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700-46-6005Page 1 of 1
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET MODEL BD-700-1A10 (BD-700) Discard the Revision 01 of this Service Bulletin dated Mar 20/2015, and replace in its entirety with this Revision 02.
Service Bulletin No. 700-46-6005 Date of Basic Issue Feb 23/2015 Revision No. 01 Dated Mar 20/2015 Revision No. 02 Dated Jun 18/2015 This revision has no effect for aircraft on which the Basic Issue or Rev. 01 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. Revise, in the Service Bulletin Summary Sheet, the Effectivity row, and Paragraph
1.A., Effectivity to delete aircraft, Serial No. 9313.
2. Add, in Paragraph 1, Planning Information, NOTE 4, a new paragraph.
3. Add, in Paragraph 2.C.(19), NOTE, a reference to a TASK number.
4. Add, in Paragraph 2.D., TESTING, a CAUTION.
5. Add, in Paragraph 2.D.(1)(a), a NOTE.
6. Revise Paragraph 2.D.(4), for clarity.
7. Replace Figure 7, figure replaced with figure displayed when using PMAT 5.
8. Make miscellaneous minor changes, as necessary, with no change of context.
Basic Issue: Feb 23/2015 700-46-6005Revision 01: Feb 25/2015 Page 1 of 1
PILOTS INFORMATION SHEET MODEL BD-700-1A10 (BD-700) ATA 46-31
INFORMATION SYSTEMS ICA – MODIFICATION – INFORMATION MANAGEMENT SYSTEM –
DEACTIVATION OF CES ETHERNET INTERFACE TO CABIN PRINTER Bombardier has been advised by Rockwell Collins that on aircraft with Service Bulletins 700-34-6017 and/or 700-23-6012 installed; the implementation of the network interface between the Information Management System (IMS-6000) unit and the CES cabin network may affect the Avionics Control Domain (ACD).
The IMS-6000 unit is connected by a Local Area Network (LAN) cable to the CES server providing flight crew with cabin printing capabilities.
Bombardier and Rockwell Collins are working on a solution. Until the final solution is available, the connection between the IMS and the CES has been deactivated by cap and stowing wires at the IMS.
Basic Issue: Feb 23/2015 700-46-6005Revision 02: Jun 18/2015 Page 1 of 1 SERVICE BULLETIN SUMMARYThis Service Bulletin is available at:
www.cic.bombardier.com MODEL BD-700-1A10 (BD-700) ATA 46-31
INFORMATION SYSTEMS ICA – MODIFICATION – INFORMATION MANAGEMENT SYSTEM –
DEACTIVATION OF CES ETHERNET INTERFACE TO CABIN PRINTER The information below is provided for your reference. For full details, please see corresponding paragraph contained within this bulletin.
RECOMMENDEDSPECIFIED TIME COMPLIANCE
COMPLIANCE TIME Within 15 Months from Service Bulletin Release (Basic Issue) EFFECTIVITY: A/C Serial No. 9381, 9432 to 9708, 9711 to 9718 and 9720 to 9730 MANPOWER: Part A – 1 man-hour Part B – 3 man-hours
CONTINUED AIRWORTHINESS (CAW)
FLEET CAMPAIGN YES NO TLMC, CH 5 AFFECTED YES NO 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 SB includes Instructions for Continued Airworthiness (ICA). Refer to Paragraph 1, (Planning Information) and Paragraph 1.D. (Compliance) for details.
To place an order for parts or kits, please call Bombardier Aerospace Parts Services at:
514-855-2999 or 1-866-538-1247
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: Feb 23/2015 700-46-6005Revision 02: Jun 18/2015 Page 1 of 14 SERVICE BULLETINThis Service Bulletin is available at:
www.cic.bombardier.com MODEL BD-700-1A10 (BD-700) ATA 46-31
INFORMATION SYSTEMS ICA – MODIFICATION – INFORMATION MANAGEMENT SYSTEM –
DEACTIVATION OF CES ETHERNET INTERFACE TO CABIN PRINTER
1. PLANNING INFORMATION NOTES: 1. For any technical issues, contact CSE, Technical Support, Global Express by e-mail at SRPSA@aero.bombardier.com.
2. For aircraft In Service, because of the lead-time necessary to get the new files for the Aircraft Personality Module (APM) we recommend that you send, four weeks in advance, a SRPSA and pages 1, 2 and 3 of Appendix 1 to Customer Support Engineering (CSE), Technical Support, Global Express by e-mail at SRPSA@aero.bombardier.com before you schedule the incorporation of this Service Bulletin.
3. After incorporation of this Service Bulletin the IMS/CES interface is disconnected and functionality affected is as follows:
(i) Printing from the cockpit to the cabin printer is not available, if the option was installed, and
(ii) Physical link from the cabin network to the OMS is removed.
4. The APM Option file number configuration is APMOPTION_6XXXXXXXXXXXXX. The 8th character from right to left (shown in bold) indicates the status of installed printers.
The possible codes are: 0 for no printers installed, 1 for cockpit printer installed, C for cabin printer installed and B for both cockpit and cabin printers installed.
