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SPECIAL CHECK – FRONT AND REAR ENGINE MOUNT ASSEMBLIES –
INSPECTION OF BUSHINGS ON THE ENGINE MOUNT SYSTEM 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 Refer to Paragraph 1.D.
EFFECTIVITY: A/C Serial No. 9861, 9872, 60001 to 60004, 60009, and 60016 MANPOWER: Refer to Paragraph 1.F.
CONTINUED AIRWORTHINESS (CAW)
FLEET CAMPAIGN NOYES TLMC, CH 5 AFFECTED NOYES KITS and/or PARTS NOYES
TOOLING/GSE YES NO
PLANNING INFORMATION NOYES
DEDICATED SCHEDULE NOYES PREREQUISITE SERVICE BULLETINS: N/A NOTE: This Service Bulletin may be subject to an Airworthiness Directive which will make it necessary to implement this Service Bulletin.
To place an order for parts or kits, please call Bombardier 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 71−23, 71−24
POWERPLANT Basic Issue: Dec 14/2020 700−71−6501 Page 1 of 1 This Service Bulletin is available at:
SPECIAL CHECK – FRONT AND REAR ENGINE MOUNT ASSEMBLIES – INSPECTION OF BUSHINGS ON THE ENGINE MOUNT SYSTEM1.
PLANNING INFORMATION NOTE: Before you do this Service Bulletin, examine all STC, STA or equivalent action changes to make sure that this Service Bulletin can be completed.
A. Effectivity BD−700−1A10 aircraft, Serial No. 9861, 9872, 60001 to 60004, 60009, and 60016.
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. Evidence:
There have been reports that bushings were missing from the forward engine mount system.
2. Objective/Benefit:
This Service Bulletin instructs to inspect the forward and aft engine mount system for missing bushings and to verify the proper installation of the sliding bushings. Continued operation of engine with bushings missing will result in redistribution of load/stress in the engine mount system and may lead to the damage of mount components.
SERVICE BULLETIN my.businessaircraft.bombardier.com MODEL BD−700−1A10 (BD−700) ATA 71−23, 71−24
POWERPLANT 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.
2020 Bombardier Inc. All rights reserved Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.
Basic Issue: Dec 14/2020 700−71−6501 Page 1 of 26 This Service Bulletin is available at:
C. Description This Service Bulletin gives instructions in PART A to:
− Inspect at the upper and lower side of front mount beam for proper installation of sliding bushing, Part No. BRR15811.
This Service Bulletin gives instructions in PART B to:
− Inspect at the thrust strut front location for proper installation of sliding bushing, Part No. BRR15808.
This Service Bulletin gives instructions in PART C to:
− Inspect at the thrust strut aircraft pylon interface for proper installation of sliding bushing, Part No. BRR15823.
This Service Bulletin gives instructions in PART D to:
− Inspect at the front mount beam interface with the aircraft pylon upper and lower installation for proper installation of sliding bushing, Part No. BRR15804.
This Service Bulletin gives instructions in PART E to:
− Inspect at the rear mount beam interface with the aircraft pylon upper and lower installation for proper installation of sliding bushing, Part No. BRR15841.
D. Compliance Recommended in less than 750 flight hours or 15 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.
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.
MODEL BD−700−1A10 (BD−700) Basic Issue: Dec 14/2020 700−71−6501 Page 2 of 26
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. 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 man−hours and should be considered for planning purposes before you schedule this Service Bulletin
10.5 man−hours are necessary to do this Service Bulletin.
The labor required to do this Service Bulletin is at no cost if:
− the work is done during new aircraft warranty period, and − the work is done at Bombardier Business Aviation Services (BBAS) or Authorized Service Facilities (ASF), and − this Service Bulletin is scheduled in less than 750 flight hours or 15 months, whichever comes first, from its release date (Basic Issue).
G. Material − Cost and Availability No kit or parts are necessary to do this Service Bulletin.
H. Tooling The equipment and tools listed below are necessary to do this modification:
GSE REFERENCE NO. PART NO. DESCRIPTION 20X−10−01 S4933959−501 Tag, Circuit Breaker (Red Ring) 71X−13−02 G700−711302−1 Protective Mats − Lower Engine Cowl Commercially available − Feeler Gauge Commercially available − Wrench, Torque 125 to 250 lbf in (14.13 to 28.24 Nm) NOTES: 1. Refer to the Global 6500 Illustrated Tool and Equipment Manual (ITEM) to make sure that you use the correct equipment configuration.
MODEL BD−700−1A10 (BD−700) Basic Issue: Dec 14/2020 700−71−6501 Page 3 of 26
2. Refer to the Liability Statement in the ITEM for the G6500 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 Aviation, Restriction and/or Special Instruction (RSI), C−01793, Rev. −−.
− Rolls Royce, Engine Maintenance Manual (EMM), Chapters 70 and 71.
− Global 6500 BD−700 Aircraft Maintenance Manual (AMM), Chapters 6, 24, 71 and 78.
− Global 6500 BD−700 Illustrated Tool and Equipment Manual (ITEM), Chapters 20 and 71.
