# Bombardier Service Bulletin 8-32-176

Copy: Revision A ("U.S. DOT/FAA - SB8-32-176A"), 20 pages: PDF https://openairdocs.org/files/sha256/f7/63/f76348c751f49388d2896d1b091ce3ea180c0170532f992de9c982bb5cf1b1f0; text https://openairdocs.org/service-documents/bombardier/sb-8-32-176/file/f76348c751f4.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2014-0171; AD 2014-06-08 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: 8-32-176
- Latest revision known: 8-32-176, Revision A, dated February 22, 2013 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/bombardier/sb-8-32-176

## ADs that cite it (2) (OpenAirDocs)

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

- [AD 2015-04-08](https://openairdocs.org/ad/2015-04-08.md), effective Apr 27, 2015: Revision A
- [AD 2014-06-08](https://openairdocs.org/ad/2014-06-08.md), effective Apr 14, 2014: Revision A

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-8-32-176/proposed.md).

## Text (20 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2014-0171; AD 2014-06-08 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

Revision ‘A’ 22 Feb 2013
DHC-8 (DASH 8)
SERVICE BULLETIN 8-32-176
Landing Gear - Alternate Downlock Indication System - Introduction of
Fault Monitoring Circuit to Eliminate Possibility of False Indication -
ModSum 8Q101955
NOTE: The initial issue of this service bulletin is not posted on RACS and was
issued to one customer for “release to service” of verification aircraft
serial number 342.
This page transmits Revision ‘A’ of Service Bulletin 8-32-176, pages 1 thru
16 dated 22 Feb 2013.
This service bulletin is re-issued in its entirety for the reasons that follow:
-t h e I n - S e r v i c e p a r t o f t h eEffectivity section is revised to include all DHC-8
aircraft s/n’s (003 thru 672). Was limited to only s/n 342.
-t h e Reason section is revised to make an editorial change in the Cause section.
Was “EDI”, now “EDIS” and provided additional information in the Solution
section.
-t h e Description section is revised to make spelling correction. Was “fight”,
now “flight”
-t h e Compliance section is revised to include a new “ NOTE”
-t h e References section is revised to convey the latest revision of this service
bulletin
-t h e Job Set-Up section is revised to make an editorial change.
Was “sht”, now “sheet”

### Page 2

-t h e Procedure section is revised to make a few editorial changes that follow
in various steps:
Was “Connect / terminate”, now “Connect and/or terminate”
Was “sht”, now “sheet”
Was “a” now “an”
Was “turn”, now “rotate”
step (5) is deleted
step (6) is revised to provide details on how to do a continuity check and
provide a maximum resistance limit.
The Compliance in the previous issue(s) of this service bulletin is not affected by
this revision. No additional rework to the aircraft is introduced by this revision.
Remove the initial issue of Service Bulletin 8-32-176 and replace with attached.
Previous issue(s) of Service Bulletin 8-32-176:
Initial issue - Pages 1 thru 16 dated 11 Feb 2013

### Page 3

D
S.B. 8-32-176
Page 1 of 16
11 Feb 2013
LSRevision ‘A’ 22 Feb 2013
SERVICE BULLETIN
Customer
Support
ATA SYSTEM: 3261 NUMBER: 8-32-176
BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS
SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND
URGES OPERATORS TO PROMPTLY EVALUATE THE CONTENTS
SUBJECT: Landing Gear - Alternate Downlock Indication System - Introduction
of Fault Monitoring Circuit to Eliminat e Possibility of False Indication
- ModSum 8Q101955
1. PLANNING INFORMATION
A. Effectivity
Aircraft Affected:
In-Service: DHC-8 Aircraft Models 102, 103, 106, 201, 202, 301, 311, 314
and 315 Serial Numbers 003 thru 672 with Mod 8/0235,
8/0461 and 8/0534 installed.
Verification: ModSum 8Q101955 has been installed on DHC-8 Aircraft
Model 311 Serial Number 342.
NOTE: The instructions in this service bulletin are only applicable to the systems
and parts installed at the time of delivery on the aircraft or as changed by
Bombardier Aerospace Service Bulletin(s). Before you do this bulletin,
examine all STC or equivalent action changes to make sure this bulletin
can be completed.
Spares Affected:
None

