Bombardier Service Bulletin 700-53-6008

Aug 03/2017 700-53-6008Page 1 of 1

SERVICE BULLETIN INFORMATION SHEET MODEL BD-700-1A10 (BD-700) ATA 53-61

FUSELAGE MODIFICATION – BELLY FAIRINGS –

REPLACEMENT OF ATTACHMENTS FOR THE ACCESS PANELS Service Bulletin No.: 700-53-6008 Issue: Revision 01 Dated: Dec 16/2016 The following data is supplied for information only. No revision to the Service Bulletin is necessary.

Keep this Information Sheet and the Information Sheet dated Mar 13/2017 with subject Service Bulletin. Discard the Information Sheet dated Jan 03/2017.

This Information Sheet is issued to revise the labor and parts free-of-charge period in Paragraphs 1.F. and 1.G.

In Paragraph 1.F., Manpower, the second statement should read as follows:

The labor required to do this Service Bulletin is at no cost if:

(1) the work is done at Bombardier Business Aviation Services (BBAS) or Authorized Service Facilities (ASF), and

(2) this Service Bulletin is scheduled before Feb 01/2018.

In Paragraph 1.G., Material - Cost and Availability, the second statement should read as follows:

The kit and parts are available at no cost if:

- a no-charge purchase order is sent to Bombardier Aerospace before Feb 01/2018.

March 13/2017 700-53-6008Page 1 of 1

SERVICE BULLETIN INFORMATION SHEET MODEL BD-700-1A10 (BD-700) ATA 53-61

FUSELAGE MODIFICATION – BELLY FAIRINGS –

REPLACEMENT OF ATTACHMENTS FOR THE ACCESS PANELS Service Bulletin No.: 700-53-6008 Issue: Revision 01 Dated: Dec 16/2016 The following data is supplied for information only. No revision to the Service Bulletin is necessary.

Keep this Information Sheet and the Information Sheet dated Jan 03/2017 with subject Service Bulletin.

This Information Sheet is issued to update the compliance time in the Service Bulletin Summary Sheet and in Paragraph 1.D. of the Service Bulletin.

The first row in the Service Bulletin Summary Sheet should read as follows:

RECOMMENDED

RELIABILITY/DISPATCHABILITY/COST AVOIDANCE

COMPLIANCE TIME Within 12 months from this Service Bulletin Release Date (Basic Issue).

The compliance statement in Paragraph 1.D., Compliance should read as follows:

Recommended within 12 months from this Service Bulletin release date (Basic Issue).

Discard the Basic Issue of this Service Bulletin dated Jul 14/2016 and replace in its entirety with this Revision 01.

Service Bulletin No. 700−53−6008 Date of Basic Issue Jul 14/2016 Revision No. Basic Dated Jul 14/2016 Revision No. 01 Dated Dec 16/2016 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. Add, in Paragraph 1.C., to spotface the sealant.

2. Add, in Paragraph 1.H., necessary tooling.

3. Revise, in Paragraph 1.K., Modsum R700T400609 to Rev F.

4. Revise, in Paragraph 1.K., Kit Drawing KGC991 –1473 to Rev F.

5. Revise, in Paragraph 2.B., steps (4) to (6), (8), (9) and (23).

6. Revise, in Paragraph 2.B., the order to accomplish some of the steps.

7. Revise drawing KGC991 –1473.

8. Make miscellaneous minor changes, as necessary, with no change of context.

SERVICE BULLETIN MODEL BD−700−1A10 (BD−700) 700−53−6008 Page 1 of 1

REVISION TRANSMITTAL SHEET

MODIFICATION — BELLY FAIRINGS —

REPLACEMENT OF ATTACHMENTS FOR THE ACCESS PANELS 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

RELIABILITY/DISPATCHABILITY/COST AVOIDANCE

COMPLIANCE TIME Not applicable EFFECTIVITY: A/C Serial No. 9313, 9381, 9432 to 9770 and 9772 to 9781 MANPOWER: 4 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 YES NO 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 53−61

FUSELAGE Basic Issue: Jul 14/2016 Revision 01: Dec 16/2016 700−53−6008 Page 1 of 1 This Service Bulletin is available at:

MODIFICATION — BELLY FAIRINGS —

REPLACEMENT OF ATTACHMENTS FOR THE ACCESS PANELS

1. PLANNING INFORMATION NOTE: This Service Bulletin is covered by a dedicated schedule. Dedicated schedules are used to reserve and manage inventory due to limited availability of rotable stock, parts and/or kits. Parts are limited, therefore, advance part scheduling with our In−Service Implementation Team (ISIT) is recommended prior to a maintenance visit. Please contact your Regional Manager (RM), Field Service Representative (FSR) or Customer Service Representative (CSR) to schedule your aircraft as there is a limited availability. The parts will be allocated on a first come first serve basis.

