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Installation Manual

1. Revision 1 3 38 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E passed Altitude Reporting test General A sufficient number of test points should be checked to ensure that the altitude reporting equipment and transponder perform their intended function through their entire range while ascending or descending Tests some altitude steps to ensure proper operation of each altitude code segment of the encoder Verify that the correspondence error value of the altimeter system is 125 feet or less Verify that exceeding 50 000 ft and 1 000 ft generates an out of range error message if using the internal alticoder Verify that exceeding 62 700 ft and 1 000 ft generates an out of range error message if using external alticoders If alticoder set to 100 ft resolution Verify in all cases that the Q bit is set to 0 If alticoder set to 25 ft resolution Verify in all cases that the Q bit is set to 1 for altitudes up to 50 170 ft For altitudes above 50 170 ft the Q bit must be set to 0 Airspeed Fixed Field Interrogate the equipment to confirm the maximum airspeed report On the Ground Condition If a means for automatically indicating the on the ground condition e g a weight on wheels or struct switch is available Verify that the equipment correctly reports the on the ground condition in the CA FS and VS fields Verify that the equipment correctly re
2. GARRECHT Avionik GmbH The system will be operated using the following devices Mode key Selects the operating mode 4 Double shaft encoder with push on Enters or modifies values capability for inner knob 4 1 On Off key To enable the system press key 1 shortly After the start the unit performs the built in test and shows the operating mode For switching off press key 1 for at least 3 seconds Release the key when the LCD becomes blank 4 2 Ident key Pressing key 2 invokes the ident mode for 18 seconds Use this function only when the ATC requires to sqawk ident 4 3 Mode key Key 3 selects the following modes e SBY Standby System is switched on no replies or squitters will be sent e ON Selected reply code will be replied for Mode A C interrogations altitude information is set to zero squittering is enabled Mode S interrogations will be replied e ALT Selected reply code will be replied for Mode A C interrogations altitude information is set to indicated value squittering is enabled Mode S interrogations will be replied 4 4 Double shaft rotary encoder Main input device for setting values is the double shaft rotary encoder Rotating the outer knob selects the position to be modified Rotating the inner knob changes the selected value The edit mode will be started rotating the inner or outer knob of the double shaft encoder Pushing the inner knob confirms the selected value and cancels the edit mo
3. site Ot enti Debe obe ape ptt i E 27 Z nntennadstallaliopss orbe ai 30 IQ 30 7 2 Special instructions for antenna installation in composite aircraft 30 7 2 1 Mounting 4 5 2 een 30 7 22 Ground Plane SIZE Ds 30 8 Antenna cables E IE 31 9 Post installation configuration and Setup otto rp etie ente 32 9 1 Setting up pilot specific data esc ne ie 32 Revision 1 3 3 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 9 1 1 Flight ID alrerattregisttation ar see a a als 32 9 1 2 Display CODE Bebo ioo ein ts Ws 33 9 1 3 Display ea 33 9 2 Setting up password protected data 34 ee Tota e 34 9 2 2 ECD COnthas ee 34 9 23 ssaa lle lai 34 922 Alreralt data n ea Ne iano era 35 10 Determining installed equipment performance 38 10 1 Checking equipment installation 38 10 2 Equipment performance 38 10 3 Flight test procedures s ceca c seele 40 GOhBr alo stona id a A ADEL Ae E 40 10 3 2 Flight tests instructions csse 24 eee tete eene 40 Appendix Ac DIRIBFISIOS oor Er Ere SERERE EE EE EE RM EE 41 VT 01 Steerin
4. DO NOT POWER ON THE TRANSPONDER WITH THE ANTENNA M DISCONNECTED Ks Damage to the RF unit caused by a disconnected antenna can be determined by the manufacturer and is not covered by the manufacturers warranty 6 2 4 1 Connector wiring CN1 CN1 is used as the main connector for the aircraft installation All signals lines listed in the following table need to be connected to CN1 CN1 Use for connecting the following signals lines Power GND Suppression On ground RS 232 for ADS B Rear view of steering unit Revision 1 3 21 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E Wire the female SUB D 9 plug to be connected to CN1 back of the steering unit as described in the following table Refer to chapter 17 for a proper cable installation and assembling of the connector viewed from back of SUB D 9 female connector Connect to common GND of airframe Do not connect if no on ground signal is provided by aicraft installation Terminate as shown next page Connect to common GND of airframe Revision 1 3 22 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 6 2 4 2 Wiring the connection between the steering unit and the central unit CN2 Use for connecting to the central unit via connector of the mounting kit Perform a 1 1 connection to the craddle connector Power GND Supp
5. english Document 01 0200 11E In this case the following messages appears in the startup screen confirm this message by pressing lt Ident gt or Modes or push button of rotary encoder confirm this message by pressing lt Ident gt or lt Mode gt or push button of rotary encoder 9 2 4 2 Flight ID Here you can enter the flight ID corresponding to the aircraft address Mode S address Refer to par 9 1 1 to learn how to set up the flight ID The flight ID entered in this menu can be overwritten by the pilot entering the unprotected area if required 9 2 4 3 Aircraft Maximum Speed maxspeed This submenu shown contains the settings for the aircraft maximum speed This data needs to be set for communication with the TCAS system installed in larger aircraft Consult your aircraft s flight manual to determine the required information To enter the desired value follow these steps e Press the inner knob of the double shaft rotary encoder The underlined first digit of the speed range shown on the screen indicates the edit mode e Use the inner knob of the double shaft rotary encoder to select the appropriate range for the aircraft the unit has been installed in Entering a certain value manually is not possible Please use the values suggested by the system To finish editing the maximum speed press the push button of the rotary encoder If you do not know the aircraft maximum speed please select lt unkno
6. Use the outer knob of the rotary encoder to select the desired submenu Sets the basic value for the LCD contrast Additionally the system provides an automatic temperature dependent contrast control To modify the value press the inner button of the rotary encoder and use the inner encoder to set up the desired values 9 1 3 Display illumination The next screen shown is the illumination set up Possible values on LCD backlight and button illumination on automatic brightness control by ambient light sensor off LCD backlight and button illumination always off Press the inner knob of the rotary encoder and rotate it to set up the desired values This menu will be shown only if the unit provides an illuminated display Revision 1 3 33 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 9 2 Setting up password protected data The input fields for aircraft related data such as 24 bit Mode S or aircraft maximum speed address is password protected to prevent unwanted modifications by unauthorised persons The password for this set up area is 10795C Here are step by step instructions for entering the Mode S address and other aircraft related data e Check if the transponder antenna has been connected to the device properly e If so switch on the unit by pressing key 1 e Ifthe BITE build in self test has been performed successfu
