EP's

Question 1

Autorotative landing

Answer 1

1. lower collective and maintain NR in green
2. 65 kts
3. Move fuel control to shutdown position
4. Relight engine or close fuel shutoff cock and turn off; boost pumps, generator, and electrical
5. manuever into wind
6. 65 ft, flare to a nose up attitude
7. 20-25 ft and at a constant attitude, gradually apply collective pitch to
   reduce sink-rate.
8. Resume level attitude before touch-down, cancel any side-slip tendency
9. Gently reduce collective pitch after touch-down.

Question 2

Engine Failure in Hover IGE

Answer 2

1. Do not reduce collective pitch.
2. Control yaw.
3. Cushion touch-down by increasing collective pitch.
4. Reduce collective pitch as soon as the aircraft is on the ground.

Question 3

Engine Failure in Hover OGE

Answer 3

1. Reduce collective pitch.
2. Apply forward cyclic pitch to gain air speed according to available height.
3. Terminate in accordance with autorotative landing procedure.

Question 4

Flame-out in Flight

Answer 4

The symptoms of an engine failure are as follows:
-Left yaw axis
-NR drop (aural warning sounds below 360 rpm).
-Torque at zero.
-Ng falling off to zero.
Generator waring light illuminates.
Engine oil light should also illuminate
- In the event of an engine failure in flight, carry out autorotation procedure.

Question 5

Relighting the Engine in Flight

Answer 5

The normal relighting ceiling is 13000ft but relighting may be attempted throughout the altitude envelope.
- Booster pumps ON
-Generator ON
- Wait until Ng falls below 30% then carry out normal starting procedure.
-In order to avoid any jerk on re-synchronization, accelerate the engine progressively, when free turbine speed approaches rotor speed.

Question 6

Governor Failures, Large Drop in Fuel Flow Rate

Answer 6

Same symptoms as for complete engine failure but after a few seconds, Ng stabilizes at a low rpm value (less than 70%)
- Establish autorotation IAS 65 kt,
-advance the fuel flow control into the
emergency sector. Ng and t4 should rise.
- Control engine speed to 70% Ng.
- If necessary, increase collective pitch to bring rotor speed to 350 rpm.
- Increase fuel flow until rotor speed is approximately 380 rpm.
- Trim collective pitch and fuel flow control to hold level flight at this rotor speed.
-Shallow approach , at lAS = 65 kt
-hold NR at (394 rpm) using the fuel flow control.
-In final approach, reduce forward speed without touching the fuel flow control. The rotor speed will drop when the collective pitch is increased on touchdown. After touchdown, reduce the fuel flow control setting before decreasing the collective pitch.

Question 7

Governor Failures, Excessive Fuel Flow Rate

Answer 7

Ng, t4, NR and torque increase
- Do not reduce collective pitch.
- Reduce fuel until NR is the center of the green area.
- Continue the flight with the governor out of action. Reduction of collective=increase in NR which must be counteracted by adjusting the fuel flow control position.
-set up shallow approach , at lAS = 65 kt, holding NR 394 rpm using the fuel flow control. In final approach, reduce forward speed without touching the fuel flow control. The rotor speed will drop when the collective pitch is increased on touchdown. After touchdown, reduce the fuel flow control setting before decreasing the collective pitch.

Question 8

Governor Failures, Surging

Answer 8

Surging is evidenced by hunting of the rpm, torque and t4 indications and jerks in the yaw axis.
- Reduce collective pitch setting.
- If surging persists while fuel pressure and engine oil pressure are correct, reduce fuel flow slightly to leave the governed range.
- If surging still persists, Land as soon as POSSIBLE and Shut down engine if rotor and engine dont stay joined

Question 9

Engine Fire during Start

Answer 9

• Close the fuel shut-off cock
• Apply the rotor brake if necessary.
• Switch off the booster pumps
• Crank the engine for 10 seconds then switch off the battery.
• Use the nearby extinguishers to fight the fire.

Question 10

Engine Fire in Flight

Answer 10

• Enter autorotation.
• Close the fuel shut-off cock to shut down the engine.
• Switch off the booster pumps and generator.
• Switch off the electrical master

Question 11

Smoke in the Cabin

Answer 11

• If source of smoke is identified.
  Shut off the corresponding system.
  If necessary, use the fire extinguisher. Air the cabin by opening:
  The front vent.
  The ventilation ports.
  The bad weather windows.
  Continue flight depending on failed system.
• If source of smoke is not identified.
  Shut off the heating and demisting system. If the smoke does not clear:
  Electrical master “ALL OFF” switch.
  When smell disappears, set all switches “OFF”, including the generator, close the cabin ventilators.
  Reset battery to “ON”
  Reset the “ALL OFF” electrical switch to normal position. Switch on the generator, check voltage and current.
  If everything is normal, switch on the circuits one by one until the malfunction is identified.