For more information on dedicated schedules, refer to SB 700−00−6002.

A. Effectivity BD−700−1A10 aircraft, Serial No. 9313, 9381, 9432 to 9770 and 9772 to 9781.

All other subsequent BD−700−1A10 aircraft are scheduled for the modification in production (Ref.: Modification Summaries 700T101073 and 700T810070).

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 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.

 2016 Bombardier Inc. All rights reserved Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.

Basic Issue: Jul 14/2016 Revision 01: Dec 16/2016 700−53−6008 Page 1 of 20 This Service Bulletin is available at:

B. Reason

1. Condition Some operators have reported losing belly fairings (185CL/186CR) in flight.

2. Evidence The fasteners may have been over torqued and cause damage to the access panels mounting holes. Fastener grip length may be too short and not fully engage in fastener receptacle. Fastener grip length may be too long and foul on the bottom of the receptacle. A build up of sealant in the fastener receptacle may also prevent fastener to fully engage in receptacle.

3. Objective/Benefit This Service Bulletin introduces new self−locking nutplates with associated hardware (retaining rings and studs). This will ensure that the fasteners are fully engaged. A bracket is also added to provide two additional attachments points to assure the belly fairings are safely secured, thus avoiding unexpected downtime and costly repairs.

C. Description This Service Bulletin gives instructions to:

− Remove the belly fairing access−panels (185CL/186CR), − Install the new bracket, − Drill holes at new attachment points in access−panels, − Remove and discard the existing receptacles, studs and retaining rings, − Install the new nutplates, − Replace the self−contouring sealing pad, − Spotface sealant, − Install the belly fairing access−panels (185CL/186CR) with the new studs and retaining rings, and − Do a check of the aerodynamic smoothness of the access panels.

D. Compliance Recommended − Reliability/Dispatchability/Cost Avoidance MODEL BD−700−1A10 (BD−700) Basic Issue: Jul 14/2016 Revision 01: Dec 16/2016 700−53−6008 Page 2 of 20

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.

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.

4 man−hours are necessary to do this modification.

The labor required to do 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 15 months from this Service Bulletin release date (Basic Issue).

G. Material − Cost and Availability Kit 700K53–6008A or 700K53–6008B is necessary to do this modification.

AIRCRAFT

EFFECTIVITY KIT NO. PRICE Aircraft Serial No. 9313 to 9530 700K53–6008A Please contact Bombardier Aerospace Parts Services, in Montreal, for delivery lead times and confirmation of prices.

Aircraft Serial No. 9532 to 9781 700K53–6008B MODEL BD−700−1A10 (BD−700) Basic Issue: Jul 14/2016 Revision 01: Dec 16/2016 700−53−6008 Page 3 of 20

In addition to the kits shown above, the parts in Paragraph 3 are necessary to do this modification.

This kit and parts are available at no cost if:

− a no−charge purchase order is sent to Bombardier Aerospace in less than 15 months from this Service Bulletin release date (Basic Issue).

This Service Bulletin is covered by a dedicated schedule. Dedicated schedules are used to reserve and manage inventory due to limited availability of rotable stock, parts and/or kits. Parts are limited, therefore, advance part scheduling with our In−Service Implementation Team (ISIT) is recommended prior to a maintenance visit. Please contact your Regional Manager (RM), Field Service Representative (FSR) or Customer Service Representative (CSR) to schedule your aircraft as there is a limited availability. The parts will be allocated on a first come first serve basis.

For more information on dedicated schedules, refer to SB 700−00−6002.

During or after the above free period, Smart Parts Plus does not pay for the kit or parts.

H. Tooling The equipment and tools listed below are necessary to do this modification:

GSE REFERENCE NO. PART NO. DESCRIPTION − − Roller − − Sealant Applicator − − Spot Face 0.375 in

(9.50 mm) − − Wrench, Torque 15 to 25 lbf in (1.70 to 2.83 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 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.

