# Bombardier Service Bulletin 100-30-06

Copy: No revision named ("100-30-06"), 31 pages: PDF https://openairdocs.org/files/sha256/2c/a2/2ca265a92c8e37eb141f824292d5643c3fca6f91886a3a5dc0a3dc96c1098682; text https://openairdocs.org/service-documents/bombardier/sb-100-30-06/file/2ca265a92c8e.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2024-0758; AD 2024-16-13 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Bombardier](https://openairdocs.org/service-documents/bombardier.md)
- Type: Service bulletin (Service Bulletin)
- Number: 100-30-06
- Page: https://openairdocs.org/service-documents/bombardier/sb-100-30-06

## ADs that cite it (1) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2024-16-13](https://openairdocs.org/ad/2024-16-13.md), effective Oct 29, 2024: No revision named

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-100-30-06/proposed.md).

## Text (31 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2024-0758; AD 2024-16-13 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

MODIFICATION – AIR DATA PROBES AND SENSORS – ADDITION OF
INDEPENDENT MONITORING CIRCUIT TO DETECT SINGLE POINT FAILURE IN THE
HEAT CONTROLLER UNIT (HCM)
A. Objective
The Service Bulletin provides instructions to install a monitoring circuit comprising of relays,
external to HCM units. This additional circuit will detect the loss of the affected probe heating
function and signals the Remote Data Concentrator (RDC) to post the applicable CAS
messages.
B. Systems Impacted
An internal Control and Monitoring function within the HCM could fail in such a way where all
on−side probes may be turned OFF without annunciation to the flight crew. This additional
circuit introduced in this Service Bulletin will detect the loss of the affected probe heating
function and signals the Remote Data Concentrator (RDC) to post the applicable CAS
messages.
C. Flight Compartment Procedures Impacted
Two new Non−Normal procedures have been added to the AFM: LEFT (RIGHT) AIR DATA
HEAT FAIL. In addition, the pilot actions for the following CAS messages have changed:
− L(R) PITOT HEAT FAIL (C)
− STBY PITOT HEAT FAIL (C)
− L(R) STBY STAT HT FAIL (C)
− L(R) AOA VANE HEAT FAIL (C)
D. Passenger Compartment Procedures Impacted
Not Applicable.
E. Pilot Training
Not Applicable.
MODEL BD−100−1A10 (CH−300)
ATA 30−31
ICE AND RAIN PROTECTION
Basic Issue: Dec 29/2022 100−30−06
Page 1 of 2
PILOTS INFORMATION SHEET

### Page 2

F. AFM References
The publication that follows is required after the Service Bulletin has been incorporated:
− CH 300 Airplane Flight Manual (AFM), CSP 100−1 (Imperial or Metric), Revision 70
dated Sep 27/2022 or later approved revisions as applicable.
G. Additional Information
Not Applicable.
H. Flight Planning Information
Not Applicable.
I. Recording
After Service Bulletin 100−30−06 is incorporated, make sure to update the aircraft logbook to
show that Service Bulletin 100−30−06 Basic Issue as incorporated and if applicable provide
a copy of the Pilot Information Sheet to the flight crew.
MODEL BD−100−1A10 (CH−300)
Basic Issue: Dec 29/2022 100−30−06
Page 2 of 2

### Page 3

MODIFICATION – AIR DATA PROBES AND SENSORS – ADDITION OF
INDEPENDENT MONITORING CIRCUIT TO DETECT SINGLE POINT FAILURE IN THE
HEAT CONTROLLER UNIT (HCM)
The information below is provided for your reference. For full details, including labor and part
coverage, please see corresponding paragraph contained within this bulletin.
RECOMMENDED
SPECIFIED TIME COMPLIANCE
COMPLIANCE TIME
Within 60 months from this Service Bulletin
release date (Basic Issue)
EFFECTIVITY: A/C Serial No. 20003 to 20500
MANPOWER: 70 man−hours
CONTINUED AIRWORTHINESS (CAW)
FLEET CAMPAIGN NOYES
TLMC, CH 5 AFFECTED NOYES
KITS and/or PARTS YES NO
TOOLING/GSE YES NO
PLANNING INFORMATION NOYES
DEDICATED SCHEDULE YES NO
PREREQUISITE SERVICE BULLETINS: N/A
NOTE: This Service Bulletin may be subject to an Airworthiness Directive which will make
it necessary to implement this Service Bulletin.
To place an order for kit, please call Bombardier Aviation Parts Services at:
514−855−2999 or 1−866−538−1247
SERVICE BULLETIN SUMMARY
my.businessaircraft.bombardier.com
MODEL BD−100−1A10 (CH−300)
ATA 30−31
ICE AND RAIN PROTECTION
Basic Issue: Dec 29/2022 100−30−06
Page 1 of 1
This Service Bulletin is available at:

