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(WARNING)
RED MESSAGE (CAUTION)
AMBER MESSAGE (ADVISORY)
CYAN MESSAGE (STATUS)
WHITE MESSAGE Require immediate crew attention. These messages are accompanied by flashing master warning, triple chime attenson with or without voice message or dedicated tone. Require immediate crew awareness and future crew action may be required in the form of alternate system selection or performance limitation. These message are accompanied by flashing master caution and a single chime. Indicate safe or normal system operation which require crew awareness, over and above the dark cockpit philosophy. Indicate minor failures or reduction in systems capability, which require no crew action.

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For AOG assistance contact:

CRC Montreal (YUL)
Quick Links

03/04/21

Message Overview:

Message Name:

ANTI-ICE COMMAND 1B

Message Code:

B3-302147

Associated CAS:

None

Reporting LRU: ANTI-ICE PANEL
System Description: 30-21-00
Schematic Diagram: 75-10-00
Wiring Diagram: 75-10-01
75-10-05

Message Description:

Right engine anti-ice command fault 1B. A fault between the flight deck engine anti-ice command and the ECU B was sensed.

Possible Causes:

  • Anti-Ice Harness
  • Anti-Ice Switch (SDS4)
  • W1 Wiring Harness
  • Right Full Authority Digital Engine Control (FADEC) Electronic Control Unit (ECU) B (A42)
  • Associated Wiring

Troubleshooting Tips:

Advisory Wire/Service Bulletin: None

Forum Articles/Infoservice/Newsletter: None

NOTE: ECU B Right Engine W1 harness listed in AIPC 71-50-05-02

Quick Links:

Anti-Ice System - Component Location AMM 30-11-00-992-801
Removal of the Anti-Ice Control Panel AMM 30-11-09-000-801
Installation of the Anti-Ice Control Panel AMM 30-11-09-400-801
Operational Test of the Nacelle Anti-Ice System AMM 30-21-00-710-801
Leak Test of the Nacelle Anti-Ice System AMM 30-21-00-790-801
Engine Nacelle Anti-Ice - Component Location AMM 30-21-00-992-801
Removal of the Cowl Anti-Ice Valve AMM 30-21-01-000-801
Installation of the Cowl Anti-Ice Valve AMM 30-21-01-400-801
Removal of the Anti-Ice Dual Pressure Switch AMM 30-21-03-000-801
Installation of the Anti-Ice Dual Pressure Switch AMM 30-21-03-400-801
Removal of the Anti-Ice Tubes AMM 30-21-05-000-801
Installation of the Anti-Ice Tubes AMM 30-21-05-400-801
Removal of the Engine Electronic Control Unit (ECU) AMM 76-10-05-000-801
Installation of the Engine Electronic Control Unit (ECU) AMM 76-10-05-400-801
Wiring - Maintenance Practices - ALL SPM 20-12-00-02
Wire Repair - Maintenance Practices - ALL SPM 20-12-10-02

Troubleshooting Recommendations:

  1. Perform the power-up check, did the fault clear?

    1. If YES, do close out.
    2. If NO, continue to next step.

  2. Ensure CB2-E11 is closed.
  3. Perform a voltage check per the following table:

    PL19 SDS4 From: To: Expected Results: Results:
    OPEN PL19J2/P2 pin T (A42J1 pin 44 (R FADEC B (A42) Nacelle A/I Selected) GND 28 VDC
    CLOSED PL19J2/P2 pin T (A42J1 pin 44 (R FADEC B (A42) Nacelle A/I Selected) GND 0 VDC

    1. Do you have the proper voltages?

      1. If YES, go to Step 13.
      2. If NO, continue with next step.

  4. Remove the electrical power from the aircraft.
  5. Open and tag the applicable circuit breakers.
  6. Disconnect and examine the Pylon Connector W1P1 and the R ECU B (A42) Connector W1P2 for damaged wires and other damage. Refer to the AMM.
  7. Perform a continuity check per the following table:

    From: To: PL19 SDS4 Results:
    GS2048 W1P2 pin 44 (R FADEC B (A42) Nacelle A/I Selected) OPEN ∞
    GS2048 W1P2 pin 44 (R FADEC B (A42) Nacelle A/I Selected) CLOSED ≈ 0Ω

    1. Do you have the correct continuity?

      1. If YES, go to Step 13.
      2. If NO, continue with next step.

  8. Perform a continuity check per the following table:

    From: To: Expected Results: Results:
    PL19J2 pin T SDS4P1 pin 2NO 0Ω
    PL19J2 pin P SDS4P1 pin 2C 0Ω

    1. Do you have the correct continuity?

      1. If YES, go to Step 13.
      2. If NO, continue with next step.

  9. Perform a continuity check per the following table:

    From: To: PL19 SDS4 Expected Results: Results:
    GS2048 PL19P2 pin P ≈ 0Ω
    GS2048 PL19J2 pin T CLOSED ≈ 0Ω
    GS2048 PL19J2 pin T OPEN ∞

  10. Do you have the correct continuity?

    1. If YES, go to Step 13.
    2. If NO, replace SDS4 or PL19.

      1. Continue with next step.

  11. Perform a continuity check per the following table:

    From: To: Expected Results: Results:
    Pylon Disconnect W1P1 pin 54 W1P2 pin 44 (Nacelle A/I Selected) ≈ 0Ω
    W1P2 pin 44 (Nacelle A/I Selected) W1P2 Back Shell (GND) ≈ 0Ω
    J802 pin 54 (Pylon Disconnect) PL19P2 pin T ≈ 0Ω

    1. Do you have the correct continuity?

      1. If YES, go to Step 13.
      2. If NO, continue with next step.

  12. Repair/Replace W1 wiring harness.
  13. Remove the tags, put the circuit breakers in the ON position, and perform a system check.
  14. Perform the power-up check, did the fault clear?

    1. If YES, do close out.
    2. If NO, continue with next step.

  15. Open and tag the applicable circuit breakers.
  16. Replace the R ECU B (A42) per AMM 76-10-05-000-801.
  17. Remove the tags, put the circuit breakers in the ON position, and perform a system check.
  18. Do the power-up check, did the fault clear?

    1. If YES, do close out.
    2. If NO, contact CRC for additional support.

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