Electrical Power − Air Driven Generator − Replacement of the Wire Cable and

Backshell of ADG Mating Connector G4P1

1. PLANNING INFORMATION

A. Effectivity

(1) Aircraft Affected:

Service Bulletin: CL−600−2C10 Canadair Regional Jet (CRJ)

Aircraft Serial Numbers 10003 thru 10302.

Production: This change will be incorporated before delivery on

CL−600−2C10 Canadair Regional Jet (CRJ)

Aircraft Serial Numbers 10303 and subsequent.

Service Bulletin: CL−600−2D15 Canadair Regional Jet (CRJ) and

CL−600−2D24 Canadair Regional Jet (CRJ)

Aircraft Serial Numbers 15001 thru 15259.

Production: This change will be incorporated before delivery on

CL−600−2D15 Canadair Regional Jet (CRJ) and

CL−600−2D24 Canadair Regional Jet (CRJ)

Aircraft Serial Numbers 15260 and subsequent.

SERVICE BULLETIN

ATA SYSTEM: 24−23 NUMBER: 670BA−24−027

S.B. 670BA−24−027

Page 1 of 22

Sep 17/2009

Technical

Publications

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

THIS SERVICE BULLETIN MUST BE SENT TO THE LESSEE. IF THE OPERATOR HAS SOLD AIRCRAFT OR

TRANSFERRED SPARES IN THE LAST SIX MONTHS, THIS SERVICE BULLETIN MUST BE SENT TO THE

NEW OWNER, UNLESS CONFIRMATION WAS RECEIVED THAT BOMBARDIER COMMERCIAL AIRCRAFT

DIVISION HAS INCLUDED THE NEW OPERATOR ON THE DISTRIBUTION LIST.

SUBJECT:
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 Bulletin(s). Before you do this

bulletin, examine all STC, STA or equivalent action changes to

make sure this bulletin can be completed.

B. Reason

(1) Condition

The wires in the cable of ADG mating connector G4P1 (written as connector

G4P1 in this service bulletin) are silver plated. It is possible that the silver

plated wires are corroded. Corroded wires can create an open circuit and

prevent the ADG to operate correctly.

(2) Evidence

This condition was found during testing on three in−service aircraft.

(3) Objective/Benefit

This service bulletin gives the procedure to replace the wire cable, the

backshell and change the routing of connector G4P1.

The wires of the replacement cable are tin plated. Incorporation of this

service bulletin will prevent the the wires in the cable of connector G4P1

from corroding.

C. Description

Circuit breakers are opened. The main avionics−compartment door is opened.

The flight compartment floor panel is removed. The RH forward−fuselage access

panel is removed. The ADG is deployed. The external service panel assembly is

removed.

In the ADG bay, connector G4P1 is disconnected from the ADG. The wire cable

and the backshell of connector G4P1 are replaced. Two new spacer nutplates

are installed and the routing of connector G4P1 is changed.

Connector G4P1 is connected to the ADG, and the external service panel

assembly is installed. The circuit breakers are closed and return to service tests

are done. The RH forward−fuselage access panel is installed and the main

avionics−compartment door is closed.

SERVICE BULLETIN 670BA−24−027

S.B. 670BA−24−027

Page 2 of 22

Sep 17/2009
D. Compliance

Recommended Service Bulletin. Bombardier recommends that this service

bulletin be done as shown on table below or no later than six years from the

release date on this service bulletin, unless otherwise directed by the

airworthiness authority of the operator.

AIRCRAFT ACCUMULATED FLIGHT

HOURS

TIME LIMITATION TO DO THIS

SERVICE BULLETIN

15000 or more 6000 flight hours

Less than 15000 12000 flight hours

NOTE: This service bulletin must be incorporate on all aircraft, including parked

aircraft.

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.

F. Manpower

The man−hours given below are an estimate for direct labor done by an

experienced crew on an aircraft prepared for maintenance.

