# Bombardier Service Bulletin 84-53-43

Copy: No revision named ("U.S. DOT/FAA - Service Bulletin"), 26 pages: PDF https://openairdocs.org/files/sha256/8e/bf/8ebf5787c92e6e8e7116b18f509798e3af57b353b05a53384839537f93b210dc; text https://openairdocs.org/service-documents/bombardier/sb-84-53-43/file/8ebf5787c92e.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2010-1157; AD 2011-09-12 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: 84-53-43
- Page: https://openairdocs.org/service-documents/bombardier/sb-84-53-43

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

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

- [AD 2011-09-12](https://openairdocs.org/ad/2011-09-12.md), effective Jun 6, 2011: No revision named

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-84-53-43/proposed.md).

## Text (26 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2010-1157; AD 2011-09-12 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. This text is OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1 (OCR)

de HAVILLAND
BOMBARDIER  DASH8
SERVICE BULLETIN
Customer
Support
ATA SYSTEM: 5310  NUMBER: 84-53-43
SUBJECT: Fuselage - Installation of Drains in Windshield Lower Frames -
ModSum 4-113564
PLANNING INFORMATION
A. Effectivity
Aircraft Affected:
In-Service:  DHC-8 Aircraft Models 401 and 402 Serial Numbers 4001,
4003, 4004, 4006, 4008 thru 4274.
Production:  ModSum 4-113564 will be installed before delivery on
applicable DHC-8 Aircraft at Serial Number 4275 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.
Spares Affected:
None
B. Reason
Problem: Operators have reported an accumulation of moisture in the lower frame
along the bottom of the windshields. Moisture in the frame may result in
corrosion.
Solution: This ModSum introduces a drain in each lower frame which is designed
to minimize corrosion due to moisture accumulation.
27 Apr 2010  S.B. 84-53-43
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### Page 2 (OCR)

SERVICE BULLETIN 84-53-43
C. Description
The procedures in this service bulletin give the instructions to do the tasks that
follow:
- pilot's and copilot's seats are removed
- both windshields are removed
- panels in both side consoles are removed
- upholstery panels and insulation are removed for access to the windshield lower
frames and sidewall structure
- an operational check of the windshield electrical system is done
- close out.
D. Compliance
Installation of ModSum 4 - 113564 may be done at the operator's discretion.
Transport Canada Airworthiness Directive 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.
Manpower
It will take an estimated 20.0 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  1.50
Procedure  16.00
Test / RTS  1.00
Close-Out  1.50
27 Apr 2010  S.B. 84-53-43
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### Page 3 (OCR)

SERVICE BULLETIN 84-53-43
G. Material - Price and Availability
ModKit 8MK4025-007 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
8MK4025-007  Kit Windshield Drain
H. Tooling - Price and Availability
None
I. Weight and Balance
Moment
A/C Type and  Weight (Lb)  Arm (Inches)  (Inches x Lb)
Model  × 0.001
DHC-8 Model 401  + 1.53  -98.0  -0.15
DHC-8 Model 402  + 1.53  -98.0  -0.15
J. Electrical Load Data
Not affected
K. Publications Affected
Dash 8 Illustrated Parts Catalogue  PSM 1-84-4
ModSums Manual .  PSM 1-84-12
27 Apr 2010  S.B. 84-53-43
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### Page 4 (OCR)

SERVICE BULLETIN 84-53-43
L. References
The initial issue of this service bulletin was prepared to the engineering drawings
and related data that follows:
DRAWING  SHEET  REV
8MK4025  E
8Z2176  1
2
3
(100 & 300 series only)
4
ModSum 4Q113564 Rev. 'E'
ModSum 4 - 113564 Rev. 'E'
PCA 42117 Revision - - (for internal reference only)
Transport Canada Airworthiness Directive Pending
2.  MATERIAL INFORMATION
A. Parts Required Per Aircraft
(1) Modification Kit 8MK4025-007, Kit- Windshield Drain.
(2)  Detailed Kit Content:
Quantity Per Kit  Part Number  Description
- 007
1  8MK4025  Drwg. - Kit
8Z2176  Drwg. - Retrofit-Instl.
8Z2176-103  Drain Tube (Tygothan Clear Tube)
1  8Z2176-115  Drain Tube (Tygothan Clear Tube)
2  85312868-101  Drain Fitting
1  85313046-001  Drain Fitting Assy
27 Apr 2010  S.B. 84-53-43
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### Page 5 (OCR)

