# Bombardier Service Bulletin 601R-32-110

## Copies (2)

Copies the FAA filed in AD dockets on regulations.gov, newest revision first. A newer revision may exist.

- Revision C ("SB 601R-32-110 Rev C"), 44 pages: PDF https://openairdocs.org/files/sha256/a9/af/a9af1650c01111233910cae580470c9ad5189ff36c1e3dc50e94d3bf029f0523; text https://openairdocs.org/service-documents/bombardier/601r-32-110/file/a9af1650c011.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2016-9190; AD 2017-04-02 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- U.S. DOT/FAA - Service Bulletin 601R-32-110 ("U.S. DOT/FAA - Service Bulletin 601R-32-110"), 20 pages: PDF https://openairdocs.org/files/sha256/b5/91/b591069ba044acc502d5da489e76fcaa1acb4798205a5d1ec2668784e5e4a70e; text https://openairdocs.org/service-documents/bombardier/601r-32-110/file/b591069ba044.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2014-0489; AD 2014-23-06 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Bombardier](https://openairdocs.org/service-documents/bombardier.md)
- Type: Service bulletin (Service Bulletin)
- Number: 601R-32-110
- Latest revision known: 601R-32-110, Revision C, dated May 4, 2016 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/bombardier/601r-32-110

## ADs that cite it (2) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2017-04-02](https://openairdocs.org/ad/2017-04-02.md), effective Mar 28, 2017: Revisions A, B, C and NC
- [AD 2014-23-06](https://openairdocs.org/ad/2014-23-06.md), effective Dec 26, 2014: No revision named

Also cited in [2 proposed ADs](https://openairdocs.org/service-documents/bombardier/601r-32-110/proposed.md).

## Text (44 pages)

Revision C, the newest copy. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2016-9190; AD 2017-04-02 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

the evolution of mobility
SB 601R- - - 32- - - 110
Page 1 of 1
May 04/2016
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
CL- - -600- - -2B19 Canadair Regional Jet (CRJ) Aircraft
SERVICE BULLETIN 601R - - -32 - - -110
SUBJECT : Landing Gear - - - Brake System - - - Installation of a Block on the Left and the
Right Lower-Aft Wing Planks to Prevent Connection of the Hydraulic Lines
of the Brakes to the Incorrect Swivel Assembly Ports
This page transmits:
Revision C of Service Bulletin 601R- - - 32- - - 110, dated May 04/2016
and
Revision A of Appendix A, dated Oct 29/2015.
For aircraft that have had the initial issue of this service bulletin
incorporated, it is necessary to do PART B of this service bulletin.
The changes in this revision have no effect on aircraft that have had
Revision A or B of this service bulletin incorporated.
Reason:
Revised Accomplishment Instructions, paragraph 2., to:
Add a caution
Change a step
Change some illustrations.
This revision also includes small editorial changes that do not have an effect on the technical
content.
Instructions:
Discard the copy of Service Bulletin 601R- - - 32- - - 110 dated Jan 26/2016. Replace with the
copy attached.
Service Bulletin History:
Initial issue, dated Dec 19/2013
Revision A, dated Oct 29/2015
Revision B, dated Jan 26/2016
1

### Page 2

the evolution of mobility
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 1 of 38
SERVICE BULLETIN
T echnical
Publications
THIS SERVICE BULLETIN IS SENT TO EACH OPERATOR. IF THE OPERATOR HAS LEASED AIRCRAFT ,
TRANSFERRED SPARES IN THE LAST SIX MONTHS, SEND THIS SERVICE BULLETIN TO THE NEW
OWNER, UNLESS CONFIRMATION WAS RECEIVED THAT BOMBARDIER HAS INCLUDED THE NEW
OPERATOR ON THE DISTRIBUTION LIST .
SEND THIS SERVICE BULLETIN TO THE LESSEE. IF THE OPERATOR HAS SOLD AIRCRAFT OR
ATA SYSTEM: 32- - -43 NUMBER: 601R - - -32- - -110
SUBJECT : Landing Gear - - - Brake System - - - Installation of a Block on the Left and the
Right Lower-Aft Wing Planks to Prevent Connection of the Hydraulic Lines
of the Brakes to the Incorrect Swivel Assembly Ports
1. PLANNING INFORMATION
A. Effectivity
(1) Aircraft Affected:
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.

### Page 3

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 2 of 38
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 block on the left and the
right lower aft wing-planks. The block will prevent the hydraulic brake lines to
be connected to the incorrect ports on the swivel assembly of the MLG.
C. Description
This service bulletin is divided into two parts: PART A and PART B.
For aircraft that have not had the initial issue of this service bulletin incorporated
PART A - - - Installation of a Block on the Left and the Right Lower Aft
Wing-Planks
The landing gear lockpins are installed. If necessary, the aircraft is put on jacks.
The left and the right swivel assembly and inboard brake hydraulic line installation
a r ee x a m i n e da n dc h a n g e di fn e c e s s a r y .Ab l o c ki si n s t a l l e do nt h el e f ta n dt h er i g h t
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.
For aircraft that have had the initial issue of this service bulletin incorporated
PART B - - - Removal of the Bracket and Installation of a Block on the Left and
the Right Lower Aft Wing-Planks
The landing gear lockpins are installed. If necessary, the aircraft is put on jacks.
The brackets are removed from the left and the right lower aft wing-planks. The left
and the right swivel assembly and inboard brake hydraulic line installation are
examined and changed if necessary. A block 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.

### Page 4

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 3 of 38
D. Compliance
Recommended service bulletin.
For aircraft that have not had the initial issue of this service bulletin incorporated
B o m b a r d i e rr e c o m m e n d st h a tP a r tAo ft h i ss e r v i c eb u l l e t i nb ed o n ea tn om o r e
than 4400 flight hours or no later than 24 months from the release date on Revision
A of this service bulletin, 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 24 months from the release date on Revision A of this service bulletin.
For aircraft that have had the initial issue of this service bulletin incorporated
B o m b a r d i e rr e c o m m e n d st h a tP a r tBo ft h i ss e r v i c eb u l l e t i nb ed o n ea tn om o r e
than 6600 flight hours or no later than 37 months from the release date on Revision
A of this service bulletin, 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 37 months from the release date on Revision A of this service bulletin.
For all aircraft
This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage
T olerance Inspections (DTIs).
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.
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.

### Page 5

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 4 of 38
F. M a n p o w e r
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.
FOR PART A
It will take an estimated 8.00 man-hours to complete PART A of this service bulletin.
The man-hours are divided in the table that follows (elapsed cure time is not
included in the man-hour summary given above):
TASK MAN-HOURS
(1) Job Set-Up 1.25
(2) Procedure 4.50
(3) T est 1.00
(4) Job Close-Out 1.25

### Page 6

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 5 of 38
FOR PART B
It will take an estimated 8.50 man-hours to complete PART B of this service bulletin.
The man-hours are divided in the table that follows (elapsed cure time is not
included in the man-hour summary given above):
TASK MAN-HOURS
(1) Job Set-Up 1.25
(2) Procedure 5.00
(3) T est 1.00
(4) Job Close-Out 1.25
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.
FOR PART A
KIT NUMBER NAME
601R32- - - 110K1A A n t iB r a k eL i n eI n v e r s i o nK i t
FOR PART B
KIT NUMBER NAME
601R32- - - 110K2 A n t iB r a k eL i n eI n v e r s i o nK i t
(2) Please send a purchase order to the address below to schedule kit delivery:
Bombardier
Service Bulletin Kit Support T eam
123 Garratt Blvd, N42- - - 24
T oronto, 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 T eam at the address above for
terms and conditions.

