INTEGRA Installation Manual
Contents
1. 7 1 7 1 EXPLANATION OF POSSIBLE aa e erete tre asses nsns 7 2 7 2 BACK UP SYSTEM RECOMMENDATION 7 2 7 3 INTEGRA CONNECTOR 7 3 8 SENSOR CONNECTION 8 1 9 TL ELEKTRONIC EQUIPMENT CONNECTIONLN 9 1 9 1 REMOTE COMPASS u uu Sunqu Susa ee ee een 9 1 9 2 SERVO ee 9 1 9 3 VIDEO CAMERA yw EE PU ee Ve ea Eee e EE PERDE ERN 9 2 10 OTHER EQUIPMENT CONNECTION 10 1 Installation manual Page ii Rev E TL 6524 EFIS INTEGRA 10 1 CO GUARDIAN a I MEN SAL 10 1 10 2 CARMINS INUENIT 10 2 10 3 TRANSPONIDER mia E siete etm EL MM MM 10 3 10 4 GG reso mE dee MI MIEL 10 3 10 5 OTHER COMPATIBLE eser 10 4 11 CONCLUSION E 11 1 Installation manual Page iii Rev E 1 Revision Table TL 6524 EFIS INTEGRA Rev Revision Date Description ECO n By A 1 10 2008 In2. AVIONICS AIRCRAFT P1 FUSE __ SWITCH MASTER SWITCH MAIN SWITCH 2 ON De ov O JA 10 32V AIRCRAFT POWER 1 AICRAFTGROUND 14 AL AEN E BATTERY INTEGRA ___ SWITCHES D NOTE Protection by fuse of pin no 2 is recommended as it is shown on picture The reason is protection against accidental short circuit caused by connector manipulation or failure of cable insulation Advantage of this option The Integra Quick Start function is available for this option of power supply connection With this function the Integra can perform quick switch on in 2 seconds after Aircraft Master Switch and Avionics Switch is ON Disadvantage of this option The Integra is permanently consumes power of 0 5 mA of aircraft battery due its standby state Installation manual Page 6 11 Rev E TL 6524 EFIS INTEGRA 6 2 1 2 Recommended option AVIONICS P1 FUSE __ SWITCH MAIN SWITCH 2 AIRCRAFT FUSE MASTER SWITCH 10 32V AIRCRAFT POWER 1 Ow AICRAFT GROUND 14 JA J omaat O ansan INTEGRA 5 T OTHER SWITCHES D NOTE Protection by fuse of pin no 2 is recommended as it is shown on picture The reason is protection against accidental short circuit caused by connector manipulation or failure of cable insulation Advantage of this option When the Avion
3. 5 4 5 3 REAR VIEW 5 5 5 4 FRONT VIEW OF MOUNTING 5 5 5 5 SIDE VIEW OF THE MOUNTING 5 6 5 6 CUTOUT 5 6 27 INTEGRA MOUNTING DIAGRAM 5 7 6 ELECTRICAL DRAWING sicsscsscvessecosecoccscsnssesovenssosessocesssndetsssunsdessssnesosetatssseessesedessoessstassessesasesseesesceces 6 1 6 1 PIN FUNCTION 6 1 6 1 1 Possibilities of Power Signalization Transceiver and iFamily Interconnect 6 2 6 1 2 Transponder Interconnect ii son e 6 3 6 1 3 Auxiliary Ports and iFamily amp 1 ae a a a e a a entente 6 6 6 1 4 Auxiliary Input Output Interconnect 6 7 6 1 5 JAT and OAT Interconhect Vasa wer 6 8 6 1 6 Position Interconneti 6 9 6 1 7 Engine RPM Interconnect for future use 6 10 6 2 RECOMMENDED CONNECTIONS 6 11 6 2 1 Possibilities of Power Supply connection eese emen 6 11 0 2 2 Possible connection to frame ssi te ettet tiere eerte nba ea eken am vaan VR 6 13 6 2 3 Possibilities of Volts and Current Shunt Sensors Connection aee 6 14 6 2 4 Transceiver CONNECHON 6 16 7 INTEGRA DATA SHARING
4. RS 232 RS 232 GROUND CO Guardian m H Installation manual IH Page 10 1 lt RS 232 RS 232 GROUND CO Guardian Rev E 10 2 Garmin SL 30 TL 6524 EFIS INTEGRA The SL30 can be used as a VOR localizer or ILS localizer glide slope source for the HSI Diagram for connect to COMI COM1 RS 232 TX 4 COM1 RS 232 RX 3 COM1 GROUND 16 INTEGRA Diagram for connect to COM2 P02 RS 232 RS 232 TX GROUND GARMIN SL 30 2 RS 232 TX 18 COM RS 232 RX 17 COM2 GROUND 5 _ m INTEGRA Installation manual Page 10 2 tI RS 232 RS 232 TX GROUND GARMIN 51 30 Rev TL 6524 EFIS INTEGRA 10 3 Transponder Transponder Connection PIN 8 PIN 9 PIN10 PIN11 PIN12 PIN20 PIN21 PIN22 PIN23 PIN 24 14 13 19 17 16 21 18 Disable ARC RT359A 459A 859A 17 22 21 Disable BECKER ATC 2000 3401 14 17 Disable BECKER ATC 4401 3 Disable BENDIX TRP 2060 2061 660 Disable BENDIX TR541A 641B Disable COLLINS TDR 950 950L 2 EDO AIRE RT 777 Disable GARMIN 320 320A 327 3 GENAVE BETA 5000 Disable KING KT76 78 Disable KING KT76A 78A 76C 79 Disable KING 750A 5 KING KT75 Disable MICROAIR T2000 5 NARCO AT50
