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1. 8 14 98 APPROVED KCL FILE NAME 028 A33 J DWG DIRECTORY 4028 IU T mamaq WE 9808 016 8 14 98 BASELINE RELEASE ECO REV DATE BY JAPP D i NOT TC 1002 048 R H FUEL FLOW P C B GROUND gt 14 F ADC 2000 P N 962830 3 5 4 101 GROUND tE R H SIG 43 SIG lt SIG I bel sic 1001 1 FACTOR IS 21 980 L H PC047 OFFSET 150 42 ONE SET F ADC SWITCHES AS SIGNAL le FUEL FLOW FOLLOWS 5 1 0 SWe E SW3 0 SW4 0 E1001 FUEL FLOW pan INDICATUR SHADIN MINNEAPOLIS MN 55426 WIRING F ADC 2000 MS m WITH DC I CESSNA CITATION S25 JET 4 u DRAVING NU Ure 4028 34 7 e F ADC 2000 962830 1 5 4 24 ENGINE FUEL FLOW SIGNAL 10 GROUND NGINE mj X L E Y JE T CARD 12 LEFT ENGINE FUEL P N 542 1158 02 FLOW SIGNAL NOTES 1 THIS INSTALLATION APPLICABLE TO AIRCRAFT WITH JET FUEL MODULE PART NUMBER 542 1158 02 ONLY JE T MODULE NOS 542 1158 01 MAY BE CHANGED TO 542 1158 02 MOS 1158 7A 2 K FACTDR IS 860 SET SWITCHES AS FOLLOWS SW1 D SW2 D SW3 D SW4 D CARD P
2. DESCRIPTION PART NUMBER 900 PC900 XAXXXXPH 1 6 A 1 2 uv 8 2 1 2 CURVED FACE C SEE NOTE 3 PART NUMBER PC900 CR A 1 2 7 8 1 2 CURVED FACE FLAT FACE SEE NOTE 3 SEE NOTE 5 PART NUMBER SEE NOTE 3 PART NUMBER 900 PART NUMBER i PART NUMBER PC900 XAXXXXPH 1 8 A 0 CURVED FLAT FACE SEE NOTE 2 SEE NOTE 3 USE THIS DRAWNG FOR 200 P N 962830 3 5 4 ONLY CONTACT SHADIN CO IF THIS INDICATOR IS INSTALLED K FACTORS DOWN BY BEECH INDICATOR PART BEECH INDICATOR K FACTOR LOFFSET 90 380009 2 77 000 416 90 380009 5 77 000 416 101 384153 1 3 30 770 0 900 1 0600 38 460 0 PC900 1A0750 XXX 30 770 0 PC900 1A0800 XXX 28 850 0 OLR m dll MINNEAPOLIS 55426 INSTALLATION WIRING F ADC 2000 W ANALOG F F TO BEECH KING AIR INDICATORS RIGHT ENGINE FF INDICATDR A LEFT ENGINE FF INDICATOR AS 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 FLOWMETER 28 VDC RETURN INTERNAL TEST POINT SIGNAL RETURN TO TOTALIZER CASE GROUND NOTES F ADC 2
3. P N93700 03f Shadin Avionics File Name Copy of IK9630A 1HP doc DIRECTORY INSTALL KITS Report 4028B ECO Date April 9 2007 ECO 0704 003 Rev H Release Date 4 9 07 Sec IX Approved ZK Page 1011 PARTS LIST Part IK9630A 1 Drawing s N A Description INSTALL KIT ADC2000 MS CONN NO OAT FN P N QTY DESCRIPTION MFG MEG DESIGNATION COMMENTS 232721 1 CONN 55 Pin St Plug Socket ______ MS24266R2B55SN 233273 1 CONN Clamp Straight 822 MS27291 6 J e 15 612826 1 TRAY Mounting ADC 2000 5 1408154 15 62926 Alt MOUNTING TRAY ASSEMBLY SHA 40847 Thermal Label 4 x 1 s 8601 4 items 90 580009 2 90 580009 5 SEE NOTE 5 PART NUMBER 90 580009 2 OR 90 580009 5 SEE NOTE 3 D C FUEL FLOW OPTION 962830 3 5 4 Jt 5 TO 10 FOR FULL SCALE MODEL DEPENDANT SHIELD GROUND SIG 96 LEFT FUEL FLOW SHIELD GROUND PART NUMBER 101 384153 1 oR 101 384153 3 SEE NOTE 3 PART NUMBER 101 384153 1 101 384153 3 SEE NOTE 5 NOTES 2 y 9 2 a 3 26 08 sre FOR P N 90 380009 5 CHANGED NOTE 3 FROM 26150 875 OLD FILE 4028 876 0 0 028 Sas IT 4028 876 ECO g REV OAT BY
4. WEIGHT oz 05422 RX i DEFAULT NO JUMPER SEP D gt POWER CONSUMPTION SINGLE ENGINE 7 210 6 28v D TWIN ENGINE DEFAULT NO JUMPER 0501 032 UPDATED TITLE BLOCK CONVERTER WAS TXMTR 3801 025 10 2 98 DMD PG 9707 023 17 15 97 PG BASELINE RELEASE DATE EL APPD 1 THE CONVERTER BE MOUNTED IN ANY ORIENTATION 4 SPACING IS REQUIRED ABOVE CONNECTOR 3 NO COOLING IS REQUIRED 4 THE CONVERTER CAN BE INSTALLED IN A PRESSURIZED OR NON PRESSURIZED AREA PROVIDING TEMPERATURE DOES NOT DROP BELOW 20 9 1 AMP CIRCUIT BREAKER IS REQUIRED 6 NO SHOCK MOUNT REQUIRED 7 USE HARDWARE PROVIDED IN INSTALL KIT P N IK9337 TO ASSEMBLE MATING CONNECTOR CONNECTOR KEY PIN FUNCTION 1 RS232 OR RS422 SELECT 2 TWIN DR SINGLE ENGINE SELECT dE s SEE 4 SELECTOR S NC TABLE 6 N C 7 SELECT POWER OUTPUT 8 14 TO 28 DC POWER IN 9 NC 10 SIGNAL GROUND 5422 RX SHADIN ADC 12 25422 RX gt USE RS 232 DR RS 422 13 RS232 RX NUT BOTH 14 RS232 TX TO ARGUS 5000 7000 15 POWER GND UNLESS OTHERWISE NOTED DIMENSIONS ARE IN INCHES TOLERANCES X X 01 XXX 30 01 APPROVED m E Am MATERIAL NONE EET E SHADE MINNEAPOU MN 55426 INSTALLATION SERIAL TO ARGUS 5000 7000 CONVERTER
5. E na RELEASE L amp ca REv BY _ 1 CONSULT INSTALLATION MANUAL FUR F ADC PROGRAMMING INSTRUCTIONS 2 MATING CONNECTOR MS 24266 22 555 SHADIN PN 233272 OR EQUIVALENT 28VDC GND TX RSe3e RX RSe3e SHADIV MINNEAPOLIS MN 55426 PETA CATION WIRING LOUP F ADC 200 2000 DRAWING ND P N APPROVED DIRECTORY ALE BASELINE ym n MANUFACTURING NOTES APPLICATION NOTES 1 MATCH FONT STYLE AND SIZES ALL OTHER A CONFIGURATION IS NECESSARY PRINT SWITCH DIMENSIONS AS SHOWN SETTINGS IN SPACE PROVIDED PRINT N A WHEN SWITCHES ARE NOT USED 2 SWITCH BOX DIMENSIONS ARE AS FOLLOWS MANUFACTURER IGNORE HEIGHT 200 2 50 ACCESS COVER RO 13 x8 SWITCH SETTINGS swi swe SW3 sw gt P N 712801 BACKGROUND BLACK SILVER LETTERING amp BOXES SILVER a 32 LABEL ADC200 2000 ACCESS COVE up m 501 2 MARNE 12700 T1528 OO ee 3M 7985 CO S e It IY 1 DESCRIPTION __ 3 18 MATING CONNECTDR SHADIN P N 230036 17 DA15S SHADIN P N 230038 HOOD DA 246 15 PIN MALE CONNECTOR SELECTOR TABLE RS238 RX TIE J17
6. 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Page 9 12 Stage 3 Loopback configuration Switch 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 5 4 and 962830A 2 S 4 only 0 Standard K FACTOR Matrix 0 Table 2 in this manual Alternate K FACTOR Matrix 1 Table 3 in this manual 2 5 DO NOT USE SWITCH 3 FUEL FLOW DELAY TIME 0 Delay 1 5 Second Delay 2 10 Second Delay 3 15 Second Delay 4 20 Second Delay 5 25 Second Delay 6 30 Second Delay 7 35 Second Delay 9 40 Second Delay 9 45 Second Delay DONOT USE SWITCH 4 SPECIAL OPTION DESCRIPTION 0 ARINC 429 labels 206 IAS and 210 TAS are not transmitted 1f the IAS 20 knots 1 ARINC 429 labels 206 IAS and 210 TAS transmitted as zero knots 1f the AS lt 20 knots 2 F Reserved DO NOT USE 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Page 9 13 Stage 4 Loopback configuration Switch 1 is set to 4 to indicate that the stage 4 loopback 15 being performed Refer to the OAT probe calibration certificate for the Ta Tb Tc calibration code selection
7. 200 20 22 ___ 200 0 0 200 200 275G LRN Status Word 20 200 0 200 20 300 Navigation 00 O0 O 00 3055 Waypoint Group __ 00 O0 O o 00 3046 Message ID Characters 13 100 0 o 00 3055 Message ID Characters 46 100 0 O 0 __ 100 3066 Waypoint Latitude 1 100 O0 O 00 3070 WaypoinLongitude 100 00 00 310 Present Latitude 00 O0 o 200 200 311 Present Longitude 00 200 200 312 GroumdSped 50 0 0 50 50 313 TmeTrck 1 0 0 0 200 200 34 TmeHeading 10 ofo 100 10 315 WindSped 100 100 0 100 jio 316 Wind Direction True 10 100 O 100 __ 100 320 Magnetic Headings 100 O 100 100 31 jDrfrAnge 50 50 0 50 50 347 Lef RightFuelFlow 200 200 0 200 200 351G Distance to Final Destination 0 0 o 0 352G Time to Final Destination 0 0 jo Equipment ID 0 10 0 2122194 N S S 2 O OI OCO 9191 v er sere s S 1 ojojo olojo Table 5 ARINC Label Configuration 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4
8. PROTECTIVE CAP amp PLUGS J1 PINOUT 21 TX RS232 Ad J1 PINOUT J1 PINOUT 22 ARINC 429 8 1 N C 11 N C 23 SHIELD GROUND 2 A Y SYNCHRO INPUT 12 LEFT SINE FF INPUT 24 RIGHT SINE FF INPUT 3 13 N C 25 N C 4 SHIELD GROUND 14 N C 26 LEFT SINE FF INPUT 5 BARO INPUT 15 N C 27 N C 6 N C 16 BARO INPUT 28 N C 7 HEADING X SYNCHRO INPUT 17 _ 29 N C 8 N C 18 HEADING 26 30 N C 9 TX RS232 19 RS422 51 10 SHIELD GROUND 20 RX 5422 32 EDO F Z 0503 001 AMEMEE US REDRAW CORRECTED PITOT STATIC LOCATON _ _________ 2777 RELEASE OESCRIPTION FEMALE J1 PINOUT 33 34 35 36 37 38 39 40 41 2 43 44 45 46 47 DRAWING DATE 8 29 97 AW ui LE 5 4 SCALE DRAWING sur io i MATING CONNECTOR SUPPLIED AS PART OF INSTALL KIT P1 CONN MS24266R22B55SN P N 333272 CLAMP MS27291 6 P N 233273 3 83 3 83 PINOUT SIGNAL 48 49 HEADING 26 50 TX 65422 A 51 FLAG RESERVED 52 OAT POWER RS422 53 BARO WIPER RS232 54 POWER GROUND ARINC 429 A 55 28V N C 42 RX RS232 RIGHT SINE FF INPUT INSTALLATION
9. PROBE IN UR NEAR PRUP AIRSTREAM ENGINE EXHAUST FLUW PATH CABIN HEATERS EXHAUST FLOW PATH TRANSMITTING ANTENNAS DME TXP COMM DARK PAINTED AREAS INI em 681201 J apana FN L3 IN L BS MAXJ SN NY ln 7 NES 10 4X DRILL 0 0989 AIRCRAFT FUSELAGE ol 40 4 PL DRILL 0 3598 30 20 0 50 0 50 1 00 DETAIL MUUNTING AOLE DETAIL DRAWING DATE UNLESS OTHERWISE NOTED DRAWING SHADIN serena Sis HRA 0 01 TOLERANCES lus 20 TT NIST INSTALLATION 0501 0308 2 14 05 WMP UPDATED TITLE BLOCK amp NOTE 4 ADDED KIT TO TITLE 0111 001 B 11 14 01 KCL STANDARDIZED DWG FORMAT MIMIC DWG 4012 177 FILE NAME sod R B S E M B L Y K I 0002 036 3 11 96 WMP PG CAD ADD NOTES 1 AND 3 MATERIAL DIRECTORY DRAWING Mi REV N A 4 8 91 DAP SES BASELINE RELEASE 681201 1 4028 005 681201 1 ECU REV DATE APP D DESCRIPTION SCALE NONE SHEET 1 OF 1 Avionics Filename 681201 1HP doc DIRECTORY 681201 1 Report 4032D ECO Date April 4 2007 ff 0704 002 Rev H Release date 4 6 2007 Sec IX Approved ZK Page of 1 PARTS LIST Part 681201 1 Drawing 5 4028 005 Rev Description OAT PROBE ASSEMBLY KIT EN P N QTY DESCRIPTION DESIGNATION
