background
x
loader
Operations
arrow By ATA By Message Color By Observed Faults By CAIMS By 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.

For AOG assistance contact:

CRC Montreal (YUL)
Quick Links

A

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
AC POWER DISTRIBUTION EQUIPMENT (ACPDE) RESET
REV: 1		 Refer to AC Power Distribution Equipment (ACPDE) Reset link. Global 5000
Global XRS
 
ACARS DMU FAIL (FMS CDU)
REV: 2		 NOTE: Vendor software fix available. Refer to AW for details.
On the EMS CDU:
1 - SYSTEM/COMM/DATALINK circuit breaker __________ RESET
------------------- END -------------------		 AW700T-0123 Rev 1
AW700-23-0372
 
ADC 1-3 DEGRADED, SHAKER 1 FAIL, STALL PROTECT FAIL (CAS MESSAGES)
REV: 1		 NOTE: These messages may appear on power-up if the two AOA vanes are too far from one another in degrees, e.g. one was ‎moved or rotated by cleaning or cover removal while the aircraft was parked.
ACTION: Rotate the vanes so that they are at relative equal angles.		  
 
AFCS 1 FAIL
REV: 2		 On the EMS CDU:
1 - SYSTEM/AFCS/IAC 1 circuit breaker ______________RESET
------------------- END -------------------		  
 
AFCS 2 FAIL
REV: 2		 On the EMS CDU:
1 - SYSTEM/AFCS/IAC 2 circuit breaker ______________ RESET
------------------- END -------------------		  
 
AFT XFER OFF SCHED CAUTION MESSAGES
REV: 1		 Refer to Ground Operations Checklist for more information on AFT XFER OFF SCHED caution and advisory CAS messages. Ground Operations Checklist
See Non-Normal Procedures section
 
AIR CART ADAPTER
REV: 2		 At some locations, an air adapter for a commercial 'Huffer' air cart may be required to start an engine without the use of APU bleed air (ie. APU bleed deactivated under MMEL). Depending of the airport equipment, a Ground Supply Connector Extension may be required (GSE 36X-11-03).  
 
AIRSPEED SPLITS (Fwd equipment bay door)
REV: 2		 NOTES: There have been some instances of airspeed splits due to the left forward equipment bay door not being flush, causing a disturbance in front of the left pitot probe (up to 10 knots of airspeed split).
ACTION: After reconnecting the Avionics battery, close/latch the forward latch of the left forward equipment compartment door first.		  
 
APU BATT FAIL
REV: 3		 On the DC SYNOPTIC page:
1 - APU BATT voltages ____________CHECK 22 V minimum
2 - AC ELECTRICAL POWER _______________________APPLY
If Fault remains:
3 - AC ELECTRICAL POWER __________________OFF, then ON
NOTE: When the Avionics battery and/or the APU battery are disconnected, the AV BATT FAIL message and/or the APU BATT FAIL message will be displayed on the EICAS before AC power is applied.
Advisory Wire 700T-0083 provides the necessary steps to determine if the AV BATT FAIL or APU BATT FAIL messages, when posted on EICAS after AC power being applied, are due to a nuisance fault being detected by the respective battery charger. Check Advisory Wire 700T-0103 if problem persists.
------------------- END -------------------		 AW700T-0083
AW700T-0103
OH&T preflight preparation #3
 
APU BATTERY
REV: 2		 With a low APU battery, an EXT DC CART can start the APU, but limit the power to 1500 AMPS otherwise the ASCA fuse might blow (located in the aft equipment bay). Note that the Avionics Battery does assist in an APU start, so it must be serviceable.
The minimum battery voltage for APU start is 22 VDC. Use an external DC cart if battery voltage is less than 22 VDC.		  
 
APU BLEED DISABLED (A/C shutdown procedure)
REV: 2		 NOTE: Recommended shutdown procedure to minimize the APU BLEED DISABLED on the next APU start.
Before APU shutdown
1 - APU BLEED switch _____________________________OFF
On BLEED/ANTI-ICE synoptic page:
2 - BLEED MANIFOLD PRESSURE _________________ 0 PSI
3 - APU switch __________________________________ OFF
Wait until the APU is completely OFF.
4 - APU BLEED switch __________________________ AUTO
On BLEED/ANTI-ICE synoptic page:
5 - L and R ENGINE PRV __________ CONFIRMED CLOSED
------------------- END -------------------		 Customer Forum & Newsletter Volume 6 issue 04 (February 24 2009)
 
APU BLEED DISABLED (Reset)
REV: 3		 NOTE: This procedure is a work-around procedure in case of an APU BLEED DISABLED EICAS message being posted after APU power up.
With APU running:
CAUTION: When the BMC circuit breakers are out, there is no Bleed Leak protection available. Keep the BMC offline time to a minimum.
On the EMS CDU:
1 - SYSTEM/BLEED/L & R BMC CH A and CH B_________OUT
On the BLEED/AIR COND panel
2 - APU BLEED switch ____________________________ON
Wait 10 seconds
3 - APU BLEED switch __________________________AUTO
On the EMS CDU:
4 - SYSTEM/BLEED/L & R BMC CH A and CH B__________IN
------------------- END -------------------		 Customer Forum & Newsletter Volume 6 issue 04 (February 24 2009)
AW700-36-0287
 
APU RPM FLUCTUATIONS
REV: 1		 NOTE: During APU operations, if the APU load is changed by either turning the ECS (Packs) to ON, Engine Start or Engine Crank, it is common to notice a slight RPM drop by few percent then back to 100%. The same applies when the load is removed: the APU RPM rises slightly above 100% then back down to 100%. This is normal and is due to the APU FADEC reacting to the load change and governing its fuel schedule to maintain its RPM at 100%.  
 
APU START (cold soaked)
REV: 1		 To prevent a cold APU valve not opening fully due to rapid descent from very cold to very hot humid air, select the start switch to RUN for about 30 seconds prior to selecting START.
This will allow the APU BITE to take place, open the APU door and run some warm outside air around the APU.		  
 
ASCB FAULT
REV: 1		 NOTE: Indicates a single ASCB bus controller failure on the ground. Pull the IAC breakers one at the time. If the failure occurs on Battery power only, suspect IAC 1 or IAC 3 at fault. If it appeared after AC power is applied, it is most likely an IAC 2 failure. This usually happens when the ASCB bus controller in that IAC doesn't power up correctly.
NOTE: Wait at least 1 minute before resetting the circuit breaker. Cascading EICAS messages and loss of certain displays will result of the IAC reset.
On the EMS CDU:
1 - SYSTEM/AFCS/IAC 1(2) or (3) circuit breaker ______ RESET
------------------- END -------------------		  
 
AV BATT FAIL
REV: 4		 NOTE: When the Avionics battery and/or the APU battery are disconnected, the AV BATT FAIL message and/or the APU BATT FAIL message will be displayed on the EICAS before AC power is applied.
Advisory Wire 700T-0083 provides the necessary steps to determine if the AV BATT FAIL or APU BATT FAIL messages, when posted on EICAS after AC power being applied, are due to a nuisance fault being detected by the respective battery charger. Check Advisory Wire 700T-0103 if problem persists.
On the DC SYNOPTIC page:
1 - AV BATT voltages _________CHECK 22 V minimum
2 - AVIONIC BATTERY TEMPERATURE__________CHECKED
- IF ABOVE 57 deg C, refer to AW700T-0048 for recommendations.
3 - AC ELECTRICAL POWER ____________________APPLY
If Fault remains:
4 - AC ELECTRICAL POWER _______________OFF, then ON
------------------- END -------------------		 AW700T-0048
AW700T-0083
AW700T-0103
OH&T preflight preparation #3

11/14/19

B

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
BAGGAGE DOOR
REV: 2		 NOTE: Make sure the baggage door is properly closed prior to starting engines. Do NOT open baggage door after engine start to load items onto the aircraft.
OPENING: When opening the baggage door, to prevent any binding and/or misalignment of the door in its tracks, apply light pressure to the lower aft corner prior to unlatching the handle.
CLOSING: When closing the baggage door, apply light pressure to the lower aft corner to ensure the door is properly seated in its aperture before it is latched closed. If the baggage door was closed and latched from the baggage compartment, it is recommended to visually ensure that the door outside profile is flush in relation to the door surrounding structure.		 AW700-52-0214
OH&T Preflight #9-10
 
BATTERIES (CHARGING AFTER DISCONNECT)
REV: 1		 NOTE: After disconnecting the Avionics and APU batteries for several days, if you want to recharge the batteries with APU or AC external power, it is recommended to keep the AC power applied to the aircraft for a minimum of 1 hour as it may take that much time for the APU battery to reach 80% of its charge capacity.  
 
