EMS Technologies Canada JETWAVE2 Jetwave User Manual 23 15 29R004

EMS Technologies Canada, Ltd. Jetwave 23 15 29R004

User Manual_Part 1

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Document Description	User Manual_Part 1
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Date Submitted	2017-08-17 00:00:00
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Creation Date	2017-05-22 15:05:47
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Document Title	23-15-29R004.book
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Draft as of 31 May 2017
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
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
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
23-15-29
Publication Number D201401000049, Revision 4
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page T-1
Initial 16 Jan 2015
Revised 3 Mar 2017
Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
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23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page T-2
3 Mar 2017
Draft as of 31 May 2017
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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23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page T-3
3 Mar 2017
Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
PERFORMANCE, DEALING, USAGE, OR TRADE, WHICH ARE HEREBY EXPRESSLY DISCLAIMED, OR (ii)
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WARNING: BEFORE THE MATERIALS CALLED OUT IN THIS PUBLICATION ARE USED, KNOW THE
HANDLING, STORAGE AND DISPOSAL PRECAUTIONS RECOMMENDED BY THE MANUFACTURER OR
SUPPLIER. FAILURE TO OBEY THE MANUFACTURERS’ OR SUPPLIERS’ RECOMMENDATIONS CAN
RESULT IN PERSONAL INJURY OR DISEASE.
This publication describes physical and chemical processes which can make it necessary to use chemicals,
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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
INSTRUCTIONS AND/OR HONEYWELL’S FAA/SFAR 36 REPAIR AUTHORIZATION. NEITHER DOES
HONEYWELL ASSUME RESPONSIBILITY FOR SPECIAL TOOLS AND TEST EQUIPMENT FABRICATED BY
COMPANIES OTHER THAN HONEYWELL.
WARNING: INCORRECTLY REPAIRED COMPONENTS CAN AFFECT AIRWORTHINESS OR DECREASE
THE LIFE OF THE COMPONENTS. INCORRECTLY FABRICATED SPECIAL TOOLING OR TEST
EQUIPMENT CAN RESULT IN DAMAGE TO THE PRODUCT COMPONENTS OR GIVE UNSATISFACTORY
RESULTS.
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page T-4
3 Mar 2017
Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Copyright - Notice
Copyright 2015, 2017 Honeywell International Inc. All rights reserved.
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
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page T-5
3 Mar 2017
Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Blank Page
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page T-6
3 Mar 2017
Draft as of 31 May 2017
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.
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
Revision History
Table TI-2 shows the revision history of this SDIM.
Table TI-2. Revision History
Revision
Revision Date
16 Jan 2015
16 Sep 2015
6 Nov 2015
17 Aug 2016
3 Mar 2017
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.
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page TI-1
3 Mar 2017
Draft as of 31 May 2017
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
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page TI-2
3 Mar 2017
Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table of Highlights (Continued)
Page
Description of Change
Effectivity
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
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page TI-3
3 Mar 2017
Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table of Highlights (Continued)
Page
Description of Change
Effectivity
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).
All
Paragraph 4.2, revised the title to add the word “Internal”.
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 All
Mode, Discrete Signal Ground (Modman MP12F) and Discrete
Signal Ground (KANDU J1-B).
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
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page TI-4
3 Mar 2017
Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table of Highlights (Continued)
Page
Description of Change
Effectivity
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
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page TI-5
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table of Highlights (Continued)
Page
Description of Change
Effectivity
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”.
All
Added a new bullet for GoGo for distribution partners.
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page TI-6
3 Mar 2017
Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table of Highlights (Continued)
Page
Description of Change
Effectivity
6-2
Paragraph 6.1, revised “maximum spot beam capacity” to
“defined Maximum Information Rate” and “or Minimum” as “for
95% of the time”.
All
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"
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”.
All
Updated Step 6.3C(1) and added Step (2).
Replaced Figure 6-8 with the latest version.
Added Note that follows Step 6.3D.
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”.
All
Paragraph 6.4, added additional information for full
Optimization of Jetwave system.
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page TI-7
3 Mar 2017
Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table of Highlights (Continued)
Page
Description of Change
Effectivity
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
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page TI-8
3 Mar 2017
Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table of Highlights (Continued)
Page
Description of Change
Effectivity
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.
All
Revised Repair Action for L3 Codes 0x 0007 thru 0x 000A and
L2 code Software runtime (FE) completely.
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
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page TI-9
3 Mar 2017
Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table of Highlights (Continued)
Page
Description of Change
Effectivity
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).
All
Added new L3 codes for L2 codes GNSS sensor status word
(80) and IRS discrete word (81).
7-96
Tale 7-6, added 0x 0002 to L3 code and description.
All
Step 7.3 (1)(b)1, revised to add additional step to validate
communication cabling.
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
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page TI-10
3 Mar 2017
Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table of Highlights (Continued)
Page
Description of Change
Effectivity
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.
