# Bombardier Service Bulletin 604-29-013

Copy: Revision 02 ("604−29−013_Rev 2- BOMBARDIER"), 58 pages: PDF https://openairdocs.org/files/sha256/5e/16/5e16e0ea1f605913bcfc3a55bb510153f512ac4a7b24b3c936345bebea7197d5; text https://openairdocs.org/service-documents/bombardier/sb-604-29-013/file/5e16e0ea1f60.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2018-0790; AD 2019-08-08 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Bombardier](https://openairdocs.org/service-documents/bombardier.md)
- Type: Service bulletin (Service Bulletin)
- Number: 604-29-013
- Latest revision known: 604-29-013, Revision 02, dated April 18, 2016 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/bombardier/sb-604-29-013

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

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

- [AD 2019-08-08](https://openairdocs.org/ad/2019-08-08.md), effective Jun 27, 2019: Revisions 01 and 02

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-604-29-013/proposed.md).

## Text (58 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2018-0790; AD 2019-08-08 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Some pages are 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

Sep 21/2016 604-29-013
Page 1 of 1
SERVICE BULLETIN INFORMATION SHEET
MODEL CL-600-2B16
ATA 29-12
HYDRAULIC POWER
MODIFICATION – HYDRAULIC SYSTEM NO. 3 – RELOCATION OF THE HYDRAULIC
SYSTEM NO. 3 ACCUMULATOR
Service Bulletin No.: 604-29-013 Issue: Revision 02 Dated: Apr 18/2016
The following data is supplied for information only.  No revisi on to the Service Bulletin
is necessary.
Keep this Information Sheet with subject Service Bulletin.
This Information Sheet is issued to modify the Smart Parts Plus  statement in
Paragraph 1.G., Material – Cost and Availability.
The statement now reads as follows:
Smart Parts Plus pays for the kits up to 8 years from the Servi ce Bulletin distribution
date (Basic Issue).

### Page 2

Discard the Revision 01 of this Service Bulletin dated Oct 19/2015, and replace in its
entirety with this Revision 02.
Service Bulletin No. 604−29−013
Date of Basic Issue Apr 30/2015
Revision No. 01 Dated Oct 19/2015
Revision No. 02 Dated Apr 18/2016
This Revision has no effect for aircraft on which the Basic Issue or Revision 01 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 incorporate the changes given in Modification Summary 600−6330,
Rev. K, and to update the Service Bulletin per latest Kit Drawing K604−75209. The changes
are as follows:
1. Change, in Paragraph 1.K., the revision of Modification Summary 600−6330 to Rev. K
and the Kit Drawing K604−75209 to Rev. F.
2. Revise, Paragraph 2.B.4.(g), to add a note for the recommended orientation of the
pressure gauge/valve for easier reading/servicing access.
3. Revise, the Kit Drawing K604−75209 to Rev. F.
4. Make miscellaneous minor changes, as necessary, with no change of context.
SERVICE BULLETIN
MODEL CL−600−2B16
604−29−013
P a g e1o f1
REVISION TRANSMITTAL SHEET

### Page 3

MODIFICATION - HYDRAULIC SYSTEM NO. 3 - RELOCATION OF THE HYDRAULIC
SYSTEM NO. 3 ACCUMULATOR
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
See Paragraph 1. D.
EFFECTIVITY: AC Serial No. 5301 to 5665
MANPOWER: 126 man−hours are necessary to do the modification.
CONTINUED AIRWORTHINESS (CAW)
FLEET CAMPAIGN NOYES
TLMC, CH 5 AFFECTED YES NO
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 CL−600−2B16
ATA 29−12
HYDRAULIC POWER
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
P a g e1o f1
This Service Bulletin is available at:

### Page 4

MODIFICATION - HYDRAULIC SYSTEM NO. 3 - RELOCATION OF THE HYDRAULIC
SYSTEM NO. 3 ACCUMULATOR
1. PLANNING INFORMATION
NOTES: 1. 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 604−00−002.
2. To minimize aircraft downtime and cost, it is recommended to do the
Service Bulletin when you remove the AFT lavatory or equipment and
furnishings installed between FS559.00 and FS589.00, during the 96
month inspection.
A. Effectivity
CL−600−2B16 aircraft Serial No. 5301 to 5665.
If the aircraft listed in the table below that has already incorporated the Basic Issue
of this Service Bulletin and has already recorded the listed Service
Non−Incorporated Engineering Order (SNIEO) S01, S02, S03, S04, S05 and S08
of Drawing K604−75209 in their logbook, it meets the intent of the Basic Issue of
this Service Bulletin.
SERVICE BULLETIN
www.cic.bombardier.com
MODEL CL−600−2B16
ATA 29−12
HYDRAULIC POWER
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.
© 2015−2016 Bombardier Inc.  All rights reserved
Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 1 of 53
This Service Bulletin is available at:

### Page 5

AIRCRAFT SERIAL NO. DRAWING K604−75209
SNIEO NUMBER
5650 S01. S02, S03, S04, S05 and S08
B. Reason
The hydraulic system No. 3 Accumulator screw cap and/or end cap may rupture, in
very rare occasions, due to fatigue. The end cap and/or screw cap failure can result
in a high energy rupture (compressed nitrogen) and cause system and/or structural
damage to the components installed in the rupture trajectory.
In the current installation, in case of screw cap and/or end cap failure, it is possible
that the projectiles can cause damage to multiple system components which could
potentially combine to ignite a fire within a non−fire designated zone. Although no
screw cap and/or end cap failure has been reported on the CL600−2B16 (CL−604),
it is recommended to relocate the accumulator to prevent such failure.
This Service Bulletin gives instructions to remove the existing hydraulic system No.
3 accumulator and its pressure gauge/valve from the main landing gear bay and
relocate them to the left hand side, rear wing−to−fuselage fairing area.
C. Description
This Service Bulletin gives instructions to:
− Get access to the hydraulic system No. 3 accumulator and hydraulic system No.
3 hydraulic tubes,
− Remove the hydraulic accumulator No. 3 and its pressure gauge/valve,
− Remove all associated supporting brackets, hydraulic system No. 3 tubes and
nitrogen tubes from the landing gear bay,
− Install new supporting brackets, hydraulic system No. 3 tubes and nitrogen
tubes to the new location on left hand side of the rear wing−to−fuselage fairing
area at FS559.00L,
− Install the hydraulic accumulator No. 3 and pressure gauge/valve to the new
location,
− Do the access panel modification on the left side of the aft rear
wing−to−fuselage fairing (if necessary), and
− Do all the necessary tests to make sure that the hydraulic system No. 3
accumulator operates correctly.
D. Compliance
Recommended within 8 years from this Service Bulletin release date (Basic Issue).
MODEL CL−600−2B16
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604−29−013
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### Page 6

