SB 670BA ---52---037 Page 1 of 1 Sep 16/2013 

## SERVICE BULLETIN REVISION TRANSMITTAL SHEET
SERVICE BULLETIN 670BA ---52 ---037
SUBJECT: Door --- Aft Baggage Bay Door --- Replacement of the Fittings Around the Aft Baggage Bay-Door This Page transmits: Revision B of Service Bulletin 670BA --- 52 --- 037, pages 1 thru 31, dated Sep 16/2013. The changes in this revision have no effect on aircraft that have had this service bulletin incorporated.
Reason: Revised Planning Information, paragraph 1., to: Change the title of Part A. Revised Accomplishment Instructions, paragraph 2., to: Change the inspection from a general visual to a detailed. Correct part numbers in figure 3. This revision also includes small editorial changes that do not have an effect on the technical content.
Instructions: Discard the copy of Service Bulletin 670BA --- 52 --- 037, Revision A, dated Jul 16/2013. Replace with the copy attached. Service Bulletin History: Initial issue, dated Jun 17/2013. Revision A, dated Jul 16/2013. 1SB 670BA−52−037 Page 1 of 31 Jun 17/2013 Revision B, Sep 16/2013 

# 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: 52−31 NUMBER: 670BA−52−037 SUBJECT: Door − Aft Baggage Bay Door − Replacement of the Fittings Around the Aft Baggage Bay-Door
1. PLANNING INFORMATION A. Effectivity (1) Aircraft Affected:
AIRCRAFT MODEL SERVICE AIRCRAFT SERIAL NUMBERS PRODUCTION AIRCRAFT SERIAL NUMBERS CL−600−2C10 10303 thru 10333 [1] CL−600−2D24 15257 thru 15284 [1] CL−600−2E25 19011 thru 19024 [1] [1] There is no production effectivity. 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), Supplemental Type Approvals (STAs) or equivalent action changes to make sure you can complete this service bulletin.

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 2 of 31 Jun 17/2013 Revision B, Sep 16/2013 B. Reason (1) Condition The stop fittings and related components installed around the structure of the aft baggage bay-door were not correctly made. This can cause the stop fittings to break and then the aft baggage bay-door to open. (2) Evidence This condition was found during the manufacturing process of the surround fittings. (3) Objective/Benefit This service bulletin gives the instruction to do a detailed visual inspection for cracks or obvious deformations of the striker plates and the fittings installed on the structure of the aft baggage bay-door and gives the procedure to replace the striker plates, the fittings and the serrated plates. Replacement of the components will make sure that the aft baggage bay-door stays in the locked position during flight. C. Description This service bulletin is divided into two parts: PART A and PART B. PART A − Detailed Visual Inspection of the Striker Plates and the Fittings The aft baggage bay-door is opened. A detailed visual inspection for cracks or obvious deformations is done on the striker plates and the fittings. If a crack or obvious deformations are found on one of the striker plates or the fittings, PART B is done. If no cracks and no obvious deformations are found, no more step is necessary. The aft baggage bay-door is closed. PART B − Replacement of the Striker Plates and the Fittings The aft baggage bay-door is opened. The step plate is removed from the aft baggage bay-door. The liners are removed from the aft baggage bay-door. If necessary, the coamings are removed from the structure. Circuit breakers are opened. The striker plates, the fittings, and their serrated plates on the structure of the aft baggage bay-door are replaced. If removed, the coamings are installed. The step plate is installed. The circuit breakers are closed. The operational test and the adjustment of the aft baggage bay-door are done. The fits and clearances check of the aft baggage bay-door is done. The liners are installed. The aft baggage bay-door is closed.

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 3 of 31 Jun 17/2013 Revision B, Sep 16/2013 D. Compliance Recommended Service Bulletin. Bombardier recommends that this service bulletin be done as shown in the table that follows, unless otherwise directed by the airworthiness authority of the operator:
COMPLIANCE INSPECTION RESULT INSTRUCTIONS REPEATED INSPECTION

INTERVAL

It is necessary to do PART A of this service bulletin at no more than 600 flight hours from the release date of this service bulletin. If a crack or obvious deformations are found on one of thestriker plates or the fittings. Do PART B of this service bulletin before the next flight. None.

OR If no cracks or obvious deformations are found on all of the striker plates and the fittings. None. Do PART A of this service bulletin at no more than 2000 flight hours from the last time PART A was done. It is necessary to do PART B at no more than 6000 flight hours from the release date of this service bulletin. None. None. It is not necessary to do PART A of this service bulletin when PART B of this service bulletin is done. 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 670BA−52−037

SB 670BA−52−037 Page 4 of 31 Jun 17/2013 Revision B, Sep 16/2013 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 email at thd.crj@aero.bombardier.com. FOR PART A It will take an estimated 1.00 man-hour to complete PART A of this service bulletin. The man-hours are divided in the table that follows: TASK MAN-HOURS (1) Job Set-Up 0.25 (2) Procedure 0.50 (3) Test N/A (4) Job Close-Out 0.25

