SB 670BA ---27---062 Page 1 of 1 Feb 13/2015 

## SERVICE BULLETIN REVISION TRANSMITTAL SHEET SERVICE BULLETIN 670BA ---27 ---062 SUBJECT: Flight Controls --- Elevator Control System --- Modification of the Elevator Lever Assemblies and the Control Rods This page transmits: Revision C of Service Bulletin 670BA --- 27 --- 062, dated Feb 13/2015. The changes in this revision have no effect on aircraft that have had this service bulletin incorporated. Reason: Revised Accomplishment Instructions, paragraph 2., to: Change and add some steps. Change an illustration. This revision also includes small editorial changes that do not have an effect on the technical content. Instructions: Discard the copy of Service Bulletin 670BA --- 27 --- 062, Revision B, dated Oct 10/2014. Replace with the copy attached. Service Bulletin History: Initial issue, dated Dec 12/2013 Revision A, dated Apr 01/2014 Revision B, dated Oct 10/2014 1SB 670BA−27−062 Page 1 of 45 Dec 12/2013 Revision C, Feb 13/2015 

# 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: 27−31 NUMBER: 670BA−27−062 SUBJECT: Flight Controls − Elevator Control System − Modification of the Elevator Lever Assemblies and the Control Rods
1. PLANNING INFORMATION A. Effectivity (1) Aircraft Affected: AIRCRAFT MODEL SERVICE AIRCRAFT SERIAL NUMBERS PRODUCTION AIRCRAFT SERIAL NUMBERS CL−600−2C10 10002 thru 10337 10338 and subsequent serial numbers [1] CL−600−2D15 and CL−600−2D24 15001 thru 15298 15299 and subsequent serial numbers [1] [1] Aircraft will have an equivalent modification incorporated before delivery. 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), Supplemental Type Approvals (STAs) or equivalent action changes to make sure you can complete this service bulletin.

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 2 of 45 Dec 12/2013 Revision C, Feb 13/2015 B. Reason (1) Condition A break between one of the elevator control rod and a lever assembly can occur. This can cause a difference between the position of the left and the right elevator control surface more than the permitted limits. (2) Evidence This condition was found during the certification of the CL−600−2E25 aircraft and confirmed on the CL−600−2C10, CL−600−2D15, and CL−600−2D24 aircraft. (3) Objective/Benefit This service bulletin gives the procedure to replace the left and the right fixed control rods and the lever assemblies. This will prevent a break between the components of the elevator system, if a failure occurs. C. Description The elevator control surfaces are moved in the neutral position. The hydraulic pressure is released from the systems. Circuit breakers are opened. Some access panels from the vertical stabilizer are removed. The fixed control rods and the lever assemblies are replaced. The access panels are installed. The circuit breakers are closed. The operational test of the elevator control system and the functional test of the pitch feel system are done. D. Compliance Recommended Service Bulletin. Bombardier recommends that this service bulletin be done at no more than 9200 flight hours from the release date of this service bulletin, unless otherwise directed by the airworthiness authority of the operator. NOTE: This service bulletin supersedes Service Bulletin 670BA−27−022, Flight Controls − El evator Control System − Replacement of the Elevator Lever Assemblies. NOTE: For aircraft that have had Service Bulletin 670BA−27−022 incorporated, it is necessary to incorporate this service bulletin. 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).

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 3 of 45 Dec 12/2013 Revision C, Feb 13/2015 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. It will take an estimated 14.0 man-hours to complete this service bulletin. The man-hours are divided in the table that follows: TASK MAN-HOURS (1) Job Set-Up 1.5 (2) Procedure 10.0 (3) Test 1.5 (4) Job Close-Out 1.0

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 4 of 45 Dec 12/2013 Revision C, Feb 13/2015 G. Material − Price and Availability (1) The kits in the table that follows are available from Bombardier. NOTE: For a list of kit contents, refer to paragraph 3.A.
KIT NUMBER NAME 670BA27062K1 [1] Kit − Elevator Disconnect Modification 670BA27062K2 [2] Blank Idler Aft Brackets [1] One kit is necessary for each aircraft. [2] A limited quantity of kits are available for each operator and can be necessary until P/N A V670−21569−009SB and P/N A V670−21569−010SB replace P/N AV670−21569−009 and P/N AV670−21569−010 in kit 670BA27062K1 or later kit revisions. (2) Please send a purchase order to the address below to schedule kit delivery: 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 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 kit in the table that follows is available from Bombardier. NOTE: For a list of the kit contents, refer to paragraph 3.A.
KIT NUMBER NAME 670BA27062K90 Kit − Reamers

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 5 of 45 Dec 12/2013 Revision C, Feb 13/2015 (2) Please send a purchase order to the address below to schedule kit delivery: 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 Please contact the Service Bulletin Kit Support Team at the address above for terms and conditions. I. Weight and Balance For CL−600−2C10 aircraft
WEIGHT ARM MOMENT +1.2 lb +1311.8 in. +1.574 (1000 lb-in) +0.54 kg +33.32 m +0.0181 (1000 kg-m)The value in the Moment column is divided by 1000. Refer to Weight and Balance Manual.
For CL−600−2D15 and CL−600−2D24 aircraft
WEIGHT ARM MOMENT +1.2 lb +1463.8 in. +1.757 (1000 lb-in) +0.54 kg +37.18 m +0.0202 (1000 kg-m)The value in the Moment column is divided by 1000. Refer to Weight and Balance Manual.
J. Electrical Load Data Not changed.

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 6 of 45 Dec 12/2013 Revision C, Feb 13/2015 K. References Refer to the SB Introduction document for definition or explanation of service bulletin content. Restriction and/or Special Instruction (RSI) C−27−1254−00, Revision E Modification Summary 670T040513, Revision J Aircraft Maintenance Manual (AMM) Structural Repair Manual (SRM) For Bombardier reference only: PCA 74115 L. Other Publications Affected Aircraft Maintenance Manual (AMM) Aircraft Illustrated Parts Catalogue (AIPC) M. Relationship Chart
PRE-SB PART NUMBER NAME POST-SB PART NUMBER NAME AV670−21569−001 or

AV670−21569−005 Idler bracket, aft KBA670−93707−3 [1] Idler bracket, aft AV670−21569−002 or

AV670−21569−006 Idler bracket, aft KBA670−93707−4 [2] Idler bracket, aft

BA670−92367−3 Lever assembly, forward KBA670−93707−5 Lever assembly, forward BA670−92602−39 Control rod, fixed BA670−93722−3 Link assembly BA670−93786−1, BA670−93772−1, or

BA670−93772−3 Lever assembly, aft BA670−93787−3, or BA670−93787−951 Lever assembly, aft BA670−93771−1, or

BA670−93771−3 Lever assembly BA670−93784−3 Lever assembly [1] P/N AV670−21569−009 was installed during the incorporation of the initial issue or Revision A of this service bulletin. [2] P/N AV670−21569−010 was installed during the incorporation of the initial issue or Revision A of this service bulletin.

