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. 1SB 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 4For 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 AS SEMBLY. IF YOU DO NOT DO THIS, YOU CAN HAVE CONT AMINA TION 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 3rsb601r32109_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 FORWARDrsb601r32109_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 applicablelogbooks: 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.

1THANK YOU FOR ANSWERING THIS EVALUATION FORM UPON COMPLETION OF THIS EVALUATION FORM/COMPLIANCE SHEET, FAX TO 450-476-7300 or email to CRJ_SB_Evaluation_Form@aero.bombardier.com 

### SERVICE BULLETIN EVALUATI ON FORM/COMPLIANCE SHEET (YOUR IDEAS WILL HELP US PROVIDE BETTER BULLETINS)
SERVICE BULLETIN : ISSUE:

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

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

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

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

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

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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