HALO ASCB-D/CANaerospace/ARINC825 User`s Manual Telemetry
Contents
1. HALO ASCB D CANaerospace ARINC825 Telemetry Interface System TIS User s Manual HALO TIS User s Manual Rev 1 5 C Stock Flight Systems 2011 1 Telemetry Interface System Overview The Telemetry Interface System TIS is a 19 rack mounted computer that interfaces to the HALO aircraft Pilot or Copilot Side Secondary ASCB D bus and a CANaerospace ARINC 825 network The TIS performs the following functions in real time ASCB D data stream decoding and formatting ASCB D data stream recording to external USB Harddisk CANaerospace ARINC 825 data encoding decoding Transmission of formatted ASCB D data via a configurable 10 100 1000 Mbit s Ethernet UDP IP interface Bidirectional data translation between CANaerospace ARINC 825 and the configurable 10 100 1000 MBit s Ethernet UDP IP interface The TIS uses the SuSE Linux 10 3 operating system with a customized 1000HZz realtime kernel and provides the following computer interfaces Keyboard mouse via USB External recording Harddisk via USB VGA monitor Combined CD ROM DVD drive rear side Two additional USB ports rear side The TIS operates from a single 18 36VDC aircraft supply and draws 3A of current at 28VDC The total weight of the unit is 10kg The mechanical dimensions of the TIS unit are 435mm wide 88mm high and 370mm deep The TIS will automatically start on power up and cease operation on po wer down without user intervention System boot time is lt 2 minutes Fig2. CAN High n c 1 9 Ee CANaerospace ARINC825 Figure 17 TIS CANaerospace ARINC825 Connector Pinout 4 Telemetry System Operation The TIS automatically boots after power is applied and shuts down when power is removed No user intervention is required for normal operation other than reading the continuously transmitted UDP IP packets from the Ethernet interface on the specified port numbers Connecting a VGA mo nitor and a USB keyboard mouse however monitoring the TIS operation and interacting with it can be accomplished at any time 4 1 System Startup After the boot process has been completed the KDE window manager is started and an automatic login of dlruser password dlruser is performed Within the KDE wndow manager the tis ap plication is started and continues to run until the system is shut down by removing the 28VDC po wer or by a corresponding operating system command i e poweroff shutdown or halt If an external USB hard disk has been detected during system startup all received ASCB D data is stored on the hard disk until it is full Using a 500GB disk formatted with the FAT32 file system more than 20 hours of flight data can be stored and used for post flight data analysis or playback operations Every 18 2 minutes a new file with an increasing number in the filename extension is generated and filled with data The files have structured names as shown in the examples below e Tue_De
3. Configuration inclu ding all lines belonging to it shall be ignored The data types used for element attributes are Data Type Description ASCII text string describing a single precision floating point value according to IEEE754 1985 fe text string describing a signed integer ae string ASCII text string of variable length maximum 256 Bytes 5 1 TIS Config Element The TIS Config element uniquely identifies a TIS Configuration file Element lt TISCOoOnTig gt srs lt TiSeContig gt Max Instances al Parent None Optional No Attributes Attribute Optional Type Description Name Kill a a File version in the File version in the format Major Minor Major Minor HALO TIS User s Manual Rev 1 5 page 14 of 17 C Stock Flight Systems 2011 5 2 Bus Element The bus element contains the bus specification Element lt Bus gt lt Bus gt Max Instances Unlimited Parent TESCOnEIG Optional No Attributes Attribute Optional Type Description Name emna 42424 w lea tector ine bus eihar ssdd or text name of the bus either ascbd or can Identifier of the bus used to distinct between multiple buses of the same name The de fault value is O 5 2 1 Function Element The function element contains a function Element lt Function gt lt Function gt Max Instances Unlimited Parent Bus Optional Yes Attributes Attribute Optional Type Descripti