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 7 of 45 Dec 12/2013 Revision C, Feb 13/2015 For Aircraft 10150 thru 10226, 10228, and 15024 thru 15039 pre-SB 670BA−27−022 PRE-SB PART NUMBER NAME POST-SB PART NUMBER NAME BA670−30000−8955, BA670−30000−9993, BA690−30000−496, or

BA690−30000−4989 Control rod BA670−92602−13 Control rod

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 8 of 45 Dec 12/2013 Revision C, Feb 13/2015 2. ACCOMPLISHMENT INSTRUCTIONS
Reference Information REFERENCE DESIGNATION AMM 12−00−00−867−801 Standard Aircraft Configuration for Maintenance AMM 12−00−06−862−802 Release Hydraulic Pressure of Systems No.1 and No.2 AMM 12−00−06−862−804 Release Hydraulic Pressure of System No.3 AMM 20−21−00−910−801 Torquing of Threaded Fasteners AMM 20−31−00−400−801 Thermal Installation of Interference Fit Bushings AMM 20−51−00−000−801 Removal of Cotter Pins AMM 20−51−00−400−801 Installation of Cotter Pins AMM 20−51−00−000−802 Removal of Lockwire AMM 20−51−00−400−802 Installation of Lockwire AMM 20−51−00−000−807 Removal of Safety Cables AMM 20−51−00−400−807 Installation of Safety Cables AMM 24−00−00−910−801 Electrical/Electronic Safety Precautions AMM 27−00−00−910−802 Flight-Control Safety Precautions AMM 27−31−00−710−801 Operational Test of the Elevator Control System AMM 27−31−00−720−805 Functional Test of the Pitch Feel System AMM 27−31−00−864−801 Move the Elevator Control Surfaces in the Neutral Position AMM 27−31−25−000−810 Removal of the Vertical Stabilizer Control−Rod from FS1308.44 to FS1317.47 AMM 55−32−32−000−801 Removal of the Elevator-Quadrant Access Door (325EL/325ER) AMM 55−32−32−400−801 Installation of the Elevator-Quadrant Access Door (325EL/325ER)

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 9 of 45 Dec 12/2013 Revision C, Feb 13/2015 REFERENCE DESIGNATION AMM 55−32−32−000−804 Removal of the Load-Limiter Access Door (325FL) AMM 55−32−32−400−804 Installation of the Load-Limiter Access Door (325FL) AMM 55−32−32−000−805 Removal of the Gain-Changer Access Door (325BL) AMM 55−32−32−400−805 Installation of the Gain-Changer Access Door (325BL) AMM 55−32−86−000−805 Removal of the Lower Fairing Panel (326BL/326BR) AMM 55−32−86−400−805 Installation of the Lower Fairing Panel (326BL/326BR) AMM 55−32−86−000−807 Removal of the Lower Visor Fairing (326CL/326CR) AMM 55−32−86−400−807 Installation of the Lower Visor Fairing (326CL/326CR) SRM 51−21−11−001−001 Corrosion Prevention Procedures SRM 51−23−00−001−001 Pressure, Environmental, Fuel Tank and Firewall Sealing SRM 51−25−06−001−001 Fluid-Resistant (FR) Epoxy Primer SRM 51−25−16−001−001 Fluid-Resistant (FR) Polyurethane Topcoat SRM 51−26−00−001−001 Cleaning SRM 51−41−02−001−001 Bolts, Screws and Related Items Tolerance Information Linear Tolerances Angular Tolerance X.XX in. (X.X mm) X.X in. (X mm) +/−0° 30" +/− 0.03 in. +/− 0.1 in. +/− 0.8 mm +/− 3 mm NOTE: The tolerances above apply to the dimensions given in this service bulletin, except when specified differently.

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 10 of 45 Dec 12/2013 Revision C, Feb 13/2015 A. Job Set-Up 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. (1) Make sure that the aircraft is in standard configuration for maintenance (refer to AMM 12−00−00−867−801). (2) Move the elevator control surfaces in the neutral position (refer to AMM 27−31−00−864−801). (3) Obey all the flight-control safety precautions (refer to AMM 27−00−00−910−802). (4) Release the pressure of hydraulic systems No.1 and No.2 (refer to AMM 12−00−06−862−802). (5) Release the pressure of hydraulic system No.3 (refer to AMM 12−00−06−862−804). (6) Obey all the electrical/electronic safety precautions (refer to AMM 24−00−00−910−801). (7) Open, safety, and tag the circuit breakers that follow: CB PANEL CB NO. NAME

CBP−1 F1 SSCU 1 CH A CBP−1 F11 HYD SYST AC PUMP CONT 3B CBP−1 F14 HYD SYST AC PUMP CONT 2 CBP−2 F1 SSCU 1 CH B CBP−2 F13 HYD SYST AC PUMP CONT 1 CBP−2 F14 HYD SYST AC PUMP CONT 3A CBP−2 LOWER R3 SSCU 2 CH A CBP−2 LOWER R4 SSCU 2 CH B

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 11 of 45 Dec 12/2013 Revision C, Feb 13/2015 (8) Remove the access panels that follow:
PANEL NAME REFERENCE 325BL Gain-Changer Access Door AMM 55−32−32−000−805 325EL/325ER Elevator-Quadrant Access Door AMM 55−32−32−000−801 325FL Load-Limiter Access Door AMM 55−32−32−000−804 326CL/326CR Lower Visor Fairing AMM 55−32−86−000−807 (9) If necessary, remove the access panel that follows:
PANEL NAME REFERENCE 326BL/326BR Lower Fairing Panel AMM 55−32−86−000−805
B. Procedure NOTE: This procedure is applicable to the left and the right sides. The procedure that follows is written for the left side. The differences are given. Refer to Figure 1. (1) Install rigging pins P1 and P2. (2) Remove and discard the vertical stabilizer control-rods (1) from, FS1308.44 to FS1317.47, and their related hardware (refer to AMM 27−31−25−000−810). Refer to Figure 2. (3) Remove the cotter pin (3), the nut (4), the washer (5), the bolt (6), and the upper end of the load limiter (1) from the forward lever assembly (2) (refer to AMM 20−51−00−000−801). Discard the cotter pin (3) and the nut (4). (4) Remove the centering springs (7), the link (8), and the adjustable studs (9) from the aft lever assembly (10) as follows: (a) Remove the lockwire from the jam nut (13) (refer to AMM 20−51−00−000−802).

