Page 1 of 1 SB 601R---30---031 Feb 03/2010 

## SERVICE BULLETIN REVISION TRANSMITTAL SHEET CL ---600 ---2B19Canadair 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.
1Page 1 of 126 SB 601R---30---031 May 15/2009 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) AircraftAffected: 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

Page 2 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

Page 3 of 126 SB 601R---30---031 May 15/2009 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

Page 4 of 126 SB 601R---30---031 May 15/2009 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

Page 5 of 126 SB 601R---30---031 May 15/2009 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

Page 6 of 126 SB 601R---30---031 May 15/2009 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

Page 7 of 126 SB 601R---30---031 May 15/2009 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

Page 8 of 126 SB 601R---30---031 May 15/2009 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

Page 9 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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

Page 10 of 126 SB 601R---30---031 May 15/2009 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

Page 11 of 126 SB 601R---30---031 May 15/2009 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

Page 12 of 126 SB 601R---30---031 May 15/2009 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

Page 13 of 126 SB 601R---30---031 May 15/2009 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

Page 14 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

Page 15 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

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

Page 16 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 CB PANEL ZONE NAME CB NO. 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).

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

Page 17 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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).

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

Page 18 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

Page 19 of 126 SB 601R---30---031 May 15/2009 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).

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

Page 20 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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.

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

Page 21 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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).

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

Page 22 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

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

Page 23 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 For Aircraft that have kit 601R30 ---031K2 (a) Remove and discard sleeve kit 601R30---031K111. For all AircraftNOTE: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.

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

Page 24 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

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

Page 25 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 WIRE TERMINAL TO FROM 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

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

Page 26 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 WIRE TERMINAL TO TERMINAL FROM 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).

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

Page 27 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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).

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

Page 28 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

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

Page 29 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 CB PANEL ZONE NAME CB NO. 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).

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

Page 30 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

Page 31 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

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

Page 32 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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).

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

Page 33 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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).

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

Page 34 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

Page 35 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

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

Page 36 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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

Page 37 of 126 SB 601R---30---031 May 15/2009 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

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

Page 38 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

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

Page 39 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

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

Page 40 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 CB PANEL ZONE NAME CB NO. 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).

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

Page 41 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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.

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

Page 42 of 126 SB 601R---30---031 May 15/2009 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 ---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).

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

Page 43 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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.

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

Page 44 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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).

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

Page 45 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

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

Page 46 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 For Aircraft that have kit 601R30 ---031K3 (a) Remove and discard sleeve kit 601R30---031K112. For all AircraftNOTE: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.

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

Page 47 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

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

Page 48 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 WIRE TERMINAL TO FROM 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

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

Page 49 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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).

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

Page 50 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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).

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

Page 51 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

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

Page 52 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 CB PANEL ZONE NAME CB NO. 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).

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

Page 53 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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.”

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

Page 54 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

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

Page 55 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

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

Page 56 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

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

Page 57 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

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

Page 58 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 CB PANEL ZONE NAME CB NO. 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).

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

Page 59 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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).

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

Page 60 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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).

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

Page 61 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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).

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

Page 62 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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).

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

Page 63 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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.

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

Page 64 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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.

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

Page 65 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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.

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

Page 66 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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.

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

Page 67 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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).

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

Page 68 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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).

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

Page 69 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

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

Page 70 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

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

Page 71 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 CB PANEL ZONE NAME CB NO. 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 aftera 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

Page 72 of 126 SB 601R---30---031 May 15/2009 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

Page 73 of 126 SB 601R---30---031 May 15/2009 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

Page 74 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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

Page 75 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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

Page 76 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

Page 77 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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

Page 78 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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

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

Page 79 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 WIRE W TERMINAL TO TERMINAL FROM 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

Page 80 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

Page 81 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 CB PANEL ZONE NAME CB NO. 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 aftera 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

Page 82 of 126 SB 601R---30---031 May 15/2009 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

Page 83 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

Page 84 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

Page 85 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 (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

Page 86 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

Page 87 of 126 SB 601R---30---031 May 15/2009 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

Page 88 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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 2rsb601r30031_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

Page 89 of 126 SB 601R---30---031 May 15/2009 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 4 B 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 Rivets to be removed. 1 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

Page 90 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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. Faying surface sealant area. 2

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

Page 91 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

Page 92 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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 DOUBLER (REF) 1

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE NOTES 1 Not installed on all aircraft.