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
604−00−002.
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.
126 man−hours are necessary to do this modification for aircraft that already have
the LH hydraulic access door installed.
An additional 11 man−hours are necessary for aircraft that do not have the LH
hydraulic access door installed.
Bombardier does not pay for the labor to do this modification.
G. Material − Cost and Availability
Kit 605K29−006 and Kit 605K29−006A are necessary to do this modification. For
aircraft that already have the LH hydraulic access door installed by STC, Kit
605K29−006A is not required.
KIT NO. PRICE
605K29−006
Please contact Bombardier Aerospace
Parts Services, in Montreal, for delivery
lead times and confirmation of prices.
605K29−006A
Please contact Bombardier Aerospace
Parts Services, in Montreal, for delivery
lead times and confirmation of prices.
MODEL CL−600−2B16
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 3 of 53

### Page 7

Bombardier Aerospace does not pay for the kits to do this modification.
Smart Parts Plus does not pay for the kits to do this modification.
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 604−00−002.
H. Tooling
The equipment and tools listed below are necessary to do this modification:
GSE REFERENCE NO. PART NO. DESCRIPTION
24−00−24 S4933959−501 Tag, Circuit Breaker
29−10−02 DLTFRPSKT3001 Kit − DeutschPermaswage
Commercially Available − Container, HydraulicFluid
Commercially Available −
Wrench, Torque 100 to
140 lbf in (11.30 to 15.82
Nm)
Commercially Available −
Wrench, Torque 133 to
147 lbf in (15.03 to 16.6
Nm)
Commercially Available −
Wrench, Torque 135 to
190 lbf in (15.26 to 21.46
Nm)
Commercially Available −
Wrench, Torque 150 to
195 lbf in (16.95 to 22.03
Nm)
Commercially Available −
Wrench, Torque 180 to
199 lbf in (20.34 to 22.48
Nm)
MODEL CL−600−2B16
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604−29−013
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### Page 8

GSE REFERENCE NO. PART NO. DESCRIPTION
Commercially Available −
Wrench, Torque 17.91 to
23.33 lbf ft (24.30 to
31.63 Nm)
Commercially Available −
Wrench, Torque 22.16 to
24.50 lbf ft (30.06 to
33.21 Nm)
Commercially Available −
Wrench, Torque 39.58 to
43.75 lbf ft (53.66 to
59.31 Nm)
NOTES: 1. Refer to the CL−604 Illustrated Tool and Equipment Manual to make
sure you use the correct equipment configuration.
2. Refer to the Liability Statement for the CL−604 for acceptable GSE
equivalents.
I. Weight and Balance
AIRCRAFT WEIGHT MOMENT
5301− 5665 +3.4 pounds (1.5 kg) +2753 pound−inches(31.72 kgm)
NOTE: This weight and moment data covers the impact of the mechanical and
structural modification only and does not include the existing hydraulic
accumulator installed on the aircraft. The existing hydraulic accumulator is
not required to be factored in this new data.
J. Electrical Load Data
No change.
K. References
− Bombardier Aerospace, Modification Summary 600−6330, Rev. K.
− Bombardier Aerospace, Restriction and/or Special Instruction (RSI), C−4099,
Rev. A.
− Bombardier Aerospace, Kit Drawing K604−75209, Rev. F.
− CL−604 Aircraft Maintenance Manual (AMM), Chapters 6, 12, 21, 24, 29, 51
and 53.
− CL−604 Aircraft Illustrated Tool and Equipment Manual (ITEM), Chapters 24
and 29.
− Bombardier Aerospace, Standard Practices Manual (SPM), Chapters 20 and 51.
− Bombardier Aerospace, Structural Repair Manual (SRM), Chapter 51.
MODEL CL−600−2B16
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604−29−013
Page 5 of 53

### Page 9

L. Publications Affected
− CL−604 Aircraft Maintenance Manual (AMM), Chapter 29.
− CL−604 Aircraft Illustrated Parts Catalog (AIPC), Chapter 29.
− CL−604 Time Limits/Maintenance Checks (TLMC), Part 2, Section 5−10−30.
M. Equivalent Service Bulletins
− For the Challenger CL−600 aircraft, use SB 600−0767.
− For the Challenger CL−601 aircraft, use SB 601−0637.
− For the Challenger CL−605 aircraft, use SB 605−29−006.
2. ACCOMPLISHMENT INSTRUCTIONS
NOTES: 1. All TASKs given in the procedures that follow are from the CL−604 Aircraft
Maintenance Manual unless otherwise specified.
2. All references made to zones, access panels and/or doors, are from the
CL−604 Aircraft Maintenance Manual, Chapter 6.
3. All finish codes and finish specs are in accordance with the CL604
Structural Repair Manual Chapter 51−01−04.
A. Aircraft Setup
WARNING: OBEY ALL HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO
WORK ON THE HYDRAULIC SYSTEM AND HYDRAULIC SYSTEM
COMPONENTS. IF YOU DO NOT OBEY THE SAFETY
PRECAUTIONS, YOU CAN CAUSE INJURY TO PERSONS AND
DAMAGE TO THE EQUIPMENT.
(1) Obey all hydraulic safety precautions. Refer to AMM 29−00−00−910−801.
(2) Obey all the hydraulic technical precautions. Refer to
AMM 29−00−00−910−802.
(3) Use best shop practices and make a placard to state “Do not apply hydraulic
system No. 3 power” (or similar) and install it on the HYDRAULIC control panel
installed in the overhead panel of the flight compartment.
(4) Release the hydraulic pressure from hydraulic system No. 3. Refer to
AMM 12−00−04−862−804.
WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO
MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC
EQUIPMENT. IF YOU DO NOT OBEY THE SAFETY
PRECAUTIONS, YOU CAN CAUSE INJURY TO PERSONS AND
DAMAGE TO THE EQUIPMENT.
(5) Obey all electrical/electronic safety precautions. Refer to
AMM 24−00−00−910−801.
(6) Remove electrical power from the aircraft. Refer to AMM 24−00−00−861−802.
MODEL CL−600−2B16
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### Page 10

