# Bombardier Service Bulletin 601R-57-048 Copy: Revision C ("SB 601R-57-048 Rev C"), 78 pages: PDF https://openairdocs.org/files/sha256/86/5d/865db26f0f9abc20e22154d9c9ef7dcbcfc388604fb50fd2458ff72f797e4814; text https://openairdocs.org/service-documents/bombardier/601r-57-048/file/865db26f0f9a.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2018-0801; AD 2019-08-11 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. ## Details - Manufacturer: [Bombardier](https://openairdocs.org/service-documents/bombardier.md) - Type: Service bulletin (Service Bulletin) - Number: 601R-57-048 - Latest revision known: 601R-57-048, Revision C, dated June 6, 2013 (OpenAirDocs) - Page: https://openairdocs.org/service-documents/bombardier/601r-57-048 ## ADs that cite it (1) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2019-08-11](https://openairdocs.org/ad/2019-08-11.md), effective Jul 11, 2019: Revisions A, B and C Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/601r-57-048/proposed.md). ## Text (78 pages) Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2018-0801; AD 2019-08-11 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 SB 601R- - - 57- - - 048 Page 1 of 1 Jun 06/2013 SERVICE BULLETIN REVISION TRANSMITTAL SHEET CL- - -600- - -2B19Canadair Regional Jet (CRJ) Aircraft SERVICE BULLETIN 601R - - -57 - - -048 SUBJECT : Wings - - - Center Wing Primary Structure - - - Cold Work of Holes on the web of the Main Landing Gear (MLG) Trunnion This page transmits: Revision C of Service Bulletin 601R- - - 57- - - 048, pages 1 thru 67, dated Jun 06/2013 and Initial issue of Appendix A, pages A1 thru A9, dated Aug 24/2012. The changes in this revision have no effect on aircraft that have had this service bulletin incorporated. Reason: Revised Planning Information, paragraph 1., to: Add revision A to kit 601R57- - - 048K90. Revised Accomplishment Instructions, paragraph 2., to: Add revision A to kit 601R57- - - 048K90. Revised Material Information, paragraph 3., to: Add revision A to kit 601R57- - - 048K90. This revision also includes small editorial changes that do not have an effect on the technical content. Instructions: Discard the copy of Service Bulletin 601R- - - 57- - - 048, Revision B, dated Aug 24/ 2012. Replace with the copy attached. Service Bulletin History: Initial issue, dated Jul 17/2009. Revision A, dated Nov 24/2009. Revision B, dated Aug 24/2012. 1 ### Page 2 SB 601R−57−048 Page 1 of 67 Jul 17/2009 Revision C, Jun 06/2013 SERVICE BULLETIN Technical Publications THIS SERVICE BULLETIN IS SENT TO EACH OPERATOR. IF THE OPERATOR HAS LEASED HAS SOLD AIRCRAFT OR TRANSFERRED SPARES IN THE LAST SIX MONTHS, THIS SERVICE BULLETIN MUST BE SENT TO THE NEW OWNER, UNLESS CONFIRMATION WAS RECEIVED THAT BOMBARDIER REGIONAL AIRCRAFT DIVISION HAS INCLUDED THE NEW OPERATOR AIRCRAFT , THIS SERVICE BULLETIN MUST BE SENT TO THE LESSEE. IF THE OPERATOR ON THE DISTRIBUTION LIST . ATA SYSTEM: 57−11 NUMBER: 601R−57−048 SUBJECT: Wings − Center Wing Primary Structure − Cold Work of Holes on the web of the Main Landing Gear (MLG) Trunnion 1. PLANNING INFORMATION A. Effectivity (1) Aircraft Affected: Service Bulletin: CL−600−2B19 Canadair Regional Jet (CRJ) Aircraft Serial Numbers 7003 thru 7067, 7069 thru 7990, and 8000 thru 8106. Production: This change will be incorporated before delivery on Aircraft Serial Numbers 8107 and subsequent. NOTE: The instructions in this service bulletin are only applicable to the systems and parts installed at the time of delivery of the aircraft or as changed by Bombardier Service Bulletins. Before you do this bulletin, examine all Supplemental Type Certificates (STCs), Supplemental Type Approvals (STAs) or equivalent action changes to make sure you can complete this service bulletin. NOTE: The procedure in this service bulletin was validated on Aircraft Serial Number 7731. ### Page 3 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 2 of 67 Jul 17/2009 Revision C, Jun 06/2013 B. Reason (1) Condition It is possible that cracks can occur in the fastener and tooling holes on the web of the Main Landing Gear (MLG) trunnion. (2) Evidence Engineering analysis, supported by component fatigue test has found that cracks can occur in the holes on the web of the MLG trunnion. (3) Objective/Benefit This service bulletin gives the procedure to cold work the holes on the web of the MLG trunnion. This will prevent cracks in the MLG trunnion and stop the repetitive inspection in the Maintenance Requirement Manual (MRM). C. Description This service bulletin is divided in three parts: PART A, PART B and PART C. PART A − Cold Work the Web of the Left MLG Trunnion The electrical extension of the flaps is done. The electrical power is removed from the aircraft. The pressure of hydraulic system No. 2 and No. 3 is released. Circuit breakers are opened. The aircraft is put on jacks. The MLG is removed. Cold work is done to the holes on the web of the MLG trunnion. Identification of the MLG trunnion is done. The MLG is installed. The flaps are retracted. The circuit breakers are closed. The hydraulic system No. 2 and No. 3, and the breaks are bled. The functional test of the landing gear extension/retraction system is done. The operational test of the landing gear manual-release-system is done. The operational test of the brake system is done. The aircraft is removed from the jacks. PART B − Cold Work the Web of the Right MLG Trunnion The electrical extension of the flaps is done. The electrical power is removed from the aircraft. The pressure of hydraulic system No. 2 and No. 3 is released. Circuit breakers are opened. The aircraft is put on jacks. The MLG is removed. Cold work is done to the holes on web of the MLG trunnion. Identification of the MLG trunnion is done. The MLG is installed. The flaps are retracted. The circuit breakers are closed. The hydraulic system No. 2 and No. 3, and the breaks are bled. The functional test of the landing gear extension/retraction system is done. The operational test of the landing gear manual-release-system is done. The operational test of the brake system is done. The aircraft is removed from the jacks. ### Page 4 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 3 of 67 Jul 17/2009 Revision C, Jun 06/2013 For Aircraft that have incorporated issue NC or revision A of this service bulletin PART C − Identification of the Left and Right MLG Trunnion Lockpins are installed in the nose landing gear (NLG) and MLG. The left and right MLG trunnions are identified. For all Aircraft D. Compliance Recommended Service Bulletin. Bombardier Aerospace recommends that PART A and PART B of this service bulletin be done before the aircraft has 34900 flight cycles, unless otherwise directed by the airworthiness authority of the operator. For Aircraft that have incorporated issue NC or revision A of this service bulletin Recommended Service Bulletin. Bombardier Aerospace recommends that PART C of this service bulletin be done before the aircraft has 38900 flight cycles, unless otherwise directed by the airworthiness authority of the operator. NOTE: If the identification of the MLG trunnion was done with Service Bulletin 601R−57−046 or 601R−57−047, it is not necessary to do PART C of this service bulletin. For all Aircraft This service bulletin affects Airworthiness Limitations (AWLs) and/or Damage Tolerance Inspections (DTIs). Reference applicable Post/Pre Modsum TC601R17554 and/or Service Bulletin 601R−57−048 in the Maintenance Requirements Manual (MRM). E. Approval The technical content of this service bulletin has been approved under the authority of the TCCA Design Approval Organization No: DAO #93−Q−02. F . Manpower These estimates do not include the time necessary for: − Administrative functions such as planning, liaison, familiarization, and report writing. − Non productive elapsed time such as rest time, having meals, and crew shift changes. ### Page 5 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 4 of 67 Jul 17/2009 Revision C, Jun 06/2013 − Elapsed time such as for paint to dry, sealant to cure, and fuel tank venting. − Preparation for modification (unless specified in the accomplishment instructions) such as cleaning and getting parts, tools, consumables, and ground equipment. − Quality assurance inspections, troubleshooting and/or correction of discrepancies found when a task is done. − All other activities that are not considered by Bombardier Aerospace as directly related to the accomplishment of this procedure. NOTE: For any on-site labor assistance, please speak with a Fleet Services representative for a quote. The Fleet Services Team can be contacted through the CRC at 514−855−8500 or email at thd.crj@aero.bombardier.com. PART A − Cold Work the Web of the Left MLG Trunnion It will take an estimated 26.0 man−hours to complete PART A of this service bulletin. The man−hours are divided as shown in the table that follows: TASK MAN−HOURS (1) Job Set−Up 10.0 (2) Procedure 7.0 (3) Test 5.0 (4) Job Close−Out 4.0 PART B − Cold Work the Web of the Right MLG Trunnion It will take an estimated 26.0 man−hours to complete PART B of this service bulletin. The man−hours are divided as shown in the table that follows: TASK MAN−HOURS (1) Job Set−Up 10.0 (2) Procedure 7.0 (3) Test 5.0 (4) Job Close−Out 4.0 ### Page 6 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 5 of 67 Jul 17/2009 Revision C, Jun 06/2013 PART C − Identification of the Left and Right MLG Trunnion It will take an