# Bombardier Service Bulletin 700-71-6002

Copy: Revision 01 ("SB 700-71-6002 R01"), 28 pages: PDF https://openairdocs.org/files/sha256/19/91/1991a4528f437cfa0d389a7b7ad25030e885a626feb4887db4504fd9f5096456; text https://openairdocs.org/service-documents/bombardier/sb-700-71-6002/file/1991a4528f43.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2016-9503; AD 2016-25-18 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: 700-71-6002
- Latest revision known: 700-71-6002, Revision 01, dated June 30, 2016 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/bombardier/sb-700-71-6002

## ADs that cite it (2) (OpenAirDocs)

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

- [AD 2018-09-15](https://openairdocs.org/ad/2018-09-15.md), effective Jun 15, 2018: Revision 01
- [AD 2016-25-18](https://openairdocs.org/ad/2016-25-18.md), effective Jan 3, 2017: Revision 01

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-700-71-6002/proposed.md).

## Text (28 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2016-9503; AD 2016-25-18 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

Discard the Basic Issue of this Service Bulletin dated May 31/2016, and replace in its
entirety with this Revision 01.
Service Bulletin No. 700−71−6002
Date of Basic Issue May 31/2016
Revision No. 01 Dated Jun 30/2016
This revision has no effect for aircraft on which the Basic Issue, of this Service
Bulletin was done thus no other action is necessary. Do not sign the log book if you
have not done this revision. Keep the previous log book entry. You may make an
entry as "Not Applicable" for this revision.
This revision is issued to:
1. Revise, in Service Bulletin Summary Sheet, and Paragraph 1.A., the effectivity.
2. Revise, in Service Bulletin Summary Sheet, Planning Information to "YES".
3. Add, in Paragraph 1, Planning Information, a NOTE.
4. Add, in Paragraph 1.F., a NOTE to include the SRPSA number when submitting a
warranty claim.
5. Add, in Paragraphs 1.G., and 3.B., a NOTE to submit a copy of the SRPSA with the PO
when placing an order for the parts.
6. Revise, in Paragraph 1.K., the RSI to Rev. B.
7. Revise, in Paragraph 2.B.(8), to not measure the torque value.
8. Revise, in Paragraph 2.B.(8)(a) and (b), to make a check mark in the related box of
Appendix A for the torque.
9. Add, in Paragraph 2.B.(8)(a)(i), NOTES.
10.Revise, in Paragraph 2.B.(9), to read "Gap A".
SERVICE BULLETIN
MODEL BD−700−1A10 (BD−700)
700−71−6002
Page 1 of 2
REVISION TRANSMITTAL SHEET

### Page 2

11.Add, in Paragraph 2.B.(9), NOTE 1 to measure Gap A between the head of the mount
pin and the shouldered bushing, if applicable.
12.Revise, in Paragraph 2.B.(9), Figure 2 to show where to measure Gap A when the mount
pin is installed from the opposite side.
13.Revise, in Paragraph 2.B.(10), to read "Gap B".
14.Add, in Paragraph 2.C.(1)(f) NOTE 1, instruction to apply the torque by the nut only.
15.Revise, in Paragraph 2.C.(2), to read "Gap A".
16.Add, in Paragraph 2.C.(2), NOTE 1 to measure Gap A between the head of the pin and
the shouldered bushing, if applicable.
17.Revise, in Paragraph 2.C.(2), Figure 2 to show where to measure Gap A when the mount
pin is installed from the opposite side.
18.Revise, in Paragraph 2.C.(3), to read "Gap B".
19.Add, in Appendix A, Table 5, information to not measure the torque value.
20.Add, in Appendix A, Table 6 to measure Gap A between the head of the pin and the
shouldered bushing, if applicable.
21.Add, in Appendix A, Table 7 to read "Gap B".
MODEL BD−700−1A10 (BD−700)
700−71−6002
Page 2 of 2

### Page 3

SPECIAL CHECK/REWORK — REAR MOUNT — INSPECT THE RETAINING BOLT
AND NUT ON THE LOWER/UPPER ENGINE REAR MOUNT ASSEMBLY
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 4 months,
whichever comes first
EFFECTIVITY: A/C Serial No. 9313, 9381, 9432 to 9763, 9765 and 9767 to 9770
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: See important
information at the start of Paragraph 1. YES NO
DEDICATED SCHEDULE NOYES
PREREQUISITE SERVICE BULLETINS: N/A
To place an order for parts or kits, please call Bombardier Aerospace Parts Services
at:
514−855−2999 or 1−866−538−1247
SERVICE BULLETIN SUMMARY
www.cic.bombardier.com
MODEL BD−700−1A10 (BD−700)
ATA 71−24
POWER PLANT
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 1 of 1
This Service Bulletin is available at:

