LIST OF EFFECTIVE PAGES The effective pages to this Service Bulletin following incorporation of Revision 5 are as follows: Page Revision Number Revision Date

Bulletin R 1 5 Mar.21/11 R 2 5 Mar.21/11 R 3 5 Mar.21/11 R 4 5 Mar.21/11 R 5 5 Mar.21/11 R 6 5 Mar.21/11 R 7 5 Mar.21/11 R 8 5 Mar.21/11 R 9 5 Mar.21/11 R 10 5 Mar.21/11 R 11 5 Mar.21/11 R 12 5 Mar.21/11 R 13 5 Mar.21/11 R 14 5 Mar.21/11 R 15 5 Mar.21/11 R 16 5 Mar.21/11 R 17 5 Mar.21/11 R 18 5 Mar.21/11 R 19 5 Mar.21/11 R 20 5 Mar.21/11 R 21 5 Mar.21/11 R 22 5 Mar.21/11 R 23 5 Mar.21/11 Appendix 1 R 1 5 Mar.21/11Printed in Great Britain



# RB.211−72−AG264 Transmittal - Page 21. Planning Information A. Effectivity BOEING 777 RB211 TRENT 800 Engines not incorporating SB72-G401
B. Reason (1) Problem Following inspection at shop visit, a crack was found on a Trent 800 Intermediate Pressure (IP) compressor shaft rear balance land. This was the first occurrence of an issue on this feature. In response to this finding, Non-Modification Service Bulletin (NMSB) 72-AF260 was raised to specify an at overhaul visual inspection. NMSB 72-AF313 was raised to specify one-off on-wing borescope inspection of the balance land on the Trent 800 engines. Recently, a crack has been found in a second Trent 800 IP compressor shaft in a similar location. This NMSB is being issued to specify repeat on-wing borescope inspections and supersedes NMSB 72-AF313. (2) Substantiation This NMSB instructs an on-wing visual borescope inspection of the IP compressor rear balance land, gaining access through the intermediate case vane 8. This inspection can also be performed at overhaul, if the rear of the IP compressor module is not accessible to perform NMSB 72-AG085. Revision 1 of this NMSB was issued to amend torque values in 3. Accomplishment Instructions and to remove the requirement to use the LP immobiliser at overhaul. References to in-shop were changed to at overhaul, annotation was added to Fig.5 and Fig.6 clip point references were corrected. Revision 2 of this NMSB was issued to amend units used for torque values that were incorrectly used in 3. Accomplishment Instructions and to remove AIPC Fig/Items. A note was also added in the overhaul and on-wing part of the accomplishment instructions. Also amended were Fig 2, Fig 5 and Fig 7 for graphic clarity. ENGINE - IP COMPRESSOR SHAFT - VISUAL BORESCOPE INSPECTION OF BALANCE LAND - NON-MODIFICATION SERVICE BULLETIN - NON - MOD.72-AG264Printed in Great Britain



# RB.211−72−AG264 Page 1 of 23 Jul 30/09 Mar.21/11 RRevision 3 of this NMSB was issued to confine the Effectivity (1.A.) to engines which did not incorporate Service Bulletin 72-G401, see 1.I., References. Reference was made to SB72-G401 in the revised note in the Accomplishment Instructions and the note regarding the inspection of the area around the balance weights was deleted and the content of the note was incorporated into the inspection instructions. Revision 4 of this NMSB was R issued to amend the illustration of a properly fitted balance weight (see Fig.7) and also note that this NMSB was R subject to an EASA Airworthiness Directive (AD). Revision 5 of this NMSB is issued to amend the illustration of a correctly fitted balance weight (see Fig.7) and also to change the part name from nut to bolt head in 3. Accomplishment Instructions. R R R (3) Effect of Bulletin on (a) Operation Not affected. (b) Maintenance Not affected. (c) Overhaul Not affected. (d) Repair Schemes Not affected. (e) Interchangeability Not affected. C. Description This NMSB instructs an on-wing visual borescope inspection of the IP compressor shaft rear balance land in order to maintain serviceability. Advise your Rolls-Royce service representative of NMSB accomplishment and inspection results, regardless of findings (refer to Appendix 1.). D. Compliance
ALERTPrinted in Great Britain



