EIS-61000

Instructions for Continued

Airworthiness

Electroair
5097 Williams Lake Road
Waterford, MI 48329 U.S.A.
Ph: 248-674-3433 Fax: 248-674-4231
Email: sales@electroair.net

Electroair Acquisition Corp. ICA EIS-61000 Page 1 of 18

Revision 14 Prepared by: EAC 12/17/2021
 Table of Contents
Table of Contents ............................................................................................................ 1
Revision Log ................................................................................................................... 3
1.0 Introduction: .............................................................................................................. 4
2.0 System Description ................................................................................................... 4
2.1 Dual Electronic Ignition Systems Limitations and Requirements ............................... 6
3.0 System Operating Information ................................................................................... 7
3.1 Placards .................................................................................................................... 7
4.0 Service Information ................................................................................................... 7
5.0 Maintenance Instructions .......................................................................................... 8
5.1 Precautionary Statements: ........................................................................................ 8
5.2 Scheduled Maintenance ............................................................................................ 8
5.2.1 Annually: ................................................................................................................ 8
5.2.2 Each 1000 hours or five years: ............................................................................... 9
5.2.3 At 2500 hours or Sudden Stoppage: ...................................................................... 9
5.3 Installation and Removal Instructions ...................................................................... 10
5.4 Trouble-shooting ..................................................................................................... 10
5.4.1 Specification Checks ............................................................................................ 10
5.4.2 Higher than Normal RPM drops during Ignition Check ......................................... 11
5.4.3 Engine runs poorly or rough ................................................................................. 12
5.4.4 High CHTs ............................................................................................................ 12
5.4.5 Hard Starting and/or Engine Kick-Back during starting ........................................ 13
5.4.6 Engine runs poorly or rough at high RPM and/or high engine load ...................... 13
5.4.7 EIS dropping off-line or is intermittent. ................................................................. 13
5.4.8 EIS will not start.................................................................................................... 14
5.5 Special Inspection ................................................................................................... 14
6.0 Receiving and Acceptance Checking of EIS Kit: ..................................................... 15
7.0 Eligibility: ................................................................................................................. 16
8.0 Manual Reference: .................................................................................................. 16
9.0 Airworthiness Limitations Section (ALS):................................................................. 17
10.0 Glossary and Abbreviations: ................................................................................. 18

Electroair Acquisition Corp. ICA EIS-61000 Page 2 of 18

Revision 14 Prepared by: EAC 12/17/2021
 Revision Log
Pages Date of Approved Date of
Revision Description of Revision
Affected Revision by Approval
00 08/26/2013 Initial Release KP 08/26/2013

01 09/30/2013 Document Maintenance KP 09/30/2013

Corrected issues from FAA
02 10/01/2013 memo dated 08/30/2013 and KP 10/01/2013
received 09/30/2013
03 11/01/2013 Added handling information. KP 11/04/2013
Corrected issues from AEG
04 11/25/2013 follow up email dated KP 11/25/2013
11/22/2013.
Added information regarding
05 11/25/2013 MTH cover orientation to KP 11/25/2013
annual inspection.
06 05/06/2014 ECO 1116-0050 05/06/2014

07 09/03/2014 ECO 1116-0071 10/01/2014

08 01/28/2015 ECO 1116-0110 03/16/2015

09 08/10/2015 ECO 1116-0136 08/10/2015

10 12/14/2015 ECO 1116-0144 12/18/2015

11 1,3,5,6,8 03/20/2018 ECO 1019-0051 JMS 03/20/2018

12 3,6,8 05/17/2019 SA09950CH-A JMS 07/24/2019

SA09966CH-A: Electronic
13 2-13 05/20/2021 Ignition Timing Software JMS
Project
14 2-18 12/17/2021 Dual EIS Updates JMS

Electroair Acquisition Corp. ICA EIS-61000 Page 3 of 18

Revision 14 Prepared by: EAC 12/17/2021
1.0 Introduction:
This Instruction for Continued Airworthiness contains the necessary information
required for the maintenance of the electronic ignition system (EIS) approved for
installation in accordance with STC SA03286CH. Electroair is responsible for this
document and any changes to it will be made electronically.