estimated 0.25 man-hours to complete PART C of this service bulletin. The man-hours are divided as shown in the table that follows: TASK MAN-HOURS (1) Job Set−Up 0.0 (2) Procedure 0.25 (3) Test 0.0 (4) Job Close−Out 0.0 G. Material − Price and Availability (1) The kits in the tables that follow are available from Bombardier Commercial Aircraft. Refer to the paragraphs below for terms and conditions. NOTE: For a list of the kit contents, refer to paragraph 3.A. For Aircraft 7003 thru 7067, 7069 thru 7990 and 8000 thru 8017 KIT NUMBER NAME 601R57−048K2 MLG trunnion cold work oversize NOTE: The kit 601R57−048K2 contains alternate oversize hardware(s) for the incorporation of PART A and PART B. For Aircraft 7003 thru 7067, 7069 thru 7990 and 8000 thru 8017, that do PART A KIT NUMBER NAME 601R57−048K1 Left side MLG trunnion cold work ### Page 7 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 6 of 67 Jul 17/2009 Revision C, Jun 06/2013 For Aircraft 7003 thru 7067, 7069 thru 7990 and 8000 thru 8017, that do PART B KIT NUMBER NAME 601R57−048K5 Right side MLG trunnion cold work For Aircraft 8018 thru 8106 KIT NUMBER NAME 601R57−048K4 MLG trunnion cold work oversize NOTE: The kit 601R57−048K4 contains alternate oversize hardware(s) for the incorporation of PART A and PART B. For Aircraft 8018 thru 8106, that do PART A KIT NUMBER NAME 601R57−048K3 Left side MLG trunnion cold work For Aircraft 8018 thru 8106, that do PART B KIT NUMBER NAME 601R57−048K6 Right side MLG trunnion cold work For all Aircraft (2) Please send a purchase order to the address below to schedule the kits: Bombardier Service Bulletin Kit Support Team 123 Garratt Blvd, N42−24 Toronto, Ontario Canada M3K 1Y5 ### Page 8 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 7 of 67 Jul 17/2009 Revision C, Jun 06/2013 Fax: 416−375−3060 Phone: 416−375−3920 Email: sbkits@aero.bombardier.com Please contact the Service Bulletin kit Support Team at the address above for terms and conditions. (3) Refer to paragraph 3.B. for a list of consumables for this service bulletin. H. Tooling − Price and Availability (1) The tool kits in the tables that follow are available from Bombardier. Refer to the paragraphs below for the terms and conditions. NOTE: For a list of the kit contents, refer to paragraph 3.A. KIT NUMBER NAME 601R57−048K90A Drills and Reamers kit − MLG Trunnion 601R57−048K91B Cold work kit −MLG Trunnion 601R57−048K92 Cold work kit for Offset Adapter SBTOOL−004K90 FTI Hydraulic powerpak SBTOOL−005K90 LB Puller assy SBTOOL−008K90 LB Offset Adapter Refer to paragraph 3.C. for a list of special tools and equipment for this service bulletin. (2) Please send a purchase order to the address below to schedule the kits: Bombardier Service Bulletin Kit Support Team 123 Garratt Blvd, N42−24 Toronto, Ontario Canada M3K 1Y5 Fax: 416−375−3060 Phone: 416−375−3920 Email: sbkits@aero.bombardier.com ### Page 9 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 8 of 67 Jul 17/2009 Revision C, Jun 06/2013 Please contact the Service Bulletin Kit Support Team at the address above for terms and conditions. NOTE: When this service bulletin is completed, tooling kits SBTOOL−004K90, SBTOOL−005K90 and SBTOOL−008K90 must be returned to the address below. Please contact the Customer Account Service Team − Kit Group to get a Return Material Approval (RMA): Bombardier − Chicago Warehouse Distribution 251−A Wille Road Des Plaines, Illinois USA 60018−1817 I. Weight and Balance Not changed. J. Electrical Load Data Not changed. K. References Modification Summary TC601R17554, Revision D Restriction and/or Special Instruction C−A201, Revision D Aircraft Maintenance Manual (AMM) Structural Repair Manual (SRM) Non Destructive Testing Manual (NDTM) For Bombardier Aerospace reference only: PCA 3993. L. Other Publications Affected Aircraft Illustrated Parts Catalogue (AIPC) Maintenance Requirement Manual (MRM) ### Page 10 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 9 of 67 Jul 17/2009 Revision C, Jun 06/2013 M. Relationship Chart PRE−SB PART NUMBER NAME POST−SBPART NUMBER NAME 601R10031−1 MLG Trunnion K601R10032−1 /C0001 or K601R10032−3 /C0019 or K601R10032−9 /C0004 MLG Trunnion 601R10031−2 MLG Trunnion K601R10032−2 /C0001 or K601R10032−4 /C0019 or K601R10032−10 /C0004 MLG Trunnion 601R10031−11 MLG Trunnion K601R10032−3 /C0006 MLG Trunnion 601R10031−12 MLG Trunnion K601R10032−4 /C0006 MLG Trunnion 601R10068−1 MLG Trunnion K601R10032−5 /C0007 MLG Trunnion 601R10068−2 MLG Trunnion K601R10032−6 /C0007 MLG Trunnion 601R10068−5 MLG Trunnion K601R10032−7 /C0008 MLG Trunnion 601R10068−6 MLG Trunnion K601R10032−8 /C0008 MLG Trunnion ### Page 11 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 10 of 67 Jul 17/2009 Revision C, Jun 06/2013 PRE−SB PART NUMBER NAMEPOST−SBPART NUMBERNAME /C0001 For Aircraft 7003−7010, 7013−7067 and 7069−7138 Pre−REO 601R−57−21−003 and Pre−SB 601R−32−054 that have incorporated Service Bulletins 601R−57−046, 601R−57−047 and 601R−57−048. /C0019 For Aircraft 7003−7010, 7013−7067 and 7069−7138 Post−REO 601R−57−21−003 or Post−SB 601R−32−054 that have incorporated Service Bulletins 601R−57−046, 601R−57−047 and 601R−57−048. /C0004 For Aircraft 7011 and 7012 that have incorporated Service Bulletins 601R−32−097, 601R−57−046 and 601R−57−048. /C0006 For Aircraft 7139−7990 and 8000−8017 that have incorporated Service Bulletins 601R−57−046, 601R−57−047 and 601R−57−048. /C0007 For Aircraft 8018−8079 that have incorporated Service Bulletins 601R−57−046 and 601R−57−048. /C0008 For Aircraft 8080−8106 that have incorporated Service Bulletins 601R−57−046 and 601R−57−048. ### Page 12 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 11 of 67 Jul 17/2009 Revision C, Jun 06/2013 2. ACCOMPLISHMENT INSTRUCTIONS PART A − Cold Work the Web of the Left MLG Trunnion A. Job Set−Up Reference Information REFERENCE DESIGNATION AMM 06−44−00 Access Panel AMM 07−11−01−582−801 Put the Aircraft on Jacks AMM 07−11−01−582−804 Removal of the Aircraft from Jacks AMM 10−11−00−000−801 Removal of the Nose Landing Gear Lockpin AMM 10−11−00−000−802 Removal of the Main Landing Gear Lockpins AMM 10−11−00−400−801 Installation of the Nose Landing Gear Lockpin AMM 10−11−00−400−802 Installation of the Main Landing Gear Lockpins AMM 12−00−06−863−802 Release Hydraulic Pressure − System No. 1 and No. 2 AMM 12−00−06−863−804 Release Hydraulic Pressure − System No. 3 AMM 12−00−07−861−801 Connect External AC Power AMM 12−00−07−861−802 Remove External AC Power AMM 24−00−00−910−801 Electrical/Electronic Safety Precautions AMM 27−54−00−866−801 Electrical Extension of the Flaps AMM 27−54−00−866−802 Electrical Retraction of the Flaps AMM 29−00−00−910−801 Hydraulic Safety Precautions AMM 29−10−00−870−801 Bleed Hydraulic System No.1 AMM 29−10−00−870−802 Bleed Hydraulic System No.2 AMM 29−10−00−870−803 Bleed Hydraulic System No.3 AMM 32−11−00−000−801 Removal of the MLG ### Page 13 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 12 of 67 Jul 17/2009 Revision C, Jun 06/2013 REFERENCE DESIGNATION AMM 32−11−00−400−801 Installation of the MLG AMM 32−12−01−000−801 Removal of the Main Landing Gear Doors AMM 32−12−01−400−801 Installation of the Main Landing Gear Doors AMM 32−12−01−820−801 Adjustment of Main Landing Gear Doors AMM 32−30−00−720−801 Functional Test of the Landing Gear Extension/Retraction System AMM 32−34−00−710−801 Operational Test of the Landing Gear Manual−Release−System AMM 32−43−00−710−801 Operational Test of the Brake System NDTM 53−00−097 Eddy Current SRM 51−21−11 Corrosion Prevention Procedures SRM 51−23−00 Pressure, Environment, Fuel Tank and Firewall Sealing SRM 51−24−38 Cold Working of Fastener Holes SRM 51−25−06 Fluid−Resistant (FR) Epoxy Primer SRM 51−25−16 Fluid−Resistant (FR) Polyurethane Topcoat SRM 51−26−00 Cleaning SRM 51−42−21 Hi−Lite Fasteners (1) Install the lockpins on the nose and the main landing gears (Refer to AMM 10−11−00−400−801 and AMM 10−11−00−400−802). WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS, INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT CAN OCCUR. (2) Obey all the electrical/electronic safety precautions (Refer to AMM 24−00−00−910−801). ### Page 14 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 13 of 67 Jul 17/2009 Revision C, Jun 06/2013 (3) Connect the external AC power to the aircraft (Refer to AMM 12−00−07−861−801). WARNING: PUT THE SAFETY DEVICES, THE WARNING SIGNS, AND THE WARNING PLACARDS IN POSITION BEFORE YOU START A PROCEDURE ON OR NEAR: − FLIGHT CONTROLS − FLIGHT CONTROL SURFACES AND − COMPONENTS THAT MOVE. MAKE SURE THAT THERE ARE NO PERSONS OR EQUIPMENT ON OR NEAR THE FLIGHT CONTROL SURFACE. ACCIDENTAL MOVEMENT OF THE FLIGHT CONTROL CAN CAUSE INJURIES TO PERSON AND/OR DAMAGE TO EQUIPMENT . WARNING: OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON ANY HYDRAULIC SYSTEM OR ON A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS, YOU CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. (4) Obey all the hydraulic safety precautions (Refer to AMM 29−00−00−910−801). (5) Extend the flaps (Refer to AMM 27−54−00−866−801). (6) Release the hydraulic pressure from system No.1 and No.2 (Refer to AMM 12−00−06−863−802). (7) Release the hydraulic pressure from system No.3 (Refer to AMM 12−00−06−863−804). (8) On the inboard flap, pull the movable leading−edge vane in the direction of the flap to get access to the work area on the rear spar. (9) Use a strap to keep the movable leading−edge vane retracted. (10) Remove external AC power from