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SPECIAL CHECK/MODIFICATION – AFT FUSELAGE SKIN AND ACCESS PANELS – INSPECT FOR MISSING RIVETS AT AFT FUSELAGE STRINGER 19 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. 70020 to 70039, 70041, 70046 and 70047 MANPOWER: 5 man−hours
CONTINUED AIRWORTHINESS (CAW)
FLEET CAMPAIGN YES NO
AIRWORTHINESS LIMITATIONS (AWL) NOYES KITS and/or PARTS YES NO
TOOLING/GSE YES NO
PLANNING INFORMATION NOYES
DEDICATED SCHEDULE NOYES PREREQUISITE SERVICE BULLETINS: NA 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−700−2A12 (BD−700) ATA 53−42
FUSELAGE Basic Issue: Jul 21/2021 700−53−7547 Page 1 of 1 This Service Bulletin is available at:
SPECIAL CHECK/MODIFICATION – AFT FUSELAGE SKIN AND ACCESS PANELS – INSPECT FOR MISSING RIVETS AT AFT FUSELAGE STRINGER 19
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. For any technical issues, contact CSE, Technical Support, Global Express by e−mail at SRPSA@aero.bombardier.com.
A. Effectivity BD−700−2A12 aircraft Serial No. 70020 to 70039, 70041, 70046 and 70047.
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. Condition:
In the aft fuselage LH panel assembly, three rivets are missing on stringer 19 attaching to skin between FS945.75 and FS961.45 (FWD engine mount frame).
Due to missing rivets, skin may be subjected to inter−rivet buckling condition repeatedly, resulting in visible aircraft damage.
2. Objective/Benefit:
The objective is to inspect for rivets, damages, do any repair if necessary, and if found missing rivets, install the rivets or fasteners attaching stringer 19 and skin between FS945.75 and FS961.45.
SERVICE BULLETIN my.businessaircraft.bombardier.com MODEL BD−700−2A12 (BD−700) ATA 53−42
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.
2021 Bombardier Inc. All rights reserved Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.
Basic Issue: Jul 21/2021 700−53−7547 Page 1 of 13 This Service Bulletin is available at:
C. Description This Service Bulletin gives instructions to:
− Get access to aft fuselage skin, − Inspect for missing rivets, − Inspect for damages, − Repair any damage if necessary, and − If necessary, install the rivets or fasteners.
D. Compliance Specified Time Compliance Recommended before 2,500 flight cycles or within 36 months 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.
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 700−00−7502.
2. 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.
5 man−hours are necessary to do this modification.
MODEL BD−700−2A12 (BD−700) Basic Issue: Jul 21/2021 700−53−7547 Page 2 of 13
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 2,500 flight cycles or within 36 months from its release date (Basic Issue).
G. Material − Cost and Availability No kits are necessary to do this modification. For material data, refer to Paragraph 3.
The parts in Paragraph 3.B. are necessary to do this modification.
The parts are available at no cost if:
− ordered during new aircraft warranty period, and − a no−charge purchase order is sent to Bombardier Aviation in less than 2,500 flight cycles or within 36 months from its release date (Basic Issue).
Smart Parts does not pay for this recommended Service Bulletin at any time.
H. Tooling The equipment and tool listed below is necessary to do this modification.
GSE REFERENCE NO. PART NO. DESCRIPTION Commercially Available − Torque Wrench NOTES: 1. Refer to the Global 7500 Illustrated Tool and Equipment Publication (ITEP) to make sure that you use the correct equipment configuration.
2. Refer to the Liability Statement in the ITEP for the G7500 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 AMP, WM, Chapter 20, then the tools called in the AMP, 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.
MODEL BD−700−2A12 (BD−700) Basic Issue: Jul 21/2021 700−53−7547 Page 3 of 13
K. References − Bombardier Aviation, Restriction and/or Special Instruction (RSI), C−70583, Rev. −−.
− Bombardier Aviation, Drawing G05360001, Rev. D.
