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Bell 429 > EP's // CAS Messages > Flashcards

EP's // CAS Messages Flashcards

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1
Q

Door

A

Any door ajar with Nr greater than 75% - advisory message will indicate which door

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2
Q

Avionics Fan

A

Avionics cooling fan inop

applicable maint action required before next flight

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3
Q

Cabin Heat Hot

A

Cabin heater duct over-temp condition

CABIN HEAT switch - OFF

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4
Q

Instr Fan

A

Instrument panel area cooling fan inop.

1) If OAT is greater than 116f land as soon as practical.
2) Applicable maint action required.

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5
Q

ENG 1 INTAKE
ENG 2 INTAKE

A

Respective Engine intake filter air flow restricted.

ENG INTAKE BYPASS switch (affected engine) - Depress (open) if MGT power margin required.

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6
Q

ENG 1 BYPASS
ENG 2 BYPASS

A

Respective engine intake filer bypass door is open or system not powered.

ENG INTAKE BYPASS switch (affected engine) - Verify selection.

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7
Q

DUAL GEN

A

Generator 1 and 2 offline.
NOTE: with generators OFF and BUS INTCON and CTR-DU EMERG PWR switches in NORM, a fully charged 25 amp-hour battery provides approx. 37 minutes of power for basic helicopter emergency bus operation.

1) Both GEN switches - OFF, RESET, then ON.
If neither generator restored: Both GEN switches: OFF
3) CTR-DU EMERG PWR switch: OVRD ON, if desired, to maintain center DU or to restore center DU.
NOTE: With a dual gen failure, battery automatically powers both emergency buses. If necessary, BUS INTCON switch may be selected to OVRD ON to restore power to essential buses; however, battery power duration will be shortened. N-ESS BUS switch may then be selected to OVRD ON to restore power to non-essential bus.
4) BUS INTCON switch - OVRD ON (as required)
5)N-ESS BUS switch - OVRD ON (as required)
6)Land as soon as practical

note: center DU will extinguish if selection of CTR-DU EMERG PWR to OVR ON is not carried out with 30 seconds of both gens being offline.

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8
Q

DUAL GEN

A

Generator 1 and 2 indicate 0 load. Loss of power to essential and non-essential busses.

1) Airspeed - 120kts or less

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9
Q

BATT RELAY

A

abnormal status of battery relay (contacts either closed when should be open, or open when should be closed)

1)BATT RELAY switch - RESET then NORM.
2) If desired, verify system status on ELECTRICAL SCHEMATIC page of EICAS-SYS

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10
Q

ELECTRIC TREND

A

Voltage or current approaching a limit.
1)EICAS display - select full EICAS presentation
2)EICAS display - monitor system status in relation to limits.

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11
Q

INTCON RELAY

A

Abnormal status of interconnect relay. (contacts either closed when should be open, or open when should be closed)
1)BUS INTCON switch - Verify position. Select OVRD OFF if both generators or online.
2)if message remains, verify system status on ELECTRICAL SCHEMATIC page of EICAS-SYS.

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12
Q

BATT PWR OFF

A

Battery switch is OFF, or RCCB, which provides battery power to emergency busses is inoperative.
1)BATT switch - Verify position
2)If desired, verify system status on ELECTRICAL SCHEMATIC page of EICAS-SYS.

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13
Q

GEN 1
GEN 2

A

Respective generator is offline

1)GEN switch (affected generator) - OFF, RESET, then ON.
NOTE: if GEN message is in conjunction with associated ENG START advisory message, select BUS INTCON switch - OVRD OFF
If affected generator is not restored:
2)GEN switch (affected gen) - OFF
3) N-ESS BUS switch - OVRD ON, if desired.
4) Amps (A) - maintain within limits
5) land as soon as practical

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14
Q

EMERG BUS 1
EMERG BUS 2

A

Respective emergency bus is offline.
Loss of electrical power detected on emergency bus by ADIU
1)Verify system status on ELECTRICAL SCHEMATIC page of EICAS-SYS
2)Land as soon as practical

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15
Q

ESS BUS 1
ESS BUS 2

A

Respective essential bus is offline with on-side generator operating or other essential bus has power with INTCON relay closed.
No power detected on respective essential BUS by ADIU
1) Verify electrical power control switches
2) verify system status on ELECTRICAL SCHEMATIC page of EICAS-SYS
3)Land as soon as practical

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16
Q

N ESS BUS

A

Non essential bus is offline with both generators online.
No power detected on non-essential bus by ADIU.
1) Verify electrical power control switches
2)verify system status on ELECTRICAL SCHEMATIC page of EICAS-SYS

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17
Q

EXT PWR ON

A

electrical power applied to external power plug

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18
Q

ENG 1 START
ENG 2 START

A

respective engine starter engaged.