the aircraft (Refer to AMM 12−00−07−861−802). WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS, INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT CAN OCCUR. ### Page 15 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 14 of 67 Jul 17/2009 Revision C, Jun 06/2013 (11) Obey all the electrical/electronic safety precautions (Refer to AMM 24−00−00−910−801). (12) Open, safety, and tag the circuit breakers that follow: CB PANEL CB NO. NAME ZONE CBP−1 A2 HYD PUMP 3B 221 CBP−1 A5 HYD PUMP 2 221 CBP−1 F4 FLAPS CONT CH 1 221 CBP−1 F6 LGC/D1 221 CBP−1 F7 WOW 1 221 CBP−1 G3 BRAKE TEMP MON 221 CBP−1 G4 ANTI SKID 221 CBP−1 G11 HYD SYST AC PUMP CONT 3B 221 CBP−1 G14 HYD SYST AC PUMP CONT 2 221 CBP−2 A2 HYD PUMP 3A 222 CBP−2 F3 SECS PWR 2 222 CBP−2 F9 PROX SENS WOW 2 222 CBP−2 G4 ANTI SKID 222 CBP−2 G14 HYD SYST AC PUMP CONT 1 222 CBP−2 G15 HYD SYST AC PUMP CONT 3A 222 CBP−2 N8 SECU2 222 CBP−2 P2 LGC/D1 222 CBP−2 P3 LGC/D2 WOW 1 + 2 222 CBP−2 F4 FLAPS CONT CH 2 222 CBP−4 B13 LGC/D2 222 ### Page 16 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 15 of 67 Jul 17/2009 Revision C, Jun 06/2013 (13) Remove the access panel that follows: ACCESS DESIGNATION 540AT Access Panel CAUTION: INSTALL THE DOOR SUPPORT CABLE IF THE DOOR WILL BE OPEN AT ANY TIME THE AIRCRAFT IS ON THE JACKS. IF YOU DO NOT INSTALL THE SUPPORT CABLE, YOU CAN CAUSE DAMAGE TO THE PASSENGER DOOR. (14) Put the aircraft on jacks (Refer to AMM 07−11−01−582−801). ### Page 17 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 16 of 67 Jul 17/2009 Revision C, Jun 06/2013 B. Procedure (1) Remove the left Main Landing Gear (MLG) from aircraft (Refer to AMM 32−11−00−000−801). (2) Remove the left Main Landing Gear (MLG) door from aircraft (Refer to AMM 32−12−01−000−801). Refer to Figure 1. (3) Remove the door hinge fittings (3) as follows: (a) Remove and discard the six nuts (6) and washers (2) that attach the door hinge fittings (3). (b) Remove the two door hinge fittings (3), two serrated plates (4), and the two laminated shims (5) from the stud pins (8). (c) Measure and record the thickness, and the location of the laminated shims (5). (d) Discard the laminated shims (5). (e) Remove the six nuts (1) and the radius washer (10) from the stud pins (8). (f) Discard the nuts (1). (g) Remove and keep the radius washers (10). (h) Remove and discard the stud pins (8) from the MLG trunnion. (i) Remove and discard the two hi−lites (7) and collars (9) from the MLG trunnion. (4) If hi−lites are installed in the tooling holes, remove and discard two hi−lites (7) and collars (9) from the MLG trunnion (Refer to Figure 1, Note 2). ### Page 18 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 17 of 67 Jul 17/2009 Revision C, Jun 06/2013 Refer to Figures 2 and 3. NOTE: Use SBTOOL−004K90 (hydraulic powerpak), SBTOOL−005K90 (LB puller assy) and SBTOOL−008K90 (LB offset adapter) to do the cold work procedures. NOTE: Use tool kit 601R57−048K90A (drills and reamers), 601R57−048K91B (cold work) and 601R57−048K92 (cold work for LB offset adapter). (5) Cold work six countersink holes (1/4") in the MLG trunnion as follows (Refer to SRM 51−24−38): (a) Make sure that holes for stud pins (8), (9) and (10) have countersinks on the inboard side of MLG trunnion (Refer to Figure 4 and 5). (b) If no countersinks are found, do countersinks for stud pins (8), (9) and (10) on the inboard side of the MLG trunnion (Refer to Figure 4 and 5). (c) With starting reamer (P/N 601R57048K90−9), increase the countersink holes to a diameter of 0.2526 to 0.2544 in. (6.416 to 6.462 mm). (d) Do a detailed inspection of the six countersink holes as follows: 1 With a combination gage (go−no−go) (P/N 601R57048K91−17), make sure that the diameter of holes is correct. 2 Do an eddy current on the inner surface of the six holes (Refer to NDTM 53−00−097). (e) For the hole(s) that have no damage on the inner surface and that have a diameter of 0.2526 to 0.2544 in. (6.416 to 6.462 mm), do as follows: 1 Cold work the countersink hole(s) in the MLG trunnion with nosecap P/N KBC−081−1A, mandrel P/N KBM−8−1−N−1−35−V1 and straight sleeves P/N CBS−8−1−N−16S. NOTE: Point the split in the sleeve to the up or down position. The standard tool diameter number to cold work holes is (STDN) 8−1−N. ### Page 19 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 18 of 67 Jul 17/2009 Revision C, Jun 06/2013 2 With the first oversize final reamer (P/N 601R57048K90−21), increase the countersink holes to a diameter of 0.2620 to 0.2646 in. (6.655 to 6.721 mm), (Refer to Figure 3). 3 Make sure that countersinks have no ridge(s). 4 If ridge(s) is/are found, manually remove the ridge(s) with a countersink tool. 5 Apply chemical conversion coating inside the hole. (f) For hole(s) that have damage on the inner surface and/or have a diameter more than 0.2544 in. (6.462 mm), do as follows: 1 With starting reamer (P/N 601R57048K90−11), increase the countersink hole(s) to a diameter of 0.2684 to 0.2694 in. (6.817 to 6.843 mm). 2 Do a detailed inspection as follows: a With a combination gage (go−no−go) (P/N 601R57048K91−25), make sure that the diameter of holes is/are correct. b Do an eddy current on the inner surface of the hole(s), (Refer to NDTM 53−00−097). 3 For hole(s) that have no damage on the inner surface and have a diameter of 0.2684 to 0.2694 in. (6.817 to 6.843 mm), do as follows: a Cold work the countersink hole(s) for the second oversize with nosecap P/N KBC−082−1A, mandrel P/N KBM−8−2−N−1−35−V1 and straight sleeves P/N CBS−8−2−N−16S. NOTE: Point the split in the sleeve to the up or down position. The standard tool diameter number to cold work holes is (STDN) 8−2−N. b With the second oversize final reamer (P/N 601R57048K90−23), increase the hole (s) to a diameter of 0.2775 to 0.2802 in. (7.049 to 7.117 mm). ### Page 20 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 19 of 67 Jul 17/2009 Revision C, Jun 06/2013 c Make sure that the countersinks have no ridge(s). d If ridge(s) is/are found, manually remove the ridge(s) with a countersink tool. e Apply chemical conversion coating inside the hole. 4 For hole(s) that have damage on the inner surface and/or have a diameter more than 0.2694 in. (6.843 mm), do as follows: a Speak with a representative of Bombardier Aerospace at the Customer Response Center (CRC) at phone number 514−855−8500 for a disposition. (6) Cold work two straight holes (3/16") in the MLG trunnion as follows (Ref. SRM 51−24−38): (a) With starting reamer (P/N 601R57048K90−13), increase two holes to a diameter of 0.1703 to 0.1715 in. (4.326 to 4.356 mm). (b) Do a detailed inspection of the two straight holes as follows: 1 With a combination gage (go−no−go) (P/N 601R57048K91−3), make sure that the diameter of holes is correct. 2 Do an eddy current on the inner surface of the two straight holes (Refer to NDTM 53−00−097). (c) For hole(s) that have no damage on the inner surface and have a diameter of 0.1703 to 0.1715 in. (4.326 to 4.356 mm), do as follows: 1 Cold work the straight hole(s) in the MLG trunnion with nosecap P/N MEN−14A−0601F , mandrel P/N CBM−4−4−N−1−30−V1 and flared sleeves P/N CBS−4−4−N−16F . NOTE: Point the split in the sleeve to the up or down position. The standard tool diameter number to cold work holes is (STDN) 4−4−N. 2 With final reamer (P/N 601R57048K90−25), increase the hole(s) to a diameter of 0.1865 to 0.1890 in. (4.737 to 4.801 mm), (Refer to Figure 3). 3 Apply chemical conversion coating inside the hole. ### Page 21 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 20 of 67 Jul 17/2009 Revision C, Jun 06/2013 (d) For hole(s) that have damage on the inner surface and/or have a diameter more than 0.1715 in. (4.356 mm), do as follows: 1 With starting reamer (P/N 601R57048K90−15), increase the damaged hole(s) to a first oversize diameter of 0.1935 to 0.1953 in. (4.915 to 4.961mm). 2 Do a detailed inspection as follows: a With a combination gage (go−no−go) (P/N 601R57048K91−11), make sure that the diameter of holes is correct. b Do an eddy current on the inside of the straight hole(s) (Refer to NDTM 53−00−097). 3 For hole(s) that have no damage on the inner surface and have a diameter of 0.1935 to 0.1953 in. (4.915 to 4.961mm), do as follows: a Cold work the hole(s) for the first oversize with nosecap P/N MEN−14A−0601F , mandrel P/N CBM−6−1−N−1−30−V1 and flared sleeves P/N CBS−6−1−N−16F . NOTE: Point the split in the sleeve to the up or down position. The standard tool diameter number to cold work holes is (STDN) 6−1−N. b With the first oversize final reamer (P/N 601R57048K90−27), increase hole(s) to a diameter of 0.1995 to 0.2021 in. (5.067 to 5.133 mm), (Refer to Figure 3). c Apply chemical conversion coating inside the hole. 4 For hole(s) that have damage on the inner surface and/or have a diameter more than 0.1953 in. (4.961mm), do as follows: a Speak with a representative of Bombardier Aerospace at the Customer Response Center (CRC) at phone number 514−855−8500 for a disposition. ### Page 22 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 21 of 67 Jul 17/2009 Revision C, Jun 06/2013 (7) Cold work two tooling holes (5/16") in the MLG trunnion as follows (Refer to SRM 51−24−38): (a) With a drill no.19/64 in., increase two tooling holes to a diameter of 0.2969 in. (7.541 mm). (b) With starting reamer (P/N 601R57048K90−17), increase the two holes to a diameter of 0.2995 to 0.3005 in. (7.607 to 7.633 mm). (c) Do a detailed inspection of the two tooling holes as follows: 1 With a combination gage (go−no−go) (P/N 601R57048K91−33), make sure that the diameter of holes is correct. 