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Feb 03/2010 SB 601R---30---031

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

CL ---600 ---2B19 Canadair Regional Jet (CRJ) Aircraft

SERVICE BULLETIN 601R ---30 ---031

SUBJECT: Ice and Rain Protection --- Wing Anti --- Icing System --- Installation of Low

Heat Detection ---Switches on the Leading Edge

This page transmits:

Revision D of Service Bulletin 601R --- 30 --- 031,

pages 1 thru 126, dated Feb 03/2010.

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:

Change the data in a wire table of PART D.

Add the P/N of the crimping tool for terminal lug P/N MS20659---101.

Add an alternate task for the operational test of the wing anti---ice ducts.

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 --- 30 --- 031, Revision C, dated Dec 23/2009.

Replace with the copy attached.

Service Bulletin History:

Initial issue, dated May 15/2009.

Revision A, dated Sep 08/2009.

Revision B, dated Oct 28/2009.

Revision C, dated Dec 23/2009.

1
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Revision D, Feb 03/2010

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: 30 ---12 NUMBER: 601R ---30 ---031

SUBJECT: Ice and Rain Protection --- Wing Anti --- Icing System --- Installation of Low

Heat Detection ---Switches on the Leading Edge

1. PLANNING INFORMATION

A. Effectivity

(1) Aircraft Affected:

Service Bulletin: CL ---600---2B19 Canadair Regional Jet (CRJ) Aircraft Serial

Numbers 7003 thru 7067, 7069 thru 7990 and 8000 thru

8101.

Production: This change will be incorporated before delivery on Aircraft

Serial Numbers 8102 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 Aerospace Service Bulletin(s). Before you

do this bulletin, examine all STC, STA or equivalent action changes

to make sure this bulletin can be completed.

NOTE: The procedure in this service bulletin was validated on Aircraft Serial

Number 7028.
SERVICE BULLETIN 601R---30 ---031

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B. Reason

(1) Condition

It is possible for the Wing Anti---Ice (WAI) system to not correctly sense low

heat on the outboard leading edges.

(2) Evidence

The wing anti---ice system of some aircraft in service did not correctly sense a

low heat condition on the wing during a malfunction of the piccolo duct.

(3) Objective/Benefit

This service bulletin gives the procedure to install two low heat

detection---switches on the outboard leading edge. This will monitor the

temperature and indicate low heat conditions at the wing tip during all phases

of the flight.

C. Description

This service bulletin is divided into six parts: PART A, PART B, PART C, PART D,

PART E and PART F.

PART A --- Installation of the Low Heat Detection ---Switches on the Left Wing

Circuit breakers are opened. The electrical power is removed. Access panels are

removed. The left leading edges are removed.

The shroud is removed from the outboard leading edge. Holes are drilled through

the outboard leading edge and the shroud. Two low heat detection---switches

(written as “thermal switches” in this service bulletin) are installed in outboard

leading edge.

New wires are installed from the thermal switches to a connector on the wing. The

shroud is installed on the outboard leading edge. The left leading edges are

installed. The circuit breakers are closed. The electrical power is applied.

For Aircraft that have incorporated PART A from the initial issue of this service bulletin

PART B --- Activation of the Low Heat Detection ---Switches

Circuit breakers are opened. The electrical power is removed. The Data

Concentrator Units (DCUs) are removed. In the main avionics ---compartment, two

wires per DCUs are connected. The circuit breakers are closed. The electrical

power is applied. The operational test of the outboard low heat

detection---switches and the DCUs are done.
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

For all Aircraft

PART C --- Installation of the Low Heat Detection ---Switches on the Right Wing

Circuit breakers are opened. The electrical power is removed. Access panels are

removed. The leading edges are removed.

The shroud is removed from the outboard leading edge. Holes are drilled through

the outboard leading edge and the shroud. Two thermal switches are installed in

the outboard leading edge.

New wires are installed from the thermal switches to a connector on the wing. The

shroud is installed on the outboard leading edge. The leading edges are installed.

The circuit breakers are closed. The electrical power is applied.

PART D --- Installation of the Wing A/ICE box assembly on the Left Side of the

Main Avionics ---Compartment

Circuit breakers are opened. The electrical power is removed. Some passenger

seats on the left side are removed. Floor covering and some floor panels are

removed. Access panels are removed. DCU 1, the Global Positioning Unit Sensor

Unit (GPSU 1) and the Attitude and Heading Computer (AHC 1) are removed.

New wires are installed from connector J423, at FS409L+128, to the main

avionics ---compartment. The wires to DCU 1 are caped and stowed. The WING

A/ICE box assembly is installed and connected. Circuit breakers, on the WING

A/ICE box assembly, are opened. AHC 1, GPSU1 and the DCUs are installed. The

circuit breakers are closed. The electrical power is applied.

The access panels are installed. The floor panels and floor covering are installed.

The passenger seats are installed.

PART E --- Installation of the wires for the Wing A/ICE box assembly on the

Right Side of the Main Avionics ---Compartment

Circuit breakers are opened. The electrical power is removed. Some passenger

seats on the right side are removed. Floor covering and some floor panels are

removed. Access panels are removed.

New wires are installed from connector J422, at FS409R+128, to the main

avionics ---compartment. The wires to DCU 2 are caped and stowed. If DCU 3 is

installed, the wires to DCU 3 are caped and stowed. DCU 2 is installed. If

applicable, DCU 3 is installed. The circuit breakers are closed. The electrical power

is applied.

The access panels are installed. The floor panels and floor covering are installed.

The passenger seats are installed.
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

PART F --- Activation of the Low Heat Detection ---Switches

NOTE: PART A, PART C, PART D and PART E are prerequisites to do PART F.

Circuit breakers are opened. The avionics ---compartment door is opened. In the

main avionics ---compartment, some wires are unstowed and connected to the

connectors of the WING A/ICE box assembly. The lockrings are removed from the

circuit breakers of the WING A/ICE box assembly. The circuit breakers are closed.

The electrical power is applied. The operational test of the outboard low heat

detection---switches is done.

D. Compliance

For Aircraft that have incorporated PART A from the initial issue of this service

bulletin

Recommended Service Bulletin. Bombardier Aerospace recommends that PART B

of the initial issue or subsequent revision of this service bulletin be done no more

than 24 months from the initial release date on this service bulletin, unless

otherwise directed by the airworthiness authority of the operator.

For Aircraft that have not incorporated the initial issue of this service bulletin

Recommended Service Bulletin. Bombardier Aerospace recommends that PART A,

PART C, PART D, PART E and PART F of this service bulletin be done no more than

24 months from the initial release date on this service bulletin, unless otherwise

directed by the airworthiness authority of the operator.

For Aircraft 7003 thru 7067, 7069 thru 7990 and 8000 thru 8095

NOTE: Service Bulletin 601R---31---034 Indicating and Recording Systems ---

General --- Data Concentrator Unit (DCU---4000) Update is a prerequisite

to PART B and PART F of this service bulletin.

For all Aircraft

NOTE: When this service bulletin is incorporated, use Airplane Flight Manual

(AFM) Temporary Revision TR RJ/164---2 or subsequent applicable

revision.

This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage

Tolerance inspections (DTIs).

E. Approval

The technical content of this service bulletin has been approved under the authority

of the TCCA Design Approval Organization No: DAO #93---Q ---02.
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

F. Manpower

Man hours given below are an estimate for direct labor done by an experienced

crew on an aircraft prepared for maintenance.

These estimates do not include the time necessary for:

− Administrative functions such as planning, 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 Aerospace as directly

related to the accomplishment of this procedure.

NOTE: For on --- site labor assistance, please speak with a Fleet Services

representative for a quote. The Fleet Services Team can be

contacted via the CRC at 514 --- 855 --- 8500 or email at

thd.crj@aero.bombardier.com.

PART A --- Installation of the Low Heat Detection ---Switches on the Left Wing

It will take an estimated 18.0 man---hours to complete this service bulletin. The

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

TASK MAN ---HOURS

(2) Job Set ---Up 4.0

(3) Procedure 8.0

(4) Test 0.0¡

(5) Job Close---Out 6.0

¡ Does not include the time to do AMM 20---10---00---910---803
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

PART B --- Activation of the Low Heat Detection ---Switches

It will take an estimated 5.0 man---hours to complete PART B of this service bulletin.

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

TASK MAN ---HOURS

(2) Job Set ---Up 0.5

(3) Procedure 2.0

(4) Test 2.0

(5) Job Close---Out 0.5

PART C --- Installation of the Low Heat Detection ---Switches on the Right Wing

It will take an estimated 18.0 man---hours to complete this service bulletin. The

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

TASK MAN ---HOURS

(2) Job Set ---Up 4.0

(3) Procedure 8.0

(4) Test 0.0¡

(5) Job Close---Out 6.0

¡ Does not include the time to do AMM 20---10---00---910---803
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

PART D --- Installation of the Wing A/ICE box assembly on the Left Side of the Main

Avionics ---Compartment

It will take an estimated 18.0 man---hours to complete this service bulletin. The

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

TASK MAN ---HOURS

(2) Job Set ---Up 4.0

(3) Procedure 10.0

(4) Test 0.0 ¡

(5) Job Close---Out 4.0

¡ Does not include the time to do AMM 20---10---00---910---803

PART E --- Installation of the wires for the Wing A/ICE box assembly on the Right Side of

the Main Avionics ---Compartment

It will take an estimated 13.0 man---hours to complete this service bulletin. The

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

TASK MAN ---HOURS

(2) Job Set ---Up 4.0

(3) Procedure 6.0

(4) Test 0.0 ¡

(5) Job Close---Out 3.0

¡ Does not include the time to do AMM 20---10---00---910---803
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

PART F --- Activation of the Low Heat Detection ---Switches

It will take an estimated 4.0 man---hours to complete this service bulletin. The

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

TASK MAN ---HOURS

(2) Job Set ---Up 0.5

(3) Procedure 1.5

(4) Test 1.5

(5) Job Close---Out 0.5

G. Material --- Price and Availability

(1) The kits in the table that follows are available from Bombardier Aerospace

Regional Aircraft. Refer to the paragraphs below for terms and conditions.

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

KIT NUMBER NAME

601R30---031K2A Wing A/Ice System --- (Left Wing)

601R30---031K3A Wing A/Ice System --- (Right Wing)

601R30---031K4 Wing A/Ice System --- (Left Fuselage)

601R30---031K5 Wing A/Ice System --- (Right Fuselage)

601R30---031K6 Wing A/Ice System --- (Final Installation)
SERVICE BULLETIN 601R---30 ---031

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

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.

For Aircraft that have not incorporated PART A and PART C of this service bulletin

and that have ordered kits 601R30 ---031K2 and 601R30 ---031K3

(3) It is possible that the parts in the table that follows are replaced during the

incorporation of PART A and PART C of this service bulletin. These parts are

available from Bombardier Commercial Aircraft.

PART NUMBER NAME QUANTITY

202K153---25---01/225---0 Boot 2

600---052---1 Strap 2

(4) Please send a purchase order to the address below to schedule the parts:

Bombardier

Service Bulletin Kit Support Team

123 Garratt Blvd, N42---24

Toronto, Ontario

Canada M3K 1Y5

Fax: 416---375---3060

Phone: 416---375---3920

Email: sbkits@aero.bombardier.com

Please contact the Service Bulletin Kit Support Team at the address above for

terms and conditions.

(5) Refer to paragraph 3.B. for a list of consumables for this service bulletin.

H. Tooling --- Price and Availability

There are no tool kits for this service bulletin.
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

I. Weight and Balance

PART A --- Installation of the Low Heat Detection ---Switches on the Left Wing

WEIGHT ARM MOMENT ¡

1.0 (lb) 510.4 (in.) 0.510 ( 1000 lb---in.)

0.5 (kg) 12.96 (m) 0.006 (1000 kg ---m)

¡ The value in the Moment column is divided by 1000. Refer

to the Weight & Balance Manual CSP A ---041.

PART B --- Activation of the Low Heat Detection ---Switches

Not changed.

PART C --- Installation of the Low Heat Detection ---Switches on the Right Wing

WEIGHT ARM MOMENT ¡

1.0 (lb) 510.4 (in.) 0.510 ( 1000 lb---in.)

0.5 (kg) 12.96 (m) 0.006 (1000 kg ---m)

¡ The value in the Moment column is divided by 1000. Refer

to the Weight & Balance Manual CSP A ---041.

PART D --- Installation of the Wing A/ICE box assembly on the Left Side of the Main

Avionics ---Compartment

WEIGHT ARM MOMENT ¡

2.1 (lb) 280.3 (in.) 0.589 ( 1000 lb---in.)

1.0 (kg) 7.12 (m) 0.007 (1000 kg ---m)

¡ The value in the Moment column is divided by 1000. Refer

to the Weight & Balance Manual CSP A ---041.
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

PART E --- Installation of the wires for the Wing A/ICE box assembly on the Right Side of

the Main Avionics ---Compartment

WEIGHT ARM MOMENT ¡

0.4 (lb) 338.9 (in.) 0.136 ( 1000 lb---in.)

0.2 (kg) 8.61 (m) 0.002 (1000 kg ---m)

¡ The value in the Moment column is divided by 1000. Refer

to the Weight & Balance Manual CSP A ---041.

For aircraft that have the third DCU option (CR31---310 or CR31---001), it is

necessary to add the table that follows:

WEIGHT ARM MOMENT ¡

0.1 (lb) 281.8 (in.) 0.028 ( 1000 lb---in.)

0.05 (kg) 7.16 (m) 0.0003 (1000 kg ---m)

¡ The value in the Moment column is divided by 1000. Refer

to the Weight & Balance Manual CSP A ---041.

PART F --- Activation of the Low Heat Detection ---Switches

Not changed.

J. Electrical Load Data

Not changed.

K. References

Restriction and/or Special Instruction (RSI) C ---A220.

Modification Summary TC601R17364, Revision N.

Service Non Incorporated Engineering Order K601R54002 SNIEO S04

Service Non Incorporated Engineering Order K601R50586 SNIEO S04

Aircraft Maintenance Manual, CSP A ---001.

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

CSP A ---115.

For Bombardier Aerospace reference only: PCA 04858.
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

L. Other Publications Affected

Aircraft Maintenance Manual (AMM) CSP A ---001 ...................

Wiring Diagram Manual (WDM) CSP A ---003 .......................

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

Fault Isolation Manual (FIM) CSP A ---009 ..........................

Maintenance Requirement Manual (MRM) CSP A ---053 .............

Flight Crew Operating Manual Vol 2 CSP A ---013 ...................

Airplane Flight Manual (AFM) CSP A ---012 ........................

Quick Reference Handbook (QRH) CSP A ---022 ...................

M. Relationship Chart

Not applicable.
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

2. ACCOMPLISHMENT INSTRUCTIONS

PART A --- Installation of the Low Heat Detection ---Switches on the Left Wing

A. Job Set ---Up

Reference Information

REFERENCE DESIGNATION

AMM 11---30---00---400---801 Installation of the Adhesive---Backed Label

AMM 20---10---00---910---803 Connector Integrity After a Disconnect and

Re---connection

AMM 20---21---00---910---801 Torque Procedures for Threaded Fasteners

AMM 24---00---00---861---802 Remove Electrical Power to the Aircraft

AMM 24---00---00---910---801 Electrical/Electronic Safety Precautions

AMM 30---11---00---740---801 Self---Test of the Anti Ice Duct System

AMM 30---11---00---790---801 Operational test of the Wing Anti---Ice Ducts

(External Air Supply)

AMM 30---11---00---790---802 Operational test of the Wing Anti---Ice Ducts

(Engine Bleed Air Supply)

AMM 30---11---41---000---801 Removal of the Leading Edge Anti---Ice Wing

Ducts (Piccolo Tubes)

AMM 30---11---41---400---801 Installation of the Leading Edge Anti---Ice Wing

Ducts (Piccolo Tubes)

AMM 30---12---17---720---801 Functional Test of the Backup Sufficient ---Heat

Switches

AMM 33---43---00---710---801 Operational Test of the Wing Inspection Lights

AMM 36---21---00---710---801 Operational Test of the Bleed ---Air Leak

Detection and Warning System

AMM 51---80---00---100---802 Surface Preparation for Electrical Bonding

AMM 51---80---00---760---802 Electrical Bonding Resistance Values
SERVICE BULLETIN 601R---30 ---031

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REFERENCE DESIGNATION

AMM 53---82---01---000---803 Removal of the Left Forward Wing ---to ---Fuselage Fairing

AMM 53---82---01---400---803 Installation of the Left Forward Wing ---to

Fuselage Fairing

AMM 57---41---01---000---803 Removal of the Inboard Leading Edge Assembly 520JL (620JL)

AMM 57---41---01---000---804 Removal of the Center Leading Edge Assembly

530JL (630JL)

AMM 57---41---01---000---806 Removal of the Outboard Leading Edge

Assembly 530KL (630KL)

AMM 57---41---01---140---803 Polishing of the Wing Leading Edges

AMM 57---41---01---400---803 Installation of the Inboard Leading Edge

Assembly 520JL (620JL)

AMM 57---41---01---400---804 Installation of the Center Leading Edge

Assembly 530JL (630JL)

AMM 57---41---01---400---806 Installation of the Outboard Leading Edge

Assembly 530KL (630KL)

ESPM 20---11---00 Wire Stripping and Wire/Cable Damage Repair

Maintenance Practices

ESPM 20---12---00 Wiring --- Removal/Installation

ESPM 20---12---01 Electrical Wiring --- Continuity Testing

ESPM 20---14---00 Convolex Tubing/Conduit ---

Removal/Installation

ESPM 20---17---10 Electrical Connectors --- Maintenance Practices

ESPM 20---20---00 Terminal Lugs --- Removal/Installation

ESPM 20---23---00 Circuit Breakers --- Removal/Installation

SRM 51---21---11 Corrosion Prevention Procedures

SRM 51---21---16 Finish Codes

SRM 51---22---00 Bonding and Attaching Parts with Adhesives
SERVICE BULLETIN 601R---30 ---031

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REFERENCE DESIGNATION

SRM 51---23---00 Pressure, Environmental, Fuel Tank and Firewall

Sealing

SRM 51---25---06 Fluid ---Resistant (FR) Epoxy Primer

SRM 51---25---16 Fluid ---Resistant (FR) Polyurethane Topcoat

SRM 51---26---00 Cleaning

SRM 51---41---04 Torque Procedures --- Bolts and Screws

SRM 51---42---06 Solid Rivets

SRM 51---42---10 Blind Rivets --- General

Tolerance Information

Linear Tolerances Angular Tolerance

0.XX in. (0.X mm) 0.X in. (X mm)

/ 0° 30” +/ --- 0.03 in. +/--- 0.1 in. +/---0° 30”

+/ --- 0.8 mm +/ --- 2 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 to the aircraft

(Refer to AMM 24---00---00---861---802).