5. unit Max amps 20 mA AIRCRAFT POWER 10 32 Volts AIRCRAFT POWER 10 32 Volts j uuo249ju ndjyno ndur p p9 V9 DOH LINI SIHH 7659 11 Tenueur 5 8 9 e IAT TEMP SENSOR GROUND FOR IAT TEMP SENSOR OAT TEMP SENSOR GROUND FOR OAT TEMP SENSOR INTEGRA P2 12 24 13 25 NOIN lt p lt INSIDE AIR TEMPERATURE SENSOR IAT OUTSIDE AIR TEMPERATURE SENSOR OAT sro LVO pue LVI VADOHINI SIHH 7559 11 TL 6524 EFIS INTEGRA 6 1 6 Position Interconnect FLAPS OR OTHER POSITION SENSOR ra I N w N H E gt 2 a a z Z lt o o a amp oO 5 E 2 5 Installation manual Page 6 9 Rev E TL 6524 EFIS INTEGRA 6 1 7 Engine RPM Interconnect for future use ENGINE RPM us 1 6 7 19 2 6 7 19 20 LOW AMLITUDE HIGH AMPLITUDE GROUND FOR SENSOR POSITIVE PULSE ONLY INTEGRA Installation manual Page 6 10 Rev E TL 6524 EFIS INTEGRA 6 2 Recommended connections 6 2 1 Possibilities of Power Supply connection The following possibilities of power supply connection are applied in case the backup battery of Integra is not connected 6 2 1 1 Mostly recommended option
6. The diagram below shows the outside dimensions of the INTEGRA Note that the instrument and tray extend about 100 mm or 3 93 behind the panel Use the dimensions found on the diagram to plan for the space required by the instrument Take the following considerations into account when selecting a mounting location for the INTEGRA Avoid placing the instrument near heater vents or any source of extremely hot or cold air Air surrounding the INTEGRA during operation may be no warmer than 60 C Plan a panel location that allows convenient viewing of the instrument with no obstruction When flying straight and level the panel angle from vertical may not be greater than 30 degrees The unit must be aligned as close as possible with the longitudinal and lateral axes of the aircraft The firmware supports an adjustment for panel tilt but not for mounting errors in yaw or roll Correct attitude performance depends on mounting the INTEGRA square with the direction of flight To mount the INTEGRA you must make a rectangular cut out in your panel Ensure that the dimensions of the cut out are 7 283 185 mm wide and 5 650 143 mm tall Place the INTEGRA series mounting tray behind the cut out Secure it to your panel by Riveting or Screws Riveting is recommended but drilling holes for mounting screws and nuts will work as well Installation manual Page 4 1 Rev E TL 6524 EFIS INTEGRA 7 WARNING Avoid applying paint to the mounting rack The thic
7. x AUX AUDIO GROUND Intercom Connect other TL elektronic instruments via the iFamily amp Bus dE 3A MAIN SWITCH AIRCRAFT POWER EXTERNAL BATTERY OPTIONAL pue JaAroosue J uonezi eusiS JO T T 9 V9 DOH LINI SIHH 7659 11 uone pe1sug 6 9 AON ALTITUDE OUTPUT A1 ALTITUDE OUTPUT A2 ALTITUDE OUTPUT A4 ALTITUDE OUTPUT B1 ALTITUDE OUTPUT B2 ALTITUDE OUTPUT B4 ALTITUDE OUTPUT C1 ALTITUDE OUTPUT C2 ALTITUDE OUTPUT C4 STROBE SIGNAL GROUND INTEGRA P1 10 11 20 21 23 24 25 STROBE GND Transponder Topuodsue1 7 1 9 SIHH 7559 71 TL 6524 EFIS INTEGRA Inputs and Communication Connector P02 type D SUB25 Female connector on INTEGRA Pin Name iFamily Bus2 CANH N A COMI RS 232 RX RS 232 TX COM2 RS 232 GND RPM Positive pulse only for future use RPM High amplitude for future use Auxiliary No 1 Auxiliary No 2 ja Auxiliary No 3 Position input ja N Inside air temperature sensor ja Outside air temperature sensor iFamily Bus2 CANL N A COMI RS 232 GND COM2 RS 232 RX COM2 RS 232 TX P ja ja nN
8. ja ja 00 RPM Low amplitude for future use N RPM Ground for sensor for future use N ja Auxiliary No 4 N N Auxiliary No 5 N Ground for position input Ground for inside air temperature sensor Ground for outside air temperature sensor notation of pins D SUB 25 Female connector Installation manual Page 6 4 Rev E TL 6524 EFIS INTEGRA Installation manual Page 6 5 Rev E Tenueur 5 9 9 e COM1 RS 232 TX COM1 RS 232 RX COM1 GROUND RS 232 TX COM RS 232 RX COM2 GROUND IFAMILY BUS2 CANH IFAMILY BUS2 CANL INTEGRA P2 18 17 IN OUT GROUND IC AUX PORT1 IN m OUT GROUND LA 2 lt TL elektronic instruments via the iFamily amp Bus in Connect other Nalle JIIUUOITIU GAULLE JI pue S 10J SIHH 7659 11 Tenueur 5 1 9 e AUX INPUT OUTPUT 1 AUX INPUT OUTPUT 2 AUX INPUT OUTPUT 3 AUX INPUT OUTPUT 4 AUX INPUT 5 INTEGRA P2 10 21 22 BACKLIGHT POSSIBLE CONNECTION Positive detection INTEGRA AUX INPUT OUTPUT 470 ohm r Ground detection Control Output Customer 4