SERVICE BULLETIN 84-53-43
Quantity Per Kit  Part Number  Description
- 007
2  85312310-101  Doubler
18  M7885/6-4-02  Blind Rivet
20  MS3367-1-9  Strap- Tie Down
2  MS35489-149  Grommet
4  B02050116AD4-5C  Rivet
1  N5TUB5  Tee
6  NAS43DD3-32FC  Spacer
NAS1801-3-7  Bolt
1  NAS1801-3-8  Bolt
1  NAS1801-3-10  Bolt
4  NAS1801-3-16  Bolt
З  MS21042L3  Nut
16  NAS1149D0316J  Washer
З  MS21919WDG4  Clamp
9  MS21919WDG8  Clamp
1  DSC91-23-2  Tape
(3)  In addition to the above parts), 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
Consumable Products Manual PSM 1-84- 18.
Part Number  Quantity  Description
Per Aircraft
PR1776 B2  6 oz  Fillet Sealant DHMS S3.01 B2
PS870 C-80  3 Oz  Fay Sealant DHMS S3.06 TYPE II
MIL-S -22473  2 oz  Sealant-Loctite Grade AA
F13 GR3 TYPE I|  6 oz  Anti Corrosion Compound DHMS C4.12 TYPE I|
27 Apr 2010  S.B. 84-53-43
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### Page 6 (OCR)

SERVICE BULLETIN 84-53-43
B. Parts Required to Modify Spares
None
C. Special Tools and Equipment Required
None
D. Existing Parts Accountability
None
3. ACCOMPLISHMENT INSTRUCTIONS
A. Job Set-Up
(1)  Refer to Aircraft Maintenance Manual PSM 1-84-2 TASK 12-00-01-860-801
and put the aircraft into standard configuration for maintenance.
(2)  Remove the furnishings as follows for access to angular side post extensions
below windshield/side windows.
- pilot and copilot seats
- panel from windshield sill
- panel from both side consoles
- upholstery panels trom sidewalls above side consoles
- insulation as required.
(3) Remove both windshields.
B. Procedure
(1) Clean corrosion inhibiting compound from window frame and sill using acetone.
(2) Inspect anchor nuts for corrosion. Remove and replace anchor nuts if found
corroded.
(3)  Inspect window frame for signs of corrosion. Contact The Bombardier Help Desk
if found corroded.
(4)  Refer to Figure 1, Figure 2, Figure 3, Figure 4 and rework the left and right lower
window sill for installation of a drain fitting as follows:
(a)  Measure and mark two hole centers in windshield lower frame (left and
right hand at 11.50 inches inboard from the reinforcing angle.
27 Apr 2010  S.B. 84-53-43
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### Page 7 (OCR)

SERVICE BULLETIN 84-53-43
(b) At each center mark, make a hole 0.3122/0.3129 inch diameter thru the left
and right hand lower frame and sill structure.
(c) Trial fit one new drain fitting 85312868 in each new hole. Ream the new
hole (s) it required for a press fit.
(d) Deburr, clean away swart, treat bared metal using alodine 1200, 1200S or
1201 and coat with epoxy chromate primer.
(5)  Refer to Figure 12, Figure 13 and install new doubler 85312310-101 as follows:
NOTE: The procedure that follows gives the instructions to install the left side
doubler. The procedure to install the right side doubler is the same. The
coordinate positions are opposite.
(a)  On the left side of the flight deck floor locate the position of the coordinates
X-98.0, Y36.50 and Z112.00.
(b)  Drill out four existing rivets from the the flight deck floor.
(C)  Align the pilot hole along the straight edge side of the doubler with the
vacated rivet holes thru the flight deck floor. Secure the doubler in position
using suitable clecos.
Make five new holes thru the doubler and flight deck floor using a #30 drill
(use the pilot holes in the doubler as a guide). Install suitable clecos thru
the new holes.
(e)  Remove the clecos from the straight edge side of the doubler. Backdrill the
pilot hole thru the doubler using a #30 drill.
(†)  Remove the doubler.
(g) Make the 0.774/0.765 inch diameter drain hole thru the flight deck floor.
(h) Deburr, clean away swarf, treat bared metal using alodine 1200, 1200S or
1201 and coat with epoxy chromate primer.
Wipe mating surface of the doubler 85312310-101 and the flight deck (in
side consoles) using methyl ethyl ketone. Apply a thin even coat of fay
sealant PS870 C-80 to doublers and flight deck.
Attach the doubler in position using nine rivets M7885/6-4-02.
Refer to Figure 12 and install new grommet MS35489-149 in the doubler.
(Б)  Refer to Figure 12, Figure 13, Figure 14 and blend radius of cleat 85310895 as
snown.
7)  Refer to Figure 1, Figure 7, Figure 10, Figure 11 and install the new drain fitting
assembly 85313046-001 on the forward pressure bulkhead as follows:
27 Apr 2010  S.B. 84-53-43
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### Page 8 (OCR)

