Operating and Installation Instructions

Important Installation Information Important Installation Information Important Installation Information Important Installation Information Important Installation Information 1218121 1. Leave slack in the cable to allow for engine movement and vibration. All steps All steps All steps All steps All steps must must must must must be read before installing a probe. be read before installing a probe. be read before installing a probe. be read before installing a probe. be read before installing a probe. F E 2. Do Not Overtighten. Over time, tight wire wraps will cause the wire to break. Hose Clamp. S.S. Washer. 3. Both clip rings must be on the inside of the hose clamp. The rubber band is used to hold the washer on during shipping. 4. The Type-K thermocouple wire's yellow and red insulation must be stripped 3/8" for proper overlap in the OLC-1 (Over-Lap Con- nector). Back out the set screw, insert wires into opposite ends (matching colors) so wire insulation is just inside the nylon housing and the ends of the wires are not exposed on the opposite side. Tighten the set screw until the set screw stops turning and the hex driver starts to flex (4-5 in-lbs). Tug on the wires (1-2 lbs) to insure proper connection. P-110 Standard EGT Probe Drill 13/64" Hole (See II Manual) Important Installation Information Important Installation Information Important Installation Information Important Installation Information Important Installation Information 1218122 1. Leave slack in the cable to allow for engine movement and vibration. All steps All steps All steps All steps All steps must must must must must be read before installing a probe. be read before installing a probe. be read before installing a probe. be read before installing a probe. be read before installing a probe. F E 2. Do Not Overtighten. Over time, tight wire wraps will cause the wire to break. Hose Clamp. 3. The slit in the ferrule must be placed perpendicular to the hose clamp band and the spring must be 3/8" back from the ferrule. If the probe is placed in a hole larger than 0.130", use a S.S. washer between the exhaust pipe and the ferrule. 4. The Type-K thermocouple wire's yellow and red insulation must be stripped 3/8" for proper overlap in the OLC-1 (Over-Lap Con- nector). Back out the set screw, insert wires into opposite ends (matching colors) so wire insulation is just inside the nylon housing and the ends of the wires are not exposed on the opposite side. Tighten the set screw until the set screw stops turning and the hex driver starts to flex (4-5 in-lbs). Tug on the wires (1-2 lbs) to insure proper connection. P-110 Fast Response EGT Probe Drill 0.130" Hole (See II Manual) 3/8" Contents Contents Contents Contents Contents Warranty --------------------------------------------------------------------------- Warranty --------------------------------------------------------------------------- Warranty --------------------------------------------------------------------------- Warranty --------------------------------------------------------------------------- Warranty --------------------------------------------------------------------------- 2 22 22 Operating Instructions ------------------------------------------------- Operating Instructions ------------------------------------------------- Operating Instructions ------------------------------------------------- Operating Instructions ------------------------------------------------- Operating Instructions ------------------------------------------------- 3 33 33 Features --------------------------------------------------------------------------------------------- 3 EGTs ------------------------------------------------------------------------------------------------- 4 CHTs ------------------------------------------------------------------------------------------------- 7 Carburetor Temperature ----------------------------------------------------------------------- 8 Outside Air Temperature ---------------------------------------------------------------------- 8 Installation Instructions ------------------------------------------------ Installation Instructions ------------------------------------------------ Installation Instructions ------------------------------------------------ Installation Instructions ------------------------------------------------ Installation Instructions ------------------------------------------------ 9 99 99 1. Important Information and Initial Check Out --------------------------------------- 9 2. CHT Probe Installation ------------------------------------------------------------------- 10 3. EGT Probe Installation -------------------------------------------------------------------- 10 4. Carb. Temp. Probe Installation ---------------------------------------------------------- 10 5. OAT Probe Installation ------------------------------------------------------------------- 11 6. Route the Extension Cables -------------------------------------------------------------- 11 7. Hook Up Connecting Wires --------------------------------------------------------------- 12 8. Connect and Install the Instrument and/or Remote Switch ------------------------- 12 9. System Ground Test ------------------------------------------------------------------------- 13 Troubleshooting Suggestions ----------------------------------------- Troubleshooting Suggestions ----------------------------------------- Troubleshooting Suggestions ----------------------------------------- Troubleshooting Suggestions ----------------------------------------- Troubleshooting Suggestions ----------------------------------------- 1 3 1 3 1 3 1 3 1 3 1. Instrument Check Out --------------------------------------------------------------------- 13 2. Probe Check Out --------------------------------------------------------------------------- 13 3. Extension Cable Check Out -------------------------------------------------------------- 13 Specifications and Operating Features ----------------------------- Specifications and Operating Features ----------------------------- Specifications and Operating Features ----------------------------- Specifications and Operating Features ----------------------------- Specifications and Operating Features ----------------------------- 1 5 1 5 1 5 1 5 1 5 Instrument Wiring Diagram ------------------------------------------ Instrument Wiring Diagram ------------------------------------------ Instrument Wiring Diagram ------------------------------------------ Instrument Wiring Diagram ------------------------------------------ Instrument Wiring Diagram ------------------------------------------ 1 6 1 6 1 6 1 6 1 6 Remote Switch Diagram Remote Switch Diagram Remote Switch Diagram Remote Switch Diagram Remote Switch Diagram (RS-4-1, RS-4-2, RS-6-1, and RS-6-2) (RS-4-1, RS-4-2, RS-6-1, and RS-6-2) (RS-4-1, RS-4-2, RS-6-1, and RS-6-2) (RS-4-1, RS-4-2, RS-6-1, and RS-6-2) (RS-4-1, RS-4-2, RS-6-1, and RS-6-2) ----- ----- ----- ----- ----- 1 7 1 7 1 7 1 7 1 7 Remote Switch Diagram Remote Switch Diagram Remote Switch Diagram Remote Switch Diagram Remote Switch Diagram (RS-8-1 and RS-12-1) (RS-8-1 and RS-12-1) (RS-8-1 and RS-12-1) (RS-8-1 and RS-12-1) (RS-8-1 and RS-12-1) ----------------------- ----------------------- ----------------------- ----------------------- ----------------------- 1 8 1 8 1 8 1 8 1 8 STC Information -------------------------------------------------------- STC Information -------------------------------------------------------- STC Information -------------------------------------------------------- STC Information -------------------------------------------------------- STC Information -------------------------------------------------------- 1 9 1 9 1 9 1 9 1 9 1 2 W W W W War ar ar ar arranty / ranty / ranty / ranty / ranty / Agr Agr Agr Agr Agreement eement eement eement eement Electronics International Inc. warrants this instrument and system components to be free from defects in materials and workmanship for a period of one year from the user invoice date. Electronics Interna- tional Inc. will repair or replace any item under the terms of this Warranty provided the item is returned to the factory prepaid. 1. This Warranty shall not apply to any product that has been repaired or altered by any person other than Electronics International Inc., or that has been subjected to misuse, accident, incorrect wiring, negligence, improper or unprofessional assembly or improper installation by any person. This warranty This warranty This warranty This warranty This warranty does not cover any reimbursement for any personís time for installation, removal, assembly or repair. does not cover any reimbursement for any personís time for installation, removal, assembly or repair. does not cover any reimbursement for any personís time for installation, removal, assembly or repair. does not cover any reimbursement for any personís time for installation, removal, assembly or repair. does not cover any reimbursement for any personís time for installation, removal, assembly or repair. Electronics International retains the right to determine the reason or cause for warranty repair. 2. This warranty does not extend to any machine, vehicle, boat, aircraft or any other device to which the Electronics International Inc. product may be connected, attached, interconnected or used in conjunction with in any way. 3. The obligation assumed by Electronics International Inc. under this warranty is limited to repair, replacement or refund of the product, at the sole discretion of Electronics International Inc. 4. Electronics International Inc. is not liable for expenses incurred by the customer or installer due to factory updates, modifications, improvements, upgrades, changes, or any other alterations to the product that may affect the form, fit, function or operation of the product. 5. Personal injury or property damage do to misinterpretation or lack of understanding this product is solely the pilots responsibility. The pilot must must must must must understand the operation of this product before flying the aircraft. Do not allow anyone to operate the aircraft that does not know the operation of this product. Keep the Operating Manual in the aircraft at all times. 6. E. I. Inc. is not responsible for shipping charges or damages incurred under this Warranty. 7. No representative is authorized to assume any other liability for Electronics International Inc. in connection with the sale of Electronics International Inc. products. 