L. Other Publications Affected None.
M. Equivalent Service Bulletins − For the Global Express and Global Express XRS BD−700−1A10 aircraft, use Service Bulletin 700−71−005.
− For the Global 5000 BD−700−1A11 aircraft, use Service Bulletin 700−1A11−71−005.
− For the Global 5000 BD−700−1A11 Featuring Global Vision Flight Deck aircraft, use Service Bulletin 700−71−5005.
− For the Global 6000 BD−700−1A10 aircraft, use Service Bulletin 700−71−6005.
− For the Global 5500 BD−700−1A11 aircraft, use Service Bulletin 700−71−5501.
MODEL BD−700−1A10 (BD−700) Basic Issue: Dec 14/2020 700−71−6501 Page 4 of 26
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 NOTE: The steps in the Aircraft Setup section of this Service Bulletin are recommended steps. The steps give a recommendation to get access to the work area. This recommendation is to give a safe work area and to minimize possible damage to surrounding aircraft parts. Alternative steps can be used at the operator’s discretion.
(1) Obey all electrical/electronic safety precautions. Refer to AMM 24−00−00−910−801.
(2) In the flight compartment, on the EMS CDU, set the circuit breakers that follow to OUT or 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
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 MODEL BD−700−1A10 (BD−700) Basic Issue: Dec 14/2020 700−71−6501 Page 5 of 26
SYSTEM NAME CIRCUIT BREAKER NAME
BUS NAME 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
(3) Open and tag the circuit breakers that follow to make sure the heaters do not come on:
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 MODEL BD−700−1A10 (BD−700) Basic Issue: Dec 14/2020 700−71−6501 Page 6 of 26
LOCATION CB NO. NAME ZONE 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
(4) 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 DCPC A4 R ENG FUEL SOV 130
(5) 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.
(6) Obey all the thrust reverser safety precautions. Refer to AMM 78−30−00−910−801.
MODEL BD−700−1A10 (BD−700) Basic Issue: Dec 14/2020 700−71−6501 Page 7 of 26
(7) Do the deactivation of the thrust reverser (for maintenance). Refer to EMM BR700NG−A−78−30−00−01AAA−560A−A.
(8) Obey all engine safety precautions. Refer to AMM 71−00−00−910−801.
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.
(9) Remove the pylon panel for thrust strut and front mount 412AB/422AB. Refer to AMM 54−52−01−000−801.
(10) Remove the pylon panel for rear mount 412BB/422BB. Refer to AMM 54−52−01−000−801.
(11) Remove the firebox lower access panel 432BT/442BT. Refer to CMM 71−14−51 or 71−14−52.
(12) Open the lower cowl 432AB/442AB. Refer to AMM 71−10−00−010−801.
NOTE: Lower cowl need not to be removed but must be opened.
(13) Remove the upper cowl 432AT/442AT. Refer to AMM 71−10−00−010−801.
(14) Remove the firebox lid 432CT/442CT. Refer to CMM 71−14−51 or 71−14−52.
B. PART A — Inspection of Sliding Bushing (BRR15811) at the Upper and Lower Side of Front Mount Beam NOTE: If it is not possible to complete all the instructions in this Service Bulletin because of the configuration of the aircraft, submit an SRPSA for analysis and to get an approved disposition to complete this Service Bulletin.
(1) Do the gap check at upper side of front mount beam as follows, refer to Figure 1, Detail C and D:
(a) Using a feeler gauge, measure Gap A between front mount beam pin, Part No. BRR15812 and the shouldered bushing installed on the front mount beam (standard installation), or gap between the shouldered bushing installed on the front mount beam and the washer Part No. BRR15810 (alternative installation), must be between 0.004 and 0.055 in (0.10 and
1.40 mm).
Record the results in Appendix (Table 1) and send it to TS by E−mail at tech.services.global.series@aero.bombardier.com.
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: Dec 14/2020 700−71−6501 Page 8 of 26
(b) For Pre SB BR700−71−101976 aircraft, inspect the nut, Part No. AS54364 and bolt, Part No. AS53914 at the upper side of front mount beam for missing or physical damage.
NOTE: If missing or physical damage found, fill out an SRPSA and send it by E−mail at:
SRPSA@aero.bombardier.com
(c) Make sure that the bolt must not be free to turn with finger pressure.
NOTE: If bolt can be turned with finger pressure, fill out an SRPSA and send it by E−mail at:
SRPSA@aero.bombardier.com
(2) Do the gap check at lower side of front mount beam as follows, refer to Figure 1, Detail C and D:
(a) Using a feeler gauge, measure Gap B between front mount beam pin, Part No. BRR15812 and the shouldered bushing installed on the front mount beam (standard installation), or gap between the shouldered bushing installed on the front mount beam and the washer Part No. BRR15810 (alternative installation), must be between 0.004 and 0.055 in (0.10 and
1.40 mm).
Record the results in Appendix (Table 1) and send it to TS by E−mail at tech.services.global.series@aero.bombardier.com.
