Messier-Dowty Ltd

Service Bulletin No.A33/34-32-272 Page 1 of 16 CAGE: K0654 Cheltenham Road, Gloucester, GL2 9QH, England Telephone: +44 (0) 1452 712424 Fax: +44 (0) 1452 713821 

# SERVICE BULLETIN

LANDING GEAR - MAIN LANDING GEAR - INSPECTION OF THE BOGIE BEAM IN TERNAL DIAMETER FOR CORROSION 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.: 201490 Series (Main Landing Gear Complete) 201252 Series (Main Landing Gear Complete) which includes 201486 Series (Bogie and Dressings) 201274 Series (Bogie and Dressings) which includes 201485 Series (Bogie Assembly) 201272 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 t he bogie beam adjacent to the bogie beam pivot pin may have contributed to the fracture. 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) The removal of the bogie and dressings from the main landing gear complete. (b) A visual examination of the inte rnal diameter for corrosion or damage to protective treatments of the bogie beam. (c) Repair of any corrosion or damage to protective treatments. (2) Messier-Dowty Limited tells you that you must complete the proforma in Appendix D to report results of the inspection and return it to the address shown in Appendix D. (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 base material.

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E. Compliance (1) It is expected that the contents of this Service Bulletin will be made MANDATORY by EASA. (2) Messier-Dowty recommends that you do th is Service Bulletin as soon as possible. (a) For details of compliance refer to Ai rbus cover Service Bulletin A330-32-3225 and A340-32-4268. 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 th at it will take approximately 9 man-hours to do this Service Bulletin. The elapsed time will be 4.5 hours. The time given is for the visual inspection with the bogie and dressings removed. 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 32-12-01. (2) Messier-Dowty Limited Component Maintenance Manual 32-12-04. (3) Messier-Dowty Limited Component Maintenance Manual 32-12-05. (4) Messier-Dowty Limited Component Maintenance Manual 32-11-70. (5) Messier-Dowty Limited Component Maintenance Manual 32-11-94. (6) Messier-Dowty Limited Component Maintenance Manual 32-11-95. (7) Messier-Dowty Limited Component Maintenance Manual 32-11-74. (8) Messier-Dowty Standard Practices Manual 20-00-10. (9) Airbus Service Bulletin A330-32-3225 and A340-32-4268. (10) Aircraft Maintenance Manual. J. Other Publications Affected (1) None.

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2. Material Information A. Material - Price and Availability (1) The prices shown in this material sectio n are valid for the year, ending December 31st 2007. Refer to the Messier-Dowty Spare Parts Price Catalog for subsequent year prices or contact your regi onal Messier-Dowty Customer Support Centre for the latest price and availability information. B. Material Necessary For Each Unit The I/D codes below give information which help you to understand the instruction/disposition. I/D Code Instruction/information A New part B Part that can be obtained from the old one C Expendable part D Old part to be discarded E Part of new design valid for new manufacture F Part number change only Interchangeability codes (IC) given below show basic information to help you understand the interchangeability of parts. For full explanation of interchangeability codes, please refer to the latest edition of ATA specification 2000. IC Instruction/information 01 One-way interchangeable 02 Two-way interchangeable 03 Not interchangeable 04 Interchangeable as a set 05 Qualified Interchangeability C. The table that follows tells operators of the items that are necessary to do this Service Bulletin. It does not include tools or materials that are referred to in the Component Maintenance Manuals. New Part No. Qty. Per Unit Keyword Old Part No. Instructions/ Disposition IC

MS17825-4 11 Nut - Replacement Parts (D) - MS17825-3 2 Nut - - NAS1149F0632P 4 Washer - - NAS1149F0663P 2 Washer - - NAS1149F0432P 51 Washer - -

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D. Tooling (1) These special tools are necessary: NOTE: Alternative equivalents are permitted.

(2) Other tools necessary to do this Service Bulletin are included in SPECIAL TOOLS, FIXTURES, EQUIPMENT AND CONSUMAB LES: refer to the applicable CMM. 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 (MDLPS, M-DLNDT and PCS) are in the Standard Practices Manual. A. Procedure for visual inspection of the internal diameter of the bogie beam: refer to the Aircraft Maintenance Manual, CMM 32-12-01, CMM 32-12-04, CMM 32-12-05, CMM 32-11-70, CMM 32-11-94, CMM 32-11-95, CMM 32-11-74 and Figures 1 to 4 of this Service Bulletin. (1) Make sure the aircraft is in a safe condition: refer to the Aircraft Maintenance Manual. (2) Raise the aircraft on jacks: refer to the Aircraft Maintenance Manual. NAS1149F0463P 8 Washer - Replacement Parts (D) - NAS1149F0363P 2 Washer - - NAS1611-129A 4 Seal - - MS24665-153 18 Split Pin - - NSA5060E5 8 Nut - - AN960C516L 16 Washer - - NAS1149C0563R 16 Washer - - MS24665-132 4 Split Pin - - NAS1149F0332P 8 Washer - - MS17826-4 4 Nut - - NAS1021N3 6 Nut - -

Part No. Special Tool Function OLYMPUS Model No. IV7650A-2 Boroscope To inspect the bogie beam internally DRT67093 Holding Tool To hold the spigot nuts DRT67088 Torque Spanner To remove/torque spigots New Part No. Qty. Per Unit Keyword Old Part No. Instructions/ Disposition IC

