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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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Quick Links

08/02/19

Message Overview:

Fault Message:

FWC 1 - DISPLAY UNIT FAULT

Fault Code:

3151007FW1

Associated CAS:

CHECK DU 1
(Caution)

CHECK DU 2
(Caution)

CHECK DU 3
(Caution)

CHECK DU 4
(Caution)

CHECK DU 5
(Caution)

CHECK DU 6
(Caution)

Reporting LRU: Display Unit 1
System Description: 31-61-00
Schematic Diagram: 31-61-00 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Wiring Diagram: 31-61-01 [ Global Express ]  [ G5000 ]  [ Global XRS ]

Fault Description:

Display Unit 1 shows data that does not agree with the initial sensor data.

NOTE: A Display Unit wraparound ARINC 429 signal is routed to each IAC where it is compared with the original sensor data by the FWC portion of the IAC.

Possible Causes:

  • Display Unit (DU) 1 (M7)
  • Integrated Avionics Computer (IAC) 1 (A11)
  • Associated Wiring

Troubleshooting Tips:

Advisory Wire/Service Bulletin:

Forum Articles/Infoservice/Newsletter: None

The normal system configuration (no reversion) is as follows:

  1. IAC 1 (EDS 1) supplies display data to the pilot's primary flight display (PFD) and multi-function display (MFD).
  2. IAC 2 (EDS 2) supplies display data to the copilot's PFD and MFD.
  3. IAC 3 (EDS 3) supplies display data to the EICAS engine and system displays.

NOTE: A blank display is an indication of a power supply failure.

Quick Links:

Removal of the Integrated Avionics Computers (IAC) AMM 31-41-01-000-801 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Installation of the Integrated Avionics Computers (IAC) AMM 31-41-01-400-801 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Removal of the Electronic Flight-Display Units AMM 31-61-01-000-801 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Installation of the Electronic Flight-Display Units AMM 31-61-01-400-801 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Access to System Diagnostics AMM 45-45-00-970-804 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Integrated Maintenance Test (IMT) Fault Code Look-Up AMM 45-45-00-970-826 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Wire Repair - Maintenance Practices - ALL SPM 20-12-10-02 [ Global Express ]  [ G5000 ]  [ Global XRS ]

Troubleshooting Recommendations:

  1. Swap DU 1 with DU 3.

    1. If fault is transferred or gone, record IMT code to identify the cause of failure of DU 1 and go to step 4.
    2. If fault remains, continue with next step.

  2. Swap IAC 1 with IAC 2.

    1. If fault is transferred or gone, record IMT code to identify the cause of failure of IAC 1 and go to step 5.
    2. If fault remains, continue with next step.

  3. Perform wiring checks of DU 1 ARINC Wraparound.

    1. If wiring checks are not good, repair defective wiring as required and do close out.
    2. If wiring checks are good, go to step 6.

  4. Connect CAIMS PMAT and perform the system diagnostics Display Units Test for DU 1.
    NOTE: Original defective DU 1.

    1. If test passed, do close out.
    2. If an IMT fault code is generated, replace DU 1 and do close out.

  5. Connect CAIMS PMAT do the system diagnostics IAC EDS/Core Test for IAC 1.
    NOTE: Original defective IAC 1.

    1. If test passed, do close out.
    2. If an IMT fault code is generated, replace IAC 1 and do close out.

  6. Connect CAIMS PMAT and perform the system diagnostics Reversion Controller Test. Repair as required.
  7. Do close out.

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