2 Do an eddy current on the inside of the two tooling holes (Refer to NDTM 53−00−097). (d) For hole(s) that have no damage on the inner surface and have a diameter of 0.2995 to 0.3005 in. (7.607 to 7.633 mm), do as follows: 1 Cold work two tooling holes (5/16") in the MLG trunnion with nosecap P/N MEN−14A−1001F , mandrel P/N CBM−10−0−N−1−40−V1 and flared sleeves P/N CBS−10−0−N−16F. 2 If you don’t have sufficient space to do the cold work, it is possible to install LB offset adapter (P/N SBTOOL−008K90) on the puller (P/N SBTOOL−005K90). Use nosecap P/N CBC−40−1001F and mandrel P/N CBM−10−0−N−1−10−V1 from tool kit P/N 601R57−048K92. NOTE: Refer to Appendix A for installation of the LB offset adapter (P/N SBTOOL−008K90) on the puller (P/N SBTOOL−005K90). NOTE: Point the split in the sleeve to the up or down position. The standard tool diameter number to cold work holes is (STDN) 10−0−N. 3 With final reamer (P/N 601R57048K90−29), increase tooling hole(s) to a diameter of 0.3090 to 0.3105 in. (7.849 to 7.887 mm), (Refer to Figure 3). 4 Apply chemical conversion coating inside the hole. ### Page 23 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 22 of 67 Jul 17/2009 Revision C, Jun 06/2013 (e) For hole(s) that have damage on the inner surface and/or have a diameter more than 0.3005 in. (7.633 mm), do as follows: 1 With starting reamer (P/N 601R57048K90−19), increase the damaged hole(s) to a diameter of 0.3155 to 0.3165 in. (8.014 to 8.039 mm). 2 Do a detailed inspection as follows: a With a combination gage (go−no−go) (P/N 601R57048K91−41), make sure that the diameter of holes is correct. b Do an eddy current on the inside of the hole(s), (Refer to NDTM 53−00−097). 3 For hole(s) that have no damage on the inner surface and have a diameter of 0.3155 to 0.3165 in. (8.014 to 8.039 mm), do as follows: a Cold work the tooling hole(s) for the first oversize with nosecap P/N MEN−14A−1001F , mandrel P/N CBM−10−1−N−1−40−V1 and straight sleeves P/N CBS−10−1−N−16F . b If you don’t have sufficient space to do the cold work, it is possible to install LB offset adapter (P/N SBTOOL−008K90) on the puller (P/N SBTOOL−005K90). Use nosecap P/N CBC−40−1001F and mandrel P/N CBM−10−1−N−1−10−V1 from tool kit P/N 601R57−048K92. NOTE: Refer to Appendix A for installation of the LB offset adapter (P/N SBTOOL−008K90) on the puller (P/N SBTOOL−005K90). NOTE: Point the split in the sleeve to the up or down position. The standard tool diameter number to cold work holes is (STDN) 10−1−N. c With the first oversize final reamer (P/N 601R57048K90−31), increase the hole(s) to a diameter of 0.3245 to 0.3261 in. (8.242 to 8.283 mm), (Refer to Figure 3). d Apply chemical conversion coating inside the hole. ### Page 24 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 23 of 67 Jul 17/2009 Revision C, Jun 06/2013 4 For hole(s) that have damage on the inner surface and/or have a diameter more than 0.3165 in. (8.039 mm), do as follows: a Speak with a representative of Bombardier Aerospace at the Customer Response Center (CRC) at phone number 514−855−8500 for a disposition. For Aircraft 7003 thru 7067, 7069 thru 7990 and 8000 thru 8017 Refer to Figure 4. (8) Install the two door hinge fittings (3) to the MLG trunnion as follows: (a) With a drill, increase the hole of the radius washer (7) to a diameter of 0.266 to 0.270 in. (6.76 to 6.86 mm) for the first oversize hole in the MLG trunnion. (b) If necessary, use a drill to increase hole of the radius washer (7) to diameter of 0.281 to 0.285 in. (7.14 to 7.24 mm) for the second oversize hole in the MLG trunnion, (Refer to view B). (c) Apply chemical conversion coating inside hole of radius washer (7). (d) With sealant, wet−install the stud pins (8) and (9) on the MLG trunnion with the nuts (1) and the radius washer (7), (Refer to view A and B). NOTE: Use kit 601R57−048K1 for first oversize (1/4"). If necessary, use kit 601R57−048K2 for second oversize. (e) Peel laminated shims (5) to the same dimension before removal. (f) Apply MIL−PRF−81733 type IV sealant on both sides of the laminated shims (5). (g) Install the two door hinge fittings (3), two laminated shims (5), two serrated plates (4) on the stud pins with the washers (2) and nuts (6), (Refer to view B, sheet 2). (9) With sealant, wet−install two hi−lites and nuts (11) and (13) in the two tooling holes of the MLG trunnion. NOTE: Use kit 601R57−048K1 for next fastener size (5/16"). If necessary, use kit 601R57−048K2 for first oversize. ### Page 25 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 24 of 67 Jul 17/2009 Revision C, Jun 06/2013 (10) With sealant, wet−install two hi−lites and nuts (15) and (17) in the two holes of the MLG trunnion and the fittings. NOTE: Use kit 601R57−048K1 for next fastener size (3/16"). If necessary, use kit 601R57−048K2 for first oversize. For Aircraft 8018 thru 8106 Refer to Figure 5. (11) Install two door hinge fittings (3) to the MLG trunnion as follows: (a) With a drill, increase the hole of the radius washer (7) to a diameter of 0.266 to 0.270 in (6.76 to 6.86 mm) for first oversize hole in the MLG trunnion. (b) If necessary, use a drill to increase the hole of the radius washer (7) to diameter of 0.281 to 0.285 in. (7.14 to 7.24 mm) for the second oversize in the MLG trunnion, (Refer to view B). (c) Apply chemical conversion coating in the hole of the radius washer (7) and in the cold worked holes of the MLG trunnion. (d) With sealant, wet−install the stud pins (8), (9) and (10) in the MLG trunnion with the nuts (1) and the radius washer (7), (Refer to view A and B). NOTE: Use kit 601R57−048K3 for first oversize (1/4"). If necessary, use kit 601R57−048K4 for second oversize. (e) Peel laminated shims (5) to the same dimension before removal. (f) Apply MIL−PRF−81733 type IV sealant on both sides of the laminated shims (5). (g) Attach two laminated shims (5), two serrated plates (4), two door hinge fittings (3) on the stud pins with the washers (2) and nuts (6), (Refer to view B, sheet 2). (12) With sealant, wet−install two hi−lites and nuts (11) and (13) in the two tooling holes of the MLG trunnion. NOTE: Use kit 601R57−048K3 for next fastener size (5/16"). If necessary, use kit 601R57−048K4 for first oversize. ### Page 26 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 25 of 67 Jul 17/2009 Revision C, Jun 06/2013 (13) With sealant, wet−install two hi−lites and nuts (15) and (17) in the two holes of the MLG trunnion and the fittings. NOTE: Use kit 601R57−048K3 for next fastener size (3/16"). If necessary, use kit 601R57−048K4 for first oversize. For all Aircraft (14) Install the left MLG on aircraft (Refer to AMM 32−11−00−400−801). (15) Install the left MLG door on aircraft (Refer to AMM 32−12−01−400−801). (16) Do the identification of the MLG trunnion as follows: (a) If an MLG trunnion was repaired or replaced, speak with a representative of the Customer Response Centre (CRC) at 514−855−8500 for an identification number. For Aircraft 7011 and 7012 (b) If Service Bulletins 601R−32−097, 601R−57−046 and 601R−57−048 have been incorporated, do as follows: 1 Clean the identification areas with solvent (refer to SRM 51−26−00). 2 Identify the MLG trunnion as K601R10032−9. 3 Apply a layer of clear polyurethane topcoat on the identifications (refer to SRM 51−25−16). For Aircraft 7003−7010, 7013−7067 and 7069−7138 Pre-REO 601R−57−21−003 and Pre-SB 601R−32−054 (c) If Service Bulletins 601R−57−046, 601R−57−047 and 601R−57−048 have been incorporated, do as follows: 1 Clean the identification areas with solvent (refer to SRM 51−26−00). 2 Identify the MLG trunnion as K601R10032−1. 3 Apply a layer of clear polyurethane topcoat on the identifications (refer to SRM 51−25−16). ### Page 27 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 26 of 67 Jul 17/2009 Revision C, Jun 06/2013 For Aircraft 7003−7010, 7013−7067 and 7069−7138 Post-REO 601R−57−21−003 or Post-SB 601R−32−054 (d) If Service Bulletins 601R−57−046, 601R−57−047 and 601R−57−048 have been incorporated, do as follows: 1 Clean the identification areas with solvent (refer to SRM 51−26−00). 2 Identify the MLG trunnion as K601R10032−3. 3 Apply a layer of clear polyurethane topcoat on the identifications (refer to SRM 51−25−16). For Aircraft 7139−7990 and 8000−8017 (e) If Service Bulletins 601R−57−046, 601R−57−047 and 601R−57−048 have been incorporated, do as follows: 1 Clean the identification areas with solvent (refer to SRM 51−26−00). 2 Identify the MLG trunnion as K601R10032−3. 3 Apply a layer of clear polyurethane topcoat on the identifications (refer to SRM 51−25−16). For Aircraft 8018−8079 (f) If Service Bulletins 601R−57−046 and 601R−57−048 have been incorporated, do as follows: 1 Clean the identification areas with solvent (refer to SRM 51−26−00). 2 Identify the MLG trunnion as K601R10032−5. 3 Apply a layer of clear polyurethane topcoat on the identifications (refer to SRM 51−25−16). For Aircraft 8080−8106 (g) If Service Bulletins 601R−57−046 and 601R−57−048 have been incorporated, do as follows: 1 Clean the identification areas with solvent (refer to SRM 51−26−00). 2 Identify the MLG trunnion as K601R10032−7. 