Service Bulletin No. A33/34-32-278

Page 1 of 8

CAGE: K0654

Cheltenham Road, Gloucester, GL2 9QH, England

Telephone: +44 (0) 1452 712424 Fax: +44 (0) 1452 713821

SERVICE BULLETIN

Messier-Dowty Ltd

 ©MESSIER-BUGATTI-DOWTY 2011 (AND SUBSEQUENT REVISION PAGE DATES)

This document and all information contained herein is the sole property of Messier-Bugatti-Dowty. No intellectual property rights are

granted by the delivery of this document or the disclosure of its content. This document shall not be reproduced to a third party without the

express written consent of Messier-Bugatti-Dowty.

Safran and Messier-Bugatti names are marks owned respectively by Safran and Messier-Bugatti-Dowty companies. The mark Dowty is

used under licence.

LANDING GEAR - MAIN LANDING GEAR - 

INSPECTION OF THE BOGIE BEAM INTERNAL DIAMETER FOR CORROSION AT OVERHAUL

1. Planning Information

A. Effectivity

Aircraft affected: AIRBUS A330/340

Unit affected: Main Landing Gear Complete

which includes

Bogie and Dressings

which includes

Bogie Assembly

Part/Type Nos.: 201252 Series (Main Landing Gear Complete)

201490 Series (Main Landing Gear Complete)

10-210101 Series (Main Landing Gear Complete LH)

10-210201 Series (Main Landing Gear Complete RH)

which includes

201274 Series (Bogie and Dressings)

201486 Series (Bogie and Dressings)

10-211501 Series (Bogie and Dressings)

which includes

201272 Series (Bogie Assembly)

201485 Series (Bogie Assembly)

10-211701 Series (Bogie Assembly)

B. Concurrent Requirements

(1) None.

C. Reason

(1) A bogie beam has fractured in-service.

(2) Corrosion of the internal diameter of the bogie beam adjacent to the bogie beam pivot

pin may have contributed to the fracture.

(3) To perform specific inspections of the bogie beam bore condition, before removal of the

protective finishes.

D. Description

(1) Messier-Dowty Limited tells you that this Service Bulletin includes details to do a visual

inspection on the bogie beam. The inspection includes:

(a) A visual examination of the internal diameter for corrosion or damage to

protective treatments of the bogie beam.

Feb 17/2010

Aug 24/2011 (Revision 1)
Service Bulletin No. A33/34-32-278

Page 2

SERVICE BULLETIN

Messier-Dowty Ltd

(b) Measurement of the paint thickness on the internal bore.

(2) Messier-Dowty Limited tells you that you must complete the proforma in Appendix B to

report results of the inspection and return it to the address shown in Appendix B.

(a) The information to be recorded is:

1 Any results showing no damage to protective treatments.

2 Any damage to paint.

3 Any damage to cadmium plate.

4 Any damage or corrosion of the base material.

E. Compliance

(1) Messier-Dowty recommend that you do this Service Bulletin at next overhaul.

(2) It is expected that the contents of this Service Bulletin will be made MANDATORY by

EASA.

F. Approval

(1) The technical content of this Service Bulletin has been approved under the authority of

the EASA Design Organisation Approval No. EASA.21J.031.

G. Manpower

(1) Messier-Dowty Limited make an estimate that it will take approximately an additional 4

man-hours to do this Service Bulletin at overhaul.

NOTE: It is assumed that the equipment has been placed in a maintenance

status. The man-hour estimates do not include preparation, close out or

administrative functions.

H. Weight and Balance

(1) None.

I. References

(1) Messier-Dowty Limited Component Maintenance Manual 32-11-70.

(2) Messier-Dowty Limited Component Maintenance Manual 32-11-74.

(3) Messier-Dowty Limited Component Maintenance Manual 32-11-94.

(4) Messier-Dowty Limited Component Maintenance Manual 32-11-95.

(5) Messier-Dowty Limited Component Maintenance Manual 32-12-01.

(6) Messier-Dowty Limited Component Maintenance Manual 32-12-04.

(7) Messier-Dowty Limited Component Maintenance Manual 32-12-05.

(8) Messier-Dowty Limited Component Maintenance Manual 32-12-60.

(9) Messier-Dowty Limited Component Maintenance Manual 32-12-63.

(10) Messier-Dowty Limited Component Maintenance Manual 32-12-64.