7. determined by the manufacturer and is not covered by the manufacturers warranty Revision 1 3 27 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 6 3 3 1 Connector wiring The VT 01 UltraCompact comes with a prewired connector Anyway if modifications on this connector are required or a new connector should be needed follow the instructions of this chapter Wire the female plug to be connected to the connector CN3 on the back of the central unit as described in the following table viewed from the back of the SUB D 9 female connector Pin Function Additional information mutual suppression Do not connect if no on ground signal is provided by aircraft System Unit VT 0104 xxx Always install the CAN Fuse 3A bus termination 10 to 28 V DC gt DME Suppresion Data in Supp Voltage Suppression RS 232 RX CAN LO GND PWR Enable on Ground CAN HI GND CAN Termination 100 Ohms Recommended cable types 2 Power Input AWG 18 TEFZEL 22759 16 18 Red and blue wire Interfaces AWG 24 TEFZEL 22759 16 24 Wire or AWG 22 TEFZEL 27500 22TG1T14 Single core shielded Suppression AWG 22 TEFZEL 27500 22TG1T14 Single core shielded
8. zarten 9 5 3 EcUpmellbeldss sss oot ee ML ii 10 5 4 Mode S transponder level i 10 5 5 Equivalences to FAA TSO C112 10 5 6elimialions pae gat nl nio SEL 10 5 7 Environmental GaledOrles uoto ERE Rd eliche 11 CINTO ale 11 5 7 2 V TOT UllraCombpaoL oi ote coto nett tee E 12 sm mele WAL TOW GI eT m 13 5 9 Telecommunication 13 5 10 Logic of on Ground interface nn 13 5 11 CAN Bus interface claire 13 qb 14 6 1 InstallattonV 01 single block ocio 14 6 1 1 Assembling the steering unit and central unit 14 6 1 2 Panel 15 6 1 3 Static pressure 15 Sm nis CPP 16 6 2 Installation V T 01 s3WOSDIOCR arri 19 6 2 1 Installing the mounting kit cradle 20 6 2 2 Panel MO NG e hoteles 20 6 2 3 Static pressure connection scesi ni 20 RAN SOCII a ae eure a 21 6 2 5 Cradle handling iea osea ae on ee euo 25 6 3 Installation VT 01 UltraCompact aa lea iano 27 Panel TOL D Dee noo nre ie 27 6 3 2 Static pressure connection i 27 63 3
9. Avionik GAV 4709 0005A I Suppression 2 2 f 2 I PWR Enable 6 6 7 t 6 I CAN LO 4 4 7 4 can 8 8 7 ae 8 I CN2 FS232RX 3 3 T 3 on Ground 7 7 l 7 Supp Voltage 1 1 1 mE GND 5 5 1 ij i a 5 on GND 9 9 9 max 10 meters 30 ft Revision 1 3 23 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 6 2 4 3 Power supply The transponder is supplied by the aircrafts s primary power source 10 V to 28 V DC The system provides a protection against reverse polarity Always install a fuse 6 2 4 4 Suppression interface The suppression line needs to be wired to other avionic components such as DME or TACAN to suppress any replies from the transponder that void capabilty of such systems while operating The suppression line provides IN and OUT capability to prevent data transmission either to the transponder or to other equipment Wiring the suppression line requires a qualified avionic technician or engineer to prevent any kind of malfunction of the installed equipment All equipment connected to the suppression line must be re inspected and re approved before operation Refer to chapter 5 for specifications of the suppression interface 6 2 4 5 On ground interface If your aircraft installation provides an on ground signal it should be connected to this pin The transponder replies only to discretely addressed Mode S
10. MODE gt button returns to the next higher menu level 9 2 4 5 Alticoder set up This menu can be activated only if the system has been set into the ALT mode for at least 10 sec after switching on and a firmware version of the main processor board unit is at least rel 1 50 Possible values int 25ft uses the internal pressure sensor for alticoding with 25ft resolution int 100ft uses the internal pressure sensor for alticoding with 100ft resolution Other values are for future enhancements e g external alticoder and must not be selected Press the inner button of the rotary encoder and use the inner encoder to set up the desired values Revision 1 3 37 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 10 Determining installed equipment performance In order to comply with EUROCAE ED 73B it is required to determine equipment performance of the installed equipment The complete aircraft installation must be certified by authorized personal before operation 10 1 Checking equipment installation passed Accessibility Controls provided for in flight operation shall be readily accessible from the operator s normal seated position Displayed information shall be clearly viewable without obstruction from the normal seated position s of the appropriate operator crew member s Aircraft Environment Insta
11. Manual english Interfaces Human machine interface User input capablity Automatic input capability On Ground interface Suppression interface Alitcoder capability Self test routines BIT 5 2 Certification base ETSO 2C112a EUROCAE ED 73B Revision 1 3 Document 01 0200 11E The system provides 3 buttons and a twinaxle rotary encoder for inputting values and selecting operational modes System messages and entered values are displayed on a 2 lines 12 characters LCD display The system detects the input of an on ground switch If the aircrafts frame does not supply such an information the input channel will be set to airborne always ref to chapter 5 10 Logic 0 on ground condition The system provides an suppression interface to prevent interference with other instruments installed in the same aircraft such as DME Impedances DC 0 4 V to 30 V 7 2 kOhms DC lt 0 4 V 1 kOhms AC 1 kOhms Levels output 10 V input 7V 30V The system contains an integral digital alticoder to provide data about pressure altitude for Mode C information in 100 ft steps It s line has to be connected to the aircraft s static pressure system Range 1000ft to 40 000ft After powering on the system runs several internal self test routines permanently In case of errors the user gets warned visble and audible and depending on the level of error the system stops operating with a
12. Revision 1 3 28 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 6 3 3 2 Power supply The transponder is supplied by the aircrafts s primary power source 10 V to 28 V DC The system provides protection against reverse polarity Always install a Fuse 6 3 3 3 Suppression interface The suppression line needs to be wired to other avionic components working in the 962 1213 MHz frequency band such as DME or TACAN to suppress any replies from the transponder that void the capabilty of such systems while operating The suppression line provides IN and OUT capability to prevent data transmission either to the transponder or other equipment Wiring the suppression line requires a qualified avionic technician or engineer to prevent any kind of malfunction of the installed equipment All equipment connected to the suppression line must be re inspected and re approved before operation Refer to chapter 5 for specifications of the suppression interface 6 3 3 4 On ground interface If your aircraft installation provides an on ground signal it should be connected to this pin The tranponder replies only to discretely addressed Mode S interrogations if the on ground signal is present The permament emission of squitters will not be effected Refer to chapter 5 10 for logic table of this interface 6 3 3 5 RS 232 interface This interface is intended for ADS B applications It may be used for
