EMS Technologies Canada JETWAVE2 Jetwave User Manual 23 15 29R004

EMS Technologies Canada, Ltd. Jetwave 23 15 29R004

User Manual_Part 6

SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ SystemPage 4-131 3 Mar 2017© Honeywell International Inc. Do not copy without express permission of Honeywell.23-15-29Figure 4-36. (Sheet 8 of 8) JetWave™ System Interconnect Diagram - FMA (KRFU Outside Aircraft Fuselage), (90401047-1, REV F)Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ SystemPage 4-132 3 Mar 2017© Honeywell International Inc. Do not copy without express permission of Honeywell.23-15-29Figure 4-37. (Sheet 1 of 12) Alternative KRFU Outside Aircraft Fuselage Configuration (90405210, REV D)Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ SystemPage 4-133 3 Mar 2017© Honeywell International Inc. Do not copy without express permission of Honeywell.23-15-29Figure 4-37. (Sheet 2 of 12) Alternative KRFU Outside Aircraft Fuselage Configuration (90405210, REV D)Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ SystemPage 4-134 3 Mar 2017© Honeywell International Inc. Do not copy without express permission of Honeywell.23-15-29Figure 4-37. (Sheet 3 of 12) Alternative KRFU Outside Aircraft Fuselage Configuration (90405210, REV D)Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ SystemPage 4-135 3 Mar 2017© Honeywell International Inc. Do not copy without express permission of Honeywell.23-15-29Figure 4-37. (Sheet 4 of 12) Alternative KRFU Outside Aircraft Fuselage Configuration (90405210, REV D)Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ SystemPage 4-136 3 Mar 2017© Honeywell International Inc. Do not copy without express permission of Honeywell.23-15-29Figure 4-37. (Sheet 5 of 12) Alternative KRFU Outside Aircraft Fuselage Configuration (90405210, REV D)Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ SystemPage 4-137 3 Mar 2017© Honeywell International Inc. Do not copy without express permission of Honeywell.23-15-29Figure 4-37. (Sheet 6 of 12) Alternative KRFU Outside Aircraft Fuselage Configuration (90405210, REV D)Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ SystemPage 4-138 3 Mar 2017© Honeywell International Inc. Do not copy without express permission of Honeywell.23-15-29Figure 4-37. (Sheet 7 of 12) Alternative KRFU Outside Aircraft Fuselage Configuration (90405210, REV D)Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ SystemPage 4-139 3 Mar 2017© Honeywell International Inc. Do not copy without express permission of Honeywell.23-15-29Figure 4-37. (Sheet 8 of 12) Alternative KRFU Outside Aircraft Fuselage Configuration (90405210, REV D)Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ SystemPage 4-140 3 Mar 2017© Honeywell International Inc. Do not copy without express permission of Honeywell.23-15-29Figure 4-37. (Sheet 9 of 12) Alternative KRFU Outside Aircraft Fuselage Configuration (90405210, REV D)Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ SystemPage 4-141 3 Mar 2017© Honeywell International Inc. Do not copy without express permission of Honeywell.23-15-29Figure 4-37. (Sheet 10 of 12) Alternative KRFU Outside Aircraft Fuselage Configuration (90405210, REV D)Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ SystemPage 4-142 3 Mar 2017© Honeywell International Inc. Do not copy without express permission of Honeywell.23-15-29Figure 4-37. (Sheet 11 of 12) Alternative KRFU Outside Aircraft Fuselage Configuration (90405210, REV D)Draft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ SystemPage 4-143 3 Mar 2017© Honeywell International Inc. Do not copy without express permission of Honeywell.23-15-29Figure 4-37. (Sheet 11 of 12) Alternative KRFU Outside Aircraft Fuselage Configuration (90405210, REV DDraft as of 31 May 2017
SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ SystemPage 4-144 3 Mar 2017© Honeywell International Inc. Do not copy without express permission of Honeywell.23-15-29Blank PageDraft as of 31 May 2017
Page 5-1 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.SECTION 5SOFTWARE CONFIGURATION5.1 ARINC 615A Software Data Load ProcessA. IntroductionAs a minimum, APM system configuration files need to be loaded onto the JETWAVE™ system.The JetWave™ LRUs are preloaded with a full software load and there may be a need to perform a field data load under normal conditions during installation. If a new software release is desired by means of a Service Bulletin, or if all of the LRUs are not at the same software release level, then a new data load will be required.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.Whenever an LRU is exchanged in a JETWAVE™ System, confirmation is required to make sure that the replacement LRU contains software that is compatible with the software configuration of the other boxes. The software upgrade procedures must be rerun for that particular LRU each time an LRU is replaced, to make sure there is compatibility within the JETWAVE™ System.The JETWAVE™ System does not allow for any mix of Honeywell and non-Honeywell furnished LRUs.The JetWave™ LRU operational data files are available from the Honeywell Portal. The software data load can be carried out when the data load 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 RequirementsFor data load, the data loader is to be interfaced with Modman through the ARINC 600 Modman AV1 Ethernet port unless APM configuration does specify other port / IPs settings. 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 Draft as of 31 May 2017
Page 5-2 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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. OverviewThis section contains the instructions for data loading of JetWave™ software to any of the JetWave™ LRUs through the Ethernet interface maintenance port of Modman. Data loading of JetWave™ system can be performed while:• JetWave™ system is in normal operation • During system initialization • When in AES Critical Fault Mode. The maintenance operator is responsible for determining which loads are presented to the JetWave™ AES system through the 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 loading JetWave™ LRUs other than through the Modman. The system configuration files are stored in nonvolatile memory in the APM and does not lose its contents due to loss of APM power. Upon 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 purposes, snap shots of the AIT make F-SIM-LDR ARINC 615A data loader simulator are included within this document. (1) Parts Needed:•Data load files from the Honeywell Portal. •ARINC 615A compliant data. The JetWave™ AES system software is loaded through the Modman loader. NOTE: The JetWave™ AES loadable software part, part number varies for each release. (2) System Software/Database UpdatesUnder normal circumstances, time required to carry out data load operation of all JetWave™ AES LRUs can be performed within a total time of between 1.0 and 2.25 hours. This includes the Modman, KANDU, and antenna. Installation for the FMA takes significantly less time than for the TMA.The data sets as shown in Table 5-1 can be transferred through the data load port of the Modman.Draft as of 31 May 2017
Page 5-3 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.: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 data load package includes *.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 data load set for the JetWave™ system comprises of: • LOADS.LUM: Describes the loads that the data load device carries, one or more. • FILES.LUM: Lists all the files, excluding itself, on the data load. • *.LUH is the load part index file that 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 data load 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. Table 5-1. Data Sets LRU Data Set Transfer ProcessModman JetWave™ Modman LRU Operational file Upload onlyAPM APM configuration file Upload only through the ModmanKANDU JetWave™ KANDU LRU operational file Upload only through the ModmanKRFU JetWave™ KRFU LRU operational file Upload only through the ModmanOAE-FMAorOAE-TMAJetWave™ OAE LRU operational file Upload only through the ModmanDraft as of 31 May 2017
Page 5-4 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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. D. Procedure (AIT Flight Simulyzer v3.0.0)(1) Refer to the latest revision of SBs JETWAVE-23-0001, JETWAVE-23-0002, and JETWAVE-23-0003 or later SB for the software upload procedures.(2) SetupNOTE: These setup steps must be run each time the Data Loader application is closed and opened again.(a) Open the AIT ‘Flight Simulyzer’ application.(b) Select the “Settings” button on the left side of the screen.Draft as of 31 May 2017
Page 5-5 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(c) Right click “Lan Configuration” and select “Import HostLan Configuration…”(d) Browse to the “LanConfig.hex” file and select “Open”. (This file needs to be present by the installer on the data loader computer.)Draft as of 31 May 2017
Page 5-6 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(e) Expand “Lan Configurations” and then also expand “TFTP” on the left side of the screen.Draft as of 31 May 2017
Page 5-7 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(f) Select “Client Configurations” on the left side of the screen and verify the settings appear as in the screenshot below.Draft as of 31 May 2017
Page 5-8 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(g) Select “Server Configurations” on the left side of the screen and verify the settings appear as in the screenshot below.(3) Data-loading GXA with the AIT Flight Simulyzer SoftwareNOTE: Replace “<LRU NAME>” below with the LRU to be loaded.(a) Power on the system.(b) Wait until the Modman front panel LEDs (‘POWER’ and ‘STATUS’) are both solid green in color. This would indicate the system is in “Normal Operation” mode. If the MM does not get to a solid green color, then that should be investigated before the SW upload process begins.(c) Make sure that the ‘Data Load Enable’ discrete is set to the ‘Enabled’ state.(d) On the installers data load PC, open a web browser and in the location bar enter IP address 172.29.55.1, hit enter. This will open the AES GUI as shown in the figure below. Draft as of 31 May 2017
Page 5-9 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Log in and view the system status info at the top of the GUI window. At the GUI login, the username is "User" and there is no password.(e) Wait until all of the LRUs indicate a status of “OK” before continuing, to ensure the system has booted up fully. Should the GX system come up in “Init” mode or “Critical Fault” mode, the data loader process may still be performed to update the software if the cause was known to be related to the previous version software. Otherwise, the system fault should be investigated and a “Normal Operation” state restored.Draft as of 31 May 2017
Page 5-10 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(f) In the AIT ‘Flight Simulyzer’ application, select the “Simulation” button on the left side of the screen.Draft as of 31 May 2017
Page 5-11 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(g) The LRU name (i.e. ‘GXA <LRU NAME>’) should now be visible in the left side window pane under “A615A Data Loader”.(h) Right click the LRU name (‘GXA <LRU NAME>’) on the left side window pane and select “Load Operations…”Draft as of 31 May 2017
Page 5-12 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(i) Select the “Refresh” button near the bottom right part of the screen.(j) Verify that the “Target Information” for the LRU appears on the right side of the screen. This will ensure communication between the 615A Data Loader and the Modman.Draft as of 31 May 2017
Page 5-13 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(k) Select “Add LSP…” and browse to the .luh file in the 665 data load package for the LRU, select it and click “Open”.Draft as of 31 May 2017
Page 5-14 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(l) The package should now be visible in the “File Transfer” window.(m) Select the “Upload” button when ready to begin the transfer to the LRU.(n) When complete, the “Status” heading in the “File Transfer” window will indicate “Complete” and a green status bar at the bottom of the screen will indicate “Data load Draft as of 31 May 2017
Page 5-15 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.has completed successfully. Once all LRUs are updated, de-assert the data load discrete to reset the system (100%)”.(o) If loading additional software, again execute the steps above starting with Step (h).(p) Once all software upgrades are completed, toggle the ‘Data Load Enable’ discrete to the ‘Disabled’ state. This will cause a system reboot. (q) On the data load PC, using a web browser (preferably Firefox or Chrome), point to IP address ‘172.29.55.1’ in the browser to open the AES GUI as shown below. Log in and view the system status info at the top of the GUI window. At the GUI login, the username is "User" and there is no password.(r) Each LRU can be checked by selecting the respective LRU name under “Version & Manufacturing Information”.(s) Each LRU page will have the hardware part and serial numbers, as well as the software part numbering information and CRCs for each sub part. This information should match Draft as of 31 May 2017
Page 5-16 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.the VDDs which were loaded. For details on the software versions, refer to the applicable SB.E. A615 LanConfig.Hex File Creation and Settings(1) Open the AIT Flight Simulyzer Tool and select the ‘Settings’ pushbutton. Under the local host tree, select the “A615A DataLoader”. Select “ADD” to add the seven entries as shown in Step (b). Each time you select “ADD,” you will be prompted to automatically create a TFTP Client and Server for each target. Select “Yes”.Draft as of 31 May 2017
Page 5-17 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(2) Enter all the A615A DataLoader settings as shown in the following screenshots.Draft as of 31 May 2017
Page 5-18 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(3) In the Local Host Tree, select “ Lan Configuration”, “TFTP”, “Client Configurations”. Enter the settings as shown in the following screenshots.Draft as of 31 May 2017
Page 5-19 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(4) In the Local Host Tree, select “ Lan Configuration”, “TFTP”, “Server Configurations”. Enter the settings as shown in the following screenshots.Draft as of 31 May 2017
Page 5-20 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(5) Once all settings have been entered, select “LAN Configuration” from the tree and right click, “Export HostLan Configuration to a file.” Save to a folder and name the file LanConfig.hex.(6) This configuration file can now be loaded anytime you want to run a data load.Draft as of 31 May 2017
Page 6-1 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.SECTION 6SYSTEM COMMISSIONING6.1 Provisioning of User ServicesWithin 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 the JetWaveTM system.The commencement of RF transmission and reception of the JetWaveTM system during normal operation is as follows:• Satellite Search: The JetWaveTM system is looking for the satellite in the closest longitude proximity. In this state, the JetWaveTM system does not transmit.• 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 Distribution Partners is correct at the time of publishing but may change. • Distribution Partners:•GoGoDraft as of 31 May 2017
Page 6-2 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.• Satcom1/GoDirect• Satcom Direct•SITA OnAir•Thales• ARINC DirectThe actual throughputs achieved by the GXA terminal are dependent on the 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 defined Maximum Information Rate. All instantaneous demand will be matched to provisioned CIRs for 95% of the time 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 get connected is configurable through the ground based NMS of the Value Added Resellers/Distribution Partners of Inmarsat GX network. The configuration by the VLAN may be managed over the air by the VAR. This is utilized to dynamically optimize network operations. The updates do not adversely affect system safety, nor operational capabilities and does not impact flight crew workload.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 Number, the JetWaveTM system first gets associated to the Inmarsat network and the system is associated to the appropriate VAR/DP network, where the Service Level Agreements, the aircraft Tail Number and the pre-assigned JetWaveTM system terminal ids are linked for billing and service. A. Product Support Services(1) Customer Support OverviewThe 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. (2) 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. Draft as of 31 May 2017
Page 6-3 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.B. Terminal Activation(1) To activate the terminal with your service provider you need to provide the ACM TPK.(2) The TPK is written on the test report document delivered with the MODMAN.(3) The TPK may be viewed using the MODMAN GUI.6.2 Certification and ApprovalsAll antenna installations must obtain the approval of the appropriate government air/radio authority, such as the FAA, EASA, or Transport Canada. Contact the authorities when you begin planning your communication system in order to minimize approval and certification issues.All system configurations are subject to Inmarsat type approval. New configurations (changes to inter-LRU wiring losses, radome and/or IRS data sources) are subject to re-evaluation and must be coordinated through Honeywell.6.3 Post Installation System Checkout ProceduresA. General OverviewThis 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. B. System Health and ConfigurationThis 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 7-1.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 6-1 to change the AES aircraft ID information.To just view the aircraft tail number information, the user level can be used. At the GUI login, the username is "User" and there is no password.Draft as of 31 May 2017
