EMS Technologies Canada JETWAVE KA Band Aviation Radio User Manual 23 15 29R001

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Honeywell International Inc.

400 Maple Grove Road

Ottawa, Ontario

Canada K2V 1B8

CAGE: 38473

Telephone: (800) 601-3099 (Toll Free U.S.A./Canada)

Telephone: +1-(602) 365-3099 (International Direct)

Website: www.myaerospace.com

Page T-1

Publication Number D201401000049, Revision 1 Initial 16 Jan 2015

Revised 16 Sep 2015

23-15-29

This document contains technical data and is subject to U.S. export regulations. These commodities,

technology, or software were exported from the United States in accordance with the export administration

regulations. Diversion contrary to U.S. law is prohibited.

ECCN: 7E994

JetWave™ System

System Description and Installation Manual

This guide provides procedures for installation, configuration, and operation of the equipment listed

below.

Model Part Number

JetWave™ System Class A Forced Air KRFU 90401028-001

JetWave™ System Class A Conduction Cooled KRFU, Version 1 90401028-002

JetWave™ System Class A Conduction Cooled KRFU, Version 2 90401028-003

JetWave™ System Class B Forced Air KRFU 90401027-001

JetWave™ System Class B Conduction Cooled KRFU, Version 1 90401027-002

JetWave™ System Class B Conduction Cooled KRFU, Version 2 90401027-003

JetWave™ System Class A Conduction Cooled KRFU, Version 2, FMA 90401027-004

JetWave™ System Class A Forced Air KRFU, Version 2, FMA 90401027-005

A791 Radome Package 90400017-XXX

Non-A791 Radome Package 90400016-XXX

Legal Notice

Export Control

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Proprietary Information

Honeywell – Confidential

THIS COPYRIGHTED WORK AND ALL INFORMATION ARE THE PROPERTY OF HONEYWELL

INTERNATIONAL INC., CONTAIN TRADE SECRETS AND MAY NOT, IN WHOLE OR IN PART, BE USED,

DUPLICATED, OR DISCLOSED FOR ANY PURPOSE WITHOUT PRIOR WRITTEN PERMISSION OF

Honeywell Materials License Agreement

The documents and information contained herein (“the Materials”) are the proprietary data of Honeywell

International Inc. These Materials are provided for the exclusive use of Honeywell Service Centers;

Honeywell-authorized repair facilities; operators of Honeywell aerospace products subject to an applicable

product support agreement, their wholly owned-subsidiaries or a formally designated third party service provider;

and direct recipients of Materials from Honeywell’s Aerospace Technical Publication Distribution. The terms and

conditions of this License Agreement govern your use of these Materials, except to the extent that any terms

and conditions of another applicable agreement with Honeywell regarding the operation, maintenance, or repair

of Honeywell aerospace products conflict with the terms and conditions of this License Agreement, in which

case the terms and conditions of the other agreement will govern. However, this License Agreement will govern

in the event of a conflict between its terms and conditions and those of a purchase order or acknowledgment.

1. License Grant - If you are a party to an applicable product support agreement, a Honeywell Service Center

agreement, or an authorized repair facility agreement, Honeywell hereby grants you a limited, non-exclusive

license to use these Materials to operate, maintain, or repair Honeywell aerospace products only in accordance

with that agreement.

If you are a direct recipient of these Materials from Honeywell’s Aerospace Technical Publication Distribution

and are not a party to an agreement related to the operation, maintenance or repair of Honeywell aerospace

products, Honeywell hereby grants you a limited, non-exclusive license to use these Materials to maintain or

repair the subject Honeywell aerospace products only at the facility to which these Materials have been shipped

("the Licensed Facility"). Transfer of the Materials to another facility owned by you is permitted only if the original

Licensed Facility retains no copies of the Materials and you provide prior written notice to Honeywell.

2. Rights In Materials - Honeywell retains all rights in these Materials and in any copies thereof that are not

expressly granted to you, including all rights in patents, copyrights, trademarks, and trade secrets. No license

to use any Honeywell trademarks or patents is granted under this License Agreement.

3. Confidentiality - You acknowledge that these Materials contain information that is confidential and proprietary

to Honeywell. You agree to take all reasonable efforts to maintain the confidentiality of these Materials.

4. Assignment And Transfer - This License Agreement may be assigned to a formally designated service

designee or transferred to a subsequent owner or operator of an aircraft containing the subject Honeywell

aerospace products. However, the recipient of any such assignment or transfer must assume all of your

obligations under this License Agreement. No assignment or transfer shall relieve any party of any obligation

that such party then has hereunder.

5. Copies of Materials - Unless you have the express written permission of Honeywell, you may not make or

permit making of copies of the Materials. Notwithstanding the foregoing, you may make copies of only portions

of the Material for your internal use. You agree to return the Materials and any copies thereof to Honeywell upon

the request of Honeywell.

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6. Term - This License Agreement is effective until terminated as set forth herein. This License Agreement will

terminate immediately, without notice from Honeywell, if you fail to comply with any provision of this License

Agreement or will terminate simultaneously with the termination or expiration of your applicable product support

agreement, authorized repair facility agreement, or your formal designation as a third party service provider.

Upon termination of this License Agreement, you will return these Materials to Honeywell without retaining any

copies and will have one of your authorized officers certify that all Materials have been returned with no copies

retained.

7. Remedies - Honeywell reserves the right to pursue all available remedies and damages resulting from a

breach of this License Agreement.

8. Limitation of Liability - Honeywell does not make any representation regarding the use or sufficiency of the

Materials. THERE ARE NO OTHER WARRANTIES, WHETHER WRITTEN OR ORAL, EXPRESS, IMPLIED

OR STATUTORY, INCLUDING, BUT NOT LIMITED TO, (i) WARRANTIES ARISING FROM COURSE OF

PERFORMANCE, DEALING, USAGE, OR TRADE, WHICH ARE HEREBY EXPRESSLY DISCLAIMED, OR (ii)

WARRANTIES AGAINST INFRINGEMENT OF INTELLECTUAL PROPERTY RIGHTS OF THIRD PARTIES,

EVEN IF HONEYWELL HAS BEEN ADVISED OF ANY SUCH INFRINGEMENT. IN NO EVENT WILL

HONEYWELL BE LIABLE FOR ANY INCIDENTAL DAMAGES, CONSEQUENTIAL DAMAGES, SPECIAL

DAMAGES, INDIRECT DAMAGES, LOSS OF PROFITS, LOSS OF REVENUES, OR LOSS OF USE, EVEN IF

INFORMED OF THE POSSIBILITY OF SUCH DAMAGES. TO THE EXTENT PERMITTED BY APPLICABLE

LAW, THESE LIMITATIONS AND EXCLUSIONS WILL APPLY REGARDLESS OF WHETHER LIABILITY

ARISES FROM BREACH OF CONTRACT, WARRANTY, TORT (INCLUDING BUT NOT LIMITED TO

NEGLIGENCE), BY OPERATION OF LAW, OR OTHERWISE.

9. Controlling Law - This License shall be governed and construed in accordance with the laws of the State of

New York without regard to the conflicts of laws provisions thereof. This license sets forth the entire agreement

between you and Honeywell and may only be modified by a writing duly executed by the duly authorized

representatives of the parties.

Safety Advisory

WARNING: BEFORE THE MATERIALS CALLED OUT IN THIS PUBLICATION ARE USED, KNOW THE

HANDLING, STORAGE AND DISPOSAL PRECAUTIONS RECOMMENDED BY THE MANUFACTURER OR

SUPPLIER. FAILURE TO OBEY THE MANUFACTURERS’ OR SUPPLIERS’ RECOMMENDATIONS CAN

RESULT IN PERSONAL INJURY OR DISEASE.

This publication describes physical and chemical processes which can make it necessary to use chemicals,

solvents, paints, and other commercially available materials. The user of this publication must get the Material

Safety Data Sheets (OSHA Form 174 or equivalent) from the manufacturers or suppliers of the materials to be

used. The user must know the manufacturer/supplier data and obey the procedures, recommendations, warnings

and cautions set forth for the safe use, handling, storage, and disposal of the materials.

Warranty/Liability Advisory

WARNING: HONEYWELL ASSUMES NO RESPONSIBILITY FOR ANY HONEYWELL EQUIPMENT WHICH

IS NOT MAINTAINED AND/OR REPAIRED IN ACCORDANCE WITH HONEYWELL’S PUBLISHED

INSTRUCTIONS AND/OR HONEYWELL’S FAA/SFAR 36 REPAIR AUTHORIZATION. NEITHER DOES

HONEYWELL ASSUME RESPONSIBILITY FOR SPECIAL TOOLS AND TEST EQUIPMENT FABRICATED BY

COMPANIES OTHER THAN HONEYWELL.

WARNING: INCORRECTLY REPAIRED COMPONENTS CAN AFFECT AIRWORTHINESS OR DECREASE

THE LIFE OF THE COMPONENTS. INCORRECTLY FABRICATED SPECIAL TOOLING OR TEST

EQUIPMENT CAN RESULT IN DAMAGE TO THE PRODUCT COMPONENTS OR GIVE UNSATISFACTORY

RESULTS.

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JetWave™ System

Honeywell is a registered trademark of Honeywell International Inc.

All other marks are owned by their respective companies.

JetWave™ System, System Description, Installation, and Maintenance Manual

Document Number: D201401000049, Revision 1

16 Sep 2015

Our products are under continuous research and development. Any information may therefore be changed

without prior notice. Honeywell reserves the right to make improvements or changes in the product described

in this manual at any time without notice. While reasonable efforts have been made in the preparation of this

document to assure its accuracy, Honeywell assumes no liability resulting from any errors or omissions in this

document, or from the use of the information contained herein.

Honeywell International Inc.

400 Maple Grove Road

Ottawa, Ontario, K2V 1B8

Canada



Reception: 613-591-9064

Product Support: Aerospace Technical Support

1-855-808-6500 (U.S. and Canada) or +1-602-365-6500 (International)

E-mail: AeroTechSupport@Honeywell.com

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TRANSMITTAL INFORMATION

TO THE HOLDERS OF JETWAVE™ SYSTEM SDIM, ATA NO. 23-15-29 (PUB. NO. D201401000049), ISSUED

FOR USE IN SUPPORT OF THE FOLLOWING:

Table TI-1 shows the applicable components.

Revision History

Table TI-2 shows the revision history of this SDIM.

This revision is a full replacement. All changed pages have a new date. Revision bars identify the changed data.

Remove and discard all pages of the manual and replace them with the attached pages. Write the revision

number, revision date, and replacement date on the Record of Revisions page.

The table of highlights tells users what has changed as a result of the revision. The table consists of three

columns.

Table TI-1. Applicable Components

Component PN Nomenclature

90401028-001 JetWave™ System Class A Forced Air KRFU

90401028-002 JetWave™ System Class A Conduction Cooled KRFU, Version 1

90401028-003 JetWave™ System Class A Conduction Cooled KRFU, Version 2

90401027-001 JetWave™ System Class B Forced Air KRFU

90401027-002 JetWave™ System Class B Conduction Cooled KRFU, Version 1

90401027-003 JetWave™ System Class B Conduction Cooled KRFU, Version 2

90401027-004 JetWave™ System Class A Conduction Cooled KRFU, Version 2, FMA

90401027-005 JetWave™ System Class A Forced Air KRFU, Version 2, FMA

90400017-XXX A791 Radome Package

90400016-XXX Non-A791 Radome Package

Table TI-2. Revision History

Revision Revision Date

0 16 Jan 2015

1 16 Sep 2015

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The Task/Page column identifies the blocks of changed information, such as a task, subtask, graphic, or parts

list, and the page on which that block starts. Revision marks, when provided, identify the location of the change

within the block.

The Description of Change column tells about the change or changes within each block. The description of

change is often preceded by a paragraph or figure reference that applies to the block of information.

The Effectivity column tells the user the part number(s) to which the block of information applies. The default

value for this column is “All.” “All” means that the block applies to all parts.

Table of Highlights

Page Description of Change Effectivity

All Global Change: The editorial changes and data that were

moved or reformatted are not identified with revision bars. All

All Global Change: Some paragraphs, tables, and figures have

been renumbered and are not identified with revision bars.

All

All Global Change: Added Component PNs 90401027-004 and

90401027-005. All

All Due to the extent and complexity of changes made in this

revision, individual changes are not detailedDQGUHYLVLRQEDUV

DUHQRWXVHG.

All

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RECORD OF REVISIONS

When revisions are received, insert revised pages, record the date, and initial.

Revision Number Issue Date Date Inserted Inserted by (initial)

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RECORD OF TEMPORARY REVISIONS

Instructions on each page of a temporary revision tell you where to put the pages in your manual. Remove

temporary revision pages only when discard instructions are given. For each temporary revision, put the

applicable data in the record columns on this page.

Definition of Status column: TR may be active, incorporated, or deleted. “Active” is entered by the holder of

manual. “Incorporated” means a TR has been incorporated into the manual and includes the revision number

of the manual when the TR was incorporated. “Deleted” means a TR has been replaced by another TR, a TR

number will not be issued, or a TR has been deleted.

Temporary

Revision

Number Status Page

Number Issue

Date Date Put in

Manual By

Date

Removed

From Manual By

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SERVICE BULLETIN LIST

Service Bulletin

Number Subject Manual Rev.

Number Manual Rev.

Date

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Title

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Transmittal Information

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Service Bulletin List

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JetWave AES System Configuration

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Appendix A: Specifications

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Appendix B: MIB / SNMP

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Appendix C: Installation Information Sheet

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Appendix D: Installation Checklist

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TABLE OF CONTENTS

Title Page

INTRODUCTION

1. How to Use This Manual ..................................................................................................INTRO-1

A. General .......................................................................................................................INTRO-1

B. Observance of Manual Instructions ............................................................................INTRO-1

C. Symbols ......................................................................................................................INTRO-1

D. Units of Measure ........................................................................................................INTRO-2

E. Illustration ...................................................................................................................INTRO-2

2. Scope ...............................................................................................................................INTRO-2

3. Part Numbers ...................................................................................................................INTRO-2

4. Organization .....................................................................................................................INTRO-2

5. Customer Support ............................................................................................................INTRO-3

A. Honeywell Aerospace Online Technical Publications Website ...................................INTRO-3

B. Honeywell Aerospace Contact Team .........................................................................INTRO-3

6. References .......................................................................................................................INTRO-3

A. Honeywell/Vendor Publications ..................................................................................INTRO-3

B. Other Publications ......................................................................................................INTRO-3

7. Precautions.......................................................................................................................INTRO-4

8. Acronyms and Abbreviations............................................................................................INTRO-4

A. General .......................................................................................................................INTRO-4

DESCRIPTION AND OPERATION

1. Overall JetWave™ System Architecture ...................................................................................1-1

A. JetWave™ System LRUs ....................................................................................................1-1

B. JetWave™ System LRU Leading Particulars .....................................................................1-2

2. Honeywell JetWave™ System Architecture ..............................................................................1-7

A. Outside Antenna Equipment ................................................................................................1-8

B. KRFU ...................................................................................................................................1-9

C. KANDU ................................................................................................................................1-9

D. Modman ..............................................................................................................................1-9

E. APM ...................................................................................................................................1-10

3. Honeywell Implementation ......................................................................................................1-10

4. JetWave™ System Modes of Operation .................................................................................1-11

A. Power On Mode .................................................................................................................1-11

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B. System Initialization Mode ................................................................................................1-11

C. Normal Operating Mode ....................................................................................................1-11

D. Critical Fault Mode ............................................................................................................1-12

E. Data Load Mode ................................................................................................................1-12

F. Commanded Mode ............................................................................................................1-12

5. About Inmarsat Services .........................................................................................................1-12

