Honeywell SD 700A User Manual

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SYSTEM DESCRIPTION, INSTALLATION,

AND MAINTENANCE MANUAL

MCS-4000/7000

TEMPORARY REVISION NO. 23-2

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SYSTEM DESCRIPTION, INSTALLATION AND MAINTENANCE MANUAL

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MANUAL, PUB. NO. A15--5111--001, MCS 4000/7000 MULTI--CHANNEL SATCOM SYSTEM

REVISION NO.

002 DATED 5FEB2008

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System Description, Installation, and

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MCS--4000/7000

Multi--Channel SATCOM System

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Description

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Subheading and Page Date Subheading and Page Date

Title

T--1 T--2 T--3 T--4

Record of Revisions

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Service Bulletin List

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List of Effective Pages

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Table of Contents

TC--1 TC--2 TC--3 TC--4 TC--5 TC--6 TC--7 TC--8 TC--9 TC--10

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TC--11 TC--12 TC--13 TC--14

Introduction

INTRO--1 INTRO--2 INTRO--3 INTRO--4 INTRO--5 INTRO--6 INTRO--7 INTRO--8 INTRO--9 INTRO--10

System Description

1--1 30 Aug 2002 1--2 30 Aug 2002

1--3/1--4 30 Aug 2002 1--5 30 Aug 2002 1--6 30 Aug 2002 1--7 30 Aug 2002 1--8 30 Aug 2002 1--9 30 Aug 2002 1--10 30 Aug 2002 1--11 30 Aug 2002 1--12 1--13 30 Aug 2002 1--14 1--15 30 Aug 2002 1--16 30 Aug 2002

1--17/1--18 30 Aug 2002 1--19 30 Aug 2002 1--20 30 Aug 2002 1--21 30 Aug 2002

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Subheading and Page

1--22 30 Aug 2002 1--23 30 Aug 2002 1--24 30 Aug 2002 1--25 30 Aug 2002 1--26 30 Aug 2002 1--27 30 Aug 2002 1--28 30 Aug 2002 1--29 30 Aug 2002 1--30 30 Aug 2002

1--31/1--32 30 Aug 2002 1--33 30 Aug 2002 1--34 30 Aug 2002 1--35 30 Aug 2002 1--36 30 Aug 2002 1--37 30 Aug 2002 1--38 30 Aug 2002 1--39 30 Aug 2002 1--40 30 Aug 2002 1--41 30 Aug 2002 1--42 30 Aug 2002 1--43 30 Aug 2002 1--44 30 Aug 2002 1--45 30 Aug 2002 1--46 30 Aug 2002

System Operation

2--1 30 Aug 2002 2--2 30 Aug 2002 2--3 30 Aug 2002 2--4 30 Aug 2002 2--5 30 Aug 2002 2--6 30 Aug 2002 2--7 30 Aug 2002 2--8 30 Aug 2002 2--9 30 Aug 2002 2--10 30 Aug 2002 2--11 30 Aug 2002 2--12 30 Aug 2002 2--13 30 Aug 2002 2--14 30 Aug 2002

Date Subheading and Page Date

2--15 30 Aug 2002 2--16 30 Aug 2002 2--17 30 Aug 2002 2--18 30 Aug 2002 2--19 30 Aug 2002 2--20 30 Aug 2002 2--21 30 Aug 2002 2--22 30 Aug 2002 2--23 30 Aug 2002 2--24 30 Aug 2002 2--25 30 Aug 2002 2--26 30 Aug 2002 2--27 30 Aug 2002 2--28 30 Aug 2002

Cabin/Cockpit Communications

3--1 30 Aug 2002 3--2 30 Aug 2002

3--3/3--4 30 Aug 2002 3--5 30 Aug 2002 3--6 30 Aug 2002 3--7 30 Aug 2002 3--8 30 Aug 2002 3--9 30 Aug 2002 3--10 30 Aug 2002 3--11 30 Aug 2002 3--12 30 Aug 2002 3--13 30 Aug 2002 3--14 30 Aug 2002 3--15 30 Aug 2002 3--16 30 Aug 2002 3--17 30 Aug 2002 3--18 30 Aug 2002

Mechanical Installation

4--1 30 Aug 2002 4--2 30 Aug 2002 4--3 30 Aug 2002 4--4 30 Aug 2002

4--5/4--6 30 Aug 2002

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Subheading and Page

4--7/4--8 30 Aug 2002

4--9/4--10 30 Aug 2002

4--11/4--12 30 Aug 2002

4--13/4--14 30 Aug 2002

4--15/4--16 30 Aug 2002

4--17/4--18 30 Aug 2002

4--19/4--20 30 Aug 2002

4--21/4--22 30 Aug 2002

4--23/4--24 30 Aug 2002

Electrical Installation

5--1 30 Aug 2002 5--2 30 Aug 2002 5--3 30 Aug 2002 5--4 30 Aug 2002 5--5 30 Aug 2002 5--6 30 Aug 2002 5--7 30 Aug 2002 5--8 30 Aug 2002 5--9 30 Aug 2002 5--10 30 Aug 2002 5--11 30 Aug 2002 5--12 30 Aug 2002 5--13 30 Aug 2002 5--14 30 Aug 2002 5--15 30 Aug 2002 5--16 30 Aug 2002 5--17 30 Aug 2002 5--18 30 Aug 2002 5--19 30 Aug 2002 5--20 30 Aug 2002 5--21 30 Aug 2002 5--22 30 Aug 2002 5--23 30 Aug 2002 5--24 30 Aug 2002 5--25 30 Aug 2002 5--26 30 Aug 2002

5--27/5--28 30 Aug 2002

5--29/5--30 30 Aug 2002

5--31/5--32 30 Aug 2002

Date Subheading and Page Date

5--33 30 Aug 2002 5--34 30 Aug 2002

5--35/5--36 30 Aug 2002

5--37/5--38 30 Aug 2002

5--39/5--40 30 Aug 2002

5--41/5--42 30 Aug 2002

5--43/5--44 30 Aug 2002 5--45 30 Aug 2002 5--46 30 Aug 2002 5--47 30 Aug 2002 5--48 30 Aug 2002 5--49 30 Aug 2002 5--50 30 Aug 2002 5--51 30 Aug 2002 5--52 30 Aug 2002 5--53 30 Aug 2002 5--54 30 Aug 2002 5--55 30 Aug 2002 5--56 30 Aug 2002 5--57 30 Aug 2002 5--58 30 Aug 2002 5--59 30 Aug 2002 5--60 30 Aug 2002

Testing/Fault Isolation

6--1 6--2 30 Aug 2002 6--3 30 Aug 2002 6--4 30 Aug 2002 6--5 30 Aug 2002 6--6 30 Aug 2002 6--7 30 Aug 2002 6--8 30 Aug 2002 6--9 30 Aug 2002 6--10 30 Aug 2002 6--11 30 Aug 2002 6--12 30 Aug 2002 6--13 30 Aug 2002 6--14 30 Aug 2002 6--15 30 Aug 2002

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Subheading and Page

6--16 30 Aug 2002 6--17 30 Aug 2002 6--18 30 Aug 2002 6--19 30 Aug 2002 6--20 30 Aug 2002 6--21 30 Aug 2002 6--22 30 Aug 2002 6--23 30 Aug 2002 6--24 30 Aug 2002 6--25 30 Aug 2002 6--26 30 Aug 2002 6--27 30 Aug 2002 6--28 30 Aug 2002 6--29 30 Aug 2002 6--30 30 Aug 2002 6--31 30 Aug 2002 6--32 30 Aug 2002 6--33 30 Aug 2002 6--34 30 Aug 2002 6--35 30 Aug 2002 6--36 30 Aug 2002 6--37 30 Aug 2002 6--38 30 Aug 2002 6--39 30 Aug 2002 6--40 30 Aug 2002 6--41 30 Aug 2002 6--42 30 Aug 2002 6--43 30 Aug 2002 6--44 30 Aug 2002 6--45 30 Aug 2002 6--46 30 Aug 2002 6--47 30 Aug 2002 6--48 30 Aug 2002 6--49 30 Aug 2002 6--50 30 Aug 2002 6--51 30 Aug 2002 6--52 30 Aug 2002 6--53 30 Aug 2002 6--54 30 Aug 2002

Date Subheading and Page Date

6--55 30 Aug 2002 6--56 30 Aug 2002 6--57 30 Aug 2002 6--58 30 Aug 2002 6--59 30 Aug 2002 6--60 30 Aug 2002 6--61 30 Aug 2002 6--62 30 Aug 2002 6--63 30 Aug 2002 6--64 30 Aug 2002 6--65 30 Aug 2002 6--66 30 Aug 2002 6--67 30 Aug 2002 6--68 30 Aug 2002 6--69 30 Aug 2002 6--70 30 Aug 2002 6--71 30 Aug 2002 6--72 30 Aug 2002 6--73 30 Aug 2002 6--74 30 Aug 2002 6--75 30 Aug 2002 6--76 30 Aug 2002 6--77 30 Aug 2002 6--78 30 Aug 2002 6--79 30 Aug 2002 6--80 30 Aug 2002 6--81 30 Aug 2002 6--82 30 Aug 2002 6--83 30 Aug 2002 6--84 30 Aug 2002 6--85 30 Aug 2002 6--86 30 Aug 2002 6--87 30 Aug 2002 6--88 30 Aug 2002 6--89 30 Aug 2002 6--90 30 Aug 2002 6--91 30 Aug 2002 6--92 30 Aug 2002 6--93 30 Aug 2002

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Subheading and Page

6--94 30 Aug 2002 6--95 30 Aug 2002 6--96 30 Aug 2002 6--97 30 Aug 2002 6--98 30 Aug 2002 6--99 30 Aug 2002 6--100 30 Aug 2002 6--101 30 Aug 2002 6--102 30 Aug 2002 6--103 30 Aug 2002 6--104 30 Aug 2002 6--105 30 Aug 2002 6--106 30 Aug 2002 6--107 30 Aug 2002 6--108 30 Aug 2002 6--109 30 Aug 2002 6--110 30 Aug 2002 6--111 30 Aug 2002 6--112 30 Aug 2002

Maintenance Practices

7--1 30 Aug 2002 7--2 30 Aug 2002 7--3 30 Aug 2002 7--4 30 Aug 2002 7--5 30 Aug 2002 7--6 30 Aug 2002

Appendix A Vendor Equipment

A--1 30 Aug 2002 A--2 30 Aug 2002 A--3 30 Aug 2002 A--4 30 Aug 2002

A--5/A--6 30 Aug 2002 A--7 30 Aug 2002 A--8 30 Aug 2002 A--9 30 Aug 2002 A--10 30 Aug 2002 A--11 30 Aug 2002 A--12 30 Aug 2002

Date Subheading and Page Date

A--13/A--14 30 Aug 2002 A--15 30 Aug 2002 A--16 30 Aug 2002 A--17 30 Aug 2002 A--18 30 Aug 2002 A--19 30 Aug 2002 A--20 30 Aug 2002 A--21 30 Aug 2002 A--22 30 Aug 2002 A--23 30 Aug 2002 A--24 30 Aug 2002 A--25 30 Aug 2002 A--26 30 Aug 2002 A--27 30 Aug 2002 A--28 30 Aug 2002 A--29 30 Aug 2002 A--30 30 Aug 2002

Appendix B Installation Procedures For SATCOM Air Filtration Systems

B--1 30 Aug 2002 B--2 30 Aug 2002 B--3 30 Aug 2002 B--4 30 Aug 2002 B--5 30 Aug 2002 B--6 30 Aug 2002 B--7 30 Aug 2002 B--8 30 Aug 2002

Appendix C Owner Requirements Table

C--1 30 Aug 2002 C--2 30 Aug 2002 C--3 30 Aug 2002 C--4 30 Aug 2002 C--5 30 Aug 2002 C--6 30 Aug 2002 C--7 30 Aug 2002 C--8 30 Aug 2002 C--9 30 Aug 2002

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Subheading and Page

C--10 30 Aug 2002 C--11 30 Aug 2002 C--12 30 Aug 2002 C--13 30 Aug 2002 C--14 30 Aug 2002

Appendix D Fault Codes

D--1 D--2 D--3 D--4 D--5 D--6 D--7 D--8 D--9 D--10 D--11 D--12 D--13 D--14 D--15 D--16 D--17 D--18 D--19 D--20 D--21 D--22 D--23 D--24 D--25 D--26 D--27 D--28 D--29 D--30 D--31 D--32

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Date Subheading and Page Date

D--33 D--34 D--35 D--36 D--37 D--38 D--39 D--40 D--41 D--42 D--43 D--44 D--45 D--46 D--47 D--48 D--49 D--50 D--51 D--52 D--53 D--54 D--55 D--56 D--57 D--58 D--59 D--61 D--62 D--63 D--64 D--65 D--66 D--67 D--68 D--69 D--70 D--71 D--72

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Subheading and Page

D--73 D--74 D--75 D--76 D--77 D--78 D--79 D--80 D--81 D--82 D--83 D--84 D--85 D--86 D--87 D--88 D--89 D--90 D--91 D--92 D--93 D--94 D--95 D--96 D--97 D--98 D--99 D--100 D--101 D--102 D--103 D--104 D--105 D--106 D--107 D--108 D--109

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Date Subheading and Page Date

D--110 D--111 D--112 D--113 D--114 D--115 D--116 D--117 D--118 D--119 D--120 D--121 D--122 D--123 D--124 D--125 D--126 D--127 D--128 D--129 D--130 D--131 D--132 D--133 D--134 D--135 D--136 D--137 D--138 D--139 D--140 D--141 D--142 D--143 D--144 D--145 D--146

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Subheading and Page

Index

INDEX--1 30 Aug 2002 INDEX--2 30 Aug 2002 INDEX--3 INDEX--4 30 Aug 2002

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Date Subheading and Page Date

INDEX--5 30 Aug 2002 INDEX--6 30 Aug 2002 INDEX--7 30 Aug 2002 INDEX--8 30 Aug 2002

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Subject Page

INTRODUCTION INTRO--1...........................................................

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

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

B. Symbols INTRO--1..........................................................

C. Weights and Measurements INTRO--1.........................................

2. Customer Support INTRO--2......................................................

A. Honeywell Aerospace Online Technical Publications Web Site INTRO--2...........

B. Complete Customer Care Center INTRO--2.....................................

3. References INTRO--2............................................................

A. Honeywell Publications INTRO--2.............................................

B. Other Publications INTRO--2..................................................

4. Acronyms and Abbreviations INTRO--3............................................

A. General INTRO--3...........................................................

5. Maximum Permissible Exposure Level INTRO--8....................................

A. General INTRO--8...........................................................

SECTION 1

SYSTEM DESCRIPTION 1--1...................................................

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

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

B. Aircraft Earth Station 1--2................................................

C. Space Segment 1--9....................................................

D. Ground Earth Station 1--9...............................................

E. Terrestrial Data and Voice Networks 1--9..................................

2. System Components 1--12...................................................

A. General 1--12...........................................................

3. System Description 1--14.....................................................

A. General 1--14...........................................................

B. Satellite Data Unit 1--19..................................................

C. High Power Amplifier 1--24...............................................

D. Avionics Configurations 1--25.............................................

4. MCS Component Descriptions 1--25...........................................

A. Physical Description 1--25................................................

B. Satellite Data Unit (SDU) 1--26............................................

C. High--Power Amplifier (40 Watt) 1--30......................................

D. High--Power Amplifier (20 Watt) 1--35......................................

E. CMA--2200 Intermediate Gain Antenna 1--38...............................

F. CMA--2200 Diplexer/Low Noise Amplifier 1--40..............................

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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

MCS--4000/7000

Subject

G. Radio Frequency Unit Interface Adapter (RFUIA) 1--43.......................

H. ARINC 429 Data Requirements 1--44......................................

I. Nameplates 3 (SDU and HPA) 1--44.......................................

J. Software and Hardware Compatibility (SDU and HPA) 1--46..................

SECTION 2

SYSTEM OPERATION 2--1.....................................................

