# Bombardier Service Bulletin 700-29-6502

## Copies (3)

Copies the FAA filed in AD dockets on regulations.gov, newest revision first. A newer revision may exist.

- No revision named, part 1 of 3 ("700-29-6502_Part1"), 16 pages: PDF https://openairdocs.org/files/sha256/29/a3/29a3da83cb3517be8bc89c98ea6694c12d0732d835b4637558869fb5d07ac564; text https://openairdocs.org/service-documents/bombardier/sb-700-29-6502/file/29a3da83cb35.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2024-2720; AD 2025-07-11 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- No revision named, part 2 of 3 ("700-29-6502_Part2reduced"), 1 page: PDF https://openairdocs.org/files/sha256/ca/52/ca52e406cd06bc5d14b979cef8d3937a88a6c374629dd33f446ad7525592aea3; text https://openairdocs.org/service-documents/bombardier/sb-700-29-6502/file/ca52e406cd06.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2024-2720; AD 2025-07-11 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- No revision named, part 3 of 3 ("700-29-6502_Part3"), 2 pages: PDF https://openairdocs.org/files/sha256/dd/db/dddb6ad342dabcac65c03e20a9fda12bf6dea88bb7014012bad12f6b8419572b; text https://openairdocs.org/service-documents/bombardier/sb-700-29-6502/file/dddb6ad342da.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2024-2720; AD 2025-07-11 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Bombardier](https://openairdocs.org/service-documents/bombardier.md)
- Type: Service bulletin (Service Bulletin)
- Number: 700-29-6502
- Page: https://openairdocs.org/service-documents/bombardier/sb-700-29-6502

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

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

- [AD 2025-07-11](https://openairdocs.org/ad/2025-07-11.md), effective Jul 2, 2025: No revision named

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-700-29-6502/proposed.md).

## Text (16 pages)

No revision named, part 1 of 3, the newest copy. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2024-2720; AD 2025-07-11 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

SPECIAL CHECK/REWORK – NO. 1 AND NO. 2 HYDRAULIC SYSTEMS –
INSPECTION OF ENGINE DRIVEN PUMP HYDRAULIC HOSES CLEARANCE
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 500 flight hours or 18 months from
the Service Bulletin release date (Basic
Issue)
EFFECTIVITY: A/C Serial No. 60001 to 60075, 60083 and 60089
MANPOWER: Refer to Paragraph 1.F.
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, please call Bombardier Aviation Parts Services at:
514−855−2999 or 1−866−538−1247
SERVICE BULLETIN SUMMARY
my.businessaircraft.bombardier.com
MODEL BD−700−1A10 (BD−700)
ATA 29−12
HYDRAULIC POWER
Basic Issue: Nov 29/2023 700−29−6502
Page 1 of 1
This Service Bulletin is available at:

### Page 2

SPECIAL CHECK/REWORK – NO. 1 AND NO. 2 HYDRAULIC SYSTEMS –
INSPECTION OF ENGINE DRIVEN PUMP HYDRAULIC HOSES CLEARANCE
1. PLANNING INFORMATION
NOTES:1 . Before you do this Service Bulletin, examine all STC, STA or
equivalent action changes to make sure that this Service Bulletin can
be completed.
2. For any technical issues, contact CSE, Technical Support, Global Express
by e−mail at SRPSA@aero.bombardier.com.
A. Effectivity
BD−700−1A10 aircraft, Serial No. 60001 to 60075, 60083 and 60089.
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 Aviation Service Bulletin(s).
B. Reason
1. Condition:
The fouling of the hydraulic systems No. 1 and No. 2 engine driven pump hoses
against the pylon can lead to hydraulic systems leaks and failures, which can
result in a loss of the hydraulic systems.
2. Evidence:
There have been reports of some aircraft experiencing significant chafing of the
hydraulic hose which can result in a loss of hydraulic systems.
SERVICE BULLETIN
my.businessaircraft.bombardier.com
MODEL BD−700−1A10 (BD−700)
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.
 2023 Bombardier Inc.  All rights reserved
Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.
Basic Issue: Nov 29/2023 700−29−6502
Page 1 of 16
This Service Bulletin is available at:

