# Bombardier Service Bulletin 700-53-050

Copy: Revision 01 ("700-53-050 Rev1"), 25 pages: PDF https://openairdocs.org/files/sha256/30/63/306397b17fc0cc26fc0987a55e4163f29b39af54469f3aa747c92cd323ca765a; text https://openairdocs.org/service-documents/bombardier/sb-700-53-050/file/306397b17fc0.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2018-0546; AD 2018-21-03 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: 700-53-050
- Latest revision known: 700-53-050, Revision 01, dated December 16, 2016 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/bombardier/sb-700-53-050

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

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

- [AD 2018-21-03](https://openairdocs.org/ad/2018-21-03.md), effective Nov 19, 2018: Revision 01

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-700-53-050/proposed.md).

## Text (25 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2018-0546; AD 2018-21-03 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

Aug 03/2017 700-53-050Page 1 of 1
SERVICE BULLETIN INFORMATION SHEET
MODEL BD-700-1A10 (BD-700)
ATA 53-61
FUSELAGE
MODIFICATION – BELLY FAIRINGS –
REPLACEMENT OF ATTACHMENTS FOR THE ACCESS PANELS
Service Bulletin No.: 700-53-050 Issue: Revision 01 Dated: Dec 16/2016
The following data is supplied for information only.  No revision to the Service Bulletin
is necessary.
Keep this Information Sheet and the Information Sheet dated Mar 13/2017 with subject
Service Bulletin.  Discard the Information Sheet dated Jan 03/2017.
This Information Sheet is issued to revise the labor and parts free-of-charge period
in Paragraphs 1.F. and 1.G.
In Paragraph 1.F., Manpower, the second statement should read as follows:
The labor required to do this Service Bulletin is at no cost if:
(1) the work is done at Bombardier Business Aviation Services (BBAS)
or Authorized Service Facilities (ASF), and
(2) this Service Bulletin is scheduled before Feb 01/2018.
In Paragraph 1.G., Material - Cost and Availability, the second statement should read
as follows:
The kit and parts are available at no cost if:
- a no-charge purchase order is sent to Bombardier Aerospace
before Feb 01/2018.

### Page 2

March 13/2017 700-53-050Page 1 of 1
SERVICE BULLETIN INFORMATION SHEET
MODEL BD-700-1A10 (BD-700)
ATA 53-61
FUSELAGE
MODIFICATION – BELLY FAIRINGS –
REPLACEMENT OF ATTACHMENTS FOR THE ACCESS PANELS
Service Bulletin No.: 700-53-050 Issue: Revision 01 Dated: Dec 16/2016
The following data is supplied for information only.  No revision to the Service Bulletin
is necessary.
Keep this Information Sheet and the Information Sheet dated Jan 03/2017 with subject
Service Bulletin.
This Information Sheet is issued to update the compliance time in the Service Bulletin
Summary Sheet and in Paragraph 1.D. of the Service Bulletin.
      The first row in the Service Bulletin Summary Sheet should read as follows:
RECOMMENDED
RELIABILITY/DISPATCHABILITY/COST AVOIDANCE
COMPLIANCE TIME
Within 12 months from this Service
Bulletin Release Date (Basic Issue).
The compliance statement in Paragraph 1.D., Compliance should read as follows:
    Recommended within 12 months from this Service Bulletin release date
    (Basic Issue).

