EPs Flashcards by Matt Anderson

BAT
TEMP

Conditions/Indications
Battery overtemperature (above 70°C)
− Warning GONG will be activated

ON GROUND
1. BAT MSTR sw − OFF
2. Engines − Shut down
CAUTION BATTERY MUST BE INSPECTED OR REPLACED PRIOR TO NEXT FLIGHT.

IN FLIGHT
− Single pilot operation:
1. BAT MSTR sw − OFF
2. LAND AS SOON AS POSSIBLE
3. Engine shutdown − Perform
4. Visual inspection of battery − Perform
If visual inspection reveals no indication of battery overheating:
5. Start-up procedure − Perform
6. BAT MSTR sw − OFF
NOTE Continue flight in VMC only. On CAD the BAT DISCON caution will appear.
7. LAND AS SOON AS PRACTICABLE

Dual pilot operation:
1. BAT MSTR sw − OFF
2. LAND AS SOON AS POSSIBLE
3. Pilot remaining on seat − “Hands on”
4. Engines − Leave running in IDLE
5. Visual inspection of battery − Perform
NOTE Continue flight (VMC) only if visual inspection reveals no indication of battery overheating. Leave battery OFF or disconnect battery.
On CAD the BAT DISCON caution will appear.
6. LAND AS SOON AS PRACTICABLE

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CHECK
ENG

Conditions/Indications
− Raising the collective while not both engines are in FLIGHT condition
− Beeping warning tone will be activated, not resettable for 5 seconds
− CHECK ENG flashes

NOTE
* Acknowledging the CHECK ENG warning might result in a general warning panel GONG which can be acknowledged by a repeated pushing of the reset button on the cyclic stick.
* Under very particular OEI conditions, i.e. autorotation flight at cold temperatures with a very large right hand pedal input, the collective lever value might fall below the SETO condition and the CHECK ENG warning will be triggered.

1. Abort T/O
2. Affected engine − Identify
3. Respective ENG MAIN sw − Check IDLE or OFF
If engine is in IDLE:
4. Respective ENG MAIN sw − FLIGHT
If engine is OFF:
4. Refer to para 4.4.1.2 “Starting Second Engine” of the basic FLM

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FIRE or FIRE
(ENGINE 1) (ENGINE 2)

Conditions/Indications
Overtemperature in engine compartment
− Warning BELL will be activated

ON GROUND
1. Respective EMER OFF sw − Open switch guard, press and release
NOTE Respective engine will be automatically cut off, “ACTIVE” will illuminate on the EMER OFF SW panel and F VALVE CL will illuminate on the CAD.
2. Both FUEL PRIME PUMPS − Check OFF
3. Double engine emergency shutdown − Perform
IN FLIGHT
1. OEI flight condition − Establish
2. Respective EMER OFF sw − Open switch guard, press and release
NOTE Respective engine will be automatically cut off, “ACTIVE” will illuminate on the EMER OFF SW panel and F VALVE CL will illuminate on the CAD.
3. Affected engine − Identify
4. Single engine emergency shutdown − Perform
If FIRE WARNING light is off:
5. LAND AS SOON AS POSSIBLE
If FIRE WARNING light remains on:
5. LAND IMMEDIATELY
NOTE For safety reasons alert and evacuate the passengers as soon as possible.

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LOW FUEL 1 and/or LOW FUEL 2
(systemI) (systemII)

Conditions/Indications
− Respective supply tank fuel quantity below threshold value
− Warning GONG will be activated