### Page 4

SPECIAL CHECK/REWORK — REAR MOUNT — INSPECT THE RETAINING BOLT
AND NUT ON THE LOWER/UPPER ENGINE REAR MOUNT ASSEMBLY
1. PLANNING INFORMATION
NOTE: If rework is required, include the SRPSA number when you order parts and
when you submit a claim to warranty. Refer to Paragraphs 1.F. and 1.G.
A. Effectivity
BD−700−1A10 aircraft, Serial No. 9313, 9381, 9432 to 9763, 9765 and 9767 to
9770.
NOTE: The instructions given in this Service Bulletin are only applicable to the
systems and parts installed at the time of delivery of the aircraft or as
changed by Bombardier Aerospace Service Bulletin(s).
Before you do this bulletin, examine all STC, STA or equivalent action
changes to make sure that this bulletin can be completed.
B. Reason
1. Condition
An operator reported, while the aircraft was in maintenance, that the mount pin
at the lower rear engine mount was found backed out of the rear mount link. The
retaining bolt that passes through the mount pin, which holds the mount pin in
place, was found broken. The nut was found separated from the assembly on
the lower cowl below the engine.
SERVICE BULLETIN
www.cic.bombardier.com
MODEL BD−700−1A10 (BD−700)
ATA 71−24
POWER PLANT
Refer to applicable governmental agency regulations and requirements and make sure that the work described in this
Service Bulletin is performed in compliance with manufacturer’s recommendations and/or acceptable industry standards.
This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or
by any means without the prior written consent of Bombardier Inc. and/or its affiliates.
 2016 Bombardier Inc.  All rights reserved
Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 1 of 23
This Service Bulletin is available at:

### Page 5

2. Evidence
The investigation has found that the bolt failed under static tension loading with
no evidence of fatigue related to the fracture. There was no nonconformance
discovered with the hardware.
3. Objective/Benefit
This Service Bulletin is released to inspect the attachment points (four per
engine) of the links between the engine rear mount assemblies, until new design
hardware is introduced.
C. Description
This Service Bulletin gives instructions in PART A to:
− Inspect and record the condition of the bolts, the nuts and the torque seal,
− Check and record the existing torque of the nuts,
− Measure and record the gaps as indicated,
− Send the recorded values to Bombardier Aerospace, and
− If required, send an SRPSA to Technical Services Global Series (TS).
This Service Bulletin gives instructions in PART B to:
− If required, install the new bolt(s), nut(s) and washer(s),
− Measure and record the gaps as indicated,
− If required, send an SRPSA to Technical Services Global Series (TS), and
− Send the recorded values to Bombardier Aerospace.
D. Compliance
Recommended in less than 500 flight hours or 4 months, whichever comes first
from this Service Bulletin release date (Basic Issue).
NOTE: This Service Bulletin is in reference to Advisory Wire AW700 –71–0557.
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.
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 2 of 23

### Page 6

F. Manpower
NOTES: 1. The man−hours given are estimates to help you schedule the tasks
given in this bulletin. The estimates are for direct labor performed by
an experienced crew and do not include the time for familiarization,
planning, aircraft preparation in hangar such as towing and
positioning of scaffolds, removal of interior furnishings, repainting,
supervision and inspection.
For more information related to the manpower estimates, refer to
SB 700−00−6002.
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.
1 man−hour is necessary to do PART A of this Service Bulletin.
Bombardier Aerospace does not pay for the labor to do PART A.
0.25 man−hour for each hardware replacement (one bolt, one washer and one nut)
is necessary to do PART B of this Service Bulletin.
The labor required to do PART B 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 4 months,
whichever comes first, from this Service Bulletin release date (Basic Issue).
NOTE: Include the SRPSA number in your warranty claim.
G. Material − Cost and Availability
No kit or parts are necessary to do PART A of this Service Bulletin.
The parts in Paragraph 3.B. may be necessary to do PART B of this Service
Bulletin. For material data, refer to Paragraph 3.
The parts are available at no cost if a no−charge purchase order is sent to
Bombardier Aerospace in less than 500 flight hours or 4 months, whichever comes
first, from this Service Bulletin release date (Basic Issue).
NOTE: Submit a copy of the SRPSA with your purchase order.
During or after the above free period, Smart Parts Plus does not pay for the part(s).
H. Tooling
The equipment and tools listed below are necessary to do this special
check/rework:
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 3 of 23

