Lycoming TEO-540-C1A Maintenance Manual page 495

TEO-540-C1A Engine Maintenance Manual
Fault ID 256
Primary: -reserved-
Fault
Secondary: Engine ID Sensor Range
Description
This fault occurs if the Engineering value of the measured parameter is outside the expected
window defined by the calibratable Highest and Lowest Valid Engineering Values.
Root Cause The Highest and Lowest possible engineering values define the range of values that can be
expected for the entire engine operating envelope. Any value observed outside this
envelope is flagged as a sensor range fault.
1. Run the engine in accordance with the engine and aircraft maintenance manuals. Is the fault active? If
yes, go to step 2. If no, go to step 4.
2. With Ignition switch in OFF position, remove ECU power by pulling the ECU circuit breaker. Wait 10s
before resetting. Is fault still active? If yes, go to step 3. If no, monitor engine operation for the fault to
repeat.
3. Remove harness connector A001-P2 from ECU connector A001-J2. Using a multi-meter, check for
continuity (or a specific resistance if a resistor is installed) between pins 33 and 42 of A001-P2. Does
continuity (or correct resistance) exist? If yes, reconnect A001-J2, and go to step 4. If no, contact
Lycoming Engines.
4. Clear Service fault history and start engine. If the fault is still active replace the ECU.
NOTE: By default, this configurable parameter has been disabled hence this fault should only occur if this is
enabled in the calibration for an engine specific installation.
Fault ID 257
Primary: -reserved-
Fault
Secondary: Op Mode Selector Sensor
Description
This fault occurs if the Engineering value of the measured parameter is outside the expected
window defined by the calibratable Highest and Lowest Valid Engineering Values.
Root Cause The Highest and Lowest possible engineering values define the range of values that can be
expected for the entire engine operating envelope. Any value observed outside this
envelope is flagged as a sensor range fault.
1. Is there an active fault(s) that correspond to the fault numbers listed in the Root Cause box, items 1 and
2? If yes, go to troubleshooting procedure for the active fault(s). If no, go to step 2.
2. Inspect wires and resistors connected to switch for breaks or damage. Are wires or resistors broken or
damaged? If yes, repair in accordance with the aircraft maintenance manual. If no, go to step 3.
3. Disconnect wires from switch and disconnect ECU connector A001-P2. Measure resistance from A001-
P2 pin 48 to each wire and check for resistance as shown in the table below. Are the resistances
measured within the table limits? If yes, go to step 4. If no, but resistance is present and not within
table limits, replace the defective resistor in accordance with the aircraft maintenance manual. If no, and
circuit is open, go to step 5.
Switch Position
C
NORM
S
© 2018 Avco Corporation. All Rights Reserved
November 2018
Fault Group 33
Fault
Troubleshooting Steps
Fault Group 33
Range Fault
Troubleshooting Steps
Resistance Tolerance
330kΩ
±10%
1.01MΩ
±10%
3.21MΩ
±10%
[FAULT: analogue engine identifier
Fault Name
range]
Fault Lamp
[FAULT: analogue pilot operating
Fault Name
mode range]
Fault Lamp
TLO
TLO
Appendix D
Page 465