(3) Open, safety, and tag the circuit breakers that follow:

CB PANEL CB NO. NAME ZONE

CBP ---1 F10 14th ST B/AIR SOV L 221
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CB PANEL ZONE CB NO. NAME

CBP ---1 G2 A/ICE AUTO 1 221

CBP ---1 G9 WING INSP 221

CBP ---1 M2 ENG IGN A 221

CBP ---1 M3 ENG IGN B 221

CBP ---2 F10 14th ST B/AIR SOV R 221

CBP ---2 G2 A/ICE AUTO 2 222

CBP ---2 N5 A/ICE MAN 2 222

CBP ---2 Q2 EICAS DCU 1 CH A 222

CBP ---2 Q3 EICAS DCU 1 CH B 222

CBP ---2 Q4 EICAS DCU 2 CH A 222

CBP ---2 Q5 EICAS DCU 2 CH B 222

CBP ---3 B1 B/LEAK CONT L 221

CBP ---3 B2 B/LEAK CONT R 221

CBP ---4 B2 BLEED LEAK TEST 222

CBP ---4 B4 A/ICE MAN 1 222

CBP ---4 C10 EICAS DCU 1 CH A 222

CBP ---4 C11 EICAS DCU 1 CH B 222

CBP ---5 A6 DCU 2/3 311

(4) Remove the Left Forward Wing ---to ---Fuselage Fairing 191BB

(Refer to AMM 53---82---01---000---803).

(5) Remove inboard leading edge assembly 520JL

(Refer to AMM 57---41---01---000---803).

(6) Remove center leading edge assembly 530JL

(Refer to AMM 57---41---01---000---804).

(7) Remove outboard leading edge assembly 530KL

(Refer to AMM 57---41---01---000---806).
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(8) Remove the access panel 530KZ and 530LZ

(Refer to AMM 30---11---41---000---801).

(9) Remove the outboard leading edge anti---ice wing ducts

(Refer to AMM 30---11---41---000---801).
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B. Procedure

NOTE: Use kit 601R30---031K2A to do PART A

Refer to Figure 1.

(1) Remove the shroud from the outboard leading edge as follows:

(a) Remove and discard the rivets that hold the shroud.

(b) Remove the shroud.

Refer to Figure 2, View B.

(2) On the leading edge, at approximately WS355.99, drill two holes as follows:

(a) Drill one hole to a diameter of 0.120 in. (3.05 mm) at 0.95 in. (24.1 mm)

inboard of the vent hole and 2.17 in. (55.1 mm) forward of the center of

the holes that attach the leading edge.

(b) Use the bracket of thermal switch P/N M2SL0920305---101 as a template

to drill a second 0.120 in. (3.05 mm) hole inboard of the vent hole.

(c) Do two countersinks on the outboard side of the leading edge for the

screws (2) (Refer to Figure 4 sheet 1 and sheet 2).

(d) Remove the burrs and the sharp edges.

(3) On the leading edge, at approximately WS362.77, drill two holes as follows:

(a) Drill one hole to a diameter of 0.120 in. (3.05 mm) at 0.77 in. (19.6 mm)

outboard of the vent hole and 2.09 in. (53.1 mm) forward of the center of

the holes that attach the leading edge.

(b) Use the bracket of thermal switch P/N M2SL0920305---101 as a template

to drill a second 0.120 in. (3.05 mm) hole outboard of the vent hole.

(c) Do two countersinks on the outboard side of the leading edge for the

screws (2) (Refer to Figure 4 sheet 1 and sheet 2).

(d) Remove the burrs and the sharp edges.
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

Refer to Figure 1, View D.

(4) Visually identify the configuration of leading ---edge shroud that is installed

(Refer to Figure 1, View D).

NOTE: Do not use the number written on the shroud to identify the

configuration. This number identifies a production work station and can

be mistaken for the part number.

For Aircraft that have the configuration 2 (P/N 601R12310 ---1) leading edge installed

Refer to Figure 2, View C and F.

(5) Between WS352 and WS366, on the shroud, drill four holes as follows:

NOTE: If you are not able to respect 4D pitch between the holes or minimal

edge distance, it is possible to drill the holes at different locations inside

the grey area (Refer to view F).

(a) Drill one hole to a diameter between 0.241 in. and 0.246 in. (6.12 mm

and 6.25 mm) at 1.35 in. (34.3 mm) outboard of the access hole and

0.48 in. (12.2 mm) below the upper shroud edge (Refer to view C).

(b) Drill one hole to a diameter between 0.241 in. and 0.246 in. (6.12 mm

and 6.25 mm) at 1.35 in. (34.3 mm) outboard of the access hole and

1.60 in. (40.6 mm) below the upper shroud edge.

(c) Drill one hole to a diameter between 0.241 in. and 0.246 in. (6.12 mm

and 6.25 mm) at 1.80 in. (45.7 mm) inboard of the access hole and

0.63 in. (16.0 mm) below the upper shroud edge.

(d) Drill one hole to a diameter between 0.241 in. and 0.246 in. (6.12 mm

and 6.25 mm) at 1.60 in. (45.7 mm) inboard of the access hole and

1.60 in. (45.7 mm) below the upper shroud edge.

(e) Remove the burrs and sharp edges.

For Aircraft that have the configuration 1 (P/N 601R12062 ---3 or ---5 or ---7) leading edge

installed

Refer to Figure 2, View D and G.

(6) Between WS352 and WS366, on the shroud, drill four holes as follows:

NOTE: If you are not able to respect 4D pitch between the holes or minimal

edge distance, it is permitted to drill the holes at different locations

inside the grey area (Refer to view G).
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(a) Drill one hole to a diameter between 0.241 in. and 0.246 in. (6.12 mm

and 6.25 mm) at 1.35 in. (34.3 mm) inboard of the shroud and 1.75 in.

(44.5 mm) from lower edge of the shroud (Refer to view D).

(b) Drill one hole to a diameter between 0.241 in. and 0.246 in. (6.12 mm

and 6.25 mm) at 2.00 in. (50.8 mm) inboard of the shroud edge and 1.10

in. (27.9 mm) from lower edge of the shroud.

(c) Drill one hole to a diameter between 0.241 in. and 0.246 in. (6.12 mm

and 6.25 mm) at 4.00 in. (101.6 mm) inboard of the shroud edge and

1.75 in. (44.5 mm) from lower edge of the shroud.

(d) Drill one hole to a diameter between 0.241 in. and 0.246 in. (6.12 mm

and 6.25 mm) at 4.65 in. (118.0 mm) inboard of the shroud edge and

1.10 in. (27.9 mm) from lower edge of the shroud.

(e) Remove the burrs and sharp edges.

For all Aircraft

(7) Clean the area with solvent (Refer to SRM 51---26---00).

(8) Apply chemical conversion coating to bare metal areas

(Refer to SRM 51---21---11).

Refer to Figure 2 View E.

(9) On the leading edge, prepare the surface for electrical bonding

(Refer to AMM 51---80---00---100---802).

Refer to Figure 3.

(10) Prepare the thermal switches (1) 1S7HA and 1S8HA for the installation as

follows:

(a) Install approximately 10 in. (254 mm) of the thermal insulating cover (2)

on the wires of the thermal switches.

(b) Install the lacing cord (3) at 0.50 ±0.25 in. (12.7 mm ±6.4 mm) from the

thermal switches (1) (Refer to ESPM 20---12---00).

(c) Apply Glyptol on the knot of the lacing cord.
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Refer to Figure 4.

(11) Install the thermal switches (3) 1S7HA and 1S8HA as follows:

(a) Clean the installation area of the thermal switches (3) with naphtha and

dry immediately with a clean cloth.

CAUTION: MAKE SURE TO APPLY THERMAL COMPOUND ON THE

COMPLETE CONTACT SURFACE OF THE THERMAL SWITCH, IF

THERMAL COMPOUND IS NOT APPLIED ON ALL THE CONTACT

SURFACE OF THE THERMAL SWITCH THE ANTI ---ICE SYSTEM

WILL NOT OPERATE CORRECTLY.

(b) With a spatula, apply a layer of thermal compound (4) to the leading

edge and on the temperature sensitive side of the thermal switches (3).

NOTE: The temperature sensitive side of the thermal switch (3) must be

installed against the leading edge. The temperature sensitive side

of the thermal switch (3) is specified on the thermal switch (3) as

TEMP SIDE.

(c) Put the thermal switches (3) in position on the leading edge.

(d) Carefully push on the thermal switches (3) and make sure that the

thermal compound (4) comes out along the outer edges of the thermal

switches (3).

(e) Install the thermal switches and the bracket (3) with the screws (2) and

nuts (1).

(f) Torque the screws (2) to 5 to 7 lbf•in. (0.6 to 0.8 N•m)

(Refer to AMM 20---21---00---910---801).

(g) Do a detailed inspection of the thermal switches (3). Make sure that

there is a small amount of thermal compound (4) around the thermal

switches (3).

(h) Remove the unwanted thermal compound (4) with a clean dry cloth.

(i) Measure the resistance between the top of the thermal switches (3) and

the leading edge (Refer to AMM 51---80---00---760---802).

(j) Apply chemical conversion coating to the bare metal areas

(Refer to SRM 51---21---11).
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CAUTION: MAKE SURE THE SILICONE COVERS COMPLETELY THE

THERMAL SWITCH AND SCREWS. IF SILICONE DOES NOT

COVER COMPLETELY THE THERMAL SWITCH AND SCREWS

THE SYSTEM WILL NOT OPERATE CORRECTLY.

(k) Apply a layer of silicone (5), maximum thickness of approximately

0.10 in. (2.5 mm), on the thermal switches (3) and the screws (2)

(Refer to SRM 51---23---00).

Refer to Figure 2, sheet 2, View B.

(12) Between WS353 and WS365, in the leading edge, install the decals that

follow:

(a) Install decals 1S7HA, 1S8HA

(Refer to AMM 11---30---00---400---801).

(b) Apply a layer of clear polyurethane topcoat over the decals.

Refer to Figure 2, sheets 3 and 4.

(13) Between WS352.00 and WS362, on the back side of the shroud, install the

decals that follow:

(a) Install decals TB1HA, TB3HA, TB5HA and TB7HA

(Refer to AMM 11---30---00---400---801).

(b) Apply a layer of clear polyurethane topcoat over the decals.

Refer to Figure 4.

(14) In the leading edge, between WS350 and WS366, connect the thermal

switches to the applicable terminal block as follows:

FROM TO TERMINAL

1S7HA WIRE 1 TB7HA MS20659---101

1S7HA WIRE 2 TB1HA MS20659---101

1S8HA WIRE 1 TB5HA MS20659---101

1S8HA WIRE 2 TB3HA MS20659---101
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For Aircraft that have kit 601R30 ---031K2

(a) Remove and discard sleeve kit 601R30---031K111.

For all Aircraft

NOTE: The installation of shrinkable identification sleeves is not recommended

on these wires.

(b) Cut the wires and the thermal insulating covers (6) to the correct length.

(c) Remove the insulation from the wires

(Refer to ESPM 20---17---10).

(d) Install the terminal lugs (10) on the wires

(Refer to ESPM 20---20---00).

NOTE: Crimping tools WT ---110M (for the insulation support) and AMP

49935 with Die 16---22 or equivalent can be used.

(e) Attach the thermal insulating cover (6) to the lug barrel (10) with lacing

cord (16) (Refer to ESPM 20---12---00).

(f) Attach the thermal insulating cover (6) with lacing cord (16) as shown

(view B) (Refer to ESPM 20---12---00).

(g) Apply Glyptol on the knots of the lacing cord.

(h) Connect each thermal switch wire on the shroud with the screw (8),

three washers (9), the shoulder washer (11), washer (12), lock washer

(13) and the nut (14) (Refer to SRM 51---41---04).

(15) Attach the wires of the thermal switches to the leading edge and shroud with

beads of silicone (7) at intervals of 2 in. (50 mm).

(16) If there is no clearance between the wires of the thermal switches and the

nutplates, add a bead of silicone on the wires and the nutplates so that the

wires do not move.

NOTE: The thermal insulating cover (6), installed on the wires of thermal switch

can touch the nutplate but not the threaded part of the fastener that will

be installed.
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Refer to Figure 4 and Figure 6.

(17) At the back of the leading edge, between WS350.00 and WS366.00, connect

the wires that follow:

WIRE TO TERMINAL

1HA2N22 TB1HA MS20659---101

1HA2T22 TB3HA MS20659---101

1HA51N22 TB5HA MS20659---101

1HA51G22 TB7HA MS20659---101

(a) Remove the insulation from the wires

(Refer to ESPM 20---17---10).

(b) Put the wires through the nipple terminals (15).

(c) Install the terminal lugs on the wires

(Refer to ESPM 20---20---00).

NOTE: Crimping tools WT ---110M (for the insulation support) and AMP

49935 with Die 16---22 or equivalent can be used.

(d) Install the crimped terminal lugs on the screws (8) with the washers (9),

lock washers (13) and nuts (14) (Refer to SRM 51---41---04).

(e) Install the nipple terminals (15).

Refer to Figure 5, sheet 1.

(18) Near WS45.00, disconnect connector P427 from receptacle J427.

Refer to Figure 5, sheet 1 thru sheet 5, and Figure 6.

(19) Between WS45.00 and WS362.00, install and connect the wires that follow:

.

WIRE FROM TO TERMINAL

1HA2N22 TB1HA J427---A M39029/58---363

1HA2T22 TB3HA J427---B M39029/58---363

1HA51N22 TB5HA J427---C M39029/58---363
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WIRE TERMINAL FROM TO

1HA51G22 TB7HA J427---S M39029/58---363

(a) Install the wires along with wire LJ20C22.

(b) If necessary, remove and replace clamps and/or cable ties to help the

wiring installation. If necessary, replace the clamp to get the correct fit

around the wires.

(c) If necessary, use a minimum of three turns of fiberglass tape to prevent

damage to the harness.

Refer to Figure 5, Sheet 5.

(d) If necessary, install conduit P/N S10155C14 or equivalent on the four

wires in the area between the wing and the leading edge electrical

harness.

NOTE: The conduit will prevent damage on the four wires during the

installation of the leading edge on the wing.

Refer to Figure 5, sheet 1, and Figure 6.

(e) Remove the insulation from the wires (Refer to ESPM 20---17---10).

(f) Install the terminals on the wires (Refer to ESPM 20---20---00).

(g) Install the wires in receptacles J427 (Refer to ESPM 20---17---10).

(h) Do a continuity check of the installed wires (Refer to ESPM 20---12---01).

Refer to Figure 5, sheet 6.

(20) At FS409+128, disconnect connector P423 from receptacle J423.

Refer to Figure 5, sheet 1, and Figure 6.

(21) Between WS29.42 and BL45.00, install and connect the wires that follow:

.

WIRE FROM TERMINAL TO TERMINAL

1HA2M22 P427---A M39029/56---351 P423---J M39029/58---363

1HA2S22 P427---B M39029/56---351 P423---K M39029/58---363
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WIRE TERMINAL FROM TERMINAL TO

1HA51M22 P427---C M39029/56---351 P423---L M39029/58---363

1HA51F22 P427---S M39029/56---351 P423---d M39029/58---363

(a) If necessary, remove and replace clamps and/or cable ties to help the

wiring installation. If necessary, replace the clamp to get the correct fit

around the wires.

(b) If necessary, use a minimum of three turns of fiberglass tape to prevent

damage to the harness.

(c) Install the new wires along with wires 1HA48B22 and 1HA2H22.

(d) If necessary, to help the installation of the wires in the conduit, remove

the backshell of connector P423 as follows:

1 Disconnect and tag all the wires from connector P423.

2 Remove and discard the boot and the tinel--- ring.

3 Remove and keep the backshell of connector P423.

(e) Install the wires through the conduit.

(f) If removed, install the boot and the backshell of connector P423 as

follows (Refer to ESPM 20---14---00):

1 Put boot P/N 202K153---25---01/225---0 and strap P/N 600---052---1

on the conduit.

2 Put the backshell in the conduit.

3 Put the braid from the conduit on the backshell.

4 With the hand banding tool P/N 600---058 or equivalent, install the

strap over the braid and the backshell.

5 Install the boot on the backshell and the conduit.

(g) Remove the insulation from the wires (Refer to ESPM 20---17---10).
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(h) Install the applicable terminal on the wires (Refer to ESPM 20---20---00).

(i) Install the wires in connector P427 (Refer to ESPM 20---17---10).

(j) Install the wires in connector P423 (Refer to ESPM 20---17---10).

(k) Do a continuity check of the installed wires (Refer to ESPM 20---12---01).

Refer to Figure 5.

(22) Near WS45.00, connect connector P427 to receptacle J427.

(23) At FS409+128, connect connector P423 to receptacle J423.

For Aircraft that have the configuration 2 (P/N 601R12310 ---1) leading edge installed

Refer to Figure 7, sheets 1 and 2.

(24) Install the shroud on the leading edge as follows:

(a) Apply adhesive on the mating surfaces of the shroud and the leading

edge (Refer to SRM 51---22---00).

(b) Apply faying surface sealant on each rib (Refer to SRM 51---23---00).

(c) Put the shroud in position on the leading edge.

(d) Wet install the rivets (2) (Refer to SRM 51---42---06).

(e) Wet install the blind rivets (1) and (3) (Refer to SRM 51---42---10).

(f) Apply silicone adhesive on the head of blind rivets (1) and (3)

(Refer to SRM 51---23---00).

Refer to Figure 7, sheet 2, view C.

(g) Seal gaps with sealant at the outboard end of the leading edge.

(Refer to SRM 51---23---00).

For Aircraft that have the configuration 1 (P/N 601R12062 ---3 or ---5 or ---7) leading edge

installed

Refer to Figure 7, sheet 3 and 4.

(25) Install the shroud on the leading edge as follows:

(a) Apply faying surface sealant on the mating surfaces of the shroud and

the leading edge assembly (Refer to SRM 51---23---00).

(b) Put the shroud in position on the leading edge.

(c) Wet install the blind rivets (4), (5), (6) and (7) (Refer to SRM 51---42---10).

(d) Apply silicone adhesive on the head of blind rivets (4), (5), (6) and (7)

(Refer to SRM 51---23---00).
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C. Job Close ---Out

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

(2) Polish the outboard leading edge on the local work area

(Refer to AMM 57---41---01---140---803).

For all Aircraft

(3) Install the outboard leading edge anti---ice wing ducts

(Refer to AMM 30---11---41---400---801).

(4) Install the access panel 530KZ and 530LZ

(Refer to AMM 30---11---41---400---801).

(5) Install the outboard leading edge assembly 530KL

(Refer to AMM 57---41---01---400---806).

(6) Install center leading edge assembly 530JL

(Refer to AMM 57---41---01---400---804).

(7) Install the inboard leading edge assembly 520JL

(Refer to AMM 57---41---01---400---803).

(8) Install the left forward wing ---to ---fuselage fairing 191BB

(Refer to AMM 53---82---01---400---803).

