# Bombardier Service Bulletin 100-49-04

Copy: No revision named ("SB 100-49-04"), 14 pages: PDF https://openairdocs.org/files/sha256/5e/b6/5eb6a9cb64164c2a7b0cb9c4020ffcb0ea5802b22f5256188c92c8c110d3632c; text https://openairdocs.org/service-documents/bombardier/sb-100-49-04/file/5eb6a9cb6416.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2018-0274; AD 2018-14-05 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: 100-49-04
- Page: https://openairdocs.org/service-documents/bombardier/sb-100-49-04

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

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

- [AD 2018-14-05](https://openairdocs.org/ad/2018-14-05.md), effective Aug 13, 2018: No revision named

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-100-49-04/proposed.md).

## Text (14 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2018-0274; AD 2018-14-05 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 - ENGINE CONTROL SYSTEM - MODIFICATION OF THE
ELECTRONIC CONTROL UNIT (ECU) WIRING HARNESS TO ENABLE AUTO
SHUTDOWN AND TO INHIBIT A SECOND START ATTEMPT IN FLIGHT
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 30 months from the
release of this Service Bulletin
(Basic Issue)
EFFECTIVITY: A/C Serial No. 20003 to 20500
MANPOWER: 3 maníhours
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 NOYES
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 parts or kits, please call Bombardier Aerospace Parts Services
at:
514í855í2999 or 1í866í538í1247
SERVICE BULLETIN SUMMARY
www.cic.bombardier.com
MODEL BDí100í1A10 (CHí300)
ATA 49í61
AIRBORNE AUXILIARY POWER
Basic Issue: Mar 29/2017 100í49í04
P a g e1o f1
This Service Bulletin is available at:

### Page 2

MODIFICATION - ENGINE CONTROL SYSTEM - MODIFICATION OF THE
ELECTRONIC CONTROL UNIT (ECU) WIRING HARNESS TO ENABLE AUTO
SHUTDOWN AND TO INHIBIT A SECOND START ATTEMPT IN FLIGHT
1. PLANNING INFORMATION
A. Effectivity
BDí100í1A10 aircraft, Serial No. 20003 to 20500.
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 Aerospace Service Bulletin(s).
Before you do this bulletin, examine all STC, STA or equivalent action
changes to make sure that this bulletin can be completed.
B. Reason
There have been incidents of APU inlet fires occurring in flight following two or
more APU start attempts.
This Service Bulletin introduces a modification to the ECU wiring harness to prevent
a second attempt to start the APU following a failed start in flight. All of the existing
protective auto shutdown logic that applies on the ground will now apply in the air.
Also, ’One Start’ limitation placards are installed in the cockpit. The benefits to the
operator are improved safety and reduced maintenance costs.
C. Description
This Service Bulletin gives instructions to:
í Get access to the APU ECU,
í Do the modification to ECU wire harness,
SERVICE BULLETIN
www.cic.bombardier.com
MODEL BDí100í1A10 (CHí300)
ATA 49í61
AIRBORNE AUXILIARY POWER
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.
© 2017 Bombardier Inc.  All rights reserved
Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.
Basic Issue: Mar 29/2017 100í49í04
Page 1 of 11
This Service Bulletin is available at:

### Page 3

í Install the placards in the cockpit, and
í Do the necessary tests to make sure that the system operates correctly.
D. Compliance
Recommended within 30 months from this Service Bulletin release date (Basic
Issue).
NOTE: This Service Bulletin is in reference to Advisory Wire AW300 í49í0140.
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 #93íQí02.
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 in
accordance with established procedures.
F. Manpower
NOTES: 1. The man íhours given are to help you schedule the tasks given in this
bulletin. The maníhours 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
100í00í02.
2. This Service Bulletin may require consumable materials that have
specific curing times (refer to Paragraph 3). The accumulated curing
time is not included in the maníhours and should be considered for
planning purposes before you schedule this Service Bulletin.
3 maníhours are necessary to do this modification.
The labor required to do this Service Bulletin is at no cost if:
í the work is done during new aircraft warranty period, and
í the work is done at Bombardier Business Aviation Services (BBAS) or
Authorized Service Facilities (ASF), and
í this Service Bulletin is scheduled in less than 30 months from its release date
(Basic Issue).
G. Material í Cost and Availability
Kit 100K49í04 is necessary to do this modification.
MODEL BDí100í1A10 (CHí300)
Basic Issue: Mar 29/2017 100í49í04
P a g e2o f1 1