### Page 3

3. Objective/Benefit:
This Service Bulletin instructs to inspect the No. 1 (LH) and No. 2 (RH) hydraulic
systems engine driven pump hoses for adequate clearance, any damage and if
necessary rework the installation of the hoses to meet the clearance
requirements.
C. Description
This Service Bulletin gives instructions in Paragraph 2.B. (Inspection) to:
− Get access to No. 1 and No. 2 hydraulic system driven pump hoses,
− Inspect the No. 1 and No. 2 hydraulic system driven pump hoses for any
damage and minimum clearance,
− If any damage is found on the hydraulic pressure hoses, do the replacement as
given in Paragraph 2.D. of this Service Bulletin,
− If no damage, and if clearance is less than 0.500 in (12.70 mm), do the
adjustment as given in Paragraph 2.C. of this Service Bulletin, and
− If no damage, and If clearance is greater than or equal to 0.500 in (12.70 mm),
go to Paragraph 2.E. Step (1), then proceed to Paragraph 2.F. (Close−out).
This Service Bulletin gives instructions in Paragraph 2.C. (Adjustment) to:
− Adjust the No. 1 and No. 2 hydraulic system driven pump hoses for minimum
clearance, and
− Proceed to Paragraph 2.E. (Testing).
This Service Bulletin gives instructions in Paragraph 2.D. (Replacement) to:
− Remove and replace the applicable damaged hoses, and
− Maintain the minimum clearance between the hoses and pylon.
After Paragraph 2.C. and/or Paragraph 2.D. as applicable:
− Do the necessary tests to make sure that the system operates correctly, and
− Proceed to Paragraph 2.F. (Close−out).
D. Compliance
Specific Time Compliance
Recommended within 500 flight hours or 18 months, whichever comes first from
this Service Bulletin release date (Basic Issue).
NOTE: If it is not possible to complete all the instructions in this Service Bulletin
because of the aircraft configuration, submit an SRPSA for analysis and to
get an approved disposition to complete this Service Bulletin. Standard
SRPSA fees may apply. Refer to the Services section of the Bombardier
Customer portal for the latest prices, rates and fees.
MODEL BD−700−1A10 (BD−700)
Basic Issue: Nov 29/2023 700−29−6502
Page 2 of 16

### Page 4

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
under the Canada/EU bilateral Aviation Safety Agreement.
F. Manpower
NOTES: 1. The man−hours given are to help you schedule the tasks given in this
Service 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, refer to
SB 700−00−6502.
2. Labor hours are based on the fact that the inspection will be done at
the next scheduled maintenance task or inspection. Therefore no
man−hours are allotted to prepare the aircraft for maintenance or to
prepare for this Service Bulletin.
1.5 man−hours are necessary to do the inspection for this Service Bulletin.
2 man−hours are necessary to do the adjustment or replacement for this Service
Bulletin.
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 500 flight hours or 18 months from
its release date (Basic Issue).
G. Material − Cost and Availability
No kit is necessary to do this special inspection. For material data, refer to
Paragraph 3.C.
The parts in Paragraph 3.B. may be necessary to do this special inspection.
The parts are available at no cost if:
− a no−charge purchase order is sent to Bombardier Aviation in less than
500 flight hours or 18 months from this Service Bulletin release date (Basic
Issue).
MODEL BD−700−1A10 (BD−700)
Basic Issue: Nov 29/2023 700−29−6502
Page 3 of 16

### Page 5

For all parts transactions, Bombardier Aviation’s current Spare Parts and
Component Repair Price Catalogue General Terms and Conditions apply. These
terms and conditions are found on the Bombardier Customer Portal at:
my.businessaircraft.bombardier.com
Smart Parts does not pay for this recommended Service Bulletin at any time.
H. Tooling
The equipment and tools listed below may be necessary to do this
special inspection:
GSE REFERENCE
NO. PART NO. DESCRIPTION
12X−12–02 WF160–9 Servicing Unit − Skydrol LD4(1.0 qt (U.S.) (0.946 L))
12X−12–03 PF54115–23P Servicing Unit − Skydrol LD4(2.0 gal (U.S.) (7.571 L))
20X−00−04 M1–G−KIT Portable Bonding Tester
29X−00–01 54300FHZCM Hydraulic Power Unit
Commercially Available − Borescope
Commercially Available − Container, Hydraulic Fluid,1 U.S. gal (3.8 L)
Commercially Available − Container, Hydraulic Fluid,5 U.S. gal (19 L)
Commercially Available − Wrench, Torque 16.2 to 19.8 lbf in(1.84 to 2.23 Nm)
Commercially Available − Wrench, Torque 215 to 280 lbf in(24.29 to 31.63 Nm)
Commercially Available − Wrench, Torque 620 to 745 lbf in(70.05 to 84.17 Nm)
Commercially Available − Wrench, Torque 1140 to 1370 lbf in(128.80 to 154.78 Nm)
NOTES: 1. Refer to the Global 6500 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 the G6500 for
acceptable GSE equivalents.
MODEL BD−700−1A10 (BD−700)
Basic Issue: Nov 29/2023 700−29−6502
Page 4 of 16