13. ground system replies not to Mode A C and Mode S all call interrogations squitters active airborne system replies to all interrogations squitters active Do not install an manual on ground switch in the cockpit of your aircraft If no adequate on ground switch is provided in the airframe leave the on ground input unconnected 5 11 CAN Bus interface The system provides a CAN Bus interface for communication between steering unit and central unit A detailed description of the interface can be obtained by the manufacturer for system integrators or OEMs only Revision 1 3 13 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 6 Aircraft installation The VT 01 provides maximum levels of flexibility Depending on the space in your cockpit you can have a single block or two block equipment installation The two block system requires a mounting kit cradle PN VT 0103 1 to carry the central unit It allows a quick installation and removal of the complete central unit without using tools If each aircraft in a fleet carries a steering unit and a mounting cradle the central unit can be interchanged between all aircraft All aircraft related data is stored in the steering unit which always remains in an aircraft General All installation work shall be performed in accordance with the acceptable methods techniques and practices for aircraft alterations inspections and repair sho
14. instructions of FAA AC 42 13 2B regarding antenna installation e Select a suitable position for installing the antenna The manufacturer of your aircraft should give you detailed information regarding this issue e Mount the transponder antenna as described by the antenna manufacturer e To prevent damages by moisture seal all antenna mounts e When choosing a position for installation always be sure not to damage structural devices of the airframe e For antenna installation in pressurized aircraft follow the special instructions of FAA AC 42 13 2B 7 2 Special instructions for antenna installation in composite aircraft 7 2 1 Mounting Preparation The electrical bonding of the antenna to the aircraft ground is extremely important If this is not done properly antenna performance characteristics may become distorted and nulls may appear in the antenna radiation pattern This in turn may cause erratic navigational readings or signal drop out The electrical bonding of antennas to composite aircraft is best accomplished by direct metal to metal contact of the antenna mounting hardware to an internal ground plane To do this you must have the mounting screws washers and nuts make direct contact to the internal ground plane with the use of a backing plate The backing plate must make direct contact to the internal ground plane Sandwich the aircraft skin and internal ground plane between the antenna base plate and internally mounted backin
15. reported altitude responses to Mode C should also be checked d Verify if ATC confirms valid replies with gear down if applicable and flaps set to landing configuration e Verify if interference with other electronic equipment installed in the aircraft occurs during the flight For detailed information regarding flight tests refer to document FAA AC 23 8B Chapter 5 Revision 1 3 40 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E Appendix A Dimensions VT 01 Steering unit and System unit a 47 30 65 x Revision 1 3 41 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E VT 01 Mounting kit with craddle Revision 1 3 42 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E VT 01 UltraCompact Revision 1 3 43 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E Appendix B Template for panel cutout Revision 1 3 44 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E Appendix C Assembling BNC TNC plugs for AIRCELL 7 coaxial cable Slip the nut the pressure ring and the rubber gasket over the cable end Hint With a small amount of vaseline the rubber gasket will slide more easily Bend copper braid at 90 degrees
16. 70 Watt antenna central unit P N VT 0102 070 or system unit central unit P N VT 0104 070 Cable Type Maximum length m Maximum length ft RG 58 C U 607109 AIRCELL 7 60 118 not certified for aircraft installation o The tables above are showing several antenna cable types and it s maximum lengths for reference only If other cable lengths or types should be used be sure not to exceed a maximum loss of 2 5 dB For connectors in the antenna line assume a loss of 0 2 dB each Please always check if certified cable is required for the installation in your aircraft f Revision 1 3 31 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 9 Post installation configuration and setup 9 1 Setting up pilot specific data 9 1 1 Flight ID aircraft registration A Mode S transponder broadcasts the flight id company callsign for commercial aircraft or the aircraft registration for smaller private operated aircraft flight id may be changed if required Usually the FID is the callsign of your uf aircraft unless field 7 of the flight plan contains other data Always check before each flight if your flight id has been set correctly If the transponder is operated in several aircraft with installed cradles then the steering units usually installed in the instrument panel need to remain in the same aircraft The steering uni
17. Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Revision 1 3 Document 01 0200 11E VT 01 Secondary Surveillance Radar Transponder Mode S Installation Manual Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E Record of Revisions Always keep this page in front of this document Page s Description of Change inserted by 110805 110 all released _ 27 09 05 1 1 modifications in wording after review JG 12 01 06 1 2 chapter 11 added JG Information about setting up aircraft related data 14 02 07 1 3 Inew P N VT 0104 VT 01 UltraCompact introduced aires Revision 1 3 2 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 1 Table of Contents RecordorRevisionsas esse a M 2 COMES ater ta ra aneignen 3 2 PIOIBOO oce HIER DE REM RU UEM MI 5 Unpacking and part identification 000 5 E 5 3 2 VTSOTDIEAGCOTIDACL ER Hu lenta 6 4 Input Devices human machine 7 AN MOT COU 7 ceri M eee 7 Z3 Mode Koy oit DU SD LU D D LLL M 7 4 4 Double shaft rotary encoder eh eR oi ER ER 7 5 Technical data and specifications esca dee I 8 TEE 511K ttt ti 8 5 2 Gerliiiealion base