### Page 4

MODIFICATION – AIR DATA PROBES AND SENSORS – ADDITION OF
INDEPENDENT MONITORING CIRCUIT TO DETECT SINGLE POINT FAILURE IN THE
HEAT CONTROLLER UNIT (HCM)
1. PLANNING INFORMATION
NOTES:1 . Before you do this Service Bulletin, examine all STC, STA or
equivalent action changes to make sure that this Service Bulletin can
be completed.
2. This Service Bulletin is covered by a dedicated schedule. Dedicated
schedules are used to reserve and manage inventory due to limited
availability of rotable stock, parts and/or kits. Parts are limited, therefore,
advance part scheduling with our In−Service Implementation Team (ISIT)
is recommended prior to a maintenance visit. They can be reached at
bacs_isit@aero.bombardier.com. The parts will be allocated on a first
come first serve basis.
Should you require additional information, please contact your Regional
Sales Manager (RM) or Field Service Representative (FSR).
For more information on dedicated schedules, refer to SB 100−00−02.
A. Effectivity
BD−100−1A10 aircraft, Serial No. 20003 to 20500.
The intent of this Service Bulletin was met on the aircraft that follow with the
Pre−Published Service Bulletin 100−30−06 listed below:
SERVICE BULLETIN
my.businessaircraft.bombardier.com
MODEL BD−100−1A10 (CH−300)
ATA 30−31
ICE AND RAIN PROTECTION
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this
Service Bulletin is performed in compliance with manufacturer’s recommendations and/or acceptable industry standards.
This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or
by any means without the prior written consent of Bombardier Inc. and/or its affiliates.
 2022 Bombardier Inc.  All rights reserved
Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.
Basic Issue: Dec 29/2022 100−30−06
Page 1 of 26
This Service Bulletin is available at:

### Page 5

AIRCRAFT SERIAL NO. PRE-PUBLISHED DATE
20277 Oct 25/2022
NOTE: The instructions given 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 Aviation Service Bulletin(s).
B. Reason
1. Condition:
The Heater Current Monitor (HCM) is designed with a single Programmable
Logic Device (PLD) responsible for control and monitoring/indication of all
on−side probe heaters.
The PLD could fail in such a way where all on−side probe heaters may be
turned OFF without annunciation to the flight crew.
2. Objective/Benefit:
The Service Bulletin provides instructions to install a monitoring circuit
comprising of relays, external to HCM units. This additional circuit will detect the
loss of the affected probe heating function and signals the Remote Data
Concentrator (RDC) to post the applicable CAS message.
C. Description
This Service Bulletin gives instructions to:
− Get access to the LH and RH Heater Current Monitor (HCM),
− Rework the plate assembly,
− Install the relay bracket assembly,
− Install the relays and the rail terminal module,
− Do the wiring installation for the relays, and
− Do the necessary tests to make sure that the system operates correctly.
D. Compliance
Specified Time Compliance
Recommended within 60 months from this Service Bulletin release date (Basic
Issue).
NOTE: If it is not possible to complete all the instructions in this Service Bulletin
because of the aircraft configuration, submit an SRPSA for analysis and to
get an approved disposition to complete this Service Bulletin. Standard
SRPSA fees may apply. Refer to the Services section of the Bombardier
customer portal for the latest prices, rates and fees.
MODEL BD−100−1A10 (CH−300)
Basic Issue: Dec 29/2022 100−30−06
Page 2 of 26

### Page 6

E. Approval
The technical content of this Service Bulletin has been approved under the
authority of Transport Canada Civil Aviation (TCCA) Design Approval Organization
(DAO) No. DAO #93−Q−02.
NOTES: 1. The technical content of this Service Bulletin is accepted by the FAA
under the Canada/USA bilateral Aviation Safety Agreement.
2. The technical content of this Service Bulletin is accepted by EASA
under the Canada/EU Bilateral Aviation Safety Agreement.
F. Manpower
NOTES: 1. The man−hours given are to help you schedule the tasks given in this
Service Bulletin. The man−hours are for direct labor performed by an
experienced crew and do not include the time for familiarization,
planning, aircraft preparation in hangar such as towing and
positioning of scaffolds, removal of interior furnishings, repainting,
supervision and inspection.
For more information related to the manpower, refer to
SB 100−00−002.
2. Labor hours are based on the fact that the modification will be done at
the next scheduled maintenance task or inspection. Therefore no
man−hours are allotted to prepare the aircraft for maintenance or to
prepare for this Service Bulletin.
70 man−hours are necessary to do this modification.
The labor required to do this Service Bulletin is at no cost if:
− the work is done during new aircraft warranty period, and
− the work is done at Bombardier Business Aviation Services (BBAS) or
Authorized Service Facilities (ASF), and
− this Service Bulletin is scheduled in less than 60 months from its release date
(Basic Issue).
G. Material − Cost and Availability
Kit 350K30−001 is necessary to do this modification. For material data, refer to
Paragraph 3.C.
KIT NO. PRICE
350K30−001
Please contact Bombardier Aviation Parts Services, in
Montreal, for delivery lead times and confirmation of
prices.
MODEL BD−100−1A10 (CH−300)
Basic Issue: Dec 29/2022 100−30−06
Page 3 of 26

### Page 7

This kit is available at no cost if:
− ordered during new aircraft warranty period, and
− a no−charge purchase order is sent to Bombardier Aerospace in less than
60 months, from this Service Bulletin release date (Basic Issue).
The kit can be purchased by sending a purchase order to Bombardier Aviation
Parts Services, Montreal.
This Service Bulletin is covered by a dedicated schedule. Dedicated schedules are
used to reserve and manage inventory due to limited availability of rotable stock,
parts and/or kits. Parts are limited, therefore, advance part scheduling with our
In−Service Implementation Team (ISIT) is recommended prior to a maintenance
visit. They can be reached at bacs_isit@aero.bombardier.com. The parts will be
allocated on a first come first serve basis.
Should you require additional information, please contact your Regional Sales
Manager (RM) or Field Service Representative (FSR).
For more information on dedicated schedules, refer to SB 100−00−02.
For all parts transactions, Bombardier Aviation’s current Spare Parts and
Component Repair Price Catalogue General Terms and Conditions apply. These
terms and conditions are found on the Bombardier Customer Portal at:
my.businessaircraft.bombardier.com
Smart Parts does not pay for this recommended Service Bulletin at any time.
H. Tooling
The equipment and tools listed below are necessary to do this modification:
GSE REFERENCE NO. PART NO. DESCRIPTION
24−00−24 S4933959−501 Tag, Circuit Breaker
Commercially Available − Brush, CRES Wire
Commercially Available − Grip Measurement Gauge
Commercially Available − Rivet Installation Tools
MODEL BD−100−1A10 (CH−300)
Basic Issue: Dec 29/2022 100−30−06
Page 4 of 26