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19
Q

N ESS OVRD ON

A

Power is detected on non-essential bus when generator(s) inoperative.

N-ESS BUS switch in OVRD ON position.

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20
Q

INTCON OVRD ON

A

Battery relay and essential bus interconnect relay closed with both generators inoperative.

BUS INTCON switch in OVRD ON or external power connected.

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21
Q

GEN 1 DEGRADED
GEN 2 DEGRADED

A

Respective generator regulator control unit output voltage less than 25 volts or GEN reset signal stuck or start signal stuck
(inhibited during start sequence)
-Applicable maintenance required

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22
Q

FUEL 1 PRESS
FUEL 2 PRESS

A

Respective engine fuel px low
1)Altitude - reduce, if practical
2)prepare for possible engine failure
3)land as soon as practical

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23
Q

FUEL 1 LOW

A

Fuel qt below appx 110lbs in mid 1 tank.
Note: during refueling if fuel 1 low message doesn’t extinguish with greater than 120 lbs indicated in mid 1 tank, cycle helicopter electrical power or cycle FWD XFER switch to OPEN and back to NORM

1)EICAS - Select SYS softkey
2)FUEL/WT & BAL - Select
3) Fuel quantity - verify mid 1 tank.
4) land as soon as practical

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24
Q

FUEL 2 LOW

A

Fuel qt below appx 90 lbs in mid 2 tank.
1)EICAS - Select SYS softkey
2)FUEL/WT & BAL - Select
3) Fuel quantity - verify mid 2 tank.
4) land as soon as practical