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

For all Aircraft

CB PANEL CB NO. NAME ZONE

CBP ---1 F10 14th ST B/AIR SOV L 221

CBP ---1 G2 A/ICE AUTO 1 221

CBP ---1 G9 WING INSP 221

CBP ---1 M2 ENG IGN A 221

CBP ---1 M3 ENG IGN B 221

CBP ---2 F10 14th ST B/AIR SOV R 221

CBP ---2 G2 A/ICE AUTO 2 222

CBP ---2 N5 A/ICE MAN 2 222
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CB PANEL ZONE CB NO. NAME

CBP ---2 Q2 EICAS DCU 1 CH A 222

CBP ---2 Q3 EICAS DCU 1 CH B 222

CBP ---2 Q4 EICAS DCU 2 CH A 222

CBP ---2 Q5 EICAS DCU 2 CH B 222

CBP ---3 B1 B/LEAK CONT L 221

CBP ---3 B2 B/LEAK CONT R 221

CBP ---4 B2 BLEED LEAK TEST 222

CBP ---4 B4 A/ICE MAN 1 222

CBP ---4 C10 EICAS DCU 1 CH A 222

CBP ---4 C11 EICAS DCU 1 CH B 222

CBP ---5 A6 DCU 2/3 311

(10) Do the connector integrity after a disconnect and re---connection

(Refer to AMM 20---10---00---910---803).

(11) Do the self---test of the anti ---ice duct system

(Refer to AMM 30---11---00---740---801).

(12) Do the operational test of the WING A/ICE ducts

(Refer to AMM 30---11---00---790---801 or AMM 30---11---00---790---802).

(13) Do the operational test of the bleed ---air leak detection system

(Refer to AMM 36---21---00---710---801).

(14) Do the operational test of the wing inspection lights

(Refer to AMM 33---43---00---710---801).

(15) Do the functional test of the backup sufficient ---heat switches

(Refer to AMM 30---12---17---720---801).
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For all Aircraft

(16) When PART A of 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

601R---30---031, Revision D, PART A, incorporated.”

(17) When PART A of this service bulletin is completed, make this entry in the

applicable logbook(s): “ Service Bulletin 601R---30---031, Revision D, Ice and

Rain Protection --- Wing Anti---Icing System --- Installation of Low Heat

Detection---Switches on the Leading Edge, PART A, incorporated.”
SERVICE BULLETIN 601R---30 ---031

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For Aircraft that have incorporated PART A from the initial issue of this service bulletin

PART B --- Activation of the Low Heat Detection ---Switches

D. Job Set ---Up

Reference Information

REFERENCE DESIGNATION

AMM 24---00---00---861---802 Remove Electrical Power to the Aircraft

AMM 24---00---00---910---801 Electrical/Electronic Safety Precautions

AMM 30---12---15---710---801 Operational Test of the Outboard Low Heat

Switches

AMM 31---41---04---000---801 Removal of the DCU

AMM 31---41---04---400---801 Installation of the DCU

AMM 31---41---04---710---801 Operational Test of the DCU

ESPM 20---11---00 Wire Stripping and Wire/Cable Damage Repair

Maintenance Practices

ESPM 20---17---10 Electrical Connectors --- Maintenance Practices

ESPM 20---20---00 Terminal Lugs --- Removal/Installation

ESPM 20---23---00 Circuit Breakers --- Removal/Installation

(1) Obey all the electrical/electronic safety precautions

(Refer to AMM 24---00---00---910---801).

(2) Open, safety, and tag the circuit breakers that follow:

For Aircraft with the third DCU option (CR31 ---310 or CR31 ---001)

CB PANEL CB NO. NAME ZONE

CBP ---2 K6 EICAS DCU 3 CH A 222

CBP ---2 K7 EICAS DCU 3 CH B 222
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For all Aircraft

CB PANEL CB NO. NAME ZONE

CBP ---2 N5 A/ICE MAN 2 222

CBP ---2 Q2 EICAS DCU 1 CH A 222

CBP ---2 Q3 EICAS DCU 1 CH B 222

CBP ---2 Q4 EICAS DCU 2 CH A 222

CBP ---4 B4 A/ICE MAN 1 222

CBP ---4 C10 EICAS DCU 1 CH A 222

CBP ---4 C11 EICAS DCU 1 CH B 222

CBP ---5 A6 DCU 2/3 311

(3) Remove DCU 1 and DCU 2 (Refer to AMM 31---41---04---000---801).

For Aircraft with the third DCU option (CR31 ---001 or CR31 ---310)

(4) Remove DCU 3

(Refer to AMM 31---41---04---000---801).
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E. Procedure

Refer to Figure 5, sheet 6.

NOTE: This wiring diagram configuration is not shown on the Figures.

(1) On left side of the main avionics ---compartment, at FS384.00, unstow and

connect the wires that follow:

WIRE FROM TO TERMINAL W

2HA51L22 P595---12 1P1WA ---B---11A B0802050---010 8

1HA51A22 P595---13 1P1WA ---A ---11A B0802050---010 8

(a) Remove the insulation from the wires (Refer to ESPM 20---11---00).

(b) Install the applicable terminals on the wires (Refer to ESPM 20---20---00).

(c) Install the wires at the locations given (Refer to ESPM 20---17---10).

(d) Do a continuity check of the installed wires (Refer to ESPM 20---17---10).

Refer to Figure 5, sheets 6, and 7.

NOTE: This wiring diagram configuration is not shown on the Figures.

(2) On the right side of the main avionics ---compartment, at FS374, unstow and

connect the wires that follow:

WIRE FROM TO TERMINAL W

2HA51A22 J194---27 2P1WA ---B---11A B0802050---010 9

1HA54A22 J196---87 2P1WA ---A ---11A B0802050---010 9

(a) Remove the insulation from the wires (Refer to ESPM 20---11---00).

(b) Install the applicable terminal on the wires (Refer to ESPM 20---20---00).

(c) Install the wires at the locations given (Refer to ESPM 20---17---10).

(d) Do a continuity check of the installed wires (Refer to ESPM 20---12---01).
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For Aircraft with the third DCU option (CR31 ---001 or CR31 ---310)

Refer to Figure 5, sheets 6 and 7.

NOTE: This wiring diagram configuration is not shown on the Figures.

(3) In the main avionics ---compartment, at FS386, unstow and connect the wires

that follow:

WIRE FROM TO TERMINAL W

1HA52A22 J193---47 P1WH---B---11A B0802050---010 9

1HA53A22 J196---90 P1WH---A ---11A B0802050---010 9

(a) Remove the insulation from the wire ends (Refer to ESPM 20---11---00).

(b) Install the applicable terminal on the wires (Refer to ESPM 20---20---00).

(c) Install the wires in the connectors (Refer to ESPM 20---17---10).

(d) Do a continuity check of the installed wires (Refer to ESPM 20---12---01).

(4) Remove the lockrings and close the circuit breakers of the WING A/ICE box

assembly (1) that follows (Refer to ESPM 20---23---00):

CB ON THE WAI

BOX

NAME

1CB2HA RHS OUTBOARD 1

2CB2HA RHS OUTBOARD 2

1CB1HA LHS OUTBOARD 1

2CB1HA LHS OUTBOARD 2
SERVICE BULLETIN 601R---30 ---031

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F. Job Close ---Out

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

For Aircraft with the third DCU option (CR31 ---001 or CR31 ---310)

(2) Install DCU 3 (Refer to AMM 31---41---04---400---801).

For all Aircraft

(3) Install DCU 1 and DCU 2 (Refer to AMM 31---41---04---400---801).

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

For Aircraft with the third DCU option (CR31 ---310 or CR31 ---001)

CB PANEL CB NO. NAME ZONE

CBP ---2 K6 EICAS DCU 3 CH A 222

CBP ---2 K7 EICAS DCU 3 CH B 222

For all Aircraft

CB PANEL CB NO. NAME ZONE

CBP ---2 N5 A/ICE MAN 2 222

CBP ---2 Q2 EICAS DCU 1 CH A 222

CBP ---2 Q3 EICAS DCU 1 CH B 222

CBP ---2 Q4 EICAS DCU 2 CH A 222

CBP ---2 Q5 EICAS DCU 2 CH B 222

CBP ---4 B4 A/ICE MAN 1 222

CBP ---4 C10 EICAS DCU 1 CH A 222

CBP ---4 C11 EICAS DCU 1 CH B 222

CBP ---5 A6 DCU 2/3 311
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(5) Do the operational test of the outboard low heat detection---switches

(Refer to AMM 30---12---15---710---801).

(6) Do the operational test of the DCU (Refer to AMM 31---41---04---710---801).

For all Aircraft

(7) Close the main avionics ---compartment door.

(8) When PART B of this service bulletin is completed, make this entry in the

applicable logbook(s): “ Service Bulletin 601R---30---031, Revision D, Ice and

Rain Protection --- Wing Anti---Icing System --- Installation of Low Heat

Detection---Switches on the Leading Edge, PART B, incorporated.”
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

PART C --- Installation of the Low Heat Detection ---Switches on the Right Wing

G. Job Set ---Up

Reference Information

REFERENCE DESIGNATION

AMM 11---30---00---400---801 Installation of the Adhesive---Backed Label

AMM 20---10---00---910---803 Connector Integrity After a Disconnect and

Re---connection

AMM 20---21---00---910---801 Torque Procedures for Threaded Fasteners

AMM 24---00---00---861---802 Remove Electrical Power to the Aircraft

AMM 24---00---00---910---801 Electrical/Electronic Safety Precautions

AMM 30---11---00---740---801 Self---Test of the Anti Ice Duct System

AMM 30---11---00---790---801 Operational test of the Wing Anti---Ice Ducts

(External Air Supply)

AMM 30---11---00---790---802 Operational test of the Wing Anti---Ice Ducts

(Engine Bleed Air Supply)

AMM 30---11---41---000---801 Removal of the Leading Edge Anti---Ice Wing

Ducts (Piccolo Tubes)

AMM 30---11---41---400---801 Installation of the Leading Edge Anti---Ice Wing

Ducts (Piccolo Tubes)

AMM 30---12---17---720---801 Functional Test of the Backup Sufficient ---Heat

Switches

AMM 33---43---00---710---801 Operational Test of the Wing Inspection Lights

AMM 36---21---00---710---801 Operational Test of the Bleed ---Air Leak

Detection and Warning System

AMM 51---80---00---100---802 Surface Preparation for Electrical Bonding

AMM 51---80---00---760---802 Electrical Bonding Resistance Values

AMM 53---82---01---000---802 Removal of the Right Forward Wing ---to ---Fuselage Fairing

AMM 53---82---01---400---802 Installation of the Right Forward Wing ---to ---Fuselage Fairing
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REFERENCE DESIGNATION

AMM 57---41---01---000---803 Removal of the Inboard Leading Edge Assembly 520JL (620JL)

AMM 57---41---01---000---804 Removal of the Center Leading Edge Assembly

530JL (630JL)

AMM 57---41---01---000---806 Removal of the Outboard Leading Edge

Assembly 530KL (630KL)

AMM 57---41---01---140---803 Polishing of the Wing Leading Edges

AMM 57---41---01---400---803 Installation of the Inboard Leading Edge

Assembly 520JL (620JL)

AMM 57---41---01---400---804 Installation of the Center Leading Edge

Assembly 530JL (630JL)

AMM 57---41---01---400---806 Installation of the Outboard Leading Edge

Assembly 530KL (630KL)

ESPM 20---11---00 Wire Stripping and Wire/Cable Damage Repair

Maintenance Practices

ESPM 20---12---00 Wiring --- Removal/Installation

ESPM 20---12---01 Electrical Wiring --- Continuity Testing

ESPM 20---14---00 Convolex Tubing/Conduit ---

Removal/Installation

ESPM 20---17---10 Electrical Connectors --- Maintenance Practices

ESPM 20---20---00 Terminal Lugs --- Removal/Installation

ESPM 20---23---00 Circuit Breakers --- Removal/Installation

SRM 51---21---11 Corrosion Prevention Procedures

SRM 51---21---16 Finish Codes

SRM 51---22---00 Bonding and Attaching Parts with Adhesives

SRM 51---23---00 Pressure, Environmental, Fuel Tank and Firewall

Sealing

SRM 51---25---06 Fluid ---Resistant (FR) Epoxy Primer

SRM 51---25---16 Fluid ---Resistant (FR) Polyurethane Topcoat
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REFERENCE DESIGNATION

SRM 51---26---00 Cleaning

SRM 51---41---04 Torque Procedures --- Bolts and Screws

SRM 51---42---06 Solid Rivets

SRM 51---42---10 Blind Rivets --- General

Tolerance Information

Linear Tolerances Angular Tolerance

0.XX in. (0.X mm) 0.X in. (X mm)

/ 0° 30” +/ --- 0.03 in. +/--- 0.1 in. +/---0° 30”

+/ --- 0.8 mm +/ --- 2 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 to the aircraft (Refer to AMM 24---00---00---861---802).

(3) Open, safety, and tag the circuit breakers that follow:

CB PANEL CB NO. NAME ZONE

CBP ---1 F10 14th ST B/AIR SOV L 221

CBP ---1 G2 A/ICE AUTO 1 221

CBP ---1 G9 WING INSP 221

CBP ---1 M2 ENG IGN A 221

CBP ---1 M3 ENG IGN B 221
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CB PANEL ZONE CB NO. NAME

CBP ---2 F10 14th ST B/AIR SOV R 221

CBP ---2 G2 A/ICE AUTO 2 222

CBP ---2 N5 A/ICE MAN 2 222

CBP ---2 Q2 EICAS DCU 1 CH A 222

CBP ---2 Q3 EICAS DCU 1 CH B 222

CBP ---2 Q4 EICAS DCU 2 CH A 222

CBP ---2 Q5 EICAS DCU 2 CH B 222

CBP ---3 B1 B/LEAK CONT L 221

CBP ---3 B2 B/LEAK CONT R 221

CBP ---4 B2 BLEED LEAK TEST 222

CBP ---4 B4 A/ICE MAN 1 222

CBP ---4 C10 EICAS DCU 1 CH A 222

CBP ---4 C11 EICAS DCU 1 CH B 222

CBP ---5 A6 DCU 2/3 311

(4) Remove the right forward wing ---to ---fuselage fairing 192BB

(Refer to AMM 53---82---01---000---803).

(5) Remove inboard leading edge assembly 620JL

(Refer to AMM 57---41---01---000---803).

(6) Remove center leading edge assembly 630JL

(Refer to AMM 57---41---01---000---804).

(7) Remove outboard leading edge assembly 630KL

(Refer to AMM 57---41---01---000---806).

(8) Remove the access panel 630KZ and 630LZ

(Refer to AMM 30---11---41---000---801).

(9) Remove the outboard leading edge anti---ice wing ducts

(Refer to AMM 30---11---41---000---801).
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H. Procedure

NOTE: Use kit 601R30---031K3A to do PART C.

Refer to Figure 1

(1) Remove the shroud from the outboard leading edge as follows:

(a) Remove and discard the rivets that hold the shroud.

(b) Remove the shroud.

Refer to Figure 2, View B.

(2) On the leading edge, at approximately WS355.99, drill two holes as follows:

(a) Drill one hole to a diameter of 0.120 in. (3.05 mm) at 0.95 in. (24.1 mm)

inboard of the vent hole and 2.17 in. (55.1 mm) forward of the center of

the holes that attach the leading edge.

(b) Use the bracket of thermal switch P/N M2SL0920305---101 as a template

to drill a second 0.120 in. (3.05 mm) hole inboard of the vent hole.

(c) Do two countersinks on the outboard side of the leading edge for the

screws (2) (Refer to Figure 4 sheet 1 and sheet 2).

(d) Remove the burrs and the sharp edges.

(3) On the leading edge, at approximately WS362.77, drill two holes as follows:

(a) Drill one hole to a diameter of 0.120 in. (3.05 mm) at 0.77 in. (19.6 mm)

outboard of the vent hole and 2.09 in. (53.1 mm) forward of the center of

the holes that attach the leading edge.

(b) Use the bracket of thermal switch P/N M2SL0920305---101 as a template

to drill a second 0.120 in. (3.05 mm) hole outboard of the vent hole.

(c) Do two countersinks on the outboard side of the leading edge for the

screws (2) (Refer to Figure 4 sheet 1 and sheet 2).

(d) Remove the burrs and the sharp edges.
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Refer to Figure 1, View D.

(4) Visually identify the configuration of leading ---edge shroud that is installed

(Refer to Figure 1, View D).

NOTE: Do not use the number written on the shroud to identify the

configuration. This number identifies a production work station and can

be mistaken for the part number.

For Aircraft that have the configuration 2 (P/N 601R12310 ---2) leading edge installed

Refer to Figure 2, View C and F.

(5) Between WS352 and WS366, on the shroud, drill four holes as follows:

NOTE: If you are not able to respect 4D pitch between the holes or minimal

edge distance, it is permitted to drill the holes at different locations

inside the grey area (refer to view F).

(a) Drill one hole to a diameter between 0.241 in. and 0.246 in. (6.12 mm

and 6.25 mm) at 1.35 in. (34.3 mm) outboard of the access hole and

0.48 in. (12.2 mm) below the upper shroud edge (Refer to view C).

(b) Drill one hole to a diameter between 0.241 in. and 0.246 in. (6.12 mm

and 6.25 mm) at 1.35 in. (34.3 mm) outboard of the access hole and

1.60 in. (40.6 mm) below the upper shroud edge.

(c) Drill one hole to a diameter between 0.241 in. and 0.246 in. (6.12 mm

and 6.25 mm) at 1.80 in. (45.7 mm) inboard of the access hole and

0.63 in. (16.0 mm) below the upper shroud edge.

(d) Drill one hole to a diameter between 0.241 in. and 0.246 in. (6.12 mm

and 6.25 mm) at 1.60 in. (45.7 mm) inboard of the access hole and

1.60 in. (45.7 mm) below the upper shroud edge.

(e) Remove the burrs and sharp edges.

For Aircraft that have the configuration 1 (P/N 601R12062 ---4 or ---6 or ---8) leading edge

installed

Refer to Figure 2, View D and G.

(6) Between WS352 and WS366, on the shroud, drill four holes as follows:

NOTE: If you are not able to respect 4D pitch between the holes or minimal

edge distance, it is permitted to drill the holes at different locations

inside the grey area (refer to view G).
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(a) Drill one hole to a diameter between 0.241 in. and 0.246 in. (6.12 mm

and 6.25 mm) at 1.35 in. (34.3 mm) inboard of the shroud and 1.75 in.

(44.5 mm) from lower edge of the shroud (Refer to view D).

(b) Drill one hole to a diameter between 0.241 in. and 0.246 in. (6.12 mm

and 6.25 mm) at 2.00 in. (50.8 mm) inboard of the shroud edge and 1.10

in. (27.9 mm) from lower edge of the shroud.

(c) Drill one hole to a diameter between 0.241 in. and 0.246 in. (6.12 mm

and 6.25 mm) at 4.00 in. (101.6 mm) inboard of the shroud edge and

1.75 in. (44.5 mm) from lower edge of the shroud.

(d) Drill one hole to a diameter between 0.241 in. and 0.246 in. (6.12 mm

and 6.25 mm) at 4.65 in. (118.0 mm) inboard of the shroud edge and

1.10 in. (27.9 mm) from lower edge of the shroud.