All
Paragraph 1.B, in the table, revised the item description for the
parameter “Electrical wiring - APM to Modman”.
C-11
Revised the figure reference as Figures 4-21 and 4-22.
All
Paragraph 1.C, in the table, revised the item description for the
parameter “Electrical wiring - APM to Modman”.
C1 thru C6
Paragraph 1, rearranged and renumbered the tables in
Appendix E as follows:
All
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.
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page TI-11
3 Mar 2017
Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Blank Page
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page TI-12
3 Mar 2017
Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
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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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Blank Page
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Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
RECORD OF TEMPORARY REVISIONS
Instructions on each page of a temporary revision tell you where to put the pages in your manual. Remove
temporary revision pages only when discard instructions are given. For each temporary revision, put the
applicable data in the record columns on this page.
Definition of Status column: TR may be active, incorporated, or deleted. “Active” is entered by the holder of
manual. “Incorporated” means a TR has been incorporated into the manual and includes the revision number
of the manual when the TR was incorporated. “Deleted” means a TR has been replaced by another TR, a TR
number will not be issued, or a TR has been deleted.
Temporary
Revision
Number
Status
Page
Number
Issue
Date
Date Put in
Manual
By
Date
Removed
From Manual
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By
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3 Mar 2017
Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Blank Page
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Page RTR-2
3 Mar 2017
Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
SERVICE BULLETIN LIST
Service Bulletin
Number
Manual Rev.
Number
Subject
Manual Rev.
Date
JETWAVE-23-0001, COMMUNICATIONS - JETWAVE™ SYSTEM Rev. 0
Software Upgrade for the GXA System Line
Replaceable Units (LRU)
17 Aug 2016
JETWAVE-23-0002, COMMUNICATIONS - JETWAVE™ SYSTEM Rev 3
Software Release for the GXA System Line
Replaceable Units (LRU)
3 Mar 2017
JETWAVE-23-0003, COMMUNICATIONS - JETWAVE™ SYSTEM Rev 0
Software Release for the GXA System Line
Replaceable Units (LRU)
3 Mar 2017
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 1
3 Mar 2017
Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Blank Page
23-15-29
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3 Mar 2017
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Subheading and Page
Date
Title
T-1
T-2
T-3
T-4
T-5
T-6
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
Transmittal Information
TI-1
TI-2
TI-3
TI-4
TI-5
TI-6
TI-7
TI-8
TI-9
T-10
T-11
T-12
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
Record of Revisions
3 Mar 2017
3 Mar 2017
Record of Temporary Revisions
RTR-1
RTR-2
3 Mar 2017
3 Mar 2017
Service Bulletin List
List of Effective Pages
LEP-1
LEP-2
LEP-3
LEP-4
LEP-5
LEP-6
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
Table of Contents
TC-1
3 Mar 2017
Subheading and Page
Date
TC-2
TC-3
TC-4
TC-5
TC-6
TC-7
TC-8
TC-9
TC-10
Introduction
1-1
1-2
1-3
1-4
1-5
1-6
1-7
1-8
Description
2-1
2-2
2-3
2-4
2-5
2-6
2-7
2-8
2-9
2-10
2-11
2-12
2-13
2-14
System Pre-configuration
3-1
3-2
3-3
3-4
Installation
4-1
4-2
4-3
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
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3 Mar 2017
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3 Mar 2017
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3 Mar 2017
3 Mar 2017
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indicates a changed or added page.
indicates a foldout page.