Page 6-4 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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 6-1 for the AES aircraft ID information page.Figure 6-1. Aircraft ID Display/Update Information PageThe JetWave™ system LRUs are shipped with the operational software preloaded. Refer to SECTION 5 SOFTWARE CONFIGURATION to verify that all of the LRUs are at the same software level, or if a software upgrade is required for any of the LRUs.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. Draft as of 31 May 2017
Page 6-5 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.There are two LEDs on the front panel of Modman. One is for the power and the second one is for status. Use Table 6-1 to identify the current operating mode of Modman with the power LED indicating powered up status. 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 number for the AES GUI service is 80. The laptop's Ethernet port will need to be configured with a static IP address of 172.29.55.x, where x is 10 or above.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.On any of the Internet browser (Internet Explorer 8 compatible), enter 172.29.55.1 in the address bar. Login page will be presented as the root page, allowing entry of the user name and password. Figure 6-2 shows the login page. Table 6-1. Modman LED Status IndicationsStatus LED ModeOff 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 operationOn - red Modman in Fault ModeDraft as of 31 May 2017
Page 6-6 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 6-2. AES GUI Login Page (a) 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 6-3.The information supplied on the AES Home page is as follows:• Network status• 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 6-3, lets the operator navigate to all applicable options depending on the access level.Draft as of 31 May 2017
Page 6-7 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 6-3. AES Home and Status Info PageView and verify the AES configuration data, navigate to the "Configuration Files" information pages under the other information and control menu. The typical configuration file information page is shown in Figure 6-4. To view and make sure that the AES configuration settings are current, click the AES configuration file to display.The configuration data should be verified by going to the APM page in the Version and Manufacturing Information menu and verifying the part numbers for the APM configuration dataDraft as of 31 May 2017
Page 6-8 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 6-4. View Configuration Files PageTo 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 allow you to view and make sure of the health status of the JetWave™ system. The AES summary and interlink status are shown in Figure 6-5.Figure 6-5. Health Statuses (excerpt), AES Summary and Link Statuses Draft as of 31 May 2017
Page 6-9 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.To see the AES LRUs hardware and software version and part number, navigate to the Version and Manufacturing Information menu. Figure 6-6 shows the typical Modman Version and Manufacturing Information page. Make sure the version and manufacturing information are current for all the LRUs.NOTE: Follow appropriate Jetwave Service Bulletin reference to validate the SW currently installed on the Jetwave system.Figure 6-6. AES Modman and Manufacturing Information PageUpdate 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 6-7.Figure 6-7. Aircraft Tail Number PageDraft as of 31 May 2017
Page 6-10 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.C. Discrete Input Testing(1) If wired, activate the Modman Reset by toggling Modman reset switch on the JetWave™ AES control panel. (2) If the Modman Reset is not wired, then reset the system from the GUI.(3) Monitor the Modman ”power” and “status” LEDs flash continuously. (4) Toggle the Modman Reset switch on the Satcom test panel to the open/non-grounded position. (5) Monitor the “status” LED on the front of the Modman, progresses from red color to steady state green as seen during initial power-on. (6) 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 6-8.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.Figure 6-8. Discrete I/O StateD. ARINC 429 Input Interface TestingFor the operation of the JetWaveTM system, the aircraft must have a functional IRS providing ARINC 429 labels to the KANDU. Functional IRS is interfaced with the KANDU through Receive only ARINC 429 interface through which the required ARINC 429 labels as defined in the APM configuration file are made available.Navigate to the Link Status page and scroll down to see the aircraft status. Refer to Figure 6-9. NOTE: GUI displays roll, pitch, and yaw information in the Aircraft Summary and Link status page. The aircraft yaw information is calculated from True Heading and True Track ARINC 429 labels from the aircraft. If True Track label is not configured, yaw value in the GUI page will indicate as “Unavailable”. There will be no other effects if True Track is not configured, other than that GUI status.This page will be updated with current latitude and longitude position of the aircraft. Draft as of 31 May 2017
Page 6-11 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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 6-9. Aircraft StatusesE. Manual Steering of the AntennaTo 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 6-10.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 the GUI to a safe antenna orientation position before removal. Consult aircraft specific SDIM for detailed instructions.NOTE: New Radomes should be checked for any possible interference with normal Antenna movement prior to activation. This can be accomplished many ways using manually steering the Antenna with the Radome/Tail Cap lightly attached to structure. Placing masking tape along critical paths inside the Radome and looking for breaks in the tape after test and removal is one method of detecting interference.Draft as of 31 May 2017
Page 6-12 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 6-10. Manual Antenna Steering F. System Available (Cockpit Control Panel) OutputOnce 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. Refer to Figure 6-11. 6.4 Cable CalibrationThe 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.Cable calibration initiates automatically during the initial system commissioning process or after Modman or KRFU replacement. Cable calibration must be initiated using a GUI commanded test after Tx IF cable manipulation, connector re-seating and cable replacement. 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. During calibration, the power amp of the BUC is disabled.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.Cable Calibration is available through the GUI Commanded Test - Calibrate Transmit Cable. The Cable Calibration procedure only takes up to 15 minutes to perform.To maintain a fully optimized Jetwave system, it is recommended to perform a single cable calibration in the 20 year service life, at around 8,000 to 12,000 hours of operation. This optimization will minimize minor effects of device aging in the transmit chain, and can be performed conveniently using the GUI to Draft as of 31 May 2017
Page 6-13 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.initiate the "Calibrate Transmit Cable" commanded test. The recommendation is not mandatory and Jetwave will continue to operate at a high level of performance over the service life.To maintain a fully optimized Jetwave system, it is recommended to perform a single cable calibration in the 20 year service life, at around 8,000 to 12,000 hours of operation. This optimization will minimize minor effects of device aging in the transmit chain, and may be performed conveniently using the GUI to initiate the "Calibrate Transmit Cable" commanded test. The recommendation is not mandatory and Jetwave will continue to operate at a high level of performance over the service life.Figure 6-11. Calibrate Transmit Cable Status Page6.5 TMA and FMA Antenna Alignment ProcedureA. Antenna Assembly OrientationFor the JetWave™ system to point to the servicing satellite correctly, it is important to align the antenna assembly after installation or replacement. The TMA/FMA assembly has a built in IMU and its orientation must be aligned with respect to the principal axes of the aircraft which is determined through aircraft IRS.(1) To do the automatic antenna alignment calibration, aircraft should have a functional IRS, interfaced with the KANDU through A429 interface, and should have the required ARINC 429 labels as defined in the APM configuration file. (2) During the physical installation, the IMU principal axes of the TMA/FMA must be aligned with those of the aircraft within ± 1° on the pitch, roll, and yaw axis. The installation offsets, are then calculated by the KANDU automatically from data received from the aircraft Inertial Navigational System, the TMA/FMA IMU assembly and the satellite signal. Draft as of 31 May 2017
Page 6-14 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(3) It is required to do the automatic antenna alignment calibration with the Radome installed. The antenna alignment process can be initiated through the GUI interface. The JetWave™ system GUI service is supported on AV1 10/100 Base T Ethernet interfaces (AV1 being default configuration, ports may vary depending on specific APM configuration). (4) Automatic Antenna AlignmentThe antenna alignment should be performed only after completion of system power up. The health status of each LRU should be checked on the GUI, and there should be no display of system muting. Only then should the Initiate button be pressed on the Antenna Alignment GUI page. The JetWave™ system GUI service is supported on AV1 and AG1 10/100 Base T Ethernet interfaces. (5) On any Internet browser (Internet Explorer 8 compatible), enter 172.29.55.1 in the address bar. The Login page appears. Figure 6-12 shows the Login page. Figure 6-12. GUI Login Page(6) Enter the username and password below to access the maintenance interface.• Username: "Maintenance" and Password: "Earthbound".B. Positioning of Aircraft for Antenna Alignment(1) On the GUI Calibrate Antenna Alignment page, as shown in Figure 6-13, the current location of aircraft in terms of latitude and longitude is indicated along with the selection of the servicing Geo stationary satellite used for the antenna alignment. Draft as of 31 May 2017
Page 6-15 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 6-13. GUI Calibrate Antenna Alignment Page(2) For the automatic antenna alignment calibration, it is recommended to tow and put the aircraft in an open area away from aircraft hangars such that there is clear visibility to the open sky with the true heading (not magnetic heading) of the aircraft pointed in one of four recommended aircraft true heading values displayed on the GUI antenna calibration page. (3) The automatic antenna alignment calibration can be carried out at up to four different aircraft headings. Out of the available headings, it is required to do only one automatic alignment calibration while the aircraft true heading is toward one of the preferred directions.NOTE: The values displayed in Figure 6-14 will change depending on the location and attitude of the aircraft.Draft as of 31 May 2017
Page 6-16 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(4) The recommended values are dependent on the radome and these values are calculated by the KANDU based on the input from the aircraft IRS and the selected satellite coordinates and the APM configuration data. The Auto Alignment application automatically presents the four true headings to the operator when a target satellite is selected from the “recommended” target which is also location dependent. There is a recommended tolerance range for these headings which is dependent on the radome and configured in the APM configuration data.The chosen recommended true headings are used so that the radome has consistent performance (i.e. no large changes in curvature) over the area being used during alignment.NOTE: It is advised not to do the automatic antenna alignment during rains with heavily clouded sky.(a) The antenna alignment should be performed only after completion of system power up. The health status of each LRU should be checked on the GUI, and there should be no display of system muting due to Initialization. Only then should the Initiate button be pressed on the Antenna Alignment GUI page.(b) The JetWave™ system uses the following input parameters during the antenna alignment procedure:• Aircraft IRS data• OAE IMU data• RSSI as reported from the Modman.(c) The GUI page indicates the status of the aircraft. In order to proceed with the antenna calibration process, all LRUs of the JetWave™ system need to be powered up with aircraft IRS system functioning and providing valid inputs. The GUI page indicates the IRS status. (d) Once the aircraft is aligned to within the tolerance range of any of the recommended aircraft heading, the grayed out on the “Initiate” button will be changed, indicating the system readiness to commence the antenna alignment process. (e) The GUI Antenna Alignment Calibration progress status bar is shown in Figure 6-14.(f) On successful completion of the antenna calibration, the status changes to “Aligned”.NOTE: If for some reason the Calibration procedure fails, the operator will be given the opportunity to repeat the procedure. This may require several attempts to finalize and confirm the offsets.Draft as of 31 May 2017
Page 6-17 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 6-14. GUI Antenna Alignment Calibration Page Extract6.6 On-ground Testing and CommissioningNOTE: There are restrictions to testing the JetWave™ system for the commissioning process. Each country has its own restrictions to on-ground testing and transmission. Verify regulations before testing the system. Particular attention must be observed the first time the system is turned on and able to transmit. At this point the system will download a map detailing the areas where transmission is and is not allowed. This map will take effect on the next power-up.A. Testing and Commissioning Process with Restrictions(1) The JetWave™ system under normal operating conditions mutes transmit and also disables the modem when the Air/Ground status in "On Ground".(2) The Air/Ground status will be set to "Air" when one of the conditions that follow are met (otherwise the Air/Ground status will be set to "On Ground"):• IF AES Configuration System KANDU Ground Speed is being received from the KANDU (Refer to SRS1525), and it has been received with non NULL valve, and is indicating a ground speed of greater than 50 knots, orDraft as of 31 May 2017
Page 6-18 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.• If AES Configuration System wow is configured to be connected and it is indicating it is in the air. (3) Ground transmission can be enabled by asserting the ground transmit enable discrete of the JetWave™ system.(a) The ground operation depends on location and country of aircraft registration.(b) The reason for restrictions on transmission from the current aircraft location can be accessed through the GUI Home page under text display “Reasons for Transmission Mute”.(4) For the testing and commissioning process, the aircraft must be positioned so as to have a clear line of sight to the satellite. (5) To control the transmission of the terminal within certain locations and at different heights, the terminal stores and uses a geographical map. The map indicates regions around the globe where the terminal may legally transmit. The map is provided by Inmarsat and requested by the terminal when it first enters the network. The terminal will retrieve the map file from the Inmarsat server using the FTP protocol over the management VLAN. Make sure that this ground test procedure is being performed in a location that permits operation on the ground for the terminal's configured geographic map.B. Data Link Available (Control Panel) OutputOnce 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 6-8.Make sure the “Datalink Available” status is indicated in the control panel. 6.7 Final System CheckoutA. Network StatusNavigate to the AES Summary and Link Status page and scroll down to see the Network status of the JetWave™ system. An example of an AES network status is shown in Figure 6-15. Make sure that the network connectivity is in accordance with the aircraft configuration plan. With the use of another laptop, make sure that there is 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 there is 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 the internet is established, move the aircraft around in a circular 360 degree pattern (no faster than 3° per second). Draft as of 31 May 2017
Page 6-19 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.NOTE: Based on the geographical location, surrounding obstructions, etc., the 360 degree connectivity access can be limited.Verify that the connectivity remains available through the 360-degree turn by monitoring the datalink status discrete.Connect to each of the configured Ethernet ports to make sure there is data connectivity.Figure 6-15. Network StatusesB. 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 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 Aircraft Statuses as part of the AES Summary and Link Status page. Refer to Figure 6-9.(5) In case of any RF interference, there will be significant variation of the C/N and Eb/No parameters. Draft as of 31 May 2017
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Page 7-1 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.SECTION 7TROUBLESHOOTING7.1 Post-installation TroubleshootingThis section supplies troubleshooting procedures for the JetWave™ system. Airline maintenance engineers can troubleshoot the JetWave™ system on the ground, with the health status information and Fault Details and Isolation assistance displayed on the AES GUI.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.7.2 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 are available 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 7-1 for the screen-shot of the login page.Figure 7-1. AES GUI Login PageDraft as of 31 May 2017
