# Bombardier Service Bulletin 601R-32-112 Copy: No revision named ("SB-601R-32-112-Rev-NC"), 25 pages: PDF https://openairdocs.org/files/sha256/d2/8f/d28f0337f0cf7beb28084eca2db1612f0376ea8631c4b84ebbe6bd3e7df79750; text https://openairdocs.org/service-documents/bombardier/601r-32-112/file/d28f0337f0cf.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2020-0691; AD 2021-01-01 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-32-112 - Page: https://openairdocs.org/service-documents/bombardier/601r-32-112 ## ADs that cite it (1) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2021-01-01](https://openairdocs.org/ad/2021-01-01.md), effective Mar 30, 2021: No revision named Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/601r-32-112/proposed.md). ## Text (25 pages) Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2020-0691; AD 2021-01-01 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−32−112 Page 1 of 25 Nov 11/2019 SERVICE BULLETIN Technical Publications THIS SERVICE BULLETIN IS SENT TO EACH OPERATOR. IF THE OPERATOR HAS LEASED AIRCRAFT , TRANSFERRED SPARES IN THE LAST SIX MONTHS, SEND THIS SERVICE BULLETIN TO THE NEW OWNER, UNLESS CONFIRMATION WAS RECEIVED THAT BOMBARDIER HAS INCLUDED THE NEW OPERATOR ON THE DISTRIBUTION LIST . SEND THIS SERVICE BULLETIN TO THE LESSEE. IF THE OPERATOR HAS SOLD AIRCRAFT OR ATA SYSTEM: 32−00 NUMBER: 601R−32−112 SUBJECT: Landing Gear − General − Check of the Accumulated Flight Cycles of the Main and Nose Landing Gear Parts Repaired by Bombardier Repair Engineering Orders (REO) Affected by Specific Airworthiness Limitation (SAL) 1. PLANNING INFORMATION A. Effectivity (1) Aircraft Affected: Service Bulletin: CL−600−2B19 aircraft with the components that follow installed: Nose Landing Gear REO NUMBER: 601R−32−21−489, 601R−32−21−661 Part Number: 16114−( ) PART SERIAL NUMBERS: DCL512, SAM1518, ### Page 2 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 2 of 25 Nov 11/2019 REO NUMBER: 601R−32−21−225, 601R−32−21−227, 601R−32−21−526, 601R−32−21−557, 601R−32−21−635, 601R−32−21−663, 601R−32−21−685, 601R−32−21−689, 601R−32−21−691, 601R−32−21−692, 601R−32−21−693, 601R−32−21−1002, 601R−32−21−1022 Part Number: 16122−( ) PART SERIAL NUMBERS: SAM−3070, SAM3551, WHM1027, WHM1058, WHM1107, WHM1111, WHM1121, WHM1269, WHM−1365, WHM1414, WHM1434, WHM−1479, WHM1509 REO NUMBER: 601R−32−21−414, 601R−32−21−536, 601R−32−21−555, 601R−32−21−562, 601R−32−21−570, Part Number: 16124−( ) PART SERIAL NUMBERS: DCL210, DCL398 PLT0458, PLT0626, PLT0739 REO NUMBER: 601R−32−21−535 Part Number: 16404−( ) PART SERIAL NUMBERS: DCL153 ### Page 3 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 3 of 25 Nov 11/2019 INSTALLED AT THE TIME OF DELIVERY ON AIRCRAFT SERIAL NUMBERS: 7003 to 8999 SPARES: Examine all spare parts. If a part with a serial number listed in the TABLE 1 in the Procedure section is found, it is necessary to incorporate latest REO revision associated with the maintenance program. Main Landing Gear REO NUMBER: 601R−32−11−183, 601R−32−11−367, 601R−32−11−627, 601R−32−11−630, 601R−32−11−712, 601R−32−11−783, 601R−32−11−786, 601R−32−11−918, 601R−32−11−956, 601R−32−11−1017, 601R−32−11−1084, 601R−32−11−1153, 601R−32−11−1250 Part Number: 17040−( ) PART SERIAL NUMBERS: DCL026, DCL356, DCL688, DCL690, DCL753, DCL975, DCL1150, DCL1232, DCL1234, DCL1277, DCL1279, DCL1384, DCL1592 REO NUMBER: 601R−32−11−1224, 601R−32−11−1251,601R−32−11−1255, Part Number: 17041−( ) PART SERIAL NUMBERS: DCL1528,DCL1602, DCL1640 ### Page 4 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 4 of 25 Nov 11/2019 REO NUMBER: 601R−32−11−086, 601R−32−11−089, 601R−32−11−634, 601R−32−11−835, 601R−32−11−1187, 601R−32−11−1673 Part Number: 17050−( ) PART SERIAL NUMBERS: DCL064, DCL066, DCL488, EXC1069, EXC1646, EXC1678 REO NUMBER: 601R−32−11−913, 601R−32−11−921, 601R−32−11−951, 601R−32−11−955, 601R−32−11−958, 601R−32−11−1041, 601R−32−11−1154, 601R−32−11−1206, 601R−32−11−1219, 601R−32−11−1220, 601R−32−11−1286, 601R−32−11−1302, 601R−32−11−1650, 601R−32−32−056, 601R−32−32−076 Part Number: 17076−( ) PART SERIAL NUMBERS: 07MDT3307, DCL654, DCL746, DCL752, DCL979, DCL1013, DCL1035, DCL1233, DCL1245, DCL1564, DCL1738, DCL1852, DCL2946, DCL2977 INSTALLED AT THE TIME OF DELIVERY ON AIRCRAFT SERIAL NUMBERS: 7003 to 8999 SPARES: Examine all spare parts. If a part with a serial number listed in the TABLE 2 in the Procedure section is found, it is necessary to incorporate latest REO revision associated with the maintenance program. ### Page 5 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 5 of 25 Nov 11/2019 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 service bulletin, examine all Supplemental