SB 601R---24---128 Page 1 of 1 May 14/2010 

## SERVICE BULLETIN REVISION TRANSMITTAL SHEET CL ---600 ---2B19 Canadair Regional Jet (CRJ) 

### Aircraft SERVICE BULLETIN 601R ---24 ---128
SUBJECT: Electrical Power --- Air Driven Generator (ADG) --- Replacement of the Wire Cable and Backshell of ADG Mating Connector P1XC This page transmits: Revision C of Service Bulletin 601R --- 24 --- 128, pages 1 thru 23, dated May 14/2010 The changes in this revision have no effect on aircraft that have incorporated a previous issue of this service bulletin.
Reason: Revised Accomplishment Instructions, paragraph 2., to: Correct typing mistakes. This revision also includes small editorial changes that do not have an effect on the technical content.
Instructions: Discard the copy of Service Bulletin 601R --- 24 --- 128, Revision B, dated Apr 16/ 2009. Replace with the copy attached. Service Bulletin History: Initial issue, dated Sep 17/2009. Revision A, dated Nov 27/2009. Revision B, dated Apr 16/2009. 1SB 601R---24---128 Page 1 of 23 Sep 17/2009 Revision C, May 14/2010 

# SERVICE BULLETIN

Technical Publications

THIS SERVICE BULLETIN IS SENT TO EACH OPERATOR. IF THE OPERATOR HAS LEASED 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 HAS INCLUDED THE NEW OPERATOR AIRCRAFT, THIS SERVICE BULLETIN MUST BE SENT TO THE LESSEE. IF THE OPERATOR

ON THE DISTRIBUTION LIST.

ATA SYSTEM: 24 ---23 NUMBER: 601R ---24 ---128 SUBJECT: Electrical Power --- Air Driven Generator (ADG) --- Replacement of the Wire Cable and Backshell of ADG Mating Connector P1XC

1. PLANNING INFORMATION A. Effectivity (1) Aircraft Affected: Service Bulletin: CL ---600---2B19 Canadair Regional Jet (CRJ) Aircraft Serial Numbers 7305 thru 7990, 8000 thru 8107. Production: This change will be incorporated before delivery on Aircraft Serial Numbers 8108 and subsequent. 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 e quivalent action changes to make sure this bulletin can be completed.

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 2 of 23 Sep 17/2009 Revision C, May 14/2010 B. Reason (1) Condition The wires in the cable of ADG mating connector P1XC (written as connector P1XC in this service bulletin) are silver-plated. Moisture in the ADG bay can cause corrosion of the wires. Corrosion of the wires can cause an open circuit and prevent correct operation of the ADG. (2) Evidence This condition was found on three in---service aircraft. (3) Objective/Benefit This service bulletin gives the procedure to replace the wire cable, the ground wire, and the backshell of connector P1XC. The wires of the replacement cable are tin-plated. Incorporation of this service bulletin will prevent corrosion of the wires in the cable of connector P1XC. C. Description The electrical power is removed from the aircraft. The pilot seat is removed. Access panels are removed. The flight ---compartment floor ---panel is removed. The ADG is extended. Circuit Breaker Panel 3 (CBP ---3) is removed. The RH and the LH forward ---fuselage access panels are removed. The external service panel assembly is removed. The aft equipment ---compartment door is opened. In the ADG bay, connector P1XC is disco nnected from the ADG. The wire cable and the backshell of connector P1XC are replaced. A new standoff is installed and the routing of connector P1XC is changed. CBP ---3 is installed. The pilot seat is installed. Connector P1XC is connected to the ADG and the external service---panel assembly is installed. Return---to ---service tests are done. The RH and the LH forward ---fuselage access panels are installed. The flight ---compartment floor ---panel is installed. The aft equipment ---compartment door is closed. The access panels are installed.

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 3 of 23 Sep 17/2009 Revision C, May 14/2010 D. Compliance Recommended Service Bulletin. Bombardier recommends that this service bulletin be done as shown on the 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 LIMIT TO DO THIS SERVICE BULLETIN
15000 or more 6000 flight hours Less than 15000 12000 flight hours

NOTE: This service bulletin must be incorporated on all aircraft, including parked aircraft. 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. 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 601R---24 ---128

SB 601R---24---128 Page 4 of 23 Sep 17/2009 Revision C, May 14/2010 It will take an estimated 9.50 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 0.50 (2) Procedure 8.00 (3) Test 0.25 (4) Job Close---Out 0.75
NOTE: For on --- site labor assistance, please speak with a Fleet Services representative for a quote. The Fleet Services Team can be contacted via the CRC at 514 --- 855 --- 8500 or email at thd.crj@aero.bombardier.com. 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. For Aircraft that have not incorporated a previous issue of this service bulletin and that have not yet ordered kits

