Electronics CGR-30P User Manual

Primary Glass Panel Engine Monitor

CGR-30P

Installation Instructions

II 02151301 Rev. B: 6/21/13

You must read this manual before installing or operating the instrument. This manual contains warranty and other information that may affect your decision to install this product and/or the safety of your aircraft.

The CGR-30P is a FAA Approved Primary Replacement for Engine and Aircraft System Instruments

Model #:

S/N:

Electronics International Inc. ®

63296 Powell Butte Hwy • Bend, OR 97701 • [phone] • Buy-EI.com

Important Notice

***** MUST READ *****

Page 1 of 4

If you think it is not important to read this manual, you're wrong! This manual contains important operating information that may affect the safety of the pilot, passengers, aircraft, operation of the system or time to install the system. You MUST read the manual prior to installing this system. Any deviation from these installation instructions is the sole responsibility of the installer and should be done in accordance with AC 43.13.

Read the Warranty/Agreement. There is information in the Warranty/Agreement that may alter your decision to install this product. If you do not accept the terms of the Warranty/Agreement, do not install this product. This product may be returned for a refund. Contact Electronics International Inc. for details.

If you are not an FAA Certified Aircraft Mechanic familiar with the issues of installing aircraft EGT, CHT, RPM, M.P, Fuel Level, Fuel Flow, Fuel Pressure, Volt, Amp, Oil Temperature and Pressure instruments, Do Not attempt to install this instrument. The installer should use current aircraft standards and practices to install this system (refer to AC

43.13).

If the installer does not have the skills, knowledge, tools, equipment or facility, to perform and determine whether the installation of this product is safe, reliable and accurate and to determine whether this product is operating properly after installation, DO NOT INSTALL THIS PRODUCT. If the owner/pilot and/ or installer are unwilling to take the responsibility for the installation and operation of this product, DO NOT INSTALL THIS PRODUCT. This product may be returned for a refund. Contact Electronics International Inc. for details.

By installing this product, the aircraft owner/pilot and installer agree to hold Electronics International Inc. harmless and in no way responsible for monetary compensation, including punitive damages for any incident, harm and/or damage associated with this product. If you do not agree to the above, DO NOT INSTALL THIS PRODUCT. This product may be returned for a refund. Contact Electronics International Inc. for details.

Electronics International Inc. is not liable or responsible for a pilot’s action or any situation that results in personal injury, property damage, missed commitments, lack of use of an aircraft or any expenses incurred due to: product failure, inaccuracy in displayed data or text files, display or display format issues, software bugs or problems, upgrade or customization issues, misinterpretation of the display, warning and/or limit settings, calibration problems, installation issues (leaks, mis-wiring, obstructions, damage to aircraft or components, incorrect installation of any parts, wrong parts, parts that don’t fit, etc.) or any other issues related to the installation or operation of this product. All of the above are solely the pilot’s and/or installer’s responsibility. The pilot must understand the operation of this product before flying the aircraft. The pilot must not allow anyone to operate the aircraft that does not know the operation of this product. The pilot must keep the instrument Operating Instructions in the aircraft at all times. If you do not agree to the above, DO NOT INSTALL THIS PRODUCT. This product may be returned for a refund. Contact Electronics International Inc. for details.

Important Notice

***** MUST READ *****

Page 2 of 4

Do not install a non-certified CGR-30P (CGR) in a certified aircraft. A certified CGR lists the applicable TSO numbers at the bottom of the Model Label.

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.

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

The accuracy and proper operation of each function displayed on the CGR should be verified before the aircraft is released for flight.

When the installation is finished, inspect the system for loose fittings, connections, clamps, probes and inspect for leaks, chafing, obstructions, heat damage and anything that may cause unsafe flight before the 1st run-up, after the 1st run-up and after the first flight.

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

Before allowing anyone to operate the aircraft they must read the Operating Manual including the Important Notice there in. Keep the Operating Instructions in the aircraft at all times.

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

Important Notice

***** MUST READ *****

Page 3 of 4

Fuel LevelAccuracy Limitations:

The accuracy limitations of the CGR are listed below. It is the pilot/owner’s obligation to make anyone flying the aircraft aware of these limitations.

1. Angle of Attack - The CGR must be calibrated with the aircraft in a cruise angle of attack. If the aircraft is in an angle of attack other than cruise, the CGR may display inaccurate fuel levels (depending on the mounting location and type of sensor used). If your aircraft does not sit at a cruise angle of attack when on the ground, it may not display accurate fuel levels. Test your aircraft at different angles of attack to see the affects on the CGR fuel level readings.

2. Full Fuel Readings - As a tank is filled the fuel sensor may not be able to detect the fuel entering the upper corners of the fuel tank. If this is the case with your sensor, the CGR will display lower fuel levels than the actual fuel in the tanks when the tanks are full. When the fuel level drops to a point where the fuel sensor starts to detect a change, the displayed fuel level should be accurate.

Check the accuracy of your system by comparing the displayed fuel levels on the CGR to the fuel levels listed in the flight manual at each fill up.

