On this page
ADs that cite it · 1
Newest first, with the revision each names, as OpenAirDocs read it from the AD’s text: check it against the AD.
Also cited in 1 proposed AD.
Text · 23
From the PDF’s text layer: layout, tables and figures are lost. The PDF is the document. © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2017-0775; AD 2018-09-15 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
Query with SQL
duckdb -csv -c "SELECT p.page, p.text_source, p.text, f.rights_holder, f.license FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256) WHERE p.file_sha256 = '4810be19d37774ad674368aaf1607783d052c680b297d35f320026d76743cecb' ORDER BY p.page"
Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.
SELECT p.page, p.text_source, p.text, f.rights_holder, f.license FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256) WHERE p.file_sha256 = '4810be19d37774ad674368aaf1607783d052c680b297d35f320026d76743cecb' ORDER BY p.page
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
MODIFICATION — REAR MOUNT — REPLACEMENT OF 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 1000 flight hours or 12 months, whichever comes first, from Service Bulletin release date (Basic Issue) EFFECTIVITY: A/C Serial No. 9313, 9381 and 9432 to 9785 MANPOWER: PART A: 1 man−hour PART B: 2.5 man−hours
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: Dec 05/2016 700−71−6003 Page 1 of 1 This Service Bulletin is available at:
MODIFICATION — REAR MOUNT — REPLACEMENT OF RETAINING BOLT AND NUT
ON THE LOWER/UPPER ENGINE REAR MOUNT ASSEMBLY
1. PLANNING INFORMATION NOTES: 1. If Service Bulletin 700 –71–6002 was incorporated on your aircraft, PART A of this Service Bulletin 700–71–6003 is not applicable. Do PART B of Service Bulletin 700–71–6003 only.
2. Service Bulletin 700 –71–6002 is no longer applicable after the incorporation of this Service Bulletin 700–71–6003, as this is a change of design.
A. Effectivity BD−700−1A10 aircraft, Serial No. 9313, 9381 and 9432 to 9785.
All other subsequent BD−700−1A10 aircraft are scheduled for the modification in production (Ref.: Modification Summary 700T02578).
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.
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: Dec 05/2016 700−71−6003 Page 1 of 20 This Service Bulletin is available at:
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.
3. Objective/Benefit:
This Service Bulletin replaces the existing bolts and self locking nuts located at the attachment points (four per engine) of the links, between the engine rear mount assemblies, with new bolts with castellated self locking nuts and additional cotter pins.
C. Description This Service Bulletin gives instructions in PART A to:
− Measure gaps on existing hardware installation.
This Service Bulletin gives instructions in PART B to:
− Replace the hardware on the left and right engine rear mount assemblies, and − Measure gaps on new hardware installation.
D. Compliance Recommended in less than 1000 flight hours or 12 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: Dec 05/2016 700−71−6003 Page 2 of 20
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.
2.5 man−hours are necessary to do PART B of this Service Bulletin.
The labor required to do PART B of 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 1000 flight hours or 12 months, whichever comes first from this Service Bulletin release date (Basic Issue).
MODEL BD−700−1A10 (BD−700) Basic Issue: Dec 05/2016 700−71−6003 Page 3 of 20
G. Material − Cost and Availability Kit 700K71–6003 is necessary to do this modification. For material data, refer to Paragraph 3.
KIT NO. PRICE 700K71–6003 Please contact Bombardier Aerospace Parts Services, in Montreal, for delivery lead times and confirmation of prices.
This kit is available at no cost if a no−charge purchase order is sent to Bombardier Aerospace in less than 1000 flight hours or 12 months, whichever comes first from this Service Bulletin release date (Basic Issue).
During or after the above free period, Smart Parts Plus does not pay for the kit.
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 − − Wrench, Torque 40 to 200 lbf in (4.5 to 22.5 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 Refer to Rolls−Royce, Service Bulletin SB−BR700−71−101975, Revision 1, dated Nov 17/16.
MODEL BD−700−1A10 (BD−700) Basic Issue: Dec 05/2016 700−71−6003 Page 4 of 20
J. Electrical Load Data No change.
K. References − TCCA Airworthiness Directive (pending).
− Bombardier Aerospace, Modification Summary, 700T02578, Rev. A2.