KIT NUMBER NAME 601R24---128K1A ADG Power Cable Replacement Kit For Aircraft 7305 thru 7884, 7886 thru 7913, 7915 thru 7924, 7926 thru 7931, 7933 that have not incorporated a previous issue of this service bulletin but that have ordered kit 601R24 ---128K1

KIT NUMBER NAME 601R24---128K2 Plate K601R50195---2007

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 5 of 23 Sep 17/2009 Revision C, May 14/2010 (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 the Service Bulletin Kit Support Team at the address above for terms and conditions. (3) Refer to paragraph 3.B. for a list of consumables for this service bulletin. 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. I. Weight and Balance Not changed. J. Electrical Load Data Not changed. K. References Restriction and/or Special Instruction (RSI) C ---A235, Revision A. Modification Summary TC601R17827, Revision C. Aircraft Maintenance Manual, CSP A ---001. Structural Repair Manual, CSP A ---008. Electrical/Electronic Components - Standard Practices Manual (ESPM), CSP A-115. For Bombardier reference only: PCA 05932.

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 6 of 23 Sep 17/2009 Revision C, May 14/2010 L. Other Publications Affected Wiring Diagram Manual (WDM) CSP A ---003

....................... Illustrated Parts Catalog (IPC) CSP A ---006

........................ M. Relationship Chart

PRE ---SB PART NUMBER NAME POST ---SB PART NUMBER NAME M85049/53---22W or 450AS005M22 Backshell M85049/43S22W Backshell

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 7 of 23 Sep 17/2009 Revision C, May 14/2010 2. ACCOMPLISHMENT INSTRUCTIONS A. Job Set ---Up Reference Information
REFERENCE DESIGNATION AMM 20---24---00---910---802 Lockwire --- Maintenance Practices AMM 20---24---00---910---803 Safety Cable --- Maintenance Practices AMM 24---00---00---861---802 Remove Electrical Power to the Aircraft AMM 24---00---00---910---801 Electrical/Electronic Safety Precautions AMM 24---02---30---000---801 Removal of Circuit Breaker Panel CBP ---3 AMM 24---02---30---400---801 Installation of Circuit Breaker Panel CBP ---3 AMM 24---23---01---720---803 Functional Test of the Dry ADG AMM 24---23---01---840---804 Manual Lowering of the Dry ADG AMM 24---23---01---840---805 Retraction of the Dry ADG After Deployment AMM 24---24---01---000---801 Removal of the External Service---Panel Assembly AMM 24---24---01---400---801 Installation of the External Service---Panel Assembly AMM 24---24---01---710---801 Operational Test of the External Service---Panel Assembly AMM 25---11---01---000---801 Removal of the Pilot/Copilot Seat AMM 25---11---01---400---801 Installation of the Pilot/Copilot Seat AMM 51---31---00---990---801 Consumable Materials AMM 53---10---34---000---801 Removal of the Forward ---Fuselage Access Panels AMM 53---10---34---400---801 Installation of the Forward ---Fuselage Access Panels ESPM 20---11---00 Wire Stripping and Wire/Cable Damage Repair --- Maintenance Practices

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 8 of 23 Sep 17/2009 Revision C, May 14/2010 REFERENCE DESIGNATION ESPM 20---12---00 Wiring --- Removal/Installation ESPM 20---12---01 Electrical Wiring --- Continuity Testing ESPM 20---17---10 Electrical Connectors --- Maintenance Practices ESPM 20---20---00 Terminal Lugs --- Removal/Installation SRM 51---21---11 Corrosion Prevention Procedures SRM 51---23---00 Pressure, Environmental, Fuel Tank and Firewall Sealing SRM 51---26---00 Cleaning SRM 51---42---06 Solid Rivets

Tolerance Information Linear Tolerances Angular Tolerance X.XX in. (0.X mm) X.X in. (X mm) / 0 ° 3 0 ” +/ --- 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. 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. (1) Obey all the electrical/electronic safety precautions (Refer to AMM 24---00---00---910---801). (2) Remove electrical power from the aircraft (Refer to AMM 24---00---00---861---802). (3) Open the aft equipment ---compartment door.