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

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

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

6. Defective Fuel Level Sensors - Fuel sensors can become intermittent or change resistance with age. It is not uncommon to find intermittent problems even in new sensors. An intermittent problem with a fuel sensor most likely will show up as wandering or inaccurate readings on the CGR.

Always crosscheck the measured fuel levels in the tanks with the readings on the CGR at each fill up.

If you ever find an inaccuracy	issue or any	other problem with a fuel level display on
the CGR, troubleshoot and fix	the problem	before flying the aircraft.

If you do not agree to all of the above, DO NOT INSTALL THIS PRODUCT. This product may be returned for a refund. Contact Electronics International Inc. for details.

Important Notice

***** MUST READ *****

Page 4 of 4

ImportantFuelLevelConsiderations:

DO NOT RELY SOLELY ON THE FUEL LEVEL DISPLAYED ON THE CGR TO DETERMINE THE FUEL LEVELS IN THE AIRCRAFT. The use of the CGR does not eliminate or reduce the necessity for the pilot to use good flight planning, preflight and in-flight techniques for managing fuel. It is important the pilot adopt the practices listed below. If you are not familiar with these techniques, contact the FAA to acquire proper training.

1.A copy of the Operating Manual must be in the aircraft at all times.

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

3.Preflight - Do not rely on the CGR to determine the fuel level in the fuel tanks. The pilot must visually check/measure the fuel levels in the tanks before every takeoff.

Crosscheck the measured fuel levels with the displayed levels on the CGR. Also, crosscheck these levels with the fuel requirements for the flight listed in your flight plan.

4.In Flight - Make the CGR part of your normal instrument scan. Crosscheck the fuel levels displayed on the CGR with your flight plan at each leg of the flight or every 30 minutes

(whichever happens first). If there is a discrepancy, land the aircraft at the nearest airport and verify the fuel levels. Discrepancies should be taken seriously.

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

If you do not agree or are unwilling to comply with the information/requirements contained within this Important Notice, DO NOT INSTALL THIS PRODUCT. This product may be returned for a refund. Contact Electronics International Inc. for details.

		Contents
		(Page 1 of 3)
Warranty/Agreement--------------------------------------------------------------------------------------			1A
1.0 System Overview -------------------------------------------------------------------------------------			2
1.1	System Description ---------------------------------------------------------------------------		3
	1.1.1	CGR Display ----------------------------------------------------------------------------	3
	1.1.2	EDC-33P ---------------------------------------------------------------------------------	3
	1.1.3	Probes, Transducers and Modules ---------------------------------------------------	3
	1.1.4	Wiring & Extension Cables -----------------------------------------------------------	3
1.2 Operational Overview -------------------------------------------------------------------------------			4
1.3 Installation Overview ---------------------------------------------------------------------------------			4
1.4 Password Protection ----------------------------------------------------------------------------------			5
1.4.1 User Password -------------------------------------------------------------------------------			5
1.4.2 Maintenance Password ---------------------------------------------------------------------			5
1.4.3 OEM/Experimental Password ------------------------------------------------------------			6
2.0 Hardware Installation --------------------------------------------------------------------------------			7
2.1 Important Information and Initial Check Out: -------------------------------------------			8
2.2	Review the "EDC Wiring Work Sheets:" -------------------------------------------------		9
2.3	Verify you have all the necessary Probes, Modules, Transducers and Cables: -----		9
2.4	Install the CGR Display: ---------------------------------------------------------------------		9
2.5	Install the Temperature Probes: -------------------------------------------------------------		10
2.6	Install the Pressure Transducers: -----------------------------------------------------------		12
2.7	Install the Interface Circuit for Annunciators --------------------------------------------		14
2.8	Install the CO Detector, G-Sensor and/or Other Available CGR Options -------		15
2.9	Install the Shunt: ------------------------------------------------------------------------------		15
2.10 Install the Fuel Flow Transducer: --------------------------------------------------------			17
2.11 Install the P-300C Fuel Level Probes (OEM or Experimental) ---------------------			24
2.12 Install the P-300M Fuel Levl Sender: ----------------------------------------------------			24
2.13 Install the Resistive Fuel Level Module (RFLM-4-X): -------------------------------			25
2.14 Install the Voice Alarm Control Panel (OEM or Experimental): -------------------			25
2.15 Install the Intensity Control Pot (Optional): --------------------------------------------			25
2.16 Install the Master Warning (red) and Caution (yellow) Lights: -----------------------			26
2.17 Install the EDC-33P: ------------------------------------------------------------------------			26
3.0 Install the EDC Wire Harnesses and Route Wires ----------------------------------------------			27
3.1	Attach the three EDC 37-pin wire harnesses to the EDC: ----------------------------		28
3.2	Connect the EDC Harness to the Temperature Probes: --------------------------------		28
3.3	Connect the EDC Harness to the Pressure Transdcueres: -----------------------------		28
3.4	Connect the EDC Harness to the Shunt: --------------------------------------------------		29
3.5	Connect the EDC Harness to the Fuel Flow Transducer: -----------------------------		29
3.6 Connect the EDC Harness to the Existing Capacitive Fuel Level System: --------			29
3.7	Connect the RFLM-4-x Harness to the EDC Connector and to the Resistive
Fuel Level Sensors: -------------------------------------------------------------------------------			30