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Page LEP-1
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Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Subheading and Page
Date
4-4
4-5
4-6
4-7
4-8
4-9
4-10
4-11
4-12
4-13
4-14
4-15
4-16
4-17
4-18
4-19
4-20
4-21
4-22
4-23
4-24
4-25
4-26
4-27
4-28
4-29
4-30
4-31
4-32
4-33
4-34
4-35
4-36
4-37
4-38
4-39
4-40
4-41
4-42
4-43
4-44
4-45
4-46
4-51
4-52
4-53
4-54
4-55
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
Subheading and Page
4-56
4-57
4-58
4-59
4-60
4-61
4-62
4-63
4-64
4-65
4-66
4-67
4-68
4-69
4-70
4-71
4-72
4-73
4-74
4-75
4-76
4-77
4-78
4-79
4-80
4-81
4-82
4-83
4-84
4-85
4-86
4-87
4-88
4-89
4-90
4-91
4-92
4-93
4-94
4-95
4-96
4-97
4-98
4-99
4-100
4-101
4-102
4-103
Date
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
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indicates a foldout page.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Subheading and Page
Date
4-104
4-105
4-106
4-107
4-108
4-109
4-110
4-111
4-112
4-113
4-114
4-115
4-116
4-117
4-118
4-119
4-120
4-121
4-122
4-123
4-124
4-125
4-126
4-127
4-128
4-129
4-130
4-131
4-132
4-133
4-134
4-135
4-136
4-137
4-138
4-139
4-140
4-141
4-142
4-143
4-144
Software Configuration
5-1
5-2
5-3
5-4
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
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3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
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3 Mar 2017
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3 Mar 2017
3 Mar 2017
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Subheading and Page
5-5
5-6
5-7
5-8
5-9
5-10
5-11
5-12
5-13
5-14
5-15
5-16
5-17
5-18
5-19
5-20
Date
System Commissioning
6-1
6-2
6-3
6-4
6-5
6-6
6-7
6-8
6-9
6-10
6-11
6-12
6-13
6-14
6-15
6-16
6-17
6-18
6-19
6-20
Troubleshooting
7-1
7-2
7-3
7-4
7-5
7-6
7-7
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
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Page LEP-3
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Subheading and Page
Date
7-8
7-9
7-10
7-11
7-12
7-13
7-14
7-15
7-16
7-17
7-18
7-19
7-20
7-21
7-22
7-23
7-24
7-25
7-26
7-27
7-28
7-29
7-30
7-31
7-32
7-33
7-34
7-35
7-36
7-37
7-38
7-39
7-40
7-41
7-42
7-43
7-44
7-45
7-46
7-47
7-48
7-49
7-50
7-51
7-52
7-53
7-54
7-55
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
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Subheading and Page
7-56
7-57
7-58
7-59
7-60
7-61
7-62
7-63
7-64
7-65
7-66
7-67
7-68
7-69
7-70
7-71
7-72
7-73
7-74
7-75
7-76
7-77
7-78
7-79
7-80
7-81
7-82
7-83
7-84
7-85
7-86
7-87
7-88
7-89
7-90
7-91
7-92
7-93
7-94
7-95
7-96
7-97
7-98
Date
3 Mar 2017
3 Mar 2017
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3 Mar 2017
3 Mar 2017
Maintenance and Repair
8-1
8-2
8-3
indicates a changed or added page.
indicates a foldout page.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Subheading and Page
Date
8-4
8-5
8-6
Appendix A: Specifications
A-1
A-2
A-3
A-4
A-5
A-6
A-7
A-8
A-9
A-10
A-11
A-12
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
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
Subheading and Page
C-2
C-3
C-4
C-5
C-6
C-7
C-8
C-9
C-10
C-11
C-12
C-13
C-14
Date
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
3 Mar 2017
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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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
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.
B.
1.6
Honeywell Aerospace Online Technical Publications Website ................................................ 1-3
Honeywell Aerospace Contact Team ....................................................................................... 1-3
References ........................................................................................................................................ 1-3
A.
B.
Honeywell/Vendor Publications ............................................................................................... 1-3
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.
B.
2.2
JetWave™ System LRUs ........................................................................................................ 2-2
JetWave™ System LRU Leading Particulars .......................................................................... 2-3
Honeywell JetWave™ System Architecture ...................................................................................... 2-8
A.
B.
C.
D.
E.
Outside Antenna Equipment .................................................................................................... 2-9
KRFU ..................................................................................................................................... 2-10
KANDU .................................................................................................................................. 2-11
Modman ................................................................................................................................. 2-11
APM ....................................................................................................................................... 2-11
2.3
Honeywell Implementation .............................................................................................................. 2-12
2.4
JetWave™ System Modes of Operation ......................................................................................... 2-12
A.
B.
C.
D.
E.
F.
Power On Mode ..................................................................................................................... 2-12
System Initialization Mode ..................................................................................................... 2-13
Normal Operating Mode......................................................................................................... 2-13
Critical Fault Mode ................................................................................................................. 2-13
Data Load Mode .................................................................................................................... 2-13
Commanded Mode ................................................................................................................ 2-14
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
2.5
About Inmarsat Services ................................................................................................................. 2-14
SECTION 3 - SYSTEM PRE-CONFIGURATION
3.1
AES Configuration Data .................................................................................................................... 3-1
A.
B.
C.
AES System Configurations .................................................................................................... 3-1
Regulatory Log Configuration Parameters .............................................................................. 3-3
Aircraft Service Configuration .................................................................................................. 3-3
SECTION 4 - INSTALLATION
4.1
Overview ............................................................................................................................................ 4-1
A.
4.2
Installation Procedure Overview for the JetWave™ System .................................................... 4-1
JetWave™ System LRU Installation .................................................................................................. 4-2
A.
B.
C.
Modman.................................................................................................................................... 4-2
APM .......................................................................................................................................... 4-4
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.
B.
C.
4.6
KRFU ............................................................................................................................................... 4-14
A.
B.
C.
D.
E.