3 Apply a layer of clear polyurethane topcoat on the identifications (refer to SRM 51−25−16). ### Page 28 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 27 of 67 Jul 17/2009 Revision C, Jun 06/2013 C. Job Close−Out (1) Remove all tools, equipment, and unwanted materials from the work area. (2) Remove the tags and close the circuit breakers that follow: CB PANEL CB NO. NAME ZONE CBP−1 A2 HYD PUMP 3B 221 CBP−1 A5 HYD PUMP 2 221 CBP−1 F4 FLAPS CONT CH 1 221 CBP−1 F6 LGC/D1 221 CBP−1 F7 WOW 1 221 CBP−1 G3 BRAKE TEMP MON 221 CBP−1 G4 ANTI SKID 221 CBP−1 G11 HYD SYST AC PUMP CONT 3B 221 CBP−1 G14 HYD SYST AC PUMP CONT 2 221 CBP−2 A2 HYD PUMP 3A 222 CBP−2 F3 SECS PWR 2 222 CBP−2 F9 PROX SENS WOW 2 222 CBP−2 G4 ANTI SKID 222 CBP−2 G14 HYD SYST AC PUMP CONT 1 222 CBP−2 G15 HYD SYST AC PUMP CONT 3A 222 CBP−2 N8 SECU2 222 CBP−2 P2 LGC/D1 222 CBP−2 P3 LGC/D2 WOW 1 + 2 222 CBP−2 F4 FLAPS CONT CH 2 222 CBP−4 B13 LGC/D2 222 (3) Apply external AC power to the aircraft (Refer to AMM 12−00−07−861−801). (4) Bleed hydraulic system No.1 (Refer to AMM 29−10−00−870−801). ### Page 29 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 28 of 67 Jul 17/2009 Revision C, Jun 06/2013 (5) Bleed hydraulic system No.2 (Refer to AMM 29−10−00−870−802). (6) Bleed hydraulic system No.3 (Refer to AMM 29−10−00−870−803). (7) Adjust the MLG door (Refer to AMM 32−12−01−820−801). (8) Retract the inboard flap, (Refer to AMM 27−54−00−866−802). (9) Do the functionnal test of the landing gear extension and retraction system (Refer to AMM 32−30−00−720−801). (10) Do the operational test of the landing gear manual release system (Refer to 32−34−00−710−801). (11) Do the operational test of the brake system, (Refer to 32−43−00−710−801). (12) Install the access panel that follows: ACCESS DESIGNATION 540AT Access Panel (13) Remove the nose landing gear lockpin (Refer to AMM 10−11−00−000−801). (14) Remove the MLG lockpins (Refer to AMM 10−11−00−000−802). (15) Remove the aircraft from jacks (Refer to AMM 07−11−01−582−804). (16) When PART A of this service bulletin is completed, make this entry in the applicable logbook(s): /quoteblleftService Bulletin 601R−57−048, Revision C, Wings − Center Wing Primary Structure − Cold Work of Holes on the web of the Main Landing Gear (MLG) Trunnion, PART A, incorporated." ### Page 30 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 29 of 67 Jul 17/2009 Revision C, Jun 06/2013 PART B − Cold Work the Web of the Right MLG Trunnion D. Job Set−Up Reference Information REFERENCE DESIGNATION AMM 06−44−00 Access Panel AMM 07−11−01−582−801 Put the Aircraft on Jacks AMM 07−11−01−582−804 Removal of the Aircraft from Jacks AMM 10−11−00−000−801 Removal of the Nose Landing Gear Lockpin AMM 10−11−00−000−802 Removal of the Main Landing Gear Lockpins AMM 10−11−00−400−801 Installation of the Nose Landing Gear Lockpin AMM 10−11−00−400−802 Installation of the Main Landing Gear Lockpins AMM 12−00−06−863−802 Release Hydraulic Pressure − System No. 1 and No. 2 AMM 12−00−06−863−804 Release Hydraulic Pressure − System No. 3 AMM 12−00−07−861−801 Connect External AC Power AMM 12−00−07−861−802 Remove External AC Power AMM 24−00−00−910−801 Electrical/Electronic Safety Precautions AMM 27−54−00−866−801 Electrical Extension of the Flaps AMM 27−54−00−866−802 Electrical Retraction of the Flaps AMM 29−00−00−910−801 Hydraulic Safety Precautions AMM 29−10−00−870−801 Bleed Hydraulic System No.1 AMM 29−10−00−870−802 Bleed Hydraulic System No.2 AMM 29−10−00−870−803 Bleed Hydraulic System No.3 AMM 32−11−00−000−801 Removal of the MLG AMM 32−11−00−400−801 Installation of the MLG AMM 32−12−01−000−801 Removal of the Main Landing Gear Doors ### Page 31 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 30 of 67 Jul 17/2009 Revision C, Jun 06/2013 REFERENCE DESIGNATION AMM 32−12−01−400−801 Installation of the Main Landing Gear Doors AMM 32−12−01−820−801 Adjustment of Main Landing Gear Doors AMM 32−30−00−720−801 Functional Test of the Landing Gear Extension/Retraction System AMM 32−34−00−710−801 Operational Test of the Landing Gear Manual−Release−System AMM 32−43−00−710−801 Operational Test of the Brake System NDTM 53−00−097 Eddy Current SRM 51−21−11 Corrosion Prevention Procedures SRM 51−23−00 Pressure, Environment, Fuel Tank and Firewall Sealing SRM 51−24−38 Cold Working of Fastener Holes SRM 51−25−06 Fluid−Resistant (FR) Epoxy Primer SRM 51−25−16 Fluid−Resistant (FR) Polyurethane Topcoat SRM 51−26−00 Cleaning SRM 51−42−21 Hi−lite Fasteners (1) Install the lockpins on the nose and the main landing gears (Refer to AMM 10−11−00−400−801 and AMM 10−11−00−400−802). WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS, INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT CAN OCCUR. (2) Obey all the electrical/electronic safety precautions (Refer to AMM 24−00−00−910−801). ### Page 32 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 31 of 67 Jul 17/2009 Revision C, Jun 06/2013 (3) Connect the external AC power to the aircraft (Refer to AMM 12−00−07−861−801). WARNING: PUT THE SAFETY DEVICES, THE WARNING SIGNS, AND THE WARNING PLACARDS IN POSITION BEFORE YOU START A PROCEDURE ON OR NEAR: − FLIGHT CONTROLS − FLIGHT CONTROL SURFACES AND − COMPONENTS THAT MOVE. MAKE SURE THAT THERE ARE NO PERSONS OR EQUIPMENT ON OR NEAR THE FLIGHT CONTROL SURFACE. ACCIDENTAL MOVEMENT OF THE FLIGHT CONTROL CAN CAUSE INJURIES TO PERSON AND/OR DAMAGE TO EQUIPMENT . WARNING: OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON ANY HYDRAULIC SYSTEM OR ON A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS, YOU CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. (4) Obey all the hydraulic safety precautions (Refer to AMM 29−00−00−910−801). (5) Extend the flaps (Refer to AMM 27−54−00−866−801). (6) Release the hydraulic pressure from system No.1 and No.2 (Refer to AMM 12−00−06−863−802). (7) Release the hydraulic pressure from system No.3 (Refer to AMM 12−00−06−863−804). (8) On the inboard flap, pull the movable leading−edge vane in the direction of the flap to get access to the work area on the rear spar. (9) Use a strap to keep the movable leading−edge vane retracted. (10) Remove the external AC power from the aircraft (Refer to AMM 12−00−07−861−802). WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS, INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT CAN OCCUR. ### Page 33 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 32 of 67 Jul 17/2009 Revision C, Jun 06/2013 (11) Obey all the electrical/electronic safety precautions (Refer to AMM 24−00−00−910−801). (12) Open, safety, and tag the circuit breakers that follow: CB PANEL CB NO. NAME ZONE CBP−1 A2 HYD PUMP 3B 221 CBP−1 A5 HYD PUMP 2 221 CBP−1 F4 FLAPS CONT CH 1 221 CBP−1 F6 LGC/D1 221 CBP−1 F7 WOW 1 221 CBP−1 G3 BRAKE TEMP MON 221 CBP−1 G4 ANTI SKID 221 CBP−1 G11 HYD SYST AC PUMP CONT 3B 221 CBP−1 G14 HYD SYST AC PUMP CONT 2 221 CBP−2 A2 HYD PUMP 3A 222 CBP−2 F3 SECS PWR 2 222 CBP−2 F9 PROX SENS WOW 2 222 CBP−2 G4 ANTI SKID 222 CBP−2 G14 HYD SYST AC PUMP CONT 1 222 CBP−2 G15 HYD SYST AC PUMP CONT 3A 222 CBP−2 N8 SECU2 222 CBP−2 P2 LGC/D1 222 CBP−2 P3 LGC/D2 WOW 1 + 2 222 CBP−2 F4 FLAPS CONT CH 2 222 CBP−4 B13 LGC/D2 222 ### Page 34 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 33 of 67 Jul 17/2009 Revision C, Jun 06/2013 (13) Remove the access panel that follows: ACCESS DESIGNATION 640AT Access Panel CAUTION: INSTALL THE DOOR SUPPORT CABLE IF THE DOOR WILL BE OPEN AT ANY TIME THE AIRCRAFT IS ON THE JACKS. IF YOU DO NOT INSTALL THE SUPPORT CABLE, YOU CAN CAUSE DAMAGE TO THE PASSENGER DOOR. (14) Put the aircraft on jacks (Refer to AMM 07−11−01−582−801). ### Page 35 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 34 of 67 Jul 17/2009 Revision C, Jun 06/2013 E. Procedure (1) Remove the right Main Landing Gear (MLG) from aircraft (Refer to AMM 32−11−00−000−801). (2) Remove the right Main Landing Gear (MLG) door from aircraft (Refer to AMM 32−12−01−000−801). Refer to Figure 1. (3) Remove the door hinge fittings (3) as follows: (a) Remove and discard the six nuts (6) and washers (2) that attach the door hinge fittings (3). (b) Remove the two door hinge fittings (3), two serrated plates (4), and the two laminated shims (5) from the stud pins (8). (c) Measure and record the thickness, and the location of the laminated shims (5). (d) Discard the laminated shims (5). (e) Remove the six nuts (1) and the radius washer (10) from stud pins (8). (f) Discard the nuts (1). (g) Remove and keep the radius washer (10). (h) Remove and discard the stud pins (8) from the MLG trunnion. (i) Remove and discard the two hi−lites (7) and collars (9) from the MLG trunnion. (4) If hi−lites are installed in the tooling holes, remove and discard two hi−lites (7) and collars (9) from the MLG trunnion (Refer to Figure 1, Note 2). ### Page 36 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 35 of 67 Jul 17/2009 Revision C, Jun 06/2013 Refer to Figures 2 and 3. NOTE: Use SBTOOL−004K90 (hydraulic powerpak), SBTOOL−005K90 (LB puller assy) and SBTOOL−008K90 (LB offset adapter) to do the cold work procedures. NOTE: Use tool kit 601R57−048K90A (drills and reamers), 601R57−048K91B (cold work) and 601R57−048K92 (cold work for LB off set adapter). (5) Cold work six countersink holes (1/4") in the MLG trunnion as follows (Ref. SRM 51−24−38): (a) Make sure that holes for stud pins (8), (9) and (10) have countersinks on the inboard side of MLG trunnion (Refer to Figure 4 and 5). (b) If no countersinks are found, do countersinks for stud pins (8), (9) and (10) on the inboard side of the MLG trunnion (Refer to Figure 4 and 5). (c) With starting reamer (P/N 601R57048K90−9), increase the six countersink holes to a diameter of 0.2526 to 0.2544 in. (6.416 to 6.462 mm). (d) Do a detailed inspection of the six countersink holes as follows: 1 With a combination gage (go−no−go) (P/N 601R57048K91−17), make sure that the diameter of holes is correct. 