If the current APM Option file shows B, then a new APM Option file indicating a 1 must be requested by SRPSA.
If the current APM Option file shows C, then a new APM Option file indicating a 0 must be requested by SRPSA.
When the SRPSA is submitted, include the current APM Option file number on the request.
MODEL BD-700-1A10 (BD-700) Basic Issue: Feb 23/2015 700-46-6005Revision 02: Jun 18/2015 Page 2 of 14 A. Effectivity BD-700-1A10 aircraft, Serial No. 9381, 9432 to 9708, 9711 to 9718 and 9720 to 9730.
NOTES: 1. All other BD700-1A10 aircraft are scheduled for modification in production. Refer to Modification Summary Z700T901412.
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.
B. Reason Condition:
Bombardier has been advised by Rockwell Collins that on aircraft with Service Bulletin 700-34-6017 and/or 700-23-6012 installed; the implementation of the network interface between the Information Management System (IMS-6000) unit and the CES cabin network may affect the Aircraft Control Domain (ACD). This scenario has been determined by analysis and was not reported from the in-service aircraft.
Evidence:
The IMS-6000 unit is connected by a Local Area Network (LAN) cable to the CES server providing flight crew with Cabin printing capabilities. Since the IMS-6000 becomes a client of the CES server, it can potentially compromise the operational integrity of the avionics system.
Objective/Benefits:
Bombardier and Rockwell Collins are working on a solution. Until the final solution is available, print function from the cockpit to the cabin printer must be disabled.
C. Description This Service Bulletin gives instructions in:
PART A:
– Verify printer status in the APM Option file, – Remove the IMS, – Inspect connector A459P1, and – Verify pins are present.
PART B:
– Cap and stow wires, – Install the IMS, – Install updated APM Option file, if required, and – Do the necessary tests to make sure that the system operates correctly.
MODEL BD-700-1A10 (BD-700) Basic Issue: Feb 23/2015 700-46-6005Revision 02: Jun 18/2015 Page 3 of 14 D. Compliance Recommended within 15 months from this Service Bulletin release date (Basic Issue).
NOTE: The issuance of an Airworthiness Directive (AD) to incorporate this Service Bulletin is expected to be released by Transport Canada.
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 700-00-6002.
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.
1 man-hour is necessary to do PART A.
3 man-hours are necessary to do PART B.
4 man-hours are necessary to do PART A and PART B.
The labor required to do this Service Bulletin is at no cost if:
(i) the work is done at Bombardier Business Aviation Services (BBAS) or Authorized Service Facilities (ASF), and
(ii) this Service Bulletin is scheduled in less than 15 months from its release date (Basic Issue).
MODEL BD-700-1A10 (BD-700) Basic Issue: Feb 23/2015 700-46-6005Revision 02: Jun 18/2015 Page 4 of 14 G. Material - Cost and Availability No kit is necessary to do this modification. For parts, refer to Paragraph 3.B.
The parts are available at no cost if a no-charge purchase order is sent to Bombardier Aerospace in less than 15 months from this Service Bulletin release date (Basic Issue).
During or after the above free period, Smart Parts does not pay for the parts.
H. Tooling The tool listed below is necessary to do this modification:
GSE REFERENCE NO. PART NO. DESCRIPTION
- M81969/14-01 Insertion/Extraction Tool I. Weight and Balance No change.
J. Electrical Load Data No change.
K. References – TCCA Airworthiness Directive, (pending).
– FAA Airworthiness Directive,(pending).
– Bombardier Aerospace, Modification Summary, R700T400577, Rev. C1.
– Global 6000 BD-700 Aircraft Maintenance Manual (AMM), Chapters 6, 24, 25, 46 and 52.
– Bombardier Aerospace, Standard Practices Manual (SPM), Chapter 20, Wiring and 51 Structures.
– Bombardier Aerospace, Supplemental Wiring Diagram Manual (SMM), Chapter 44.
– Appendix 1 – Information Feedback Sheet (attached).
L. Other Publications Affected – BD-700-1A10 Flight Crew Operating Manual, GL 6000 FCOM, Revision 14 dated May 11/2015 or later revisions as applicable.
M. Equivalent Service Bulletin – For the Global 5000 BD-700-1A11 (BD-700) Featuring Global Vision Flight Deck aircraft, use SB 700-46-5005.
MODEL BD-700-1A10 (BD-700) Basic Issue: Feb 23/2015 700-46-6005Revision 02: Jun 18/2015 Page 5 of 14
2. ACCOMPLISHMENT INSTRUCTIONS NOTES: 1. All TASKs given in the procedures that follow are from Global 6000 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 6000 BD-700-1A10, Aircraft Maintenance Manual (AMM), Chapter 6.
A. Aircraft Setup
(1) Obey all electrical/electronic safety precautions. Refer to TASK 24-00-00-910-801.
(2) Obey all electrostatic discharge safety precautions.
Refer to TASK 24-00-00-910-802.