10. C a DU SCALE L OF NOTES N FROM RIGHT ENGINE FF TRANSMITTER FROM LEFT ENGINE FF TRANSMITTER SIGNAL CUND Jl P N 620 0098 425 0098 RIGHT SIG RIGHT SIG LEFT 510 LEFT SIG F ADC 2000 P N 9628304 2 5 4 SIG COND K FACTUR 5 1 SWe 5 3 SWA4 620 0098 33800 6 9 6 9 SHADIN meesracis 55426 PPAR INSTALLATION WIRING JF ADC 2000 TO MITSUBISHI MS CONN SINE FF DRAWING 4028 A32 slp APPROVED 0077031 74 RH TADD UR PC 423 0098 080 REA DWG 58087016 97 KCL BASELINE RELEASE ECA Mm ix P76 J50 P50 GND E04a20N R H E08A20 V E08B20 SIGNAL 06 20 06 20 GRDUND 05 20 5 05 20 9 c F ADC 2000 P N 962830 3 5 4 10 GROUND eS e R H SIG E 13 R H SIG K le L H sic J4Je amp L H SIG 4 4 1K FACTOR IS 16 270 L H OFFSET IS 0 9 E P EDS CCS N SET F ADC SWITCHES AS SIGNAL F 16 20 U 16 20 FOLLOWS 5 1 0 SWe C 18 20 V E18B20 SW3 0 SW4 0 GND 7 E14A20N IND 15 FUEL FLOW INDICATOR SHADIN 55426 INSTALLATIUN WIRING F ADC 2000 5 WITH DC FF CESSNA CITATION 500 501 550 5550 551 552 DRAVING REV 4028 a33 P N
11. SWITCH 2 OAT Ta CALIBRATION CODE SELECTION Refer to calibration certificate for A code selection to F SWITCH 3 OAT Tb CALIBRATION CODE SELECTION Refer to calibration certificate for code selection to SWITCH 4 OAT Tc CALIBRATION CODE SELECTION Refer to calibration certificate for code selection to Note Switch 2 3 and 4 are set to position zero if the OAT probe does not have a calibration code marking 1 e 0 Bz0 C O 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Page 9 14 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 not 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
12. 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 1s less than 20 knots 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER 10 0 P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 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 system 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 962830A 1 S 4 Digital 962830A 2 S 4 Sine Wave 962830A 3 S 4 Analog Use the switch settings from the appropriate table to set the K Factor For Digital or Sine units P N s 962830A 1 S 4 and 962830A 2 S 4 use the Digital K Factor Settings Tables Switch 1 2 selects the left Factor Switch 3 amp 4 selects the right K Factor Due to possible fuel flow system peculiarities switch 1 amp 2 and switch 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 962830A 3 S 4 use the Analog K Factor Settings Table Switch 1 amp 2 selects the main engine K Factor Switch 3 amp 4 selects the offset The offset is simply the value represented by switches 3 amp 4 in the Analog K Factor S
13. FUEL AIR DATA COMPUTER ADC 2000 P NS 962830 X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 INSTALLATION MANUAL REV M 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 AXS4 IM2830 AXS4M DOC DIR 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830 2 5 4 962830A 3 S 4 PAGE CONTROL CHART SECTION DESCRIPTION PAGE NO REVISION LOG 1 0 OVERVIEW 1 1 1 1 The Manual 1 1 1 2 Product Information 1 1 1 3 System Configuration 1 2 1 4 Fuel Totalizer Configuration 1 3 1 5 F ADC2000 Argus Moving Map Configuration 1 3 2 0 FUEL AND AIR DATA SYSTEM SPECIFICATIONS 2 1 21 Input Data Range 2 1 2 2 Output Range 2 1 Table 1 Calibrated Airspeed Tolerance 222 Table 2 Pressure Altitude Tolerance 2 2 Table 3 Vertical Speed Tolerance 2 3 Table 4 MACH Tolerance 2 4 23 Dimensions 2 5 2 4 Power Requirements 2 5 253 Output Data 2 5 2 5 Serial Output Data Parameters 2 5 2 5 2 ARINC 429 GAMA Output Labels 2 6 Table 5 ARINC Label Configuration 2 6 2 5 3 ARINC 429 Labels Associated with Switch Settings 2 7 2 5 4 Start Up Temperature and Times for Output Data Valid 2 8 2 6 Limitations 2 6 2 6 1 Warm up Time 2 8 2 6 2 Supplemental Equipment 2 8 2 6 3 Static Pitot Source Error Correction SSEC PSEC 2 8 2 6 4 SSEC PSEC Listing
14. Page 5 2 amp 8 1 changed by OAT kit Page 5 4 changed by adding Sandel hdg source Pages 9 1 9 2 amp 9 3 changed by software revision Pages 9 7 changed to correct Bendix descriptions Altimeter Types heading added to page 9 5 9 8 Page 9 11 moved to 9 16 Pages 9 11 to 9 15 added for Procedure 3 Page 5 5 changed to add one more 816 fitting Page 2 6 changed by adding TSO statement under Section 2 6 10 06 00 Correct units for IVS Accuracy to 40 ft min and range to 10 000 ft Min Added sections 2 8 and 2 9 Updated sections 5 1 5 7 and 9 2 Moved section 9 0 to page iii Moved page 9 16 to 9 21 Updated Dwg 4028 A44 Baseline release Cfg C with software versions 93 04 02 and 71 73 03 Added P N G 9 26 02 EDJ 681201 OAT probe installation and parts list to page iv drawing list Updated Page 2 4 and 2 5 ARINC Table Corrected page 10 3 Table 2 Replaced pages 9 11 to 9 16 Changed Alternate Digital K Factor table to include 48000 PPG Removed 681201 A 1 H 9 26 03 EDJ install drawing and parts list Updated Section 2 5 2 amp 2 6 1 Deleted Loopback Procedure 1 and renumbered Procedure 2 amp 3 to 1 amp 2 Updated Section 9 0 amp 9 2 3 7 05 Changed Company Name Updated pages 9 5 9 10 and Section 11 0 9 22 05 Updated 2 2 IK9630A 1 4028 395 4028 875 4028 B98 sections 3 1 5 1 8 1 and page 10 5 4 25 07 Changed Company Name Updated IK9630A 1 and 681201 1 parts list M 5 17 11 ZK Incorporated 4028 B98 Rev D 4028 8
15. Performance Standard Charts Pages 4 17 4 18 FAA approved Altimeter Position Correction Figure 4 5 Revision 37 Pilot amp Copilot Douglas DC SSEC Airplane Manual Douglas DC 8 Section IV Performance Page 20 FAA approved Altitude Correction 33161 10 1 66 Pilot amp Copilot system PSEC Airplane Manual Douglas 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 48 Sept 1 77 Altitude Correction 5 143 Copilot system Falcon 20 SSEC only Maintenance Instruction Manual 34 18 03 Section 5 DTM30528 Altitude Correction Subsection 20 DGAC Approved Copilot system Page 4 1 2830 54 DIRECTORY 962830 5 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 SSEC PSEC LISTING Continued Falcon 50 SSEC Airplane Flight Manual Section 5 Performance Page 5 25 2 DGAC approved Copilot for A C equipped with one ADC Revision 24 PSEC Airplane Flight Manual Section 5 Performance Page 5 25 2 DGAC approved Pilot normal and Copilot MACH Indicators Revision 24 Lear 24 SSEC only Airplan
16. ADC2000 MS CONN SINE FF QUICK START DRAWING NO SIZE REV 4026 872 ors 3 83 1 INSTALLED WEIGHT 2 8 LB CONNECTOR SUPPLIED AS PART OF INSTALL KIT ZN USE FOUR 46 MOUNTING SCREWS 3 ONN 5242668228555 P N 233272 COMMUNICATION RX TX WITH LORAN OR GPS USE EITHER RS232 OR RS422 NOT BOTH CLAMP MS27291 6 P N 254275 RS232 PORT 2 RESERVED FOR FUTURE USE 7 5 of LLL SS I _ F TD F gt k is oq ee AURI Vya a nEUKP A an _ FF L n r Y rrns oo D gt h gt o7nP i i 22 4 FEMALE HM 1 2 PROTECTIVE amp PLUGS J J CC OO 5 5 w Ji PINOUT Ji PINOUT 33 SIGNAL 48 we gt 34 49 IGHT SIDE 35 HEADING 26 50 36 TX RS422 51 37 FLAG RESERVED 52 OAT POWER 38 RX RS422 53 BARO WPER EE d A 39 RX RS232 54 POWER GROUND 40 ARINC 429 A 55 428V J1 PINOUT J1 PINOUT 22 ARINC 429 B 41 N C 1 11 23 SHIEL
17. GROUND RIGHT RIGHT SHIELD GROUND MINNEAPOLIS 55426 INSTALLATION WIRING ADC 2000 APPROVED 0504 046 C 5 2 05 CB EDJ ADDED P N 9628 1 1 5 8 2 5 8 amp 3 5 8 m QUICKSTART DIGITAL SINE AND DC 0304 037 B 4 23 03 PAB EDJ ADDED P NS 962830 962830A 2 5 8 amp FUEL FLOW ADDED P N 962830 1 5 7 4028 8 5C DWG _0105 012 APP D DESCRIPTION DO NOT SCALE DRAWNG SHEET o 1 4028 875 AERDSONIC 102220 1188 28711 500 600 SERIES IDC P KTS 45152 10 410 346 08 ps P N 962930 1 5 7 P N 962930 5 4 e 3 NOTES EXCITATION VOLTAGE USUALLY SUPPLIED BY AIRCRAFT HARNESS 55 12 VDC 5 TO EXCITATION 116 TO GND EXCITATION VOLTAGE MAY BE SUPPLIED BY AIRCRAFT HARNESS 5 VDO 5 TO EXCITATION TO GND AX EXCITATION VOLTAGE SUPPLIED BY AIRCRAFT HARNESS 10VDC 71 16 TO EXCITATION 15 TO GND 0152 5VDC POWER BE USED FOR EXCITATION MAXIMUM DIFFERENTIAL INPUT BETWEEN BARO lt AND BARO lt gt IS SHADIN 98082 DER APPROVED INSTALLATION WIRING ADC 2000 0103 012 TROL Wa Jab RESPECTI Ms CONN QS ALTIM N 0077091 A Y IN SPERRY LABEL VAS 7 P N 4028 A44 4028 4442 P 98087034