	Contents
	(Page 2 of 3)
3.8	Connect the EDC Harness to the EI P-300C Capacitive Fuel Level Probes: -----	30
3.9	Connect the EDC Harness to the P-300M Magnetic Fuel Level Senders: ----------	31
3.10 Connect the EDC Harness (Volts Meassurement Pin) to the Bus: -----------------		31
3.11 Connect the EDC Harness to the RPM Signals: ----------------------------------------		31
3.12 Setup the EDC for a 4 or 6-Cylinder Engine: -------------------------------------------		31
3.13 Connect the EDC Harness to the VI-221's (Voltage Interface Units): -------------		31
3.14 Connect the EDC Harness to Power and Ground: ------------------------------------		32
3.15 Route the EDC 5V-Serial Wire to the CGR Connector: ------------------------------		32
4.0 Install the CGR Wire Harness and Route the Wires -------------------------------------------		33
4.1	Attach the CGR 25-pin D-sub Connector to the CGR: --------------------------------	34
4.2	Connect the EDC 5V-Serial Output Wire to the CGR 5V-Serial Input Wire: -----	34
4.3	Connect the CGR Harness to the Master Warning and Caution Lights: -------------	34
4.4	Connect the CGR Harness to the Voice Alarm Control Panel (AV-17CP): --------	34
4.5	Connect the CGR Harness to the Audio Panel (OEM/Experimental): -------------	35
4.6	Connect the CGR Harness to the Backlight Control Pot: ------------------------------	35
4.7	Connect the CGR Harness to the Moving Map Data Out from the GPS: ----------	35
4.8	Connect the CGR Harness to the Fuel Data Input on the GPS: ----------------------	35
4.9	Connect the CGR Harness to Power and Ground: --------------------------------------	36
4.10 Connect the CGR Harness to the CO-Guardian CO Detector: ---------------------		36
5.0 Mandatory System Setup and Checkout ---------------------------------------------------------		37
5.1	Power-On Checkout --------------------------------------------------------------------------	38
5.2	Perform all Steps Listed in the "CGR-30P Setup Checklist" ------------------------	38
5.3	Ground Run Checkout ------------------------------------------------------------------------	38
5.4	First Flight Checkout --------------------------------------------------------------------------	39
5.5	Read the "Warranty/Agreement" and the "Important Notice" -----------------------	39
6.0 Installation Data --------------------------------------------------------------------------------------		40
6.1 Instructions for Continued Airworthiness (ICA): -----------------------------------------		41
6.2 Airworthiness Limitations: --------------------------------------------------------------------		41
6.3 Installing a D-sub Pin onto a TC or Tin Copper Wire: ----------------------------------		41
CGR-30P Wiring Work Sheet --------------------------------------------------------------------		43
EDC Wiring Work Sheet Top Connector ------------------------------------------------------		44
EDC Wiring Work Sheet Middle Connector ---------------------------------------------------		45
EDC Wiring Work Sheet Bottom Connector --------------------------------------------------		46
EDC Template --------------------------------------------------------------------------------------		47
7.0 Troubleshooting ---------------------------------------------------------------------------------------		48
7.1 CGR or EDC Problem ------------------------------------------------------------------------		49
7.2	Pressure Problem with one Function -------------------------------------------------------	50
7.3	Temperature Problem on all Channels -----------------------------------------------------	50
7.4	Temperature Problem with one Function -------------------------------------------------	51
7.5	RPM Problem -----------------------------------------------------------------------------------	51
7.6	Fuel Flow Problem -----------------------------------------------------------------------------	52

Contents
(Page 3 of 3)
7.7 Amp Problem -----------------------------------------------------------------------------------	53
7.8 Resistive Fuel Level Problem ----------------------------------------------------------------	53
7.9 Capacitive Fuel Level Problem --------------------------------------------------------------	54
7.10 Voltage Problem ------------------------------------------------------------------------------	55
7.11 Annunciator Problem ------------------------------------------------------------------------	55
8.0 Technical Data ----------------------------------------------------------------------------------------	56
Specifications, Functions and Features ----------------------------------------------------------	57
Appendix ----------------------------------------------------------------------------------------------------	A
A1.0 Appendix: LASAR Ignition RPM Filter --------------------------------------------------	A1.0
A2.0 Appendix EDC-33P-8 for 7, 8, 9-Cylinder Engines and High RPM Engines ----	A2.0
A3.0 Appendix Connecting an EDC RPM Channel to a Lightspeed Plasma II or
III Ignition ---------------------------------------------------------------------------------------	A3.0

Warranty / Agreement

Electronics International Inc. (EI) 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. EI will repair or replace any item under the terms of this Warranty provided the item is returned to the factory prepaid.

