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 4. Fault Isolation
_______________
 A. If EGT fluctuations have been reported and other engine parameters were stable:
 - Do a check of the Post Flight Report (PFR), of the Schedule Maintenance Report (SMR) or Class 3 Report (Ref. AMM TASK 73-21-60-740-007), and of the FADEC Last Leg Report for a T495 SNSR failure message.
 (1) If message is found:

 - Do the related troubleshooting procedure.

 (2) If nothing is found:

 - Disconnect the CJ13 harness from the T495 main junction box (located in the left core compartment), and visually examine the T495 junction box receptacle and the CJ13 harness connector for damaged pins or contamination (Ref. AMM TASK 73-21-50-210-001). Clean the connector and the receptacle using a bristle brush and stoddart solvant (CP 2011) or white spirit (CP 2010).
 (a) If damage is found:

 - replace or repair as necessary.

 (b) If nothing is found:

 - Disconnect the J13 harness from the ECU (4000KS), and visually examine the ECU receptacle and the harness connector for damaged pins or contamination (Ref. AMM TASK 73-21-50-210-001).
 1 If damage is found:
_ - repair or replace as required.
 2 If nothing is found, continue the troubleshooting as follows.
_
 (3) Do a visual inspection of the J13 and CJ13 harnesses connectors for looseness.
 (a) If a connector is found loose:

 - do a cleanning of the connector and the receptacle using a bristle brush and stoddart solvant (CP 2011) or white spirit (CP 2010) (Ref. AMM TASK 73-21-50-210-001)

 (b) If nothing is found:

 - do a visual inspection of the T495 probes lead assemblies and check for damage.
 1 If damage is found:
_
 - repair or replace damaged hardware as required.
 (4) If the fault continues during the subsequent flight:
 - Do an electrical resistance test through the Main Electrical Junction Box between: . pins A and B (1 to 10 ohms) . pin A and the ground (> 20 megohms)
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 (a) If the resistances are out of the specified limits:

 - Do an electrical resistance test of the T495 thermocouple wiring harness (probes lead assemblies and extension leads assemblies) (Ref. AMM TASK 77-21-10-200-001)
 (b) If the resistances are in the specified limits:
 - replace the CJ13 Harness (Ref. AMM TASK 73-21-50-000-005) and (Ref. AMM TASK 73-21-50-400-005).
 (5) If the fault continues during the subsequent flight:

 - Replace the Main Junction Box assembly (Ref. AMM TASK 77-21-10-000-002) and (Ref. AMM TASK 77-21-10-400-002).

 (6) If the fault continues during the subsequent flight:

 - Replace the ECU (4000KS) (Ref. AMM TASK 73-21-60-000-001) and (Ref. AMM TASK 73-21-60-400-001).

 (7) If the fault continues during the subsequent flight:

 - Replace the J13 Harness (Ref. AMM TASK 73-21-50-000-012) and (Ref. AMM TASK 73-21-50-400-012).
 5. Close-up________
 A. Do a minimum idle check (Ref. AMM TASK 71-00-00-710-006).
 (1) Repeat the fault isolation procedure, if the fault continues.
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 ANALYZERS - FAULT ISOLATION PROCEDURES

______________________________________
 TASK 77-30-00-810-801
 Loss of the Vibration Indications on the two Engines
 1. Possible Causes
_______________
 - EVMU (2EV)

 - aircraft wiring

 - C/B-ENGINE/ENG1 AND 2/EVMU (1EV)

 2. Job Set-up Information
______________________
 A. Referenced Information
 -------------------------------------------------------------------------------
REFERENCE DESIGNATION
 -------------------------------------------------------------------------------
AMM 77-32-34-000-042 Removal of the Engine Vibration Monitoring Unit (EVMU) AMM 77-32-34-400-042 Installation of the Engine Vibration Monitoring Unit (EVMU) R AMM 77-32-34-710-040 Operational Check of EVMU through CFDS ASM 77-32/02
　
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