2 Do an eddy current on the inner surface of the six holes (Refer to NDTM 53−00−097). (e) For the hole(s) that have no damage on the inner surface and that have a diameter of 0.2526 to 0.2544 in. (6.416 to 6.462 mm), do as follows: 1 Cold work the countersink hole(s) in the MLG trunnion with nosecap P/N KBC−081−1A, mandrel P/N KBM−8−1−N−1−35−V1 and straight sleeves P/N CBS−8−1−N−16S. NOTE: Point the split in the sleeve to the up or down position. The standard tool diameter number to cold work holes is (STDN) 8−1−N. ### Page 37 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 36 of 67 Jul 17/2009 Revision C, Jun 06/2013 2 With the first oversize final reamer (P/N 601R57048K90−21) , increase the countersink holes to a diameter of 0.2620 to 0.2646 in. (6.655 to 6.721 mm), (Refer to Figure 3). 3 Make sure that the countersinks have no ridge(s). 4 If ridge(s) is/are found, manually remove the ridge(s) with a countersink tool. 5 Apply chemical conversion coating inside the hole. (f) For hole(s) that have damage on the inner surface and/or have a diameter more than 0.2544 in. (6.462 mm), do as follows: 1 With starting reamer (P/N 601R57048K90−11), increase the countersink hole(s) to a diameter of 0.2684 to 0.2694 in. (6.817 to 6.843 mm). 2 Do a detailed inspection as follows: a With a combination gage (go−no−go) (P/N 601R57048K91−25), make sure that the diameter of holes is/are correct. b Do an eddy current on the inner surface of the hole(s), (Refer to NDTM 53−00−097). 3 For hole(s) that have no damage on the inner surface and have a diameter of 0.2684 to 0.2694 in. (6.817 to 6.843 mm), do as follows: a Cold work the countersink hole(s) for the second oversize with nosecap P/N KBC−082−1A, mandrel P/N KBM−8−2−N−1−35−V1 and straight sleeves P/N CBS−8−2−N−16S. NOTE: Point the split in the sleeve to the up or down position. The standard tool diameter number to cold work holes is (STDN) 8−2−N. b With the second oversize final reamer (P/N 601R57048K90−23), increase the hole (s) to a diameter of 0.2775 to 0.2802 in. (7.049 to 7.117 mm). ### Page 38 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 37 of 67 Jul 17/2009 Revision C, Jun 06/2013 c Make sure that countersinks have no ridge(s). d If ridge(s) is/are found, manually remove the ridge(s) with a countersink tool. e Apply chemical conversion coating inside the hole. 4 For hole(s) that have damage on the inner surface and/or have a diameter more than 0.2694 in. (6.843 mm), do as follows: a Speak with a representative of Bombardier Aerospace at the Customer Response Center (CRC) at phone number 514−855−8500 for a disposition. (6) Cold work two straight holes (3/16") in the MLG trunnion as follows (Ref. SRM 51−24−38): (a) With starting reamer (P/N 601R57048K90−13), increase two holes to a diameter of 0.1703 to 0.1715 in. (4.326 to 4.356 mm). (b) Do a detailed inspection of the two straight holes as follows: 1 With a combination gage (go−no−go) (P/N 601R57048K91−3), make sure that the diameter of holes is correct. 2 Do an eddy current on the inner surface of the two straight holes (Refer to NDTM 53−00−097). (c) For hole(s) that have no damage on the inner surface and have a diameter of 0.1703 to 0.1715 in. (4.326 to 4.356 mm), do as follows: 1 Cold work the straight hole(s) in the MLG trunnion with nosecap P/N MEN−14A−0601F , mandrel P/N CBM−4−4−N−1−30−V1 and flared sleeves P/N CBS−4−4−N−16F . NOTE: Point the split in the sleeve to the up or down position. The standard tool diameter number to cold work holes is (STDN) 4−4−N. 2 With final reamer (P/N 601R57048K90−25), increase the hole(s) to a diameter of 0.1865 to 0.1890 in. (4.737 to 4.801 mm), (Refer to Figure 3). 3 Apply chemical conversion coating inside the hole. ### Page 39 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 38 of 67 Jul 17/2009 Revision C, Jun 06/2013 (d) For hole(s) that have damage on the inner surface and/or have a diameter more than 0.1715 in. (4.356 mm), do as follows: 1 With starting reamer (P/N 601R57048K90−15), increase the damaged hole(s) to a first oversize diameter of 0.1935 to 0.1953 in. (4.915 to 4.961mm). 2 Do a detailed inspection as follows: a With a combination gage (go−no−go) (P/N 601R57048K91−11), make sure that the diameter of holes is correct. b Do an eddy current on the inside of the straight hole(s) (Refer to NDTM 53−00−097). 3 For hole(s) that have no damage on the inner surface and have a diameter of 0.1935 to 0.1953 in. (4.915 to 4.961mm), do as follows: a Cold work the hole(s) for the first oversize with nosecap P/N MEN−14A−0601F , mandrel P/N CBM−6−1−N−1−30−V1 and flared sleeves P/N CBS−6−1−N−16F . NOTE: Point the split in the sleeve to the up or down position. The standard tool diameter number to cold work holes is (STDN) 6−1−N. b With the first oversize final reamer (P/N 601R57048K90−27), increase hole(s) to a diameter of 0.1995 to 0.2021 in. (5.067 to 5.133 mm), (Refer to Figure 3). c Apply chemical conversion coating inside the hole. 4 For hole(s) that have damage on the inner surface and/or have a diameter more than 0.1953 in. (4.961mm), do as follows: a Speak with a representative of Bombardier Aerospace at the Customer Response Center (CRC) at phone number 514−855−8500 for a disposition. ### Page 40 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 39 of 67 Jul 17/2009 Revision C, Jun 06/2013 (7) Cold work two tooling holes (5/16") in the MLG trunnion as follows (Refer to SRM 51−24−38): (a) With a drill no.19/64 in., increase two tooling holes to a diameter of 0.2969 in.(7.541 mm). (b) With starting reamer (P/N 601R57048K90−17), increase the two holes to a diameter of 0.2995 to 0.3005 in. (7.607 to 7.633 mm). (c) Do a detailed inspection of the two tooling holes as follows: 1 With a combination gage (go−no−go) (P/N 601R57048K91−33), make sure that the diameter of holes is correct. 2 Do an eddy current on the inside of the two tooling holes (Refer to NDTM 53−00−097). (d) For hole(s) that have no damage on the inner surface and have a diameter of 0.2995 to 0.3005 in. (7.607 to 7.633 mm), do as follows: 1 Cold work two tooling holes (5/16") in the MLG trunnion with nosecap P/N MEN−14A−1001F , mandrel P/N CBM−10−0−N−1−40−V1 and flared sleeves P/N CBS−10−0−N−16F. 2 If you don’t have sufficient space to do the cold work, it is possible to install LB offset adapter (P/N SBTOOL−008K90) on the puller (P/N SBTOOL−005K90). Use nosecap P/N CBC−40−1001F and mandrel P/N CBM−10−0−N−1−10−VI from tool kit P/N 601R57−048K92. NOTE: Refer to Appendix A for installation of the LB offset adapter (P/N SBTOOL−008K90) on the puller (P/N SBTOOL−005K90). NOTE: Point the split in the sleeve to the up or down position. The standard tool diameter number to cold work holes is (STDN) 10−0−N. 3 With final reamer (P/N 601R57048K90−29), increase tooling hole(s) to a diameter of 0.3090 to 0.3105 in. (7.849 to 7.887 mm), (Refer to Figure 3). 4 Apply chemical conversion coating inside the hole. ### Page 41 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 40 of 67 Jul 17/2009 Revision C, Jun 06/2013 (e) For hole(s) that have damage on the inner surface and/or have a diameter more than 0.3005 in. (7.633 mm), do as follows: 1 With starting reamer (P/N 601R57048K90−19), increase the damaged hole(s) to a diameter of 0.3155 to 0.3165 in. (8.014 to 8.039 mm). 2 Do a detailed inspection as follows: a With a combination gage (go−no−go) (P/N 601R57048K91−41), make sure that the diameter of holes is correct. b Do an eddy current on the inside of the hole(s), (Refer to NDTM 53−00−097). 3 For hole(s) that have no damage on the inner surface and have a diameter of 0.3155 to 0.3165 in. (8.014 to 8.039 mm), do as follows: a Cold work the tooling hole(s) for the first oversize with nosecap P/N MEN−14A−1001F , mandrel P/N CBM−10−1−N−1−40−V1 and straight sleeves P/N CBS−10−1−N−16F . b If you don’t have sufficient space to do the cold work, it is possible to install LB offset adapter (P/N SBTOOL−008K90) to the puller (P/N SBTOOL−005K90). Use nosecap P/N CBC−40−1001F and mandrel P/N CBM−10−0−N−1−10−V1 from tool kit P/N 601R57−048K92. NOTE: Refer to Appendix A for installation of the LB offset adapter (P/N SBTOOL−008K90) on the puller (P/N SBTOOL−005K90). NOTE: Point the split in the sleeve to the up or down position. The standard tool diameter number to cold work holes is (STDN) 10−1−N. c With the first oversize final reamer (P/N 601R57048K90−31), increase the hole(s) to a diameter of 0.3245 to 0.3261 in. (8.242 to 8.283 mm), (Refer to Figure 3). d Apply chemical conversion coating inside the hole. ### Page 42 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 41 of 67 Jul 17/2009 Revision C, Jun 06/2013 4 For hole(s) that have damage on the inner surface and/or have a diameter more than 0.3165 in. (8.039 mm), do as follows: a Speak with a representative of Bombardier Aerospace at the Customer Response Center) CRC) at phone number 514−855−8500 for a disposition. For Aircraft 7003 thru 7067, 7069 thru 7990 and 8000 thru 8017 Refer to Figure 4. (8) Install the two hinge door fittings (3) to the MLG trunnion as follows: (a) With a drill, increase the hole of the radius washer (7) to a diameter of 0.266 to 0.270 in. (6.76 to 6.86 mm) for the first oversize hole in the MLG trunnion. (b) If necessary, use a drill to increase hole of the radius washer (7) to