18. amage structural devices of the airframe Cut a 57mm 2 inch diameter hole with 4 x 4 1mm holes for the mounting screws see chapter 15 for detailed locations A minimum space of 62 mm x 62 mm behind the panel cut out is required for clearance with adjacent instruments A depth of 205mm is recommended to accommodate the transponder and electrical connectors 6 3 2 Static pressure connection The system contains an integral alticoder Connect the static pressure line of the aircraft to the connector on back of the central unit The integral alticoder supplies data immediatly after switching on the VT 01 No warm up period is required For calibration of the internal alticoder an instruction will be provided by the manufacturer to qualified installers 6 3 3 Wiring Wiring electrical components shall be performed by qualified personal only to prevent damages and hazardous situations that could result in loss of life All wires except the antenna line related to the VT 01 in single block configuration are connected to one SUB D 9 pin connector on the back of the central unit Ensure that the Sub D connector is fastened to the housing of the central unit correctly before operating the unit in flight The following subchapters describe the different lines required for operating the transponder DO NOT POWER ON THE TRANSPONDER WITH THE ANTENNA JE DISCONNECTED Damage to the RF unit caused by a disconnected antenna can be
19. aused by a disconnected antenna can be determined by the manufacturer and is not covered by the manufacturers warranty Revision 1 3 16 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 6 1 4 1 Connector wiring Wire the female plug to be connected to the connector CN3 on the back of the central unit as described in the following table Refer to chapter 17 for a proper cable installation and assembling of the connector viewed from the back of the SUB D 9 female connector Pin Function Additional Information 9V 28V DC Connect to aircraft primary power source mutual suppression Connect to DME suppression bus use shielded line RS 232 RX For ADS B Data in Not used in single block installation do not connect oe ee installation Steering Unit Central Unit Always install the CAN VT 0101 0 0 0 0102 n bus termination 3A 111 Supp Voltage 1 1 pe 9to 28 VDC 2 2 Suppression 2 2 O r DME Suppresion 3 3 RS 232 RX 3 3 4 Datain 4 4 CAN LO 4 4 515 GND 5 5 CAN 6 6 PWR Enable 6 6 Termination onGround 7 7 I 100 Ohms 8 8 CAN HI 8 8 9 9 GND 9 9 Recommended cable types Power Input AWG 22 TEFZEL 22759 16 16 Red an
20. cking and part identification 3 1 VT 01 The VT 01 transponder system is supplied with the following P N VT 0101 Steering unit P N VT 0102 070 Central unit Class 2 71 Watt or VT 0102 125 Central unit Class 1 125 Watt Document 01 0200 10 User s guide Document 01 0200 11 Installation manual this document Available options P N VT 0103 1 Mounting kit wiring harness with installation cradle required for installation of VT 01 as a two block system with remote steering unit It also allows simple and quick installation and removal of the central unit VT 01UC cannot be installed as two block systems P N VT 0103 2 Mounting kit wiring harness without installation cradle Document 01 0200 12 Maintenance and repair manual for avionic repairshops only Revision 1 3 5 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 3 2 VT 01UltraCompact The VT 01 UltraCompact transponder system is supplied with the following P N VT 0104 070 System unit or VT 0104 070 P N VT 0103 2 Mounting kit wiring harness without installation cradle Available options Document 01 0200 12 for maintenance and repair manual for avionic repairshops only Revision 1 3 6 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 4 Input Devices human machine interface Picture of front panel with Input devices
21. connecting a GPS receiver to broadcast the current position with extended squitters Minimum recommended NMEA sentences are GPRMC GPGGA GPGSA The baud rate is 4800 bps 6 3 3 6 CAN Bus interface The CAN Bus interface is used for communication between steering unit and central unit If the one block configuration will be installed a resistor 100 ohms must be used for proper termination of the bus A missing termination results in COMM error and malfunction of the system For pinout refer to the wiring diagram shown on the previous page 6 3 3 7 Antenna connection Connect the BNC plug of the antenna line to the connector in the back of the central unit Be sure that the plug has been fastened to prevent disconnection caused by vibration DO NOT POWER ON THE TRANSPONDER WITH THE ANTENNA K i DISCONNECTED Damage to the RF unit caused by a disconnected antenna can be determined by the manufacturer and is not covered by the manufacturers warranty Refer to chapter 9 for details about installing a transponder antenna in your aircraft Revision 1 3 29 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 7 Antenna installation 7 1 General Any type of suitable transponder antenna may be used for connection to VT 01 Antenna installation should be done by qualified personal only It is strongly recommend to follow the step by step instruction below Generally follow the
22. d Black Wire Interfaces AWG 22 TEFZEL 22759 16 22 Wire or AWG 22 TEFZEL 27500 22TG1T14 Single core shielded Suppression AWG 22 TEFZEL 27500 22TG1T14 Single core shielded Revision 1 3 17 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 6 1 4 2 Power supply The transponder is supplied by the aircrafts s primary power source 10 V to 28 V DC The system provides protection against reverse polarity Always install a Fuse 6 1 4 3 Suppression interface The suppression line needs to be wired to other avionic components working in the 962 1213 MHz frequency band such as DME or TACAN to suppress any replies from the transponder that void the capabilty of such systems while operating The suppression line provides IN and OUT capability to prevent data transmission either to the transponder or other equipment Wiring the suppression line requires a qualified avionic technician or engineer to prevent any kind of malfunction of the installed equipment All equipment connected to the suppression line must be re inspected and re approved before operation Refer to chapter 5 for specifications of the suppression interface 6 1 4 4 On ground interface If your aircraft installation provides an on ground signal it should be connected to this pin The tranponder replies only to discretely addressed Mode S interrogations if the on ground signal is present The pe
23. de Now rotate the outer knob to view and change the settings of the selected profile as shown in the following subchapters NOTE If you have not purchased for the multiple Mode S profile feature only Profile 1 can be selected 9 2 4 1 Aircraft address A proper installation and operation of a Mode S transponder requires the installer to set a unique 24 bit Mode S Address the aircraft maximum speed as well as the flight id or aircraft registration The 24 bit Mode S address needs to be obtained from your national aviation authority Contact the department where you got the aircraft registration from The first submenu shown in a profile contains the 24 bit address To modify the address follow these steps e Press the inner knob of the double shaft rotary encoder The underlined first digit of the 24 bit address indicates the edit mode e Use the outer knob of the rotary encoder to select the position to be modified Use the inner knob of the rotary encoder to modify the selected value Do not enter dashes or blanks The data must be entered left aligned e To finish editing the 24 bit address press the push button of the rotary encoder e Exit the flight id page by pressing the mode key A correct 24 bit Mode S address is required for proper Mode S operation If no address has been entered the system works as a Mode A C transponder Revision 1 3 35 Garrecht Avionik GmbH VT 01 Transponder Installation Manual