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 5 of 31 Jun 17/2013 Revision B, Sep 16/2013 FOR PART B It will take an estimated 22.0 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 4.0 (2) Procedure 6.0 (3) Test 6.0 (4) Job Close-Out 6.0
G. Material − Price and Availability (1) The kits in the tables that follow are available from Bombardier Commercial Aircraft. NOTE: For a list of kit contents, refer to paragraph 3.A. For Aircraft 10303 thru 10331, 15257 thru 15271, 15273 thru 15276, 15278, 19011 thru 19022
KIT NUMBER NAME 670BA52037K2 Aft Baggage Bay-Door − Fitting Replacement
For all aircraft
KIT NUMBER NAME 670BA52037K1 Aft Baggage Bay-Door − Fitting Replacement

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 6 of 31 Jun 17/2013 Revision B, Sep 16/2013 (2) Please send a purchase order to the address below to schedule kit(s) 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) The parts in the table that follows are necessary to do this service bulletin and are available from Bombardier Commercial Aircraft.

PART NUMBER NAME QTY NAS8702−3 Screw 20 MS21042L08 Nut 20 MS24694−S54 Screw 15 (4) Please send a purchase order to the address below to schedule parts 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. (5) Refer to paragraph 3.B. for a list of consumables for this service bulletin. 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 670BA−52−037

SB 670BA−52−037 Page 7 of 31 Jun 17/2013 Revision B, Sep 16/2013 I. Weight and Balance Not changed. J. Electrical Load Data Not changed. K. References Restriction and/or Special Instruction (RSI) C−52−1550−00, Revision C Modification Summary 670T014042, Revision B Refer to the SB Introduction document for definition or explanation of service bulletin content. Aircraft Maintenance Manual (AMM) Structural Repair Manual (SRM) Electrical/Electronic Components − Standard Practices Manual (ESPM) Nondestructive Testing Manual (NDTM) For Bombardier reference only: PCA 75331 L. Other Publications Affected Aircraft Illustrated Parts Catalogue (AIPC) M. Relationship Chart

PRE-SB PART NUMBER NAME POST-SB PART NUMBER NAME MM670−35531−001 Serrated plate AF670−35531−001 Serrated plate MM670−35531−003 Serrated plate AF670−35534−001 Serrated plate MM670−35532−001 Serrated plate AF670−35532−001 Serrated plate MM670−35532−003 Serrated plate AF670−35533−001 Serrated plate MM670−35536−001 Laminated shim AF670−35536−001 Laminated shim MM670−35536−003 Laminated shim AF670−35539−001 Laminated shim MM670−35537−001 Laminated shim AF670−35537−001 Laminated shim

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 8 of 31 Jun 17/2013 Revision B, Sep 16/2013 PRE-SB PART NUMBER NAME POST-SB PART NUMBER NAME MM670−35537−003 Laminated shim AF670−35538−001 Laminated shim S5316−40−75−197 Laminated shim S10249−40−75−197C Laminated shim For Aircraft 10303 thru 10331, 15257 thru 15271, 15273 thru 15276, 15278, 19011 thru 19022
PRE-SB PART NUMBER NAME POST-SB PART NUMBER NAME MM670−35529−001 Fitting AF670−35529−001 Fitting

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 9 of 31 Jun 17/2013 Revision B, Sep 16/2013 2. ACCOMPLISHMENT INSTRUCTIONS PART A − Detailed Visual Inspection of the Striker Plates and the Fittings Reference Information
REFERENCE DESIGNATION AMM 12−00−00−867−801 Standard Aircraft Configuration for Maintenance

NDTM 51−20−009−210 Visual − Inspection Procedures A. Job Set-Up (1) Make sure that the aircraft is in standard configuration for maintenance (refer to AMM 12−00−00−867−801). (2) Open the aft baggage bay-door.
B. Procedure Refer to Figure 1 . (1) Do a detailed visual inspection of the two striker plates and the eight fittings for cracks or obvious deformations (refer to NDTM 51−20−009−210). (2) If a crack or obvious deformations are found on one of the striker plates or the fittings, do PART B. (3) If no cracks and no obvious deformations are found on the striker plates and the fittings, do the Job Close-Out. C. Job Close-Out (1) Remove all tools, equipment, and unwanted materials from the work area. (2) Close the aft baggage bay-door. (3) When PART A of this service bulletin is completed, make this entry in theapplicable logbooks: Service Bulletin 670BA−52−037, Revision B, Door − Aft Baggage Bay Door − Replacement of the Fittings Around the Aft Baggage Bay-Door, PART A, incorporated."