### Page 7

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 6 of 38
(3) As an alternative to kit 601R32- - - 110K1A, some parts can be made as shown
in Appendix A of this service bulletin. If kit 601R32- - - 110K1A is not used, the
parts in the table that follows can be necessary and are available from
Bombardier.
PART NUMBER NAME QTY
MS21042- - - 5 Nut 2
MS20426AD4- - - 9 Rivet, CSK 4
(4) As an alternative to kit 601R32- - - 110K2, some parts can be made as shown in
Appendix A of this service bulletin. If kit 601R32- - - 110K2 is not used, the parts
in the table that follows can be necessary and are available from Bombardier.
PART NUMBER NAME QTY
MS21042- - - 5 Nut 2
MS20426AD4- - - 9 Rivet, CSK 4
NAS1149D0316K Washer 8
NAS1149D0332K Washer 8
NAS1401- - - 3D5G Radius Washer 4
B0202032- - - 31NK Washer 8
B0202032- - - 31K Washer 4
B0203038- - - 3 Collar 4

### Page 8

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 7 of 38
(5) Please send a purchase order to the address below to schedule part delivery:
Bombardier
Service Bulletin Kit Support T eam
123 Garratt Blvd, N42- - - 24
T oronto, 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 T eam at the address above for
terms and conditions.
(6) 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).
T o place an order for parts or kits, please call Bombardier Parts Logistics at
514- - - 855- - - 2999 or 1- - - 866- - - 538- - - 1247.
H. T ooling - - - 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, Revision C
Modification Summary TC601R18330, Revision B- - - 1
Modification Summary TC601R18436, Revision B
Aircraft Maintenance Manual (AMM)
Structural Repair Manual (SRM)
For Bombardier reference only: PCA 6666

### Page 9

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 8 of 38
L. Other Publications Affected
Aircraft Maintenance Manual (AMM)
Maintenance Requirements Manual (MRM)
M. Relationship Chart
FOR PART A
Not applicable.
FOR PART B
PRE-SB
PART NUMBER NAME POST-SBPART NUMBER NAME
601R75317- - - 1
OR
K601R75217- - - 3
Bracket (LH) K601R75319- - - 5 Block (LH)
601R75317- - - 2
OR
K601R75217- - - 4
Bracket (RH) K601R75319- - - 6 Block (RH)

### Page 10

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 9 of 38
2. ACCOMPLISHMENT INSTRUCTIONS
For aircraft that have not had the initial issue of this service bulletin incorporated
PART A - - - Installation of a Block on the Left and the Right Lower Aft Wing-Planks
Reference Information
REFERENCE DESIGNATION
A M M 0 7 --- 1 1 --- 0 1 --- 5 8 2 --- 8 0 1 Put the Aircraft on Jacks
A M M 0 7 --- 1 1 --- 0 1 --- 5 8 2 --- 8 0 4 Removal of the Aircraft from Jacks
A M M 1 0 --- 1 1 --- 0 0 --- 4 0 0 --- 8 0 1Installation of the Nose Landing Gear Lockpin
A M M 1 0 --- 1 1 --- 0 0 --- 4 0 0 --- 8 0 2Installation of the Main Landing Gear Lockpins
A M M 3 2 --- 1 1 --- 2 0 --- 4 0 0 --- 8 0 1Installation of the Upper Brake Swivel Assembly
A M M 3 2 --- 4 3 --- 0 0 --- 7 1 0 --- 8 0 1 Operational T est of the Brake System
S R M 5 1 --- 2 1 --- 1 6 Finish Codes
S R M 5 1 --- 2 3 --- 0 0 Pressure, Environmental, Fuel T ank and Firewall
Sealing
S R M 5 1 --- 2 6 --- 0 0 Cleaning
S R M 5 1 --- 4 0 --- 1 1 How to Prepare Fastener Holes
S R M 5 1 --- 4 2 --- 0 6 Solid Rivets
S R M 5 1 --- 4 2 --- 2 1 Hi-Lite Fasteners
T olerance Information
Linear T olerances Angular T olerance
X.XX in. (X.X mm) X.X in. (X mm)
+ / --- 0˚ 30”+/- - - 0.03 in. +/--- 0.1 in.
+ / --- 0 . 8 m m + / --- 3 m m
NOTE: The tolerances above apply to the dimensions given in this service
bulletin, except when specified differently.

### Page 11

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 10 of 38
A. Job Set-Up
NOTE: The steps in the Job Set-Up section of this service bulletin are
recommended steps. The steps give a recommendation to get access
to the work area. This recommendation is to give a safe work area and
to minimize possible damage to surrounding aircraft parts. Alternative
steps can be used at the operator discretion.
(1) 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 applicable to the left and the right sides. The procedure
that follows is written for the left side. The differences are given.
(1) If it is not possible to complete all the instructions in this service bulletin
because of the configuration of the aircraft, speak with a representative of
Bombardier in the CRC at 1- - - 844- - - 272- - - 2720 (1- - - 844- - - CRC - - - CRC0) or
1- - - 514- - - 855- - - 8500 or e-mail at thd.crj@aero.bombardier.com for analysis
and to get an approved disposition to complete this service bulletin.
Refer to Figure 1.
(2) Make sure the forward port of the swivel assembly points down, in the
direction of the lower aft wing-plank.
(3) Make sure that the hydraulic line of the inboard brake is connected to the
forward port of the swivel assembly.
(4) 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).
Refer to Figure 2.
(5) Make index lines on the block (1) as follows:
( a ) O nt h eu p p e ra f ts u r f a c ea n do nt h ea f te d g eo ft h eb l o c k( 1 ) ,m a k ea
line with a marker at 0.96 in. 0.06 in. (24.4 mm 1.5 mm) from the
inboard edge of the block (1).
( b ) O nt h eu p p e ra f ts u r f a c ea n do nt h ea f te d g eo ft h eb l o c k( 1 ) ,m a k ea
line with a marker at 1.81 in. 0.06 in. (46.0 mm 1.5 mm) from the
inboard edge of the block (1).

### Page 12

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 11 of 38
Refer to Figure 3.
CAUTION: DO NOT USE METAL SCRAPERS TO REMOVE DIRT . IF YOU DO
THIS, YOU CAN DAMAGE THE SURFACES.
(6) If there is dirt in the work area, remove it with a vacuum and/or a nonmetallic
scraper .
(7) Remove and discard the nut (1). Do not remove the Hi-Lite pin.
( 8 ) C l e a n t h e w o r k a r e a w i t h s o l v e n t ( r e f e r t o S R M 5 1 --- 2 6 --- 0 0 ) a n d a s f o l l o w s :
(a) Do a precleaning of the work area with isopropyl alcohol or MIL-PRF-680
solvent.
(b) Do a final cleaning of the work area (refer to SRM 51- - - 26- - - 00).
Refer to Figure 4.
(9) T emporarily install the block (1), the retainer (3), and the laminated shim (2)
on the lower aft wing-plank and trunnion as follows:
(a) Put the block (1) on the lower aft wing-plank and against the trunnion.
NOTE: It is necessary for the block (1) to be against the trunnion at the
forward and outboard point, and between the index lines.
(b) Make sure there is a minimum clearance of 0.080 in. (2.03 mm) between
the forward edge of the block (1) and the fitting of the inboard brake
hydraulic line.
(c) If an oversize Hi-Lite pin is installed where the retainer (3) will be
attached to the trunnion, do the steps that follow:
1 For a 1st oversize Hi-Lite pin HST111AG10 or equivalent, increase
the diameter of the retainer (3) attachment hole to 0.328 - - - 0.332 in.
(8.33 - - - 8.43 mm).
2 For a 2nd oversize Hi-Lite pin HST411AG10 or equivalent, increase
the diameter of the retainer (3) attachment hole to 0.344 - - - 0.348 in.
(8.74 - - - 8.84 mm).
(d) Put the retainer (3) on the trunnion and above the block (1) with the
Hi-Lite pin through the retainer (3) attachment hole.
NOTE: It is permitted to have threads of the Hi-Lite pin in the retainer (3)
attachment hole.
(e) Align the most inboard edge of the retainer (3) with the inboard edge of
the block (1).