### Page 4

SERVICE BULLETIN 8-32-176
S.B. 8-32-176
Page 2 of 16
11 Feb 2013
LSRevision ‘A’ 22 Feb 2013
B. Reason
Problem: One operator has recently experienced an incident and reported that the
emergency downlock indication system (EDIS) had given a false “down
and locked” indication when the landing gear was not downlocked.
Cause: Analysis of the EDIS indicates that a false indiction, regardless of the
condition of the landing gear, can be caused by a failure of the
photo-transistors or wiring, or the presence of scattered ambient light.
Solution: This service bulletin introduces ModSum 8Q101955.
The ModSum introduces a fault monitoring circuit to the EDIS. When the
EDIS is in the normally off position and the aircraft is in the air, relays
monitor each channel. When a ground signal that would provide a false
locked down indication is detected by the relay, after a few seconds
another relay is latched to turn on a new caution light and inhibit the
affected EDIS channel from illuminating.
A WOW signal and time delay relay is used to enable the fault monitoring
circuit only when the aircraft is the air, such that landing gear transition
conditions and scattered light from ground mounted light sources are not
falsely annunciated as faults.
An intermediate relay/diode/resist or panel assembly is introduced to be
put in between the EDIS and the aircraft wiring. The existing EDIS switch
is replaced with p/n MS24523-33. A new connection to the caution and
warning panel is added for indication, and another connection is made to
the relay panel for the WOW signal.
C. Description
The procedures in this service bulletin give the instructions to do the tasks that
follow:
- the aircraft electrical system is de-energized
- lock pins are installed through each main gear and main gear door mechanism
- the nose gear ground lock is engaged
- the terminal connector from the Main and Auxiliary batteries are disconnected
- flight compartment ceiling panels (pilot s side) and overhead console instruments
are removed for access to the annunciator (caution and warning) panel cable
assemblies
- front lower access panel 122BR is removed

### Page 5

SERVICE BULLETIN 8-32-176
S.B. 8-32-176
Page 3 of 16
11 Feb 2013
LSRevision ‘A’ 22 Feb 2013
- the forward panel of the wardrobe is opened
- access is gained to the relay panel No. 1, 2 and 3 as applicable
- relay panels are released (as required) to provide access to the wiring and relay
base plates
- the lavatory is removed to gain access to aft side of co-pilot bulkhead
- a connector bracket p/n 82411123-101 is installed to bulkhead
- two existing tooling holes are prepared for ground stud installation
- the flight compartment center floor panel is removed
- the existing filter at position 55 on the Annunciator Panel is replace with filter p/n
25-1195-122
- cable assemblies 8Z9678-011, -013 and -015 (post mod 8/1485 100 series only) are
installed
- existing wiring is reterminated as required
- r e l a yp a n e lN o .1i sr e - a t t a c h e d
- continuity check of the wiring is done
- the battery terminal connector is re-connected to the Main and Auxiliary battery
- functional test procedure is completed
- the lavatory is installed
- all access panels, floor panels, overhead console and ceiling panels are re-installed
and closed
- close out.
D. Compliance
Bombardier Inc. highly recommend that ModSum 8Q101955 be incorporated at
the earliest opportunity unless otherwise directed by the operator’s airworthiness
authority.
A Transport Canada Airworthiness Directive is Pending.
NOTE: Do Service Bulletin 8-32-173 (Landing Gear - Special Inspection and
Rectification - Alternate Downlock Indication System) before
commencing this modification to ensure there are no dormant faults
with ALT IND SYS which otherwise delay the incorporation of this
Service Bulletin 8-32-176.

### Page 6

SERVICE BULLETIN 8-32-176
S.B. 8-32-176
Page 4 of 16
11 Feb 2013
LSRevision ‘A’ 22 Feb 2013
E. Approval
The technical content of this service bulletin has been approved under the
authority of the Transport Canada Civil Aviation (TCCA) Design Approval
Organization No: DAO #93-Q-02.
This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage
Tolerance Inspections (DTIs).
F. Manpower
It will take an estimated 40 man-hours to complete this service bulletin. The
breakdown of the man-hours is shown in the table that follows:
TASK MAN-HOURS
Job Set-Up 18.00
Procedure 10.00
Test/RTS 2.00
Close-Out 10.00
For any on-site labor assistance, please speak with a Fleet Services representative
for a quote. The Fleet Services group can be contacted via the Q Series Technical
Help Desk by telephone at 416-375-4000 or email at:
thd.qseries@aero.bombardier.com
G. Material - Price and Availability
The ModKit listed in the table below is available through the Customer Accounts
Service Team at Bombardier Aerospace Regional Aircraft division. Operators
should submit a purchase order specifying aircraft serial number(s) to:
Bombardier Aerospace
Customer Accounts Services Team (Mail Stop N11-32)
123 Garratt Blvd.
Toronto
Ontario
Canada M3K-1Y5
Facsimile: (416) 375-3060
Telephone: (416) 375-3920
Kit Number Description
8MK4456-001 Kit - Redesign of EDIS to Eliminate
Possibility of False Indication