WARNING IRRESPECTIVE OF FUEL QUANTITY INDICATIONS, LOW FUEL WARNING PROCEDURE SHALL BE OBEYED.
1. Clock − Start stopwatch
If both LOW FUEL warning lights are on:
2. LAND WITHIN 8 MINUTES
WARNING AFTER 8 MINUTES, A FLAME-OUT OF BOTH ENGINES MUST BE EXPECTED. IF NO ADEQUATE LANDING SITE IS FOUND WITHIN 6
MINUTES, CONSIDER PERFORMING A POWER-ON IMMEDIATE LANDING.
If one LOW FUEL warning light is on:
2. Expect single engine failure (after approx. 8 minutes)
3. Fuel quantity indication − Check
If positive fuel indication in the main tank:
4. Both fuel pump XFER sw (F + A) − Check ON
5. Both fuel pump XFER circuit breaker (F + A) − Check in
NOTE Due to fuel sloshing, the LOW FUEL warning light on the warning unit may come on/off a few times.
If both LOW FUEL warning lights remain on:
6. Air Condition (if installed) − Switch OFF
7. Bleed Air − Switch OFF (If OAT > 5 C)
8. LAND WITHIN 8 MINUTES
WARNING AFTER 8 MINUTES, A FLAME-OUT OF BOTH ENGINES MUST BE EXPECTED. IF NO ADEQUATE LANDING SITE IS FOUND WITHIN 6
MINUTES, CONSIDER PERFORMING A POWER-ON IMMEDIATE LANDING.
If one LOW FUEL warning light remains on:
6. Air Condition (if installed) − Switch OFF
7. Bleed Air − Switch OFF (If OAT > 5 C)
8. Expect single engine failure (after approx. 8 minutes)

10 min times for larger 710 liter tanks

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ROTOR
RPM

Conditions/Indications
NRo LOW
− NRO 97% or less - steady light
− Audio signal - intermittent low tone (800 Hz)
NRo HIGH
− NRO 106% or above - flashing light and warning GONG
− Audio signal at 112% or above - flashing light and continuous high tone (2400 Hz)

NRO LOW / NRO HIGH
1. Rotor RPM indicator − Check
2. Collective lever − Adjust as necessary to maintain NRO within normal range
NOTE If in addition to the above indications NRO is below both N2 suspect NRO indication system failure. In this case maintain torque above 10% to keep N2 and Rotor RPM matched.

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XMSN
OIL P

Conditions/Indications
XMSN oil pressure is below minimum
− Both XMSN OIL P cautions on CAD are on
− Warning GONG will be activated

1. LAND AS SOON AS POSSIBLE
NOTE Reduce power as much as possible. If immediate safe landing is impossible, reduce power to a minimum for the continuation of the flight (Vy in level flight) to a safe landing site. Main gearbox dryrun capabilities have been demonstrated in a bench test (AEO condition) over more than 25 minutes.

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ENG CHIP or ENG CHIP
(SYSTEM I) (SYSTEM II)

Conditions/Indications
Metal particles detected in engine oil.

ON GROUND
1. Affected engine − Identify
2. Single engine emergency shutdown − Perform
IN FLIGHT
1. OEI flight condition − Establish
2. Affected engine − Identify
Alternative
3. Single engine emergency shutdown − Perform
Alternative
3. ENG main switch − IDLE
CAUTION THE SECOND ALTERNATIVE ENABLES THE CREW TO USE THE AFFECTED ENGINE FOR LANDING IF NECESSARY. BE PREPARED FOR ENGINE FAILURE. MONITOR N1, TOT, TORQUE, OIL PRESSURE AND TEMPERATURE OF AFFECTED ENGINE CLOSELY. IF THE PARAMETERS FLUCTUATE OR THEIR LIMITS ARE EXCEEDED PERFORM SINGLE ENGINE EMERGENCY SHUTDOWN IMMEDIATELY.
4. LAND AS SOON AS PRACTICABLE

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ENG EXCEED or/and ENG EXCEED
(SYSTEM I) (SYSTEM II)

ON GROUND (before takeoff or after landing)
Conditions/Indications
Counter for OEI 30 sec./2 min. power limitations expired or engine parameter has been exceeded.
IN FLIGHT (If the caution is irreversible)
Conditions/Indications
Engine I or/and II was operated above certified limits.

ON GROUND
1. Maintenance action required before flight.
IN FLIGHT
If the caution is irreversible (Engine I or/and II was operated above certified limits)
1. LAND AS SOON AS POSSIBLE
If the caution is reversible (ENG EXCEED triggered by FADEC for exceedance of single excursion time limits)
1. LAND AS SOON AS PRACTICABLE
NOTE Avoid operating in the OEI 30 sec./2 min. power ranges.

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ENG FAIL or ENG FAIL
(SYSTEM I) (SYSTEM II)

Conditions/Indications
− Respective N1-RPM below threshold value.

1. OEI flight condition − Establish
2. Affected engine − Identify
3. Single engine emergency shutdown − Perform
4. LAND AS SOON AS PRACTICABLE

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ENG OIL P or ENG OIL P
(SYSTEM I) (SYSTEM II)

Conditions/Indications
Affected engine oil pressure below minimum.