BATTERIES DISCONNECT
REV: 2		 NOTE: If the aircraft is to be parked for more than a one or two day period of time without AC electrical power being applied, it is recommended to disconnect the Avionics and APU batteries.
If the Avionics battery and/or the APU battery were disconnected and reconnected prior to the next power-up, the AV BATT FAIL message and/or the APU BATT FAIL message will be displayed on the EICAS before AC power is applied.		 AW700T-0083
OH&T Preflight Preparation #3
 
BATTERY TIPS
REV: 3		 BATTERY SWITCH:
Ensure that the Master Battery switch is selected to 'OFF' not the 'EMS' position. EMS position will drain the batteries.
BATTERY DRAINING:
To prevent battery drainage, ensure that both the Refuel / Defuel Control Panels are selected to OFF.
BATTERY CHARGING:
Minimum battery voltage to accept a charge is 7 Volts.		  
 
BLEED FAILURES
REV: 2		 NOTE: Unlike most other systems, all Bleed-related failures automatically latch, which keeps the Failure message posted even after the problem has been isolated. The associated Bleed selector must be physically selected OFF (for a few seconds) to clear the indications.
1 - L (R) ENG BLEED SWITCH _______________________OFF
Wait 10 seconds.
2 - L (R) ENG BLEED SWITCH ______________________AUTO		  
 
BOMBARDIER OPERATIONAL HINTS & TIPS
REV: 2		 NOTE: Pre-flight preparation, airborne and after landing Hints & Tips. They could be found under the PILOT ZONE in the SmartFix Plus website. OH&T
 
BRAKE FAULT
REV: 1		 NOTE: Make sure chocks are installed before doing this procedure. The NORM BRAKE FAIL CAS message will be posted during the circuit breaker reset:
On the EMS CDU:
1 - SYSTEM/LDG GEAR/BRAKE CTL CH A and CH B ______RESET
------------------- END -------------------		  
 
BRAKE FAULT (while towing)
REV: 1		 NOTE: If the APU is started or if the Battery master switch is selected to ON during towing, the BRAKE FAULT message will post due to the BCU PBIT detecting wheel movement. After parking and aircraft chocked, the message can be cleared by performing the following reset procedure.
NOTE: NORM BRAKE FAIL EICAS message will post during the reset procedure.
On the EMS CDU:
1 - SYSTEM/LDG GEAR/BRAKE CTL CH A and CH B _______RESET
------------------- END -------------------		  
 
BRAKES (FREEZING)
REV: 2		 NOTE: If the brakes have been exposed to moisture, flight crews are reminded to:
1. During taxi, use light brake applications to warm the brakes before takeoff (until approx 4 BTMS units).
2. When landing, carry out a positive landing to ensure initial wheel spin up and breakout of frozen brakes if icing has occurred.
3. During the landing roll and subsequent taxi, use brakes to prevent build-up of ice on the wheels and brakes.		 AW700-32-0244, Rev 1
FCOM Volume 1 Cold weather Operations 07-01
 
BRAKES (LOSS OF)
REV: 2		 NOTE: When performing a high speed landing at airspeeds above 155 knots, the wheelspeed transducer signals could degrade to a point where partial or complete brake capability could be lost momentarily. Initially use Thrust Reversers to decelerate and normal braking should start to work normally when wheelspeed decreases below 155 knots. AW700-32-0200
 
(PARKING) BRAKES (SETTING and RELEASE)
REV: 4

PROBLEM: Possible transfer of hydraulic fluid between systems 2 and 3.
ACTION: Set and release the brakes in the SAME sequence. If you set them by pressing the brake pedals first then pulling on the Park brake handle, then release them the same way (press and hold the brake pedals then release the Park brake handle). It is recommended that crews come to an agreement on which way their aircraft brakes will be set.

The recommended parking brake set and release procedure is as follows:

PARKING BRAKE------------------------------ON

  • Brake Pedals-------------------PRESS
  • Parking brake------------------ON
  • Brake Pedals-------------------RELEASE

PARKING BRAKE------------------------------OFF

  •  Brake Pedals-------------------PRESS
  •  Parking brake------------------OFF
  •  Brake Pedals-------------------RELEASE
------------------- END -------------------		 OH&T Preflight #7

11/15/19

C

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
CABIN POWER
REV: 1		 ON: Ensure that both cockpit touch screens have completed their loading before selecting CABIN POWER.
OFF: Always make sure CABIN POWER is turned OFF on aircraft shutdown.		  
 
CABIN POWER (ROCKWELL COLLINS CES)
REV: 3		 NOTE: On Collins CMS equipped aircraft, brief the flight attendant to wait approximately 15 minutes after CABIN POWER has been selected to ON to allow all functions to boot-up properly.
Always make sure CABIN POWER is turned OFF on aircraft shutdown.		 Service Information Letter - Effective Use of the Startup Manager
 
CAIMS INFO
REV: 1		 NUISANCE L (R) PACK FAULT : Some nuisance CAIMS messages may be posted as along with valid CAIMS fault messages and it is almost impossible to discriminate between them. Therefore during troubleshooting, it is recommended not using CAIMS in active mode while the packs are operating. AW700-21-0160
 
CAS MESSAGES AFTER POWER-UP
REV: 2		 NOTE: Following a power-up sequence, if any 'unusual' CAS messages are posted, consider powering down the aircraft completely, allowing the systems to shutdown before powering up again and re-booting the computers. If the problems persist, as a last resort, power down again and disconnect both the APU and AVIONICS batteries. Wait a few minutes, reconnect the batteries and power-up again.  
 
CB TRIP
REV: 3		 CAUTION
One circuit breaker reset is permitted only if required for continued safe flight.
On the EMS CDU:
1 - STATUS _____________ SELECT and ACKNOWLEDGE
------------------- END -------------------		 Ref. FCOM Volume 1, 05-08-2, CB TRIP (Advisory)
 
CES SYSTEM
REV: 2		 NOTE: If CES system does not power up properly, the aircraft will need to be shutdown and rebooted. Remove aircraft power and select battery master switch to OFF and wait for about 5 minutes. Then re-power the aircraft normally and let the CES system boot up.
If the CES control panel button gets stuck in the pressed position, it could freeze the CES system by overloading the databus.		 OH&T, Airborne #3
 
CES POWER UP SEQUENCE
REV: 1		 Do not operate any CES equipment until the Power Up Status page is displayed on the galley monitor with the two (2) MCEs showing green 'Ready' check marks.
Both (CMC) EFBs can be powered up but the CES application on the EFBs should not be launched until the above condition is met.

CES RESET
REV. 1
  1. To ensure a full reset of the CES, turn off the cabin power switch and pull the MCE#1 and MCE#2 breakers for 30 seconds.
  2. Reset the breakers and put cabin power back on. After power-up, there is a power-up page that comes up and you need to wait for the Power-Up page to show only green check marks (approx 10-15 mins).
 
CHOCKS
REV: 2		 NOTE: Ensure the aircraft is properly chocked. If the only wheel chocked is the nose wheel, along with the torque link being disconnected (NEITHER main wheel chocked) ensure BOTH nose wheel tires are chocked. Chocking a single wheel on a sloped ramp may cause the nose wheel to turn 90° and potentially jump the chocks.  
 
COVERS
REV: 2		 NOTE: Remove all probe covers prior applying AC power to the aircraft. On power-up, the HBMU (Heater/Brake Temperature Monitoring Unit) applies heat to each probe for testing purposes. This test cycle could damage the different covers. Also, check the probe covers for evidence of fraying. Frayed fibers could infiltrate the Pitot-Static ports.  
 
