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Discard the Basic Issue of this Service Bulletin dated May 31/2016, and replace in its entirety with this Revision 01.
Service Bulletin No. 700−71−5002 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−700−1A11 (BD−700) 700−71−5002 Page 1 of 2
REVISION TRANSMITTAL SHEET
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−700−1A11 (BD−700) 700−71−5002 Page 2 of 2
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. 9386, 9401 and 9445 to 9768 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−700−1A11 (BD−700) ATA 71−24
POWER PLANT Basic Issue: May 31/2016 Revision 01: Jun 30/2016 700−71−5002 Page 1 of 1 This Service Bulletin is available at:
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−700−1A11 aircraft, Serial No. 9386, 9401 and 9445 to 9768.
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.
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.
SERVICE BULLETIN www.cic.bombardier.com MODEL BD−700−1A11 (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 700−71−5002 Page 1 of 23 This Service Bulletin is available at:
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−700−1A11 (BD−700) Basic Issue: May 31/2016 Revision 01: Jun 30/2016 700−71−5002 Page 2 of 23
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 700−00−5002.
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−700−1A11 (BD−700) Basic Issue: May 31/2016 Revision 01: Jun 30/2016 700−71−5002 Page 3 of 23
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 5000 Featuring Global Vision Flight Deck 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 GVFD) 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 5000 Featuring Global Vision Flight Deck BD−700 Illustrated Tool and Equipment Manual (ITEM), Chapters 20 and 71.
− Global 5000 Featuring Global Vision Flight Deck 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−700−1A11 (BD−700) Basic Issue: May 31/2016 Revision 01: Jun 30/2016 700−71−5002 Page 4 of 23
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 6000 BD−700−1A10 aircraft, use SB 700−71−6002.
2. ACCOMPLISHMENT INSTRUCTIONS NOTES: 1. All TASKs given in the procedures that follow are from the Global 5000 BD−700−1A11 Featuring Global Vision Flight Deck Aircraft Maintenance Manual (AMM) unless otherwise specified.
2. All references made to zones, access panels and/or doors, are from the Global 5000 BD−700−1A11 Featuring Global Vision Flight Deck) 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−700−1A11 (BD−700) Basic Issue: May 31/2016 Revision 01: Jun 30/2016 700−71−5002 Page 5 of 23
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−700−1A11 (BD−700) Basic Issue: May 31/2016 Revision 01: Jun 30/2016 700−71−5002 Page 6 of 23
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−700−1A11 (BD−700) Basic Issue: May 31/2016 Revision 01: Jun 30/2016 700−71−5002 Page 7 of 23
LOCATION CB NO. NAME ZONE DCPC A4 R ENG FUEL SOV 130
(6) Open the 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−700−1A11 (BD−700) Basic Issue: May 31/2016 Revision 01: Jun 30/2016 700−71−5002 Page 8 of 23
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−700−1A11 (BD−700) Basic Issue: May 31/2016 Revision 01: Jun 30/2016 700−71−5002 Page 9 of 23