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1. FEMALE 1 8 NPTF 2 Je PINOUT 1e 28v DC POWER INPUT NC RX RS 422 RX RS 422 RX RS 232 TX RS 232 TX ARINC429 A TX ARINC429 B GROUND J3 PINOUT NC NC NC NC NC NC NC NC NC Ji PINOUT FUEL FLOW RIGHT lt gt 1 2 3 4 5 6 7 8 9 FUEL FLOW RIGHT gt GROUND HEADING Y HEADING X 26V 400Hz H 26V 400Hz Z BARD WIPER FUEL FLOW LEFT lt gt FUEL FLOW LEFT GROUND lt gt OAT DAT Signal 5 V 0501 03e D 3 21 05 wMP UPDATED TITLE BLOCK CH TITLE CORR PITOT STC LABEL LOCNS 19706 017 C 6997 WMP KCL UPDATE J3 9505 028 5 17 95 DAP SES REVERSE FF POLARITY 19505 014 A 5 11 95 WMP SES ADD SPRING LATCH CLIPS 9412 005 12 7 94 DAP SES BASELINE RELEASE REV D DESCRIPTION z GROVES DO NOT SCALE DRAWING SHEET NC TX RS 422 TX RS 422 NC SIGNAL GND NC USE RS 232 OR RS 422 NOT BOTH SHADIN 1 55426 INSTALLATION DWG ADC2000 SINE FUEL FLOW DRAWING NO 4028 431 DRAFTER DAP APPROVED SES FILE NAME 962830 2DJ DWG DIRECTORY 962830 1 OF 1 ALONE 5 0 Q NC NC NC NC NC NC A P N 962830 2 MATING CONNECTORS PL 230051 CONN SHELL MALE 230054
2. 7 8 DO NOT USE 9 Type 9 DO NOT USE IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev J P N 962830 1 962830 2 962830 3 Page 9 13 ALTIMETER TYPES Type 1 Kollsman PD 44929 935 done for Cessna 525 Type 2 Bendix King KEA 130A and KEA 346 versions King P N 066 3062 XX XX 08 through 11 versions 00 though 07 have no Baro Potentiometer Type 3 ARINC 575 3 specification for ratio to Altitude Correction calculation Kollsman IDC 28007 427 429 Kollsman IDC 28704 A1001 A2001 A4001 B4001 C4001 D1001 D2001 D4001 D4101 4E2101 F2101 and 495 Type 4 Kollsman IDC 28711 621 thru 624 Type 5 Kollsman IDC 28007 431 433 Honeywell Sperry BA 141 Type 6 Kollsman IDC 28711 500 series and 600 series Type 7 Kollsman IDC 28711 065 and 066 Type 8 Reserved for future use DO NOT USE Type 9 Aerosonic P N 10420 11968E IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev J P N 962830 1 962830 2 962830 3 Stage 2 Loopback configuration Switch 1 is set to 2 to indicate that the stage 2 loopback is being performed SWITCH 2 Fuel Filter Type 0 Injector 1 Carburetor Page 9 14 SWITCH 3 AND SWITCH 4 CORRECTION For SSEC PSEC Select F ADC Software Version ex OO O COC Oo oO COCO oO Co oO oO oO CC D OO
3. MET TO AERUSFATIALE DAUPHIN 0501 032 A 2 14 05 UPDATED TITLE BLOCK mm DWG GENE er SS O 4028 949 n ECO DATE APP D DESCRIPTIUN SCALE tr DT 4028 949 F ADC 200 P N 962810 2 P N 962820 2 RIGHT ENGINE FUEL FLOW P160 F ADC 2000 TRANSMITTER 41 P N 962830 2 SIG RIGHT SIG ENGINE GROUND FUEL FLOW 161 LEFT ENGINE FUEL FLOW TRANSMITTER 516 LEFT ENGINE SIG FUEL FLOW NOTES 1 FOR AIRCRAFT WITH FAURE HERMAN FUEL FLOW TRANSMITTERS PART 25 512 231 1 2 CONFIGURE THE F ADC FOR THE ALTERNATE DIGITAL K FACTOR TABLE MATRIX 1 K FACTOR IS 194 1 940 PPO SET AIRDATA SWITCHES TD SW1 8 SWe 0 SW3 8 SW4 0 APPROVED INSTALLATION WIRING F ADC 200 2000 SHADIN m 55426 FILE NAME 0501 032 A 2 14 05 UPDATED TITLE BLOCK 4088 950AJ DWG 9803 041 3 86 98 SRB KCL BASELINE RELEASE DIRECTORY DRAWING PN F ECO 8 DATE BY lAPPD DESCRIPTION SCALE s er idri 4028 950 AEROSPATIALE AS332 SUPER PUMA F ADC 200 P N 962810 3 P N 962820 3 F ADC 2000 F ADC 2000 P N 962830A 3 P N 962830 3 962830 3 5 4 A DIGIDATA Jt P N 962830 3 S 5 Ji P N 962830 3 5 1 P N 912802 03 GROUND 11 GROUND RIGHT ENGINE FF INDICATOR FUEL AN v FLOW 2 124 SIGNAL RIGHT ENGINE 143 SIGNAL 7
4. Temp Sensor 4005 266 30 670505 1 WASHER Flat OAT 4005 303 35 670506 1 WASHER Shoulder OAT 4005 304 40 681201 1 4005 794 45 IM1201 1 Installation Manual 681201 1 SHA 50 PK1002 1 BAG 3 x 4 4 MIL Zip Lock 55 PK1009 1 BAG 6 x 12 4 MIL 60 753217 1 COMPUTER LABEL 3 5x15 16 AVR 4013 14 items Report N A Date January 17 2005 Rev A Sec Ix Page of 1 Drawing s N A FN PIN QTY 20 12300 9H 1 6 40 5102 6 4 5207 6 350 401 6 1 PK109 1 DESCRIPTION TRAY Mounting ADC 2000 MOUNTING TRAY ASSEMBLY SPRING LATCH CLIP CONN 15Pin D Sub F Crimp w Contacts CONN 15 Pin D Sub M Crimp w Contacts CONN Hood 15 Pin D Sub SCREW 4 40 x 14 L Phil Pan HD SS NUT 4 40 3 16 x 1 16 SS WASHER 4 Split Lock SS COMPUTER LABEL 3 x 15 16 BAG 2 5 x 3 4 MIL Zip Lock BAG 6 x 12 4 MIL 34 items SHA SHA SHA TTI TTI CIN MCM AFT MCM AVR PARTS LIST MFG 4028 T54 4028 437 4028 074 M24308 2 2 M24308 4 2 DA 24658 91772A106 HNSP188 04C000 92147A005 4013 DESIGNATION Shadin Filename DIRECTORY IK96301AP doc IKXXXX ECO 0501 032 Release date 3 21 05 Approved WMP Part IK9630 1 Description INSTALL KIT ADC2000 COMMENTS PART NUMBER PART NUMBER PART NUMBER PART NUMBER PART NUMBER A
5. 0501 006 C 1 17 05 PAB ZK 0211 047 B 2 7 03 PAB BAL 0009 006 9 6 00 PAB 9803 025 3 26 98 SRB KCL ECO 8 962810 X 962820 X 962830 X DIDI ADDED CNX 80 DEL PIN 9 ADDED GND GARMIN 430 530 ADD GARMIN 430 530 GPS BASELINE RELEASE DESCRIPTION BENDIX KING KLN90 KLN90B GARMIN 150 155 155XL 165 250 250XL 300 300XL FOSTER IIMORROW IIMDRRDW IIMORROV IIMORROW ARNAV MAGELLAN NMS2001 820 FMS7000 SKYNAV Gx 55 R5000 STARS000 360 TX TX SOFTWARE SELECT 19 37 SA DIM 55426 FE INSTALLATION WIRING F ADC 200 2000 PAB ere NAPE TO NAV RECEIVERS W RS 232 4028 943CJ DWG DIRECTORY DRAWING NO 4028 943 P N F ADC 200 P N 962810 2 P N 962820 2 RIGHT ENGINE FUEL FLOW F ADC 2000 TRANSMITTER P N 962830 2 SIG RIGHT SIG ENGINE GROUND FUEL FLOW LEFT ENGINE FUEL FLOW TRANSMITTER LEFT SIG ENGINE SIG FUEL FLOW NOTES 1 FOR AIRCRAFT WITH FAURE HERMAN FUEL FLOW TRANSMITTERS PART 25 1024 118 2 CONFIGURE THE F ADC FOR THE ALTERNATE DIGITAL K FACTOR TABLE MATRIX 1 K FACTOR IS 3 88 3 880 SET AIRDATA SWITCHES AS FOLLOWS SW1 0 SWe 7 SW3 0 SW4 7 SAADIN MINNEAPOLIS 55426 INSTALLATION WIRING F ADC 200 2000
6. 49300 9 40400 9 49700 50000 50200 50400 50600 50800 55500 55550 57000 57100 57200 57300 57400 57500 57600 Table 2 continued IM2830LG doc DIR 962830 IM2830 Shadin Rev G INSTALLATION MANUAL P N 962830 1 962830 2 962830 3 FUEL AIRDATA COMPUTER Page 10 6 Matrix 1 Alternate Digital K Factor Setting Table software version 93 00 61 elo ojo a gt ON m QN 4 I PPG 200 400 490 530 540 600 660 60 800 850 880 900 1000 1200 1400 1600 1800 Table 3 N IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 SECTION 11 0 INSTALLATION DRAWINGS AND INSTALL KIT PARTS LISTS J1 PINOUT FUEL FLOW RIGHT POWER FUEL FLOW RIGHT SIGNAL GROUND HEADING HEADING X 26V 400Hz H 26V 400Hz Z C BARD WIPER FUEL FLOW LEFT POWER FUEL FLOW LEFT SIGNAL GROUND lt gt OAT Signal 5 2 05017032 3 21 05 UPDATED TITLE BL
7. Configuration 2 sends all labels at a 50 msec rate for Flight Visions HUD T Configuration 8 sends all labels at a 100 msec rate for Collins FMS 800 Configuration 9 sends all labels at a 50 msec rate for GPWS Configuration A sends all labels at a 50 msec rate for Mk VI and EGPWS available w ARINC software version 71 73 01 and above Only IM2830LG doc DIR 962830 IM2830 Shadin Rev J INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 2 5 2 5 4 ARINC 429 Labels Associated with Switch Settings 0 Honeywell SPZ 5000 for Cessna 5 ASINC Airshow Cabin Display 1 Bendix KLN90B or Global 6 Trimble 8100 No label 275 GNSXC LS 7 TNL 8100 2 HUD Heads Up Display for Flt 8 Collins FMS 800 100 ms rate Visions 9 Mk VII GPWS 50 ms rate 3 A Mk VI amp VIII 50 mSec rate 4 EFIS40 50 Note that 3 and 6 are the same except for label 275 The following is a list of the different switch settings that the ARINC switch may be set to The ARINC switch position is shown in section 9 2 0 1 Long Range Nav function of Honeywell SPZ 5000 Flight Guidance EFIS System installed on the Cessna Citation Jet Aircraft Bendix to Global Cabin Info System installed on the Cessna Citation Jet Aircraft Reserved 8100 UNSI Bendix King EFIS 40 50 ASINC Airshow 8100 UNS1 except no label 275 Use when there is no serial navigation data being rece
8. be selected Read the following paragraphs for a description of these special circumstances On a few aircraft installations which have digital fuel flow and use a very low K factor 858 pulses per gallon there has been a problem with the Airdata reporting a large jump in fuel used as well as a corresponding decrease in fuel remaining at engine startup This is not considered to be a Shadin Airdata problem but rather has been defined as an aircraft problem involving noise on the digital fuel flow signal A solution for this problem is to use the Airdata fuel flow delay feature This feature suppresses the fuel flow and its affect on fuel used and remaining for a startup delay time each time the engine starts Fuel flow delay time is selectable in the Airdata loopback mode with selections of 0 5 10 15 20 25 30 35 40 and 45 seconds delay available If a fuel flow delay is needed start by reconfiguring the ADC to use a large delay i e 45 seconds If the large fuel flow mitigated the problem try reducing the delay until the problem returns Then use the least amount of fuel flow delay that suppresses the problem When a fuel flow delay time is selected the Airdata checks for fuel flow below 15 pph If the fuel flow is below 15 pph the Airdata considers the engine to be off and returns a fuel flow of 0 Then as soon as the fuel flow exceeds 15 pph the Airdata continues to return a fuel flow of 0 until the delay time has expire
9. factor for fuel flow transducers or aircraft model for DC fuel flow sensors Refer to Table 1 analog for fuel flow and Table 2 or Table 3 for digital fuel flow 2 Refer to the specific Navigational Receiver Operator Manuals for the serial port set up IM2830LG doc DIR 962830 1 2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev H P N 962830 1 962830 2 962830 3 Page 8 1 8 0 MAJOR COMPONENTS OF THE SYSTEM 1 Nav Receiver Input Output 2 Fuel AirData Computer 3 Outside Air Temperature Probe Shadin P N 681201 IM2830LG doc DIR 962830 1 2830 Shadin Rev J 9 0 9 1 INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 9 1 CONFIGURING THE AIRDATA Part number 962830 X X or 2 or 3 AirData Computer needs to be configured to program it for the particular installation The procedure contained in this Installation Manual is for software versions 93 00 16 to 93 00 29 93 00 51 to 93 00 71 93 00 77 and 93 00 82 and above There are two methods to accomplish this task The first method is to follow the procedures as set forth in the ADSETUPF User Manual The second method is to manually enter the information by performing a Loop Back procedure Configuring with ADSETUPF User Manual The ADSETUPF User Manual is a configuration utility that allows setting the ADC configuration by running a program on a PC The PC is connected to the unit via the serial
10. E UT EE W C C 4 Piper 1 Piper l LearJet 7 Learlet Model 36 5V 0 2 Learet Model36 10V 0 8 0 Boeing Boeimg 737 300 0 9 0 3 British Aero BAEATP 0 7 0 0 15380 British Aero BAE 125 800 0 A 0 0 British Aero HS 125 0 B 0 o 10490 Canadian 1600 0 F 0 0 Canadian Dornier EM Daussault 9 Daussault 0 Daussault 7600 Sweamgen MERLIN 0 0 38460 Gulfstream 2880 1 Len 1 1 4 D 9 1 4650 0 Gulfstream GULFSTREAM 2310 HI Aerospatiale 1 DHC DHC DASH8 1 IAI 7 2188 AL WESTWIND 1124 1 8 0 Sikosky S 76A 1 1 o o 46150 Sikorsky S 7B 0 6 o o 28850 Sabre SABRE6S 1 7 o 5 9230 2188 Table 1 IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev G P N 962830 1 962830 2 962830 3 Matrix 0 Digital K Factor Settings PPG SWI SW2 PPG SWI SW2 PPG SWI Page 10 3 SW2 86 0 8800 5000 5050 5100 5150 5200 5250 9200 9400 9600 9800 10000 10100 10200 10300 10400 10500 10600 10700 10800 10900 11000 11100 11200 11300 11400 11500 14500 14600 14700 14800 14900 15000 15100 15200 C F PPG 860 5000 5050 5100 5150 5200
