SB 670BA ---27---065 Page 1 of 21 Nov 15/2013 

# 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 COMMERCIAL AIRCRAFT 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 ---21 NUMBER: 670BA ---27 ---065 SUBJECT: Flight Controls --- Rudder Control System --- Inspection of Rudder Pedal Tubes P/N 600 ---90204 ---3 for Cracks and Replacement of the Rudder Bar Assemblies on the Pilot’s Rudder Pedal Assembly

1. PLANNING INFORMATION A. Effectivity (1) Aircraft Affected:

AIRCRAFT MODEL SERVICE AIRCRAFT SERIAL NUMBERS PRODUCTION AIRCRAFT SERIAL NUMBERS CL ---600---2C10 10002 thru 10342 10343 and subsequent serial numbers [1] CL ---600---2D15 and CL ---600---2D24 15001 thru 15337 15338 and subsequent serial numbers [1] CL ---600---2E25 19001 thru 19040 19041 and subsequent serial numbers [1] [1] Aircraft will have this change 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 changes to make sure you can complete this service bulletin.

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 2 of 21 Nov 15/2013 B. Reason (1) Condition It is possible that there are cracks on P/N 600---90204---3 rudder pedal tubes installed on the pilot’s rudder pedal assembly. (2) Evidence Two rudder pedal mechanism incidents occurred on in-service aircraft. (3) Objective/Benefit This service bulletin gives the procedure to do a detail visual inspection or an eddy current inspection on P/N 600---90204---3 rudder pedal tubes, on the pilot’s side, for cracks. Also, the procedure to replace the rudder bar assemblies on the pilot’s rudder pedal assembly is given. The detailed visual inspection or the eddy current inspection on P/N 600---90204---3 rudder pedal tubes or the replacement of the rudder bar assemblies will prevent rudder pedal mechanism incidents. C. Description This service bulletin is divided into two parts: PART A and PART B. PART A --- Detail Visual Inspection or Eddy Current Inspection of P/N 600 ---90204 ---3 Rudder Pedal Tubes, on the Pilot’s Side, for Cracks Access panels are removed. If necessary, the pilot’s rudder pedal assembly is removed. A detail visual inspection or an eddy current inspection is done on P/N 600---90204---3 rudder pedal tubes of the pilot’s rudder pedal assembly. If no cracks are found, the removed access panels are installed. If removed, the pilot’s rudder pedal assembly is installed. If a crack is found, PART B of this service bulletin is done. PART B --- Replacement of the Rudder Bar Assemblies on the Pilot’s Rudder Pedal Assembly The pilot’s rudder pedal assembly is removed. The rudder bar assemblies are replaced. The pilot’s rudder pedal assembly is installed.

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 3 of 21 Nov 15/2013 D. Compliance Recommended Service Bulletin. Bombardier recommends that PART A of this service bulletin be done as shown in the table below, unless otherwise directed by the airworthiness authority of the operator. NOTE: It is not necessary to do PART A of this service bulletin if PART B of this service bulletin is done before. TIME LIMIT TO DO PART A OF THIS SERVICE BULLETIN TIME LIMIT TO DO REPEATED INSPECTION

Before the aircraft has 26000 flight cycles It is necessary to do a repeated inspection at intervals of 750 flight cycles from the last detail visual inspection or It is necessary to do a repeated inspection at intervals of 1250 flight

cycles from the last eddy current inspection

Bombardier recommends that PART B of this service bulletin be done at the earliest convenience of the operator, unless otherwise directed by the airworthiness authority of the operator. This service bulletin affects Airworthiness Limitations (AWLs) and/or Damage Tolerance Inspections (DTIs). Reference applicable 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.

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 4 of 21 Nov 15/2013 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 a quote. Contact the Fleet Services Team through the CRC at 514-855-8500 or email at thd.crj@aero.bombardier.com. For PART A It will take an estimated 3.0 man-hours to complete PART A of this service bulletin. The man-hours are divided in the table that follows: TASK MAN-HOURS (1) Job Set-Up 0.5 (2) Procedure 2.0 (3) Test N/A (4) Job Close-Out 0.5

NOTE: These estimates do not include the man-hours necessary to remove and install the pilot’s rudder pedal assembly.

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 5 of 21 Nov 15/2013 For PART B It will take an estimated 6.0 man-hours to complete PART B of this service bulletin. The man-hours are divided in the table that follows: TASK MAN-HOURS (1) Job Set-Up 0.5 (2) Procedure 4.0 (3) Test 0.5 (4) Job Close-Out 1.0
G. Material --- Price and Availability For PART A (1) There are no kits for PART A of this service bulletin. The parts in the table that follows are necessary to do PART A of this service bulletin and are available from Bombardier Commercial Aircraft.