1.Engine oil pressure indicator (VEMD) − Check
If indication out of limit
2.OEI flight condition − Establish
3.Affected engine − Identify
4.Single engine emergency shutdown − Perform
5.LAND AS SOON AS PRACTICABLE
If indication in the limits
2.LAND AS SOON AS PRACTICABLE

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FADEC FAIL or FADEC FAIL
(SYSTEM I) (SYSTEM II)

Conditions/Indications
Fuel metering valve is blocked.
TOT indication and Torque indication may not be available.
Following functions of the respective engine are inoperative:
− automatic acceleration, deceleration during power (collective) changes
− N1 / TOT/ torque limiter
− NORM start is impossible

1. Collective lever − Adjust as necessary to maintain NRO within normal range
NOTE No immediate action is required as long as power setting (collective) can remain constant.
In case of FADEC FAIL indication during an acceleration/ deceleration phase, wait until engine parameters are stabilized.
2. Affected engine − Identify by small collective changes
3. Respective TWIST GRIP − Adjust slowly to set 80% (+/-2%) N1 on the affected engine (TWIST GRIP caution may come on) Simultaneously adjust collective to maintain engine within limits
NOTE When the OAT is below −10 C, adjust N1 to 77% (+/-2%) instead of 80%.
WARNING OPERATE THE TWIST GRIP WITH GREAT CARE AND AVOID QUICK TWIST GRIP ROTATIONS.
HOLD MIN. 10% TORQUE ON THE NORMAL ENGINE TO MAINTAIN AUTOMATIC CONTROL OF VARIABLE NRO IN ACCORDANCE WITH SECTION 7 / FIG 7-18.
CAUTION DO NOT MOVE TWIST GRIP OF NORMAL ENGINE.
NOTE If the flight situation requires maximum engine power, the power setting of the affected engine may be increased. However, rotor speed and engine parameters shall be observed closely. Do not exceed the N1 / torque value of the normal engine and the AEO limits.
4. LAND AS SOON AS PRACTICABLE
After landing:
5. Respective TWIST GRIP − Reduce, before lowering the collective lever to full down position (to keep N2/NRO within limits)
CAUTION THERE IS NO NRO GOVERNING FOLLOWING FADEC FAILURES OF BOTH ENGINES. NRO AND POWER MUST BE CONTROLLED BY THE PILOT USING A COMBINATION OF COLLECTIVE AND TWIST GRIP MOVES.
NOTE Perform appropriate logbook entry. Maintenance action is required.

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FUEL FILT and / or FUEL FILT
(SYSTEM I) (SYSTEM II)

Conditions/Indications
Engine fuel filter(s) contaminated.

One caution indication:
1. LAND AS SOON AS PRACTICABLE
NOTE Be prepared for single engine failure.
Both caution indications:
1. LAND AS SOON AS POSSIBLE
CAUTION BE PREPARED FOR DOUBLE ENGINE FAILURE.

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GEN OVHT or GEN OVHT
(SYSTEM I) (SYSTEM II)

Conditions/Indications
Temperature of generator high.

1. Affected GEN switch − OFF
If GEN OVHT caution indication remains on for more than 1 minute:
2. OEI flight condition − Establish
3. Affected engine − Identify
4. Single engine emergency shutdown − Perform
5. LAND AS SOON AS PRACTICABLE

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XMSN OIL P or XMSN OIL P
(SYSTEM I) (SYSTEM II)

Conditions/Indications
XMSN oil pressure in respective pump system is below minimum.

1. XMSN oil pressure indication − Check in normal range
2. LAND AS SOON AS PRACTICABLE

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XMSN OIL T

Conditions/Indications
Transmission oil temperature above maximum.