CTR FUEL XFER FAIL
CTR XFER FAULT
REV: 3		 NOTE: Some operators have reported that the center transfer pumps failed to produce pressure in flight, even though the pumps were submerged in fuel and running. This condition occurred when the pump failed to re-prime while the aircraft was climbing through the 30,000 to 40,000 feet range, and few failures occurred in cruise. See Advisory Wire for details and instructions.
NOTE: Although Center tank fuel is considered unusable, the Center tank quantity will slowly decrease due to the operation of the fuel scavenge system.;		 AW700-28-0072
AFM NON-NORMAL PROCEDURES
05-11-3 OR 05-11-21

D

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
DC Power Distribution Equipment (DCPDE) Reset
REV: 1		 Refer to DC Power Distribution Equipment (DCPDE) Reset link according to the aircraft model G5000
XRS
 
DEICING/ANTI-ICING
REV: 2		 BOMBARDIER DEICING / ANTI-ICING FLUID APPLICATION INFORMATION GUIDE. It can also be found under the OPERATIONS MAINTENANCE ZONE Hints & Tips in the SmartFix Plus website.  
 
DISPLAY UNITS COOLING
REV: 1		 NOTE: During high ambient air temperature operations, limit the Display unit use to 30 minutes when the cockpit or cabin temperatures are above 40 degrees Celsius. For continued operations, maintain the cockpit and cabin temperatures below 30 degrees Celsius by using either the aircraft air conditioning systems (PACKS) or by using forced cool air. If the display units are not required, it is recommended to turn them OFF. AW700-31-0226
 
DISPLAY UNIT LOCK-UP
REV: 1		 1 - Affected SG switch ___________________________ALTN
NOTE: During normal and non-reverted operations:
SG 1 supplies the DU 1 & 2
SG 2 supplies the DU 5 & 6
SG 3 supplies the DU 3 & 4.
2 - Affected SG switch __________________________NORM		  

E

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
EGPWS Callouts
REV: 1		 NOTE: Due to a potential conflict between the 'MINIMUMS MINIMUMS' and the '100' Callouts, especially during a CAT II approach with a DH setting of 100 feet which could lead to the MINIMUMS MINIMUMS Callout not being heard, Service Bulletin 700-31-024 has been issued. For aircrafts POST SB 700-31-024 the following EGPWS Callouts will be in effect: '50' '30' & '10'. SB700-31-024
 
ELEC SYS FAIL
REV: 1		 1 - BATT MASTER SWITCH _________ CYCLED (ON to OFF to ON)
If the message(s) does not clear, follow the procedures in the Advisory Wire.
2 - COMPLETE AIRCRAFT POWER __________________ REMOVE
3 - BATT MASTER SWITCH ____________________________OFF
4 - EXTERNAL AC CART _________________________CONNECT
5 - EXT AC PBA (overhead panel) ____________________SELECT
6 - ELEC SYS FAULT or ELEC SYS FAIL __________NOT POSTED
7 - AC & DC SYNOPTIC PAGES ____________________ NORMAL
8 - BATT MASTER SWITCH ____________________________ ON
9 - ELEC SYS FAULT or ELEC SYS FAIL __________ NOT POSTED
10 - AC & DC SYNOPTIC PAGES ___________________ NORMAL
------------------- END -------------------		 AW700-24-0252
AW700-24-0136
 
ELEC SYS FAULT
REV: 1		 1 - BATT MASTER SWITCH _________ CYCLED (ON to OFF to ON)
If the message(s) does not clear, follow the procedures in the Advisory Wire.
2 - COMPLETE AIRCRAFT POWER __________________ REMOVE
3 - BATT MASTER SWITCH ____________________________OFF
4 - EXTERNAL AC CART _________________________CONNECT
5 - EXT AC PBA (overhead panel) ____________________SELECT
6 - ELEC SYS FAULT or ELEC SYS FAIL __________NOT POSTED
7 - AC & DC SYNOPTIC PAGES ____________________ NORMAL
8 - BATT MASTER SWITCH ____________________________ ON
9 - ELEC SYS FAULT or ELEC SYS FAIL __________ NOT POSTED
10 - AC & DC SYNOPTIC PAGES ___________________ NORMAL
------------------- END -------------------		 AW700-24-0252
AW700-24-0136
 
EVAC TOILET
REV: 2		 PRIOR TO AIRCRAFT SHUTDOWN:
1 - Potable water system (PWS) _____________________OFF
NOTE: A minimum of 5 seconds between the PWS shutdown and the cabin power shutdown should be observed for proper pump selector valve closure.
After 5 seconds MINIMUM:
2 - CABIN POWER ________________________OFF
IN FLIGHT:
NOTE: In the event of a loss of power for the PWS during flight, monitor and flush every hour the fwd and aft lavatory toilets for water overflow until landing.		 AW700-38-0273
 
EXTERNAL POWER HINTS AND TIPS
REV: 2		 PROBLEM 1: AC power only comes on line intermittently.
ACTION 1: Make sure external AC power cart is adjusted to exactly 115VAC.
PROBLEM 2: External AC power kicks off when turning a hydraulic pump on.
ACTION 2: Apply 115VAC EXT AC to the aircraft. Reduce the external AC power cart voltage to 113VAC. When the checks requiring a hydraulic pump are finished, the cart voltage should be returned to 115VAC.		  

F

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
FD/AFCS LOC Capture and Tracking Performance
REV: 1		 PROBLEM: During an ILS approach, the crew noticed an unusually late AFCS capture and unstable tracking of the LOC beam. The discrepancy was due to the AFCS use of erroneous range-to-nav aid data based on an incorrect navaid selection by the FMS out of the FMS database.
ACTION: For all AFCS coupled ILS approaches (Flight Director or Autopilot) to a facility without co-located DME, it is recommended that the VHF NAV radio tuning be accomplished by allowing the FMS to Autotune the appropriate ILS frequency, or alternatively by using the FMS Tune-By-Ident feature.		 AW700-34-0278
 
FDR FAIL
REV: 3		 NOTE: No action is required. The message will clear when the engines are started.
If on APU electrical power only, the FDR FAIL EICAS message will not clear on PEM activation since the DAU 4, by design, won’t send data to the FDR through its dedicated ARINC 717 databus.
If the engines are running:
1 - Pilot Event Marker (PEM) __________________Press and hold for 10 seconds.
------------------- END -------------------		  
 
FLT SPOILERS FAIL
REV: 1		 NOTE: Only 1 hydraulic pump operation is available during APU generator ONLY operations. External AC cart or engines running is required in order to perform the following task.
1 - Hydraulic systems 1 -2 -3 _________________PRESSURIZED
On the EMS CDU:
2 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA __________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 1 CHB __________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 2 CHA __________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 2 CHB __________PULLED
NOTE: Wait 30 seconds. Reset all circuit breakers within 10 seconds.
3 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA ___________RESET
SYSTEM/FLT CONTROLS/FLT CTL 1 CHB ___________RESET
SYSTEM/FLT CONTROLS/FLT CTL 2 CHA ___________RESET
SYSTEM/FLT CONTROLS/FLT CTL 2 CHB ___________RESET
NOTE: SPLRS STAB IN TEST will be posted on the EICAS. Do not touch any flight controls during the test. A minimum of 3 minutes without any cockpit and flight controls inputs should be observed.
After the 3 minutes time delay
4 - SPLRS STAB IN TEST EICAS message ___________CLEARED
------------------- END -------------------		  
 
FLT SPOILERS FAULT
REV: 1		 NOTE: Only 1 hydraulic pump operation is available during APU generator ONLY operations. External AC cart or engines running is required in order to perform the following task.
1 - Hydraulic systems 1 -2 -3 _________________PRESSURIZED
On the EMS CDU:
2 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA __________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 1 CHB __________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 2 CHA __________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 2 CHB __________PULLED
NOTE: Wait 30 seconds. Reset all circuit breakers within 10 seconds.
3 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA ___________RESET
SYSTEM/FLT CONTROLS/FLT CTL 1 CHB ___________RESET
SYSTEM/FLT CONTROLS/FLT CTL 2 CHA ___________RESET
SYSTEM/FLT CONTROLS/FLT CTL 2 CHB ___________RESET
NOTE: SPLRS STAB IN TEST will be posted on the EICAS. Do not touch any flight controls during the test. A minimum of 3 minutes without any cockpit and flight controls inputs should be observed.
After the 3 minutes time delay
4 - SPLRS STAB IN TEST EICAS message ___________CLEARED
------------------- END -------------------		  
 
FMS (cycling)
REV: 1		 Cycling the FMS button on the glareshield could cause FMS 3 (if installed) to become the selected NAV source. If this is the case, it is difficult to determine because the magenta color of the indication for FMS 1 is the same as for FMS 3. TOLD speeds may not be displayed in this case.  
 