### Page 7

GSE REFERENCE NO. PART NO. DESCRIPTION
20X−10−01 S4933959−501 Tag, Circuit Breaker (Red
Ring)
71X−13−02 G700−711302 Protective Mats − Lower
Engine Cowl
− − Wrench, Torque 125 to
250 lbf in (14.13 to 28.24
Nm)
NOTES: 1. Refer to the Global 6000 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 G6000) for
acceptable GSE equivalents.
3. This list is provided for quick reference. In case of discrepancy
between this list and the tools called in the SPM, WM, Chapter 20,
then the tools called in the SPM, WM prevail. Other approved
alternative tools are acceptable and can also be used.
I. Weight and Balance
No change.
J. Electrical Load Data
No change.
K. References
− TCCA Airworthiness Directive (pending).
− Bombardier Aerospace, Restriction and/or Special Instruction (RSI), C−01687,
Rev. B.
− Appendix A (attached).
− Advisory Wire AW700 –71–0557.
− Global 6000 BD−700 Illustrated Tool and Equipment Manual (ITEM), Chapters
20 and 71.
− Global 6000 BD−700 Aircraft Maintenance Manual (AMM), Chapters 6, 24, 71
and 78.
− Bombardier Aerospace, Standard Practices Manual (SPM), Chapter 20.
L. Other Publications Affected
None.
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 4 of 23

### Page 8

M. Equivalent Service Bulletin
− For the Global Express and Global Express XRS BD−700−1A10 aircraft, use
SB 700−71−002.
− For the Global 5000 BD−700−1A11 aircraft, use SB 700−1A11−71−002.
− For the Global 5000 BD−700−1A11 Featuring Global Vision Flight Deck aircraft,
use SB 700−71−5002.
2. ACCOMPLISHMENT INSTRUCTIONS
NOTES: 1. All TASKs given in the procedures that follow are from the Global 6000
Aircraft Maintenance Manual (AMM) unless otherwise specified.
2. All references made to zones, access panels and/or doors, are from the
Global 6000 BD−700−1A10 Aircraft Maintenance Manual (AMM),
Chapter 6.
A. Aircraft Setup
WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO
MAINTENANCE ON OR NEAR THE ENGINE. IF YOU DO NOT
OBEY THE SAFETY PRECAUTIONS, YOU CAN CAUSE INJURY
TO PERSONS AND DAMAGE TO EQUIPMENT.
(1) Obey all engine safety precautions. Refer to AMM 71−00−00−910−801.
(2) Obey all electrical/electronic safety precautions. Refer to
AMM 24−00−00−910−801.
(3) In the flight compartment, on the EMS CDU, set the circuit breakers that follow
to LOCKED, refer to AMM 24−00−00−863−801:
For the left engine,
SYSTEM NAME CIRCUIT BREAKER
NAME
BUS NAME
APU APU START BATT
ENGINE L FADEC CH A BATT
ENGINE L FADEC CH B BATT
ENGINE L ENG IGN 1 BATT
ENGINE L ENG IGN 2 BATT
ENGINE L ENG FUEL HPSOV BATT
ENGINE L ENG START A BATT
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 5 of 23

### Page 9

SYSTEM NAME CIRCUIT BREAKER
NAME
BUS NAME
ENGINE L ENG START B BATT
THRUST REVERSER L T/R CTL VALVE BATT
THRUST REVERSER L T/R UPPER LOCK BATT
THRUST REVERSER L T/R LOWER LOCK BATT
THRUST REVERSER L T/R TQA LOCK BATT
HYD HYD PUMP 1B AC 3
For the right engine,
SYSTEM NAME CIRCUIT BREAKER
NAME
BUS NAME
APU APU START BATT
ENGINE R FADEC CH A BATT
ENGINE R FADEC CH B BATT
ENGINE R ENG IGN 1 BATT
ENGINE R ENG IGN 2 BATT
ENGINE R ENG FUEL HPSOV BATT
ENGINE R ENG START A BATT
ENGINE R ENG START B BATT
THRUST REVERSER R T/R CTL VALVE BATT
THRUST REVERSER R T/R UPPER LOCK BATT
THRUST REVERSER R T/R LOWER LOCK BATT
THRUST REVERSER R T/R TQA LOCK BATT
HYD HYD PUMP 2B AC 2
(4) Open and tag the circuit breakers that follow to make sure the heaters do not
come on:
For the left engine:
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 6 of 23

