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1. COADNMAPWNKCTMUADWPFPUOAANDUNUSRWNYN O d CORRECTION For SSEC PSEC Select 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 5550 Falcon 10 Falcon 50 Raytheon Hawker HS125 700A LearJet 35 LearJet 55 Sabreliner 60 SSEC Only Lockheed Jetstar Reserved for future DO NOT USE Shadin Avionics Page 9 19 F ADC Software Version 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 IM2830SG doc DIR 962830 1M2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY 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
2. SWITCH 4 0 1 2 3 F Gallons Single Engine Liters Lbs 5 8 i Lbs 6 71 Kilograms h Lbs 6 5 Lbs 6 3 not used i Gallons Twin Engine Liters Lbs 5 8 Lbs 6 71 Kilograms Lbs 6 5 Lbs 6 3 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 16 IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 9 17 Stage 1 Loopback Configuration Switch 1 is set to 1 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 C 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 B fuel only 8 Garmin G 9 F Do Not Use SWITCH 4 Altimeter Selection for Baro DC Input 0 None 1 Type 1 2 2 3 3 4
3. 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 A 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 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 F ADceoo 2000 TU UR DIGIDATA WITH DC F CESSNA CITATION S25 JET SPP Eo 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 CARD i LEFT ENGINE FUEL 542 158 02 FLOW SIGNAL NOTES 1 THIS INSTALLATION APPLICABLE TO AIRCRAFT WITH FUEL MODULE PART NUMBER 542 1158 02 ONLY J E T MODULE NDS 542 1158 01 MAY BE CHANGED TO 542 1158 02 BY J E T 5 542 1158 7 K FACTOR IS 860 SET F ADC SWITCHES AS FOLLOWS SW1 D SWe 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 A JE T CARD PIN 12 CORRESPONDS TO FUEL MONITOR PIN X 1 0501 006 1 17 05 ZK CORRECTED NOTES 1 5 amp 6
4. 4028 431 DRAFTER DAP APPRDVED 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 P1 230051 CONN SHELL MALE 230054 CONN PINS MALE 230038 CONN HOOD 15 Pe 230050 CONN SHELL FEMALE a m 230055 CONN PINS FEMALE ac 230038 CONN HOOD 15 PIN TA J FEMALE 1 8 2 Je PINOUT J3 PINOUT 1e 28v DC POWER INPUT 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 85 422 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 X 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 BARD BARD lt gt Signo 5V 1 2 3 4 5 6 7 8 9 ARGUE o o Q WY S OO 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 KCL UP
5. 7 0 0 1580 0 Leardet Model 36 5V 0 2 o o 11540 0 Learlet Model36 10V o 8 o o 23080 o Boeing Boeing73730 0 9 o 3 1790 0 British Aero BAEATP 0 7 0 o 15380 0 British Aero 125 800 0 A o o 8240 378 British Aero_ 55 0 B o o 1040 0 Canadian CLO0 0 F 0 o 650 0 Canadian CLO0 1 0 O 0 530 0 Domier 0028 1 1 0 650 0 Daussaut _ FALCON10 1 2 o o 154 0 Daussaut FALCON20 1 2 0 o 7690 0 TFE 371 1 2 0 790 0 Sweamgen MERLIN 0 4 0 o 340 0 Gulfstream GULFSTREAM 1 3 0 o 290 0 Gulfstream GULFSTREAM III Aerospatiale pac Toe pars 31 ASTRA 1125 1 SESI Skani sa Sikorsky Sabre Table 6 Analog K Factor Settings IM2830SG doc DIR 962830 IM2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 10 3 oa gt N un N jr on ING 5000 6 5050 6 5100 6 5150 6 500 6 5250 1 7 5300 7 500 6 5650 6 500 6 580 6 5850 6 sasa 5050 6 600 6 6
6. KTS 45152 10 410 D SUB CONN TD ALTIMETER BARO 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 SHADIN 200 2000 RSe3e TX RSe3e RX SHADIN FUEL FLUW METER GARMIN 430 P4001 26 GARMIN OTES GARMIN 330 P5001 26 1 CONFIGURE SHADIN F ADC 200 2000 FOR FLOWMETER GARMIN CONFIGURE SHADIN FUEL FLOW METER I O FOR ON AIRDATA CONFIGURE GARMIN 430 530 1 0 FOR CHANNEL 1 TO SHADIN FADC AVIATION MICROFLO 91204XT 38D DIGIFLU DIGIFLO MINIFLO P N 91053XT P N 91053XP P N 91204X 4 MINIMUM SOFTWARE LEVEL ADC 200 2000 93 XX 77 GARMIN 430 2 17 GARMIN 530 2 02 DIGIFLO L 60 10 84 MINIFLO L 60 01 83 MICROFLO L 60 08 86 5 FUEL FLOW TRANSDUCER SIGNALS ARE CONNECTED TO THE SHADIN FUEL FLOW METER NO FUEL SIGNAL CONNECTED TO THE ADC 11047005 B 4 29 11 02117047 CHANGED SOFTWARE LEVEL NOTE 4 3711703 CHANGED TABLE TO NOTE 4 ADDED NOTE 5 UPDATED SW VERSIONS OF FLOW METERS 00087028 9712700 BASELINE RELEASE APPROVED EDJ FILE NAME 4028 B94BJ DWG DIRECTORY 4028 DRAWING DATE 8 21 00 SHAD INSTALLATION WIRING SHADIN F ADC200 2000 SHADIN FUEL FLOW INDICATORS TO GARMIN 430 530
7. Table 3 Vertical Airspeed Tolerance IM2830SG doc DIR 962830 1M2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 2 4 This table is used as the tolerance for MACH Number For values between table rows linearly interpolate between the adjacent table points ALTITUDE TOLERANCE FEET MACH MACH 0 3 012 4 012 5 010 6 0075 10 000 A 012 5 010 6 0075 7 005 20 000 A 012 5 010 6 0075 7 005 30 000 6 0075 T 005 80 005 90 005 95 0075 40 000 70 005 80 005 90 005 95 0075 50 000 75 005 90 005 95 0075 1 00 015 Table 4 MACH Tolerance IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 2 5 2 3 Dimensions including mounting rack Size 7 4 L x 4 3 H x 3 9 W Weight 36 oz 2 4 Power Requirements System Power required 28 VDC 1300 mA 14 VDC 900 mA 2 5 Output Data 1 Electric Format RS 422 or RS 232 2 ARINC 429 low speed See paragraph 2 5 3 for ARINC 429 output data capabilities 2 5 1 Serial Output Data Parameters Fuel Group Air Data 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 Indicated Air Speed IAS Baro Pressure Fuel Used Right Wind Directi
8. 64 gu E po e 8 6 1 262 77 ae m i ET esl 2 _ C IM2830SG doc DIR 962830 IM2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 10 6 N N SW2 s ME p E ien fuum Gu DECEM E asi Eph B EAE ED eed REQUE D D Esp NE ss 6 F NN pagi DESC XD et _ j p eee E Table 8 Matrix 1 Alternate Digital K Factor Setting software version 93 00 61 Note The Digital K Factor Settings for SW1 and SW2 are the same for SW3 and SW4 respectively IM2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830 XY SECTION 11 0 INSTALLATION DRAWINGS AND INSTALL KIT PARTS LISTS J1 PINOUT FUEL FLOW RIGHT POWER FUEL FLOW RIGHT SIGNAL GROUND HEADING Y HEADING X 26V 400Hz H 26V 400Hz Z
9. 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 SCI 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 Updated 4028 395 4028 944 IK9630 1 Parts List and section 2 2 55 Corrected N 7 25 06 Updated company logo amp formatting Added tolerance tables for IAS TAS PALT IVS and MACH Number in Section 2 2 updated ARINC Label Configuration Table in Section 2 5 2 6 04 07 DU added Software Certification Level to Part Numbering Scheme in Section 2 7 updated Certification Section 3 0 added Loopback Procedure 5 for S W Version 93 00 87 added Pin 11 to DWG No 4028 425 and updated 681201 1 amp IK9630 1 Parts Lists Released by ERN 0703 007 Added Antonov and Yak 40 SSEC information in Section 2 6 4 Corrected 6 19 07 RIW True amp Magnetic heading text from C to in Section 2 2 Changed software 93 00 87 amp above to 93 00 85 amp above in Sections 2 7 and Loopback Procedure 5 in section 9 2 he information in th
10. REV MINNEAPOLIS 55426 DRAWING 4028 B94 Shadin Avionics Filename Copy of 681201 1HP doc DIRECTORY 681201 1 Report 4032D ECO Date April 4 2007 ECO 0704 002 Rev H Release date 4 6 07 Sec IX Approved ZK Page 1 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 AN4703 4 or MS20470AD3 4 15 543216 1 OAT STIFFENER RING SHA 4032 082 20 670503 1 SHIELD Temp Sensor Assy 4005 265 25 670504 1 NUT Temp Sensor SHA 4005 266 30 670505 1 WASHER Flat OAT SHA 4005 303 35 670506 1 WASHER Shoulder OAT SHA 4005 304 40 681201 1 OAT PROBE SHA 4005 794 10 items Report N A ECO Date March 15 2007 Rev D Sec IX Page 1 of 1 PARTS LIST Drawing s N A P N QTY DESCRIPTION MFG 15 612826A TRAY Mounting ADC 2000 4028 T54 20 230019H 1 SPRING LATCH CLIP 4028 074 230050C CONN 15Pin D Sub F Crimp w Contacts POS M24308 2 2 RD15F10000 50 230051C CONN 15 Pin D Sub M Crimp w Contacts POS M24308 4 2 RD15M10000 50 35 230038 CONN Hood 15 Pin D Sub DA 24658 4 511002 SCREW 4 40 x 4 Phil HD SS 91772A106 512007 NUT 4 40 3 16 x 1 16 SS HNSP188 04C000 541001 WASHER 4 Split Lock SS 92147A005 31 items Shadin Avionics File Name COPY OF IK9630 1DP DOC DIRECTORY Install
