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.

1
SB 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

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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

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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 the

striker 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

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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

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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

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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

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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

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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

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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 the

applicable 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

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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

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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

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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

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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
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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.
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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).
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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

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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).
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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 INSTALLED

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 the

applicable 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

4 2

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

FWD FS1045.1

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)

A

ba7717a02.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.

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