Question 12

Tail Rotor Drive Failure in a Hover or at Low Speed

Answer 12

• IGE: Bring the aircraft to the ground by reducing collective pitch before the yaw rate is too high.
• OGE: Reduce collective pitch moderately to reduce yaw torque and simultaneously start to increase speed.
  General note - LANDING IS EASIER WITH WIND COMING FROM THE RIGHT. IF THE AIR-SPEED IS LOWER THAN 20 KTS (36 KM/H), GO-AROUND IS IMPOSSIBLE DUE TO THE LOSS OF EFFICIENCY OF THE FIN. failure results in left yaw

Question 13

Tail Rotor Drive Failure in Forward Flight

Answer 13

• In forward flight reduce the power as much as possible and maintain forward speed
  -Select a suitable landing area for a steep approach at a power enabling reasonably coordinated flight.
• On final approach, shut down the engine and make an autorotative landing at the lowest possible speed at touchdown.

Question 14

Tail Rotor Control Failure

Answer 14

• Set IAS 70 kts in level flight.
  -pres the “HYD TEST” push-button. After 5 seconds, reset the test button to the normal position.
  -Make a shallow approach to a clear landing area with a slight side slip to the left. Perform a run-on landing; the side slip will be reduced progressively as power is applied.

Question 15

No fuel pressure

Answer 15

• Failure is confirmed by the illumination of the FUEL P. warning light:
  Refer to FUEL P. warning light illumination procedure.
• If failure is not confirmed, the faulty item is the fuel pressure gauge:
  Flight may be continued.

Question 16

Low fuel pressure

Answer 16

• Failure is confirmed by the illumination of the F. FILT. warning light:
  Refer to F. FILT. warning light illumination procedure.
• If failure is not confirmed, the faulty item is the fuel pressure gauge:
  Flight may be continued.

Question 17

Low Engine Oil Pressure (Gauge pointer in red arc when Ng above 85%)

Answer 17

• Test Warning-Caution-Advisory Panel and check ENG P light illuminates.
  Light does not illuminate when tested:
  If torquemeter reading is much too low:
  Shut down engine and make autorotation landing.
  If torquemeter readings correct: LASA Possible
  Light illuminates when tested:
  If torquemeter reading is much too low: LASA Possible
  If torquemeter reading is correct: LASA Practical, monitor ENG. P. light.

Question 18

ENG P Light (Engine oil pressure alarm)

Answer 18

• Reduce power.
• Check engine oil pressure indicator:
  If pressure is low or zero read torquemeter:
  If reading is very low, shut down engine
  If reading correct, Land IMMEDIATELY.
  If both pressure and torquemeter readings are correct, land as soon as POSSIBLE.

Question 19

High Engine Oil Temperature

Answer 19

• At low speed or in Hover
  Land if possible.
  Stop the engine.
  Check that the cooler fan operates. If landing is impossible:
  Fly at approximately 80 kts.
  The temperature should fall rapidly.
  If this result is not obtained, land as soon as POSSIBLE.
• In Cruising Flight Reduce power
  Land if possible.
  Stop the engine.
  Check that the cooler fan operates. If landing is impossible:
  Fly at approximately 80 kts.
  The temperature should fall rapidly.
  If this result is not obtained, land as soon as POSSIBLE.

Question 20

ENG CHIP Light (Metal particles in engine oil system)

Answer 20

• Land as soon as POSSIBLE.
• Take-off is prohibited until the checks specified in Turbomeca maintenance manual have been performed.

Question 21

Ng indicator failure

Answer 21

• In the event of an indicator failure do not exceed the maximum authorized torque value, and keep the t4 temperature below the following limits:
  OAT T4 limit
  Below 15°C-730°C
  Above 15°C-750°C

Question 22

T4 indicator failure

Answer 22

• Comply with the Ng limitations.
• Do not attempt to start the engine.

Question 23

Nr/Nf readings below green arc

Answer 23

• Nf and NR values agree
  Excessive power demand: reduce collective pitch. Indicator reading should rise to governed value.
  If not, follow procedures for a governor failure.

Question 24

Different NR/Nf readings

Answer 24

• NR reading exceeds Nf
  NR reading is incorrect, proceed as in the event of rotor rpm indicator failure except in autorotation.
• Nf reading exceeds NR
  On the ground during the starting sequence:
  Reduce the engine fuel flow control setting to check for possible freewheel slippage.
  In flight
  NR reading is probably incorrect, proceed as in the event of a rotor rpm indicator failure.

Question 25

Rotor RPM Indicator Failure

Answer 25

- In the event of a complete loss of NR indication: Maintain engine torque above 10%: NR reading is given by the Nf pointer. - Land as soon as PRACTICABLE

Question 26

Free Turbine RPM Indicator Failure

Answer 26

- Check that NR reading remains within governed range when collective pitch is slowly modified with engine torque above 0%. - Continue flight.

