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Some pages are OCR from a scan. OCR can misread letters and numbers. © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2018-0796; AD 2018-25-07 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
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SPECIAL CHECK/REWORK — BELLY FAIRINGS — INSPECT FORWARD AND MIDDLE ACCESS PANEL (181BB) AND (183BB) FOR DRAINAGE HOLE BLOCKAGE,
AND IF NECESSARY REMOVE SEALANT 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 750 flight hours or 20 months, whichever comes first, from this Service Bulletin release date (Basic Issue) EFFECTIVITY: A/C Serial No. 9386, 9401 and 9445 to 9737 MANPOWER: PART A: 1 man−hour PART B: 5 man−hours
CONTINUED AIRWORTHINESS (CAW)
FLEET CAMPAIGN YES NO 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
SERVICE BULLETIN SUMMARY www.cic.bombardier.com MODEL BD−700−1A11 (BD−700) ATA 53−61
FUSELAGE Basic Issue: May 17/2017 700−53−5010 Page 1 of 1 This Service Bulletin is available at:
SPECIAL CHECK/REWORK — BELLY FAIRINGS — INSPECT FORWARD AND MIDDLE ACCESS PANEL (181BB) AND (183BB) FOR DRAINAGE HOLE BLOCKAGE,
AND IF NECESSARY REMOVE SEALANT
1. PLANNING INFORMATION A. Effectivity BD−700−1A11 aircraft, Serial No. 9386, 9401 and 9445 to 9737.
All other subsequent BD−700−1A11 aircraft are scheduled for the modification in production (Ref.: Modification Summary 700T810087).
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:
The fluid drainage gaps between the fairing and access panels 181BB and 183BB may be obstructed with sealant.
2. Evidence:
The aerodynamic sealant applied on the panel contours obstructs the gaps provided for the evacuation of fuel/hydraulic fluids from the belly fairing in the event of a system leakage. As a result, any fluid leakage will be retained inside the belly fairing and therefore not be observed during daily inspection.
SERVICE BULLETIN www.cic.bombardier.com MODEL BD−700−1A11 (BD−700) ATA 53−61
FUSELAGE 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.
2017 Bombardier Inc. All rights reserved Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.
Basic Issue: May 17/2017 700−53−5010 Page 1 of 11 This Service Bulletin is available at:
3. Objective/Benefit:
The drain channels allow detection of local fuel/hydraulic fluid leakage. They prevent the accumulation of flammable fluids in the belly fairing, and the potential subsequent ignition of these accumulated fluids. This Service Bulletin is released to inspect the aerodynamic sealant and, if necessary, locally remove the sealant to allow for drainage.
C. Description This Service Bulletin gives instructions in PART A, to :
− Inspect the aerodynamic sealant of access panels 181BB and 183BB.
This Service Bulletin gives instructions in PART B, to:
− Remove access panels 181BB and 183BB, − Locally remove the sealant at the location of the 12 drain gaps, − Install access panels 181BB and 183BB, − Apply aerodynamic sealant as per engineering drawing, and − Check the aerodynamic smoothness of access panels 181BB and 183BB.
D. Compliance Recommended in less than 750 flight hours or 20 months, whichever comes first from this Service Bulletin release date (Basic Issue).
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 17/2017 700−53−5010 Page 2 of 11
F. Manpower NOTES: 1. The man−hours given are to help you schedule the tasks given in this 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 700−00−5002.
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 man−hours and should be considered for planning purposes before you schedule this Service Bulletin.
3. Labor hours are based on the fact that the modification 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.
PART A: 1 man−hour is necessary to do this special check.
Bombardier Aerospace does not pay for the labor to do PART A of this Service Bulletin.
PART B: 5 man−hours are necessary to do this rework.
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 750 flight hours or 20 months, whichever comes first from this Service Bulletin release date (Basic Issue).
G. Material − Cost and Availability No kit or parts are necessary to do this special check/rework. For material data, refer to Paragraph 3.
MODEL BD−700−1A11 (BD−700) Basic Issue: May 17/2017 700−53−5010 Page 3 of 11
H. Tooling The equipment and tools listed below are necessary to do this special check/rework:
GSE REFERENCE NO. PART NO. DESCRIPTION Commercially Available − Sealant Gun Commercially Available − Wrench, Torque 15 to 25 lbf in (1.70 to 2.82 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 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 − Bombardier Aerospace, Restriction and/or Special Instruction (RSI), C−01692, Rev. −−.
− Bombardier Aerospace, Modification Summary, 700T810087, Rev. A3.
− Bombardier Aerospace, Standard Practices Manual (SPM), Chapter 20.
− Bombardier Aerospace, Drawing GS298−0001, NIEO R130270.
− Global 5000 Featuring Global Vision Flight Deck BD−700 Aircraft Maintenance Manual (AMM), Chapters 6 and 51.
− Global 5000 Featuring Global Vision Flight Deck BD−700 Structural Repair Manual (SRM), Chapter 51.
L. Other Publications Affected None.
MODEL BD−700−1A11 (BD−700) Basic Issue: May 17/2017 700−53−5010 Page 4 of 11
M. Equivalent Service Bulletin − For the Global Express and Global Express XRS BD−700−1A10 aircraft, use SB 700−53−051.
− For the Global 5000 BD−700−1A11 aircraft, use SB 700−1A11−53−026.
− For the Global 6000 BD−700−1A10 aircraft, use SB 700−53−6009.
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 No setup required.
B. PART A − Inspection of Sealant
(1) Check the aerodynamic sealant around access panels 181BB and 183BB.
(2) If the access panels 181BB and 183BB do not have aerodynamic sealant at the locations indicated in Figure 1, Section C−C, you have met the intent of this Service Bulletin. Continue to Paragraph 2.E. Recording, and make an entry in the aircraft log book for PART B as N/A.