11. pu Joar J Jol T T j 212 VenicalSpeedivs 213 TAT Static Jof fof lof 234 Baro Correction mo fof j L I j 235 Correction 244 TotalFuelFlow 251 Distance ToGo 0 fol j J 22 TimeToGo 25 4 0120 J 300 Navigation Aid Info 0 lofo 50 Waypoint Group Header 0 fofo j 304 Message ID Characters 13 OT lofo j 305 MessageIDCharacters4 6 O fofo j j 56 WaypointLatimde 0 lofo 307 Waypoint Longitude 0 fofo j j j j 310 Present Latitude 0 1 Present Longitude 0 1 01 j J j 312 Ground Speed 0 83 meTak j meHaing 1010 35 WindSpeed 1 0 fofo of ol 316 WindDirection 1 30 MagneticHeading 0 fol j DriftAmgle Tme olo ToT 47 Lef RightFuelFlow______ OJO j 31 Distanceto Final Destination JOT 32 Time to Final Destination L L L L IL L l l l
12. 5250 5650 6400 6420 6440 6460 6480 6500 6520 6540 6560 6580 6660 7640 50 5 ESE a E Bx px D 6 ESS e e HER ET D 281 un Table 2 gs IM2830LG doc DIR 962830 1 2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev G P N 962830 1 962830 2 962830 3 Page 10 4 Matrix 0 Digital K Factor Settings Continued 25800 4 D 29800 F B 40000 9 4 4000 9 5 30200 F 40400 9 6 24400 B A 9 EA 240 B 33800 6 9 40300 9 24800 B C jJ 37000 B 9 41000 9 E 2500 37200 B 8 41200 9 F 25200 BTS 77 21 1 02 25400 j 37600 B 6 41600 1 2560 C 37800 B 5 41800 1 2 25800 C 1 38000 8 0 42000 1 3 26000 C 2 3810 8 1 42200 1 4 26200 C 4 38200 8 2 42400 1 5 sim i m 2660 C 6 38400 8 4 42800 1 7 26800 C 7 3850 8 5 43000 1 8 2700 C 8 38600 8 6 43200 1 9 27200 9 38700 8 7 38800 8 8 400 1 27600 0 38900 8 9 45800 39000 8 4000 ft Lb 3940 8 E 288
13. Bendix D Bendix King and F ADC with Baro Interface Shadin S IIMorrow GX50 55 60 Bendix B fuel only Do Not Use I ON EU D 1 SWITC an Altimeter Selection for Baro DC Input None Type 1 Type 2 Type 3 4 Type 5 Type 6 Type7 DO NOT USE Type 9 DONOT USE gt D O 1 IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev J P N 962830 1 962830 2 962830 3 Page 9 8 ALTIMETER TYPES Type 1 Kollsman PD 44929 935 done for Cessna 525 Type 2 Bendix King KEA 130A and KEA 346 versions King P N 066 3062 XX XX 08 through 11 versions 00 though 07 have no Baro Potentiometer Type 3 ARINC 575 3 specification for ratio to Altitude Correction calculation Kollsman IDC 28007 427 429 Kollsman IDC 28704 A1001 A2001 A4001 B4001 C4001 D1001 D2001 D4001 D4101 4E2101 F2101 and 495 Type 4 Kollsman IDC 28711 621 thru 624 Type 5 Kollsman IDC 28007 431 433 Honeywell Sperry BA 141 Type 6 Kollsman IDC 28711 500 series and 600 series Type 7 Kollsman IDC 28711 065 and 066 Type 8 Reserved for future use DO NOT USE Type 9 Aerosonic P N 10420 11968E IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev J P N 962830 1 962830 2 962830 3 Stage 2 Loopback configuration Switch 1 is set to
14. Falcon 20 C D E LearJet 25D Douglas DC 8 Beechjet 400 Boeing 707 321B Cessna Citation S550 Falcon 10 Falcon 50 Raytheon Hawker HS125 700A LearJet 35 LearJet 55 Sabreliner 60 SSEC Only Lockheed Jetstar Reserved for future DO NOT USE ALL 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 58 93 00 63 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev J P N 962830 1 962830 2 962830 3 Page 9 20 Stage 3 Loopback configuration Switch 1 is set to 3 to indicate that the stage 3 loopback is being performed SWITCH 2 K FACTOR TABLE SELECTION For F ADC 962830 1 and 962830 2 only 0 Standard K FACTOR Matrix 0 Table 2 in this manual 1 Alternate K FACTOR Matrix 1 Table 3 in this manual 2 DO NOT USE SWITCH 3 FUEL FLOW DELAY TIME No Delay 5 Second Delay 10 Second Delay 15 Second Delay 20 Second Delay 25 Second Delay 30 Second Delay 35 Second Delay 40 Second Delay 45 Second Delay DO NOT USE
15. Listed below are the navigational systems that the ADC 2000 has been designed to be compatible with Receives Serial Data from Magellan Skynav 5000 ARNAV Trimble Bendix King STAR 5000 2000 2000A KLN90 FMS 7000 2100 3000 KLN90A R5000 3100 2101 KLN90B KLN89 89B Garmin BFGoodrich IIMorrow 150 155 155XL 165 Pronav LNS 6000 611 612 618 230 230XL NMS 2001 300 300XL 800 820 360 430 530 GX50 55 60 Transmits Serial Data to ARNAV Magellan Note To find out which particular receiver Bendix King Trimble models have Airdata receive capability contact Garmin the manufacturers Transmits ARINC Data to ASINC Bendix King Honeywell Universal Airshow EFIS 40 50 SPZ 5000 UNS 1M Data Nav III Global Trimble IIMorrow Garmin GNSX TNL8100 2101 430 530 GNS XIs IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev H P N 962830 1 962830 2 962830 3 Page 1 2 13 System Configuration The Fuel AirData system is a remote mounted box which is connected to the GPS receiver via serial data and standard ARINC 429 output It is also connected to the pitot and static line OAT probe fuel flow sensors and the aircraft heading source In addition optional barometric information my be received from the aircraft altimeter 1f available PITOT STATIC NAV OAT RECEIVER MAG HEADING FUEL AIRDATA COMPUTER L ENGINE F F STANDARD ARINC 429 R ENGINE F F OUTPUT TO EFIS FLIGHT
16. MANAGEMENT SYSTEM BARO POT Optional SYSTEM CONFIGURATION IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev H P N 962830 1 962830 2 962830 3 Page 1 3 1 4 Fuel Totalizer Configuration Shown below is an optional system configuration utilizing a Shadin Fuel Flow Indicator Note that the only navigational receiver supported in this configuration are the Bendix King KLN and Garmin 430 530 series Consult Drawing Number 4028 947 contained in this manual for installation information for the Bendix King KLN series Consult Drawing Number 4028 B94 for installation information for the Garmin 430 530 Bendix King Shadin B n L Fuel Flow Transmitter KLN900 MicroFlo R Fuel Flow Transmitter Shadin F ADC200 F ADC2000 1 5 F ADC2000 Argus Moving Map Configurations Shown below is the system configuration that supports output to a Eventide Argus moving map using the Shadin serial to serial data converter P N 937000 03 The fuel and airdata are displayed on the Eventide Argus moving map Consult Drawing numbers 4070 005 and 4028 948 contained in section 11 Shadin RS 232 or RS422 20 Shadin Eventide Navigational Argus Receiver Converter RS 232 or RS422 P N 937000 03 Moving Map F ADC2000 P N 5000 P N 7000 IM2830LG doc DIR 962830 IM2830 Shadin Rev J 2 0 2 1 2 2 2 3 2 4 INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1
17. Management System pages Select heading page Slew compass through 360 The error should be within 1 Select the OAT page Compare to the reported ambient temperature The error should be within 2 C Run the engines and select the fuel flow page Compare the fuel flow readout with the engine manufacturer s fuel flow charts under the ambient temperature and pressure conditions Set the Barometric pressure to a known value and verify that the reported barometric pressure at the Navigational Receiver is that value 0 01 In Hg if the option is installed IM2830LG doc DIR 962830 1 2830 Shadin Rev F INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 6 1 6 0 OPERATING INSTRUCTIONS I 2 Power the avionics DC bus and the Navigation Management System After the warm up period density altitude and PALT are available IAS will be available but will be out of range until actual airspeed is available Winds aloft will be available if IAS gt 40 knots and magnetic heading is within 40 of magnetic track Fuel Flow Fuel Used Fuel Remaining Heading and OAT will be available after power up Refer to the specific Nav Receiver Operator s Manual for page selection of various data IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev F P N 962830 1 962830 2 962830 3 Page 7 1 7 0 INITIALIZATION 1 The system requires initialization of
18. SIGNAL qo c 13 R SIGNAL LEFT ENGINE FF INDICATOR ENGINE FUEL es FLOW SIGNAL 14 L SIGNAL SIGNAL 15 1 SIGNAL RAGEN P N 3265013 0601 FLOW SIGNAL FROM FLOWMETER FLOW SIGNAL TO TOTALIZER INTERNAL TEST POINT 28 VDC INPUT REF SUPPLY TO TOTALIZER REF SUPPLY TO FLOWMETER 28 VDC RETURN INTERNAL TEST POINT SIGNAL RETURN TO TOTALIZER RAGEN P N 3265013 0801 FLOW SIGNAL FROM FLOWMETER FLOW SIGNAL TO TOTALIZER ALT FLOW SIGNAL TO TOTALIZER 28 VDC INPUT REF SUPPLY TO TOTALIZER REF SUPPLY TO FLOWMETER 28 VDC RETURN SIGNAL RETURN FROM FLOWMETER SIGNAL RETURN TO TOTALIZER SIGNAL RETURN FROM FLOWMETER FLOW SIGNAL FROM FLOWMETER ALT FLOW SIGNAL TO TOTALIZER RAGEN P N 3265013 1201 FLOW SIGNAL TO TOTALIZER 28 VDC INPUT REF SUPPLY TO TOTALIZER REF SUPPLY TO FLOWMETER 28 VDC RETURN SIGNAL RETURN TO TOTALIZER ATV Po Mmeam CASE GROUND CASE GROUND CASE GROUND NOTES FOR AIRCRAFT WITH THE FOLLOWING INDICATOR TRANSMITTERS SEE TABLE FOR INDICATOR WIRING INDICATOR PART CRAGEN 3265013 0601 w TRANSMITTER PART ND RAGEN gt 3268011 0101 INDICATOR PART RAGEN 3265013 0801 3265013 1201 w TRANSMITTER PART CRAGEN TFF 2905 9 OR PIPER P N 489 487 A SET AIRDATA SWITCHES AS FOLLOWS 5 1 1 SWe 1 SW3 0 SW4 0 A PROGRAM DIGIDATA FOR LEFT K
19. gt Loan D 1 n SWITCH4 SPECIAL OPTION DESCRIPTION F ADC Software Version 0 ARINC 429 labels 206 IAS and 210 TAS are not 93 00 67 and up transmitted if the IAS lt 20 knots 1 ARINC 429 labels 206 IAS and 210 TAS are transmitted 93 00 67 and up as zero knots if the IAS lt 20 knots 2 F Reserved DO NOT USE IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev J P N 962830 1 962830 2 962830 3 Page 9 21 Stage 4 Loopback configuration Switch 1 is set to 4 to indicate that the stage 4 loopback 15 being performed Refer to the OAT probe calibration certificate for the Ta Tb Tc calibration code selection SWITCH 2 OAT Ta CALIBRATION CODE SELECTION 0 Refer to calibration certificate for A code selection O to SWITCH 3 OAT Tb CALIBRATION CODE SELECTION 0 Refer to calibration certificate for code selection O to SWITCH 4 OAT Tc CALIBRATION CODE SELECTION 0 Refer to calibration certificate for code selection O to Note Switch 2 3 and 4 are set to position 0 zero if the OAT probe does not have a calibration code marking i e A 0 0 0 IM2830LG doc DIR 962830 IM2830 Shadin Rev J INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 9 22 SELECT NO DELAY Only under special circumstances should a fuel flow delay time other than No Delay
20. 1 Table 3 in this manual 2 DO NOT USE SWITCH 3 FUEL FLOW DELAY TIME No Delay 5 Second Delay 10 Second Delay 15 Second Delay 20 Second Delay 25 Second Delay 30 Second Delay 35 Second Delay 40 Second Delay 45 Second Delay DO NOT USE gt Loan D 1 n SWITCH4 SPECIAL OPTION DESCRIPTION F ADC Software Version 0 ARINC 429 labels 206 IAS and 210 TAS are not 93 00 67 and up transmitted if the IAS lt 20 knots 1 ARINC 429 labels 206 IAS and 210 TAS are transmitted 93 00 67 and up as zero knots if the IAS lt 20 knots 2 F Reserved DO NOT USE IM2830LG doc DIR 962830 IM2830 Shadin Rev J INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Loopback Procedure 4 for Software Version 93 00 82 Stage 0 Loopback Configuration Switch 1 is set to 0 to indicate that the stage 0 loopback is being performed SWITCH 2 m gt Q Q D SWITCH 4 0 1 2 3 F Fuel Units and Engine Type Gallons Single Engine Liters 4 Lbs 5 8 Lbs 6 71 i Kilograms Lbs 6 5 A 5 Lbs 6 3 2 not used 4 Gallons Twin Engine Liters Lbs 5 8 Lbs 6 71 5 Kilograms Lbs 6 5 i Lbs 6 3 d DO NOT USE 9600 BAUD Loran Input Type Trimble ARNAV Bendix or IIMorrow Apollo NMS2001 800 820 Garmin Northstar Foster IIMorrow 611 612 and 618 Shadin Flow Meter DO NOT US