4.7
General ................................................................................................................................... 4-14
KRFU Thermal Pad Kit ........................................................................................................... 4-15
KFRU - Waveguide/coax RF Losses......................................................................... 4-16
KRFU - Thermal Conduction Path .......................................................................................... 4-16
KRFU/Waveguide Installation................................................................................................. 4-17
Fuselage Mount Antenna (If applicable) .......................................................................................... 4-17
A.
B.
C.
D.
E.
F.
G.
H.
I.
4.8
Install the LAIM and Radome Skirt Fairing Bonding Straps.................................................... 4-13
Install the LAIM to the Aircraft Fuselage................................................................................. 4-13
Install the Radome Skirt Fairing.............................................................................................. 4-14
Introduction ............................................................................................................................. 4-17
The FMA Installation General ................................................................................................. 4-18
Advisories ............................................................................................................................... 4-19
Unpacking and Inspection ...................................................................................................... 4-19
FMA Installation Kits ............................................................................................................... 4-19
Airframe Structural Modifications............................................................................................ 4-20
Mounting Guidelines ............................................................................................................... 4-20
FMA Bonding .......................................................................................................................... 4-21
FMA Installation Procedure .................................................................................................... 4-21
Tail Mount Antenna (If applicable) ................................................................................................... 4-34
A.
B.
C.
D.
Introduction ............................................................................................................................. 4-34
TMA Installation General ........................................................................................................ 4-35
Advisories ............................................................................................................................... 4-35
TMA Unpacking and Inspection.............................................................................................. 4-36
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
E.
F.
G.
H.
I.
J.
K.
L.
4.9
TMA Installation Kit Details ..................................................................................................... 4-36
TMA Airframe Structural Modifications ................................................................................... 4-37
TMA Mounting Guidelines....................................................................................................... 4-37
TMA Physical Placement ........................................................................................................ 4-37
TMA Interface Mount Brackets (if required) ............................................................................ 4-37
TMA Radome and Radome Fairing ........................................................................................ 4-38
TMA Assembly........................................................................................................................ 4-38
TMA Assembly Orientation ..................................................................................................... 4-38
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.
B.
C.
D.
E.
Introduction .............................................................................................................................. 5-1
System Requirements............................................................................................................... 5-1
Overview ................................................................................................................................... 5-2
Procedure (AIT Flight Simulyzer v3.0.0) ................................................................................... 5-4
A615 LanConfig.Hex File Creation and Settings .................................................................... 5-16
SECTION 6 - SYSTEM COMMISSIONING
6.1
Provisioning of User Services ........................................................................................................... 6-1
A.
B.
Product Support Services ........................................................................................................ 6-2
Terminal Activation .................................................................................................................. 6-3
6.2
Certification and Approvals ............................................................................................................... 6-3
6.3
Post Installation System Checkout Procedures ................................................................................ 6-3
A.
B.
C.
D.
E.
F.
General Overview .................................................................................................................... 6-3
System Health and Configuration ............................................................................................ 6-4
Discrete Input Testing ............................................................................................................ 6-10
ARINC 429 Input Interface Testing ........................................................................................ 6-10
Manual Steering of the Antenna ............................................................................................ 6-11
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.
B.
6.6
On-ground Testing and Commissioning .......................................................................................... 6-17
A.
B.
6.7
Antenna Assembly Orientation .............................................................................................. 6-13
Positioning of Aircraft for Antenna Alignment ........................................................................ 6-14
Testing and Commissioning Process with Restrictions ......................................................... 6-17
Data Link Available (Control Panel) Output ........................................................................... 6-18
Final System Checkout ................................................................................................................... 6-18
A. Network Status............................................................................................................................. 6-18
B.
EMC Interference to Other Systems .........................................................................6-19
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
SECTION 7 -TROUBLESHOOTING
7.1
Post-installation Troubleshooting ....................................................................................................... 7-1
7.2
Accessing the Maintenance Interface ................................................................................................ 7-1
A.
B.
C.
D.
E.
F.
G.
H.
Checking Status Information..................................................................................................... 7-2
Downloading LRU Logs ............................................................................................................ 7-4
System Data Load Failure ........................................................................................................ 7-7
SNMP ....................................................................................................................................... 7-7
System Reset ........................................................................................................................... 7-7
Electrical and Mechanical Inspection and Check ..................................................................... 7-7
Visual Inspection and Check .................................................................................................... 7-8
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
RTCA/DO-160G Environmental Characteristics ............................................................................... A-1
A.
B.
C.
D.
E.
F.
Modman....................................................................................................................................A-1
APM ..........................................................................................................................................A-3
KANDU .....................................................................................................................................A-4
KRFU ........................................................................................................................................A-6
TMA ..........................................................................................................................................A-8
FMA ........................................................................................................................................A-10
APPENDIX B
Aircraft Information Sheet ..................................................................................................................B-1
JetWave™ AES Subsystem Components .........................................................................................B-1
A.
B.
