J.P. INSTRUMENTS EDM-350 Installation Guide

Approved Installation Manual for the Experimental Report No 350
EDM-350 Page 1 of 41 Rev IR
Engine Data Management System Date 12-06-17

TABLE OF CONTENTS

Section Page

1. Revisions ______________________________________________________________________________________ 2

2. Read This First _________________________________________________________________________________ 2

3. Remote Alarm Light EDM 350 _____________________________________________________________________ 4

4. Locating and Installing the Indicator Display (Alert Light) _______________________________________________ 7

5. Routing the Wiring Harnesses ______________________________________________________________________ 8

6. Pressurized Aircraft wire Routing ___________________________________________________________________ 8

7. Power Connection _______________________________________________________________________________ 9

8. Probe Wiring ___________________________________________________________________________________ 9

9. Exhaust Gas Temperature Probe (EGT) Installation ___________________________________________________ 10

10. Cylinder Head Temperature (CHT) Probe Installation__________________________________________________ 11

11. CHT (spark plug gasket) _________________________________________________________________________ 11

12. Outside Air Temperature (OAT) Probe Installation ____________________________________________________ 11

13. Oil Temperature Probe Installation ________________________________________________________________ 11

14. Oil Pressure Sensor Installation ___________________________________________________________________ 12

15. Fuel Pressure Sensor Installation using combination sensor _____________________________________________ 12

16. Ammeter Shunt Installation _______________________________________________________________________ 13

17. General Fuel Flow Transducer Installation __________________________________________________________ 14

18. Fuel Level Sender Wiring Types ___________________________________________________________________ 15

19. Fuel Flow Totalizer, Refuel Question _______________________________________________________________ 21

20. GPS Interface _________________________________________________________________________________ 21

21. Manifold Pressure (MAP) Sensor __________________________________________________________________ 21

22. RPM Sensor installation _________________________________________________________________________ 23

23. EDM-350 Specifications and Limitations ____________________________________________________________ 24

24. EMI Radio Test and functional check:_______________________________________________________________ 25

25. Component Parts _______________________________________________________________________________ 26

26. Weight and Balance Data ________________________________________________________________________ 28

27. Pilot Programming _____________________________________________________________________________ 28

28. Programming the HP Constant ____________________________________________________________________ 30

29. Programming the MAP __________________________________________________________________________ 30

30. Selecting Fuel Pressure Type _____________________________________________________________________ 31

31. Customizing Non-Primary Data (EDM350 only) ______________________________________________________ 31

32. K Factor______________________________________________________________________________________ 32

33. Fine tuning the K Factor _________________________________________________________________________ 32

34. Adjusting the K Factor___________________________________________________________________________ 32

35. Programming Accumulate Trip Total _______________________________________________________________ 33

36. Trouble Shooting _______________________________________________________________________________ 33

37. GPS Interface Diagnostics _______________________________________________________________________ 34

43. Connector Pin Assignments on EDM, J1 through J5 ___________________________________________________ 35

44. J3 RPM, MP, Oil-P_____________________________________________________________________________ 38

The Owner of the EDM-350 must keep this manual

J.P. INSTRUMENTS

PO BOX 7033

HUNTINGTON BEACH CA

Last printed 2/1/2018 5:06:00 PM

Approved Installation Manual for the Experimental Report No 350
EDM-350 Page 2 of 41 Rev IR
Engine Data Management System Date 12-06-17

1. Revisions

REV Description Date Approval

IR

Initial Release

12-06-2017 JFP

2. Read This First

 The following notes apply to a new installation. Read this section before proceeding.

 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.

 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.

 Do not use aluminum fittings or Teflon tape with the FXT-201 or FXT-231 fuel flow transducer.

 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.

 Determine the locations of all holes before drilling to ensure that nothing interferes with the probe, clamp, clamp

screw or wire.

 Provide service loops at the instrument so that it can be moved for maintenance or troubleshooting.

 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.

 Dress all wires away from high temperature components such as exhaust stacks.

 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.

 Observe correct polarity on all probe wires. Connect like colors together (red to red, yellow to yellow).

 The instrument must be grounded at the engine, not at the avionics ground.

 Make an entry in the aircraft logbook.

 Note: Removal of probes, sensors and the instrument is the reverse of the installation procedure.

Do not install an Experimental EDM-350 in a certified aircraft.

Approved Installation Manual for the Experimental Report No 350
EDM-350 Page 3 of 41 Rev IR
Engine Data Management System Date 12-06-17

If the EDM-350 is configured to monitor the aircrafts fuel tanks, the EDM-350 must be calibrated to the aircraft fuel
system and the EDM-350's accuracy must be verified before flying the aircraft.

Before allowing the aircraft to be flown, verify the instrument markings displayed on the EDM-350 screens are
accurate with the aircraft’s POH for every function displayed on the EDM-350.

The use of the EDM-350 requires recurring training for any pilot who will be flying the aircraft in which it is installed.
Recurring training should include reading the EDM-350 Installation Manual ,Pilots Guide and seeking a flight
instructor for proper interpretation of information being displayed to the pilot.

Fuel Level Accuracy Limitations:

1. Angle of Attack - The EDM-350 must be calibrated with the aircraft in a cruise angle of attack. If

the aircraft is in an angle of attack other than cruise, the EDM-350 may display inaccurate fuel levels
(depending on the mounting location and type of sensor used). If your aircraft does not sit at a cruise
angle of attack when on the ground, it may not display accurate fuel levels. Test your aircraft at
different angles of attack to see the effects on the EDM-350 fuel level readings.