18. Typical Time for Start Temperature Output Data Valid 23 lt minute 20 C 2 5 minutes 55 C 3 5 minutes In the Serial Output Data the Q record is used to report if the ADC has completed its warm up period and the Altitude Airspeed Data 15 accurate Record 0 PALT IAS data valid 1 PALT IAS data not valid Limitations 2 6 1 Warm up time The Pressure Altitude Indicated Airspeed Vertical Speed and Barometric Altitude are not valid until the Q record is valid 1 a value of 707 The installer is responsible to ensure that only valid data 1s displayed 2 6 2 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 The are not intended to be used as a primary system to drive altimeters or airspeed indicators The F ADC fuel section is not a fuel quantity system and therefore reports only what was manually entered by the operator 2 6 3 Static Source Error Correction SSEC Pitot Source Error Correction PSEC For certain models of aircraft 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 uncorr
19. the following parts could be used It is recommended to use all aluminum fittings Existing Pitot Static lines gt AN910 1D ANS16 2D gt 2 Hose with female fittings AN910 DASH NUMBER PIPE AN816 DASH NUMBER nid PIPE SIZE STEEL ALUM ALLOY 8 BRASS ALUM ALLOY 520825 STEEL ALUM ALLOY O D THREAD ove ue p we HOSE Stratoflex 193 2 or Aeroquip 306 2 with MS27404 P N 311 2D each SA Air source 520825 Tee AN910 gt A 2 NS ADC2000 MS27404 lt lt lt as 10 1 2830 54 DIRECTORY 962830 5 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 5 8 Connection to the Navigation Management System 1 Use installation wiring diagram 428 874 to connect the Fuel Air Data Computer s Connector J1 to the navigation management system 2 2 circuit breaker should be used for powering the system Mark the circuit breaker by engraving painting or other approved method 3 Keep the cables away from power cables DME and transponder cables 4 Refer to the specific Nav Receiver Installation Manuals for details 5 If the ARINC 429 output is used refer to the digital EFIS or flight management installation manual and sections 2 5 2 2 5 4 in this manual 5 9 Connection to the Alti
20. 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 Lb 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 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 18 750 158 1M2830 A 54 Shadin Avionics IM2830 AXSAM DOC DIRECTORY 962830A X S 4 INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830 1 S 4 962830A 2 S 4 962830A 3 S 4 Page 2 13 2 7 Part Numbering Scheme P N 962830 A Y Quick Start PALT IAS ADC2000 with MS Connector Shadin OAT Probe Fuel Sensor Type Y X None Y 1 Digital Y 2 Sine wave Y 3 DC voltage 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER 962830A 1 962830A 2 962830A 3 Page 2 14 2 8 Electrical Interface Specifications The specifications for the interfaces heading fuel flow and baro are listed in this secti
21. 2 9 2 6 4 SSEC PSEC Listing Continued 2 10 2 6 4 SSEC PSEC Listing Continued 2 11 2 6 4 SSEC PSEC Listing Continued 2 12 2 7 Part Numbering Scheme 2 13 2 8 Electrical Interface Specifications 2 14 2 8 1 Heading Interface 2 14 2 8 2 Fuel Flow Interfaces 2 14 2 8 2 1 Digital Fuel Flow 2 14 2 8 2 2 Sine Wave Fuel Flow 2 15 2 6 2 3 DC Voltage Fuel Flow 2 15 2 8 3 Baro Interface 2 15 2 0 Statistical Specifications 2 16 2 9 Mean Time Between Failures 2 16 3 0 CERTIFICATION 3 1 4 0 PLACING AN ORDER 4 1 IM2830 AXS4M DOC DIR 962830A X S 4 INSTALLATION MANUAL FUEL AIR DATA COMPUTER 1M2830 AXS4 Shadin Avionics Sec VII P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 SECTION NO 5 0 6 0 7 0 8 0 DESCRIPTION INSTALLATION PROCEDURE 5 1 252 5 3 5 4 5 5 5 6 5 7 5 8 5 9 5 10 F ADC Location Selection Mounting the F ADC Mounting the Probe Connection to the Fuel Flow Sensor Connection to the Heading Source Connection to the Pitot and Static Lines Connection to the Navigation Management System Connection to the Altimeter Baro Pot Post Installation Checkout OPERATING INSTRUCTIONS INITIALIZATION MAJOR COMPONENTS OF THE SYSTEM PAGE 5 5 5 6 6 1 7 1 8 1 IM2830 AXS4M DOC DIR 962830 5 4 INSTALLATIONMANUAL FUEL AIR DATA COMPUTER 1M2830 AXS4 Shadin Avionics Sec VII SECTION NO 9 0 10 0 P N 962830A X S 4 962830A 1 S 4
22. 9 m 30 000 40 000 50 000 Table 4 MACH Tolerance 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 2 3 2 4 2 5 2 5 1 Dimensions including mounting rack Size 7 4 L x 4 3 Hx 3 9 W Weight 36 oz Power Requirements System Power required 28 VDC 1300 mA 14 VDC 900 mA Output Data 1 Electric Format RS 422 or RS 232 2 ARINC 429 low high speed GAMA Has to be configured at the factory See paragraph 2 5 3 for ARINC 429 output data capabilities Serial Output Data Parameters Fuel Group AIR DATA Group L ENG Fuel Flow Pressure Altitude PALT Rate of Turn R ENG Fuel Flow Density Altitude MACH Number Fuel Used Total Barometric Corrected Altitude Wind Direction and Speed Total Fuel Used Indicated Air Speed IAS Baro Correction mb 1 Fuel Used L ENG True Air Speed TAS Baro Correction hg Fuel Used R ENG Vertical Speed Fuel Remaining True Air Temperature TAT NM Fuel Unit ground Outside Air Temperature OAT Fuel to Destination Drift Angle Fuel at Destination Magnetic Heading Note Not all parameters will be available to all navigational receivers Contact the manufacturer for display capabilities 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830
23. 962830 2 5 4 962830A 3 S 4 DESCRIPTION CONFIGURING THE AIR DATA 9 1 9 2 Configuring with ADSETUP User Manual Configuring Manually Loopback Procedure 1 for S W Version 93 02 67 Stage 0 Loopback Configuration Stage 1 Loopback Configuration Stage 1 Loopback Configuration Stage 2 Loopback Configuration Stage 3 Loopback Configuration Loopback Procedure 2 for S W Version 93 04 02 and above Stage 0 Loopback Configuration Stage 1 Loopback Configuration Stage 1 Loopback Configuration Stage 2 Loopback Configuration Stage 3 Loopback Configuration Stage 4 Loopback Configuration Select No Delay Special Options 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 Continued Table 7 Digital K Factor Settings Matrix 0 Continued Table 8 Alternate Digital K Factor Setting Table 3 Matrix 1 PAGE 9 1 9 1 9 2 9 3 9 3 9 4 9 5 9 6 9 7 9 8 9 8 9 9 9 10 9 11 9 12 9 13 9 14 9 14 10 1 10 1 10 2 10 3 10 4 10 5 10 6 IM2830 AXS4M DOC DIR 962830 5 4 INSTALLATIONMANUAL FUEL AIR DATA COMPUTER IM2830 AXS4 Shadin Avionics Sec VII 11 0 Drawing No 4028 005 N A 4028 395 4028 857 4028 871 4028 872 4028 873 4028 874 4028 875 4028 A44 4028 A62 4028 A80 4070 005 N A 4028 876 P N 962830A X S 4 962830A 1 S
24. COMMENTS 10 511201 4 RIVET AN4703 4 or MS20470AD3 4 fT 15 5316 1 OATSTIFFENERRING SHA 4202 20 __ 670503 SHIELD Temp Sensor Assy SHA 4005 55 SHA 4005 2606 30 ___ 670505 1 WASHER FlatOAT SHA 4005 303 C SHA 4005304 SHA 4005 794 PP 10 items 2 NY 6 25 x2 NOTES USE 6 MOUNTING HARDWARE 2 DELETED 3 USE THIS DRAWING TO INSTALL SHADIN P N 612826B 612826A OR 612826 UNLESS OTHERWISE NOTED DRAWING DATE DIMENSIONS ARE IN INCHES 9 22 94 X X 1 64 X XX 0 01 Z 1 X XXX 0 005 05077053 c 6 1 05 PAB or NOTE s C C C C C C C C C C C U C Y qis 05017032 3 3 05 Pas WP DELETED NOTE 2 z 10 DIMENSIONS ADDED NOTES 102111047 2 7 03 PaB BAL ADDED DIMENSIONS TRIAL 1215 95 O DESCRIPTION 3D CAD FILE AVAIL YES SCALE 1 1 SHEET 1 C MINNEAPOLIS 55426 INSTALLATION MOUNTING TRAY ADC2000 MATING CONNECTOR Sere eee AS PART OF INSTALL KIT CONN MS24266R22B55SN P N 233272 CLAMP MS27291 6 P N 233273 NOTES 1 INSTALLED WEIGHT 2 8 LB ZX USE FOUR 6 MOUNTING SCREWS ZA FOR COMMUNICATION RX TX WITH LORAN OR GPS USE EITHER 5422 5232 PORT 2 RESERVED FOR FUTURE USE 7 5
25. Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 ALTIMETER TYPES Type Kollsman PD 44929 935 done for Cessna 525 Type 2 Bendix King KEA 130A and KEA 346 versions King P N 066 3062 XX XX 08 through 11 versions 00 though 07 have no Baro Potentiometer Type 3 ARINC 575 3 specification for ratio to Altitude Correction calculation Kollsman IDC 28007 427 429 Kollsman IDC 28704 A1001 A2001 A4001 B4001 C4001 D1001 D2001 D4001 D4101 4E2101 F2101 and 495 Type 4 Kollsman IDC 28711 621 thru 624 Type 5 Kollsman IDC 28007 431 433 Honeywell Sperry BA 141 Type 6 Kollsman IDC 28711 500 series and 600 series Type 7 Kollsman IDC 28711 065 and 066 Type 8 Reserved for future use DO NOT USE Type 9 Aerosonic P N 102220 1188T 10420 11968E 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Stage 2 Loopback configuration Switch is set to 2 to indicate that the stage 2 loopback is being performed SWITCH2 Fuel Filter Type 0 Injector 1 Carburetor SWITCH 3 AND SWITCH 4 CORRECTION For SSEC PSEC Select No correction MITSUBISHI MU 300 CESSNA CITATION 500 501 CESSNA 525 CESSNA 550 Citation 560 SN lt 259 Citation 560 SN gt 260 Citation 650 Sabrelin