4. all three of them Q Secondary Backup Bus non inverting SEC n c n c n c n c SEC Secondary Backup Bus inverting n c n c n c OOOO OOO O TIS Figure 9 Bus Isolation Unit TIS Connector Pinout HALO TIS User s Manual Rev 1 5 page 5 of 17 C Stock Flight Systems 2011 Power to the BIU is on a 6 pin circular Bendix 9429 PTO2SE 10 6P connector Power is on Pin A 28VDC and Pin D DC GND all other pins are unused The connector pinout is shown in Figu re 10 A 28VDC D DC GND Figure 10 Bus Isolation Unit Power Supply Connector Pinout The wiring from the aircraft ASCB D test interface connector to the Bus Coupler has to include the required termination resistors for the Primary and Backup Bus According to the Honeywell speci fication these resistors are 124Q 1 tolerance 1 4W metal film resistors The corresponding part used for all 124Q resistors in the TIS installation is DigiKey P N MFR 25FBF 124R The internal circuit schematics of the Bus Coupler is shown in Figure 11 J1 CONS D aii t Figure 11 Internal Circuit Schematics of the Honeywell Bus Coupler The combination of the Honeywell Bus Coupler and the BIU allows non certified commercial of the shelf COTS equipment to interface to the ASCB D bus Both units are transformer coupled The BIU uses the same circuit and components as the Honeywell MAU NIC to interface to the ASCB D bus Additionally the BIU has on opti
5. information required by the tis application to generate the appropriate UDP IP pak kets xml2cfg reads the XML configuration file displays the detected functions and processes all parameters to create tis cfg A sample XML configuration file is shown below lt xml version 1 0 encoding UTF 8 gt lt TISConfig version 1 0 name HALO Demo Config gt lt Bus name ascbd id 0 gt lt Function name ADS description Air Data System gt lt Parameter name baroAltitude1 gt lt Handle function 4 instance 1 channel 0 identifier 4 gt lt Signal data_type Float unit ft rate 50 00 min 2100 00 max 61000 00 resolution 0 50 data_bits 17 gt lt Information group_name airData50msec group_desc 50 msec Air Data Parameter Group signal_desc Pilot Baro Altitude gt lt Parameter gt lt Parameter name baroAltitude1 gt lt Handle function 4 instance 2 channel 0 identifier 4 gt lt Signal data_type Float unit ft rate 50 00 min 2100 00 max 61000 00 resolution 0 50 data_bits 17 gt lt Information group_name airData50msec group_desc 50 msec Air Data Parameter Group signal_desc Pilot Baro Altitude gt lt Parameter gt lt Parameter name staticAirlfemperature gt lt Handle function 4 instance 1 channel 0 identifier 16 gt lt Signal data_type Float unit Deg C rate 50 00 min 105 00 max 65 00 resolution 0 00 data_bits 17 gt lt Information grou
6. unit Deg Angle rate 12 50 min 180 00 max 180 00 resolution 0 00 data_bits 19 gt lt Information group_name irs12msec429 group_desc 12 msec A429 Inertial Reference System Data signal_desc Pitch Angle gt HALO TIS User s Manual Rev 1 5 page 12 of 17 C Stock Flight Systems 2011 lt Parameter gt lt Parameter name pitchAngle gt lt Handle function 7 instance 2 channel 0 identifier 12 gt lt Signal data_type Float unit Deg Angle rate 12 50 min 180 00 max 180 00 resolution 0 00 data_bits 19 gt lt Information group_name irs12msec429 group_desc 12 msec A429 Inertial Reference System Data signal_desc Pitch Angle gt lt Parameter gt lt Parameter name pitchAngle gt lt Handle function 7 instance 2 channel 1 identifier 12 gt lt Signal data_type Float unit Deg Angle rate 12 50 min 180 00 max 180 00 resolution 0 00 data_bits 19 gt lt Information group_name irs12msec429 group_desc 12 msec A429 Inertial Reference System Data signal_desc Pitch Angle gt lt Parameter gt lt Parameter name pitchAngle gt lt Handle function 7 instance 3 channel 0 identifier 12 gt lt Signal data_type Float unit Deg Angle rate 12 50 min 180 00 max 180 00 resolution 0 00 data_bits 19 gt lt Information group_name irs12msec429 group_desc 12 msec A429 Inertial Reference System Data signal_desc Pitch Angle gt lt Parameter gt lt Parameter name p