### Page 6

3. This list is provided for quick reference. In case of discrepancy
between this list and the tools called in the SPM, then the tools called
in the SPM prevail. Other approved alternative tools are acceptable
and can also be used.
I. Weight and Balance
Negligible.
J. Electrical Load Data
No change.
K. References
− TCCA Airworthiness Directive (Pending).
− Bombardier Aviation, Modification Summary, 700T1075323, Rev. A.
− Bombardier Aviation, Restriction and/or Special Instruction (RSI), C−01880,
Rev. −−.
− Bombardier Aviation, Standard Practices Manual (SPM), Chapters 20 and 51.
− Global 6500 BD−700 Aircraft Maintenance Manual (AMM), Chapters 6, 12, 24,
27, 29, 52 and 54.
− Global 6500 BD−700 Aircraft Illustrated Parts Catalog (AIPC), Chapter 29.
L. Other Publications Affected
− Global 6500 BD−700 Aircraft Illustrated Parts Catalog (AIPC), Chapter 29.
M. Equivalent Service Bulletins
− For the Global 6000 BD−700−1A10 aircraft, use SB 700−29−6011.
− For the Global 5500 BD−700−1A11 aircraft, use SB 700−29−5502.
2. ACCOMPLISHMENT INSTRUCTIONS
NOTES: 1. All TASKs given in the procedures that follow are from the Global 6500
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 6500 BD−700−1A10 Aircraft Maintenance Manual (AMM),
Chapter 6.
A. Aircraft Setup
(1) Obey all the electrical/electronic safety precautions. Refer to
AMM 24−00−00−910−801.
(2) Obey the hydraulic safety precautions. Refer to AMM 29−00−00−910−801.
(3) Obey the hydraulic technical precautions. Refer to AMM 29−00−00−910−802.
MODEL BD−700−1A10 (BD−700)
Basic Issue: Nov 29/2023 700−29−6502
Page 5 of 16

### Page 7

(4) Obey all the cleaning safety precautions. Refer to AMM 12−21−00−910−801.
(5) In the flight compartment, on the EMS CDU, set the circuit breaker that follows
to LOCKED. Refer to AMM 24−00−00−863−801.
For the No. 1 hydraulic system,
SYSTEM NAME CIRCUIT BREAKER NAME BUS NAME
HYD HYD PUMP 1B AC 3
For the No. 2 hydraulic system,
SYSTEM NAME CIRCUIT BREAKER NAME BUS NAME
HYD HYD PUMP 2B AC 2
(6) Put a warning placard in the flight compartment to make sure that no persons
operate the flight controls.
(7) Connect the AC electrical power to the aircraft. Refer to
AMM 24−22−00−861−801.
(8) Release hydraulic pressure from the No. 1 and No. 2 hydraulic system. Refer
to AMM 29−10−00−860−802.
(9) Remove the electrical power from the aircraft. Refer to
AMM 24−00−00−861−802.
(10) Open the aft equipment−compartment door (311BB). Refer to
AMM 52−41−00−010−801.
(11) Remove the pylon access panels (412AB/422AB). Refer to
AMM 54−52−01−000−801.
B. Inspection
NOTE: If it is not possible to complete all the instructions in this Service Bulletin
because of the aircraft configuration, submit an SRPSA for analysis and to
get an approved disposition to complete this Service Bulletin. Standard
SRPSA fees may apply. Refer to the Services section of the Bombardier
Customer portal for the latest prices, rates and fees.
MODEL BD−700−1A10 (BD−700)
Basic Issue: Nov 29/2023 700−29−6502
Page 6 of 16