(7) Open and tag the circuit breakers that follow:
CB PANEL CB NO. CB NAME ZONE
CBP−1 A2 HYD PUMP 3B 221
CBP−2 A2 HYD PUMP 3A 222
CBP−2 G4 HYD SYST AC PUMP
CONT 3A
222
CBP−2 P2 HYD SYST PUMP CONT
3B
222
(8) Remove the left and right main−landing−gear wheel bins (163AZ/164AZ).
Refer to AMM 53−65−01−000−801.
(9) Remove the rear wing−to−fuselage fairing, left/right (195AL/196AR). Refer to
AMM 53−63−01−000−802.
(10) Remove the AFT lavatory or equipment and furnishings installed between
FS559.00L and FS589.00L. Refer to the SMM of your aircraft.
(11) Remove the Passenger Compartment Floor Panel, 231KLF at FS559.00L.
Refer to AMM 53−01−01−000−802.
(12) Remove the cargo compartment floor panels 241CLF and 241ELF, between
FS559.00L and FS589.00L to gain access to the below−floor area. Refer to
AMM 53−01−01−000−803.
(13) Remove and tag the wires from the flight−compartment air−conditioning−duct
temperature sensor, Part No. 627962−2. Refer to AMM 21−21−11−000−801
and Figure 1.
(14) Remove the flight−compartment air−conditioning−duct, Part No.
600−95312−1003 between FS561.50L and FS593.00L. Refer to Figure 1.
(15) Remove and keep the two lowest insulation blankets between FS559.00L and
FS574.00L. Fold back the two adjacent blankets between 574.00L and
FS589.00L to create access for the structural modification. Refer to Figure 2.
(16) Remove the insulation blankets as necessary for the new installation of the
Hydraulic System No.3 accumulator and beacon light cable, Part No. 8KA 401
890−63. Refer to Sheet 2 of Kit Drawing K604−75209.
MODEL CL−600−2B16
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### Page 11 (OCR)

CHÄLLÊNGËŘ 604
MODEL CL-600-2B16
FLIGHT COMPARTMENT
DUCT TEMPERATURE SENSOR
PART NO. 627962-2
CUSHIONED
LOOP CLAMP
HOSE CLAMP  FLIGHT COMPARTMENT
AIR CONDITIONING DUCT
PART NO. 600-95312-1003
Flight Compartment Air-Conditioning Duct (FS561.50L to FS593.00L)
Figure 1
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### Page 12 (OCR)

ćHẤLLỀNGÉŘ604
MODEL CL-600-2B16
SB604_29_013_001
Looking outboard and down showing the two lowest blankets (FS559.00L to FS574.00L)
removed and the two adjacent blankets (FS574L to FS589.00L) peeled back.
Basic Issue: Apr 30/2015  Figure 2  604-29-013
I Revision 02: Apr 18/2016  Page 9 of 53

### Page 13

B. Modification
(1) Remove the hydraulic system No. 3 accumulator and pressure gauge/valve as
follows: Refer to Sheet 1 of Kit drawing K604−75209.
NOTE: Plug redundant holes per CL604 Structural Repair Manual, Chapter
51−42−08.
(a) Disconnect and remove the accumulator from the aircraft. Refer to
AMM 29−12−25−000−801.
(b) Make sure you retain the accumulator to reinstall later.
(c) Remove and retain the pressure gauge/valve to reinstall later. Refer to
AMM 29−12−28−000−801.
(d) Remove and discard the clamps, brackets, collars, union reducers,
o−rings, and other hardware as per Sheet 1 of Kit Drawing K604−75209.
(2) Modify the hydraulic system No. 3 tubes as follows: Refer to Sheet 2 of Kit
Drawing K604−75209.
NOTES: 1. Make sure to do a pre−fit before making any permanent
connections.
2. Disconnect any fairlead supports and hydraulic tubes as
necessary to make it possible to install the union fitting, Part No.
B0301010−06 to the existing tube assembly, Part No.
604−75239−47 at the exact location as shown in Figure 4, to
create new tube assembly, Part No. K604−75209−6.
3. Make sure to do all the related return−to−service testing for all
the hydraulic tubes and fairlead supports that were disconnected
or disturbed to do the hydraulic tube modifications.
4. If difficulties are encountered during installation, it is permissible
to cut lines and swage segments together. Refer to CL−604
Standard Practices Manual, Chapter 20−30−00.
5. To avoid fouling with any existing hydraulic tubes make sure you
do a pre−fit of the tubes and fittings to meet the approximate
location given in R−R of Kit Drawing K604−75209.
6. Torque plumbing fittings per CL604 Standard Practices Manual,
Chapter 20−22−00.
7. Install hose clamps per CL604 Standard Practice Manual,
Chapter 20−30−00.
8. For all finish codes and finish specs refer to CL604 Structural
Repair Manual Chapter 51−01−04.
(a) Remove and discard the three rivets Part No. MS20470AD5 from the
structure to allow the installation of the new support bracket Part No.
604−75264−1.
MODEL CL−600−2B16
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### Page 14

(b) Install the support bracket, Part No. 604−75264−1 with three rivets, Part
No. MS20470AD5−7A on the structure as shown in View D.
(c) Remove and discard washer Part No. AN960KD10L and screw Part No.
NAS1096−3−20 as shown in View D.
(d) Rework the tube assembly, Part No. 604−75239−75 and install cap, Part
No. B0301021−06 on open end as close as possible to the existing cross
reducer. Refer to Figure 3.
MODEL CL−600−2B16
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### Page 15 (OCR)

cHÄLLỀNGÉŘ6o4
MODEL CL-600-2B16
•605
SUGGESTED LOCATION TO INSTALL CAP
PART NO. B0301021-06
ORIGINAL HYD SYS NO. 3
HYDRAULIC TUBE TO ACCUMULATOR
(REF. PART NO. 604-75239-75)
SB605_29_013_002
Cap installed on hydraulic tube Part No. 604-75239-75
Figure 3
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### Page 16

Location to cut tube assembly Part No. 604−75239−47 and install permaswage union fitting
Part No. B0301010−06, to create new tube assemly Part No. K604−75209−6.
Figure 4
MODEL CL−600−2B16
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### Page 17