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

A. General 2--1...........................................................

2. AES Management 2--1......................................................

A. General 2--1...........................................................

3. System Log-On/Log-Off 2--3.................................................

A. General 2--3...........................................................

B. Automatic Log-On 2--5..................................................

C. Constrained Log-On 2--6................................................

D. Log-On Mode Selection 2--6.............................................

E. Handover 2--7.........................................................

F. Log-Off 2--7...........................................................

4. System Software/Database Updates 2--8......................................

A. General 2--8...........................................................

B. Software Upload Process 2--8...........................................

C. Validation of the Software Upload File 2--9.................................

5. Owner Requirements Table 2--10..............................................

A. General 2--10...........................................................

6. ORT Upload/Download Process 2--11..........................................

A. General 2--11...........................................................

B. Startup 2--11............................................................

C. ORT Download 2--11....................................................

D. Control Mode ORT Upload Procedures 2--11................................

E. Auto Mode ORT Upload Procedure 2--13...................................

7. Circuit-Mode Services 2--13..................................................

A. Circuit-Mode Voice 2--13.................................................

B. Circuit-Mode Data 2--13..................................................

8. Packet-Data Services 2--15...................................................

A. General 2--15...........................................................

9. Dual SATCOM Configuration 2--16............................................

A. Overview 2--16..........................................................

B. Dual System Control/Status Interfaces 2--17................................

C. System Reversion 2--18..................................................

D. Antenna Configurations 2--19.............................................

Page

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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

MCS--4000/7000

Subject

E. Cockpit Voice Configurations and Functionality 2--27.........................

10. ACARS/Aircraft Flight Information System (AFIS) Peripheral Function 2--28........

A. General 2--28...........................................................

SECTION 3

CABIN/COCKPIT COMMUNICATIONS 3--1.......................................

1. Cabin Communications 3--1.................................................

A. General 3--1...........................................................

B. Cabin Communications System 3--1......................................

C. Analog Audio Channels 3--2.............................................

2. Cockpit Communications 3--14................................................

A. General 3--14...........................................................

B. Headset Off-Hook Signaling 3--14.........................................

C. Headset On-Hook Signaling 3--15.........................................

D. Voice Codec Module Audio Switching 3--15.................................

E. Voice Codec Module Sidetone 3--15.......................................

F. Voice Interface Module Stored Audio Messages 3--15........................

G. Voice Interface Module Dedication 3--17....................................

SECTION 4

MECHANICAL INSTALLATION 4--1..............................................

1. Overview 4--1..............................................................

A. General 4--1...........................................................

2. Equipment and Materials 4--1................................................

A. General 4--1...........................................................

3. Mechanical Installation Design 4--1...........................................

A. LRU Mechanical Installation 4--1.........................................

B. Installation Dependent Considerations 4--2................................

C. Owner Requirements Table (ORT) Uploading 4--2..........................

D. Cable Loss Requirements 4--2...........................................

E. Cooling Requirements 4--3..............................................

F. Vendor Supplied Equipment 4--4.........................................

SECTION 5

ELECTRICAL INSTALLATION 5--1..............................................

1. Overview 5--1..............................................................

A. General 5--1...........................................................

2. Equipment and Materials 5--1................................................

A. General 5--1...........................................................

3. Electrical Installation Procedure 5--1..........................................

A. Connector Layout and Contact Arrangement 5--1...........................

B. Electrical Installation 5--16................................................

Page

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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

MCS--4000/7000

Subject

4. Configuration Pins 5--45......................................................

A. General 5--45...........................................................

B. Availability of ARINC 429 SSR MODE S (AES ID) from CMU Ports 5--46.......

C. FMC Connection to SDU 5--48............................................

D. ARINC 429 Speed to/from CMU No. 1 and CMU No. 2 5--48..................

E. Cabin Packet Data Function (CPDF) 5--49..................................

F. ARINC 429 BUS Speed of AES ID Input 5--49..............................

G. Strap Parity (ODD) 5--49.................................................

H. Cabin Communications System (CCS) 5--50................................

I. Inertial Reference System (IRS) 5--51......................................

J. HPA/Antenna Subsystem Configuration 5--51...............................

K. CFDS/CMC 5--53........................................................

L. SDU Configuration 5--54.................................................

M. SDU Number 5--54......................................................

N. CMU No. 1 and No. 2 Configuration 5--55..................................

O. MCDU/SCDU No. 1 thru No. 3 Configuration 5--55...........................

P. Priority 4 Calls to/from Cockpit 5--56.......................................

Q. ARINC 429 BUS Speed to SCDU No. 1 / SCDU No. 2 / SCDU No. 3 5--57......

R. Cockpit Voice Call Light/Chime Option 5--57................................

S. SDU CODEC 1 and CODEC 2 Wiring 5--58.................................

T. Cockpit Hookswitch Signaling Method 5--58................................

SECTION 6

TESTING/FAULT ISOLATION 6--1...............................................

1. Overview 6--1..............................................................

A. General 6--1...........................................................

B. Definitions 6--2.........................................................

C. Failure Detection and Reporting Levels 6--3...............................

D. LRU Coverage 6--3.....................................................

E. Monitoring and Testing Functions 6--4.....................................

F. Failure Recording 6--7..................................................

G. Failure Reporting 6--8...................................................

H. Miscellaneous BITE Requirements 6--18...................................

I. Maintenance Activity Log 6--19............................................

2. SATCOM Control and Display Unit 6--20.......................................

A. General 6--20...........................................................

B. SCDU Display Terminology and Basic Operation 6--20.......................

C. SCDU Page Hierarchy 6--24..............................................

D. SCDU Pages 6--24......................................................

3. Maintenance Computer Interface 6--84.........................................

Page

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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

MCS--4000/7000

Subject

A. General 6--84...........................................................

B. Boeing 747--400 CMC/777 OMS 6--84.....................................

C. Airbus/Douglas CFDS 6--87...............................................

D. Central Aircraft Information and Maintenance System 6--88...................

E. Level I Failure Messages and ATA Reference Numbers 6--89.................

4. SCDU for Dual SATCOM 6--110................................................

A. General 6--110...........................................................

B. SATCOM Logical Channels 6--110..........................................

C. SATCOM MAIN MENU (Cross-Talk Bus Failed) 6--110........................

D. SATCOM CHANNEL STATUS 6--110.......................................

E. SATCOM MAINTENANCE Menus 6--110....................................

5. Maintenance Panel Assembly 6--110............................................

A. General 6--110...........................................................

SECTION 7

MAINTENANCE PRACTICES 7--1...............................................

1. Overview 7--1..............................................................

A. General 7--1...........................................................

2. Equipment and Materials 7--1................................................

A. General 7--1...........................................................

3. Procedure for Antennas 7--2.................................................

A. General 7--2...........................................................

B. Antenna Weather Protection 7--2.........................................

C. Antenna Hardware 7--2.................................................

D. General Antenna Removal Instructions 7--3................................

4. Procedure for the LRUs 7--3.................................................

A. LRU Removal 7--3......................................................

B. LRU Installation 7--3....................................................

5. Owner Requirements Table Uploading 7--4....................................

A. General 7--4...........................................................

6. Instructions for Continued Airworthiness, FAR 25.1529 7--5......................

A. General 7--5...........................................................

APPENDIX A

VENDOR EQUIPMENT A--1.....................................................

1. Overview A--1..............................................................

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

2. Electronic Cable Specialists A--1.............................................

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

B. Radio Frequency Components A--1.......................................

C. Cable Assembly Fabrication A--1.........................................

Page

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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

MCS--4000/7000

Subject

D. Cable Assembly Testing A--2.............................................

E. ARINC 600 Connectors A--2.............................................

F. SATCOM Avionics Unit Mounting Hardware A--4...........................

G. SATCOM Hardware Component Kits A--4..................................

H. Air Filtration Assemblies A--8.............................................

I. SATCOM Shelf Assemblies A--9..........................................

J. Additional Avionics Installation Components A--9...........................

K. Antenna System Provisions A--9..........................................

L. Cabin Communications System Provisions A--9............................

M. Wire Harnesses A--9....................................................

N. Complete Integrated SATCOM Installation Kits A--9.........................

3. Hollingsead International A--10................................................

A. General A--10...........................................................

B. Engineering Services A--10...............................................

C. LRU Mounting Requirements A--10........................................

D. Installation Kit Components A--11..........................................

4. Signal Conditioning Unit A--16.................................................

A. General A--16...........................................................

B. Operator Functions A--17.................................................

C. Control Functions A--18..................................................

D. System Functions A--19..................................................

E. ARINC 600 Connector Pin Assignments A--23...............................

APPENDIX B

INSTALLATION PROCEDURES FOR SATCOM AIR FILTRATION SYSTEMS B--1.....

1. Introduction B--1............................................................

A. General B--1...........................................................

2. Continued Airworthiness B--1................................................

A. General B--1...........................................................

3. Equipment and Materials B--2................................................

A. General B--2...........................................................

4. Installation Instructions B--4..................................................

A. Top Mount Assembly B--4...............................................

B. Body--Mounted Assembly B--6...........................................

C. Tray--Mounted Assembly B--7............................................

APPENDIX C

OWNER REQUIREMENTS TABLE C--1...........................................

1. Overview C--1..............................................................

A. General C--1...........................................................

APPENDIX D

FAULT CODES D--1............................................................

INDEX INDEX--1....................................................................

Page

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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

MCS--4000/7000

List of Illustrations

Figure Page

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

Figure Intro--2. Radio Frequency Energy Levels INTRO--9..............................

Figure 1-1. Aviation Satellite Communications System 1--2.....................

Figure 1-2. Aircraft Earth Station Block Diagram 1--3..........................

Figure 1-3. INMARSAT Four-Region Satellite Coverage 1--11...................

Figure 1-4. MCS Avionics Block Diagram 1--17................................

Figure 1-5. MCS--4000/7000 SDU Equipment Description 1--19..................

Figure 1-6. Satellite Data Unit 1--27..........................................

Figure 1-7. High--Power Amplifier (40 and 20 Watt) 1--31........................

Figure 1-8. RFUIA System Interface Diagram 1--43.............................

Figure 2-1. Satellite Audio System 2--14......................................

Figure 2-2. Dual System Wiring Diagram 2--18.................................

Figure 2-3. HGA + LGA Configuration with Top-Mounted HGA 2--21..............

Figure 2-4. HGA + LGA Configuration with Side-Mounted HGA 2--21.............

Figure 2-5. HGA + HGA Configuration with Two Top-Mounted HGAs 2--22........

Figure 2-6. HGA + HGA Configuration with Two Side-Mounted HGAs 2--22.......

Figure 2-7. HGA + HGA Configuration with One Side-Mounted HGA + One

Top-Mounted HGA (Dissimilar HGA) 2--23..........................

Figure 2-8. LGA + LGA Configuration 2--23...................................

Figure 2-9. (HGA + LGA) + HGA Configuration with Two Side-Mounted HGAs 2--24 Figure 2-10. (HGA + LGA) + HGA Configuration with the LGA Paired with

One Side-Mounted HGA 2--25....................................

Figure 2-11. (HGA + LGA) + HGA Configuration with the LGA Paired with

One Top-Mounted HGA 2--26.....................................

Figure 2-12. (HGA + LGA) + HGA Configuration with Two Top-Mounted

HGAs 2--27.....................................................

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Figure 3--1. Audio Interfaces 3--3............................................

Figure 4-1. Cable Attenuations 4--2.........................................

Figure 4-2. Satellite Data Unit Outline and Installation Diagram 4--5.............

Figure 4-3. 40 Watt High Power Amplifier Outline and Installation Diagram 4--7... Figure 4-4. 20 Watt High Power Amplifier Outline and Installation Diagram 4--9...

Figure 4-5. Intermediate Gain Antenna Outline and Installation Diagram 4--13.....

Figure 4-6. D/LNA Outline and Installation Diagram 4--17.......................

23--20--27

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MCS--4000/7000

List of Illustrations (cont)

Figure Page

Figure 4-7. RFUIA Outline and Installation Diagram 4--21.......................

Figure 5-1. SDU ARINC 600 Connector Layout 5--4...........................

Figure 5-2. Contact Arrangements for Bottom Insert, SDU ARINC

600 Connector 5--7.............................................

Figure 5-3. HPA ARINC 600 Connector Layout 5--8...........................

Figure 5-4. Contact Arrangements for Top Insert, HPA (40 Watt) ARINC

600 Connector 5--9.............................................

Figure 5-5. Contact Arrangements for Middle Insert, HPA (40 Watt) ARINC

600 Connector 5--10.............................................

Figure 5-6. Contact Arrangements for Bottom Insert, HPA (40 Watt) ARINC

600 Connector 5--11.............................................

Figure 5-7. Contact Arrangements for Top Insert, HPA (20 Watt) ARINC

600 Connector 5--12.............................................

Figure 5-8. Contact Arrangements for Middle Insert, HPA (20 Watt) ARINC

600 Connector 5--13.............................................

Figure 5-9. Contact Arrangements for Bottom Insert, HPA (20 Watt) ARINC

600 Connector 5--14.............................................

Figure 5-10. RFUIA ARINC 600 Connector Layout 5--15.........................

Figure 5-11. Satellite Data Unit Interface Diagram 5--17..........................

Figure 5-12. WH--10 Handset Interface Diagram 5--20...........................

Figure 5-13. Four--to--Two Wire Interface Diagram 5--21.........................

Figure 5-14. Avtech Fax Interface Diagram 5--22................................

Figure 5-15. HF--SAT Transfer Panel Interface Diagram 5--23.....................

Figure 5-16. Signal Conditioning Unit Interface Diagram 5--24....................

Figure 5-17. Maintenance Panel Assembly Interface Diagram 5--25...............

Figure 5-18. Intermediate Gain Antenna Interface Diagram 5--27..................

Figure 5-19. CMC Top--Mount High Gain Antenna Interface Diagram 5--29.........

Figure 5-20. Tecom Top--Mount High Gain Antenna Interface Diagram 5--31........

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Figure 5-21. Racal Mechanically Steered High Gain Antenna

Interface Diagram 5--33..........................................

Figure 5-22. AMT--50 Mechanically Steered High Gain Antenna

Interface Diagram 5--35..........................................

Figure 5-23. Dassault Conformal High Gain Antenna Interface Diagram 5--37......

Figure 5-24. Ball Conformal High Gain Antenna Interface Diagram 5--39...........

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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

MCS--4000/7000

List of Illustrations (cont)

Figure Page

Figure 5-25. Low Gain Antenna Interface Diagram 5--41.........................

Figure 5-26. Toyocom Top--Mount High Gain Antenna Interface Diagram 5--43......

Figure 6-1. System BITE Communication 6--1................................

Figure 6-2. SATCOM SCDU Page Hierarchy 6--25.............................

Figure 6-3. SATCOM SCDU Main Menu Page 6--26............................

Figure 6-4. SATCOM SUBMENU Page 6--28..................................

Figure 6-5. SATCOM MAINTENANCE Page 6--29.............................

Figure 6-6. TEST Page 6--31................................................

Figure 6-7. SATCOM SELF--TEST Page 6--36.................................

Figure 6-8. Configuration Data 6--39..........................................

Figure 6-10. DATA LOADER MENU 6--60......................................

Figure 6-11. LAST LEG REPORT Page 6--67...................................

Figure 6-12. PREVIOUS LEG REPORT Page 6--69.............................

Figure 6-13. LRU IDENTIFICATION Page 6--73.................................

Figure 6-14. TROUBLE SHOOTING DATA Page 6--76...........................

Figure 6-15. LAST LEG CLASS 3 FAULTS Page 6--78...........................

Figure 6-16. GROUND REPORT Page 6--80...................................

Figure 6-17. GROUND REPORT TROUBLE SHOOTING DATA Page 6--82........

Figure 6-18. Configuration Data Pages for Boeing 777 Installation 6--86...........

Figure A--1.1. ARINC Connectors A--3.........................................

Figure A--1.2. ARINC Assembly A--3...........................................

Figure A--1.3. Dimensions for ECS Tray Assemblies A--5.........................

Figure A--1.4. Dimensions for Hollingsead Tray Assemblies A--13...................

Figure B--1.1. ECS Top Mount Air Filtration Assembly B--5........................

Figure B--1.2. Front and Side Views Showing Filter Removal B--8.................

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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

MCS--4000/7000

List of Tables

Table Page

Table 1-1. Classes of Installations 1--8.....................................

Table 1-2. Types of RF Channels 1--8......................................

Table 1-3. Ground Earth Stations 1--10......................................

Table 1-4. System Components Supplied by Honeywell 1--12..................

Table 1-5. System Components Not Supplied by Honeywell 1--12..............

Table 1-6. SDU Configurations 1--13........................................

Table 1-7. HPA (40 Watt) Configurations 1--13...............................

Table 1-8. HPA (20 Watt) Configurations 1--14...............................

Table 1-9. SDU Leading Particulars 1--27....................................

Table 1-10. SDU DO--160D Environmental Categories 1--29....................

Table 1-11. HPA (40 Watt) Leading Particulars 1--33...........................

Table 1-12. HPA (40 Watt) DO--160C Environmental Categories 1--34............

Table 1-13. HPA (20 Watt) Leading Particulars 1--36...........................

Table 1-14. HPA (20 Watt) DO--160D Environmental Categories 1--37............

Table 1-15. CMA--2200 Intermediate Gain Antenna Features 1--38..............

Table 1-16. CMA--2200 IGA Leading Particulars 1--39..........................

Table 1-17. CMA--2200 IGA DO--160C Environmental Categories 1--40..........

Table 1-18. CMA--2200 D/LNA Features 1--41.................................