Page 7-2 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(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”.• 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 7-2 shows the log out page.Figure 7-2. JetWave™ Logout PageA. 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 7-3 shows the GUI page listing the health status of JetWave™ system LRUs.NOTE: The Health Status page does not automaticaly refresh. (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 a critical LRU fault is 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 Draft as of 31 May 2017
Page 7-3 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.configuration data is supplied. Figure 7-3 shows the AES Summary and Link Status page.Figure 7-3. JetWave™ Summary and Link Status (Sheet 1 of 2)Draft as of 31 May 2017
Page 7-4 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 7-3. JetWave™ Summary and Link Status (Sheet 2 of 2)(2) The JetWave™ system status can be viewed through the GUI. Refer to AES system status verification section on page 6-3 for description.SUmmary and link statusB. Downloading LRU Logs(1) To view the historical fault logs, under the AES historical logs pane, select the "Fault Log". A screenshot of fault log page is shown in Figure 7-4.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 records as follows: • Since power on• Number of days and select actual number of days from the dropdown (not reconmended)• 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. Draft as of 31 May 2017
Page 7-5 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 7-4. 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 7-5 for an example of a viewable fault log.Draft as of 31 May 2017
Page 7-6 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 7-5. 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 7-6 will come into view. Save to the computer to open and view the fault log.Figure 7-6. JetWave™ Fault Log Download PageDraft as of 31 May 2017
Page 7-7 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.C. System Data Load 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 ARINC 615A data loader is connected to the correct port:NOTE: Port AV1 is by default the Modman Maintenance Port, but this may have been modified by the APM configuration loaded.D. System ResetThe JetWave™ system can be reset with any of the methods that follow: • GUI• Through the SNMP• By grounding the Modman Reset Pin (MP10C).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. The operator's JetWave Customer Support can be contacted for further support.E. 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. 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.WARNING: FAILURE TO DISCONNECT CIRCUIT BREAKERS CAN LEAD TO INJURY TO THE OPERATOR AND DAMAGE TO THE EQUIPMENT. (1) Disconnect all circuit breakers to the JetWave™ AES OAE assembly, LRUs and associated systems.(2) Visually examine the FMA or TMA radome for any damage or defects. Please refer to the radome supplier’s Structural Repair Manual (SRM) for the specific radome inspection and damage repair instructions.NOTE: Saint Gobain SRM-100 is applicable to all radomes. FMA radome, PN SCD-90401395-01, is covered specifically by Saint Gobain SRM-5249 structural repair manual.Draft as of 31 May 2017
Page 7-8 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.G. JetWave™ System Fault Codes(1) BITE Philosophy(a) Description1The JetWave™ AES consists of the Modman, KANDU, KRFU, TMA or FMA LRUs, plus the APM.2The 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.3The BITE system divides the responsibility for BITE and historical logs in a BITE hierarchy as illustrated in Figure 7-7.Figure 7-7. Bite Hierarchy4In charge of the 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.5Each 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).6The 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 7-8.Draft as of 31 May 2017
Page 7-9 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Figure 7-8. AES and LRU Controller Interaction7The AES Controller resides in the Modman LRU.8Each 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).• Events: These are BITE events which occur but do not have a set or clear state.9The 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.10 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.Draft as of 31 May 2017
Page 7-10 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.11 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.12 The AES controller has its own historical logs which allow it to record events about the whole system.13 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.14 The LRU and AES remember information about BITE events that have occurred, in both non-volatile memory and volatile memory.15 The historical logs are kept by the LRU and AES controller.16 Each BITE event is described by an LRU code, encoded in three numbers (L1, L2 and L3) to uniquely identify the event.17 Section 5 has more details on the format of this LRU code system.18 The BITE events themselves have a description of the L1 thru L3 code and the additional text to be used for that event.19 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.(a) Status Memory1The 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 service and transmission.Draft as of 31 May 2017
Page 7-11 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.• 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”.2The LRUs remember 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.• 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.Draft as of 31 May 2017
Page 7-12 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(2) LRU CodesBITE 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 a 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.(3) L1 Codes(a) The event L1 code uses two hexadecimal digits to identify a LRU or an interface within an AES LRU, coded as follows:Table 7-1. L1 Codes Group L1 Code L1 DescriptionSystem 0x 00 SystemThe 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 Modman0x 02 KRFU0x 03 TMA0x 04 FMA0x 05 APM0x 06 KANDUDraft as of 31 May 2017
Page 7-13 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Intra-system Interconnect 0x 20 Modman KANDU Ethernet bus0x 21 Modman APM serial bus0x 23 Modman input discretes from LRU0x 24 Modman output discretes0x 30 KANDU OAE Ethernet Bus0x 31 KANDU OAE Serial Control Bus 0x 32 KANDU OAE serial IMU bus0x 33 KANDU KRFU serial bus0x 34 KANDU input discretes from OAE0x 35 KANDU input discretes from Modman0x 36 KANDU input discretes from KRFU0x 41 KRFU input discretes from KANDU0x B0 RF TX Modman to KRFU0x B1 RF TX KRFU to OAE0x B2 RF RXAircraft Interconnect 0x 70 IRU input bus0x 71 Aircraft state input bus0x 72 Modman aircraft discrete input0x 73 KANDU aircraft discrete inputAISD Network 0x 80 AISD Network: Ethernet AG10x 81 AISD Network: Ethernet AV10x 82 AISD Network: Ethernet AV20x 83 AISD Network: Ethernet AV3PIESD Network 0x 88 PIESD Network: Ethernet EG10x 89 PIESD Network: Ethernet EN50x 8A PIESD Network: Ethernet EN60x 8B PIESD Network: Ethernet EN70x 8C PIESD Network: Ethernet EN8Table 7-1. L1 Codes (Continued)Group L1 Code L1 DescriptionDraft as of 31 May 2017
Page 7-14 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.NOTE: All other codes not explicitly stated are spare.(4) L2 Codes(a) The event L2 code uses two hexadecimal digits to identify a shop-replaceable module within an AES LRU, coded as follows:PODD Network 0x 90 PODD Network: Ethernet PG10x 91 PODD Network: Ethernet PA10x 92 PODD Network: Ethernet PA20x 93 PODD Network: Ethernet PA30x 94 PODD Network: Ethernet PA4Table 7-2. L2 Codes – Module Within an AES LRU L1 L2 Code L2 DescriptionSystem (00) 0x 00 Unknown0x 01 Mode0x 02 AES menu access level0x 03 Configuration0x 04 AES SFTP0x 05 SNMP engineering0x 06 SNMP ARINC 7910x 07 Regulatory logs0x 08 Information eventsModman (01) 0x 00 Unknown0x 01 ACM0x 02 Controller/Router0x 03 Power supply unit0x 04 Backplane0x FA Operational information0x FB IP security0x FC Reset0x FD Software configuration0x FE Software runtimeTable 7-1. L1 Codes (Continued)Group L1 Code L1 DescriptionDraft as of 31 May 2017
Page 7-15 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Modman (01) 0x FF TemperatureKRFU (02) 0x 00 Unknown0x 01 Power supply unit0x 02 Block up converter0x 04 Power amplifier0x 05 Monitor and control0x 07 Fan0x 08 Failed on start-up0x 2A BDC0x FA Operational information0x FC Reset0x FD Software configuration0x FE Software runtime0x FF TemperatureTMA (03)FMA (04) 0x 00 Unknown or not applicable0x 02 Inertial measurement unit0x 03 Low noise amplifier0x 04 Motors and sensors0x 05 Position control unit0x 06 Power supply unit0x 0B MDU0x 0C R2D0x FA Operational information0x FB IP security (FMA only)0x FC Reset0x FD Software configuration0x FE Software runtime0x FF TemperatureAPM (05) 0x FA Operational information0x FD Software configurationTable 7-2. L2 Codes – Module Within an AES LRU (Continued)L1 L2 Code L2 DescriptionDraft as of 31 May 2017
Page 7-16 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(b) The event L2 code further identifies specific inter LRU interfaces, coded as follows:KANDU (06) 0x 00 Unknown or not applicable0x 01 ASC0x 02 Power supply unit0x 11 ASC BITE EMIFA0x 12 ASC BITE A429 IRS0x 13 ASC BITE A429 AUX0x 14 ASC BITE Ethernet switch0x FA Operational information0x FB IP security0x FC Reset0x FD Software configuration0x FE Software runtime0x FF TemperatureTable 7-3. L2 Codes – Inter LRU Interfaces L1 L2 Code L2 DescriptionModman KANDU Ethernet bus (20) 0x 01 Modman input0x 02 KANDU inputModman APM Serial Bus (21) 0x 01 Modman inputModman Input discretes from KANDU (23) 0x 00 UnknownModman Output: Discrete from Modman (24) 0x 01 Reset0x 02 ARINC TX mute0x 03 Filter select0x 04 Keyline transmit0x 05 System available0x 06 Data link availableKANDU OAE Ethernet Bus (30) 0x 01 KANDU input0x 02 OAE inputTable 7-2. L2 Codes – Module Within an AES LRU (Continued)L1 L2 Code L2 DescriptionDraft as of 31 May 2017
Page 7-17 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.KANDU OAE Serial Control Bus (31) 0x 01 KANDU input0x 02 OAE inputKANDU OAE Serial IMU Bus (32) 0x 01 KANDU input0x 02 OAE inputKANDU KRFU Serial Bus (33) 0x 01 KANDU input0x 02 KRFU inputKANDU Input: Discrete from OAE (34) 0x 01 FMA TX mute inputKANDU Input: Discrete from Modman (35) 0x 01 Reset0x 02 ARINC TX mute0x 03 Filter select0x 04 TX MuteKANDU Input: Discrete from KRFU (36) 0x 00 UnknownKRFU Input: Discrete from KANDU (41) 0x 01 Reset0x 02 KRFU TX mute0x 03 Filter selectRF TX Modman to KRFU (B0) 0x 00 UnknownRF TX KRFU to OAE (B1) 0x 00 UnknownRF RX(B2) 0x 00 UnknownTable 7-3. L2 Codes – Inter LRU Interfaces (Continued)L1 L2 Code L2 DescriptionDraft as of 31 May 2017
Page 7-18 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(c) The event L2 code further identifies ARINC 429 and ARINC 791 discrete interfaces, coded as follows:Table 7-4. L2 Codes – ARINC Discrete InterfacesL1 L2 Code L2 DescriptionIRU Input Bus (70)Aircraft state Bus (71) 0x 00 Unknown0x 01 Pitch angle label0x 02 Roll angle label0x 03 Pitch rate label0x 04 Roll rate label0x 05 Yaw rate label0x 06 Body longitudinal acceleration0x 07 Body vertical acceleration0x 08 True heading labelIRU Input Bus (70)Aircraft state Bus (71)0x 09 Body lateral acceleration0x 11 Latitude label0x 12 Longitude label0x 13 Altitude0x 14 Vertical velocity0x 15 N-S velocity0x 16 E-W velocity0x 21 Horizontal stabilization0x 31 Time label0x 32 Date label0x 41 Flight phase label0x 42 MLG ground condition0x 80 GNSS sensor status word 0x 81 IRS discrete word #1Draft as of 31 May 2017
Page 7-19 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(d) The event L2 code further identifies user interfaces, coded as followsModman Aircraft Discrete Input (72) 0x 06 WOW0x 07 Cell TX OK0x 08 Ground transmit enable0x 09 Public services disable0x 0A Remote manager0x 0B Cooling available0x 0C Local data loadKANDU Aircraft Discrete Input (73) 0x 0C TX controlTable 7-5. L2 Codes – User InterfaceL1 L2 Code L2 DescriptionAISD 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 inputTable 7-4. L2 Codes – ARINC Discrete InterfacesL1 L2 Code L2 DescriptionDraft as of 31 May 2017
Page 7-20 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(5) L3 Codes (a) The L3 code is four hexadecimal digits, used to uniquely identify the fault or event against an L1, L2 code pair.(b) Each LRU defines their own L3 codes. These are given in the fault table, refer to Table 7-6.Table 7-6. L3 Codes L1 L2 L3 Code L3 Description Repair ActionSystem (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 - Info events - Recording what happened in the LRU.- If it is a warning, It is info only.0x 0001 Data Load mode entry0x 0002 Commanded mode entry0x 0003 Normal mode entryAES menu access level (02)0x 0000 Maintenance0x 0001 Factory0x 0002 Engineering0x 0021 Log clearance AES operational historical log0x 0022 Log clearance AES fault historical logDraft as of 31 May 2017
Page 7-21 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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 aircraft0x 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 it is defective 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 it is defective since the APM should not forget an APM file), do the first fit operation again.AES SFTP (04) 0x 0000 Maintenance - Info events - Recording what happened in the LRU.- If it is a warning, it is info only.0x 0001 Factory0x 0002 EngineeringSNMP Engineering (05)0x 0000 Maintenance0x 0001 Factory0x 0002 Engineering0x 0021 Log clearance AES operational historical log0x 0022 Log clearance AES fault historical log0x 0023 Log clearance AES usage historical logSNMP ARINC 791 (06)0x 0000 Maintenance0x 0001 Factory0x 0002 EngineeringTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-22 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.System (00)Regulatory Log (07)0x 0000 Regulatory log upload failure NO ACTION –System will continue to try and upload the file as directed by the regulatory log requirements on frequency of upload attempts. 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. User data traffic will be disabled until the log is successfully uploaded.Information Events (08)0x 0000 User service enabled NO ACTION: - This is AES Information Event0x 0001 User service disabled NO ACTION: - Will recover next time0x 0002 Geographic map stored NO ACTION: - This is information event0x 0003 Geographic map download failed NO ACTION: - Will recover next system power cycle.0x 0004 Aircraft on ground NO ACTION: - This is Information Event0x 0005 Aircraft in air NO ACTION: - This is Information Event0x 0006 AES in network NO ACTION: - This is Information Event0x 0007 AES out of network NO ACTION: - This is Information Event0x 0008 AES network operating parameters NO ACTION: - This is Information EventSoftware Runtime (FE)0x 0000 No Comms with OAE – KANDU OK No action required, software faults and events are dealt with by criticality in the following manner: -Critical: An unrecoverable software error has occurred, the system will reset in order to recover. -Warning: An unexpected but recoverable software error has occurred, the system will continue normal operation. -Information: Recording information related to software execution within the LRU. 0x 0001 System POST Event0x 0002 LRU Comms Established0x 0003 LRU Comms Not EstablishedTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-23 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Modman (01)Unknown (00) 0x 0000 Mute state Info events - Recording what happened in the LRU.0x 0011 LRU menu access - maintenance0x 0012 LRU menu access - factory0x 0013 LRU menu access - engineering0x 0014 LRU SFTP access - maintenance0x 0015 LRU SFTP access - factory0x 0016 LRU SFTP access - engineering0x 0021 Log clearance LRU operational0x 0022 Log clearance LRU faultACM (01) 0x 0001 ACM not responding Hardware faults and events:- Replace the Modman.0x 0002 ACM BIST fault0x 0003 ACM over tempController/router (02)0x 0001 DSP Fault0x 0002 Ethernet Main Switch0x 0003 Ethernet PODD SwitchTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-24 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Modman (01)Controller/router (02)0x 0004 Ethernet PIES Switch Hardware faults and events:- Replace the Modman.0x 0005 Ethernet AISD Switch0x 0006 Down converter0x 0007 NOR flash0x 0008 NAND flash0x 0009 A429 driver0x 000B Reset control I/O0x 000C Board config I/O0x 000D Ethernet FP PHY0x 000E Ethernet ACM PHY0x 000F Ethernet EN3 PHY0x 0010 Ethernet Server PHY0x 0011 Ethernet AV1 PHY0x 0012 Ethernet AV2 PHY0x 0013 Ethernet AV3 PHY0x 0014 Ethernet AG1 PHY0x 0015 Ethernet EN5 PHY0x 0016 Ethernet EN6 PHY0x 0017 Ethernet EN7 PHY0x 0018 Ethernet EN8 PHY0x 0019 Ethernet EG1 PHY0x 001A Ethernet PA1 PHY0x 001B Ethernet PA2 PHY0x 001C Ethernet PA3 PHY0x 001D Ethernet PA4 PHY0x 001E Ethernet PG1 PHY0x 001F MM & ACD ETH link status IO0x 0020 PIES/PODD ETH link status IO0x 0021 BITE status inputs IO0x 0022 Server card in/out IOTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-25 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Modman (01)Controller /router (02)0x 0023 RSSI control in/out IO Hardware faults and events:- Replace the Modman.0x 0024 Unique ID chip0x 0030 5V ISO good - power fail0x 0031 12V ISO good - power fail0x 0032 1V2 AR power good - power fail0x 0033 APM power good - power fail0x 0034 RSSI VDD power good - power fail0X0035 RSSI +1V3 power good - power failPower supply unit (03)0x 0001 PSU input power fail0x 0002 PSU good power failBackplane (04) 0x 0001 ACM 18V power goodOperational information (FA)0x 0000 Mode Transition Info events - Recording what happened in the LRU.0x 0001 Parameter0x 0002 Operational event0x 0004 Connect event0x 0005 Disconnect event0x 0006 User Bytes passed0x 000A Standard electronic information0x 000B Honeywell electronic information0x 000C Subassembly informationIP security (FB) 0x 0000 Critical IP events NO ACTION:- This is information event.0x 0001 Warning IP security events NO ACTION:- This is information event.0x 0020 Configuration fault Use correct network configurationReset (FC) 0x 0000 Power Cycle Info events - Recording what happened in the LRU.0x 0001 Watchdog0x 0002 Software Command0x 0003 Reset Pin Info events - Recording what happened in the LRU.0x 0004 SW exceptionTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-26 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Modman (01)Software configuration (FD)0x 0001 HW SW compatibility Reload compatible software with the A615A data loading process.0x 0002 LRU SW compatibility0x 0003 Configuration parameter missing Reload the configuration data with the A615A data loading process.0x 0004 Primary image corruption warning - Reboot the LRU after 10 minutes of power application. - If not, then reloading of software is required to load a 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 after 10 minutes of power application. - If not, then a reloading of software is required to load a fresh image.0x 0007 Data load Info events - Recording what happened in the LRU. 0x 0008 Data loader connect0x 0009 Data loader disconnect0x 000A Operating image list0x 000B Secondary image corruption warning Perform a system reset.0X 0040 VLAN MAPPING TO SPECIFIC PORTS DISALLOWEDNO ACTION - It is info only. This warning gets generated if the mapping ordered by the ACM fails due to the configuration data.