# Bombardier Service Bulletin 84-30-10

Copy: Revision E ("84-30-10E"), 32 pages: PDF https://openairdocs.org/files/sha256/35/4d/354d44e4fd849b67a45f7cc268cb8826310dfa9f091aeff2aa14592b0c8bb512; text https://openairdocs.org/service-documents/bombardier/sb-84-30-10/file/354d44e4fd84.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2016-6148; AD 2016-19-11 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: 84-30-10
- Latest revision known: 84-30-10, Revision E, dated October 10, 2014 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/bombardier/sb-84-30-10

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

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

- [AD 2016-19-11](https://openairdocs.org/ad/2016-19-11.md), effective Nov 2, 2016: Revisions A, B, C, D and E

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-84-30-10/proposed.md).

## Text (32 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2016-6148; AD 2016-19-11 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 ‘E’ 10 Oct 2014
DHC-8 (DASH 8)
SERVICE BULLETIN 84-30-10
Ice & Rain Protection - Air Intake Thermostat - Relocation In Front
Fuselage - ModSum 4-126402
This page transmits Revision ‘E’ of Service Bulletin 84-30-10 pages 1 thru 28
dated 10 Oct 2014.
This service bulletin is re-issued in its entirety for the reasons that follow:
- the Compliance section is revised to indicate that a Transport Canada
Directive is pending
- the References section is revised to convey the latest revision of the service
bulletin and engineering documentation, and to indicate that the Transport
Canada Directive is pending
Remove the previous issue of Service Bulletin 84-30-10 and replace with
attached.
Previous issue(s) of Service Bulletin 84-30-10
Initial issue - Pages 1 thru 26 dated 07 Sep 2007
Revision ‘A’ - Pages 1 thru 28 dated 07 Apr 2008
Revision ‘B’ - Pages 1 thru 28 dated 20 Jan 2010
Revision ‘C’ - Pages 1 thru 28 dated 14 Jul 2011
Revision ‘D’ - Pages 1 thru 28 dated 20 Dec 2011

### Page 2

(No text on this page.)

### Page 3

D
S.B. 84-30-10
Page 1 of 28
07 Sep 2007
RR
Revision ‘E’ 10 Oct 2014
SERVICE BULLETIN
Customer
Support
ATA SYSTEM: 3021 NUMBER: 84-30-10
BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS
SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND
URGE OPERATORS TO PROMPTLY EVALUATE THE CONTENTS
SUBJECT: Ice & Rain Protection - Air Intake Thermostat - Relocation In Front
Fuselage - ModSum 4-126402
1. PLANNING INFORMATION
A. Effectivity
Aircraft Affected:
In-Service: DHC-8 Aircraft Models 401 and 402 Serial Numbers 4003,
4004, 4006, 4008 thru 4184.
Production: ModSum 4-126402 will be installed before delivery on
applicable DHC-8 Aircraft at Serial Number 4185 and
subsequent.
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.

### Page 4

SERVICE BULLETIN 84-30-10
S.B. 84-30-10
Page 2 of 28
07 Sep 2007
RR
Revision ‘E’ 10 Oct 2014
Spares Affected:
None
B. Reason
Problem: While troubleshooting a malfunctioning No. 2 engine intake heater
circuit, an operator had discovered that the engine intake heater circuit
thermostats and the aircraft skin where the thermostats are installed had
corroded. The corrosion had progressed completely through the
fuselage skin structure where the thermostats made contact with the
aircraft fuselage skin.
Cause: The thermostats are installed in a location that is prone to moisture
pooling and insufficient sealing of the installation to prevent corrosion.
Solution: This service bulletin conveys ModSum 4-126402.
The ModSum relocates existing thermostat from a lower position on the
aircraft skin at X-54.00 between stringers 31P and 32P (next to the
centerline) to a higher position at X-54.00 between stringers 26P and
27P.
Moisture is less likely to pool or accumulate in the higher location.
C. Description
The procedures in this service bulletin give the instructions to do the tasks that
follow:
- all aircraft electrical power is switched OFF
- lock pins are installed thru each main gear and main gear door mechanism
- the nose gear ground lock is engaged
- access panel 121DZ and related cover are removed
- the existing thermostat in the underfloor area at station X-54.00 between
stringers (STG) 31P and 32P is removed
- the existing thermostat bracket assembly 82410004-001 is discarded
- the two support brackets attached to stringers 31P and 32P are left in place
- a visual inspection for signs of corrosion and deterioration on the thermostat
4100S025 exterior mounting surface and mating surface of fuselage skin is
accomplished

