CH-53E Caution/Advisory Lights

BIM

Loss of main rotor spar integrity or spar pressure indicator malfunctioning. IBIS radiation detector, signal processor, or AC power malfunction.
Can also illuminate due to electromagnetic interference.
Procedure:
*1. Airspeed - 80 KIAS, minimize maneuveri

ICE DETECTED

Ice is building up on helicopter.

COMPASS FAIL

AHRS has malfunctioned.

ROTOR LOCKED

Gust lock is applied.

ROTOR BRAKE PRESS

Rotor brake system is pressurized to at least 10 psi.

CHIP DETECTED

Gearbox or engine metallic chips have been detected.
Check chip locater panel and procedure with specified procedure.

AFCS

Dual computer failure
Procedure:
1. Cycle computer power OFF then ON
If this does not extinguish caution light:
*1. IMC - Land as soon as possible
2. VMC - Land as soon as practical

NO.1 RECT

No. 1 transformer-rectifier has malfunctioned.
Procedure:
1. If either fails - Land as soon as practical
2. Extend landing gear
3. If both fail, or if either fails at night or in IMC - Land as soon as possible

NO.2 RECT

No. 2 transformer-rectifier has malfunctioned.
Procedure:
1. If either fails - Land as soon as practical
2. Extend landing gear
3. If both fail, or if either fails at night or in IMC - Land as soon as possible

NO.1 GEN

No. 1 generator has malfunctioned, or if on the ground and below 91-96% Nr, a momentary underfrequency has been experienced.
Procedure:
1. Affected generator - RESET/OFF, then ON
2. If one or two fail - Land as soon as practical
3. If all generators fail

NO.2 GEN

No. 2 generator has malfunctioned, or if on the ground and below 91-96% Nr, a momentary underfrequency has been experienced.
Procedure:
1. Affected generator - RESET/OFF, then ON
2. If one or two fail - Land as soon as practical
3. If all generators fail

NO.3 GEN

No. 3 generator has malfunctioned, or if on the ground and below 91-96% Nr, a momentary underfrequency has been experienced.
Procedure:
1. Affected generator - RESET/OFF, then ON
2. If one or two fail - Land as soon as practical
3. If all generators fail

IGB OIL PRESS

Intermediate gearbox oil pressure is below 7�1 psi.

NO.2 ENGINE OVERHEAT

An overheat condition exists in the No. 2 engine compartment (575� F)
Procedure:
*1. Collective - Maintain Nr
*2. Airspeed - As required
*3. Pickle - External load as required
*4. Tanks - Jettison as required
*5. Speed control levers - No. 2 engine shutof

2 STG OIL HOT

Second stage hydraulic temperature above 107� C and/or the second stage system heat exchanger blower motor has shut down.
Procedure:
1. Follow PCL
2. If pressure and quantity remain nromal, yet the light remains illuminated - Land as soon as practical

NO.1 ENG FLTR BYPASS

Pressure drop across the No. 1 fuel system airframe fuel filter is over 1.37�0.5 psi, and filter is partially clogged.
Procedure:
For all three fuel filters being bypassed:
*1. Engine instruments - Monitor
*2. Land as soon as possible
For one or two:
1. E

NO.2 ENG FLTR BYPASS

Pressure drop across the No. 2 fuel system airframe fuel filter is over 1.37�0.5 psi, and filter is partially clogged.
Procedure:
For all three fuel filters being bypassed:
*1. Engine instruments - Monitor
*2. Land as soon as possible
For one or two:
1. E

NO.3 ENG FLTR BYPASS

Pressure drop across the No. 3 fuel system airframe fuel filter is over 1.37�0.5 psi, and filter is partially clogged.
Procedure:
For all three fuel filters being bypassed:
*1. Engine instruments - Monitor
*2. Land as soon as possible
For one or two:
1. E

TGB OIL PRESS

Tail gearbox oil pressure is below 7�1 psi.

BLADE PYLON FOLD

Blade/pylon fold system activated and/or gust lock engaged. Helicopter unsafe for flight.

UTILITY OIL HOT

Utility hydraulic tempearture above 107� C and/or the utility system heat exchanger blower motor has shut down.
Procedure:
1. Follow PCL
2. If pressure and quantity remain normal, yet the light remains illuminated - Land as soon as practical

NO.1 ENG FUEL BOOST

No. 1 boost pump output below 8.5�0.5 psi.
Possible indication of Compressor Stall.
Engine-driven fuel pump will supply enough fuel for normal operation.
Procedure:
1. Land as soon as practical.