### Page 8

(1) Using a borescope from the rear bay or opening pylon access panel, inspect
the routing of hydraulic systems No. 1 and No. 2 engine driven pump pressure
hoses over the length for any damage and to make sure that a minimum of
0.500 in (12.70 mm) clearance between the engine driven pump hydraulic
pressure hose, Part No. GD478−1126−1 and case drain, Part
No. AS647−06−0200A, suction pressure hose, Part No. AS648−16−0213A and
surrounding pylon structure. Refer to Figure 1 for hose(s) location and for an
example of the hydraulic pressure hose, Part No. GD478−1126−1 touching the
case drain hose clamp, and Figure 2 for hose(s) installation clearance
requirements and SPM−MM 20−22−00−220−801.
(a) If any damage is found, do the replacement of the applicable pressure
hose(s) as given in Paragraph 2.D. of this Service Bulletin.
(b) If no damage, and If the clearance is less than 0.500 in (12.70 mm), go to
Paragraph 2.C. of this Service Bulletin.
(c) If no damage, and If the clearance is greater than or equal to 0.500 in
(12.70 mm), go to Paragraph 2.E. Step (1), then proceed to
Paragraph 2.F. (Close−out).
C. Adjustment
NOTES: 1. If it is not possible to complete all the instructions in this Service
Bulletin because of the aircraft configuration, submit an SRPSA for
analysis and to get an approved disposition to complete this Service
Bulletin. Standard SRPSA fees may apply. Refer to the Services
section of the Bombardier Customer portal for the latest prices, rates
and fees.
2. The procedure that follows are for LH and is same for RH.
(1) Adjust the applicable hose(s), Part No. GD478−1126−1 or AS647−06−0200A
or AS648−16−0213A to obtain a minimum clearance as follows:
(a) Put protective film or equivalent, on drip tray and adjacent area, to prevent
damage to the surface.
(b) Put the hydraulic fluid container below the work area.
(c) Loosen the hydraulic hose(s).
(d) Before final torque of both ends, adjust the orientation to obtain 0.500 in
(12.7 mm) minimum clearance between the engine driven pump hydraulic
pressure hose, Part No. GD478−1126−1 and case drain, Part
No. AS647−06−0200A, suction pressure hose, Part No. AS648−16−0213A
and surrounding pylon structure.
CAUTION: USE TWO WRENCHES WHEN YOU REMOVE/TORQUE THE
HOSES/TUBES.  USE ONE WRENCH TO HOLD THE FITTING,
AND THE OTHER WRENCH TO LOOSEN/TORQUE THE
COUPLING NUT.  IF YOU DO NOT DO THIS, YOU CAN
CAUSE DAMAGE TO THE COMPONENTS.
MODEL BD−700−1A10 (BD−700)
Basic Issue: Nov 29/2023 700−29−6502
Page 7 of 16

### Page 9

(e) Torque the applicable pressure hose(s) assembly as follows. Refer to
SPM−MM 20−22−00−02−910−801.
NOTE: Use best shop practice and hold the bulkhead fitting to prevent
rotation while torquing.
− Torque the hydraulic pressure hose, Part No. GD478−1126−1 from
620 to 745 lbf in (70.05 to 84.17 Nm).
− Torque the case drain, Part No. AS647−06−0200A from 215 to
280 lbf in (24.29 to 31.63 Nm).
− Torque the suction pressure hose, Part No. AS648−16−0213A from
1140 to 1370 lbf in (128.80 to 154.78 Nm).
(f) Make sure that a minimum clearance of 0.500 in (12.70 mm) between the
engine driven pump hydraulic pressure hose, Part No. GD478−1126−1
and case drain, Part No. AS647−06−0200A, suction pressure hose, Part
No. AS648−16−0213A and surrounding pylon structure.
(g) Remove the protective film or equivalent, on drip tray and adjacent area,
to prevent damage to the surface.
(h) Remove the hydraulic fluid container from the work area.
(2) Proceed to Paragraph 2.E (Testing).
D. Replacement
NOTES: 1. If it is not possible to complete all the instructions in this Service
Bulletin because of the aircraft configuration, submit an SRPSA for
analysis and to get an approved disposition to complete this Service
Bulletin. Standard SRPSA fees may apply. Refer to the Services
section of the Bombardier Customer portal for the latest prices, rates
and fees.
2. The procedure that follows are for LH and is same for RH.
(1) Remove and replace the applicable damaged pressure hose(s), Part
No. GD478−1126−1 or any of the surrounding hydraulic pressure hoses, Part
No. AS647−06−0200A and AS648−16−0213A as follows. Refer to
AIPC 29−15−02−40, Figure 60, Items 170, 325 and 55, and 29−15−06−40,
Figure 60, Items 545, 300 and 55, and refer to Figure 3 for example of hose
damage.
(a) Put protective film or equivalent, on drip tray and adjacent area, to prevent
damage to the surface.
(b) Put the hydraulic fluid container below the work area.
(c) If necessary, remove the hardware attaching to the hose(s) assembly.
(d) Remove and discard the damaged hose(s) assembly.
(e) Install the new hose(s) assembly.
MODEL BD−700−1A10 (BD−700)
Basic Issue: Nov 29/2023 700−29−6502
Page 8 of 16

