W DOC AIRBUS | TSM A320F

Master Lever Position Discrete Disagrees with EIU Data

TASK 73-11-00-810-824-A
Master Lever Position Discrete Disagrees with EIU Data

1. Possible Causes
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
1
MULTIMETER - STANDARD
No specific
1
PLIERS - JAWED, SOFT
 B. Referenced Information
REFERENCE
DESIGNATION
TSM TASK 71-00-00-810-834-A
General Troubleshooting Guidelines for Additional Troubleshooting Information
TSM TASK 71-00-00-810-835-A
Component and Harness Intermittent Troubleshooting Procedure for Guidance Troubleshooting Intermittent Faults
AMM 24-41-00-861-002
Energize the Aircraft Electrical Circuits from the External Power
AMM 70-70-00-910-803
SPOP 6 - Cleaning of the Contact Points and Wiring Harnesses
AMM 73-21-01-000-801
Removal of the Electronic Engine Control (EEC)
AMM 73-21-01-400-801
Installation of the Electronic Engine Control (EEC)
AMM 73-21-61-000-802
Removal of the Electronic Engine Control (EEC) Wiring Harness (WF01)
AMM 73-21-61-400-802
Installation of the Electronic Engine Control (EEC) Wiring Harness (WF01)
AMM 73-21-62-000-802
Removal of the EEC Wiring Harness (WF02)
AMM 73-21-62-400-802
Installation of the EEC Wiring Harness (WF02)
AMM 73-25-34-000-802
Removal of the Engine Interface Unit (EIU)
AMM 73-25-34-400-802
Installation of the Engine Interface Unit (EIU)
AMM 73-25-34-860-806
Engine Interface Unit (EIU) DISCRETE INPUTS Menu Data Status
AWM 732538
AWM 732539
AMM 78-36-00-010-802
Opening of the Thrust Reverser Cowl-Doors
AMM 78-36-00-410-802
Closing of the Thrust Reverser Cowl-Doors
F EEC Wiring Harnesses
F Pylon Junction Box Connections
F Master Lever Channel A Wiring Schematic
F Master Lever Channel B Wiring Schematic
F EIU Channel A Wiring Schematic
3. Fault Confirmation
Subtask 73-11-00-710-078-A ** ON A/C NOT FOR ALL
A. Turn the power on to the EEC and look at the ground scanning report to confirm this maintenance message.
   (1) Energize the aircraft electrical circuits
AMM 24-41-00-861-002.
   (2) On the ENG section of maintenance panel 50VU :
     (a) Release the FADEC GND PWR/1(2) pushbutton switch (the ON legend comes on).
NOTE: After the FADEC is energized, wait ten seconds before you stop the FADEC ground power. If you do not wait ten seconds, the interactive mode stops the EEC self-test and this can cause spurious faults.
   (3) On MCDU screen, check if the fault is displayed on ground scan report.
NOTE: The Electronic Engine Control (EEC) has detected the circuits for the Master Lever and Engine Interface Unit (EIU) do not agree. The Master Lever is located in the cockpit. The EIU is located in the avionics compartment.
   (4) If the maintenance message does not come back, examine the harnesses and electrical connectors as described in the component and harness intermittent fault isolation procedure (Ref. TSM TASK 71-00-00-810-835).
     (a) If no problems are found, return the engine to service. Monitor the engine for reoccurring maintenance message.
   (5) If the maintenance message comes back (hard fault), go to the Para. Fault Isolation.
4. Fault Isolation
WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE AFTER SHUTDOWN. THE ENGINE CAN STAY HOT FOR A LONG TIME. IF YOU DO NOT OBEY THIS WARNING, INJURY CAN OCCUR.
WARNING: REFER TO THE MSDS FOR ALL MATERIAL USED AND THE MANUFACTURER'S SAFETY INSTRUCTIONS FOR ALL EQUIPMENT USED. IF YOU DO NOT OBEY THIS WARNING, INJURY CAN OCCUR.
CAUTION: MAKE SURE YOU REMOVE ELECTRICAL POWER FROM THE EEC BEFORE YOU REMOVE THE ELECTRICAL CONNECTORS. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE EEC CAN OCCUR.
Subtask 73-11-00-810-073-A ** ON A/C NOT FOR ALL
A. If there is confirmation of the fault:
   (1) Open the thrust reverser cowl-doors AMM 78-36-00-010-802.
   (2) Do the EIU discrete input interactive test AMM 73-25-34-860-806.
     (a) Check that the status of discrete for both Master Lever positions is correct AMM 73-25-34-860-806.
     (b) If the status is not correct, troubleshoot for a discrete input fault (Ref. TSM 73-25-00).
     (c) Do the test given in Para. 3.
   (3) If the discrete status is correct or if fault continues:
     (a) Examine the WF02 (4218KS) and WF01 (4217KS) harnesses, connectors P1 (4000KS-P1) and P2 (4000KS-P2) - EEC (4000KS) and connectors P406 (406VC-A), P407 (407VC-A) and P402 (402VC-A) - Pylon junction box, for problems which are possible between the EEC (4000KS) and the pylon junction box.
     (b) Inspect for harness damage.
     (c) Inspect for loose or damaged connectors.
NOTE: Loose connectors must be disconnected and examined for further wear or damage.
     (d) If a problem is found with the harnesses or connectors:
       1 Replace HARNESS-FAN, WF02 [4218KS] AMM 73-21-62-000-802 and AMM 73-21-62-400-802, or
       2 Replace HARNESS-FAN, WF01 [4217KS] AMM 73-21-61-000-802 and AMM 73-21-61-400-802.
       3 Do the test given in Para. 3.
   (4) If no problems are found with the harnesses or the fault continue, use a PLIERS - JAWED, SOFT to disconnect the electrical connectors P1 (4000KS-P1) and P2 (4000KS-P2) from the EEC (4000KS) and connectors P406 (406VC-A), P407 (407VC-A) and P402 (402VC-A) from the pylon junction box.
     (a) Examine the pins and sockets (contacts) for alignment and damage. Look for contacts pushed rearward into the connector face. Replace parts as necessary.
     (b) Clean the contacts with contact cleaner and clean cloth per SPOP 6. Blow dry with air (at less than 30 psi) across the connector face AMM 70-70-00-910-803.
     (c) Reconnect the electrical connectors P1 (4000KS-P1) and P2 (4000KS-P2) to the EEC(4000KS) and connectors P406 (406VC-A), P407 (407VC-A) and P402 (402VC-A) to the pylon junction box.
     (d) Do the test given in Para. 3.
   (5) If the fault continues:
     (a) Disconnect the electrical connectors P1 (4000KS-P1) and P2 (4000KS-P2) from the EEC (4000KS) and connectors P406 (406VC-A), P407 (407VC-A) and P402 (402VC-A) from the pylon junction box. Use a MULTIMETER - STANDARD to test the Master Lever and EIU circuits in the harnesses. Refer to Table 1 and Table 2. Look for:
       1 Wire-to-wire shorts
       2 Shorts to ground
       3 Continuity (less than 5 ohms resistance).
NOTE: A short to ground is found when the resistance is less than 100 000 (100K) ohms.
Table 1: Master Lever Channel A Connector Contacts
WF02 (4218KS) Harness P1 (4000KS-P1) EEC (4000KS) Connector Contacts
WF02 (4218KS) Harness P406 (406VC-A) Pylon Junction Box Connector Contacts
EE
2
DD
9

