Lycoming TEO-540-C1A Maintenance Manual page 494

Fault ID 254
Primary: -reserved-
Fault
Secondary: MAP (Manifold Absolute
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 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 damaged, replace the sensor 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, replace the sensor. If
fault is still active, 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, and if fault
persists, replace the ECU.
Fault ID 255
Fault Primary: -reserved-
Description Secondary: FPP 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 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.
Appendix D
Page 464
Fault Group 32
Pressure) Range Fault
Troubleshooting Steps
Fault Group 32
Troubleshooting Steps
TEO-540-C1A Engine Maintenance Manual
Fault Name
[FAULT: manifold pressure range]
Fault Lamp
Fault Name
[FAULT: fuel pump pressure range]
Fault Lamp
© 2018 Avco Corporation. All Rights Reserved
TLO
TLO
November 2018