PART NUMBER NAME QTY AN386---2---14 Pin, taper 4 AN975---3 Washer, taper pin 4 MS14145L3 Nut, self-locking 4 MS24665---69 Pin, cotter 4 (2) Please send a purchase order to the address below to schedule part 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 e-mail: sbkits@aero.bombardier.com Please contact the Service Bulletin Kit Support Team at the address above for terms and conditions.

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 6 of 21 Nov 15/2013 For PART B (3) The kit in the table that follow is available from L ---3 Communications. NOTE: For a list of kit contents, refer to paragraph 3.A.

PART NUMBER NAME QTY 670BA27065K1 Rudder Bar Assembly --- Replacement kit 1

(4) Please send a purchase order to the address below to schedule kit delivery: L3 Communications 10,000 Helen-Bristol Street Mirabel, Quebec Canada J7N 1H3 Phone: 450---476---4434 Fax: 450---476---4908 Email: sbkits.mas@L ---3 com.com (5) Refer to paragraph 3.B. for a list of consumables 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 For PART A Not changed. For PART B
WEIGHT ARM MOMENT ¡ 0.6 lb 218.80 in. 0.131 (1000 lb-in.) 0.27 kg 5.56 m 0.0015 (1000 kg-m) ¡ The value in the Moment column is divided by 1000. Refer to Weight and Balance Manual CSP A ---041.
J. Electrical Load Data Not changed.

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 7 of 21 Nov 15/2013 K. References Refer to the SB Introduction document for definition or explanation of service bulletin content. Restriction and/or Special Instruction (RSI) C ---27---1537---00, Revision A Modification Summary 670T014158, Revision B Aircraft Maintenance Manual (AMM) Structural Repair Manual (SRM) For Bombardier reference only: PCA 75284 and 75328 L. Other Publications Affected Aircraft Illustrated Parts Catalogue (AIPC) Maintenance Requirement Manual (MRM) M. Relationship Chart For PART A Not applicable. For PART B

PRE-SB PART NUMBER NAME POST-SB PART NUMBER NAME

BA670---93408---1 Bar assembly, rudder BA670---93413---1 Bar assembly, rudder
BA670---93408---2 Bar assembly, rudder BA670---93413---2 Bar assembly, rudder

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 8 of 21 Nov 15/2013 2. ACCOMPLISHMENT INSTRUCTIONS PART A --- Detail Visual Inspection or Eddy Current Inspection of P/N 600 ---90204 ---3 Rudder Pedal Tubes, on the Pilot’s Side, for Cracks
Reference Information
REFERENCE DESIGNATION AMM 12---00---00---867---801 Standard Aircraft Configuration for Maintenance AMM 20---21---00---910---801 Torquing of Threaded fasteners 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 25---15---20---000---801 Removal of the Rudder Pedal Console AMM 27---21---01---000---801 Removal of the Rudder Pedals AMM 27---21---01---400---801 Installation of the Rudder Pedals AMM 27---21---00---710---801 Operational Test of the Rudder Control System AMM 27---21---00---864---801 Move the Rudder Control Surface in the Neutral Position AMM 51---26---00---110---801 Solvent Cleaning AMM 53---12---32---000---801 Flight Controls Access Panel SRM 51---21---11 Corrosion Prevention Procedures SRM 51---25---06 Fluid-Resistant (FR) Epoxy Primer SRM 51---43---00 Taper Pins

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 9 of 21 Nov 15/2013 A. Job Set-Up 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 CONTROL SURFACES. ACCIDENTAL MOVEMENT OF THE FLIGHT CONTROLS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. (1) Make sure that the aircraft is in standard configuration for maintenance (refer to AMM 12---00---00---867---801). (2) Install placards on the pilot’s and the copilot’s control columns to give warnings against movement of the rudder pedals.
B. Procedure Refer to Figure 1. (1) If necessary, remove the pilot’s rudder pedal assembly (refer to AMM 27---21---01---000---801) or do the steps that follow: (a) Move the rudder control surface in the neutral position (refer to AMM 27---21---00---864---801). (b) Remove rudder pedal console 221GZ (refer to AMM 25---15---20---000---801). (c) Remove the forward-fuselage access panel 131AL (refer to AMM 53---12---32---000---801). (d) Install the rigging pin (P1) in the lever (L1) of the forward pivot assembly on the left side (refer to View A). (2) Do the steps that follow to get access to the two aft tapered holes in the rudder pedal tubes (5): NOTE: The procedure that follows is applicable for one rudder pedal tube (5). The procedure for the other rudder pedal tube (5) is the same. (a) Remove and discard the lockwire from the bolt (8) (refer to AMM 20---51---00---000---802).

