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Discard the Basic Issue of this Service Bulletin dated Jun 23/2015 and replace in its entirety with this Revision 01.
Service Bulletin No. 605−22−002 Date of Basic Issue Jun 23/2015 Revision No. 01 Dated Jul 25/2016 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 clarify the instructions applicable to each PART. The changes are as follows:
1. Revise the Service Bulletin Summary Sheet, to add a reference to PART A and PART B for the man−hours.
2. Revise Paragraph 1, to update the planning information Note 1.
3. Revise Paragraph 1.C., to update the instructions applicable to PART A.
4. Revise Paragraph 1.F., to revise and clarify the man−hours applicable to PART A and PART B.
5. Revise Paragraph 2.A., to add a reference to PART A for the Special Check and clarify the instructions.
6. Revise Paragraph 2.B., to add a reference to PART B for the Aircraft Setup.
7. Revise Paragraph 2.F., to update the Recording Statement.
8. Make miscellaneous minor changes, as necessary, with no change of context.
SERVICE BULLETIN MODEL CL−600−2B16 605−22−002 Page 1 of 1
REVISION TRANSMITTAL SHEET
SPECIAL CHECK / MODIFICATION - YAW DAMPER SYSTEM - AUTOMATIC FLIGHT
CONTROL SYSTEM (AFCS) WIRING CHANGE TO PREVENT UN-COMMANDED YAW
DAMPER/LINEAR ACTUATOR MOTION AFTER POWER SUPPLY FAILURE 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 Recommended in less than 48 months from this Service Bulletin release date (Basic Issue).
EFFECTIVITY: A/C Serial No. 5701 to 5911, 5913 and 5914 MANPOWER: 0.5 man−hour is necessary to do the special check in PART A.
50 man−hours are necessary to do the modification in PART 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 CL−600−2B16 ATA 22−22
AUTO FLIGHT Basic Issue: Jun 23/2015 Revision 01: Jul 25/2016 605−22−002 Page 1 of 1 This Service Bulletin is available at:
SPECIAL CHECK / MODIFICATION - YAW DAMPER SYSTEM - AUTOMATIC FLIGHT
CONTROL SYSTEM (AFCS) WIRING CHANGE TO PREVENT UN-COMMANDED YAW
DAMPER/LINEAR ACTUATOR MOTION AFTER POWER SUPPLY FAILURE
1. PLANNING INFORMATION NOTES: 1. Consult the log book to verify the part numbers of both Yaw Damper Linear Actuators. If the part number information is unavailable, refer to the Accomplishment Instructions in Paragraph 2.A. of this Service Bulletin.
2. Due to the lead−time required for obtaining kits and parts, operators are advised to order the kits and parts in advance before scheduling the incorporation of this Service Bulletin. Please contact Parts Services, in Montreal, for delivery lead times and confirmation of prices.
A. Effectivity CL−600−2B16 aircraft, Serial No. 5701 to 5911, 5913 and 5914.
The intent of this Service Bulletin was met on aircraft, Serial Nos. 5912, 5915 and all other subsequent CL−600−2B16 aircraft with the Production Modification Summary 600−5900, and the Restriction and /or Special Instruction (RSI), C−4098.
NOTES: 1. For these aircraft that have had SVL−4000 YD−LA Part No.
622−9968−102 installed in Production, the Part Interchangeability has been revised to no longer allow Part No. 622−9968−002 to be installed on the CL−600−2B16 aircrafts.
2. 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 CL−600−2B16 ATA 22−22
AUTO FLIGHT 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.
2015−2016 Bombardier Inc. All rights reserved Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.
Basic Issue: Jun 23/2015 Revision 01: Jul 25/2016 605−22−002 Page 1 of 15 This Service Bulletin is available at:
B. Reason Certain SVL−4000 YD−LA with Part No. 622−9968−002 have an internal −12 VDC power supply failure mode that can lead to an uncommanded actuator motion.
During the failure mode, the −12 VDC output becomes unstable and randomly varies between −14 and +1 VDC. Since, the −12 VDC power supply output is tied to the position feedback circuit and brake/motor control units, this failure can produce:
− Command Voltage Offset inside the actuator which leads to disengage the brake of actuator and release the servo motor.