Table 1-19. CMA--2200 D/LNA Leading Particulars 1--41.......................

Table 1-20. CMA--2200 D/LNA DO--160C Environmental Categories 1--42........

Table 1-21. RFUIA Leading Particulars 1--44..................................

Table 2-1. Data Set Upload/Download 2--8.................................

Table 2-2. Basic Antenna Configurations 2--20...............................

Table 3-1. SDU to WH-10 Handset Actions 3--5.............................

Table 3-2. Global-Wulfsberg Flitephone WH-10 Commands 3--7...............

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Table 3-3. Assignment of DTMF Digits in the APBX Interface 3--13.............

Table 3-4. SDU to APBX Off-Hook Actions 3--13..............................

Table 3-5. Stored Audio Messages 3--16....................................

Table 4-1. Cable Loss Requirements 4--3...................................

Table 4-2. Cooling Requirements 4--3......................................

Table 5-1. ARINC 615 Connector Pin Callouts 5--2..........................

Table 5-2. ARINC 600 Connector Requirements 5--3.........................

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MCS--4000/7000

List of Tables (cont)

Table Page

Table 5-3. Contact Arrangements for Top Insert, SDU ARINC

600 Connector 5--5.............................................

Table 5-4. Contact Arrangements for Middle Insert, SDU ARINC

600 Connector 5--6.............................................

Table 5-5. ICAO Block Strapping 5--19......................................

Table 5-6. Configuration Pins 5--45.........................................

Table 5-7. Availability of ARINC 429 SSR MODE S (AES ID) from

CMU Ports 5--46................................................

Table 5-8. FMC Connection to SDU 5--48....................................

Table 5-9. ARINC 429 Speed to/from CMU No. 1 and CMU No. 2 5--48.........

Table 5-10. Cabin Packet Data Function (CPDF) 5--49.........................

Table 5-11. ARINC 429 Bus Speed of AES ID Input 5--49.......................

Table 5-12. Call Light On (Air/Ground Calls) 5--49..............................

Table 5-13. Strap Parity (ODD) 5--49.........................................

Table 5-14. Cabin Communications System (CCS) 5--50........................

Table 5-15. Inertial Reference System (IRS) 5--51.............................

Table 5-16. HPA/Antenna Subsystem Configuration 5--52.......................

Table 5-17. CFDS/CMC 5--53...............................................

Table 5-18. SDU Configuration 5--54.........................................

Table 5-19. SDU Number 5--54..............................................

Table 5-20. CMU No. 1 5--55................................................

Table 5-21. CMU No. 2 5--55................................................

Table 5-22. MCDU/SCDU No. 1 5--55........................................

Table 5-23. MCDU/SCDU No. 2 5--55........................................

Table 5-24. MCDU/SCDU No. 3 5--56........................................

Table 5-25. Priority 4 Calls to/from Cockpit 5--56...............................

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Table 5-26. ARINC 429 Bus Speed to SCDU No. 1 / SCDU No. 2/

SCDU No. 3 5--57...............................................

Table 5-27. Cockpit Voice Call Light/Chime Option 5--57........................

Table 5-28. SDU Analog Interface No. 1 Wiring 5--58...........................

Table 5-29. SDU Analog Interface No. 2 Wiring 5--58...........................

Table 5-30. Cockpit Hookswitch Signaling Method 5--58........................

Table 6-1. Levels of Failure 6--3...........................................

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MCS--4000/7000

List of Tables (cont)

Table Page

Table 6-2. HPA Indicators/Controls 6--9....................................

Table 6-3. SDU Indicators/Controls 6--10....................................

Table 6-4. Level 1 Failure Messages 6--12...................................

Table 6-5. List of Part Numbers 6--17.......................................

Table 6-6. MAR Information 6--19...........................................

Table 6-7. LS Key/Line Pair Relations 6--20..................................

Table 6-8. Special Symbols 6--23...........................................

Table 6-9. System Configuration Pin Mapping 6--39...........................

Table 6-10. Textual Message Display (Page 6 -- Lines 4 thru 9) 6--45.............

Table 6-11. Textual Message Display (Page 7 -- Lines 4, 5, an 6) 6--47...........

Table 6-12. Textual Message Display (Page 9 -- Lines 8 and 9) 6--51.............

Table 6-13. Textual Message Display (Page 10 -- Lines 4 and 5) 6--53............

Table 6-14. Textual Message Display (Page 10 -- Lines 8 and 9) 6--53............

Table 6-15. DATA LOADER MENU Page Prompts 6--64........................

Table 6-16. LRU Acronyms 6--72............................................

Table 6-17. Boeing Level I Failure Messages and ATA Reference Numbers 6--90..

Table 6-18. Airbus Level I (SDU No. 1) Failure Messages and ATA No. 6--93......

Table 6-19. Airbus Level I (SDU No. 2) Failure Messages and ATA No. 6--100......

Table 6-20. McDonnell Douglas Level I Failures Messages and

ATA Reference Numbers 6--106....................................

Table 6-21. Commissioning and Maintenance Terminal Panel Lamps 6--111........

Table 7-1. Materials 7--1..................................................

Table A--1.1. ECS Cables and Connectors A--2................................

Table A--1.2. ECS Attenuators A--2...........................................

Table A--1.3. HP--600 HPA (40W) Hardware Component Kit,

Part No. 998HQS--900--1XX A--7................................

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Table A--1.4. HP--700 HPA (20W) Hardware Component Kit,

Part No. 998HQS--904--1XX A--7................................

Table A--1.5. SD--700 SDU Hardware Component Kit,

Part No. XXXXXX--XXX--1XX A--8................................

Table A--1.6. BSU Hardware Component Kit, Part No. 970HQS--903--1XX A--8....

Table A--1.7. Tray Assembly Part Numbers A--12................................

Table A--1.8. ARINC 429 Data Requirements A--17..............................

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MCS--4000/7000

List of Tables (cont)

Table Page

Table A--1.9. SCU Discrete Functions A--17....................................

Table A--1.10. SCU Error Code A--18...........................................

Table A--1.11. SCU Manual Signal Selection A--19...............................

Table A--1.12. ARINC 561 Binary Data A--20.....................................

Table A--1.13. ARINC 561 BCD Data A--20......................................

Table A--1.14. ARINC 571 Data, ARINC 429 Format A--21.........................

Table A--1.15. ARINC 571 Data, ARINC 419 Format A--21.........................

Table A--1.16. ARINC 404 Data, ARINC 429 Format A--21.........................

Table A--1.17. SCU Attitude Data Inputs A--22...................................

Table A--1.18. Contact Arrangements for SCU ARINC 600 Connector A--24.........

Table A--1.19. Signal Source Select Lines A--28..................................

Table A--1.20. SCU Program Pin Combinations A--29.............................

Table B--1.1. Materials B--2..................................................

Table B--1.2. Air Filtration Systems from ECS for a Top Mount Assembly B--2......

Table B--1.3. Air Filtration Systems from ECS for a Body--Mounted Design B--3....

Table B--1.4. Air Filtration Systems from ECS for a Tray--Mounted Design B--3.....

Table C--1.2. ORT Characteristics C--1........................................

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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

1. How to Use this Manual

A. General

(1) The purpose of this manual is to help you install, operate, maintain, and troubleshoot

the MCS--4000/7000 Multi--Channel SATCOM System. Common system maintenance procedures are not presented in this manual. The best established shop and flight line practices should be used.

(2) This manual gives general system description and installation information for the

MCS--4000/7000 Multi--Channel SATCOM System. It also gives block diagram and interconnect information to permit a general understanding of the system interface.

MCS--4000/7000

INTRODUCTION

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

• A WARNING gives a condition that, if you do not obey, can cause injury or death.

• A CAUTION gives a condition that, if you do not obey, can cause damage to the

equipment.

• A NOTE gives data to make the work easier or gives direction to go to a procedure.

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

applicable paragraph or step.

(5) All personnel who operate equipment and do the specified maintenance must know

and obey the safety precautions.

B. Symbols

(1) The symbols in Figure Intro--1 identify ESDS and moisture sensitive devices in this

manual, if applicable.

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ESDS

Figure Intro--1. Symbols

C. Weights and Measurements

(1) All weights and measurements are in U.S. and SI (metric) values.

Moisture Sensitive

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2. Customer Support

A. Honeywell Aerospace Online Technical Publications Web Site

(1) If you have access to the Internet, go to the Honeywell Online Technical Publications

web site at http://portal.honeywell.com/wps/portal/aero

• Download or see publications online

• Make an order for a publication

• Tell Honeywell of a possible data error (report a discrepancy) in a publication.

B. Complete Customer Care Center

(1) If you do not have access to the Honeywell Online Technical Publications web site,

send an e--mail message or a fax, or speak to a person at the Complete Customer Care Center:

to:

• E--mail: cas--publications--distribution@honeywell.com

• Fax: 602--822--7272

• Phone: 800--601--3099 (U.S.A.)

• Phone: 602--365--3099 (International).

(2) Also, the Complete Customer Care Center is available if you need to:

• Identify a change of address, telephone number, or e--mail address

• Make sure that you get the next revision of this manual.

3. References

A. Honeywell Publications

(1) The list that follows identifies Honeywell publications that are related to this manual:

• ATA No. 23--20--03 (Pub. No. A32--5111--008), HP--600 High Power Amplifier Component Maintenance Manual

• ATA No. 23--20--25 (Pub No. A09--5111--025), HP--700 Watt High Power Amplifier Component Maintenance Manual

• ATA No. 23--20--26 (Pub. No. A09--5111--026), SD--700 Satellite Data Unit Component Maintenance Manual

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• Pub. No. A09--1100--001, Handling, Storage, and Shipping Procedures for Honeywell Avionics Equipment Instruction Manual

B. Other Publications

(1) These publications are standard references:

• The United States Government Printing Office (GPO) Style Manual 2000 (available at http://www.gpoaccess.gov/stylemanual/browse.html)

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• ANSI/IEEE Std 260 (1978), Standard Letter Symbols for Units of Measurement (available from the American National Standards Institute, New York, NY)

• ASME Y14.38--1999 (Formerly ASME Y1.1--1989), Abbreviations for Use on Drawings and in Text (available from the American National Standards Institute, New York, NY)

• ANSI/IEEE Std 315--1975 (Replaces ANSI Y32.2--1975), Graphic Symbols for Electrical and Electronics Diagrams (available from the American National Standards Institute, New York, NY)

• ANSI/IEEE Std 91 (1984), Graphic Symbols for Logic Functions (available from the American National Standards Institute, New York, NY).

4. Acronyms and Abbreviations

A. General

(1) Refer to the list that follows for acronyms and abbreviations in this manual.

MCS--4000/7000

List of Acronyms and Abbreviations

Term

AAC Aeronautical Administrative Communications ACARS Aircraft Communications Addressing and Reporting System ACP audio control panel ACU antenna control unit ADL airborne data loader ADS automatic dependent surveillance APC Aeronautical passenger communications AES aircraft earth station AFIS aircraft flight information system AMS audio management system AMU audio managment unit AOC Aeronautical Operational Control AOR--E Atlantic Ocean Region--East AOR--W Atlantic Ocean Region--West

Full Term

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APBX analog private branch exchange APC Aeronautical passenger communications APHONE analog telephone APOS actual power out status ARINC Aeronautical Radio, Inc.

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List of Acronyms and Abbreviations (cont)

Term Full Term

ATA Air Transport Association ATC air traffic control ATS air traffic services BIT built--in test BITE built--in test equipment BSU beam steering unit CAIMS central aircraft information and maintenance system CCA circuit card assembly CCS cabin communications system CF/M cubic feet per minute CFDIU centralized fault display interface unit CFDS central fault display system CGU communications gateway unit CLR clear CM continuous monitoring CMC central maintenance computer CMT commissioning and maintenance terminal CMU communications management unit CPDF cabin packet data function CRC cyclic redundancy check CTM cabin telecommunications CTU cabin telecommunications unit D/LNA diplexer/low noise amplifier DEL delete DIP dual in--line packaging

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DIU data interface unit DTE data terminal equipment DTMF dual tone multifrequency ECS electronic cable specialists EIRP effective isotopic radiated power

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List of Acronyms and Abbreviations (cont)

Term Full Term

FAX facsimile FMC flight management computer FWP fault warning processor GES ground earth station GMT Greenwich Mean Time GSDB GES--specific data broadcast GSPD groundspeed HGA high gain antenna HMN Honeywell Material Number HPA high power amplifier HPR high power relay I/O input/output ICAO International Civil Aviation Organization ID identification IGA intermediate gain antenna INMARSAT International Maritime Satellite Organization INS inertial navigation system IOR Indian Ocean Region IPC illustrated parts catalog IRS inertial reference system ISO International Standards Organization ISU initial signal unit ITU International Telecommunications Union LED light emitting diode LGA low gain antenna

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LRU line replaceable unit LS line select MAR maintenance activity record MCDU multifunction control display unit MCS MCS--4000/7000 Multi--Channel SATCOM

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List of Acronyms and Abbreviations (cont)

Term Full Term

MCU modular concept unit MEL minimum equipment list MTBF mean--time--between--failure MU management unit NVM non--volatile memory OCXO oven controlled crystal oscillator OEM Original Equipment Manufacturer OMS onboard maintenance system ORT owner requirements table PABX private automatic branch exchange PAST person--activated self--test PDL portable data loader PF power factor PLO phase--locked oscillator PMAT portable maintenance access terminal POC power--on counter POR Pacific Ocean Region POST power--on self--test PROM programmable read--only memory PSTN Public Switched Telephone Network PSU power supply unit PTT push--to--talk RFM radio frequency module RFU radio frequency unit RFUIA radio frequency unit interface adapter

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RTC real--time clock RTCA radio technical commission for aeronautics SAL system address label SCDU SATCOM control and display unit SCPC single channel per carrier

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List of Acronyms and Abbreviations (cont)

Term Full Term

SCU signal conditioning unit SDI source destination identifier SDU satellite data unit SITA Satellite Aircom SMT surface mount technology SRU shop replaceable unit SSM sign--status matrix TDM time division multiplex TDMA time division multiple access TIF terminal interface function TOTC total on--time clock TSPO time since power--on TTCM triple transcoder modem UTC universal time coordinated VCM voice codec module VSWR voltage standing wave ratio XTB

cross--talk bus

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5. Maximum Permissible Exposure Level

A. General

(1) The radio frequency energy generated by the MCS system may be hazardous to

personal health. To eliminate the potential danger, Honeywell recommends that operators of the MCS system implement safety procedures.

(2) When the MCS system is in operation, personnel should remain at a distance from

the antenna that is greater than the maximum permissible exposure level (MPEL) radius. Because there are many possible antenna locations, antenna gains, and system output powers, it is the responsibility of the operator to ascertain the MPEL radius for their MCS system configuration and train their personnel in safe ground procedures. The following warnings state Honeywell’s MPEL recommendations for both high and low gain antennas.

WARNING: TO AVOID POTENTIALLY DANGEROUS EXPOSURE TO RADIO

FREQUENCY ENERGY ABOVE THE ANSI C95.1 LIMIT AND OTHER WORLD STANDARDS (SEE FIGURE INTRO--2) WHEN USING A HIGH GAIN ANTENNA (12 dB NOMINAL ANTENNA), DO NOT OPERATE THE MCS SYSTEM WHEN ANY PERSONNEL ARE WITHIN 8.5 FEET OF THE ANTENNA OR WITHIN 20 FEET OF THE ANTENNA FOR PERIODS OF LONGER THAN 3 MINUTES PER HOUR.

WARNING: TO AVOID POTENTIALLY DANGEROUS EXPOSURE TO RADIO

FREQUENCY ENERGY ABOVE THE ANSI C95.1 LIMIT AND OTHER WORLD STANDARDS (SEE FIGURE INTRO--2) WHEN USING AN INTERMEDIATE GAIN ANTENNA (6 dB NOMINAL ANTENNA), DO NOT OPERATE THE MCS SYSTEM WHEN ANY PERSONNEL ARE WITHIN 3 FEET OF THE ANTENNA OR WITHIN 6 FEET OF THE ANTENNA FOR PERIODS OF LONGER THAN 3 MINUTES PER HOUR.

WARNING: TO AVOID POTENTIALLY DANGEROUS EXPOSURE TO RADIO

FREQUENCY ENERGY ABOVE THE ANSI C95.1 LIMIT AND OTHER WORLD STANDARDS (SEE FIGURE INTRO--2) WHEN USING A LOW GAIN ANTENNA (0 dB NOMINAL ANTENNA), DO NOT OPERATE THE MCS SYSTEM WHEN ANY PERSONNEL ARE WITHIN 1.5 FEET OF THE ANTENNA OR WITHIN 3 FEET OF THE ANTENNA FOR PERIODS OF LONGER THAN 3 MINUTES PER HOUR.