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 10 of 21 Nov 15/2013 (b) Remove the bolt (8) and the washer (9) that connect the control rod assembly (7) to the connecting rod fitting (6). (c) Remove and discard the two cotter pins (1), the nuts (2), the washers (3), and the taper pins (4) that connect the connecting rod fitting (6) to the rudder pedal tube (5) (refer to SRM 51---43---00---001---001 and AMM 20---51---00---000---801). (d) Move the connecting rod fitting (6) along the rudder pedal tube (5) to expose the two aft tapered holes (refer to View B). (e) Clean the area around the two aft tapered holes (refer to View C) (Refer to AMM 51---26---00---110---801). (3) Do a detail visual inspection or an eddy current inspection for cracks around the two aft tapered holes in the rudder pedal tubes (5). NOTE: You must use a 10X Triplet magnifying glass or better to do the detail visual inspection or the procedure given in Appendix A, of this service bulletin, to do the eddy current inspection. (4) If no cracks are found around the aft tapered holes in the rudder pedal tubes (5), do the steps that follow: (a) Install the connecting rod fitting (6) on the rudder pedal tube (5) with the new taper pins (4) wet with fluid-resistant epoxy primer, the new washers (3), and the new nuts (2) (refer to SRM 51---43---00---001---001). (b) Torque the nuts (2) to 20---28 lbf  ̄ in.(2.26---3.16 N  ̄ m) (refer to AMM 20---21---00---910---801). (c) Safety the nuts (2) with the cotter pins (1) (refer to AMM 20---51---00---400---801). (d) Connect the control rod assembly (7) to the connecting rod fitting (6) with the bolt (8) and the washer (9). (e) Tighten the bolt (8) (refer to SRM 51---41---02---001---001). (f) Safety the bolt (8) with lockwire (refer to AMM 20---51---00---400---802). (g) Remove the rigging pin (P1) from the level (L1) of the forward pivot assembly on the left side (refer to View A). (h) Continue to the Job Close-Out section.

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 11 of 21 Nov 15/2013 (5) If a crack is found around the aft tapered holes in the rudder pedal tubes (5), do PART B of this service bulletin before the next flight. (6) If damage is found at a different location on the rudder pedal tubes (5), speak with a representative of Bombardier at the Technical Help Desk, before the next flight, at phone number 514-855-8500 for an approved disposition. C. Job Close-Out (1) Remove all tools, equipment, and unwanted materials from the work area. (2) If removed, install the pilot’s rudder pedal assembly (refer to AMM 27---21---01---400---801) (3) Install rudder pedal console 221GZ (refer to AMM 25---15---20---400---801). (4) Install forward-fuselage access panel 131AL (refer to AMM 53---12---32---400---801). (5) Do the operational test of the rudder control system (refer to AMM 27---21---00---710---801). (6) When PART A of this service bulletin is completed, make this entry in the applicable logbooks: “Service Bulletin 670BA ---27---065, Flight Controls --- Rudder Control System --- Inspection of Rudder Pedal Tubes P/N 600---90204---3 for Cracks and Replacement of the Rudder Bar Assemblies on the Pilot’s Rudder Pedal Assembly, PART A, incorporated.”

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 12 of 21 Nov 15/2013 Rudder Pedal Tubes Tapered Holes --- Locator Figure 1 (Sheet 1 of 1) A

A B

B 1 2 3 4 LEGEND 1. Pin, cotter MS24665--69. 2. Nut, self--locking MS14145L3. 3. Washer AN975--3. 4. Pin, tapered AN386--2--14. 5. Tube, rudder pedal 600--90204--3. 6. Fitting, connecting rod. 7. Rod assembly, control. 8. Bolt. 9. Washer.

0.250 in. (6.35 mm) RUDDER PEDAL TUBE

(REF) INSPECTION AREA

C TYPICAL C 5

6 9 8

7 P1

AFT TAPERED HOLES (REF)ba7987a01.cgm, kp, July 16, 2013 NOTE 1 1

Connecting rod fittin (6) moved down to expose tappered holes.

