# Gulfstream TRANSMITTAL SHEET

Transmittal Page 1 of 2 This sheet transmits Revision 1, dated October 27, 2011, to Gulfstream Service Bulletin (SB) 200-32-389 dated Oc tober 20, 2011, titled Landi ng Gear - Brake Assembly - Brake Wear Indicator Pin - Detailed Inspection / Modification Reason for Revision PLANNING INFORMATION 1. Effectivity Information is updat ed adding aircraft serial numbers 241-250. NOTE is updated advising that all brakes are affected. 3. Reason Information updated explaining brake assemb lies not called out in original issue were found with improperly sized wear indicator pins. 4. Description Information updated deleting reference to an affected seri al number range. 5. Compliance NOTE is added recommending operators with brakes in excess of 1,500 landings to consider SB revision compliance. 7. Manpower Information updated deleting man-hours to inspect for suspect serial numbers. ACCOMPLISHMENT INSTRUCTIONS Steps 3-5 Information updated deleting reference to Appendix A. Added note to Figure 3

October 27, 2011

# Gulfstream TRANSMITTAL SHEET

Transmittal Page 2 Effect of Revision on Prior Accomplishments This service bulletin revision replaces SB 200-32-389. Airc raft in compliance with the original issue of this servic e bulletin must accomplish this SB revision by inspecting and modifying, if necessary, all brake assemblies . Aircraft that have inspected and modified all brake assemblies per the in structions of the original issue of this SB require no further action. Operators s hould return the service repl y card marked “Previously complied with” , stating all brake assemb lies have been inspected. This is a COMPLETE REISSUE of Gulfstream Service Bulletin 200-32-389. List of Effective Pages

Previous revisions to service bulletin 200-32-389 None

Page No. Date 1 through 8 Oct ober 27, 2011

October 27, 2011

## SUBJECT 

# SERVICE BULLETIN
NUMBER 200-32-389 Rev 1

LANDING GEAR (ATA 32) - BRAKE ASSEMBLY

- BRAKE WEAR INDICATOR PIN - DETAILED INSPECTION / MODIFICATION

OCTOBER 27, 2011

# Gulfstream

....................... ..................... . SERVICE BULLETIN

Service Bulletin No. 200-32-389 Page 1 of 8 LANDING GEAR - BRAKE ASSEMBLY - BRAKE WEAR INDICATOR PIN - DETAILED INSPECTION / MODIFICATION PLANNING INFORMATION 202 1. Effectivity Aircraft serial numbers 004-250 NOTE: All brake assemblies installed on ai rcraft serial numb ers 004-250 and any spare units must be inspected. 2. Concurrent Requirement None 3. Reason Recently, two G200 operators exper ienced degraded brake performance after landing. Subsequent investigat ion revealed that in both cases t he brake wear pins showed remaining life, but th e brakes were worn to t he minimum pad thickness as specified in the brake Meggitt Aircraft Braking Systems Co mponent Maintenance Manual (CMM). This deficiency has been tr aced to wear indicator pins that were improperly sized during t he brake overhaul process. After release of the original issue of this SB, brake a ssemblies not called out in Appendix A were also found to have improperly sized brake wear indicator pins. 4. Description This service bulletin revision provides instructions to inspect all main landing gear (MLG) brake assemblies, P/N 4AS255 0003-501/-503/-505 (5012889/-1/-2), in the above aircraft effectivity for properly sized brake wear indicator pi ns. Instructions are also provided to measure and cut (if necessary ) the pin to the manufacturer’s specified length as instructed in this service bulletin. 5. Compliance Compliance with this service bulletin is mandatory at the nex t suitable planned maintenance period not to exceed De cember 19, 2011. NOTE: Operators with brakes having in exce ss of 1,500 landings should consider compliance with this SB revision at the earliest convenient opportunity.