2.0 System Description

For STC SA03286CH, the Electroair EIS-61000 Electronic Ignition System can be used
as a single magneto replacement, or with certain limitations, can replace both
magnetos. An aircraft equipped with an EIS-61000 and a single magneto or two EIS-
61000s will make up the dual ignition system. The EIS-61000 kit consists of the
following components: Controller (EA-21000), Coil Pack (EA-8000), Spark Plug Wires
(EA-4000(T)), Wire Harness (EA-22000), and Trigger Mechanism (EA-11000, EA-
9000A, EA-10000, EA-12000, EA-16000, EA-17000, and EA-19000). One trigger
mechanism per kit.

Figure 1: EIS-61000-1M Kit

The EIS-61000 Electronic Ignition System performs its function by delivering energy
generated by the coil pack to each spark plug attached to the system. This high voltage
from the coil pack (on the order of 70,000V), creates a high intensity, long duration
spark which more effectively ignites a wide range of fuel/air mixtures inside of the
cylinder. The EIS-61000 is also able to vary the ignition timing (spark event) during the
combustion cycle so as to more closely have the peak pressure as a result of
combustion occur at an optimal range for a piston engine. The adjustment of ignition
timing is based on MAP inside the engine. The combination of a high energy spark and
variable timing, the two principle differences between the EIS-61000 and a magneto,
permits more an efficient operation of the engine. The trigger mechanisms send a
speed and position signal to the controller. The trigger mechanisms attach to the engine

Electroair Acquisition Corp. ICA EIS-61000 Page 4 of 18

Revision 14 Prepared by: EAC 12/17/2021
either at the magneto hole (MAG Timing Housing(MTH), EA-10000, EA-12000, EA-
16000, EA-17000, and EA-19000) or on the crankshaft (Crank Shaft Trigger Wheel
(CSTW), EA-11000 or EA-9000A). One trigger mechanism per kit.

Figure2: EA-12000 MTH (from EIS-61000-5M kit)

Figure 3: EA-9000A CSTW Kit (Missing magnetic sensor)

The EIS-61000 is operated by DC power provided by the aircraft’s power bus. There
are two circuit protection devices used for the EIS-61000; reference table one for the
type and size of the protection devices. These circuit protection devices are not
normally accessed during flight.

The EIS-61000 is controlled by using the switch labeled “EIS”. The EIS-61000 may be
disabled by setting the switch labeled “EIS” to the OFF position. Pilots should
familiarize themselves with the location of the “EIS” before proceeding with the pre-flight
checklist.
FUNCTION IDENT RATING BUS POWER SUPPLY
EA-21000 Power EIS 2.0 AMP Aircraft Power 12/24VDC
EA-8000 Power EIS 10.0 AMP Aircraft Power 12/24VDC
Table One: DC Circuit Protection

Electroair Acquisition Corp. ICA EIS-61000 Page 5 of 18

Revision 14 Prepared by: EAC 12/17/2021
2.1 Dual Electronic Ignition Systems Limitations and Requirements

The electrical power requirements for engines equipped with dual electronic ignition systems will
require a separate source of backup electrical power that is independent of the primary source.
The separate source of electrical power can take one to the following forms:

 Dual Electrical System: On aircraft with a dual battery or dual alternator/generator

systems with independent primary electrical busses, power from each of the electrical
busses can be used when the failure of one electrical system is isolated from the other
system.
o Note: Twin-engine applications with dual electrical systems may share a common
backup power source, independent of either engine’s primary power source, which
can provide electrical power after loss of power from both independent electrical
systems.
 Backup Alternator/Generator System: This system differs from the Dual Electrical
System because the backup alternator/generator is not used as a primary source of
aircraft electrical power. The backup alternator/generator is used, as an alternate source
of electrical power should the primary system fail. These systems are usually attached to
either a dedicated or an essential buss and offer reduced current capability when
compared to the primary system.

