SB 601R---32---109

Page 1 of 1

Feb 26/2013

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

CL ---600 ---2B19 Canadair Regional Jet (CRJ) Aircraft

SERVICE BULLETIN 601R ---32 ---109

SUBJECT: Landing Gear --- Extension and Retraction, Main Gear --- Installation of

Stopper Plates to Prevent Incorrect Installations of MLG Uplock

Assemblies

This page transmits:

Revision A of Service Bulletin 601R --- 32 --- 109,

pages 1 thru 16, dated Feb 26/2013

The changes in this revision have no effect on aircraft that have

incorporated a previous issue of this service bulletin.

Reason:

Revised Planning Information, paragraph 1.G. Material --- Price and Availability, to:

Add supercession information for parts that are listed.

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 --- 109, Initial Issue, dated May 29/2012.

Replace with the copy attached.

Service Bulletin History:

Initial issue, dated May 29/2012.

1
SB 601R−32−109

Page 1 of 16

May 29/2012

Revision A, Feb 26/2013

SERVICE BULLETIN

Technical

Publications

THIS SERVICE BULLETIN IS SENT TO EACH OPERATOR. IF THE OPERATOR HAS LEASED AIRCRAFT,

TRANSFERRED SPARES IN THE LAST SIX MONTHS, SEND THIS SERVICE BULLETIN TO THE NEW

OWNER, UNLESS CONFIRMATION WAS RECEIVED THAT BOMBARDIER COMMERCIAL AIRCRAFT

HAS INCLUDED THE NEW OPERATOR ON THE DISTRIBUTION LIST.

SEND THIS SERVICE BULLETIN TO THE LESSEE. IF THE OPERATOR HAS SOLD AIRCRAFT OR

ATA SYSTEM: 32−32 NUMBER: 601R−32−109

SUBJECT: Landing Gear − Extension and Retraction, Main Gear − Installation of

Stopper Plates to Prevent Incorrect Installations of MLG Uplock

Assemblies

1. PLANNING INFORMATION

A. Effectivity

(1) Aircraft Affected:

Service: CL−600−2B19 aircraft with serial numbers 7003 thru 7067,

7069 thru 7990 and 8000 thru 8999.

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 Supplement Type Certificates (STCs),

Supplemental Type Approvals (STAs) or equivalent action changes

to make sure you can complete this bulletin.

B. Reason

(1) Condition

It is possible to have an incorrect installation of the MLG uplock assembly

when the upper bolt is installed through the structure only and not through the

MLG uplock assembly. This could prevent the extension of the MLG.
SERVICE BULLETIN 601R−32−109

SB 601R−32−109

Page 2 of 16

May 29/2012

Revision A, Feb 26/2013

(2) Evidence

Incorrect installation of the MLG uplock assembly was found in-service.

(3) Objective/Benefit

This service bulletin gives the instructions to install a new stopper plate

adjacent to the MLG uplock assembly. This will prevent incorrect installation of

the MLG uplock assembly.

C. Description

Lockpins are installed in the NLG and MLG. The circuit breakers are opened and

tagged. The MLG wheel bins are removed.

New stopper plates are installed adjacent to the MLG uplock assembly.

A test of the manual-release-system is done. The MLG wheel bins are installed.

The circuit breakers are closed. An operational test of the MLG overheat detection

and warning system is done.

D. Compliance

Recommended Service Bulletin.

Bombardier recommends that this service bulletin be done at no more than 5500

flight hours from the release date of this service bulletin, 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 48 months from the release date of this service bulletin, unless otherwise

directed by the airworthiness authority of the operator.

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

Tolerance Inspections (DTIs).

E. Approval

The technical content of this service bulletin has been approved under the authority

of the TCCA Design Approval Organization No: DAO #93−Q−02.
SERVICE BULLETIN 601R−32−109

SB 601R−32−109

Page 3 of 16

May 29/2012

Revision A, Feb 26/2013

F. Manpower

The man-hours given below are estimates for direct labor done by an experienced

crew on an aircraft prepared for maintenance.

These estimates do not include the time necessary for:

 Administrative functions such as planning, liaising, familiarization, and report writing.

 Non-productive elapsed time such as rest time, having meals, and crew shift changes.

 Elapsed time such as for paint to dry, sealant to cure, and fuel tank venting.

 Preparation for modification (unless specified in the Accomplishment Instructions)

such as cleaning and getting parts, tools, consumables, and ground equipment.

 Quality assurance inspections, troubleshooting and/or correction of

discrepancies found when a task is done.