Type Certificates (STCs), and Supplemental Type Approvals (STAs) or equivalent action changes to make sure you can complete this service bulletin. B. Reason (1) Condition Some components of the Nose Landing Gears (NLG) and Main Landing Gears (MLG) have been repaired by Bombardier Repair Engineering Orders (REO). A limited number of these Bombardier REO have a Specific Airworthiness Limitation (SAL). These parts repaired by REO with an SAL have a structural component life limit that is lower than the life limit written in the Maintenance Requirements Manual (MRM) Part 2. To comply with this lower life limit, a new revision of these REOs with a Structural Deviation Inspection Requirement (SDIR) sheet was released. (2) Evidence There is evidence that some of the components of the NLG and/or the MLG repaired with REOs that have an SAL, do not have the related SDIR attached to the REO. The SDIR was not incorporated in the SDIR aircraft document and the revised life limit of the repaired components of the NLG and/or the MLG (given by the SDIR) compared with the life limit given in the MRM Part 2 was not taken into account . ### Page 6 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 6 of 25 Nov 11/2019 (3) Objective/Benefit This service bulletin gives the procedure to do an inspection of the aircraft and spares inventory records, to find out which components must have their life limit revised in accordance with the REO SDIR. A specific repair with a new life limit is released within the REO as an SDIR and is to be put into the aircraft SDIR document. C. Description This service bulletin is divided into four parts: PART A, PART B, PART C and PART D. PART A − Inspection of the Part Numbers, Serial Numbers and accumulated flight cycles of the repaired NLG and/or MLG part(s). Identify if the affected NLG and/or MLG is/are installed on aircraft or are spares parts. Compare the number of accumulated flight cycles of these repaired parts with the one given by the Structural Deviation Inspection Requirement (SDIR) of the REO. PART B − Implementation of the SDIR life limit of the repaired NLG and/or MLG part(s) in the Aircraft Maintenance Program. The Aircraft Maintenance Program is updated with the SDIR life limit for the affected part(s). PART C − Replacement of the repaired NLG part(s) The repaired NLG part is removed, discarded and replaced. PART D − Replacement of the repaired MLG part(s) The repaired MLG part is removed, discarded and replaced. D. Compliance Recommended service bulletin. Bombardier recommends PART A of this service bulletin be done within six months from the release date of this service bulletin, unless otherwise directed by the airworthiness authority of the operator. If the component accumulated flight cycles is less that the REO SDIR life limit minus 2000 flight cycles, Bombardier recommends to do PART B of this service bulletin within 12 months from the completion date of PART A unless otherwise directed by the airworthiness authority of the operator. ### Page 7 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 7 of 25 Nov 11/2019 If the component accumulated flight cycles is more than or equal to the REO SDIR life limit minus 2000 flight cycles, Bombardier recommends to do PART C and/or PART D of this service bulletin within 12 months or 2000 flight cycles from the completion date of PART A, whichever comes first, unless otherwise directed by the airworthiness authority of the operator. NOTE: If it is not possible to complete all the instructions in this service bulletin because of the configuration of the aircraft, speak with a representative of Bombardier in the CRC at 1−844−272−2720 (1−844−CRC−CRC0) or 1−514−855−8500 or e-mail at thd.crj@aero.bombardier.com for analysis and to get an approved disposition to complete this service bulletin. This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage Tolerance Inspections (DTIs). 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 The man-hours given below are estimates for direct labor done by an experienced crew on an aircraft prepared for maintenance. These estimates do not include the time necessary for: −Administrative functions such as planning, liaising, familiarization, and report writing. −Non-productive elapsed time such as rest time, having meals, and crew shift changes. −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 as directly related to the accomplishment of this procedure. NOTE: For on-site labor assistance, please speak with a Fleet Services representative for an estimate. Call the Fleet Services Team through the CRC at 1−844−272−2720 (1−844−CRC−CRC0) or 1−514−855−8500 or e-mail at