INSTALLATION MANUAL FUEL/AIR DATA COMPUTER

4028-936 Installation Wiring, F/ADC200, 2000 or DigiData with DC FF to Cessna Citation 500, 501, 550, S550, 551, 552 02/14/05 A 4028-937 Installation Wiring, F/ADC200, 2000 or DigiData with DC FF to Cessna Citation 525 Jet 02/14/05 A 4028-938 Installation Wiring, F/ADC200, 2000 or DigiData with Digital FF to BomBardier LearJet 24, 25D 01/17/05 A 4028-939 Installation Wiring, F/ADC200, 2000 with Sine FF to Rockwell Commander 690 and 695 02/14/05 A 4028-940 Installation Wiring, F/ADC200, 2000 or DigiData with DC FF to Raytheon Beechjet 400A Aircraft 02/14/05 A 4028-941 Installation Wiring, F/ADC200, 2000 or DigiData with DC FF to Westwind 1124 Models 02/14/05 A 4028-942 Installation Wiring, F/ADC200, 2000 to Fairchild SA226 Series Aircraft 01/17/05 A 4028-949 Installation Wiring, F/ADC200, 2000 to Aerospatiale AS365N2 Dauphin 02/14/05 A 4028-950 Installation Wiring, F/ADC200, 2000 to Aerospatiale AS332 Super Puma 02/14/05 A 4028-A29 Installation Wiring, F/ADC200, 2000 or DigiData with DC FF Piper Cheyenne PA31T 01/17/05 C IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: vi of vi REVISION LOG REV. DATE APP’D CHANGE – 6/08/95 RR Release A 9/12/95 SES Miscellaneous updates B 6/09/97 KCL 4 stage loop back procedure, Report to 4028B, Expand Index C 6/23/97 KCL Revise Limitations Section D 3/27/98 KCL Format change, SSEC listing, software configuration update, new installation DWGs. E 12/09/98 KCL Update pages 1-1, 9-9, 10-2, DWG 4028-944 and 4070-005 and include DWG’s 4028- A29 and 4028-A80. F 3/16/99 KCL Updated Drawings 4028-411 and 4028-A29, and Install Kit P/N IK9628 G 1/31/00 EDJ Added Bendix B & Garmin, Format G, to page 9-7. Added one more Ragen Indicator/Transmitter to page 11-31. H 9/18/00 EDJ Page 1-1 & 1-3 changed to add Garmin 430/530 GPS. Page 2-1 changed by OAT tolerance, IVS changing to 10,000 fpm, and Pitot and IAS set to 18 knots for low speed. Page 2-6 & 2-7 changed by correcting LearJet HS-125 to Raytheon Hawker HS-125 and moving to page 2-7. Page 5-1 changed by adding TSO paragraph. Page 5-2 & 8-1 changed by OAT kit. Page 5-4 changed by adding Sandel hdg source. Page 9-1 & 9-2 changed by SW version numbers. Pages 9-5 & 9-8 (blank pages) removed. Pages 9-9 to 9-12 added for loopback procedure 3. New page 9-8 changed to remove Switch 4 ARINC setting. Page iv changed by OAT kit, 4028-411, 4028-943, and 4028-B94. J 11/03/00 KCL Add sections 2.8 and 2.9. Update sections 2.0, 5.1 and 5.7. K 08/30/02 EDJ Added P/N 681201-1 OAT probe installation and parts list to page iv drawing list. Corrected page 10-3 Table 2. Added pages 9-13 to 9-21. Page 9-13 became 9-22. L 02/25/05 ZK Changed Company name. Removed 681201A-1 dwg, parts list, and 93.00.79 Loopback procedure. Corrected Table 1 page 10-2, 4028-A29, 4028-938, 4028-942, and 4028-943. Incorporated updated IK9628 and P/N 681201-1 Parts list. Updated Section 11.0. M 09/22/05 ZK Updated 4028-944 and section 2.2. Corrected typos on pages 2-3, 5-1 and 10-5. N 04/06/07 ZK Changed Company name. Updated 681201-1 and IK9628 parts list. P 04/29/08 EDJ Updated all sections with P/N 962820-1(A), -2(A), & -3(A), updated Section 2.2, 2.7, 3.0, and 9.0. Added Antonov and Yak-40 SSEC information in Section 2.6.4. R 04/29/11 ZK Updated Drawings 4028-B94 and 4005-642. T 10/11/21 ZK Corrected SAT and TAT description on page 2-5. Updated company address. The information in this 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. IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) 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 200). 1.2 Product Information The Shadin ADC 200 system is designed to provide a combined source of fuel and air data. Listed below are the navigational systems that the ADC 200 has been designed to be compatible with. Receives Serial Data from: Magellan Avidyne Skynav 5000 440, 540 ARNAV Trimble Bendix King STAR 5000 2000/2000A KLN90 FMS 7000 2100/3000 KLN90A R5000 3100/2101 KLN90B KLN89/89B KLN900 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, 60 650, 750 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. IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 1-2 1.3 System Configuration The Fuel/Air data system is a remote mounted box, 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 and the aircraft heading source. FUEL/AIRDATA L. ENGINE FUEL FLOW R. ENGINE FUEL FLOW PITOT STATIC OAT MAG. HEADING SYSTEM CONFIGURATION NAV RECEIVER IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) 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 series and the Garmin 430/530. Consult Drawing Number 4028-947 contained in section 11 for installation information on the Bendix/King KLN series, and Drawing Number 4028-B94 for the Garmin 430/530. Bendix/King KLN90, A, B KLN89 KLN900 Shadin DigiFlo MiniFlo MicroFlo Shadin F/ADC200 RS-232 RS-232 RS-232 L. Fuel Flow Transmitter R. Fuel Flow Transmitter Garmin 430, 530 or 1.5 F/ADC200, Argus Moving Map Configurations. Shown below is the system configuration that supports output to a Eventide Argus moving map using the Shadin serial to serial data converter P/N 937000-03. The fuel and Air data are displayed on the Eventide-Argus moving map. Consult Drawing numbers 4070-005 and 4028-948 contained in section 11. Navigational Receiver Shadin F/ADC200 RS-232 or RS422 Shadin Converter P/N 937000-03 Eventide Argus Moving Map P/N 5000 P/N 7000 RS-232 RS-232 or RS422 IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 2-1 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 1 to 450 GPH Range Selected K Factor 500 to 130000 PPG Continuous 2.2 Output Data Range PARAMETER Accuracy* RANGE IAS Table A 20 to 350 kts. P.ALT Table B –1000 to 50000 ft. OAT ±1.5°C per TSO –60°C to +60°C TRUE HEADING ±2° 0 - 360 degrees MAGNETIC HEADING ±1° 0 - 360 degrees IVS Table C ± 10,000 ft./min. TAS Table A 20 - 600 kts. MACH Table D .2 - .95 WIND SPEED ±5 kts. 5 - 360 kts. WIND DIRECTION ±10° 0 - 360 degrees FUEL FLOW ±2% 1-450 GPH * Listed accuracies are after warm-up is complete per the ambient temperatures listed in Section 2.6.1 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 KNOTS TOLERANCE ± 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 A - Calibrated Airspeed Tolerance IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 2-2 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 FEET TOLERANCE ± 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 B -Pressure Altitude Tolerance IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) 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 FPM 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 Table C- Vertical Airspeed Tolerance IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) 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 .4 .012 .5 .010 .6 .0075 .7 .005 20,000 .4 .012 .5 .010 .6 .0075 .7 .005 30,000 .6 .0075 .7 .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 D - MACH Tolerance IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 2-5 2.3 Dimensions (including mounting rack) Size: 6.3"L x 3.5"H x 3.1"W Weight: 20 oz. 2.4 Power Requirements System Power required: 28 VDC @ 1300 mA 14 VDC @ 900 mA 2.5 Output Data Electric Format: RS-422 or RS-232 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) Pressure Altitude Fuel Used Right Wind Direction and Speed Rate of Turn Fuel Used Left Vertical Speed Fuel Remaining Static Air Temperature (SAT) NM/Gal (ground) Total Air Temperature (TAT) Fuel to Destination Fuel at Destination Note: Not all parameters will be available to all navigational receivers. Contact the manufacturer for display capabilities. IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 2-6 2.6 Limitations 2.6.1 Warm-up time 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 15 minutes warm-up required -40°C ambient 20 minutes warm-up required If the ADC has been configured for a fuel flow delay, fuel flow and thus fuel used information shall be unavailable at startup for the duration of the selected delay. 