background
x
loader
Troubleshooting
arrow By ATA By Message Color By Observed Faults by MDCBy Tips

Select color for CAS message that you wish to troubleshoot

(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.

This page includes :

For AOG assistance contact:

CRC Montreal (YUL)
Quick Links

02/19/24

Message Overview:

R ENG ANTI-ICE FAIL (Caution)

DDG Reference: 30-10-06
30-10-07
30-10-08
Pilot Action (QRH): ICE 12-4
System Description: 30-11-00 - Anti-Ice System
30-21-00 - Engine Nacelle Anti-Ice System
Schematic Diagram: SSM 24-61-00-101 - DC Power Center (DCPC) System
SSM 75-10-00-101 - Engine Anti-Icing
SSM 76-11-00-101 - Full-Authority Digital Engine-Control (FADEC) System
Wiring Diagram: WM 24-61-01-1_001 - Sheet 1 - DC Power Center (DCPC) Left - ALL
WM 30-11-09-1_001 - Sheet 1 - Anti-Ice Control - ALL
WM 71-50-01-1_003 - Sheet 3 - Engine Electrical Harness - ALL
WM 71-50-01-1_004 - Sheet 4 - Engine Electrical Harness - ALL
WM 75-10-05-1_001 - Sheet 1 - Engine Nacelle Anti-Ice (RHS) - ALL

Message Description:

The amber 'R ENG ANTI-ICE FAIL' caution CAS message is set when the Engine Anti-Ice is set to ON and the pressure decreases to less than 9.50 psig (65.50 kPa) in the system. The message will go out of view when the pressure increases above 13 psig (89.63 kPa). This indicates bleed air pressure to the respective Nacelle is too low for effective anti-icing.

Bleed air comes from the Engine High Pressure (HP) Bleed Port. Hot bleed air goes through Anti-Ice Tubes to an Annular Piccolo Tube in the Nacelle Air Intake Lip. The Anti-Ice Valve pneumatically controls the bleed air pressure in the nacelle anti-ice system at a nominal 45 psig (310.26 kPa). The Anti-Ice Dual Pressure-Switch monitors the pressure in the anti-ice tube. (MCID 1309).

Possible Causes:

  • Right Protection Printed Circuit Board (PCB) (Right DC Power Center Printed Circuit Board 2 (R DCPC PCB))
  • Anti-Ice Panel (PL19) Right Nacelle (R NAC) Anti-Ice Switch (SDS4)
  • Anti-Ice Differential Pressure Switch
  • Right Nacelle Anti-Ice Solenoid (V02)
  • Right Full Authority Digital Engine Control Channel A (R FADEC A) System (A40)
  • Right Full Authority Digital Engine Control Channel B (R FADEC B) System (A42)
  • TT2 Heater (A44)
  • TT2 Sensor Probe
  • W1 Engine Harness
  • W3 Engine Harness
  • W4 Engine Harness
  • W5 Engine Harness
  • W6 Engine Harness
  • Right Nacelle (R NAC) SB (CB2-E11)
  • Circuit Breaker (CB1-A12) Right Full Authority Digital Engine Control Channel A (R FADEC CH A)
  • Circuit Breaker (CB2-A12) Right Full Authority Digital Engine Control Channel B (R FADEC CH B)

Troubleshooting Tips:

Advisory Wire/Service Bulletin:

  • AW300-72-0348 - AS907 Engine Diffuser Seal and Anti-Ice Valve
  • AW300-30-0400 - Thermal Anti-Ice Valve (TAIV)
  • Honeywell SIL D202208002772 - AS907 Engine Thermal Anti-Ice Valve (TAIV) PN WBG3020G103-003
  • SB 350-76-002 - MODIFICATION – ENGINE CONTROLS – UNCONTROLLABLE HIGH THRUST – EASA RETRO-FIT

Forum Articles/Infoservice/Newsletter: None

    NOTE:

  • The ECU Engine Harness can be found in the SmartPubs, 71-50-05-02 - ECU A Electrical Harness (RH).

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
Engine Nacelle Anti-Ice - Component Location AMM 30-21-00-992-801
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
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
Electrical Connectors - Maintenance Practice - ALL SPM 20-20-00-02

Troubleshooting Recommendations:

  1. Interrogate the MDC as follows:

    1. On the cursor control panel, ensure the toggle switch is to the right and select Anti-Ice, ECS and Fuel buttons simultaneously. The MDC main menu should now be displayed on Display Unit 3.
    2. Using the joystick, select Current Faults (if the fault is active) or Aircraft History to research stored faults. From Aircraft History you can then select Fault Message History and locate the air condition fault logged.
    3. Select the MDC fault from the drop down below to provide additional information to assist in troubleshooting:

  2. Do close out.

Registered and/or unregistered trademarks of Bombardier Inc. or its subsidiaries. © 2015 Bombardier Inc. All rights reserved.