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 12 of 45 Dec 12/2013 Revision C, Feb 13/2015 (b) Remove and discard the jam nuts (13) and the locking devices (14) from the adjustable studs (9). (c) Remove the cotter pin (3), the nut (4), the washer (11), the bolt (12), and the link (8) from the aft lever assembly (10) (refer to AMM 20−51−00−000−801). Discard the cotter pin (3), the nut (4), the washer (11), and the bolt (12). (5) Remove the forward end of the horizontal stabilizer control-rod (15) from the aft lever assembly (10) as follows: (a) Remove the cotter pin (3), the nut (4), the washer (11), the bushing (16), the countersunk washer (17), and the bolt (12) from the aft lever assembly (10) (refer to AMM 20−51−00−000−801). (b) Discard the cotter pin (3), the nut (4), the washer (11), the bushing (16), and the bolt (12). Refer to Figure 3. (6) Remove the lever assemblies (1) and (2) and the idler brackets (3) and (4) as follows: (a) Remove the nuts (5) and (6), the washers (7) and (8), the bolts (9) and (10), and the idler forward bracket (3) from the canted rib. Discard the nuts (5) and (6). (b) Remove the cotter pin (11), the nut (12), the washer (13), the bushing (14), the countersunk washer (15), the bolt (16), and the forward lever assembly (1) from the idler forward bracket (3) (refer to AMM 20−51−00−000−801). Discard the cotter pin (11), the nut (12), the washer (13), and the bolt (16). (c) Remove the nuts (5), the washers (7), the bolts (17), and the idler aft bracket (4) from the canted rib. Discard the nuts (5). NOTE: Keep the idler aft bracket (4), it can be used in a subsequent step to drill the holes if a new blank idler aft bracket is used. (d) Remove the cotter pin (11), the nut (12), the washer (13), the bushing (18), the countersunk washer (15), the bolt (16) and the aft lever assembly (2) from the idler aft bracket (4) (refer to AMM 20−51−00−000−801). Discard the cotter pin (11), the nut (12), the washer (13), the bushing (18), the bolt (16), and the aft lever assembly (2).

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 13 of 45 Dec 12/2013 Revision C, Feb 13/2015 Refer to Figure 4. (7) Increase the diameter of the outboard hole for the left forward lever assembly (1) and the inboard hole for the right forward lever assembly (1) as follows (refer to View A): (a) Assemble the reamer guide assembly on the forward lever assembly (1) as follows: 1 Put the flange stopper (2) between the aft flanges of the forward lever assembly (1). 2 With the alignment pin (3), install the guide bushing (4) through the right flange of the forward lever assembly (1) and the flange stopper (2). 3 Tighten the screws of the flange stopper (2). 4 Install the washer (5) and, with your hand, tighten the nut (6) on the guide bushing (4). 5 Remove the alignment pin (3). (b) With step reamer (7) P/N 670BA27062K90−13 and cutting fluid, ream the hole to a diameter of 0.3050 to 0.3052 in. (7.747 to 7.752 mm). (c) With step reamer (7) P/N 670BA27062K90−15 and cutting fluid, ream the hole to a diameter of 0.3600 to 0.3602 in. (9.144 to 9.149 mm) . (d) With final reamer (7) P/N 670BA27062K90−17 and cutting fluid, ream the hole to a diameter of 0.3750 to 0.3752 in. (9.525 to 9.530 mm). (e) Disassemble the reamer guide assembly as follows: 1 Loosen the screws of the flange stopper (2) to remove the reamer guide assembly. 2 Remove the nut (6), the washer (5), the guide bushing (4), and the flange stopper (2) from the forward lever assembly (1). (f) Remove the burrs and the sharp edges. (g) Apply chemical conversion coating on the bare metal areas (refer to SRM 51−21−11−001−001).

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 14 of 45 Dec 12/2013 Revision C, Feb 13/2015 (h) With a clean cloth moist with solvent, remove the identification of the forward lever assembly (1) (refer to SRM 51−26−00−001−001). (i) If the identification number continues to be visible, apply one layer of fluid-resistant primer over the identification (refer to SRM 51−25−06−001−001). (j) With an indelible ink pen or equivalent, identify the forward lever assembly (1) as KBA670−93707−5. (k) Apply a layer of clear polyurethane topcoat on the identification (refer to SRM 51−25−16−001−001). NOTE: Let the ink dry for 30 minutes before you apply the clear polyurethane topcoat. Refer to Figure 11. (8) If you have idler aft bracket (1), do as follows: NOTE: The diameter of the holes in the canted rib are not increased. (a) Increase the diameter of the four holes in the idler aft bracket (1) to 0.198−0.203 in. (5.03−5.16 mm). (b) Remove the burrs and the sharp edges. (c) Make sure the holes in the idler aft bracket (1) align with the holes in the canted rib and the four bolts (3) can be installed. (d) If the four bolts (3) can not be installed, idler aft bracket (1) is not used. Go to step (9) to use idler aft bracket (2). (e) Apply chemical conversion coating on the bare metal areas of the idler aft bracket (1) (refer to SRM 51−21−11−001−001). (f) With a clean cloth moist with solvent, remove the identification of the idler aft bracket (1) (refer to SRM 51−26−00−001−001). (g) If the identification number continues to be visible, apply one layer of fluid−resistant primer over the identification (refer to SRM 51−25−06−001−001).

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 15 of 45 Dec 12/2013 Revision C, Feb 13/2015 (h) With an indelible ink pen or equivalent, identify the idler aft bracket (1) as follows: 1 For the left idler aft bracket (1), identify as KBA670−93707−3. 2 For the right idler aft bracket (1), identify as KBA670−93707−4. (i) Apply a layer of clear polyurethane topcoat on the identification (refer to SRM 51−25−16−001−001). NOTE: Let the ink dry for 30 minutes before you apply the clear polyurethane topcoat. Refer to Figure 3 and Figure 11. (9) If you do not have idler aft bracket (1), or if it is not possible to install the idler aft bracket (1), use the idler aft bracket (2) as follows: NOTE: The diameter of the holes in the canted rib are not increased. (a) Drill four holes in the blank idler aft bracket (2) to a diameter of 0.198−0.203 in. (5.03−5.16 mm) to align with the four holes in the canted rib. Make sure you drill the holes so the idler aft bracket (2) is installed at the same location as the idler aft bracket (4). (b) Remove the burrs and the sharp edges. (c) Apply chemical conversion coating on the bare metal areas (refer to SRM 51−21−11−001−001). (d) With a clean cloth moist with solvent, remove the identification of the idler aft bracket (2) (refer to SRM 51−26−00−001−001). (e) If the identification number continues to be visible, apply one layer of fluid−resistant primer over the identification (refer to SRM 51−25−06−001−001). (f) With an indelible ink pen or equivalent, identify the idler aft bracket (2) as follows: 1 For the left idler aft bracket (2), identify as KBA670−93707−3. 2 For the right idler aft bracket (2), identify as KBA670−93707−4.

