# Bombardier Service Bulletin 100-53-32

Copy: No revision named ("SB 100-53-32 basic 16-Feb-2017"), 37 pages: PDF https://openairdocs.org/files/sha256/91/f3/91f3a6a0fb4726d04c054aab9018da2bbbd26680df91f4eb6142e7dd17f41535; text https://openairdocs.org/service-documents/bombardier/sb-100-53-32/file/91f3a6a0fb47.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2017-0696; AD 2017-14-16 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Bombardier](https://openairdocs.org/service-documents/bombardier.md)
- Type: Service bulletin (Service Bulletin)
- Number: 100-53-32
- Page: https://openairdocs.org/service-documents/bombardier/sb-100-53-32

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

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

- [AD 2017-14-16](https://openairdocs.org/ad/2017-14-16.md), effective Aug 1, 2017: No revision named

## Text (37 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2017-0696; AD 2017-14-16 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

Feb 22/2017 100-53-32
Page 1 of 1
SERVICE BULLETIN INFORMATION SHEET
MODEL BD-100-1A10 (CH-300)
ATA 53-30
FUSELAGE
MODIFICATION - CENTER FUSELAGE - REPLACEMENT OF IMPROPERLY
INSTALLED HI-LITES
Service Bulletin No.: 100-53-32 Issue: Basic Dated: Feb 16/2017
The following data is supplied for information only.  No revision to the Service Bulletin
is necessary.
Keep this Information Sheet with subject Service Bulletin.
This Information Sheet is issued to inform operators of a typographical error in
Paragraph 3.A.
Therefore, in the parts list of Paragraph 3.A, the quantity of O-ring, Part No.
M25988/2−218 is changed to 10.

### Page 2

MODIFICATION - CENTER FUSELAGE - REPLACEMENT OF IMPROPERLY
INSTALLED HI-LITES
The information below is provided for your reference. For full details, including labor and part
coverage, please see corresponding paragraph contained within this bulletin.
RECOMMENDED
SPECIFIED TIME COMPLIANCE
COMPLIANCE TIME
Within 7500 Flight cycles from
aircraft delivery
EFFECTIVITY: A/C Serial No. 20003 to 20433
MANPOWER: 37 man−hours. Refer to Paragraph 1.F. for details.
CONTINUED AIRWORTHINESS (CAW)
FLEET CAMPAIGN NOYES
TLMC, CH 5 AFFECTED NOYES
KITS and/or PARTS YES NO
TOOLING/GSE YES NO
PLANNING INFORMATION NOYES
DEDICATED SCHEDULE NOYES
PREREQUISITE SERVICE BULLETINS: N/A
NOTE: This Service Bulletin may be subject to an Airworthiness Directive which will make
it necessary to implement this Service Bulletin.
To place an order for parts or kits, please call Bombardier Aerospace Parts Services
at:
514−855−2999 or 1−866−538−1247
SERVICE BULLETIN SUMMARY
www.cic.bombardier.com
MODEL BD−100−1A10 (CH−300)
ATA 53−30
FUSELAGE
Basic Issue: Feb 16/2017 100−53−32
P a g e1o f1
This Service Bulletin is available at:

### Page 3

MODIFICATION - CENTER FUSELAGE - REPLACEMENT OF IMPROPERLY
INSTALLED HI-LITES
1. PLANNING INFORMATION
A. Effectivity
BD−100−1A10 aircraft, Serial No. 20003 to 20433.
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
It was found that some hi−lites were not installed in accordance with specified
procedure. This can cause premature cracks in the FS587.00 fitting and/or frame.
This Service Bulletin installs new hi−lites that accommodate the angle, gaps of the
holes, or unwanted burrs around the holes. This will improve the service life of the
fitting and frame.
C. Description
This Service Bulletin gives instructions to:
− Get access to the fasteners to be replaced,
− Replace all fasteners,
− Install all the components, fuel and hydraulic lines removed for access, and
− Do the necessary tests to make sure the units work correctly.
SERVICE BULLETIN
www.cic.bombardier.com
MODEL BD−100−1A10 (CH−300)
ATA 53−30
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.
© 2017 Bombardier Inc.  All rights reserved
Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.
Basic Issue: Feb 16/2017 100−53−32
Page 1 of 33
This Service Bulletin is available at:

### Page 4

D. Compliance
Recommended within 7500 flight cycles from aircraft delivery.
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 to help you schedule the tasks given in this
bulletin. The man−hours 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
100−00−02.
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.
3. The man −hours are based on the fact that the modification will be
done at the 7500 flight cycle (mid−life) scheduled inspection, including
NDTM Task ET−53−41−003. Therefore no man−hours are allotted to
prepare the aircraft for maintenance or for access for this Service
Bulletin. Some steps of this Service Bulletin, such as
removal/installation/testing of the flap power unit, removal and
installation of hydraulic and fuel lines, bleeding of the hydraulic
systems, are not covered by these labor hours.
40 man−hours are necessary to do the removal and installation of the hydraulic and
fuel lines. Bombardier Aerospace does not pay for the labor to do the removal and
installation of the hydraulic and fuel lines, as this is necessary to do NDTM Task
ET−53−41−003.
37 man−hours are necessary to do the replacement of hi−lites.
The labor required to do the replacement of hi−lites is at no cost if:
− the work is done at Bombardier Business Aviation Services (BBAS) or
Authorized Service Facilities (ASF), and
MODEL BD−100−1A10 (CH−300)
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### Page 5