11. 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 5 422 RS 485 FILE NAME 02117047 3 11 03 DEL PIN 9 ADDED GND Tiara 98037025 3726 98 SRB KCL BASELINE RELEASE 4028 028 9 46 P N ECO DATE BY APP D DESCRIPTION NOT TO SCALE SHEET 1 OF 1 4 APPROVED _ 1 1L j KCL 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 91053XT 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 SIGNALCS ARE CONNECTED TO THE SHADIN FUEL FLOW METER NO FUEL SIGNAL CONNECTION TO THE ADC S 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
12. 0 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 0 B 0 0 IM2830SG doc DIR 962830 IM2830 Shadin Avionics Rev 5 INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830 XY Loopback Procedure 5 for Software Version 93 00 85 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 0 Gallons Single Engine 1 Liters 2 Lbs 5 8 T 3 Lbs 6 71 4 Kilograms 5 Lbs 6 5 6 Lbs 6 3 A 7 not used i amp Gallons Twin Engine 9 Liters i A Lbs 5 8 i B Lbs 6 71 Kilograms D Lbs 6 5 E E Lbs 6 3 y F DO NOT USE SWITCH3 9600 BAUD Loran Input Type 0 Trimble 1 ARNAV 2 Bendix or IIMorrow Apollo NMS2001 800 820 3 Garmin 4 Northstar 5 Foster 6 IIMorrow 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 IIMorrow 611 612 618 1200 BAUD 3 F DO NOT USE Page 9 22 IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 9 23 Stage 1 Loopback Configuration Switch 1 is set to to indicate that the stage 1 loopback is being performed SWITCH 2 OAT Probe Type
13. 0160 Except Airplanes Incorporating 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 IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 2 11 SSEC PSEC LISTING Continued 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 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
14. 1 962830 2 and 962830 3 are identical to their corresponding Part Numbers with an A suffix software versions 93 00 85 and above except for their Software Certification Level and additional five SSEC corrections IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 2 15 28 Electrical Interface Specifications 2 8 1 2 8 2 The specifications for the interfaces heading fuel flow and baro are listed in this section Heading Interface The heading interface follows the ARINC 407 standard 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 2 8 2 1 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 R R 47 k 5 Vdc 0 5Vdc where R is the input impedance of the aircraft fuel flow indicator For example with an input impedan
15. 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 Supplemental equipment All Shadin F ADC s and ADC s are not designed to replace factory installed Air Data 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 Static Source Error Correction SSEC Pitot Source Error Correction PSEC For certain models of aircraft the Fuel Air Data System will make corrections to pressure altitude by compensating for static source error For some of these models the Fuel Air Data 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 Air Data System performs calculations based solely on indicated airspeed and pressure altitude The SSEC PSEC corrections w
16. 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 Air Data 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 IM2830SG doc DIR 962830 IM2830 Shadin Avionics Rev 5 10 0 INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830 XY 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 1Y Digital 962830 2Y Sine Wave 962830 3Y Analog Use the switch settings from the appropriate table to set the K Factor For Digital or Sine units P N s 962830 1Y and 2Y use the Digital K Factor Settings Tables Switches 1 amp 2 select the left K Factor Switches 3 amp 4 select 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 3Y use the Analog K Factor Sett
17. 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S 5 0 5 1 5 2 5 3 P N 962830 X Y Page 5 1 INSTALLATION PROCEDURE General The conditions and tests required for TSO approval of this article are minimum performance standards It is the responsibility of those installing this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards TSO articles must have separate approval for installation in an aircraft The article may be installed only if performed under 14 CFR part 43 or the applicable airworthiness requirements All work must conform to AC 43 13 1B or later Location Selection The Fuel Air Data 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 location The equipment may be installed in non pressurized and non controlled temperature locations 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
18. 4 5 5 6 Type 6 7 Type 7 8 DO NOT USE 9 Type 9 DO NOT USE B Type 11 C F DO NOT USE IM2830SG doc DIR 962830 1 2830 Shadin Avionics Rev S 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 AIR DATA COMPUTER P N 962830 XY Page 9 18 ALTIMETER TYPES Kollsman PD 44929 935 done for Cessna 525 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 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 IM2830SG doc DIR 962830 IM2830 Rev 5 INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830 XY 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 SWITCH 3 AND SWITCH 4 me RE RR RR Rr
19. 9 1 Each Part Number 962830 XYAir Data 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 communication port Following the steps as set forth in the user manual allow the Air Data to be configured See the ADSETUPF User Manual for more details IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 9 2 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 back harness is to tie RS 232 transmit and receive ports togeth
20. 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 9 27 Stage 4 Loopback configuration Switch 1 is set to 4 to indicate that the stage 4 loopback is 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 code selection 0 to SWITCH 3 OAT Tb CALIBRATION CODE SELECTION 0 Refer to calibration certificate for code selection 0 to SWITCH 4 OAT Tc CALIBRATION CODE SELECTION 0 Refer to calibration certificate for code selection 0 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 0 B 0 0 IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 9 28 SELECT NO DELAY Only under special circumstances should a fuel flow delay time other than No Delay 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 Air Data reporting a large jump in fuel used as well as a corresponding decrease in fuel remaining at engine startup This is n
21. 962830 1 and 962830 2 only 0 Standard K FACTOR Matrix 0 Table 7 in this manual 1 Alternate K FACTOR Matrix 1 Table 8 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 O Q 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 IM2830SG doc DIR 962830 1M2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 9 21 Stage 4 Loopback configuration Switch 1 is set to 4 to indicate that the stage 4 loopback is 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 code selection 0 to SWITCH 3 OAT Tb CALIBRATION CODE SELECTION 0 Refer to calibration certificate for code selection 0 to SWITCH 4 OAT Tc CALIBRATION CODE SELECTION 0 Refer to calibration certificate for code selection