The following must be shown for any backup power supply configuration proposed on any
airplane engine installation equipped with a dual EIS.

(1) If any emergency or other procedure recommends or requires the shutoff of any or
all electrical systems in flight, such as for smoke in the cabin or loss of a power
generation, then a dedicated backup power source must be provided, which is
independent of the primary electrical system and automatically available when any
electrical system is shutoff in flight. This applies to both single and dual buss systems on
single and multi-engine airplanes.
(2) For any one engine on a single or multi-engine airplane, it must take at least two
independent power source failures for a LOPC event
(3) For twin-engine airplanes, it must take at least three independent power source
failures for a LOPC event in both engines.
(4) For twin-engine installations, the design must continue to meet the powerplant
isolation requirements of §23.903(c), including in at least one configuration, an
independent power supply for at least one EIS on each engine.

The minimum requirements for the electrical power system are addressed in 14 CFR 23.1309,
23.1351, 23.1353, 23.1357, 23.1359, 23.1361, 23.1365 and 23.1367. The time required in 14
CFR 23.1353(h) is the minimum time for backup electrical power in the event of a failure of
primary aircraft electrical power. The backup power does not need to be wholly dedicated to the
electronic ignition system since other critical systems may be supplied by the backup electrical
power. However, following the loss of the primary power generation system, a minimum of 60
minutes of backup electrical power for the electronic ignition system is highly recommended.
Additionally, the inherent redundancy of an independent power source dedicated to the
electronic ignition system is also highly recommended when considering an aircraft electrical
power failure.

Please contact Electroair with any questions or clarifications.

Electroair Acquisition Corp. ICA EIS-61000 Page 6 of 18

Revision 14 Prepared by: EAC 12/17/2021
3.0 System Operating Information
Under normal operating conditions, the EIS-61000 Electronic Ignition System will be
controlled by the flight crew in the same manner as the magneto that was previously
installed. The AFM has been updated to reflect the change to the aircraft ignition
system. Refer to Operation Manual: AFMS EIS-61000 revision 09 or later FAA
approved revision. Installation Manual: IM EIS-61000 revision 16 or later FAA approved
revision.

3.1 Placards

Ignition system will be placarded in accordance with installation instructions, identifying

the magneto and the EIS. In the case of two or more EISs, placards should differentiate
between each EIS.

4.0 Service Information

Refer to aircraft maintenance manual for access and locations of components.
No servicing is required for the EIS-61000 and its components.

Electroair Acquisition Corp. ICA EIS-61000 Page 7 of 18

Revision 14 Prepared by: EAC 12/17/2021
5.0 Maintenance Instructions
5.1 Precautionary Statements:

 Read this entire document before starting any processes listed within. If there
are any questions please contact Electroair before starting to resolve them.
(248-674-3433 or sales@electroair.net)
 If an EIS is improperly installed, maintained, or misfired; the EIS, the aircraft, the
engine, or the installer could be seriously damaged.
 Always use appropriate work and safety practices.
 Spark plug leads shall be disconnected from the ignition system before
inspection.
 DO NOT NEGLECT the required maintenance of the remaining magneto or
pressurize magneto.
 For the latest up to date information refer to www.electroair.net (ICA, AML,
Installation Manual, AFMS, etc.)
 For abnormal operation, for ignition systems that have a suspected failure, refer
to the Electroair Trouble Shooting Instructions at
http://electroair.net/pdfs/troubleshooting_the_EIS.pdf
 For AD notes, service bulletins, or other product notes, review Electroair website
(www.electroair.net).
 For ordering or questions about replacement parts, please contact Electroair.
(248-674-3433 or sales@electroair.net)