2. Full Fuel Readings - As a tank is filled the fuel sensor may not be able to detect the fuel entering
the upper corners of the fuel tank. If this is the case with your sensor, the EDM-350 will display lower
fuel levels than the actual fuel in the tanks when the tanks are full. When the fuel level drops to a
point where the fuel sensor starts to detect a change, the displayed fuel level should be accurate.
Check the accuracy of your system by comparing the displayed fuel levels on the EDM-350
to the fuel levels listed in the flight manual at each fill up.

3. Low Fuel Readings - Do not rely on the EDM-350 to determine the fuel level in the tank
for an indicated tank level below 1/8. You should always fly the aircraft in such a manner as to
maintain at least the FAA minimum fuel requirements in the aircraft at all times.

4. Improper Calibration - If the EDM-350 has not been properly calibrated it will not display accurate
fuel levels in the tanks. It is important you verify the accuracy of the EDM-350. Always crosscheck
your measured fuel levels in the tanks with the readings on the EDM-350 before each flight.

5. Poor Connections - Poor connections between the wires leading from the EDM to the fuel
sensors can become intermittent. An intermittent connection most likely will show up as wandering or
inaccurate readings on the EDM-350. Always crosscheck your measured fuel levels in the tanks
with the readings on the EDM-350 before each flight.

6. Defective Fuel Level Sensors - Fuel sensors can become intermittent or change resistance
with age. It is not uncommon to find intermittent problems even in new sensors. An intermittent
problem with a fuel sensor most likely will show up as wandering or inaccurate readings on the EDM-350.
Always crosscheck the measured fuel levels in the tanks with the readings on the EDM-350 at
each fill up. If you ever find an inaccuracy issue or any other problem with a fuel level display on
the EDM-350, troubleshoot and fix the problem before the next flight.

DETERMINE THE FUEL LEVELS IN THE AIRCRAFT.

1.The use of the EDM-350 does not eliminate or reduce the necessity for the pilot to use good flight planning,

preflight and in-flight techniques for managing fuel. It is important the pilot adopt the practices listed below. If you are
not familiar with these techniques, contact the FAA to acquire proper training.

2. Flight Planning - Always calculate the fuel requirement for each leg of a flight, including any
alternate plans for bad weather. Keep this information available in the aircraft during the
flight. Keep a chart of the published fuel flows for various flight/engine conditions in the
aircraft. Keep a chart of the measured fuel flows for various flights in the aircraft. Measured
fuel flows can be considerably different from published figures. This usually is due to old,
inaccurate engine instruments.

Approved Installation Manual for the Experimental Report No 350
EDM-350 Page 4 of 41 Rev IR
Engine Data Management System Date 12-06-17

3. Preflight - Do not rely on the EDM-350 to determine the fuel level in the fuel tanks. The
pilot must visually check/measure the fuel levels in the tanks before every takeoff.
Crosscheck the measured fuel levels with the displayed levels on the EDM-350. Also, crosscheck
these levels with the fuel requirements for the flight listed in your flight plan.

4. In Flight - Make the EDM-350 part of your normal instrument scan. Crosscheck the fuel levels
displayed on the EDM-350 with your flight plan at each leg of the flight or every 30 minutes
(whichever happens first). If there is a discrepancy, land the aircraft at the nearest airport and
verify the fuel levels. Discrepancies should be taken seriously.

5. New Pilot or Owner of the Aircraft - If there is a new pilot or owner of the aircraft, it is
the previous aircraft pilot/owner’s responsibility to insure the new pilot has read this
manual and is aware of any accuracy limitations and other important considerations.
All limitations and operating characteristics learned from operating the EDM-350 must be
passed on to the new pilot/owner.

3. Remote Alarm Light EDM 350

The remote alarm light is a Red or Yellow light depending on the alarm condition. The EDM-350 incorporates a
single light that alerts the pilot that a problem existing within the engine. 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”.

Alarm hierarchy for the EDM-350

When a measurement limit is reached, the pilot should momentarily depress the STEP button on the EDM-350
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.

2. FP_LO.

3. OILT_HI.

4. CHT.

5. TIT.

6. FLVL.

7. REM.

8. FP_HI.

9. MAP.

10. DIF.

11. CLD.

12. RPM.

13. OILT_LO.

14. VOLTS.

15. OILP_HI.

16. AMPS.

17. CDT.

18. RES.

19. EGT.

20. Fuel Flow.

3.1 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 #3 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.

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EDM-350 Page 5 of 41 Rev IR
Engine Data Management System Date 12-06-17

EDM-350 Display

Approved Installation Manual for the Experimental Report No 350
EDM-350 Page 6 of 41 Rev IR
Engine Data Management System Date 12-06-17

Remote Alert Light
comes with the
placard “Engine”

EDM-350 system mounts in a 3.125 inch diameter instrument panel hole.

Approved Installation Manual for the Experimental Report No 350
EDM-350 Page 7 of 41 Rev IR
Engine Data Management System Date 12-06-17

4. Locating and Installing the Indicator Display (Alert Light)

Single Engine Aircraft EDM-350

The EDM-350 display should be located as close as possible to the pilot with an unobstructed view and for
easy access to the buttons on the instrument.

The light for the EDM-350 is mounted in a 3/8” diameter hole.

Mounting bracket for the EDM-350

EDM-350 Model:

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 ½” 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 3.0 inches deep less connectors.

Mounts in a standard 3-1/8” instrument hole. First, place the mounting bracket on the

Approved Installation Manual for the Experimental Report No 350
EDM-350 Page 8 of 41 Rev IR
Engine Data Management System Date 12-06-17

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.

