SB 601R---24---128

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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.

1
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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 equivalent action changes to make

sure this bulletin can be completed.
SERVICE BULLETIN 601R---24 ---128

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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 disconnected 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

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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

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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

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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

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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

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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
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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° 30” +/ --- 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.
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(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).
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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).
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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.
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(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.

.
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(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).
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(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).
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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

D XC51A8N

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)
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Connector P1XC --- Backshell Position

Figure 1 (Sheet 2 of 4)

rsb601r24128_002.dg

A

12 O’CLOCK

9 O’CLOCK 3 O’CLOCK

6 O’CLOCK

C

C

A

BACKSHELL

POSITION

8 O’CLOCK
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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
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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)

STIFFENER 1

(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

A

rsb601r24128_003.dg, eg, mar 29/2010
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Sep 17/2009

Revision C, May 14/2010

Circuit Breaker Panel 3 --- Wiring Changes

Figure 2

rsb601r24128_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

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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.

1
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 : 601R-24-128C ISSUE: C

 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