5.2 Scheduled Maintenance

5.2.1 Annually:
1. Inspect all wire connectors. Verify connections are securely attached and free from
damage such as chaffing or excessive heat exposure.
2. Inspect all ground connections. Verify the connections have continuity with the
ground terminal on the aircraft battery or other acceptable ground buss using an
Ohmmeter.
3. Inspect “Gasket” area on MAG Time Housing (MTH), if installed. Ensure no oil leaks
coming from the gasket area. If a new gasket is required contact the factory for
replacement part number: EA-001J.
4. Inspect for oil seal failures if MTH is installed.
a. Remove the MTH cover.
b. Inspect for oil pooling. If oil seal has failed, MTH must be replaced. Note: A thin
film of oil does not indicate a failure.
c. Replace the cover in the same orientation it was removed.
d. NOTE: The MTH is not a field serviceable or repairable unit.
5. Inspect all spark plug wires to check for exterior damage such as cuts in silicone,
chaffing, evidence of arcing or burn marks. Replace wires if damage is evident. If
any wire is suspected of misfiring, verify continuity and resistance values of the wire.
Resistance values: Blue Wire (p/n EA-4090) resistance is 350 ohms/ft ±10%. Red
Wire (p/n EA-4091) resistance is 5700 ohms/ft ±10%. If wire does not have

Electroair Acquisition Corp. ICA EIS-61000 Page 8 of 18

Revision 14 Prepared by: EAC 12/17/2021
 continuity or is out of resistance value range, replace spark plug wire. Use part
number EA-4000REM if using REM spark plugs. Use part number EA-
4000RHMRHB if using RHM or RHB spark plugs. Refer to the installation manual,
IM EIS-61000, for instructions on how to install spark plug wires.
6. Remove and inspect spark plugs.
a. Replace if fouled or out of acceptable resistance range. Acceptable resistance
range of Electroair sparkplugs should be 5000Ω or less. For non-Electroair spark
plugs, refer to the spark plug manufacturer for resistance values.
b. Verify spark plug gap at this time. For non-Electroair manufactured spark plugs,
refer to manufacturers maintenance instructions on how to adjust the gap. Adjust
as required.
c. The gap for the Electroair spark plugs is preset at 0.036 inches. Acceptable
range is 0.028-0.038. Gaps larger than the acceptable range should be closed to
acceptable range.
7. Inspect all placards and labels for existence and legibility. If missing or no longer
readable, replace. Any original placards were created by original install. Refer to
Installation manual, IM EIS-61000 Revision15 or later FAA approved revision, for
required placards or labels and follow those instructions if replacements are needed.
8. If fuses were used instead of circuit breakers, inspect for the existence of readily
accessible spare fuses. (Note: 14CFR 91.205(c)(6) applies when using fuses.)

5.2.2 Each 1000 hours or five years:

1. Replace spark plug wires and attaching hardware with new Electroair spark plug
wires and attaching hardware. Use part number EA-4000REM if using REM spark
plugs. Use part number EA-4000RHMRHB if using RHM or RHB spark plugs. Refer to
the installation manual, IM EIS-61000 revision15 or later FAA approved revision, for
instructions on how to install spark plug wires.

5.2.3 At 2500 hours or Sudden Stoppage:

1. Replace MAG Timing Housing (MTH), if installed, with a new or rebuilt Electroair
MTH part number EA-10000, EA-12000, EA-16000, EA-17000, or EA-19000 series
appropriate for the engine, at 2500 hours after installation or sudden stoppage. Reinstall
MTH in accordance with the installation manual: IM EIS-61000 revision15 or later FAA
approved revision.