This estimate does not include the time necessary for:

− Administrative functions such as planning, liaison, 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.

SERVICE BULLETIN 670BA−24−027

S.B. 670BA−24−027

Page 3 of 22

Sep 17/2009
It will take an estimated 10.00 man−hours to complete this service bulletin. The

man−hours are divided as shown in the table that follows :

TASK MAN−HOURS

(1) Job Set−Up 0.75

(2) Procedure 8.00

(3) Test 0.25

(4) Job Close−Out 1.00

G. Material − Price and Availability

(1) The kit in the table that follows is available from Bombardier Commercial

Aircraft

NOTE: For a list of the kit contents, refer to paragraph 3.A

KIT NUMBER NAME

670BA24027K1 ADG Power Cable Replacement Kit

(2) Please send a purchase order to the address below to schedule the kit(s):

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 your 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.

H. Tooling − Price and Availability

There are no tool kits for this service bulletin.

SERVICE BULLETIN 670BA−24−027

S.B. 670BA−24−027

Page 4 of 22

Sep 17/2009
(1) Refer to paragraph 3.C. for a list of special tools and equipment for this

service bulletin.

I. Weight and Balance

WEIGHT ARM MOMENT [1]

+ 0.086 (lb) 201.7 (in.) + 0.017 (1000 lb·in)

+ 0.039 (kg) 5.123 (m) + 0.0002 (1000 kg·m)

[1] The value in the Moment column is divided by 1000. Refer to the Weight &

Balance Manual CSP B−041.

J. Electrical Load Data

Not changed.

K. References

− Restriction and/or Special Instruction (RSI), C−24−1154−00.

− Modification Summary 670T31774, Revision B−1.

− Aircraft Maintenance Manual (AMM), CSP B−001, Revision 28.

− Electrical/Electronic Components − Standard Practices Manual (ESPM),

CSP BC−115, Revision 21.

− Structural Repair Manual (SRM), CSP B−008, Revision 24.

− For Bombardier reference only: PCA 73581.

L. Other Publications Affected

− Aircraft Illustrated Parts Catalog (IPC), CSP B−006.

− Aircraft Illustrated Parts Catalog (IPC), CSP C−006.

− Wiring Diagram Manual (WDM), CSP B−003.

− Wiring Diagram Manual (WDM), CSP C−003.

SERVICE BULLETIN 670BA−24−027

S.B. 670BA−24−027

Page 5 of 22

Sep 17/2009
M. Relationship Chart

PRE−SB PART

NUMBER NAME POST−SB PART

NUMBER NAME

M85049/53−22W Backshell M85049/43S22W Backshell

SERVICE BULLETIN 670BA−24−027

S.B. 670BA−24−027

Page 6 of 22

Sep 17/2009
2. ACCOMPLISHMENT INSTRUCTIONS

A. Job Set−Up

(1) 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 20−51−00−000−802 Removal of Lockwire

AMM 20−51−00−400−802 Installation of Lockwire

AMM 20−51−00−000−807 Removal of Safety Cables

AMM 20−51−00−400−807 Installation of Safety Cables

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

Precautions

AMM 24−23−01−720−801 Functional Test of the ADG

AMM 24−23−01−840−801 Extension of the ADG

AMM 24−23−01−840−802 Retraction of the ADG

AMM 24−41−01−000−801 Removal of the External Service

Panel

AMM 24−41−01−400−801 Installation of the External Service

Panel

AMM 24−41−01−710−801 Operational Test of the External

Service Panel

AMM 53−00−47−000−804 Removal of the Flight Compartment

Floor Panel (221ALF)

AMM 53−00−47−400−804 Installation of the Flight

Compartment Floor Panel (221ALF)

AMM 53−12−32−000−801 Removal of the Flight Controls

Access Panels (131AL/132AR)