thd.crj@aero.bombardier.com. ### Page 8 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 8 of 25 Nov 11/2019 FOR PART A It will take an estimated 1.0 man-hours to complete this service bulletin. The man-hours are divided in the table that follows (elapsed cure time is not included in the man-hour summary given above): TASK MAN-HOURS (1) Job Set-Up 0.0 (2) Procedure 1.0 (3) Test 0.0 (4) Job Close-Out 0.0 FOR PART B It will take an estimated 0.5 man-hours to complete this service bulletin. The man-hours are divided in the table that follows (elapsed cure time is not included in the man-hour summary given above): TASK MAN-HOURS (1) Job Set-Up 0.0 (2) Procedure 0.5 (3) Test 0.0 (4) Job Close-Out 0.0 ### Page 9 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 9 of 25 Nov 11/2019 FOR PART C It will take an estimated 2.0 man-hours to complete this service bulletin. The man-hours are divided in the table that follows (elapsed cure time is not included in the man-hour summary given above): TASK MAN-HOURS (1) Job Set-Up 1.5 (2) Procedure See Note (3) Test See Note (4) Job Close-Out 0.5 NOTE: Because of the different possibilities (replacement of the main fitting (P/N 16114), piston axle (P/N 16122), axle assembly (P/N 16124), drag brace or apex pin (P/N 16404)) only the job Set−Up and Job Close Out given in PART C of this Service Bulletin are covered in the table above. FOR PART D It will take an estimated 2.0 man-hours to complete this service bulletin. The man-hours are divided in the table that follows (elapsed cure time is not included in the man-hour summary given above): TASK MAN-HOURS (1) Job Set-Up 1.5 (2) Procedure See Note (3) Test See Note (4) Job Close-Out 0.5 NOTE: Because of the different possibilities (replacement of the pintle pin (P/N 17040), pivot pin (P/N 17041), MLG axle (P/N 17050), side stay pin (P/N 17076)) only the job Set−Up and Job Close Out given in PART D of this Service Bulletin are covered in the table above. ### Page 10 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 10 of 25 Nov 11/2019 G. Material − Price and Availability There are no kits for this service bulletin. H. Tooling − Price and Availability There are no tool kits for this service bulletin. Refer to paragraph 3.C. for a list of special tools and equipment for this service bulletin. I. Weight and Balance Not changed. J. Electrical Load Data Not changed. K. References Refer to the SB Introduction document for definition or explanation of service bulletin content. Repair Engineering Order (REO): 601R−32−11−XXX, refer to Table 2 for all REO numbers. 601R−32−21−XXX, refer to Table 1 for all REO numbers. 601R−32−32−XXX, refer to Table 2 for all REO numbers. For Bombardier reference only: Restriction and/or Special Instruction (RSI) C−A308, Revision E. For Bombardier reference only: PCA 07305. L. Other Publications Affected Maintenance Requirements Manual (MRM) M. Relationship Chart Not applicable. ### Page 11 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 11 of 25 Nov 11/2019 2. ACCOMPLISHMENT INSTRUCTIONS PART A − Inspection of the Part Numbers, Serial Numbers and accumulated flight cycles of the repaired NLG and/or MLG part(s). A. Job Set-Up Not Applicable B. Procedure For all aircraft (1) If it is not possible to complete all the instructions in this service bulletin because of the configuration of the aircraft, speak with a representative of Bombardier in the CRC at 1−844−272−2720 (1−844−CRC−CRC0) or 1−514−855−8500 or e-mail at thd.crj@aero.bombardier.com for analysis and to get an approved disposition to complete this service bulletin. Nose Landing Gear Component Part Numbers and Serial Numbers (2) Do an inspection of the aircraft and spares inventory records, to determine if a component that is listed in the table below is installed on the aircraft nose landing gear or is in the spares inventory. TABLE 1 REO 601R−32−21−XXX PART NUMBER NAME SERIAL NUMBER ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−489 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16114−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ Main Fitting ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ DCL512 ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−661 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16114−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ ÁÁÁÁÁÁ Main Fitting ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ SAM1518 ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−557 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16122−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ Piston Axle ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ WHM1121 601R−32−21−225 