MODEL BD−700−1A10 (BD−700) Basic Issue: Jul 14/2016 Revision 01: Dec 16/2016 700−53−6008 Page 4 of 20

J. Electrical Load Data No change.

K. References − Bombardier Aerospace, Modification Summary, R700T400609, Rev. F.

− Bombardier Aerospace, Standard Practices Manual (SPM), Chapters 20 and 51.

− Bombardier Aerospace, Kit Drawing KGC991 –1473, Rev. F.

− Global 6000 BD−700 Aircraft Maintenance Manual (AMM), Chapters 6 and 53.

− Global 6000 BD−700 Structural Repair Manual (SRM), Chapter 51.

L. Other Publications Affected − Global 6000 BD−700 Aircraft Illustrated Parts Catalog (AIPC).

M. Equivalent Service Bulletin − For the Global Express and Global Express XRS BD−700−1A10 aircraft, use SB 700–53–050.

− For the Global 5000 BD−700−1A11 aircraft, use SB 700−1A11−53 –025.

− For the Global 5000 BD−700−1A11 Featuring Global Vision Flight Deck aircraft, use SB 700–53–5009.

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 None.

B. Modification

(1) Remove the aft access−panel (185CL). Refer to AMM 53−61−19−000−801.

NOTE: Do not remove the joint strap from access panel (186CR).

(2) Remove the aft access−panel (186CR). Refer to AMM 53−61−19−000−801.

(3) On FS813.00, remove the self−contouring sealing pad as required, to gain access to the rivets that will be removed. Refer to Kit Drawing KGC991–1473, Section C−C and Detail A. Refer to SPM−Maintenance Chapter 51–23–00.

MODEL BD−700−1A10 (BD−700) Basic Issue: Jul 14/2016 Revision 01: Dec 16/2016 700−53−6008 Page 5 of 20

(4) Remove the five rivets, on FS813.00, where the angle, Item 3, will be installed.

Refer to Kit Drawing KGC991–1473, Section B−B. Refer to SRM Chapter 51–42–08.

(5) If applicable, remove the two rivets on the lower flange at FS813.00, where the angle, Item 3, will be installed. Refer to Kit Drawing KGC991–1473, Section D−D and Detail A. Refer to SRM Chapter 51–42–08.

(6) Locate angle, Item 3, and pick up the existing holes from the structure. Refer to Kit Drawing KGC991–1473, Sections B−B and D−D.

(7) Drill the four holes for the rivets through the angle where the nutplates will be installed, and do the countersinks. Refer to SRM Chapter 51–40–08.

NOTES: 1. Do not install the nutplates at this moment.

2. Make sure the nutplates can be installed after the angle is attached to the structure.

(8) Install angle, Item 3, to frame with rivets, Item 9. Refer to Kit Drawing KGC991–1473, Section B−B. Refer to SRM Chapter 51–42–08.

(9) If removed, install two rivets, Item 11, through the lower flange and the bracket, Item 3. Refer to Kit Drawing KGC991–1473, Section D−D. Refer to SRM Chapter 51–42–08.

(10) Temporarily install access panel (185CL).

(11) Use angle, Item 3, and mark the location of the new fastener hole to be drilled on the access panel.

(12) Remove access panel (185CL).

(13) Temporarily install access panel (186CR).

(14) Use angle, Item 3, and mark the location of the new fastener hole to be drilled on the access panel.

(15) Remove access panel (186CR).

(16) Drill one hole diameter 0.1875 to 0.1905 in (4.763 to 4.838 mm) in each access panel (185CL/186CR) at the location of the new attachments.

(17) Countersink holes to 100°. Refer to SRM Chapter 51–40–08.

(18) Drill out the rivets, and remove and discard the eight receptacles, Part No.

B0209022–001, located at FS813.00. Refer to Kit Drawing KGC991–1473, Detail A (Pre−Mod) and to SRM Chapter 51–42–08.

NOTE: For aircraft Serial No. 9432 to 9530, the receptacles are mounted on a plate.

(19) Install the nutplates on angle, Item 3. Refer to Kit Drawing KGC991–1473 and to SRM Chapter 51–42–08.

NOTES: 1. For aircraft Serial No. 9313 to 9530, use Item 4 and Item 6.