1. XMSN oil temperature and oil pressure indication − Check
If indications are within limits:
2. LAND AS SOON AS PRACTICABLE
If indications are out of limits:
2. Power − Reduce, as much as possible
If oil temperature indication remains out of limits:
3. LAND AS SOON AS POSSIBLE

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Single Engine Failure - HIGE

Conditions/Indications
− Slight jerk in the yaw axis, nose left
− Possible change in noise level
Affected engine:
− ENG FAIL caution indication (CAD & FLI)
− ENG OIL P caution indication
− FUEL PRESS caution indication
− GEN DISCON caution indication
− Instruments indicate power loss

1. Collective lever − Adjust to maintain rotor RPM
2. Landing attitude − Establish
3. Collective lever − Raise as necessary to stop descent and cushion landing
NOTE Below 95% rotor RPM, the torque could increase from 128% up to 133%.
After landing:
4. Affected engine − Identify
5. Single engine emergency shutdown − Perform

Single Engine Failure - HOGE

1. Airspeed − Increase if possible
and simultaneously
2. Collective lever − Adjust to maintain rotor RPM
FORCED LANDING
3. Landing attitude − Establish
4. Collective lever − Raise as necessary to stop descent and cushion landing
NOTE Below 95% rotor RPM, the torque could increase from 128% up to 133%.
After landing:
5. Affected engine − Identify
6. Single engine emergency shutdown − Perform
TRANSITION TO OEI - FLIGHT
3. Airspeed − Gain, 65 KIAS (VY)
and simultaneously
4. Collective lever − Adjust to OEI-limits or below
After reaching safe altitude:
5. Collective lever − Reduce to OEI MCP or below
6. Affected engine − Identify
7. Single engine emergency shutdown − Perform
8. LAND AS SOON AS PRACTICABLE

Single Engine Failure - Takeoff

1. Collective lever − Adjust to maintain rotor RPM
REJECTED TAKEOFF
2. Landing attitude − Establish
3. Collective lever − Raise as necessary to stop descent and cushion landing
NOTE Below 95% rotor RPM, the torque could increase from 128% up to 133%.
After landing:
4. Affected engine − Identify
5. Single engine emergency shutdown − Perform
TRANSITION TO OEI - FLIGHT
2. Collective lever − Adjust to OEI-limits or below
3. Airspeed − Gain, 65 KIAS (VY)
After reaching safe altitude:
4. Collective lever − Reduce to OEI MCP or below
5. Affected engine − Identify
6. Single engine emergency shutdown − Perform
7. LAND AS SOON AS PRACTICABLE

Single Engine Failure - Flight

1. OEI flight condition − Establish
2. Affected engine − Identify
3. Single engine emergency shutdown − Perform
4. LAND AS SOON AS PRACTICABLE

Single Engine Emergency Shutdown

NOTE
* Before performing an inflight single engine emergency shutdown, determine if the situation will allow for OEI flight.
* Make certain that:
− the controls of the affected engine are selected, and
− the collective lever is adjusted to maintain the normal engine within the OEI limits
− START cb is not pulled
* In case of a single engine failure/ emergency shutdown, the bleed air heating will be switched off automatically. Depending on the power margin of the normal engine, the bleed air heating may be re engaged by selecting heater switch position EMER.
* If CAD message BLEED AIR remains on after single engine failure, the system must be switched off manually. Depending on the power margin of the normal engine, the bleed air heating may be re engaged.
1. ENG MAIN sw (affected engine) − IDLE, check indications, then OFF
NOTE If the FADEC of the affected engine is switched off, caution light FADEC MINR of the remaining engine will appear due to missing parameter redundancy. Therefore, the FADEC switch should remain in ON position.
If there is an indication that the engine is still running or TOT is rising abnormally:
2 Respective TWIST GRIP − Turn to min. fuel stop, verify correct engine then shut off
NOTE A ventilation is only possible when the START cb is not pulled.

Engine Overspeed - Driveshaft Failure

Conditions/Indications
− NRO decrease
Affected engine:
− Torque decreases to zero
− N2 increases above NRO and oscillates if engine overspeed protection system is active
Normal engine:
− Torque, N1 and TOT increase
− N2 decrease/increase depending on previous torque setting

1. Collective lever − Raise to maintain N2 and NR within limits
2. Affected engine − Identify
3. TWIST GRIP (affected engine) − Reduce torque until the normal engine takes the load
(TWIST GRIP and ENG MANUAL cautions come on)
4. Collective lever − Readjust as required to stay within limits
5. ENG MODE SEL sw (affected engine) − MAN
6. TWIST GRIP (affected engine) − Adjust torque manually to 20−30% according to weight and ambient conditions
7. Collective lever − Readjust as necessary without changing TWIST GRIP position
8. LAND AS SOON AS PRACTICABLE
After landing:
9. TWIST GRIP (affected engine) − Reduce before lowering the collective lever to full down position (to keep N2/NRO within limits)
WARNING OPERATE THE TWIST GRIP WITH GREAT CARE AND AVOID QUICK TWIST GRIP ROTATIONS.
HOLD MIN. 10% TORQUE ON THE NORMAL ENGINE TO MAINTAIN AUTOMATIC CONTROL OF VARIABLE NRO IN ACCORDANCE WITH
SECTION 7 / FIG 7-18.

