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FAA Approved Installation Manual for the Report No

1. ANE IT BREAKER 4 B TING FII INSTRUMENT PANEI INSTRUMENT PANEL EDM 4 RNESS ENGINE BLOCK GROUND PLACE Y FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 49 of 50 Rev J Primary Engine Data Management System Date 5 24 2014 45 Appendix A Connector Pin Assignments on EDM J1 J2 Only with ARINC 42 Production J1 DB25M Version LU J2 DB25F Production Version ARINC IN 1A 2 Oil Temp R Spare RS232 Data In To Flight Data Ground Oil Pr Hydr Pr N ARINC IN 1B C2 GPS RS232 Data In A GPS RS232 Data Out Oil Pr input 0 5V Oil Hydr Pr 5V power o Fuel Flow Signal o Fuel Flow 12V pwr Torque 5V power N Fuel Flow Ground Torque input 0 5V FQ 1 0 5V coo FQ 2 0 5V 10 e connected to 11 AMPS 1 generator shunt 10 Fuel Temp RTD 11 Fuel Temp RTD nCAL a 007 Annunciator 2 18 Annunciator 3 ee NNI 20 decal 21 Fuel Pr input 0 5V BEEN 21 FQ 4 0 5V Fuel Pr Gnd 22 N2 Np connected to 24 N1 Ng 24 ix c battery shunt FAA Approved Installation Manual f
2. If you fail to validate the fuel quantity readings when complete fuel quantity readings presented by the EDM should not be used for flight YES RESTART 00 31 19 EDM960 DEMO N123JPI 2 Tap YES when you see Do you have table data Fuel Table Data By continuing into the Fuel Table Editor you acknowledge that you have read and understand the Fuel Table Data Editor instructions that came with your J P Instruments EDM 930 It is your responsibilitu to validate the correctness of fuel leuels represented by the system If you fail to validate the fuel quantity readings when complete fuel quantity readings presented by the EDM should not be used for flight BACK 00 32 07 EDM960 DEMO N123JPI FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 25 of 50 Rev J Primary Engine Data Management System Date 5 24 14 3 Tap USER when you see Do you want to restore user table Note tapping FACTORY causes the fuel table stored on the Key Card to over write any previous user entries in the fuel table Use FACTORY if you want to start from the original factory default Fuel Table Data fy continuing into the Fuel Table Editor you ackmmledpe that you haw read and understand the Fucl Table Date Editor instructions thal came with your J P Instruments EDH 0 It is aur responsibility to validate the correctmess of fuel levels represented hy the spilen If you Fall to validate the fuel quantity
3. Master switch Starter VV external shunt Starter solenoid Load Meter Configuration 20 2 Load Meter Configuration Alternatively the shunt can be installed between the alternator output and the main bus in which case it will be the load meter configuration showing alternator load positive only Be sure that the negative side of the shunt is connected to the main bus in the oad meter configuration There is no alarm 21 General Fuel Flow Transducer Installation Use the J4 connector harness 700708 labeled FFSIG white FFPWR red and FFGND black If no previous fuel flow transducer is installed install transducer per APPENDIX A Report 503 FUEL FLOW TRANSDUCER INSTALLATION FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 19 of 50 Rev J Primary Engine Data Management System Date 5 24 14 The EDM 900 930 receives signal from any installed FloScan Transducer with the following FloScan P N s embossed on to the top of the transducer The K Factor is marked on the side of the Transducer and on a white ticket Wire per drawing 700744 Route the JPI wires along the existing wiring bundle lacing every foot The EDM is approved to work with the following Shadin equivalent PN FloScan PN Shadin equivalent PN NA NA 1 680501 680600 NA 1 NA 680503 Before connecting any hoses to the transducer thoroughly clean them and insure they are free of any loose material Never pass air
4. J1 FOR 7 8 and 9 cylinder installations red 19 red 17 red 13 black 25 wht 11 wht 24 THEE TE TET TETTE TEE eee e e e e P ee T e e e 9 e e o e e To 9 o 9 9 VF S S S S S 9 e S e S e e 9 P T T 9 T P T T T 9 9 Vaeatatatatatatatatatatatatatatat ata tat atat tata tata T fictum BI MD ve T T 9 9 9 9 9 9 9 9 e e o S e 9 e P T Tr 2S a a a ata ata ata atat atat atat EGT 7 SAU 94949499949494 494949494 4 494 4 94 9 97 Ho 4 REESS EGT 8 94 FF 9 9 9 9 O O O O OO 9 9 9 OOOO OOOO OO 49 9 94 REEE S EGT 9 9 FMM FOF FOF GOO OOOO GOO OOOO OOO OO OT REESS ELL 3 Lp mST SS S S S e P OOOO OOO 9 9 P P T 9 P 9 9 9 9 9 9 9 9 9 Vaeaata5atat a6 atat atat atat atat 2555 525 a a a a a a a a a ad Remote temperature voltage alarm light option TIT 1 sensor D du 12 or 24 vdc power lead Aircraft engine ground lead DATA IN DATA OUT FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 44 of 50 Rev J Primary Engine Data Management System Date 5 24 2014 J2 CHT sensors x4 or x6 EGT sensors x4 or x6 ST 0 E FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 45 of 50 Rev J Primary Engine Data Management System Date 5 24 2014 44 J3 RPM MP Oil P J3 RPM 420815 1 or 2 RPM sic 1 2 RPM around green 1 black 2 red 3 RPM power
5. 3 im a di HORIZONTAL ORIENTATION The EDM display may be mounted from the vertical centerline of the Primary Flight Instrument T to a maximum of 21 to the further most gauge of the EDM display and to the left of the centerline as much as needed VERTICAL ORIENTATION The EDM display is to be mounted within 10 from the horizontal centerline of the Primary Flight Instrument T The installer should insure that the EDM display is not obstructed by either the glare shield or the control wheel The installing A amp P and IA must insure that the installation location complies with the viewing angle requirements listed above 8 EDM 900 930 Key information installation Aircraft specific configuration information is loaded differently on both the EDM 900 and the EDM 930 The configuration data is the same for both instruments The data for the EDM 900 930 is loaded via the mini USB port on the EDM 900 and a standard USB port for the EDM 930 FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 11 of 50 Rev J Primary Engine Data Management System Date 5 24 14 Be sure to verify that this matches your aircraft Note If your EDM should ever have to be replaced with a different unit the factory will reprogram it to match your configuration You should always retain your fuel quantity calibration records as these may need to be manually re entered in a different or serviced unit 9 R
6. Oil P i2s 0 5v PN power 159936A 0 150 psi black oiL P Il EE signal Green 6 uu MM sue MAP i2S 0 5v PN Green 8 159934A 0 30 psia 9 NC J 3 Harness with i2s Oil and manifold pressure sender FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 46 of 50 Rev J Primary Engine Data Management System Date 5 24 2014 J4 FF GPS AMP 2 White 1 Data out to GPS Gray 2 Data in from GPS Serial communications white 4 red 5 ME black 6 if Main FF 700900 1 201 2 231 White 12 FA Return FF 700900 1 201 2 231 Optional Right low i l_ fuel switch optional 5 6 p Remote fuel flow alarm light option F Power and ground connect F2 to pins 5 and 6 tivel Left low pins 5 and 6 respectively l fuel switch White 14 3 Optional Gray 15 159920 P FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 47 of 50 Rev J Primary Engine Data Management System Date 5 24 2014 44 1 J5 PN 790723 fuel tanks fuel press amps Main Tanks Voltage to Resistance interface box for MAIN amp AUX tank PN 790802 Pennycap and Gull require FQ resistive senders PN 790802 MAIN amp AUX tanks 1 White S2 PN 791802 White Sig 1 2 Green c MAIN White sig 2 S 12 Red i Gnd S D PN 790723 3 Blk N S as Bik x2 N P d Fuel Press Sig Ground at Sender N L A 4 Green
7. The OAT option is displayed as an independent digital temperature bar graph such as 75 16 1 Induction Air IAT Compressor Discharge Temperature Probe Install optional Use the J1 connector harness 790200 and insert the yellow wire into the connector pin 3 and the red wire into pin 4 All wiring must be type K thermocouple wire The Induction Air Temperature probe IAT is installed just after the inter cooler and the Compressor Discharge Temperature CDT just before the inter cooler The probe is the same as an EGT probe and installed similarly to an EGT probe A large clamp is supplied to fit around the air duct leaving the inter cooler Alternately a 1 8 NPT fitting is available IAT option is displayed as an independent digital FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 15 of 50 Rev J Primary Engine Data Management System Date 5 24 14 temperature like 125 IAT On non turbo engines the IAT in reality is the Carburetor temperature and displayed as 34 CRB 16 2 Carburetor Probe Installation optional Use the J1 connector harness 790200 and insert the yellow wire into the connector pin 5 and the red wire into pin 6 All wiring must be type K thermocouple wire Do not splice ordinary copper wire in any temperature probe circuits Locate the access hole 1 4 24 thread in the carburetor near the butterfly valve Remove the screw plug now in that hole and screw the CRB probe into the carburetor t
8. 8 Component Parts list for Kit 1480 Differential Fuel Pressure only if required by POH 1 P N 159938 Fuel pressure sensor 1 P N 159961 Clamp Loop Cushioned 1 P N 174204 Connector MS 3116F8 4S 29 9 Component Parts list for ampere shunt Kit 1300 1 P N 159920 100 amp shunt 2 Ring Terminals 29 10 Component Parts list for Fuel Flow Transducer 1 fuel flow transducer 201 or 231 PN 700900 1 2 8 inches of 1 5 dia fire sleeve 1 3 pin connector housing 3 female pins 2 AN816 4 4 fittings Continental or AN816 4 6 Lycoming 29 11 Component Parts list for MAP sensor KIT 1440 1 P N 159934A Manifold pressure sensor 1 P N 159961 Clamp Loop Cushioned 1 P N 174402 Connector Pack 3 Pin and Terminals 29 12 Components Parts list for non pressurized RPM sensor P N depends on Magneto make and model Bendix magneto 20 1200 P N 420815 2 Slick magneto 4000 or 6000 P N 420815 1 Bendix dual ccccceeeseeeeeeees P N 420808 FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 34 of 50 Rev J Primary Engine Data Management System Date 5 24 2014 29 13 Components Parts list for pressurized RPM sensor P N depends on Magneto make and model SIICK 5000 deatendeniek cownexetuneeeiac P N 420809 Bendix magneto 20 slick 600 P N 420806 Bendix Dual P N 420808 Bendix 1200 5 iter brs esa ooi ny pat P N 420807 30 Weight and Balance Data 31 Pil
