Lycoming TEO-540-C1A Maintenance Manual page 461

TEO-540-C1A Engine Maintenance Manual
Fault ID 144
Fault
Turbine Inlet Temperature 1 Slew rate
Description
Fault ID 145
Fault
Turbine Inlet Temperature 2 Slew rate
Description
This fault indicates the temperature sensor slew rate is greater than the calibrated
Root Cause
maximum.
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 TIT sensor, and lead for any damage (eg...burned, broken or frayed wires, cracked or broken
connectors, burned or broken sensors). Replace any damaged sensors per the "Sensor Replacement
Procedures" section in Chapter 72-70. If no damage is found, go to step 4.
4. Inspect TIT 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. 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.
*NOTE: This fault could be caused by another TIT fault. If there are any other active TIT faults, go to
troubleshooting steps for the corresponding TIT fault.
Fault ID 146
Fault Local Manifold temperature slew rate
Description fault
This fault indicates the temperature sensor slew rate is greater than the calibrated
Root Cause
maximum.
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. Swap the sensor giving the fault with opposite sensor and run the engine. Did the fault move with the
sensor? If yes, replace the sensor per the "Sensor Replacement Procedures" section in Chapter 72-70. If
no, 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 ECU.
*NOTE: This fault could be caused by another manifold air temperature fault. If there are any other active
manifold air temperature faults go to troubleshooting steps for the corresponding manifold air
temperature fault.
© 2018 Avco Corporation. All Rights Reserved
November 2018
Fault Group 19
Fault Group 19
Troubleshooting Steps for Faults 144 and 145
Fault Group 19
Troubleshooting Steps
[FAULT: turbine inlet temperature 1
Fault Name
slew rate]
Fault Lamp
[FAULT: turbine inlet temperature 2
Fault Name
slew rate]
Fault Lamp
[FAULT: local manifold
Fault Name
temperature slew rate]
Fault Lamp
None
None
None
Appendix D
Page 431