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WARNING: DO NOT GET HYDRAULIC FLUID ON YOUR SKIN OR IN YOUR EYES. DO NOT BREATHE THE FUMES. ONLY USE IN A LOCATION THAT HAS A CONTINUOUS FLOW OF CLEAN AIR. HYDRAULIC FLUID IS POISONOUS AND DANGEROUS. (3) Disassemble the main landing gear complete sufficiently to remove the bogie and dressings (1-60, CMM 32-12-01 and CMM 32-11-70): refer to the Aircraft Maintenance Manual and Airbus cover Service Bulletins A330-32-3225 and A340-32-4268. NOTE: This inspection check can be done with the bogie and dressings and the wheels and brakes attached. NOTE: Protect the ends of the electrical harnesses and hydraulic hoses, to prevent contamination or damage. (4) Disassemble the bogie assembly to remove the diaphragms: (a) Remove the split pin (1-70, CMM 32-12-05 and CMM 32-11-74), remove the nut (1-80, CMM 32-12-05 and CMM 32-11-74), the washers (1-90, CMM 32-12-05 and CMM 32-11-74) and the bolt (1-100, CMM 32-12-05 and CMM 32-11-74). (b) Remove the nut (1-110, CMM 32-12-05 and CMM 32-11-74) and the jacking dome (1-120, CMM 32-12-05 and CMM 32-11-74). (c) Remove the bolts (1-130, CMM 32-12-05 and CMM 32-11-74), the washers (1-140, CMM 32-12-05 and CMM 32-11-74) and the locking segment (1-150, CMM 32-12-05 and CMM 32-11-74). (d) Use the Holding Tool DRT67093 to hold the axle spigot nut (1-170, CMM 32-12-05 and CMM 32-11-74) and use the Torque Spanner DRT67088 to remove the spigot (1-160, CMM 32-12-05 and CMM 32-11-74). (e) Remove the axle spigot nut (1- 170, CMM 32-12-05 and CMM 32-11-74). (f) Remove the diaphragm (1-180, CMM 32-12-05 and CMM 32-11-74). (g) Remove the split pin (2-20, CMM 32-12-05 and CMM 32-11-74), remove the nut (2-30, CMM 32-12-05 and CMM 32-11-74), the washers (2-40, CMM 32-12-05 and CMM 32-11-74) and the bolt (2-50, CMM 32-12-05 and CMM 32-11-74). (h) Remove the nut (2-60, CMM 32-12-05 and CMM 32-11-74) and the jacking dome (2-70, CMM 32-12-05 and CMM 32-11-74). (i) Remove the towing bracket subassembly (2-10, CMM 32-12-05 and CMM 32-11-74). (j) Remove the bolts (2-110, CMM 32-12-05 and CMM 32-11-74), the washers (2-120, CMM 32-12-05 and CMM 32-11-74) and the locking segment (2-130, CMM 32-12-05 and CMM 32-11-74). (k) Use the Holding Tool DRT67093 to hold the axle spigot nut (2-150, CMM 32-12-05 and CMM 32-11-74) and use the Torque Spanner DRT67088 to remove the spigot (2-140, CMM 32-12-05 and CMM 32-11-74). (l) Remove the axle spigot nut (2- 150, CMM 32-12-05 and CMM 32-11-74).

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(m) Remove the diaphragm (2-170, CMM 32-12-05) or (2-160, CMM 32-11-74). WARNING: DO NOT GET CLEANING AGENTS ON YOUR SKIN, IN YOUR EYES OR NEAR A FLAME. DO NOT BREATHE THE FUMES. ONLY USE IN A LOCATION THAT HAS A CONTI NUOUS FLOW OF CLEAN AIR. CLEANING AGENTS ARE POISONOUS AND FLAMMABLE. (5) Clean all the internal surfaces of th e bogie beam (3-180, CMM 32-12-05 and CMM 32-11-74) 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. (6) Use a boroscope to fully inspect the internal diameter of the bogie beam (3-180, CMM 32-12-05 and CMM 32-11-74) for corrosion or damage to the protective treatments: refer to CHECK in the applicable CMM and Figures 3 and 4. NOTE: If there is no damage to the protective treatments record this on the proforma in Appendix D and return a completed copy to the address shown in Appendix D. NOTE: This inspection check can be done with the bogie and dressings and the wheels and brakes attached. (7) If you find corrosion or damage to the protective treatments: refer to Appendix A of this Service Bulletin for details of repair. (8) Apply protective treatment ARDROX AV1 00D to the internal diameter of the bogie beam (3-180, CMM 32-12-05 and CMM 32-11-74): refer to PCS-2800. (9) Assemble the diaphragms to the bogie assembly: (a) Refer to PCS-7302. Apply grease paste, Material Ref. Item 04-578 to: 1 The face of the spigot (2-140, CMM 32-12-05 and CMM 32-11-74) that will be against the diaphragm (2-170, CMM 32-12-05) or (2-160, CMM 32-11-74). 2 The thread of the spigot (2-140, CMM 32-12-05 and CMM 32-11-74). 3 The rounded part of the axle spigot nut (2-150, CMM 32-12-05 and CMM 32-11-74). 4 The threads of the bolt (2-110, CMM 32-12-05 and CMM 32-11-74). 5 The face of the locking segment (2-130, CMM 32-12-05 and CMM 32-11-74) that will be against the diaphragm (2-170, CMM 32-12-05) or (2-160, CMM 32-11-74). 6 The curved surface of the diaphragm (2-170, CMM 32-12-05) or (2-160, CMM 32-11-74) where it will touch the axle (3-10, CMM 32-12-05 and CMM 32-11-74).

