# BOMBARDIER 

# SERVICE BULLETIN

_____ Technical Publications THIS SERVICE BULLETIN IS SENTTO EACH OPERATOR. IF THE OPERATOR HAS LEASED AIRCRAFT, SEND THIS SERVICE BULLETIN TO THE LESSEE. IF THE OPERATOR HAS SOLD AIRCRAFT OR 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. ATA SYSTEM: 32-43 NUMBER: 601 R-32-11 0 

### SUBJECT: Landing Gear - Brake System - Installation of a Bracket to Prevent Connection ofthe Hydraulic Lines ofthe Brakes tothe Incorrect Swivel Assembly Ports 1. PLANNING INFORMATION A. Effectivity (1) Aircraft Affected:

Dec 19/2013 Service: CL-600-2B19 aircraft serial numbers 7003 thru 7067, 7069 thru 7990, and 8000 thru 8999. Production: There is no production effectivity at this time. NOTE: The instructions in this service bulletin are only applicable to the systems and parts installed at the time of delivery ofthe aircraft or as changed by Bombardier service bulletins. Before you dothis 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.

SB 601 R-32-11 0 Page 1 of 16

### SERVICE BULLETIN 601R-32-110
B. Reason (1) Condition The inboard and the outboard hydraulic lines ofthe brakes can be connected to the incorrect port on the swivel assembly ofthe Main Landing Gear (MLG). The incorrect installation ofthe brake hydraulic lines can cause the brakes and/orthe anti-skid system to operate incorrectly. {2) Evidence During in-service maintenance, some inboard and outboard hydraulic lines of the brakes were found connected to the incorrect ports on the swivel assembly ofthe MLG. (3) Objective/Benefit This service bulletin gives the procedure to install a new bracket on the left and the right lower aft wing-planks. The bracket will prevent the hydraulic brake lines to be connected tothe incorrect ports on the swivel assembly of the MLG. 

### C. Description The landing gear lockpins are installed. If necessary, the aircraft is put on jacks. The swivel assembly and the inboard brake hydraulic line installation is verified and changed if necessary. A bracket is installed on the left and the right lower aft wing-planks. Ifthe aircraft was put on jacks, the aircraft is removed from the jacks. The operational test ofthe brake system is done. 

### D. Compliance Recommended service bulletin. Bombardier recommends that this service bulletin be done at no more than 6600 flight hours from the release date on this service bulletin or before Mar 29/2017, whichever comes first, unless otherwise directed bythe airworthiness authority of the operator. For Business/Corporate operators (i.e. operators who do not have a commercial airline operation) , Bombardier recommends that this service bulletin be done no laterthan Mar 29/2017. This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage Tolerance Inspections {OTis) . 

### E. Approval The technical content ofthis service bulletin has been approved underthe authority ofthe TCCA Design Approval Organization No: DAO #93-Q-02. Dec 19/2013 SB 601 R-32-11 0 Page 2 of 16

### SERVICE BULLETIN 601 R-32-110
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, sealantto 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 speakwith a Fleet Services representative for a quote. Contactthe Fleet Services Team through the CRC at 514-855-8500 or e-mail at thd.crj@aero.bombardier.com. It will take an estimated 7.50 man-hours to complete this service bulletin. The man-hours are divided in the table thatfollows (elapsed cure time is not included in the man-hour summary given above): TASK (1) Job Set-Up (2) Procedure (3) Test (4) Job Close-Out

Dec 19/2013 MAN-HOURS 1.25 4.00 1.00 1.25

SB 601 R-32-110 Page 3 of 16

### SERVICE BULLETIN 601R-32-110
G. Material - Price and Availability (1) The kits in the tables that follow are available from Bombardier. NOTE: For a list of kit contents, refer to paragraph 3.A. KIT NUMBER NAME 601 R32-11 OK1 Anti Brake Line Inversion Kit (2) Please send a purchase order to the address below to schedule kit delivery: Bombardier Service Bulletin Kit SupportTeam 123 Garratt Blvd, N42-24 Toronto, Ontario Canada M3K 1 Y5 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. (3) The parts in the table thatfollows can be necessary to dothis service bulletin if kit 601 R32-11 OK1 is not used and are available from Bombardier. PART NUMBER NAME QTY B0206002AG6-6 Hi-Lite Pin 5 B0203013-3 Collar 5 HST111AG6-6 Hi-Lite Pin (1st oversize) 5