# RB.211−72−AG264 Page 2 Jul 30/09 Mar.21/11 RThis Non-Modification Service Bulletin must be accomplished within 475 flight cycles of the publication of this Service Bulletin, unless NMSB 72-AG085 is accomplished within this time period on this IP compressor shaft. This Non-Modification Service Bulletin must then be repeated on an ongoing basis within 475 flight cycles of the last previous accomplishment of NMSB 72-AG264 or NMSB 72-AG085 on the IP compressor shaft. This Non-Modification Service Bulletin is subject to EASA AD 2010-0266. E. Approval The technical content of this Non-Modification Service Bulletin was approved under the authority of Design Organisation Approval EASA.21J.035 on Jul.30/09, Sep.16/09, Dec.9/09, Dec.17/10, Feb.25/11 R and was re-approved on Mar.15/11. F. Manpower (1) In service (a) Time to gain access 1 hour (after normal engine cooling down and opening of C-ducts) (1 person). (b) Time to Inspect 1.5 hours (2 persons). (c) Time to restore to serviceable condition 0.5 hours (1 person). (2) At overhaul (a) Time to gain access 0.5 hours (1 person). (b) Time to Inspect 1.5 hours (2 persons). (c) Time to restore to serviceable condition 0.5 hours (1 person).Printed in Great Britain



# RB.211−72−AG264 Page 3 Jul 30/09 Mar.21/11 RG. Material Price and Availability
Item Description OMat 238 Lockwire OMat 2/142 Safety cable H. Tooling Price and Availability Rolls-Royce recommends the use of the tools specified below for the accomplishment of this NMSB. (1) Rolls-Royce recommends the use of: Probe No. 4 in accordance with Aircraft Maintenance Manual, 72-00-00, Intermediate Pressure (IP) Compressor Blades (Borescope) Inspection.

or 6 mm flexible borescope in accordance with Engine Manual, 72-00-00, Intrascope Inspection of the Intermediate Pressure (IP) Compressor Blades. Flexible borescope: Specification: - 6 mm nominal diameter - Forward viewing - Near focus, field of view 60 degrees - Low magnification Model used during Rolls-Royce inspection was model IPLEX 6 available from: Olympus Industrial KeyMed House Stock Road Southend-on-Sea Essex SS2 5QH United Kingdom Tel: +44 (0) 1702 616333Printed in Great Britain



# RB.211−72−AG264 Page 4 Jul 30/09 Mar.21/11 RFax: +44 (0) 1702 465677 (2) IP rotor turning tool HU40324. (3) LP system immobiliser HU40308. I. References (1) Rolls-Royce RB211 Service Bulletin: 72-G401 Engine - IP compressor shaft - Introduction of revised balancing weights and balancing method. (2) Rolls-Royce RB211 Non-Modification Service Bulletins: (a) 72-AF260 Engine - IP compressor shaft - Visual inspection of balance land (b) 72-AF313 Engine - IP compressor shaft - Visual borescope inspection of balance land (c) 72-AG085 Engine - IP compressor shaft - Eddy current inspection of balance land (3) In service (a) Aircraft Maintenance Manual, 72-00-00, 78-31-00, 27-81-00, 70-20-01, 70-51-00, 71-11-04, 72-03-11, Maintenance Practices (b) Aircraft Maintenance Manual, 72-00-00, Intermediate Pressure (IP) Compressor Blades (Borescope) Inspection (c) Aircraft Maintenance Manual, 70-01-02, The types of damage to metal parts (d) Aircraft Maintenance Manual, 70-12-04, Locking Techniques for threaded partsPrinted in Great Britain



# RB.211−72−AG264 Page 5 Jul 30/09 Mar.21/11 R(4) At overhaul (a) Engine Manual, 72-00-00, Intrascope Inspection of the Intermediate Pressure (IP) Compressor Blades (b) Standard Practices Manual, 70-01-02, Specified types of damage (c) Engine Illustrated Parts Catalogue, 72-33-10, Compressor Intermediate Case (d) Engine Illustrated Parts Catalogue, 75-22-49, Cooling and Sealing Air Tubes LP Core Engines (e) Engine Illustrated Parts Catalogue, 72-32-31, IP Compressor Shaft (f) Standard Practice Manual, 70-12-04, Procedure used to lock threaded parts.Printed in Great Britain