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Figure Intro--2. Radio Frequency Energy Levels

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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

1. Overview

A. General

(1) The MCS--4000/7000 Multi-Channel SATCOM (MCS) system is a mobile avionics

communications system that supplies continuous worldwide voice and data communications services to and from the aircraft through satellite. The MCS system interfaces at baseband with various avionics data equipment, as well as with crew and passenger voice equipment on–board the a ircraft. It interfaces with the antenna subsystem through L--band RF signals that emanate from (and are received by) satellites in geostationary orbit. These satellites then convey the information to and from ground stations that interface with the terrestrial telephone network.

(2) The MCS system augments and/or supersedes the present high frequency

transceiver by supplying higher quality voice service and by supplying data services at higher bit rates needed by some future datalink (ATN) applications, such as automatic dependent surveillance (ADS) and an international aircraft communications addressing and reporting system (ACARS). Additional services include cockpit communications with administrative and operational personnel and with governmental bodies such as air traffic services (ATS). The system is designed to ensure that communications for safety and regularity of flight are not delayed by the transmission and reception of other types of messages.

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SECTION 1

SYSTEM DESCRIPTION

(3) The MCS--4000/7000 system supports seven communication channels capable of

simultaneous full duplex voice communications and one channel of data communications. The MCS--4000 system operates identically to the MCS--7000 except four communication channels rather than seven are supplied. Both the MCS--7000 and MCS--4000 SATCOM systems supply one channel of data communications. The MCS system acco mmodates the four categories of communications:

• Air traffic control (ATC)

• Aeronautical operational control (AOC)

• Aeronautical administrative communications (AAC)

• Aeronautical passenger communications (APC).

(4) The four communication categories are recognized by the International Civil Aviation

Organization (ICAO) and the International Telecommunications Union (ITU), and have been assigned priorities for communications purposes.

(5) The total aviation satellite communications system, shown in Figure 1-1, is made up

of the following:

• Aircraft earth station (airborne avionics subsystems and an tenna sub system)

• Space segment (satellite network)

• Ground earth stations

• Terrestrial data and voice networks.

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Figure 1-1. Aviation Satellite Communications System

B. Aircraft Earth Station

(1) General

(a) The aircraft earth station (AES) is fully compliant with requirements of

Aeronautical Radio, Inc (ARINC) Characteristics 741/761. Standard interfaces between the MCS avionics and other aircraft avionics enable the AES to accept data and voice messages from various sources, encode and modulate this information onto appropriate RF carrier frequencies, and transmit these carriers to the space segment for relay to a ground earth station (GES). The AES also receives RF signals from a GES through the satellite, demodulates these signals, performs the necessary decoding of the encoded messages, and outputs the data or voice message for use by either the pilot, copilot,or the passengers.

(2) AES Components

(a) General

A block diagram of the AES is shown in Figure 1-2. The AES is made up of the following components:

• MCS avionics

• Antenna subsystem

• Cabin communications services

• Analog connected telephones

• Cockpit voice sources

• Aircraft avionics.

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Figure 1-2. Aircraft Earth Station Block Diagram

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(b) MCS Avionics

The MCS avionics are made up of the satellite data unit (SDU) and high power amplifier (HPA). The SDU supplies the interface to all aircraft avionics, and implements all functionality associated with modulation/demodulation, error correction, channel rate/frequency selection, and RF translation for seven communication channels. The SDU supports seven communication channels capable of simultaneous full duplex voice and data communication services. The SDU manages the RF link protocols on the satellite side and supplies the system interface with communications management avionics. The SDU interface to other aircraft avionics involves the exchange of ARINC 429 and discrete data.

A cockpit audio system conveys cockpit voice to and from the SDU. Messages requiring cockpit action or initiation appear on the multifunction control display unit (MCDU) and/or other cockpit annunciators. The communications management unit (CMU) or equivalent routes packet data messages to and from the SDU. Cabin communications use either a cabin communications system (CCS) or an analog equivalent (cabin unit) to supply voice telephony communication. Enhancements supply facsimile (FAX) service and secure voice and personal computer modem interfaces.

The SDU supplies all essential services required to accommodate effective air/ground communications through satellite using the antenna and related RF components. Both the 40 Watt and 20 Watt HPAs supply linear power amplification to boost the RF signals up to the power levels required for transmitting to the satellite. In addition, the 20 Watt HPA (used primarily for the intermediate gain antenna) supports a beam steering function which converts tracking and pointing coordinates from the SDU into signals needed to select the desired (beam) direction towards the satellite.

Two additional LRUs may be required for some aircraft configurations:

• Radio frequency unit interface adapter (RFUIA)

• Signal conditioning unit (SCU).

The RFUIA is used in place of the radio frequency unit (RFU) in the

MCS--7000 system.

The SCU is used in MCS installations on older generation aircraft having an inertial navigation system (INS) that doe s not output n avigation da t a in an ARINC 429 high speed format which is consistent with the ARINC 704 characteristic.

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The primary function of the antenna subsystem is to complete the

communication link between the GES, the space segment, and the AES. The diplexer is a three-port RF device (antenna, transmit, and receive), which supplies signal routing and filtering functions. Signals in the receive band are routed from the antenna port to the receive port, and transmit signals are routed from the transmit port to the antenna port. The low noise amplifier establishes the noise floor of the communication system by boosting the signals and noise received from the antenna to a level much greater than the noise level of subsequent components in the receive path.

The high gain antenna (HGA) and intermediate gain antenna (IGA) transmit L--band RF signals from the HPA to a satellite, and receive L--band RF signals from a satellite for the SDU. The low gain antenna (LGA) supplies backup communications (packet data only) for the high gain antenna or intermediate gain antenna by supplying low rate packet data communication services.

The beam steering unit used in the HGA system converts tracking and pointing coordinates (aircraft relative azimuth and elevation) from the SDU into signals needed to select the antenna array elements in combinations that point the antenna beam in the desired direction towards the satellite. An antenna control unit (ACU) is required for mechanically steered antenna arrays. The antenna control unit translates digitized beam position data and beam position change commands from the SDU into a format needed to position the antenna beam in the desired direction toward the satellite. A beam steering function is incorporated into the 20 Watt HPA for use with the IGA.

(d) Cabin Communications System (CCS)

The CCS, in conjunction with the MCS avionics and a worldwide network of ground stations, supplies cabin services such as telephone, facsimile, and other communication interfaces. The CCS is partitioned into two sections: the cabin telecommunications unit (CTU) and cabin/passenger communications equipment (digitally connected telephones).

The CTU performs onboard private automatic branch exchange (PABX) telephony functions letting the digitally connected telephones make the best use of resources supplied by the MCS avionics. The CTU supplies the interface between the digitally connected phones and the SDU. A specialized interface conversion function supplies compatibility between the ARINC 746 CTU and the ARINC 741/761 SDU. This interface is made up of a high-speed (CEPT--E1) serial bus pair that accommodates up to 32 digitized voice channels along with status and control information.

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The digitally connected phones (handsets) are primarily supplied for passenger use and can be located throughout the aircraft. The digital handsets interface indirectly to the satellite communications equipment and are controlled by the CCS.

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(e) Analog Connected Telephones

The SDU has provisions to support up to two simultaneous analog audio

channels. Each analog channel supports two interface types: Global-Wulfsberg Flitephone WH--10 and the analog private branch exchange (APBX). The WH--10 is a stand-alone handset with a 12-button keypad. The APBX has analog trunk lines and in-line dual tone multifrequency (DTMF) signaling.

(f) Cockpit Voice Sou rce s

The SDU supports headset interfaces for cockpit use only. These interfaces incorporate off-hook/on-hook signaling and dialing through the combination of a control and display unit (either [SATCOM control and display unit] SCDU or MCDU), and push-to-talk (PTT) or similar switches. When the PTT switch is pushed, a microphone audio signal is sent to the selected voice channel and a discrete signal is sent to the SDU. An audible chime and call lamps announce call connections.

(g) Aircraft Avionics

Standard interfaces between the MCS avionics and the other aircraft avionics include the following:

• Communications management unit (CMU), or the management unit (MU) of the Aircraft Communications Addressing and Reporting System (ACARS), where installed.

• SATCOM control and display unit (SCDU), where installed, to supply an interface to the MCS system for system log-on, GES selection, cockpit voice call setup, data loading, and to access the SATCOM maintenance pages including fault messages.

• Central fault display system (CFDS), central maintenance computer (CMC), or on--board maintenance system (OMS), where installed, for fault reporting.

• The inertial reference system (IRS), where installed, to supply the SDU with navigation coordinates for positioning the antenna platform.

• Channels are also supplied for voice and data communication with ATC to support departure clearances by datalink, as well as ADS for non radar position reporting in oceanic regions.

• There is an ARINC 615 Airborne or portable data loader (ADL or PDL) for uploading operational software and the owner requirements table (ORT). Connections are made through front and back panel connectors on the MCS avionics LRUs.

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• The 24-bit ICAO address identifies the aircraft in which the SDU is installed. Address pins identified to take on the binary one state must be left open. Address pins identified to take on the binary zero state must be wired to address common on the airframe side of the connector. ARINC 429 interface options for the ICAO address are also supplied.

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(3) AES Classifications

(a) Each AES is classified according to the configuration and dynamic capabilities of

its aircraft avionics and antenna subsystem. An AES can be fitted with any combination of the classes of installations given in Table 1-1.

Table 1-1. Classes of Installations

Class Description

1 A Class 1 AES installation uses a low gain antenna only and supplies low rate

packet-mode data services only.

2 A Class 2 AES installation uses a high gain antenna or intermediate gain antenna,

and supplies telephony and optional circuit-mode services.

3 A Class 3 AES installation uses a high gain antenna or intermediate gain antenna,

and supplies telephony services, packet-mode data services, and optional circuit-mode data services.

4 A Class 4 AES installation uses a high gain antenna or intermediate gain antenna,

and supplies packet-mode data services only.

(4) GES Communication Links

(a) The MCS avionics supply access to ground-based networks through the ground

earth stations. Each GES supplies system synchronization and coordination through ground-to-aircraft transmissions. Four types of RF channels are defined forusewiththeMCSavionicsasgiveninTable1-2.

Table 1-2. Types of RF Channels

RF Channel Description

P--Channel

R--Channel

T--Channel

Packet-mode time division multiplex (TDM) channel used in the forward (outbound) direction (ground-to-aircraft) to carry signaling and packet-mode data. The transmission is continuous from each GES in the satellite network.

Random access (slotted Aloha) channel used in the return (inbound) direction (aircraft-to-ground) to carry signaling and packet-mode data, specifically the initial signals of a transaction (typically request signals).

Reservation time division multiple access (TDMA) channel used in the return direction only. The receiving GES reserves time slots for transmissions requested by an AES according to message length. The sending AES transmits the messages in the reserved time slots.

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C--Channel

Circuit-mode single channel per carrier (SCPC) channel used in both forward and return directions to carry digital voice or data/facsimile traffic. The use of the channel is controlled by assignment and release signaling at the start and end of each call or FAX transmission.

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C. Space Segment

(1) The space segment is made up of satellites placed in geostationary orbits to supply

air-ground packet-switched data services and voice communications, both of which use worldwide standardized conventions and capabilities. The satellites function as communication transponders to support L --band links to and from the aircraft, and supply links to and from ground earth stations. The space segment supplier for airline aeronautical satellite communications is the International Maritime Satellite Organization (INMARSAT), whose system supplies worldwide coverage. The four-region satellite system supplied by INMARSAT is shown in Figure 1-3.

D. Ground Earth Station

(1) Each GES has the necessary equipment to communicate with terrestrial networks

and communicate through satellites with the aircraft. The ground earth stations are designed to supply the airline customer with a diverse routing of national and international voice and data communications through submarine cable, satellite, and microwave links to all destinations. Automatic traffic management systems ensure efficient routing o f communications by using optimum links into public switched telephone networks (PSTN) and avoiding multiple satellite connections whenever possible.

(2) Ground earth stations are located strategically around the globe to supply

redundancy and diversity in the terrestrial extension of communications. Aircraft are connected to a GES through an in -view satellite depending on the service preference settings encoded in the SDU ORT. Some problems may be encountered when the aircraft flies in polar regions with a latitude greater than 75 degrees.

E. Terrestrial Data and Voice Networks

(1) Data and voice services available through satellites and ground earth stations include

9.6 and 4.8 kilobit/second digital voice, and packet-mode data at RF channel rates ranging from 600 bit/second up to 10.5 kilobit/second. The present worldwide complement of ground earth stations including location, operator, and coverage region are summarized in Table 1-3. Aeronautical communications through the INMARSAT satellites are transmitted to and from the terrestrial phone and data networks through these ground earth stations. The satellite regions that service these ground earth stations are shown in Figure 1-4.

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Table 1-3. Ground Earth Stations

GES Name GES ID SAT ID Service Provider

Goonhilly--AW 001 000 (AOR--W) Stratos

Southbury--AW 002 000 Telenor

Eik--AW 004 000 Telenor

Aussaguel--AW 005 000 Satellite Aircom (SITA)

Goonhilly--AE 101 001 (AOR--E) Stratos

Aussaguel--AE 103 001 SITA

Eik--AE 104 001 T elenor

Sentosa--P 201 002 (POR) Sing--Tel

Santa Paula--P 202 002 Telenor

Yamaguchi--P 203 002 KDD

Perth--P 205 002 SITA

Eik--I 301 003 (IOR) Telenor

Nunthaburi--I 302 003 Telenor

Perth--I 305 003 SITA

Yamaguchi--I 306 003 KDD

Sentosa--I 310 003 Sing--Tel

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Figure 1-4. INMARSAT Four-Region Satellite Coverage

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2. System Components

A. General

(1) The MCS avionics is comprised of the following components:

• Satellite data unit (SDU)

• High power amplifier (HPA).

(2) These components are compatible with ARINC Characteristic 741. Table 1-4 gives

the MCS system components supplied by Honeywell. Table 1-5 gives the MCS system components not supplied by Honeywell. Table 1-6 thru Table 1-8 give system component configuration information.

Table 1-4. System Components Supplied by Honeywell

MCS--4000/7000

Component Model No. Honeywell Part No.

Satellite Data Unit SD--700 7516118--xxyyy

High Power Amplifier (40 W) HP--600 7516250--xxyyy

High Power Amplifier (20 W) HP--700 7516251--xxyyy

Diplexer/Low Noise Amplifier -- Aero--I -- -- 7516193--901 Intermediate Gain Antenna -- -- 7516194--901 Radio Frequency Unit Interface Adapter (RFUIA)

NOTES:

1. The five digit dash number (xxyyy) corresponds to the hardware/software version of the unit where the first two digits correspond to the hardware version and the last three digits correspond to the software version.

2. The RFUIA is installed with the 115 V ac/400 Hz, 7--channel SDU (6 voice, 1 data), or 28 V dc.

-- -- 7516222--901

Figure 1-6

Figure 1-7

Table 1-5. System Components Not Supplied by Honeywell

Component Comments

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SDU Installation Equipment (See Note) ARINC 600 6--MCU tray, cables, connectors, assemblies,

mounting hardware, and kits

HPA (40 W) Installation Equipment (See Note)

HPA (20 W) Installation Equipment (See Note)

Signal Conditioning Unit (SCU) RACAL Part No. 56047--010XX

ARINC 600 8--MCU tray, cables, connectors, assemblies, mounting hardware, and kits

ARINC 600 4--MCU tray, cables, connectors, assemblies, mounting hardware, and kits

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SYSTEM DESCRIPTION, INSTALLATION,

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TEMPORARY REVISION NO. 23-2

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Page 2 of 3

20 Jun 2017

SDU Part Number

Description

7516118-27010

115 V ac/400 Hz, 7-channel SOU (6 voice, 1 data)

7516118-77010

115 V ac/400 Hz, 7-channel SDU (6 voice, 1 data), Digital RFM

7516118-57010

+28 V dc, 7- channel SOU (6 voice, 1 data)

7516118-24010

115 V ac/400 Hz, 4-channel SOU (3 voice, 1 data)

7516118-74010

115 V ac/400 Hz, 4-channel SDU (3 voice, 1 data), Digital RFM

7516118-54010

+28 V dc, 4- channel SOU (3 voice, 1 data)

7516118-27020

115 V ac/400 Hz, 7-channel SDU (6 voice, 1 data) for Airbus applications, (HW MOD J contains Digital RFM)

7516118-24020

115 V ac/400 Hz, 4-channel SDU (6 voice, 1 data) for EPIC applications, (HW MOD J contains Digital RFM)

7516118-27011

115 V ac/400 Hz, 7-channel SOU (6 voice, 1 data) for EPIC applications

7516118-57011

+28 V dc, 7-channel SOU (6 voice, 1 data) for EPIC applications

7516118-24011

115 V ac/400 Hz, 4-channel SOU (3 voice, 1 data) for EPIC applications

7516118-54011

+28 V dc, 4- channel SOU (3 voice, 1 data) for EPIC applications

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INSERT PAGE 2 OF 3 FACING PAGE 1-13. Reason: To add PN 7516118-77010 and PN 7516118-74010, and to change description for PNs

75166118-27020 and -24020 in Table 1-6.