1.If you do not agree to and accept ALL the terms of this Warranty/Agreement, DO NOT Install This Product. You may return the product for a refund, contact Electronics International Inc. for details.

2.Electronics International Inc. is not liable or responsible for a pilot’s action or any situation that results in personal injury, property damage, missed commitments, lack of use of an aircraft or any expenses incurred due to: product failure, inaccuracy in displayed data or text files, display or display format issues, software bugs or problems, upgrade or customization issues, misinterpretation of the display, warning and/or limit settings, calibration problems, installation issues (leaks, mis-wiring, obstructions, damage to aircraft or components, incorrect installation of any parts, wrong parts, part that don’t fit, etc.) or any other issues related to the installation or operation of this product. All of the above are solely the pilot’s and/or installer’s responsibility. The pilot must understand the operation of this product before flying the aircraft. The pilot will not allow anyone to operate the aircraft that does not know the operation of this product. The pilot will keep the instrument's Operating Instructions in the aircraft at all times.

By installing this product, the aircraft owner/pilot and installer agree to hold Electronics International Inc. harmless and in no way responsible for monetary compensation, including punitive damages for any incident, harm and/or damage associated with this product (including but not limited to the ones listed above). If you do not agree to any part of this Warranty/Agreement, DO NOT INSTALL THIS PRODUCT.

3.This Warranty/Agreement 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 does not cover any reimbursement for any person’s time for installation, removal, assembly or repair. Electronics International retains the right to solely determine the reason or cause for warranty repair.

4.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.

5.Personal injury or property damage due to misinterpretation or lack of understanding of this product is solely the pilots' responsibility. The pilot must understand all aspects of the operation of this product before flying the aircraft. If he/she does not, he or she agrees to seek training from a knowledgeable instructor. The pilot also agree that no one will be allowed to operate the aircraft that does not know the operation of this

product and will Keep the Operating Instructions in the aircraft at all times.

6.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.

7.Electronics International Inc. is not liable for expenses incurred by the customer or installer due to factory updates, modifications, improvements, changes, or any other alterations to the product that may affect the form, fit, function or operation of the product.

More On Back of this Page

1A

8.Electronics International is not responsible for shipping charges or damages incurred under this Warranty.

9.No representative is authorized to assume any other liability for Electronics International Inc. in connection with the sale of Electronics International Inc. products.

10. You must read the entire Installation and Operating Instructions for this instrument. If you do not agree to and accept the terms of this Warranty/Agreement and the responsibilities set forth in these manuals, DO NOT install this product, contact E.I. for a refund.

This Warranty is made only to the original user. THIS WARRANTY IS IN LIEU OF ALL OTHER

WARRANTIES OR OBLIGATIONS: EXPRESS OR IMPLIED. MANUFACTURER EXPRESSLY DISCLAIMS ALL IMPLIED WARRANTIES OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE. PURCHASER AGREES THAT IN NO EVENT SHALL MANUFACTURER BE LIABLE FOR SPECIAL, INCIDENTAL OR CONSEQUENTIAL DAMAGES, INCLUDING LOST PROFITS OR LOSS OF USE OR OTHER ECONOMIC LOSS. EXCEPT AS EXPRESSLY PROVIDED HEREIN, MANUFACTURER DISCLAIMS ALL OTHER LIABILITY TO PURCHASER OR ANY OTHER PERSON IN CONNECTION WITH THE USE OR PERFORMANCE OF MANUFACTURER’S PRODUCTS, INCLUDING SPECIFICALLY LIABILITY IN TORT.

1B

1.0

System Overview

1.1System Description

1.1.1CGR Display:

1.1.2EDC-33P:

1.1.3Probes, Transducers and Modules:

1.1.4Wiring & Extension Cables:

1.2Operational Overview:

1.3Installation Overview:

1.4Password Protection:

1.4.1User Password:

1.4.2Maintanance Password:

1.4.3OEM/Experimental Password:

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1.1 System Description:

The CGR-30P Glass Panel Engine Monitor installation consists of four major components: the CGR Display, the Engine Data Converter (EDC-33P), the Probes, Transducers & Modules, and the Wiring and Extension Cables.

1.1.1 CGR Display:

The CGR-30P (CGR) display measures 3.25" wide by 3.25" high by 4.36" deep and is designed to be mounted from behind the aircraft instrument panel.

The 25-pin D-sub connector on the back of the CGR display is used to interface the CGR to the EDC33P, Power & Ground, GPS, Master Warning and Caution Lights and Audio Panel (experimental only).

1.1.2 EDC-33P:

The EDC-33P (Engine Data Converter, "EDC") converts all of the engine and aircraft system signals into serial data. This data is transmitted to the CGR display via one wire 5V-Serial Bus. Up to two EDC’s can be connected to the CGR display. The EDC measures 4.5" long by 3.5" wide by 2.2" high and is to be mounted on cockpit side of the firewall or in an equipment bay. The EDC reduces the wire bundle to the instrument panel by over 100 wires. There are three 37-pin D-sub connectors that interface the EDC to the various probes, transducers and modules.