2.6.2 Supplemental equipment All Shadin F/ADC(s) and ADC(s) are not designed to replace factory installed 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. 2.6.3 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 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. IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 2-7 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&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&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&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 & Copilot PSEC Airplane Flight Manual, Boeing 707, Section IV, Performance Page 18 FAA approved 9/20/66, D6-1588 Airspeed Calibration FLAPS UP Pilot & 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 & Copilot system Page 4-17.1 IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 2-8 2.6.4 SSEC/PSEC LISTING (Continued) 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 & 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 & 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 & Copilot system Page 4-15 Cessna 560 (SSEC only) Airplane Flight Manual, Model 560, S/N 259 & Below, Section IV, Performance FAA approved Altitude Correction Figure 4-5 Original Pilot & Copilot system Page 4-17 Cessna 560 (SSEC only) Airplane Flight Manual, Model 560 , S/N 260 & Up, Section IV, Performance FAA approved Altitude Correction Figure 4-5 56FMA-00 Pilot & Copilot system Page 4-19 Cessna Citation S550 (SSEC only) Airplanes -0115 through -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 & Copilot IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 2-9 2.6.4 SSEC/PSEC LISTING (Continued) Douglas DC-8 SSEC Airplane Manual, Douglas DC-8, Section IV, Performance Page 20 FAA approved Altitude Correction DAC-33161 10/1/66 Pilot & Copilot system PSEC Airplane Manual, Douglas DC-8, Section IV, Performance Page 11 FAA approved Airspeed Correction DAC-33161 10/1/66 Pilot & 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 & 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 IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 2-10 2.6.4 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 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 & Copilot system Page 4-16 LearJet 25D (SSEC only) Airplane Manual, LearJet 25D/F AFM, Performance FAA approved 10/14/86 Altitude Correction Figure 5-10 FM-018 Release A Copilot system Page 5-18 LearJet 35 (SSEC only) Flight Manual, LearJet 35, Normal System, Flaps up, Gear up Page 5-18 FAA approved, 4/30/76 Altitude Position Correction Figure 5-10 Reissued 2/25/81 Pilot’s Altimeter- STBY & 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 IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 2-11 2.6.4 SSEC/PSEC LISTING (Continued) 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, 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 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 & 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 lbs. Yak-40 (SSEC only) Airplane Flight Manual, Sect. 7.1.3. Page 7 Yak-40, 1995 Altitude correction IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 2-12 2.7 Part Numbering Scheme P/N 962820 - X A ADC200 D-SUB Connector Fuel Sensor Type X=1, Frequency/Level Interface X=2, Sine Wave X=3, DC “A” means software has been certified to RTCA/DO-178B Level D “ “ blank means software has been certified to RTCA/DO-178A Level II IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 2-13 2.8 Electrical Interface Specifications The specifications for the heading and fuel flow interfaces are listed in this section. 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 X 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 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 impedance R = 1 Mohm, 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. IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 2-14 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 2.9 Statistical Specifications 2.9.1 Mean Time Between Failures MTBF: 17,660 hours IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 3-1 3.0 CERTIFICATION TSO -C106, -C44a Environmental Categories RTCA/DO-160B Temp. ALT F2 Temp. Variation B Humidity A Shock & Vibration P, K, S, M, N, O Magnetic Effect B Power Input B Voltage Spike B AF Conducted Susceptibility B Induced Signal Susceptibility B RF Susceptibility A RF Emission B Software Certification P/N 962820-1, 962820-2, and 962820-3 conforms to level II as defined by RTCA/DO-178A. P/N 962820-1A, 962820-2A, and 962820-3A conforms to level D as defined by RTCA/DO- 178B. IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) 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 or RS-422) information may also prove useful. We may request a wiring diagram of the aircraft's fuel flow system and transducer and/or K- factors. IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 5-1 5.0 INSTALLATION PROCEDURE 5.1 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; latest release. 5.2 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 is favorable, in order to avoid running all of these signals to the tail of the aircraft. 5.3 Mounting the F/ADC The computer should be mounted per Drawing 4028-604, -605, -606, and Drawing 4028-411, 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. IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 5-2 5.4 Mounting the OAT Probe 1. Refer to Drawing 4028-005 and OAT Probe Assy Kit P/N 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 4028-607: +5V is supplied to the OAT probe from (red wire) J1:15. The OAT signal is the white (or black) wire from J1:14. 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 °C to microampere conversion chart. The amperage can be measured by connecting an ammeter in series between the signal wire of the OAT probe and the ADC200. This information is provided for trouble shooting purposes only. OAT ºC Input μA OAT ºC Input μA OAT ºC Input μA OAT ºC Input μA -60 213 -20 253 +20 293 +60 333 -50 223 -10 263 +30 303 -40 233 0 273 +40 313 -30 243 +10 283 +50 323 1°C = 1 μA IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 5-3 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 4028-608 (Freq. Option) to connect the fuel flow transducer to the computer. 5. *If the aircraft is equipped with a digital fuel flow transducer (P/N 680501), use Drawing 4028-608 (High-Level Option) 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. *If the aircraft is equipped with a DC fuel flow system, use Drawing 4028-608 (DC Fuel Flow Option) and the STC covering the installation. 8. *If the aircraft is equipped with a sine wave pickup coil type of fuel flow transducer, use Drawing 4028-608 (Sine Wave Signal). Use the Converter, P/N 631201. Note that if this is a new installation, use part number 962820-2(A) ADC200. 9. Install the sine to square converter, P/N 631201, between the fuel flow transducer and the F/ADC as depicted in 4028-608 and 4005-642. 10. Make sure that the system is initialized with the proper transducer K factor for a digital or sine systems and with the proper airframe make and model for the DC fuel flow systems. See the attached tables in section 10.0. * Consult section 11 for specific aircraft installation wiring drawings. IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) 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 Heading ARINC 407 FUEL Air Data J1 Collins 328A-2A 2P1 Collins HSI331A P1 Collins MCS 65 P1 Collins 328A-5 King KI525A P2 King KSG105 P1 Sperry Gyro- syn Comp. P1 Sigma- Tek DG Sandel SN3308 P1 P2 X 5 11 S 25 32 s t L A 25 Y 4 4 T 40 22 v p M B 6 Z 7 3 U 24 12 t k K D 4 H 6 26 V 6 53 r c 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). IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 5-5 5.7 Connection to the Pitot and Static Lines The pitot static line should be cut and a tee installed, to tap into these lines. Use the appropriate type of fittings to match the type installed in the aircraft. Refer to CFR part 43, appendix E for approved practices in installing and verifying these connections. PITOT/STATIC adapter helpful hints To make an adapter for the Shadin ADC200, the following parts could be used. It is recommended to use all aluminum fittings. Existing Pitot/Static lines AN910-1D AN816-2D #2 Hose(with female fittings) AN910 DASH NUMBER PIPE AN816 DASH NUMBER TUBE PIPE BRASS ALUM. ALLOY SIZE STEEL ALUM. ALLOY O. D. THREAD -1 -1D 1/8” -2 -2D 1/8” 1/8” -2 -2D 1/4” -3 -3D 3/16” 1/8” -3 -3D 3/8” -4 -4D 1/4” 1/8” -4 -4D 1/2” -5 -5D 5/16” 1/8” -6 -6D 3/4” -6 -6D 3/8” 1/4” -8 -8D 1” -8 -8D 1/2” 3/8” -10 -10D 5/8” 1/2” -12 -12D 3/4” 3/4” -16 -16D 1” 1” MS20825 TEE TUBE PIPE STEEL ALUM. ALLOY O. D. THREAD -2 -2D 1/8” 1/8” -3 -3D 3/16” 1/8” -4 -4D 1/4” 1/8” -5 -5D 5/16” 1/8” HOSE: Stratoflex 193-2 or Aeroquip 306-2 with MS27404 (P/N 311-2D) on each end. Air source MS20825 Tee AN910 AN816 ADC200 MS27404 IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 5-6 5.8 Connection to the Navigation Management System 1. Use the appropriate installation wiring diagram (4028-943 or -946) to connect the Fuel Air data Computer's Connector J2 to the navigation management system. 