Emergency Procedures Flashcards
Land immediately
Land as soon as possible
Land as soon as practicable
Land immediately: Land or ditch immediately
Land as soon as possible: Land at the nearest site at which a safe landing can be made
Land as soon as practicable: extended flight is not recommended. The landing site and duration of the flight are at the discretion of the pilot.
Autorotation Landing following Engine Failure
- Set low collective pitch to maintain NR in the green range.
- Establish approximately 65 kts airspeed.
- Move the fuel flow control to the shutdown position.
- According to the cause of the loss of the engine:
- Re-light the engine.
- Otherwise: close the fuel shut-off cock and turn off:
▪ Booster pumps
▪ Generator
▪ Electrical power master “ALL-OFF” switch (if smell of burning) - Maneuver to head the helicopter into the wind in final approach.
- At a height of approximately 65 ft AGL, flare to a nose up attitude.
- At a height of 20-25 ft and at a constant attitude, gradually apply collective pitch to
reduce sink-rate. - Resume level attitude before touch-down, cancel any side-slip tendency.
- Gently reduce collective pitch after touch-down.
Engine Failure in Hover I.G.E.
- Do not reduce collective pitch
- Control yaw (left pedal)
- Cushion touch down by increasing collective pitch
- Reduce collective pitch as soon as the aircraft is on the ground
Engine Failure in Hover O.G.E.
- Reduce collective pitch
- Apply forward cyclic to gain air speed accord to available height.
- Terminate in accordance with Autorotation Landing
Engine Failure: Flame-Out in Flight
Symptoms:
- Jerk in the yaw axis (only in high power setting)
- Drop in rotor speed (aural warning sounds below 360 RPM)
- Torque at zero
- Ng falling off to zero
- Generator warning light illuminates
In the event of an engine failure in flight, carry out autorotation transition procedure.
Engine Failure: Relighting the Engine in Flight
Relighting Ceiling is 13000 ft, but relighting may be attempted throughout the altitude envelope.
Procedure:
1. Booster pumps - ON
2. Generator - ON
3. Wait until Ng falls below 30% then carry out normal starting procedure
Note: In order to avoid any jerk on re-synchronization, accelerate the engine progressively, when free turbine speed (Nf) approaches rotor speed.
Governor Failure: Large Drop in Fuel Flow Rate
Same symptoms as for complete engine failure but after a few seconds, Ng stabilizes at low RPM value (less than 70%)
- Establish autorotation with IAS 65 kts, then 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.
The landing approach should be made along a low gradient path, at IAS 65 kts, holding the rotor speed at the upper limit of the green area (394 RPM) using the fuel flow control. On final approach, reduce forward speed without touching the fuel flow control. 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.
Governor Failure: Excessive Fuel Flow Rate
Ng, T4, NR and torque increase.
- Do not reduce collective pitch.
- Reduce fuel flow until rotor speed corresponds to a position of the indicator pointer in the centre of the green area.
- Continue flight with the governor out of action. Any reduction of collective pitch will cause an increase in rotor speed which must be counteracted by adjusting the fuel flow control position.
The landing approach should be made along a low gradient path, at IAS 65 kts, holding the rotor speed at the upper limit of the green area (394 RPM) using the fuel flow control. On final approach, reduce forward speed without touching the fuel flow control. 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.
Governor Failure: Surging
Surging is evidenced by hunting of the RPM, torque and T4 indications and jerks in the yaw axis.
- Change the 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 the engine if there is a tendency of divergence. ( Perform autorotation landing)
Engine Fire: Fire during Engine Start
- Close the fuel shut off cock and 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.
Fire in Flight (“Fire” light ON)
- Enter autorotation
- Close the fuel shut-off cock to shut down the engine.
- Switch off the booster pumps, generator and alternator (if installed)
- Switch off the electrical master “ALL OFF” switch if there is a smell of burning.
Smoke in Cabin: Source of Smoke is identified
- Shut off the corresponding system
- If necessary, use the fire extinguisher
- Air the cabin by opening:
- The front ventilator
- The ventilation ports
- The bad weather windows
Smoke in Cabin: Source of Smoke is not identified
- Shut off the heating/demisting system
If smoke does not clear: - Switch off the electrical master switch (“ALL OFF”)
- When the smell of smoke has cleared, set all switches to “OFF”, including the generator and alternator (if installed), close the cabin ventilators
- Reset the “ALL OFF” electrical master 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.
Note: If the electrical power supply system is faulty, carry out the appropriate procedure, as detailed in the appropriate EP.
Tail Rotor Failure in Hover or Low Speed
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 pick up speed.
CAUTION: Landing is made easier by a wind coming from the right. If the airspeed is lower than 20 kts, GO-AROUND is impossible due to the loss of efficiency of the fin.
Tail Rotor Failure in Forward Flight
- In forward flight reduce the power as much as possible and maintain forward speed (weathercock effect), select a suitable landing area for a steep approach at a power enabling a reasonably coordinated flight.
- On final approach, shut down the engine and make an autorotative landing at the lowest possible speed.
Tail Rotor Control Failure (Stuck Pedal)
- Set IAS 70 kts, in level flight.
- Press the hyd. accumulator test push-button (this cuts off hydraulic power to the yaw servo control and depressurizes the load-compensating servo accumulator). 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.
Fuel System Failure: No Fuel Pressure
Failure is confirmed by illumination of the FUEL P. warning light.
If failure is not confirmed, the faulty item is the fuel pressure gauge. Flight may be continued.