1.1.3 Probes, Transducers and Modules:

The various probes, transducers and modules are mounted in the aircraft at appropriate locations.

1.1.4 Wiring & Extension Cables:

The extension cables and wiring provide the connections from the probes, modules or direct connections to the EDC inputs. Once the Wiring and Extension Cables are installed into the aircraft they become semi-permanent. Everything else (CGR, EDC, Probes and Modules) can be easily disconnected and removed.

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1.2 Operational Overview:

The CGR system measures a primary engine or aircraft function using a probe or transducer and displays that function on the CGR screen using the following steps:

A.A probe is mechanically connected to the aircraft and electrically connected to an EDC input. The pre-wired harness provides most of the electrical connections from the probes to the EDC inputs.

B.The EDC converts the signals from the probes to a digital format and sends the data to the CGR through the serial bus. The EDC has 33 inputs. Many of these inputs can be used to monitor various types of functions.

C.The CGR receives the data from the EDC and the data is processed through the CGR as follows:

1.A Function is created in the CGR and is linked to an EDC input.

2.The function is assigned a screen location onto the Main or System Screen of the CGR.

3.Calibration, units, redlines, limits etc. are assigned to the data coming into that function.

Much of the setup for the certified CGR is done at the factory and cannot be changed by the pilot or installer. See the following Password Protection Section for more information.

1.3 Installation Overview:

For a twin engine installation refer to appendix A8.0. The installer should start the installation by reviewing the CGR and EDC Wiring Work Sheets. There are four work sheets, one for each of the 37-pin D-Sub connectors on the EDC and one for the CGR. The work sheets are packaged with each of the three EDC wire harnesses and one for the CGR. The work sheets provide a list of the functions and probes/transducers included with this kit. The installation is achieved by performing the following steps:

A.The CGR display is installed. The CGR is mounted from behind the instrument panel in a standard 3 1/8" hole.

B.Probes and Transducers are installed.

C.Control Panels, Pots and Warning Lights are installed.

D.The EDC is installed. The EDC should be installed on the inside of the cockpit or in an instrument bay. For a twin-engine aircraft it can be installed on the backside (not the engine side) of the firewall.

E.The Wire Harnesses are installed. The wire harnesses for the EDC and CGR are pre-wired and included in the kit.

F.Field Calibration/Setup steps are performed. If installed Fuel Tanks are calibrated/setup. Calibration/ Setup requires a password. See the following Password Protection section for more information.

G.System Checkout is performed.

4

1.4 Password Protection:

The CGR provides a number of screens for the pilot to use during flight, none of which require a password. It also provides many System Configuration Screens that are used to configure the CGR for a specific aircraft. Fuel level, if installed, must be calibrated during installation before the aircraft is flown.

The CGR provides three levels of passwords for configuring and calibrating the unit.

1.4.1User Password:

The User Password is for the pilot or operator of the aircraft. This password allows the pilot to perform the following:

A.Adjust the K-Factor for the fuel flow.

B.Set the Local and Zulu Clocks.

C.Setup some Bar Graph limits.

D.Download recorded flight log data and change recording sample rate.

E.Set the Recurring Fuel Alarm.

F.Backup Config Files.

G.Change or disable the User Password.

H.Set Com3 and Com4

I.Set the Voice Level and test a Voice File.

J.Perform the Input/Output Tests.

K.View a Function and Probe Configuration.

By default the User Password is blank, if left blank you will not need to enter a password to access these features. If the CGR installed in an aircraft that is primarily owner operated we recommend leaving the password blank. However, if this aircraft is used by renters or students, we recommend setting a password to keep unauthorized changes from happening.

1.4.2Maintenance Password:

The Maintenance Password is for the installer or maintenance personnel. This password allows the installer to perform all of User Password operations plus the following:

A.Update the Software.

B.Retrieve the Config Files.

C.Change the Maintenance Password.

D.Set Tach and Engine Time.

E.Set Com1 and Com2.

F.Set the Display Backlight levels.

G.Calibrate Fuel Tanks.

For a non-certified CGR, Maintenance Password is “00100.” For a certified CGR, this password will be provided in the kit. To qualify for the maintenance password you must be a certified mechanic or a FAA approved shop.

This password protects the CGR from unauthorized access to calibration data. If calibration data is improperly changed, it could lead to engine or aircraft damage and/or personal injury. Once the CGR is

5

installed and checked out, this password should be changed (whether a certified or non-certified CGR) to a unique number and should be protected from unauthorized access.

If the new password is lost or a new shop requires access to calibration data (as allowed by the Maintenance Password), Electronics International has a method of providing the Maintenance Password to any FAA authorized shop or certified mechanic.

1.4.3OEM/Experimental Password:

The OEM Password is for OEM's or Experimental installers. This password allows access to all System Configuration Data. For a non-certified CGR, the OEM Password is “00100.” For a certified CGR this password is only released under a contract or agreement.

This password protects the CGR from unauthorized access to calibration data. If calibration data is improperly changed, it could lead to engine or aircraft damage and/or personal injury. Once the CGR is installed and checked out, this password should be changed (whether a certified or non-certified CGR) to a unique number and should be protected from unauthorized access.