7. B D Interface Overview 28VDC HALO TIS User s Manual Rev 1 5 page 2 of 17 C Stock Flight Systems 2011 Figure 4 shows the Honeywell Bus Coupler which is installed very close to the ASCB D test con nector panel on the right side of the rear cockpit section of the aircraft Figure 5 shows the Bus Iso lation Unit BIU Figure 4 Honeywell Bus Coupler Figure 5 Bus Isolation Unit BIU HALO TIS User s Manual Rev 1 5 page 3 of 17 C Stock Flight Systems 2011 nation provides 100 isolation and read only access to the aircraft ASCB D bus and prevents any Figure 6shows the firewall concept based on the Bus Coupler and Bus Isolation Unit This combi adverse effects on the safety critical side 80 y 8487 uey O pappsuuos si y sng q ssj YUM zuswdinbs g2SY ay umop aye JOU pue 0 uonejosi jeando payoys aq ues jey juawbas pue jeonyoaja AjUO sng pej e Os pue sapiaoid peal Aem auo pajdnog osje pue Sng pajsauuos au JALWOJSUBI SAPIADI4 0 PEO PIEPUe s e SAPIADI4 IDR Be i y 18948 I gt enano sng 1 T SLOD WeWicenbe jemo ig J0 4 aaa L06 99SLc02 LS WiSLUTUL LINN janMASUOH S34snd juewdinb3 NOILWIOSI SNd LAVYOUIV uolisinboy d 49S Y Sul Y BAST G d SV sasn yene OTVH Ul paesu sy C Stock Flight Systems 2011 page 4 of 17 Figure 6 Firewall Concept based on Bus Coupler and Bus Isolation Unit HALO TIS Users Manual Rev 1 5 The ASCB D connector pinout of the Honeywell Bus
8. Coupler is shown in Figure 7 Bus Output non inverting BUSOUT 5 n c 4 9 BUSOUT Bus Output inverting n c 3 8 n c Bus Input non inverting BUSIN 2 7 BUSIN Bus Input vereng Bus Input non inverting BUSIN 1 6 BUSIN Bus Input inverting Figure 7 Honeywell Bus Coupler ASCB D Connector Pinout Both the aircraft side bus and the isolated bus going to the BIU are on the same and only ASCB D connector of the Bus Coupler Also the termination resistor for the aircraft bus stub is attached to dedicated pins for this purpose The BIU ASCB D connector pinout is shown in Figure 8 Only Pins 1 and 6 of the the ASCB D connector going to the Bus Coupler are used on the BIU The ASCB D connector on the BIU is a 9 pin male D Sub and requires a 9 Pin female on the aircraft wiring to mate with the BIU O n c 5 n c 4 9 ne n c 3 8 ae see 2 7 n c Secondary Backup Bus non inverting SEC 1 6 SEC Secondary Backup Bus inverting O ASCB D Figure 8 Bus Isolation Unit ASCB D Connector Pinout On the output side of the BIU that connects to the TIS platform is a 9 Pin female D sub with data on Pins 1 and 6 shown in Figure 9 requiring a male 9 Pin D Sub on the wiring going to the TIS The TIS platform also has a 9 pin D Sub that is male requiring a 9 pin female on the end connec ting to the TIS Pins 1 and 6 are used on both sides of the BIU and on the TIS 9 pin connector Only these two pins are used on these D Sub connectors