### Page 10

LOCATION CB NO. NAME ZONE
CCBP H7 PITOT 1 HT A 222
CCBP F5 PITOT 1 HT B 222
CCBP F6 PITOT 3 HT 222
CCBP F4 L AOA HEAT 222
CCBP F3 TAT HT 1 222
For the right engine:
LOCATION CB NO. NAME ZONE
CCBP B1 PITOT 2 HT 222
CCBP F10 STBY PITOT HT 222
CCBP H9 R AOA HEAT A 222
CCBP F8 R AOA HEAT B 222
CCBP F9 TAT HT 2 222
(5) Open and tag the circuit breakers that follow:
For the left engine,
LOCATION CB NO. NAME ZONE
DCPC A1 FIREX CH A 130
DCPC A2 FIREX CH B 130
DCPC A3 L ENG FUEL SOV 130
For the right engine,
LOCATION CB NO. NAME ZONE
DCPC A1 FIREX CH A 130
DCPC A2 FIREX CH B 130
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 7 of 23

### Page 11

LOCATION CB NO. NAME ZONE
DCPC A4 R ENG FUEL SOV 130
(6) Open access door (311BB).
WARNING: MAKE SURE THAT YOU DO A DEACTIVATION OF THE THRUST
REVERSER BEFORE YOU DO WORK ON THE ENGINE. THE
THRUST REVERSER CAN ACCIDENTALLY OPERATE. THIS CAN
CAUSE INJURY TO PERSONS OR DAMAGE TO THE EQUIPMENT.
(7) Do the deactivation of the thrust reverser. Refer to AMM 78−30−00−040−801.
(8) Open the cowls. Refer to AMM 71−10−00−010−801.
B. PART A — Inspection of the Engine Rear Mount Assemblies
NOTES: 1. This Service Bulletin requires you to fill out and send Appendix A to
TS. Send Appendix A only to the E−mail address that follows:
tech.services.global.series@aero.bombardier.com
2. This Service Bulletin may require you to fill out and send an SRPSA
to TS. Send the SRPSA only to the E−mail address that follows:
SRPSA@aero.bombardier.com
WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE DURING
OR AFTER AN ENGINE OPERATION. THE ENGINE PARTS STAY
HOT FOR APPROXIMATELY THREE HOURS AFTER THE ENGINE
STOPS. THIS CAN CAUSE INJURY TO PERSONS.
WARNING: BE CAREFUL IF YOU MUST DO WORK ON HOT COMPONENTS.
USE APPROVED GLOVES AND PROTECTIVE CLOTHING. IF YOU
DO NOT DO THIS, YOU CAN CAUSE INJURY TO PERSONS.
(1) Inspect the bolts, Part No. AS54002 and AS54020 (two of each per engine),
located on the upper and lower links, between the rear mount beam and the
engine ring. Record the condition of each bolt in Appendix A − Table 1. Refer
to Figure 1:
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 8 of 23

### Page 12

exclusive property of Bombardier Inc. and
their copy or reproduction by any third party
is strictly forbidden.
Drawings and data contained herein are the
GSB7124_001
NUT
PIN
BOLT (AS54002)
PIN
BOLT (AS54020)
NUT
REFERENCE ONLY
ENGINE
MOUNT 
BEAM
(REF)
ENGINE
MOUNT 
BEAM
(REF)
WASHER
BUSHING
BUSHING
ENGINE
RING
(REF)
Engine Rear Mount Inspection
Figure 1
(2) Inspect the nuts, Part No. AS54365 (four per engine), located on the upper and
lower links, between the rear mount beam and the engine ring. Record the
condition of each nut in Appendix A − Table 2.
(3) Inspect the torque seal on each nut. Record the condition of the torque seal of
each nut in Appendix A − Table 3.
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 9 of 23