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 16 of 45 Dec 12/2013 Revision C, Feb 13/2015 (g) Apply a layer of clear polyurethane topcoat on the identification (refer to SRM 51−25−16−001−001). NOTE: Let the ink dry for 30 minutes before you apply the clear polyurethane topcoat. Refer to Figure 5. (10) Make sure that the bolts (10), (16), and (17) are put in position on the idler brackets (2) and (14) before the installation of the lever assemblies (1) and (13). (11) Install the aft lever assembly (1) on the idler aft bracket (2) with the bolt (3), the countersunk washer (4), the bushing (5) and (6), the washer (7), the self-locking nut (8), and the cotter pin (9) (refer to AMM 20−21−00−910−801, AMM 20−51−00−400−801, and SRM 51−41−02−001−001). NOTE: The countersunk side of the washer (4) must be installed under the head of the bolt (3). NOTE: The bushing (6) must be installed between t he idler aft bracket (2) and the aft lever assembly (1). (12) Install the idler aft bracket (2) on the canted rib with the bolts (10), the washers (11), and the self-locking nuts (12) (refer to AMM 20−21−00−910−801 and SRM 51−41−02−001−001). (13) Install the forward lever assembly (13) on the idler forward bracket (14) with the bolt (3), the countersunk washer (4), the bushing (15), the washer (7), the self-locking nut (8), and the cotter pin (9) (refer to AMM 20−21−00−910−801, AMM 20−51−00−400−801, and SRM 51−41−02−001−001). NOTE: The countersunk side of the washer (3) must be installed under the head of the bolt (4). (14) Install the idler forward bracket (14) on the canted rib with the bolts (16) and (17), the washers (11) and (18), and the self-locking nuts (12) and (19) (refer to AMM 20−21−00−910−801 and SRM 51−41−02−001−001).

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 17 of 45 Dec 12/2013 Revision C, Feb 13/2015 Refer to Figure 6. (15) Install the link assembly (1) as follows: (a) Install the link assembly (1) on the aft lever assembly (2) with the bolt (3), the washer (4), the self-locking nut (5), the washer key (6), the bushing (7), the bolt (8), the washer (9), the flat washer (10), the self-locking nut (11), and the cotter pin (12) (refer to AMM 20−51−00−400−801 and SRM 51−41−02−001−001). (b) Torque the self-locking nut (11) from 30 to 40 lbf• in. (3.4 to 4.5 N • m) (refer to AMM 20−21−00−910−801). (c) Install the link assembly (1) on the forward lever assembly (13) with the bolt (14), the countersunk washer (15), the bushings (16) and (17), the washer (18), the self-locking nut (11), and the cotter pin (12) (refer to AMM 20−21−00−910−801, AMM 20−31−00−400−801, AMM 20−51−00−400−801, and SRM 51−41−02−001−001). NOTE: The countersunk side of the washer (15) must be installed under the head of the bolt (14). NOTE: The bushing (16) is installed between the link assembly (1) and the lug of the forward lever assembly (13). Refer to Figure 7. (16) Install rigging pin P3. (17) Align the fastener hole of the load limiter (1) with the fastener hole of the forward lever assembly (2). (18) If the fastener hole of the load limiter (1) does not align with the fastener hole of the forward lever assembly (2), do the steps that follow: (a) Remove the lockwire or the safety cable from the jam nut (3) (refer to AMM 20−51−00−000−802 or 20−51−00−000−807). (b) Loosen the jam nut (3) of the load limiter (1) sufficiently to disengage the locking device (4). (c) Adjust the length of the load limiter (1) to align the fastener hole of the load limiter (1) with the fastener hole of the forward lever assembly (2). (d) Tighten the jam nut (3) of the load limiter (1) sufficiently to engage the locking device (4).

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 18 of 45 Dec 12/2013 Revision C, Feb 13/2015 (19) Install the aft end of the load limiter (1) to the forward lever assembly (2) with the bolt (5), the washer (6), the self-locking nut (7), and the cotter pin (8) (refer to AMM 20−21−00−910−801, AMM 20−51−00−400−801, and SRM 51−41−02−001−001). (20) Make sure that rigging pins P1 and P3 move easily. (21) If the lockwire or the safety cable was removed, safety the jam nuts (3) of the load limiter (1) with lockwire or safety cable (refer to AMM 20−51−00−400−802 or 20−51−00−400−807). (22) Install rigging pin P4. (23) Remove rigging pins P1 and P3. (24) Remove the cotter pin (9), the nut (10), the washer (11), the bolt (12), and the control rod (13) from the elevator quadrant (refer to AMM 20−51−00−000−801). Discard the cotter pins (9). (25) Remove the cotter pin (9), the nut (14), the washer (15), the bolt (16), and the control rod (17) from the gain-changer (refer to AMM 20−51−00−000−801). Discard the cotter pins (9). (26) Install the centering springs (18) with the link (19) and the adjustable studs (20) as follows: (a) Apply Mastinox compound or corrosion inhibiting compound on the hooks of the centering springs (18). (b) Install the link (19) and the centering springs (18) on the aft lever assembly (21) with the bolt (22), the washer (23), the self-locking nut (24), and the cotter pin (8) (refer to AMM 20−21−00−910−801, AMM 20−51−00−400−801, and SRM 51−41−02−001−001). (c) Install the adjustable studs (20) on the canted rib bracket with the locking devices (25) wet with Mastinox compound or corrosion inhibiting compound and the jam nuts (26) (refer to SRM 51−23−00−001−001). (d) Adjust the jam nuts (26) of the adjustable studs (20) until rigging pin P3 can be installed and moved easily. (e) Remove rigging pin P3. (27) Move the control rod (17) quickly to operate the centering springs (18). (28) Temporarily install rigging pin P3.