### Page 5

SERVICE BULLETIN 84-30-10
S.B. 84-30-10
Page 3 of 28
07 Sep 2007
RR
Revision ‘E’ 10 Oct 2014
- a new (or existing) thermostat, thermostat bracket assembly 82410004-003,
related angle brackets 85313619-001 and 85313630-001 and SPC nut plates
B0204037AL-4W are installed at new location X-54.00 between stringers 26P
and 27P
- related wiring is re-routed, re-identified and secured using tie wraps and clamps
- sections of the wiring are protected with spiral wrap
- existing label p/n 81111200 (thermostat location label) is removed from aircraft
exterior (front fuse left side). New label 81111200-101 is installed
- access panel 121AZ and related cover are installed
- log book entries are made
D. Compliance
Bombardier Inc. recommends incorpora tion of ModSum 4-126402 at the earliest
opportunity unless otherwise directed by the operator’s airworthiness authority.
A Transport Canada Airworthiness Directive is Pending.
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 12 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 0.50
Procedure in Part A 8.00
Test / RTS 3.00
Close-Out 0.50

### Page 6

SERVICE BULLETIN 84-30-10
S.B. 84-30-10
Page 4 of 28
07 Sep 2007
RR
Revision ‘E’ 10 Oct 2014
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
ModKit 8MK4377-001 and 8MK4377-051 are available through the Customer
Accounts Service Team at Bombardier Aerospace Regional Aircraft division.
Operators should submit a purchase order s pecifying 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 Price (US$) Delivery
8MK4377-001 Structural Provisions
Front Fuselage
Thermostat Retrofit
Quoted at
time of order
Will be given
at time of
order
8MK4377-051 Label - Thermostat
Location Delta Kit
Quoted at
time of order
Will be given
at time of
order
NOTE: Both Kits listed in the above table are required to complete the rework.
H. Tooling - Price and Availability
None
I. Weight and Balance
None
J. Electrical Load Data
Not affected

### Page 7

SERVICE BULLETIN 84-30-10
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Page 5 of 28
07 Sep 2007
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Revision ‘E’ 10 Oct 2014
K. Publications Affected
Maintenance Manual PSM 1-84-2................................
Wiring Diagrams Manual PSM 1-84-2W............................
Dash 8 Illustrated Parts Catalogue PSM 1-84-4....................
ModSums Manual PSM 1-84-12..................................
L. References
Revision ‘E’ of this service bulletin was prepared to the engineering drawings and
related data that follows:
DRAWING SHEET REV
8MK4377 1 C
8Z4846 1 A
8Z4868 1 B
8Z4868 2 A
ModSum 4Q126402 Rev. ‘D’
ModSum 4-126402 Rev. ‘C’
PCA 41518 Revision 3 (for internal reference only)
Bombardier Inc. Service Bulletin 84-30-09 - Engine Air Intake Heater Circuit -
Corrosion of Thermostat - Special Inspection/Rectification
A Transport Canada Airworthiness Directive is Pending.
2. MATERIAL INFORMATION
A. Parts Required Per Aircraft
(1) Detailed Kit Content for Modification Kit 8MK4377-001:
NOTE: Installation of Modification Kit 8MK4377-001 and Delta Kit 8MK4377-051
are required to incorporate the intent of ModSum 4-126402.