− Position feedback sensor signal error (output from LVDT) which leads to an erroneous command of actuator position.
This Service Bulletin modifies the wiring connection of Automatic Flight Control System (AFCS) which will lead to cut off the yaw damper actuator power supply when the yaw damper DISC switch is pushed. In consequence, the yaw damper DISC switch will be able to remove the internal un−commanded yaw actuator motion.
C. Description This Service Bulletin gives instructions in:
PART A, to:
Do the part number verification for both Yaw Damper Linear Actuators to visually witness the part number, if the part number of both Yaw Damper Linear Actuators can not be verified by a log book entry.
− If one or both of the Yaw Damper Linear Actuator installed is Part No.622−9968−002, proceed to PART B in Paragraph 2.B.
− If the Yaw Damper Linear Actuator Part No. 622−9968−102 is installed in both positions, proceed to the Close Out in Paragraph 2.E.
PART B, to:
− Get access to Junction Boxes JB14 and JB15, − Do the wiring modification related to Automatic Flight Control System (AFCS), and − Do the necessary operational and functional tests to make sure that the system operates correctly.
D. Compliance Recommended in less than 48 months from this Service Bulletin release date (Basic Issue).
MODEL CL−600−2B16 Basic Issue: Jun 23/2015 Revision 01: Jul 25/2016 605−22−002 Page 2 of 15
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 605−00−002.
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.
0.5 man−hour is necessary to do the special check in PART A.
50 man−hours are necessary to do the modification in PART B.
Bombardier Aerospace does not pay the labor to do the special check (record/visual check) in PART A.
The labor required to do the modification in PART B is at no cost if:
1. the aircraft was under warranty at the time of release of this Service Bulletin (Basic Issue),
2. the work is done at Bombardier Business Aviation Services (BBAS) or Authorized Service Facilities (ASF), and
3. this Service Bulletin is scheduled in less than 12 months from its release date (Basic Issue).
MODEL CL−600−2B16 Basic Issue: Jun 23/2015 Revision 01: Jul 25/2016 605−22−002 Page 3 of 15
G. Material − Cost and Availability Kit 605K22−002 is necessary to do this modification.
KIT NO. PRICE 605K22−002 Please contact Bombardier Aerospace Parts Services in Montreal, for delivery lead times and confirmation of prices.
Sufficient kits will be kept for the estimated amount of orders.
This kit is available at no cost if a no−charge purchase order is sent to Bombardier Aerospace in less than 12 months from this Service Bulletin release date (Basic Issue).
Due to the lead−time for obtaining kits and parts, operators are advised to order the kits and parts in advance before scheduling the incorporation of this Service Bulletin. Please contact Parts Services, in Montreal, for delivery lead times and confirmation of prices.
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 24−00−24 S4933959−501 Tag, Circuit Breaker Refer to the Standard Practices Manual (SPM), Wiring Manual (WM), Chapter 20, and the table that follows for the tools applicable to the wiring modification:
LUG/
CONTACT TOOL
CRIMP POSITIONER INSERTION EXTRACTION M39029/1−101 M22520/1−01 M22520/1−02 M81969/14−11 M81969/14−11 M39029/5−116 M22520/1−01 M22520/1−02 M81969/14−03 M81969/14−03 MODEL CL−600−2B16 Basic Issue: Jun 23/2015 Revision 01: Jul 25/2016 605−22−002 Page 4 of 15
LUG/
CONTACT TOOL
CRIMP POSITIONER INSERTION EXTRACTION M39029/ 92−534 M22520/1−01 M22520/1−02 M81969/14−03 M81969/14−03 NOTES: 1. Refer to the CL−605 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.
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.
J. Electrical Load Data No change.
K. References − Bombardier Aerospace, Modification Summary, 600−6358, Rev. C.
− Bombardier Aerospace, Modification Summary, 600−5900, Rev. B2.
− Bombardier Aerospace, Restriction and/or Special Instruction (RSI), C−4098, Rev. −−.
− Bombardier Aerospace, Functional Test Engineering Requirements, FTER 604DX−222001, Rev. A.
− Bombardier Aerospace, Kit Drawing K604−70200, Rev. B.