22. 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 system and with the proper airframe make and model for the DC fuel flow system See the attached tables in section 10 0 Consult section 11 for specific aircraft installation wiring drawings IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 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 Collins Collins King King Sperry Sigma Sandel Heading Air 328A 2A HSI331A MCS 328A 5 KI525A KSG105 Gyro Tek SN3308 ARINC Data 2P1 1 65 P2 syn DG 407 P1 Comp 2 x 5 11 5 25 32 S t L A 25 Y 4 T 40 22 M 6 Z 7 3 U 24 12 t k K D 4 H 6 26 V 6 53 r H E 4 C 7 22 w 5 57 u f J H 4 The C wire AC common and the Z wire must be connected together at the source bootstrap IM2830SG doc DIR 962830 1M2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY 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 in
23. CONN PINS MALE 230038 CONN HOOD 15 Pe 230050 CONN SHELL FEMALE 230055 CONN PINS FEMALE 230038 CONN HOOD 15 PIN FEMALE 1 8 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 Signo 5 0501 032 D 3 21 05 WMP UPDATED TITLE BLOCK CH TITLE CORR PITOT STC LABEL LOCNS 9706 017 C 6997 WMP KCL UPDATE J33 0 00 0 00 0 0 0 9505 028 B 5 17 95 DAP SES REVERSE FF POLARITY gt S 9505 014 A 5 11 95 WMP SES ADD SPRING LATCH CLIPS 9419 005 18 7 94 DAP SES BASELINE RELEASE REV D DESCRIPTION z GROVES DO NOT SCALE DRAWING SHEET NC TX 85 422 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
24. FUEL FLOW TRANSMITTERS PART lt 25 1024 118 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 5 4 7 SHADIN MINNEAPOLIS 55426 INSTALLATION WIRING F ADC 200 2000 MET TO AERUSFATIALE ASIGNE DAUPHIN 0501 032 2 14 05 UPDATED TITLE BLOCK mm GENE er SS 4028 949 n ECU 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 Ji 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 DL LT FILE NAME 05017032 2 14 05 UPDATED TITLE BLOCK 4028 950AJ DWG 98037041 3 86 98 SRB KCL BASELINE RELEASE DIRECTORY DRAWING ND PN F DATE BY 2 DESCRIPTION SCALE idri 4028 950 AEROSPAT
25. SIGNAL 15 1 SIGNAL 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 P160 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 2 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 TEMP SENSOR SIGNAL GROUND DC GROUND TOTALIZER GROUND SIGNAL GROUND TOTALIZER OUTPUT FLOW TURBINE FROM PROB TEMP SENSOR 5 VDC LIGHT gt gt gt NOTES 1 FOR AIRCRAFT WITH FUEL FLOW INDICATOR PART NIS DSF 1549 e2 4 5 SEE TABLE FOR INDICATOR PINOUTS 2 K FACTOR IS 26 8 26 800 3 SET AIRDATA SWITCHES AS FOLLOWS SW1 C TRAYS SW2 7 SW3 S
26. Section 5 Document No H S 1 10 Static Position Error Figure 5 4 CAA Approved Correction to Altimeter Page 13 Raytheon Hawker HS125 700A SSEC only 125 Crew Manual First Officer Section 2 Flaps Retracted Page 2 30 Static Position Correction to Altimeter Figure 6 Revision G 4 77 Sabreliner 60 SSEC only Sabreliner Pilot s Manual SR 75 064 Weight 16 000 Lbs 9 1 76 Altitude Calibration Figure 7 2 Sabreliner 65 SSEC only Pilots Manual SR 78 028 Altitude Correction Figures 7 1 through 7 5 Pilot amp Copilot system 265 65 7 31 32A 33 IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 2 13 SSEC PSEC LISTING Continued Westwind 1124A SSEC only Airplane Flight Manual 1124A Section V Performance CAA approved Altitude Correction Figures 5 13 Flaps 0 Copilot system Pages V 25 NOTE Gross Weight averaged at 18 750 lbs Yak 40 SSEC only Airplane Flight Manual Sect 7 1 3 Page 7 Yak 40 1995 Altitude correction IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 2 14 27 Part Numbering Scheme P N 962830 XY ADC2000 D SUB Connector Fuel Sensor Type Software Certification Level X 1 Digital Y Blank RTCA DO 178A Level 2 X 2 Sine Wave Y A RTCA DO 178B Level D X 3 DC Note In Section 11 the Part Numbers 962830
27. 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 K FACTOR KNOWN SHADIN ADC200 2000 SWITCH SETTINGS PART NUMBER K FACTOR OFFSET AUX RATE OUTPUT 502 505 504 900 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 0 6 0 0 A THE FOLLOWING BEECH INDICATOR P NS POSSESS A KNOWN TO SHADIN ADC200 2000 SWITCH SETTINGS PART NUMBER K FACTOR OFFSET 5 1 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 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 PXPAS INSTALLATION WIRING F ADC 200 2000 W ANALOG F F TO BEECH KING AIR INDICATORS 0211 047 eas Gee Te __ _ D SUB CONNECTOR 9803 022 3 26 98 SRB KCL CHANGED NOTE 3 90 380009 5 FRO 26 150 416 REMOVE P N 9628 0 3 DWG RAUNG NO 9706 007 6 13 97 BASELINE RELEASE 4028 818 P N ECO 4 APPO DESCRIPTION SCALE NONE sr ert 4028 818 NOTES A FROM RIGHT ENGINE FF TRANSMITTER A FROM LEFT ENGINE FF T
28. 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 2 Use the Installation wiring diagram 4028 A82 to connect the altimeter to J1 of the Air Data computer Remember to select the correct altimeter type in the software configuration See section 9 in this manual Post Installation Checkout 1 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 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 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 inHg if the option is installed IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 9628
29. lt lt SHADIN AVIONICS FUEL AIR DATA COMPUTER ADC 2000 P NS 962830 INSTALLATION MANUAL REV S Shadin Avionics 6831 Oxford Street St Louis Park MN 55426 USA Sales 800 328 0584 Customer Service 800 388 2849 www shadin com P N IM2830 IM2830SG doc DIR 962830 1M2830 Shadin Avionics Rev S SECTION NO 1 0 2 0 INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830 XY PAGE CONTROL CHART DESCRIPTION REVISION LOG OVERVIEW 1 1 The Manual 1 2 Product Information 1 3 System Configuration 1 4 Fuel Totalizer Configuration 1 5 F ADC2000 Argus Moving Map Configuration FUEL AND AIR DATA SYSTEM SPECIFICATIONS 2 1 2 2 2 3 2 4 2 5 2 6 2 7 2 8 2 9 Input Data Range Output Data Range Dimensions Power Requirements Output Data 2 5 1 Serial Output Data Parameters 2 5 2 ARINC 429 Labels Associated with Switch Settings 2 5 3 ARINC 429 Labels Associated with Switch Settings Limitations 2 6 1 Warm up Time 2 6 2 Supplemental Equipment 2 6 3 Static Pitot Source Error Correction SSEC PSEC 2 64 SSEC PSEC Listing Part Numbering Scheme Electrical Interface Specifications 2 8 1 Heading Interface 2 8 2 Fuel Flow Interfaces 2 8 2 1 Digital Fuel Flow 2 8 2 2 Sine Wave Fuel Flow 2 8 2 3 DC Voltage Fuel Flow 2 8 3 Baro Interface Statistical Specifications 2 9 1 Mean Time Between Failures PAGE 2 8 2 8 2 8 2 8 2 9 2 14 2 15 2 15 2 15 2 1
30. tail of the aircraft Mounting the F ADC The computer should be mounted per Drawings 4028 394 431 432 and 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 IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 5 2 54 Mounting the OAT Probe 1 Refer to Drawing 4028 005 and OAT Probe Assy P N 681201 1 Use supplied stiffener to support the probe Keep the probe away from transmitting antennas and static ports of autopilots to avoid interference 5V is supplied to the OAT probe from red wire J1 15 for P N 962830 XY The OAT signal is the white wire from J1 14 for P N 962830 XY The lead wire to the computer should be shielded and terminated at the ADC2000 only The sun shield must be installed for proper indication of OAT 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 Below is an OAT to C temperature conversion chart for use if testing the OAT POAT C OAT C inputya OAT ec Input ya 60 23 20 25 20 293 5 23 J 263 J o 36 23 o