Engine Oil Temperature High

Conditions/Indications
Affected engine:
− Oil temperature indication out of limits

1. Airspeed − Increase if possible
If engine oil temperature decreases below limit:
2. LAND AS SOON AS PRACTICABLE
If engine oil temperature remains above limit:
2. Affected engine − Identify
3. OEI flight condition − Establish
4. Engine main sw (affected engine) − Ground Idle
5. Oil temperature indicator (affected engine) − Monitor
If engine oil temperature decreases below limit:
6. LAND AS SOON AS PRACTICABLE
NOTE If conditions require, engine can be switched back to FLIGHT.
If engine oil temperature still remains above limit:
6. Single engine emergency shutdown − Perform
7. LAND AS SOON AS PRACTICABLE

Double Engine Failure - HIGE

Conditions/Indications
− Yawing motion nose left
− NRO and both N2 decrease
− ROTOR RPM warning (NRO low) on
− Both ENG FAIL caution indications (CAD & FLI)
− Both ENG OIL P caution indications
− Both FUEL PRESS caution indications
− Both GEN DISCON caution indications
− Instruments indicate power loss

1. Right pedal − Apply as necessary to stop yaw
2. Landing attitude − Establish
3. Collective lever − Raise as necessary to cushion landing
After steady ground contact:
4. Collective lever − Lower rapidly

Double Engine Failure - Flight

Conditions/Indications
− Yawing motion, nose left
− NRO and both N2 decrease
− ROTOR RPM warning (NRO low) on
− Both ENG FAIL caution indications (CAD & FLI)
− Both ENG OIL P caution indications
− Both FUEL PRESS caution indications
− Both GEN DISCON caution indications
− Instruments indicate power loss

1. Autorotation − Perform

Double Engine Emergency Shutdown

ON GROUND **1. Both ENG MAIN sw − OFF 2. Both FADEC sw − OFF 3. Both Fuel PRIME PUMP sw − OFF 4. BAT MSTR sw − OFF** If there is an indication that the engines are still running or TOT is rising abnormally: **5. Both TWIST GRIPS − Turn to shut off** IN FLIGHT **1. Both ENG MAIN sw − OFF 2. Both FADEC sw − OFF** NOTE The shut off valves are inoperative when START cb is pulled. If there is an indication that the engines are still running or TOT is rising abnormally: **3. Both TWIST GRIPS − Turn to shut off**

Autorotation

**1. Collective lever − Reduce to maintain NRO within limits 2. Airspeed − 75 KIAS recommended** NOTE -Maximum range airspeed is 90 KIAS -Minimum rate-of -descent airspeed is 60 KIAS **3. Double engine emergency shutdown − Perform** AT APPROXIMATELY 100 FT AGL: 4. Flare attitude − Establish TOUCHDOWN: 5. Landing attitude − Establish 6. Heading − Maintain 7. Collective lever − Increase to stop descent and cushion landing AFTER TOUCHDOWN: 8. Collective lever − Lower slowly to prevent an abrupt stop of the helicopter 9. Cyclic stick − Maintain in neutral position **10. BAT MSTR sw − OFF**

Cabin Fire ## Footnote Conditions/Indications − Smoke, burning odor, flames

ON GROUND **1. Double engine emergency shutdown − Perform 2. Passengers − Alert/Evacuate 3. Fire − Extinguish if possible** IN FLIGHT **1. Airspeed − Reduce, if necessary (65 KIAS recommended) 2. Passengers − Alert 3. Heating/Air conditioning (if installed) − OFF 4. Fire − Extinguish if possible 5. Fumes, smoke − Eliminate, open sliding doors, windows and vents (fresh air) 6. LAND AS SOON AS POSSIBLE** After landing: **7. Double engine emergency shutdown − Perform**

