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MODIFICATION - EQUIPMENT RACKS - MODIFICATION OF THE LEFT AND THE
RIGHT EQUIPMENT RACKS 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 96 months from this Service Bulletin release date (Basic Issue) EFFECTIVITY: A/C Serial No. 20003 to 20500 MANPOWER: 5 man−hours for each PART (PARTS A and B)
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−100−1A10 (CH−300) ATA 25−72
EQUIPMENT/FURNISHINGS Basic Issue: Oct 26/2015 100−25−39 Page 1 of 1 This Service Bulletin is available at:
MODIFICATION - EQUIPMENT RACKS - MODIFICATION OF THE LEFT AND THE
RIGHT EQUIPMENT RACKS
1. PLANNING INFORMATION NOTE: It is recommended to do this modification at the 96−month inspection.
A. Effectivity BD−100−1A10 aircraft, Serial No. 20003 to 20500.
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 It was found that the Secondary Power Center (SPC) is heavier than designed. This can cause stress on the equipment rack structure.
This Service Bulletin installs a doubler on the structure of the rack, which increases the strength of the structure to sustain the increased structural load of the heavier SPC.
C. Description This Service Bulletin gives instructions in PART A to:
− Install doubler and packers on the left equipment rack.
SERVICE BULLETIN www.cic.bombardier.com MODEL BD−100−1A10 (CH−300) ATA 25−72
EQUIPMENT/FURNISHINGS 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.
2015 Bombardier Inc. All rights reserved Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.
Basic Issue: Oct 26/2015 100−25−39 Page 1 of 22 This Service Bulletin is available at:
This Service Bulletin gives instructions in PART B to:
− Install doubler and packers on the right equipment rack.
D. Compliance Recommended in less than 96 months 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.
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 100−00−02.
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.
3. Labor hours are based on the fact that the modification will be done at the next 96−month inspection or next earlier access. Therefore no man−hours are allotted to prepare the aircraft for maintenance, to prepare for this Service Bulletin or access other than the one specified in this Service Bulletin.
5 man−hours are necessary to do each PART of 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 MODEL BD−100−1A10 (CH−300) Basic Issue: Oct 26/2015 100−25−39 Page 2 of 22
− this Service Bulletin is done at the next 96−month inspection or next earlier access.
NOTE: No labor hours will be covered for access (i.e interior removal/installation) based on the fact that the modification will be done at the next 96−month inspection or next earlier access.
G. Material − Cost and Availability Kit 100K25−39 is necessary to do PART A of this modification and Kit 100K25−39A is necessary to do PART B of this modification .
KIT NO. PRICE 100K25−39 Please contact Bombardier Aerospace Parts Services, in Montreal, for delivery lead times and confirmation of prices.100K25−39A These kits are available at no cost, if a no−charge purchase order is sent to Bombardier Aerospace in less than 96−months 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 Commercially Available − Wrench, Torque NOTES: 1. Refer to the CH300 BD−100 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 acceptable GSE equivalents.
I. Weight and Balance
PART WEIGHT MOMENT A +0.104 pound (+0.047kg) +35.75 pound−inches(+0.41 kgm) B +0.123 pound (+0.056kg) +42.28 pound−inches(+0.49 kgm) MODEL BD−100−1A10 (CH−300) Basic Issue: Oct 26/2015 100−25−39 Page 3 of 22
J. Electrical Load Data No change.
K. References − Bombardier Aerospace, Restriction and/or Special Instruction (RSI), C−100−000−25−0029, Rev. −−.
− Bombardier Aerospace, Modification Summary, BB100T010755, Rev. C.
− Bombardier Aerospace, Standard Practices Manual (SPM), Chapters 20 and 51.
− Bombardier Aerospace, Kit Drawing K1000070316, Rev. A.
− Bombardier Aerospace, SB 100−00−02, Service Bulletin Description and Policy.
− CH300 BD−100 Aircraft Maintenance Manual (AMM), Chapters 6, 21, 24 and
25.
− CH300 BD−100 Structural Repair Manual (SRM), Chapter 51.
L. Other Publications Affected None.
M. Equivalent Service Bulletin For the Challenger 350 aircraft, use SB 350−25−002.
2. ACCOMPLISHMENT INSTRUCTIONS NOTE: All references made to zones, access panels and/or doors, are from the BD−100 AMM, Chapter 6.
A. Aircraft Setup
(1) Obey all electrical/electronic safety precautions. Refer to AMM 24−00−00−910−801.
(2) Remove the electrical power from the aircraft AMM 24−00−00−861−802.
(3) For PART A (left side), do the steps that follow:
(a) Remove the access panels that follows. Refer to AMM 25−72−01−000−803:
(i) 221AZ
(ii) 221BZ
(b) Remove part of the tape and lift the drip tray away from the work area.