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# SERVICE BULLETIN
(b) Refer to PCS-7200. Apply sealant, Material Ref. Item 09-510A, to the external diameter of the diaphragm (2-170, CMM 32-12-05) or (2-160, CMM 32-11-74) where it will touch the bogie beam and axle subassembly (3-1, CMM 32-12-05 and CMM 32-11-74). (c) Install the diaphragm (2-170, CMM 32-12-05) or (2-160, CMM 32-11-74) in the bogie beam and axle subassembly (3-1, CMM 32-12-05 and CMM 32-11-74). Remove all of the unwanted sealant from the joint. NOTE: Make sure the diaphragm is installed with the flat at the bottom of the bogie beam assembly. (d) Use the Holding Tool DRT67093 to install the axle spigot nut (2-150, CMM 32-12-05 and CMM 32-11-74) in the axle (3-10, CMM 32-12-05 and CMM 32-11-74) and hold it in position. (e) Install the spigot (2-140, CMM 32-12-05 and CMM 32-11-74) through the diaphragm (2-170, CMM 32-12-05) or (2-160, CMM 32-11-74) and the axle (3-10, CMM 32-12-05 and CMM 32-11-74) into the axle spigot nut (2-150, CMM 32-12-05 and CMM 32-11-74). (f) Use the Torque Spanner DRT67088 to torque the spigot (2-140, CMM 32-12-05 and CMM 32-11-74) to between 100 and 120 N m (73.80 and 88.56 lbf ft). (g) Remove the Holding Tool DRT67093. (h) Install the locking segment (2-130, CMM 32-12-05 and CMM 32-11-74), the washers (2-120, CMM 32-12-05 and CMM 32-11-74) and the bolts (2-110, CMM 32-12-05 and CMM 32-11-74). (i) Torque the bolts (2-110, CMM 32-12-05 and CMM 32-11-74) to between 3 and 4 N m (27 and 36 lbf in). (j) Safety the bolts (2-110, CMM 32-12-05 and CMM 32-11-74) with lockwire: refer to PCS-7610. (k) Refer to PCS-7200. Apply sealant, Material Ref. Item 09-510A, to: 1 The heads of the bolts (2-110, CMM 32-12-05 and CMM 32-11-74). 2 The joint between the diaphragm (2-170, CMM 32-12-05) or (2-160, CMM 32-11-74) and the bogie beam assembly (3-20, CMM 32-12-05 and CMM 32-11-74). NOTE: Do not fill the space between the bottom of the diaphragm and the bogie beam assembly with sealant. (l) Refer to PCS-7302. Apply grease paste, Material Ref. Item 04-578, to: 1 The diameter and threads of the jacking dome (2-70, CMM 32-12-05 and CMM 32-11-74). 2 The face of the jacking dome (2-70, CMM 32-12-05 and CMM 32-11-74) that will touch the towing bracket subassembly (2-10, CMM 32-12-05 and CMM 32-11-74).

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3 The threads of the bolt (2-50, CMM 32-12-05 and CMM 32-11-74). (m) Install the towing bracket subassembly (2-10, CMM 32-12-05 and CMM 32-11-74). (n) Install the jacking dome (2-70, CMM 32-12-05 and CMM 32-11-74). (o) Install the nut (2-60, CMM 32-12-05 and CMM 32-11-74). (p) Torque the nut (2-60, CMM 32-12-05 and CMM 32-11-74) to 136 N m (100 lbf ft) and then reduce the torque to zero. (q) Do para (p) two more times. (r) Torque the nut (2-60, CMM 32-12-05 and CMM 32-11-74) to 81 N m (60 lbf ft). NOTE: You can increase the torque to a maximum of 339 N m (250 lbf ft) to let you install the bolt (2-50, CMM 32-12-05 and CMM 32-11-74). (s) Install the bolt (2-50, CMM 32-12-05 and CMM 32-11-74), the washers (2-40, CMM 32-12-05 and CMM 32-11-74) and the nut (2-30, CMM 32-12-05 and CMM 32-11-74)

. (t) Torque the nut (2-30, CMM 32-12-05 and CMM 32-11-74) to between 2,70 and 3,15 N m (24 and 28 lbf in). (u) Install the split pin (2-20, CMM 32-12-05 and CMM 32-11-74) and safety it: refer to PCS-7610. (v) Refer to PCS-7200. Apply sealant, Material Ref. Item 09-510A, to: 1 The hexagonal nut of the jacking dome (2-70, CMM 32-12-05 and CMM 32-11-74). 2 The nut (2-60, CMM 32-12-05 and CMM 32-11-74). 3 The bolt (2-50, CMM 32-12-05 and CMM 32-11-74), the washers (2-40, CMM 32-12-05 and CMM 32-11-74) and the nut (2-30, CMM 32-12-05 and CMM 32-11-74). (w) Refer to PCS-7302. Apply grease paste, Material Ref. Item 04-578, to: 1 The face of the spigot (1-160, CMM 32-12-05 and CMM 32-11-74) that will be against the diaphragm (1-180, CMM 32-12-05 and CMM 32-11-74). 2 The thread of the spigot (1-160, CMM 32-12-05 and CMM 32-11-74). 3 The rounded part of the axle spigot nut (1-170, CMM 32-12-05 and CMM 32-11-74). 4 The threads of the bolt (1-130, CMM 32-12-05 and CMM 32-11-74). 5 The face of the locking segment (1-150, CMM 32-12-05 and CMM 32-11-74) that will be against the diaphragm (1-180, CMM 32-12-05 and CMM 32-11-74). 6 The curved surface of the diaphragm (1-180, CMM 32-12-05 and CMM 32-11-74) where it will touch the axle (3-10, CMM 32-12-05 and CMM 32-11-74).