8. If you do not agree to and accept the terms of this warranty, you may return the product for a If you do not agree to and accept the terms of this warranty, you may return the product for a If you do not agree to and accept the terms of this warranty, you may return the product for a If you do not agree to and accept the terms of this warranty, you may return the product for a If you do not agree to and accept the terms of this warranty, you may return the product for a refund. refund. refund. refund. refund. This Warranty is made only to the original user. THIS WARRANTY IS IN LIEU OF ALL OTHER THIS WARRANTY IS IN LIEU OF ALL OTHER THIS WARRANTY IS IN LIEU OF ALL OTHER THIS WARRANTY IS IN LIEU OF ALL OTHER THIS WARRANTY IS IN LIEU OF ALL OTHER WARRANTIES OR OBLIGATIONS: EXPRESS OR IMPLIED. MANUFACTURER EXPRESSLY WARRANTIES OR OBLIGATIONS: EXPRESS OR IMPLIED. MANUFACTURER EXPRESSLY WARRANTIES OR OBLIGATIONS: EXPRESS OR IMPLIED. MANUFACTURER EXPRESSLY WARRANTIES OR OBLIGATIONS: EXPRESS OR IMPLIED. MANUFACTURER EXPRESSLY WARRANTIES OR OBLIGATIONS: EXPRESS OR IMPLIED. MANUFACTURER EXPRESSLY DISCLAIMS ALL IMPLIED WARRANTIES OF MERCHANTABILITY OR FITNESS FOR A DISCLAIMS ALL IMPLIED WARRANTIES OF MERCHANTABILITY OR FITNESS FOR A DISCLAIMS ALL IMPLIED WARRANTIES OF MERCHANTABILITY OR FITNESS FOR A DISCLAIMS ALL IMPLIED WARRANTIES OF MERCHANTABILITY OR FITNESS FOR A DISCLAIMS ALL IMPLIED WARRANTIES OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE. PURCHASER AGREES THAT IN NO EVENT SHALL MANUFAC- PARTICULAR PURPOSE. PURCHASER AGREES THAT IN NO EVENT SHALL MANUFAC- PARTICULAR PURPOSE. PURCHASER AGREES THAT IN NO EVENT SHALL MANUFAC- PARTICULAR PURPOSE. PURCHASER AGREES THAT IN NO EVENT SHALL MANUFAC- PARTICULAR PURPOSE. PURCHASER AGREES THAT IN NO EVENT SHALL MANUFAC- TURER BE LIABLE FOR SPECIAL, INCIDENTAL OR CONSEQUENTIAL DAMAGES, IN- TURER BE LIABLE FOR SPECIAL, INCIDENTAL OR CONSEQUENTIAL DAMAGES, IN- TURER BE LIABLE FOR SPECIAL, INCIDENTAL OR CONSEQUENTIAL DAMAGES, IN- TURER BE LIABLE FOR SPECIAL, INCIDENTAL OR CONSEQUENTIAL DAMAGES, IN- TURER BE LIABLE FOR SPECIAL, INCIDENTAL OR CONSEQUENTIAL DAMAGES, IN- CLUDING LOST PROFITS OR LOSS OF USE OR OTHER ECONOMIC LOSS. EXCEPT AS CLUDING LOST PROFITS OR LOSS OF USE OR OTHER ECONOMIC LOSS. EXCEPT AS CLUDING LOST PROFITS OR LOSS OF USE OR OTHER ECONOMIC LOSS. EXCEPT AS CLUDING LOST PROFITS OR LOSS OF USE OR OTHER ECONOMIC LOSS. EXCEPT AS CLUDING LOST PROFITS OR LOSS OF USE OR OTHER ECONOMIC LOSS. EXCEPT AS EXPRESSLY PROVIDED HEREIN, MANUFACTURER DISCLAIMS ALL OTHER LIABILITY EXPRESSLY PROVIDED HEREIN, MANUFACTURER DISCLAIMS ALL OTHER LIABILITY EXPRESSLY PROVIDED HEREIN, MANUFACTURER DISCLAIMS ALL OTHER LIABILITY EXPRESSLY PROVIDED HEREIN, MANUFACTURER DISCLAIMS ALL OTHER LIABILITY EXPRESSLY PROVIDED HEREIN, MANUFACTURER DISCLAIMS ALL OTHER LIABILITY TO PURCHASER OR ANY OTHER PERSON IN CONNECTION WITH THE USE OR PERFOR- TO PURCHASER OR ANY OTHER PERSON IN CONNECTION WITH THE USE OR PERFOR- TO PURCHASER OR ANY OTHER PERSON IN CONNECTION WITH THE USE OR PERFOR- TO PURCHASER OR ANY OTHER PERSON IN CONNECTION WITH THE USE OR PERFOR- TO PURCHASER OR ANY OTHER PERSON IN CONNECTION WITH THE USE OR PERFOR- MANCE OF MANUFACTURERíS PRODUCTS, INCLUDING SPECIFICALLY LIABILITY IN MANCE OF MANUFACTURERíS PRODUCTS, INCLUDING SPECIFICALLY LIABILITY IN MANCE OF MANUFACTURERíS PRODUCTS, INCLUDING SPECIFICALLY LIABILITY IN MANCE OF MANUFACTURERíS PRODUCTS, INCLUDING SPECIFICALLY LIABILITY IN MANCE OF MANUFACTURERíS PRODUCTS, INCLUDING SPECIFICALLY LIABILITY IN TORT. TORT. TORT. TORT. TORT. Operating Instructions Operating Instructions Operating Instructions Operating Instructions Operating Instructions Features Features Features Features Features OPERA OPERA OPERA OPERA OPERATING INSTR TING INSTR TING INSTR TING INSTR TING INSTRUCTIONS UCTIONS UCTIONS UCTIONS UCTIONS Features Features Features Features Features 1. 1. 1. 1. 1. Instruments Instruments Instruments Instruments Instruments The Electronics International line of single and multi-channel instruments offer the following features: A. A. A. A. A. Digital Display - Digital Display - Digital Display - Digital Display - Digital Display - The digital display allows you to read absolute temperatures at a glance. It does not require interpretation of dials or tic marks. In a short period of time you will be come familiar with the normal operating temperatures of your engine. Abnormal temperatures will be easy to spot. The digital display is easily viewable in direct sunlight. If the instrument backlight has been permanently powered up (as recommended), the digital display will be easier to see during low ambient light condi- tions and at night. B. B. B. B. B. 1 Degree Resolution - 1 Degree Resolution - 1 Degree Resolution - 1 Degree Resolution - 1 Degree Resolution - The digital display resolves temperatures to 1 degree. This allows you to interpret trends quickly. This can be very helpful in diagnosing problems and leaning your engine. Also, any unit may be ordered to display in degrees F or degrees C. C. C. C. C. C. 1/2% Accuracy - 1/2% Accuracy - 1/2% Accuracy - 1/2% Accuracy - 1/2% Accuracy - Electronics International instruments are not affected by shake, shock, vibration, tilt, stick-slip, bearing wear, spring wear, lead resistance, probe resistance, magnetic fields or the many other factors that plague analog instrument accuracy. All E.I. instruments are temperature compensated to read cabin temperature when a probe is discon- nected. E.I. instruments should never need recalibration. 3 Selector Switch. Digital Display. Ice Zone Warning Light. Only available on the Carb. Temp/OAT instruments. D. D. D. D. D. Flexibility - Flexibility - Flexibility - Flexibility - Flexibility - Electronics International instruments are compatible with any type K ungrounded probe. This means any instrument, regardless of what is printed on the front panel (EGT, CHT, OAT, etc.), will work with any of our probes (i.e., an OAT channel can read EGT or CHT probes accurately). Also, lead resistance does not affect the accuracy of these units. You may use any length extension cable between the unit and the probe withoutaffecting the accuracy of the instrument. E. Upgradable - E. Upgradable - E. Upgradable - E. Upgradable - E. Upgradable - Any single channel EGT and/or CHT unit may be upgraded to a full multi-channel analyzer by simply adding a remote switch to the system. The instruments, remote switches, extension cables and probes were designed in a modular fashion with slip-on connectors. This means a remote switch may be added to your existing system by simply mounting it into your instrument panel, installing the additional wires and probes and plugging it in. You do not have to buy a new system to upgrade to a full analyzer. EGTs EGTs EGTs EGTs EGTs Operating Instructions Operating Instructions Operating Instructions Operating Instructions Operating Instructions 4 2. 2. 2. 2. 2. Remote Switches Remote Switches Remote Switches Remote Switches Remote Switches A remote switch may be connected to any channel on any Electronics International Instrument. This gives the instrument multi-channel capa- bility. There are two types of remote switches available, single deck and double deck. If a single deck four channel remote switch (RS-4-1) is connected to the EGT channel on an EC-1, the instrument would be capable of measuring four EGTs and one CHT. The remote switch will select which EGT channel would be isplayed on the EC-1 instrument when the instrument's selector switch is placed in the EGT position. If a double deck four channel remote swithc (RS-4-2) is connect to the EGT and CHT channels on an EC-1, the instrument will be capable of measur- ing four EGTs and four CHTs. The EC-1 will select whether EGT or CHT will be displayed. The Remote Switch will select which channel will be displayed. EGTs EGTs EGTs EGTs EGTs 1. 1. 1. 1. 1. Leaning Leaning Leaning Leaning Leaning You will want to lean your engine in cruise. A rich running engine wastes fuel needlessly and tends to run rough. This creates vibration, which causes deterioration of engine accessories and engine mounts. Also, proper leaning at cruise and during descent means less spark plug fouling, longer life for the plugs, reduced maintenance costs and considerable fuel savings. Furthermore, good leaning techniques result in cleaner combustion chambers with fewer lead salt deposits on the pistons and exhaust valves. Under certain conditions, these deposits invite preignition and higher maintenance costs. Proper leaning at cruise during cool or cold weather aids in raising engine and oil temperatures to desireable minimums in order to evaporate the water and acids out of the oil. Water and acids attack the insides of an engine, causing rust and corrosion. To properly lean your engine using a multi-channel analyzer perform the following steps: A. Rough Leaning: A. Rough Leaning: A. Rough Leaning: A. Rough Leaning: A. Rough Leaning: Select the hottest EGT cylinder. Adjust the mixture control from the full rich position to a leaner setting that results in a slight drop in engine RPM or to a setting near peak EGT, as dictated by experience. The mixture control should be left at this setting until the EGTís stabilize. It will take about 20 seconds for the temperatures to stabilize within 1∞F. This lag is due to the combustion walls and piston domes increasing in temperature, which affect the combustion and exhaust gas temperatures. To correctly lean an engine you To correctly lean an engine you To correctly lean an engine you To correctly lean an engine you To correctly lean an engine you must wait for the engine to thermally stabilize must wait for the engine to thermally stabilize must wait for the engine to thermally stabilize must wait for the engine to thermally stabilize must wait for the engine to thermally stabilize. Less sensitive gauges will not pick up these subtle changes, which are important in leaning and diagnosing problems. B. Precision Leaning: B. Precision Leaning: B. Precision Leaning: B. Precision Leaning: B. Precision Leaning: Again select the hottest EGT cylinder. This cylinder may be differ- ent than the one you started with. This is the cylinder on which you should perform your precision leaning. Again, start leaning, making only very small adjustments and waiting 3 to 5 seconds between adjustments. As you approach peak, the exhaust gas temperature will rise much slower until it starts to decrease. When this happens you have reached peak EGT. The Instrument displaying EGT for channel #2. 