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 1 If the resistance values are in the specified limits:
_
 - replace the ECU (4000KS) (Ref. AMM TASK 73-21-60-000-001) and (Ref. AMM TASK 73-21-60-400-001).
 2 If the resistance values are out of the specified limits:
_
 - disconnect the harness J13 from the fuel flow transmitter and do a check of the transmitter resistance between: . pins 1 and 2 (250 to 350 ohms) . pins 2 and 3 (250 to 350 ohms) . pins 1 and 4 (> 10 megohms) . pin 1 and the ground (> 10 megohms).
 a If the resistance values are in the specified limits:
_
 - replace the harness J13 (Ref. AMM TASK 73-21-50-000-046) and (Ref. AMM TASK 73-21-50-400-046).
 b If the resistance values are out of the specified limits:
_
 - replace the fuel flow transmitter (Ref. AMM TASK 73-31-10-000-002) and (Ref. AMM TASK 73-31-10-400-002).
 D. Do the test given in Para. 3.A.
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ECES  TASK 73-00-00-810-870 Flexible Temperature not Entered

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 1. Possible Causes
_______________
 - aircraft wiring
 2. Job Set-up Information
______________________
 A. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
ASM 73-25/06
 3. Fault Confirmation
__________________
 A. Test
 (1) On the MCDU, make sure that the FLEX TEMP value is correctly entered.
 4. Fault Isolation
_______________
 A. If the fault symptom is identified by the ECAM warning message FLEX TEMP NOT SET:
 NOTE : Do this procedure on the two engines.
____
 - do a check and repair the aircraft wiring between the MCDU (3CA1) (3CA2)/FCU (2CA)/FMGC (1CA1) (1CA2)/EIU (1KS1) (1KS2) and the ECU (4000KS) (Ref. ASM 73-25/06).
 B. After the subsequent flight, make sure that the fault does not continue.
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ECES

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 INTENTIONALLY BLANK

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E TASK 73-00-00-810-871 Autothrust Deactivation in Flight

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 1. Possible Causes
_______________
 - aircraft wiring
 2. Job Set-up Information

______________________
 Not Applicable

 3. Fault Confirmation

__________________
 A. Test
 (1) Not applicable, you cannot confirm this fault on the ground.
 4. Fault Isolation
_______________
 A. If the fault symptom is identified by the crew observation:
 AUTOTHRUST-deactivation in flight:

 NOTE : Do this procedure on the two engines.
____
 (1) Do a check and repair the aircraft wiring between the FMGC (1CA1) (1CA2), FCU (2CA), EIU (1KS1) (1KS2) and ECU (4000KS).
 B. After the subsequent flight, make sure that the fault does not continue.
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ECES

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 TASK 73-00-00-810-872
R Idle Speed Difference between Engine 1 and Engine 2
 1. Possible Causes
_______________
 - IDG, FRV (Oil temp)

 - SFCC-1(2) (21CV(22CV))

 - EIU-1(2) (1KS1(1KS2))

 - P/BSW-ANTI ICE/ENG 1 (2DN1)

 - P/BSW-ANTI ICE/ENG 2 (2DN2)

 - wing anti-ice valve L

 - wing anti-ice valve R

 - PO/P12/T12

 - BMC-1(2) (1HA1(2))

 - ECU (4000KS)

 2. Job Set-up Information
______________________
 A. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
　
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