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 10 of 31 Jun 17/2013 Revision B, Sep 16/2013 Fittings and Striker Plates − Detailed Visual Inspection Figure 1 (Sheet 1 of 1)ba0010a01.cgm, cr, 08−mar−2013 FS1047.00
FS1031.00

FS1015.00

FS1000.00

STGR11L

STGR17L STRIKER PLATE (REF)
FITTING (REF) A

A

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 11 of 31 Jun 17/2013 Revision B, Sep 16/2013 PART B − Replacement of the Striker Plates and the Fittings Reference Information
REFERENCE DESIGNATION AMM 12−00−00−867−801 Standard Aircraft Configuration for Maintenance AMM 20−21−00−910−801 Torquing of Threaded Fasteners AMM 24−00−00−910−801 Electrical/Electronic Safety Precautions AMM 24−00−00−910−802 Electrostatic Discharge Safety Precautions AMM 25−52−01−000−801 Removal of the Aft Baggage Bay Liners AMM 25−52−01−400−801 Installation of the Aft Baggage Bay Liners AMM 51−23−00−390−810 Wet Installation of Fasteners AMM 52−31−00−220−801 Fits and Clearances of the Aft Baggage Bay Door AMM 52−31−00−710−801 Operational Test of the Aft Baggage Bay Door

AMM 52−31−00−820−801 Adjustment of the Aft Baggage Bay Door

AMM 53−62−34−000−801 Removal of the Aft Baggage-Bay Step-Plate AMM 53−62−34−400−801 Installation of the Aft Baggage-Bay Step-Plate SRM 51−21−11−001−001 Corrosion Prevention Procedures SRM 51−21−16−001−001 Finish Codes SRM 51−23−00−001−001 Pressure, Environmental, Fuel Tank and Firewall Sealing SRM 51−25−06−001−001 Fluid-Resistant (FR) Epoxy Primer SRM 51−25−16−001−001 Fluid-Resistant (FR) Polyurethane Topcoat SRM 51−26−00−001−001 Cleaning SRM 51−41−02−001−001 Bolts, Screws and Related Items SRM 51−42−06−001−001 Solid Rivets

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 12 of 31 Jun 17/2013 Revision B, Sep 16/2013 D. Job Set-Up (1) Make sure that the aircraft is in standard configuration for maintenance (refer to AMM 12−00−00−867−801). (2) Open the aft baggage bay-door. (3) If necessary, remove the step plate installed below the aft baggage bay-door (refer to AMM 53−62−34−000−801). (4) Remove the necessary aft baggage bay-liners to get access to the structure area around the aft baggage bay-door (refer to AMM 25−52−01−000−801). Refer to Figure 2 . (5) If necessary, remove the lower coaming (1) and the upper coaming (2) from the structure around the aft baggage bay-door as follows: (a) Remove the screws (3) from the lower coaming (1) and the upper coaming (2). CAUTION: DO NOT USE TOO MUCH PRESSURE TO REMOVE THE SCREWS (6) FROM THE LOWER AND THE UPPER COAMINGS (1) AND (2), YOU CAN CAUSE DAMAGE TO THE BRACKETS THAT ARE INSTALLED UNDER THE COAMINGS (1) AND (2). (b) Remove the nuts (4), the washers (5), and the screws (6) from the lower coaming (1) and the upper coaming (2). (c) Remove the sealant from the structure around the aft baggage bay-door with a plastic scraper or equivalent. (d) Remove the sealant from the lower coaming (1) and the upper coaming (2) with a plastic scraper or equivalent. Refer to Figure 3 . (6) Carefully remove the sealant from the fittings (5), (11), and (27), and their related hardware.

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 13 of 31 Jun 17/2013 Revision B, Sep 16/2013 WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS, INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT CAN OCCUR. (7) Obey all the electrical/electronic safety precautions (refer to AMM 24−00−00−910−801). (8) Open, safety, and tag the circuit breakers that follow: CB PANEL CB NO. NAME

CBP−1 A12 HEATERS TAT CBP−1 A13 HEATERS AOA R CBP−1 A14 HEATERS PITOT R CBP−1 G1 PSEU CH A CBP−1 G14 HEATERS STATIC R CBP−1 LOWER T7 HEATERS PITOT L
CBP−1 LOWER T8 HEATERS AOA L
CBP−1 LOWER T9 HEATERS PITOT STBY
CBP−2 G1 PSEU CH B CBP−2 P1 PSEU CH A CBP−2 P2 PSEU CH B CBP−2 LOWER R8 DOOR IND 1
CBP−2 LOWER R9 DOOR IND 2
CBP−2 LOWER S1 HEATERS STATIC L