21. 103 CHANNELS YG1761B 962830 X Je WHITE WHITE BLUE BLUE TX 7 WIRE WIRE ARINC429 A WHITE WIRE ARINC429 B NOTES ZN FOR THE B 8 D CABIN DISPLAY THE ARINC 429 LABELS RECEIVED ARE DEPENDANT UPON THE WAY THE B amp D WAS BUILT NOT SHADIN ALSO THE P N OF THE B 8 D INDICATES IF IT IS SET UP FOR RECEIVE A OR RECEIVE B FOR EXAMPLE P N 2700 X XX YY ZZ X XXXXX IF YY THEN REC IF ZZ THEN REC B 2 THERE MAY BE OTHER TYPES OF EQUIPMENT THAT WILL USE ARINC 429 LABELS SHADIN meros 55426 INSTALLATION WIRING ADC2000 TO NAV RECEIVERS ARINC 429 ILE NAME 02117047 A 3 11 03 ADDED NOTE 2 SHIELD amp GND DEL F amp 200 FROM TITLE 98037025 3 26 98 SRB KCL BASELINE RELEASE 4028 028 9 45 P N ECO amp REV DATE BY APP D DESCRIPTION NOT TO SCALE SHEET 11 4 APPROVED KCL TRIMBLE TRIMBLE NORTHSTAR 1000 MIA 2000 M2 962810 M3 962820 X gt X 3000 962830 X RS 422 TX SDA RX SDB RX SDB 8 TX SDA TX SDA TX SDA 37 11 TX SDB TX SDB 5 6 SHADLN 55426 INSTALLATION WIRING F ADC200 2000 TO NAV RECEIVERS W RS 422 RS 485 FILE NAME 0211 047 3 11 03 DEL 9 ADDED GND pa MA 98037025 3 26 98 SRB KCL BASELINE RELEASE 4028 028 9 46 P N ECO DATE BY APP D DESCRIPTION NOT TO SCALE SHEET
22. 962830 2 962830 3 FUEL AND AIRDATA SYSTEM SPECIFICATIONS Input Data Range Pitot 20 to 350 kts Static 1000 to 55 000 ft OAT 60 C to 60 C Heading 0 360 Fuel Flow 1 to 450 GPH Range Selected K Factor 500 to 130000 PPG Continuous Output Data Range PARAMETER Accuracy RANGE IAS 1 kts 20 to 350 kts P ALT 25 ft 1000 to 5000 ft P ALT 30 ft 5000 to 11000 ft P ALT 40 ft 11000 to 30000 ft P ALT 100 ft 30000 to 55000 ft OAT 2 C 60 to 60 C HEADING 1 0 360 degrees IVS 40 ft min 10 000 ft min TAS 2 kts 20 600 kts MACH 01 2 95 WIND SPEED 1 kts 5 360 kts WIND DIRECTION 5 0 360 degrees FUEL FLOW 2 1 450 Dimensions including mounting rack Size 7 4 L x 4 3 Hx 3 9 W Weight 36 oz Power Requirements System Power required 28 VDC 1300 mA 14 VDC 900 mA Page 2 1 IM2830LG doc DIR 962830 IM2830 Shadin Rev J 2 5 2 5 1 2 5 2 INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 2 2 Output Data 1 Electric Format RS 422 or RS 232 2 ARINC 429 low high speed GAMA Has to be configured at the factory See paragraph 2 5 3 for ARINC 429 output data capabilities Serial Output Data Parameters Fuel Group AirData Group Left Fuel Flow Aircraft Type Density Altitude Right Fuel Flow MACH Number Drift Angle Fuel Used Total True Air Speed TAS Magnetic Heading Total Fuel Used
23. KNOWN TO SHADIN ADC200 2000 SWITCH SETTINGS PART NUMBER K FACTOR OFFSET AUX RATE OUTPUT SW 542 505 544 900 1 0600 1 38 460 0 0 5 VDC 0 4 0 0 PC900 1A0750 XX1 30 770 0 0 5 VDC 0 5 0 0 900 1 0800 1 28 850 0 0 5 VDC 0 6 0 0 THE FOLLOWING BEECH INDICATOR P NS POSSESS A KNOWN SHADIN ADC200 2000 SWITCH SETTINGS PART NUMBER K FACTOR OFFSET SW SW2 SW SW4 90 380009 2 77 000 416 0 0 0 1 90 380009 5 77 000 416 0 0 0 1 101 384153 1 30 777 0 0 5 0 0 101 384153 3 30 777 0 0 5 0 0 ZA THE J1 CONNECTOR OF THE ADC 200 AND ADC 2000 HAVE THE SAME FUEL FLOW PIN LOCATIONS 6 USE SHIELDED WIRE BUT GROUND ONLY ON ADC UNIT END TO PREVENT A GROUND LOOP SHADIN MINNEAPOLIS MN 55426 OPA INSTALLATION WIRING F ADC 200 2000 W ANALOG F F TO BEECH KING AIR INDICATORS 0211 047 eas Gee Te 00000000 D SUB CONNECTOR 9803 022 3 26 98 SRB KCL CHANGED NOTE 3 90 380009 5 FRO 26 150 416 REMOVE P N 9628X0 3 DWG 9706 007 6 13 97 BASELINE RELEASE 4028 818 P N ECO 4 APP D DESCRIPTION SCALE NONE sx o 4028 818 NOTES A FROM RIGHT ENGINE FF TRANSMITTER A FROM LEFT ENGINE FF TRANSMITTER BN F ADC SWITCH SETTINGS AIRCRAFT S FUEL FLOW SIGNAL CONDITIONER P N 45 86801 003 gt SHLD GND FLOW SIGNAL IN FLOW SIGNAL IN TEMP SIGNAL IN TEMP SIGNAL IN FLOW METER FLOW METER 25V DC IN POWER GND POWER GN
24. King KEA 130A and KEA 346 versions King P N 066 3062 XX XX 08 through 11 versions 00 though 07 have no Baro Potentiometer ARINC 575 3 specification for ratio to Altitude Correction calculation Kollsman IDC 28007 427 429 Kollsman IDC 28704 1001 A2001 A4001 4001 C4001 D1001 D2001 D4001 D4101 4E2101 F2101 and 495 Kollsman IDC 28711 621 thru 624 Kollsman IDC 28007 431 433 Honeywell Sperry BA 141 Kollsman IDC 28711 500 series and 600 series Kollsman IDC 28711 065 and 066 Reserved for future use DO NOT USE Aerosonic P N 10420 11968E Reserved for future use DO NOT USE IDC P N KTS B45152 10 410 IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev J P N 962830 1 962830 2 962830 3 Stage 2 Loopback configuration Switch 1 is set to 2 to indicate that the stage 2 loopback is being performed SWITCH 2 Fuel Filter Type 0 Injector 1 Carburetor Page 9 19 SWITCH 3 AND SWITCH 4 CORRECTION For SSEC PSEC Select F ADC Software Version ex OO O COC Oo oO COCO oO Co oO oO oO CC D OO Z gt oo amp D No correction MITSUBISHI MU 300 CESSNA CITATION 500 501 CESSNA 525 CESSNA 500 Citation 560 SN lt 259 Citation 560 SN gt 260 Citation 650 Sabreliner 65 WestWind 1124A LearJet 24 Raytheon Hawker HS 125 3A Falcon 20 F
25. OFFSET IS 0 A SET F ADC SWITCHES AS FOLLOWS SW1 0 SW2 E SW3 0 SW4 0 PROGRAM DIGIDATA FOR LEFT K FACTOR RIGHT K FACTOR 21 980 LEFT OFFSET RIGHT OFF SET 0 SHADZV MINNEAPOLIS 55426 INSTALLATION WIRING E ADC200 2000 TU UR DIGIDATA WITH DC F CESSNA CITATION S25 JET SPP Eo PA NOT TO SCALE 4028 937 F ADC 200 FUEL MONITOR P N 962810 1 TAIL P N 962820 1 F ADC 2000 P N 962830 1 RIGHT ENGINE RIGHT ENGINE FUEL FLOW SIGNAL GROUND LEFT ENGINE JET CARD i LEFT ENGINE FUEL 542 1158 02 FLOW SIGNAL NOTES 1 THIS INSTALLATION APPLICABLE TO AIRCRAFT WITH J E T FUEL MODULE PART NUMBER 542 1158 02 ONLY JET MODULE NOS 542 1158 01 MAY BE CHANGED TO 542 1158 02 BY JET 5 542 1158 7 2 K FACTOR IS 860 SET F ADC SWITCHES AS FOLLOWS SW1 D SW2 D SW3 D SW4 D A PROGRAM THE DIGIDATA FOR LEFT K FACTOR RIGHT K FACTOR 860 PPG LEFT OFFSET RIGHT OFFSET 0 JET CARD PIN 11 CORRESPONDS TO FUEL MONITOR PIN Z JET CARD PIN 12 CORRESPONDS TO FUEL MONITOR PIN X 0501 006 A 1 17 05 ZK CORRECTED NOTES 1 5 8 6 98037025 3 26 98 SRB KCL BASELINE RELEASE DATE DESCRIPTION NOT TD SCALE DIGIDATA P1 P N 912802 13 RIGHT FUEL FLOW SIGNAL 15 LEFT FUEL FLOW SIGNAL GROUND SHADIN MINNEAPOLIS 55426 INSTALLATION WIRING F ADC200 200
26. P N 962830 1 962830 2 962830 3 Page 9 10 Stage 3 Loopback configuration Switch 1 is set to 3 to indicate that the stage 3 loopback is being performed SWITCH 2 K FACTOR TABLE SELECTION For F ADC 962830 1 and 962830 2 only 0 Standard K FACTOR Matrix 0 Table 2 in this manual 1 Alternate K FACTOR Matrix 1 Table 3 in this manual 2 DO NOT USE SWITCH 3 FUEL FLOW DELAY TIME No Delay 5 Second Delay 10 Second Delay 15 Second Delay 20 Second Delay 25 Second Delay 30 Second Delay 35 Second Delay 40 Second Delay 45 Second Delay DO NOT USE gt Loan D 1 n SWITCH4 SPECIAL OPTION DESCRIPTION F ADC Software Version 0 ARINC 429 labels 206 IAS and 210 TAS are not 93 00 67 and up transmitted if the IAS lt 20 knots 1 ARINC 429 labels 206 IAS and 210 TAS are transmitted 93 00 67 and up as zero knots if the IAS lt 20 knots 2 F Reserved DO NOT USE IM2830LG doc DIR 962830 IM2830 Shadin Rev J INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Loopback Procedure 3 for Software Version 93 00 77 Stage 0 Loopback Configuration Switch 1 is set to 0 to indicate that the stage 0 loopback is being performed SWITCH 2 Fuel Units and Engine Type Gallons Single Engine Liters Lbs 5 8 5 Lbs6 71 Kilograms i Lbs6 5 Lbs 6 3 4 not used Gallons Twin Engine Li
27. Page 2 4 and 2 5 changed to clarify configuration A parameters Page 5 4 changed to include Sandel heading source Page 9 1 9 2 9 6 and 9 7 changed to clarify software version useage Page 9 11 moved to 9 16 Pages 9 11 to 9 15 added for Procedure 3 Page 5 1 changed to add TSO paragraph Add sections 2 8 and 2 9 Update sections 2 0 5 1 5 7 and 9 2 Moved page 9 16 to 9 21 Included updated Dwg 4028 82 Corrected typo in section 1 3 system figure Added 681201 OAT probe installation and parts list to page iv drawing list Updated Page 2 4 ARINC table Corrected page 10 3 Table 2 Added pages 9 21 to 9 26 Page 9 21 became 9 27 Changed Shadin Company Inc and SCT to Shadin everywhere Updated rev levels of cited documents Removed loopback procedure for S W Version 93 00 79 From 2 5 3 removed unsupported ARINC 429 Label 247 From 11 0 Install Drawings and Install Kits Parts Lists removed 4012 177 and PL 681201A 1 Updated Aerosonic altimeter 10420 11968E replacing 102220 1188 Indicates change since previous revision IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev H P N 962830 1 962830 2 962830 3 Page 1 1 1 0 OVERVIEW 1 1 The Manual This manual is designed to facilitate the installation of the Shadin Fuel AirData Computer ADC 2000 12 Product Information The Shadin ADC 2000 system is designed to provide a combined source of fuel and air data
28. RSe3e TX NOTES USE RS 232 OR RS422 NOT BOTH A CONNECT SHADIN CONVERTER P N 937000 03 IN PARALLEL WITH NAVIGATIONAL RECEIVERS SERIAL DATA INPUT A CONSULT DRAWING NUMBER 4070 005 FOR WIRING AND STRAPPING INFORMATION SHADIN MINNEAPOLIS 55426 INSTALLATION WIRING F ADC200 2000 AND APPROVED SHADIN CONVERTER TO EVENTIDE ARGUS 05017032 2 14 05 WMP UPDATED TITLE BLOCK 4028 348AJ DWG 98037025 3 26 98 SRB KCL BASELINE RELEASE DIRECTORY DRAWING NO P N F ECO DATE BY APPD DESCRIPTION NOT TO SCALE ser 4028 948 A APPLICATION NOTES MANUFACTURING NOTES ALL OTHER A SETTINGS IN SPACE PROVIDED WHEN SWITCHES ARE NOT USED MANUFACTURER IGNORE IF CONFIGURATION IS NECESSARY PRINT SWITCH PRINT N A 1 MATCH FONT STYLE AND SIZES DIMENSIONS AS SHOWN 2 SWITCH SETTING BOX DIMENSIONS ARE AS FOLLOWS WIDTH 295 HEIGHT 200 ACCESS COVER SWITCH SETTINGS Swi SW2 SW3 SW4 ARING P N 712801 BACKGROUND ETTERING amp UNLESS OTHERWISE NOTED SHADIV wnnearous 55426 de Ha APPROVED LABEL ADC200 2000 ACCESS COVER FINISH 0501 032 A 2 14 05 WMP UPDATED TITLE BLOCK MATERIAL SHANG AID F 9812 002 12 3 98 BASELINE RELEASE 3M 7983 P N 712801 N APPD DESCRIPTION SCALE FULL ser 1011 4028 A8
29. communication port Following the steps as set forth in the user manual allow the AirData to be configured See the ADSETUPF User Manual for more details IM2830LG doc DIR 962830 IM2830 Shadin Rev J 9 2 INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 9 2 Configuring Manually Loop Back The switches that are available from the back side of the unit need to be set to the appropriate positions as determined by the switch settings listed below After the correct switch positions have been selected the unit is powered using the Loop Back harness consult drawing number 4028 944 contained in section 11 The purpose of the loop back harness is to tie the RS 232 transmit and receive ports together This allows the software when the unit is powered on to read the switch positions Switch 1 is set to different positions to select the separate stages that the loopback is performing There are 5 different loopback procedures Use loopback procedure 1 for Software Versions 93 00 16 93 00 29 Use loopback procedure 2 for software versions 93 00 51 93 00 71 Use loopback procedure 3 for software versions 93 00 77 Use loopback procedure 4 for software version 93 00 82 and above Note that procedure has 2 stages Procedure 2 3 and 4 have 4 stages and procedure 5 has 5 stages Remember to cycle power between stages and that the F ADC is to be powered on for 1 minute for
