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Honeywell International Inc.

400 Maple Grove Road

Ottawa, Ontario

Canada K2V 1B8

CAGE: 38473

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

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

Website: www.myaerospace.com

Page T-1

Publication Number D201401000049, Revision 4 Initial 16 Jan 2015

Revised 3 Mar 2017

23-15-29

This document contains technical data and is subject to Canadian and U.S. export regulations. If these

commodities, technology, or software were exported from Canada, no export permit is required. If these

commodities, technology, or software were exported from the United States, they must be exported in

accordance with the Export Administration Regulations. Diversion contrary to Canadian or U.S. Law or

regulations is prohibited.

Canadian ECL: C-NEPR

ECCN: EAR99

JetWave™ System

System Description and Installation Manual

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

Model Part Number

JetWave™ System MCS 8200 Class A Forced Air KRFU 90401028-001

JetWave™ System MCS 8200 Class A Conduction Cooled KRFU, Version 1 90401028-002

JetWave™ System MCS 8200 Class A Conduction Cooled KRFU, Version 2 90401028-003

JetWave™ System MCS 8250 Class A Modman, Version 2 90406164-001

JetWave™ System MCS 8250 Class A KANDU, Version 2 90406164-XXX

JetWave™ System MCS 8250 Class A Conduction Cooled KRFU, Version 2 90406164-XXX

JetWave™ System MCS 8000 Class B Forced Air KRFU 90401027-001

JetWave™ System MCS 8000 Class B Conduction Cooled KRFU, Version 1 90401027-002

JetWave™ System MCS 8000 Class B Conduction Cooled KRFU, Version 2 90401027-003

JetWave™ System MCS 8000 Class A Conduction Cooled KRFU, Version 2, FMA 90401027-004

JetWave™ System MCS 8000 Class A Forced Air KRFU, Version 2, FMA 90401027-005

A791 Radome Package 90400017-XXX

Non-A791 Radome Package 90400016-XXX

Legal Notice

Export Control

Draft as of 31 May 2017

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SYSTEM DESCRIPTION AND INSTALLATION MANUAL

JetWave™ System

Proprietary Information

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Draft as of 31 May 2017

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SYSTEM DESCRIPTION AND INSTALLATION MANUAL

JetWave™ System

adhere to all U.S. export regulations as published and released from time to time by the U.S. Government. You

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Draft as of 31 May 2017

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SYSTEM DESCRIPTION AND INSTALLATION MANUAL

JetWave™ System

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

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

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WARNING: HONEYWELL ASSUMES NO RESPONSIBILITY FOR ANY HONEYWELL EQUIPMENT WHICH

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

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HONEYWELL ASSUME RESPONSIBILITY FOR SPECIAL TOOLS AND TEST EQUIPMENT FABRICATED BY

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RESULTS.

Draft as of 31 May 2017

Page T-5

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SYSTEM DESCRIPTION AND INSTALLATION MANUAL

JetWave™ System

Honeywell is a registered trademark of Honeywell International Inc.

All other marks are owned by their respective companies.

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

Document Number: D201401000049, Revision 4

3 Mar 2017

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

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

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

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

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

Honeywell International Inc.

400 Maple Grove Road

Ottawa, Ontario, K2V 1B8

Canada

Reception: 613-591-9064

Product Support: Aerospace Technical Support

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

E-mail: AeroTechSupport@Honeywell.com

Draft as of 31 May 2017

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JetWave™ System

Blank Page

Draft as of 31 May 2017

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SYSTEM DESCRIPTION AND INSTALLATION MANUAL

JetWave™ System

TRANSMITTAL INFORMATION

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

FOR USE IN SUPPORT OF THE FOLLOWING:

Table TI-1 shows the applicable components.

Revision History

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

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

See Transmittal information for history of revisions to this SDIM.

Table TI-1. Applicable Components

Component PN Nomenclature

90401028-001 JetWave™ System MCS 8200 Class A Forced Air KRFU

90401028-002 JetWave™ System MCS 8200 Class A Conduction Cooled KRFU, Version 1

90401028-003 JetWave™ System MCS 8200 Class A Conduction Cooled KRFU, Version 2

90406164-001 JetWave™ System MCS 8250 Class A Modman, Version 2

90406164-XXX JetWave™ System MCS 8250 Class A KANDU, Version 2

90406164-XXX JetWave™ System MCS 8250 Class A Conduction Cooled KRFU, Version 2

90401027-001 JetWave™ System MCS 8000 Class B Forced Air KRFU

90401027-002 JetWave™ System MCS 8000 Class B Conduction Cooled KRFU, Version 1

90401027-003 JetWave™ System MCS 8000 Class B Conduction Cooled KRFU, Version 2

90401027-004 JetWave™ System MCS 8000 Class A Conduction Cooled KRFU, Version 2, FMA

90401027-005 JetWave™ System MCS 8000 Class A Forced Air KRFU, Version 2, FMA

90400017-XXX A791 Radome Package

90400016-XXX Non-A791 Radome Package

Table TI-2. Revision History

Revision Revision Date

0 16 Jan 2015

1 16 Sep 2015

2 6 Nov 2015

3 17 Aug 2016

4 3 Mar 2017

Draft as of 31 May 2017

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SYSTEM DESCRIPTION AND INSTALLATION MANUAL

JetWave™ System

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

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

Revision bars mark the technical data that changed in this revision; those changes are described in the Table

of Highlights. Editorial changes are not marked with a revision bar.

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

columns.

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

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

within the block.

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

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

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

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

Table of Highlights

Page Description of Change Effectivity

Global Change: Changed the content and format to agree with

the Honeywell processes in effect at the time of the release of

this revision. These changes are not identified with revision

bars.

All

Global Change: The editorial changes and data that were

moved or reformatted are not identified with revision bars.

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

renumbered and are not identified with revision bars.

T-1 Added MCS 8200 and MCS 8000 to all model.

Added MCS 8250 Class A Modman Version 2, KANDU Version

2 and Conduction Cooled Version 2.

All

TI-1 Revised nomenclature in Table TI-1 for all part numbers.

Added MCS 8250 Class A Modman Version 2, KANDU Version

2 and Conduction Cooled Version 2.

All

TI-1 thru TI-5 Updated for Revision 4. All

SBL-1 Added SB JETWAVE-23-0002, Rev 3 and SB

JETWAVE-23-0003, Rev 0. All

1-2 Revised nomenclature in Paragraph 3 for all part numbers.

Added MCS 8250 Class A Modman Version 2, KANDU Version

2 and Conduction Cooled Version 2.

All

1-3 Updated Paragraph 1.5.B. to show the latest Honeywell

template information. All

1-4 Updated CAGE code website address to

https://cage.dla.mil/search. All

Draft as of 31 May 2017

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2-1 Paragraph 2.1, revised the title from “Overall Jetwave System

Architecture” to “Jetwave System Overview”. All

2-2 Table 2-1, revised the PN for TMA from 904000013-0001 to

904000013-0001.

All

2-3 Table 2-4, revised the operating temperature range and

deleted APM in Interfaces.

All

2-5 Table 2-6, Added the KANDU variant 2 reference to Cooling. All

2-5 Table 2-7, revised the specifications for weight, power

consumption, power dissipation and cooling for

conduction-cooled 1 configuration.

All

2-6 Table 2-7, revised the specifications for power consumption,

power dissipation and cooling for conduction-cooled 2

configuration and the specifications for power consumption for

Forced air configuration.

All

2-7 Table 2-7, revised the specifications for power dissipation and

operating temperature for forced air configuration.

All

2-12 Paragraph 2.3, Revised Step 3 to "ARINC 791 TX Mute

between the Modman and the KANDU is optional, the

Honeywell implementation uses RS422 signaling on

manufacturer-specific circuits 3 to 4 instead”.

2-13 Paragraph 2.4B, revised “the Modman starts continuous BITE”

with “the Modman starts additional POST and BITE”.

All

2-13 Paragraph 2.4C, revised “Access system” with “GUI”. All

2-13 Paragraph 2.4D, revised “Access system” with “GUI”. All

2-13 Paragraph 2.4E, revised “Access system” with “GUI”. All

2-14 Paragraph 2.4F, revised “SNMP” to “GUI” and deleted “manual

antenna alignment”.

All

2-14 Paragraph 2.4F, added new step “The system will exit the

commanded mode by a System reset”.

All

3-1 Paragraph 3.1, revised to add additional configuration data

information. All

Table of Highlights (Continued)

Page Description of Change Effectivity

Draft as of 31 May 2017

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SYSTEM DESCRIPTION AND INSTALLATION MANUAL

JetWave™ System

3-1 Table 3-1, removed the Primary/Secondary concept. Grouped

Combined the rows for Labels 254, 255, 261, 132, 175 and

Labels 112, 110, 111, 76 and 314.

Removed rows for Labels 331, 332 and 333.

All

3-2 Table 3-1, removed the Acceptable Replacement to Primary

Labels 361 and 312 and added Labels 125. All

3-3 Paragraph 3.1C, deleted “Weight on Wheels” in the airframe

specification information. All

3-3 Paragraph 3.1C, revised to add OTA access. All

4-1 Paragraph 4.1, moved the existing steps from Paragraph 4.2.

4-1 Paragraph 4.1A, deleted “Provide” and revised as “For new

configurations”.

All

4-1 Paragraph 4.1A, added new subsection for Jetwave System

installation procedure.

All

4-1 Paragraph 4.1A, merged the existing bullets (1) and (2) to

include “or”.

All

4-2 Paragraph 4.1A, deleted the existing bullets (7), (8) and (9).

Added “on completion of post installation checks” to bullet (6).

Paragraph 4.2, revised the title to add the word “Internal”.

All

4-3 Paragraph 4.2A.(4), revised to update 60 dB to 120 dB. All

4-4 Added input signal range note that follows Table 4-2. All

4-4 Paragraph 4.2B, revised to add APM to Modman interconnect

cable ARINC standards and PN of the cable.

All

4-5 Paragraph 4.2C.(2), Added descriptions for Front Panel Enable

Mode, Discrete Signal Ground (Modman MP12F) and Discrete

Signal Ground (KANDU J1-B).

All

4-6 Table 4-3, revised “Ground to open transition” to “Open to

ground transition” and “Open to ground transition” to “Ground

to open transition” for Local Data Load.

All

4-6 Table 4-3, revised “Change” to “Mandatory” for

Ground Transmit Enable.

All

4-7 Table 4-3, revised front panel enable mode description. All

Table of Highlights (Continued)

Page Description of Change Effectivity

Draft as of 31 May 2017

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SYSTEM DESCRIPTION AND INSTALLATION MANUAL

JetWave™ System

4-8 Paragraph 4.3(1), added reference to Figure 4-26 and updated

Step (1)(g).

All

4-9 Paragraph 4.3, Moved the existing Step (2)(a) to (1)(g).

Added Steps (2)(a), (2)(b) and (2)(c) for KANDU receptacle

A3J, KANDU receptacle A3J2 and KANDU receptacle A3J3.

All

4-14 Paragraph 4.6, revised the title as “KRFU”. All

4-15 Added Paragraph 4.6B title “KRFU Thermal Pad Kit”.

Added existing steps from Paragraph 4.6B under Paragraph

4.A General.

All

4-16 Paragraph 4.6A, revised to amend the operation of the AES

and added an additional step for conduction-cooled KRFU.

All

4-17 Paragraph 4.6D, revised the bullet as “The KRFU includes

bonding measuring points on the chassis bosses which are not

used for mounting feet.”

All

4-17 Step 4.6E.(1)(e), changed the reference to 4.6. All

4-20 Paragraph 4.7G, added “per ARINC791 P1-2”. All

4-22 Paragraph 4.7I I(b), added "or LAIM." All

4-27 Paragraph 4.7I(6), revised a step to change “2 dB” to “stay

within 0.5 to 2 dB”.

All

4-28 Paragraph 4.7l(6)(d), added offset to procedure. All

4-29 Figure 4-14, updated the TMA RF TX and RF J4 interface

connector and bonding strap locations graphic to include an

additional view.

All

4-32 Paragraph 4.7.(6)(g), revised “KANDU to KRFU” to “MODMAN

to KRFU”.

All

4-33 Paragraph 4.7.(6)(g)4, removed the default position. All

4-39 Paragraph 4.9, added new paragraph for “Radome Installation

Bonding Resistance”.

All

4-40 Paragraph 4.10, added new paragraph for “Inspection of

Waveguide”.

All

4-41 Table 4-10, revised Conductor Type “Single conductor,

stranded” as “Twisted pair”.

All

Table of Highlights (Continued)

Page Description of Change Effectivity

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JetWave™ System

4-41 Paragraph 4-11, revised “Variant 1” as “Variant 2” in the step

referring to Figure 4-26.

All

4-41 Paragraph 4-11, added reference to new Figure 4-24. All

4-43 Paragraph 4.11, added note stating that the Fuselage Mount

Radome is offered as a standard part with varying skirts to the

step referring to Figure 4-32.

All

4-55 and 4-56 Figure 4-24, add new figure for APM Outline and Installation

Drawing. All

4-63 thru 4-71 Figure 4-27, updated to the latest engineering drawing. All

4-82 thru 4-101 Figures 4-31 and 4-32, updated to the latest engineering

drawings. All

4-106 thru 4-143 Figures 4-34 thru 4-37, updated to the latest engineering

drawings. All

5-1 Paragraph 5.1A, added a new step for the APM system

configuration minimum. Revised to add “or if all of the LRUs are

not at the same software release level, then”.

All

5-1 Paragraph 5.1B, revised to add “unless APM configuration

does specify other port / IPs settings”.

Paragraph 5.1C, revised the maintenance port data.

All

5-2 Paragraph 5.1C, revised Title from “Procedure” to “Overview”

and the maintenance port data. All

5-2 Paragraph 5.1C, revised Step (2) as per SB

JETWAVE-23-0002 and SB JETWAVE-23-0003. All

5-4 Paragraph 5.1D, revised Title from “Setup of 615A Data Loader

Application (AIT Flight Simulyzer v3.0.0)” to “Procedure (AIT

Flight Simulyzer v3.0.0)”.

All

5-15 Paragraph 5.1, Step D.(3)(s), revised the step stating to refer to

the applicable SB.

6-1 Paragraph 6.1, revised the step for “Satellite Search”.

Added a new bullet for GoGo for distribution partners.

All

Table of Highlights (Continued)

Page Description of Change Effectivity

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SYSTEM DESCRIPTION AND INSTALLATION MANUAL

JetWave™ System

6-2 Paragraph 6.1, revised “maximum spot beam capacity” to

“defined Maximum Information Rate” and “or Minimum” as “for

95% of the time”.