NO.2 ENG FUEL BOOST

No. 2 boost pump output below 8.5�0.5 psi.
Possible indication of Compressor Stall.
Engine-driven fuel pump will supply enough fuel for normal operation.
Procedure:
1. Land as soon as practical.

NO.3 ENG FUEL BOOST

No. 3 boost pump output below 8.5�0.5 psi.
Possible indication of Compressor Stall.
Engine-driven fuel pump will supply enough fuel for normal operation.
Procedure:
1. Land as soon as practical.

1 STG M/R SERVO BYPASS

A servo has malfunctioned in a manner to cause it to bypass hydraulic pressure or a loss of system pressure.

2 STG M/R SERVO BYPASS

A servo has malfunctioned in a manner to cause it to bypass hydraulic pressure or a loss of system pressure.

UTILITY T/R PRESS

Utility, pressure, downstream of the second stage servo shutoff valve in the utility module, has dropped below 1,500 psi. Inadequate utility pressure to the second stage side of the tail rotor tandem servo.

NO.1 ENG OIL PRESS LOW

Low oil pressure in the No. 1 engine (10�3 psi or below).
Procedure:
1. Reduce power to minimum for immediate requirement
2. Transition to single- or dual-engine procedures as quickly as possible, perform Engine Shutdown in flight.

NO.2 ENG OIL PRESS LOW

Low oil pressure in the No. 2 engine (10�3 psi or below).
Procedure:
1. Reduce power to minimum for immediate requirement
2. Transition to single- or dual-engine procedures as quickly as possible, perform Engine Shutdown in flight.

NO.3 ENG OIL PRESS LOW

Low oil pressure in the No. 3 engine (10�3 psi or below).
Procedure:
1. Reduce power to minimum for immediate requirement
2. Transition to single- or dual-engine procedures as quickly as possible, perform Engine Shutdown in flight.

1 STG T/R SERVO BYPASS

A servo has malfunctioned in a manner to cause it to bypass hydraulic pressure or loss of system pressure.

BLANK CAPSULE

Possible system malfunction.

2 STG T/R SERVO BYPASS

A servo has malfunctioned in a manner to cause it to bypass hydraulic pressure or loss of system pressure.

NO.1 NGB OIL PRESS

No. 1 nose gearbox oil pressure below 14�2 psi.
Indication of an NGB Oil System Failure.

MGB OIL PRESS

Main gearbox oil pressure below 14�2 psi.
Indication of an MGB Oil System Failure.

NO.3 NGB OIL PRESS

No. 3 nose gearbox oil pressure below 14�2 psi.
Indication of an NGB Oil System Failure.

1 STG PRESS M/R T/R

First stage flight control system below 2,000 psi.

2 STG PRESS M/R

Second stage flight control system hydraulic pressure below 2,000 psi.

UTILITY PRESS

Utility hydraulic system pressure below 1,500 psi.

NO.1 NGB OIL HOT

No. 1 nose gearbox oil temperature above 121��5.5�C.
Indication of an NGB Oil System Failure.

MGB OIL HOT

Main gearbox above 121��5.5�C.
Indication of an MGB Oil System Failure.
Spefically associated with this procedure:
*4. Maintain reduced airspeed and low altitude
*5. Land as soon as possible
6. When flying over water, return to the nearest suitable landin

NO.3 NGB OIL HOT

No. 3 nose gearbox oil temperature above 121��5.5�C.
Indication of an NGB Oil System Failure.