### Page 7

SERVICE BULLETIN 8-32-176
S.B. 8-32-176
Page 5 of 16
11 Feb 2013
LSRevision ‘A’ 22 Feb 2013
H. Tooling - Price and Availability
None
I. Weight and Balance
A/C Type and Model Weight (Lb) Arm (Inches)
Moment
(Inches x Lb)
x 0.001
DHC-8 Model 102, 103 &
106
(Pre Mod 8/1485)
+2.10 182.40 +0.38
DHC-8 Model 102, 103 &
106
(Post Mod 8/1485)
+2.23 183.98 +0.41
DHC-8 Model 201 & 202 +2.10 182.40 +0.38
DHC-8 Model 301, 311,
314 & 315
+2.10 109.40 +0.23
J. Electrical Load Data
1. Direct Current (DC) Load Change
Item Equipment Bus Bus Code Load Operating
Condition
32D1 NLG ADI
FLR MNT
RLY (0.16)
28 V DC Right
Essential Bus
H2 +0.00 Amps N/A
32D2 LMLG ADI
FLR MNT
RLY (0.16)
28 V DC Right
Essential Bus
H2 +0.00 Amps N/A
32D3 RMLG ADI
FLR MNT
RLY (0.16)
28 V DC Right
Essential Bus
H2 +0.00 Amps N/A

### Page 8

SERVICE BULLETIN 8-32-176
S.B. 8-32-176
Page 6 of 16
11 Feb 2013
LSRevision ‘A’ 22 Feb 2013
2. Alternating Current (AC) Load Change
Item Equipment Bus Bus
Code
Phase VA PF Load Operating
Conditions
N/A N/A N/A N/A N/A N/A N/A N/A N/A
K. Publications Affected
Aircraft Operating Data Manual PSM 1-81-1 and.......................
PSM 1-82-1 and
PSM 1-83-1
Flight Manual PSM 1-81-1A and......................................
PSM 1-82-1A and
PSM 1-83-1A
PSM 1-82-1B and
PSM 1-83-1B
Maintenance Manual PSM 1-8-2 and................................
PSM 1-82-2 and
PSM 1-83-2
Wiring Diagrams Manual PSM 1-8-2W and............................
PSM 1-82-2W and
PSM 1-83-2W
Weight and Balance Manuals PSM 1-8-8 and........................
PSM 1-82-8 and
PSM 1-83-8
Dash 8 Illustrated Parts Catalogue PSM 1-8-4 and....................
PSM 1-82-4 and
PSM 1-83-4
Modifications Manual PSM 1-813-12...............................

### Page 9

SERVICE BULLETIN 8-32-176
S.B. 8-32-176
Page 7 of 16
11 Feb 2013
LSRevision ‘A’ 22 Feb 2013
L. References
Revision ‘A’ of this service bulletin was prepared to the engineering drawings and
related data that follows:
DRAWING SHEET REV
8MK4456 1 B
8Z8602 1 --
8Z9678 1 F
8Z9678 2 A
8Z9678 3 A
8Z9678 4 --
8Z9678 5 B
8Z9678 6 --
8Z9678 7 B
82411123 1 --
82411122 1 --
ModSum 8Q101955 Rev. ‘H’
PCA 06824 Revision 1 (for internal reference only)
Transport Canada Airworthiness Directive Pending
Bombardier Inc. Modification 8/0235 (Service Bulletin 8-39-03)
Bombardier Inc. Modification 8/0534 (Service Bulletin 8-32-41 Rev. A)
Bombardier Inc. Modification 8/0461 and 8/0820 (Service Bulletin 8-32-42 Rev. A)
Bombardier Inc. Service Bulletin 8-32-173
A Transport Canada Airworthiness Directive is Pending.