FMS ANOMALIES IN VNAV
REV: 2		 NOTE: During VNAV Capture descent, if the crew decides to alter the vertical path angle through the FMS CDU 2, there could be a momentary loss of A/T, Lat/Vert AFCS Modes (PTCH and ROLL reversion), FMS Reverting to Single Operation, and FMS CDU display blinking (warm start). All of the above observations can be reset. See Advisory Wire AW700-34-0190 for details. AW700-34-0190
 
FMS DATABASE LOADING
REV: 1		 NOTES: To load the FMS databases, ensure IRS are OFF. Ensure that FMS 3 (if installed) is not in AUTO mode. Load one FMS at a time  
 
FMS - FULL PERF + SMART PERF
REV: 2		 NOTES:
1 - Under the PERF INDEX page on the FMS CDU, when selecting the Performance Initialization (PERF INIT) page, use POUNDS of Fuel Reserve instead of NBAA or Minutes.
2 - If the FMS System continuously drops from FULL PERF to GS/FF, the vendor suggests reloading the Aircraft Database in all FMS.
3 - It is recommended to turn the SMART PERF LEARNING to ON until the crew is satisfied with the performance predictions (+/- 3% fuel/time). Usually, the performance should be acceptable after approximately 10 hours of flight. Once the crew is satisfied with the performance predictions, turn SMART PERF LEARNING to OFF and ask maintenance to save the Customized ACDB to a disk so it can be reloaded if needed (IAC replacement for example).		 AW700-34-0145
 
FMS OPTIMUM ALTITUDE INACCURATE
REV: 2		 NOTE: If the FMS Optimum Altitude is questionable, refer to the Cruise Altitude Selection chart in the Flight Planning and Cruise Control Manual (FPCCM) for Optimum Altitude confirmation. AW700-34-0210
 
FMS PAIRING TIPS
REV: 1		 As per the AFM LIMITATIONS Section 02-09 Navigation Systems - DEPARTURE, ARRIVAL AND APPROACH:
“The flight plans on the paired FMSs must be identical when conducting FMS approaches”.
When a different FMS is selected to be part of the pair, that FMS begins operating in the selected mode without a cold start. The two FMSs which are operating as a pair determine the master based on the EFIS selection. The new slave then synchronizes its flight plan and performance initialization with the master. If the custom databases do not match, the pilot must transfer the custom database before going to DUAL or INITIATED XFER.
NOTE: The FMS pairing modes are DUAL, INITIATED XFER, INDEPENDENT and SINGLE. In order to have the FMS synchronized in either DUAL or INITIATED XFER, the following conditions have to be met:
  1. NZ Software version identical
  2. Navigation database and cycle identical
  3. Custom database identical
  4. FMS positions within 10 NM
  5. Configuration pins identical
Should one of those conditions is not met when the pairing mode is selected, a PROBLEMS line select key will be prompted on the lower right corner of the FMS CDU. Pressing that LSK will display the reason for the aborted mode selection. The possible problems for a failed mode selection are as follow:
MODE DIFF :
Indicates one FMS is in a different operating mode than the other(s) FMS(s).
SW PROGRAM :
IAC do not have the same software.
PPOS DIFF :
FMS 1 & FMS 2 present positions differ by more than 10 NM.
CONFIG PIN:
Certain configuration pins do not match between FMS systems.
NAV DB:
Navigation Databases between NZs are not selected to the same cycle on the NAV IDENT page.
CUSTOM DB:
Custom Databases between NZs are not identical.
FMS x INOP:
FMS 1 INOP indicates that FMS 2 does can not “see” FMS 1. FMS 2 INOP indicates that FMS 1 does can not “see” FMS 2.		  
 
FMS TOLD
REV: 1		 FMS TOLD data only reads brake temperatures from the left outboard and right inboard brake temperature sensors. If any other brake temperature is higher than that displayed in the FMS, that higher brake temperature must be used for TOLD calculations. This should be fixed in Batch 3. AW700-34-0247
 
FUEL ADDITIVES
REV: 1		 NOTES: Refer to Ground Operations Checklist for a list of approved fuel additives. Ground Operations Checklist
See Limitations section
 
FUEL AUTO INHIBIT (DURING REFUELING)
REV: 2		 NOTES:
1 - The following conditions could cause an INHIBIT message during AUTO refueling:
- Fuel load between 5000 - 7000 lbs and fuel in the CTR and/or AFT tank
- Pre-Selected fuel load between 32000 - 35000 lbs
- Any interruption during the AUTO refueling process between 13000-19000 lbs
- If the AUTO refueling is aborted, the INHIBIT message will be posted
On the RDCP (Refuel Defuel Control Panel)
1 - MANUAL/AUTO Mode selector ____________OFF
2 - MANUAL/AUTO Mode selector ____________AUTO
If unsuccessful:
3 - MANUAL/AUTO Mode selector ____________MANUAL
4 - Manual SOV switches __________________AS REQUIRED
------------------- END -------------------		 AW700-28-0177
 
FUEL LOAD (HOW TO GET A FULL FUEL LOAD)
REV: 1		 NOTES: Use the MANUAL REFUEL mode whenever refueling the aircraft to maximum capacity. The intended use of the AUTO REFUEL is to select fuel levels (less than full) where a specific amount of fuel in pounds or kilograms is desired.
In the MANUAL REFUEL mode, refueling will automatically stop when the fuel level reaches the high-level sensor threshold for all tanks. This is indicated on the RDCP by a 'FULL' message in all the individual tank quantity displays.
Refer to Ground Operations Checklist provides the High Level Sensor (HLS) minimum and maximum HLS thresholds in the MANUAL REFUEL mode for different types of fuel.		 Ground Operations Checklist
See Normal Procedures section
 
FUEL QTY DEGRADED
REV: 1		 NOTE: On the ground, the display of the 'FUEL QTY DEGRADED' message is related to the FMQGCs inability to upgrade the fuel density value due to incorrect refueling procedure or system malfunctions. When these conditions occur, the message will be displayed 3 minutes after the completion of the refueling operation. Follow these procedures in order to avoid the FUEL QTY DEGRADED nuisance message during refueling or how to reset it
Prevention:
In AUTO refueling mode:
On the RDCP (Refuel Defuel Control Panel)
1 - PRESEL window ________________ 'COMPLETE' msg posted
2 - START/STOP/SOV TEST switch _____________________ STOP
3 - SOV STOP message ___________________________ POSTED
4 - MANUAL/AUTO Mode selector ________________________ OFF
------------------- END -------------------
In MANUAL refueling mode:
On the RDCP (Refuel Defuel Control Panel)
1 - ALL Manual SOV switches __________________________ OFF
2 - MANUAL/AUTO Mode selector _______________________ OFF
------------------- END -------------------
RESET:
On BATT power only:
1 - MANUAL/AUTO Mode selector _______________________ OFF
On AC power:
On the EMS CDU:
1 - SYSTEM/FUEL/FUEL COMPUTR CH A & B _____________ OUT
Wait 5 seconds…
2 - SYSTEM/FUEL/FUEL COMPUTR CH A & B ___________ RESET
------------------- END -------------------		 AW700-28-0185
 
FUEL-RELATED CAS MESSAGES
REV: 1		 NOTES: For a list and an interpretation of fuel CAS messages, refer to Ground Operations Checklist. Ground Operations Checklist
See Non-Normal Procedures section
 
FUEL TEMP SENSOR
REV: 1		 NOTE: If the aircraft is shutdown to Battery power only, you should have a FUEL TEMP SENSOR (amber) message posted within approximately 15 seconds. If you do not see this message, one of the Refuel/Defuel Control Panels (RDCPs) has been most likely left to ON (or AUTO / MANUAL modes depending of your RDCP configuration). Leaving one of your RDCP to ON (or AUTO/MANUAL) could potentially lead to an APU battery drainage.  
 