### Page 3

Discard the Basic Issue of this Service Bulletin dated Jul 14/2016 and replace in its
entirety with this Revision 01.
Service Bulletin No. 700−53−050
Date of Basic Issue Jul 14/2016
Revision No. Basic Dated Jul 14/2016
Revision No. 01 Dated Dec 16/2016
This revision has no effect for aircraft on which the Basic Issue of this Service
Bulletin was done thus no other action is necessary. Do not sign the log book if you
have not done this revision. Keep the previous log book entry. You may make an
entry as "Not Applicable" for this revision.
This revision is issued to:
1. Add, in Paragraph 1.C., to spotface the sealant.
2. Add, in Paragraph 1.H., necessary tooling.
3. Revise, in Paragraph 1.K., Modsum R700T400609 to Rev F.
4. Revise, in Paragraph 1.K., Kit Drawing KGC991 –1473 to Rev F.
5. Revise, in Paragraph 2.B., steps (4) to (6), (8), (9) and (23).
6. Revise, in Paragraph 2.B., the order to accomplish some of the steps.
7. Revise drawing KGC991 –1473.
8. Make miscellaneous minor changes, as necessary, with no change of context.
SERVICE BULLETIN
MODEL BD−700−1A10 (BD−700)
700−53−050
Page 1 of 1
REVISION TRANSMITTAL SHEET

### Page 4

MODIFICATION — BELLY FAIRINGS —
REPLACEMENT OF ATTACHMENTS FOR THE ACCESS PANELS
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
RELIABILITY/DISPATCHABILITY/COST AVOIDANCE
COMPLIANCE TIME
Not applicable
EFFECTIVITY: A/C Serial No. 9002 to 9312, 9314 to 9380 and 9384 to 9429
MANPOWER: 4 man−hours
CONTINUED AIRWORTHINESS (CAW)
FLEET CAMPAIGN NOYES
TLMC, CH 5 AFFECTED NOYES
KITS and/or PARTS YES NO
TOOLING/GSE YES NO
PLANNING INFORMATION: See important
information at the start of Paragraph 1. YES NO
DEDICATED SCHEDULE YES NO
PREREQUISITE SERVICE BULLETINS: N/A
To place an order for parts or kits, please call Bombardier Aerospace Parts Services
at:
514−855−2999 or 1−866−538−1247
SERVICE BULLETIN SUMMARY
www.cic.bombardier.com
MODEL BD−700−1A10 (BD−700)
ATA 53−61
FUSELAGE
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 1 of 1
This Service Bulletin is available at:

### Page 5

MODIFICATION — BELLY FAIRINGS —
REPLACEMENT OF ATTACHMENTS FOR THE ACCESS PANELS
1. PLANNING INFORMATION
NOTE: This Service Bulletin is covered by a dedicated schedule. Dedicated schedules
are used to reserve and manage inventory due to limited availability of rotable
stock, parts and/or kits. Parts are limited, therefore, advance part scheduling
with our In−Service Implementation Team (ISIT) is recommended prior to a
maintenance visit. Please contact your Regional Manager (RM), Field Service
Representative (FSR) or Customer Service Representative (CSR) to schedule
your aircraft as there is a limited availability. The parts will be allocated on a
first come first serve basis.
For more information on dedicated schedules, refer to SB 700−00−002.
A. Effectivity
BD−700–1A10 aircraft, Serial No. 9002 to 9312, 9314 to 9380 and 9384 to 9429.
The intent of this Service Bulletin was met on the aircraft that follows with the
Service Requests for Product Support Action (SRPSA) listed in the table that
follows:
SERVICE BULLETIN
www.cic.bombardier.com
MODEL BD−700−1A10 (BD−700)
ATA 53−61
FUSELAGE
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.
 2016 Bombardier Inc.  All rights reserved
Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 1 of 19
This Service Bulletin is available at:

### Page 6

AIRCRAFT SERIAL NO. SRPSA NO.
9378 124026
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
1. Condition
Some operators have reported losing belly fairings (185CL/186CR) in flight.
2. Evidence
The fasteners may have been over torqued and cause damage to the access
panels mounting holes. Fastener grip length may be too short and not fully
engage in fastener receptacle. Fastener grip length may be too long and foul on
the bottom of the receptacle. A build up of sealant in the fastener receptacle
may also prevent fastener to fully engage in receptacle.
3. Objective/Benefit
This Service Bulletin introduces new self−locking nutplates with associated
hardware (retaining rings and studs). This will ensure that the fasteners are fully
engaged. A bracket is also added to provide two additional attachment points to
assure the belly fairings are safely secured, thus avoiding unexpected downtime
and costly repairs.
C. Description
This Service Bulletin gives instructions to:
− Remove the belly fairing access−panels (185CL/186CR),
− Install the new bracket,
− Drill holes at new attachment points in access−panels,
− Remove and discard the existing receptacles, studs and retaining rings,
− Install the new nutplates,
− Replace the self−contouring sealing pad,
− Spotface sealant,
− Install the belly fairing access−panels (185CL/186CR) with the new studs and
retaining rings, and
− Do a check of the aerodynamic smoothness of the access panels.
MODEL BD−700−1A10 (BD−700)
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 2 of 19