# RB.211−72−AG264 Page 6 Jul 30/09 Mar.21/11 R2. Material Information A. Parts referenced in this Service Bulletin: 75-22-49
FIG ITEM NO. NEW PART NO. QTY PART TITLE MAT OLD PART NO. INSTR DISP

13060 332W5910 -175 or FK28526 AR Bracket, ECS control - 332W5910 -175 or FK28526 -

13100 FK19864 AR Tube, assy IP8 air - intercase disconn (strut 8) to - FK19864 -

13106 AS48513 AR Bolt, 0.250 in. dia x 0.812 in. - AS48513 -

72-33-10
NOTE : The following parts are only replaced if found damaged when the bolts shown above are removed.
FIG ITEM NO. NEW PART NO. QTY PART TITLE MAT OLD PART NO. INSTR DISP
05315 AGS3732 AR Insert, screw thread 0.250 in. dia x 1.5 D - AGS3732 -Printed in Great Britain



# RB.211−72−AG264 Page 7 Jul 30/09 Mar.21/11 R3. Accomplishment Instructions A. At overhaul

NOTE : Some steps may not be required since certain parts may already have been disassembled or the applicable system is not available.
NOTE : All Fig/Item references quoted below are for the EIPC. (1) Prepare the engine for borescope inspection of the Intermediate Pressure (IP) compressor stage 8 balance land (EIPC Ref. 72-32-31, IP compressor shaft). (a) Attach the Rolls-Royce Trent IP rotor turning tool (HU40324) to turn the IP system in accordance with EM 72-00-00, Intrascope Inspection of the Intermediate Pressure (IP) Compressor Blades. (b) Gain access to the intermediate case, vane 8, by removing the air tube (EIPC Ref. 75-22-49, Fig/Item No. 13-100). Refer to Fig.6.
CAUTION : YOU MUST HOLD THE TUBE(S) WHEN YOU LOOSEN/TIGHTEN THE CONNECTIONS. MAKE SURE THAT THE TUBE(S) CANNOT TWIST. DAMAGE TO THE TUBE(S) CAN OCCUR IF THEY DO TWIST. (i) Remove and retain the two clipstacks CP40243 and CP40244. Refer to Fig.6, Fig.8 and Fig.9. (ii) Disconnect the rear end of the air tube (EIPC Ref. 75-22-49, Fig/Item No. 13-100) from the air tube (EIPC Ref. 75-22-49, Fig/Item No. 13-500). (iii) Disconnect the front end of the air tube (EIPC Ref. 75-22-49, Fig/Item No. 13-100) from the intermediate case by removing the 4 bolts (EIPC Ref. 75-22-49, Fig/Item No. 13-106).
NOTE : If the inserts are damaged when the bolts are removed, replace them as required (see 2. Material Information). (iv) Retain the air tube (EIPC Ref. 75-22-49, Fig/Item No. 13-100), the bracket (EIPC Ref. 75-22-49, Fig/Item No. 13-060) and the 4 bolts (EIPC Ref. 75-22-49, Fig/Item No. 13-106). (2) Perform the borescope inspection of the Intermediate Pressure (IP) compressor stage 8 balance land. (a) Insert the borescope into the intermediate case, vane 8. The vane will guide the borescope to the rear of the IP compressor drum. Articulate the borescope to view the balance land at the rear of the IP compressor stage 8 from two directions. Refer to Fig.1. The view from the borescope should be similar to that shown in Fig.2 and Fig.3.Printed in Great Britain