1 STG QTY M/R T/R

Hydraulic fluid quantity is at an unsatisfactory low level.
Procedure:
1. First and second stage hydraulic systems fluid quantity low - Land as soon as possible
2. First and utility hydraulic systems fluid low - Land as soon as possible
3. First or second

2 STG QTY M/R

Hydraulic fluid quantity is at an unsatisfactory low level.
Procedure:
1. First and second stage hydraulic systems fluid quantity low - Land as soon as possible
2. First or second stage hydraulic systems fluid low - Land as soon as practical
3. Second sta

UTILITY QTY T/R

Hydraulic fluid quantity is at an unsatisfactory low level.
Procedure:
1. First and utility hydraulic systems fluid low - Land as soon as possible
2. Second stage and utility systems fluid quantity low - Land as soon as practical
3. Utility hydraulic syst

NO.1 ENG OIL PRESS HIGH

High oil pressure in the No. 1 engine (100�3 psi or above).
Procedure:
1. Maintain reduced speed/power until temp is within range
Procedure:
2. Reduce power to minimum for immediate requirement
3. Transition to single- or dual-engine procedures as quickly

NO.2 ENG OIL PRESS HIGH

High oil pressure in the No. 2 engine (100�3 psi or above).
Procedure:
1. Maintain reduced speed/power until temp is within range
Procedure:
2. Reduce power to minimum for immediate requirement
3. Transition to single- or dual-engine procedures as quickly

NO. 3 ENG OIL PRESS HIGH

High oil pressure in the No. 3 engine (100�3 psi or above).
Procedure:
1. Maintain reduced speed/power until temp is within range
Procedure:
2. Reduce power to minimum for immediate requirement
3. Transition to single- or dual-engine procedures as quickly

C/G HOOK INOP

CG hook load system not functioning or not functioning correctly.

ACC GB OIL PRESS

Accessory gearbox oil pressure below 7�1 psi.
Indication of an AGB Oil System Failure.

NO.1 ENG OIL QTY LOW

No. 1 engine oil at or below refill level.
Procedure:
1. Replenish from aux tank.

NO.2 ENG OIL QTY LOW

No. 2 engine oil at or below refill level.
Procedure:
1. Replenish from aux tank.

NO.3 ENG OIL QTY LOW

No. 3 engine oil at or below refill level.
Procedure:
1. Replenish from aux tank.

DIRCM POWER FAIL

Will illuminate anytime there is an absence of 28 VDC to the CIU with either a UDM or MUDM INSTALLED.

ACC GB OIL HOT

Accessory gearbox oil temperature above 145�.
Indication of an AGB Oil System Failure.

NO.1 ENG ANTI-ICE

Duct temperature below 35�C, or electrical failure in system.

TAIL ROTOR HIGH STRESS

The capsule will only illuminate during PRESS TO TEST for the CAUTION/ADVISORY panel. This capsule is disabled and does not receive illumination signals from the aircraft.

NO.3 ENG ANTI-ICE.

Duct temperature below 35�C, or electrical failure in system.

DIRCM FAIL

When there is a fault displayed on the CIU or during normal initialization, for approximately 3-10 seconds about 20 seconds after initialization starts, or while IBIT is running (approximately 25 seconds).

BEARING VIB LIMIT

Vibration level from at least one of the swashplate sensors (SP-1 and/or SP-2) has reached 2.5 Gs, or vibration level from the tail rotor drive shaft disconnect coupling bearing has reached 4 Gs.
Procedure:
1. Aircrew - Alert
2. Land as soon as practical

BEARING TEMP DETECT

Temperature level from at least one of the swashplate sensors (SP-1 and/or SP-2) or the tail rotor drive shaft disconnect coupling bearing (DISC) has reached 275� F.
Procedure:
1. Aircrew - Alert
*2. Land as soon as possible

BEARING TEMP LIMIT

Temperature level from at least one of the swashplate sensors (SP-1 and/or SP-2) or the tail rotor drive shaft disconnect coupling bearing (DISC) has reached 350� F.
Procedure:
1. Aircrew - Alert
*2. Land immediately

MGB AUX LUBE PUMP

Main gearbox auxiliary oil pressure below 14�2 psi.
Indication of an MGB Oil System Failure.
Specific Procedure:
If MGB OIL PRESS is also illuminated
*1. Land immediately

ENGINE OVERTORQUE

Total engine torque exceeds 137%.

EAPS HIGH PRESS LOSS

Dual pressure switch or relay malfunction. Too much drop in system pressure due to filter clogging.

IFF

When operating in MODE 4, system has malfunctioned, or being interrogated with no reply being made.

2 PT FLT UNARMED

LOAD/UNLOAD mode selected for two-point external cargo system.

NO.1 FUEL LOW

About 666�30 lbs of fuel remains in No.1 tank.

NO.2 FUEL LOW

About 333�15 lbs of fuel remains in the No. 2 left or right tanks.