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-27 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Modman (01)Software runtime (FE)0x 0000 Heartbeat failure No Action required, software faults and events are dealt with by criticality in the following manner: -Critical: An unrecoverable software error has occured, the system will reset in order to recover. -Warning: An unexpected but recoverable software error has occured, the system will continue normal operation. -Information: Recording information related to software execution within the LRU.0x 0001 GENERAL module failure0x 0006 Application Controller Database Invalid0x 0007 Application Not Present0x 0008 Application Unable to Start0x 0009 Application fails during monitoring0x 000A Base Application Construction failure0x 000B Base Application Initialization failure0x 000C Base Application runtime warning0x 000D Base Application runtime failure0x 000E F&E DB fails to open0x 000F F&E DB invalid0x 0010 F&E ODB fails to open0x 0011 F&E code unknown0x 0012 F&E Networking error0x 0013 F&E Bite Action Error0x 0014 F&E Persistent DB fails to open0x 0015 F&E Persistent Store Write Error0x 0016 F&E Bite Action Inhibit0x 0017 Data Loader TFTP timeout0x 0018 Data Loader out of memory0x 0019 Data Loader Load Installer missing0x 001A Data Loader Load Installer memory error 0x 001B Data Loader primary image corruption0x 001C Data Loader incompatible image0x 001D ICC unable to load driver Missing KANDU Information - Ground0x 0020 Speed0x 0021 File System FullTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-28 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Modman (01)Software runtime (FE)0x 0022 ACM Load Installer - comms failure No Action required, software faults and events are dealt with by criticality in the following manner: -Critical: An unrecoverable software error has occurred, the system will reset in order to recover. -Warning: An unexpected but recoverable software error has occurred, the system will continue normal operation. -Information: Recording information related to software execution within the LRU.0x 0023 ACM Load Installer - package rejected0x 0024 ACM Load Installer - package activation failure0x 0025 ACM Load Installer - package activation successful0x 0026 AES Controller unable to open well known socket0x 0027 AES Controller network resource limitation - socket0x 0028 AES Controller server network resource limitation - buffer0x 0029 Switch fabric could not be configured for data load0x 002A ACM Manager Data Request0x 002B Maint MIB Invalid data0x 002C Maint MIB data not in correct format0x 002D Maint MIB data not in correct format0x 002E Network SNMP agent Database Invalid0x 002F Network SNMP No NSC response 0x 0030 Network SNMP - no valid data 0x 0031 ACM Power Transition0x 0032 DNS Fails named lookup0x 0033 Network switch control error0x 0034 RSSI Engine Lock status changed0x 0035 RSSI Engine Sampling fault0x 0036 RSSI Engine Internal software fault0x 0050 C/R Post Time OutTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-29 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Modman (01)Software runtime (FE)0x 0800 MES client registration fails No Action required, software faults and events are dealt with by criticality in the following manner: -Critical: An unrecoverable software error has occurred, the system will reset in order to recover. -Warning: An unexpected but recoverable software error has occurred, the system will continue normal operation. -Information: Recording information related to software execution within the LRU.0x 0801 MES client publish fail due to attempted blocking send0x 0802 MES server unable to open well known socket0x 0803 MES server network resource limitation - socket 0x 0804 MES server network resource limitation - buffer0x 0805 MES server message ID map corruption0x 0806 MES Client receives non-subscribed message0x 0807 MES proxy database invalid0x 0808 MES proxy cannot remotely subscribe0x 0809 EUI data missing0x 080A ACM General Error0x 080B APM Client - Data not available0x 080C APM Client - Data validated0x 080D APM Client - Data not validated0x 080E RSSI Manager unable to open well known socketTemperature(FF)0x 0001 C/R temperature sensor 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.0x 0002 PSU temperature sensorTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-30 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.KRFU (02)Unknown (00) 0x 0000 Mute state Info events - Recording what happened in the LRU.0x 0001 Primary power interruptionPower supply (01)0x 0002 Power supply internal fault Hardware faults and events:- Replace the KRFUBlock up converter (02)0x 0001 BUC lockloss: Transmit BITE status0x 0002 BUC lockloss: Transmit BITE statusPower amplifier (04)0x 0002 PA overdriven: Transmit BITE statusMonitor and control (05)0x 0001 Flash fault0x 0002 RAM fault0x 0003 Watchdog resetBDC (2A) 0x 0001 BITE status0x 0002 BDC lockloss: Receive It is info only. KRFU recovered from the loss of KANDU heartbeats.Operational information (FA)0x 000A Standard electronic information Info events - Recording what happened in the LRU.0x 000B Honeywell electronic informationReset (FC) 0x 0001 Watchdog0x 0002 Software command0x 0004 SW exception0x 0005 Power cycle or Reset pinSoftware configuration (FD)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 reloading of software is required to load a fresh image0x 0006 LRU PRI-SEC image mismatch - Reboot the LRU to load valid primary image and check if fault goes away. - If not, then reloading of software is required to load a fresh imageTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-31 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.KRFU (02)Software configuration (FD)0x 0007 Data load Info events - Recording what happened in the LRU.0x 000A Operating image list0x 0008 Data loader connected0x 0009 Data loader disconnected0x 000B Secondary image corruption warning A reloading of software is required to load a fresh image.Software runtime (FE)0x 0000 KRFU - KANDU Heartbeat failure No Action required, software faults and events are dealt with by criticality in the following manner: -Critical: An unrecoverable software error has occurred, the system will reset in order to recover. -Warning: An unexpected but recoverable software error has occurred, the system will continue normal operation. -Information: Recording information related to software execution within the LRU.0x 0001 KANDU - KRFU heartbeat failureTemperature (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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-32 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.TMA (03) Unknown (00) 0x 0001 Primary power interruption Info events - Recording what happened in the LRU.0x 0011 LRU menu access - maintenance0x 0012 LRU menu access - factory0x 0013 LRU menu access - engineering0x 0014 LRU SFTP access - maintenance0x 0015 LRU SFTP access - factory0x 0016 LRU SFTP access - engineering0x 0021 Log clearance LRU operational0x 0022 Log clearance LRU faultInertial Measurement Unit (02)0x 0001 No response Replace the TMALNA (03) 0x 0001 LNA current 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.Motor and sensors (04)0x 0001 AZ sensor detection0x 0002 EL INIT sensor detection0x 0003 EL LIMIT sensor detectionTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-33 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.TMA (03) Position control unit (05)0x 0001 DSP fault 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 0002 AZ motor current draw0x 0003 El motor current draw0x 0004 Initialization incompletePSU (06) 0x 0003 OMAP PWR 3.3V: Out-of Spec0x 0004 OMAP PWR 5V: Out-of Spec0x 0005 MOT PWR 12V: Out-of Spec0x 0006 LNA PWR 12V: Out-of SpecOperational information (FA)0x 0000 Mode transition Info events - Recording what happened in the LRU0x 0001 Parameter0x 0002 Event0x 000A Standard electronic information0x 000B Honeywell electronic information0x 000C Subassembly informationIP Security (FB) 0x 0000 IP Security event Use well defined port and IP AddressReset (FC) 0x 0000 Power cycle Info events - Recording what happened in the LRU0x 0001 Watchdog0x 0002 Software command0x 0004 SW exceptionTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-34 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.TMA (03) Software Configuration (FD)0x 0001 HW SW compatibility Reload compatible software with the A615A data loading process.0x 0002 LRU SW compatibility0x 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 reloading of software is required to load a fresh image.0x 0006 TMA PRI-SEC image mismatch - Reboot the LRU to load valid primary image and check if fault goes away. - If not, then reloading of software is required to load a fresh image.0x 0007 Data load Info events:- Recording what happened in the LRU.0x 0008 Data loader connect0x 0009 Data loader disconnect0x 000A Operating image list0x 000B Secondary image corruption warning A reloading software is required to load a fresh image.Software runtime (FE)0x 0000 Heartbeat failure No Action required, software faults and events are dealt with by criticality in the following manner: -Critical: An unrecoverable software error has occurred, the system will reset in order to recover. -Warning: An unexpected but recoverable software error has occurred, the system will continue normal operation. -Information: Recording information related to software execution within the LRU.0x 0001 DSP task timeout0x 0002 ARM-DSP communication0x 0003 DSP task timeout0x 0004 ARM-DSP COMMUNICATION0x 0005 Application Controller Database Invalid 0x 0006 Application Not Present0x 0007 Application Unable to Start0x 0008 Application fails during monitoring0x 0009 Application fails during monitoring0x 000A Base Application Construction failure0x 000B Base Application Initialization failureTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-35 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.TMA (03) Software runtime (FE)0x 000C Base Application runtime warning No Action required, software faults and events are dealt with by criticality in the following manner: -Critical: An unrecoverable software error has occurred, the system will reset in order to recover. -Warning: An unexpected but recoverable software error has occurred, the system will continue normal operation. -Information: Recording information related to software execution within the LRU.0x 000D Base Application runtime failure0x 000E F&E DB fails to open0x 000F F&E DB invalid0x 0010 F&E ODB fails to open0x 0011 F&E code unknown0x 0012 F&E Networking error0x 0013 F&E Bite Action error0x 0014 F&E Persistent DB fails to open0x 0015 F&E Persistent Store Write error0x 0016 F&E Bite Action inhibit0x 0017 Data Loader TFTP timeout0x 0018 Data Loader out of memory0x 0019 Data Loader Load installer missing0x 001A Data Loader Load installer memory error0x 001B Data Loader primary image corruption0x 001C Data Loader incompatible image0x 001D ICC unable to load driver0x 001E Inter LRU serial comms overrun0x 001F Tunnel interface errors0x 0021 Alignment - fail to open file0x 0022 Alignment - empty file0x 0023 Alignment - corrupt file0x 0024 Alignment - write file0x 0025 Configuration Data Manager ICC open failure0x 0026 Configuration Data Manager Database not consistent0x 0027 TMA Controller ICC open failure0x 002A DSP Manager Data Manager ICC open failure0x 002B DSP Manager Task’s stoppedTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-36 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.TMA (03) Software runtime (FE)0x 002C DSP Manager heartbeat failure No Action required, software faults and events are dealt with by criticality in the following manner: -Critical: An unrecoverable software error has occurred, the system will reset in order to recover. -Warning: An unexpected but recoverable software error has occurred, the system will continue normal operation. -Information: Recording information related to software execution within the LRU.0x 002D OAE Configuration Data Manager incompatible version data0x 002E DSP Application Manager unable to allocate resources0x 0046 Unable to allocate ICC transmit buffer0x 0047 IP Tunnel driver - fails to initialize0x 0048 Tunnel Driver ICC open failure0x 0049 Unable to configure routing to ASC0x 004A TMA/KANDU network configuration conflict0x 0050 Post Timeout0x 0800 MES client registration fails0x 0801 MES client publish fail due to attempted blocking send0x 0802 MES server unable to open well known socket0x 0803 MES server network resource limitation - socket0x 0804 MES server network resource limitation - buffer0x 0805 MES server message ID map corruption 0x 0806 MES client receives non-subscribed message0x 0807 MES proxy database invalid0x 0808 MES proxy cannot remotely subscribe0x 0809 EUI data missing0x 080A ACM General Error0x 080B APM Client - Data not available0x 080C APM Client - Data validated0x 080D APM Client - Data not validated 0x 080E RSSI Manager unable to open well known socketTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-37 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.TMA (03) Temperature (FF)0x 0001 Motor driver circuit - If is a warning, it is for info only.- If it is critical, the LRU shut itself down functionally: suggest the LRU is not correctly installed or a subassembly in the LRU may be generating too much heat.0x 0002 Ambient FMA (04) Unknown (00) 0x 0001 Enter shed load Info events - Recording what happened in the LRU.0x 0002 Exit shed load0x 0011 LRU menu access - maintenanceTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-38 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.FMA (04)Unknown (00) 0x 0012 LRU menu access - factory Info events - Recording what happened in the LRU0x 0013 LRU menu access - engineering0x 0014 LRU SFTP access - maintenanceUnknown (00) 0x 0015 LRU SFTP access - factory Info events - Recording what happened in the LRU0x 0016 LRU SFTP access - engineering0x 0021 Log clearance LRU operational0x 0022 Log clearance LRU fault0x 0081 Azimuth home find fail Hardware faults and events:- Replace the FMA.0x 0082 Elevation home find fail0x 0085 Ice breaker AZ0x 0086 Ice breaker EL0x 0087 Azimuth axis out of band0x 0088 Elevation axis out of bandInertial measurement unit (02)0x 0001 No response Replace the FMAPosition control unit (05)0x 0001 DSP fault Hardware faults and events:- Replace the FMA.0x 0081 1.2V voltage0x 0082 1.5V voltage0x 0083 1.8V voltage0x 0084 3.3V voltage0x 0085 5V positive voltage0x 0086 1.2V current0x 0087 1.5V current 0x 0088 1.8V current0x 0089 3.3V current0x 008A 5V positive currentPSU (06) 0x 0003 PSU low power detected0x 0004 PSU low power not detected0x 0005 PSU LNA current eventTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-39 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.FMA (04) MDU (0B) 0x 0001 1.25V voltage Hardware faults and events:- Replace the FMA.0x 0002 1.5V voltage0x 0003 3.3V voltage0x 0004 12V positive voltage0x 0005 12V negative voltage0x 0006 38.5V voltage0x 0007 1.5V current0x 0008 3.3V current0x 0009 12V positive current 0x 000A 12V negative current0x 000B Serial communications failure0x 000C Azimuth motor current 0x 000D Elevation motor current 0x 000E Serial communications failure0x 000F Azimuth axis low temperature high current failed0x 0010 Elevation axis low temperature high currentR2D (0C) 0x 0001 1.5V voltage0x 0002 3.3V voltage0x 0003 5V digital voltage0x 0004 5V positive voltage0x 0005 5V negative voltage0x 0006 12V positive voltage0x 0007 12V negative voltage0x 0008 1.5V current0x 0009 3.3V current0x 000A 12V positive current0x 000B 12V negative current0x 000F Serial communications failure0x 0010 CCA initialization failedTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-40 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.FMA (04) R2D (0C) 0x 0011 Azimuth axis resolver reading error Hardware faults and events:- Replace the FMA0x 0012 Elevation axis resolver reading errorOperational information (FA)0x 0000 Mode transition Info events - Recording what happened in the LRU0x 0001 Parameter0x 0002 Event0x 000A Standard electronic information0x 000B Honeywell electronic information0x 000C Subassembly informationIP security (FB) 0x 0000 IP security eventReset (FC) 0x 0000 Power cycle0x 0001 Watchdog0x 0002 Software command0x 0003 RESET PIN0x 0004 SW exceptionSoftware configuration (FD)0x 0001 HW SW Compatibility Reload compatible software with the A615A data loading process.0x 0002 LRU SW Compatibility0x 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 reloading of software is required to load a fresh image.0x 0006 LRU PRI-SEC image mismatch - Reboot the LRU to load valid primary image and check if fault goes away. - If not, then reloading of software is required to load a fresh image.0x 0007 Data load Info events- Recording what happened in the LRU.0x 0008 Data loader connect0x 0009 Data loader disconnect0x 000A Operating image listFMA (04) Software configuration (FD)0x 000B Secondary image corruption warning A reloading of software is required to load a fresh image.