### Page 8

GSE REFERENCE NO. PART NO. DESCRIPTION
Commercially Available − Torque Wrench
NOTES: 1. Refer to the BD−100 Illustrated Tool and Equipment Manual (ITEM) to
make sure that you use the correct equipment configuration.
2. Refer to the Liability Statement in the ITEM for the BD−100 for
acceptable GSE equivalents.
3. This list is provided for a quick reference. In case of discrepancy
between this list and the tool called out in the SPM−WM, Chapter 20,
then the tool called in the SPM−WM will prevail. Other approved
alternative tools are acceptable and can also be used.
I. Weight and Balance
WEIGHT MOMENT
+0.92 pounds (0.42 kg) +263.22 pound−inches (3.03 kgm)
J. Electrical Load Data
This modification increases the continuous load as follows:
BUS AMPS KW KVAR
L ESS 0.22 amps(continuous) − −
R ESS 0.22 amps(continuous) − −
K. References
− TCCA Airworthiness Directive (pending).
− Bombardier Aviation, Modification Summary, BB100T011108, Rev. A−1.
− Bombardier Aviation, Kit Drawing K1000070493, Rev. A.
− Bombardier Aviation, Kit Drawing K1003030002, Rev. A.
− CH 300 Aircraft Maintenance Manual (AMM), Chapters 6, 24, 25, 30, 33, 52, 53
and 74.
− Bombardier Aviation, Standard Practices Manual (SPM), Chapters 20 and 51.
− CH 300 Structural Repair Manual (SRM), Chapter 51.
L. Other Publications Affected
− CH 300 Airplane Flight Manual (AFM), CSP 100−1 (Imperial or Metric),
Revision 70 dated Sep 27/2022.
MODEL BD−100−1A10 (CH−300)
Basic Issue: Dec 29/2022 100−30−06
Page 5 of 26

### Page 9

M. Equivalent Service Bulletin
− For the Challenger 350 aircraft, use Service Bulletin 350−30−001.
2. ACCOMPLISHMENT INSTRUCTIONS
NOTES: 1. All TASKs given in the procedures that follow are from the BD−100,
Aircraft Maintenance Manual unless otherwise specified.
2. All references made to zones, access panels and/or doors, are from the
BD−100, Aircraft Maintenance Manual, Chapter 6.
A. Aircraft Setup
(1) Obey all electrical/electronic safety precautions. Refer to
AMM 24−00−00−910−801.
(2) Remove the lower nose−compartment access panels (141AL/142AR,
141BL/142BR). Refer to AMM 52−45−01−000−801.
(3) On left and right avionics rack, remove the upper and lower face panels. Refer
to AMM 25−24−03−000−801.
(4) On the right side of the center pedestal, remove the forward access panel
211ARZ and the center access panel 211DRZ.
(5) Remove the flight compartment step panel 221AZF. Refer to
AMM 53−11−03−000−801.
(6) Remove the flight compartment access panel 141BZF. Refer to
AMM 53−11−05−000−802.
WARNING: DO NOT OPEN THE L OR R PROBE CTRL CIRCUIT BREAKERS
WITH ONE OR ALL OF THE PROBE POWER CIRCUIT BREAKERS
PUSHED IN. THE PROBES CAN BE HOT AND CAUSE INJURY TO
PERSONS AND DAMAGE TO THE EQUIPMENT.
(7) Open and tag the circuit breakers that follow:
(a) To make sure the vane/probe heaters do not come on, open and tag the
circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
LCBP E2 L PITOT 211
LCBP E3 L STBY STATIC 211
LCBP E5 L AOA VANE 211
LCBP E6 L AOA CASE 211
RCBP E3 STBY PITOT 212
MODEL BD−100−1A10 (CH−300)
Basic Issue: Dec 29/2022 100−30−06
Page 6 of 26