### Page 13

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 12 of 38
(f) With the retainer (3) flat on the trunnion, peel the laminated shim (2) to fill
the gap between the block (1) and the retainer (3).
NOTE: With the laminated shim (2) on the block (1), it is permitted to have
a maximum clearance of 0.005 in. (0.13 mm) between the
laminated shim (2) and retainer (3).
(g) Put the laminated shim (2) between the block (1) and the retainer (3).
(h) Align the inboard, outboard, and forward edges of the laminated shim
(2) with the edges of the retainer (3).
(i) Align the inboard edges of the laminated shim (2) and the retainer (3)
with the inboard edge of the block (1).
(10) Drill two holes for the rivets (4) as follows:
CAUTION: THE RIVETS (4) ARE INSTALLED THROUGH THE BLOCK (1), THE
LAMINATED SHIM (2) AND THE RETAINER (3) ONLY . THE RIVETS
(4) ARE NOT INSTALLED THROUGH THE LOWER AFT
WING-PLANK. DO NOT DRILL INTO THE WING-PLANK WHEN
YOU DRILL THE HOLES FOR THE RIVETS (4).
(a) Backdrill two holes for the rivets (4) to a diameter of 0.098 in. (2.49 mm)
from the retainer (3) to the laminated shim (2) and the block (1).
NOTE: For the rivets (4), a minimum edge distance of 2D is necessary.
(b) Increase the diameter of the two holes for the rivets (4), in the retainer
(3), the laminated shim (2), and the block (1) to 0.128 - - - 0.132 in. (3.25
- - - 3.35 mm).
(11) On the bottom of the block (1), do a countersink in the two holes for the rivets
(4) (refer to SRM 51- - - 40- - - 11).
(12) Increase the diameter of the retainer (3) attachment hole to 0.328 - - - 0.332 in.
(8.33 - - - 8.43 mm), or as follows if an oversize Hi-Lite pin is installed:
(a) For a 1st oversize Hi-Lite pin HST111AG10 or equivalent, increase the
diameter of the retainer (3) attachment hole to 0.344 - - - 0.348 in. (8.74 - - -
8.84 mm).
(b) For a 2nd oversize Hi-Lite pin HST411AG10 or equivalent, increase the
diameter of the retainer (3) attachment hole to 0.360 - - - 0.364 in. (9.14 - - -
9.25 mm).

### Page 14

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 13 of 38
(13) Remove burrs and sharp edges from the laminated shim (2), the block (1)
and the retainer (3).
(14) Apply finish code A044 on the retainer (3) attachment hole (refer to SRM
51- - - 21- - - 16).
(15) Prepare the faying surfaces of the block (1), the laminated shim (2) and the
retainer (3) for sealant as follows:
(a) Clean the faying surfaces with solvent (refer to SRM 51- - -26- - -00, final
cleaning prior adhesive bonding).
(b) Abrade the faying surfaces with a scotchbrite pad. Remove the gloss
finish but not the top coat.
(c) Clean the faying surfaces with solvent (refer to SRM 51- - -26- - -00 final
cleaning prior adhesive bonding).
(16) Assemble the block (1), the laminated shim (2) and the retainer (3) as follows:
(a) Apply faying surface sealant on the bottom and the top surfaces of the
laminated shim (2) (refer to SRM 51- - - 23- - - 00).
(b) Attach the retainer (3), the laminated shim (2), and the block (1) with the
r i v e t s ( 4 ) w e t w i t h s e a l a n t ( r e f e r t o S R M 5 1 --- 4 2 --- 0 6 a n d S R M
51- - - 23- - - 00).
(c) Apply finish code X186 on the rivets (4) (refer to SRM 51- - - 21- - - 16).
(17) T emporarily install the assembled block (1), laminated shim (2) and retainer
(3) on the lower aft wing-plank and trunnion with the forward and outboard
point of the block (1) against the trunnion.
(18) Make sure there is a minimum clearance of 0.080 in. (2.03 mm) between the
forward edge of the block (1) and the fitting of the inboard brake hydraulic
line.
(19) Remove the assembled block (1), laminated shim (2) and retainer (3).
(20) Do the final installation of the assembled block (1), laminated shim (2) and
retainer (3) as follows:
(a) Prepare the faying surfaces of the block (1), the retainer (3), the
trunnion, and the lower aft wing-plank for sealant as follows:
1 Clean the faying surfaces with solvent (refer to SRM 51- - - 26- - - 00,
final cleaning prior adhesive bonding).
2 Abrade the faying surfaces with a scotchbrite pad. Remove the
gloss finish but not the top coat.

### Page 15

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 14 of 38
3 Clean the faying surfaces with solvent (refer to SRM 51- - - 26- - - 00
final cleaning prior adhesive bonding).
(b) Apply faying surface sealant on the bottom surface of the retainer (3),
where it will be installed on the trunnion (refer to SRM 51- - - 23- - - 00).
(c) Apply faying surface sealant on the bottom surface of the block (1), on
the aft and outboard edge of the block (1) and on the fwd edge of the
trunnion (refer to SRM 51- - - 23- - - 00).
NOTE: It is necessary to use a sufficient amount of sealant to have it
squeeze out to fill the chamfer area of the block (1).
(d) Put the assembled block (1), laminated shim (2) and retainer (3) on the
lower aft wing-plank with the forward and outboard point of the block (1)
against the trunnion.
(e) Install and torque the nut (5) to 110- - - 140 lbf Sin. (12.43- - - 15.82 NSm)
( r e f e r t o S R M 5 1 --- 4 2 --- 2 1 )
NOTE: It is permitted to have threads of the Hi-Lite pin in the retainer (3)
attachment hole.
(f) Apply finish code X186 on the nut (5) (refer to SRM 51- - - 21- - - 16).
(g) Apply injection sealant between the block (1) and the retainer (3) (refer
t o S R M 5 1 --- 2 3 --- 0 0 ) .
(h) Apply sealant along the block (1) and the trunnion, from the outboard
edge of the retainer (3) to the forward and outboard point of the block
(1) (refer to SRM 51- - - 23- - - 00).

### Page 16

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 15 of 38
C. Job Close-Out
NOTE: The steps in the Job Close-Out section of this service bulletin, except for
the return-to-service tests, are recommended steps. The steps give a
recommendation to install components removed during the Job Set-Up.
This recommendation is to make sure that the aircraft is safe and ready
to return to service. Alternative steps can be used at the operator
discretion.
(1) Remove all tools, equipment, and unwanted materials from the work area.
(2) 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 601R- - - 32- - - 110, Revision C, Landing Gear - - -
Brake System - - - Installation of a Block on the Left and the Right Lower-Aft
Wing Planks to Prevent Connection of the Hydraulic Lines of the Brakes to the
Incorrect Swivel Assembly Ports, PART A, incorporated.”