 All other activities that are not considered by Bombardier as directly related to the

accomplishment of this procedure.

NOTE: For on-site labor assistance, please speak with a Fleet Services

representative for a quote. Contact the Fleet Services Team

through the CRC at 514-855-8500 or e-mail at

thd.crj@aero.bombardier.com.

It will take an estimated 5.0 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 MAN-HOURS

(1) Job Set-Up 1.0

(2) Procedure 2.5

(3) Test 0.5

(4) Job Close-Out 1.0
SERVICE BULLETIN 601R−32−109

SB 601R−32−109

Page 4 of 16

May 29/2012

Revision A, Feb 26/2013

G. Material − Price and Availability

There are no kits for this service bulletin.

(1) There are no kits for this service bulletin. The parts in the table that follows are

necessary to do this service bulletin and are available from Bombardier

Commercial Aircraft.

PART NUMBER NAME QUANTITY

B0206002AG5−6 Hi-Lite 5/32 Dia. 4

B0203013−08 Nut 4

For allowable superceded parts refer to the Parts Supercession Cross

 References Lists at www.iflybombardier.com under

 Resources−Engineering Documents.

(2) Please send a purchase order to the address below to schedule part delivery:

Bombardier

Service Bulletin Kit Support Team

123 Garratt Blvd, N42−24

Toronto, Ontario

Canada M3K 1Y5

Fax: 416-375-3060

Phone: 416-375-3920

Email: sbkits@aero.bombardier.com

Please contact the Service Bulletin Kit Support Team at the address above for

terms and conditions.

(3) Refer to paragraph 3.B. for a list of consumables for this service bulletin.

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.
SERVICE BULLETIN 601R−32−109

SB 601R−32−109

Page 5 of 16

May 29/2012

Revision A, Feb 26/2013

I. Weight and Balance

Not changed.

J. Electrical Load Data

Not changed.

K. References

Restriction and/or Special Instruction (RSI) C−A279, Issue NC

Modification Summary TC601R18206, Revision A

Refer to the SB introduction document for definition or explanation of Service

Bulletin content.

Aircraft Maintenance Manual (AMM)

Structural Repair Manual (SRM)

For Bombardier reference only: PCA 6637

L. Other Publications Affected

Aircraft Maintenance Manual (AMM)

M. Relationship Chart

Not applicable.
SERVICE BULLETIN 601R−32−109

SB 601R−32−109

Page 6 of 16

May 29/2012

Revision A, Feb 26/2013

2. ACCOMPLISHMENT INSTRUCTIONS

Reference Information

REFERENCE DESIGNATION

AMM 10−11−00−400−801 Installation of the Nose Landing Gear Lockpin

AMM 10−11−00−400−802 Installation of the Main Landing Gear Lockpins

AMM 12−00−06−863−804 Release Hydraulic Pressure − System No. 3

AMM 24−00−00−910−801 Electrical/Electronic Safety Precautions

AMM 26−14−00−710−801 Operational Test of the MLG Overheat Detection

and Warning System

AMM 32−22−01−980−801 Open and Isolate the Nose-Landing-Gear

Forward Doors

AMM 32−32−05−400−801 Installation of the MLG Uplock Assembly

AMM 32−34−00−710−801 Operational Test of the Landing Gear ManualRelease-System

AMM 53−83−01−000−801 Removal of the MLG Wheel Bin

AMM 53−83−01−400−801 Installation of the MLG Wheel Bin

SRM 51−21−11 Corrosion Prevention Procedures

SRM 51−23−00 Pressure, Environmental, Fuel Tank and Firewall

Sealing

SRM 51−24−36 Cutting of Sheet Metal

SRM 51−25−06 Fluid−Resistant (FR) Epoxy Primer

SRM 51−25−16 Fluid−Resistant (FR) Polyurethane Topcoat

SRM 51−26−00 Cleaning

SRM 51−40−11 How to Prepare Fastener Holes

SRM 51−42−21 Hi-Lite Fasteners
SERVICE BULLETIN 601R−32−109

SB 601R−32−109

Page 7 of 16

May 29/2012

Revision A, Feb 26/2013

Tolerance Information

Linear Tolerances Angular Tolerance

X.XX in. (X.X mm) X.X in. (X mm)

+/−0° 30" +/− 0.03 in. +/− 0.1 in.

+/− 0.8 mm +/− 3 mm

NOTE: The tolerances above apply to the dimensions given in this service

bulletin, except when specified differently.

A. Job Set-Up

(1) Make sure that the NLG and MLG lockpins are installed

(refer to AMM 10−11−00−400−801 and AMM 10−11−00−400−802).