INSTALLATION

1. Overview ...................................................................................................................................2-1

A. JetWave™ System Components ........................................................................................2-1

B. Installation Procedure Overview for the JetWave™ System ...............................................2-1

2. Certification and Approvals .......................................................................................................2-1

3. On-ground Testing and Commissioning....................................................................................2-1

A. Testing and Commissioning Process with Restrictions .......................................................2-2

4. JetWave™ System LRU Installation .........................................................................................2-3

A. Maintenance Panel ............................................................................................................. 2-3

B. Modman ..............................................................................................................................2-3

C. APM ....................................................................................................................................2-5

D. KANDU ...............................................................................................................................2-6

E. KRFU ..................................................................................................................................2-9

F. KRFU Thermal Pad Kit ......................................................................................................2-10

G. Deleted ............................................................................................................................. 2-11

H. Deleted ..............................................................................................................................2-11

I. Tail Mount Antenna ............................................................................................................2-11

J. OAE TMA Installation Procedure .......................................................................................2-16

K. TMA Alignment ..................................................................................................................2-21

L. TMA Human Exposure to RF EM Fields ...........................................................................2-21

M. Fuselage Mount Antenna .................................................................................................2-22

N. FMA Installation Procedure ...............................................................................................2-30

O. FMA Alignment ................................................................................................................. 2-36

P. FMA Human Exposure to RF EM Fields ...........................................................................2-36

Q. TMA and FMA Antenna Alignment Procedure ..................................................................2-37

5. Electrical Installation................................................................................................................2-40

6. Cabling Requirements.............................................................................................................2-40

7. Drawings and Diagrams..........................................................................................................2-41

JETWAVE™ AES SYSTEM CONFIGURATION

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1. Provisioning of User Services....................................................................................................3-1

2. About Installation and Registration............................................................................................3-2

3. Product Support Services..........................................................................................................3-2

A. Customer Support Overview ...............................................................................................3-2

B. Customer Support Contacts: ...............................................................................................3-3

4. AES Configuration Data ............................................................................................................3-3

A. Aircraft ID .............................................................................................................................3-4

B. View AES System Configurations .......................................................................................3-5

C. Regulatory Log Configuration Parameters ..........................................................................3-5

D. Aircraft Service Configuration ..............................................................................................3-5

5. ARINC 615A Software Dataload Process .................................................................................3-7

A. Introduction ..........................................................................................................................3-7

B. System Requirements .........................................................................................................3-7

C. Procedure ............................................................................................................................3-7

D. JetWave™ Data Load Procedure ......................................................................................3-10

6. Cable Calibration.....................................................................................................................3-14

7. Post Installation System Checkout Procedures.......................................................................3-15

A. General Overview ..............................................................................................................3-15

B. System Power Supply .......................................................................................................3-15

C. ARINC 429 Input Interface Testing ...................................................................................3-22

D. Manual Steering of the Antenna ........................................................................................3-22

E. Antenna Calibration Testing ..............................................................................................3-23

F. Cable Calibration Testing ..................................................................................................3-23

G. ARINC 615 Data Load ......................................................................................................3-24

H. System Available (Cockpit Control Panel) Output .............................................................3-24

I. Data Link Available (Control Panel) Output ........................................................................3-24

J. Network Status ...................................................................................................................3-24

K. EMC Interference to Other Systems ..................................................................................3-25

8. Post-Installation Troubleshooting ............................................................................................3-26

A. System Fails Post-installation Checks ...............................................................................3-26

B. Incorrect Navigation Data ..................................................................................................3-26

C. System Will Not Connect to the Network ..........................................................................3-27

D. Connectivity of Each Ethernet Port ...................................................................................3-27

9. Maintenance and Repair .........................................................................................................3-29

A. Maintenance Requirements ...............................................................................................3-29

B. Continued Airworthiness, FAR 25.1529 ............................................................................3-29

C. Airworthiness Limitations ...................................................................................................3-30

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D. General Instructions for Inspection ...................................................................................3-30

E. Electrical and Mechanical Inspection and Check ..............................................................3-30

F. Scheduled Maintenance and Inspections ..........................................................................3-30

G. Unscheduled Maintenance ...............................................................................................3-31

H. Repair Requirements ........................................................................................................3-32

10. Troubleshooting.....................................................................................................................3-32

A. Accessing the Maintenance Interface ...............................................................................3-33

B. Checking Status Information .............................................................................................3-34

C. Downloading LRU Logs ....................................................................................................3-36

D. System Dataload Failure ...................................................................................................3-39

11. Network Monitoring ...............................................................................................................3-39

12. System Reset........................................................................................................................3-39

A. Electrical and Mechanical Inspection and Check ..............................................................3-39

B. Instructions for Continued Airworthiness ..........................................................................3-39

C. Visual Inspection and Check .............................................................................................3-40

13. JetWave™ System Fault Codes ...........................................................................................3-41

A. BITE Philosophy ................................................................................................................ 3-41

B. LRU Codes ........................................................................................................................ 3-46

C. L1 Codes ...........................................................................................................................3-46

D. L2 Codes ...........................................................................................................................3-48

E. L3 Codes ...........................................................................................................................3-53

14. SNMP..................................................................................................................................3-107

APPENDIX A

1. RTCA/DO-160G Environmental Characteristics .......................................................................A-1

A. Modman ..............................................................................................................................A-1

B. APM ....................................................................................................................................A-3

C. KANDU ...............................................................................................................................A-4

D. KRFU ..................................................................................................................................A-6

E. TMA .....................................................................................................................................A-8

F. FMA ...................................................................................................................................A-10

APPENDIX B

1. MIB Objects...............................................................................................................................B-1

A. MIB Structure ......................................................................................................................B-1

B. Detailed MIB Definition ........................................................................................................B-2

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APPENDIX C

1. Aircraft Information Sheet......................................................................................................... C-1

2. JetWave™ AES Subsystem Components................................................................................ C-1

A. JetWave™ AES OAE - FMA/TMA Installation Information Sheet ...................................... C-1

B. JetWave™ AES KANDU Installation Information Sheet ..................................................... C-1

C. JetWave™ AES KRFU Installation Information Sheet .......................................................C-1

D. JetWave™ AES Modman Installation Information Sheet ...................................................C-2

E. JetWave™ AES APM Installation Information Sheet ......................................................... C-2

APPENDIX D

1. Installation Checklist................................................................................................................. D-1

A. OAE-TMA Checklist ............................................................................................................ D-1

B. A791 Based OAE-FMA with the AIM Checklist ..................................................................D-6

C. Non-A791 Based OAE-FMA with the LAIM Checklist ......................................................D-10

APPENDIX E

1. List of Airframe Specific Information Required for JetWave™ System Configuration .............. E-1

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LIST OF FIGURES

Figure Description Page

Figure INTRO-1. Symbols ....................................................................................................INTRO-1

Figure 1-1.Ka-Band System.............................................................................................................1-1

Figure 1-2. JetWave™ System Block Diagram ....................................................................1-8

Figure 2-1. KRFU Thermal Pads .......................................................................................2-11

Figure 2-2. TMA Installation Location ................................................................................2-14

Figure 2-3. TMA Assembly Isometric View ........................................................................2-15

Figure 2-4. KRFU and TMA Interconnect Arrangement .....................................................2-16

Figure 2-5. TMA RF TX J3 and RF RX J4 Interface Connector and Bonding Strap Locations

2-17

Figure 2-6. WR42 Waveguide to 2.92 mm Coaxial Connector Adapter ............................2-18

Figure 2-7. KRFU Bonding Strap Arrangement .................................................................2-19

Figure 2-8. View of H Plane and E Plane Bends ...............................................................2-20

Figure 2-9. FMA Install Location ........................................................................................2-26

Figure 2-10. Typical Ground Strap Arrangement for A791 Compliant Fittings ....................2-27

Figure 2-11. Aircraft Coordinate System Orientation and Fitting Layout .............................2-27

Figure 2-12. AIM Assembly Placement on Aircraft ..............................................................2-28

Figure 2-13. LAIM Assembly ................................................................................................2-29

Figure 2-14. Radome Skirt Fairing and LAIM Assembly Position on Aircraft .......................2-30

Figure 2-15. FMA Assembly ................................................................................................2-31

Figure 2-16. FMA Assembly Lifting Fixture Removal ...........................................................2-32

Figure 2-17. View of H Plane and E Plane Bends ...............................................................2-34

Figure 2-18. A791 Based AIM Assembly with FMA and KRFU Placement on Aircraft ........2-35

Figure 2-19. LAIM Assembly with FMA and KRFU Placement on Aircraft ..........................2-35

Figure 2-20. Radome Assembly Mounted on Radome Skirt Fairing (LAIM) ........................2-36

Figure 2-21. GUI Login Page ...............................................................................................2-38

Figure 2-22. GUI Calibrate Antenna Alignment Page ..........................................................2-39

Figure 2-23. GUI Antenna Alignment Calibration Page Extract ...........................................2-40

Figure 2-24.Modman Outline and Installation Drawing (Sheet 1 of 4) 2-41

Figure 2-25.APM Outline and Installation Drawing (Sheet 1 of 2) 2-49

Figure 2-26.KANDU Outline and Installation Drawing (Sheet 1 of 3) 2-53

Figure 2-27.KRFU, Conduction-Cooled 1, Outline and Installation Drawing (Sheet 1 of 3) 2-59

Figure 2-28.KRFU, Conduction-Cooled 2, Outline and Installation Drawing (Sheet 1 of 3) 2-65

Figure 2-29.KRFU, Forced Air Cooled, Outline and Installation Drawing (Sheet 1 of 3) 2-71

Figure 2-30.TMA Outline and Installation Drawing (Sheet 1 of 4) 2-77

Figure 2-31.FMA Outline and Installation Drawing (Sheet 1 of 12) 2-85

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Figure 2-32.Fuselage Mount Radome Outline and Installation Drawing (Sheet 1 of 6) 2-109

Figure 2-33.JetWave™ System Interconnect Diagram - TMA (Sheet 1 of 10) 2-121

Figure 2-34.JetWave™ System Interconnect Diagram - FMA (KRFU Inside Aircraft Fuselage) (Sheet

1 of 8) 2-141

Figure 2-35.JetWave™ System Interconnect Diagram - Boeing Specific FMA (External KRFU) (Sheet

1 of 8) 2-157

Figure 2-36.JetWave™ System Interconnect Diagram - A350 FMA (Sheet 1 of 10) 2-173

Figure 3-1. AES User Level, Aircraft ID Display/Update Information Page .........................3-5

Figure 3-2. AES Configuration Tool .....................................................................................3-6

Figure 3-3. AIT F-SIM-LDR ARINC 615A Dialog Box .......................................................3-10

Figure 3-4. AIT F-SIM-LDR ARINC 615A Find Dialog Box ...............................................3-11

Figure 3-5. AIT F-SIM-LDR ARINC 615A Data Upload Information Dialog Box ...............3-13

Figure 3-6. AES GUI Login Page ......................................................................................3-16

Figure 3-7. AES Home and Status Info Page ....................................................................3-17

Figure 3-8. View Configuration Files Page ........................................................................3-18

Figure 3-9. Health Statuses (excerpt), AES Summary and Link Statuses ........................3-19

Figure 3-10. AES Modman and Manufacturing Information Page .......................................3-20

Figure 3-11. Aircraft Tail Number Page ...............................................................................3-20

Figure 3-12. Discrete I/O State ............................................................................................3-21

Figure 3-13. Aircraft Statuses ..............................................................................................3-22

Figure 3-14. Manual Antenna Steering ................................................................................3-23

Figure 3-15. Calibrate Transmit Cable Status Page ............................................................3-24

Figure 3-16. Network Statuses ............................................................................................3-25

Figure 3-17. Contents of Aircraft Services Configuration File .............................................3-28

Figure 3-18. AES GUI Login Page ......................................................................................3-33

Figure 3-19. JetWave™ Logout Page .................................................................................3-34

Figure 3-20. JetWave™ Summary and Link Status (Sheet 1 of 2) ......................................3-35

Figure 3-18. JetWave™ Summary and Link Status (Sheet 2 of 2) ......................................3-36

Figure 3-19. JetWave™ Fault Log Download Configuration Page ......................................3-37

Figure 3-20. JetWave™ Fault Log Data ..............................................................................3-38

Figure 3-21. JetWave™ Fault Log Download Page ............................................................3-38

Figure 3-22. Bite Hierarchy ..................................................................................................3-42

Figure 3-23. AES and LRU Controller Interaction ...............................................................3-43

Figure B-1. MIB Object Structure .........................................................................................B-1

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LIST OF TABLES

Table Description Page

Table 1-1.JetWave™ System LRUs ...............................................................................................1-1

Table 1-2.Modman Leading Particulars ..........................................................................................1-2

Table 1-3.APM Leading Particulars ................................................................................................1-3

Table 1-4.KANDU Leading Particulars ...........................................................................................1-3

Table 1-5.KRFU Leading Particulars ..............................................................................................1-4

Table 1-6.TMA Leading Particulars ................................................................................................1-6

Table 1-7.FMA Leading Particulars ................................................................................................1-6

Table 1-8.B757 FMA Radome Leading Particulars ........................................................................1-7

Table 2-1.ARINC 600 Connectors ..................................................................................................2-4

Table 2-2.Modman Cable Loss Values ...........................................................................................2-5

Table 2-3.Thermal Pad Kit Contents .............................................................................................2-10

Table 2-4.Special Tools for TMA Installation ................................................................................2-12

Table 2-5.TMA Installation Kits .....................................................................................................2-14

Table 2-6.Special Tools for FMA Installation ................................................................................2-23

Table 2-7.FMA installation Kits .....................................................................................................2-24

Table 2-8.Cabling Requirements ..................................................................................................2-41

Table 3-1.ARINC 429 Label List .....................................................................................................3-3

Table 3-2.Data Sets ........................................................................................................................3-8

Table 3-11.Modman LED Status Indications ................................................................................3-15

Table 3-12.Scheduled Maintenance .............................................................................................3-31

Table 3-13.Unscheduled Maintenance .........................................................................................3-32

Table 3-14.Modman LED Status Indications ................................................................................3-32

Table 3-15.L1 Codes ....................................................................................................................3-46

Table 3-16.L2 Codes – Module within a AES LRU .......................................................................3-48

Table 3-17.L2 Codes – Inter LRU Interfaces ................................................................................3-50

Table 3-18.L2 Codes – ARINC Discrete Interfaces ......................................................................3-51

Table 3-19.L2 Codes – User Interface ..........................................................................................3-53

Table 3-20.L3 Codes ....................................................................................................................3-53

Table B-1.Link Status Related Object ........................................................................................... B-2

Table B-2.Temporary Service Enumeration Types ........................................................................ B-2

Table B-3.Health Status Enumeration Type .................................................................................. B-3

Table B-4.Thermal State Enumeration Type ................................................................................. B-3

Table B-5.Discrete Input State Enumeration Type ....................................................................... B-3

Table B-6.Discrete Output State Enumeration Type ...................................................................... B-3

Table B-7.IRS Status Enumeration Type ...................................................................................... B-4

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Table B-8.Mute Reason Enumeration Type ...................................................................................B-4

Table B-9.Satellite Handover Enumeration Type ...........................................................................B-5

Table B-10.Transmission State on Ground Enumeration Type ......................................................B-5

Table B-11.Port Link Status Enumeration Types ............................................................................B-5

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INTRODUCTION

1. How to Use This Manual

A. General

(1) This manual provides information about the installation of the AES Systems.

(2) Standard maintenance procedures that technicians must know are not given in this manual.

(3) This publication is written in agreement with the ATA Specification.