### Page 4

KIT NO. PRICE
100K49í04
Please contact Bombardier Aerospace
Parts Services, in Montreal, for delivery
lead times and confirmation of prices.
This kit is available at no cost if:
í ordered during new aircraft warranty period, and
í a noícharge purchase order is sent to Bombardier Aerospace in less than 30
months , from this Service Bulletin release date (Basic Issue).
For all parts transactions, Bombardier Aerospace’s current Spare Parts and
Component Repair Price Catalogue General Terms and Conditions apply. These
terms and conditions are found on the CIC website.
Smart Parts Plus does not pay for the kits at any time.
H. Tooling
The equipment and tools listed below are necessary to do this modification:
GSE REFERENCE NO. PART NO. DESCRIPTION
20Xí00í04 M1íGíKIT Portable Bonding Tester
24í00í24 S4933959í501 Tag, Circuit Breaker
Commercially Available í Digital Ohmmeter
Refer to the Standard Practices Manual (SPM), Wiring Manual (WM), Chapter 20,
and the table that follows for the tools applicable to the wiring modification:
LUG/CONTACT
WIRING TOOL (SEE NOTE 3)
CRIMP POSITIONER/DIE INSERTION EXTRACTION
B0802050í010 í í í M81969/14í01
MODEL BDí100í1A10 (CHí300)
Basic Issue: Mar 29/2017 100í49í04
Page 3 of 11

### Page 5

LUG/CONTACT
WIRING TOOL (SEE NOTE 3)
CRIMP POSITIONER/DIE INSERTION EXTRACTION
Dí436í83 M22520/37í01 í í í
NOTES: 1. Refer to the BD í100 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 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 SPMíWM, Chapter 20,
then the tool called in the SPMíWM will prevail. Other approved
alternative tools are acceptable and can also be used.
I. Weight and Balance
No change.
J. Electrical Load Data
No change.
K. References
í Bombardier Aerospace, Modification Summary, BB100T010811, Rev. A.
í Bombardier Aerospace, Restriction and/or Special Instruction (RSI),
Cí100í000í49í0051, Rev. A.
í Bombardier Aerospace, Standard Practices Manual (SPM), Chapter 20.
í Bombardier Aerospace, Kit Drawing K1000070376, Rev. íí.
í Bombardier Aerospace, Kit Drawing K1004930001, Rev. íí.
í Bombardier Aerospace, SB 100í00í02, Service Bulletin Description and Policy.
í Advisory Wire AW300í49í0140.
í CH 300 Aircraft Maintenance Manual (AMM), Chapters 6, 24, 49, 51 and 52.
í CH 300 Illustrated Tool and Equipment Manual (ITEM) Chapters 20 and 24.
L. Other Publications Affected
CH 300 Wiring Manual (WM), Chapter 49.
CH 300 Aircraft Illustrated Parts Catalog (AIPC), Chapter 11.
M. Equivalent Service Bulletin
For CH 350 aircraft, use SB 350í49í001.
MODEL BDí100í1A10 (CHí300)
Basic Issue: Mar 29/2017 100í49í04
P a g e4o f1 1

### Page 6

2. ACCOMPLISHMENT INSTRUCTIONS
NOTE: All references made to zones, access panels and/or doors, are from the
CH 300 AMM, Chapter 6.
A. Aircraft Setup
(1) Obey all electrical/electronic safety precautions. Refer to
AMM 24í00í00í910í801.
(2) Obey all electrostatic ídischarge safety precautions. Refer to
AMM 24í00í00í910í802.
(3) Obey all APU safety precautions. Refer to AMM 49 í00í00í910í801.
(4) Open the aft equipment ícompartment door 182GL. Refer to
AMM 52í41í00í010í801.
(5) Open and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
LCBP B8 APU PRI 211
RCBP B8 APU SEC 212
B. Modification
CAUTION: OBEY ALL ELECTROSTATIC DISCHARGE-SENSITIVE (ESDS)
PRECAUTIONS. STATIC VOLTAGES CAN CAUSE DAMAGE TO
ESDS COMPONENTS.
(1) Obey all electrostatic discharge safety precautions. Refer to
AMM 24í00í00í910í802.
(2) Remove the APU ECU. Refer to AMM 49 í61í01í000í801.
(3) Do the modification to the ECU wiring harness as follows, refer to Figure 1:
(a) Locate and remove the wire, RAF J030 í22 from connector A39BP1,
contact 4A.
(b) Locate the splice SP358. Cut the wires, RAF 1276 í18, RAF J029í18 and
RAF J030 as close as possible to the splice SP358, Discard the splice and
wire RAF J030í22.
(c) Connect the wires RAF 1276 í18 and RAF J029í18 with new splice, Part
No. Dí436í83. Refer to SPMíWM 20í16í05 (Sealed Crimp Splice
section).
NOTE: Use crimper, Part No. M22520/37 í01 to crimp new splice SP358,
Part No. Dí436í83.
(4) Do a continuity and/or ground check of all new or modified wires. Refer to SPM
WM20í12í01í05.
(5) Install the APU ECU. Refer to AMM 49 í61í01í400í801.
MODEL BDí100í1A10 (CHí300)
Basic Issue: Mar 29/2017 100í49í04
Page 5 of 11