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(x) Refer to PCS-7200. Apply Sealant, Material Ref. Item 09-510A, to the external diameter of the diaphragm (1-180, CMM 32-12-05 and CMM 32-11-74), where it will touch bogie beam and axle subassembly (3-1, CMM 32-12-05 and CMM 32-11-74). (y) Install the diaphragm (1-180, CMM 32-12-05 and CMM 32-11-74) in the bogie beam and axle subassembly (3-1, CMM 32-12-05 and CMM 32-11-74). Remove all of the unwanted sealant from the joint. NOTE: Make sure the diaphragm is installed with the flat at the bottom of the bogie beam assembly. (z) Use the Holding Tool DRT67093 to install the axle spigot nut (1-170, CMM 32-12-05 and CMM 32-11-74) in the axle (3-10, CMM 32-12-05 and CMM 32-11-74) and hold it in position. (aa) Install the spigot (1-160, CMM 32-12-05 and CMM 32-11-74) through the diaphragm (1-180, CMM 32-12-05 and CMM 32-11-74) and the axle (3-10, CMM CMM 32-12-05 and CMM 32-11-74) into the axle spigot nut (1-170, CMM 32-12-05 and CMM 32-11-74). (ab) Use the Torque Spanner DRT67088 to torque the spigot (1-160, CMM 32-12-05 and CMM 32-11-74) to between 100 and 120 N m (73.80 and 88.56 lbf ft). (ac) Remove the Holding Tool DRT67093. (ad) Install the locking segment (1-150, CMM 32-12-05 and CMM 32-11-74), the washers (1-140, CMM 32-12-05 and CMM 32-11-74) and the bolts (1-130, CMM 32-12-05 and CMM 32-11-74). (ae) Torque the bolts (1-130, CMM 32-12-05 and CMM 32-11-74) to between 3 and 4 N m (27 and 36 lbf in). (af) Safety the bolts (1-130, CMM 32-12-05 and CMM 32-11-74) with lockwire: refer to PCS-7610. (ag) Refer to PCS-7200. Apply sealant, Material Ref. Item 09-510A, to: 1 The heads of the bolts (1-130, CMM 32-12-05 and CMM 32-11-74). 2 The joint between the diaphragm (1-180, CMM 32-12-05 and CMM 32-11-74) and the bogie beam assembly (3-20, CMM 32-12-05 and CMM 32-11-74). NOTE: Do not fill the space between the bottom of the diaphragm and the bogie beam assembly with sealant. (ah) Refer to PCS-7302. Apply grease paste, Material Ref. Item 04-578, to: 1 The diameter and threads of the jacking dome (1-120, CMM 32-12-05 and CMM 32-11-74). 2 The threads of the bolt (1-100, CMM 32-12-05 and CMM 32-11-74). (ai) Install the jacking dome (1-120, CMM 32-12-05 and CMM 32-11-74).

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(aj) Install the nut (1-110, CMM 32-12-05 and CMM 32-11-74). (ak) Torque the nut (1-110, CMM 32-12-05) to 40 N m (30 lbf ft). NOTE: You can increase the torque to the nearest locking position. OR (al) Torque the nut (1-110, CMM 32-11-74) to 136 N m (100 lbf ft) and then reduce the torque to zero. (am) Do para (al) two more times. (an) Torque the nut (1-110, CMM 32-11-74) to 81 N m (60 lbf ft). NOTE: You can increase the torque to a maximum of 339 N m (250 lbf ft) to let you install the bolt (1-100, CMM 32-12-05 and CMM 32-11-74). (ao) Install the bolt (1-100, CMM 32-12-05 and CMM 32-11-74), the washers (1-90, CMM 32-12-05 and CMM 32-11-74) and the nut (1-80, CMM 32-12-05 and CMM 32-11-74)

. (ap) Torque the nut (1-80, CMM 32-12-05 and CMM 32-11-74) to between 2,70 and 3,15 N m (24 and 28 lbf in). (aq) Install the split pin (1-70, CMM 32-12-05 and CMM 32-11-74) and safety it: refer to PCS-7610. (ar) Refer to PCS-7200. Apply sealant, Material Ref. Item 09-510A, to: 1 The hexagonal nut of the jacking dome (1-120, CMM 32-12-05 and CMM 32-11-74). 2 The nut (1-110, CMM 32-12-05 and CMM 32-11-74). 3 The bolt (1-100, CMM 32-12-05 and CMM 32-11-74), the washers (1-90, CMM 32-12-05 and CMM 32-11-74) and the nut (1-80, CMM 32-12-05 and CMM 32-11-74). (10) Install the bogie and dressings (1-60, CMM 32-12-01 and CMM 32-11-70) to the main strut and dressings (1-70, CMM 32-12-01 and CMM 32-11-70). (11) Set the proximity switches and targets: refer to ASSEMBLY in the applicable CMM. (12) Complete all checks on the main landing gear: refer to the Aircraft Maintenance Manual. (13) Lower the aircraft and remove the jacks: refer to the Aircraft Maintenance Manual. B. Identification (1) After you have done this Service Bulletin: - write Service Bulletin number A33/34-32-272 in the applicable aircraft and main landing gear records.