9. PNP type AUX IN Input positive 10 32 Volts Input GND Output 20 mA max internal resistor 470 2 Position Sensor Backlight control Manual control turn knob Automatic control sun sensor External control 5 12 24 Volts max 32 Volts Temperature Sensor 0 8000 2 0 5 4 5 Volts Oil water AUX Temperature Installation manual Page 3 3 Rev E TL 6524 EFIS INTEGRA 4 Install Recommendation 4 1 Introduction Careful planning and consideration are reguired to achieve the desired performance and reliability from the INTEGRA 4 2 Rack Consideration Plan a location that gives the pilot complete and comfortable access to the entire INTEGRA and so that it is plainly visible from the pilot s perspective Check that there is adequate depth for the rack in the instrument panel A place away from heating vents or other sources of heat generation is optimal 4 3 Calibration and testing of static pressure measurement for altitude determination 7 WARNING It s necessary to pressurized all three outlets AOA Static Pitot during process of calibration and testing of static pressure sensor for altitude determination 4 4 Installation into Panel WARNING Connect the cables into the connector WARNING If possible always use insulated wires connect to connect the Intercom so that you prevent possible interference from other equipment which could result in interference in the headphones
10. or equipment within the iFamily amp CAN BUS system AN CAUTION not interconnect the CAN BUS within one Integra Installation manual Page 7 3 Rev E TL 6524 EFIS INTEGRA 8 Sensor Connection The Integra can be connected only to the approved sensors see the Integra accessories list on our Website AN CAUTION Other sensors can damage the Integra therefore do not connect them to the Integra under any circumstances O NOTE Sensors intended for guantities measurement that have resistive output and are connected to the Integra cannot be shared with any other analogue or digital instrument to duplicate the displayed value Installation manual Page 8 1 Rev E TL 6524 EFIS INTEGRA 9 TLelektronic Equipment Connection 9 1 Remote Compass TL elektronic Remote Compass is source for the heading data P02 iFAMILY 8052 1 n A AI 7 iFAMILY BUS CANH iFAMILYS BUS 2 14 ja 8 iFAMILY BUS CANL INTEGRA REMOTE COMPASS 9 2 Servo TL elektronic Servo is necessary eguipment to use autopilot P02 iFAMILY BUS2 1 A A 7 iFAMILY BUS CANH N iFAMILY BUS2 14 1 17 8 iFAMILY BUS INTEGRA SERVO O NOTE The terminating resistors 1200hm on the iFamily should be put to more distant places i e to the Int
11. you connect TL 6524 with TL 6724 you will be able to share the screen data between the two instruments 0 1 0 0 1 0 EFIS TL 6524 EMS TL 6724 If you connect TL 6524 with TL 6824 you will be able to read the same data on TL 6824 as you have on TL 0 1 0 0 1 0 6524 EFIS TL 6524 REMOTE TL 6824 If you connect TL 6724 with TL 6824 you will be able to read the same data on TL 6824 as you have on TL 6724 EMS TL 6724 REMOTE TL 6824 If you connect TL 6624 with TL 6824 you will be able to read the same data on TL 6824 as you have on TL ca 6624 EFIS amp EMS TL 6624 REMOTE TL 6824 7 2 Back up System Recommendation We recommend this configuration for safe panel system redundancy TL 6524 and 6624 8 i e i 8 EFIS amp EM 5 TL 6624 EFIS TL 6524 In the case of instrument failure flight information will be available on the second instrument Installation manual Page 7 2 Rev E TL 6524 EFIS INTEGRA 7 3 INTEGRA Connector Location When running iFamily BUS at its higher speeds it is necessary to terminate the bus at both ends with 120 Ohms The resistors are there to prevent reflections of communication bus P01 P01 iFAMILYG BUS1 D D 1209 0 6W 4 iFAMILY BUS1 4 1200 0 6W lt iFAMILY BUS1 iFAMILYG BUS1 INTEGRA 1 INTEGRA 2 AN CAUTION A twisted pair cable must be used to connect instruments