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 9 of 23 Sep 17/2009 Revision C, May 14/2010 (4) Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE

CBP ---2 N6 ADG DEPLOY CONT AUTO 222 CBP ---2 N7 ADG DEPLOY CONT MAN 222 CBP ---5 B10 ADG AUTO 311 CBP ---5 B11 ADG MAN 311 CBP ---5 B12 EXT PWR 311 (5) Remove the external service panel (Refer to AMM 24---24---01---000---801). (6) Manually lower the dry ADG (Refer to AMM 24---23---01---840---804). (7) Remove the pilot seat (Refer to AMM 25---11---01---000---801). (8) Remove access panels 221BZ and 222BZ. (9) Remove CBP ---3 (Refer to AMM 24---02---30---000---801). (10) If necessary, remove the cover of Junction Box (JB) 6. (11) Remove floor panel 221ALF. (12) Remove forward-fuselage access-panels 131AL and 132AL (Refer to AMM 53---10---34---000---801).

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 10 of 23 Sep 17/2009 Revision C, May 14/2010 B. Procedure Refer to Figure 1. (1) Remove and discard the wire cable between connector P1XC and CBP ---3---TB2 as follows: (a) Disconnect connector P1XC from the ADG. (b) Remove the screw (12), the washer (11), and the clamp (10) that attach the wire bundle of connector P1XC to the spacer nutplate (16). Keep the clamp (10), the washer (11), and the screw (12). (c) Disconnect and remove all the wires from connector P1XC with an extraction tool. (d) Loosen and remove the backshell (4) from connector P1XC. Keep connector P1XC. (e) Remove the nut (14) and the washer (13) that attach wire XC51A8N to ground stud N792 (9). Keep the nut (14) and the washer (13). (f) Disconnect, remove, and discard wire XC51A8N from ground stud N792 (9) (Refer to ESPM 20---11---00). (g) Cut the lockwire or safety cable and loosen the mounting nut of bulkhead feedthru FT202---D to help removal and installation of the wires. (h) In the forward avionics compartment and in the flight compartment, carefully remove the clamps that attached the wire cable of connector P1XC. Keep all protective sleeving, cable clamps, and their mounting hardware. (i) Cut, remove, and discard the wire cable of connector P1XC (Refer to ESPM 20---11---00). Refer to Figure 2. (j) In CBP ---3 (1), remove and keep the cover assembly (3) from Terminal Block TB2 (2). (k) Remove and keep the nuts (4) and the washers (5) that attach the terminal lugs (9) to the studs of TB2 (2). (l) Remove wires XC1A8AWHT (6), XC2A8BBLU (7), and XC3A8CORN (8) from TB2 (2) (Refer to ESPM 20---11---00).

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 11 of 23 Sep 17/2009 Revision C, May 14/2010 For Aircraft 7885, 7914, 7925, 7932, and 7934 thru 8107 Refer to Figure 1 (Sheet 3 of 4). (2) In the ADG bay, install the spacer nutplate (7) as follows: (a) Drill one hole to a diameter of 0.128---0.132 in. (3.25---3.35 mm) at 7.95 in. (20.19 cm) above the bracket and 0.32 in. (8.13 mm) inboard of the outboard edge of the stiffener. (b) Put the spacer nutplate (7) in position with a temporary fastener. (c) Backdrill one hole to a diameter of 0.128---0.132 in. (3.25---3.35 mm) from the spacer nutplate (7) through the stiffener. (d) Remove the burrs. (e) Clean the work area with solvent (Refer to SRM 51---26---00). (f) Apply chemical conversion coating to the bare metal areas (Refer to SRM 51---21---11). (g) Apply faying surface sealant to the mating surfaces of the spacer nutplate (7) and the stiffener (Refer to SRM 51---23---00). (h) Install the spacer nutplate (7) with wet ---installed rivets (8) (Refer to SRM 51---23---00 and SRM 51---42---06). For Aircraft 7305 thru 7884, 7886 thru 7913, 7915 thru 7924, 7926 thru 7931, and 7933 Refer to Figure 1 (Sheet 4 of 4). (3) In the ADG bay, install the spacer nutplate (7) and plate (18) as follows: (a) At 8.15 in. (20.7 cm) from the bracket, remove the rivet from the inboard of the outer edge of the stiffener (Refer to SRM 51---42---06). (b) Remove the rivet that is above the rivet removed in the previous step (Refer to SRM 51---42---06). (c) Temporarily install the plate (18) on the stiffener.