(e) Remove the burrs and sharp edges.

For all Aircraft

(7) Clean the area with solvent (Refer to SRM 51---26---00).

(8) Apply chemical conversion coating to bare metal areas

(Refer to SRM 51---21---11).

Refer to Figure 2, View E.

(9) On the leading edge, prepare the surface for electrical bonding

(Refer to AMM 51---80---00---100---802).

Refer to Figure 3.

(10) Prepare the thermal switches (1) 2S7HA and 2S8HA for installation as follows:

(a) Install approximately 10 in. (254 mm) of the thermal insulating cover (2)

on the wires of the thermal switches.

(b) Install the lacing cord (3) at 0.50 ±0.25 in. (12.7 mm ±6.4 mm) from the

thermal switches (1) (Refer to ESPM 20---12---00).

(c) Apply Glyptol on the knot of the lacing cord.
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Refer to Figure 4, sheets 1, and 2.

(11) Install the thermal switches (3) 2S7HA and 2S8HA as follows:

(a) Clean the installation area of the thermal switches (3) with naphtha and

dry immediately with a clean cloth.

CAUTION: MAKE SURE TO APPLY THERMAL COMPOUND ON THE

COMPLETE CONTACT SURFACE OF THE THERMAL SWITCH, IF

THERMAL COMPOUND IS NOT APPLIED ON ALL THE CONTACT

SURFACE OF THE THERMAL SWITCH THE ANTI ---ICE SYSTEM

WILL NOT OPERATE CORRECTLY.

(b) With a spatula, apply a layer of thermal compound (4) to the leading

edge and on the temperature sensitive side of the thermal switches (3).

NOTE: The temperature sensitive side of the thermal switch (3) must be

installed against the leading edge. The temperature sensitive side

of the thermal switch (3) is specified on the thermal switch (3) as

TEMP SIDE.

(c) Put the thermal switches (3) in position on the leading edge.

(d) Carefully push on the thermal switches (3) and make sure that the

thermal compound (4) comes out along the outer edges of the thermal

switches (3).

(e) Install the thermal switches and the bracket (3) with the screws (2) and

nuts (1).

(f) Torque the screws (2) to 5 to 7 lbf•in. (0.6 to 0.8 N•m)

(Refer to AMM 20---21---00---910---801).

(g) Do a detailed inspection of the thermal switches (3). Make sure that

there is a small amount of thermal compound (4) around the thermal

switches (3).

(h) Remove the unwanted thermal compound (4) with a clean dry cloth.

(i) Measure the resistance between the top of the thermal switches (3) and

the leading edge (Refer to AMM 51---80---00---760---802).

(j) Apply chemical conversion coating to the bare metal areas

(Refer to SRM 51---21---11).
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CAUTION: MAKE SURE THE SILICONE COVERS COMPLETELY THE

THERMAL SWITCH AND SCREWS. IF SILICONE DOES NOT

COVER COMPLETELY THE THERMAL SWITCH AND SCREWS

THE SYSTEM WILL NOT OPERATE CORRECTLY.

(k) Apply a layer of silicone (5), maximum thickness of approximately

0.10 in. (2.5 mm), on the thermal switches (3) and the screws (2)

(Refer to SRM 51---23---00).

Refer to Figure 2, sheet 2, View B.

(12) Between WS353 and WS365, in the leading edge, install the decals that

follow:

(a) Install decals 2S7HA, 2S8HA

(Refer to AMM 11---30---00---400---801).

(b) Apply a layer of clear polyurethane topcoat over the decals.

Refer to Figure 2, sheets 2, and 3.

(13) Between WS352.00 and WS362, on the back side of the shroud, install the

decals that follow:

(a) Install decals TB2HA, TB4HA, TB6HA and TB8HA

(Refer to AMM 11---30---00---400---801).

(b) Apply a layer of clear polyurethane topcoat over the decals.

Refer to Figure 4 and Figure 9.

(14) In the leading edge, between WS350 and WS366, connect the thermal

switches to the applicable terminal block as follows:

FROM TO TERMINAL

2S7HA WIRE 1 TB8HA MS20659---101

2S7HA WIRE 2 TB2HA MS20659---101

2S8HA WIRE 1 TB6HA MS20659---101

2S8HA WIRE 2 TB4HA MS20659---101
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For Aircraft that have kit 601R30 ---031K3

(a) Remove and discard sleeve kit 601R30---031K112.

For all Aircraft

NOTE: The installation of shrinkable identification sleeves is not recommended

on these wires.

(b) Cut the wires and the thermal insulating covers (6) to the correct length.

(c) Remove the insulation from the wires (Refer to ESPM 20---17---10).

(d) Install the terminal lugs (10) on the wires (Refer to ESPM 20---20---00).

NOTE: Crimping tools WT ---110M (for the insulation support) and AMP

49935 with Die 16---22 or equivalent can be used.

(e) Attach the thermal insulating cover (6) to the lug barrel (10) with lacing

cord (16) (Refer to ESPM 20---12---00).

(f) Attach the thermal insulating cover (6) with lacing cord (16) as shown

(view B) (Refer to ESPM 20---12---00).

(g) Apply Glyptol on the knots of the lacing cords.

(h) Connect each thermal switch wire on the shroud with the screw (8),

three washers (9), one shoulder washer (11), one washer (12), one lock

washer (13) and the nut (14) (Refer to SRM 51---41---04).

(15) Attach the wires of the thermal switches to the leading edge and shroud with

beads of silicone (7) at intervals of 2 in. (50 mm).

(16) If there is no clearance between the wires of the thermal switches and the

nutplates, add a bead of silicone on the wires and the nutplates so that the

wires do not move.

NOTE: The thermal insulating cover (6), installed on the wires of thermal switch

can touch the nutplate but not the threaded part of the fastener that will

be installed.
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Refer to Figure 4 and Figure 9.

(17) At the back of the leading edge, between WS350 and WS366, connect the

wires that follow:

WIRE TO TERMINAL

2HA2Q22 TB2HA MS20659---101

2HA2U22 TB4HA MS20659---101

2HA51T22 TB6HA MS20659---101

2HA51K22 TB8HA MS20659---101

(a) Remove the insulation from the wires (Refer to ESPM 20---17---10).

(b) Put the wires through the nipple terminals (15).

(c) Install the terminals on the wires (Refer to ESPM 20---20---00).

NOTE: Crimping tools WT ---110M (for the insulation support) and AMP

49935 with Die 16---22 or equivalent can be used.

(d) Install the crimped terminal lugs on the screws (8) with the washers (9),

lock washers (13) and nuts (14) on the terminal board

(Refer to SRM 51---41---04).

(e) Install the nipple terminals (15) over the terminal board.

Refer to Figure 5, sheet 1.

(18) Near WS45.00, disconnect connector P426 from receptacle J426.

Refer to Figure 5, sheet 1 thru sheet 5, and Figure 9.

(19) Between WS45.00 and WS362.00 install and connect the wires that follow:

.

WIRE FROM TO TERMINAL

2HA2Q22 TB2HA J426---A M39029/58---363

2HA2U22 TB4HA J426---B M39029/58---363

2HA51T22 TB6HA J426---C M39029/58---363
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WIRE TERMINAL FROM TO

2HA51K22 TB8HA J426---S M39029/58---363

(a) Install the wires along with wire LJ19D22.

(b) If necessary, remove and replace clamps and/or cable ties to help the

wiring installation. If necessary, replace the clamp to get the correct fit

around the wires.

(c) If necessary, use a minimum of three turns of fiberglass tape to prevent

damage to the harness.

Refer to Figure 5, Sheet 5.

(d) If necessary, install conduit P/N S10155C14 or equivalent on the four

wires in the area between the wing and the leading edge electrical

harness.

NOTE: The conduit will prevent damage on the four wires during the

installation of the leading edge on the wing.

Refer to Figure 5, sheet 1, and Figure 9.

(e) Remove the insulation from the wires (Refer to ESPM 20---17---10).

(f) Install the applicable terminal on the wires (Refer to ESPM 20---20---00).

(g) Install the wires in receptacles J426 (Refer to ESPM 20---17---10).

(h) Do a continuity check of the installed wires (Refer to ESPM 20---12---01).

Refer to Figure 5, sheet 6.

(20) At FS409+128, disconnect connector P422 from receptacle J422.

Refer to Figure 5, sheet 1, and Figure 9.

(21) Between WS29.42 and BL45.00, install and connect the wires that follow:

.

WIRE FROM TERMINAL TO TERMINAL

2HA2P22 P426---A M39029/56---351 P422---J M39029/58---363

2HA2T22 P426---B M39029/56---351 P422---K M39029/58---363

2HA51S22 P426---C M39029/56---351 P422---L M39029/58---363

2HA51J22 P426---S M39029/56---351 P422---d M39029/58---363
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(a) If necessary, remove and replace clamps and/or cable ties to help the

wiring installation. If necessary, replace the clamp to get the correct fit

around the wires.

(b) If necessary, use a minimum of three turns of fiberglass tape to prevent

damage to the harness.

(c) Install the new wires along with wires 2HA48B22 and 2HA2H22.

(d) If necessary, to help the installation of the wires in the conduit, remove

the backshell of connector P422 as follows:

1 Disconnect and tag all the wires from connector P422.

2 Remove and keep the backshell of connector P422.

3 Remove and discard the boot and the tinel--- ring.

(e) Install the wires through the conduit.

(f) If removed, install the boot and the backshell of connector P422 as

follows (Refer to ESPM 20---14---00):

1 Put boot P/N 202K153---25---01/225---0 and strap P/N 600---052---1

on the conduit.

2 Put the backshell in the conduit.

3 Put the braid from the conduit on the backshell.

4 With the hand banding tool P/N 600---058 or equivalent, install the

strap over the braid and the backshell.

5 Install the boot on the backshell and the conduit.

(g) Remove the insulation from the wires (Refer to ESPM 20---17---10).

(h) Install the applicable terminal on the wires (Refer to ESPM 20---20---00).

(i) Install the wires in connector P426 (Refer to ESPM 20---17---10).

(j) Install the wires in connector P422 (Refer to ESPM 20---17---10).
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(k) Do a continuity check of the installed wires (Refer to ESPM 20---12---01).

Refer to Figure 5.

(22) Near WS45.00, connect connector P426 to receptacle J426.

(23) At FS409+128, connect connector P422 to receptacle J422.

For Aircraft that have the configuration 2 (P/N 601R12310 ---2) leading edge installed

Refer to Figure 7, sheet 1, and 2.

(24) Install the shroud on the leading edge as follows:

(a) Apply adhesive on the mating surfaces of the shroud and the leading

edge (Refer to SRM 51---22---00).

(b) Apply faying surface sealant on each rib (Refer to SRM 51---23---00).

(c) Put the shroud in position on the leading edge.

(d) Wet install the rivets (2) (Refer to SRM 51---42---06).

(e) Wet install the blind rivets (1) and (3) (Refer to SRM 51---42---10).

(f) Apply silicone adhesive on the head of blind rivets (1) and (3)

(Refer to SRM 51---23---00).

Refer to Figure 7, sheet 2, View C.

(g) Seal gaps with sealant at the outboard end of the leading edge.

(Refer to SRM 51---23---00).

For Aircraft that have the configuration 1 (P/N 601R12062 ---4 or ---6 or ---8) leading edge

installed

Refer to Figure 7, sheets 3 and 4.

(25) Install the shroud on the leading edge as follows:

(a) Apply faying surface sealant on the mating surfaces of the shroud and

the leading edge assembly (Refer to SRM 51---23---00).

(b) Put the shroud in position on the leading edge.

(c) Wet install the blind rivets (4), (5), (6) and (7) (Refer to SRM 51---42---10).

(d) Apply silicone adhesive on the head of blind rivets (4), (5), (6) and (7)

(Refer to SRM 51---23---00).
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I. Job Close ---Out

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

(2) Polish the leading edge at the area of the installation of the thermal switches

(AMM 57---41---01---140---803).

For all Aircraft

(3) Install the outboard leading edge anti---ice wing ducts

(Refer to AMM 30---11---41---400---801).

(4) Install the access panel 630KZ and 630LZ

(Refer to AMM 30---11---41---400---801).

(5) Install the outboard leading edge assembly 630KL

(Refer to AMM 57---41---01---400---806).

(6) Install center leading edge assembly 630JL

(Refer to AMM 57---41---01---400---804).

(7) Install the inboard leading edge assembly 620JL

(Refer to AMM 57---41---01---400---803).

(8) Install the right forward wing ---to ---fuselage fairing 192BB

(Refer to AMM 53---82---01---400---803).

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

For all Aircraft

CB PANEL CB NO. NAME ZONE

CBP ---1 F10 14th ST B/AIR SOV L 221

CBP ---1 G2 A/ICE AUTO 1 221

CBP ---1 G9 WING INSP 221

CBP ---1 M2 ENG IGN A 221

CBP ---1 M3 ENG IGN B 221

CBP ---2 F10 14th ST B/AIR SOV R 221

CBP ---2 G2 A/ICE AUTO 2 222

CBP ---2 N5 A/ICE MAN 2 222
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CB PANEL ZONE CB NO. NAME

CBP ---2 Q2 EICAS DCU 1 CH A 222

CBP ---2 Q3 EICAS DCU 1 CH B 222

CBP ---2 Q4 EICAS DCU 2 CH A 222

CBP ---2 Q5 EICAS DCU 2 CH B 222

CBP ---3 B1 B/LEAK CONT L 221

CBP ---3 B2 B/LEAK CONT R 221

CBP ---4 B2 BLEED LEAK TEST 222

CBP ---4 B4 A/ICE MAN 1 222

CBP ---4 C10 EICAS DCU 1 CH A 222

CBP ---4 C11 EICAS DCU 1 CH B 222

CBP ---5 A6 DCU 2/3 311

(10) Do the connector integrity after a disconnect and re---connection

(Refer to AMM 20---10---00---910---803).

(11) Do the self---test of the anti ---ice duct system

(Refer to AMM 30---11---00---740---801).

(12) Do the operational test of the WING A/ICE ducts

(Refer to AMM 30---11---00---790---801 or AMM 30---11---00---790---802).

(13) Do the operational test of the bleed ---air leak detection system

(Refer to AMM 36---21---00---710---801).

(14) Do the operational test of the wing inspection lights

(Refer to AMM 33---43---00---710---801).

(15) Do the functional test of the backup sufficient ---heat switches

(Refer to AMM 30---12---17---720---801).
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(16) When PART C of 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

601R---30---031, Revision D, PART C, incorporated.”

(17) When PART C of this service bulletin is completed, make this entry in the

applicable logbook(s): “ Service Bulletin 601R---30---031, Revision D, Ice and

Rain Protection --- Wing Anti---Icing System --- Installation of Low Heat

Detection---Switches on the Leading Edge, PART C, incorporated.”
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PART D --- Installation of the Wing A/ICE box assembly on the Left Side of the Main

Avionics ---Compartment

J. Job Set ---Up

Reference Information

REFERENCE DESIGNATION

AMM 11---30---00---400---801 Installation of the Adhesive---Backed Label

AMM 20---10---00---910---803 Connector Integrity After a Disconnect and

Re---connection

AMM 20---21---00---910---801 Torque Procedures for Threaded Fasteners

AMM 24---00---00---861---802 Remove Electrical Power to the Aircraft

AMM 24---00---00---910---801 Electrical/Electronic Safety Precautions

AMM 25---21---01---000---801 Removal of the Passenger Seat

AMM 25---21---01---400---801 Installation of the Passenger Seat

AMM 25---25---01---000---801 Removal of the Textile Floor Covering

AMM 25---25---01---400---801 Installation of the Textile Floor Covering

AMM 31---41---04---000---801 Removal of the DCU

AMM 31---41---04---400---801 Installation of the DCU

AMM 31---41---04---710---801 Operational Test of the DCU

AMM 34---21---01---000---801 Removal of the AHC

AMM 34---21---01---400---801 Installation of the AHC

AMM 34---21---01---710---801 Operational Test of the AHC

AMM 34---58---01---000---801 Removal of the Global Positioning System

Sensor Unit

AMM 34---58---01---400---801 Installation of the GPSSU

AMM 34---58---01---700---801 Operational Test of the Global Positioning

System Sensor Unit

AMM 51---80---00---100---802 Surface Preparation for Electrical Bonding
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REFERENCE DESIGNATION

AMM 51---80---00---760---802 Electrical Bonding Resistance Values

AMM 53---01---01---000---802 Removal of the Passenger Compartment Floor

Panels

AMM 53---01---01---400---802 Installation of the Passenger Compartment

Floor Panels

AMM 53---82---01---000---803 Removal of the Left Forward Wing ---to ---Fuselage Fairing

AMM 53---82---01---400---803 Installation of the Left Forward Wing ---to

Fuselage Fairing

ESPM 20---11---00 Wire Stripping and Wire/Cable Damage Repair

Maintenance Practices

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

ESPM 20---23---00 Circuit Breakers --- Removal/Installation

SRM 51---21---11 Corrosion Prevention Procedures

SRM 51---21---16 Finish Codes

SRM 51---25---06 Fluid ---Resistant (FR) Epoxy Primer

SRM 51---25---16 Fluid ---Resistant (FR) Polyurethane Topcoat

SRM 51---26---00 Cleaning

SRM 51---41---04 Torque Procedures --- Bolts and Screws

SRM 51---42---06 Solid Rivets

SRM 51---45---00 Nut Plates (Anchor Nuts) ---General
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Tolerance Information

Linear Tolerances Angular Tolerance

0.XX in. (0.X mm) 0.X in. (X mm)

/ 0° 30” +/ --- 0.03 in. +/--- 0.1 in. +/---0° 30”

+/ --- 0.8 mm +/ --- 2 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 to the aircraft (Refer to AMM 24---00---00---861---802).