(4) Warnings, cautions, and notes in this manual give the data that follows:

• A WARNING gives a condition or tells personnel what part of an operation or

maintenance procedure, which if not obeyed, can cause injury or death.

• CAUTION gives a condition or tells personnel what part of an operation or maintenance

procedure, which if not obeyed, can cause damage to the equipment.

• A NOTE gives data, not commands. The NOTE helps personnel when they do the related

instruction.

(5) Warnings and cautions go before the applicable paragraph or step. Notes follow the

applicable paragraph or step.

B. Observance of Manual Instructions

(1) All personnel must carefully obey all safety, quality, operation, and shop procedures for the

unit.

(2) All personnel who operate equipment and do maintenance specified in this manual must

know and obey the safety precautions.

C. Symbols

(1) The symbols and special characters are in agreement with IEEE Publication 260 and IEC

Publication 27. Special characters in text are spelled out.

(2) The signal mnemonics, unit control designators, and test designators are shown in capital

letters.

(3) The signal names followed by an “*” show an active low signal.

(4) The symbols in Figure INTRO-1 show non-ionizing radiation hazard, ESDS, and moisture

sensitive devices.

Figure INTRO-1. Symbols

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D. Units of Measure

(1) Measurements, weights, temperatures, dimensions, and other values are expressed in the

USMS followed by the appropriate SI metric units in parentheses. Some standard tools or

parts such as drills, taps, bolts, nuts, etc. do not have an equivalent.

E. Illustration

(1) Supplemental illustrations use a suffix number to the basic figure number. For example, if

Figure 501-5 is used, it signifies that it is an illustration of the item identified by index number

5 in Figure 501.

(2) Illustrations with no specific designation are applicable to all units.

2. Scope

This manual provides detailed information for avionics technicians about the wiring and installation of

every component of the JetWave™ System. The installer is responsible for the approval and certification

of system components on the aircraft, and for the installation of wiring in the aircraft.

3. Part Numbers

This manual applies to the JetWave™ System components described below:

• 90401028-001 - JetWave™ System Class A Forced Air KRFU

• 90401028-002 - JetWave™ System Class A Conduction Cooled KRFU, Version 1

• 90401028-003 - JetWave™ System Class A Conduction Cooled KRFU, Version 2

• 90401027-001 - JetWave™ System Class B Forced Air KRFU

• 90401027-002 - JetWave™ System Class B Conduction Cooled KRFU, Version 1

• 90401027-003 - JetWave™ System Class B Conduction Cooled KRFU, Version 2

• 90401027-004 - JetWave™ System Class A Conduction Cooled KRFU, Version 2, FMA

• 90401027-005 - JetWave™ System Class A Forced Air KRFU, Version 2, FMA

• 90400017-XXX - A791 Radome Package

• 90400016-XXX - Non-A791 Radome Package.

4. Organization

This manual includes the following sections:

• INTRODUCTION - Information about the JetWave™ system

• DESCRIPTION AND OPERATION - General description and operation of the JetWave™ system

• INSTALLATION - Information and procedures for the installation of the JetWave™ system

• APPENDIX A - Environmental specifications for every piece of equipment available with the

JetWave™ system

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• APPENDIX B - JetWave™ system network performance data (MIB objects and SNMP traps)

• APPENDIX C - Installation information sheets

• APPENDIX D - Installation checklist

• APPENDIX E - Airframe specific information required for configuration.

5. Customer Support

A. Honeywell Aerospace Online Technical Publications Website

(1) Go to the Honeywell Online Technical Publications Website at http://www.myaerospace.com

• To download or see publications online

• To order a publication

• To tell Honeywell of a possible data error in a publication.

B. Honeywell Aerospace Contact Team

(1) If you do not have access to the Honeywell Technical Publications Website, or if you need to

speak to personnel about non-Technical Publication matters, the Honeywell Aerospace

Global Customer Care Center gives 24/7 customer service to Air Transport & Regional,

Business & General Aviation, and Defense & Space customers around the globe.

(2) Aerospace Technical Support

• Telephone: 855-808-6500 (Toll Free U.S.A./Canada)

• Telephone: +1-602-365-6500 (International).

6. References

A. Honeywell/Vendor Publications

(1) Related Honeywell publications in this manual are shown in the list that follows:

• Not Applicable

B. Other Publications

(1) These publications are standard references:

• The United States GPO Style Manual (available at

http://www.gpo.gov/fdsys/pkg/GPO-STYLEMANUAL-2008/content-detail.html)

• IEEE Std 260.1, Standard Letter Symbols for Units of Measurement (available from the

American National Standards Institute at http://www.ansi.org)

• ASME Y14.38, Abbreviations for Use on Drawings and Related Documents (available

from the American National Standards Institute at http://www.ansi.org)

• ASME Y14.5, Dimensioning and Tolerancing (available from the American National

Standards Institute at http://www.ansi.org)

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• ANSI/IEEE Std 91, Graphic Symbols for Logic Functions (available from the American

National Standards Institute at http://www.ansi.org)

• H4/H8 CAGE Codes (available from DLA Logistics Information Services at

http://www.logisticsinformationservice.dla.mil)

• IEEE 315/ANSI Y32.2, Graphic Symbols for Electrical and Electronics Diagrams

(available from the American National Standards InstituteInstitute at http://www.ansi.org)

• ARINC 791P1-2 Mark I Aviation Ku-Band and Ka-Band Satellite Communication System,

Part 1, Physical Installation and Aircraft Interfaces.

7. Precautions

When working with avionics and satellite communications equipment, be aware of the following warnings

and cautions.

CAUTION: TO PREVENT RADIO FREQUENCY OVEREXPOSURE, THE AREAS WHICH THE RISK

EXISTS IS BASED UPON THE LOCATION OF THE ANTENNA AND THE INSTALLED

HARDWARE END STOPS. TECHNICIANS WORKING IN CLOSE PROXIMITY OF THE

ANTENNA MUST BE PROTECTED BY DISABLING THE TRANSMITTER BEFORE THEY

APPROACH THAT AREA OF THE AIRCRAFT.

CAUTION: SERVICE TECHNICIANS MUST OBEY STANDARD SAFETY PRECAUTIONS, SUCH AS

WEARING SAFETY GLASSES, TO PREVENT PERSONAL INJURY WHILE INSTALLING

OR PERFORMING SERVICE ON THIS SYSTEM.

CAUTION: TURN OFF POWER BEFORE DISCONNECTING ANY TERMINAL FROM WIRING.

DISCONNECTING THE TERMINAL WITHOUT TURNING POWER OFF MAY CAUSE

VOLTAGE TRANSIENTS THAT CAN DAMAGE THE TERMINAL.

CAUTION: THIS EQUIPMENT INCLUDES ITEMS THAT ARE ELECTROSTATIC DISCHARGE

SENSITIVE DEVICES. ELECTROSTATIC DISCHARGE SENSITIVE DEVICES ARE

SUBJECT TO DAMAGE BY EXCESSIVE LEVELS OF VOLTAGE AND/OR CURRENT. THE

LOW-ENERGY SOURCE THAT MOST COMMONLY DESTROYS ESDS DEVICES IS THE

HUMAN BODY, WHICH, IN CONJUNCTION WITH NONCONDUCTIVE GARMENTS AND

FLOOR COVERINGS, GENERATES AND RETAINS STATIC ELECTRICITY. TO

ADEQUATELY PROTECT ESDS DEVICES, THE DEVICE AND EVERYTHING THAT

CONTACTS IT MUST BE BROUGHT TO GROUND POTENTIAL BY PROVIDING A

CONDUCTIVE SURFACE AND DISCHARGE PATHS. USE STANDARD INDUSTRY

PRECAUTIONS TO KEEP RISK OF DAMAGE TO A MINIMUM WHEN TOUCHING,

REMOVING, OR SERVICING THE EQUIPMENT.

8. Acronyms and Abbreviations

A. General

(1) The abbreviations are used in agreement with ASME Y14.38.

(2) Acronyms and non-standard abbreviations used in this publication are as follows:

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List of Acronyms and Abbreviations

Term Full Term

AC alternating current

ACM aeronautical core module

AES aircraft earth station

AISD airline information services domain

AIM aircraft interface mount

AIT Avionics Interface Technologies

AMIP open antenna to modem interface protocol

ANSI American National Standards Institute

APM aeronautical personality module

ARINC Aeronautical Radio, Incorporated

ASC antenna subsystem controller

ASME American Society of Mechanical Engineers

ATA Air Transport Association

AWG American wire gauge

BDC block down-converter

BIT built-in test

BITE built-in test equipment

BRS business and regional aviation segment

BUC block up-converter

C Celsius

CAGE commercial and government entity

CAT commercial air transport

CBIT continuous built-in test

CIR committed information rate

cm centimeter

CSU cabin services unit

dB decibel

DER designated engineering representative

DHCP dynamic host configuration protocol

DID data item description

DNS domain name system

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DP distribution partner

EMEA Europe, the Middle East, and Africa

ESDS electrostatic discharge sensitive

EST Eastern Standard Time

F Fahrenheit

FAA Federal Aviation Administration

FAR Federal Aviation Regulations

FMA fuselage mount antenna

FTP file transfer protocol

FXS foreign exchange subscriber

GHz gigahertz

GPO Government Printing Office

GPS global positioning system

GNSS global navigation satellite system

GSC global signaling channel

GTE ground transmit enable

GUI graphic user interface

HPA high-power amplifier

hPa hectopascal

HTP horizontal tail plane

Hz hertz

IEC International Electrotechnical Commission

IEEE Institute of Electrical and Electronics Engineers

IF intermediate frequency

IMU inertial measurement unit

in-lb inch-pound

I/O input and output

IP Internet protocol

IRS inertial reference system

IRU inertial reference unit

ISDN integrated services digital network

ISP Inmarsat service provider or internet service provider

List of Acronyms and Abbreviations (Cont)

Term Full Term

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Ka part of the radio frequency spectrum: 26.5 thru 40 GHz

KANDU Ku/Ka band aircraft network data unit

KRFU Ku/Ka band radio frequency unit

kg kilogram

Ku part of the radio frequency spectrum: 12 thru 18 GHz

LAIM local aircraft interface mount

LAN local area network

LED light emitting diode

LNA low noise amplifier

LRU line replaceable unit

LSAP loadable software airplane part

m meter

mΩmilliohm

mA milliampere

Mbps megabits per second

MCU modular concept unit

MHz megahertz

MIB management information base

MIR maximum information rate

mm millimeter

Modman modem manager

ms millisecond

NA not applicable

NEXT near end cross talk

Nm Newton meter

NMS network management system

OAE outside aircraft equipment

OID object identifier

OMT orthogonal mode transducer

Pa pascal

PCU position control unit

PIESD passenger information and entertainment services domain

List of Acronyms and Abbreviations (Cont)

Term Full Term

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PN part number

PODD passenger owned devices domain

POTS plain old telephone system

POST power-on self test

PSI pound per square inch

RF radio frequency

RFM radio frequency module

RMA return material authorization

RSSI receive signal strength indicator

RX receive

SAS satellite access station

SATCOM satellite communication

SDIM system description, and installation manual

SLA service level agreement

SNMP simple network management protocol

SSPP service subscriber plan

SVN secure virtual network

TMA tail mount antenna

TNC threaded Neill-Concelman

TX transmit

UNC unified coarse thread

USB universal serial bus

USMS United States Measurement System

VAC volt alternating current

VAR value added reseller

VDC volt direct current

VLAN virtual local area network

VoIP voice over Internet protocol

VPN virtual private network

VSAT very small aperture terminal

VTP vertical tail plane

WAN wide area network

List of Acronyms and Abbreviations (Cont)

Term Full Term

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WOW weight on wheels

List of Acronyms and Abbreviations (Cont)

Term Full Term

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DESCRIPTION AND OPERATION

1. Overall JetWave™ System Architecture

The JetWave™ SATCOM system supplies a broadband communication link that can be used to supply

data, video, and voice communications for passengers communications and entertainment. The AES

communicates to the SAS through a satellite as shown in Figure 1-1.

Figure 1-1. Ka-Band System

A Modman is provided within the AES to enable two-way communications. The forward channel provides

a communication path from the SAS to the AES. The return channel provides a communication path from

the AES to the SAS. The AES receives in the forward channel in K-band and transmits in the Ka-band.

The AES system provides the RF data link between the aircraft and the servicing satellite. An AES system

includes an antenna which is steered towards the servicing satellite by mechanical means.

The JetWave™ system operating frequency range is 29 to 30 GHz (TX, Ka-band) and 19.2 to 20.2 GHz

(RX, K-band).

A. JetWave™ System LRUs

The JetWave™ system is made up of the LRUs in Table 1-1..

Table 1-1. JetWave™ System LRUs

LRU PN

Modman 90400012-0001

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B. JetWave™ System LRU Leading Particulars

(1) Refer to Table 1-2 for the Modman leading particulars.

(2) Refer to Table 1-3 for the APM leading particulars.

(3) Refer to Table 1-4 for the KANDU leading particulars.

(4) Refer to Table 1-5 for the KRFU leading particulars.

(5) Refer to Table 1-6 for the TMA leading particulars.

(6) Refer to Table 1-7 for the FMA leading particulars.

(7) Refer to Table 1-8 for the B757 FMA radome perticulars.

APM 90401121

KANDU 90401566

KRFU CC1 90401203

KRFU CC2 90402346

KRFU 90401202

FMA 90000380-1

TMA 904000013-0001

A791 FM radome 90400017

Non-A791 FM radome 90400016

Table 1-2. Modman Leading Particulars

Characteristic Specification

Length 14.41 inches (366.0 mm) maximum

Width 5.02 inches (127.5 mm) maximum

Height 7.88 inches (200.2 mm) maximum

Weight 14.00 pounds (6.4 kg) maximum

Operating voltage 115 VAC, 400 Hz

Power consumption 60 watts maximum

NOTE: Honeywell recommends that wiring and cooling is

designed for 100 watts in order to allow for seamless upgrades

to the Modman with enhanced capability at a later date.