5 EGTs EGTs EGTs EGTs EGTs Operating Information Operating Information Operating Information Operating Information Operating Information 1∞F resolution of the digital display will be invaluable in helping you precisely detect peak EGT. C. Finding The Cylinder That Peaks First: C. Finding The Cylinder That Peaks First: C. Finding The Cylinder That Peaks First: C. Finding The Cylinder That Peaks First: C. Finding The Cylinder That Peaks First: For most engines Step B (Precision Leaning) will result in a properly leaned engine. If you find this to be the case with your engine, this step will not be necessary. But if you want to verify that you have leaned to the cylinder that peaked first and your engine is operating properly, perform the following with the cylinder found in step B at peak EGT. Slightly enrich the mixture and quickly step through each cylinder. Any cylinder that shows a rising temperature is a leaner cylinder. Check that this cylinder does not rise more than 15∞F before it starts decreasing in temperature. If a cylinder rises more than 15∞F it may have a problem. When installing a single channel EGT instrument in an aircraft there is no guarantee that the probe is installed on the leanest cylinder. Every engine operates a little differently. For the same make and model of engine installed in the same type of aircraft there can be differences between the leanest cylinders. Furthermore, there can be a difference between operating temperatures and the temperature spread between cylinders. Every engine has its own unique operating tempera- tures. To properly lean your engine using a single channel EGT unit using a single channel EGT unit using a single channel EGT unit using a single channel EGT unit using a single channel EGT unit perform the following steps: A. Rough Leaning: A. Rough Leaning: A. Rough Leaning: A. Rough Leaning: A. Rough Leaning: Adjust the mixture control from the full rich position to a leaner setting that results in a slight drop in engine RPM or to a setting near peak EGT, as dictated by experience. The mixture control should be left at this setting until the EGTís stabilize. It will take about 20 seconds for the temperatures to stabilize within 1∞F. This lag is due to the combustion walls and piston domes increasing in temperature and, therefore, affecting the combustion and exhaust gas temperatures. To correctly lean an engine you must wait To correctly lean an engine you must wait To correctly lean an engine you must wait To correctly lean an engine you must wait To correctly lean an engine you must wait for the engine to thermally stabilize for the engine to thermally stabilize for the engine to thermally stabilize for the engine to thermally stabilize for the engine to thermally stabilize. Less sensitive gauges will not pick up these subtle changes, which are important in leaning and diagnosing problems. B. Precision Leaning: B. Precision Leaning: B. Precision Leaning: B. Precision Leaning: B. Precision Leaning: Again, start leaning, making only very small adjustments and waiting 3 to 5 seconds between adjustments. As you approach peak the exhaust gas tempera- ture will rise much slower until it starts to decrease. When this happens you have reached peak EGT. The 1∞F resolution of the digital display will be invaluable in helping you precisely detect peak EGT. You will then need to enrichen the mixture for an EGT reading 30∞F lower than peak to insure there is no cylinder operating on the lean side of peak EGT. If your engine runs rough before peak EGT is reached, note the temperature reading on the EGT instrument. When an engine starts to run rough (not when it loses power, but actually runs rough) the leanest cylinder has gone past peak EGT by 30 to 50 degrees F. The leanest cylinder is lean misfiring causing the engine to run rough. From this point enrichen the mix- ture to obtain a 50 degrees F lower EGT from the noted temperature. This will set the leanest cylinder slightly on the rich side of peak EGT. The rest of the cylinders will be running richer than the leanest by an amount dictated by the temperature spread for your engine. With this method you can reasonably lean an engine even when the probe has not been mounted on the leanest cylinder. Electronics International's unique stable display allows you to precisely lean to peak EGT or to a specific temperature below peak for most engines. Peak EGT with a float-type carbureted engine is frequently a vague point because of the fuel/air distribution issues in these lower horsepower Operating Information Operating Information Operating Information Operating Information Operating Information 6 EGTs EGTs EGTs EGTs EGTs engines. As a result, these engines tend to operate smoother at 25∞F on the rich side of peak EGT. Fuel-injected engines will provide a more precise peak. Most engines normally operate within an EGT range of 1300∞F to 1600∞F at cruise power. Some engine manufacturers allow leaning to peak EGT at 75% power and below on their direct drive normally aspirated engines. For your engine, check the engine manufacturerís For your engine, check the engine manufacturerís For your engine, check the engine manufacturerís For your engine, check the engine manufacturerís For your engine, check the engine manufacturerís recommended procedures recommended procedures recommended procedures recommended procedures recommended procedures..... It is not recommended to lean to peak EGT above 75% It is not recommended to lean to peak EGT above 75% It is not recommended to lean to peak EGT above 75% It is not recommended to lean to peak EGT above 75% It is not recommended to lean to peak EGT above 75% power settings power settings power settings power settings power settings..... The richer mixture is needed to cool the combustion temperatures and keep the anti-knock capability of the fuel high enough to prevent detonation from occurring at the higher power settings. 2. 2. 2. 2. 2. EGT Diagnostics EGT Diagnostics EGT Diagnostics EGT Diagnostics EGT Diagnostics Since the EGT is directly related to the combustion temperature, it is an indication of the engineís ability to produce power. If the engine is not producing the correct amount of power, the EGT instrument can be a very valuable troubleshooting tool as well an early warning system before engine failure occurs. With 1∞F resolution, our digital EGT instruments will react to the slightest changes in the combustion process. To detect a problem, become familiar with your engineís normal EGT readings during run-up, climb, cruise and descent. Any difference from the norm can be a sign of trouble. During normal operation the EGT will stabilize to 1∞F for a given throttle and mixture setting. If it does not stabilize, this can also be the first sign of trouble. With rate and trend information being displayed instantaneously and with temperatures being read to 1∞F, few problems can escape the pilot flying one of Electronics Internationalís analyzer systems. The following is a list of EGT/ CHT symptoms and possible problems: Symptom Possible Problem One EGT reads abnormally high. The corre- sponding CHT reads lower than normal. Burned valve or broken ring, defective plug, plug wire or mag. One EGT reads abnormally high. The corre- sponding CHT reads higher than normal. Plugged injector, intake leak. One EGT reads abnormally low. Over-sized injector, restricted exhaust, broken or leaky exhaust header. High CHTs and/or high EGTs on all cylinders. Excessive leaning with power settings over 75%. Detonation due to bad fuel. Closed or restricted cowl flaps. Missing or loose baffling. High EGTs and/or low CHTs on all channels. Jumpy readings on one channel. This is not an engine problem. Check all connections and the probe for proper opera- tion. See Troubleshooting Section of this manual. Timing problem or defective mag. Operating Information Operating Information Operating Information Operating Information Operating Information 7 CHTs CHTs CHTs CHTs CHTs It is not necessary to continually monitor the EGTs in order to detect a problem. Most problems worsen over a period of time and can be easily detected before they become a safety hazard by thoroughly checking the EGT readings at run-up and once or twice during a flight. CHTs CHTs CHTs CHTs CHTs 1. 1. 1. 1. 1. CHT Operation CHT Operation CHT Operation CHT Operation CHT Operation The Cylinder Head Temperature (CHT) instrument helps the pilot protect his engine against the threat of excessive heat. Most general aviation aircraft monitor the hottest CHT, as determined by extensive flight tests done by the airframe manufacture. Minimum in-flight CHT should be 150∞F, and maximum in most direct drive normally aspirated Avco Lycoming engines is 500∞F. Some of the higher powered, more complex engines have a limit of 475∞F. Although these are minimum and maximum limits, the pilot should operate the engine at more reasonable tempera- tures in order to achieve the expected overhaul life of the powerplant. It would be normal during all-year operations in climb and cruise to see cylinder head temperatures in the range of 350∞F to 435∞F. Sudden cooling of the CHT (known as shock cooling) is a problem that is common with aircraft engines. This is caused by fast descents with little or no power and rich mixtures. This may result in bent pushrods due to exhaust valves sticking, burned valves, spark plug fouling, broken piston rings, cracked cylinders at the spark plug and valve ports and warped exhaust valves. To avoid these problems, do not allow the CHT to cool more rapidly than 1∞F every 3 seconds during in-flight operation. This can be easily detected with our 1∞F digital display. During climbs, the cylinder head temperatures will rise rapidly until the heat absorbed by the combustion walls is dissipated out the engineís cooling fins. At this point, the CHT will stabilize. Any change in throttle, mixture, cowl or airspeed will affect the CHT and the rate at which it will change. Since rate and trend information can be easily interpreted from our digital display, changing any one of these parameters to stabilize, slow or reduce the CHT is possible with almost immediate results. Our digital instrument takes the guesswork out of controlling your CHT. 2. 2. 2. 2. 2. CHT Diagnostics CHT Diagnostics CHT Diagnostics CHT Diagnostics CHT Diagnostics The source of heat in an engine is from the combustion of the fuel/air mixture producing temperatures of approximately 4000∞F. Some of this heat energy goes into heating the cylinder heads through radiation and conduction. This heat is sinked away from the engine by the air flow over the cylinder heads. When the heat being generated in the cylinder heads equalizes with the heat being sinked away, the cylinder head temperature will stabilize. If a problem arises in the combustion chamber or in the ability of the cooling system to sink away heat, the CHTs will be affected. To detect a problem, become familiar with your engineís CHT operating temperatures during run-up, climb, cruise and descent. Any differences from normal can be a sign of trouble. 