J.P. Instruments EDM 760 Installation Manual

Installation manual for the EDM-760 Twin STC SA00729SE

Report No. 760

Temperature indicating system with Fuel Flow

Date 7/20/99 Rev NC

Page 1 of 19

THE OWNER OF THE EDM-760 MUST KEEP THIS MANUAL

		TABLE OF CONTENTS
			Page
1.	INSTALLING THE INDICATOR		2
2.	EXHAUST GAS TEMPERATURE PROBE		2
3.	TURBINE INLET TEMPERATURE PROBE		2
4.	USING ORIGINAL TIT PROBE		2
5.	CYLINDER HEAD TEMPERATURE PROBE		2
6.	SPARK PLUG GASKET CHT PROBE		3
7.	INDUCTION AIR/CARBURETOR TEMPERATURE		3
8.	OIL TEMPERATURE PROBE		3
9.	OUTSIDE AIR TEMPERATURE PROBE		3
10.	FUEL FLOW OPTION		3
11.	DATA PORT		3
12.	WIRING		3
13.	EGT AND CHT PROBE WIRING MARKINGS		4
14.	ROUTING THE WIRING HARNESS		4
15.	INDICATOR INSTALLATION & RECORD		4
16.	DESCRIPTION OF INSTRUMENT		5
17.	INSTRUMENT OPERATION		6
18.	OPERATION		6
19.	SPECIFICATIONS AND LIMITATIONS		6
20.	COMPONENT PARTS LIST FOR EGT/ TIT PROBE		7
21.	COMPONENT PARTS LIST FOR CHT PROBE		7
22.	COMPONENT PARTS LIST FOR OIL PROBE		7
23.	COMPONENT PARTS LIST FOR OAT PROBE		7
24.	COMPONENT PARTS LIST FOR IAT PROBE		7
25.	COMPONENT PARTS LIST FOR TWIN ENGINE EGT/CHT		7
26.	WEIGHT AND BALANCE DATA		7
27.	CHANGING PROGRAMMED LIMITS		8
28.	TROUBLE-SHOOTING		9
FIG-1 INSTRUMENT BEZEL TEMPLATE (DWG. 760124)			10
FIG-2		EGT/CHT/TIT PROBE PLACEMENT	11
FIG-3		EGT PROBE INSTALLATION	12
FIG-4 OIL PROBE INSTALLATION FOR LYCOMING			13
FIG-5 OIL PROBE INSTALLATION FOR CONTINENTAL			14
FIG-6 DRAWING 5057 WIRE PREPARATION			15
FIG-7 WIRING LIST TWIN EDM-760, DRAWING 760701			16
FIG-8 WIRING THERMOCOUPLE DIAGRAM DRAWING 760202			17
Fig-9 WIRING FUEL FLOW DIAGRAM 760744			18
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS (ICA)			19
APPENDIX – A, FUEL FLOW TRANSDUCER INSTALLATION

J.P.INSTRUMENTS

PO BOX 7033

HUNTINGTON BEACH CA 92615

Last printed 7/15/04

Installation manual for the EDM-760 Twin STC SA00729SE

Report No. 760

Temperature indicating system with Fuel Flow

Date 7/20/99 Rev NC

Page 2 of 19

1) INSTALLING THE INDICATOR

Installation Should Be Done In Accordance With Advisory Circular AC43.13-1A

A steel template supplied with the installation kit is used as a guide for drilling two buttonholes in the instrument panel. Align and Mount the Template into the instrument panel hole. First drilling a 0.125 hole. Remove the template and check the instrument alignment, if OK re-drill with a 0.147 drill. The plastic buttons are removable by pulling off. The EDM-760 mounts in a standard 3.125" instrument hole. The instrument configures itself automatically for Twin 4 or 6 cylinder, 14/28 volt aircraft. The instrument is 7.5” deep less connectors and is 3.20 square behind the panel..

TO PREVENT DISPLAY DAMAGE IT IS ESSENTIAL THAT THE FOUR MOUNTING SCREWS NOT PENETRATE THE INSTRUMENT MORE THAN .12 INCHES. DAMAGE OF THIS NATURE IS NOT COVERED UNDER WARRANTY.