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-41 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.FMA (04) Software runtime (FE)0x 0000 Heartbeat failure Software events:- Critical, will cause the unit to reset.-Warning, then the event was unexpected, and may cause shortened life but does not stop current function. -Info, recording what happened in the LRU.(For software faults there is no reason to return box.)0x 0001 General Module Failure0x 0006 Application Controller Database Invalid0x 0007 Application Not Present0x 0008 Application Unable to Start0x 0009 Application fails during monitoring0x 000A Base Application Construction failure0x 000B Base Application Initialization 0x 000C Base Application runtime warning0x 000D Base Application runtime failure0x 000E F&E DB fails to open0x 000F F&E DB invalid0x 0010 F&E ODB fails to open0x 0011 F&E code unknown0x 0012 F&E Networking error0x 0013 F&E Bite Action error0x 0014 F&E Persistent DB fails to open0x 0015 F&E Persistent Store Write error0x 0016 F&E Bite Action Inhibit0x 0017 Data Loader TFTP timeout0x 0018 Data Loader out of memory0x 0019 Data Loader Load installer missing0x 001A Data Loader Load Installer memory error0x 001B Data Loader primary image corruption error0x 001C Data Loader incompatible image0x 001D ICC unable to load driver0x 0020 File System Full0x 0021 Alignment - fail to open file0x 0022 Alignment - empty fileTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-42 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.FMA (04) Software runtime (FE)0x 0023 Alignment - corrupt file Software events:- Critical, will cause the unit to reset.-Warning, then the event was unexpected, and may cause shortened life but does not stop current function. -Info, recording what happened in the LRU.(For software faults there is no reason to return box.)0x 0024 Alignment - write fail0x 0026 Configuration Data Manager ICC open failure0x 0027 Configuration Data Manager Database not consistent0x 0028 FMA Controller ICC open failure0x 002A DSP Manager Data Manager ICC open failure0x 002B DSP Manager Task’s stopped0x 002C DSP Manager heartbeat failure0x 002D OAE Configuration Data Manager incompatible version data0x 002E DSP Application Manager unable to allocate resources0x 0050 Post Timeout0x 0800 MES client registration fails0x 0801 MES client publish fail due to attempted blocking send0x 0802 MES server unable to open well known socket0x 0803 MES server network resource limitation - socket0x 0804 MES server network resource limitation - buffer0x 0805 MES server message ID map corruption0x 0806 MES Client receives non-subscribed message 0x 0807 MES Proxy database invalid0x 0808 MES Proxy cannot remotely subscribe0x 0809 EUI data missing0x 080A ACM General Error0x 080B APM Client - Data not available0x 080C APM Client - Data validatedTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-43 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.FMA (04) Software runtime (FE)0x 080D APM Client - Data not validated Software events:- Critical, will cause the unit to reset.-Warning, then the event was unexpected, and may cause shortened life but does not stop current function. -Info, recording what happened in the LRU.(For software faults there is no reason to return box.)0x 080E RSSI Manager unable to open well known socketTemperature (FF)0x 0001 PCU CCA - 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 a subassembly in the LRU may be generating too much heat.0x 0004 R2D CCA0x 0005 MDU CCA0x 0006 Azimuth Motor0x 0007 Elevation MotorAPM (05) Software configuration (FD)0x 0007 Data load Info events - Recording what happened in the LRU0x 0008 Data loader connected0x 0009 Data loader disconnectedOperational information (FA)0x 000A Standard electronic information0x 000B Honeywell electronic informationKANDU (06)Unknown (00) 0x 0000 Mute State0x 0001 Primary power interruption0x 0011 LRU menu access - maintenance0x 0012 LRU menu access - factory0x 0013 LRU menu access - engineering0x 0014 LRU SFTP access - maintenance0x 0015 LRU SFTP access - factory0x 0016 LRU SFTP access - engineering0x 0021 Log clearance LRU operational0x 0022 Log clearance LRU faultTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-44 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.KANDU (06)ASC (01) 0x 0001 DSP fault Hardware faults and events:- Replace the KANDU.0x 0020 ASC 1.2 V: Out-of-spec0x 0021 ASC 1.5 V: Out-of-spec0x 0022 ASC 1.8 V: Out-of-spec0x 0023 ASC 2.5 V: Out-of-spec0x 0024 ASC 3.3 V: Out-of-spec0x 0025 ASC 5.0 V: Out-of-spec0x 0026 ASC 12 V input: Out-of-spec0x 0027 ASC 1.2 V current: Out-of-spec0x 0028 ASC 1.5 V current: Out-of-spec0x 0029 ASC 1.8 V current: Out-of-spec0x 002A ASC 2.5 V current: Out-of-spec0x 002B ASC 3.3 V current: Out-of-spec0x 002C ASC 5 V current: Out-of-specPower supply unit (02)0x 0000 Power supply out of regulationASC BITE EMIFA (11)0x 0000 EMIFA unresponsive0x 0001 EMIFA incorrect data0x 0002 EMIFA OK0x 0003 EEPROM unresponsive0x 0004 EEPROM Incorrect Data0x 0005 EEPROM OKASC BITE A429 IRS (12)0x 0000 ARINC 429 IRS post unresponsive0x 0001 ARINC 429 IRS incorrect dataTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-45 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.KANDU (06)ASC BITE A429 IRS (12)0x 0002 ARINC 429 IRS post OK Hardware faults and events:- Replace the KANDU.ASC BITE A429 AUX (13)0x 0000 ARINC 429 AUX post unresponsive0x 0001 ARINC 429 AUX incorrect data0x 0002 ARINC 429 AUX post OKASC BITE Ethernet switch (14)0x 0000 Ethernet MDIO unresponsive0x 0001 Ethernet MDIO unexpected data0x 0002 Ethernet MDIO OKTemperature Multiple LRU (F9)0x 0001 thru 0x 007FUnique per temperature sensor with LRUOperational information (FA)0x 0000 Mode Transition Info events - Recording what happened in the LRU.0x 0001 Parameter0x 0002 Event0x 000A Standard electronic information0x 000B Honeywell electronic information0x 000C Subassembly information0x 0080 Auto Alignment Pass0x 0081 Auto Alignment Start0x 0082 Auto Alignment Fail Incorrect Modes0x 0083 Auto Alignment in Progress0x 0084 Auto Alignment Solution Check Pass0x 0085 Auto Alignment Solution Check Fail - Heading0x 0086 Auto Alignment Solution Check Fail - Pitch0x 0087 Auto Alignment Solution Check Fail - Roll0x 0088 Auto Alignment Solution Check Fail - RF%Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-46 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.KANDU (06)0x 0089 Auto Alignment CCW Check Info events - Recording what happened in the LRU0x 008A Auto Alignment CW Check0x 008B Auto Alignment Check Fail0x 008C Auto Alignment Fail - Sensor Fail0x 008D Auto Alignment Fail - OAE Comms Fail0x 008E Auto Alignment Fail - Init Physical Lock Fail0x 008F Auto Alignment Fail - Init RF Lock Fail0x 0090 Auto Alignment Fail - In Progress Physical Lock Fail0x 0091 Auto Alignment Fail - In Progress RF Lock FailIP security (FB) 0x 0000 IP security event Use well defined port and IP AddressReset (FC) 0x 0001 Watchdog Info events - Recording what happened in the LRU.0x 0002 Software command0x 0004 SW exception0x 0005 Power cycle or reset pinSoftware configuration (FD)0x 0001 HW SW Compatibility Reload compatible software with the A615A data loading process.0x 0002 LRU SW Compatibility0x 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, reloading of software is required to load a fresh image.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-47 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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, reloading of software is required to load a fresh image.0x 0007 Data load Info events - Recording what happened in the LRU0x 0008 Data loader connect0x 0009 Data loader disconnect0x 000A Operating image list0x 000B Secondary image corruption warning A reloading of software is required to load a fresh image.0x 0080 No valid alignment data Reload the configuration data with the A615A data loading process.Software runtime (FE)0x 0000 Heartbeat failure No Action required, software faults and events are dealt with by criticality in the following manner: -Critical: An unrecoverable software error has occurred, the system will reset in order to recover. -Warning: An unexpected but recoverable software error has occurred, the system will continue normal operation. -Information: Recording information related to software execution within the LRU.0x 0001 GENERAL Module failure0x 0002 RSSI Failure0x 0003 OPEN Amip failure0x 0004 Pointing failure0x 0006 Application Controller Database Invalid0x 0007 Application not Present0x 0008 Application Unable to Start 0x 0009 Application fails during monitoring 0x 000A Base Application Construction failure 0x 000B Base Application Initialization failure0x 000C Base Application runtime warning 0x 000D Base Application runtime failure0x 000E F&E DB fails to open0x 000F F&E DB invalid0x 0010 F&E ODB fails to open 0x 0011 F&E code unknown0x 0012 F&E Networking error0x 0013 F&E Bite Action Error0x 0014 F&E Persistent DB fails to openTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-48 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.KANDU (06)Software runtime (FE)0x 0015 F&E Persistent Store Write error No Action required, software faults and events are dealt with by criticality in the following manner: -Critical: An unrecoverable software error has occurred, the system will reset in order to recover. -Warning: An unexpected but recoverable software error has occurred, the system will continue normal operation. -Information: Recording information related to software execution within the LRU.0x 0016 F&E Bite Action Inhibit0x 0017 Data Loader TFTP timeout 0x 0018 Data Loader out of memory 0x 0019 Data Loader Load Installer missing 0x 001A Data Loader Load installer memory error 0x 001B Data Loader primary image corruption0x 001C Data Loader incompatible image0x 001D ICC unable to load driver0x 001E Inter LRU serial comms overrun0x 001F Tunnel interface errors0x 0020 FILE SYSTEM FULL 0x 0021 Aircraft Info Server – CVT register access failed0x 0022 Aircraft Info Server –no messages from DSP0x 0023 Aircraft Info Server ICC open failure0x 0024 Antenna Control Status - Configured for no OAE 0x 0025 Antenna Control Status – Configured for manual pointing 0x 0026 Antenna Control Status ICC open failure0x 0027 Configuration Data Manager ICC open failure0x 0028 Configuration Data Manager Database not consistent0x 0029 Configuration Data Manager OAE Alignment store no response 0x 002A Configuration Data Manager OAE Alignment store not consistent0x 002B DSP Manager Data Manager ICC open failure0x 002C DSP Manager Task’s stopped Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-49 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.KANDU (06)Software runtime (FE)0x 0031 DSP Manager heartbeat failure No Action required, software faults and events are dealt with by criticality in the following manner: -Critical: An unrecoverable software error has occurred, the system will reset in order to recover. -Warning: An unexpected but recoverable software error has occurred, the system will continue normal operation. -Information: Recording information related to software execution within the LRU.0x 0032 RSSI Manager ICC open failure0x 0033 RSSI Manager Loss of UDP messages0x 0034 Open AMIP unable to open well known socket0x 0035 Open AMIP resource limitation – buffer 0x 0036 Open AMIP Find protocol error0x 0037 Open AMIP Target satellite change0x 0038 Open AMIP Antenna Lock Status0x 0039 Open BMIP unable to open well known socket 0x 003A Open BMIP resource limitation – buffer0x 003B Open BMIP No Calibration file available0x 0x 003C Open BMIP Kermit file transmit failure0x 003D Open BMIP Calibration started 0x 003E Open BMIP RFM Error response 0x 003F RFM Load installer – loss of comms 0x 0040 RFM Load installer – KRFU dataload rejected 0x 0041 RFM Manager ICC open failure0x 0042 RFM Manager – Calibration file retrieval failure0x 0043 ARINC Navigation Input Configuration0x 0044 ASC Configuration Data Manager incompatible version data0x 0045 DSP Application Manager unable to allocate resources0x 0046 Unable to allocate ICC transmit buffer0x 0047 Loss of RSSI data0x 0048 Loss of RSSI dataTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-50 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.KANDU (06)Software runtime (FE)0x 0049 IP Tunnel driver – fails to initialize No Action required, software faults and events are dealt with by criticality in the following manner: -Critical: An unrecoverable software error has occurred, the system will reset in order to recover. -Warning: An unexpected but recoverable software error has occurred, the system will continue normal operation. -Information: Recording information related to software execution within the LRU.0x 0050 Tunnel Driver ICC open failure 0x 004A Unable to configure routing to TMA0x 004B KANDU /TMA network configuration conflict 0x 0050 KANDU Post Time Out0x 0800 MES client registration fails 0x 0801 MES client publish fail due to attempted blocking send 0x 0802 MES server unable to open well known socket00x 0803 MES server network resource limitation - socket 0x 0804 MES server network resource limitation – buffer0x 0805 MES server message ID map corruption 0x 0806 MES Client receives non-subscribed message0x 0807 MES proxy database Invalid0x 0x 0808 MES Proxy cannot remotely subscribe 0x 0809 EUI data missing 0x 080A ACM General Error0x 0x 080B APM Client – Data not available0x 080C APM Client – Data validated0x 080D APM Client – Data not validated 0x 080E RSSI Manager unable to open well known socket Temperature (FF)0x 0001 ASC 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 a subassembly in the LRU may be generating too much heat.0x 0002 KANDU PSU remote temperatureTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-51 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Modman KANDU Ethernet bus (20)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 no 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.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 no 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.Modman APM Serial Bus (21)Modman input (01)0x 0001 APM serial inactive Is a warning that no traffic has been seen on the bus:- Far end is not talking.- Wiring problem.- Input problem.0x 0003 APM serial normal System is good.GPS Input (22)Time label (31) 0 x 0001 Missing0x 0002 SSM FT0x 0003 SSM FW0x 0004 SSM FW0x 0005 SSM NO (normal operation)GNSS sensor status word0x 0000 Self test mode0x 0001 Initialization mode0x 0002 Acquisition mode0x 0003 Navigation mode0x 0004 Altitude aiding mode0x 0007 Fault0x 0008 MissingTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-52 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Modman Output: Discretes from Modman (24)Reset (01) 0x 0002 Input output mismatch Modman faultARINC TX Mute (02)0x 0002 Input output mismatch Modman fault0x 0003 Modman/KANDU input output mismatchModman/KRFU wiring faultFilter Select (03) 0x 0002 Input output mismatch Modman fault0x 0003 Modman/KANDU input output mismatchModman/KRFU wiring faultKeyline Transmit (04)0x 0002 Input output mismatch Modman fault0x 0003 Modman/KANDU input output mismatchSystem available (05)0x 0002 Input output mismatch Modman faultData link available (06)0x 0002 Input output mismatch Modman faultKANDU OAE Ethernet Bus (30)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 no 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.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 no 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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-53 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.KANDU OAE Serial Control Bus (31)KANDU input (01)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.OAE input (02) 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.KANDU OAE Serial IMU Bus (32)KANDU input (01)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.OAE input (02) 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.KANDU OAE Serial IMU Bus (32)OAE input (02) 0x 0003 Serial Normal System is good.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-54 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.KANDU KRFU Serial Bus (33)KANDU input (01)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.KRFU input (02) 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.KANDU Input: Discretes from OAE (34)FMA transmit mute (01)0x 0001 Mute line not asserting at 180 Check the FMA, FMA to KANDU wiring and the KANDU0x 0002 Mute line asserting at 0KANDU Input: Discretes from Modman (35)Reset (01) 0x 0000 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.0x 0001 De-asserted0x 0002 KANDU reset of KRFR ResetARINC TX mute (02)0x 0000 Asserted0x 0001 De-assertedFilter Select (03) 0x 0000 Asserted0x 0001 De-assertedTX Mute (04) 0x 0000 Asserted0x 0001 De-assertedKRFU Input Discrete from KANDU (41)Reset (01) 0x 0000 Asserted0x 0001 De-assertedKRFU TX mute (02)0x 0000 Asserted0x 0001 De-asserted0x 0003 KRFU not muted during system testTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-55 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.KRFU Input Discrete from KANDU (41)Filter Select (03) 0x 0000 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.0x 0001 De-asserted0x 0004 Line not responding on KRUIRU 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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-56 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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.Pitch rate label (03)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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-57 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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.Roll rate label (04)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. Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-58 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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.Yaw rate label (05)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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-59 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.IRU Input Bus (70)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.