12. 50A 150 12 NARCO AT5 6 6A 19 RADAIR 250 12 TERRA TRT250 250D Disable UPS APPLLO SL70 Disable WILCOX 1014A Disable GARMIN GTX 328 e IK 1 4 12 7 3 4 6 M G 6 9 7 2 7 5 13 K 10 4 GPS The GPS can be used as a data source for the EFIS HSI and Fuel pages as well as TL elektronic s EFIS based Autopilot P02 COM1 RS 232 TX 4 f IN 1 RS 232 3 OUT GPS COM1 GROUND 16 Y Ed GROUND INTEGRA Installation manual Page 10 3 Rev E TL 6524 EFIS INTEGRA 10 5 Other Compatible Equipment Notice Sensor Configuration is detailed in the Configuration Manual O NOTE Be sure that the external eguipment shares a common ground with the INTEGRA If your GPS is battery powered and not normally connected to aircraft ground you must connect the ground pin on its serial output to a ground common to the INTEGRA Installation manual Page 10 4 Rev E TL 6524 EFIS INTEGRA 11 Conclusion INSTRUCTIONS FOR RETURN If none of the above sections have helped resolve an ongoing issue with your INTEGRA please call TL electronic at 420 495 48 23 93 to discuss the issue with Technical Support In case the issue cannot be resolved we will provide you with an RMA number to use when shipping the
13. EGRA Table of contents TABLE OF CONTENT SS II 1 REVISION TABLE Dc 1 1 2 GENERAL DESCRIPTION i sssss ss s ssssssassasaaasaansvaaaa aavan aaaau avaus asua uaaau naa 2 1 2 1 GENERAL INFORMATION 2 1 2 2 LIMITED WARRANTY 2 1 3 TECHNICAL SPECIFICATIONS scisssscssssesscsvissonssessvssssosersssestsctsessecsoseessecstsiscssusisocsenssessssoescessscc venss 3 1 4 INSTALL RECOMMENDATION 4 1 4 1 INTRODUCTION Q Su 4 1 4 2 RACK CONSIDERATION u eee eceetectedeeteeeeee s cede eee e ai coe use Sa SSS a NQ uq 4 1 4 3 CALIBRATION AND TESTING OF STATIC PRESSURE MEASUREMENT FOR ALTITUDE DETERMINATION 4 1 4 4 INSTAELATION INTO PANBIZ secs ai dees coh n aqna q uq aqu ha C 4 1 4 5 RECOMMENDED WIRING PRACTICES 4 2 4 6 HARNESS 4 2 4 7 POWER REQUIREMENTS s 4 2 4 8 WIRING OVERVIEW usaq u usus 4 2 4 9 CGROUNDING au ul usan M aq a u ayau 4 3 5 MECHANICAL DRAWING eco cesses assasssssssasssssasssessssssssssesassssassssesssssssssssssasasssesasssseasssssssessessasass 5 4 5 1 FRONTPIBW 5 4 5 2 SIDE VIE
14. H MASTER SWITCH M Ow 5 zs SWITCH aur p ALTERNATOR BATTERY Protection by fuse is recommended as it is shown on picture The reason is protection against accidental short circuit caused by connector manipulation or failure of cable insulation Cables for voltage measurement should be as short as possible Because of cable voltage drop this is cause of possible measurement imprecision Page 6 15 Rev E TL 6524 EFIS INTEGRA 6 2 4 Transceiver connection PHONE A TRANSCEIVER PHONE MIC TRANSCEIVER MIC GROUND TRANSCEIVER GROUND TRANSCEIVER N INTERCOM P1 WARNING RECORDING AUDIO SIGNAL 7 GROUND FOR WARN REC AUDIO SIGNAL 19 INTEGRA PHONE A MIC GROUND 5 AUX IN Y TRANSCEIVER 100uF 10V P1 1kohm WARNING RECORDING AUDIO SIGNAL 7 joouF tov GROUND FOR WARN REC AUDIO SIGNAL 19 Y INTEGRA Installation manual Page 6 16 Rev E TL 6524 EFIS INTEGRA 7 INTEGRA Data Sharing iFamily amp iFamily amp BUS2 Other servos or units Servo 1 A Remote Compass Installation manual Page 7 1 Rev E TL 6524 EFIS INTEGRA 7 1 Explanation of Possible Connections Here are a few Instrument connection Possibilities If
15. INTEGRA Installation Manual TL 6524 P N TLD 6524X DI 001_RevE TL 6524 EFIS INTEGRA Copyright 2008 2010 TL elektronic Rights Reserved Except as expressly provided below no part of this manual may be downloaded transmitted copied reproduced disseminated or stored in any storage medium for any purpose without the express prior written consent of the TL elektronic company Address your questions about the technical information to TL elektronic Other information about sale distribution should be directed to our exclusive distributors see World Distributor list on our website Producer s address TL elektronic Inc Airport Building 125 503 41 Hradec Kralove Czech Republic Fax 420 49 548 23 94 E mail info tl elektronic com Web Site Address www tl elektronic com Please send your e mail address to customer tl elektronic com to receive the latest information about software upgrade Send your ideas to innovation tl elektronic com We will evaluate your suggestion and provide an update Windows is registered trademark of Microsoft Corporation All trademarks and registered trademarks are acknowledged SchecK is registered trademark of TL elektronic iFamily is registered trademark of TL elektronic sModern is registered trademark of TL elektronic All information in this User s manual is subject to change without prior notice Installation manual Page i Rev E TL 6524 EFIS INT