### Page 13

(4) Make sure that none of the bolts can be turned with your hand from the bolt
head, and from the nut. Record if each bolt can be turned with your hand in
Appendix A − Table 4.
(5) If a bolt is broken or missing, fill out an SRPSA and send it by E−mail at
SRPSA@aero.bombardier.com.
(6) If a nut is missing, fill out an SRPSA and send it by E−mail at
SRPSA@aero.bombardier.com.
(7) If you can turn a bolt with your hand, fill out an SRPSA and send it by E−mail
at SRPSA@aero.bombardier.com. Refer to Paragraph 2.C.(1) for replacement
instructions.
(8) Check if the torque is more or less than 150 lbf in (16.95 Nm). Set the torque
wrench to 150 lbf in (16.95 Nm) and do the steps that follow for each nut:
(a) If the existing torque of the nut is less than 150 lbf in (16.95 Nm), do a
check mark in the related box on Appendix A − Table 5, and do the
following:
(i) Torque the nut to 150 lbf in (16.95 Nm). Refer to SPM−Maintenance,
Chapter 20–20–00.
NOTES: 1. Torque by the nut only. It is not permissible to torque by
the bolt.
2. Do not add running torque.
(ii) Make a mark or stripe on the nut with the lacquer. Refer to
SPM−Maintenance, Chapter 20–21–00.
(b) If the existing torque of the nut is 150 lbf in (16.95 Nm) or more, do a
check mark in the related box on Appendix A − Table 5, and make sure
the torque seal stays intact. If necessary, make a mark or stripe on the nut
with the lacquer. Refer to SPM−Maintenance, Chapter 20–21–00.
(9) Measure Gap A between the shouldered bushing fitted on the mount beam,
and the washer, Part No. BRR15837. The gap must be between 0.002 and
0.045 in (0.051 and 1.142 mm). Record Gap A in Appendix A − Table 6. Refer
to Figure 2.
NOTES: 1. The mount pin, Part No. BRR15835, can be installed from either
direction. If applicable, measure Gap A between the shouldered
bushing fitted on the mount beam, and the head of the mount pin.
Refer to Figure 2.
2. If the gap is not within acceptable limits, fill out an SRPSA and
send it by E−mail at:
SRPSA@aero.bombardier.com
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 10 of 23

### Page 14

exclusive property of Bombardier Inc. and
their copy or reproduction by any third party
is strictly forbidden.
Drawings and data contained herein are the
GSB7124_003
REAR LINK
SECTION  
GAP A
REFERENCE ONLY
NUT
(AS54365)
WASHER
(BRR15837)
BOLT
(AS54002)
BUSHING
(BRR15836)
PIN
(BRR15835)
GAP A
WASHER
SHOULDERED BUSHING
MOUNT PIN
SHOULDERED BUSHING
Gap A
Figure 2
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 11 of 23

### Page 15

(10) On the engine ring, measure Gap B between the engine ring lug, Part No.
BRR21165, and the head of the mount pin, Part No. BRR15838. The gap must
be between 0.025 and 0.050 in (0.635 and 1.270 mm). Record Gap B in
Appendix A − Table 7. Refer to Figure 3.
NOTE: If the gap is not within acceptable limits, fill out an SRPSA and send it
by E−mail at:
SRPSA@aero.bombardier.com
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 12 of 23

### Page 16

exclusive property of Bombardier Inc. and
their copy or reproduction by any third party
is strictly forbidden.
Drawings and data contained herein are the
GSB7124_002
PIN
BOLT
NUT
BUSHING
REAR LINK
GAP B
SECTION  
(BRR15838)
(AS54020)
(AS54365)
(BRR15839)
ENGINE RING
(BRR21165)
LEFT HAND AND RIGHT HAND
TYPICAL INSTALLATION
ENGINE RING
LUG
PIN
Gap B
Figure 3
(11) Send the completed Appendix A to TS by E−mail, at:
tech.services.global.series@aero.bombardier.com
(12) Go to Paragraph 2.D. Close−out.
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 13 of 23