31. up 93 00 63 and up IM2830SG doc DIR 962830 1M2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY 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 7 in this manual 1 Alternate K FACTOR Matrix 1 Table 8 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 O Q 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 IM2830SG doc DIR 962830 IM2830 Shadin Avionics Rev S INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830 XY 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 Fuel Units and Engine Type m g O m gt xo oo N
32. zero knots if the IAS lt 20 knots 2 F Reserved DO NOT USE IM2830SG doc DIR 962830 1 2830 Shadin Avionics Rev S INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830 XY Page 9 11 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 m g O m gt xo oo N SWITCH4 0 1 2 3 F Gallons Single Engine Liters Lbs 5 8 i Lbs 6 71 Kilograms Lbs 6 5 Lbs 6 3 not used Gallons Twin Engine Liters Lbs 5 8 Lbs 6 71 Kilograms Lbs 6 5 Lbs 6 3 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 IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 9 12 Stage 1 Loopback Configuration Switch 1 is set to 1 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 DO NOT U
33. 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 C Bendix King and F ADC without Baro Interface 5 Bendix D Bendix King and F ADC with Baro Interface 6 Shadin S IIMorrow GX50 55 60 7 Bendix B 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 Type 3 4 Type 4 5 5 6 Type 6 7 7 8 DO NOT USE 9 Type 9 DO NOT USE B Type 11 C F DO NOT USE IM2830SG doc DIR 962830 1 2830 Shadin Avionics Rev S 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 AIR DATA COMPUTER P N 962830 XY Page 9 24 ALTIMETER TYPES Kollsman PD 44929 935 done for Cessna 525 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 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
34. 0 DC Fuel Flow 3 21 05 D P N 962830 3 4028 005 Installation OAT Probe Assembly Kit 2 14 05 C P N 681201 1 4028 395 Installation Mounting Tray ADC2000 8 01 05 C 4070 005 Installation Serial to Argus 5000 7000 Converter 2 14 05 B P N 937000 03 4028 423 Installation Wiring Fuel Air Data Computer ADC200 2000 to Fuel Systems 3 11 03 B 4028 425 Installation Wiring Fuel Air Data Computer ADC2000 to OAT Heading 5 17 07 B System 4028 944 Installation Wiring Loop Back Harness for F ADC200 2000 D Sub 9 19 05 C Connector 4028 945 Installation Wiring ADC2000 to Nav Receivers with ARINC 429 3 11 03 A 4028 946 Installation Wiring F ADC200 2000 to Navigational Receivers with RS 422 3 11 03 A RS 485 4028 947 Installation Wiring F ADC200 2000 Shadin Fuel Flow Indicators to 3 11 03 A Bendix King Nav Receiver 4028 948 Installation Wiring F ADC200 2000 and Shadin Converter to Eventide Argus 2 14 05 A 4028 A80 Label ADC200 2000 Access Cover P N 712801 2 14 05 A 4028 A82 Installation Wiring ADC 2000 D Sub Connector to Altimeter Baro Pot 3 11 03 C 4028 B94 Installation Wiring F ADC200 2000 Shadin Fuel Flow Indicators to Garmin 4 29 11 B 430 530 N A Parts List OAT Probe Assembly Kit 4 6 07 H P N 681201 1 N A Parts List Install Kit ADC2000 6 4 07 D P N IK9630 1 IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page v of vi 11 0 INSTALL D
35. 23 J 35 0 29 o 323 1 C 1 pA IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 5 3 5 5 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 Air Data only 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 2Y
36. 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 9 14 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 SWITCH 3 AND SWITCH 4 CORRECTION For SSEC PSEC Select F ADC Software Version 0 No correction ALL A Q S O G gt gt 2 QO tS d 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 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
37. 3 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 93 00 85 and up 93 00 85 and up 93 00 85 and up 93 00 85 and up 93 00 85 and up IM2830SG doc DIR 962830 1M2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 9 26 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 1Y and 962830 2Y only 0 Standard K FACTOR Matrix 0 Table 7 in this manual 1 Alternate K FACTOR Matrix 1 Table 8 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 ON A amp 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 IM2830SG doc DIR
38. 30 XY Page 6 1 6 0 OPERATING INSTRUCTIONS p 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 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 IM2830SG doc DIR 962830 1M2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 7 1 7 0 INITIALIZATION 1 The system requires initialization of the K factor for fuel flow transducers or aircraft model for DC fuel flow sensors Refer to Table 6 for analog fuel flow and Table 7 or Table 8 for digital fuel flow 2 Referto the specific Navigational Receiver Operator Manuals for the serial port set up IM2830SG doc DIR 962830 1M2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 8 1 8 0 MAJOR COMPONENTS OF THE SYSTEM 1 Nav Receiver Input Output 2 Fuel Air Data Computer 3 Outside Air Temperature Probe Shadin P N 681201 IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 9 1 9 0 CONFIGURING THE AIR DATA
39. 40 620 6440 6460 C 6480 D 600 6520 D 6540 D 6560 D 6580 660 6 L 7640 Table 7 Matrix 0 Digital K Factor Settings Note The Digital K Factor Settings for SW1 and SW2 are the same for SW3 and SW4 respectively IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 10 4 Table 7 Matrix 0 Digital K Factor Settings continued Note The Digital K Factor Settings for SW1 and SW2 are the same for SW3 and SW4 respectively IM2830SG doc DIR 962830 IM2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 10 5 Eu Table 7 Matrix 0 Digital K Factor Settings continued Note The Digital K Factor Settings for SW1 and SW2 are the same for SW3 and SW4 respectively 90000 pope A ME ue E A tme Be n 3 1 LB 2 Ea Wt 5 MCN NE lc 93h 12 EE NEN NND 1 9 s NES ER sr sama j sa 0 1 A rp I ole 5 pep a ae 9 1 2 A s ue 2 E He dr m
40. 5 2 16 2 16 2 16 2 17 Page i of vi IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page ii of vi SECTION DESCRIPTION PAGE NO 3 0 CERTIFICATION 3 1 4 0 PLACING AN ORDER 4 1 5 0 INSTALLATION PROCEDURE 5 1 General 5 1 5 2 F ADC Location Selection 5 1 5 3 Mounting the F ADC 5 1 5 4 Mounting the OAT Probe 5 2 5 5 Connection to the Fuel Flow Sensor 5 3 5 6 Connection to the Heading Source 5 4 5 7 Connection to the Pitot and Static Lines 5 5 5 8 Connection to the Navigation Management System 5 6 5 9 Connection to the Altimeter Baro Pot optional 5 6 5 10 Post Installation Checkout 5 6 6 0 OPERATING INSTRUCTIONS 6 1 7 0 INITIALIZATION 7 1 8 0 MAJOR COMPONENTS OF THE SYSTEM 8 1 IM2830SG doc DIR 962830 IM2830 Shadin Avionics Rev 5 SECTION NO 9 0 INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830 XY DESCRIPTION CONFIGURING THE AIR DATA 9 1 9 2 Configuring with ADSETUP User Manual 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 Loopback Configuration Loopback Procedure 3 for S W Version 93 00 77 Stage 0 Loopback Configuration Stage 1 Loo
41. 54 111 540 PPG OFFSET IS 0 A SET F ADC SWITCHES TO SW1 0 SW2 2 SW3 0 SW4 AN 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 ECO 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 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 GULL 151 909 001 2 K FACTOR IS 10 49 10 490 PPG OFFSET IS 0 AXSET AIRDATA SWITCHES AS FOLLOWS SW1 1 SW2 8 SW3 ZA 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
