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Discard the Revision 02 of this Service Bulletin dated Jun 05/2018, and replace in its entirety with this Revision 03.
Service Bulletin No. 100−27−17 Date of Basic Issue Dec 05/2012 Revision No. 01 Dated Jul 20/2017 Revision No. 02 Dated Jun 05/2018 Revision No. 03 Dated Jun 19/2020 For action applicable to aircraft on which Basic Issue, Revision 01, or Revision 02 of this Service Bulletin was done, refer to the retroactive action box on Page 1 of this Service Bulletin.
This revision is issued to:
1. Change, in the Service Bulletin Summary Sheet, to revise the Compliance Time to within 12 months from this Service Bulletin release date (Revision 03).
2. Change, in the Service Bulletin Summary Sheet and Paragraph 1.A., the effectivity.
3. Add, in the Service Bulletin Summary Sheet, an Airworthiness Directive Note.
4. Add, in Paragraph 1, a retroactive action box.
5. Revise, in Paragraphs 1.D., the Compliance Time to within 12 months from this Service Bulletin release date (Revision 03).
6. Add, in Paragraph 1.D., a Note as per latest template.
7. Change, in Paragraphs 1.F., to revise the labor required to do this Service Bulletin statement.
8. Change, in Paragraph 1.G., to revise kit and parts required to do this Service Bulletin statement.
SERVICE BULLETIN MODEL BD−100−1A10 (CH−300) 100−27−17 Page 1 of 2
REVISION TRANSMITTAL SHEET
9. Add, in Paragraph 1.K., a reference to TCCA Airworthiness Directive, (Pending).
10.Delete, in Paragraph 1.K., a reference to RSI C−100−000−27−0297, Rev. E.
11.Add, in Paragraph 1.K., a reference to RSI C−100−000−27−0318, Rev. A.
12.Revise, in Paragraph 1.M., to add CH 350 equivalent Service Bulletin.
13.Change, in Paragraph 2.B., to revise step (1).
14.Make miscellaneous minor changes, as necessary, with no change of context.
MODEL BD−100−1A10 (CH−300) 100−27−17 Page 2 of 2
SPECIAL CHECK/MODIFICATION – MULTI-FUNCTION SPOILER – REPLACEMENT
OF THE MULTIFUNCTION SPOILER POWER CONTROL UNIT (MFS PCU) SEALS 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 12 months from this Service Bulletin release date (Revision 03) EFFECTIVITY: A/C Serial No. 20003 to 20457 MANPOWER: Refer to Paragraph 1.F.
CONTINUED AIRWORTHINESS (CAW)
FLEET CAMPAIGN YES NO 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 NOTE: This Service Bulletin is subject to an Airworthiness Directive which will make it necessary to implement this Service Bulletin.
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−100−1A10 (CH−300) ATA 27−62
FLIGHT CONTROLS Basic Issue: Dec 05/2012 Revision 03: Jun 19/2020 100−27−17 Page 1 of 1 This Service Bulletin is available at:
SPECIAL CHECK/MODIFICATION – MULTI-FUNCTION SPOILER – REPLACEMENT
OF THE MULTIFUNCTION SPOILER POWER CONTROL UNIT (MFS PCU) SEALS
RETROACTIVE ACTION
THE ACTION THAT FOLLOWS IS RECOMMENDED FOR AIRCRAFT ON WHICH THE BASIC ISSUE, REVISION 01, REVISION 02 OF THIS SERVICE BULLETIN WAS DONE:
(1) DO REVISION 03 OF THIS SERVICE BULLETIN.
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. 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 100−00−02.
3. Two persons are necessary to remove and install the Multi−Function Spoiler Power Control Unit (MFS PCU).
SERVICE BULLETIN my.businessaircraft.bombardier.com MODEL BD−100−1A10 (CH−300) ATA 27−62
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.
2012−2020 Bombardier Inc. All rights reserved Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.
Basic Issue: Dec 05/2012 Revision 03: Jun 19/2020 100−27−17 Page 1 of 18 This Service Bulletin is available at:
4. This Service Bulletin is also applicable to the MFS PCUs in the operator’s stock room.
5. The MFS are operated by two separate hydraulic systems as follows:
The Left Hydraulic System operates the inboard MFS.
The Right Hydraulic System operates the outboard MFS.
For aircraft where inboard and outboard MFC PCUs are replaced, it is necessary to bleed both hydraulic systems.