9. c_ 2 23 _13_11_2008 01 e Tue_Dec__2 23 13_11_2008 02 HALO TIS User s Manual Rev 1 5 page 9 of 17 C Stock Flight Systems 2011 The user screen of the TIS available through the VGA connector after the completed boot process is shown in Figure 18 0 a an om z E openSUS O Online Help Konsole Ro ra i ra 1 a diruser DLRTIS Shell Layers Channels Paths A A J 2 A A 2 cine IW Untitied 1 0 RGB 1 layer OS 08 41 am Ej Figure 18 TIS screen after completed boot process The tis application can be invoked with the LIVE shell script in the DLRTIS directory manually This script calls tis with the following parameters tis tis cfg Escape le_reg nic le_reg LIVE 192 9 200 255 3000 0O The blue parameter is the IP address on which the UPD packets will be sent while the red para meter indicates the first UDP port number that will be used One UDP packet consists of 256 para meters If more parameters than 256 are specified in tis cfg these parameters are transmitted on ascending UDP port numbers Note that the IP address used in the LIVE shell script has to corre spond with the general network settings of the Ethernet interface eth1 which may be modified using the Linux yast2 configuration tool Alternatively the tis application can be invoked automatically after the TIS has booted This is ac complished by the startup script TIS autostart whi
10. cally isolated one way data path The wiring between the aircraft test connector the Bus Coupler the BIU and the TIS uses the Ho neywell specified ASCB D cable ECS P N 322402 and is shown in Figure 12 The total length of the cable between the aircraft test connector and the Bus Coupler is 210mm while the length of the cable between the Bus Coupler and the BIU is 2 1m After the BIU the cable length to the TIS is 10 8m but can easily be extended to 15m if required Opening any connection between the BIU and the TIS has absolutely no effect on the ASCB D bus integrity at all Positronic P N RD9S10000 connectors are used as the mating connectors for the No 1 2 Bus Test Interfacer and the Bus Coupler HALO TIS User s Manual Rev 1 5 page 6 of 17 C Stock Flight Systems 2011 ca 200mm 4 q 3 4m BIU ASCB D Connector Mission Interface Panel Receptacle TIS Connector white 10 0m white Mission Interface Panel Connector BIU TIS N Ea l PH 7 Bus Coupler white F e a nE EE Hee ee eee NHH NHN NHE NHE NREN NRN Nnn NREN NHE NHE Nnnn Nnn NHE NEn EHE EHE nE E mE E 0 8m 1240 E EZTEIL No 1 2 Bus Test Interface Figure 12 Wiring between Test Interface Connector Bus Coupler BIU and TIS HALO TIS Users Manual Rev 1 5 page 7 of 17 C Stock Flight Systems 2011 3 Telemetry Interface System Connections and Operator Interface The TIS is basically a rugged SUSE Linux bas
11. ch is placed in the home dlruser kde Autostart directory The content of TlS autostart is Desktop Entry Comment Comment en_US Encoding UTF 8 Exec e home dliruser DLRTIS tis GenericName DLR TIS Application GenericName en_US DLR TIS Application lcon yast kdump Mime Type Name DLR TIS V1 0 Name en_US DLR TIS V1 0 Path e HOME StartupNotify true Terminal true HALO TIS User s Manual Rev 1 5 page 10 of 17 C Stock Flight Systems 2011 TerminalOption TerminalOptions home dlruser DLRTIS tis cfg nome dliruser DLRTIS Escape le_reg nome dlru ser DLRTIS nic le_reg LIVE 192 9 200 255 3000 0 noclose Type Application Version 1 0 X DCOP Service Type none X KDE SubstituteUID false X KDE Username X SuSE translate true The tis application continuously displays the status of the processed ASCB D data together with the 12 5ms frame count and the value of the parameters specified in the tis cfg file as shown in Figure 19 Additionally the remaining recording time and fill status of the external USB hard disk is shown With the start of the LIVE script the tis application creates three logfiles in tmp e tmp TIS_log txt e tmp config_log txt e tmp WRITE_THREAD_log txt These readable files contain all system messages about the boot process including the network setup TIS_log txt the content of the tis cfg file config_log txt and the data storage process on the exte