Table 1-6 is changed as follows:

Table 1-6. SDU Configurations

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SeeTR

SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

MCS--4000/7000 Multi--Channel SATCOM System

Table 1-5. System Components Not Supplied by Honeywell (cont)

Component Comments

High Gain Antenna Equipment BAE Systems -- Canada

Ball Aerospace -- USA Dassault Electroniq -- France

NOTE:

Installation of this equipment is dependent on the specific requirements of the operator. Refer to Appendix A, Vendor Equipment, for additional information.

Table 1-6. SDU Configurations

SDU Part Number Description

75161 18--27010 115 V ac/400 Hz, 7--channel SDU (6 voice, 1 data)

75161 18--57010 +28 V dc, 7--channel SDU (6 voice, 1 data)

75161 18--24010 115 V ac/400 Hz, 4--channel SDU (3 voice, 1 data)

75161 18--54010 +28 V dc, 4--channel SDU (3 voice, 1 data)

75161 18--27020 115 V ac/400 Hz, 7--channel SDU (6 voice, 1 data) for Airbus

applications

75161 18--24020 115 V ac/400 Hz, 4--channel SDU (3 voice, 1 data) for Airbus

applications

75161 18--27011 115 V ac/400 Hz, 7--channel SDU (6 voice, 1 data) for EPIC

applications

75161 18--57011 +28 V dc, 7--channel SDU (6 voice, 1 data) for EPIC applications

75161 18--24011 115 V ac/400 Hz, 4--channel SDU (3 voice, 1 data) for EPIC

applications

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75161 18--54011 +28 V dc, 4--channel SDU (3 voice, 1 data) for EPIC applications

Table 1-7. HPA (40 Watt) Configurations

Software

HPA Part No.

7516250--10001 A 3--channel initial release

7516250--15020 B 3--channel update with cabin voice

7516250--18033 C0.0 6--channel cabin voice and data (1--data, 5--voice) and fax

7516250--18036 C2.0 6--channel cabin voice and data (1--data, 5--voice) and fax

7516250--19034 C3.0 Improves log--on capability and reversion; adds maintenance

7516250--19037 C3.5 Adds Boeing 777 capability

Package

(2400/4800 bps)

pages

Description

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Table 1-7. HPA (40 Watt) Configurations (cont)

Software

HPA Part No. Description

7516250--19037 C3.5 Adds Boeing 777 capability 7516250--20050 D2.0 Adds several improvements to BITE, including antenna VSWR

7516250--55050 D2.0 Adds several improvements to BITE, including antenna VSWR

7516250--60001 A 3--channel initial release 7516250--60020 B 3--channel update with cabin voice 7516250--60033 C0.0 6--channel cabin voice and data (1--data, 5--voice) and fax

Package

detection reporting and compatibility with hardware Mod D (Software Mod F); Uses 115 V ac primary power.

(2400/4800 bps)

7516250--60050 D2.0 Adds several improvements to BITE, including antenna VSWR

detection reporting and compatibility with hardware Mod D (Software Mod F); Uses 28 V dc primary power.

NOTE: For the various part numbers, --1XXXX refers to an air transport LRU, while --55XXX and --6XXXX

refers to a business and commuter LRU. The functional descriptions are the same for both.

Table 1-8. HPA (20 Watt) Configurations

Software

HPA Part Number

7516251--20060 E1.5 20 Watt HPA with Aero--I IGA beam steering functionality; Uses

7516251--60060 E1.5 20 Watt HPA with Aero--I IGA beam steering functionality; Uses

NOTE: For the various part numbers, --2XXXX refers to an air transport LRU, while --6XXXX refers to a

business and commuter LRU. The functional descriptions are the same for both.

Package

Description

115 V ac or 28 V dc power supply.

3. System Description

A. General

(1) The system description gives a general overview and summary of the features and

interfaces that the MCS implements. Figure 1-7 is a simplified block diagram of the MCS system.

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(2) The core of the AES avionics subsystem is the MCS avionics, supporting data, and

voice communications at rates from 600 to 21,000 bits per second. Interfaces to various aircraft systems including cockpit voice, cabin voice/data, aircraft avionics, and the antenna subsystem enable the MCS avionics to handle data and voice messaging functions for the AES.

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(3) The SDU supplies all essential services required to accommodate effective

air/ground communications through satellite, using the antenna and related RF components. The SDU manages the RF link protocols on the AES side and supplies the system interface with communications management avionics. The HPA boosts the signal to be transmitted up to the power levels required for transmission to the satellite.

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Blank Page

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Figure 1--4. MCS Avionics Block Diagram

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B. Satellite Data Unit

(1) General

(a) The SDU is the core element of the MCS avionics and is responsible for overall

AES control and monitoring. The unit interfaces to many aircraft avionics (e.g., CFDS, primary/secondary IRS, CMU 1/2, MCDU 1/2/3, ADL, etc) and has operational functionality, including coding and decoding all system voice and data signals and defining system protocols. The SDU contains six channels capable of supplying simultaneous full duplex voice communication, one channel of data 2/3 communication, and RF circuitry sufficient to operate the AES. Figure 1-5 shows the circuit card assembly (CCA) layout for the MCS--7000 SDU. Removal of one of the triple transcoder modem (TTCM) CCA results in the MCS--4000 SDU.

MCS--4000/7000 Multi--Channel SATCOM System

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Figure 1-5. MCS--4000/7000 SDU Equipment Description

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(b) The format for voice/da t a codes follows the INMARSAT system definitions for

voice an d data transmission and reception. The INMARSAT system uses a digital format for voice and data. The SDU digitizes the voice or data signal and adds special codes to make the aircraft-to-ground station connection possible. Voice signals are transmitted at a rate designed to supply high voice quality (perceived quality is close to that of a good quality public telephone line). When signal processing is complete, the coded voice/data signal is sent to HPA. The SDU also controls the protocols for automatic call, setup, and clear-down. System protocols are defined so the designated GES recognizes it is being called by the AES.

for voice and data service, and the RF transmit/receive circuitry needed to convert modulated baseband signals to an L-band frequency (and vice versa). All AES satellite signals use digital coding and modulation, which include the voice circuits. The voice interface modules translate baseband analog voice signals to and from the 9600 bps or 4800 bps digital coding standard. Efficient information compression and coding techniques supply high voice quality at an economical bit rate. The modems, one for each communication channel, perform all of the physical layer signal processing functions, including multiplexing/demultiplexing, interleaving/de--interleaving, scrambling/unscrambling, modulation/demodulation, and Doppler effect correction.

(d) The SDU system table memory contains the location of all satellites. When a

GES is selected, the SDU uses this location information and aircraft positional information (through an ARINC 429 interface) from the IRS to compute the position of the satellite relative to the aircraft. The SDU then transmits pointing and tracking coordinates (aircraft relative azimuth and elevation) to the beam steering unit (BSU) to permit optimum signal transmission and reception between the high gain antenna subsystem and the satellite.

(e) The high gain antenna subsystem translates these steering commands into

control signals to the antenna(s). Once the beam has been steered toward the satellite, the SDU receives the pilot tone from the satellite transponder through its receive RF link from the antenna subsystem.

(f) The SDU is now free to route communications data over the satellite link. The

SDU accomplishes this by sending commands to the MU and the CTU. These commands are sent through ARINC 429 and CEPT E1 interfaces between the SDU and the MU/CTU. Data is then routed from the MU/CTU to the SDU. In the SDU, the baseband data modulates RF carriers, which are sent to the HPA for amplification, and then to the antenna subsystem for transmission to the satellite. The SDU can adjust the transmission frequency in one-Hertz increments to compensate for the Doppler shift caused by the speed of the aircraft. The receive mode is handled in a similar manner. Since the MCS is a full-duplex system, the transmit and receive signals are processed simultaneously a s in conventional terrestrial telephone equipment.

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(2) Output Power Control

(a) General

The AES output power to the satellite, specified and calculated as effective isotopic radiated power (EIRP) from the antenna in the direction of the satellite, is controlled by the SDU as specified in the following paragraphs. The SDU is capable of controlling up to one HGA HPA, one LGA HPA, or one IGA HPA. These HPA(s) can be a linear or class C type in any combination. The SDU does not establish a C-channel voice call using a class C HGA HPA or through any LGA HPA.

(b) Assumed Initial C-Channel EIRP

The SDU calculates the assumed initial C-channel EIRP as being the lowest of the currently GES-commanded EIRPs for any/all C-channels in progress. If there are no C-channels currently in progress, the SDU uses the value in ORT item xxx, or the value in ORT item xxx reduced by 6 dB if the SDU is currently logged on through a spot-beam.

The SDU calculates the current reserved EIRP as the summation in Watts of the following EIRPs:

• The power reserved for the R/T-channel transmission, for the highest bit rate assigned, calculated from the EIRP assigned in the log-on confirm signal, or the most recent data channel reassignment, if any.

• The GES-assigned EIRPs of all the currently active C-channel carriers, if any.

• The cockpit reserved channel power if the reservation has been made through ORT option vii and is not in use. This continuously tracks the assumed initial C-channel EIRP. If it is in use, then the actual GES-assigned EIRP is used.

• The power reserved for any C-channel calls in the process of being set up (i.e., after resources have been allocated but no C-channel assignment signal has been received). For each such channel, the assumed initial C-channel EIRP is used.

(d) Current and Projected or Peak-To-Average Power Ratio

1 If the HPA is linear, the SDU calculates the current peak-to-average power

ratio based on the EIRP levels for all the carriers considered in the current reserved EIRP calculation. The current peak-to-average ratio value is sent to the HPA periodically, alternating with the projected peak-to-average ratio (i.e., what the peak-to-average ratio would be if one additional C-channel were established).

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The SDU waits at least 450 milliseconds after transmitting the HPA

command word before assuming the received HPA maximum available RMS output power corresponds to the most recently sent peak-to-average ratio in the HPA command words. The current peak-to-average ratio is sent in order to calculate the current available EIRP from the returned maximum available RMS power. The projected peak-to-average ratio is sent in order to determine (along with other criteria) if an additional C-channel can be established, if and when it is requested. If all carriers are at the same power level (not true in general), the peak-to-average ratio is equal to the number of carriers. If the HPA is class C, the SDU always sends a peak-to-average ratio equal to 1.

(3) Installation Dependent Considerations

(a) General

The SDU stores the following installation dependent values to enable it to set the EIRPs accurately:

• SDUtoHPAloss(assumedcommonforbothLGAandHGAHPAs)

• HPA to antenna loss (two values are stored, one for the HGA HPA, and a

separate value for the LGA HPA)

• HPA in use is class C, the SDU stores the HPA maximum output power.

(b) SDU to HPA Loss

The SDU stores the calibrated SDU to HPA loss in nonvolatile memory. When the HPA is linear, this value is calculated once whenever there is an R--or T--channel burst transmission in the absence of C--channel transmission. This value is also calculated whenever there is a single C--channel transmission in the absence of R-- or T--channel, unless the reported actual power output value in the HPA status word:

• Matches or is less than the minimum reportable actual power value stored in ORT item xxix

• Matches either the unique code 00100 or 3 dB greater than 40 W or the flag was set indicating the HPA or modem backoff was limited.

for at/below measurable range

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When a single measurable carrier (R -- /T--or C-- channel) is present, the SDU recalculates the SDU to HPA loss as the actual output power reported by the HPA, less the HPA nominal gain, plus the HPA backoff, or SDU calculated RFM power. This value includes the actual cable loss, plus any uncompensated variation from nominal in the HPA gain, and any variation from the calibrated RFM output power (due to temperature). This value also lets the SDU accurately determine the common transmit gain. If the calibration results in a value outside the range of 10 dB to 30 dB, a failure is raised for the HGA HPA and LGA HPA.

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The SDU is capable of storing in nonvolatile memory the actual loss (to the nearest tenth of a dB) between the HPA and the input to the antenna for use in the power control computation. This loss is the sum of the HPA to diplexer cable loss, the high power relay loss (if used), the diplexer loss, and the diplexer to antenna cable loss in an ARINC 741 system. This value is expected to be between 0.9 and 2.5 dB, but the SDU allows the entry of values in the range of 0.0 to 5.0 dB. A separate value is maintained and used for each an t enna subsystem.

This loss value is necessary to enable the SDU to accurately set the antenna EIRPs, and to determine power availability for additional C-channels. This value is not part of the ORT and is not an option. The value is e stimated /ca librated at th e time of system installation or commissioning, and can vary among otherwise identical installations. It is inadequate to assume a default of either end of the range, since at the low end the AES would not necessarily make the return link in marginal conditions. At the high end, the SDU would radiate all carriers high, wasting power and prematurely inhibiting further calls from being set up.

(d) Class C HPA Maximum Output Power

When the HPA is class C, the SDU stores the calibrated HPA maximum output power value in nonvolatile memory. This value is calculated once per burst when there is a single measurable carrier present, unless the reported actual power output value in the HPA status word:

• Matches or is less than the minimum reportable actual power value stored in ORT item xxix

• Matches either the unique code 00100 or 3 dB greater than 40 W; or the flag was set indicating the HPA or modem backoff was limited.

This value is the actual output power reported by the HPA, plus the HPA backoff. If the calibration results in a value outside the range of 14 dBW to 21 dBW, a failure is raised for the HGA HPA and LGA HPA.

(4) Antenna Subsystem Selection

(a) The purpose of installing both HGA and LGA subsystems simultaneously is to

increase system availability and geographical orientation coverage. When the SDU has the choice of antenna subsystems (HGA o r LGA), eithe r as part of a single MCS system or in its role as half of a dual system, reversion from HGA t o LGA (and from LGA to HGA) is accomplished by automatic means. Automatic reversion from the HGA to the LGA occurs only upon failure of the HGA subsystem. The SDU automatically switches from the LGA to the HGA if the HGA subsystem reverts to a normal state. In lieu of a physically separate LGA, an HGA is also usable as a steered LGA when its gain drops below the level specified by ORT item xxii.

for at/below measurable range

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(b) Loss of reliable communications with a GES normally occurs as a result of

channel degradation. When channel degradation occurs, the AES considers itself logged-off and searches for another GES. If no GES is found for communications using the HGA subsystem, au tomatic switching to the LGA subsystem does occur. Manual reversion through the SCDU is the only way the SDU switches from the HGA subsystem to the LGA subsystem.

The satellite spot beams supply a times 8 (x8) amplification. Less power is required for C--channel (circuit mode) operation that equates to less cost per minute of operation.

C. High Power Amplifier

(1) The SDU sends such information as power amplifier on/off commands and

amplification gain commands to the HPA. The bidirectional link carries status and maintenance information to the SDU such as gain verification, standing wave ratio data, and indication of dangerous system conditions such as temperature warnings or power supply failures.

(2) The HPA supplies RF power amplification of the L-band signals generated by the

SDU to a power level required for transmission to the satellite. Because multiple signals are transmitted through the HPA, the HPA is a linear device (i.e., operating class AB) capable of amplifying more than one signal at a time. An average of 40 Watts RF output power is developed by the HPA (up to 25 Watts RF power by the 20 Watt HPA) while passing multiple signals without generating excessive intermodulation products.

(3) In addition to providing RF power amplification, the HPA must control output power to

supply the desired EIRP from the AES. The SDU controls the gain of the Honeywell HPA over a 25-dB range in 1-dB increments through the ARINC 429 interface. This lets automatic adjustment of signal strength compensate for a wide variety of conditions. The HPA also measures output power and available power and reports to the SDU, which uses the information to determine if additional calls can be accommodated.

(4) Under favorable propagation conditions, the full output power capability of the HPA is

not required. The HPA automatically consumes less power and dissipates less heat when full power is not used.

(5) The 20 Watt HPA supplies beam steering capabilities previously implemented in the

antenna beam steering unit. Commands are generated to steer the antenna elements based on the SDU, IRS information, and beam map data stored in the HPA.

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D. Avionics Configurations

(1) The SDU determines the configuration installed on the aircraft, including the

presence of optional peripherals, by examining the system configuration pins. The SDU supports interaction only with those peripherals indicated as being present by the configuration pins.

(2) The Aero H+ SATCOM system requires installation of an SDU and 40 Watt HPA, and

supports seven independent simultaneous channels for voice and data communications. One channel is dedicated to data and system management transactions. The remaining six channels are available for analog or digital voice communications.