### Page 7

D. Compliance
Recommended − Reliability/Dispatchability/Cost Avoidance
E. Approval
The technical content of this Service Bulletin has been approved under the
authority of Transport Canada Civil Aviation (TCCA) Design Approval Organization
(DAO) No. DAO #93−Q−02.
NOTES: 1. The technical content of this Service Bulletin is accepted by the FAA
under the Canada/USA bilateral Aviation Safety Agreement.
2. The technical content of this Service Bulletin is accepted by EASA in
accordance with established procedures.
F. Manpower
NOTES: 1. The man−hours given are estimates to help you schedule the tasks
given in this bulletin. The estimates 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 estimates, refer to
SB 700−00−002.
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 labor estimates and should be considered
for planning purposes before you schedule this Service Bulletin.
4 man−hours are necessary to do this modification.
The labor required to do this Service Bulletin is at no cost if:
− the work is done at Bombardier Business Aviation Services (BBAS) or
Authorized Service Facilities (ASF), and
− this Service Bulletin is scheduled in less than 15 months from this Service
Bulletin release date (Basic Issue).
G. Material − Cost and Availability
Kit 700K53–6008A is necessary to do this modification.
KIT NO. PRICE
700K53–6008A Please contact Bombardier Aerospace
Parts Services, in Montreal, for delivery
lead times and confirmation of prices.
MODEL BD−700−1A10 (BD−700)
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 3 of 19

### Page 8

In addition to the kit shown above, the parts in Paragraph 3 are necessary to do this
modification.
This kit and parts are available at no cost if:
− a no−charge purchase order is sent to Bombardier Aerospace in less than 15
months from this Service Bulletin release date (Basic Issue).
This Service Bulletin is covered by a dedicated schedule. Dedicated schedules are
used to reserve and manage inventory due to limited availability of rotable stock,
parts and/or kits. Parts are limited, therefore, advance part scheduling with our
In−Service Implementation Team (ISIT) is recommended prior to a maintenance
visit. Please contact your Regional Manager (RM), Field Service Representative
(FSR) or Customer Service Representative (CSR) to schedule your aircraft as there
is a limited availability. The parts will be allocated on a first come first serve basis.
For more information on dedicated schedules, refer to SB 700−00−002.
During or after the above free period, Smart Parts Plus does not pay for the kit or
parts.
H. Tooling
The equipment and tools listed below are necessary to do this modification:
GSE REFERENCE NO. PART NO. DESCRIPTION
− − Roller
− − Sealant Applicator
− − Spot Face 0.375 in
(9.50 mm)
− − Wrench, Torque 15 to 25
lbf in (1.70 to 2.83 Nm)
NOTES: 1. Refer to the Global Express or Global Express XRS Illustrated Tool
and Equipment Manual (ITEM) to make sure that you use the correct
equipment configuration.
2. Refer to the Liability Statement for the GX/XRS for acceptable GSE
equivalents.
3. This list is provided for quick reference. In case of discrepancy
between this list and the tools called in the SPM, WM, Chapter 20,
then the tools called in the SPM, WM prevail. Other approved
alternative tools are acceptable and can also be used.
I. Weight and Balance
No change.
MODEL BD−700−1A10 (BD−700)
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 4 of 19