(3) Open, safety, and tag the circuit breakers that follow:

For Aircraft with the third DCU option (CR31 ---310 or CR31 ---001)

CB PANEL CB NO. NAME ZONE

CBP ---2 K6 EICAS DCU 3 CH A 222

CBP ---2 K7 EICAS DCU 3 CH B 222

For Aircraft with the Global Positioning System (GPS) Option (CR34 ---352 or

CR34 ---350)

CB PANEL CB NO. NAME ZONE

CBP ---1 H13 GPS 1 221
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For Aircraft with the Attitude and Heading Reference System (AHRS) Option

(TS34 ---320)

CB PANEL CB NO. NAME ZONE

CBP ---2 H14 AHRS 2 222

CBP ---2 H15 AHRS FAN 2 222

CBP ---4 D8 AHRS 1 222

CBP ---4 D9 AHRS FAN 1 222

For Aircraft 7003 thru 7609 with the Attitude and Heading Reference System

(AHRS) Option (TS34 ---320)

CB PANEL CB NO. NAME ZONE

CBP ---5 A8 ATT/HDG 1 311

CBP ---5 A9 ATT/HDG 2 311

CBP ---5 A7 STBY PWR CONT 311

For Aircraft 7610 thru 7990 and 8000 thru 8101 with the Attitude and Heading

Reference System (AHRS) Option (TS34 ---320)

CB PANEL CB NO. NAME ZONE

CBP ---1 N4 ATT/HDG 1 221

CBP ---1 N5 ATT/HDG 2 221

For all Aircraft

CB PANEL CB NO. NAME ZONE

CBP ---1 F10 14th ST B/AIR SOV L 221

CBP ---1 G2 A/ICE AUTO 1 221

CBP ---1 G9 WING INSP 221

CBP ---1 M2 ENG IGN A 221

CBP ---1 M3 ENG IGN B 221

CBP ---2 F10 14th ST B/AIR SOV R 221
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CB PANEL ZONE CB NO. NAME

CBP ---2 G2 A/ICE AUTO 2 222

CBP ---2 N5 A/ICE MAN 2 222

CBP ---2 Q2 EICAS DCU 1 CH A 222

CBP ---2 Q3 EICAS DCU 1 CH B 222

CBP ---2 Q4 EICAS DCU 2 CH A 222

CBP ---2 Q5 EICAS DCU 2 CH B 222

CBP ---3 B1 B/LEAK CONT L 221

CBP ---3 B2 B/LEAK CONT R 221

CBP ---4 B2 BLEED LEAK TEST 222

CBP ---4 B4 A/ICE MAN 1 222

CBP ---4 C10 EICAS DCU 1 CH A 222

CBP ---4 C11 EICAS DCU 1 CH B 222

CBP ---5 A6 DCU 2/3 311

(4) On the left side, remove the passenger seats from FS349.00 to FS424.00

(Refer to AMM 25---21---01---000---801).

(5) On the left side, remove the floor covering between the FS349.00 to FS424.00

(Refer to AMM 25---25---01---000---801).

(6) Remove the inboard floor panels (241CLF and 251CLF)

(Refer to AMM 53---01---01---000---802).

(7) Remove the left forward wing ---to ---fuselage fairing 191BB

(Refer to AMM 53---82---01---000---803).

(8) Open the main avionics ---compartment door.

(9) Remove DCU 1 (Refer to AMM 31---41---04---000---801).
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For Aircraft with the Global Positioning System (GPS) Option (CR34 ---352 or

CR34 ---350)

(10) Remove the Global Positioning System Sensor Unit (GPSSU 1) (Refer to AMM

34---58---01---000---801).

For Aircraft with the Attitude and Heading Reference System (AHRS) Option

(TS34 ---320)

(11) Remove the Attitude and Heading Computer (AHC 1)

(Refer to AMM 34---21---01---000---801).
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K. Procedure

NOTE: Use kit 601R30---031K4 to do PART D.

Refer to Figure 5, sheet 6.

(1) At FS409+128, disconnect connector P423 from receptacle J423.

Refer to Figure 5, View N.

(2) Near FS409+20, disconnect the connectors that follow:

(a) Disconnect P197 from J197

(b) Disconnect P192 from J192

(c) Disconnect P194 from J194

(d) Disconnect P196 from J196

Refer to Figure 5, sheets 6, 7, and Figure 10.

(3) In the main avionics ---compartment, between FS409+20 and FS409+128,

change the location of the wire that follows:

WIRE FROM TO

(PRE ---MOD)

TO

(POST ---MOD)

TERMINAL

1HA2G22 P124---93 J423---S P595---11 M39029/56---348

(a) Remove the wire from receptacle J423 (Refer to ESPM 20---17---10).

(b) Cut the wire to the correct length.

(c) Put the wires for connector P595 through identification sleeve

”P595/J595” and backshell P/N 450HA005NF11. Do not apply heat to

the identification sleeve at this time.

(d) Remove the insulation from the wire ends (Refer to ESPM 20---11---00).

(e) Crimp the applicable terminals on the wires (Refer to ESPM 20---20---00).

(f) Install the wires in the connectors (Refer to ESPM 20---17---10).

(g) Do a continuity check of the installed wires (Refer to ESPM 20---12---01).
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(4) Between FS409+20 and FS409+128, install and connect the wires that follow:

.

WIRE FROM TERMINAL TO TERMINAL W

1HA2L22 J423---J M39029/56---351 P595---Stow TC4001 8

1HA2R22 J423---K M39029/56---351 P594---Stow TC4001 9

1HA51L22 J423---L M39029/56---351 P594---8 M39029/56---348 9

1HA51E22 J423---d M39029/56---351 P595---8 M39029/56---348 8

1HA2KK22 J423---S M39029/56---351 P595---6 M39029/56---348 8

(a) If necessary, remove and replace clamps and/or cable ties to help the

wiring installation. If necessary, replace the clamp to get the correct fit

around the wires.

(b) If necessary, use a minimum of three turns of fiberglass tape to prevent

damage to the harness.

(c) Install the wires along the applicable wire harness

(Refer to ESPM 20---12---00).

(d) Make sure that you obey the wire separation “W” code.

(e) Put the wires for connector P594 through identification sleeve

”P594/J594” and backshell P/N 450HA005NF11. Do not apply heat to

the identification sleeve at this time.

(f) Put the wires for connector P595 through identification sleeve

”P595/J595” and backshell P/N 450HA005NF11. Do not apply heat to

the identification sleeve at this time.

(g) Install the end cap on the applicable wires (Refer to ESPM 20---17---10).

(h) Fold back and stow the applicable wires (Refer to ESPM 20---17---10).

(i) Remove the insulation from the applicable wire ends

(Refer to ESPM 20---11---00).

(j) Crimp the applicable terminals on the wires (Refer to ESPM 20---20---00).
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(k) Install the applicable wires in the connectors

(Refer to ESPM 20---17---10).

(l) Do a continuity check of the installed wires

(Refer to ESPM 20---12---01).

(5) At FS409+128, connect connector P423 to receptacle J423.

(6) Between FS384.00 and FS400.00, install and connect the wires that follow:

.

WIRE FROM END CAP TO TERMINAL W

2HA51L22 P595---Stow TC4001 1P1WA ---B---11A B0802050---010 8

1HA51A22 P595---Stow TC4001 1P1WA ---A ---11A B0802050---010 8

(a) If necessary, remove and replace clamps and/or cable ties to help the

wiring installation. If necessary, replace the clamp to get the correct fit

around the wires.

(b) If necessary, use a minimum of three turns of fiberglass tape to prevent

damage to the harness.

(c) Install the wires along the applicable wire harness

(Refer to ESPM 20---12---00).

(d) Make sure that you obey the wire separation “W” code.

(e) Remove the insulation from the wires (Refer to ESPM 20---11---00).

(f) Install the applicable terminals and end caps on the wires

(Refer to ESPM 20---20---00).

(g) Install the wires at the locations given.

(Refer to ESPM 20---17---10).

(h) Fold back and stow the wires (Refer to ESPM 20---17---10).
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(7) Between FS400.00 and FS409.00+20, install and connect the wires that

follow:

.

WIRE FROM TERMINAL TO TERMINAL W

2HA2R22 P192---H M39029/57---357 P594---Stow TC4001 9

2HA51F22 P197---CC M39029/58---363 P595---7 M39029/56---348 8

2HA2M22 P197---BB M39029/58---363 P595---Stow TC4001 8

2HA51Q22 P192---J M39029/57---357 P594---7 M39029/56---348 9

2HA2KK22 P192--- r M39029/57---357 P594---6 M39029/56---348 9

2HA51B22 P194---27 M39029/58---360 P594---Stow TC4001 9

1HA54B22 P196---87 M39029/58---360 P594---Stow TC4001 9

2HA52A22 P194---26 M39029/58---360 P594---11 M39029/56---348 9

(a) If necessary, remove and replace clamps and/or cable ties to help the

wiring installation. If necessary, replace the clamp to get the correct fit

around the wires.

(b) If necessary, use a minimum of three turns of fiberglass tape to prevent

damage to the harness.

(c) Install the wires along the applicable wire harness

(Refer to ESPM 20---12---00).

(d) Make sure that you obey the wire separation “W” code.

(e) Remove the insulation from the wires (Refer to ESPM 20---11---00).

(f) Install the applicable terminals or end caps on the wires

(Refer to ESPM 20---20---00).

(g) Put the wires for connector P594 through identification sleeve

“P594/J594” and backshell P/N 450HA005NF11. Do not apply heat to

the identification sleeve at this time.

(h) Put the wires for connector P595 through the identification sleeve

”P595/J595” and backshell P/N 450HA005NF11. Do not apply heat to

the identification sleeve at this time.
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(i) Install the wires in the connectors (Refer to ESPM 20---17---10).

(j) Fold back and stow the applicable wires (Refer to ESPM 20---17---10).

(k) Do a continuity check of the installed wires (Refer to ESPM 20---12---01).

WARNING: DO NOT TOUCH THE HEAT GUN REFLECTOR WHEN YOU HEAT THE

IDENTIFICATION SLEEVE. YOU CAN GET BURNED.

(8) With a heat gun, apply heat to the identification sleeve on connector P594 and

P595.

(9) Install an unwired terminal P/N M39029/56---348 and sealing plug

P/N MS27488---22 in the empty holes of connectors P594 and P595

(Refer to ESPM 20---20---00).

For Aircraft with the third DCU option (CR31 ---001 or CR31 ---310)

Refer to Figure 5, sheet 7, View N.

(10) Near FS409+20, disconnect the connector P193 from J193

Refer to Figure 5 sheets 6 and 7 and Figure 10.

(11) Between FS400 and FS409+20, install and connect the wires that follow:

.

WIRE FROM END CAP TO TERMINAL W

1HA52B22 P594---Stow TC4001 P193---47 M39029/58---360 9

1HA53B22 P595---Stow TC4001 P196---90 M39029/58---360 9

(a) If necessary, remove and replace clamps and/or cable ties to help the

wiring installation. If necessary, replace the clamp to get the correct fit

around the wires.

(b) If necessary, use a minimum of three turns of fiberglass tape to prevent

damage to the harness.

(c) Install the wires along the applicable harness

(Refer to ESPM 20---12---00).

(d) Make sure that you obey the wire separation “W” code.
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(e) Remove the insulation from the wire ends (Refer to ESPM 20---11---00).

(f) Install the applicable terminal or end caps on the wires

(Refer to ESPM 20---20---00).

(g) Install the wires in the connectors

(Refer to ESPM 20---17---10).

(h) Fold back and stow the wires (Refer to ESPM 20---17---10).

(12) Near FS409+20, connect the connector P193 to receptacle J193.

For all Aircraft

Refer to Figure 5, sheet 7, View N.

(13) Near FS409+20, connect the connectors that follow:

(a) P197 to J197

(b) P192 to J192

(c) P194 to J194

(d) P196 to J196

(14) At FS409+128, connect connector P423 to receptacle J423.

Refer to Figure 8, sheet 1.

(15) In the main avionics ---compartment, between FS394.00 and FS409.00, make

marks on the inboard avionic support ---structure to install the wing anti---ice

box as follows:

(a) With an indelible pen, make a mark at 5.59 in. (142.0 mm) aft of the

forward edge of the avionic support structure and at 1.37 in. (34.8 mm)

outboard of the inboard edge avionic support structure.

(b) With an indelible pen, make a mark at 4.24 in. (107.7 mm) and (6.94 in.

(176.8 mm) aft of the forward edge of the avionic support structure and

at 0.48 in. (12.2 mm) outboard of the inboard edge avionic support

structure.
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For Aircraft that have a GPS tray

(16) Temporarily put the wing anti---ice box on the inboard avionic

support ---structure and align the mounting holes with the three marks.

(17) If the wing anti---ice box touches the GPS 1 tray, move the GPS 1 tray forward

as follows:

For Aircraft that have GPS tray 601R51741 or 601R720808

(a) Remove GPS 1 tray with the four screws (13) and washers (11)

(Refer to Figure 8, view E).

(b) Discard screws (13) and washers (11).

For Aircraft that have GPS tray 601R51655

(c) Remove GPS 1 tray with the four screws (12), (13), washers (11)

(Refer to Figure 8, view E).

(d) Discard screws (12), (13) and washers (11).

For Aircraft that have a GPS tray

(e) Remove and discard the four nutplates (14) to the avionic support

structures.(Refer to Figure 8, sheet 2, view A and D).

(f) Do countersinks and plug the holes with the rivets (5) and (6) on the

avionic support structure in the nutplate holes.

(g) With an indelible pen, make a line at 0.51 in. (12.9 mm) inboard of the

outboard edge of the inboard avionic support structures.

(h) Temporarily put the wing anti---ice box on the avionic support structure

and align the mounting holes with the three previous marks.

(i) Temporarily install the GPS 1 tray on the avionic support structures at a

minimum of 0.060 in. (1.52 mm) and a maximum of 0.545 in. (13.84 mm)

aft from the beam. Align the inboard holes of the GPS 1 tray with the line

made before.

(j) Make sure the GPS 1 tray does not touch the wing anti---ice box.

(k) Use the GPS 1 tray as a template to drill four pilot holes in the avionic

support structures.
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(l) Make sure the pilot holes are away from the plugged holes.

(m) Drill four holes on the avionic support structures to a diameter of 0.204

in. (5.18 mm).

(n) Install the four nutplates (7) with the eight rivets (8) on the avionic

support structures (Refer to SRM 51---45---00).

(o) Make sure the nutplates (7) are at 90 degrees from the initial

installations.

For Aircraft that have GPS tray 601R51741 or 601R720808

(p) Install the GPS 1 tray with the four screws (13) and washers (11) (Refer

to Figure 8, view E).

For Aircraft that have GPS tray 601R51655

(q) Install the GPS 1 tray with the four screws (12), (13) and two washers

(11) (Refer to Figure 8, view E).

For all Aircraft

Refer to Figure 8, sheets 1.

(18) Drill three holes in the inboard avionic support ---structure as follows:

(a) Drill one hole to a diameter of 0.256 to 0.263 in. (6.50 to 6.68 mm) at

5.59 in. (142.0 mm) aft of the forward edge of the avionic support

structure and at 1.37 in. (34.8 mm) outboard of the inboard edge avionic

support structure.

(b) Drill two holes to a diameter of 0.256 to 0.263 in. (6.50 to 6.68 mm) at

4.24 in. (107.7 mm) and 6.94 in. (176.8 mm) aft of the forward edge of

the avionic support structure and at 0.48 in. (12.2 mm) outboard of the

inboard edge avionic support structure.

(c) Remove burrs and sharp edges.

(d) Apply chemical conversion coating to the bare metal areas

(Refer to SRM 51---21---11).

(e) Apply primer to the area (Refer to SRM 51---25---06).

Refer to Figure 8, sheets 1, and 3.

(19) In the main avionics ---compartment, between FS394 and FS409, install the

WING A/ICE box assembly (1) on the avionic support structure as follows:

(a) Prepare the surface for electrical bonding as shown in View C

(Refer to AMM 51---80---00---100---802).

(b) Install the WING A/ICE box assembly (1) on the avionic support structure

with the screws (2) and washers (3).
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(c) Make sure that the resistance between the WING A/ICE box assembly

(1) and the avionic support structure is satisfactory.

(Refer to AMM 51---80---00---760---802).

(d) Connect to the WING A/ICE box assembly (1), the connectors that

follow:

1 P594 to J594.

2 P595 to J595.

(e) Install the decal (4) on the avionic support structure (Refer to AMM

11---30---00---400---801).

(f) Apply a layer of clear polyurethane topcoat over the decal

(Refer to SRM 51---25---16).

Refer to Figure 8, sheet 3.

(20) Open and install the lockrings (9) on the circuit breakers, of the WING A/ICE

box assembly (1), that follow (Refer to ESPM 20---23---00):

CB ON THE WAI

BOX

NAME

1CB2HA RHS OUTBOARD 1

2CB2HA RHS OUTBOARD 2

1CB1HA LHS OUTBOARD 1

2CB1HA LHS OUTBOARD 2

(21) Install the INOP label (10) on the front of the WING A/ICE box assembly (1).
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L. Job Close ---Out

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

For Aircraft with the Attitude and Heading Reference System (AHRS) Option

(TS34 ---320)

(2) If removed, install the AHC 1 (Refer to AMM 34---21---01---400---801).

For Aircraft with the Global Positioning System (GPS) Option (CR34 ---352 or

CR34 ---350)

(3) If removed, install the GPSSU 1 (Refer to AMM 34---58---01---400---801).

For all Aircraft

(4) Install the DCU 1 (Refer to AMM 31---41---04---400---801).

(5) Install the left forward wing ---to ---fuselage fairing 191BB

(Refer to AMM 53---82---01---400---803).

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

For Aircraft with the Global Positioning System (GPS) Option (CR34 ---352 or

CR34 ---350)

CB PANEL CB NO. NAME ZONE

CBP ---1 H13 GPS 1 221

For all Aircraft with the Attitude and Heading Reference System (AHRS) Option

(TS34 ---320)

CB PANEL CB NO. NAME ZONE

CBP ---2 H14 AHRS 2 222

CBP ---2 H15 AHRS FAN 2 222

CBP ---4 D8 AHRS 1 222

CBP ---4 D9 AHRS FAN 1 222
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For Aircraft 7003 thru 7609 with the Attitude and Heading Reference System

(AHRS) Option (TS34 ---320)

CB PANEL CB NO. NAME ZONE

CBP ---5 A8 ATT/HDG 1 311

CBP ---5 A9 ATT/HDG 2 311

CBP ---5 A7 STBY PWR CONT 311

For Aircraft 7610 thru 7990 and 8000 thru 8101 with the Attitude and Heading

Reference System (AHRS) Option (TS34 ---320)

CB PANEL CB NO. NAME ZONE

CBP ---1 N4 ATT/HDG 1 221

CBP ---1 N5 ATT/HDG 2 221

For all Aircraft

CB PANEL CB NO. NAME ZONE

CBP ---1 F10 14th ST B/AIR SOV L 221

CBP ---1 G2 A/ICE AUTO 1 221

CBP ---1 G9 WING INSP 221

CBP ---1 M2 ENG IGN A 221

CBP ---1 M3 ENG IGN B 221

CBP ---2 F10 14th ST B/AIR SOV R 221

CBP ---2 G2 A/ICE AUTO 2 222

CBP ---2 N5 A/ICE MAN 2 222

CBP ---2 Q2 EICAS DCU 1 CH A 222

CBP ---2 Q3 EICAS DCU 1 CH B 222

CBP ---2 Q4 EICAS DCU 2 CH A 222

CBP ---2 Q5 EICAS DCU 2 CH B 222

CBP ---3 B1 B/LEAK CONT L 221
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CB PANEL ZONE CB NO. NAME

CBP ---3 B2 B/LEAK CONT R 221

CBP ---4 B2 BLEED LEAK TEST 222

CBP ---4 B4 A/ICE MAN 1 222

CBP ---4 C10 EICAS DCU 1 CH A 222

CBP ---4 C11 EICAS DCU 1 CH B 222

CBP ---5 A6 DCU 2/3 311

(7) Do the connector integrity after a disconnect and re---connection

(Refer to AMM 20---10---00---910---803).