Revised to state that the updates do not adversely affect

system safety, operational capabilities and does not impact

flight crew workload.

Revised to remove "On the next power up"

All

6-3 Paragraph 6.1B, Step (2), replaced “Flight Load result” with

“test report”.

Paragraph 6.2, revised to add additional information on

certifications for antenna installations.

All

6-3 Paragraph 6.3B, revised the title as “System Health and

Configuration”. All

6-4 Figure 6-1, revised the title to delete “AES User Level”. All

6-5 Paragraph 6.3B, added step “The laptop's Ethernet port will

need to be configured with a static IP address of 172.29.55.x,

where x is 10 or above“.

Replaced “open the link index.html” with “enter 172.29.55.1 in

the address bar”.

6-9 Paragraph 6.3B, added a note to follow the appropriate

Jetwave Service Bulletin to validate the software currently

installed.

All

6-10 Paragraph 6.3C, revised the title from “Modman Reset Input” to

“Discrete Input Testing”.

Updated Step 6.3C(1) and added Step (2).

Replaced Figure 6-8 with the latest version.

Added Note that follows Step 6.3D.

All

6-11 Paragraph 6.3E, updated the first note that follows Step E. All

6-12 Paragraph 6.4, added a new step for cable calibration. All

6-12 and 6-13 Paragraph 6.4, “AES Menu Access System” is replaced by

“GUI”.

Paragraph 6.4, added additional information for full

Optimization of Jetwave system.

All

Table of Highlights (Continued)

Page Description of Change Effectivity

Draft as of 31 May 2017

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SYSTEM DESCRIPTION AND INSTALLATION MANUAL

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6-13 Paragraph 6.5A, revised to add “or replacement” condition. All

6-13 Paragraph 6.5A, Step (2), revised the physical installation

procedure.

All

6-14 Paragraph 6.6A., Step (3) revised the requirement for antenna

alignment.

All

6-14 Paragraph 6.6A, Step (5), replaced “open the link index.html”

with “enter 172.29.55.1 in the address bar”.

Step 6.6C(1), revised to add information for Geo stationary

satellite.

All

6-15 Steps 6.5C, Step (1), updated Figure 6-13 to latest. All

6-15 Paragraph 6.6B, Step (2) and Step (3), revised to change

“headings” to “true headings”.

Added note to Paragraph 6.6B, Step (3) referring to the values

displayed.

All

6-16 Step 6.6B, Step (4), revised to change “headings” to “true

headings”. All

6-17 Step 6.6B, Step (4), updated Figure 6-14 to latest. All

6-17 and 6-18 Step 6.6A, Step (2), revised step (2) and added "If AES

Configuration System KANDU Ground Speed.

All

6-18 Step 6.7A(5), revised control of the transmission of the

terminal.

All

6-19 Paragraph 6.7A, added a note to give information that the 360

degree connectivity access can be limited for the Jetwave

system.

All

6-19 Paragraph 6.7A, Figure 6-15 was revised to include the latest

data.

All

7-2 Paragraph 7.2A, Step (1), added note for the health status

page.

All

7-3 Paragraph 7.2A. Step (1), updated Figure 7.3 to latest. All

7-6 Paragraph 7.2B, Step (5) updated Figure 7.5 to latest. All

7-7 Paragraph 7.2D, revised “By closure of the Modman reset pin

(MP10C) to ground” as “By grounding the Modman Reset Pin

(MP10C)”

All

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7-7 Paragraph 7.2F, Step (2), added a note to refer to Saint Gobain

SRM for FMA radome.

7-14 Table 7-1, added L1 code 0x23 with description “Modman input

discretes from LRU”. All

7-16 Table 7-3, added “Modman input discretes from KANDU (23)”

under L1 column with 0x 00 under L2 Code and “Unknown”

under L2 Description column.

All

7-22 Table 7-6, deleted entries 0x 0002, 0x 0003 and 0x 0004 L3

codes under L2 Regulatory Log (07).

All

7-22 Table 7-6, revised the description for L3 code 0x 0003 under

L2 Information Events (08).

All

7-22 Table 7-6, added L3 codes 0x 0004 thru 0008 under L2

Information Events (08).

All

7-22 Table 7-6, added new L2 Code. All

7-25 Table 7-6, revised L3 Code IP security. All

7-26 Table 7-6, revised Repair Action for L3 Codes 0x 0007 thru 0x

000B.

All

7-27 thru 7-29 Table 7-6, revised L2 code software runtime (FE) completely. All

7-30 Table 7-6, deleted the L2 entires Fan (07) and “Failed on startup

(08)”.

Under L2 entry BDC (2A), added new L3 code 0x 0002.

All

7-31 Table 7-6, revised L3 description and added new L3 code for L2

entry Software runtime (FE) and Repair Action. All

7-34 Table 7-6, added L3 codes 0x 0008 and 0x 0009.

Revised Repair Action for L3 Codes 0x 0007 thru 0x 000A and

L2 code Software runtime (FE) completely.

All

7-35 and 7-36 Table 7-6, revised L2 code Software runtime (FE) completely. All

7-38 Table 7-6, added new L3 codes 0x 00087 and 0x 00088. All

7-39 Table 7-6, revised L3 description texts “CCA Initialization to

read as “Azimuth Axis Low temperature High Current” and

“Azimuth Axis Low temperature High Current” to read as

“Elevation Axis Low temperature High Current”.

All

7-40 Table 7-6, revised Repair Action for L3 code 0x 0007. All

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7-41 thru 7-43 Table 7-6, revised L2 code Software runtime (FE) completely. All

7-43 Table 7-6, moved L3 code 0x 0022 and its L3 description and

repair action entries under L2 Unknown (00). All

7-44 Table 7-6, moved L2 code ASC (01) to KANDU (06).

Deleted entry ASC (05). All

7-45 Table 7-6, added new L2 code “Temperature Multiple LRU (F9)”

and new L3 codes 0x 0080 thru 0x 0088. All

7-46 Table 7-6, added L3 codes. All

7-47 thru 7-50 Table 7-6, revised L2 code Software runtime (FE) completely. All

7-51 Table 7-6, added GPS input for L1, L2, time label (31), and L3

GNSS sensor status word. All

7-52 Table 7-6, deleted entry L2 BUC mute (04) and added new L3

code 0x 0003. All

7-54 Table 7-6, added new L3 code. All

7-55 Table 7-6, Added L3 code 0 x 0004. All

7-70 and 7-71 Table 7-6, under GNSS sensor status word (80), added L3 code

0x 0008.

Under IRS Discrete word (81), revised L3 Description “Align

mode / Not Ready” to read as “Self Test Mode”, “Revisionary

Altitude mode” to read as “Initialization Mode” and “Normal

mode” to read as “Acquisition Mode”.

Added L3 code 0x 0008.

All

7-70 thru 7-73 Table 7-6, added L2 Ground speed (43), Body Pitch

Acceleration (50), Body Roll Acceleration (51) and Body Yaw

Acceleration (52).

Added new L3 codes for L2 codes GNSS sensor status word

(80) and IRS discrete word (81).

All

7-96 Tale 7-6, added 0x 0002 to L3 code and description.

Step 7.3 (1)(b)1, revised to add additional step to validate

communication cabling.

All

7-97 Step 7.3.(1)(i)3, revised to add information on software

validation. All

7-98 Paragraph 7.6, updated Figure 7-9 to latest. All

C-2 Revised the figure reference as Figures 4-21 and 4-22. All

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C-3 Paragraph 1.A, in the table, revised the item description for the

parameter “Electrical wiring - APM to Modman”. All

C-5 Revised the figure reference from 4-21 to Figures 4-30. All

C-7 Revised the figure reference as Figures 4-21 and 4-22.

Paragraph 1.B, in the table, revised the item description for the

parameter “Electrical wiring - APM to Modman”.

All

C-11 Revised the figure reference as Figures 4-21 and 4-22.

Paragraph 1.C, in the table, revised the item description for the

parameter “Electrical wiring - APM to Modman”.

All

C1 thru C6 Paragraph 1, rearranged and renumbered the tables in

Appendix E as follows:

Table C-1. Value Added Reseller (VAR/DP)

Table C-2. Aircraft Information

Table C-3. Air Data Inertial Reference Unit/Multi Mode Receiver

Table C-4. ARINC 429 Labels

Table C-5. Airframe Structural Blockage Information

Table C-6. Weight on Wheels

Table C-7. ARINC Tx Mute and Tail Sector Mute Switch

Table C-8. ARINC791 Equipped

Table C-9. Modman Serial Number

Table C-10. Modman Ethernet Configuration Table

Table C-11. KRFU Location

Table C-12. Antenna Location

Table C-13. Waveguide Manufacturer

Table C-14. Radome Manufacturer

Revised Table D-7 title and added additional rows for new entry

“Tail Sector Mute Switch Wired”.

Added Table C-9 for Modman Serial Number and Table C-10 for

Modman Ethernet Configuration Table.

All

Table of Highlights (Continued)

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RECORD OF REVISIONS

For each revision, write the revision number, revision date, date put in the manual, and your initials in the

applicable column.

NOTE: Refer to the Revision History in the TRANSMITTAL INFORMATION section for revision data.

Revision Number Issue Date Date Inserted Inserted by (initial)

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RECORD OF TEMPORARY REVISIONS

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

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

applicable data in the record columns on this page.

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

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

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

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

Temporary

Revision

Number

Status

Page

Number

Issue

Date

Date Put in

Manual

Date

Removed

From Manual

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SERVICE BULLETIN LIST

Service Bulletin

Number Subject Manual Rev.

Number Manual Rev.

Date

JETWAVE-23-0001,

Rev. 0 COMMUNICATIONS - JETWAVE™ SYSTEM -

Software Upgrade for the GXA System Line

Replaceable Units (LRU)

3 17 Aug 2016

JETWAVE-23-0002,

Rev 3 COMMUNICATIONS - JETWAVE™ SYSTEM -

Software Release for the GXA System Line

Replaceable Units (LRU)

4 3 Mar 2017

JETWAVE-23-0003,

Rev 0 COMMUNICATIONS - JETWAVE™ SYSTEM -

Software Release for the GXA System Line

Replaceable Units (LRU)

4 3 Mar 2017

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Subheading and Page Date Subheading and Page Date

* indicates a changed or added page.

F indicates a foldout page.

Title

T-1 * 3 Mar 2017

T-2 * 3 Mar 2017

T-3 * 3 Mar 2017

T-4 * 3 Mar 2017

T-5 * 3 Mar 2017

T-6 * 3 Mar 2017

Transmittal Information

TI-1 * 3 Mar 2017

TI-2 * 3 Mar 2017

TI-3 * 3 Mar 2017

TI-4 * 3 Mar 2017

TI-5 * 3 Mar 2017

TI-6 * 3 Mar 2017

TI-7 * 3 Mar 2017

TI-8 * 3 Mar 2017

TI-9 * 3 Mar 2017

T-10 * 3 Mar 2017

T-11 * 3 Mar 2017

T-12 * 3 Mar 2017

Record of Revisions

1 3 Mar 2017

2 3 Mar 2017

Record of Temporary Revisions

RTR-1 3 Mar 2017

RTR-2 3 Mar 2017

Service Bulletin List

1 * 3 Mar 2017

2 3 Mar 2017

List of Effective Pages

LEP-1 3 Mar 2017

LEP-2 3 Mar 2017

LEP-3 3 Mar 2017

LEP-4 3 Mar 2017

LEP-5 3 Mar 2017

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Table of Contents

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Introduction

1-1 3 Mar 2017

1-2 * 3 Mar 2017

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Description

2-1 * 3 Mar 2017

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2-14 * 3 Mar 2017

System Pre-configuration

3-1 * 3 Mar 2017

3-2 3 Mar 2017

3-3 * 3 Mar 2017

3-4 3 Mar 2017

Installation

4-1 * 3 Mar 2017

4-2 * 3 Mar 2017

4-3 * 3 Mar 2017

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F 4-104 3 Mar 2017

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Software Configuration

5-1 * 3 Mar 2017

5-2 * 3 Mar 2017

5-3 3 Mar 2017

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System Commissioning

6-1 * 3 Mar 2017

6-2 * 3 Mar 2017

6-3 * 3 Mar 2017

6-4 * 3 Mar 2017

6-5 * 3 Mar 2017

6-6 3 Mar 2017

6-7 3 Mar 2017

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Troubleshooting

7-1 3 Mar 2017

7-2 3 Mar 2017

7-3 * 3 Mar 2017

7-4 3 Mar 2017

7-5 3 Mar 2017

7-6 * 3 Mar 2017

7-7 * 3 Mar 2017

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* indicates a changed or added page.

F indicates a foldout page.

7-8 3 Mar 2017

7-9 3 Mar 2017

7-10 3 Mar 2017

7-11 3 Mar 2017

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Maintenance and Repair

8-1 3 Mar 2017

8-2 * 3 Mar 2017

8-3 * 3 Mar 2017

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Subheading and Page Date Subheading and Page Date

* indicates a changed or added page.

F indicates a foldout page.