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 19 of 45 Dec 12/2013 Revision C, Feb 13/2015 (29) Make sure that rigging pin P3 moves easily. (30) Remove rigging pin P3. (31) Safety the two forward jam nuts (26) of the adjustable studs (20) together with lockwire (refer to AMM 20−51−00−400−802). NOTE: Do not install the lockwire through the locking devices (25). (32) Safety the two aft jam nuts (26) of the adjustable studs (20) together with lockwire (refer to AMM 20−51−00−400−802). NOTE: Do not install the lockwire through the locking devices (25). (33) Install the control rod (17) to the gain-changer with the bolt (16), the washer (15), the nut (14), and the cotter pin (9) (refer to AMM 20−21−00−910−801, AMM 20−51−00−400−801, and SRM 51−41−02−001−001). (34) Align the fastener hole of the horizontal stabilizer control-rod (27) with the fastener hole of the aft lever assembly (21). (35) If the fastener hole of the horizontal stabilizer control-rod (27) does not align with the fastener hole of the aft lever assembly (21), do as follows: (a) Remove the cotter pin (9), the self-locking nut (28), the washers (29) and (30), the bolt (31), and the horizontal stabilizer control-rod (27) from the bearing rod end (refer to AMM 20−51−00−000−801). Discard the cotter pin (9). (b) Remove the lockwire or safety cable from the jam nut (32) of the horizontal stabilizer control-rod (27) (refer to AMM 20−51−00−000−802 and AMM 20−51−00−000−807). (c) Loosen the jam nut (32) of the horizontal stabilizer control-rod (27) sufficiently to disengage the locking device (33). (d) Adjust the length of the horizontal stabilizer control-rod (27) to align the fastener hole of the horizontal stabilizer control-rod (27) with the fastener hole of the bearing rod end and the aft lever assembly (21). (e) Tighten the jam nut (32) of the horizontal stabilizer control-rod (27) sufficiently to engage the locking device (33). (f) Install the aft end of the horizontal stabilizer control-rod (27) to the bearing rod end with the bolt (31), the washers (29) and (30), the self-locking nut (28), and the cotter pin (9) (refer to AMM 20−51−00−400−801).

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 20 of 45 Dec 12/2013 Revision C, Feb 13/2015 (36) Install the forward end of the horizontal stabilizer control-rod (27) to the aft lever assembly (21) with the bolt (34), the countersunk washer (35), the bushing (36), the washer (37), the self-locking nut (24), and the cotter pin (8) (refer to AMM 20−21−00−910−801, AMM 20−51−00−400−801, and SRM 51−41−02−001−001). NOTE: The countersunk side of the washer (35) must be installed under the head of the bolt (34). (37) Make sure that rigging pin P2 moves easily. (38) Temporarily install rigging pin P3. (39) Make sure that rigging pin P3 moves easily. (40) Remove rigging pins P3. (41) If the lockwire or the safety cable was removed, safety the jam nuts (32) of the horizontal stabilizer control-rod (27) with lockwire or safety cable (refer to AMM 20−51−00−400−802 or 20−51−00−400−807). (42) Install the control rod (13) to the elevator quadrant with the bolt (12), the washer (11), the nut (10), and the cotter pin (9) (refer to AMM 20−21−00−910−801, AMM 20−51−00−400−801, and SRM 51−41−02−001−001). (43) Install rigging pin P3. (44) Remove rigging pin P4. Refer to Figure 8. For Aircraft 10150 thru 10226, 10228, and 15024 thru 15039 pre-SB 670BA−27−022(45) Remove the arrow and the FWD" marking from the horizontal stabilizer control-rod (1) as follows: (a) With a Scotchbrite pad, lightly rub the area to remove the clear coating applied on the marks. (b) Make sure that you remove the clear coating only.(c) With a clean cloth moist with solvent, remove the arrow and the FWD" marking from the horizontal stabilizer control-rod (1) (refer to SRM 51−26−00−001−001).(d) If the arrow and/or the FWD" marking continues to be visible, apply onelayer of polyurethane topcoat on the arrow and/or the FWD" marking (refer to SRM 51−25−16−001−001).

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 21 of 45 Dec 12/2013 Revision C, Feb 13/2015 (46) With a indelible ink pen or equivalent, identify the horizontal stabilizer control-rod (1) as BA670−92602−13. (a) Apply a layer of clear polyurethane topcoat on the identification (refer to SRM 51−25−16−001−001). NOTE: Let the ink dry for 30 minutes before you apply the clear polyurethane topcoat. For all aircraft Refer to Figure 9. (47) Remove rigging pins P2 and P3. Refer to Figure 10. (48) Make sure that the clearance between the aft lever assembly and the fasteners of the lower skin is 0.250 in. (6.35 mm) minimum throughout the full travel of the elevator. (49) Make sure that the clearance between the head of the bolt that attaches the forward lever assembly to the link assembly and the pivot fitting of the horizontal stabilizer is 0.200 in. (5.08 mm) minimum through the full travel of the elevator. (50) 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. C. Job Close-Out (1) Remove all tools, equipment, and unwanted materials from the work area.

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 22 of 45 Dec 12/2013 Revision C, Feb 13/2015 (2) Install the access panels that follow:
PANEL NAME REFERENCE 325BL Gain-Changer Access Door AMM 55−32−32−400−805 325EL/325ER Elevator-Quadrant Access Door AMM 55−32−32−400−801 325FL Load-Limiter Access Door AMM 55−32−32−400−804 326CL/326CR Lower Visor Fairing AMM 55−32−86−400−807 (3) If removed, install the access panel that follows:
PANEL NAME REFERENCE 326BL/326BR Lower Fairing Panel AMM 55−32−86−400−805 (4) Remove the tags and close the circuit breakers that follow: CB PANEL CB NO. NAME

CBP−1 F1 SSCU 1 CH A CBP−1 F11 HYD SYST AC PUMP CONT 3B CBP−1 F14 HYD SYST AC PUMP CONT 2 CBP−2 F1 SSCU 1 CH B CBP−2 F13 HYD SYST AC PUMP CONT 1 CBP−2 F14 HYD SYST AC PUMP CONT 3A CBP−2 LOWER R3 SSCU 2 CH A CBP−2 LOWER R4 SSCU 2 CH B (5) Do the operational test of the elevator control system (refer the AMM 27−31−00−710−801). (6) Do the functional test of the pitch feel system (refer the AMM 27−31−00−720−805).

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 23 of 45 Dec 12/2013 Revision C, Feb 13/2015 (7) When this service bulletin is completed, add the weight and balance data shown in paragraph 1.I. of this service bulletin to the Weight and BalanceManual. Under ‘Description of Change’ enter Service Bulletin 670BA−27−062, Revision C, incorporated." (8) When this service bulletin is completed, make this entry in the applicablelogbooks: Service Bulletin 670BA−27−062, Revision C, Flight Controls − Elevator Control System − Modification of the Elevator Lever Assemblies and the Control Rods, incorporated."

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 24 of 45 Dec 12/2013 Revision C, Feb 13/2015 Rigging Pins − Installation Figure 1 (Sheet 1 of 1)ba7599a01.cgm, cr, 02−apr−2013 B

C A

CONTROL ROD (REF) P2

BEARING ROD END (REF) P1 A

LOAD LIMITER (REF) 1 C

B

GAIN

− CHANGER (REF)

NOTE Left side shown, right side opposite. CONTROL ROD (REF)

LEGEND P. Rigging pin. 1. Vertical stabilizer control

− rod.

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 25 of 45 Dec 12/2013 Revision C, Feb 13/2015 Load Limiter, Control Rod, and Centering Springs − Removal Figure 2 (Sheet 1 of 2)ba7602a01.cgm, sc, 16 oct 2012 3 4 5

6 2 LEGEND 1. Load limiter. 2. Forward lever assembly. 3. Cotter pin. 4. Nut. 5. Washer. 6. Bolt.