Question 27

HYD Light (Loss of Hydraulic pressure)

Answer 27

- HIGE, Takeoff, Short Final: (If landing within 30 seconds is possible) Land normally Fuel flow control lever Idle position Collective Lock Shutdown procedure Apply - In flight: Set and maintain angle of bank below 30° Avoid abrupt maneuvers. Smoothly achieve 40-60 kts Hydraulic cut-off switch (collective grip) OFF Land as soon as POSSIBLE. Perform a flat approach into the wind. Make a slow no-hover running landing at around 10 kts ground speed. Do not hover or taxi without hydraulic pressure. After landing: Fuel flow control lever: Idle Position Collective: Lock Shutdown procedure: Apply

Question 28

Yaw Servo-control Slide-valve Seizure

Answer 28

- In Hover: If no movement about the yaw axis, land normally If rotation about the yaw axis, cut off hydraulic pressure by actuating the switch situated on the collective pitch control lever. - In cruising flight: Reduce speed, entering into a side-slip if necessary, then cut off hydraulic pressure by actuating the switch situated on the collective pitch control lever.

Question 29

Main Servo-control Slide-valve Seizure

Answer 29

- Actuate the switch, situated on the collective pitch control lever, to cut off hydraulic pressure. -Load feedback will be felt immediately. -Reduce to 60 kts and proceed as in "HYD" light illuminated.

Question 30

MGB.P Light (Main gearbox oil minimum pressure)

Answer 30

- Reduce power, land as soon as POSSIBLE Time limit - can run for 45 mins with zero oil pressure at minimum power for flight

Question 31

MGB.T Light (Main gearbox oil max temperature)

Answer 31

- Test the warning caution advisory panel to check the MGB.P light. If the light does not illuminate, proceed as for MGB oil pressure at zero. If the light illuminates, land and check the MGB oil level. If the oil level is normal, fly to the nearest base.

Question 32

CHIP MGB Light (Metal particles detected in MGB)

Answer 32

- Reduce engine power. - Monitor MGB.P and MGB.T lights. - Land as soon as POSSIBLE.

Question 33

CHIP TGB Light (Metal particles detected in TGB)

Answer 33

- Continue flight avoiding prolonged hovering.

Question 34

Bleed Valve Stuck Open

Answer 34

- Indicated by a bleed valve flag at high power settings. Maximum engine power will not be available.

Question 35

Bleed Valve Stuck Closed

Answer 35

- Indicated by a lack of a bleed valve flag at low power settings. The engine may surge. Avoid sudden changes in power settings.

Question 36

GENE Light (DC power supply failure)

Answer 36

-Check the DC voltage. -Check the position of the push-button. -Attempt to reset. -If unsuccessful: Shed the least essential consumer circuits; continue flight according to circumstances, keeping a close check on voltage (22 volts minimum). Land as soon as PRACTICABLE.

Question 37

BATT LIGHT (Battery isolated from the DC network, no longer charging)

Answer 37

-Check the push-button (ON). -If OFF: Switch ON and continue flight If ON: Monitor voltage and land as soon as PRACTICABLE.

Question 38

HORN Light (Horn not set)

Answer 38

- Set the horn by actuating the push-button situated on the control pedestal panel.

Question 39

DOORS Light (One or both baggage hold side doors unlocked)

Answer 39

- Reduce IAS, 70 kts maximum. - Land as soon as PRACTICABLE. - Descent and approach at a low rate of descent.

Question 40

PITOT Light (Pitot heating system not energized)

Answer 40

- Check the push-button (ON). - Monitor airspeed indicator.

Question 41

FUEL Light (Fuel quantity less than 15.8 US gal)

Answer 41

- Avoid large attitude changes. -(Approximately 18 minutes level flight remain at maximum continuous power).

Question 42

FUEL FILT Light (Fuel filter clogging)

Answer 42

- Reduce engine power. If light goes out, continue flight at reduced power. If light remains on: Land as soon as POSSIBLE.

Question 43

FUEL P Light (Fuel pressure lower than 0.2 bar on either or both pumps)

Answer 43

- Check fuel pressure: If pressure is normal, only one pump is faulty: Continue flight If pressure is zero, both pumps are faulty: Continue flight at an altitude lower than 5000 ft.

Question 44

Continuous Horn

Answer 44

- Reduce collective pitch. - Reduce speed, and level up If the HYD light is on, the malfunction is in the hydraulics system; Refer to procedure for illumination of the HYD light. If reducing collective pitch and speed has muted the horn, the malfunction was a drop in rotor speed below 360 rpm. -This can logically only occur subsequently to an engine failure, when the fuel flow control is in the "flight" detent. -Check the engine parameters, applying collective pitch very gradually.

Question 45

Intermittent Horn

Answer 45

- If NR above 410 rpm: Slightly increase collective pitch in order to not exceed 430 rpm.