2) EXHAUST GAS TEMPERATURE PROBE (EGT)

The Model M-111 Probe will fit any existing holes in the exhaust stack in any engine having the diameter of 1/8" to 1/4". 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 a uniform distance from the exhaust stack flange. A nominal distance of 2 to 4 inches from the exhaust flange is recommended. (See fig-2). 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, and clamp screw or wire. Careful matching of probe position will provide best temperature readings.

Insert the probe in the exhaust or previously drilled hole (see fig-3) 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.

3) TURBINE INLET TEMPERATURE PROBE (TIT)

The standard 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 (4) inches from the Turbine inlet if possible, on the wastgate side of the turbine. TIT will appear as the seventh column “T “and the expression “1650 TIT” will be seen when the dot is in place over it.

4) USE ORIGINAL TIT BY PIGGY BACKING ORIGINAL

The EDM-760 input is compatible with the aircraft’s factory TIT and will not load the factory probe. Connect the EDM-760 TIT wire to the same red/yellow leads on the factory probe. Check calibration by running up the engine and noting if there is and difference between the factory reading and the EDM-760 reading. Note any difference and mark it down plus or minus. Then Hold the two buttons in and Program/Rate - 4 will display. Again hold the two buttons in and TIT +0 / ADJ. will appear. Tap the LF to subtract and hold to add. When the correct difference is displayed tap step to go to back to TIT reading. Reading should be close to correct, repeat as required.

5) CYLINDER HEAD TEMPERATURE PROBE (CHT), BAYONET

The Bayonet probe 5050-T has the 3/8-24 boss as part of the probe and is screwed into the base of the cylinder (See fig-2). The bayonet probe has a screwdriver slot to facilitate tightening.

NOTE: Required original equipment that has a Red Line may not be replaced by the EDM-760 TIT or CHT installation. This includes but is not limited to all aircraft with adjustable cowl flaps and on aircraft with placards on the instrument panel showing a climb air speed, for cooling, different from the best rate of climb air speed.

If a previously installed TIT, CHT or EGT is not required for certification (or STC modification), it may be replaced by the EDM 760.

Installation manual for the EDM-760 Twin	STC SA00729SE
Report No. 760
Temperature indicating system with Fuel Flow	Date 7/20/99 Rev NC
	Page 3 of 19
6) SPARK PLUG GASKET CHT PROBE

Most factory installed cylinder head temperature gauges utilize a bayonet or screw-in resistive type probe that occupies one of the bayonet sockets. This probe is not compatible with the thermocouple probes required for the EDM-760.

The spark plug gasket probe, P/N M-113, replaces the standard copper spark plug gasket on one spark plug. The plug chosen, upper or lower, should be the one that provides the best correlation with the other temperature probes.

Due to the spark plug location, the gasket probe may read 25oF higher or lower than the factory probe. The probe is usually placed under the plug that receives the most direct cooling air. After many removals the probe may be annealed for re-use. Heat and quench in water. At additional cost an adapter probe (bayonet) is available that permits the factory CHT probe and a JPI probe to fit the same bayonet location.

7) Induction Air/Carburetor Temperature

Install P/N 130 Induction air/carburetor probe in the induction air housing or in the throat of the carburetor. Marvel carburetors have a ¼-28 threaded plug in the neck, remove and place the probe in that location.

8) OIL TEMPERATURE PROBE

The Oil Temperature Probe P/N 400505-C-L is installed as a supplemental oil temperature indicator. The -L part number is for all Lycoming Direct Drive Engines and is installed in the Right (passenger side) front Oil galley by removing the present 1/8 NPT plug (see fig-4). The -C part number is for all Continental Direct Drive engines and is installed in the Left (pilot side) front Oil galley by removing the present 3/8 NPT plug (see fig-5). Oil temperature will be displayed as an independent temperature like "230 OIL" and will be displayed In the seventh column automatically if TIT is not available. The original oil temperature gauge and sensor must remain. Check for oil leaks before first flight.