Left side shown, right side opposite. NOTE

1 A

B PRE − MOD AB

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 26 of 45 Dec 12/2013 Revision C, Feb 13/2015 Load Limiter, Control Rod, and Centering Springs − Removal Figure 2 (Sheet 2 of 2)ba7602a02.cgm, sc, 16 oct 2012 Left side shown, right side opposite. NOTE

3 7 4 11 8 12

16 17 12 11 4 3

15 10

13 14 13 9 13

C PRE − MOD A C LEGEND 3. Cotter pin. 4. Nut. 7. Centering spring. 8. Link. 9. Adjustable stud. 10. Aft lever assembly. 11. Washer. 12. Bolt. 13. Jam nut. 14. Locking device. 15. Horizontal stabilizer control

− rod. 16. Bushing. 17. Countersunk washer.

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 27 of 45 Dec 12/2013 Revision C, Feb 13/2015 Lever Assemblies and Idler Brackets − Removal Figure 3 (Sheet 1 of 1)ba7600a01.cgm, YL, Feb 20, 2014 PRE − MOD A B

NOTE Left side shown, right side opposite. A

B 1
11 12 13

14
15 16 3

5 6 7 8 10 9 11 12 13 15 18 17 17
4

16

7 5 2

CANTED RIB (REF) LEGEND 1. Forward lever assembly BA670

− 92367

− 3. 2. Aft lever assembly BA670

− 93786

− 1 or BA670

− 93772

− 1 or BA670

− 93772

− 3. 3. Idler forward bracket. 4. Idler aft bracket AV670

− 21569

− 001 or AV670

− 21569

− 005 (LH), AV670

− 21569

− 002 or AV670

− 21569

− 006 (RH). 5. Nut. 6. Nut. 7. Washer. 8. Washer. 9. Bolt. 10. Bolt. 11. Cotter pin. 12. Nut. 13. Washer. 14. Bushing. 15. Countersunk washer. 16. Bolt. 17. Bolt. 18. Bushing.

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 28 of 45 Dec 12/2013 Revision C, Feb 13/2015 Forward Lever Assembly − Modification Figure 4 (Sheet 1 of 1) 1ba7705a01.cgm, cr/kp, Jan. 6, 2015 LEGEND 1. Forward lever assembly BA670

− 92367

− 3 (pre

− mod) KBA670

− 93707

− 5 (post

− mod). 2. Flange stopper 670BA27062K90

− 7. 3. Alignment pin 670BA27062K90

− 27. 4. Guide bushing 670BA27062K90

− 3. 5. Washer 670BA27062K90

− 11. 6. Nut 670BA27062K90

− 5. 7. Reamer.

REAMER (ITEM 7) PART NUMBER 670BA27062K90

− 13 670BA27062K90

− 15 670BA27062K90

− 17 0.3050 to 0.3052 in. (7.747 to 7.752 mm) 0.3600 to 0.3602 in. (9.144 to 9.149 mm) 0.3750 to 0.3752 in. (9.525 to 9.530 mm) HOLE −FINAL DIAMETER A

A 2

4 3

7

DRILL (REF) 5 6 SCREW (REF)

OUT BOARD HOLE FOR THE LEFT ASSEMBLY, INBOARD HOLE FOR THE RIGHT ASSEMBLY (REF).

B B

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 29 of 45 Dec 12/2013 Revision C, Feb 13/2015 Lever Assemblies and Idler Brackets − Installation Figure 5 (Sheet 1 of 1) 13
9 8 7

15 4 3 14

12 19 11 18 17 16 6

4 10 10 2

3

11
12ba7618a01.cgm, yl/kl, 11 June 2014 POST− MOD A 1

5

CANTED RIB (REF)

C A

C

LEGEND 1. Aft lever assembly BA670

− 93787

− 3 or BA670

− 93787

− 951. 2. Idler aft bracket KBA670

− 93707

− 3 (LH), KBA670

− 93707

− 4 (RH). 3. Bolt. NAS6305

− 27D. 4. Countersunk washer. 5. Bushing B0309008

− 05

− 040. 6. Bushing B0309008

− 05

− 006. 7. Washer NAS1149E0563P. 8. Self

− locking nut B0203011L5. 9. Cotter pin MS24665

− 153. 10. Bolt. 11. Washer. 12. Self

− locking nut MS21042L3. 13. Forward lever assembly KBA670

− 93707

− 5. 14. Idler forward bracket. 15. Bushing. 16. Bolt. 17. Bolt. 18. Washer. 19. Self

− locking nut MS21042L4. 9 8 7

1 NOTE For the left and right side, the bushing (item 15) is installed on the outboard side of the bracket (item 14). 1

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 30 of 45 Dec 12/2013 Revision C, Feb 13/2015 Link Assembly − Installation Figure 6 (Sheet 1 of 1) A

A B

Bba7603a01.cgm, kp, March 10, 2013 LEGEND 1. Link assembly BA670

− 93722

− 3. 2. Aft lever assembly. 3. Bolt NAS6304U21D. 4. Washer NAS1149E0432R. 5. Self

− locking nut MS21083C6. 6. Washer key BA698

− 93726

− 3. 7. Bushing S10008

− 782A. 8. Bolt BA698

− 93725

− 3. 9. Washer B0202013C1614

− 16. 10. Flat washer NAS620C416P. 11. Self

− locking nut B0203011L4. 12. Cotter pin MS24665

− 153. 13. Fwd lever assembly. 14. Bolt NAS2814C15DP. 15. Countersunk washer MS20002C4. 16. Bushing NAS76A4

− 004P. 17. Bushing NAS76A4

− 009P. 18. Washer NAS1149E0463P. 12

16

15 14 18 8 11 10 9

1312 11 6 5 4 3 7

14

12 11 15 18 16

17 1

2

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 31 of 45 Dec 12/2013 Revision C, Feb 13/2015 Load Limiter, Control Rod, and Centering Springs − Installation Figure 7 (Sheet 1 of 4)ba7619a01.cgm, sc/cr, 31−jan−2013

POST− MOD A A

P3

5

1

IDLER ASSEMBLY (REF) 4 3 8 7 6 2

1. Left side shown, right side opposite. NOTES

LEGEND 1. Load limiter. 2. Forward lever assembly. 3. Jam nut. 4. Locking device. 5. Bolt. 6. Washer 7. Self

− locking nut MS14145L4. 8. Cotter pin MS24665

− 153. P. Rigging pin.

