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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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01/04/24

Message Overview:

Message Name:

LEFT HI PRESS BLEED SOV CMD /L HPV

Message Code:

3615320BMC

Reporting LRU: Bleed Management Controller (BMC)
Associated CAS: L BLEED SYS FAIL (Caution)
L BLEED FAULT (Advisory)
System Description: 36-11-00 - Bleed Air System
Schematic Diagram: [ G5000 ]  [ Global Express ]  [ Global XRS ] SSM 36-11-00-101 - Bleed Air System - Electrical Schematic
Wiring Diagram: [ G5000 ]  [ Global Express ]  [ Global XRS ] WM 30-11-00-1_001 - Sheet 1 - Left Wing Distribution (Pre SB 700-30-023) - [9004-9010]
[ G5000 ]  [ Global Express ]  [ Global XRS ] WM 30-11-01-1_001 - Sheet 1 - Pre SB 700-1A11-30-005 - [9127-9215]
[ G5000 ]  [ Global Express ]  [ Global XRS ] WM 30-11-01-1_001 - Sheet 1 - Pre SB 700-30-023 - [9159 TO 9215]
[ G5000 ]  [ Global Express ]  [ Global XRS ] WM 71-50-00-1_001 - Sheet 1 - EEC to Aircraft Pylon Disconnect (Lane A) - ALL
[ G5000 ]  [ Global Express ]  [ Global XRS ] WM 71-50-01-1_001 - Sheet 1 - EEC To Aircraft Pylon Disconnect (Lane A) - ALL

Message Description:

The High Pressure Bleed Shut-off Valve (HPV) failed in the open or closed position. Inhibited during Take-Off and Landing.

Possible Causes:

  • Left High Pressure Bleed Shut-off Valve (L HPV)
  • Secondary Power Distribution Assembly 2 (SPDA) (A14)
  • Bleed Management Controller 1 (BMC) (A69)
  • Data Acquisition Unit 3 (DAU) (A30)
  • Associated Wiring

Troubleshooting Tips:

Advisory Wire/Service Bulletin:

  • AW700-36-0365 - Bleed Management Controller - Data Gathering to Reduce No Fault Found (NFF) rate

Forum Articles/Infoservice/Newsletter:

  • Forum Article 2011-VOL 8 issue 23 - Bleed Management Controller (BMC) Top 10 No Fault Found (NFF) vs. Reliability Improvement Modification Program (RIMP) implementation

Flight Operation Notifications Manual (FONM): None

NOTES:

  • Always verify you are working with the current document revision. Access the CIC website to ensure the latest document revision.
  • Questionnaire for replacing the BMC. Follow instructions using this (Fill out form)

Monitor the HPV position via CAIMS.

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 Secondary-Power Distribution Assemblies [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM24-62-01-000-801
Installation of the Secondary-Power Distribution Assemblies [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM24-62-01-400-801
Operational Test of the Secondary-Power Distribution Assembly 2 [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM24-62-01-710-802
Operational Test of the Data Acquisition System [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM31-42-00-710-801
Removal of the Data Acquisition Units (DAU) [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM31-42-01-000-801
Installation of the Data Acquisition Units (DAU) [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM31-42-01-400-801
Removal of the High-Pressure-Bleed Shutoff Valve [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM36-11-01-000-801
Installation of the High-Pressure-Bleed Shutoff Valve [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM36-11-01-400-801
Operational Test of the High-Pressure-Bleed Shutoff Valve [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM36-11-01-710-801
Removal of the Bleed Management Controller [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM36-11-33-000-801
Installation of the Bleed Management Controller [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM36-11-33-400-801
Operational Test of the Bleed Management Controller [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM36-11-33-710-801
CAIMS PMAT General Instructions [ G5000 ]  [ Global Express ]  [ Global XRS ] AMM45-45-00-970-801
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
Wire Repair - Maintenance Practices - ALL [ G5000 ]  [ Global Express ]  [ Global XRS ] SPM20-12-10-02

Troubleshooting Recommendations:

  1. Inspect the HP valve.
    NOTE: To prevent distortion of the valve body during installation follow the instructions regarding the orientation of the couplings in AMM task "36-11-01-400-801 - Installation of the High-Pressure-Bleed Shutoff Valve".

    1. If defects found, go to step 3.
    2. If no defects can be seen, continue with next step.

  2. Interchange the L HP Valve with the R HP valve and Run the aircraft engines to test the system.

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

  3. Perform wiring checks between the L HPV and its ground.

    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. Perform wiring checks between the L HPV and BMC 1.

    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.

  5. Perform wiring checks between the L HPV and SPDA 2.

    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.

  6. Perform wiring checks between the L HPV and DAU 3.

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

  7. Interchange BMC 1 with BMC 2.

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

  8. Interchange DAU 3 with DAU 1.

    1. If system checks are good, replace DAU 3 and do close out.
    2. If fault remains, continue with next step.

  9. Replace SPDA 2.
  10. Do close out.

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