### Page 7

(6) Do the electrical bonding test of the APU ECU between the connector shell
and the ECU mounting tray. Refer to AMM 51í80í00í760í801.
NOTE: Make sure that the resistance value is not more than 0.005 ohm.
(7) Install the placards, Part No. 1005323415 í001 and 1005323420í001, as
shown per SPMíMM 20í80í01í400í801. Refer to Figure 2.
NOTE: Do not apply a layer of polyurethane clear coat.
C. Testing
(1) Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
LCBP B8 APU PRI 211
RCBP B8 APU SEC 212
(2) Do the operational test of the APU. Refer to AMM 49 í11í01í710í801.
D. Close íout
(1) Remove all tools, equipment and unwanted materials from the aircraft.
(2) Close the aft equipment ícompartment door 182GL. Refer to
AMM 52í41í00í410í801.
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).
In an effort to improve the quality of our technical communications, we are
requesting your feedback. Please take a moment to fill out our easy oníline Service
Bulletin survey:
http://csefeedback.aero.bombardier.com
3. MATERIAL INFORMATION
A. Kits
Kit 100K49í04 is necessary to do this Service Bulletin and contains the parts that
follow:
MODEL BDí100í1A10 (CHí300)
Basic Issue: Mar 29/2017 100í49í04
P a g e6o f1 1

### Page 8

NEW PART NO. QTY ITEM USED PARTNO. INSTRUCTIONS- DISPOSITION
1005323415í001 2
APU One
Start
Limitation
Placard
í í
1005323420í001 1
APU One
Start
Limitation
Placard
í í
Dí436í83 1 Splice Dí436í83 Discard
NOTES: 1. In case of discrepancy between this list and the Service Bulletin Kit
Parts List contained in the respective kit, then the latter 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.
MODEL BDí100í1A10 (CHí300)
Basic Issue: Mar 29/2017 100í49í04
Page 7 of 11

### Page 9

CSB4961000 _003
MODEL BDí100í1A10 (CHí300)
APU Essential Operation Mode Wiring Modification
Figure 1
Basic Issue: Mar 29/2017 100í49í04
P a g e8o f1 1

### Page 10

C
CSB4961000_001
A
A
B
PILOT’S SIDE INSTRUMENT PANEL
0.07 in (1.70 mm)
1 0.10 in
(2.50 mm)
MODEL BDí100í1A10 (CHí300)
APU One Start Limitation Placard Installation
Figure 2 (Sheet 1 of 2)
Basic Issue: Mar 29/2017 100í49í04
Page 9 of 11

### Page 11

C
APU CONTROL PANEL
NO
RESTART
AFTER ABORTED
START  /  FLT
2
0.05 to 0.08 in
(1.30 to  2.00 mm)
CSB4961000_002
B
COPILOT’S SIDE INSTRUMENT PANEL
0.07 in (1.70 mm)
10.10 in
(2.50 mm)
MODEL BDí100í1A10 (CHí300)
APU One Start Limitation Placard Installation
Figure 2 (Sheet 2 of 2)
Basic Issue: Mar 29/2017 100í49í04
Page 10 of 11

### Page 12

B. Parts
No parts required.
C. Material
The materials that follow, or equivalent, are necessary to do this Service Bulletin.
These can be purchased from a local supplier. Bombardier Aerospace does not pay
for these consumables.
DESCRIPTION PARTNO./NAME SPECIFICATION QUANTITY
SUPPLIER
(SEE
NOTE)
Alcohol,
Isopropyl í TTíIí735, GradeA or B As Necessary Code: A
Cloth, NoíLint í í As Necessary Code: A
NOTES: 1. Refer to the table that follows for each suppliers address listed by
codes.
2. 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
No publications required.
MODEL BDí100í1A10 (CHí300)
Basic Issue: Mar 29/2017 100í49í04
Page 11 of 11

### Page 13

100í49í04 Basic Mar 29/2017
MODIFICATION í ENGINE CONTROL SYSTEM í MODIFICATION OF
THE ELECTRONIC CONTROL UNIT (ECU) WIRING HARNESS TO
ENABLE AUTO SHUTDOWN AND TO INHIBIT A SECOND START
ATTEMPT IN FLIGHT
In an effort to improve the quality of our technical communications, we are replacing the
standard Service Bulletin Evaluation Form with an oníline Service Bulletin Survey
and we are requesting your feedback. Please take a moment to fill out our easy oníline
Service Bulletin survey at:
http://csefeedback.aero.bombardier.com
SERVICE BULLETIN EVALUATION FORM
(Your ideas will help us provide better bulletins)
SERVICE BULLETIN: ISSUE: DATED:
TITLE:

### Page 14

SERVICE BULLETIN INCORPORATION SHEET í "100í49í04"
Upon completion of the Service Bulletin, please fillíin, fax to
(514) 855í8798 or eímail to Fracas at fracas.montreal@aero.bombardier.com
If your aircraft is registered on CAMP and you are reporting to them,
please do not send the incorporation sheet to Bombardier. If your aircraft
is on another tracking system, please contact Bombardier to make
arrangements for automated data submission.
100í49í04 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
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.
(dd/mm/yy)
Signature not required if sent by EíMail (dd/mm/yy)

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