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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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03/01/21

A

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
APM STATUS - 'FAILED'
(FMS Message)

If on FMS Data Link (DL) APM CONFIG page, APM STATUS shows 'FAILED', the cause is the CMU failed to write to the APM (APM may or may not be connected).

This status can be cleared by selecting MEMORY DUMP* on the same page, and then cycling aircraft power. 

B

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
BLEED LOOP FAULT
(Advisory)		 BLEED LOOP FAULT advisory CAS message could be displayed at the end of the PBIT (Power up Built-in-Test of the IASCs) within 3 minutes after the aircraft is powered on.

On the MDC by accessing the current fault:

  1. Confirm that only one bleed leak detection element is detected open or shorted by the IASC.
  2. Power down the aircraft and wait for 2 minutes, then power on the aircraft.
  3. If the procedure is completed with no anomalies noted, it can be concluded that the message was related to a nuisance condition.

C

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK

CVR FAIL
(Advisory)

 The CVR FAIL advisory CAS message should be considered a nuisance under the following conditions:
  1. When the aircraft is powered on, if the Recorder Independent Power Supply (RIPS) is not fully charged, a CVR FAIL CAS message will be displayed as long as the RIPS is in "charge mode". The duration of the "charge mode" may take one to ten minutes.
  2. While the aircraft is in flight and the RIPS is exposed to temperatures below 0⁰C/32⁰F, the RIPS battery heater may be activated multiple times and trigger the CVR FAIL message for approximately 3 minutes each time.

AW300-23-0148

FCOM 2 section 06

F

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
FLAPS FAULT
(Caution)		 Upon aircraft power-up, if a FLAPS FAULT (Caution) CAS message is displayed and no previous attempt to move the flaps or flap handle was performed by the flight crew, proceed with a flap reset by way of the flap reset switch maintenance panel in the entry way.

H

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
HYDRAULIC FLUID TRANSFER BETWEEN RESERVOIRS
  1. Pressurize the LH and RH hydraulic systems.
  2. Left to Right Reservoir Fluid Transfer
    1. Set the Emergency/Parking brake handle.
    2. Fully press both brake pedals.
    3. Release the Emergency/Parking brake handle.
    4. Release both brake pedals.
    5. Repeat steps 2(A) to 2(D) as required until desired quantity has been transferred.
  3. Right to Left Reservoir Fluid Transfer
    1. Fully press both brake pedals.
    2. Set the Emergency/Parking brake handle.
    3. Release both brake pedals.
    4. Release the Emergency/Parking brake handle.
    5. Repeat steps 3(A) to 3(D) as required until desired quantity has been transferred.
  4. Release pressure from the LH and RH hydraulic systems.
 AW300-29-0056

P

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
PITOT-STATIC PROBE uncommanded heated The circuit breakers CB1-E2 (L PITOT) and CB2-E2 (R PITOT) should be opened and tagged after flight on ground and during maintenance to prevent it from remaining heated. AW300-30-0082 Rev. 2

R

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
RUDDER LIMITER FAULT
(Advisory)		 NOTE: The RUDDER LIMITER FAULT (Advisory) CAS message will be displayed after landing if the flight cycle counter within the HSTECU is set to 10.This fault condition can be reset/cleared by performing the Operational Test of the Rudder Travel Limiter Actuator (RTLA):
  1. Make sure the standby instrument is powered on.
  2. Ensure the AOA vanes are neutral and do not have excessive split.
  3. Make sure the Rudder is at 0.
  4. On the SYSTEM TEST control panel, turn the knob to STALL/RUD LIM and PUSH TO TEST and allow the test to complete.
  5. Power the aircraft down and power back up.
  6. Make sure the following messages are not displayed:
    RUDDER LIMITER FAIL (Caution)
    RUDDER LIMITER FAULT (Advisory)
    RUD LIMITER IN TEST (Status)

RUDDER LIMITER FAULT
(Advisory)

STALL PROTECT FAIL
(Caution)

 NOTE: The STALL PROTECT FAIL (Caution) and RUDDER LIMITER FAULT (Advisory) CAS messages could be displayed together if there is water in the Pitot system. The Maintenance Data Computer (MDC) reports a ISI/ADC MACH DISAGREE fault under the Stall Protection Computer (SPC).

CAUTION: ENSURE THE PROBE COVERS ARE REMOVED.

  1. Activate the probe heaters on ground with the following Limitation:
    • The probe heaters should not be activated on ground, in still air for longer than 5 minutes. Activating the probe heaters on the ground, beyond 5 minutes, in still air may result in degradation of the probe life.
  2. After five minutes, if the CAS messages are still present, It is safe to say that water in the probes is not the cause of the failure and further troubleshooting of the system is required.
 AW300-27-34-0010

S

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK

SPOILERS FAULT
(Caution)

RUDDER LIMITER FAULT
(Advisory)

STAB TRIM FAULT
(Advisory)

 Make sure all spoiler panels are sitting flush on the wing surface. If not, push spoiler panels down flush.

NOTE: During aircraft power-up, the SPOILERS FAULT (Caution), RUDDER LIMITER FAULT (Advisory) and STAB TRIM FAULT (Advisory) CAS messages will be displayed together if the control wheel is tilted more than 8 degrees prior to applying hydraulic pressure.

This fault condition can be reset/cleared by leveling the control wheel to the near zero degrees position and resetting the SECU 1 and 2 circuit breakers (CB).

  • Circuit Breaker SPOILER CTRL 1 CBP1-B9
  • Circuit Breaker SPOILER CTRL 2 CBP2-B9
 AW300-27-0086

W

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK

WING ANTI-ICE LEAK
(Warning)

 NOTE: The WING ANTI-ICE LEAK (Warning) CAS message may be displayed during climb. If the message appeared once during climb and not a second time, 2 minutes after the WING ANTI-ICE switch OFF/ON in climb (CLB) power set, perform the following:
  1. Using the MDC, access LRU TEST, IASC-1B or IASC-2B Leak Event Location History.
  2. Confirm that the leak location is less than 15% on the PYLON/WING and FUSE/WING loop (from Wing Station WS 262 to WS 356).
  3. Perform the Operational Test of the wing anti-ice system per AFM Normal Procedure Section 04-03.
  4. If the procedure is completed with no anomalies noted, it can be concluded that the message was related to the nuisance condition.
 AW300-36-0008
L WINDOW HEAT FAIL
(Caution)

L WSHLD HEAT FAIL
(Caution)

R WINDOW HEAT FAIL
(Caution)

R WSHLD HEAT FAIL
(Caution)

 NOTE: The L(R) WINDOW HEAT FAIL or L (R) WSHLD HEAT FAIL could be displayed on ground with certain climatic conditions:
  1. Cold weather operation (cold soaked aircraft and windshield/side window frosted over or snow covered):
    The windshield/side window heat systems should not be used to melt large amounts of snow and ice. Windshield/Window heat should be selected to ON during initial power up only if the windshield is free of snow and ice.
  2. Hot weather operation (hot soaked aircraft and windshield/side window exposed to sun on ground):
    The windshield/side window heat systems should not be used to unnecessarily overheat the windshield/side window. Windshield/Window heat should be selected to OFF.
  3. Overheat protection circuits for each windshield or side window remove power from the affected surface during an overheat condition. Selecting the L(R) WSHLD/WINDOW off de-energizes the applicable windshield or side window and resets the temperature controller.

FCOM Volume 1. 05-27-7 Ice & Rain Protection.

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