FUEL TRANSFER AFTER SHUTDOWN
REV: 1		 NOTE: If aircraft power is removed during AUTO or manual ( à or ß ) wing to wing fuel transfer, the associated wing transfer shutoff valve (SOV) will remain opened, therefore creating a path for fuel to flow from the high fuel wing to the low fuel wing. The severity of the issue increases if the aircraft is parked on an unlevelled surface.
Preventive actions:
Before removing aircraft power:
1 - CAS message list _____________________________REVIEW
Check for any Caution, Advisory or Status messages <- (->) FUEL XFER ON
Make sure that the automatic wing-to-wing transfer is completed, i.e. when the advisory <- (->) FUEL XFER ON message is no longer displayed.
If the manual wing-to-wing transfer is initiated, continue the transfer until the wing balance is achieved, and set the WING XFER rotary switch to AUTO before removing the aircraft power.
NOTE: Check for any Caution, Advisory or Status messages <- (->) FUEL XFER ON
On the FUEL SYNOPTIC page:
2 - Both WING XFER SOV _________________CONFIRM CLOSED
------------------- END -------------------		 Customer Forum & News Letter Volume 08 / Issue 19
See page 5 of 10
 
FUEL TYPES
REV: 1		 NOTE: Refer to Ground Operations Checklist for a list of fuels approved for use. Ground Operations Checklist
See Limitations section
 
FUEL SCAVENGING (towing)
REV: 3		 NOTE: It is possible that an aircraft being towed with more than 12,000 lbs of fuel in each wing tank may have fuel enter the vent system and cause a fuel spill at the next refueling event. Fuel system MUST be scavenged. Refer to your maintenance department for the Aircraft Maintenance Manual task (09-10-00-584-801) and instructions. Ground Operations Checklist (GEX)-See NORMAL PROCEDURES
QRH (GEX)-See SUPP-09
AMM (GEX)-See task 09-10-00-584-801
----
Ground Operations Checklist (G5000)-See NORMAL PROCEDURES
QRH (G5000)-See SUPP-09
AMM (G5000)-See task 09-10-00-584-801
----
Ground Operations Checklist (XRS)-See NORMAL PROCEDURES
QRH (XRS)-See SUPP-09
AMM (XRS)-See task 09-10-00-584-801
 
FWD FAIL AND INHIBIT ON RDCP (refueling)
REV: 1		 NOTE: During automatic refueling system operation (SOV test), there is a possibility for fuel to enter and accumulate in the forward tank, even when no fuel is scheduled for this tank. If fuel is permitted to accumulate between refueling sessions, it could cause the RDCP to display FWD FAIL and INHIBIT messages and to possibly display CTR tank quantity indication on the EICAS. Refer to Advisory Wire AW700-28-0221 for recommended refueling instructions. AW700-28-0221

G

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
GALLEY (precautions)
REV: 1		 NOTE: Prior to take-off, ensure no objects are stored behind the galley tambour door that would inadvertently open the faucets.  
 
GLD WILL NOT TEST or Erratic RAD ALT indications
REV: 2		 NOTE: The Radio Altimeters antennas are located aft of the rear bay access compartment door. Any contaminants (such as accumulated water or snow) or obstacles (such as declined slope, ditch, storm drain, concrete wall) under them will interfere with the Radio Altitude indications. The Radio Altitudes are part of the GLD test logic. Moving the aircraft over a flat and non-contaminated surface should rectify this issue. OH&T, preflight prep #5

11/14/19

H

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
HDG FAIL (EFIS ANNUNCIATION)
REV: 3		 NOTE: Possible 'HDG FAIL' annunciation on PDF HSI display and MFD when the aircraft enters or exits the Northern Polar region between latitudes of 70 and 72.5 degrees N (and between 90 and 120 degrees W longitude).
On FMS CDU / MAINTENANCE / page 3/3:
1 - SELECTED HDG MODE ________________________TRUE
------------------- END -------------------		 AW700-34-0235
 
HORIZONTAL STAB (when exposed to rain)
REV: 3		 NOTE:
PROBLEM: Water accumulating in the Horizontal Stab while the aircraft is left to stand under raining conditions, especially with the horizontal stab in the full nose up position..
RECOMMENDATIONS: It is recommended to park the aircraft with the horizontal stab positioned to the neutral position. If the aircraft has been exposed to rain or was deiced, it is recommended, prior to dispatch, to fully cycle and hold the elevators and Horizontal Stab in both directions until all water/deicing fluid has drained.
ACTIONS: Recommended Service Bulletin SB 700-55-004 has been issued as a corrective action to this problem (drain holes).		 700T-0034
SB 700-55-004
 
HOT MIC BETWEEN PILOTS SENSITIVITY
REV: 1		 ISSUE: At times, the Hot Mic between the pilots cuts in and out unless the boom is very close to the mouth.
RECOMMENDATION: By selecting the PA Microphone Selection button 'out', (not the transmit), this will reduce, if not eliminate this problem.
 
HUD COMBINER
REV: 2		 NOTE: If the HUD combiner glass is accidentally moved and locked into the crash position, to safely return it to the operational position, push the Crash Reset Button located at the top left of the locking handle. 700T-0118
 
HYDRAULIC FLUID TRANSFER (system 2 & 3)
REV: 4

NOTE: There is a possibility to transfer fluid over time between hydraulic systems 2 & 3 through the brake shuttle valves if the Parking Brake is not set and released in the proper sequence. Refer to the (PARKING) "BRAKES (SETTING and RELEASE)" SmartOps task for the proper sequence. Also, refer to Advisory Wire and InfoService for the procedure on how to transfer hydraulic fluid from System 2 back to System 3 or from System 3 back to System 2.

 700T-0022 Rev.1
April 2002 Issue No. 2

I

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
IRSs Fail to Align
REV: 1
 When IRSs fail to align, try selecting 'Last Known Position' instead of 'GPS position'.  
 
ICE
REV: 1
 NOTES: Heavy rain has been known to generate an 'ICE' CAS advisory message on the ground  
 
ICE
or
ICE
and
STALL WARN ADVANCE
REV: 2
 NOTE: If posted on the ground, these 2 messages could be associated with Anti-Icing fluid type II or IV applications or heavy rain.
Actions:
If the ICE message goes out and remains out for at least 45 seconds:
On the EMS CDU:
1 - CNTL/STALL WARN ADVANCE ___________ REVERT to NORM
If the ICE message remains:
CAUTION: Wing Anti-ice system is NOT to be selected to ON if Anti-icing fluid SAE type II, type III or type IV have been applied. Refer to AFM Limitations for details and instructions.
On the ANTI-ICE overhead panel:
1 -WING Anti-ice switch ______________________________ ON
On the BLEED/ANTI-ICE synoptic page:
2 - Wings leading edges flow lines ____________________ GREEN
Wait 45 seconds:
On the EMS CDU:
3 - CNTL/STALL WARN ADVANCE __________ REVERT to NORM
------------------- END -------------------		 AFM Limitations 02-04

L

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
L BLEED FAULT
REV: 2		 NOTE: Unlike other systems, all Bleed-related failures automatically latch, which keeps the Failure message posted even after the problem has been isolated. The associated Bleed selector must be physically selected OFF (for a few seconds) to clear the indications.
1 - L ENG BLEED SWITCH ___________________________OFF
Wait 10 seconds.
2 - L ENG BLEED SWITCH __________________________ AUTO
------------------- END -------------------		  
 
L FADEC N1 CTL
REV: 1		 NOTE: If any TAT HT 1 (2) (3) FAIL EICAS messages is posted, refer to the recommended actions for those messages first, reset and proceed with step 1 below.
1 - L EPR / N1 switch __________________________RESET
------------------- END -------------------		  
 
L PACK FAULT
REV: 2		 NOTE: It is NOT unusual the see this message being displayed if the PMAT is ON and CAIMS is active (AW700-21-0160). Closing CAIMS will clear the L PACK FAULT nuisance message.
NOTE: It is NOT unusual to see this message being displayed while on APU bleed in hot / high elevations. If this is the case, switching to engine bleed will eventually clear the message.
1 - TRIM AIR ________________________________ OFF THEN ON
2 - L PACK _________________________________ OFF THEN ON
If message doe not clear:
3 - TRIM AIR ______________________________________ OFF
4 - L PACK _______________________________________ OFF
On the EMS CDU:
5 - SYSTEM/AIR COND-PRESS/L (R) PACK CTLR CH A ___ RESET
6 - SYSTEM/AIR COND-PRESS/L (R) PACK CTLR CH B ___ RESET
7 - TRIM AIR ______________________________________ ON
8 - L PACK _______________________________________ ON
------------------- END -------------------		 AW700-21-0160
 
L REVERSER FAIL
REV: 1		 NOTE: L / R REVERSER FAIL CAS message has been seen when the pilot 'walks' the throttle towards reverse.
Actions:
Make sure the thrust reverser is selected and in the detent (stops) within a second or two. Try to restart engines if unable to clear CAS.		  
 