42. 6 1588 Airspeed Calibration FLAPS UP Pilot 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 IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 2 10 SSEC PSEC LISTING Continued Cessna 501 SSEC only Airplane Flight Manual Cessna Citation I SP Model 501 Section 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 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 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
43. 98037025 3 26 98 SRB KCL BASELINE RELEASE DATE DESCRIPTION SCALE DIGIDATA P1 P N 912802 13 RIGHT FUEL FLOW SIGNAL 15 LEFT FUEL FLOW SIGNAL GROUND SHADIN MINNEAPOLIS 55426 INSTALLATION WIRING F ADC200 2000 OR DIGIDATA WITH DIGITAL FF TO BOMBARDIER LEARJET 24 25 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 INDICATOR PART NOS 850590 1 850590 507 DSF1549 D5154 9 TRANSMITTER PART NOS 850590 513 850590 515 905 1 DR 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 ou 4028 2 P N REV DATE BY APP DESCRIPTION NOT TO SCALE 101 4008 939 _ 05017032 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 K FACTOR IS 11
44. C BARD WIPER FUEL FLOW LEFT POWER FUEL FLOW LEFT SIGNAL GROUND BARD BARD lt gt OAT OAT Signal 5 2 05017032 3 21 05 WMP UPDATED TITLE BLOCK CH TITLE CORR PITOT STC LABEL LOCNS 9803 054 D 3 26 98 SRB KCL CORRECT Jl DES FOR PIN AND PIN 9706 017 C 6 9 97 WMP KCL UPDATE J3 9505 014 5 11 95 SES ADD SPRING LATCH CLIPS 94127005 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 1e 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 m on Es x USE RS e3e UR RS 422 NOT BOTH SHADIN 15 55426 DRAFTER INSTALLATION DWG ADC2000 DIGITAL FUEL FLOW FILI 962830 1E J DWG DIRECTORY 962830 DO NOT SCALE DRAWING SHEET 1 OF 1 DRAWING NO 4028 394 P N 962830 1 MATING CONNECTORS P1 230051 CONN SHELL MALE 230054
45. DATE 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 962830 I 962830 3 REV D DESCRIPTIDN DO NOT SCALE DRAWING SHEET 1 OF 1 4028 438 A NOTES 1 REFERENCE P N 681201 1 PROBE ASSEMBLY KIT AVOID INSTALLING 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 A 5 7 dri AIRCRAFT FUS DRI 0 3598 23 64 1 00 UNTING H DRAVING DATE MON ARE IN oder 522A DIIV 55426 t 0 01 INSTALLATION 05017032 2 14 05 WMP UPDATED TITLE BLOCK amp NOTE 4 ADDED TO TITLE 0 1 PROBE ASSEMBLY KIT 01117001 B 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 M A 555 BASELINE RELEASE P N681201 1 T EVITE APPD DESCRIPTION 101 4028 005 NOTES USE 6 MOUNTING HARDWARE 2 DELETED 3 USE THIS DRAWING TO INSTALL SHAD
46. DD PC 425 0098 4028 909BJ DWG 97117051 1 8 98 DMD KCL BASELINE RELEASE DIRECTORY DRAWING PN 5 DATE APPD DESCRIPTION DO sce seer 4028 909 B J50 P50 GND 8 lD E04A20N E08A20 08 20 SIGNAL E06A20 06 20 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 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 SET F ADC SWITCHES AS SIGNAL F E16A20 U 16 20 5 3 0 SW4 0 PROGRAM DIGIDATA FOR E LEFT K FACTOR RIGHT GND 7 E14A20N K FACTOR 16 270 PPG LEFT OFFSET RIGHT OFFSET 0 IND 15 FUEL FLOW INDICATOR SHADIN MINNEAPOLIS 55426 DRAFTER INSTALLATION WIRING F ADC200 2000 OR DIGIDATA WITH DC FF TO T 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 Pri DRAWING NU 98037025 3 26 98 SRB KCL BASELINE RELEASE 4008 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 2 14 05 UPDATED TITLE BLOCK 9803 0065 3 26 98 SRB KCL BASELINE RELEASE ECO
47. ETER 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 IM2830SG doc DIR 962830 IM2830 Shadin Avionics Rev S Loopback Procedure 2 for Software Version 93 00 51 93 00 71 INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830 XY Stage 0 Loopback Configuration Switch 1 is set to to indicate that the stage 0 loopback is being performed SWITCH 2 Fuel Units and Engine Type m m gt N SWITCH4 0 1 3 F Gallons Single Engine Liters Lbs 5 8 i Lbs 6 71 Kilograms h Lbs 6 5 Lbs 6 3 not used i Gallons Twin Engine Liters Lbs 5 8 Lbs 6 71 Kilograms Lbs 6 5 Lbs 6 3 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 Inp
48. Global GNSXC LS 2 HUD Heads Up Display for Flt Visions 3 4 EFIS40 50 5 ASINC Airshow Cabin Display 6 Trimble 8100 No label 275 7 TNL 8100 8 Collins FMS 800 100 ms rate 9 Mk VII GPWS 50 ms rate A Mk VI amp VIII 50 mSec rate 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 Long Range Nav function of Honeywell SPZ 5000 Flight Guidance EFIS System installed on the Cessna Citation Jet Aircraft 1 Bendix to Global Cabin Info System installed on the Cessna Citation Jet Aircraft 2 Reserved 3 8100 4 Bendix King EFIS 40 50 5 ASINC Airshow 6 8100 except no label 275 Use when there is no serial navigation data being received by the ADC2000 7 NL 8100 with total fuel flow label 244 8 Collins FMS 800 9 Allied Signal Mk GPWS 50 ms rate A Allied Signal Mk VI amp VIII 50 ms rate for ARINC software version 71 73 01 and up IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 2 8 2 6 Limitations 2 6 1 Warm up time 2 6 2 2 6 3 The Fuel Air Data 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
49. IALE 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 5 5 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 R SIGNAL 7 R SIGNAL qo c 13 R SIGNAL LEFT ENGINE FF INDICATOR ENGINE FUEL es FLOW 1 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 TRANS
50. IN P N 612826B 612826A OR 612826 MOUNTING TRAY DIMENSIONS ARE 8 Nos Ai SHADIN MINNEAPOLIS 55426 ah ee INSTALLATION MOUNTING 0507 053 f 8 1 05 ZK NOTE 3 mu XXxx 30 005 SES 0501 032 B 3 3 05 PAB WMP DELETED NOTE 2 amp 10 DIMENSIONS ADDED NOTE 3 0211 047 2 7 03 BAL ADDED DIMENSIONS MATERIAL N A DIRECTORY 9512 017 12 13 95 WMP SES BASELINE RELEASE TRAY ADC2000 MATING CONNECTOR SHADIN P N 230036 17 04155 SHADIN P N 230038 HOOD DA 246 SELECTOR TABLE RSe3e RX TIE J17 TO RS422 DEFAULT JUMPER REQ D SINGLE ENGINE J1 7 TO TWIN ENGINE DEFAULT NO JUMPER gt 3 05 3 24 WEIGHT 8 POWER CONSUMPTION 210 mo 6 28 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 8 14 TU 28 V DC POWER IN 9 10 SIG
51. Kits ECO 0703 007 Release Date 6 4 07 Approved DU Part 1 9630 1 Description INSTALL KIT ADC2000 DESIGNATION COMMENTS PART NUMBER PART NUMBER PART NUMBER PART NUMBER PART NUMBER ADC 200 2000 90 380009 2 101 384153 1 900 900 900 D SUB CONNECTOR OR OR ne 1 2 7 8 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 7 7 f FX PART NUMBER PART NUMBER PART NUMBER PART NUMBER PART NUMBER m 90 380009 2 101 384153 1 900 900 PC900 XAXXXXPH 2 OR OR 1 6 1 2 7 8 1 2 1 8 0 m 90 380009 5 101 384153 3 CURVED FACE FLAT FACE CURVED FLAT FACE nies 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 PC900 XAXXXXPH XXO IS NOT SUPPORTED THE AUXILIARY RATE OUTPUT OF THIS UNIT IS 0 1 mA INDICATOR P NS THAT END
52. METER SW VERSIONS meee RW MG DATE DESCRIPTION SCAL seer 4028 94 F ADC200 2000 P N 962810 P N 962820 X gt X 1 P N 962830 X NAVIGATIONAL RECEIVER gt RS232 RX E RS422 RX IL RS422 RX SHADIN CONVERTER P N 937000 03 EVENTIDE ARGUS P N 5000 RS422 RX RS422 RX AA P N 7000 KID RSe3e INPUT HI RSe3e INPUT LOW 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 _ obf f SHADIN CONVERTER TO EVENTIDE ARGUS 05017032 2 14 05 WMP UPDATED TITLE BLOCK 40287948A J DWG 98037025 3 26 98 SRB KCL BASELINE RELEASE DIRECTORY DRAWING NO P N F DATE BY APPD DESCRIPTION NOT TO SCALE torr 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