26. and model for the DC fuel flow systems See the attached tables in section 10 0 Consult section 11 for specific aircraft installation wiring drawings 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER 5 6 P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Connection to the Heading Source The system is designed to interface with any ARINC 407 heading system 7 with no effect on the heading system or the bootstrap XYZ Collins Collins Collins Collins King King Sperry i Sandel Heading 328A 2A HSI331A MCS 328A 5 525 KSG105 Gyro SN3308 ARINC 2P1 P1 65 2 407 4 a 2 _ 6 26 V 6 53 ic The wire common and Z must connected together source bootstrap 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 5 7 Connection to the Pitot and Static Lines The pitot static line should be cut and a tee installed to tap into these lines Use the appropriate type of fittings to match the type installed in the aircraft Refer to CFR part 43 appendix E for approved practices in installing and verifying these connections PITOT STATIC adapter helpful hints To make an adapter for the Shadin ADC2000
27. zero knots 1f the AS lt 20 knots 2 F Reserved DO NOT USE 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Loopback Procedure 2 for Software Version 93 04 02 and above Stage 0 Loopback Configuration Switch 1 is set to 0 to indicate that the stage 0 loopback is being performed SWITCH 2 Fuel Units and Engine Type Gallons single Engine Liters Lbs 5 8 166 71 Kilograms Lbs6 5 i Lbs 6 3 not used E Gallons Twin Engine Liters Lbs 5 8 i Lbs 6 71 Kilograms 6 6 5 d Lbs 6 3 i DO NOT USE xo O Q tS SWITCH 3 9600 BAUD Loran Input Type Trimble 0 1 ARNAV 2 Bendix or IIMorrow Apollo NMS2001 800 820 3 Garmin 4 Northstar 5 Foster 6 IMorrow 611 612 and 618 7 Shadin Flow Meter 6 DO NOT USE Use this position to make selection on SWITCH 4 SWITCH 4 Other Loran Input Type 0 Northstar 1200 BAUD 1 Foster 1200 BAUD 2 611 612 618 1200 BAUD DO NOT USE 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Stage 1 Loopback Configuration Switch 1 is set to to indicate that the stage
28. 0 ME 2 s k REV T pare BY I DESCRIPTIC RIGHT ENGINE FUEL FLOW 7160 F ADC 2000 TRANSMITTER J1 P N 962830 2 5 4 43 SIG RIGHT 241546 ENGINE 10 GROUND FUEL FLOW LEFT ENGINE FUEL FLOW TRANSMITTER 26 SIG LEFT SIG 12 SIG SIG FUEL FLOW NOTES 1 FOR AIRCRAFT WITH FAURE HERMAN FUEL FLOW TRANSMITTERS PART 5 512 231 1 CONFIGURE THE F ADC FOR THE ALTERNATE DIGITAL K FACTOR TABLE MATRIX 1 K FACTOR IS 1 94 1 940 PPG 3 SET AIRDATA SWITCHES SW1 8 2 0 SW3 8 SW4 0 MINNEAPOLIS 55426 ui _ INSTALLATION WIRING F ADC 2000 MS CONN APPROVED ie AERUSPATIALE AS332 SUPER PUMA eee 6028 441 206 9808 016 1 8 14 98 BASELINE RELEASE DIRECTORY DRAWING REV Pecos Rev Dare TAPP 4028 A41 4 1 BENDIX KING 962830A Y S 4 X L 3 KLN90 A B KLN89 KLN900 962830 1 7 P901 P891 9002 NOTES 1 CONFIGURE SHADIN F ADC 2000 1 0 FOR FLOWMETER BENDIX C OR FLOWMETER BENDIX D IF USING THE BARO METRIC INTERFACE CONFIGURE SHADIN FUEL FLOW METER IZO FOR DN AIRDATA SHADIN F ADC 2000 RSe3e TX RSe3e RX SHADIN FUEL FLUW METER MICROFLO L 9120
29. 0 2 E _ 47600 2 F 49000 9 8 4900 9 9 49200 9 A _ 49300 9 B 49400 9 49500 2 0 REN 50000 E 4 XN 50000 E 5 ME NE 50400 E 6 E 50500 E 7 3 50800 E 8 0 1 55500 C 3 KCCCONENE wa 57000 A 0 ONE E MN 57200 A 2 5500 4 NE CNN _ 57400 A 4 NE _ 57500 5 _ 1 57600 ET EE p wass F i ss pug s F 7 DA 1 1 RE 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Page 10 6 Matrix 1 Alternate Digital K Factor Setting Table software version 93 04 04 PPG SWi SW2 PPG swi SW2 5 SW2 __200 1 1940 8 1600 4 E 40 1 1 jJ 20 3 D 16301 4 F 1 2 D 22001 91 ES 316900 5 0 53100 1 4 _ 2600 4 0 16800 5 5 520 5 30 Jp X Jj s ete 560 1 9 3600 4 5 j 1780 5 7 570 1 A 360 9300 6 3 58 1 B 3650 0 1 380 6 4 3590 Re Ee 2 31900 62 O 600 1 D 370 3 320 6 6 60 1 E 3760 4 340 6 7
30. 00 P N 962810 3 P N 962820 3 F ADC 2000 P N 962830 3 P N 962830 3 5 5 RIGHT ENGINE FUEL FLOW LEFT ENGINE FUEL FLOW L RAGEN 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 CASE GROUND Nol aoM GROUND SIGNAL R SIGNAL L SIGNAL L SIGNAL F ADC 2000 P N 962830A 3 P N 962830 3 5 4 P N 962830 3 5 DIGIDATA P N 912802 03 11 GROUND 7 R SIGNAL a AP gt 13 R SIGNAL m AA e 14 L SIGNAL 15 6 SIGNAL 3265013 1201 FLOW SIGNAL FROM FLOWMETER FLOW SIGNAL 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 CASE GROUND NFUR AIRCRAFT WITH THE FOLLOWING INDICATOR TRANSMITTERS SEE TABLE FOR INDICATOR WIRING INDICATOR PART CRAGEN 3265013 0601 w TRANSMITTER PART CRAGEN 3268011 0101 INDICATOR PART NU CRAGEN D 3265013 0801 3265013 1201 w TRANSMITTER PART CRAGEN TFF 2905 9 OR PIPER P N 489 487 AIRDATA SWITCHES AS FOLLOWS Swi 1 3 PROGRAM DIGIDATA
31. 1 loopback is being performed SWITCH 2 OAT Probe Type Shadin OAT Probe 1 ARINC 575 DO NOT USE 2 Rosemount 500 DO NOT USE 3 DO NOT USE SWITCH 3 Output 0 Format Z Trimble and Garmin Format X ARNAV 2 Generic 3 Surveyor 4 Bendix Bendix King and F ADC without Baro Interface 5 Bendix D Bendix King and F ADC with Baro Interface 6 Shadin S IIMorrow GX50 55 60 7 Bendix B fuel only 9 Garmin G 9 F Do Not Use SWITCH 4 Altimeter Selection for Baro DC Input None Type 1 Type 2 Type 3 Type 4 Type 5 Type 6 7 DO NOT USE Type 9 DO NOT USE Type 11 DO gt O Q 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER 1 2 3 4 5 6 7 8 9 10 11 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Page 9 10 ALTIMETER TYPES Kollsman PD 44929 935 done for Cessna 525 Bendix King KEA 130 and KEA 346 versions King 066 3062 XX XX 08 through 11 versions 00 though 07 have Baro Potentiometer ARINC 575 3 specification for ratio to Altitude Correction calculation Kollsman IDC 28007 427 429 Kollsman IDC 2870
32. 2 5 3 ARINC 429 Labels Associated with Switch Settings 0 Honeywell SPZ 5000 for Cessna 6 Trimble 8100 No label 275 1 Bendix KLN9OB or Global GNSXC LS 7 TNL 8100 2 HUD Heads Up Display for Flt Visions 8 Collins FMS 800 100 ms rate 3 UNSI 9 Mk VII GPWS 50 ms rate 4 EFIS40 50 A Mk VI amp VIII EGPWS 50 ms rate 5 ASINC Airshow Cabin Display Note that 3 and 6 are the same except for label 275 The following 15 a list of the different switch settings that the ARINC switch may be set to The ARINC switch position 15 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 Cessna Citation Jet Aircraft 2 Reserved 3 8100 UNSI 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 TNL 8100 with total fuel flow label 244 9 Collins FMS 800 100 ms rate 9 Allied Signal Mk VII GPWS 50 ms rate A Allied Signal Mk VI and VIII EGPWS 50 ms rate 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 2 5 4 Start Up Temperature and Times for Output Data Valid 2 6 Typical times for Output Data Valid
33. 30A 3 S 4 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 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 O 5 Table 2 Pressure Altitude Tolerance 1 2830 54 DIRECTORY 962830 5 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 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 2 Table 3 Vertical Speed Tolerance 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 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 10 000 Ea 4 2 5 6 NUN 06 E um 20 000 6 80 90 LA 9 E 2
34. 4 Northstar 1200 or 9600 baud 1200 is default for Northstar 5 Foster 6 IMorrow 611 612 and 618 1200 baud 7 Shadin Flow Meter 9 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 Morrow 611 612 618 1200 BAUD DO NOT USE 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Stage 1 Loopback Configuration Switch 1 is set to to indicate that the stage 1 loopback is being performed SWITCH 2 OAT Probe Type 0 Shadin OAT Probe 1 ARINC 575 DO NOT USE 2 Rosemount 500 DO NOT USE 3 DO NOT USE SWITCH 3 Output Format Z Trimble and Garmin Format X ARNAV Generic DO NOT USE Surveyor Bendix C Bendix King and F ADC without Barometric Interface Bendix D Bendix King and F ADC with Barometric Interface Shadin S IIMorrow GX50 55 60 Bendix B fuel only F DO NOT USE ON Q 2 SWITCH 4 Altimeter Selection for Baro DC Input 0 None 1 1 2 2 3 3 4 4 5 5 6 Type 6 7 7 9 NOT USE 9 9 DO NOT USE 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4
