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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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11/19/25

Message Overview:

Message Name:

DISC INTF MOV DCPC/ SFCU#1/WRG

Message Code:

2751249STD

Reporting LRU: Slat / Flap Control Unit 1 (SFCU)
Associated CAS: SLAT FLAP BIT (Advisory)
System Description: 27-51-00 - Slats and Flaps Control and Indication System
Schematic Diagram: [ G5000 ]  [ Global Express ]  [ Global XRS ] SSM 27-50-00-101 - Flaps and Slats System - Electrical Schematic
Wiring Diagram: [ G5000 ]  [ Global Express ]  [ Global XRS ] WM 27-50-00-1_007 - Sheet 7 - Power Drive Unit (PDU) Motors No. 1 - ALL
[ G5000 ]  [ Global Express ]  [ Global XRS ] WM 27-50-07-1_001 - Sheet 1 - Control Motors No. 1 - ALL

Message Description:

MOVING 1/FLAPS IN MOTION discrete output from the Slat / Flap Control Unit 1 (SFCU) is defective.

Possible Causes:

  • Slat / Flap Control Unit 1 (SFCU) (A124)
  • DC Power Center (DCPC) (A63)
  • DC Power Center (DCPC) (A63)/Primary Logic Card 1 (PLC)
  • DC Power Center (DCPC) (A63)/Primary Logic Card 2 (PLC)
  • DC Power Center (DCPC) (A63)/Primary Logic Card 3 (PLC)
  • Associated Wiring

Troubleshooting Tips:

Advisory Wire/Service Bulletin: None

Full Throttle Blog/Forum Articles/Infoservice/Newsletter: None

Flight Operation Notifications Manual (FONM): None

NOTES:

  • The DCPC provides a 28 Volts DC discrete signal to the SFCU. The SFCU grounds this signal when the flap system is in motion. Performing a SLAT FLAP RESET on the EMS CDU may clear this fault.
  • Wait at least one minute after SFCU reset to allow self test to run.

Quick Links:

Grounding of the Aircraft [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM10-11-00-867-801
Removal of the Covers and Plugs [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM10-12-00-020-801
Installation of the Covers and Plugs [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM10-12-00-420-801
Standard Aircraft Configuration for Maintenance [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM12-00-00-867-801
Aircraft Walkaround (for Maintenance) [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM12-00-00-867-802
Connect Electrical Power to the Aircraft [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM24-00-00-861-801
Remove the Electrical Power from the Aircraft [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM24-00-00-861-802
Electrical/Electronic Safety Precautions [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM24-00-00-910-801
Electrostatic Discharge Safety Precautions [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM24-00-00-910-802
Removal of the DC Power Center (DCPC) [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM24-61-00-000-801
Installation of the DC Power Center (DCPC) [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM24-61-00-400-801
Operational Test of the DC Power Center (DCPC) [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM24-61-00-710-801
Removal of the DC Power Center (DCPC) Primary Logic [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM24-61-09-000-801
Installation of the DC Power Center (DCPC) Primary Logic [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM24-61-09-400-801
Operational Test of the DC Power Center (DCPC) Primary Logic [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM24-61-09-710-801
Operational Test of the Slat/Flap Control System [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM27-51-00-710-801
Removal of the Slat/Flap Control Unit (SFCU) [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM27-51-05-000-801
Installation of the Slat/Flap Control Unit (SFCU) [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM27-51-05-400-801
Access to Active Faults [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM45-45-00-970-802
Access to Stored Faults [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM45-45-00-970-803
Access to System Diagnostics [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM45-45-00-970-804
Flight Deck Effect to Fault Correlations [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM45-45-00-970-821
Safety Precautions - Maintenance Practices - ALL [ G5000 ]  [ Global Express ]  [ Global XRS ] SPM20-00-01-02
Electrical Wiring - Continuity Test - Adjustment /Test - ALL [ G5000 ]  [ Global Express ]  [ Global XRS ] SPM20-12-01-05
Wire Repair - Maintenance Practices - ALL [ G5000 ]  [ Global Express ]  [ Global XRS ] SPM20-12-10-02

Troubleshooting Recommendations:

  1. Interchange SFCU 1 with SFCU 2 and confirm that they are installed properly and securely. Select a different Slat Flap Control Handle position.

    1. If system checks are good, replace SFCU 1 and do close out.
    2. If fault remains, continue with next step.

  2. Remove SFCU 1 and perform voltage check on the connector A124AP1 as follow:

    SFCU 1 Expected Result Result
    A124AP1-16 28 Volt

    1. If there is 28 Volts, do close out.
    2. If there is no 28 Volts, continue with next step.

  3. Perform wiring checks as follow:

    From To Result
    A124AP1-16 A63P1-M

    1. If wiring checks are not good, repair defective wiring as required and do close out.
    2. If wiring checks are good, continue with next step.

  4. Remove the Primary Logic Cards one at a time and apply aircraft power.

    1. If fault clears after removal of any one primary logic card, replace that specific card and do close out.
    2. If fault remains, continue with next step.

  5. Remove all three DCPC Primary Logic Cards. Perform wiring check as follows:

    From To Result
    P110B-5 A63P1-M
    P210B-5 A63P1-M
    P310B-5 A63P1-M
    Aircraft Ground A63P1-M

    1. If wiring checks are not good, repair defective wiring as required and do close out.
    2. If wiring checks are good, continue with next step.
      CAUTION: TO PREVENT DAMAGE TO THE ACPC MOTHER BOARD CONNECTORS, ENSURE THAT THE JUMPER WIRE PINS OUTSIDE DIAMETER (OD) DOES NOT EXCEED 0.025 INCH.

  6. Replace DCPC.
  7. Do close out.
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