October 20, 2011 Revision 1 October 27, 2011

# Gulfstream SERVICE BULLETIN

Service Bulletin No. 200-32-389 Page 2 of 8 6. Approval This service bulletin contains no modification information that revises the approved configuration and theref ore does not require regul atory agency approval. 7. Manpower The following information is for planning purposes only: Estimated man-hours: 4 hours to jack aircraft 2 hours to remove and in stall each MLG wheel 1 hour to measure and cut wear i ndicator pin (per brake assy) 8. Weight and Balance None 9. Electrical Load Data No Change 10. Software Accomplishment Summary None 11. References G200 Aircraft Maintena nce Manual (AMM), Chapt ers 07, 12, 20 and 32 Meggitt Aircraft Braking Systems Br ake Component Mainte nance Manual (CMM) 12. Other Publications Affected AMM, Chapter 32 13. Interchangeability or In termixability of Parts None

October 20, 2011 Revision 1 October 27, 2011

# Gulfstream

....................... ..................... . SERVICE BULLETIN

Service Bulletin No. 200-32-389 Page 3 of 8 MATERIAL INFORMATION 1. Material - Price and Availability The parts required to accomp lish this service bulletin are available by contacting Spare Parts Sales at 800-810 -GULF (4853) or 912-965-4178. 2. Warranty Information This service bulletin will be accomplished at no charge if perform ed at a Gulfstream G200 Authorized Warranty Repair Facility within the recommended compliance time stated in this document. If this service bulletin is perform ed at other than a Gulfstream G200 Authorized Warranty Repair Facility, the labor will be an owner responsibility. 3. Material Necessary for Each Aircraft A. Material to be Procured:

B. Materials Supplied by the Operator: None 4. Reidentified Parts None 5. Special Tooling Torque wrench, 40-2 00 in.lbs. GSE5100721 (Q C1R200) or equivalent Torque wrench, 100- 1000 in.lbs. GSE5100722 (See GS E Catalog) or equivalent New P/N Keyword Old P/N Qty MS24665-90 Cotter Pin A/R

October 20, 2011 Revision 1 October 27, 2011

# Gulfstream SERVICE BULLETIN

Service Bulletin No. 200-32-389 Page 4 of 8 ACCOMPLISHMENT INSTRUCTIONS CAUTION: PROTECT WIRE BUNDLE S, CONNECTORS AND SURROUNDING STRUCTURE DURING ANY MAIN TENANCE PROCEDURES FROM SHAVINGS, DEBRIS AND CONTAMIN ATION. MAINTAIN A PROPERLY CLEANED WORK AREA THROUGHOUT THE PROCEDURE TO ENSURE THE INTEGRITY OF THE AFFECTED COMPONENT/SYSTEM. VISUALLY INSPECT WORK AREA US ING ADDITIONAL LIGH T AS NECESSARY TO VERIFY ABSENCE OF ANY DEBRIS PRIOR TO COMPLETION OF PROCEDURE. FAILURE TO COMPLY MAY RESULT IN DAMAGE TO COMPONENTS AND/OR SYSTEMS. 1. Prepare aircraft for safe maintenance. Refer to Aircraft Maintenance Manual, Chapter 20. CAUTION: MAKE SURE ELECTRICAL POWER IS DISCONNECTED FROM AIRCRAFT. FAILURE TO COMPLY MAY RESULT IN INJURY TO PERSONNEL AND/OR DAMAGE TO AIRCRAFT. 2. Disconnect external electrical power from aircraft. Refe r to Aircraft Maintenance Manual, Chapter 12. 3. Jack aircraft. Refer to AMM, Chapter 07. 4. Remove MLG wheels as necessa ry. Refer to AM M, Chapter 32. 5. Remove brake wear indicato r pin by removing co tter pin from the cap screw. Refer to Figure 2. 6. Measure and cut indica tor pin to 1.41 inches (35.8 mm) ± 0.020 (± .5 mm). Refer to Figure 3. NOTE: If pin is within limits show n, no cutting is required. 7. Break sharp edges. 8. Reinstall wear indicator pi n and secure with new cotter pin, P/ M MS24665-90. Refer to Figure 2. 9. Perform Steps 4 thr ough 8 for each remain ing brake assembly. 10. Perform Normal Brake Wear In spection per AMM, Chapter 32. 11. Replace any brakes that fail brake wear inspection. Refer to AMM, Chapter 32. 12. Reinstall all removed wheel asse mblies. Refer to AMM, Chapter 32. October 20, 2011 Revision 1 October 27, 2011