2. Inspect Crank Shaft Trigger Wheel (CSTW), if installed, and brackets.

a. Replace magnetic sensor, part number: EA-9070.
b. Inspect brackets for any damage (bending or cracking). Replace damaged
brackets.
c. Remove crank trigger wheel and inspect for damage (bending or
cracking). Replace if damaged. Reinstall CSTW assembly in accordance
with the installation manual: IM EIS-61000.

Electroair Acquisition Corp. ICA EIS-61000 Page 9 of 18

Revision 14 Prepared by: EAC 12/17/2021
5.3 Installation and Removal Instructions

1. For removal, follow the EIS-61000 Installation Manual in reverse order.

2. For instructions on reinstalling individual EIS-61000 components or the entire system,
refer to the EIS-61000 Installation Manual that was included with the EIS 61000 kit. If
the original manual is not with the system, contact the factory for an up to date
replacement installation manual (248-674-3433 or sales@electroair.net) or retrieve from
the factory’s website www.electroair.net.
3. After re-install, to verify the operation of the EIS system, perform a normal start and
ignition check per aircraft’s Pilot Operating Handbook (POH) and AFMS EIS-61000
revision 09 or later FAA approved revision.

5.4 Trouble-shooting

If experiencing abnormal conditions not listed in this section or these troubleshooting

instructions do not solve the issue, contact Electroair for assistance.

5.4.1 Specification Checks

These specification checks are not required to be performed on a periodic basis. They
are provided here for reference in the event that the EIS is malfunctioning.

1. Magnetic Sensor Resistance Check: Electroair has two types of magnetic

sensors. Both function in the same way and have three wires, but have different
resistance values. Resistance is checked across two of the three wires at the
connector. The sensor has either a red, black, and bare wire, or a white, black,
and bare wire.
- Measured resistance across the red and black wires should be between 600-
800 Ohms.
- Measured resistance across the white and black wires should be between 900-
1100 Ohms.
2. Gap between magnetic sensor and trigger wheel check: A feeler gauge can
be used to check the gap between the magnetic sensor and the trigger wheel on
the MTH or CSTW.
- MTH Gap: 0.008-0.015”. Set at 0.011” at factory.
- CSTW Gap: 0.024”
3. Coil Pack Resistance Check: Resistance of coils on the EA-2000 or EA-8000
should be between 10k-12k ohms. To check resistance, measure from tower to
tower across the same coil. Tower 1 to Tower 2 and Tower 3 to Tower 4 for the
EA-2000. Tower A to A, B to B, and C to C for the EA-8000.
4. Spark Plug Wire Resistance Check: Spark plug wire resistance is measured
from end to end. Boot terminal to boot terminal, or boot terminal to spring end.
- Blue Wire (part # EA-4090): 350 ohms per foot (+/- 10%)
- Red Wire (part # EA-4091): 5700 ohms per foot (+/- 10%)

Electroair Acquisition Corp. ICA EIS-61000 Page 10 of 18

Revision 14 Prepared by: EAC 12/17/2021
5. Spark Plug Gap Check: The gap for the Electroair spark plugs is preset at 0.036
inches. Acceptable range is 0.028-0.038. Gaps larger than the acceptable range
should be closed to acceptable range.