Power dissipation 59 watts maximum

Table 1-1. JetWave™ System LRUs (Cont)

LRU PN

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Cooling 48.5 lb/hr (22 kg/hr) at 104°F (40°C)

Operating temperature 5°F (-15°C) to 131°F (55°C)

Mounting information 4-MCU, forced-air, ARINC 600 series tray

Maintenance No scheduled maintenance required

Interfaces J1A - PODD, PIESD, and AISD

J1B - APM, Aircraft, APM, PODD, PIESD, AISD, and KANDU

J1C - IF to/from KRFU and aircraft power

Table 1-3. APM Leading Particulars

Characteristic Specification

Length 4.50 inches (101.6 mm) without connector

Width 4.00 inches (79.8 mm) maximum

Height 1.3 inches (33 mm) maximum

Weight 12 ounces (0.34 kg) maximum

Operating voltage 5 VDC, 300 mA maximum, from the Modman

Power consumption 0.3 watts maximum

Power dissipation 0.3 watts maximum

Cooling No forced-air cooling required

Operating temperature 5°F (-15°C) to 131°F (55°C)

Maintenance No scheduled maintenance required

Interface J1 - Modman

Table 1-4. KANDU Leading Particulars

Characteristic Specification

Length 11.02 inches (28 cm) maximum

Width 9.075 inches (23.05 cm) maximum

Height 4.76 inches (12.1 cm) maximum

Weight 8.8 pounds (4.0 kg) maximum

Operating voltage 115 VAC, 400 Hz

Power consumption 200 watts Class A maximum average power

115 watts Class B maximum average power

Table 1-2. Modman Leading Particulars (Cont)

Characteristic Specification

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Power dissipation 50 watts Class A maximum average power

42 watts Class B maximum average power

Cooling Cooling clearance is 2.0 inches (5.1 cm) above and 1 inch (2.54

cm) at the sides minimum

No forced-air cooling required

Operating temperature -67°F (-55°C) to 158°F (70°C)

Maintenance No scheduled maintenance required

Interfaces J1 - Aircraft and Modman

J2 - Power to OAE and IMU (38.5 and 24 VDC)

J3 - KRFU, OAE, and maintenance

J4 - Ethernet (quadrax)

Table 1-5. KRFU Leading Particulars

Characteristic Specification

Conduction-cooled 1 configuration:

Length 16.55 inches (42.0 cm) maximum

Width 10.03 inches (25.5 cm) maximum

Height 2.08 inches (7.1 cm) maximum

Weight 11.30 pounds (5.1 kg) maximum

Operating voltage 115 VAC, 400 Hz

Power consumption 150 watts maximum

Power dissipation 132 watts maximum

Cooling Conductive-cooled through the baseplate with thermal pad

Operating temperature -67°F (-55°C) to 158°F (70°C)

Maintenance No scheduled maintenance required

Interfaces J1 - Aircraft power input

J2 - Control interface from KANDU

J3 - RF TX to OAE

J4 - RF RX from OAE

J5 - IF TX from Modman

J6 - IF RX to Modman

Conduction-cooled 2 configuration:

Table 1-4. KANDU Leading Particulars (Cont)

Characteristic Specification

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Length 16.55 inches (42.0 cm) maximum

Width 9.01 inches (22.9 cm) maximum

Height 2.08 inches (7.1 cm) maximum

Weight 11.30 pounds (5.1 kg) maximum

Operating voltage 115 VAC, 400 Hz

Power consumption 150 watts at maximum output power

Power dissipation 132 watts at maximum output power

Cooling Conductive-cooled through the baseplate with thermal pad

Operating temperature -67°F (-55°C) to 158°F (70°C)

Maintenance No scheduled maintenance required

Interfaces J1 - Aircraft power input

J2 - Control interface from KANDU

J3 - RF TX to OAE

J4 - RF RX from OAE

J5 - IF TX from Modman

J6 - IF RX to Modman

Forced air configuration:

Length 18.05 inches (45.8 cm) maximum

Width 9.01 inches (22.9 cm) maximum

Height 3.23 inches (8.4 cm) maximum

Weight 14.6 pounds (6.6 kg) maximum

Operating voltage 115 VAC, 400 Hz

Power consumption 150 watts at maximum output power

Power dissipation 132 watts at maximum output power

Cooling Forced air, 169.8 lb/hr (77 kg/hr) at 104°F (40°C) at sea level

Operating temperature -67°F (-55°C) to 158°F (70°C)

Maintenance No scheduled maintenance required

Table 1-5. KRFU Leading Particulars(Cont)

Characteristic Specification

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Interfaces J1 - Aircraft power input

J2 - Control interface from KANDU

J3 - RF TX to OAE

J4 - RF RX from OAE

J5 - IF TX from Modman

J6 - IF RX to Modman

Table 1-6. TMA Leading Particulars

Characteristic Specification

Length 13.38 inches (339.9 mm) maximum

Width 12.00 inches (304.8 mm), maximum reflector sweep volume

Height 13.57 inches (344.7 mm) maximum

Weight 10 pounds (4.55 kg)

Operating voltage 38.5 VDC and 24 VDC for IMU supplied by the KANDU

Power consumption 85 watts at maximum output power

Cooling Natural convection and radiation only

Operating temperature -67°F (-55°C) to 158°F (70°C)

Maintenance No scheduled maintenance required

Interfaces J2 - Power/control interface from KANDU

J3 - RF TX from KRFU

J4 - RF RX to KRFU

Table 1-7. FMA Leading Particulars

Characteristic Specification

Length 23.03 inches (585 mm) maximum

Width 35.72 inches (907.3 mm), maximum reflector sweep volume

Height 9.40 inches (238.8 mm) maximum

Weight 83 pounds (37.6 kg) maximum

NOTE: The lifting fixture is 5.5 pounds (2.5 kg)

Operating voltage 38 VDC and 24 VDC for IMU supplied by the KANDU

Power consumption 160 watts maximum

Table 1-5. KRFU Leading Particulars(Cont)

Characteristic Specification

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2. Honeywell JetWave™ System Architecture

This section describes the Inmarsat AES system that Honeywell has implemented for the following

classes of terminal:

• Class A aftermarket satellite terminal: For use on CAT types of aircraft. This uses a FMA

assembly. The terminal can also be used in the large aircraft segment of the BRS.

• Class A OEM satellite terminal: For use on CAT types of aircraft but will be compliant to ARINC

791 standard.

• Class B satellite terminal: For use on BRS. This uses the compact TMA.

Both terminal types share the same core avionics, differing only in the antenna assembly. Each LRU in

the system (APM, Modman, KRFU, KANDU, and OAE) is designed to work only with other Honeywell

LRUs, not with third-party LRUs. Refer to Figure 1-2 for the JetWave™ system block diagram.

Cooling Natural convection and radiation only

Maintenance No scheduled maintenance required

Interfaces P1 - Power from KANDU

P2 - Control interface from KANDU

P3 - IMU power and control from KANDU

J4 - RF RX to KRFU

J5 - RF TX from KRFU

Table 1-8. B757 FMA Radome Leading Particulars

Characteristic Specification

Length 95.472 inches (585 mm) maximum

Width 43.881 inches (907.3 mm), maximum

Height 11.892 inches (238.8 mm) maximum

Weight 53.5 pounds (24.27 kg) maximum

Table 1-7. FMA Leading Particulars

Characteristic Specification

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Figure 1-2. JetWave™ System Block Diagram

The JetWave™ system LRUs are as follows:

A. Outside Antenna Equipment

• The OAE is made up of a mechanically steered antenna:

• Either fuselage mount or tail mount

• Radome package.

• The antenna includes an aperture.

• The OAE is powered by the KANDU.

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• Contains an LNA for amplification of signals in the receive path.

• Includes the mechanical pointing system, positioner, motors and sensors, and an INU to detect

movement of the platform.

• The TMA or FMA accepts the transmit Ka-band signal from the KRFU for the antenna.

• The antenna K-band receive path is amplified by the LNA and sent to the KRFU by the TMA or

FMA.

• The TMA or FMA receives power from the KANDU.

• The TMA or FMA accepts the control interface from the KANDU and lets the antenna aperture

report status, BITE, and gyro position back to the KANDU.

• Radome packages are unique to each fuselage and can be made up of the kits that follow:

• Radome kit

• A791 compliant AIM or LAIM kit

• Skirt fairing.

NOTE: Not all aircraft will have a skirt fairing.

B. KRFU

• Is made up of a BUC to convert the transmit IF frequencies (950-1950 MHz) to Ka-band

frequencies (29-30GHz)

• An HPA increases the signal strength for transmission by the antenna

• Contains a BDC to convert the received K-band frequencies (19.2-29.2 GHz) to IF (950-1950

MHz)

• Accepts 115 VAC aircraft power.

C. KANDU

• Receives commands from the Modman through an Ethernet interface to configure the

antenna/KRFU and reports status over this Ethernet interface.

• Contains the positioning algorithm to allow the pointing of the antenna with inputs from the IRU,

information from the RSSI detector in the Modman, and the IMU from the antenna.

• Provides power and control to the antenna.

• Provides control signals to the KRFU through the RS-422 interface.

• Accepts 115 VAC aircraft power.

D. Modman

• Is the overall controller of the system.

• Receives and transmits information to the KRFU along the IF frequency between 950-1950

MHz.

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• It supplies the user interfaces to the aircraft and passengers as follows:

• The PODD interfaces provide service to the passengers through the use of Ethernet

(10/100/1000 Base T).

• The PIESD interfaces provide services to passenger entertainment devices installed on

the aircraft (in flight entertainment systems). This system uses Ethernet (10/100/1000

Base T).

• The AISD interfaces provide services to the aircraft/cockpit, such as the electronic flight

bag, data load, etc. This system uses Ethernet (10/100/1000 Base T) interfaces.

• The discrete I/O for aircraft status and for reporting system status.

• Has two LEDs to provide power and fault status on the front panel.

• Accepts 115 VAC from the aircraft.

• Manages the BIT for the complete AES.

• Contains the modem, which transmits and receives to/from the KRFU.

• Controls the KRFU and KANDU (and through it, the OAE) through the Ethernet interface and

RS-422 discretes.

E. APM

• The APM holds the configuration data for the system.

• Is powered by the Modman.

3. Honeywell Implementation

The Honeywell implementation varies from the ARINC 791 configuration as follows:

• No ARINC 629 support is provided (optional in ARINC 791).

• No EN1 Ethernet functionality between the KRFU and KANDU is provided (the provisioned

standard inter-wiring is not utilized).

• ARINC 429 TX mute between the Modman and the KANDU is not implemented (manufacturer

specific RS422 signaling is used instead).

• Manufacturer-specific circuits 1 to 6 carry a BUC Mute signal, a Filter Select signal, and an

KANDU Reset signal.

• The RSSI function is in the Modman.

• No EN2 Ethernet interface functionality between the KANDU and OAE on the TMA variant (the

provisioned standard inter-wiring is not utilized).

• There are LED indicators on the front panel of the Modman to show status.

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Refer to JetWave™ AES system Configuration, AES Configuration Data for the details of ARINC 429

labels required for the JetWave™ System.

4. JetWave™ System Modes of Operation

The JetWave™ system supports the following modes of operation:

• Power On

• System Initialization

• Normal Operation

• Critical Fault

• Data-Load

• Commanded.

A. Power On Mode

Each LRU enters Power On Mode when power is applied. RF transmission is disabled in this mode.

In this mode, the Modman does POST and other invasive tests. If no failures are detected, the

system enters into the system initialization mode.

NOTE: SNMP and continuous BITE are not available at all times during this mode.

B. System Initialization Mode

In the System Initialization Mode, the Modman starts continuous BITE, system access, and SNMP

services. The Modman attempts to establish communication with KANDU and OAE. The RF

transmission is disabled in this mode.

While in System Initialization Mode, the RS422, discrete signal and the Ethernet interfaces are

available and active on all the JetWave™ LRUs which are powered up. In Modman, when powered

up, the power supply to APM is available on Modman P23B connector. When power is applied to

the KANDU LRU, the Antenna Power and IMU power is available on the KANDU receptacle J2.

Refer to the applicable interconnection diagrams for the electrical specifications of these interfaces.

There is no timeout for system initialization since the Modman, the KRFU, and the KANDU LRUs

(which power the OAE) are powered independently from the aircraft power supply.

Once the communication with other LRUs is established, the BITE parameters of other LRUs are

extracted and more system wide testing is performed. The system wide testing includes the

hardware compatibility checks, software part number compatibility check, checking for availability

of important input data and configuration files, etc. If there are no critical failures, the system enters

into the Normal Operating Mode.

C. Normal Operating Mode

In Normal Operating Mode, the RF transmission is enabled and establishment of satellite

connection is initiated subject to the system meeting the following conditions – aircraft is in the air,

there is no geographic restriction, and the antenna has a line of sight to the satellite. Ground

operation is possible if the GTE is asserted and regulatory conditions do not restrict it. The user

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traffic can be started once the antenna is pointed correctly to the satellite and the terminal locks on

to the satellite for providing the connectivity. The system enables all the supported services like

continuous BITE, SNMP, Access system, user services, etc. in this mode.

The system enters the Normal Operating Mode approximately 5 minutes after continuous power is

applied to the last LRU.

D. Critical Fault Mode

The system enters into Critical Fault Mode when any LRU reports a critical fault that cannot be

recovered and will affect satellite connectivity. The RF transmission is muted and user services are

disconnected. The system may support minimal services like SNMP, continuous BITE, Access

system, etc. in this mode.

E. Data Load Mode

The system enters Data Load Mode when aircraft is on ground and local data load discrete on the

Modman is asserted. The SNMP, Access System, and continuous BITE services may not be

supported in data load mode. The RF transmission is disabled in data load mode. The Modman

provides ARINC 615A Ethernet data loading to itself and other LRUs through its own interface in

Data Load Mode. Additionally, LRUs individually provide ARINC 615A data loading via their

configured ports. The APM and the KRFU do not support ARINC 615A data loading individually and

are data loaded via the Modman and the KANDU, respectively. The system can exit to Data Load

Mode when local data load discrete is asserted.

F. Commanded Mode

The system also provides a Commanded Mode of operation which may be initiated through the

SNMP when the aircraft is on ground. This mode provides access to user initiated tests for system

testing e.g. manual antenna alignment, initiating automatic antenna alignment, transmit cable

calibration, manual antenna pointing to defined location, etc.

5. About Inmarsat Services

The JetWave™ system is made up of a fleet of Ka-band broadband satellite network from Inmarsat. The

Inmarsat-5 (I-5) geostationary satellites have high power Ka-band steerable and fixed spot beams that

supply global in-flight connectivity services to business, commercial, and government aviation customers

around the world.

The JetWave™ AES provides Ka-band communication utilizing an airborne VSAT. The AES

communicates through a satellite to an SAS. TX and RX interface provided within the AES enables

two-way communication. The forward channel provides a communication path from the SAS to the AES.

The return channel provides a communication path from the AES to the SAS.

The JetWave™ system may not be available on the ground or in the air in certain geographical areas.

Some countries do not allow access to this service in their airspace. The service availability would also

depend on the country in which the aircraft is registered with. The aircraft operators may approach the

respective Value Added Resellers /Distribution Partners for further details where JetWave™ services are

not available.

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INSTALLATION

1. Overview

A. JetWave™ System Components

The JetWave™ system includes five LRUs:

• Modman

•APM

• KANDU

•KRFU

• OAE - either a TMA or FMA.

NOTE: OAE equipment must be installed within an approved radome.

B. Installation Procedure Overview for the JetWave™ System

The overview of the installation procedure for the JetWave™ system is as follows:

(1) Install adapter plate for the FMA. The adapter plates required for mounting the FMA are

available in installation kits from various suppliers.

(2) The TMA is installed on the top ribs of the tail of the aircraft. In some cases an install bracket

can be used.

(3) Install the OAE and JetWave™ components in accordance with the installation drawings.

(4) Install wiring in accordance with the interconnection diagram. The cables and adapters are

available as installation kits from various suppliers.

(5) Do wiring and RF cable checks to make sure they are installed correctly and meet the

installation requirements.

(6) Apply power to the system.

(7) Do the post-installation checks.

(8) Test the system on the ground if local regulations permit.

2. Certification and Approvals

All antenna installations must be inspected and approved by an FAA authorized Designated Engineering

Representative and must be documented on FAA form 8110-3.

3. On-ground Testing and Commissioning

NOTE: There are restrictions to testing the JetWave™ system for the commissioning process.

NOTE: Each country has its own restrictions to on-ground testing and transmission. Verify regulations

before testing the system. Particular attention must be observed the first time the system is turned

on and able to transmit. At this point the system will download a map detailing the areas where

transmission is and is not allowed. This map will take effect on the next power-up.

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A. Testing and Commissioning Process with Restrictions

(1) The JetWave™ system under normal operating conditions mutes and disables the modem

when the Air/Ground status in "On Ground".

(2) The Air/Ground status will be set to "On Ground" when one of the conditions that follow are

met:

• Weight on wheels discrete is enabled in the system configuration and is indicating

"Weight on Wheels”.

• The ground speed is less than 50 knots.

• The JetWave™ system is configured to receive ground speed labels on an ARINC 429

bus but the ground speed readings have not been available for longer than 20 seconds.

(3) Ground transmission can be enabled by asserting the ground transmit discrete of JetWave™

system.

(a) The ground operation depends on location and country of aircraft registration.