− CL−605 Aircraft Maintenance Manual (AMM), Chapters 12, 22, 24 and 31.
− CL−605 Standard Practices Manual (SPM), Chapter 20.
L. Other Publications Affected None.
M. Equivalent Service Bulletin For the Challenger 604 aircraft, use SB 604−22−007.
MODEL CL−600−2B16 Basic Issue: Jun 23/2015 Revision 01: Jul 25/2016 605−22−002 Page 5 of 15
2. ACCOMPLISHMENT INSTRUCTIONS NOTES: 1. All TASKs given in the procedures that follow are from the CL−605 Aircraft Maintenance Manual unless otherwise specified.
2. All references made to zones, access panels and/or doors, are from the CL−605 Aircraft Maintenance Manual, Chapter 6.
A. Part A − Special Check − Yaw Damper Linear Actuators Part Number Verification
(1) If the part number of both Yaw Damper Linear Actuators can not be verified by a log book entry, the part number verification must be carried out by physically accessing both the Yaw Damper Linear Actuators to visually witness the part number.
(2) To access the Yaw Damper Linear Actuator, refer to AMM 55−30−43−000−808. If Yaw Damper Linear Actuator Part No.
622−9968−002 is installed,
(a) proceed to Paragraph 2.B., Aircraft Setup.
(b) If Yaw Damper Linear Actuator Part No. 622−9968−102 is installed in both positions, proceed to Paragraph 2.E., Close Out.
B. Part B − Aircraft Setup CAUTION: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO
MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. YOU CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT.
(1) Obey all electrical/electronic safety precautions. Refer to AMM 24−00−00−910−801.
(2) Remove the electrical power from the aircraft. Refer to AMM 24−00−00−861−802.
(3) Remove the external AC power. Refer to AMM 12−00−07−861−802.
(4) Disconnect the auxiliary power unit (APU) battery. Refer to AMM 24−32−00−040−802.
(5) Remove the Pilot and Copilot seats. Refer to AMM 25−11−01−000−801.
(6) Remove the access panels that follow:
ACCESS DESIGNATION 221EZ Panel, Pilot side Console, Forward 222EZ Panel, Copilot Side Console, Forward MODEL CL−600−2B16 Basic Issue: Jun 23/2015 Revision 01: Jul 25/2016 605−22−002 Page 6 of 15
CAUTION: OBEY ALL ELECTROSTATIC DISCHARGE-SENSITIVE (ESDS) PRECAUTIONS. STATIC VOLTAGES CAN CAUSE DAMAGE TO ESDS COMPONENTS.
(7) Obey all electrostatic discharge−sensitive (ESDS) safety precautions. Refer to AMM 24−00−00−910−802.
(8) On copilot side console, remove the lamp driver unit (LDU). Refer to AMM 31−52−01−000−801.
C. Modification
(1) Remove Junction Boxes JB14 and JB15 from the aircraft in order to accomplish these modifications. For JB14 removal, refer to AMM 24−01−14−000−801. For JB15 removal, refer to AMM 24−01−15−000−801.
(2) Do the wiring modification in Junction Boxes JB14 and JB15 as per SPM Chapter 20. Refer to K604−70200, detail −24, Installation.
NOTE: Make sure JB14 and JB15 are identified post−modification per Kit Drawing K604−70200, note 3.
(3) Do an electrical continuity check on all wiring introduced or disturbed by this modification.
(a) Install Ground Studs for Ground Wire installation. Refer to Bombardier Aerospace, Kit Drawing K604−70200, Rev. B, Flag Note 5.
(4) Install Junction Boxes JB14 and JB15 in the aircraft. For JB14 installation, refer to AMM 24−01−14−400−801. For JB15 installation, refer to AMM 24−01−15−400−801 .
(5) Install the lamp driver unit. Refer to AMM 31−52−01−400−801.
(6) Install the access panels that follow:
ACCESS DESIGNATION 221EZ Panel, Pilot side Console, Forward 222EZ Panel, Copilot Side Console, Forward
(7) Install the Pilot and Copilot seats. Refer to AMM 25−11−01−400−801.
D. Testing
(1) Connect and energize the external AC power. Refer to AMM 12−00−07−861−801.