For Aircraft with the Global Positioning System (GPS) Option (CR34 ---352)

(8) Do the operational test of the GPSSU (Refer to AMM 34---58---01---700---801)

For Aircraft with the Attitude and Heading Reference System (AHRS) Option

(TS34 ---320)

(9) Do the operational test of the AHC (Refer to AMM 34---21---01---710---801)

For all Aircraft

(10) Do the operational test of the DCU (Refer to AMM 31---41---04---710---801)

(11) Install the floor panels (241CLF and 251CLF)

(Refer to AMM 53---01---01---400---802).

(12) Install the floor covering between the FS349.00 to FS424.00

(Refer to AMM 25---25---01---400---801).

(13) Install passenger seats from FS349.00 to FS424.00

(Refer to AMM 25---21---01---400---801).

(14) Close the main avionics ---compartment door.

(15) When PART D of 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

601R---30---031, Revision D, PART D, incorporated.”

(16) When PART D of this service bulletin is completed, make this entry in the

applicable logbook(s): “ Service Bulletin 601R---30---031, Revision D, Ice and

Rain Protection --- Wing Anti---Icing System --- Installation of Low Heat

Detection---Switches on the Leading Edge, PART D, incorporated.”
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

PART E --- Installation of the wires for the Wing A/ICE box assembly on the Right Side of

the Main Avionics ---Compartment

M. Job Set ---Up

Reference Information

REFERENCE DESIGNATION

AMM 11---30---00---400---801 Installation of the Adhesive---Backed Label

AMM 20---10---00---910---803 Connector Integrity After a Disconnect and

Re---connection

AMM 20---21---00---910---801 Torque Procedures for Threaded Fasteners

AMM 24---00---00---861---802 Remove Electrical Power to the Aircraft

AMM 24---00---00---910---801 Electrical/Electronic Safety Precautions

AMM 25---21---01---000---801 Removal of the Passenger Seat

AMM 25---21---01---400---801 Installation of the Passenger Seat

AMM 25---25---01---000---801 Removal of the Textile Floor Covering

AMM 25---25---01---400---801 Installation of the Textile Floor Covering

AMM 31---41---04---000---801 Removal of the DCU

AMM 31---41---04---400---801 Installation of the DCU

AMM 31---41---04---710---801 Operational Test of the DCU

AMM 51---80---00---100---802 Surface Preparation for Electrical Bonding

AMM 51---80---00---760---802 Electrical Bonding Resistance Values

AMM 53---01---01---000---802 Removal of the Passenger Compartment Floor

Panels

AMM 53---01---01---400---802 Installation of the Passenger Compartment

Floor Panels

AMM 53---82---01---000---802 Removal of the Right Forward Wing ---to ---Fuselage Fairing

AMM 53---82---01---400---802 Installation of the Right Forward Wing ---to ---Fuselage Fairing
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

REFERENCE DESIGNATION

ESPM 20---11---00 Wire Stripping and Wire/Cable Damage Repair

Maintenance Practices

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

ESPM 20---23---00 Circuit Breakers --- Removal/Installation

SRM 51---21---11 Corrosion Prevention Procedures

SRM 51---21---16 Finish Codes

Tolerance Information

Linear Tolerances Angular Tolerance

0.XX in. (0.X mm) 0.X in. (X mm)

/ 0° 30” +/ --- 0.03 in. +/--- 0.1 in. +/---0° 30”

+/ --- 0.8 mm +/ --- 2 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).
SERVICE BULLETIN 601R---30 ---031

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(2) Open, safety, and tag the circuit breakers that follow:

For Aircraft with the third DCU option (CR31 ---310 or CR31 ---001)

CB PANEL CB NO. NAME ZONE

CBP ---2 K6 EICAS DCU 3 CH A 222

CBP ---2 K7 EICAS DCU 3 CH B 222

For all Aircraft

CB PANEL CB NO. NAME ZONE

CBP ---1 F10 14th ST B/AIR SOV L 221

CBP ---1 G2 A/ICE AUTO 1 221

CBP ---1 G9 WING INSP 221

CBP ---1 M2 ENG IGN A 221

CBP ---1 M3 ENG IGN B 221

CBP ---2 F10 14th ST B/AIR SOV R 221

CBP ---2 G2 A/ICE AUTO 2 222

CBP ---2 N5 A/ICE MAN 2 222

CBP ---2 Q2 EICAS DCU 1 CH A 222

CBP ---2 Q3 EICAS DCU 1 CH B 222

CBP ---2 Q4 EICAS DCU 2 CH A 222

CBP ---2 Q5 EICAS DCU 2 CH B 222

CBP ---3 B1 B/LEAK CONT L 221

CBP ---3 B2 B/LEAK CONT R 221

CBP ---4 B2 BLEED LEAK TEST 222

CBP ---4 B4 A/ICE MAN 1 222

CBP ---4 C10 EICAS DCU 1 CH A 222

CBP ---4 C11 EICAS DCU 1 CH B 222

CBP ---5 A6 DCU 2/3 311
SERVICE BULLETIN 601R---30 ---031

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(3) On the right side, remove the passenger seats from FS349.00 to FS424.00

(Refer to AMM 25---21---01---000---801).

(4) On the right side, remove the floor covering between the FS349.00 to

FS424.00

(Refer to AMM 25---25---01---000---801).

(5) Remove the floor panels (242CRF and 252CRF)

(Refer to AMM 53---01---01---000---802).

(6) Remove the right forward wing ---to ---fuselage fairing 192BB

(Refer to AMM 53---82---01---000---802).

(7) Open the main avionics ---compartment door.

(8) Remove DCU 2 (Refer to AMM 31---41---04---000---801).

For Aircraft with the third DCU option (CR31 ---001 or CR31 ---310)

(9) Remove DCU 3

(Refer to AMM 31---41---04---000---801).
SERVICE BULLETIN 601R---30 ---031

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N. Procedure

NOTE: Use kit 601R30---031K5 to do PART E.

Refer to Figure 5, sheet 6.

(1) At FS409+128, disconnect the connector P422 from receptacle J422.

Refer to Figure 5, sheet 7, View N.

(2) Near FS409+20, disconnect the connectors that follow:

(a) Disconnect P197 from J197

(b) Disconnect P192 from J192

(c) Disconnect P194 from J194

(d) Disconnect P196 from J196

Refer to Figure 5, sheets 6, 7, and Figure 11.

(3) Between FS409+20 and FS409+128, change the location of the wire that

follows:

WIRE FROM TO

(PRE ---MOD)

TO

(POST ---MOD)

TERMINAL

2HA2G22 P139---88 J422--- r J194---26 M39029/57---354

(a) Remove the wire from receptacle J422 (Refer to ESPM 20---17---10).

(b) Cut the wire to the correct length.

(c) Remove the insulation from the wire end

(Refer to ESPM 20---11---00).

(d) Crimp the applicable terminal on the wire

(Refer to ESPM 20---20---00).

(e) Install the wire in connector J194 (Refer to ESPM 20---17---10).

(f) Do a continuity check of the installed wire (Refer to ESPM 20---12---01).
SERVICE BULLETIN 601R---30 ---031

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(4) Between FS409+20 and FS409+128, install and connect the wires that follow:

.

WIRE FROM TERMINAL TO TERMINAL W

2HA2N22 J422---J M39029/56---351 J197---BB M39029/57---357 8

2HA2S22 J422---K M39029/56---351 J192---H M39029/58---363 9

2HA51R22 J422---L M39029/56---351 J192---J M39029/58---363 9

2HA51G22 J422---d M39029/56---351 J197---CC M39029/57---357 8

2HA2LL22 J422--- r M39029/56---351 J192--- r M39029/58---363 9

(a) If necessary, remove and replace clamps and/or cable ties to help the

wiring installation. If necessary, replace the clamp to get the correct fit

around the wires.

(b) If necessary, use a minimum of three turns of fiberglass tape to prevent

damage to the harness.

(c) Install the wires along the applicable wire harness

(Refer to ESPM 20---12---00).

(d) Make sure that you obey the wire separation “W” code.

(e) Remove the insulation from the wires (Refer to ESPM 20---11---00).

(f) Install the applicable terminal on the wires (Refer to ESPM 20---20---00).

(g) Install the wires at the locations given (Refer to ESPM 20---17---10).

(h) Do a continuity check of the installed wires (Refer to ESPM 20---17---10).

(5) Between FS374 and FS409+20, install and connect the wires that follow:

.

WIRE FROM TERMINAL TO TERMINAL W

2HA51A22 J194---27 M39029/57---354 2P1WA ---B---11A B0802050---010 9

1HA54A22 J196---87 M39029/57---354 2P1WA ---A ---11A B0802050---010 9
SERVICE BULLETIN 601R---30 ---031

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(a) If necessary, remove and replace clamps and/or cable ties to help the

wiring installation. If necessary, replace the clamp to get the correct fit

around the wires.

(b) If necessary, use a minimum of three turns of fiberglass tape to prevent

damage to the harness.

(c) Install the wires along the applicable wire harness

(Refer to ESPM 20---12---00).

(d) Make sure that you obey the wire separation “W” code.

(e) Remove the insulation from the wires (Refer to ESPM 20---11---00).

(f) Install the applicable terminal on the wires (Refer to ESPM 20---20---00).

(g) Install the wires at the locations given (Refer to ESPM 20---17---10).

(h) Do a continuity check of the installed wires (Refer to ESPM 20---12---01).

(6) Near FS409+20, connect the connectors that follow:

(a) P197 to J197

(b) P192 to J192

(c) P194 to J194

(d) P196 to J196

For Aircraft with the third DCU option (CR31 ---001 or CR31 ---310)

Refer to Figure 5, sheet 7, View N.

(7) Near FS409+20, disconnect connector P193 from receptacle J193.

Refer to Figure 5 and Figure 11.

(8) Between FS386 and FS409+20, install and connect the wires that follow:

.

WIRE FROM TERMINAL TO TERMINAL W

1HA52A22 J193---47 M39029/57---354 P1WH---B---11A B0802050---010 9
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WIRE FROM TERMINAL TO TERMINAL W

1HA53A22 J196---90 M39029/57---354 P1WH---A ---11A B0802050---010 9

(a) If necessary, remove and replace clamps and/or cable ties to help the

wiring installation. If necessary, replace the clamp to get the correct fit

around the wires.

(b) If necessary, use a minimum of three turns of fiberglass tape to prevent

damage to the harness.

(c) Install the wires along the applicable harness

(Refer to ESPM 20---12---00).

(d) Make sure that you obey the wire separation “W” code.

(e) Remove the insulation from the wire ends (Refer to ESPM 20---11---00).

(f) Install the applicable terminal on the wires (Refer to ESPM 20---20---00).

(g) Install the wires in the connectors (Refer to ESPM 20---17---10).

(h) Do a continuity check of the installed wires (Refer to ESPM 20---12---01).

(9) Near FS409+20, connect connector P193 to J193.

For all Aircraft

Refer to Figure 5, sheet 7, View N.

(10) Near FS409+20, connect the connectors that follow:

(a) P197 to J197

(b) P192 to J192

(c) P194 to J194

(d) P196 to J196

Refer to Figure 5 sheet 6.

(11) At FS409+128, connect connector P422 to receptacle J422.
SERVICE BULLETIN 601R---30 ---031

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O. Job Close ---Out

For Aircraft with the third DCU option (CR31 ---001 or CR31 ---310)

(1) Install DCU 3 (Refer to AMM 31---41---04---400---801).

For all Aircraft

(2) Install DCU 2 (Refer to AMM 31---41---04---400---801).

(3) Install the right forward wing ---to ---fuselage fairing 192BB

(Refer to AMM 53---82---01---400---802).

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

For Aircraft with the third DCU option (CR31 ---310 or CR31 ---001)

CB PANEL CB NO. NAME ZONE

CBP ---2 K6 EICAS DCU 3 CH A 222

CBP ---2 K7 EICAS DCU 3 CH B 222

For all Aircraft

CB PANEL CB NO. NAME ZONE

CBP ---1 F10 14th ST B/AIR SOV L 221

CBP ---1 G2 A/ICE AUTO 1 221

CBP ---1 G9 WING INSP 221

CBP ---1 M2 ENG IGN A 221

CBP ---1 M3 ENG IGN B 221

CBP ---2 F10 14th ST B/AIR SOV R 221

CBP ---2 G2 A/ICE AUTO 2 222

CBP ---2 N5 A/ICE MAN 2 222

CBP ---2 Q2 EICAS DCU 1 CH A 222

CBP ---2 Q3 EICAS DCU 1 CH B 222

CBP ---2 Q4 EICAS DCU 2 CH A 222

CBP ---2 Q5 EICAS DCU 2 CH B 222
SERVICE BULLETIN 601R---30 ---031

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CB PANEL ZONE CB NO. NAME

CBP ---3 B1 B/LEAK CONT L 221

CBP ---3 B2 B/LEAK CONT R 221

CBP ---4 B2 BLEED LEAK TEST 222

CBP ---4 B4 A/ICE MAN 1 222

CBP ---4 C10 EICAS DCU 1 CH A 222

CBP ---4 C11 EICAS DCU 1 CH B 222

CBP ---5 A6 DCU 2/3 311

(5) Do the connector integrity after a disconnect and re---connection

(Refer to AMM 20---10---00---910---803).

(6) Do the operational test of the DCU

(Refer to AMM 31---41---04---710---801).

For all Aircraft

(7) Install the inboard floor panels (242CRF, 252CRF)

(Refer to AMM 53---01---01---400---802).

(8) Install the floor covering between the FS349.00 to FS424.00

(Refer to AMM 25---25---01---400---801).

(9) Install passenger seats from FS349.00 to FS424.00

(Refer to AMM 25---21---01---400---801).

(10) Close the main avionics ---compartment door.

(11) When PART E of 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

601R---30---031, Revision D, PART E, incorporated.”

(12) When PART E of this service bulletin is completed, make this entry in the

applicable logbook(s): “ Service Bulletin 601R---30---031, Revision D, Ice and

Rain Protection --- Wing Anti---Icing System --- Installation of Low Heat

Detection---Switches on the Leading Edge, PART E, incorporated.”
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

For Aircraft that have incorporated PART A, and PART C thru PART E of Revision A or

later revision of this service bulletin

PART F --- Activation of the Low Heat Detection ---Switches

P. Job Set ---Up

Reference Information

REFERENCE DESIGNATION

AMM 11---30---00---000---801 Removal of Adhesive---Backed Label

AMM 24---00---00---861---802 Remove Electrical Power to the Aircraft

AMM 24---00---00---910---801 Electrical/Electronic Safety Precautions

AMM 30---12---15---710---801 Operational Test of the Outboard Low Heat

Switches

ESPM 20---11---00 Wire Stripping and Wire/Cable Damage Repair

Maintenance Practices

ESPM 20---17---10 Electrical Connectors --- Maintenance Practices

ESPM 20---20---00 Terminal Lugs --- Removal/Installation

ESPM 20---23---00 Circuit Breakers --- Removal/Installation

(1) Obey all the electrical/electronic safety precautions

(Refer to AMM 24---00---00---910---801).

(2) Open the main avionics ---compartment door.

(3) Remove electrical power to the aircraft

(Refer to AMM 24---00---00---861---802).

(4) Open, safety, and tag the circuit breakers that follow:

For Aircraft with the third DCU option (CR31 ---310 or CR31 ---001)

CB PANEL CB NO. NAME ZONE

CBP ---2 K6 EICAS DCU 3 CH A 222

CBP ---2 K7 EICAS DCU 3 CH B 222
SERVICE BULLETIN 601R---30 ---031

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For all Aircraft

CB PANEL CB NO. NAME ZONE

CBP ---2 N5 A/ICE MAN 2 222

CBP ---2 Q2 EICAS DCU 1 CH A 222

CBP ---2 Q3 EICAS DCU 1 CH B 222

CBP ---2 Q4 EICAS DCU 2 CH A 222

CBP ---2 Q5 EICAS DCU 2 CH B 222

CBP ---4 B4 A/ICE MAN 1 222

CBP ---4 C10 EICAS DCU 1 CH A 222

CBP ---4 C11 EICAS DCU 1 CH B 222

CBP ---5 A6 DCU 2/3 311
SERVICE BULLETIN 601R---30 ---031

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Q. Procedure

NOTE: Use kit 601R30---031K6 to do PART F

Refer to Figure 5, sheet 6, and Figure 10.

(1) In the main avionics ---compartment, at FS400.00, unstow and connect the

wires that follow:

WIRE FROM TO TERMINAL W

1HA2L22 J423---J P595---4 M39029/56---348 8

2HA2M22 P197---BB P595---5 M39029/56---348 8

2HA51L22 1P1WA ---B---11A P595---12 M39029/56---348 8

1HA51A22 1P1WA ---A ---11A P595---13 M39029/56---348 8

1HA2R22 J423---K P594---4 M39029/56---348 9

2HA2R22 P192---H P594---5 M39029/56---348 9

2HA51B22 P194---27 P594---12 M39029/56---348 9

1HA54B22 P196---87 P594---13 M39029/56---348 9

For Aircraft with the third DCU option (CR31 ---001 or CR31 ---310)

WIRE FROM TO TERMINAL W

1HA52B22 P193---47 P594---3 M39029/56---348 9

1HA53B22 P196---90 P595---3 M39029/56---348 9

For all Aircraft

(a) Disconnect connectors P594 and P595 from the WING A/ICE box

assembly (1).

(b) Remove the insulation from the wires (Refer to ESPM 20---11---00).

(c) Install the applicable terminals on the wires (Refer to ESPM 20---20---00).

(d) Install the wires at the locations given (Refer to ESPM 20---17---10).

(e) Do a continuity check of the installed wires (Refer to ESPM 20---17---10).
SERVICE BULLETIN 601R---30 ---031

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(f) Connect connectors P594 and P595 to the WING A/ICE box assembly

(1).

Refer to Figure 8, sheet 3.

(2) Remove the lockrings (9) and close the circuit breakers, of the WING A/ICE

box assembly (1), that follows (Refer to ESPM 20---23---00):

CB ON THE WAI

BOX

NAME

1CB2HA RHS OUTBOARD 1

2CB2HA RHS OUTBOARD 2

1CB1HA LHS OUTBOARD 1

2CB1HA LHS OUTBOARD 2

(3) Remove the INOP label (10) from the WING A/ICE box assembly (1)

(Refer to AMM 11---30---00---000---801).
SERVICE BULLETIN 601R---30 ---031

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R. 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:

For Aircraft with the third DCU option (CR31 ---310 or CR31 ---001)

CB PANEL CB NO. NAME ZONE

CBP ---2 K6 EICAS DCU 3 CH A 222

CBP ---2 K7 EICAS DCU 3 CH B 222

For all Aircraft

CB PANEL CB NO. NAME ZONE

CBP ---2 N5 A/ICE MAN 2 222

CBP ---2 Q2 EICAS DCU 1 CH A 222

CBP ---2 Q3 EICAS DCU 1 CH B 222

CBP ---2 Q4 EICAS DCU 2 CH A 222

CBP ---2 Q5 EICAS DCU 2 CH B 222

CBP ---4 B4 A/ICE MAN 1 222

CBP ---4 C10 EICAS DCU 1 CH A 222

CBP ---4 C11 EICAS DCU 1 CH B 222

CBP ---5 A6 DCU 2/3 311

(3) Do the operational test of the outboard low heat detection---switches

(Refer to AMM 30---12---15---710---801).