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 12 of 23 Sep 17/2009 Revision C, May 14/2010 (d) Backdrill two holes to a diameter of 0.160---0.164 in. (4.06---4.17 mm) from the holes of the removed rivets on the stiffener to the plate (Refer to SRM 51---42---06). (e) Temporarily install the spacer nutplate (7) on the plate (18). (f) Backdrill two holes to a diameter of 0.128---0.132 in. (3.25---3.35 mm) from the spacer nutplate (7) through the plate (18) (Refer to SRM 51---42---06). (g) Remove the spacer nutplate (7) and the plate (18). (h) Remove the burrs. (i) Clean the work area with solvent (Refer to SRM 51---26---00). (j) Apply chemical conversion coating to the bare metal areas (Refer to SRM 51---21---11). (k) Apply faying surface sealant to the mating surfaces of the spacer nutplate (7) and the plate (18) (Refer to SRM 51---23---00). (l) Install the spacer nutplate (7) with wet ---installed rivets (8) (Refer to SRM 51---23---00 and SRM 51---42---06). (m) Apply faying surface sealant to the mating surfaces of the plate (18) and the stiffener (Refer to SRM 51---23---00). (n) Install the plate (18) with wet ---installed rivets (19) (Refer to SRM 51---23---00 and SRM 51---42---06). For all Aircraft Refer to Figures 1 and 2. (4) Install the the new wire cable and ground wire as shown in the table below: WIRE FROM TERMINAL TO TERMINAL W ¡ XC1A8AWHT P1XC ---A M39029/29---214 CBP ---3---TB2---1 MS25036---115 1J XC2A8BBLU P1XC ---B M39029/29---214 CBP ---3---TB2---2 MS25036---115 1J XC3A8CORN P1XC ---C M39029/29---214 CBP ---3---TB2---3 MS25036---115 1J XC51A8N P1XC ---D M39029/29---214 N792 MS25036---118

--- ¡ Wire separation “W” code. (a) In the forward avionics compartment, install the new cable with the clamps, the screws, and the washers.

.

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 13 of 23 Sep 17/2009 Revision C, May 14/2010 (b) Cut the wires of the new cable to the correct length (Refer to ESPM 20---11---00). (c) Remove the insulation from the wire ends with a wire stripper (Refer to ESPM 20---11---00). (d) Install the applicable terminal lugs on the wires of the new cable with a crimping tool (Refer to ESPM 20---17---10). (e) Install the terminal lugs (9) on the studs of TB2 (2) with the washers (5) and the nuts (4). (f) Torque the nut (4) (Refer to ESPM 20---20---00). (g) Put the wires of the new cable through bulkhead feedthru FT202---D from the right access hole. (h) Tighten bulkhead feedthru FT202---D and install the lockwire or safety cable (Refer to AMM 20---24---00---910---803). (i) Remove and discard the supplied screws and lock washers from the saddle clamp of the new backshell (4). Keep the saddle clamp. (j) Put the wires for connector P1XC through the sleeve (5), the identification sleeve (6), and the new backshell (4). (k) Cut the wires of the new cable to the correct length (Refer to ESPM 20---11---00). NOTE: The length of the wire cable between the backshell (4) of connector P1XC and the new spacer nutplate must be 13 in. (33 cm). (l) Remove the insulation from the wire ends with a wire stripper (Refer to ESPM 20---11---00). (m) Install the applicable terminal on the wires of the new cable with a crimping tool (Refer to ESPM 20---17---10). (n) Install the wires of the new cable in connector P1XC with an insertion tool at the given locations (Refer to ESPM 20---17---10). (o) Cut new wire XC51A8N to the correct length (Refer to ESPM 20---11---00).

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 14 of 23 Sep 17/2009 Revision C, May 14/2010 (p) Install the terminal lug (15) on new wire XC51A8N with a crimping tool (Refer to ESPM 20---17---10). (q) Install the terminal lug (15) of wire XC51A8N to ground stud N792 (9) with the washer (13), the lock washer (17), and the nut (14). (r) Torque the nut (14) (Refer to ESPM 20---20---00). (s) Do a continuity check of the installed wires (Refer to ESPM 20---12---01). (t) Connect connector P1XC to the ADG. (u) Put the backshell (4) of connector P1XC at the 8 o’clock position (Refer to Figure 1, View C). (v) Tighten and torque the backshell (4) (Refer to ESPM 20---17---10). (w) Attach the wire bundle to the backshell (4) of connector P1XC as follows: 1 Apply four to eight 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), the lock washers (2), and the washers (3). NOTE: The taped area of the wire bundle must not move inside the saddle clamp and there must be no tension on the terminals and wires. WARNING: DO NOT TOUCH THE HEAT GUN REFLECTOR. THE HEAT GUN REFLECTOR CAN GET VERY HOT AND CAUSE INJURY IF YOU TOUCH IT. (x) With a heat gun, apply heat to shrink the identification sleeve (6) (Refer to ESPM 20---17---10). (5) Install the external service panel (Refer to AMM 24---24---01---400---801). (6) Attach the bundle of connector P1XC to the new spacer nutplate (7) with the clamp (10) the washer (11) and the screw (12). (7) Make sure that the length of the wire cable between the backshell (4) of connector P1XC and the clamp (10) is 13 in. (33 cm). (8) Safety connector P1XC to the adjacent screw with lockwire or safety cable (Refer to AMM 20---24---00---910---803).