### Page 17

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 16 of 38
For aircraft that have had the initial issue of this service bulletin incorporated
PART B - - - Removal of the Bracket and Installation of a Block on the Left and the Right
Lower Aft Wing-Planks
Reference Information
REFERENCE DESIGNATION
A M M 0 7 --- 1 1 --- 0 1 --- 5 8 2 --- 8 0 1 Put the Aircraft on Jacks
A M M 0 7 --- 1 1 --- 0 1 --- 5 8 2 --- 8 0 4 Removal of the Aircraft from Jacks
A M M 1 0 --- 1 1 --- 0 0 --- 4 0 0 --- 8 0 1Installation of the Nose Landing Gear Lockpin
A M M 1 0 --- 1 1 --- 0 0 --- 4 0 0 --- 8 0 2Installation of the Main Landing Gear Lockpins
A M M 3 2 --- 1 1 --- 2 0 --- 4 0 0 --- 8 0 1Installation of the Upper Brake Swivel Assembly
A M M 3 2 --- 4 3 --- 0 0 --- 7 1 0 --- 8 0 1 Operational T est of the Brake System
S R M 5 1 --- 2 1 --- 1 6 Finish Codes
S R M 5 1 --- 2 3 --- 0 0 Pressure, Environmental, Fuel T ank and Firewall
Sealing
S R M 5 1 --- 2 6 --- 0 0 Cleaning
S R M 5 1 --- 4 0 --- 1 1 How to Prepare Fastener Holes
S R M 5 1 --- 4 2 --- 0 6 Solid Rivets
S R M 5 1 --- 4 2 --- 2 1 Hi-Lite Fasteners
T olerance Information
Linear T olerances Angular T olerance
X.XX in. (X.X mm) X.X in. (X mm)
+ / --- 0˚ 30”+/- - - 0.03 in. +/--- 0.1 in.
+ / --- 0 . 8 m m + / --- 3 m m
NOTE: The tolerances above apply to the dimensions given in this service
bulletin, except when specified differently.

### Page 18

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 17 of 38
D. Job Set-Up
NOTE: The steps in the Job Set-Up section of this service bulletin are
recommended steps. The steps give a recommendation to get access
to the work area. This recommendation is to give a safe work area and
to minimize possible damage to surrounding aircraft parts. Alternative
steps can be used at the operator discretion.
(1) 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).
E. 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.
(1) If it is not possible to complete all the instructions in this service bulletin
because of the configuration of the aircraft, speak with a representative of
Bombardier in the CRC at 1- - - 844- - - 272- - - 2720 (1- - - 844- - - CRC - - - CRC0) or
1- - - 514- - - 855- - - 8500 or e-mail at thd.crj@aero.bombardier.com for analysis
and to get an approved disposition to complete this service bulletin.
Refer to Figure 1.
(2) Make sure the forward port of the swivel assembly points down, in the
direction of the lower aft wing-plank.
(3) Make sure that the hydraulic line of the inboard brake is connected to the
forward port of the swivel assembly.
(4) 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).
Refer to Figure 2.
(5) Make index lines on the block (1) as follows:
( a ) O nt h eu p p e ra f ts u r f a c ea n do nt h ea f te d g eo ft h eb l o c k( 1 ) ,m a k ea
line with a marker at 0.96 in. 0.06 in. (24.4 mm 1.5 mm) from the
inboard edge of the block (1).
( b ) O nt h eu p p e ra f ts u r f a c ea n do nt h ea f te d g eo ft h eb l o c k( 1 ) ,m a k ea
line with a marker at 1.81 in. 0.06 in. (46.0 mm 1.5 mm) from the
inboard edge of the block (1).

### Page 19

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 18 of 38
Refer to Figure 5.
CAUTION: DO NOT USE METAL SCRAPERS TO REMOVE DIRT . IF YOU DO
THIS, YOU CAN DAMAGE THE SURFACES.
(6) If there is dirt in the work area, remove it with a vacuum and/or a nonmetallic
scraper .
(7) Remove and discard the nut (1). Do not remove the Hi-Lite pin.
(8) Remove and discard the collars (2). Do not remove the Hi-Lite pins.
(9) Remove and discard the bracket (3) and laminated shim (4).
(10) Clean the work area with solvent (refer to SRM 51- - - 26- - - 00) and as follows:
(a) Do a precleaning of the work area with isopropyl alcohol or MIL-PRF-680
solvent.
(b) Do a final cleaning of the work area (refer to SRM 51- - - 26- - - 00).
Refer to Figure 6.
(11) For each nominal Hi-Lite pin B0206002AG6 or equivalent installed in the lower
aft wing plank, where the old bracket and laminated shim were removed, do
the step that follows:
(a) Apply faying surface sealant on the top and bottom surfaces of the
radius washer (1) (refer to SRM 51- - - 23- - - 00).
(b) Install the radius washer (1), washer(s) (2) and/or (3) if necessary, and
collar (6) on the Hi-Lite pin (refer to SRM 51- - - 42- - - 21).
NOTE: It is permitted to use as many washers (2) and/or (3) as necessary.
(12) For each first oversize Hi-Lite pin HST111AG6 or equivalent installed in the
lower aft wing plank, where the old bracket and laminated shim were
removed, do the steps that follow:
(a) Increase the diameter of the hole in the radius washer(s) (1) to 0.203 - - -
0.213 in. (5.16 - - - 5.41 mm).
( b ) A p p l yf i n i s hc o d eA 0 4 4o nt h ei n s i d eo ft h eh o l eo ft h er a d i u sw a s h e r ( s )
(1) (refer to SRM 51- - - 21- - - 16).
(c) Apply faying surface sealant on the top and bottom surfaces of the
radius washer (1) (refer to SRM 51- - - 23- - - 00).

### Page 20

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 19 of 38
(d) Install the radius washer (1), washer(s) (4) and/or (5) if necessary, and
collar (6) on the Hi-Lite pin (refer to SRM 51- - - 42- - - 21).
NOTE: It is permitted to use as many washers (4) and/or (5) as necessary.
Refer to Figure 7.
(13) T emporarily install the block (1), the retainer (3), and the laminated shim (2)
on the lower aft wing-plank and trunnion as follows:
(a) Put the block (1) on the lower aft wing-plank and against the trunnion.
NOTE: It is necessary for the block (1) to be against the trunnion at the
forward and outboard point, and between the index lines.
(b) Make sure there is a minimum clearance of 0.080 in. (2.03 mm) between
the forward edge of the block (1) and the fitting of the inboard brake
hydraulic line.
(c) If an oversize Hi-Lite pin is installed where the retainer (3) will be
attached to the trunnion, do the steps that follows:
1 For a 1st oversize Hi-Lite pin HST111AG10 or equivalent, increase
the diameter of the retainer (3) attachment hole to 0.328 - - - 0.332 in.
(8.33 - - - 8.43 mm).
2 For a 2nd oversize Hi-Lite pin HST411AG10 or equivalent, increase
the diameter of the retainer (3) attachment hole to 0.344 - - - 0.348 in.
(8.74 - - - 8.84 mm).
(d) Put the retainer (3) on the trunnion and above the block (1) with the
Hi-Lite pin through the retainer (3) attachment hole.
NOTE: It is permitted to have threads of the Hi-Lite pin in the retainer (3)
attachment hole.
(e) Align the most inboard edge of the retainer (3) with the inboard edge of
the block (1).
(f) With the retainer (3) flat on the trunnion, peel the laminated shim (2) to fill
the gap between the block (1) and the retainer (3).
NOTE: With the laminated shim (2) on the block (1), it is permitted to have
a maximum clearance of 0.005 in. (0.13 mm) between the
laminated shim (2) and retainer (3).
(g) Put the laminated shim (2) between the block (1) and the retainer (3).
(h) Align the inboard, outboard, and forward edges of the laminated shim
(2) with the edges of the retainer (3).