(c) Remove the ground stud and washers, and disconnect the bonding jumper.
MODEL BD−100−1A10 (CH−300) Basic Issue: Oct 26/2015 100−25−39 Page 4 of 22
(d) Remove the harnesses from the attachment point, and keep hardware for later installation.
(e) Remove any insulation blanket to get access as required. Refer to AMM 25−80−21−000−801.
(f) Remove the screw, Part No. NAS6604−4 (10), NAS6604−3 (1) and NAS1297−4−3 (3), washers, Part No. MS21299C4 (9) and (2), U312−0130−S (4), B0202013S2118−32 (5) and B0202013S2118−60 (6), and remove the fittings 1005336308−007 (8) and the plate 1005331423−011 (7). Refer to Figure 1.
(g) Remove the upper landing, Part No. 1005331425 as follow. Refer to Figure 2.
(i) Remove the bottom rivets. Refer to SRM 51−42−08.
(ii) Remove the three screw, Part No. NAS1801−3−5 (1) and washers Part No. NAS1149D0332K (2).
(iii) Remove the upper landing.
(4) For PART B (right side), do the steps that follow:
(a) Remove the access panels that follows. Refer to AMM 25−72−01−000−803.
(i) 222AZ
(ii) 222BZ
(b) Remove the bolts, Part No. NAS6604−4 (10), NAS6604−3 (1) and NAS1297−4−3 (3), washers, Part No. MS21299C4 (9) and (2), U312−0130−S (4), B0202013S2118−32 (5) and B0202013S2118−60 (6), and remove the fittings 1005336308−007 (6) and the plate 1005331412−003 (7). Refer to Figure 1.
(c) Remove the bolts, Part No NAS1801−3−9 (1) and the washers, Part No.
NAS1149D0332J (2), and remove the clamps, Part No. MS21919WDG14
(4). Move the flight−compartment gasper feed duct (4) away from the work area. Refer to Figure 3.
(d) Remove the nut and washers, and disconnect the bonding jumper.
(e) Remove part of the tape and lift the drip tray away from the work area.
(f) Remove the harnesses from the attachment point, and keep hardware for later installation.
(g) Remove any insulation blanket to get access as required. Refer to AMM 25−80−21−000−801.
(5) Make sure to protect all electrical/electronic equipment and wiring from debris.
B. PART A − Left Rack Modification
(1) Remove the rivets (12), and remove the stand−off lug (11). Refer to Figure 1.
(2) Remove the hi−lites that attach angle Part no. 1005336361−011 to aft sidewall.
Refer to SRM 51−42−36 and drawing K1000070316, Sheet 1, Pre−Mod view.
MODEL BD−100−1A10 (CH−300) Basic Issue: Oct 26/2015 100−25−39 Page 5 of 22
(3) Put the packers Part No. K1000070316−005 and K1000070316−006, and the doubler Part No. K1005336304−001 in position with clamps. Refer to drawing K1000070316, Sheet 1, View D.
(4) Make sure you have correct edge distance, and a minimum of 0.19 in (4.83 mm) at both end.
(5) Backdrill seven holes from the doubler to the top of the machined sidewall, to a diameter of 0.160 to 0.164 in (4.06 to 4.17 mm). Refer to drawing K1000070316, Sheet 1,View E.
(6) Backdrill two holes from the upper angle and the machined sidewall through the doubler and the packer, to a diameter of 0.159 to 0.162 in (4.039 to 4.115 mm). Refer to drawing K1000070316, Sheet 1,View E.
(7) Backdrill two holes from the machined sidewall and angle through the packers and the doubler, to a diameter of 0.159 to 0.162 in (4.039 to 4.115 mm). Refer to drawing K1000070316, Sheet 1,View F.
(8) Backdrill four holes from the doubler through the machined sidewall to a diameter of 0.159 to 0.162 in (4.039 to 4.115 mm). Refer to drawing K1000070316, Sheet 1,View F.
(9) Remove the doubler and the packers.
(10) Countersink the seven holes in the doubler for installation of rivets B0205018AD5. Refer to drawing K1000070316, page 1,View E.
(11) Remove burrs and sharp edges.
(12) Touch up holes with chemical conversion coating.
(13) Install doubler and packers on the machine sidewall and angle with rivets Part No. MS20470AD5−6A, B0205018AD5−5S, and hi−lites B02060001AG5−4 with collars B0203013−08. Refer to drawing K1000070316, page 1 view E and F, SRM 51−42−36, and SRM 51−42−08.
(14) Install the removed stand−off lug (11) with the rivets, Part no.
B0205018AD4−5S (12). Refer to Figure 1.
(15) Touch up fastener heads with primer and topcoat, finish code X186. Refer to SRM 51−01−04.
C. PART B − Right Rack Modification
(1) Remove the rivets (12), and remove the stand−off lug (11). Refer to Figure 1.