(11) Messier-Dowty Standard Practices Manual 20-00-10.

(12) Aircraft Maintenance Manual.

Aug 24/2011 (Revision 1)
Service Bulletin No. A33/34-32-278

Page 3

SERVICE BULLETIN

Messier-Dowty Ltd

J. Other Publications Affected

(1) None.

2. Material Information

A. Material - Price and Availability

(1) None.

3. Accomplishment Instructions

The figure/item numbers in parentheses in the text agree with those that are in the illustrated

parts list. Only the primary figure/item numbers are used. The Process Specifications (M-DLPS,

M-DLNDT and PCS) are in the Standard Practices Manual.

A. Procedure for a visual inspection of the internal diameter of the bogie beam for corrosion or

damage.

(1) After disassembly of the bogie beam to detail level and before paint strip, clean all the

internal surfaces of the bogie beam (3-180, CMM 32-12-05, CMM 32-11-74 or 3-190

CMM 32-12-64). Remove all grease, dirt and loose or damaged paint: refer to

CLEANING in the applicable CMM.

NOTE: Use of pressure washer with water only to remove the main debris

within the bogie beam was found to be effective during the development

of this inspection procedure. Final cleaning by hand will still be

necessary.

(2) Fully inspect the internal diameter of the bogie beam (3-180, CMM 32-12-05, CMM

32-11-74 or 3-190 CMM 32-12-64) for corrosion or damage to the protective

treatments. Measure and record the depth of the protective treatments (A-H) using a

permascope: refer to CHECK in the applicable CMM and Figures 3 and 4 of this

Service Bulletin.

NOTE: Record the condition of the surface protection: record any flaking,

discolouration, blistering and lack of coverage. If there is no corrosion

or damage to the protective treatments record this on the proforma in

Appendix B. Record the depth (A-H) of protective treatment on the

proforma. Return a completed copy to the address shown in Appendix

B.

(3) If you find corrosion: refer to Appendix A of this Service Bulletin for details of repair

limits.

NOTE: If you find corrosion or damage to the protective treatments record this

on the proforma in Appendix B.

(4) When you have completed the proforma in Appendix B, continue with the overhaul:

refer to the applicable Component Maintenance Manual.

B. Identification

(1) After you have done this Service Bulletin:

- write the Service Bulletin number A33/34-32-278 in the applicable aircraft and

main landing gear records.

Aug 24/2011 (Revision 1)
Service Bulletin No. A33/34-32-278

Page 4

SERVICE BULLETIN

Messier-Dowty Ltd

Main Landing Gear Complete - Area of Inspection

Figure 1

AREA OF

INSPECTION

A340A4408-1

Aug 24/2011 (Revision 1)
Service Bulletin No. A33/34-32-278

Page 5

SERVICE BULLETIN

Messier-Dowty Ltd

Bogie Beam - Area of Inspection

Figure 2

A340A4851-1

BOGIE ASSEMBLY

Y

Y(SEE FIGURE 4)

Z

(SEE FIGURE 3)

Z

Aug 24/2011 (Revision 1)
Service Bulletin No. A33/34-32-278

Page 6

SERVICE BULLETIN

Messier-Dowty Ltd

Bogie Beam - Area of Inspection

Figure 3

SECTION Z-Z

A340A4410-1

AREA OF

INTERNAL

DIAMETER

INSPECTION

Aug 24/2011 (Revision 1)
Service Bulletin No. A33/34-32-278

Page 7

SERVICE BULLETIN

Messier-Dowty Ltd

Bogie Beam - Area of Inspection

Figure 4

SECTION Y-Y

AREA OF

INTERNAL

DIAMETER

INSPECTION

(360 DEGREES)

A340A4411-1

Aug 24/2011 (Revision 1)
Service Bulletin No. A33/34-32-278

Page 8

SERVICE BULLETIN

Messier-Dowty Ltd

4. Messier-Dowty and Messier Services Contacts

A. Refer to the Messier-Dowty website (safranmbd.com) for the latest list of contact names,

addresses and numbers.

Original Equipment Manufacturers

Messier-Dowty Inc.