2. For aircraft Serial No. 9532 to 9781, use Item 5 and Item 7.

MODEL BD−700−1A10 (BD−700) Basic Issue: Jul 14/2016 Revision 01: Dec 16/2016 700−53−6008 Page 6 of 20

(20) Install the nutplates on the frame at FS813.00. Refer to Kit Drawing KGC991–1473, Detail A (Post−Mod) and to SRM Chapter 51–42–08.

NOTES: 1. For aircraft Serial No. 9313 to 9530, use Item 4 and Item 6.

2. For aircraft Serial No. 9532 to 9781, use Item 5 and Item 7.

(21) Do touch−up on the rivets with primer and topcoat grey #16473. Refer to SRM Chapters 51–01–06 and 51–01–08.

(22) Remove and discard the four retaining rings, Part No. B0209020–001, and the four studs, Part No. B0209021–2S or B0209021–3S, from the fwd side of each access−panel (185CL/186CR).

(23) Install the new bolts, Part No. 121016–3–897, on the access panels and do one of the following:

(a) If the aircraft is down long enough for the self−contouring sealing pad to cure, do not install the new retaining rings at this moment and do the following steps:

(i) Replace the self−contouring sealing pad where it was removed on FS813.00. Refer to SPM−Maintenance Chapter 51–23–00.

NOTES: 1. Examine the self−contouring sealing pad on the fuselage structure for damage or deterioration. If necessary, replace the self−contouring sealing pad.

2. If applicable, fill the gap between the angle, Item 3, and the access panels with self−contouring sealant. Refer to Kit Drawing KGC991–1473, Section D−D.

3. Make sure the sealant does not enter the nutplates and receptacles.

(ii) Allow time for sealant to fully cure. Refer to SPM−Maintenance Chapter 51–23–00.

(iii) Remove access panels (185CL/186CR).

(iv) If the self−contouring sealing pad is less than 0.23 in (0.58 mm), install the retaining rings, Item 10, and continue to step (24).

(v) Spotface to remove a minimum of 0.023 in (0.58 mm) of sealant to allow clearance for retaining rings, Item 10. Refer to Kit Drawing KGC991–1473, Note 13.

(vi) If applicable, spotface a minimum of 0.025 in (0.63 mm) of Part No.

GD297–1707 and touch up reworked area as per SRM Chapter 51–01–04. Refer to Kit Drawing KGC991–1473, Note 14.

(vii) Install the retaining rings, Item 10.

(b) If the aircraft is not down long enough for the self−contouring sealing pad to cure, install the new retaining rings, Item 10.

MODEL BD−700−1A10 (BD−700) Basic Issue: Jul 14/2016 Revision 01: Dec 16/2016 700−53−6008 Page 7 of 20

(i) Replace the self−contouring sealing pad where it was removed on FS813.00. Refer to SPM−Maintenance Chapter 51–23–00.

NOTES: 1. Examine the self−contouring sealing pad on the fuselage structure for damage or deterioration. If necessary, replace the self−contouring sealing pad.

2. If applicable, fill the gap between the angle, Item 3, and the access panels with self−contouring sealant. Refer to Kit Drawing KGC991–1473, Section D−D.

3. Make sure the sealant does not enter the nutplates and receptacles.

(24) Examine the retainers and studs for good condition and make sure that there is no sealant inside the retainers and the studs.

(25) Make sure that the surfaces are clean with no corrosion, paint, grease, or preservation fluids.

(26) Install access panel (186CR). Refer to AMM 53−61−19−400−801.

(27) Install access panel (185CL). Refer to AMM 53−61−19−400−801.

(28) Torque the 10 bolts, Part No. 121016–3–897, on the forward side of the access panels, from 20 to 25 lbf in (2.26 to 2.83 Nm). Refer to SPM−Maintenance Chapter 20–21–00.

NOTE: For every 60th installation of the panel, install new nutplates. Refer to SRM Chapter 51–44–06.

(29) Torque the bolts on the rest of the access panels from 15 to 20 lbf in (1.70 to

2.26 Nm). Refer to SPM−Maintenance Chapter 20–21–00.

NOTE: For every 100th installation of the panel, install new receptacles.

Refer to SRM Chapter 51–44–06.

(30) Do a check of the aerodynamic smoothness of the access panels. Refer to SRM Chapter 51–14–04.

C. Close−out Remove all tools, equipment, and unwanted materials from the work area.

D. Recording When 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 MODEL BD−700−1A10 (BD−700) Basic Issue: Jul 14/2016 Revision 01: Dec 16/2016 700−53−6008 Page 8 of 20