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 14 of 31 Jun 17/2013 Revision B, Sep 16/2013 E. Procedure Refer to Figure 3 . (1) Remove the screws (2), the striker plates (1), the shims (3), and the laminated shims (4) from the upper structure area of the aft baggage-bay-door. (2) Discard the striker plates (1), the shims (3), and the laminated shims (4). (3) Remove the fittings (5) and (11) from FS1000.00 as follows: NOTE: You can make marks on the structure to show the position of the fittings (5) and (11) to help the installation of the fittings (5) and (11) in a subsequent step. (a) Between stringer 13 and stringer 14, remove the bolts (6), the washers (7), the fitting (5), the serrated plate (8), and the laminated shim (9) from the structure. (b) Between stringer 14 and stringer 15, remove the bolts (12), the washers (13), the fitting (11), the serrated plate (14), the laminated shim (15), the shim (31), and the proximity sensor assembly (32) from the structure. (c) Between stringer 15 and stringer 16, remove the bolts (6), the washers (7), the fitting (5), the serrated plate (8), and the laminated shim (9) from the structure. For Aircraft 10303 thru 10331, 15257 thru 15271, 15273 thru 15276, 15278, 19011 thru 19022 (4) Discard the fitting (5), the serrated plates (8) and (14), and the laminated shim (9) and (15). For Aircraft 10332, 10333, 15272, 15277, 15279 thru 15284, 19023, and 19024 (5) Discard the serrated plates (8) and (14), and the laminated shim (9) and (15). For all aircraft (6) Remove the fittings (5) and (27) from FS1047.00 as follows: NOTE: You can make marks on the structure to show the position of the fittings (5) and (27) to help the installation of the fittings (5) and (27) in a subsequent step. (a) Between stringer 13 and stringer 14, remove the bolts (22), the washers (7), the fitting (5), the serrated plate (23), and the laminated shim (24) from the structure.

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 15 of 31 Jun 17/2013 Revision B, Sep 16/2013 (b) Between stringer 14 and stringer 15, remove the bolts (28), the washers (13), the fitting (27), the serrated plate (29), and the laminated shim (30) from the structure. (c) Between stringer 15 and stringer 16, remove the bolts (26), the washers (7), the fitting (5), the serrated plate (23), and the laminated shim (24) from the structure. For Aircraft 10303 thru 10331, 15257 thru 15271, 15273 thru 15276, 15278, 19011 thru 19022 (7) Discard the fittings (5), the serrated plates (23) and (29), and the laminated shims (24) and (30). For Aircraft 10332, 10333, 15272, 15277, 15279 thru 15284, 19023, and 19024 (8) Discard the serrated plates (23) and (29), and the laminated shims (24) and (30). For Aircraft 10303 thru 10331, 15257 thru 15271, 15273 thru 15276, 15278, 19011 thru 19022 (9) Remove the fittings (16) and (21) from the bottom structure of the aft baggage-bay-door area as follows: NOTE: You can make marks on the structure to show the position of the fittings (16) and (21) to help the installation of fittings (16) and (21) in a subsequent step. (a) At FS1015.00, remove the bolts (17), the washers (18), the fitting (16), the serrated plate (19), and the laminated shim (20) from the structure. (b) At FS1031.00, remove the bolts (17), the washers (18), the fitting (21), the serrated plate (19), and the laminated shim (20) from the structure. (c) Discard the fittings (16) and (21), the serrated plates (19), and the laminated shims (20). For all aircraft (10) Install the striker plates (1) on the upper structure of the aft baggage bay-door area as follows: (a) Clean the installation areas of the striker plates (1) with solvent cleaner (refer to SRM 51−26−00−001−001).

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 16 of 31 Jun 17/2013 Revision B, Sep 16/2013 (b) At FS1015.00, install the laminated shim (4), the shim (3) and the striker plate (1) on the structure with the screws (2). NOTE: The pre-mod and the post-mod part numbers for the striker plate (1) and the shim (3) are the same. It is not permitted to install the the striker plate (1) and the shim (3) that were discarded in a step before. 1 Temporarily attach the laminated shim (4), the shim (3), and the striker plate (1) together. 2 Backdrill two holes to a diameter of 0.190 to 0.194 in. (4.83 to 4.93 mm) from the striker plate (1) to the laminated shim (4) and the shim (3). 3 Remove the burrs and sharp edges from the laminated shim (4) and the shim (3). 4 Apply chemical conversion coating on the bare metal areas of the laminated shim (4) and the shim (3) (refer to SRM 51−21−11−001−001). 5 Apply a layer of of fluid-resistant primer on the bare metal areas of the laminated shim (4) and the shim (3) (refer to SRM 51−25−06−001−001). 6 If necessary, peel the laminated shim (4). NOTE: The removed laminated shim (4) can be used as a reference for the thickness of the new laminated shim (4). 7 Apply a layer of fluid-resistant primer on the laminated shim (4) (refer to SRM 51−25−06−001−001). 8 Install the laminated shim (4), the shim (3) and the striker plate (1) on the structure with the screws (2).