LOC (ILS) & BC S-TURNING (when FD coupled to reverted SG)
REV: 1		 NOTE: Couple the FD to the non-reverted PFD. AW700-22-0209

M

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
MAN PRESS FAULT
REV: 1
 On the EMS CDU:
1 - SYSTEM/AIR COND -PRESS/AUTO PRESS 1 CB________RESET
If the MAN PRESS FAULT EICAS message is still posted, go to step 2.
2 - SYSTEM/AIR COND -PRESS/AUTO PRESS 2 CB________RESET
------------------- END -------------------		  

O

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
OIL REPLENISHMENT SYSTEM
REV: 1
 NOTE: When replenishing the engine and/or APU oil (in the allowable time frame), if the system does not operate when depressing the PBA (left engine or right engine or APU on Remote Replenishment Panel) for 1 to 2 seconds, depress the PBA for several seconds (5 to 6) to ensure all contacts are made and the enable logic is satisfied. OH&T, after landing #7
 
OUTLETS IN CABIN (TOTAL LOSS)
REV: 1
 NOTE: If you loose 115V power at all the outlets in the cabin, perform the following action in an attempt to reset the system.
On the RH Cockpit bulkhead (behind the Copilot Seat):
1 - OXYGEN TEST/RESET SWITCH _________HOLD IN RESET
Wait few seconds,
2 - OXYGEN TEST/RESET SWITCH ________RELEASE TO OFF
------------------- END -------------------		  
 
OXYGEN SERVICING
REV: 1
 NOTE: Due to local Regulatory rules, Korea and Japan do not have any Oxygen Servicing capability. Contact your FBO for further details.
At some locations in China and Russia, an Oxygen adapter may be required to Service the Oxygen system. Contact your FBO for further details.		  

P

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
PACK TEMPERATURE SPLIT
REV: 1		 NOTE: Provided there is no associated Pack CAS messages, it is not unusual to observe a pack outlet temperature split of 40 degrees Celsius between the left and right packs, Provided all the Zone temperature selected targets are reached, consider the pack split as a normal behavior, especially during hot and humid environments.  
 
PASSENGER DOOR
REV: 1		 NOTE: When closing the Passenger door, ensure that the bottom step retracts before the door reaches the closed position. If the bottom step does not retract, depending of your door switch operation configuration, either push the door switch again or release the door switch in order to stop the closing process and re-open the door.  
 
PAVEMENT DATA
REV: 1		 NOTE: Refer to the Airport Facility Manual - Section 07. Airport Facility Manual - Section 07
 
PHONE SYSTEM
REV: 1		 NOTE: The phone system defaults to the Iridium system. If you want to force the phone system to use the Inmarsat option, press '**' on the handset and then dial your number.
**00 + Country Code + Area/City Code + Number		  
 
PILOT EVENT MARKER (PEM)
REV: 1		 NOTE: When logging an Event (whether caused by a Failure, Exceedance or Pilot Event Marker button), record the DATE, UTC TIME and flight conditions in order to help maintenance in their PMAT investigation.  
 
PITCH FEEL FAULT
REV: 2		 NOTE: Only 1 hydraulic pump operation is available during APU generator ONLY operations. External AC cart or engines running is required in order to perform the following task.
On HYDRAULIC Control Panel:
1 - Hydraulic systems 1 -2 -3___________________PRESSURIZED
On the EMS CDU:
2 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA ____________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 1 CHB____________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 2 CHA ____________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 2 CHB____________PULLED
NOTE: Wait 30 seconds. Reset all circuit breakers within 10 seconds.
3 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA _____________RESET
SYSTEM/FLT CONTROLS/FLT CTL 1 CHB _____________RESET
SYSTEM/FLT CONTROLS/FLT CTL 2 CHA _____________RESET
SYSTEM/FLT CONTROLS/FLT CTL 2 CHB _____________RESET
NOTE: SPLRS STAB IN TEST will be posted on the EICAS. Do not touch any flight controls during the test. A minimum of 3 minutes without any cockpit and flight controls inputs should be observed.
After the 3 minutes time delay
4 - SPLRS STAB IN TEST EICAS message ____________CLEARED.
------------------- END -------------------		  
 
PITOT 1 HT FAIL
PITOT 2 HT FAIL
PITOT 3 HT FAIL
L AOA HEAT FAIL
R AOA HEAT FAIL
ICE DETECTOR FAULT
L PROBE MON FAIL
R PROBE MON FAIL
TAT HT 1 FAIL
TAT HT 2 FAIL
TAT HT 3 FAIL
REV: 2		 On the EMS CDU:
1 - SYSTEM/ICE/HBMU 1 and HBMU 2 __________________RESET
------------------- END -------------------		 OH&T, Pre-flight #6
 
PMAT
REV: 1		 AW SYNOPSIS: When shutting down the PMAT, never press the 'Green' button while power is on and applications are running and never abort an Auto Shutdown. The two methods of shutting down the PMAT are:
- Auto Shutdown
- Manual Shutdown
See the Advisory Wire for details
NOTE: If you start up the PMAT in flight, some EICAS messages related to IAC and AFCS could come up intermittently.
NOTE: Shutdown PMAT before selecting battery master to OFF.		 700T-0015
 
POTABLE WATER SYSTEM RESET
REV: 1		 NOTE: Reset procedures for the Potable water system through the CES touchscreen or Backup Control Panel. Reset of the Potable Water System

R

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
R BLEED FAULT
REV: 2		 NOTE: Unlike most other systems, all Bleed-related failures automatically latch, which keeps the Failure message posted even after the problem has been isolated. The associated Bleed selector must be physically selected OFF (for a few seconds) to clear the indications.
1 - R ENG BLEED SWITCH ___________________________OFF
Wait 10 seconds.
2 - R ENG BLEED SWITCH __________________________ AUTO
------------------- END -------------------		  
 
R FADEC N1 CTL
REV: 1		 NOTE: If any TAT HT 1 (2) (3) FAIL EICAS messages is posted, refer to the recommended actions for those messages first, reset and proceed with step 1 below.
1 - R EPR / N1 switch __________________________RESET
------------------- END -------------------		  
 
RESET OF THE INTERIOR LIGHTING SYSTEM DIRECTOR (ILSD)
REV: 1		 NOTE: Reset procedures for the INTERIOR LIGHTING DIRECTOR (ILSD) through the CES touchscreen. Reset of the ILSD
 
R PACK FAULT
REV: 2		 NOTE: It is NOT unusual the see this message being displayed if the PMAT is ON and CAIMS is active (AW700-21-0160). Closing CAIMS will clear the R PACK FAULT nuisance message.
NOTE: It is NOT unusual to see this message being displayed while on APU bleed in hot / high elevations. If this is the case, switching to engine bleed will eventually clear the message.
1 - TRIM AIR ________________________________ OFF THEN ON
2 - R PACK _________________________________ OFF THEN ON
If message doe not clear:
3 - TRIM AIR ______________________________________ OFF
4 - R PACK _______________________________________ OFF
On the EMS CDU:
5 - SYSTEM/AIR COND-PRESS/L (R) PACK CTLR CH A ___ RESET
6 - SYSTEM/AIR COND-PRESS/L (R) PACK CTLR CH B ___ RESET
7 - TRIM AIR ______________________________________ ON
8 - R PACK _______________________________________ ON
------------------- END -------------------		 AW700-21-0160
 
R REVERSER FAIL
REV: 1		 NOTE: L / R REVERSER FAIL CAS message has been seen when the pilot 'walks' the throttle towards reverse.
Actions:
Make sure the thrust reverser is selected and in the detente (stops) within a second or two. Try to restart engines if unable to clear CAS.		  
 