16. INTEGRA to us If your unit is still under warranty the repairs will be performed and the INTEGRA will be returned promptly If your warranty has expired the TL electronic representative will make arrangements with you and make you fully aware of the costs before proceeding with the repair While TL electronic makes every effort to save and restore your unit s settings and calibrations we cannot guarantee that this will happen Please note that after you receive your unit back from TL electronic with a factory calibration the heading display on the INTEGRA may be inaccurate once re installed in your aircraft Installation manual Page 11 1 Rev E
17. connected to frame and onboard systems are simultaneously connected to dashboard current would flow through the case of Integra and it may result in damage of the Integra Installation manual Page 6 13 Rev E TL 6524 EFIS INTEGRA 6 2 3 Possibilities of Volts and Current Shunt Sensors Connection 6 2 3 1 The typical connection in case of one current shunt sensor P3 AMPS 1 HI 17 n AMPS 1 LO 35 VOLT1 15 VOLTS GND 33 mi AIRCRAFT OTHER SWITCHES O NOTE 1 Protection by fuse is recommended as it is shown on picture The reason 15 protection against accidental short circuit caused by FUSE INTEGRA MASTER SWITCH ALTERNATOR connector manipulation or failure of cable insulation Installation manual Page 6 14 FUSE See Note 1 1A BATTERY 1 Rev E TL 6524 EFIS INTEGRA 6 2 3 2 Possible connection for full configuration P3 VOLT1 15 VOLT2 16 VOLT3 34 V VOLTS GND 33 AMPS 1 HI 17 AMPS1 LO 35 AMPS2 HI 18 2 LO 36 J AMPS3 HI 19 AMPS3 LO 37 U INTEGRA PUMP avionics T Le See Note 2 NOTE1 D 2 Installation manual FUSE FUSE Note 1 1A 1A AIRCRAFT PUMP SWITC
18. egra connector and to the more distant instrument e g compass On one bus there is possible to have only two resistors Installation manual Page 9 1 Rev E TL 6524 EFIS INTEGRA 9 3 Video Camera Visual information provided by video camera is useful especially in case of towing a glider Video camera is not directly connected to the Integra it uses TL elektronic Video server This solution enables connect up to four video cameras Cycling through views of cameras is controlled by the Integra buttons Check operation and pictures of displayed Towing screens of the Integra in User Manual section Integra Menu Other Setting EN mini USB TL 6524 Video server TL 6624 0024 63 V4 V3 V2 V1 Video input P Video camera 0024 64 S Video output P power P S s video s V2 Power 12V Installation manual Page 9 2 Rev E TL 6524 EFIS INTEGRA 10 Other Equipment Connection NOTE 10 1 CO Guardian There could be only one external equipment connected to each port We recommended as CO Guardian type 452 452R 353 or 353R Following diagrams are just for these types Diagram for connection to COMI COM1 RS 232 TX COM1 RS 232 RX COM1 GROUND INTEGRA P02 OF Diagram for connection to COM2 COM2 RS 232 TX COM2 RS 232 RX COM2 GROUND INTEGRA 18 17
19. following pages provide wiring diagrams and details for each of these harnesses 4 7 Power Requirements 22 AWG wire is normally sufficient for the power supply and grounding but we recommend that you consult a wire sizing chart and determine the size required for the wire routing in your particular aircraft Ensure that the power supply include a circuit breaker 4 8 Wiring Overview The INTEGRA power requirement is as low as 3 amps in a 12 24 volt system And therefore you can use a 3 amp circuit breaker See the technical specification chart for details Installation manual Page 4 2 Rev E TL 6524 EFIS INTEGRA 4 9 Grounding Many of the engine sensors require a connection to a aircraft ground with the INTEGRA There are many places on an aircraft where you could connect these sensors However the ideal location to ground these sensors is near the INTEGRA to minimize voltage differences between the sensor and instrument grounds Some sensors e g oil pressure and oil temperature connect to ground via their cases contact with the engine or aircraft body There must be a solid connection between this ground and the INTEGRA ground The oil temperature sensor is very susceptible to voltage differences between the engine case and the negative terminal of the battery Ensure that solid thick electrical connections exist between the engine and battery ground Some sensors do not have a grounded case and have two leads instead Th