NO.3 FUEL LOW

About 666�30 lbs of fuel remains in No.3 tank.

ENG STARTER ON

Lights when any engine starter circuit is energized.

EXT PWR CONNECTED

External power connected to the helicopter.

RAMP OPEN

Cargo ramp or door is open.

NO.1 IGV ANTI-ICE ON

No. 1 engine air and inlet anti-icing systems are turned on.

NO.2 IGV ANTI-ICE ON

No. 2 engine air and inlet anti-icing systems are turned on.

NO.3 IGV ANTI-ICE ON

No. 3 engine air and inlet anti-icing systems are turned on.

APP ON

APP is operating above 92%.

ISOLATION VALVE OPEN

Isolation valve is open.

PARKING BRAKE ON

Parking brake handle is extended.

EAPS DOOR CLOSED

All three EAPS bypass doors are closed.

ROTOR BRAKE ON

Rotor brake is fully pressurized to 975�25 psi.

ENG START HEAD POS

Main rotor head is positioned for engine start.

AUTO RELEASE ON

Single-point cargo hook master switch is at AUTO to selected automatic release mode.

FWD HOOK OPEN

Two-point hook release latch open or not fully closed.

IMDS

Indicates a level one exceedance has been detected by the system and unsafe operating condition exists.
1. Aircrew - Alert
2. Verify exceedance through secondary indications
3. In the event secondary indications are present, the appropriate Emergency Proc

PURGING

PURGE pushbottun on the 8.5 minute purge taking place. Advisory light goes off when purge automatically terminates or PURGE pushbutton pressure to off.

AFCS DEGRADED

Any AFCS failure, other than dual computer failure, will cause light to flash.

SINGLE HOOK OPEN

Hook release latch open or not fully closed.

GPWS ALERT

Warns of potentially unsafe conditions in respect to ground proximity.

DIRCM ENGAGED

During normal initialization, the DIRCM ENGAGED light is active for approximately 3-10 seconds about 20 seconds after initialization starts and during IBIT, the DIRCM ENGAGED light is active for approximately 25 seconds while the system is running IBIT an

GPWS INOP

Indicates a system failure.

BIM

Loss of main rotor spar integrity or spar pressure indicator malfunctioning. IBIS radiation detector, signal processor, or AC power malfunction.
Can also illuminate due to electromagnetic interference.
Procedure:
*1. Airspeed - 80 KIAS, minimize maneuveri

ICE DETECTED

Ice is building up on helicopter.

COMPASS FAIL

AHRS has malfunctioned.

ROTOR LOCKED

Gust lock is applied.

ROTOR BRAKE PRESS

Rotor brake system is pressurized to at least 10 psi.

CHIP DETECTED

Gearbox or engine metallic chips have been detected.
Check chip locater panel and procedure with specified procedure.

AFCS

Dual computer failure
Procedure:
1. Cycle computer power OFF then ON
If this does not extinguish caution light:
*1. IMC - Land as soon as possible
2. VMC - Land as soon as practical

NO.1 RECT

No. 1 transformer-rectifier has malfunctioned.
Procedure:
1. If either fails - Land as soon as practical
2. Extend landing gear
3. If both fail, or if either fails at night or in IMC - Land as soon as possible

NO.2 RECT

No. 2 transformer-rectifier has malfunctioned.
Procedure:
1. If either fails - Land as soon as practical
2. Extend landing gear
3. If both fail, or if either fails at night or in IMC - Land as soon as possible

NO.1 GEN

No. 1 generator has malfunctioned, or if on the ground and below 91-96% Nr, a momentary underfrequency has been experienced.
Procedure:
1. Affected generator - RESET/OFF, then ON
2. If one or two fail - Land as soon as practical
3. If all generators fail

NO.2 GEN

No. 2 generator has malfunctioned, or if on the ground and below 91-96% Nr, a momentary underfrequency has been experienced.
Procedure:
1. Affected generator - RESET/OFF, then ON
2. If one or two fail - Land as soon as practical
3. If all generators fail

NO.3 GEN

No. 3 generator has malfunctioned, or if on the ground and below 91-96% Nr, a momentary underfrequency has been experienced.
Procedure:
1. Affected generator - RESET/OFF, then ON
2. If one or two fail - Land as soon as practical
3. If all generators fail

IGB OIL PRESS

Intermediate gearbox oil pressure is below 7�1 psi.