(2) Remove the hi−lites that attach angle Part No. 1005336361−011 to aft sidewall. Refer to SRM 51−42−36 and drawing K1000070316, page 1, Pre−Mod view.
(3) Remove the blind ground stud.
NOTE: Make sure to remove the sleeve. Final diameter of the hole is 0.312 in. (7.92 mm).
(4) Put the packers Part No. K1000070316−005 and K1000070316−006, and the doubler Part No. K1005336304−002 in position with clamps. Refer to drawing K1000070316, Sheet 2, Detail J.
MODEL BD−100−1A10 (CH−300) Basic Issue: Oct 26/2015 100−25−39 Page 6 of 22
(5) Make sure you have correct edge distance, and a minimum of 0.19 in (4.83 mm) at both end.
(6) Backdrill six holes from the doubler to the top of the machined sidewall, to a diameter of 0.160 to 0.164 in (4.06 to 4.17 mm). Refer to drawing K1000070316, Sheet 2,View H.
(7) Backdrill two holes from the top of the machined sidewall and upper angle through the doubler and the packer, to a diameter of 0.1590 to 0.1620 in.
(4.039 to 4.115 mm). Refer to drawing K1000070316, Sheet 2,View H.
(8) Backdrill two holes from the machined sidewall and upper angle through the packer and the doubler, to a diameter of 0.1590 to 0.1620 in (4.039 to 4.115 mm). Refer to drawing K1000070316, Sheet 2,View G.
(9) Backdrill four holes from the doubler through the machined sidewall to a diameter of 0.160 to 0.164 in (4.06 to 4.17 mm). Refer to drawing K1000070316, Sheet 2,View G.
(10) Drill hole for ground in the middle of the previous hole for ground in the machined sidewall through the doubler to a diameter of 0.189 to 0.192 in (4.81 to 4.87 mm).
(11) Remove the doubler and the packers.
(12) Countersink the six holes in the doubler for installation of rivets B0205018AD5.
Refer to drawing K1000070316, Sheet 2,View H.
(13) Remove burrs and sharp edges.
(14) Touch up holes (except the hole for the ground) with chemical conversion coating.
(15) Install doubler and packers on the machine sidewall and angle with rivets Part No. MS20470AD5−6A, B0205018AD5−5S, and hi−lites B02060001AG5−4 with collars B0203013−08. Refer to drawing K1000070316, Sheet 2, views G and H, SRM 51−42−36, and SRM 51−42−08.
(16) Install the removed stand−off lug (11) with the rivets, Part no.
B0205018AD4−5S (12). Refer to Figure 1.
(17) Touch up fastener heads with primer and topcoat, finish code X186. Refer to SRM 51−01−04.
(18) Prepare the surface around the hole for ground return. Refer to SPM−MM 51−80−00−140−801.
(19) Install the screw Part No. MS35207−266, the lockwasher Part No.
MS35338−43, the washers Part No. NAS1149D0332J and B0202013S1320−63, and the nut MS35650−302 and connect the bonding strap. Refer to SPM−MM 51−80−00−400−801. Torque the nut from 16 to 22 lbf in (1.81 to 2.48 Nm).
D. Close−out
(1) Remove all tools, equipment and unwanted materials from the aircraft.
(2) For PART A (left side), do the steps that follow:
MODEL BD−100−1A10 (CH−300) Basic Issue: Oct 26/2015 100−25−39 Page 7 of 22
(a) Install the fittings 1005336308−007 (8) and the plate 1005331423−011 (7) with the bolts, Part No. NAS6604−4 (10), NAS6604−3 (1) and NAS1297−4−3 (3), washers, Part No. MS21299C4 (9) and (2), U312−0130−S (4), B0202013S2118−32 (5) and B0202013S2118−60 (6).
Torque the bolts (10) and (11) from 70 to 90 lbf in (7.91 to 10.16 Nm) and the bolt (3) from 50 to 70 lbf in (5.65 to 7.90 Nm). Refer to Figure 1.
(b) Install the drip tray with tape.
NOTE: It is permissible to have a gap under the drip tray. It is also permissible to cold work the drip tray. Refer to Note 11 and SRM 51−28−32.
(c) Install the upper landing, Part No. 1005331425 as follow. Refer to Figure
2.
(i) Put the upper landing in position.
(ii) Install the three screws, Part No. NAS1801−3−5 (1) with washers, Part No. NAS1149D0332K (2). Torque the screws to 12 to 15 lbf in
(1.36 to 1.69 Nm).
(iii) Install the bottom rivets, Part No. MS20470AD4−4A and B0205018AD3−4S. Refer to SRM 51−42−08.
(iv) Apply fillet seal between the upper landing and the frame. Refer to SPM−MM 51−23−00−390−805.