### Page 8

SERVICE BULLETIN 84-30-10
S.B. 84-30-10
Page 6 of 28
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Revision ‘E’ 10 Oct 2014
Quantity Per Kit
-001
Part Number Description Remarks
2 4100S025 Thermostat
1 82410004-003 Thermostat Bracket
4 AN960D10L Washer
8 M39029/1-101 Contact Pin
5 TMC-SCE/16-2. 0-9 Ident Tape
10 inch 2E125SCL9 Spiral Wrap
6 CSCS-M Cross Spacer
6 CR4H Connector Ring
60 MS3367-1-9 Tiedown Strap
3 MS21919WDG2 Clamp
2 NAS1149D0316J Washer
1 NSA1801-3-5 Hex Head Screw
4 NAS5903-7 Screw
2 B0204037AL-4W SPC Nut Plate
4 B0205016AD4-4S Solid Rivet See Note
6 B0205016AD4-5S Rivet See Note
1 85313619-001 Angle Bracket
1 85313630-001 Angle Bracket
1 8Z4868 Structural Provisions Drawing
1 8Z4846 Structural Provisions Drawing
1 8MK4377 Structural Provisions
Front Fuse. Thermo-
stat Retrofit
Drawing
NOTE: Rivets MS20470AD4 may be used in lieu of B0205016AD4 rivets.
(2) Detailed Kit Content for Modification Kit 8MK4377-051 (Delta Kit -051):
Quantity Per Kit
-051
Part Number Description Remarks
2 81111200-101 Label - Thermostat
Locations

### Page 9

SERVICE BULLETIN 84-30-10
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Page 7 of 28
07 Sep 2007
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Revision ‘E’ 10 Oct 2014
(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
DHMS S3.01 500 mL or less Class B1/2 or B2
Type I or II
Sealant
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
82410004-001 Bracket 1 A DIS 82410004-003 S

### Page 10

SERVICE BULLETIN 84-30-10
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Revision ‘E’ 10 Oct 2014
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 part number.
X Reworked part and superseding part are functionally and physically
equivalent but not identical.
3. ACCOMPLISHMENT INSTRUCTIONS
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 1-84-2.
(2) Make sure that lock pins are installed thru each main gear and main gear door
mechanism.
(3) Make sure the nose gear ground lock is engaged.
B. Procedure
NOTE: For operators that have incorporated the previous issue of this SB
and have not installed replacement label 81111200-101 (offered by
Delta Kit 8MK4377-051) refer to the la bel replacement instructions at
the end of this Procedure section.

### Page 11

SERVICE BULLETIN 84-30-10
S.B. 84-30-10
Page 9 of 28
07 Sep 2007
RR
Revision ‘E’ 10 Oct 2014
Structural Provisions - Rework / Installation
(1) Remove thermostat bracket assembly 82410004-001 (Pre Mod) as follows:
(a) Remove and retain Center Pedestal Floor access panel 121DZ and related
floor covering (Refer to AMM TASK 06-43-00-992-801).
NOTE: Removal of Hand Pump Access Door panel 122DZ may make it easier to
do the rework (Refer to AMM TASK 06-43-00-992-806).
(b) Locate existing thermostat in the underfloor area at approx.. X-54.00
between stingers (STG) 31P and 32P (Refer to Figure 1).
(c) Remove and discard existing screws, washer, clamp and spacer used to
secure the thermostat bracket assembly 82410004-001 to the fuselage
support brackets on stringer 31P and 32P.
(d) Lift bracket 82410004-001 a small distance then remove thermostat from
transfer tape.
(e) Disconnect thermostat lead wires from quick disconnect.
(f) Discard bracket assembly 82410004-001. Leave existing support brackets
on stringer 31P and 32P in place.
(2) Visually inspect the thermostat 4100S025 exterior mounting surfaces (area of
thermostat that touches fuselage skin) for any signs of corrosion or
deterioration.
(a) If no corrosion or deterioration is found keep thermostat for re-installation.
(b) If thermostat is slightly corroded, remove and discard. Install new
thermostat 4100S025 as required.
(3) Visually inspect the fuselage skin surface (at X-54.000 between stringer 31P and
32P) for any signs of corrosion or deterioration:
(a) If no corrosion or deterioration is found refer to step (4) and carry on with
thermostat relocation.
(b) If fuselage skin surface is slightly corroded, up to 0.001 inch deep remove
the corrosion and treat bare metal surfaces as required (refer to SRM, PSM
1-84-3, TASK 51-21-00).
(c) If severe corrosion or deterioration, deeper than 0.001 inch, is found on the
mating surface of the fuselage skin, report finding(s) to: the ‘‘Toronto Help
Desk at telephone number (416) 375-4000 or facsimile (416) 375-4539’’ or
E-mail: thd.qseries@aero.bombardier.com for a corrective action.