53. MITTERS SEE TABLE FOR INDICATOR WIRING INDICATOR PART CRAGEN 3265013 0601 w TRANSMITTER PART ND CRAGEN 3268011 0101 INDICATOR PART 3265013 0801 3265013 1201 w TRANSMITTER PART RAGEN TFF 2905 9 OR PIPER P N 489 487 ENSET AIRDATA SWITCHES AS FOLLOWS SW1 1 SWe 1 SW3 0 SW4 0 A PROGRAM DIGIDATA FOR LEFT K FACTOR RIGHT K FACTOR 46 160 PPG LEFT OFFSET RIGHT OFFSET 0 SHADIIV MINNEAPOLIS MN 55426 DRAFTER INSTALLATION WIRING F ADC 200 2000 AFER 05017006 C 1 17 05 PAB ZK ADD IND 3265013 0801 amp RAGEN P N TABLES OR DIGIDATA WITH DC FF PIPER 00017016 B 1 31 00 LJM EDJ IND 3265013 1201 XMTR 2905 9 NOTE 1 9901 015 1 20 99 DMD KCL ADD P NS 9628304 3 5 5 962830 3 5 5 9808 012 877798 BASELINE RELEASE CHEYENNE PA31T 4028 A29 4058 DWG
54. NAL GROUND l 5422 RX SHADIN ADC 12 5422 RX USE RS 232 OR RS 422 13 RS232 RX NOT BOTH 14 RS232 TX TO ARGUS 5000 7000 15 POWER GND 0501 032 B 2 14 05 PAB WMP UPDATED TITLE BLOCK CONVERTER WAS TXMTR 9801 025 10 12 98 DMD PG ADDED 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 SHADIN MINNEAPOLIS MN 55426 pe INSTALLATION SERIAL TO ARGUS 5000 7000 CONVERTER DRAWNG NO REV REV DATE BY APPD DESCRIPTION SE NONE 4070 005 P N 937000 0518 FILE 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 6605 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 CONNECTOR SHARE THE SAME FUEL FLOW PIN LOCATIONS SINE FUEL FLOW OPTION D C FUEL FLOW OPTION A WHEN INSTALLING TO ANY EXISTING FREQUENCY 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 G
55. NESS FOR F ADC200 2000 D SUB 0501 032 2 14 05 UPDATED TITLE BLOCK CONNECTOR FILE NAME 98097022 9 28 98 CORRECTED PIN OUT ee ae 9803 025 3 26 98 SRB BASELINE RELEASE an A055 pN DATE APP D DESCRIPTIUN OT TO SCA SHEET 18F1 AIRSHOW UNIVERSAL TRIMBLE HONEY UNS 1M 8100 WELL B amp D A LAZER CABIN NAV DISPLAY 962810 amp 1 CHANNELS YG1761B 962830 X Je WHITE WHITE BLUE BLUE TX 7 WIRE WIRE ARINC429 A WHITE TX WIRE ARINC429 B NOTES N FOR THE B amp 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 amp D INDICATES IF IT IS SET UP FOR RECEIVE OR RECEIVE 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 3 11 03 ADDED NOTE 2 SHIELD amp GND DEL F amp 200 FROM TITLE 058 O u WG Ae NA 98037025 3 26 98 SRB KCL BASELINE RELEASE 4028 028 9 45 P N REV DATE BY APP D DESCRIPTION NOT TO SCALE SHEET ori 4 APPROVED KCL TRIMBLE TRIMBLE NORTHSTAR 1000 2000 962810 M3 962820 X gt X 3000 962830 X RS 42e2 TX
56. RANSMITTER 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 FLOW METER FLOW METER 25V DC IN POWER GND POWER GND 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 25V DC IN M F ADC 2000 P N 962830 2 A 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 wMP UPDATED MODEL 400 BEECHJET 9803 02 pp d CHANGE TITLE CHANGE FILE NAME FROM 4028 819 DWG 4026 8198 J DWG DESCRIPTION DU NUT SCALE SHEET 1 OF 1 4028 819 NOTES FROM RIGHT ENGINE FF TRANSMITTER FROM LEFT ENGINE FF TRANSMITTER SIGNAL COND P N 620 0098 PC 425 0098 RIGHT SIG 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 2 lt SHADIN MINNEAPOLIS 55426 INSTALLATION WIRING APPROVED 200 lt 20002 TO MITSUBISHI 05017032 B 2 14 05 UPDATED TITLE BLOCK rite MARE MU e W FOXBORO 620 SYSTEM 00077031 7719700 RH A
57. RAWINGS AND INSTALL KITS PARTS LISTS continued Drawing No Description Part Number DATE REV AIRCRAFT SPECIFIC 4028 818 Installation Wiring F ADC 200 2000 w Analog FF to Beech King Air 3 11 03 B Indicators D Sub Connector 4028 819 Installation Wiring F ADC 200 2000 Sine FF to Mitsubishi MU 300 and 2 14 05 B Model 400 Beechjet 4028 909 Installation Wiring F ADC 200 2000 to Mitsubishi MU 2 2 14 05 B w Foxboro PC 620 System 4028 936 Installation Wiring F ADC200 2000 or DigiData with DC FF to Cessna 2 14 05 A Citation 500 501 550 5550 551 552 4028 937 Installation Wiring F ADC200 2000 or DigiData with DC FF to Cessna 2 14 05 A Citation 525 Jet 4028 938 Installation Wiring F ADC200 2000 or DigiData with Digital FF to 1 17 05 A BomBardier LearJet 24 25D 4028 939 Installation Wiring F ADC 200 2000 with Sine FF to Rockwell Commander 2 14 05 A 690 and 695 4028 940 Installation Wiring F ADC 200 2000 or DigiData with DC FF to Raytheon 2 14 05 A Beechjet 400A Aircraft 4028 941 Installation Wiring F ADC 200 2000 or DigiData with DC FF to Westwind 2 14 05 A 1124 Models 4028 942 Installation Wiring F ADC 200 2000 to Fairchild A226 Series Aircraft 1 17 05 A 4028 943 Installation Wiring F ADC 200 2000 to Nav Receivers w RS 232 1 17 05 C 4028 949 Installation Wiring F ADC 200 2000 to Aerospatiale AS365N2 Dauphin 2 14 05 A 4028 950 Installation Wiring F ADC 200 2000 to Aerospatiale AS332 Super Puma 2 14 05 A 4028 A29 Instal
58. ROUND LUDP 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 SZADIV MINNEAPOLIS 55426 DRAFTER INSTALLATION WIRING FUEL AIRDATA OR COMPUTER ADC 200 ADC 2000 2222 2234 22101422 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 1277794 DAP SES BASELINE RELEASE DATE BY IAPP D DESCRIPTION SCALE NONE SHEET 1 OF 1 962830 X SPLICE POWER DAT SIGNAL WHT or BLK COMPASS HEADING 26V 400Hz DRAWING DATE SHADIN DRAFTER lt lt L AIRDATA acc ie COMPUTER ADC2000 gt eas sel 4 AE S eed fay 0501 032 2 14 05 UPDATED TITLE BLOCK 94127005 12 7 94 DAP SES BASELINE RELEASE DATE BY DESCRIPTION SCALE NONE SEE Ex DF 1 4028 425 Je 28VDC GND RX RSe3e TX RS232 NOTES 1 CONSULT INSTALLATION MANUAL FOR F ADC PROGRAMMING INSTRUCTIONS 2 MATING CONNECTOR 15 PIN FEMALE D SUB CSHADIN 230050 2 EQUIVALENT SHADIN MINNEAPOLIS 55426 INSTALLATION WIRING LOOP APPROVED 05097028 9 19 05 ZK CORRECTED PIN OUT 425 amp 6 EDITED NOTE 2 BACK HAR
59. SE 3 DONOT USE SWITCH 3 Loran Output Type 0 Format Z Trimble and Garmin 1 Format X ARNAV 2 Generic 3 Surveyor 4 Bendix C 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 Do Not Use SWITCH4 Altimeter Selection for Baro DC Input 0 None 1 Type 1 2 2 3 3 4 4 5 Type 5 6 Type 6 7 Type 7 8 DO NOT USE 9 9 DO NOT USE IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY 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 1001 A2001 A4001 4001 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 IM2830SG doc DIR 962830 1
60. Swi SW2 SW3 SW4 ARING P N 712801 BACKGROUND amp UNLESS OTHERWISE NOTED 55426 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 4028 A80 IDC IDC IDC IDC IDC SPERRY IDC AEROSONIC IDC 28007 427 28704 A1001 28711 621 28711 500 28007 431 BA141 28711 065 10420 11968E KTS 45152 10 410 KEA130A 346 429 600 SERIES 433 066 08 P N 962830 1 D1001 D2001 P N 962830 2 D4001 2101 P N 962830 3 di z m EXCITATION VOLTAGE USUALLY SUPPLIED BY AIRCRAFT HARNESS 5 12 VDC Jide TO EXCITATION J113 TO GND EXCITATION VOLTAGE MAY BE SUPPLIED BY AIRCRAFT HARNESS 65 VDC Ji18 TO EXCITATION J113 TO GND EXCITATION VOLTAGE SUPPLIED BY AIRCRAFT HARNESS 10VDO J113 TO EXCITATION 4112 TO GND 115 SVDC POWER MAY BE USED FOR EXCITATION MAXIMUM DIFFERENTIAL INPUT VOLTAGE BETWEEN BARO AND BARO lt gt IS 1eVDC P P P gt SHADIN MINNEAPOLIS 55426 INSTALLATION WIRING ADC 2000 KCL 0211 047 DEL 11 ADDED GND 0011 003 KEA 346 WAS amp RESPECTIVELY ADD IDC P N
61. T USE 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 IM2830SG doc DIR 962830 1M2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY 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 7 in this manual 1 Alternate K FACTOR Matrix 1 Table 8 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 O Q 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
62. W4 7 pee sum APPROVED INSTALLATION WIRING F ADC 200 2000 TO FAIRCHILD 226 SERIES AIRCRAFT FILE NAME 05017006 2714 05 WMP CORRECTED PINDUTS amp NOTE 1 e 5 DESCRIPTION SCALE 4028 9402 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 962810 962820 962830 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 IIMORROW IIMDRROW ARNAV MAGELLAN NMS2001 820 57000 SKYNAV Gx 55 R5000 STAR5000 360 TX TX SOFTWARE SELECT 871 19 37 SHADLN wvweororis 35426 es INSTALLATIUN WIRING F ADC 800 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 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