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.Body vertical acceleration (07)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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-60 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.IRU Input Bus (70)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.True heading label (08)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. Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-61 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.IRU Input Bus (70)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.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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-62 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.IRU Input Bus (70) 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 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.Longitude label (12)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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-63 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.IRU Input Bus (70)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.Altitude (13) 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. Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-64 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.IRU Input Bus (70)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.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. 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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-65 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.IRU Input Bus (70)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.E-W velocity (16)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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-66 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.IRU Input Bus (70)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.Horizontal stabilization (21)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. Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-67 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.IRU Input Bus (70) 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.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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-68 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.IRU Input Bus (70)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.Flight phase (41) 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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-69 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.IRU Input Bus (70)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.MLG ground condition (42)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. Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-70 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.IRU Input Bus (70)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.Ground speed (43)0x 0001 Missing0x 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 Pitch Acceleration (50)0x 0001 Missing0x 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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-71 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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 Roll Acceleration (51)0x 0001 Missing0x 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 Yaw Acceleration (52)0x 0001 MissingTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-72 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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.GNSS sensor status word (80)0x 0000 Self test mode Will be available in future revision0x 0001 Initialization mode0x 0002 Acquisition mode0x 0003 Navigational mode0x 0004 Attitude aiding mode0x 0007 Fault0x 0008 MissingIRS discrete word (81)0x 0000 Align Mode/Not Ready Will be available in future revision0x 0001 Revisionary Attitude Mode0x 0002 Normal Mode0x 0008 MissingTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-73 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Aircraft State Input Bus (71)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. Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-74 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Aircraft State Input Bus (71)Pitch angle label (01)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.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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-75 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Aircraft State Input Bus (71)Pitch rate label (03)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.Roll rate label (04)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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-76 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Aircraft State Input Bus (71)Roll rate label (04)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)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. Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-77 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Aircraft State Input Bus (71)Yaw rate label (05)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 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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-78 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Aircraft State Input Bus (71)Body vertical acceleration (07)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)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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-79 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Aircraft State Input Bus (71)True heading label (08)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)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. Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-80 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Aircraft State Input Bus (71)Body lateral acceleration (090x 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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-81 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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.Longitude label (12)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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-82 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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.Altitude (13) 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. Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-83 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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.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. 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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-84 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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.E-W velocity (16)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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-85 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-86 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Horizontal stabilization (21)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. Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-87 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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.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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-88 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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.Flight phase (41) 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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-89 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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.MLG ground condition (42)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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-90 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Aircraft State Input Bus (71)Ground Speed (43)0x0001 Missing0x0002 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.0x0003 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.0x0004 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.0x0005 SSM NO Normal operation, system is good.Body Pitch Acceleration (50)0x0001 Missing0x0002 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.0x0003 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.0x0004 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.0x0005 SSM NO Normal operation, system is good.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-91 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Aircraft State Input Bus (71)Body YawAcceleration (52)0x0001 Missing0x0002 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.0x0003 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.0x0004 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.0x0005 SSM NO Normal operation, system is good.GNSS sensor status word (80)0x 0000 Self test mode Will be available in future revision 0x 0001 Initialization mode 0x 0002 Acquisition mode0x 0003 Navigational (normal) mode0x 0004 Altitude aiding mode0x 0007 Fault0x 0008 MissingIRS discrete word (81)0x 0000 Align Mode/Not Ready Will be available in future revision.0x 0001 Revisionary Attitude Mode0x 0002 Normal Mode0x 0008 MissingTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-92 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Modman Aircraft Discrete Input (72)WOW (06) 0x 0000 Asserted 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.0x 0001 De-assertedGround transmit enable (08)0x 0000 Asserted0x 0001 De-assertedPublic Svr disable (09)0x 0000 Asserted0x 0001 De-assertedLocal data load (0C)0x 0000 Asserted0x 0001 De-assertedKANDU Aircraft Discrete Input (73)TX control (0C) 0x 0000 Asserted 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.0x 0001 De-assertedAISD 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 no 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)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 no 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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-93 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.AISD Network: Ethernet AV2 (82)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 no 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 AV3 (83)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 no 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 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 no 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: Ethernr5et EN5 (89)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 no 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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-94 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.PIESD Network: Ethernet EN6 (8A)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 no 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 EN7 (8B)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 no 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 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 no 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)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 no 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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-95 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.PODD Network: Ethernet PA1 (91)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 no 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 PA2 (92)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 no 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 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 no 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 PA4 (94)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 no 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.Table 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-96 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.7.3 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 ARINC 615A Software Data Load Process and this section 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.1Do continuity checks on wiring, validate communication cabling for Tx, Rx signal integrity via cable analyzers, test RF cables with specialized RF cable testers, and do power on and ground checks with LRUs disconnected for the check.(c) Make sure that all LRUs power up and report "OK" status.1System status can be viewed at the AES Home and Status Info Page Figure 6-3.(d) Make sure that the cable calibration procedure has been done. Refer to Cable Calibration on page 6-12.(e) Make sure that the navigation data is correct and that the antenna alignment has been done. (f) Check for system internal interconnect faults. Refer to JetWave™ System Fault Codes on page 7-8.(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:1 Check wiring and or make sure that the APM is configured for how the system is wired.(h) Check the system for User port Ethernet No layer 1 faults. If faults are received, do as follows:1Check the APM for correct configuration.RF TX Modman to KRFU (B0)Unknown (00) 0x 0001 TX IF Check the interconnecting RF connection between the Modman and KRFU LRUs.0x 0002 50 MHz RefRF 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.0x 0002 Global beam lock TBDTable 7-6. L3 Codes (Continued)L1 L2 L3 Code L3 Description Repair ActionDraft as of 31 May 2017
Page 7-97 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.2Make sure that the connecting equipment is operating correctly. 3Check the wiring.(i) Make sure that the system has the correct software loaded. The GUI screen has a Software Validity Flag, which if it is clear, then ALL system software is OK. If so, do as follows:1Check for LRU software errors.2Check for LRU hardware/software incompatibilities.3Validate the system has the correct overall software load by validating the software version of each LRU that matches with the expected system configuration. Valid system configurations are defined for each Black Label software release and communicated via the service bulletin process.7.4 Incorrect Navigation Data(1) 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 the bus.(2) If the system is reporting an incorrect label status on the bus (FW, NCD, FT), do as follows:(a) Wait for equipment providing the labels to report Normal Operation.7.5 System Will Not Connect to the Network(1) View the AES Home and Status Info Page Figure 6-3 to see reason transmission is muted and address the reasons.(2) If the Radome is not installed, visually make sure that the Antenna is pointing toward the proper I-5 Satellite for the region.(3) 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.(4) Make sure you have clear line of sight to the satellite.(5) Make sure the system has been activated by the ISP. Activation should be checked by contacting the ISP provider to ensure service is active before commencing with testing.(6) Make sure that the system is not configured for data loading. The system will not transmit while the local data enable input is closed to ground.7.6 Connectivity of Each Ethernet PortNOTE: The JetWave™ system configuration files can be updated in the field. Honeywell can create a new system configuration file if needed. 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.Draft as of 31 May 2017
Page 7-98 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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 6-4 shows the typical configuration file Information page. The network status and the VLAN ID can be viewed as shown in Figure 6-11.The IP address assigned can be viewed by pressing the “Display” tab of the Contents of Aircraft Configuration File as shown in Figure 7-9.Figure 7-9. Contents of Aircraft Services Configuration FileThere 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 7-9. 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 OAEDraft as of 31 May 2017
Page 7-99 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.• 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• 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) Check the APM settings, as follows:1Make sure that the port is enabled.2Check system errors.3Check for system reporting No layer 1 or No traffic faults.(b) Is the device connecting to it operating correctly? If so, check the wiring.(2) It there is poor performance on one port only, do as follows: (a) Check for port reporting high packet loss. If so, check wiring and verify that there is traffic. (3) 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.Check with the service provider to make sure that the VLANs have been correctly configured for the terminal.Draft as of 31 May 2017
Page 7-100 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Blank PageDraft as of 31 May 2017
Page 8-1 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.SECTION 8MAINTENANCE AND REPAIR8.1 Maintenance Requirements(1) The maintenance-free design of the JetWave™ AES system does not require field maintenance to maintain airworthiness. (2) Maintenance of the JetWave™ AES system is limited to replacement of LRUs on verified failure. (3) OAE do not require field maintenance, such as lubrication of moving parts.(4) If functional problems occur, the BITE can identify the faulty JetWave™ AES LRU and the Modman collates this information which can be accessed through the GUI provided. Refer to BITE Philosophy on page 7-8 of this document for information on how to access the BITE data. If replacement of an LRU is deemed necessary, in consultation with the customer's authorized JetWave product support, It is strongly recommended that all repairs be performed only at the Honeywell authorized facility.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. •Remove the primary AC power delivered to the KANDU via aircraft circuit breaker. This will power down the KANDU, including the 38.5 VDC and the 24 VDC power supply to the FMA or TMA.• Wait 1 minute following the removal of power to KANDU before attempting cable disconnect from FMA or TMA, or any physical contact with the FMA or TMA.• Disconnect FMA or TMA Plug P1 and measure the voltage across Pin A and Pin B using a voltmeter (38.5 VDC voltage line). The measurement should not exceed 1 VDC. • Disconnect FMA or TMA Plug P3 and measure the voltage across Pin 5 and Pin 6 using a voltmeter (24 VDC voltage line). The measurement should not exceed 1 VDC.8.2 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. 8.3 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.Draft as of 31 May 2017