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 15 of 23 Sep 17/2009 Revision C, May 14/2010 Connector P1XC and Backshell --- Wiring Changes Figure 1 (Sheet 1 of 4)rsb601r24128_001.dg A A

B B

13.0 in. (33.0 cm)

B 1 2

3 LEGEND

PRE--MOD

XC1A8AWHT XC2A8BBLU XC3A8CORN

AIR DRIVEN GENERATOR C B A P1XC G1XC FS193L

N792 XC51A8N D XC1A8AWHT XC1A8BBLU XC1A8CORN CLAMP 13.0 in. (33.0 cm)

W1J FS202L

FT202--D 2 1

3 CBP--3 FS230L 1. Screw MS35206--246. 2. Lock washer MS35338--42. 3. Washer NAS1149DN816J. 4. Connector M85049/43S22W. 5. Sleeve S10155E8. 6. Identification sleeve.

4 P1XC

6 5 P1XC

POST--MOD 4 SADDLE CLAMP (REF)

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 16 of 23 Sep 17/2009 Revision C, May 14/2010 Connector P1XC --- Backshell Position Figure 1 (Sheet 2 of 4)rsb601r24128_002.dg A

12 O’CLOCK

3 O’CLOCK 9 O’CLOCK

6 O’CLOCK

C C

A

BACKSHELL POSITION 8 O’CLOCK

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 17 of 23 Sep 17/2009 Revision C, May 14/2010 Spacer Nutplate --- Installation Figure 1 (Sheet 3 of 4)rsb601r24128_004.dg, eg, mar 29/2010 C

7.95 in. (20.19 cm) 7 8

10 11 12 D

16

WIREXC51A8N (REF)

1 STIFFENER (REF)

BRACKET (REF) 0.32 in. (8.1 mm) NOTE Installation of the clamp 10 on spacer nutplate 16 (pre--mod), and on spacer nutplate 7 (post--mod). 1

A For Aircraft 7885, 7914, 7925, 7932 and 7934--8107.

LEGEND 7. Spacer nutplate B0204040AL--5W. 8. Rivet MS20470AD4--5A. 9. Ground stud N792. 10. Clamp. 11. Washer. 12. Screw. 13. Washer. 14. Nut. 15. Terminal lug MS25036--118. 16. Spacer nutplate. 17. Lock washer. E E 15 13 17 14 9

D

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 18 of 23 Sep 17/2009 Revision C, May 14/2010 Spacer Nutplate --- Installation Figure 1 (Sheet 4 of 4) 15 13 17 14 9

D C

8.15 in. (20.7 cm) 7

8

10 11 12 D

16

WIREXC51A8N (REF) 1 STIFFENER (REF)

BRACKET (REF) NOTE Installation of the clamp 10 on spacer nutplate 16 (pre--mod), and on spacer nutplate 7 (post--mod). 1

19 18 For Aircraft 7305--7884, 7886--7913, 7915--7924, 7926--7931, 7933.

LEGEND 7. Spacer nutplate B02040AL--5W. 8. Rivet MS20470AD4--5A. 9. Ground stud N792. 10. Clamp. 11. Washer. 12. Screw. 13. Washer. 14. Nut. 15. Terminal lug MS25036--118. 16. Spacer nutplate. 17. Lock washer. 18. Plate K601R50195--2007SB. 19. Rivet MS20470AD5--6A. E E Arsb601r24128_003.dg, eg, mar 29/2010

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 19 of 23 Sep 17/2009 Revision C, May 14/2010 Circuit Breaker Panel 3 --- Wiring Changes Figure 2rsb601r24128_003.dg, yf, 24/07/09 LEGEND 2

