Lycoming TEO-540-A1A Installation And Operation Manual page 77

TEO-540-A1A Engine Installation and Operation Manual
A. The pre-flight test operates in the following sequence (with a calibrated delay between
each test in the pre-flight test):
(1) Exhaust bypass valve controls the manifold pressure
(2) Propeller pitch will change if the electronic governor is installed.
(3) Transition from the current fueling setpoint to a calibrated lean setting (i.e. Fuel
Sweep)
(4) Engine transition from the calibrated lean setting to the calibrated rich setting
(5) Transition from the calibrated rich setting back to the usual fueling setpoint
(6) EECS fuel control transitions from one control channel to the alternate channel and
back to the original control channel
(7) All cylinders operate correctly when only the primary sparks are enabled and the
fueling is set to a specified air-fuel ratio
(8) All cylinders operate correctly when only the secondary spark is enabled and the
fueling is set to a specified air-fuel ratio
B. The EECS enables and disables each pre-flight test in sequence through calibration. The
EECS continues the pre-flight test to completion even if the expected system response
does not occur.
NOTICE: Allow sufficient time for the pre-flight test to complete (as shown by the PFT
annunciator) before making any power control changes. Otherwise the pre-flight
test could be inadvertently cancelled with no other indication that the check is
incomplete.
C. If the PFT annunciator:
(1) Never came on, the pre-flight test did not run.
(2) Blinks, the pre-flight test was aborted. Press the PFT button momentarily to
acknowledge that the check was not completed. After an aborted start PFT, wait 5
seconds after re-establishing correct engine speed and ensure average CHT is within
limits before pressing the PFT button again.
D. Once the pre-flight test starts, it will abort if any of the following occur:
• Power control changes more than ± 5% from where it was at the start of the sequence
• Engine speed goes below 1000 rpm
• Engine speed goes above 2300 rpm
• Engine load goes below 15%
• Average CHT goes below 140º (60ºC)
• Average CHT goes above 425ºF (218ºC)
• If the PFT button is pressed while the pre-flight test is running.
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October 2018
Engine Initiation
Page 55