12. e of the signal data type HALO TIS Users Manual Rev 1 5 page 16 of 17 C Stock Flight Systems 2011 Description Clear text name of the signal unit Update rate of the signal in milliseconds Minimum value of the signal in engineering units Maximum value of the signal in engineering units Resolution of the signal in engineering units data_bits yes int Number of valid data bits for this signal within the 32 bit parameter rightmost arrangement 5 2 1 1 3 Information Element The information element defines additional information associated with a parameter Element lt Information gt lt Information gt Max Instances Unlimited Parent Parameter Optional Yes Attributes Attribute Optional Type Description Name Clear text description of the signal group HALO TIS Users Manual Rev 1 5 page 17 of 17 C Stock Flight Systems 2011
13. ed PC with the corresponding I O connections For operation within HALO the following interfaces are used 28VDC Power Supply Input VGA Monitor Interface USB Keyboard Mouse Interface USB Harddisk Interface ASCB D Interface CANaerospace ARINC825 Interface 10 100 1000 Mbit s Ethernet Interface The following interfaces are available in addition but are used only for maintenance system upgra de purposes e DVD CD ROM Drive e Reset Switch e Power Switch Figure 13 shows the TIS front panel layout with its corresponding connectors Figure 14 the rear panel The VGA USB and Ethernet connectors are according to standard PC specification Power to the TIS is on a 2 pin circular Amphenol ALOOF11 2P connector requiring a ALO6F11 2S mating plug on the aircraft wiring Power is on Pin A 28VDC and Pin B GND the connector pinout is shown in Figure 15 The pinout of the ASCB D connector and the CANaerospace ARINC825 con nector are shown in Figures 16 and 17 THTABITFS WHS IS ttt eie ere RAHI GLU JDA EP tps C U UKA m Figure 14 TIS Rear Panel layout A 28VDC B DC GND 18 36VDC Figure 15 TIS Power Connector Pinout HALO TIS Users Manual Rev 1 5 page 8 of 17 C Stock Flight Systems 2011 e n c 5 n c 4 9 n c n c 3 8 ne n c 2 f ue ASCB D Bus non inverting SEC 1 6 SEC ASCB D Bus inverting Figure 16 TIS ASCB D Connector Pinout n c 5 n c 4 9 TG n c 3 8 n c CAN Low 2 7
14. following files generated by Gulfstream during the avionics system configuration of the aircraft e Planeview_Configuration_Data mdb e Planeview_ASCB_Data mdb e Escape le_reg from the Escape MODULE TISPROC APPBIN directory e nic le_reg from any Escape MODULE directory These files generated using original Honeywell tools will change from software load to software load Therefore the TIS needs to be upgraded each time a new software load is installed in the air craft While the Escape le_reg and nic le_reg files can be used as is the mdb database files have to be converted by ICS Stock Flight Systems into an XML file using the format as specified in Appendix A of this manual The name of this master ASCB D bus configuration file is e HALOMasterConfig xml A maximum of 4096 parameters may be selected from this file and be used to create flight test specific configuration files of the same format The parameters specified in the flight test specific file used for a mission will be continuously read from the ASCB D bus converted into engineering data and transmitted in one or more UDP IP packets every 12 5ms The data renewal rate of 80 per second is fixed and directly driven by the ASCB D bus data flow The flight test specific configuration file has to be converted into a special format for the tis appli cation using a converter program called xml2cfg The resulting file has the name tis cfg and contains all