1 9 3

7 8

1. CBP--3. 2. Terminal block TB2. 3. Cover assembly. 4. Nut. 5. Washer. 6. Wire XC1A8AWHT. 7. Wire XC2A8BBLU. 8. Wire XC3A8CORN. 4
5

A B

B A 6

9

9. Terminal lug MS25036--115.

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 20 of 23 Sep 17/2009 Revision C, May 14/2010 C. Job Close ---Out (1) Remove all tools, equipment, and unwanted materials from the work area. (2) Install circuit breaker panel CBP ---3 (Refer to AMM 24---02---30---400---801). (3) Install the cover of JB ---6. (4) Do the retraction of the ADG after deployment (Refer to AMM 24---23---01---840---805). (5) Make sure that the wire bundle of connector P1XC does not touch the aircraft structure or installed components. (6) Remove the tags and close the circuit breakers that follow: CB PANEL CB NO. NAME ZONE

CBP ---2 N6 ADG DEPLOY CONT AUTO 222 CBP ---2 N7 ADG DEPLOY CONT MAN 222 CBP ---5 B10 ADG AUTO 311 CBP ---5 B11 ADG MAN 311 CBP ---5 B12 EXT PWR 311 (7) Do the operational test of the external service panel (Refer to AMM 24---24---01---710---801). (8) Do the functional test of the dry ADG (Refer to AMM 24---23---01---720---803). NOTE: The wire bundle of connector P1XC must not touch the aircraft structure or installed components. (9) Install floor panel 221ALF. (10) Install access panels 221BZ and 222BZ. (11) Install forward ---fuselage access panels 131AL and 132AL (Refer to AMM 53---10---34---400---801). (12) Install the pilot’s seat (Refer to AMM 25---11---01---000---801). (13) Close the aft equipment ---compartment door. (14) When this service bulletin is completed, make this entry in the applicable logbook(s): “Service Bulletin 601R---24---128, Revision C, Electrical Power --- Air Driven Generator (ADG) --- Replacement of the Wire Cable and Backshell of ADG Mating Connector P1XC, incorporated.”

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 21 of 23 Sep 17/2009 Revision C, May 14/2010 3. MATERIAL INFORMATION
A. Kit Information

KIT 601R24 ---128K1A
PART NUMBER QUANTITY NAME ALTERNATE PARTS NOTES
601R24---128K100 1 Wire kit

--- --- 601R24---128K101 1 Sleeve kit

--- --- B0204040AL ---5W 1 Spacer nutplate

--- --- K601R50195-2007SB 1 Plate

--- --- M39029/29---214 4 Contact

--- --- M85049/43S22W 1 Backshell

--- --- MS20470AD4---5A 2 Solid rivet

--- --- MS20470AD5---6A 2 Solid rivet

--- ---

MS25036---115 3 Terminal lug

--- --- MS25036---118 1 Terminal lug

--- --- MS35206---246 2 Screw

--- --- MS35338---42 2 Lock washer

--- --- NAS1149DN816J 2 Washer

--- --- S10155E8 1 Sleeve

--- ---

KIT 601R24 ---128K2
PART NUMBER QUANTITY NAME ALTERNATE PARTS NOTES
K601R50195-2007SB 1 Plate

--- ---

MS20470AD5---6A 2 Solid rivet

--- ---

### SERVICE BULLETIN 601R---24 ---128

SB 601R---24---128 Page 22 of 23 Sep 17/2009 Revision C, May 14/2010 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 ¡
MIL ---I ---19166 As necessary Tape, insulating, elect. high temperature glass fiber 05---094 ¡
MS3367, Type I, Class I As necessary Strap, tiedown, electrical components, adjustable, self---clinching, plastic 05---057 ¡

MS20995C20 As necessary Lockwire, CRES, 0.020 in. dia. 05---003 ¡
AS3510---0109C As necessary Cable, safety, 0.020 in. (0.51 mm) dia. 05---132 ¡
AS3510---01F As necessary Ferrule, for 0.020 in. (0.51 mm) dia. safety cable 05---135 ¡

¡ Refer to AMM 51---31---00---990---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 601R---24 ---128

SB 601R---24---128 Page 23 of 23 Sep 17/2009 Revision C, May 14/2010 D. Disposition of Parts The table that follows shows the disposition of installed parts on the aircraft (or spares), and the relation of 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 or 450AS005M22 Backshell 1 MUI M85049/43S22W Backshell
Disposition code (DC): MUI: Multiple Usage Item: Return to stock if serviceable. 1THANK 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 : 601R-24-128C ISSUE: C

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