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 13 of 21 Nov 15/2013 PART B --- Replacement of the Rudder Bar Assemblies on the Pilot’s Rudder Pedal Assembly

REFERENCE DESIGNATION AMM 12---00---00---867---801 Standard Aircraft Configuration for Maintenance AMM 20---21---00---910---801 Torquing of Threaded fasteners AMM 20---24---00---910---801 Cotter Pins --- Maintenance Practices 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 Cable AMM 20---51---00---400---807 Installation of Safety Cable AMM 27---21---01---000---801 Removal of the Rudder Pedal Assembly AMM 27---21---01---400---801 Installation of the Rudder Pedal Assembly AMM 32---43---14---820---801 Adjustment of the Brake Pedal Rod SRM 51---21---11 Corrosion Prevention Procedures SRM 51---21---16 Finish Codes D. 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).

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 14 of 21 Nov 15/2013 E. Procedure (1) Remove the pilot’s rudder pedal assembly (refer to AMM 27---21---01---000---801). Refer to Figure 2. (2) Do the steps that follow to remove the rudder bar assemblies (1) on the pilot’s rudder pedal assembly. NOTE: The procedure that follows is applicable for one rudder bar assembly (1). The procedure for the other rudder bar assembly (1) is the same. (a) At the pedal assembly (2), remove and discard the cotter pin (5). (b) Remove the nut (6) and the washer (7) that connect the pedal assembly (2) to the rudder bar assembly (1) and the pedal link (8). Discard the nut (6). (c) Remove the pedal assembly (2). (d) At the brake control lever (4), remove and discard the cotter pin (9). (e) Remove the nut (10), the washers (11), and the bolt (12), that connect the brake control rod (3) to the brake control lever (4). Discard the nut (10) (f) Remove and keep the brake control rod (3) and the pedal link (8). NOTE: The pedal link (8) must not be disconnected from the brake control rod (3). (g) At the outboard end of the rudder pedal assembly, remove and discard the cotter pin (13). (h) Remove the nut (14) and the washer (15) from the pivot bolt (16). Discard the nut (14). (i) Remove the pivot bolt (16) and the brake control levers (4). (j) Remove and discard the rudder bar assemblies (1).

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 15 of 21 Nov 15/2013 (3) Do the steps that follow to install the new rudder bar assemblies (1) on the pilot’s rudder pedal assembly. NOTE: The procedure that follows is applicable for one rudder bar assembly (1). The procedure for the other rudder bar assembly (1) is the same. (a) Put the outboard brake control lever (4) in position between the outboard rudder bar assembly (1) and the outboard face of the center attachment lug on the torque tube assembly (17). (b) Put the inboard brake control lever (4) in position between the inboard rudder bar assembly (1) and the inboard face of the center attachment lug on the torque tube assembly (17). (c) Align the inner bores of the inboard and the outboard rudder bar assemblies (1), the inboard and the outboard brake control levers (4), and the three attachment lugs on the torque tube assembly (17). (d) Assemble the rudder bar assembly (1) together with the pivot bolt (16) wet with CA1000 corrosion inhibiting compound or Mastinox compound (refer to SRM 51---21---16). (e) Install the bolt (16) with the washer (15) and the new nut (14). (f) Torque the nut (14) to 200---300 lbf  ̄ in. (23---34 N  ̄ m) (refer to AMM 20---21---00---910---801). (g) Safety the nut (14) with the cotter pin (13) (refer to AMM 20---51---00---400---801). (h) Connect the brake control rod (3) to the brake control lever (4) with the bolt (12), the washer (11), and the new nut (10). Make sure that the bolt (12) is installed so that it points towards the center-line of the rudder pedal assembly. (i) Torque the nut (10) to 9.6---12 lbf  ̄ in. (1.09---1.36 N  ̄ m) (refer to AMM 20---21---00---910---801). (j) Safety the nut (10) with the cotter pin (9) (refer to AMM 20---51---00---400---801). (k) Connect the pedal assembly (2) to the rudder bar assembly (1) and the pedal link (8) with the washer (7) and the new nut (6). (l) Torque the nut (6) to 150---200 lbf  ̄ in. (17---23 Nm) (refer to AMM 20---21---00---910---801). (m) Safety the nut (6) with the cotter pin (5) (refer to AMM 20---51---00---400---801).

