the

structure.

b Open the pilot holes to between 4.06 mm and 4.17 mm (0.160 in. to

0.164 in.) diameter.

2 As shown in Fig. A-GBEAA Sheet 01, wet install:

3 Rivet EN6081D5-14 Item 3

with:

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 18

6

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@A330

SERVICE BULLETIN

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in

accordance with SRM 51-75-12.

(6) Subtask 533218-831-206-001 - Install the Fasteners at FR65, STGR22A, STGR23

and STGR25 RH

Work Zones and Access Panels

Zone Access/Work location

260 Access Door 831

Panel 262QX, Panel 262RX, Panel 262UX,

Panel 262WX

Work location Frame 65

Stringer 22ARH

Stringer 23RH

Stringer 25RH

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Kit 533218D01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 EN6081D5-14 6 RIVET

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

References

Structural Repair Manual (SRM) 51-75-12

Fig. A-GBFAA

Installation of the fasteners at FR65,

STGR22A, STGR23 and STGR25 RH

Sheet 01

(a) Install the fasteners at FR65, STGR22A, STGR23 and STGR25 RH.

1 As shown in Fig. A-GBFAA Sheet 01:

a Transfer drill the pilot holes to 2.5 mm (0.0984 in.) in the structure.

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 19

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SERVICE BULLETIN

b Open up the holes to between 4.06 mm and 4.17 mm (0.160 in. and

0.164 in.) diameter.

2 As shown in Fig. A-GBFAA Sheet 01, wet install:

6 Rivet EN6081D5-14 Item 3

with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in

accordance with SRM 51-75-12.

(7) Subtask 533218-831-207-001 - Install the Fasteners at FR65 to FR66, STGR37 RH

Work Zones and Access Panels

Zone Access/Work location

160 Access Door 823

Panel 162EW

Work location from Frame 65 to Frame 66

Stringer 37RH

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 533218D01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 EN6081D5-14 4 RIVET

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

References

Structural Repair Manual (SRM) 51-75-12

Fig. A-GBGAA

Installation of the fasteners at FR65 to

FR66, STGR37 RH

Sheet 01

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 20

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SERVICE BULLETIN

(a) Install the fasteners at FR65 to FR66, STGR37 RH.

1 As shown in Fig. A-GBGAA Sheet 01:

a Transfer drill the pilot holes to 2.5 mm (0.0984 in.) diameter in the

structure.

b Open up the fastener holes to between 4.780 mm and 4.821 mm (0.1882

in. and 0.1898 in.) diameter.

2 As shown in Fig. A-GBGAA Sheet 01, wet install:

4 Rivet EN6081D5-14 Item 3

with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in

accordance with SRM 51-75-12.

(8) Subtask 533218-831-208-001 - Install the Fastener at FR65 to FR66, STGR45 to

STGR46 RH

Work Zones and Access Panels

Zone Access/Work location

160 Access Door 823

Panel 162BF

Work location from Frame 65 to Frame 66

from Stringer 45RH to Stringer 46RH

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

Material necessary to do the job

Kit 533218D01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 DAN6-6-8 1 PIN

5 NSA5075-6 1 COLLAR

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 21

6

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

SERVICE BULLETIN

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

References

Structural Repair Manual (SRM) 51-75-12

Fig. A-GBHAA

Installation of the fasteners at FR65 to

FR66, STGR45 to STGR46 RH

Sheet 01

(a) Install the fastener at FR65 to FR66, STGR45 to STGR46 RH.

1 As shown in Fig. A-GBHAA Sheet 01:

a Mark the fastener hole position and pilot drill the hole to 2.5 mm (0.0984

in.) diameter in the structure.

b Open the fastener hole to between 4.780 mm and 4.821 mm (0.1882 in.

to 0.1898 in.) diameter and countersink.

2 As shown in Fig. A-GBHAA Sheet 01, wet install:

1 Pin DAN6-6-8 Item 2

1 Collar NSA5075-6 Item 5

with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in

accordance with SRM 51-75-12.