16122−( ) Piston Axle SAM−3070 ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−227 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16122−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ Piston Axle ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ WHM1027 ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−526 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16122−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ Piston Axle ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ WHM1107 ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−635 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16122−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ ÁÁÁÁÁÁ Piston Axle ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ WHM1058 ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−663 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16122−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ Piston Axle ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ WHM1269 ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−685 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16122−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ ÁÁÁÁÁÁ Piston Axle ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ WHM1111 ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−689 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16122−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ Piston Axle ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ WHM1509 ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−691 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16122−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ Piston Axle ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ WHM1414 ### Page 12 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 12 of 25 Nov 11/2019 TABLE 1 continue ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−692 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16122−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ ÁÁÁÁÁÁ Piston Axle ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ SAM3551 ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−693 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16122−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ Piston Axle ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ WHM1434 ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−1002 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16122−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ ÁÁÁÁÁÁ Piston Axle ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ WHM−1365 ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−1022 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16122−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ Piston Axle ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ WHM−1479 ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−414 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16124−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ Axle ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ PLT0458 ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−536 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16124−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ ÁÁÁÁÁÁ Axle ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ DCL398 ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−555 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16124−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ Axle ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ DCL210 ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−562 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16124−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ ÁÁÁÁÁÁ Axle ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ PLT0739 ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−570 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16124−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ Axle ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ PLT0626 ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁÁ 601R−32−21−535 ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ 16404−( ) ÁÁÁÁÁÁ ÁÁÁÁÁÁ ÁÁÁÁÁÁ Drag Brace Apex Pin ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ ÁÁÁÁÁÁÁÁ DCL153 (3) If a part number with the associated serial number listed in the table above is installed on the aircraft, or is in the spares inventory, do the steps that follow: (a) Speak with a representative of Bombardier in the CRC at 1−844−272−2720 (1−844−CRC−CRC0) or 1−514−855−8500 or e-mail at thd.crj@aero.bombardier.com to get the latest revision of the applicable