Page 8-2 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(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) Aircraft Manufacturers may also impose return to service criteria on installed aircraft equipment after lightning or bird strike events. 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 8-1.8.4 General Instructions for InspectionThis 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.(3) Do the inspections and checks presented in Electrical and Mechanical Inspection and Check.(4) Remove the primary AC power delivered to the KANDU via aircraft circuit breaker. This will power down the KANDU, including the 38.5 VDC and the 24 VDC power supply to the FMA/TMA.(5) Wait 1 minute following the removal of power to KANDU before attempting cable disconnect from FMA/TMA, or any physical contact with the FMA/TMA.(6) In case of FMA, disconnect FMA Plug P1 and measure the voltage across Pin A and Pin B using a voltmeter (38.5 VDC voltage line). The measurement should not exceed 1 VDC.(7) In case of TMA, disconnect TMA Plug P22 and measure the voltage across Pin G and Pin H using a voltmeter (38.5 VDC voltage line). The measurement should not exceed 1 VDC.(8) In case of FMA, disconnect FMA Plug P3 and measure the voltage across Pin 5 and Pin 6 using a voltmeter (24 VDC voltage line). The measurement should not exceed 1 VDC.(9) In case of TMA, disconnect TMA Plug P22 and measure the voltage across Pin U and Pin V (TMA) using a voltmeter (24 VDC voltage line). The measurement should not exceed 1 VDC.Draft as of 31 May 2017
Page 8-3 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.8.5 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. 8.6 Instructions for Continued Airworthiness This section supplies the special instructions and maintenance requirements for continued airworthiness of the JetWave™ AES subsystems.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.If a JetWave™ AES OAE assembly or an LRU is inoperative, do as follows: (a) Collar applicable switches and circuit breakers (b) Secure cables and wiring (c) Remove the unit (d) Placard the JetWave™ AES LRU and associated items as “inoperative” in accordance with the Aircraft Maintenance Manual (AMM)(e) Before flight, do as follows: (f) Record the removal of the unit in the aircraft log book (g) Revise the equipment list. Refer to section 91.213 of the FAR or the aircraft’s Minimum Equipment List (MEL)(h) Revise the weight and balance data as applicable.(i) In case of Modman replacement, the VAR/DP needs to be notified so that the system is recommissioned to the new terminal ID.JetWave™ AES system LRUs are not field-repairable. Return the faulty LRU(s) to the Honeywell authorized facility for repair. Install repaired or replacement LRUs on the aircraft in accordance with the installation instructions supplied in this manual. Refer to ARINC 615A Software Data Load Process on page 5-1 for instructions on how to bring the repaired or replacement LRU up to current software release.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. Enter the approval for return to service in the appropriate logbook as required by FAR Section 43.9.Add the scheduled maintenance tasks to the aircraft operator’s appropriate aircraft maintenance program as follows:Draft as of 31 May 2017
Page 8-4 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(a) Recommended periodic scheduled servicing tasks: None required. (b) Recommended periodic inspections: (c) Scheduled maintenance inspections supplied in Table 8-1 and in accordance the aircraft’s inspection and maintenance schedule. (d) Recommended periodic scheduled preventative maintenance tests (to determine system condition and/or latent failures): None required.8.7 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.WARNING: FAILURE TO DISCONNECT CIRCUIT BREAKERS CAN LEAD TO INJURY TO THE OPERATOR AND DAMAGE TO THE EQUIPMENT. (1) Disconnect all circuit breakers to the JetWave™ AES OAE assembly, LRUs and associated systems.(2) Visually examine the FMA or TMA radome for any damage or defects. Please refer to the radome supplier’s Structural Repair Manual (SRM) for the specific radome inspection and damage repair instructions.(e) Saint Gobain SRM-100 is applicable to all radomes. FMA radome, PN SCD-90401395-01, is covered specifically by Saint Gobain SRM-5249 structural repair manual.8.8 Scheduled Maintenance and Inspections(1) The JetWave™ AES system does not require routine maintenance for continued airworthiness. (2) It is recommended to follow the Standard Practices Chapter of the Aircraft Maintenance Manual and do all required inspections and repairs. Refer to Table 8-1 for scheduled maintenance.Table 8-1. Scheduled Maintenance SI No. Item Interval Potential Damage Inspection InspectionLightning diverters In accordance with the aircraft inspection schedule and after flying in known conditions of lightningPaint damage, structural damage, de-lamination External visualFuselage mount radome exterior, radome skirt exterior/tail mount radome exteriorIn accordance with the aircraft inspection schedule and after flying in known conditions of lightning/hail.Paint damage, structural damage, de-lamination, puncture, dark marks/streakingExternal visualDraft as of 31 May 2017
Page 8-5 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Antenna interface mount In accordance with the aircraft inspection scheduleCorrosion, loose, or missing fasteners External visualOAE – FMA/TMA connectors In accordance with the aircraft inspection scheduleCorrosion, loose, or missing connectors External visualOAE-FMA/TMA grounding and bondingIn accordance with the aircraft inspection scheduleNon conform electrical bonding External visual and 5 mΩ testOAE-FMA/TMA wiring In accordance with the aircraft inspection scheduleChafing, cracks in insulation, breaks External visualKANDU connectors In accordance with the aircraft inspection scheduleCorrosion, loose, or missing connectors External visualKANDU grounding and bonding In accordance with the aircraft inspection scheduleNon conform electrical bonding External visual and 5 mΩ testModman and APM connectors In accordance with the aircraft inspection scheduleCorrosion, loose, or missing connectors External visualModman and APM grounding and bondingIn accordance with the aircraft inspection scheduleNon conform electrical bonding External visual and 5 mΩ testTable 8-1. Scheduled Maintenance (Continued)SI No. Item Interval Potential Damage Inspection InspectionDraft as of 31 May 2017
Page 8-6 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Blank Page8.9 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 8-2.(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 8-3. 8.10 Repair Requirements(1) The BITE functionality of JetWave™ AES system can identify the faulty LRU in the case of 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.Table 8-2. Unscheduled MaintenanceItem Potential Damage InspectionJetWave™ AES FMA OAE/TMA OAE Heavy rain/hail Paint erosion External visualbird strike Paint damage/radome puncture External visualJetWave™ AES system Failure NA NA RemovalTable 8-3. Modman LED Status IndicationsStatus LED ModeOff 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 operationOn - red Modman in Fault ModeDraft as of 31 May 2017
Page A-1 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.APPENDIX A1. RTCA/DO-160G Environmental CharacteristicsA. ModmanThe following characteristics are taken from the core equipment qualification program and do not reflect any additional qualification conducted on a per installation basis.Section Condition Category4 Temperature and altitude A1(V)NOTE: Below 5˚F (-15˚C), user services are not offered. Altitude for all units extended to 55,000 feet (16,764 m) during the qualification test. Overpressure 28.9 PSI (199 kPa), Decompression 6,000 to 55,000 (1828.8 to 16,764 m) in 2 seconds.5 Temperature variation B6 Humidity B7 Operational shocks and crash safety B8 Vibration CAT S, CURVE B29 Explosive atmosphere X - not required10 Waterproofness Y 11 Fluids specification X - not required12 Sand and dust X - not required13 Fungus resistance F14 Salt fog X - not required15 Magnetic effect A16 Power input A (WF) HLPINOTE: Extended low frequency operation to 320 Hz.17 Voltage spike ANOTE: Extended to 1,000 volts.18 Audio frequency conducted susceptibility KNOTE: Amplitude of applied signal to be 10% of nominal AC voltage.19 Induced signal susceptibility ZWNOTE: Extended low frequency operations to 320 Hz.Draft as of 31 May 2017
Page A-2 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.20 Radio frequency susceptibility RR (custom)NOTE: Radiated: Additional subjectionsSW: 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 M22 Lightning induced transient susceptibility A2K2L3NOTE: Modified to extend single stroke to waveform 3 level 3 and multi-stroke to waveform 4 level 2.23 Lightning direct effects X - not required24 Icing X - not required25 Electrostatic discharge A26 Fire, flammability C - covers 14 CFR 25.853Section Condition CategoryDraft as of 31 May 2017
Page A-3 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.B. APMSection Condition Category4 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.5 Temperature variation B6 Humidity B7 Operational shocks and crash safety B8 Vibration CAT S, CURVE B29 Explosive atmosphere X - not required10 Waterproofness Y11 Fluid susceptibility X - not required12 Sand and dust X - not required13 Fungus resistance F14 Salt fog X - not required15 Magnetic effect A16 Power input X - not required17 Voltage spike X - not required18 Audio frequency conducted susceptibility X - not required19 Induced signal susceptibility ZC20 Radio frequency susceptibility RR21 Emissions of RF energy M22 Lightning induced transient susceptibility A2K2L3NOTE: Modified to extend single stroke to waveform 3 level 3 and multi-stroke to waveform 4 level 2.23 Lightning direct effects X - not required24 Icing X - not required25 Electrostatic discharge A26 Fire, flammability C - covers 14 CFR 25Draft as of 31 May 2017
Page A-4 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.C. KANDUSection Condition Category4 Temperature and altitude D2NOTE: 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).5 Temperature variation A6 Humidity B7 Operational shocks and crash safety E and B8 Vibration CAT R, CURVE ECAT R, CURVE E1NOTE: The sinusoidal sweep rate not to exceed 0.5 octaves/minute.9 Explosive atmosphere E10 Waterproofness Y and R11 Fluid susceptibility F NOTE: De-ice Ethylene Glycol, Hydraulic fluid phosphate ester AS1241 Type IV and V.12 Sand and dust D13 Fungus resistance F14 Salt fog S15 Magnetic effect Z16 Power input A (WF) HZPINOTE: 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 CWNOTE: 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 19.3.1.20 Radio frequency susceptibility RYNOTE:- 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).Draft as of 31 May 2017
Page A-5 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.21 Emissions of RF energy QNOTE: 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 A3K3L3NOTE: Extended to include pin injection waveform 5A level 2.23 Lightning direct effects X - not required24 Icing A25 Electrostatic discharge A26 Fire, flammability C - covers 14 CFR 25.853Section Condition CategoryDraft as of 31 May 2017
Page A-6 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.D. KRFUSection Condition Category4 Temperature and altitude D2NOTE: 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).5 Temperature variation A6 Humidity BNOTE: At least six spot checks required.7 Operational shocks and crash safety E and B8 Vibration CAT R, CURVE ECAT R, CURVE E1NOTE: The sinusoidal sweep rate not to exceed 0.5 octaves/minute.9 Explosive atmosphere E10 Waterproofness Y and R11 Fluid susceptibility F NOTE: Ethylene Glycol, Propylene Glycol, AEA Type 1, AEA Type 2.12 Sand and dust D13 Fungus resistance F14 Salt fog S15 Magnetic effect Z16 Power input A (WF) HZPINOTE: 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 CWNOTE: 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).20 Radio frequency susceptibility MYNOTEL:- 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).Draft as of 31 May 2017
Page A-7 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.21 Emissions of RF energy PNOTE: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 A3K3L3NOTE: Extended to include pin injection waveform 5A level 2.23 Lightning direct effects X - not required24 Icing A25 Electrostatic discharge A26 Fire, flammability C - covers 14 CFR 25.853Section Condition CategoryDraft as of 31 May 2017
Page A-8 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.E. TMASection Condition Category4 Temperature and altitude F25 Temperature variation A6 Humidity B7 Operational shocks and crash safety E8 Vibration CAT R, CURVE ECAT R, CURVE E19 Explosive atmosphere E and H10 Waterproofness Y and W11 Fluid susceptibility F (de-icing fluids)NOTE: Ethylene Glycol.12 Sand and dust D13 Fungus resistance F14 Salt fog S15 Magnetic effect A16 Power input X - not required17 Voltage spike ANOTE: 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 RNOTE: 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 ZC20 Radio frequency susceptibility YQ (custom)NOTE: Q (custom) only - SW/CW (un-modulated) signal Operational:200V/m for 100 MHz to 12 GHz0.1 V/m 12 GHz to 16.6 GHzNo damage:200V/m for 12 GHz to 16.6 GHz0.1 V/m for 16.6 GHz to 18 GHz21 Emissions of RF energy H22 Lightning induced transient susceptibility A3K3L3 modifiedNOTE: 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).Draft as of 31 May 2017
Page A-9 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.23 Lightning direct effects X - not required24 Icing B25 Electrostatic discharge A26 Fire, flammability C - covers 4 CFR 25.853Section Condition CategoryDraft as of 31 May 2017
Page A-10 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.F. FMASection Condition Category4 Temperature and altitude F2NOTE: Extended operating high to 194˚F (90˚C).5 Temperature variation A6 Humidity BNOTE: At least six spot checks are required.7 Operational shocks and crash safety B and E8 Vibration CAT S, CURVE CCAT R, CURVE C1NOTE: The sinusoidal sweep rate not to exceed 0.5 octaves/minute9 Explosive atmosphere E10 Waterproofness Y and W11 Fluid susceptibility - De-ice fluids only F12 Sand and dust D13 Fungus resistance F14 Salt fog S15 Magnetic effect B16 Power input X - not required17 Voltage spike X - not required18 Audio frequency conducted susceptibility X - not required19 Induced signal susceptibility ZC20 Radio frequency susceptibility YQNOTE: Q (custom) only - SW/CW (un-modulated) signal Operational:200V/m for 100 MHz to 12 GHz0.1 V/m 12 GHz to 16.6 GHzNo damage:200V/m for 12 GHz to 16.6 GHz0.1 V/m for 16.6 GHz to 18 GHz21 Emissions of RF energy HNOTE: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 MHzDraft as of 31 May 2017
Page A-11 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.22 Lightning induced transient susceptibility A3K3L3NOTE: 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 required24 Icing B25 Electrostatic discharge A26 Fire, flammability C - covers 14 CFR 25.853Section Condition CategoryDraft as of 31 May 2017
Page A-12 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Blank PageDraft as of 31 May 2017
Page B-1 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.APPENDIX BNOTE: 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 Sheet2. JetWave™ AES Subsystem Components A. JetWave™ AES OAE - FMA/TMA Installation Information Sheet B. JetWave™ AES KANDU Installation Information Sheet C. JetWave™ AES KRFU Installation Information Sheet OwnerTail NumberSerial NumberModel/TypePart NumberSerial NumberHardware Revision Mod StatusPart NumberSerial NumberHardware Revision Mod StatusPart NumberSerial NumberHardware Revision Mod StatusDraft as of 31 May 2017
Page B-2 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.D. JetWave™ AES Modman Installation Information Sheet E. JetWave™ AES APM Installation Information Sheet Part NumberSerial NumberHardware Revision Mod StatusPart NumberSerial NumberHardware Revision Mod StatusDraft as of 31 May 2017
Page C-1 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.APPENDIX C1. Installation Checklist A. OAE-TMA Checklist Aircraft Identification:Name Signature DateInstallation/Checks completed by:Approved/Witnessed by:Section Parameter Item NA √ValueA. Maintenance Panel Applicability If the system is not wired to another aircraft system, an installer provided maintenance panel is required.Discrete output connections System available (Modman MP13E) connected to a lampData link available (Modman MP13F) connected to a lampDiscrete input connections Local data load enable (Modman MP10B) connected to a normally open switchGround transmit enable (Modman MP11D) connected to a normally open switchPublic service disable (Modman MP11E) connected to a normally open switchModman reset (Modman MP10C) connected to a normally open switchTx mute (KANDU J1D) connected to a normally open switchEthernet port connections AV1 (Modman TP BB1 thru 4) connected to a RJ45 Ethernet connectorAdditional electrical wiringElectrically wire and interconnect in accordance with Figure 4-34.Draft as of 31 May 2017
Page C-2 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.A. Modman Physical Examine for physical damage.Environmental conditions, refer to Figure 4-22.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 surfacesElectrical connector ARINC 600 mating connector and pins, refer to Table 4-1. ARINC 600 ConnectorsARINC 600 polarized pinsElectrical bonding Bonding, refer to page 4-3.Electrical wiring Electrically wire and interconnect in accordance with Figure 4-21 or Figure 4-22 and Figure 4-34.Electrical RF coaxial Equalizer in the TX pathTX path loss, refer to Table 4-2. Modman Cable Loss ValuesAttenuator in the RX pathRX path loss, refer to Table 4-2. Modman Cable Loss ValuesNOTE: Input signal range: -79 to -5 dBm. Output signal range -30 to +5 dBm. Incross talk requirement: -25 dBc. Output cross talk requirement: -40 dBc.APMPhysical Examine for physical damage.Environmental conditions, refer to Figure 4-21 and Figure 4-22.Mounting Can be installed in any orientation, refer to Figure 4-21 and Figure 4-22.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 4-4.Section Parameter Item NA √ValueDraft as of 31 May 2017