# RB.211−72−AG264 Page 8 Jul 30/09 Mar.21/11 RCAUTION : YOU MUST MAKE SURE THAT THE BORESCOPE IS NOT IN THE PATH OF ANY ROTATING COMPONENTS WHEN YOU TURN THE ENGINE. IF THE BORESCOPE AND ROTATING COMPONENT TOUCH, DAMAGE TO EITHER THE ROTATING COMPONENT OR BORESCOPE WILL OCCUR. (b) Inspect zone A of the balance land, as shown in Fig.4, over the entire circumference (the criteria for this inspection is in Accomplishment Instructions (3.A.(3)). Look for the following: (i) Cracks (for example of previous crack position, refer to Fig.5) (ii) Dents or nicks (iii) Balance weights and surrounding area (1) Check for gaps between balance weight, clamp, washer or bolt head, R R which indicate that the balance weight is loose. Fig.7 illustrates a properly fitted balance weight. (2) Carefully inspect the area around the balance weights. Carefully inspect all around the edge of the clamp plate to make sure there is no cracking that has started underneath the clamp plate.
NOTE : In some instances no balance weights will be fitted to the balance land (because they were not needed to balance the IP Compressor Shaft at the previous shop visit or because SB72-G401 has been accomplished). If SB72-G401 has been accomplished it is not necessary to complete the inspection (see 1.A., Effectivity), otherwise complete the inspection of zone A of the balance land over the entire circumference. (c) Withdraw the borescope from the intermediate case, vane 8. (d) Install the air tube (EIPC Ref. 75-22-49, Fig/Item No. 13-100).
CAUTION : YOU MUST HOLD THE TUBE(S) WHEN YOU LOOSEN/TIGHTEN THE CONNECTIONS. MAKE SURE THAT THE TUBE(S) CANNOT TWIST. DAMAGE TO THE TUBE(S) CAN OCCUR IF THEY DO TWIST. (i) Attach the air tube (EIPC Ref. 75-22-49, Fig/Item No. 13-100) together with the bracket (EIPC Ref. 75-22-49, Fig/Item No. 13-060) to the intermediate case with 4 bolts (EIPC Ref. 75-22-49, Fig/Item No. 13-106). Torque tighten the bolts to 11,5 Nm (100 lbfin.).
NOTE : Make sure the bracket (EIPC Ref. 75-22-49, Fig/Item No. 13-060) is fitted in the correct orientation in accordance with Fig.6.Printed in Great Britain



# RB.211−72−AG264 Page 9 Jul 30/09 Mar.21/11 R(ii) Attach the adaptor (EIPC Ref. 75-22-49, Fig/Item No. 13-242) to the tube coupling nut (EIPC Ref. 75-22-49, Fig/Item No. 13-601) and torque to 99 Nm (876 lbfin.). Safety with OMat 2/142 Safety cable or OMat 238 lockwire in accordance with SPM 70-12-04, Procedure to lock threaded parts. (iii) Install the two clipstacks CP40243 and CP40244 and torque tighten the nuts (AS20624) 2 off to 6,2 Nm (55 lbfin.). Refer to Fig.6, Fig.8 and Fig.9. (e) Make sure all tools and equipment are removed from the work area. (f) Remove the Rolls-Royce Trent IP rotor turning tool (HU40324) in accordance with EM 72-00-00, Intrascope Inspection of the Intermediate Pressure (IP) Compressor Blades. (3) Acceptance criteria.
PROCEDURE (a) Cracked RELATED DATA Reject. Inform Rolls-Royce as soon as practically possible. (b) Dented or nicked Reject (c) Loose balance weights RejectPrinted in Great Britain