REO. (b) Get the accumulated flight cycles of the part installed on your aircraft or in the spares inventory. (c) Get the specific life limit given in the SDIR which is attached to the latest revision of the applicable REO. (d) Compare the accumulated flight cycles of the part with the specified life limit given in the SDIR and do the applicable steps that follow: 1 If the component accumulated flight cycles is less that the REO SDIR life limit minus 2000 flight cycles, do PART B of this service bulletin. NOTE: Refer to the compliance section of this service bulletin to know when you need to do PART B of this service bulletin. ### Page 13 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 13 of 25 Nov 11/2019 2 If the component accumulated flight cycles is more than or equal to the REO SDIR life limit minus 2000 flight cycles, do PART C of this service bulletin. NOTE: Refer to the compliance section of this service bulletin to know when you need to do PART C of this service bulletin. (4) If no NLG part number with the associated serial number listed in the table 1 above are installed on the aircraft, or are in the spares inventory, then do the steps that follow: (a) No further action is required for the NLG parts. (b) Do the inspection of the main landing gear component part numbers and serial numbers as per the next steps. Main Landing Gear Component Part Numbers and Serial Numbers (5) Do an inspection of the aircraft and spares inventory records, to determine if a component that is listed in the table below is installed on the aircraft main landing gear or is in the spares inventory. TABLE 2 REO 601R−32−11−XXX PART NUMBER NAME SERIAL NUMBER 601R−32−11−1250 17040−( ) Pintle Pin DCL1592 601R−32−11−183 17040−( ) Pintle Pin DCL026 601R−32−11−367 17040−( ) Pintle Pin DCL753 601R−32−11−627 17040−( ) Pintle Pin DCL1234 601R−32−11−630 17040−( ) Pintle Pin DCL1232 601R−32−11−712 17040−( ) Pintle Pin DCL690 601R−32−11−783 17040−( ) Pintle Pin DCL356 601R−32−11−786 17040−( ) Pintle Pin DCL1277 601R−32−11−918 17040−( ) Pintle Pin DCL688 601R−32−11−956 17040−( ) Pintle Pin DCL1150 601R−32−11−1017 17040−( ) Pintle Pin DCL975 ### Page 14 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 14 of 25 Nov 11/2019 TABLE 2 continue 601R−32−11−1084 17040−( ) Pintle Pin DCL1384 601R−32−11−1153 17040−( ) Pintle Pin DCL1279 601R−32−11−1224 17041−( ) Pivot Pin DCL1602 601R−32−11−1251 17041−( ) Pivot Pin DCL1528 601R−32−11−1255 17041−( ) Pivot Pin DCL1640 601R−32−11−634 17050−( ) Axle EXC1069 601R−32−11−086 17050−( ) Axle DCL064 601R−32−11−089 17050−( ) Axle DCL066 601R−32−11−835 17050−( ) Axle DCL488 601R−32−11−1187 17050−( ) Axle EXC1678 601R−32−11−1673 17050−( ) Axle EXC1646 601R−32−11−913 17076−( ) Side Stay Pin DCL1013 601R−32−11−921 17076−( ) Side Stay Pin DCL654 601R−32−11−951 17076−( ) Side Stay Pin DCL979 601R−32−11−955 17076−( ) Side Stay Pin DCL2977 601R−32−11−958 17076−( ) Side Stay Pin DCL979 601R−32−11−1041 17076−( ) Side Stay Pin DCL1035 601R−32−11−1154 17076−( ) Side Stay Pin DCL1245 601R−32−11−1206 17076−( ) Side Stay Pin DCL1233 601R−32−11−1219 17076−( ) Side Stay Pin DCL746 601R−32−11−1220 17076−( ) Side Stay Pin 07MDT3307 601R−32−11−1286 17076−( ) Side Stay Pin DCL1564 601R−32−11−1302 17076−( ) Side Stay Pin DCL1738 601R−32−11−1650 17076−( ) Side Stay Pin DCL2946 601R−32−32−056 17076−( ) Side Stay Pin DCL752 601R−32−32−076 17076−( ) Side Stay Pin DCL1852 ### Page 15 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 15 of 25 Nov 11/2019 (6) If a part number with the associated serial number listed in the table above is installed on the aircraft, or is in the spares inventory, do the steps that follow: (a) Speak with a representative of Bombardier in the CRC at 1−844−272−2720 (1−844−CRC−CRC0) or 1−514−855−8500 or e-mail at thd.crj@aero.bombardier.com to get the latest revision of the applicable REO. (b) Get the accumulated flight cycles of the part installed on your aircraft or in the spares inventory. (c) Get the specific life limit given in the SDIR which is attached to the latest revision of the applicable REO. (d) Compare the accumulated flight cycles of the part with the specified life limit given in the SDIR and do the applicable steps that follow: 1 If the component accumulated flight cycles is less that the REO SDIR life limit minus 2000 flight cycles, do PART B of this service bulletin. NOTE: Refer to the compliance section of this service bulletin to know when you need to do PART B of this service bulletin. 