### Page 10

CB PANEL CB NO. NAME ZONE
LCBP E4 TAT 211
RCBP E2 R PITOT 212
RCBP E4 R STBY STATIC 212
RCBP E5 R AOA VANE 212
RCBP E6 R AOA CASE 212
CB PANEL CB NO. NAME ZONE
LCBP E1 L PROBE CTRL 211
RCBP E1 R PROBE CTRL 212
(8) Remove the lighting control panel. Refer to AMM 33−41−01−000−801.
(9) Remove the engine control panel. Refer to AMM 74−30−01−000−801.
(10) Remove the anti−ice control panel. Refer to AMM 30−11−09−000−801.
(11) Remove the air−data−sensor heater−current monitor. Refer to
AMM 30−31−01−000−801.
(12) Remove the windshield temperature controller. Refer to
AMM 30−41−01−000−801.
(13) Remove the side−window temperature controller. Refer to
AMM 30−41−05−000−801.
(14) Remove and retain the hardware securing the left side plate assembly, Part
No. 1005320141−007. Place plate assembly on a clean bench for the rework in
Paragraph 2.B.
(15) Remove and retain the hardware securing wire harness brackets located at the
top and bottom of the right side plate assembly, Part No. 1005320141−002.
(16) Remove and retain the hardware securing the right side plate assembly, Part
No. 1005320141−002. Place plate assembly on a clean bench for the rework in
Paragraph 2.B.
B. Modification — Installation of Relays on the Heater Current Monitor (HCM)
NOTE: If it is not possible to complete all the instructions in this Service Bulletin
because of the configuration of the aircraft, submit an SRPSA for analysis
and to get an approved disposition to complete this Service Bulletin.
MODEL BD−100−1A10 (CH−300)
Basic Issue: Dec 29/2022 100−30−06
Page 7 of 26

### Page 11

(1) Do the rework of the plate assemblies, Part No. 1005320141−007 (Left side)
and 1005320141−002 (Right side), as follows. Refer to Kit
Drawing K1000070493, Section D−D and E−E.
(a) Drill holes (qty 2) of diameter 0.220 to 0.226 in (5.59 to 5.74 mm), thru the
plate assemblies, Part No. 1005320141−007 (Left side) and
1005320141−002 (Right side), at the locations shown in Kit
Drawing K1000070493, Section D−D and E−E.
(b) Install the nut plates, Part No. MS21075L3N (qty 2), on the plate
assemblies, Part No. 1005320141−007 (Left side) and 1005320141−002
(Right side), with rivets, Part No. B0205017AD3−4S. Refer to
SRM 51−42−08.
(c) Re−identify the left side plate assembly as K1000070493−101 and right
side plate assembly as K1000070493−102.
(d) Prepare the reworked surfaces (holes) on the plate assemblies, Part
No. K1000070493−101 and K1000070493−102, for electrical bonding.
Refer to SPM−MM 51−80−00.
(e) Do the electrical bonding in the reworked surfaces (holes). Refer to
SPM−MM 51−80−00.
(f) Touch−up bare metal surfaces surrounding holes with Alodine 1132
(MIL−DTL−81706, Class 3) on the plate assemblies, Part
No. K000070493−101 and K1000070493−102, per finish code A047.
Refer to SRM 51−01−04.
(2) Install the relays, Part No. M83536/18−008L, M83536/2−024M, and
M83726/28−5001P, on the far side of relay bracket assembly, Part
No. K1000070439−001. Refer to SPM−WM 20−39−00−02 and Kit
Drawing K1000070493, Section B−B and C−C.
(3) Install the rail terminal module, Part No. M81714/67−02, on the relay bracket
assembly, Part No. K1000070439−001, with screws, Part
No. MS35206−244 (qty 2), and washers, Part No. NAS1149DN832J (qty 2).
Refer to SRM 51−41−04 and Kit Drawing K1000070493, Section B−B and
C−C.
(4) Prepare and install the applicable electrical idents, Part
No. K1000070493−003, near the relays and the rail terminal modules. Refer to
SPM−MM 20−10−10 and 20−80−01.
(5) Install the ground return stacks on the relay bracket assembly, Part
No. K1000070439−001, as follows. Refer to Kit Drawing K1000070493,
Section B−B and C−C.
(a) Install the grounding stud, Part No. B0807007−001, and the ground wire,
with washers, Part No. NAS1149D0532J, NAS1149D0332J and
MS35338−43, and the nut, Part No. MS35650−302, on the relay bracket
assembly, Part No. K1000070439−001.
(b) Prepare the surfaces of the ground return stack for electrical bonding.
Refer to SPM−MM 51−80−00.
MODEL BD−100−1A10 (CH−300)
Basic Issue: Dec 29/2022 100−30−06
Page 8 of 26

### Page 12

(c) Do the electrical bonding on the ground return stack. Refer to
SPM−MM 51−80−00.
(d) Prepare and install the applicable electrical idents, Part
No. K1000070493−003, near the ground return stacks. Refer to
SPM−MM 20−10−10 and 20−80−01.
(6) Do the wiring installation for the relays, Part No. M83536/18−008L,
M83536/2−024M, and M83726/28−5001P, as per Kit drawing K1003030002.
(7) Install the left side plate assembly, Part No. K1000070493−101 with hardware
retained.
(8) Install the right side plate assembly, Part No. K1000070493−102 with
hardware retained.
(9) Install the wire harness brackets located at the top and bottom of the right side
assembly, Part No. K1000070493−102 with hardware retained.
(10) Install the relay bracket assembly, Part No. K1000070439−001, on the plate
assemblies, Part No. K1000070493−101, with screws, Part
No. NAS1801−3−8 (qty 2), and washers, Part No. NAS1149D0316J (qty 2).
Refer to SRM 51−41−04 and Kit Drawing K1000070493, Section B−B and
C−C.
(11) Apply HumiSeal all around the ground return stacks. Refer to
SPM−MM 20−40−00. Refer to Kit Drawing K1000070493, Section B−B and
C−C.
(12) Install the air−data−sensor heater−current monitor. Refer to
AMM 30−31−01−400−801.
(13) Install the windshield temperature controller. Refer to
AMM 30−41−01−400−801.
(14) Install the side−window temperature controller. Refer to
AMM 30−41−05−400−801.
(15) Install the anti−ice control panel. Refer to AMM 30−11−09−400−801.
(16) Install the lighting control panel. Refer to AMM 33−41−01−400−801.
(17) Install the engine control panel. Refer to AMM 74−30−01−400−801.
C. Testing
(1) Do the procedure that follow:
(a) Make sure that the ANTI−ICE control panel is set as follows:
REFERENCE POSITION/INDICATION
L PROBES and R
PROBES PBA
Not pushed in, the push button annunciator
(PBA) lights are on. L PROBE HEAT OFF (C)
and R PROBE HEAT OFF (C) displayed on
EICAS (to keep the probe heaters OFF).
MODEL BD−100−1A10 (CH−300)
Basic Issue: Dec 29/2022 100−30−06
Page 9 of 26