### Page 10

CAUTION: USE TWO WRENCHES WHEN YOU REMOVE/TORQUE THE
HOSES/TUBES.  USE ONE WRENCH TO HOLD THE FITTING,
AND THE OTHER WRENCH TO LOOSEN/TORQUE THE
COUPLING NUT.  IF YOU DO NOT DO THIS, YOU CAN CAUSE
DAMAGE TO THE COMPONENTS.
(2) Torque the applicable pressure hose(s) assembly as follow. Refer to
SPM−MM 20−22−00−02−910−801.
NOTE: Use best shop practice and hold the bulkhead fitting to prevent
rotation while torquing.
− Torque the hydraulic pressure hose, Part No. GD478−1126−1 from 620 to
745 lbf in (70.05 to 84.17 Nm).
− Torque the case drain, Part No. AS647−06−0200A or AS647G−0204SSA
from 215 to 280 lbf in (24.29 to 31.63 Nm).
− Torque the suction pressure hose, Part No. AS648−16−0213A from 1140 to
1370 lbf in (128.80 to 154.78 Nm).
(3) Make sure that a minimum clearance of 0.500 in (12.70 mm) between the
engine driven pump hydraulic pressure hose, Part No. GD478−1126−1 and
case drain, Part No. AS647−06−0200A or AS647G−0204SSA, suction
pressure hose, Part No. AS648−16−0213A and surrounding pylon structure.
(4) Remove the hydraulic fluid container and discard the unwanted hydraulic fluid
correctly.
CAUTION: USE ONLY APPROVED CLEANING AGENTS WHEN YOU CLEAN
THE HYDRAULIC FLUID LEAKAGE. SOME CLEANING AGENTS
CAN CAUSE DAMAGE TO HYDRAULIC PARTS.
(5) Clean all the hydraulic fluid from the work area.
(6) Apply a stripe of lacquer on all torqued fittings.
(7) Remove the protective film or equivalent, from the drip tray and adjacent area.
E. Testing
(1) In the flight compartment, on the EMS CDU, set the circuit breakers that follow
to IN. Refer to AMM 24−00−00−863−802:
For the No. 1 hydraulic system,
SYSTEM NAME CIRCUIT BREAKER
NAME
BUS NAME
HYD HYD PUMP 1B AC 3
For the No. 2 hydraulic system,
MODEL BD−700−1A10 (BD−700)
Basic Issue: Nov 29/2023 700−29−6502
Page 9 of 16

### Page 11

SYSTEM NAME CIRCUIT BREAKER
NAME
BUS NAME
HYD HYD PUMP 2B AC 2
(2) Do the electrical bonding test of the hydraulic tubes. Maximum resistance is
500 milliohms. Refer to SPM−MM 51−80−00−760−801.
(3) Connect the AC electrical power to the aircraft. Refer to
AMM 24−22−00−861−801.
(4) Verify the hydraulic systems No. 1 and No. 2 reservoirs quantity indication and
if less than placard limits, do the servicing of the No. 1 and No. 2 hydraulic
system reservoir. Refer to AMM 12−12−00−611−801.
(5) Perform partial bleeding of the No. 1 and No. 2 hydraulic system using engine
driven pump 1 and 2. Refer to AMM 29−10−00−870−803.
(6) Inspect the hoses installation and make sure that there is no hydraulic fluid
leakage at the fittings and hoses connections.
(7) Do the operational test of the filter manifold for hydraulic system No. 1 and
No. 2. Refer to AMM 29−12−09−710−801.
(8) Remove the electrical power from the aircraft. Refer to
AMM 24−00−00−861−802.
F. Close−out
(1) Remove all tools, equipment and unwanted materials from the work area.
(2) Install the removed pylon access panels (412AB/422AB). Refer to
AMM 54−52−01−400−801.
(3) Close the aft equipment−compartment door (311BB). Refer to
AMM 52−41−00−400−801.
(4) Remove the warning placard from the flight compartment.
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).
For information, correction(s), comment(s) and/or feedback regarding Service
Bulletins released on the Customer Portal, please contact the Service Bulletin
Group at the following email address:
bbad_SBgroup@aero.bombardier.com
MODEL BD−700−1A10 (BD−700)
Basic Issue: Nov 29/2023 700−29−6502
Page 10 of 16