2. 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. 3. Keep the cables away from power cables, DME and transponder cables. 4. Refer to the specific Nav Receiver Installation Manuals for details. 5.9 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 +2°C. 5. 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. IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 6-1 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 but will be out of range until actual airspeed is available. Winds aloft will be available if IAS > 40 Kts and magnetic heading is 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. IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 7-1 7.0 INITIALIZATION 1. The system requires initialization of K 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 sine fuel flow. 2. Refer to the specific Navigational Receiver Operator Manuals for the serial port set up. IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) 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, P/N 681201( ) IM2820 Shadin Avionics INSTALLATION MANUAL1 FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 9-1 9.0 CONFIGURING THE AIR DATA Part number 962820-X(A) (X= 1 or 2 or 3) Air data Computer needs to be configured to program it for the particular installation. The procedures contained in this Installation Manual are 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. 9.1 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 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. IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 9-2 9.2 Configuring Manually (Loop-Back) The switches that are available from the backside of the unit need to be set to the appropriate positions as determined by the switch settings listed below. After the correct switch positions have been selected, the unit is powered using the 'Loop-Back' harness (consult drawing number 4028-944 contained in section 11). The purpose of the 'loop back' harness is to tie the RS-232 transmit and receive ports together. This allows the software, when the unit is powered on, to read the switch positions. Switch 1 is set to different positions to select the separate stages that the loopback is performing. There are 5 different ‘loopback’ procedures. Use ‘loopback’ procedure 1 for Software Versions 93.00.16-93.00.29. Use ‘loopback’ procedure 2 for software versions 93.00.51-93.00.71. Use ‘loopback’ procedure 3 for software versions 93.00.77. Use 'loopback' procedure 4 for software version 93.00.82 and above. Note that procedure 1 has 2 stages. Procedure 2, and 3 have 4 stages and procedure 4 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: Switches 2 VIEW FROM END A Connectors End A End B 1 3 4 IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 9-3 Loop-back Procedure 1 for Software Version 93.00.16 - 93.00.29 Stage 0 Loopback Configuration: Switch 1 is set to 0 to indicate that the stage 0 loopback is being performed. SWITCH 2 Fuel Units and Engine Type: 0 - Gallons Single Engine 1 - Liters " " 2 - Lbs 5.8 " " 3 - Lbs 6.71 " " 4 - Kilograms " " 5 - Lbs 6.5 " " 6 - Lbs 6.3 " " 7 - (not used) " " 8 - Gallons Twin Engine 9 - Liters " " A - Lbs 5.8 " " B - Lbs 6.71 " " C - Kilograms " " D - Lbs 6.5 " " E - Lbs 6.3 " " F - (DO NOT USE) SWITCH 3 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) IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) 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 5-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-F - (DO NOT USE) SWITCH 4 Altimeter Selection for Baro DC Input: 0 - None (Use this selection) 1 - Type 1 (Not available) 2 - Type 2 (Not available) 3 - Type 3 (Not available) 4 - Type 4 (Not available) 5 - Type 5 (Not available) 6 - Type 6 (Not available) 7 - Type 7 (Not available) 8-F - (not used) IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 9-5 Loopback Procedure 2 for Software Version 93.00.51-93.00.71 Stage 0 Loopback Configuration: Switch 1 is set to 0 to indicate that the stage 0 loopback is being performed. SWITCH 2 Fuel Units and Engine Type: 0 - Gallons Single Engine 1 - Liters " " 2 - Lbs 5.8 " " 3 - Lbs 6.71 " " 4 - Kilograms " " 5 - Lbs 6.5 " " 6 - Lbs 6.3 " " 7 - (not used) " " 8 - Gallons Twin Engine 9 - Liters " " A - Lbs 5.8 " " B - Lbs 6.71 " " C - Kilograms " " D - Lbs 6.5 " " E - Lbs 6.3 " " F - (DO NOT USE) SWITCH 3 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) IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 9-6 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 Ω (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-F - (DO NOT USE) SWITCH 4 Altimeter Selection for Baro DC Input: 0 - None (Use this selection) 1 - Type 1 (Not Available) 2 - Type 2 (Not Available) 3 - Type 3 (Not Available) 4 - Type 4 (Not Available) 5 - Type 5 (Not Available) 6 - Type 6 (Not Available) 7 - Type 7 (Not Available) 8 - (DO NOT USE) 9 - Type 9 (Not Available) A-F - (DO NOT USE) IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 9-7 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 0 - No correction ALL 0 1 - MITSUBISHI MU-300 93.00.29 and up 0 2 - CESSNA CITATION 500/501 93.00.29 and up 0 3 - CESSNA 525 93.00.29 and up 0 4 - CESSNA 550 93.00.29 and up 0 5 - Citation 560 SN <=259 93.00.29 and up 0 6 - Citation 560 SN >=260 93.00.29 and up 0 7 - Citation 650 93.00.29 and up 0 8 - Sabreliner 65 93.00.29 and up 0 9 - WestWind 1124A 93.00.29 and up 0 A - LearJet 24 93.00.29 and up 0 B - Raytheon Hawker HS 125-3A 93.00.29 and up 0 C - Falcon 20-F 93.00.29 and up 0 D - Falcon 20-C, D, E 93.00.29 and up 0 E - LearJet 25D 93.00.29 and up 0 F - Douglas DC-8 93.00.58 and up 1 0 - Beechjet 400 93.00.63 and up 1 1 - Boeing 707-321B 93.00.63 and up 1 2 - Cessna Citation S550 93.00.63 and up 1 3 - Falcon 10 93.00.63 and up 1 4 - Falcon 50 93.00.63 and up 1 5 - Raytheon Hawker HS125-700A 93.00.63 and up 1 6 - LearJet 35 93.00.63 and up 1 7 - LearJet 55 93.00.63 and up 1 8 - Sabreliner 60 (SSEC Only) 93.00.63 and up 1 9 - Lockheed Jetstar II 93.00.63 and up 1 A-F - Reserved for future (DO NOT USE) IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 9-8 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 962820-1(A) and 962820-2(A) 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 8 - 40 Second Delay 9 - 45 Second Delay A-F - (DO NOT USE) IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 9-9 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: 0 - Gallons Single Engine 1 - Liters " " 2 - Lbs 5.8 " " 3 - Lbs 6.71 " " 4 - Kilograms " " 5 - Lbs 6.5 " " 6 - Lbs 6.3 " " 7 - (not used) " " 8 - Gallons Twin Engine 9 - Liters " " A - Lbs 5.8 " " B - Lbs 6.71 " " C - Kilograms " " D - Lbs 6.5 " " E - Lbs 6.3 " " F - (DO NOT USE) SWITCH 3 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) IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 9-10 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 Ω (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, CNX80 