2 If the component accumulated flight cycles is more than or equal to the REO SDIR life limit minus 2000 flight cycles, do PART D of this service bulletin. NOTE: Refer to the compliance section of this service bulletin to know when you need to do PART D of this service bulletin. C. Job Close-Out (1) When this service bulletin is completed, make this entry in the applicable logbook: Service Bulletin 601R−32−112, Landing Gear − General − Check of the accumulated flight cycles of the main and nose landing gear parts repaired by Bombardier Repair Engineering Order (REO) affected by Specific Airworthiness Limitation (SAL), PART A, incorporated. NOTE: From the completion date of PART A, if applicable, the incorporation of PART B of this service bulletin must be completed within 12 months. NOTE: From the completion date of PART A, if applicable, the incorporation of PART C and/or PART D of this service bulletin must be completed within 12 months or 2000 flight cycles, which ever comes first. ### Page 16 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 16 of 25 Nov 11/2019 PART B − Implementation of the SDIR life limit of the repaired NLG and/or MLG part(s) in the Aircraft Maintenance Program. D. Job Set-Up Not Applicable E. Procedure (1) If it is not possible to complete all the instructions in this service bulletin because of the configuration of the aircraft, speak with a representative of Bombardier in the CRC at 1−844−272−2720 (1−844−CRC−CRC0) or 1−514−855−8500 or e-mail at thd.crj@aero.bombardier.com for analysis and to get an approved disposition to complete this service bulletin. (2) Make sure you have the latest copy of the REO applicable to the component listed in Table 1 and/or Table 2 of PART A that is installed on the aircraft or in your spares inventory. (3) Make sure that the SDIR sheet is attached to the latest revision of the applicable REO. (4) Incorporate the revised life limit of the part in the aircraft maintenance program per the latest revision of the applicable REO to agree with the SDIR. (5) If damage is found, speak with a CRC representative at 1−844−272−2720 (1−844−CRC−CRC0) or 1−514−855−8500 or send an e-mail at thd.crj@aero.bombardier.com for a disposition. F . Job Close-Out (1) When this service bulletin is completed, make this entry in the applicable logbook: Service Bulletin 601R−32−112, Landing Gear − General − Check of the accumulated flight cycles of the main and nose landing gear parts repaired by Bombardier Repair Engineering Order (REO) affected by Specific Airworthiness Limitation (SAL), PART B, incorporated. ### Page 17 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 17 of 25 Nov 11/2019 PART C − Replacement of the repaired NLG part(s) Reference Information REFERENCE DESIGNATION AMM 07−11−01−582−801 Put the Aircraft on Jacks AMM 07−11−01−582−804 Removal of the Aircraft from Jacks AMM 10−11−00−400−801 Installation of the Nose Landing Gear Lockpin AMM 10−11−00−400−802 Installation of the Main Landing Gear Lockpins AMM 12−00−06−863−804 Release Hydraulic Pressure − System No. 3 AMM 29−00−00−910−801 Hydraulic Safety Precautions AMM 32−21−01−000−801 Removal of the NLG Shock Strut AMM 32−21−01−400−801 Installation of the NLG Shock Strut AMM 32−21−05−000−801 Removal of the NLG Drag Brace AMM 32−21−05−400−801 Installation of the NLG Drag Brace AMM 32−21−15−000−801 Removal of the NLG Axle Assembly AMM 32−21−15−400−801 Installation of the NLG Axle Assembly AMM 32−21−30−000−801 Removal of the NLG Sliding Member AMM 32−21−30−400−801 Installation of the NLG Sliding Member AMM 32−22−01−980−801 Open and Isolate the Nose−Landing−Gear Forward Doors CMM 32−20−04 COMPONENT MAINTENANCE MANUAL NOSE LANDING GEAR ASSEMBLY ### Page 18 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 18 of 25 Nov 11/2019 G. Job Set-Up NOTE: The steps in the Job Set-Up section of this service bulletin are recommended steps. The steps give a recommendation to get access to the work area. This recommendation is to give a safe work area and to minimize possible damage to surrounding aircraft parts. Alternative steps can be used at the operator discretion. WARNING: MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT . THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT . (1) Install the safety lockpins at the nose landing gear and at the main landing gear (refer to AMM 10−11−00−400−801 and 10−11−00−400−802). WARNING: OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT . (2) Obey all the hydraulic safety precautions (refer to AMM 29−00−00−910−801). WARNING: IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: − ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE"OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 − RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT . (3) Open and isolate the NLG forward doors (refer to AMM TASK 