(b) The reason for restrictions on transmission from the current aircraft location can be

accessed through the GUI Home page under text display “Reasons for Transmission

mute”.

(4) On completion of JetWave™ LRU installation activities, the AES system needs to be

commissioned by associating the installed JetWave™ AES system to a specific SSPP. This

SSPP may correspond to an actual VAR but may also point to a test VAR in case the actual

VAR or SSPP is not known at the time the terminal integration is finalised. The operational

life commences once the AES system is commissioned.

(5) For the testing and commissioning process, the aircraft must be positioned so to have a clear

line of sight to the satellite.

(6) To control the transmission of the terminal within certain locations and at different heights,

the terminal stores and uses a geographical map. The map indicates regions around the

globe where the terminal may legally transmit. The map is provided by Inmarsat and

requested by the terminal when it first enters the network. The terminal will retrieve the map

file from the Inmarsat server using the FTP protocol over a SVN. The SVN used for the geo

restrictions maps shall be [2] NSD Management VLAN.

(7) The APM is configured with information pertaining to the aircraft and the terminal installation.

The two important aspects of APM configuration with respect to commissioning of the

terminal are as follows:

• The private authentication key which is used to uniquely identify the logging data

transmitted by the aircraft to the regulatory server on the ground.

• The aircraft identification “Tail ID”.

(8) The Modman houses the ACM.

(a) The ACM directly connects and interacts with the JetWave™ NMS.

(b) The ACM embeds a private secret key that allows it to be recognized by the NMS as a

“Satellite Router”.

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associated DIDs of the ACM are communicated to the Inmarsat service provider as part

of pre-provisioning.

(d) The Modman and associated DIDs of the ACM also allocated a specific SSPP. This

SSPP is required to verify the terminal connectivity to the NMS.

(9) When commissioning a terminal, a VAR has to assign a service plan to the subscriber which

becomes effective by associating an SSPP to the JetWave™ AES system.

4. JetWave™ System LRU Installation

This section includes information about installing the equipment in the core JetWave™ system. Contact

Honeywell about installation kits that include mating connectors and cables.

Honeywell recommends that LRUs be installed in accessible locations that are compatible with the

environmental levels that the equipment is certified to handle.

Refer to APPENDIX D for the installation reference checklist.

A. Maintenance Panel

If the JetWave™ system is not wired to other systems on the aircraft, the discrete I/O and Ethernet

ports must be brought out to a suitable panel to allow for system checks and routine maintenance,

such as system software upgrades. The discrete I/O and Ethernet ports that are needed are as

follows:

(1) Discrete Outputs:

• System available (Modman MP13E) connected to a lamp

• Data link available (Modman MP13F) connected to a lamp.

(2) Discrete Inputs:

• Local data load enable (Modman MP10B) connected to a normally open switch

• Ground transmit enable (Modman MP11D) connected to a normally open switch

• Public service disable (Modman MP11E) connected to a normally open switch

• Modman reset (Modman MP10C) connected to a normally open switch.

(3) Ethernet Port:

• AV1 (Modman TP BB1 thru 4) connected to a RJ45 Ethernet connector

NOTE: The AVI is the default data loading port, any other Ethernet ports can be selected as

long as the APM configuration file is configured to allow that port to data load.

For LRU pin details, refer to the applicable system interconnect diagram, Figure 2-33 thru

Figure 2-36.

B. Modman

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Install the Modman in a standard 4-MCU tray. The customer is responsible for providing the

mounting tray, the mating ARINC 600 connector, contacts, as well as all the cabling for the

installaton.

Refer to Figure 2-24 for outline and installation information, and Figure 2-33 thru Figure 2-36 for

the applicable interconnect diagram.

There are no special tools, fixtures, and equipment required for the Modman installation.

Minimum clearance for the Modman: 1.0 inch (25.4 mm) clearance from top face, 0.5 inch (12.7

mm) clearance from all the other faces not interfacing with the mounting tray.

(1) The Modman mounting kits are as follows:

The customer is responsible for providing the mounting tray. Carlisle Interconnect

Technologies supplies 4-MCU ARINC 600 kits in various configurations, contact Carlisle at

www.carlisleit.com.

(2) The Modman connectors are as follows:

Table 2-1 provides the connector part numbers for the Modman rear connector. The mating

connector (Radiall PN NSXN2B875S00) is supplied by the customer.

NOTE: While engineering the JetWave™ System LRU interconnections, make sure the GXA LRU

quadrax terminations do not distort natural wire distortions. There are geometric

relationships that must be maintained between the quadrax contact and the natural twist of

the star-quad wire. Wire bend radii and clamping conditions typical of aircraft installations

should not cause deviation from NEXT parameters of the A664 compliant star quad cables

Table 2-1. ARINC 600 Connectors

Connector PN Description Qty

Radiall PN 620 601 191 ARINC 600 connector shell Size 2 with inserts 1

Insert A:

Radiall PN 620075050

Arrangement Q11, Shell Size 2:

Size 8 quadrax contact for Ethernet connections 11

Insert B:

PN: D38999/26FH35PN

D38999/26FD35PN

Radiall PN 620075050

Arrangement 120Q2, Shell Size 2:

#22 contacts

Size 8 quadrax contact for Ethernet connections

118

Insert C:

PN: D38999/26FE6PN

PN: not included

PN: 620022

Arrangement 12F5C2, Shell Size 2:

#12 contacts

#16 contacts

Size 16 optical contacts (not used)

Size 5 coax contact for RF connections

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for Ethernet interfaces terminating on Quadrax receptacles. Refer to the applicable

interconnection diagrams for the indicator that the connector rotation of the wire is in a

clockwise direction.

(3) The Modman bonding is as follows:

The Modman must be electrically bonded to the airframe. Make sure that the mating surfaces

are free from contaminants such as paints or other non-conductive elements. A bonding test

point is available on the front panel. The bonding resistance must be less than or equal to 2.5

mΩ.

(4) The TX and RX IF cables between the Modman and KRFU must have a minimum loss of

11dB at 950 MHz and a maximum loss of 21.2 dB at 950 MHz.

If the chosen cable loss is too small, an equalizer should be inserted in the TX path and an

attenuator in the RX path. The choice of parts are detailed in Table 2-2.

NOTE: An attenuator cannot be used in the TX path as the TX path also passes the

reference to the KANDU and the attenuator will introduce too much loss to that

portion of the signal.

C. APM

The APM can be installed in any orientation. Refer to Figure 2-25 for outline and installation

information and Figure 2-33 thru Figure 2-36 for the applicable interconnect diagram.

There are no special tools, fixtures, and equipment required for the APM installation.

There are no clearance requirements for the APM.

Use 0.164-32 UNC-2A corrosion resistant mounting fasteners. Do not exceed 25 in-lb (2.8 Nm)

when you torque the screws.

Connect the APM to the Modman with cable made up of two twisted shielded 24 AWG pairs with

Teflon insulation or aerospace grade shielded CAT5/CAT5e cable, with a maximum length of 9.8

feet (3 m).

The APM to Modman pendant cable, Honeywell recommends ECS PN 92240 or equivalent that is

a composite (a shielded conductor bundle) construction to support the environmental conditions

required.

Table 2-2. Modman Cable Loss Values

Cable Loss @ 950 MHz

< 6.5 dB > 6.5 dB, <11 dB > 11 dB

Equalizer in TX path 10.5 dB

Minicircuits, PN TA-10R5DC1

or equivalent

4.8 dB

Minicircuits, PN TA-4R8DC1

or equivalent

None

Attenuator in RX path 10.5 dB

Minicircuits, PN TAT-10R5-1

or equivalent

4.8 dB

Minicircuits, PN TAT-4R8-1 or

equivalent

None

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The APM must be electrically bonded to the airframe through contact with the base of the unit or

through a bonding cable attached to M3 earth stud. The APM bonding resistance must be less than

or equal to 2.5 mΩ.

D. KANDU

Refer to Figure 2-26 for outline and installation information. Refer to Figure 2-33 thru Figure 2-36

for the applicable interconnect diagram.

There are no special tools, fixtures, and equipment required for the installation of the KANDU.

The customer is responsible for the bulkhead connectors.

(1) KANDU to FMA bulkhead interconnect specification is as follows:

(a) Power and control signals required for the JetWave™ system LRUs installed outside the

aircraft will be routed through the power and control bulkhead interface connectors

which will be sealed to maintain cabin pressure (max 14.5 PSI (1,000 hPa)) inside the

cabin.

(b) Maximum round trip wiring interconnection resistance between KANDU A3J2 and

OAE-FMA- A5P1 must not exceed 0.326 ohms (considering the 16 AWG wire cables of

length 32.8 feet (10 m)).

contacts as KANDU bulkhead control connector for KANDU interwiring to the

OAE-FMA. To be labeled as BI-control.

(d) It is recommended to use MIL-DTL-38999 series III, insert 17-8, normal keying with eight

contacts as KANDU bulkhead power connector. To be labeled as BI-power.

(e) It is recommended to use TNC/N-Type hermetically sealed bulkhead interface in

accordance with MIL-C-87104/2 for the routing of the TX-IF signals between the

Modman and KRFU. The TX-IF interface to be labeled blue.

(f) It is recommended to use TNC hermetically sealed bulkhead interface in accordance

with MIL-C-87104/2 for the routing of the RX-IF signals between the Modman and

KRFU. The RX-IF interface to be labeled green.

(g) The bulkhead interface design must be jam-nut or flange in consultation. If flange design

connector is used, it must be installed such that the flange is located on the pressurized

area of the aircraft. If jam nut connector is used, jam-nut connector should utilize a lock

wire.

(h) Bulkhead interface should be installed such that receptacle pins are on the pressurized

area and receptacle sockets are on unpressurized side of the aircraft.

(i) The bulkhead interface connectors must be electrically bonded to the aircraft.

(2) KANDU to TMA interconnect specification is as follows:

(a) KANDU receptacle A3J1 is MIL-DTL-38999/20FD19PN, series Ill, flange mount

receptacle, insert 15-19, normal keying, with 19 pin-type contacts of size 20 AWG.

Mates with D38999/26FD19SN for aircraft interface.

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(b) KANDU receptacle A3J2 is MIL-DTL-38999/20FC4SN, series Ill, flange mount

receptacle, insert 13-4, normal keying, with four socket-type contacts of size 16 AWG.

Mates with D38999/26FC4PN for power output.

receptacle, insert 21-35, normal keying, with 79 pin-type contacts of size 22 AWG.

Mates with D38999/26FG35SN for control interface.

(d) KANDU receptacle A3J4 is TVPOORGQF-21-75P (Amphenol) or equivalent. Mates

with TV06RQF-21-75S (Amphenol) or equivalent for Ethernet interface.

(e) Maximum round trip wiring interconnection resistance between KANDU A3J2 and

OAE-TMA A5J2 must not exceed 0.684 ohms (considering 20 AWG wire cables of

length 32.8 feet (10 m)).

(f) KANDU bonding to the aircraft must be achieved through the mounting structure

(fasteners) and KANDU A3J1-A.

The bulkhead interface is as follows:

(g) It is recommended to use MIL-DTL-38999 series III, insert 19-35, normal keying with 66

contacts as KANDU bulkhead control connector for KANDU inter-wiring to MODMAN if

KANDU is installed in an unpressurized location inside aircraft.

(h) It is recommended to use MIL-DTL-38999 series III, insert 19-35, normal keying with 66

contacts as KANDU bulkhead control connector for KANDU inter-wiring to KRFU and

OAE-TMA if KANDU is installed in pressurized location inside aircraft.

(i) It is recommended to use MIL-DTL-38999 series III, insert 17-8, normal keying with eight

contacts as KANDU bulkhead power connector if 115 VAC power is not provisioned in

unpressurized location of aircraft.

(j) The bulkhead interface design could be either jam-nut or flange in consultation. If flange

design connector is used, it must be installed such that the flange is located on the

pressurized area of the aircraft. If jam nut connector is used, jam-nut connector should

utilize a lock wire.

(k) Bulkhead interface must be installed such that receptacle pins are on the pressurized

area and receptacle sockets are on unpressurized side of the aircraft.

(l) The bulkhead interface connectors should be electrically bonded to the aircraft.

(3) The KANDU must be electrically bonded to the airframe through contact with the base of the

unit as follows:

• At least one of the four mechanical attachment points must be used for electrical

bonding. Make sure that the mating surfaces are free from contaminants such as

paints or other non-conductive elements.

• A circular or elongated conductive area must be provided around the mounting hole

of the equipment base plate. A diameter of the conductive area must be 0.12 inch (3

mm) larger than the diameter of the washer.

• The KANDU must include a 0.59 inch (15 mm) diameter bonding measuring point

on one of the attachment tabs, as near as possible to the bonding element, but not

on the bonding element.

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The KANDU bonding resistance measured from the measuring point and the surface the unit

is mounted must be less than 2.5 mΩ.

E. KRFU

A waveguide is used for the KRFU to OAE RF TX connection. The waveguide run must include a

short length of seamless flexible waveguide along the routing to accommodate tolerances. The

waveguide must have mounting points to interface to the attachment points provided.

NOTE: A coax cable can be used in the place of the waveguide as long as the total loss number is

met.

The requirements for waveguide installation vary for each aircraft.

NOTE: Make sure the waveguide is connected before powering the KRFU. Always connect J1 last

and disconnect J1 first (J1 contains the A/C power).

Refer to Figure 2-27, Figure 2-28, and Figure 2-29 for outline and installation information. Refer to

Figure 2-33 thru Figure 2-36 for the applicable interconnect diagram.

There are no special tools, fixtures, and equipment required for the installation of the KRFU.

For FMA configuratiions, Honeywell recommends that the WR28 to WR34 adapter is put at the

KRFU end of the cable.

The TX path interconnect loss between the KRFU and the FMA must not exceed 1.5 dB. The

loss is from KRFU flange to antenna flange.

The RX path interconnect loss between the KRFU and the FMA must not exceed 2.9 dB.

The KRFU to TMA connection must be WR28 for TX, coax for RX. The KRFU to FMA WR34

connection needs to include an adapter for TX to adapt from WR28 to WR34.

The TX path interconnect loss between the KRFU and the TMA must not exceed 0.6 dB.

The RX path interconnect loss between the KRFU and the TMA must be a minimum of 0.5

dB, not exceed 2 dB.

NOTE: RX connection requires a transition from coax to WR42 at the KRFU.

Honeywell recommends that the WR42 to coax adapter is put at the KRFU end of the cable.

The operation of the AES is limited if the conduction-cooled KRFU is installed under the radome

and the mounting plate temperature exceeds 185°F (85°C).

If the shutdown temperature is exceeded, a low-power mode (non-RF communicating) is entered

until the temperature reduces to approximately ten degrees below the shutdown temperature. Refer

to Figure 3-20 for the temperature status report.

NOTE: When the aircraft is on the ground and the AES is transmitting, and the ambient outside

temperature is very hot, then the mounting plate temperature can be exceeded. The exact

outside air temperature and operating conditions are installation dependent. Consult with

your hardware supplier for further details.

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The KRFU must be electrically bonded to the airframe through contact with the base of the unit as

follows:

• At least one of the four mechanical attachment points must be used for electrical

bonding.

• Make sure that the mating surfaces are free from contaminants such as paints or

other non-conductive elements.

• A circular or elongated conductive area must be provided around the mounting hole of

the equipment base plate.

• A diameter of the conductive area must be 0.12 inch (3 mm) larger than the

diameter of the washer.

•The KRFU must include a 0.59 inch (15 mm) diameter bonding measuring point on one

of the attachment tabs, as near as possible to the bonding element, but not on the

bonding element.

The KRFU bonding resistance measured from the measuring point and the surface upon which the

unit is mounted, must be less than 2.5 mΩ.