JetWave™ AES OAE - FMA/TMA Installation Information Sheet ............................................B-1
JetWave™ AES KANDU Installation Information Sheet...........................................................B-1
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
C.
D.
E.
JetWave™ AES KRFU Installation Information Sheet..............................................................B-1
JetWave™ AES Modman Installation Information Sheet..........................................................B-2
JetWave™ AES APM Installation Information Sheet................................................................B-2
APPENDIX C
1.
Installation Checklist...........................................................................................................................C-1
A.
B.
C.
OAE-TMA Checklist ..................................................................................................................C-1
A791 Based OAE-FMA with the AIM Checklist.........................................................................C-6
Non-A791 Based OAE-FMA with the LAIM Checklist.............................................................C-10
APPENDIX E
List of Airframe Specific Information Required for JetWave™ System Configuration ........................D-1
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
LIST OF TABLES
Table
Description
Page
Table 2-1
JetWave™ System LRUs ............................................................................................... 2-2
Table 2-2
Table 2-3
Table 2-4
Table 2-5
Table 2-6
Table 2-7
Table 2-8
Table 2-9
Table 2-10
Table 2-11
Table 3-1
Table 4-1
Table 4-2
Table 4-3
Table 4-4
Table 4-5
Table 4-6
Table 4-7
Table 4-8
Table 4-9
Table 4-10
Table 5-1
Table 6-1
Table 7-1
Table 7-2
Table 7-3
Table 7-4
Table 7-5
Table 7-6
Table 8-1
Table 8-2
Table 8-3
Table D-1
Table D-2
Table D-3
Table D-4
Table D-5
A791 Style Radome Package Variant ............................................................................ 2-2
Non A791 Style Radome Package Variant .................................................................... 2-3
Modman Leading Particulars ......................................................................................... 2-3
APM Leading Particulars ............................................................................................... 2-4
KANDU Leading Particulars ........................................................................................... 2-4
KRFU Leading Particulars ............................................................................................. 2-5
TMA Leading Particulars ................................................................................................ 2-7
FMA Leading Particulars ................................................................................................ 2-8
JetWave™ Fuselage Mount Radome Leading Particulars ............................................ 2-8
Radome Packages ....................................................................................................... 2-10
AR INC 429 Label List ................................................................................................... 3-1
ARINC 600 Connectors .................................................................................................. 4-2
Modman Cable Loss Values ........................................................................................... 4-4
Discretes Table ............................................................................................................... 4-5
Thermal Pad Kit Contents ............................................................................................ 4-15
Special Tools for FMA Installation ............................................................................... 4-18
ARINC 791 Style Installation Kit .................................................................................. 4-20
Non ARINC 791 Style Installation Kit ........................................................................... 4-20
Special Tools for TMA Installation ............................................................................... 4-35
TMA RF Interconnect Common Installation Components ............................................ 4-36
Cabling Requirements ................................................................................................. 4-41
Data Sets ....................................................................................................................... 5-3
Modman LED Status Indications..................................................................................... 6-5
L1 Codes ...................................................................................................................... 7-12
L2 Codes – Module Within an AES LRU ..................................................................... 7-14
L2 Codes – Inter LRU Interfaces ................................................................................. 7-16
L2 Codes – ARINC Discrete Interfaces ....................................................................... 7-18
L2 Codes – User Interface ........................................................................................... 7-19
L3 Codes ...................................................................................................................... 7-20
Scheduled Maintenance ................................................................................................ 8-4
Unscheduled Maintenance ............................................................................................ 8-6
Modman LED Status Indications .................................................................................... 8-6
Value Added Reseller (VAR/DP) ...................................................................................D-1
Aircraft Information..........................................................................................................D-1
Air Data Inertial Reference Unit/Multi Mode Receiver ...................................................D-1
ARINC 429 Labels .........................................................................................................D-1
Airframe Structural Blockage Information ......................................................................D-3
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table D-6
Table D-7
Table D-8
Table D-9
Table D-11
Table D-12
Table D-13
Table D-14
Weight on Wheels ..........................................................................................................D-4
ARINC Tx Mute and Tail Sector Mute Switch ................................................................D-4
ARINC791 Equipped .....................................................................................................D-4
Modman Serial Number .................................................................................................D-5
Waveguide Manufacturer ...............................................................................................D-6
Radome Manufacturer ...................................................................................................D-6
KRFU Location ..............................................................................................................D-6
Antenna Location ...........................................................................................................D-6
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
LIST OF FIGURES
Figure
Description
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
Figure 4-22
(Sheet 1 of 4) Modman Outline and Installation Drawing (90400059-0001, REV F) ... 4-45
(Sheet 1 of 4) Modman Outline and Installation Drawing Variant 2 (90400059-0002,
REV A) ......................................................................................................................... 4-49