− this Service Bulletin is scheduled at aircraft 7500 flight cycles (mid−life)
inspection.
G. Material − Cost and Availability
Kit 100K53−32 is necessary to do this modification.
KIT NO. PRICE
100K53−32
Please contact Bombardier Aerospace
Parts Services, in Montreal, for delivery
lead times and confirmation of prices.
This kit is available at no cost if:
− a no−charge purchase order is sent to Bombardier Aerospace, and
− this Service Bulletin is scheduled at aircraft 7500 flight cycles (mid−life)
inspection.
For all parts transactions, Bombardier Aerospace’s current Spare Parts and
Component Repair Price Catalogue General Terms and Conditions apply. These
terms and conditions are found on the CIC website.
During or after the above free period, Smart Parts Plus does not pay for the kit.
H. Tooling
The equipment and tools listed below are necessary to do this modification:
GSE REFERENCE NO. PART NO. DESCRIPTION
20−00−04 KS5549 Inclinometer
20X−00−04 M1−G−KIT Portable Bonding Tester
20−00−26 G604−200026−1 Gaseous Test Panel
24−00−24 S4933959−501 Circuit Breaker Tag
29−10−02 DLTFRPSKT3001 Deutsch PermaswagingTool Kit
− BH7475−T7351 Calibration ReferenceStandard
− Hocking Model: 33A103or equivalent Cable
− Hocking Model: Phasec2200 or equivalent Eddy Current Instrument,Impedence Plane−type
MODEL BD−100−1A10 (CH−300)
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Page 3 of 33

### Page 6

GSE REFERENCE NO. PART NO. DESCRIPTION
− Hocking Model: 33A100or equivalent Mini Drive Unit
−
NDT Eng Corp Model:
BYMH 3/16−14 or
equivalent
Plastic Rotating
Bolt−hole Probe, 100
kHz to 1.0 MHz
frequency range,
differential, shielded,
0.187 in (4.75 mm)
diameter adjustable to
0.250 in. (6.35 mm)
− ST8954C or equivalent Spreader
− Commercially Available Chipless Tube Cutter
− Commercially Available High Intensity LightSource
− Commercially Available Caps, Plastic, Fuel andHydraulic Fluid resistant
− Commercially Available Container, Hydraulicfluid, 1 gallon
− Commercially Available Stopwatch
− Commercially Available Tape, Double−sided
− Commercially Available Torque Wrench
NOTES: 1. Refer to the CH 300 Illustrated Tool and Equipment Manual (ITEM) to
make sure that you use the correct equipment configuration.
2. Refer to the Liability Statement in the ITEM for acceptable GSE
equivalents.
I. Weight and Balance
No change.
J. Electrical Load Data
No change.
K. References
− Bombardier Aerospace, Modification Summary, BB100T010801, Rev. C.
MODEL BD−100−1A10 (CH−300)
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### Page 7

− Bombardier Aerospace, Restriction and/or Special Instruction (RSI),
C−100−000−53−0068, Rev. A.
− Bombardier Aerospace, Kit Drawing K1000070322, Rev. B.
− Bombardier Aerospace, SB 100−00−02, Service Bulletin Description and Policy.
− CH 300 Aircraft Maintenance Manual (AMM), Chapters 6, 7, 24, 27, 28, 29, 31
and 53.
− CH 300 Structural Repair Manual (SRM), Chapter 51.
− CH 300 Nondestructive Testing Manual (NDTM), Part 1.
− Bombardier Aerospace, Standard Practices Manual (SPM), Chapters 20 and 51.
− Appendix 1: Fasteners Condition Report Form (attached).
L. Other Publications Affected
None.
M. Equivalent Service Bulletin
None.
2. ACCOMPLISHMENT INSTRUCTIONS
NOTE: All references made to zones, access panels and/or doors, are from the CH
300 AMM, Chapter 6.
A. Aircraft Setup
(1) Obey all electrical/electronic safety precautions. Refer to
AMM 24−00−00−910−801.
(2) Obey all fuel safety precautions. Refer to AMM 28 −00−00−910−801.
(3) Obey all hydraulic safety precautions. Refer to AMM 29 −00−00−910−801.
(4) Obey all hydraulic technical precautions. Refer to AMM 29 −00−00−910−802.
(5) Put the aircraft on jacks. Refer to AMM 07 −10−01−582−801.
(6) Release hydraulic pressure from the left and right hydraulic systems. Refer to
AMM 29−10−00−862−802.
(7) Remove the electrical power from the aircraft. Refer to
AMM 24−00−00−861−802.
(8) Make sure to protect all electrical/electronic equipment and wiring from debris.
(9) Prepare the fuel tank for access. Refer to AMM 28 −10−00−840−801.
(10) Remove the Left and Right Main Landing Gear (MLG) Wheel Bin. Refer to
AMM 53−32−01−000−801.
(11) Remove the Aft Under−Wing Fairing 182BB. Refer to
AMM 53−63−05−000−801.
MODEL BD−100−1A10 (CH−300)
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### Page 8