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Main Landing Gear Complete - Area of Inspection Figure 1 AREA OF INSPECTION

A340A4408-1

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Bogie Beam - Area of Inspection Figure 2 A340A4409-1 

## Y

Y (SEE FIGURE 4) 

## Z (SEE FIGURE 3)



## Z

BOGIE ASSEMBLY SHOWN WITH DIAPHRAGMS ATTACHED
OTHER PARTS REMOVED FROM ILLUSTRATION FOR CLARITY THIS LEVEL OF DISASSEMBLY IS NOT REQUIRED

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Bogie Beam - Area of Inspection Figure 3 SECTION 

## Z-Z

A340A4410-1 AREA OF INTERNAL DIAMETER INSPECTION

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Bogie Beam - Area of Inspection Figure 4 SECTION 

## Y-Y AREA OF INTERNAL DIAMETER INSPECTION (360 DEGREES)

A340A4411-1

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4. Messier-Dowty and Messier Services Contacts A. Refer to the Messier-Dowty website ( messier-dowty.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-Dowty SA Zone Aeronautique L. Breguet BP10 78142 Velizy Cedex FRANCE Tel : +33 146 29 18 00 Fax : +33 146 29 8770 Customer Support Centers Messier-Dowty CSC Americas 620 Herndon Parkway, Suite 200 Herndon Virginia 20170 USA Tel : 703-450-8200 Fax : 703-430-1621 Messier-Dowty (Singapore) Pte. Ltd. Tampines South Post Office 21 Loyang Crescent, SINGAPORE 508985 Tel : (65) 6543 0626 Fax : (65) 6542 2718 Messier-Dowty CSC EAME Zone Aeronautique L. Breguet BP10 78142 Velizy Cedex FRANCE Tel : +33 146 29 18 00 Fax : +33 146 29 18 18

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

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# SERVICE BULLETINMessier-Dowty Ltd

Appendix A Service Bulletin No.A33/34-32-272 Page 1 of 6 CAGE: K0654 Cheltenham Road, Gloucester, GL2 9QH, England Telephone: +44 (0) 1452 712424 Fax: +44 (0) 1452 713821 

# SERVICE BULLETIN

APPENDIX A METHOD OF REPAIR TO THE BO GIE BEAM PROTECTIVE TREATMENTS 1. Procedure A. Method of repair to the bogie beam if the pai nt 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 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 locally mask the surrounding area and strip 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 D, Figure 2. Return a completed copy of Appendix D to the address shown in Appendix D. (3) Visually check the cadmium plating. (a) If the cadmium plating is satisfactory (yellow/brown in color) NOTE: Check the depth of cadmium plating with a Permascope. The depth of cadmium plating must be 0,01 to 0,02 mm (0.0004 to 0.0008 in). (b) If the cadmium plating depth is satisfactory 1 Apply paint: refer to PCS-2500. NOTE: Before applying top coat apply 2 coats of primer with total 30 to 40 microns dry film thickness. (c) If the cadmium plating is damaged (grey in color) or the plating depth is not satisfactory but the base material is not corroded 1 Carefully remove the cadmium plating using Scotchbrite or fine emery paper. 2 Measure area of cadmium plate removed NOTE: Measure and record the location of the reworked area in Appendix D, Figure 2. Return a completed copy of Appendix D to the address shown in Appendix D.

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(d) Check to make sure the base material is not corroded 1 Apply cadmium plate: refer to PCS-2141 and Appendix C of this Service Bulletin. NOTE: Messier-Dowty Limited tells you that you can cadmium plate to a maximum area of 46451,52 mm square (72 square in) but you must only do it in steps of 7741,92 mm square (12 square in) maximum area at a time. The area around the 7741,92 mmsquare (12 square in) must be masked off before you cadmium plate. NOTE: If you have used cadmium plating solution and a procedure that has satisfactorily passed the hydrogen embrittlement test in AMS2451/4 then de-embrittlement of the bogie beam after cadmium plating is not required. 2 Check the depth of cadmium plating with a Permascope. NOTE: The depth of cadmium plating must be 0,01 to 0,02 mm (0.0004 to 0.0008 in). 3 Apply paint: refer to PCS-2500. NOTE: Before applying top coat apply 2 coats of primer with total 30 to 40 microns dry film thickness. (4) If the base material has corrosion or damage (a) Use Scotchbrite, fine emery paper or low powered hand tools to locally repair the corroded or damaged area: refer to M-DLPS1004-4-1 and Figure 1 or Figure 2 of this Appendix. WARNING: BLEND RADIUS MUST BE APPLIED ALL AROUND THE REWORKED AREA. MAKE SURE ALL BLENDS ARE SMOOTH. (b) 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. (c) Measure the depth and area of material removed, this can be done using Plastiform KVAD. NOTE: Measure and record the location of the reworked area in Appendix D, Figure 2. Return a completed copy of Appendix D to the address shown in Appendix D.