(9) Subtask 533218-831-209-001 - Install the Fastener at FR66, STGR27 RH

Work Zones and Access Panels

Zone Access/Work location

160 Access Door 823

Panel 162EW

Work location Frame 66

Stringer 27RH

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 22

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@A330

SERVICE BULLETIN

Material necessary to do the job

Kit 533218D01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 DAN6-6-7 1 PIN

5 NSA5075-6 1 COLLAR

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant -

General Purpose Brushable

06AAA1 As required

References

Structural Repair Manual (SRM) 51-75-12

Fig. A-GBJAA

Installation of the fasteners at FR66,

STGR27 RH

Sheet 01

(a) Install the fastener at FR66, STGR27 RH.

1 As shown in Fig. A-GBJAA Sheet 01:

a Transfer drill the pilot holes to 2.5 mm (0.0984 in.) diameter in the

structure.

b Open up the fastener holes to between 4.780 mm and 4.821 mm (0.1882

in. and 0.1898 in.) diameter and countersink.

2 As shown in Fig. A-GBJAA Sheet 01, wet install:

1 Pin DAN6-6-7 Item 1

1 Collar NSA5075-6 Item 5

with:

Polysulfide Sealant

- General Purpose

Brushable

06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in

accordance with SRM 51-75-12.

D. TEST

None

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 23

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@A330

SERVICE BULLETIN

E. CLOSE-UP

(1) Subtask 533218-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

150 Access Door 822

Panel 152WK, Panel 151KC

260 Access Door 831

Panel 261DX, Panel 261EX, Panel 261FX, Panel

261JX, Panel 261XW, Panel 261YW, Panel

261ZW, Panel 262QX, Panel 262RX, Panel

262UX, Panel 262WX

160 Access Door 823

Panel 162BF, Panel 162EW

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-53-00-400-801

Task 25-54-00-400-001

Task 25-55-22-400-801

Task 25-80-00-400-801

Task 52-10-00-410-801

Task 52-30-00-410-801

Task 52-30-00-410-803

Task 53-00-00-400-803

Task 53-00-00-400-804

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

equipment.

(b) Install the insulation blankets which you removed to get access to the work areas,

refer to AMM Task 25-80-00-400-801.

(c) In the bulk cargo-compartment, install the sidewall panel 162EW, refer to AMM

Task 25-54-00-400-001.

(d) In the bulk cargo-compartment, install the floor panel 162BF, refer to AMM Task

53-00-00-400-804.

(e) In the AFT cargo-compartment, install the floor panel 152WK, refer to AMM Task

53-00-00-400-803.

(f) In the AFT cargo-compartment, install ceiling panel 151KC, refer to

(g) In the Main-Deck Cargo Compartment (MDCC), install the lining panels 261XW,

261YW, 261ZW, 261DX, 261EX, 261FX, 262JX, 262QX, 262RX, 262UX and

262WX, refer to AMM Task 25-55-22-400-801.

(h) Close the bulk cargo-compartment door 823, refer to AMM Task 52-30-00-410-803.

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 24

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@A330

SERVICE BULLETIN

(i) Close the AFT cargo-compartment door 822, refer to AMM Task 52-30-00-410-801.

(j) Remove the access platforms.

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 25

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@A330

SERVICE BULLETIN

**CONF ALL

STGR15LH

STGR14LH

B

VIEW LOOKING FORWARD

Z260

A

FR59

FR59

FR60

A

FR58

STGR15LH

STGR14LH

B

10.0 mm (0.393 in)

± 0.2 mm (0.007 in)

10.0 mm (0.393 in)

± 0.2 mm (0.007 in)

26.0 mm (1.023 in)

± 0.2 mm (0.007 in)

3

DIMENSIONS ARE GIVEN IF HOLES DO NOT EXIST.