8 Carburetor Temperature Carburetor Temperature Carburetor Temperature Carburetor Temperature Carburetor Temperature Operating Information Operating Information Operating Information Operating Information Operating Information Continuous change in the CHT can also be a sign of trouble. Because of the large thermal mass of the engine, the CHTs change slowly after the initial climb. Any continuous change in one or all of the CHTs after this initial climb can be the sign of trouble. The rate and trend of this change can easily be detected with Electronics Internationalís 1∞F resolution digital display. This information allows the pilot to make changes in flight attitude or engine operation and see the effects almost instantaneously. Carbur Carbur Carbur Carbur Carburetor etor etor etor etor T T T T Temperatur emperatur emperatur emperatur emperature e e e e Venturi affect and atomization of fuel can cause temperatures in the carburetor to drop 30∞F or more. When the atmospheric conditions are right for the aircraft's current flight altitude (moder- ate to high humidity), the moisture in the carburetor venturi can freeze quickly. Within minutes ice can choke off the venturi and the engine will stop with little warning. When Carb. Temp. is selected on the Electronics International Carb. Temp. instrument, the carburetor temperature is continuously monitored and the ìIce Zoneî warning light over the display is activated for that channel. The ìIce Zoneî warning light is only active for the channel selected. At 39∞F (before ice can form in the venturi of the carburetor) the ìIce Zoneî warning light will light up. When this happens, apply carburetor heat, making small adjustments to bring the carburetor temperature above 39∞F, thereby avoiding any possible carburetor icing condition. An additional benefit of running carburetor temperatures 9∞F above freezing is improved atomization of the fuel which results in fewer lead deposits, cleaner plugs and better economy. If the carburetor temperature is below 10∞F the ìIce Zoneî warning light will go off. Below 10∞F there is not enough moisture in the air to form ice in the carburetor. The ìIce Zoneî warning light has the advantage of catching your attention without having to continuously monitor the unit. At night this light may be too bright. An LED Intensity Control Line is provided which may be connected to the aircraft panel rheostat. When the instrument panel lights are turned up the ìIce Zoneî warning light will dim. Monitoring carburetor temperature to 1∞F can also help with hard to start engines. If the engine becomes flooded and fuel starts to drip from the carburetor, the unit will display a drop in carbu- retor temperature as the fuel starts to evaporate. If the engine backfires and a fire starts in the venturi, the unit will display a rapid rise in the carburetor temperature. The carburetor probe is rated for 700∞F, so probe damage is not likely. Outside Outside Outside Outside Outside Air Air Air Air Air T T T T Temperatur emperatur emperatur emperatur emperature e e e e The Electronics International OAT instrument has three features that make it a valuable tool when measuring outside air temperatures. The first of these features is its superior accuracy and linearity over conventional gauges. Outside air temperatures have a big affect on your aircraftís ability to lift Installation Instructions Installation Instructions Installation Instructions Installation Instructions Installation Instructions Important Information Important Information Important Information Important Information Important Information 9 and on engine horsepower. Accurate OAT readings are essential if you are looking for maximum performance from your aircraft. The second valuable feature is the instrument's ability to detect small temperature changes (1∞F). This gives the pilot rate and trend information (in what direction and how fast the temperatures are changing) at a glance. This is valuable for detecting changing atmospheric conditions and avoiding thunderstorms and icing conditions. It can also help to find cooler flying conditions in warm weather. The third feature is the instrument's Ice Zone Warning Light. This light will come on when the OAT drops to 39∞F and stays above 10∞F. This feature can be very useful to a pilot by warning him of the possibility of structural ice if weather conditions are right. The Electronics International OAT instrument resolves outside air temperatures to 1∞F and is very sensitive to air temperatures changes. For this reason, when the OAT probe is in still air and near a heat source, such as hot asphalt, a hangar heater, etc., the unit will read the actual tem- perature to which the probe is subjected. When the engine starts and there is a flow to air over the probe, the unit will read the air temperature accurately and display changes quickly. INST INST INST INST INSTALLA ALLA ALLA ALLA ALLATION INSTR TION INSTR TION INSTR TION INSTR TION INSTRUCTIONS UCTIONS UCTIONS UCTIONS UCTIONS 1. 1. 1. 1. 1. Important Information and Initial Check Out Important Information and Initial Check Out Important Information and Initial Check Out Important Information and Initial Check Out Important Information and Initial Check Out A. A. A. A. A. The installer and aircraft owner must read the Warranty before starting the The installer and aircraft owner must read the Warranty before starting the The installer and aircraft owner must read the Warranty before starting the The installer and aircraft owner must read the Warranty before starting the The installer and aircraft owner must read the Warranty before starting the installation. installation. installation. installation. installation. There is information in the Warranty that may alter your decision to install this instrument. If you do not accept the terms of the Warranty, do not install this instru- If you do not accept the terms of the Warranty, do not install this instru- If you do not accept the terms of the Warranty, do not install this instru- If you do not accept the terms of the Warranty, do not install this instru- If you do not accept the terms of the Warranty, do not install this instru- ment. ment. ment. ment. ment. B. B. B. B. B. If you are not an FAA Certified Aircraft Mechanic familiar with the issues of installing aircraft EGT, CHT, Carb Temp and/or OAT instruments, Do Not attempt to install this instrument. The installer should use current aircraft standards and practices to install this instrument (refer to AC 43.13). C. C. C. C. C. Check that any necessary FAA Approvals (STC's, etc.) are available for your Check that any necessary FAA Approvals (STC's, etc.) are available for your Check that any necessary FAA Approvals (STC's, etc.) are available for your Check that any necessary FAA Approvals (STC's, etc.) are available for your Check that any necessary FAA Approvals (STC's, etc.) are available for your aircraft before starting the installation. STC's are located at the back of this aircraft before starting the installation. STC's are located at the back of this aircraft before starting the installation. STC's are located at the back of this aircraft before starting the installation. STC's are located at the back of this aircraft before starting the installation. STC's are located at the back of this manual. manual. manual. manual. manual. D. D. D. D. D. Read the entire Installation Instructions and resolve any issues you may have before starting the installa- tion. This may eliminate any delays once the installation is started. E. E. E. E. E. THIS INSTALLATION MAY REQUIRE SOME PARTS UNIQUE TO YOUR AIR- THIS INSTALLATION MAY REQUIRE SOME PARTS UNIQUE TO YOUR AIR- THIS INSTALLATION MAY REQUIRE SOME PARTS UNIQUE TO YOUR AIR- THIS INSTALLATION MAY REQUIRE SOME PARTS UNIQUE TO YOUR AIR- THIS INSTALLATION MAY REQUIRE SOME PARTS UNIQUE TO YOUR AIR- CRAFT THAT ARE NOT SUPPLIED IN THE KIT. CRAFT THAT ARE NOT SUPPLIED IN THE KIT. CRAFT THAT ARE NOT SUPPLIED IN THE KIT. CRAFT THAT ARE NOT SUPPLIED IN THE KIT. CRAFT THAT ARE NOT SUPPLIED IN THE KIT. Acquire all the parts necessary to install this instrument before starting the installation. F. F. F. F. F. Check that the instrument make and model are correct before starting the installation. Installation Instructions Installation Instructions Installation Instructions Installation Instructions Installation Instructions 10 Probe Installation Probe Installation Probe Installation Probe Installation Probe Installation G. G. G. G. G. Before starting the installation make sure the unit will fit in the location you intend to install it without obstructing the operation of any controls. H. H. H. H. H. If this instrument is to replace an existing unit in the aircraft, it is the installer's responsibility to move or replace any existing instruments or components in accordance with FAA approved methods and procedures. The following Installation Instructions do not cover moving or the removal of any existing instruments or components. 2. 2. 2. 2. 2. CHT Probe Installation CHT Probe Installation CHT Probe Installation CHT Probe Installation CHT Probe Installation A single CHT probe should be placed on the hottest cylinder. In a 6-cylinder engine this would be one of the center cylinders. On a 4-cylinder engine this would be one of the back cylinders. If a second CHT probe is to be installed it should be placed on one of the front unobstructed cylinders. This will allow the unit to detect shock-cooling. Most engines have a port just below the lower spark plug for the CHT probe. If your engine If your engine If your engine If your engine If your engine has a primary CHT probe in one of the cylinders, do not remove it has a primary CHT probe in one of the cylinders, do not remove it has a primary CHT probe in one of the cylinders, do not remove it has a primary CHT probe in one of the cylinders, do not remove it has a primary CHT probe in one of the cylinders, do not remove it..... Select another cylinder for your probe. If you are putting a CHT probe on every cylinder use our P-102 Gasket CHT Probe for secondary readings on your primary cylinder. 3. 3. 3. 3. 3. EGT Probe Installation EGT Probe Installation EGT Probe Installation EGT Probe Installation EGT Probe Installation A single EGT probe should be installed in the exhaust stack of the leanest cylinder. Each engine has its own characteristics and the leanest cylinder can be different from aircraft to aircraft. As a general rule, the leanest cylinder is one of the back cylinders on a carbureted engine and one of the center cylinders on a fuel-injected engine. Look at each exhaust stack and determine the best location at which all of the EGT probes can be mounted at the same distance down from the exhaust ports. The ideal location is 1 1/2", but ease of installation should prevail. Drill a 13/64" diameter hole in each exhaust stack. Insert the probe and tighten the hose clamp. As the hose clamp is heated and cooled, it will become loose as it conforms to the exhaust stack. After the first 10 hours of operation, each hose clamp should be retightened. IMPORTANT NOTE: For Cessna 210ís or any aircraft using a slip joint in the exhaust system, install the EGT probes ABOVE OR BELOW THE SLIP JOINT. Installing a EGT probe in the slip joint can damage the probe. 4. 4. 4. 4. 4. Carb Temp Probe Installation Carb Temp Probe Installation Carb Temp Probe Installation Carb Temp Probe Installation Carb Temp Probe Installation Remove the threaded plug located in the carburetor housing just below the throttle valve. Install the Carbure- tor Temperature Probe in this hole using a lock washer. Care should be taken not to over-tighten the probe and strip the threads in the carburetor housing. If your carburetor does not have a factory tapped hole, remove the carburetor from the engine. Drill out the lead plug located just below the throttle valve with a 7/32 drill and tap this hole with a 1/4 x 28 tap. Remove all burrs and metal shavings from the interior and exterior of the carbure- tor. Install the carburetor temperature probe as outlined above. Reinstall the carburetor on the engine. 5. 5. 5. 5. 5. OAT Probe Installation OAT Probe Installation OAT Probe Installation OAT Probe Installation OAT Probe Installation Mount the OAT Probe in an appropriate location on the aircraft, using the hardware supplied. The OAT Probe is sensitive to air temperature changes. For this reason, do not mount the OAT probe in the path of the cowl or engine exiting air (i.e., on the belly of the aircraft). Also, the probe should not be mounted within 8 inches of an exhaust pipe. The radiant energy from the exhaust pipe can cause the probe to read slightly high. Other than these considerations the OAT Probe may be mounted in an air intake vent, on the side of the cowling or anywhere else on the aircraft. 6. 6. 6. 6. 