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

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DEVELOPMENT - Release - 23 Sep 2014 12:14:52 MST - Printed on 14 Nov 2014
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Figure 2-34. JetWave™ System Interconnect Diagram - FMA (KRFU Inside Aircraft Fuselage) (Sheet
1 of 8)
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Figure 2-34. JetWave™ System Interconnect Diagram - FMA (KRFU Inside Aircraft Fuselage) (Sheet
2 of 8)
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Figure 2-34. JetWave™ System Interconnect Diagram - FMA (KRFU Inside Aircraft Fuselage) (Sheet
3 of 8)
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Figure 2-34. JetWave™ System Interconnect Diagram - FMA (KRFU Inside Aircraft Fuselage) (Sheet
4 of 8)
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Figure 2-34. JetWave™ System Interconnect Diagram - FMA (KRFU Inside Aircraft Fuselage) (Sheet
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Figure 2-34. JetWave™ System Interconnect Diagram - FMA (KRFU Inside Aircraft Fuselage) (Sheet
6 of 8)
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JetWave™ System
Figure 2-34. JetWave™ System Interconnect Diagram - FMA (KRFU Inside Aircraft Fuselage) (Sheet
7 of 8)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Figure 2-34. JetWave™ System Interconnect Diagram - FMA (KRFU Inside Aircraft Fuselage) (Sheet
8 of 8)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Figure 2-35. JetWave™ System Interconnect Diagram - Boeing Specific FMA (External KRFU)
(Sheet 1 of 8)
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Figure 2-35. JetWave™ System Interconnect Diagram - Boeing Specific FMA (External KRFU)
(Sheet 2 of 8)
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Figure 2-35. JetWave™ System Interconnect Diagram - Boeing Specific FMA (External KRFU)
(Sheet 3 of 8)
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Figure 2-35. JetWave™ System Interconnect Diagram - Boeing Specific FMA (External KRFU)
(Sheet 4 of 8)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Figure 2-35. JetWave™ System Interconnect Diagram - Boeing Specific FMA (External KRFU)
(Sheet 5 of 8)
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JetWave™ System
Figure 2-35. JetWave™ System Interconnect Diagram - Boeing Specific FMA (External KRFU)
(Sheet 6 of 8)
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JetWave™ System
Figure 2-35. JetWave™ System Interconnect Diagram - Boeing Specific FMA (External KRFU)
(Sheet 7 of 8)
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JetWave™ System
Figure 2-35. JetWave™ System Interconnect Diagram - Boeing Specific FMA (External KRFU)
(Sheet 8 of 8)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Figure 2-36. JetWave™ System Interconnect Diagram - A350 FMA (Sheet 1 of 10)
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JetWave™ System
Figure 2-36. JetWave™ System Interconnect Diagram - A350 FMA (Sheet 2 of 10)
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JetWave™ System
Figure 2-36. JetWave™ System Interconnect Diagram - A350 FMA (Sheet 3 of 10)
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Figure 2-36. JetWave™ System Interconnect Diagram - A350 FMA (Sheet 4 of 10)
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Figure 2-36. JetWave™ System Interconnect Diagram - A350 FMA (Sheet 5 of 10)
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JetWave™ System
Figure 2-36. JetWave™ System Interconnect Diagram - A350 FMA (Sheet 6 of 10)
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JetWave™ System
Figure 2-36. JetWave™ System Interconnect Diagram - A350 FMA (Sheet 7 of 10)
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JetWave™ System
Figure 2-36. JetWave™ System Interconnect Diagram - A350 FMA (Sheet 8 of 10)
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Figure 2-36. JetWave™ System Interconnect Diagram - A350 FMA (Sheet 9 of 10)
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JetWave™ System
Figure 2-36. JetWave™ System Interconnect Diagram - A350 FMA (Sheet 10 of 10)
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JETWAVE™ AES SYSTEM CONFIGURATION
1.
Provisioning of User Services
Within the JetWaveTM system, the Modman LRU is responsible for bringing Inmarsat satellite
network IP access to onboard users through In-flight Entertainment Systems or through Onboard
Network Systems. The Modman LRU coordinates with the Inmarsat Satellite Access Station (SAS)
for modulation, demodulation, power control, terminal authentication, configuration, IP
communication, QoS aspects and initiating tracking and beam switching for JetWaveTM system.
The commencement of RF transmission and reception of JetWaveTM system during normal
operation is as follows:
• Satellite Search: The JetWaveTM system is looking for the correct satellite. In this state,
the JetWaveTM system does not transmit.
• Global Signaling Channel: The JetWaveTM system is in this state when it successfully
locks to the GSC signal. The Global Signaling Channel is used by the Inmarsat GX
network to inform the JetWaveTM system terminal of the current satellite configurations
and location. Inmarsat satellite generates a global beam which illuminates the entire
service region in the satellite’s footprint. Global Signaling Channel makes the frequencies
and locations of each spot beam known to the JetWaveTM system and allows automatic
network configuration and rapid network log-in.
• Data Communication: The JetWaveTM system is logged into the network, and is sending
and receiving data. In the data communication state, the JetWaveTM system may be
switched from one data carrier to another. This can occur for either load balancing
reasons, or because of the JetWaveTM system moved into a different spot beam. During
this transition, the JetWaveTM system continues transmitting normally. At some point,
depending on the aircraft movements, directed satellite handover is used when the
JetWaveTM system needs to switch between the satellites. The antenna re-pointing is
required. The frequency band of the transmissions shifts and the KANDU will track on the
new carrier. During this satellite transition, there will be a momentary disruption to the IP
data connectivity.
Inmarsat GX Aviation services operate as a managed subscription service model and the services
are provisioned through various Value Added Resellers / Distribution partners. To provision the user
services, the Airline Operator need to associate the JetWaveTM system with any of the Value Added
Resellers or Distribution Partners and subscribe to the desired Service Subscription Package
services. The following is the current list of Value Added Resellers for AT&R market and Distribution
Partners for BGA market:
NOTE: The list of Value Added Resellers and Distribution Partners is correct at the time of
publishing but may change.
• Value Added Resellers:
• OnAir
• GoGo
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• ARINC
• MCN (for the China market)
• INMARSAT (for Lufthansa, Germanwings, Swiss, Austrian, and Eurowings)
• Distribution Partners:
• Satcom1
• Satcom Direct
• SITA OnAir
• Gogo Business Aviation
• ARINC Direct
The actual throughputs achieved by the GXA terminal are dependent on the Airline Operator
subscription. Each subscription will have a defined Committed Information Rate which is the
minimum throughput guaranteed to each subscriber. The delivered services will be able to exceed
those CIRs where the resources allow up to maximum spot beam capacity. All instantaneous
demand will be matched to provisioned CIRs for every priority level before any remaining
bandwidth is allocated to satisfy any provisioned Maximum Information Rates.
The user connectivity is provided by the Modman LRU of the JetWaveTM system. The Modman
traffic ports to which these user devices gets connected is configurable through the ground based
NMS of the Value Added Resellers / Distribution Partners of Inmarsat GX network. This over the air
configuration functionality supports the ARINC 791 domain segregation and other VAR/ DP
requirements. In addition, the VAR /DPs may also gather statistics on the user domain ports of the
JetWaveTM system for reporting at their NMS.
On initial power-up of the system, after uploading the JetWaveTM system configuration files and
entering the aircraft tail no, the JetWaveTM system first gets associated to the Inmarsat test
network. On the next power up the system is associated to the appropriate VAR / DP network,
where the Service Level Agreements, the aircraft tail no and the pre-assigned JetWaveTM system
terminal ids are linked for billing and service.
2.
About Installation and Registration
The JetWave™ subsystem LRUs that follow support registration of hardware targets with the FIND
protocol in accordance with the A615A data load protocol:
3.
(1)
Modman
(2)
KANDU
(3)
OAE- either FMA or TMA.
Product Support Services
A.
Customer Support Overview
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The JetWave™ system is manufactured by Honeywell as sole supplier of Inmarsat GX Aviation
equipment. Honeywell manufactures and sells this hardware to end customers, as well as to VARs
and DPs.
B.
Customer Support Contacts:
If you purchased your JetWave™ hardware from any of the Inmarsat GX Aviation VARs/DPs,
please contact their customer support phone number for all JetWave™ installation, integration,
configuration, service activation, and troubleshooting issues.
If however, you purchased your JetWave™ hardware directly from Honeywell, please contact
Honeywell Customer Support according to the information provided at the time of your JetWave™
system activation.
4.
AES Configuration Data
NOTE: Any tools for preparing the config files for the terminal must be licensed from Honeywell.
The AES configuration data is a set of configuration files, stored on the APM. Each configuration file
contains a set of airplane-unique parameters. The parameters define the configuration of the AES
necessary for the initialization and operation of the Honeywell JetWave™ AES system. The AES
configuration data holds information such as:
•
Aircraft registration number
•
Aircraft blockage information
•
ARINC 429 label set for positioning and steering used by the KANDU
•
WOW input and polarity etc
•
USER operational preferences.
The details of ARINC 429 lables required for the JetWave™ System are mentioned in the table below.
Table 3-1. ARINC 429 Label List
Maximum
Transmit
Delay
(M Sec)
Maximum
Transmit
Interval
(Msec)
Approximate
Resolution
Label Set
Required
ARINC 429
Labels
Description
Primary
Label
150
For best
accuracy
Yes
Preferred Label Set
UTC Time
1000
1 sec
260
Yes
Date
1000
1 day
270
Yes
Status
254
Yes
255
Yes
261
Yes
Present position –
latitude
Present position –
longitude
Altitude
Source
500
500
Hybrid
160
100
Hybrid
160
100
Hybrid
65
40
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0.000172
degrees
0.000172
degrees
0.125 ft
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132
Yes
True heading
Hybrid
110
50
324
Yes
Pitch angle
INS
50
20
325
Yes
Roll angle
INS
50
20
330
Yes
Yaw rate
INS
50
20
326
Yes
Pitch rate
INS
50
20
327
Yes
Roll rate
INS
50
20
331
Yes
INS
60
20
332
Yes
INS
60
20
0.001 g
333
Yes
Body longitudinal
acceleration
Body lateral
acceleration
Body vertical
Acceleration
0.015
degrees/sec
0.015
degrees/sec
0.015
degrees/sec
0.001 g
INS
60
20
0.001g
Secondary
Label
110
Same accuracy as Primary
GNSS latitude
GNSS
1000
20
0.000172
degrees
0.000172
degrees
0.125 ft
111
GNSS longitude
GNSS
1000
20
76
GNSS altitude
(MSL)
GNSS
1000
20
A.
0.0055
degrees
0.011
degrees
0.01 degrees
Aircraft ID
This section describes the AES System configuration setting to be carried out on completion of LRU
installation activities for updating the aircraft tail number.
Aircraft tail number is the unique identifier used by the Inmarsat system to identify the user aircraft
within the network. The aircraft ID file contains aircraft identity information as follows (columns are
Item, LRU, Data):
To update the aircraft tail number in AES system, maintenance level access is required through the
web based GUI. Refer to Accessing the Maintenance Interface on page 3-33.
The GUI AES status summary screen lets the maintainer navigate to all applicable options. At the
maintenance level, the Other Information & Control has an option to display/update the current
Aircraft ID stored in the AES Configuration data. Refer to Figure 3-1 to change the AES aircraft ID
information.
To just view the aircraft tail number information, the user level is required.
(1)
At the GUI login, the username is "User" and there is no password.
The GUI AES status summary screen lets the user navigate to all applicable options. At the User
level, the Other Information & Control has an option to display the current Aircraft ID stored in the
AES Configuration data. Refer to Figure 3-1 for the AES aircraft ID information page.
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Figure 3-1. AES User Level, Aircraft ID Display/Update Information Page
B.
View AES System Configurations
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 3-1 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.
C.
Regulatory Log Configuration Parameters
The regulatory log configuration parameters file contains details of the remote server to use to
transfer the regulatory log data.
D.
Aircraft Service Configuration
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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.
A Honeywell proprietary configuration tool is used to generate the JetWave™ configuration files, which
are typically stored on the Airplane Personality Module (APM) LRU of the JetWave™ system. The tool
then takes these configuration files and produces an ARINC 665 package of files compatible with the
Modman LRU 615A data loader. Figure 3-2 shows the JetWave™ Configuration Tool GUI interface.
Figure 3-2. AES Configuration Tool
The following airframe specific information is required for creating the JetWave™ configuration files:
•
Applicable ARINC 429 Label sets from Aircraft IRS/ IRU and GNSS
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•
Weight on Wheels discrete input availability and its polarity
•
User Ethernet Ports which are to be configured and the type of services to be enabled (such as
Dataload, SNMP and GUI).
•
Particulars of VAR/DPs providing the IP services
•
Aircraft blockage data.
Refer to APPENDIX E on page D-1 for more details.
5.
ARINC 615A Software Dataload Process
A.
Introduction
The JetWave™ LRUs are preloaded with a full software load and there is no need to perform field
dataload under normal conditions during installation.
On completion of physical installation and interconnection of JetWave™ LRUs in the aircraft, it is
to be verified that the appropriate version of the JetWave™ LRU operational data and APM
configuration file is data loaded onto the JetWave™ LRUs.
The JetWave™ LRU operational data and APM configuration file are supplied as a media file. The
software data load can be carried out when the media files are issued separately along with Service
Bulletins for any in-service system updates.
Only Honeywell approved software is loadable onto JetWave™ LRUs.
This section of the document supplies information on how to accomplish ARINC 615A data loading
of JetWave™ system in the field.
The data loading of JetWave™ system is done while the aircraft is on ground. During the data load,
there will not be any RF transmission.
B.
System Requirements
For data load, the data loader is to be interfaced with Modman through the ARINC 600 Modman
AV1 Ethernet port. The AES JetWave™ Modman is designed to enter into data load mode when
the discrete signal interface for Data load Enable is asserted (grounded) by ARINC 615A compliant
data loading utility. The discrete input electrical specification is in accordance with the specification
in ARINC 763 Section 2.9.6.
It is recommended that the Modman AV1 Maintenance port and Modman Data Load Enable
discrete interface be wired for JetWave™ AES data load and AES log extraction.
An ARINC 615A compliant data loading utility is recommended to be used for JetWave™ AES data
loading. The data loading software-based utility may be hosted on a PC architecture device such
as an Electronic Flight Bag (EFB) or other portable computing device, an on-board portable device,
or an avionics device. Since the Aircraft loading procedures can vary due to different type of
uploading means, it is recommended to refer to the appropriate Aircraft Maintenance Manual before
attempting data loading of JetWave™ AES system.
C.
Procedure
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This section contains the instructions for data loading of JetWave™ software to any of the
JetWave™ LRUs through the ARINC 600 AV1 (Maintenance Port) Ethernet interface of Modman.
Data loading of JetWave™ system can be performed while:
•
JetWave™ system is in normal operation
•
During system initialization
•
When in critical fault mode.
The maintenance operator is responsible for determining which loads are presented to the
JetWave™ AES system through Modman for data load. JetWave™ AES system in turn will
determine the files required to meet the data load request.
The JetWave™ AES system data loading of all LRUs including uploading of the AES configuration
data can be performed through Modman. For data load purpose, Modman acts as a gateway to
JetWave™ LRUs and LRUs themselves do the data load. It is not recommended to attempt field
data load of JetWave™ LRUs directly other than through Modman.
The system configuration file is stored in nonvolatile memory in the APM and does not lose its
contents due to the loss of APM power.
On transfer of the loaded software, the Modman makes sure that the software presented by the data
loader has been loaded correctly before responding that the load is complete and will report part
numbers of the loaded software.
For illustration purpose, snap shots of AIT make F-SIM-LDR ARINC 615A data loader simulator are
included as part of this document.
(1)
Parts Needed:
• Object Media CD
• ARINC 615A compliant data loading utility. The JetWave™ AES system software is
loaded through the Modman.
The JetWave™ AES loadable software part, part number varies for each release.
(2)
System Software/Database Updates
Under normal circumstances, time required to carry out data load operation of all JetWave™
AES LRUs will not exceed 45 minutes for a fuselage mount systems and 60 minutes for a tail
mount system.
The data sets as shown in Table 3-2 can be transferred through the data load port in Modman
Table 3-2. Data Sets
LRU
Data Set
Transfer Process
Modman
JetWave™ Modman LRU Operational
file
Upload only
APM
APM configuration file
Upload only, through the Modman
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Table 3-2. Data Sets(Cont)
LRU
Data Set
Transfer Process
KANDU
JetWave™ KANDU LRU operational
file
Upload only, through the Modman
KRFU
JetWave™ KRFU LRU operational
file
Upload only, through the Modman
OAE-FMA
or
OAE-TMA
JetWave™ OAE LRU operational file
Upload only, through the Modman
In the above listing, upload is defined as the transfer of a data set from the ARINC 615A data
loader and a download is defined as the transfer of a data set from Modman to the ARINC
615A data loader. For JetWave™ AES LRUs where data download operation is not
supported, the system will return 0x1002 status code.
The ARINC 665 media package include *.LUM files for each of JetWave™ LRUs. This along
with LOADS.LUM and FILES.LUM are assembled to form a 665 package which include a
manifest file as a compressed file format. The ARINC 665 media set of JetWave™ system
comprises of:
• LOADS.LUM: Describes the loads that the media device carries, one or more.
• FILES.LUM: Lists all the files, excluding itself, on the media.
• *.LUH is the load part index file which the LOADS.LUM points to.
• *.LUP is the data file which contains compressed software image/images and manifest
files.
During the data loading process, the respective LRU unzips the file and extracts the manifest
file and the images. Each LRU identifies the part for itself from the manifest file.
The .LUP files that follow are included as part of ARINC665 media file for different AES LRUs.
• Modman operational data
• AES configuration data
• KRFU operational image
• KANDU operational image
• OAE-TMA operational image
• OAE- FMA operational image.
NOTE: More than one CONFIG sub parts may be present in a configuration load, one per
AES configuration file type.
For the ARINC 615A data load operations, an A615A target connection must be defined.
Target connection defines a TFTP client on the Modman and TFTP server on the data loader
that will be used for file transfer.
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D.
JetWave™ Data Load Procedure
(1)
General Preparation
(a)
Power up the AES system.
(b)
Power up the ARINC 615A compliant data loader and ensure data loader is interfaced
with Modman and is ready to upload.
(c)
Load the media CD with the copy of the released JetWave™ software and configuration
file.
The media (CD) contains a configuration file and a file containing the software to be
uploaded. The configuration file is located in the root directory of the media and is
named CONFIG.LDR. This configuration file contains information for the data loader to
configure itself for operation. The data loader reads the configuration file and initializes
itself according to the parameters read.
(d)
Make sure that the AES system hardware configuration is correct. Refer to the Service
Bulletin for part number validity.
(e)
The dialog box for the ATI make F-SIM-LDR ARINC 615A data loader is shown in Figure
3-3.
Figure 3-3. AIT F-SIM-LDR ARINC 615A Dialog Box
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(2)
(3)
Preparation for Loading Software
(a)
Click to bring up the 665 Media window on the data loader.
(b)
Select Media Repository and click OK button. Most of the data loader will automatically
select the media repository folder and brings up the Select Media Set window.
(c)
In the Select Media Set window, the operator will be able to see the packaged software
data files.
FIND Loadable Targets
(a)
The ARINC 615A FIND operation is used to identify available loadable target systems.
The loadable targets responding to the FIND request will be shown after the timeout on
the data loader, indicating target identification and source address (IP) information.
Figure 3-4 shows the screen shot of AIT F-SIM-LDR ARINC 615A FIND dialog box.
Figure 3-4. AIT F-SIM-LDR ARINC 615A Find Dialog Box
(b)
For Data load operation, following static IP addresses are assigned to JetWave™ AES
LRUs.
Modman IP address: 172.29.55.1/24
KANDU IP address: 172.29.55.2/24
OAE IP address: 172.29.55.3/24.
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(4)
Getting Target Information
(a)
The ARINC 615A INFORMATION operation is used to retrieve software configuration
information from a loadable target.
(b)
The Modman advertise two data load hardware targets, one for the Modman and the
other for the AES Configuration, as follows:
Modman LRU:
• Target Hardware Identifier: "HNIGXMODMAN0"
• Target Type Name: "MODMAN"
• Target Position: "0"
• Literal Name: "JetWave™ MODMAN"
• Manufacture Code: "HNI".
APM Configuration Data:
• Target Hardware Identifier: "HNIGXCONFIG0"
• Target Type Name: "APM"
• Target Position: "0"
• Literal Name: "JetWave™ APM"
• Manufacture Code: "HNI".
(5)
Data Upload
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(a)
The ARINC 615A UPLOAD operation is used to transfer the data files to the Modman.
The AIT F-SIM-LDR ARINC 615A data upload information dialog box screen shot is
shown in Figure 3-5.
Figure 3-5. AIT F-SIM-LDR ARINC 615A Data Upload Information Dialog Box
(b)
The UPLOAD process is initiated by selecting an individual LSAP or ARINC 665 media
set containing one or more LSAPs.
(c)
In the Upload File Selection dialog, the Files of type: drop down list can be used to select
if either a Media set (Loads(*.LUM)) or an individual LSAP (Header Files (*.LUH)) will be
selected for the UPLOAD.
(d)
In the ARINC-665 Upload File Selection dialog window, the operator can view the list of
files.
The files can be selected either as a media set or an individual LSAP for the
UPLOAD.
Individual LSAPs are selected by choosing the Load Header (.LUH) (Header Files
(*.LUH)) file associated with the load.
For loading entire JetWave™ AES media set, the Loads.LUM file at the root of the
media set must be selected (Loads (*.LUM)).
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(e)
Update the field for target IP address of the JetWave™ Modman as 172.29.55.1 for
loading the entire JetWave™ AES media set.
(f)
Update the field for target IP address of the JetWave™ LRUs for respective LRU IP
address and by choosing the Load Header (.LUH) (Header Files (*.LUH)) file associated
for data load of respective JetWave™ AES LRUs.