Hydraulic Tube Part No. K604−75209−6 with Union Fitting Part No. B0301010−06.
Figure 5
(e) Fabricate tube assembly Part No. K604−75209−6 as follows: Refer to
View D, and Figures 4 and 5.
(i) Cut tube assemblies, Part No. 604−75214−1 and Part No.
604−75239−47 and connect the two tube assemblies with the union
fitting, Part No. B0301010−06 to create new tube assembly Part No.
K604−75209−6. Refer to SPM20−30−00−910−807 and Figure 4.
NOTES: 1. Disconnect any fairlead supports and hydraulic tubes as
necessary to make it possible to install the union fitting,
Part No. B0301010−06 to the tube assemblies.
2. Do all the pre−fits of the tubes and fittings to meet the
approximate location given in View R−R of the kit
drawing K604−75209 without fouling with any hydraulic
tubes. Make as many swage joints off the aircraft before
making the permanent connection to the existing
installed tube assembly Part No. 604−75239−47 and all
the subsequent tubes.
3. The tube assembly Part No. 604−75215−1 that
connects to bulkhead FS559.00L is the governing factor
for the drilling of the hole on FS559.00L bulkhead.
MODEL CL−600−2B16
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### Page 18

(ii) Remove and discard the tube assemblies Part No. 604−75239−39
and 604−75239−41, tee reducer Part No. D100223−040406 and
associated hardware, as shown in View D.
NOTES: 1. It is not necessary to cut the old tube assembly, Part No.
604−75214−1 and swage the union fitting, Part No.
B0301010−06 at this time.
When the existing tube assembly, Part No.
604−75239−47 is cut at the exact location shown in
Figure 4, the old tee reducer, Part No.
D100223−040406 and the old tube assemblies: Part
Nos. 604−75239−39 (with the adaptor) and
604−75239−41 can be disconnected and be removed as
one piece without making many cuts.
2. Put all fittings in place temporarily and put the removed
one−piece assembly on the work bench. Then use the
old tube assembly, Part No. 604−75214−1 as a template
in order to locate where the new tube assembly, Part
No. 604−75214−1 should be cut to join with the cross
reducer, Part No. B0301015−06060404. Refer to Figure
6.
(iii) Identify the fabricated tube assembly as Part No. K604−75209−6 per
best shop practices.
MODEL CL−600−2B16
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### Page 19

Old tube assembly Part No.604−75214−1 used as template shown on bench.
Figure 6
MODEL CL−600−2B16
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### Page 20