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2.0

Hardware Installation

2.1Important Information and Initial Checkout:

2.2Review the "EDC Wiring Work Sheets:"

2.3Verify You Have all the Probes, Modules, Transducers and Cables:

2.4Install the CGR Display:

2.5Install the Temperature Probes:

2.6Install the Pressure Transducers:

2.7Install the Interface Circuit for Annunciators:

2.8Install the CO Detector, G-Sensor and/or Other Available CGR Options:

2.9Install the Shunt:

2.10Install the Fuel Flow Transducer:

2.11Install the EI P-300C Fuel Level Probes (OEM or Experimental Only):

2.12Install the EI P-300M Fuel Level Sender:

2.13Install the Resistive Fuel Level Module (RFLM-4-X):

2.14Install the Voice Alarm Control Panel (OEM/Experimental Only):

2.15Install the Intensity Control Pot (Optional):

2.16Install the Master Warning (red) and Caution (yellow) Lights:

2.17Installing the EDC-33P:

7

2.1Important Information and Initial Checkout:

A.The installer and aircraft owner must read the Warranty/Agreement before starting the installation. There is information in the Warranty/Agreement that may alter your decision to install this instrument. If you do not accept the terms of the Warranty/Agreement, do not install this instrument.

B.If you are not an FAA Certified Aircraft Mechanic familiar with the issues of installing

engine and aircraft 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. Check that any	necessary	FAA	Approvals are	available	for your	aircraft before starting
the installation.	The STC	and	AML is located	in section	8 of this	manual.

D.Read the Installation Instructions entirely and resolve any issues you may have before starting the installation. This may eliminate any delays once the installation is started.

E.Inspect the contents of this package prior to installation. If the CGR-30P system is to be installed into a certified aircraft, check that the Model Number listed on the TSO label

incorporates the Aircraft ID for which it is to be installed. Each CGR-30P display is configured for a specific aircraft and should only be installed in that aircraft only.

F.Do not install a non-certified CGR in a certified aircraft. A certified CGR lists the applicable TSO numbers at the bottom of the Model Label attached to the back panel of the CGR.

G. Before starting the installation make sure the instrument will fit in the intended installation location without obstructing the operation of any controls. CFR 23.1321(a) states,

“Each flight, navigation, and powerplant instrument for use by any required pilot during takeoff, initial climb, final approach, and landing must be located so that any pilot seated at the controls can monitor the airplane’s flight path and these instruments with minimum head and eye movement.”

AC 23.1311 provides one method (but not the only method) of complying with this CFR. AC 23.1311 recommends a powerplant instrument be installed within a distance of 21" from the pilot’s visual centerline to the middle of the instrument. The pilot’s visual centerline is a perpendicular line from the pilot’s eye to the instrument panel. In most aircraft, installing the CGR-30P to the right of the Radio Stack would be acceptable. In some aircraft, the visual centerline falls to the right of the Attitude Indicator.

If the powerplant instrument cannot be installed within 8" of the pilot’s visual centerline, AC 23.1311 recommends Master Caution and Warning Lights be installed. Installation of Master Caution and Warning Lights is covered in this manual.

H.If this instrument is to replace an existing gauge 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 (see AC 43.13).

I.An Installation Checklist is provided to assist the installation of the CGR system. It does not replace the instructions located in this manual.

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2.2 Review the "EDC Wiring Work Sheets:"

There are a number of probes and extension cables that will need to be installed. The key to keeping the installation simple is to organize the work using the "EDC Wiring Work Sheets" supplied with this kit. Review the functions assigned to each EDC input on the EDC Wiring Work Sheets. The work sheets are prepared at the factory with the functions and probes already assigned.

2.3 Verify You Have all the Probes, Modules, Transducers and Cables:

The three EDC 37-pin D-sub connectors and the CGR 25-pin D-sub connector are pre-wired at the factory. The three EDC connectors are marked Top, Middle and Bottom. The EDC Wiring Work Sheets provide a list of the probes supplied with this kit.

A.Check that you have all the probes listed on the EDC Wiring Work Sheets.

B.Check that the three EDC 37 pin-D-sub wire harnesses are provided with the proper wires for each of the probes shown on the EDC Wiring Work Sheets.

C.Check that the CGR 25-pin D-sub wire harness is provided.

2.4 Install the CGR Display:

Before starting the installation make sure the instrument will fit in the location you intend to install it without obstructing the operation of any controls. Also, the pilot should have a clear view of the CGR display without any visual obstructions. The CGR display is installed from behind the panel into a standard 3 1/8" hole.

CFR 23.1321(a) states, “Each flight, navigation, and powerplant instrument for use by any required pilot during takeoff, initial climb, final approach, and landing must be located so that any pilot seated at the controls can monitor the airplane’s flight path and these instruments with minimum head and eye movement.” To comply with this requirment mount the CGR-30P 21" or less from the pilot’s visual centerline to the middle of the instrument. The pilot’s visual centerline is a perpendicular line from the pilot’s eye to the instrument panel. In some aircraft, the visual centerline falls to the right of the Attitude Indicator.