30. 0 IDC IDC IDC IDC IDC SPERRY IDC AEROSONIC IDC 28007 427 28704 A1001 28711 621 28711 500 28007 431 BA141 e8711 065 10420 11968E KTS B45152 10 410 KEA130A 346 429 600 SERIES 433 066 08 TO 11 P N 962830 1 D1001 D2001 P N 962830 2 D4001 2101 P N 962830 3 di z 6 m EXCITATION VOLTAGE USUALLY SUPPLIED BY AIRCRAFT HARNESS 5 12 VDC Jide TO EXCITATION J1 13 TO GND EXCITATION VOLTAGE MAY BE SUPPLIED BY AIRCRAFT HARNESS 65 VDC 2112 TO EXCITATION J1 13 TO GND EXCITATION VOLTAGE SUPPLIED BY AIRCRAFT HARNESS 10VDO 4113 TO EXCITATION 11 TO GND 4115 5VDC POWER MAY BE USED FOR EXCITATION MAXIMUM DIFFERENTIAL INPUT VOLTAGE BETWEEN AND BARO lt gt IS 12VDC P P P gt SHADIN MINNEAPOLIS 55426 INSTALLATION WIRING ADC 2000 KCL 0211 047 DEL PIN 11 ADDED GND 0011 003 KEA 346 WAS amp RESPECTIVELY ADD IDC P N KTS 45152 10 410 D SUB CONN TO ALTIMETER BARDO POT 9812 001 12 14 98 BASELINE RELEASE DATE DESCRIPTION SCALE NONE SHEET 1 OF 1 FILE NAME 0007 031 7 19 00 PAB RH IN SPERRY LABEL WAS V 4028 A82CJ DWG Ez GARMIN GARMIN 430 GARMIN 530 P4001 P5001 SHADIN F ADC 200 2000 RSe3e TX 27 RS232 RX 26 56 NOTES 1 CONFIGURE SHADIN F ADC 200 2000 1 0 FOR FLOWMETER GARMIN 2 CONFIGURE SHADIN
31. 0 OR DIGIDATA WITH DIGITAL FF TO BOMBARDIER LEARJET 24 25D DIRECTORY DRAWING NO REV 4028 938 FILE NAME 028 938AJ DWG F ADC 200 P N 962810 2 P N 962820 2 F ADC 2000 P N 962830 2 FUEL FLOW IND RIGHT ENGINE FUEL SIG FLOW SIG 2 RIGHT ENGINE FUEL FLOW IND LEFT ENGINE FUEL SIG FLOW SIG NOTES 1 FOR AIRCRAFT WITH THE FOLLOWING INDICATORS TRANSMITTERS A INDICATOR PART NOS 850590 1 850590 507 DSF1549 D5154 9 TRANSMITTER PART NOS 850590 513 850590 515 TFF2905 11 151906 001 2 K FACTOR IS 27 6 27 600 PPG SET F ADC SWITCHES TO Swi SHADIN MINNEAPOLIS MN 55426 RB INSTALLATION WIRING F ADC 200 2000 WITH SINE FF TO ROCKWELL COMMANDER 690 AND 695 DWG oo TT 4028 2 P N REV DATE BY APPD DESCRIPTION NOT TO SCALE ser 101 4008 939 y E EEE 0501 032 2 14 05 UPDATED TITLE BLOCK RIGHT ENGINE F F IND 080 LEFT ENGINE F F IND P079 NOTES 1 FOR AIRCRAFT SERIAL NOS RK 45 RK 49 AND AFTER WITH FUEL INDICATOR PART 900 3 2000 2 IS 1154 11 540 PPG OFFSET IS 0 A SET F ADC SWITCHES TO SW1 0 SW2 2 SW3 0 SW4 4 PROGRAM DIGIDATA FOR LEFT K FACTOR RIGHT K FACTOR 11 540 PPG LEFT OFFSET RIGHT OFFSET 0 0501 032 2 14 05 UPDATED TITLE BLOCK 9803 025 3 26 98 SRB KCL BASELINE RELEASE EC
32. 0 1 962830 2 962830 3 Loopback Procedure 2 for Software Version 93 00 51 to 93 00 71 Stage 0 Loopback Configuration Switch 1 is set to 0 to indicate that the stage 0 loopback is being performed SWITCH 2 MH HO O m gt xo Q amp D Fuel Units and Engine Type Gallons Single Engine Liters Lbs 5 8 5 Lbs 6 71 Kilograms i Lbs 6 5 Lbs 6 3 4 not used Gallons Twin Engine Liters Lbs 5 8 Lbs 6 71 5 Kilograms Lbs 6 5 i i Lbs 6 3 i DO NOT USE 9600 BAUD Loran Input Type Trimble ARNAV Bendix or IIMorrow Apollo NMS2001 800 820 Garmin Northstar Foster IIMorrow 611 612 and 618 Shadin Flow Meter DO NOT USE Use this position to make selection on SWITCH 4 Other Loran Input Type Northstar 1200 BAUD Foster 1200 BAUD IIMorrow 611 612 618 1200 BAUD DO NOT USE Page 9 6 IM2830LG doc DIR 962830 IM2830 Shadin Rev J INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 9 7 Stage 1 Loopback Configuration Switch 1 is set to to indicate that the stage 1 loopback is being performed SWITCH 2 OAT Probe 0 Shadin OAT Probe 1 ARINC 575 DO NOT USE 2 Rosemount 500 Q DO NOT USE 3 DO NOT USE SWITCH Loran Output Format Z Trimble and Garmin Format X ARNAV Generic Surveyor Bendix C Bendix King and F ADC without Baro Interface
33. 00 p 6 3950 8 P 5001 2 2 39600 9 o 45200 2 3 929200 E 58 199700 9 55 11 454004 2 29400 E 9 m 29600 3900 9 3 45800 2 6 Table 2 continued IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev G P N 962830 1 962830 2 962830 3 Page 10 5 Matrix 0 Digital K Factor Settings Continued swi sw2 PPG swi sw2 PPG swi 2 57700 93000 7 0 0 46000 46200 46400 46600 46800 47000 47200 47400 47600 49000 EC NE G 2 2 gs 8 58600 9 58700 A 58800 58900 C 6000 2 7000 E 3 78000 1 24 22 5 i 1 _ 2 12371 6 49200 49300 0 49700 50000 50200 50400 50600 50800 55500 55550 57000 57100 57200 57300 57400 57500 57600 4 5 7 1 2 3 0 4 0 0 1 0 2 0 3 0 4 0 5 0 7 0 0 0 0 0 0 0 4 90000 5 91000 92000 7 2 3 7 3 F 1 A 2 3 IIIIIIOIII T III n sl les gt a ta s 02 to z 16 PPG SW1 46000 2 46200 2 46400 2 46600 2 46800 2 47000 2 47200 2 47400 2 47600 2 49000 9 49100 EU 49200 9
34. 1 OF 1 4 APPROVED KCL 1 BENDIX KING KLN90 A B KLN89 KLN900 P901 P891 P9002 SHADIN F ADC 200 2000 36 38 RSe3e TX RS232 RX NOTES 1 CONFIGURE SHADIN F ADC 200 1 0 SHADIN FUEL FLOW METER FOR FLOWMETER BENDIX C 2 CONFIGURE SHADIN F ADC 2000 1 0 FOR FLOWMETER BENDIX C OR DIGIFLO DIGI LO MINIF LO MICROFLO FLOWMETER BENDIX D IF USING THE P N 91053 P N 91053XP P N 91204X 91204XT 38D METRIC INTERFACE 3 CONFIGURE SHADIN FUEL FLOW METER 1 0 FOR ON AIRDATA 4 FUEL FLOW TRANSDUCER SIGNAL S gt ARE CONNECTED TO THE SHADIN FUEL FLOW METER NO FUEL SIGNAL CONNECTION TO THE ADC 5 MINIMUM SOFTWARE LEVEL DIGIFLO 60 10 77 MINIFLO 60 01 77 MICROFLO 60 08 77 ADC 200 2000 93 77 SHADIN MINNEAPOLIS 55426 RH INSTALLATION WIRING F ADC200 2000 SHADIN FUEL FLOW INDICATORS BENDIX KING RECEIVER 02117047 3 11 03 ADDED NOTES 4 amp 5 ADDED FUEL FLOW METER SW VERSIONS meee e ECO 8 DATE DESCRIPTION SCAL 4028 94 F ADC200 2000 P N 962810 P N 962820 X gt X 1 2 P N 962830 X NAVIGATIONAL RECEIVER gt RS232 RX RS422 RX RS422 RX SHADIN CONVERTER P N 937000 03 EVENTIDE ARGUS P N 5000 RS422 RX RS422 RX P N 7000 KID RSe3e INPUT HI RSe3e INPUT LOW
35. 10 12 303G BNR 100 Message Length Type Number 304G BNR 100 Message Character 1 3 305G BNR 100 Message Character 4 6 306G BNR 100 NAV WPT AP Latitude 307G BNR 100 NAV WPT AP Longitude 310 BNR 200 Present Position Latitude 311 BNR 200 Present Position Longitude 312 BNR 50 Ground Speed 313 BNR 50 Track Angle T 314 BNR 100 True Heading T 315 BNR 100 Wind Speed 316 BNR 100 Wind Angle T 320 BNR 100 Magnetic Heading M 321 BNR 100 Drift Angle 347 BNR 100 Left and Right Fuel Flow 351G BNR 200 Distance to Destination 352G BNR 200 Estimated Time to Destination Not all labels are available at the same time Certain sets of labels are available depending on the switch selections IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev J P N 962830 1 962830 2 962830 3 Page 2 4 2 5 3 ARINC 429 Labels Associated with Switch Settings LABEL Description AA pat III ne jj 100 Selected Course 1 1 11 113 Waypoint Group Checksum O fofo j j 14 Desired Track True 0 115 Waypoint Bearing True 116 Cross Track Distance o 1 147 Magnetic Variation 203 101325 ojojoj 24 PALT BaroCorrected 205 mam _ jojojo j gt 206 Indicated Airspeed 01 j 210 True Airspeed folo
36. 11 047 2 7 03 PAB BAL ADDED DIMENSIONS e 4058 39564 0WG MATERIAL S EP N 78 REV DATE DESCRIPTION 30 CAD FILE AVAIL YES SCALE 1 2 1 40 28 3 9 5 MATING CONNECTOR SHADIN P N 230036 17 DA15S SHADIN P N 230038 HOOD DA 246 SELECTOR TABLE RS232 RX TIE J1 7 TO RS422 RX DEFAULT NO JUMPER REQ D gt SINGLE ENGINE J1 7 TO TWIN ENGINE DEFAULT NO JUMPER REQ D gt 3 05 3 24 WEIGHT 8 oz POWER CONSUMPTION 210 mo e 28v DC kwh m THE CONVERTER CAN MOUNTED ORIENTATION 4 SPACING IS REQUIRED ABOVE CONNECTOR NO COOLING IS REQUIRED THE CONVERTER CAN BE INSTALLED IN A PRESSURIZED NON PRESSURIZED AREA PROVIDING TEMPERATURE DOES NOT DROP BELOW 20 C 1 AMP CIRCUIT BREAKER IS REQUIRED 6 NO SHOCK MOUNT REQUIRED 7 USE HARDWARE PROVIDED IN INSTALL KIT P N IK9337 UNLESS OTHERWISE NOTED TO ASSEMBLE MATING CONNECTOR CONNECTOR KEY PIN FUNCTION 1 RS232 OR RS422 SELECT 2 TWIN OR SINGLE ENGINE SELECT SEE 4 SELECTOR NE TABLE 6 NC 7 SELECT POWER COUTPUT 8 14 TO 28 V DC POWER IN 9 10 SIGNAL GROUND l RS422 RX SHADIN ADC 12 RS422 RX USE RS 232 OR RS 422 13 RS232 RX NOT BOTH 14 RS232 TX TO ARGUS 5000 7000 15 POWER GND 0501 032 2 14 05 PAB WMP UPDATED TITLE BLOCK CONVERTER WAS TXMTR 9801 025 10 12 98 DMD PG AD
37. 2 to indicate that the stage 2 loopback is being performed SWITCH 2 Fuel Filter Type 0 Injector 1 Carburetor Page 9 9 SWITCH 3 AND SWITCH 4 CORRECTION For SSEC PSEC Select F ADC Software Version ex OO O COC Oo oO COCO oO Co oO oO oO CC D OO Z gt oo amp D No correction MITSUBISHI MU 300 CESSNA CITATION 500 501 CESSNA 525 CESSNA 500 Citation 560 SN lt 259 Citation 560 SN gt 260 Citation 650 Sabreliner 65 WestWind 1124A LearJet 24 Raytheon Hawker HS 125 3A Falcon 20 F Falcon 20 C D E LearJet 25D Douglas DC 8 Beechjet 400 Boeing 707 321B Cessna Citation S550 Falcon 10 Falcon 50 Raytheon Hawker HS125 700A LearJet 35 LearJet 55 Sabreliner 60 SSEC Only Lockheed Jetstar Reserved for future DO NOT USE ALL 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 58 93 00 63 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev J
38. 28 395 Installation Mounting Tray ADC2000 4070 005 Installation Dwg Serial to Argus 5000 7000 Converter P N 937000 03 4028 423 Installation Wiring Fuel Airdata Computer ADC2000 to Fuel System 4028 425 Installation Wiring Fuel Airdata Computer ADC2000 to OAT Heading System 4028 944 Installation Wiring Loop Back Harness for F ADC200 2000 D Sub Connector 4028 945 Installation Wiring F ADC200 2000 to Navigational Receivers with ARINC 429 4028 946 Installation Wiring F ADC200 2000 to Navigational Receivers with RS 422 RS 485 4028 947 Installation Wiring F ADC200 2000 Shadin Fuel Flow Indicators to Bendix King Nav Receiver 4028 948 Installation Wiring F ADC200 2000 and Shadin Converter to Eventide Argus 4028 A80 Label ADC200 2000 Access Cover P N 712801 4028 A82 Installation Wiring ADC 2000 D Sub Connector to Altimeter Baro Pot 4028 894 Installation Wiring F ADC200 2000 Shadin Fuel Flow Indicators to Garmin 430 530 N A Parts List OAT Probe Assembly Kit P N 681201 1 N A Parts List ADC2000 Installation Kit P N IK9630 1 Indicates change since previous revision Page iv of vi DATE REV 3 21 05 E 3 21 05 D 3 21 05 D 2 14 05 3 03 05 2 14 05 B 3 11 03 B 2 14 05 A 2 14 05 B 3 11 03 A 3 11 03 A 3 11 03 A 2 14 05 A 2 14 05 A 3 11 03 3 11 03 2 14 05 G 3 21 05 A IM2830LG doc DIR 962830 1 2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 I
39. 5 4 5 6 Connection to the Heading Source The system is designed to interface with any ARINC 407 heading system X Y Z with no effect on the heading system or the bootstrap XYZ FUEL Collins Collins i King Sperry Sigma Sandel Heading AirData HSI331A KSG105 Gyro SN3308 ARINC P1 syn DG Comp P1 P1 P2 t L A 25 p M B 6 k K D 4 H E 4 f J H 4 The C wire AC common and the Z wire must be connected together at the source bootstrap IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev J P N 962830 1 962830 2 962830 3 Page 5 5 5 7 Connection to the Pitot and Static Lines The pitot static line should be cut and a tee installed to tap into these lines Use the appropriate type of fittings to match the type installed in the aircraft Refer to CFR part 43 appendix E for approved practices in installing and verifying these connections PITOT STATIC adapter helpful hints To make an adapter for the Shadin ADC2000 the following parts could be used It is recommended to use all aluminum fittings Existing Pitot Static lines gt AN910 1D ANS16 2D gt 2 Hose with female fittings AN910 DASH NUMBER PIPE AN816 DASH NUMBER TUBE PIPE BRASS ALUM ALLOY SIZE THREAD STEEL ALUM ALLOY MS20825 TEE TUBE PIPE STEEL ALUM ALLOY THREAD HOSE Stratoflex 193 2 or Aeroquip 306 2 with MS27404 P N 311 2D on each end Ai
40. 60 FLOW INDICATOR DSF 1549 4 SIG RIGHT SIG ENGINE FUEL 3 GROUND FLOW LEFT ENGINE FUEL FLOW INDICATOR DSF 1549 4 LEFT SIG ENGINE FUEL SIG FLOW DSF 1549 e DSF 1549 4 DSF 1549 5 FLOW TURBINE FROM PROB COMPENSATOR CENVIRONMENT gt SIGNAL GROUND CASE GROUND DC POWER INPUT APPROX 28 VDO SV LIGHT RETURN 28 VDC POWER INPUT 28 VDC POWER RETURN CASE GROUND COMPENSATOR ENVIRONMENT SIGNAL GROUND FLOW TURBINE FROM PROB COMPENSATOR CENVIRONMENT gt GROUND CASE GROUND DC POWER INPUT APPROX 28 VDO SIGNAL GROUND TOTALIZER OUTPUT TEMP SENSOR DC GROUND TOTALIZER LOW lt gt TOTALIZER OUTPUT gt TEMP SENSOR SIGNAL GROUND DC GROUND TOTALIZER GROUND SIGNAL GROUND TOTALIZER OUTPUT FLOW TURBINE FROM PROB gt TEMP SENSOR 5 VDC LIGHT CHIQNMEO ON gt CcIco mo ON D gt gt NOTES 1 FOR AIRCRAFT WITH FUEL FLOW INDICATOR PART NOS DSF 1549 2 4 5 SEE TABLE FOR INDICATOR PINOUTS 2 K FACTOR IS 26 8 26 800 3 SET AIRDATA SWITCHES AS FOLLOWS SW1 C 227512 SHADIN eure SW2 7 SW3 SW4 7 pee ses APPROVED INSTALLATION WIRING F ADC 200 2000 TO FAIRCHILD 226 SERIES AIRCRAFT FILE NAME 05017006 2 14 05 WMP CORRECTED PINDUTS amp NOTE 1 E DESCRIPTION SCALE 4028 9402