(2) Obey all the electrical/electronic safety precautions

(refer to AMM 24−00−00−910−801).

(3) Open, safety, and tag the circuit breaker that follows:

CB PANEL CB NO. NAME ZONE

CBP−2 N9 MLG BAY OVHT DET 222

(4) Remove the MLG wheel bins (refer to AMM 53−83−01−000−801).

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 2 .

(1) Use 2024−T3 aluminum alloy of 0.125 in. (3.18 mm) thick to make the

stopper plate (1) to the temporary dimensions.

Refer to Figure 3 .

(2) Install the stopper plate (1) on the aft uplock frame (3) as follows:

(a) Make sure that the MLG uplock assembly (4) is correctly installed with

its two attachment bolts (refer to AMM 32−32−05−400−801).

NOTE: The MLG uplock assembly (4) is correctly installed when you have

a maximum distance of 0.83 in. (21.1 mm) between the inboard

edge of the aft uplock frame (3) and the inboard edge of the cutout

in the MLG uplock assembly (4).
SERVICE BULLETIN 601R−32−109

SB 601R−32−109

Page 8 of 16

May 29/2012

Revision A, Feb 26/2013

CAUTION: BEFORE THE DRILLING PROCEDURES IT IS NECESSARY TO PUT

PROTECTION ON THE MLG UPLOCK ASSEMBLY. IF YOU DO NOT

DO THIS, YOU CAN HAVE CONTAMINATION IN THE MLG UPLOCK

ASSEMBLY THAT COULD PREVENT CORRECT OPERATION.

(b) Make sure that you put sufficient protection on the MLG uplock

assembly (4) to prevent contamination during installation of the stopper

plate (1).

(c) Clean the work area with solvent (refer to SRM 51−26−00).

(d) Temporarily install the stopper plate (1) on the aft uplock frame (3) as

follows:

NOTE: Make sure to keep a minimum edge distance of 1.5D.

NOTE: Make sure to keep a pitch distance between 3.5D and 6.5D.

1 On the aft side of the aft uplock frame, draw a horizontal line at

1.94 in. (49.3 mm) from the lower edge of the pocket that contains

the upper attachment hole of the MLG uplock assembly (4) (refer

to view C).

2 Draw a vertical line at 0.43 in. (10.9 mm) from the inboard edge of

the pocket that contains the upper attachment hole of the MLG

uplock assembly (4) (refer to view C).

3 Draw a vertical line at 1.13 in. (28.7 mm) from the inboard edge of

the aft uplock frame (3) in the pocket that contains the upper

attachment hole of the MLG uplock assembly (4) (refer to view C).

4 At the intersection of the two lines, drill two holes to a diameter of

0.098 in. (2.49 mm) with a #40 drill.

5 Temporarily install the stopper plate (1) on the forward side of the

aft uplock frame (3). Make sure that the inboard edge of the

stopper plate (1) is flush with the inboard edge of the aft uplock

frame (3). Make sure that the lower edge of the stopper plate (1) is

against the MLG uplock assembly (4).

6 With a #40 drill, backdrill two holes from the aft uplock frame (3) to

the stopper plate (1) to a diameter of 0.098 in. (2.49 mm).
SERVICE BULLETIN 601R−32−109

SB 601R−32−109

Page 9 of 16

May 29/2012

Revision A, Feb 26/2013

7 Open the holes in the stopper plate (1) and the aft uplock frame (3)

to a final diameter of 0.159 to 0.162 in. (4.04 to 4.11 mm)(refer to

SRM 51−42−21).

NOTE: It is also permitted to have a final diameter of 0.164 to 0.167

in. (4.17 to 4.24 mm) in the stopper plate (1) and the aft

uplock frame (3) (refer to SRM 51−42−21).

8 Remove the stopper plate (1) from the aft uplock frame (3).

Refer to Figure 2 .

9 Remove 0.09 in. (2.3 mm) of material from the lower area of the

stopper plate to get to the final dimensions (refer to SRM

51−24−36).

NOTE: Make sure that the lower edge of the stopper plate (1) has

the same contour than the MLG uplock assembly (4).

Refer to Figure 3 .

10 Remove the burrs and sharp edges.

11 Apply chemical conversion coating on the bare metal areas (refer

to SRM 51−21−11).

12 Apply a layer of fluid-resistant primer on the stopper plate (1) (refer

to SRM 51−25−06).

13 Apply a layer of grey fluid-resistant topcoat on the stopper plate (1)

(refer to SRM 51−25−16).