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25
FUEL 1 VALVE FUEL 2 VALVE
Respective fuel valve is in transition, or not in commanded position, or not powered. If condition persists, land as soon as practical.
26
FUEL BAL PUMP
Fuel balance pump not operating correctly. 1)BAL PUMP switch - OFF 2)Fuel quantity display - monitor
27
FUEL IMBALANCE
Fuel distribution between systems 1 and 2 indicates fuel imbalance condition of appx 100lbs. 1) FWD XFER switch - Verify position 2)BAL PUMP switch - Verify position 3) Fuel BAL, DU softkey - verify operational.
28
FUEL INDICATION
Fuel quantity indications/low-level sensors do not correlate in relation to forward fuel transfer pump and fuel interconnect valve settings Fuel quantity display - monitor
29
FUEL INTCON
Fuel interconnect valve in transition or not in commanded position or not powered. 1)BAL PUMP switch - Verify position 2)Fuel quantity display - Monitor.
30
FWD XFR PUMP
Forward (system 1) fuel transfer pump not pumping while fuel remains in forward tank or pumping while no fuel remains in forward tank. 1)FWD XFER switch - verify position 2)Fuel qt display - monitor unusable fuel qt 3)FWD XFER switch - NORM or OFF, if system 1 indicates less than 285lbs 4) FWD XFER switch - OPEN, as required; majority of yellow hatched marked fuel will be recovered as usable up to 150 lbs will remain hatched as unusable depending on helicopter attitude.
31
FUEL XFR VALVE
Forward (system 1) fuel transfer valve in transition or not in the commanded position or not powered. 1)FWD XFER switch - verify position 2)Fuel qt display - monitor unusable fuel qt.
32
FUEL LL1 MAINT FUEL LL2 MAINT
Fault indicated in fuel low level sensor or associated wiring Applicable maintenance required.
33
FUEL 1 CLOSED FUEL 2 CLOSED
Respective engine airframe fuel shutoff valve closed.
34
REFUEL
appears above fuel indication section of systems monitor area when FWD XFER and BAL PUMP valves are in REFUEL position.
35
ECU 1 FAIL ECU 2 FAIL
Respective ECU - critical malfunction (failure causes manual mode to automatically engage) 1) FLY STOP REL (affected engine) - disengage 2)Throttle (affected engine) and collective - coordinate and adjust as necessary to maintain PSI needle of affected engine slightly below PSI needle of normal engine. 3)Land as soon as practical
36
ENG 1 OIL HOT ENG 2 OIL HOT
Respective Engine oil temp high 1) Power - reduce 2) Engine oil px - check 3) affected engine - if pilot deems necessary, shut down when practical 4) Land as soon as practical
37
ENG 1 OIL PRESS ENG 2 OIL PRESS
Respective engine oil pressure low. 1) power - reduce 2) affected oil px display - check 3)affected engine - if pilot deems necessary, shut down when practical 4) land as soon as practical
38
ENG 1 OUT ENG 2 OUT
Respective engine - Ng less than 50% or ECU senses flameout. 1)Verify engine condition 2)Single engine failure procedure.
39
FIRE
Respective engine compartment fire sensor detect high temperature. 1) Emergency descent - initiated if possible. 2)Prepare for OEI operation -Collective - adjust to control Nr and desired power -Airspeed - below OEI Vne 3)Throttle (affected engine) - IDLE 4)FIRE switch (affected engine) - ARM and confirm ENG OUT. Note: complete engine shutdown may take up to 50 seconds. 5)AGENT REL switch - select MAIN. 6)N - ESS BUS switch - OVRD ON, as required. 8) Amps (a) maintain within limits. 9)Land as soon as possible
40
FUEL 1 PX FUEL 2 PX
Respective engine fuel px low. 1)Altitude - reduce if practical 2) prepare for possible engine failure 3)land as soon as practical
41
LIMIT
Primary power parameter at or above the max limit (EICAS PSI needle in the red range) Power/Maneuver - adjust as required.
42
LMT OVRD
ECU 30 sec limiter is disabled. OEI LMT switch - as required.
43
OVRD USED
30 second OEI power limit has been exceeded. 1)Land as soon as possible 2)applicable maintenance action required prior to next flight
44
RPM (without audio)
Nr above 107% 1)Collective - Increase 2) Maneuver - Reduce severity
45
ENG 1 CD INOP ENG 2 CD INOP
Respective chip detector inop Land as soon as practical
46
ENG 1 CHIP ENG 2 CHIP
Ferrous particles detected in respective engine oil Note: no automatic burn is performed for engine detectors 1)power - reduce 2) engine - if pilot deems necessary, shut down engine when practical 3)land as soon as practical
47
ENG 1 EXCEED ENG 2 EXCEED
Respective engine has recorder an exceedance. Applicable maintenance before next flight
48
ENG 1 MANUAL ENG 2 MANUAL
Respective ECU in manual mode operation. AUTO/MAN switch - verify selection.
49
FIRE DET 1 INOP FIRE DET 2 INOP
Respective Fire Detection system failed. Land as soon as practical
50
FUEL 1 COLD FUEL 2 COLD *D2 ENGINES ONLY
Fuel temp less than 39f at affected engine fuel pump. Land as soon as practical
51
FUEL 1 HOT FUEL 2 HOT *D2 ENGINES ONLY
Fuel temp greater than 176f at affected engine pump 1)Power - reduce, if possible 2)Altitude - reduce, if possible 3) Land as soon as practical
52
FUEL 1 FILTER FUEL 2 FILTER
Respective engine fuel filter is partially blocked. Land as soon as practical
53
NG OAT LIMIT
Engine(s) NG limited due to OAT Power/Altitude - reduce.
54
1 OEI TIME LOW 2 OEI TIME LOW
Insufficient time remaining in either 2 minute or 3 second range. Applicable maint required before next flight.
55
1 OEI TIME USED 2 OEI TIME USED
Respective engine has recorded use of 2 minute or 30 second OEI power. Applicable maint required before next flight.
56
OEI TRNG
OEI training has been selected. Confirm selected.
57
OIL TREND
Engine or transmission oil px or temp approaching limit. 1)EICAS Display - select full EICAS presentation. 2)EICAS display - monitor system status in relation to limits.
58
RPM (with low RPM audio)