(2) Connect the auxiliary power unit (APU) battery. Refer to AMM 24−32−00−440−802.
(3) Do the operational tests given in the table that follows:
MODEL CL−600−2B16 Basic Issue: Jun 23/2015 Revision 01: Jul 25/2016 605−22−002 Page 7 of 15
DESIGNATION TASK Operational test of the junction box JB14. AMM 24−01−14−710−801 Operational test of the junction box JB15. AMM 24−01−15−710−801 Operational test of the Integrated Avionics Processor System (IAPS).
AMM 22−12−00−710−801 Do the operational test of the yaw damper linear actuator.
AMM 22−22−01−710−801 Do the operational test of the yaw damper control−panel.
AMM 22−22−04−710−801 Do the operational test of the yaw damper engage buttons.
AMM 22−11−00−710−802
(4) Do the yaw damper engagement test as follows:
(a) Momentarily set the MAINT switch at FS 280L to MFD 2.
(b) Make sure that TO ENTER FCC DIAGNOSTICS page is shown on the MFD 2.
(c) On the FCP, simultaneously push the right FD button and any two other mode select buttons to enter FCC DIAGNOSTICS mode.
(d) On the FCP, simultaneously push two mode select buttons until the INPUT MODE is shown.
(e) On the flight control panel (FCP), turn the pitch wheel until LH RUDPWR parameter is shown. Make sure that TRUE is shown in the left column on the MFD 2.
(f) On the basic reversionary control panel set the AFCS SEL switch to 1.
(g) Push the YD 1 on the yaw damper control panel. Push the DISC button to disengage the yaw damper 1.
(h) Push the YD 2 on the yaw damper control panel. Push the DISC button to disengage the yaw damper 2.
(i) Engage YD 1. Make sure the EICAS message YD 2 INOP (white) is shown.
(j) On the flight control panel (FCP), turn the pitch wheel until LH RUDPWR parameter is shown and, TRUE is shown in the left column on the MFD 2.
(k) Push the DISC button on the yaw damper control panel. Make sure the EICAS message YAW DAMPER (amber) is shown.
(l) On the flight control panel (FCP), turn the pitch wheel until RH RUDPWR parameter is shown and, TRUE is shown in the left column on the MFD 2.
MODEL CL−600−2B16 Basic Issue: Jun 23/2015 Revision 01: Jul 25/2016 605−22−002 Page 8 of 15
(m) Engage YD 2. Make sure the EICAS message YD 1 INOP (white) is shown.
(n) On the flight control panel (FCP), turn the pitch wheel until RH RUDPWR parameter is shown and, TRUE is shown in the left column on the MFD 2.
(o) Push the DISC button on the yaw damper control panel. Make sure the EICAS message YAW DAMPER (amber) is shown.
(p) On the basic reversionary control panel set the AFCS SEL switch to 2.
Repeat the steps from (g) to (o) again.
E. Close−out Remove all tools, equipment and unwanted materials from the aircraft.
F. Recording You can do each PART of this Service Bulletin independently. When any PART of 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. Kit Kit 605K22−002 is necessary to do this Service Bulletin and contains the parts that follow:
NEW PART NO. QTY ITEM USED PART NO.
INSTRUCTIONS
- DISPOSITION B0808005−006N 2 Terminal Lug − − K604−70200−1/02 1 Wire Kit − − K604−70200−24/01 1 Wire Kit − − M12883/47−04 2 Relay Socket − − M83536/26−002L 2 Relay − − MS35207−265 2 Screw − − MS35338−43 4 Lock Washer − − MODEL CL−600−2B16 Basic Issue: Jun 23/2015 Revision 01: Jul 25/2016 605−22−002 Page 9 of 15
NEW PART NO. QTY ITEM USED PART NO.
INSTRUCTIONS
- DISPOSITION MS35650−302 4 Nut − − NAS1149D0332J 6 Washer − − NOTES: 1. In case of discrepancy between this list and the ’Service Bulletin Kit Parts List’ contained in the respective kit, then the latter 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.
C. Material No materials required.
D. Publications No publications required.
MODEL CL−600−2B16 Basic Issue: Jun 23/2015 Revision 01: Jul 25/2016 605−22−002 Page 10 of 15