35. 4 962830A 2 S 4 962830A 3 S 4 Description Part Number Installation OAT Probe Assembly Kit P N 681201 1 Parts List OAT Probe Assembly Kit P N 681201 1 Installation Mounting Tray ADC 2000 Installation ADC2000 MS Conn No FF Quick Start P N 962830A X S 4 Installation ADC2000 MS Conn Digital FF Quick Start P N 962830A 1 S 4 Installation ADC2000 MS Conn Sine FF Quick Start P N 962830A 2 S 4 Installation ADC2000 MS Conn DC FF Quick Start P N 962830A 3 S 4 Installation Wiring ADC 2000 to COMM PWR BARO OAT Heading Quick Start Installation Wiring ADC 2000 Quick Start Digital Sine and DC Fuel Flow Installation Wiring ADC2000 MS Conn QS to Altimeter Baro Pot Installation Wiring Loop Back Harness for F ADC 200 2000 MS Connector Label ADC 200 2000 Access Cover P N 712801 Installation Serial to Argus 5000 7000 Converter 937000 03 Parts List Install ADC2000 MS Conn No OAT P N IK9630A 1 Installation Wiring F ADC 2000 w Analog to Beech King Air Indicators INSTALLATION DRAWINGS AND INSTALL KIT PARTS LISTS DATE 02 14 05 04 06 07 08 01 05 03 07 05 03 07 05 03 07 05 03 07 05 03 19 01 05 02 05 03 19 01 09 28 98 02 14 05 02 14 05 04 09 07 03 26 98 IM2830 AXS4M DOC DIR 962830 5 4 INSTALLATION MANUAL FUEL AIR DATA COMPUTER IM2830 AXS4 Shadin Avionics Sec VII 11 0 4028 A29 4028 A31 4028 A32 4028 A33
36. 4 962830A 3 S 4 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 F ADC 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 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 1s favorable 1n order to avoid running all of these signals to the tail of the aircraft Mounting the F ADC Consult the Drawings 4028 857 or 4028 871 or 4028 872 or 4028 873 and Drawing 4028 395 before mounting the ADC2000 Use the recommended hardware Any orientation is acceptable Make sure that
37. 4 A1001 A2001 A4001 B4001 4001 01001 D2001 D4001 D4101 4E2101 2101 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 102220 1188T 10420 11968 Reserved for future use DO NOT USE IDC P N KTS B45152 10 410 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Page 9 11 Stage 2 Loopback configuration Switch is set to 2 to indicate that the stage 2 loopback is being performed SWITCH2 Fuel Filter Type 0 Injector 1 Carburetor SWITCH 3 AND SWITCH 4 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 5125 700 LearJet 35 LearJet 55 Sabreliner 60 SSEC Only Lockheed Jetstar II Reserved for future DO NOT USE N 4 Q tS m m Q gt
38. 4028 A34 4028 A35 4028 A36 4028 A37 4028 A38 4028 A39 4028 A40 4028 41 4028 42 4028 43 4028 898 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 INSTALLATION DRAWINGS AND INSTALL KIT PARTS LISTS cont AIRCRAFT SPECIFIC Installation Wiring F ADC 200 2000 or DigiData with DC FF Piper Cheyenne PA31T Installation Wiring F ADC 2000 MS Conn Sine FF to Mitsubishi MU 300 and Model 400 Beechjet Installation Wiring F ADC 2000 to Mitsubishi MS Conn Sine FF MU 2 w Foxboro PC 620 System Installation Wiring F ADC 2000 MS Conn with DC FF to Cessna Citation 500 501 550 5550 551 552 Installation Wiring F ADC 2000 MS Conn with DC FF to Cessna Citation 525 Jet Installation Wiring 2000 MS Conn with Digital FF to Bombardier LearJet 24 25D Installation Wiring F ADC 2000 MS Conn with Sine FF to Rockwell Commander 690 and 695 Installation Wiring F ADC 2000 MS Conn with DC FF to Raytheon BeechJet 400A Aircraft Installation Wiring F ADC 2000 MS Conn with DC FF to Westwind 1124 Models Installation Wiring F ADC 2000 MS Conn to Fairchild SA226 Series Aircraft Installation Wiring F ADC 2000 MS Conn to Aerospatiale AS365N2 Dauphin Installation Wiring F ADC 2000 MS Conn to Aerospatiale 5332 Super Puma Installation Wiring 2000 MS Conn Shadin FF Indicators to Bendix King Nav Receiver Installation Wiring F ADC 2000 MS Conn and Shadin Conv
39. 422 NOT BOTH CLAMP 527291 6 P N AT RS232 PORT 2 RESERVED FOR FUTURE USE 3 83 7 5 amp PLUGS PINOUT J1 PINOUT 33 OAT SIGNAL 48 N C 34 N C 49 N C 35 HEADING 26 VAC C 50 N C 36 RS422 51 N C 37 FLAG RESERVED 52 OAT POWER 38 RS422 53 BARO WIPER PINOUT 532 39 RX RS232 54 POWER GROUND 40 ARINC 429 55 28V J1 PINOUT J PINOUT 22 ARINC 429 B 41 N C 1 N C 11 N C 23 RIGHT TXDR GROUND 42 RX 85232 A 3 N 13 25 44 4 SHIELD GROUND 14 N C 26 LEFT TXDR POWER de 5 BARO INPUT 15 N C 27 N C 46 N C 6 N C 16 BARO INPUT 28 N C 47 N C 7 HEADING X SYNCHRO INPUT 17 N C 29 N C 8 N C 18 HEADING 26 30 N C 9 TX 5232 19 TX RS422 31 10 LEFT FF TXDR GROUND 20 RX RS422 32 N C SRAETEUXR INSTALLATION ADC2000 rs V CONN DIGITAL FF QUICK START 4028 87 a NE a ca as 4 ka 5777051 VLC CORRECTED stand can 9710 028 10 27 97 OR PG 9628304 X 9 4 lal Ta T NOTES 1 INSTALLED WEIGHT 2 8 LB ZX USE FOUR 6 MOUNTING SCREWS FOR COMMUNICATION RX TX WITH LORAN OR GPS USE EITHER RS232 OR RS422 NOT BOTH RS232 PORT 2 RESERVED FOR FUTURE USE 7 5 T
40. 4XT 38D DIGIFLU L DIGIFLO L MINIFLO L P N 91053XT P N 91053XP P N 91204X 277 MINNEAPOLIS 55426 INSTALLATIUN WIRING F ADC 2000 MS SHADIN FUEL FLOW INDICATORS BENDIX KING NAV RECEIVER DRAWING ND remm Meet rer 4028 EPIS 54 EDJ ADDED P N 962830A 1 7 9808 06 KCL BASELINE RELEASE REV DAle APP D F ADC e P N 962830 5 4 P N 9628304 1 5 4 P N 962830A e S 4 P N 962830 3 5 4 1 5 7 P N 962830A NAVIGATIONAL RECEIVER RS232 TX RS422 TX RS422 TX RSe3e RX RS422 RX RS422 RX SHADIN CONVERTER P N 937000 03 EVENTIDE ARGUS P N 3000 RS422 RX RS422 RX P N 7000 ux RSe3e RX RSe3e TX RS232 INPUT HI RSe3e INPUT LOW NOTES USE RS 232 OR RS422 NOT BOTH CONNECT SHADIN CONVERTER P N 937000 03 IN PARALLEL WITH NAVIGATIONAL RECEIVERS SERIAL DATA INPUT CONSULT DRAWING NUMBER 4070 005 FOR WIRING AND STRAPPING INFORMATION DRAWING DA 8014298 umens m 53426 INSTALLATIUN WIRING F ADC 2000 MS AND APPROVED a KCL OGUA T3757 T Pas d EDD PADDED PON disi CUNVERTER TD EVENTIDE ARGUS iii ia ADDED P N 9628304 1 5 7 00097012 9 8 00 EDJ E VAS ADD RSE327RS422 TERMS
41. 75 RevC 4028 395 Rev C 681201 1 Rev 9630 1 Rev H changed Sec 2 2 removed 2 5 2 an 2 5 3 and added 2 5 3 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER 1 0 1 1 1 2 P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 OVERVIEW The Manual This manual is designed to facilitate the installation of the Shadin Fuel AIR DATA Computer ADC 2000 Product Information The Shadin ADC 2000 system is designed to provide a combined source of fuel and 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 KLN9O FMS 7000 2100 3000 KLN90A R5000 3100 2101 KLN90B KLN89 89B KLN900 Garmin BFGoodrich IIMorrow 150 155 155 XL 165 Pronav LNS 6000 611 612 618 230 230XL NMS 2001 300 300XL 900 820 360 430 530 GX50 55 60 Transmits Serial Data to ARNAV Magellan Note To find out which particular receiver Bendix King Trimble models have AIR DATA receive capability Garmin contact the manufacturers Transmits ARINC Data to ASINC Bendix King Honeywell Universal Airshow EFIS 40 50 SPZ 5000 UNS 1M Data Nav III Global Trimble IIMorrow GNSX TNL810O 2101 GNS XlIs 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATI
42. A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 2 5 2 ARINC 429 GAMA Output Labels 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 LABEL Description 9 2 3 4 5 074G Header 1000 o o 0 __ 1000 1000 0O75G Waypoint To From 100 o 100 100 100 jSeletedCouse 0 0 20 200 200 1155 Waypoint Group Checksum 100 o O o 100 100 114 Desired Track Tru 50 010 50 50 50 115 Waypoint Bearing True 50 0 0 50 50 50 116 Cross Track Distance 50 O0 O 50 50 50 147G Magnetic Variation 20 o 200 20 2093 PALT 1013258 200 50 200 jo 24 PALT Corrected 0 200 50 200 0 205 200 50 200 jo 206 Indicated Airspeed IAS 5 200 0 210 True Airspeed 10 100 O 100 21 200 0 20 jo 22 Vertical Speed AVS 0 200 50 200 10 23 TAT Static 2070 20 jo 244 0 0 0 jo 25106 ToGo 200
43. D GROUND 42 RS232 A 3 N C 13 N C 25 N C 44 4 SHIELD GROUND 14 N C 26 LEFT DC FF INPUT 45 5 INPUT 15 27 46 6 16 BARO INPUT 28 47 7 HEADING X SYNCHRO INPUT 17 29 8 N C 18 HEADING y H 30 N C ERRAT sus 10 SHIELD GROUND 20 RX RS422 No T ic SHADIN INSTALLATION ADC2000 MS CONN DC FF QUICK START DRAWNG NO SIZE REV 4028 873 D N 3 5 4 BEST Mundi a oe re PPT a 10522700 1370105 SAI REDRAWN CORRECTED stane LOCATION h anozo BASEUNE 19 27 97 PG BASELINE RELEASE M SEIO x 5 tcos luv oam 1 er omn SCALE DRAWING i P N 962830 5 4 Y X 1 2 3 4 962830 1 5 7 xyz COLLINS COLLINS COLLINS COLLINS SPERRY SIGM GMA SANDEL HEADING 528 2 51331 328 5 GRO SN3308 oc A f or 2 1 1 cou BUE ER V V X dee eeepc BENDIX KING GARMIN GARMIN LNS FOSTER OSTER ARNAV LN89 2155 430 530 6000 LRNSOO LENSON pes R501 R21 R30 R40 io 50 5000 5 0 m AV iH 0 cps HEADING HEADING 26 400HZ GP
44. E CI 5 5 FRONT VIEW amp PLUGS REMOVED PINOUT gt 33 SIGNAL 34 rc 35 HEADING 26 1 RIGHT SIDE gt 36 5422 pe 37 FLAG 5 2 PINOUT 58 RX 5422 Jl PINOUT J1 PINQUT Ji PINOUT ST TC 292 A 39 RX 85232 48 N C 1 11 22 ARINC 429 B 40 ARINC 429 A 49 N C 2 HEADING Y SYNCHRO INPUT 12 N C 23 SHIELD CROUND 41 N C 5 N C 13 24 42 RX 65232 51 4 SHIELD GND 14 25 43 52 5 INPUT 15 26 44 53 BARO 6 16 BARO INPUT 27 45 54 POWER GROUND 7 HEADING X SYNCHRO INPUT 17 N C 28 N C 46 N C 8 18 HEADING 26 VAC 29 47 9 TX 65252 19 TX 5422 30 DRAWING DATE 10 SHIELD GND 20 RX RS422 31 N C 32 N C INSTALLATION ADC2000 MS CONN NO FF QUICK START EV 4028 857 mom 00250 5 4 ser ioi 0505 00 2 T O 21 o REDRAWN CORRECTED PITOT STATIC LOCATION 9710 028 4007 97 PG CORRECTED PNOUTS _ 2 1 5 WEIGHT 2 8 LB MATING CONNECTOR e SUPPLIED AS PART OF INSTALL KIT Z USE FOUR 6 MOUNTING SCREWS P1 CONN MS24266R22B55SN P N 233272 ZA COMMUNICATION RX TX WITH LORAN OR GPS USE EITHER 65232 OR RS