9. 908 EDM 900 and EDM 930 Page 26 of 50 Rev J Primary Engine Data Management System Date 5 24 14 7 Tap TANK to select the next active tank and repeat previous step Continue until all tanks points have been set 8 Tap TABLE You see Fuel Table Data White at top of screen with a table You may change any of the fuel levels in the left column except for empty You will enter the readings taken previously on paper into the right column Fuel Table Data LEFT 102 0 GAL wor STEP EDIT BACK 00 43 01 EDM960 DEMO N123JPI 9 Tap hold STEP to select the cell you want to edit Tap EDIT to change the value Tap or hold Modify to change digit Tap digit to change another part of the number 10 Tap SAVE to record it Follow the on screen menus to edit the value Repeat previous step until all tanks data have been entered 11 You see Save fuel tank data Answer SAVE to store all final data values or CANCEL to return to table editing To complete the process tap SAVE a second time Fuel Table Data RIGHT wow ft SAVE CANCEL 01 57 43 EDM960 DEMO N123JPI 23 Fuel Flow Totalizer Refuel Question The fuel flow totalizer can be set to a different value than the fuel level tank size To reprogram the Refuel setting for Main total and Auxiliary total enter the Factory Program Mode by holding buttons 1 and 2 in for a few seconds until the display reads Program Keep tapping next until you see END A
10. 930 Page 16 of 50 Rev J Primary Engine Data Management System Date 5 24 14 18 1 Alternate method of installation keeping the original sensors in the aircraft operational The oil pressure sensor should tee off the oil pressure line feeding the original aircraft gauge or the oil pressure switch is removed and the sender is installed in that location 19 Fuel Pressure Sensor Installation using combination sensor Use the J5 connector harness 790723 Mount the pressure sensor to the pressure line using a flexible hose and fittings not supplied as depicted in the drawing below Use Aluminum Clamps MS21919WDG25 or WDG14 to mount the pressure sensor to engine mount structure or firewall Do not mount the sensor s directly to the engine Connect the other end of the hose to the existing pressure line Later you will connect the pressure sensor to the three pressure sensor wires through the supplied 3 pin connector i2s sensor PN 159935A Normally Aspirated or Turbo Normalized or PN 159938 for turbocharged Fuel pressure sensors are only supplied if the POH requires it If not in the POH Fuel pressure can be supplied at additional cost P 2 GRN FP Sig 7 16 UNJF P 3 RED FP PWR 5 4 fitting MS 24587 FITTING P 1 BLK FP GND y L DMD AEROQUIP 303 Flex hose _ E PN 159935A or PN 159938 Differential port 7 DO NOT MOUNT SENSOR DIRECTLY TO ENGINE L om on PN 159938 Vll FAA Approved Installation Manual for th
11. NON TSO 30 Record time 6 sec intervals NON TSO 31 Hobbs on at 1000 RPM NON TSO On 14 vdc systems during start up the EDM may reset it self This is normal due to extremely low battery voltage The conditions and test required for TSO approval of this article are minimum performance standards It is the responsibility of those desiring to install 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 The article may be installed only if installation of the article is approved by the Administrator The functions of Volts Amps and Horse Power were tested to DO 160D and DO 178B but not TSO d since no TSO exist for these functions Deviation granted for TSO C49b to include digital display and sensor All TSO required probes transmitters and sensors also tested to DO 160D FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 31 of 50 Rev J Primary Engine Data Management System Date 5 24 2014 28 EMI Radio Test and functional check Even through the EDM 900 930 has been tested to DO 160E Section 20 EMI the installation itself could creates radio interference on specific frequencies The following test is to insure that this does not exist EMI RFI TESTS perform tests in accordance to the table below to insure wire routing and connectivity has not compromised the signal integrity of the NAV COM receivers Power up th
12. UA PN 159935A ord 5 White or 159938 i2s Fuel Pressure 0 50 PSIG 6 red PN 159935A or 7 black 0 100 PSID PN 159938 Differential Pressure Differential port for upper deck pressure i i Electrical Connections are the same for PN 159938 URS both 9 white ig White Sig 1 iio PN 790802 White sig 2 _ z isst cs 12 red AUX Tanks S puis s i N 3 black N cl N Y Blk x2 13 white Aux Pwr IN optional Sea RN gs Signal AMP 14 White 15 Gray AMPS 1 FUEL TANK CONFIGURATION 7 Black L MAIN L MAIN R MAIN R MAIN L AUX R AUX TWIN 8 White PN 159920 sincte TWN L NC FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 48 of 50 Rev J Primary Engine Data Management System Date 5 24 2014 J 5 Harness with i2s fuel pressure sender OIL TEMI PROBE w EGT PROBE O ECT PROBE O CHT PROBE S CHT PROBE JMBERS ARE TYPICAL FOR LYCOM gt ENGINES IN OSITE CO LY LINDER PL LP fitum s esse EL EGT PROBE T EGT PROBE O CHT PROBE 4 HT PROBE ll NOTED MATL V LAYO OTHERWISE E RE MENT Er n 5 ye C Iw SIPOBp 4 d UU JNLE Ne EGT PROBE T PROBE O ECT PROBE PRE CHT PROBE PICTORAL INSTI ul ato a E a Li lt i EGT PROBE CHT PROBE
13. located as close as possible to the pilot with an unobstructed view and for easy access to the buttons on the instrument The least desirable view angle is landscape looking up To improve the view angle call the factory A remote display is also provided for alarm indications and should be directly in front of the pilot B The RAD PN 790749 mounts in a 5 8 inch hole in the panel directly in front of the pilot for the EDM 930 and an alert light for the EDM 900 is mounted in a 3 8 dia hole The diagram below should be used as a guide for cutting and drilling the mounting and buttonholes in the instrument panel The dimensions shown are for the finished cutout Allow extra clearance for any panel finish such as powder coat The EDM mounts from behind the panel through this cutout Fabricate the appropriate cut out using the fig below as a guide If the panel has too many holes for a clean installation it is recommended that a 0 10 aluminum overlay panel be constructed and installed over the original instrument panel and the EDM be installed into this overlay panel The Remote Alarm Display PN 790749 mounts in a 5 8 inch hole in the panel immediately above the Attitude Gyro D G HSI 0 5 inches from their centerline directly in front of the pilot a de fo N fr ai P4 4g ri ERE 5584 E K Ye s F 4 6 6 861 Fa P d A 4 787 Pd EDM 930 tne P4 PANEL CUTOUT per d mi 4 1 Figure 1 FAA Ap
14. the K Factor 39 Programming Accumulate Trip Total 40 Trouble Shooting 41 GPS Interface Diagnostics 42 Connector Pin Assignments on EDM J1 through J5 43 Connector Pin Assignments on EDM JI through J5 44 J3 RPM MP Oil P 45 Appendix A Connector Pin Assignments on EDM J1 J2 Only with ARINC 42 46 Appendix B ICA Report No 908 Page 1 of 50 Rev J Date 5 24 14 Page Co MAR t YW bo LO 10 11 12 12 13 14 14 14 15 15 16 17 18 20 26 2 24 26 30 31 32 34 34 35 35 36 36 37 38 38 39 40 4 42 45 49 50 The Owner of the EDM 900 930 must keep this manual J P INSTRUMENTS PO BOX 7033 HUNTINGTON BEACH CA Last printed 6 2 2014 10 18 00 AM FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 2 of 50 Rev J Primary Engine Data Management System Date 5 24 14 1 Revisions Added new pictures of 900 and 930 page 6 Abbreviations page 4 Revised how the LA 28 2011 JPI data base functions page 3 Added revision box Page 2 Added fuel level calibration page 22 Renumbered all pages Revised to include new trouble shooting section for ICA and renumber pages Updated 12 02 2011 pressure sensors to i2s ee ie TSO Label to show PR eal eee I a cL change and added ARINC 429 wire chart 1 peo 2013 a pp Updated Part Numbers and Added new ICA and Pressure bulkhead paragraph 5 24 2014 sacar pF 2 Read This First e The following notes apply to a new installation R
15. D leaning 10 F per second OFF SCALE EGT COLUMNS Off scale EGT column readings EDM in Return to Standard mode by holding IS NOT THE HOTTEST the hottest MAGNETO CHECK DURING LOW POWER low power settings OPERATION register signals sensor or wiring signals OPEN PRB Open probe Wiring to probe is open circuit Check troubleshoot connection Swap probes to troubleshoot RED X DRAWN THROUGH Measurement out of range Have the mechanic verify if it is the A SINGLE GAUGE engine or the sensor Replace as necessary RED X DRAWN THROUGH DAU failure or DAU communications error Check power to DAU and wiring a uer FOR AN harness connections CAL ERR Calibration error Return unit to factory DSP XXX Internal communication error Return unit to factory COMM ERR Internal communication error Return unit to factory NO 5 MV Calibration error Return unit to factory FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 40 of 50 Rev J Primary Engine Data Management System Date 5 24 2014 NO 50MV Calibration error Return unit to factory NO 2 5V Calibration error Return unit to factory WARNCAL WARNCFG Transient warning messages warning messages Return unit to Return unit to factory HOBSERR Bisonsionii aon s RN time of the most recent flight may not a unit to factory be reflected in the HOBBS meter HOBSBAD The HOBBS data has been corrupted Return unit to factory HANGCFG HAN