The KRFU bonding and KRFU interconnection details from and to either the TMA or FMA are

detailed along wiht the TMA or FMA installation instructions in subsequent sections.

F. KRFU Thermal Pad Kit

(1) General

(a) The thermal pad kit, PN SCD-90402388, is intended to provide a conduction interface

between the bottom surface of the KRFU conduction units of two configurations, PN

90401203 and PN 90402346, and airplane cold plate or mounting panel. Before

mounting units on airplane the thermal pad must be installed on the units.

(2) Kit contents

(a) The thermal pad kit, PN SCD-90402388, contains the parts identified in Table 2-3.

(3) To install the thermal pad kit, do as follows:

(a) Turn the KRFU conduction unit over to expose bottom side.

(b) The thermal pad kit is made up of two different pads. There is a clear backing material

protecting the tacky side of the pads and a white opaque backing material protecting the

non-tacky side of the pads.

MPW0000118.

Table 2-3. Thermal Pad Kit Contents

PN Description Quantity

MPW0000118 Thermal pad, conduction, 60 Mil T-Flex Ka airborne, Part 1 1

MPW0000122 Thermal pad, conduction, 60 Mil T-Flex Ka airborne, Part 2 1

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(d) Apply tacky side of thermal pad to the bottom side of unit as shown in Figure 2-1.

1Making sure to keep a setback dimension of 0.032 to 0.125 inch (0.79 to 3.18 mm)

around the edges of the installed thermal pad.

(e) Remove the clear protective backing to expose the tacky side of thermal pad PN

MPW0000122.

(f) Apply the pad flush to the interior edge of the thermal pad PN MPW0000118, in order to

maintain consistent setback dimension of 0.032 to 0.125 inch (0.79 to 3.18 mm) around

the edges of the installed thermal pad.

NOTE: The configuration of the mounting feet shown in Figure 2-1 is representative only and may not be

the exact configuration for all KRFUs.

Figure 2-1. KRFU Thermal Pads

CAUTION: THE THERMAL PAD OPAQUE PROTECTIVE BACKING MUST BE

REMOVED FROM BOTH THERMAL PADS BEFORE USE IN THE FINAL

APPLICATION. FAILURE TO DO SO CAN RESULT IN PREMATURE

SHUTDOWN OF THE KRFU DUE TO OVERHEATING.

(g) Immediately before installing the KRFU into the aircraft, remove white opaque protective

backing on both pads to expose the non-tacky side of the thermal pad.

NOTE: If the KRFU unit is to be shipped or stored before installation, do NOT remove

the white opaque backing on the thermal pads.

G. Deleted

H. Deleted

I. Tail Mount Antenna

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(1) Introduction

The TMA assembly is to be installed on the top of the tail empennage of the aircraft. For the

JetWave™ system to correctly point the antenna, the installation offsets should not exceed

more than 1 degree off heading, pitch or roll with respect to principle axis of aircraft.

Depending on the airframe, the LRUs and assemblies that follow would be installed outside

aircraft fuselage as part of tail mount OAE:

•The TMA assembly

• KRFU LRU

• Radome assembly

• Radome fairing (if required).

The exact install location of the TMA assembly and KRFU is airframe specific.

The radome, radome fairing (if required), and TMA/KRFU to aircraft interface brackets are

airframe specific and the details are not covered in this manual.

Consideration must be given when deciding where to install the antenna on the factors that

follow:

• Other antennas or equipment that may block the JetWave™ antenna from being able to

see the satellite

• The JetWave™ antenna blocking other antennas

• Potential interference by the JetWave™ transmitted signal degrading the received signal

of other aircraft RF systems

• Potential interference by other RF systems degrading the received signal of the

JetWave™ system.

The TMA complies with form as defined in JetWave™ TMA outline and installation drawing

in Figure 2-30, the KRFU outline and installation drawing Figure 2-28, and the interconnect

diagram in Figure 2-33.

Refer to Table 2-4 for special tools, fixtures, and equipment for the TMA installation.

Antenna clearance for sweep volume is 12 inches (304.8 mm) minimum around dish sweep

area.

(2) TMA Installation General

Before installing any components or cabling, read all notes on drawings and read all

installation procedures.

Table 2-4. Special Tools for TMA Installation

Number Description Source

NA Hoist system Commercially available

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The installer must select the appropriate gauge of wire as specified in the TMA

interconnection diagram in Figure 2-33 for power and control connections. Interconnect

cables must be routed away from sources of potential electromagnetic interference.

(3) Advisories

The JetWave™ TMA and the KRFU subsystems include components that radiate RF and

microwave emissions in the band between 29.0 and 30.0 GHz.

All service technicians and operators should be informed of the potential hazards of RF and

microwave radiation. When installing and servicing equipment, exercise the safety

precautions that follow.

WARNING: THIS EQUIPMENT RADIATES HIGH FREQUENCY RADIATION AND POSES A

RADIATION HAZARD. CONSIDERING THE WORST CASE CONDITION OF 100

PERCENT REFLECTION FOR TAIL MOUNT ANTENNA, HONEYWELL DEEMS IT

NECESSARY TO ASSURE OEM FUSELAGE ATTENUATION EXCEEDS 19.48 dB FOR

TAIL MOUNTED ANTENNAS SYSTEM INSTALLATION. THIS IS THE MINIMUM

ATTENUATION REQUIRED FROM THE AIRCRAFT FUSELAGE TO ATTENUATE THE

KA BAND RADIATION TO MEET A SAFE HUMAN EXPOSURE OF 1 MW/CM2 INSIDE

THE AIRCRAFT.

WARNING: SERVICE TECHNICIANS AND OPERATORS MUST EXERCISE CARE TO KEEP

CLEAR OF THE ANTENNA’S BEAM WHILE PERFORMING OPERATIONAL TESTS OR

INSTALLATION VERIFICATION PROCEDURES. DO NOT APPROACH WITHIN 30.3

FEET (9.24 METERS) OF THE TAIL MOUNT ANTENNA ASSEMBLY DURING RADIO

FREQUENCY TRANSMISSION

WARNING: DURING ANTENNA OPERATION (TRANSMISSION), ENSURE MINIMUM EXPOSURE

OF ALL PERSONNEL TO ANY REFLECTED, SCATTERED, OR DIRECT BEAMS.

CAUTION: SERVICE TECHNICIANS MUST OBEY STANDARD SAFETY PRECAUTIONS, SUCH AS

WEARING SAFETY GLASSES, TO PREVENT PERSONAL INJURY WHILE

INSTALLING OR PERFORMING SERVICE ON THIS UNIT.

(4) TMA Unpacking and Inspection

This section describes how to make sure that the equipment is in good condition after

shipping. To unpack and inspect the equipment, do as follows:

(a) Unpack the equipment components from the shipping container.

(b) Make sure that all the components of the tail mount OAE subsystem as indicated on the

parts list / bill of materials are included.

(5) TMA Installation Kit Details

Other than the parts list specified in Figure 2-5, the installation kit for waveguide and coax

assemblies, wiring assemblies, brackets, clamps and mounting assembly will be airframe

specific. Refer to airframe specific wiring diagram for details.

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CAUTION: THE TAIL MOUNT OAE ASSEMBLY IS ELECTROSTATIC-SENSITIVE. STANDARD

ELECTROSTATIC-SENSITIVE HANDLING PROCEDURES MUST BE OBSERVED.

(6) TMA Airframe Structural Modifications

For the installation of TMA, structural modifications to the tail empennage of the airframe may

be required to accommodate the additional mass of the antenna assembly and aerodynamic

loads.

The aerodynamic loads are dependent on the aircraft type as well as the installation location

of the tail mount antenna assembly and KRFU on the aircraft, and are therefore installation

specific.

The appropriately qualified personnel should derive the loads and perform a structural

analysis to verify the suitability of the modifications.

The installer is responsible for all structural modifications to the aircraft.

(7) TMA Mounting Guidelines

This section describes the mounting guidelines for the tail mount OAE.

The radome installation is aircraft specific.

The airframe manufacturer can be consulted to determine the torque requirements for

mounting the TMA assembly, KRFU, radome, and radome fairing for each unique installation.

(8) TMA Physical Placement

The TMA and KRFU must be mounted on the top of the tail empennage for clear satellite

communications. Figure 2-2 shows a typical installation location for the tail mount antenna

assembly on an aircraft.

Figure 2-2. TMA Installation Location

Table 2-5. TMA Installation Kits

PN Description

SCD-90402677 WR42 to 2.92 mm coax adapter

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(9) TMA Interface Mount Brackets (if Required)

Depending on the airframe, there may be a need to install a TMA to airframe interface mount

brackets, which adapts to the tail empennage of the aircraft and in turn supplies a firm flat

base for the TMA assembly.

This is not detailed in this document as the requirement of antenna interface mount is air

frame specific.

(10) TMA Radome and Radome Fairing

Depending on the airframe, there may be a need to install radome fairing which adapts to the

tail empennage of the aircraft.

This is not detailed in this document as the requirement of radome fairing is airframe specific.

(11) TMA Assembly

The tail mount OAE assembly is typically mounted on the Ku SATCOM radio slot on top of

empennage of the aircraft vertical stabilizer.

Consult the airframe manufacturer for identification of appropriate airframe specific

installation slots on the empennage.

The isometric rear and front views of the TMA assembly is shown in Figure 2-3.

Figure 2-3. TMA Assembly Isometric View

The TMA assembly attaches to the base in five (05) locations. Refer to Figure 2-3 and Figure

2-30 for details.

(12) TMA Assembly Orientation

Orientation of the TMA assembly is defined with respect to the principal axes of the aircraft.

The TMA assembly is to be installed such that the TMA J2 connector side is located towards

the front of aircraft as indicated by the arrow as shown in Figure 2-3.

(13) KRFU Installation Location with the TMA

The KRFU install location at the top of aircraft tail empennage is airframe specific.

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The KRFU can be installed either on front or rear of tail mount antenna assembly horizontally

or vertically depending on space availability.

The KRFU is conduction cooled through the base plate with thermal pad. Mount the

Honeywell recommended thermal pad (refer to KRFU Thermal Pad Kit installation in section

3.F.) while installing KRFU LRU.

The KRFU must be installed close to the TMA assembly so as to minimize the

waveguide/coax RF losses on the RF interconnect.

It is recommended to use flexible waveguide/coax RF interface with interconnect losses not

exceeding 0.6 dB on the transmit path and 2 dB on the receive path between the KRFU and

the TMA assembly.

The typical KRFU LRU and TMA assembly (swept volume model of antenna shown)

interconnect arrangement is shown in Figure 2-4.

Figure 2-4. KRFU and TMA Interconnect Arrangement

(14) TMA Bonding Requirements

The ground straps are installed before proceeding with installation of the TMA assembly on

the antenna adapter plate or on the tail empennage airframe structure. The TMA assembly

and KRFU must be bonded to the airframe.

Consult the airframe manufacturer for the correct torque values.

J. OAE TMA Installation Procedure

Before doing any installation procedures, the installer must read and be aware of the safety

advisories listed in this manual. Only authorized technical personnel who are trained in general

aviation workmanship and have a basic understanding of satellite communication systems should

proceed with the following installation procedure.

The installation activities are detailed in subsequent sections as follows:

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• Connecting the waveguide, RF coax interface to the TMA.

• Positioning and installation of the TMA assembly onto tail empennage antenna slot/antenna

interface mount, installation of bonding straps.

• Installation of the KRFU and bonding straps.

• Installation of the waveguide and coax between the TMA and KRFU.

• Connecting the TMA interface, KRFU power, and control interfaces.

• Position and installation of the radome.

(1) Waveguide and RF Coax interconnection to Tail Antenna assembly

The waveguide and RF coax interconnect designs are aircraft specific. Consult aircraft

specific SDIM for detailed installation instructions.

(2) Installation of the TMA Assembly

(a) Carefully position and secure the TMA assembly to antenna interface mount / tail

empennage structure by making sure that the aligning stubs are aligned and fitted

correctly to the TMA alignment groves.

(b) Loosely connect and hand tight the TMA assembly with fasteners at the five mounting

locations. Apply the specified torque to the fasteners in defined sequence for firmly

mounting to the antenna interface mount / tail empennage of the aircraft.

strap location.

Figure 2-5. TMA RF TX J3 and RF RX J4 Interface Connector and Bonding Strap Locations

(3) KRFU Installation

(a) Make sure that the thermal pads are attached to the bottom of the KRFU. Refer to

Section 3.F. KRFU Thermal Pad Kit.

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(b) Before proceeding with the KRFU installation, connect the WR42 waveguide to 2.92 mm

coaxial connector adapter to KRFU J4 RF RX.

1The adapter allows connection between a WR-42 waveguide cover flange

UG595/U per MIL-DTL-3922/54 (modified with threaded mounting holes) and a

2.92 mm coaxial connector.

2The WR42 waveguide side of the adapter has a mechanical flange interface with

four 0.117 inch (2.97 mm) diameter through holes for mating with KRFU J4.

3The WR42 waveguide to 2.92 mm coaxial connector adapter is shown in Figure 2-6.

Figure 2-6. WR42 Waveguide to 2.92 mm Coaxial Connector Adapter

coaxial connector. Visually inspect connector ends and make sure that there is no debris

in the cavities.

(d) Install an O-ring and mount the adapter onto KRFU J4 with four screws. Firm tight the

WR42 waveguide to 2.92 mm coaxial connector to KRFU waveguide flange for all

fasteners in opposite sequences. Do not use power tools to torque connection.

(e) Attach the KRFU assembly to the KRFU interface mount with fasteners and tighten.

Minimum torque recommended to compress the thermal pad is 22 in-lb (2.5 Nm). Apply

torque to the fasteners in defined sequence for firmly mounting to the antenna interface

mount or the tail empennage of the aircraft. Do not use power tools to torque connection.

(f) Install one end of the ground straps to the antenna interface mount or the tail

empennage structure plate at labeled ground points with screw and washers.

(g) Install the other end of the ground straps to grounding points on the KRFU. The KRFU

bonding strap arrangement is shown in Figure 2-7.



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Figure 2-7. KRFU Bonding Strap Arrangement

(4) Installation of the Waveguide and Coaxial Cable Interconnect Between the TMA and

KRFU

(a) Loosely attach the waveguide and coax support brackets to antenna interface mount or

the tail empennage structure. The flexible wave guide and coax cable assembly kit and

its routing is aircraft specific.

(b) Remove the protective covers from the TMA J3 RF TX. Visually inspect connector ends

and make sure that there is no debris in the cavities.

gasket. Hand tight the fasteners.

(d) Loosely attach the waveguide and coax support brackets to the antenna interface mount

or the tail empennage structure.

(e) Loosely connect the waveguide to KRFU with a sealing gasket.

(f) Apply torque to KRFU waveguide flange for all fasteners in defined sequences as

recommended.

(g) Firmly attach the waveguide support brackets to the adapter plate or the tail empennage

structure.

The minimum allowable bend radius to the center line for flexible waveguide is 1 inch (25.4

mm) in H plane (bend along the long axis of the waveguide) and 0.5 inch (12.7 mm) in E plane

(bend along the short axis of the waveguide). The minimum allowable bend radius for the

coax cable is 0.25 inch (6.35 mm). Refer to Figure 2-8.

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Figure 2-8. View of H Plane and E Plane Bends

(5) Connecting the TMA interface, KRFU Power, and Control Interface

Power and control signals for the TMA assembly is supplied from the KANDU and is

connected to TMA J2 receptacle. Install location of KANDU is airframe specific. KANDU

could be installed in unpressurized area near the tail empennage of the aircraft or inside

pressurized area of the aircraft. In case of KANDU install location is inside pressurized

location, the KANDU to KRFU and KANDU to TMA interconnect may be routed through a

Bulkhead Interface connector.