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 16 of 21 Nov 15/2013 (4) With an indelible ink pen or equivalent, identify the rudder pedal assembly as shown in the table that follows: NOTE: The new part number of the rudder pedal assembly must be written below the serial number of the rudder bar assemblies (1).
RUDDER BAR ASSEMBLY PART NUMBER PEDAL ASSEMBLY PART NUMBER RUDDER PEDAL ASSEMBLY PART NUMBER BA670---93413---1 600---90240---1 KBA670---93407---3 BA670---93413---2 600---90240---2 KBA670---93407---4 BA670---93413---1 600---90240---3 KBA670---93407---5 BA670---93413---2 600---90240---4 KBA670---93407---6 (5) Install the pilot’s rudder pedal assembly (refer to AMM 27---21---01---400---801). (6) At the applicable rudder pedal cover, turn the stature control crank to move the rudder pedals to the fully aft position. Push on the rudder pedals to move them through their full range of travel. Make sure that there is a minimum clearance of 0.250 in. (6.35 mm) between the brake control lever (4) (and its related attaching parts) and the adjacent brake control lever, other components, or structure. (7) Turn the stature control crank to move the rudder pedals to the fully forward position. Push on the rudder pedals to move them through their full range of travel. Make sure that there is a minimum clearance of 0.250 in. (6.35 mm) between the brake control lever (4) (and its related attaching parts) and the adjacent brake control lever, other components, or structure. (8) Turn the stature control crank to set the rudder pedals to the middle position again (count the number of turns from fully forward to fully aft and divide by two). (9) Make sure that there is a minimum clearance of 0.180 in. (4.572 mm) between the side panel, the adjacent parts, and the rudder bar assembly (1) during the movement of the pedal assemblies (2) (refer to View C ---C). (10) Make sure that there is a minimum clearance of 0.375 in. (9.525 mm) between the two pedal shafts (refer to View C ---C).

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 17 of 21 Nov 15/2013 F. Job Close-Out (1) Remove all tools, equipment, and unwanted materials from the work area. (2) Do the adjustment of the brake pedal rods (refer to AMM 32---43---14---820---801). (3) When PART B of this service bulletin is completed, make this entry in the applicable logbooks: “Service Bulletin 670BA ---27---065, Flight Controls --- Rudder Control System --- Inspection of Rudder Pedal Tubes P/N 600---90204---3 for Cracks and Replacement of the Rudder Bar Assemblies on the Pilot’s Rudder Pedal Assembly, PART B, incorporated.”

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 18 of 21 Nov 15/2013 Rudder Bar Assemblies --- Replacement Figure 2 (Sheet 1 of 2) 5 6 7 8

A A

1

16 3

10 9

4
12 15
13 14 2

17 LEGEND

1. Rudder bar assembly BA670--93408--2 (Pre--Mod), BA670--93413--1 or BA670--93413--2 (Post--Mod). 2. Pedal assembly. 3. Control rod, rudder pedal brake. 4. Lever, brake assembly. 5. Pin, cotter MS24665--372.

7. Washer. 8. Link, pedal. 9. Pin, cotter MS24665--88. 10. Nut MS14145L3. 11. Washer. 12. Bolt. 13. Pin, cotter MS24665--372. 14. Nut, MS14145L12. 15. Washer. 16. Bolt, pivot. 17. Torque tube. BA670--93408--1 or

6. Nut MS14145--9.

ATTACHMENT LUG (REF) 11ba7989a01.cgm, kp, July 22, 2013

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 19 of 21 Nov 15/2013 Rudder Bar Assemblies --- Replacement Figure 2 (Sheet 2 of 2)ba7986a02.cgm, kp, July 17, 2013

C

-- C SIDE PANEL (REF) SIDE PANEL (REF) PEDAL SHAFT (REF) CONSOLE (REF) CONSOLE (REF)

C

B C B

A minimum clearance of 0.180 in. (4.572 mm) is necessary between the rudder bar assembly and the side panel. NOTE

A minimum clearance of 0.375 in. (9.525 mm) is necessary between the two pedal shafts. 2

2

RUDDER BAR (REF) 1 1 1

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 20 of 21 Nov 15/2013 3. MATERIAL INFORMATION

A. Kit Information Kit Contents:

KIT 670BA27065K1 PART NUMBER QTY NAME ALTERNATIVE NOTES BA670---93413---1 1 Bar assembly, rudder

--- --- BA670---93413---2 1 Bar assembly, rudder

--- --- MS14145L12 1 Nut, self-locking MS17826---12

--- MS14145L3 2 Nut, self-locking MS17826---3

--- MS14145---9 2 Nut, self-locking MS14145L ---9

--- MS24665---372 3 Pin, cotter

--- --- MS24665---88 2 Pin, cotter

--- ---

B. Consumable Information The materials that follow are necessary to do this service bulletin. You can order them from Bombardier or purchased 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 AS3510---0218C As necessary Safety cable 05---099B ¡
AS3510---02F As necessary Ferrule 05---100 ¡
MS20995C20 As necessary Lockwire, corrosion-resistant steel 05---003 ¡
MS20995C32 As necessary Lockwire, corrosion-resistant steel 05---004 ¡