24. de cursor stops blinking Revision 1 3 7 Garrecht Avionik GmbH 5 Technical data and specifications 5 1 General Technical characteristics Data Mechanical VT 01 Dimensions Mounting Weights VT 01 UltraCompact Dimensions Mounting Weight Environmental Max Altitude Temperature Cooling Vibration Shock Electrical Voltage nom Voltage operational Current nom 13 8 V and 1200 A C replies sec Standby sqitters active RF power antenna Replyrate Output Impedance max VSWR Revision 1 3 VT 01 Transponder Steering unit 65x65x34 5 mm w o connectors Central unit 65x65x128 mm w o connectors 57 mm panel mount Steering unit 0 21 kg Central unit 0 61 kg 61 5 x 61 5 x 170mm 57 mm panel mount 0 57 kg 50 000 ft internal alticoder limited to 40 000ft see also limitiations chap 5 6 20 C 55 C passive no auxiliary cooling required DO160D Cat S Curve M Operational 6g crash safety 20g 13 8 V DC 9 to 32 V DC VT 0102 070 VT 0104 070 0 35 A VT 0102 125 VT 0104 125 0 45 A VT 0102 070 VT 0104 070 0 16 A VT 0102 125 VT 0104 125 0 17 A VT 0102 070 VT 0104 070 gt 70 Wp VT 0102 125 VT 0104 125 gt 125 Wp min 1200 s Mode A C min 50 s Mode S 50 Ohms 1 5 1 Installation Manual english Document 01 0200 11E Garrecht Avionik GmbH VT 01 Transponder Installation
25. em should start if power will be supplied to the main of the device i e by the avionic main switch To select the desired value follow these steps e Press the inner knob of the double shaft rotary encoder to invoke the edit mode e Rotate the inner knob of the double shaft rotary encoder to select the desired value Entering a certain value manually is not possible Please use the values suggested by the system e To finish editing the settings press the push button of the rotary encoder Possible values off System remains switched off after applying electrical power Standby System powers up in standby mode after applying electrical power Revision 1 3 34 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 9 2 4 Aircraft data All aircraft related data of the following chapters are stored in a profile If using the system in different aircraft i e balloons a special firmware feature provides up to five different profiles that can be selected by the pilot before takeoff To enter the following submenus press the inner knob of the rotary encoder if the acft data menu item has been selected The screen shows e To change the profile selection press the inner knob of the encoder and rotate it then to select the desired profile e If the desired profile has been selected press the inner knob of the rotary encoder again to finish the edit mo
26. enna connector first in to the cradle The shoulder washer will slide into the slots in the left and right wall of the cradle Then press the central unit down and Move it into the direction of the antenna connector If inserted correctly the spring lock will flip up Revision 1 3 25 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 6 2 5 1 1 Removal of the central unit form the cradle Press the spring lock down and pull the central unit into the direction of the spring lock When the shoulder washer contact the wall of the slots in the left and right side of the cradle s wall move the central unit up and take it out of the cradle Revision 1 3 26 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 6 3 Installation VT 01 UltraCompact The VT 01 UltraCompact is a very compact size unit with a low weight that allows installation in small cockpits General All installation work shall be performed in accordance with the acceptable methods techniques and practices for aircraft alterations inspections and repair shown in FAA documents AC 43 13 1B and AC 43 13 2A see www faa gov to obtain this documents free of charge in digital form 6 3 1 Panel mounting Determine a suitable position in the instrument panel that is in view of the pilot in command When choosing a position for installation always be sure not to d
27. g plate To test the electrical bonding of the blade to the aircraft a reading of 003 ohms between the antenna base plate and ground should be achieved 7 2 2 Ground Plane Size UHF antennas will require a metal ground plane size of 24 by 24 OR LARGER As large as practical will assure optimum antenna performance Most other antennas may also use the 24 by 24 rule but with ground planes larger is always better After installation double check that a reading of 003 ohms between the antenna base plate and ground has been achieved Revision 1 3 30 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 8 Antenna cable The antenna line connects the RF connector of the transponder to the antenna For a proper installation it is recommended to follow the instructions below e Follow the instructions of the cable and plug manufacturer e Fora proper installation avoid shorts and cable interruptions in the antenna line e For the most type of installation a special aircraft grade cable need to be used Do not exceed the maximum cable lengths specified below Class 1 instruments with 125 Watt antenna central unit P N VT 0102 125 or system unit P N VT 0104 125 Cable Type Maximum length m Maximum length ft RG 58 C U 11 60 o RG 213 15 9 6 RG 400 0 0 AIRCELL 7 602 1196 not certified for aircraft installation Class 2 instruments with
28. g unit and System UnNit ii 41 VT 01 Mounting kit with craddle hiciste eee eue ee 42 VT 01 UltraCompact Secs Sates lla eave Es etu ud tud 43 ee 44 APPEndix 45 Assembling BNC TNC plugs for AIRCELL 7 coaxial cable 45 Assembling the Sub D Connectors for interconnection wiring 46 Revision 1 3 4 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 2 Preface This manual contains installation information and instructions for the Mode S transponder VT 01 It shall be read before installing your VT 01 transponder The installation shall be carried out or supervised by a qualified person Damage caused by installation by unqualified persons is not covered by the manufacturers warranty Safety symbols The following symbols and terms are used in this manual Warning Warning statements identify conditions or practices that could result in injury or loss of life Caution K Caution statements identify conditions or practices that could result in damage of this product or other property Important note Indicates important or usefull information It is strongly recommended to read understand and follow the statement 3 Unpa
29. he following steps need to be performed Unfasten the 4 Screws 3 and remove the steering unit 1 from the central unit 2 Fasten a shoulder washer 5 with screws 4 on each side of the central unit Front of central unit Replace the quick lock terminals in back of the central unit with screws Rear view of central unit Revision 1 3 19 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E Replace the screws in the back of the steering unit with quick lock terminals Rear view of steering unit 6 2 1 Installing the mounting kit cradle Select a suitable place for installation of the mounting kit cradle P N VT 0103 1 in your aircraft Consider the space needed for inserting removing the central unit In order to remove make sure it is possible to reach and operate the lock device on the end of the cradle The maximum distance between steering unit and central unit is limited by the data interface cable used for communication between the system It shall not exceed 10 metres in length Fasten the mounting kit to the airframe using 4 x M4x5 screws 6 2 2 Panel mounting Determine a suitable position in the instrument panel that is in view of the pilot in command When choosing a position for installation always be sure not to damage structural devices