(g)
Click Upload LSAPs.
(h)
The data loader application initializes the uploading through an initialization message to
Modman to determine if it is operational.
(i)
If the Initialization step is accepted, the data loader application will initiate the load list
transfer by sending the list of loads which are to be uploaded which is analyzed by the
Modman and sends its status.
(j)
On indication of the acceptance or the denial of this message request, the data
loader application notifies the status to the operator.
If one of the loads is not accepted, it is recommended to reject the complete list.
When the upload is complete, the Status Description field will display the message:
“Upload Operation completed successfully”.
(k)
Close the LSAP upload/upload schedule display.
On completion of the data load, the software part numbers which are loaded into the system can
be verified through the AES GUI interface or through the SNMP service.
6.
Cable Calibration
The Modman will not transmit until it has been calibrated, with the transmit cable calibration. After the AES
is physically installed and connected, the Modman will automatically initiate cable calibration during
start-up.
The transmit cable calibration calibrates the terminal to allow accurate control of transmitter power, taking
into account IF output loss, cable loss, and KRFU (BUC) performance. Transmit cable calibration uses
the Open BMIP BUC interface. During calibration, the power amp of the BUC is disabled and the BUC
must support PA disable.
For the Modman to operate normally:
• The Modman-ACM board calibration file must be present
• The KRFU-BUC calibration file must be present and the serial number must be equal to the BUC
reported serial number
• The IF calibration file must be present.
If any of the conditions are not met, the Modman-ACM enters an inactive state, and deletes any IF
calibration files. The ACM declares itself in need of calibration. When this occurs, the ACM enters a state
whereby it awaits the command to proceed with the calibration, typically through the AES Menu Access
System.
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When calibration is completed successfully, the ACM proceeds to its configured mode of operation as if
it had been restarted. When commissioning is not completed successfully, either due to an error condition
or a user cancellation, the ACM enters an inactive state.
One Touch Commissioning (OTC) is available on the AES Menu Access System.
7.
Post Installation System Checkout Procedures
A.
General Overview
This section supplies the information required to determine the operational readiness of the
JetWave™ system, made up of the Modman, APM, KRFU, KANDU, and OAE FMA or OAE TMA.
The installed LRUs require operational and diagnostic testing for one of the reasons listed below:
•
Operational verification tests that verify the operational readiness of the unit after installation on
an aircraft.
•
Fault verification and diagnostics to verify that a fault exists and produce system reports for
trouble shooting purposes
•
Operational verification of repairs that verify the operational readiness of units that have been
repaired before re-installation on an aircraft.
Only qualified technical personnel, familiar with avionics systems, should perform the test
procedures provided in this document. Before performing any test or fault isolation procedures,
read the safety advisories.
B.
System Power Supply
The JetWave™ system LRUs are shipped with the operational software preloaded.
Make sure that the JetWave™ LRUs are wired and all the receptacles are connected in accordance
with applicable interconnection diagram.
Power up the JetWave™ LRUs, close applicable aircraft circuit breakers to supply power. After 5
minutes, check the Modman front panel for the Modman status.
There are two LEDs on the front panel of Modman. One is for the power and the second one is for
status. Use Table 3-11 to identify the current operating mode of Modman with the power LED
indicating powered up status.
Table 3-11. Modman LED Status Indications
Status LED
Mode
Off
No electrical power / electrical power is
supplied but prior to boot.
Flash green at a minimum
of 10 seconds
Modman initialization
On - green
Modman in normal operation
On - red
Modman in Fault Mode
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On completion of AES system installation activities, the installer can view and make sure that the
JetWave™ LRUs status, AES configuration settings, discrete input and output status, and antenna
alignment status through the GUI as described in this section.
Once the Modman is powered up, the JetWave™ GUI page can be accessed. The JetWave™
system GUI service is supported on AV1 10/100 Base T Ethernet interface. The Modman static IP
address assigned is 172.29.55.1 and the port no for the AES GUI service is 80.
Connect a laptop to the AV1 port of Modman through aircraft Ethernet interface. It is recommended
to use a laptop computer with the following minimum requirements:
•
Intel i5 CPU
•
8 GB of RAM
•
At least 500 MB of available hard drive space
•
An available 10/100/1000 Ethernet interface
•
Windows 7 operating system, 64-bit.
On any of the Internet browser (Internet Explorer 8 compatible), open the link "index.html". Login
page will be presented as the root page, allowing entry of the user name and password. Figure 3-6
shows the login page.
(l)
Figure 3-6. AES GUI Login Page
The GUI is configured to have the login accounts that follow:
• User interface with Username: "User" and Password: empty (no) password
• Maintenance interface with Username: "Maintenance" and Password: "Earthbound".
On successful login, the AES Home page screen is shown. Refer to Figure 3-7.
The information supplied on the AES Home page is as follows:
•
Network status
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•
Ground status
•
Mute Reason
•
Link start and end time
•
Heath status of the system LRUs.
The GUI AES Home page screen, as shown in Figure 3-7, lets the operator navigate to all
applicable options depending on the access level.
Figure 3-7. AES Home and Status Info Page
View and verify the AES configuration data, navigate to the "Configuration Files" formation pages
under the other information and control menu.
The typical configuration file information page is shown in Figure 3-8. To view and make sure that
the AES configuration settings are current, click the AES configuration file to display.
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Figure 3-8. View Configuration Files Page
To view the health status of the JetWave™ system, navigate to the "AES Summary and Link
Status" under the Health Statuses menu on the left.
This will let you to view and make sure of the health status of the JetWave™ system.
The AES summary and interlink status are shown in Figure 3-9.
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Figure 3-9. Health Statuses (excerpt), AES Summary and Link Statuses
To see the AES LRUs hardware and software version and part number, navigate to the Version and
Manufacturing Information menu. Figure 3-10 shows the typical Modman Version and
Manufacturing Information page.
Make sure the vesion and manufacturing information are current for all the LRUs.
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Figure 3-10. AES Modman and Manufacturing Information Page
Update the aircraft tail number, navigate to the "Aircraft Tail Number" page under the other
information and control menu. The aircraft tail number page is shown in Figure 3-11.
Figure 3-11. Aircraft Tail Number Page
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Modman Reset Input
(1)
Activate the Modman Reset by toggling Modman reset switch on the JetWave™ AES control
panel.
(2)
Monitor the Modman ”power” and “status” LEDs flash continuously.
(3)
Toggle the Modman Reset switch on the Satcom test panel to the open/non-grounded
position.
(4)
Monitor the “status” LED on the front of the Modman, progresses from red color to steady
state green as seen during initial power-on.
(5)
Check for the Aircraft Tail number page and make sure that the aircraft tail number page is
updated with the aircraft Tail number.
Navigate to the AES Summary and Link Status page and scroll down to see the ARINC 791
Discrete input and output state of the JetWave™ system. Refer to Figure 3-12.
For illustration, the figure that follows shows the AES discrete signal state. Use the wired aircraft
interfaces to toggle and see if the applicable discrete are asserted or de-asserted.
C.
Figure 3-12. Discrete I/O State
ARINC 429 Input Interface Testing
For the operation of JetWaveTM system, the aircraft must have a functional IRS providing ARINC
429 labels to KANDU. Functional IRS is interfaced with the KANDU through Receive only ARINC
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429 interface through which the required ARINC 429 labels as defined in APM configuration file are
made available.
Navigate to the AES Summary and Link Status page and scroll down to see the aircraft status.
Refer to Figure 3-13.
This page will be updated with current latitude and longitude position of the aircraft.
Once the JetWave™ system starts receiving the valid navigational input from aircraft IRS system,
make sure that the values are correct as compared to the aircraft navigational system outputs.
Figure 3-13. Aircraft Statuses
D.
Manual Steering of the Antenna
To do a commanded test to manually steer the antenna, navigate to "Manual Antenna Steering"
under the commanded test menu. Monitor the antenna movement in accordance with the
commanded test fed through the GUI tool. Refer to Figure 3-14.
NOTE: In order to see the antenna movement, the radome can be removed. If it is an OAE-TMA,
Honeywell recommends manually steering the TMA through GUI to a safe antenna
orientation position before removal. The TMA parking position is included in the AES
System Configuration File, which can be accessed through the GUI web interface and by
navigating to Configuration File page. Consult aircraft specific SDIM for detailed
instructions.
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Figure 3-14. Manual Antenna Steering
E.
Antenna Calibration Testing
Do the Antenna Calibration in accordance with the detailed instructions in TMA Alignment or FMA
Alignment section.
Navigate to Antenna Calibration Status under the commanded test menu and make sure that the
current calibration status, calibration is “Aligned”.
F.
Cable Calibration Testing
Do the cable calibration, navigate to the "Calibrate Transmit Cable" page under the commanded
test menu.
Make sure that the cable calibration is completed successfully. The cable calibration page is shown
in Figure 3-15.
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Figure 3-15. Calibrate Transmit Cable Status Page
G.
ARINC 615 Data Load
Do the data load as detailed in ARINC 615A Software Dataload Process section. Make sure that
the data load operation is completed successfully.
H.
System Available (Cockpit Control Panel) Output
Once the JetWave™ system is powered up, monitor the “System Available” status discrete. Make
sure that the discrete state agrees with the discrete output in the GUI.
I.
Data Link Available (Control Panel) Output
Once the network connectivity is achieved, the “Datalink Available” discrete output on the ARINC
791 page will be asserted.
To see the “Datalink Available” discrete output, navigate to the AES Summary and Link Status page
and scroll down to see the ARINC 791 page and make sure the discrete output status is asserted,
Refer to the Discrete I/O state page Figure 3-12.
Make sure the “Datalink Available” status is indicated in control panel.
J.
Network Status
Navigate to the AES Summary and Link Status page and scroll down to see the Network status of
the JetWave™ system.
An example of a AES network status is shown in Figure 3-16.
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Make sure that the network connectivity in accordance with the aircraft configuration plan.
With the use of another laptop, make sure that the network connectivity on each active port once
the data link available output is available.
Begin a two way (Rx and Tx) video conference call with a tool such as Microsoft Lync or Skype.
Make sure that the availability of the uninterrupted data connectivity. Monitor the Kilobytes sent and
received fields on the home page.
While the JetWave™ system is up and connectivity to internet is established, move the aircraft
around in a circular 360 degree pattern (no faster than 3° per second).
Verify that the connectivity remains available through the 360 degrees turn by monitoring the
datalink status discrete.
Connect to each of the configured Ethernet port to make sure there is data connectivity.
Figure 3-16. Network Statuses
K.
EMC Interference to Other Systems
(1)
Power up the system and let it acquire to the network.
(2)
Begin a two way (Rx and Tx) video conference call with a tool such as Microsoft Lync or
Skype.
(3)
Test the functioning of other communication systems with antennas installed adjacent to the
FMA or TMA and observe for any mutual interference.
(4)
Monitor the link signal quality C/N and Eb/No parameters. These parameters are found under
Aircrarft Statuses as part of the AES Summary and Link Status page. Refer to Figure 3-13.
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(5)
8.
In case of any RF interference, there will be significant variation of the C/N and Eb/No
parameters.
Post-Installation Troubleshooting
A.
System Fails Post-installation Checks
(1)
To make sure that the system is correctly installed, do as follows:
(a)
Make sure that the APM has been correctly configured and loaded. Refer to “ARINC
615A Software Dataload Process”and "Troubleshooting" to access the GUI to check
that the correct APM version is installed.
(b)
Make sure that all the LRUs and connections have been correctly installed.
(c)
Do continuity checks on wiring, test RF cables with specialized RF cable testers,
and do power on and ground checks with LRUs disconnected for the check.
Make sure that all LRUs power up.
System status can be viewed at the AES Home and Status Info Page Figure 3-7
(d)
Make sure that the cable calibration procedure been done. Refer to Cable Calibration
on page 3-14.
(e)
Make sure that the navigation data is correct and the antenna alignment has been done.
• Refer to Installation Section 4.Q. TMA and FMA Antenna Alignment Procedure on
page 2-36.
(f)
Check for system internal interconnect faults. Refer to JetWave™ System Fault Codes
on page 3-41.
(g)
Make sure the system is connected correctly to the navigation busses, check the system
for No traffic faults on the A429 ports. If No traffic faults are received, do as follows:
(h)
(i)
B.
Check wiring and or make sure that the APM is configured for how the system is
wired.
Check the system for User port Ethernet No layer 1 faults. If faults are received, do as
follows:
Check the APM for correct configuration.
Make sure that the connecting equipment is operating correctly.
Check the wiring.
Make sure that the system has the correct software loaded. If so, do as follows:
Check for LRU software errors.
Check for LRU hardware / software incompatibilities.
Check the system for software incompatibilities.
Incorrect Navigation Data
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(1)
(2)
If the system is reporting labels missing, do as follows:
(a)
Check that the APM is configured to have correct labels on the correct bus.
(b)
Make sure that the labels are present on bus.
If the system is reporting an incorrect label status on the bus (FW, NCD, FT), do as follows:
(a)
C.
Wait for equipment providing the labels to report Normal Operation.
System Will Not Connect to the Network
(1)
View the AES Home and Status Info Page Figure 3-7 to see reason transmission is muted
and address the reasons.
(2)
Make sure the system is not limited by geographical restraints.
The system can only transmit in authorized areas and will report if it cannot transmit for this
reason.
(3)
Make sure you have clear line of sight to the satellite.
(4)
Make sure the system has been activated by the ISP.
(5)
Make sure that the system is not configured for data loading.
The system will not transmit while the local data enable switch is closed.
D.
Connectivity of Each Ethernet Port
NOTE: The JetWave™ system configuration files are update by the field. The creation files are not
loaded by the field. This is done at the factory as part of production process with a
Honeywell proprietary tool. Honeywell can be contacted for generating the creation file. 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 verify the AES system configuration, a web based GUI is supplied. The JetWave™
Ethernet configuration data can be viewed and verified by navigating to the “Contents of Aircraft
Services Configuration Files” page from "Configuration Files" under the Other Information & Control
menu. Figure 3-8 shows the typical configuration file Information page.
The network status and the VLAN ID can be viewed as shown in Figure 3-16.
The IP address assigned can be viewed by pressing the “Display” tab of Contents of Aircraft
Configuration File as shown in Figure 3-17.
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Figure 3-17. Contents of Aircraft Services Configuration File
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 port PA1 configured for engineering SNMP and AES access services. Refer to
Figure 3-16. It contains the parameters that follow:
• User Port PA1/2/3/4/PG1/EN5/6/7/8/EG1/AV1/2/3/AG1 data load
• Data Load IP Modman
• Data Load IP KANDU
• Data Load IP OAE
• User Port PA1/2/3/4/PG1/EN5/6/7/8/EG1/AV1/2/3/AG1 AES services config Modman
• User Port PA1/2/3/4/PG1/EN5/6/7/8/EG1/AV1/2/3/AG1 AES services config KANDU
• User Port PA1/2/3/4/PG1/EN5/6/7/8/EG1/AV1/2/3/AG1 AES services config OAE
• User Port PA1/2/3/4/PG1/EN5/6/7/8/EG1/AV1/2/3/AG1 AES services IP Modman
• User Port PA1/2/3/4/PG1/EN5/6/7/8/EG1/AV1/2/3/AG1 AES services IP KANDU
• User Port PA1/2/3/4/PG1/EN5/6/7/8/EG1/AV1/2/3/AG1 AES services IP OAE
• User Port AES services IP subnet
• User Port PA1/2/3/4/PG1/EN5/6/7/8/EG1/AV1/2/3/AG1 traffic services
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• User Port IP filter 1 thru 150.
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.
(1)
If the Ethernet port is not active, do as follows:
(a)
(b)
(2)
9.
Make sure that the port is enabled.
Check system errors.
Check for system reporting No layer 1 or No traffic faults.
Is the device connecting to it operating correctly? If so, check the wiring.
It there is poor performance on one port only, do as follows:
(a)
(3)
Check the APM settings, as follows:
Check for port reporting high packet loss. If so, check wiring and verify that there is
traffic.
If not supplying access to the correct services, do as follows:
(a)
Make sure the APM is configured for the correct services.
(b)
Make sure the APM is configured to access the correct VLANs.
(c)
Check with the service provider to make sure that the VLANs have been correctly
configured for the terminal.
Maintenance and Repair
A.
Maintenance Requirements
(1)
The maintenance-free design of the JetWave™ AES system does not require field
maintenance to maintain airworthiness.
(2)
Maintenance for the JetWave™ AES system is limited to replacement of LRUs on verified
failure.
(3)
Field lubrication or other maintenance procedures are not required for fuselage mount
antenna assembly / tail mount antenna assembly where there are moving mechanical parts.
(4)
If functional problems occur, the BITE can identify the faulty JetWave™ AES LRU and the
Modman collates this BIT information which can be accessed through the GUI provided.
Refer to theRefer to BITE Philosophy on page 3-41 of this document for information on how
to access the BIT data.
If replacement of the unit is deemed necessary, in consultation with Honeywell product support, It is
strongly recommended that all repairs be performed only at the Honeywell authorized facility.
B.
Continued Airworthiness, FAR 25.1529
The sections that follow supply instructions for continued airworthiness for the JetWave™ AES
system. The sections that follow are supplied in response to Federal Aviation Regulation 25.1529,
Instructions for Continued Airworthiness.
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C.
Airworthiness Limitations
(1)
Installation of the JetWave™ AES OAE assembly and LRUs on an aircraft by supplemental
type certificate (STC) or Form 337 obligates the aircraft operator to include the maintenance
information supplied by this manual in the operator’s Aircraft Maintenance manual and the
operator’s Aircraft Scheduled Maintenance Program.
(2)
It is recommended that this section be appended to the Airplane Maintenance Manuals. The
information contained herein supplements the Airplane Maintenance Manuals in areas
covered by the JetWave™ AES FMA/TMA installation.
(3)
It is recommended to consult basic Airplane Maintenance Manuals for limitations and
procedures not contained in this supplement. The inspections and airworthiness limitations
specified in this section are FAA approved.
(4)
This section and the sections that follow specifies the inspections and other maintenance
required under sections 433.16 and 91.403 of the Federal Aviation Regulations unless an
alternative program has been FAA approved.
Initial and recurring inspections of the JetWave™ AES OAE assembly and LRUs and its associated
provisions are required. Specific inspection intervals are contained in Table 3-12.
D.
General Instructions for Inspection
This section provides general instructions for the inspection of the JetWave™ AES OAE assembly
and LRUs .
(1)
Gain access to the installation location on the fuselage for fuselage mount antenna assembly
or to the top of the aircraft vertical stabilizer in the case of tail mount antenna assembly
(2)
Clean all visible surfaces of the antenna, radome assembly, and base plate.
(a)
E.
Do the inspections and checks presented in Electrical and Mechanical Inspection and
Check.
Electrical and Mechanical Inspection and Check
Periodic inspections of the mechanical and electrical interfaces of the JetWave™ AES OAE
assembly and LRUs to the aircraft should be completed as defined by the governing airworthiness
body (such as Transport Canada, the FAA, or the JAA) Instructions for Continued Airworthiness for
the installation.
For the general guidelines refer to Visual Inspection and Check and Scheduled Maintenance and
Inspections sections.
F.
Scheduled Maintenance and Inspections
(1)
The JetWave™ AES system does not require routine maintenance for continued
airworthiness.
(2)
Scheduled inspections items in Table 3-12 must be done at a minimum of once a year preferably scheduled along with the other annual maintenance activities.
(3)
It is recommended to periodically check JetWave™ AES cable connectors and, if required,
tighten connectors to recommended value.
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(4)
It is recommended to follow the Standard Practices Chapter of the Aircraft Maintenance
Manual and do all required inspections and repairs.
Table 3-12. Scheduled Maintenance
SI
No.
G.
Item
Interval
Potential Damage
Inspection
Inspection
Lightning diverters In accordance with the
aircraft inspection
schedule and after flying in
known conditions of
lightning
Paint damage, structural
damage, de-lamination
External visual
Fuselage mount
radome exterior,
radome skirt
exterior / tail
mount radome
exterior
In accordance with the
aircraft inspection
schedule and after flying in
known conditions of
lightning/hail.
Paint damage, structural
damage, de-lamination,
puncture
External visual
Antenna interface
mount
In accordance with the
aircraft inspection
schedule
Corrosion, loose, or
missing fasteners
External visual
OAE – FMA/TMA
connectors
In accordance with the
aircraft inspection
schedule
Corrosion, loose, or
missing connectors
External visual
OAE-FMA/TMA
grounding and
bonding
In accordance with the
aircraft inspection
schedule
Non conform electrical
bonding
External visual and
5 mΩ test
OAE-FMA/TMA
wiring
In accordance with the
aircraft inspection
schedule
Chafing, cracks in
insulation, breaks
External visual
KANDU
connectors
In accordance with the
aircraft inspection
schedule
Corrosion, loose, or
missing connectors
External visual
KANDU grounding In accordance with the
and bonding
aircraft inspection
schedule
Non conform electrical
bonding
External visual and
5 mΩ test
Modman and
APM connectors
In accordance with the
aircraft inspection
schedule
Corrosion, loose, or
missing connectors
External visual
Modman and
APM grounding
and bonding
In accordance with the
aircraft inspection
schedule
Non conform electrical
bonding
External visual and
5 mΩ test
Unscheduled Maintenance
(1)
Follow the Standard Practices Chapter of the Aircraft Maintenance Manual and do all the
required inspections and repairs, as shown in Table 3-13.
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Table 3-13. Unscheduled Maintenance
Item
Potential Damage
Inspection
JetWave™ AES FMA
OAE/TMA OAE
Heavy rain / hail
Paint erosion
External visual
bird strike
Paint damage/radome
puncture
External visual
JetWave™ AES
system Failure
NA
NA
Removal
(2)
JetWave™ AES system status can be viewed through the GUI. Refer to Checking Status
Information section for description.
(3)
On the Modman LRU the status indicator LED is on the Modman front panel. The various
Modman status indications are shown in Table 3-14.