(12) Remove the wing−tank access panels that follow. Refer to
AMM 28−11−01−000−801:
ACCESS DESIGNATION
161AB/162AB Wing−Tank Access panel
161BB/162BB Wing−Tank Access panel
161AZ/162AZ Wing−Tank Access panel
(13) Remove the Flap Power Unit. Refer to AMM 27−52−33−000−801.
(14) Remove the Triaxial Accelerometer. Refer to AMM 31−31−09−000−801.
B. Fuel and Hydraulic Line Removal
CAUTION: MAKE SURE THAT YOU PUT A PROTECTIVE COVER OR CAP ON
ALL OPEN HYDRAULIC AND FUEL LINES AND COMPONENT
FITTINGS. IF YOU DO NOT DO THIS IMMEDIATELY AFTER THEY
ARE DISCONNECTED, UNWANTED MATERIALS CAN GO INTO
THE HYDRAULIC AND FUEL SYSTEM. THIS CAN CAUSE
DAMAGE TO THE HYDRAULIC AND FUEL SYSTEM.
(1) Remove the engine and auxiliary power unit (APU) fuel lines (8), (9), and (10)
and connections as follow. Refer to Figure 1.
(a) Remove the four screws (1) and four washers (2) and open the two
clamps (3), as shown in Detail C.
(b) Disconnect and remove the tubes (8), (9), and (10) from the fittings (19)
and (20) as follow. Refer to Details D and E.
(i) Open the couplings (16) and (15), and disconnect the tube (8) from
the fitting (19). Refer to Detail D.
(ii) Open the couplings (18) and (17), and disconnect the tubes (9) and
(10) from the fittings (20). Refer to Detail E.
(iii) Discard the o −rings (21), (22), and (23).
(c) Disconnect and remove the tubes (8), (9), and (10) as follow. Refer to
Detail F.
(i) Open the couplings,(5) and (7), disconnect and remove the tube (8).
(ii) Open the couplings, (4) and (6), disconnect and remove the tubes (9)
and (10).
(iii) Discard the o −rings (11), (12), (13) and (14).
(d) Remove the motive flow line (45) as follow:
(i) Disconnect the coupling (50) as follow. Refer to Detail I.
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a Loosen the fitting and disconnect the tube (48) from the coupling
(50). Discard the packing (49)
b Open the coupling (50) and disconnect the motive flow line (45).
c Discard the o−rings (51).
(ii) Disconnect the coupling (46) as follow. Refer to Detail H.
a Open the coupling (46) and remove the motive flow line (45).
b Discard the o−rings (47).
(e) Remove the fittings (19) and (20) as follow. Refer to Detail G.
(i) Loosen and disconnect reducers (31), (32) and (33). Discard the three
o−rings (34).
(ii) Remove the fitting (19) as follows:
a Remove the sealant around the fitting (19) and the bolts (25).
Refer to SPM−MM 51−23−00−100−801.
b Remove the four bolts (25) and four washers (27).
c Remove the two bolts (26), two washers (28), and two nuts (30).
d Open the coupling (35), and remove the fitting (19) and plate
(36). Discard the o−rings (37) and (38), and gasket (39).
(iii) Remove each fitting (20) as follows:
a Remove the sealant around the fitting (20) and the bolts (25).
Refer to SPM−MM 51−23−00−100−801.
b Remove the four bolts (25) and four washers (27).
c Remove the two bolts (26), two washers (28), and two nuts (30).
d Open the couplings (40), and remove the fittings (20) and plates
(41). Discard the o−rings (42) and (43) and gaskets (44).
(2) Remove the hydraulic brackets (13) and (14) as follow. Refer to Figure 2,
Detail B.
(a) Disconnect the hoses (1), (2), (3) and (4).
(b) Remove the two nuts (5), two nuts (6), two washers (7) and two washers
(8).
(c) Remove the screw (9) and the washer (10), and pull away the harness
with the clamp (11).
(d) Drill off the 12 rivets (12) from the brackets (13) and (14).
(e) Remove the brackets (13) and (14).
MODEL BD−100−1A10 (CH−300)
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### Page 10