A. Effectivity BD−100−1A10 aircraft, Serial No. 20003 to 20457.
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 During production flight tests, at the emergency descent testing (Maximum Mach Operating (MMO) speed and spoilers at EMER position), there was a malfunction of the inboard multifunction spoiler system at deployment. This malfunction shut down the Proportional Lift Dumping (PLD) and Ground Lift Dumping (GLD) function of this pair of spoilers. Detailed inspection of the MFS PCU showed that the piston seal did not have the necessary notches. These notches are necessary to prevent internal leakage when a load is applied to the actuator. This Service Bulletin replaces the MFS seals with ones that have the applicable notches. This prevents internal leakage and improves MFS reliability.
C. Description This Service Bulletin gives instructions to:
− Get access to the MFS PCUs, − Identify the MFS PCU serial numbers, − Replace the applicable MFS PCU, and − Do the necessary tests to make sure that the system operates correctly.
D. Compliance Recommended within 12 months from this Service Bulletin release date (Revision 03).
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.
MODEL BD−100−1A10 (CH−300) Basic Issue: Dec 05/2012 Revision 03: Jun 19/2020 100−27−17 Page 2 of 18
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 the JAA and 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 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 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 man−hours and should be considered for planning purposes before you schedule this Service Bulletin.
PART A: 1 man−hour are necessary to do this modification.
PART B: 5 man−hours are necessary to do this modification.
PART C: 5 man−hours are necessary to do this modification.
PART D: 4 man−hours are necessary to do this modification if PART C is incorporated at the same time. 5 man−hours are necessary to do this modification if PART C is not incorporated at the same time.
PART E: 4 man−hours are necessary to do this modification if PART B is incorporated at the same time. 5 man−hours are necessary to do this modification if PART B is not incorporated at the same time.
Bombardier Aviation does not pay for the labor to do this modification.
G. Material − Cost and Availability PART A: No kit or parts are necessary to do this special check.
PART B, PART C, PART D and PART E: Kit 100K27−17 and the parts given in Paragraph 3.B. are necessary to do this modification.
MODEL BD−100−1A10 (CH−300) Basic Issue: Dec 05/2012 Revision 03: Jun 19/2020 100−27−17 Page 3 of 18
KIT NO. PRICE 100K27−17 Please contact Bombardier Aviation Parts Services, in Montreal, for delivery lead times and confirmation of prices.
Bombardier Aviation does not pay for the kit and parts to do this modification.
This Service Bulletin is covered by a dedicated schedule. To ensure a timely and effective return/upgrade program, advance scheduling is required through our In−Service Implementation Team (ISIT). Please contact your Regional Manager (RM), Field Service Representatives (FSR) or Customer Service Representative (CSR) as soon as is practical to schedule your aircraft.
Send units for rework or upgrade or disposal to Bombardier Aviation at the address given below:
Learjet Inc. − Core Returns 251−A Wille Road Des Plaines, Illinois 60018−1861 USA or Distribution Centre Frankfurt − Core Returns Bombardier Aviation Germany Gmb H Hans−Boeckler−Strasse 9 GROSS−GERAU Hesse 64521 Germany Refer to your Material Return Authorization (MRA) form to find the applicable return address.
NOTE: Bombardier Aviation is maintaining a rotable pool of replacement MFS PCUs, to be supplied to the operators under the terms and conditions given below:
− The removed MFS PCU must be returned to Bombardier Aviation, Parts Services in less than 10 days of receipt of replacement unit, with documentation showing the serial number of the aircraft.
− If the removed MFS PCU is not returned in less than 10 days, the operator will be charged for the replacement unit.
For all parts transactions, Bombardier Aviation’s current Spare Parts and Component Repair Price Catalogue General Terms and Conditions apply. These terms and conditions are found on the Bombardier Customer Portal at:
my.businessaircraft.bombardier.com Smart Parts does not pay for the kit or parts at any time.
MODEL BD−100−1A10 (CH−300) Basic Issue: Dec 05/2012 Revision 03: Jun 19/2020 100−27−17 Page 4 of 18
H. Tooling The equipment and tools listed below are necessary to do this modification:
GSE REFERENCE NO. PART NO. DESCRIPTION 10−10−10 − Wheel Chocks, Rubber 20−00−04 − Inclinometer (Qty. 3 or 5)See Note 3 20−00−24 S4933959−501 Tag, Circuit Breaker 20X−00−04 − Portable Bonding Testeror equivalent − Commercially Available Container, Hydraulic Fluid, 5 U.S. gal (18.92 L) − Commercially Available Scraper, Non−Metallic − Commercially Available Tape, Double Sided − Commercially Available Tube, Transparent Extension, Hydraulic Fluid Draining − Commercially Available Wrench, Torque NOTES: 1. Refer to the 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 the BD−100, for acceptable GSE equivalents.