6. Route the Extension Cables Route the Extension Cables Route the Extension Cables Route the Extension Cables Route the Extension Cables Mark both ends of each cable with the appropriate cylinder and/or probe type. Strip wires and connect probe to extension cable, matching wire colors, using the supplied OLC-1 (Over-Lap Connectors). When tie wrapping these cables down, be sure there is no strain or pulling on the cable against the probe housing. Each probe should have 3 to 4 inches of slack to allow the engine to move in its mount without breaking any wires. Also, there should be a tie wrap near the probe connectors. Dress each cable up to the instrument or remote switch keeping them away from any hot areas (exhaust stacks, cylinder heads, etc.). If you must shorten the cable, pull any excess cable length through the fire wall and cut it off at this time. However, it is recommended you leave some extra wire length under the instrument panel for later modifications. Varying cable lengths will not not not not not affect the accuracy of this instrument so cables of any length may be ordered from the factory. The Extension Cables and probe wires are made of type K thermocouple wire that must not be substituted or extended with regular copper wire. Also, it is important these wires not be kinked (i.e., do not bend the wires on a do not bend the wires on a do not bend the wires on a do not bend the wires on a do not bend the wires on a radius less than 1 inch radius less than 1 inch radius less than 1 inch radius less than 1 inch radius less than 1 inch). ).). ).). Connect the Extension Cables using the OLC-1 connectors as described below: A. Strip back the insulation on the two mating wires 3/8". Be careful not to nick the wires. B. Place the hex driver (0.050") in the OLC-1 set screw and back out the set screw to the last thread. C. Inset the two wires into the ends of the connector so the wire insulation is just inside the nylon housing and the ends of the wires are not exposed on the opposite side. D. Tighten the set screw until the set screw stops turning and the hex driver starts to flex (4 to 5 in.-lbs.) E. Tug on the wires (1 to 2 lbs.) to insure proper connection. 11 Probe Installation Probe Installation Probe Installation Probe Installation Probe Installation Installation Instructions Installation Instructions Installation Instructions Installation Instructions Installation Instructions Installation Instructions Installation Instructions Installation Instructions Installation Instructions Installation Instructions 12 Hook-Up Connecting Wires Hook-Up Connecting Wires Hook-Up Connecting Wires Hook-Up Connecting Wires Hook-Up Connecting Wires Tie off any excess cable under the instrument panel. Be sure these cables do not obstruct the freedom of travel of any controls. Cable length does not affect the accuracy of our units, so cables of any length may be ordered from the factory. 7. 7. 7. 7. 7. Hook-Up Connecting Wires Hook-Up Connecting Wires Hook-Up Connecting Wires Hook-Up Connecting Wires Hook-Up Connecting Wires Connect the red wire in the harness to the 12 or 24 volt bus via a 1 amp fuse or circuit breaker (see the Wiring Diagram at the back of this manual). Connect the black wire in the harness to ground. Connect the white/violet to the 12V bus (leave it open for a 24V system). Connect the white/gray wire to the 24V bus (connect to ground for a 12V system connect to ground for a 12V system connect to ground for a 12V system connect to ground for a 12V system connect to ground for a 12V system). If this unit has an "Ice Zone" warning light, connect the white/orange wire to the Panel Light Rheostat to dim the "Ice Zone" warning light at night. Tie off any excess cable under the instrument panel. Be sure these cables do not obstruct the freedom of travel of any controls. 8. 8. 8. 8. 8. Connect and Install the Instrument and/or Remote Switch Connect and Install the Instrument and/or Remote Switch Connect and Install the Instrument and/or Remote Switch Connect and Install the Instrument and/or Remote Switch Connect and Install the Instrument and/or Remote Switch Connect the extension cables and all other wires to the instrument and/or remote switch as shown in the appropriate wiring instructions at the back of this manual. Be sure the OLC-1 connec- Be sure the OLC-1 connec- Be sure the OLC-1 connec- Be sure the OLC-1 connec- Be sure the OLC-1 connec- tors are installed properly tors are installed properly tors are installed properly tors are installed properly tors are installed properly. Install the unit from behind the instrument panel using 6 x 32 screws. These screws must not be longer than 0.4 inches. Install the remote switch through a 1" square hole cut into the aircraft instrument panel. Tie wrap cables as needed. Be sure these cables do not obstruct the freedom of travel of any controls. 9. 9. 9. 9. 9. System Ground Test System Ground Test System Ground Test System Ground Test System Ground Test A . A . A . A . A . Turn the master switch on and look for a near ambient temperature reading on each channel. If the instrument does not power-up (display a reading), check the power and ground leads (red and black leads) for an open, loose or poor connection. If you suspect any channel is not receiving a signal remove the probe from the engine (leaving it connected to the Extension Cable) and apply a temperature to it. Look for an increase in reading on the display for that channel. Check the other channels for an increase in reading. You may have connected the probe to the wrong Extension Cable. If the reading is decreasing, you may have reversed the connectors on the Extension Cable leads (the yellow wire on the probe must connect to the yellow wire on the Extension Cable). B . B . B . B . B . Start the engine and check each channel for a proper reading. On the ground EGTs will read around 900∞F and CHTs will read around 200∞F. If you suspect any channel is not receiving a signal properly, see the ìTroubleshootingî section of this manual. TR TR TR TR TROUBLESHOO OUBLESHOO OUBLESHOO OUBLESHOO OUBLESHOOTING SUGGESTIONS TING SUGGESTIONS TING SUGGESTIONS TING SUGGESTIONS TING SUGGESTIONS Because high reliability is designed into Electronics Internationalís equipment, there is no reason to put up with poor operation. We have few problems with our probes, cables and units and installation is simple. Usually fixing a problem is just a matter of inspecting the installation at a few key points. Strategy Strategy Strategy Strategy Strategy If you have more than one problem, FIX ONE PROBLEM AT A TIME FIX ONE PROBLEM AT A TIME FIX ONE PROBLEM AT A TIME FIX ONE PROBLEM AT A TIME FIX ONE PROBLEM AT A TIME..... Trying to fix all of them at once can be confusing and misleading. In many cases fixing one problem first will lead you to the solution for fixing all of the problems. Therefore, take one problem on one channel and proceed with the following: 1. 1. 1. 1. 1. Instrument Check Out Instrument Check Out Instrument Check Out Instrument Check Out Instrument Check Out If there is an identical symptom on each channel, then the instrument may have a problem. But if even one channel of the instrument is operating properly, the instrument probably does not have a problem. A good method to test the instrument is to remove all the Extension Cables. Then look for a reading on all channels to be near cabin temperature. The only inputs a unit requires to operate properly and measure cabin temperature is power (red lead) and ground (black lead). Check the power and ground leads for proper connection (pull on the wire at each connector). NOTE: Few problems turn out to be the instrument. 2. 2. 2. 2. 2. Probe Check Out Probe Check Out Probe Check Out Probe Check Out Probe Check Out There are two good methods of testing a probe. Perform one or both of the following: A. A. A. A. A. A probe can be tested with an ohmmeter. Disconnect the probe from the Extension Cable. When testing the resistance between the connectors, the probe should measure a ìshortî (less than 5 ohms). When measuring from one lead (either lead) of the probe to the probe sheath (metal tip), there should be an ìopenî (10kohm or greater). B. B. B. B. B. Another method of checking a probe is to plug the suspected bad probe into a channel that is working properly. If the problem follows the probe, you have a defective probe. 3. 3. 3. 3. 3. Extension Cable Check Out Extension Cable Check Out Extension Cable Check Out Extension Cable Check Out Extension Cable Check Out With the Extension Cable connected to the unit, remove the probe from the suspected bad Exten- sion Cable. Set the unit to the proper channel and look for a near cabin temperature reading on the display. A very high or low reading indicates a short to ground in the cable. Next, connect an 13 Troubleshooting Suggestions Troubleshooting Suggestions Troubleshooting Suggestions Troubleshooting Suggestions Troubleshooting Suggestions Instrument Check Out Instrument Check Out Instrument Check Out Instrument Check Out Instrument Check Out Troubleshooting Suggestions Troubleshooting Suggestions Troubleshooting Suggestions Troubleshooting Suggestions Troubleshooting Suggestions Extention Cable Check Out Extention Cable Check Out Extention Cable Check Out Extention Cable Check Out Extention Cable Check Out 14 ohmmeter, set to 10K range, to the open probe ends of the suspected bad Extension Cable. Set the unit to the proper channel and look for a very high (+ or -) reading on the digital display. A near cabin temperature reading or no change in reading indicates an open in the cable or its connec- tors. Also, look for a reading on the ohmmeter around 12K ohms. Most problems of this kind are usually one of the following: A. A. A. A. A. Improper OLC-1 Connections: Improper OLC-1 Connections: Improper OLC-1 Connections: Improper OLC-1 Connections: Improper OLC-1 Connections: Pull on wires installed in the Over-Lap Connector to check the connection. You may have insulation in the overlap area. Remove the wires from the OLC-1 and inspect. B. B. B. B. B. Broken Wire: Broken Wire: Broken Wire: Broken Wire: Broken Wire: A wire can be broken from a too-tight tie-wrap or by repeatedly flexing the wire. Inspect the wires for a break. Note: A wire can be broken while the insulation is still intact. C. C. C. C. C. Cable Chafed to Ground: Cable Chafed to Ground: Cable Chafed to Ground: Cable Chafed to Ground: Cable Chafed to Ground: If a cable is routed around a metal object, it will over time chafe the wire and short to the object. Inspect the wires for chafing. SPECIFIC SPECIFIC SPECIFIC SPECIFIC SPECIFICA A A A ATIONS and OPERA TIONS and OPERA TIONS and OPERA TIONS and OPERA TIONS and OPERATING FEA TING FEA TING FEA TING FEA TING FEATURES TURES TURES TURES TURES S0908941 9/8/94 Models: Models: Models: Models: Models: (Temperature Monitoring Instruments) E-1, C-1, A-1, CA-1, EAC-1, EAE-1, EC-1, EC-2, E-2, C-2, E-4, C-4, E-6 and C-6. Weight: Weight: Weight: Weight: Weight: E-1, C-1, A-1, CA-1, EAC-1, EAE-1, EC-1, EC-2, E-2 and C-2 - 7 oz. (unit only) E-4 and C-4 - 7.6 oz. (unit only) E-6 and C-6 - 8.3 oz. (unit only) 6' T.C. Cable - 2 oz. EGT or CHT Probe - 1.6 oz. Environmental: Environmental: Environmental: Environmental: Environmental: Meets TSO C43a Power Requirements: Power Requirements: Power Requirements: Power Requirements: Power Requirements: 7.5 to 30 Volts, 1/10 Amp. Display: Display: Display: Display: Display: LCDís (viewable in direct sunlight), with 12 and 24 volt backlight control wires. Ice Zone Warning Light: Ice Zone Warning Light: Ice Zone Warning Light: Ice Zone Warning Light: Ice Zone Warning Light: This light comes on when the displayed temperature is between 39∞F and 10∞F. An Intensity Control Line is provided to dim this light for night operation. Display Temperature Range: Display Temperature Range: Display Temperature Range: Display Temperature Range: Display Temperature Range: 1999∞F to -1999∞F Accuracy: Accuracy: Accuracy: Accuracy: Accuracy: 1/2% in accordance with TSO C43a. Resolution: Resolution: Resolution: Resolution: Resolution: 1∞F (with enhanced stability and response circuits). Probes: Probes: Probes: Probes: Probes: Type K, Ungrounded (for improved accuracy, stability and reliability). Extension Cables: Extension Cables: Extension Cables: Extension Cables: Extension Cables: Type K, any length or size (you may use your existing type K cables). Models: Models: Models: Models: Models: (Remote Switches) RS-4-1, RS-4-2, RS-6-1, RS-6-2, RS-8-1 and RS-12-1 Weight: Weight: Weight: Weight: Weight: RS-4-1, RS-4-2, RS-6-1 and RS-8-1 - 3.2 oz. (unit only) RS-6-2 and RS-12-1 - 4.9 oz. (unit only) Environmental: Environmental: Environmental: Environmental: Environmental: Meets TSO C43a Contacts: Contacts: Contacts: Contacts: Contacts: Gold Contact Resistance: Contact Resistance: Contact Resistance: Contact Resistance: Contact Resistance: <50 milliohms Angle of Throw: Angle of Throw: Angle of Throw: Angle of Throw: Angle of Throw: 30 degrees Rotational Torque: Rotational Torque: Rotational Torque: Rotational Torque: Rotational Torque: 3.5 to 7.5 ounce-inches 15 16
    
               !  !   " # $! %  &    ' $!     # ! %  (    )  *+, -*+  .*-+ ' -
 /    
 ' "  # # % , % 0 #   1 2, 3  4 4" % $ 2, 5  4 # 4" % 67 4   4" % 67 $ 2, (  4 # .4 % 6 .47 1 2, 5  4   .4 % 6 .47 8 2, 3  4 # -94 % 6 -947  2,   4   -94 % 6 -947 *+, .+  -+ 3+  - .-+ +  - 4 -' : 4" % 67 4 -' : 4" % 67 4 -' :( 4" % 6(7 4 -' :$ 4" % 6$7 .+$, -+$, .+  -+ +  - $ 2,  (  4 -' :& 4" % .+  -+ ' 6&7  2, &  4 -' : 4" % .+  -+ ' 67 1 2, 3  4 -% 4" % 6-*7 $ 2, 5  4 )*4 "% 6)*47 -*+ 3+  - 1 2, 5  4 .4 % 6.47 8 2, 3  4 )*4 % 6)*47  2,   4 -94 % 6-947 .*-+ +  - .+  -+ 3+  - *
 1 2, 3  $ 2, (  1 2, 5  8 2, 3   2,   8( - $ 2, 5  4 .4 b 6.47 4 -94 % 6-947 .-+ 3+  - 1 2, 3  17 Remote Switch Wiring Diagram Remote Switch Wiring Diagram Remote Switch Wiring Diagram Remote Switch Wiring Diagram Remote Switch Wiring Diagram RS-4-1, RS-4-2, RS-6-1 and RS-6-2 RS-4-1, RS-4-2, RS-6-1 and RS-6-2 RS-4-1, RS-4-2, RS-6-1 and RS-6-2 RS-4-1, RS-4-2, RS-6-1 and RS-6-2 RS-4-1, RS-4-2, RS-6-1 and RS-6-2 RS-4-2 and RS-6-2 Only RS-4-2 and RS-6-2 Only RS-4-2 and RS-6-2 Only RS-4-2 and RS-6-2 Only RS-4-2 and RS-6-2 Only From the back of the RS-6-2 and RS-4-2 there are two groups of the above wires. Connect one group to the EGT Probes (or left channel for a twin installation) and connect the other group to the CHT (or right channel for a twin installation). +  - ;+$+ $ 2, (   2, &  4 4"
  2, &  1 2, 5  +  - ;++  2, &  4 4"
 -' : % -' :( % -' :$ %  2,   -' :  % ) #  "%  $ 2, (   2, &  1 2, 5  -' : % -' :( % -' :$ %  2,   -' :  % 8 2, 3   2,   -' :& % -' : % "0     < ) #  "%  "0     < )-+  #   )-+  #   Remote Switch Wiring Diagram Remote Switch Wiring Diagram Remote Switch Wiring Diagram Remote Switch Wiring Diagram Remote Switch Wiring Diagram RS-8-1 and RS-12-1 RS-8-1 and RS-12-1 RS-8-1 and RS-12-1 RS-8-1 and RS-12-1 RS-8-1 and RS-12-1 18 +  - ;+1+ $ 2, (   2, &  4 4"
 -' : % -' :( % -' :$ %  2, &  1 2, 5  -' :& % -' : % 8 2, 3   2,    2,   -' :  % 3+  - $ 2, (  -' :1 %  2,   -' :5 % +  - ;++ $ 2, (   2, &  4 4"
 -' : 4" % -' :( 4" % -' :$ 4" %  2, &  1 2, 5  -' :& 4" % -' : 4" % 8 2, 3   2,    2,   )  4" % +  - $ 2, (  -' :1 4" % -' :3 4" %  2, &   2,   -' :5 4" % -' :8 4" % 1 2, 5  -' : 4" % -' : 4" % 8 2, 3   2,   ) #  "%  "0     < ) #  "%  "0     < )-+  #   )-+  #   )-+  #   )-+  #   tinittd ~ l l l t t s or 21mcri!a Bcpartmtnt of ~ r a n s p o r t a t i o n -.federal 2l\1iation 2ldmini.Stration ~ u p p l r m r n t a l 1 C ~ p r <irrtificatr ~ SA1626NM ~ . a . d < k · ~ ~ . / k r . d , r f o < k ~ ~ ~ . « X d . . / k £ . ~ . n = i . c ~ ~ ~ ~ # ~ ~ .. / k ~ ~ ~ F ~ . . , t ' 9 . a # * ¥'./k Civil/Federal ~ - ~ ~ - ~ ~ ~ * See attached Approved Model List No. SA1626NM for list of approved airplane models and applicable airworthiness regulations. vltak. Jtdd.· 9 ' ~ . . . r . Y . ; u , i i 2 ..~ . · remote s w i t t h ~ , p r ~ , cab1es, International, Inc. Installation later FAA approved revisions. Installation of Electronics International EGT's/CHT's, and accessories in accordance with Electronics Instruction No. 070781, dated February 25, 1985, or Model ~ Model ~ EC-1 EGT/CHT C-6 6 Channel CHT E-4 4 Channel EGT EC-2 EGT/CHT E-6 6 Channel EGT E-2 EGT C.,4 4 Channel CHT C-2 CHT (Continued page 3) . . £ n ~ . n = i 6 . . . u / . : & , . . u • Approva 1 of this change applies to the above model aircraft only. This approval should not be extended to aircraft of this model on which other previously approved modifications are incorporated unless it is determined that the relationship between this change and any of those other previously approved modifications, including changes in type design will introduce no adverse effect upon the airworthiness of that aircraft. A copy of this Certificate, Addendum, Approved Model List No. SA1626NM, and Electronics International, Inc. Installation Instructions No. 070781, dated February 25, 1985, or later FAA approved revisions, must b . ! < j Z 1 ~ J ~ ; J c ~ ~ ~ ~ ~ ! J ~ J ~ ~ n ; : ~ ~ ' a ; % , d J ) , ? ~ , ~ ' ~ ' " ' ~ j ~ 0 ; ! , ~ , ! t ~ 5 ! : ~ ; / ~ , \ £ ~ , : _ pg · 3) September 20, 1982 7, 1986; ( Szgnatuu) Acting Manager, Special Certif tion Branch Seattle Aircraft Certification Office ( Titlt) Any alteration of this certificate is punishable ~ } ! a fine of not exceed1"ng 11,000, or imprisonment not exceedz.ng 3 yearJ, or both. This urt[ficaU may be transferred m accordar1u with FAR 21.17. fM FOIM 8110-2 ( 10-68) 1lnittd ~ t Q t t . s or 2!mnica 1Bcpartmcnt of 'aeran.sportation-jcdcral Sllliation Sldministration ~ u p p l c m c n t a l 1rnpc <tcrtificatc (Q:ontinnation iihert) ~ ~ ~ SA1626NM SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA1626NM Description of Type Design Change: (Continued from page I) Model J:.vQg_ RS4-1 4 Channels, Single Function RS-6-1 6 Channels, Single Function RS-8-1 8 Channels, Single Function RS-12-1 12 Channels, Single Function RS-4-2 4 Channels, Dua 1 Function RS-6-2 6 Channels, Dua 1 Function E-1 Single Channel, EGT Unit EC-ID Single Channel, EGT Unit with Differentia 1 C-1 Single Channel, CHT Unit Limitations and Conditions: (Continued) NOTE: The Electronic International EGT's/CHT's monitoring units are not approved for use as alternates to required equipment. If the EGT/CHT gauge is a required instrument on the aircraft, then Electronic International's monitoring units can be used, only if it is a standby to the primary instrument. - END - Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both. FAA FORM Bll0-2·1 (10-69) This certificate may be transferred in accurdance with FAR 21.47. PAGE 3 OF 3 PAGES List of Active Pages for Approved Model List (AML) SA1626NM Last Page Amendment Date This Page ------------------------- 3/9/93 1 ------------------------------ 3/9/93 2 ------------------------------ 3/9/93 3 ------------------------------ 3/9/93 4 ------------------------------ 6/2/92 5 ------------------------------ 3/9/93 6 ------------------------------ 6/2/92 7 ------------------------------ 6/2/92 8 ------------------------------ 6/2/92 FAA Approved by: Date: 80602921 3/9/93 FAA Approved Electronics International, Inc. Approved Model List (AML) SA1626NM for Installation Of Electronics International Digital EGT/CHT Instruments and Accessories Issue Date: May 24, 1988 Original Certification FAA Sealed Drawings Installation Type Basis Instructions AML Aircraft Aircraft Certificate for Amend. Item Make Model Number Alteration Number Rev. No. Nl.Jilber Date Date TD121161 12!11/86 070781 2/25/85 1. Aerocar I 4A16 CAR 3 " " " " None Inc. 2. Aeronca C-2 Series ATC 351 FAR 23 " " " " 6/02/92 Inc. C-3 Series A 396 "(also see K&50 trytek) Series -688, -676 " L Series ATC 596 & 614 " 15 Series A802 " 3. Aero- SE 3160 H1 IN CAR 10 " " " " 6/02/92 spatiale ALovette- " Ill H1 IN CAR 10 (Also see SA 315 Socata) Series H1 IN CAR 10 SA 316 Series H1 IN CAR 10 " SA 319 Series H1 IN CAR 10 262A Series A6 EU CAR 10 SN·601 A37 EU FAR 21.29 " SA·350 & 360 Series H8 EU FAR 21.29 SA·365 Series H10 EU FAR 21.29 4. Aircraft " " " " 6/02/92 Associates Inc. J·2 ATC 620 FAR 23 5. Air AT·300, A9SW FAR 21.25 TD121161 5/24/88 Tractor -300,-302, (a)(1) Inc. ·400 6. Artie Air- S·1A " " " " None craft Co. Series A737 CAR 4a S-1 B Series A754 CAR 4a 7. Ayres S·2R A3SW CAR 3 " " " " None Corp. A4SW CAR 8 s Series 2A9 CAR 6/02/92 8.10(a)(1) " 2A7 "600 Series A3SW CAR 3 S2RSeries A4SW CAR 8 " 8. Bal Lauer Funk 2·564 CAR 04.031 " " " " None Series 9. Balloon Fire Flys A14SO FAR 31 " " " " 3!09!93 'Works, The Page 1 FAA Approved Electronics International, Inc. Approved Model List (AML) SA1626NM for Installation Of Electronics International Digital EGT/CHT Instruments and Accessories Issue Date: Ma 24, 1988 Original Certification FAA Sealed Drawings Installation Type Basis Instructions AML Aircraft Aircraft Certificate for Amend. Item Make Model Number Alteration Number Rev. No. Number Date Date TD121161 12!11!86 070781 2/25/85 10. Beech B17B,B17L, ATC 560 CAR 4a " " " " 3!09!93 Aircraft SB17L CAR 4a Corp. B17R ATC 579 C17B,C17L ATC 602 " C17R ATC 604 CAR Part 3 18 Series A·757, -765, CAR Part 3 6/02/92 19,23,24 Car Part 03 Series A1CE CAR Part 3 33,35,36 FAR Part 23 Series 3A15 45 Series 5A3 CAR 3 6!02!92 50 Series 5A4 None 60 Series A12CE Part 23 65, Part 23 70, 90 3A20 Part 23 6!02/92 Series None 76 Series A29CE CAR Part 3 6/02/92 77 Series A30CE FAR Part 23 F90 Series A31CE " 95,55,56, FAR Part 23 58 Series 3A16 FAR Part 23 A23CE 99, 100 6/02/92 Series A14CE FAR Part 23 200 Series A24CE 300, 1900,& 1900C Series A24CE 11. Bell Heli- 47 Series H-1 , 2H3, CAR 6 " " " " 6/02/92 copter 2·H1 Textron 204&205 Series H 1 S ~ CAR 7 212 Series H 4 S ~ FAR Part 29 " 214 Series H6SIJ FAR Part 29 222 Series H 9 S ~ FAR Part 29 206 Series H 2 S ~ CAR 6 " 12. Bellanca 7 Series A· 759, CAR 4a " " " " None Aircraft 11 Series A·761, CAR 4a Corp. 14, 17' Series A-18CE FAR Part 23 " 8 Series A21CE FAR Part 23 300 Series ATC328 FAR Part 23 400 Series ATC319 FAR Part 23 13. British Twin " " " " None Aerospace Pioneer Series 2&3 7A7 CAR 10 Beagle 8206 Series 1&2 A1 1EU FAR 21.29 (CAR 3) Beagle 8121 Series A22EU FAR 21.29 1,2, &3 A22CE (FAR 23) 14. Camair Navi on 480 2A2 CAR 3 " " " " 6/02/92 Aircraft Corp. Page 2 FAA Approved Electronics International, Inc. Approved Model list (AML) SA1626NM for Instal latlon Of Electronics International Digital EGT/CHT Instruments and Accessories Issue Date: May 24, 1988 Original Cert 1f i cation FAA Sealed Drawings Installation Type Basis Instructions AML Aircraft Aircraft Certificate for Amend. Item Make Model Number Alteration Nllllber Rev. No. Number Date Date TD121161 12/11/86 070781 2/25/85 15. Cessna 120,140 .. .. .. .. None Aircraft series A768, CAR 4a 5A2 CAR 3(CAR 4a) (Also see 150, 152 Reims) Series 3A19 CAR Part 3 170 Series A799 CAR Part 03 172,175 Series 3A12, 3A17 CAR Part 3 177 Series A13CE,A20CE FAR Part 23 .. 