(4) Close the main avionics ---compartment door.

(5) When PART F of this service bulletin is completed, make this entry in the

applicable logbook(s): “ Service Bulletin 601R---30---031, Revision D, Ice and

Rain Protection --- Wing Anti---Icing System --- Installation of Low Heat

Detection---Switches on the Leading Edge, PART F, incorporated.”
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

Outboard Leading Edge locator

Figure 1 (sheet 1 of 4)

rsb601r30031_022.dg

WS350.35

WS386.35

1

1

1

1

1

1

A

SHROUD (REF)

2

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

A

5

Rivets to be removed.

NOTES

1

2 For aircraft that have configuration 2 leading

edge assembly (P/N 601R12310--1 and --2).

Ignore the identification that is on the

assembly. The leading edge P/N

601R12310--1 and --2 are of configuration 2.

5
SERVICE BULLETIN 601R---30 ---031

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Outboard Leading Edge locator

Figure 1 (Sheet 2 of 4)

A

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

NOTES

Ignore the identification that is on

the assembly. The leading edge

P/N 601R12062--3, --4, --5, --6, --7,

and --8 are of configuration 1

with flat shroud.

Ignore the identification that is on

the assembly. The leading edge

P/N 601R12310--1 and --2 are of

configuration 2 with the ”L” shroud.

CONFIGURATION 1

LEADING EDGES P/N

601R12062--3, --4,

--5, --6, --7 AND --8

D

D

CONFIGURATION 2

LEADING EDGES P/N

601R12310--1 AND 2

rsb601r30031_041.dg

WS350.35

WS386.35

D

4

5

4

5

FASTENER

(REF)

FASTENER

(REF)

”L” SHROUD

(REF)

FLAT SHROUD

(REF)
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

Outboard Leading Edge ---Locator

Figure 1 (sheet 3 of 4)

B

A

STA366.00 STA358.86 STA350.35 STA342.30

SHROUD

1

VIEW LOOKING FWD

3

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

ACCESS PANEL

(REF)

ACCESS PANEL

(REF)

rsb601r30031_033.dg

B 4

A

Ignore the identification that is on the assembly.

The leading edge P/N 601R12062--3, --4, --5, --6, --7

and --8 are of configuration 1.

NOTES

1 Rivets to be removed.

3 For aircraft that have configuration 1 leading edge

assembly (P/N 601R12062--3, --4, --5, --6, --7, and --8 ).

4
SERVICE BULLETIN 601R---30 ---031

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Outboard Leading Edge locator

Figure 1 (Sheet 4 of 4)

rsb601r30031_040.dg

C

LEGEND

1. Screw

ACCESS PANEL

(REF)

1

SHROUD (REF)

ACCESS PANEL

(REF)

1

2

4

ANGLES

(REF)

LEADING EDGE

(REF)

VIEW LOOKING UP

A 4

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

C

A

CONFIGURATION 1

LEADING EDGES P/N

601R12062--1 AND --3, --4, --5, --6, AND --7

4

NOTES

4 Ignore the identification that is on the assembly.

The leading edge P/N 601R12062--3, --4, --5, --6, --7

and --8 are of configuration 1.

2 Faying surface sealant area.
SERVICE BULLETIN 601R---30 ---031

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Leading Edge Modifications

Figure 2 (sheet 1 of 5)

rsb601r30031_013.dg, sd, 20/19/09

G

F

A

A

WS350.00

WS358.86

BLEED SWITCH

(REF)

WS366.00

B

D

SHROUD

(REF)

E

DOUBLER (REF)

Not installed on all aircraft.

NOTE

1

1

C

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE
SERVICE BULLETIN 601R---30 ---031

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Leading Edge Modifications

Figure 2 (sheet 2 of 5)

rsb601r30031_014.dg, sd, 20/12/09

2.09 in.

(53.1 mm)

VENT HOLE

(REF) 2.17 in.

(55.1 mm)

WS350.37

1S8HA

(2S8HA)

L/E SKIN 0.95 in.

(24.1 mm)

WS362.77

WS355.99

0.77 in.

(19.6 mm)

1.25 in.

(31.8 mm)

(REF)

B

0.120 in. (3.05 mm)

4 PLACES

DECAL

1S7HA

(2S7HA)

DECAL

1 DOUBLER (REF)

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

NOTES

1 Not installed on all aircraft.
SERVICE BULLETIN 601R---30 ---031

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Leading Edge Modifications

Figure 2 (Sheet 3 of 5)

rsb601r30031_039.dg, sd, 20/12/09

F

OUTBOARD LOWER

SHROUD (REF) ACCESS HOLE

(REF)

0.63 in.

(16.0 mm)

1.80 in.

(45.7 mm)

1.60 in.

(40.6 mm)

OUTBOARD UPPER

SHROUD (REF) WS363.00 TB7HA

(TB8HA)

TB1HA

(TB2HA)

TB5HA (TB6HA)

TB3HA

(TB4HA)

1.35 in.

(34.3 mm)

1.60 in.

(40.6 mm)

0.48 in.

(12.2 mm)

DECAL

DECAL

DECAL

DECAL

0.241 in. (6.12 mm)

0.246 in. (6.25 mm)

DIAMETER 0.241 in. (6.12 mm)

0.246 in. (6.25 mm)

DIAMETER

ACCESS HOLE

(REF)

OUTBOARD LOWER

SHROUD (REF)

6.24 in. (15.85 cm)

1.50 in.

(38.1 mm)

DIAMETER

0.75 in.

(19.05 mm)

0.83 in. DIAMETER

(21 mm)

WS363.00 WS352.70

0.25 in. (6.35 mm)

DIAMETER

12 PLACES

0.75 in.

(19.05 mm)

DIAMETER

1.79 in.

(45.5 mm)

0.83 in.

1.75 in. (21 mm)

(44.5 mm)

TYPICAL

1.75 in.

(44.5 mm)

TYPICAL

6

C 4

1.60 in.

(40.6 mm)

NOTES

4

6 Alternate location of terminals for configuration 2 leadingedges

For aircraft that have leading edge.assembly P/N 601R12310--1 and --2.

8 Drill four 0.241 in to 0.246 in (6.12 mm to 6.25 mm) holes within shaded area, similar to view C.

8 8 EXISTING HOLE FOR

BONDING JUMPER
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

Leading Edge Modifications

Figure 2 (sheet 4 of 5)

rsb601r30031_032.dg

TB5HA

(TB6HA)

0.241 in. to 0.246 in.

(6.12 mm to 6.25 mm)

DIAMETER (4 PLACES) 1.75 in.

(44.5 mm)

TYP

2.00 in.

(50.8 mm)

TB7HA

(TB8HA)

TB1HA

WS366.00 (TB2HA)

TB3HA

(TB4HA)

WS353.00

SHROUD

601R12062

REF

1.10 in.

(27.9 mm)

TYP

1.35 in.

(34.3 mm)

4.00 in.

(101.6 mm) 4.65 in.

(118.0 mm) D 5

0.25 in. (6.35 mm)

G

0.75 in.

(19.05 mm)

DIAMETER FS366.00

LOWER EDGING

REF

EDGING SHROUD

REF FS358.866 FS350.348

0.23 in.

(5.84 mm)

TYP

0.23 in.

(5.84 mm)

TYP

7.95 in. (20.19 cm)

0.95 in.

(24.1 mm)

REF

SHROUD

REF

EXISTING NUTPLATE

REF DIAMETER

(8 PLACES)

5 7

HOLE FOR BONDING

BONDING JUMPER

NOTE

5 For aircraft that have leading edge

assembly configuration 1.

Alternate location of terminals for

configuration 1 leading edges.

7

Drill four 0.241 in to 0.246 in (6.12 mm to 6.25 mm)

holes within shaded area, similar to view D.

9

9
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Leading Edge Modifications

Figure 2 (sheet 5 of 5)

rsb601r30031_025.dg

NOTES

2 Electrical bonding surface.

3 Thermal switch and bracket mounting area.

E

WS350.37

WS355.99 WS362.77

VENT HOLE

(REF)

DOUBLER (REF)

(NOT INSTALLED

ON ALL AIRCRAFT)

2 2 3 3

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE
SERVICE BULLETIN 601R---30 ---031

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Thermal Switch Modification

Figure 3

rsb601r30031_026.dg, gb, 02/02/09

0.50 0.25 in.

(12.70 6.40 mm)

THERMAL SWITCH

WIRES (REF)

1 3

LEGEND

1. Thermal Switch M2SL0920305--101.

2. Thermal Insulating Wire Cover 10 in. (254 mm).

3. Lacing Cord.

NOTE

Enamel dope for knot

holding (Glyptol) .

1

1

2

2
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Thermal Switch Installation

Figure 4 (sheet 1 of 4)

rsb601r30031_020.dg, sd, 20/12/09

A

C LEADING EDGE

(REF)

3

A

B

1

2

B

3

4

LEGEND

1. Nut MS21042L04.

2. Screw MS24693--S2.

3. Thermal switch and bracket.

4. Thermal compound.

5. Silicone (RTV--106).

C

LEADING EDGE

(REF)

THERMAL SWITCH

INSTALLATION

1S7HA

(2S7HA)

6. Thermal insulating cover E53690VW--1.

WS366.00

WS350.00

M2SL0920305--101.

7. Silicone (RTV--3145).

1

16. Lacing cord.

(2 PLACES)

(2 PLACES)

1S8HA

(2S8HA) 3

3

3

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

NOTES

1 Temperature sensing side of the thermal switch

The temperature sensitive side is specified

on the thermal switch as TEMP SIDE.

2 Enamel dope for knot holding (Glyptol).

3 For aircraft that have configuration 2

leading edge assembly

(P/N 601R12310--1 and --2)

LEADING EDGE

(REF)

B

5

16

7

6

2

(2 PLACES)

3
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Revision D, Feb 03/2010

Thermal Switch Installation

Figure 4 (sheet 2 of 4)

rsb601r30031_028.dg, sd, 20/12/09

A

C LEADING EDGE

(REF)

3

A

B

1

2

B

3

4

LEGEND

1. Nut MS21042L04.

2. Screw MS24693--S2.

3. Thermal switch and bracket.

4. Thermal compound.

5. Silicone (RTV--106).

C

LEADING EDGE

(REF)

THERMAL SWITCH

INSTALLATION

1S7HA

(2S7HA)

6. Thermal insulating cover E53690VW--1.

WS366.00

WS350.00

M2SL0920305--101.

7. Silicone (RTV--3145).

1

16. Lacing cord.

(2 PLACES)

(2 PLACES)

1S8HA

(2S8HA) 4

4

4

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

LEADING EDGE

(REF)

5

16

7

6

2

B

(2 PLACES)

4

NOTES

1 Temperature sensing side of the thermal switch

The temperature sensitive side is specified

on the thermal switch as TEMP SIDE.

2 Enamel dope for knot holding (Glyptol).

4 For aircraft that have configuration 1 leading edge

assembly (P/N 601R12062--3, --4, --5, --6, --7, and --8 ).
SERVICE BULLETIN 601R---30 ---031

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Thermal Switch Installation

Figure 4 (sheet 3 of 4)

rsb601r30031_015.dg, sd, 20/12/09

8. Screw NAS1801--06--12.

14

8

13

9

12

11

13

9

14

9

SHROUD

(REF)

B TYPICAL 4 PLACES

10

9. Washer NAS1149DN632J.

10. Terminal lug MS20659--101.

11. Shoulder washer SHW8266--T.

12. Washer NAS1515M06.

13. Lockwasher MS35338--41.

14. Nut MS25082--1.

15. Nipple terminal MS25171--1S.

15

9

LEGEND

WIRE FROM WIRING

HARNESS (REF)

A

16. Lacing cord.

10

WIRE FROM

THERMAL SWITCH

(REF)

16

TB3HA

(TB4HA)

B

TB7HA

(TB8HA)

WS350.00

WS366.00

TB1HA

(TB2HA)

TB5HA

(TB6HA)

1S8HA

(2S8HA)

1S7HA (2S7HA)

THERMAL SWITCH

A

NOTES

2 Enamel dope for knot holding (Glytol).

3 For aircraft that have configuration 2

leading edge assembly

(P/N 601R12310--1 and --2).

3

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

2
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Thermal Switch Installation

Figure 4 (sheet 4 of 4)

rsb601r30031_029.dg, sd, 20/12/09

8. Screw NAS1801--06--12.

14

8

13

9

12

11

13

9

14

9

SHROUD

(REF)

B TYPICAL 4 PLACES

10

9. Washer NAS1149DN632J.

10. Terminal lug MS20659--101.

11. Shoulder washer SHW8266--T.

12. Washer NAS1515M06.

13. Lockwasher MS35338--41.

14. Nut MS25082--1.

15. Nipple terminal MS25171--1S.

15

9

LEGEND

WIRE FROM WIRING

HARNESS (REF)

A

16. Lacing cord.

10

WIRE FROM

THERMAL SWITCH

(REF)

16

NOTES

2 Enamel dope for knot holding (Glytol).

2

A

WS366.00

WS350.00

1S7HA (2S7HA)

THERMAL SWITCH

1S8HA

(2S8HA)

TB7HA

(TB8HA)

TB1HA

(TB2HA)

TB3HA

(TB4HA)

TB5HA

(TB6HA)

B

4 For aircraft that have configuration 1

leading edge assembly

(P/N 601R12062--3, --4, --5, --6, --7, and --8).

4

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE
SERVICE BULLETIN 601R---30 ---031

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Wiring Installation

Figure 5 (sheet 1 of 7)

WS65.75

1 2 3

rsb601r30031_006.dg, gb, 07/07/09

WS45.00

WS29.42

RECEPTACLE

J427 (LH)

J426 (RH)

1HA2M22 (2HA2P22)

1HA2S22 (2HA2T22)

1HA51M22 (2HA51S22)

1HA51F22 (2HA51J22)

NOTE

It is permitted to replace the clamp as

necessary to get correct fit around the wires.

A

LEGEND

1. Clamp B0305090C8N08.

2. Clamp B0305090C8N07.

3. Clamp B0305090C8N05.

A

1HA2N22 (2HA2Q22)

1HA2T22 (2HA2U22)

1HA51N22 (2HA51T22)

1HA51G22 (2HA51K22)

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

Wiring Installation

Figure 5 (sheet 2 of 7)

rsb601r30031_007.dg, gb, 31/10/07

B

C

WS137.60

WS148.02 WS163.00 WS178.00

2 2 2

C

LEGEND

2. Clamp B0305090C8N07.

WS85.50

WS106.40

WS127.25

2 2

B

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE
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Revision D, Feb 03/2010

Wiring Installation

Figure 5 (sheet 3 of 7)

2 1 2

D

WS199.00

WS242.00

WS220.00

WS264.00

2

2 4 4 4

1HA2N22 (2HA2Q22)

1HA2T22 (2HA2U22)

1HA51G22 (2HA51K22)

1HA51N22 (2HA51T22)

E

rsb601r30031_008.dg, gb, 07/07/09

1HA2N22 (2HA2Q22)

1HA2T22 (2HA2U22)

1HA51G22 (2HA51K22)

1HA51N22 (2HA51T22)

LEGEND

1. Clamp B0305090C8N08.

2. Clamp B0305090C8N07.

4. Clamp B0305090C8N04.

D

E

1

NOTE

Install the wires along with

wire LJ20C22 (LJ19D22).

1

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

Wiring Installation

Figure 5 (sheet 4 of 7)

WS286.97 WS306.69

WS325.94

4

4 4

4 G

F

rsb601r30031_009.dg, gb, 07/07/09

F G

LEGEND

1. Clamp B0305090C8N08.

4. Clamp B0305090C8N04.

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

Wiring Installation

Figure 5 (sheet 5 of 7)

rsb601r30031_010.dg,sd, 20/12/09

1HA2N22 (2HA2Q22)

1HA2T22 (2HA2U22)

1HA51G22 (2HA51K22)

1HA51N22 (2HA51T22)

5

WS341.10 WS353.00

H

LEGEND

5. Clamp B0305090C8N03.

H

TYPICAL VIEW TYPICAL VIEW

SCREW

WASHER

CLAMP

WS362.00

(REF)

(REF)

(REF)

CLAMP

(REF)

WASHER

(REF)

SCREW

(REF)

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

2

NOTE

If necessary, the wires are installed

in conduit P/N S10155C14.

2
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Revision D, Feb 03/2010

Wiring Installation

Figure 5 (sheet 6 of 7)

rsb601r30031_011.dg, gb, 25/02/08

WING A/ICE SYSTEM

BOX ASSEMBLY

FS349.00 FS379.00 FS409+32

FS409+128 FS394.00

J423

LBL2.00

J422

ROUTE WIRE

FWD

TO CONNECTOR P139

AT FS280.00

BL0.00 TO CONNECTOR P124

AT FS280.00

TO CB2

TO CB4

LBL19.12

FS280.00 FS333.00

J

N

K

J

DCU NO. 1 GPS 1 AHRS #1

DCU NO. 2 DCU NO. 3

K

JB8 JB9

3 AHRS and GPS are optional

and not installed on all aircraft.

3

3
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

Wiring Installation

Figure 5 (sheet 7 of 7)

J192

J197

J196 CROSS--OVER

J193

N

FS409+16

FS409+32

J595

J594

M

rsb601r30031_012.dg, gb, 03/04/09

L

L

M

J194

5

LEGEND

5. WING A/ICE system box assembly

601R52070--1SB.
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

Left Wing Wiring Diagram for Thermal Switches Installation

Figure 6

1S7HA -- WS362

1S8HA -- WS356

TB1HA

TB3HA

TB5HA

LEFT WING

TB7HA

P427 J427

J

K

L

d

S

A

B

C

S

d

LH WING DISCONNECT

FS409L + 128

J423 P423

1HA2N22

1HA2T22

1HA51N22

1HA51G22

1HA2M22

1HA2S22

1HA51M22

1HA51F22

1HA2H22 TO 1J5HA--9

1

NOTE

1 Wire already installed.

rsb601r30031_036.dg, gb, 09/07/09
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Revision D, Feb 03/2010

Shroud Installation

Figure 7 (sheet 1 of 4)

rsb601r30031_021.dg

CONFIGURATION 2

LEADING EDGES P/N

601R12310--1 AND --2

ACCESS PANEL

(REF)

1

1

(4 PLACES) 2

FS386.00

L SHROUD

(REF)

ANGLE

(REF) 1

5

VIEW LOOKING UP

E

E

WS350.35

WS386.35

A

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

1 Adhesive surface area.

NOTES

2 Faying surface sealant area.

5 Ignore the identification that is on the assembly.

The leading edge P/N 601R12310--1 and --2 are

of configuration 2 with the ”L” shroud.
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

Shroud Installation

Figure 7 (sheet 2 of 4)

rsb601r30031_024.dg, sd, 20/12/09

WS350.35

WS386.35

Location of sealant.