### Page 13

WARNING: IF PROBE CTRL BREAKERS ARE OPEN AND PROBES BREAKERS
ARE CLOSED, PROBES WILL HEAT AND MAY CAUSE INJURY OR
DAMAGE TO PROBES.
(b) To power the system for testing, remove the tags and close the circuit
breakers that follow.
CB PANEL CB NO. NAME ZONE
LCBP E1 L PROBE CTRL 211
RCBP E1 R PROBE CTRL 212
CB PANEL CB NO. NAME ZONE
LCBP E2 L PITOT 211
LCBP E3 L STBY STATIC 211
LCBP E5 L AOA VANE 211
LCBP E6 L AOA CASE 211
RCBP E3 STBY PITOT 212
LCBP E4 TAT 211
RCBP E2 R PITOT 212
RCBP E4 R STBY STATIC 212
RCBP E5 R AOA VANE 212
RCBP E6 R AOA CASE 212
(c) On the ANTI−ICE control panel, select L PROBES PBA On, so that "OFF"
extinguishes on the L PROBES PBA and L PROBE HEAT OFF (C) clears
from EICAS.
(d) On the ANTI−ICE control panel, select R PROBES PBA On, so that "OFF"
extinguishes on the R PROBES PBA and R PROBE HEAT OFF (C) clears
from EICAS.
(e) Observe for five minutes that NO probe heater failure message is
displayed on the EICAS.
(f) After the test is pass, proceed to the next step.
(g) Make sure that the ANTI−ICE control panel is set as follows:
MODEL BD−100−1A10 (CH−300)
Basic Issue: Dec 29/2022 100−30−06
Page 10 of 26

### Page 14

REFERENCE POSITION/INDICATION
L PROBES and R
PROBES PBA
Not pushed in, the push button annunciator
(PBA) lights are on. L PROBE HEAT OFF (C)
and R PROBE HEAT OFF (C) displayed on
EICAS (to keep the probe heaters OFF).
(2) Do the operational test of the wing anti−ice system. Refer to
AMM 30−10−00−710−801.
(3) Do the operational test of the nacelle anti−ice system. Refer to
AMM 30−21−00−710−801.
(4) Do the operational test of the windshield anti−ice system. Refer to
AMM 30−41−00−710−801.
(5) Do the operational test of the heater−current monitor/controller (HCM/C), as
follows:
NOTES: SYSTEM CLEAR PROCEDURE − After completing each test point
C002/C003 and C004, and starting the next test point run the steps
that follow to bring the system back in normal condition:
1. On the ANTI−ICE control panel, deselect L PROBES PBA. Make
sure “OFF” is illuminated on the L PROBES PBA and L PROBE
HEAT OFF (C) DOES post to EICAS.
2. On the ANTI−ICE control panel, deselect R PROBES PBA. Make
sure “OFF” is illuminated on the R PROBES PBA and R PROBE
HEAT OFF (C) DOES post to EICAS.
3. On the system test control panel, rotate the PUSH TO TEST
selector to PROBES and perform system test.
4. After Probe system test is complete, verify the following CAS
Message DOES post to EICAS:
− PROBE HEAT TEST OK (S)
Test Points:
(a) C001: L PROBE OFF AND R PROBE OFF − NO SIMULATED HCM
FAILURE
(i) On the ANTI−ICE control panel, deselect L PROBES PBA. Make sure
“OFF” is illuminated on the L PROBES PBA and L PROBE HEAT
OFF (C) DOES post to EICAS.
(ii) On the ANTI−ICE control panel, deselect R PROBES PBA. Make
sure “OFF” is illuminated on the R PROBES PBA and R PROBE
HEAT OFF (C) DOES post to EICAS.
(iii) On the system test control panel, rotate the PUSH TO TEST selector
to PROBES and perform system test.
MODEL BD−100−1A10 (CH−300)
Basic Issue: Dec 29/2022 100−30−06
Page 11 of 26