15. itchAngle gt lt Handle function 7 instance 3 channel 1 identifier 12 gt lt Signal data_type Float unit Deg Angle rate 12 50 min 180 00 max 180 00 resolution 0 00 data_bits 19 gt lt Information group_name irs12msec429 group_desc 12 msec A429 Inertial Reference System Data signal_desc Pitch Angle gt lt Parameter gt lt Function gt lt Bus gt lt TISConfig gt The execution of the xml2cfg converter program creating the tis cfg file will generate the follo wing output xml2cfg DemoConfig xml Input file DemoConfig xml opened Bus name ascbd id 0 Function name ADS Function name IRS 15 Parameters written to tis fg closing file The NIC le_reg and Escape le_reg files together with the flight test specific tis cfg have to be pla ced into the DLRTIS directory where the tis application is started from Upon program start tis reads all these files to configure its ASCB D interface and data processing 4 3 UDP IP Packet Format Description The UDP IP packets transmitted over the Ethernet interface by the tis application every 12 5ms have a fixed length of 1040 bytes each The packet format consists of 32 bit wide parameters or ganized in Little Endian data representation The Packet format is shown below Packet Size ASCB D Frame Number Packet Identifier Parameter n CRC The first 4 bytes of the packet form a 32 bit integer value indica
16. on Name no sting o lceanetnamestihe anciom text name of the function descriptio yes sting oo Description of the function in clear text 5 2 1 1 Parameter Element The parameter element defines a TIS parameter Element lt Parameter gt lt Parameter gt Max Instances Unlimited Parent Function Optional Yes Attributes HALO TIS Users Manual Rev 1 5 page 15 of 17 C Stock Flight Systems 2011 Attribute Optional Type Description Name Clear text name of the parameter 5 2 1 1 1 Handle Element The handle element defines a parameter handle Element lt Handle gt lt Handle gt Max Instances Unlimited Parent Parameter Optional Yes Attributes Attribute Optional Type Description Name function it Function l Function identifier of the parameter associa of the parameter associa ted with the handle instance no int Instance of the parameter associated with the handle channel Channel of the parameter associated with the handle 0 pilot side 1 copilot side identifier Identifier of the parameter associated with the handle 5 2 1 1 2 Signal Element The signal element defines the signal associated with a parameter Element lt Signal gt lt Signal gt Max Instances Unlimited Parent Parameter Optional Yes Attributes Attribute Optional Type Description Name data_type yes stigs Clear text name of the signal data type text nam
17. p_name airData50msec group_desc 50 msec Air Data Parameter Group signal_desc Static Air Temp gt lt Parameter gt lt Parameter name totalAirlTemperature gt lt Handle function 4 instance 1 channel 0 identifier 23 gt lt Signal data_type Float unit Deg C rate 50 00 min 80 00 max 105 00 resolution 0 00 data_bits 17 gt lt Information group_name airData50msec group_desc 50 msec Air Data Parameter Group signal_desc Total Air Temp gt lt Parameter gt lt Parameter name pressureAltitude gt lt Handle function 4 instance 1 channel 0 identifier 24 gt lt Signal data_type Float unit ft rate 50 00 min 2100 00 max 61000 00 resolution 0 50 data_bits 17 gt lt Information group_name airData50msec group_desc 50 msec Air Data Parameter Group signal_desc Pressure Altitude gt lt Parameter gt lt Function gt lt Function name IRS description Micro Inertial Reference System gt lt Parameter name pitchAngle gt lt Handle function 7 instance 1 channel 0 identifier 12 gt lt Signal data_type Float unit Deg Angle rate 12 50 min 180 00 max 180 00 resolution 0 00 data_bits 19 gt lt Information group_name irs12msec429 group_desc 12 msec A429 Inertial Reference System Data signal_desc Pitch Angle gt lt Parameter gt lt Parameter name pitchAngle gt lt Handle function 7 instance 1 channel 1 identifier 12 gt lt Signal data_type Float