diameter of 0.281 to 0.285 in. (7.14 to 7.24 mm) for the second oversize hole in the MLG trunnion, (Refer to view B). (c) Apply chemical conversion coating inside hole of radius washer (7). (d) With sealant, wet−install the stud pins (8), and (9) on the MLG trunnion with the nuts (1) and the radius washer (7), (Refer to view A and B). NOTE: Use kit 601R57−048K5 for first oversize (1/4"). If necessary, use kit 601R57−048K2 for second oversize. (e) Peel laminated shims (5) to the same dimension before removal. (f) Apply MIL−PRF−81733 type IV sealant on both sides of the laminated shims (5). (g) Install the two door hinge fittings (3), two laminated shims (5), two serrated plates (4) on the stud pins with the washers (2) and nuts (6), (Refer to view B, sheet 2). (9) With sealant, wet−install two hi−lites and nuts (11) and (13) in the two tooling holes of the MLG trunnion. NOTE: Use kit 601R57−048K5 for next fastener size (5/16"). If necessary, use kit 601R57−048K2 for first oversize. ### Page 43 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 42 of 67 Jul 17/2009 Revision C, Jun 06/2013 (10) With sealant, wet−install two hi−lites and nuts (15) and (17) in the two holes of the MLG trunnion and the fittings. NOTE: Use kit 601R57−048K5 for next fastener size (3/16"). If necessary, use kit 601R57−048K2 for first oversize. For Aircraft 8018 thru 8106 Refer to Figure 5. (11) Install the two door hinge fittings (3) to the MLG trunnion as follows: (a) With a drill, increase the hole of the radius washer (7) to diameter of 0.266 to 0.270 in. (6.76 to 6.86 mm) for first oversize hole in the MLG trunnion. (b) If necessary, use a drill to increase the hole of the radius washer (7) to diameter of 0.281 to 0.285 in. (7.14 to 7.24 mm) for the second oversize hole in the MLG trunnion, (Refer to view B). (c) Apply chemical conversion coating in the hole of the radius washer (7) and in the cold worked holes of the MLG trunnion. (d) With sealant, wet−install the stud pins (8), (9) and (10) in the MLG trunnion with the nuts (1) and the radius washer (7), (Refer to view A and B). NOTE: Use kit 601R57−048K6 for first oversize (1/4"). If necessary, use kit 601R57−048K4 for second oversize. (e) Peel laminated shims (5) to the same dimension before removal. (f) Apply MIL−PRF−81733 type IV sealant on both sides of laminated shims (5). (g) Install the two laminated shims (5), two serrated plates (4), two door hinge fittings (3) on the stud pins with the washers (2) and nuts (6), (Refer to view B, sheet 2). (12) With sealant, wet−install two hi−lites and nuts (11) and (13) in the two tooling holes of the MLG trunnion. NOTE: Use kit 601R57−048K6 for next fastener size (5/16"). If necessary, use kit 601R57−048K4 for first oversize. ### Page 44 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 43 of 67 Jul 17/2009 Revision C, Jun 06/2013 (13) With sealant, wet−install two hi−lites and nuts (15) and (17) in the two holes of the MLG trunnion and the fittings. NOTE: Use kit 601R57−048K6 for next fastener size (3/16"). If necessary, use kit 601R57−048K4 for first oversize. For all Aircraft (14) Install the right MLG on aircraft (Refer to AMM 32−11−00−400−801). (15) Install the right MLG door on aircraft (Refer to AMM 32−12−01−400−801). (16) Do the identification of the MLG trunnion as follows: (a) If an MLG trunnion was repaired or replaced, speak with a representative of the Customer Response Centre (CRC) at 514−855−8500 for an identification number. For Aircraft 7011 and 7012 (b) If Service Bulletins 601R−32−097, 601R−57−046 and 601R−57−048 have been incorporated, do as follows: 1 Clean the identification areas with solvent (refer to SRM 51−26−00). 2 Identify the MLG trunnion as K601R10032−10. 3 Apply a layer of clear polyurethane topcoat on the identifications (refer to SRM 51−25−16). For Aircraft 7003−7010, 7013−7067 and 7069−7138 Pre-REO 601R−57−21−003 and Pre-SB 601R−32−054 (c) If Service Bulletins 601R−57−046, 601R−57−047 and 601R−57−048 have been incorporated, do as follows: 1 Clean the identification areas with solvent (refer to SRM 51−26−00). 2 Identify the MLG trunnion as K601R10032−2. 3 Apply a layer of clear polyurethane topcoat on the identifications (refer to SRM 51−25−16). ### Page 45 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 44 of 67 Jul 17/2009 Revision C, Jun 06/2013 For Aircraft 7003−7010, 7013−7067 and 7069−7138 Post-REO 601R−57−21−003 or Post-SB 601R−32−054 (d) If Service Bulletins 601R−57−046, 601R−57−047 and 601R−57−048 have been incorporated, do as follows: 1 Clean the identification areas with solvent (refer to SRM 51−26−00). 2 Identify the MLG trunnion as K601R10032−4. 3 Apply a layer of clear polyurethane topcoat on the identifications (refer to SRM 51−25−16). For Aircraft 7139−7990 and 8000−8017 (e) If Service Bulletins 601R−57−046, 601R−57−047 and 601R−57−048 have been incorporated, do as follows: 1 Clean the identification areas with solvent (refer to SRM 51−26−00). 2 Identify the MLG trunnion as K601R10032−4. 3 Apply a layer of clear polyurethane topcoat on the identifications (refer to SRM 51−25−16). For Aircraft 8018−8079 (f) If Service Bulletins 601R−57−046 and 601R−57−048 have been incorporated, do as follows: 1 Clean the identification areas with solvent (refer to SRM 51−26−00). 2 Identify the MLG trunnion as K601R10032−6. 3 Apply a layer of clear polyurethane topcoat on the identifications (refer to SRM 51−25−16). For Aircraft 8080−8106 (g) If Service Bulletins 601R−57−046 and 601R−57−048 have been incorporated, do as follows: 1 Clean the identification areas with solvent (refer to SRM 51−26−00). 2 Identify the MLG trunnion as K601R10032−8. 3 Apply a layer of clear polyurethane topcoat on the identifications (refer to SRM 51−25−16). ### Page 46 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 45 of 67 Jul 17/2009 Revision C, Jun 06/2013 F . Job Close−Out (1) Remove all tools, equipment, and unwanted materials from the work area. (2) Remove the tags and close the circuit breakers that follow: CB PANEL CB NO. NAME ZONE CBP−1 A2 HYD PUMP 3B 221 CBP−1 A5 HYD PUMP 2 221 CBP−1 F4 FLAPS CONT CH 1 221 CBP−1 F6 LGC/D1 221 CBP−1 F7 WOW 1 221 CBP−1 G3 BRAKE TEMP MON 221 CBP−1 G4 ANTI SKID 221 CBP−1 G11 HYD SYST AC PUMP CONT 3B 221 CBP−1 G14 HYD SYST AC PUMP CONT 2 221 CBP−2 A2 HYD PUMP 3A 222 CBP−2 F3 SECS PWR 2 222 CBP−2 F9 PROX SENS WOW 2 222 CBP−2 G4 ANTI SKID 222 CBP−2 G14 HYD SYST AC PUMP CONT 1 222 CBP−2 G15 HYD SYST AC PUMP CONT 3A 222 CBP−2 N8 SECU2 222 CBP−2 P2 LGC/D1 222 CBP−2 P3 LGC/D2 WOW 1 + 2 222 CBP−2 F4 FLAPS CONT CH 2 222 CBP−4 B13 LGC/D2 222 (3) Apply external AC power to the aircraft (Refer to AMM 12−00−07−861−801). (4) Bleed hydraulic system No.1 (Refer to AMM 29−10−00−870−801). ### Page 47 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 46 of 67 Jul 17/2009 Revision C, Jun 06/2013 (5) Bleed hydraulic system No.2 (Refer to AMM 29−10−00−870−802). (6) Bleed hydraulic system No.3 (Refer to AMM 29−10−00−870−803). (7) Adjust the MLG door (Refer to AMM 32−12−01−820−801). (8) Retract the inboard flap, (Refer to AMM 27−54−00−866−802). (9) Do the functionnal test of the landing gear extension and retraction system (Refer to AMM 32−30−00−720−801). (10) Do the operational test of the landing gear manual release system (Refer to AMM 32−34−00−710−801). (11) Do the operational test of the brake system, (Refer to AMM 32−43−00−710−801). (12) Install the access panel that follows: ACCESS DESIGNATION 640AT Access Panel (13) Remove the nose landing gear lockpin (Refer to AMM 10−11−00−000−801). (14) Remove the MLG lockpins (Refer to AMM 10−11−00−000−802). (15) Remove the aircraft from jacks (Refer to AMM 07−11−01−582−804). (16) When PART B of this service bulletin is completed, make this entry in the applicable logbook(s): /quoteblleftService Bulletin 601R−57−048, Revision C, Wings − Center Wing Primary Structure − Cold Work of Holes on the web of the Main Landing Gear (MLG) Trunnion, PART B, incorporated." ### Page 48 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 47 of 67 Jul 17/2009 Revision C, Jun 06/2013 Removal of door hinge fitting and fasteners Figure 1 MLG TRUNNION (REF) rsb601r57048_002.dg, gb, 04/09/09 A 9 7 7 9 1 8 5 5 4 4 3 3 2 6 2 6 LEGEND 1. Nut. 2. Washer. 3. Door hinge fitting. 4. Serrated plate. 5. Laminated shim. 6. Nut. 7. Hi−Lite. 8. Stud pin. A 9. Collar. 8 10. Radius washer. 