8-4 * 3 Mar 2017

8-5 * 3 Mar 2017

8-6 * 3 Mar 2017

Appendix A: Specifications

A-1 3 Mar 2017

A-2 3 Mar 2017

A-3 3 Mar 2017

A-4 3 Mar 2017

A-5 3 Mar 2017

A-6 3 Mar 2017

A-7 3 Mar 2017

A-8 3 Mar 2017

A-9 3 Mar 2017

A-10 3 Mar 2017

A-11 3 Mar 2017

A-12 3 Mar 2017

Appendix B: Installation Information Sheet

B-1 3 Mar 2017

B-2 3 Mar 2017

Appendix C: Installation Checklist

C-1 * 3 Mar 2017

C-2 * 3 Mar 2017

C-3 * 3 Mar 2017

C-4 * 3 Mar 2017

C-5 * 3 Mar 2017

C-6 * 3 Mar 2017

C-7 * 3 Mar 2017

C-8 * 3 Mar 2017

C-9 * 3 Mar 2017

C-10 * 3 Mar 2017

C-11 * 3 Mar 2017

C-12 * 3 Mar 2017

C-13 * 3 Mar 2017

C-14 3 Mar 2017

Appendix D: List of Airframe Specific Information

Required for JetWave™ System Configuration

D-1 * 3 Mar 2017

D-2 * 3 Mar 2017

D-3 * 3 Mar 2017

D-4 * 3 Mar 2017

D-5 * 3 Mar 2017

D-6 * 3 Mar 2017

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TABLE OF CONTENTS

Title Page

SECTION 1 - INTRODUCTION

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

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

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

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

D. Units of Measure .......................................................................................................................... 1-2

E. Illustration ..................................................................................................................................... 1-2

1.2 Scope ................................................................................................................................................ 1-2

1.3 Part Numbers .................................................................................................................................... 1-2

1.4 Organization ...................................................................................................................................... 1-3

1.5 Customer Support ............................................................................................................................. 1-3

A. Honeywell Aerospace Online Technical Publications Website ................................................ 1-3

B. Honeywell Aerospace Contact Team ....................................................................................... 1-3

1.6 References ........................................................................................................................................ 1-3

A. Honeywell/Vendor Publications ...............................................................................................1-3

B. Other Publications .................................................................................................................... 1-4

1.7 Precautions ....................................................................................................................................... 1-4

1.8 Acronyms and Abbreviations ............................................................................................................. 1-5

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

SECTION 2 - DESCRIPTION

2.1 JetWave™ System Overview ............................................................................................................ 2-1

A. JetWave™ System LRUs ........................................................................................................ 2-2

B. JetWave™ System LRU Leading Particulars .......................................................................... 2-3

2.2 Honeywell JetWave™ System Architecture ...................................................................................... 2-8

A. Outside Antenna Equipment ....................................................................................................2-9

B. KRFU ..................................................................................................................................... 2-10

C. KANDU .................................................................................................................................. 2-11

D. Modman................................................................................................................................. 2-11

E. APM ....................................................................................................................................... 2-11

2.3 Honeywell Implementation .............................................................................................................. 2-12

2.4 JetWave™ System Modes of Operation ......................................................................................... 2-12

A. Power On Mode ..................................................................................................................... 2-12

B. System Initialization Mode ..................................................................................................... 2-13

C. Normal Operating Mode......................................................................................................... 2-13

D. Critical Fault Mode................................................................................................................. 2-13

E. Data Load Mode .................................................................................................................... 2-13

F. Commanded Mode ................................................................................................................ 2-14

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2.5 About Inmarsat Services ................................................................................................................. 2-14

SECTION 3 - SYSTEM PRE-CONFIGURATION

3.1 AES Configuration Data .................................................................................................................... 3-1

A. AES System Configurations .................................................................................................... 3-1

B. Regulatory Log Configuration Parameters .............................................................................. 3-3

C. Aircraft Service Configuration .................................................................................................. 3-3

SECTION 4 - INSTALLATION

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

A. Installation Procedure Overview for the JetWave™ System .................................................... 4-1

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

A. Modman.................................................................................................................................... 4-2

B. APM.......................................................................................................................................... 4-4

C. Maintenance Panel................................................................................................................... 4-4

4.3 KANDU............................................................................................................................................... 4-8

4.4 Installation Guidelines for the A791 Based AIM (If applicable) ........................................................ 4-10

4.5 Installation Guidelines for the LAIM (If applicable)........................................................................... 4-13

A. Install the LAIM and Radome Skirt Fairing Bonding Straps.................................................... 4-13

B. Install the LAIM to the Aircraft Fuselage................................................................................. 4-13

C. Install the Radome Skirt Fairing..............................................................................................4-14

4.6 KRFU ............................................................................................................................................... 4-14

A. General................................................................................................................................... 4-14

B. KRFU Thermal Pad Kit ........................................................................................................... 4-15

C. KFRU - Waveguide/coax RF Losses.........................................................................4-16

D. KRFU - Thermal Conduction Path.......................................................................................... 4-16

E. KRFU/Waveguide Installation................................................................................................. 4-17

4.7 Fuselage Mount Antenna (If applicable) .......................................................................................... 4-17

A. Introduction............................................................................................................................. 4-17

B. The FMA Installation General................................................................................................. 4-18

C. Advisories ............................................................................................................................... 4-19

D. Unpacking and Inspection ......................................................................................................4-19

E. FMA Installation Kits............................................................................................................... 4-19

F. Airframe Structural Modifications............................................................................................ 4-20

G. Mounting Guidelines............................................................................................................... 4-20

H. FMA Bonding.......................................................................................................................... 4-21

I. FMA Installation Procedure ....................................................................................................4-21

4.8 Tail Mount Antenna (If applicable) ................................................................................................... 4-34

A. Introduction............................................................................................................................. 4-34

B. TMA Installation General ........................................................................................................ 4-35

C. Advisories ............................................................................................................................... 4-35

D. TMA Unpacking and Inspection.............................................................................................. 4-36

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E. TMA Installation Kit Details..................................................................................................... 4-36

F. TMA Airframe Structural Modifications ................................................................................... 4-37

G. TMA Mounting Guidelines.......................................................................................................4-37

H. TMA Physical Placement........................................................................................................4-37

I. TMA Interface Mount Brackets (if required)............................................................................ 4-37

J. TMA Radome and Radome Fairing ........................................................................................ 4-38

K. TMA Assembly........................................................................................................................ 4-38

L. TMA Assembly Orientation ..................................................................................................... 4-38

4.9 Radome............................................................................................................................................ 4-38

A. FMA Human Exposure to RF EM Fields................................................................................. 4-39

4.10 Inspection of Waveguide .................................................................................................................. 4-40

4.11 Cabling and Drawings ...................................................................................................................... 4-40

SECTION 5 - SOFTWARE CONFIGURATION

5.1 ARINC 615A Software Data Load Process ........................................................................................ 5-1

A. Introduction .............................................................................................................................. 5-1

B. System Requirements............................................................................................................... 5-1

C. Overview................................................................................................................................... 5-2

D. Procedure (AIT Flight Simulyzer v3.0.0)................................................................................... 5-4

E. A615 LanConfig.Hex File Creation and Settings .................................................................... 5-16

SECTION 6 - SYSTEM COMMISSIONING

6.1 Provisioning of User Services ........................................................................................................... 6-1

A. Product Support Services ........................................................................................................ 6-2

B. Terminal Activation .................................................................................................................. 6-3

6.2 Certification and Approvals ............................................................................................................... 6-3

6.3 Post Installation System Checkout Procedures ................................................................................6-3

A. General Overview .................................................................................................................... 6-3

B. System Health and Configuration ............................................................................................ 6-4

C. Discrete Input Testing ............................................................................................................ 6-10

D. ARINC 429 Input Interface Testing ........................................................................................ 6-10

E. Manual Steering of the Antenna ............................................................................................ 6-11

F. System Available (Cockpit Control Panel) Output ................................................................. 6-12

6.4 Cable Calibration ............................................................................................................................. 6-12

6.5 TMA and FMA Antenna Alignment Procedure ................................................................................ 6-13

A. Antenna Assembly Orientation .............................................................................................. 6-13

B. Positioning of Aircraft for Antenna Alignment ........................................................................ 6-14

6.6 On-ground Testing and Commissioning .......................................................................................... 6-17

A. Testing and Commissioning Process with Restrictions ......................................................... 6-17

B. Data Link Available (Control Panel) Output ........................................................................... 6-18

6.7 Final System Checkout ................................................................................................................... 6-18

A. Network Status............................................................................................................................. 6-18

B. EMC Interference to Other Systems .........................................................................6-19

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SECTION 7 -TROUBLESHOOTING

7.1 Post-installation Troubleshooting ....................................................................................................... 7-1

7.2 Accessing the Maintenance Interface ................................................................................................ 7-1

A. Checking Status Information..................................................................................................... 7-2

B. Downloading LRU Logs ............................................................................................................ 7-4

C. System Data Load Failure ........................................................................................................ 7-7

D. SNMP ....................................................................................................................................... 7-7

E. System Reset ........................................................................................................................... 7-7

F. Electrical and Mechanical Inspection and Check ..................................................................... 7-7

G. Visual Inspection and Check .................................................................................................... 7-8

H. JetWave™ System Fault Codes............................................................................................... 7-8

7.3 System Fails Post-Installation Checks ............................................................................................. 7-96

7.4 Incorrect Navigation Data................................................................................................................. 7-97

7.5 System Will Not Connect to the Network ......................................................................................... 7-97

7.6 Connectivity of Each Ethernet Port .................................................................................................. 7-97

SECTION 8 - MAINTENANCE AND REPAIR

8.1 Maintenance Requirements ............................................................................................................... 8-1

8.2 Continued Airworthiness, FAR 25.1529 ............................................................................................. 8-1

8.3 Airworthiness Limitations.................................................................................................................... 8-1

8.4 General Instructions for Inspection .................................................................................................... 8-2

8.5 Electrical and Mechanical Inspection and Check...............................................................................8-3

8.6 Instructions for Continued Airworthiness............................................................................................ 8-3

8.7 Visual Inspection and Check.............................................................................................................. 8-4

8.8 Scheduled Maintenance and Inspections .......................................................................................... 8-4

8.9 Unscheduled Maintenance................................................................................................................. 8-6

8.10 Repair Requirements ......................................................................................................................... 8-6

APPENDIX A

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

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

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

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

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

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

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

APPENDIX B

1 Aircraft Information Sheet ..................................................................................................................B-1

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

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

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

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

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

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

APPENDIX C

1. Installation Checklist...........................................................................................................................C-1

A. OAE-TMA Checklist..................................................................................................................C-1

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

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

APPENDIX E

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

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LIST OF TABLES

Table Description Page

Table 2-1 JetWave™ System LRUs ............................................................................................... 2-2

Table 2-2 A791 Style Radome Package Variant ............................................................................ 2-2

Table 2-3 Non A791 Style Radome Package Variant .................................................................... 2-3

Table 2-4 Modman Leading Particulars ......................................................................................... 2-3

Table 2-5 APM Leading Particulars ............................................................................................... 2-4

Table 2-6 KANDU Leading Particulars ........................................................................................... 2-4

Table 2-7 KRFU Leading Particulars ............................................................................................. 2-5

Table 2-8 TMA Leading Particulars ................................................................................................ 2-7

Table 2-9 FMA Leading Particulars ................................................................................................ 2-8

Table 2-10 JetWave™ Fuselage Mount Radome Leading Particulars ............................................ 2-8

Table 2-11 Radome Packages ....................................................................................................... 2-10

Table 3-1 AR INC 429 Label List ................................................................................................... 3-1

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

Table 4-2 Modman Cable Loss Values........................................................................................... 4-4

Table 4-3 Discretes Table............................................................................................................... 4-5

Table 4-4 Thermal Pad Kit Contents ............................................................................................ 4-15

Table 4-5 Special Tools for FMA Installation ............................................................................... 4-18

Table 4-6 ARINC 791 Style Installation Kit .................................................................................. 4-20

Table 4-7 Non ARINC 791 Style Installation Kit ........................................................................... 4-20

Table 4-8 Special Tools for TMA Installation ............................................................................... 4-35

Table 4-9 TMA RF Interconnect Common Installation Components ............................................ 4-36

Table 4-10 Cabling Requirements ................................................................................................. 4-41

Table 5-1 Data Sets ....................................................................................................................... 5-3

Table 6-1 Modman LED Status Indications..................................................................................... 6-5

Table 7-1 L1 Codes ...................................................................................................................... 7-12

Table 7-2 L2 Codes – Module Within an AES LRU ..................................................................... 7-14

Table 7-3 L2 Codes – Inter LRU Interfaces ................................................................................. 7-16

Table 7-4 L2 Codes – ARINC Discrete Interfaces ....................................................................... 7-18

Table 7-5 L2 Codes – User Interface ........................................................................................... 7-19

Table 7-6 L3 Codes ...................................................................................................................... 7-20

Table 8-1 Scheduled Maintenance ................................................................................................ 8-4

Table 8-2 Unscheduled Maintenance ............................................................................................ 8-6

Table 8-3 Modman LED Status Indications .................................................................................... 8-6

Table D-1 Value Added Reseller (VAR/DP) ...................................................................................D-1

Table D-2 Aircraft Information..........................................................................................................D-1

Table D-3 Air Data Inertial Reference Unit/Multi Mode Receiver ...................................................D-1

Table D-4 ARINC 429 Labels .........................................................................................................D-1

Table D-5 Airframe Structural Blockage Information ......................................................................D-3

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Table D-6 Weight on Wheels ..........................................................................................................D-4

Table D-7 ARINC Tx Mute and Tail Sector Mute Switch ................................................................D-4

Table D-8 ARINC791 Equipped .....................................................................................................D-4

Table D-9 Modman Serial Number .................................................................................................D-5

Table D-11 Waveguide Manufacturer ...............................................................................................D-6

Table D-12 Radome Manufacturer ...................................................................................................D-6

Table D-13 KRFU Location ..............................................................................................................D-6

Table D-14 Antenna Location ...........................................................................................................D-6

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LIST OF FIGURES

Figure Description Page

Figure 1-1 Symbols ......................................................................................................................... 1-2

Figure 2-1 Ka-Band System ............................................................................................................ 2-1

Figure 2-2 JetWave™ System Block Diagram ................................................................................ 2-9

Figure 4-1 Typical Ground Strap Arrangement for A791 Compliant Fittings ................................. 4-10

Figure 4-2 Aircraft Coordinate System Orientation and Fitting Layout .......................................... 4-11

Figure 4-3 AIM Assembly Placement on Aircraft ........................................................................... 4-12

Figure 4-4 A791 Based AIM Assembly with FMA and KRFU Placement on Aircraft .................... 4-12

Figure 4-5 LAIM Assembly ............................................................................................................ 4-13

Figure 4-6 Radome Skirt Fairing and LAIM Assembly Position on Aircraft ................................... 4-14

Figure 4-7 KRFU Thermal Pads.................................................................................................... 4-15

Figure 4-8 FMA Install Location .................................................................................................... 4-21

Figure 4-9 FMA Assembly ............................................................................................................. 4-22

Figure 4-10 FMA Assembly Lifting Fixture Removal........................................................................ 4-23

Figure 4-11 View of H Plane and E Plane Bends ............................................................................ 4-24

Figure 4-12 LAIM Assembly with FMA and KRFU Placement on Aircraft ....................................... 4-26

Figure 4-13 KRFU and TMA Interconnect Arrangement ................................................................. 4-27

Figure 4-14 TMA RF TX J3 and RF RX J4 Interface Connector and Bonding Strap Locations ...... 4-29

Figure 4-15 WR42 Waveguide to 2.92 mm Coaxial Connector Adapter ......................................... 4-30

Figure 4-16 KRFU Bonding Strap Arrangement .............................................................................. 4-31

Figure 4-17 View of H Plane and E Plane Bends ............................................................................ 4-32

Figure 4-18 TMA Installation Location ............................................................................................. 4-37

Figure 4-19 TMA Assembly Isometric View .................................................................................... 4-38

Figure 4-20 Radome Assembly Mounted on Radome Skirt Fairing (LAIM) .................................... 4-40