5. Routing 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:

Conn Harness PN

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

700702

P3 790420 RPM, MAP, Oil pressure

P4 700708 Serial data to GPS, Serial data from GPS, Fuel flow transducer

P5 790723 Fuel Pressure, Fuel Level (Resistive and Capacitive ), Amps

RAL 790547 Category 5 jack and cable for RAL (Remote Alarm light)

CHT, EGT 6 cylinder

CHT, EGT 4 cylinder

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 destroy 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.

6. 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 compartment to the display unit. Upon accomplishing this reseal
the opening with factory recommended sealant.

Approved Installation Manual for the Experimental Report No 350

ring terminal

EDM-350 Page 9 of 41 Rev IR
Engine Data Management System Date 12-06-17

7. Power Connection

The EDM automatically adapts to either a 14 or 28-volt electrical system. The Avionics Bus power wire to the EDM
should be 20ga copper. A 5 amp circuit breaker is required. Connect the EDM ground wire to the engine block.
For lighting, no connection to the aircraft dimmer system is required because the instrument dims automatically with
reductions in ambient light. Required power for the 350 is 1.0 amp at 14vdc

8. Probe Wiring

When cutting the pair of leads to the proper length to connect to the probes, leave enough slack in the wiring so that
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 color­coding.

2 1/4"

yellow

Thermocouple wire harness

red

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.

1/4" 1 1/2"

Fold back wire
double before
crimping terminals

shrink tubing

Place a ¼ 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

to instrument

necessary

to probe

Slide the sleeve over the joint and secure with three tie-wraps.

tie-wrap 3 places

1/4 x 4" sleeve

The most common installation problems are related to poor quality terminations.

8.1 Wiring Markings

The EDM-350 is supplied with special Teflon insulated Chromel-Alumel factory assembled wiring harness configured
for the correct number of cylinders. The wire harness is marked E1= EGT-1, C1= CHT-1, etc.

NOTE: Unlike most other EGT & 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.

Approved Installation Manual for the Experimental Report No 350
EDM-350 Page 10 of 41 Rev IR
Engine Data Management System Date 12-06-17

9. Exhaust Gas Temperature Probe (EGT) Installation

Use the J2 connector harness 700700 or 700702 labeled E1 through E4 or E6. Replace with JPI probe M-111 in all
exhaust stacks.

The Model M-111 Probe will fit any engines where
the existing holes in the exhaust stack are 1/8" to

EGT probe
Drill no. 40
pilot hole,
then no. 30
hole.

exhaust stack

2" to 4"

CHT probe

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 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

note orientation of

Thimble

Probe

slot

Position probe

in approximate

center of

exhaust

9.1 Turbine Inlet Temperature (TIT) Probe Installation (optional)Kit 1200

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 approximately 4 inches from the turbine inlet if possible, on the waste-gate side of the turbine.

9.2

TIT for second Turbine Inlet Temperature Kit 1200

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.

Approved Installation Manual for the Experimental Report No 350
EDM-350 Page 11 of 41 Rev IR
Engine Data Management System Date 12-06-17

10. Cylinder Head Temperature (CHT) Probe Installation

Use the P2 connector harness 700700 or 700702 labeled C1 through C4 or C6. The JPI probe is a bayonet probe
P/N 5050 that has a captive 3/8-24 boss that is screwed into the head of each cylinder.

11. CHT (spark plug gasket)mm-113

Cylinder head temperatures are measured with a spark plug gasket type probe placed under the rear sparkplugs.
The spark plug gasket probe, P/N M-113, replaces the standard copper spark plug gasket on one spark plug. The
probe is placed on the rear plug for a cleaner installation and less chance of chaffing the thermocouple wiring. After
many removals the probe may be annealed for re-use. Heat to 1100 oF and quench in water.

12. Outside Air Temperature (OAT) Probe Installation

Use the P1 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.

The outside aluminum shield tube is used to both hold the probe in place and shield it from radiated heat from the
sun. The OAT option is displayed as an independent digital temperature bar graph such as "75.”

12.1 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
temperature like "125 IAT". On non-turbo engines the IAT in reality is the Carburetor temperature and displayed as
“34 CRB.”

12.2 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 throat. No drilling or machining of the carburetor is necessary.

13. 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.

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Engine Data Management System Date 12-06-17

14. Oil Pressure Sensor Installation

Use the P3 connector harness 790420 labeled OIL-P for a pressure sensor two wire VDO

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.

14.1 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.

15. 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.

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Engine Data Management System Date 12-06-17

16. Ammeter Shunt Installation

Use the P5 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.

16.1 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.

Master switch

contactor

- BATT +

Master switch

Starter Starter solenoid

Ammeter Configuration

Master switch

contactor

- BATT +

Master switch

Alternator

F G

B

external shunt

Alternator

F G

B

+

external shunt

+

Fuse Signals

with 1 amp inline

Bus

Bus

Starter Starter solenoid

Load Meter Configuration

Approved Installation Manual for the Experimental Report No 350

pump.

EDM-350 Page 14 of 41 Rev IR
Engine Data Management System Date 12-06-17

16.2 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 load meter configuration. There is no alarm.

17. General Fuel Flow Transducer Installation

Use the P4 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.

The EDM-350 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. Route the
PI 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
201-A NA
201-B 680501/680600
201-C NA
231 680503

Before connecting any hoses to the transducer, thoroughly clean them and insure they are free of any loose
material. Never pass air pressure through the transducer or use Teflon tape/pipe cement; damage will occur.
Use only steel fittings supplied never use aluminum fittings on transducer (Additional fittings are available from JPI).
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 ½ 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 __________.