Table 3-14. Modman LED Status Indications
H.
Status LED
Mode
Off
No electrical power / electrical power is
supplied but prior to boot.
Flash green at a minimum
of 10 seconds
Modman initialization
On - green
Modman in normal operation
On - red
Modman in Fault Mode
Repair Requirements
(1)
The BITE functionality of JetWave™ AES system can identify the faulty LRU in case any
occurrence of functional problems and this can be accessed through Modman.
(2)
In accordance with continued airworthiness instructions, if a JetWave™ AES system is
inoperative, use Standard Practices Chapter of the Aircraft Maintenance Manual to:
• Remove the unit
• Secure cables and wiring
• Collar applicable switches and circuit breakers, and placard them as “inoperative”.
Before flight, revise the equipment list and weight and balance data as applicable, and record the removal
of the unit in the log book. Refer to section 91.213 of the FAR or the aircraft’s minimum equipment list. All
repairs must be done at the Honeywell factory.
10.
Troubleshooting
This section supplies troubleshooting procedures for JetWave™ system. Airline maintenance
engineers can troubleshoot JetWave™ system on the ground, with the Health Status Information
and Fault Details and Isolation assistance displayed on the AES GUI.
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Only qualified avionics personnel who are knowledgeable in the technical and safety issues related
to the troubleshooting of aircraft communications equipment should do the troubleshooting
procedures supplied in this manual.
NOTE: If any of the KANDU unmonitored voltage rails are not working the troubleshooting output of the
JetWave™ system would not identify the problem directly.
A.
Accessing the Maintenance Interface
(1)
For maintenance activities, the JetWave™ system can be accessed through a GUI.
(2)
The GUI service is supported on AV1 and AG1 10/100 Base T Ethernet interface.
NOTE: Once the configuration file is loaded, the ports where the GUI is available on can be
different.
(3)
The Modman static IP assigned is 172.29.55.1 and the port number for the AES GUI service
is port 80.
NOTE: This port is configured by the AES configuration user port services support
information.
(4)
On any of the Internet browsers (Internet Explorer 8 compatible), open the link "index.html".
(5)
Login page will be shown as the root page, for you to enter the user name and password.
Refer to Figure 3-18 for the screen-shot of the login page.
Figure 3-18. AES GUI Login Page
(6)
Use the applicable login account with well defined password in the login page for accessing
the interface level required. The login for the maintenance interface and user interface is as
follows:
• Access maintenance interface with Username: "Maintenance" and Password:
"Earthbound".
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• Access the user interface with Username: "User" and no password.
(7)
User may press Log out button to log out. Upon logging off, log in page will be presented by
default. Figure 3-19 shows the log out page.
Figure 3-19. JetWave™ Logout Page
B.
Checking Status Information
(1)
The health status of the JetWave™ system can be monitored by selecting AES Summary and
Link Status under the Health Status pane menu. Figure 3-20 shows the GUI page listing the
health status of JetWave™ system LRUs.
(a)
In the health status page, the GUI lists the last five AES failure codes.
(b)
The JetWave™ system will enter into critical fault mode when critical LRU fault
encountered or the AES Configuration data is missing or invalid.
(c)
The JetWave™ system will be back to normal operation mode only when all the LRU
critical faults are removed, receiving valid navigation information, and a valid AES
configuration data is supplied. Figure 3-20 shows the AES Summary and Link Status
page.
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Figure 3-20. JetWave™ Summary and Link Status (Sheet 1 of 2)
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Figure 3-18. JetWave™ Summary and Link Status (Sheet 2 of 2)
(2)
C.
The JetWave™ system status can be viewed through the GUI. Refer to AES system status
verification section on page 3-5 for description.
Downloading LRU Logs
(1)
To view the hystorical fault logs, under the AES historical logs pane, select the "Fault Log". A
screenshot of fault log page is shown in Figure 3-19.
NOTE: The JetWave™ System Usage log and the Operational log can be downloaded
through GUI with User access level. For downloading the JetWave™ System Fault
log and the Security records, the system must be accessed through the Maintenance
access level on the GUI.
(2)
The log files can be viewed a number of ways. You can choose how many resords as follows:
• Since power on
• Number of days and select actual number of days from the dropdown
• Number of latest records and select the number of records form the dropdown
(3)
Select the record order by clicking on latest first or oldest first.
(4)
Select the Apply button.
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Figure 3-19. JetWave™ Fault Log Download Configuration Page
(5)
The fault log contains the details that follow:
• LRU POST and BITE fault codes
• Watch dog reset events
• Software exception events
• LRU Recorded Temperature, if available
• LRU Recorded Time, if available
• LRU Antenna pointing information, if applicable
• Fault count.
Refer to Figure 3-20 for an example of a viewable fault log.
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Figure 3-20. JetWave™ Fault Log Data
(6)
To download the fault log data for analysis and trouble shooting, press the “Download”
button. The window as shown in Figure 3-21 will come into view. Save to the computer to
open and view the fault log.
Figure 3-21. JetWave™ Fault Log Download Page
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D.
System Dataload Failure
(1)
Make sure that the system is configured for ground operation.
(2)
Make sure that the local data load enable switch is closed.
(3)
Make sure that the 615A data loader is connected to the correct port:
NOTE: AV1 by default, but this may have been modified by the configuration loaded on the
APM.
(4)
11.
Make sure you are trying to load a valid set of files into the correct LRU.
Network Monitoring
The JetWave™ system supplies network performance data to SNMP applications. The available MIB
objects and traps can be found in APPENDIX B on page B-1.
12.
System Reset
The JetWave™ system can be reset with any of the methods that follow:
• Through the Web GUI
• Through the SNMP
• By closure of the Modman reset pin (MP10C) to ground.
NOTE: The maintenance technician can attempt to cycle power to the Modman in case the system fails
to respond to the reset. If the problem persists, the respective AES sub assembly needs to be
replaced. Honeywell Field Support Engineers can be contacted for further support.
A.
Electrical and Mechanical Inspection and Check
Periodic inspections of the mechanical and electrical interfaces of the JetWave™ AES OAE
assembly and LRUs to the aircraft should be completed as defined by the governing airworthiness
body (such as Transport Canada, the FAA, or the JAA) Instructions for Continued Airworthiness for
the installation.
For the general guidelines, refer to Visual Inspection and Check and Scheduled Maintenance and
Inspections sections.
B.
Instructions for Continued Airworthiness
This section supplies the special instructions and maintenance requirements for continued
airworthiness of the JetWave™ AES subsystems.
(1)
JetWave™ AES OAE assembly and LRUs are considered on-condition units. No additional
or routine maintenance is required for the on-condition JetWave™ AES OAE assembly and
LRUs.
(2)
If a JetWave™ AES OAE assembly or an LRU is inoperative, do as follows:
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(a)
Remove the unit
(b)
Secure cables and wiring
(c)
Collar applicable switches and circuit breakers
(d)
Placard the JetWave™ AES LRU and associated items as “inoperative” in accordance
with the aircraft maintenance manual
(e)
Before flight, do as follows:
Record the removal of the unit in the log book
Revise the equipment list. Refer to section 91.213 of the FAR or the aircraft’s
minimum equipment list.
Revise the weight and balance data as applicable.
(3)
JetWave™ AES system LRUs are not field-repairable. Return the faulty LRUs or sub
assembly to the Honeywell authorized facility for repair.
(4)
Install repaired LRUs on the aircraft in accordance with the installation instructions supplied
in this manual.
(5)
Make sure that all repaired units operate correctly before you approve them for return to
service, with the operational verification tests and procedures provided in this SDIM.
Approval for return to service must be entered in the logbook as required by section 43.9 of
the FAR.
(6)
Enter the approval for return to service in the appropriate logbook as required by FAR Section
43.9.
(7)
Add the scheduled maintenance tasks to the aircraft operator’s appropriate aircraft
maintenance program as follows:
(a)
Recommended periodic scheduled servicing tasks: None required.
(b)
Recommended periodic inspections:
• Scheduled maintenance inspections supplied in Table 3-12 and in accordance the
aircraft’s inspection and maintenance schedule.
(c)
C.
Recommended periodic scheduled preventative maintenance tests (to determine
system condition and/or latent failures): None required.
Visual Inspection and Check
Do the procedures that follow to examine the JetWave™ AES OAE assembly and LRUs after
installation of the unit onto the aircraft. Follow all approved safety standards and practices during
the inspection.
CAUTION:
(1)
FAILURE TO DISCONNECT CIRCUIT BREAKERS CAN LEAD TO INJURY TO THE
OPERATOR AND DAMAGE TO THE EQUIPMENT.
Disconnect all circuit breakers to the JetWave™ AES OAE assembly, LRUs and associated
systems.
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(2)
Visually examine the FMA or TMA radome for any damage or defects.
(a)
Remove the JetWave™ AES OAE FMA or TMA assembly and LRUs from service if you
find:
• Punctures in the radome
• Cracks in the radome
• Chips, nicks, or gouges more than 0.250 inch (6.35 mm) across in any direction
• Erosion lamination because of impact more than 0.250 inch (6.35 mm) across in any
direction
• Erosion of lamination because of impact more than 0.031 inch (0.79 mm) from the
exterior surface of the radome
• Damaged areas within 4 inches (101.6 mm) of each other
• Any damage because of lightning.
(3)
Examine the connection for loose, damaged, or missing hardware.
(4)
Examine each lightning diverter strip.
(a)
Remove the JetWave™ AES OAE FMA or TMA assembly from service if:
• Three or more sequential buttons are missing on a lightning diverter strip
• More than 10 percent of the buttons are missing on a lightning diverter strip
• The lightning diverter strip is burned or scorched through to the radome material.
(5)
Examine the base plate.
(a)
Remove the JetWave™ AES OAE FMA or TMA assembly from service if:
• A corrosion area is greater than 1/8 inch (3.16 mm) across
• There is damage to greater than 10 percent of the area thickness.
(6)
Examine cables and connections.
(a)
Contact Honeywell to gauge the severity of the damage if you find:
• Corrosion
• Chafing
• Wear
• Damage.
(7)
13.
Tighten any loose connectors to the manufacturer’s recommended value.
JetWave™ System Fault Codes
A.
BITE Philosophy
(1)
Description
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(a)
The JetWave™ AES consists of the Modman, KANDU, KRFU, TMA or FMA LRUs, plus
the APM.
(b)
The APM is a simple memory device with no software and performs no BITE by itself.
Any BITE required for the APM is performed by the Modman. The APM is not shown in
these diagrams.
(c)
The BITE system divides the responsibility for BITE and historical logs in a BITE
hierarchy as illustrated in Figure 3-22.
Figure 3-22. Bite Hierarchy
(d)
In charge of JetWave™ system is the AES controller. This controller is in charge of the
LRUs of the JetWave™ system, and it:
• Maintains the overall state of the AES system
• Controls the initialization and operation of the system
• Generates BITE events applicable to the system level
• Records BITE events reported by a LRU and itself in an AES historical log.
(e)
Each LRU has a LRU controller that:
• Maintains the state of the LRU
• Generates BITE events applicable to the LRU
• Sends relevant BITE events to the AES controller (for the AES controller to make a
decision on overall AES state, and for it to record in its AES historical log).
(f)
The diagram that follows is a detailed description of how the AES controller, the LRU
controllers, the historical logs, and the means of access to those logs interact. Refer to
Figure 3-23.
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Figure 3-23. AES and LRU Controller Interaction
(g)
The AES Controller resides in the Modman LRU.
(h)
Each LRU Controller monitors the LRU for BITE events. BITE events are classified into
two categories:
• Faults: These are BITE events which have a SET state (occurring) or CLEAR state
(fault has disappeared).
•
(i)
Events: These are BITE events which occur but do not have a set or clear state.
The LRU records the BITE event into a specific LRU log, dependent on the type of fault
or event.
NOTE: Not all BITE events indicate an error situation. BITE events are also used for
storing significant events in the historical logs, either on the LRU or in the AES
controller, or for informing the AES controller of important system wide
information.
(j)
BITE events are sent to the AES controller. The AES controller may react to an event
by changing the overall state of the AES system. Actions include disabling the system,
rebooting the system, etc.
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(k)
The AES controller has a sub-part called the AES controller fault and event handler
which is in charge of responding to BITE events reported by the AES controller or a LRU
controller. This is mentioned in some reaction tables described below.
(l)
The AES controller has its own historical logs which allow it to record events about the
whole system.
(m) Included on the diagram are the Secure File Transport Protocol (SFTP) services and the
GUI services which allow the users to access the AES and LRU historical logs.
• AES controller logs are available from the Modman LRU GUI or SFTP service,
accessible through one of the Ethernet connections on the Modman.
• Modman LRU logs are available from the Modman LRU SFTP service, accessible
through one of the Ethernet connections on the Modman.
• KANDU LRU Logs and KRFU LRU Logs are available from the KANDU LRU SFTP
service, accessible through one of the Ethernet connections on the Modman.
• TMA/FMA LRU Logs are available from the TMA/FMA LRU SFTP service,
accessible through one of the Ethernet connections on the Modman.
(n)
The LRU and AES remember information about BITE events that have occurred, in both
non-volatile memory and volatile memory.
(o)
The historical logs are kept by the LRU and AES controller.
(p)
Each BITE event is described by an LRU code, encoded in three numbers (L1, L2 and
L3) to uniquely identify the event.
(q)
Section 5 has more details on the format of this LRU code system.
(r)
The BITE events themselves have a description of the L1 thru L3 code and the
additional text to be used for that event.
(s)
Each BITE event is also associated with a reaction table which describes the
confirmation actions, and event actions, the LRU should take when this BITE event
occurs. For events that are reported to the AES controller, there is a reaction table
describing what the AES controller should do when the event is reported to it.
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(2)
Status Memory
(a)
The AES Controller remembers the following information:
• The AES Controller maintains an overall mode of operational state, of UNKNOWN
(Default), DATA LOAD, CRITICAL FAULT, COMMANDED MODE, OPERATIONAL
MODE.
• The AES controller maintains an overall service state, of AVAILABLE (default) or
UNAVAILABLE. This service state, when set to UNAVAILABLE, disables user
servicer and transmission.
• For each unique L1 thru L3 code, maintained across reset/power down, it records if
the code has occurred (SET), cleared after occurring (CLEAR), or never seen
(NO_ERROR).
• For each unique L1 thru L3 code, maintained across reset/power down, it records
the number of occurrences and the time of the last occurrence.
• For every link in the system, it records the status: UNKNOWN (default after power
on), DISABLED, INACTIVE, NO_LAYER_1 (when applicable),
HIGH_PACKET_LOSS, ACTIVE (normal). It also records the time of the last report,
and the long term link status: NOFAULT, FAULT.
• For every ARINC 429 label the AES accepts on a per LRU basis, it records the
status: DISABLED, UNKNOWN (default after power on), ACTIVE, SSMERROR,
MISSING.
• For every input discrete the AES LRUs possesses, it records the status: UNKNOWN
(default after power on), ASSERTED, DEASSERTED.
• For every temperature sensor on every LRU the AES controller records its status:
NORMAL (default after power on), WARNING, CRITICAL.
• For the Modman, KRFU, KANDU, TMA, FMA the AES controller records it overall
hardware state: NORMAL (default after power on), WARNING, FAILED.
• The AES controller maintains in memory the mute state of each LRU, and the
reason for mute. Default is "INITIALIZATION".
(b)
The LRUs remembers the following information:
• For each unique L1 thru L3 code, maintained across reset/power down, it records if
the code has occurred (SET), cleared after occurring (CLEAR), or never seen
(NO_ERROR).
• For each unique L1-L3 code, maintained across reset/power down, it records the
number of occurrences and the time of the last occurrence.
• For every link the LRU has, it records the status: UNKNOWN (default after power
on), DISABLED, INACTIVE, NO_LAYER_1 (when applicable),
HIGH_PACKET_LOSS, ACTIVE (normal). It also records if the link is causing a
mute of the system.
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• For every ARINC 429 label the LRU understands, it records the status: DISABLED,
UNKNOWN (default after power on), ACTIVE, SSMERROR, MISSING. It also
records if the label is causing a mute of the system.
• For every input discrete the LRU possesses, it records the status: ASSERTED,
DEASSERTED.
• The LRU maintains in memory the reason, if any, for muting.
B.
LRU Codes
BITE event information is encoded by the LRUs in three values. The values are named L1 thru L3:
•
L1 denotes the LRU or interface (generated by an LRU on its behalf) which is generating the
event
•
L2 denotes the Shop Replaceable Module within an LRU for a event relating to an LRU, or for
interfaces it denotes an particular part of the interface which is generating the event.
•
L3 further defines the unique event that occurred.
Each fault or event also has an additional text field which can carry additional information helpful to
understand the fault or event that happened.
The combination of L1 thru L3 alone uniquely identifies a BITE event in the system.
C.
L1 Codes
(1)
The event L1 code uses two hexadecimal digits to identify a LRU or an interface within an
AES LRU, coded as follows:
Table 3-15. L1 Codes
Group
L1 Code
L1 Description
System
0x 00
System
The L1 code of 00 shall be used if
the LRU is unknown or if the error
is applicable to a system level,
such as an invalid or unknown
system configuration error, or a
system event not specific to an
LRU.
AES
0x 01
Modman
0x 02
KRFU
0x 03
TMA
0x 04
FMA
0x 05
APM
0x 06
KANDU
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Table 3-15. L1 Codes (Cont)
Group
L1 Code
L1 Description
Intra-system Interconnect
0x 20
Modman KANDU Ethernet bus
0x 21
Modman APM serial bus
0x 24
Modman output discretes
0x 30
KANDU OAE Ethernet Bus
0x 31
KANDU OAE Serial Control Bus
0x 32
KANDU OAE serial IMU bus
0x 33
KANDU KRFU serial bus
0x 34
KANDU input discretes from OAE
0x 35
KANDU input discretes from
Modman
0x 36
KANDU input discretes from
KRFU
0x 41
KRFU input discretes from
KANDU
0x B0
RF TX Modman to KRFU
0x B1
RF TX KRFU to OAE
0x B2
RF RX
0x 70
IRU input bus
0x 71
Aircraft state input bus
0x 72
Modman aircraft discrete input
0x 73
KANDU aircraft discrete input
0x 80
AISD Network: Ethernet AG1
0x 81
AISD Network: Ethernet AV1
0x 82
AISD Network: Ethernet AV2
0x 83
AISD Network: Ethernet AV3
0x 88
PIESD Network: Ethernet EG1
0x 89
PIESD Network: Ethernet EN5
0x 8A
PIESD Network: Ethernet EN6
0x 8B
PIESD Network: Ethernet EN7
0x 8C
PIESD Network: Ethernet EN8
Intra-system Interconnect
Aircraft Interconnect
AISD Network
PIESD Network
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Table 3-15. L1 Codes (Cont)
Group
L1 Code
L1 Description
PODD Network
0x 90
PODD Network: Ethernet PG1
0x 91
PODD Network: Ethernet PA1
0x 92
PODD Network: Ethernet PA2
0x 93
PODD Network: Ethernet PA3
0x 94
PODD Network: Ethernet PA4
NOTE: All other codes not explicitly stated are spare.
D.
L2 Codes
(1)
The event L2 code uses two hexadecimal digits to identify a shop-replaceable module within
an AES LRU, coded as follows:
Table 3-16. L2 Codes – Module within a AES LRU
L1
L2 Code
L2 Description
System (00)
0x 00
Unknown
0x 01
Mode
0x 02
AES menu access level
0x 03
Configuration
0x 04
AES SFTP
0x 05
SNMP engineering
0x 06
SNMP ARINC 791
0x 07
Regulatory logs
0x 08
Information events
0x 00
Unknown
0x 01
ACM
0x 02
Controller/Router
0x 03
Power supply unit
0x 04
Backplane
0x FA
Operational information
0x FB
IP security
0x FC
Reset
0x FD
Software configuration
0x FE
Software runtime
Modman (01)
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Table 3-16. L2 Codes – Module within a AES LRU (Cont)
L1
L2 Code
L2 Description
Modman (01)
0x FF
Temperature
KRFU (02)
0x 00
Unknown
0x 01
Power supply unit
0x 02
Block up converter
0x 04
Power amplifier
0x 05
Monitor and control
0x 07
Fan
0x 08
Failed on start-up
0x 2A
BDC
0x FA
Operational information
0x FC
Reset
0x FD
Software configuration
0x FE
Software runtime
0x FF
Temperature
0x 00
Unknown or not applicable
0x 03
Low noise amplifier
0x 04
Motors and sensors
0x 05
Position control unit
0x 06
Power supply unit
0x 0B
MDU
0x 0C
R2D
0x FA
Operational information
0x FB
IP security (FMA only)
0x FC
Reset
0x FD
Software configuration
0x FE
Software runtime
0x FF
Temperature
0x FA
Operational information
0x FD
Software configuration
TMA (03)
FMA (04)
APM (05)
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Table 3-16. L2 Codes – Module within a AES LRU (Cont)
L1
L2 Code
L2 Description
KANDU (06)
0x 00
Unknown or not applicable
0x 01
ASC
0x 02
Power supply unit
0x 11
ASC BITE EMIFA
0x 12
ASC BITE A429 IRS
0x 13
ASC BITE A429 AUX
0x 14
ASC BITE Ethernet switch
0x FA
Operational information
0x FB
IP security
0x FC
Reset
0x FD
Software configuration
0x FE
Software runtime
0x FF
Temperature
(2)
The event L2 code further identifies specific inter LRU interfaces, coded as follows:
Table 3-17. L2 Codes – Inter LRU Interfaces
L1
L2 Code
L2 Description
Modman KANDU Ethernet bus (20)
0x 01
Modman input
0x 02
KANDU input
Modman APM Serial Bus (21)
0x 01
Modman input
Modman Output: Discrete from
Modman (24)
0x 01
Reset
0x 02
ARINC TX mute
0x 03
Filter select
0x 04
Keyline transmit
0x 05
System available
0x 06
Data link available
0x 01
KANDU input
0x 02
OAE input
0x 01
KANDU input
0x 02
OAE input
KANDU OAE Ethernet Bus (30)
KANDU OAE Serial Control Bus (31)
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Table 3-17. L2 Codes – Inter LRU Interfaces (Cont)
L1
L2 Code
L2 Description
KANDU OAE Serial IMU Bus (32)
0x 01
KANDU input
0x 02
OAE input
0x 01
KANDU input
0x 02
KRFU input
KANDU Input: Discrete from OAE
(34)
0x 01
FMA TX mute input
KANDU Input: Discrete from Modman
(35)
0x 01
Reset
0x 02
ARINC TX mute
0x 03
Filter select
0x 04
TX Mute
KANDU Input: Discrete from KRFU
(36)
0x 00
Unknown
KRFU Input: Discrete from KANDU
(41)
0x 01
Reset
0x 02
KRFU TX mute
0x 03
Filter select
RF TX Modman to KRFU (B0)
0x 00
Unknown
RF TX KRFU to OAE (B1)
0x 00
Unknown
RF RX(B2)
0x 00
Unknown
KANDU KRFU Serial Bus (33)
(3)
The event L2 code further identifies ARINC 429 and ARINC 791 discrete interfaces, coded
as follows:
Table 3-18. L2 Codes – ARINC Discrete Interfaces
L1
L2 Code
L2 Description
IRU Input Bus (70)
Aircraft state Bus (71)
0x 00
Unknown
0x 01
Pitch angle label
0x 02
Roll angle label
0x 03
Pitch rate label
0x 04
Roll rate label
0x 05
Yaw rate label
0x 06
Body longitudinal acceleration
0x 07
Body vertical acceleration
0x 08
True heading label
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Table 3-18. L2 Codes – ARINC Discrete Interfaces
L1
L2 Code
L2 Description
IRU Input Bus (70)
Aircraft state Bus (71)
0x 09
Body lateral acceleration
0x 11
Latitude label
0x 12
Longitude label
0x 13
Altitude
0x 14
Vertical velocity
0x 15
N-S velocity
0x 16
E-W velocity
0x 21
Horizontal stabilization
0x 31
Time label
0x 32
Date label
0x 41
Flight phase label
0x 42
MLG ground condition
0x 80
GNSS sensor status word
0x 81
IRS discrete word #1
0x 06
WOW
0x 07
Cell TX OK
0x 08
Ground transmit enable
0x 09
Public services disable
0x 0A
Remote manager
0x 0B
Cooling available
0x 0C
Local data load
0x 0C
TX control
Modman Aircraft Discrete Input (72)
KANDU Aircraft Discrete Input (73)
(4)
The event L2 code further identifies user interfaces, coded as follows:
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Table 3-19. L2 Codes – User Interface
E.
