A to D
| Recommended Actions | Reference / Link |
|---|---|
| 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. |
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On the EMS CDU: 1 - SYSTEM/AFCS/IAC 1 circuit breaker_________________RESET ------------------- END ------------------- |
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On the EMS CDU: 1 - SYSTEM/AFCS/IAC 2 circuit breaker_________________RESET ------------------- END ------------------- |
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Refer to Ground Operations Checklist for more information on AFT XFER OFF SCHED caution and advisory CAS messages. |
See Non-Normal Procedures section |
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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 provide 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 ------------------- |
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NOTE: Recommended shutdown procedure to minimize the APU BLEED DISABLED on the next APU start. 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 |
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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 off-line 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) |
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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 ------------------- |
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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 AW 700T-0048 for recommendations. 3 - AC ELECTRICAL POWER ______________________APPLY If Fault remains: 4 - AC ELECTRICAL POWER _________________OFF then ON ------------------- END ------------------- |
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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 ------------------- |
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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 ------------------- |
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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) |
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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. |
AFM NON-NORMAL PROCEDURES OR |
E to K
| Recommended Actions | Reference / Link |
|---|---|
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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 ------------------- |
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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 ------------------- |
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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 secs ------------------- END ------------------- |
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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 NOTE: Wait 30 seconds. Reset all circuit breakers within 10 seconds. 3 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA ___________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 ------------------- |
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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 NOTE: Wait 30 seconds. Reset all circuit breakers within 10 seconds. 3 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA ___________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 ------------------- |
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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 refuelling 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" message 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 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 ------------------- |
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NOTE: For a list and an interpretation of fuel CAS messages, refer to Ground Operations Checklist. |
See Non-Normal Procedures section |
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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. |
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Heavy rain has been known to generate an "ICE" CAS advisory message on ground. |
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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 ------------------- |
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L to R
| Recommended Actions | Reference / Link |
|---|---|
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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 ENG BLEED SWITCH ___________________________OFF Wait 10 seconds. 2 - L ENG BLEED SWITCH __________________________ AUTO ------------------- END ------------------- |
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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 ------------------- |
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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 ------------------- |
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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. ------------------- END ------------------- |
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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 ------------------- |
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On the EMS CDU: 1 - SYSTEM/ICE/HBMU 1 and HBMU 2 __________________RESET ------------------- END ------------------- |
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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 NOTE: Wait 30 seconds. Reset all circuit breakers within 10 seconds. 3 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA _____________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 ------------------- |
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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 ------------------- |
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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 ------------------- |
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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 ------------------- |
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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. |
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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 ------------------- |
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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 NOTE: Wait 30 seconds. Reset all circuit breakers within 10 seconds. 3 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA ________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 ------------------- |
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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 NOTE: Wait 30 seconds. Reset all circuit breakers within 10 seconds. 3 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA ________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 ------------------- |
S to W
| Recommended Actions | Reference / Link |
|---|---|
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On the EMS CDU: SYSTEM/FLT CONTROLS/SPC CH A _______________RESET ------------------- END ------------------- |
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On the EMS CDU: SYSTEM/FLT CONTROLS/SPC CH B _______________RESET ------------------- END ------------------- |
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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 ------------------- |
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The SLAT−FLAP HALFSPD or FLAP HALFSPD or SLAT HALFSPD cyan message may be posted on Ground. On the EMS CDU:
Wait 30 seconds. 2. Circuit Breakers reset as follows:
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. 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 ------------------- |
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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 NOTE: Wait 30 seconds. Reset all circuit breakers within 10 seconds. 3 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA _________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 |
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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. |
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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 NOTE: Wait 30 seconds. Reset all circuit breakers within 10 seconds. 4 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA _________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 ------------------- |
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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 NOTE: Wait 30 seconds. Reset all circuit breakers within 10 seconds. 4 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA _________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 ------------------- |
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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 NOTE: Wait 30 seconds. Reset all circuit breakers within 10 seconds. 4 - SYSTEM/FLT CONTROLS/FLT CTL 1 CHA ________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 ------------------- |
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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 ------------------- |
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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 ------------------ |