NO.2 ENGINE OVERHEAT

An overheat condition exists in the No. 2 engine compartment (575� F)
Procedure:
*1. Collective - Maintain Nr
*2. Airspeed - As required
*3. Pickle - External load as required
*4. Tanks - Jettison as required
*5. Speed control levers - No. 2 engine shutof

2 STG OIL HOT

Second stage hydraulic temperature above 107� C and/or the second stage system heat exchanger blower motor has shut down.
Procedure:
1. Follow PCL
2. If pressure and quantity remain nromal, yet the light remains illuminated - Land as soon as practical

NO.1 ENG FLTR BYPASS

Pressure drop across the No. 1 fuel system airframe fuel filter is over 1.37�0.5 psi, and filter is partially clogged.
Procedure:
For all three fuel filters being bypassed:
*1. Engine instruments - Monitor
*2. Land as soon as possible
For one or two:
1. E

NO.2 ENG FLTR BYPASS

Pressure drop across the No. 2 fuel system airframe fuel filter is over 1.37�0.5 psi, and filter is partially clogged.
Procedure:
For all three fuel filters being bypassed:
*1. Engine instruments - Monitor
*2. Land as soon as possible
For one or two:
1. E

NO.3 ENG FLTR BYPASS

Pressure drop across the No. 3 fuel system airframe fuel filter is over 1.37�0.5 psi, and filter is partially clogged.
Procedure:
For all three fuel filters being bypassed:
*1. Engine instruments - Monitor
*2. Land as soon as possible
For one or two:
1. E

TGB OIL PRESS

Tail gearbox oil pressure is below 7�1 psi.

BLADE PYLON FOLD

Blade/pylon fold system activated and/or gust lock engaged. Helicopter unsafe for flight.

UTILITY OIL HOT

Utility hydraulic tempearture above 107� C and/or the utility system heat exchanger blower motor has shut down.
Procedure:
1. Follow PCL
2. If pressure and quantity remain normal, yet the light remains illuminated - Land as soon as practical

NO.1 ENG FUEL BOOST

No. 1 boost pump output below 8.5�0.5 psi.
Possible indication of Compressor Stall.
Engine-driven fuel pump will supply enough fuel for normal operation.
Procedure:
1. Land as soon as practical.

NO.2 ENG FUEL BOOST

No. 2 boost pump output below 8.5�0.5 psi.
Possible indication of Compressor Stall.
Engine-driven fuel pump will supply enough fuel for normal operation.
Procedure:
1. Land as soon as practical.

NO.3 ENG FUEL BOOST

No. 3 boost pump output below 8.5�0.5 psi.
Possible indication of Compressor Stall.
Engine-driven fuel pump will supply enough fuel for normal operation.
Procedure:
1. Land as soon as practical.

1 STG M/R SERVO BYPASS

A servo has malfunctioned in a manner to cause it to bypass hydraulic pressure or a loss of system pressure.

2 STG M/R SERVO BYPASS

A servo has malfunctioned in a manner to cause it to bypass hydraulic pressure or a loss of system pressure.

UTILITY T/R PRESS

Utility, pressure, downstream of the second stage servo shutoff valve in the utility module, has dropped below 1,500 psi. Inadequate utility pressure to the second stage side of the tail rotor tandem servo.

NO.1 ENG OIL PRESS LOW

Low oil pressure in the No. 1 engine (10�3 psi or below).
Procedure:
1. Reduce power to minimum for immediate requirement
2. Transition to single- or dual-engine procedures as quickly as possible, perform Engine Shutdown in flight.

NO.2 ENG OIL PRESS LOW

Low oil pressure in the No. 2 engine (10�3 psi or below).
Procedure:
1. Reduce power to minimum for immediate requirement
2. Transition to single- or dual-engine procedures as quickly as possible, perform Engine Shutdown in flight.

NO.3 ENG OIL PRESS LOW

Low oil pressure in the No. 3 engine (10�3 psi or below).
Procedure:
1. Reduce power to minimum for immediate requirement
2. Transition to single- or dual-engine procedures as quickly as possible, perform Engine Shutdown in flight.