### Page 21

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 20 of 38
(i) Align the inboard edges of the laminated shim (2) and the retainer (3)
with the inboard edge of the block (1).
(14) Drill two holes for the rivets (4) as follows:
CAUTION: THE RIVETS (4) ARE INSTALLED THROUGH THE BLOCK (1), THE
LAMINATED SHIM (2) AND THE RETAINER (3) ONLY . THE RIVETS
(4) ARE NOT INSTALLED THROUGH THE LOWER AFT
WING-PLANK. DO NOT DRILL INTO THE WING-PLANK WHEN
YOU DRILL THE HOLES FOR THE RIVETS (4).
(a) Backdrill two holes for the rivets (4) to a diameter of 0.098 in. (2.49 mm)
from the retainer (3) to the laminated shim (2) and the block (1).
NOTE: For the rivets (4), a minimum edge distance of 2D is necessary.
(b) Increase the diameter of the two holes for the rivets (4), in the retainer
(3), the laminated shim (2), and the block (1) to 0.128 - - - 0.132 in. (3.25
- - - 3.35 mm).
(15) On the bottom of the block (1), do a countersink in the two holes for the rivets
(4) (refer to SRM 51- - - 40- - - 11).
(16) Increase the diameter of the retainer (3) attachment hole to 0.328 - - - 0.332 in.
(8.33 - - - 8.43 mm), or as follows if an oversize Hi-Lite pin is installed:
(a) For a 1st oversize Hi-Lite pin HST111AG10 or equivalent, increase the
diameter of the retainer (3) attachment hole to 0.344 - - - 0.348 in. (8.74 - - -
8.84 mm).
(b) For a 2nd oversize Hi-Lite pin HST411AG10 or equivalent, increase the
diameter of the retainer (3) attachment hole to 0.360 - - - 0.364 in. (9.14 - - -
9.25 mm).
(17) Remove burrs and sharp edges from the laminated shim (2), the block (1)
and the retainer (3).
(18) Apply finish code A044 on the retainer (3) attachment hole (refer to SRM
51- - - 21- - - 16).
(19) Prepare the faying surfaces of block (1), the laminated shim (2) and the
retainer (3) for sealant as follows:
(a) Clean the faying surfaces with solvent (refer to SRM 51- - -26- - -00, final
cleaning prior adhesive bonding).
(b) Abrade the faying surfaces with a scotchbrite pad. Remove the gloss
finish but not the top coat.
(c) Clean the faying surfaces with solvent (refer to SRM 51- - -26- - -00 final
cleaning prior adhesive bonding).

### Page 22

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 21 of 38
(20) Assemble the block (1), the laminated shim (2) and the retainer (3) as follows:
(a) Apply faying surface sealant on the bottom and the top surfaces of the
laminated shim (2) (refer to SRM 51- - - 23- - - 00).
(b) Attach the retainer (3), the laminated shim (2), and the block (1) with the
r i v e t s ( 4 ) w e t w i t h s e a l a n t ( r e f e r t o S R M 5 1 --- 4 2 --- 0 6 a n d S R M
51- - - 23- - - 00).
(c) Apply finish code X186 on the rivets (4) (refer to SRM 51- - - 21- - - 16).
(21) T emporarily install the assembled block (1), laminated shim (2) and retainer
(3) on the lower aft wing-plank and trunnion with the forward and outboard
point of the block (1) against the trunnion.
(22) Make sure there is a minimum clearance of 0.080 in. (2.03 mm) between the
forward edge of the block (1) and the fitting of the inboard brake hydraulic
line.
(23) Remove the assembled block (1), laminated shim (2) and retainer (3).
(24) Do the final installation of the assembled block (1), laminated shim (2) and
retainer (3) as follows:
(a) Prepare the faying surfaces of block (1), the retainer (3), the trunnion,
and the lower aft wing-pla nk for sealant as follows:
1 Clean the faying surfaces with solvent (refer to SRM 51- - - 26- - - 00,
final cleaning prior adhesive bonding).
2 Abrade the faying surfaces with a scotchbrite pad. Remove the
gloss finish but not the top coat.
3 Clean the faying surfaces with solvent (refer to SRM 51- - - 26- - - 00
final cleaning prior adhesive bonding).
(b) Apply faying surface sealant on the bottom surface of the retainer (3),
where it will be installed on the trunnion (refer to SRM 51- - - 23- - - 00).

### Page 23

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 22 of 38
(c) Apply faying surface sealant on the bottom surface of the block (1), on
the aft and outboard edge of the block (1) and on the fwd edge of the
trunnion (refer to SRM 51- - - 23- - - 00).
NOTE: It is necessary to use a sufficient amount of sealant to have it
squeeze out to fill the chamfer area of the block (1).
(d) Put the assembled block (1), laminated shim (2) and retainer (3) on the
lower aft wing-plank with the forward and outboard point of the block (1)
against the trunnion.
(e) Install and torque the nut (5) to 110- - - 140 lbf Sin. (12.43- - - 15.82 NSm)
( r e f e r t o S R M 5 1 --- 4 2 --- 2 1 )
NOTE: It is permitted to have threads of the Hi-Lite pin in the retainer (3)
attachment hole.
(f) Apply finish code X186 on the nut (5) (refer to SRM 51- - - 21- - - 16).
(g) Apply injection sealant between the block (1) and the retainer (3) (refer
t o S R M 5 1 --- 2 3 --- 0 0 ) .
(h) Apply sealant along the block (1) and the trunnion, from the outboard
edge of the retainer (3) to the forward and outboard point of the block
(1) (refer to SRM 51- - - 23- - - 00).
F. J o b C l o s e - O u t
NOTE: The steps in the Job Close-Out section of this service bulletin, except for
the return-to-service tests, are recommended steps. The steps give a
recommendation to install components removed during the Job Set-Up.
This recommendation is to make sure that the aircraft is safe and ready
to return to service. Alternative steps can be used at the operator
discretion.
(1) Remove all tools, equipment, and unwanted materials from the work area.
(2) 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 601R- - - 32- - - 110, Revision C, Landing Gear - - -
Brake System - - - Installation of a Block on the Left and the Right Lower-Aft
Wing Planks to Prevent Connection of the Hydraulic Lines of the Brakes to the
Incorrect Swivel Assembly Ports, PART B, incorporated.”