L1
L2 Code
L2 Description
AISD Network: Ethernet AG1 (80)
AISD Network: Ethernet AV1 (81)
AISD Network: Ethernet AV2 (82)
AISD Network: Ethernet AV3 (83)
PIESD Network: Ethernet EG1 (88)
PIESD Network: Ethernet EN5 (89)
PIESD Network: Ethernet EN6 (8A)
PIESD Network: Ethernet EN7 (8B)
PIESD Network: Ethernet EN8 (8C)
PODD Network: Ethernet PG1 (90)
PODD Network: Ethernet PA1 (91)
PODD Network: Ethernet PA2 (92)
PODD Network: Ethernet PA3 (93)
PODD Network: Ethernet PA4 (94)
0x 01
Modman input
L3 Codes
(1)
The L3 code is four hexadecimal digits, used to uniquely identify the fault or event against an
L1, L2 code pair.
(2)
Each LRU defines their own L3 codes. These are given in the fault table, refer to Table 3-20.
Table 3-20. L3 Codes
L1
L2
L3 Code
L3 Description
Repair Action
System (00)
Unknown (00)
0x 0001
OAE not pointed
correctly
Try a manual point and see if it works.
Mode (01)
0x 0000
Critical fault mode entry
0x 0001
Dataload mode entry
- Info events - Recording what happened
in the LRU.
- If it is a warning, It is info only.
0x 0002
Commanded mode
entry
0x 0003
Normal mode entry
0x 0000
Maintenance
0x 0001
Factory
0x 0002
Engineering
0x 0021
Log clearance AES
operational historical
log
0x 0022
Log clearance AES fault
historical log
AES menu access
level (02)
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Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
System (00)
AES menu access
level (02)
0x 0023
Log clearance AES
usage historical log
- Info events - Recording what happened
in the LRU.
- If it is a warning, It is info only.
Configuration (03)
0x 0000
Tail number missing
Use the AES Menu interface at
maintenance level to enter the valid tail
number of the aircraft
0x 0001
Configuration file
missing
- First fit: Data load the configuration data
to the Modman LRU with the 615A data
loading process.
- After operational: Replace the APM
LRU (presume its broke since the APM
should not forget an APM file), do the first
fit operation again.
0x 0002
Inter LRU SW
incompatibility
Verify versions of SW with the GUI or
AES menu tool on all LRUs and replace
with correctly configured set of SW.
0x 0003
Geographical map
missing
NO ACTION – this will be updated when
the system is in operation.
0x 0004
Configuration file in
APM missing
- First fit: Data load the configuration data
to the Modman LRU with the 615A data
loading process.
- After operational: Replace the APM
LRU (presume its broke since the APM
should not forget an APM file), do the first
fit operation again.
0x 0000
Maintenance
0x 0001
Factory
- Info events - Recording what happened
in the LRU.
- If it is a warning, It is info only.
0x 0002
Engineering
0x 0000
Maintenance
0x 0001
Factory
0x 0002
Engineering
0x 0021
Log clearance AES
operational historical
log
0x 0022
Log clearance AES fault
historical log
0x 0023
Log clearance AES
usage historical log
0x 0000
Maintenance
0x 0001
Factory
0x 0002
Engineering
AES SFTP (04)
SNMP
Engineering (05)
SNMP ARINC 791
(06)
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Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
System (00)
Regulatory Log
(07)
0x 0000
Regulatory log upload
failure
0x 0001
Reg log full
NO ACTION –System will continue to try
and upload the file as directed by the
regulatory log requirements on frequency
of upload attempts.
0x 0002
FTP address invalid
NO ACTION - These are warnings
0x 0003
FTP connection refused
0x 0004
FTP records
misalignment
- Info events - Recording what happened
in the LRU.
0x 0000
User service enabled
NO ACTION: - This is AES Information
Event
0x 0001
User service disabled
NO ACTION: - Will recover next time
0x 0002
Geographic map stored
- Info events - Recording what happened
in the LRU.
0x 0003
Geographic map
received corrupted
NO ACTION: - Will recover next time
0x 0000
Mute state
0x 0011
LRU menu access maintenance
Info events - Recording what happened
in the LRU.
0x 0012
LRU menu access factory
0x 0013
LRU menu access engineering
0x 0014
LRU SFTP access maintenance
0x 0015
LRU SFTP access factory
0x 0016
LRU SFTP access engineering
0x 0021
Log clearance LRU
operational
0x 0022
Log clearance LRU fault
0x 0001
ACM not responding
0x 0002
ACM BIST fault
0x 0003
ACM over temp
0x 0001
DSP Fault
0x 0002
Ethernet Main Switch
0x 0003
Ethernet PODD Switch
Information
Events (08)
Modman (01)
Unknown (00)
ACM (01)
Controller/router
(02)
Hardware faults and events:
- Replace the Modman.
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Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Modman (01)
Controller/router
(02)
0x 0004
Ethernet PIES Switch
0x 0005
Ethernet AISD Switch
Hardware faults and events:
- Replace the Modman.
0x 0006
Down converter
0x 0007
NOR flash
0x 0008
NAND flash
0x 0009
A429 driver
0x 000B
Reset control I/O
0x 000C
Board config I/O
0x 000D
Ethernet FP PHY
0x 000E
Ethernet ACM PHY
0x 000F
Ethernet EN3 PHY
0x 0010
Ethernet Server PHY
0x 0011
Ethernet AV1 PHY
0x 0012
Ethernet AV2 PHY
0x 0013
Ethernet AV3 PHY
0x 0014
Ethernet AG1 PHY
0x 0015
Ethernet EN5 PHY
0x 0016
Ethernet EN6 PHY
0x 0017
Ethernet EN7 PHY
0x 0018
Ethernet EN8 PHY
0x 0019
Ethernet EG1 PHY
0x 001A
Ethernet PA1 PHY
0x 001B
Ethernet PA2 PHY
0x 001C
Ethernet PA3 PHY
0x 001D
Ethernet PA4 PHY
0x 001E
Ethernet PG1 PHY
0x 001F
MM & ACD ETH link
status IO
0x 0020
PIES/PODD ETH link
status IO
0x 0021
BITE status inputs IO
0x 0022
Server card in/out IO
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Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Modman (01)
Controller/router
(02)
0x 0023
RSSI control in/out IO
0x 0024
Unique ID chip
Hardware faults and events:
- Replace the Modman.
0x 0030
5V ISO good - power
fail
0x 0031
12V ISO good - power
fail
0x 0032
1V2 AR power good power fail
0x 0033
APM power good power fail
0x 0034
RSSI VDD power good
- power fail
0X0035
RSSI +1V3 power good
- power fail
Power supply unit
(03)
0x 0001
PSU input power fail
0x 0002
PSU good power fail
Backplane (04)
0x 0001
ACM 18V power good
Operational
information (FA)
0x 0000
Mode Transition
0x 0001
Parameter
0x 0002
Operational event
0x 0004
Connect event
0x 0005
Disconnect event
0x 0006
User Bytes passed
0x 000A
Standard electronic
information
0x 000B
Honeywell electronic
information
0x 000C
Subassembly
information
0x 0000
IP security event
Use a well defined port and IP address
0x 0001
Segregation fault
Use a well defined IP address
0x 0020
Configuration fault
Use correct network configuration
0x 0000
Power Cycle
0x 0001
Watchdog
Info events - Recording what happened
in the LRU.
0x 0002
Software Command
IP security (FB)
Reset (FC)
Info events - Recording what happened
in the LRU.
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Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Modman (01)
Reset (FC)
0x 0003
Reset Pin
0x 0004
SW exception
Info events - Recording what happened
in the LRU.
0x 0001
HW SW compatibility
0x 0002
LRU SW compatibility
0x 0003
Configuration
parameter missing
Reload the configuration data with the
A615A data loading process.
0x 0004
Primary image
corruption warning
- Reboot the LRU to load valid primary
image and check if fault goes away.
- If not, then a fresh data load of software
is required to load the fresh image.
0x 0005
No valid image
Reload compatible software with the
A615A data loading process.
0x 0006
LRU PRI-SEC image
mismatch
- Reboot the LRU to load valid primary
image and check if fault goes away.
- If not, then a fresh data load of software
is required to load the fresh image.
0x 0007
Data load
0x 0008
Data loader connect
0x 0009
Data loader disconnect
0x 000A
Operating image list
Unit configuration events:
- Critical, something needs to be done
(reload software).
- Warning, then the event was
unexpected, but will sort itself out.
- Info, recording what happened in the
LRU.
0x 000B
Secondary image
corruption warning
A fresh data load of software is required
to load the fresh image.
0x 0000
Heartbeat failure
0x 0001
GENERAL module
failure
0x 0020
Missing KANDU
information
0x 0021
File system full
Software events:
- Critical, will cause the unit to reset.
-Warning, then the event was
unexpected, but will sort itself out.
-Info, recording what happened in the
LRU.
(For software faults there is no reason to
return box.)
0x 0022
thru
0x 007F
Other SW errors
0x 0001
C/R temperature sensor
0x 0002
PSU temperature
sensor
Software
configuration (FD)
Software runtime
(FE)
Temperature (FF)
Reload compatible software with the
A615A data loading process.
- If it is a warning, It is info only.
- If it is critical, the LRU will shut down
functionally: The LRU is not correctly
installed or there can be a fault in the box
generating the heat.
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Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
KRFU (02)
Unknown (00)
0x 0000
Mute state
0x 0001
Primary power
interruption
Info events - Recording what happened
in the LRU.
Power supply (01)
0x 0002
Power supply internal
fault
Block up converter
(02)
0x 0001
BUC lockloss: Transmit
BITE status
0x 0002
BUC lockloss: Transmit
BITE status
Power amplifier
(04)
0x 0002
PA overdriven: Transmit
BITE status
Monitor and
control (05)
0x 0001
Flash fault
0x 0002
RAM fault
0x 0003
Watchdog reset
Fan (07)
0x 0000
Fan
Failed on startup
(08)
0x 0000
Failed on startup
BDC (2A)
0x 0001
BDC lockloss: Receive
BITE status
Operational
information (FA)
0x 000A
Standard electronic
information
0x 000B
Honeywell electronic
information
0x 0001
Watchdog
0x 0002
Software command
0x 0004
SW exception
0x 0005
Power cycle or Reset
pin
0x 0001
HW SW compatibility
Reload compatible software with the
A615A data loading process.
0x 0004
Primary image
corruption warning
- Reboot the LRU to load valid primary
image and check if fault goes away.
- If not, then a fresh data load of software
is required to load the fresh image
0x 0005
No valid image
Reload compatible software with the
A615A data loading process.
Reset (FC)
Software
configuration (FD)
Hardware faults and events:
- Replace the KRFU
Info events - Recording what happened
in the LRU.
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Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
KRFU (02)
Software
configuration (FD)
0x 0006
LRU PRI-SEC image
mismatch
- Reboot the LRU to load valid primary
image and check if fault goes away.
- If not, then a fresh data load of software
is required to load the fresh image.
0x 0007
Data load
0x 000A
Operating image list
Unit configuration events:
- Critical, something needs to be done
(reload software).
- Warning, then the event was
unexpected, but will sort itself out.
- Info, recording what happened in the
LRU.
0x 000B
Secondary image
corruption warning
A fresh data load of software is required
to load the fresh image.
Software runtime
(FE)
0x 0000
Heartbeat failure
Software events:
- Critical, will cause the unit to reset.
-Warning, then the event was
unexpected, but will sort itself out.
-Info, recording what happened in the
LRU.
(For software faults there is no reason to
return box.)
Temperature (FF)
0x 0001
KRFU main
temperature sensor
- If is a warning, it is for info only.
- If it is critical the LRU will shut down
functionally: suggest the LRU is not
correctly installed or there can be a fault
in the box generating the heat.
Unknown (00)
0x 0001
Primary power
interruption
Info events - Recording what happened
in the LRU.
0x 0011
LRU menu access maintenance
0x 0012
LRU menu access factory
0x 0013
LRU menu access engineering
0x 0014
LRU SFTP access maintenance
0x 0015
LRU SFTP access factory
0x 0016
LRU SFTP access engineering
0x 0021
Log clearance LRU
operational
0x 0022
Log clearance LRU fault
TMA (03)
23-15-29
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Page 3-60
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
TMA (03)
LNA (03)
0x 0001
LNA current
Motor and sensors
(04)
0x 0001
AZ sensor detection
0x 0002
EL INIT sensor
detection
0x 0003
EL LIMIT sensor
detection
Hardware faults and events:
- Replace the TMA.
NOTE: Before removing the Tail Mount
Radome, Honeywell
recommends manually steering
the TMA through GUI to a safe
antenna orientation position.
The TMA parking position is
included in the AES System
Configuration File, which can be
accessed through the GUI web
interface and by navigating to
Configuration File page.
Consult aircraft specific SDIM
for detailed instructions.
0x 0001
DSP fault
0x 0002
AZ motor current draw
0x 0003
El motor current draw
0x 0004
Initialization incomplete
0x 0003
OMAP PWR 3.3V:
Out-of Spec
0x 0004
OMAP PWR 5V: Out-of
Spec
0x 0005
MOT PWR 12V: Out-of
Spec
0x 0006
LNA PWR 12V: Out-of
Spec
0x 0000
Mode transition
0x 0001
Parameter
0x 0002
Event
0x 000A
Standard electronic
information
0x 000B
Honeywell electronic
information
0x 000C
Subassembly
information
IP Security (FB)
0x 0000
IP Security event
Use well defined port and IP Address
Reset (FC)
0x 0000
Power cycle
0x 0001
Watchdog
Info events - Recording what happened
in the LRU
0x 0002
Software command
0x 0003
Reset pin
Position control
unit (05)
PSU (06)
Operational
information (FA)
Hardware faults and events:
- Replace the TMA.
NOTE: Before removing the Tail Mount
Radome, Honeywell
recommends manually steering
the TMA through GUI to a safe
antenna orientation position.
The TMA parking position is
included in the AES System
Configuration File, which can be
accessed through the GUI web
interface and by navigating to
Configuration File page.
Consult aircraft specific SDIM
for detailed instructions.
Info events - Recording what happened
in the LRU
23-15-29
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Page 3-61
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
TMA (03)
Software
Configuration (FD)
0x 0003
Configuration
parameter missing
Reload the configuration data with the
A615A data loading process.
0x 0004
Primary image
corruption warning
- Reboot the LRU to load valid primary
image and check if fault goes away.
- If not, then a fresh data load of software
is required to load the fresh image.
0x 0005
No valid image
Reload software with the A615A data
loading process.
0x 0006
TMA PRI-SEC image
mismatch
- Reboot the LRU to load valid primary
image and check if fault goes away.
- If not, then a fresh data load of software
is required to load the fresh image.
0x 0007
Data load
0x 0008
Data loader connect
0x 0009
Data loader disconnect
0x 000A
Operating image list
Unit configuration events:
- Critical, something needs to be done
(reload software).
- Warning, then the event was
unexpected, but will sort itself out.
- Info, recording what happened in the
LRU.
0x 000B
Secondary image
corruption warning
A fresh data load of software is required
to load the fresh image.
0x 0000
Heartbeat failure
0x 0001
DSP task timeout
0x 0002
ARM-DSP
communication
0x 0003
DSP task timeout
0x 0004
ARM-DSP
communication
Software events:
- Critical, will cause the unit to reset.
-Warning, then the event was
unexpected, but will sort itself out.
-Info, recording what happened in the
LRU.
(For software faults, there is no reason to
return box.)
0x 0020
thru
0x 007F
Other SW errors
0x 0001
Motor driver circuit
0x 0002
Ambient
0x 0001
Enter shed load
0x 0002
Exit shed load
0x 0011
LRU menu access maintenance
Software runtime
(FE)
Temperature (FF)
FMA (04)
Unknown (00)
- If is a warning, it is for info only.
- If it is critical, the LRU will shut down
functionally: suggest the LRU is not
correctly installed or there can be a fault
in the box generating the heat.
Info events - Recording what happened
in the LRU.
23-15-29
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Page 3-62
16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
FMA (04)
Unknown (00)
0x 0012
LRU menu access factory
Info events - Recording what happened
in the LRU
0x 0013
LRU menu access engineering
0x 0014
LRU SFTP access maintenance
0x 0015
LRU SFTP access factory
0x 0016
LRU SFTP access engineering
0x 0021
Log clearance LRU
operational
0x 0022
Log clearance LRU fault
0x 0081
Azimuth home find fail
0x 0082
Elevation home find fail
0x 0001
DSP fault
0x 0081
1.2V voltage
0x 0082
1.5V voltage
0x 0083
1.8V voltage
0x 0084
3.3V voltage
0x 0085
5V positive voltage
0x 0086
1.2V current
0x 0087
1.5V current
0x 0088
1.8V current
0x 0089
3.3V current
0x 008A
5V positive current
0x 0003
PSU low power
detected
0x 0004
PSU low power not
detected
0x 0005
PSU LNA current event
0x 0001
1.25V voltage
0x 0002
1.5V voltage
0x 0003
3.3V voltage
FMA (04)
Unknown (00)
Position Control
Unit (05)
PSU (06)
MDU (0B)
Info events - Recording what happened
in the LRU
Hardware faults and events:
- Replace the FMA.
23-15-29
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Page 3-63
16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
FMA (04)
MDU (0B)
0x 0004
12V positive voltage
0x 0005
12V negative voltage
Hardware faults and events:
- Replace the FMA.
0x 0006
38.5V voltage
0x 0007
1.5V current
0x 0008
3.3V current
0x 0009
12V positive current
0x 000A
12V negative current
0x 000B
Serial communications
failure
0x 000C
Azimuth motor current
0x 000D
Elevation motor current
0x 000E
Serial communications
failure
0x 000F
CCA initialization failed
0x 0010
Azimuth axis low
temperature high
current
0x 0001
1.5V voltage
0x 0002
3.3V voltage
0x 0003
5V digital voltage
0x 0004
5V positive voltage
0x 0005
5V negative voltage
0x 0006
12V positive voltage
0x 0007
12V negative voltage
0x 0008
1.5V current
0x 0009
3.3V current
0x 000A
12V positive current
0x 000B
12V negative current
0x 000F
Serial communications
failure
0x 0010
CCA initialization failed
0x 0011
Azimuth axis resolver
reading error
0x 0012
Elevation axis resolver
reading error
R2D (0C)
23-15-29
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Page 3-64
16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
FMA (04)
Operational
information (FA)
0x 0000
Mode transition
0x 0001
Parameter
Info events - Recording what happened
in the LRU
0x 0002
Event
0x 000A
Standard electronic
information
0x 000B
Honeywell electronic
information
0x 000C
Subassembly
information
IP security (FB)
0x 0000
IP security event
Reset (FC)
0x 0000
Power cycle
0x 0001
Watchdog
0x 0002
Software command
0x 0004
SW exception
0x 0001
HW SW Compatibility
0x 0002
LRU SW Compatibility
0x 0003
Configuration
parameter missing
Reload the configuration data with the
A615A data loading process.
0x 0004
Primary image
corruption warning
- Reboot the LRU to load valid primary
image and check if fault goes away.
- If not, then a fresh data load of software
is required to load the fresh image.
0x 0005
No Valid Image
Reload software with the A615A data
loading process.