NOTE:

01

01

G_SB_533218_6_BAAA_01_01

Figure A-GBAAA - Sheet 01

Installation of the fasteners at FR59, STGR15 LH

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 26

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@A330

SERVICE BULLETIN

**CONF ALL

Z150

A

FR59 FR59A

B

A

STGR47RH

STGR43RH

FR59

FWD

B

FR59A

4

G_SB_533218_6_BBAA_01_00

Figure A-GBBAA - Sheet 01

Installation of the fasteners at FR59A, STGR45 to STGR47 RH

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 27

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@A330

SERVICE BULLETIN

**CONF ALL

Z150

A

FR60 FR60A FR61

B

A

STGR26RH B

FR60

FR61

FWD

FR60A

3

G_SB_533218_6_BCAA_01_00

Figure A-GBCAA - Sheet 01

Installation of the fasteners at FR60A, STGR26 RH

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 28

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@A330

SERVICE BULLETIN

**CONF ALL

B

VIEW LOOKING FORWARD

Z260

A

FR61

FR62

A

FR60

STGR15LH

STGR14LH

B

FR61

STGR15LH

STGR14LH

12.0 mm (0.472 in)

± 0.2 mm (0.007 in)

64.2 mm (2.527 in)

(3 x 21.4 mm (0.842 in))

12.0 mm (0.472 in)

± 0.2 mm (0.007 in)

26.3 mm (1.035 in)

± 0.2 mm (0.007 in)

(8 POS)

3

DIMENSIONS ARE GIVEN IF HOLES DO NOT EXIST.

NOTE:

01

01

± 0.2 mm (0.007 in)

G_SB_533218_6_BDAA_01_01

Figure A-GBDAA - Sheet 01

Installation of the fasteners at FR61, STGR14 to STGR15 LH

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 29

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@A330

SERVICE BULLETIN

**CONF ALL

VIEW LOOKING FORWARD

STGR23RH

STGR24RH

STGR25ARH

FR64

B

FR66

FR65

FR64 STGR24RH

A

Z150 B

A

3

G_SB_533218_6_BEAA_01_00

Figure A-GBEAA - Sheet 01

Installation of the fasteners at FR64, STGR24 RH

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 30

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@A330

SERVICE BULLETIN

**CONF ALL

Z150

A

VIEW LOOKING AFT

FR65 B

STGR23RH

STGR22ARH

STGR24RH

STGR25RH

C

F

W

D

C

TYPICAL

INSTALLATION

FR65

C

C

FR66

FR65

FR64

STGR25RH

A

STGR22ARH

B

3

G_SB_533218_6_BFAA_01_00

Figure A-GBFAA - Sheet 01

Installation of the fasteners at FR65, STGR22A, STGR23 and STGR25 RH

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 31

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@A330

SERVICE BULLETIN

**CONF ALL

Z150

A

STGR37RH STGR39RH

STGR38RH

FR65

C

VIEW LOOKING AFT

B

STGR37RH

STGR38RH

STGR39RH

C

F

W

D

FR66

FR65

FR64

STGR37RH

A

B

STGR38RH

3

G_SB_533218_6_BGAA_01_00

Figure A-GBGAA - Sheet 01

Installation of the fasteners at FR65 to FR66, STGR37 RH

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 32

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@A330

SERVICE BULLETIN

**CONF ALL

Z150

A

STGR45RH

STGR46RH

STGR47RH

STGR48RH

FR66

FWD

VIEW LOOKING ON

OUTBOARD SKIN

B

STGR45RH

A

B

FR66

FR65

25.3 mm (0.996 in)

± 0.2 mm (0.007 in) 10.0 mm (0.393 in)

± 0.2 mm (0.007 in)

DIMENSIONS ARE GIVEN IF HOLES DO NOT EXIST.

NOTE:

01

01 2

5

G_SB_533218_6_BHAA_01_01

Figure A-GBHAA - Sheet 01

Installation of the fasteners at FR65 to FR66, STGR45 to STGR46 RH

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 33

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@A330

SERVICE BULLETIN

**CONF ALL

Z150

A

FWD

VIEW LOOKING ON

OUTBOARD SKIN

B

FR66

STGR26RH

STGR26XRH

STGR27RH

STGR27RH

A

FR65

FR66

B

5

1

G_SB_533218_6_BJAA_01_00

Figure A-GBJAA - Sheet 01

Installation of the fasteners at FR66, STGR27 RH

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 34

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@A330

SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - GENERAL - IMPROVE RIVETING IN REAR FUSELAGE

AREA AT SECTION 17 FROM FR59 TO FR66

MODIFICATION No.: 203702D50758

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: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 1

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@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: May 06/14 SERVICE BULLETIN No.: A330-53-3218

REVISION No.: 00 - May 06/14 Page: 1

6

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