(3) Loosen the hydraulic lines (16) and (17), and remove line (18) and (19) as
follow. Refer to Figure 2.
(a) Loosen the nuts and disconnect the hose (20). Refer to Detail C.
(b) Remove the nut (22) and washers (24) and (25). Refer to Detail C.
(c) Loosen the nuts and disconnect the hoses (21). Refer to Detail D.
(d) Remove the nut (23) and the two washers (26). Refer to Detail D.
(e) Loosen the b −nuts (28), (29), and (30). Refer to Detail E.
(f) Loosen the b −nuts (27) and (31). Refer to Detail F.
(g) Remove the two screws (34) and the two washer (15) and open the
fairlead block (35). Refer to Detail F.
(h) Remove the five screws (32) and the five washers (33). Refer to Details B,
E, and F.
(i) Remove the hydraulic lines (18) and (19). Refer to Detail B.
(j) Cut the hydraulic line (16) as follows.
NOTE: Make sure you are within the repair limits of the hydraulic line
(16). Refer to SPM−MM 20−22−00−910−805.
(i) At a minimum 1.5625 in (39.69 mm) from the start of the bend, cut the
hydraulic line (16) with a chipless cutter. Refer to Detail G.
(ii) Remove the hydraulic line (16).
(iii) Install caps on the open ends of the hydraulic line (16).
(k) Move the hydraulic lines (16) and (17) away from the work zone, and hold
in place with ropes or tie−wraps. Refer to Detail F.
NOTE: Make sure not to cause any permanent deformation of the
hydraulic lines.
C. Hi −Lite Replacement
(1) Replace each hi −lite that attaches the fitting to the frame as follow. Refer to Kit
Drawing K1000070322.
NOTES: Remove and install 20 fasteners at a time, in the sequence that
follows. Refer to the figure in note 12 of the kit drawing for location of
rows.
1. Forward (Row 1 and 2)
2. Aft (Row 1 and 2)
(a) Do an inspection for missing, broken, or deformed fastener. Record the
inspection on the Fasteners Condition Report Form. Refer to Appendix 1.
(b) Clean the area around the holes to remove contaminant.
MODEL BD−100−1A10 (CH−300)
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(c) Remove the hi −lites. Refer to SRM 51−42−36.
NOTES: 1. Use the spreader if necessary to remove the hi −lites pins
from the holes.
2. Make sure not to cause damage to the fitting or the
surrounding structure.
(d) Deburr and chamfer the holes, if required. Refer to SRM 51 −42−36.
(e) Do an eddy current inspection of the hole for damage as follows.: Refer to
NDT Manual, Part 1, Section 6E. If damage is found, do as follows:
(i) Record the damage on the Fasteners Condition Report Form. Refer
to Appendix 1.
(ii) Send an SRPSA with the necessary details by e −mail at
SRPSA@aero.bombardier.com
(f) If required, touch −up the area around the holes with primer. Refer to
SRM 51−01−06.
(g) Wet install the hi −lites with sealant. Refer to
SPM−MM 51−23−00−390−809.
NOTE: Fasteners can be installed in any direction.
(h) Install the collars wet with primer at the mating surface of the collar and
the structure.
(2) Touch up fastener with topcoat.
(3) Scan and send the completed Fasteners Condition Report Form (Appendix 1)
to:
bbad_challenger_stress@aero.bombardier.com
D. Fuel and Hydraulic Line Connection
(1) Put the hydraulic lines (16) and (17) in position. Refer to Figure 2.
NOTE: Make sure there is no permanent deformation of the hydraulic lines.
(2) Install the nut (22) and the washers (24) and (25). Refer to
SPM−MM 20−22−00−910−801 and Figure 2, Detail C.
(3) Connect the hose (20). Refer to SPM −MM 20−22−00−910−801 and Figure 2,
Detail C.
(4) Put hydraulic line (17) in position with the nut (23) and the two washers (26).
Refer to SPM−MM 20−22−00−910−801 and Figure 2, Detail D.
(5) Connect the hose (21). Refer to SPM −MM 20−22−00−910−801 and Figure 2,
Detail D.
MODEL BD−100−1A10 (CH−300)
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### Page 12

(6) Install the hydraulic brackets as follow. Refer to Figure 2, Detail B:
(a) Put the brackets (13) and (14) in position, with faying surface sealant.
Refer to SPM−MM 51−23−00−390−803.
(b) Wet install the 12 rivets, Part no. MS20470AD5 −8 (12). Refer to
SPM−MM 51−23−00−390−809 and SRM 51−42−08.
(c) Put the harness and the clamp (11) back into position, and install the
screw (9) and the washer (10). Refer to SPM−MM 20−21−00−910−801.
(d) Put the hydraulic line (18) and (19) in position. Install the clamps with two
of the screws (32) and two washers (33). Refer to Detail B and E.
(e) Install the two nuts (5), the two nuts (6), the four washers (7) and two
washer (8). Refer to SPM−MM 20−22−00−910−801.
(7) Connect the hoses (1), (2), (3), (4). Refer to SPM −MM 20−22−00−910−801
and Figure 2, Detail B.
(8) Connect the hydraulic lines (16) and (17) and tighten the b −nuts (27) and (31).
Refer to SPM−MM 20−22−00−910−801 and Figure 2, Detail F.
(9) Connect hydraulic line (16) as follow. Refer to Figure 2, Detail G.
(a) Prepare the ends of the hydraulic line (16). Refer to
SPM−MM 20−30−00−910−807.
(b) Put the union (36), Part no. B0301010 −10 in position over the hydraulic
line (16).
(c) Swage the union (36) on the hydraulic line (16). Refer to
SPM−MM 20−30−00−910−807.
(10) Connect the hydraulic lines (18) and (19) and tighten the b−nuts (28), (29), and
(30). Refer to SPM−MM 20−22−00−910−801 and Figure 2, Detail E.
(11) Install the three clamps holding the hydraulic line (16) and (17) with the three
screws (32) and the three washers (33). Refer to Figure 2, Detail F.
(12) Install the fairlead (35) with the two screws (34) and the two washers (15).
Refer to Figure 2, Detail F.
(13) Install the engine and APU fuel lines as follow. Refer to Figure 1.
(a) Install the fitting (19) as follow. Refer to Detail G.
(i) Lubricate the new o −rings, one Part No. MS29513−114 (37) and two
o−rings, Part No. M25988/2−015 (38) with petrolatum.
(ii) Install new o −rings (37) and (38) on the fitting (19) and tube to be
connected.
(iii) Put the fitting (19) and the plate (36) with the new gasket, Part No.
1005714057−007 (39) in position.
(iv) Close the coupling (35). Refer to SPM −MM 20−30−00−910−804.
(v) Install the fitting (19), the plate (36), and the gasket (39).
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### Page 13