3. Three inclinometers are necessary if only inner OR outer MFS PCUs must be replaced. Five inclinometers are necessary if only inner AND outer MFS PCUs must be replaced.
The equipment and tools listed below may be necessary to do this modification:
GSE REFERENCE NO. PART NO. DESCRIPTION 07−10−01 − Pad, Jacking 07−10−02 − Jack, Tripod, Wing 07−10−03 − Jack, Forward Fuselage 07C−10−06 − Support, Rear Fuselage MODEL BD−100−1A10 (CH−300) Basic Issue: Dec 05/2012 Revision 03: Jun 19/2020 100−27−17 Page 5 of 18
GSE REFERENCE NO. PART NO. DESCRIPTION 27C−00−02 G1002720042−063 Rigging Pin Kit NOTES: 1. Refer to the 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 the BD−100, for acceptable GSE equivalents.
I. Weight and Balance No change.
J. Electrical Load Data No change.
K. References − TCCA Airworthiness Directive, (Pending).
− Bombardier Aviation, Restriction and/or Special Instruction (RSI), C−100−000−27−0318, Rev. A.
− Bombardier Aviation, Modification Summary, BB100T010703, Rev. A.
− Bombardier Aviation, Standard Practices Manual (SPM), Chapter 20 and 51.
− Bombardier Aviation, SB 100−00−02, Service Bulletin Description and Policy.
− CH 300 Aircraft Maintenance Manual (AMM), Chapters 6, 24, 27, 29 and 57.
− CH 300 Aircraft Illustrated Parts Catalog (AIPC), Chapter 27 and 57.
− Moog Aerospace Group, Service Bulletin C47030−27−01.
L. Other Publications Affected None.
M. Equivalent Service Bulletin − For the Challenger 350 aircraft, use Service Bulletin 350−27−010.
2. ACCOMPLISHMENT INSTRUCTIONS NOTES: 1. All TASKs given in the procedures that follow are from the BD−100 Aircraft Maintenance Manual unless otherwise specified.
2. All references made to zones, access panels and/or doors, are from the BD−100 Aircraft Maintenance Manual, Chapter 6.
MODEL BD−100−1A10 (CH−300) Basic Issue: Dec 05/2012 Revision 03: Jun 19/2020 100−27−17 Page 6 of 18
A. Aircraft Setup NOTE: The steps in the Aircraft Setup section of this Service Bulletin are recommended steps. The steps give a recommendation to get access to the work area. This recommendation is to give a safe work area and to minimize possible damage to surrounding aircraft parts. Alternative steps can be used at the operator’s discretion.
(1) Obey all flight−control safety precautions. Refer to AMM 27−00−00−910−801.
(2) Obey all electrical/electronic safety precautions. Refer to AMM 24−00−00−910−801.
(3) Connect the electrical power to the aircraft. Refer to AMM 24−00−00−861−801.
(4) Obey all hydraulic safety precautions. Refer to AMM 29−00−00−910−801.
(5) Obey all hydraulic technical precautions. Refer to AMM 29−00−00−910−802.
(6) Make sure that the weight of the fuel in left and right fuel tanks is approximately equal.
WARNING: BEFORE YOU PRESSURIZE THE HYDRAULIC SYSTEMS, MAKE
SURE THAT NO PERSONS OR EQUIPMENT ARE NEAR THE FLIGHT CONTROLS AND THE HYDRAULIC COMPONENTS.
WHEN YOU PRESSURIZE THE HYDRAULIC SYSTEMS, THE
FLIGHT CONTROLS CAN MOVE AND THE HYDRAULIC COMPONENTS CAN EJECT HYDRAULIC FLUID. THIS CAN
CAUSE INJURY TO PERSONS AND DAMAGE TO THE EQUIPMENT.
(7) Pressurize the left and right hydraulic systems. Refer to AMM 29−10−00−862−801.
(8) Set the FLAP lever to the 30 degree position.
(9) Make sure that the flap control surfaces are fully extended.
(10) Set the flight−spoiler control lever (FSCL) in the flight compartment to the MAX position.
(11) Release the pressure from the left and right hydraulic systems. Refer to AMM 29−10−00−862−802.
(12) Remove the electrical power from the aircraft. Refer to AMM 24−00−00−861−802.