# RB.211−72−AG264 Page 10 Jul 30/09 Mar.21/11 RB. On wing

WARNING : DO NOT TOUCH HOT PARTS WITHOUT APPLICABLE GLOVES. HOT PARTS CAN CAUSE INJURY. WARNING : DO NOT TOUCH THE COMPONENTS OF THE OIL SYSTEM IF THE ENGINE IS HOT THESE COMPONENTS STAY HOTTER THAN OTHER COMPONENTS. HOT COMPONENTS CAN BURN.
CAUTION : IN ORDER TO REDUCE THE POTENTIAL FOR MULTIPLE-ENGINE IN-FLIGHT SHUTDOWN, POWER LOSS OR OTHER ANOMALY DUE TO MAINTENANCE ERROR, ROLLS-ROYCE RECOMMENDS THAT OPERATORS AVOID PERFORMING MAINTENANCE ON MULTIPLE ENGINES INSTALLED ON THE SAME AIRCRAFT AT THE SAME TIME. IF IT IS NOT POSSIBLE TO AVOID MAINTENANCE ON MORE THAN ONE ENGINE AT THE SAME TIME, ROLLS-ROYCE RECOMMENDS THAT ADDITIONAL CONTROLS ARE APPLIED IN ORDER TO MAKE SURE THAT MAINTENANCE TASKS HAVE BEEN COMPLETED AS DEFINED. MAINTENANCE GUIDELINES SHOULD BE REVISED, WHERE POSSIBLE, TO PROMOTE THIS RECOMMENDATION.
CAUTION : DO NOT START A BORESCOPE INSPECTION FOR 2-3 HOURS AFTER ENGINE HAS STOPPED. THE ENGINE IS HOT IMMEDIATELY AFTER THE ENGINE IS STOPPED AND CAN CAUSE BURNS AND DAMAGE TO BORESCOPE INSPECTION EQUIPMENT. (1) Prepare the engine for borescope inspection of the Intermediate Pressure (IP) compressor stage 8 balance land. (a) Open the applicable circuit breakers and install safety tags in accordance with Aircraft Maintenance Manual (AMM) 72-00-00, Intermediate Pressure (IP) Compressor Blades (Borescope) Inspection. (b) Safely open the left and right thrust reversers in accordance with AMM 72-00-00, Intermediate Pressure (IP) Compressor Blades (Borescope) Inspection. (c) Use the LP system immobiliser (HU40308) to prevent movement of the LP compressor in accordance with AMM 72-00-00, Turn the Intermediate Pressure (IP) System. (d) Attach the Rolls-Royce Trent IP rotor turning tool (HU40324) to turn the IP system in accordance with AMM 72-00-00, Turn the Intermediate Pressure (IP) System. (e) Gain access to the intermediate case, vane 8, by removing the air tube (FK19864). Refer to Fig.6.
CAUTION : YOU MUST HOLD THE TUBE(S) WHEN YOU LOOSEN/TIGHTEN THE CONNECTIONS. MAKE SURE THAT THE TUBE(S) CANNOT TWIST. DAMAGE TO THE TUBE(S) CAN OCCUR IF THEY DO TWIST. (i) Remove and retain the two clipstacks CP40243 and CP40244. Refer to Fig.6, Fig.8 and Fig.9.Printed in Great Britain



# RB.211−72−AG264 Page 11 Jul 30/09 Mar.21/11 R(ii) Disconnect the rear end of the air tube (FK19864) from the air tube (FK19865). (iii) Disconnect the front end of the air tube (FK19864) from the intermediate case by removing the 4 bolts (AS48513).
NOTE : If the inserts are damaged when the bolts are removed, replace them as required (see 2. Material Information). (iv) Retain the air tube (FK19864), the bracket (FK28526) and the 4 bolts (AS48513). (2) Perform the borescope inspection of the Intermediate Pressure (IP) compressor stage 8 balance land. (a) Insert the borescope into the intermediate case, vane 8. The vane will guide the borescope to the rear of the IP compressor drum. Articulate the borescope to view the balance land at the rear of the IP compressor stage 8 from two directions. Refer to Fig.1. The view from the borescope should be similar to that shown in Fig.2 and Fig.3.
CAUTION : YOU MUST MAKE SURE THAT THE BORESCOPE IS NOT IN THE PATH OF ANY ROTATING COMPONENTS WHEN YOU TURN THE ENGINE. IF THE BORESCOPE AND ROTATING COMPONENT TOUCH, DAMAGE TO EITHER THE ROTATING COMPONENT OR BORESCOPE WILL OCCUR. (b) Inspect zone A of the balance land, as shown in Fig.4, over the entire circumference (the criteria for this inspection is in Accomplishment Instructions (3.B.(4)). Look for the following: (i) Cracks (for example of previous crack position, refer to Fig.5). (ii) Dents or nicks. (iii) Balance weights and surrounding area (1) Check for gaps between balance weight, clamp, washer or bolt head, R R which indicate that the balance weight is loose. Fig.7 illustrates a properly fitted balance weight.Printed in Great Britain