574 Monarch Avenue

Ajax, Ontario

L1S 2G8 

CANADA

Tel: 905-683-3100

Fax: 905-683-6936

Messier-Dowty Limited

Cheltenham Road

Gloucester

GL2 9QH

ENGLAND

Tel: +44(0)1452 712424

Fax: +44(0)1452 713821

Messier-Bugatti-Dowty 

Landing Gear & Systems 

Integration Division

Zone Aeronautique L. Breguet

BP10

78140 Velizy - Villacoublay

FRANCE

Tel: +33 146 29 18 00

Fax: +33 146 29 8770

Technical Assistance and Spares Support Centers (TASSC)

For AOG (commercial and technical): aogtassc@safranmbd.com

For Europe - Africa - Middle East customers: eametassc@safranmbd.com

Tel: +33 1 5521 2590

For Americas customers: americatassc@safranmbd.com

Tel: +1 404 305 2626

For Asia-Pacific customers: asiatassc@safranmbd.com

Tel: +65 6245 5688

Repair and Overhaul Facilities

Messier Services R&O Facility

574 Monarch Avenue

Ajax, Ontario

L1S 2G8

CANADA

Tel: 905-683-3100

Fax: 905-683-0378

Messier Services R&O Facility

Meteor Business Park

Cheltenham Road

Gloucester GL2 9QL

ENGLAND

Tel: +44(0)1452 713111

Fax: +44(0)1452 716500

Messier Services R&O Facility

3, rue Antoine de St Exupery, 

BP110

67124 Molsheim Cedex

France

Tel: (33) 38838 9200

Fax: (33) 38838 9399

Messier Services (Asia) Pte. Ltd. 

R&O Facility

21 Loyang Crescent, 

Loyang Industrial Estate

SINGAPORE 508985

Tel: (65) 6545 9455

Fax: (65) 6542 3936

Messier Services R&O Facility - 

Americas

Av. La Noria

Parque Industrial Querétaro

Carretera QRO-SLP, Km. 28.5

Querétaro, QRO 76220

MEXICO

Tel: +52 (442) 19 25 800

Fax:+52 (442) 19 25 801

HYDREP Aéroport de 

Dinard-Pleurtuit-Saint-Malo

Bâtiment 20

BP90154

35801 DINARD Cedex

FRANCE

Tel: (33) 2 99 82 79 79

Fax: (33) 2 99 82 79 97

Aug 24/2011 (Revision 1)
APPENDIX A

Service Bulletin No. A33/34-32-278

Page 1 of 4

CAGE: K0654

Cheltenham Road, Gloucester, GL2 9QH, England

Telephone: +44 (0) 1452 712424 Fax: +44 (0) 1452 713821

SERVICE BULLETIN

Messier-Dowty Ltd

 ©MESSIER-BUGATTI-DOWTY 2011 (AND SUBSEQUENT REVISION PAGE DATES)

This document and all information contained herein is the sole property of Messier-Bugatti-Dowty. No intellectual property rights are

granted by the delivery of this document or the disclosure of its content. This document shall not be reproduced to a third party without the

express written consent of Messier-Bugatti-Dowty.

Safran and Messier-Bugatti names are marks owned respectively by Safran and Messier-Bugatti-Dowty companies. The mark Dowty is

used under licence.

APPENDIX A

METHOD OF REPAIR TO THE BOGIE BEAM PROTECTIVE TREATMENTS

1. Procedure

A. For the method of repair to the bogie beam if the paint has lifted or if scratched or damaged

paint is found or if damage/corrosion or cracking of the bogie beam are found, refer to CMM

32-12-05, CMM 32-11-74 or CMM 32-12-64 and Messier-Dowty Standard Practices Manual

20-00-10.

B. The Process Specifications (M-DLPS, M-DLNDT and PCS) are in the Standard Practices

Manual.

(1) If the paint is damaged. Record damage before locally masking the surrounding area

and stripping the paint: refer to PCS-2700.

OR

(2) Carefully remove damaged paint using Scotchbrite or fine emery paper.

(a) Measure area of paint removed.

NOTE: Measure and record the location of the reworked area in Appendix

B, Figure 2. Return a completed copy of Appendix B to the address

shown in Appendix B.

(3) Visually check the cadmium plating.

(a) If the cadmium plating is damaged (grey in colour) or the plating depth is not

satisfactory but the base metal is not corroded.

1 Carefully remove the cadmium plating using Scotchbrite or fine emery

paper.

2 Measure the area of cadmium plating removed.

NOTE: Measure and record the location of the reworked area in

Appendix B, Figure 2. Return a completed copy of Appendix B

to the address shown in Appendix B.

(4) If the base material has corrosion or damage.

