Warning Light Indications

AP A.TRIM

AFCS is disconnected manually or due to failure. This warning is indicated for 10 sec-onds and disappears automatically even if AFCS remains disconnected.

Procedure: Fly the helicopter manually.

BAT DISCH

Battery is the only electrical power source. Normal during engine start.

Procedure: Reduce electrical consumption as much as possible. Land as soon as practicable.

BAT TEMP

Battery overtemperature

Procedure: BAT MSTR off. In flight: Land as soon as possible. 

FIRE (ENGINE 1 or ENGINE 2)

Overtemperature in engine compartment

Procedure: If in flight, establish OEI condition. Press respective EMER OFF switch and shutdown the affected engine. Land immediately. 

Note: Pressing the FIRE switch, the emergency shut off valve will be closed. When the emergency shut off valve is closed the caution F VALVE CL appears on the CAD.

LOW FUEL 1 and/or LOW FUEL 2

Respective supply tank fuel quantity below 24 kg

Procedure: Check both XFER pumps on. If both FUEL LOW warning lights remain on: Land within 10 minutes. 

ROTOR RPM

NRO 97% or less – steady light

NRO 106% or above – flashing light

Procedure: Adjust collective lever as necessary to maintain NRO within normal range. 

XMSN OIL P

XMSN oil pressure is below minimum

Procedure: Land as soon as possible. 

Caution Light Indications

MASTER CAUTION

Caution indication appeared on CAD

Procedure: Check indication on CAD and perform corresponding emergency procedure. Push CDS/AUDIO RES switch (on cyclic stick) or SELECT button (on CAD) to reset. 

CPDS caution Indications

ACTUATION (MISC)

Failure of a series actuator (AFCS)

AUTOPILOT (MISC)

AFCS is disconnected manually or due to failure. 

Procedure: Fly the helicopter manually. 

BAT DISCON (MISC)

Battery is off-line (normal when BAT MSTR switch is in OFF position).

Procedure: Check BAT MSTR switch. If indication remains on, land as soon as practicable. 

BUSTIE OPN (SYSTEM I or II)

Electrical systems are separated. High load bus disconnected. 

Procedure: Respective BUSTIE sw RESET. If caution indication comes on again: Land as soon as practicable. 

DECOUPLE (MISC)

An upper AFCS mode is decoupled. This caution is indicated for 10 seconds.

DEGRADE (SYSTEM I or II)

Indicates a change or loss of a number of governing functions

ENG CHIP (SYSTEM I or II)

Metal particles detected in engine oil. 

Procedure: Establish OEI flight conditions. Perform emergency shutdown of affected engine. Land as soon as practicable. As an alternative to the emergency shutdown eng switch of affected engine can be set to IDLE position. This allows to use the engine for landing. It is necessary to be prepared for engine failure and to monitor N1, TOT, TRQ, oil pressure and oil temperature of the affected engine closely. 

ENG EXCEED (SYSTEM I or II)

Counter for OEI 30 sec./ 2min. power limitations expired or engine parameter has been exceeded. Indication only on ground. 

Procedure: Maintenance action required before flight. 

ENG FAIL (SYSTEM I or II / CAD and FLI)

Respective N1-RPM below threshold value.

Procedure: Establish OEI flight conditions. Perform emergency shutdown of affected engine. Land as soon as practicable.

ENG IDLE (SYSTEM I or II / CAD and FLI)

The respective engine switch is in IDLE position.

ENG MANUAL (SYSTEM I or II)

Engine MANUAL mode is selected by switching ENG MODE SEL from NORM to MAN. There is no automatic governing function. Throttle has to be controlled manually by twist grip.

Returning to NORM mode: ENG MODE SEL switch to NORM. ENG MANAUL caution disappears. Then turn twist grip carefully to neutral Position. Check TWIST GRIP caution off.

ENG OIL P (SYSTEM I or II)

Affected engine oil pressure below minimum.

Procedure: Establish OEI flight conditions. Perform emergency shutdown of affected engine. Land as soon as practicable.

EPU DOOR (MISC)

External power receptacle access door is open. 

EXT PWR (MISC)

External power is applied. 

FADEC FAIL (SYSTEM I or II / CAD and FLI)

Fuel metering valve is blocked. Automatic acceleration, deceleration during power changes and NORM start are impossible.

Procedure: Adjust collective lever as necessary to maintain N_RO within normal range. Adjust torque of affected engine manually by respective TWIST GRIP. 

MANUAL mode is only available in

FLI FAIL (SYSTEM I or II / CAD and FLI)

Loss of two out of three signals (N1, TRQ, TOT) of the same engine. The numerical values of the failed parameters disappeared. The parameter designation is yellow. The Needle of the respective engine disappeared. If FLI FAIL and FADEC FAIL appear simultaneously, refer to FADEC FAIL procedure. 

F PUMP AFT (MISC)

Failure of aft fuel transfer pump, or dry run.