− Bombardier Aerospace, Standard Practices Manual (SPM), Chapter 20.
− Bombardier Aerospace, SB 700 –71–6002 Special Check/Rework — Rear Mount — Inspect the Retaining Bolt and Nut on the Lower/Upper Engine Rear Mount Assembly.
− Rolls−Royce, Service Bulletin SB−BR700−71−101975, Revision 1, dated Nov 17/16. (attached) − Advisory Wire AW700 –71–0557.
− Global 6000 BD−700 Aircraft Maintenance Manual (AMM), Chapters 6, 24, 71 and 78.
− Global 6000 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 SB 700−71−003.
− For the Global 5000 BD−700−1A11 aircraft, use SB 700−1A11−71−003.
− For the Global 5000 BD−700−1A11 Featuring Global Vision Flight Deck aircraft, use SB 700−71−5003.
2. ACCOMPLISHMENT INSTRUCTIONS NOTES: 1. All TASKs given in the procedures that follow are from the Global 6000 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 6000 BD−700−1A10 Aircraft Maintenance Manual (AMM), Chapter 6.
A. Aircraft Setup
(1) Obey all electrical/electronic safety precautions. Refer to AMM 24−00−00−910−801.
MODEL BD−700−1A10 (BD−700) Basic Issue: Dec 05/2016 700−71−6003 Page 5 of 20
(2) 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
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 MODEL BD−700−1A10 (BD−700) Basic Issue: Dec 05/2016 700−71−6003 Page 6 of 20
SYSTEM NAME CIRCUIT BREAKER NAME
BUS NAME
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 MODEL BD−700−1A10 (BD−700) Basic Issue: Dec 05/2016 700−71−6003 Page 7 of 20
(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 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 MODEL BD−700−1A10 (BD−700) Basic Issue: Dec 05/2016 700−71−6003 Page 8 of 20
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 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.
(7) Do the deactivation of the thrust reverser (for maintenance). Refer to AMM 78−30−00−040−801.
(8) Obey all engine safety precautions. Refer to AMM 71−00−00−910−801.
(9) Open the cowls. Refer to AMM 71−10−00−010−801.
MODEL BD−700−1A10 (BD−700) Basic Issue: Dec 05/2016 700−71−6003 Page 9 of 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 SSB2206_001
MAIN ISOMETRIC VIEW OF
REAR MOUNT BEAM ASSEMBLY
VIEW LOOKING FORWARD
ON LEFT HAND ENGINE INSTALLATION
MAIN ISOMETRIC VIEW OF
REAR MOUNT BEAM ASSEMBLY
VIEW LOOKING FORWARD
ON RIGHT HAND ENGINE INSTALLATION MODEL BD−700−1A10 (BD−700) Figure 1 Basic Issue: Dec 05/2016 700−71−6003 Page 10 of 20
B. PART A — Measurement of the Gaps on the Engine Rear Mount Assembly Hardware NOTE: Refer to Figure 1 for the eight installation positions where the bolts and nuts are replaced in this Service Bulletin.
(1) If Service Bulletin 700 –71–6002 was incorporated on your aircraft, PART A of this Service Bulletin is not applicable. Go to Paragraph 2.C. and do PART B of this Service Bulletin.
(2) If Service Bulletin 700 –71–6002 was not incorporated on your aircraft, do the steps that follow:
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.
(a) Measure Gap A at positions A, B, C and D, as shown in Figure 2, views A−A. The gap between the shouldered bushing fitted on the mount beam and the washer, Part No. BRR15837, must be between 0.004 and 0.043 in
(0.1 and 1.1 mm).
NOTES: 1. The mount pin, Part No. BRR15835, can be installed from either direction. If applicable, measure the gap between the shouldered bushing fitted on the mount beam, and the head of the mount pin.
2. If the gap is not within acceptable limits, fill out an SRPSA and send it by E−mail at:
SRPSA@aero.bombardier.com
(b) Measure Gap B at positions E, F, G and H, as shown in Figure 2, views A−A. The gap between the engine ring lug, Part No. BRR21165, and the head of the mount pin, Part No. BRR15838, must be between 0.028 and
0.048 in (0.7 and 1.2 mm).
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 05/2016 700−71−6003 Page 11 of 20