41. A LE COMPUTER ADC 200 ADC 2000 AA A A A 02117047 3 11 03 REMOVED GNDS ADDED NOTES amp ADC 200 TITLE FILE NAME FUEL SYSTEMS 9505 028 5 17 95 DAP SES CORRECT SINE FF LABELING 94127005 12 7 94 DAP SES BASELINE RELEASE ECO DATE BY IAPP D DESCRIPTION SCALE NONE SHEET 1 OF 1 962830 X SPLICE WHT or BLK COMPASS HEADING 26V 400Hz MINNEAPOLIS 55426 INSTALLATION WIRING FUEL AIRDATA COMPUTER lt ADC2000 TO DAT HEADING FILE SYSTEM 0501 032 2 14 05 WMP UPDATED TITLE BLOCK 4028 425AJ DWG 9412 005 12 7 94 DAP SES BASELINE RELEASE DIRECTORY DRAWING NO FPN OS Eco DATE DESCRIPTION SCALE NONE s er 101 4028 425 Je 28VDC GND TX RS232 RX RS232 NOTES 1 CONSULT INSTALLATION MANUAL FOR F ADC PROGRAMMING INSTRUCTIONS 2 MATING CONNECTOR 15 PIN MALE D SUB SHADIN PN 2300510 OR EQUIVALENT SHADIN MINNEAPOLIS 55426 INSTALLATION WIRING LOOP Lp o f BACK HARNESS FOR F ADC200 2000 D SUB 0501 032 B 2 14 05 PAB UPDATED TITLE BLOCK CONNECTOR FILE NAME 98097022 9 28 98 CORRECTED PIN OUT ES 4028 944 A P N ECO DATE APPD DESCRIPTION NOT TO SCA sheer 4028 944 AIRSHOW UNIVERSAL TRIMBLE HONEY UNS 1M 8100 WELL B amp D A LAZER CABIN NAV DISPLAY 962810
42. CONN PINS MALE 230038 CONN HOOD 15 PIN Pe 230050 CONN SHELL FEMALE a EL 230055 CONN PINS FEMALE ac 230038 CONN HOOD 15 PIN TA J FEMALE 1 8 2 Je PINOUT 43 PINOUT 12 28v DC POWER INPUT NC NC NC RX RS 422 NC RX RS 422 NC RX RS 232 NC TX RS 232 NC TX ARINC429 A NC TX ARINC429 B NC GROUND NC NC NC TX RS 422 NC TX RS 422 NC NC NC SIGNAL GND NC NC NC Ji PINOUT FUEL FLOW RIGHT lt gt FUEL FLOW RIGHT GROUND HEADING Y HEADING 26V 400Hz H 26V 400Hz Z C BARD WIPER FUEL FLOW LEFT lt gt USE RS 232 OR RS 422 NOT BOTH FUEL FLOW LEFT gt GROUND lt gt Signal DAT C 5V 1 2 3 4 5 6 7 8 9 ARGUE o o Q WY AROVES SHADILN 55426 05017032 D 3721 05 WMP UPDATED TITLE BLOCK CH TITLE CORR PITOT STC LABEL LOCNS APPROVED INSTALLATION DWG ADC2000 9706 07 C 6 9 97 WMP KCL UPDATE J3 9505 08 B 5 17 95 SES REVERSE FF POLARITY FILE NAME DC FUEL FLOW 9505 04 A S lI 95 WMP SES ADD SPRING LATCH CLIPS us 9412 05 18 7 94 DAP SES BASELINE RELEASE _ o oSCo OSOS 962830
43. D SHLD GND FLOW SIGNAL IN FLOW SIGNAL IN TEMP SIGNAL IN TEMP SIGNAL IN F ADC 200 P N 962810 2 FLOW METER P N 962820 2 FLOW METER AE EE 25V DC IN M F ADC 2000 P N 962830 2 SIG COND P N K FACTOR 5 1 SWe SW3 SW4 45 586801 003 5150 PPG 6 6 55426 INSTALLATION WIRING F ADC 200 2000 SINE FF TO MITSUBISHI MU 300 AND 0501 038 2 14 05 PAB UPDATED MODEL 400 BEECHJET 9803 02 SIE CHANGE TITLE CHANGE FILE NAME FROM 4028 819 DWG 4085 SI9BJDWG ECO DESCRIPTION DO NOT SCALE SET 1 OF 1 4028 819 NOTES ZN FROM RIGHT ENGINE FF TRANSMITTER FROM LEFT ENGINE FF TRANSMITTER SIGNAL COND P N 620 0098 PC 425 0098 RIGHT SIG IN EHO RIGHT SIG IN D LEFT SIG IN LEFT SIG IN B F ADC 200 P N 962810 2 P N 962820 2 F ADC 2000 P N 962830 2 SIG COND P N K FACTOR SW1 PC 620 0098 33800 6 72 72 SHADIN MINNEAPOLIS 55426 INSTALLATION WIRING APPROVED F ADC 200 2000 TO MITSUBISHI 05017032 B 2 14 05 UPDATED TITLE BLOCK rite MARE MU 2 W FOXBORO 620 SYSTEM 00077031 7719700 RH ADD PC 425 0098 4028 909BJ DWG 97117051 1 8 98 DMD KCL BASELINE RELEASE DIRECTORY DRAWING PN F DATE APPD DESCRIPTION bo Nor SCALE SHEET 4028 909 B 450 P50 GND lD E04A20N 08 20 08 20 SIGNAL E06A20
44. DC 200 2000 90 380009 2 101 384153 1 900 900 900 D SUB CONNECTOR OR OR ne 1 2 7 8 A 1 2 1 8 0 90 380009 5 101 384153 3 CURVED FACE FLAT FACE CURVED FLAT FACE A A A A AA AA AA T 5 2 7 f A eS PON 203 PART NUMBER PART NUMBER PART NUMBER PART NUMBER PART NUMBER m 90 380009 2 101 384153 1 900 900 PC900 XAXXXXPH a OR OR 1 6 A 1 2 7 8 1 2 1 8 0 a ar 90 380009 5 101 384153 3 CURVED FACE FLAT FACE CURVED FLAT FACE nies A AA AA AA NOTES 1 THIS SCHEMATIC IS USED FOR KNOWN BEECH KING AIR MODELS SOME INDICATORS ARE NOT LISTED BUT MAY BE INTERFACED CALL SHADIN TECH SUPPORT IF YOU DO NOT SEE THE PART NUMBER OF YOUR INDICATOR LISTED INDICATOR PART NUMBERS POSSESSING A PREFIX PC900 ARE XOTECHNOLOGIES TYPE INDICATORS THE LAST DIGIT REPRESENTS THE INDICATOR AUXILIARY RATE OUTPUT 1 NUMBER SHADIN SUPPORTS THE 1 MODELS ONLY XOTECHNOLOGIES INDICATOR P N 900 IS NOT SUPPORTED THE AUXILIARY RATE OUTPUT OF THIS UNIT IS 0 1 mA INDICATOR P NS THAT END WITH A XX2 WILL ENCOUNTER A DEGRADATION IN PERFORMANCE DUE TO THE AUX RATE OUTPUT OF 0 5 333 VDC INDICATOR P NS ENDING WITH AN ARE UNKNOWN THE FOLLOWING XOTECHNOLOGIES INDICATOR P NS POSSESS A
45. DED NOTE 7 CORRECTED HEIGHT PROVIDED SHADIN P N FOR MATING CONN 9707 023 7 15 97 PG BASELINE RELEASE DIMENSIONS ARE IN INCHES TOLERANCES X X 0 1 0 01 FINISH MATERIAL N A SAADIN MINNEAPOLIS MN 55426 INSTALLATION SERIAL ARGUS 5000 7000 CONVERTER DRAWING NO REV DATE BY APPD DESORPMON SE NONE seen 16 1 4070 005 P N 937000 03 FILE NAME FREQUENCY FF INTERFACE OPTION LEVEL FF INTERFACE OPTION 962830 1 962830 1 962820 1 962820 1 Jl Ji RIGHT 15V TRANSDUCER FUEL SHADIN P N FLOW SIG 680501 OR SIG GND 6605XX 15V TRANSDUCER SHADIN P N SIGNAL FROM SIG 680501 X EXISTING SYSTEM OR SIG GND 6605XX NOTES 1 THE ADC 200 AND ADC 2000 D SUB CONNECTER SHARE THE SAME FUEL FLOW PIN LOCATIONS SINE FUEL FLOW OPTION D C FUEL FLOW OPTION A WHEN INSTALLING TO ANY EXISTING FREQUENCY 32555 2658303 FUEL FLOW TRANSDUCER USE ONLY THE SIGNAL 3 PICKUPS 31 LINE DO NOT CONNECT POWER AND GROUND LINES THIS COULD DAMAGE THE ADC AND OR R ENGINE AIRCRAFT INSTRUMENTS SIG UNIT END TO PREVENT A GROUND LOUP EM 42755 USE SHIELDED WIRE BUT GROUND ONLY ON ADC L ENGINE E J FLOW SIG 5 TO 10V DC FOR FULL SCALE MODEL DEPENDENT SHADIN MINNEAPOLIS MN 55426 RATES INSTALLATION WIRING FUEL AIRDAT
46. E Use this position to make selection on SWITCH 4 Other Loran Input Type Northstar 1200 BAUD Foster 1200 BAUD IIMorrow 611 612 618 1200 BAUD DO NOT USE Page 9 16 IM2830LG doc DIR 962830 IM2830 Shadin Rev J INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 9 17 Stage 1 Loopback Configuration Switch 1 is set to to indicate that the stage 1 loopback is being performed SWITCH 2 OAT Probe Type 0 Shadin OAT Probe 1 ARINC 575 DO NOT USE 2 Rosemount 500 Q DO NOT USE 3 F DO NOT USE SWITCH 3 Loran Output Type 0 Format Z Trimble and Garmin 1 Format X ARNAV 2 Generic 3 Surveyor 4 Bendix Bendix King and F ADC without Baro Interface 5 Bendix D Bendix King and F ADC with Baro Interface 6 Shadin S Morrow GX50 55 60 7 Bendix fuel only 8 Garmin G 9 F Do Not Use SWITCH 4 Altimeter Selection for Baro DC Input 0 None 1 Type 1 2 Type 2 3 3 4 4 3 Types 6 Type 6 7 Type 7 8 DO NOT USE 9 Type 9 DO NOT USE B Type 11 C F DO NOT USE IM2830LG doc DIR 962830 IM2830 Shadin Rev J Type 1 Type 2 Type 3 Type 4 Type 5 Type 6 Type 7 Type 8 Type 9 Type 10 Type 11 INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 9 18 ALTIMETER TYPES Kollsman PD 44929 935 done for Cessna 525 Bendix
47. E06B20 GROUND 05 20 05 20 F ADC 200 P N 962810 3 P N 962820 3 DIGIDATA F ADC 2000 P N 912802 03 P N 962830 3 P N 912802 03 G 11 GROUND TNI R H SIG 13 R H SIG 1 R H SIG o 10 L H SIG 9 L H SIG NOTES 1 FACTOR IS 16 270 J49 P49 OFFSET IS 0 L H A SET F ADC SWITCHES AS SIGNAL F E16A20 U 16 20 SW3 0 SW4 0 PROGRAM DIGIDATA FOR E LEFT K FACTOR RIGHT GND 7 4 14 0 K FACTOR 16 270 PPG LEFT OFFSET RIGHT OFFSET 0 IND 15 FUEL FLOW INDICATOR SHADIN MINNEAPOLIS MN 55426 DRAFTER INSTALLATION WIRING F ADC200 2000 OR DIGIDATA WITH DC FF TO j Cj i CESSNA CITATION 500 501 550 aysaypi SSE Se Cae FILE NAME 550 551 552 0501 032 A 2 14 05 WMP UPDATED TITLE BLOCK MES res DWG DRAWING NU 98037025 3 26 98 SRB KCL BASELINE RELEASE 4028 4028 9 36 P N ECO REV DATE BY DESCRIPTION SCALI SHEET 1 OF 1 R H SIGNAL GROUND L H GROUND SIGNAL 10012 FUEL FLOW INDICATUR 0501 032 e 14 05 UPDATED TITLE BLOCK 9803 0065 3 26 98 SRB BASELINE RELEASE ECO REV DATE APP D DESCRIPTION FUEL FLOW P C B FUEL FLOW P C B F ADC 200 P N 962810 3 P N 962820 3 DIGIDATA F ADC 2000 P N 912802 03 P N 962830 3 P N 912802 03 G R H SIG 10 L H SIG 9 L H SIG NOTES 1 K FACTOR IS 21 980
48. FACTOR RIGHT K FACTOR 46 160 PPG LEFT OFFSET RIGHT OFFSET 0 SHADIIV MINNEAPOLIS MN 55426 DRAFTER INSTALLATION WIRING F ADC 200 2000 APPROVED a 0501 006 C 1 17 05 PAB ZK IND 3265013 0801 amp RAGEN P N TABLES OR DIGIDATA WITH DC FF PIPER 0001 016 B 1 31 00 LJM EDJ ADD IND 3265013 1201 XMTR TFF 2905 9 TO NOTE 1 9901 015 A 1 20 99 DMD KCL ADD P NS 9628304 3 5 5 962830 3 5 5 9808 012 8 7 98 LE BASELINE RELEASE CHEYENNE PA3IT ECO 4028 A29 4058 DWG
49. FUEL FLOW METER 1 0 FOR MICROF LO ON AIRDATA 3 CONFIGURE GARMIN 430 530 1 0 FOR CHANNEL 1 TO SHADIN FADC AVIATION SHADIN FUEL FLOW METER DIGIFLO DIGIFLO MINIFLO P N 91053XT P N 91053XP P N 91204X 91204XT 38D 4 MINIMUM SOFTWARE LEVEL ADC 200 2000 93 XX 77 GARMIN 430 2 17 GARMIN 530 2 02 DIGIFLO L 60 10 77 MINIFLO L 60 01 77 MICROFLO L 60 08 77 5 FUEL FLOW TRANSDUCER SIGNAL S ARE CONNECTED TO THE SHADIN FUEL FLOW METER NO FUEL SIGNAL CONNECTED TO THE ADC SHADIN MINNEAPOLIS MN 55426 DRAFTER INSTALLATION WIRING F ADC200 2000 APPROVED LEE SHADIN FUEL FLOW INDICATORS TO GARMIN 430 530 02117047 3 11 03 BAL CHANGED TABLE NOTE 4 ADDED NOTE 5 UPDATED SW VERSIONS OF FLOW METERS pnm recle 0008 028 9 12 00 Pas BASELINE RELEASE IRE 4028 894 A P N DESCRIPTION SCALE 4028 B94 A Shadin Filename 681201 1GP doc DIRECTORY 681201 1 Report 4032D ECO Date January 17 2005 ECO 0501 032 Rev G Release date 02 14 05 Sec Ix Approved WP Page of 1 PARTS LIST Part 681201 1 Drawing s 4028 005 Rev C Description OAT PROBE ASSEMBLY KIT EN P N QTY DESCRIPTION MFG MFG DESIGNATION COMMENTS 10 511201 4 RIVET AN470AD3 4 or MS20470AD3 4 15 543216 1 OAT STIFFENER RING 4032 082 20 670503 1 SHIELD Temp Sensor Assy 4005 265 25 670504 1
50. I 962830 3 REV D DESCRIPTIDN DO NOT SCALE DRAWING SHEET 1 OF 1 4028 438 A NOTES 1 REFERENCE P N 681201 1 DAT PROBE ASSEMBLY KIT AVOID INSTALLING DAT PROBE IN OR NEAR PROP AIRSTREAM ENGINE EXHAUST FLOW PATH CABIN HEATERS EXHAUST FLOW PATH TRANSMITTING ANTENNAS DME TXP COMM DARK PAINTED AREAS PROBE P N 681201 AN T RQUE NUT FN 25 TO 13 IN LBS MAX re 5 7 dri AIRCRAFT FUS DRI 0 3598 23 64 1 00 UNTING H DRAVING DATE MON ARE IN oder SHADIN 3 0 01 INSTALLATION 0501 038 2 14 05 WMP UPDATED TITLE BLOCK amp NOTE 4 ADDED TO TITLE PROBE ASSEMBLY KIT 01117001 11 14 01 STANDARDIZED DWG FORMAT TO MIMIC DWG NO 4012 177 00027036 A 3 1 96 WMP PG CONVERT TO CAD ADD NOTES 1 AND 3 MATERIAL 120v wa rap ses BASELINE RELEASE mt ASA P N681201 1 T EVITE APP D DESCRIPTION s er 1 0F1 4028 005 6 25 x2 7 NOTES 7 1 AN USE 6 MOUNTING HARDWARE 2 DELETED 3 USE TO INSTALL SHADIN P N 612826A OR 612826 TRAY DIMENSIONS ARE IN INCHES SA DV 55426 XYK 1 64 20 01 INSTALLATION MOUNTING 0501 032 B 3 3 05 PAB WMP DELETED NOTE 2 amp 10 DIMENSIONS ADDED NOTE 3 N A 02