Figure 4-21 (Sheet 1 of 4) Modman Outline and Installation Drawing (90400059-0001, REV F) ... 4-45

Figure 4-22 (Sheet 1 of 4) Modman Outline and Installation Drawing Variant 2 (90400059-0002,

REV A) .........................................................................................................................4-49

Figure 4-23 (Sheet 1 of 2) APM Outline and Installation Drawing (90401592, REV F) ................... 4-53

Figure 4-24 (Sheet 1 of 2) APM Outline and Installation Drawing (90405762, REV A) .................. 4-55

Figure 4-25 (Sheet 1 of 3) KANDU Outline and Installation Drawing (90401657, REV E) .............. 4-57

Figure 4-26 (Sheet 1 of 3) KANDU Variant 2 Outline and Installation Drawing (90405004,

REV C)..........................................................................................................................4-60

Figure 4-27 (Sheet 1 of 9) KRFU, Conduction-Cooled 1, Outline and Installation Drawing (90401573,

REV F) ..........................................................................................................................4-63

Figure 4-28 (Sheet 1 of 3) KRFU, Conduction-Cooled 2, Outline and Installation Drawing (90402347,

REV F) .........................................................................................................................4-72

Figure 4-29 (Sheet 1 of 3) KRFU, Forced Air Cooled, Outline and Installation Drawing (90401571,

REV D) .........................................................................................................................4-75

Figure 4-30 (Sheet 1 of 4) TMA Outline and Installation Drawing (90401428, REV F) ................... 4-78

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Figure 4-31 (Sheet 1 of 14) FMA Outline and Installation Drawing (90000380ICD, REV L) ........... 4-82

Figure 4-32 (Sheet 1 of 6) Fuselage Mount Radome Outline and Installation Drawing (90401395,

REV D) .........................................................................................................................4-96

Figure 4-33 (Sheet 1 of 4) LAIM Outline and Installation Drawing (90404861, REV A) ................ 4-102

Figure 4-34 (Sheet 1 of 10) JetWave™ System Interconnect Diagram - TMA (90400189-0001,

REV D) ....................................................................................................................... 4-106

Figure 4-35 (Sheet 1 of 8) JetWave™ System Interconnect Diagram - FMA (KRFU Inside

Aircraft Fuselage), (90400259-0001, REV C) ............................................................ 4-116

Figure 4-36 (Sheet 1 of 8) JetWave™ System Interconnect Diagram - FMA (KRFU Outside

Aircraft Fuselage), (90401047-1, REV F) .................................................................. 4-124

Figure 4-37 (Sheet 1 of 12) Alternative KRFU Outside Aircraft Fuselage Configuration (90405210,

REV D) ....................................................................................................................... 4-132

Figure 6-1 Aircraft ID Display/Update Information Page ................................................................. 6-4

Figure 6-2 AES GUI Login Page ..................................................................................................... 6-6

Figure 6-3 AES Home and Status Info Page .................................................................................. 6-7

Figure 6-4 View Configuration Files Page ....................................................................................... 6-8

Figure 6-5 Health Statuses (excerpt), AES Summary and Link Statuses ....................................... 6-8

Figure 6-6 AES Modman and Manufacturing Information Page ..................................................... 6-9

Figure 6-7 Aircraft Tail Number Page ............................................................................................. 6-9

Figure 6-8 Discrete I/O State ........................................................................................................ 6-10

Figure 6-9 Aircraft Statuses .......................................................................................................... 6-11

Figure 6-10 Manual Antenna Steering ............................................................................................ 6-12

Figure 6-11 Calibrate Transmit Cable Status Page ........................................................................ 6-13

Figure 6-12 GUI Login Page ........................................................................................................... 6-14

Figure 6-13 GUI Calibrate Antenna Alignment Page ...................................................................... 6-15

Figure 6-14 GUI Antenna Alignment Calibration Page Extract ....................................................... 6-17

Figure 6-15 Network Statuses ......................................................................................................... 6-19

Figure 7-1 AES GUI Login Page ..................................................................................................... 7-1

Figure 7-2 JetWave™ Logout Page ................................................................................................ 7-2

Figure 7-3 JetWave™ Summary and Link Status (Sheet 1 of 2) .................................................... 7-3

Figure 7-3 JetWave™ Summary and Link Status (Sheet 2 of 2) .................................................... 7-4

Figure 7-4 JetWave™ Fault Log Download Configuration Page .................................................... 7-5

Figure 7-5 JetWave™ Fault Log Data ............................................................................................. 7-6

Figure 7-6 JetWave™ Fault Log Download Page ........................................................................... 7-6

Figure 7-7 Bite Hierarchy ................................................................................................................ 7-8

Figure 7-8 AES and LRU Controller Interaction .............................................................................. 7-9

Figure 7-9 Contents of Aircraft Services Configuration File ........................................................... 7-98

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SECTION 1

INTRODUCTION

1.1 How to Use This Manual

A. General

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

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

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

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

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

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

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

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

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

instruction.

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

applicable paragraph or step.

B. Observance of Manual Instructions

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

unit.

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

know and obey the safety precautions.

C. Symbols

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

Publication 27. Special characters in text are spelled out.

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

letters.

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

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

devices.

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Figure 1-1. Symbols

D. Units of Measure

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

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

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

E. Illustration

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

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

5 in Figure 501.

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

1.2 Scope

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

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

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

1.3 Part Numbers

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

• 90401028-001 - JetWave™ System MCS 8200 Class A Forced Air KRFU

• 90401028-002 - JetWave™ System MCS 8200 Class A Conduction Cooled KRFU, Version 1

• 90401028-003 - JetWave™ System MCS 8200 Class A Conduction Cooled KRFU, Version 2

• 90406164-001 - JetWave™ System MCS 8250 Class A Modman, Version 2

• 90406164-XXX- JetWave™ System MCS 8250 Class A KANDU, Version 2

• 90406164-XXX- JetWave™ System MCS 8250 Class A Conduction Cooled KRFU, Version 2

• 90401027-001 - JetWave™ System MCS 8000 Class B Forced Air KRFU

• 90401027-002 - JetWave™ System MCS 8000 Class B Conduction Cooled KRFU, Version 1

• 90401027-003 - JetWave™ System MCS 8000 Class B Conduction Cooled KRFU, Version 2

• 90401027-004 - JetWave™ System MCS 8000 Class A Conduction Cooled KRFU, Version 2, FMA

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• 90401027-005 - JetWave™ System MCS 8000 Class A Forced Air KRFU, Version 2, FMA

• 90400017-XXX - A791 Radome Package

• 90400016-XXX - Non-A791 Radome Package.

1.4 Organization

This manual includes the following sections:

• SECTION 1 INTRODUCTION - Information about the JetWave™ system

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

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

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

JetWave™ system

• APPENDIX B - Installation information sheets

• APPENDIX C - Installation checklist

• APPENDIX D - Airframe specific information required for configuration.

1.5 Customer Support

A. Honeywell Aerospace Online Technical Publications Website

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

• To download or see publications online

• To order a publication

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

B. Honeywell Aerospace Contact Team

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

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

Contact Team gives 24/7 customer service to Air Transport & Regional, Business & General

Aviation, and Defense & Space customers around the globe.

(2) Aerospace Technical Support

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

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

1.6 References

A. Honeywell/Vendor Publications

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

• Not Applicable

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B. Other Publications

(1) These publications are standard references. Check for the latest version of the publication.

• The United States GPO Style Manual (available at

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

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

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

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

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

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

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

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

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

• CAGE codes and manufacturers’ addresses are available at https://cage.dla.mil

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

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

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

Part 1, Physical Installation and Aircraft Interfaces.

1.7 Precautions

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

and cautions.

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

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

HARDWARE END STOPS. TECHNICIANS WORKING IN CLOSE PROXIMITY OF THE

ANTENNA MUST BE PROTECTED BY DISABLING THE TRANSMITTER BEFORE

THEY APPROACH THAT AREA OF THE AIRCRAFT.

WARNING: SERVICE TECHNICIANS MUST OBEY STANDARD SAFETY PRECAUTIONS, SUCH

AS WEARING SAFETY GLASSES, TO PREVENT PERSONAL INJURY WHILE

INSTALLING OR PERFORMING SERVICE ON THIS SYSTEM.

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

DISCONNECTING THE TERMINAL WITHOUT TURNING POWER OFF MAY CAUSE

VOLTAGE TRANSIENTS THAT CAN DAMAGE THE TERMINAL.

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CAUTION: THIS EQUIPMENT INCLUDES ITEMS THAT ARE ELECTROSTATIC DISCHARGE

SENSITIVE DEVICES. ELECTROSTATIC DISCHARGE SENSITIVE DEVICES ARE

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

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

HUMAN BODY, WHICH, IN CONJUNCTION WITH NONCONDUCTIVE GARMENTS AND

FLOOR COVERINGS, GENERATES AND RETAINS STATIC ELECTRICITY. TO

ADEQUATELY PROTECT ESDS DEVICES, THE DEVICE AND EVERYTHING THAT

CONTACTS IT MUST BE BROUGHT TO GROUND POTENTIAL BY PROVIDING A

CONDUCTIVE SURFACE AND DISCHARGE PATHS. USE STANDARD INDUSTRY

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

REMOVING, OR SERVICING THE EQUIPMENT.

1.8 Acronyms and Abbreviations

A. General

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

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

List of Acronyms and Abbreviations

Term Full Term

AC alternating current

ACM aeronautical core module

AES aircraft earth station

AISD airline information services domain

AIM aircraft interface mount

AIT Avionics Interface Technologies

AMIP open antenna to modem interface protocol

ANSI American National Standards Institute

APM aeronautical personality module

ARINC Aeronautical Radio, Incorporated

ASC antenna subsystem controller

ASME American Society of Mechanical Engineers

ATA Air Transport Association

AWG American wire gauge

BDC block down-converter

BIT built-in test

BITE built-in test equipment

BOSS Broadband Off-board Services System

BRS business and regional aviation segment

BUC block up-converter

C Celsius

CAGE commercial and government entity

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CAT commercial air transport

CBIT continuous built-in test

CIR committed information rate

cm centimeter

dB decibel

DER designated engineering representative

DHCP dynamic host configuration protocol

DID data item description

DNS domain name system

DP distribution partner

EMEA Europe, the Middle East, and Africa

ESDS electrostatic discharge sensitive

EST Eastern Standard Time

F Fahrenheit

FAA Federal Aviation Administration

FAR Federal Aviation Regulations

FMA fuselage mount antenna

FTP file transfer protocol

FXS foreign exchange subscriber

GHz gigahertz

GPO Government Printing Office

GPS global positioning system

GNSS global navigation satellite system

GSC global signaling channel

GTE ground transmit enable

GUI graphic user interface

HPA high-power amplifier

hPa hectopascal

HTP horizontal tail plane

Hz hertz

IEC International Electrotechnical Commission

IEEE Institute of Electrical and Electronics Engineers

IF intermediate frequency

IMU inertial measurement unit

in-lb inch-pound

I/O input and output

IP Internet protocol

IRS inertial reference system

List of Acronyms and Abbreviations (Continued)

Term Full Term

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IRU inertial reference unit

ISDN integrated services digital network

ISP Inmarsat service provider or internet service provider

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

KANDU Ku/Ka band aircraft network data unit

KRFU Ku/Ka band radio frequency unit

kg kilogram

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

LAIM local aircraft interface mount

LAN local area network

LED light emitting diode

LNA low noise amplifier

LRU line replaceable unit

LSAP loadable software airplane part

m meter

mΩmilliohm

mA milliampere

Mbps megabits per second

MCU modular concept unit

MHz megahertz

MIB management information base

MIR maximum information rate

mm millimeter

Modman modem manager

MOP maximum operating power

ms millisecond

NA not applicable

NEXT near end cross talk

Nm Newton meter

NMS network management system

O&I outline and installation

OAE outside antenna equipment

OID object identifier

OMT orthogonal mode transducer

OTA over the air

Pa pascal

PCU position control unit

PIESD passenger information and entertainment services domain

List of Acronyms and Abbreviations (Continued)

Term Full Term

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PN part number

PODD passenger owned devices domain

POTS plain old telephone system

POST power-on self test

PSI pound per square inch

RF radio frequency

RFM radio frequency module

RMA return material authorization

RSSI receive signal strength indicator

RX receive

SAS satellite access station

SATCOM satellite communication

SDIM system description, and installation manual

SLA service level agreement

SNMP simple network management protocol

SSPP service subscriber plan

SVN secure virtual network

TMA tail mount antenna

TNC threaded Neill-Concelman

TPK terminal provisioning key

TX transmit

UNC unified coarse thread

USB universal serial bus

USMS United States Measurement System

VAC volt alternating current

VAR value added reseller

VDC volt direct current

VLAN virtual local area network

VoIP voice over Internet protocol

VPN virtual private network

VSAT very small aperture terminal

VTP vertical tail plane

WAN wide area network

WOW weight on wheels

List of Acronyms and Abbreviations (Continued)

Term Full Term

Draft as of 31 May 2017

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SECTION 2

DESCRIPTION

2.1 JetWave™ System Overview

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

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

communicates to the SAS through a satellite as shown in Figure 2-1.

Figure 2-1. Ka-Band System

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

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

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

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

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

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

K-band).

A. JetWave™ System LRUs

The JetWave™ system is made up of the LRUs in Table 2-1, Table 2-2, and Table 2-3.

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Table 2-1. JetWave™ System LRUs

LRU PN

Modman 90400012-0001

Modman Variant 2 90400012-0002

APM 90401121

KANDU 90401566

KANDU Variant 2 90404518

KRFU Conduction Cooled Variant 1 90401203

KRFU Conduction Cooled Variant 2 90402346

KRFU Forced Air Cooled 90401202

FMA 90000380-1

TMA 90400013-0001

A791 FM radome 90400017-XXX

Non-A791 FM radome 90400016-XXX

Table 2-2. A791 Style Radome Package Variant

Aircraft A791 Style Radome Package Variant

A319/A320/A321 90400017-01

A330/A340 90400017-02

A350 90400017-03

A380 90400017-04

B737/B757 90400017-05

B747 90400017-06

B777 90400017-08

B787 90400017-09

B767 90400017-10

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B. JetWave™ System LRU Leading Particulars

(1) Refer to Table 2-4 for the Modman leading particulars.

(2) Refer to Table 2-5 for the APM leading particulars.

(3) Refer to Table 2-6 for the KANDU leading particulars.

(4) Refer to Table 2-7 for the KRFU leading particulars.

(5) Refer to Table 2-8 for the TMA leading particulars.

(6) Refer to Table 2-9 for the FMA leading particulars.