(Sheet 1 of 2) APM Outline and Installation Drawing (90401592, REV F) ................... 4-53
(Sheet 1 of 2) APM Outline and Installation Drawing (90405762, REV A) .................. 4-55
(Sheet 1 of 3) KANDU Outline and Installation Drawing (90401657, REV E) .............. 4-57
(Sheet 1 of 3) KANDU Variant 2 Outline and Installation Drawing (90405004,
REV C).......................................................................................................................... 4-60
(Sheet 1 of 9) KRFU, Conduction-Cooled 1, Outline and Installation Drawing (90401573,
REV F) .......................................................................................................................... 4-63
(Sheet 1 of 3) KRFU, Conduction-Cooled 2, Outline and Installation Drawing (90402347,
REV F) ......................................................................................................................... 4-72
(Sheet 1 of 3) KRFU, Forced Air Cooled, Outline and Installation Drawing (90401571,
REV D) ......................................................................................................................... 4-75
(Sheet 1 of 4) TMA Outline and Installation Drawing (90401428, REV F) ................... 4-78
Figure 4-23
Figure 4-24
Figure 4-25
Figure 4-26
Figure 4-27
Figure 4-28
Figure 4-29
Figure 4-30
Page
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Figure 4-31
Figure 4-32
Figure 4-33
Figure 4-34
Figure 4-35
Figure 4-36
Figure 4-37
(Sheet 1 of 14) FMA Outline and Installation Drawing (90000380ICD, REV L) ........... 4-82
(Sheet 1 of 6) Fuselage Mount Radome Outline and Installation Drawing (90401395,
REV D) ......................................................................................................................... 4-96
(Sheet 1 of 4) LAIM Outline and Installation Drawing (90404861, REV A) ................ 4-102
(Sheet 1 of 10) JetWave™ System Interconnect Diagram - TMA (90400189-0001,
REV D) ....................................................................................................................... 4-106
(Sheet 1 of 8) JetWave™ System Interconnect Diagram - FMA (KRFU Inside
Aircraft Fuselage), (90400259-0001, REV C) ............................................................ 4-116
(Sheet 1 of 8) JetWave™ System Interconnect Diagram - FMA (KRFU Outside
Aircraft Fuselage), (90401047-1, REV F) .................................................................. 4-124
(Sheet 1 of 12) Alternative KRFU Outside Aircraft Fuselage Configuration (90405210,
REV D) ....................................................................................................................... 4-132
Figure 6-1
Figure 6-2
Figure 6-3
Figure 6-4
Figure 6-5
Figure 6-6
Figure 6-7
Figure 6-8
Figure 6-9
Figure 6-10
Figure 6-11
Figure 6-12
Figure 6-13
Figure 6-14
Figure 6-15
Figure 7-1
Aircraft ID Display/Update Information Page ................................................................. 6-4
AES GUI Login Page ..................................................................................................... 6-6
AES Home and Status Info Page .................................................................................. 6-7
View Configuration Files Page ....................................................................................... 6-8
Health Statuses (excerpt), AES Summary and Link Statuses ....................................... 6-8
AES Modman and Manufacturing Information Page ..................................................... 6-9
Aircraft Tail Number Page ............................................................................................. 6-9
Discrete I/O State ........................................................................................................ 6-10
Aircraft Statuses .......................................................................................................... 6-11
Manual Antenna Steering ............................................................................................ 6-12
Calibrate Transmit Cable Status Page ........................................................................ 6-13
GUI Login Page ........................................................................................................... 6-14
GUI Calibrate Antenna Alignment Page ...................................................................... 6-15
GUI Antenna Alignment Calibration Page Extract ....................................................... 6-17
Network Statuses ......................................................................................................... 6-19
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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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
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)
B.
C.
Warnings and cautions go before the applicable paragraph or step. Notes follow the
applicable paragraph or step.
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.
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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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Figure 1-1. Symbols
D.
Units of Measure
(1)
E.
1.2
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.
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.
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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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
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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JetWave™ System
CAUTION:
1.8
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.
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
Celsius
CAGE
commercial and government entity
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List of Acronyms and Abbreviations (Continued)
Term
Full Term
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
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
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JetWave™ System
List of Acronyms and Abbreviations (Continued)
Term
Full Term
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
meter
mΩ
milliohm
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
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JetWave™ System
List of Acronyms and Abbreviations (Continued)
Term
Full Term
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
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JetWave™ System
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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JetWave™ System
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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JetWave™ System
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
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 2-4. 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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JetWave™ System
Table 2-4. Modman Leading Particulars (Continued)
Characteristic
Specification
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
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JetWave™ System
Table 2-6. KANDU Leading Particulars (Continued)
Characteristic
Specification
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
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JetWave™ System
Table 2-7. KRFU Leading Particulars (Continued)
Characteristic
Specification
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.
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Table 2-7. KRFU Leading Particulars (Continued)
Characteristic
Specification
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
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JetWave™ System
Table 2-9. FMA Leading Particulars
Characteristic
Specification
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)
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.