0x 0006
LRU PRI-SEC image
mismatch
- Reboot the LRU to load valid primary
image and check if fault goes away.
- If not, then a fresh data load of software
is required to load the fresh image.
0x 0007
Data load
0x 0008
Data loader connect
0x 0009
Data loader disconnect
0x 000A
Operating image list
Unit configuration events:
- Critical, something needs to be done
(reload software).
- Warning, then the event was
unexpected, but will sort itself out.
- Info, recording what happened in the
LRU.
0x 000B
Secondary image
corruption warning
Software
configuration (FD)
Reload compatible software with the
A615A data loading process.
A fresh data load of software is required
to load the fresh image.
23-15-29
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Page 3-65
16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
FMA (04)
Software runtime
(FE)
0x 0000
Heartbeat failure
0x 0001
General module failure
0x 0020
File system full
0x 0021
thru
0x 007F
Other SW errors
Software events:
- Critical, will cause the unit to reset.
-Warning, then the event was
unexpected, but will sort itself out.
-Info, recording what happened in the
LRU.
(For software faults there is no reason to
return box.)
0x 0001
PCU CCA
0x 0004
R2D CCA
0x 0005
MDU CCA
0x 0006
Azimuth Motor
0x 0007
Elevation Motor
Software
configuration (FD)
0x 0007
Data load
Operational
information (FA)
0x 000A
Standard electronic
information
0x 000B
Honeywell electronic
information
0x 0000
Mute State
0x 0001
Primary power
interruption
0x 0011
LRU menu access maintenance
0x 0012
LRU menu access factory
0x 0013
LRU menu access engineering
0x 0014
LRU SFTP access maintenance
0x 0015
LRU SFTP access factory
0x 0016
LRU SFTP access engineering
0x 0021
Log clearance LRU
operational
0x 0022
Log clearance LRU fault
0x 0020
ASC 1.2 V: Out-of-spec
Temperature (FF)
APM (05)
KANDU (06)
Unknown (00)
ASC (01)
- If is a warning, it is for info only.
- If it is critical the LRU will shut down
functionally: suggest the LRU is not
correctly installed or there can be a fault
in the box generating the heat.
Info events - Recording what happened
in the LRU
Hardware faults and events:
- Replace the KANDU.
23-15-29
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Page 3-66
16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
KANDU (06)
ASC (01)
0x 0021
ASC 1.5 V: Out-of-spec
0x 0022
ASC 1.8 V: Out-of-spec
Hardware faults and events:
- Replace the KANDU.
0x 0023
ASC 2.5 V: Out-of-spec
0x 0024
ASC 3.3 V: Out-of-spec
0x 0025
ASC 5.0 V: Out-of-spec
0x 0026
ASC 12 V input:
Out-of-spec
0x 0027
ASC 1.2 V current:
Out-of-spec
0x 0028
ASC 1.5 V current:
Out-of-spec
0x 0029
ASC 1.8 V current:
Out-of-spec
0x 002A
ASC 2.5 V current:
Out-of-spec
0x 002B
ASC 3.3 V current:
Out-of-spec
0x 002C
ASC 5 V current:
Out-of-spec
Power supply unit
(02)
0x 0000
Power supply out of
regulation
ASC (05)
0x 001A
RAM fault
ASC BITE EMIFA
(11)
0x 0000
EMIFA unresponsive
0x 0001
EMIFA incorrect data
0x 0002
EMIFA OK
0x 0003
EEPROM unresponsive
0x 0004
EEPROM Incorrect
Data
0x 0005
EEPROM OK
0x 0000
ARINC 429 IRS post
unresponsive
0x 0001
ARINC 429 IRS
incorrect data
0x 0002
ARINC 429 IRS post
OK
ASC BITE A429
IRS (12)
23-15-29
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
KANDU (06)
ASC BITE A429
AUX (13)
0x 0000
ARINC 429 AUX post
unresponsive
Hardware faults and events:
- Replace the KANDU.
0x 0001
ARINC 429 AUX
incorrect data
0x 0002
ARINC 429 AUX post
OK
0x 0000
Ethernet MDIO
unresponsive
0x 0001
Ethernet MDIO
unexpected data
0x 0002
Ethernet MDIO OK
0x 0000
Mode Transition
0x 0001
Parameter
0x 0002
Event
0x 000A
Standard electronic
information
0x 000B
Honeywell electronic
information
0x 000C
Subassembly
information
IP security (FB)
0x 0000
IP security event
Use well defined port and IP Address
Reset (FC)
0x 0001
Watchdog
0x 0002
Software command
Info events - Recording what happened
in the LRU.
0x 0004
SW exception
0x 0005
Power cycle or reset pin
0x 0001
HW SW Compatibility
0x 0002
LRU SW Compatibility
0x 0003
Configuration
parameter missing
Reload the configuration data with the
A615A data loading process.
0x 0004
Primary image
corruption warning
- Reboot the LRU to load valid primary
image and check if fault goes away.
- If not, then a fresh data load of software
is required to load the fresh image.
0x 0005
No Valid Image
Reload software with the A615A data
loading process.
ASC BITE
Ethernet switch
(14)
Operational
information (FA)
Software
configuration (FD)
Hardware faults and events:
- Replace the KANDU.
Info events - Recording what happened
in the LRU.
Reload compatible software with the
A615A data loading process.
23-15-29
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Page 3-68
16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
KANDU (06)
Software
configuration (FD)
0x 0006
LRU PRI-SEC image
mismatch
- Reboot the LRU to load valid primary
image and check if fault goes away.
- If not, then a fresh data load of software
is required to load the fresh image.
Software
configuration (FD)
0x 0007
Data load
0x 0008
Data loader connect
0x 0009
Data loader disconnect
0x 000A
Operating image list
Unit configuration events:
- If it is critical, something needs to be
done (reload software).
- If it is a warning, then the event was
unexpected, but will sort itself out.
- If it is info, recording what happened in
the LRU.
0x 000B
Secondary image
corruption warning
A fresh data load of software is required
to load the fresh image.
0x 0080
No valid alignment data
Reload the configuration data with the
A615A data loading process.
0x 0000
Heartbeat failure
0x 0001
General module failure
0x 0002
RSSI failure
0x 0003
OPENAmip failure
0x 0004
Pointing failure
Software events:
- Critical, will cause the unit to reset.
-Warning, then the event was
unexpected, but will sort itself out.
-Info, recording what happened in the
LRU.
(For software faults there is no reason to
return box.)
0x 0005
IMU failure
0x 0020
thru
0x 007F
Other SW errors
0x 0001
ASC main temperature
sensor
0x 0002
KANDU PSU remote
temperature
0x 0000
Ethernet no layer 1
Indicates nothing is connected:
- Check wiring between boxes.
- Check TX box is operating.
- Check RX box is operating.
0x 0001
Ethernet no traffic
Is a warning that on traffic has been seen
on the bus, but layer 1 is established so a
physical link exists
0x 0002
Ethernet high packet
loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Ethernet normal
System is good.
Software runtime
(FE)
Temperature (FF)
Modman
KANDU
Ethernet bus
(20)
Modman input
(01)
- If is a warning, it is for info only.
- If it is critical the LRU will shut down
functionally: suggest the LRU is not
correctly installed or there can be a fault
in the box generating the heat.
23-15-29
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Page 3-69
16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Modman
KANDU
Ethernet bus
(20)
KANDU input (02)
0x 0000
Ethernet no layer 1
Indicates nothing is connected:
- Check wiring between boxes.
- Check TX box is operating.
- Check RX box is operating.
0x 0001
Ethernet no traffic
Is a warning that on traffic has been seen
on the bus, but layer 1 is established so a
physical link exists.
0x 0002
Ethernet high packet
loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Ethernet normal
System is good.
0x 0001
APM serial inactive
Is a warning that on traffic has been seen
on the bus:
- Far end is not talking.
- Wiring problem.
- Input problem.
0x 0003
APM serial normal
System is good.
Reset (01)
0x 0002
Input output mismatch
Modman fault
ARINC TX Mute
(02)
0x 0002
Input output mismatch
Modman fault
0x 0003
Modman/KANDU input
output mismatch
Modman/KRFU wiring fault
Filter Select (03)
0x 0002
Input output mismatch
Modman fault
0x 0003
Modman/KANDU input
output mismatch
Modman/KRFU wiring fault
Keyline Transmit
(04)
0x 0002
Input output mismatch
Modman fault
BUC mute (04)
0x 0003
Modman/KANDU input
output mismatch
Modman/KRFU wiring fault
System available
(05)
0x 0002
Input output mismatch
Modman fault
Data link available
(06)
0x 0002
Input output mismatch
Modman fault
KANDU input (01)
0x 0000
Ethernet no layer 1
Indicates nothing is connected:
- Check wiring between boxes.
- Check TX box is operating.
- Check RX box is operating.
0x 0001
Ethernet no traffic
Is a warning that on traffic has been seen
on the bus, but layer 1 is established so a
physical link exists
0x 0002
Ethernet high packet
loss
There is an intermittent wiring problem or
hardware fault.
Modman APM
Serial Bus (21)
Modman
Output:
Discretes from
Modman (24)
KANDU OAE
Ethernet Bus
(30)
Modman input
(01)
23-15-29
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Page 3-70
16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
KANDU OAE
Ethernet Bus
(30)
KANDU input (01)
0x 0003
Ethernet normal
System is good.
OAE input (02)
0x 0000
Ethernet no layer 1
Indicates nothing is connected:
- Check wiring between boxes.
- Check TX box is operating.
- Check RX box is operating.
0x 0001
Ethernet no traffic
Is a warning that on traffic has been seen
on the bus, but layer 1 is established so a
physical link exists.
0x 0002
Ethernet high packet
loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Ethernet normal
System is good.
0x 0001
Serial Inactive
Is a warning that on traffic has been seen
on the bus:
- Far end is not talking.
- Wiring problem.
- Input problem.
0x 0002
Serial High packet loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Serial Normal
System is good.
0x 0001
Serial Inactive
Is a warning that on traffic has been seen
on the bus:
- Far end is not talking.
- Wiring problem.
- Input problem.
0x 0002
Serial High packet loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Serial Normal
System is good.
0x 0001
Serial Inactive
Is a warning that on traffic has been seen
on the bus:
- Far end is not talking.
- Wiring problem.
- Input problem.
0x 0002
Serial High packet loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Serial Normal
System is good.
0x 0001
Serial Inactive
Is a warning that on traffic has been seen
on the bus:
- Far end is not talking.
- Wiring problem.
- Input problem.
0x 0002
Serial High packet loss
There is an intermittent wiring problem or
hardware fault.
KANDU OAE
Serial Control
Bus (31)
KANDU input (01)
OAE input (02)
KANDU OAE
Serial IMU Bus
(32)
KANDU input (01)
OAE input (02)
23-15-29
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16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
KANDU OAE
Serial IMU Bus
(32)
OAE input (02)
0x 0003
Serial Normal
System is good.
KANDU KRFU
Serial Bus (33)
KANDU input (01)
0x 0001
Serial Inactive
Is a warning that on traffic has been seen
on the bus:
- Far end is not talking.
- Wiring problem.
- Input problem.
0x 0002
Serial High packet loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Serial Normal
System is good.
0x 0001
Serial Inactive
Is a warning that no traffic has been seen
on the bus:
- Far end is not talking.
- Wiring problem.
- Input problem.
0x 0002
Serial High packet loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Serial Normal
System is good.
0x 0001
Mute line not asserting
at 180
Check the FMA, FMA to KANDU wiring
and the KANDU
0x 0002
Mute line asserting at 0
0x 0000
Asserted
0x 0001
De-asserted
ARINC TX mute
(02)
0x 0000
Asserted
0x 0001
De-asserted
Filter Select (03)
0x 0000
Asserted
0x 0001
De-asserted
0x 0000
Asserted
0x 0001
De-asserted
0x 0000
Asserted
0x 0001
De-asserted
0x 0000
Asserted
0x 0001
De-asserted
0x 0003
KRFU not muted during
system test
KRFU input (02)
KANDU Input:
Discretes from
OAE (34)
FMA transmit
mute (01)
KANDU Input:
Discretes from
Modman (35)
Reset (01)
TX Mute (04)
KRFU Input
Discrete from
KANDU (41)
Reset (01)
KRFU TX mute
(02)
System interconnect:
Is a Debug aid to allow maintainer or
installer to see inputs on various boxes
on system interconnect.
If not working correctly:
- Check cables.
- Check TX LRU.
- Check RX LRU.
23-15-29
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Page 3-72
16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
KRFU Input
Discrete from
KANDU (41)
Filter Select (03)
0x 0000
Asserted
0x 0001
De-asserted
System interconnect:
Is a Debug aid to allow maintainer or
installer to see inputs on various boxes
on system interconnect.
If not working correctly:
- Check cables.
- Check TX LRU.
- Check RX LRU.
IRU Input Bus
(70)
Unknown (00)
0x 0000
Inactive link
Aircraft Interconnect.
Means no labels on the bus:
- Check wiring
- Check source
- Check KANDU and Modman.
Pitch angle label
(01)
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
23-15-29
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
IRU Input Bus
(70)
Roll angle label
(02)
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
Pitch rate label
(03)
23-15-29
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
IRU Input Bus
(70)
Pitch rate label
(03)
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
Pitch rate label
(03)
Roll rate label (04)
23-15-29
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
IRU Input Bus
(70)
Roll rate label (04)
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
Yaw rate label (05)
Body longitudinal
acceleration (06)
23-15-29
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
IRU Input Bus
(70)
Body longitudinal
acceleration (06)
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
Body vertical
acceleration (07)
23-15-29
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
IRU Input Bus
(70)
Body vertical
acceleration (07)
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
True heading label
(08)
23-15-29
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
IRU Input Bus
(70)
Body lateral
acceleration (09)
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
Latitude label (11)
23-15-29
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
IRU Input Bus
(70)
Latitude label (11)
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
Longitude label
(12)
23-15-29
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16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
IRU Input Bus
(70)
Longitude label
(12)
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
Altitude (13)
23-15-29
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
IRU Input Bus
(70)
Vertical velocity
(14)
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
Blank Page
N-S velocity (15)
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
23-15-29
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Page 3-82
16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
IRU Input Bus
(70)
N-S velocity (15)
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
E-W velocity (16)
23-15-29
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
IRU Input Bus
(70)
E-W velocity (16)
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
Horizontal
stabilization (21)
23-15-29
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16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
IRU Input Bus
(70)
Time label (31)
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
Date label (32)
23-15-29
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16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
IRU Input Bus
(70)
Date label (32)
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
Flight phase (41)
23-15-29
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16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
IRU Input Bus
(70)
Flight phase (41)
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0000
Self test mode
Will be available in future revision
0x 0001
Initialization mode
0x 0002
Acquisition mode
0x 0003
Navigational mode
0x 0004
Attitude aiding mode
MLG ground
condition (42)
GNSS sensor
status word (80)
23-15-29
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
IRU Input Bus
(70)
GNSS sensor
status word (80)
0x 0007
Fault
Will be available in future revision
IRS discrete word
(81)
0x 0000
Align mode/Not ready
0x 0001
Revisionary altitude
mode
0x 0002
Normal mode
Unknown (00)
0x 0000
Inactive link
Aircraft Interconnect.
Means we see no labels on the bus:
- Check wiring
- Check source
- Check KANDU and Modman.
Pitch angle label
(01)
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
Aircraft State
Input Bus (71)
23-15-29
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Aircraft State
Input Bus (71)
Roll angle label
(02)
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
Pitch rate label
(03)
23-15-29
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16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Aircraft State
Input Bus (71)
Pitch rate label
(03)
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
Blank
SSM
NOPage
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
Roll rate label (04)
23-15-29
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16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Aircraft State
Input Bus (71)
Roll rate label (04)
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
Yaw rate label (05)
23-15-29
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16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Aircraft State
Input Bus (71)
Body longitudinal
acceleration (06)
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
Body vertical
acceleration (07)
23-15-29
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Page 3-92
16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Aircraft State
Input Bus (71)
Body vertical
acceleration (07)
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
True heading label
(08)
23-15-29
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16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Aircraft State
Input Bus (71)
True heading label
(08)
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
Body lateral
acceleration (09)
23-15-29
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16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Aircraft State
Input Bus (71)
Latitude label (11)
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, system will continue to
operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
Longitude label
(12)
23-15-29
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16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Aircraft State
Input Bus (71)
Longitude label
(12)
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
Altitude (13)
23-15-29
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16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Aircraft State
Input Bus (71)
Altitude (13)
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
Vertical velocity
(14)
23-15-29
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16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Aircraft State
Input Bus (71)
N-S velocity (15)
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
E-W velocity (16)
23-15-29
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16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Aircraft State
Input Bus (71)
E-W velocity (16)
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
Horizontal
stabilization (21)
23-15-29
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16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Aircraft State
Input Bus (71)
Horizontal
stabilization (21)
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
Time label (31)
23-15-29
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16 Sep 2015
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Aircraft State
Input Bus (71)
Date label (32)
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
Flight phase (41)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Aircraft State
Input Bus (71)
Flight phase (41)
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0001
Missing
Expected label is not there:
- Make sure that the system configuration
expects the correct label.
- Check aircraft system is supplying the
correct label on the bus.
If fault is critical, the system will not work.
If fault is a warning, the label is expected
but not there, the system will continue to
operate.
0x 0002
SSM FT
Expected label is in functional test:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0003
SSM NCD
Expected label is in no computed data:
This is expected, but is recorded as a
debug aid.
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
MLG ground
condition (42)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
Aircraft State
Input Bus (71)
MLG ground
condition (42)
0x 0004
SSM FW
Expected label is in failure warning:
If a fault is critical, the system will not
work.
If the fault is a warning, the label is
expected but not there, system will
continue to operate.
0x 0005
SSM NO
Normal operation, system is good.
0x 0000
Self test mode
Will be available in future revision
0x 0001
Initialization mode
0x 0002
Acquisition mode
0x 0003
Navigational (normal)
mode
0x 0004
Altitude aiding mode
0x 0007
Fault
0x 0000
Asserted
0x 0001
De-asserted
0x 0000
Asserted
0x 0001
De-asserted
Ground transmit
enable (08)
0x 0000
Asserted
0x 0001
De-asserted
Public Svr disable
(09)
0x 0000
Asserted
0x 0001
De-asserted
Remote manager
(0A)
0x 0000
Asserted
0x 0001
De-asserted
Cooling available
(0B)
0x 0000
Asserted
0x 0001
De-asserted
Local data load
(0C)
0x 0000
Asserted
0x 0001
De-asserted
TX control (0C)
0x 0000
Asserted
0x 0001
De-asserted
GNSS sensor
status word (80)
Modman
Aircraft
Discrete Input
(72)
KANDU
Aircraft
Discrete Input
(73)
WOW (06)
Cell TX OK (07)
Aircraft interconnect:
This is an aid to installation. Lets the
installer and /or maintainer check the
system to see the state of the lines
coming into it.
- If not tracking,
-- Check the interconnect and what is
driving it.
-- Check the KANDU or Modman for error
on input not working.
Aircraft interconnect:
This is an aid to installation. Lets the
installer and /or maintainer check the
system to see the state of the lines
coming into it.
- If not tracking,
-- Check the interconnect and what is
driving it.
-- Check the KANDU or Modman for error
on input not working.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
AISD Network:
Ethernet AG1
(80)
Modman Input
(01)
0x 0000
Ethernet no layer 1
Indicates nothing is connected:
- Check wiring between boxes.
- Check TX box is operating.
- Check RX box is operating.
0x 0001
Ethernet no traffic
Is a warning that on traffic has been seen
on the bus, but layer 1 is established so a
physical link exists.
0x 0002
Ethernet high packet
loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Ethernet normal
System is good.
0x 0000
Ethernet no layer 1
Indicates nothing is connected:
- Check wiring between boxes.
- Check TX box is operating.
- Check RX box is operating.
0x 0001
Ethernet no traffic
Is a warning that on traffic has been seen
on the bus, but layer 1 is established so a
physical link exists.
0x 0002
Ethernet high packet
loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Ethernet normal
System is good.
0x 0000
Ethernet no layer 1
Indicates nothing is connected:
- Check wiring between boxes.
- Check TX box is operating.
- Check RX box is operating.
0x 0001
Ethernet no traffic
Is a warning that on traffic has been seen
on the bus, but layer 1 is established so a
physical link exists.
0x 0002
Ethernet high packet
loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Ethernet normal
System is good.
0x 0000
Ethernet no layer 1
Indicates nothing is connected:
- Check wiring between boxes.
- Check TX box is operating.
- Check RX box is operating.
0x 0001
Ethernet no traffic
Is a warning that on traffic has been seen
on the bus, but layer 1 is established so a
physical link exists.
0x 0002
Ethernet high packet
loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Ethernet normal
System is good.
AISD Network:
Ethernet AV1
(81)
AISD Network:
Ethernet AV2
(82)
AISD Network:
Ethernet AV3
(83)
Modman Input
(01)
Modman Input
(01)
Modman Input
(01)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
PIESD
Network:
Ethernet EG1
(88)
Modman Input
(01)
0x 0000
Ethernet no layer 1
Indicates nothing is connected:
- Check wiring between boxes.
- Check TX box is operating.
- Check RX box is operating.
0x 0001
Ethernet no traffic
Is a warning that on traffic has been seen
on the bus, but layer 1 is established so a
physical link exists.
0x 0002
Ethernet high packet
loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Ethernet normal
System is good.
0x 0000
Ethernet no layer 1
Indicates nothing is connected:
- Check wiring between boxes.
- Check TX box is operating.
- Check RX box is operating.
0x 0001
Ethernet no traffic
Is a warning that on traffic has been seen
on the bus, but layer 1 is established so a
physical link exists.
0x 0002
Ethernet high packet
loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Ethernet normal
System is good.
0x 0000
Ethernet no layer 1
Indicates nothing is connected:
- Check wiring between boxes.
- Check TX box is operating.