20. he User Manual in the aircraft at all times 2 2 Limited Warranty This manual contains important information that may affect the safety of the pilot passengers aircraft the operation of the system or time to install the system You MUST read the manual prior to installing this system Any deviation from these installation instructions is the sole responsibility of the installer and should be done in accordance with AC 43 13 Read the Warranty Agreement There is information in the Warranty Agreement that may alter your decision to install this product If you do not accept the terms of the Warranty Agreement do not install this product This product may be returned for a refund Contact TL elektronic Inc for details 7 WARNING If the installer does not have the skills knowledge tools equipment or facility to perform and determine whether the installation of this product is safe reliable and accurate and to determine whether this product is operating properly after installation DO NOT INSTALL THIS PRODUCT If the owner pilot and or installer are unwilling to take the responsibility for the installation and operation of this product DO NOT INSTALL THIS PRODUCT This product may be returned for a refund Contact TL elektronic Inc for details Installation manual Page 2 1 Rev E NOTE D NOTE 4 WARNING WARNING Installation manual TL 6524 EFIS INTEGRA By installing this product the aircraft owner pilot and ins
21. he installation make sure the unit will fit in the location you intend to install it without obstructing the operation of any controls Page 2 2 Rev E TL 6524 EFIS INTEGRA 3 Technical Specifications Physical characteristic Width 192 mm 7 559 Height 148 mm 5 827 Depth 76 5 mm 3 012 Panel rectangle hole Weight without battery 185x143 mm 7 283 5 63 Weight with battery General Specifications Operating Temperature Range 20 to 60 Humidity 95 non condensing Altitude Range 4600 meters max 15100 feet max Power Range 10 0 to 32 0 Volts Max Signalization 30 Volts 1 Ampere Power Consumption 1 15 Ampere 14VDC without ext sensors 1 83 Ampere when battery is charging Vibration 5 to 500 Hz Show Rate LCD Refresh Long term Memory and communication Storing Rate 15 fps depends on volume of information displayed 0 1 to 60 seconds user selectable Memory Capacity Scheck method Data Saved Endurance 30 years Rolling Memory life time Communication 100 000 hours 1 second storing rate up to 115 200 bps 12 Mb s 480 Mb s Installation manual Page 3 1 Rev E 1 Mb s TL 6524 EFIS INTEGRA Display parameters Resolution 800x480 pixels Brightness 800 cd m2 Memory Card INTEGRA support SD and SDHC memory card Encoder Type of encoder Mode C Positive
22. ics Switch disconnects the pin no 2 the Integra will detect off state and will be switched off by regular way in 5 seconds Then the Integra power supply could be disconnected without any harm by Aircraft Master Switch Disadvantage of this option If the Integra power supply is disconnected by Aircraft Master Switch sooner than in 5 seconds the latest records in memory could be damaged and therefore they could not be available for inspection This does not apply to Crash Memory Installation manual Page 6 12 Rev E TL 6524 EFIS INTEGRA 6 2 1 3 The least convenient option AVIONICS P1 FUSE SWITCH MAIN SWITCH 2 ON o W AIRCRAFT MASTER SWITCH 10 32V AIRCRAFT POWER 1 ow AICRAFT GROUND 14 E i NETT i BATTERY INTEGRA SWITCHES Advantage of this option It s simple Disadvantages of this option The switch Avionics Switch or Aircraft Master Switch disconnects the Integra from power supply This can result in error of data storage In case of the error the sequence of latest records in memory could be damaged and therefore it could not be available for inspection This does not apply to Crash Memory 6 2 2 Possible connection to frame 0 The connection to frame of dashboard is recommended because the metal case of Integra is in contact with metal plate of dashboard In case dashboard is not