### Page 10

SERVICE BULLETIN 8-32-176
S.B. 8-32-176
Page 8 of 16
11 Feb 2013
LSRevision ‘A’ 22 Feb 2013
2. MATERIAL INFORMATION
A. Parts Required Per Aircraft
(1) Modification Kit 8MK4456-001
(2) Detailed Kit Content:
Quantity Per Kit
-001
Part Number Description Remarks
2 NAS1801-3-16 Screw
2 CSP192-6-00 Washer
2 M7885/6-4-2 Rivet
2 B0816031-002 Tie Mount or Click Bond
CB3019AA3N
3 B0205016AD4-4S Rivet
1 8Z8602 Drawing-EDIS
Bracket Instln
Drawing Only
1 82411123 Drawing-EDIS
Conn Bracket
Drawing Only
1 82411123-101 Bracket
1 82411122 Drawing-EDIS
Relay Bracket
Drawing Only
1 B0816035AA3N Tie Mount or Click Bond
CB3019AA3N
2 NAS1149D0363J Washer
4 NAS1149D0316J Washer
2 MS35650-302 Nut
2 MS35338-43 Lock Washer
500 MS3367-1-9 Tie Wrap Quantity may
be surplus to
account for
losses
2 MS21042L3 Nut, Self Locking
2 NAS1801-3-10 Screw
1 25-1195-122 Filter

### Page 11

SERVICE BULLETIN 8-32-176
S.B. 8-32-176
Page 9 of 16
11 Feb 2013
LSRevision ‘A’ 22 Feb 2013
Quantity Per Kit
-001
RemarksDescriptionPart Number
1 CSP255-3261-K10 Label For A/C Post
Mod 8/1485
1 CSP255-3262-P4B Label
1 CSP255-3262-P4 Label
1 CSP255-3262-J4A Label
1 CSP255-3262-GS1 Label
1 CSP255-3262-GS2 Label
1 SO-1066-001 Relay Base For A/C Post
Mod 8/1485
1 Y-D4N Relay For A/C Post
Mod 8/1485
1 MS24523-33 Switch
1 8Z9678-015 Cable Assembly For A/C Post
Mod 8/1485
1 8Z9678-013 Cable Assembly
1 8Z9678-051 Relay Assembly
1 8Z9678 Drawing-EDIS
Wiring
Drawing Only
(3) In addition to the above part(s), the following material(s) are required for the
completion of this service bulletin and may be procured as single items from
Bombardier Aerospace Regional Aircraft or purchased directly from industry
sources.
Addresses of manufacturers and suppliers not shown below are listed in
either Maintenance Manual Chapter 20 or in Structural Repair Manual Chapter
51 or, for 400 Series Aircraft, in Consumable Products Manual PSM 1-84-18.
Part Number Qty. Per Aircraft Description Remarks
MIL-C-5541 1/2 Quart Alodine 1200 C1 - Chemical Con-
version Coating
DHMS C4.01 As Required Epoxy Primer Type 2
(F19)

### Page 12

SERVICE BULLETIN 8-32-176
S.B. 8-32-176
Page 10 of 16
11 Feb 2013
LSRevision ‘A’ 22 Feb 2013
Part Number Remarks DescriptionQty. Per Aircraft
DHMS C4.04
(F24)
As Required Enamel, Polyure-
thane
B. Parts Required to Modify Spares
None
C. Special Tools and Equipment Required
None
D. Existing Parts Accountability
The following parts may be affected by this service bulletin. Indented parts are
components of the next higher assembly. The quantity (Qty.) column lists the
quantity that may be affected per aircraft for non-indented parts and the quantity
p e rn e x th i g h e ra s s e m b l yf o ri n d e n t e dp a r t s .
Existing
Part Number Description Qty. IC DC
New Part
Number PNC
85311889 Web, RH Upper
Bulkhead
1 C RWK 8Z8602-001 R
MS24523-24 Switch 1 B DIS MS24523-33 N
IC Interchangeability Code
A Not interchangeable.
B Removed Part. No direct replacement.
C Conditionally Interchangeable. Inst allation of superseded part negates the
intent of this service bulletin.
DC Disposition
DIS Discard Part.
MUI Multiple Usage Item: Return to stock if serviceable.
RWK Rework existing part in accordance with this service bulletin.
RWI Rework existing part per .....
SAL Salvage. Return to operator’s stores for salvage consideration.
PNC Part Number Code
N No equivalent Bombardier Inc. part number for reworked part. Indicate on
part that this service bulletin has been accomplished.
R Part number after rework.
S Superseding or equivalent part number.
X Reworked part and superseding part are functionally and physically
equivalent but not identical.