SERVICE BULLETIN 670BA−24−027

S.B. 670BA−24−027

Page 7 of 22

Sep 17/2009
REFERENCE DESIGNATION

AMM 53−12−32−400−801 Installation of the Flight Controls

Access Panels (131AL/132AR)

ESPM 20−11−00 Wire Stripping

ESPM 20−12−00 Wiring

ESPM 20−16−00 Crimp Wire

ESPM 20−24−00 Connectors Accessories

ESPM 20−26−00 Electrical Connectors

SRM 51−26−00−001−001 Cleaning

SRM 51−40−06−001−001 Fastener Edge Distance and Pitch

SRM 51−42−06−001−001 Solid Rivets

SRM 51−42−10−001−001 Blind Rivets

(2) Tolerance Information

Linear Tolerances Angular Tolerance

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

+/−0.03 in. +/−0.1 in. +/−0°30”

+/−0.8 mm +/−3 mm

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

bulletin except if specified differently.

(3) Make sure that the aircraft is in standard configuration for maintenance

(AMM 12−00−00−867−801).

(4) Obey all the electrical/electronic safety precautions (AMM

24−00−00−910−801).

SERVICE BULLETIN 670BA−24−027

S.B. 670BA−24−027

Page 8 of 22

Sep 17/2009
(5) Open, safety, and tag the circuit breakers that follow:

CB−PANEL CB NO. NAME

CBP−2 N6 ADG DEPLOY AUTO

CBP−2 N7 ADG DEPLOY MAN

(6) Remove the flight compartment floor panel 221ALF (AMM

53−00−47−000−804).

(7) Open the main avionics−compartment door.

(8) Remove the flight controls access panel 132AR (AMM 53−12−32−000−801).

(9) Manually extend the ADG (AMM 24−23−01−840−801).

(10) Remove the external service panel (AMM 24−41−01−000−801).

B. Procedure

Refer to Figure 1, 2, and 3.

(1) Remove and discard the wire cable between connector G4P1 and the ADG

Printed Circuit (PC) as follows:

(a) In the ADG bay, remove the lockwire or safety cable and disconnect

connector G4P1 from the ADG (AMM 20−51−00−000−802 or

AMM20−51−00−000−807).

(b) Remove the screw (5), washer (6) and the clamp (4) that attach the wire

bundle of connector G4P1 to the bonded standoff. Discard the clamp

(4), washer (6), and screw (5) (Refer to Figure 2, View B).

NOTE: The clamps (3), washers (6) and screws (5), that attached the cable

of the external service panel (2), were removed during the removal

of the external service panel from the aircraft.

(c) With an extraction tool, disconnect and remove all the wires from

connector G4P1.

(d) Loosen and remove the backshell (4) from connector G4P1. Keep

connector G4P1 (Refer to Figure 1, View B).

SERVICE BULLETIN 670BA−24−027

S.B. 670BA−24−027

Page 9 of 22

Sep 17/2009
(e) Remove the nut (9), lock washer (10), and washer (11) that attach the

terminal lug (8) of wire SAA0002N−8 to ground stud GS6 (7). Keep the

the nut (9), lock washer (10) and washer (11) (Refer to Figure 2, View

C).

(f) Disconnect, remove and discard the terminal lug (8) and wire

SAA0002N−8 from ground stud GS6 (7).

(g) Remove the lockwire or safety cable and loosen the mounting nut of

bulkhead feedthru FT2, to help the removal and installation of the wires

(AMM 20−51−00−000−802 or AMM20−51−00−000−807).

(h) In the forward avionics compartment, carefully remove the clamps that

attached the wire cable of connector G4P1. Keep all protective sleeving,

cable clamps and their mounting hardware.

(i) In the main avionics compartment , carefully remove the clamps that

attached the wire cable of connector G4P1. Keep all protective sleeving,

cable clamps and their mounting hardware.

(j) In the main avionics compartment, disconnect the terminal lugs (5) from

the terminal studs of the ADGPC (1) as follows (Refer to Figure 3, View

C):

1 Carefully open the rocker doors (2).

2 Remove the nuts (3) and washers (4) that attach the terminal lugs

(5) to the terminals studs (6) of the ADGPC (1).