9) OUTSIDE AIR TEMPERATURE PROBE, OAT

Install the OAT probe, P/N 400510 in the airframe manufactures recommended location. If this is not possible, it is recommended that the OAT probe be placed 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 43.12-2a "Acceptable Methods, Techniques and Practices". The outside aluminum tube is used to both hold the probe in place and shield it from radiated heat. OAT option is displayed as an independent digital temperature like "75 OAT".

10) FUEL FLOW OPTION

Install the Fuel Flow transducer FXT-201 in accordance with Appendix-A, report 760. The EDM-760 can receive signal from any fuel flow transducer that was previously installed by the OEM or by STC, the EDM-760 with Fuel Flow option can share the transducer signal, specifically the FlowScan P/N 201-B or the Shadin PN 680501X / 680600X transducer. Wire per drawing 760744 and route the JPI wires along the existing wiring bundles lacing every foot. Install the Function switch per drawing 760124.

The placard "Do Not Rely on Fuel Flow Instrument to Determine Fuel Levels in Tanks" (PN 700905) must be mounted on the aircraft instrument panel near the EDM-760 with fuel flow option.

If the aircraft is equipped with a primary fuel flow, the following placard must be mounted on the aircraft instrument panel near the EDM-760, WITH FUEL FLOW OPTION: "Refer to Original Fuel Flow Instrumentation for Primary Information". (PN 700905)

11) DATA PORT RS-232 or DATA Storage

Data output is a line of data every 6 seconds at 9600 Baud. This data can be captured by any palmtop or laptop computer through the COM port in the modem receive mode or stored in memory and down load at a later time. Set modem to 9600 Baud, no parity and 1 stop bit. JPI also offers a program that will make it easier to load the data that can be converted into a Lotus or Excel format. JPI’s program is IBM compatible. Mac Computers loading through the Com/modem method.

Installation manual for the EDM-760 Twin STC SA00729SE

Report No. 760

Temperature indicating system with Fuel Flow

Date 7/20/99 Rev NC

Page 4 of 19

12) WIRING (12 / 24 volt)

The EDM-760 automatically accommodates both 14 and 28-volt electrical systems. Using the 15 pin connector, connect the power lead (red) to a separate 2 amp circuit breaker (or 2 amp in-line fuse) connected to the avionics power buss. The avionics master switch will then be used to turn off the instrument during engine start-up. The EDM-760 has a 10-second warm-up. If the panel lacks an avionics master switch we recommend that one be installed or a pull circuit breaker switch be provided to turn off the EDM-760 during engine start-up. No connection to the aircraft dimmer system is required because the instrument dims automatically with reductions in ambient light. A fully assembled harness is supplied with 21ft t/c leads.

13) EGT and CHT Probe Wiring Markings

The EDM-760 is supplied with special Teflon insulated Chromel Alumel factory assembled wiring harness configured for the correct number of cylinders. The wire harness is marked (E-1= EGT-1), (C-1= CHT-1), etc. TIT is marked “T”,

Oil Temp = “O” and OAT = “A”.

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.

The Temperature probes must be wired with the correct polarity. Each wire is marked with the cylinder number. The EGT and CHT probes connect to the temperature indicator with yellow jacket Teflon Chromel Alumel wire supplied. Strip the wires according to drawing 5057 and terminate with the crimp-on ring terminals provided. Verify the quality of each crimp with a sharp pull on the wire. The terminal should be almost impossible to pull off when crimped correctly. With in a few inches of the instrument terminal strip a connector may be installed.

NOTE: The ring terminals may be crimped with a " service type " tool, however AMP part number 48518 tool is recommended. Be sure to test each crimp by pulling on the wire to assure it will not come out.

The most common installation problems are poor quality terminations.