RAT GEN FAIL
with
ELEC SYS FAIL (nuisance)
REV: 1		 AW SYNOPSIS: It recommended to perform RAT TEST twice, via the EMS CDU, if the 'RAT GEN FAIL' and 'ELEC SYS FAIL' are posted after landing. The first RAT TEST clears the 'ELEC SYS FAIL' and the second RAT TEST clears the 'RAT GEN FAIL'.
Actions:
On the EMS CDU:
1 - TEST/RAT TEST _______________________________ SELECT
------------------- END -------------------		 AW700-24-0153
 
RUD LIMITER FAIL
RUD AUTHORITY LOW
or
RUD AUTHORITY HIGH
or
RUD AUTHORITY SAFE
REV: 3		 NOTE: Only 1 hydraulic pump operation is available during APU generator ONLY operations. External AC cart or engines running is required in order to perform the following task.
NOTE: Confirm the RUDDER trim switch is set to the middle position and verify that the rudder surface is centered (rudder pointer on the EICAS FLIGHT CONTROLS synoptic page).
On HYDRAULIC Control Panel
1 - Hydraulic systems 1 -2 -3 ______________PRESSURIZED
On the EMS CDU:
2 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA _______PULLED
SYSTEM/FLT CONTROLS/FLT CTL 1 CHB __________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 2 CHA __________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 2 CHB __________PULLED
NOTE: Wait 30 seconds. Reset all circuit breakers within 10 seconds.
3 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA ________RESET
SYSTEM/FLT CONTROLS/FLT CTL 1 CHB ___________RESET
SYSTEM/FLT CONTROLS/FLT CTL 2 CHA ___________RESET
SYSTEM/FLT CONTROLS/FLT CTL 2 CHB ___________RESET
NOTE: SPLRS STAB IN TEST will be posted on the EICAS. Do not touch any flight controls during the test. A minimum of 3 minutes without any flight controls switches and flight controls surfaces inputs should be observed.
After the 3 minutes time delay
4 - SPLRS STAB IN TEST EICAS message ________CLEARED		  
 
RUD LIMITER FAULT
REV: 3		 NOTE: Only 1 hydraulic pump operation is available during APU generator ONLY operations. External AC cart or engines running is required in order to perform the following task.
NOTE: Confirm the RUDDER trim switch is set to the middle position and verify that the rudder surface is centered (rudder pointer on the EICAS FLIGHT CONTROLS synoptic page).
On HYDRAULIC Control Panel:
On HYDRAULIC Control Panel
1 - Hydraulic systems 1 -2 -3 ______________PRESSURIZED
On the EMS CDU:
2 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA _______PULLED
SYSTEM/FLT CONTROLS/FLT CTL 1 CHB __________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 2 CHA __________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 2 CHB __________PULLED
NOTE: Wait 30 seconds. Reset all circuit breakers within 10 seconds.
3 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA ________RESET
SYSTEM/FLT CONTROLS/FLT CTL 1 CHB ___________RESET
SYSTEM/FLT CONTROLS/FLT CTL 2 CHA ___________RESET
SYSTEM/FLT CONTROLS/FLT CTL 2 CHB ___________RESET
NOTE: SPLRS STAB IN TEST will be posted on the EICAS. Do not touch any flight controls during the test. A minimum of 3 minutes without any flight controls switches and flight controls surfaces inputs should be observed.
After the 3 minutes time delay
4 - SPLRS STAB IN TEST EICAS message __________CLEARED
------------------- END -------------------		  

03/09/22

S

CAS Message / Issue Recommended Actions Reference / Link
SG REVERSION
REV: 2		 NOTE: During an ILS approach, if an SG issue occurs before the localizer beam captures, couple the FD to the non-reverted PFD immediately with SG reversion. If the ILS approach has already been initiated using the reverted PFD, then after coupling to the non-reverted PFD and re-arming the APR mode (LOC & GS), the FD will capture and track the localizer with the next subsequent pass. AW700-22-0209
 
SHAKER 1 FAIL
REV: 1		 On the EMS CDU:
SYSTEM/FLT CONTROLS/SPC CH A _______________RESET
------------------- END -------------------		  
 
SHAKER 2 FAIL
REV: 1		 On the EMS CDU:
SYSTEM/FLT CONTROLS/SPC CH B _______________RESET
------------------- END -------------------		  
 
SLAT FAIL
SLAT FAULT
FLAP FAIL
FLAP FAULT
SLAT- FLAP BIT
REV: 1		 1 - SLAT FLAP CONTROL LEVER___SELECT ANOTHER POSITION
On the EMS CDU:
2 - CNTL/SLAT-FLAP RESET _____________________SELECTED
If the message does not clear, there could be a latched fault in the Slat/Flap system.
NOTE: Latched faults could only be cleared through the PMAT. Further investigation is required by maintenance.
------------------- END -------------------		  
 
SLAT HALFSPD
FLAP HALFSPD
SLAT - FLAP HALFSPD
REV: 3

The SLAT−FLAP HALFSPD or FLAP HALFSPD or SLAT HALFSPD cyan message may be posted on Ground.

On the EMS CDU:
1. Circuit Breakers set as follows:

  • SYSTEM/FLT CONTROLS/SLAT/FLAP CTLR 1___________OUT
  • SYSTEM/FLT CONTROLS/SLAT/FLAP CTLR 2___________OUT

Wait 30 seconds.

2. Circuit Breakers reset as follows:

  • SYSTEM/FLT CONTROLS/SLAT/FLAP CTLR 1___________IN
  • SYSTEM/FLT CONTROLS/SLAT/FLAP CTLR 2___________IN
Wait one minute.

3. IF the SLAT−FLAP HALFSPD or FLAP HALFSPD or SLAT HALFSPD message is no longer shown:

a. Perform one cycle up and down of the Slats and Flap.
b. SLAT / FLAP __________________________________ As required:

4. IF the SLAT−FLAP HALFSPD message is still posted, REPORT TO MAINTENANCE.

The Slat Flap Control System (SFCS) may occasionally post sporadic SLAT−FLAP HALFSPD or FLAP HALFSPD or SLAT HALFSPD messages during the aircraft power−up sequence or while on the ground:

No corrective action required.

------------------- END -------------------

  
 
SPLRS/STAB BIT
REV: 2		 NOTE: Only 1 hydraulic pump operation is available during APU generator ONLY operations. External AC cart or engines running is required in order to perform the following task.
On HYDRAULIC Control Panel:
1 - Hydraulic systems 1 -2 -3 ______________PRESSURIZED
On the EMS CDU:
2 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA ________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 1 CHB ___________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 2 CHA ___________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 2 CHB ___________PULLED
NOTE: Wait 30 seconds. Reset all circuit breakers within 10 seconds.
3 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA _________RESET
SYSTEM/FLT CONTROLS/FLT CTL 1 CHB ____________RESET
SYSTEM/FLT CONTROLS/FLT CTL 2 CHA ____________RESET
SYSTEM/FLT CONTROLS/FLT CTL 2 CHB ____________RESET
NOTE: SPLRS STAB IN TEST will be posted on the EICAS. Do not touch any flight controls during the test. A minimum of 3 minutes without any flight controls switches and flight controls surfaces inputs should be observed.
After the 3 minutes time delay
4 - SPLRS STAB IN TEST EICAS message _________CLEARED
If SPLRS / STAB BIT EICAS message still posted, carry out steps 1 to 4 again. For the MDU nuisance, it can take up to 5 resets to clear the fault after what, maintenance investigation is required.
NOTE: SPLRS / STAB BIT EICAS message can be dispatched as per MMEL.		 AW700-27-0218
 
SPRLS/STAB in test
REV: 2		 NOTE: Do not move any flight deck controls (including the Slats/Flaps and Thrust levers) until the SPLRS / STAB IN TEST message clears. Do not confuse with the SPLRS / STAB BIT CAS message that requires Advisory Wire actions.  
 