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JetWave™ System
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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JetWave™ System
• 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 configurations. 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:
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
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.
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JetWave™ System
C.
D.
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.
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.
E.
•
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.
APM
•
The APM holds the configuration data for the system.
•
Is powered by the Modman.
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JetWave™ System
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:
A.
•
Power On
•
System Initialization
•
Normal Operation
•
Critical Fault
•
Data-Load
•
Commanded.
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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JetWave™ System
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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JetWave™ System
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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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
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:
A.
•
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.
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
Label
150
Required
ARINC
429
Labels
For best
accuracy
Yes
Description
Source
Preferred Label Set
UTC Time
260
Yes
Date
254
/110
Yes
Present Position –
Latitude
/GNSS Latitude
Hybrid
/GNSS
Maximum
Transmit
Delay
(Msec)
Maximum
Transmit
Interval
(Msec)
Nil
1000
1°
1000
1 day
100
/20
0.000172°
160
/1000
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Approximate
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JetWave™ System
Table 3-1. ARINC 429 Label List
255
/111
Yes
261
/76
132
/314
324
Yes
Hybrid
/GNSS
160
/1000
100
/20
0.000172°
65
/1000
110
40
/20
50
0.125 ft
Pitch Angle
Hybrid
/GNSS
Hybrid
/INS
INS
50
20
0.0055°
/0.4°
0.011°
325
Yes
Roll Angle
INS
50
20
0.01°
330
Yes
Yaw Rate
INS
50
20
326
Yes
Pitch Rate
INS
50
20
327
Yes
Roll Rate
INS
50
20
175
/112/312
Yes
Ground Speed
/GNSS Ground Speed
Hybrid
/GNSS/
INS
110
/Nil
40
0.015
degrees/sec
0.015
degrees/sec
0.015
degrees/sec
0.125 knots
(kn)
INS
1200
200
Label
125
Yes
/No
Yes
Present Position –
Longitude
/GNSS Longitude
Altitude
/GNSS Altitude (MSL)
True Heading
Acceptable Replacement to Primary
UTC Time
0.1 min.
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.
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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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JetWave™ System
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.
or
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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4.2
(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.
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
Insert A:
Arrangement Q11, Shell Size 2:
Radiall PN 620075050
Size 8 quadrax contact for Ethernet connections
Insert B:
Arrangement 120Q2, Shell Size 2:
#22 contacts
PN: D38999/26FH35PN
D38999/26FD35PN
11
118
Size 8 quadrax contact for Ethernet connections
Radiall PN 620075050
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JetWave™ System
Table 4-1. ARINC 600 Connectors (Continued)
Connector PN
Description
Qty
Insert C:
Arrangement 12F5C2, Shell Size 2:
PN: D38999/26FE6PN
#12 contacts
PN: D38999/26FE6PN
#16 contacts
Size 16 optical contacts (not used)
Size 5 coax contact for RF connections
PN: not included
PN: 620022
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.
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JetWave™ System
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
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
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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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JetWave™ System
Table 4-3. Discretes Table (Continued)
Discrete I/O
Pin
Description
Mandatory / Optional
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
Mandatory
•
Ground to open
ground transition:
Request for reset of
system (if in data
load mode)
Signal type: Input
TX Control
KANDU J1-D
The discrete shall
disable the transmission
of signals when
grounded, and allow
transmission when
open.
Mandatory
Signal type: Input
Public Services Disable
ModMan J1-MP11E
The discrete shall
disable the PODD
interfaces when
grounded, and enable
PODD interfaces when
open.
Optional
Signal type: Input
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.
•
Mandatory
Open = Normal.
Signal type: Input
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Table 4-3. Discretes Table (Continued)
Discrete I/O
Pin
Description
Mandatory / Optional
ModMan Reset
ModMan J1-MP10C
This discrete can be
used to reset the
ModMan (and, in turn
the entire AES)
• Ground = ModMan/AES reset
Optional
•
Open = ModMan/AES normal
operation
•
Signal type: Input
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
Mandatory
•
Open = Disable
Front Panel
Connector.
Signal type: Input
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NOTE: The following ARINC 791 discretes are not supported:
4.3
•
Cell Transmit Enable (ModMan J1-MP11B)
•
Remote Management Enable (ModMan J1-MP10A)
•
Cooling System Available (ModMan J1-MP11F).
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)).
(c)
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
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:
The connector shall use a flange integrated into the connector shell with an
integrated seal and a washer and jam nut.
The jam nut shall be capable of accepting locking wire.
The 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.
or
(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.
(c)
KANDU receptacle A3J3 is MIL-DTL-38999/20FG35PN, series III, flange mount
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.
(c)
It is recommended to use MIL-DTL-38999 series III, insert 17-8, normal keying with eight
contacts as KANDU bulkhead power connector if 115 VAC power is not provisioned in
unpressurized location of aircraft.
