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Discard the Basic Issue of this Service Bulletin dated Oct 04/2022, and replace in its entirety with this Revision 01.
Service Bulletin No. 700−27−6509 Date of Basic Issue Oct 04/2022 Revision No. 01 Dated May 05/2023 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., the Planning Information Note 3 and 4.
2. Change, in Paragraph 1.A., to revise the effectivity.
3. Change, in Paragraph 1.K., to revise the Modsum R700T400776 to Rev. B3.
4. Change, in Paragraph 1.K., to revise the Kit Drawing KGC991−1671 to Rev. B.
5. Change, in Paragraph 2.C., to delete Step (10).(a), and Step 19 as it is redundant.
6. Change, in Paragraph 2.C., to revise Steps (11).(a).(ii)., (15).(b)., (17).(b)., (27).(g).(ii).,
(27).(m)., and (28).(d).
7. Change, in Paragraph 2.C., to revise Step (30).(a)., and add a Note.
8. Change, in Paragraph 2.C., to add Step (34).
9. Revise Figure 10, to remove the laminated shim in Sheet 1.
10.Make miscellaneous minor changes, as necessary, with no change of context.
SERVICE BULLETIN MODEL BD−700−1A10 (BD−700) 700−27−6509 Page 1 of 1
REVISION TRANSMITTAL SHEET
SPECIAL CHECK/MODIFICATION – FLAP SYSTEM –
INSTALLATION OF IMPROVED INBOARD FLAP SEAL PLATE 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: Refer to Paragraph 1.A.
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 NOYES
DEDICATED SCHEDULE YES NO PREREQUISITE SERVICE BULLETINS: N/A NOTE: This Service Bulletin may be subjected to an Airworthiness Directive which will make it necessary to implement this Service Bulletin.
To place an order for kit, 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 27−52
FLIGHT CONTROLS Basic Issue: Oct 04/2022 Revision 01: May 05/2023 700−27−6509 Page 1 of 1 This Service Bulletin is available at:
SPECIAL CHECK/MODIFICATION – FLAP SYSTEM –
INSTALLATION OF IMPROVED INBOARD FLAP SEAL PLATE
1. PLANNING INFORMATION NOTES:1 . Before you do this Service Bulletin, examine all STC, STA or equivalent action changes to make sure that this Service Bulletin can be completed.
2. 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. They can be reached at bacs_isit@aero.bombardier.com. The parts will be allocated on a first come first serve basis.
Should you require additional information, please contact your Regional Sales Manager (RM) or Field Service Representative (FSR).
For more information on dedicated schedules, refer to SB 700−00−6502.
3. Aircraft must be de−fueled to proceed with the inner flap seal plate rigging upon re−installation of the seal plate. Operators are advised to make necessary planning for de−fueling.
4. Kits 700K27−6509A or 700K27−6509B is required to do this Service Bulletin. While both kits 700K27−6509A and 700K27−6509B are equivalent and can be used to accomplish this Service Bulletin, kit 700K27−6509B consist of improved version alleviating the need for trimming operation. Kit 700K27−6509B also include all required hardware with extra quantities to ensure straightforward installation as opposed to kit 700K27−6509A that only include the non standard hardware.
SERVICE BULLETIN my.businessaircraft.bombardier.com MODEL BD−700−1A10 (BD−700) ATA 27−52
FLIGHT CONTROLS 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.
2022−2023 Bombardier Inc. All rights reserved Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.
Basic Issue: Oct 04/2022 Revision 01: May 05/2023 700−27−6509 Page 1 of 31 This Service Bulletin is available at:
A. Effectivity BD−700−1A10 aircraft, Serial No. 9861, 9872, 60001 to 60101.
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).
The intent of this Service Bulletin was met on the aircraft that follow with the Pre−Published Service Bulletin 700−27−6509 listed below:
AIRCRAFT SERIAL NO. PRE_PUBLISED DATE 60077 Aug 20/2022 B. Reason
1. Condition:
There have been reports of cracked inner flap seal plate attachment angles which could allow the seal plate to detach.
2. Objective/Benefit:
This Service Bulletin instructs to replace both (LHS and RHS) existing inner flap seal plate assembly with an improved one.
C. Description This Service Bulletin gives instructions in PART A to:
− Get access to the inner flap seal plate, − Inspect the seal plate assembly for cracks,
(i) If cracks are found, do PART B of this Service Bulletin, or contact Bombardier via SRPSA for alternative solution.
(ii) If no cracks are found, operators may defer retrofit up to 18 months with repeat inspections every 250 flight hours (or) do PART B of this Service Bulletin.
This Service Bulletin gives instructions in PART B to:
− Install the new inner flap seal plate assembly.
D. Compliance Recommended to inspect within 250 flight hours from this Service Bulletin release date (Basic Issue).
However for the aircraft with more than 750 flight hours from this Service Bulletin release date (Basic Issue), must do the initial inspection within 100 flight hours.