16. FAA Approved Installation Manual for the EDM 900 and EDM 930 Primary Engine Data Management System TABLE OF CONTENTS Section l Revisions 2 Read This First 3 Instrument Labeling 4 Primary TSO Label 5 Operation and Abbreviations 6 Remote Alarm Light EDM 900 7 Locating and Installing the Indicator and Remote Alarm Display RAD and Alert Light 8 EDM 900 950 Key information installation 9 Routing the Wiring Harnesses 10 Pressurized Aircraft wire Routing 11 Power Connection 12 Probe Wiring 13 Exhaust Gas Temperature Probe EGT Installation 14 Cylinder Head Temperature CHT Probe Installation 15 Radial Engine CHT spark plug gasket 16 Outside Air Temperature OAT Probe Installation 17 Oil Temperature Probe Installation 18 Oil Pressure Sensor Installation 19 Fuel Pressure Sensor Installation using combination sensor 20 Ammeter Shunt Installation 21 General Fuel Flow Transducer Installation 22 Fuel Level Sender Wiring Types 23 Fuel Flow Totalizer Refuel Question 24 GPS Interface 25 Manifold Pressure MAP Sensor 26 RPM Sensor installation 27 EDM 900 930 Specifications and Limitations 26 EMI Radio Test and functional check 29 Component Parts 30 Weight and Balance Data 31 Pilot Programming 32 Programming the HP Constant 33 Programming the MAP 34 Selecting Fuel Pressure Type EDM 900 only 35 Customizing Non Primary Data EDM900 only 36 K Factor 37 Fine tuning the K Factor 38 Adjusting
17. GCAL Internal system errors Return unit to factory 41 GPS Interface Diagnostics Problem Situation Correction Measurements xxx REQ No communications from GPS receiver to No connection or aircraft GPS is off XXX RES AND XXX EDM MPG are all missing from the scan NO COM message and Communications are received by EDM and Verify correct output format setup in xxx REQ XXX RES AND the Auto Protocol setup is in process GPS receiver check GPS XXX MPG are all missing connections from the scan NO SIG message and GPS receiver has insufficient signal for Check GPS signal xxx REQ XXX RES AND valid data XXX MPG are all missing from the scan NO WPT message and No waypoints are programmed into the Program way points xxx REQ XXX RES are aircraft GPS receiver all missing from the scan FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 41 of 50 Rev J Primary Engine Data Management System Date 5 24 2014 42 Connector Pin Assignments on EDM J1 through J5 Rear view of EDM 930 Showing Connector Locations View facing rear of instrument RPM MAP OP 1 0000 0 0 9 9 9 B JO RAD QVO FP FQ Amps 9 15 QAO FF GPS female connector Q5 9 Options power e 000000000000 14 O Leete o ooo o EGT CHT FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930
18. M 900 and EDM 930 Page 6 of 50 Rev J Primary Engine Data Management System Date 5 24 14 Se ES SSE RAE Sos S OIL T OIL P FUEL P 2400 2400 250 100 40 153 304 50 ct EE 253 UE 1007 03 3 196 SQ 19 3 7 4 150 2600 AMPS CDT 25 5 3 300 e MANIFOL 4 gt 153 E 15 7 PRESS A 35 ha 5 t byt 13 TE 7 20 30 453 1903 19 sup p mate t 11 2d Strip Chart Gauges I r TIT 1537 1540 1525 1550 391 389 390 4 J X Gar P497 1527 1536 1531 389 388 391 EGT Wer WE TM FUEL QTY 8450 FUEL FLW LEFT RIGHT y 25 F F z 400 f 1350 152 EGT CHT f300 1034 z 1250 53 456T 123456 0 EN NE Message Area HT H M TRUE EE NS all functions F Dim EGTIFF 13 54 32 M20K TSIO 360 N1151M show up here Step Lean Manual EGT FuelFlow USB RS 232 Auto Dimming Button Find Dimming Switch DataPort Port CD Cell Button Download EDM 930 Display FAA Approved Installation Manual for the EDM 900 and EDM 930 Primary Engine Data Management System Report No 908 Page 7 of 50 Rev J Date 5 24 14 EDM 900 TFT Flat panel display Portrait Mode Remote Alert Light With the placard 7 CHT in Green Engine EGT CHT TIT No 3 Cyl in Message area EDM 900 TFT Flat panel display Precent of Outside HorsePower All engine Temp s Fort TIT RPM P MR CIJU aF OAT TS F iS Tod 147 Landscape Mode Dal BAT ALL RIS STEP LF 3 amp j f rd i fi Manual dimmi
19. Page 42 of 50 Rev J Primary Engine Data Management System Date 5 24 2014 43 Connector Pin Assignments on EDM J1 through J5 Rear view of EDM 900 Showing Connector Locations P5 15 000 00 0 0 0 12 0 0 79 Q0 0 Ae QU Alert Light 1 P3 Du d P1 18 0 O FOL vor 30 ev 9r 29 07 NO WO 20s 202 4 Dn SA P2 3 0 0000000000 0 20 Tq 15 0 0 0000o 8 207 000000 0k h P4 FAA Approved Installation Manual for the EDM 900 and EDM 930 Primary Engine Data Management System Report No 908 Page 43 of 50 Rev J Date 5 24 2014 yel 1 red 2 yel 3 red 4 yel 5 red 6 yel 14 red 15 yel 16 red 17 yel 18 red 19 gray 12 red 13 black 25 J1 For 4 and 6 cylinder installations SER NNNEEEID OIL temperature sensor IND temperature sensor ALAA 9 Pi tt 9 o 9 9 o 9 9 9 9 9 9o 9 9 9 9 99 9 9 9 9 9 9 9 9 Se See So So So Se Se So So So So Se Se So So So So See Se So So So e Se So So So See fF i eee NN NNS TW Bll 7 Carb temperature sensor L APA tee POO OOOO OOOO OOOO OOOO l I O A AA 75 45 7 AA f P I p P f f i P P f i f f p f I f i f P i f P d i A SERRE RARER RRR TIT 1 sensor TIT 2 sensor 9949494 4 4 4 994 4 9494 49494999494 4 49494 4 494949 9494949474 ERE R RRR EERE RRR Remote temperature voltage alarm light option 12 or 24 vdc power lead Aircraft engine ground lead
20. SIY JS 43QN3S lv QNO 3NION3 319NIS xnwv Iz31 IS BIUN3S 1v OND 3NION3 379NIS NIVW IRS dd H3JN3S lv CNO 3NIDN3 319NIS NIVN 1331 9i 102 LHOMAGOD SIUDUIMIISUL df JO NOLLVINSIOJNI AYVLSdOUd SNIVLNOS ONIA vC SIHI NML 319NIS 614084 SS3NNVH Sd SYM 3 I9N3 3 0NIS INY Z4064 SS3NkWH SZ d MOJ 35 3H ES Si 3S 313Y NOu202084 ON 704 704 COJ cod coz ZO LO3 t d x18 LHA yE LHA 5iS ONS AS Ong 1HM Ong LHA 3NI N3 JINIS gt SNISN3 JI9NIS p SxNvl xnv SHAWL X v v Nld s4 E B Nld e ssSEZz zzzd77 381 77 T f T l rT eai a i e ss Ees end ARTT pas 1 T1 r1 1 c Nid 222 9g z acon 03 __F Lid 1 L Nid 2777 d 6 L j 9d var dWAv 489 e dNY LHA e 13 4 N39 c 3n34 ONB d 3na Q3 Nid e c08064 Id LOWINGSD SNOLLWHNSIANOD ALO 1374 3410 N03 JuvOCHVH HUM Q3X420vd ONIMVWHO BuviddOdddy OL 434394 CNv XOS NOILONNALLOION ZOBL6L JSA ALO T3043 TINS ONY CVOANN3d YOd _ NOILVANSIANOD TWOldAL SI XO8 ALO T3n3 SAILSISSH 208062 i QaiiDsds 3S M43H1O SS3 Nh S3L FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 22 of 50 Rev J Primary Engine Data Management System Date 5 24 14 22 3 Voltage Output Type Sender System Voltage output type systems usually have a convertor box This is typical with the Pennycap brand capacitive sender system The Pennycap convertor box measures sender capacitance
21. and converts it to a DC voltage output signal for the aircrafts fuel level gauge In some cases the Pennycap convertor box alternately monitors two tanks per wing controlled by cockpit selector switch positions This is typical for Cessna s having 4 selectable tanks The EDM can interface to this system with the addition of the dashed interface hardware PN 791802 shown below NOTE This drawing is accurate for most models of the Pennycap system however it is the installer s responsibility to verify proper connections to the Pennycap output signal 22 4 Fuel Tank Calibration Setting Fuel Calibration Points The EDM interfaces to various fuel level sensor types to facilitate direct reading of the fuel level in the aircraft fuel tanks The EDM has a multi point fuel calibration table that you must enter This table contains calibration values stored in non volatile memory used to translate sensor readings into the displayed fuel quantity values The calibration information is collected and recorded on paper for later entry into the EDM NOTE Fuel quantity gauges will not be functional until the fuel calibration information has been entered into the EDM You will use the EDM instrument itself as the measuring device to collect calibration data The following describes the basic procedures necessary for collection and entry of data into the fuel level calibration table Note Any changes to fuel table data will be temporary until you execute the SAVE fun
22. art No Displayed on 930 4 Primary TSO Label PN 790000 A xxx Wt 1 7 Ibs J P Instruments Inc PN 790000 B xxx Wt 1 7 Ibs SN XXXxx Costa Mesa CA 92626 Lie recon ci wee ee A PN 790000 C 120 Wt 2 7 Ibs MFG DATE xx xx xxxx TSO C43c CLASS 1A TSO C45a TYPE TSO C55c TYPE Il Bld 1 xxx Xx xxxx TSO C4A4b TSO C47 TYPE Il TSO C49b TYPE VII POWER 14 28 VDC DO 160E ENV CAT DIXBAB SBM XXXXXXABBBAWM B3K33 xxA CURRENT 4 0 AMP MAX DO 178B LEVEL C H W 7999 x S W PN 7990 x Note EDM 900 930 950 TSO C55 incomplete system for Type Float Inst no sensor tested Note EDM 950 Display less incomplete system for all TSO s Note PN790000 C 120 incomplete system Display only FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 4 of 50 Rev J Primary Engine Data Management System Date 5 24 14 5 Operation and Abbreviations The EDM 900 930 is a combined electronic indicating system which simultaneously displays to the pilot powerplant and aircraft systems operating parameters It includes the following indicating systems replacing all previous primary digital and or analog instruments Message Area Abbreviation in parenthesis X denotes cylinder No Gauge Function ESSE em 8 Alarm Abbreviation Engine Manifold Pressure MAP xx x in hg Engine Cylinder Head Temp CHT2 xxx F Outside Air Temp Estimated Fuel required to Waypoint Est WP REQ xx GAL Estimat
23. at probe may be interchanged to an adjacent cylinder if necessary for trouble shooting and servicing Thermocouple wire length is not critical and should be trimmed to any length as required for a clean installation The Temperature probe must be wired with the correct polarity The temperature probe connects to its temperature indicator with yellow jacket Teflon Chromel Alumel wire supplied Strip the wires as shown below observing color coding ee keca yellow 4 Fold back wire Thermocouple wire harness ue m sa red 41 4 beg 1 1 2 Terminate each wire with a crimp on ring terminal provided The ring terminals may be crimped with an AMP part number 48518 crimp tool is recommended however a service type tool may also be used Verify the quality of each crimp with a sharp tug on the wire The terminal should be impossible to pull off when crimped correctly shrink tubing Place a x 4 inch sleeve over each pair of wires in the wiring Connect the wire ring lug to the probe ring lug using the supplied number 4 screws and nuts placing the star washer between the ring lugs not against the nut Important place star waster between two ring terminals and tighten nut and bolt as necessary to instrument to probe Slide the sleeve over the joint and secure with three tie wraps nee N i x 4 sleeve tie wrap 3 places The most common installation problems are related to poor quality ter