3 Remove and discard the terminal lugs (5) of wires SAA0001W−8,

SAA0001B−8, and SAA0001O−8 from the terminal studs (6) of the

ADGPC (1).

(2) In the ADG bay, carefully remove and discard the two bonded standoffs on

the stiffener (Refer to Figure 2, View B).

(3) Clean the exposed bare metal areas on the stiffener with solvent.

(4) Apply primer and topcoat on the stiffener.

(5) In the ADG bay, install the brackets (12) and standoffs (14) on the stiffener

as follows (Refer to Figure 2, Views E and F):

(a) On the larger flange of the brackets (12), use the standoffs (14) for hole

locations and open two holes in each bracket (12) to a diameter of 0.128

to 0.132 in. (3.25 to 3.35 mm) (Refer to view E).

SERVICE BULLETIN 670BA−24−027

S.B. 670BA−24−027

Page 10 of 22

Sep 17/2009
(b) Temporarily install the upper bracket (12) on the inboard side of the

stiffener at 1.18 in. (30 mm) above the center of the ground stud GS6.

Make sure the two forward holes of the upper bracket (12) are at 0.63

in. (16 mm) aft of the forward edge of the stiffener.

(c) Temporarily install the lower bracket (12) on the inboard side of the

stiffener at 1.04 in. (26.4 mm) above the center of the ground stud GS2.

Make sure the two forward holes of the lower bracket (12) are at 0.63 in.

(16 mm) aft of the forward edge of the stiffener.

(d) Backdrill four holes from the each bracket (12) through the stiffener to a

diameter of 0.098 in. (2.49 mm).

(e) Open four holes in each bracket (12) and the stiffenter to a diameter of

0.162 to 0.164 (4.11 to 4.17 mm).

(f) Remove the brackets (12) from the stiffener.

(g) Remove the burrs and sharp edges from the stiffener and the brackets

(12).

(h) Clean the work area with solvent.

(i) Apply chemical conversion coating to the bare metal areas.

(j) Install the standoffs (14) on each bracket (12) with wet−installed rivets

(15) (Refer to view E).

(k) Install each bracket (12) on the stiffener with the blind bolts (13).

(l) Apply fillet sealant around the brackets (12).

(6) Install the the new wire cable and ground wire as shown in the table below

(Refer to Figure 1, Sheet 1 of 2):

WIRE FROM TERMINAL TO TERMINAL W

SAA0001W−8 G4P1−A M39029/

29−214

ADGPC−PH−A MS25036−116 1D

SAA0001B−8 G4P1−B M39029/

29−214

ADGPC−PH−B MS25036−116 1D

SAA0001O−8 G4P1−C M39029/

29−214

ADGPC−PH−C MS25036−116 1D

SAA0002N−8 G4P1−D M39029/

29−214

GS6 MS25036−116 −

SERVICE BULLETIN 670BA−24−027

S.B. 670BA−24−027

Page 11 of 22

Sep 17/2009
(a) In the main avionics compartment, install the new cable with the clamps

screws and washers.

NOTE: Make sure that you obey the wire separation ’W’ code.

(b) Route and install the new cable from the main avionics compartment to

the forward avionics compartment.

(c) Cut the wires of the new cable to the correct length.

(d) With a wire stripper, remove the insulation from the wire ends.

(e) With a crimping tool, install the applicable terminal lugs on the wires of

the new cable.

(f) Install the terminal lugs (5) on the terminals (6) of the ADGPC (1) with

the washer (4) and nut (3) (Refer to Sheet 3, View C).

(g) Torque the nut (3) from 33 to 41.5 lbf•in (3.82 to 4.69 N•m).

(h) From the right access hole, put the wires of the new cable through

bulkhead feedthru FT2.

