700-46-5005

Page 1 of 1

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

MODEL BD-700-1A11 (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. 700-46-5005

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. Add, in Paragraph 1, Planning Information NOTE 4, a new paragraph.

2. Add, in Paragraph 2.C.(19), NOTE, a reference to a TASK number.

3. Add, in Paragraph 2.D., TESTING, a CAUTION.

4. Add, in Paragraph 2.D.(1)(a), a NOTE.

5. Revise Paragraph 2.D.(4), for clarity.

6. Replace Figure 7, figure replaced with figure displayed when using PMAT 5.

7. Make miscellaneous minor changes, as necessary, with no change of context.
Feb 23/2015 700-46-5005

 Page 1 of 1 

PILOTS INFORMATION SHEET

MODEL BD-700-1A11 (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 

Bulletin 700-34-5017 and/or 700-23-5013 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 700-46-5005

Revision 02: Jun 18/2015 Page 1 of 1

SERVICE BULLETIN SUMMARY

This Service Bulletin is available at:

www.cic.bombardier.com

MODEL BD-700-1A11 (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.

RECOMMENDED

SPECIFIED TIME COMPLIANCE

COMPLIANCE TIME

Within 15 Months from Service Bulletin

Release (Basic Issue)

EFFECTIVITY: A/C Serial No. 9386, 9401, 9445 to 9707, 9710 to 9717, 9722, 9732,

9734 and 9737

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 700-46-5005

Revision 02: Jun 18/2015 Page 1 of 14

SERVICE BULLETIN

This Service Bulletin is available at:

www.cic.bombardier.com

MODEL BD-700-1A11 (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_5XXXXXXXXXXXXX. 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-700-1A11 (BD-700)

Basic Issue: Feb 23/2015 700-46-5005

Revision 02: Jun 18/2015 Page 2 of 14

A. Effectivity

BD-700-1A11 aircraft, Serial No. 9386, 9401, 9445 to 9707, 9710 to 9717, 9722,

9732, 9734 and 9737.

NOTES: 1. All other BD700-1A11 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 700-34-5017 and/or 700-23-5013 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 inservice 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 be 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.
MODEL BD-700-1A11 (BD-700)

Basic Issue: Feb 23/2015 700-46-5005

Revision 02: Jun 18/2015 Page 3 of 14

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.

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.
MODEL BD-700-1A11 (BD-700)

Basic Issue: Feb 23/2015 700-46-5005

Revision 02: Jun 18/2015 Page 4 of 14

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 700-00-5002.

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).

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 equipment and tools listed below are necessary to do this modification:

GSE REFERENCE NO. PART NO. DESCRIPTION

- M81969/14-01 Insertion/Extraction

Tool

I. Weight and Balance

No change.
MODEL BD-700-1A11 (BD-700)

Basic Issue: Feb 23/2015 700-46-5005

Revision 02: Jun 18/2015 Page 5 of 14

J. Electrical Load Data

No change.

K. References

– TCCA Airworthiness Directive, (pending).

– FAA Airworthiness Directive,(pending)

– Bombardier Aerospace, Modification Summary, R700T400577, Rev. C1.

– Global 5000 Featuring Global Vision Flight Deck 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-700-1A11 Flight Crew Operating Manual, GL 5000 GVFD FCOM,

Revision 14 dated May 11/2015 or later revisions as applicable.

M. Equivalent Service Bulletin

– For the Global 6000 BD-700-1A10 (BD-700) use SB 700-46-6005.

2. ACCOMPLISHMENT INSTRUCTIONS

NOTES: 1. All TASKs given in the procedures that follow are from the Global 5000

BD-700-1A11 Featuring Global Vision Flight Deck, Aircraft Maintenance

Manual (AMM) unless otherwise specified.

2. All references made to zones, access panels and/or doors, are from the

Global 5000 BD-700-1A11 Featuring Global Vision Flight Deck, 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.
MODEL BD-700-1A11 (BD-700)

Basic Issue: Feb 23/2015 700-46-5005

Revision 02: Jun 18/2015 Page 6 of 14

B. PART A – Verify Connector Pins are Present

(1) Remove the IMS 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 are present.

(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.

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 Rook MST Cap

Locking Ring
MODEL BD-700-1A11 (BD-700)

Basic Issue: Feb 23/2015 700-46-5005

Revision 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-700-1A11 (BD-700)

Basic Issue: Feb 23/2015 700-46-5005

Revision 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-700-1A11 (BD-700)

Basic Issue: Feb 23/2015 700-46-5005

Revision 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.
MODEL BD-700-1A11 (BD-700)

Basic Issue: Feb 23/2015 700-46-5005

Revision 02: Jun 18/2015 Page 10 of 14

Figure 4: OMS Main Page

(2) Do the connectivity test on the Wardrobe OMS port as follows:

(a) Connect PMAT, using RJ45 LAN cable, to Wardrobe OMS port receptacle.

Figure 5: IMS Wardrobe Connections

(b) Power on PMAT and select ON-BOARD MAINT.SYS. tab.

(c) Click IP UTILITY button.
MODEL BD-700-1A11 (BD-700)

Basic Issue: Feb 23/2015 700-46-5005

Revision 02: Jun 18/2015 Page 11 of 14

(d) From pop up window, check Wardrobe and SUBMIT.

(e) Click on OMS Wardrobe button.

(f) Observe OMS main page display on the PMAT.

(g) If PMAT displays the OMS main page, as shown in Figure 4, the test

passes.

(h) Test completed - Disconnect PMAT from the Wardrobe OMS port.