24. ction available after last cell of the last tank table is entered Before beginning the fuel table entry edit process you must have properly installed and tested for correct functionality of the fuel sensors WARNING e Never add or remove fuel from the aircraft when the master switch is turned on e Fuel quantity gauge performance is affected by many factors such as the integrity of the sensor performance the accuracy of the calibration data you collected and entered and most importantly your validation that the EDM fuel quantity gauge is accurate and repeatable after installation and calibration You should not use the fuel quantity gauge system for any flight related operations until this validation criteria has been met FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 23 of 50 Rev J Primary Engine Data Management System Date 5 24 14 Getting Started Collecting Fuel Level Calibration Data using the EDM as a meter 1 With power off hold in Button 4 Button 1 being far left and then turn on power For each EDM monitored tank create a paper table with the desired number of calibration points 2 to 5 and at what volume each will be Number of calibration points to be entered into the system later The zero gallon point reading is always taken with unusable fuel in the tank Example of a completed 3 point table for LEFT tank 39 0 GAL 1907 19 5 GAL 1154 2 This screen shown bel
25. ctory Program Mode 4 After Factory is displayed in the scanner message area tap the NEXT button until CUSTOMIZE DISPLAY is displayed in the scanner message area 5 Hold the STEP and LF buttons until the word ADJUST appears in the message area 6 You will see a prompt like 1VOLTS or similar This describes the data channel to be displayed in the first non primary data location 7 Tap the CHANGE button to change to the next non primary data channel The new data channel selected will be displayed in the Tap the NEXT button to select the next non primary location such as 22AMPS 10 When all changes have been made hold the STEP and LF buttons until the word SET appears in the message area 11 Tap the STEP button repeatedly until the message END is displayed in the message area 12 Tap the button labeled YES to save changes and restart the EDM 36 K Factor The K factor is shown on the fuel flow transducer as a four digit number which is the number of pulses generated per gallon of fuel flow Before installing the transducer write down the K factor here To enter the number move the decimal point three places to the left For example if the K factor on the fuel flow transducer is 29 123 enter 29 12 in the K factor parameter If the K factor is increased the indicated fuel flow will decrease and vice versa When the K factor is changed during a trip calculations of fuel used fuel remaining and time to empty are n
26. e Report No 908 EDM 900 and EDM 930 Page 17 of 50 Rev J Primary Engine Data Management System Date 5 24 14 19 1 Adding a non primary gauge to the system Requirements All EDM930 and EDM960 units manufactured after Sep 15 2012 have the EDM Configuration Editor built into a separate utility memory area of the EDM To start the EDM Configuration Editor hold the left two EDM buttons STEP amp LF while powering up the EDM This will start the EDM in a special AppLoader mode Once the EDM Configuration Editor program is found a button will be labeled CFG EDITOR Press the button to run the EDM Configuration Editor program Follow prompts and continue to the Usage Agreement page and press ACCEPT to continue Tap YES or NO for SHOW CONFIGURATION TUTORIAL Tap NEXT to skip RESTORE FROM USB DRIVE Continue tapping NEXT until you see EDIT GAUGES Tap YES to begin the process Using the NEXT button will scroll through the available non primary gauges on the display Once the gauge you wish to modify appears tap MODIFY Tap NEXT until the title block FUEL P or whatever non primary gauge you selected is highlighted Tap MODIFY then YES when Change Gauge Channel appears Follow prompts to select a new gauge title Tap SAVE to save changes to the gauge YES to confirm Tap DONE to exit gauge editing mode Tap NEXT repeatedly until EDIT CHANNELS is displayed Tap YES to edit channels This will take you to
27. e aircraft bus or buses in accordance with normal engine prestart procedures see Aircraft Pilot Operating Handbook Verify that the EDM 900 930 is operating normally and there are no bad probes or alarm messages Set the frequency and audio panel to listen to that radio Loud buzzing humming is considered unusual noise in the context of these tests also the OBS needle should not move Should any EMI noise be found that is attributed to the EDM 900 930 system it must be corrected by shielding and or rerouting wiring to eliminate the noise If unusual noise is heard remove power from the EDM 900 930 system to check if it is the source of this noise If the EDM 900 930 system is not the source of unusual noise then mark the table with a PASS Saag EASSEAID HPASSFAIL FAA Approved Installation Manual for the EDM 900 and EDM 930 Primary Engine Data Management System 29 Component Parts Display EDM 930 P N 790000 C xxx Report No 908 Page 32 of 50 Rev J Date 5 24 2014 Single engine Singeengne 6 Cyl 8 Cyl 9 Cyl EGTpobeKITPN1280t J 4 6 7 8 9 CHTpobeKITPN120 d 4 6 7 8 9 OAT probe with option KIT 1300 IAT probe with option KIT 1144 Ew J Se p cg p m np o Ammetershunt PN 159920 1 1 1 1 I d IL I1 lI ek l I I ll 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 29 1 Component Parts Lis
28. ead this section before proceeding e The JPI warranty found in the back of the pilots guide clearly states that JPI will replace defective parts under warranty but does NOT cover labor to remove or install any parts e The most common cause of probe problems is poor terminal crimps Crimp ring terminals with AMP tool or equivalent Fold back the wire double before crimping terminals e Do not use aluminum fittings or Teflon tape or pipe sealant with the FXT 201 or FXT 231 fuel flow transducer e Write down the K factor engraved on the side of the fuel flow transducer here Once the transducer is installed and covered with the fire sleeve you will not be able to access this K factor e Determine the locations of all holes before drilling to ensure that nothing interferes with the probe clamp clamp screw or wire e Provide service loops at the instrument so that it can be moved for maintenance or troubleshooting e Thermocouple wire length is not critical Trim to required length allowing for service loops at the engine so that probes can be swapped with probes on adjacent cylinders for troubleshooting purposes e Dress all wires away from high temperature components such as exhaust stacks e Never splice thermocouple wire using copper wire Use only K type thermocouple wire Solder using zinc chloride flux such as Nokorode brand rosin flux alone will not work e Observe correct polarity on all probe wires Connect like colors toge
29. ed Fuel Remaining at Waypoint Est WP RES xx GAL Nautical Miles per Gallon ECON xx x MPG Brightness Dim control DIM BRT FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 5 of 50 Rev J Primary Engine Data Management System Date 5 24 14 6 Remote Alarm Light EDM 900 The remote alarm light is a Red or Yellow light depending on the alarm condition The EDM 900 incorporates a single light that alerts the pilot that a problem existing within the engine This light is place in with the primary flight instruments and required only if the display is more than 8 inches from the center of the instrument T to a max of 21 inches It is a single light that changes color with condition and the label associated with the light must be lit by a post light or such that you can see the word ENGINE 6 1 Remote Alarm Display RAD Operation EDM 930 The RAD is a 0 2 high 8 character independent display found on the EDM 930 only The RAD will still function if the main display is inoperable An alarm such as the CHT is 480 on cylinder number 2 is displayed as 480CHT2 The label CHT2 will flash whenever an over temperature exists and will extinguish when the temperature falls below the limit temperature Other alarms would be displayed as for example 2780 RPM The RAD is located directly in front of the pilot and displays digital caution and limit excedances when any of the parameters have reached its preset trigger po
30. erwise the next step will be skipped panei KE 23 90 T Adjust the instrument s K factor to match the fuel flow transducer K factor TR IP N TR IP N N No Upon informing the EDM that you refueled the aircraft reset total fuel used to O pan Y Yes accumulate total fuel used rather than reset to 0 at each refueling See page DR PS DATE AND Displays the Date and time TIME FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 35 of 50 Rev J Primary Engine Data Management System Date 5 24 2014 END Y END A STEP exits the pilot programming mode LF reenters pilot programming mode 32 Programming the HP Constant You must adjust the HP Constant once for your aircraft You must perform this adjustment in the air while the aircraft is in flight between 5 000 and 8 000 feet MSL 1 Enter the pilot program mode by simultaneously holding the STEP and LF buttons for five seconds 2 ap STEP repeatedly until you see for example HPC 125 Then hold both the STEP and LF buttons display until you see ADJUST followed by HPC 125 The adjustment range for the HP Constant is 45 to 180 Set the MP and RPM per your POH to 70 percent power Let conditions stabilize Change the HP reading on the EDM 900 to 70 percent by adjusting the HP constant in the lower display by holding or tapping the LF button Percent HP should be close to 100 percent during takeoff at sea level 5 Tap the STEP button to