(i) Tighten bulkhead feedthru FT2 and secure with lockwire or safety cable

(AMM 20−51−00−400−802 or AMM20−51−00−400−807).

(j) Remove and discard the supplied screws and lock washers from the

saddle clamp of the new backshell (4). Keep the saddle clamp (Refer to

Figure 1, View B).

(k) Put the wires for connector G4P1 through the sleeve (5), identification

sleeve (6) and the new backshell (4) (Refer to Figure 1, View B).

(l) Cut the wires of the new cable to the correct length.

NOTE: Make sure that the length of the wire cable between the backshell

(4) of connector G4P1 and the clamp is 13 in. (330.2 mm).

(m) With a wire stripper, remove the insulation from the wire ends.

(n) With a crimping tool, install the applicable terminal on the wires of the

new cable.

(o) With an insertion tool, install the wires of the new cable in connector

G4P1 at the locations given.

SERVICE BULLETIN 670BA−24−027

S.B. 670BA−24−027

Page 12 of 22

Sep 17/2009
(p) Cut new wire SA0002N–8 to the correct length.

(q) With a crimping tool, install the terminal lug (20) on new wire

SA0002N–8.

(r) Install the terminal lug (20) of wire SA0002N–8 to ground stud GS6 (7)

with the washer (11), lock washer (10) and nut (9).

(s) Torque the nut.

(t) Do a continuity check of the installed wires.

(u) Connect connector G4P1 to the ADG.

(v) Put the backshell (4) of connector G4P1 at the 8 o’clock position (Refer

to Figure 1, View C).

(w) Tighten and torque the backshell.

(x) Attach the wire bundle to the backshell (4) of connector G4P1 as follows

(Refer to Figure 1, View B):

1 Apply 4−8 turns of fiberglass tape around the wire bundle.

2 Install the saddle clamp, on the taped area of the wire bundle, with

the screws (1) lock washers (2) and washers (3).

NOTE: Make sure that the taped area of the wire bundle does not

move inside the saddle clamp and there is no tension on the

terminals and wires.

(y) With a heat gun, apply heat to shrink the identification sleeve (6).

(7) Install the external service panel with the new clamps (16), washers (19),

and screws (18) (AMM 24−41−01−400−801).

(8) In the ADG bay, attach the bundle of connector G4P1 to the new standoff

(14) with the clamp (17), washer (19), and screw (18).

NOTE: Make sure that the length of the wire cable between the backshell (4) of

connector G4P1 and the clamp (17) is 13 in. (330.2 mm).

(9) Safety connector G4P1 to the adjacent screw with lockwire or safety cable

(AMM 20−51−00−400−802 or AMM20−51−00−400−807).

(10) As necessary, install the protective sleeving on the new wires to prevent

chafing.

SERVICE BULLETIN 670BA−24−027

S.B. 670BA−24−027

Page 13 of 22

Sep 17/2009
ba5929a01.cgm

13.0 in. (330 mm)

1 2 3

LEGEND

PRE−MOD

SAA0001W−8

SAA0001B−8

SAA0001O−8

AIR DRIVEN

GENERATOR

C

B

A

G4P1

G4 FS193R

GS6

D SAA0002N−8 CLAMP

13.0 in. (33.0 cm)

W1D

ADGPC FS400

1. Screw MS35206−246.

2. Lock washer MS35338−42.

3. Washer NAS1149DN816J.

4. Backshell

 M85049/53−22W (PRE−MOD)

 M85049/43S22W (POST−MOD).