30. interrogations if the on ground signal is present The permament emission of squitters will not be effected Refer to chapter 5 10 for logic table of this interface 6 2 4 6 RS 232 interface This interface is intended ADS B applications It may be used for connecting a GPS receiver to broadcast the current position in the squitters Minimum recommended NMEA sentences are GPRMC GPGGA GPGSA The baud rate is 4800 bps 6 2 4 7 CAN Bus interface The CAN Bus interface is used for communication between steering unit and central unit If the two block configuration will be installed on each device a resistor 120 Ohms must be used for proper termination of the data bus A missing termination results in COMM Error and malfunction For pinout refer to the wiring diagram shown on the previous page 6 2 4 8 Antenna connection Connect the antenna line to the connector in the craddle When inserting the central unit into the cradle the antenna plug fits into the antenna socket of the cradle DO NOT POWER ON THE TRANSPONDER WITH THE ANTENNA E x DISCONNECTED Damage to the RF unit caused by a disconnected antenna can be determined by the manufacturer and is not covered by the manufacturers warranty Revision 1 3 24 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 6 2 5 Cradle handling 6 2 5 1 Inserting the central unit into the cradle Insert the central unit with the ant
31. lled equipment shall be compatible with the environmental conditions present in the specific location in the aircraft where the equipment is installed Display Visibility Displays shall be readable from the crew members normal position in all ambient light conditions for which the equipment is required 10 2 Equipment performance passed Reply Frequency Interrogate the installed transponder and verify that the reply frequency is 1090 MHz 1 MHz for both Class 1 and Class 2 equipment Transmitter Power Output a Verify that Class 1 transponders have a peak pulse power at the antenna end of the transmission line of at least 21 dBW and not more than 27 dBW b Verify that Class 2 transponders have a peak pulse power at the antenna end of the transmission line of at least 18 5 dBW and not more than 27 dBW Receiver Sensitivity a Verify that for Mode A C interrogations the receiver sensitivity of the equipment at the antenna end of the transmission line is 73 dBm 4 dB b Verify that for Mode S P6 type interrogations the sensitivity of the equipment at the Li antenna end of the transmission line is 74 dBm 3 dB Pressure altitude transmissions Select the mode lt ONs internal alticoder disabled and verify that 1 the transponder response to Mode C interrogations consists only of framing pulses Fl and F2 and 2 the transponder response to Mode 5 interrogations UF 4 UF 20 contains all ZEROs in the AC field
32. lly the system is ready for the next steps e f no valid Mode S address has been entered skip the messages by pressing the inner knob of the rotary encoder Always set the device into the lt SBY gt mode if you want to modify the settings in this menu e Enter the installation set up by simultaneously pressing key 1 and the push button of the rotary encoder e Enter the password shown above If entered correctly rotate the outer knob to navigate through the different menus as shown in this chapter e Press the inner knob of the rotary encoder to enter or edit the selected menu The edit mode will be indicated by underlining the first character of the menu entry e Anentered password remains active until switching off and on the unit 9 2 1 Illumination The first submenu shown in the password protected area is the illumination set up Refer to par 9 1 2 to learn how to set up the illumination of the device This setting is possible in the unprotected and password protected mode This menu will be shown only if the unit provides an illuminated display 9 2 2 LCD contrast The second submenu shown in the password protected area is the LCD contrast set up Refer to par 9 1 3 to learn how to set up the illumination of the device This setting is possible in the unprotected and password protected mode 9 2 3 Power up Mode The third submenu shown contains the settings for the power up mode Here you can define in which mode the syst
33. ltage Spike Conducted Audio Frequency Conducted Suscepibmy 180 nduedSigna Swscepibi y Radio Frequency Susceptibility 20 0 S radiated susc een ae esse di ia Jer je of harmonics of 1090 MHz Lightning Induced Transient Susceptibiiy 220 id Lightning Direct Effects cing Electrostatic Discharge ESD see chapter 5 6 for restrictions Revision 1 3 12 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 5 8 Software level The software level for VT 01 has been determined to be Level D Software whose anomalous behavior as shown by the system safety assessment process would cause or contribute to a failure of system function resulting in a minor failure condition for the aircraft 5 9 Telecommunication specifications Emission power with central unit VT 0102 125 or system unit VT 0104 125 250 Watts max with central unit VT 0102 070 or system unit VT 0104 070 200 Watts max Emission class 12M0M1D Frequency 1090 MHz 5 10 Logic of on Ground interface The transponder has an on ground interface which should be connected to your aircraft installation if an adequate signal will be provided The following table shows the system behaviour for different configurations and input at the interface on ground configuration in Menu on ground switch settings no on ground switch present on ground on wes Lu on
34. nductive aluminium tape braid which has former been flipped over the outer insulation e Install the hood cable clamps as shown in this and the following picture e Remove the shielding of each twisted pair Revision 1 3 47 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E e Insert the cable with the cable clamp into the hood as shown e Cut all pairs and the wire made of the braid to appropriate length for installation of a Sub D Connector not shown in this picture Always use shrink line when attaching the wires to the Connector Revision 1 3 48
35. of the airframe Cut a 57mm 2 inch diameter hole with 4 x 4 1mm holes for the mounting screws see chapter 15 for detailed locations A minimum space of 65 5mm x 65 5mm behind the panel cut out is required for clearence with adjacent instruments A depth of 50mm is recommended to accomodate the steering unit and electrical connectors 6 2 3 Static pressure connection The steering unit contains an integral alticoder Connect the static pressure line of the aircraft to the connector on back of the steering unit The integral alticoder supplies data immediatly after switching on the VT 01 No warm up period is required For calibration of the internal alticoder an instruction will be provided by the manufacturer to qualified installers Revision 1 3 20 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 6 2 4 Wiring Wiring electrical components should be performed by qualified personal only to prevent damages and hazardous situations that could result in loss of life All wires except antenna line related to the VT 01 in two block configuration are connected to several SUB D 9 pin connectors in the back of the steering unit and the central unit Ensure that the Sub D connectors are fastened to the housing of the central unit or steering unit correctly before operating the unit in flight The following subchapters describe the different lines required for operating the transponder