7 - Bendix B – (fuel only) 8 - Garmin G 9-F - (DO NOT USE) SWITCH 4 Altimeter Selection for Baro DC Input: 0 - None (Use this selection) 1 - Type 1 (Not Available) 2 - Type 2 (Not Available) 3 - Type 3 (Not Available) 4 - Type 4 (Not Available) 5 - Type 5 (Not Available) 6 - Type 6 (Not Available) 7 - Type 7 (Not Available) 8 - (DO NOT USE) 9 - Type 9 (Not Available) A-F - (DO NOT USE) IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 9-11 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 0 - No correction ALL 0 1 - MITSUBISHI MU-300 93.00.29 and up 0 2 - CESSNA CITATION 500/501 93.00.29 and up 0 3 - CESSNA 525 93.00.29 and up 0 4 - CESSNA 550 93.00.29 and up 0 5 - Citation 560 SN <=259 93.00.29 and up 0 6 - Citation 560 SN >=260 93.00.29 and up 0 7 - Citation 650 93.00.29 and up 0 8 - Sabreliner 65 93.00.29 and up 0 9 - WestWind 1124A 93.00.29 and up 0 A - LearJet 24 93.00.29 and up 0 B - Raytheon Hawker HS 125-3A 93.00.29 and up 0 C - Falcon 20-F 93.00.29 and up 0 D - Falcon 20-C, D, E 93.00.29 and up 0 E - LearJet 25D 93.00.29 and up 0 F - Douglas DC-8 93.00.58 and up 1 0 - Beechjet 400 93.00.63 and up 1 1 - Boeing 707-321B 93.00.63 and up 1 2 - Cessna Citation S550 93.00.63 and up 1 3 - Falcon 10 93.00.63 and up 1 4 - Falcon 50 93.00.63 and up 1 5 - Raytheon Hawker HS125-700A 93.00.63 and up 1 6 - LearJet 35 93.00.63 and up 1 7 - LearJet 55 93.00.63 and up 1 8 - Sabreliner 60 (SSEC Only) 93.00.63 and up 1 9 - Lockheed Jetstar II 93.00.63 and up 1 A-F - Reserved for future (DO NOT USE) IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 9-12 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 962820-1(A) and 962820-2(A) 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 8 - 40 Second Delay 9 - 45 Second Delay A-F - (DO NOT USE) IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 9-13 Loopback Procedure 4 for Software Version 93.00.82 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: 0 - Gallons Single Engine 1 - Liters " " 2 - Lbs 5.8 " " 3 - Lbs 6.71 " " 4 - Kilograms " " 5 - Lbs 6.5 " " 6 - Lbs 6.3 " " 7 - (not used) " " 8 - Gallons Twin Engine 9 - Liters " " A - Lbs 5.8 " " B - Lbs 6.71 " " C - Kilograms " " D - Lbs 6.5 " " E - Lbs 6.3 " " F - (DO NOT USE) SWITCH 3 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) IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 9-14 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 Ω (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 (Use this selection) 1 - Type 1 (Not Available) 2 - Type 2 (Not Available) 3 - Type 3 (Not Available) 4 - Type 4 (Not Available) 5 - Type 5 (Not Available) 6 - Type 6 (Not Available) 7 - Type 7 (Not Available) 8 - (DO NOT USE) 9 - Type 9 (Not Available) A - (DO NOT USE) B - Type 11 (Not Available) C-F - (DO NOT USE) IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 9-15 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 0 - No correction ALL 0 1 - MITSUBISHI MU-300 93.00.29 and up 0 2 - CESSNA CITATION 500/501 93.00.29 and up 0 3 - CESSNA 525 93.00.29 and up 0 4 - CESSNA 550 93.00.29 and up 0 5 - Citation 560 SN <=259 93.00.29 and up 0 6 - Citation 560 SN >=260 93.00.29 and up 0 7 - Citation 650 93.00.29 and up 0 8 - Sabreliner 65 93.00.29 and up 0 9 - WestWind 1124A 93.00.29 and up 0 A - LearJet 24 93.00.29 and up 0 B - Raytheon Hawker HS 125-3A 93.00.29 and up 0 C - Falcon 20-F 93.00.29 and up 0 D - Falcon 20-C, D, E 93.00.29 and up 0 E - LearJet 25D 93.00.29 and up 0 F - Douglas DC-8 93.00.58 and up 1 0 - Beechjet 400 93.00.63 and up 1 1 - Boeing 707-321B 93.00.63 and up 1 2 - Cessna Citation S550 93.00.63 and up 1 3 - Falcon 10 93.00.63 and up 1 4 - Falcon 50 93.00.63 and up 1 5 - Raytheon Hawker HS125-700A 93.00.63 and up 1 6 - LearJet 35 93.00.63 and up 1 7 - LearJet 55 93.00.63 and up 1 8 - Sabreliner 60 (SSEC Only) 93.00.63 and up 1 9 - Lockheed Jetstar II 93.00.63 and up 1 A - Antonov (AN 12) 93.00.85 and up 1 B - Antonov (AN 24) 93.00.85 and up 1 C - Antonov (AN 26) 93.00.85 and up 1 D - Antonov (AN 30) 93.00.85 and up 1 E - Yakovlev (YAK 40) 93.00.85 and up IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 9-16 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 962820-1(A) and 962820-2(A) 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 8 - 40 Second Delay 9 - 45 Second Delay A-F - (DO NOT USE) IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 9-17 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-F - Refer to calibration certificate for “A” code selection 0 to F. SWITCH 3, OAT Tb CALIBRATION CODE SELECTION 0-F - Refer to calibration certificate for “B” code selection 0 to F. SWITCH 4, OAT Tc CALIBRATION CODE SELECTION 0-F - Refer to calibration certificate for “C” code selection 0 to F. Note: Switch 2, 3, and 4 are set to position 0 (zero), if the OAT probe does not have a calibration code marking, (i.e. A=0, B=0, C=0). IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 9-18 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 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 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. IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 10-1 10.0 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 962820-1(A) Digital 962820-2(A) Sine Wave 962820-3(A) Analog Use the switch settings from the appropriate table to set the K Factor. For Digital or Sine units (P/N (s) 962820-1(A) and -2(A)) use the Digital K Factor Settings Tables. Switch 1 & 2 selects the left K Factor Switch 3 & 4 selects the right K Factor Due to possible fuel flow system peculiarities, switch 1 & 2 and switch 3 & 4 do not necessarily need to be set to the same setting. For a one engine system, use switches 1 & 2. For Analog units (P/N 962820-3(A)) use the Analog K Factor Settings Table. Switch 1 & 2 selects the main engine K Factor Switch 3 & 4 selects the offset. The offset is simply the value represented by switches 3 & 4 in the Analog K Factor Settings 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 be 0, 4. Configuration is now complete. IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 10-2 Analog K Factor Settings Table Standalone Air data MKII Analog Fuel Flow Chart Manufacturer Model SW1 SW2 SW3 SW4 K-Factor Offset Beech KingAir B200 0 0 0 1 77000 416 Beech KingAir A100 0 1 0 2 26150 875 Beech KingAir C90 0 1 0 2 26150 875 Beech KingAir F90 0 0 0 1 77000 416 Beech KingAir C90A 0 0 0 1 77000 416 Beech KingAir 200 0 0 0 1 77000 416 Beech BeechJet 0 2 0 0 11540 0 Beech KingAir B100 0 3 0 2 26150 875 Beech Beech 600 0 4 0 0 38460 0 Beech Beech 750 0 5 0 0 30770 0 Beech Beech 800 0 6 0 0 28850 0 Cessna Citation, Ametek Gauge 02C208E 0 C 0 0 16270 0 Cessna Citation, Simmons Gauge 393002-009 1 C 0 0 14300 0 Cessna Citation II/SII 0 C 0 0 16270 0 Cessna Citation III 0 D 0 4 9620 1094 Cessna Model 525 0 E 0 0 21980 0 Piper Cheyenne III 1 9 0 0 41960 0 Piper Cheyenne IV 1 1 0 0 46150 0 LearJet LearJet 0 7 0 0 15380 0 LearJet Model 36 (5V) 0 2 0 0 11540 0 LearJet Model 36 (10V) 0 8 0 0 23080 0 Boeing Boeing-737-300 0 9 0 3 1790 0 British Aero BAE ATP 0 7 0 0 15380 0 British Aero BAE-125-800 0 A 0 0 8240 378 British Aero HS-125 0 B 0 0 10490 0 Canadian CL600 0 F 0 0 6590 0 Canadian CL601 1 0 0 0 5130 0 Dornier DO-228 1 1 0 0 46150 0 Daussault FALCON 10 0 2 0 0 11540 0 Daussault FALCON 20 1 2 0 0 7690 0 Daussault TFE-371 1 2 0 0 7690 0 Swearngen MERLIN 0 4 0 0 38460 0 Gulfstream GULFSTREAM II 1 3 0 0 2880 0 Gulfstream GULFSTREAM III 1 4 0 0 2310 0 Aerospatiale PUMA 1 5 0 0 76920 0 DHC DHC DASH 8 1 6 0 0 19230 0 IAI ASTRA 1125 1 7 0 5 9230 2188 IAI WESTWIND 1124 1 8 0 0 10490 0 Sikorsky S-76A 1 1 0 0 46150 0 Sikorsky S-76B 0 6 0 0 28850 0 Sabre SABRE 65 1 7 0 5 9230 2188 Table 1 IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 10-3 Matrix 0 - Digital K Factor Settings PPG SW1 SW2 PPG SW1 SW2 PPG SW1 SW2 860 D D 8800 5 0 15300 E F 5000 6 B 9000 5 1 18000 3 0 5050 6 C 9200 5 2 18200 3 1 5100 6 D 9400 5 3 18400 2 2 5150 6 E 9600 5 4 18600 3 3 5200 6 F 9800 5 5 18800 3 4 5250 7 0 10000 5 6 19000 3 5 5300 7 1 