(7) Refer to Table 2-10 for the B757 FMA radome particulars..

Table 2-3. Non A791 Style Radome Package Variant

Aircraft Non A791 Style Radome Package Variant

A319/A320/A321 90400016-01

A330/A340 90400016-02

A350 90400016-03

A380 90400016-04

B737/B757 90400016-05

B747 90400016-06

B777 90400016-08

B787 90400016-09

B767 90400016-10

Table 2-4. Modman Leading Particulars

Characteristic Specification

Length 15.32 inches (389.1 mm) maximum

Width 5.02 inches (127.5 mm) maximum

Height 7.88 inches (200.2 mm) maximum

Weight 14.0 pounds (6.35 kg) maximum

Operating voltage 115 VAC, 400 Hz

Power consumption 60 watts maximum

NOTE: Honeywell recommends that wiring and cooling is

designed for 100 watts in order to allow for seamless upgrades

to the Modman with enhanced capability at a later date.

Power dissipation 59 watts maximum

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

Operating temperature -40°F (-40°C) to 158°F (70°C)

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

Maintenance No scheduled maintenance required

Interfaces J1A - PODD, PIESD, and AISD

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

J1C - IF to/from KRFU and aircraft power

Table 2-5. APM Leading Particulars

Characteristic Specification

Length 4.515 inches (114.68 mm) without connector

Width 4.015 inches (101.98 mm) maximum

Height 1.315 inches (33.40 mm) maximum

Weight 12 ounces (0.34 kg) maximum

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

Power consumption Power supplied by Modman

Power dissipation 0.3 watts maximum

Cooling No forced-air cooling required

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

Maintenance No scheduled maintenance required

Interface J1 - Modman

Table 2-6. KANDU Leading Particulars

Characteristic Specification

Length 11.020 inches (279.91 mm) maximum

Width 9.075 inches (230.50 mm) maximum

Height 4.760 inches (120.90 mm) maximum

Weight 8.8 pounds (4.0 kg) maximum

Operating voltage 115 VAC, 400 Hz

Power consumption 200 watts Class A maximum average power

115 watts Class B maximum average power

Power dissipation 50 watts Class A maximum average power

42 watts Class B maximum average power

Cooling See 90401567 Outline and Installation Drawing for cooling

clearance requirement

See 90405004 Outline and Installation Drawing for the KANDU

Variant 2 for cooling clearance requirement

No forced-air cooling required

Table 2-4. Modman Leading Particulars (Continued)

Characteristic Specification

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

Maintenance No scheduled maintenance required

Interfaces J1 - Aircraft and Modman

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

J3 - KRFU, OAE, and maintenance

J4 - Ethernet (quadrax)

Table 2-7. KRFU Leading Particulars

Characteristic Specification

Conduction-cooled 1 configuration:

Length 16.55 inches (420.4 mm) maximum

Width 10.03 inches (254.8 mm) maximum

Height 2.08 inches (52.8 mm) maximum

Weight 12.00 pounds (5.4 kg) maximum (including thermal pad)

KRFU 11.25 pounds (11.25 kg) nominal

Thermal pad 0.75 pounds (0.34 kg) nominal

Operating voltage 115 VAC, 400 Hz

Power consumption 300 watts maximum at transmit amplifier saturation.

220 watts maximum at MOP for 100% duty cycle.

127watts typical at MOP for 50% duty cycle when the base plate

is at 77°F (25°C).

55 watts typical with transmit mute.

Power dissipation 200 watts maximum at MOP for 100% duty cycle.

115 watts typical at MOP for 50% duty cycle when the base plate

is at 77°F (25°C).

55 watts typical with transmit mute.

Cooling Conductive - cooled through the baseplate with thermal pad.

KRFU will mute the transmit RF signal if the hottest point on the

aircraft baseplate exceeds 185°F (85°C) to reduce heat dissipation.

KRFU will automatically un-mute once KRFU cools below 167˚F

(75˚C).

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

Maintenance No scheduled maintenance required

Interfaces J1 - Aircraft power input

J2 - Control interface from KANDU

J3 - RF TX to OAE

J4 - RF RX from OAE

J5 - IF TX from Modman

J6 - IF RX to Modman

Table 2-6. KANDU Leading Particulars (Continued)

Characteristic Specification

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Conduction-cooled 2 configuration:

Length 16.55 inches (420.4 mm) maximum

Width 9.01 inches (228.8. mm) maximum

Height 2.08 inches (52.8 mm) maximum

Weight 11.30 pounds (5.1 kg) maximum

Operating voltage 115 VAC, 400 Hz

Power consumption 300 watts maximum at transmit amplifier saturation.

220 watts maximum at maximum nominal system transmit power.

185 watts typical at maximum nominal system transmit power when

base plate is at 77°F (25°C).

210 watts typical at maximum nominal system transmit power when

KRFU base plate is at 158°F (70°C).

Power dissipation 260 watts maximum at transmit amplifier saturation.

200 watts maximum at maximum nominal system transmit power.

167 watts typical at maximum nominal system transmit power when

base plate is at 77°F (25°C).

192 watts typical at maximum nominal system transmit power when

KRFU base plate is at 158°F (70°C).

Cooling Conductive - cooled through the baseplate with thermal pad.

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

KRFU will mute the transmit RF signal if the hottest point on KRFU

baseplate exceeds 158°F (70°C).

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

Maintenance No scheduled maintenance required

Interfaces J1 - Aircraft power input

J2 - Control interface from KANDU

J3 - RF TX to OAE

J4 - RF RX from OAE

J5 - IF TX from Modman

J6 - IF RX to Modman

Forced air configuration:

Length 18.05 inches (458.5 mm) maximum

Width 9.01 inches (228.8 mm) maximum

Height 3.230 inches (82.04 mm) maximum

Weight 14.6 pounds (6.6 kg) maximum

Operating voltage 115 VAC, 400 Hz

Power consumption 300 watts maximum at transmit amplifier saturation.

220 watts maximum at maximum nominal system transmit power.

185 watts typical at maximum nominal system transmit power.

Table 2-7. KRFU Leading Particulars (Continued)

Characteristic Specification

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Power dissipation 260 watts maximum at transmit amplifier saturation.

200 watts maximum at maximum nominal system transmit power.

167 watts typical at maximum nominal system transmit power.

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

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

KRFU will mute the transmit RF signal if insufficient cooling air is

supplied.

Maintenance No scheduled maintenance required

Interfaces J1 - Aircraft power input

J2 - Control interface from KANDU

J3 - RF TX to OAE

J4 - RF RX from OAE

J5 - IF TX from Modman

J6 - IF RX to Modman

Table 2-8. TMA Leading Particulars

Characteristic Specification

Length 13.70 inches (348.0 mm) maximum

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

Height 13.57 inches (344.7 mm) maximum

Weight 10 pounds (4.55 kg)

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

Power dissipation 85 watts maximum

Cooling Natural convection and radiation only

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

Maintenance No scheduled maintenance required

Interfaces J2 - Power/control interface from KANDU

J3 - RF TX from KRFU

J4 - RF RX to KRFU

Table 2-9. FMA Leading Particulars

Characteristic Specification

Length 23.03 inches (585 mm) maximum

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

Height 9.39 inches (238.51 mm) maximum

Table 2-7. KRFU Leading Particulars (Continued)

Characteristic Specification

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2.2 Honeywell JetWave™ System Architecture

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

classes of terminal:

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

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

• Class A OEM satellite terminal: For use on CAT types of aircraft but will be designed with

consideration given to the ARINC 791 standard.

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

Refer to Figure 2-2 for the JetWave™ system block diagram.

Weight 83 pounds (37.6 kg) maximum

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

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

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

Power dissipation 135 W @ steady state

Cooling Natural convection and radiation only

Maintenance No scheduled maintenance required

Interfaces P1 - Power from KANDU

P2 - Control interface from KANDU

P3 - IMU power and control from KANDU

J4 - RF RX to KRFU

J5 - RF TX from KRFU

Table 2-10. JetWave™ Fuselage Mount Radome Leading Particulars

Characteristic Specification

Length 95.472 inches (242.99 mm) (typical)

Width 43.881 inches (1,114.58 mm) (typical)

Height 11.892 inches (302.06 mm) (typical)

Weight 53.5 pounds (24.27 kg) (typical)

Table 2-9. FMA Leading Particulars

Characteristic Specification

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Figure 2-2. JetWave™ System Block Diagram

The JetWave™ system LRUs are as follows:

A. Outside Antenna Equipment

• The OAE can include the following components:

• Mechanically steered antenna - either fuselage mount or tail mount.

• Radome package - fuselage mount configuration only (tail mount individual radomes are

available per aircraft type).

•KRFU

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• RF component kit - fuselage mount configuration only. (tail platforms installation kits

containing RF interconnects are available depending on aircraft type).

• OAE installation kit (optional, for ARINC 791 style configuration only).

• The antenna includes an aperture.

• The OAE is powered by the KANDU.

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

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

movement of the platform.

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

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

• The TMA or FMA receives power from the KANDU.

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

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

• RF component kits are available for both ARINC 791 Style and Non ARINC 791 style configura-

tions. The RF component kit includes: Tx waveguide, Rx coax cable, Rx coax to waveguide

adapter, sealing o-rings, and waveguide and adapter attachment.

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

NOTE: Not all aircraft will have a skirt fairing.

B. KRFU

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

frequencies (29-30 GHz)

• An HPA to increase the signal strength for transmission by the antenna

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

MHz)

• Accepts 115 VAC aircraft power.

Table 2-11. Radome Packages

ARINC 791 Style Radome Package Non ARINC 791 Style Radome Package

Fuselage mount radome Fuselage mount radome

ARINC 791 style AIM kit (aircraft specific) Skirt fairing (aircraft specific)

LAIM KIT

Radome attach hardware kit

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C. KANDU

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

antenna/KRFU and reports status over this Ethernet interface.

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

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

• Provides power and control to the antenna.

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

• Accepts 115 VAC aircraft power.

D. Modman

• Is the overall controller of the system.

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

MHz.

• Supplies the user interfaces to the aircraft and passengers as follows:

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

(10/100/1000 Base T).

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

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

Base T).

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

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

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

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

•Accepts 115 VAC from the aircraft.

• Manages the BIT for the complete AES.

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

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

RS-422 discretes.

E. APM

• The APM holds the configuration data for the system.

•Is powered by the Modman.

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2.3 Honeywell Implementation

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

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

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

standard inter-wiring is not utilized).

• ARINC 791 TX Mute between the Modman and the KANDU is optional, the Honeywell

implementation uses RS422 signaling on manufacturer-specific circuits 3 to 4 instead.

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

KANDU Reset signal.

• The RSSI function is in the Modman.

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

provisioned standard inter-wiring is not utilized).

• The A350 variant of the ARINC 791 style configuration, has AIM kit fittings that deviate from the

ARINC 791 coordinate listing for the 7 fitting.

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

Refer to SECTION 3 SYSTEM PRE-CONFIGURATION, AES Configuration Data for the details of ARINC

429 labels required for the JetWave™ System.

2.4 JetWave™ System Modes of Operation

The JetWave™ system supports the following modes of operation:

• Power On

• System Initialization

• Normal Operation

• Critical Fault

• Data-Load

• Commanded.

A. Power On Mode

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

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

system enters into the system initialization mode.

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

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B. System Initialization Mode

In the System Initialization Mode, the Modman starts additional POST and BITE, system access,

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

The RF transmission is disabled in this mode.

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

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

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

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

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

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

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

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

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

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

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

into the Normal Operating Mode.

C. Normal Operating Mode

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

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

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

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

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

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

continuous BITE, SNMP, GUI, user services, etc. in this mode.

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

applied to the last LRU.

D. Critical Fault Mode

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

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

disconnected. The system may support minimal services like SNMP, continuous BITE, GUI, etc. in

this mode.

E. Data Load Mode

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

Modman is asserted. The SNMP, GUI, and continuous BITE services may not be supported in data

load mode. The RF transmission is disabled in data load mode. The Modman provides ARINC 615A

Ethernet data loading to itself and other LRUs through its own interface in Data Load Mode. Data

Load mode can be entered from "Normal Operating mode", "System Initialization mode", or

"Critical Fault mode". The system will exit Data Load Mode once the local data load discrete is

de-asserted.

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F. Commanded Mode

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

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

initiating automatic antenna alignment, transmit cable calibration, manual antenna pointing to

defined location, etc.

The system will come out of the commanded mode by a System reset.

2.5 About Inmarsat Services

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

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

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

around the world.

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

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

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

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

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

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

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

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

not available.

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SECTION 3

SYSTEM PRE-CONFIGURATION

3.1 AES Configuration Data

NOTE: Any tools for preparing the config files for the terminal must be licensed from Honeywell.

The AES configuration data is a set of configuration files, stored on the APM. Each configuration file

contains a set of airplane-unique parameters. The parameters define the configuration of the AES

necessary for the initialization and operation of the Honeywell JetWave™ AES system. The AES

configuration data holds information such as:

•Aircraft tail registration number

• Aircraft structural blockage information

• ARINC 429 label definition set for positioning and steering used by the KANDU

• WOW input and polarity, etc

• USER operational preferences

• BOSS configuration data

• LAN network configuration data

• Default satellite configuration.

A. AES System Configurations

The details of the ARINC 429 labels required for the JetWave™ System are mentioned in the table

below:

Table 3-1. ARINC 429 Label List

Label Set

Required

ARINC

429

Labels Description Source

Maximum

Transmit

Delay

(Msec)

Maximum

Transmit

Interval

(Msec) Approximate

Resolution

Label For best

accuracy Preferred Label Set

150 Yes UTC Time Nil 1000 1°

260 Yes Date 1000 1 day

254

/110

Yes Present Position –

Latitude

/GNSS Latitude

Hybrid

/GNSS

160

/1000

100

/20

0.000172°

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The AES system configuration includes the aircraft installation information.

NOTE: The AES System configuration file update is not a field activity. This is done by the

equipment supplier as part of production process. On completion of AES system installation

activities, the installer can view and verify the AES configuration settings through the GUI

as described in this section.

To view and make sure the AES configuration data is correct, navigate to the “Configuration Files”

information pages under the “Other Information & Control” menu. Figure 6-4 shows the typical

configuration file Information page.

NOTE: The AES system does not lose its configuration data because of the loss of its primary

power. The validity of the AES configuration content is determined by the AES system with

a checksum process. The checksum is done at the time of each power-up. An invalid

checksum results in the AES system reverting to the default values.