36. ole with 4 x 4 1mm holes for the mounting screws see chapter 15 for detailed locations A minimum space of 65 5mm x 65 5mm behind the panel cut out is required for clearence with adjacent instruments A depth of 205mm is recommended to accomodate the transponder and electrical connectors 6 1 3 Static pressure connection The system contains an integral alticoder Connect the static pressure line of the aircraft to the connector on back of the central unit Revision 1 3 15 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E The integral alticoder supplies data immediatly after switching on the VT 01 No warm up period is required For calibration of the internal alticoder an instruction will be provided by the manufacturer to qualified installers 6 1 4 Wiring Wiring electrical components shall be performed by qualified personal only to prevent damages and hazardous situations that could result in loss of life All wires except the antenna line related to the VT 01 in single block configuration are connected to one SUB D 9 pin connector on the back of the central unit Ensure that the Sub D connector is fastened to the housing of the central unit correctly before operating the unit in flight The following subchapters describe the different lines required for operating the transponder DO NOT POWER ON THE TRANSPONDER WITH THE ANTENNA Er DISCONNECTED Damage to the RF unit c
37. permanent error message Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 5 3 Equipment class Class 1 If using central unit VT 0102 125 If using system unit VT 0104 125 Class 2 If using central unit VT 0102 070 If using system unit VT 0104 070 5 4 Mode S transponder level Level 2se Mode S transponder 5 5 Equivalences to FAA TSO C112 Classes If using central unit VT 0102 125 or If using system unit VT 0104 125 Equal to FAA TSO C112 Class 2A1 120 010 If using central unit VT 0102 070 or If using system unit VT 0104 070 Equal to FAA TSO C112 Class 2B1 020 010 5 6 Limitations 1 To reach the required minimum RF peak power the use of an antenna cable with a total loss of less or equal 2 5 dB is required 2 The range of the internal alticoder is limited to a maximum altitude of 40 000 ft 3 The system using the CLASS 2 central unit P N VT 0102 070 or the system unit VT 0104 070 may be operated in aircraft not exceeding a maximum speed of 175 kts a maximum altitude of 15 000 ft and a MTOW of 5700 kg 4 The system using the CLASS 1 central unit P N VT 0102 125 or the system unit VT 0104 125 may be operated in aircraft not exceeding a maximum speed of 250 kts a maximum altitude of 50 000 ft and a MTOW of 5 700 kg Revision 1 3 10 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Documen
38. ports the airborne condition in the CA FS and VS fields If a means for automatically indicating the on the ground condition e g a weight on wheels or struct switch is not available Verify that the FS and VS fields indicate that the aircraft is airborne and that the CA field indicates that the aircraft is either airborne or on the ground CA 6 Also verify that when the unit is in the inhibit replies condition on the ground the transponder continues to generate Mode S squitters and replies to discretely addressed Mode S interrogations UF 0 4 5 16 20 21 24 but does not reply to Mode A C S All Call or Mode S Only All Call interrogations some installations may inhibit Mode A C If the unit is not in the inhibit replies condition Airborne condition verify that the transponder continues to generate Mode S squitters and also replies to Mode A C Mode A C S All Call or Mode S Only all Call and discretely addressed Mode S interrogation UF 0 4 5 16 20 21 24 Aircraft Identification AIS Interrogate the equipment with UF 4 or 5 and correct aircraft address with RR 18 and DI 7 or DI 7 and RRS 0 Verify that the equipment correctly reports the AIS information in the MB field of the reply Revision 1 3 39 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 10 3 Flight test procedures 10 3 1 General This guidance material offers examples of flight test procedu
39. res for demonstrating selected performance functions Flight demonstration of installed performance may be required to determine the performance and characteristics of the installed antenna If the aircraft has been equipped with a transponder before the flight test after installing the VT 02 might be obsolete if the following conditions are fulfilled e The rated RF output power of the old device was less or equal to the RF output power of the VT 02 e The antenna used for the VT 02 is the same as used before NOTE Replacing the old antenna by a new antenna of the same type is also sufficient to fulfil this requirement e f a new antenna line need to be installed be sure that the maximum loss of the new line does not exceed the loss of the old antenna line 10 3 2 Flight tests instructions For determining performance in flight all tests on ground as shown in 10 1 need to be performed successfully Arrange a schedule with the area air traffic control facility so that a controller is available to observe the transponder reply and communicate with the test aircraft to confirm performance of the transponder a Select a test area such that line of sight signal propagation is ensured distance 60 nm to selected ATC facilityx b So that ATC can confirm valid returns through normal flight attitudes test manoeuvres may include standard rate turns through 360 degrees climbs and descents c Verification of Mode A codes selected and
40. ression On ground RS 232 for ADS B CAN Bus Back of steering unit Wire the female SUB D 9 plug to be connected to CN2 back of the steering unit to the cable leading to the craddle as described in the following table Pin Function 10V to 28V DC Suppression RS232 RX CAN Low GND Pwr_enable On Ground CAN High GND CO Ni Go PO viewed from back of SUB D 9 female connector Steering Unit Craddle of mounting Kit VT 0103 VT 0101 0 0 0 with Central unit VT0101 xxx Always install the CAN Supp Voltage 1 1 jpe 8 28 V DC 4 1 I 1 Suppression 2 2 bus term ination RS 232 RX 313 Data in CAN LO 4 4 Recommended cable types GND 5 5 Termination PWR Enable 6 6 i m ohms Power Input AWG 22 TEFZEL 22759 18 16 Red and Black Wire Ground 7 7 Sa o Interfaces AWG 22 TEFZEL 22759 16 22 Wire or onSroun d AWG 22 TEFZEL 27500 22TG1T14 Single core shielded CAN HI 8 8 Suppression AWG 22 TEFZEL 27500 22TG1T14 Single core shielded GND 919 a Interconnection cable central unit steering unit Ethernet Cat 5 cable 4 x 2 twisted pair AVVG 24 S pel FAR 23 certified Type Garrecht