10100 5 7 19200 3 6 5600 6 0 10200 5 8 19400 3 7 5650 6 1 10300 5 A 19600 3 8 5700 6 2 10400 5 B 19800 3 9 5750 6 3 10500 5 C 20000 3 A 5800 6 4 10600 5 D 20200 3 B 5850 6 5 10700 5 E 20400 3 C 5900 6 6 10800 5 F 20600 3 D 5950 6 7 10900 D 6 20800 3 E 6000 6 8 11000 D 7 21000 3 F 6380 C B 11100 D 8 21200 4 0 6400 C C 11200 D 9 21400 4 1 6420 C D 11300 D A 21600 4 2 6440 C E 11400 D B 21800 4 3 6460 C F 11500 D C 22000 4 4 6480 D 0 14500 D E 22200 4 5 6500 D 1 14600 D F 22400 4 6 6520 D 2 14700 E 9 22600 4 7 6540 D 3 14800 E A 22800 4 8 6560 D 4 14900 E B 23000 4 9 6580 D 5 15000 E C 23200 4 A 6660 6 A 15100 E D 23400 4 B 7640 5 9 15200 E E 23600 4 C Table 2 IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 10-4 Matrix 0 - Digital K Factor Settings (Continued) PPG SW1 SW2 PPG SW1 SW2 PPG SW1 SW2 23800 4 D 29800 F B 40000 9 4 24000 4 E 30000 F C 40200 9 5 24200 4 F 30200 F D 40400 9 6 24400 B A 30400 F E 40600 9 7 24600 B B 33800 6 9 40800 9 D 24800 B C 37000 B 9 41000 9 E 25000 B D 37200 B 8 41200 9 F 25200 B E 37400 B 7 41400 1 0 25400 B F 37600 B 6 41600 1 1 25600 C 0 37800 B 5 41800 1 2 25800 C 1 38000 8 0 42000 1 3 26000 C 2 38100 8 1 42200 1 4 26200 C 4 38200 8 2 42400 1 5 26400 C 5 38300 8 3 42600 1 6 26600 C 6 38400 8 4 42800 1 7 26800 C 7 38500 8 5 43000 1 8 27000 C 8 38600 8 6 43200 1 9 27200 C 9 38700 8 7 43400 1 A 27400 C A 38800 8 8 43600 1 B 27600 F 0 38900 8 9 43800 1 C 27800 F 1 39000 8 A 44000 1 D 28000 F 2 39100 8 B 44200 1 E 28200 F 3 39200 8 C 44400 1 F 28400 F 4 39300 8 D 44600 2 0 28600 F 5 39400 8 E 44800 2 1 28800 F 6 39500 8 F 45000 2 2 29000 F 7 39600 9 0 45200 2 3 29200 F 8 39700 9 1 45400 2 4 29400 F 9 39800 9 2 45600 2 5 29600 F A 39900 9 3 45800 2 6 Table 2 continued IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 10-5 Matrix 0 - Digital K Factor Settings (Continued) PPG SW1 SW2 PPG SW1 SW2 PPG SW1 SW2 46000 2 7 57700 A 7 93000 7 2 46200 2 8 57800 A 8 94000 7 3 46400 2 9 57900 A 9 95000 7 4 46600 2 A 58000 A A 96000 7 5 46800 2 B 58100 A B 97000 7 6 47000 2 C 58200 A C 98000 7 7 47200 2 D 58300 A D 99000 7 8 47400 2 E 58400 A E 100000 7 9 47600 2 F 58500 A F 101000 7 A 49000 9 8 58600 B 0 102000 7 B 49100 9 9 58700 B 1 103000 7 C 49200 9 A 58800 B 2 104000 7 D 49300 9 B 58900 B 3 105000 7 E 49400 9 C 60000 B 4 106000 7 F 49500 E 2 77000 0 0 49700 E 3 78000 0 1 50000 E 4 79000 0 2 50200 E 5 80000 0 3 50400 E 6 81000 0 4 50500 E 7 82000 0 5 50800 E 8 83000 0 6 55500 C 3 84000 0 7 55550 F F 85000 0 8 57000 A 0 86000 0 9 57100 A 1 87000 0 A 57200 A 2 88000 0 B 57300 A 3 89000 0 C 57400 A 4 90000 0 D 57500 A 5 91000 0 E 57600 A 6 92000 0 F Table 2 continued IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER Rev: T P/N 962820-1(A), 962820-2(A), 962820-3(A) Page: 10-6 Matrix 1 - Alternate Digital K-Factor Setting Table (software version 93.00.61+) PPG SW1 SW2 PPG SW1 SW2 PPG SW1 SW2 200 1 0 1940 8 0 16100 4 E 400 1 1 2000 3 D 16300 4 F 440 1 2 2200 3 E 16500 5 0 490 1 3 2400 3 F 16600 5 1 510 1 4 2600 4 0 16800 5 2 520 1 5 2800 4 1 17000 5 3 530 1 6 3000 4 2 17200 5 4 540 1 7 3200 4 3 17400 5 5 550 1 8 3400 4 4 17600 5 6 560 1 9 3600 4 5 17800 5 7 570 1 A 3610 0 0 30600 6 3 580 1 B 3650 0 1 30800 6 4 590 1 C 3690 0 2 31000 6 5 600 1 D 3730 0 3 31200 6 6 610 1 E 3760 0 4 31400 6 7 620 1 F 3800 0 5 31600 6 8 630 2 0 3800 4 6 31800 6 9 640 2 1 3840 0 6 32000 6 A 650 2 2 3880 0 7 32200 6 B 660 2 3 3920 0 8 32400 6 C 670 2 4 3960 0 9 32600 6 D 680 2 5 4000 0 A 32800 6 E 690 2 6 4000 4 7 33000 6 F 700 2 7 4040 0 B 33200 7 0 710 2 8 4080 0 C 33400 7 1 720 2 9 4120 0 D 33600 7 2 730 2 A 4160 0 E 34000 7 3 740 2 B 4200 0 F 34200 7 4 750 2 C 4200 4 8 34400 7 5 760 2 D 4400 4 9 34600 7 6 770 2 E 4700 4 A 34800 7 7 780 2 F 11700 5 8 35000 7 8 790 3 0 11900 5 9 35200 7 9 800 3 1 12100 5 A 35400 7 A 810 3 2 12400 5 B 35600 7 B 820 3 3 12600 5 C 35800 7 C 840 3 4 12800 5 D 36000 7 D 850 3 5 13000 5 E 36400 7 E 880 3 6 13500 5 F 36800 7 F 900 3 7 14000 6 0 1000 3 8 14200 6 1 1200 3 9 14400 6 2 1400 3 A 15500 4 B 1600 3 B 15700 4 C 1800 3 C 15900 4 D Table 3 IM2820 Shadin Avionics INSTALLATION MANUAL FUEL/AIR DATA COMPUTER P/N 962820-1(A), 962820-2(A), 962820-3(A) SECTION 11.0 INSTALLATION DRAWINGS AND INSTALL KIT PARTS LISTS ---.;........--------- .. ." - NOTES: 1. REFERENCE PIN 681201-1 OAT PROBE ASSEMBL Y KIT 2. AVOID INSTALLING OAT PROBE IN OR NEAR: PROP AIRSTREAM ENGINE EXHA0sT FLD~ PATH CABIN HEATERS EXHAUST FLo~ PATH TRANSMITTING ANTENNAS <DME, TXP, COMMJ DARK PAINTED A~EAS ,- @&& OA T PROBe PIN 681201 &.TORQUE NUT, FN 25, TO 1.3 IN-LBS (MAX) DRILL O.098¢ AIRCRAFT FUSELAGE (#40) 4 PL. DRILL O.359¢ o 30 (23/64") 0.50 f 1.0'0 DETAIL A MOUNTING HOLE DETAIL ~~~:~1H~~I~~ ~~r:s SHA.DfN HINN£AP(LJS. MN S5~ TOLERANCES' ±o.Ol· INST ALLATIDN ~iLI:~~~~~~~~~~~~~==========1F'iRI~7."':'N/A:-----D~---1DA T PROBE ASSEM.BLJ Y KIT MATERIAL. ...fA »RAVING. rtl. PIN' 681201 1 R£V SIZE 4028-005 A - C 3,10 2.00 Q o , '1-~ IL~l, /1 1 \ ' J I , / / ~ . / I .55 /1-' ·tLtl \,,+0 "/'-~ ¢.15 (x4) /.~~J~G5+1 \\+' /'-~ /1 tL+ '\\-, 0~j \,'y/ / , '. '. I l .. ,_., _ ... _LtST OF _M~TE~IAL ."j I 1,55 .20 ~ ¢85~ 3.25 6.35 ? ~ 0.50 ~ ------1.. .;;T I .16 MOUNTING HARDWARE REQUIRED: QTY REV .8 542801' A. 4 4 4 (AN526-632-8) SCREWS (AN960-6) LOCKWASHERS (AN364-6"32) NUTS UNLESS OTHERWISE NOTED ORAWlI;l.GDATt: C'LT'A' nrwDIt.4ENSlONS ARE IN INCHES 10/12/94 A.J~-' L/.LJ t.41NNEAPOUS. MN 554-26 TOLERANCES: X.X - ±O.1 I~ X~_±±~!64/X~~::: :g:g65 APPRO~D INSTALLATION, h"'L VLV I 0 I ,u.... .J/"" I LJM 1 KCL 1AODED P7N TO TITLE BLOCK ,FlNISH: N/A FlLESENSAME MOU N TI NG TR AY 19902/0201 A 1 3/2/99 1 CMG 1 PG IUPDATED TRAY USED It.4A IA S"'2801A8J.DWG I I I .- ,.- ,_. DAP I SES IBASEUNE RELEASE I TER L: N/A D1RE§I~~J1A DRAWINC NO. I SIZE I / BY :lAPPD] DESCRIPTION -.1.30 CAD FILE AVAIL: YES I SCALE: 1 : 1 SHEET 10F 1 4028- 411 , A ,P N '-e e •NOTES & USE RS-232 OR RS-422, BUT NOT BOTH. 2. ALL DIMENSIONS ARE REFERENCE ONLY. Jl PINDUT 1. F"UEL F"LDIJ, RIGHT - POIJER 2. ruEL F"LDIJ, RIGHT - SIGNAL 3. F"urL F"LOIJ RIGHT - GROUND 4. HEADING Y S. HEADING X 6. 26V400Hz, H 7. 26V 400Hz, Z, C 9. NC 9. F"UEL F"LOIJ, LEFT - POIJER 10. rUEL F"LDIJ, LEn - SIGNAL U. rUEL F"LO'J LEH - GROUND ------i 2.000 ~ 3.125 3.280 12. NC 13. NC 14. OAT - (SIgnal) 15. OAT + (+5V) @ J2 PINOUT 1. 12 - 28v DC POIJER INPUT 2. NC l' 3. RX+, RS-422 0.125 I {4. RX-, RS-422 0563l ~ S. RX, RS-232 6. TX, RS-232 7. NC 8. NC 9. GROUND 10. HC MATING CONNECTORS' l' {11. l'X+, RS-422 ~ 12. TX-, RS-422 P2 13 .. -NC 230050 - CONN, SHELL, FEMALE 14. SIGNAL GND .230055. - CONN, PINS, FEMALE IS. NC 230038 - CONN, HOOD, 15 PIN P1 230051 - CONN, SHELL, MALE 230054 - CONN, PINS, MALE 230038 - CONN, HOOD, 15 PIN 6.250 @ SHA.DIlV. HINN(AP(1.IS. HN s:l426 INSTALLATION) ADC200 FREQ/LEVEL INT FF DRA \lING NO. ISIZE I REV A 962820-1 4028-604 P/ NBASELINE RELEASE DESCRIPTIDN -------•., .-.~----- NOTES •&. USE RS-232 DR RS-422, BUT NOT BOTH. 2. ALL DIMENSIONS ARE REFERENCE ONLY. Jl PINOUT 1. FUEL FLO"', RIGHT - (-) 2. FUEL FLO"', RIGHT - (+) 3. FUEL FLO'" RIGHT - GROUND 4. HEADING Y 5. HEADING X 6. 26V 400Hz, H 7. 26V 400Hz, Z, C 9. HC 9. FUEL FLO"', LEF"T - (-) 10. FUEL FLO"', LEF"T - (+) 11. FUEL FLO'" LEF"T - GROUND 3.280 12. HC 13. NC 14. OAT - (Signal) 15. OAT + (+5V) ® @ J2 PINOUT 1. 12 - 28v DC P[]'JER INPUT 3. RX+, RS-422 'i' ----=i~ I ~ 1375 I 3.250 {4. RX-, RS-422 0.563 -IT- 2.000 ~ S. RX, RS-232 6. TX, RS-232 1- 3.125 6.250 7. HC 9. NC 9. GROUND 10. NC MATING If {11. TX+, RS-422 ~ 12. TX-, RS-422 P2 13. Ne 230050 14. SIGNAL GND 230055 IS. HC 230038 PI 230051 230054 230038 2. NC 0.125 • I CONNECTORSI - CONN, SHELL. FEMALE - CONN, PINS, FEMALE - CONN, HOOD. 15 PIN - CONN, SHELL MALE - CONN, PINS, MALE - CONN, HOOD. 15 PIN SHAPIN MINNEAPOLIS. HN 55426 INSTALLATION) ADC200 SINE'WAVE FF DRA "'ING NO. ISIZE I REV A 962820-2 4028.-605 PINBASELINE RELEASE DESCRIPTION • • NOTES &. USE RS-232 OR RS-422 1 BUT NOT BOTH. 2. ALL DIMENSIONS ARE REFERENCE ONLY, Jl PINDUT 1. rUEL n.D1J. RIGHT - (-) 2. F'UEL rLDIJ,RIGHT - (+) 3. F'UEL rLDIJ RIGHT - GRDUND 4. HEADING Y 5. HEADING X 6. 