Marked Critical Spot on FS559.00L Bulkhead in MLG bay area.
Figure 7
(f) Without making any permanent connections, use the cross reducer Part
No. B0301015−06060404 to join the new tube assemblies, Part No’s.
604−75239−39 (and D10021A−04 90 DEG adaptor), 604−75239−41 and
604−75215−1 to newly reidentified tube assembly Part No.
K604−75209−6 then position 604−75215−1 at FS559.00L to mark hole
location. Refer to View D and Figure 7.
NOTE: To get exact hole location at FS559.00L, use the new cross
reducer, Part No. B0301015−06060404 as a junction reference
and temporarily hand tighten the new 90° adaptor with its tube
assembly, Part No. 604−75239−39 inserted into the new cross
reducer. And also include the new tube assemblies, Part Nos.
604−75214−1 and 604−75239−41.
After the tube assembly, Part No. 604−75215−1 is inserted into
the new cross reducer, attach it to the newly installed support
bracket, Part No. 604−75264−1 with associated support clamp
and hardware. Do the same at related fairlead with new support
clamp and hardware.
(g) Swage the bulkhead adaptor Part No. B0302124−06 onto the tube
assembly Part No. 604−75215−1 on the bench and then to the cross
reducer, Part No. B0301015−06060404 on the aircraft. Refer to Figure 8.
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(h) Drill a 0.568 to 0.588 in. dia. (14.43mm to 14.93mm dia.) hole in the
bulkhead FS559.00, making sure the tube assembly, Part No.
604−75215−1 does not foul with any existing hydraulic tubes. Refer to
View R−R (Sheet 2) and Figure 7.
(i) Install the bulkhead adaptor doubler Part No. K604−75209−21 with the
associated rivets, on both sides of the bulkhead FS 559.00 at the drilled
hole location. Refer to Kit Drawing K604−75209, View R−R and Detail −21
of Sheet 2.
(j) Install the bulkhead adaptor, Part No. B0302124−06 with nut and washer
on far side of the bulkhead FS 559.00. Refer to View D and CL604
Structural Repair Manual, Chapter 51−41−04.
(k) Secure the tube assembly, Part No. 604−75215−1 with cushioned clamps,
Part No. B0305030−6E and associated hardware. Refer to View D of
Sheet 2.
Final swage of the new tube assembly to the cross reducer.
Figure 8
(3) Reroute cable Part No. 8KA 401 890−63 with the associated hardware. Refer
to Kit Drawing K604−75209, View R−R and View S−S of Sheet 2.
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(4) Install the hydraulic system No. 3 accumulator and pressure gauge/valve on
the left hand side of the fuselage under the belly fairing, aft of the wing as
follows: Refer to Sheets 1 and 2 and Notes 44 to 48 in PL of Kit Drawing
K604−75209.
NOTE: Make sure to do a pre−fit of all parts before permanent installation to
make sure there is no tension on the tube assemblies.
(a) Remove and discard the 13 rivets Part No. MS20426−5−() from the
structure to allow the installation of the new machined brackets. Refer to
View L of Sheet 2.
(b) Align and set up brackets Part Nos. 600−75275−1 (Outboard) and
600−75276−1 (Inboard) and stiffening plate, Part No. 604−75201−1 with
the aircraft structure as shown in View P−P of Sheet 1, and View L of
Sheet 2, and do as follows:
NOTE: Install the protruding head of the hi−lites from inside of the
aircraft fuselage to facilitate installation.
(i) Pick up rivet hole from the aircraft skin onto pilot hole of machined
bracket, Part No. 600−75275−1 (Outboard) as shown in View L.
Continue to position the edge of the bracket parallel to FS574.00 as
shown and pick up remaining holes from the aircraft skin to the
bracket.
(ii) Align machined bracket, Part No. 600−75275−1 (Outboard) with
stiffening plate, Part No. 604−75201−1 and accumulator outboard
clip, Part No. 600−75250−1 using existing pilot holes.
(iii) Align accumulator inboard clip, Part No. 600−75256−1 with stiffening
plate, Part No. 604−75201−1 using existing pilot holes.
(iv) Align machined bracket Part No. 600−75276−1 (Inboard) with aircraft
skin and with stiffening plate, Part No. 604−75201−1 as shown in
View L, and transfer hole locations from skin and from stiffening plate.
Make sure there is a minimum 2D edge distance for all fasteners on
both faces of this machined bracket.
(c) Install the five nut standoffs permanent but install the loop clamps with the
associated hardware finger tight on the stiffening plate Part No.
604−75201−1, per views H, K and P−P of Sheet 1.
(d) Put the hydraulic system No. 3 accumulator in position on the inboard and
outboard clips with the hose clamps as shown in View C and all related
views.
(e) To ensure correct connection without any tension on the tube assemblies
loosely attach the two tube assemblies and flareless tube reducers to the
accumulator and then remove only the accumulator.
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Cut Skin Damping Material and Drilled Holes from Exterior of Fuselage
Figure 9
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Installed Machined Brackets and Stiffening Plate with Accumulator Clips.
Figure 10
(f) Install the removed hydraulic accumulator. Refer to
AMM 29−12−25−400−801.
(g) Install the pressure gauge/valve on the outboard accumulator clip, Part
No. 600−75250−1. Refer to Kit Drawing K604−75209, Section N−N of
Sheet 1 and AMM 29−12−28−400−801.
NOTE: It is optional, for easier reading and access to the pressure
gauge/valve for servicing, to install the nitrogen charging valve
and dust cap to point forward and outboard.
(h) For aircraft equipped with hydraulic accumulator Part No. 601R75139−3,
install the teflon shims, Part No. 604−75209−5 on the inboard and
outboard accumulator clips to ensure tightly secured positioning of the
accumulator.
(i) Connect and tighten the two tube assemblies and flareless tube reducers
to the accumulator and bulkhead adaptor, Part No. B0302124−06 at
FS559.00L. Refer to Torquing of Plumbing Line Fittings
SPM−MM 20−22−00−910−801.
(j) Torque all associated hardware that attach the five nut standoffs and loop
clamps. Refer to Torquing of Threaded Fasteners
SPM−MM 20−21−00−910−801.
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(k) Install the standoff doubler, Part No. K604−75209−20 with the associated
rivets on the bulkhead per View R−R and Detail AA (sheet 2) of Kit
Drawing K604−75209.
(l) Install the nut standoff Part No. B0204034AL−12W at correct location to
suit installation of the tube assembly Part No. 604−75207−9 with the
associated rivets as shown in View L and View R−R of Sheet 2 and all
related notes in Kit Drawing and Service Bulletin.
NOTE: To suit installation of the tube assembly Part No. 604−75207−5 in
lieu of the tube assembly Part No. 604−75207−9, Refer to
instructions in Note 72 of Parts List K604−75209.
(5) Install the bonding jumpers Part No. M83413/8−A004BB and Part No.
M83413/8−A007BB in the steps that follow. Refer to
SPM−MM 51−80−00−400−801 for the installation of electrical bonding jumpers
and View H and View P−P (Sheet 2) of Kit Drawing K604−75209.
(a) Prepare the bonding surfaces. Refer to SPM−MM 51−80−00−140−806.
(b) Install one end of the bonding jumper Part No. M83413/8−A004BB on the
tube assembly Part No. 604−75206−5 with clamp Part No. AN735C4 and
associated hardware, per View AC of Sheet 3.
(c) Install other end of the bonding jumper Part No. M83413/8−A004BB on
the tube assembly Part No. 604−75207−9 or −5 with clamp Part No.
AN735C6 and associated hardware, per View AD of Sheet 3.