### Page 12

3. MATERIAL INFORMATION
A. Kit
No kits required.
B. Parts
The parts that follow may be necessary to do this Service Bulletin and are available
from Bombardier Aviation Parts Service, Montreal:
NEW PART NO. QTY ITEM USED PARTNO. INSTRUCTIONS- DISPOSITION
AS647−06−0200A
or
AS647G−0204SSA
(See Note 2)
1 or 2 Hose − −
AS648−16−0213A
(See Note 3) 1 or 2 Hose − −
GD478−1126−1
(See Note 4) 1 or 2 Hose − −
NOTES: 1. 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.
2. Hose, Part No. AS647−06−0200A or AS647G−0204SSA is necessary
only if damage is found.
3. Hose, Part No. AS648−16−0213A is necessary only if damage is
found.
4. Hose, Part No. GD478−1126−1 is necessary only if damage is found.
C. Material
The materials that follow, or equivalent, are necessary to do this Service Bulletin.
These can be purchased from a local supplier. Bombardier Aviation does not pay
for these consumables.
DESCRIPTION PARTNO./NAME SPECIFICATION QUANTITY
SUPPLIER
(SEE
NOTE)
Alodine 1200S MIL−C−81706 As necessary Code: A
MODEL BD−700−1A10 (BD−700)
Basic Issue: Nov 29/2023 700−29−6502
Page 11 of 16

### Page 13

DESCRIPTION PARTNO./NAME SPECIFICATION QUANTITY
SUPPLIER
(SEE
NOTE)
Fluid,
Hydraulic,
Phosphate
Ester
Fire−Resistant
Skydrol LD−4
HYJET IV−A
Plus
− As necessary Code: B
Lacquer,
Gloss, for
Aircraft
A−A−3165 − As necessary Code: C
Cloth,
Cleaning,
Low−Lint
− − As necessary Code: D
Oil,
Lubricating,
Preservative
− MIL−L−3150 As necessary Code: D
Seal and Coat
Compound
(Pro
Seal 870)
06−165
MIL−PRF−81733
Type II, Class 1
Grade A
As necessary Code: D
NOTES: 1. Refer to the table that follows for each suppliers address listed by
codes.
2. 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
Henkel Corp.
23343 Sherwood Ave.
Warren, MI 48091
U.S.A.
Tel.: 1–586–759–5555
www.henkel.com
Code: B
Solutia Inc
702 Clydesdale Ave.
Anniston, AL 36201
U.S.A.
Tel.: 1–256–236–6381
MODEL BD−700−1A10 (BD−700)
Basic Issue: Nov 29/2023 700−29−6502
Page 12 of 16

### Page 14

SUPPLIERS ADDRESSES BY CODES
Code: C
Tempo Paint and Varnish Co.
205 Fenmar Dr.
Weston, Ontario
Canada, M9L 2X4
Tel.: 1–416–746–2233
www.tempo−aerospace.com
Code: D
Commercially Available
D. Publications
None.
MODEL BD−700−1A10 (BD−700)
Basic Issue: Nov 29/2023 700−29−6502
Page 13 of 16

### Page 15

SB700−29−6502_011ENGINE DRIVEN PUMP (EDP) PRESSURE HOSE LOCATION
ON LH PYLON
ON LH PYLON
MODEL BD−700−1A10 (BD−700)
Figure 1
Basic Issue: Nov 29/2023 700−29−6502
Page 14 of 16

### Page 16

SB700−29−6502_012
ENGINE DRIVEN PUMP (EDP) PRESSURE HOSE(S) INSTALLATION CLEARANCES
0.500 in (12.70 mm)
minimum clearance
0.500 in (12.70 mm)
minimum clearance
0.500 in (12.70 mm)
minimum clearance
0.500 in (12.70 mm) minimum clearance
between the hose to the P−clamp
MODEL BD−700−1A10 (BD−700)
Figure 2
Basic Issue: Nov 29/2023 700−29−6502
Page 15 of 16

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