45. FOR LEFT K FACTOR PPG LEFT OFFSET RIGHT OFFSET 0 1 25 ADD IND 3265013 0801 amp RAGEN P N EN w REV pad DMD SWe 1 SW3 0 SW4 0 46 160 TABLES 1 4028 LNUT d Or 7 CHEYENNE 1 INSTALLATION WIRING F ADC 200 2000 DR DIGIDATA WITH DC FF PIPER a DMD KCL ADD 5 962830 3 5 5 962830 3 5 5 DRAWING ND SLE REV oe 4058 a 2 NDTES JN FROM RIGHT ENGINE FF TRANSMITTER FROM LEFT ENGINE FF TRANSMITTER F amp DC SWITCH SETTINGS 9 AIRCRAFT S FUEL FLOW SIGNAL CONDITIONER P N 454586801 003 C SHLD GND FLOW SIGNAL IN FLOW SIGNAL IN TEMP SIGNAL IN TEMP SIGNAL IN FLOW METER FLOW METER 25V DC IN POWER GND X pm a POWER GND SHLD GND FLOW SIGNAL IN FLOW SIGNAL IN TEMP SIGNAL IN TEMP SIGNAL IN J H G F E FLOW METER F ADC 2000 P N 962830 2 5 4 SIG COND P N K FACTOR SWI 4SAS86801 003 5150 PPG 6 2 N 2 2 E A aio SHADIN x ran INSTALLATION WIRING F ADC 2000 MS CONN SINE FF TO MITSUBISHI MU 300 AND MODEL 400 DRAWING NO F ECC 5795 14 IESU RELEASE LECH DATE
46. IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 5 5 Connection to the Fuel Flow Sensor 1 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 2 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 3 Note that for single engines all fuel flow types should use left side inputs only 4 Install the transducers according to the engine STC using Drawing 4028 875 to connect the fuel flow transducer to the computer 5 the aircraft 1s equipped with a digital fuel flow system using transducer P N 680501 use Drawing 4028 875 refer to note 1 on that drawing and the STC drawing covering the installation 6 Before hooking to an existing fuel system in a turbine or jet application consult all installation drawings contained in this manual 7 the aircraft is equipped with a DC fuel flow system use Drawing 4028 875 for P N 962830A 3 S 4 and the STC covering the installation 6 the aircraft is equipped with a sine wave pickup coil type of fuel flow transducer use Drawing 4028 875 for P N 962830A 2 S 4 9 Make sure that the system is initialized with the proper transducer K factor for a digital or sine systems and with the proper airframe make
47. IN 11 CORRESPONDS FUEL MONITOR Z A CARD 12 CORRESPONDS TO FUEL MONITOR PIN X Lu 14 98 BASELINE RELEASE REV BY APPD pESCRIPT IQ IV 53426 M INSTALLATION WIRING F ADC 2000 MS CONN APPROVED APPROVED WITH DIGITAL FF BOMBARDIER LEARJET 24 25 028 DIRECTURY DRAVING 4028 035 P N F ADC 2000 P N 962830 2 5 4 FUEL FLOW IND RIGHT ENGINE FUEL FLOW RIGHT SIG SIG ENGINE FUEL FLOW IND LEFT ENGINE FUEL FLOW LEFT SIG 510 ENGINE NDTES 1 F R AIRCRAFT WITH THE FOLLOWING INDICATURS TRANSMITTERS INDICATOR PART NOS 850590 1 850590 507 DSF1549 OR 5154 9 TRANSMITTER PART NDS 850590 513 850590 515 2905 11 OR 151906 001 K FACTOR IS 27 6 27 600 PPG SET F ADC SWITCHES SW1 F SWe 0 SW3 F SW4 0 SHADIN m 35426 INSTALLATION WIRING F ADC 2000 MS CONN WITH SINE FF TO ROCKWELL COMMANDER 690 AND 695 282 th K i i A FILE NAME 1 E eel NEN BASELINE RELEASE xr ad LECO REV DATE BY JAPP D X DESCRIPTIO k rr AN F ADC 2000 P N 962830 3 5 4 RIGHT ENGINE F F IND P080 Ji SIG 43 SIG RIGHT SIG 24 516 FUEL 10 G
48. NAV RCVR 4028 438 Oe DESCRIPTION Nn GARMIN GARMIN 430 GARMIN 530 4001 5001 SHADIN F ADC 2000 MS RS232 TX ES 57 RS232 RX 56 SHADIN FUEL FLUW METER NOTES 1 CONFIGURE SHADIN F ADC 2000 1 0 FOR FLOWMETER GARMIN CONFIGURE SHADIN FUEL FLOW METER 1 0 FOR ON AIRDATA CONFIGURE GARMIN 430 530 170 FOR CHANNEL 1 TO SHADIN FADC AVIATION DIGIFLL L DIGIFLLU L MINIFLL L MICROFLO L P N 91053XT 91053XP P N 91204XT D 91204XT 38 D 4 MINIMUM SOFTWARE LEVEL ADC 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 12 FUEL FLOW TRANSDUCER SIGNALCS ARE CONNECTED THE SHADIN FUEL FLOW METER NO FUEL SIGNAL CONNECTED THE ADC INSTALLATION WIRING AE lt LSHADIN F ADC2000 MS CONN 111047005 D 4 29 31 ZK CHANGED SOFTWARE LEVEL IN NOTE 4 APPROVED SHADIN FUEL FLOW Sos c pas a URRECTED INDICATORS TO GARMIN 0211 047 B 3711 03 CONVERTED TABLE NOTE 4 ADDED w L MODELS TH TABLE ADDED NOTE 5 MINNEAPOLIS MN 55426 430 530 01037012 3 19 01 REMOVED SOFTWARE VERSION AND ADDED L FF METER BLOCK 4028 B98DJ DWG ECO DATE APP D DESCRIPTION NOT TO SCALE SHEET 1 OF 1 4028
49. O W X DESCRIPT SCA SHEET 1 OF 1 4028 A38 m F ADC 2000 P160 Ji P N 962830 2 5 4 RIGHT ENGINE FUEL FLOW INDICATOR SIG H e Es RIGHT SIG K ENGINE FUEL 10 GROUND FLOW LEFT ENGINE FUEL 161 FLOW INDICATOR LEFT H ENGINE te FUEL FLOW NOTES 1 FOR AIRCRAFT WITH FUEL FLOW INDICATOR PART NOS DSF1549 e 4 5 2 K FACTOR IS 26 8 26 800 PPG 3 SET AIRDATA SWITCHES AS FOLLOWS SW1 SWe m sS WS mU Z SHADIN esa Scie s5426 INSTALLATION WIRING F ADC 2000 MS CONN FILE NAM TO FAIRCHILD SA226 SERIES AIRCRAFT E 7 _ 6_ _ _ 9 _ _ 0 8 39 J DWG REV DATE L BY DESCRIPTION wa e 4028 A39 RIGHT ENGINE FUEL FLOW P169 F ADC 2000 TRANSMITTER 962830 2 4 1 43 SIG RIGHT le E 24 16 ENGINE 10 GROUND FUEL FLOW LEFT ENGINE FUEL FLOW TRANSMITTER 26 SIG LEFT SIG 1 SIG FUEL FLOW NOTES 1 FOR AIRCRAFT WITH FAURE HERMAN FUEL FLOW TRANSMITTERS PART lt 425 1024 118 CONFIGURE THE F ADC FUR THE ALTERNATE DIGITAL K FACTOR TABLE MATRIX 1 K FACTOR IS 3 88 3 880 PPG 3 SET AIRDATA SWITCHES AS FOLLOWS SW1 0 5 2 7 SW3 0 SW4 7 SHAADI INSTALLATION WIRING F ADC 2000 MS AEROSPATIALE 5365 2 DRAWING REV 4028 4
50. ON MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 13 System Configuration The Fuel AIR DATA system is a remote mounted computer which is connected to the GPS receiver via serial data It is also connected to the pitot and static line OAT probe fuel flow sensors altimeter barometric pressure potentiometers and the aircraft heading source Magnetic heading Navigational Left engine Receiver fuel flow Right engine fuel flow PITOT F ADC 2000 STATIC Arinc 429 output Barometric Pressure Interface IM2830 AXS4 Shadin Avionics IM2830 AXS4M DOC DIRECTORY 962830A X S 4 INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 14 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 series and the Garmin 430 530 Consult Drawing Number 4028 A42 contained in this manual for installation information for the Bendix King KLN series Consult Drawing Number 4028 B98 for installation information for the Garmin 430 530 Bendix King Shadin KLN90 A DigiFlo CE Fuel Flow Transmitter Shadin F ADC200 F ADC2000 15 F ADC2000 Argus Moving Map Configurations Shown below 15 the system configuration that supports output to a Eventide Argus movi
51. ROUND FLOW LEFT ENGINE F F IND P079 FLOW 26 516 LEFT 12 SIG FUEL NOTES 1 FOR AIRCRAFT SERIAL NOS RK 45 RK 49 AND AFTER WITH FUEL INDICATOR PART 900 3 2000 2 K FACTOR IS 1154 11 540 PPG OFFSET IS 0 BNSET F ADC SWITCHES TO SW1 0 SW2 2 SW3 0 SW4 0 ssie INSTALLATION WIRING F ADC 2000 MS CONN WITH DC FF TO RAYTHEON a a rs ss ILE NAME BEECHJET 400A AIRCRAFT l E wr 4008 7 rir A F ADC 2000 P N 962830 3 5 4 RIGHT ENGINE FUEL FLOW INDICATOR SIG 2 43816 RIGHT ENGINE SIG n 24 SIG FUEL 10 GROUND FLOW LEFT ENGINE FUEL FLOW INDICATOR SIG SIG FLOW L 26 516 LEFT K 12 16 FUEL NOTES 1 FOR AIRCRAFT WITH THE FOLLOWING INDICATOR TRANSMITTERS INDICATOR PART ND CRAGEN 1291 2 B TRANSMITTER PART ND GULL 151 909 001 2 K FACTOR IS 10 49 10 490 PPG OFFSET IS 0 3 SET AIRDATA SWITCHES AS FOLLOWS SW1 1 SW2 8 SW3 0 SW4 0 sexum INSTALLATION WIRING F ADC 2000 MS CONN WITH DC FF WESTWIND m 1124 MODELS APPRUVED KCL j M I ____ __ BASELINE RELEASE ee 4028 9 EC
52. S 5232 _ We TR eas poe epee o us R 1 AIRSHOW ense TE ws n ne A220943001 ARINC 429 OUTPUT TX s Ss er Ke wre WHITE eee ee Lowe wer wi 36 BARO d INPUT SEE SPECIFIC AIRCRAFT SECTION OR BLACK AN J RESERVED NOTE NUSE EITHER RS232 OR RS422 NOT BOTH NAV GPS TO BATT BUS 28VDC GROUND 10 57 _ 55426 asf INSTALLATION WIRING ADC 2000 PWR cF HEADING QUICKg S TART 101037012 5728 1000970121 9 ADO GARMIN 430 530 GPS AND SANDEL HDG SOURCE 9710 028 OLR PG IBASEUNE RELEASE 1028 PA 5 ECO g DATE BY DESCR i DO N SCALI RAWIN SHEET 10F 1 4028 874 B P N 9628314 3 5 8 P N 962831 1 5 8 962850 3 5 8 962850 1 5 8 P N 962850 3 5 4 P N 962830 1 5 9 P N 962850 1 5 7 P N 962830 1 5 4 LEFT ANALOG SHIELD LEFT SIGNAL IN LEFT TXDR PWR LEFT TXDR GND FUEL GROUND FLOW RIGHT RIGHT SHIELD RIGHT SIGNAL IN GROUND RIGHT TXDR PWR RIGHT TXDR GND P N 9628314 2 5 8 P N 962830 2 5 8 P N 962830 2 5 4 NOTE NDO NOT CONNECT J1 P1 26 OR J1 P1 43 WHEN INTERFACING WITH EXISTING FUEL FLOW SYSTEM LEFT SHIELD