### Page 24

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 23 of 38
Swivel Assembly - - - Installation
F i g u r e1( S h e e t1o f1 )
rsb601r32110_006, kp, July 13, 2015
OUTBOARD
BRAKE
HYDRAULIC
LINE (REF)
AFT
PORT
(REF)
SWIVEL
ASSEMBLY
(REF)
FORWARD
PORT (REF)
B
A
B
VIEW LOOKING FORWARD
IN LEFT MLG BA Y
A
INBOARD BRAKE
HYDRAULIC LINE (REF)
1. Left side shown, right side opposite.
2. Some hydraulic lines are not shown
for clarity.
NOTES

### Page 25

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 24 of 38
B l o c k --- I n d e x L i n e s
F i g u r e2( S h e e t1o f1 )
LEGEND
1. Block
K601R75319- -5 (LH).
K601R75319- -6 (RH).
rsb601r32110_007, kp, July 14, 2015
1
1.81 +/- - 0.06 in.
(46.0 +/- - 1.5 mm)
INDEX
LINE (REF)
0.96 +/- - 0.06 in.
(24.4 +/- - 1.5 mm)
INBOARD
EDGE (REF)
NOTE
Left block shown,
right block opposite.
1
INDEX
LINE
(REF)

### Page 26

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 25 of 38
Block Installation - - - Preparation
F i g u r e3( S h e e t1o f1 )
rsb601r32110_008, kp, June 26, 2015
A
VIEW LOOKING FORWARD
IN LEFT MLG BA Y
B
PRE- -MOD
1
INBOARD BRAKE
HYDRAULIC LINE
(REF)
FORWARD
PORT (REF)
SWIVEL
ASSEMBLY
(REF)
LOWER WING
SKIN (REF)
LOWER
AFT WING
PLANK (REF)
MLG MOUNTING
TRUNNION (REF)
AFT
PORT
(REF)
LEGEND
1. Nut.
B
A
3 The Hi- -Lite pin is not removed.
1. Left side shown, right side opposite.
NOTES
2. Some hydraulic lines are not shown for clarity.
3

### Page 27

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 26 of 38
Block - - - Installation
F i g u r e4( S h e e t1o f4 )
rsb601r32110_009, YL, Aug21, 2015
LEGEND
1. Block
K601R75319- -5 (LH)
K601R75319- -6 (RH).
C
3
A
B
C
VIEW LOOKING FORWARD
IN LEFT MLG BA Y
A
B
4
INBOARD
BRAKE
HYDRAULIC
LINE (REF)
MLG
MOUNTING
TRUNNION
(REF)
INDEX
LINE
(REF)
1
FORWARD AND
OUTBOARD
POINT OF
BLOCK (REF)
FITTING
(REF)
3
NOTES
1. Left side shown, right side opposite.
2. Some hydraulic lines are not shown
for clarity.
It is necessary for the block (1) to be
against the trunnion at the forward
and outboard point, and between
the index lines.
A minimum clearance of 0.080 in.
(2.03 mm) is necessary between
the block (1) and the fitting of the
inboard brake hydraulic line.
3
4

### Page 28

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 27 of 38
Block - - - Installation
F i g u r e4( S h e e t2o f4 )
rsb601r32110_010, YL, Aug21, 2015POST- -MOD
FORWARD
PORT
(REF)
SWIVEL
ASSEMBLY
(REF)
LOWER WING
SKIN (REF)
AFT
PORT
(REF)
MLG MOUNTING
TRUNNION (REF)
2
1
VIEW LOOKING FORWARD
IN LEFT MLG BA Y
B
3
A
B
INBOARD
BRAKE
HYDRAULIC
LINE (REF)HI- -LITE
PIN
(REF)
LOWER
AFT WING
PLANK (REF)
LEGEND
1. Block K601R75319- -5 (LH).
K601R75319- -6 (RH).
2. Laminated shim
K601R75319- -9.
3. Retainer
K601R75319- -7.
5
5
5
RETAINER
ATTACHMENT
HOLE (REF)
NOTES
1. Left side shown, right side opposite.
2. Some hydraulic lines are not shown for clarity.
It is necessary for the most inboard edge of the
retainer (3) and laminated shim (2) to be aligned with
inboard edge of the block (1).
5

### Page 29

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 28 of 38
Block - - - Installation
F i g u r e4( S h e e t3o f4 )
rsb601r32110_016, kp, Apr. 6, 2016POST- -MOD
B
LEGEND
1. Block K601R75319- -5 (LH).
K601R75319- -6 (RH).
2. Laminated shim K601R75319- -9.
3. Retainer K601R75319- -7.
4. Rivet MS20426AD4- -9.
5. Nut MS21042- -5.
B
VIEW LOOKING FORWARD
IN LEFT MLG BA Y
A
FORWARD
PORT (REF)
SWIVEL
ASSEMBLY
(REF)
LOWER WING
SKIN (REF)
AFT
PORT
(REF)
MLG MOUNTING
TRUNNION (REF)
2
1
4
3
INBOARD
BRAKE
HYDRAULIC
LINE (REF)
RETAINER
ATTACHMENT
HOLE (REF)
HI- -LITE
PIN (REF)
LOWER
AFT WING
PLANK (REF)
5
D
D
9
NOTES
1. Left side shown, right side opposite.
2. Some hydraulic lines are not shown for clarity.
The rivets (4) are installed through the block (1),
the laminated shim (2) and the retainer (3) only.
The rivets (4) are not installed through the lower
aft wing- -plank.
9
9

### Page 30

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 29 of 38
Block - - - Installation
F i g u r e4( S h e e t4o f4 )
rsb601r32110_011, kp, Apr. 6, 2016
8
INBOARD
BRAKE
HYDRAULIC
LINE (REF)
MLG
MOUNTING
TRUNNION
(REF)
B
5 4 3
2
1
4
FORWARD
AND
OUTBOARD
POINT OF
BLOCK
(REF)
1
3
2
FITTING
(REF)
6
7
LEGEND
1. Block
K601R75319- -5 (LH).
K601R75319- -6 (RH).
2. Laminated shim
K601R75319- -9.
3. Retainer
K601R75319- -7.
4. Rivet
MS20426AD4- -9.
5. Nut
MS21042- -5.
F
F
E
E
NOTES
1. Left side shown, right side opposite.
2. Some hydraulic lines are not shown for clarity.
A minimum clearance of 0.080 in. (2.03 mm)
is necessary between the block (1) and the
fitting of the inboard brake hydraulic line.
Area for injection sealant.
Area for sealant.
Chamfer area.
The rivets (4) are installed through the
block (1), the laminated shim (2) and the
retainer (3) only. The rivets (4) are not
installed through the lower aft wing- -plank.
4
6
7
8
9
9
LOWER
AFT WING
PLANK (REF) 9

### Page 31

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 30 of 38
Block Installation - - - Preparation
F i g u r e5( S h e e t1o f1 )
rsb601r32110_012, kp, June 26, 2015
B
PRE- -MOD
2
1
INBOARD BRAKE
HYDRAULIC LINE
(REF)
FORWARD
PORT (REF)
SWIVEL
ASSEMBLY
(REF)
LOWER WING
SKIN (REF)
LOWER
AFT WING
PLANK (REF)
MLG MOUNTING
TRUNNION (REF)
3
4
AFT
PORT
(REF)
B
A
VIEW LOOKING FORWARD
IN LEFT MLG BA Y
A
3
NOTES
1. Left side shown, right side opposite.
2. Some hydraulic lines are not shown for clarity.
The Hi- -Lite pin is not removed.3
LEGEND
1. Nut.
2. Collar.
3. Bracket.
4. Laminated shim.
3