− Bombardier Aviation, Drawing G05362000, Rev. AC.
− Global 7500 Aircraft Maintenance Publication (AMP), Chapters 12, 20, 24, 51, 52, and 53.
− Global 7500, Aircraft Structure Repair Publication (ASRP), Chapter 51.
L. Other Publications Affected None.
M. Equivalent Service Bulletins None.
2. ACCOMPLISHMENT INSTRUCTIONS NOTES: 1. All TASKs given in the procedures that follow are from the Global 7500 BD−700−2A12, Aircraft Maintenance Publication (AMP) unless otherwise specified.
2. All references made to zones, access panels and/or doors, are from the Global 7500 BD−700−2A12 Aircraft Maintenance Publication (AMP), Chapter 6.
A. Aircraft Setup
(1) Obey all electrical/electronic safety precautions. Refer to BD700−A−J24−00−00−00AAA−012A−A.
(2) Obey all oil−system safety precautions. Refer to BD700−A−J12−14−00−00AAA−012A−A.
(3) Open the aft equipment−compartment door (185KL). Refer to BD700−A−J52−41−01−00AAA−540A−A.
(4) Get access to aft fuselage skin at stringer 19 between FS945.75 and FS961.45. Refer to Figure 1.
B. Modification 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 get an approved disposition to complete this Service Bulletin.
MODEL BD−700−2A12 (BD−700) Basic Issue: Jul 21/2021 700−53−7547 Page 4 of 13
(1) Inspect for rivets, Part No. B0205020AD5−6S (qty 3) on the stringer 19, Part No. G05362149–101. The rivets are common to Outer Mold Line (OML) skin between FS945.75 and forward engine mount frame FS961.45.
(a) If the rivets, Part No. B0205020AD5−6S (qty 3), are installed, no further action is necessary. Go to Paragraph 2.D. (Close−out).
(b) If the rivets, Part No. B0205020AD5−6S (qty 3), are found missing, do the steps that follow.
(2) For general repair procedures, refer to ASRP BD700−A−J51−70−04−00AAA−663A−A.
(3) Do a detail visual inspection of the skin, Part No. G05362101−105, stringer 19, Part No. G05362149−101. Do a detail visual inspection of adjacent fasteners from inside and outside within 6.00 in. (152.40 mm) radius around missing rivets. Refer to Figure 1, Detail D and E.
NOTE: Use a magnifier and a flashlight as inspection aids.
(a) If damages are found, submit an SRPSA for analysis and request for disposition.
(4) Make sure that there are no deformation, gap between stringer and skin, cracks, lose or additional missing fasteners and other signs of damage.
(a) If damages are found, submit an SRPSA for analysis and request for disposition.
(b) If no damages are found, do step (5) for solution 1 or step (6) for solution 2.
(5) Install the rivets, Part No. B0205020AD5−6S (qty 3) per solution 1 as follow;
(a) Remove the aft fairing, Part No. G05384000−001 (185GB). Refer to BD700−A−J53−67−41−00AAA−520A−A.
(b) Install the rivets, Part No.B0205020AD5−6S (qty 3) per document listed in Paragraph 1.K. Refer to ASRP BD700−A−J51−42−08−00AAA−078A−A and Figure 1, Detail F.
(c) Install the aft fairing, Part No.G05384000−001 (185GB). Refer to BD700−A−J53−67−41−00AAA−720A−A.
(6) Install the fasteners per solution 2 as follows:
(a) Drill pilot holes at two places on stringer 19, Part No. G05362149−101, through skin, Part No. G05362101−105, and through aft fairing, Part No.
G05384000−001. Refer to Figure 1, Detail H. Drill from inside and make sure the minimum edge distance is achieved per ASRP BD700−A−J51−40−04−00AAA−078A−A.
NOTE: Make sure to protect skin with stainless plate between skin and fairing before trimming.