Procedure: Check fuel quantity in main tank. If quantity is sufficient to keep both fuel pumps wet, check FUEL PUMP XFER-A switch on. Switch OFF if indication remains on. If main tank fuel quantity is low, switch FUEL PUMP XFER-A OFF.

F PUMP FWD (MISC)

Failure of forward fuel transfer pump, or dry run.

Procedure: Check fuel quantity in main tank. If quantity is sufficient to keep both fuel pumps wet, check FUEL PUMP XFER-F switch on. Switch OFF if indication remains on. If main tank fuel quantity is low, switch FUEL PUMP XFER-F OFF.

FUEL (MISC)

The fuel quantities of the supply tanks begin to decrease. Caution appears when fuel quantity is approx. 36 kg (tank 1) or 32kg (tank 2).

Procedure: Chek fuel quantity indication of main tank and supply tanks. Check fuel XFER pump swiches on. Land as soon as practicable.

FUEL PRESS (SYSTEM I or II)

Engine fuel pump inlet pressure low.

Procedure: Switch FUEL PRIME PUMP (affected engine) ON. If caution indication remains, switch pump OFF and land as soon as practicable.

FUEL VALVE (SYSTEM I or II)

Fuel valve is in a position other than commanded.

Procedure: Land as soon as practicable.

F VALVE CL (SYSTEM I or II)

Fuel valve is in closed position.

NOTE The F VALVE CL caution indication will come on after pressing the respective EMER OFF switch marked “FIRE”.

GEN DISCON (SYSTEM I or II)

Respective generator has failed or is disconnected from the power distribution system. Normal while Starter is running.

Procedure: Affected GEN switch RESET, then NORM (via OFF). If GEN DISCON caution indication remains on: Affected GEN switch OFF. DC VOLTS, GEN AMPS and BAT AMPS check. If battery is discharged: Reduce electrical consumers as much as possible. Land as soon as practicable.

NOTE One generator alone will provide sufficient power for normal services.

GEN DISCON (SYSTEM I and II)

Both generators have failed or are disconnected from the power distribution system. Only ESS BUS I + II are available.

Procedure: Each GEN switch RESET, then NORM (via OFF). If both GEN DISCON caution indications remain on: Both GEN switch OFF. Reduce electrical consumers as much as possible. NOTE: The battery will supply the ESS BUS I and II. SHED BUS sw EMER ON if necessary. DC VOLTS and BAT AMPS check. Land as soon as practicable.  

NOTE: Flight endurance depends on battery loading.  

SHED BUS switch is available only in

GYRO (MISC)

Failure of a sensor such as AHRS or Rate Gyro.

HYD PRESS (SYSTEM I or II)

Pressure loss in the respective system, the other system retains power.

Procedure: Land as soon as practicable.

NO TG INST (MISC)

No Twist Grips installed. Caution comes up for 10 seconds if switched to MANUAL throttle mode without having installed or configured throttle rheostats.

OVSP (SYSTEM I or II)

Overspeed protection system failure. 

Procedure: Land as soon as practicable. 

P DAMPER (MISC)

Failure of the Pitch Damper.

PITOT HTR (SYSTEM I or II)

Pitot/Static heater is switched off or failed.

P/R SAS (MISC)

Failure of P/R SAS or inoperative.

PRIME PUMP (SYSTEM I and /or II)

Prime pump(s) in operation.

NOTE Prime pumps must be OFF during normal flight operations.

REDUND (SYSTEM I or II)

Indicates loss of redundancy or failure with no effect on fuel control system.

ROTOR BRK (MISC)

Rotor brake engaged.

Procedure: Check rotor brake lever in Off position. If indication remains on, land as soon as possible.

SAND FILT (MISC)

Inlet Barrier Filter (IBF) is clogged or has blower failure. The caution is also displayed when the IBF system is switched off.

SHED EMER (MISC)

SHED BUS switch is switched to EMER ON.

Procedure: Reduce electrical consumers as much as possible. Land as soon as practicable.  

SHED BUS switch is available only in

STARTER (SYSTEM I or II)

If STARTER caution indication remains on after reaching IDLE speed a relay blockade is evident. The indication is normal during engine starting. 

Procedure: Perform emergency shutdown of affected engine. Land as soon as practicable.

TRIM (MISC)

Failure of AFCS’s autotrim.

TWIST GRIP (SYSTEM I or II)

Twist grip is not in its neutral position. 

Returning to NORM mode: ENG MODE SEL switch to MANUAL, then NORM. ENG MANAUL caution disappears. Then turn twist grip carefully to neutral Position. Check TWIST GRIP caution off.

MANUAL mode is only available in

XMSN OIL P (SYSTEM I or II)

XMSN oil pressure in respective pump system is below minimum.

Procedure: Land as soon as practicable.

XMSN OIL T (MISC)

Transmission oil temperature above maximum.

Procedure: Reduce power as much as possible. Land as soon as possible. 

YAW SAS (MISC)

Failure of Yaw SAS or inoperative.

Single Engine Emergency Shutdown

Inflight Restart

Autorotation