900591B Clamp

MS 21919

Clamp as required

to carburetor, flow
divider, or fuel
injector

Aeroquip

6 inches maximum from

Cut slit in fire sleeve

Transducer

support

OUT

up

Fittings 1/4 NPT. Do NOT
use aluminum fittings

IN

Aeroquip Fire Sleeve
AE102/62-24

Aeroquip
303 hose

from fuel tank,
throttle body or
engine driven fuel

The EDM-350 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

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Engine Data Management System Date 12-06-17

18. 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 calibration (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.

18.1 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 terminal on the sender, and the black wire to the
terminal mounted on the metal body on the sender. See illustration on following page.

18.2 Resistive 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 ground terminal on the
sender. See illustration on following page.

Approved Installation Manual for the Experimental Report No 350
EDM-350 Page 16 of 41 Rev IR
Engine Data Management System Date 12-06-17

Example harness arrangement for an aircraft with resistive output senders

Resistive Harness PN 790719-3

Approved Installation Manual for the Experimental Report No 350

WARNING

EDM-350 Page 17 of 41 Rev IR
Engine Data Management System Date 12-06-17

18.3 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 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 interface hardware (PN 791802). NOTE: This drawing is
sent with the kit if applicable and 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.

18.4 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’ function (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 with the airplane in flight attitude.

:

 Never add or remove fuel from the aircraft when the master switch is turned on.

 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.

 JPI strongly recommends replacing the fuel quantity senders before calibration.

DO NOT RELY SOLELY ON THE FUEL LEVEL DISPLAYED ON THE EDM-350 TO
DETERMINE THE FUEL LEVELS IN THE AIRCRAFT. The use of the EDM-350 does not

eliminate or reduce the necessity for the pilot to use good flight planning, preflight and in-flight
techniques for managing fuel. It is important the pilot adopt the practices listed below. If you are
not familiar with these techniques, contact the FAA to acquire proper training.

Approved Installation Manual for the Experimental Report No 350
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Engine Data Management System Date 12-06-17

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 5 calibration points and at what volume each will be. The zero-gallon
point reading is always taken with unusable fuel in the tank. Example of a completed table for LEFT tank:

LEFT

F 39.0 GAL 1907

¾ 29.3 GAL 1431

½ 19.5 GAL 1145

¼ 9.8 GAL 971

E 0.0 GAL 685

2. This screen shown below 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 have been recorded for each tank.

With AUX it would

say LAUX and

RAUX

Actual Screen Shot

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Engine Data Management System Date 12-06-17

18.4.1 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.

2. Tap YES when you see ‘Do you have table data?’.

Approved Installation Manual for the Experimental Report No 350
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Engine Data Management System Date 12-06-17

3. Tap USER when you see ‘Do you want to restore user table?’

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).

4.

Tap TANK to select the next active tank and repeat previous step. Continue until all tanks ‘points’ have

been set.

5.

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.

(Note: tapping FACTORY

6.

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.

7.

Tap SAVE to record it. Follow the on-screen menus to edit the value. Repeat previous step until all
tanks data have been entered.

8.

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.

Approved Installation Manual for the Experimental Report No 350
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Engine Data Management System Date 12-06-17

19. 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”. At this point hold in button 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.

20. GPS Interface

Use the P4 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.

21. Manifold Pressure (MAP) Sensor

Install a T-fitting (not supplied) in the aircraft’s MP gage line in the cockpit near the MP gage. Install the JPI MAP
sensor P/N 604010 on the T-fitting. Connect the JPI MP sensor to the wiring harness using the 4-pin connector
supplied. The MAP sensor uses a 1/8 NPT fitting. Note: this is eligible for installation on all 4 & 6 cylinder engines

only. There are no alarm limits

.

. Keep sensor on cold side of firewall

MP Sensor

connector

from engine

T-fitting

AN818-2

AN832-2

MP gage

Fire Wall

AN818-2

1/8 Aluminum Tube

to Engine Manifold

Approved Installation Manual for the Experimental Report No 350
EDM-350 Page 22 of 41 Rev IR
Engine Data Management System Date 12-06-17

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 vary 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
Elev.MPFACTOR

-500 1.0182

-400 1.0145

-300 1.0109

-200 1.0073

-100 1.0036
0 1.0000

100 0.9964
200 0.9928
300 0.9892
400 0.9856
500 0.9821
600 0.9785
700 0.9750
800 0.9714

900 0.9679
1000 0.9644
1100 0.9609

1200 0.9574
1300 0.9539
1400 0..4
1500 0.9469
1600 0.9435
1700 0.9400
1800 0.9366
1900 0.9332
2000 0.9298
2100 0.9264
2200 0.9230
2300 0.9196
2400 0.9162
2500 0.9129
2600 0.9095
2700 0.9062
2800 0.9028
2900 0.8995
3000 0.8962

3100 0.8929
3200 0.8896
3300 0.8863
3400 0.8830
3500 0.8798
3600 0.8765
3700 0.8733
3800 0.8700
3900 0.8668
4000 0.8636
4100 0.8604
4200 0.8572

4300 0.8540
4400 0.8508
4500 0.8477
4600 0.8445
4700 0.8414
4800 0.8382
4900 0.8351

5000 0.8320
5100 0.8289
5200 0.8258
5300 0.8227
5400 0.8196
5500 0.8165
5600 0.8135
5700 0.8104
5800 0.8074
5900 0.8043
6000 0.8013
6100 0.7983
6200 0.7953
6300 0.7923
6400 0.7893
6500 0.7863
6600 0.7833
6700 0.7804

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Engine Data Management System Date 12-06-2017

22. RPM Sensor installation

Use the P3 connector harness 790420 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 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 pressurized Bendix -20, 200
series & S6LSC-25P and non-pressurized Slick 600 use JPI P/N 420806. Mount the sensor in the vent plug closest to
the base of the magneto as shown in the appropriate diagram. Note: this is eligible for installation on all 4 & 6 cylinder
engines only.