SERVICE BULLETIN 84-53-43
(a) Remove access panels 121AL and 122BR from lower front end of fuselage.
(b) On the interior face of the forward pressure bulkhead measure and mark a
drain hole center position at YO.00 and Z104.25. Drill a hole to 0.329/0.322
inch diameter thru the marked position.
(c) Align the new drain fitting assembly 85313046-001 over the new drain
hole. Mark four rivet centers on the bulkhead thru the holes in drain fitting
assembly.
(d) Drill centers to 0.128 inch diameter. Deburr drain and rivet holes, clean
away swarf, treat bared metal using alodine 1200, 1200S or 1201 and coat
with epoxy chromate primer.
(e) When primer is cured, wipe mating surface of bulkhead and drain fitting
assembly using a clean, white, cotton cloth dampened in methyl ethyl
ketone.
(f)  Apply a thin even coat of fay sealant PS870 C-80 to fitting and to
bulkhead. Secure fitting to bulkhead immediately with four rivets
B0205016AD4-5C.
Refer to Figure 4 and install the left and right side drain fittings 85312868-101
as follows:
(a) Wipe bore and area surrounding drain holes in windshield lower frame
using methyl ethyl ketone.
(b) Apply a thin even coat of sealant Loctite AA to short end of new drain
fittings 85312868-101.
(c) Press a fitting into each drain hole ensuring top of fitting is flush with
windshield frame.
(d) Heat cure sealant for 30 minutes at 120 to 150 degrees F.
(9)  Wipe around ends of existing reinforcing angles on windshield lower frame
using methyl ethyl ketone. Apply a fillet of sealant PR1776 B2 around ends.
(10) Refer to Figures 5 thru 9, Figure 12, Figure 13, Figure 15 and install tubing
8Z2176-103 as follows:
(a)  Cut two lengths of tubing 822176-103 and route from windshield drains
thru the drain hole in each doubler to the drain fitting assembly on forward
pressure bulkhead.
(D)  Install clamps MS21919WDG8 and MS21919WDG4 with bolts
NAS1801-3-7, NAS1801-3-16, spacers NAS43DD3-32FC, nut
MS21042L3 and washers NAS1149D0316J along new and existing
locations on the lower pilots bulkhead as shown in Figure 7.
(C)  Route the drain lines along with existing frame members. Avoid making
sharp bends or traps when routing the drain line horizontal to the drain
fitting.
27 Apr 2010  S.B. 84-53-43
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### Page 9 (OCR)