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 32 of 45 Dec 12/2013 Revision C, Feb 13/2015 Load Limiter, Control Rod, and Centering Springs − Installation Figure 7 (Sheet 2 of 4)ba7619a02.cgm, sc, 14 oct 2012
1. Left side shown, right side opposite. NOTES POST− MOD A P1 P3 LOAD LIMITER (REF) IDLER ASSEMBLY (REF)

B C 17

13 B P4

13 12 9 10 11 ELEVATOR QUADRANT (REF)

C 16 17

GAIN

− CHANGER (REF) 15 9 14 LEGEND 9. Cotter pin. 10. Nut. 11. Washer. 12. Bolt. 13. Control rod. 14. Nut. 15. Washer. 16. Bolt. 17. Control rod. P. Rigging pin.

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 33 of 45 Dec 12/2013 Revision C, Feb 13/2015 Load Limiter, Control Rod, and Centering Springs − Installation Figure 7 (Sheet 3 of 4)ba7619a03.cgm, sc/cr,29 jan 20113 8 18 24

23 19 22

35 34 37 24 8

27 21

26 25 26 20 POST− MOD A Left side shown, right side opposite. The bolt for the left and the right lever assembly is in the same direction. NOTES

2 1.

2
CANTED RIB BRACKET (REF)

2 26

D LINK ASSEMBLY NOT SHOWN FOR CLARITY

D

P3 36 LEGEND 8. Cotter pin MS24665

− 153. 18. Centering spring. 19. Link. 20. Adjustable stud. 21. Aft lever assembly. 22. Bolt NAS6304

− 8D. 23. Washer NAS1149E0463P. 24. Self

− locking nut B0203011L4. 25. Locking device NAS559

− 1 26. Jam nut NAS1423C4. 27. Horizontal stabilizer control

− rod. 34. Bolt NAS6304

− 17D. 35. Countersunk washer. 36. Bushing B0309008

− 04

− 027. 37. Washer NAS1149E0463R. P. Rigging pin.

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 34 of 45 Dec 12/2013 Revision C, Feb 13/2015 Load Limiter, Control Rod, and Centering Springs − Installation Figure 7 (Sheet 4 of 4)ba7619a04.cgm, sc, 14 oct 2012 Left side shown, right side opposite. NOTES 1. POST− MOD A LEGEND 9. Cotter pin. 27. Horizontal stabilizer control

− rod. 28. Self

− locking nut. 29. Washer. 30. Washer. 31. Bolt. 32. Jamnut. 33. Locking device. P. Rigging pin. E

E P2

27 33 32 9 28 29 30 31

BEARING ROD END (REF)

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 35 of 45 Dec 12/2013 Revision C, Feb 13/2015 Horizontal Stabilizer Control-Rod − Identification Figure 8 (Sheet 1 of 1)ba7601a01.cgm, sc, 3 oct 2012 A LEGEND 1. Horizontal

− stabilizer control

− rod BA670

− 30000

− 8955, BA670

− 30000

− 9993, BA690

− 30000

− 496, or BA690

− 30000

− 4989 (Pre

− Mod), BA670

− 92602

− 13 (Post

− Mod).

PRE − MOD A 1 NOTES 1. Left side shown, right side opposite. 2. For Aircraft 10150 thru 10226, 10228 and 15024 thru 15039 pre

− SB 670BA

− 27

− 022.

1
POST− MOD A

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 36 of 45 Dec 12/2013 Revision C, Feb 13/2015 Rigging Pins − Removal Figure 9 (Sheet 1 of 1)ba7610a01.cgm, sc/kp, July 16, 2014 LEGEND P. Rigging pin. NOTE Left side shown, right side opposite.

A

CONTROL ROD (REF) P2

BEARING ROD END (REF) B A

LOAD LIMITER (REF)

CONTROL ROD (REF) B

C

AFT LEVER ASSEMBLY (REF)

CONTROL ROD (REF)

C P3

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 37 of 45 Dec 12/2013 Revision C, Feb 13/2015 Lever Assemblies − Clearances Figure 10 (Sheet 1 of 2)ba8127a01.cgm, cr, 013−nov−2013 0.250 in. (6.35 mm) MINIMUM BL0.00

CONTROL ROD (REF)
AFT LEVER ASSEMBLY (REF) CONTROL ROD (REF)

VIEW LOOKING FORWARD LOWER SKIN (REF) A

AFT LEVER ASSEMBLY (REF) 0.250 in. (6.35 mm) MINIMUM

NOTE: Hardware are not shown for clarity. B B A

B B FASTENER (REF) C

C

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 38 of 45 Dec 12/2013 Revision C, Feb 13/2015 Lever Assemblies − Clearances Figure 10 (Sheet 2 of 2)b8127a02.cgm, cr, 13−nov−2013 C C BL0.00

HORIZONTAL STABILIZER PIVOT FITTING (REF) 0.200 in. (5.08 mm) MINIMUM 0.200 in. (5.08 mm) MINIMUM FORWARD LEVER ASSEMBLY (REF)

VIEW LOOKING UP LINK ASSEMBLY (REF)

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 39 of 45 Dec 12/2013 Revision C, Feb 13/2015 Idler Aft Bracket − Modification Figure 11 (Sheet 1 of 1)ba8260a01.cgm, kl, 15 July 2014 A

B LEFT SIDE SHOWN RIGHT SIDE OPPOSITE B LEFT SIDE SHOWN RIGHT SIDE OPPOSITE 2 LEGEND 1. Idler aft bracket AV670

− 21569

− 009 (LH), AV670

− 21569

− 010 (RH), KBA670

− 93707

− 3 (LH, Post

− Mod), KBA670

− 93707

− 4 (RH, Post

− Mod). 2. Idler aft bracket AV670

− 21569

− 009SB (LH), AV670

− 21569

− 010SB (RH), KBA670

− 93707

− 3 (LH, Post

− Mod), KBA670

− 93707

− 4 (RH, Post

− Mod). 3. Bolt. 1 A B 3

CANTED RIB (REF)

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 40 of 45 Dec 12/2013 Revision C, Feb 13/2015 3. MATERIAL INFORMATION
A. Kit Information Kit Contents: KIT 670BA27062K1 PART NUMBER QTY NAME ALTERNATE PARTS NOTES AV670−21569−009 1 Idler bracket assembly AV670−21569−009SB [1] AV670−21569−010 1 Idler bracket assembly AV670−21569−010SB [2] B0202013C1614−16 2 Washer
− − B0203011L4 8 Nut, self-locking
− − B0203011L5 4 Nut, self-locking
− − B0309008−04−027 2 Bushing, straight
− − B0309008−05−006 2 Bushing, straight
− − B0309008−05−040 2 Bushing, straight
− − BA670−93722−3 2 Link assembly
− − BA670−93787−3 2 Riveted (aft) lever assembly BA670−93787−951
− BA698−93725−3 2 Bolt
− − BA698−93726−3 2 Washer
− − MS14145L4 2 Nut, self-locking
− − MS20002C4 2 Washer, countersunk
− − MS21042L3 12 Nut, self-locking
− − MS21042L4 2 Nut, self-locking
− − MS21083C6 2 Nut, self-locking
− − MS24665−153 14 Cotter pin
− − NAS1149E0432R 2 Washer
− − NAS1149E0463P 4 Washer
− − NAS1149E0463R 2 Washer
− −