23. is sensor with tow out puts will not be affected by the differences described above In the case of one output sensors second output is the body of sensors measuring can be affected by current drawn between the instrument ground and the battery ground that can cause voltage differences which adversely affect engine sensor readings Installation manual Page 4 3 Rev E TL 6524 EFIS INTEGRA 5 Mechanical Drawing 5 1 Front View 15 827 5 2 Side View Rev E Page 5 4 Installation manual TL 6524 EFIS INTEGRA 5 3 Rear View AOA Static Pitot 9 909 5 4 Front View Mounting Rack Installation manual Page 5 5 Rev E TL 6524 EFIS INTEGRA 26 5 5 Side View of the Mounting Rack 1 024 163 5 6 437 5 6 Panel Cutout For more information about installation into the panel look at chapter 4 4 D NOTE Rev E Page 5 6 Installation manual TL 6524 EFIS INTEGRA 5 7 INTEGRA Mounting Diagram D NOTE For more information about installation into the panel look at chapter 4 4 Installation manual Page 5 7 Rev E TL 6524 EFIS INTEGRA 6 Electrical Drawing 6 1 PIN FUNCTION list Main Connector P01 type D SUB25 Male connector on INTEGRA Pin Name Aircraft Power 10 to 32V Main switch 10 to 32 V N A iFamily CANH Audio out Left HI pilot headphones or IC Audio out Right HI pilo
24. itial version 0001 Jezek B 2 2 2009 Language correction Jezek C 14 7 2009 New function added Jezek D 1 10 2009 Revision on P2 connector Jezek E 5 12 2010 New function added Hovorka Installation manual Page 1 1 Rev E TL 6524 EFIS INTEGRA 2 General description 2 1 General Information The INTEGRA stores general information The pilot and or owner of the aircraft is responsible for verifying that this information is accurate and complete The pilot and or owner is further responsible on a regular basis for maintaining this information and insuring that it is up to date and accurate If the pilot and or owner of the aircraft is unable or unwilling to do this the files must be deleted When the installation is finished inspect the system for loose fittings connections clamps probes and inspect for leaks chafing obstructions heat damage and anything that may cause unsafe flight before the Ist run up after the Ist run up and after the first flight The INTEGRA allows the pilot to enter checklists and general information through the USB port This data must be verified for its accuracy by the pilot before it is used Before allowing the aircraft to be flown verify the instrument markings displayed on the INTEGRA screens are accurate with the aircraft s POH Pilot s Operating Handbook for every function displayed on the INTEGRA Before allowing anyone to operate the aircraft read the User Manual including Notices therein Keep t
25. kness of a coat of paint may distort the rack dimensions O NOTE When mounting the INTEGRA frame will not be flush with rack mounting screws The screws will be exposed after mounting the INTEGRA Before painting it is necessary to apply putty around the Screws Upon securing the mounting rack to the back of your panel slide the INTEGRA into it 4 5 Recommended Wiring Practices For all electrical connections use correct wiring techniques taking care to properly insulate any exposed wire or cables A short circuit between any of the wires may cause damage to the INTEGRA and or your aircraft Make all connections to your harness before connecting it into any of the components of the system Do not make connections while INTEGRA is turned on or power is applied at any point in the system We recommend that all wire you use also meets 22 AWG Mil Standard MIL W 22759 16 with the exception of the thermocouple harnesses When using any pre manufactured harness verify that each pin has continuity with the expected wire on the wiring diagram This test can be easily done with a multimeter When verifying harnesses Use the wiring charts and diagrams in this guide Use appropriate strain relief at all junctions between wires and connectors We recommend that you secure all wires at regular intervals along wiring runs to accommodate vibration effects 4 6 Harness Mating The following diagram shows the connectors on the back of the INTEGRA The