NOTE: If the gap is not within acceptable limits, fill out an SRPSA and send it by E−mail at:
SRPSA@aero.bombardier.com
(b) For Pre SB BR700−71−101976 aircraft, inspect the nut, Part No. AS54364 and bolt, Part No. AS53914 at the lower side of front mount beam for missing or physical damage.
NOTE: If missing or physical damage found, fill out an SRPSA and send it by E−mail at:
SRPSA@aero.bombardier.com
(c) Make sure that the bolt must not be free to turn with finger pressure.
NOTE: If bolt can be turned with finger pressure, fill out an SRPSA and send it by E−mail at:
SRPSA@aero.bombardier.com C. PART B – Inspection of Sliding Bushing (BRR15808) at the Thrust Strut Front Location NOTE: If it is not possible to complete all the instructions in this Service Bulletin because of the configuration of the aircraft, submit an SRPSA for analysis and to get an approved disposition to complete this Service Bulletin.
MODEL BD−700−1A10 (BD−700) Basic Issue: Dec 14/2020 700−71−6501 Page 9 of 26
(1) Do the gap check at the thrust strut front location as follows, refer to Figure 1, Detail E and F:
(a) Using a feeler gauge, measure Gap C between the front mount beam pin, Part No. BRR15809 and the shouldered bushing installed on the front mount beam, must be between 0.008 and 0.050 in (0.20 and 1.30 mm).
Record the results in Appendix (Table 2) and send it to TS by E−mail at tech.services.global.series@aero.bombardier.com.
NOTE: If the gap is not within acceptable limits, fill out an SRPSA and send it by E−mail at:
SRPSA@aero.bombardier.com
(b) For Pre SB BR700−71−101976 aircraft, inspect the nut, Part No. AS54364 and bolt, Part No. AS53912 at the thrust strut front location for missing or physical damage.
NOTE: If missing or physical damage found, fill out an SRPSA and send it by E−mail at:
SRPSA@aero.bombardier.com
(c) Make sure that the bolt must not be free to turn with finger pressure.
NOTE: If bolt can be turned with finger pressure, fill out an SRPSA and send it by E−mail at:
SRPSA@aero.bombardier.com D. PART C — Inspection of Sliding Bushing (BRR15823) at the Thrust Strut Aircraft Pylon Interface NOTE: If it is not possible to complete all the instructions in this Service Bulletin because of the configuration of the aircraft, submit an SRPSA for analysis and to get an approved disposition to complete this Service Bulletin.
(1) Do the gap check at the thrust strut aircraft pylon interface as follows, refer to Figure 1, Detail E and G:
(a) Using a feeler gauge, measure the Gap D between the thrust strut pin, Part No. BRR15824 and the shouldered bushing installed on the thrust strut, must be between 0.008 and 0.055 in (0.20 and 1.40 mm).
Record the results in Appendix (Table 3) and send it to TS by E−mail at tech.services.global.series@aero.bombardier.com.
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: Dec 14/2020 700−71−6501 Page 10 of 26
(b) For Pre SB BR700−71−101976 aircraft, inspect the nut, Part No. AS54364 and bolt, Part No. AS53912 at the thrust strut aircraft pylon interface for missing or physical damage.
NOTE: If missing or physical damage found, fill out an SRPSA and send it by E−mail at:
SRPSA@aero.bombardier.com
(c) Make sure that the bolt must not be free to turn with finger pressure.
NOTE: If bolt can be turned with finger pressure, fill out an SRPSA and send it by E−mail at:
SRPSA@aero.bombardier.com E. PART D — Inspection of Sliding Bushing (BRR15804) at the Front Mount Beam Interface with the Aircraft Pylon Upper and Lower Installation NOTE: If it is not possible to complete all the instructions in this Service Bulletin because of the configuration of the aircraft, submit an SRPSA for analysis and to get an approved disposition to complete this Service Bulletin.
(1) Do the gap check at the front mount beam Interface with the aircraft pylon upper installation as follows, refer to Figure 1, Detail C and H:
(a) Using a feeler gauge, measure Gap E between the front mount beam pin, Part No. BRR15805 and the shouldered bushing installed on the front mount beam (standard installation) or gap between the washer Part No.
BRR15807 and the shouldered bushing installed on the front mount beam (alternative installation), must be in between 0.008 and 0.048 in (0.20 and
1.20 mm).
Record the results in Appendix (Table 4) and send it to TS by E−mail at tech.services.global.series@aero.bombardier.com.
NOTE: If the gap is not within acceptable limits, fill out an SRPSA and send it by E−mail at:
SRPSA@aero.bombardier.com
(2) Do the gap check at the front mount beam Interface with the aircraft pylon lower installation as follows, refer to Figure 1, Detail C and H:
(a) Using a feeler gauge, measure Gap F between the front mount beam pin, Part No. BRR15805 and the shouldered bushing installed on the front mount beam (standard installation) or gap between the washer Part No.
BRR15807 and the shouldered bushing installed on the front mount beam (alternative installation), must be in between 0.008 and 0.048 in (0.20 and
1.20 mm).
MODEL BD−700−1A10 (BD−700) Basic Issue: Dec 14/2020 700−71−6501 Page 11 of 26