### Page 12

SERVICE BULLETIN 84-30-10
S.B. 84-30-10
Page 10 of 28
07 Sep 2007
RR
Revision ‘E’ 10 Oct 2014
(4) Retrofit new thermostat bracket assembly 82410004-003 and new angle
brackets 85313619-001 and 85313630-001 as follows (ModSum 4-126402):
(a) Refer to the locator views shown on Figures 2 and 3, then find the affected
rework area in lower front fuselage at station X-54.00 between stringers
26P and 27P (portside).
(b) Measure and matchmark three new rivet hole locations on stinger 27P
(Refer to Figures 4 and 5 detail B-B). Using a #40 drill carefully make a
pilot hole thru each matchmark.
(c) Secure new angle bracket 85313619-001 in an aligned position on stinger
27P using a suitable C-clamp (Refer to Figure 5).
(d) Drill out one existing rivet and measure and matchmark two new rivet hole
locations on stinger 26P (Refer to Figures 4 and 6 detail C-C). Using a #40
drill carefully make a pilot hole thru each matchmark.
(e) Secure new angle bracket 85313630-001 in an aligned position on stinger
26P using a suitable C-clamp (Refer to Figure 6).
(f) Carefully open the pilot holes (thru both stringers and angle brackets) to
final size using a #30 drill. Release t he clamps, clean out and deburr new
holes thru stringers 26P, 27P and angle brackets as required.
(g) Treat bared metal using alodine 1200, 1200S or 1201 and then flush
Alodine prepared areas with water and dry with a clean dry cloth (Refer to
applicable instruction in SRM PSM 1-84-3, TASK 51-21-10-02-01) and
prime using epoxy chromate primer (Refer to applicable instruction in SRM
PSM 1-84-3, TASK 51-25-15-02-01).
(h) Attach angle bracket 85313630-001 in position to stinger 26P using three
rivets B0205016AD4-5S (refer to Figure 6 View C-C).
(i) Attach angle bracket 85313619-001 in position to stinger 27P using three
rivets B0205016AD4-5S (Refer to Figure 5 View B-B).
NOTE: Rivets MS20470AD4 may be used in lieu of B0205016AD4 rivets.
(5) Install SPC nut plates B0204037AL-4W to floor support strut 85314810 (frame at
X-54.000) as follows (Refer to Figures 4 and 7 view D-D):
(a) Measure and matchmark four new rivet hole locations on floor support
strut 85314810. Using a #40 drill carefully make a pilot hole thru each
matchmark.
(b) Secure two new SPC nut plates B0204037AL-4W in aligned position to
floor support strut 85314810 using a suitable C-clamps.