5.4.2 Higher than Normal RPM drops during Ignition Check

1. Perform an ignition check and note the RPM drops. If magneto has higher than
normal RPM drop, service the magneto. If EIS has higher than normal RPM drop,
proceed to step 2.
2. If engine is running poorly or rough, proceed to Section 5.4.3 “Engine runs poorly
or rough”. If engine is not running poorly or rough, proceed to step 3.
3. Check Cylinder Head Temperatures (CHTs). If any CHT is high, proceed to
Section 5.4.4 “High CHTs”.
4. Perform and induction leak check. If there is a leak, repair the leak and then
verify if the RPM drop problem has been fixed. If there is no leak or the RPM drop has
not been fixed, proceed to step 5.
5. Inspect MTH for oil seal failure or other damage.
a. Remove the MTH cover.
b. Inspect for oil pooling. If oil seal has failed, MTH must be replaced. Note:
A thin film of oil does not indicate a failure.
c. Inspect tamper paint and trigger wheel. If tamper paint has been disturbed
or trigger wheel has been loosened from the screws and shaft, MTH must be
replaced.
d. Replace the cover in the same orientation it was removed.
e. NOTE: The MTH is not a field serviceable or repairable unit.
6. Check the gap between magnetic sensor and trigger wheel. Make sure the
sensor is held firmly in place by the set screws. Verify that the trigger wheel has not
struck the sensor. If the trigger wheel has struck the sensor, then the sensor needs to
be replaced.
7. Verify the correct installation of the MTH or CSTW. The trailing edge of the 11 th
tooth after the two missing teeth on the trigger wheel needs to be centered under the
sensor with the engine at TDC cylinder #1. Correct as necessary, then verify RPM drop
has been fixed. See Figure 4 for tooth alignment.

Figure 4: Trigger Wheel Positioning for TDC

Electroair Acquisition Corp. ICA EIS-61000 Page 11 of 18

Revision 14 Prepared by: EAC 12/17/2021
5.4.3 Engine runs poorly or rough

1. Verify all ground connections are competent and have continuity with the ground
terminal on the aircraft battery or other acceptable ground buss using an ohmmeter.
2. Verify that spark plug wires are set to correct firing order and securely connected
at the coil tower and spark plug.
3. Inspect all spark plug harness for evidence of arcing or arc-out (indicated by
small burn marks near the spark plug/spring); round black marks on spark plug wire
near attaching hardware. Repair or replace as necessary.
4. Inspect all spark plugs for proper gap, cracked ceramic, cleanliness, wear and
resistance. Resistance values should be 5k ohms or less. Repair or replace as
necessary.
5. Verify placarded timing on controller matches engine placarded timing.
6. Record RPM rise on shutdown. Verify that this meets engine requirements. If it
doesn’t meet the engine requirements, follow the steps from the engine manufacture
instructions to fix the problem.
7. If one or more cylinders can be identified as dropping off, swap wires at coil
towers. If problem remains with suspect cylinder, inspect and repair plug or wire as
necessary. If problem moves to a different cylinder, replace the coil pack.

5.4.4 High CHTs

1. Verify placarded timing on controller matches engine placarded timing.

2. Verify the correct fuel is being used and verify the fuel system is working
correctly.
3. Perform and induction leak check. If there is a leak, repair the leak and then
verify if the problem has been fixed. If there is no leak or the problem has not been
fixed, proceed to step 4.
4. Inspect the MTH for oil seal failure or other damage.
a. Remove the MTH cover.
b. Inspect for oil pooling. If oil seal has failed, MTH must be replaced. Note:
A thin film of oil does not indicate a failure.
c. Inspect tamper paint and trigger wheel. If tamper paint has been disturbed
or trigger wheel has been loosened from the screws and shaft, MTH must be
replaced.
d. Replace the cover in the same orientation it was removed.
e. NOTE: The MTH is not a field serviceable or repairable unit.
5. Check the gap between magnetic sensor and trigger wheel. Make sure the
sensor is held firmly in place by the set screws. Verify that the trigger wheel has not
struck the sensor. If the trigger wheel has struck the sensor, then the sensor needs to
be replaced.
6. Verify the correct installation of the MTH or CSTW. The trailing edge of the 11th
tooth after the two missing teeth on the trigger wheel needs to be centered under the
sensor with the engine at TDC cylinder #1. Correct as necessary. See Figure 4 for tooth
alignment.