(b) Trim aft fairing, Part No. G05384000−001. Refer to ASRP BD700−A−J51−75−11−11AAA−659A−A and Figure 1, Detail J.
MODEL BD−700−2A12 (BD−700) Basic Issue: Jul 21/2021 700−53−7547 Page 5 of 13
(c) Do an inspection of the skin. If damages are found, submit an SRPSA for analysis and request for disposition.
(d) With sealant (06−002), wet install the bolts, Part No. B0206002AG5−3 (qty 2) and the nuts, Part No. B0203013−08 (qty 2). Refer to ASRP BD700−A−J51−42−36−00AAA−078A−A and AMP BD700−A−J51−23−13−00AAA−690B−A. Make sure the bolts head are outside and the nuts are inside. Refer to Figure 1, Detail K.
(e) Torque the nuts Part No. B0203013−08 (qty 2) from 15 to 25 lbf·in (1,70 to 2,82 Nm). Refer to BD700−A−J20−50−00−00AAA−711A−A.
(f) Touch up with primer (09−009) and apply top coat on the nuts, Part No.
B0203013−08 (qty 2). Refer to ASRP BD700−A−J51−01−06−00AAA−257A−A.
(g) Touch up with primer (09−009) and apply top coat on the bolts, Part No.
B0206002AG5−3 (qty 2). Refer to ASRP BD700−A−J51−01−06−00AAA−257A−A.
(h) Seal the trimmed edge of fairing by applying Hysol EA956 A/B and cure per manufacturer.
(i) Apply the sealant (06−001) for an aerodynamic seal to the aft fairing, Part No. G05384000−001. Refer to BD700−A−J51−23−37−00AAA−690B−A.
(j) Apply a layer of epoxy primer (09−009) on sealant and one layer of polyurethane top coat (09−143). Refer to ASRP BD700−A−J51−01−06−00AAA−257A−A and BD700−A−J51−01−08−00AAA−257A−A.
C. Testing No testing required.
D. Close−out
(1) Remove all tools, equipment and unwanted materials from the aircraft.
(2) Close the aft equipment−compartment door (185KL). Refer to BD700−A−J52−41−01−00AAA−740A−A.
E. Recording When this Service Bulletin is completed, make an entry in the aircraft log and send the attached Incorporation Notice to Bombardier Aviation Customer Services (BACS).
For information, corrections, comments and/or feedback regarding Service Bulletins released on the Customer Portal, please contact the Service Bulletin Group at the following email address:
bbad_SBgroup@aero.bombardier.com MODEL BD−700−2A12 (BD−700) Basic Issue: Jul 21/2021 700−53−7547 Page 6 of 13
3. MATERIAL INFORMATION A. Kit No kits required.
B. Parts The parts that follow are necessary to do this Service Bulletin and are available from Bombardier Aviation Parts Services, Montreal:
NEW PART NO. QTY ITEM USED PART NO.
INSTRUCTIONS
- DISPOSITION B0203013−08 (See Note 5) 2 NUT, SELF
LOCKING − − B0205020AD5−6S (See Note 4) 3 RIVET SOLID DOMED CSK HD − − B0206002AG5−3 (See Note 5) 2 BOLT, SHEAR,
FLUSH HD − − NOTES: 1. The part numbers for the items listed above are subject to change without revision to this Service Bulletin. In case of discrepancy between this list and any other list, the Illustrated Parts Data Publication prevails and shall be used to determine the latest part number.
2. Due to the lead−time for obtaining parts, operators are advised to order the parts six (6) weeks in advance before scheduling the incorporation of this Service Bulletin. Please contact Parts Services, in Montreal, for delivery lead times and confirmation of prices.
3. The actual quantity for some of the hardware contained in the kit can be greater than the amount shown in the table as these items are supplied in prepackaged quantities.
4. Rivets are necessary for solution 1.
5. Fasteners are necessary for solution 2.
C. Material The materials that follow, or equivalent, are necessary to do this Service Bulletin.
These can be purchased from a local supplier. Bombardier Aviation does not pay for these consumables.