B0203038-3 Collar (1st oversize) 5

Dec 19/2013 SB 601 R-32-11 0 Page 4 of 16

### SERVICE BULLETIN 601 R-32-110 (4) Please send a purchase orderto the address belowto schedule part delivery: Bombardier Service Bulletin Kit Support Team 123 Garratt Blvd, N42-24 Toronto, Ontario Canada M3K 1 Y5 Fax: 416-375-3060 Phone: 416-375-3920 e-mail: sbkits@aero.bombardier.com Please contact the Service Bulletin Kit SupportTeam atthe address above for terms and conditions. (5) Refer to paragraph 3.B. for a list ofconsumables for this service bulletin. For Business/Corporate Operators All Business/Corporate operators (i.e. operators who do not have a commercial airline operation) refer to SB 800-00-004 for commercial policy coverage and logistics/planning arrangements (refer to www.cic.bombardier.com/technical library/service bulletins/challenger/850/SB 800-00-004). To place an orderfor parts or kits, please call Bombardier Parts Logistics at 514-855-2999 or 1-866-538-1247. H. Tooling - Price and Availability There are notool kits for this service bulletin. Refer to paragraph 3.C. for a list of special tools and equipmentfor this service bulletin. 

### I. Weight and Balance Not changed. 

### J. Electrical Load Data Not changed. K. References Refer tothe SB Introduction documentfor definition or explanation of service bulletin content. Restriction and/or Special Instruction (RSI) C-A284 Modification SummaryTC601 R18330, Revision B Aircraft Maintenance Manual (AMM) Structural Repair Manual (SRM) For Bombardier reference only: PCA 6666 Dec 19/2013 SB 601 R-32-11 0 Page 5 of 16

### SERVICE BULLETIN 601R-32-110
L. Other Publications Affected None. 

### M. Relationship Chart Not applicable.

Dec 19/2013 SB 601 R-32-11 0 Page 6 of 16

### SERVICE BULLETIN 601 R-32-110
2. ACCOMPLISHMENT INSTRUCTIONS Reference Information 

### REFERENCE DESIGNATION AMM 07-11-01-582-801 Put the Aircraft on Jacks AMM 07-11-01-582-804 Removal ofthe Aircraft from Jacks AMM 10-11 -00-400-801 Installation ofthe Nose Landing Gear Lockpin AMM 10-11 -00-400-802 Installation ofthe Main Landing Gear Lockpins AMM 32-11-20-400-801 Installation ofthe Upper Brake Swivel Assembly AMM 32-43-00-710-801 Operational Test ofthe Brake System SAM 51-23-00 Pressure, Environmental, Fuel Tank and Firewall Sealing SAM 51-25-06 Fluid-Resistant (FR) Epoxy Primer SAM 51-25-16 Fluid-Resistant (FR) Polyurethane Topcoat SAM 51-26-00 Cleaning SAM 51-42-21 Hi-Lite Fasteners Tolerance Information Linear Tolerances Angular Tolerance X.XX in. (X.X mm) X.X in. (X mm) 

### +I-0.03 in. +/- 0.1 in. +/-0° 30" 

### +I- 0.8 mm 

### +I- 3 mm NOTE: The tolerances above apply to the dimensions given in this service bulletin, except when specified differently.

Dec 19 /2013 SB 601 R-32-11 0 Page 7 of 16

### SERVICE BULLETIN 601 R-32-110
A. Job Set-Up 

### (1) Make sure that the NLG and MLG lockpins are installed (refer to AMM 10-11-00-400-801 and 10-11-00-400-802). (2) If necessary, put the aircraft on jacks (refer to AMM 07-11-01-582-801). B. Procedure 

### NOTE: This procedure is applicableto 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) Make sure the forward port ofthe swivel assembly points down, in the direction ofthe lower aft wing-plank. (2) Make sure that the hydraulic line ofthe inboard brake is connected to the forward port ofthe swivel assembly. (3) If necessary, align the swivel assembly and connect the hydraulic line ofthe inboard brake to the forward port ofthe swivel assembly (refer to AMM 32-11-20-400-801) . (4) Clean the work area with solvent (referto SAM 51-26-00). (5) Remove and discard the Hi-Lite pins (1) and the collars (2) from the lower aft wing-plank and the lower wing skin. (6) Install the laminated shim (3) and the bracket (4) as follows: NOTE: The laminated shim (3) and the bracket (4) can be made as shown in Appendix A ofthis service bulletin or are available from Bombardier (kit number 601 R32-110K1) . (a) Peel the laminated shim (3) until the bracket (4) sits flat on the lower aft wing-plank. (b) Temporarily secure the laminated shim (3) and the bracket (4) to the lower aft wing-plank as follows: NOTE: A minimum edge distance of 1.50 is necessary. 