(3) The Aero I SATCOM system requires installation of an SDU and 20 Watt HPA, and

4. MCS Component Descriptions

A. Physical Description

(1) The LRUs are designed to perform reliably under field conditions and to supply ease

of maintenance when required. Each LRU is designed as a modular concept unit (MCU), as defined by ARINC Characteristic 600, to permit easy replacement of each shop replaceable unit (SRU). The SRUs use both digital and analog solid state circuitry constructed using a mixture of surface mount technology (SMT) and dual in-line packaging (DIP) technology.

(2) All SRUs are built to standards that qualify them for both airline and business aircraft

usage. Adjustment mechanisms are accessible with the SRU installed in the LRU. These SRUs can be removed to reduce the number of functional channels without compromising the functionality of the remaining channels.

(3) The MCS system components meet the requirements specified in parts A and B of

the Minimum Operational Performance Standards for Aeronautical Mobile Satellite Services Document, Document No. RTCA/DO--210.

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B. Satellite Data Unit (SDU)

(1) The SDU is packaged as an ARINC 600 6 -- MCU suitable for mounting in the

equipment bay. The mechanical chassis is constructed of lightweight aluminum alloy sheet metal; forced air moving through the chassis in an upward or downward direction supplies internal cooling. Two hold-down clamps enable the unit to be firmly clamped in the mounting rack. The unit is carried by a fixed C-shaped handle mounted to the front panel assembly.

(2) The front panel assembly contains a 20-character alphanumeric display for displaying

built-in test equipment (BITE) failure messages, system LRU part numbers, and the ORT identification. The display remains inactive when its temperature is less than

-- 1 0 °C(+14°F) or greater than +50 °C(+122°F). The front panel also contains two momentary action buttons labeled TEST and CM/SCROLL. The TEST button initiates BITE in the SDU. The CM/SCROLL button lets the alphanumeric display scroll through the BITE failure messages and the software confirmation numbers.

(3) The front panel also contains an ARINC 615 portable data loader connector and a

primary cell for the real-time clock/calendar function of the processor module.

(4) The rear connector receptacle is a size No. 2 shell assembly (in accordance with

ARINC 600) that engages a mating connector in the mounting rack when the SDU is installed. The top and middle inserts are type 02 arrangements and the bottom insert is a type 04 arrangement. Index pin code 04 is used on both the SDU and the mounting rack connectors.

(5) The SDU is shown in Figure 1-6. The SDU leading particulars are given in Table 1-9.

DO--160D environmental categories for the SDU are given in Table 1-10.

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Figure 1-6. Satellite Data Unit

Table 1-9. SDU Leading Particulars

Characteristic Specification

Dimensions (maximum):

• Height ................................ 7.624 in. (193.65 mm)

• Width ................................. 7.51 in. (190.75 mm)

• Length ................................ 15.26 in. (337.60 mm)

Weight (maximum) ....................... 21 lb (9.6 kg)

Power Requirements:

• ACVoltage ............................ 104 to 122 V ac, 380 to 420 Hz (normal operation)

97 V ac, 360 Hz minimum; 134 V ac, 440 Hz maximum

• DCVoltage ............................ 22.0 to 30.3 V dc (normal operation)

20.5 V dc minimum, 32.2 V dc maximum

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Table 1-9. SDU Leading Particulars (cont)

Characteristic Specification

AC Current Requirements1.:

• Nominal at 115 V ac (Current/Power Factor) 1.3 amps/0.70

• Maximum at 104 V ac (Current/Power

Factor)................................

DC Current Requirements:

• Nominal at 28 V dc ..................... 3.8 amps

• Maximum at20.5V dc .................. 7.0 amps

Circuit Breaker Ratings:

• 115VacCircuitBreaker ................ 3 amp TYPE A

2.1 amps/0.91

• 28VdcCircuit Breaker ................. 10 amp TYPE A

User Replaceable Parts ................... None

OperatingTemperature.................... -- 5 5 _C(--67_F) to +70 _C (158 _F)

OperatingAltitude ........................ to 70,000 ft (21.34 kilometers)

Cooling Requirements2.:

• Minimum ..............................

• Maximum .............................

Power Dissipation3.:

• Nominal ............................... 105 W

• Maximum ............................. 198 W

Mating Connectors:

• J1 .................................... Radiall Part No. NSXN2P201X004

• J2 .................................... Honeywell Part No. 4004295--160, ITT Part No.

Mounting ................................ ARINC 600 6--MCU Tray Assembly

NOTES:

1. All power factors (PF) are leading.

2. Refer to Appendix A, Vendor Equipment, for mounting trays with integral cooling fans that meet the cooling requirements.

3. The SDU draws an additional 20 W during the first 10 minutes (maximum) of operation at 25_C(77_F) because of the OCXO. The OCXO continuously dissipates this additional 20 W at --55 _C(--67_F).

0.15±0.05 in. (3.81±1.27 mm) of water at a flow rate of

72.8

2.0 lb (33.0±0.9 kg) per hour

0.25±0.05 in. (6.35±1.27 mm) of water at a flow rate of

96.2

2.0 lb (43.6±0.9 kg) per hour

KJ6F18A53P

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Table 1-10. SDU DO--160D Environmental Categories

Environmental Condition Category

Temperature and Altitude Category A2E1/Z (E1)

Temperature Variation Category B

Humidity Category A

Shock Category B

Vibration Category SB2

Explosion Category E

Waterproofness Category X

Fluids Susceptibility Category X

Sand and Dust Category X

Fungus Resistance Category X

Salt Spray Category X

Magnetic Effect Category Z

Power Input -- 115 V ac Category E

Power Input -- 28 V dc Category BZ

Voltage Spike Category A

Audio Frequency Susceptibility -- 115 V ac Category E

Audio Frequency Susceptibility -- 28 V dc Category Z

Induced Signal Susceptibility Category Z

Radio Frequency Susceptibility Category RRR

Radio Frequency Emissions Category M

Lightning Induced Category A3E3

Lightning Direct Category X

Icing Category X

Electro Static Discharge Category A

NOTES:

1. E1 -- Operating High Temperature/High Short Time = 70 °C (158 °F).

2. Z -- The power input requirements for the 28 V dc LRU are category Z except for an emergency operation, in which case the requirements of category B apply.

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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

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C. High--Power Amplifier (40 Watt)

(1) The HPA is packaged as an ARINC 600 8--MCU suitable for mounting in the

equipment bay or near the antenna system. The mechanical chassis is constructed o f lightweight aluminum alloy sheet metal. Forced air moving through the chassis in an upward or downward direction supplies internal cooling. Two hold-down clamps let the unit be firmly clamped in the mounting rack. The unit is carried by a fixed C-shaped handle mounted to the front panel assembly.

(2) The front panel assembly contains a PTT switch to initiate BITE and a red (FAIL) and

green (PASS) light emitting diode(LED) to indicate BITE status. The front panel also contains an ARINC 615 portable data loader connector and an RF monitor port.

(3) The rear connector receptacle is a size No. 2 shell assembly (in accordance with

ARINC 600) that engages a mating connector in the mounting rack when the HPA is installed. The top insert is a type 08 arrangement, the middle insert is a type 05 arrangement, and the bottom insert is a type 04 arrangement. Index pin code 08 is used on both the HPA and mounting rack connectors.

(4) The HPA (40 Watt) is shown in Figure 1-7. The leading particulars for the HPA (40

Watt) are given in Table 1-11. DO--160C environmental categories for the HPA (40 Watt) are given in Table 1-12.

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Figure 1-7. High--Power Amplifier (40 and 20 Watt)

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Table 1-11. HPA (40 Watt) Leading Particulars

Characteristic Specification

Dimensions (maximum):

• Height ................................ 7.813 in. (198.45 mm)

• Width ................................. 10.22 in. (259.59 mm)

• Length ................................ 15.20 in. (386.08 mm)

Weight (maximum) ....................... 29.15 lb (13.22 kg)

Power Requirements:

• ACVoltage ............................ 104 to 122 V ac, 380 to 420 Hz (normal operation)

97 V ac, 360 Hz minimum; 134 V ac,440 Hz maximum

• DCVoltage ............................ 22.0 to 30.3 V dc (normal operation)

20.5 V dc minimum, 32.2 V dc maximum

AC Current Requirements1.:

• Nominal at 115 V ac (Current/Power Factor) 1.94 amps/0.95

• Maximum at 104 V ac (Current/Power

Factor)................................

DC Current Requirements:

• Nominal at 28 V dc ..................... 7.3 amps

• Maximum at20.5V dc .................. 8.2 amps

RF Power Output:

• Rated operating power .................. 40 W (multiple carriers)

• Maximum power ....................... 80 W (short duration, single carrier)

Circuit Breaker Ratings:

• 115VacCircuitBreaker ................ 7.5 amp TYPE A

• 28 V dc Circuit Breaker2................. 30 amp TYPE A

User Replaceable Parts ................... None

OperatingTemperature.................... -- 5 5 _C(--67_F) to +70 _C (158 _F)

OperatingAltitude ........................ to 70,000 ft (21.34 kilometers)

2.2 amps/0.96

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Cooling Requirements3.:

• Minimum ..............................

• Maximum .............................

Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.

0.15±0.05 in. (3.81±1.27 mm) of water at a flow rate of

121.3

2.0 lb (55.0±0.9 kg) per hour

0.25±0.05 in. (6.35±1.27 mm) of water at a flow rate of

176.4

2.0 lb (80.0±0.9 kg) per hour

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Table 1-11. HPA (40 Watt) Leading Particulars (cont)

Characteristic Specification

Power Dissipation:

• Nominal ............................... 300 W

• Maximum ............................. 362 W

Mating Connectors:

• J1 .................................... Radiall Part No. NSXN2P221X0008

• J2 .................................... Honeywell Part No. 4004295--160,

ITT Part No. KJ6F18A53P

• J3 .................................... BNC Plug

Mounting ................................ ARINC 600 8--MCU Tray Assembly

NOTES:

1. All PF are leading.

2. Wiring can not exceed 18 V dc drop at 30 amps.

3. Refer to Appendix A, Vendor Equipment, for mounting trays with integral cooling fans that meet the cooling requirements.

Table 1-12. HPA (40 Watt) DO--160C Environmental Categories

Environmental Condition Category

Temperature and Altitude Category A2E1/Z (E1)

Temperature Variation Category B

Humidity Category A

Shock Category B

Vibration Category BLMY

Explosion Category E1

Waterproofness Category X

Fluids Susceptibility Category X

Sand and Dust Category X

Fungus Resistance Category X

Salt Spray Category X

Magnetic Effect Category Z

Power Input -- 115 V ac Category E

Power Input -- 28 V dc Category Z

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Voltage Spike Category A

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MCS--4000/7000 Multi--Channel SATCOM System

Table 1-12. HPA (40 Watt) DO--160C Environmental Categories (cont)

Environmental Condition Category

Audio Frequency Susceptibility -- 115 V ac Category E

Audio Frequency Susceptibility -- 28 V dc Category Z

Induced Signal Susceptibility Category Z

Radio Frequency Susceptibility Category W

Radio Frequency Emissions Category Z

Lightning Induced Category K

Lightning Direct Category X

Icing Category X

NOTES:

1. E1 -- Operating High Temperature/High Short Time = 70 °C (158 °F).

2. Z -- The power input requirements for the 28 V dc LRU are category Z except for an emergency operation, in which case the requirements of category B apply.

3. W -- Performance of this test is required to satisfy the HIRF requirements. The LRUs must survive a category W event without degradation (i.e., regain normal operation at the termination of the HIRF event), and must operate through (with performance degradation permitted) and after (without performance degradation) a category T event.

D. High--Power Amplifier (20 Watt)

(1) The HPA is packaged as an ARINC 600 4--MCU suitable for mounting in the

(2) The front panel assembly contains a PTT switch to initiate BITE and a red (FAIL) and

green (PASS) LED to indicate BITE status. The front panel also contains an ARINC 615 portable data loader connector.

(3) The rear connector receptacle is a size No. 2 shell assembly (in accordance with

(4) The HPA (20 Watt) is shown in Figure 1-7. The leading particulars for the HPA (20

Watt) are given in Table 1-13. DO--160D environmental categories for the HPA (20 Watt) are given in Table 1-14.

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Table 1-13. HPA (20 Watt) Leading Particulars

Characteristic Specification

Dimensions (maximum):

• Height ................................ 7.64 in. (194.056 mm)

• Width ................................. 4.90 in. (124.46 mm)

• Length ................................ 15.26 in. (387.604 mm)

Weight (maximum) ....................... 15.80 lb (7.17 kg)

Power Requirements:

• ACVoltage ............................ 104 to 122 V ac, 380 to 420 Hz (normal operation)

97 V ac, 360 Hz minimum; 134 V ac, 440 Hz maximum

• DCVoltage ............................ 22.0 to 30.3 V dc (normal operation)

20.5 V dc minimum, 32.2 V dc maximum

AC Current Requirements1.:

• Nominal at 115 V ac (Current/Power Factor) 1.94 amps/0.96

• Maximum at 104 V ac (Current/Power

Factor)................................

DC Current Requirements:

• Nominal at 28 V dc ..................... 7.3 amps

• Maximum at20.5V dc .................. 12 amps

RF Power Output:

• Rated operating power .................. 25.1 W (under all conditions)

• Maximum power ....................... 25.1 W (under all conditions)

Circuit Breaker Ratings:

• 115VacCircuitBreaker ................ 7.5 amp TYPE A

• 28VdcCircuit Breaker ................. 15 amp TYPE A

User Replaceable Parts ................... None

OperatingTemperature.................... -- 1 5 _C(5_F) to +70 _C (158 _F)

OperatingAltitude ........................ to 55,000 ft (16.76 kilometers)

2.2 amps/0.96

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Cooling Requirements (Minimum)2..........

Power Dissipation:

• Nominal ............................... 150 W

• Maximum ............................. 219 W

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0.20±0.12 in. (5±3 mm) of water at a flow rate of 72.8

2.0 lb (33.0±0.9 kg) per hour

23--20-- 27

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MCS--4000/7000 Multi--Channel SATCOM System

Table 1-13. HPA (20 Watt) Leading Particulars (cont)

Characteristic Specification

Mating Connectors:

• J1 .................................... Radiall Part No. NSXN2P221X0008

• J2 .................................... Honeywell Part No. 4004295--160, ITT Part No.

KJ6F18A53P

Mounting ................................ ARINC 600 4--MCU Tray Assembly

NOTES:

1. All PF are leading.

2. Refer to Appendix A, Vendor Equipment, for mounting trays with integral cooling fans that meet the cooling requirements.

Table 1-14. HPA (20 Watt) DO--160D Environmental Categories

Environmental Condition Category

Temperature and Altitude Category A2E1/Z (E1)

Temperature Variation Category B

Humidity Category A

Shock Category B

Vibration Category SB2

Explosion Category E

Waterproofness Category X

Fluids Susceptibility Category X

Sand and Dust Category X

Fungus Resistance Category X

Salt Spray Category X

Magnetic Effect Category Z

Power Input -- 115 V ac Category E

Power Input -- 28 V dc Category BZ

Voltage Spike Category A

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Audio Frequency Susceptibility -- 115 V ac Category E

Audio Frequency Susceptibility -- 28 V dc Category Z

Induced Signal Susceptibility Category Z

Radio Frequency Susceptibility Category RRR

Radio Frequency Emissions Category M

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Table 1-14. HPA (20 Watt) DO--160D Environmental Categories (cont)

Environmental Condition Category

Lightning Induced Category A3E3

Lightning Direct Category X

Icing Category X

Electrostatic Discharge Category A

NOTES:

1. E1 -- Operating High Temperature/High Short Time = 70 °C (158 °F).

2. BZ -- The power input requirements for the 28 V dc version of the 20 Watt HPA are category Z except for an emergency operation, in which case the requirements of category B apply.

3. RRR -- Performance of this test is required to satisfy the HIRF requirements.

E. CMA--2200 Intermediate Gain Antenna

(1) The Intermediate Gain Antenna supplies a minimum of 6 dB antenna gain (8 dB

nominal) and operates with the 20 W HPA. The IGA is manufactured by BAE Systems Canada Inc. (formerly Canadian Marconi Company Aerospace) under both BAE Systems -- Canada Part No. 100--602372--000 and Honeywell Part No. 7516194--901. Features of the IGA are given in Table 1-15.

Table 1-15. CMA-- 2200 Intermediate Gain Antenna Features

Characteristic Specification

Servicecoverage.........................

•

Receive

•

Transmit

Polarization ..............................

Receive figure of merit (G/T)

..............................

.............................

............

less than 95% of the Inmarsat hemisphere

1525.0 -- 1559.0 MHz

1626.5 -- 1660.5 MHz

Right hand circular

-- 15.5 dB/K typical, -- 19 dB/K minimum

Effective Isotropic Radiated Power (EIRP) 19.5 dBW typical, 16.5 dBW minimum

Phase discontinuity

.....................

2.5_ typical, less than 30_ for 99% of all beam steering increments

Beam switch ing

.........................

50 µs maximum

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Carrier/Multipath

Satellite discrimination

........................