NOTES

3

C

LEGEND

1. Blind rivet NAS9301E--4--02.

2. Rivet B0205017AD4--4S.

1

1

1

1

2

2

4 Add silicone on blind rivet head.

3. Blind rivet NAS9301E--4--03.

3

3

3

4

4

4

4

4

4

A

4

4

4

3 4

5 For aircraft that have configuration 2

leading edge assembly

(P/N 601R12310--1 and --2).

5

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

5

C

VIEW LOOKING OUTBOARD

3

RIB (REF)

SKIN (REF)

SHROUD (REF)

5
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

Shroud Installation

Figure 7 (sheet 3 of 4)

rsb601r30031_034.dg, sd, 20/19/09

A

LEGEND

1. Screw

NOTES

6 For aircraft that have configuration 1

leading edge assembly

(P/N 601R12062--3, --4, --5, --6, --7, and --8).

2 Faying surface sealant area.

LEADING EDGE

(REF)

VIEW LOOKING UP

A

B

6

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

B

ACCESS PANEL

(REF)

1

SHROUD (REF)

ACCESS PANEL

(REF)

1

2

D

6
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Revision D, Feb 03/2010

Shroud Installation

Figure 7 (sheet 4 of 4)

rsb601r30031_031.dg, sd, 20/12/09

STA366.00 STA358.86 STA350.35 STA342.30

ACCESS PANEL

REF

ACCESS PANEL

SHROUD REF

FASTENER CODE

Blind rivet NAS9301E--4--01.

Blind rivet NAS9301E--4--02.

Blind rivet NAS9301E--4--03.

Blind rivet NAS9301E--4--04.

4

4

4

4

D 6

NOTES

6 For aircraft that have configuration 1

leading edge assembly

(P/N 601R12062--3, --4, --5, --6, --7,and --8).

4 Silicone adhesive applied on rivet head.

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

4.

5.

6.

7.
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WING A/ICE Box Assembly --- Installation

Figure 8 (sheet 1 of 3)

rsb601r30031_005.dg, gb, 26/08/08

LBL28.76

LBL19.12

1.37 in.

(34.8 mm)

0.48 in.

(12.2 mm)

0.256 to 0.263 in.

(6.50 mm to 6.68 mm)

DIAMETER

1

6.94 in.

(176.8 mm)

5.59 in.

(142.0 mm)

4.24 in.

(107.7 mm)

C

NOTE

Electrical bond 0.50 in. (12.70 mm)

typical 3 places.

1

FS394.00

AVIONIC SUPPORT

STRUCTURE (REF)

A

A

B

C

(TYP)

5 AHRS and GPS are optional and

not installed on all aircraft.

5

5
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

WING A/ICE Box Assembly --- Installation

Figure 8 (sheet 2 of 3)

D

A

FWD

A

rsb601r30031_030.dg, gb, 08/07/09

E

2

E

11

13

12 FWD

GPS TRAY

601R51655

(REF)

NOTE

Refer to View D, if the distance between AHRS 1 and GPS 1 is

not satisfactory for the installation of the WING ANTI/ICE

box assembly.

2

5. Rivet MS20426AD3--5.

6. Rivet MS20426AD5--7.

7. Nutplate MS21059L06.

8. Rivet MS20426AD3--6.

11. Washer NAS1149DN616J.

12. Screw MS24693S27.

13. Screw NAS1801--06--7.

LEGEND

FS409.00 FS394.00

D

LBL28.76

6

(4 PLACES)

GPS TRAY

REF

FS409.00

TYPICAL

8

(8 PLACES)

7

(4 PLACES)

LBL19.12

.060 in. min (1.52 mm)

.545 in. max (13.84 mm)

0.51 in. (12.9 mm)

TYPICAL

5

(8 PLACES)

E

(4 PLACES)

11

13

601R720808

GPS TRAY

601R51741 OR

(REF)

14. Nutplates.

14

(4 PLACES)

90

BEAM (REF)

AVIONIC

SUPPORT

STRUCTURE

(REF)

0.204 in. (5.18 mm)

(4 PLACES)

5 AHRS and GPS are optional and not installed on all aircraft.

5

5
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Revision D, Feb 03/2010

WING A/ICE Box Assembly --- Installation

Figure 8 (sheet 3 of 3)

rsb601r30031_016.dg, gb, 03/04/09

B

FS409.00 FS394.00

FWD 2

3

2

3 4

WING A/ICE

OUTBORAD

LOW HEAT

AVIONIC SUPPORT

STRUCTURE (REF)

10

9

(4 PLACES)

F 1

F 3 F 4

LEGEND

1. WING A/ICE box assembly

2. Screw NAS1801--3--9.

3. Washer NAS1149D0332K.

4. WING A/ICE outboard low heat decal.

9. Lockring S--4933959--501.

10. INOP label 601R51723--9

601R52070--1.

NOTES

PRE--SB 601R--30--031, Part F.

POST--SB 601R--30--031, Part A, C, D, E and F.

3

4

AHRS and GPS are optional and not installed on all aircraft. 5

5 5
SERVICE BULLETIN 601R---30 ---031

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Revision D, Feb 03/2010

Right Wing Wiring Diagram for Thermal Switches Installation

Figure 9

2S7HA -- WS362

2S8HA -- WS356

RIGHT WING

TB2HA

TB4HA

TB6HA

TB8HA

RH WING DISCONNECT

FS409R + 128

J422 P422 P426 J426

A

B

C

S

d

J

K

L

d

2HA2Q22

2HA2U22

2HA51T22

2HA51K22

2HA2P22

2HA2T22

2HA51S22

2HA51J22

r 2HA2H22 TO 2J5HA--9

1

NOTE

1 Wire already installed.

rsb601r30031_037.dg, gb, 09/07/09
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Revision D, Feb 03/2010

Left Main Avionic ---Compartment Wiring Installation

Figure 10

rsb601r30031_038.dg, sd, 20/12/09

47

W9

1HA52B22

P594

3

SYS BOX FS400L

DISCONNECT

FS409R +20

J193 P193

WING A/ICE

90 1HA53B22

P595

3

J196 P196

W9

2 3

1P1WA--B

11A

11A

DCU 1

1P1WA--A

1A1WA FS384L

RH WING

LH WING

87

27

2HA51L22

1HA51A22

DISCONNECT

FS409R + 20

J194 P194

J196 P196

26

W9

2HA52A22

2HA51B22

1HA54B22

P594

11

12

13

SYS BOX FS 400 LHS

P595

11

12

13

W8

J595 P595

J594 P594

7

5

7

5

6

4

8

DISCONNECT

FS409R + 20

J194 P194

2HA2M22

2HA51F22

2HA2R22

2HA51Q22

2HA2KK22

BB

CC

DISCONNECT

FS409R + 20

P197 J197

P192 J192

H

J

r

1

2

3

4

5

WING A/ICE

OB LOW HEAT

OB LOW HEAT

1HA2G22

1

3

W8

W8

W8

8

4

6

J595 P595

1HA2L22

1HA2R22

1HA51L22

1HA51E22

1HA2KK22

3

Post SB601R--30--031 Part D and Pre SB601R--30--031 Part F, wires are stowed as shown.

Post SB601R--30--031 Part F, the wires are connected.

3

1 Wire 1HA2G22 is removed from J423--S and installed at P595--11.

J

K

L

d

S

LH WING DISCONNECT

FS409L + 128

J423 P423

NOTE

2 For aircraft with option CR31--001 or CR31--310 (Third DCU).

3

3

W9 3
SERVICE BULLETIN 601R---30 ---031

Page 118 of 126

May 15/2009 SB 601R---30---031

Revision D, Feb 03/2010

Right Main Avionic ---Compartment Wiring Installation

Figure 11

and installed at J194--26.

NOTE

1 Wire 2HA2G22 is removed from J422--r

W9

2HA51A22

1HA54A22

2P1WA--B

11A

11A

DCU 2

2P1WA--A

2A1WA FS374R

RH WING

LH WING 87

27

J196 P196

26

DISCONNECT

FS409R + 20

J194 P194

OB LOW HEAT

OB LOW HEAT

2HA2G22

1

BB

CC

DISCONNECT

FS409R + 20

P197 J197

P192 J192

H

J

r

W9

RH WING DISCONNECT

FS409R + 128

J422 P422

2HA2N22

2HA51G22

J

K

L

2HA2S22 d

2HA51R22

2HA2LL22

W8

r

NOTE

2 For aircraft with option CR31--001 or CR31--310 (Third DCU).

W9

1HA52A22

1HA53A22

P1WH--B

11A

11A

DCU 3

P1WH--A

A1WH FS386R

RH WING OB LOW HEAT

LH WING OB LOW HEAT

47

DISCONNECT

FS409R +20

J193 P193

1HA52A22

1HA53A22 90

J196 P196

2

2

rsb601r30031_035.dg, gb, 09/07/09
SERVICE BULLETIN 601R---30 ---031

Page 119 of 126

May 15/2009 SB 601R---30---031

Revision D, Feb 03/2010

3. MATERIAL INFORMATION

A. Kit Information

Kit Content:

KIT 601R30 ---031K2A

PART NUMBER QUANTITY

¡ NAME ALTERNATEPARTS NOTES

202K153---25---01/225---0 1 Boot

600---052---1 1 Strap

601R30---031K105 1 Wire Kit Left Wing

601R30---031K109 1 Decals Left Wing

601R30---031K111 1 Sleeves --- Left

Wing

B0205017AD4---4S 5 Rivet

B0305090C8N03 3 Clamp

B0305090C8N04 12 Clamp

B0305090C8N05 3 Clamp

B0305090C8N07 19 Clamp

B0305090C8N08 5 Clamp

E53690VW---1 1 Thermal Insul Wire

Cover

Length: 90 in.

M2SL0920305---101 2 Switch

M39029/56---351 5 Contact Socket

M39029/58---363 9 Contact Pin

MS20659---101 9 Terminal Lug

MS21042L04 5 Nut

MS24693---S2 5 Screw

MS25082---1 9 Nut
SERVICE BULLETIN 601R---30 ---031

Page 120 of 126

May 15/2009 SB 601R---30---031

Revision D, Feb 03/2010

PART NUMBER NOTES ALTERNATE

PARTS NAME QUANTITY¡

MS25171---1S 5 Nipple Electrical

Terminal

MS35338---41 9 Lock Washer

NAS1149DN632J 18 Washer

NAS1515M06 5 Washer

NAS1801---06---12 5 Screw

NAS9301E ---4---01 29 Blind Rivet

NAS9301E ---4---02 17 Blind Rivet

NAS9301E ---4---03 6 Blind Rivet

NAS9301E ---4---04 3 Blind Rivet

SHW8266---T 5 Shoulder Washer

¡ The kit can contain more hardware and/or material than necessary.

KIT 601R30 ---031K3A

PART NUMBER QUANTITY

¡ NAME ALTERNATEPARTS NOTES

202K153---25---01/225---0 1 Boot

600---052---1 1 Strap

601R30---031K106 1 Wire kit Right Wing

601R30---031K110 1 Decals Right Wing

601R30---031K112 1 Sleeves --- Right

Wing

B0205017AD4---4S 5 Rivet

B0305090C8N03 3 Clamp

B0305090C8N04 12 Clamp

B0305090C8N05 3 Clamp
SERVICE BULLETIN 601R---30 ---031

Page 121 of 126

May 15/2009 SB 601R---30---031

Revision D, Feb 03/2010

PART NUMBER NOTES ALTERNATE

PARTS NAME QUANTITY¡

B0305090C8N07 19 Clamp

B0305090C8N08 5 Clamp

E53690VW---1 1 Thermal Insul Wire

Cover

Length: 90 in.

M2SL0920305---101 2 Switch

M39029/56---351 5 Contact Socket

M39029/58---363 9 Contact Pin

MS20659---101 9 Terminal Lug

MS21042L04 5 Nut

MS24693---S2 5 Screw

MS25082---1 9 Nut

MS25171---1S 5 Nipple Electrical

Terminal

MS35338---41 9 Lock Washer

NAS1149DN632J 18 Washer

NAS1515M06 5 Washer

NAS1801---06---12 5 Screw

NAS9301E ---4---01 29 Blind Rivet

NAS9301E ---4---02 17 Blind Rivet

NAS9301E ---4---03 6 Blind Rivet

NAS9301E ---4---04 3 Blind Rivet

SHW8266---T 5 Shoulder Washer

¡ The kit can contain more hardware and/or material than necessary.
SERVICE BULLETIN 601R---30 ---031

Page 122 of 126

May 15/2009 SB 601R---30---031

Revision D, Feb 03/2010

KIT 601R30 ---031K4

PART NUMBER QUANTITY

¡ NAME ALTERNATEPARTS NOTES

450HA005NF11 2 Backshell

601R30---031K107 1 Wire kit Left

Fuselage

601R30---031K113 1 Decals Left

Fuselage

601R30---031K114 1 Sleeves Left

Fuselage

601R51723---9 1 Inop Label

601R52070---1SB 1 Wing A/Ice

System Box

B0802050---010 3 Contact pin

D38999/26WB35SA 1 Connector Plug

D38999/26WB35SN 1 Connector Plug

M39029/56---348 14 Contact Socket

M39029/56---351 6 Contact Socket

M39029/57---357 4 Contact Socket

M39029/58---360 6 Contact Pin

M39029/58---363 3 Contact Pin

MS20426AD3---5 9 Rivet

MS20426AD3---6 9 Rivet

MS20426AD5---7 8 Rivet

MS24693S27 3 Rivet

NAS1149D0332K 4 Washer

NAS1149DN616J 5 Washer

NAS1801---06---7 5 Screw

NAS1801---3---9 4 Screw

MS21059L06 5 Nutplate
SERVICE BULLETIN 601R---30 ---031

Page 123 of 126

May 15/2009 SB 601R---30---031

Revision D, Feb 03/2010

PART NUMBER NOTES ALTERNATE

PARTS NAME QUANTITY¡

S---4933959---501 4 Lockring

TC4001 9 End cap

¡ The kit can contain more hardware and/or material than necessary.

KIT 601R30 ---031K5

PART NUMBER QUANTITY

¡ NAME ALTERNATEPARTS NOTES

601R30---031K108 1 Wire kit Right

fuselage

B0802050---010 5 Contact Pin

M39029/56---351 6 Contact Socket

M39029/57---354 6 Contact Pin

M39029/57---357 3 Contact Socket

M39029/58---363 4 Contact Pin

¡ The kit can contain more hardware and/or material than necessary.

KIT 601R30 ---031K6

PART NUMBER QUANTITY

¡ NAME ALTERNATEPARTS NOTES

M39028/56---348 9 Contact socket

¡ The kit can contain more hardware and/or material than necessary.
SERVICE BULLETIN 601R---30 ---031

Page 124 of 126

May 15/2009 SB 601R---30---031

Revision D, Feb 03/2010

B. Consumable Information

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

ordered from Bombardier Aerospace Regional Aircraft or purchased directly from

industry sources. If the material is ordered from Bombardier Aerospace Regional

Aircraft, there can be some lead time because of shelf life of the material.

CONSUMABLES

SPECIFICATION QUANTITY NAME REFERENCE

Wakefield T ---120 As necessary Thermal compound 09---007 ¡

BAMS 565---002 As necessary Polyurethane

topcoat (clear)

16---003 ¡ ©

MIL ---C ---81706 As necessary Chemical

Conductive

Conversion

Treatment Alodine

1000 or equivalent

05---067 ¡

TT ---N ---95

Type II

As necessary Aliphatic, naphtha 12---001 ¡

AMS 3276 Class B As necessary Sealing compound 09---017 ¡

A ---A ---59323 As necessary Low---lint cloth 05---001 ¡

Varglass #46 As necessary Fiberglass tying

material

(Lacing cord)

05---093 ¡

Glyptal G1201 or

MIL ---D---5549

As necessary 1201 Glyptal Red

Enamel (Glyptol) or

Dope, Clear

Cellulose---Acetate---

Butyrate or

equivalent

05---116 ¡

S10155C14 or

equivalent

As necessary Conduit, Glass Fiber

Sleeve

05---117 ¡

3M Scotchbrite,

very fine grit 7447

or 8447

As necessary Scotchbrite pads 05---012 ¡
SERVICE BULLETIN 601R---30 ---031

Page 125 of 126

May 15/2009 SB 601R---30---031

Revision D, Feb 03/2010

SPECIFICATION REFERENCE QUANTITY NAME

MIL ---I ---19166 As necessary Tape Insulating,

electrical, high

temperature glass

fiber

05---094 ¡

MIL ---A ---46146B

Group II

As necessary GE RTV 167 or

Dow Corning

RTV 3145

Adhesive---sealant,

silicone

08---014 ¡

MIL ---A ---46106

Type I, Group III

As necessary GE RTV 106

Adhesive---sealant,

silicone

08---015 ¡

EA9309.3 NA B/A As necessary Hysol

EA9309.3 NA B/A

Cement, molding

compound

www.aerospace.henkel.us

MIL ---PRF---81733

Type lV

As necessary Sealant 09---020 ¡

MS27488---22 As necessary Sealing plug

¡ Refer to AMM 51---31---00---990---801

© It is permitted to use the other references that are related to BAMS 565---002.

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

references in this service bulletin

C. Special Tools and Equipment

SPECIAL TOOLS AND EQUIPMENT

PART NUMBER QUANTITY NAME ALTERNATE PART(S)

600---058 1 Hand Banding

Tool

AMP 49935 or

equivalent

1 Crimping Tool M22520---38,

M22520---24
SERVICE BULLETIN 601R---30 ---031

Page 126 of 126

May 15/2009 SB 601R---30---031

Revision D, Feb 03/2010

PART NUMBER ALTERNATE PART(S) QUANTITY NAME

WT ---110M or

equivalent

1 Crimping Tool

NOTE: To complete this list of special tools and equipment, refer to the different

tasks given as references in this service bulletin.

D. Disposition of Parts

Not applicable.

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 : ISSUE: 

 STRONGLY DISAGREE NEUTRAL AGREE STRONGLY 

 DISAGREE AGREE 

• Instructions to do the Service Bulletin 

were accurate. 

Comments:

    

• Illustration(s), figure(s), picture(s) and/or 

kit drawing(s) were helpful to carry out 

instructions. 

Comments:

    

• If a parts kit was required, did the kit 

contents received agree with the 

contents listed in the bulletin? 

Comments: 

    

• Aircraft hands-on work was 

accomplished in estimated time. 

 Comments:

    

• Overall, I was satisfied with this Service 

Bulletin. 

 Comments: 

    

PLEASE SUPPLY US WITH THE FOLLOWING DATA AND FAX TO (450) 476-7300: 

OPERATOR: NAME (Please print) 

SERVICE CENTER: TELEPHONE: 

AIRCRAFT SERIAL NO.: FACSIMILE: 

DATE OF SB 

INCORPOARTION