Page C-3 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.NOTE: Input signal range: -79 to -5 dBm. Output signal range -30 to +5 dBm. Incross talk requirement: -25 dBc. Output cross talk requirement: -40 dBc. (Cont)Electrical wiring Electrically wire and interconnect in accordance with Figure 4-24 and Figure 4-34.Electrical wiring - APM to ModmanAPM to Modman interconnect cable shall use ARINC 664 compliant 2 Shielded Twisted Pair 24 AWG (or Aerospace Grade Shielded Cat 5/Cat 5E Minimum). Part No. ECS 922404 or Equivalent, with a maximum length of 9.8 feet (3 m).4.3 KANDU Physical Examine for physical damage.Environmental conditions, refer to Figure 4-25 and Figure 4-26Electrical wiring Electrically wire and interconnect in accordance with Figure 4-25, Figure 4-26, and Figure 4-34.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 - KANDU to TMARefer to JetWave™ System Internal LRU Installation, KANDU on page 4-8.Electrical wiring - KANDU bulkhead interfaceRefer to JetWave™ System Internal LRU Installation, KANDU on page 4-8.Section Parameter Item NA √ValueDraft as of 31 May 2017
Page C-4 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.4.6 KRFU Physical Examine for physical damage.Environmental conditions, refer to Figure 4-27, Figure 4-28, or Figure 4-29 depending on configuration used.Install the thermal pad in accordance with KRFU on page 4-16.The KRFU is installed with the TMA, refer to OAE TMA Installation Procedure on page 4-30.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 - KRFU to TMA Connection must be WR28 for TX and coaxial cable for RX.The TX interconnect path lossThe RX interconnect path lossRX connection at the KRFU requires a WR42 to coax transition adapter at the KRFU J4Electrical wiring Electrically wire and interconnect in accordance with outline drawing Figure 4-27, Figure 4-28, or Figure 4-29 and interconnect drawing Figure 4-34.Electrical bonding Electrically bond in accordance with page 4-18.(b) OAE TMA Installation Procedure Physical Refer to OAE TMA Installation Procedure.TMA mounting Refer to OAE TMA Installation Procedure.TMA interface mount bracketsRefer to OAE TMA Installation Procedure.Section Parameter Item NA √ValueDraft as of 31 May 2017
Page C-5 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.(b) OAE TMA Installation Procedure (Cont)TMA install Refer to OAE TMA Installation Procedure.TMA radome and radome fairingDepending 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 Figure 4-30.TMA alignment Automatic alignment, manual alignment, or command, refer to TMA Alignment on page 2-23 and Inspection of Waveguide on page 4-43Section Parameter Item NA √ValueDraft as of 31 May 2017
Page C-6 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.B. A791 Based OAE-FMA with the AIM Checklist Section Parameter Item NA √ValueA. Maintenance Panel Applicability If the system is not wired to another aircraft system, an installer provided maintenance panel is required.Discrete output connections System available (Modman MP13E) connected to a lampData link available (Modman MP13F) connected to a lampDiscrete input connections Local data load enable (Modman MP10B) connected to a normally open switchGround transmit enable (Modman MP11D) connected to a normally open switchPublic service disable (Modman MP11E) connected to a normally open switchModman reset (Modman MP10C) connected to a normally open switchTx mute (KANDU J1D) connected to a normally open switchEthernet port connections AV1 (Modman TP BB1 thru 4) connected to a RJ45 Ethernet connectorAdditional electrical wiringElectrically wire and interconnect in accordance with Figure 4-35 thru Figure 4-37.A. Modman Physical Examine for physical damage.Environmental conditions, refer to Figure 4-21 or Figure 4-22.Mounting tray Install applicable 4-MCU tray, supplied by customer.Draft as of 31 May 2017
Page C-7 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.A. Modman (Cont) Clearance Minimum 1 inch (25.4 mm) from top surface and 0.5 inch (12.7 mm) from all other surfacesElectrical connector ARINC 600 mating connector and pins, refer to Table 4-1. ARINC 600 ConnectorsARINC 600 polarized pinsElectrical bonding Bonding, refer to page 4-3Electrical wiring Electrically wire and interconnect in accordance with Figure 4-21 or Figure 4-22 and Figure 4-35 thru Figure 4-37, depending on the configuration being used.Electrical RF coaxial Equalizer in the TX pathTX path loss, refer to Table 4-2. Modman Cable Loss ValuesAttenuator in the RX pathRX path loss, refer to Table 4-2. Modman Cable Loss ValuesNOTE: Input signal range: -79 to -5 dBm. Output signal range -30 to +5 dBm. Incross talk requirement: -25 dBc. Output cross talk requirement: -40 dBc.APMPhysical Examine for physical damage.Environmental conditions, refer to Figure 4-21 and Figure 4-22.Mounting Can be installed in any orientation. Refer Figure 4-21 and Figure 4-22.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 4-4.Electrical wiring Electrically wire and interconnect in accordance with Figure 4-24 and Figure 4-35 thru Figure 4-37, depending on the configuration being used.Section Parameter Item NA √ValueDraft as of 31 May 2017
Page C-8 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.NOTE: Input signal range: -79 to -5 dBm. Output signal range -30 to +5 dBm. Incross talk requirement: -25 dBc. Output cross talk requirement: -40 dBc. (Cont)Electrical wiring - APM to ModmanAPM to Modman interconnect cable shall use ARINC 664 compliant 2 Shielded Twisted Pair 24 AWG (or Aerospace Grade Shielded Cat 5/Cat 5E Minimum). Part No. ECS 922404 or Equivalent, with a maximum length of 9.8 feet (3 m).4.3 KANDU Physical Examine for physical damage.Environmental conditions, refer to Figure 4-25 or Figure 4-26.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-FMARefer to JetWave™ System Internal LRU Installation, KANDU on page 4-8.4.6 KRFU Physical Examine for physical damage.Environmental conditions, refer to Figure 4-27, Figure 4-28, or Figure 4-29 depending on configuration used.Install the thermal pad in accordance with KRFU on page 4-16.The KRFU is installed with the FMA, refer to FMA Installation Procedure on page 4-24.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 - KRFU to FMA Connection must be WR28 for TX and coaxial cable for RX.The TX interconnect path lossSection Parameter Item NA √ValueDraft as of 31 May 2017
Page C-9 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.4.6 KRFU (Cont) Waveguide - KRFU to FMA (Cont)The RX interconnect path lossRX 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 4-27, Figure 4-28, or Figure 4-29 and interconnect drawing Figure 4-35 or Figure 4-37, depending on the configuration being used.Electrical bonding Electrically bond in accordance with page 4-18.N. FMA Installation ProcedurePhysical Examine the FMA AIM for physical damage.Examine the FMA assembly for physical damage.Examine the radome for physical damage. Refer to Figure 4-32.Environmental conditions, refer to Figure 4-31.Positioning The aircraft fuselage mount OAE must be mounted on the top of the fuselage.FMA AIM Refer to Fuselage Mount Antenna (If applicable) (8).FMA Install Refer to Fuselage Mount Antenna (If applicable) (8).FMA radome Attach the radome assembly onto the AIM.FMA bonding Electrically bond in accordance with page 4-16.FMA alignment Automatic alignment, manual alignment, or command, refer to FMA Alignment on page 2-39 and Inspection of Waveguide on page 4-43.Section Parameter Item NA √ValueDraft as of 31 May 2017
Page C-10 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.C. Non-A791 Based OAE-FMA with the LAIM Checklist Section Parameter Item NA √ValueA. Maintenance Panel Applicability If the system is not wired to another aircraft system, an installer provided maintenance panel is required.Discrete output connections System available (Modman MP13E) connected to a lampData link available (Modman MP13F) connected to a lampDiscrete input connections Local data load enable (Modman MP10B) connected to a normally open switchGround transmit enable (Modman MP11D) connected to a normally open switchPublic service disable (Modman MP11E) connected to a normally open switchModman reset (Modman MP10C) connected to a normally open switchTx mute (KANDU J1D) connected to a normally open switchEthernet port connections AV1 (Modman TP BB1 thru 4) connected to a RJ45 Ethernet connectorAdditional electrical wiringElectrically wire and interconnect in accordance with Figure 4-35 thru Figure 4-37, depending on the configuration being used.A. Modman Physical Examine for physical damage.Environmental conditions, refer to Figure 4-21 or Figure 4-22.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 4-1. ARINC 600 ConnectorsARINC 600 polarized pinsDraft as of 31 May 2017
Page C-11 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.A. Modman (Cont) Electrical bonding Bonding, refer to page 4-3Electrical wiring Electrically wire and interconnect in accordance with Figure 4-21 or Figure 4-22 and Figure 4-35thru Figure 4-37, depending on the configuration being used.Electrical RF coaxial Equalizer in the TX pathTX path loss, refer to Table 4-2. Modman Cable Loss ValuesAttenuator in the RX pathRX path loss, refer to Table 4-2. Modman Cable Loss ValuesNOTE: Input signal range: -79 to -5 dBm. Output signal range -30 to +5 dBm. Incross talk requirement: -25 dBc. Output cross talk requirement: -40 dBc.APMPhysical Examine for physical damage.Environmental conditions, refer to Figure 4-21 and Figure 4-22.Mounting Can be installed in any orientation. Refer to Figure 4-21 and Figure 4-22.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 4-4.Electrical wiring Electrically wire and interconnect in accordance with Figure 4-23 and Figure 4-35 thru Figure 4-37, depending on the configuration being used.Electrical wiring - APM to ModmanAPM to Modman interconnect cable shall use ARINC 664 compliant 2 Shielded Twisted Pair 24 AWG (or Aerospace Grade Shielded Cat 5/Cat 5E Minimum). Part No. ECS 922404 or Equivalent, with a maximum length of 9.8 feet (3 m).Section Parameter Item NA √ValueDraft as of 31 May 2017
Page C-12 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.4.3 KANDU Physical Examine for physical damage.Environmental conditions, refer to Figure 4-25 or Figure 4-26.Electrical wiring Electrically wire and interconnect in accordance with Figure 4-25 or Figure 4-26 and Figure 4-34, thru Figure 4-37, depending on the configuration being used.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 -FMARefer to KANDU (1).Electrical bonding Electrically bond in accordance with page 4-10.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.4.6 KRFU Physical Examine for physical damage.Environmental conditions, refer to Figure 4-27, Figure 4-28, or Figure 4-29 depending on configuration used.Install the thermal pad in accordance with KRFU on page 4-16.The KRFU is installed with the FMA. refer to FMA Installation Procedure on page 4-24.Section Parameter Item NA √ValueDraft as of 31 May 2017
Page C-13 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.4.6 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 Make sure the waveguide is connected before powering the KRFU.Waveguide - KRFU to FMA Connection must be WR28 for TX and coaxial cable for RX.The TX interconnect path lossThe RX interconnect path lossRX 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 4-27, Figure 4-28, or Figure 4-29 and interconnect drawing Figure 4-34 thru Figure 4-37, depending on the configuration being used.Electrical bonding Electrically bond in accordance with page 4-18.I. FMA Installation Procedure Physical Examine the FMA AIM for physical damage.Examine the FMA assembly for physical damage.Examine the radome for physical damage. Refer to Figure 4-32.Environmental conditions, refer to Figure 4-31.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 (If applicable) (8).Install radome skirt fairing Install and attach the radome skirt fairing to fuselage with 39 fasteners.Section Parameter Item NA √ValueDraft as of 31 May 2017
Page C-14 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.I. FMA Installation Procedure (Cont) Install radome skirt fairing Install and attach the radome skirt fairing to fuselage with 39 fasteners.FMA install Refer to Fuselage Mount Antenna (If applicable) (8).FMA radome Attach the radome assembly onto the radome skirt fairing.FMA bonding Electrically bond in accordance with page 4-16.FMA alignment Automatic alignment, manual alignment, or command, refer to FMA Alignment on page 2-39 and Inspection of Waveguide on page 4-43.Section Parameter Item NA √ValueDraft as of 31 May 2017
Page D-1 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.APPENDIX D1. List of Airframe Specific Information Required for JetWave™ System ConfigurationA 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.Table D-1. Value Added Reseller (VAR/DP)Name of the Service ProviderTable D-2. Aircraft InformationAircraft Model/Type Tail Number Serial Number Expected Activation DateTable D-3. Air Data Inertial Reference Unit/Multi Mode ReceiverADIRU Part Number MMR Part NumberTable D-4. ARINC 429 Labels ARINC 429 Interface Speed Interface Bus SpeedARINC 429 IRS Interface Bus SpeedARINC 429 Aircraft State Interface Bus SpeedLabel Number Label Name Accuracy Label LatencyTotal Latency(Msec)Minimum Transmission Rate (Msec) Jitter314 True Heading125 UTC Time 150 UTC Time 260 Date 254 Present Position – Latitude 255 Present Position – Longitude 261 Altitude 132 True Heading 175 Ground SpeedDraft as of 31 May 2017
Page D-2 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.313 True Track315 Horizontal Stabilization324 Pitch Angle 325 Roll Angle 330 Yaw Rate 326 Pitch Rate 327 Roll Rate 110 GNSS Latitude 111 GNSS Longitude 112 GNSS Ground Speed76 GNSS Altitude (MSL)270 IRS Discrete Status 312 Ground speedTable D-4. ARINC 429 Labels (Continued)ARINC 429 Interface Speed Interface Bus SpeedARINC 429 IRS Interface Bus SpeedARINC 429 Aircraft State Interface Bus SpeedLabel Number Label Name Accuracy Label LatencyTotal Latency(Msec)Minimum Transmission Rate (Msec) JitterDraft as of 31 May 2017
Page D-3 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Table D-5. Airframe Structural Blockage Information Blockage Angle Value in Degrees RemarksBlockage 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).Blockage Angle c Angle “c” refers to the point of the wing, where an antenna radiating at -10-degrees elevation would find the wing’s leading edge.Blockage Angle d Angle “d” refers to the outer, aft-most tip of the wing (including vortex eliminators, if present).Blockage Angle e Angle “e” provides the azimuth range of the Vertical Tail Plane (VTP) region of blockage in its broadest case.Blockage Angle f Angle “f” is between the fuselage centerline and the outer, forward-most tip of the HTP.Blockage Angle h Angle “h” provides the Vertical Tail Plane (VTP) region of blockage in elevation from -10 degrees up.Blockage Angle i Angle “i” is between the horizontal plane where the antenna emitting point is located and upper, forward-most part of the fuselage.Blockage Angle k Angle “k” is the angle between the horizontal plane where the antenna emitting point is located and the aft-most tip of the HTP.Blockage Angle m 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). Blockage Angle p Angle “p” is from the emitter point to upper, aft-most wing tip (including vortex eliminators, if present).Draft as of 31 May 2017
Page D-4 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.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.Table D-6. Weight on WheelsWeight on Wheels Discrete Input Available Y/N Polarity of Weight on Wheels Discrete SignalTable D-7. Ground Transmit EnableGround Transmit Enable Discrete Y/N Polarity of Ground Transmit Enable DiscreteTable D-8. ARINC Tx Mute and Tail Sector Mute SwitchARINC Tx Mute Connected Yes/NoTail Sector Mute Switch Wired Yes/No Table D-9 ARINC791 EquippedY N Frame Number for Fittings 3 and 4 Frame NumberDraft as of 31 May 2017
Page D-5 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.Table D-10. Modman Serial NumberModman Serial NumberTable D-11. Modman Ethernet Configuration TableModman Ethernet Interface User OTA Traffic Enabled / DisabledAES Services to be EnabledStatic IP / Local IP Address(Modman/KANDU/FMA or TMA)AISD Ethernet AV1 10/100 Mbps 615A DL (Data Load)AESSFTPSNMPGUI172.29.55.1/.2/.3AISD Ethernet AV2 10/100 Mbps AISD Gigabit Ethernet AG1 10/100/1000 Mbps 615A DL (Data Load)AESSFTPSNMPGUI172.29.55.1/.2/.3PODD Ethernet PA1 10/100 Mbps PODD Ethernet PA2 10/100 Mbps PODD Ethernet PA3 10/100 Mbps PODD Ethernet PA4 10/100 Mbps PODD Gigabit Ethernet PG1 10/100/1000 Mbps PIESD Ethernet EN5 10/100 Mbps PIESD Ethernet EN6 10/100 Mbps PIESD Ethernet EN7 10/100 Mbps PIESD Ethernet EN8 10/100 Mbps PIESD Gigabit Ethernet EG1 10/100/1000 MbpsNOTE 1: When User OTA Traffic and any AES Services are enabled on the same port, then the Static IP addresses must be on a unique subnet per each distinct OTA SVN.NOTE 2: The Static IP addresses are for internal AES services. The IP addresses for User OTA Traffic is configured in the provisioning gateway.Draft as of 31 May 2017
Page D-6 3 Mar 201723-15-29SYSTEM DESCRIPTION AND INSTALLATION MANUALJetWave™ System© Honeywell International Inc. Do not copy without express permission of Honeywell.NOTE 3: Select the appropriate AES services. AES services available are: (a) 615A DL (Data Load) (b) AESSFTP (c) SNMP and (d) GUI. NOTE 4: The Static/local IP addresses shown are the default values the terminal uses until it has read a non-blank APM. Table D-12. KRFU LocationInside Cabin Inside RadomeTable D-13. Antenna LocationFuselage Mount Tail MountTable D-14. Waveguide ManufacturerHoneywell Other Manufacturer Part NumberYNTable D-15. Radome ManufacturerHoneywell Other ManufacturerYNTable D-11. Modman Ethernet Configuration TableDraft as of 31 May 2017

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