.

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EDM-350 Page 24 of 41 Rev IR
Engine Data Management System Date 12-06-2017

23. EDM-350 Specifications and Limitations

The following parameters must be customized for the aircraft into which the EDM-350 is installed.

Factory set limits or default values for EDM-350

1. TIT 1650 F TSO-C43

2. CHT 450 F 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 set to 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 NON TSO

30. Record time, 6 sec intervals NON TSO

31. Hobbs on at 1000 RPM NON TSO

32. Indicator (instrument) EDM 350 NON TSO

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EDM-350 Page 25 of 41 Rev IR
Engine Data Management System Date 12-06-2017

24. EMI Radio Test and functional check:

Even through the EDM-350 has been tested to DO-160E Section 20 (EMI) the installation itself could create radio
interference on specific frequencies. The following test is to ensure 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 the aircraft bus (or buses) in accordance with
normal engine prestart procedures (see Aircraft Pilot Operating Handbook). Verify that the EDM-350 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-350 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-350 system to
check if it is the source of this noise. If the EDM-350 system is not the source of ‘unusual noise’ then mark the table
with a ‘PASS’.

Frequency NAV/COM 1

(PASS/FAIL)

108.00

112.00

115.00

117.00

120.00

121.00

122.00

123.00

124.00

125.00

126.00

127.00

128.00

129.00

130.00

132.00

NAV/COM 2
(PASS/FAIL)

Comments

Approved Installation Manual for the Experimental Aircraft Report No 350
EDM-350 Page 26 of 41 Rev IR
Engine Data Management System Date 12-06-2017

25. Component Parts

Single engine

-4 Cyl -6 Cyl
Display EDM-350 P/N 350000-(xxx) 1 1
EGT probe KIT PN 1280 4 6
TIT probe with option KIT 1200 1 1
CHT probe KIT PN 1260 4 6
OAT probe with option KIT 1220 1 1
IAT probe with option KIT 1300 1 1
Carb temp probe KIT 1250 PN 500409 1 1
Oil Temp probe with option KIT 1255 PN 400409 1 1
Oil pressure sender KIT 1460 PN 159936 1 1
Fuel pressure sender KIT 1450 PN 159935 1 1
Fuel pressure differential sender Kit 1480 PN 159938 1 1
Ammeter shunt PN 159920 1 1
Fuel Flow transducer PN 700900-1 or -2 1 1
Fuel Level sender option 1 1
MAP KIT 1440 PN 159934A 1 1
RPM one of P/N 420806 or 420809 Pressurized 1 1
RPM one of P/N 420815-1, -2 Non Pressurized 1 1
RAL P/N-790547 1 1

25.1 Component Parts List 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”

25.2 Component Parts list for CHT KIT 1260

1 Bayonet Probe Thermocouple type K Spring loaded PN 5050
2 Ring Terminals
2 Screws and Nuts 6-32 X 1/4"
1 Fiberglass tube 3/8” x 5”

25.3 Component Parts list for IAT (KIT 1300) probe

1 Thermocouple type K probe PN M-111
1 Stainless Steel Clamp &Thimble

1 Stainless Steel Exhaust Seal Washer

25.4 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”

25.5 Component Parts list for CARB (KIT 1190) probe

1 P/N 400128, CARB probe
2 Ring Terminals
2 Screws and Nuts 6-32 X1/4"
1 Fiberglass tube 3/8” x 5”

Approved Installation Manual for the Experimental Aircraft Report No 350
EDM-350 Page 27 of 41 Rev IR
Engine Data Management System Date 12-06-2017

25.6 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”

25.7 Components Parts list for OIL pressure PN 306018 Kit 1170

1 P/N 306018 OIL pressure transducer VDO

2 Ring Terminals

25.8 Component Parts list for Kit 1480 Differential Fuel Pressure

1 P/N 159938 Fuel pressure
1 P/N 159961 Clamp, Loop

1 P/N 174204 Connector MS

sensor

Cushioned

3116F8-4S

25.9 Component Parts list for ampere shunt Kit 1120

1 P/N 159920 100 amp shunt
2 Ring Terminals

25.10 Component Parts list for Fuel Flow Transducer

1 fuel flow transducer, 201 or 231 PN 700900-1,-2
1 3-pin connector housing
3 female pins

25.11 Component Parts list for MAP sensor Kit 1330

P/N 604010, Manifold pressure sensor with 1/8 NPT tee.

25.12 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 ………………………….P/N 420808

Approved Installation Manual for the Experimental Aircraft Report No 350
EDM-350 Page 28 of 41 Rev IR
Engine Data Management System Date 12-06-2017

25.13 Components Parts list for pressurized RPM sensor P/N depends on Magneto make and model

Slick 6000………………………….….P/N 420809
Bendix magneto 20, slick 600………P/N 420806
Bendix Dual ………………………….P/N 420808
Bendix 1200………………………….P/N 420807

26. Weight and Balance Data

Indicator PN 350000-(xxx) EDM-350 1.0 Lbs
EGT / TIT / CDT / IAT / OAT probe 2.0 oz. each / 0.125 lbs
CHT / Oil Temperature probe 1.5 oz. each / 0.094 lbs
4/6 Cylinder Harness 8 ft. 14.0 oz. each / 0.88 lbs
RPM 1.5 oz each / .094 lbs
MAP 5.0 oz / 0.42 lbs
Fuel Pressure Sender 5.0 oz / 0.42 lbs
Oil Pressure Sender 5.0 oz / 0.42 lbs
Harness each 1.0 Lbs

27. Pilot Programming

To start the Pilot Program procedure, ensure no alarms are being displayed in the message area. If this is the case,
STEP to clear all faults first, then 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

advances next

item

PROGRAM
FUEL N FILL? N

SOFTWARE
INFO?