(vi) Install the four bolts (25) with the four washers (27). Refer to
SPM−MM 20−21−00−910−801.
(vii) Do an electrical bonding test between the fitting (19) and the
structure. Make sure the value is less than 100 milliohms. Refer to
SPM−MM 51−80−00−760−801.
(viii) Do a fillet seal around the fitting (19) and the plate (36). Refer to
SPM−MM 51−23−00−390−805.
(ix) Brushcoat seal the bolts (25). Refer to
SPM−MM 51−23−00−390−811.
NOTE: Make sure the sealing of the bolt (25) meets the requirement
that follow:
− Sealant over the bolts (25) must be at least 0.06 in
(1.53 mm) thick.
− Sealant thickness at the base of the bolts (25) and
around washers (27) must be at least 0.1 in (2.54 mm)
thick.
− No exposed metal.
− No voids or holes in the outer surface of the sealant.
− No visible outline of the bolts (25) threads.
(b) Install the two fitting (20) as follow. Refer to Detail G.
(i) Lubricate the new o −rings, Part No. MS29513−127 (42) and Part No.
MS25988/2−218 (43) with petrolatum.
(ii) Install the new o −rings (42) and (43) on the fitting (20) and the tube to
be connected.
(iii) Put the fitting (20) and the plate (41) with the new gasket, Part No.
1005714057−003 (44) in position.
(iv) Close the coupling (40). Refer to SPM −MM 20−30−00−910−804.
(v) Install the fitting (20) and the plate (41). Refer to
SPM−MM 51−23−00−390−803
(vi) Install the four bolts (25) with the four washers (27). Refer to
SPM−MM 20−21−00−910−801.
(vii) Do an electrical bonding test between the fittings (20) and the
structure. Make sure the value is less than 100 milliohms. Refer to
SPM−MM 51−80−00−760−801.
(viii) Do a fillet seal around the fitting (20) and the plate (41). Refer to
SPM−MM 51−23−00−390−805.
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(ix) Brushcoat seal the bolts (25). Refer to
SPM−MM 51−23−00−390−811.
NOTE: Make sure the sealing of the bolt (25) meets the requirement
that follow:
− Sealant over the bolts (25) must be at least 0.06 in
(1.53 mm) thick.
− Sealant thickness at the base of the bolts (25) and
around washers (27) must be at least 0.1 in (2.54 mm)
thick.
− No exposed metal.
− No voids or holes in the outer surface of the sealant
− No visible outline of the bolts (25) threads.
(c) Install the two bolts (26) with the two washers (28), and the two nuts (30)
at the fitting (19) and (20). Refer to SPM−MM 20−21−00−910−801 and
Detail G.
(d) Connect and torque the reducers (31), (32) and (33), with new o −rings,
Part No. MS29512−04 (34), lubricated with petrolatum. Refer to
SPM−MM 20−22−00−910−801 and Detail G
(e) Connect the tube (8) to the fitting (19) with the new o −rings, Part No.
MS25988/2−015 (21) and MS25988/2−218 (22). Close the couplings (15)
and (16). Refer to SPM−MM 20−30−00−910−804 and Detail D.
(f) Connect the tubes (9) and (10) to the two fittings (20) with the new
o−rings, Part No. MS25988/2−218 (22) and MS25988/2−226 (23). Close
the couplings (17) and (18). Refer to SPM−MM 20−30−00−910−804 and
Detail E.
(g) Connect the tube (8) with new o −rings, Part No. M25988/1−015 (11) and
MS25988/1−218 (12). Close the couplings (5) and (7). Refer to
SPM−MM 20−30−00−910−804 and Detail F.
(h) Connect the tubes (9) and (10) with the new o −rings, Part No.
MS25988/1−218 (13) and MS259881−226 (14). Close the couplings (6)
and (4). Refer to SPM−MM 20−30−00−910−804 and Detail F.
(i) Install the motive flow line (45) as follow.
(i) Put the motive flow line (45) in position.
(ii) Connect the coupling (50) as follow. Refer to Detail I.
a Lubricate the o−rings (51), Part No. M25988/1−222 and packing
(49), Part No. MS29512−06, with petrolatum.
b Connect the motive flow line (45) with the o−rings (51) and the
coupling (50). Close the coupling (50). Refer to
SPM−MM 20−30−00−910−804.
c Connect the tube (48) to the coupling (50) with the packing (49)
MODEL BD−100−1A10 (CH−300)
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### Page 15