Electroair Acquisition Corp. ICA EIS-61000 Page 12 of 18

Revision 14 Prepared by: EAC 12/17/2021
5.4.5 Hard Starting and/or Engine Kick-Back during starting

1. Verify all ground connections are competent and have continuity with the ground
terminal on the aircraft battery or other acceptable ground buss using an ohmmeter.
2. Check for a weak battery.
3. Check for bad/worn/small gauge starter cables.
4. Verify that the RPM is above 60RPM during starting.
5. Verify the correct installation of the MTH or CSTW. The trailing edge of the 11th
tooth after the two missing teeth on the trigger wheel needs to be centered under the
sensor with the engine at TDC cylinder #1. Correct as necessary. See Figure 4 for tooth
alignment.
6. Verify placarded timing on controller matches engine placarded timing.
7. Verify that fuel system is working correctly.

5.4.6 Engine runs poorly or rough at high RPM and/or high engine load

This indicates possible failure of either a spark plug or spark plug wire.

1. Inspect all spark plug harness for evidence of arcing or arc-out (indicated by
small burn marks near the spark plug/spring); round black marks on spark plug wire
near attaching hardware.
2. Inspect all spark plugs for proper gap, cracked ceramic, cleanliness, wear and
resistance. Resistance values should be 5k ohms or less. Repair or replace wires
and/or spark plugs as necessary.

5.4.7 EIS dropping off-line or is intermittent.

1. Perform a Magnetic Sensor Resistance Check. See section 5.4.1. Replace

sensor if resistance is outside of the specified range.
2. Inspect the power supply to the controller. Check voltage at Pin 6 on the C1
connector in the EA-22000(T) wire harness. Voltage needs to be at least 10 volts for
EIS to run.
3. Inspect the power supply to the coil pack. Check voltage at Pin 4 on the C2
connector in the EA-22000(T) wire harness (See Figure 5). Voltage needs to be at least
10 volts for EIS to run.

Electroair Acquisition Corp. ICA EIS-61000 Page 13 of 18

Revision 14 Prepared by: EAC 12/17/2021
 Figure 5: Power Pin of Coil Pack Connector (C2)

5.4.8 EIS will not start

1. With power on to the system, check the LED on the EA-20000 controller. If the
LED is not on, then the system is not receiving power. Inspect wiring for bad
connections or damage. Repair as necessary.
2. Check to see is controller and coil pack are receiving enough voltage. Voltage
needs to be at least 10 volts during the starting sequence for the EIS to run.
3. Verify that the RPM during starting is at least 60 RPMs. The EIS needs to be
able to read 2 consistent rotations of the engine above 60 RPM before it starts.
4. Perform a Magnetic Sensor Resistance Check. See section 5.4.1. Replace
sensor if resistance is outside of the specified range.

5.5 Special Inspection

Lightning Strikes, Engine Fires, Water Immersion:

1. Inspect the EIS wiring harness and controller.
2. If there is obvious damage, replace the damaged parts.
3. If there is no obvious damage, perform a ground run-up. If no problems are found,
continue with the standard procedures as stated in the AFMS.
4. If unsure, contact factory (248-674-3433 or sales@electroair.net)

Electroair Acquisition Corp. ICA EIS-61000 Page 14 of 18

Revision 14 Prepared by: EAC 12/17/2021
6.0 Receiving and Acceptance Checking of EIS Kit:
1. Review the packaging before acceptance from the freight carrier. If damaged refuse.
2. Open the package. Components of the EIS kit are inserted into different sections
and each component should be handled with care.
3. Review the contents of the package to the content listing on the package.
4. Are all of the materials there?
a. Yes, proceed to step 4.
b. No, contact the factory. Have the serial number of the kit available when
contacting. (factory 248-674-3433 or sales@electroair.com)
5. Review the controller for damage to the aluminum housing.
6. Review the wires for nicks and cracks.
7. Review the coil pack and plate for external damage.
8. Review the CSTW/MTH for external damage.
9. Are all materials acceptable?
a. Yes, proceed with installation.
b. No, contact the factory. Have the serial number of the kit available when
contacting. (factory 248-674-3433 or sales@electroair.com)

If possible, store parts in original packaging when not in use. If not possible, wrap parts
in cushioning material and place in one location. Review as above prior to
reinstallation.