If the CGR display is not installed within 8" of the pilot’s visual centerline, the external Master Caution and Warning Lights should be installed. Installation of Master Caution and Warning Lights are covered in this manual.

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2.5 Install the Temperature Probes:

Install only the Temperature Probes applicable for your configuration.

A. EGT Probe Installation:

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 210s or any aircraft having a slip joint in the exhaust system, install the EGT probes ABOVE OR BELOW THE SLIP JOINT. Installing an EGT probe in the slip joint can damage the probe.

To EDC	(Red)
TempInput	(Yel)
(MiddleorBottom
Connector)

P-110 Hose Clamp, Type K. Used on most engines.

B.TIT Probe Installation:

The TIT probe should be installed on the inlet of the Turbocharger one to two inches before the Turbocharger flange. Look at each exhaust stack and determine the best location to install the TIT probe. It should be routed away from the exhaust pipe and should not come in contact with other aircraft components. When installing the P-110 probe, drill a 13/64" diameter hole in the exhaust stack. Insert the probe and tighten the hose clamp.

To EDC	(Red)
TempInput	(Yel)
(MiddleorBottom
Connector)

P-110 Hose Clamp, Type K. Used on most engines.

If a P-111, P-112 or P-114 TIT probe is to be installed, perform the steps outlined in the “TIT Probe Depth Adjustment Procedure” that comes with the TIT probe.

NOTE: After the first 10 hours of operation, the hose clamp on the P-110 probe should be retightened. As the hose clamp is heated and cooled, it will become loose as it conforms to the exhaust stack.

	To EDC	(Red)
	TempInput

(MiddleorBottom (Yel) Connector)

P-111 (1/8" NPT), Type K P-112 (7/16" -20), Type K P-114 (1/4" NPT), Type K Screws into a boss welded onto the exhaust pipe.

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C. CHT Probe Installation:

Most engines have threaded ports for the CHT probes just below the lower spark plug. Install the CHT probes into these threaded ports.

	To EDC	(Red)
	TempInput

(MiddleorBottom (Yel) Connector)

D. OIL Temperature Probe Installation:

P-100 CHT Probe,

3/8" -24, Type K. Used on most engines.

Oil temperature can vary throughout an engine. Your engine’s oil temperature specifications are based on a specific location of the oil temperature probe. If the CGR is to be used as the primary oil temperature instrument, install the oil temperature probe (P-120) in the primary oil temperature pick up point for your engine.

To EDC	(Red)
TempInput
(MiddleorBottom	(Yel)
Connector)

P-120 Oil Temp Probe, 5/8" -18, Type K. Used on most engines.

E. Carb Temp Probe Installation:

Remove the threaded plug located in the carburetor housing just below the throttle valve. Install the Carburetor Temperature Probe (P-128) in this hole using a lock washer. Care should be taken not to over-tighten the probe, thereby stripping the threads in the carburetor housing.

To EDC	P-128 Carb Temp / OAT Probe,
TempInput	1/4" -28, Type K. Used on most
(MiddleConnector,Ch8	engines.
Recommended)

F. 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, if the probe is mounted in the cowling area near a turbo or hot cylinder head, radiant heat may influence the probe temperature. 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.

To EDC	P-128 Carb Temp / OAT Probe,
TempInput	1/4" -28, Type K. Used on most
(MiddleConnector,Ch8	engines.
Recommended)

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G. Other Temperature Probe Installation:

Other temperature probes (Cowl Temp, CDI Temp, Water Temp, etc.) may be installed using current aircraft standards and practices (refer to AC 43.13). Make sure these probes do not interfere with the operation of the engine or aircraft.

2.6 Install the Pressure Transducers:

Install only the Pressure Transducers applicable for your configuration.

A. Manifold Pressure Transducer Installation:

Mount the PT-30ABS Pressure Transducer on the inside firewall or in the equipment bay under the aircraft instrument panel. Use the holes in the bottom plate to mount the PT-30ABS. Only two mounting holes are required.

An equipment bay can be made from a sheet of aluminum. Any piece of equipment or module used with the CGR-30P can be mounted on the aluminum sheet using a Nut Plate or Riv-Nut to allow easy installation and removal. The aluminum sheet is then mounted to the inside firewall of the aircraft (using short spacers) and should never have to be removed. Many aircraft are designed with an equipment bay.

Connect the aircraft manifold pressure line to the pressure port on the PT-30ABS Pressure Transducer. A flare or barb fitting may be used to connect these lines. Care should be taken not to put excess pressure on the flexible line leading to the pressure transducer. Make sure there are no kinks in the flexible pressure lines.

Note: Many certified aircraft have a very small hole in the manifold pressure line to create airflow back to the intake manifold. This small flow of air keeps fuel from working its way into the manifold pressure gauge (or transducer), which can cause damage to the transducer over time.

Note: The PT-30ABS can measure manifold pressure up to 36.0" Hg. For manifold pressures above 36.0" Hg. use the PT-60ABS pressure transducer.