41. rmament emission of squitters will not be effected Refer to chapter 5 10 for logic table of this interface 6 1 4 5 RS 232 interface This interface is intended for ADS B applications It may be used for connecting a GPS receiver to broadcast the current position with extended squitters Minimum recommended NMEA sentences are GPRMC GPGGA GPGSA The baud rate is 4800 bps 6 1 4 6 CAN Bus interface The CAN Bus interface is used for communication between steering unit and central unit If the one block configuration will be installed a resistor 100 ohms must be used for proper termination of the bus A missing termination results in COMM error and malfunction of the system For pinout refer to the wiring diagram shown on the previous page 6 1 4 7 Antenna connection Connect the BNC plug of the antenna line to the connector in the back of the central unit Be sure that the plug has been fastened to prevent disconnection caused by vibration DO NOT POWER ON THE TRANSPONDER WITH THE ANTENNA E i DISCONNECTED Damage to the RF unit caused by a disconnected antenna can be determined by the manufacturer and is not covered by the manufacturers warranty Refer to chapter 9 for details about installing a transponder antenna in your aircraft Revision 1 3 18 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 6 2 Installation VT 01 two block To install as a two block system t
42. t 01 0200 11E 5 7 Environmental categories 5 7 1 VT 01 Section Category Conditions Temperature Altitude D1 aa 55 Temperature Variaion umdy 1 S A 20 G crash safety Vibration S Vibration curve 90 5 Explosion Profness Water Profness S X ERE X BEEN Fluids Susceptibilities X Po X pm X BEEN X 2 Sand and Dust Fungus Resistance Salt Spray BR Magnetic Effect Power Input DC peer RT Voltage Spike Conducted Audio Frequency Conducted 180 B Induced Signal Susceptibility 1940 JAP Radio Frequency Susceptibility 200 171 Pene ee IP QUEE of harmonics of 1090 MHz induced Transient Susceptbiniy 20 AEXXX Lightning Direct Effects eing Electrostatic Discharge ESD see chapter 5 6 for restrictions Revision 1 3 11 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 5 7 2 VT 01 UltraCompact Section Category Conditions Tempeaue AludeDi 0 Di __ 70 oc Temperature Varon fso B eomme C e E 20 G crash safety Vibration U2 Vibration curve F F1 poson Promes ooo o S oo WaterPimess oo KR 1 lidsSusepibilles __ no o Sandanadus E Fungus Resistans 100 X o Salt Seray 4K Power Input DC 22 aa _O_O O_ Vo
43. t carries the flight id So no changes are required when moving the central unit to another aircraft Follow these steps to set the flight id aircraft registration e Set the unit to standby SBY mode e Press the on off key and hold it Press the mode key within 3 seconds e The current flight id will be shown on the screen now Flight ID aircraft registration e To modify the flight id press the inner knob of the double shaft rotary encoder The underlined first digit of the flight id indicates the edit mode e Use the outer knob of the rotary encoder to select the position to be modified Use the inner knob of the rotary encoder to modify the selected value Do not enter dashes or blanks even when used in your aircraft registration or company callsign The data must be entered left aligned e To finish editing the flight id press the inner knob of the rotary encoder e the flight id page by pressing the mode key Revision 1 3 32 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english 9 1 2 Display contrast Document 01 0200 11E Check if the transponder antenna has been connected to the device properly If so switch on the unit by pressing key 1 If the BITE build in selft test has been performed successfully the system is ready for the next steps e Enter the installation setup by simultaneously pressing key 1 and the push button of the rotary encoder The screen shows as follows
44. to cable Remove 8 mm of the PVC sheath from the body Push in contact ferrule between end of the cable with a knife copper foil and braid until stop Trim braid even to rim of ferrule Slide rubber gasket down to the contact ferrule Slide teflon disk over center conductor insert center pin and solder carefully through the little hole Slide the prepared cable end into the connector housing until stop Tighten smoothly with two wrenches 16 mm so that there is still a small gap visible between the nut and the connector housing Slide teflon isolator on center pin Revision 1 3 45 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E Assembling the Sub D Connectors for interconnection wiring For a proper shielding of the interconnection wiring follow these steps e Remove the outer insulation of the interconnection cable 65mm 2 5 e Split the silver plated copper braid into two parts Leave about 15mm 1 6 of the braid e Twist one part of the braid to a wire e Cut the other part e Flip the remaining part of the braid over the outer insulation of the interconnection wire I lt ERS gt r FILIERA e Remove the conductive aluminium tape around the cable bundle Leave about 15mm 1 6 of the tape Revision 1 3 46 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E e Flip the co
45. wn gt Possible values unknown select this value if no information is present for your aircraft lt 75 kt 76 150 kt 151 300 kt 301 600 kt 601 1200kt gt 1200kt Note The maximum speed the VT 02 is allowed to use for is 250 kts Higher values are for reference only Revision 1 3 36 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E 9 2 4 4 Configuring on ground switch auto gnd The third submenu allows configuring the on ground switch input of the transponder It needs to be configured if the unit has been connected to an on ground switch provided by the airframe e Press the inner knob of the double shaft rotary encoder The underlined first digit on the screen indicates the edit mode e Use the inner knob of the double shaft rotary encoder to select the desired value Set it to YES if an airborne information will be provided by the aircraft and the transponder has been connected to this switch Select NO if no such switch is available in your aircraft If no on ground switch is available in your airframe the system broadcasts an airborne message permanently e To finish the edit mode press the push button of the rotary encoder If you do not know if an external on ground switch has been connected or works properly please select no for the auto gnd option To leave the configuration menu press the lt IDENT gt button Pressing the lt
46. wn in FAA documents AC 43 13 1B and AC 43 13 2A see www faa gov to obtain this documents free of charge in digital form 6 1 Installation VT 01 single block To install as a single block system the following steps need to be performed 6 1 1 Assembling the steering unit and central unit a connector the steering unit plug and the central unit plug are clean If not a __ Before attaching the steering unit to the central unit Check if the pressure remove all foreign bodies from the parts Replace the Quicklock terminals in the back of the steering unit with screws 4 pal amp 40 if installed Rear view of steering unit Revision 1 3 14 Garrecht Avionik GmbH VT 01 Transponder Installation Manual english Document 01 0200 11E Replace the screws 4 40 in the back of the central unit with quicklock terminals if installed Rear view of central unit 1 Assemble mating pressure connector and plug for both units in the correct orientation 2 Push the steering unit 1 onto the central unit 2 Use the 4 screws 3 to fasten both units Front of central unit 6 1 2 Panel mounting Determine a suitable position in the instrument panel that is in view of the pilot in command When choosing a position for installation always be sure not to damage structural devices of the airframe Cut a 57mm 2 inch diameter h

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