MODEL BD−700−1A10 (BD−700) Basic Issue: Oct 04/2022 Revision 01: May 05/2023 700−27−6509 Page 2 of 31
During inspection, if cracks are found in the inner flap seal plate, improved assembly should be installed per PART B. If it is not possible, alternative repair solution can be provided via SRPSA.
If no cracks are found during inspection, operator may defer installation of improved assembly (PART B) up to 18 months from this Service Bulletin release date (Basic Issue), with repeat inspections every 250 flight hours.
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. Standard SRPSA fees may apply. Refer to the Services section of the Bombardier customer portal for the latest prices, rates and fees.
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.
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 labor man−hours 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 on LHS and RHS.
23 man−hours are necessary to do PART B of this Service Bulletin.
Bombardier Aviation does not pay for the labor to do PART A 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 MODEL BD−700−1A10 (BD−700) Basic Issue: Oct 04/2022 Revision 01: May 05/2023 700−27−6509 Page 3 of 31
− this Service Bulletin is scheduled within 18 months from this Service Bulletin release date (Basic Issue).
G. Material − Cost and Availability Kit 700K27−6509A (or) 700K27−6509B is necessary to do PART B of this Service Bulletin. For material data, refer to Paragraph 3.C.
KIT NO. PRICE 700K27−6509A (OR) 700K27−6509B Please contact Bombardier Aviation Parts Services, in Montreal, for delivery lead times and confirmation of prices.
The kit is available at no cost if:
− a no−charge purchase order is sent to Bombardier Aviation within 18 months from this Service Bulletin release date (Basic Issue).
Smart Parts does not pay for this recommended Service Bulletin at any time.
H. Tooling The equipment and tools listed below are necessary to do this modification.
GSE REFERENCE NO. PART NO. DESCRIPTION 20X−10−01 − Tag, Circuit Breaker (Red Ring) Commercially Available − Grip Measurement Gauge Commercially Available − NAS1789 Nut Plate Drill Jig Commercially Available − Rivet Installation Tools Commercially Available − Torque Wrench NOTES: 1. Refer to the Global 6500 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 Global 6500 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.
MODEL BD−700−1A10 (BD−700) Basic Issue: Oct 04/2022 Revision 01: May 05/2023 700−27−6509 Page 4 of 31
I. Weight and Balance
WEIGHT MOMENT +1.62 lbs (0.74 kg) 1255.8 lbs−in (14.47 kgm) J. Electrical Load Data No change.
K. References − TCCA Airworthiness Directive, (pending).
− Bombardier Aviation, Modification Summary R700T400776, Rev. B3 .
− Bombardier Aviation, Kit Drawing KGC991−1671, Rev. B .
− Global 6500 BD−700 Aircraft Maintenance Manual (AMM), Chapters 6, 20, 24 and 27.
− Global 6500 BD−700 Aircraft Illustrated Parts Catalog (AIPC), Chapter 27.
− Global 6500 BD−700 Structural Repair Manual (SRM), Chapter 51.
− Bombardier Aviation, Standard Practices Manual (SPM), Chapters 20 and 51.
L. Other Publications Affected − Global 6500 BD−700 Aircraft Maintenance Manual (AMM), Chapter 27.
− Global 6500 BD−700 Aircraft Illustrated Parts Catalog (AIPC), Chapter 27.
M. Equivalent Service Bulletin − For the Global 5500 BD−700−1A11 aircraft, use SB 700−27−5509.
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
(1) Obey all electrical/electronic safety precautions. Refer to AMM 24−00−00−910−801.
(2) Obey all flight control safety precautions. Refer to AMM 27−00−00−910−801.
(3) Connect electrical power to the aircraft. Refer to AMM 24−00−00−861−801.
(4) Set the SLAT/FLAP control lever to OUT/30°.
MODEL BD−700−1A10 (BD−700) Basic Issue: Oct 04/2022 Revision 01: May 05/2023 700−27−6509 Page 5 of 31
(5) Remove the electrical power from the aircraft. Refer to AMM 24−00−00−861−802.
(6) In the flight compartment, on the EMS CDU, set the circuit breaker that follows to LOCKED. Refer to AMM 24−00−00−863−801.
For the left inner flap panel:
SYSTEM NAME CIRCUIT BREAKER NAME BUS NAME FLT CONTROLS SLAT/FLAP CTLR 1 BATT For the right inner flap panel:
SYSTEM NAME CIRCUIT BREAKER NAME BUS NAME FLT CONTROLS SLAT/FLAP CTLR 2 DC ESS
(7) Open and tag the circuit breaker that follows:
For the left inner flap panel:
LOCATION CB NO. NAME ZONE CCBP G9 SLAT/FLAP PWR 1 222 For the right inner flap panel:
LOCATION CB NO. NAME ZONE CCBP E2 SLAT/FLAP PWR 2 222 B. PART A — Inspection of Inboard Flap Seal Plate 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.
Do the procedure that follows for the LHS and RHS flap.