(a) Measure and record the maximum depth of corrosion.

NOTE: Record the location, area and depth of corrosion on the proforma:

refer to Appendix B.

(b) Locally repair the corroded or damaged area: refer to the applicable Component

Maintenance Manual.

Aug 24/2011 (Revision 1)
APPENDIX A

Service Bulletin No. A33/34-32-278

Page 2

SERVICE BULLETIN

Messier-Dowty Ltd

WARNING: BLEND RADIUS MUST BE APPLIED ALL AROUND THE REWORKED

AREA. MAKE SURE ALL BLENDS ARE SMOOTH.

(c) The depth of material removal must be kept to a minimum making sure corrosion

or damage is removed. The maximum permitted depth of material removal is:

1 0,30 mm (0.012 in), this can be done to the internal diameter along the

length of the bogie beam: refer to Figure 1.

 OR

2 0,40 mm (0.015 in), this can be done internally but only over the limited

width shown: refer to Figure 2.

NOTE: The blend radius must be minimum 10,00 mm (0.394 in) in

Area A or minimum 100,00 mm (3.937 in) in Area B within the

positions shown: refer to Figure 1 or Figure 2.

(d) Measure the depth and area of material removed.

NOTE: Measure and record the location, area and depth of the reworked

area in Appendix B, Figure 2. Return a completed copy of

Appendix B to the address shown in Appendix B.

(e) Inspect the repaired area for corrosion or cracking: refer to the applicable

Component Maintenance Manual.

(f) If the depth of material removed is more than 0,038 mm (0.0015 in) but less than

0,40 mm (0.015 in) shot peen the repaired area: refer to PCS-2300 and REPAIR

in the applicable Component Maintenance Manual.

(5) Complete the overhaul of the bogie beam: refer to the applicable Component

Maintenance Manual.

Aug 24/2011 (Revision 1)
APPENDIX A

Service Bulletin No. A33/34-32-278

Page 3

SERVICE BULLETIN

Messier-Dowty Ltd

Bogie Beam - Area of Repair

Figure 1

100,00mm

(3.937in)

RADIUS

BOGIE

PIVOT 

POINT

0,30mm (0.012in) MAXIMUM DEPTH REMOVAL

MAY BE USED AT ANY POSITION ALONG

THE LENGTH AND AROUND THE INTERNAL

CIRCUMFERENCE OF THE BOGIE BEAM A340A4918-1

0,30mm (0.012in)

MAXIMUM

100,00mm (3.937in) MINIMUM IN AREA B

or

10,00mm (0.394in) MINIMUM IN AREA A

BLEND RADIUS WITHIN

THE POSITION SHOWN

(SEE VIEW ABOVE)

AXLE

238,85mm (9.404in)

DIAMETER

AREA B

REMOVE DAMAGED OR

CORRODED MATERIAL. USE

100mm (3.937in) MINIMUM

BLEND RADIUS

WITHIN THIS 

LENGTH

20,00mm (0.787in)

MAKE EDGES SMOOTH

10,00mm (0.394in)

MINIMUM BLEND RADIUS

AREA A

REMOVE DAMAGED OR

CORRODED MATERIAL. USE

10mm (0.394in) MINIMUM BLEND RADIUS

WITHIN THIS LENGTH

Aug 24/2011 (Revision 1)
APPENDIX A

Service Bulletin No. A33/34-32-278

Page 4

SERVICE BULLETIN

Messier-Dowty Ltd

Bogie Beam - Area of Repair

Figure 2

100,00mm (3.937in)

RADIUS

20,00mm (0.787in)

15 DEGREES

15 DEGREES

IF REQUIRED 0,40mm (0.015in) MAXIMUM REMOVAL

MAY BE USED AT ANY POSITION ALONG THE LENGTH AND

AROUND THE INTERNAL CIRCUMFERENCE OF THE BOGIE BEAM

ONLY WITHIN THE AREA INDICATED

0,40mm (0.015in)

MAXIMUM

238,85mm

(9.404in)

DIAMETER

A330A4919-1

BOGIE

PIVOT POINT

AXLE

10,00mm (0.394in) MINIMUM IN AREA A

or 100,00mm (3.937in) MINIMUM IN AREA B

BLEND RADIUS

WITHIN THE POSITIONS SHOWN

(SEE VIEW ABOVE AND BELOW)

MAXIMUM WIDTH OF REPAIR

62,53mm (2.462in)