- Check RX box is operating.
0x 0001
Ethernet no traffic
Is a warning that on traffic has been seen
on the bus, but layer 1 is established so a
physical link exists.
0x 0002
Ethernet high packet
loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Ethernet normal
System is good.
0x 0000
Ethernet no layer 1
Indicates nothing is connected:
- Check wiring between boxes.
- Check TX box is operating.
- Check RX box is operating.
0x 0001
Ethernet no traffic
Is a warning that on traffic has been seen
on the bus, but layer 1 is established so a
physical link exists.
0x 0002
Ethernet high packet
loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Ethernet normal
System is good.
PIESD
Network:
Ethernet EN5
(89)
PIESD
Network:
Ethernet EN6
(8A)
PIESD
Network:
Ethernet EN7
(8B)
Modman Input
(01)
Modman Input
(01)
Modman Input
(01)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
PIESD
Network:
Ethernet EN8
(8C)
Modman Input
(01)
0x 0000
Ethernet no layer 1
Indicates nothing is connected:
- Check wiring between boxes.
- Check TX box is operating.
- Check RX box is operating.
0x 0001
Ethernet no traffic
Is a warning that on traffic has been seen
on the bus, but layer 1 is established so a
physical link exists.
0x 0002
Ethernet high packet
loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Ethernet normal
System is good.
0x 0000
Ethernet no layer 1
Indicates nothing is connected:
- Check wiring between boxes.
- Check TX box is operating.
- Check RX box is operating.
0x 0001
Ethernet no traffic
Is a warning that on traffic has been seen
on the bus, but layer 1 is established so a
physical link exists.
0x 0002
Ethernet high packet
loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Ethernet normal
System is good.
0x 0000
Ethernet no layer 1
Indicates nothing is connected:
- Check wiring between boxes.
- Check TX box is operating.
- Check RX box is operating.
0x 0001
Ethernet no traffic
Is a warning that on traffic has been seen
on the bus, but layer 1 is established so a
physical link exists.
0x 0002
Ethernet high packet
loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Ethernet normal
System is good.
0x 0000
Ethernet no layer 1
Indicates nothing is connected:
- Check wiring between boxes.
- Check TX box is operating.
- Check RX box is operating.
0x 0001
Ethernet no traffic
Is a warning that on traffic has been seen
on the bus, but layer 1 is established so a
physical link exists.
0x 0002
Ethernet high packet
loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Ethernet normal
System is good.
PODD
Network:
Ethernet PG1
(90)
PODD
Network:
Ethernet PA1
(91)
PODD
Network:
Ethernet PA2
(92)
Modman Input
(01)
Modman Input
(01)
Modman Input
(01)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Table 3-20. L3 Codes (Cont)
L1
L2
L3 Code
L3 Description
Repair Action
PODD
Network:
Ethernet PA3
(93)
Modman Input
(01)
0x 0000
Ethernet no layer 1
Indicates nothing is connected:
- Check wiring between boxes.
- Check TX box is operating.
- Check RX box is operating.
0x 0001
Ethernet no traffic
Is a warning that on traffic has been seen
on the bus, but layer 1 is established so a
physical link exists.
0x 0002
Ethernet high packet
loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Ethernet normal
System is good.
0x 0000
Ethernet no layer 1
Indicates nothing is connected:
- Check wiring between boxes.
- Check TX box is operating.
- Check RX box is operating.
0x 0001
Ethernet no traffic
Is a warning that on traffic has been seen
on the bus, but layer 1 is established so a
physical link exists.
0x 0002
Ethernet high packet
loss
There is an intermittent wiring problem or
hardware fault.
0x 0003
Ethernet normal
System is good.
0x 0001
TX IF
0x 0002
50 MHz Ref
Check the interconnecting RF connection
between the Modman and KRFU LRUs.
PODD
Network:
Ethernet PA4
(94)
Modman Input
(01)
RF TX
Modman to
KRFU (B0)
Unknown (00)
RF TX KRFU
to OAE (B1)
Unknown (00)
0x 0001
TX Ka Band
Check the interconnecting RF connection
between the KRFU and OAE LRUs.
RF RX (B2)
Unknown (00)
0x 0001
RX cabling
Check the interconnecting RF connection
between the effected LRUs.
14.
SNMP
Refer to APPENDIX B on page B-1 for MIB and SNMP information and instructions.
23-15-29
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Blank Page
23-15-29
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
APPENDIX A
1.
RTCA/DO-160G Environmental Characteristics
A.
Modman
Section
Condition
Category
Temperature and altitude
A1(V)
NOTE: Below 5˚F (-15˚C), user services are not offered. Altitude test extended to 50,000 feet
(15,240 m). Overpressure 28.9 PSI (199 kPa), Decompression 6,000 to 55,000 (1828.8 to
16,764 m) in 2 seconds.
Temperature variation
Humidity
Operational shocks and crash safety
Vibration
CAT S, CURVE B2
Explosive atmosphere
X - not required
10
Waterproofness
11
Fluids specification
X - not required
12
Sand and dust
X - not required
13
Fungus resistance
14
Salt fog
X - not required
15
Magnetic effect
16
Power input
A (WF) HLPI
NOTE: Extended low frequency operation to 320 Hz.
17
Voltage spike
NOTE: Extended to 1,000 volts.
18
Audio frequency conducted susceptibility
NOTE: Amplitude of applied signal to be 10% of nominal AC voltage.
19
Induced signal susceptibility
ZW
NOTE: Extended low frequency operations to 320 Hz.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Section
Condition
Category
20
Radio frequency susceptibility
RR (custom)
NOTE:
Radiated: Additional subjections
SW: 0.4 to 8 GHz: 28 V/m (1 kHz square mod with greater than 90% depth switched on and off
at 1 Hz rate and 50% duty cycle).
PM: 0.4 to 8 GHz: 150 V/m (Pulse repetition frequency of 1 kHz and a duty cycle of 1%, switched
on and off at 1 Hz rate and 50% duty cycle). Pulse width is 10 µsec (1% of 1 kHz).
PM: 0.3 to 6 GHz: 20 V/m, (Pulse repetition frequency of 200 Hz and a duty cycle of 12.5%).
Pulse width is 625 μsec (12.5% of 200Hz).
21
Emissions of RF energy
22
Lightning induced transient susceptibility
A2K2L3
NOTE: Modified to extend single stroke to waveform 3 level 3 and multi-stroke to waveform 4
level 2.
23
Lightning direct effects
X - not required
24
Icing
X - not required
25
Electrostatic discharge
26
Fire, flammability
C - covers 14 CFR 25.853
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
B.
APM
Section
Condition
Category
Temperature and altitude
A1(V)
NOTE: Altitude test extended to 50,000 feet (15,240 m). Overpressure 28.9 PSI (199 kPa),
Decompression 6,000 to 55,000 (1828.8 to 16,764 m) in 2 seconds.
Temperature variation
Humidity
Operational shocks and crash safety
Vibration
CAT S, CURVE B2
Explosive atmosphere
X - not required
10
Waterproofness
11
Fluid susceptibility
X - not required
12
Sand and dust
X - not required
13
Fungus resistance
14
Salt fog
X - not required
15
Magnetic effect
16
Power input
X - not required
17
Voltage spike
X - not required
18
Audio frequency conducted susceptibility
X - not required
19
Induced signal susceptibility
ZC
20
Radio frequency susceptibility
RR
21
Emissions of RF energy
22
Lightning induced transient susceptibility
A2K2L3
NOTE: Modified to extend single stroke to waveform 3 level 3 and multi-stroke to waveform 4
level 2.
23
Lightning direct effects
X - not required
24
Icing
X - not required
25
Electrostatic discharge
26
Fire, flammability
C - covers 14 CFR 25
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
C.
KANDU
Section
Condition
Category
Temperature and altitude
D2
NOTE: Altitude test extended to 51,000 feet (15,544.8 m). Overpressure 28.9 PSI (199 kPa),
Decompression 6,000 to 55,000 (1,828.8 to 16,764.0 m).
Temperature variation
Humidity
Operational shocks and crash safety
E and B
Vibration
CAT R, CURVE E
CAT R, CURVE E1
NOTE: The sinusoidal sweep rate not to exceed 0.5 octaves/minute.
Explosive atmosphere
10
Waterproofness
Y and R
11
Fluid susceptibility
NOTE: De-ice Ethylene Glycol, Hydraulic fluid phosphate ester AS1241 Type IV and V.
12
Sand and dust
13
Fungus resistance
14
Salt fog
15
Magnetic effect
16
Power input
A (WF) HZPI
NOTE: Extended low frequency operation to 320 Hz.
NOTE: Power factor – leading greater than 0.98.
17
Voltage spike
A (modified to 1,000 volts)
18
Audio frequency conducted susceptibility
K (WF)
NOTE: RMS amplitude of the audio signal extended to not less than 10% of the maximum normal
AC input voltage and with a power source frequency of 320 Hz in addition to 360 Hz and 800 Hz.
19
Induced signal susceptibility
CW
NOTE: Extended low frequency operation to 320 Hz.
NOTE: With current and distance modified to 50 A at a distance of 0.4 inch (10 mm) for section
19.3.1.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Section
Condition
Category
20
Radio frequency susceptibility
RY
NOTE:
- 0.4 to 8 GHz: 150 V/m (Pulse repetition frequency of 1 kHz and a duty cycle of 1%, switched
on and off at a 1 Hz rate and 50% duty cycle). Pulse width is 10 μsec (1% of 1 kHz).
- 0.3 to 6 GHz: 20 V, (Pulse repetition frequency of 200 Hz and a duty cycle of 12.5%). Pulse
width is 625 μsec (12.5% of 200 Hz).
21
Emissions of RF energy
NOTE:
Extension of conducted emissions limits to 200 MHz at 20 dBμA and power line limits from 30
MHz to 108 MHz at 20 dBμA.
Extension of radiated emissions to start at 45 dBμV/m at 150 kHz to 40 dBμV/m at 2 MHz, and
at 30 dBμV/m at 2 MHz to 25 dBμV/m at 25 MHz, and at 25 dBμV/m at 25 MHz to 26.3 dBμV/m
at 30 MHz, and at 36.3 dBμV/m at 30 MHz to 44.5 dBμV/m at 100 MHz.
All conducted emissions limits, including interconnecting bundles limits, are set in accordance
with Category Q power line limit levels.
22
Lightning induced transient susceptibility
A3K3L3
NOTE: Extended to include pin injection waveform 5A level 2.
23
Lightning direct effects
X - not required
24
Icing
25
Electrostatic discharge
26
Fire, flammability
C - covers 14 CFR 25.853
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
D.
KRFU
Section
Condition
Category
Temperature and altitude
D2
NOTE: Altitude test extended to 51,000 feet (15,544.8 m). Overpressure 28.9 PSI (199 kPa),
Decompression 6,000 to 55,000 (1,828.8 to 16,764.0 m).
Temperature variation
Humidity
NOTE: At least six spot checks required.
Operational shocks and crash safety
Vibration
E and B
CAT R, CURVE E
CAT R, CURVE E1
NOTE: The sinusoidal sweep rate not to exceed 0.5 octaves/minute.
Explosive atmosphere
10
Waterproofness
Y and R
11
Fluid susceptibility
NOTE: Ethylene Glycol, Propylene Glycol, AEA Type 1, AEA Type 2.
12
Sand and dust
13
Fungus resistance
14
Salt fog
15
Magnetic effect
16
Power input
A (WF) HZPI
NOTE: Extended low frequency operation to 320 Hz.
NOTE: Power Factor – leading greater than 0.98.
17
Voltage spike
A (modified to 1,000 volts)
18
Audio frequency conducted susceptibility
K (WF)
NOTE: RMS amplitude of the audio signal extended to not less than 10% of the maximum normal
AC input voltage and with a power source frequency of 320 Hz in addition to 360 Hz and 800 Hz.
19
Induced signal susceptibility
CW
NOTE: Extended low frequency operation to 320 Hz.
NOTE: Section 19.3.1 performed with 50 A at a distance of 0.4 inch (10 mm).
23-15-29
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Section
Condition
Category
20
Radio frequency susceptibility
MY
NOTEL:
- 0.4 to 8 GHz: 150 V/m (Pulse repetition frequency of 1 kHz and a duty cycle of 1%, switched
on and off at a 1 Hz rate and 50% duty cycle). Pulse width is 10 μsec (1% of 1 kHz).
- 0.3 to 6 GHz: 20 V/m, (Pulse repetition frequency of 200 Hz and a duty cycle of 12.5%). Pulse
width is 625 μsec (12.5% of 200 Hz).
21
Emissions of RF energy
NOTE:
Extension of conducted emissions limits to 200 MHz at 20 dBμA and power line limits from
30MHz to 108MHz at 20 dBμA.
Extension of radiated emissions to start at 45 dBμV/m at 150 kHz to 40 dBμV/m at 2 MHz, and
at 30 dBμV/m at 2 MHz to 25 dBμV/m at 25 MHz, and at 25 dBμV/m at 25 MHz to 26.3 dBμV/m
at 30 MHz, and at 36.3 dBμV/m at 30 MHz to 44.5 dBμV/m at 100 MHz.
22
Lightning induced transient susceptibility
A3K3L3
NOTE: Extended to include pin injection waveform 5A level 2.
23
Lightning direct effects
X - not required
24
Icing
25
Electrostatic discharge
26
Fire, flammability
C - covers 14 CFR 25.853
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
E.
TMA
Section
Condition
Category
Temperature and altitude
F2
Temperature variation
Humidity
Operational shocks and crash safety
Vibration
CAT R, CURVE E
CAT R, CURVE E1
Explosive atmosphere
E and H
10
Waterproofness
Y and W
11
Fluid susceptibility
F (de-icing fluids)
NOTE: Ethylene Glycol.
12
Sand and dust
13
Fungus resistance
14
Salt fog
15
Magnetic effect
16
Power input
X - not required
17
Voltage spike
NOTE: Do DO-160G/17.0 on TMA with the KANDU attached as the UUT.
The length of test cable between TMA and KANDU shall be 40 ft (12 m).
18
Audio frequency conducted susceptibility
NOTE:
A. Frequency range from 324 Hz to 650 Hz.
B. Do DO-160G/18.0 on TMA with the KANDU attached as the UUT.
The length of test cable between TMA and KANDU shall be 40 ft (12 m).
19
Induced signal susceptibility
ZC
20
Radio frequency susceptibility
YQ (custom)
NOTE: Q (custom) only - SW/CW (un-modulated) signal Operational:
200V/m for 100 MHz to 12 GHz
0.1 V/m 12 GHz to 16.6 GHz
No damage:
200V/m for 12 GHz to 16.6 GHz
0.1 V/m for 16.6 GHz to 18 GHz
21
Emissions of RF energy
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Section
Condition
Category
22
Lightning induced transient susceptibility
A3K3L3 modified
NOTE: Pin Injection waveform 5A level 2. Single stroke WF 4, level 3 (extended to 300V/1000A),
Multi-stroke WF4 level 3 (extended to 120V/400A 1st stroke, 75V/150A subsequent strokes),
Extend WF5A level 3 (extended 120V/400A 1st stroke, 75V/150A subsequent strokes).
23
Lightning direct effects
X - not required
24
Icing
25
Electrostatic discharge
26
Fire, flammability
C - covers 4 CFR 25.853
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F.
FMA
Section
Condition
Category
Temperature and altitude
F2
NOTE: Extended operating high to 194˚F (90˚C).
Temperature variation
Humidity
NOTE: At least six spot checks are required.
Operational shocks and crash safety
B and E
Vibration
CAT S, CURVE C
CAT R, CURVE C1
NOTE: The sinusoidal sweep rate not to exceed 0.5 octaves/minute
Explosive atmosphere
10
Waterproofness
Y and W
11
Fluid susceptibility - De-ice fluids only
12
Sand and dust
13
Fungus resistance
14
Salt fog
15
Magnetic effect
16
Power input
X - not required
17
Voltage spike
X - not required
18
Audio frequency conducted susceptibility
X - not required
19
Induced signal susceptibility
ZC
20
Radio frequency susceptibility
YQ
NOTE: Q (custom) only - SW/CW (un-modulated) signal Operational:
200V/m for 100 MHz to 12 GHz
0.1 V/m 12 GHz to 16.6 GHz
No damage:
200V/m for 12 GHz to 16.6 GHz
0.1 V/m for 16.6 GHz to 18 GHz
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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Section
Condition
Category
21
Emissions of RF energy
NOTE:
Extension of conducted emissions limits to 200 MHz at 20 dBμA and power line limits from
30MHz to 152MHz at 20 dBμA.
All conducted emissions limits, including interconnecting bundles limits, are set in accordance
with Category H power line limit levels.
Radiated emissions to start at 40 dBμV/m at 2 MHz to 35 dBμV/m at 25 MHz, and at 35 dBμV/m
at 25 MHz to 44.6 dBμV/m at 100 MHz
22
Lightning induced transient susceptibility
A3K3L3
NOTE: Pin Injection waveform 5A level 125V/125A and 400V/4A. Single stroke WF 4, level 3
(extended to 300V/1000A), Multi-stroke WF4 level 3 (extended to 120V/400A 1st stroke,
60V/120A subsequent strokes).
23
Lightning direct effects
X - not required
24
Icing
25
Electrostatic discharge
26
Fire, flammability
C - covers 14 CFR 25.853
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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APPENDIX B
1.
MIB Objects
A.
MIB Structure
(1)
SNMP applications can monitor the MIB objects. The Modman implements the Honeywell
engineering SNMP MIB with OIDs as shown in Figure B-1.
Figure B-1. MIB Object Structure
(2)
The Honeywell engineering SNMP service provides information to the external entity
covering two areas of concern, link/service status and maintenance/BITE status. The data is
provided through the SERVICE MIB and MAINTENANCE MIB.
(3)
Access to the branches on the MIB is controlled by having four levels of user access that
range from the lowest of “User” to ‘“Maintenance” followed by “Factory” and to the highest
level of “Engineering”. The “User” level is not password protected but the other levels require
a password to access the services. To access the User or Maintenance levels do as follows:
• Access the user interface with Username: "User" and no password.
• Access maintenance interface with Username: "Maintenance" and Password:
"Earthbound".
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B.
Detailed MIB Definition
(1)
Object Types
This section describes all the special object types in individual sections and tables, which are
not defined in the SNMP and MIB standard.
(a)
Link Status Type Definician
The SNMP Type HonAkSatLinkState reports the network link state and link state of the
terminal. It is an enumerated integer value with the structure shown in Table B-1.
Table B-1. Link Status Related Object
SNMP Type
inNetwork
inAcquisition
waitingForAcquisition
Detected
waiting For Rx Lock
rxOnly
wrongNetwork
Unavailable
Fault
notActive
userServiceDisabledRegulatoryLogs
Number
10
11
serviceDisabled
12
(b)
Description
In network (service is available)
In acquisition mode (modem state transition)
Waiting for acquisition (modem state transition)
Link detected (modem state transition)
Waiting for RX lock (modem state transition)
RX only (modem state transition)
Wrong Network accessed
Link status unavailable
AES is in critical fault mode
Modem not active yet
User service is disabled due to failure to upload regulatory logs
– System will be active only to try and upload the logs
Service is disabled – see AKMuteStateReason
Temporary Service Unavailable Reason Type Definition
The temporary service unavailable reason will be reflected by the type
honAkServUnavailReason. It is an enumerated integer value with the structure shown
in Table B-2.
Table B-2. Temporary Service Enumeration Types
SNMP Type
undefined (1)
Number
startingUp (2)
shortWithSelfRecovery (3)
blockageZone (4)
indefinite (5)
onGroundMute(6)
geographicRestrictions (7)
noLineOfSight(8)
Description
Default state
System is in Boot state or communication has not established
between LRUs
Service unavailable as Cabin attempt to hold services due to
RF blockage, Handover, power interruptions
Blockage Zone
Service unavailable as Crew Muted using TX Control discrete
If landing Terminate any existing services on JetWave™,
choose an alternative path while on ground, monitor for state
change, If takeoff, services were never set up
Service restricted because of Geographical constraints.
Link loss due to antenna in key hole situation, insufficient
elevation to the satellite or any other equivalent
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(c)
Health Status Type definition
The SNMP type HonAkHealthStatus report the health status of the AES. It is an
enumerated integer value with the structure as shown in Table B-3.
Table B-3. Health Status Enumeration Type
Number
SNMP Type
normal
warning
failed
Unavailable
(d)
Description
The item is OK
The item is in WARNING
The item has FAILED
LRU only, not AES: The LRU health state is not available
Thermal State Definitian
The SNMP Type HonAkThermalState reports the thermal status of the Modman. It is an
enumerated integer value with the structure as shown in Table B-4.
Table B-4. Thermal State Enumeration Type
Number
SNMP Type
normal
warning
critical
(e)
Description
The unit is functioning within its normal operating temperature
range
The unit is functioning but outside of its normal operating
temperature range
The unit is critical and may be in shutdown due to operating
outside of its normal operating temperature range
Discrete Input State Type Definition
The SNMP type HonAkDiscreteInputState reports the value of the input discrete. It is an
enumerated integer value with the structure as shown in Table B-5.
Table B-5. Discrete Input State Enumeration Type
SNMP Type
Ground
Number
Open
(f)
Description
Discrete is in the ground state – requirement text indicates
what ground state means for a particular discrete.
Discrete is in the open state.
Discrete Output State Type definition
The SNMP type HonAkDiscreteOutputState reports the value of the output discrete. It
is an enumerated integer value with the structure as shown in Table B-6.
Table B-6. Discrete Output State Enumeration Type
SNMP Type
ground
open
Fail
Number
Description
Discrete is in the ground state
Discrete is in the open state.
Failed to set output discrete
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(g)
Tenths Unsigned32 Type definition
The SNMP type HonAkTenthsUnsigned32 cause an Unsigned32 that expresses
something in tenths to be displayed in a floating point way.
• For example, consider the case where an object that uses this TC and contains a
value of '1234'. This object would be displayed as '123.4'.