### Page 17

C. PART B — Replacement of the Hardware
(1) If you can turn a bolt with your hand, do the steps that follow:
(a) Remove and discard the nut, Part No. AS54365.
(b) Keep the washer, Part No. BRR15837 (for the installation of bolt, Part No.
AS54002, only).
(c) Remove the bolt.
NOTE: Make sure the mount pin and bushing stay in the link.
(d) Lubricate the threads of the new bolt, Part No. AS54002 or AS54020, with
lubricating oil.
(e) Install the new bolt, the washer, Part No. BRR15837 (if removed), and the
new nut, Part No. AS54365.
(f) Torque the nut to 210 lbf in (23.73 Nm). Refer to SPM−Maintenance,
Chapter 20–21–00.
NOTES: 1. Torque by the nut only. It is not permissible to torque by the
bolt.
2. Do not add running torque for this installation.
(g) Make a mark or stripe on the nut with the lacquer. Refer to
SPM−Maintenance, Chapter 20–21–00.
(2) Measure Gap A between the shouldered bushing fitted on the mount beam,
and the washer, Part No. BRR15837. The gap must be between 0.002 and
0.045 in (0.051 and 1.142 mm). Record Gap A in Appendix A − Table 6. Refer
to Figure 2.
NOTES: 1. The mount pin, Part No. BRR15835, can be installed from either
direction. If applicable, measure Gap A between the shouldered
bushing fitted on the mount beam, and the head of the mount pin.
Refer to Figure 2.
2. If the gap is not within acceptable limits, fill out an SRPSA and
send it by E−mail at:
SRPSA@aero.bombardier.com
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 14 of 23

### Page 18

exclusive property of Bombardier Inc. and
their copy or reproduction by any third party
is strictly forbidden.
Drawings and data contained herein are the
GSB7124_003
REAR LINK
SECTION  
GAP A
REFERENCE ONLY
NUT
(AS54365)
WASHER
(BRR15837)
BOLT
(AS54002)
BUSHING
(BRR15836)
PIN
(BRR15835)
GAP A
WASHER
SHOULDERED BUSHING
MOUNT PIN
SHOULDERED BUSHING
Gap A
Figure 2
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 15 of 23

### Page 19

(3) On the engine ring, measure Gap B between the engine ring lug, Part No.
BRR21165, and the head of the mount pin, Part No. BRR15838. The gap must
be between 0.025 and 0.050 in (0.635 and 1.270 mm). Record Gap B in
Appendix A − Table 7. Refer to Figure 3.
NOTE: If the gap is not within acceptable limits, fill out an SRPSA and send it
by E−mail at:
SRPSA@aero.bombardier.com
(4) Send the completed Appendix A to TS by E−mail, at:
tech.services.global.series@aero.bombardier.com
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 16 of 23

### Page 20

exclusive property of Bombardier Inc. and
their copy or reproduction by any third party
is strictly forbidden.
Drawings and data contained herein are the
GSB7124_002
PIN
BOLT
NUT
BUSHING
REAR LINK
GAP B
SECTION  
(BRR15838)
(AS54020)
(AS54365)
(BRR15839)
ENGINE RING
(BRR21165)
LEFT HAND AND RIGHT HAND
TYPICAL INSTALLATION
ENGINE RING
LUG
PIN
Gap B
Figure 3
D. Close−out
(1) Remove all tools, equipment and unwanted materials from the aircraft.
(2) Close the cowls. Refer to AMM 71−10−00−410−801.
(3) Do the activation of the thrust reverser. Refer to AMM 78−30−00−440−801.
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 17 of 23

### Page 21

(4) Close access door (311BB).
(5) 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 left engine,
SYSTEM NAME CIRCUIT BREAKER
NAME
BUS NAME
APU APU START BATT
ENGINE L FADEC CH A BATT
ENGINE L FADEC CH B BATT
ENGINE L ENG IGN 1 BATT
ENGINE L ENG IGN 2 BATT
ENGINE L ENG FUEL HPSOV BATT
ENGINE L ENG START A BATT
ENGINE L ENG START B BATT
THRUST REVERSER L T/R CTL VALVE BATT
THRUST REVERSER L T/R UPPER LOCK BATT
THRUST REVERSER L T/R LOWER LOCK BATT
THRUST REVERSER L T/R TQA LOCK BATT
HYD HYD PUMP 1B AC 3
For the right engine,
SYSTEM NAME CIRCUIT BREAKER
NAME
BUS NAME
APU APU START BATT
ENGINE R FADEC CH A BATT
ENGINE R FADEC CH B BATT
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 18 of 23