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 17 of 31 Jun 17/2013 Revision B, Sep 16/2013 (c) At FS1031.00, install the laminated shim (4), the shim (3) and the striker plate (1) on the structure with the screws (2). NOTE: The pre-mod and the post-mod part numbers for the striker plate (1) and the shim (3) are the same. It is not permitted to install the the striker plate (1) and the shim (3) that were discarded in a step before. 1 Temporarily attach the laminated shim (4), the shim (3), and the striker plate (1) together. 2 Backdrill two holes to a diameter of 0.190 to 0.194 in. (4.83 to 4.93 mm) from the striker plate (1) to the laminated shim (4) and the shim (3). 3 Remove the burrs and sharp edges from the laminated shim (4) and the shim (3). 4 Apply chemical conversion coating on the bare metal areas of the laminated shim (4) and the shim (3) (refer to SRM 51−21−11−001−001). 5 Apply a layer of of fluid-resistant primer on the bare metal areas of the laminated shim (4) and the shim (3) (refer to SRM 51−25−06−001−001). 6 If necessary, peel the laminated shim (4). NOTE: The removed laminated shim (4) can be used as a reference for the thickness of the new laminated shim (4). 7 Apply a layer of fluid-resistant primer on the laminated shim (4) (refer to SRM 51−25−06−001−001). 8 Install the laminated shim (4), the shim (3) and the striker plate (1) on the structure with the screws (2). (11) At FS1000.00, install the fittings (5) and (11) on the structure area of the aft baggage bay-door as follows: (a) Clean the installation areas of the fittings (5) and (11) with solvent cleaner (refer to SRM 51−26−00−001−001).

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 18 of 31 Jun 17/2013 Revision B, Sep 16/2013 (b) Between stringer 13 and stringer 14, install the laminated shim (9), the serrated plate (8), and the fitting (5) on the structure with the washers (7), and the bolts (6). NOTE: For Aircraft 10332, 10333, 15272, 15277, 15279 thru 15284, 19023, and 19024, the removed fitting (5) is used for the installation. 1 If necessary, peel the laminated shim (9). NOTE: The removed laminated shim (9) can be used as a reference for the thickness of the new laminated shim (9). 2 Apply a layer of fluid-resistant primer on the laminated shim (9) (refer to SRM 51−25−06−001−001). (c) Between stringer 14 and stringer 15, install the shim (31), the proximity sensor assembly (32), the laminated shim (15), the serrated plate (14), and the fitting (11) on the structure with the washers (13), and the bolts (12). 1 If necessary, peel the laminated shim (15). NOTE: The removed laminated shim (15) can be used as a reference for the thickness of the new laminated shim (15). 2 Apply a layer of fluid-resistant primer on the laminated shim (15) (refer to SRM 51−25−06−001−001). (d) Between stringer 15 and stringer 16, install the laminated shim (9), the serrated plate (8), and the fitting (5) on the structure with the washers (7), and the bolts (6). NOTE: For Aircraft 10332, 10333, 15272, 15277, 15279 thru 15284, 19023, and 19024, the removed fitting (5) is used for the installation. 1 If necessary, peel the laminated shim (9). NOTE: The removed laminated shim (9) can be used as a reference for the thickness of the new laminated shim (9). 2 Apply a layer of fluid-resistant primer on the laminated shim (9) (refer to SRM 51−25−06−001−001). (12) At FS1047.00, install the fittings (5) and (27) on the structure area of the aft baggage bay-door as follows: (a) Clean installation areas of the fittings (5) and (27) with solvent cleaner (refer to SRM 51−26−00−001−001).

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 19 of 31 Jun 17/2013 Revision B, Sep 16/2013 (b) Between stringer 13 and stringer 14, install the laminated shim (24), the serrated plate (23), and the fitting (5) on the structure with the washers (7), and the bolts (22). NOTE: For Aircraft 10332, 10333, 15272, 15277, 15279 thru 15284, 19023, and 19024, the removed fitting (5) is used for the installation. 1 If necessary, peel the laminated shim (24). NOTE: The removed laminated shim (24) can be used as a reference for the thickness of the new laminated shim (24). 2 Apply a layer of fluid-resistant primer on the laminated shim (24) (refer to SRM 51−25−06−001−001). (c) Between stringer 14 and stringer 15, install the laminated shim (30), the serrated plate (29), and the fitting (27) on the structure with the washers (13), and the bolts (28). 1 If necessary, peel the laminated shim (30). NOTE: The removed laminated shim (30) can be used as a reference for the thickness of the new laminated shim (30). 2 Apply a layer of fluid-resistant primer on the laminated shim (30) (refer to SRM 51−25−06−001−001). (d) Between stringer 15 and stringer 16, install the laminated shim (24), the serrated plate (23), and the fitting (5) on the structure with the washers (7), and the bolts (26). NOTE: For Aircraft 10332, 10333, 15272, 15277, 15279 thru 15284, 19023, and 19024, the removed fitting (5) is used for the installation. 1 If necessary, peel the laminated shim (24). NOTE: The removed laminated shim (24) can be used as a reference for the thickness of the new laminated shim (24). 2 Apply a layer of fluid-resistant primer on the laminated shim (24) (refer to SRM 51−25−06−001−001).