Electrical Fire / Short Circuit ## Footnote Conditions/Indications − Odor of burning insulation and/or acrid smoke

ON GROUND **1. Double engine emergency shutdown − Perform 2. Passengers − Alert/Evacuate 3. EPU, if connected − Disconnect 4. Fire − Extinguish if possible** IN FLIGHT WARNING BE PREPARED FOR LOSS OF DISPLAY SYSTEMS, AFCS, COM. SYSTEMS AND OTHER HELICOPTER SYSTEMS EXCEPT STANDBY INSTRUMENTS. NOTE -If conditions require, open window(s) or sliding door(s) and vents for fresh air. -If the source of the smoke or fire can be positively identified, remove electrical power to the equipment, either by switching it off, or by pulling the associated circuit breaker. -HYD PRESS caution will illuminate when power is lost to the respective essential bus. The respective hydraulic system is not turned off. -Affected electrical systems can generate a caution on the CAD. **1. Both BUS TIE sw’s − OFF 2. Both BUSTIE OPN cautions − Check on 3. DC VOLTS, GEN AMPS and BAT AMPS − Compare, note higher load 4. BAT MSTR sw − OFF** If fire / smoke continues: **5. Respective GEN sw (higher load) − OFF** 6. Respective GEN DISCON caution − Check on If fire / smoke continues: **7. Both GEN sw’s − NORM** 8. Both GEN DISCON cautions − Check off **9. Other GEN sw − OFF** 10. Respective GEN DISCON caution − Check on If fire / smoke continues: CAUTION WITH BATTERY AND GENERATORS SWITCHED OFF, ALL ELECTRICAL SYSTEMS WILL BE OFF (BLACK COCKPIT). **11. Both GEN sw’s − OFF 12. LAND AS SOON AS POSSIBLE** If fire / smoke eliminated: **11. LAND AS SOON AS POSSIBLE** If fire / smoke eliminated: **7. LAND AS SOON AS POSSIBLE** If fire / smoke eliminated: **5. LAND AS SOON AS POSSIBLE**

Tail Rotor Drive Failure - Hover ## Footnote Conditions/Indications Complete loss of tail rotor thrust − Tail rotor failure in power-on flight is indicated by a yawing motion nose right; the yaw rate depends on the aircraft power at the time of failure.

HOVER IN GROUND EFFECT **1. Both TWIST GRIP‘s − Turn to minimum** and simultaneously: **2. Landing attitude − Establish 3. Collective lever − Apply as necessary** After landing: **4. Double engine emergency shutdown − Perform** HOVER OUT OF GROUND EFFECT **1. Collective lever − Reduce immediately 2. Both TWIST GRIP‘s − Turn to minimum** If height permits: **3. Airspeed − Gain 4. Collective lever − Raise to stop descent and cushion landing** After landing: **5. Double engine emergency shutdown − Perform**

Tail Rotor Drive Failure / Fixed-pitch Tail Rotor Control Failure - Forward Flight ## Footnote Conditions/Indications − No directional response after pedal inputs and/or − Complete loss of tail rotor thrust and/or − Locked pedals

NOTE The procedure will vary depending on flight conditions, power setting and mass of the helicopter **1. Collective lever − Reduce to obtain minimum sideslip angle 2. Airspeed − Maintain 70 KIAS or higher** 3. Suitable landing area − Select NOTE -Surface of the landing area should be hard (e.g. concrete, asphalt) and flat. -Crosswind from the left is advantageous **4. Shallow approach with nose left − Perform** If the airspeed can be reduced below 40 kts with the nose still pointing to the left: **5. Airspeed − Reduce close to the ground until nose is aligned with the flight direction 6. Landing − Perform** If the nose direction changes from left to right at airspeeds higher than 40 kts: **5. Airspeed − Increase (nose down) 6. Approach − Abort, climb to sufficient height for autorotation** NOTE Headwind is advantageous **7. Autorotation − Perform** NOTE -In autorotation zero sideslip can be expected at about 60 to 70 kts. -Before touchdown, the groundspeed should be reduced to a minimum -In final phase of flare the helicopter can yaw to the left due to friction effects.

Abnormal Vibration During Flight ## Footnote Conditions/Indications Possible deposit of foreign objects (e.g. water, ice etc.) in the control cuff(s).

**1. LAND AS SOON AS POSSIBLE**