32−22−01−980−801). (4) Release the hydraulic pressure from system No. 3 (refer to AMM 12−00−06−863−804). (5) Put the aircraft on jacks (refer to AMM 07−11−01−582−801). ### Page 19 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 19 of 25 Nov 11/2019 H. Procedure NOTE: It is acceptable to replace components on wing with AMM tasks or, off wing, by an approved shop repair facility. (1) If it is not possible to complete all the instructions in this service bulletin because of the configuration of the aircraft, speak with a representative of Bombardier in the CRC at 1−844−272−2720 (1−844−CRC−CRC0) or 1−514−855−8500 or e-mail at thd.crj@aero.bombardier.com for analysis and to get an approved disposition to complete this service bulletin. (2) If applicable replace the repaired main fitting (P/N 16114) as follows: (a) Remove the NLG Shock Strut (refer to AMM 32−21−01−000−801). (b) Send the NLG shock strut to an approved maintenance repair and overhaul facility to get the repaired main fitting replaced (refer to CMM 32−20−04). (c) Install a new or serviceable NLG Shock Strut (refer to AMM 32−21−01−400−801). (3) If applicable replace the repaired piston axle (P/N 16122) as follows: (a) If you have a new or serviceable piston axle do that follows: 1 Remove and discard the repaired piston axle (refer to AMM 32−21−30−000−801). 2 Install a new or serviceable piston axle (refer to AMM 32−21−30−400−801). (b) If you do not have a new or serviceable piston axle do that follows: 1 Remove the NLG Shock Strut (refer to AMM 32−21−01−000−801). 2 Send the NLG shock strut to an approved maintenance repair and overhaul facility to get the repaired piston axle replaced (refer to CMM 32−20−04). ### Page 20 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 20 of 25 Nov 11/2019 (4) If applicable replace the repaired axle assembly (P/N 16124) as follows: (a) If you have a new or serviceable axle assembly do that follows: 1 Remove and discard the repaired NLG Axle Assembly (refer to AMM 32−21−15−000−801). 2 Install a new or serviceable NLG Axle Assembly (refer to AMM 32−21−15−400−801). (b) If you do not have a new or serviceable axle assembly, do the steps that follow: 1 Remove the NLG Shock Strut (refer to AMM 32−21−01−000−801). 2 If removed, install a new or serviceable NLG Shock Strut (refer to AMM 32−21−01−400−801). or 3 Remove the piston axle (refer to AMM 32−21−30−000−801). 4 If removed, install a new or serviceable piston axle (refer to AMM 32−21−30−400−801). (5) If applicable replace the repaired drag brace apex pin (P/N 16404) as follows: (a) If you have a new or serviceable drag brace apex pin do that follows: 1 Remove and discard the repaired drag brace apex pin (refer to AMM 32−21−05−000−801). 2 Install a new or serviceable drag brace apex pin (refer to AMM 32−21−05−400−801). ### Page 21 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 21 of 25 Nov 11/2019 (b) If you do not have a new or serviceable drag brace apex pin do that follows: 1 Remove the NLG Shock Strut (refer to AMM 32−21−01−000−801). 2 Send the NLG shock strut to an approved maintenance repair and overhaul facility to get the repaired axle assembly replaced (refer to CMM 32−20−04). 3 Install a new or serviceable NLG Shock Strut (refer to AMM 32−21−01−400−801). I. Job Close-Out NOTE: The steps in the Job Close-Out section of this service bulletin, except for the return-to-service tests, are recommended steps. The steps give a recommendation to install components removed during the Job Set-Up. This recommendation is to make sure that the aircraft is safe and ready to return to service. Alternative steps can be used at the operator discretion. (1) Remove all tools, equipment, and unwanted materials from the work area. (2) Lower the aircraft and remove the jacks (refer to AMM 07−11−01−582−804). (3) When PART C of this service bulletin is completed, make this entry in the applicable logbooks: /quoteblleftService Bulletin 601R−32−112, Landing Gear − General − Check of the accumulated flight cycles of the main and nose landing gear parts repaired by Bombardier repair engineering orders (REO) affected by Specific Airworthiness Limitation (SAL), PART C, incorporated." ### Page 22 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 22 of 25 Nov 11/2019 PART D − Replacement of the repaired MLG part(s) Reference Information REFERENCE DESIGNATION AMM 07−11−01−582−801 Put the Aircraft on Jacks AMM 07−11−01−582−804 Remove the Aircraft from Jacks 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 32−11−00−000−801 Removal of the MLG AMM 32−11−00−400−801 Installation of the MLG AMM 32−11−10−000−801 Removal of the Trailing Arm AMM 32−11−10−400−801 