(d)
The following bulkhead connector design principles are recommended:
The connector shall use a flange integrated into the connector shell with an
integrated seal and a washer and jam nut.
The jam nut shall be capable of accepting locking wire.
The 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:
A.
B.
•
Install the LAIM and radome skirt fairing bonding straps.
•
Install the LAIM to the aircraft fuselage.
•
Install the radome skirt fairing.
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.
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)
C.
Refer to the airframe specific kits and assembly for fastener specifications to install LAIM to
aircraft.
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)
B.
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.
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.
Table 4-4. Thermal Pad Kit Contents
PN
Description
Quantity
MPW0000118
Thermal pad, conduction, 60 Mil T-Flex Ka airborne, Part 1
MPW0000122
Thermal pad, conduction, 60 Mil T-Flex Ka airborne, Part 2
(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.
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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)
4.7
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.
(c)
When the KRFU is installed under the radome the conduction cooled variant must be
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
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.
or
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.
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)
B.
The FMA Installation General
Before installing any components or cabling, read all notes on drawings and read all installation
procedures.
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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:
D.
THE FUSELAGE MOUNT OAE ASSEMBLY IS ELECTROSTATIC-SENSITIVE.
STANDARD ELECTROSTATIC-SENSITIVE HANDLING PROCEDURES MUST BE
OBSERVED.
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.
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
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.
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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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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
•
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.
(c)
Remove the FMA lifting fixture. Refer to Figure 4-10.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Figure 4-10. FMA Assembly Lifting Fixture Removal
(2)
(3)
(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.
Visually inspect connector and make sure that there are no debris in cavities.
Visually inspect the center conductor and verify that it is still straight and the finish
is intact.
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.
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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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
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.
(c)
Loosely connect the WR34 flexible waveguide to the FMA J3 waveguide flange with
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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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
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)
(b)
(c)
(d)
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.
Clean 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.
Make sure that the over braid of the cable assembly is terminated to connectors at
both the FMA and KANDU ends.
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.
Clean the connectors with the contact cleaner and connect the cable assembly for
fuselage mount from the KANDU J3 receptacle to the KRFU J2 receptacle.
Make sure that the over braid of the cable assembly is terminated to connectors at
both the KRFU and KANDU ends.
Remove the protective covers from the KRFU J5 and KRFU J6 receptacles. Visually
examine the connector ends and ensure there is no debris in central connector cavity.
Clean the connectors with the contact cleaner before connecting.
Make sure that the TX-IF coax cable is banded blue and RX-IF coax cable is
banded green at connector ends.
Make sure that the over braid of the cable assembly is terminated to connectors at
both the KRFU and bulkhead interface feed through ends.
The over braid can be terminated to the connector shield/housing or directly to the
housing.
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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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
FUSELAGE
ANTENNA
MOUNT
LOCAL
ANTENNA
INTERFACE
MOUNT
KRFU
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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
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.
Connecting the Tx waveguide and RF Rx coax interfaces to the TMA per Step (c).
Positioning and installation of the TMA assembly onto tail tip antenna slot/antenna
interface mount; installation of bonding straps per Step (d).
Installation of the KRFU and bonding straps per Step (e).
Installation of the waveguide and coax between the TMA and KRFU per Step (f).
Connecting the TMA interface, KRFU power, and control interfaces per Step (g).
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
(c)
Position and installation of the radome per Step (h).
Waveguide and RF Coax interconnection to Tail Antenna assembly
The waveguide and RF coax interconnect designs are aircraft specific. Consult aircraft
specific SDIM for detailed installation instructions.
NOTE: The waveguide and RF coax shall be connected to the TMA prior to installing
the TMA to the aircraft.
(d)
Remove 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.
Connect 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.
Connect 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.
Attach 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).
Installation of the TMA Assembly
Carefully 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.
Install 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.
Connect 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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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Figure 4-14. TMA RF TX J3 and RF RX J4 Interface Connector and Bonding Strap Locations
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
(e)
KRFU Installation
Make sure that the thermal pads are attached to the bottom of the KRFU. Refer to
Section 4.6. KRFU.
Before proceeding with the KRFU installation, connect the WR42 waveguide to 2.92
mm coaxial connector adapter to KRFU J4 RF RX.
The adapter allows connection between the Rx WR-42 waveguide port on the
KRFU and a 2.92mm coaxial connector.
The 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.
The 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
Remove 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.
Install 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.
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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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
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.
Install 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.
Install 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
Support 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.
Attach 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
Complete 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
23-15-29
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EMS Technologies Canada JETWAVE2 Jetwave User Manual 23 15 29R004

EMS Technologies Canada, Ltd. Jetwave 23 15 29R004

Contents

User Manual_Part 1

FCC ID Filing: K6KJETWAVE2

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