Control signals for the KRFU is supplied from the KANDU and is connected to KRFU J2

receptacle. 115 VAC power supply for KRFU is supplied from aircraft power and is connected

to KRFU J1 receptacle. IF TX and IF RX signals to KRFU are supplied from Modman. Refer

to the TMA interconnection diagram Figure 2-33 for details.

(a) Remove the protective covers from the TMA J2 and KANDU J2 receptacles. Visually

inspect connectors and make sure that the pins are straight and not damaged.

1Clean the connectors with the contact cleaner and connect the cable assembly for

tail mount from KANDU J2 receptacle to TMA J2 receptacle.

2Make sure that the over braid of the cable assembly is terminated to connectors at

both TMA and KANDU ends.

(b) Remove the protective covers from the KRFU J2 and KANDU J3 receptacles. Visually

inspect connectors and make sure that the pins are straight and undamaged.

1Clean the connectors with the contact cleaner and connect the cable assembly for

tail mount from KANDU J3 receptacle to KRFU J2 receptacle.

2Make sure that the over braid of the cable assembly is terminated to connectors at

both KRFU and KANDU ends.

inspect connector ends and make sure that there is no debris in central connector cavity.

1Clean the connectors with the contact cleaner before connecting.

aTX-IF connects from the Modman through the bulkhead J4B to KRFU J5.

bRX-IF connects from the Modman through the bulkhead J3B to KRFU J6.

2Make sure that the TX-IF coax cable is banded blue and RX-IF coax cable is

banded green at connector ends.

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3Make sure that the over braid of the cable assembly is terminated to connectors at

both KRFU and Modman or the bulkhead interface feed through ends.

4The over braid can be terminated to connector shield/housing or directly to housing.

(d) Make sure that all cable assembly routing are firmly held with wire clamps in accordance

with the airframe specific wiring diagram and there are no obstruction to the free

movement of tail mount antenna.

On completion of LRU interconnection and applying power to TMA, the tail mount antenna

will move in azimuth and elevation direction and move itself to its home position. The default

position is 0° in azimuth and 45° in elevation if the TMA is not talking to the rest of the system,

otherwise the default position is configured by a setting in the APM.

(6) Radome and Radome Fairing Installation with the TMA Interface Mount

Radome and fairing installation is aircraft specific. See aircraft specific SDIM for details.

NOTE: Before removing the Tail Mount Radome, Honeywell recommends manually steering the

TMA to a safe antenna orientation position using the JetWave™ GUI. The TMA parking

position is included in the AES System Configuration File and this can be accessed through

the GUI web interface and by navigating to Configuration File page.Consult aircraft specific

SDIM for detailed instructions.

K. TMA Alignment

On completion of physical installation of the TMA, the installed antenna system has to be aligned

and calibrated for any possible installation offsets. The antenna alignment for the JetWave™

system is designed to be performed automatically once initialized through a GUI interface.

It is recommended to do the antenna alignment calibration after initial installation and whenever the

OAE-TMA is removed and replaced. Only qualified avionics personnel who are knowledgeable in

the technical and safety issues related to the antenna systems should perform the alignment

procedures provided in this SDIMM.

Refer to Section 4.Q. for the TMA and FMA Antenna Alignment Procedure.

L. TMA Human Exposure to RF EM Fields

WARNING: THE JETWAVE™ SYSTEM IS A SOURCE OF NON-IONIZING RADIATION.

(1) The Minimum Safe Distance:

• TMA = 30.3 feet (9.24 m).

NOTE: The minimum safe distance for occupational/controlled exposure is determined

based on the computational method specified in FCC Office of Engineering and

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Technology; Bulletin Number 65, Edition 97-01: Evaluating compliance with FCC

Guidelines for human exposure to Radio Frequency Electromagnetic fields.

(2) The areas which the risk exists are based upon the location of the antenna. This means

personnel operating on the apron, transient personnel, and the general population in the

controlled exposure category will not be exposed to levels in excess of the limits.

Maintenance personnel working close to the tail must be protected by disabling the

transmitter before they approach that area of the aircraft.

(3) The JetWave™ system incorporates three fail-safe features to limit the potential for human

exposure to non-ionizing radiation:

(a) The system will not transmit unless the receiver is receiving a valid signal, therefore if

the received signal were to become blocked the transmitter would be disabled.

(b) The antenna subsystem includes a hardware end-stop that prevents the antenna

pointing more than two degrees below the horizontal.

disable the RF transmission. This switch would be used to prevent any radiation from

the antenna in the event of aircraft operations in the vicinity of the antenna, for instance

when de-icing the aircraft. This would be achieved by a defined procedure on the

aircraft.

M. Fuselage Mount Antenna

(1) Introduction

The OAE FMA assembly will be installed on the top of the fuselage of the aircraft. For the

JetWave™ system to correctly point the antenna, the installation offsets should notexceed

more than 1 degree off heading, pitch or roll with respect to principle axis of aircraft.

Depending on the airframe, as part of the OAE FMA, the LRUs and assemblies that follow

will be installed outside aircraft:

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•FMA LRU

• KRFU LRU (if installed outside aircraft)

• Radome assembly

• A791 based AIM or the LAIM

• Radome skirt fairing.

The exact install location of the A791 based AIM or LAIM and KRFU is airframe specific.

The KRFU can be installed on the inside or outside the fuselage of the aircraft. Honeywell

recommends to install the KRFU on the A791 based AIM or LAIM outside the fuselage of the

aircraft.

The radome, skirt fairing, and FMA/KRFU to aircraft interface brackets are airframe specific

and said details are not covered by this manual.

NOTE: The A791 based AIM and the LAIM solutions differ in that the AIM is intended to be

broadly applicable accross all airframes. The LAIM, however refers to a solution that

would be designed specifically for the exact airframe that the JetWave™ system is

installed on. The LAIM solution will vary between airframes, in some cases by a large

amount. All specific figures and references to the LAIM that are included in this

manual are only an example of generic LAIM solutions. The user must not infer

applicability or design direction for the LAIM from any related material presented

herin.

Refer to the FMA outline and installation drawing in Figure 2-31, the KRFU outline and installation

drawings in Figure 2-27, Figure 2-28, and Figure 2-29, and the radome outline and installation

drawing in Figure 2-32. Depending on the aricraft configuration, refer to the interconnect diagrams

in Figure 2-34 for the KRFU installed inside the fuselage, Figure 2-35, or Figure 2-36 for external

KRFU.

Refer to Table 2-6 for special tools, fixtures, and equipment for the FMA installation.

(2) The FMA Installation General

Before installing any components or cabling, read all notes on drawings and read all

installation procedures.

(3) Advisories

The JetWave™ FMA and the KRFU subsystems include components that radiate RF and

microwave emissions in the band between 29.0 and 30.0 GHz.

All service technicians and operators must be informed of the potential hazards of RF and

microwave radiation. When installing and servicing equipment, exercise the safety

precautions that follow.

Table 2-6. Special Tools for FMA Installation

Number Description Source

NA Hoist system Commercially available

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WARNING: THIS EQUIPMENT RADIATES HIGH FREQUENCY RADIATION AND POSES A

RADIATION HAZARD. CONSIDERING THE WORST CASE CONDITION OF 100

PERCENT REFLECTION FOR THE FUSELAGE MOUNT ANTENNA,

HONEYWELL DEEMS IT NECESSARY TO ASSURE OEM FUSELAGE

ATTENUATION EXCEEDS 21.03 dB FOR FUSELAGE MOUNTED ANTENNAS

SYSTEM INSTALLATION. THIS IS THE MINIMUM ATTENUATION REQUIRED

FROM THE AIRCRAFT FUSELAGE TO ATTENUATE THE KA-BAND RADIATION

TO MEET A SAFE HUMAN EXPOSURE OF 1 MW/CM2 INSIDE THE AIRCRAFT.

WARNING: SERVICE TECHNICIANS AND OPERATORS MUST EXERCISE CARE TO KEEP

CLEAR OF THE ANTENNA’S BEAM WHILE PERFORMING OPERATIONAL

TESTS OR INSTALLATION VERIFICATION PROCEDURES. DO NOT

APPROACH WITHIN 66.6 FEET (20.3 METERS) OF THE FUSELAGE MOUNTED

ANTENNA ASSEMBLY DURING RADIO FREQUENCY TRANSMISSION.

WARNING: DURING ANTENNA OPERATION (TRANSMISSION), MAKE SURE THAT

MINIMIZE THE EXPOSURE OF ALL PERSONNEL TO ANY REFLECTED,

SCATTERED, OR DIRECT BEAMS.

CAUTION: SERVICE TECHNICIANS MUST OBEY STANDARD SAFETY PRECAUTIONS,

SUCH AS WEARING SAFETY GLASSES, TO PREVENT PERSONAL INJURY

WHILE INSTALLING OR PERFORMING SERVICE ON THIS UNIT.

CAUTION: THE FUSELAGE MOUNT OAE ASSEMBLY IS ELECTROSTATIC-SENSITIVE.

STANDARD ELECTROSTATIC-SENSITIVE HANDLING PROCEDURES MUST BE

OBSERVED.

(4) Unpacking and Inspection

This section describes how to make sure that the equipment is in good condition after

shipping. To unpack and inspect the equipment do as follows:

(a) Unpack the equipment components from the shipping container.

(b) Make sure that all components of the fuselage mount OAE subsystem as indicated on

the parts list / bill of materials are included.

(5) FMA Installation Kits

Other than the parts list specified in Table 2-7, the installation kit for the A791 based AIM or

the LAIM, waveguide and coax assemblies, wiring assemblies, brackets, clamps, and

mounting assembly will be airframe specific. Refer to airframe specific wiring diagram for

details. The radome skirt fairing will be airframe specific. The LAIM will be a custom solution

for a particular airframe.

Table 2-7. FMA installation Kits

PN Description

SCD-90402677 WR42 to 2.92 mm coax adapter

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(6) Airframe Structural Modifications

For the installation of OAE-FMA, structural modifications to the airframe may be required in

the region where the OAE-FMA is to be mounted to accommodate the additional mass of the

antenna assembly and resulting aerodynamic loads.

The aerodynamic loads are dependent on the aircraft type as well as the installation location

of the OAE-FMA on the aircraft, and are therefore installation specific.

Bird strike and rapid decompression need to be considered for analysis and structural

substantiation.

The appropriately qualified personnel should derive the loads and do a structural analysis to

make sure of the suitability of the modifications.

The installer is responsible for all structural modifications to the aircraft.

(7) Mounting Guidelines

This section describes the mounting guidelines for fuselage mount OAE.

Physical Placement:

The aircraft fuselage mount OAE is installed on top of the fuselage for clear satellite

communications.

Figure 2-9 shows a typical installation location for the fuselage mount OAE on an aircraft.

Honeywell recommends not installing the FMA at the mid fuselage station location of the

aircraft near the wings or slightly aft of the wings.

90404243 RF component kit (KRFU to FMA waveguide

and RX coax cable FMA to KRFU)

Table 2-7. FMA installation Kits(Cont)

PN Description

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Figure 2-9. FMA Install Location

The fuselage antenna assembly and KRFU (if installed outside the aircraft) will be mounted

on the antenna interface mount and it suplies a means to secure all equipment and wiring

mounted on it.

Depending on the airframe, the A791 based AIM or LAIM is installed to provide a firm flat

base for installation of the FMA and KRFU. These are detailed in the next sections.

(8) Installation Guidelines for the A791 Based AIM

The skirt fairing comes attached to the ARINC 791 based AIM plate. The installation

sequence suggested for mounting A791 based AIM is as follows:

•Install the A791 based AIM bonding straps.

• Install the A791 based AIM fittings to the aircraft fuselage.

• Mount the A791 based AIM.

• Install the A791 based AIM bonding straps to the A791 based AIM assembly.

Before putting the A791 based AIM assembly onto aircraft, install bonding straps to the

aircraft fittings. Refer to the airframe specific kits and assembly drawings for fastener details.

Figure 2-10 shows a typical ground strap connection.

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Figure 2-10. Typical Ground Strap Arrangement for A791 Compliant Fittings

The aircraft coordinate system orientation and fitting layout are shown in Figure 2-11.

Figure 2-11. Aircraft Coordinate System Orientation and Fitting Layout

(a) Position and install the A791 based AIM fittings onto aircraft fittings for fittings #1, #2,

#5, #6, and #7.

(b) Use the alignment tools to make sure that the fitting slip in X-direction is centered for

fittings #2, #6, and #7.

you lower the A791 based AIM onto aircraft fittings and the installed fittings pass through

openings in A791 based AIM.

(d) Put the A791 based AIM assembly onto aircraft with an aircraft servicing hoist. Attach

the hoist to the A791 based AIM adapter plate at three locations labeled “Hoist Point”.

Make sure that the previously installed fittings on aircraft are still oriented vertically so

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that they will pass through the openings in the adapter plate as AIM assembly is lowered

onto aircraft. Refer to Figure 2-12.

(e) Refer to the airframe specific kits and assembly for fastener specifications to install A791

complaint AIM fittings to aircraft fittings.

NOTE: Consult airframe manufacturer for choosing the correct torque values.

(f) Wet the fuselage skin with water on skirt seal contact area before you put the AIM

assembly on aircraft.

Figure 2-12. AIM Assembly Placement on Aircraft

(9) Installation Guidelines for the LAIM

NOTE: The LAIM is custom designed to the aircraft they will be installed on.

The installation sequence suggested for mounting the LAIM is as follows:

• Install the LAIM and radome shirt fairing bonding straps.

• Install the LAIM to the aircraft fuselage.

• Install the radome skirt fairing.

Install the LAIM and Radome Shirt Bonding Straps

(a) Before mounting the LAIM assembly onto the aircraft, install bonding straps to aircraft

fittings. There are eight bonding straps. Six of the bonding straps are installed between

the bonding points and the radome skirt fairing. Two bonding straps are installed

between the bonding points and the LAIM structure.

(b) Refer to the airframe specific kits and assembly drawings for fastener details.

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Install the LAIM to the Aircraft Fuselage

(a) Make sure that all the fittings are oriented vertically with the alignment tools, to help

when you lower the LAIM onto aircraft fittings.

(b) Put the LAIM assembly onto aircraft install location. Refer to Figure 2-13 for a generic

LAIM installation on airframe structure.

Figure 2-13. LAIM Assembly

four fittings each have four attachment points, through the aircraft skin to the

intercostals. The two aft fittings each have four attachment points through aircraft skin

to the stringer rivet hole locations. Machined brackets will get attached to intercostals

with fasteners.

Refer to the airframe specific kits and assembly for fastener specifications to install LAIM

to aircraft.

Install the Radome Skirt Fairing

(a) Before mounting the radome skirt fairing assembly onto aircraft, make sure that all the

fittings are oriented vertically with the alignment tools, to help when you lower the

radome skirt fairing assembly onto the aircraft fittings.

(b) Put the radome skirt fairing assembly onto the aircraft. Refer to the airframe specific kits

and assembly for fastener specifications to install radome skirt fairing assembly to

aircraft. Figure 2-14 shows the radome skirt assembly along with LAIM.

aircraft skin into gusset attached to the outer flange of the intercostals and into gusset

attached to the inner flange of the intercostals (1 at the forward center and 19 on each

side).

NOTE: Consult airframe manufacturer for choosing the correct torque values.

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Figure 2-14. Radome Skirt Fairing and LAIM Assembly Position on Aircraft

(10) FMA Bonding

The bonding straps are installed before proceeding with installation of FMA assembly on the

A791 based AIM or LAIM.

The FMA assembly and KRFU must be bonded to the airframe.