180 Series 5A6 CAR Part 3 182, 185 Series 3A13, 3A24 CAR Part 3 A· 761 CAR 4a .. 188 Series A9CE FAR Part 23 190,195 CAR 3 03!09!93 Series A·790 CAR Part 3 6!02!92 206 Series A4CE FAR Part 23 207 Series A16CE CAR Part 3 Rev B 6!02!92 210 Series 3A21 5/23/86 303, 305 CAR Part 3 Series 5A5, 3A14 CAR 3 2/25/85 None 310 Series 3A10 320, 335, CAR Part 3 340 Series 3A25 CAR 3 336, A2CE CAR Part 3 337, A6CE 401, 402, 411, 414, 421, 425 CAR Part 3 Series A7CE FAR Part 23 .. 404 A25CE 16. Christen S-1,S-2, A8SO FAR 21 .. .. .. None Industries Series (FAR 23) Inc. (Pitts) 17. Child S-1, S-2 .. .. .. .. 6/02/92 Doyle F. Series ABSO FAR 21 (Pitts) (FAR 23) 18. Consoli- Colonial .. .. .. .. None dated C. Series, Aeronautic lake LA Series 1A13 CAR 03 19. De DH Series A8EU FAR 21.29 .. .. .. .. 6/02/92 HavilLand 2·439 FAR 21.29 .. 2·393 FAR 21.29 7A10 CAR 10 A·816 CAR 10 .. A·807 CAR 10 DHC Series A9EA CAR 3 AR·33 CAR 8 .. AR·13 CAR 8 1A19 CAR 10 20. Enstrom F Series HICE CAR Part 6 .. .. .. .. None Hel i- 280 Series copters 21. Great 2T Series ATC354 FAR 23 .. .. .. .. 6!2!92 Lakes ATC·167 2·3339 ATC228 A18EA Page 3 FAA Approved Electronics International, Inc. Approved Model list (AMl) SA1626NM for Installation Of Electronics International Digital EGT/CHT Instruments and Accessories Issue Date: May 24, 1988 Original Certification FAA Sealed Drawings Installation Type Basis Instructions AML Aircraft Aircraft Certificate for Amend. Item Make Model Number Alteration Number Rev. No. Number Date Date TD121161 12!11/86 070781 2!25!85 22. Gulfstream 111 Series 1150 FAR 23 " " " " 6!02!92 Aerospace 112 Series A12SO (FAR 36) 114 Series A12SO 23. Gulfstream Grunman: " " " " None American G·164 Series 1A16 CAR 8.10 (a)(1) G Series 1A17, A12EA CAR 4b AA Series A11EA FAR 23 A16EA Corrmander GA Series A17SO FAR 23 Division 500 Series 6A1 CAR 3 " " " " 6!02!92 111 A11SO FAR 23 112Series, (Far 21) 114Series A12SO FAR 23 " (Far 36) 24. HelioAir· H·250 1A8 CAR 3 " " " " None craft l TO H·295 1A8 CAR 3 (Navion) HT-295 1A8 CAR 3 H-391 1A8 CAR 3 H-391B 1A8 CAR 3 H·395 1A8 CAR 3 H-395A CAR 3 500 A2EA CAR 3 25. Hiller UH-12 6H1, 6H2, CAR 6 " " " " None Aviation Series 4H10, 4H11, H 1 ~ E 26. Huges 300 Series 4H12 CAR Part 6 " " " " 6/02/92 Hel i · 269 Series None copters 27. Husky A-1 AZZNM FAR 23 " " " " 6/02/92 28. Hynes H-2, H-4 2HZ CAR Part 6 " " " " None 29. Industrie PO 808/526 A12EU FAR 21.29 3!09!93 Aeronautic he E P. 166 Meccaniche Series 7A4 CAR 10 "(See Piaggio) 30. lake See con· sol idated Aeronautic s 31. Maule M Series 3A23 CAR Part 3 " " " " None Air-craft Corp. 32. McDonnell DC3 Series A-807 CAR ?a " " " " 6/02/92 Douglas DC4 Series A-618 CAR ?a 33. Mooney MZO Series 2A3 CAR 3 " " " " None (Mooney) MZZ A 6 S ~ CAR 3 6/02/92 34. Navion See Camiar Ryan and Thompson Page 4 FAA Approved Electronics International, Inc. Approved Model List (AML) SA1626NM for Installation Of Electronics International Digital EGT/CHT Instruments and Accessories Issue Date: Ma 24, 1988 Original Certification FAA Sealed Drawings Installation Type Basis Instructions AML Aircraft Aircraft Certificate for Amend. Item Make Model Number Alteration Number Rev. No. Number Date Date TD121161 12/11/86 070781 2/25/85 35. North AT·6 A-2-575 CAR 4a " " " " None American Aviation 36. Partenavia P68 Series A31EU FAR 21.29 " " " " None Cost· (FAR 23) truzioni Aero- nautiche 37. Piaggio P.136-L 03!09!93 (See Series A 813 CAR 10 Industrie) 38. Pi latus BN Series A17EU FAR 21.29, " " " " None Britten- FAR 23 Norman 39. Piper J2 Series ATC595 FAR 23 " " " " 6/02/92 Aircraft J3 Series ATC660 FAR 23 " Corp_ A-691 CAR 4a None A-691 CAR4a A-692 CAR4a A-698 CAR 4a 695 695 J4 series A-703 CAR4a 708, 708 A-740,721 CAR4a JS Series A-725 CAR4a PA12Series A-780 CAR 3 PA14Series A-797 CAR 3 PA15Series A-800 CAR 3 PA16Series 1A 1 CAR 3 " " " " " PA17Series A-805 CAR 3 PA18Series 1A2 CAR 3 AR-7 CAR 8.10(b) PA20Series 1A4 CAR 3 PA22Series 1A6 CAR 3 PA23Series 1A10 CAR 3 PA24Series 1A15 CAR 3 PA25Series 2A8, CAR 3 2A10 CAR 8.10(b) PA28Series 2A13 CAR 3 " " " " 6/02!92 PA 30,39, None 40 Series A1EA CAR 3 PA31Series A8EA CAR 3 6/02/9211 A20SO (FAR 23) " " " " 4/25!88 PA32Series A3SO CAR 3 None PA34Series A?SO FAR 23 PA36Series A9SO FAR 23 A10SO FAR 21 PA38Series A18SO FAR 23 PA44Series A19SO FAR 23 PA46Series A25SO FAR 23 PA-60-600 A171JE FAR 23 PA-60-601 A171JE FAR 23 PA-60-601P A17\JE FAR 23 PA-60-602P A17\JE FAR 23 PA-60-700P A17\JE FAR 23 " " 40. Pitts See Child 41. Prop-Jets 200 Series 3A18 CAR 3 " " " " None Inc. (Aero CAR 3 Corrmander) CAR 3 Page 5 FAA Approved Electronics International, Inc. Approved Model List (AML) SA1626NM for Installation Of Electronics International Digital EGT/CHT Instruments and Accessories Issue Date: May 24, 1988 Original Certification FAA Sealed Drawings Installation Type Basis Instructions AML Aircraft Aircraft certificate for Amend. Item Make Model Number Alteration Number Rev. No. Number Date Date TD121161 12!11/86 070781 2/25/85 42. Reims 172Series A4EU CAR 10 u u u u None Aviation A18EU FAR 21.29 (Cessna) (CAR 3) 150Series A13EU FAR 21.29 182Series A42EU CAR PART 3 337Seri es A23EU FAR 21.29 (FAR 23) 177Seri es A26EU FAR PART 23 43. Robinson R 22 H 1 0 ~ E FAR 27 u u u u None Helicopter 44. RockwelL 111Series A12SO FAR 23 u u u u None Inter- (FAR 36) national 112Series A12SO (Also see 114Series A12SO Ayres) 500,520 560,680, 681,690, 695,720 A7SO, 6A1 FAR 23, CAR 3 6/02/92 45. Rust, 21,22 Robert F. Series A44EU FAR 21.29 u u u u None (Chipmunk) 46. Ryan Aero- S C ~ · 1 4 5 658 CAR 4a u u u u 6/02/92 nautical ST Series ATC 571 CAR 4a co. ATC 681 A·749 47. Ryan B Series ATC 25 CAR 4a u u u u 6/02/92 Aircraft Corp. 48. Sikorsky H19 Series HR1SO FAR 21.25 u u u u 6/02/92 Aircraft s-39Series ATC·375 FAR 21.25 S·41·B 2·286 FAR 21.25 S-43Series A·593 Aero Bul-7A VS·44·A 752 CAR 4A u S·51Series H·2 CAR 6 s-52Series H·3 CAR 6 S-SSSeries 1H4 CAR 6 S-58Series 1 H11 CAR 6 S-61Series 1 H15 CAR 7 S·62A Series 1 H13 CAR 7 S-64seri es H1EA CAR 8 S-76Seri es H1NE FAR 29 u 49. Socata TB9, 10, A51EU u u u u 6/02/92 Group 20,21 Aero- spatiale 50. Stearman C3 Series ATC55, FAR 23 u u u u 6/02/92 Aircraft 2-159 2-445 ATC251 u 4 Series 2-155 FAR 23 ATC-305 ATC-292 6 Series ATC459 FAR 23 u Page 6 FAA Approved Electronics International, Inc. Approved Model list (AML) SA1626NM for Installation Of Electronics International Digital EGT/CHT Instruments and Accessories Issue Date: May 24 1988 Original Certification FAA Sealed Drawings Installation Type Basis Instructions AML Aircraft Aircraft Certificate for Amend. Item Make Model NliTlber Alteration Nunber Rev. No. Number Date Date TD121161 12!1 1!86 070781 2/25/85 51. Stinson SM Series ATC16 CAR 4a " " " " 6!02!92 ATC136 ATC48 ATC145 ATC161 ATC294 ATC98 SR Series ATC519 CAR 4a " ATC530 ATC580 ATC594 ATC608 ATC609 SR Series ATC621 CAR 4a ATC625 ATC640 " " " " " 52. Stol UC·1 A6EA CAR 3 " " " " None Amphibian (Twin· Bee) Corp. Republic A·769 CAR 03 RC·3 " " " " " 53. Swift GC Series A·766 CAR 4a " " " 6!02!92 Museum Foundation 54. Taylor· BC & BCS " " " " None craft Series A·696 CAR Part 04 Aviation 19 & F21 1A9 CAR Part 3 DC Series A746 CAR 4a BF Series A·699 CAR 4a Bl Series A·700 CAR 4a 55. Thompson, A through A-782 CAR 3 " " " " 6/02/92 J i rrmi e, z Series Enterprise (Navion) 56. Trytek, Aeronca " " " " 6!02!92 E.J. CF ,KC ATC 655 FAR 23 K KS A-634 FAR 23 57. Univar 108 Series A·767 CAR 3 " " " " None Aircraft A·718 Corp. (Forney) F-1 CAR 3 F-1A A-787 CAR 3 CErco) E A·787 CAR 3 (Stinson) (Mooney) CAR 3 G A·787 CAR 3 415·0 A·787 CAR 3 CAl on) A·2 A-787 CAR 3 A2·A A-787 CAR 3 (Mooney) M10 A-787 CAR 3 (Erco) 415·C A· 718 CAR 4a 415·CO A·718 CAR 4a 58. Varga Air- 2150Series 4A19 CAR 3 " " " " None craft Corp. Page 7 FAA Approved Electronics International, Inc. Approved Model List (AML) SA1626NM for Installation Of Electronics International Digital EGT/CHT Instruments and Accessories Issue Date: May 24, 1988 Original Certification FAA Sealed Drawings Installation Type Basis Instructions AML Aircraft Aircraft certificate for Amend. Item Make Model NL.ri>er Alteration NL.ri>er Rev. No. Number Date Date TD121161 12/11/86 070781 2/25/85 59. Yaco Air- A Series ATC26, CAR 4a " " " " 6/02/92 craft 644 6n 598 714 ATC41 ATC123 B&C Series ATC168 "ATC538 " D Series ATC639 " " " " " ATC597 ATC42 E Series 665 " 2·430 G Series ATC 13 " 2·363 I, J. K series 2-361 " ATC 313 0, p 1 Q Series ATC468 " ATC464 ATC491 ATC453 ATC502 R&S Series ATC466 " ATC311 ATC543 u, y, z Series ATC542 " ATC586 ATC627 " " " " " 60. Yeatherly 201Series A10WE FAR 21.25 (a) " " " " None Aviation (CAMS) 620Series A26WE FAR 21.25 (a) None Page 8 'lanitcd .Statc.s or 2!mrctra Brpartmcnr oF '[:ransportation -jrdcral 21\liation 2ldminisrration ~ u p p l c m c n t a l 1 t ~ p c <rcrtificatc SA2350NM (- ' -_'M-r4/u4'4'1:ca&:-iM-<udlv El t onJ."cs InternatJ."onal Inc 7<· . • ec r , • f : ~ j u ; n . a . / . ~ - ~ ~ - u / - , _ / # t . , - 6 ~ - ' l ' i ~ ~ : a k / , _ ·f{un/•a- · ' liah,. .1(,/,./ * * * * Civil Air * See Attached Master Eligibility List (MEL) Number SA2350NM for list of approved airplane models and applicable airworthiness regulations. ! . t ' d c ~ / ' ; , ' ' " . ; : ' i # t £ Y ~ " ' ~ : Y " GA,u;y'· Installation of Electronics International, Inc. Digital Carburetor/Outside Air Temperature Gauges listed on the attached Continuation Sheet, and the associated accessories in accordance with Electronics International, Inc. Installation Instructions No. II 070781-1. Approval of this change in type design applies to the above referenced models only. This approval should not be extended to other aircraft of these models on which other previously approved modifications are incorporated unless it is determined that the relationship between this change and any of those other previously approved modifications, including changes in type design, will introduce no adverse effect upon the airworthiness of that aircraft. (Continued on Page 3 of 3, Continuation Sheet.) '_/:l:_v_a ~ j t C H / e / .t:r.tu.l//w . 4 - U j y ' u ~ - - ~ ; y - _.--hla ..u~/ch-.M/ .//u//HM~;£7<--~/'-'J<&"td Ah.a/1/J'b7rLa~::n, I · ' n < . c / J f r ~ / ---urt-U:/Aa4V- July 8, 1983 February 16, 1984 May 26, 1987 :iJ;:y-~ J « < 4 : 0 n - "'- - ' l h ~ - - ,2/dnu:n.-i.Jba/eF ~ (Sig Assistant Manager, Sea tle Aircraft Certification Office Al!Y alteration of this cerqjicate is punishable try a .fine of not exceedz'ng $1,000, or imprisonment not txceeding J )-'Can, or both. 