(d) Install one end of the bonding jumper Part No. M83413/8−A007BB on the
tube assembly Part No. 604−75206−5 with clamp Part No. AN735C4 and
associated hardware, per View AC of Sheet 3.
(e) Install other end of the bonding jumper Part No. M83413/8−A007BB on
the structure with the associated hardware, per View AE of Sheet 1.
(f) Do the electrical bonding test of the accumulator. For the electrical
bonding resistance values, refer to SPM−MM 51−80−00−760−802.
NOTE: Measure the resistance between the hydraulic fitting and a
conductive point on the aircraft primary structure.
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CAUTION: TO MAINTAIN PROPER VENTILATION AIRFLOW IN THE AFT
WING FAIRING, WHEN REINSTALLING ANY INSULATION
BLANKETS, MAKE SURE THERE IS A MINIMUM CLEARANCE OF
1.00 IN (2.54 CM) AROUND THE VENTILATION HOLES ON
BULKHEAD AT FS559.00, AND MAKE SURE THERE IS A MINIMUM
CLEARANCE OF 3.00 IN (7.62 CM) AROUND THE
CUTOUTS/VENTILATION HOLES ON SUPPORT RIB P/N
600-35049-25/-26 LOCATED AT FS621.00 ON BOTH LEFT AND
RIGHT HAND SIDES.
(6) Modify the insulation blankets. Refer to View V and View W−W, Sheet 3 of Kit
Drawing K604−75209 as a modification reference only.
NOTES: 1. The insulation blankets on your CL−604 (AC Serial No. 5301 to
5665) are installed by Supplemental Type Certificate (STC).
Make sure you refer to the applicable maintenance manuals for
instructions and limitations. Before modifying any blanket,
operators are responsible for ensuring that their STC is modified
appropriately in order to reflect this change, since any
modifications done are modifications to STC installed parts.
2. You must only use the data from Auxiliary View V and View W−W
for reference only as a guide to modify the insulation blankets. It
is not permissible to use the insulation blanket Part Numbers
given in these two views for your CL−604 aircraft. These views
are used in their entirety and only applicable to CL−605 aircraft.
3. It is permissible to create internal cutouts and notches where
necessary on the blankets and skin damping pads to provide
clearance for the installation of brackets, tube assemblies and
bulkhead connector.
4. Make sure there is a maximum clearance of 0.25 in (6.35 mm)
around tube assemblies and the bulkhead structure.
5. Seal the cut edges of modified insulation blankets. Refer to the
applicable maintenance manuals for instructions and limitations.
6. Use double sided tape as necessary to re−install insulation
blankets. Refer to the applicable maintenance manuals for
instructions and limitations.
7. For insulation blanket replacement, you must meet the
Thermal/Acoustic insulation materials requirement, FAR 25.856
(a).
(a) Modify the insulation blankets as necessary and reinstall the insulation
blankets related to the newly installed Hydraulic System No. 3
accumulator and beacon light cable, Part No. 8KA 401 890−63.
(b) Re−identify the modified blankets with SB number. Refer to NOTE 54 in
PL of Kit Drawing K604−75209 and Figure 11.
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Modified Blankets and Ventilation Holes (shown at support rib of FS621.00L)
Figure 11
(7) Do the access panel assembly modification as follows: Refer to Sheet 1 and 2
of Kit Drawing K604−75209.
(a) For aircraft that already have the LH hydraulic access door installed by
STC, omit the steps that follow to do the access panel assembly
modification and only install the placard on the access door, as shown in
View M of Kit Drawing K604−75209.
(i) For aircraft Post SB604−29−012 install placard S8490−1. For aircraft
Pre SB604−29−012 install placard S5151−2.
(b) For aircraft that do not have the LH hydraulic access door already
installed, do the access panel assembly modification as follows: Refer to
−3 Kit Installation on Sheet 1 and 2 of Kit Drawing K604−75209.
(i) Remove and discard the existing door panel Part No. 604−35313−1
or 604−35313−5 from the left hand side of the aft fairing.
(ii) Install the new LH access panel assembly Part No. 604−36910−1 on
the aft fairing.
NOTE: The Access door Part No. 604−36912 is installed on the
access panel assembly 604−36910−1.
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(iii) Remove and discard key lock anchor plate Part No. 604−33501−1
and key lock spacer Part No. 604−33505−1.
NOTE: If a lock is required, retain the key lock anchor plate Part No.
604−33501−1 and key lock spacer Part No. 604−33505−1,
and install a lock by an STC only.
(iv) If no lock is required install shim, Part No. K604−75209−71 and plate,
Part no. K604−75209−72 as shown in View T−T of Sheet 2.
NOTE: Make sure there is aerodynamic smoothness of the external
surfaces of the aircraft. Refer to CL604 Structural Repair
Manual, Chapter 51−14−00.
(v) Paint access door panel to match aircraft color. Refer to CL604
Aircraft Maintenance Manual, Chapter 11−00−00.
(vi) Install the placard on the access door as shown in View M of Sheet 1.
NOTE: For aircraft Post SB604−29−012 install placard S8490−1.
For aircraft Pre SB604−29−012 install placard S5151−2.
C. Testing
(1) Do the electrical bonding test of the new and modified hydraulic tubes. Refer to
CL604 Standard Practice Manual, Chapter 51−80−00.
(2) Remove tags and close the circuit breakers that follow:
CB PANEL CB NO. CB NAME ZONE
CBP−1 A2 HYD PUMP 3B 221
CBP−2 A2 HYD PUMP 3A 222
CBP−2 G4 HYD SYST AC PUMP
CONT 3A
222
CBP−2 P2 HYD SYST PUMP CONT
3B
222
(3) Remove the safety placard from the HYDRAULIC control panel.
(4) Connect electrical power to the aircraft. Refer to AMM 24−00−00−861−801.
(5) Do a quantity check of the hydraulic fluid of hydraulic system No. 3. Refer to
AMM 12−12−29−210−802.
(6) Do a servicing of the hydraulic system No. 3 reservoir. Refer to
AMM 12−12−29−611−801.
(7) Do a quantity check of the nitrogen pressure in the hydraulic system
accumulator of hydraulic system No. 3. Refer to AMM 12−12−29−210−803.
(8) Do the servicing of the accumulator. Refer to AMM 12−12−29−614−801.
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(9) Bleed the hydraulic system No. 3. Refer to AMM 29−10−00−870−802.
NOTE: The aircraft must be on jacks to do the extension/retraction of the
landing gear.
(10) Do a visual check of the area around the accumulator and the hydraulic fitting
for hydraulic fluid leakage. There must be no leakage.
(11) Use the leak detector compound and do a leak test of the nitrogen tube fitting.
Make sure that there are no bubbles or spray.
(12) Do the necessary return to service checks for all hydraulic tubes that were
disconnected or disturbed for this hydraulic tube modification.
(13) Do an operational test of the hydraulic system No. 3. Refer to
AMM 29−10−00−710−803.
(14) Do a quantity check of the nitrogen pressure in the hydraulic system
accumulator of hydraulic system No. 3. Refer to AMM 12−12−29−210−803.
D. Close−Out
(1) Fold back in position the two adjacent blankets between 574.00L and
FS589.00L and install the two lowest insulation blankets between FS559.00L
and FS574.00L that were removed from inside the aircraft for access to do the
structural modification. Refer to Sheet 3 of Kit Drawing K604−75209.
(2) Install the flight−compartment air−conditioning−duct, Part No.
600−95312−1003 between FS561.50L and FS593.00L. Refer to Figure 1.
(3) Remove the tags and connect the wires to the flight−compartment