Installation of the Trailing Arm AMM 32−11−15−000−801 Removal of the MLG Axle AMM 32−11−15−400−801 Installation of the MLG Axle AMM 32−32−01−000−802 Removal of MLG Side Stay Pin AMM 32−32−01−400−802 Installation of MLG Side Stay Pin ### Page 23 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 23 of 25 Nov 11/2019 J. Job Set-Up NOTE: The steps in the Job Set-Up section of this service bulletin are recommended steps. The steps give a recommendation to get access to the work area. This recommendation is to give a safe work area and to minimize possible damage to surrounding aircraft parts. Alternative steps can be used at the operator discretion. (1) Electrically extend the flaps to 45 degrees to get access to the work area (refer to AMM 27−54−00−866−801). WARNING: OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT . (2) Obey all the hydraulic safety precautions (refer to AMM 29−00−00−910−801). (3) Put the aircraft on jacks (refer to AMM 07−11−01−582−801). K. Procedure NOTE: It is acceptable to replace components on wing with AMM tasks or, off wing, by an approved shop repair facility. (1) If it is not possible to complete all the instructions in this service bulletin because of the configuration of the aircraft, speak with a representative of Bombardier in the CRC at 1−844−272−2720 (1−844−CRC−CRC0) or 1−514−855−8500 or e-mail at thd.crj@aero.bombardier.com for analysis and to get an approved disposition to complete this service bulletin. (2) If applicable replace the repaired pintle pin (P/N 17040) as follows: (a) Remove and discard the pintle pin (refer to AMM 32−11−00−000−801). (b) Install a new or serviceable pintle pin (refer to AMM 32−11−00−400−801). (3) If applicable replace the repaired pivot pin (P/N 17041) as follows: (a) Remove the Trailing Arm (refer to AMM 32−11−10−000−801). 1 Discard the pivot pin (P/N 17041). ### Page 24 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 24 of 25 Nov 11/2019 (b) Install the Trailing Arm with a new or serviceable pivot pin (refer to AMM 32−11−10−400−801). (4) If applicable replace the repaired MLG Axle (P/N 17050) as follows: (a) Remove and discard the MLG Axle (refer to AMM 32−11−15−000−801). (b) Install a new or serviceable the MLG Axle (refer to AMM 32−11−15−400−801). (5) If applicable replace the repaired side stay pin (P/N 17076) as follows: (a) Remove and discard the side stay pin (refer to AMM 32−32−01−000−802). (b) Install a new or serviceable the side stay pin (refer to AMM 32−32−01−400−802). L. Job Close-Out NOTE: The steps in the Job Close-Out section of this service bulletin, except for the return-to-service tests, are recommended steps. The steps give a recommendation to install components removed during the Job Set-Up. This recommendation is to make sure that the aircraft is safe and ready to return to service. Alternative steps can be used at the operator discretion. (1) Electrically retract the flaps (refer to AMM 27−54−00−866−802). (2) Lower the aircraft and remove the jacks (refer to AMM 07−11−01−582−804). (3) Remove all tools, equipment, and unwanted materials from the work area. (4) When PART D of this service bulletin is completed, make this entry in the applicable logbooks: /quoteblleftService Bulletin 601R−32−112, Landing Gear − General − Check of the accumulated flight cycles of the main and nose landing gear parts repaired by Bombardier repair engineering orders (REO) affected by Specific Airworthiness Limitation (SAL), PART D, incorporated." ### Page 25 SERVICE BULLETIN 601R−32−112 SB 601R−32−112 Page 25 of 25 Nov 11/2019 3. MATERIAL INFORMATION A. Kit Information None. NOTE: For permitted alternative to superseded parts, refer to the Parts Supersession Cross References Lists at www.iflybombardier.com under Resources − Engineering Documents. NOTE: Some parts listed in the kit content of this service bulletin are supplied in a temporary condition of supply configuration. These parts are identified with a −SB, /SB, SB or other suffix after the Bombardier engineering part number. When the parts are installed, with the instructions given in the Accomplishment Instructions of this service bulletin, the parts agree with the requirements of the engineering configuration. Refer to the SB Introduction document for more explanation. B. Consumable Information For a list of consumables, refer to the different tasks that are given as references in this service bulletin. C. Special Tools and Equipment For a list of special tools and equipment, refer to the different tasks that are given as references in this service bulletin. D. Disposition of Parts Not applicable. 1 --- 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.