SERVICE BULLETIN 84-53-43
(d) Connect the lower end of each drain tube to the new tee N5TUB5 and
secure with tie wraps MS3367-1-9.
(e) Cut a short length of tubing 822176-105 and connect between tee and
bulkhead fitting. Secure with tie wraps MS3367-1-9.
(t)  Secure tubing to floor beam using clamps MS21919WDG8, spacers
NAS43DD3-32FC, bolts NAS1801-3-8, bolts NAS1801-3-10 and
washers NAS1149D0316.
(g) Along trame X98.00, use tie down straps MS3367-1-9 at lightening holes
to secure tubing as shown in Figure 12. In addition, tape tubing to inboard
face of insulation blanket using tape DSC91-23-2.
(h) Secure each drain tube to the related drain fitting in windshield frame with
tie wraps MS3367 -1-9.
Install edge grommet on the edge of adjacent structure and/or in lightening
holes as required to protect the tubing 822176-103.
C. Close Out
(1) Make sure the drain tube assemblies are free of any blockage or debris.
(2) Refer to AMM TASK 56-10-01-400-801 and install both windshields.
(3) Install lower access panels 121AL and 122BR
(4)  install the furnishings that follow:
- insulation
- upholstery panels from sidewalls above side consoles
- panel from both side consoles
- panel from windshield sill
- pilot and copilot seats.
(5) Remove all tools and equipment from the work area.
(6)  On incorporation of this ModSum, make an entry that conforms to local
regulatory requirements in the applicable logbook(s). Enter component serial
numbers it applicable. Enter this ModSum number only after complete and
functional incorporation of all work defined in this service bulletin.
27 Apr 2010  S.B. 84-53-43
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### Page 10 (OCR)

SERVICE BULLETIN 84-53-43
X-39.00
SIDE CONSOLE 85311451
LOWER PANEL 85311456 REMOVED
TO GAIN ACCESS FOR ROUTING
OF DRAIN TUBING
® +
2100.032
Z100.032
LWR P/BLKHD DIM  STR23 DTM STR22 DTM
85313850
X-98.00
VIEW LOOKING INBOARD ON LHS
ca0480a01.da, sr/cv. oct20/2009
Figure 1
27 Apr 2010  S.B. 84-53-43
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### Page 11 (OCR)

SERVICE BULLETIN 84-53-43
TENSION PLATE
85312636
(REF)
= 11.50 in.
0.3122/0.3120 in. DIA.
HOLE (FOR PRESS FIT)
LOCATE ON CENTERLINE
OF EXISTING FASTENERS
AS SHOWN
LOOKING DOWN ON  cg0480a02. dq, av/cv, oct21/2009
WINDSHIELD FRAME
(R.H. OPP)
Figure 2
S.B. 84-53-43
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### Page 12 (OCR)

SERVICE BULLETIN 84-53-43
WINDOW FRAME
85310776
(REF)  REINFORCING
ANGLE
85312610
(REF)
FILLET SEAL
WINDSHIELD  PR1776B2  TENSION PLATE
ASSEMBLY  85312605
8SC0043  PACKER  (REF)
(REF)  85312611
(REF)
FILLET SEAL
PR1776B2
LOWER SILL DATUM
(REF)
FILLET SEAL
PR1776B2
WINDOW FRAME
85310776
(REF)
REINFORCING  cg0480a03.dg, av/gv, oct20/2009
ANGLE
85312610
(REF)
Figure 3
27 Apr 2010  S.B. 84-53-43
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### Page 13 (OCR)

SERVICE BULLETIN 84-53-43
PANEL ASSEMBLY
82510209
REMOVED FOR
ACCESS
WINDOW FRAME
85310776
(REF)
DRAIN FITTING
85312868-101
1 REQ'D
1 REQ'D R.H.
PRESS FIT
WINDSHIELD TO BE
REMOVED PRIOR TO
DRILLING FOR
DRAIN FITTING
TIE DOWN STRAP
MS3367-1-9
(REF)
INSULATION
LOWER SILL DATUM  BLANKET
(REF)  (REF)
D-O  cg0482a04.dg, av/gv, oct20/2009
Figure 4
27 Apr 2010  S.B. 84-53-43
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### Page 14 (OCR)

SERVICE BULLETIN 84-53-43
TUBE ASSEMBLY
83500414
OXYGEN LINE
83500415  TEE
X-124.00
X-111.00
X-98.00
OXYGEN LINE  UNION
83500414
cg0480a05.dg, sr/gv, oct20/2009
Figure 5
27 Apr 2010  S.B. 84-53-43
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SERVICE BULLETIN 84-53-43
-→ Z112.00
EXISTING  SPACER
CLAMP  _ NAS43DD3-32FC
OXYGEN LINE
\BOLT
NAS1801-3-8
CLAMP  WASHER
MS21919WDG8  NAS149DD316J
TYGOTHAN TUBE
8Z2176-103
→- Z112.00
EXISTING
SPACER  • CLAMP
NAS43DD3-32FC
OXYGEN LINE
BOLT  TYGOTHAN TUBE  cg0480a06.dg, sr/gv, oct20/2009
NAS1801-3-10  CLAMP  8Z2176-103
WASHER  MS21919WDG8
NAS149D316J
G- G
Figure 6
27 Apr 2010  S.B. 84-53-43
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### Page 16 (OCR)