### 1 Put the laminated shim (3) and the bracket (4) on the lower aft wing-plank as follows: Dec 19/2013 SB 601 R-32-11 0 Page 8 of 16

### SERVICE BULLETIN 601R-32-110

f! Make sure that the forward and aft edges ofthe laminated shim (3) are aligned with the forward and aft edges ofthe bracket (4) . .Q Make sure that the inboard edge ofthe laminated shim (3) and the inboard edge ofthe bracket (4) are aligned with the inboard edge ofthe lower aft wing-plank. .Q Make sure there is a clearance of 0.25 in. (6.4 mm) between the aft edge ofthe bracket (4) and the mounting trunnion of the MLG, as shown on Sheet 3, View D . 

### .Q Make sure that there is a minimum clearance of0.130 in. (3.30 mm) between the forward edge of the bracket (4) and the fitting ofthe hydraulic line, as shown on Sheet 3, View D. 

### 2 Measure the diameter ofthe two holes in the lower aft wing-plank and the lower wing skin where the two Hi-Lite pins (1) were removed.**~** Ifthe diameter of one orthe two holes in the lower aft wing-plank and/orthe lower wing skin is/are 0.1850 in. (4.699 mm) or more, do as follows: f! Backdrill the hole(s) from the lower aft wing-plank and the lower wing skin to the laminated shim (3) and the bracket (4). .Q Increasethe diameter ofthe hole(s) to 0.1981-0.2011 in. (5.032-5.108 mm) in the lower aft wing-plank, the lower wing skin, the laminated shim (3) , and the bracket (4). 

### 1 If the diameter of one orthe two holes in the lower aft wing-plank and/orthe lower wing skin is/are less than 0.1850 in. (4.699 mm) , do as follows: f! Backdrill the hole(s) from the lower aft wing-plank and the lower wing skin to the laminated shim (3) and the bracket (4). .Q Increase the diameter ofthe hole(s) to 0.1850-0.1880 in. (4.699-4.775 mm) in the lower aft wing-plank,the lower wing skin,the laminated shim (3) , and the bracket (4). (c) Remove the laminated shim (3) and the bracket (4). (d) Remove burrs and sharp edges from the laminated shim (3) and the bracket (4) . Dec 19/2013 SB 601 R-32-110 Page 9 of 16

### SERVICE BULLETIN 601R-32-110 (e) If necessary, remove burrs and sharp edges from the lower aft wing-plank and the lower wing skin. 

### (f) Clean the work area with solvent (refer to SRM 51-26-00). (g) Do the final installation ofthe laminated shim (3) and the bracket (4) on the lower aft wing-plank as follows: 

### 1 Apply faying surface sealant on the mating surface ofthe bracket (4) (refer to SRM 51-23-00). 

### .2 Applyfaying surface sealant on the mating surface ofthe laminated shim (3) (refer to SRM 51-23-00). .3_ Install the laminated shim (3) and the bracket (4) on the lower aft wing-plank with the Hi-Lite pins (5) wet with sealant with their heads on the lower side and the collars (6) (refer to SRM 51-23-00 and SRM 51-42-21). 

### 1 Apply injection sealant on the area between the laminated shim (3), the bracket (4), and the radius ofthe lower aft wing-plank, as shown on Sheet 3, View C (refer to SRM 51-23-00).

**~** Apply fluid-resistant primertothe head ofthe Hi-Lite pins (5) and the collars (6) (refer to SRM 51-25-06). .Q Apply polyurethane topcoatto the head ofthe Hi-Lite pins (5) and the collars (6) (refer to SRM 51-25-16) . 

### C. Job Close-Out (1) Remove all tools, equipment, and unwanted materials from the work area. (2) Ifthe aircraft was put on jacks, remove the aircraft from the jacks (refer to AMM 07-11 -01 -582-804) . (3) Do the operational test ofthe brake system (refer to AMM 32-43-00-710-801). (4) When this service bulletin is completed , make this entry in the applicable logbooks: "Service Bulletin 601 R-32-11 0, Landing Gear - Brake System - Installation of a Bracket to Prevent Connection ofthe Hydraulic Lines ofthe Brakes to the Incorrect Swivel Assembly Ports."

Dec 19/2013 SB 601 R -32-11 0 Page 10 of 16

### SERVICE BULLETIN 601 R-32-110

NOTE 1. Left side shown, right side opposite.