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 20 of 31 Jun 17/2013 Revision B, Sep 16/2013 For Aircraft 10303 thru 10331, 15257 thru 15271, 15273 thru 15276, 15278, 19011 thru 19022 (13) Install the fittings (16) and (21) on the lower structure of the aft baggage bay-door area as follows: (a) Clean the installation areas of the fittings (16) and (21) with solvent cleaner (refer to SRM 51−26−00−001−001). (b) At FS1015.00, install the fitting (16) on the structure as follows: NOTE: The pre-mod and the post-mod part numbers for the fitting (16), the serrated plate (19), and the laminated shim (20). are the same. It is not permitted to install the fitting (16), the serrated plate (19), and the laminated shim (20) that were discarded in a step before. 1 If necessary, peel the laminated shim (20). NOTE: The removed laminated shim (20) can be used as a reference for the thickness of the new laminated shim (20). 2 Apply a layer of fluid-resistant primer on the laminated shim (20) (refer to SRM 51−25−06−001−001). 3 Apply a layer of fluid-resistant polyurethane topcoat on the laminated shim (20) (refer to SRM 51−25−16−001−001). 4 Apply sealant on the faying surfaces between the structure sill and the laminated shim (20) (refer to SRM 31−23−00−001−001). 5 Apply sealant on the faying surfaces between the laminated shim (20) and the serrated plate (19) (refer to SRM 51−23−00−001−001). 6 Install the laminated shim (20), the serrated plate (19) and the fitting (16) on the structure with the washers (18) and the bolts (17).

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 21 of 31 Jun 17/2013 Revision B, Sep 16/2013 (c) At FS1031.00, install the fitting (21) on the structure as follows: NOTE: The pre-mod and the post-mod part numbers for the fitting (21), the serrated plate (19), and the laminated shim (20). are the same. It is not permitted to install the fitting (21), the serrated plate (19), and the laminated shim (20) that were discarded in a step before. 1 If necessary, peel the laminated shim (20). NOTE: The removed laminated shim (20) can be used as a reference for the thickness of the new laminated shim (20). 2 Apply a layer of fluid-resistant primer on the laminated shim (20) (refer to SRM 51−25−06−001−001). 3 Apply a layer of fluid-resistant polyurethane topcoat on the laminated shim (20) (refer to SRM 51−25−16−001−001). 4 Apply sealant on the faying surfaces between the structure sill and the laminated shim (20) (refer to SRM 51−23−00−001−001). 5 Apply sealant on the faying surfaces between the laminated shim (20) and the serrated plate (19) (refer to SRM 51−23−00−001−001). 6 Install the laminated shim (20), the serrated plate (19) and the fitting (21) on the structure with the washers (18) and the bolts (17).

.

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 22 of 31 Jun 17/2013 Revision B, Sep 16/2013 F. Job Close-Out (1) Remove all tools, equipment, and unwanted materials from the work area. Refer to Figure 2 . (2) If removed, install the lower coaming (1) and the upper coaming (2) on the structure as follows: CAUTION: IF TOO MUCH PRESSURE IS USED TO INSTALL THE SCREWS (6) ON THE LOWER AND THE UPPER COAMINGS (1) AND (2), DAMAGE CAN OCCUR TO THE BRACKETS THAT ARE INST ALLED UNDER THE LOWER AND THE UPPER COAMINGS (1) AND (2). (a) Wet-install the screws (3) through the lower coaming (1) and the lower structure (refer to AMM 51−23−00−390−810). (b) Wet-install the screws (3) through the upper coaming (2) and the upper structure (refer to AMM 51−23−00−390−810). (c) Wet-install the screws (6) through the lower coaming (1), the upper coaming (2), the side structure, the washers (5), and the nuts (4) (refer to AMM 51−23−00−390−810). (d) Apply a layer of polyurethane topcoat on the head of the screws (3) and (6) (refer to SRM 51−25−16−001−001). (3) Apply a layer of polyurethane topcoat on the applicable structure areas of the aft baggage bay-door (refer to SRM 51−21−11−001−001 and SRM 51−25−16−001−001). (4) Remove the tags and close the circuit breakers that follow: CB PANEL CB NO. NAME

CBP−1 A12 HEATERS TAT CBP−1 A13 HEATERS AOA R CBP−1 A14 HEATERS PITOT R CBP−1 G1 PSEU CH A CBP−1 G14 HEATERS STATIC R CBP−1 LOWER T7 HEATERS PITOT L

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 23 of 31 Jun 17/2013 Revision B, Sep 16/2013 CB PANEL NAME CB NO. CBP−1 LOWER T8 HEATERS AOA L
CBP−1 LOWER T9 HEATERS PITOT STBY
CBP−2 G1 PSEU CH B CBP−2 P1 PSEU CH A CBP−2 P2 PSEU CH B CBP−2 LOWER R8 DOOR IND 1
CBP−2 LOWER R9 DOOR IND 2
CBP−2 LOWER S1 HEATERS STATIC L

(5) Do the operational test of the aft baggage bay-door (refer to AMM 52−31−00−710−801). (6) Do the adjustment of the aft baggage bay-door (refer to AMM 52−31−00−820−801). (7) Examine the fits and clearances of the aft baggage bay-door (refer to AMM 52−31−00−220−801). Refer to Figure 3 . (8) With a brush, apply a layer of sealing compound on the hardware of the fittings (5), (11), (16), (21), and (27) (refer to SRM 51−23−00−001−001). (9) Install the access panels and the liners on the structure area around the aft baggage bay-door (refer to AMM 25−52−01−400−801). (10) Apply a fillet of sealant to bond the liners around the fittings (5), (11), and (27) (refer to SRM 51−23−00−001−001). (11) Apply a fillet of sealant to bond the liners around the striker plates (1) (refer to SRM 51−23−00−001−001).