31. estroy this high temperature wire Secure wires along the route to the indicator Secure wire using original clamps tape or tie wrap if possible Note The probe wires must not be tied in with ignition alternator or engine cabin heater ignition wires or transceiver coax cables because of potential induced interference with readings The temperature probe wiring harness is made of Chromel Alumel alloy wires that must not be substituted or extended with copper wire Temperature probe leads must be spliced with the same type of wire typically Chromel Alumel for JPI temp probes using copper butt splices The other signal and power wires are made from normal copper and must meet MIL W 32759 16 or equivalent CAUTION Be sure the installation does not result in interference with any aircraft control movements When the installation is complete all wires should be secured using ties and carefully checked for interference rubbing or chafing with flight controls and associated cables or any other moving parts 10 Pressurized Aircraft wire Routing Pressurized Aircraft have a factory installed pressure bulkhead pass thru boot or connector at the pressure vessel or firewall where all electrical wires from the engine pass through to the cockpit If you can not find the opening follow the wires from the engine to the pressure vessel If a boot with sealant is used remove the sealant pass the signal wires from the transducers mounted in the engine compart
32. flange as space permits Do not mount probes in slip joints Be certain to locate all holes BEFORE drilling to ensure that nothing interferes with the probe clamp screw or wire Careful matching of probe position will provide best temperature readings Insert the probe in the exhaust or previously drilled hole so that the tip of the probe is in the center of the exhaust stream Tighten the stainless steel clamp to a torque of 45 in Lbs Cut off the excess strap close to the screw Clamp Seal Washer MU Thimble note orientation of slot Probe m eue ERR 13 1 RADIAL Engine EGT Position probe in approximate center of exhaust Radial engine exhaust require a larger EGT clamp supplied to fit the 2 5 inch exhaust pipe The EGT probe is installed in the same fashion as a Lycoming or Continental engine and should be placed between the exhaust pipe flange and the accumulator at a distance of 2 to 3 inches from the engine exhaust flange Refer to the engine manufactures recommended location Do not route the EGT CHT harness in with the ignition harness Do not extend the yellow thermocouple leads with copper wire 13 2 Turbine Inlet Temperature TIT Probe Installation optional Use the J1 connector harness 790200 and insert the yellow wire into the connector pin 16 and the red wire into pin 17 The standard TIT probe PN M111 T with a 48 clamp is placed in the exhaust stack accumulator to a maximum depth of 1 2 inch and a
33. ft was refueled Select Yes to display total fuel used for an extended trip with multiple fuel stops This selection affects only the USD measurement During normal operation to reset the accumulated fuel used display at any time tap STEP until you see USD Hold both STEP and LF until the display shows 0 USD FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 39 of 50 Rev J Primary Engine Data Management System Date 5 24 2014 40 Trouble Shooting Diagnostic Testing on Startup and During Flight When your EDM 1s first turned on it tests internal components calibration and integrity of the probes During flight probes are constantly checked for inconsistent or intermittent signals Probem Situation Correction A MISSING COLUMN IN THE diagnostic routine has found an open line Replace the EGT or CHT probe shown A MISSING COLUMN IN THE areading that is jumping around or Replace the EGT or CHT probe shown incorrect in the error message on the next flight The probe is removed from the line up BEREZ On mimos maa ee DISPLAY FREEZES OR MAY processors to malfunction BE INCORRECT Failure to pre lean before performing Continue to lean without stopping LEANFIND FINDS A PEAK LeanFind or stopping while leaning Lean more rapidly TOO SOON Leaning too slowly PEAK NOT FOUND DURING Lean Find not activated or stopping while Lean at the speed of approximately LEANFIN
34. hat has a captive 3 8 24 boss that is screwed into the head of each cylinder 15 Radial Engine CHT spark plug gasket Cylinder head temperatures are measured with a spark plug gasket type probe placed under the front sparkplugs Front spark plugs will read 15 to 20 degrees cooler than the rear plugs The spark plug gasket probe P N M 113 replaces the standard copper spark plug gasket on one spark plug The probe is usually placed on the plug that receives the most direct cooling air After many removals the probe may be annealed for re use Heat to 1100 F and quench in water 16 Outside Air Temperature OAT Probe Installation Use the J1 connector harness 790200 labeled OAT All wiring must be type K thermocouple wire Do not splice ordinary copper wire in any temperature probe circuits Install the OAT probe PN 400510 in the airframe manufacturer s recommended location If this information is not available place the OAT probe in clean airflow such as in a cabin air scoop or below the underside of the wing away from engine heat or exhaust In this case it is recommended that the installation be done similar to the antenna installation instructions of AC 43 13 2b Acceptable Methods Techniques and Practices aircraft sheet metal doces shield tube used to secure p d probe washer ae b washer probe The outside aluminum shield tube is used to both hold the probe in place and shield it from radiated heat from the sun
35. hroat No drilling or machining of the carburetor is necessary 17 Oil Temperature Probe Installation The sensor port is a standard 5 8 18 thread for both the Continental and Lycoming engines Probe PN 400509 is a complete assembly using type K thermocouple wire red yellow Connect the wire marked oil temperature observing polarity to pin 1 and 2 on 790200 Wire length has no effect on the readings Oil temperature will be displayed as an independent temperature digital and bar graph Check with engine manufactures proper location for oil temperature Check for oil leaks before first flight 5 8 18 Thd 18 Oil Pressure Sensor Installation Use the J3 connector harness 790422 labeled OIL P for a pressure sensor three wire i2s sensor 0 5vdc P 2 GRN FP Sig 7 16 UNJF P 3 RED FP PWR 5 4 fitting MS 24587 FITTING P 1 BLK FP GND y y p LL pem tb m ic pz Oil pressure DO NOT MOUNT SENSOR DIRECTLY TO ENGINE PN 159936A 0 150 PSIG Oil pressure sensor mount using an aluminum clamp MS21919 Mount to firewall Mount the pressure sensor to the pressure line using a flexible hose and fittings not supplied as depicted in the drawing below Use aluminum clamp to mount the pressure sensor to firewall Do not mount the sensor directly to the engine Connect the other end of the hose to the engine manufacturer s recommended location for engine oil pressure FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM
36. ibration no other equipment is needed To implement the EDM fuel tank gauge functionality the EDM is connected directly to the senders or in some cases to the aircraft s fuel sender signal conditioner for example the Pennycap system typically found in Cessna The EDM has the capability to process signals from three types of sender signals Resistive output Voltage output or Frequency output JPI provides the appropriate interface hardware the P5 harness and any associated signal conditioners based on information you provided when your order was placed Once installation is completed you will perform a fuel level calibration The EDM stores this calibration internally NOTE The fuel quantity function will not be available until this calibration has been performed successfully 22 1 Capacitive Sender Frequency Output Type Sender System Although frequency output type senders are uncommon in certified aircraft JPI supports this interface The P5 harness has two 3 conductor cables labeled LEFT TNK and RT TANK that are connected directly to the left and right senders See the drawing below for basic connection information only right tank shown for illustration purposes Final route the LEFT TNK and RT TANK cables as necessary then crimp the female contacts onto each cables GRN BLK RED wires then insert them into the connector housing Connect this to the sender s cable connector Connect the white wire of the pod cable to the center insulated term
37. inal on the sender and the black wire to the terminal mounted on the metal body on the sender See illustration on following page 222 Hesistive Output Type Sender System Float type most common Locate the wires that run between the existing ships fuel gauges and the senders and disconnect them For tanks that have more than one sender the wiring between the senders must be retained Make sure the senders do not have voltage on them before connecting to the EDM Connect the EDM to the senders using the wire pairs coming from the signal conditioner as shown below Note that one pair is for MAIN and the other is for AUX Connect the SIG wire to the senders signal terminal typically the center stud and the GND wire to the closest ground terminal near or on that sender See illustration on following page Report No 908 Page 21 of 50 Rev J Date 5 24 14 ft with resistive output senders ircra Primary Engine Data Management System Example harness arrangement for ana FAA Approved Installation Manual for the EDM 900 and EDM 930 b aw sane 3NI9N3 319NIS SS3NHYH SZ Sd Wwuovid 9NINVIM 3 Sd Vv d 1ana ALO 13n3 0 6 006 918067 v ON ama fazis ddy VINBOZI YO vS3 4 Y15093 Sueunysy gif ab SL NMC LT SS3NuvH e2 Gd ezeose t 3AuSSx X8 0vi931M TWNOIS 2304 zoaass E ONO 1333 OZ FVD HNWL TAM 4d ae M3QNSS LY OND 3NION3 JIONIS xNv IR
