Lycoming TEO-540-C1A Maintenance Manual page 493

TEO-540-C1A Engine Maintenance Manual
Fault ID 252
Fault Primary: FRP Sensor Range Fault
Description Secondary: -reserved-
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 3. If no, go to step 2.
2. Using the FST, download active and service fault logs, then clear fault logs and monitor engine
operation for the fault to repeat.
3. Inspect sensor, and lines for any damage (eg...burned, broken or frayed wires, cracked or broken
connectors or hoses, burned or broken sensors). If damage is found, replace the damaged part per the
"Sensor Replacement Procedure" in Chapter 72-70. If no damage is found, go to step 4.
4. Inspect harness connection for any damage (eg...burned, broken or frayed wires, cracked or broken
connectors). Contact Lycoming if harness damage is found. If no damage found, go to step 5.
5. Swap fuel rail pressure sensor with fuel pump pressure sensor and run the engine. Does the fault move
with the sensor? If yes, replace the sensor. If no, go to step 6.
6. Complete a continuity test of the harness from the harness sensor connector to the ECU connector using
the engine system schematic. If the continuity check fails, isolate to affected harness by disconnecting
the firewall connection, then contact Lycoming Engines. If the continuity checks good, replace the
sensor. If fault persists, replace the ECU.
Fault ID 253
Fault Primary: TPS Sensor Range Fault
Description Secondary: TPS Sensor Range Fault
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 3. If no, go to step 2.
2. Using the FST, download active and service fault logs, then clear fault logs and monitor engine operation
for the fault to repeat.
3. Inspect the sensor, sensor connector. If there is damage found, replace the throttle body* per the
"(Electronic) Throttle Body Replacement" procedure in Chapter 73-20. If there is no damage, go to step 4.
4. Inspect engine harness for visible signs of damage. If damage is found, contact Lycoming Engines. If no
damage is found, go to step 5.
5. Complete a continuity test of the harness from the harness sensor connector to the ECU connector using
the engine system schematic. If the continuity check fails, isolate to affected harness by disconnecting
the firewall connection, then contact Lycoming Engines. If the continuity checks good, go to step 6.
6. Replace the throttle body. Is the fault active? If yes, replace the ECU.
7. If the above steps are unsuccessful, contact Lycoming
*NOTE: This sensor is a sub-part of throttle body assembly hence replacing the sensor is not possible and
requires replacement of the entire throttle body assembly.
© 2018 Avco Corporation. All Rights Reserved
November 2018
Fault Group 32
Troubleshooting Steps
Fault Group 32
Troubleshooting Steps
Fault Name
[FAULT: fuel rail pressure range]
Fault Lamp
[FAULT: local throttle position
Fault Name
range]
Fault Lamp
TLO
TLO
Appendix D
Page 463