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(d) Inspect the repaired area for corrosion or cracking: refer to M-DLNDT 17 and Appendix B of this Service Bulletin. NOTE: After NDT if you have indications of corrosion or cracking contact your regional Messier-Dowty Customer Support Center. (e) If the depth of material removed is more than 0,038 mm (0.0015 in) rotary flap peen the repaired area: refer to PCS-2302. (f) Apply cadmium plate: refer to PCS-2141 and Appendix C of this Service Bulletin. NOTE: Messier-Dowty Limited tells you that you can cadmium plate to a maximum area of 46451,52 mm square (72 square in) but you must only do it in steps of 7741,92 mm square (12 square in) maximum area at a time. The area around the 7741,92 mm square (12 square in) must be masked off before you cadmium plate. NOTE: If you have used cadmium plating solution and procedure that has satisfactorily passed the hydrogen embrittlement test in AMS2451/4 then de-embrittlement of the bogie beam after cadmium plating is not required. (g) Check the depth of cadmium plating with a Permascope. NOTE: The depth of cadmium plating must be 0,01 to 0,02 mm (0.0004 to 0.0008 in). (h) Apply paint: refer to PCS-2500. NOTE: Before applying top coat apply 2 coats of primer with total 30 to 40 microns dry film thickness. (5) After you have done this repair refer to this Service Bulletin and continue with step 3.A.(8).

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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
A340A4444-1 0,30mm (0.012in) MAXIMUM 100,00mm (3.937in) MINIMUM IN AREA B or 10.00mm (0.0394in) MINIMUM IN AREA A BLEND RADIUS WITHIN THE POSITION SHOWN (SEE VIEW ABOVE) AXLE

238,85mm (9.404in) DIAMETER AREA B REMOVE DAMAGED PROTECTION AND ANY 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 PROTECTION AND ANY CORRODED MATERIAL. USE 10mm (0.394in) MINIMUM BLEND RADIUS WITHIN THIS LENGTH

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Bogie Beam - Area of Repair Figure 2 100,00mm (3.937in) RADIUS

20,00mm (0.787in)

1 5 D E

G

R

E

E

S 1 5 D E

G

R

E

E

S

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

A330A4445-1 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 PROTECTION AND ANY CORRODED MATERIAL. USE 100mm (3.937in) MINIMUM BLEND RADIUS

WITHIN THIS LENGTH AREA A REMOVE DAMAGED PROTECTION AND ANY CORRODED MATERIAL. USE 10mm (0.394in) MINIMUM BLEND RADIUS WITHIN THIS LENGTH

MAKE EDGES SMOOTH 10,00mm (0.394in) MINIMUM BLEND RADIUS

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# SERVICE BULLETINMessier-Dowty Ltd

Appendix B Service Bulletin No.A33/34-32-272 Page 1 of 6 CAGE: K0654 Cheltenham Road, Gloucester, GL2 9QH, England Telephone: +44 (0) 1452 712424 Fax: +44 (0) 1452 713821 

# SERVICE BULLETIN

APPENDIX B MESSIER-DOWTY LIMITED GLOUCESTER NDT PRODUCT SUPPORT TECHNIQUE NO. PS 351ET ISSUE 2 EDDY CURRENT INSPECTION OF AIRBUS A330/340 MAIN LANDING GEAR BOGIE BEAM 1. Scope A. This NDT technique is designed to detect cracking in the bogie beam bore, following the repair of visually identified areas of corrosion. NOTE: The inspection area is limited to locally repaired areas of the bore only. B. The repaired areas are to have a 100% complete Eddy Current inspection check. C. The controlling specification for this technique is Messier-Dowty Limited NDT17. 2. Equipment Required A. The equipment required to do the inspection is listed below (1) Phasec 2d, Eddy Current Flaw Detector. (2) Calibration Block DRT95819: refer to Figure 1. The block contains a total of 4 calibration slots (0,2mm and 0,6mm slots inboth the longitudinal and circumferential directions). (3) Probe, Shielded Spade, 500kHz. OR (4) Probe, Shielded Pencil, 500kHz. NOTE: The settings detailed in 5.A(1) are relevant to the specified equipment only. This inspection may be achieved with the use of similar equipments with phase discrimination capabilities when specifically agreed by the approved NDT Level 3 specialist nominated by Messier-Dowty Limited. (5) If inspection equipment is required contact your regional Messier-Dowty Customer Support Center. 3. Personnel A. The inspection procedure is to be carried out by NDT personnel who are certified to EN4179 level 2 (or equivalent - as agreed by the Messier-Dowty Ltd Nominated Level 3) in the Eddy Current method as detailed in Messier-Dowty Limited NDT10. 4. Preparation A. Before the inspection technique can continue (1) Make sure the bogie beam is removed from the aircraft. (2) Make sure the inspection area is th oroughly clean, degreased and free from any foreign matter. Inspection shall take place after repair and before protective treatments have been applied.

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5. Examination Procedure A. Instrument Settings (1) Press ‘Menu’ and install the settings listed in the table that follows.

(2) Sensitivity (a) Connect the probe and lead to the test set. Select the operating screen. Position probe on the purpose made Calibration Block DRT95819, away from slots and edges. Do a 2 second press of the ‘Exec/Load’ button to automatically select. (b) Do a 2 second press of the ‘Balance/lift-off’ button to initiate automatic probe balancing and lift off adjustment. Manuallyadjust the lift off signal phase angle to the 9 o’clock position if required. GAIN XY 1 20.0/40.0 ACTIVE None MODE Normal Single PHASE As reqd ACTION Off PROBE ID Unknown FREQ 1 KHZ 500 STRETCH 50 Ms LOAD UH 47 FILTER 1 BP Ratio SHAPE Sector DRIVE DB 0 HP/LP 1 DC/200 TOP/BTM Off/Off BAL/CLR MOD Single INPUT GAIN Low LFT/RGHT Off/Off PROBE 1 Locator START/END Off/Off POWER DOWN Off IN/OUTER Off/Off KEY CLICK Off CONTRAST As reqd DISPLAY Spot SCREEN MODE Normal GRATICULE Grid 1 SPOT XY 98/-25 RESET Exec