### SERVICE BULLETIN 670BA ---27 ---065

SB 670BA ---27---065 Page 21 of 21 Nov 15/2013 SPECIFICATION REFERENCE NAME QTY 6856K As necessary Corrosion inhibitor. Mastinox 13---001 ¡
BAMS 552---010 (CA 1000) As necessary Compound, non-chromate, corrosion-inhibiting 15---035 ¡

¡ Refer to AMM 51---31---00---992---801
NOTE: To complete this list of consumables, refer to the different tasks and the appendix 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 and the appendix 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

BA670---93408---1 Bar assembly, rudder 1 DIS BA670---93413---1 Bar assembly, rudder
BA670---93408---2 Bar assembly, rudder 1 DIS BA670---93413---2 Bar assembly, rudder Disposition code (DC): DIS: Discard Part. 1APPENDIX A Page A1 of A10 Nov 15/2013 

# APPENDIX A SERVICE BULLETIN 670BA -- 27 -- 065

NON-DESTRUCTIVE TESTING (NDT) PROCEDURE

The procedure contained in this appendix is given as reference in the Accomplishment Instructions of Service Bulletin 670BA ---27---065.

### APPENDIX A SERVICE BULLETIN 670BA ---27 ---065

APPENDIX A Page A2 of A10 Nov 15/2013 SPECIAL DETAILED INSPECTION OF THE PILOT’S RUDDER PEDAL TUBES AT THE CONNECTING ROD FITTING
1. General
A. The nondestructive testing procedure that follows is for the inspection of surface cracks in the parts that follow: ---Pilot’s left and right Rudder Pedal Tubes at the Connecting Rod Fitting. B. This inspection must be done by a Level II or Level III eddy current qualified individual certified to an NDT Standard approved by the National Airworthiness Authority. 2. Effectivity: All aircraft
3. Job Set-Up Information
A. Tools and Equipement
REFERENCE DESIGNATION Hocking Phasec 2200 Eddy Current Instrument-Impedance --- Plane Type Techna NDT SPEN92-5 Surface Probe 90 deg. Tip, 50 to 500 kHz frequency, NFe, Absolute shielded 0.062 in. (1.57 mm) tip diameter, 5.00 in. (12.7mm) length, 0.250 in. (6.35 mm) tip length Al 29---32 Bombardier Aerospace CRS, made from Aluminum alloy (Conductivity value of 29% to 32% IACS), containing 0.008 in. (0.20 mm), 0.020 in. (0.5 mm) and 0.040 in. (1.02 mm) deep electrical discharge machined (EDM) notches. Refer to Figure 2 Commercially Available Coaxial Cable --- BNC to Microdot Commercially Available Non-conductive plastic plug (insert) Commercially Available Explosion proof light source

### APPENDIX A SERVICE BULLETIN 670BA ---27 ---065

APPENDIX A Page A3 of A10 Nov 15/2013 NOTE: Equivalent equipment can be used for area access or personal selection. It must satisfy the requirement of the task and resolve the reference notches in the calibration reference standard at the required level of resolution and sensitivity. To get access to the inspection area due to accessibility or user preference, it is permissible to use a probe of different configuration from the one specified. The test frequency used may range from 100 kHz to 2.0 MHz for surface inspection. B. Parts

ITEM No. DESIGNATION DRAWING NUMBER MATERIAL 1 Rudder Pedal Tube 600---90204---3 2024---T3
C. Reference Information
REFERENCE DESIGNATION NDT 51---20---06 (Part 01) Eddy current --- General Information AMM Rudder Pedal Assembly Removal/Installation SRM Finish Codes SRM Cleaning
4. Preparation and Cleaning
A. Make sure the inspection area is clean. B. If the finish on the inspection area is damaged or deteriorated, removre the finish.

### APPENDIX A SERVICE BULLETIN 670BA ---27 ---065

APPENDIX A Page A4 of A10 Nov 15/2013 5. Procedure Refer to Figures 1, 2, and 3. A. Do the steps that follow for the inspection of the Rudder Pedal Tubes at the Connecting Rod Fitting. NOTE: The manufacturer’s instrument instructions must be obeyed when you operate the test equipment. (1) Calibrate the equipment as follows: (a) Connect probe SPEN92---5 with the coaxial cable to the eddy current instrument. (b) Turn the instrument ON. Adjust and set the instrument controls as shown in Figure 1. (c) Place the probe (coil) tip perpendicular to the surface of the AL 29---32 calibration reference standard (CRS), away from the 0.040 in. (1.02 mm) deep EDM notch and the edge. (d) Balance [BAL] the eddy current instrument. Adjust the instrument [PHASE] control to get a horizontal lift-off signal moving from right-to-left (with increasing lift-off) across the screen display. (e) Slide the probe (coil) tip across the 0.040 in. (1.02 mm) deep EDM notch, and adjust the instrument sensitivity (gain) to get an amplitude signal as shown in Figure 1, screen display.