AREA B

REMOVE DAMAGED OR

CORRODED MATERIAL. USE

100mm (3.937in) MINIMUM

BLEND RADIUS

WITHIN THIS 

LENGTH

AREA A

REMOVE DAMAGED OR

CORRODED MATERIAL. USE

10mm (0.394in) MINIMUM BLEND RADIUS

WITHIN THIS LENGTH

MAKE EDGES SMOOTH

10,00mm (0.394in)

MINIMUM BLEND RADIUS

Aug 24/2011 (Revision 1)
APPENDIX B

Service Bulletin No. A33/34-32-278

Page 1 of 4

CAGE: K0654

Cheltenham Road, Gloucester, GL2 9QH, England

Telephone: +44 (0) 1452 712424 Fax: +44 (0) 1452 713821

SERVICE BULLETIN

Messier-Dowty Ltd

 ©MESSIER-BUGATTI-DOWTY 2011 (AND SUBSEQUENT REVISION PAGE DATES)

This document and all information contained herein is the sole property of Messier-Bugatti-Dowty. No intellectual property rights are

granted by the delivery of this document or the disclosure of its content. This document shall not be reproduced to a third party without the

express written consent of Messier-Bugatti-Dowty.

Safran and Messier-Bugatti names are marks owned respectively by Safran and Messier-Bugatti-Dowty companies. The mark Dowty is

used under licence.

APPENDIX B

AIRBUS A330/340 - MAIN LANDING GEAR - BOGIE AND DRESSINGS

PROFORMA FOR REPORTING RESULTS OF INSPECTION SERVICE BULLETIN A33/34-32-278

Customer Details Address From Which The Item Has Been Sent

Contact Name:

Contact Tel. Number:

Contact Fax Number:

Regional CSC:

Aircraft Details

Operator: Aircraft Type:

Aircraft MSN: Aircraft TSN: Aircraft CSN:

M.L.G Serial No: M.L.G TSN: M.L.G CSN:

Bogie and Dressings LH MLG or RH MLG (tick box as necessary) Details

Part Number: TSN:

Serial No: CSN:

Bogie Beam LH MLG or RH MLG (tick box as necessary) Details

Part Number: TSN:

*Serial No (see page 3): CSN:

Return Address For Proforma Appendix B

MR D . PARSONS,

SENIOR TECHNICAL TEAM LEADER,

MESSIER-DOWTY CUSTOMER SERVICES

DEPARTMENT,

MESSIER DOWTY LIMITED,

CHELTENHAM ROAD,

GLOUCESTER,

GL2 9QH,

ENGLAND,

FAX No: + 44 01452 711972.

Aug 24/2011 (Revision 1)
APPENDIX B

Service Bulletin No. A33/34-32-278

Page 2

SERVICE BULLETIN

Messier-Dowty Ltd

Bogie Beam - Developed View of Bogie Beam Bore - Area of Repair

Figure 1

A340A4916-1

PART SECTION Z-Z

DAMAGED/REPAIR

AREA

VIEW ON ARROW A

A

XXXmm

(XXXin)

XXXmm

(XXXin)

XXXmm

(XXXin)

XXXmm

(XXXin)

XXXmm

(XXXin)

XXXmm

(XXXin)

XXXmm (XXXin)

MAXIMUM DEPTH

OF BLEND

XXXmm (XXXin)

WIDTH

XXX DEGREES

Z Z

BOGIE PIVOT PIN

CENTERLINE

AXLE

AXLE

FWD

AFT

DEVELOPED VIEW OF BOGIE BEAM BORE

KEY

BASE MATERIAL

COROSION

CADMIUM PLATE

PAINT

THIS IS AN EXAMPLE

OF HOW TO RECORD AREA

DIMENSIONS AND

LOCATION OF DAMAGE TO

PROTECTIVE TREATMENTS

AND BASE MATERIAL

AND AREA OF REPAIR

DAMAGE FOUND

NO DAMAGE FOUND

RECORD RESULTS ON PAGE 3

OF APPENDIX B.