(h)
Tenths Integer32 Type definition
The SNMP type HonAkTenthsInteger32 cause an Integer32 that expresses something
in tenths to be displayed in a floating point way.
• For example, consider the case where an object that uses this TC and contains a
value of '-1234'. This object would be displayed as '-123.4'.
(i)
IRS Status definition
The SNMP honAkIrsStatus reports the IRS status. It is an enumerated integer value with
the structure as shown in Table B-7.
Table B-7. IRS Status Enumeration Type
SNMP Type
ok
IRS Aligning
IRS Inactive
IRS Fail
Number
(j)
Description
IRS is active and OK
IRS is in alignment
IRS is not active and not reporting data
IRS has indicated failure
Mute Reason Type definition
The SNMP honAkTxMutedReason report the reason the terminal has self muted. It is
an enumerated integer value with the structure as shown in Table B-8.
Table B-8. Mute Reason Enumeration Type
SNMP Type
notMuted(1)
skewAngle(2)
notLocked(3)
notPointing(4)
structureBlockage(5)
onGround(6)
fault(7)
notReady(8)
geoRestriction(9)
Number
Description
Not muted, transmitting
Muted because skew angle exceeds regulatory limits
Not locked
Not currently pointed
Aircraft structure blockage
On-ground
Fault
Not Ready for operation, booting etc
Service is disabled due to Geographic position inside a
restricted region
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(k)
Satellite Handover Type definition
The SNMP honAkSatHandoverPending reports the satellite handover state. It is an
enumerated integer value with the structure as shown in Table B-9.
Table B-9. Satellite Handover Enumeration Type
Number
SNMP Type
yes
no
unavailable
(l)
Description
Satellite Handover is pending.
Satellite Handover is not pending
Satellite Handover information not available
Transmission State on Ground Type Definition
The SNMP honAkServTxOnGround report if transmission on the ground is allowed. It is
enabled by discrete input. It is an enumerated integer value with the structure as shown
in Table B-10.
Table B-10. Transmission State on Ground Enumeration Type
Number
SNMP Type
txAllowed
txInhibited
(m)
Description
RF Transmission is allowed on the ground
RF Transmission is not allowed on the ground
Port link status Type definition
The SNMP honAkPortInfoOperStatus indicates the current link status of the port. That
is, whether the port is currently passing data in either direction within a 10 second trailing
window. It is an enumerated integer value with the structure as shown in Table B-11.
Table B-11. Port Link Status Enumeration Types
SNMP Type
active
inactive
(2)
Number
Description
Port Link Status is active
Port Link Status is not active
MIB Object Under Mandatory Branches
This section contains various branches detailing what is in each branch and the parameters
/meanings.
(a)
MIB Version Related Objects
The .honAkVersion (1) folder contains only one object .honAkEngMibVer as shown in
the detail below:
Object Identifier
.honAkEngMibVer (1)
(b)
Type
Unsigned32
Range
Description
This object defines the version number of this MIB
Service Related objects
The .honAkService (2) folder contains all service relevant information and some
configurable parameters that can be set by a client application as follows:
Link Status Related Sub Branch
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The .honAkLinkStatus (1) folder contains object as shown in the details below:
Object Identifier
.honAkServSatLinkState (1)
Type
HonAkSatLink
State
honAkServTxO
nGround
.honAkServTxOnGround (2)
Range
Description
This object shows the state of the satellite link.
This object indicates whether RF Transmission is
allowed on Ground or not.
System Related Sub Branch
The .honAkSystem (2) folder contains objects as shown in the details below:
Object Identifier
.honAkServSysManufacture (1)
Type
DisplayString
.honAkServUnavailReason (2)
honAkServUna
vailReason
Range
0..32
Description
ASCII String with up to 32 characters to reports the
name of the system manufacture.
The reason the Internet service is not available.
Service Notification configuration Related Sub Branch
The .honAkServTrapsConfig (3) folder contains objects as shown details below:
Object Identifier
.honAkServTrapsDestIpAddr (1)
Type
IpAddress
Range
.honAkServTrapsDestPort (2)
Unsigned32
0..65535
(c)
Description
The destination IP Address for Service traps.
If the value of the object is 0.0.0.0, the trap will not
be sent.
The destination port number for Service traps.
Default on reset 162.
Maintenance Related objects
The .honAkMaintenance (3) folder contains all maintenance relevant information
including system health status, interface status, link status, equipment information and
some configurable parameters that can be set by a client application.
Operation Status Related Sub Branch
The .honAkInstallAndCalibration (1) folder contains objects as shown in the
detail below:
Object Identifier
. honAkInstallNoOae (1)
Type
TruthValue
Range
Description
Default on reset is False, True means operation
without an OAE operation is allowed
System Health Related Sub Branch
The .honAkSystemHealth (2) folder contains objects as shown in the details
below:
Object Identifier
.honAkAesHealthStatus(1)
Type
HonAkHealthStatus
Range
Description
This object reports the health status
of the AES. It is an enumerated
integer. Normal during initialization.
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.honAkModmanHealthStatus(2)
HonAkHealthStatus
.honAkKanduHealthStatus(3)
HonAkHealthStatus
.honAkKrfuHealthStatus(4)
HonAkHealthStatus
.honAkOaeHealthStatus(5)
HonAkHealthStatus
.honAkApmHealthStatus(6)
.honAkAesFailureCode(7)
HonAkHealthStatus
DisplayString
.honAkAesFailureText(8)
DisplayString
.honAkModmanToKanduEthernet(9)
TruthValue
.honAkModmanToKanduTxFilterSelectRs422(10)
TruthValue
.honAkModmanToKanduTxKeylineRs422(11)
TruthValue
.honAkKanduToKrfuRs422(12)
TruthValue
.honAkKrfuToKanduRs422(13)
TruthValue
.honAkKanduToFmaEthernet(14)
TruthValue
.honAkKanduToOaeRs422(15)
TruthValue
.honAkOaeToKanduRs422(16)
TruthValue
.honAkKanduToOaeImuRs422(17)
TruthValue
.honAkOaeImuToKanduRs422(18)
TruthValue
This object reports the health status
of Modman. Normal during
initialization.
The health status of the KANDU.
Unavailable is to be reported when
the KANDU is not in communication
with the Modman
The health status of the KRFU.
Unavailable is to be reported when
the KRFU is not in communication
with the Modman
The health status of the OAE.
Unavailable is to be reported when
the OAE is not in communication
with the Modman
The health status of the APM.
Last system failure code. The failure
code is a 12-digit hexadecimal
number. When there is no fault, all
Octets will be set to zero.
A textual description of the last
system failure code
Report Modman to Kandu Ethernet
status. True = Okay/Not Available,
False = Failed
The Modman to KANDU transmit
filter select RS422 state. True =
Okay/Not Available, False = Failed
The Modman to KANDU transmit
keyline RS422 state. True =
Okay/Not Available, False = Failed
The KANDU to KRFU RS422 serial
data state. True = Okay/Not
Available, False = Failed
The KRFU to KANDU RS422 serial
data state. True = Okay/Not
Available, False = Failed
The KANDU to FMA Ethernet data
state. True = Okay/Not Available,
False = Failed
The KANDU to OAE RS422 serial
data state. True = Okay/Not
Available, False = Failed
The OAE to KANDU RS422 serial
data state. True = Okay/Not
Available, False = Failed
The KANDU to OAE IMU RS422
serial data state. True = Okay/Not
Available, False = Failed
The OAE IMU to KANDU RS422
serial data state. True = Okay/Not
Available, False = Failed
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.honAkModmanToKrfuRfLink(19)
TruthValue
.honAkKrfuToModmanRfLink(20)
TruthValue
.honAkOaeToKrfuRfLink(21)
TruthValue
.honAkApmToModman(22)
TruthValue
.honAkIrsStatus(23)
honAkIrsStatus
.honAkAesReset(24)
TruthValue
.honAkModmanThermalState(25)
HonAkThermalStat
HonAkThermalStat
HonAkThermalStat
HonAkThermalStat
.honAkKanduThermalState(26)
.honAkKrfuThermalState(27)
.honAkOaeThermalState(28)
The Modman to KRFU RF link state.
True = Okay/Not Available, False =
Failed
The KRFU to Modman RF link state.
True = Okay/Not Available, False =
Failed
The OAE RF Link to KRFU state.
True = Okay/Not Available, False =
Failed
The APM to Modman serial data
state. True = Okay/Not Available,
False = Failed
This object reports the IRS status.
IRS inactive is to be reported if the
KANDU is not in communication
with the Modman and it is the IRS
source.
Write = True cause a system reset,
a write = False causes no action. A
read always returns false and
perform no Action.
the thermal state of the Modman
the thermal state of the KANDU
the thermal state of the KRFU
the thermal state of the OAE
In Service Related Sub Branch
The .honAkInService (3) folder contains objects to supports in-service status and
statistics for the maintenance branch of the MIB as shown in the below details:
Object Identifier
.honAkMaintSatLinkState(1)
Type
HonAkSatLinkState
Range
.honAkTxMuted(2)
TruthValue
.honAkTxMutedReason(3)
honAkTxMutedReason
.honAkSatHandoverPending(4)
.honAkLinkStartTime(5)
honAkSatHandoverPendin
DateAndTime
RFC2759
.honAkLinkEndTime(6)
DateAndTime
RFC2759
Description
The state of the satellite link
Whether or not the terminal has
muted the satellite transmission. True
= muted, False = may be transmitting
Reason for muting the satellite
transmission
whether a satellite handover is
expected shortly
Time at which the current satellite was
established, or 1/1/1970 after a reset
or if the link is not active
Time at which the satellite link was
closed. After a reset and before a
satellite has been established, the
value will equate to 1/1/1970.
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.honAkLinkTxCount(7)
Unsigned32
.honAkLinkRxCount(8)
Unsigned32
.honAkLinkSignalQuality(9)
HonAkTenthsUnsigned32
.honAkLinkSignalLevel(10)
HonAkTenthsInteger32
.honAkLinkEbNoSignalQuality(11)
HonAkTenthsUnsigned32
.honAkTxCtrlState(12)
HonAkDiscreteInputState
.honAkWowState(13)
HonAkDiscreteInputState
.honAkCellularTxState(14)
HonAkDiscreteInputState
.honAkGroundTxState(15)
HonAkDiscreteInputState
.honAkPublicServState(16)
HonAkDiscreteInputState
.honAkCoolingSysAvailState(17)
HonAkDiscreteInputState
.honAkRemoteMgrState(18)
HonAkDiscreteInputState
.honAkLocalDataLoadState(19)
HonAkDiscreteInputState
.honAkFactoryBenchModeState(20)
HonAkDiscreteInputState
.honAkArincTxMuteState(21)
HonAkDiscreteOutputState
.honAkSysAvailState(22)
.honAkDataLinkAvailState(23)
.honAkAircraftLatitude(24)
HonAkDiscreteOutputState
HonAkDiscreteOutputState
Integer32
.honAkAircraftLongitude(25)
Integer32
.honAkAircraftAltitude(26)
Integer32
.honAkAircraftRollAngle(27)
HonAkTenthsInteger32
.honAkAircraftPitchAngle(28)
HonAkTenthsInteger32
.honAkAircraftTrueHeading(29)
HonAkTenthsUnsigned32
-999999 |
-324000..3
24000
-999999 |
-647999..6
48000
-999999 |
-10000..10
0000
-999999 |
-900..900
-999999 |
-900..900
0..3599 |
9999
The total number of kilobytes
transmitted over the currently active
satellite link. This object is reset to
zero when the satellite link is closed
The total number of kilobytes received
over the currently active satellite link
The carrier to noise signal quality in
tenths of a db/Hz. zero if no signal is
being received
The Signal level of the satellite link in
tenths of a dBm. zero if no downlink
carrier is being received
Calculated satellite link EB/No signal
quality in tenths of a dB
whether or not satellite transmission
control analogue input to KANDU is
enabled
whether or not there is weight on
wheels
Indicates whether or not cellular
transmission is enabled
whether or not satellite transmission is
allowed while on the aircraft is ground
whether or not Public Service is
enabled
whether or not aircraft cooling
availability is enabled
whether or not remote management is
enabled
whether or not local data loading is
enabled
whether or not Factory/Bench Mode is
enabled
whether or not the ARINC
transmission is muted
status of system availability
status of the data link
The latitude position of the aircraft in
arc seconds. -999,999 indicates that
the data is not available
The longitude position of the aircraft in
arc seconds. -999,999 indicates that
the data is not available.
The altitude of the aircraft in feet
The roll angle of the aircraft in tenths
of a degree
The pitch angle of the aircraft in tenths
of a degree
The true heading of the aircraft in
tenths of a degree. 9,999 indicates
that the data is not available
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.honAkAircraftOnGround(30)
TruthValue
.honAkAircraftGroundSpeed(31)
Unsigned32
0..1500 |
9999
Indicates whether or not the aircraft is
on the ground
Reports the ground speed of the
aircraft. The range of the object is
from 0 to 1,500 knots. 9,999 indicates
that the data is not available
System Configuration Related Sub Branch
The .honAkSystemConfiguration (4) folder contains objects to supports the
system configuration for the maintenance branch of the MIB as shown in the below
details:
Object Identifier
.honAkModmanLruName(1)
Type
DisplayString
Range
0..32
.honAkModmanOemHwPn(2)
DisplayString
0..32
.honAkModmanSn(3)
DisplayString
0..32
.honAkModmanSwPnSwValid(4)
DisplayString
0..32
.honAkModmanSwSubpartVer(5)
.honAkModmanOemId(6)
DisplayString
DisplayString
0..255
0..32
.honAkModmanHoneywellHwPn(7)
DisplayString
0..32
.honAkModmanSubassemblyId(8)
DisplayString
0..32
.honAkKanduLruName(9)
DisplayString
0..32
.honAkKanduOemHwPn(10)
DisplayString
0..32
.honAkKanduSn(11)
DisplayString
0..32
.honAkKanduSwPnSwValid(12)
DisplayString
0..32
.honAkKanduSwSubpartVer(13)
.honAkKanduOemId(14)
DisplayString
DisplayString
0..255
0..32
.honAkKanduHoneywellHwPn(15)
DisplayString
0..32
.honAkKanduSubassemblyId(16)
DisplayString
0..32
.honAkKrfuLruName(17)
DisplayString
0..32
.honAkKrfuOemHwPn(18)
DisplayString
0..32
.honAkKrfuSn(19)
DisplayString
0..32
Description
ASCII String with up to 32 characters to show the
Modman LRU name. Empty if no Standard Electronic
Information is stored in the Modman.
ASCII String with up to 32 characters to show Modman
OEM hardware part number.
ASCII String with up to 32 characters to show Modman
serial number.
ASCII String with up to 32 characters to show Modman
software part number and software validity.
The Modman software sub part version number
ASCII String with up to 32 characters to show Modman
OEM identifier.
ASCII String with up to 32 characters to show Modman
Honeywell-specific part identifier.
ASCII String with up to 32 characters to show Modman
sub-assembly ID.
ASCII String with up to 32 characters to show the
KANDU LRU name. Empty if no Standard Electronic
Information is stored in the KANDU or the KANDU is not
attached or powered up.
ASCII String with up to 32 characters to show KANDU
OEM hardware part number.
ASCII String with up to 32 characters to show KANDU
serial number.
ASCII String with up to 32 characters to show KANDU
software part number and software validity.
The KANDU software sub part version number
ASCII String with up to 32 characters to show KANDU
OEM identifier.
ASCII String with up to 32 characters to show KANDU
Honeywell-specific part identifier.
ASCII String with up to 32 characters to show KANDU
sub-assembly ID.
ASCII String with up to 32 characters to show the KRFU
LRU name. Empty if no Standard Electronic Information
is stored in the KRFU or the KRFU is not attached or
powered up.
ASCII String with up to 32 characters to show KRFU
OEM hardware part number.
ASCII String with up to 32 characters to show KRFU
serial number.
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.honAkKrfuSwPnSwValid(20)
DisplayString
0..32
.honAkKrfuSwSubpartVer(21)
.honAkKrfuOemId(22)
DisplayString
DisplayString
0..255
0..32
.honAkKrfuHoneywellHwPn(23)
DisplayString
0..32
.honAkOaeLruName(24)
DisplayString
0..32
.honAkOaeOemHwPn(25)
DisplayString
0..32
.honAkOaeSn(26)
DisplayString
0..32
.honAkOaeSwPnSwValid(27)
DisplayString
0..32
.honAkOaeSwSubpartVer(28)
DisplayString
0..255
.honAkOaeOemId(29)
DisplayString
0..32
.honAkOaeHoneywellHwPn(30)
DisplayString
0..32
.honAkOaeSubassemblyId(31)
DisplayString
0..32
.honAkApmLruName(32)
DisplayString
0..32
.honAkApmOemHwPn(33)
DisplayString
0..32
.honAkApmSn(34)
DisplayString
0..32
.honAkApmOemId(35)
DisplayString
0..32
.honAkAircraftTailNbr(36)
DisplayString
0..32
.honAkCfgInfo(37)
DisplayString
0..255
.honAkGeoRestriction(38)
DisplayString
0..255
ASCII String with up to 32 characters to show KRFU
software part number and software validity.
The KRFU software sub part version number
ASCII String with up to 32 characters to show KRFU
OEM identifier.
ASCII String with up to 32 characters to show KRFU
Honeywell-specific part identifier
ASCII String with up to 32 characters to show the OAE
LRU name. Empty if no Standard Electronic Information
is stored in the OAE or the OAE is not attached or
powered up.
ASCII String with up to 32 characters to show OAE OEM
hardware part number.
ASCII String with up to 32 characters to show OAE
serial number.
ASCII String with up to 32 characters to show OAE
software part number and software validity.
The OAE software sub part version number. Empty if the
OAE is not attached or powered up
ASCII String with up to 32 characters to show OAE OEM
identifier.
ASCII String with up to 32 characters to show OAE
Honeywell-specific part identifier.
ASCII String with up to 32 characters to show OAE
sub-assembly ID. Empty if the OAE is not attached or
powered up
ASCII String with up to 32 characters to show the APM
LRU name. Empty if no Standard Electronic Information
is stored in the APM or the APM is not attached.
ASCII String with up to 32 characters to show APM
OEM hardware part number.
ASCII String with up to 32 characters to show APM
serial number.
ASCII String with up to 32 characters to show APM
OEM identifier.
ASCII String with up to 32 characters to show aircraft tail
number
ASCII String to show overall configuration data part
numbers and CRCs
ASCII String to show state of the geographic restriction
map
Network Configuration Related Sub Branch
The .honAkNetworkConfiguration(5) folder contains the following:
Port info Number
The .honAkPortInfoNumber (1) object report the number of supported
Ethernet ports. Nominal is 14.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
b Port Info Table
The .honAkPortInfoTable (2) table supports information pertaining to various
Ethernet ports. This table has objects as shown in the below detail:
Object Identifier
.honAkPortInfoIndex(1)
Type
Unsigned32
Range
1..4294
967295
.honAkPortInfoName(2)
DisplayString
0..16
.honAkPortInfoUserDataSupported(3)
TruthValue
.honAkPortInfoOperStatus(4)
honAkPortInfoOperStatu
.honAkPortInfoVlanIdList(5)
DisplayString
.honAkPortInfoDataLoadSupported(6)
TruthValue
.honAkPortInfoArinc791SnmpSupported(7)
TruthValue
.honAkPortInfoMaintSnmpSupported(8)
TruthValue
.honAkPortInfoMagic839Supported(9)
TruthValue
.honAkPortInfoAesAccessServSupported(10)
TruthValue
.honAkPortInfoLruAccessServSupported(11)
TruthValue
.honAkPortInfoGuiSupported(12)
TruthValue
.honAkPortInfoDevelServSupported(13)
TruthValue
0..255
Description
The index for an entry that
represents a particular Ethernet
port.
ASCII string with up to 16
characters to show the name of
the port
whether or not the port is
configured for user data
operation
report the port link status (active
if the port is passing data in either
direction in the last 10 seconds)
Report list of VLAN IDs currently
assigned to the port. Empty string
indicates no VLAN IDs assigned
to this port.
Report whether or not data load
is supported
Report whether or not ARINC
791 SNMP is supported
Whether or not
maintenance/engineering SNMP
is supported
Report whether or not MAGIC
839 client is supported
Whether or not AES-level access
services are supported
whether or not LRU-level access
services are supported
Report whether or not the GUI is
supported
Report whether or not
development services are
supported
Maintenance Traps Configuration Related Sub Branch
The .honAkMaintTrapsConfig(6) folder contain objects as shown in the below
details:
Object Identifier
..honAkMaintTrapsDestIpAddr
(1)
Type
IpAddress
Range
RFC
2578
..honAkMaintTrapsDestPort (2)
Unsigned32
065535
Description
This object to configure the IP address that maintenance
notification traps are sent to and if they are enabled (0.0.0.0
means do not send traps and is the default after reset), as
an IPAddress (RFC 2578) value
This object configure which IP port traps are addressed to
(0-65535, default on reset 162), as an Unsigned32 value
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
(3)
Traps under Engineering Notification Branch
This honAkEngNotifications(3) branch contain service and maintenance notification’s
folder for maintenance and service related traps.
(a)
Service Trap Related Sub Branch
The .honAkServTrap(0)Branch contains the object as shown in the below details:
Trap (OID)
.honAkServLinkStateChgTrap (1)
(b)
Monitored Objects
honAkServSatLinkState
Description
This trap has to be sent, when the value of the link
state of terminal object changes
Maintenance Trap related sub branch
The .honAkMaintTrap(0) branch contains the objects as shown in the below details:
Trap (OID)
.honAkMaintLinkStateChgTrap (1)
.honAkMaintTxMuteChgTrap (2)
.honAkMaintSysAvailChgTrap (3)
.honAkMaintDataLinkAvailChgTrap (4)
.honAkMaintAesHealthStatusChgTrap
(5)
Monitored Objects
honAkMaintSatLinkSt
atus
honAkTxMutedReaso
honAkSysAvailState
honAkDataLinkAvailS
tate
honAkAesHealthStatu
Description
This trap has to be sent, if satellite link changes
This trap has to be sent, if transmit mute reason
changes
This trap has to be sent if system availability
changes
This trap has to be sent, if the data link availability
changes
This trap has to be sent, if the AES health status
changes.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Blank Page
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
APPENDIX C
NOTE: The JetWave™ LRU labels do contain data such as Software Part No., Software Version
No. or Software Mod dots. To see the JetWave™LRUs hardware and software version and
part number, navigate to the Version and Manufacturing Information menu on the GUI.