Dec 19/2013 

## I 

## I I I BRAKE OUTBOARD HYDRAULIC LINE (REF)



### 0 AFT PORT (REF) SWIVEL ASSEMBLY (REF)

FORWARD PORT (REF)

BRAKE INBOARD 

# ® HYDRAULIC LINE (REF) Swivel**A~sembly-** Bracket Installation F1gure 

### 1 (Sheet 

### 1 of 4) SB 601 R-32-11 0 Page 11 of 16

### SERVICE BULLETIN 601R-32-110

NOTES 1 . Left side shown, right side opposite. 2. Some hydraulic lines are not shown for clarity. 

# 0 LEGEND 1 . Pin, Hi-Lite. 2. Collar.

Dec 19/2013 

# ® PRE-MOD VIEW LOOKING FORWARD IN LEFT MLG BAY

BRAKE INBOARD / HYDRAULIC LINE (REF)



## ----

Swivel Assembly- Bracket Installation Figure 1 (Sheet 2 of 4) SB 601 R-32-11 0 Page 12 of 16

### SERVICE BULLETIN 601 R-32-110

® 3. Laminated shim 601 R75318-1 or K601 R75217-5. 4. Bracket ® 601 R75317-1 or K601 R75217-3 (LH). 601 R75317-2 or K601 R75217-4 (RH). 5. Pin, Hi-Lite B0206002AG6-6. ® 6. Collar B0203013-3.

VIEW LOOKING FORWARD SWIVEL IN LEFT MLG BAY ASSEMBLY NOTES 1. Left side shown, right side opposite. 2. Some hydraulic lines are not shown for clarity. 

# ffi It is necessary for the inboard edge ofthe bracket and the laminated shim to be aligned with the inboard edge of the lower aft wing plank. 

# & It is permitted to install 1st oversize Hi-Lite pin HST111AG6-6 and collar B0203038-3.

POST-MOD / (REF) FORWARD PORT (REF)

BRAKE INBOARD HYDRAULIC LINE

# ~ 

# (R/**~~ 6&** 

® Swivel Assembly - Bracket Installation Figure 1 (Sheet 3 of 4) Dec 19/2013 SB 601 R-32-11 0 Page 13 of 16

### SERVICE BULLETIN 601 R-32-110



# ® LEGEND 3. Laminated shim 601 R75318-1 or K601 R75217-5. 4. Bracket 601R75317-1 or K601R75217-3 (LH) . 601 R75317-2 or K601 R75217-4 (RH). NOTES 1 . Left side shown, right side opposite. 2. Some hydraulic lines are not shown for clarity. 

# ffi It is necessary for the inboard edge of the bracket and the laminated shim to be aligned with the inboard edge ofthe lower aft wing plank. 

# & A minimum clearance of 0.130 in. (3.30 mm) is necessary between the bracket and the brake inboard hydraulic fitting. 

# & Injection sealant between laminated shim, bracket, and lower aft wing plank radius.

SWIVEL ASSEMBLY (REF)

4 BRAKE INBOARD HYDRAULIC LINE (REF) / /

# c==:~=**Jt~** LOWER AFT WING PLANK (REF) 

# 3&

4 

# & I t LOWER WING SKIN (REF)

0.25 in. (6.4 mm) Swivel Assembly - Bracket Installation Figure 1 (Sheet 4 of 4) Dec 19/2013 SB 601 R-32-11 0 Page 14 of 16

### SERVICE BULLETIN 601R-32-110

3. MATERIAL INFORMATION 

### A. Kit Information Kit Contents: KIT 601 R32-11OK1 [I] PART NUMBER QTY NAME ALTERNATE PARTS 601 R75317-1 1 Bracket (LH) K601 R75217-3 601 R75317-2 1 Bracket (RH) K601 R75217-4 601 R75318-1 2 Laminated shim K601 R75217-5 B0206002AG6-6 5 Pin, Hi-Lite - HST111AG6-6 5 Pin, Hi-Lite - (1st oversize) B0203013-3 5 Collar

- B0203038-3 5 Collar - (1st oversize) 

# rn The kit can contain more hardware and/or material than necessary. NOTE: For allowable 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 ofthis service bulletin are supplied in atemporary condition ofsupply configuration. These parts are identified with a -SB,/SB, SB or other suffix afterthe Bombardier engineering part number. When the parts are installed, with the instructions given in the Accomplishment Instructions ofthis service bulletin,the parts agree with the requirements of the engineering configuration. Refer to the SB Introduction documentfor more explanation.