RATE 4 0 … 9
TRIP
USED?

DIGITAL
FUEL
WITH FUEL
FLOW
MONITORIN
G

EGT
DISPLAY
IN 1’S

OAT Display
ºF

OAT
ADJUSTME
NT 0
HPC I25 70 HP

LF sequences

through these

values

INFO

YES  NO

YES  NO

YES 
NO

EGT 1?N



EGT 10?Y

F  C

PLUS 
MINUS

HPC= I25

Comments

Stays on for two seconds.

Tap LF to change fuel status. Exits program mode when done.

Software PN: & Version.

Index rate (pause time in seconds) in the Automatic Mode. 0 disables the Automatic Mode.

NO: When Refuel mode used on EDM, total fuel used is reset to 0.
YES: accumulate total fuel used rather than reset to 0 at each refueling. See page Error! Bookmark
not defined..

This allows a choice between Digital or Analog fuel gauges. Digital will show a digital quantity
under the strip gauge.
Only appears when digital gauges are chosen. (This feature compares the fuel totalizer value against
the strip gauge total and alarms if it’s greater than 5 gal.) Only available with 2 tank aircraft with
AUX = 0.

Y—Yes—sets the digital display to one-degree resolution; N—No—sets 10°. (10°
resolution is easier to interpret the EGT’s.)

Tap C to display OAT in Celsius, F to display in Fahrenheit. Hold STEP and LF for 5 seconds to
ADJUST the OAT calibration.

Adjust the indicated temperature up or down by up to 10° using PLUS or MINUS. For example,
OAT3 adjust the OAT 3° higher.

%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. Otherwise the next step will be skipped.

Approved Installation Manual for the Experimental Aircraft Report No 350

to adjust.

EDM-350 Page 29 of 41 Rev IR
Engine Data Management System Date 12-06-2017

MAP

29.9
KF1

MAP 20 
32
EDIT

29.90
KF2

EDIT

29.90

CARB? Y

YES 

NO
CARB =
1

TIME:
18:23:59

DATE:
05/14/09

RECORD
TIME: 6

TAIL NO:
TEST
END? Y END? Y STEP exits the pilot programming mode.

FACTORY
MODE

FACTORY
RESET ?

PLUS 

MINUS

00:00:00 

23:59:59

01/01/00 

12/31/99

PLUS 

MINUS

EDIT Enter tail number of aircraft.

FACTORY Stays on 2 seconds.

NEXT

YES  NO

Adjust the MAP.

Adjust the instrument’s K-factor to match the fuel flow transducer K-factor.

Adjust the instrument’s K-factor to match the fuel flow transducer K-factor.

Set to NO if injected. Tap SAVE to save changes.

F/F Filter (Higher the number the better the dampening effect) (Fuel pump pulses).

Hold NEXT and button 2 for 5 seconds until you see ADJUST. Use Hours, Minutes,
Seconds to adjust. Tap SAVE to save changes. Tap NEXT to skip to next item.

Hold NEXT and button 2 for 5 seconds until you see ADJUST. Use Month, Day, Year to
adjust. Tap SAVE to save changes. Tap NEXT to skip to next item.

Record time in seconds.

LF reenters pilot programming mode.

Tap YES to reset to factory configuration. Tap NO to leave it alone.

FUEL UNITS:
GAL

MAIN TANK
SIZE =

AUX TANK SIZE
=

FUEL USD
REMINDER

REMINDER
TIMEOUT = 5

MAP SENSOR = NEXT Allows a choice of Motorola or i2s. Tap SAVE to save value.

OIL-P SENSOR =
i2s
FUEL-P SENSOR NEXT Allows for a VDO 2 wire 30 psi., 2 wire 150 psi Tap SAVE to save value.

FUEL LEVEL
SENSOR =
CHANGE
ADVISORY
LIMITS

CHANGE PRE­ALARMS
LAST FLIGHT
NO =

AVERAGE
CRUISE RPM
2400

AMPS
ADJUSTMENT +
0

GAL, KGS, LTR,
LBS

PLUS 
MINUS

PLUS  MINUS

PLUS  MINUS

PLUS  MINUS

NEXT Allows a choice of i2s or VDO. Tap SAVE to save value.

NEXT Allows a choice of VOLTAGE or FREQUENCY. Tap SAVE to save value.

YES  NO

YES  NO

EDIT Tap EDIT to adjust PLUS or MINUS the flight number. Tap SAVE to save change. Allows

NEXT Tap EDIT to adjust. Tap PLUS or MINUS to adjust, then SAVE to save the change. Average

PLUS  MINUS

Default unit is GAL. TAP EDIT then CHANGE to choose a different unit. Tap SAVE to save the
new fuel unit.

In gallons or preset value. Use PLUS or MINUS to adjust. Tap SAVE to save the change. Tap
NEXT to skip to the next item.

In gallons or preset value. Use PLUS or MINUS to adjust. Tap SAVE to save change. Tap
NEXT to skip to the next item.

In gallons or preset value. Use PLUS or MINUS to adjust. Tap SAVE to save value. Tap
NEXT to skip to the next item.