### Page 22

SYSTEM NAME CIRCUIT BREAKER
NAME
BUS NAME
ENGINE R ENG IGN 1 BATT
ENGINE R ENG IGN 2 BATT
ENGINE R ENG FUEL HPSOV BATT
ENGINE R ENG START A BATT
ENGINE R ENG START B BATT
THRUST REVERSER R T/R CTL VALVE BATT
THRUST REVERSER R T/R UPPER LOCK BATT
THRUST REVERSER R T/R LOWER LOCK BATT
THRUST REVERSER R T/R TQA LOCK BATT
HYD HYD PUMP 2B AC 2
(6) Remove the tags and close the circuit breakers that follow:
For the left engine,
LOCATION CB NO. NAME ZONE
DCPC A1 FIREX CH A 130
DCPC A2 FIREX CH B 130
DCPC A3 L ENG FUEL SOV 130
For the right engine,
LOCATION CB NO. NAME ZONE
DCPC A1 FIREX CH A 130
DCPC A2 FIREX CH B 130
DCPC A4 R ENG FUEL SOV 130
(7) Remove the tags and close the circuit breakers that follow:
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 19 of 23

### Page 23

For the left engine:
LOCATION CB NO. NAME ZONE
CCBP H7 PITOT 1 HT A 222
CCBP F5 PITOT 1 HT B 222
CCBP F6 PITOT 3 HT 222
CCBP F4 L AOA HEAT 222
CCBP F3 TAT HT 1 222
For the right engine:
LOCATION CB NO. NAME ZONE
CCBP B1 PITOT 2 HT 222
CCBP F10 STBY PITOT HT 222
CCBP H9 R AOA HEAT A 222
CCBP F8 R AOA HEAT B 222
CCBP F9 TAT HT 2 222
E. Recording
When any PART of 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
No kits required.
B. Parts
The parts that follow are necessary to do PART B of this Service Bulletin and are
available from Bombardier Aerospace Parts Services, Montreal:
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 20 of 23

### Page 24

NEW PART NO. QTY ITEM USED PART
NO.
INSTRUCTIONS
- DISPOSITION
AS54002 Up to
4
Bolt AS54002 Discard
AS54020 Up to
4
Bolt AS54020 Discard
AS54365 Up to
8
Nut AS54365 Discard
BRR15837 Up to
4
Washer BRR15837 Discard
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. Submit a copy of the SRPSA with your purchase order.
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 21 of 23

### Page 25

C. Material
The materials that follow, or equivalent, are necessary to do this Service Bulletin.
These can be purchased from a local supplier. Bombardier Aerospace does not pay
for these consumables.
DESCRIPTION PART
NO./NAME
SPECIFICATION QUANTITY SUPPLIER
(SEE
NOTE)
Brush, Paint,
Natural or
Synthetic
Bristle
− − As Necessary Code: A
Lacquer,
Cellulose
Nitrate, Gloss,
for Aircraft
Use
− TT−L−32 As Necessary Code: A
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 22 of 23

### Page 26

DESCRIPTION PART
NO./NAME
SPECIFICATION QUANTITY SUPPLIER
(SEE
NOTE)
Oil,
Lubricating,
Aircraft
Turbine
Engine,
Synthetic
Base
Aeroshell/
Royco
Turbine Oil
500
Aeroshell/
Royco
Turbine Oil
560
BP or Exxon
or Eastman
Turbo Oil
2197
BP or Exxon
or Eastman
Turbo Oil
2380
Castrol Aero
5000
Mobil Jet Oil II
Mobil Jet Oil
254
MIL−PRF−23699
(TYPE II)
As Necessary Code: A
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
Commercially Available
D. Publications
No publications required.
MODEL BD−700−1A10 (BD−700)
Basic Issue: May 31/2016
Revision 01: Jun 30/2016
700−71−6002
Page 23 of 23

### Page 27

700−71−6002 Rev. 01 Jun 30/2016
SPECIAL CHECK/REWORK — REAR MOUNT — INSPECT THE
RETAINING BOLT AND NUT ON THE LOWER/UPPER ENGINE REAR
MOUNT ASSEMBLY
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 28

SERVICE BULLETIN INCORPORATION SHEET − "700−71−6002"
Upon completion of the Service Bulletin, please fill−in, fax to
(514) 855−8798 or e−mail to Fracas at fracas.montreal@aero.bombardier.com
If your aircraft is registered on CAMP and you are reporting to them,
please do not send the incorporation sheet to Bombardier. If your aircraft
is on another tracking system, please contact Bombardier to make
arrangements for automated data submission.
700−71−6002 01
COMPLIED WITH
YES    NO    N/A
PART A
PART B
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)

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.