63. 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 IM2830SG doc DIR 962830 IM2830 Rev 5 INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830 XY 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 SWITCH 3 AND SWITCH 4 SS SSS eS Se OO OCC oO oO m O O m gt o co G Q tS onti G gt o co Q S CORRECTION For SSEC PSEC Select 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 5550 Falcon 10 Falcon 50 Raytheon Hawker HS125 700A LearJet 35 LearJet 55 Sabreliner 60 SSEC Only Lockheed Jetstar Antonov AN 12 Antonov AN 24 Antonov AN 26 Antonov AN 30 Yakovlev YAK 40 Shadin Avionics Page 9 25 F ADC Software Version 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 9
64. aximum Input Voltage 12 Vdc i The altimeters supported are listed in section 9 2 and are dependent upon the ADC2000 software version level IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 2 17 2 9 Statistical Specifications 2 9 1 Mean Time Between Failures MTBF 17 660 hours IM2830SG doc DIR 962830 1 2830 Shadin Avionics Rev R 3 0 CERTIFICATION INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830 XY Page 3 1 TSO C106 C44b Incomplete System Environmental Categories RTCA DO 160B 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 O UJ UU UU UIS Un IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 4 1 4 0 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 RS 232 RS 422 and ARINC 429 information may also prove useful We may request a wiring diagram of the aircraft s fuel flow system and transducer and or K factors IM2830SG doc DIR 962830 1
65. ce 1 Mohn the voltage swing Vs 4 27 Vdc With the fuel flow information encoded in frequency and not amplitude the loading effects do not produce an error provided the aircraft indicator can detect the signal transitions IM2830SG doc DIR 962830 1M2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 2 16 2 8 2 2 Sine Wave Fuel Flow Interface 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 operating 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 2 8 2 3 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 2 8 3 Baro Interface The baro interface requires a three wire connection to the potentiometer housed in the aircraft altimeter 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 M
66. e em B ues 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 an Eventide Argus moving map using the Shadin serial to serial data converter P N 937000 03 The fuel and Air Data 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 Shadin Eventide Navigational Argus Receiver Converter RS 232 or RS422 P N 937000 03 Moving Map F ADC2000 P N 5000 P N 7000 IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 2 1 2 0 FUEL AND AIR DATA SYSTEM SPECIFICATIONS 2 1 Input Data Range Pitot 20 to 350 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 22 Output Data Range PARAMETER Accuracy RANGE IAS Table 1 20 to 350 kts P ALT Table 2 1000 to 50000 ft OAT 1 5 C per TSO 60 to 60 C TRUE HEADING 42 0 360 degrees MAGNETIC HEADING 1 0 360 degrees IVS Table 3 10 000 ft min TAS Table 1 20 600 kts MACH Table 4 2 95 WIND SPEED 5 kts 5 360 kts WIND DIRECTION 10 0 360 degrees FUEL FLOW 2 1 450 GPH IM2830SG doc DIR 962830 1 2830 Shadin Avi
67. e manufacturers Honeywell SPZ 5000 Data UMorrow 2101 Universal UNS 1M Garmin 430 530 IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 1 2 13 System Configuration The Fuel Air Data 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 may be received from the aircraft altimeter if available PITOT STATIC NAV OAT RECEIVER MAG HEADING FUEL AIR DATA COMPUTER L ENGINE F F STANDARD ARINC 429 R ENGINE F F OUTPUT TO EFIS FLIGHT MANAGEMENT SYSTEM BARO POT Optional SYSTEM CONFIGURATION IM2830SG doc DIR 962830 1M2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY 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 receivers 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 p
68. er 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 each stage The following figure shows the approximate switch positions Connectors End A End B Switches ARINC 429 Switch IVIEW FROM END A IM2830SG doc DIR 962830 IM2830 Shadin Avionics Rev S Loop back Procedure 1 for Software Version 93 00 16 93 00 29 INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830 XY 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 m gt xo Q N Gallons Single Engine Liters i Lbs 5 8 H Lbs 6 71 Kilograms Lbs 6 5 Lbs 6 3 k not used Twin Engine Liters Lbs 5 8 Lbs 6 71 i Kilogra
69. ere 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 IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 2 9 2 6 4 SSEC PSEC LISTING Antonov An 12 SSEC only Airplane Flight Manual An 12 Sect 1 General Information Page 9 1991 MCA USSR Subsect 1 5 S amp DSECs approved 02 05 1992 Antonov An 24 SSEC only Airplane Flight Manual An 24 Sect 6 Flight Characteristics Page 81 2001 Ukrainian SAA Subsect 6 7 S amp DSECs approved 03 29 2002 Antonov An 26 SSEC only Airplane Flight Manual An 26 Sect 6 Flight Characteristics Page 53 2001 Ukrainian SAA Subsect 6 10 S amp DSECs approved 03 29 2002 Antonov An 30 SSEC only Airplane Flight Manual An 30 Sect 6 Airplane Characteristics Page 31 1982 MCA USSR Subsect Flight Characteristics approved 12 25 1979 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 D
70. ings Table Switches 1 amp 2 select the main engine K Factor Switches 3 amp 4 select 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 IM2830SG doc DIR 962830 IM2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 10 2 Beech KingAirB200 0 o o 7700 46 Beech 00 o 1 o 2 26150 8755 Beech KingAirCOO o 1 o 2 2650 875 Beech KingArFOO o 0 o 7700 46 Beech KingAirCOUA 0 0 o 1 7700 46 Beech 200 0 O o 1 7700 46 Beech 0 2 o o 154 o Beech 0 0 3 o 2 26150 875 Beech Beech 00 o 4 o o 340 0 ZEE EN 28850 0 a a _ s Gauge 393002 009 Cessna 0 C o o 16270 0 Sasi sam o o 4 5 amp 0 104 Cessna Model525 0 E o o 219800 0 Piper Cheynnelll 1 9 o o 41900 0 Piper CheynneIV 1 1 o o 650 0 Leadet Leajet 0
71. is manual is subject to change without notification To ensure complete and current updates note the Revision Log above and call Technical Assistance for updated information Added Bendix B amp Garmin 430 530 Format G to page 9 7 Added one more 11 03 00 Add sections 2 8 and 2 9 Update sections 2 0 5 1 5 7 and 9 2 6 27 02 3 21 05 IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 1 1 1 0 OVERVIEW 1 1 The Manual This manual is designed to facilitate the installation of the Shadin Fuel Air Data Computer ADC 2000 12 Product Information The Shadin ADC 2000 system is designed to provide a combined source of fuel and air data 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 Bendix King Trimble Garmin Transmits ARINC Data to ASINC Bendix King Airshow EFIS 40 50 Global Trimble GNSX TNL8100 GNS XIs Note To find out which particular receiver models have Air Data receive capability contact th
72. lation Wiring F ADC 200 2000 or DigiData with DC FF Piper 1 17 05 Cheyenne IM2830SG doc DIR 962830 IM2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page vi of vi REVISION LOG DATE D 16 23 97 1 8 98 Miscellaneous updates format change Added new sections 5 9 5 10 Switch 4 table page 9 10 Special Options 12 17 98 page 9 11 updated table 1 page 10 2 updated Dwg 4028 944 and included 7 26 00 m Dwg s 4028 A29 4028 A80 and 4028 A82 and new parts list IK9630 1 Ragen Indicator Transmitter to page 11 32 Added Garmin 430 530 to EDJ page 1 1 Added ARINC Label 234 amp 235 to page 2 4 Changed OAT Install kit to 681201A 1 on page iii Changed pages 11 11 13 16 21 amp 29 Added Allied Signal to page 2 5 Moved Raytheon Hawker HS 125 3A to page 2 9 Added 2 AN816 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 Page 2 4 and 2 5 9 13 00 EDJ 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 usage 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 Moved page 9 16 to 9 21 Included updated Dwg 4028 82