(iii) Connect the coupling (46) as follow. Refer to Detail H.
a Lubricate the o−rings (47), Part No. M25988/2−224 with
petrolatum.
b Connect the motive flow line (45) with the o−rings (47) and the
coupling (46). Close the coupling (46). Refer to
SPM−MM 20−30−00−910−804.
(j) Do an electrical bonding test of the APU and engine fuel line (8), (9), and
(10), and the motive flow line (45), across the couplings (4), (5), (16), (18),
(46), and (50). Make sure the value is less than 1000 milliohms. Refer to
SPM−MM 51−80−00−760−801.
(k) Close the two clamps (3), with the screws (1) and the washers (2). Refer
to SPM−MM 20−21−00−910−801 and Detail C.
(14) Apply corrosion−inhibiting compound on the reworked area. Refer to
SRM 51−27−16.
E. Testing
(1) Install the Flap Power Unit. Refer to AMM 27 −52−33−400−801.
(2) Install the Triaxial Accelerometer. Refer to AMM 31 −31−09−400−801.
(3) Remove all tools, equipment and unwanted materials from the aircraft.
(4) Close the fuel tank after maintenance. Refer to AMM 28 −10−00−840−803.
(5) Install the wing −tank access panels that follow. Refer to
AMM 28−11−01−400−801:
ACCESS DESIGNATION
161AB/162AB Wing−Tank Access panel
161BB/162BB Wing−Tank Access panel
161AZ/162AZ Wing−Tank Access panel
(6) Bleed the left and right hydraulic systems. Refer to AMM 29 −10−00−870−801.
(7) Lower the aircraft from jacks. Refer to AMM 07 −10−01−586−801.
(8) Do a functional test (pressure test) of the Fuel Line Shroud. Refer to
AMM 28−21−00−780−801.
(9) Apply fuel pressure to the engine. Refer to AMM 28 −21−00−862−801.
(10) Make sure that there is no fuel leak and that hydraulic leaks are within the
limits. Refer to AMM 29−00−00−790−801.
(11) Do an operational test of the APU fuel line as follow:
(a) Make sure that the right dc boost pump is turned to AUTO.
MODEL BD−100−1A10 (CH−300)
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### Page 16

(b) Make sure that the condition that follows occurs:
REFERENCE POSITION/INDICATION
On the fuel synoptic page The fuel feed lines to the APU
show green or white
WARNING: OBEY ALL THE APU SAFETY PRECAUTIONS WHEN YOU DO
MAINTENANCE ON OR NEAR THE APU AND RELATED
EQUIPMENT. IF YOU DO NOT OBEY THE SAFETY
PRECAUTIONS, YOU CAN CAUSE INJURY TO PERSONS
AND DAMAGE TO THE EQUIPMENT.
WARNING: BE CAREFUL WHEN YOU ARE BELOW THE APU ACCESS
PANEL OR NEAR THE APU DRAIN OPENINGS. VERY HOT
FLUIDS CAN COME OUT OF THE DRAIN OPENINGS. THIS
CAN OCCUR DURING AN APU START SEQUENCE, WHILE
THE APU OPERATES, OR AT THE APU SHUTDOWN (AND A
SHORT TIME AFTER). THIS CAN CAUSE INJURY TO
PERSONS.
(c) Start the APU. Refer to AMM 49 −11−00−866−801.
(d) Operate the APU for 10 minutes
(e) While the APU operates, examine the APU fuel −feed line and connections
for leaks. No leaks are permitted.
(f) Do an APU shutdown (normal). Refer to AMM 49 −11−00−866−802.
(g) Make sure that the condition that follows occurs:
REFERENCE POSITION/INDICATION
On the fuel synoptic page The line from the right dc boost
pump to the right engine shows
white
(h) Examine the APU fuel line (8) and connections again for leaks. No leaks
are permitted.
(12) Do the leak test for the Flap Power Unit. Refer to AMM 27−52−33−790−801.
(13) Do the electrical rigging of the Flap System. Refer to
AMM 27−52−00−820−801.
(14) Do the operational test of the Flap Transmission Brake. Refer to
AMM 27−52−19−710−801.
(15) Do the functional test of the Flap System (Stopwatch Check). Refer to
AMM 27−52−00−720−801.
(16) Do the functional test of the Flap System (Clinometer Check). Refer to
AMM 27−52−00−720−805.
MODEL BD−100−1A10 (CH−300)
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### Page 17

F. Close −out
(1) Remove all tools, equipment and unwanted materials from the aircraft.
(2) Install the Aft Under −Wing Fairing 182BB. Refer to AMM 53−63−05−400−801.
(3) Install the Left and Right Main Landing Gear (MLG) Wheel Bin. Refer to
AMM 53−32−01−400−801.
G. 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
3. MATERIAL INFORMATION
A. Kits
Kit 100K53−32 is necessary to do this modification and contains the parts that
follow:
NEW PART NO. QTY ITEM USED PARTNO. INSTRUCTIONS-DISPOSITION
1005714057−003 2 Gasket 1005714057−003 Discard
1005714057−007 1 Gasket 1005714057−007 Discard
B0301010−10 1 Union,Permaswage − −
HST1275TP6AWU
(B0206019TP6AWU) 44
Collar,
Tension,
Self−Align
B0206010CK
B0206013DU Discard
HST536NAP6NAT−9 27
Pin,
Tension,
Self−Align
B0206001AG6−9 Discard
HST536NAP6NAT−10 18
Pin,
Tension,
Self−Align
B0206003AG6−10 Discard
MODEL BD−100−1A10 (CH−300)
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### Page 18