### Page 15

(iv) Verify the following CAS Messages DO NOT post on EICAS:
− L PITOT HEAT FAIL (C)
− R PITOT HEAT FAIL (C)
− L STBY STAT HT FAIL (C)
− R STBY STAT HT FAIL (C)
− TAT HEAT FAIL (A)
− STBY PITOT HEAT FAIL (C)
− L AOA VANE HEAT FAIL (C)
− R AOA VANE HEAT FAIL (C)
− L AOA CASE HEAT FAIL (A)
− R AOA CASE HEAT FAIL (A)
− L PROBE HT CTRL FAIL (A)
− R PROBE HT CTRL FAIL (A)
(v) After probe system test is complete, verify the following CAS
message DOES post to EICAS for approximately 10 seconds:
− PROBE HEAT TEST OK (S)
(vi) End of test.
(b) C002: L PROBE ON AND R PROBE OFF − LEFT HCM SIMULATED
HCM FAILURE
(i) On the ANTI−ICE control panel, select L PROBES PBA On so that
“OFF” extinguishes on the L PROBES PBA and L PROBE HEAT OFF
(C) clears from EICAS.
(ii) On the ANTI−ICE control panel, deselect R PROBES PBA. Make
sure “OFF” is illuminated on the R PROBES PBA and R PROBE
HEAT OFF (C) DOES post to EICAS.
(iii) Wait at least five seconds from L PROBES PBA selection to ON.
(iv) On the system test control panel, rotate the PUSH TO TEST selector
to PROBES and perform system test.
(v) Verify the following CAS Messages DO NOT post on EICAS:
− R PITOT HEAT FAIL (C)
− L STBY STAT HT FAIL (C)
− R STBY STAT HT FAIL (C)
− TAT HEAT FAIL (A)
− R AOA VANE HEAT FAIL (C)
− L AOA CASE HEAT FAIL (A)
− R AOA CASE HEAT FAIL (A)
− R PROBE HT CTRL FAIL (A)
MODEL BD−100−1A10 (CH−300)
Basic Issue: Dec 29/2022 100−30−06
Page 12 of 26

### Page 16

(vi) Verify R PROBE HEAT OFF (C) remains posted on EICAS.
(vii) Verify the following CAS Messages DO post to EICAS:
− L PITOT HEAT FAIL (C)
− L AOA VANE HEAT FAIL (C)
− STBY PITOT HEAT FAIL (C)
(viii) On the ANTI−ICE control panel, deselect L PROBES PBA. Make sure
“OFF” is illuminated on the L PROBES PBA and L PROBE HEAT
OFF (C) DOES post to EICAS.
(ix) Verify the following CAS Messages clear from EICAS:
− L PITOT HEAT FAIL (C)
− L AOA VANE HEAT FAIL (C)
− STBY PITOT HEAT FAIL (C)
(x) End of test.
(xi) RUN THE SYSTEM CLEAR PROCEDURE. Refer to
Paragraph 2.C.(5). NOTES.
(c) C003: L PROBE OFF AND R PROBE ON − RIGHT SIMULATED HCM
FAILURE
(i) On the ANTI−ICE control panel, deselect L PROBES PBA. Make sure
“OFF” is illuminated on the L PROBES PBA and L PROBE HEAT
OFF (C) DOES post to EICAS.
(ii) On the ANTI−ICE control panel, select R PROBES PBA On so that
“OFF” extinguishes on the R PROBES PBA and R PROBE HEAT
OFF (C) clears from EICAS.
(iii) Wait at least five seconds from R PROBES PBA selection to ON.
(iv) On the system test control panel, rotate the PUSH TO TEST selector
to PROBES and perform system test.
(v) Verify the following CAS Messages DO NOT post on EICAS:
− L PITOT HEAT FAIL (C)
− L STBY STAT HT FAIL (C)
− TAT HEAT FAIL (A)
− STBY PITOT HEAT FAIL (C)
− L AOA VANE HEAT FAIL (C)
− L AOA CASE HEAT FAIL (A)
− R AOA CASE HEAT FAIL (A)
− L PROBE HT CTRL FAIL (A)
(vi) Verify L PROBE HEAT OFF (C) remains posted on EICAS.
MODEL BD−100−1A10 (CH−300)
Basic Issue: Dec 29/2022 100−30−06
Page 13 of 26

### Page 17

(vii) Verify the following CAS Messages DO post to EICAS:
− R PITOT HEAT FAIL (C)
− R AOA VANE HEAT FAIL (C)
− R STBY STAT HT FAIL (C)
(viii) On the ANTI−ICE control panel, deselect R PROBES PBA. Make
sure “OFF” is illuminated on the R PROBES PBA and R PROBE
HEAT OFF (C) DOES post to EICAS.
(ix) Verify the following CAS Messages clear from EICAS:
− R PITOT HEAT FAIL (C)
− R AOA VANE HEAT FAIL (C)
− R STBY STAT HT FAIL (C)
(x) End of test.
(xi) RUN THE SYSTEM CLEAR PROCEDURE. Refer to
Paragraph 2.C.(5). NOTES.
(d) C004: L PROBE ON AND R PROBE ON − LEFT & RIGHT SIMULATED
HCM FAILURE
(i) On the ANTI−ICE control panel, select L PROBES PBA On so that
“OFF” extinguishes on the L PROBES PBA and L PROBE HEAT OFF
(C) clears from EICAS.
(ii) On the ANTI−ICE control panel, select R PROBES PBA On so that
“OFF” extinguishes on the R PROBES PBA and R PROBE HEAT
OFF (C) clears from EICAS.
(iii) Wait at least five seconds from R PROBES PBA selection to ON.
(iv) On the system test control panel, rotate the PUSH TO TEST selector
to PROBES and perform system test.
(v) Verify the following CAS Messages DO NOT post on EICAS:
− L STBY STAT HT FAIL (C)
− TAT HEAT FAIL (A)
− L AOA CASE HEAT FAIL (A)
− R AOA CASE HEAT FAIL (A)
(vi) Verify the following CAS Messages DO post to EICAS:
− L PITOT HEAT FAIL (C)
− L AOA VANE HEAT FAIL (C)
− STBY PITOT HEAT FAIL (C)
− R PITOT HEAT FAIL (C)
− R AOA VANE HEAT FAIL (C)
− R STBY STAT HT FAIL (C)
MODEL BD−100−1A10 (CH−300)
Basic Issue: Dec 29/2022 100−30−06
Page 14 of 26