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 24 of 31 Jun 17/2013 Revision B, Sep 16/2013 Refer to Figure 2 . (12) If the upper coaming (1) and the lower coaming (2) were removed, or if the sealant was damaged during the removal of the fittings, do as follows: (a) Apply a fillet of sealant (7) between the coamings (1) and (2) and the structure as shown on Figure 2 , view C-C (refer to SRM 51−23−00−001−001). (b) Apply sealant in the clearance between the lower coaming (1) and the upper coaming (2) (refer to SRM 51−23−00−001−001). (c) Apply sealant in the clearance between the lower coaming (1) and the inboard and outboard structure (refer to SRM 51−23−00−001−001). (d) Apply sealant in the clearance between the upper coaming (2) and the inboard and outboard structure (refer to SRM 51−23−00−001−001). (13) If removed, install the step plate (refer to AMM 53−62−34−400−801). (14) Close the aft baggage bay-door. (15) When PART B of this service bulletin is completed, make this entry in theapplicable logbooks: Service Bulletin 670BA−52−037, Revision B, Door − Aft Baggage Bay Door − Replacement of the Fittings Around the Aft Baggage Bay-Door, PART B, incorporated."

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 25 of 31 Jun 17/2013 Revision B, Sep 16/2013 Coaming − Removal/Installation Figure 2 (sheet 1 of 1)ba7716a01.cgm, sc, 5−avril−2013 A

B B
A 2 4 5 6

6 5 4

4

1 3 5 6

6 5 4 1

NOTE Aft installation is shown, forward installation is opposite. 1 C 4 5

LEGEND 1. Lower coaming. 2. Upper coaming. 3. Screw. 4. Nut, self

− locking. 5. Washer. 6. Screw. 7. Sealant MIL

− PRF

− 81733 type II, class 1, grade A. C C FILLET SEAL APPLICATION (TYPICAL) 7 FS1045.1 FWD C

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 26 of 31 Jun 17/2013 Revision B, Sep 16/2013 Door Fitting − Removal/Installation Figure 3 (Sheet 1 of 2)ba7717a01.cgm, sc, 5−avril−2013 12

13 11 14 15

6 7

5 8 9 6 7 5 8 9 4 3 1 2

18

20 19 16 17 1 31 32 FS1000.00

B AT FS1031.00 1
20 19 21 17

18

C AT FS1015.00 FS1015.00 NOTES For Aircraft 10303 thru 10331 15257 thru 15271,15273 thru 15276, 15278 and 19011 thru 19022. For Aircraft 10332, 10333, 15272, 15277, 15279 thru 15284, 19023 and 19024. 1

2

3

1

2 LEGEND

1. Striker plate MM670

− 35697

− 001. 2. Screw. 3. Shim S5324

− 80

− 75

− 197B. 4. Laminated shim S5316

− 40

− 75

− 197 (Pre

− Mod), S10249

− 40

− 75

− 197C (Post

− Mod). 5. Fitting MM670

− 35529

− 001 (Pre

− Mod), AF670

− 35529

− 001 (Post

− Mod). 5. Fitting MM670

− 35529

− 001. 6. Bolt. 7. Washer. 8. Serrated plate MM670

− 35531

− 001(Pre

− Mod), AF670

− 35531

− 001 (Post

− Mod). 9. Laminated shim MM670

− 35536

− 001 (Pre

− Mod), AF670

− 35536

− 001 (Post

− Mod). 11. Fitting. 12. Bolt. 13. Washer. 14. Serrated plate MM670

− 35532

− 001 (Pre

− mod), AF670

− 35532

− 001 (Post

− Mod). 15. Laminated shim MM670

− 35537

− 001 (Pre

− Mod), AF670

− 35537

− 001 (Post

− Mod). 16. Fitting MM670

− 35651

− 001. 17. Bolt. 18. Washer. 19. Serrated plate MM670

− 35652

− 001. 20. Laminated shim MM670

− 35654

− 001. 21. Fitting MM670

− 35653

− 001. 31. Shim. 32. Proximity sensor assembly. C

A B 3 A Same striker plate installation for FS1031.00.