NEW PART NO. QTY ITEM USED PARTNO. INSTRUCTIONS-DISPOSITION
M25988/1−015 2 O−ring M25988/1−015 Discard
M25988/1−218 6 O−ring M25988/1−218 Discard
M25988/1−222 2 O−ring M25988/1−222 Discard
M25988/1−226 4 O−ring M25988/1−226 Discard
M25988/2−015 4 O−ring M25988/2−015 Discard
M25988/2−218 6 O−ring M25988/2−218 Discard
M25988/2−224 2 O−ring M25988/2−224 Discard
M25988/2−226 4 O−ring M25988/2−226 Discard
MS20470AD5−8A 18 Rivet MS20470AD5−8A Discard
MS29512−04 3 Packing,Preformed MS29512−04 Discard
MS29512−06 1 Packing,Preformed MS29512−06 Discard
MS29513−114 1 Packing,Preformed MS29513−114 Discard
MS29513−127 4 Packing,Preformed MS29513−127 Discard
NOTES: 1. In case of discrepancy between this list and the Service Bulletin Kit
Parts List contained in the respective kit, then the later 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
No parts required.
C. Material
The materials that follow, or equivalent, are necessary to do this Service Bulletin.
These can be purchased from a local supplier. Bombardier Aerospace does not pay
for these consumables.
MODEL BD−100−1A10 (CH−300)
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Page 16 of 33

### Page 19

DESCRIPTION PARTNO./NAME SPECIFICATION QUANTITY
SUPPLIER
(SEE
NOTE)
Polyurethane
Topcoat
CT: 6 hours
−
BAMS 565−002
Color: Grey
#16473 per
FED−STD−595)
As Necessary Code: A
Primer, Epoxy
CT: 3.5 hours − BAMS 565−001 As Necessary Code: A
Sealant
CT: B−1/2 (30
hrs)
B−2 (48 hrs)
B−4 (72 hrs)
Pro−Seal 870
Class B
MIL−PRF−81733
Type II, Class 1,
Grade A
As Necessary Code: B
Compound,
Corrosion
Inhibiting
ARDROX
AV−8
or
Cor−Ban 23
MIL−PRF−16173,
Type 1 As Necessary Code: CCode: D
Grease,
Long−Term
Lubrication
Molykote DX − As Necessary Code: E
Marker DykemDX−100 − As Necessary Code: F
Aliphatic
Naphta − TT−N−95, TypeII As Necessary Code: G
Cloth,
Lint−Free − − As Necessary Code: G
Coating
Chemical
Conversion
Alodine
1200S
MIL−DTL−81706,
Class 1A As Necessary Code: G
Ferrule,
Safety Cable − SAEAS3510−02F As Necessary Code: G
Grease,
Aircraft and
Instrument
Gear and
Actuator
Screw
− MIL−PRF−23827C,Type I As Necessary Code: G
MODEL BD−100−1A10 (CH−300)
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Page 17 of 33

### Page 20

DESCRIPTION PARTNO./NAME SPECIFICATION QUANTITY
SUPPLIER
(SEE
NOTE)
Lockwire,
CRES 0.032
in (0.81mm)
− MS20995C32 As Necessary Code: G
Oil,
Lubricating,
Presevative,
Medium
− MIL−PRF−3150 As Necessary Code: G
Petrolatum − VV−P−236 As Necessary Code: G
Safety Cable − SAEAS3510−0206C As Necessary Code: G
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
Tempo Aerospace.
205 Fenmar Dr.
North York, ON, Canada
M9L 2X4
Tel.: (416) 746−2233
Tel.: (416) 746−2235
www.tempo−aeropace.com
Code: B
PRC−DeSoto International Inc.
5454 San Fernando Road,
PO Box 1800
Glendale, CA 91209
U.S.A.
Tel.: (818) 240−2060
Fax: (818) 549−7627
www.ppg.com/prc−desoto
MODEL BD−100−1A10 (CH−300)
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Page 18 of 33

### Page 21

SUPPLIERS ADDRESSES BY CODES
Code: C
Chemetall North America
675 Central Avenue
New Providence, NJ 07974
Tel.: (908) 464−6900
Tel.: (908) 464−7914
www.chemetallna.com
Code: D
ZIP CHEM Products
400 Jarvis Drive
Morgan Hill, CA 95037
U.S.A.
Tel.: (408) 782−2335
Fax: (408) 782−6304
www.zipchem.com
Code: E
Dow Corning Corporation
2200 W. Salzburg Rd.
PO Box 994
Auburn MI 48611
U.S.A.
Tel.: (800) 248−7875
www.dowcorning.com
Code: F
ITW Pro Brands
805 E. Old Highway
Olathe KS 66061
U.S.A.
Tel.: (800) 443−9536
itwprofessionalbrands.com
Code: G
Commercially Available
D. Publications
No publications required.
MODEL BD−100−1A10 (CH−300)
Basic Issue: Feb 16/2017 100−53−32
Page 19 of 33

### Page 22

A
CSB5332_010
A
G
B
MODEL BD−100−1A10 (CH−300)
Fuel Line Access
Figure 1  (Sheet 1 of 6)
Basic Issue: Feb 16/2017 100−53−32
Page 20 of 33