SPOT INFO None TRACE THICKEN Off PERSIST 0.5S LANGUAGE English SWEEP 0.5S BAUD 115200 TIME As reqd SAVE Setup DATE As reqd ANALOGUE O/P 1 X1 RECALL Setup ANALOGUE O/P 2 X1 TRACE REC Off CODE Exec

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(c) Slide the probe tip over the 0,2mm depth circumferencial slot in the longitudinal direction (at 90 Degrees to slot length) and set the gain to give a working spot deflection of 2 main scale divisions, or a minimum of 40% full screen height if an alternative Eddy Current Flaw detector is used. (d) Re-check the sensitivity setting by moving the probe off, balancing, and then back over the slot as necessary to achieve a consistent calibration and sensitivity setting. If necessary, adjust the gain to achieve the detailed working spot deflection and the phase angle such that the lift off signal is horizontal and the calibration signal from the 0.2mm slot is vertical. See Figure 2. Make sure the sensitivity and phase relationship is as Figure 2 and adjust as necessary. (e) Check the response of the equipment by running the probe over the 0,6 mm depth circumferencial slot, and ensure the associated increase in amplitude. B. Procedure NOTE: The inspection procedure is to be carried out by NDT personnel who are certified to EN4179 level 2 (or equivalent - as agreed by the Messier-Dowty Ltd Nominated Level 3) in the Eddy Current method as detailed in Messier-Dowty Limited NDT10. (1) Place the probe on component, balance probe and check lift off. Ensure sensitivity and phase relationship is as Figure 2 and adjust as necessary. (2) To assist with scanning and coverage of the inspection area, when possible create a 10mm x 10mm grid pattern over the complete repaired/test area and do a series of horizontal scans at 1mm increments with an overlap of grid lines ensuring 100% coverage of the scan area. Re-balance at each new grid square. When such a grid pattern cannot be achieved, do a series of vertical and horizontal scans at 1mm increments ensuring 100% coverage of the repaired/test area. (3) Repeat para 5.A.(2)(b), Para 5.A.(2)(c) and Para 5.A.(2)(d) using the 0,2mm depth of axial slot and Para 5.A(2)(e) using the 0,6 mm depth axial slot. (4) Repeat para 5.B(1) and 5.B(2) in the opposite direction at 90 Degrees to the direction of the initial scan. C. Examination standard (1) Any indication (regardless of amplitude) that cannot be attributed to edge effect, geometry, lift off or probe handling is to be considered a “relevant indication”. All indications are to be reported, showing their position and length. (2) The indication length is to be measured from a vertical spot movement of 1 main scale division while scanning towards the indication at 90 Degrees to the major dimension of the indication. D. Reporting procedure (1) All indications are to be reported showing indication position, l ength and direction. If possible equipment screen displays, showing both lift off signals and indication signals, should be obtained and included in the report.

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E. Estimated manhours (1) As required. F. Additional information (1) Any suspect indications shall be cause fo r rejection and for further investigation. (2) If this instruction cannot be successfully completed the inspection is to cease and the relevant NDT Level 3 informed.

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Calibration Block - DRT95819 Figure 1

Screen Display Figure 2 LIFT OFF SIGNAL AT 9 O'CLOCK 0,2mm SLOT SIGNAL RESPONSE

A340A4483-1 One mainscale division

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# SERVICE BULLETINMessier-Dowty Ltd

Appendix C Service Bulletin No.A33/34-32-272 Page 1 of 4 CAGE: K0654 Cheltenham Road, Gloucester, GL2 9QH, England Telephone: +44 (0) 1452 712424 Fax: +44 (0) 1452 713821 

# SERVICE BULLETIN

APPENDIX C PROCEDURE FOR LOW EMBRITTLEMENT BR USH CADMIUM PLATING THE BOGIE BEAM 1. Scope A. Method of cadmium plating the bogie beam: refer to PCS-2141 and Messier-Dowty Standard Practices Manual 20-00-10. B. This appendix describes the materials and procedures for the local deposition of cadmium on steels of all strength levels and on non-ferrous alloys. C. The process is to be used to re-protect surfaces which have been reworked after damage during manufacture or in service, or to apply a supplementary plating to bare areas resulting from jigs or fixtures during bath plating. D. General details of the equipment required are given in M-DLPS118, Brush Plating. E. No reference is made to details of procedu re normally associated with proper shop practice and good workmanship. Specific training in the skills of brush plating is a requirement of this specification. 2. Associated Specifications A. M-DLPS100 Cadmium Plating. B. M-DLPS118 Brush Plating. C. M-DLPS131 Cadmium Plat ing of Ultra-high Tensile Steels. D. ISO 9227 ) Salt Spray Corrosion Tests in artificial atmospheres. (BS 7479) ) 3. Health and Safety A. The plating operation must be carried out in a well ventilated area with local fume extraction as cadmium is toxic and the fumes evolved durin g plating are irritants. Consult the plating solution supplier's health and safety data sheet for further information. B. Rubber or plastic gloves must be worn for the cleaning and plating processes. C. After using this process, hands must be thoroughly washed. D. There must be no eating, drinking or smoking in the workshop. 4. Solutions Required A. Plating Solutions (1) Plating solutions approved for use against this specification are: (a) Selectron LHE Cadmium Plating Solution Code No SPS-5070.
or (b) Selectron Cadmium (No Bake) Solution Code No 2023/1.
or