MODEL BD−700−2A12 (BD−700) Basic Issue: Jul 21/2021 700−53−7547 Page 7 of 13
DESCRIPTION PARTNO./NAME SPECIFICATION QUANTITY SUPPLIER Cleaning Solvent (DS−108) (07−002) − As Necessary Code: A Epoxy primer, green 44GN072 (Base) / 44GN072CAT (Catalyst) (09−009) (See Note 3) BAMS 565−001 GR B, CAT 2, TY 2 As Necessary Code: A Sealant Pro−Seal 870 B (06−002) (See Note 3) MIL−PRF−81733 TYPE IV, CL 1, GR A As Necessary Code: A Sealant Pro−Seal 870 C (06−001) (See Note 3) MIL−PRF−81733 TYPE II, CL 1, GR A As Necessary Code: A Enamel coating PG−21 series (base) / PH−63 (hardener) (09−143) (See Note 3) BAMS 565−002, CLASS 20 OR 33 As Necessary Code: B Adhesive, Epoxy Loctite EA 956 Aero Hysol EA 956 A/B As Necessary Code: C Wiper Cloth (05−442)(See Note 3) − As Necessary Code: D NOTES: 1. Refer to the table that follows for each suppliers address listed by codes.
2. 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.
3. Refer to PART No.s listed in AMP BD700−A−J51−31−00−00AAA−070A−A for details.
MODEL BD−700−2A12 (BD−700) Basic Issue: Jul 21/2021 700−53−7547 Page 8 of 13
SUPPLIERS ADDRESSES BY CODES Code: A PRC−Desoto International 5676 Timberlea Blvd.
Mississauga, Ontario Canada, L4W 4M6 Tel.: (905) 629−7999 Fax.: (905) 629−7009 www.ppgaerospace.com Code: B Hentzen Coatings, Inc 6937 W mil Rd Milwaukee WI − 53218−1225 United States www.hentzen.com Code: C Henkel Corporation Aerospace 2850 Willow Pass Road P. O. Box 312 Bay Point, CA 94565 USA Tel.: 925.458.8000 Fax: 925.458.8030 www.henkel−adhesives.com Code: D Commercially Available D. Publications None.
MODEL BD−700−2A12 (BD−700) Basic Issue: Jul 21/2021 700−53−7547 Page 9 of 13
C A STR20L FS833.00 STR6L FS1016.66 STR19L A FWD B C FS961.45 FS945.75 SB700−53−7547_001 FS961.45 FS945.75 STR19L B0205020AD5−6S (MISSING RIVETS) G05362000−003 (AFT FUSELAGE
PANEL ASSEMBLY) B FS961.45 FS945.75 FWD F D EG H MODEL BD−700−2A12 (BD−700) Installation of Rivets and Fasteners on STR 19L between FS945.75 and FS961.45 Figure 1 (Sheet 1 of 4) Basic Issue: Jul 21/2021 700−53−7547 Page 10 of 13
SB700−53−7547_002 K FS961.45 FS945.75 STR19L
6.00 in
(152.40 mm) FS945.75 FS961.45 STR19L
6.00 in
(152.40 mm) FS945.75 FS961.45 STR19L B0205020AD5−6S (MISSING RIVETS) G05362000 (AFT FUSELAGE
PANEL ASSEMBLY) G05384000 (AFT FAIRING
ASSEMBLY) FS961.45 FS945.75 STR19L G05362000−003 (AFT FUSELAGE
PANEL ASSEMBLY) D F E G J B0205020AD5−6S (RIVETS) (QTY 3) MODEL BD−700−2A12 (BD−700) Installation of Rivets and Fasteners on STR 19L between FS945.75 and FS961.45 Figure 1 (Sheet 2 of 4) Basic Issue: Jul 21/2021 700−53−7547 Page 11 of 13