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

Page 93 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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) DIAMETER 0.83 in. (21 mm) WS352.70 WS363.00 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. (21 mm) 1.75 in. (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.
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 8 EXISTING HOLE FOR BONDING JUMPER

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

Page 94 of 126 SB 601R---30---031 May 15/2009 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 (TB2HA) WS366.00 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) 5 D

0.25 in. (6.35 mm)

G 0.75 in. (19.05 mm) DIAMETER FS366.00

LOWER EDGING REFEDGING 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

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

Page 95 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 Leading Edge Modifications Figure 2 (sheet 5 of 5)rsb601r30031_025.dg NOTES Electrical bonding surface. 2 Thermal switch and bracket mounting area. 3 E WS350.37 WS362.77 WS355.99 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

Page 96 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 Thermal Switch Modification Figure 3rsb601r30031_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

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

Page 97 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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

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

Page 98 of 126 SB 601R---30---031 May 15/2009 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 knotholding (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

Page 99 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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)

TYPICAL 4 PLACES B 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

WS366.00TB1HA (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

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

Page 100 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 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)

TYPICAL 4 PLACES B 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 knotholding (Glytol).

2 A
WS366.00 WS350.00

1S7HA (2S7HA) THERMAL SWITCH 1S8HA (2S8HA) TB7HA (TB8HA) TB1HA (TB2HA)

TB3HA (TB4HA) TB5HA (TB6HA) B

4For 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

Page 101 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 Wiring Installation Figure 5 (sheet 1 of 7) WS65.75

1 2 3rsb601r30031_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

Page 102 of 126 SB 601R---30---031 May 15/2009 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

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

Page 103 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 Wiring Installation Figure 5 (sheet 3 of 7) 1 2 2 D WS199.00

WS242.00 WS220.00

WS264.00 2

4 2 4 4 1HA2N22 (2HA2Q22) 1HA2T22 (2HA2U22) 1HA51G22 (2HA51K22) 1HA51N22 (2HA51T22) Ersb601r30031_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

Page 104 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 Wiring Installation Figure 5 (sheet 4 of 7) WS286.97 WS306.69

WS325.94 4

4 4 4 G Frsb601r30031_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

Page 105 of 126 SB 601R---30---031 May 15/2009 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 WS353.00 WS341.10

H LEGEND 5. Clamp B0305090C8N03. H

TYPICAL VIEW TYPICAL VIEW SCREWWASHER 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

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

Page 106 of 126 SB 601R---30---031 May 15/2009 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 JB8JB9 3 AHRS and GPS are optional and not installed on all aircraft.

3 3

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

Page 107 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 Wiring Installation Figure 5 (sheet 7 of 7) J192 J197

J196 CROSS--OVER J193

NFS409+16

FS409+32 J595

J594

Mrsb601r30031_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

Page 108 of 126 SB 601R---30---031 May 15/2009 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 P427J427
J

K
L

d S A

B
C

S
d LH WING DISCONNECT FS409L + 128 P423 J423
1HA2N22

1HA2T22

1HA51N22

1HA51G22 1HA2M22

1HA2S22
1HA51M22

1HA51F22
1HA2H22 TO 1J5HA--9

1

NOTE Wire already installed. 1rsb601r30031_036.dg, gb, 09/07/09

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

Page 109 of 126 SB 601R---30---031 May 15/2009 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 2 (4 PLACES) 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

Page 110 of 126 SB 601R---30---031 May 15/2009 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

Add silicone on blind rivet head. 4

3. Blind rivet NAS9301E--4--03. 3 3 3

4
4 4

4 4 4 A 4 4 4

34

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) (REF) SHROUD

5

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

Page 111 of 126 SB 601R---30---031 May 15/2009 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). Faying surface sealant area. 2 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

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

Page 112 of 126 SB 601R---30---031 May 15/2009 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 REF SHROUD

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). Silicone adhesive applied on rivet head. 4 LEFT SIDE SHOWN RIGHT SIDE OPPOSITE

4. 5. 6. 7.