(1) Inspect the stiffeners, Part No. GM147−2355−1/−2, for cracks. Refer to Figure 1.
MODEL BD−700−1A10 (BD−700) Basic Issue: Oct 04/2022 Revision 01: May 05/2023 700−27−6509 Page 6 of 31
(2) Do a Detail Visual Inspection (DVI) of inner flap seal plate assembly attaching angles (GM147−2355−1/−2, GM147−2355−3/−4 and GM147−2352) to make sure that there is no visual crack. Refer to Figure 1.
NOTE: Any other type of damage would consist of valid findings and should be reported to Bombardier for further advise.
(a) If cracks are found, do as follows:
(i) Do PART B of this Service Bulletin, or
(ii) Contact Bombardier via SRPSA to get an alternative repair solution.
(b) If no cracks are found, do as follows:
(i) Operators may defer PART B up to 18 months from this Service Bulletin release date (Basic Issue), with repeat inspections every 250 flight hours, or
(ii) Do PART B of this Service Bulletin.
SB700−27−6509_023 Inspection of Inner Flap Seal Plate Assembly Figure 1 MODEL BD−700−1A10 (BD−700) Basic Issue: Oct 04/2022 Revision 01: May 05/2023 700−27−6509 Page 7 of 31
C. PART B — Replacement of Inboard Flap Seal Plate NOTES: 1. 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.
2. Touch−up all the fasteners per finish code X186. Refer to SRM 51−01−04.
Do the procedure that follows on the LHS flap.
(1) Remove and retain the existing inner flap seal plate. Refer to AMM 27−52−17−000−801.
(2) Remove and discard the stiffeners, Part No. GM147−2355−1/−2. Refer to Figure 2.
(3) Remove the P−seal, Part No. GM147−2529, from the trailing edge of end rib as follows. Refer to Figure 2.
(a) Remove the nuts, Part No. NAS1291C08M (qty 12), washers, Part No. NAS1149CN816R (qty 11), filler, Part No. GM148−3001−21, screws, Part No. NAS1102V08−8 (qty 12), shims, Part No. S5324−63−90−296 (Qty 2), laminated shims, Part No. S10249−63−0−296 (Qty 1), and the P−seal, Part No. GM147−2529.
(b) Retain the filler, Part No. GM148−3001−21, shims, Part No. S5324−63−90−296 (Qty 2), laminated shims, Part No. S10249−63−0−296 (Qty 1), and the P−seal, Part No. GM147−2529.
(c) Discard the nuts, Part No. NAS1291C08M (qty 12), washers, Part No. NAS1149CN816R (qty 11), and the screws, Part No. NAS1102V08−8 (qty 12).
(4) Remove and discard the clip assembly, Part No. GM141−3331, and the attaching screws, Part No. NAS1580V3T4 (qty 4), from the trailing edge of end rib. Refer to Figure 2.
(5) Remove the sealant residues from both upper and lower areas of the trailing edge of end rib. Refer to SPM−MM 51−23−00−100−801 and Figure 2.
MODEL BD−700−1A10 (BD−700) Basic Issue: Oct 04/2022 Revision 01: May 05/2023 700−27−6509 Page 8 of 31
SB700−27−6509_021 NOTE 1 Retain for re−use.
1 1 Figure 2
(6) Do a Detail Visual Inspection (DVI) of flap inboard closing rib and trailing edge for damage.
(7) Perform an Eddy Current Inspection of flap inboard closing rib holes (qty 6) common to the OUTBD stiffener, Part No. GM147−2355−1/−2, and angle, Part No. GM147−2352 per NDTM Part 1 Section 6E to make sure no cracks are running out of rib holes. It is acceptable to use Liquid Penetrant Inspection per NDTM Part 1 Section 8 in lieu of Eddy Current Inspection. Refer to Figure 3.
(8) If any damages are found in the inspection, contact Bombardier via SRPSA for alternative solution.
MODEL BD−700−1A10 (BD−700) Basic Issue: Oct 04/2022 Revision 01: May 05/2023 700−27−6509 Page 9 of 31
RIB HOLES (QTY 6)
FLAP CLOSING INBOARD RIB SB700−27−6509_022 Inspection of Inboard Flap Closing Rib Figure 3
(9) Position the bracket assembly, Part No. KGC991−1675. Refer to Figure 10, Detail B and D.
(10) Attach OUTBD stiffener, Part No. KGC991−1672, to the flap end rib with screws, Part No. MS27039−1−10 (qty 2) and washers, Part No. B0202013−1328−32 (qty 2). Refer to Figure 4 and Figure 10, Detail B.
(a) Make sure that the OUTBD stiffener, Part No. KGC991−1672, is positioned parallel to the lower surface of the flap.
(b) Hand tighten the screws, Part No. MS27039−1−10 (qty 2).
MODEL BD−700−1A10 (BD−700) Basic Issue: Oct 04/2022 Revision 01: May 05/2023 700−27−6509 Page 10 of 31