(13) Open and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE LCBP B9 SPOILER CTRL 1 211 LCBP B13 L FLAP IND 211 LCBP B14 FLAP CTRL 211 LCBP C9 L HYDRAULIC IND 211 MODEL BD−100−1A10 (CH−300) Basic Issue: Dec 05/2012 Revision 03: Jun 19/2020 100−27−17 Page 7 of 18
CB PANEL CB NO. NAME ZONE LCBP C11 R HYDRAULIC DC PUMP 211 LCBP D10 AUX HYDRAULIC DCPUMP 211 RCBP B9 SPOILER CTRL 2 212 RCBP B12 R FLAP IND 212 RCBP C8 R HYDRAULIC IND 212 RCBP C11 L HYDRAULIC DC PUMP 212 B. PART A − Visual Check of the MFS PCU Serial Numbers
(1) Look at each of the four MFS PCUs and make a record of the serial numbers.
Replace MFC PCUs which have serial numbers between 0001 and 1410, except for serial numbers in the table below and MFS PCU with suffix −A at the end of the Serial No (example SER NO.1025A). These MFS PCUs were inspected and repaired by the vendor (Moog) prior to release of the Service Bulletin revision and do not need to be returned.
MFS Control Units with the following Serial Numbers DO NOT need to be replaced.
66 498 887 1373 1400 72 499 991 1376 1401 175 561 1049 1380 1403 200 605 1208 1382 1404 331 671 1236 1385 1405 441 720 1284 1386 1406 448 727 1287 1387 1407 449 728 1334 1388 1408 456 773 1337 1394 1409 470 778 1368 1395 − 494 812 1369 1396 − 495 831 1370 1397 − MODEL BD−100−1A10 (CH−300) Basic Issue: Dec 05/2012 Revision 03: Jun 19/2020 100−27−17 Page 8 of 18
(2) For aircraft that do not need any MFS PCU replacement (refer to Paragraph
2.B.(1)), no further action is necessary. Go to Close−Out, Paragraph 2.G.
(3) For aircraft where the serial number of the left outboard MFS PCU is one that must be replaced (refer to Paragraph 2.B.(1)), do PART B of this Service Bulletin.
(4) For aircraft where the serial number of the left inboard MFS PCU is one that must be replaced (refer to Paragraph 2.B.(1)), do PART C of this Service Bulletin.
(5) For aircraft where the serial number of the right inboard MFS PCU is one that must be replaced (refer to Paragraph 2.B.(1)), do PART D of this Service Bulletin.
(6) For aircraft where the serial number of the right outboard MFS PCU is one that must be replaced (refer to Paragraph 2.B.(1)), do PART E of this Service Bulletin.
C. PART B − Replacement of the Left Outboard MFS PCU NOTE: If it is not possible to complete all the instructions of this Service Bulletin because of the configuration of the aircraft, submit an SRPSA for analysis and to get an approve disposition to complete this Service Bulletin.
(1) Remove the trailing edge access panels 571DB and 571EB. Refer to AMM 57−52−01−000−801.
(2) Remove the left outboard MFS PCU. Refer to AMM 27−62−01−000−801.
NOTE: Use the Table 1 to record the MFS angles as necessary.
(3) Discard the self−locking nuts, Part No. MS21042L3, MS35650−302 and cotter pins, Part No. MS24665−162 and MS24665−302. Keep the remaining hardware for later installation.
(4) Send the MFS control unit for repair to the address shown in Paragraph 1.G.
(5) Install a reworked/new MFS PCU using the retained hardware and the new self−locking nuts, Part No. MS21042L3, MS35650−302 and cotter pins, Part No. MS24665−162 and MS24665−302 supplied in the kit. Torque the nuts, Part No. MS21042L3, from 12 to 15 lbf in (1.36 to 1.69 Nm). Torque the nuts, Part No. MS35650−302, from 20 to 25 lbf in (2.26 to 2.82 Nm). Refer to AMM 27−62−01−400−801.
NOTE: The replacement MFS PCU will have the suffix −A at the end of the Serial No. if it was reworked as a result of MOOG SB C47030−27−01.
However, you can have a replacement MFS PCU without the suffix −A if it was not affected by Bombardier Aviation SB 100−27−17 (Moog SB C47030−27−01).
(6) Do the electrical bonding test of the MFS PCU. Refer to SPM−MM 51−80−00−760−801.
NOTE: The maximum allowable resistance is 10 milliohms between the unit and the aircraft primary structure.
MODEL BD−100−1A10 (CH−300) Basic Issue: Dec 05/2012 Revision 03: Jun 19/2020 100−27−17 Page 9 of 18