26. pulse 10 to 32 Volts if positive pulse is applied the output encoding data is enable Strobe signal from the transponder Altitude encoded Range Resolution 500 m to 9750 m 1013 25 mbar 1m Altitude amp Encoder 1600 to 32000 feet Airspeed Range Resolution Aap sued 20 to 350 km h 5 km 10 8 knots to 189 knots P 2 7 knots Absolute maximum speed 500 km h 270 knots Audio Input Output 0 2 to 2 Volts typ 0 5 V 1kHz input Transceiver input line impedance 600 Voice warning output line typ 300 mV 1kHz output impedance 600 Q Audio output line typ 300 mV 1kHz output impedance 600 RPM and Engine Hours for future use Range Resolution RPM 0 to 9999 rpm 1 or 10 rpm to 9999 hours I min to 99 hours and 1 10 hour from 100 hours 2 seconds 1 hour to 9999 hours 1min to 99 hours and 1 10 hour from 100 hours 2 seconds 1 hour Engine time Flight time Installation manual Page 3 2 Rev E TL 6524 EFIS INTEGRA Sensor parameters Instrument Measured Range Accuracy Low RPM Voltage for future use 6 to 50 300 to 9999 rpm 1 rpm High RPM Voltage for future use 25 to 80 300 to 9999 rpm 1 rpm 6 to 60 VDC 300 to 9999 rpm 1 rpm can Positive RPM Only for future use be use VAC AUX future use Input parameter Positive pulse 8 to 32 Volts Type of Switch Inductive sensor of
27. t headphones or IC Transceiver Phone Altitude output A1 Altitude output A2 Altitude output A4 Altitude output B1 Altitude output B2 2 s ja N ja External Signalization Aircraft GND External Back Up battery 10 to 32 V N A iFamily CANL Ground for audio out gt ja An On ja ja oo ja Ground for transceiver phone Altitude output B4 Altitude output C1 Altitude output C2 Altitude output C4 Strobe signal Ground Strobe signal is function of the transponder which use strobe signals to enable and disable the encoder N N N N N EN N notation of pins D SUB 25 connector Installation manual Page 6 1 Rev E Tenueur 5 7 9 e MAIN SWITCH EXTERNAL SIGNALIZATION 10 32V AIRCRAFT POWER AICRAFT GROUND WARNING RECORDING AUDIO SIGNAL GROUND FOR WARN REC AUDIO SIGNAL LEFT AUDIO OUT RIGHT AUDIO OUT GROUND FOR AUDIO OUT IFAMILY BUS1 CANH IFAMILY BUS1 CANL EXTERNAL BACK UP BATTERY INTEGRA P1 13 15 warning unit Lamp Buzzer TRANCEIVER PHONE HI TRANSCEIVER PHONE LO AUX AUDIO IN LEFT AUX AUDIO IN RIGHT H lt
28. taller agree to hold TL elektronic Inc in no way responsible for monetary compensation including punitive damages for any incident harm and or damage associated with this product If you do not agree to the above DO NOT INSTALL THIS PRODUCT This product may be returned for a refund Contact TL elektronic Inc for details TL elektronic Inc is not liable or responsible for a pilot s action or any situation that results in personal injury property damage missed commitments lack of use of an aircraft or any expenses incurred due to product failure inaccuracy in displayed data or text files display or display format issues software bugs or problems upgrade or customization issues misinterpretation of the display warning and or limit settings calibration problems installation issues leaks incorrect wiring obstructions damage to aircraft or components incorrect installation of any parts wrong parts parts that don t fit etc or any other issues related to the installation or operation of this product of the above are solely the pilot s and or installer s responsibility The pilot must understand the operation of this product before flying the aircraft The pilot will not allow anyone to operate the aircraft that does not know the operation of this product The pilot will keep the instrument Operating Instructions in the aircraft at all times Do not install a non certified INTEGRA in a certified aircraft Before starting t
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