'Jlw certl}icate mr.ry be transferred in acrordance unlh FAR 21.47. FAA FORM 8110-2 (10-68) tinittd .Statts or llmcrire llcpartmcnt or 't:ransportation-jcdcral 9:11iation 9:dministration ~ u p p l t m c n t a l 1 t ~ p c Q:crtifiratc (liontinuation ~ h c c t ) J V ~ ( 3 / ) t SUPPLEMENTAL TYPE CERTIFICATE NO. SA235011M Description of Type Design Change: (Continued) Approved Electronics International, Inc. Carburetor/Outside Air Temperature Gauges: Model EAE-1 A-1 EAC-1 CA-1 EGT Left, OAT and EGT Right OAT Gauge EGT, OAT and CHT Gauge Carb/Outside Air Temp. Gauge NOTE: The models listed herein are designed for monitoring exhaust gas and cylinder head temperatures and are not primary instruments. Limitations and Conditions: (Continued) A copy of this Certificate, Continuation Sheet, Master Eligibility List (MEL) SA2350NM, Electronics International, Inc. Installation Instructions No. II 070781-1 and Operating Instructions No. OI 040831 shall be maintained as part of the permanent records for the modified aircraft. -END- Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both. FAA FORM 8110-2-1 (10-69) This cn-tiftcate may be transferred in accordana with FAR 21.47. PAGE 3 OF 3 PAGES DATE LIST of ACTIVE PAGES fc:: Approved Model List (AML) SA2350NM June 6, 1990 AMENDMENT DATE This Page June 6, 1990 1 ------------------------------- None 2 ------------------------------- None 3 ------------------------------- None 4 ------------------------------- June 6, 1990 5 ------------------------------- None 6 ------------------------------- None 7 ------------------------------- Nvne 8 ------------------------------- None 9 ------------------------------- None 10 ------------------------------- None 11 ------------------------------- June 6, 1990 J..meroded ______________________ _ :GS130C4 FAA APPROVED • ELECTRONICS INTERNATlONAL, INC. MASTER ELIGIBILITY LIST (HEL) SA2350Nl1 FOR INSTALLATION OF ELECTRONICS INTERNATIONAL DIGITAL CARBURETOR/OUTSIDE AIR TEMPERATUHE GAUGES DATE: February 16 1984 . r ITEM I fdHCRJ;FT AIRCRAFT ORIGINAL CERTIFICATION FAA SEALED AFM r-IEL ' f.!\1\KE MODEL TYPE BASIS DRAWING/ SUPPLEMENT AMENDMENT CERTIFICATE FOR DRAWING LIST NUMBER/ DATE NUMBER ALTERATION DATE NUMBER REV. I. Aerocar Inc. I 4AI6 CAR 3 TD 010972 2. Aeronca Inc. C-2 Series ATC 351 ATC 351 C-3 Series A 396 Aero Bul. 7-A K & 50 688, 676 688, 676 Series L Series ATC 596 ATC 596 & 614 & 614 15 Series A802 CAR 3 3. Air·c.caft l Associates i Inc. J-2 ATC 620 ATC 620 Lt • I 1\rct. ic Air- S-IA Series A737 CAR 4a I cr.:.:.ft Cu ~ S-IB Series A754 I CAR 4a 5. A]l't2S CGrp. S2R Series A3SW, CAR 3 I I A4SW CAR 8 ' I 6. I Air T ~ .;h' tor AT-300, A9SW FAR 21.25(a)( I 1ne .. -300, -302 -400 7. I nr:s.l L J . U < - ~ ! ' Funk Serie• 2-564 CAR 04.031 'I I I I Page 1 of 11 FAA APPROVED ELECTRONICS INTERNATIONAL, INC. KASTER ELIGIBILITY LIST (MEL) SA235011.K EUR INSTALLATION OF ELECTRONICS INTERNATIONAL DIGITAL CARBURETOR/OUTSIDE AIR TEMPERATURE GAUGES Issue Date: February 16, 1984 I FAA SEALED I - - - - ~ I I I I I I I ORIGINAL I CERTIFICATION DRAWING/ I I I I I I I I I TYPE I BASIS DRAWING LIST AFM I !1EL I I I I I I I I AIRCRAFT AIRCRAFT CERTIFICATE I FOR I REVISION NO. SUPPLEMENT I AMEND MEN" I I I I I liTEM I MAKE MODEL NUMBER I ALTERATION NUMBER I AND DATE NUMBER/DATE I DATE I ~ I I I *8. i Beech Air- 18 Series A-757, CAR 4a TD 0109721 I I I I l craft Corp 1 -765 I CAR 03 I I I I I I I I I 19' 23' 24 A-1CE I CAR Part 3 I I I I I I I I I I I Series I I I I I I I I I I I I 33' 35' 36, 3A15 I CAR Part 3 I I I I I I I I I I I Series I I I I I I I I I I I I I I 45 Series I 5A3 I CAR Part 03 I I I I I I I I I I I I 50 Series I 5A4 I CAR Part 3 I I I I I I I I I I I l 60 Series I A12CE I FAR Part 23 I I I I I I I I I I l65' 90 Ser.J 3A20 I CAR 3 I I I I I I I I I l 76 Series l A29CE I Part 23 I I I I I I I I I l 77 Series I A30CE I Part 23 I I I I I I I I I I l95' 55, 56 I 3A16 I CAR Part 3 I I I I I I I I I I I Series I I I I I I I I I I I l 58 Series A23CE I FAR Part 23 I I I I I Series I I I I I I I I I I 9. lBell Heli-l 47 Series H-1 , 2H3, I CAR 6 TD 010972 I I copter I 2H1 I I I I I Textron I I I I I I I I I I * NOTE: Amended Item #8 to remove Beech F90' 99' 100 and 200 Series aircraft on 5/26/87. Page 2 of 11 • ITEM AIRCRAFT MAKE 10. Bellanca' Aircraft- Corp. II. I Bri(ish .:\erospace 12. Cer..sna Ail·ct-aft I FAA APPROVED ELECTRONICS INERNATIONAL, INC • MASTER ELIGIRlLITY LIST (MEL) SA2350Nl1 FOR INSTALLATION OF ELECTRONICS INTERNATIONAL DIGITAL CARBURETOR/OUTSIDE AIR TEMPERATUHE GAUGES DATE: February 16, 1984 AIRCRAFT ORIGINAL CERTIFICATION FAA SEALED AFM MEL MODEL TYPE BASIS DRAWING/ SUPPLEMENT AMENDMENT CERTIFICATE FOR DRAWING LIST NUMBER/ D A ~ - NUMBER ALTERATION DATE NUMBER REV. 7 Series A-759 CAR Part 4a TD 01097? II Series A-761, CAR 4a 796 :CAR 3 14. 17 Serie A-ISCE :FAR Part 23 B Series A21CE 'FAR Part 23 300 Series ATC328 ATC328 400 Series ATC319 ATC319 Twin Pioneer Series 2 & 3 7A7 CAR 10 Beagle B206 Series I & 2 A liEU FAR 2 I. 29 (CAR 3) Beagle Bl21 A22EU FAR 2 I. 29 Series I • 2 (FAR 23) & 3 120, 140 A768, CAR 4a Series 5A2 CAR 3 (CAR 4a) 150, 152 Series 3AI9 CAR Part 3 170 Series A799 CAR Part 03 172. 175 Series 3AI2, CAR Part 3 3AI7 177 Series AI3CE, FAR Part 23 A20CE I 180 Series 5A6 CAR Part 3 n ___ 0 -C .. Ff\l\ i \ P P f { O ~ ~ ! J ) t"10DEL I.TST (AML) 110. : - : ; r i 2 3 S O ~ ~ f v i F L I C I ! ~ \ H i f l . S lrHERNI\1 IONI\1, UK. rem INSIALLAT!ON Of ELECfRONJCS JNTERNAl!ONAL OIG!IAL CARBURETOR/OUTS!OE AIR l ~ M P E R A T U R E GAUGES ~ - - - ------ .. -- ·r --------------1 I I I ORIGINAL I TYPE I AIRCRAFT AIRCRAFT CERTIFICATE I ITEM! MAKE MODEL NUMBER r--- i ·---------·- r · --- ----------+--------- -- t 1 12 Cessna 1 182, 185 3Al3, 3A24 1 Aircraftj Series 1 I (Cont.) I 188 Seriesf A9CE 1 1 190 Seriesf A-790 I 206 Series I A4CE 13 Child Doyle F. 14 Consoli- dated Aero- nautics I 207 Series I A16CE 1 210 Seriesf 3A21 I 303, 305 I 5A5, 3A14 1 Series 1 1 310 Seriesf 3A10 j320,335,340f 3A25 1 Series 1 I 336, 337 I A2CE, A6CE I 401, 402 1 A7CE 1411,414,4211 1 425 Seriesj I 404 Series 1 A25CE I I S-1, S-2, ASSO 1 Series 1 (Pitts) I jColonial C.f 1Al3 jSeries,Lakej iLA Series 1 I I 15 : Enstt·o:n iF Series, H1C[ . Hel icopterj 280 Series ------------- ___ ] CERT IF I CAliON BASIS CAR FOR ALTERATION CAR Part 3 FAR Part 21 CAR 3 CAR Part 3 FAR Part 23 CAR Part 3 CAR Part 3 CAR 3 CAR Part 3 3, CAR Part CAR Part 3 FAR Part 23 Issue Date: l'ebruary 16, 1984 ----T ------------------T----- FAA APPROVEIJ i IJRAvJING I DRAWOMG LIST I ! -- ... ______ T _______ -- I 1\FM I \ ~ 1 L I I REVISION NO. I SUPPLEMENT AMENDMENT 1 NUMBER I AND DATE I NO. AND DATE 1 DATE ·---·---------- I· -- ·-------' · --------------·f-------· --, 3 TO 0109721 I ~ I I I I I I I I 6/06/90 I I I I I I I I FAR 21 (FAR 23) CAR 03 CAR Part 6 1.- . Page 4 of 11 • l liTEM AIRCRAFT t MAKE I I . ' I 16. Great Lakes l I 17. Gulfstream American i I 18. Hiller l Aviation I i9. Hughes Helicopters 20. Hynes 21. 11aule Ai.r- craft Corp. 22. 11ooney Aircraft I1 FAA APPROVED ELECTRONICS INTERNATIONAL, INC. MASTER ELIGIBILITY LIST (MEL) SA 2:J50NM. FOR INSTALLATION OF ELECTRONICS INTER!lATIONAL DIGITAL CARBURETOR/OU1'5IDE AIR TEMPEHATURE GAUGES DATE : F b e ruary 16 AIRCRAFT ORIGINAL CERTIFICATION FAA SEALED AFM ' MODEL TYPE BASIS DRAWING/ SUPPLEMENT CERTIFICATE FOR ORAIIIING LIST NUMBER/ NUMBER ALTERATION DATE NUMBER REV.· 2T Series ATC-167 ATC-167 TD 010972 2-3339 2-3339 ATC228 ATC228 ATC354 ATC354 AlSEA FAR 23 Gruounan: IAI6 CAR S.IO(a)( I) G-164 Series G Series lA 17, CAR 4b A 12EA AA Series AIlEA, FAR 23 Al6EA GA Series A 17SO FAR 23 UH-12 Series 6H I, 6H2, CAR 6 4HIO, 4H II, HIWE 300 Series, 4Hl2 CAR Part 6 269 Series ' H-2, H-4 2H2 CAR Part 6 Series .. M Series 3A23 CAR Part 3 M20 Series 2A3 CAR 3 Page 5 of 11 • 198 4 MEL AMENDJt£NT DATE - .. '• fnEM AIRCRAF'T MAKE ! . : :l,, 23. North Americ- i can Aviation ~ ~ " ' 24. Partenavi.a. ; ~ Costruzioni j Aeronautiche :1 ~ ' 25. Pilat us I ' Brit ten- 1 Norman 26. Piper Air- craft Corp. FAA APPKOVEU. ELECTRONICS INTERNATIONAL, INC. MASTER ELIGIBILITY LIST (MEL) SA 2350Nl1 FOR INSTALLATION OF ELECTRONICS INTERNATIONAL DIGITAL CARBURETOR/OUTSIDE AIH TEMPERATURE GAUGES DATE: February 16, !9J4 AIRCRAFT ORIGINAL CERTIFICATION FAA SEALED AFM ' MEL MODEL TYPE BASIS DRAWING/ SUPPLEMENT AMENDMENT CERTIFICATE FOR nRAWTNt: LlST NUMBER/ DATE NUMBER ALTERATION DATE NUMBER REV,· AT-6 Series A-2-575 CAR 4a Til 01097? P68 Series A3!EU FAR 21.29 (FAR 23) ' BN Series A 17EU FAR 21.29. FAR 23 J2 Series ATC595 ATC595 J3 Series ATC660, ATC 660 A-69 I, CAR 4a A-692, CAR 4a A698, CAR 4a 695 695 J4 Series A-703, CAR 4a 708, 708 A-740, 721 CAR 4a JS Series A-725 CAR 4a PAIZ Series A-780 CAR 3 'PA 14 Series A-797 CAR 3 PAIS Series A-800 CAR 3 PAI6 Series lA I CAH 3 PA 17 Series A-805 CAR 3 PAIS Series IA2, CAR 3 AR-7 CAR S.IO(b) PA20 Series IA4 CAR 3 I ! ' Page 6 of 1 j - • I •I ~ T E M AIRCRAF'f i MAKE I . ' II 26. Piper Air- I I craft Corp.I ! (Cont'd) ' I I; i i ! I; 27. Prop-Jets Inc ! (Aero '' Commander) ) ( I. ' 28. Eeims Avia- l tion ( C c S ~ i l B . ) j 29. Robinson - Heliccf:,L.;;.;: ' FAA APPROVED ELECTRONICS INTERNATIONAL, INC. MASTER ELIGIBILITY LIST (HEL) SA2J50NE FOR INSTALLATION OF ELECTRONICS INTERNATIONAL DIGITAL CARBURETOR/OUTSIDE AIR TEMPERATURE GAUGES DATE: Februarv AIRCRAFT ORIGINAL CERTIFICATION FAA SEALED AFM ' MODEL TYPE BASIS DRAWING/ SUPPLEMENT CERTI I'I CATE FOR "'' LIST NUMBER/ NUMBER ALTERATION DATE NUMBER REV. PA22 Series IA6 CAR 3 Tf! CJ10972 PA23 Series lA 10 CAR 3 PA24 Series IA15 CAR 3 PA25 Series 2A8, CAR 3 2AIO CAR 8.10(b) PA 30, 39. 40 A lEA CAR 3 Series I PA31 Series A8EA CAR 3 (FAR 23) PA36 Series A9SO, FAR 23 AIOSO FAR 21 PA38 Series A IBSO FAR 23 PA28 Series 2A13 CAR 3 PA32 Series A3SO, CAR 3 A7SO FAR 23 PA44 Series A19SO FAR 23 ' 200 Series 3A18 CAR 3 172 Series A4EU, CAR 10 A18EU FAR21.29 (CAR 3) ' ISO Series A 13EU FAR 21.29 182 Series - A42EU CAR Part 3 337 Series A23EU FAR 21.29(FAR 23) 177 Series A26EU FAR Part 23 R22 H10WE FAR 27 Page 7 of 11 16. 1964 MEL AMENDMEHT DATE - i liTEM i i i . ro. Ij3 I • ''•l t r Irl 3. ' ' I • FAA APPROVED ELECTRONICS INTEKNATIONAL, INC. MASTER ELIGIBILITY LIST (MEL) SA2350l,l1 FOR INSTALLATION OF ELECTRONICS INTERNATIONAL DIGITAL CARBURETOR/OUTSIDE AIR TEMPERATURE GAUGES DATE: February 16, 1984 AIRCRAFT AIRCRAFT ORIGINAL CERTIFICATION FAA SEALED AFM ' MEL MAKE MODEL TYPE BASIS DRAWING/ SUPPLEMENT AMENDMENT CERTIFICATE FOR ,.,.,, LlST NUMBER/ DATE NUMBER ALTERATION . DATE ! NUMBER REV. - Rockwell Ill Series, AI2SO FAR 23 (FAR 36) TD 010Y72 International 112 Series, II Series Rust, RoGert 2 I, 22 A44EU FAR21.29 E. Series (Chipmunk) i Stearman C3 Series ATC55, ATC55 Aircraft 2-159 2-159 2-445 2-445 ATC251 ATC251 4 Series 2-155 2-155 ATC305 ATC305 ATC292 ATC292 6 Series ATC459 ATC459 Stinsvn SM Series ATCI6 ATCi6 Division ATCI36 ATC 136 ATC48 ATC48 ATCI45 ATCI45 ATCI61 ATCI61 ' ATC194 ATC194 .. ATC298 ATC298 SR Series ATC5!9 ATCSI9 ATC530 ATC530 ATC580 ATC580 ATC594 ATC594 ATC608 ATC608 ATC609 ATC609 ~ n - .c 1 1 - • FAA APPROVED ELECTRONICS I N T E R N ~ T I O N A L , INC. MASTER ELIGIBILITY Lis'f (MEL) SA 2J50Nl1 FOR INSTALLATION OF ELECTRONICS INTERNATIONAL DIGITAL CARBURETOR/OUTSIDE AIR TEMPERATURE GAUGES ITEM 33. AlRCHAf'T MAKE Stinson Division (Cont'd) 34. Taylorcraft Aviation 35. T h o m p s o ~ , Jimmie, Enterprise (Navion) 36. Varga AL·- craiL ~ - · ..... 1 : ~ . AIRCRAFT MODEL SR Series (Cont'd) BC & BCS Series 19 & F21 Series DC Series BF Series BL Series A through H Series 2 150 Series 37. WacuAir ..~laft A Series B & C Series ' ORIGINAL TYPE CERTIFICATE NUMBER ATC621 ATC625 ATC640 A-696 IA9 A746 A-699 A-700 A-782 4AI9 ATC 26, 664, 677, 598, 714. ATC 41 ATC 123 ATC 168. ATC 538 CERTIFICATION BASIS FOR ALTERATION ATC621 ATC625 ATC640 C