38. int Whenever limit alarms are not triggered the RAD continuously displays MAP and RPM On initial startup or whenever power is turned on the words EDM 930 PRIMARY are displayed followed by the make and model of the aircraft with STC information for which the primary limits were set Alarm hierarchy for the EDM 900 930 When a measurement limit is reached the pilot should momentarily depress the STEP button on the EDM 900 930 instrument to extinguish the particular flashing alarm acronyms If another function has also reached its limit that label will then begin to flash The pilot should continue to monitor the affected parameters as he would if a conventional analog display had reached a limit The bar graph functions of CHT EGT and TIT remain displayed for easy reference should one of these limits be reached Alarm hierarchy is shown in the table below 1 OILP LO 6 FLVL 11 CLD 16 AMPS 2 FP LO 7 REM 12 RPM 17 CDT 3 OILT HI 8 FP HI 13 OILT LO 18 RES 4 CHT 9 MAP 14 VOLTS 19 ECT 5 TIT 10 DIF 15 OILP HI 20 Fuel Flow 62 Dimming Automatic dimming is provided to dim both the panel display and the remote alarm display Dimming can also be accomplished manually to change the Automatic setting Button 8 initiates the manual Dim function and shows which button to press for Dim or Bright changes The display starts up in the max brightness mode FAA Approved Installation Manual for the Report No 908 ED
39. ket Magneto body Sensor must be over moving magnet armature Remove this screw to mount sensor bracket engine Slick 600 series JPI PN 420806 non pressurized rev Dec 2010 FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 30 of 50 Rev J Primary Engine Data Management System Date 5 24 2014 27 EDM 900 930 Specifications and Limitations The following parameters must be customized for the aircraft into which the EDM 900 930 is installed Factory set limits or default values for EDM 900 930 1 TIT 1650 F TSO C43 2 CHT 450F TSO C43 3 Oil Temp Low 90 F TSO C43 4 Oil Temp HI 230F TSO C43 5 Oil Press low 15 psi TSO 47 6 Oil Press Hi 100 psi TSO 47 7 Vacuum 0 15 hg TSO 47 8 RPM 2700 Limit and range TSO C49 9 RPM setto cyl 6 TSO C49 10 Map 32 In hg HI TSO C45 11 Map setting 29 90 In Hg TSO C45 12 Fuel Pressure Hi 35 psi Injected TSO 47 13 Fuel Pressure Lo 15 psi Injected TSO 47 14 Fuel Pressure Hi 8 psi Carb TSO 47 15 Fuel Pressure Lo 5 psi Carb TSO 47 16 Fuel Flow 24 GPH TSO C44 17 K factor 29 99 18 Carburetor filter smoothing 1 19 Ammeter configuration load or charge discharge Load NON TSO 20 HC 120 of HP NON TSO 21 Fuel Level Resistive Capacitive TSO 55 22 Low fuel 10 Gal 23 Low time 45 Min 24 Main tank 75 gallons 25 Aux tank 0 26 GPS set at GARMIN 27 Diff 500 degrees TSO C43 28 CLD 60 degrees per minute TSO C43 29 Amps limit 100 amps
40. ment to the display unit Upon accomplishing this reseal the opening with factory recommended sealant An alternate method for a cannon connector is to use existing wires in the aircraft going thru the pressure bulkhead The EDM 900 930 replaces the RPM MAP CHT Oil Temperature Oil Pressure Fuel Pressure Fuel Flow and TIT gauges which have wires going thru the pressure bulkhead Making a new hole in the pressure bulkhead is beyond the scope of this document and will require a DER or other FAA approval FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 12 of 50 Rev J Primary Engine Data Management System Date 5 24 14 11 Power Connection The EDM automatically adapts to either a 14 or 28 volt electrical system Master Bus power wire to the EDM should be 20ga copper connected directly to the master solenoid located at the battery to avoid a line drop when cranking A 5 amp circuit breaker is required Connect the EDM ground wire to the engine block The instrument is designed to reset at less than 10vdc bus power therefore the instrument may reset on engine start typical for 14vdc systems For lighting no connection to the aircraft dimmer system is required because the instrument dims automatically with reductions in ambient light Required power for 900 or 930 is 1 0 amp at 14vdc 12 Probe Wiring When cutting the pair of leads to the proper length to connect to the probes leave enough slack in the wiring so th
41. minations 12 1 Wiring Markings The EDM 900 930 is supplied with special Teflon insulated Chromel Alumel factory assembled wiring harness configured for the correct number of cylinders The wire harness is marked E12 EGT 1 C12 CHT 1 etc NOTE Unlike most other EGT amp CHT installations the probe wire length is not critical and should be trimmed to any length as required for a clean installation Do not extend the thermocouple wire with copper wire FAA Approved Installation Manual for the EDM 900 and EDM 930 Primary Engine Data Management System 13 Exhaust Gas Temperature Probe EGT Installation Report No 908 Page 13 of 50 Rev J Date 5 24 14 Use the J2 connector harness 700700 or 700702 labeled E1 through E4 or E6 Remove the existing EGT gauge and Probe Replace with JPI probe M 111 in all exhaust stacks EGT probe Drill no 40 pilot hole then no 30 hole CHT probe 2 to 4 The Model M 111 Probe will fit any engines where the existing holes in the exhaust stack are 1 8 to 1 4 in diameter If no hole exists it will require the drilling of a 1 8 diameter hole and ream to fit It is important that each probe be mounted the same distance from its exhaust stack flange A nominal distance of 2 to 4 inches from the exhaust flange is recommended If the recommended distance is impractical because of obstructions slip joints or bends in the exhaust system then position the probes a uniform distance from the
42. ng with CD Coll bias L Message area ean USB Port gauges digital only Air F or C Primary Area Strip instruments Step Enter Button Lean Find utton USB port for Down up Load i Manual Dimming Message Area select switch Non Primary instrument area Auto Dimming CD cell Turbin Inlet Temp Message Area All functions show up here by tapping step Primary gauges only L v DlL T 163 F x DRL P 44 Fa M i FLF 90 Pai LFU 23 GAL v ATTE V GAL fuel level Select button ALL TEMP FUEL EDM 900 system mounts in a 3 125 inch diameter instrument panel hole in either a portrait or landscape position depending on panel hole location By holding the Step button first on left for approx 10 seconds and arrow will appear on the display showing which way the rotation will use as up Use the LF Second from left button to index the rotation arrow When the proper position is achieved tap the step button Tap STEP to save the new rotation At this point properly the rotation will be saved and the unit will reboot to the new rotation The rotation will not occur if the engine is running FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 8 of 50 Rev J Primary Engine Data Management System Date 5 24 14 7 Locating and Installing the Indicator and Remote Alarm Display RAD and Alert Light Single Engine Aircraft EDM 900 930 A The EDM 900 930 display should be
43. of 50 Rev J Primary Engine Data Management System Date 5 24 2014 38 Adjusting the K Factor This procedure is different than for setting other parameters 1 If you haven t already done so start the Pilot Program Mode by clearing all alarms by tapping step repeatedly then simultaneously hold the STEP and LF buttons for about five seconds until you see the word PROGRAM followed by FUEL N Tap STEP repeatedly until you see K FACTOR 29 90 this value may be different on your unit C9 Hold both the STEP and LF buttons simultaneously until a digit begins flashing This indicates editing has been enabled Tap or hold the LF button to change the flashing digit to the desired value Tap or hold the STEP button to select the next digit to edit Hepeat steps 4 and 5 until the displayed value is set to your desired value one OM um To save new value hold STEP and LF buttons simultaneously for about five seconds until the K factor parameter exits 8 Tap STEP repeatedly until you see END Y then Tap STEP once more to exit the Pilot Program Mode 39 Programming Accumulate Trip Total Accumulate default is OFF resets the fuel used to 0 every time you inform the EDM 900 that the aircraft was refueled With accumulate ON fuel used will not be reset to 0 when you inform the EDM 900 that the aircraft was refueled Select No if you wish to display total fuel used since the last time you informed the EDM 900 that the aircra
44. ogram Mode After Factory is displayed in the scanner message area tap the NEXT button until FUEL PRESSURE z is displayed in the scanner message area Hold the STEP and LF buttons until the word ADJUST appears in the message area Tap the PLUS or MINUS buttons to change the selected Fuel Pressure sensor type To save the selected value hold the STEP and LF buttons until the word SET appears in the message area Tap the STEP button repeatedly until the message END is displayed in the message area Tap the button labeled YES to save changes and restart the EDM P ONDU FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 36 of 50 Rev J Primary Engine Data Management System Date 5 24 2014 35 Customizing Non Primary Data EDM900 only You can customize change or re order non primary data channels in the non primary portion of the EDM display non primary values are displayed as text gauges without redline values See Pilot s Guide for more information Non primary data channels are numbered from 1 up to 6 depending on your particular aircraft configuration and EDM installation To customize the LCD layout of non primary data follow these steps 1 Enter Pilot Program Mode by holding the STEP and LF buttons for 5 seconds 2 When the EDM enters Program Mode tap the button labeled NEXT until END Is displayed in the scanner message area 3 Again hold the STEP and LF buttons until the EDM enters Fa
45. or the Report No 908 EDM 900 PN 790000 A EDM 930 PN 790000 C Page 50 of 50 Rev J Primary Engine Data Management System Date 5 24 2014 46 Appendix B ICA Refer to Supplement No 905 01 Revision E or later Check the web page jpinstruments com for the latest revision to the ICA
46. ot Programming To start the Pilot Program procedure simultaneously hold the STEP and LF buttons for five seconds You will see the word PROGRAM for two seconds and then the sequence shown in the chart below Tap the STEP button to advance to the next item in the list Hold the STEP button to step back to the previous item Tap the LF button to select alternate values of that item Simultaneously hold both STEP and LF to exit STEP LF sequences advances next through these item values Comments Hoc Stars on foro seconds Tap LF to change fuel status Exits program mode when done E CC OE EM Index rate pause time in seconds in the Automatic Mode 0 disables the Automatic Mode OAT F To calibrate the OAT 10 hold both the STEP and LF buttons simultaneously for five seconds which will proceed to the next step Otherwise the next step will be skipped OAT IO This step will be normally be skipped OATFLO Adjust the indicated temperature up or down by up to 10 For example OAT 3 adjust the OAT 3 higher Y Yes sets the digital display to one degree resolution N No sets 10 10 resolution is easier to interpret the EGT s HP display will change when HP constant is adjusted Hold STEP and LF for 5 seconds until you see ADJUST to set the HP calibration Tap STEP to continue to the next step To adjust the MAP hold both the STEP and LF buttons simultaneously for five seconds which will proceed to the next step Oth