### Page 32

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 31 of 38
Block - - - Installation
F i g u r e6( S h e e t1o f1 )
rsb601r32110_017, YL, Aug31, 2015
B
VIEW LOOKING FORWARD
IN LEFT MLG BA Y
A
MLG MOUNTING
TRUNNION (REF)
AFT
PORT
(REF)
6
3O R5
2O R41
B
C
C
CC
LOWER
AFT WING
PLANK (REF)
LOWER WING
SKIN (REF)
6
3O R5
2O R4
1
RADIUS OF
LOWER AFT
WING PLANK
(REF)
HI- -LITE
PIN (REF)
1. Radius washer
NAS1401- -3D5G.
2. Washer
NAS1149D0332K.
3. Washer
NAS1149D0316K.
4. Washer
B0202032- -31K.
5. Washer
B0202032- -31NK.
6. Collar
B0203038- -3.
4
4
3
3
LEGEND
A
LOWER
AFT WING
PLANK
(REF)
LOWER WING
SKIN (REF)
SWIVEL
ASSEMBLY
(REF)
FORWARD
PORT (REF)
INBOARD BRAKE
HYDRAULIC LINE
(REF)
3
NOTES
1. Left side shown,
right side opposite.
2. Some hydraulic lines are
not shown for clarity.
For nominal B0206002AG6 or
equivalent Hi- -Lite pins.
For 1st oversize HST111AG6 or
equivalent Hi- -Lite pins.
4
POST- -MOD

### Page 33

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 32 of 38
Block - - - Installation
F i g u r e7( S h e e t1o f4 )
rsb601r32110_013, YL, Aug21, 2015
4
INBOARD
BRAKE
HYDRAULIC
LINE (REF)
MLG
MOUNTING
TRUNNION
(REF)
INDEX
LINE
(REF)
C
B
LEGEND
1. Block
K601R75319- -5 (LH)
K601R75319- -6 (RH).
3
1
3
FORWARD
AND
OUTBOARD
POINT OF
BLOCK (REF)
B
A
VIEW LOOKING FORWARD
IN LEFT MLG BA Y
A
NOTES
1. Left side shown, right side opposite.
2. Some hydraulic lines are not shown
for clarity.
It is necessary for the block (1) to be
against the trunnion at the forward
and outboard point, and between
the index lines.
A minimum clearance of 0.080 in.
(2.03 mm) is necessary between
the block (1) and the fitting of
the inboard hydraulic line.
3
4
FITTING
(REF)
C

### Page 34

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 33 of 38
Block - - - Installation
F i g u r e7( S h e e t2o f4 )
rsb601r32110_014, YL, Aug21, 2015POST- -MOD
FORWARD
PORT
(REF)
SWIVEL
ASSEMBLY
(REF)
LOWER WING
SKIN (REF)
AFT
PORT
(REF)
MLG MOUNTING
TRUNNION (REF)
2
1
VIEW LOOKING FORWARD
IN LEFT MLG BA Y
B
3
A
B
INBOARD
BRAKE
HYDRAULIC
LINE (REF)HI- -LITE
PIN
(REF)
LOWER
AFT WING
PLANK (REF)
LEGEND
1. Block K601R75319- -5 (LH).
K601R75319- -6 (RH).
2. Laminated shim
K601R75319- -9.
3. Retainer
K601R75319- -7.
5
5
5
RETAINER
ATTACHMENT
HOLE (REF)
NOTES
1. Left side shown, right side opposite.
2. Some hydraulic lines are not shown for clarity.
It is necessary for the most inboard edge of the
retainer (3) and laminated shim (2) to be aligned with
inboard edge of the block (1).
5

### Page 35

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 34 of 38
Block - - - Installation
F i g u r e7( S h e e t3o f4 )
rsb601r32110_018, kp, Apr. 6, 2016
B
LEGEND
1. Block K601R75319- -5 (LH).
K601R75319- -6 (RH).
2. Laminated shim K601R75319- -9.
3. Retainer K601R75319- -7.
4. Rivet MS20426AD4- -9.
5. Nut MS21042- -5.
B
VIEW LOOKING FORWARD
IN LEFT MLG BA Y
A
FORWARD
PORT (REF)
SWIVEL
ASSEMBLY
(REF)
LOWER WING
SKIN (REF)
AFT
PORT
(REF)
MLG MOUNTING
TRUNNION (REF)
2
1
4
3
INBOARD
BRAKE
HYDRAULIC
LINE (REF)
RETAINER
ATTACHMENT
HOLE (REF)
HI- -LITE
PIN (REF)
LOWER
AFT WING
PLANK (REF)
5
POST- -MOD
D
D
NOTES
1. Left side shown, right side opposite.
2. Some hydraulic lines are not shown for clarity.
The rivets (4) are installed through the block (1),
the laminated shim (2) and the retainer (3) only.
The rivets (4) are not installed through the lower
aft wing- -plank.
9
9
9

### Page 36

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 35 of 38
Block - - - Installation
F i g u r e7( S h e e t4o f4 )
rsb601r32110_015, kp, Apr. 6, 2016
8
INBOARD
BRAKE
HYDRAULIC
LINE (REF)
MLG
MOUNTING
TRUNNION
(REF)
5 4 3
2
1
4
FORWARD
AND
OUTBOARD
POINT OF
BLOCK (REF)
1
3
2
FITTING
(REF)
6
7
LEGEND
1. Block
K601R75319- -5 (LH).
K601R75319- -6 (RH).
2. Laminated shim
K601R75319- -9.
3. Retainer
K601R75319- -7.
4. Rivet
MS20426AD4- -9.
5. Nut
MS21042- -5.
B
F
E
E
F
NOTES
1. Left side shown, right side opposite.
2. Some hydraulic lines are not shown for clarity.
A minimum clearance of 0.080 in. (2.03 mm)
is necessary between the block (1) and the fitting
of the inboard brake hydraulic line.
Area for injection sealant.
Area for sealant.
Chamfer area.
The rivets (4) are installed through the
block (1), the laminated shim (2) and the
retainer (3) only. The rivets (4) are not
installed through the lower aft wing- -plank.
4
6
7
8
9
9
LOWER
AFT WING
PLANK (REF) 9

### Page 37

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 36 of 38
3. MATERIAL INFORMATION
A. Kit Information
Kit Contents:
KIT 601R32 - - -110K1A¡
PART NUMBER QTY NAME ALTERNATE PARTS
K601R75319- - - 5 1 Block (LH) © ---
K601R75319- - - 6 1 Block (RH) © ---
K601R75319- - - 7 2 Retainer © ---
K601R75319- - - 9 2 Laminated shim © ---
MS20426AD4- - - 9 5 Rivet, CSK ---
MS21042- - - 5 2 Nut, self locking ---
¡ The kit can contain more hardware and/or material than necessary.
© This part can be made as shown in Appendix A of this service
bulletin.
KIT 601R32 - - -110K2¡
PART NUMBER QTY NAME ALTERNATE PARTS
B0202032- - - 31K 5 Washer ---
B0202032- - - 31NK 9 Washer ---
B0203038- - - 3 5 Collar ---
K601R75319- - - 5 1 Block (LH) © ---
K601R75319- - - 6 1 Block (RH) © ---
K601R75319- - - 7 2 Retainer © ---
K601R75319- - - 9 2 Laminated shim © ---
MS20426AD4- - - 9 5 Rivet, CSK ---
MS21042- - - 5 2 Nut, self locking ---
NAS1149D0316K 9 Washer ---