26 V 400Hz. H 7. 26V 400Hz. Z, C 8. NC 9. rUEL rLDIJ; LErT - (-) 10. rUEL rLDIJ. LEn - ( ... ) U. rUEL rLDIJ LEn - GROUND 12. NC 13. Nt 14. DAT - (Signal> ·15. DAT ... (+5V> J2 PINDUT 1. 12 - 28v DC PDIJER INPUT 2. NC 3. RX+. RS-422 {4. RX-, RS-422 S63 l 2.000 =D~ l' S. RX, RS-232 O. ~6. TX, RS-232 3.125 6.250 7. NC 8. NC 9. GROUND 10. NC l' {11. TX+. RS-422 ~ 12. TX-, RS-422 13. NC 14. SIGNAL GND lS. NC • 3,280 MA TING CONNECTORS. P2 230050 - CONN. SHELL, FEMALE 230055 - CONN. PINS. FEMALE 230038 - CONN. HOOD. 15 PIN 0.125 -I ® PI 230051 - CONN, SHELL, MALE 230054 .- CONN. PINS. MALE 230038 - CONN. HOOD. 15 PIN SHA.DIlV MlNNEAP{LIS. HN :s:l4Z6 INSTALLATION) ADC200 DC FF DRAIJING NO. ISIZE REV 962820-3 4028-606 A IP INBASELINE RELEASE DESCRIPTION lSi 1 ·._. . • ADC200 962810-X 962820-X • SHADIlV HINN[AP(LIS. HN SS426 INSTALLATION \JIRING, FUEL AIRDATA COMPUTER (ADC200) TO OAT/HEADING SYSTEM . DRAW'ING NO. ISIZE Ip / N IREV 4028~607 A A Jl [ PD\JE~ OAT SIGNAL 1 14 I Y I 4 COMPASS HEADING x 5 26V 400Hz H 6 ZIC I 7 GND I 11 SPLICE \ 1\ f\ ~ \JHT or BLK ' fREQUENCY FT INTERF"AC£ [P~ D.C. fUEL F"lO.... [J'TIDN •..-...;.._------~~- .-------• 0:: RI~T '~T GROUND 13 h to ~I m_aaR nn. SHADIN PIN F"LD\I SIG 2 B 68O:lOl-X [R liND 3 C 6605XX ' ~181 f\ LETT 2 nn. SHADIN PIN 5 TO 10V DC ~r~ fLO\I B ~-X [R .SIG 10 "~I ' F"CR F1.U. SCALE CHDDEl. DEPENDANT> 12 GND It ~ ~X V '3 10 It He IZ "r LEVa rr INTIRF" ACE [PTI~ 96Z8lD-l 962820-1 Jl GRtUlD 13Q 2 5 $181 ) SIGNAl. F"RDH EXISTlNG SYSTEM ~ sro'+i' 962910-1 962910-3 962921)-3 Jl 96Z820-1 JI RIGHT -SIG F'UEL F"LD\I +SIG He LEn -SIG F"IJEL F"LD\I +SIG He LEVEl. FT INTERrACE [PTIaf 96Z810-1 SINE SINE SINE fUEL fLDV [PTIDN 962820-2 HAGNES(N fF. F"REQUENCY IT Itm:RF" ACE [PTIDN TO F"RElt CONERTER 962810-1 962820-1 PIN 930503 Jl [=4~ L F"REQ. fF. WT ITt R. F'REQ. f F. WT OJ lIZ ~;:~:~ ~ 13 GROOND ./ "-I 962910-2 96282G-2 RI~T - SIG F"UEL F"LOW' + SIG GHD LEn - SIG fUEl F"LO .... • SIG GHD \lAVE Jl \lAVE F1JEL F"LD\I PICKUPS It ENGINE 1 3 9 10 11 n.n Jl F1...DV PICKUPS . RIGHT +15V F"IJEL 1 F"LOW' SIG 2 GND 3 u:n +15'1 F'UEI.. 9 fLOW' SIG 10 GND 11 IDRA'w'l/olG DATE I C"LTA nTW 1216/'34 AJ~a.v.L.i HINNEAPll.lS. HN 55426 I DRArTER 'WMP . APPROV<> INST ALLA nON 'WIRING, FUELI AIRDA TA 9509/015 I A I 9/13/95 I 'w'HP I SES ICORRECT PIN ON LEVEL ff INTERfACE OPTION 1~~~~:~;~J.D'WGr_ ----;:C~0:7M:::P::U:-:::T:-E-R-(...,ArD-C-2"T"""0-O-) _T_O_F_U_E_L__S_Y_S_T_E_M--.J 9506/011 BASELINE RELEASr- • -. DRA'WING NO. ISIZE (p / N {REV ECO" DESCRIPTION 4028-608 A A • • • 962810"X} 962820-X X = 1, 2, 3 962830-X ' J2 /-\ 5 RS-232 " I \ RX I \ , I I ,I I , \ RS-232 \ I : 6 \ I TX '/, I..- l l-J AJK. ADDED CNX 80 0211/047 C. IN:'-ID~ PAB 0501/006 DEL PIN 9) ADDED GND 0009/006 PAB BAL B 2/7/03· ADD GARHIN 430/530 GPS 9803/025 PAB EDJ A 9/6/00 BASELINE RELEASE ECD. SRB .KCL 3/26/98 - DESCRIPTION APP'D BY REV. DATE ·CNX 80 GARMIN 430, 530 BENDIX/ KING KLN90 KLN90B BENDIX/ KING KLN89 GARMIN 150, 155, 155XL, 165, 250, 250XL 300, 300XL LNS 6000 BENDIX/ KING KLN 900 roSTER 7000 IIMORRO'w' 360 IIMORRO'w' NHS2001 TX 22 TX 56 TX 13 TX 2 TX 24 TX 25 TX 6 TX A TX 8/1 TX (SOFTIJARE SELECT> 19/37 RX RX RX RX RX RX RX RX RX RX 21 57 36 1 17 26 38 R 20/14 21/38 IIMORRO'w' 820 TX 6 RX 7 IIMORRO'w' ARNAV IIHORRO'w' MAGELLAN GX 50, FHS7000, SKYNAV GX 55 60 R5000 5000 STAR5000 A B TX TX TX TX TX 5 12 25 6 3 RX RX RX RX RX 4 4 11 7 23 IDR~~~~J'8A TE IllJo(AJ'gl~~R APPROVED PAB rILE NAME 402B-943CJ.DIJG DIRECTORY 4029 SHEET 1 OF 1 SHAPIN HlNNEAPO...IS MN 55<426 INSTALLATION "'IRING, F IADe-200, 2000 TO NAV RECEIVERS ~/RS-232 DRAIJING NO. ISIZE fP/ N (REV 4028-943 A c. NOT TO SCALE • " DR'1'"j~S~9D8A TE SHA.DIlV HIN€APtLlS. HN :550426 .~ INSTALLATION "'IRING, LOOP APPROVED KCL BACK HARNESS FOR F IADC200, 2000, D-SUB rILE NAME CONNECTOR ' 4029-944CJ.D\lG DIRECTORY ~A'JIN(j NO. , SIZE'P / N C4029 NOT TO SCALE ISHEET nF" 1 4028-944 '" - • J2 1\+28VDC 1 GND 9 ~ -- RX j RS232 5 TX j RS232 6 ~ llilIES!. 1. C'ONSUL T INSTALL AnON MANUAL FOR F / ADC PROGRAMMING INSTRUCTIONS. 2. MA TING CONNECTOR; 15 PIN FEMALE D-SUB (SHADIN PN 230050C) OR EQUIVALENT CORRECTED PIN OUT J2'S a. 6/ EDITED NOTE 2 UPDATED TITLE BLOCK CORRECTED PIN OUT BASELINE RELEASE ' DArE . i)ESCRIPT N BY I REV. APP'D E:Cll • 'R 0509/028 'C q J NJOIi PAB 'J.j/I\. 0501/032 B' 2J'14/05 PAD \IMP CJ809/022 A 9/281198 DLR KCL - 3....;26~98 SRB KCL 9803/025 ••..• 962810-X} 962820-X X 962830-X J2 1"\ RS-422 11 TX, SDA+ RS-422 12 TX, SDB RS-422 3 RX, SDA+ RS-422 R, SDB 4 U 0211/047 A 3/11/03 98tl3/025 - 3/26/98 I"CD .. REV. n4TE = 1, 2, 3' /-, / \ '. I I I I I I I I I I I I I I I I I I I I " ,I ,I \ I 'I. \ I \ I \ JI \ / \ . 7" \ I I I , I I I I I I I I I I I I I ,I I I :I I \ I " I \ , / T I I I '-l TRIMBLE TRIMBLE NORTSTAR 1000, 2100, MIA 2000, 2101. M2 3000 3100 M3 60/600 RX, SDA+ RX, SDA+ N/A 16 7 RX, SDB~ RX, SDB N/A 4 8 " TX, SDA+ TX, SDA+ TX, SDA+ 15 37 11 TX, SDB TX, SDB TX, SDB 3 5 6 PAD DAL DEL PIN 9, ADDED GND SRB KCL' BASELINE RELEASE BY APP'D DESCRIPTION NO seA _E • • DRA'Wt~ _UATE SHA.lJIlV MtNNEAf'[JJs. K'l 55-426 'fiR~12~98 INSTALLATION \JIRING, F/ADC200, 2000 APPROVED KCL TO NAV RECEIVERS 'vI/RS-422, RS-485 FILE NAME 4028-946AJ,D'w'G IRADIRECTORY DRA'WING NC. ISIZE IP / N 4028 4028-946 A ,<:\·U'-F rll" . . . , . _..... BENDIX/KING _ J2 ( SHADIN F IADC 2001 2000 1\ RS232 TX 6 5 r 1-1...-----------------------, RS232 RX L..J KLN90 J AJ B KLN89 KLN900 P901 P891 P9002 36 1 38 13 2 6 .till.I.E..S! 1. CONFIGURE SHADIN F I ADC 200 110 SHA·DIN 'FUEL FLDV METER FOR FLoW'METER/BENDIX C. 2. CONFIGURE SHADIN F I ADC 2000 110 FOR FLoW'METER/BENDIX C OR MICROFLO DIGIFLO I DIGIFLO I MINIFLO FLoW'METER/BENDIX D IF USING THE BARO PIN 91053XT PIN 91053XP PIN 91204X 91204XT -38D METRIC INTERFACE. I I I 3. CONFIGURE SHADIN FUEL FLOW' METER I/O FOR oNI AIR DATA. 4. FUEL FLOW' TRANSDUCER SIGNAL(S) ARE CONNECTED TO THE SHADIN FUEL FLOW' J 5 6 6 r METER. NO FUEL SIGNAL CONNECTION TO THE ADC. 5. MINIMUM SOFTW'ARE LEVELl DIGIFLO 60.10.77 I I I MINIFLO 60.01. 77 H I 12 I 9 I 9 MICRoFLo 60.08.77 ADC 200/2000 ·93.XX.77 DRA3~k~.f8ATE I SHAD/lV MINN£APlLIS. HN 55.26 DRA!ol..,ER INSTALLATION '-'IRING, F /ADC200, 2000, APPKRC~VED SHADIN FUEL FLO\J INDICATORS TO 0211/047 A 3/11/03 PAB BAL ADDED NOTES. &. S, ADDED F"UEL F"LOIJ METER SIJ VERSIONS rJ~ij-~~~~J,DIJG BENDIX/KING NAV. RECEIVER. 9803/025 - 3/26/98 SRB KC~ BASELINE RELEASE DIRf~13RY DRAIJrNG NO. {SrZE (p / N ECO 1* REV. ~TE BY APP D DESCRIPTION NO]: l:t:J ~ ~T..!..Q["'!' 402 8 - 9 4 7 A 1R A • • •F IA.. ,,2000 PIN 962810-X >PIN 962820-X X = L 2, 3 PIN 962830-X ~ ,-,I NA VIGA TIONAL RS422 RX+ .3 RECEIVER RS232 RX 51: ¥ & II RS422 RX- 4 . (~) RS232 TX I 6 I-I I RS232 RX ¥ & &, IRS422 RX+ RS42? TX+ I 11 . RS422 R'X RS422 TX- 12 SHADIN CONVERTER PIN 937000-03 RS422 RX RS422 RX+ ~ n - ~ Jl 12 I 11 .:x:. I ~ &.& ~ -I \ 13 ~ ¥ - 14 RS232 TX NoTESr ,& USE RS-232 OR RS422 NOT BOTH. £ CONNECT SHADIN CONVERTER PIN 937000-03 IN PARALLEL \.lITH NAVIGATIONAL RECEIVERS SERIAL DATA INPUT. ,& CONSULT DRA\.IING NUMBER 4070-005 FOR \JIRING AND STRAPPING INFORMATION. I I IOSOV032 A 12-''''6$ PAB ....... UPDATED TITLE BLOCK· I 9803/025 - 3/26/98 SRB KCL BASELINE RElEASE . Nr: SCALE -rcD. r REV. DA:K Jrr APP1 DE~N . r EVENTIDE ARGUS PIN 5000 ~ 161P/N 7000 RS232 INPUT 4 I RS232 INPUT HI LO\.l DRA~J~G DATE I SHAPIN MINNEAPtJ..rs,HN :55-426 3/25/98 ~ INSTALLATION \rIIRING, FIADC200, 2006 .AND APPROVED Kct. SHADIN CONVERTER TO EVENTIDE ARGUS rr~_~~J~~G ~ DIRECTORY DRA'JING NO. fREV lSIZElp / N4028 4028 - 9 4 8 A J A~ I..QE.1 -------. -------.MANUFACTURING NOTES:. APPLICATION NOTES: 1. M;A TCH·· FONT STYLE AND SIZES. ALL OTHER A. IF CONFIGURATION IS NECESSARY PRINT SWITCH DIMENSIONS AS SHOWN. SETTINGS IN SPACE PROVIDED. PRINT "N/A" WHEN SWITCHES ARE NOT USED. 2. SWITCH SETTING BOX DIMENSIONS ARE AS FOLLOWS: (MANUFACTURER IGNORE)WIDTH = .295 HEIGHT = .200 C 250 :: , ACCESS COVER RO.13 (x8) NGS' ' SWITCH SETTI SW4 S~3 J 1.50 SW1 SW2 •• U•• ARINC • BACKGROUND BLACKSILVER LETTERING & BOXES SILVER ;..... SHADIJV MINNEAPOlIS, UN 55426 LABEL, ADC200/2000 ACCESS COVER UPDATED Tl1l.E BLOCK REV DRA"'NG NO. ISIZE' / BASBJNERE1.