### Page 18

(vii) On the ANTI−ICE control panel, deselect L PROBES PBA On so that
“OFF” is illuminated on the L PROBES PBA and L PROBE HEAT
OFF (C) DOES post to EICAS.
(viii) On the ANTI−ICE control panel, deselect R PROBES PBA On so that
“OFF” is illuminated on the R PROBES PBA and R PROBE HEAT
OFF (C) DOES post to EICAS.
(ix) Verify the following CAS Messages clear from EICAS:
− L PITOT HEAT FAIL (C)
− L AOA VANE HEAT FAIL (C)
− STBY PITOT HEAT FAIL (C)
− R PITOT HEAT FAIL (C)
− R AOA VANE HEAT FAIL (C)
− R STBY STAT HT FAIL (C)
(x) End of test.
(xi) RUN THE SYSTEM CLEAR PROCEDURE. Refer to
Paragraph 2.C.(5). NOTES.
D. Close−out
(1) Remove all tools, equipment and unwanted materials from the aircraft.
(2) On the right side of the center pedestal, install the forward access panel
211ARZ and the center access panel 211DRZ.
(3) Install the flight compartment step panel 221AZF. Refer to
AMM 53−11−03−400−801.
(4) Install the flight compartment access panel 141BZF. Refer to
AMM 53−11−05−400−802.
(5) On left and right avionics rack, install the upper and lower face panels. Refer to
AMM 25−24−03−400−801.
(6) Install the lower nose−compartment access panels (141AL/142AR,
141BL/142BR). Refer to AMM 52−45−01−400−801.
E. Recording
When this Service Bulletin is completed, make an entry in the aircraft log and send
the attached Incorporation Notice to Bombardier Business Aircraft Customer
Services (BBACS).
For information, correction(s), comment(s) and/or feedback regarding Service
Bulletins released on the Customer Portal, please contact the Service Bulletin
Group at the following email address:
bbad_SBgroup@aero.bombardier.com
MODEL BD−100−1A10 (CH−300)
Basic Issue: Dec 29/2022 100−30−06
Page 15 of 26

### Page 19

3. MATERIAL INFORMATION
A. Kit
Kit 350K30−001 is necessary to do this Service Bulletin and contains the parts that
follow:
NEW PART NO. QTY ITEM USEDPART
NO.
INSTRUCTIONS
- DISPOSITION
B0205017AD3−4S 8 Rivet, Solid CSK − −
B0808018−002 2 Terminal Block − −
K1003030002/01 1 Wire Kit − −
K1000070493−003/01 1 Ident, Kit − −
MS21075L3N 4 Nutplate,Self−LKG − −
MS35206−244 4 Screw − −
MS35207−265 4 Screw, PAN Head − −
MS35338−43 8 Washer, Lock − −
MS35650−302 8 Nut, Plain,Hexagon − −
M12883/40−23 2 Relay Socket − −
M12883/40−24 2 Relay Socket − −
M12883/45−01 2 Relay Socket − −
M81714/67−02
or
SJTC02000
or
DCR−1A−02
2 Rail, TerminalModule − −
M83536/18−008L 2 Relay − −
M83536/2−024M 2 Relay − −
M83726/28−5001P 2 Relay − −
NAS1149DN832J 4 Washer − −
MODEL BD−100−1A10 (CH−300)
Basic Issue: Dec 29/2022 100−30−06
Page 16 of 26

### Page 20

NEW PART NO. QTY ITEM USEDPART
NO.
INSTRUCTIONS
- DISPOSITION
NAS1149D0316J 4 Washer − −
NAS1149D0332J 12 Washer, Flat − −
NAS1801−3−8 4 Screw, Hex HD − −
K1000070439−001 2 Bracket Assembly,Relay − −
NOTES: 1. In case of discrepancy between this list and the Service Bulletin Kit
Parts List contained in the respective kit, then the later list prevails.
2. The actual quantity for some of the hardware contained in the kit can
be greater than the amount shown in the table as these items are
supplied in prepackaged quantities.
B. Parts
No parts required.
C. Material
The materials that follow are necessary to do this Service Bulletin. These can be
purchased from a local supplier. Bombardier Aviation does not pay for this
consumable.
DESCRIPTION PARTNO./NAME SPECIFICATION QUANTITY
SUPPLIER
(SEE
NOTE)
Abrasive
paper − − As Necessary Code: A
Chemical
conversion
coating
Alodine 1132 MIL−DTL−81706,Class 3 As Necessary Code: A
Cloth,
Cleaner,
Low−lint
− − As Necessary Code: A
Fluid resistant
Epoxy Primer − BAMS 565−001 As Necessary Code: A
HumiSeal − − As Necessary Code: A
MODEL BD−100−1A10 (CH−300)
Basic Issue: Dec 29/2022 100−30−06
Page 17 of 26