Table 2: Master Lever Channel B Connector Contacts
WF01 (4217KS) Harness P2 (4000KS-P2) EEC (4000KS) Connector Contacts
WF01 (4217KS) Harness P407 (407VC-A) Pylon Junction Box Connector Contacts
EE
2
DD
9
     (b) If a problem is found with the harnesses or connectors:
       1 Replace HARNESS-FAN, WF02 [4218KS] AMM 73-21-62-000-802 and AMM 73-21-62-400-802, or
       2 Replace HARNESS-FAN, WF01 [4217KS] AMM 73-21-61-000-802 and AMM 73-21-61-400-802.
       3 Do the test given in Para. 3.
   (6) If no problem is found or if the fault continues, check the ENG/MASTER control switch and the aircraft wiring AWM 732539 or AWM 732538:
     (a) Disconnect the electrical connector P407 (407VC-A) from the pylon junction box.
     (b) Check for continuity between pins 2 and 9 at (407VC-A).
     (c) In cockpit, on the ENG panel 115VU:
       1 FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
  • Put the ENG/MASTER control switch 1 (3KC) in ON position.
       2 FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
  • Put the ENG/MASTER control switch 2 (2KC) in ON position.
     (d) At pylon junction box, at the electrical connector P407 (407VC-A), check pins 2 and 9 for:
  • Short to ground
  • Wire-to-wire short.
     (e) If a problem is found on the ENG/MASTER control switch or aircraft wiring:
       1 Remove the ENG panel 115VU.
       2 On ENG panel 115VU side, with the ENG/MASTER control switch in ON position:
         a FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
Check pins L and X for:
  • Short to ground
  • Wire-to-wire short.
         b FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
Check pins T and U for:
  • Short to ground
  • Wire-to-wire short.
       3 On ENG panel 115VU side, with the ENG/MASTER control switch in OFF position:
         a FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
  • Check for continuity at pins L and X.
         b FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
  • Check for continuity at pins T and U.
       4 If a problem is found:
         a FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
  • Replace CTL SW-ENG/MASTER 1 [3KC] or repair the ENG panel 115VU.
         b FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
  • Replace CTL SW-ENG/MASTER 2 [2KC] or repair the ENG panel 115VU.
         c Do the test given in Para. 3.
       5 If no problem is found, repair or replace the aircraft wiring :
         a For ENG1 fault, refer to AWM 732539.
         b For ENG2 fault, refer to AWM 732538.
         c Do the test given in Para. 3.
       6 If you have not found any problem on the ENG/MASTER control switch or aircraft wiring or if the fault continues, go to the next step.
   (7) If the fault continues:
     (a) Replace EIU-1 [1KS1] or EIU-2 [1KS2] AMM 73-25-34-000-802 and AMM 73-25-34-400-802.
     (b) Do the test given in Para. 3.
   (8) If the fault continues:
     (a) Replace [4000KS] AMM 73-21-01-000-801 and AMM 73-21-01-400-801.
     (b) Do the test given in Para. 3.
5. Close-up
Subtask 73-11-00-860-073-A ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
   (1) Make sure that the work area is clean and clear of tools and other items.
     (a) Close the thrust reverser cowl-doors AMM 78-36-00-410-802.
[Rev.8 from Aug 2018] 2026.04.04 04:36:34 UTC
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