Sets duration on display in minutes. Use PLUS or MINUS to adjust. Tap SAVE to save value.
Tap NEXT to skip to the next item.

Tap YES or NO to enter gauges with no yellow bands displayed. Tap PLUS or MINUS
Tap SAVE to save value. This affects, Volts Hi, Volts Low, EGT Span DIF, Shock Cooling
CLD, Low time to empty, Low fuel REM.

Tap YES to enable pre-alarms for HI EGT, HI CHT, HI OIL-T, LOW TANK.

setting the last flight no. Used during a factory reset-continues numerical order.

cruise is based on a percentage of RPM redline. A one to one ratio for TACH TIME is achieved
at this setting.

Use PLUS or MINUS to adjust. Tap SAVE to save change. Tap NEXT to skip to the next item.

Approved Installation Manual for the Experimental Aircraft Report No 350

CO GUARDIAN?

EDM-350 Page 30 of 41 Rev IR
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ENGINE TEMPS
IN Deg F
Engine HP 210 NEXT or EDIT TAP NEXT to skip. Tap EDIT to adjust. TAP PLUS or MINUS to change. TAP SAVE to save

Engine Constant

13.7

R-FACTOR CYL
= 6

CUSTOMIZE
DISPLAY?
REMEMBER
CHANNEL
EXCLUSIONS =
No
LOP DFLT? N

REMOTE
DISPLAY I/O?
NONE

Y
FDR OUTPUT? Y

END?

AIRFRAME
HOBBS

TACH TIME NEXT OR EDIT Tap EDIT to enter/change Airframe Hobbs.

END?

F OR C Tap NEXT to skip. Tap EXIT to exit program. Tap F for Farenheit or C for Centigrade.

change.

NEXT or EDIT TAP NEXT or EDIT. Tap PLUS or MINUS to adjust. TAP SAVE to save. (Use 13.7 for

turbo’d , 14.9 for naturally aspirated or turbo normalized engines).

PLUS  MINUS

YES  NO

NEXT, EXIT OR
CHANGE

YES  NO

NEXT, EXIT OR
EDIT

YES  NO

YES  NO

YES  NO

NEXT OR EDIT Tap EDIT to enter/change Airframe Hobbs.

EXIT  NO

Tap PLUS or MINUS to adjust. Tap SAVE to save change. For the number of cylinders for
your engine, double R-Factor for dual mags.

Allows swapping of RPM and MAP gauges, adjusts sequence of primary and advisory gauges.

Tap NEXT to move to next function. Tap EXIT to exit program mode. Tap CHANGE to change
the value from No to Yes.

Tap YES to make LOP your default setting. Tap NO to keep ROP your default setting.

Tap NEXT to move to next function. Tap EXIT to exit program mode. Tap EDIT to change to
“OUTPUT TO REMOTE”.

To activate CO Guardian select YES. Tap SAVE to save. Tap NEXT to go to the next item.

Allows export of recording instead of recording in memory. Tap SAVE to save or NEXT to go to
the next item.

YES exits the Factory program mode. NO brings you back to the beginning of the Factory
program mode. Holding both buttons 1&2 will get you to Airframe Hobbs and TACH TIME.

Tap DIGIT to move through each digit. Tap PLUS or MINUS to change the value. Tap SAVE
to save value.

Tap DIGIT to move through each digit. Tap PLUS or MINUS to change the value. Tap SAVE
to save value.

Tap EXIT to restart the unit. Tap NO to start at Airframe Hobbs/Tach Time again.

28. 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. Tap STEP repeatedly until you see—for example— HPC = I25. Then hold both the STEP and LF buttons display
until you see ADJUST, followed by HPC= I25. The adjustment range for the HP Constant is 45 to 180.

3. Set the MP and RPM per your POH to 70 percent power. Let conditions stabilize.

4. Change the HP reading on the EDM-350 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 proceed to the next step.

29. 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 (see page 27).

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 .

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3. Then hold both the first two buttons until you see ADJUST, followed by MAP+0. The adjustment range for the MAP
is ±3.0 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. Tap the 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.
.

30. Selecting Fuel Pressure Type

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 Program Mode.

4. After “Factory” is displayed in the scanner message area, tap the NEXT button until FUEL PRESSURE = is

displayed in the scanner message area.

5. Hold the STEP and LF buttons until the word ADJUST appears in the message area

6. Tap the PLUS or MINUS buttons to change the selected Fuel Pressure sensor type.

7. To save the selected value, hold the STEP and LF buttons until the word SET appears in the message area.

8. Tap the STEP button repeatedly until the message END? is displayed in the message area

9. Tap the button labeled YES to save changes and restart the EDM.

31. Customizing EDM350

You can customize – change or re-order the data channels in the EDM display. The data channels are numbered from
1 up to 6, depending on your particular aircraft configuration and EDM installation. To customize the LCD layout of the
gauges, 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 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 “1=VOLTS” (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

8. Tap the “NEXT” button to select the next non-primary location (such as 2=AMPS).

9. When all changes have been made, hold the STEP and LF buttons until the word SET appears in the
message area.

10. Tap the STEP button repeatedly until the message END? is displayed in the message area

11. Tap the button labeled YES to save changes and restart the EDM.

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32. 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 not retroactively recalculated.

33. 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-350 calculation of the fuel used for each flight USD.

Fuel USED shown by EDM

Flight

1
2
3

Total

(total tank - REM) Actual fuel used by topping tanks

 

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 Adjustment ratio:

Adjustment ratio = ( /  ) – 1

2

5. New K Factor =  x (Adjustment ratio +1).

Record the values here:

Date

EDM

fuel used

actual

fuel used

Current K

factor

New K factor Pilot’s

initials

34. 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’.