### Page 13

SERVICE BULLETIN 84-30-10
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(c) Using the match marks as a guide carefully open the four new pilot holes
thru the floor support strut 85314810 and SPC nut plates B0204037AL-4W
to final size using a #30 drill. Release the clamps, clean out and deburr
n e wh o l e sa sr e q u i r e d .
(d) Treat bared metal using alodine 1200, 1200S or 1201 and then flush
Alodine prepared areas with water and dry with a clean dry cloth (Refer to
applicable instruction in SRM PSM 1-84-3, TASK 51-21-10-02-01) and
prime using epoxy chromate primer (Refer to applicable instruction in SRM
PSM 1-84-3, TASK 51-25-15-02-01).
(e) Attach SPC nut plates B0204037AL-4W to floor support strut 85314810
using solid rivets B0205016AD4-4S.
NOTE: Rivets MS20470AD4 may be used in lieu of B0205016AD4 rivets.
Electrical Harness - Rework
(1) Rework/reroute existing thermostat wiring harness as follows:
(a) De-pin wires from each end of splices 3000-E8, E9, E10 and E11 (located
between stringers 31 and 32). Keep splices for later use. (refer to Figures
9).
(b) Release wires that follow from existing clipping to the breakout at the main
loom (refer to Figures 8 and 9).
- 3000-15B-22-4
- 3000-60B-22-4
- 3000-30B-22-4
- 3000-43A-22-4.
(c) Reroute the released wires to agree with detail views shown on Figure 8
view B-B and C-C and Figure 9 view D-D.
NOTE: If necessary wire lengths may be shortened to match installation
requirements.
(d) Identify each splice end and reidentify cable assembly as 8Z4846-011
using TMS-SCE/16-2. 0-9 indent tape.
(e) Reconnect splices at new location (Refer to Figures 11 and 12).

### Page 14

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(f) In two locations secure rerouted wires to new clipping provision on strut
85318410 using clamps MS21919WDG2, hex head screws NAS1801-3-5
and washers NAS1149D0316J (Refer to Figure 10 SECTION F-F).
(g) Use connector rings CR4H, tiedowns MS3367-1-9 and cross spacers
CSCS-M to maintain separation from wi ring of different waycodes (Refer to
flagnote 1 on Figure 11).
NOTE: Prior to installation make sure that the mounting surfaces of the
thermostats and aircraft skin are clean with no corrosion, paint or grease.
Renew corrosion inhibiting coatings on aircraft skin as required.
NOTE: The thermostat to be placed between pad and skin no less than 0.250
inch (6.35 mm) from pad edges.
(h) Set the temp side of thermostat 4100S025 against aircraft skin between
stringers 26P and 27P at X-54.00 (Refer to Figures 13 and 14).
(i) Fillet seal perimeter of pad using DHMS S3.01 Type I or II sealant (Refer to
Figure 14).
(j) Install bracket 82410004-003 (to secure the thermostats in place) using
screws NAS5903-7 and washers AN960D10L (Refer to Figure 13).
(k) Do a continuity check with a Ohmmeter to verify compliance with the wiring
diagram shown on Figure 12.
(l) Connect thermostat lead wires to quick disconnect.
(m) At stringer 27P, secure thermostat lead wires with existing provisions of
adjacent wiring run using new clamp MS21919WDG2 (Refer to Figure 11).
Butterfly new clamp with existing clamp and secure using existing
hardware.
(n) Wrap thermostat lead wires with spiral wrap 2E125SCL9 at locations where
the cables are routed near structural edges (Refer to flagnote 1 on Figure
11).
Label P/N 81111200-101 - Replacement
(1) Locate, remove and discard existing label p/n 81111200 (thermostat location
label) from aircraft exterior front fuse lower left side (Refer to Figure 15).
(2) Install new label p/n 81111200-101 at new location on aircraft exterior to agree
with applicable instruction given in AMM TASK 20-00-16-400-801(Refer to Figure
15 for new label location).

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C. Close Out
(1) Do an operational test of the Engine Air Intake Anti-icing system (Refer to AMM
TASK 30-21-00-710-801).
(2) Remove all tools and equipment from the work area.
(3) Install access panel 121DZ, 122DZ (if removed) and floor covering (Refer to
AMM TASK 06-43-00-992-801).
(4) On incorporation of this ModSum, make an entry that conforms to local
regulatory requirements in the applicable logbook(s). Enter component serial
numbers if applicable. Enter this ModSum number only after complete and
functional incorporation of all work defined in this service bulletin.