# Gulfstream SERVICE BULLETIN

Service Bulletin No. 200-32-389 Page 5 of 8 13. Remove aircraft from jacks . Refer to AMM, Chapter 07. 14. Ensure work area is clean a nd clear of foreign objects (FOD). 15. Record compliance with this service bulletin revision in the aircraft’s permanent maintenance records and return aircraft to flight status. 16. Report compliance with this service bulletin revision to Gulfstream CMP via electronic transmittal or fill out and fax the attached service reply card. If technical assistan ce is required, contact your area Gulfstream Field Service Representative or call Gulf stream Customer Support at 800-810-GULF (4853) or 912-965-4178 (fax 912-965-4184).

October 20, 2011 Revision 1 October 27, 2011

# Gulfstream SERVICE BULLETIN

Service Bulletin No. 200-32-389 Page 6 of 8 HEAT SHIELD

Brake Wear Indicato r Pin Installation Figure 1 October 20, 2011 Revision 1 October 27, 2011 WEAR INDICATOR PIN PRESSURE PLATE

# Gulfstream SERVICE BULLETIN

Service Bulletin No. 200-32-389 Page 7 of 8 Break Wear Indicator Pin Removal And Installation Figure 2 October 20, 2011 Revision 1 October 27, 2011

# Gulfstream SERVICE BULLETIN

Service Bulletin No. 200-32-389 Page 8 of 8 CUT PIN TO 1.41 INCHES (35.8 MM ) ± 0.020 (.5 MM) WEAR INDICATOR PIN, P/N 5010453-1

Brake Wear Indicator Pin Length - Adjustment Figure 3 October 20, 2011 Revision 1 October 27, 2011 NOTE: THE DIMENSION IS TAKEN FROM THE FRONT OF THE SECURING HO LE IN THE WEAR INDICATOR PIN

NOTE: ALL BRAKE ASSEMBLIES MUST BE INSPECTED. NO AIRCRAFT (004-250) OR BRAKE ASSEMBL IES ARE EXEMP T FROM THE REQUIREMENTS CALLED OUT IN THIS SB EFFECTIVITY

## GULFSTREAM G200 SERVICE BULLETIN NO. 200-32-389 REV 1 SERVICE REPLY CARD

Service Bulletin prepared by Gulfstream Aerospace, 500 Gulfstream Road, P.O. Bo x 2206, Savannah, Georgia 31402-2206, USA. © 2011 Gulfstream Aerospac e. All rights reserved, including the ri ght to reproduce this publication. No part may be reproduced, stored in any retrieval syst em, or transmitted in any part or form or by any means, electronic, photocopying, microfilm, mi crofiche, mechanical, or otherwise, without prior written permission of Gulfstream Aerospace. This technical data is controll ed under the Export Administration Regulations by General License TSU. It may not be transferred to a third party with out the prior written approval of the U.S. Department of Commerce. PLEASE FAX THIS PAGE TO GULFSTREAM AEROSPACE CMP FAX # 800-944-1775 or 912-963-0265. THE FOLLOWING SERVICE BULLETI N HAS BEEN COMPLIED WITH: SB CMP NUMBER A/C AIRCRAFT TYPE COMPLIANCE DATE 983891 Galaxy/Gulfstream G200

AIRCRAFT HOURS: AIRCRAFT LANDINGS: PREVIOUSLY COMPLIED WITH: DATE: NOT APPLICABLE: DATE:

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