..................

Latitude global Inmarsat satellite coverage

Required antenna gain

...............................

..................

Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.

15 dB typical, 10 dB minimum at 5_ elevation; 20 dB typical,12 dB minimum a t 20_ elevation

16 dB typical, 7 dB minimum

86 degrees

6dB

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Table 1-15. CMA--2200 Intermediate Gain Antenna Features (cont)

Characteristic Specification

Support/Test equipment required

........

None at organizational level

Design characteristics (RTCA/ARINC/TSO/etc.)

................

DO--160C, ARINC 761, MOPS, SARPS

(2) Other features of the CMA--2200 IGA include:

• Inmarsat Generation 3 Spot Beam coverage

• Proven compatibility with ARINC 761 intermediate--gain antenna subsystems

• BIT status reporting.

(3) The leading particulars for the CMA--2200 IGA are given in Table 1-16. DO--160C

environmental categories for the CMA--2200 IGA are given in Table 1-17.

Table 1-16. CMA--2200 IGA Leading Particulars

Characteristic Specification

Dimensions (maximum):

• Height ................................ 3.82 in. (97.0 mm)

• Width:

-- At radome ........................... 3.22 in. (81.8 mm)

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-- Atbase ............................. 4.25 in. (108.0 mm)

• Length ................................ 29.92 in. (760.0 mm)

Weight (maximum) ....................... 6lb(2.7kg)

Power Requirements ..................... 15 V dc, 8 V dc and --80 V dc (7 Watts)

Operating Environment:

• Temperature range (operating) ........... -- 5 5 _ to +70_ C(--67_ to +158_ F)

• Temperature range (non--operating) ....... -- 5 5 _ to +85_ C(--67_ to +158_ F)

• Operatingaltitude ...................... to 70,000 ft (21.34 km)

Mating Connectors:

• J1 .................................... Circular Connector -- Part No. D38999/26FB35SN

• J2 .................................... TNC JACK -- Mates with TNC plug

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Table 1-17. CMA-- 2200 IGA DO--160C Environmental Categories

Environmental Condition Category

Temperature and Altitude E1

In--Flight Loss of Cooling X

Temperature Variation A

Humidity C

Operational Shock and Crash Safety -- --

Vibration E

Explosion Proofness X

Waterproofness S

Fluids Susceptibility F

Sand and Dust D

Fungus Resistance F

Salt Spray S

Magnetic Effect X

Power Input X

Voltage Spike X

Audio Frequency Conducted Susceptibility A

Induced Signal Susceptibility A

Radio Frequency Susceptibility U

Radio Frequency Emissions A

Lightning Induced XXE3

Lightning Direct Effects 2A

Icing C

F. CMA--2200 Diplexer/Low Noise Amplifier

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(1) The CMA--2200 Diplexer/Low Noise Amplifier (D/LNA) supplies the RF transmit

(diplexer) and RF receive (low noise amplifier) paths between the HGA, IGA, or LGA and the HPA and SDU, respectively. The D/LNA is manufactured by BAE Systems -Canada (formerly Canadian Marconi Company Aerospace) under both BAE Systems

-- Canada Part No. 100--602200 --001 and the Honeywell Part No. 7516193--901. The features of the D/LNA are given in Table 1-18.

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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

Characteristic Specification

Frequency range:

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Table 1-18. CMA--2200 D/LNA Features

• Receive ...............................

•

Transmit

Receive gain

Noise figure

Support/Test equipment required

Design characteristics

.............................

...........................

............................

........ N

..................

(RTCA/ARINC/TSO/etc)

(2) Other features of the CMA--2200:

• Proven compatibility with:

-- ARINC 761 intermediate--gain a n tenna subsyste ms

-- ARINC 741 high--gain or low--gain antenna subsystems

• Self--test function.

(3) The leading particulars for the CMA--2200 D/LNA are given in Table 1-19. DO--160C

environmental categories for the CMA--2200 D/LNA are given in Table 1-20.

1525.0 -- 1559.0 MHz

1626.5 -- 1660.5 MHz

53 dB minimum, 60 dB maximum

0.8 dB maximum at 25_ C.

one at organizational level

DO--160C, ARINC 741/761, MOPS, SARPS

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Table 1-19. CMA-- 2200 D/LNA Leading Particulars

Characteristic Specification

Dimensions (maximum):

• Height ................................ 2.00 in. (50.8 mm)

• Width ................................. 7.78 in. (197.6 mm)

• Length ................................ 11.59 in. (294.4 mm)

Weight (maximum) ....................... 6.5lb(3.0kg)

Power Requirements ..................... 115 V ac, 400 Hz, 150 milliamps maximum

Operating Environment:

• Temperature range (operating) ........... -- 5 5 _ to +70_ C(--67_ F to +158_ F)

• Temperature range (non--operating) ....... -- 5 5 _ to +85_ C(--67_ F to +158_ F)

• Operatingaltitude ...................... to 70,000 ft (21.34 km)

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Table 1-20. CMA--2200 D/LNA DO-- 160C Environmental Categories

Environmental Condition Category

Temperature and Altitude E1

In--Flight Loss of Cooling X

Temperature Variation B

Humidity A

Operational Shock and Crash Safety -- --

Vibration C

Explosion Proof E2

Waterproof W

Fluids Susceptibility X

Sand and Dust X

Fungus Resistance F

Salt Spray X

Magnetic Effect A

Power Input E

Voltage Spike A

Audio Frequency Conducted Susceptibility E

Induced Signal Susceptibility Z

Radio Frequency Susceptibility V

Radio Frequency Emissions Z

Lightning Induced XXE3

Lightning Direct Effects X

Icing X

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G. Radio Frequency Unit Interface Adapter (RFUIA)

(1) The RFUIA is packaged as an ARINC 600 4--MCU suitable for mounting in the

equipment bay or near the antenna system. It consists o f a housing assembly integrated with an ARINC 600 connector on the back of the unit.

(2) The RFUIA is not an operational unit and it does not contain active internal electronic

components. No aircraft power is needed. This unit is installed in the aircraft in place of the RFU to complete the RF receive and transmit paths for the MCS--700 0 system.

(3) The housing is constructed of lightweight aluminum alloy sheet metal. No forced air

cooling is required. Two hold-down clamps let the unit be firmly clamped in the mounting rack. The unit is carried by a fixed C-shaped handle mounted to the front panel assembly.

(4) Figure 1-8 is a block diagram that shows how the RFUIA interfaces to the other

system LRUs. The leading particulars for the CMA--2200 D/LNA are given in Table 1-21.

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Figure 1-8. RFUIA System Interface Diagram

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Table 1-21. RFUIA Leading Particulars

Characteristic Specification

Dimensions (maximum):

• Length ................................

• Width .................................

• Height ................................

Weight (maximum) 4lb(1.82kg)

Power requirements None

Cooling Convection, no forced air required

12.76 in. (324.1 mm)

4.90 in. (124.5 mm)

7.64 in. (194.1 mm)

H. ARINC 429 Data Requirements

(1) The MCS system requires ARINC 429 data for antenna pointing, antenna

stabilization, and Doppler frequency correction. If the aircraft does not have an IRS that supplies this ARINC data, the SCU can be used to convert INS data sources. Refer to Appendix A, Vendor Equipment, for additional information about the SCU and the ARINC 429 data requirements.

I. Nameplates 3 (SDU and HPA)

(1) General

(a) Each LRU has two externally mounted nameplates consisting of:

• Front panel--mounted LRU nameplate

• Second LRU nameplate that reflects the full hardware and software status of

the LRU.

(b) The details of these nameplates are specified in the following paragraphs. See

Figure 1-6 and Figure 1-7 for the location of each nameplate.

(2) Front Panel LRU Nameplate

(a) Each front panel LRU nameplate contains each company’s logo (Honeywell and

Racal), the name of the system, and the LRU equipment name.

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(3) LRU Hardware and Software Nameplate

(a) Each LRU hardware and software nameplate contains the following information:

• Name of the company responsible for manufacturing it

• Model number (e.g., SD700, HP600, or HP700)

• LRU equipment name

• LRU hardware part number

• LRU serial number

• Weight

• Applicable DO--160C/DO--160D categories

• FCC identifier

• LRU hardware modification level

• LRU end item part number

• LRU software part number

• Software modification level

• Applicable DO--178A or DO--178B software level.

(b) The model number is a five--digit alphanumeric sequence. The first two digits are

upper--case alphabetic characters in the range AA to ZZ and the last three digits are numeric characters in the range 100 to 999. The LRU equipment name is displayed with as many upper--case letters as are required to spell out the equipment name. The LRU serial number consists of an eight--digit numeric sequence; the first two digits indicate the year of manufacture, the second two digits indicate the month of manufacture, and the final four digits indicate how many LRUs of this type have been manufactured. The range of the last four digits is 0100 to 9999.

a mix of numeric and upper --case alphabetic characters. See Table 1-10, Table 1-12, or Table 1-14 for a list of environmental categories applicable to the MCS LRUs.

(d) The FCC identifier applicable to all MCS LRUs is GB8MCS--4000 or

GB8MCS-- 7000 . The LRU hardware modification level is indicated by the set of all marked modification level identifiers. Each modification level identifier is a maximum of two upper--case alphabetic characters that range from A to ZZ, with letters I, O, Q, and X excluded.

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(e) The LRU end item part number consists of a seven--digit base part number and a

five--digit dash number. The first two digits of the dash number indicate the L RU’s hardware configuration and consist of numeric values ranging from 10 to 99. The last three digits of the dash number reflect the LRU’s software configuration number and consist of numeric values ranging from 001 to 999.

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(f) The software modification level consists of a maximum of two upper--case

alphabetic characters ranging from A (or “--”) to ZZ, with letters I, O, Q, and X excluded. Usage of this nameplate characteristic reflects the implementation of minor software changes.

(g) The DO--178A or DO--178B software levels applicable to the MCS LRUs is the

level an LRU was certified. This nameplate is capable of being removed and replaced when a software change is significant enough to require the three--digit software configuration number be incremented, or a hardware change is significant enough to require that the two--digit hardware configuration number be incremented.

J. Software and Hardware Compatibility (SDU and HPA)

(1) Provisions for a set of discrete wire jumpers (straps) are included in each MCS LRU

to ensure hardware and software compatibility. The code setting for these straps is manually changed each time a hardware revision is made that is not compatible with all previously released versions of software. The status of these straps is tested every time an LRU undergoes a cold start (power--on self--test [POST], or person--activated self--test [PAST] ), and every time a software load is attempted from an ARINC 615 portable data loader.

(2) The LRU header records in the ARINC 615 data loader software upload file and in

the operational software itself, contain a list of hardware/software compatibility strap codes with which the software is compatible. This list of codes is compared with the wired hardware/software compatibility strap code in the LRU; if any of the codes in the software upload file match the hardware/software compatibility strap code in the LRU, then the software upload process is allowed (otherwise it is inhibited). Similarly, if any of the codes in the software itself match the strap code in the LRU, normal LRU operation is allowed (otherwise it remains in an inert state).

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SECTION 2

SYSTEM OPERATION

1. Overview

A. General

The AES accepts data and voice signals from various sources, encodes the signals, modulates the information onto the appropriate RF carrier frequencies, and transmits these carriers to a GES through satellite. The AES also receives RF signals from the satellites, demodulates and decodes these signals, and outputs data or voice message for passengers or flight crew members. System operation begins when the P --channel transmission from a GES in the satellite region is received. The AES then logs onto the GES to establish the uplink and exchange information. System operation terminates when the AES logs off from the GES.

2. AES Management

A. General

(1) At any time, different satellite regions can have different satellite configurations. All

satellites have the global beam capability to receive the continuous Psmc--channel transmission of every GES in view. For a spot beam satellite, each spot beam is associated with at least one GES having a continuous P --channel transmission. Selected channels from the Psmc-- and Pd--channels are designated by INMARSAT for satellite and spot beam selection.

(2) An AES logs onto a GES to enter the satellite communications system and logs off to

terminate its operation in the system. Log-off is initiated automatically or by a user command issued as part of normal operational procedures.

(3) The AES also logs off before initiating handover. The AES does not log off if

handover is initiated because of degradation or loss of the P--channel. Handover can be initiated by the flight crew, or can be carried out automatically by the AES without human intervention. A handover procedure is followed automatically when an AES needs to change the log-on GES or to access a different satellite.

(4) When an AES receives a higher level instruction, for example a command from the

flight crew, to change its log-on to another GES operating in the same satellite region, any previously established data communication channels are maintained until clearing before the handover is carried out. In the case of a user command initiated satellite-to-satellite handover, the AES ensures all communication channels are clear prior to starting the handover procedure. If any connections are in progress, the AES applies time supervision of three minutes and then clears any remaining connections.

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(5) Automatic handover is initiated upon detection of Pd--channel link degradation

defined as:

• Error rate rises above 10

• More than 10 short--term interruptions (loss of P--channel clock synchronization for

less than 10 seconds) in any 3 minute period.

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over an averaging period of 3 minutes

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(6) Automatic handover is also initiated upon detection of loss of the Pd--channel defined

as:

• Loss of clock synchronization for more than 10 seconds

• Log-on renewal procedure is unsuccessful.

(7) A GES-to-GES handover is carried out by logging onto a new GES in the same

satellite region. The required P --channel frequency can be found in the system table. Each GES maintains an up-to-date status table of all AESs that have logged on. Each GES also has an inter-GES signaling capability letting the GES set up calls with any AES operating in the same satellite region as that GES, and manages the AESs during handover.

(8) If the AES attempts to renew its log-on and fails to log on to its previous GES or to

the preferred alternative GES after a log-on prompt, loss of P--channel quality, or a log-on renewal request from an application, the AES returns to the latter stages of the initial search procedure and scans the spot beam primary Pd--channels on its current satellite to identify an alternative spot beam. The required P--channel frequencies are found in the system table. Once an alternative spot beam is identified, the AES renews its log-on automatically to a preferred GES.

(9) During log-on renewal, if the AES is unable to log onto its previous GES or to another

GES in the same satellite region, then the AES enters the search mode to select the Psmc--channel frequency of a GES operating in a new satellite region. The required P--channel frequency is found in the system table. Having selected a new suitable quality Psmc-- channel (in another satellite region) and updating the system table for the new satellite region (if necessary), the AES carries out a log-on procedure with the new GES.

(10) Each AES maintains a system table stored in non volatile memory in the SDU. The

system table contains the satellite and GES identifying information, such as satellite Psid--channel frequencies, satellite locations and associated GES IDs, and GES Psmc--channel frequencies. The system table does not lose its contents because of loss of primary power.

(11) The SDU also maintains a bootstrap system table containing a default set of satellite

and GES identifying information. This information includes satellite Psid--channel frequencies, satellite location and associated GES IDs, plus satellite inclination and right ascension, spot beam support, and GES Psmc--channel frequencies that are set to zero.

(12) The bootstrap system table is loaded into the SDU as an inseparable part of the

upload of executable software. The SDU defaults to the bootstrap system table in the absence of a stored system table, or upon execution of a factory settings restart. The default data for a satellite is used until that satellite is first accessed, where a complete update of the data for that satellite takes place. Satellite region blocks that have not yet been updated over the air are marked with a null revision number.

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3. System Log-On/Log-Off

A. General

(1) Two operational modes are available for AES log-on:

• Automatic

• User commanded (constrained).

(2) In the automatic mode, the AES operation is fully automatic with satellite log-on and

handover procedures occurring without external control. In the user commanded mode, the flight crew or flight control system is able to select the satellite and GES for log-on and handover, and can initiate handovers at any time. The automatic mode is considered the normal mode of operation.

(3) The log-on/log-off of an AES to/from the satellite communications system lets the

GES manage the number of AESs that can receive a P--channel (Pd) and transmit on each R--channel (Rd). This controls the queuing delays and burst collision probabilities that can be experienced. When an AES is powered up, it enters a GES selection mode if the log-on policy is set to automatic. This permits the AES to select the most preferred GES operating in its visible satellite region (there may be one or two satellites visible to the AES), and that GES is selected for log-on. If the log-on policy is not set to automatic, the AES waits for the GES to be selected through the user commanded mode (or for a reversion to the automatic mode).

(4) After selecting a GES, the AES tries to acquire one of the identifying Psmc--channel

frequencies of the satellite contained in the initial system table. Typically there are two frequencies per satellite (or group of satellites if several satellites supply service to essentially one region). The AES receives that Psmc--channel until one of the system table’s broadcast signal units is received, which permits the AES to determine whether th e revision number of the system table currently stored in the SDU is valid. If the revision number for the AES is out-of-date, an AES updating procedure is implemented.