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Revision ‘E’ 10 Oct 2014
Removal of Air Intake Heater Thermostats (Pre ModSum 4-126402)
Figure 1
SCREW
NAS5903- -7
(QTY . 3)
WASHER
AN960D10L
(QTY . 4)
RUBBER PAD
TRANSFER TAPE
SUPPORT BRACKET
QUICK DISCONNECT
PLUG
STRINGER
31P
FUSELAGE SKIN
THERMOSTAT
4100S025
CLAMP
MS21919WDG6
SCREW
NAS5903- -14
SPACER
NAS43DD3- -26
THERMOSTAT , BRACKET
ASSEMBLY
82410004- -001
STRINGER
32P
SUPPORT BRACKET
A
B
B

### Page 17

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Installation of Air Intake Heater Thermostats (ModSum 4-126402)
Figure 2
STRUCTURAL PROVISIONS
AND THERMOSTAT BRACKET - INSTN
(REFER TO FIGURE 3)
NOTE: ALL MEASUREMENTS ARE GIVEN IN
INCHES

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Figure 3
Locator View - Structure

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Structural Provisions - View A-A
Figure 4
SPC NUT PLATE
B0204037AL-4W
(QTY 2)
SOLID RIVETS
B0205016AD4-4S
SOLID RIVETS
B0205016AD4-4S

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Structural Provisions - View B-B
Figure 5
85313619-001
ANGLE BRACKET
RIVETS
B0205016AD4-5S
NOTE: ALL MEASUREMENTS ARE GIVEN IN INCHES
STR 27P

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Structural Provisions - View C-C
Figure 6
ANGLE BRACKET
85313630-001
RIVETS
B0205016AD4-5S
PICKUP ON EXISTING
RIVET IN STRUCTURE
STR 26P

### Page 22

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Structural Provisions - View D-D
Figure 7
SPC NUT PLATE
B0204037AL-4W
(REFERENCE)

### Page 23

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07 Sep 2007
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Figure 8
Wiring Installation - Plan View A
1
1 MAINTAIN SEPARATION
FROM WIRING WITH DIFFERENT
WAYCODES
EXISTING

### Page 24

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Wiring Installation - View B-B
Figure 9

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Wiring Installation - View C-C
Figure 10
HEX HEAD SCREW
NAS1801-3-5
WASHER
NAS1149D0316J
CLAMP
MS21919WDG2

### Page 26

SERVICE BULLETIN 84-30-10
S.B. 84-30-10
Page 24 of 28
07 Sep 2007
RR
Revision ‘E’ 10 Oct 2014
Figure 11
Wiring Installation - View D-D
CLAMP
MS21919WDG2 (REF.)
1
1
1

### Page 27

SERVICE BULLETIN 84-30-10
S.B. 84-30-10
Page 25 of 28
07 Sep 2007
RR
Revision ‘E’ 10 Oct 2014
Figure 12
Wiring Diagram
CONTACT PIN
MS39029/1-101 (QTY 8)

### Page 28

SERVICE BULLETIN 84-30-10
S.B. 84-30-10
Page 26 of 28
07 Sep 2007
RR
Revision ‘E’ 10 Oct 2014
Thermostat Installation
Figure 13
SCREW NAS5903-7 (QTY 4)
WASHER AN960D10L (QTY 4)
THERMOSTAT BRACKET82410004-0034100S025
FILLET SEAL PERIMETER
OF PAD (REFER TO FIGURE 14)
1
2
1
2

### Page 29

SERVICE BULLETIN 84-30-10
S.B. 84-30-10
Page 27 of 28
07 Sep 2007
RR
Revision ‘E’ 10 Oct 2014
Thermostat Sealing
Figure 14
FILLET SEAL PERIMETER
OF PAD

### Page 30

SERVICE BULLETIN 84-30-10
S.B. 84-30-10
Page 28 of 28
07 Sep 2007
RR
Revision ‘E’ 10 Oct 2014
Label 81111200 - Application
Figure 15
NEW LABEL
81111200-101
1

### Page 31

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 32

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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