1.
Aircraft Information Sheet
Owner
Tail Number
Serial Number
Model/Type
2.
JetWave™ AES Subsystem Components
A.
JetWave™ AES OAE - FMA/TMA Installation Information Sheet
Part Number
Serial Number
Hardware Revision
Mod Status
B.
JetWave™ AES KANDU Installation Information Sheet
Part Number
Serial Number
Hardware Revision
Mod Status
C.
JetWave™ AES KRFU Installation Information Sheet
Part Number
Serial Number
Hardware Revision
Mod Status
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
D.
JetWave™ AES Modman Installation Information Sheet
Part Number
Serial Number
Hardware Revision
Mod Status
E.
JetWave™ AES APM Installation Information Sheet
Part Number
Serial Number
Hardware Revision
Mod Status
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
APPENDIX D
1.
Installation Checklist
Aircraft Identification:
Name
Signature
Date
Installation/Checks completed by:
Approved/Witnessed by:
A.
OAE-TMA Checklist
Section
Parameter
Item
NA
A. Maintenance Panel
Applicability
If the system is not wired to another
aircraft system, a maintenance panel is
required.
√
Value
Discrete output System available (Modman MP13E)
connections
connected to a lamp
Data link available (Modman MP13F)
connected to a lamp
Discrete input
connections
Local data load enable (Modman
MP10B) connected to a normally open
switch
Ground transmit enable (Modman
MP11D) connected to a normally open
switch
Public service disable (Modman MP11E)
connected to a normally open switch
Modman reset (Modman MP10C)
connected to a normally open switch
Ethernet port
connections
AV1 (Modman TP BB1 thru 4) connected
to a RJ45 Ethernet connector
Additional
Electrically wire and interconnect in
electrical wiring accordance with Figure 2-33.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Section
Parameter
Item
NA
B. Modman
Physical
Examine for physical damage.
√
Value
Environmental conditions, refer to
Figure 2-24.
Mounting tray
Install applicable 4-MCU tray, supplied
by customer.
Clearance
Minimum 1 inch (25.4 mm) from top
surface and 0.5 inch (12.7 mm) from all
other surfaces
Electrical
connector
ARINC 600 mating connector and pins,
refer to Table 2-1. ARINC 600
Connectors
ARINC 600 polarized pins
Electrical
bonding
Bonding, refer to page 2-5.
Electrical wiring Electrically wire and interconnect in
accordance with Figure 2-24 and
Figure 2-33.
Electrical RF
coaxial
Equalizer in the TX path
TX path loss, refer to Table 2-2. Modman
Cable Loss Values
Attenuator in the RX path
RX path loss, refer to Table 2-2. Modman
Cable Loss Values
C. APM
Physical
Examine for physical damage.
Environmental conditions, refer to
Figure 2-25
Mounting
Can be installed in any orientation, refer
to Figure 2-25.
Use 0.164-32 UNC-2A corrosion
resistant mounting fasteners.
Do not exceed 25 in-lb (2.8 Nm) when
you torque the screws.
Electrical
bonding
Electrically bond in accordance with
page 2-6.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Section
Parameter
Item
NA
C. APM (Cont)
Electrical wiring Electrically wire and interconnect in
accordance with Figure 2-25 and
Figure 2-33.
√
Value
Electrical wiring Connect the APM to the Modman with
- APM to
two twisted shielded 24 AWG pairs with
Modman
Teflon insulation or aerospace grade
shielded CAT5/CAT5e cable, maximum
length 9.8 feet (3 m).
D. KANDU
Physical
Examine for physical damage.
Environmental conditions, refer to
Figure 2-26
Electrical wiring Electrically wire and interconnect in
accordance with Figure 2-26 and
Figure 2-33.
Mounting
Install location of KANDU is airframe
specific. KANDU could be installed in
unpressurized area near the tail
empennage of the aircraft or inside
pressurized area of the aircraft.
In case of KANDU install location is
inside pressurized location, the KANDU
to KRFU and KANDU to TMA
interconnect may be routed through a
Bulkhead Interface connector.
Electrical wiring Refer to JetWave™ System LRU
- KANDU to
Installation, KANDU on page 2-6.
TMA
Electrical wiring Refer to JetWave™ System LRU
- KANDU
Installation, KANDU on page 2-6.
bulkhead
interface
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Section
Parameter
Item
NA
E. KRFU
Physical
Examine for physical damage.
√
Value
Environmental conditions, refer to
Figure 2-27, Figure 2-28, or Figure 2-29
depending on configuration used.
Install the thermal pad in accordance with
KRFU Thermal Pad Kit on page 2-9.
The KRFU is installed with the TMA, refer
to OAE TMA Installation Procedure on
page 2-15.
The KRFU feet are configured differently
depending on the part number ordered.
Make sure feet are in the correct
configuration for the aircraft application.
Waveguide
Make sure the waveguide is connected
before powering the KRFU.
Waveguide Connection must be WR28 for TX and
KRFU to TMA coaxial cable for RX.
The TX interconnect path loss
The RX interconnect path loss
RX connection at the KRFU requires a
WR42 to coax transition adapter at the
KRFU J4
Electrical wiring Electrically wire and interconnect in
accordance with outline drawing
Figure 2-27, Figure 2-28, or Figure 2-29
and interconnect drawing Figure 2-33.
Electrical
bonding
J. OAE TMA Installation Physical
Procedure
Electrically bond in accordance with
page 2-9.
Refer to OAE TMA Installation
Procedure.
TMA mounting Refer to OAE TMA Installation
Procedure.
TMA interface Refer to OAE TMA Installation
mount brackets Procedure.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Section
Parameter
J. OAE TMA Installation TMA install
Procedure (Cont)
TMA radome
and radome
fairing
Item
NA
√
Value
Refer to JetWave™ System LRU
Installation, OAE TMA Installation
Procedure.
Depending on the airframe, there may
be a need to install radome fairing which
adapts to the tail empennage of the
aircraft, consult aircraft OEM.
Radome and fairing installation is
aircraft specific. Refer to aircraft specific
SDIM for details.
NOTE: Before removing the Tail Mount
Radome, Honeywell
recommends manually steering
the TMA to a safe antenna
orientation position using the
JetWave™ GUI. The TMA
parking position is included in
the AES System Configuration
File, which can be accessed
through the GUI web interface
and by navigating to
Configuration File page.
Consult aircraft specific SDIM
for detailed instructions.
TMA bonding
Electrically bond in accordance with
page 2-15.
TMA alignment Automatic alignment, manual alignment,
or command, refer to TMA Alignment on
page 2-20 and TMA and FMA Antenna
Alignment Procedure on page 2-36
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
B.
A791 Based OAE-FMA with the AIM Checklist
Section
Parameter
Item
NA
A. Maintenance Panel
Applicability
If the system is not wired to another
aircraft system, a maintenance panel is
required.
√
Value
Discrete output System available (Modman MP13E)
connections
connected to a lamp
Data link available (Modman MP13F)
connected to a lamp
Discrete input
connections
Local data load enable (Modman
MP10B) connected to a normally open
switch
Ground transmit enable (Modman
MP11D) connected to a normally open
switch
Public service disable (Modman MP11E)
connected to a normally open switch
Modman reset (Modman MP10C)
connected to a normally open switch
Ethernet port
connections
AV1 (Modman TP BB1 thru 4) connected
to a RJ45 Ethernet connector
Additional
Electrically wire and interconnect in
electrical wiring accordance with Figure 2-33.
B. Modman
Physical
Examine for physical damage.
Environmental conditions, refer to
Figure 2-24
Mounting tray
Install applicable 4-MCU tray, supplied
by customer.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Section
Parameter
Item
NA
B. Modman (Cont)
Clearance
Minimum 1 inch (25.4 mm) from top
surface and 0.5 inch (12.7 mm) from all
other surfaces
Electrical
connector
ARINC 600 mating connector and pins,
refer to Table 2-1. ARINC 600
Connectors
√
Value
ARINC 600 polarized pins
Electrical
bonding
Bonding, refer to page 2-5
Electrical wiring Electrically wire and interconnect in
accordance with Figure 2-24 and
Figure 2-34, Figure 2-35, or Figure 2-36.
Electrical RF
coaxial
Equalizer in the TX path
TX path loss, refer to Table 2-2. Modman
Cable Loss Values
Attenuator in the RX path
RX path loss, refer to Table 2-2. Modman
Cable Loss Values
C. APM
Physical
Examine for physical damage.
Environmental conditions, refer to
Figure 2-25
Mounting
Can be installed in any orientation. Refer
to Figure 2-25.
Use 0.164-32 UNC-2A corrosion
resistant mounting fasteners.
Do not exceed 25 in-lb (2.8 Nm) when
you torque the screws.
Electrical
bonding
Electrically bond in accordance with
page 2-6.
Electrical wiring Electrically wire and interconnect in
accordance with Figure 2-25 and
Figure 2-34, Figure 2-35, or Figure 2-36.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Section
Parameter
Item
NA
C. APM (Cont)
Electrical wiring Connect the APM to the Modman with
- APM to
two twisted shielded 24 AWG pairs with
Modman
Teflon insulation or aerospace grade
shielded CAT5/CAT5e cable, maximum
length 9.8 feet (3 m).
D. KANDU
Physical
√
Value
Examine for physical damage.
Environmental conditions, refer to
Figure 2-26
E. KRFU
Mounting
Install location of KANDU is airframe
specific. 
The KANDU is installed inside a
pressurized location, the KANDU to
KRFU and KANDU to FMA interconnect
are routed through a Bulkhead Interface
connectors.
Electrical
Wiring
KANDU-FMA
Refer to JetWave™ System LRU
Installation, KANDU on page 2-6.
Physical
Examine for physical damage.
Environmental conditions, refer to
Figure 2-27, Figure 2-28, or Figure 2-29
depending on configuration used.
Install the thermal pad in accordance with
KRFU Thermal Pad Kit on page 2-9.
The KRFU is installed with the FMA, refer
to FMA Installation Procedure on
page 2-29.
The KRFU feet are configured differently
depending on the part number ordered.
Make sure feet are in the correct
configuration for the aircraft application.
Waveguide
Make sure the waveguide is connected
before powering the KRFU.
Waveguide Connection must be WR28 for TX and
KRFU to FMA coaxial cable for RX.
The TX interconnect path loss
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Section
Parameter
Item
NA
E. KRFU (Cont)
Waveguide The RX interconnect path loss
KRFU to FMA
RX connection at the KRFU requires a
(Cont)
WR42 to coax transition adapter at the
KRFU J4.
√
Value
Electrical wiring Electrically wire and interconnect in
accordance with outline drawing
Figure 2-27, Figure 2-28, or Figure 2-29
and interconnect drawing Figure 2-34,
Figure 2-35, or Figure 2-36.
N. FMA Installation
Procedure
Electrical
bonding
Electrically bond in accordance with
page 2-9.
Physical
Examine the FMA AIM for physical
damage.
Examine the FMA assembly for physical
damage.
Examine the radome for physical
damage. Refer to Figure 2-32.
Environmental conditions, refer to
Figure 2-31
Positioning
The aircraft fuselage mount OAE must
be mounted on the top of the fuselage.
FMA AIM
Refer to Fuselage Mount Antenna (8).
FMA Install
Refer to Fuselage Mount Antenna (8).
FMA radome
Attach the radome assembly onto the
AIM.
FMA bonding
Electrically bond in accordance with
page 2-29.
FMA alignment Automatic alignment, manual alignment,
or command, refer to FMA Alignment on
page 2-35 and TMA and FMA Antenna
Alignment Procedure on page 2-36.
C.
Non-A791 Based OAE-FMA with the LAIM Checklist
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Section
Parameter
Item
NA
A. Maintenance Panel
Applicability
If the system is not wired to another
aircraft system, a maintenance panel is
required.
√
Value
Discrete output System available (Modman MP13E)
connections
connected to a lamp
Data link available (Modman MP13F)
connected to a lamp
Discrete input
connections
Local data load enable (Modman
MP10B) connected to a normally open
switch
Ground transmit enable (Modman
MP11D) connected to a normally open
switch
Public service disable (Modman MP11E)
connected to a normally open switch
Modman reset (Modman MP10C)
connected to a normally open switch
Ethernet port
connections
AV1 (Modman TP BB1 thru 4) connected
to a RJ45 Ethernet connector
Additional
Electrically wire and interconnect in
electrical wiring accordance with Figure 2-33.
B. Modman
Physical
Examine for physical damage.
Environmental conditions, refer to
Figure 2-24
Mounting tray
Install applicable 4-MCU tray, supplied
by customer.
Clearance
Minimum 1 inch (25.4 mm) from top
surface and 0.5 inch (12.7 mm) from all
other surfaces
Electrical
connector
ARINC 600 mating connector and pins,
refer to Table 2-1. ARINC 600
Connectors
ARINC 600 polarized pins
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Section
Parameter
Item
NA
B. Modman (Cont)
Electrical
bonding
Bonding, refer to page 2-5
√
Value
Electrical wiring Electrically wire and interconnect in
accordance with Figure 2-24 and
Figure 2-34, Figure 2-35, or Figure 2-36.
Electrical RF
coaxial
Equalizer in the TX path
TX path loss, refer to Table 2-2. Modman
Cable Loss Values
Attenuator in the RX path
RX path loss, refer to Table 2-2. Modman
Cable Loss Values
C. APM
Physical
Examine for physical damage.
Environmental conditions, refer to
Figure 2-25
Mounting
Can be installed in any orientation. Refer
to Figure 2-25.
Use 0.164-32 UNC-2A corrosion
resistant mounting fasteners.
Do not exceed 25 in-lb (2.8 Nm) when
you torque the screws.
Electrical
bonding
Electrically bond in accordance with
page 2-6.
Electrical wiring Electrically wire and interconnect in
accordance with Figure 2-25 and
Figure 2-34, Figure 2-35, or Figure 2-36.
Electrical wiring Connect the APM to the Modman with
- APM to
two twisted shielded 24 AWG pairs with
Modman
Teflon insulation or aerospace grade
shielded CAT5/CAT5e cable, maximum
length 9.8 feet (3 m).
23-15-29
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Section
Parameter
Item
NA
D. KANDU
Physical
Examine for physical damage.
√
Value
Environmental conditions, refer to
Figure 2-26
Electrical wiring Electrically wire and interconnect in
accordance with Figure 2-26 and
Figure 2-34, Figure 2-35, or Figure 2-36.
Mounting
Install location of KANDU is airframe
specific.
The KANDU is installed inside a
pressurized location, the KANDU to
KRFU and KANDU to FMA interconnect
are routed through a Bulkhead Interface
connectors.
Electrical wiring Refer to KANDU (1).
- KANDU -FMA
Electrical
bonding
Electrically bond in accordance with
page 2-7.
KANDU bonding to the aircraft must be
achieved through the mounting
structure (fasteners) and KANDU
A3J1-A.
The bulkhead interface connectors
should be electrically bonded to the
aircraft.
E. KRFU
Physical
Examine for physical damage.
Environmental conditions, refer to
Figure 2-27, Figure 2-28, or Figure 2-29
depending on configuration used.
Install the thermal pad in accordance with
KRFU Thermal Pad Kit on page 2-9.
The KRFU is installed with the FMA. refer
to FMA Installation Procedure on
page 2-29.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Section
Parameter
E. KRFU (Cont)
Physical (Cont) The KRFU feet are configured differently
depending on the part number ordered.
Make sure feet are in the correct
configuration for the aircraft application.
Waveguide
Item
NA
√
Value
Make sure the waveguide is connected
before powering the KRFU
Waveguide Connection must be WR28 for TX and
KRFU to FMA coaxial cable for RX.
The TX interconnect path loss
The RX interconnect path loss
RX connection at the KRFU requires a
WR42 to coax transition adapter at the
KRFU J4.
Electrical wiring Electrically wire and interconnect in
accordance with outline drawing
Figure 2-27, Figure 2-28, or Figure 2-29
and interconnect drawing Figure 2-34,
Figure 2-35, or Figure 2-36.
N. FMA Installation
Procedure
Electrical
bonding
Electrically bond in accordance with
page 2-9.
Physical
Examine the FMA AIM for physical
damage.
Examine the FMA assembly for physical
damage.
Examine the radome for physical
damage. Refer to Figure 2-32.
Environmental conditions, refer to
Figure 2-31
Positioning
The aircraft fuselage mount OAE must
be mounted on the top of the fuselage
for clear satellite communications.
FMA LAIM
Refer to Fuselage Mount Antenna (8).
Install radome Install and attach the radome skirt
skirt fairing
fairing to fuselage with 39 fasteners.
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Section
Parameter
Item
NA
N. FMA Installation
Procedure (Cont)
Install radome Install and attach the radome skirt
skirt fairing
fairing to fuselage with 39 fasteners.
FMA install
Refer to Fuselage Mount Antenna (8).
FMA radome
Attach the radome assembly onto the
radome skirt fairing.
FMA bonding
Electrically bond in accordance with
page 2-29.
√
Value
FMA alignment Automatic alignment, manual alignment,
or command, refer to FMA Alignment on
page 2-35 and TMA and FMA Antenna
Alignment Procedure on page 2-36.
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
APPENDIX E
1.
List of Airframe Specific Information Required for JetWave™ System Configuration
A Honeywell proprietary configuration tool is used to generate the JetWave™ configuration files. Information
as listed in the tables below is to be provided to Honeywell for generation of JetWave™ configuration files.
Aircraft Information:
Aircraft Model/Type
Tail Number:
Serial Number:
Value Added Reseller (VAR/DP)
Name of the Service Provider
ARINC 429 Labels
ARINC 429 Interface Speed
ARINC
429
Label
No.
150
260
270
254
255
261
132
324
325
330
326
327
331
332
333
110
111
76
ARINC 429 Label Name
UTC Time
Date
Status
Present Position – Latitude
Present Position –
Longitude
Altitude
True Heading
Pitch Angle
Roll Angle
Yaw rate
Pitch rate
Roll rate
Body longitudinal
Acceleration
Body lateral Acceleration
Body vertical Acceleration
GNSS Latitude
GNSS Longitude
GNSS Altitude (MSL)
Accuracy
ARINC 429
Label
Latency
Interface Bus Speed
ARINC 429
Minimum
Total
Latency Transmission
Rate (in
(in
Msec)
Msec)
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Jitter
(Uncert
ainty in
Delay)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Weight on Wheels
Weight on Wheels Discrete Input
Available
Yes/No
User Ethernet Port Configuration
User Ethernet Port
Enable/
Disable
User Traffic
Yes/No
EN5 PIESD Ethernet
Polarity of Weight on Wheels Discrete Signal
User Services to be Enabled
Dataload
Yes/No
SNMP
Yes/No
GUI
Yes/No
EN6 PIESD Ethernet
EN7 PIESD Ethernet
EN8 PIESD Ethernet
AV1 AISD Ethernet
AV2 AISD Ethernet
AV3 AISD Ethernet
PA1 PODD Ethernet
PA2 PODD Ethernet
PA3 PODD Ethernet
PA4 PODD Ethernet
PG1 PODD Gigabit
Ethernet
EG1 PIESD Gigabit
Ethernet
AG1 AISD Gigabit
Ethernet
Airframe Structural Blockage Information
Blockage Angle
Value in Degrees
Remarks
Blockage Angle a
Angle "a" is the angle between the horizontal
plane where the antenna emitting point is located
and outer tip of the Horizontal Tail Plane (HTP).
Blockage Angle b
Angle "b" is between horizontal plane where
antenna emitting point is located and outer tip of
wing (including vortex eliminators, if present).
23-15-29
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Blockage Angle c
Blockage Angle d
Blockage Angle e
Blockage Angle f
Blockage Angle h
Blockage Angle i
Blockage Angle k
Blockage Angle m
Blockage Angle p
Angle "c" refers to the point of the wing, where an
antenna radiating at -10 degrees elevation would
find the wing’s leading edge.
Angle "d" refers to the outer, aft-most tip of the
wing (including vortex eliminators, if present).
Angle "e" provides the azimuth range of the
Vertical Tail Plane (VTP) region of blockage in its
broadest case.
Angle "f" is between the fuselage centerline and
the outer, forward-most tip of the HTP.
Angle “h” provides the Vertical Tail Plane (VTP)
region of blockage in elevation from -10 degrees
up.
Angle "i" is between the horizontal plane where
the antenna emitting point is located and upper,
forward-most part of the fuselage.
Angle "k" is the angle between the horizontal
plane where the antenna emitting point is located
and the aft-most tip of the HTP.
Angle "m" is between the horizontal plane where
the antenna emitting point is located and the HTP
leading edge root (forward-most joint to fuselage).
Angle "p" is from the emitter point to upper,
aft-most wing tip (including vortex eliminators, if
present).
NOTE:
•
All zenith view (from above) angles, except for “e,” are measured from the aircraft longitudinal
axis, being 0 degrees at the stern.
•
All side view angles are measured from the aircraft longitudinal axis, being 0 degrees at the
plane where the antenna emitter is located.
•
Refer to ARINC Characteristic 791 Mark I Aviation Ku-band and Ka-Band Satellite Communication System, Part 1- Physical Installation and Aircraft Interfaces for Aircraft blockage map
parameters.
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
JetWave™ System
Blank Page
23-15-29
© Honeywell International Inc. Do not copy without express permission of Honeywell.
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