(3) If the access panels 181BB or 183BB have aerodynamic sealant on all edges as indicated in Figure 1, Section D−D, do PART B of this Service Bulletin.
MODEL BD−700−1A11 (BD−700) Basic Issue: May 17/2017 700−53−5010 Page 5 of 11
exclusive property of Bombardier Inc. and their copy or reproduction by any third party is strictly forbidden.
Drawings and data contained herein are the SSB5361_002 ACCESS PANEL 181BB ACCESS PANEL 183BB
SEALING PAD
SEALING PAD
NO AERODYNAMIC SEAL APPLIED (TYP AFT EDGE OF PANEL 181BB) (TYP ALL EDGES OF PANEL 183BB)
AERODYNAMIC SEAL APPLIED (NOT APPLICABLE TO PANEL 183BB) SECTION − SECTION − Aerodynamic Sealant Figure 1 C. PART B − Rework − Removal of Aerodynamic Sealant
(1) Remove access panels 181BB and 183BB. Refer to AMM 53−61−19−000−801.
(2) Remove all traces of sealant from access panels 181BB and 183BB. Refer to SPM Chapter 51−23−00.
MODEL BD−700−1A11 (BD−700) Basic Issue: May 17/2017 700−53−5010 Page 6 of 11
(3) Locally remove the sealant from the aircraft structure at the four locations of the drain gaps, aft of access panel 181BB. Refer to Figure 2. Refer to SPM Chapter 51−23−00.
(4) Locally remove the sealant from the aircraft structure at the eight locations of the drain gaps, aft and forward of access panel 183BB. Refer to Figure 2.
Refer to SPM Chapter 51−23−00.
exclusive property of Bombardier Inc. and their copy or reproduction by any third party is strictly forbidden.
Drawings and data contained herein are the FSB5361_001 ACCESS PANEL 181BB ACCESS PANEL 183BB
DRAIN GAP LOCATIONS Drain Locations Figure 2 MODEL BD−700−1A11 (BD−700) Basic Issue: May 17/2017 700−53−5010 Page 7 of 11
(5) Install access panel 181BB. Refer to AMM 53−61−19−400−801 and Drawing GS298−0001, NIEO R130270 page 2.
NOTE: Omit aerodynamic sealant along the aft edge of access panel 181BB.
(6) Install access panel 183BB. Refer to AMM 53−61−19−400−801 and Drawing GS298−0001, NIEO R130270 page 3.
NOTE: Do not apply aerodynamic sealant around access panel 183BB.
D. Close−out
(1) Do a check of the aerodynamic smoothness of the access panels 181BB and 183BB. Refer to SRM Chapter 51–14–04.
(2) Remove all tools, equipment and unwanted materials from the work area.
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 No parts required.
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) Ergonomic Sealant Removal Tool − − As Necessary for PART B Code: A MODEL BD−700−1A11 (BD−700) Basic Issue: May 17/2017 700−53−5010 Page 8 of 11
DESCRIPTION PART NO./NAME
SPECIFICATION QUANTITY SUPPLIER (SEE NOTE) Sealing Compound − MIL−PRF−81733 Type II, Class 1, Grade A Pro Seal 870 B As Necessary for PART B Code: A Scraper, Non−Metallic − − As Necessary for PART B Code: B Spatula (tool to fair material) − − As Necessary for PART B Code: B Tape, Masking − − As Necessary for PART B Code: B 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 PRC−Desoto International 5676 Timberlea Blvd.
Mississauga, Ontario Canada, L4W 4M6 Tel.: (905) 629−7999 www.ppgaerospace.com Code: B Commercially Available D. Publications No publications required.
MODEL BD−700−1A11 (BD−700) Basic Issue: May 17/2017 700−53−5010 Page 9 of 11
BOMBARDIER GLOBAL 5000
FEATURING GLOBAL VISION FLIGHT DECK MODEL BD-700-1A11 (BD-700) 5 IDENTIFIER X R130270 NIEO 8 SHEET 5 IDENTIFIER EO Г NIEO X R130270 ENGINEERING ORDER (EO) 4 DRAWING NUMBER 3 MS CODE DH GS298-0001 4 DRAWING NUMBER 3 MS CODE GS298-0001 DH APPLY AERODYNAMIC SEALING ALONG LH, RH AND FORWARD EDGES OF ACCESS PANEL GS297-0583 F.NO. 293. GS297-0582 F NO. 293.
ITEM 183 REF BOMBARDIER OMIT AERODYNAMIC SEALING ALONG AFT EDGE OF ACCESS PANEL GS297-0582 F.NO. 293. BT0204-02 MW REV 2004-09 GS298-0001 - Installation of Belly Fairing (Sheet 1 of 1, Rev. NEO R130270) Basic Issue: May 17/2017 700-53-5010 Page 10 of 11
BOMBARDIER GLOBAL 5000
FEATURING GLOBAL VISION FLIGHT DECK MODEL BD-700-1A11 (BD-700) 5 IDENTIFIER EO X R130270 NIEO 8 SHEET 5 IDENTIFIER EO NIEO X R130270 ENGINEERING ORDER (EO) 4 DRAWING NUMBER 3 MS CODE DH GS298-0001 OMIT AERODYNAMIC SEALING AROUND PERIPHERY OF ACCESS PANEL GS297-0122 F.NO. 178. 4 DRAWING NUMBER 3 MS CODE GS298-0001 DH GS297-0122 ENO. 178.
CErRIL ON LE ® E BOMBARDIER BT0204-02 MW REV 2004-09 GS298-0001 - Installation of Belly Fairing (Sheet 1 of 1, Rev. NIEO R130270) Basic Issue: May 17/2017 700-53-5010 Page 11 of 11