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 41 of 45 Dec 12/2013 Revision C, Feb 13/2015 PART NUMBER NOTES ALTERNATE PARTS NAME QTY NAS1149E0563P 4 Washer
− − NAS1423C4 8 Nut
− − NAS2814C15DP 2 Bolt
− − NAS559−1 4 Locking device
− − NAS620C416P 2 Washer
− − NAS6304−17D 2 Bolt
− − NAS6304−8D 2 Bolt
− − NAS6304U21D 2 Bolt
− − NAS6305−27D 4 Bolt
− − NAS76A4−004P 2 Bushing
− − NAS76A4−009P 2 Bushing
− − S10008−782A 2 Bushing, straight
− −The kit can contain more hardware and/or material than necessary. [1] Modification and re−identification to P/N KBA670−93707−3 by this SB. [2] Modification and re−identification to P/N KBA670−93707−4 by this SB.
KIT 670BA27062K2 PART NUMBER QTY NAME ALTERNATE PARTS NOTES AV670−21569−009SB 1 Idler bracket assembly
− [1] AV670−21569−010SB 1 Idler bracket assembly
− [2]Can be necessary until P/N AV670−21569−009SB and P/N AV670−21569−010SB replace P/N AV670−21569−009 and P/N AV670−21569−010 in kit 670BA27062K1 or later kit revisions. [1] Modification and re−identification to P/N KBA670−93707−3 by this SB. [2] Modification and re−identification to P/N KBA670−93707−4 by this SB.

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 42 of 45 Dec 12/2013 Revision C, Feb 13/2015 KIT 670BA27062K90 PART NUMBER QTY NAME ALTERNATE PARTS NOTES 670BA27062K90−1 1 Fwd Elevator Lever − Reamers Kit − −Refer to paragraph 1.H. for special terms and conditions.
NOTE: For permitted 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 The materials that follow are necessary to do this service bulletin. You can order them from Bombardier or purchase them directly from industry sources. If the material is ordered from Bombardier, there can be some lead time because of the shelf life of the material. CONSUMABLES

SPECIFICATION QTY NAME REFERENCE

− As necessary Paper, abrasive, aluminum oxide, 100− to 400-grit, wet or dry 05−176 Scotchbrite

− As necessary Cloth clean, dry, lint-free cotton 05−332 − As necessary Cutting fluid Commercially available 6856K As necessary Corrosion inhibitor, Mastinox 13−001 ### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 43 of 45 Dec 12/2013 Revision C, Feb 13/2015 SPECIFICATION REFERENCE NAME QTY BAMS 552−010, type 1 As necessary Compound, non-chromate, corrosion inhibiting, jointing 15−035 CA 1000
BAMS 565−001 As necessary Fluid resistant epoxy primer, color green 13−006 BAMS 565−002 As necessary Fluid resistant Enamel for aircraft interior 07−019 (Color grey #16473 per FED−STD−595) CMS 516−07 As necessary Marker, ink 05−041 CMS 565−02 As necessary Fluid resistant Enamel for aircraft interior, clear 16−012 MIL−C−81706, class 1A As necessary Compound, chemical conversion, for coating aluminum and aluminum alloys (Alodine 1200S) 05−025 MS24665−153 As necessary Cotter pin Commercially available MS20995C32 As necessary Lockwire, corrosion-resistant steel 05−004 Refer to AMM 51−31−00−992−801 NOTE: To complete this list of consumables, refer to the different tasks that are given as references in this service bulletin.

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 44 of 45 Dec 12/2013 Revision C, Feb 13/2015 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. SPECIAL TOOLS AND EQUIPMENT PART NUMBER QTY NAME ALTERNATE PARTS G601R270001−1 1 Kit − Flight Controls Rigging Pins −Refer to the Illustrated Tool and Equipment Manual (ITEM) NOTE: To complete this list of special tools and equipment, refer to the different tasks that are given as references in this service bulletin. D. Disposition of Parts The table that follows shows the disposition of parts on the aircraft (or spares), and the relationship between these parts to the new parts to be installed through the incorporation of this service bulletin. PRE-SB PART NUMBER NAME QTY DC POST-SB PART NUMBER NAME
AV670−21569−001 or AV670−21569−005 Idler bracket, aft 1 SAL KBA670−93707−3 [1] Idler bracket, aft AV670−21569−002 or AV670−21569−006 Idler bracket, aft 1 SAL KBA670−93707−4 [2] Idler bracket, aft BA670−92367−3 Lever assembly, forward 2 RWK KBA670−93707−5 Lever assembly, forward BA670−92602−39 Control rod, fixed 2 DIS BA670−93722−3 Link assembly BA670−93786−1, BA670−93772−1, or BA670−93772−3 Lever assembly, aft 2 DIS BA670−93787−3 or BA670−93787−951 Lever assembly, aft

### SERVICE BULLETIN 670BA−27−062

SB 670BA−27−062 Page 45 of 45 Dec 12/2013 Revision C, Feb 13/2015 PRE-SB PART NUMBER NAME POST-SB PART NUMBER DCQTY NAME BA670−30000−8955, BA670−30000−9993, BA690−30000−496, or BA690−30000−4989 Control rod 2 RWK BA670−92602−13 Control rod [1] P/N AV670−21569−009 was installed during the incorporation of the initial issue or Revision A of this service bulletin. [2] P/N AV670−21569−010 was installed during the incorporation of the initial issue or Revision A of this service bulletin. Disposition code (DC): DIS: Discard Part. RWK: Rework part as shown in this service bulletin. SAL: Salvage. 1the evolution of mobility

THANK YOU FOR YOUR COMMENTS



## SERVICE BULLETIN FEEDBACK FORM/COMPLIANCE SHEET (YOUR COMMENTS HELP US WRITE BETTER SERVICE BULLETINS) Service Bulletin No.: 670BA-27-062 Revision: C Aircraft Serial Number: Date: STRONGLY DISAGREE DISAGREE AGREE STRONGLY AGREE Instructions to do the service bulletin are accurate. Comments: 

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Figure(s), picture(s), and/or Appendix were helpful to do the service bulletin. Comments: 

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Part(s) or kit(s) agreed with the service bulletin requirement. Comments: 

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The service bulletin was accomplished within the estimated time given. Comments: 

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Overall, I was satisfied with this service bulletin. Comments: 

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Operator: Service Centre: Name: Telephone or Fax: FAX your comments or feedback to (450) 476---7300 or e-mail to crj_sb_evaluation_form@aero.bombardier.com