51. Indicated Air Speed IAS Baro Pressure Fuel Used Right Wind Direction and Speed Baro Corrected Alt Fuel Used Left Vertical Speed Pressure Altitude Fuel Remaining True Air Temperature Rate of Turn NM Gal ground Outside Air Temperature OAT Baro Correction mb 1 Fuel to Destination Fuel at Destination Baro Correction hg Note Not all parameters will be available to all navigational receivers Contact the manufacturer for display capabilities ARINC 429 GAMA Output Labels LABEL TYPE RATE mS 074G DSC 100 075G DSC 100 113G BNR 100 114 BNR 50 115 BNR 50 116 BNR 50 117G BNR 50 147G BNR 1000 150 BNR 1000 162 BNR 200 163 BNR 1000 203 BNR 200 204 BNR 200 205 BNR 200 206 BNR 200 LABEL NAME Flight Plan Header Active WPT from to WPT Group Checksum Desired Track T WP Bearing T Crosstrack Distance Vertical Deviation Magnetic Variation GMT Density Altitude Wind on Nose PALT 1013 25 mB PALT Baro Corrected Mach Number IAS IM2830LG doc DIR 962830 IM2830 Shadin Rev J INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 2 3 LABEL TYPE RATE mS LABEL NAME 210 BNR 200 True Airspeed 211 BNR 200 OAT 212 BNR 200 IVS 213 BNR 200 TAT Static 234 BNR 100 Baro Correction mb 1 235 BNR 100 Baro Correction mg 251G BNR 200 Distance to Go 252 BNR 200 Time to Go 2756 DSC 200 LRN Status Flags 301G BNR 100 Message Character 7 9 302G BNR 100 Message Character
52. NSTALL DRAWINGS AND INSTALL KITS PARTS LISTS continued AIRCRAFT SPECIFIC Installation Wiring F ADC200 2000 Sine FF to Mitsubishi MU 300 amp Model Installation Wiring ADC200 2000 to Mitsubishi MU 2 Installation Wiring F ADC200 2000 or DigiData with DC FF to Cessna Installation Wiring F ADC200 2000 or DigiData with DC FF to Cessna Installation Wiring F ADC200 2000 or DigiData with Digital FF to Installation Wiring F ADC200 2000 with Sine FF to Rockwell Commander Installation Wiring F ADC200 2000 or DigiData with DC FF to Raytheon Installation Wiring F ADC200 2000 or DigiData with DC FF to Westwind Installation Wiring F ADC200 2000 to Fairchild SA226 Series Aircraft Installation Wiring F ADC200 2000 to Navigational Receivers with RS 232 Installation Wiring F ADC200 2000 to Aerospatiale AS365N2 Dauphin Installation Wiring F ADC200 2000 to Aerospatiale AS332 Super Puma Rev L 11 0 Drawing No Description Part Number 4028 818 Installation Wiring F ADC 200 2000 w Analog FF to Beech KingAir Indicators 4028 819 400 Beechjet 4028 909 w Foxboro PC 620 System 4028 936 Citation 500 501 550 5550 551 552 4028 937 Citation 525 Jet 4028 938 BomBardier LearJet 24 25D 4028 939 690 and 695 4028 940 Beechjet 400A Aircraft 4028 941 1124 Models 4028 942 4028 943 4028 949 4028 950 4028 A29 Installation Wiring F ADC 200 2000 or DigiData with DC FF Piper Cheyenne PA31T Indicates change s
53. O REV DATE APP D DESCRIPTION F ADC 200 P N 962810 3 P N 962820 3 F ADC 2000 P N 962830 3 RIGHT ENGINE FUEL FLOW NOT_TO_SCALE DIGIDATA P N 912802 03 14 L SIGNAL 15 1 SIGNAL SAADIN MINNEAPOLIS 55426 INSTALLATION WIRING F ADC 200 2000 OR DIGIDATA WITH DC FF TO RAYTHEON BEECHJET 400A AIRCRAFT ae DRAWING NO EV 4028 940 RIGHT ENGINE FUEL FLOW INDICATOR 16 SIG LEFT ENGINE FUEL FLOW INDICATOR NOTES 1 FOR AIRCRAFT WITH THE FOLLOWING INDICATOR TRANSMITTERS INDICATOR PART ND CRAGEN 1291 2 TRANSMITTER PART NO 0011 151 909 001 2 K FACTOR IS 10 49 10 490 PPG OFFSET IS 0 AXSET AIRDATA SWITCHES AS FOLLOWS SW1 1 SWe 8 SW3 4 PROGRAM DIGIDATA FOR LEFT K FACTOR RIGHT K FACTOR 10 490 PPG LEFT OFFSET RIGHT OFFSET 0 0501 032 2 14 05 UPDATED TITLE BLOCK 9803 025 3 26 98 SRB KCL BASELINE RELEASE ECO REV DATE APP D DESCRIPTION F ADC 200 P N 962810 3 P N 962820 3 F ADC 2000 P N 962830 3 SIG RIGHT ENGINE SIG FUEL GROUND FLOW 0 SW4 NOT_TO_SCALE DIGIDATA P N 912802 03 14 L SIGNAL 15 1 SIGNAL SAADIN MINNEAPOLIS 55426 INSTALLATION WIRING F ADC 200 2000 OR DIGIDATA WITH DC FF TO WESTWIND 1124 MODELS E DRAWING ND EV 4028 941 P N F ADC 200 P N 962810 2 P N 962820 2 F ADC 2000 P N 962830 2 RIGHT ENGINE FUEL P1
54. OCK CH TITLE CORR PITOT STC LABEL LOCNS 9803 054 D 3 26 98 SRB KCL CORRECT Ji DES FOR PIN AND PIN 11 9706 017 C 6 9 97 WMP KCL UPDATE 9505 014 5 11 95 SES ADD SPRING LATCH CLIPS 9412 005 12 7 94 DAP SES BASELINE RELEASE BY DESCRIPTION MATING CONNECTORS P1 P3 230051 CONN SHELL MALE 230054 CONN PINS MALE 230038 CONN HOOD 15 Pe 230050 CONN SHELL FEMALE 230055 CONN PINS FEMALE 230038 CONN HOOD 15 PIN FEMALE 1 8 NPTF 2 Je PINOUT 12 DC POWER INPUT NC RX RS 422 RX RS 422 RX RS 232 TX RS 232 TX ARINC429 A TX ARINC429 B GROUND NC TX RS 422 TX RS 422 NC SIGNAL GND NC J3 PINOUT NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC 1 2 3 4 5 6 7 8 9 Q Q 9 E sp O Q ARPWES USE RS 232 OR RS 422 NOT BOTH SHADIN 15 55426 DRAFTER INSTALLATION DWG ADC2000 DIGITAL FUEL FLOW FIL 962830 1E J DWG DIRECTORY 962830 DO NOT SCALE DRAWING SHEET 1 OF 1 DRAWING NO 4028 394 A P N 962830 1 MATING CONNECTORS P1 230051 CONN SHELL MALE 230054 CONN PINS MALE 230038 CONN HOOD 15 PIN Pe 230050 CONN SHELL FEMALE 230055 CONN PINS FEMALE 230038 CONN HOOD 15 PIN
55. Shadin FUEL AIRDATA COMPUTER ADC 2000 P NS 962830 1 962830 2 962830 3 INSTALLATION MANUAL REV L O Shadin 6831 Oxford Street St Louis Park MN 55426 USA Sales 800 328 0584 Technical Support 800 388 2849 www shadin com P N IM2830 IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev L P N 962830 1 962830 2 962830 3 Page i of vi PAGE CONTROL CHART SECTION DESCRIPTION PAGE REV NO REVISION LOG vi 1 0 OVERVIEW H 1 1 The Manual 1 1 1 2 Product Information 1 1 1 3 System Configuration 1 2 1 4 Fuel Totalizer Configuration 1 3 1 5 F ADC2000 Argus Moving Map Configuration 1 3 2 0 FUEL AND AIRDATA SYSTEM SPECIFICATIONS J 2 1 Input Data Range 2 1 22 Output Data Range 2 1 2 3 Dimensions 2 1 2 4 Power Requirements 2 1 2 5 Output Data 2 2 2 5 1 Serial Output Data Parameters 2 2 2 5 2 ARINC 429 GAMA Output Labels 2 2 2 5 3 ARINC 429 Labels Associated with Switch Settings 2 4 2 5 4 ARINC 429 Labels Associated with Switch Settings 2 5 2 6 Limitations 2 6 2 6 1 Warm up Time 2 6 2 6 2 Supplemental Equipment 2 6 2 6 3 Static Pitot Source Error Correction SSEC PSEC 2 6 2 64 SSEC PSEC Listing 2 7 2 7 Part Numbering Scheme 2 11 2 8 Electrical Interface Specifications 2 8 1 Heading Interface 2 12 2 8 2 Fuel Flow Interfaces 2 12 2 8 2 1 Digital Fuel Flow 2 12 2 8 2 2 Sine Wave Fuel Flow 2 13 2 8 2 3 DC Voltage Fuel Flow 2 13 2 8 3 Baro Interface 2 13 2 9 Statist
56. Temp ALT Temp Variation Humidity Shock amp Vibration Magnetic Effect Power Input Voltage Spike AF Conducted Susceptibility Induced Signal Susceptibility RF Susceptibility RF Emission 5 UJ gt UU US UU UD IU gt OU Page 3 1 IM2830LG doc DIR 962830 IM2830 Shadin Rev F 4 0 INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 4 1 PLACING AN ORDER Please know the aircraft year and model number its serial number and the engine make and model number when you call to place orders Information on the fuel flow system previously installed in the aircraft and any communication interface RS232 RS422 and ARINC429 information may also prove useful We may request a wiring diagram of the aircraft s fuel flow system and transducer and or K factors IM2830LG doc DIR 962830 1 2830 Shadin Rev J 5 0 5 1 5 2 5 3 INSTALLATIONMANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 5 1 INSTALLATION PROCEDURE General The conditions and test required for TSO approval of this article are minimum performance standards It is the responsibility of those desiring to install the article either on or within a specific type or class of aircraft to demonstrate that the aircraft installation conditions are within the TSO standards The article may be installed only if installation of the article is approved by the Administrator A
57. Z gt oo amp D No correction MITSUBISHI MU 300 CESSNA CITATION 500 501 CESSNA 525 CESSNA 500 Citation 560 SN lt 259 Citation 560 SN gt 260 Citation 650 Sabreliner 65 WestWind 1124A LearJet 24 Raytheon Hawker HS 125 3A Falcon 20 F Falcon 20 C D E LearJet 25D Douglas DC 8 Beechjet 400 Boeing 707 321B Cessna Citation S550 Falcon 10 Falcon 50 Raytheon Hawker HS125 700A LearJet 35 LearJet 55 Sabreliner 60 SSEC Only Lockheed Jetstar Reserved for future DO NOT USE ALL 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 29 93 00 51 93 00 58 93 00 63 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up 93 00 63 and up IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev J P N 962830 1 962830 2 962830 3 Page 9 15 Stage 3 Loopback configuration Switch 1 is set to 3 to indicate that the stage 3 loopback is being performed SWITCH 2 K FACTOR TABLE SELECTION For F ADC 962830 1 and 962830 2 only 0 Standard K FACTOR Matrix 0 Table 2 in this manual 1 Alternate K FACTOR Matrix
58. actor Settings Tables Switch amp 2 selects the left K Factor Switch 3 amp 4 selects the right K Factor Due to possible fuel flow system peculiarities switches 1 amp 2 and switches 3 amp 4 do not necessarily need to be set to the same setting For a one engine system use switches 1 amp 2 For Analog units P N 962830 3 use the Analog K Factor Settings Table Switch amp 2 selects the main engine K Factor Switch 3 amp 4 selects the offset The offset is simply the value represented by switches 3 amp 4 in the Analog K Factor Settings Table on the following page For example if you wanted an offset of 0 the switch settings would be 0 0 If you wanted an offset of 416 the switch settings would be 0 1 If you wanted an offset of 1094 the switch settings would be 0 4 Configuration is now complete IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev G P N 962830 1 962830 2 962830 3 Page 10 2 Analog K Factor Settings Table Manufacturer Beech Beech Beech Beech EEN EA KUNI 0 0 Beech KingAirc90A 0 Beech KingAir 200 0 Beech 0 0 0 EA 1 I 2 I 2 I 2 Beech 2 Beech Beech 600 Beech Beech 750 3 l 0 0 0 2 0 3 4 0 0 Beech 6 0 Cessna Citation Ametek Gauge 393002 009 Cessna 0 Cessna Citation 0 Cessna Model 525 0
59. back Configuration Loopback Procedure 3 for S W Version 93 00 77 Stage 0 Loopback Configuration Stage 1 Loopback Configuration Stage 2 Loopback Configuration Stage 3 Loopback Configuration Loopback Procedure 4 for S W Version 93 00 82 Stage 0 Loopback Configuration Stage 1 Loopback Configuration Stage 2 Loopback Configuration Stage 3 Loopback Configuration Stage 4 Loopback Configuration Select No Delay 10 0 SETTING THE K FACTOR Setting the K Factor Table 1 Analog K Factor Settings Table 1 Table 2 Digital K Factor Settings Table 2 Matrix 0 Table 2 Digital K Factor Settings Table 2 Matrix 0 Table 2 Digital K Factor Settings Table 2 Matrix 0 Table 3 Alternate Digital K Factor Setting Table 3 Matrix 1 Indicates change since previous revision PAGE 9 1 9 2 9 3 9 3 9 4 9 6 9 6 9 9 9 10 9 11 9 11 9 12 9 14 9 15 9 16 9 16 9 17 9 19 9 20 9 21 9 22 10 1 10 2 10 3 10 4 10 5 10 6 Page 111 of vi REV IM2830LG doc DIR 962830 1 2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev L P N 962830 1 962830 2 962830 3 11 0 INSTALL DRAWINGS AND INSTALL KITS PARTS LISTS Drawing No Description Part Number 4028 394 Installation DWG ADC2000 Digital Fuel Flow P N 962830 1 4028 431 Installation DWG ADC2000 Sine Fuel Flow P N 962830 2 4028 432 Installation DWG ADC2000 DC Fuel Flow P N 962830 3 4028 005 Installation DWG OAT Probe Assembly Kit P N 681201 1 40
60. d In a twin engine the Airdata zeroes both fuel flows during the startup delay for each engine SPECIAL OPTIONS Only under special circumstance should SPECIAL OPTION 1 be selected Read the following paragraphs for a description of the special circumstance Because the IAS range on the AirData computer is valid from 20 to 350 knots ARINC 429 labels 206 and 210 are transmitted with NCD status and stop being transmitted almost simultaneously if the IAS is less than 20 knots In order to interface with certain avionics equipment which exhibit warnings if a valid IAS or TAS label is not received SPECIAL OPTION 1 was implemented When the AirData computer is configured with SPECIAL OPTION 1 the Arinc 429 labels 206 and 210 are transmitted with OK status and a value of zero knots if the actual IAS is less than 20 knots IM2830LG doc DIR 962830 IM2830 Shadin Rev G 10 0 INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 10 1 SETTING THE K FACTOR The process of setting the K Factor is needed to match the F ADC to the aircraft fuel flow systems characteristics To set the K Factor into the F ADC you must first determine whether it is an Analog Digital or Sine Fuel Flow unit P N FUEL FLOW TYPE 962830 1 Digital 962830 2 Sine Wave 962830 3 Analog Use the switch settings from the appropriate table to set the K Factor For Digital or Sine units P N s 962830 1 and 2 use the Digital K F