10 1 1 2 Hi−lites and collars for tooling holes 7 2 9 7 2 2 9 2 NOTES 1. Left side is shown, Right side is opposite. ### Page 49 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 48 of 67 Jul 17/2009 Revision C, Jun 06/2013 Cold Work Figure 2 NOTES rsb601r57048_003.dg, gb, 04/09/09 A A VIEW LOOKING OUTBOARD SYMBOL FASTENERSIZE STARTING HOLE DIAMETER 3/16” 3/16” 1st O/S 0.1703 to 0.1715 in. (4.326 to 4.356 mm) 0.1935 to 0.1953 in. (4.915 to 4.961 mm) 1/4” 1st O/S 1/4” 2nd O/S 0.2526 to 0.2544 in. (6.416 to 6.462 mm) 0.2684 to 0.2694 in. (6.817 to 6.843 mm) 5/16” 5/16” 1st O/S 0.2995 to 0.3005 in. (7.607 to 7.633 mm) 0.3155 to 0.3165 in. (8.014 to 8.039 mm) COLD WORK Point the split in the sleeve to the up or down position. This is 2 2 applicable to all cold work holes. UP DOWN MLG TRUNNION (REF) FITTING (REF) FITTING (REF) 1. Left side is shown, Right side is opposite. ### Page 50 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 49 of 67 Jul 17/2009 Revision C, Jun 06/2013 Final reaming of the MLG trunnion Figure 3 Left side is shown, right side is opposite. NOTE rsb601r57048_004.dg, lr, apr02/2008 A A VIEW LOOKING OUTBOARD SYMBOL FASTENERSIZE FINAL HOLE DIAMETER 3/16” 3/16” 1st O/S 0.1865 to 0.1890 in. (4.737 to 4.801 mm) 0.1995 to 0.2021 in. (5.067 to 5.133 mm) 1/4” 1st O/S 1/4” 2nd O/S 0.2620 to 0.2646 in. (6.655 to 6.721 mm) 0.2775 to 0.2802 in. (7.049 to 7.117 mm) 5/16” 5/16” 1st O/S 0.3090 to 0.3105 in. (7.849 to 7.887 mm) 0.3245 to 0.3261 in. (8.242 to 8.283 mm) MLG TRUNNION (REF) FITTING (REF) FITTING (REF) ### Page 51 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 50 of 67 Jul 17/2009 Revision C, Jun 06/2013 Door hinge fitting installation for 601R10031−1/−2/−11/−12 MLG trunnion Figure 4 (Sheet 1 of 2) rsb601r57048_005.dg, gb, 04/09/09 A A VIEW LOOKING OUTBOARD SYMBOL NAME PART NUMBER NUT Stud pin HST245AG −8−9−8 N/A ITEM 8 OVERSIZE PART NUMBER HST345AG−8−9−8 Stud pin HST245AG −8−7−8 N/AHST345AG−8−7−89 Hi−Lite HST10AG10 −9 B0203038 −5HST110AG10−911 Hi−Lite HST10AG10 −7 B0203038 −5HST110AG10−713 Hi−Lite HST10AG6 −11 B0203013 −3HST110AG6−1115 Hi−Lite HST10AG6 −9 B0203013 −3HST110AG6−917 B MLG TRUNNION (REF) 7069−7990, and 8000−8017 or NOTES 1. Left side is shown, Right side is opposite. 2. For aircraft 7003−7067, aircraft that have MLG trunnion P/N 601R10031−1,−2,−1 1, or −12 installed. ### Page 52 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 51 of 67 Jul 17/2009 Revision C, Jun 06/2013 Door hinge fitting installation for 601R10031−1/−2/−11/−12 MLG trunnion Figure 4 (Sheet 2 of 2) rsb601r57048_006.dg, lr, mar06/2008 MLG TRUNNION (REF) NOTE 1 1 5 5 4 4 3 3 2 6 2 6 LEGEND 1. Nut B0203038−4. 2. Washer AN960KD416L. 3. Door hinge fitting. 4. Serrated plate. 5. Laminated shim 601R31181−84. 6. Nut MS21042L4. 7. Radius washer. B 7 1 1. Left side is shown, Right side is opposite. 2. For aircraft 7003−7067, 7069−7990, and 8000−8017 or aircraft that have MLG trunnion P/N 601R10031−1,−2,−11 , or −12 installed. ### Page 53 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 52 of 67 Jul 17/2009 Revision C, Jun 06/2013 Door hinge fitting installation for 601R10068−1/−2/−5/−6 MLG trunnion Figure 5 (Sheet 1 of 2) rsb601r57048_007.dg, gb, 04/09/09 A A VIEW LOOKING OUTBOARD SYMBOL NAME PART NUMBER NUT Stud pin HST245AG −8−9−8 N/A ITEM 8 OVERSIZE PART NUMBER HST345AG−8−9−8 Stud pin HST245AG −8−8−8 N/AHST345AG−8−8−89 Stud pin HST245AG −8−10−8 N/AHST345AG−8−10−810 Hi−Lite HST10AG10 −9 B0203038 −5HST110AG10−911 Hi−Lite HST10AG10 −8 B0203038 −5HST110AG10−813 Hi−Lite HST10AG6 −11 B0203013 −3HST110AG6−1115 Hi−Lite HST10AG6 −10 B0203013 −3HST110AG6−1017 B MLG TRUNNION (REF) FITTING (REF) FITTING (REF) 2. For aircraft 8018−8106 or NOTES 1. Left side is shown, Right side is opposite. aircraft that have MLG trunnion P/N 601R10068−1, −2, −5, or −6 installed. ### Page 54 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 53 of 67 Jul 17/2009 Revision C, Jun 06/2013 Door hinge fitting installation for 601R10068−1/−2/−5/−6 MLG trunnion Figure 5 (Sheet 2 of 2) rsb601r57048_009.dg, gb, 04/09/09 MLG TRUNNION (REF) 2. For aircraft 8018−8106 or aircraft that have MLG trunnion NOTES 1 1 5 5 4 4 3 3 2 6 2 6 LEGEND 1. Nut B0203038−4. 2. Washer AN960KD416L. 3. Door hinge fitting. 4. Serrated plate. 5. Laminated shim 601R31181−84. 6. Nut MS21042L4. 7. Radius washer. B 7 1 1. Left side is shown, Right side is opposite. P/N 601R10068−1,−2,−5, or −6 installed. ### Page 55 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 54 of 67 Jul 17/2009 Revision C, Jun 06/2013 For Aircraft that have incorporated the initial issue or revision A of this service bulletin PART C − Identification of the Left and Right MLG Trunnion NOTE: If the identification of the MLG trunnion was done with Service Bulletin 601R−57−046 or 601R−57−047, it is not necessary to do this PART. G. Job Set−Up Reference Information REFERENCE DESIGNATION AMM 10−11−00−400−801 Installation of the Nose Landing Gear Lockpin AMM 10−11−00−400−802 Installation of the Main Landing Gear Lockpins SRM 51−25−16 Fluid-Resistant (FR) Polyurethane Topcoat SRM 51−26−00 Cleaning (1) Make sure that the lockpins are installed in the nose and the main landing gears (Refer to AMM 10−11−00−400−801 and 10−11−00−400−802). ### Page 56 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 55 of 67 Jul 17/2009 Revision C, Jun 06/2013 H. Procedure (1) Do the identification of the MLG trunnion as follows: (a) If an MLG trunnion was repaired or replaced, speak with a representative of the Customer Response Centre (CRC) at 514−855−8500 for an identification number. For Aircraft 7011 and 7012 (b) If Service Bulletins 601R−32−097, 601R−57−046 and 601R−57−048 have been incorporated, do as follows: 1 Clean the identification areas with solvent (refer to SRM 51−26−00). 2 Identify the left MLG trunnion as K601R10032−9. 3 Identify the right MLG trunnion as K601R10032−10. 4 Apply a layer of clear polyurethane topcoat on the identifications (refer to SRM 51−25−16). For Aircraft 7003−7010, 7013−7067 and 7069−7138 Pre-REO 601R−57−21−003 and Pre-SB 601R−32−054 (c) If Service Bulletins 601R−57−046, 601R−57−047 and 601R−57−048 have been incorporated, do as follows: 1 Clean the identification areas with solvent (refer to SRM 51−26−00). 2 Identify the left MLG trunnion as K601R10032−1. 3 Identify the right MLG trunnion as K601R10032−2. 4 Apply a layer of clear polyurethane topcoat on the identifications (refer to SRM 51−25−16). For Aircraft 7003−7010, 7013−7067 and 7069−7138 Post-REO 601R−57−21−003 or Post-SB 601R−32−054 (d) If Service Bulletins 601R−57−046, 601R−57−047 and 601R−57−048 have been incorporated, do as follows: ### Page 57 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 56 of 67 Jul 17/2009 Revision C, Jun 06/2013 1 Clean the identification areas with solvent (refer to SRM 51−26−00). 2 Identify the left MLG trunnion as K601R10032−3. 3 Identify the right MLG trunnion as K601R10032−4. 4 Apply a layer of clear polyurethane topcoat on the identifications (refer to SRM 51−25−16). For Aircraft 7139−7990 and 8000−8017 (e) If Service Bulletins 601R−57−046, 601R−57−047 and 601R−57−048 have been incorporated, do as follows: 1 Clean the identification areas with solvent (refer to SRM 51−26−00). 2 Identify the left MLG trunnion as K601R10032−3. 3 Identify the right MLG trunnion as K601R10032−4. 4 Apply a layer of clear polyurethane topcoat on the identifications (refer to SRM 51−25−16). For Aircraft 8018−8079 (f) If Service Bulletins 601R−57−046 and 601R−57−048 have been incorporated, do as follows: 1 Clean the identification areas with solvent (refer to SRM 51−26−00). 2 Identify the left MLG trunnion as K601R10032−5. 3 Identify the right MLG trunnion as K601R10032−6. 4 Apply a layer of clear polyurethane topcoat on the identifications (refer to SRM 51−25−16). For Aircraft 8080−8106 (g) If Service Bulletins 601R−57−046 and 601R−57−048 have been incorporated, do as follows: 1 Clean the identification areas with solvent (refer to SRM 51−26−00). 2 Identify the left MLG trunnion as K601R10032−7. 3 Identify the right MLG trunnion as K601R10032−8. 4 Apply a layer of clear polyurethane topcoat on the identifications (refer to SRM 51−25−16). ### Page 58 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 57 of 67 Jul 17/2009 Revision C, Jun 06/2013 I. Job Close−Out For all Aircraft (1) Remove all tools, equipment, and unwanted materials from the work area. (2) When PART C of this service bulletin is completed, make this entry in the applicable logbook(s): /quoteblleftService Bulletin 601R−57−048, Revision C, Wings − Center Wing Primary Structure − Cold Work of Holes on the web of the Main Landing Gear (MLG) Trunnion, PART C, incorporated." ### Page 59 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 58 of 67 Jul 17/2009 Revision C, Jun 06/2013 3. MATERIAL INFORMATION A. Kit Information Kit Content: KIT 601R57−048K1 PART NUMBER QUANTITY/C0001 NAME ALTERNATEPARTS 601R31181−84 2 Shim laminated AN960KD416L B0203013−3 B0203038−4 B0203038−5 CBS−10−0−N−16F CBS−4−4−N−16F CBS−8−1−N−16S HST10AG10−7 HST10AG10−9 HST10AG6−11 HST10AG6−9 HST245AG−8−7−8 7 3 7 3 4 4 12 2 2 2 2 3 Washer Nut Nut 1st and 2 nd O/S Nut 1st & 2nd O/S Flared sleeve Flared sleeve Straight sleeve Hi−lites 5/16 Hi−lites 5/16 Hi−lites 3/16 Hi−lites 3/16 Stud pin 1/4 1st O/S HST245AG−8−9−8 5 Stud pin 1/4 1st O/S MS21042L4 7 Nut /C0001 The kit can contain more hardware and/or material than necessary. KIT 601R57−048K2 PART NUMBER QUANTITY/C0001 NAME ALTERNATEPARTS CBS−10−1−N−16F 8 Flared sleeve ### Page 60 SERVICE BULLETIN 601R−57−048 SB 601R−57−048 Page 59 of 67 Jul 17/2009 Revision C, Jun 06/2013 PART NUMBER ALTERNATE PARTSNAMEQUANTITY/C0001 CBS−6−1−N−16F CBS−8−2−N−16S 8 24 Flared sleeve Straight sleeve HST110AG10−7 3 Hi−lites 5/16 1st O/S HST110AG10−9 3 Hi−lites 5/16 1st O/S HST110AG6−11 3 Hi−lites 3/16 1st O/S HST110AG6−9 3 Hi−lites 3/16 1st O/S HST345AG−8−7−8 5 Stud pin 1/4 2nd O/S HST345AG−8−9−8 9 Stud pin 1/4 2nd O/S /C0001 The kit can contain more hardware and/or material than necessary. KIT 601R57−048K3 PART NUMBER QUANTITY/C0001 NAME ALTERNATEPARTS 601R31181−84 2 Shim laminated AN960KD416L 7 Washer B0203013−3 3 Nut B0203038−4 7 Nut 1st and 2 nd O/S B0203038−5 3 Nut 1st & 2nd O/S CBS−10−0−N−16F 4 Flared sleeve CBS−4−4−N−16F 4 Flared sleeve CBS−8−1−N−16S 12 Straight sleeve HST10AG10−8 2 Hi−lites 5/16 HST10AG10−9 2 Hi−lites 5/16 HST10AG6−10 2 Hi−lites 3/16 HST10AG6−11 2 Hi−lites 3/16 The text continues at https://openairdocs.org/service-documents/bombardier/601r-57-048/file/865db26f0f9a.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.