### APPENDIX A SERVICE BULLETIN 670BA ---27 ---065

APPENDIX A Page A5 of A10 Nov 15/2013 (2) Lift-Off Compensation verification: (a) After the calibration, as outlined in paragraph 5.A.(1)., place the probe (coil) tip perpendicular to the inspection surface. DO NOT balance the instrument. (b) Compare the screen displays between the operating point on the inspection surface and the balance point on the CRS for the following conditions. (c) If the operating point on the inspection surface matches the balance point on the CRS, no compensation for paint thickness is necessary. Proceed to the inspection procedure. (d) If the operating point on the inspection area does not match the balance point on the CRS, but has moved to the LEFT, compensation for the paint thickness is required. Do as follows:
1 Attach a strip of nonconductive tape or shim to cover the CRS surface including the EDM notches.
2 Place the probe (coil) perpendicular to the surface of the CRS. DO NOT balance the instrument. Compare the operating point on the inspection surface to the balance point on the CRS.
3 If the operating point on the inspection surface is still left of the balance point on the CRS, add an additional strip of tape or shim until the balance point on the CRS matches the operating point of the inspection area.
4 If the operating point on the inspection surface is to the right of the balance point on the CRS, remove a strip of tape or shim until the balance point on the CRS matches the operating point of the inspection area.
5 If lift-off compensation and calibration requirements cannot be met, remove the paint or coating before the inspection.

### APPENDIX A SERVICE BULLETIN 670BA ---27 ---065

APPENDIX A Page A6 of A10 Nov 15/2013 (3) Examine the Pilot’s Rudder Pedal Tubes at the Connecting Rod Fitting holes as follows: Refer to Figures 1 and 3. NOTE: Monitor the screen display carefully at all times and make a note of all distinct relevant indications. Include the screen height of each signal and its relative location on the part. NOTE: Use a nonconductive plastic plug (insert) for circular scans around the holes. No part of the plug (insert) shall cover the inspection surface to minimize the distance between the probe coil and the hole. (a) After the calibration, as outlined in step 5.A.(1) and 5.A.(2), insert the plastic plug into the aft tapered hole of the pilot’s left rudder pedal tube and position the probe (coil) tip against the plug (insert). (b) Balance [BAL] the instrument. If necessary, adjust instrument [PHASE] control to get a horizontal lift-off signal moving from right-to-left across the screen display. Refer to Figure 1. (c) Make a full circular (360 degrees) scan around the tapered hole using the plug (insert) as a probe guide. Make sure that the probe (coil) tip stays perpendicular to the inspection surface at all times during the scan. Refer to the inspection area and typical scan path shown in Figure 3. (d) Continue making full circular (360 degrees) scans around the tapered hole using a probe index of one probe diameter or less between scans until a width of 0.250 in. (6.35 mm) is reached. Make sure that the probe stays perpendicular to the inspection surface. (e) Repeat steps 5.A.(3).(a). to 5.A.(3).(d), for the remaining aft tapered hole. (f) Repeat steps 5.A.(3).(a) to 5.A.(3).(e) for the pilot’s right side rudder pedal tube.

### APPENDIX A SERVICE BULLETIN 670BA ---27 ---065

APPENDIX A Page A7 of A10 Nov 15/2013 (4) Do the evaluation of Indications as follows: (a) Any clear vertical deflection signal that occurs over a short scan distance (one probe tip diameter) is considered a suspect indication and is cause for further investigation. (b) Any rapid up dot movement signal that stays at the up position over a longer scan distance is considered a suspect indication and is cause for further investigation. (c) Make sure that the indication is not caused by edge effect, abrupt change in geometry, localized variation in conductivity, permeability or other non-relevant factors. (d) Examine all suspect crack indications by comparing their phase angle, amplitude and shape to the calibration standard notch EDM signal. (e) If a crack is found, find its length and location. (5) Do the acceptance and rejection criteria as follows: (a) Any clear vertical deflection signal which is equal to 50% or greater than the response from the 0.040 in. (1.02 mm) deep EDM notch as shown in Figure 1 is classified as a crack indication and cause for rejection. (b) Any rapid upward dot movement signal which equals to 50% or greater than the response from the 0.040 in. (1.02 mm) deep EDM notch as shown in Figure 1 and stays at the upward position momentarily or over a longer period of time is classified as a crack indication and cause for rejection. (c) Record and report results in accordance with company guidelines and policies. (6) Close Out (a) If the finish in the inspection area was removed, repair the finish.