£ASE . 4028-A80 A P N712801 IP A -'. . .-------, o 1. THE CONVERTER, CAN BE 2. 4' SPACING IS REQUIRED 3. NO COOLING IS REQUIRED 4, THE CONVERTER CAN' BE 2.94 ,(3.18) OR NON-PRESSURIZED AREA, MOUNTED IN ANY ORIENTATION ABOVE CONNECTOR INSTALLED IN A PRESSURIZED PROVIDING TEMPERATURE REQUIRED IN .INSTALL KIT PIN IK9337 SEE SELECTOR TABLE ENGINE SELECT (OUTPUT) POW'ER' IN SHADIN ADC RS-232 OR RS-422, BOTH) 5000/7000 SHA.DIlV t.AINNE»>buS. UN 55426 ORAWNG NO. ISIZE I' 4070-005 A P IN 937000-03\8 INSTALLATION, SE.RIAL TO ARGUS 5000/7000 CONVERTER DOES NOT DROP BELOW -20·C 5. 1 AMP CIRCUIT BREAKER IS 6. NO SHOCK MOUNT REQUIRED 7. USE HARD\lARE PROVIDED TO ASSEMBLE MATING CONNECTOR KEY MATING CONNECTORI SHADIN PIN 230036, l7-DAl5S PIN FUNCTION CONNECTOR. 15 PIN 230038, HqoD, # DA-246 MALE CONNECTOR SHADIN PIN l RS232 DR RS422 ,SELECT 2 TW'IN OR SINGLE 3 N.C. 4 N:C. 5 N.C. 6 N.C. 7 SELECT POW'ER (3.24) 8 +14 TO 28 V DC 9 N.C. 10 SIGNAL GROUND (3.05) 11 RS422 RX +~ FROM 12 RS422 RX- (USE RS232 RX NOT 13 SELECTOR TABLE 14 RS232 TX, TO ARGUS RS232 RX I TIE J117 ~D Jill 15 POW'ER GND \v'EIGHTI 8 oz. 'RS422 RX I DEFAULT (NO JUMPER REQ'D> PO\v'ER CONSUMPTION' , SINGLE ENGINE Jl17 TO --:l11~ I 210 Ma.. ~ 28v DC T\v'IN ENGINE I DEFAULT (NO JUMPER REQ'D) UNLESS OniERWlSE NOlED DIUENSIONS ARE IN INOlES TOlERANCES: x.X .. :i:O.l X.XX • %0.01 N/A NISH: 0501/032 I B r.lfI~r I PAB I~ IUPOATED l11l.EBLOCK; ·CONVERTER· WAS ·TXMTR 19801S025 ~ 10/12:/98 ~OTE7. CORRECTED HElGH""-PRO\1DED SHADIN PIN FOR t.lATlNG CONN. It.lATERlAl: 9707 023 - ,7/15197 PAS ,PG BASElJNE RElEASE ' IPTf • • •Shadin Avionics Filename: 68120 I-I HP.doc DIRECTORY' 681201-1 Report: 4032D ECO Date: April 4, 2007 ECO#: 0704/002 Release date: Rev: H 1-- /,-0-::;' Sec.: IX Approved: It-P-Page I of I PARTS LIST Part #: 681201-1 Drawing #s: 4028-005 Rev C Description: OAT PROBE ASSEMBLY KIT FN PIN QTY. DESCRlPTION MFG. MFG.# DESlGNATlON COMMENTS 10 511201 4 RIVET, AN4703-4 or MS20470AD3-4 15 543216 I OAT STIFFENER RING SHA 4032-082 20 670503 I SHIELD, Temp'Sensor Assy SHA 4005-265 25 670504 I NUT, Temp Sensor SHA 4005-266 30 670505 I WASHER, Flat OAT SHA 4005-303 35 670506 1 WASHER, Shoulder OAT SHA 4005-304 40 681201 I OAT PROBE SHA 4005-794 10 items • • • Shadin Avionics FlLE NAME: [J(9628DP.DOC DIRECTORY: InslnJl Kits Report: 4028 ECO Date: April 4, 2007 ECO# 0704/002 Rev: D Release-date: 4-6-01 Sec.: IX Approved: itAA-Page 1 of I PARTS LIST Part #: IK9628 Drawing #s: N/A Description: INSTALL KIT, F/ADC 200 FN PIN QTY. DESCRIPTION MFG. MFG.# DESIGNA TION COMMENTS 5 230019H-I 4 SPRING LATCH CLIP SHA 4028-074 10 230050C I CONN, 15Pin, D-Sub, F Crimp, w/Contacts POS M2430812-2 (RDI5FIOOOO-50) PI 15 230051C I CONN, 15 Pin, D-Sub M Crimp, w/Contacts POS M24308/4-2 (RD 15M I 0000-50) P2 20 230038 2 CONN, Hood 15 Pin D Sub ClN DA-24658 22 239001 I TOOL, InsertionlExtraction DAN M81969/1-02 25 511002 4 SCREW, 4-40 x W'L, Phil Pan HD SS MCM 91772AI06 30 512007 4 NUT, 4-40 3/16 x 1/16 SS AFT HNSPI8804COOO 35 512014-1 I KNURLED KNOB SHA 4028-132 40 541001 4 WASHER, #4 Split Lock SS MCM 92147A005 45 54280lA 1 MOUNTING TRAY SHA 4028-B05 23 items ADC 200/2000 D-SUB CONNECTOR &5 PART NUMBER 90-380009-2 OR "'\ 90-380009-5 J1 Pl :~~I DC RIGHT FUR F1.0W -SIC +SlG J ", I \ ; ; j ", I \ ( ) '...j .& \ I "ll:; \~I \ DC L£FT FUR F1.0W -SIC +SlG 1 :01 I ,.., I \ ( ;\ I 'f I , ", I \ ( } \~I /1 :~~I PART NUMBER 90-380009-2 OR . 90-380009-5 l ------l & ~ NOTES: -+ + J -~ -PART NUMBER 101-384153-1 OR 101-384153-3 .& PART NUMBER 101-384153-1 OR 101-384153-3 & -+ PART NUMBER PC9DO-XAXXXXPH f-6), (A,-), (1,2). CURVED FACE) && PC90o-XAXXXXPH f-6). (A.-). (1.2). CURVED fACE) ~ PA'TNU".~ - P + K && -+ PART NUMBER PC90o-XAXXXXPH ~7.8). (A, -), (1.2). F'lAT rACE) && PC9DO-XAXXXXPH ~7.8). (A.-). (1.2). F'lAT fACE) ~ PAATNU".~ - L + K && -+ PART NUl.IBER PC9QO-XAXXXXPH (1-8). (A.-). O. (OJR'ern/FlAT rACE) && PC9DO-XAXXXXPH ~ PAAT~~ (1-8). (A.-). o. (OJRW/FlAT rACE) - L + K I && 1. THIS SCHEMATIC IS USED FOR KNOWN BEECH KING AIR MODELS. SOME INDICATORS ARE NOT LISTED BUT MAY BE INTERFACED. CALL SHAOIN TECH SUPPORT IF YOU DO NOT SEE THE PART NUMBER OF YOUR INDICATOR LISTED. INDICATOR PART NUMBERS POSSESSING A PREFIX OF "PC900-" ARE XOTECHNOLOGIES TYPE INDICATORS. THE LAST DIGIT REPRESENTS THE INDICATOR AUXILIARY RATE OUTPUT (1 NUMBER). SHADIN SUPPORTS THE "-1" MODELS ONLY. ill XOTECHNOLOGIES IN'OICATOR P /N PC900-XAXXXXPH-XXO IS NOT SUPPORTED. THE AUXILIARY RATE OUTPUT OF THIS UNIT IS 0-1 rnA. INDICATOR P /NS THAT END WITH A .. -XX2" WILL ENCOUNTER A DEGRADATION IN PERFORMANCE DUE TO THE AUX. RATE OUTPUT OF 0-5.333 VDC. INDICATOR P /NS ENDING WITH AN ..... ARE UNKNOWN. &. THE FOLLOWING XOTECHNOLOGIES INDICATOR PINS POSSESS A K-FACTOR KNOWN TO SHADIN: ADC200/2000 SWITCH SETTINGS PART NUMBER K-FACTOR/oFFSET AUK RATE OUTPUT SW1 SJl2 s.m SW4 PC900-1 A0600-XX1 38,460/0 0-5 VOC o 400 PC900-1 A0750- XX1 30,770/0 0-5 VOC o 500 PC900-1 A0800-XX1 28,850/0 0-5 VOC o 6 00 &. THE FOLLOWING BEECH INDICATOR P /NS POSSESS A K-FACTOR KNOWN TO SHADIN: ADC200/2000 SWITCH SETTINGS PART NUMBER K-FACTOR/OFFSET SW S1t2 SW3 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. DRAWING DATE 6/9/97 I C'LT'A' n TW AJ-LU .L/J.J MINNEAPCU5, NN 55426 UKA~ It.R ';;iA' INSTALLAnON WIRING, FlADe 200/2000 WI AP~~VED ANALOG F.F. TO BEECH KING AIR INDICATORS 0211/047 9803/022 9706/007 ECO' B A - RE.,Y. 3/11'/03 3/26/98 6/13/97 DATE PAS SRB PAS BY BAL KCl KCl APPD UPDATED NOTES 1-6' CORRECTED TITLE' GROUNDED SHIELDS CHANCED NOTE J : 90-380009 5 FRO 26,150/416. REMOVE pIN 9628XO-3 BASEUNE RELEASE . DESCRIPTION ~: N~ FILE NAME tv28-818BJ.DWG DIR~~~RY ~ET 10f J. D-SUB CONNECTOR DRAWING NO. lSlZE Ip IN4028- 818 '" \ I IREV I \ 8 --A . • .------. , ... ...... lli1.IES. & FROM RIGHT ENGINE FF TRANSMITTER; ~ FROM LEFT ENGINE rF TRANSMITTER. & F / ADC $\JITCH SETTINGS AIRCRAFT'S FUEL FLO\J SIGNAL. CONDITIONER <P IN 45AS86801-003). SHLD GND J ~ I J2 '_& IFLD\J SIGNAL IN H ~ FLD\J SIGNAL IN G I • TEMP SIGNAL IN F 'J TEMP. SIGNAL IN E & FLO\J METER A FLD\J METER B +25V DC IN M: PO\JER GND K D I I -V J1 PD\JER GND . K SHLD GND i~ ~ FLD\J SIGNAL IN ~ FLO\J SIGNAL. IN TEMP SIGNAL IN TEMP SIGNAL IN E FLO\J METER ~ FLO\J METER B +25V DC IN M 8 SIG CDNJD. PIN K -FACTOR. SW'l Sv.l2 SW'3 SW'4 45AS86801-003 5150 PPG 6 E 6 E I DRAVING J1 SIG. SIG. GND. ->+ RIGHT ENGINE FUEL· FLD\J LEFT ENGINE FUEL FLO'W , I F/ADC-200 PIN 9.62810-2 PIN 962820-2 F IADC-2000 PIN 962830-2 DATE: I C"LF'A' .nTW 12/17/97 . AJL~~ .L/LJ MINNrAPrLls. MN S5426 DRAFTER INSTALLATION 'WIRING, F / ADC 200, 2000 SINE rr TO' MITSUBISHI MU-300 AND HAM FROM 4028-819- . ..., MODEl,... 400 BEECHJET DRAIJIHG NO. SIZE REV P / N 4028-819 B A I i • • . NOTES & .FROM RIGHT ENGINE FF TRANSMITTER. & FROM LEFT ENGINE FF TRANSMITTER. SIGNAL CONDo p IN PC-620~~425-0098 15: ~1 ~lIG .. _ >RIGHT A 2 SIG + ENGINE RIGHT SIG. IN E ~ .. F·UEL RIGHT SIG. INI D -..,- [ill 3GND. FLD\v' LEFT ENGINE C~' FUEL FLOW' I LEFT SIG. INI AI (', L &1L & LEF T SI G. IN B f---'--"".L...------------< '- I F IADC-200 PIN 962810-2 PIN 962820-2 1--------./ F IADC-2000 PIN 962830-2 SIG C[]ND, PIN K -FACTOR SW'l SW'2 S\J3 S\J4 PC-620-0098 33800 6 . 9 6 9 0501/03~ B ;"f'/I.DS PAB ."., UPDATED TITLE BLDCK' 0007/031 . A 7/19/00 PAD RH ADD 'DR PC-4~5-0098' 91U1021 - V8/98 ·DMD KCL BASEUNE ·RELEASE ' ~Q!...!. ~. :..1!.AIt. B.t. ~D ZSCRJPTIDN .1 ....!1Q.~~ DR1~;~~TE I SHAPIN HINNEAPOLIS. HN ~6 IDRA,f,JJR INSTALLATION 'vIIRINGI AP~c~VED FI ADC-200(2000) TO MITSUBISHI FILE NAME MU-2 VI IFOXBORO PC-620 SYSTEM 4028-909BJ.D'w' . . DIR~~JrY DRAIJING NO. jSIZElp / N fREV ~l :r:::m:::r 4028-909 A \ B I V ~ Wi .. _.... n I P13 \...../ r-------.... J50 R/H ,. ,. E08A20 V SIGNAL \I /' E06A20 T GROUND U E05A20 S ~~ J49L/H GROUND D ~ . E15A20 SIGNAL F )' ( E16A20 E "- ,./ E18A20' 1-...../--- v--- IND, 15 " n FUEL FLD\J r' I I \...../ INDICATOR : OSOV032 A ~·IS PAB .", UPDATED TITLE BLOCK - 3126/98 SRB KQ.. BASELINE RElEASE EJ • I REV. DAU. BT IN't"'D ur..