14) ROUTING THE WIRING HARNESS

Route the thermocouple wires from the probes through the firewall using fireproof rubber grommets and flame retarding silicone. Use an existing hole if possible. Following the existing wiring harnesses and connect to the indicator marking each lead with the cylinder number. All wires must be routed away from high temperature areas (exhaust stacks, turbochargers, etc.). Secure Probe leads to a convenient location on the engine approximately 8 to 12 inches from the probe, 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 airframe or engine since abrasion will destroy this high temperature wire. Secure thermocouple wires along the route to the indicator. Secure wire using original clamps, tape or tie wrap if possible.

CAUTION: Be sure the controls under the panel are not obstructed by the wiring.

Run up the Engines and confirm that the right engine is displayed on the right indicator and the left engine is displayed on the Left indicator of the EDM-760 display.

The probe wires must not be tied in with ignition, alternator or twin engine cabin heater ignition wires because of potential interference with temperature readings.

The probe wiring harness is made of Chromel-Alumel alloy wire that must not be substituted or extended with normal copper wire. The power and ground wire are normal copper. Leads may be spliced with additional Chromel-Alumel wire using copper butt splices.

When the installation is complete all wires should be secured using ties and carefully checked for interference, rubbing or chaffing with flight control cables or other moving parts.

Installation manual for the EDM-760 Twin STC SA00729SE

Report No. 760

Temperature indicating system with Fuel Flow

Date 7/20/99 Rev NC

Page 5 of 19

15) INDICATOR INSTALLATION & RECORD

Locate a 3.125” diameter hole in the instrument panel, where you would like to mount the indicator per drawing 760124. Mount the indicator in the panel, using the four 6-32 X.0.15" screws. The screws must not penetrate the bezel more than

.120". Three connectors are protruding from the rear of the instrument. Two 25 pin and one 15 pin connector. The top 25-pin connector connects the left engine harness. The bottom 25-pin connector, connects the right engine harness and the center 15-pin connector, connects the power and options like OAT.

Record the installation of the EDM-760 on a FAA form 337. Make entry in the aircraft logbook.

16) DESCRIPTION

GENERAL

The EDM-760 temperature indicator displays temperature digitally and in analog format. The analog display is an electronic bar graph of EGT & TIT temperatures presented as a percentage of 1650oF. Below the vertical columns the specific value for EGT and CHT are displayed digitally for both engines. EGT top and CHT bottom. The dot over the column indicates which cylinder's digital information is presently displayed. The missing bar in the graph represents the CHT trend, showing which cylinder is hotter or cooler and is checked digitally. Depressing the LF and STEP button simultaneously brings up the Pilot Programmable Mode in which the scan rate, OAT, and EGT resolution can be adjusted. Exit by Depressing STEP.

If the EDM-760 buttons are not depressed for 1 minutes the system will start scanning automatically. Depressing the STEP button will stop the automatic scan and index through all the functions available. During cruise, if the LF button is depressed for five seconds (normalize mode) the bar graph will level at mid scale. The leveled bars represent the peaks of each column. Each bar represents 10oF and now acts as an EGT & TIT trend monitor, quickly showing an increase or decrease in temperature. Depress again to return too normal; nothing else is affected.

TIT, OAT, OIL, BAT (voltage), Fuel flow functions and CLD (Rate of change of CHT in degrees per minute) are displayed digitally with headlines after the temperature, such as "230 OIL". A large value of "CLD" indicates shock cooling which has a detrimental effect on the engine and is usually associated with rapid descents at low power. Probes not installed will not be displayed.

An alarm causes the digital function to flash when the particular limit is reached. Factory generic set alarm limits for example: CHT (450 oF) and OIL (230 oF) are lower than the actual aircraft limits. The values may be adjusted to individual aircraft limits by pressing the reset button located on the rear of the instrument. Other factory set alarm limits are: "BAT" Voltage 15.5/12.0 or 31.0/24.0 Hi/Lo as appropriate; "DIF" (differential Hi/Lo EGT) 500 oF; "TIT" 1650 oF Hi; "OIL" Lo 90 oF; "CLD" (Rate of change of cylinder head temperature in degrees per minute) -60 degrees/minute. An alert output is available for the above functions that will sink 250 ma load. The pilot should be aware of the setting of each alarm for his particular aircraft. All alarms are "Canceled" in two ways: One by tapping the step button which will remove the alarm for 10 minutes. The second way is by holding the step button in for 5 seconds and seeing the word "OFF". Then, only that particular alarm is canceled . Canceled alarms will not appear again until the power has been removed and reapplied to the EDM-760. The entire display dims automatically depending on the ambient lighting.