air−conditioning−duct temperature sensor, Part No. 627962−2. Refer to
AMM 21−21−11−400−801.
(4) Do the operational test of the temperature control and indicating system. Refer
to AMM 21−61−00−710−801.
NOTE: Do this test before reinstalling the AFT lavatory or equipment and
furnishings.
(5) Install the Passenger Compartment Floor Panel, 231KLF at FS559.00L. Refer
to AMM 53−01−01−400−802.
(6) Install the cargo compartment floor panels 241CLF and 241ELF, between
FS559.00L and FS589.00L. Refer to AMM 53−01−01−400−803.
(7) Install the AFT lavatory or equipment and furnishings. Refer to the SMM of
your aircraft.
(8) Do the operational test(s) applicable to the AFT lavatory. Refer to the SMM of
your aircraft.
(9) Install the rear wing−to−fuselage fairing, left/right (195AL/196AR). Refer to
AMM 53−63−01−400−802.
(10) Install the left and right main−landing−gear wheel bins (163AZ/164AZ). Refer
to AMM 53−65−01−400−801.
(11) Do the operational test of the MLG Overheat Detection System. Refer to
AMM 26−13−00−710−801.
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(12) Remove all tools, equipment and unwanted materials from the work area.
E. 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. Kit
(1) For aircraft, Serial No.5301 to 5665, Kit 605K29−006 is necessary to do this
Service Bulletin and contains the parts that follow:
NEW PART NO. QTY ITEM USED PARTNO. INSTRUCTIONS- DISPOSITION
600−75250−1 1 AccumulatorClip, Outboard − −
600−75256−1 1 AccumulatorClip, Intboard − −
600−75275−1 1 Bracket,Machined − −
600−75276−1 1 Bracket,Machined − −
604−75201−1 1 Stiffening Plate − −
604−75206−5 1 Tube AssemblyAccumulator − −
604−75207−5
OR
604−75207−9
1 Tube AssemblyAccumulator − −
604−75214−1 1 Tube Assembly − −
604−75215−1 1 Tube Assembly − −
604−75239−39 1 Tube Assembly − −
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NEW PART NO. QTY ITEM USED PARTNO. INSTRUCTIONS- DISPOSITION
604−75239−41 1 Tube Assembly − −
604−75264−1S 1 Support Bracket − −
AN735C4 2 Clamp − −
AN735C6 1 Clamp − −
AS5178J06 2 Nut − −
B0202020−3−060 1 Spacer Sleeve − −
B0203013−3 11 Nut, Self Locking − −
B0203014−08 18 Nut, Self Locking − −
B0203015−08 15 Nut − −
B0204034AL−4W 2 Nut, Standoff, 2Lug − −
B0204034AL−12W 2 Nut, Standoff, 2Lug − −
B0204034AL−13W 1 Nut, Standoff, 2Lug − −
B0204037AL−4W 4 Nut, Standoff, 2Lug − −
B0204037AL−10W 2 Nut, Standoff, 2Lug − −
B0204046CRA3−24T 1 Spacer, ClickBond − −
B0206001AG6−2 10 Pin − −
B0206003AG5−4 22 Pin − −
B0206003AG5−5 11 Bolt, Protruding − −
B0206003AG5−6 3 Pin − −
B0301010−04 2 Union Fitting − −
B0301010−06 3 Union Fitting − −
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NEW PART NO. QTY ITEM USED PARTNO. INSTRUCTIONS- DISPOSITION
B0301015−06060404 1 Cross Fitting,Reducer − −
B0301021−06 1 Cap − −
B0302124−06 1 Adaptor, BKHD − −
B0305030−6E 2 Clamp, P Type,Cushioined − −
B0305090C9U03 1 Clamp − −
B0816019−003 1 Strap, Tie Down − −
CB3001CRA3−16 1 Spacer, ClickBond − −
D10021A−04 1 Adaptor, 90DEG − −
K604−75209−20 1 Standoff Doubler − −
K604−75209−21 2
Doubler,
Bulkhead
Adaptor
− −
M83413/8−A004BB 1 Jumper − −
M83413/8−A007BB 1 Jumper − −
M85052/2−4 2 Clamp, Loop − −
M85052/2−6 4 Clamp, Loop − −
MS20470AD4−5A 14 Rivet, Solid,Universal HD − −
MS20470AD4−6A 3 Rivet, Solid,Universal HD − −
MS20470AD5−4A 2 Rivet − −
MS20470AD5−5A 8 Rivet, SolidUniversal HD − −
MS20470AD5−7A 4 Rivet, Solid,Universal HD − −
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NEW PART NO. QTY ITEM USED PARTNO. INSTRUCTIONS- DISPOSITION
MS20470AD6−11A 5 Rivet, Solid,Universal HD − −
MS20470AD6−13A 2 Rivet, Solid,Universal HD − −
MS21042L3 5 Nut, Hex, SelfLock 450F − −
MS21902J4 1 Union, Flarelesstube − −
MS35207−264 1 Screw − −
MS35338−43 1 Lock Washer − −
MS35338−138 3 Lock Washer − −
MS35650−302 1 Nut − −
MS35650−304 3 Nut − −
NAS1097AD5−5A 5
Rivet, Solid, 100
Deg. Flush
shear Head
− −
NAS1149C0332R 12 Washer − −
NAS1149C0363R 3 Washer − −
NAS1149C1063R 2 Washer − −
NAS1149D0332J 16 Washer − −
NAS1149D0332K 2 Washer − −
NAS1149F0332P 2 Washer − −
NAS1612−4A 1 O−Ring − −
NAS1801−3−5 7 Screw − −
NAS1801−3−8 2 Screw − −
NAS1801−3−9 1 Screw − −
NAS1801−3−18 2 Screw − −
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NEW PART NO. QTY ITEM USED PARTNO. INSTRUCTIONS- DISPOSITION
NAS1801−3−20 2 Screw − −
NAS1801−3−32 2 Screw − −
NAS1802−3−10 3 Screw − −
NAS1922−0350−3 2 Clamp − −
NAS43DD3−15FC 1 Spacer Sleeve − −
NAS43DD3−32FC 1 Spacer Sleeve − −
NAS6203−3 6 Bolt, Hex Head,Close Tol − −
NAS9301E−4−04 2 Rivet − −
S5151−2 1
Placard
“ACCUM.
CHARGING”
− −
S8490−1 1 Placard “HYDR.SYS. ACCUM” − −
(2) For aircraft, Serial No.5301 to 5665 that do not have an access door installed
per STC, Kit 605K29−006A is necessary to do this Service Bulletin and
contains the parts that follow:
NEW PART NO. QTY ITEM USED PARTNO. INSTRUCTIONS-DISPOSITION
604−36910−1 1 Panel Assy,Access (LH) − −
B0205013M4−4 7 Rivet − −
B0209045−100S 17 Grommet − −
B0209051−5−5S 17
Stud,
Grommetted,
¼T u r n
− −
K604−75209−71 1 Shim − −
K604−75209−72 1 Plate − −
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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.
DESCRIPTION PARTNO./NAME SPECIFICATION QUANTITY SUPPLIER(SEE NOTE)
Hydraulic Fluid,
Phosphate Ester
Base
− BAMS 564−003,SAE AS 1241 As Necessary Code: A
Compound, Leak
Detection − MIL−L−255567 As Necessary Code: B
Cellulose Nitrate
Lacquer, Gloss,
White
− TT−L−32 As Necessary Code: C
Adhesive,
Clickbond LORD201/19 − As Necessary Code: D
Film,
LAMAGUARD 12 N389−9202 CommerciallyAvailable As Necessary Code: E
Lockwire − MS20995C32 As Necessary Code: E
Nitrogen −
BB−N−111,
(TYPE I) Grade
A
As Necessary Code: E
Tape, Nomex
Lacing − MIL−T−43435 As Necessary Code: E
Tape,
Pressure−Sensitivity
4 in. width
N384−7606
LT−16
MMS 01−001
Type VI
Lamart Corp.
As Necessary Code: E
Tape,
Double−sided
P−55 Permacel
1 in. width
N384−3300 CommerciallyAvailable As Necessary Code: E
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DESCRIPTION PARTNO./NAME SPECIFICATION QUANTITY SUPPLIER(SEE NOTE)
Tape,
Double−sided
P−55 Permacel
4 in. width
N384−3410 CommerciallyAvailable As Necessary Code: E
Vinyl, Protective
Tape (membrane)
P−306L
Permacel
Commercially
Available As Necessary Code: E
NOTES: 1. Refer to the table that follows for each supplier’s 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
ExxonMobil Aviation Lubricants
Technical Support Center
3225 Gallows Road
Fairfax, VA 22037
Tel: 1 800 662−4525
Fax: +1 703 846−6693
www.exxonmobilaviation.com
Code: B
American Gas & Chemical Co.
(Biomarine)
456 Creamery Way
Exton, PA 19341
USA
Tel.: 800−378−2287
www.biomarineinc.com
Code: C
Randolph Products Co.
33 Haynes Circle
Chicopee, MA 01020
Tel: 413−592−4191
Fax: 413−594−7321
www.Randolphproducts.com
Code: D
Lord Corporation
Tel.: 877−275−5673
www.Lord.com
Code: E
Commercially Available
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D. Publications
No publications required.
MODEL CL−600−2B16
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K604_75029_F_PL−S1−PL
MODEL CL−600−2B16
PL K604−75209 − Kit − Relocation of the Hydraulic system #3 Accumulator
(Sheet 1 of 10, Rev. F)
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K604_75029_F_PL−S2−PL
MODEL CL−600−2B16
PL K604−75209 − Kit − Relocation of the Hydraulic system #3 Accumulator
(Sheet 2 of 10, Rev. F)
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 36 of 53