### Page 21

DESCRIPTION PARTNO./NAME SPECIFICATION QUANTITY
SUPPLIER
(SEE
NOTE)
Sharp Knife − − As Necessary Code: A
Spatula − − As Necessary Code: A
NOTES: 1. Refer to the table that follows for each suppliers address listed by
codes.
2. The Curing Time (CT), if applicable, for each consumable material is
indicated with the description of each product.
3. At time of release of this Service Bulletin, the information on the
supplier was valid and accurate. In the event that this information has
changed, the operator is encouraged to use the World Wide Web to
find a local supplier.
SUPPLIERS ADDRESSES BY CODES
Code: A
Commercially Available
D. Publications
The publication that follows is required after the Service Bulletin has been
incorporated.
− CH 300 Airplane Flight Manual (AFM), CSP 100−1 (Imperial or Metric),
Revision 70 dated Sep 27/2022 or later approved revisions as applicable.
MODEL BD−100−1A10 (CH−300)
Basic Issue: Dec 29/2022 100−30−06
Page 18 of 26

### Page 22

SB350−30−001−70493−A−S1−PL 
MODEL BD−100−1A10 (CH−300)
PL K1000070493 − Kit − HCM − Relay Installation
(Sheet 1 of 2, Rev. A)
Basic Issue: Dec 29/2022 100−30−06
Page 19 of 26

### Page 23

SB350−30−001−70493−A−S2−PL 
MODEL BD−100−1A10 (CH−300)
PL K1000070493 − Kit − HCM − Relay Installation
(Sheet 2 of 2, Rev. A)
Basic Issue: Dec 29/2022 100−30−06
Page 20 of 26

### Page 24

SB350−30−001−70493−A−S1−1 
MODEL BD−100−1A10 (CH−300)
K1000070493 − Kit − HCM − Relay Installation
(Sheet 1 of 1, Rev. A)
Basic Issue: Dec 29/2022 100−30−06
Page 21 of 26

### Page 25

SB350−30−001−70493−A−S1−2 
MODEL BD−100−1A10 (CH−300)
K1000070493 − Kit − HCM − Relay Installation
(Sheet 1 of 1, Rev. A, continued)
Basic Issue: Dec 29/2022 100−30−06
Page 22 of 26

### Page 26

SB350−30−001−30002−A−S1 
MODEL BD−100−1A10 (CH−300)
K1003030002 − Kit Wiring Diagram Air Data Sensor Heater
(Sheet 1 of 4, Rev. A)
Basic Issue: Dec 29/2022 100−30−06
Page 23 of 26

### Page 27

SB350−30−001−30002−A−S2 
MODEL BD−100−1A10 (CH−300)
K1003030002 − Kit Wiring Diagram Air Data Sensor Heater
(Sheet 2 of 4, Rev. A)
Basic Issue: Dec 29/2022 100−30−06
Page 24 of 26

### Page 28

SB350−30−001−30002−A−S3 
MODEL BD−100−1A10 (CH−300)
K1003030002 − Kit Wiring Diagram Air Data Sensor Heater
(Sheet 3 of 4, Rev. A)
Basic Issue: Dec 29/2022 100−30−06
Page 25 of 26

### Page 29

SB350−30−001−30002−A−S4 
MODEL BD−100−1A10 (CH−300)
K1003030002 − Kit Wiring Diagram Air Data Sensor Heater
(Sheet 4 of 4, Rev. A)
Basic Issue: Dec 29/2022 100−30−06
Page 26 of 26

### Page 30

100−30−06 Basic Dec 29/2022
Modification – Air Data Probes and Sensors – Addition of Independent
Monitoring Circuit to Detect Single Point Failure in the Heat Controller Unit
(HCM)
bbad_SBgroup@aero.bombardier.com
NOTE: Please use Salesforce only for troubleshooting issues or when Engineering
deviation is necessary to accomplish the Service Bulletin modification.
SERVICE BULLETIN EVALUATION FORM
(Your ideas will help us provide better bulletins)
SERVICE BULLETIN: ISSUE: DATED:
TITLE:
For any information, correction(s), comment(s) and/or feedback regarding Service
Bulletins released on the Customer Portal, please contact the Service Bulletin Group
at the following email address:

### Page 31

SERVICE BULLETIN INCORPORATION SHEET − "100−30−06"
Upon completion of the Service Bulletin, please fill−in, fax to
(514) 855−8798 or e−mail to Fracas at fracas.montreal@aero.bombardier.com
If you’re reporting Service Bulletin (SB) Incorporations to CAMP, sending
this Incorporation Sheet to Bombardier is not mandatory. If your aircraft is
on another tracking system, please contact Bombardier to make arrangements
for automated data submission.
100−30−06 Basic
COMPLIED WITH
YES    NO    N/A
Actual hours to accomplish Service Bulletin:
* NOTES:
Aircraft Serial No. Aircraft Reg. No.
Airframe Hours: Airframe Landings
S.B. Incorporation Date Service Order No.
Facility incorporating S.B.
Name Signature Date
BOMBARDIER
SUBMISSION
Service Bulletin
Number
Rev. * Parts
Completed
Remarks/Reason
(Mandatory if N/A)
1. Where the Service Bulletin is divided into a number of parts (e.g., PARTS A,
B, C, D, etc.) which can be carried out separately, indicate only those parts
completed at this time.
2. For repetitive checks (usually PART A) only the initial check should be
reported unless otherwise stated in the Service Bulletin.
3. When more than one part is carried out at the same time, each part should
be reported.
4. Fill in ’Remark/Reason’ to explain compliance method when N/A is selected.(E.g. Part
not installed, N/A by effectivity, N/A by Part Serial Number, etc.
5. PCW means ’Previously Complied With’.
(dd/mm/yy)
Signature not required if sent by E−Mail (dd/mm/yy)

---
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