# RB.211−72−AG264 Page 12 Jul 30/09 Mar.21/11 R(2) Carefully inspect the area around the balance weights. Carefully inspect all around the edge of the clamp plate to make sure there is no cracking that has started underneath the clamp plate.
NOTE : In some instances no balance weights will be fitted to the balance land (because they were not needed to balance the IP Compressor Shaft at the previous shop visit or because SB72-G401 has been accomplished). If SB72-G401 has been accomplished it is not necessary to complete the inspection (see 1.A., Effectivity), otherwise complete the inspection of zone A of the balance land over the entire circumference. (c) Withdraw the borescope from the intermediate case, vane 8. (3) Put the aircraft back to serviceable condition. (a) Install the air tube (FK19864). Refer to Fig.6.
CAUTION : YOU MUST HOLD THE TUBE(S) WHEN YOU LOOSEN/TIGHTEN THE CONNECTIONS. MAKE SURE THAT THE TUBE(S) CANNOT TWIST. DAMAGE TO THE TUBE(S) CAN OCCUR IF THEY DO TWIST. (i) Attach the air tube (FK19864) together with the bracket (FK28526) to the intermediate case with 4 bolts (AS48513). Torque tighten the bolts to 11,5 Nm (100 lbfin.).
NOTE : Make sure the bracket (FK28526) is fitted in the correct orientation in accordance with Fig.6. (ii) Attach the adaptor (AS15820) to the tube coupling nut (AS15710) and torque to 99 Nm (876 lbfin.). Safety with OMat 2/142 Safety cable or OMat 238 lockwire in accordance with AMM 70-12-04, Locking Techniques for threaded parts. (iii) Install the two clipstacks CP40243 and CP40244 and torque tighten the nuts (AS20624) 2 off to 6,2 Nm (55 lbfin.). Refer to Fig.6, Fig.8 and Fig.9. (b) Make sure all tools and equipment are removed from the work area. (c) Remove the Rolls-Royce Trent IP rotor turning tool (HU40324) and LP system immobiliser (HU40308) in accordance with AMM 72-00-00, Turn the Intermediate Pressure (IP) System. (d) Put the aircraft back to a serviceable condition in accordance with AMM 72-00-00, Intermediate Pressure (IP) Compressor Blades (Borescope) Inspection.Printed in Great Britain



# RB.211−72−AG264 Page 13 Jul 30/09 Mar.21/11 R(4) Acceptance criteria.
PROCEDURE (a) Cracked RELATED DATA Reject. Inform Rolls-Royce as soon as practically possible. (b) Dented or nicked Reject within 20 cycles. Supply pictures of dent or nick to Rolls-Royce Technical Helpdesk. (c) Loose balance weights Reject within 20 cycles. Supply pictures of balance weights to Rolls-Royce Technical Helpdesk. (5) Record Engine Serial Number, Engine Hours Since New, Engine Cycles Since New, IP Compressor Shaft Part Number, IP Compressor Shaft Serial Number, IP Compressor Shaft Cycles Since New, IP Compressor Shaft Hours Since New and the results of the inspection from Accomplishment Instructions 3.B.(2)(b)). C. Accomplishment of this Non-Modification Service Bulletin should be recorded in the engine logbook or in accordance with the local SB tracking system procedures.Printed in Great Britain



# RB.211−72−AG264 Page 14 Jul 30/09 Mar.21/11 RIllustration of Borescope Articulation Fig.1Printed in Great Britain



# RB.211−72−AG264 Page 15 Jul 30/09 Mar.21/11 RView from Direction 1 Fig.2Printed in Great Britain



# RB.211−72−AG264 Page 16 Jul 30/09 Mar.21/11 RView from Direction 2 Fig.3Printed in Great Britain



# RB.211−72−AG264 Page 17 Jul 30/09 Mar.21/11 RIdentification of Zones to be Inspected Fig.4Printed in Great Britain



# RB.211−72−AG264 Page 18 Jul 30/09 Mar.21/11 RPosition of Crack in First Trent 800 Finding Fig.5Printed in Great Britain



# RB.211−72−AG264 Page 19 Jul 30/09 Mar.21/11 RPosition of Bracket (EIPC 75-22-49, Fig/Item No. 13-060) Fig.6Printed in Great Britain



# RB.211−72−AG264 Page 20 Jul 30/09 Mar.21/11 RR

Correctly Fitted Balance Weight R Fig.7 RPrinted in Great Britain



# RB.211−72−AG264 Page 21 Jul 30/09 Mar.21/11 RClipstack CP40243 Fig.8Printed in Great Britain



# RB.211−72−AG264 Page 22 Jul 30/09 Mar.21/11 RClipstack CP40244 Fig.9Printed in Great Britain



# RB.211−72−AG264 Page 23 Jul 30/09 Mar.21/11 RNon-Modification Service Bulletin 72-G264
1. Record accomplishment of this Non-Modification Service Bulletin in accordance with local Service Bulletin tracking system procedures. 2. Advise your local Rolls-Royce service representative of NMSB accomplishment and inspection results regardless of findings. APPENDIX 1Printed in Great Britain



# RB.211−72−AG264 Appendix 1 - Page 1 of 1 Jul 30/09 Mar.21/11 R