### Page 40

K604_75029_F_PL−S3−PL
MODEL CL−600−2B16
PL K604−75209 − Kit − Relocation of the Hydraulic system #3 Accumulator
(Sheet 3 of 10, Rev. F)
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 37 of 53

### Page 41

K604_75029_F_PL−S4−PL
MODEL CL−600−2B16
PL K604−75209 − Kit − Relocation of the Hydraulic system #3 Accumulator
(Sheet 4 of 10, Rev. F)
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 38 of 53

### Page 42

K604_75029_F_PL−S5−PL
MODEL CL−600−2B16
PL K604−75209 − Kit − Relocation of the Hydraulic system #3 Accumulator
(Sheet 5 of 10, Rev. F)
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 39 of 53

### Page 43

K604_75029_F_PL−S6−PL
MODEL CL−600−2B16
PL K604−75209 − Kit − Relocation of the Hydraulic system #3 Accumulator
(Sheet 6 of 10, Rev. F)
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 40 of 53

### Page 44

K604_75029_F_PL−S7−PL
MODEL CL−600−2B16
PL K604−75209 − Kit − Relocation of the Hydraulic system #3 Accumulator
(Sheet 7 of 10, Rev. F)
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 41 of 53

### Page 45

K604_75029_F_PL−S8−PL
MODEL CL−600−2B16
PL K604−75209 − Kit − Relocation of the Hydraulic system #3 Accumulator
(Sheet 8 of 10, Rev. F)
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 42 of 53

### Page 46

K604_75029_F_PL−S9−PL
MODEL CL−600−2B16
PL K604−75209 − Kit − Relocation of the Hydraulic system #3 Accumulator
(Sheet 9 of 10, Rev. F)
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 43 of 53

### Page 47

K604_75029_F_PL−S10−PL
MODEL CL−600−2B16
PL K604−75209 − Kit − Relocation of the Hydraulic system #3 Accumulator
(Sheet 10 of 10, Rev. F)
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 44 of 53

### Page 48

K604_75029_F_S1−1
K604−75209 − Kit − Relocation of the Hydraulic System No. 3 Accumulator
(Sheet 1 of 3, Rev. F)
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 45 of 53

### Page 49

K604_75029_F_S1−2
K604−75209 − Kit − Relocation of the Hydraulic System No. 3 Accumulator
(Sheet 1 of 3, Rev. F, continued)
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 46 of 53

### Page 50

K604_75029_F_S1−3
K604−75209 − Kit − Relocation of the Hydraulic System No. 3 Accumulator
(Sheet 1 of 3, Rev. F, continued)
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 47 of 53

### Page 51

K604_75029_F_S1−4
K604−75209 − Kit − Relocation of the Hydraulic System No. 3 Accumulator
(Sheet 1 of 3, Rev. F, continued)
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 48 of 53

### Page 52

K604_75029_F_S2−1
K604−75209 − Kit − Relocation of the Hydraulic system No. 3 Accumulator
(Sheet 2 of 3, Rev. F)
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 49 of 53

### Page 53

K604_75029_F_S2−2
K604−75209 − Kit − Relocation of the Hydraulic system No. 3 Accumulator
(Sheet 2 of 3, Rev. F, continued)
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 50 of 53

### Page 54

K604_75029_F_S2−3
K604−75209 − Kit − Relocation of the Hydraulic system No. 3 Accumulator
(Sheet 2 of 3, Rev. F, continued)
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 51 of 53

### Page 55

K604_75029_F_S3−1
K604−75209 − Kit − Relocation of the Hydraulic system No. 3 Accumulator
(Sheet 3 of 3, Rev. F)
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 52 of 53

### Page 56

K604_75029_F_S3−2
K604−75209 − Kit − Relocation of the Hydraulic system No. 3 Accumulator
(Sheet 3 of 3, Rev. F, continued)
Basic Issue: Apr 30/2015
Revision 02: Apr 18/2016
604−29−013
Page 53 of 53

### Page 57

604−29−013 Rev. 02 Apr 18/2016
MODIFICATION − HYDRAULIC SYSTEM NO. 3 − RELOCATION OF THE
HYDRAULIC SYSTEM NO. 3 ACCUMULATOR
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 58

SERVICE BULLETIN INCORPORATION SHEET − "604−29−013"
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.
604−29−013 02
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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