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

Page 113 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010WING 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)

5AHRS and GPS are optional and not installed on all aircraft. 5 5

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

Page 114 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010WING A/ICE Box Assembly --- Installation Figure 8 (sheet 2 of 3) D

A FWD Arsb601r30031_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)

AHRS and GPS are optional and not installed on all aircraft. 5 5 5

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

Page 115 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010WING 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 F 3 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 4AHRS and GPS are optional and not installed on all aircraft. 5 5 5

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

Page 116 of 126 SB 601R---30---031 May 15/2009 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 P422 J422 P426J426
A

B
C

S

d J

K
L

d 2HA2Q22

2HA2U22

2HA51T22

2HA51K22 2HA2P22

2HA2T22
2HA51S22

2HA51J22

2HA2H22 TO 2J5HA--9 r

1

NOTE Wire already installed. 1rsb601r30031_037.dg, gb, 09/07/09

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

Page 117 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 Left Main Avionic ---Compartment Wiring Installation Figure 10rsb601r30031_038.dg, sd, 20/12/09 47

W9 1HA52B22 P594 3 FS400L

SYS BOX DISCONNECT FS409R +20 P193 J193 WING A/ICE

90 1HA53B22 P595 3 P196 J196

W92 3

1P1WA--B

11A 11A

DCU 1 1P1WA--A 1A1WA FS384L

RH WING

LH WING 87 27

2HA51L22

1HA51A22 DISCONNECT FS409R + 20 P194 J194

P196 J196 26

W92HA52A22
2HA51B22

1HA54B22 P594 11
12

13 FS 400 LHS

SYS BOX

P595
11
12

13 W8 P595 J595

P594 J594 7 5

7 5

6 4 8 DISCONNECT FS409R + 20 P194 J194 2HA2M22
2HA51F22

2HA2R22 2HA51Q22 2HA2KK22 BB
CC DISCONNECT FS409R + 20 J197 P197

J192 P192
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 P595 J595 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 Wire 1HA2G22 is removed from J423--S and installed at P595--11. 1 J

K
L

d S LH WING DISCONNECT FS409L + 128 P423 J423 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 SB 601R---30---031 May 15/2009 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
P196 J196

26 DISCONNECT FS409R + 20 P194 J194

OB LOW HEAT

OB LOW HEAT 2HA2G22 1 BB
CC DISCONNECT FS409R + 20 J197 P197

J192 P192
H J r
W9 RH WING DISCONNECT FS409R + 128 P422 J422

2HA2N22

2HA51G22 J

K
L

d 2HA2S22 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 P193 J193 1HA52A22

90 1HA53A22 P196 J196 2 2rsb601r30031_035.dg, gb, 09/07/09

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

Page 119 of 126 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 3. MATERIAL INFORMATION

A. Kit Information Kit Content:

KIT 601R30 ---031K2A
PART NUMBER QUANTITY ¡ NAME ALTERNATE PARTS 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 SB 601R---30---031 May 15/2009 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 ALTERNATE PARTS 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 SB 601R---30---031 May 15/2009 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 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 KIT 601R30 ---031K4
PART NUMBER QUANTITY ¡ NAME ALTERNATE PARTS 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 SB 601R---30---031 May 15/2009 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 ALTERNATE PARTS 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 ALTERNATE PARTS 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 SB 601R---30---031 May 15/2009 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 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 SPECIFICATION REFERENCE NAME QUANTITY 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 SB 601R---30---031 May 15/2009 Revision D, Feb 03/2010 PART NUMBER ALTERNATE PART(S) NAME QUANTITY 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. 1THANK YOU FOR ANSWERINGTHIS EVALUATION FORM UPON COMPLETION OF THIS EVALUATIONFORM/COMPLIANCE SHEET, FAX TO 450-476-7300 

### SERVICE BULLETIN EVALUATION FORM/COMPLIANCE SHEET (YOUR IDEAS WILL HELP USPROVIDE 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