### Page 13

SERVICE BULLETIN 8-32-176
S.B. 8-32-176
Page 11 of 16
11 Feb 2013
LSRevision ‘A’ 22 Feb 2013
3. ACCOMPLISHMENT INSTRUCTIONS
NOTE: Do Service Bulletin 8-32-173 (Landing Gear - Special Inspection and
Rectification - Alternate Downlock Indication System) before
commencing this modification to ensure there are no dormant faults
with ALT IND SYS which otherwise delay the incorporation of this
Service Bulletin 8-32-176.
A. Job Set-Up
(1) Placard and select all aircraft electrical power to OFF. Obey all relevant
WARNINGS and CAUTIONS detailed in Maintenance Manual PSM 1-8-2, 1-82-2
or 1-83-2 Chapters 12 and 24.
(2) Make sure that lock pins are installed through each main gear and main gear
door mechanism.
(3) Make sure the nose gear ground lock is engaged.
(4) Remove access panel 122BR from the front lower fuselage - right side.
(5) Disconnect the terminal connector from the Main and Auxiliary battery.
(6) Remove the flight compartment Co-Pilot’s ceiling panel.
(7) Remove flight compartment overhead console instruments as required to gain
access to annunciator (caution and warning) panel cable assemblies.
(8) Remove the flight compartment center floor panel.
(9) Open Landing Gear Alternate Extension Door.
(10) For Dash 8 Series 100 and 200, remove panel from wardrobe for access to
Relay Panel No. 1. For Dash 8 Series 300, remove panels from the wardrobe to
gain access to relay panels No. 3 (refer to drawing 8Z9678 sheet 6 for applicable
relay panel location).
(11) For Dash 8 Series 100 and 200, remove and keep fasteners securing relay panel
No. 1. Pull panel out far enough to gain access to the wiring and relay base
plates. Support and hang the relay panel temporarily with a tie wrap or
equivalent.

### Page 14

SERVICE BULLETIN 8-32-176
S.B. 8-32-176
Page 12 of 16
11 Feb 2013
LSRevision ‘A’ 22 Feb 2013
(12) Remove the lavatory (refer to applicable instructions in PSM 1-8-2 or 1-83-2
Chapter 25-40-01 or PSM 1-82-2 TASK 25-41-05-000-801 or TASK
25-41-07-000-801).
B. Procedure
(1) Gain access to the aft side upper right hand corner of the co-pilots bulkhead
web at Station X182.00 (refer to dwg 8Z8602).
(2) Install bracket 82411123-101 to bulkhead using 3 rivets B0205016AD4-4S and
prepare two existing tooling holes (for ground studs) to agree with all of the
Notes and detail views given on drawing 8Z8602. Make sure to treat newly
opened hole edges with alodine and apply a layer of epoxy primer or
polyurethane enamel as directed per flagnotes 4 & 5 .
(3) Make sure to re-identify the web 85311889 as 8Z8602-001.
(4) Gain access to the Annunciator Panel. Remove the existing filter at position 55
of the panel and replace with filter P/N 25-1195-122 to agree with all of the Notes
and detail views given on the drawing 8Z9678 sheet 1 view labeled VIEW ON
ANNUNCIATOR PANEL.
NOTE: To change the filter in the module, pop out filter in position 55 from the
back. Apply a small drop of Loctite 430 to the back of each corner of the
new filter and secure in space position 55.
(5) Deleted
(6) Install Cable Assembly 8Z9678-011 as follows:
(a) Gain access to the rework area on the upper right hand corner of bulkhead at
Station X182.00 (refer to drawing 8Z9678 sheets 5 & 7 for location).
(b) Remove hardware and clamps (qty 3) used to secure existing cable assembly