61. each stage The following figure shows the approximate switch positions Connectors End End Switches ARINC 429 Switch VIEW FROM END IM2830LG doc DIR 962830 IM2830 Shadin Rev J INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Loop back Procedure 1 for Software Version 93 00 16 93 00 29 Stage 0 Loopback Configuration Switch 1 is set to 0 to indicate that the stage 0 loopback is being performed SWITCH 2 Fuel Units and Engine Type g O m gt xo Q Q N Gallons Single Engine Liters Lbs 5 8 z Lbs 6 71 4 Kilograms Lbs 6 5 E n Lbs 6 3 s j not used 3 Gallons Twin Engine Liters 9 Lbs 5 8 Lbs 6 71 Kilograms Lbs 6 5 i Lbs 6 3 4 DO NOT USE 9600 BAUD Loran Input Type Trimble ARNAV Bendix or IIMorrow Apollo NMS2001 800 820 Garmin Northstar Foster IIMorrow 611 612 and 618 Shadin Flow Meter DO NOT USE Use this position to make selection on SWITCH 4 Other Loran Input Type Northstar 1200 BAUD Foster 1200 BAUD IIMorrow 611 612 618 1200 BAUD DO NOT USE Page 9 3 IM2830LG doc DIR 962830 IM2830 Shadin Rev J INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 9 4 Stage 1 Loopback Configuration Switch 1 is set to to indicate that the stage 1 loopback is being performed SWITCH 2 PALT Correction static pre
62. el Airdata System will make corrections to indicated airspeed by compensating for pitot source error The System does not provide true and absolute readings for all circumstances It makes no altitude corrections when the uncorrected IAS is below 100 knots and it makes no airspeed corrections when the uncorrected IAS is below 150 knots It does not account for other factors such as the current useful weight that contribute to static source error and pitot source error Rather the Fuel Airdata System performs calculations based solely on indicated airspeed and pressure altitude The SSEC PSEC corrections were derived from specific aircraft data referred to in section 2 6 4 To configure the Shadin F ADC for a specific aircraft model refer to section 9 IM2830LG doc DIR 962830 IM2830 Shadin Rev J INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 2 7 2 6 4 SSEC PSEC LISTING Beechcraft Beechjet 400 SSEC only Airplane Flight Manual BeechJet 400 Section 6 Performance Page 6 14 FAA approved 1 86 Altitude Correction Figure 6 8 Revision A9 14 92 Copilot System Boeing 707 321B Advanced SSEC Airplane Flight Manual Boeing 707 Section IV Performance Page 19 FAA approved 3 27 69 D6 1588 Altitude Calibration FLAPS UP Revision 2 4 69 Pilot amp Copilot PSEC Airplane Flight Manual Boeing 707 Section IV Performance Page 18 FAA approved 9 20 66 206 1588 Airspeed Calibration FLAPS UP P
63. ical Specifications 2 9 1 Mean Time Between Failures 2 14 Indicates change since previous revision IM2830LG doc DIR 962830 Shadin Rev L SECTION NO 3 0 4 0 5 0 6 0 7 0 8 0 INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 DESCRIPTION CERTIFICATION PLACING AN ORDER INSTALLATION PROCEDURE 5 1 5 2 F ADC Location Selection 5 3 Mounting the F ADC 5 4 Mounting the OAT Probe 5 5 Connection to the Fuel Flow Sensor 5 6 Connection to the Heading Source 5 7 Connection to the Pitot and Static Lines 5 8 Connection to the Navigation Management System 5 9 Connection to the Altimeter Baro Pot optional 5 10 Post Installation Checkout OPERATING INSTRUCTIONS INITIALIZATION MAJOR COMPONENTS OF THE SYSTEM Indicates change since previous revision PAGE 3 1 Page ii of vi REV Fl J F F H IM2830LG doc DIR 962830 1 2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev L P N 962830 1 962830 2 962830 3 SECTION DESCRIPTION NO 9 0 CONFIGURING THE AIRDATA 9 1 Configuring with ADSETUP User Manual 9 2 Configuring Manually Loopback Procedure 1 for S W Version 93 00 16 93 00 29 Stage 0 Loopback Configuration Stage 1 Loopback Configuration Loopback Procedure 2 for S W Version 93 00 51 93 00 71 Stage 0 Loopback Configuration Stage 1 Loopback Configuration Stage 2 Loopback Configuration Stage 3 Loop
64. ilot amp Copilot Cessna 500 SSEC only Airplane Flight Manual Cessna Citation Model 500 Section IV Performance FAA approved Aug 7 74 Altitude Correction Figure 4 7 Revision 53 Dated 11 Dec 85 Pilot amp Copilot system Page 4 17 1 Cessna 501 SSEC only Airplane Flight Manual Cessna Citation I SP Model 501 Section IV Performance FAA approved Altitude Correction Figure 4 5 Original Pilot amp Copilot system Page 4 15 NOTE Uses same Hardware configuration as Cessna 500 Cessna 525 SSEC only Airplane Flight Manual Model 525 Altitude Correction Rept FT525 4 Pilot amp Copilot system Page 47 Cessna 550 SSEC only Airplane Flight Manual Cessna Citation II Model 550 Section IV Performance FAA approved Altitude Correction Figure 4 5 Original Pilot amp Copilot system Page 4 15 Cessna 560 SSEC only Airplane Flight Manual Model 560 S N 259 amp Below Section IV Performance FAA approved Altitude Correction Figure 4 5 Original Pilot amp Copilot system Page 4 17 IM2830LG doc DIR 962830 IM2830 Shadin Rev J INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 2 8 SSEC PSEC LISTING Continued Cessna 560 SSEC only Airplane Flight Manual Model 560 S N 260 amp Up Section IV Performance FAA approved Altitude Correction Figure 4 5 56FMA 00 Pilot amp Copilot system Page 4 19 Cessna Citation S550 SSEC only Airplanes 0115 through 0160 Except Airplanes Incorpora
65. ince previous revision Page v of vi DATE REV 3 11 03 B 2 14 05 B 2 14 05 B 2 14 05 A 2 14 05 A 1 17 05 A 2 14 05 A 2 14 05 A 2 14 05 A 1 17 05 A 1 17 05 2 14 05 2 14 05 1 17 05 IM2830LG doc DIR 962830 IM2830 Shadin Rev L INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page vi of vi REVISION LOG 6 8 95 SES Baseline release 6 9 97 KCL 4 Stage loop back procedure report to 4028C Expand index Correct manual rev Correct manual rev D 6 23 97 1 8 98 Miscellaneous updates format change 15 UT Added new sections 5 9 5 10 Switch 4 table page 9 10 Special Options page 9 11 updated table 1 page 10 2 updated Dwg 4028 944 and included Dwg s 4028 A29 4028 A80 and 4028 A82 and new parts list IK9630 1 Added Bendix B amp Garmin 430 530 Format G to page 9 7 Added one more Ragen Indicator Transmitter to page 11 32 Added Garmin 430 530 to page 1 1 Added ARINC Label 234 amp 235 to page 2 4 Changed OAT Install kit to 681201A 1 on page iti Changed pages 11 11 13 16 21 amp 29 Added Allied Signal to page 2 5 Moved Raytheon Hawker HS 125 to page 2 9 Added 2 816 fitting to page 5 5 Changed page iv to reflect change to 4028 943 Page iii and 1 3 changed to include Dwg 4028 B94 Page 2 1 changed for OAT tolerance IVS to 10 000 fpm and Pitot amp IAS set to 20 knots for low speed
66. ived by the ADC2000 TNL 8100 with total fuel flow label 244 Collins FMS 800 100 ms rate Allied Signal Mk GPWS 50 ms rate Allied Signal Mk VI amp VIII 50 ms rate for ARINC software version 71 73 01 and up IM2830LG doc DIR 962830 IM2830 Shadin Rev J 2 6 INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 2 6 Limitations 2 6 1 Warm up time The Fuel AirData System requires a warm up time that varies with ambient temperature 70 C ambient 5 minutes warm up required 15 C ambient 10 minutes warm up required 20 C ambient 15 minutes warm up required 40 C ambient 20 minutes warm up required If the ADC has been configured for a fuel flow delay fuel flow and thus fuel used information shall be unavailable at startup for the duration of the selected delay 2 6 2 Supplemental equipment All Shadin F ADC s and ADC s are not designed to replace factory installed airdata fuel flow systems or other gauges They are not intended to be used as a primary system to drive altimeters or airspeed indicators The F ADC fuel section is not a fuel quantity system and therefore reports only what was manually entered by the operator 2 6 3 Static Source Error Correction SSEC Pitot Source Error Correction PSEC For certain models of aircraft the Fuel Airdata System will make corrections to pressure altitude by compensating for static source error For some of these models the Fu
67. line voltage of 11 8 Vrms Synchro Leg Input Impedance H 10 kohm X 17 kohm Y 17 kohm Fuel Flow Interfaces There are three basic types of fuel flow interfaces supported The interface type is defined in the ADC2000 part number Refer to section 2 7 for the part numbering scheme Digital Fuel Flow Interface The are two possible installations for the digital fuel flow interface the first is that the ADC is connected to a dedicated fuel flow transmitter and the second is that the ADC is connected into a fuel flow system Dedicated Transmitter Fuel Flow Interface Input Impedance 47 kohm Shared Transmitter Under normal operating conditions the voltage swing the signal amplitude can be calculated using Vs RAR 47 k 5 Vdc 0 5Vdc where is the input impedance of the aircraft fuel flow indicator For example with an input impedance 1 Mohn the voltage swing Vs 4 27 Vdc With the fuel flow information is encoded in frequency and not amplitude the loading effects do not produce an error provided the aircraft indicator can detect the signal transitions IM2830LG doc DIR 962830 IM2830 Shadin Rev J INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 2 13 2 8 2 2 Sine Wave Fuel Flow Interface 2 8 2 3 The interface source signal amplitude varies with frequency Listed in the table below are the input impedance vs peak to peak input voltages of the ADC2000 under normal operati
68. ll work must conform to AC 43 13 1B F ADC Location Selection The Fuel AirData Computer should be mounted in a dry temperature stable location with enough distance from motors pulse generating equipment relays and cables carrying high DC or AC current to avoid interference with low level signals of the OAT and fuel flow Refer to aircraft specific installation drawings if available for correct installation installation location The equipment may be installed in a temperature controlled or uncontrolled environment and in a pressurized or unpressurized location In considering the location keep in mind that the F ADC requires signals from the fuel flow the OAT probe heading system and the pitot and static lines Placement in the front section of the aircraft is favorable in order to avoid running all of these signals to the tail of the aircraft Mounting the F ADC The computer should be mounted per Drawing 4028 394 431 432 and Drawing 4028 395 using the recommended hardware Any orientation is acceptable Make sure that the computer is not the lowest point in the pitot and static system to reduce the chances of collecting moisture or water in it Form a water trap if necessary IM2830LG doc DIR 962830 IM2830 Shadin Rev J 5 4 INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 5 2 Mounting the OAT Probe 1 Refer to Drawing 4028 005 and OAT Probe Assy Kit P N 681201 1 Use the s