47. ot retroactively recalculated FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 37 of 50 Rev J Primary Engine Data Management System Date 5 24 2014 37 Fine tuning the K Factor The K factor shown on the fuel flow transducer does not take into account your aircraft s particular installation Fuel hose diameters and lengths elbows fittings and routing can cause the true K factor to be different from that shown on the fuel flow transducer You must use the following procedure to fine tune the K factor 1 Make at least three flights of about two to three hours each Note the actual fuel used as determined by topping the tanks and the EDM 900 calculation of the fuel used for each flight USD Fuel USED shown by EDM Flight total tank REM Actual fuel used by topping tanks l Bd E Total 9 3 0 J9 A M 2 Total the EDM 900 calculated fuel used and the actual fuel used 3 Record the current K factor here and in the table below 4 Calculate the New K factor as follows New K factor OEDM fuel used x OCurrent K factor Oactual fuel used New K factor 0 x 98 0 Every time you fine tune the K factor change it by only half of the amount calculated above and record the measurements here OEDM Oactual OCurrent New K factor Pilot s Date fuel used fuel used K factor 0xO0 O initials FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 38
48. outing the Wiring Harnesses Five connectors are protruding from the rear of the instrument Connect the five wiring harnesses to the rear of the instrument and run the cables through the firewall into the engine compartment Allow sufficient service loop to facilitate removal of the connectors for servicing These wiring harnesses are labeled as follows P1 790200 Power Engine ground MFD input MFD output the following are optional and need to be added Oil temperature Induction temperature Carburetor temperature Outside air temperature Turbine inlet temperature Turbine inlet temperature 2 P2 700700 CHT EGT 6 cylinder 700702 CHT EGT 4 cylinder 790422 RPM MAP Oil pressure e 700708 Serial data to GPS Serial data from GPS Fuel flow transducer 790723 Fuel Pressure Fuel Level Resistive and Capacitive Amps a 790749 Category 5 jack and cable for RAD Remote Alarm Display Route the wires from the connectors through the firewall using rubber grommets and flame retarding silicone Use an existing hole if possible All wires must be routed away from high temperature areas exhaust stacks turbochargers etc Secure probe and sensor leads to a convenient location on the engine approximately 8 to 12 inches from the probe or sensor being sure there is sufficient slack to absorb engine torque It is essential in routing the probe wire that this wire not be allowed to touch metal parts of the air frame or engine since abrasion will d
49. ow provides real time readings of all active fuel level sensors Verify readings look normal Reading are arbitrary whole numbers 3 Now add fuel as needed to match the required volume for a particular point Cycle power between readings hold in button 4 then take a reading and record it on paper adjacent to that point 4 Repeat this process until all points 2 to 5 have been recorded for each tank With AUX it would say LMAIN and LAUX Fuel Level Readings LMAIN 3026 08 55 32 Actual Screen Shot FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 24 of 50 Rev J Primary Engine Data Management System Date 5 24 14 22 4 1 After you have collected your data After you have collected your data Entering Editing Fuel Level Calibration Data The Fuel Table Editor is a spreadsheet type format allowing you to easily see the volume and related calibration values side by side You can easily navigate through the cells to enter values 1 With power off hold in Button 3 Button 1 being far left and then turn on power Wait until you see Do you agree with the disclaimer Tap YES if you agree and wish to continue Fuel Table Data By continuing into the Fuel Table Editor you acknowledge that you have read and understand the Fuel Table Data Editor instructions that came with your J P Instruments EDM_930 It is your responsibility to validate the correctness of fuel levels represented by the system
50. pproximately 4 inches from the turbine inlet if possible on the waste gate side of the turbine FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 14 of 50 Rev J Primary Engine Data Management System Date 5 24 14 13 3 TIT for second Turbine Inlet Temperature Use the J1 connector harness 790200 and insert the yellow wire into the connector pin 18 and the red wire into pin 19 The standard JPI TIT probe P N M 111 T with a special clamp is placed in the exhaust stack accumulator to a maximum depth of 1 2 inch and approximately four inches from the Turbine inlet if possible on the waste gate side of the turbine 13 4 Using the Factory original TIT Probe The factory installed TIT probe K calibration is compatible with the JPI EDM 900 930 System Connect the JPI wire marked TIT in parallel with the factory probe noting color polarity Replacement probes should be purchased per part number from the aircraft manufacturer If you choose to use only the EDM 900 930 TIT display you may remove the factory installed TIT indicator and leave the TIT probe installed Connect the JPI wire marked TIT directly to the probe noting color polarity The TIT probe should now have only the JPI leads attached to it No calibration of the EDM 900 930 is necessary 14 Cylinder Head Temperature CHT Probe Installation Use the J2 connector harness 700700 or 700702 labeled C1 through C4 or C6 The JPI probe is a bayonet probe P N 5050 T t
51. pressure through the transducer or use Teflon tape pipe cement damage will occur Use only steel fittings supplied never use aluminum fittings on transducer Remove the transducer cap plugs only when ready to install the hoses Note the direction of fuel flow marked on the transducer Fuel must flow in this direction Reverse flow installations will read 1 2 the required flow Mount the transducer with the three wires pointing up The K factor is printed on the side of the transducer and on a tag Write down the K factor here for future reference Aeroquip EP 900591B Clamp Cut slit in fire sleeve Fittings 1 4 NPT Do NOT E aa MS 21919 use aluminum fittings Clamp as required N Aeroquip 303 hose to carburetor flow divider or fuel injector from fuel tank Aeroquip Fire Sleeve throttle body Or AE102 62 24 engine driven fuel pump The EDM 900 930 fuel flow transducer receives signal from any installed 201 or 231 transducer with either of these part numbers embossed on to the top of the transducer For specific engine Installations see Appendix A Report 503 6 inches maximum from support FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 20 of 50 Rev J Primary Engine Data Management System Date 5 24 14 22 Fuel Level Sender Wiring Types The EDM has the capability to interface to the aircraft s fuel level system It is also used to directly read the fuel senders for fuel cal
52. proceed to the next step 33 Programming the MAP Sets the manifold pressure calibration You may need to correct the MAP based on the altimeter setting at a sea level airport 1 Enter the pilot program mode by simultaneously holding the Step and LF buttons for five seconds 2 Tap Step OK repeatedly until you see for example MAP adjustment 0 0 3 Then hold both the first two buttons until you see ADJUST followed by MAP 0 The adjustment range for the MAP is 2 0 in Hg As you adjust the MAP up or down you will see a change in the MAP gage under RPM When you see the correct setting stop 4 Tapthe Step OK button to proceed to the next step or hold both buttons again to exit setup Do this one time and only if the MAP on your manifold pressure gauge doesn t match the MAP shown on the EDM 960 You must do this on the ground with the engine turned off 34 Selecting Fuel Pressure Type EDM 900 only To properly display Fuel Pressure values the EDM must be told what type of Fuel Pressure sensor is connected to the EDM This is normally set at the factory for new installations To set or modify the type of Fuel Pressure sensor connected to the EDM follow these steps 1 Enter Pilot Program Mode by holding the STEP and LF buttons for 5 seconds 2 When the EDM enters Program Mode tap the button labeled NEXT until END Is displayed in the scanner message area 3 Again hold the STEP and LF buttons until the EDM enters Factory Pr
53. proved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 9 of 50 Rev J Primary Engine Data Management System Date 5 24 14 TIGHTEN HEX 7 A O zZ U gt Pas Z m den 6 32 4PLC 3 5 BC Mounting bracket for the EDM 900 EDM 900 Model Mounts in a standard 3 1 8 instrument hole First place the mounting bracket on the instrument and tighten the clamp hex screw until you can just remove the instrument from the bracket The Mounting bracket is then placed behind the instrument panel hole and screwed 6 32 x 7 screws in place using the existing holes Three screws should be used leaving one hole vacant on either side of the hex screw Locate the hex screw in a location that you can easily get to from the rear of the panel The body of the instrument is 3 0 inches in diameter and 2 0 inches deep less connectors FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 10 of 50 Rev J Primary Engine Data Management System Date 5 24 14 5 EDM Display Installation Choose the Proper Installation Location The display is best located within the natural scan and easy reach of the pilot The recommended mounting location is defined as the distance from the vertical centerline of the Primary Flight Instruments to the outer edge of the further most gauge displayed on the EDM F i n LY hs d r i F r k ii 2 A p j E ANE i of P 4 i EF L a af i3 a 2