### Page 15

SERVICE BULLETIN 8-32-176
S.B. 8-32-176
Page 13 of 16
11 Feb 2013
LSRevision ‘A’ 22 Feb 2013
to the terminal block panel (refer to 8Z9678 sheet 5 view A and flagnote 7
for location).
(c) Set relay bracket 82411122-101 on the terminal block as shown on 8Z9678
sheet 5 view A. Rotate clamps and move the cable assembly as described in
flagnote 7 and 8 .
(d) Align mounting holes in relay bracket 82411122-101 and clamps with the
mounting holes in the terminal block panel. Make sure the wire looms are
facing outboard to the aircraft and the clamps and cable assembly are
positioned per step above.
(e) Using kept hardware and a washers CSP192-6-00 under each clamp secure
relay bracket 82411122-101 and clamps to the terminal block panel.
(f) Install the relay assembly 8Z9678-051 to the terminal block panel (refer to
drawing 8Z9678 sheet 7 DETAIL EB).
(g) Assemble and install new cable assembly 8Z9678-011 to agree with all the
notes and views on drawing 8Z9678 sheet 2, 5 & 7.
(h) Secure all electrical connections.
(i) Apply the identification labels where applicable (refer to applicable NOTES
and detail view on drawing 8Z9678 sheet 1 (flagnotes 4 and 5 ), sheet
2&7 ) .
(j) Secure ground wires the two ground studs (refer to drawing 8Z9678 sheet 7
DETAIL VIEW EA).
(k) Install tie mount (click bond fastener) B081635AA3N in the noted area on
drawing 8Z9678 sheet 7 FN 66.
(7) Install Cable Assembly 8Z9678-013 as follows:
(a) Open the Landing Gear Alternate Extension Door.
(b) Loosen and remove locknuts securing emergency gear downlock indicator

### Page 16

SERVICE BULLETIN 8-32-176
S.B. 8-32-176
Page 14 of 16
11 Feb 2013
LSRevision ‘A’ 22 Feb 2013
light control toggle switch assembly (refer to drawing 8Z9678 sheet 4 detail
VIEW E for location)..
(c) Disconnect wires from existing switch for retermination. Remove and discard
the existing switch MS24523-24.
(d) Install the new switch MS24523-33 (3262-S1).
(e) Install new cable assembly 8Z9678-013 and reterminate existing wires to
agree with all of the Notes and detail views given on drawing 8Z9678 sheet 3 &
6.
(f) If additional workspace is required remove LRU’s from the upper section of
the wardrobe.
NOTE: Cable Assembly 8Z9678-015 is for aircraft with post Mod 8/1485
only.
(8) For aircraft with post Mod 8/1485, install new cable assembly 8Z9678-015 to
agree with all of the Notes and detail views given in drawing 8Z9678 sheet 3.
(9) Re-install the relay panel No. 1.

### Page 17

SERVICE BULLETIN 8-32-176
S.B. 8-32-176
Page 15 of 16
11 Feb 2013
LSRevision ‘A’ 22 Feb 2013
(10) Do a continuity check of the new and the existing wires shown on drawing
8Z9678 sheet 2 & 3 as follows:
(a) Connect the negative (-) lead of an ohmmeter to one end of a wire to be tested
and the positive lead (+) of the ohmmeter to the opposite end of the same
wire.
(b) For long distance checking of a wire connect one end of a wire to be tested to
the positive lead (+) of an ohmmeter and the other end of the wire to a ground
point with a jumper wire. Connect the negative lead (-) of the ohmmeter to the
same ground point.
(c) A complete circuit (or closed circuit) from point to point must exist through
each wire. The maximum resistance permitted between the two points in a
closed circuit is 5 ohms.
NOTE: Continuity of a circuit is affected when a diode is part of a circuit. When
checking continuity across a diode the electrical polarity must be
observed.
Continuity of a circuit is affected when a resistor is part of a circuit. When
checking continuity across a resistor the value of the resistor must be
observed as follows:
R10, R20 & R30 are 510 ohms +/- 10% each
R11, R12 & R13 are 500K ohms +/- 10% each
R40 is 820K ohms +/- 10%.
Continuity of a circuit is also affected when a circuit contains computer
controllers, valves, relays, coils, circuit breakers, etc. Temporarily
disconnect or remove all the electrical components connected to the
wires to be tested. Reconnect components after testing.
(d) If the resistance exceeds 5 ohms from point to point (open circuit) recheck the
new and reworked wiring to make sure it is terminated to the correct
connection, check the wiring for mechanical damage, loose connector parts,
bent pins and corrosion. Correct the deficiency.
(11) Connect the battery terminal connector to the Main and Auxiliary battery. Make
sure to safety the battery terminal connector with copper lockwire.
CAUTION: DO NOT APPLY HYDRAULIC POWER DURING THIS FUNCTIONAL
TEST.