69. ndicators Revision 24 Lear Jet 24 SSEC only Airplane Manual LearJet Model 24 Section IV Performance FAA approved 3 17 66 Altitude Correction Figure 4 10 Revised 7 19 68 Pilot amp Copilot system Page 4 16 LearJet 25D SSEC only Airplane Manual LearJet 25D F AFM Performance FAA approved 10 14 86 Altitude Correction Figure 5 10 FM 018 Release A Copilot system Page 5 18 LearJet 35 SSEC only Flight Manual LearJet 35 Normal System Flaps up Gear up Page 5 18 FAA approved 4 30 76 Altitude Position Correction Figure 5 10 Reissued 2 25 81 Pilot s Altimeter STBY amp Copilot s Altimeter LearJet 55 SSEC only Gates LearJet 55 APM Performance Data Flaps up Gear up Page 5 20 FAA approved 3 17 81 Altitude Position Correction Figure 5 11 Change 13 Lockheed Jetstar SSEC only Airplane Flight Manual Performance Data Weight 32 000 Lb Clean Configuration Leading Edge Flaps up Trailing Edge Flaps up Landing Gear up Page 4 25 FAA approved 12 14 76 Altimeter Installation Correction Figure 4 15 IM2830LG doc DIR 962830 IM2830 Shadin Rev J INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 SSEC PSEC LISTING Continued Mitsubishi MU 300 SSEC only Airplane Flight Manual Diamond IA Section 6 Performance FAA approved Jan 11 84 Altitude Correction Copilot system Raytheon Hawker HS 125 3A SSEC only Airplane Manual Document No H S 1 10 CAA Approved Static Po
70. ng conditions Input Impedance Input Voltage 2 Mohm Input voltage less than or equal to 1 0 Vpp 24 5 kohm Input voltage greater than 1 0 Vpp Maximum Input Voltage 10 Vpp DC Voltage Fuel Flow Interface The DC voltage fuel flow interface has a differential input The specifications under normal operating conditions are listed below Positive input greater than 100 Mohm Negative input greater than 100 Mohm Maximum Input Voltage 10 2 Vdc Baro Interface The baro interface requires a three wire connection to the potentiometer housed in the aircraft altimeteri The three connections are the high side low side and wiper The specifications under normal operating conditions are listed below Input Impedance high side greater than 100 Mohm Input Impedance low side greater than 100 Mohm Input Impedance wiper greater than 100 Mohm Maximum Input Voltage 12 i The altimeters supported are listed in section 9 2 and are dependent upon the ADC2000 software version level IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev J P N 962830 1 962830 2 962830 3 Page 2 14 2 9 Statistical Specifications 2 9 1 Mean Time Between Failures MTBF 17 660 hours IM2830LG doc DIR 962830 IM2830 Shadin Rev F 3 0 INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 CERTIFICATION TSO C106 C44a Environmental Categories RTCA 160B
71. nly Note that for single engines all fuel flow types should use left side inputs only Install the transducers according to the engine STC using Drawing 4028 423 Freq Option to connect the fuel flow transducer to the computer If the aircraft is equipped with a digital fuel flow transducer P N 680501 use Drawing 4028 423 High Level Option and the STC drawing covering the installation Before hooking to an existing fuel system in a turbine or jet application consult all installation drawings contained in this manual the aircraft is equipped with a DC fuel flow system use Drawing 4028 423 DC Fuel Flow Option and the STC covering the installation If the aircraft is equipped with a sine wave pickup coil type of fuel flow transducer use Drawing 4028 423 Sine Wave Signal Use the Converter P N 631201 Note that if this is a new installation use part number 962830 2 ADC2000 Install the sine to square converter P N 631201 between the fuel flow transducer and the F ADC as indicated on the drawings Make sure that the system is initialized with the proper transducer K factor for a digital or sine systems and with the proper airframe make and model for the DC fuel flow systems See the attached tables in section 10 0 Consult section 11 for specific aircraft installation wiring drawings IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev J P N 962830 1 962830 2 962830 3 Page
72. r source MS20825 Tee TE AN910 SE ANSTO ADC2000 MS27404 gt ra pt IM2830LG doc DIR 962830 1 2830 Shadin Rev J 5 8 5 9 5 10 INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 5 6 Connection to the Navigation Management System 1 Use the appropriate installation wiring diagram to connect the Fuel AirData Computer s Connector J2 to the navigation management system A 2 amp Circuit breaker should be used for powering the system Mark the C B F ADC by engraving painting or other approved method Refer to specific aircraft installation drawings if available for correct circuit breaker location Keep the cables away from power cables DME and transponder cables Refer to the specific Nav Receiver Installation Manuals for details If the ARINC 429 output is used refer to the digital EFIS or flight management installation manual Connection to the Altimeter Baro Pot optional 1 Use the Installation wiring diagram 4028 A82 to connect the altimeter to of the AirData computer Remember to select the correct altimeter type in the software configuration See section 9 in this manual Post Installation Checkout l 2 The pitot and static system must be checked for leaks Operate the Navigation Management System select the altitude and airspeed pages Use the static and pitot test system to check the accuracy of the readout in the Navigation
73. sition Error Correction to Altimeter Raytheon Hawker HS125 700A SSEC only 125 Crew Manual First Officer Section 2 Flaps Retracted Correction to Altimeter Revision G 4 77 Figure 6 Sabreliner 60 SSEC only Sabreliner Pilot s Manual SR 75 064 Weight 16 000 Lb 9 1 76 Altitude Calibration Sabreliner 65 SSEC only Pilots Manual SR 78 028 Altitude Correction Pilot amp Copilot system Westwind 1124A SSEC only Airplane Flight Manual 1124A Section V Performance CAA approved Altitude Correction Figures 5 13 Flaps 0 Copilot system NOTE Gross Weight averaged at 18 750 158 Page 2 10 Figure 6 8 Page 6 20 Section 5 Figure 5 4 Page 13 Page 2 30 Static Position Figure 7 2 Figures 7 1 through 7 5 265 65 7 31 32A 33 Pages V 25 IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev J P N 962830 1 962830 2 962830 3 Page 2 11 2 7 Part Numbering Scheme P N 962830 X pu ADC2000 D SUB Connector Fuel Sensor Type X 1 Frequency Level Interface X 2 Sine Wave X 3 DC IM2830LG doc DIR 962830 IM2830 Shadin Rev J 2 8 2 8 2 1 INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 2 12 Electrical Interface Specifications The specifications for the interfaces heading fuel flow and baro are listed in this section 2 8 1 Heading Interface The heading interface follows the ARINC 407 standard
74. ssure correction by model 0 None 1 MU 300 2 Cessna Citation 501 3 Cessna 525 4 Cessna 550 SF DO NOT USE SWITCH 3 Loran Output Type 0 Format Z Trimble and Garmin 1 Format X ARNAV 2 Generic 3 Surveyor 4 Bendix Bendix King and F ADC without Baro Interface 5 Bendix D Bendix King and F ADC with Baro Interface 6 Shadin Morrow GX50 55 60 TF DO NOT USE 4 Altimeter Selection for Baro DC Input 0 None 1 Type 1 2 2 3 Type 3 4 Type 4 5 Types 6 Type 6 7 Type 7 8 not used IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev J P N 962830 1 962830 2 962830 3 Page 9 5 ALTIMETER TYPES Type 1 Kollsman PD 44929 935 done for Cessna 525 Type 2 Bendix King KEA 130A and 346 Type 3 ARINC 575 3 specification for ratio to Altitude Correction calculation Kollsman IDC 28007 427 429 Kollsman IDC 28704 A1001 A2001 A4001 B4001 C4001 D1001 D2001 D4001 D4101 E2101 F2101 and 495 Type 4 Kollsman IDC 28711 621 thru 624 Type 5 Kollsman IDC 28007 431 433 Honeywell Sperry BA 141 Type 6 Kollsman IDC 28711 500 series and 600 series Type 7 Kollsman IDC 28711 065 and 066 Type 8 Reserved for future use DO NOT USE Type 9 Aerosonic 10420 11968E IM2830LG doc DIR 962830 IM2830 Shadin Rev J INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 96283
75. ters Lbs5 8 1656 71 5 Kilograms 166 5 i i Lbs 6 3 i DO NOT USE M HO m gt DC JA Q amp D SWITCH 3 9600 BAUD Loran Input Type Trimble 0 1 ARNAV 2 Bendix or IIMorrow Apollo NMS2001 800 820 3 Garmin 4 Northstar 5 Foster 6 611 612 and 618 7 Shadin Flow Meter 8 E DO NOT USE F Use this position to make selection on SWITCH 4 SWITCH 4 Other Loran Input Type 0 Northstar 1200 BAUD 1 Foster 1200 BAUD 2 I IMorrow 611 612 618 1200 BAUD 3 F DO NOT USE Page 9 11 IM2830LG doc DIR 962830 IM2830 Shadin Rev J INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 9 12 Stage 1 Loopback Configuration Switch 1 is set to to indicate that the stage 1 loopback is being performed SWITCH 2 OAT Probe 0 Shadin OAT Probe 1 ARINC 575 DO NOT USE 2 Rosemount 500 Q DO NOT USE 3 DO NOT USE SWITCH Loran Output 0 Format Z Trimble and Garmin 1 Format X ARNAV 2 Generic 3 Surveyor 4 Bendix Bendix King and F ADC without Baro Interface 5 Bendix D Bendix King and F ADC with Baro Interface 6 Shadin Morrow GX50 55 60 7 Bendix fuel only 8 Garmin G 9 Do Not Use SWITCH 4 Altimeter Selection for Baro DC Input 0 None 1 Type 1 2 Type 2 3 Type 3 4 Type 4 3 5 6 6 7
76. ting SBS550 32 7 and Airplanes 0001 through 0114 Incorporating SBS550 32 1 but not SBS550 32 7 Section IV Performance Standard Charts Pages 4 17 4 18 FAA approved Altimeter Position Correction Figure 4 5 Revision 37 Pilot amp Copilot Douglas DC 8 SSEC Airplane Manual Douglas DC 8 Section IV Performance Page 20 FAA approved Altitude Correction DAC 33161 10 1 66 Pilot amp Copilot system PSEC Airplane Manual Douglas DC 8 Section IV Performance Page 11 FAA approved Airspeed Correction DAC 33161 10 1 66 Pilot amp Copilot system Falcon 10 SSEC only Airplane Flight Manual Section 6 Performance 7 Position Error Page 6 27 FAA approved 10 17 73 Position Error Revision 14 6 6 78 Pilot amp Copilot Falcon 20 C D E SSEC only Maintenance Instruction Manual 34 18 03 Page A48 Sept 1 77 Altitude Correction CS 143 Copilot system Falcon 20 F SSEC only Maintenance Instruction Manual 34 18 03 Section 5 DTM30528 Altitude Correction Subsection 20 DGAC Approved Copilot system Page 4 IM2830LG doc DIR 962830 IM2830 Shadin INSTALLATION MANUAL FUEL AIRDATA COMPUTER Rev J P N 962830 1 962830 2 962830 3 Page 2 9 SSEC PSEC LISTING Continued Falcon 50 SSEC Airplane Flight Manual Section 5 Performance Page 5 25 2 DGAC approved Copilot for A C equipped with one ADC Revision 24 PSEC Airplane Flight Manual Section 5 Performance Page 5 25 2 DGAC approved Pilot normal and Copilot MACH I
77. upplied stiffener to support the probe Keep the probe away from transmitting antennas and static ports of autopilots to avoid interference 2 5V is supplied to OAT probe from red wire J1 15 for P N 962830 X OAT signal is the white wire from J1 14 for P N 962830 X The lead wire to the computer should be shielded and terminated at the ADC2000 only 3 The sun shield must be installed for proper indication of OAT 4 For single engine installation avoid mounting the OAT probe on the belly of the aircraft to avoid erroneous reading due to the presence of hot exhaust gases 5 Below is an OAT to C temperature conversion chart for use if testing the OAT POAT C OAT ec Input ya 4205 0 293 gt 5 23 P 0 263 30 303 40 23 o 23 313 0 29 o 323 1 C 1 pA IM2830LG doc DIR 962830 IM2830 Shadin Rev J 55 INSTALLATION MANUAL FUEL AIRDATA COMPUTER P N 962830 1 962830 2 962830 3 Page 5 3 Connection to the Fuel Flow Sensor 1 10 If the aircraft is not equipped with a fuel flow source refer to the STC covering the installation of the fuel flow transducer on the engine When connecting to any fuel transducer Shadin recommends using a 3 conductor 22 gauge shielded wire with the shield terminated at the Airdata o

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