5. Sleeve S10155E8.

6. Identification sleeve.

4

G4P1

6

5

POST−MOD

4

G4P1

SADDLE

CLAMP

(REF)

FIBERGLASS

(REF)

FS201.75

FS202R

FT2

SAA0001W−8

SAA0001B−8

SAA0001O−8

A162

ADG POWER PH−A

ADG POWER PH−B

ADG POWER PH−C

A

A

B

B

B

SERVICE BULLETIN 670BA−24−027

Connector G4P1 and Backshell − Wiring Changes

Figure 1 (Sheet 1 of 2)

S.B. 670BA−24−027

Page 14 of 22

Sep 17/2009
ba5929a02.cgm

A

12

9 3

6

8

C

C

A

BACKSHELL

POSITION

SERVICE BULLETIN 670BA−24−027

Connector G4P1 and Backshell − Wiring Changes

Figure 1 (Sheet 2 of 2)

S.B. 670BA−24−027

Page 15 of 22

Sep 17/2009
A

5

6

4

1

3

2

3

5

6

BONDED

STANDOFF

(REF)

LEGEND

 1. Cable of connector

 G4P1.

 2. Cable of external

 service panel.

 3. Clamp.

 4. Clamp.

 5. Screw.

 6. Washer.

 7. Ground stud GS6.

 8. Terminal lug.

 9. Nut.

10. Lock washer.

11. Washer.

C

7

8

C

A

B

PRE−MOD B

11

10

9

STIFFENER

(REF)

FT2

(REF)

BONDED

STANDOFF

(REF)

STIFFENER

(REF)

ba5931a01.cgm

SERVICE BULLETIN 670BA−24−027

External Service Panel Cable and Connector G4P1 Cable − Routing Changes

Figure 2 (Sheet 1 of 2)

S.B. 670BA−24−027

Page 16 of 22

Sep 17/2009
1.18 in.

(30.0 mm)

0.63 in.

(16.0 mm)

2 PLACES

1.04 in.

(26.4 mm)ba5931a02.cgm

20

11

10

A

FT2

(REF)

2

1

12

12

13

13

14

15

15

16

14

16

17

19

18

18

19

LEGEND

 1. Cable of connector

 G4P1.

 2. Cable of external

 service panel.

 7. Ground stud GS6.

 9. Nut.

10. Lock washer.

11. Washer.

12. Bracket

 CC670−34157−1.

13. Blind bolt

 PLT214−5−2.

POST−MOD

D

E F

E

D

F

CL

STIFFENER

(REF)

9

14. Standoff

 B0204037AL−7W.

15. Solid Rivet

 MS20470AD4−5A.

16. Clamp

 B0305090C8U05.

17. Clamp

 B0305090C8U10.

18. Screw

 NAS1801−3−6.

19. Washer

 NAS620A10L.

20. Terminal lug

 MS25036−116.

STIFFENER

(REF)

CL

GS2

(REF)

GS6

(REF)

BL22.0

7

SERVICE BULLETIN 670BA−24−027

External Service Panel Cable and Connector G4P1 Cable − Routing Changes

Figure 2 (Sheet 2 of 2)

S.B. 670BA−24−027

Page 17 of 22

Sep 17/2009
1

A

B

C

B

C

A

6

2

5

4

3

1. ADGPC.

2. Rocker door.

3. Nut.

4. Washer.

5. Terminal lug.

6. Terminal stud.

LEGEND

ba5930a01.cgm

SERVICE BULLETIN 670BA−24−027

ADGPC − Wiring Changes

Figure 3

S.B. 670BA−24−027

Page 18 of 22

Sep 17/2009
C. Job Close−Out

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

(2) Remove the tags and close the circuit breakers that follow:

CB−PANEL CB NO. NAME

CBP−2 N6 ADG DEPLOY AUTO

CBP−2 N7 ADG DEPLOY MAN

(3) Do the retraction of the ADG after deployment (AMM 24−23−01−840−802).

(4) Do the operational test of the external service panel (AMM

24−41−01−710−801).

(5) Do the functional test of the ADG (AMM 24−23−01−720−801).

(6) Close the main avionics−compartment door.

(7) When this service bulletin is completed, add the weight and balance data

shown in paragraph 1.I. of this service bulletin to the Weight and Balance

Manual. Under ‘Description of Change’ enter " Service Bulletin

670BA−24−027, incorporated."

