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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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06/29/21

Message Overview:

Message Name:

AILERON TRIM INDICATION UNSERVICEABLE

Message Code: 271OBS002
Effectivity: All
System: Aileron
System Description: 27-10-00
Schematic Diagram: 27-10-00 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Wiring Diagram: 27-10-00 [ Global Express ]  [ G5000 ]  [ Global XRS ]

Message Description:

Aileron trim indication does not change with aileron trim inputs from the Aileron/Rudder/Stabilizer (AIL/RUD/STAB) TRIMS control panel. Ailerons do not move when the aileron trim switch is operated or aileron trim indication is unserviceable.

Possible Causes:

  • Aileron Trim Actuator (B38)
  • Aileron/Rudder/Stabilizer (AIL/RUD/STAB) TRIMS control panel (AP20)
  • Associated Wiring

Troubleshooting Tips:

Advisory Wire/Service Bulletin: None

Forum Articles/Infoservice/Newsletter: None

Quick Links:

Connect Electrical Power to the Aircraft AMM 24-00-00-861-801 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Remove the Electrical Power from the Aircraft AMM 24-00-00-861-802 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Opening of Non-Thermal Circuit Breakers AMM 24-00-00-863-801 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Closing of Non-Thermal Circuit Breakers AMM 24-00-00-863-802 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Electrical/Electronic Safety Precautions AMM 24-00-00-910-801 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Flight Control Safety Precautions AMM 27-00-00-910-801 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Operational Test of the Aileron Trim System AMM 27-12-00-710-801 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Rigging of the Aileron Trim System AMM 27-12-00-820-801 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Removal of the AIL/RUD/STAB TRIMS Control Panel AMM 27-12-01-000-801 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Installation of the AIL/RUD/STAB TRIMS Control Panel AMM 27-12-01-400-801 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Removal of the Aileron Trim Actuator AMM 27-12-05-000-801 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Installation of the Aileron Trim Actuator AMM 27-12-05-400-801 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Removal of the Data Acquisition Units (DAU) AMM 31-42-01-000-801 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Installation of the Data Acquisition Units (DAU) AMM 31-42-01-400-801 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Landing Gear Safety Precautions AMM 32-00-00-910-801 [ Global Express ]  [ G5000 ]  [ Global XRS ]
Wire Repair - Maintenance Practices - ALL SPM 20-12-10-02 [ Global Express ]  [ G5000 ]  [ Global XRS ]

Troubleshooting Recommendations:

  1. Perform the rigging of the aileron trim system.

    1. If the mechanical check is unsatisfactory, repair as required and do close out.
    2. If the mechanical check is satisfactory, continue with next step.

  2. Check if the aileron trim indication system is serviceable.

    1. If YES, go to the step 4.
    2. If NO, continue with next step.

  3. Remove DAU 2 and access connector (A18AP1) and aileron trim actuator connector (B38P1). Perform a continuity check and insulation resistance check as follows:

    From To Result
    A18AP1-B5 B38P1-F
    A18AP1-C4 B38P1-E
    A18AP1-D4 B38P1-D
    A18AP1-SH (Shield) B38P1-C (Shield)

    1. If there is continuity, go to step 10.
    2. If there is no continuity, repair defective wiring as required and continue with next step.

  4. Connect the disconnected connectors.
  5. Disconnect the aileron trim actuator connector (B38P1). Perform the voltage check as follows:
    NOTE: Push the aileron trim switch to LWD or RWD while you do the check except pin L.

    From To Expected Result Result
    B38P1-G B38P1-J 28 VDC
    B38P1-G B38P1-K 28 VDC
    B38P1-G B38P1-L 28 VDC

    1. If there is no 28 VDC, go to step 10.
    2. If there is no 28 VDC, continue with next step.

  6. Perform the voltage check at the AIL/RUD/STAB TRIMS control panel connector (AP20P2) between pins as follows:

    From To Expected Result Result
    AP20P2-A AP20P2-K (Ground) 28 VDC

    1. If there is 28 VDC, go to step 9.
    2. If there is no 28 VDC, repair the wiring or power supply and continue with next step.

  7. Connect the actuator connector.
  8. Disconnect the actuator connector.
  9. Perform the continuity check and insulation resistance check between the connectors (AP20P2 and B38P1) as follows:

    From To Result
    AP20P2-C B38P1-G
    AP20P2-J B38P1-K
    AP20P2-D B38P1-J
    AP20P2-K (Ground) B38P1-L (Ground)

    1. If there is no continuity, repair wiring and connect the aileron trim actuator and do close out.
    2. If there is continuity, go sto step 11.

  10. Replace aileron trim actuator.

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

  11. Replace AIL/RUD/STAB TRIMS control panel.
  12. Connect the actuator connector.
  13. Do close out.

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