(d) Install the harnesses to their attachment points, with kept hardware.
(e) Install any insulation blanket removed to get access. Refer to AMM 25−80−21−400−801.
(f) Install the access panels that follows. Refer to AMM 25−72−01−400−803:
(i) 221AZ
(ii) 221BZ
(3) For PART B (right side), do the steps that follow:
(a) Install the fittings 1005336308−007 (8) and the plate 1005331412−003 (7) with the bolts, Part No. NAS6604−4 (10), NAS6604−3 (1) and NAS1297−4−3 (3), washers, Part No. MS21299C4 (9) and (2), U312−0130−S (4), B0202013S2118−32 (5) and B0202013S2118−60 (6).
Torque the bolts (10) and (1) from 70 to 90 lbf in (7.91 to 10.16 Nm) and the bolt (3) from 50 to 70 lbf in (5.65 to 7.90 Nm). Refer to Figure 1.
(b) Install the drip tray with tape.
NOTE: It is permissible to have a gap under the drip tray. It is also permissible to cold work the drip tray. Refer to note 11 and SRM 51−28−32.
(c) Put the flight−compartment gasper feed duct (4) back in position with the clamps, Part No. MS21919WDG14 (3), the screw, Part No NAS1801−3−9
(1) and the washers, Part No. NAS1149D0332J (2). Torque the bolt from
22.5 to 27.5 lbf in (2.55 to 3.10 Nm). Refer to Figure 3.
MODEL BD−100−1A10 (CH−300) Basic Issue: Oct 26/2015 100−25−39 Page 8 of 22
(d) Install the harnesses to their attachment points, with kept hardware.
(e) Install any insulation blanket removed to get access. Refer to AMM 25−80−21−400−801.
(f) Install the access panels that follows. Refer to AMM 25−72−01−400−803:
(i) 222AZ
(ii) 222BZ E. 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
3. MATERIAL INFORMATION A. Kits Kit 100K25−39 is necessary to do PART A and contains the parts that follow:
NEW PART NO. QTY ITEM USED PARTNO. INSTRUCTIONS- DISPOSITION 1005336304−001 1 Doubler (LH) − − B0203013−08 5 Collar − − B0205018AD3−4S 2 Solid Rivet − − B0205018AD4−5S 3 Solid Rivet − − B0205018AD5−5S 8 Solid Rivet − − B0206001AG5−4 5 Hi−lite − − K1000070316−005 1 VerticalPacker − − K1000070316−006 1 Packer − − MS20470AD4−4 3 Solid Rivet − − MS20470AD5−6 5 Solid Rivet − − MODEL BD−100−1A10 (CH−300) Basic Issue: Oct 26/2015 100−25−39 Page 9 of 22
Kit 100K25−39A is necessary to do PART B and contains the parts that follow:
NEW PART NO. QTY ITEM USED PARTNO. INSTRUCTIONS- DISPOSITION 1005336304−002 1 Doubler (RH) − − B0202013S1320−63 1 Washer − − B0203013−08 5 Collar − − B0205018AD4−5S 3 Solid Rivet − − B0205018AD5−5S 8 Solid Rivet − − B0206001AG5−4 5 Hi−lite − − K1000070316−005 1 VerticalPacker − − K1000070316−006 1 Packer − − MS20470AD5−6 5 Solid Rivet − − MS35207−266 1 Screw − − MS35338−43 1 Lockwasher − − MS35650−302 1 Nut − − NAS1149D0332J 1 Washer − − NOTES: 1. In case of discrepancy between this list and the Service Bulletin Kit Parts List contained in the respective kit, then the later list prevails.
2. 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.
B. Parts No parts required.
MODEL BD−100−1A10 (CH−300) Basic Issue: Oct 26/2015 100−25−39 Page 10 of 22
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 PARTNO./NAME SPECIFICATION QUANTITY
SUPPLIER (SEE NOTE) Polyurethane Topcoat CT: 6 hours − BAMS 565−002 As Necessary Code: A Primer, Epoxy CT: 3.5 hours − BAMS 565−001 As Necessary Code: A Tape, Pressure Sensitive LT−16 − As Necessary Code: B Tape, Pressure Sensitive P−55 − As Necessary Code: C Sealing Compound CT: 24 hours − MIL−PRF−81733 Type II, Class I , Grade A As Necessary Code: D Aliphatic Naphtha − TT−N−95, TypeII As Necessary Code: E Coating Chemical Conversion Alodine 1200S MIL−DTL−81706, Class 1A As Necessary Code: E Coating Chemical Conversion, Electrically Conductive Alodine 1000 MIL−DTL−81706,Class 3 As Necessaryfor PART B Code: E 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.
MODEL BD−100−1A10 (CH−300) Basic Issue: Oct 26/2015 100−25−39 Page 11 of 22