~r llJN ' . " • ~76 P50 .. G GND 8 'IIP----- E04'A20N ----:... - E08B20 B - E06B20 E I-- - E05B20 C K J '- ' ~ l.:J Z F IADC-200, l.:J C;; PIN 962810-3. ~ ~ PIN 962820-3. ~ &F IADC-2000, PIN 962830-3. •~-,'" DIGIDATA PIN 912802-03 PIN 912802-03-G Jlr P1,r: A 3 GROUND ~ 11 GROUND 2 R/H SIG. + 13 R/H SIG. + I I 1 R/H SIG. - I I ,7 R/H SIG. - :::: 10 L/H SIG. + X 15 L/H SIG. + I 1 I I \...../ 9 L/H SIG. - \...../ 14 ' L/H SIG. - ' ' ~ 1. K FACTOR IS 16,270, OFFSET IS O. £ SET F I ADC ~\lITCHES AS FOLLO\lS S\l1=0, S\l2=C, S\l3=O, S\l4=0. & PROGRAM DIGIDA TA FOR LEFT K-FACTOR= RIGHT K:"'F ACTOR= 16,270 PPG, LEFT OFFSET= RIGHT DFFSET=O. ,.. J j:::) P49 - l.:J K ..... z C (/) l.:J " c-- E15B20 T - -.J ,-.J r--- E16B20 U E V I- E18B20 B G L. GND 7 IIIP-- E14A20N '-.;.... P77 NIl ~ FIADC200, 2000 TO 500, 501, 550, REV A U ~{;ALt. ID~A3'"/~'}9\A TE SHAPIN HIME INSTALLATION \tIIRING, DR DIGIDATA \tIITH DC FF 'CESSNA CITATION S550~ 551,' 552. ' APtLIs. HN IJlKSRRU< APPROVED Kct.: IFILE',NAJ£ ~-936A..lDVG D1kE~URT . DRAviNG ~ SIZE I: /' 4028-936 A P N SHEE: []F 1 9803/025 e?<. ., c. •._ ~ ..._... . ... I I PIOO2 \J r-----. PC048 R/H (FUEL FLO\ol P,C.BJ SIGNAL K I' 12 ./ GROUND M 14 L..........;~ I + l;) 8' F IADC..,..200, v; V? PIN 962810-3 ci ci PIN 9.62820-3. & DIGIDATA £ F IADC-2000, PIN 912802-03 PIN 962830-3. PIN 912802-03-G Jlr- Plr .3 GROUND 11 GROUND - ~.2 R/H SIG.. + ~ 13 R/H SIG. + I I I I' 1 R/H SIG. - 7 R/H SIG .. ':%:' X· 10 L/H SIG. + 15 L/H SIG, + I I I I f-- \J 9 L/H SIG. - \"".../ 14 L/H SIG. '- '-- PIOOl I ~ 1. K FACTOR IS 21,980 . PC047 l;) l;) OFFSET IS. O. + I L/H' ..... ..... V? V? ~ SET F IADC SVlTCHES' AS . GROUND M 14 ~ -.J -.J. FDLLO\olS; S\oI1=O, S\oI2=L SIGNAL K 12 S\.i3=O, S\oI4=0. """ ,/ (FUEL FLO\ol P.C.BJ £. PROGRAM DIGIDA TA FOR 1-.........-'-- LEFT K-FACTOR= RIGHT , K -F ACTOR= 21,980, ~ LEFT OFFSET= RIGHT OFFSET=O. " ,0,; CElDD!) ( I I FUEL FLO'vJ \J INDICATOR . I~~~J:TE SHA.DIN HIM£APtLIS. HN :5:5426 . I~~I( INSTALLATION \tIIRING, FIADC200, 2000 APPROVED DR DIGIDATA 'WITH DC FF TO' Ka.. . CESSNA CITATION 525 JET i I~~~G i 0501/032 A I~·"'VO#S PAD ~ UPDATED TITLE BLOCK DJRECTDRY 98031025 - '3/26/98 SRB Ka.. BASEl:lNE RELEASE 4028 ECO .. tREV, DATE H' IAPP'D DEsoc. PTIDN NI. I[ Xl:ALI'" ISHIU ~ 4028-937 ~Ip IN IAI ·------, .1-'----------------P20? F, ..IC-200 FOEL.. MONITOR h PIN 962810-1 (TAIL> PIN 962820-1 F IADC-2000 Jl PIN 962830-1 I, I ,& &RIGHT SIG ENGINE I I I F LA....= NGINE FUEL tu z . ~ 2 R[~~ fIGNAL i I AA I 3 GROUND LEFT (\&ENGINE SIG 112, I I I : l.J I ·6110 I LEFT ENGINE FUEL IJ.E.T. CARD ! I FLO\tl SIGNAL IPIN 542-1158-02 LJ l-------/ llilIE.S.!. 1. THIS INSTALLATION APPLICABLE TO AIRCRAFT \tIITH J.E.T. FUEL MODULE PART NUMBER 54'2-1158-02 ONLY. J,E.T. MODULE NOS, 542-1158-01 MAY BE CHANGED 'TO 542-1158-02 BY J,E,T, SB542-1158-7B. 2. K-FACToR IS 860. ~ SET FI ADC S\tIITCHES AS FoLLo\tlSJ S\tl1=D, S\tI2=D, S\tI3=D, S\tI4=D, ffi PROG~AM THE DIGIDATA FOR LEFT K-FACTOR = RIGHT K-F'ACTOR = 860 PPG, LEFT OFFSET = RIGHT OFFSET = O. & J.E.T. CARD PIN 11 CORRESPONDS TO FUEL MONITOR PIN Z. & J,E,T. CARD PIN 12 CORRESPONDS TO FUEL MONITOR PIN X, . , 0501/006 A tl'":I-/O_~ PAB ZIA.: CDRRECTED NOTES 1 5, 8. 6 9803/023 - 3/26/98 SRB KCL BASEUNE RELEASE: " .- DIGIDATA ill P! i i PIN 912802 .-----0-1131 RIGHT FUEL FLOV SIGNAL 15 LEFT FUEL FLO\tl --'----1 SIGNAL 11 GROUND DRA3~g'iG/.f9AT( I SHAPIN HNlEAPWS. HN ~426 DRA.,Q,ER INSTALLATION 'WIRING, F /ADCcOO, COOO APPRDVED KCL OR DIGIDA TA \.lITH DIGITAL FF TO F"lLE NAME BOMBARDIER LEAR.JET 24, 25D. 028-938AJ.D'w'G DIR~~jlJlRY DRA'w'ING NO. lsrzE I IREV ECO" REV. j}ATE 1!t:....~j} DESCRIPTION __ _ NOJ: lQ ~ ISHEET -l...QE 1 4028~938 to. JP IN \ A I -. . .-----,F/ADC-200 PIN 962810-2 PIN 962820-2 'F IADC-2000 Jl PIN 962830-2 FUEL FLOW' IND. I------- RIGHT ENGINE A-----1 1 I SIG FUEL I FLO\J SIG. ! j I 2 I SIG + RIGHT SIG. :rt 0. ~ 3 IGROUND ENGINE >- 9 FUEL FLO\J FUEL FLO\J IND. I-----. LEFT ENGINE SIG. SIG. -'-- I A Cf .[J II 1 SIG - } .... ' 10 SIG + LEFT ENGINE NOTES: 1. FOR AIRCRAFT 'w'ITH THE FDLLO'w'ING INDICATORS/TRANSMITTERS) A. INDICATOR PART NOS. 850590-1; 850590-507) DSF1549 DR D5154-9, B. TRANSMITTER PART NOS, 850590-513) 850590-515) TFF2905-11 OR 151906-001. 2. K-FACToR IS 27.6 (27)600 PPG), 3. SET F / ADC S'w'ITCHES" TO: S'w'1 = F) S\,/2 = 0) S'w'3 = F) S'w' 4 = 0, DRAIJIN(;IjATE I SHADIlV HINNEAPlJUS. MN ~4<6 3/24/98 DRA~FJ,fR INSTALLATION \rIIRING, F / ADC-200, 2000 APPROVEJl \lITH SINE FF TO ROCK\lELL COMMANDER r FILE NAME 6.90 AND 695 I r " 4028-939AJ.D'JG KCL lSIZElp / N lREV r0501I032 'A ~-I~.:~ PAD ~ UPDATED TITLE BLOCK DIRECTORY DRA'w'ING NO. 19803/025 - 3/26/98 SRB KCL BASEUNE RELEASE Nl T SCAlE ISHE~28 4028-939 A A(CD" 'REV. DA~ --.1ty. ~ DESCrypnON· _ _ _ rQ..l....YE.1 , .~-------.-;...---- • • FIA'De-20D PIN 962810-3 PIN 962820-3 & ill FIADC-2000 DIGIDATA PIN 962830-3 RIGHT ENGINE FIF IND. P080 Jl PI PIN 912802-03 f-----... /1111 GROUND 1 ,-.... RIGHT P SIG. ---------------rl----i. 7 ENGINE SIG > I I2 I SIG + FUEL ---------------~.;7----i SIG. + LH I 3 I GROUND FLO\J ~ ~ LEFT ENGINE FIF IND. P079 j------., ~ w ,-, ~ I SIG. P :} LEFT 9 ---------------~-,---- I 1 r 1 1SIG ! ! ENGINE : i °1 I ! I I I ---------~-----~~---- SIG. + L H ',-) 1 I,) 10 I SIG FUEL FLO\J ~ ~ 1. FOR AIRCRAFT SERIAL NOS. RK-45, RK-49 AND AFTER 'JITH FUEL INDICATOR PART NO. PC900-3B2000-PHl. 2. K-FACToR IS 11.54 (11,540 PPG), OFFSET IS O. &SET F IADC S\JITCHES Tol S\J1 = 0, S\J2 = 2, S\J3 = 0, S\J4 = O. ~PROGRAM DIGIDATA FOR LEFT K-FACTOR = RIGHT K-FACToR = 11.540 PPG, LEFT OFFSET = RIGHT OFFSET = O. I R. SIGNAL 131 R. SIGNAL + 14 I L. SIGNAL - 15 I L. SIGNAL + , I r . . . 10501/032 A I· ~ .,.,~. PAD ~ UPDATED TITLE BLOCK • CJ803/0Z5 - 3/26/98 SRB KCL BASELINE RELEASE ECD ft REV. _I1AT~ BY APP'D DESCRIPTIClti ~ T[)~ D~mG1lATE I 'SHA:lJIJV MINNEAPOLIS. MN ~26 3/24/98 IlJl(~R'kJo( INSTALLATION "'IRING, F /ADC-:200, 2000. APPRCVED"CL OR DIGIDATA \.lITH DC FF TO RAYTHEON IFlh~ Nf:\~ BEECHJET 400A AIRCRAFT !'t028-940AJ.D'JG DIRECTORY DRA'JING NO. lSIZE ',p / N IREV I 4028 4028 - 9 40 1 . 1A A ~ .lJ!LI . L.... I -- _.~,_.. .1-------FIADC-200 PIN 962810-3 PIN 962820-3 & F IADC-2000 ill DIGIDATA PIN 962830-3 Jl PI ,P IN 912802-03 RIGHT ENGINE FUEL 111 GROUND FLO\J INDICATOR r ------ ~ 7 1 R. SIGNAL SIG. -IL ~I n 1 I SIG - RIGHT > ---------41~---- ENGINE I I I ,II I --.---r -------t-..f--- 2 1SIG + FUEL --------- ! 131 R. SIGNAL + -SIG. + I K ~ 1"'- 3 IGROUND FLO\J l--/ LEFT ENGINE FUEL FLO\J INDICA TOR I .... LEFT [----------------1"1----,14 IL, SIGNAL 9 SIG. -IL ~ : I SIG -} ENGINE ! ! ! ! i : SIG + FUEL ----------------t,:j-----l 15 I L. SIGNAL + 10 SIG. + K ~ '--' 'I~ I : FLO\.l I ~ ~ " ~ 1. FOR AIRCRAFT \JITH THE FOLLO\JING INDICATOR/TRANSMITTERSJ A. INDICATOR PART NO. (RAGEN) 1291-2 B. TRANSMITTER PART NO, (GULL) 151-909-001 2. K-FACTOR IS 10.49 (10,490 PPG), OFFSET IS O. &SET AIRDATA S\JITCHES AS FOLLO\JSJ S\Jl = 1. S\J2 = 8, S\J3 = 0, S\.I4 = 0, &PROGRAM DIGIDATA FOR LEFT K-FACTOR = RIGHT 'K-FACTOR = 10.490 PPG, LEFT OFFSET = RIGHT OFFSET = O. IDRA'WINu-rrATE I SHA.DIlV MINNEAPOLIS. MN S~6 3/25/99 DRAfI:>T~ER INSTALLATION 'w'IRIN&. F IADe-200, 2000 APPROVEDJ<CL OR DIGIDATA \.lITH DC FF TO \.IEST\.IIND , FJ!"~ NAME 1124 MODELS 0501/032' 'A l"RUI~ PAD .,., UPDATED TITLE BLOCK' 028-941AJ.D'WG, I 138U3/025 - 3f2()'1'38 SRB KCl BASELINE RElEASE DIRECTORY DRA'WING NO. 1 'REV~ SIZE f ~ It LBfJ6 J!r A~ DESC~ICN JmI.IQ.~ ~8:I 4028-g41 ",P IN 'A DATE lVl •--------------F-/A-n-C--2-0-0------ • • PIN 962810-2 PIN 962820-2 FIADe-2000 J1 PIN 962830-2 RIGHT ENGINE FUEL ~O FLO'" INDICATOR DSF-1549-4 SIG. - I H F ~ I SIG - RIGHT > I - I ENGINE SIG.+IK :: IJ ~2 SIG+ FUEL 3 GROUND FLO'" ~'I LEFT ENGINE FUEL ~1 FLOW' INDICA TOR DSF-1549-4 I r---- n SIG. _ I H ~il't!-----------~r~::.....1-19 I SIG I I I : I 10 SIG. + I K ! L~ ,J t) 1 I SIG + I ~ DSF-1549-2 FLO'" TURBINE (FROM PROB) A COMPENSATOR (ENVIRONMENT) B SIGNAL GROUND C CASE GROUND D DC PO"'ER INPUT (APPROX. 28 VDC) E TOTALIZER LOV (-) F TOTALIZER OUTPUT (+) G TEMP SENSOR H SIGNAL GROUND I DC GROUND J NOTES: DSF-1549-4 5V LIGHT RE