### Page 9

J. Electrical Load Data
No change.
K. References
− Bombardier Aerospace, Modification Summary, R700T400609, Rev. F.
− Bombardier Aerospace, Standard Practices Manual (SPM), Chapters 20 and 51.
− Bombardier Aerospace, Kit Drawing KGC991 –1473, Rev. F.
− Global Express BD−700 Aircraft Maintenance Manual (AMM), Chapters 6
and 53.
− Global Express XRS BD−700 Aircraft Maintenance Manual (AMM), Chapters 6
and 53.
− Bombardier Aerospace, Structural Repair Manual (SRM), Chapter 51.
L. Other Publications Affected
− Global Express BD−700 Aircraft Illustrated Parts Catalog (AIPC).
− Global Express XRS BD−700 Aircraft Illustrated Parts Catalog (AIPC).
M. Equivalent Service Bulletin
− For the Global 5000 BD−700−1A11 aircraft, use SB 700−1A11−53 –025.
− For the Global 5000 BD−700−1A11 Featuring Global Vision Flight Deck aircraft,
use SB 700–53–5009.
− For the Global 6000 BD−700−1A10 aircraft, use SB 700 –53–6008.
2. ACCOMPLISHMENT INSTRUCTIONS
NOTES: 1. All TASKs given in the procedures that follow are from the Global Express
or Global Express XRS BD−700−1A10 Aircraft Maintenance Manual
(AMM) unless otherwise specified.
2. All references made to zones, access panels and/or doors, are from the
Global Express or Global Express XRS BD−700−1A10 Aircraft
Maintenance Manual (AMM), Chapter 6.
A. Aircraft Setup
None.
B. Modification
(1) Remove the aft access−panel (185CL). Refer to AMM 53−61−19−000−801.
NOTE: Do not remove the joint strap from access panel (186CR).
(2) Remove the aft access−panel (186CR). Refer to AMM 53−61−19−000−801.
MODEL BD−700−1A10 (BD−700)
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 5 of 19

### Page 10

(3) On FS813.00, remove the self−contouring sealing pad as required, to gain
access to the rivets that will be removed. Refer to Kit Drawing KGC991–1473,
Section C−C and Detail A. Refer to SPM−Maintenance Chapter 51–23–00.
(4) Remove the five rivets, on FS813.00, where the angle, Item 3, will be installed.
Refer to Kit Drawing KGC991–1473, Section B−B. Refer to SRM Chapter
51–42–08.
(5) If applicable, remove the two rivets on the lower flange at FS813.00, where the
angle, Item 3, will be installed. Refer to Kit Drawing KGC991–1473, Section
D−D. Refer to SRM Chapter 51–42–08.
(6) Locate angle, Item 3, and pick up the existing holes from the structure. Refer to
Kit Drawing KGC991–1473, Sections B−B and D−D.
(7) Drill the four holes for the rivets through the angle, where the nutplates will be
installed, and do the countersinks. Refer to SRM Chapter 51–40–08.
NOTES: 1. Do not install the nutplates at this moment.
2. Make sure the nutplates can be installed after the angle is
attached to the structure.
(8) Install angle, Item 3, to frame with rivets, Item 9. Refer to Kit Drawing
KGC991–1473, Section B−B. Refer to SRM Chapter 51–42–08.
(9) If removed, install two rivets, Item 11, through the lower flange and the bracket,
Item 3. Refer to Kit Drawing KGC991–1473, Section D−D. Refer to SRM
Chapter 51–42–08.
(10) Temporarily install access panel (185CL).
(11) Use angle, Item 3, and mark the location of the new fastener hole to be drilled
on the access panel.
(12) Remove access panel (185CL).
(13) Temporarily install access panel (186CR).
(14) Use angle, Item 3, and mark the location of the new fastener hole to be drilled
on the access panel.
(15) Remove access panel (186CR).
(16) Drill one hole diameter 0.1875 to 0.1905 in (4.763 to 4.838 mm) in each access
panel (185CL/186CR) at the location of the new attachments.
(17) Countersink holes to 100°. Refer to SRM Chapter 51–40–08.
(18) Drill out the rivets, and remove and discard the eight receptacles, Part No.
B0209022–001, located on the lower flange at FS813.00. Refer to Kit Drawing
KGC991–1473, Detail A (Pre−Mod) and to SRM Chapter 51–42–08.
NOTE: For aircraft Serial No. 9428 and 9429, the receptacles are mounted
on a plate.
(19) Install the nutplates, Item 6, on the new angle. Refer to Kit Drawing
KGC991–1473 and to SRM Chapter 51–42–08.
(20) Install the nutplates, Item 6, to the frame at FS813.00. Refer to Kit Drawing
KGC991–1473, Detail A (Post−Mod) and to SRM Chapter 51–42–08.
MODEL BD−700−1A10 (BD−700)
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 6 of 19