255

/111

Yes Present Position –

Longitude

/GNSS Longitude

Hybrid

/GNSS

160

/1000

100

/20

0.000172°

261

/76

Yes Altitude

/GNSS Altitude (MSL)

Hybrid

/GNSS

/1000

/20

0.125 ft

132

/314

Yes

/No

True Heading Hybrid

/INS

110 50 0.0055°

/0.4°

324 Yes Pitch Angle INS 50 20 0.011°

325 Yes Roll Angle INS 50 20 0.01°

330 Yes Yaw Rate INS 50 20 0.015

degrees/sec

326 Yes Pitch Rate INS 50 20 0.015

degrees/sec

327 Yes Roll Rate INS 50 20 0.015

degrees/sec

175

/112/312

Yes Ground Speed

/GNSS Ground Speed

Hybrid

/GNSS/

INS

110

/Nil

40 0.125 knots

(kn)

Label

Acceptable Replacement to Primary

125 UTC Time INS 1200 200 0.1 min.

Table 3-1. ARINC 429 Label List

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B. Regulatory Log Configuration Parameters

The regulatory log configuration parameters file (APM file - reglog.cfg) contains details of the

remote server to use to transfer the regulatory log data.

C. Aircraft Service Configuration

There are a number of functions that an Ethernet port can support namely, data traffic, data loading,

GUI, AES logs extraction (maintenance function) and status/control (through the SNMP). The

terminal can be configured to indicate whether an Ethernet port supports traffic, data loading,

SNMP etc, such as AG1 SNMP, and data loading, EG1 traffic, using the aircraft service

configuration file.

Once the items have been loaded into the APM the Modman reads the APM once at power-on and passes

the appropriate data to the relevant LRU or uses the information locally.

The following airframe specific information is required for creating the JetWave™ configuration files:

• Applicable ARINC 429 Label Definition sets from Aircraft IRS/IRU and GNSS

• Discrete input availability and its polarity

• User Ethernet Ports which are to be configured and the type of services to be enabled (such as

Data Load, SNMP, GUI and OTA access).

• Aircraft blockage data.

Refer to APPENDIX D on Page D-1 for more details.

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SECTION 4

INSTALLATION

4.1 Overview

A. Installation Procedure Overview for the JetWave™ System

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

VAR/DP/Honeywell about installation kits that include mating connectors and cables.

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

environmental levels that the equipment is certified to handle.

Refer to APPENDIX D for the installation reference checklist.

Complete the Airframe Specific Information sheet in APPENDIX D. For new configurations, provide

this sheet to Honeywell so an APM file can be generated.

NOTE: ARINC 429 labels may be obtained from the aircraft ADIRU or MMR or other suitable

equipment, providing they meet the required update rate, latency and accuracy.

NOTE: For FMA located in Non-ARINC791 defined positions, a structural blockage map will have

to be defined for the aircraft.

The JetWave™ system installation procedure includes:

• the Modman, APM, Maintenance Panel and Discrete wiring

• the KANDU

• the AIM or the LAIM

• the KRFU Thermal Pad and the KRFU

• the FMA or the TMA

•the Radome

• Cabling and drawings.

Refer to Table 4-3 for a detailed explanation of the discrete signal required for correct operation of

the GX system.

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

(1) Install adapter plate for the FMA. For Fuselage Mount Configurations, install either the

ARINC 791 style antenna interface mount (AIM) or non ARINC 791 local antenna interface

mount (LAIM), depending on the selected installation option. Installation shall be per

instructions related to each configuration. The adapter plates required for mounting the OAE

are available in installation kits from Honeywell and various other suppliers.

The TMA tail configuration requires that the TMA and KRFU be installed on the aircraft tail tip

under a radome specific to the tail on that aircraft. Installation brackets and provisions are

specific to each tail platform.

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

provided.

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

available as installation kits from various suppliers.

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

installation requirements.

(5) Apply power to the system.

(6) Install radome after completion of post installation checks.

4.2 JetWave™ System Internal LRU Installation

A. Modman

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

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

installaton.

Refer to Figure 4-22 for outline and installation information, and Figure 4-34 thru Figure 4-37 for

the applicable interconnect diagram.

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

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

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

(1) The Modman mounting kits are as follows:

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

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

www.carlisleit.com.

(2) The Modman connectors are as follows:

Table 4-1 provides the connector part numbers for the Modman rear connector. The mating

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

Table 4-1. ARINC 600 Connectors

Connector PN Description Qty

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

Insert A:

Radiall PN 620075050

Arrangement Q11, Shell Size 2:

Size 8 quadrax contact for Ethernet connections 11

Insert B:

PN: D38999/26FH35PN

D38999/26FD35PN

Radiall PN 620075050

Arrangement 120Q2, Shell Size 2:

#22 contacts

Size 8 quadrax contact for Ethernet connections

118

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

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

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

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

should not cause deviation from NEXT parameters of the ARINC 664 compliant Star Quad

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

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

clockwise direction.

(3) The Modman bonding is as follows:

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

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

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

mΩ.

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

11dB at 950 MHz and a maximum loss of 18 dB at 1,450 MHz and 21.2 dB at 1,950 MHz.

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

attenuator in the RX path. The choice of parts are detailed in Table 4-2.

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

reference to the KRFU and the attenuator will introduce too much loss to that portion

of the signal.

• The loss at 50 MHz in the TX path must be less than 3.1 dB.

• The TX and RX cable loss should be matched within 1dB at 1,450 MHz.

• The TX and RX coax cables should 50 ohms with a VSWR of less than 1.5:1.

• The TX and RX cables must have a minimum isolation at 2,150 MHz of 120 dB.

• The isolation specification may need to be increased if the TX and RX cables are

in close proximity to high power RF signals in the 950 MHz to 1,950 MHz band,

e.g. cellular base stations.

Insert C:

PN: D38999/26FE6PN

PN: not included

PN: 620022

Arrangement 12F5C2, Shell Size 2:

#12 contacts

#16 contacts

Size 16 optical contacts (not used)

Size 5 coax contact for RF connections

Table 4-1. ARINC 600 Connectors (Continued)

Connector PN Description Qty

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NOTE: Input signal range: -79 to -5 dBm. Output signal range -30 to +5 dBm. Incross talk

requirement: -25 dBc. Output cross talk requirement: -40 dBc.

B. APM

The APM can be installed in any orientation. Refer to Figure 4-24 for outline and installation

information and Figure 4-34 thru Figure 4-37 for the applicable interconnect diagram.

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

There are no clearance requirements for the APM.

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

minimum ultimate tensile strength of 125 KSI (861.845 newton/millimeter²) when you torque the

screws.

APM to Modman interconnect cable must use ARINC 664 compliant 2 shielded twisted pair 24

AWG (or aerospace grade shielded Cat 5/Cat 5E minimum) PN ECS 922404 or equivalent, with a

maximum length of 9.8 feet (3 m).

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

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

or equal to 2.5 mΩ.

C. Maintenance Panel

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

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

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

as follows:

(1) Discrete Outputs:

NOTE: Discrete outputs are normally open and capable of sinking 20 mA of current with a

maximum voltage of 36 VDC as per ARINC 763.

• System available (Modman MP13E) open/ ground output connected to a lamp

Table 4-2. Modman Cable Loss Values

Cable Loss @ 950 MHz

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

Equalizer in TX path 10.5 dB

Minicircuits, PN

TAT-10R5DC1+ (10.5 dB

equalizer) or equivalent

4.8 dB

Minicircuits, PN

TAT-4R8DC11+ (4.8 dB

equalizer) or equivalent

None

Attenuator in RX path 10.5 dB

Minicircuits, PN TAT-10R5-1+

(10.5 dB attenuator) or

equivalent

4.8 dB

Minicircuits, PN TAT-4R8-1+

(4.8 dB attenuator) or

equivalent

None

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• Data link available (Modman MP13F) open/ ground output connected to a lamp.

(2) Discrete Inputs:

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

GND to enable

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

GND to enable

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

GND to enable

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

enable

• Tx mute (KANDU J1D) connected to a normally open switch with a GND to enable.

• Front Panel Enable Mode (Modman MP10F) connected to a normally open switch with a

GND to enable

• Discrete Signal Ground (Modman MP12F), to be used as the ground reference for the

other Modman discrete inputs

• Discrete Signal Ground (KANDU J1-B), to be used as the ground reference for the

KANDU discrete inputs

(3) Ethernet Port:

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

NOTE: The AV1 is the default data loading port, any other Ethernet ports can be selected as

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

For LRU pin details, refer to the applicable system interconnect diagram, Figure 4-34 thru

Figure 4-37.

Refer to Table 4-3 for a list of I/O discretes.

Table 4-3. Discretes Table

Discrete I/O Pin Description Mandatory / Optional

Weight-on-Wheels

(WOW) ModMan J1-MP11A Use and sense of the

Weight on Wheels input

is to determine

Air/Ground Status, as

configured by the AES

system configuration

data.

Signal type: Input

Optional

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Local Data Load ModMan J1-MP10B The discrete shall

request the ModMan to

change mode in the

following manner:

• Open to ground

transition: Request

for data load mode

to be entered

• Ground to open

ground transition:

Request for reset of

system (if in data

load mode)

Signal type: Input

Mandatory

TX Control KANDU J1-D The discrete shall

disable the transmission

of signals when

grounded, and allow

transmission when

open.

Signal type: Input

Mandatory

Public Services Disable ModMan J1-MP11E The discrete shall

disable the PODD

interfaces when

grounded, and enable

PODD interfaces when

open.

Signal type: Input

Optional

Ground Transmit Enable ModMan J1-MP11D The discrete shall

request the AES when in

normal operation mode

to ignore Air/Ground

status and provide user

service.

• Ground = Enable RF

transmission on the

ground.

• Open = Normal.

Signal type: Input

Mandatory

Table 4-3. Discretes Table (Continued)

Discrete I/O Pin Description Mandatory / Optional

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ModMan Reset ModMan J1-MP10C This discrete can be

used to reset the

ModMan (and, in turn

the entire AES)

• Ground = Mod-

Man/AES reset

• Open = Mod-

Man/AES normal

operation

• Signal type: Input

Optional

Data Link Available ModMan J1-MP13F The Data Link Available

ARINC 791 IO discrete

output shall be grounded

when user service is

available (data

connections are

available for use), and

open when user service

is not available.

Signal type: Output

(closure to ground)

Optional

System Available ModMan J1-MP13E The System Available

ARINC 791 IO discrete

output shall be open

when the AES system is

in critical fault mode, and

grounded at all other

times (including power

on sequence)

Signal type: Output

(closure to ground)

Optional

Front Panel Enable

Mode ModMan J1-B Pin 10F The front panel enable

mode discrete enables

the Modman front panel

connectors when

asserted.

• Ground = Enable

Front Panel

Connector

• Open = Disable

Front Panel

Connector.

Signal type: Input

Mandatory

Table 4-3. Discretes Table (Continued)

Discrete I/O Pin Description Mandatory / Optional

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NOTE: The following ARINC 791 discretes are not supported:

• Cell Transmit Enable (ModMan J1-MP11B)

• Remote Management Enable (ModMan J1-MP10A)

• Cooling System Available (ModMan J1-MP11F).

4.3 KANDU

Refer to Figure 4-25 and Figure 4-26 for outline and installation information. Refer to Figure 4-34 thru

Figure 4-37 for the applicable interconnect diagram.

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

The customer is responsible for the bulkhead connectors.

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

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

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

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

cabin.

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

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

length 32.8 feet (10 m)).

normal keying with 66 contacts as KANDU bulkhead control connector for KANDU

interwiring to the OAE-FMA. To be labeled as BI-control.

(d) It is recommended to use hermetically sealed MIL-DTL-38999 series III, insert 17-8,

normal keying with eight contacts as KANDU bulkhead power connector. To be labeled

as BI-power.

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

accordance with MIL-STD-348 for the routing of the TX-IF signals between the Modman

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

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

with MIL-STD-348 for the routing of the RX-IF signals between the Modman and KRFU.

The RX-IF interface to be labeled green.

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

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

(h) The following bulkhead connector design principles are recommended:

1The connector shall use a flange integrated into the connector shell with an

integrated seal and a washer and jam nut.

2The jam nut shall be capable of accepting locking wire.

3The integrated flange shall be mounted on the pressurized side of the aircraft, with

the jam nut on the exterior unpressurized side

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(i) It is recommended that the bulkhead interface be installed such that receptacle pins are

on the pressurized area and receptacle sockets are on the unpressurized side of the

aircraft.

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

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

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

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

Mates with D38999/26FD19SN for aircraft interface.

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

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

Mates with D38999/26FC4PN for power output.

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

Mates with D38999/26FG35SN for control interface.

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

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

length 32.8 feet (10 m)).

The bulkhead interface is as follows:

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

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

KANDU is installed in an unpressurized location inside aircraft.

(b) It is recommended to use hermetically sealed MIL-DTL-38999 series III, insert 19-35,

normal keying with 66 contacts as KANDU bulkhead control connector for KANDU

inter-wiring to KRFU and OAE-TMA if KANDU is installed in pressurized location inside

aircraft.

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

unpressurized location of aircraft.

(d) The following bulkhead connector design principles are recommended:

1The connector shall use a flange integrated into the connector shell with an

integrated seal and a washer and jam nut.

2The jam nut shall be capable of accepting locking wire.

3The integrated flange shall be mounted on the pressurized side of the aircraft, with

the jam nut on the exterior unpressurized side.

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

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

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

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

unit as follows:

• At least one of the two provided mechanical attachment points for electrical bonding

must be used for bonding the KANDU to the airframe. Make sure that the all mating

surfaces in the bonding path are free from contaminants such as paints or other

non-conductive elements.

• One 0.65 inch (16.5 mm) diameter circular and one 0.65 inch (16.5 mm) diameter

by 1.02 inch (25.9 mm)diameter elongated conductive area is provided around two

of the mounting holes of the equipment base plate.

• The KANDU includes a 0.59 inch (15 mm) diameter bonding measuring point on one

of the attachment tabs, close to the bonding element, but not on the bonding

element.

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

and KANDU A3J1-A.

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

is mounted must be less than 2.5 mΩ.

4.4 Installation Guidelines for the A791 Based AIM (If applicable)

The skirt fairing comes attached to the ARINC 791 based AIM plate. The installation sequence suggested

for mounting A791 based AIM is as follows:

• Install the A791 based AIM bonding straps.

• Install the A791 based AIM fittings to the aircraft fuselage.

• Mount the A791 based AIM.

• Install the A791 based AIM bonding straps to the A791 based AIM assembly.

Before putting the A791 based AIM assembly onto aircraft, install bonding straps to the aircraft fittings.

Refer to the airframe specific kits and assembly drawings for fastener details. Figure 4-1 shows a typical

ground strap connection.