Electroair Acquisition Corp. ICA EIS-61000 Page 15 of 18

Revision 14 Prepared by: EAC 12/17/2021
7.0 Eligibility:
Make: Lycoming Continental
540 6-cylinder series
360 6-cylinder series
541 6-cylinder series
470 6-cylinder series
580 6-cylinder series
520 6-cylinder series
550 6-cylinder series
Model:
300 6-cylinder series
E-165 6-cylinder series
E-185 6-cylinder series
E-225 6-cylinder series
(See STC#03286CH Approved Model List (AML) for exact model numbers)

8.0 Manual Reference:

Electroair Kit Part Number Installation Manual Number
EIS-61000-1C IM EIS-61000
EIS-61000-T1C IM EIS-61000
EIS-61000-5C IM EIS-61000
EIS-61000-T5C IM EIS-61000
EIS-61000-TTT5C IM EIS-61000
EIS-61000-1M IM EIS-61000
EIS-61000-T1M IM EIS-61000
EIS-61000-4M IM EIS-61000
EIS-61000-5M IM EIS-61000
EIS-61000-T5M IM EIS-61000
EIS-61000-TTT5M IM EIS-61000
EIS-61000-6M IM EIS-61000
EIS-61000-T6M IM EIS-61000
EIS-61000-7M IM EIS-61000
(See STC#03286CH Approved Model List (AML) for kit part number applicability)

Electroair Acquisition Corp. ICA EIS-61000 Page 16 of 18

Revision 14 Prepared by: EAC 12/17/2021
9.0 Airworthiness Limitations Section (ALS):
Airworthiness Limitations section is FAA approved and specifies maintenance required
under 14 CFR §§43.16 and 91.403 of the Federal Aviation Regulations unless an
alternative program has been FAA approved.

For Dual Electronic Ignition System installation:

"Dual Electronic Ignition System Installation is eligible for these airplane models that
have converted to Dual Split buss electrical systems or dual alternator system by FAA
Approved means as applicable.

For aircraft with a dual, or back-up alternator, one EIS shall be attached directly to the
back-up alternator. The load attached to each alternator shall not exceed 80% of the
total capacity for the alternator, and may need to be adjusted to allow for supplying
power to one of the Electroair Electronic Ignition Systems (when dual Electroair systems
are installed). Refer to the appropriate Electroair Installation Manual for your kit to
receive additional, detailed information."

FAA Date of
Date of
Revision Description of Revision Approved FAA
Revision
by Approval
11 03/20/2018 ECO 1019-0051 07/17/2018

12 05/17/2019 SA09950CH-A 07/24/2019

14.01 03/31/2022 ALS Update

FAA Approved: _______________________________ Date:________________

Electroair Acquisition Corp. ICA EIS-61000 Page 17 of 18

Revision 14 Prepared by: EAC 12/17/2021
10.0 Glossary and Abbreviations:
 AD(s) – airworthiness directive(s)
 AFM – aircraft flight manual
 AFMS – aircraft flight manual supplement
 ALS – airworthiness limitations section
 AML – approved model list
 BTDC – before top dead center
 CFR – code of federal regulations
 CHT – Cylinder Head Temperature
 CSTW – crankshaft trigger wheel
 EIS – electronic ignition system
 FAA – federal aviation administration
 LOPC – Loss Of Power Control
 MAG -- magneto
 MAP – manifold absolute pressure
 May/Should – an optional requirement
 MTH – mag timing housing
 MEL – minimum equipment list
 Must/Shall – a mandatory requirement
 POH – Pilot Operating Handbook
 RPM – revolutions per minute
 STC – Supplemental Type Certificate
 TDC – top dead center

Electroair Acquisition Corp. ICA EIS-61000 Page 18 of 18

Revision 14 Prepared by: EAC 12/17/2021