### APPENDIX A SERVICE BULLETIN 670BA ---27 ---065

APPENDIX A Page A8 of A10 Nov 15/2013 Calibration Data for CRS AL 29-32 (Hocking Phasec 2200 Eddy Current Instrument and Probe SPEN92-5) Figure 1 (Sheet 1 of 1) CH 1 FREQ CH 1 PHASE CH 1 500 KHz

X --8 dB INSTRUMENT SETTINGS SCREEN DISPLAY

ABS CH1 XY

342.0 44.5 dB DC 200 Hz 47 40 --40 MODE DISPLAY VIEW

GAIN HI--PASS LO--PASS BAL. LOAD X--POS Y--POS X:Y

H SIGNAL FROM 0.040 in. (1.02 mm) DEEP EDM NOTCH EDGE SIGNAL 100%

0% LIFT--OFF SIGNAL BALANCE POINT 80% FSH

NOTE: Values listed in Figure 1 can vary between instruments.ba7988a01.cgm, kp, July 16, 2013

### APPENDIX A SERVICE BULLETIN 670BA ---27 ---065

APPENDIX A Page A9 of A10 Nov 15/2013 Bombardier Aerospace Calibration Reference Standard AL 29-32 Figure 2 (Sheet 1 of 1) 3. 2. NOTES Material; 2024--T3, QQ--A--250/4. Finish surface or better. Penetrant inspect NDTM 51--20--08 Identification sticker, 0.125 in. (3.18 mm) letters black color. 1.

4 125

5. EDM notches shall have a tolerance of +/--0.001 in. (+/--0.025 mm). 3.75 in. (95.3 mm) 1.00 in. (25.4 mm)

0.040 in. (1.02 mm) 0.020 in. (0.51 mm) 0.008 in. (0.20 mm)

0.25 in. (6.4 mm) 0.75 in. (19.1 mm) 0.75 in. (19.1 mm)

1.50 in. (38.1 mm) 0.005 in. (0.13 mm) WIDE (TYPICAL)

4

4 4 4

for depth and +0.00/--0.002 in. (+0.000/--0.051mm) for width.ba7988a02.cgm, kp, July 16, 2013

### APPENDIX A SERVICE BULLETIN 670BA ---27 ---065

APPENDIX A Page A10 of A10 Nov 15/2013 Inspection Area and Typical Scan Path of Rudder Pedal Tubes at the Connecting Rod Fittings Figure 3 (Sheet 1 of 1) INSPECT THE EDGES OF THE 2 AFT TAPERED HOLES.

TUBE ROTATED FOR CLARITY. INSPECT AROUND THE 2 AFT TAPERED HOLES. TYPICAL SCAN PATH EXTENDING 0.250 IN. (6.35 mm) FROM THE HOLE Aba7988a03.cgm, kp, July 16, 2013THANK YOU FOR ANSWERING THIS EVALUATION FORM UPON COMPLETION OF THIS EVALUATION FORM/COMPLIANCE SHEET, FAX TO 450-476-7300 or email to CRJ_SB_Evaluation_Form@aero.bombardier.com 

### SERVICE BULLETIN EVALUATI ON FORM/COMPLIANCE SHEET (YOUR IDEAS WILL HELP US PROVIDE BETTER BULLETINS)
SERVICE BULLETIN : 670BA-27-065 ISSUE: NC

STRONGLY DISAGREE NEUTRAL AGREE STRONGLY DISAGREE AGREE
 Instructions to do the Service Bulletin were accurate. Comments: 

##     

 Illustration(s), figure(s), picture(s) and/or kit drawing(s) were helpful to carry out instructions. Comments: 

##     

 If a parts kit was required, did the kit contents received agree with the contents listed in the bulletin? Comments: 

##     

 Aircraft hands-on work was accomplished in estimated time. Comments: 

##     

 Overall, I was satisfied with this Service Bulletin. Comments: 

##     

PLEASE SUPPLY US WITH THE FOLLOWING DATA AND FAX TO (450) 476-7300: OPERATOR: NAME (Please print) SERVICE CENTER: TELEPHONE: AIRCRAFT SERIAL NO.: FACSIMILE: DATE OF SB INCORPOARTION