1 STG T/R SERVO BYPASS

A servo has malfunctioned in a manner to cause it to bypass hydraulic pressure or loss of system pressure.

BLANK CAPSULE

Possible system malfunction.

2 STG T/R SERVO BYPASS

A servo has malfunctioned in a manner to cause it to bypass hydraulic pressure or loss of system pressure.

NO.1 NGB OIL PRESS

No. 1 nose gearbox oil pressure below 14�2 psi.
Indication of an NGB Oil System Failure.

MGB OIL PRESS

Main gearbox oil pressure below 14�2 psi.
Indication of an MGB Oil System Failure.

NO.3 NGB OIL PRESS

No. 3 nose gearbox oil pressure below 14�2 psi.
Indication of an NGB Oil System Failure.

1 STG PRESS M/R T/R

First stage flight control system below 2,000 psi.

2 STG PRESS M/R

Second stage flight control system hydraulic pressure below 2,000 psi.

UTILITY PRESS

Utility hydraulic system pressure below 1,500 psi.

NO.1 NGB OIL HOT

No. 1 nose gearbox oil temperature above 121��5.5�C.
Indication of an NGB Oil System Failure.

MGB OIL HOT

Main gearbox above 121��5.5�C.
Indication of an MGB Oil System Failure.
Spefically associated with this procedure:
*4. Maintain reduced airspeed and low altitude
*5. Land as soon as possible
6. When flying over water, return to the nearest suitable landin

NO.3 NGB OIL HOT

No. 3 nose gearbox oil temperature above 121��5.5�C.
Indication of an NGB Oil System Failure.

1 STG QTY M/R T/R

Hydraulic fluid quantity is at an unsatisfactory low level.
Procedure:
1. First and second stage hydraulic systems fluid quantity low - Land as soon as possible
2. First and utility hydraulic systems fluid low - Land as soon as possible
3. First or second

2 STG QTY M/R

Hydraulic fluid quantity is at an unsatisfactory low level.
Procedure:
1. First and second stage hydraulic systems fluid quantity low - Land as soon as possible
2. First or second stage hydraulic systems fluid low - Land as soon as practical
3. Second sta

UTILITY QTY T/R

Hydraulic fluid quantity is at an unsatisfactory low level.
Procedure:
1. First and utility hydraulic systems fluid low - Land as soon as possible
2. Second stage and utility systems fluid quantity low - Land as soon as practical
3. Utility hydraulic syst

NO.1 ENG OIL PRESS HIGH

High oil pressure in the No. 1 engine (100�3 psi or above).
Procedure:
1. Maintain reduced speed/power until temp is within range
Procedure:
2. Reduce power to minimum for immediate requirement
3. Transition to single- or dual-engine procedures as quickly

NO.2 ENG OIL PRESS HIGH

High oil pressure in the No. 2 engine (100�3 psi or above).
Procedure:
1. Maintain reduced speed/power until temp is within range
Procedure:
2. Reduce power to minimum for immediate requirement
3. Transition to single- or dual-engine procedures as quickly

NO. 3 ENG OIL PRESS HIGH

High oil pressure in the No. 3 engine (100�3 psi or above).
Procedure:
1. Maintain reduced speed/power until temp is within range
Procedure:
2. Reduce power to minimum for immediate requirement
3. Transition to single- or dual-engine procedures as quickly

C/G HOOK INOP

CG hook load system not functioning or not functioning correctly.

ACC GB OIL PRESS

Accessory gearbox oil pressure below 7�1 psi.
Indication of an AGB Oil System Failure.

NO.1 ENG OIL QTY LOW

No. 1 engine oil at or below refill level.
Procedure:
1. Replenish from aux tank.

NO.2 ENG OIL QTY LOW

No. 2 engine oil at or below refill level.
Procedure:
1. Replenish from aux tank.

NO.3 ENG OIL QTY LOW

No. 3 engine oil at or below refill level.
Procedure:
1. Replenish from aux tank.

DIRCM POWER FAIL

Will illuminate anytime there is an absence of 28 VDC to the CIU with either a UDM or MUDM INSTALLED.

ACC GB OIL HOT

Accessory gearbox oil temperature above 145�.
Indication of an AGB Oil System Failure.

NO.1 ENG ANTI-ICE

Duct temperature below 35�C, or electrical failure in system.