18. rnal USB hard disk WRITE_THREAD_log txt Note that data recorded on the external USB hard disk can also be played back using the tis ap plication A sample invocation of a recorded data playback is shown below tis tis cfg Escape le_reg nic le_reg Tue_Dec__ 2 23 13_11_2008 01 192 9 200 255 3000 0 During a playback the logfile tmp RECPLAY_log txt containing information about the playback process is created The recorded data is transmitted in realtime in the same way as it would be a live stream As all ASCB D data of the attached bus is contained in the recording file different con figurations that is tis cfg files may be used than the one during the original flight diruser DLRTIS DLRTIS Shell Konsole Session Edit View Bookmarks Settings Help DataTap based DLR ASCB D Interface UDP V11 00 Dec 4 2008 16 59 29 Copyright 4000 2009 IC5 5 G TOCK alirTemperaturestatus altitudeRate baroAltitudet calibratedAirspeed 7 OT Ee O J A mach a utcTenthsMinutes i utcOUnesMinutes Enum a a a l lal Shell l Figure 19 LIVE shell script output HALO TIS Users Manual Rev 1 5 page 11 of 17 C Stock Flight Systems 2011 4 2 Honeywell ASCB D Configuration Files The tis application reads the raw data stream from the attached ASCB D bus and continuously processes it using a periodic device driver This periodic device driver requires the
19. ting the packet size 0x00000410 1040 while the following 4 bytes contain the ASCB D frame number relating to the parameter The Packet Identifier provides information about the number of the packet with respect to the total num ber of packets transmitted based on the equation Total_Frame_Count 100 Frame_Number HALO TIS User s Manual Rev 1 5 page 13 of 17 C Stock Flight Systems 2011 The last 4 bytes form a 32 bit CRC for the entire UDP packet This CRC is a 32 bit ANSI 3 66 CRC with a generator polynomial of Oxedb88320 or X24 KOE KEE KEE KX OLKTEE KET EXTOL KEE XE KEKE XO Each UDP packet holds 256 parameters each 32 bits wide which are in the order as specified through the XML configuration file For every 256th parameter a new packet with a different port number in ascending order is generated and transmitted That means that for 513 parameters three UDP packets with a size of 1040 bytes each will be generated Unused parameters in the last packet are padded with zeroes 5 Appendix A XML Configuration File Format Description The TIS Configuration uses the XML file format which is human readable and directly compatible with word processing tools for more information please refer to www ws org TIS Configuration files shall have the suffix xml The file format uses XML tags to identify the information elements Tags are case insensitive ASCII text strings embraced by lt gt brackets Unrecognized tags within a TIS
20. ures 1 and 2 show the TIS unit front and rear view Figure 1 HALO Telemetry Interface System TIS 02A front view HALO TIS User s Manual Rev 1 5 page 1 of 17 C Stock Flight Systems 2011 Figure 2 HALO Telemetry Interface System TIS 02A rear view 2 ASCB D Bus Interface The cabling between the aircraft ASCB D No 1 2 Bus Test Interface Connector located on the front right side behind the cockpit and the TIS is shown in Figure 3 As the ASCB D bus is flight cri tical the interface to the TIS uses two firewalls A certified Honeywell ASCB D Bus Coupler Ho neywell P N 7027566 901 for electrical isolation and a Bus Isolation Unit for logical and electrical isolation The Bus Isolation Unit as well as the ASCB D interface in the TIS do not contain any transmitting devices and have read only capability exclusively The cable length between the Test Interface Connector and the Bus Coupler is around 200mm so that the impact on the total length of the Secondary Backup Bus is negeglible The cable used for all connections is be according to Honeywell ASCB D specification ECS P N 322402 From the Bus Isolation Unit to the TIS the length of the bus is 10 8m but can also be extended to a maximum of 15m Ethernet ca 20em ca 3 4m Bus Isolation Unit BIU Telemetry Interface System TIS ASCB D Bus Test Interface Honeywell Connector Bus Coupler CANaerospace ARINC 825 Figure 3 TIS ASC
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