53. _ 620 1 F 380 5 3160 6 8 60 2 _ 380 4 6 31800 6 9 _ 640 2 1 340 6 3200 6 A 60 2 3880 7 32200 6 60 2 3 320 8 32400 6 __670 2 4 3960 9 3260 6 D _ SA __690 2 6 4000 4 7 3300 6 FP __700 2 7 jJ 440 B 320 7 0 70 2 8 400 C 340 7 20 2 9 4120 D 3600 7 2 0 2 A _ ao E 3400 7 3 70 2 B 420 0 F 320 7 4 750 2 c 4200 4 8 340 7 5 7600 2 D 440 4 9 3460 7 6 770 7800 2 F uo 5 8 35000 7 8 790 3 0 11900 5 1749 35200 329 JD 4 398990 D gt 980 3 _ so 5 F 36800 7 F _ 90 3 7 14000 6 4800 8 1 1006 di m 1200 p __1200 3 9 1440 6 2 f __1400 3 A jus 4 1600 3 B Ji 4 J C 121 X 4 _ ____ 7 Table 8 Alternate Digital Factor Settings DIRECTORY 962830 5 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 SECTION 11 0 INSTALLATION DRAWINGS AND INSTALL KIT PARTS LISTS NOTES J REFERENCE PROBE ASSEMBLY KIT AVOID INSTALLING
54. 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 18 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 Then as soon as the fuel flow exceeds 15 pph the AIR DATA continues to return a fuel flow of 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 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
55. al K Factor Settings PPG SWI SW2 PPG Swi SW2 SWI SW2 80 p p soo 5 15300 E F Table 7 Digital K Factor Settings 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Page 10 4 Matrix 0 Digital K Factor Settings Continued 23800 4 29800 F B 40000 9 4 _ 40200 9 5 30200 F D 40400 9 6 _ 24400 B 4000 9 J 7 24600 B B 33800 6 9 400 9 D _ _ 24800 B C j 37000 B 9 41000 9 E 25000 B D 37200 B 8 41200 9 F _ Table 7 Continued Digital K Factor Settings 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Page 10 5 Matrix 0 Digital K Factor Settings Continued SWI Table 7 Continued Digital K Factor Settings pu SW2 PPG E ERN mE REN ME NM ME enm B ME NH ss s sami LP EE ND e LI NK UK EE NN L UE j Le PPG SWI SW2 PPG swi p 46200 2 8 46400 2 9 46600 2 46800 2 B 9000 _ C _ 47200 2 D 4740
56. e 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 Lear 25D SSEC only Airplane Manual LearJet 25D F AFM Performance FAA approved 10 14 86 Altitude Correction Figure 5 10 FM 018 Release A Copilot system Page 5 18 Learjet 35 SSEC only Flight Manual LearJet 35 Normal System Flaps up Gear up Page 5 18 FAA approved 4 30 76 Altitude Position Correction Figure 5 10 Reissued 2 25 81 Pilot s Altimeter STBY amp Copilot s Altimeter Learjet 55 SSEC only Gates Learjet 55 APM Performance Data Flaps up Gear up Page 5 20 FAA approved 3 17 81 Altitude Position Correction Figure 5 11 Change 13 Lockheed Jetstar SSEC only Airplane Flight Manual Performance Data Weight 32 000 Lb Clean Configuration Leading Edge Flaps up Trailing Edge Flaps up Landing Gear up Page 4 25 FAA approved 12 14 76 Altimeter Installation Correction Figure 4 15 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Page 2 12 SSEC PSEC LISTING Continued Mitsubishi MU 300 SSEC only Airplane Flight Manual Diamond JA 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 Section 5 Document No H S
57. ead the switch positions Switch 1 is set to different positions to select the separate stages that the loopback is performing There are 2 different loopback procedures Use loopback procedure 1 for Software Version 93 02 67 Use loopback procedure 2 for software versions 93 04 02 and above Note that procedure 1 has 4 stages and procedure 2 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 VIEW FROM END A 1 2830 54 DIRECTORY 962830 5 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Loopback Procedure 1 for Software Version 93 02 67 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 Gallons Single Engine Liters i 055 8 Lbs 6 71 I i Kilograms Lbs6 5 Lbs6 3 i not used i Gallons Twin Engine Liters i 105 5 8 Lbs 6 71 7 Kilograms Lbs 6 5 Lbs 6 3 Q gt o O Q t2 SWITCH 3 9600 BAUD Loran Input Type Trimble 0 1 ARNAV 2 Bendix or IIMorrow NMS2001 800 820 GX 50 55 60 9600 3 Garmin
58. ected 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 were derived from specific aircraft data referred to in section 2 6 4 To configure the Shadin F ADC for a specific aircraft model refer to section 9 1 2830 54 DIRECTORY 962830 5 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 2 6 4 SSEC PSEC LISTING Beechcraft Beechjet 400 SSEC only Airplane Flight Manual BeechJet 400 Section 6 Performance Page 6 14 FAA approved 1 86 Altitude Correction Figure 6 8 Revision 9 14 92 Copilot System Boeing 707 321B Advanced SSEC Airplane Flight Manual Boeing 707 Section IV Performance Page 19 FAA approved 3 27 69 06 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 06 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 Revisi
59. ency 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 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 6 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 2 8 3 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 Maximum Input Voltage 12 Vdc The altimeters supported are listed in section 9 2 and are dependent upon the ADC2000 software version level IM2830 AXSAM DOC DIRECTORY 962830A X S 4 INSTALLATION MANUAL FUEL AIR DATA COMPUTER 1M2830 A XS4 Shadin Avionics P N 962830A 1 962830A 2 962830A 3 2 9 Statistical Specifications 2 9 1 Mean Time Between Failures MTBF 17 660 hours Page 2 16 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avion
60. er 65 WestWind 1124A Lear 24 Raytheon Hawker HS 125 3A Falcon 20 F Falcon 20 C D Lear 25D Douglas DC 8 Beechjet 400 Boeing 707 321B Cessna Citation 5550 Falcon 10 Falcon 50 Raytheon Hawker 5125 700 Learjet 35 Learjet 55 Sabreliner 60 SSEC Only Lockheed Jetstar II Reserved for future DO NOT USE 3 O m mI O gt gt T 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Stage 3 Loopback configuration Switch is set to 3 to indicate that the stage 3 loopback 15 being performed SWITCH 2 K FACTOR TABLE SELECTION For F ADC 962830A 1 S 4 and 962830A 2 S 4 only 0 Standard K FACTOR Matrix 0 Table 2 in this manual 1 Alternate K FACTOR Matrix 1 Table 3 in this manual 2 F DO NOT USE SWITCH 3 FUEL FLOW DELAY TIME 0 No Delay 1 5 Second Delay 2 10 Second Delay 3 15 Second Delay 4 20 Second Delay 5 25 Second Delay 6 30 Second Delay 7 35 Second Delay 9 40 Second Delay 9 45 Second Delay DO NOT USE SWITCH4 SPECIAL OPTION DESCRIPTION 0 ARINC 429 labels 206 IAS and 210 TAS are not transmitted 1f the IAS 20 knots 1 ARINC 429 labels 206 IAS 210 TAS transmitted
61. erter to Eventide Argus Installation Wiring F ADC2000 MS Conn Shadin FF Indicators to Garmin 430 530 01 17 05 08 14 98 07 19 00 08 14 98 08 14 98 08 14 98 08 14 98 08 14 98 08 14 98 08 14 98 08 14 98 08 14 98 03 19 01 03 19 01 04 29 11 IM2830 AXS4M DOC DIR 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 REVISION LOG APPD _ 11797 KCL Baselinerelease 8 20 98 Format change update Limitations section include aircraft specific wiring drawings 12 08 98 KCL Update section 2 3 9 9 9 10 9 11 and Table 1 Update DWG No 4070 005 replace DWG No 4028 A30 with 4028 A62 and include DWG No 4028 A29 and 4028 80 EDJ Added Bendix B amp Garmin Format G Loran output to page 9 7 Changed page 1v due to change C 1 31 00 on page 11 16 Added one more Indicator Transmitter to 4028 29 Installation wirine drawing Page iii changed by OAT kit and 4028 874 upgrade Page iv changed by 4028 A43 correction and 4028 A98 new dwg Page 1 1 and 1 3 changed by Garmin 430 530 Page 2 1 changed by OAT tolerance IVS change of 10 000 fpm and lowering PITOT and IAS low end speed to 18 knots per BELL requirements Page 2 2 2 3 amp 2 4 changed by Labels 234 amp 235 and Mk VI amp 9 08 00 EDJ VIII inclusion Pages 2 9 amp 2 10 changed by Raytheon Hawker HS 125 3A page move
62. ettings Table below 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 0 4 Configuration is now complete 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Page 10 2 Analog K Factor Settings Table Standalone AIR DATA Analog Fuel Flow Chart Manufacturer _____ SWI SW2 SW3 SW4 K Factor KingAir B200 0 I 77000 Beech KingAir A100 0 1 0 2 Beech 090 o 1 0 2 Beech KingAiF0O o 0 0 I Beech 90 _ 0 0 O I Beech KingAir200 __ 0 O I Beech jBechet 0 2 o o 1150 Beech 00 0 3 0 2 Beech 0 4 0 o 3800 Beech 0 5 0 o 370 0 4 Beech o 6 0 o 2850 Cessna Citation I C 16270 Le VSDL 0C208E Gauge 393002 009 Cessna Citaioll SI 0 C 0 0 1270 Cessna Citation OO D 0 4 Cessna 525 0 E 0 0 2180 Piper Cheyenne I 1 9 0 4190 Piper 1 1 0 0 46150 Lea