2. Tap STEP repeatedly until you see K-FACTOR=29.90 (this value may be different on your unit).

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3. Hold both the STEP and LF buttons simultaneously until a digit begins flashing. This indicates editing has been
enabled.

4. Tap or hold the LF button to change the flashing digit to the desired value.

5. Tap or hold the STEP button to select the next digit to edit.

6. Repeat steps 4 and 5 until the displayed value is set to your desired value.

7. 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.

35. Programming Accumulate Trip Total

Accumulate—default is OFF: resets the fuel used to 0 every time you inform the EDM-350 that the aircraft was
refueled. With accumulate ON fuel used will not be reset to 0 when you inform the EDM-350 that the aircraft was
refueled.

Select “No” if you wish to display total fuel used since the last time you informed the EDM-350 that the aircraft 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.

36. Trouble Shooting

Diagnostic Testing on Startup and During Flight

When your EDM is first turned on it tests internal components, calibration and integrity of the probes.
During flight, probes are constantly checked for inconsistent or intermittent signals.

Problem

A MISSING COLUMN IN THE
DISPLAY UPON START UP

A MISSING COLUMN IN THE
DISPLAY DURING FLIGHT

DISPLAY FREEZES OR MAY
BE INCORRECT

LEANFIND FINDS A “PEAK”
TOO SOON

PEAK NOT FOUND DURING
LEANFIND
OFF-SCALE EGT COLUMNS,
TOO HIGH OR LOW

Diagnostic routine has found an open line
or probe with no connection.

A reading that is jumping around or
incorrect
The probe is removed from the line up
A power transient could cause the
processors to malfunction

Failure to pre-lean before performing
LeanFind or stopping while leaning.
Leaning too slowly

Lean Find not activated or stopping while
leaning

Off-scale EGT column readings. EDM in
the Normalize view (blue EGT scales).

Situation Correction

Replace the EGT or CHT probe shown
in the error message

Replace the EGT or CHT probe shown
in the error message on the next flight.

Recycle the power to the EDM

Continue to lean without stopping
Lean more rapidly

Lean at the speed of approximately
10°F per second

Return to Standard mode by holding
the LF button.

FIRST CYLINDER TO PEAK
IS NOT THE HOTTEST

EGTS RISE DURING SINGLE
MAGNETO CHECK
EGTS NOT UNIFORM
DURING LOW POWER
OPERATION

The first to cylinder peak is not necessarily
the hottest
Incomplete combustion persisting longer This is normal.

Fuel and air distribution is not optimal at
low power settings

This is normal.

This is normal.

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0.0 GPH

--- GPH

--- H.M

OPEN PRB

BAD-PRB

RED ‘X’ DRAWN THROUGH
A SINGLE GAUGE

Zero’s indicate Fuel flow is too low to

This is normal.
register
Dashes indicate No fuel flow transducer
signals
Dashes indicate No fuel flow transducer

Have the mechanic verify if it is the

sensor or wiring.

No GPS signal, check the wiring
signals
Open probe. Wiring to probe is open circuit. Check

wiring and crimps. Swap probes to

troubleshoot.
Bad probe. Erratic reading. May be poor electrical

connection. Swap probes to

troubleshoot.
Measurement out of range. Have the mechanic verify if it is the

engine or the sensor. Replace as

necessary.

RED ‘X’ DRAWN THROUGH
ALL GAUGES FOR AN
ENGINE
CAL ERR

DSP XXX
COMM ERR

NO I 5 MV

NO 50MV

NO 2.5V

WARNCAL, WARNCFG

HOBSERR

DAU failure or DAU communications error. Check power to DAU and wiring

Calibration error. Return unit to factory.
Internal communication error. Return unit to factory.
Internal communication error. Return unit to factory.

Calibration error. Return unit to factory.

Calibration error. Return unit to factory.

Calibration error. Return unit to factory.

Transient warning messages. Return unit to factory.

The time of the most recent flight may not
be reflected in the HOBBS meter.

HOBSBAD

HANGCFG, HANGCAL

The HOBBS data has been corrupted. Return unit to factory.

Internal system errors. Return unit to factory.

37. GPS Interface Diagnostics

Problem

Measurements ‘xxx REQ’,
‘XXX RES’ AND ‘XXX
MPG’ are all missing from
the scan.
NO - COM message and
‘xxx REQ’, ‘XXX RES’ AND
‘XXX MPG’ are all missing
from the scan.
NO - SIG message and
‘xxx REQ’, ‘XXX RES’ AND
‘XXX MPG’ are all missing
from the scan.
NO - WPT message and
‘xxx REQ’, ‘XXX RES’ are
all missing from the scan.

No communications from GPS receiver to
EDM.

Communications are received by EDM and
the Auto-Protocol setup is in process.

GPS receiver has insufficient signal for
valid data.

No waypoints are programmed into the
aircraft GPS receiver.

harness connections.

Return unit to factory.

Situation Correction

No connection or aircraft GPS is off.

Verify correct output format setup in

GPS receiver; check GPS

connections.

Check GPS signal

Program way points

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43. Connector Pin Assignments on EDM, P1 through P5

Rear view of EDM 350 Showing Connector Locations

P5

15

8

9

1

9

5

25

13

25

13

15

8

6

P3

1

14

1

14

1

9

1

P4

Alert Light

P1

P2

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44. J3 RPM, MP, Oil-P

J-3 Harness with Oil and manifold pressure sender

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44.1 J5 PN 790723 (fuel tanks, fuel press, amps)

J-5 Harness with 3 wire fuel pressure sender.

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