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(c) Metadalic Cadmium Plating Solution Code No 2023. NOTE: Alternative plating solutions certified to meet the hydrogen embrittlement test requirements of AMS2451/4 can be used. B. Passivation Solution (1) Sodium Dichromate: 135 - 175g (2) Sulphuric Acid: 5 - 8g (3) Water, to make: 1 litre 5. General Requirements A. Thorough operator training is essential. All brush plating operators are required to hold a certificate of competence. An operator training service is offered by Sifco Selective Plating Ltd and by Metadalic Ltd. B. Polish to remove corrosion using hand tools: refer to M-DLPS1004-4-1. C. Shot peened surfaces which have been reworked, must be re-shot peened or flap peened prior to brush plating. D. Where brush cadmium plating is called for asa supplement to bath plating, it should wherever possible, be carried out immediately following bath plating and before de-embrittlement. When this process is used to repair damaged cadmium, or parts reworked as in paragraph 5.C. de-embrittlement is not required. E. Unless otherwise stated on the Drawing, the minimum thickness of plate shall be 10 μ m (0.0004 in). 6. Procedure A. Degrease the area to be plated, including the surrounding area, with a solvent and wipe dry with a cloth or absorbent paper. B. Mask as necessary, to define the plating area. When repairing a prev iously cadmium plated area, the brush plating must overlap the existing cadmium by about 4 mm (0.157 in). C. Abrade the area to be plated, using a water wetted abrasive paper or fine Scotch-Brite pad. Rinse and wipe dry with a clean tissue or absorbent cloth. D. Before plating begins, the area must be wetted with the plating solution, ensuring freedom from liquid breaks. If necessary the area must be further cleaned to provide a liquid-break free condition. E. Soak a tampon with the plating solution and start the appropriate tampon movement over the plating area, before switching on the current. F. Plate at 15 - 20V until a visible layer of cadmium has formed, then reduce the voltage to achieve 0,93A/cm2 (6A/in2) of anode contact area. Continue plating until the calculated ampere hours have elapsed. To calculate the ampere hours required, consult the technical data provided by the plating solution supplier: FACTOR X AREA X THICKNESS OF PLATING = AMPERE HOURS G. Rinse in cold water.

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H. If the process has been carried out as re-work, swab with the passivating solution until a light golden colour is obtained. This cannot normally be expected to produce a good cosmetic match, but the corrosion protection will be fully restored. Rinse in cold water and dry by wiping with a clean cloth or absorbent paper or by means of an air blast. 7. Removal of Defective Deposits A. Defective deposits may be removed by reversing the polarity (i.e. with the component connected to the anode lead and the tampon connected to the cathode and anodically stripping the plate). Replating can be carried out from 6.D using a freshly prepared tampon. 8. Inspection A. The appearance of the plate shall be smooth, and free from porosity and burned areas. The plated area shall blend with the surroundi ng plating although appearance mis-match is inevitable and acceptable. B. The passivation treatment shall be adherent and free from powder. C. There shall be no evidence of separation of the plate when tested as follows: (1) Apply a strip of 3M's No 250 tape using firm finger pressure and then remove the tape by pulling rapidly in a perpendicular direction. Examine the adhesive side of the tape for the presence of cadmium plate. D. The thickness of the plate shall be a minimum of 10 μ m (0.00004 in) unless otherwise specified. E. Thickness shall be measured using a calibrated electronic instrument, such as the Fischer Permascope. 9. Quality Control A. Each operator shall produce a test panel annua lly to demonstrate satisfactory performance. (1) A 15 x 10 cm (6 x 4 in) low alloy stee l test panel shall be dull cadmium plated to M-DLPS100 all over, except for an area of approximately 10 x 5 cm (4 x 2 in) on one face, which shall be left bare. (2) Brush cadmium plate the bare area to this specification. B. The brush plated deposit shall meet the ins pection requirements of paragraph 8 above and after 336 hours salt spray test to ISO 9227 NSS test there shall be no rusting of the base metal.

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# SERVICE BULLETINMessier-Dowty Ltd

Appendix D Service Bulletin No.A33/34-32-272 Page 1 of 4 CAGE: K0654 Cheltenham Road, Gloucester, GL2 9QH, England Telephone: +44 (0) 1452 712424 Fax: +44 (0) 1452 713821 

# SERVICE BULLETIN

APPENDIX D AIRBUS A330/340 - MAIN LANDING GEAR - BOGIE AND DRESSINGS PROFORMA FOR REPORTING RESULTS OF IN SPECTION SERVICE BULL ETIN A33/34-32-272.

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 D 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.

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Bogie Beam - Developed View of Bogie Beam Bore - Area of Repair Figure 1 A340A4505-1 PART SECTION 

## Z-Z REWORK 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

CADMIUM PLATE

PAINT 

## THIS IS AN EXAMPLE OF HOW TO RECORD

REWORKED AREA DIMENSIONS AND LOCATION

DAMAGE FOUND

NO DAMAGE FOUND RECORD RESULTS ON PAGE 3 OF APPENDIX D. RETURN PAGES 1 AND 3 OF APPENDIX D

RETURN PAGE 1 AND PAGE 3 OF APPENDIX D 0/360 DEGREES

180 DEGREES 270 DEGREES 90 DEGREES

0 DEGREES 360 DEGREES 180 DEGREES 270 DEGREES 90 DEGREES

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USE THE ILLUSTRATION BELOW TO MARK THE LOCATION OF REPAIR

Bogie Beam - Developed View of Bogie Beam Bore - Area of Repair Figure 2 A340A4506-1 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 REWORKED AREA 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

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