SERVICE BULLETIN 84-53-43
TYGOTHAN TUBE  TYGOTHAN TUBE
822176-103  PT. Y  8Z2176-103
OXYGEN LINE  Y0.00  OXYGEN LINE
Z112.00
PT. X  PT. X
PILOTS BULKHEAD
M  85313862
cg0480a07.dg, sr/gv, oct21/2009
Figure 7
27 Apr 2010  S.B. 84-53-43
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### Page 17 (OCR)

SERVICE BULLETIN 84-53-43
_ TYGOTHAN TUBE
822176-103
CLAMP
MS21919WDG8
BOLT
NAS1801-3-16
WASHER
NAS149D0316J
EXISTING
CLAMP
OXYGEN LINE
LOWER PRESSURE
BULKHEAD
cg0480a08.dg, sr/gv, oct20/2009
Figure 8
27 Apr 2010  S.B. 84-53-43
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### Page 18 (OCR)

SERVICE BULLETIN 84-53-43
TYGOTHAN TUBE  CLAMP
8Z2176-103  MS21919WDG8
NUT
MS21042L3
WASHER
NAS149DO316J
BOLT
NAS1801-3-7
WASHER
NAS149DO316J
CLAMP
OXYGEN LINE  MS21919WDG4
(к) - (к
SPACER
TYGOTHAN TUBE  NAS43DD3-32FC
8Z2176-103
WASHER
CLAMP  NAS149D0316J
MS21919WDG8
EXISTING
OXYGEN LINE  CLAMP
LOWER PRESSURE
O-0  BULKHEAD
Figure 9
27 Apr 2010  S.B. 84-53-43
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### Page 19 (OCR)

SERVICE BULLETIN 84-53-43
YO.00
0.329/0.322 in. DIA
FITTING ASSEMBLY
85313046-001
RIVET
B0205016AD4-5C  4.17 in.
4 PLACES
NLG
HOUSING
HOLE
N
PILOTS BULKHEAD
85313862
cg0480a1 0. dg, vk/gv, oct21/2009
Figure 10
27 Apr 2010  S.B. 84-53-43
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### Page 20 (OCR)

SERVICE BULLETIN 84-53-43
PILOTS BULKHEAD
85313862
TYGOTHAN TUBE
8Z2176-105  FITTING
ASSEMBLY  2104.27
CLAMP  85313046-001
MS21919WDG8
TYGOTHAN TUBE
8Z2176-103
CLAMP
MS21919WDG4
4.17 in.
OXYGEN LINE
FAY SEAL CONTACT SURFACES
BETWEEN FITTINGS AND
BULKHEAD USING P/S 870 C-80
N-N
CLAMP
MS21919WDG8  FITTING
TYGOTHAN TUBE  ASSEMBLY
8Z2176-103  85313046-001
PILOTS BULKHEAD
TIE DOWN STRAP  TYGOTHAN TUBE  85313862
MS3367-1-9  8Z2176-105
TEE
NSTUB5
TIE DOWN STRAP  cg0480a11.dg, vk/gv, oct21/2009
MS3367-1-9
TYGOTHAN TUBE
8Z2176-103  D-D
Figure 11
27 Apr 2010  S.B. 84-53-43
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### Page 21 (OCR)