### Page 11

(21) Do touch−up on the rivets with primer and topcoat grey #16473. Refer to SRM
Chapters 51–01–06 and 51–01–08.
(22) Remove and discard the four retaining rings, Part No. B0209020–001, and the
four studs, Part No. B0209021–2S or B0209021–3S, from the fwd side of each
access−panel (185CL/186CR).
(23) Install the new bolts, Part No. 121016–3–897, on the access panels and do
one of the following:
(a) If the aircraft is down long enough for the self−contouring sealing pad to
cure, do not install the new retaining rings at this moment and do the
following steps:
(i) Replace the self−contouring sealing pad where it was removed on
FS813.00. Refer to SPM−Maintenance Chapter 51–23–00.
NOTES: 1. Examine the self−contouring sealing pad on the
fuselage structure for damage or deterioration. If
necessary, replace the self−contouring sealing pad.
2. If applicable, fill the gap between the angle, Item 3, and
the access panels with self−contouring sealant. Refer to
Kit Drawing KGC991–1473, Section D−D.
3. Make sure the sealant does not enter the nutplates and
receptacles.
(ii) Allow time for sealant to fully cure. Refer to SPM−Maintenance
Chapter 51–23–00.
(iii) Remove access panels (185CL/186CR).
(iv) If the self−contouring sealing pad is less than 0.23 in (0.58 mm),
install the retaining rings, Item 10, and continue to step (24).
(v) Spotface to remove a minimum of 0.023 in (0.58 mm) of sealant to
allow clearance for retaining rings, Item 10. Refer to Kit Drawing
KGC991–1473, Note 13.
(vi) If applicable, spotface a minimum of 0.025 in (0.63 mm) of Part No.
GD297–1707 and touch up reworked area as per SRM Chapter
51–01–04. Refer to Kit Drawing KGC991–1473, Note 14.
(vii) Install the retaining rings, Item 10.
(b) If the aircraft is not down long enough for the self−contouring sealing pad
to cure, install the new retaining rings, Item 10.
MODEL BD−700−1A10 (BD−700)
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 7 of 19

### Page 12

(i) Replace the self−contouring sealing pad where it was removed on
FS813.00. Refer to SPM−Maintenance Chapter 51–23–00.
NOTES: 1. Examine the self−contouring sealing pad on the
fuselage structure for damage or deterioration. If
necessary, replace the self−contouring sealing pad.
2. If applicable, fill the gap between the angle, Item 3, and
the access panels with self−contouring sealant. Refer to
Kit Drawing KGC991–1473, Section D−D.
3. Make sure the sealant does not enter the nutplates and
receptacles.
(24) Examine the retainers and studs for good condition and make sure that there is
no sealant inside the retainers and the studs.
(25) Make sure that the surfaces are clean with no corrosion, paint, grease, or
preservation fluids.
(26) Install access panel (186CR). Refer to AMM 53−61−19−400−801.
(27) Install access panel (185CL). Refer to AMM 53−61−19−400−801.
(28) Torque the 10 bolts, Part No. 121016–3–897, on the forward side of the access
panels, from 20 to 25 lbf in (2.26 to 2.83 Nm). Refer to SPM−Maintenance
Chapter 20–21–00.
NOTE: For every 60th installation of the panel, install new nutplates. Refer to
SRM Chapter 51–44–06.
(29) Torque the bolts on the rest of the access panels from 15 to 20 lbf in (1.70 to
2.26 Nm). Refer to SPM−Maintenance Chapter 20–21–00.
NOTE: For every 100th installation of the panel, install new receptacles.
Refer to SRM Chapter 51–44–06.
(30) Do a check of the aerodynamic smoothness of the access panels. Refer to
SRM Chapter 51–14–04.
C. Close−out
Remove all tools, equipment, and unwanted materials from the work area.
D. 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 on−line Service
Bulletin survey:
http://csefeedback.aero.bombardier.com
MODEL BD−700−1A10 (BD−700)
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 8 of 19