Consult the airframe manufacturer for the correct torque values.

N. FMA Installation Procedure

Following installation activities are detailed in subsequent sections:

• Installation of the FMA.

• Connecting the waveguide, RF coax interface to the FMA.

• Installation of KRFU and bonding straps.

• Installation of waveguide and coax between FMA and KRFU.

• Connecting Bulkhead Interface, KRFU power and control interfaces.

• Position and installation of radome.

(1) Installation of the FMA Assembly

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(a) Align the FMA assembly above adapter plate with an aircraft service hoist. Attach hoist

to the FMA lifting fixture at two locations on each side of fixture. Refer to Figure 2-15.

Figure 2-15. FMA Assembly

(b) Put the FMA onto the FMA mounting holes with alignment pins and make sure that the

waveguide flange is pointed to the rear of the AIM. Make sure that the pigtails do not

interfere to avoid damage.

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Figure 2-16. FMA Assembly Lifting Fixture Removal

(d) The orientation of the FMA assembly is defined with respect to the principal axes of the

aircraft.

(e) Attach the FMA to the AIM with screws and flat washers. The AIM is provisioned with

captive nuts. Refer to the airframe specific kits and assembly for fastener specifications

and required torque. Mounting holes in base are accessed from the top between the

antenna and turntable by rotating the assembly in azimuth.

(f) Remove protective cap from disconnect plug on harness.

1Visually inspect connector and make sure that there are no debris in cavities.

2Visually inspect the center conductor and verify that it is still straight and the finish

is intact.

(2) FMA Bonding Requirements

(a) Install one end of bonding straps to AIM at labeled bonding points with screw and

washers.

(b) Install the other end of bonding straps to bonding points on the FMA base. Refer to the

airframe specific kits and assembly for fastener specifications and required torque.

Refer to Figure 2-10 for the FMA ground strap connection.

(3) Waveguide and RF Coax Interconnection to FMA Assembly

(a) Waveguide and RF coax interconnect designs are aircraft specific. Consult aircraft

specific SDIM for detailed installation instructions.

(b) Remove protective cap on FMA J4 (2.92 mm female coax) and FMA J3. Connect K-type

disconnect plug to K-type disconnect receptacle J4 on the FMA. Connect the WR34

waveguide assembly to the FMA receptacle J3

(4) KRFU Installation Location

(a) The KRFU install location is airframe specific.

(b) The KRFU can be installed inside the aircraft or external to the aircraft under the

radome. Honeywell recommends that the KRFU is installed external to the aircraft,

under the radome.

used. This variant achieves cooling through its base plate and must be installed with the

provided thermal pad to ensure a good thermal path between the KRFU and the AIM or

LAIM. Refer to KRFU Thermal Pad Kit installation Section 4.F., before you install the

KRFU LRU.

(d) When the KRFU is installed inside the aircraft either the conduction cooled or forced air

cooled variant may be used.

(e) The KRFU must be installed close to fuselage mount antenna assembly so as to

minimize the waveguide/coax RF losses on the RF interconnect.

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(f) It is recommended to use flexible waveguide / Coax RF interface with interconnect

losses not to exceed 1.5 dB on the transmit path and 2.9 dB on the receive path between

the KRFU and FMA assembly. Honeywell has developed a RF component kit

(90404243) containing a suitable waveguide and coaxial cable.

(5) KRFU Installation

Refer to Section 4.K.(3). KRFU Installation procedure.

(6) Installation of the Waveguide and Coax Interconnect Between the FMA and Externally

Mounted KRFU

(a) Loosely attach the waveguide and coax support brackets to the AIM. The flexible wave

guide and coax cable assembly kit and its routing are aircraft specific.

(b) Remove the protective covers from the FMA J3 RF TX. Visually examine connector

ends and make sure that there is no debris in the cavities.

sealing gasket. Hand tighten the fasteners.

(d) Loosely attach the waveguide and coax support brackets to the AIM.

(e) Loosely connect the WR34 to WR28 waveguide adapter to the KRFU with sealing

gasket. Apply torque to the waveguide adapter flange for all fasteners as recommended.

(f) Loosely connect the waveguide assembly to the KRFU with a sealing gasket.

(g) Apply torque to the KRFU waveguide flange for all fasteners as recommended.

(h) Firmly attach waveguide support brackets to adapter plate.

The minimum allowable bend radius to the center line for flexible waveguide is 1 inch (25.4

mm) in H plane (bend along the long axis of the waveguide) and 0.5 inch (12.7 mm) in E plane

(bend along the short axis of the waveguide). The minimum allowable bend radius for the

coax cable is 0.25 inch (6.35 mm). Refer to Figure 2-17.

Figure 2-17. View of H Plane and E Plane Bends

(7) Connecting the FMA Interface, KRFU Power, and Control Interfaces

The control signals for the KRFU are supplied from the KANDU and are connected to KRFU

J2 receptacle.

The 115 VAC power supply for the KRFU is supplied from the aircraft power and is connected

to KRFU J1 receptacle.

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The IF TX and IF RX signals to KRFU are supplied from the Modman. These are routed

through bulkhead interface. Refer to the appropriate FMA interconnection diagram Figure

2-34, Figure 2-35, or Figure 2-36 for details.

(a) Remove the protective covers from the FMA P2 and KANDU J2 receptacles. Visually

examine the connectors and make sure that the pins are straight and undamaged.

1Clean the connectors with the contact cleaner and connect the cable assembly for

fuselage mount from the KANDU J2 receptacle to the FMA P1, P2, and P3

receptacles.

2Make sure that the over braid of the cable assembly is terminated to connectors at

both the FMA and KANDU ends.

(b) Remove the protective covers from the KRFU J2 and KANDU J3 receptacles. Visually

examine the connectors and make sure that the pins are straight and undamaged.

1Clean the connectors with the contact cleaner and connect the cable assembly for

fuselage mount from the KANDU J3 receptacle to the KRFU J2 receptacle.

2Make sure that the over braid of the cable assembly is terminated to connectors at

both the KRFU and KANDU ends.

examine the connector ends and ensure there is no debris in central connector cavity.

1Clean the connectors with the contact cleaner before connecting.

2Make sure that the TX-IF coax cable is banded blue and RX-IF coax cable is

banded green at connector ends.

3Make sure that the over braid of the cable assembly is terminated to connectors at

both the KRFU and bulkhead interface feed through ends.

4The over braid can be terminated to the connector shield/housing or directly to the

housing.

(d) Make sure that all the cable assembly routing are firmly held with wire clamps in

accordance with the airframe specific wiring diagram and there are no obstruction to the

free movement of the FMA. Refer to Figure 2-18 for the A791 based AIM and Figure

2-18 for the LAIM.

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Figure 2-18. A791 Based AIM Assembly with FMA and KRFU Placement on Aircraft

Figure 2-19. LAIM Assembly with FMA and KRFU Placement on Aircraft

On completion of the LRU interconnection and applying power to the FMA, the FMA will stay

in its current position until it is told to move by the KANDU.

(8) AIM/LAIM Radome Installation

The radome installation is aircraft specific. See aircraft specific SDIM for details.

Depending on the AIM selected, the radome gets installed differently.

With the A791 based AIM, the Radome will be installed on the A791 based AIM.

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With the LAIM, the radome will be installed on the Radome skirt fairing assembly. Refer to

the and Figure 2-20.

Figure 2-20. Radome Assembly Mounted on Radome Skirt Fairing (LAIM)

O. FMA Alignment

On completion of physical installation of the FMA, the installed antenna system has to be aligned

and calibrated for any possible installation offsets. The antenna alignment for the JetWave™

system is designed to be performed automatically once initialized through a GUI interface.

It is recommended to do the antenna alignment calibration after initial installation and whenever the

OAE-FMA is removed and replaced. Only qualified avionics personnel who are knowledgeable in

the technical and safety issues related to the antenna systems should do the alignment procedures

provided in this SDIMM.

Refer to Section 4.Q. TMA and FMA Antenna Alignment Procedure.

P. FMA Human Exposure to RF EM Fields

WARNING: THE JETWAVE™ SYSTEM IS A SOURCE OF NON-IONIZING RADIATION.

(1) The Minimum Safe Distance:

• FMA = 66.6 feet (20.3 m).

NOTE: The minimum safe distance for occupational/controlled exposure is determined

based on the computational method specified in FCC Office of Engineering and

Technology; Bulletin Number 65, Edition 97-01: Evaluating compliance with FCC

Guidelines for human exposure to Radio Frequency Electromagnetic fields.

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(2) The areas which the risk exists are based upon the location of the antenna. This means

personnel operating on the apron, transient personnel, and the general population in the

controlled exposure category will not be exposed to levels in excess of the limits.

Maintenance personnel working close to the tail must be protected by disabling the

transmitter before they approach that area of the aircraft.

(3) The JetWave™ system incorporates three fail-safe features to limit the potential for human

exposure to non-ionizing radiation:

(a) The system will not transmit unless the receiver is receiving a valid signal, therefore if

the received signal were to become blocked the transmitter would be disabled.

(b) The antenna subsystem includes a hardware end-stop that prevents the antenna from

pointing more than two degrees below its mounting plane.

disable the RF transmission. This switch would be used to prevent any radiation from

the antenna in the event of aircraft operations in the vicinity of the antenna, for instance

when de-icing the aircraft. This would be achieved by a defined procedure on the

aircraft.

Q. TMA and FMA Antenna Alignment Procedure

(1) Antenna Assembly Orientation

For the JetWave™ system to point to the servicing satellite correctly, it is important to align

the antenna assembly after installation. The TMA/FMA assembly has a built in IMU and its

orientation must be aligned with respect to the principal axes of the aircraft which is

determined through aircraft IRS.

(a) To do the automatic antenna alignment calibration, aircraft should have a functional IRS,

interfaced with the KANDU through A429 interface, and should have the required

ARINC 429 labels as defined in the APM configuration file.

(b) During the physical installation, the IMU principal axes of the TMA/FMA is aligned with

those of the aircraft within ± 1° on the pitch, roll, and yaw axis. The installation offsets,

are then estimated by the KANDU automatically from data received from the aircraft

Inertial Navigational System and the TMA/FMA IMU assembly.

installed. The antenna alignment process can be initiated through the GUI interface. The

JetWave™ system GUI service is supported on AV1 and AG1 10/100 Base T Ethernet

interfaces. Modman static IP assigned is 172.29.55.1 and the port number for the AES

GUI service is 80.

(2) Automatic Antenna Alignment GUI Interface

The JetWave™ system GUI service is supported on AV1 and AG1 10/100 Base T Ethernet

interfaces. Modman static IP assigned is 172.29.55.1 and the port number for the AES GUI

service is 80.

(a) On any Internet browser (Internet Explorer 8 compatible), open the link "index.html". The

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Figure 2-21. GUI Login Page

(b) Enter the username and password below to access the maintenance interface.

• Username: "Maintenance" and Password: "Earthbound".

(3) Positioning of Aircraft for Antenna Alignment

(a) On the GUI Calibrate Antenna Alignment page, as shown in Figure 2-22, the current

location of aircraft in terms of latitude and longitude is indicated along with the longitude

of the servicing Geo stationary satellite.

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Figure 2-22. GUI Calibrate Antenna Alignment Page

(b) For the automatic antenna alignment calibration, it is recommended to tow and put the

aircraft in an open area away from aircraft hangers such that there is clear visibility to

the open sky with the heading of the aircraft pointed in one of four recommended aircraft

heading values displayed on the GUI antenna calibration page.

aircraft headings. Out of the available headings, it is required to do only one automatic

alignment calibration while the aircraft heading is toward one of the preferred directions.

(d) The recommended values are dependent on the radome and these values are

estimated by the KANDU based on the input from the aircraft IRS and the selected

satellite coordinates.

NOTE: It is advised not to do the automatic antenna alignment during rains with heavily

clouded sky.

(4) Automatic Antenna Alignment

The JetWave™ system uses the following input parameters during the antenna alignment

procedure:

• Aircraft IRS data

• OAE IMU data

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• RSSI as reported from the Modman.

(a) The GUI page indicates the status of the aircraft. In order to proceed with the antenna

calibration process, all LRUs of the JetWave™ system need to be powered up with

aircraft IRS system functioning and providing valid inputs. The GUI page indicates the

IRS status.

(b) Once the aircraft is aligned to within ± 5 degrees of any of the recommended aircraft

heading, the grayed out on the “Initiate” button will be changed, indicating the system

readiness to commence the antenna alignment process.

(d) On successful completion of the antenna calibration, the statues changes to "Aligned".

Figure 2-23. GUI Antenna Alignment Calibration Page Extract

5. Electrical Installation

For details about electrical installation, refer to Figure 2-33 thru Figure 2-36 for the system interconnect

diagrams.

6. Cabling Requirements

Refer to Table 2-8 for the cabling requirements.

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When installing the JetWave™ system, follow the cabling requirements listed below:

• Ethernet LAN/WAN cables must meet flammability and TIA/EIA568-A CAT 5E requirements.

• Carlisle IT (ECS) 422404 or NF24Q100-01 is recommended for Quadrax connections.

• Twisted shielded pairs must meet ARINC 791 wiring requirements or equivalent.

Refer to Figure 2-33, Figure 2-34, Figure 2-35, and Figure 2-36 for wire size recommendations.

7. Drawings and Diagrams

Refer to Figure 2-24 for the Modman outline and installation drawing.

Refer to Figure 2-25 for the APM outline and installation drawing.

Refer to Figure 2-26 for the KANDU outline and installation drawing.

Refer to Figure 2-27 for the KRFU PN 90401203, conduction-cooled 1, outline and installation drawing.

Refer to Figure 2-28 for the KRFU PN 90402346, conduction-cooled 2, outline and installation drawing.

Refer to Figure 2-29 for the KRFU PN 90401202, forced air cooled, outline and installation drawing.

Refer to Figure 2-30 for the TMA outline and installation drawing.

Refer to Figure 2-31 for the FMA outline and installation drawing.

Refer to Figure 2-32 for the Fuselage Mount Radome outline and installation drawing.

Refer to Figure 2-33 for the JetWave™ System - TMA interconnect diagram.

Refer to Figure 2-34 for the JetWave™ System - FMA (baseline) interconnect diagram.

Refer to Figure 2-35 for the JetWave™ System - Boeing Specific FMA (external KRFU) interconnect

diagram.

Refer to Figure 2-36 for the JetWave™ System - A350 Specific FMA interconnect diagram.

Table 2-8. Cabling Requirements

Cable Conductor Type Single

Point Multiple

Point Minimum Conductor

Coverage by Shield

Power Lines Single conductor, stranded NA N/A N/A

Ethernet Data Quadrax, twister pair - Yes 100%

RF Coaxial, waveguide - Yes 100%

A429 Twisted pair, stranded - Yes 95%

RS-422 Twisted pair, shielded - Yes 100%

Discrete Twisted pair, shielded, KANDU

Single conductor, shielded, grounds Yes 100%

SYSTEM DESCRIPTION AND INSTALLATION MANUAL

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Figure 2-24. Modman Outline and Installation Drawing (Sheet 1 of 4)

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SYSTEM DESCRIPTION AND INSTALLATION MANUAL

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Figure 2-24. Modman Outline and Installation Drawing (Sheet 2 of 4)

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Figure 2-24. Modman Outline and Installation Drawing (Sheet 3 of 4)

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Figure 2-24. Modman Outline and Installation Drawing (Sheet 4 of 4)

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Figure 2-25. APM Outline and Installation Drawing (Sheet 1 of 2)

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EMS Technologies Canada JETWAVE KA Band Aviation Radio User Manual 23 15 29R001

EMS Technologies Canada, Ltd. KA Band Aviation Radio 23 15 29R001

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