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 27 of 31 Jun 17/2013 Revision B, Sep 16/2013 Door Fitting − Removal/Installation Figure 3 (Sheet 2 of 2) Aba7717a02.cgm, sc, 5−avril−2013 28

13

27 29 30

26 7 5 23 24 22 7 5 23 24

D D

NOTES For Aircraft 10303 thru 10331, 15257 thru 15271, 15273 thru 15276, 15278 and 19011 thru 19022. For Aircraft 10332, 10333, 15272, 15277 15279 thru 15284, 19023 and 19024. 1
2 SEALANT (REF) TYPICAL APPLICATION OF SEALANT ON BOLTS BOLT (REF) 1
2 LEGEND 5. Fitting MM670

− 35529

− 001 (Pre

− Mod), AF670

− 35529

− 001 (Post

− Mod). 5. Fitting MM670

− 35529

− 001. 6. Bolt. 7. Washer. 13. Washer. 22. Bolt. 23. Serrated plate MM670

− 35531

− 003 (Pre

− Mod), AF670

− 35534

− 001 (Post

− Mod). 24. Laminated shim MM670

− 35536

− 003 (Pre

− Mod). AF670

− 35539

− 001 (Post

− Mod). 26. Bolt. 27. Fitting. 28. Bolt. 29. Serrated plate MM670

− 35532

− 003 (Pre

− Mod). AF670

− 35533

− 001 (Post

− Mod). 30. Laminated shim MM670

− 35537

− 003 (Pre

− Mod), AF670

− 35538

− 001 (Post

− Mod). FS1047.00

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 28 of 31 Jun 17/2013 Revision B, Sep 16/2013 3. MATERIAL INFORMATION

A. Kit Information Kit Contents:
KIT 670BA52037K1 PART NUMBER QTY NAME ALTERNATE PARTS NOTES
AF670−35531−001 2 Serrated plate AF670−35532−001 1 Serrated plate AF670−35533−001 1 Serrated plate AF670−35534−001 2 Serrated plate AF670−35536−001 2 Laminated shim AF670−35537−001 1 Laminated shim AF670−35538−001 1 Laminated shim AF670−35539−001 2 Laminated shim MM670−35697−001 2 Striker S10249−40−75−197C 2 Laminated shim S5324−80−75−197B 2 Shim

KIT 670BA52037K2 PART NUMBER QTY NAME ALTERNATE PARTS NOTES
AF670−35529−001 4 Fitting MM670−35651−001 1 Fitting MM670−35652−001 2 Serrated plate MM670−35653−001 1 Fitting MM670−35654−001 2 Laminated shim

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 29 of 31 Jun 17/2013 Revision B, Sep 16/2013 B. Consumable Information The materials that follow are necessary to do this service bulletin. You can order them from Bombardier or purchase them 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 MIL−C−81706 Class 1A As necessary Chemical conversion coating 05−025 N/A As necessary Scraper, nonmetallic 05−105 CMS 565−02 As necessary Polyurethane topcoat,topcoat, fluidresistant 07−001 MIL−A−46106, Type 1, Grade III As necessary Sealing compound, high temperature (red) 08−015 MIL−PRF−81733, Type 1 As necessary Compound, sealing and coating, corrosion inhibitive 09−011 MIL−PRF−81733, Type IV As necessary Compound, sealing and coating, corrosion inhibitive 09−020 TT−I−735 As necessary Isopropyl alcohol 11−004 CMS 565−01 As necessary Fluid-resistant epoxy primer 13−006 Refer to AMM 51−31−00−992−801
NOTE: To complete this list of consumables, refer to the different tasks that are given as references in this service bulletin.

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 30 of 31 Jun 17/2013 Revision B, Sep 16/2013 C. Special Tools and Equipment For a list of special tools and equipment, refer to the different tasks that are given as references in this service bulletin. D. Disposition of Parts The table that follows shows the disposition of parts on the aircraft (or spares), and the relationship between these parts to the new parts to be installed through the incorporation of this service bulletin. PRE-SB PART NUMBER NAME QTY DC POST-SB PART NUMBER
MM670−35531−001 Serrated plate 2 DIS AF670−35531−001
MM670−35531−003 Serrated plate 2 DIS AF670−35534−001
MM670−35532−001 Serrated plate 1 DIS AF670−35532−001
MM670−35532−003 Serrated plate 1 DIS AF670−35533−001
MM670−35536−001 Laminated shim 2 DIS AF670−35536−001
MM670−35536−003 Laminated shim 2 DIS AF670−35539−001
MM670−35537−001 Laminated shim 1 DIS AF670−35537−001
MM670−35537−003 Laminated shim 1 DIS AF670−35538−001
S5316−40−75−197 Laminated shim 2 DIS S10249−40−75−197C

### SERVICE BULLETIN 670BA−52−037

SB 670BA−52−037 Page 31 of 31 Jun 17/2013 Revision B, Sep 16/2013 For Aircraft 10303 thru 10331, 15257 thru 15271, 15273 thru 15276, 15278, 19011 thru 19022 PRE-SB PART NUMBER NAME QTY DC POST-SB PART NUMBER MM670−35529−001 Fitting 4 DIS AF670−35529−001
For all aircraft Disposition code (DC): DIS: Discard Part. 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: 

##     

 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