### Page 18

SERVICE BULLETIN 8-32-176
S.B. 8-32-176
Page 16 of 16
11 Feb 2013
LSRevision ‘A’ 22 Feb 2013
(12) Do the Functional Test Procedure of the Alternate Gear Indication Fault
Monitoring system (refer to drawing 8Z9678 sheet 1).
C. Close Out
(1) Remove all tools and equipment from the work area.
(2) Install the lavatory (refer to applicable instructions in PSM 1-8-2 or 1-83-2
Chapter 25-40-01 or PSM 1-82-2 TASK 25-41-05-400-801 or TASK
25-41-07-400-801).
(3) Re-install LRU’s that were previously removed from the upper wardrobe to agree
with applicable instructions in the AMM.
(4) Re-install flight compartment center floor panels and cockpit ceiling panel.
(5) Install all access panels and the overhead console that were previously removed
or opened to do the tasks.
(6) On incorporation of this ModSum add the weight and balance data shown in
Section 1 of this service bulletin to the Weight and Balance Manual PSM 1-8-8 or
PSM 1-82-8 or PSM 1-83-8 or PSM 1-84-8. Under ‘Description of Change’ enter
“ModSum 8Q101955 incorporated.”
(7) On incorporation of this ModSum make an entry that conforms to local
regulatory requirements in the applic able logbook(s). If only part of this
ModSum is completed, use only this service bulletin number as reference and
detail exact limit of work completed. Enter component serial numbers if
applicable. Enter this ModSum number only after complete and functional
incorporation of all work defined in this service bulletin.
1

### Page 19

Jan 2009
SERVICE BULLETIN (SB) - - - RECORD OF INCORPORATION
- - - Q SERIES DASH 8 AIRCRAFT
To : CMDB Focal
Facsimile: (1) 416 375 4538
E- -mai l: cmdb.requests@aero.bombardier .com
From:
Company:
Phone: Extn:
Facsimile: Date:
E- -mai l:
The data that you provide below will help us record the incorporation of this ModSum
and the aircraft effectivity in the maintenance manual.
Operator: Service Bulletin: __________________ Revision: _________
Aircraft Serial Number: Model Number: Date Bulletin Completed:
Aircraft Serial Number: Model Number: Date Bulletin Completed:
Aircraft Serial Number: Model Number: Date Bulletin Completed:
Aircraft Serial Number: Model Number: Date Bulletin Completed:
Aircraft Serial Number: Model Number: Date Bulletin Completed:
Aircraft Serial Number: Model Number: Date Bulletin Completed:
Aircraft Serial Number: Model Number: Date Bulletin Completed:
Aircraft Serial Number: Model Number: Date Bulletin Completed:
Aircraft Serial Number: Model Number: Date Bulletin Completed:
Aircraft Serial Number: Model Number: Date Bulletin Completed:
Aircraft Serial Number: Model Number: Date Bulletin Completed:
Aircraft Serial Number: Model Number: Date Bulletin Completed:
Fax this sheet to (1) 416 375 4538 or Email PDF to:
cmdb.requests@aero.bombardier.com

### Page 20

Feb 2009
SERVICE BULLETIN (SB) - - - COMMENT SHEET - - - Q SERIES DASH 8 AIRCRAFT
To : SB Focal (T oronto), Bombardier Aerospace Commercial Aircraft
Phone: (1) 416 375 4078 Facsimile: (1) 416 375 4538
E- -mai l: syed.rizvi@aero.bombardier .com
From:
Company:
Phone: Extn:
Facsimile: Date:
E- -mai l:
Select appropriate box(es) and add comments or suggestions you would like us to know
that may enhance the quality of our service bulletins.
Service Bulletin: Revision: ModSum:
1. PLANNING INFORMATION
V Effectivity V Reason V Description V Compliance
V Approval V Manpower V Material V Weight and Balance
V Electrical Load V T ooling V References V Publications Affected
2. MATERIAL INFORMATION
V Kit Content V Special T ools/Equipment V Parts to Modify Spares
V Consumables V Disposition of Existing Parts V Other
3. ACCOMPLISHMENT INSTRUCTIONS
V J o b S e t --- U p V Procedure V Close- - -Out V Te s t
V Illustration(s) V Other
4. COMMENTS, REMARKS, SUGGESTIONS
Fax this sheet to (1) 416 375 4538 or Email PDF to:
syed.rizvi@aero.bombardier.com

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