BOMBARDIER 

SERVICE BULLETIN _____ Technical 

Publications 

THIS SERVICE BULLETIN IS SENT TO 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 of the Hydraulic Lines of the Brakes to the 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 of the aircraft or as 

changed by Bombardier service bulletins. Before you do this service 

bulletin, examine all Supplemental Type Certificates (STCs), and 

Supplemental Type Approvals (STAs) or equivalent action changes 

to make sure you can complete this service bulletin. 

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 of the brakes can be connected 

to the incorrect port on the swivel assembly of the Main Landing Gear (MLG). 

The incorrect installation of the brake hydraulic lines can cause the brakes 

and/or the 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 of the 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 to the 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. If the aircraft was put on jacks, the aircraft is removed from the jacks. 

The operational test of the 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 by the 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 

later than Mar 29/2017. 

This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage 

Tolerance Inspections {OTis). 

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. 

Dec 19/2013 SB 601 R-32-11 0 

Page 2 of 16 
SERVICE BULLETIN 601 R-32-11 0 

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 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 that follows (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-32-11 0 

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 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 Support Team at the address above for 

terms and conditions. 

(3) The parts in the table that follows can be necessary to do this 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 

HST111 AG6-6 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 order to the address below to 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 Support Team at the address above for 

terms and conditions. 

(5) Refer to paragraph 3.B. for a list of consumables 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 order for parts or kits, please call Bombardier Parts Logistics at 

514-855-2999 or 1-866-538-1247. 

H. Tooling - Price and Availability 

There are no tool kits for this service bulletin. Refer to paragraph 3.C. for a list of 

special tools and equipment for this service bulletin. 

I. Weight and Balance 

Not changed. 

J. Electrical Load Data 

Not changed. 

K. References 

Refer to the SB Introduction document for definition or explanation of service 

bulletin content. 

Restriction and/or Special Instruction (RSI) C-A284 

Modification Summary TC601 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-32-11 0 

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 of the Aircraft from Jacks 

AM M 1 0-11 -00-400-801 Installation of the Nose Landing Gear Lockpin 

AM M 1 0-11 -00-400-802 Installation of the Main Landing Gear Lockpins 

AMM 32-11-20-400-801 Installation of the Upper Brake Swivel Assembly 

AMM 32-43-00-710-801 Operational Test of the 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-32-11 0 

A. Job Set-Up 

(1) Make sure that the NLG and MLG lock pins 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 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) Make sure the forward port of the swivel assembly points down, in the 

direction of the lower aft wing-plank. 

(2) Make sure that the hydraulic line of the inboard brake is connected to the 

forward port of the swivel assembly. 

(3) If necessary, align the swivel assembly and connect the hydraulic line of the 

inboard brake to the forward port of the swivel assembly (refer to AMM 

32-11-20-400-801). 

(4) Clean the work area with solvent (refer to 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 of this 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 of the laminated 

shim (3) are aligned with the forward and aft edges of the 

bracket (4) . 

.Q Make sure that the inboard edge of the laminated shim (3) 

and the inboard edge of the bracket (4) are aligned with the 

inboard edge of the lower aft wing-plank . 

.Q Make sure there is a clearance of 0.25 in. (6.4 mm) between 

the aft edge of the 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 of 0.130 in. 

(3.30 mm) between the forward edge of the bracket (4) and 

the fitting of the hydraulic line, as shown on Sheet 3, View D. 

2 Measure the diameter of the two holes in the lower aft wing-plank 

and the lower wing skin where the two Hi-Lite pins (1) were 

removed. 

~ If the diameter of one or the two holes in the lower aft wing-plank 

and/or the 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 Increase the diameter of the hole(s) to 0.1981-0.2011 in. 

(5.032-5.1 08 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 or the two holes in the lower aft wing-plank 

and/or the 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 of the 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-32-11 0 

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 of the laminated shim (3) and the bracket (4) on 

the lower aft wing-plank as follows: 

1 Apply faying surface sealant on the mating surface of the bracket 

(4) (refer to SRM 51-23-00) . 

.2 Apply faying surface sealant on the mating surface of the 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 of the lower aft wing-plank, as 

shown on Sheet 3, View C (refer to SRM 51-23-00). 

~ Apply fluid-resistant primer to the head of the Hi-Lite pins (5) and 

the collars (6) (refer to SRM 51-25-06) . 

.Q Apply polyurethane topcoat to the head of the 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) If the aircraft was put on jacks, remove the aircraft from the jacks (refer to 

AMM 07-11 -01 -582-804). 

(3) Do the operational test of the 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 of the Hydraulic Lines of the 

Brakes to the Incorrect Swivel Assembly Ports." 

Dec 19/2013 SB 601 R-32-11 0 

Page 10 of 16 
SERVICE BULLETIN 601 R-32-11 0 

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-32-11 0 

® 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 

of the 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-32-11 0 

® 

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 of the 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 R32-11 OK1 [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 -

HST111 AG6-6 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 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. 

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 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 

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 different tasks that are 

given as references in this service bulletin 

C. Special Tools and Equipment 

There are no special tools and equipment for 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-32-11 0 

Landing Gear - Brake System - Installation of a Bracket to Prevent Connection of the 

Hydraulic Lines of the Brakes to the Incorrect Swivel Assembly Ports 

Dec 19/2013 

The 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 of A3 
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 A 1 (Sheet 1 of 2) 

Dec 19/2013 APPENDIX A 

Page A2 of A3 
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 per AMS-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 51-21-16 finish 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 of A3 
BOMBARDIER 

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Service Bulletin No.: 601 R-32-11 0 Revision:--

Aircraft Serial Number: Date: 

STRONGLY DISAGREE AGREE STRONGLY 

DISAGREE AGREE 

Instructions to do the service bulletin are 0 0 0 0 accurate. 

Comments: 

Figure(s), picture(s), and/or Appendix 0 0 0 0 

were helpful to do the service bulletin. 

Comments: 

Part(s) or kit(s) agreed with the service 0 0 0 0 bulletin requirement. 

Comments: 

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Comments: 

Overall, I was satisfied with this service 0 0 0 0 bulletin. 

Comments: 

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Name: Telephone or Fax: 

FAX your comments or feedback to (450) 476-7300 

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