Dec 19/2013 SB 601 R-32-11 0 Page 15 of 16

### SERVICE BULLETIN 601R-32-110
B. Consumable Information The materials that follow are necessaryto dothis service bulletin. You can order them from Bombardier or purchased directlyfrom industry sources. Ifthe material is ordered from Bombardier, there can be some lead time because ofthe shelf life ofthe material. CONSUMABLES SPECIFICATION QTY NAME REFERENCE AMS QQ-A-250/5 As Aluminum sheet - (AL 2024 T3) 

### OJ necessary (0.080 in. thick) AMS DTL-22499/1 , As Shim Stock, - Type 1 , Class 2 

### OJ necessary Laminated, Aluminum Alloy (0.125 in. thick) 

### OJ These materials are not necessary if kit 601 R32-11 OK1 is ordered. NOTE: To complete this list of consumables, refer to the differenttasks that are given as references in this service bulletin C. Special Tools and Equipment There are no special tools and equipmentfor this service bulletin . D. Disposition of Parts Not applicable.

Dec 19/2013 SB 601 R-32-11 0 Page 16 of 16

# BOMBARDIER

APPENDIX A SERVICE BULLETIN 601 R-32-110

Landing Gear - Brake System - Installation of a Bracketto Prevent Connection ofthe Hydraulic Lines ofthe Brakestothe Incorrect Swivel Assembly Ports

Dec 19/2013The procedure contained in this appendix is given as reference in the Accomplishment Instructions of Service Bulletin 601 R-32-11 0.

APPENDIX A Page A1 ofA3

### APPENDIX A SERVICE BULLETIN 601 R-32-110

1 .75 in. (44.5 mm)

NOTES 0.80 in. (20.3 mm)

SHIM K601R75217-5 R 0.35 in. (8.9 mm) 4 PLACES

1. Use AMS-DTL-22499/1,Type 1, Class 2 (0.125 in. (3.18 mm) thick) . 2. Make per SRM 51-24-36. 3. Break sharp edges. 4. Identify with ink per shop best practice. Shim Figure A1 (Sheet 1 of 2) Dec 19/2013 APPENDIX A Page A2 ofA3

### APPENDIX A SERVICE BULLETIN 601R-32-110

R 0.88 in. (22.4 mm) 2 PLACES 1.86 in. (47.2 mm)

- ------1 R 0.35 in. (8.9 mm) 4 PLACES R 0.13 in. (3.3 mm) 0.80 in. (20.3 mm) FLG UP X goo 0.63 in. 

## =:j (16.0 mm) I**~- ---=:--** **------:1"--- -.---**  2 PLACES X R 0.38 in. (9.7 mm)

0.75in. (19.1 mm)


# I 0.80 in. (20.3 mm)

NOTES BKL ML

3.54 in. (89.9 mm)

--------i BRACKET FLAT PATTERN K601 R75217-3 (LH) SHOWN

K601 R75217-4 (RH) OPP

1---
- 3.00 in. (76.2 mm) ± 0.06 in. (1.5mm)

# __J BRACKET FOLDED PART K601 R75217-3 (LH) SHOWN

K601 R75217-4 (RH) OPP 1 .75 in. (44.5 mm)

0.67 in. (17.0 mm)

1 . Use AL alloy 2024-T3 clad sheet perAMS-QQ-A-250/5 (0.080 in. (2.03 mm) thick) . 2. Make per SRM 51-24-36, 51-24-16 and 51-24-21 . 3. Break sharp edges. 4. Finish per SRM 51-21-16finish code A023. 5. Polyurethane topcoat color grey number #16473 per FED-STD-595. 6. Identify with ink per shop best practice. Bracket Figure A 1 (Sheet 2 of 2) Dec 19/2013 APPENDIX A Page A3 ofA3

# BOMBARDIER SERVICE BULLETIN FEEDBACK FORM/COMPLIANCE SHEET (YOUR COMMENTS HELP US WRITE BETTER SERVICE BULLETINS) Service Bulletin No.: 601 R-32-110 Revision:-- Aircraft Serial Number: Date: STRONGLY DISAGREE AGREE STRONGLY DISAGREE AGREE 

### Instructionsto dothe service bulletin are 

# 0 0 0 0 accurate. Comments: Figure(s), picture(s), and/orAppendix 

# 0 0 0 0 were helpful to dothe service bulletin. Comments: Part(s) or kit(s) agreed with the service 

# 0 0 0 0 bulletin requirement. Comments: The service bulletin was accomplished 

# 0 0 0 0 within the estimated time given. Comments: Overall, I was satisfied with this service 

# 0 0 0 0 bulletin. Comments: Operator: Service Centre: Name: Telephone or Fax: FAX your comments orfeedbackto (450) 476-7300 or e-mail to crj_sb_evaluation_form@aero.bombardier.com THANK YOU FOR YOUR COMMENTS