### Page 23

D
E
C
F
B
CSB5332_011
8 9 10
I
H
MODEL BD−100−1A10 (CH−300)
Fuel Line Access
Figure 1  (Sheet 2 of 6)
Basic Issue: Feb 16/2017 100−53−32
Page 21 of 33

### Page 24

CSB5332_012
C
E
D
3
1
2
19
21
22
15
16
22
21 8
9
22
23
18
17
23
22
20
10
MODEL BD−100−1A10 (CH−300)
Fuel Line Access
Figure 1  (Sheet 3 of 6)
Basic Issue: Feb 16/2017 100−53−32
Page 22 of 33

### Page 25

CSB5332_013
F
12
11
7
14
13
6
14
13
6
4
5
8
4
10
9
MODEL BD−100−1A10 (CH−300)
Fuel Line Access
Figure 1  (Sheet 4 of 6)
Basic Issue: Feb 16/2017 100−53−32
Page 23 of 33

### Page 26

44
26
28
30
26
28
30
25
25
27
27
20
38
35
38
36
39
37
19
34
34
42
G
20
41
31
32
4340
43
34
33
CSB5332_014
MODEL BD−100−1A10 (CH−300)
Fuel Line Access
Figure 1  (Sheet 5 of 6)
Basic Issue: Feb 16/2017 100−53−32
Page 24 of 33

### Page 27

CSB5332_015
45
H
46
47
I
51
50
51
45 48
49
MODEL BD−100−1A10 (CH−300)
Fuel Line Access
Figure 1  (Sheet 6 of 6)
Basic Issue: Feb 16/2017 100−53−32
Page 25 of 33

### Page 28

CSB5332_001
E
A
A
BC
D
MODEL BD−100−1A10 (CH−300)
Hydraulic Line Access
Figure 2 (Sheet 1 of 4)
Basic Issue: Feb 16/2017 100−53−32
Page 26 of 33

### Page 29

CSB5332_002
23
21
26D
26
B
19
8 7
5
7
33
32
5
12
8
18
6
7
7
8
6
14
21
3
4
9
10
1112
24
25
22
16
C
20
13
17
MODEL BD−100−1A10 (CH−300)
Hydraulic Line Access
Figure 2 (Sheet 2 of 4)
Basic Issue: Feb 16/2017 100−53−32
Page 27 of 33

### Page 30

CSB5332_003
E
33
32
28
30
29
18
19
MODEL BD−100−1A10 (CH−300)
Hydraulic Line Access
Figure 2 (Sheet 3 of 4)
Basic Issue: Feb 16/2017 100−53−32
Page 28 of 33

### Page 31

27
3134
15
34
15
3233
32
33
33
32
35
CSB5332_004
F
F
16
17
G
G
16
36
1.5625 in
(39.69 mm)
MINIMUM
MODEL BD−100−1A10 (CH−300)
Hydraulic Line Access
Figure 2 (Sheet 4 of 4)
Basic Issue: Feb 16/2017 100−53−32
Page 29 of 33

### Page 32

K1000070322−B−S1−PL
MODEL BD−100−1A10 (CH−300)
PL K1000070322 − Kit − Fastener Replacement, Rear Spar Frame Assy, FS 587.032
(Sheet 1 of 2, Rev. B)
Basic Issue: Feb 16/2017 100−53−32
Page 30 of 33

### Page 33

K1000070322−B−S2−PL
MODEL BD−100−1A10 (CH−300)
PL K1000070322 − Kit − Fastener Replacement, Rear Spar Frame Assy, FS 587.032
(Sheet 2 of 2, Rev. B)
Basic Issue: Feb 16/2017 100−53−32
Page 31 of 33

### Page 34

K1000070322−B−S1−1
K1000070322 − Kit − Fastener Replacement, Rear Spar Frame Assy, FS 587.032
(Sheet 1 of 1, Rev. B)
Basic Issue: Feb 16/2017 100−53−32
Page 32 of 33

### Page 35

K1000070322−B−S1−2
K1000070322 − Kit − Fastener Replacement, Rear Spar Frame Assy, FS 587.032
(Sheet 1 of 1, Rev. B, continued)
Basic Issue: Feb 16/2017 100−53−32
Page 33 of 33

### Page 36

100−53−32 Basic Feb 16/2017
MODIFICATION − CENTER FUSELAGE − REPLACEMENT OF
IMPROPERLY INSTALLED HI−LITES
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 37

SERVICE BULLETIN INCORPORATION SHEET − "100−53−32"
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.
100−53−32 Basic
COMPLIED WITH
YES    NO    N/A
Actual hours to accomplish Service Bulletin:
* NOTES:
Aircraft Serial No. Aircraft Reg. No.
Airframe Hours: Airframe Landings
S.B. Incorporation Date Service Order No.
Facility incorporating S.B.
Name Signature Date
BOMBARDIER
SUBMISSION
Service Bulletin
Number
Rev. * Parts
Completed
Remarks/Reason
1. Where the Service Bulletin is divided into a number of parts (e.g., PARTS A,
B, C, D, etc.) which can be carried out separately, indicate only those parts
completed at this time.
2. For repetitive checks (usually PART A) only the initial check should be
reported unless otherwise stated in the Service Bulletin.
3. When more than one part is carried out at the same time, each part should
be reported.
(dd/mm/yy)
Signature not required if sent by E−Mail (dd/mm/yy)

---
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