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

logbook(s): " Service Bulletin 670BA−24−027, Electrical Power − Air Driven

Generator − Replacement of the Wire Cable and Backshell of ADG Mating

Connector G4P1, incorporated."

SERVICE BULLETIN 670BA−24−027

S.B. 670BA−24−027

Page 19 of 22

Sep 17/2009
3. MATERIAL INFORMATION

A. Kit Information

Kit Content:

KIT 670BA24–027K1

PART NUMBER QUANTITY NAME ALTERNATE

PART(S)

NOTES

670BA24027K100 1 Wire kit − −

670BA24027K101 1 Sleeve kit − −

B0204037AL−7W 2 Standoff − −

B0305090C8U05 2 Clamp,

cushioned

− −

B0305090C8U10 1 Clamp,

cushioned

− −

CC670−34157−1 2 Bracket − −

M39029/29−214 4 Contact − −

M85049/43S22W 1 Backshell − −

MS20470AD4−5A 4 Rivet, solid − −

MS25036−116 4 Terminal lug − −

MS35206−246 2 Screw − −

MS35338−42 2 Lock washer − −

NAS1149DN816J 2 Washer − −

NAS1801−3−6 2 Screw − −

NAS620A10L 2 Washer − −

PLT214−5−2 8 Bolt, blind − −

S10155E8 1 Sleeve − −

SERVICE BULLETIN 670BA−24−027

S.B. 670BA−24−027

Page 20 of 22

Sep 17/2009
B. Consumable Information

The materials that follow are necessary to do this service bulletin and can be ordered

from Bombardier or purchased directly from industry sources. If the material is

ordered from Bombardier, there can be some lead time because of shelf life of the

material.

CONSUMABLES

SPECIFICATION QUANTITY NAME REFERENCE

MIL−C−81706 As

necessary

Chemical conversion

coating (Alodine 1200S or

equivalent)

05−025 [1]

MIL−I−19166 As

necessary

Tape, insulating, elect. high

temperature glass fiber

05−300 [1]

MS3367, Type I As

necessary

Strap, tiedown, electrical

components, adjustable,

self−clinching, plastic

05−057 [1]

MS20995C20 As

necessary

Lockwire, CRES, 0.020 in.

dia.

05−003 [1]

AS3510−0112C As

necessary

Cable, safety, 0.020 in.

(0.51 mm) dia.

05−258 [1]

AS3510−01F As

necessary

Ferrule, for 0.020 in. (0.51

mm) dia. safety cable

05−259 [1]

[1] Refer to AMM 51−31−00−992−801.

NOTE: To complete this list of consumables, refer to the different tasks given as

references in this service bulletin.

C. Special Tools and Equipment

For a list of special tools and equipment, refer to the different tasks given as

references in this service bulletin.

SERVICE BULLETIN 670BA−24−027

S.B. 670BA−24−027

Page 21 of 22

Sep 17/2009
D. Disposition of Parts

The table that follows shows the disposition of installed parts on the aircraft (or

spares), and the relation of the installed parts (or spares) to the new parts to be

installed with this service bulletin.

PRE−SB

PART

NUMBER

NAME QUANTITY DC POST−SB

PART

NUMBER

NAME

M85049/

53−22W

Backshell 1 MUI M85049/

43S22W

Backshell

Disposition code (DC) :

MUI: Multiple Usage Item : Return to stock if serviceable.

SERVICE BULLETIN 670BA−24−027

S.B. 670BA−24−027

Page 22 of 22

Sep 17/2009
THANK YOU FOR ANSWERING THIS EVALUATION FORM 

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

450-476-7300 

SERVICE BULLETIN EVALUATION FORM/COMPLIANCE SHEET 

(YOUR IDEAS WILL HELP US PROVIDE BETTER BULLETINS) 

SERVICE BULLETIN : 670BA-24-027 ISSUE: NC

 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