(3) Set the circuit breaker that follows to OUT (refer to TASK 24-00-00-863-801):
SYSTEM NAME CIRCUIT BREAKER NAME BUS NAME IMS IMS DC 1
(4) On the cabin systems panel, set the cabin power switch to OFF.
B. PART A – Verify Connector Pins are Present
(1) Remove the IMS-6000 unit. Refer to TASK 46-31-01-000-801.
(2) Get access to the A459P1 connector.
(3) Inspect the connector to determine if pins are present at positions 25, 27, 48 and 50.
(4) If pins are present do Paragraph 2.C. PART B Modification.
(5) If pins are not present do the following:
(a) Install the IMS unit. Refer to TASK 46-31-01-400-801.
(b) Proceed to Paragraph 2.F., Recording.
MODEL BD-700-1A10 (BD-700) Basic Issue: Feb 23/2015 700-46-6005Revision 02: Jun 18/2015 Page 6 of 14 C. PART B – Modification
(1) Remove the pilot’s seat. Refer to TASK 25-11-00-000-801.
(2) Remove pilot’s side panel to get improved access to the IMS connector.
Refer to TASK 25-12-05-000-801.
(3) Get access to the A459P1 connector and remove the backshell.
NOTES: 1. Slide the locking ring to the left to show the red indicator line.
Backshell is unlocked. Refer to Figure 1.
2. Unscrew the backshell by the composite barrel. Do not use the locking ring or the strain relief.
Figure 1: Connector Components
(4) Identify and locate wire CAM2181-24.
(5) Using the extraction tool, remove wires located on pins 25, 27, 48 and 50.
Backshell MST CapMST Rook Locking Ring
MODEL BD-700-1A10 (BD-700) Basic Issue: Feb 23/2015 700-46-6005Revision 02: Jun 18/2015 Page 7 of 14
(6) Cap and stow the wires. Refer to SPM TASK, Wiring 20-12-05-02, Stowage of Electrical Wiring and Figure 2.
NOTE: Do not remove pin terminations from the wires. Wires will be reconnected at a later date.
Figure 2: Wire Cap and Stow Position
(7) Install sealing plugs in connector where pins 25, 27 48 and 50 were located.
(8) Straighten other shields along wire bundle.
(9) Slide the MST Rook (see Figure 1) over the shields until the serrated edge on the MST Rook and connector mate.
(10) Holding the MST Rook and connector in the mated position, fold the remaining shields through the slots of the MST Rook and along the outside of the MST Rook.
Pins capped & stowed Shield capped and stowed Tie with lacing
MODEL BD-700-1A10 (BD-700) Basic Issue: Feb 23/2015 700-46-6005Revision 02: Jun 18/2015 Page 8 of 14
(11) Mate the MST Cap to the MST Rook holding the shields in place.
(12) Install backshell on connector plug A459P1 and make sure not to over tighten.
(13) Slide the locking ring (see Figure 1) to the right, hiding the red indicator line and showing the blue indicator line. Backshell is in locked position.
(14) Install the IMS unit. Refer to TASK 46-31-01-400-801.
(15) Do an electrical bonding test on the IMS unit. Refer to SPM TASK, Structures 51-80-00-760-801, Electrical Bonding Test.
NOTE: Make sure that the resistance value is not more than 0.010 ohm.
Measure from the connector shell to the aircraft structure with all mating connectors disconnected. All connectors of the unit must be tested.
(16) Connect and energize the external ac power if it is not connected. Refer to TASK 24-41-00-861-801.
NOTE: Wait five minutes after power is applied to let the IMS and the MCE in the cabin system become fully functional.
(17) Set the circuit breaker that follows to IN (refer to TASK 24-00-00-863-802):
SYSTEM NAME CIRCUIT BREAKER NAME BUS NAME IMS IMS DC 1
(18) On the cabin systems panel, set the cabin power switch to ON.
(19) If required, load the new APM Option file as determined by Appendix 1.
Refer to TASK 46-31-00-970-803.
NOTE: Updates to the APM option file must consider other options being installed at the same time to make sure all required options are enabled prior to loading a new APM option file.
Refer to TASK 31-42-09-970-802.
MODEL BD-700-1A10 (BD-700) Basic Issue: Feb 23/2015 700-46-6005Revision 02: Jun 18/2015 Page 9 of 14 D. Testing CAUTION: MAKE SURE THE WIRELESS SWITCH ON THE PMAT IS TURNED OFF. REFER TO AW700-45-0490.
(1) Do the connectivity test on the OMS AFT port as follows:
(a) Connect PMAT using RJ45 LAN cable to OMS AFT port receptacle (J2002).
NOTE: GCC will use their PMAT equivalent.
Figure 3: OMS Aft Port (J2002)
(b) Power on PMAT and select ON-BOARD MAINT.SYS. tab.
(c) Click IP UTILITY button.
(d) From pop up window, check AFT and SUBMIT.
(e) Click on OMS AFT button.
(f) Observe the OMS main page displays on the PMAT.
(g) If PMAT displays the OMS main page, as shown on Figure 4, the test passes. Refer to Figure 4.
(h) Test completed - Disconnect PMAT from the OMS Aft port.