TAIL ROTOR HIGH STRESS

The capsule will only illuminate during PRESS TO TEST for the CAUTION/ADVISORY panel. This capsule is disabled and does not receive illumination signals from the aircraft.

NO.3 ENG ANTI-ICE.

Duct temperature below 35�C, or electrical failure in system.

DIRCM FAIL

When there is a fault displayed on the CIU or during normal initialization, for approximately 3-10 seconds about 20 seconds after initialization starts, or while IBIT is running (approximately 25 seconds).

BEARING VIB LIMIT

Vibration level from at least one of the swashplate sensors (SP-1 and/or SP-2) has reached 2.5 Gs, or vibration level from the tail rotor drive shaft disconnect coupling bearing has reached 4 Gs.
Procedure:
1. Aircrew - Alert
2. Land as soon as practical

BEARING TEMP DETECT

Temperature level from at least one of the swashplate sensors (SP-1 and/or SP-2) or the tail rotor drive shaft disconnect coupling bearing (DISC) has reached 275� F.
Procedure:
1. Aircrew - Alert
*2. Land as soon as possible

BEARING TEMP LIMIT

Temperature level from at least one of the swashplate sensors (SP-1 and/or SP-2) or the tail rotor drive shaft disconnect coupling bearing (DISC) has reached 350� F.
Procedure:
1. Aircrew - Alert
*2. Land immediately

MGB AUX LUBE PUMP

Main gearbox auxiliary oil pressure below 14�2 psi.
Indication of an MGB Oil System Failure.
Specific Procedure:
If MGB OIL PRESS is also illuminated
*1. Land immediately

ENGINE OVERTORQUE

Total engine torque exceeds 137%.

EAPS HIGH PRESS LOSS

Dual pressure switch or relay malfunction. Too much drop in system pressure due to filter clogging.

IFF

When operating in MODE 4, system has malfunctioned, or being interrogated with no reply being made.

2 PT FLT UNARMED

LOAD/UNLOAD mode selected for two-point external cargo system.

NO.1 FUEL LOW

About 666�30 lbs of fuel remains in No.1 tank.

NO.2 FUEL LOW

About 333�15 lbs of fuel remains in the No. 2 left or right tanks.

NO.3 FUEL LOW

About 666�30 lbs of fuel remains in No.3 tank.

ENG STARTER ON

Lights when any engine starter circuit is energized.

EXT PWR CONNECTED

External power connected to the helicopter.

RAMP OPEN

Cargo ramp or door is open.

NO.1 IGV ANTI-ICE ON

No. 1 engine air and inlet anti-icing systems are turned on.

NO.2 IGV ANTI-ICE ON

No. 2 engine air and inlet anti-icing systems are turned on.

NO.3 IGV ANTI-ICE ON

No. 3 engine air and inlet anti-icing systems are turned on.

APP ON

APP is operating above 92%.

ISOLATION VALVE OPEN

Isolation valve is open.

PARKING BRAKE ON

Parking brake handle is extended.

EAPS DOOR CLOSED

All three EAPS bypass doors are closed.

ROTOR BRAKE ON

Rotor brake is fully pressurized to 975�25 psi.

ENG START HEAD POS

Main rotor head is positioned for engine start.

AUTO RELEASE ON

Single-point cargo hook master switch is at AUTO to selected automatic release mode.

FWD HOOK OPEN

Two-point hook release latch open or not fully closed.

IMDS

Indicates a level one exceedance has been detected by the system and unsafe operating condition exists.
1. Aircrew - Alert
2. Verify exceedance through secondary indications
3. In the event secondary indications are present, the appropriate Emergency Proc

PURGING

PURGE pushbottun on the 8.5 minute purge taking place. Advisory light goes off when purge automatically terminates or PURGE pushbutton pressure to off.

AFCS DEGRADED

Any AFCS failure, other than dual computer failure, will cause light to flash.

SINGLE HOOK OPEN

Hook release latch open or not fully closed.

GPWS ALERT

Warns of potentially unsafe conditions in respect to ground proximity.

DIRCM ENGAGED

During normal initialization, the DIRCM ENGAGED light is active for approximately 3-10 seconds about 20 seconds after initialization starts and during IBIT, the DIRCM ENGAGED light is active for approximately 25 seconds while the system is running IBIT an

GPWS INOP

Indicates a system failure.