### Page 13

3. MATERIAL INFORMATION
A. Kit
Kit 700K53–6008A is necessary to do this Service Bulletin and contains the parts
that follow:
NEW PART NO. QTY ITEM USED PART
NO.
INSTRUCTIONS
- DISPOSITION
121016−3−897 11 Stud Bolt B0209021–2S
or
B0209021–3S
Discard
B0204094−3−1 11 Nutplate B0209022–001 Discard
B0205018AD4−4S 2 Rivet B0205018AD4−4S Discard
B0209078−3 11 Retaining
Ring
B0209020–001 Discard
KGC991−1473−101 1 Angle − −
MS20470AD4−4A−5
or
MS20470AD4−4−5
5 Solid Rivet − −
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.
B. Parts
The parts that follow are necessary to do this Service Bulletin and are available
from Bombardier Aerospace Parts Services, Montreal:
For aircraft Serial No. 9002 to 9426:
NEW PART NO. QTY ITEM USED PART
NO.
INSTRUCTIONS
- DISPOSITION
B0205013M2−3 22 Rivet − −
For aircraft Serial No. 9428 and 9429:
MODEL BD−700−1A10 (BD−700)
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 9 of 19

### Page 14

NEW PART NO. QTY ITEM USED PART
NO.
INSTRUCTIONS
- DISPOSITION
B0205013M2−3 4 Rivet − −
B0205013M2−4 18 Rivet − −
NOTE: The part numbers for the items listed above are subject to change without
revision to this Service Bulletin. In case of discrepancy between this list
and any other list, the Illustrated Parts Catalog prevails and shall be used
to determine the latest part number.
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 PART
NO./NAME
SPECIFICATION QUANTITY SUPPLIER
(SEE
NOTE)
Polyurethane
Fluid−Resistant
Coating
− Grey #16473 As Necessary Code: A
Release
Agent
MS 143H − As Necessary Code: B
Release
Agent, Mold
Allied Resin
RAM 225
− As Necessary Code: C
Seal and
Coat
Compound
− MIL−PRF−81733
Type II, Class I,
Grade A Pro
Seal 870B
As Necessary Code: D
Tape,
Pressure
Sensitive
3M 5498 − As Necessary Code: E
Cloth,
Abrasive,
Aluminum
Oxide,
180–Grit
− − As Necessary Code: F
Cloth,
No−Lint
− − As Necessary Code: F
MODEL BD−700−1A10 (BD−700)
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 10 of 19