STAB CH 1 FAIL (posted after power-up)
REV: 2		 NOTE: Only 1 hydraulic pump operation is available during APU generator ONLY operations. External AC cart or engines running is required in order to perform the following task.
On HYDRAULIC Control Panel:
1 - Hydraulic systems 1 -2 -3 _______________PRESSURIZED
2 - STAB TRIM, CH1 and CH2 _____________________RESET
On the EMS CDU:
3 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA ________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 1 CHB ___________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 2 CHA ___________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 2 CHB ___________PULLED
NOTE: Wait 30 seconds. Reset all circuit breakers within 10 seconds.
4 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA _________RESET
SYSTEM/FLT CONTROLS/FLT CTL 1 CHB ____________RESET
SYSTEM/FLT CONTROLS/FLT CTL 2 CHA ____________RESET
SYSTEM/FLT CONTROLS/FLT CTL 2 CHB ____________RESET
NOTE: SPLRS STAB IN TEST will be posted on the EICAS. Do not touch any flight controls during the test. A minimum of 3 minutes without any flight controls switches and flight controls surfaces inputs should be observed.
After the 3 minutes time delay
5 - SPLRS STAB IN TEST EICAS message _________CLEARED
If STAB CH 1 (2) FAIL message still posted, carry out steps 1 to 4 again. For the MDU nuisance, it can take up to 5 resets to clear the fault after what, maintenance investigation is required.
------------------- END -------------------		 AW700-27-0218
 
STAB CH 2 FAIL (posted after power-up)
REV: 2		 NOTE: Only 1 hydraulic pump operation is available during APU generator ONLY operations. External AC cart or engines running is required in order to perform the following task.
On HYDRAULIC Control Panel:
1 - Hydraulic systems 1 -2 -3 _______________PRESSURIZED
2 - STAB TRIM, CH1 and CH2 _____________________RESET
On the EMS CDU:
3 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA ________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 1 CHB ___________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 2 CHA ___________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 2 CHB ___________PULLED
NOTE: Wait 30 seconds. Reset all circuit breakers within 10 seconds.
4 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA _________RESET
SYSTEM/FLT CONTROLS/FLT CTL 1 CHB ____________RESET
SYSTEM/FLT CONTROLS/FLT CTL 2 CHA ____________RESET
SYSTEM/FLT CONTROLS/FLT CTL 2 CHB ____________RESET
NOTE: SPLRS STAB IN TEST will be posted on the EICAS. Do not touch any flight controls during the test. A minimum of 3 minutes without any flight controls switches and flight controls surfaces inputs should be observed.
After the 3 minutes time delay
5 - SPLRS STAB IN TEST EICAS message _________CLEARED
If STAB CH 1 (2) FAIL message still posted, carry out steps 1 to 4 again. For the MDU nuisance, it can take up to 5 resets to clear the fault after what, maintenance investigation is required.
------------------- END -------------------		 AW700-27-0218
 
STAB TRIM
REV: 4		 NOTE: Only 1 hydraulic pump operation is available during APU generator ONLY operations. External AC cart or engines running is required in order to perform the following task.
On HYDRAULIC Control Panel
1 - Hydraulic systems 1 -2 -3 ______________PRESSURIZED
2 - STAB TRIM, CH1 and CH2 _____________________RESET
On the EMS CDU:
3 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA _______PULLED
SYSTEM/FLT CONTROLS/FLT CTL 1 CHB __________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 2 CHA __________PULLED
SYSTEM/FLT CONTROLS/FLT CTL 2 CHB __________PULLED
NOTE: Wait 30 seconds. Reset all circuit breakers within 10 seconds.
4 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA ________RESET
SYSTEM/FLT CONTROLS/FLT CTL 1 CHB ___________RESET
SYSTEM/FLT CONTROLS/FLT CTL 2 CHA ___________RESET
SYSTEM/FLT CONTROLS/FLT CTL 2 CHB ___________RESET
NOTE: SPLRS STAB IN TEST will be posted on the EICAS. Do not touch any flight controls during the test. A minimum of 3 minutes without any flight controls switches and flight controls surfaces inputs should be observed.
After the 3 minutes time delay
5 - SPLRS STAB IN TEST EICAS message ________CLEARED
------------------- END -------------------		  
 
STALL PROTECT FAIL (Nuisance CAS Message)
REV: 1		 NOTE: Associated with the SPC GH582-3001-13 (XRS) and GH582-3001-15 (G5000). The STALL PROTECT FAIL could be intermittently posted at the end of the SPC power-up or at the end of the Stall warning System Pilot Activated Test (PAT) performed on the EMS CDU.
If the message appeared right after the SPC power-up,
On the EMS CDU:
1 - SYSTEM/FLT CONTROLS/SPC CH A and SPC CH B____RESET
If the message appeared right after the Pilot Activated Test (PAT),
On the EMS CDU:
1 - TEST/ STALL TEST ___________________________PERFORM
------------------- END -------------------		 AW700-27-0275
 
STALL WARN ADVANCE
REV: 2		 NOTES: If associated with a SLAT FAULT or FLAP FAULT, clear the Slat/Flap issue before attempting to reset the STALL WARN ADVANCE CAS messages
On the EMS CDU:
1 - CNTL/STALL WARN ADVANCE ____________REVERT to NORM
------------------- END -------------------		  
 
SYSTEM LIMITATIONS (TEMPERATURE)
REV: 2		 This document provides a list of technical publications that provide information pertinent to specific operating temperatures. SYSTEMS LIMITATIONS and CONFIGURATIONS FOR COLD/HOT WEATHER OPERATIONS

07/30/20

T

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
TOILET ( Monogram / Magair )
REV: 1		 FAILURE: With the Monogram / Magair toilet, if you have a forward or aft toilet failure in flight, you can reset the controller and re-initiate the flush sequence simply by pushing and holding the flush switch for ONE second and then release. The flush button should turn back to green and you should be able to re-initiate a 'FLUSH'.
RECOMMENDATION: After servicing the Lav, add a pre-charge of 2 gallons to aid in keeping waste from sticking to Sensors, probes and the bottom of the tank.		  
 
TOWING ISSUES
REV: 2

NOTE: Make sure that the load on the nose landing gear (NLG) is not less than 1,900 lbs (862 kg), or that a minimum of 5,000 lb (2,268 kg) of fuel is in the tanks, and that the C of G of the aircraft is within the C of G envelope limits. With a fuel load of at least 5,000 lbs it is likely that the minimum requirement of 1,900 lbs on the nosewheel (2,000 lbs for LEKTRO Tug Towbarless Towing) will be met.

If necessary, make a fuel adjustment to get correct load. If you do not do this, you can disconnect or damage the steering mechanism and/or cause damage to the aircraft.

 Ground Operations Checklist
See page 33
 
TOWING VEHICLES
REV: 1		 Aircraft Towing Vehicle - 75,000 lbs Maximum Capacity - LEKTRO AP8750B-AL
Aircraft Towing Vehicle - 120,000 lbs Maximum Capacity - LEKTRO AP8850SDA
Aircraft Towing Vehicle - 100,000 lbs Maximum Capacity - JETporter JP-2
Aircraft Towing Vehicle - 100,000 lbs Maximum Capacity - JETporter JP-2S		  

V

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
VSPEEDS
REV: 2
 PROBLEM: V Speeds are not posted prior to takeoff.
ACTION: The VSPEEDS will only display on the PFD if ALL aircraft configuration conditions have been met and accepted. Review all FMS aircraft configuration entries and press the ACCEPT prompt again. If the conditions have not been accepted, the ACCEPT prompt will be displayed in inverse video.		  

W

CAS MESSAGE / ISSUE RECOMMENDED ACTIONS REFERENCE / LINK
WATER PURGING INSTRUCTIONS
REV: 2
 Water tank and line purge procedures, and winterizing cautions. WATER PURGING INSTRUCTIONS
 
WEATHER RADAR (excessive ground clutter)
REV: 1
 NOTES: The final fix to this issue is available through a vendor Service Bulletin upgrade of the Weather Radar RCVR/XMTR Antenna unit (RTA).
On the Weather Radar Control Panel:
1 - RADAR switch ________________SBY for 10 seconds then WX		 AW700-34-0166
 
WEATHER RADAR (FSBY over-ride)
REV: 2
 NOTE: When the radar is in FSBY (Forced Standby) and the mode controller is in STBY (Standby) mode, you can no longer exit FSBY and go to STBY mode by pressing the STAB button 4 times. Perform the following procedure to over-ride the FSBY mode.
On the Weather Radar Control Panel:
1 - RADAR Switch ___________________WX, RCT, GMAP or FP
2 - STAB Button ___________________________Press 4 times		 AW700T-0116
 
WINDSHIELD CLEANING
REV: 1
 Windshield cleaning procedures using various cleaning solutions. AMM12-21-00-110-807
Registered and/or unregistered trademarks of Bombardier Inc. or its subsidiaries. © 2015 Bombardier Inc. All rights reserved.