Nr below 95% 1)Collective - reduce 2)Throttles - FLY
59
RPM (without audio)
Nr above 107% 1) Collective - Increase 2) Maneuver - reduce severity
60
XMSN OIL HOT
Transmission oil temp above 110c 1) Power - reduce. 2)XMSN T display - verify fault 3)Land as soon as possible
61
XMSN OIL PRESS
Transmission Oil PX below 25 PSI 1) Power - Reduce 2) XMSN P Display - verify fault 3) Land as soon as possible
62
ROTOR BRAKE
Rotor brake pad(s) not retracted. 1) Rotor Brake - OFF 2)Land as soon as possible
63
IDLE UNDERSPD
Engine idle speed below 49% (tail rotor driveshaft speed in avoid speed range) 1)Throttle - increase to have Nr above lowest red radial on Nr display OR Engine switch - OFF
64
RPM AUTO
ADIU unable to control auto RPM selection. Verify Nr reference on EICAS
65
RTR OVERSPD
Rotor (Nr) overspeed (107%) event has occurred Will be latched if transient allowance exceeded. 1) Power/Maneuver - adjust as required. 2) MASTER CAUTION - depress to reset a latched message. Message will re-illuminate on shutdown if exceedance logged.
66
XMSN OVERTRQ
Transmission over torque event has occurred. Will be latched if transient allowance exceeded. 1) Power/Maneuver - adjust as required. 2) MASTER CAUTION - depress to reset a latched message. Message will re-illuminate on shutdown if exceedance logged.
67
L XMSN CHIP R XMSN CHIP MAST CHIP T/R CHIP
Ferrous particles detected in transmission oil. An automatic burn will be attempted. If debris was successfully burned indication will clear when MC reset pressed or after 3 seconds. If indication persists then actual chips have been detected. 1) Power - reduce. 2)Land as soon as possible
68
L XMSN CD INOP R XMSN CD INOP MAST CD INOP T/R CD INOP
Respective chip detector is inoperative. Land as soon as practical.
69
HYD TREND
Hydraulic pressure or temp approaching limit. 1)EICAS Display - select full EICAS presentation 2)EICAS display - monitor system status in relation to limits.
70
HYD 1 HOT HYD 2 HOT
Respective hydraulic oil temp above 120c 1) HYD P & T - Check 2) AIR COND - switch - off 3) If hovering, land if possible or transition to forward flight as soon as possible. 4) If caution remains illuminated, land as soon as practical. 5) If hydraulic temp continues to rise - HYD switch (affected system - OFF 6) land as soon as possible
71
HYD 1 PRESS HYD 2 PRESS
Respective hyd system px either below 1250 psi or above 1800 psi 1) HYD switch - verify position 2) HYD switch (affected system) - off 3) Land as soon as possible.
72
PEDL STOP ENGD
Pedal stop restrictor filed in the engaged position. 1) EMERGENCY PEDAL STOP RELEASE - pull 2) Pilot shall maintain feet on pedals.
73
PEDL STOP INOP
Pedal stop system is inoperative and/or pedal stop will not engage. (Due to either failure of the stop to engage, failure of the FCCs, or loss of air data.) Additional safety afforded by pedal stop system is not available. Pilot shall maintain feet on pedals.
74
HYD OFF OVRD
ADUI interrupt of hyd OFF selection due to fault on other hyd system. applicable maintenance required.
75
CAS MISCOMP
Cautionary advisory system data miscompare between primary and redundant source. EICAS display - monitor; CAS data may be misleading.
76
CHECK DU CONFIG
Configuration settings, parameter setup settings, or calibration settings do not match between DUs. applicable maintenance before next flight.
77
L DU C DU R DU
Respective display unit inoperative or not communicating with other display units. Select composite DU mode, as required.
78
L DU FANS R DU FANS C DU FANS
Cooling fans of respective display unit inop. 1) Display Unit - reduce brightness to reduce temp of DU. 2) Applicable maintenance before next flight.
79
EICAS MISCOMP
Miscompare of principal engine power indication(s) between primary and redundant source. Specific parameter group indicated with ALTN on EICAS display. 1) indications - compare with other data (cross engine and/or alternate source data) 2)land as soon as practical
80
ADIU CH A ADIU CH B
Respective aircraft data interface unit channel inop. applicable maintenance before next flight.
81
DU FAN MAINT
One or more display unit fans inop. applicable maint before next flight
82
DATA BUS
Integrated avionics data bus latent fault detected. applicable maint before next flight.
83
L FD & AP1 DEGRADED R FD & AP2 DEGRADED
Single magnetometer failure 1)HDG softkey (affected side) - Select valid heading source 2) FD - as required.
84
L FD & R FD AP 1 DEGRADED & AP 2 DEGRADED
Dual magnetometer failure. 1)utilize standby compass for heading reference.
85
AP 1 AP 2
Respective autopilot offline. Decoupling of respective FD, if coupled. 1) Flight controls - monitor/guard 2)AP switch (affected autopilot) - OFF, the ON. If message remains affected AP switch - OFF 3)AFCS - Monitor performance; guard flight controls. 4) Recouple FD, as required.
86
AP 1 DEGRADED AP 2 DEGRADED
respective autopilot fault detected and/or AP performance is degraded. 1) Flight controls - monitor/guard 2)AP switch (affected autopilot) - OFF, the ON. 3) AFCS - monitor performance, guard flight controls.
87
AP 1 INTCON AP 2 INTCON
respective autopilot FCC not receiving cross communication data from other FCC. 1) Flight controls - Monitor/Guard 2) AP 1 Switch - OFF 3) AFCS - monitor performance; guard flight controls
88
AP 1 PITCH AP 2 PITCH AP 1 ROLL AP 2 ROLL AP 1 YAW AP 2 YAW
respective autopilot pitch, roll, or yaw actuator inop. 1) Flight controls - monitor/guard 2) AFCS - monitor performance; guard flight controls.
89
AP 1 MAINT AP 2 MAINT
Respective autopilot latent fault, loss of redundancy, or condition requiring maintenance. Applicable maintenance required.

Bell 429 (3 decks)

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