54. readings when complete fuel quantity readings presented by the EDH should not be used for flight USER FACTRY 4 Tap POINTS when you see Do you want to edit the table Fuel Table Data By continuing into the Fuel Table Editor you acknowledge that you have read and understand the Fuel Table Data Editor instructions that came with your J P Instrumentz EDA 930 It is qour responsibility to validate the correcthess of Poel bevels represented by the sapien TP ipa fail to validate the fuel q uantitiy readings when complete fuel quantity readings presented hy the EDA should mot be used for flight TABLE POINTS 5 You see Points in LEFT the current calibration points for the LEFT tank Fuel Table Data By continuing into the Fuel Table Editor you acknowtedge that you have read and understand the Fuel Table Data Editor instructions that came with your J P Instruments EDM 939 It is your responsibilitu to validate the correctuess of fuel leuels represented by the system If you fail to validate the fuel quantity readings when complete fuel quantity readings presented by the EDM should not be used for flight TABLE VALUE TANK BACK 00 34 07 EDM960 DEMO N123JPI 6 Tap hold VALUE to change to the desired number of calibration points for this tank 2 to 5 Each Tank can have a different set of calibration points So 5 points for Main and 2 points for Aux FAA Approved Installation Manual for the Report No
55. ry with field elevation Use the chart below to calculate the MP FACTOR Multiply this MP FACTOR by the altimeter setting that you receive from ATIS or Unicom For example if the field elevation is 1700 ft and the altimeter setting is 30 1 the MP FACTOR is 0 9400 from the table Multiply 30 1 x 0 9400 to get the ambient MP of 28 29 Field MP 1200 0 9574 3100 0 8929 5000 0 8320 Elev FACTOR 1300 0 9539 3200 0 8896 5100 0 8289 500 1 0182 1400 0 4 3300 0 8863 5200 0 8258 A00 1 0145 1500 0 9469 3400 0 8830 5300 0 8227 300 1 0109 1600 0 9435 3500 0 8798 5400 0 8196 200 1 0073 1700 0 9400 3600 0 8765 5500 0 8165 100 1 0036 1800 0 9366 3700 0 8733 5600 0 8135 0 1 0000 1900 0 9332 3800 0 8700 5700 0 8104 100 0 9964 2000 0 9298 3900 0 8668 5800 0 8074 200 0 9928 2100 0 9264 4000 0 8636 5900 0 8043 300 0 0892 2200 0 9230 4100 0 8604 6000 0 8013 A00 0 9856 2300 0 9196 4200 0 8572 6100 0 7983 500 0 9821 2400 0 9162 4300 0 8540 6200 0 7953 600 0 9785 2500 0 9129 4400 0 8508 6300 0 7923 700 0 9750 2600 0 9095 4500 0 8477 6400 0 7893 800 0 9714 27700 0 9062 4600 0 8445 6500 0 7863 900 0 9679 2800 0 9028 4700 0 8414 6600 0 7833 1000 0 9644 2900 0 8995 4800 0 8382 6700 0 7804 1100 0 9609 3000 0 8962 4900 0 8351 26 RPM Sensor installation Use the J3 connector harness 790422 and connect the 3 leads using the supplied 3 pin connector and pins There are four types of magnetos commonly in use You must have the correct RPM sensor for the magneto installed in
56. t for EGT KIT 1280 TIT KIT 1200 Probe 1 Thermocouple type K probe PN M 111 1 Stainless Steel Clamp Thimble 1 Stainless Steel Exhaust Seal Washer 1 Stainless Steel Screw Type Clamp 2 Ring Terminals 2 Screws and nuts 6 32 X 1 4 1 Fiberglass tube 3 8 x 5 29 2 Component Parts list for CHT KIT 1260 1 Bayonet Probe Thermocouple type K Spring loaded PN 5050 T 2 Ring Terminals 2 Screws and Nuts 6 32 X 1 4 1 Fiberglass tube 3 8 x 5 29 3 Component Parts list for IAT KIT 1300 probe 1 Thermocouple type K probe PN M 111 1 Stainless Steel Clamp amp Thimble Stainless Steel Exhaust Seal Washer 29 4 Component Parts list for OAT KIT 1220 probe 1 P N 400510 OAT probe 2 Ring Terminals 2 Screws and Nuts 6 32 X1 4 Fiberglass tube 3 8 x 5 29 5 Component Parts list for CARB KIT 1190 probe 1 P N 400128 CARB probe FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 33 of 50 Rev J Primary Engine Data Management System Date 5 24 2014 2 Ring Terminals 2 Screws and Nuts 6 32 X1 4 1 Fiberglass tube 3 8 x 5 29 6 Component Parts list for OIL Temperature probe KIT 1250 1 P N 400509 OIL probe 1 AN900 10 crush washer 2 Ring Terminals 2 Screws and Nuts 6 32 X 1 4 1 Fiberglass tube 3 8 x 5 29 7 Component Parts list for Oil Pressure sensor KIT 1460 1 P N 1599364 Oil Pressure sensor 1 P N 159961 Clamp Loop Cushioned 1 P N 174402 Connector Pack 3 Pin and Terminals 29
57. t this point hold in button FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 27 of 50 Rev J Primary Engine Data Management System Date 5 24 14 1 and 2 again until the display 5 sec changes and you see FACTORY At this point you will see MAIN XX adjust with the Plus and Minus buttons Tap next for AUX XX and adjust Tap button twice to finish and save 24 GPS Interface Use the J4 connector harness 700708 labeled RS232 OUT TO GPS white and RS232 IN FROM GPS gray Refer to the Manufactures GPS manual for the required pin connections on the GPS 25 Manifold Pressure MAP Sensor Screw a AN816 4D flared to pipe thread into the Aeroquip 303 hose to and from the bulkhead fitting an 832 4 as shown below if not already installed from the aircraft factory MAP gauge P 2 GRN FP Sig 7 16 UNJF P 3 RED FP PWR 5 4 fitting MS 24587 FITTING P 1 BLK FP GND enas HD AEROQUIP 303 Flex hose E EL d Em Manifold Air pressure DO NOT MOUNT SENSOR DIRECTLY TO ENGINE FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 28 of 50 Rev J Primary Engine Data Management System Date 5 24 14 Manifold Pressure Calibration The manifold pressure must be calibrated to the ambient air pressure Enter the current ambient barometric pressure The engine must not be running This setting is not the same as the altimeter setting that you receive from ATIS or Unicom It will va
58. the EDM Probe amp Sensor Channels page On this page you will see values for Primary gauges in RED which are not available for alteration The values in WHITE can be selected or deselected to be displayed on the EDM An X in the box selects the gauge to be displayed Tap STEP several times to select FUEL PRESS or desired gauge input channel Tap ENABLE key to enable the input Tap SAVE then YES to save change to channels Tap STEP key repeatedly until prompted to exit configuration EDM will restart with FP or desired gauge enabled 20 Ammeter Shunt Installation Use the J5 connector harness 790723 labeled AMP and AMP Connect the harness leads using ring terminals to the smaller terminal screws on the side of the shunt 20 1 Charge Discharge configuration The shunt can be installed between the master contactor and the main bus in which case it will be in the ammeter configuration showing battery charge and discharge Be sure that the positive side of the shunt is connected to the main bus in the ammeter configuration The alarm will be triggered by a discharge condition FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 18 of 50 Rev J Primary Engine Data Management System Date 5 24 14 Master switch contactor Alternator BATT Master switch pl Starter Starter solenoid external shunt Ammeter Configuration WV Master switch contactor Alternator BATT
59. the aircraft The following part numbers apply Slick pressurized 4000 6000 series use JPI P N 420809 For the Bendix pressurized 1200 series use P N 420807 Dual magnetos use JPI PN 420808 For the Bendix 20 series and Slick 600 use JPI P N 420806 Mount the sensor as shown in the appropriate diagram below Note this is eligible for installation on all 4 amp 6 cylinder engines only FAA Approved Installation Manual for the EDM 900 and EDM 930 Primary Engine Data Management System Bendix Magnetos engine Connector to harness Bendix 20 21 200 1200 series non pressurized JPI 420815 2 Mount sensor side of bracket towards magneto body positioned over the magne armature gt 4 position limit engine position limit Connector to harness Alternate bracket locations Bendix 1200 series pressurized JPI 420807 Mount sensor side of bracket towards magneto body engine Bendix Dual Magneto JPI PN 420808 non pressurized Report No 908 Page 29 of 50 Rev J Date 5 24 2014 olick Magnetos engine Connector to harness Slick 6000 4000 series non pressurized JPI 420815 1 Mount sensor side of bracket towards magneto body Sensor ring munted under vent plug Stem at right angles to magneto center line engine Alternate bracket location Connector to harness Slick 6000 4000 series pressurized JPI 420809 Vent plug 457 spacer ring Sensor ring brac
60. ther red to red yellow to yellow e The instrument must be grounded at the engine not at the avionics ground e Record the installation of the EDM 900 or EDM 930 on a FAA form 337 Make an entry in the aircraft logbook e Note Removal of probes sensors and the instrument is the reverse of the installation procedure FAA Approved Installation Manual for the Report No 908 EDM 900 and EDM 930 Page 3 of 50 Rev J Primary Engine Data Management System Date 5 24 14 3 Instrument Labeling The TSO label on the instrument is marked as to the instrument configuration The part number of the instrument is as follows Model designation system by part number for EDM 900 930 EDM 900 PN 790000 A XXX TFT liquid crystal Type Display EDM 930 PN 790000 C XXX TFT liquid crystal Type Display INSTRUMENTS THAT CAN BE PRIMARY IF IN POH NON PRIMARY INSTRUMENTS 4 9 FLOW Alert Light 4 9 empty Fule USED TEMP PRESS CARB to WP Quantity Example PN 790000 X XXX X denotes EDM 900 or EDM 930 XXX denotes Part Number for a specific aircraft with or without and engine STC Each PN is specific to a Make and Model Aircraft with or without STC In which the information is gathered from the Aircraft POH or STC Data sheet w engine STC No if Limits found in the POH or engine STC RAD at Start up or 900 applicable for a specific aircraft message area i Cessna 182 P STC12345NW 790000 X 875 i Aircraft type JPI assigned Data Base Part No per P

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