(3) Do the connectivity test on the AFDX NETWORK A and AFDX NETWORK B

port. Refer to Figure 5. Refer to TASK 46-31-000-970-807.

(4) Test for OMS access via cabin network to verify successful disconnection as

follows:

(a) Connect LAN cable to CES-MCE RJ45 port at the rear of copilot seat.

(b) On PMAT, select ON-BOARD MAINT.SYS. tab.

(c) Click the IP Utility button.

(d) From the pop up window, select AFT and SUBMIT.

Figure 6: IP Selection Tool

(e) Click on the OMS AFT button.
MODEL BD-700-1A11 (BD-700)

Basic Issue: Feb 23/2015 700-46-5005

Revision 02: Jun 18/2015 Page 12 of 14

(f) Observe network problem report; “You’re not connected to a network” on

Internet Explorer. See Figure 7.

NOTE: PMAT, Part No. G700-454501-5, displays message shown in

Figure 7. If you use a different PMAT version, the message may

be different.

Figure 7: Disconnection Confirmation

(5) Do the operational test for the IMS. Refer to TASK 46-31-00-710-801.

E. Close-out

(1) Install pilot’s side panel. Refer to TASK 25-12-05-400-801.

(2) Install the pilot’s seat. Refer to TASK 25-11-00-400-801.

(3) Remove external ac power. Refer to TASK 24-41-00-861-802.

(4) Remove all tools, equipment and unwanted materials from the aircraft.

F. Recording

When this Service Bulletin is completed, make an entry in the aircraft log to

indicate whether only Part A was carried out or Part A and Part B were carried

out. 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
MODEL BD-700-1A11 (BD-700)

Basic Issue: Feb 23/2015 700-46-5005

Revision 02: Jun 18/2015 Page 13 of 14

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 Aerospace Parts Services, Montreal:

NEW

PART NO.

QTY ITEM USED

PART NO.

INSTRUCTIONS -

DISPOSITION

APMOPTION_5XX

XXXXXXXXXXX 1

APM Option file

(See NOTE 2)

- -

M23053/5-106-9 2 in Shrink Tube - -

MS27488−22 4 Sealing Plug - -

N344-8005 10 in Shrink Tube - -

NOTES: 1. The part number for the item listed above is subject to change

without revision to this Service Bulletin. In case of discrepancy

between this list and any other list, the Illustrated Parts Catalog

prevails and shall be used to determine the latest part number.

2. Refer to Paragraph 1, Planning Information, Note 4.
MODEL BD-700-1A11 (BD-700)

Basic Issue: Feb 23/2015 700-46-5005

Revision 02: Jun 18/2015 Page 14 of 14

C. Material

The materials that follow are necessary to do this Service Bulletin. These can be

purchased from a local supplier. Bombardier Aerospace does not pay for these

consumables.

DESCRIPTION PART

No./NAME

SPECIFICATION QUANTITY SUPPLIER

(See Note)

Tape, Lacing A-A-52081 - As

Necessary

Code: A

Tie Rap,

Plastic

B0816019 - As

Necessary

Code: A

NOTES: 1. Refer to the table that follows for each supplier’s 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.

SUPPLIERS ADDRESSES BY CODES

Code: A

Commercially Available

D. Publications

The publication that follows is required after this Service Bulletin has been

incorporated.

– BD-700-1A11 Flight Crew Operating Manual, GL 5000 GVFD FCOM, Revision

14 dated May 11/2015 or later revisions as applicable.
SERVICE BULLETIN EVALUATION FORM

(Your ideas will help us provide better bulletins)

SERVICE BULLETIN: 700-46-5005 ISSUE: Rev. 02 DATED: Jun 18/2015

TITLE: Modification – Information Management System – Deactivation of CES Ethernet

Interface to Cabin Printer

In an effort to improve the quality of our technical communications, we are replacing

the standard Service Bulletin Evaluation Form with an on-line Service Bulletin

Survey and we are requesting your feedback. Please take a moment to fill out our

easy on-line Service Bulletin survey:

(6) http://csefeedback.aero.bombardier.com
SERVICE BULLETIN INCORPORATION SHEET – “700-46-5005”

B

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B

A

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DIE

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Upon completion of the Service Bulletin, please fill-in, fax to

(514) 855-8798 or e-mail to Fracas at fracas.montreal@aero.bombardier.com

If your aircraft is registered on CAMP and you are reporting to them,

please do not send the incorporation sheet to Bombardier. If your aircraft

is on another tracking system, please contact Bombardier to make

arrangements for automated data submission.

 COMPLIED WITH

Service Bulletin

Number

Rev. * Parts

Completed

YES NO N/A Remarks/Reason

700-46-5005 02 PART A

“ “ PART B

- - -

Actual hours to accomplish Service Bulletin:

* NOTES: 1. Where the Service Bulletin is divided into a number of parts (e.g., PARTS A,

B, C, D, etc.) which can be carried out separately, indicate only those parts

completed at this time.

2. For repetitive checks (usually PART A) only the initial check should be

reported unless otherwise stated in the Service Bulletin.

3. When more than one part is carried out at the same time, each part should be

reported.

Aircraft Serial No. Aircraft Reg. No.

Airframe Hours: Airframe Landings

S.B. Incorporation date Service Order No.

(dd/mm/yy)

Facility Incorporating S.B.

Name Signature Date

Signature not required if sent by E-Mail (dd/mm/yy)
-- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- --

Bombardier Business Aircraft Customer Services (BBACS)

P.O. Box 6087, Station Centre-ville

Montreal, Québec, Canada H3C 3G9

Attention: Customer Support Department, Maintenance Engineering

-- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- --