.170" ID Flexible Tube

AircraftM.P.Line

								The PT-30ABS, Pres-
To EDC	(Red)							sure Transducer is used
	(Blk)							on most engines for
PressInput
	(Grn)							Manifold Pressure (0 to
(TopConnector) (Wht)								36" Hg.).

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#2 90' - MS20822-2D

#3 90' - MS20822-3D

* #4 90' - MS20822-4D

The PT-100GA Pressure Transducer is used on most engines for pressures up to 120 psi.

B. Gyro Vacuum Pressure Transducer Installation:

Mount the PT-05Diff Pressure Transducer on the inside firewall or in the equipment bay under the aircraft instrument panel. Use the holes in the bottom plate to mount the PT-05Diff. Only two mounting holes are required.

Connect the aircraft gyro vacuum line to the port tagged "Vac" on the PT-05Diff. Connect the port tagged "Press" to the aircraft overboard pressure line. A flare or barb fitting may be used to connect these lines. Care should be taken not to put excess pressure on the flexible line leading to the pressure transducer.

Make sure there are no kinks in the flexible pressure lines.

			PRESS
			Overboard Pressure Line
			VAC
		(Red)	Gyro Vacuum Line
	To EDC
	Press Input	(Blk)
		(Grn)	The PT-05Diff, Pressure
	(Top Connector)
		(Wht)
			Transducer (0 to 6" Hg)

C. Oil Pressure Transducer Installation:	To EDC	(Red)
	PressInput	(Blk)
Find a convenient location on the firewall or a	(TopConnector)	(Grn)
		(Wht)
bracket and mount the pressure transducer with the
clamp provided. The oil pressure line does not have

to be routed into the cabin area, although you will need access on the cabin side of the firewall to tighten the pressure transducer clamp nut. Do not mount the pressure transducer to an engine baffle or directly on the engine with the transducer supported by an adapter or fitting. Vibration can cause the adapter to break, resulting in loss of engine oil. The pressure transducer is equipped with an 1/8" NPT male port. This port can be adapted to any oil pressure line. Use only a flexible hose and fittings suitable for aircraft use. Route a flexible oil pressure line from the primary oil pressure pickup point to the pressure transducer and tighten all fittings.

Do not use the case of the pressure transducer to tighten the pressure fittings. Maintain any restrictive orifice currently in the system.

Some fittings you may want to consider using are listed below:

											* #2 Straight - AN816-2D
											#3 Straight - AN816-3D
1/8 NPT Male		1/8 NPT									#4 Straight - AN816-4D
							1/8 NPT Male
		Coupler									#2 45' - MS20823-2D
											#3 45' - MS20823-3D
PT-100GA											#4 45' - MS20823-4D

AN910-1D Flare

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The PT-30GA Pressure Transducer is used on most engines for pressures up to 40 psi.

D. Fuel Pressure Transducer Installation:
Find a convenient location on the firewall or a bracket	To EDC	(Red)
and mount the pressure transducer with the clamp	PressInput	(Blk)
		(Grn)
provided. The fuel pressure line does not have to be	(TopConnector)	(Wht)
routed into the cabin area although you will need access

on the cabin side of the firewall to tighten the pressure

transducer clamp nut. Do not mount the pressure transducer to an engine baffle or directly onto the engine with the transducer supported by an adapter or fitting. Vibration can cause the adapter to break, resulting in loss of engine fuel. The pressure transducer is equipped with a 1/8" NPT male port. This port can be adapted to any fuel pressure line. Use only a flexible hose and fittings suitable for aircraft use. Route a flexible fuel pressure line from the primary fuel pressure pick up point to the pressure transducer and tighten all fittings. Do not use the case of the pressure transducer to tighten the pressure fittings. Maintain any restrictive

orifice currently in the system.

* Some fittings you may want to consider using are listed above.

E. Other Pressure Transducer Installations:

Other pressure transducers should be mounted in the aircraft in the same manner as the Gyro Vacuum Transducer or the Oil and Fuel Pressure Transducers, as appropriate. Note: Any unused + or - pressure inputs must be wired to a ground pin on the EDC 37-pin connector.

2.7 Install the Interface Circuit for Annunciators:

Any Temperature or Resistive Fuel Level channel on the EDC may be used to monitor the state of a switch, relay or output from a device. This output can be used to trigger a light (annunciator) on the CGR. Annunciator lights such as Canopy Latch, Baggage Door, Deice, Pitot Heat, Fire, etc. can be displayed on the Main or System screen on the CGR.

To monitor a voltage, a VI-221 (Voltage Interface Unit) will be required. This consists of a 221K ohm resistor heat shrunk between two wires with a D-Sub pin crimped on one end. The following methods may be used to interface an EDC channel (using a VI-221) to a switch, relay or device:

A. Monitoring a Signal That Switches Between Any Voltage and Ground:

Device, Switch or Relay

EDC

Bus or any Voltage VI-221 Temp or Resistive Fuel Level Channel.

Load

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