### Page 15

DESCRIPTION PART
NO./NAME
SPECIFICATION QUANTITY SUPPLIER
(SEE
NOTE)
Primer − − As Necessary Code: F
Scraper,
Non−Metallic
− − As Necessary Code: F
Spatula (Tool
to Fair
Material)
− − As Necessary Code: F
Tape,
Masking
− − As Necessary Code: F
NOTES: 1. Refer to the table that follows for each suppliers address listed by
codes.
2. The Curing Time (CT), if applicable, for each consumable material is
indicated with the description of each product.
3. At time of release of this Service Bulletin, the information on the
supplier was valid and accurate. In the event that this information has
changed, the operator is encouraged to use the World Wide Web to
find a local supplier.
SUPPLIERS ADDRESSES BY CODES
Code: A
Akzo Nobel Aerospace Coatings
1 E. Water St.
Waukegan, IL, 60085–5635
U.S.A.
Tel.: (847) 625–3336
Fax: (847) 625–3222
www.akzonobel.com
Code: B
Miller−Stephenson Chemical Co.
55 Backus Ave.
Danbury, CT, 06810–7328
U.S.A.
Tel.: (203) 743–4447
Fax: (203) 791–8702
www.miller−stephenson.com
Code: C
Lilly−Ram Chemical Company
1740 E. Monticello Ct.
Ontario, CA, 91761–9699
U.S.A.
Tel.: (909) 223–9699
Fax: (909) 223–9699
www.lillyram.com
Code: D
PRC−Desoto Intl.
5676 Timberlea Blvd.
Mississauga, ON
Canada, L4W 4M6
Tel.: (905) 629–7999
Fax: (905) 629–7009
www.ppgaerospace.com
MODEL BD−700−1A10 (BD−700)
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 11 of 19

### Page 16

SUPPLIERS ADDRESSES BY CODES
Code: E
3M
3M Center Bldg 209
St−Paul, MN, 55144–1000
U.S.A.
Tel.: (800) 235–2376
Fax: (651) 736–5303
www.3m.com
Code: F
Commercially Available
D. Publications
No publications required.
MODEL BD−700−1A10 (BD−700)
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 12 of 19

### Page 17

MODEL BD−700−1A10 (BD−700)
PL KGC991−1473 − Kit − Alternate Fasteners & Brkt Instl − AFT Belly Fairing Panels
(Sheet 1 of 2, Rev. F)
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 13 of 19

### Page 18

MODEL BD−700−1A10 (BD−700)
PL KGC991−1473 − Kit − Alternate Fasteners & Brkt Instl − AFT Belly Fairing Panels
(Sheet 2 of 2, Rev. F)
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 14 of 19

### Page 19

KGC991−1473 − Kit − Alternate Fasteners & Brkt Instl − AFT Belly Fairing Panels
(Sheet 1 of 3, Rev. F)
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 15 of 19

### Page 20

KGC991−1473 − Kit − Alternate Fasteners & Brkt Instl − AFT Belly Fairing Panels
(Sheet 1 of 3 (continued), Rev. F)
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 16 of 19

### Page 21

KGC991−1473 − Kit − Alternate Fasteners & Brkt Instl − AFT Belly Fairing Panels
(Sheet 2 of 3, Rev. F)
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 17 of 19

### Page 22

KGC991−1473 − Kit − Alternate Fasteners & Brkt Instl − AFT Belly Fairing Panels
(Sheet 2 of 3 (continued), Rev. F)
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 18 of 19

### Page 23

KGC991−1473 − Kit − Alternate Fasteners & Brkt Instl − AFT Belly Fairing Panels
(Sheet 3, Rev. F)
Basic Issue: Jul 14/2016
Revision 01: Dec 16/2016
700−53−050
Page 19 of 19

### Page 24

700−53−050 Rev. 01 Dec 16/2016
MODIFICATION — BELLY FAIRINGS —
REPLACEMENT OF ATTACHMENTS FOR THE ACCESS PANELS
In an effort to improve the quality of our technical communications, we are replacing the
standard Service Bulletin Evaluation Form with an on−line Service Bulletin Survey
and we are requesting your feedback. Please take a moment to fill out our easy on−line
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 25

SERVICE BULLETIN INCORPORATION SHEET − "700−53−050"
Upon completion of the Service Bulletin, please fill−in, fax to
(514) 855−8798 or e−mail to Fracas at fracas.montreal@aero.bombardier.com
If 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.
700−53−050 01
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 E−Mail (dd/mm/yy)

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