Alarm limits set for this
instrument if different from
JPI limits.
CHT__________
OIL__________
TIT__________
DIF__________
CLD__________
BAT__________
TECH_________
DATE_________	17)

Installation manual for the EDM-760 Twin STC SA00729SE

Report No. 760

Temperature indicating system with Fuel Flow

Date 7/20/99 Rev NC

Page 6 of 19

EDM-760-6CT

With the fuel flow option a three-position mode (toggle) switch is installed in the panel per drw. 760124. The mode positions are: 1) EGT, digital and Bargraph display of temperatures, 2) FF., digital display of GPH, REM, REQ and fuel USED. Temperature Bargraph remains. 3) Both, cycles through everything installed. The data port output, sends RS232 serial data every 6 sec. A second alert output is available for the above functions that will sink 250-ma load. See drawing 760701 for wiring details.

18) OPERATION

Airplane flight manual limitations based on primary instrument indication take precedence over those of the EDM-760. CAUTION

Comply with manufacturer's Airplane/Rotor craft Flight Manual leaning procedure.

Do not exceed applicable engine or aircraft limitations.

After establishing desired cruise power depress the LF button to activate the Lean Find Mode. The pilot should start leaning one engine. The EDM-760 is waiting to see which engine starts to increase in temperature, using that engine as the engine being leaned. At this time the hottest cylinder is displayed, as a reference, along with fuel flow per hour. As the mixture is leaned, a column on the EDM-760 will begin blinking, indicating the exhaust gas temperature for that cylinder has peaked. Continue with the leaning procedure as recommended by the aircraft manufacturer while monitoring the primary engine instruments and the EDM-760 display. Depressing the LF button while the column is flashing will show the peak digital EGT value. Once the leaning procedure has been completed, depress the Step button briefly to exit the Lean Find Mode and enter the Monitor Mode. If you have the fuel flow option installed, set the mode switch to FF to monitor fuel burned per hour, fuel used, fuel remaining, and if the EDM-760 is connected to a GPS, fuel required to next way point is displayed. When the EDM-760 is first turned on with the fuel flow option, it will ask if you have filled the tanks

(Tank size preset) or how much fuel was added. If no response to fuel question in 5 minutes, system will assume no fuel added.

19) EDM-760 SPECIFICATIONS and LIMITATIONS
FACTORY LIMITS
EGT	(Exhaust Gas Temp.,K ,Max. limit 2500 oF)	1650 oF
CHT	(Cylinder Head Temp., J/K Max. limit 600 oF)	450 oF
TIT	(Turbine Inlet Temperature, K, Max. limit 2500 oF)	1650 oF
TIT-2 (Turbine Inlet Temperature, K, Max. limit 2500 oF)		1650 oF
OIL	(Oil temperature if not TIT-2, K, Max. limit 600 oF)	(Hi/Lo) 230/90 oF
OAT	(Outside Air Temp., K, Limit -40 to 300 oF)	-60 o/minute
CLD	(Rate of change of CHT)
DIF	(Maximum EGT differential)	500 oF
BAT	(Voltage, 0 to 40 volts.)	15.5/12.0 or 31.0/24.0 Hi/Lo
GPH (in Gal, lit, lbs, per hour) Fuel flow does not comply with TSO-C44
USD (Fuel Used) (999.9 gal. 9999 L/Lbs/Kg)		Low alert: fuel=10 gal.
REM (Remaining in Hours and minutes)		Low alert: Time= 45 min

REQ (Required to dest., GPS format NMEA 183/Binary/Aviation.) No limit

Operate and lean the engine in accordance with the manufacturers' recommendations for different power settings. Lycoming recommends running peak EGT only at 75% power or less. Continental recommends running peak EGT at 65% power or less.