73. ms Lbs 6 5 Lbs 6 3 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 IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 9 4 Stage 1 Loopback Configuration Switch 1 is set to 1 to indicate that the stage 1 loopback is being performed SWITCH 2 PALT Correction static pressure correction by model 0 None 1 MU 300 2 Cessna Citation 501 3 Cessna 525 4 Cessna 550 SF DO NOT USE SWITCH 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 IIMorrow GX50 55 60 7 F DONOT USE 4 Altimeter Selection for Baro DC Input 0 None 1 1 2 Type 2 3 3 4 Type 4 5 5 6 6 7 7 IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY Page 9 5 ALTIM
74. normal and Copilot MACH Indicators Revision 24 LearJet 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 IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 2 12 SSEC PSEC LISTING Continued 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 Lbs 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 Mitsubishi MU 300 SSEC only Airplane Flight Manual Diamond IA Section 6 Performance FAA approved Jan 11 84 Altitude Correction Figure 6 8 Copilot system Page 6 20 Raytheon Hawker HS 125 3A SSEC only Airplane Manual
75. on and Speed Baro Corrected Alt Fuel Used Left Vertical Speed Pressure Altitude Fuel Remaining True Air Temperature Rate of Turn Outside Air Temperature OAT Only present with Digiflo input Note Not all parameters will be available to all navigational receivers Contact the manufacturer for display capabilities IM2830SG doc DIR 962830 1M2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 2 6 2 5 2 ARINC 429 Labels Associated with Switch Settings In Table 5 ARINC Label Configuration below the heading row containing the numbers 1 A indicates the setting of the ARINC rotary switch on the back of the unit The number in the cell at the intersection of an ARINC switch setting and an ARINC label number is the repeat time in msec for that label Zero indicates that the label is not generated with that switch setting Tolerance on the rate is 10 averaged over one second TAKETA PO EM 046 Flight Plan Header 100 o o 0 00 100 o o o o 0 075G Waypoint To From 10 ofo o wof o 0 o o 0 Table 5 ARINC Label Configuration IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 2 7 2 5 3 ARINC 429 Labels Associated with Switch Settings 0 Honeywell SPZ 5000 for Cessna 1 Bendix KLN90B or
76. onics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 2 2 This table is used as the tolerance for both IAS and TAS For values between table rows linearly interpolate between the adjacent table points AIRSPEED TOLERANCE KNOTS KNOTS 50 5 0 80 3 0 100 2 0 120 2 0 150 2 0 200 2 0 250 2 4 300 2 8 350 3 2 400 3 6 450 4 0 Table 1 Calibrated Airspeed Tolerance This table is used as the tolerance for pressure altitude Note that for an altitude between points in the tables the tolerance is linearly Interpolated between the adjacent table points ALTITUDE TOLERANCE FEET FEET 0 25 1000 25 2000 25 3000 25 4000 25 5000 25 8000 30 11000 35 14000 40 17000 45 20000 50 30000 75 40000 100 50000 125 Table 2 Pressure Altitude Tolerance IM2830SG doc DIR 962830 1M2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 2 3 This table is used as the tolerance for vertical speed For values between table rows linearly interpolate between the adjacent table points VERTICAL SPEED TOLERANCE FPM 20000 1000 6000 300 4000 200 2000 100 1000 50 500 45 200 45 100 45 50 45 0 45 50 45 100 45 200 45 500 45 1000 50 2000 100 4000 200 6000 300 20000 1000
77. ot considered to be a Shadin Air Data 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 Air Data 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 Air Data 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 Air Data checks for fuel flow below 15 pph If the fuel flow is below 15 pph the Air Data considers the engine to be off and returns a fuel flow of 0 Then as soon as the fuel flow exceeds 15 pph the Air Data continues to return a fuel flow of 0 until the delay time has expired In a twin engine the Air Data 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 Air Data computer is valid from 20 to 350 knots ARINC 429 labels 206 and
78. pback 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 Loopback Procedure 5 for S W Version 93 00 85 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 6 Analog K Factor Settings Table 7 Digital K Factor Settings Matrix 0 Table 7 Digital K Factor Settings Matrix 0 Table 7 Digital K Factor Settings Matrix 0 Table 8 Alternate Digital K Factor Setting Matrix 1 PAGE 9 1 9 2 9 3 9 3 9 4 9 6 9 6 9 7 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 9 22 9 23 9 25 9 26 9 27 9 28 10 1 10 2 10 3 10 4 10 5 10 6 Page of vi IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page iv of vi 11 0 INSTALL DRAWINGS AND INSTALL KITS PARTS LISTS Drawing No Description Part Number DATE REV 4028 394 Installation DWG ADC2000 Digital Fuel Flow 3 21 05 E P N 962830 1 4028 431 Installation DWG ADC2000 Sine Fuel Flow 3 21 05 D P N 962830 2 4028 432 Installation DWG ADC200
79. sman IDC 28007 427 429 Kollsman IDC 28704 1001 A2001 A4001 4001 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 IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S P N 962830 XY Page 9 9 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 SWITCH 3 AND SWITCH 4 CORRECTION For SSEC PSEC Select F ADC Software Version 0 No correction ALL A Q S O G gt gt 2 QO tS d 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 NO
80. to 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 AN816 2D gt 2 Hose with female fittings AN910 DASH NUMBER PIPE AN816 DASH NUMBER TUBE PIPE SIZE STEEL ALUM ALLOY O D THREAD 1 8 3 16 BRASS ALUM ALLOY MS20825 TEE TUBE PIPE STEEL ALUM ALLOY O D THREAD 5D HOSE Stratoflex 193 2 or Aeroquip 306 2 with MS27404 P N 311 2D on each end BI Air source MS20825 Tee gt En AN910 Li 816 7 s ADC2000 527404 gt m SS ee IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev S 5 8 5 9 5 10 P N 962830 XY Page 5 6 Connection to the Navigation Management System 1 Use the appropriate installation wiring diagram to connect the Fuel Air Data 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
81. ut Type Northstar 1200 BAUD Foster 1200 BAUD IIMorrow 611 612 618 1200 BAUD DO NOT USE Page 9 6 IM2830SG doc DIR 962830 1 2830 Shadin Avionics Rev S INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830 XY Page 9 7 Stage 1 Loopback Configuration Switch 1 is set to 1 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 3 Loran Output Type 0 Format Z Trimble and Garmin 1 Format X ARNAV 2 Generic 3 Surveyor 4 Bendix C Bendix King and F ADC without Baro Interface 5 Bendix D Bendix King and F ADC with Baro Interface 6 Shadin S IIMorrow GX50 55 60 7 Bendix B fuel only 8 F 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 5 Type 5 6 Type 6 7 7 8 DO NOT USE 9 Type 9 DO NOT USE IM2830SG doc DIR 962830 1 2830 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER Rev 5 P N 962830 XY 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 Koll

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