(5) When the revision number is verified as correct, the AES checks for any entries in the

satellite spot beam search table. If an entry exists, the AES checks the Pd--channel frequencies of all spot beams supported by the selected GES to identify the most applicable spot beam. The AES then determines which Pd --channel has the highest signal quality. Once this task is complete, the AES is ready to log-on to the satellite communications system using the selected G ES and the o ptimum spot beam, or the global beam if the GES does not operate a P--channel in the required spot beam.

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(6) The AES initiates the log-on procedure by tuning to the Psmc--channel (global beam)

of the selected GES and sending a log-on request signal unit on one of the corresponding Rsmc--channels. If the log-on request signal unit cannot be accepted by the GES, because of reasons like GES overload, invalid message, unauthorized access, etc, the GES responds with a log-on reject signal unit, which includes the cause of the rejection. By returning a log-on confirm signal unit with a different AES class value, the GES can offer log-on in a different AES class than originally requested. The AES can either accept log-on in the offered class by continuing the log-on signaling procedure, or reject log-on by discontinuing the log-on signaling procedure.

(7) The AES uses the log-on request signal unit to supply the selected GES with its own

identification (a 24-bit ICAO aircraft identification code), plus the identification of the spot beam where the AES is located. A zero value is used in the spot beam identification field of the log-on message if:

• No spot beam on the selected satellite

• AES is out of any spot beam coverage area

• Selected GES does not operate a Pd--channel in the required spot beam.

(8) The AES also informs the GES of the number of C--channels the AES is equipped to

handle, the bit rate/coding algorithm in use on the voice channels, and the data bit rate capability for the R--channels, P--channels, and T --channels. Except for the number of C--channels and the data bit rate capability, this information is repeated in the log-on confirm signal unit for use by other GESs.

(9) An AES having circuit-mode data service capability and desiring allocation of

circuit-mode data capable channel units at the GES for every ground-to-air call, informs the GES of the type of interface required. The interface is either analog interconnect or digital interconnect. If the GES does not support circuit-mode data service, it ignores the information. If the GES supports the service, it registers the information in its log-on AES table and retransmits the information for use by other GESs.

(10) The AES supplies the GES with its flight identification number at log-on, if the

owner/operator of the AES desires to use the aircraft flight identification as the address for ground originated calls. The use of this information in the GES depends upon the services being offered, and therefore is at the discretion of the GES operator.

(11) The AES is given an EIRP setting for Rd --channels in the log-on confirm signal. If a

T--channel is assigned, the AES determines the EIRP for the T--channel in accordance with the assigned R--channel EIRP and the ratio of the R--channel and T--channel bit rates. The GES assigns a Pd -- channel from the available channels, taking into account the loadings on the channels, the need to use a P--channel of low power if possible, and the need to supply some means of recovery from P--channel degradation or failure. The ability to work with a low power P--channel is determined by the AES class. If the GES assigns a Pd--channel different than the Psmc--channel, the GES transmits the new channel frequency to the AES using the P/R--channel control signaling message following the log-on confirm.

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(12) If the GES is using more than one set of R--channel frequencies and assigns new

Rd--channels to the aircraft, the GES transmits the new channel frequencies (up to eight) to the AES using the signaling message(s) that follow the log-on confirm. In addition, the GES transmits from one to four T--channel frequencies to the AES if data services are supplied. The GES uses the following criteria to determine the channel and EIRP assignments for data services:

• Satellite in use (its return link sensitivity)

• Class of AES

• Bit rate capability of the AES.

(13) The GES assigns data channels at the highest agreeable bit rate supplied in both the

AES and GES, and supported by the combination of the satellite in use and the class of AES. Subsequent log-on transactions for handover use Rsmc-- and Psmc--channels in the same manner as the initial log-on transaction.

B. Automatic Log-On

(1) The SDU supports two types of log-on:

• Automatic

• Constrained mode.

(2) The SDU implements the automatic log-on mode upon user command if the AES is

currently logged-off, AES is logging-on, or AES is logged-on in the constrained mode. Automatic log-on is also implemented by the SDU, if ORT item i (log-on policy) indicates automatic at startup. The user command can originate from either the SCDU, from the analog connected telephone handsets, or from the commissioning and maintenance terminal (CMT).

(3) When the AES is in the automatic mode, the log-on GES/satellite/spot beam chosen

is based on the GES preference (ORT item iii). A GES with a preference level of zero is not considered for automatic log-on. The SDU allows the use of tied GES preferences. The SDU resolves tied preferences by selecting the GESs in descending order of satellite elevation. During GES selection, the set (as yet untied) of GESs with the highest preference are initially processed to exclude those GESs associated with satellites not in view.

(4) Satellites are deemed in view if they are above the elevation handover threshold

specified in ORT item xxxix, or their elevation is higher tha n 1 d e gree less than the elevation of the highest satellite. If no IRS data is available and the currently selected antenna is the low gain antenna, then all satellites are deemed to be in view. The remainder of the GESs in the preference group are then sorted into a list by satellite elevation and GES on the highest elevation satellite chosen for initial access. If more than one GES in the preference group have the same satellite elevation, then those GESs are ordered by a pseudo-random choice algorithm with a uniform probability density.

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C. Constrained Log-On

(1) Constrained log-on is where the user manually selects the specific GES to be used

for log-on. The user command can originate from either the SCDU, from the analog-connected telephone handsets, or from the CMT. The GES preferences specified in ORT item iii have no effect in the constrained log-on mode, and it is possible to execute a constrained log-on to a GES with a preference level of zero.

(2) If the user has manually selected the log-on GES, and therefore also selecting the

satellite, the SDU is constrained to search for the specific GES-related satellite Psid frequency (or frequencies), the set of spot beam Pd frequencies where the selected GES radiates P--channels, and the selected GES Psmc frequency during the log-on sequences. If the specific GESs satellite Psid frequencies cannot be acquired, the SDU takes no action other than to reattempt the acquisition with alternate modems. If none of the GES-related spot beam Pd frequencies can be acquired, the SDU starts the GES Psmc frequency search as it would normally do after acquiring a spot beam frequency. If the GES Psmc frequency cannot be acquired, the SDU reattempts the acquisition indefinitely. This state of unsuccessful satellite/GES Psmc frequency acquisition is exited either by the frequency being acquired, or by a user command to select automatic log-on, by selection of a different satellite/GES, or to log-off.

(3) Once logged-on in this mode with the GES constrained, only spot beam handover

takes place. The user is able to exit this constrained log-on mode by commanding log-off, by selecting the automatic log-on mode, or by cycling SDU primary power (if ORT item i log--on policy is auto log--on..

D. Log-On Mode Selection

(1) User selection of the automatic log-on mode while the AES is logging-on in the

constrained mode causes the SDU to abort the current log-on attempt and revert to the automatic mode. User selection of the automatic log-on mode while the AES is logged-on in the constrained mode causes the SDU to log-off from the current constrained GES, and to revert to the automatic mode if there are GESs in view with higher preference levels than the current log-on GES. User selection of the automatic mode when the AES is logged-off causes the SDU to implement automatic log-on. The SDU lets the user command log-off while the AES is logging-on or logged-on in the constrained or automatic mode.

(2) The user is able to change the selected GES if the AES is logging-on or is logged on

in the constrained mode. The user can enter the constrained mode by selecting a specified GES while the SDU is logging-on or is logged-on in the automatic mode. In both cases, providing the constrained GES selection is different from the automatically chosen GES, the SDU either aborts the current log-on attempt or logs-off from the current GES before attempting to log-on to the n ew GES, depending upon the current status.

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E. Handover

(1) The SDU causes the AES to initiate a handover procedure for the following reasons:

• Automatic handover when the AES is logged-on in the automatic or constrained mode, because of P--channel degradation.

• Automatic handover when the AES is logged-on in the automatic mode, because of the log-on satellite being below the elevation handover threshold specified in ORT item xxxix, with another satellite being at least 1 degree higher than the log-on satellite for more than 10 seconds.

• Automatic handover as specified in ORT item xxii for 10 seconds because of the reported HGA Tx gain being less than the threshold value when the AES is logged-on in the automatic or constrained mode.

• User command to select the constrained mode when the AES is logged-on (or awaiting log-on acknowledge) in the automatic mode if the constrained selection is different from the current, automatically selected GES.

• User command to select the constrained mode for a particular GES when the AES is currently logged-on (or awaiting log-on acknowledge) to a different GES, but also in the constrained mode.

• User command to select the automatic mode when the AES is logged-on (or awaiting log-on acknowledge) in the constrained mode if a GES exists with a higher preference level than the current log-on GES.

• User command to adjust the GES preference levels if the AES is logged-on (or awaiting log-on acknowledge) in the automatic mode, and the adjustment results in any GES having a higher preference level than the current log-on GES.

(2) The SDU logs off from the current log-on GES before logging onto the new GES for

all of the above handover stimuli, except for automatic handover because of P--channel degradation and automatic handover because of the reported HGA Tx gain being less than the threshold value.

(3) If any modems are being used for circuit--mode voice when a handover to a GES in a

different satellite region occurs, then the SDU terminates the current C--channel calls with an SLCV cause of 1221x. The SDU also causes a suitable voice pacifier message (Sorry, your call can no longer be sustained) to be sent to each currently in-use digital or analog headset to inform each user of the reason for the call termination. The SDU does not clear down any ongoing C--channel calls if the handover is local to the current satellite region.

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F. Log-Off

(1) Log-off is initiated in the AES by a user command, either from the SCDU, from the

analog-connected telephone handset, or from the CMT. Log-off is also initiated by the SDU as part of the handover sequence, except for handovers implemented because of P --channel degradation.

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4. System Software/Database Updates

A. General

(1) Each MCS LRU (SDU and HPA) has an ARINC 615 Airborne Data Loader (ADL) and

PDL port. The SDU and HPA are capable of transferring the data sets listed in Table 2-1 through these ports.

Table 2-1. Data Set Upload/Download

LRU Data Set Upload/Download

SDU Operational Software Upload Only

Owner Requirements Table Upload and Download

Event and Failure Logs Download Only

Maintenance Activity Log Download Only

Periodic Data Logging (SDU system and operational parameters)

HPA Operational Software Upload Only

Download Only

(2) In Table 2-1, upload is defined as the transfer of a data set from the ARINC 615 data

loader to the appropriate LRU. A download is defined as the transfer of a data set from an appropriate LRU to the ARINC 615 data loader. The data set to be transferred is independent of the port used. If during a data transfer session the other port becomes active, the session associated with the initially activated port continues to completion before initiating any session with the other port. The software upload function is resident in the bootstrap program and functions independently of any uploadable software in the LRU.

B. Software Upload Process

(1) The uploading of the software is done by either connecting a PDL to the ARINC 615

connector port on the LRU to be programmed, or (in the case of an ADL) by the user selecting the LRU to be programmed. With the data loader connected, the Link A connection is completed.

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(2) The diskette containing a configuration file and a file containing the software to be

uploaded is inserted into the disk drive of the data loader. The configuration file contains information for the data loader (ADL or PDL) to configure itself for operation. All MCS ORT download/upload diskettes contain a configuration file located in the root directory of the diskette with the filename CONFIG.LDR. The data loader reads the configuration file and initializes itself according to the parameters read. The data loader then repeatedly transmits an RTS word.

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(3) With the operational software running, the SDU software upload is initiated only after:

• SDU senses the low impedance state on Link A.

• SDU determines it is not airborne (unless the operational software is not valid

where the on-ground/airborne state is ignored).

• SDU detects receiving an RTS word with a system address label (SAL) equal to

307.

(4) The HPA software is similarly initiated only after the requirements mentioned are

satisfied, except software uploading is also enabled when a valid air/ground status from the SDU is not available to the LRU.

(5) For the LRUs, the software upload is a single pass process. Upload validation checks

both the LRU and SRU header records for applicability. Each data loader block is then transferred directly to the program store. When the software upload is completed, the program store CRC is checked over defined regions of the program store. If either validation process fails, the software upload process aborts. Further upload attempts can only be initiated by resetting both the data loader and the LRU. When successfully validated, the LRU causes the data loader to initiate the transfer complete function and the LRU remains in the data load state, while the Link A connection remains intact. When the Link A connection is removed, the HPA performs a POST and the SDU performs a factory settings restart. A factory settings restart results in Category C nonvolatile data being set to default values followed by execution of POST/PAST.

C. Validation of the Software Upload File

(1) The following items are validated when software is loaded:

• First two bytes of each LRU/SRU header record indicates a valid record type for the record position in the data sequence.

• Company name in the LRU header record must be HONEYWELL/RACAL.

• LRU name and base part number must match the current LRU specification as

given on the LRU nameplates.

• Software compatibility codes in each SRU ID PROM must appear in the list of compatible hardware/software codes for every SRU listed in the LRU header.

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5. Owner Requirements Table

A. General

(1) The ORT is stored in nonvolatile memory in the SDU. The ORT contains information

relating to different areas of functionality like log-on and telephony. The ORT does not lose its contents because of the loss of SDU primary power or as a result of PAST. All ORT contents are set to default values by a factory settings restart. The ORT contains all pilot and aircraft operator entered information preserved when the SDU is powered-down.

(2) Validity of the ORT content is determined by the SDU using a checksum process.

This verification is performed at the time of each power-up. An invalid checksum results in the SDU reverting to the default values specified in TESTING/FAULT ISOLATION, ORT default value usage. The contents of the ORT are specified in Appendix C.

(3) The ORT items are organized into two distinct partitions:

• Secured

• User.

(4) The individual ORT items defined in Table C--1.1 are assigned to a partition by the

designation of secured or user in the attributes column.

(5) The secured partition contains those items the equipment manufacturer, aircraft

manufacturers, and certification authorities have determined to be configuration-dependent and crucial to the proper operation of the SATCOM system. The user partition contains all other items of the ORT. The user partition typically includes items the aircraft operator is able to set or modify, enabling the efficient use of the equipment in normal operation. A composite ORT file contains all items (both partitions) in the ORT. This version of ORT is defined to supply a consistent interface (single ORT file) to those users that do not require the additional security supplied by the management of two partitions for essential certification.

(6) The content o f the ORTs in both SDUs in a dual system is intended to be identical.

For the sake of ORT requirements that must be capable of b eing different in SDUs 1 and 2, the ORT items affected are duplicated withintheORT.Eachofthoseitemsis capable of storing separate, independent entries for SDUs 1 and 2, to be used by each particular SDU as appropriate based on the strapping of its system configuration pins TP13E/F. The lone SDU in a single system uses the entry for SDU 1 for duplicated items. ORT items not duplicated are said to be common,wherethe single entry applie s to SDUs 1 and 2 in dual systems as well as to the lone SDU in a single system.

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Honeywell SD 700A User Manual

Specifications and Main Features

Frequently Asked Questions

User Manual

Honeywell Materials License Agreement

RECORD OF REVISIONS

RECORD OF TEMPORARY REVISIONS

SERVICE BULLETIN LIST

LIST OF EFFECTIVE PAGES

TABLE OF CONTENTS

INTRODUCTION

3. References

A. Honeywell Publications

B. Other Publications

5. Maximum Permissible Exposure Level

A. General

Figure Intro--2. Radio Frequency Energy Levels

1. Overview

A. General

Figure 1-1. Aviation Satellite Communications System

B. Aircraft Earth Station

Figure 1-2. Aircraft Earth Station Block Diagram

Table 1-1. Classes of Installations

Table 1-2. Types of RF Channels

C. Space Segment

D. Ground Earth Station

E. Terrestrial Data and Voice Networks

Table 1-3. Ground Earth Stations

Figure 1-4. INMARSAT Four-Region Satellite Coverage

2. System Components

A. General

Table 1-4. System Components Supplied by Honeywell

Table 1-5. System Components Not Supplied by Honeywell

Table 1-6. SDU Configurations

Table 1-7. HPA (40 Watt) Configurations

Table 1-8. HPA (20 Watt) Configurations

3. System Description

A. General

B. Satellite Data Unit

C. High Power Amplifier

D. Avionics Configurations

4. MCS Component Descriptions

A. Physical Description

B. Satellite Data Unit (SDU)

Figure 1-6. Satellite Data Unit

Table 1-9. SDU Leading Particulars

Table 1-11. HPA (40 Watt) Leading Particulars

Table 1-13. HPA (20 Watt) Leading Particulars

G. Radio Frequency Unit Interface Adapter (RFUIA)

Figure 1-8. RFUIA System Interface Diagram

Table 1-21. RFUIA Leading Particulars

H. ARINC 429 Data Requirements

I. Nameplates 3 (SDU and HPA)

J. Software and Hardware Compatibility (SDU and HPA)

1. Overview

A. General

2. AES Management

A. General

3. System Log-On/Log-Off

A. General

B. Automatic Log-On

C. Constrained Log-On

D. Log-On Mode Selection

E. Handover

F. Log-Off

4. System Software/Database Updates

A. General

Table 2-1. Data Set Upload/Download

B. Software Upload Process

C. Validation of the Software Upload File

5. Owner Requirements Table

A. General