14 With an indelible ink pen or equivalent, identify the stopper plate

(1) as K601R31058−20.

(e) Clean the work area with solvent (refer to SRM 51−26−00).

(f) Do the final installation of the stopper plate (1) as follows:

1 Apply faying surface sealant on the stopper plate (1)

(refer to SRM 51−23−00).
SERVICE BULLETIN 601R−32−109

SB 601R−32−109

Page 10 of 16

May 29/2012

Revision A, Feb 26/2013

2 Install the stopper plate (1) on the forward side of the aft uplock

frame (3) with hi-lites (5) wet with sealant, with their heads on the

forward side, and the collars (6) (refer to SRM 51−23−00 and SRM

51−42−21).

3 Apply a brush coat of sealant on the collars (6)

(refer to SRM 51−23−00).

(g) Make sure that there is a clearance of 0.09 in. (2.3 mm) between the

contours of the stopper plate (1) and of the MLG uplock assembly (4).

(h) Apply a layer of fluid-resistant primer on the head of the hi-lites (5) (refer

to SRM 51−25−06).

(i) Apply a layer of grey fluid-resistant topcoat on the head of the hi-lites

(5)(refer to SRM 51−25−16).

(j) Apply corrosion inhibiting compound on the aft uplock frame (3)

(refer to SRM 51−21−11).
SERVICE BULLETIN 601R−32−109

SB 601R−32−109

Page 11 of 16

May 29/2012

Revision A, Feb 26/2013

Dimensions of the Stopper Plate

Figure 2 

1.50 in.

(38.1 mm)

0.25 in. (6.4 mm)

(3 PLACES)

RADIUS

0.75 in.

(19.1 mm)

0.10 in. (2.5 mm)

(2 PLACES)

RADIUS 0.125 in.

(3.18 mm)

rsb601r32109_003.dg, sd, 11mai12

LEGEND

1. Stopper plate

 K601R31058−20.

1.50 in.

(38.1 mm)

0.25 in. (6.4 mm)

(3 PLACES)

RADIUS

0.75 in.

(19.1 mm)

0.10 in. (2.5 mm)

(2 PLACES)

RADIUS 0.125 in.

(3.18 mm)

1

TEMPORARY DIMENSIONS

FINAL DIMENSIONS

0.91 in.

(23.1 mm)

1.00 in.

(25.4 mm)

STOPPER

(REF) 1.09 in.

(27.7mm)

NOTE

0.09 in. (2.3 mm) of material is removed from the

 lower edge of the stopper plate (1) before final installation.

1.00 in.

(25.4 mm)
SERVICE BULLETIN 601R−32−109

SB 601R−32−109

Page 12 of 16

May 29/2012

Revision A, Feb 26/2013

Installation of the Stopper Plate

Figure 3 

rsb601r32109_001.dg, sd, 11mai12

LEGEND

1. Stopper plate

 K601R31058−20.

2. Forward uplock frame.

3. Aft upock frame.

4. MLG uplock assembly.

5. Hi−lite

 B0206002AG5−6.

6. Collar

 B0203013−08.

FINAL INSTALLATION

TEMPORARY INSTALLATION 1. Left side shown,

right side opposite.

NOTES

1.13 in.

(28.7 mm)

(REF)

1.94 in.

(49.3 mm)

(REF)

0.43 in.

(10.9 mm)

(REF)

3

0.09 in.

(2.3 mm)

1

3

4

4

2

3

1

6

5

4

0.83 in.

(21.1 mm)

MAXIMUM

0.99 in.

(25.1mm)

(REF)

4

STOPPER

(REF)

STOPPER

(REF)

Clearance of 0.09 in. (2.3 mm)

between the contours of the

stopper plate (1) and of the

MLG uplock assembly (4).
SERVICE BULLETIN 601R−32−109

SB 601R−32−109

Page 13 of 16

May 29/2012

Revision A, Feb 26/2013

MLG Uplock Latch Positions

Figure 4 

VIEW LOOKING FORWARD

rsb601r32109_002.dg, sd, 5avril12

UPLOCK LATCH

IN LOCKED

POSITION

UPLOCK LATCH

IN UNLOCKED

POSITION

1

LEGEND

1. MLG uplock assembly.
SERVICE BULLETIN 601R−32−109

SB 601R−32−109

Page 14 of 16

May 29/2012

Revision A, Feb 26/2013

C. Job Close-Out

(1) Remove all tools, equipment, and unwanted materials from the work area.

(2) Remove the protection that was put on the MLG uplock assembly.