Figure 4-1. Typical Ground Strap Arrangement for A791 Compliant Fittings

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The aircraft coordinate system orientation and fitting layout are shown in Figure 4-2.

Figure 4-2. Aircraft Coordinate System Orientation and Fitting Layout

(1) Position and install the A791 based AIM fittings onto aircraft fittings for fittings #1, #2, #5, #6,

and #7.

(2) Use the alignment tools to make sure that the fitting slip in X-direction is centered for fittings

#2, #6, and #7.

(3) Make sure that all the fittings are oriented vertically with the alignment tools to help when you

lower the A791 based AIM onto aircraft fittings and the installed fittings pass through

openings in A791 based AIM.

(4) Put the A791 based AIM assembly onto aircraft with an aircraft servicing hoist. Attach the

hoist to the A791 based AIM adapter plate at three locations labeled “Hoist Point”. Make sure

that the previously installed fittings on aircraft are still oriented vertically so that they will pass

through the openings in the adapter plate as AIM assembly is lowered onto aircraft. Refer to

Figure 4-3.

(5) Refer to the airframe specific kits and assembly for fastener specifications to install A791

complaint AIM fittings to aircraft fittings.

NOTE: Consult airframe manufacturer for choosing the correct torque values.

(6) Wet the fuselage skin with water on skirt seal contact area before you put the AIM assembly

on aircraft.

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Figure 4-3. AIM Assembly Placement on Aircraft

Figure 4-4. A791 Based AIM Assembly with FMA and KRFU Placement on Aircraft

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4.5 Installation Guidelines for the LAIM (If applicable)

NOTE: Please see Figure 4-33 LAIM outline and installation drawing, 90404861, for installation

details.

The installation sequence suggested for mounting the LAIM is as follows:

• Install the LAIM and radome skirt fairing bonding straps.

• Install the LAIM to the aircraft fuselage.

• Install the radome skirt fairing.

A. Install the LAIM and Radome Skirt Fairing Bonding Straps

(1) Before mounting the LAIM assembly onto the aircraft, install bonding straps to aircraft fittings.

There are eight bonding straps. Six of the bonding straps are installed between the bonding

points and the radome skirt fairing. Two bonding straps are installed between the bonding

points and the LAIM structure.

(2) Refer to the airframe specific kits and assembly drawings for fastener details.

B. Install the LAIM to the Aircraft Fuselage

(1) Put the LAIM assembly onto aircraft install location. Refer to Figure 4-5 for a generic LAIM

installation on airframe structure.

Figure 4-5. LAIM Assembly

(2) The LAIM gets attached to aircraft structure at six machined fitting locations. Forward four

fittings each have four attachment points, through the aircraft skin to the intercostals. The two

aft fittings each have four attachment points through aircraft skin to the stringer rivet hole

locations. Machined brackets will get attached to intercostals with fasteners.

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(3) Refer to the airframe specific kits and assembly for fastener specifications to install LAIM to

aircraft.

C. Install the Radome Skirt Fairing

(1) Put the radome skirt fairing assembly onto the aircraft. Refer to the airframe specific kits and

assembly for fastener specifications to install radome skirt fairing assembly to aircraft. Figure

4-6 shows the radome skirt assembly along with LAIM.

(2) The skirt fairing assembly is mounted to the aircraft with fasteners through the outer flange.

The skirt fairing does not have holes pre-drilled in the flange. The determination of location

and number of holes for the installation is the responsibility of the installer. Internal aircraft

structure to accept the skirt fairing fasteners is also the installers responsibility.

NOTE: Consult airframe manufacturer for choosing the correct torque values.

Figure 4-6. Radome Skirt Fairing and LAIM Assembly Position on Aircraft

4.6 KRFU

A. General

(1) There are no special tools, fixtures, or equipment required for the installation of the KRFU.

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

loss is from KRFU flange to antenna flange.

B. KRFU Thermal Pad Kit

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

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

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

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

(2) Kit Contents

(a) The thermal pad kit, PN SCD-90402388, contains the parts identified in Table 4-4.

(3) To install the thermal pad, refer to document Thermal Pad K, GXA KRFU Conduction

SCD-90402388. It can be found at Jetwave Customer Support .

NOTE: The configuration of the mounting feet shown in Figure 4-7 is representative only and may not be

the exact configuration for all KRFUs.

Figure 4-7. KRFU Thermal Pads

CAUTION: THE THERMAL PAD OPAQUE PROTECTIVE BACKING MUST BE

REMOVED FROM BOTH THERMAL PADS BEFORE USE IN THE FINAL

APPLICATION. FAILURE TO DO SO CAN RESULT IN PREMATURE

SHUTDOWN OF THE KRFU DUE TO OVERHEATING.

Table 4-4. Thermal Pad Kit Contents

PN Description Quantity

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

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

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

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

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

the white opaque backing on the thermal pads.

NOTE: Honeywell does not recommend applying the thermal pad to the KRFU if the

KRFU is to be shipped or stored. KRFU thermal pad installation should be done

shortly before actual KRFU installation.

C. KFRU - Waveguide/coax RF Losses

A waveguide is typically used for the KRFU to OAE RF TX connection. The waveguide run should

include a short length of seamless flexible waveguide along the routing to accommodate

tolerances. The waveguide must have mounting points to interface to the attachment points

provided.

NOTE: A coax cable can be used in the place of the waveguide as long as the maximum insertion

loss allowable for the KRFU to OAE RF TX connection is not exceeded.

The requirements for waveguide installation vary for each aircraft.

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

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

Refer to Figure 4-27, Figure 4-28, and Figure 4-29 for outline and installation information. Refer to

Figure 4-34 thru Figure 4-37 for the applicable interconnect diagram.

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

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

not exceed 2 dB.

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

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

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

D. KRFU - Thermal Conduction Path

The transmit operation of the AES is muted if the conduction-cooled KRFU is installed under the

radome and its temperature exceeds the temperature indicated in the outline and installation

drawings. Refer to Figure 4-27 thru Figure 4-29.

The conduction-cooled KRFU is dependent on heat conduction through its base to a thermally

conductive path in order to minimize the KRFU temperature. Conduction to the aircraft mounting

plate is dependent on proper installation of the KRFU thermal pad. The outline and installation

drawings in Figure 4-30 thru Figure 4-32 provide detailed thermal pad installation instructions.

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

until the temperature reduces to approximately 10° below the shutdown temperature. Refer to

Figure 7-3 for the temperature status report.

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

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

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

your hardware supplier for further details.

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

follows:

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

bonding.

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

other non-conductive elements.

• A circular or elongated conductive areas are provided around two or more of the

mounting holes of the equipment base plate.

• The KRFU includes bonding measuring points on the chassis bosses which are not used

for mounting feet.

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

unit is mounted, must be less than 2.5 mΩ.

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

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

E. KRFU/Waveguide Installation

(1) KRFU Installation Location with the FMA (if applicable)

(a) The KRFU install location is airframe specific.

(b) The KRFU can be installed inside the aircraft or external to the aircraft under the

radome. Honeywell recommends that the KRFU is installed external to the aircraft,

under the radome.

used. This variant achieves cooling through its base plate and must be installed with the

provided thermal pad to ensure a good thermal path between the KRFU and the AIM or

LAIM. Refer to KRFU, before you install the KRFU LRU.

(d) When the KRFU is installed inside the aircraft either the conduction cooled or forced air

cooled variant may be used.

(e) The KRFU must be installed close to fuselage mount antenna assembly so as to

minimize the waveguide/coax RF losses on the RF interconnect. Refer to Paragraph

4.6.C

4.7 Fuselage Mount Antenna (If applicable)

A. Introduction

The OAE FMA assembly will be installed on the top of the fuselage of the aircraft. For the

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

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than 1° off heading, pitch or roll with respect to principle axis of aircraft. Depending on the airframe,

as part of the OAE FMA, the LRUs and assemblies that follow will be installed outside aircraft:

•FMA LRU

• KRFU LRU (if installed outside aircraft)

• Radome assembly

• ARINC 791 based AIM or the LAIM

• Radome skirt fairing.

• ARINC 791 OAE installation kit (optional, for ARINC 791 installs only)

The exact install location of the ARINC 791 based AIM or LAIM and KRFU is airframe specific.

The KRFU can be installed on the inside or outside the fuselage of the aircraft. Honeywell

recommends to install the KRFU on the ARINC 791 based AIM or LAIM outside the fuselage of the

aircraft.

The radome, skirt fairing, and FMA/KRFU to aircraft interface brackets are airframe specific and

said details are not covered by this manual.

NOTE: The ARINC 791 AIM is intended to be a common design solution across multiple aircraft

platforms. The only variable is the skirt and seal that change with the aircraft specific

fuselage contour.

The non ARINC 791 design has a common LAIM plate that is intended to be used across

all platforms. The variables in this design solution are the ring fairing that the radome

attaches to and the LAIM to fuselage interface brackets. The ring fairing is a design and

shape specific to the fuselage contour at the aircrafts installation location, as are the LAIM

to fuselage interface brackets.

Refer to the FMA outline and installation drawing in Figure 4-31, the KRFU outline and

installation drawings in Figure 4-27, Figure 4-28, and Figure 4-29, and the radome outline

and installation drawing in Figure 4-32. Depending on the aircraft configuration, refer to the

interconnect diagrams in Figure 4-35 for the KRFU installed inside the fuselage, and Figure

4-36 or Figure 4-37 for external KRFU.

Refer to Table 4-5 for special tools, fixtures, and equipment for the FMA installation.

B. The FMA Installation General

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

procedures.

Table 4-5. Special Tools for FMA Installation

Number Description Source

NA Hoist system Commercially available

NA Torque wrench Commercially available

066101 5/16” crowsfoot

spanner/wrench Mountz (CAGE: 0HL78)

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C. Advisories

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

microwave emissions in the band between 29.0 and 30.0 GHz.

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

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

follow.

WARNING: THIS EQUIPMENT RADIATES HIGH FREQUENCY RADIATION AND POSES A

RADIATION HAZARD. CONSIDERING THE WORST CASE CONDITION OF 100

PERCENT REFLECTION FOR THE FUSELAGE MOUNT ANTENNA, HONEYWELL

DEEMS IT NECESSARY TO ASSURE OEM FUSELAGE ATTENUATION EXCEEDS

21.03 DB FOR FUSELAGE MOUNTED ANTENNAS SYSTEM INSTALLATION. THIS IS

THE MINIMUM ATTENUATION REQUIRED FROM THE AIRCRAFT FUSELAGE TO

ATTENUATE THE KA-BAND RADIATION TO MEET A SAFE HUMAN EXPOSURE OF 1

MW/CM2 INSIDE THE AIRCRAFT.

WARNING: SERVICE TECHNICIANS AND OPERATORS MUST EXERCISE CARE TO KEEP

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

INSTALLATION VERIFICATION PROCEDURES. DO NOT APPROACH WITHIN 66.6

FEET (20.3 METERS) OF THE FUSELAGE MOUNTED ANTENNA ASSEMBLY DURING

RADIO FREQUENCY TRANSMISSION.

WARNING: DURING ANTENNA OPERATION (TRANSMISSION), MAKE SURE THAT MINIMIZE

THE EXPOSURE OF ALL PERSONNEL TO ANY REFLECTED, SCATTERED, OR

DIRECT BEAMS.

WARNING: SERVICE TECHNICIANS MUST OBEY STANDARD SAFETY PRECAUTIONS, SUCH

AS WEARING SAFETY GLASSES, TO PREVENT PERSONAL INJURY WHILE

INSTALLING OR PERFORMING SERVICE ON THIS UNIT.

CAUTION: THE FUSELAGE MOUNT OAE ASSEMBLY IS ELECTROSTATIC-SENSITIVE.

STANDARD ELECTROSTATIC-SENSITIVE HANDLING PROCEDURES MUST BE

OBSERVED.

D. Unpacking and Inspection

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

unpack and inspect the equipment do as follows:

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

(2) Make sure that all components of the fuselage mount OAE subsystem as indicated on the

parts list/bill of materials are included.

(3) Visually examine the units for any shipping damage.

NOTE: Refer to Section 4.10 Inspection of Waveguide.

E. FMA Installation Kits

FMA installation kits are available in ARINC 791 Style configurations and non ARINC 791 style

configurations. See Table 4-6 and Table 4-7 for details on available installation kits for each

configuration.

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For the ARINC 791 configuration; the seven aircraft side fittings, internal structural modifications,

internal wiring, and bulkhead connectors are the responsibility of the installer.

For the non ARINC 791 configuration; the LAIM to fuselage interface brackets, skirt fairing attach

points, internal structural modifications, internal wiring, and external OAE power and control and IF

coax interconnects and routing hardware, are the responsibility of the installer.

F. Airframe Structural Modifications

For the installation of OAE-FMA, structural modifications to the airframe may be required in the

region where the OAE-FMA is to be mounted to accommodate the additional mass of the antenna

assembly and resulting aerodynamic loads.

The aerodynamic loads are dependent on the aircraft type as well as the installation location of the

OAE-FMA on the aircraft, and are therefore installation specific.

Bird strike and rapid decompression need to be considered for analysis and structural

substantiation.

The appropriately qualified personnel should derive the loads and do a structural analysis to make

sure of the suitability of the modifications.

The installer is responsible for all structural modifications to the aircraft.

G. Mounting Guidelines

This section describes the mounting guidelines for fuselage mount OAE.

Physical Placement:

The aircraft fuselage mount OAE is installed on top of the fuselage for clear satellite

communications per ARINC791 P1-2.

Figure 4-8 shows a typical installation location for the fuselage mount OAE on an aircraft.

Table 4-6. Special Tools for FMA Installation

Number Description Source

NA Hoist system Commercially available

NA Torque wrench Commercially available

066101 5/16” crowsfoot spanner/wrench Mountz (CAGE: 0HL78)

Table 4-7. Non ARINC 791 Style Installation Kit

Radome Package 90400016-YYY RF component Kit 90404243-01

Radome Waveguide

Radome hardware kit Rx coax

LAIM kit WR42 to coax adapter

Skirt fairing O-rings

Waveguide and adapter screws

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The FMA may be installed anywhere on the top of the aircraft, Honeywell recommends not installing

the FMA at the mid fuselage station near the wing or slightly aft of the wing due to higher aero loads.

Figure 4-8. FMA Install Location

The fuselage antenna assembly and KRFU (if installed outside the aircraft) will be mounted on the

antenna interface mount and it supplies a means to secure all equipment and wiring mounted on it.

Depending on the airframe, the AIM/LAIM is installed to provide a firm flat base for installation of

the FMA and KRFU. These are detailed in the next sections. For customers who want to build their

own AIM, please reference the third-party OAE specification, SP-90405087.

