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 17/2009D. 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 17/2009It 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 17/2009M. 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 17/20092. 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 17/2009REFERENCE 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°30 ” +/−0.03 in. +/−0.1 in. +/−0.8 mm +/−3 mm NOTE : The tolerances above apply to the dimensions given in this service bulletin except 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 17/2009ba5929a01.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 SAA0002N−8 D 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 17/2009ba5929a02.cgm A

12

3 9

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 17/2009A

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

B PRE−MOD 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 17/20091.18 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 C L 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)

C L
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 17/20091 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. LEGENDba5930a01.cgm 

### SERVICE BULLETIN 670BA−24−027

ADGPC − Wiring Changes Figure 3

S.B. 670BA−24−027 Page 18 of 22 Sep 17/2009C. 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 17/20093. 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 17/2009B. 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 17/2009D. 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 17/2009THANK YOU FOR ANSWERING THIS EVALUATION FORM UPON COMPLETION OF THIS EVALUATION FORM/COMPLIANCE SHEET, FAX TO 450-476-7300 

### SERVICE BULLETIN EVALUATI ON 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: 

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

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

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

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

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PLEASE SUPPLY US WITH THE FOLLOWING DATA AND FAX TO (450) 476-7300: OPERATOR: NAME (Please print) SERVICE CENTER: TELEPHONE: AIRCRAFT SERIAL NO.: FACSIMILE: DATE OF SB INCORPOARTION