RETURN PAGES 1 AND 3

OF APPENDIX B

RETURN PAGE 1, PAGE 3

AND PAGE 4 OF APPENDIX B

0/360

DEGREES

180

DEGREES

270

DEGREES

90

DEGREES

0

DEGREES

360

DEGREES

180

DEGREES

270

DEGREES

90

DEGREES

BASE MATERIAL

REPAIR

Aug 24/2011 (Revision 1)
APPENDIX B

Service Bulletin No. A33/34-32-278

Page 3

SERVICE BULLETIN

Messier-Dowty Ltd

USE THE ILLUSTRATION BELOW TO MARK THE LOCATION OF REPAIR

Bogie Beam - Developed View of Bogie Beam Bore - Area of Repair

Figure 2

A340A4917-1

PART SECTION Z-Z

(REFER TO FIGURE 1)

REWORK AREA

VIEW ON ARROW A

A

BOGIE PIVOT PIN

CENTERLINE

DEVELOPED VIEW OF BOGIE BEAM BORE

MEASURE AREA OF DAMAGE

TO PROTECTIVE TREATMENT

AND BASE MATERIAL AND AREA OF REPAIR

AND RECORD DIMENSIONS

AND

LOCATION ON THIS DIAGRAM

DAMAGE

FOUND

NO DAMAGE

FOUND

(TICK BOX AS NECESSARY)

AIRCRAFT MSN

BOGIE BEAM

SERIAL NUMBER

AIRCRAFT DETAILS

* LOCATION OF

BOGIE BEAM

SERIAL NUMBER

FWD

Aug 24/2011 (Revision 1)
APPENDIX B

Service Bulletin No. A33/34-32-278

Page 4

SERVICE BULLETIN

Messier-Dowty Ltd

Bogie Beam - Developed View of Bogie Beam Bore - Protective Treatment Depth Location

Figure 3

A340A4842-1

A

BOGIE PIVOT PIN

CENTERLINE

DEVELOPED VIEW OF BOGIE BEAM BORE

MEASURE THE PROTECTIVE

TREATMENT DEPTH

AND RECORD DIMENSIONS IN THE

TABLE AT LOCATIONS SHOWN

FWD

0

DEGREES

360

DEGREES

180

DEGREES

270

DEGREES

90

DEGREES

VIEW ON ARROW A

0/360 DEGREES

270

DEGREES

90

DEGREES

180 DEGREES

100mm

(3.937in)

D

C

A

B

E

F

H

G

100mm

(3.937in)

100mm

(3.937in)

100mm

(3.937in)

100mm

(3.937in)

100mm

(3.937in)

100mm

(3.937in)

100mm

(3.937in)

D

C

A

B

E

F

H

G

1 23 4 5

MEASUREMENTS A TO H MUST BE DONE IN AN AREA

WHERE THE PAINT IS NOT DAMAGED. IF THIS IS NOT

POSSIBLE MEASURE AT THE NEAREST POINT WHERE

THE PAINT IS NOT DAMAGED. FIVE MEASUREMENTS

ARE NECESSARY AT EACH LOCATION.

Aug 24/2011 (Revision 1)
Page 1 of 1

CAGE: K0654

Cheltenham Road, Gloucester, GL2 9QH, England

Telephone: +44 (0) 1452 712424 Fax: +44 (0) 1452 713821

SERVICE BULLETIN

Messier-Dowty Ltd

 ©MESSIER-BUGATTI-DOWTY 2011 (AND SUBSEQUENT REVISION PAGE DATES)

This document and all information contained herein is the sole property of Messier-Bugatti-Dowty. No intellectual property rights are

granted by the delivery of this document or the disclosure of its content. This document shall not be reproduced to a third party without the

express written consent of Messier-Bugatti-Dowty.

Safran and Messier-Bugatti names are marks owned respectively by Safran and Messier-Bugatti-Dowty companies. The mark Dowty is

used under licence.

 AIRBUS A330/A340 MAIN LANDING GEAR

SERVICE BULLETIN A33/34-32-278

TRANSMITTAL LETTER FOR REVISION 1

DATE AUG 24/2011

1. REASON

A. To add A330/340 10-210101 and 10-210201 Enhanced Main Landing Gear references.

2. ACTION

A. Remove and destroy existing pages 1 to 8 and substitute revised pages 1 to 8 dated

Aug 24/2011.

B. Appendix A. Remove and destroy existing pages 1 to 4 and substitute the revised pages 1 to 4

dated Aug 24/2011.

C. Appendix B. Remove and destroy existing pages 1 to 4 and substitute the revised pages 1 to 4

dated Aug 24/2011.

3. PREVIOUS REVISION/ISSUE DETAILS

Revision Status Date

A. Initial Issue Feb 17/2010