L-1502
MO DAY YEAR
Champion Aerospace LLC
1230 Old Norris Road
Liberty, South Carolina, U.S.A. 29657
© 2009 Champion Aerospace LLC
www.championaerospace.com
CHAMPION AEROSPACE LLC PROPRIETARY INFORMATION - Subject to the restrictions on the Title page
ISSUED
PAGE REV.
PAGE NO.
REVISED
MO DAY YEAR
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96
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C
2.2.19 Reconnect Aircraft Battery
A.
Confirm that the Master Switch and Ignition Switch are in the “OFF” position.
B.
Reconnect the negative lead of the aircraft electrical system to the negative terminal of the
aircraft battery.
WARNING
:
THE LASAR
®
SYSTEM IS ARMED AND READY TO FIRE AT ENGINE TDC WHEN THE
IGNITION SWITCH IS IN THE “BOTH” OR “START” POSITION AND THE MASTER
SWITCH IS “ON.” FORWARD AND REVERSE MOVEMENT OF THE PROPELLOR
MAY TRIGGER AN IGNITION EVENT.
2.2.20 Ground Test LASAR
®
System
A.
Prior to all flights, test the LASAR
®
System on the ground. Operate the engine according to the
Pilot Operating Handbook and Flight Manual Supplement FMS 1-96. Perform a normal magneto
check, switching from the “BOTH” position to the “RIGHT” and “LEFT” position.
2.2.21 Complete Documentation
A.
Make all appropriate logbook entries. LASAR
®
is approved by STC and requires FAA Form 337
to be filed with the FAA. Attach Flight Manual Supplement FMS 1-96 to the aircraft flight manual.
Complete and return the LASAR
®
Product Registration Card, L-1516.
2.3
INSTALLATION OF LASAR
®
SYSTEMS WITH CYLINDER HEAD TEMPERATURE CONTROL
This section describes the installation of cylinder head temperature probe assemblies that must be
used with certain LASAR
®
controllers. This section does not apply to LASAR
®
controllers which are not
configured with the CHT control feature. Install the LASAR
®
ignition system as described in Section 2.2
before continuing.
2.3.1 Identify Cylinder for CHT Probe Assembly Installation
NOTE
: The full timing advance function of LASAR
®
ignition systems equipped with CHT control
requires the proper signal from a functioning CHT probe.
Prior to installation of CHT probe assembly, the cylinder that produces the highest temperature during
full power, maximum rate of climb configurations must be identified. If this cylinder is not known, then it
may be identified using one of the following methods:
A.
Consult engine and/or airframe manufacturer’s data for location of the cylinder that produces the
highest temperature during full power, maximum rate of climb configurations for the particular
airframe model on which the LASAR
®
is to be installed.
B.
If the engine is equipped with a multi-point CHT monitoring instrument, record the maximum
temperature for EACH cylinder as the aircraft is flown in maximum power, maximum rate of climb
until the CHT stabilizes or begins to decrease. During the climb, follow procedures detailed in the
engine and airframe Pilot Operating Handbook (POH).
C.
If the engine is not equipped with CHT instrumentation, temporarily install a CHT system as a tool
to record the maximum temperature for each cylinder as the aircraft is flown in maximum power,
maximum rate of climb to an absolute altitude of 8,000 feet MSL. During the climb, follow
procedures detailed in the engine and airframe Pilot Operating Handbook (POH). A single point
CHT gauge can be used as a tool by installing the probe on each cylinder and making multiple
flights.
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