(3) Do the manual test of the MLG Uplock assemblies as follows:

NOTE: You can do the operational test of the landing gear

manual-release-system (refer to AMM 32−34−00−710−801) as

an alternative to the manual test of the MLG uplock assemblies

given below.

(a) Open and isolate the Nose-Landing-Gear (NLG) forward doors (refer to

AMM 32−22−01−980−801).

(b) Release the pressure from hydraulic system No. 3

(refer to AMM 12−00−06−863−804).

(c) In the MLG bay, manually move the two uplock latches into the locked

position (refer to Figure 4 ).

(d) In the cockpit, pull the handle of the landing-gear manual-release.

(e) In the MLG bay, make sure that the two uplock latches are in the

unlocked position (refer to Figure 4 ).

(f) Push the button and stow the handle of the landing-gear

manual-release.

(4) Install the MLG wheel bins (refer to AMM 53−83−01−400−801).

(5) Remove the tag and close the circuit breaker that follows:

CB PANEL CB NO. NAME ZONE

CBP−2 N9 MLG BAY OVHT DET 222

(6) Do the operational test of the MLG overheat detection and warning system

(refer to AMM 26−14−00−710−801).

(7) When this service bulletin is completed, make this entry in the applicable

logbooks: Service Bulletin 601R−32−109, Revision A, Landing Gear −

Extension and Retraction, Landing Gear − Installation of Stopper Plates to

Prevent Incorrect Installations of MLG Uplock Assemblies, incorporated."
SERVICE BULLETIN 601R−32−109

SB 601R−32−109

Page 15 of 16

May 29/2012

Revision A, Feb 26/2013

3. MATERIAL INFORMATION

A. Kit Information

None.

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 QUANTITY NAME REFERENCE

MIL−PRF−81733,

Type IV

As

necessary

Sealant, faying and

wet-installation



MIL−C−81706

Class 1A, Form II or

III, Method B or C

As

necessary

Chemical conversion

compound

05−025 

BAMS 565−001 As

necessary

Primer, epoxy,

fluid-resistant

13−007 

BAMS 565−006

Type I

As

necessary

Corrosion inhibiting

compound

15−004 

BAMS 565−009 As

necessary

Polyurethane paint,

fluid-resistant enamel

for aircraft exterior

(color grey 16473

per FED−STD−595)

16−011 

AMS QQ−A−250/5

(AL 2024−T3)

2  Aluminum sheet

Refer to AMM 51−31−00−990−801

 Refer to SRM 51−32−00

 (Length x Height x Thickness) = (2.0 in. (51 mm) x 1.5 in. (38 mm) x 0.125 in.

(3.175 mm))

NOTE: To complete this list of consumables, refer to the different tasks that are

given as references in this service bulletin.
SERVICE BULLETIN 601R−32−109

SB 601R−32−109

Page 16 of 16

May 29/2012

Revision A, Feb 26/2013

C. Special Tools and Equipment

There are no special tools and equipment for this service bulletin.

NOTE: To complete this list of special tools and equipment, refer to the different

tasks that are given as references in this service bulletin.

D. Disposition of Parts

Not applicable.

1 
THANK YOU FOR ANSWERING THIS EVALUATION FORM 

UPON COMPLETION OF THIS EVALUATION FORM/COMPLIANCE SHEET, FAX TO 

450-476-7300 or email to CRJ_SB_Evaluation_Form@aero.bombardier.com

SERVICE BULLETIN EVALUATION FORM/COMPLIANCE SHEET 

(YOUR IDEAS WILL HELP US PROVIDE BETTER BULLETINS) 

SERVICE BULLETIN : ISSUE: 

 STRONGLY DISAGREE NEUTRAL AGREE STRONGLY 

 DISAGREE AGREE 

 Instructions to do the Service Bulletin 

were accurate. 

Comments:

    

 Illustration(s), figure(s), picture(s) and/or 

kit drawing(s) were helpful to carry out 

instructions. 

Comments:

    

 If a parts kit was required, did the kit 

contents received agree with the 

contents listed in the bulletin? 

Comments: 

    

 Aircraft hands-on work was 

accomplished in estimated time. 

 Comments:

    

 Overall, I was satisfied with this Service 

Bulletin. 

 Comments: 

    

PLEASE SUPPLY US WITH THE FOLLOWING DATA AND FAX TO (450) 476-7300: 

OPERATOR: NAME (Please print) 

SERVICE CENTER: TELEPHONE: 

AIRCRAFT SERIAL NO.: FACSIMILE: 

DATE OF SB 

INCORPOARTION