H. FMA Bonding

The bonding straps are installed before proceeding with installation of FMA assembly on the A791

based AIM or LAIM.

The FMA assembly and KRFU must be bonded to the airframe.

Consult the airframe manufacturer for the correct torque values.

I. FMA Installation Procedure

Following installation activities are detailed in subsequent sections:

• Installation of the FMA.

• Connecting the waveguide, RF coax interface to the FMA.

• Installation of KRFU and bonding straps.

• Installation of waveguide and coax between FMA and KRFU.

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• Connecting Bulkhead Interface, KRFU power and control interfaces.

• Position and installation of radome.

(1) Installation of the FMA Assembly

(a) Align the FMA assembly above adapter plate with an aircraft service hoist. Attach hoist

to the FMA lifting fixture at two locations on each side of fixture. Refer to Figure 4-9.

Figure 4-9. FMA Assembly

(b) Put the FMA onto the FMA mounting holes with alignment pins and make sure that the

waveguide flange is pointed to the rear of the AIM or LAIM. Make sure that the pigtails

do not interfere to avoid damage.

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Figure 4-10. FMA Assembly Lifting Fixture Removal

(d) The orientation of the FMA assembly is defined with respect to the principal axes of the

aircraft.

(e) Attach the FMA to the AIM with screws and flat washers. The AIM is provisioned with

captive nuts. Refer to the airframe specific kits and assembly for fastener specifications

and required torque. Mounting holes in base are accessed from the top between the

antenna and turntable by rotating the assembly in azimuth.

(f) Remove protective cap from disconnect plug on harness.

1Visually inspect connector and make sure that there are no debris in cavities.

2Visually inspect the center conductor and verify that it is still straight and the finish

is intact.

(2) FMA Bonding Requirements

(a) Install one end of bonding straps to AIM at labeled bonding points with screw and

washers.

(b) Install the other end of bonding straps to bonding points on the FMA base. Refer to the

airframe specific kits and assembly for fastener specifications and required torque.

Refer to Figure 4-1 for the FMA ground strap connection.

(3) Waveguide and RF Coax Interconnection to FMA Assembly

(a) A common RF component kit exists for each installation type. The ARINC 791 style

installation uses PN 90404243-02. The non ARINC 791 style installation uses PN

90404243-01. Installation drawings specific to each kit are available.

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Remove protective cap on FMA J4 (2.92 mm female coax) and FMA J3. Connect K-type disconnect

plug to K-type disconnect receptacle J4 on the FMA and torque to 7 in-lb (0.79 Nm) or as specified

by the cable manufacturer. Connect the WR34 waveguide assembly to the FMA receptacle J3.

(4) Installation of the Waveguide and Coax Interconnect between the FMA and Externally

Mounted KRFU

(a) Loosely attach the waveguide and coax support brackets to the AIM or LAIM. The

flexible wave guide and coax cable assembly kit and its routing are aircraft specific.

(b) Remove the protective covers from the FMA J3 RF TX. Visually examine connector

ends and make sure that there is no debris in the cavities.

sealing gasket. Hand tighten the fasteners.

(d) Loosely attach the waveguide and coax support brackets to the AIM or LAIM.

(e) Loosely connect the WR34 to WR28 waveguide adapter to the KRFU with sealing

gasket. Apply torque to the waveguide adapter flange for all fasteners as recommended.

(f) Loosely connect the waveguide assembly to the KRFU with a sealing gasket. Make sure

the O-ring is seated correctly in the KRFU TX waveguide flange when mating the

waveguide as there is no retaining mechanism. If maintenance is conducted which

requires uncoupling the waveguide from the KRFU TX port, inspect the flange for dirt or

debris and O-ring for damage or if it is misshapen. If required, replace the O-ring and

clean the waveguide flange interfaces.

(g) Apply torque to the KRFU waveguide flange for all fasteners as recommended.

(h) Firmly attach waveguide support brackets to adapter plate.

The minimum allowable bend radius to the center line for flexible waveguide is 1 inch (25.4 mm) in

H plane (bend along the long axis of the waveguide) and 0.5 inch (12.7 mm) in E plane (bend along

the short axis of the waveguide). The minimum allowable bend radius for the coax cable is 0.25 inch

(6.35 mm). Refer to Figure 4-11.

Figure 4-11. View of H Plane and E Plane Bends

(5) Connecting the FMA Interface, KRFU Power, and Control Interfaces

The control signals for the KRFU are supplied from the KANDU and are connected to KRFU

J2 receptacle.

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The 115 VAC power supply for the KRFU is supplied from the aircraft power and is connected

to KRFU J1 receptacle.

The IF TX and IF RX signals to KRFU are supplied from the Modman. These signals are

routed through the bulkhead interface. Refer to the appropriate FMA interconnection diagram

Figure 4-35, Figure 4-36 and Figure 4-37 for details.

(a) Remove the protective covers from the FMA P2 and KANDU J2 receptacles. Visually

examine the connectors and make sure that the pins are straight and undamaged.

1Clean the connectors with the contact cleaner and connect the cable assembly for

fuselage mount from the KANDU J2 receptacle to the FMA P1, P2, and P3

receptacles.

2Make sure that the over braid of the cable assembly is terminated to connectors at

both the FMA and KANDU ends.

(b) Remove the protective covers from the KRFU J2 and KANDU J3 receptacles. Visually

examine the connectors and make sure that the pins are straight and undamaged.

1Clean the connectors with the contact cleaner and connect the cable assembly for

fuselage mount from the KANDU J3 receptacle to the KRFU J2 receptacle.

2Make sure that the over braid of the cable assembly is terminated to connectors at

both the KRFU and KANDU ends.

examine the connector ends and ensure there is no debris in central connector cavity.

1Clean the connectors with the contact cleaner before connecting.

2Make sure that the TX-IF coax cable is banded blue and RX-IF coax cable is

banded green at connector ends.

3Make sure that the over braid of the cable assembly is terminated to connectors at

both the KRFU and bulkhead interface feed through ends.

4The over braid can be terminated to the connector shield/housing or directly to the

housing.

(d) Make sure that all the cable assembly routing are firmly held with wire clamps in

accordance with the airframe specific wiring diagram and there are no obstruction to the

free movement of the FMA. Refer to Figure 4-4 for the A791 based AIM and Figure 4-12

for the LAIM.

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Figure 4-12. LAIM Assembly with FMA and KRFU Placement on Aircraft

On completion of the LRU interconnection and applying power to the FMA, the FMA will stay in its

current position until it is told to move by the KANDU.

(6) KRFU Installation Location with the TMA (if applicable)

The KRFU install location at the top of aircraft tail empennage is airframe specific.

The KRFU can be installed either forward or aft of the tail mount antenna assembly. The

KRFU can also be installed in any orientation as long as space permits, interconnection

routing is feasible, and adequate thermal conduction path is maintained. Antenna blockage

analysis/review should be carried out to ensure that acceptable system performance is

maintained.

The conduction cooled KRFU variant requires mounting of the Honeywell recommended

thermal pad to aircraft structure capable of handling KRFU thermal loads. Refer to

Paragraphs 4.6.A, 4.6.B and 4.6.C.

The forced air cooled KRFU variant may be used as an alternate installation option. A duct

and in line fan may be used to drawn hot air from the KRFU integrated heat sink and duct it

down to lower sections of the tail/empennage structure.

The KRFU must be installed close to the TMA assembly so as to minimize the

waveguide/coax RF losses on the RF interconnect.

KRFU

FUSELAGE

ANTENNA

MOUNT

LOCAL

ANTENNA

INTERFACE

MOUNT

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It is recommended to use flexible waveguide/coax RF interface and with interconnect losses

not exceeding 0.6 dB on the transmit path and stay within 0.5 to 2 dB on the receive path

between the KRFU and the TMA assembly.

The typical KRFU LRU and TMA assembly (swept volume model of antenna shown)

interconnect arrangement is shown in Figure 4-13.

Figure 4-13. KRFU and TMA Interconnect Arrangement

(a) TMA Bonding Requirements

The ground straps are installed before proceeding with installation of the TMA assembly

on the antenna adapter plate or on the tail empennage airframe structure. The TMA

assembly and KRFU must be bonded to the airframe.

Consult the airframe manufacturer for the correct torque values.

(b) OAE TMA Installation Procedure

Before doing any installation procedures, the installer must read and be aware of the

safety advisories listed in this manual. Only authorized technical personnel who are

trained in general aviation workmanship and have a basic understanding of satellite

communication systems should proceed with the following installation procedure.

1Connecting the Tx waveguide and RF Rx coax interfaces to the TMA per Step (c).

2Positioning and installation of the TMA assembly onto tail tip antenna slot/antenna

interface mount; installation of bonding straps per Step (d).

3Installation of the KRFU and bonding straps per Step (e).

4Installation of the waveguide and coax between the TMA and KRFU per Step (f).

5Connecting the TMA interface, KRFU power, and control interfaces per Step (g).

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6Position and installation of the radome per Step (h).

The waveguide and RF coax interconnect designs are aircraft specific. Consult aircraft

specific SDIM for detailed installation instructions.

NOTE: The waveguide and RF coax shall be connected to the TMA prior to installing

the TMA to the aircraft.

1Remove the protective covers from the Rx coax, waveguide, TMA J4 RF RX port,

and TMA J3 RF TX port. Visually inspect waveguide and connector ends and make

sure that there is no debris in the cavities.

2Connect the Rx coax cable connector to the TMA J4 port. Torque to 8 to 9 lbf in

(0.904 to 1.017 Nm). Route the coax cable under the provided strain relief bracket

as required. In some cases the coax strain relief bracket is a stand alone part and

in others it is integral to the waveguide secondary flange.

3Connect the WR28 flexible waveguide to TMA J3 waveguide flange with the correct

o-ring (Honeywell PN MS29513-013). Torque Honeywell recommended fasteners

(Honeywell part number 90403559) per the aircraft specific Honeywell installation

drawing.

4Attach the waveguide secondary flange to the bottom of the TMA using the

Honeywell recommended fasteners (PN MS51957-27 screw, with NAS620C6 flat

washer). Torque per the aircraft specific Honeywell installation drawing. Ensure that

the coax cable is not pinched when securing the waveguide secondary flange (if it

has integrated coax strain relief feature).

(d) Installation of the TMA Assembly

1Carefully position the TMA assembly to the mounting bracket/tail structure by

aligning the TMA mounting clearance holes with the threaded attachments on the

aircraft mounting side. As an option, the TMA mounting bracket/tail structure may

be designed to integrate alignment pins that will mate with the alignment hole and

slot on the base of the TMA (see outline and installation drawing for details).

For the JetWave™ system to correctly point the antenna, the installation offsets

should not exceed more than 1° off heading, pitch or roll with respect to principle

axis of aircraft.

2Install and hand tighten #10 fasteners at the five mounting point locations. Fastener

selection and fastener installation torque requirements are aircraft/installation

specific and are the responsibility of the installer.

3Connect the bonding strap to the TMA assembly. Refer to Figure 4-14 for the

bonding strap location. Add bond joint sealant as required by installers specific

standard operating procedures.

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Figure 4-14. TMA RF TX J3 and RF RX J4 Interface Connector and Bonding Strap Locations

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(e) KRFU Installation

1Make sure that the thermal pads are attached to the bottom of the KRFU. Refer to

Section 4.6. KRFU.

2Before proceeding with the KRFU installation, connect the WR42 waveguide to 2.92

mm coaxial connector adapter to KRFU J4 RF RX.

aThe adapter allows connection between the Rx WR-42 waveguide port on the

KRFU and a 2.92mm coaxial connector.

bThe WR42 waveguide side of the adapter has a mechanical flange interface

with four 0.117 inch (2.97 mm) diameter through holes for mating with KRFU J4.

cThe WR42 waveguide to 2.92 mm coaxial connector adapter is shown in Figure

4-15.

Figure 4-15. WR42 Waveguide to 2.92 mm Coaxial Connector Adapter

3Remove the protective covers from the KRFU J4 and WR42 waveguide to 2.92 mm

coaxial connector. Visually inspect connector ends and make sure that there is no

debris in the cavities.

4Install an MS29513-016 O-ring and mount the adapter onto KRFU J4 with four

screws (recommended screw is Honeywell part number 90403559). Make sure the

O-ring is seated correctly in the KRFU TX waveguide flange when mating the

waveguide as there is no retaining mechanism. If maintenance is conducted which

requires uncoupling the waveguide from the KRFU TX port, inspect the flange for

dirt or debris and O-ring for damage or if it is misshapen. If required, replace the

O-ring and clean the waveguide flange interfaces. Torque the four screws in an X

pattern. Torque per Honeywell provided aircraft specific installation instructions. Do

not use power tools to torque the screws.

5 Attach the KRFU assembly to the KRFU interface mount with fasteners and tighten.

Selection of KRFU attachment fasteners are the responsibility of the installer

Minimum torque recommended to compress the thermal pad is 22 in-lb (2.5 Nm).

Minimum torque shall be validated by the installer for the attachment screws

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selected. Apply torque to the fasteners in defined sequence for firmly mounting to

the antenna interface mount or the tail structure of the aircraft. Do not use power

tools to torque connection.

6Install one end of the ground straps to the antenna interface mount or the tail

structure plate at labeled ground points with screw and washers. Install bond

connection joint sealant as required by installers standard procedures.

7Install the other end of the ground straps to grounding points on the KRFU. The

KRFU bonding strap arrangement is shown in Figure 4-16. Install bond connection

joint sealant as required by installers standard procedures.

Figure 4-16. KRFU Bonding Strap Arrangement

(f) Installation of the Waveguide and Coaxial Cable Interconnect Between the TMA and

KRFU

1Support of the length of waveguide and coax cable between TMA and KRFU is

aircraft specific. See aircraft specific installation procedures for details. Any support

bracket connections would typically be done at this stage in the install.

2Attach Tx waveguide flange to KRFU J3 port using recommended screws

(Honeywell part number 90403559). Torque screws in X pattern per torque value in

aircraft specific installation drawing. Prior to assembly, place o-ring PN

MS29513-013 between the flange faces in waveguide o-ring groove

3Complete any final installation requirements on waveguide and coax supports.

The minimum allowable bend radius to the center line for flexible waveguide is 1 inch

(25.4 mm) in H plane (bend along the long axis of the waveguide) and 0.5 inch (12.7

Draft as of 31 May 2017

EMS Technologies Canada JETWAVE2 Jetwave User Manual 23 15 29R004

EMS Technologies Canada, Ltd. Jetwave 23 15 29R004

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