63. ics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 3 0 CERTIFICATION TSO C106 C44a Environmental Categories RTCA DO 160B Temp ALT F2 Temp Variation Humidity Shock amp Vibration Magnetic Effect Power Input Voltage Spike AF Conducted Susceptibility Induced Signal Susceptibility RF Susceptibility Emission Y e y N O gt 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER 4 0 P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 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 When interfacing an altimeter to the Shadin barometric pressure potentiometer option consult the list of supported altimeters contain in this manual or contact the Shadin Technical Support 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER 5 0 5 1 5 2 5 3 962830A X S 4 962830A 1 S 4 962830A 2 S
64. meter Baro Pot optional 1 Use the Installation wiring diagram 4028 A44 to connect the altimeter to J1 of the Air Data computer 2 Remember to select the correct altimeter type in the software configuration See section 9 in this manual 5 10 Post Installation Checkout 1 The pitot and static system must be checked for leaks 2 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 3 Select heading page Slew compass through 360 The error should be within 1 4 Select the OAT page Compare to the reported ambient temperature The error should be 5 engines and select fuel flow page Compare fuel flow readout with engine manufacturer s fuel flow charts under ambient temperature and pressure conditions 6 Set Barometric pressure to a known value and verify that the reported barometric pressure at the Navigational Receiver 15 that value 0 01 In Hg if the option 15 installed 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 6 0 OPERATING INSTRUCTIONS 1 Power the avionics DC buss and the Navigation Management System 2 After the warm up period density altitude and PALT are available IAS will be available b
65. ng 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 A43 contained in this manual Shadin RS 232 or 5422 Shadin Navigational Argus F ADC2000 Converter RS 232 or RS422 P N 937000 03 Moving Map P N 5000 P N 7000 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 2 0 FUEL AND AIR DATA SYSTEM SPECIFICATIONS 2 1 Input Data Range Pitot 18 to 350 kt Static 1000 to 55 000 ft OAT 60 C to 60 C Heading 0 360 Fuel Flow 110 450 Range Selected K Factor 500 to 130000 PPG Continuous 2 2 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 C to 60 C TRUE HEADING 7 0 360 degrees MAGNETIC HEADING 0 360 degrees IVS Table 3 10 000 ft min TAS Table 1 20 600 MACH Table 4 2 95 WIND SPEED 5 kts 5 360 kts WIND DIRECTION 102 0 360 degrees FUEL FLOW 2 1 450 Listed accuracy s at 25 and after warm up is complete 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 9628
66. number 962830A YS4 Y X 1 2 or 3 AIR 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 02 67 and 93 04 02 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 ADSETUP 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 AIR DATA via the serial communication port See ADSETUPF User Manual for more details 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER 9 2 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 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 62 contained in section 11 The purpose of the loop back harness is to tie the RS 232 transmit and receive ports together This allows the software when the unit is powered on to r
67. on 2 8 1 Heading Interface The heading interface follows the ARINC 407 standard line voltage of 11 8 Vrms Synchro Leg Input Impedance H 10 kohm 17 kohm Y 17 kohm 2 8 2 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 15 connected to a dedicated fuel flow transmitter and the second 15 that the ADC 15 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 0 5Vdc where R is the input impedance of the aircraft fuel flow indicator For example with an input impedance R 1 Mohm the voltage swing Vs 4 27 With the fuel flow information is encoded in frequency and not amplitude the loading effects do not produce an error provided the aircraft indicator can detect the signal transitions 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER 962830A 1 962830A 2 962830A 3 Page 2 15 2 8 2 2 Sine Wave Fuel Flow Interface The interface source signal amplitude varies with frequ
68. on 53 Dated 11 Dec 85 Pilot amp Copilot system Page 4 17 1 Cessna 501 SSEC only Airplane Flight Manual Cessna Citation I SP Model 501 Section IV Performance FAA approved Altitude Correction Figure 4 5 Original Pilot amp Copilot system Page 4 15 NOTE Uses same Hardware configuration as Cessna 500 Cessna 525 SSEC only Airplane Flight Manual Model 525 Altitude Correction Rept FT525 4 Pilot amp Copilot system Page 47 Cessna 550 SSEC only Airplane Flight Manual Cessna Citation II Model 550 Section IV Performance FAA approved Altitude Correction Figure 4 5 Original Pilot amp Copilot system Page 4 15 Cessna 560 SSEC only Airplane Flight Manual Model 560 S N 259 amp Below Section IV Performance FAA approved Altitude Correction Figure 4 5 Original Pilot amp Copilot system Page 4 17 1 2830 54 DIRECTORY 962830 5 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Page 2 10 SSEC PSEC LISTING Continued Cessna 560 SSEC only Airplane Flight Manual Model 560 S N 260 amp Up Section IV Performance FAA approved Altitude Correction Figure 4 5 56 00 Pilot amp Copilot system Page 4 19 Citation 5550 SSEC Airplanes 0115 through 0160 Except Airplanes Incorporating 5 5550 32 7 and Airplanes 0001 through 0114 Incorporating SBS550 32 1 but not SBS550 32 7 Section IV
69. r Learjet O0 7 0 o 1580 Lear Moddi360V __ 2 0 0 1150 Lear ____ 36 10 0 8 0 0 2380 Boeing Boeing73730 0 9 o 3 1790 British Aero ___ 7 0 0 1580 British Aero 125 800 0 A 0 0 British Aero HS 125 0 B 0 o 10490 Canadian CL6O0 0 F o 0 6590 Canadian CL601 1 5130 Dornier 20 228 1 1 0 46150 Daussault FALCON10 1 2 0 0 11540 Daussault FALCON20 1 2 0 0 7690 Daussault TFE 371 1 2 0 0 7090 Swearngen MERLIN 0 4 0 0 38460 Gulfstream GULFSTREAMI 1 3 0 0 280 Gulfstream GULFSTREAM II 1 4 0 2310 Aerospatiale PUMA 1 5 0 0 7620 DHC jJDHCDASH8 1 6 o 0 1930 IA 1125 1 7 0 5 WESTWINDID4 1 8 0 o 10490 Sikorsky __ 5 76 1 1 o 0 46150 Sikorsky __ 5 768 0003 10 6 o 2850 Sabre 5 6 _ 1 7 0 5 Table 6 Analog K Factor Settings Table 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 Page 10 3 Matrix 0 Digit
70. 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 1f necessary 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 5 4 Mounting the OAT Probe 1 Refer to drawing 4028 005 and OAT Probe Assy Kit 681201 1 Use the supplied stiffener to support the probe Keep the probe away from transmitting antennas and static ports of autopilots to avoid interference 2 Refer to drawing 4028 874 The OAT probe power is supplied from red wire J1 52 The OAT signal is the white wire from J1 33 At least the signal wire to the ADC2000 should be shielded and terminated at the ADC2000 only 3 The sun shield must be installed for proper indication of OAT 4 For single engine installation avoid mounting the OAT probe on the belly of the aircraft to avoid erroneous reading due to the presence of hot exhaust gases 5 Below is an OAT to C to input current conversion chart for use in testing the OAT Probe OAT C Inputa OAT C InputgA OAT C Inputa OAT C 6 23 J 20 23 20 23 50 223 J 10 263 30 303 40 233 273 o 33 30 23 jJ o 283 50 323 Input uA 1 1 uA 1 2830 54 DIRECTORY 962830A X S 4
71. ut will be out of range until actual airspeed is available Winds aloft will be available if the is greater than 40 Kts and magnetic heading 15 within 40 of magnetic track 3 Fuel Flow Fuel Used Fuel Remaining Heading and OAT will be available after power up 4 Refer to the specific Nav Receiver Operator s Manual for page selection of various data 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 7 0 INITIALIZATION 1 system requires initialization of factor for fuel flow transducers or aircraft model for DC fuel flow sensors Refer to Table 1 analog for fuel flow and Table 2 or Table 3 for digital or sinewave fuel flow 2 Refer to the specific Navigational Receiver Operator Manuals for the serial port set up 1 2830 54 DIRECTORY 962830A X S 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 8 0 MAJOR COMPONENTS OF THE SYSTEM 1 Nav Receiver Input Output 2 Fuel AIR DATA Computer 3 Outside Air Temperature Probe P N 6812010 1 2830 54 DIRECTORY 962830 5 4 IM2830 AXS4 Shadin Avionics INSTALLATION MANUAL FUEL AIR DATA COMPUTER 9 0 9 1 P N 962830A X S 4 962830A 1 S 4 962830A 2 S 4 962830A 3 S 4 CONFIGURING THE AIR DATA Part

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