SERVICE BULLETIN 84-53-43
LOWER SILL
85310787
SIDE POST
85311079
TUBE IS TIED
DOWN THROUGH HOLE
TYGOTHAN TUBE
8Z2176-103
STR15-  INBOARD FLANGE
CLEAT  85311819
85310895
STR16
STR17 ]
SIDE CONSOLE
TUBE IS TAPED TO  85311451
INBOARD FACE OF
INSULATION BLANKET  STR18
GROMMET
MS35489-149
STR19
Y-24.50
TUBE IS TIED
DOWN THROUGH HOLE
• Z112.00
STR21
TYGOTHAN TUBE
8Z2176-103
STR22
LHS SHOWN  cq0480a1 2. dg, vk/cv, oct21/2009
RHS OPP-EXCEPT AS NOTED BY DETAIL AD
VIEW LOOKING FORWARD ON FORMER
AT X-98.00
Figure 12
27 Apr 2010  S.B. 84-53-43
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SERVICE BULLETIN 84-53-43
Y-36.50
X98.00
STR17
U)-(u
VIEW LOOKING DOWN ON SIDE CONSOLE
AT STRINGER 17
RIVET  RIVET
M7885/6-4-02  M7885/6-4-02
FLIGHT DECK
WEB
DOUBLER
85312310-101
2.65 in.
HOLE
0.774 in. DIA.  0.765 in.  M7885/6-4-02  RIVET  cg0480a1 3.dg, vk/gv, oct20/2009
1.30 in.
1) -(T
VIEW LOOKING DOWN ON FLIGHT DECK
AT Z=112.00
Figure 13
27 Apr 2010  S.B. 84-53-43
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SERVICE BULLETIN 84-53-43
TANGENT REF.
CLEAT RADIUS
Y36.50
RADIUS BLENDED
0.30 in. OFF
TANGENTS
- X98.00
CLEAT
85310895
CORNER RADIUS
BLENDED 0.10 in.
2 PLACES
0.36
MAX.
cq0480a14.dg, vk/cv, oct20/2009
Figure 14
27 Apr 2010  S.B. 84-53-43
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SERVICE BULLETIN 84-53-43
PITOT
(REF)
KEEP LABEL ON AFT
SIDE OF STRUCTURE
FOR VISIBILITY
3410-P2
- STR17
TYGOTHAN TUBE
8Z2176-103
LUG ORIENTATION  FORMER
MAY BE ADJUSTED  85310890
AS REQUIRED
TO SUIT INSTALLATION  STR16
VIEW LOOKING FORWARD ON FORMER AT X98.00
GROUND
3410-GS6
X98.00
TYGOTHAN TUBE  cg0480a15.dg, vk/gv, oct20/2009
8Z2176-103
SIDE CONSOLE
85311451
VIEW LOOKING DOWN ON SIDE CONSOLE
AT STRINGER 17
Figure 15
27 Apr 2010  S.B. 84-53-43
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BOMBARDIER
SERVICE BULLETIN (SB) - RECORD OF INCORPORATION
- Q SERIES DASH 8 AIRCRAFT
To:  Partner Data Co-Ordinator (Toronto), Bombardier Aerospace Commercial Aircraft
Phone:  (1) 416 375 3534  Facsimile: (1) 416 375 4538
E-mail:  cmdb.requests@aero.bombardier.com
From:
Company:
Phone:  Extn:
Facsimile:  Date:
E-mail:
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
Jan 2009/

### Page 26 (OCR)

BOMBARDIER
SERVICE BULLETIN (SB) - COMMENT SHEET - Q SERIES DASH 8 AIRCRAFT
To:  SB Focal (Toronto), Bombardier Aerospace Commercial Aircraft
Phone:  (1) 416 375 4078  Facsimile:  (1) 416 375 4538
E-mail:  syed.rizvi@aero.bombardier.com
From:
Company:
Phone:  Extn:
Facsimile:  Date:
E-mail:
Select appropriate boxes) 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
• Effectivity  • Reason  • Description  • Compliance
• Approval  • Manpower  • Material  • Weight and Balance
• Electrical Load  • Tooling  • References  • Publications Affected
2. MATERIAL INFORMATION
• Kit Content  • Special Tools/Equipment  • Parts to Modify Spares
• Consumables  • Disposition of Existing Parts  • Other
3. ACCOMPLISHMENT INSTRUCTIONS
• Job Set-Up  • Procedure  • Close-Out  • Test
• Illustration (s)  • Other
4. COMMENTS, REMARKS, SUGGESTIONS
Fax this sheet to (1) 416 375 4538 or Email PDF to:
syed.rizvi@aero.bombardier.com
Feb 2009

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