### Page 38

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 37 of 38
PART NUMBER ALTERNATE PARTSNAMEQTY
NAS1149D0332K 9 Washer ---
NAS1401- - - 3D5G 9 Radius Washer ---
¡ The kit can contain more hardware and/or material than necessary.
© This part can be made as shown in Appendix A of this service
bulletin.
NOTE: For permitted alternative to superseded parts, refer to the Parts
Supersession Cross References Lists at www.iflybombardier.comunder
Resources - - - Engineering Documents.
B. Consumable Information
The materials that follow are necessary to do this service bulletin. Y ou 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
T T --- I --- 7 3 5 As
necessary
Isopropyl alcohol 11- - - 004¡
M I L --- P R F --- 6 8 0 As
necessary
Solvent 11- - - 002¡
7075- - - T6,
AMS- - - QQ - - - A- - - 250/13©
As
necessary
Clad Sheet
(0.063 in. thick)
---
AMS DTL- - - 22499/1,
Typ e 1, C lass 2©
As
necessary
Shim Stock,
Laminated,
Aluminum Alloy
(0.093 in. thick)
---
MIL- - - I- - - 24768/15© As
necessary
Phenolic
(0.63 in. thick)
---
AS87132, Type III,
Grade A ©
As
necessary
Cetyl alcohol 06- - - 021¡

### Page 39

SERVICE BULLETIN 601R-32-110
SB 601R-32-110Dec 19/2013
Revision C, May 04/2016 Page 38 of 38
SPECIFICATION REFERENCE NAMEQTY
Boelube
(70104/70106/70200/
70201/70307) ©
As
necessary
Lubricant www.boelube.
com
¡ Refer to AMM 51- - - 31- - - 00- - - 990- - - 801.
© These materials are not necessary if kit 601R32- - - 110K1A or 601R32- - - 110K2
is ordered.
NOTE: T o complete this list of consumables, refer to the different tasks that are
given as references in this service bulletin
C. Special T ools and Equipment
There are no special tools and equipment for this service bulletin.
D. Disposition of Parts
FOR PART A
Not applicable.
FOR PART B
The table that follows shows the relation between the new parts and/or modified
parts to be installed during the incorporation of this service bulletin and the
disposition of the affected parts from the aircraft (or spares).
PRE-SB
PART NUMBER
NAME QTY DC POST-SB
PART NUMBER
NAME
601R75317- - - 1
OR
K601R75217- - - 3
Bracket (LH) 1 DIS K601R75319- - - 5 Block (LH)
601R75317- - - 2
OR
K601R75217- - - 4
Bracket (RH) 1 DIS K601R75319- - - 6 Block (RH)
Disposition code (DC):
DIS: Discard Part.
1

### Page 40

the evolution of mobility
APPENDIX A
Page A1 of A4
Dec 19/2013
Revision A, Oct 29/2015
APPENDIX A
SERVICE BULLETIN 601R-32-110
Landing Gear - - - Brake System - - - Installation of a Block on the Left and the Right
Lower-Aft Wing Planks to Prevent Connection of the Hydraulic Lines of the Brakes to the
Incorrect Swivel Assembly Ports
The procedure contained in this appendix is given as reference in the
Accomplishment Instructions of Service Bulletin 601R-32-110.

### Page 41

APPENDIX A
SERVICE BULLETIN 601R-32-110
APPENDIX A
Page A2 of A4
Dec 19/2013
Revision A, Oct 29/2015
Block
Figure A1 (Sheet 1 of 3)
rsb601r32110_003, kp, June 26, 2015
2.66 in
(67.6 mm)
R0 . 2 2i n .
(5.6 mm)
1.09 in.
(27.7 mm)
1.40 in.
(35.6 mm)
R0 . 1 5i n .
(3.8 mm)
TYPICAL
0.15 in.
(3.8 mm)
R0 . 8 5i n .
(21.6 mm)
1.40 in.
(35.6 mm)
R0 . 0 9i n .
(2.29 mm)
0.22 in.
(5.6 mm)0.63 in.
(16.0 mm)
0.30 in.
(7.6 mm)
A
A
A A--
BLOCK
K601R75319- -5 (LH) SHOWN,
K601R75319- -6 (RH) OPPOSITE
NOTES
1. Use Phenolic MIL- -I- -24768/15 (0.63 in. (16.0 mm) thick).
2. Machine per shop best practice. The temperature of
If required, Boelube (70104/70106/70200/70201/70307) or
cetyl alcohol can be used as a cutting lubricant/coolant.
The use of any other lubricant is not allowed.
4. Finish per SRM 51- -21- -16 finish code E102, color grey #16473.
5. Identify with indelible ink stamp or equivalent per shop best practice.

### Page 42

APPENDIX A
SERVICE BULLETIN 601R-32-110
APPENDIX A
Page A3 of A4
Dec 19/2013
Revision A, Oct 29/2015
Retainer
Figure A1 (Sheet 2 of 3)
rsb601r32110_004, kp, June 26, 2015
4
0.93 in.
(23.6 mm)
R0 . 3 0i n .
(7.6 mm)
R 0.63 in. (16.0 mm)
Center 0.31 in. (7.9 mm)
0.17 in.
(4.3 mm)
R0 . 2 8i n
(7.1 mm)
R 0.280 in
(7.11 mm)
DIA. 0.317 in. (8.05mm)
0.313 in. (7.95 mm) R0 . 1 5i n .
(3.8 mm)
0.28 in.
(7.1 mm)
0.49 in.
(12.5 mm)
R0 . 2 8i n .
(7.1 mm)
R0 . 1 5i n .
(3.8 mm)
TYPICAL
R0 . 6 3i n .
(16 mm)
1.65 in.
(41.9 mm)
1.35 in.
(34.3 mm)
A
0.010 in.
(0.25 mm) AL
RETAINER
K601R75319- -7
4
NOTES
1. Use 7075- -T6 Clad sheet, AMS- -QQ- -A- -250/13 (0.063 in. (1.6 mm) thick).
2. Make per SRM 51- -24- -36.
3. Break sharp edges.
5. Finish per SRM 51- -21- -16 finish code A023, color grey #16473.
6. Identify with indelible ink stamp or equivalent per shop best practice.

### Page 43

APPENDIX A
SERVICE BULLETIN 601R-32-110
APPENDIX A
Page A4 of A4
Dec 19/2013
Revision A, Oct 29/2015
Laminated Shim
Figure A1 (Sheet 3 of 3)
rsb601r32110_005, YL, Aug21, 2015
0.60 in.
(15.2 mm)
R0 . 3 0i n .
(7.6 mm)
0.17 in.
(4.3 mm)
1.10 in.
(28.0 mm)
R0 . 1 5i n .
(3.8 mm)
R0 . 6 3i n .
(16.0 mm)
LAMINATED SHIM
K601R75319- -9
4
NOTES
1. Use AMS- -DTL- -22499/1, Type 1, Class 2 (0.093 in. (2.36 mm) thick).
2. Make per SRM 51- -24- -36.
3. Break sharp edges.
Part has no holes. Use dimensions for radius.
5. Identify with indelible ink stamp or equivalent per shop best practice.
4
4

### Page 44

the 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.: 601R-32-110 Revision: C
Aircraft Serial Number: Date:
ST R ONG LY
DISAGREE
DISAGREE AGREE ST R ONG LY
AGREE
Instructions to do the service bulletin are
accurate.
Comments:
- - - -
Figure(s), picture(s), and/or Appendix
were helpful to do the service bulletin.
Comments:
- - - -
Part(s) or kit(s) agreed with the service
bulletin requirement.
Comments:
- - - -
The service bulletin was accomplished
within the estimated time given.
Comments:
- - - -
Overall, I was satisfied with this service
bulletin.
Comments:
- - - -
Operator: Service Centre:
Name: Telephone or Fax:
FAX your comments or feedback to (450) 476- - -7300
or e-mail tocrj_sb_evaluation_form@aero.bombardier.com

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.