Fuel System Failure: Low Fuel Pressure
Failure is confirmed by illumination of the F.FILT. warning light.
If failure is not confirmed, the faulty item is the fuel pressure gauge. Flight may be continued.
Engine System Failure: Low Engine Oil Pressure
Indicated by gauge pointer in red arc for Ng above 85%
Test Warning-Caution-Advisory Panel and check ENG. P. light illuminates.
- Light does not illuminate when tested:
- If torque meter reading is much too low, shut down engine and make an autorotation landing.
- If torque meter reading is correct, land as soon as POSSIBLE. - Light illuminates when tested:
- If torque meter reading is much too low, land as soon as POSSIBLE.
- If torque meter reading is correct, land as soon as PRACTICABLE, monitor ENG. P. light.
Engine System Failure: ENG. P. Light (Engine Oil Pressure Alarm)
- Reduce Power
- Check engine oil pressure indicator
- If pressure is low or zero read torque meter:
> If reading is very low, shut down engine
> If reading is correct, land IMMEDIATELY
- If both pressure and torque meter readings are correct, land as soon as POSSIBLE.
Engine System Failure: Engine Oil Temp higher than Maximum specified
At Low Speed or in Hover
1. Land if possible:
- Stop the engine.
- Check that the cooler fan operates.
2. If landing impossible:
- Increase speed and reduce power
- Fly at approximately 80 kts
> The temperature should fall rapidly.
> If this result is not obtained, land as soon as POSSIBLE.
In Cruising Flight
1. Reduce Power > then proceed as prescribed above.
A. Land if possible:
- Stop the engine.
- Check that the cooler fan operates.
B. If landing impossible:
- Increase speed and reduce power
- Fly at approximately 80 kts
> The temperature should fall rapidly.
> If this result is not obtained, land as soon as POSSIBLE.
Engine System Failure: Engine Chip Light
- Land as soon as POSSIBLE
- Take-off is prohibited until the checks specified in Turbomeca maintenance manual have been performed.
Ng Differences Indicator Failure
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 <15 °C = T4 limit: 730 °C
- OAT >15 °C = T4 limit: 750 °C
Torquemeter Failure
In the event of a torque meter failure, do not allow the engine speed to rise above the following Ng limits:
see table
t4 Indicator Failure
- Comply with the Ng limitations
- Do not attempt to start the engine
Nr/Nf readings below green arc
Nf and Nr values agree
- Excessive power demand: reduce collective pitch. Indication reading should rise to governed value.
- If not, follow procedures for a governor failure.
Different Nr/Nf readings
A. Nr reading exceeds Nf
- Nr reading is incorrect, proceed as in the event of rotor RPM indicator failure except in autorotation.
B. 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.
Rotor RPM Indicator Failure
In the event of a complete loss of Nr indication:
1. Maintain engine torque above 10%
> Nr reading is given by the Nf pointer
2. Land as soon as PRACTICABLE
Free Turbine RPM Indicator Failure
- Check that Nr reading remains within governed range when collective pitch is slowly modified with engine torque above 0%
- Continue flight.
HYD Light (Loss of Hydraulic pressure)
A. Hover IGE, Take off, Short Final:
1. Land normally
2. Fuel flow control lever > Idle position
3. Collective > Lock
4. Shutdown procedure > Apply
B. In Flight:
1. Set and maintain angle of bank below 30°
2. Avoid abrupt maneuvers
3. Smoothly achieve 40-60 kts
4. Hydraulic cut-off switch (collective grip) > OFF
5. 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
6. After landing
- Fuel flow control lever > Idle position
- Collective > Lock
- Shutdown procedure > Apply
Yaw Servo-Control Slide-Valve Seizure
A. In Hover:
1. If no movement about the yaw axis, land normally
2. If rotation about the yaw axis, cut off hydraulic pressure by actuating the switch situated on the collective pitch control lever.
B. In cruise flight:
1. Reduce speed, entering into a slide-slip if necessary, then cut off hydraulic pressure by actuating the switch situated on the collective pitch control lever.
Main Servo-Control Slide-Valve Seizure
- Actuate the switch, situated on the collective pitch control lever, to cut off hydraulic pressure.
> Load feedback will be felt immediately - Reduce speed to 60 kts and proceed as in the case of illumination of the “HYDR” light.
Main Rotor Gearbox Oil minimum Pressure (MGB. P. Light)
- Reduce Power
- Land as soon as POSSIBLE
Main Rotor Gearbox max Temperature (MGB. T. Light)
- Test the warning caution advisory panel to check the MGB. P. light.
> If 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.
MGB CHIP Light (Metal particles detected in MGB)
- Reduce Engine Power
- Monitor MGB P. and MGB T. lights
- Land as soon as POSSIBLE
TGB CHIP Light ( Metal particles detected in TGB)
Continue flight avoiding prolonged hovering.
Bleed Valve Stuck Open
Indicated by a bleed valve flag at high power settings
> Maximum engine power will not be available
Bleed Valve Stuck Closed
Indicated by a lack of a bleed valve flag at low power settings.
> The engine may surge
> Avoid sudden changes in power settings
GENE Light (DC power supply failure)
- Test 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
BATT Light (Battery isolated from the DC network, no longer charging)
- Check the push-button (ON)
- If OFF > Switch ON and continue flight
If ON > Monitor voltage and land as soon as PRACTICABLE
HORN Light (Horn not set)
Set the horn by actuating the push-button situated on the control pedestal penal.
DOORS Light (One or both baggage hold side doors unlocked)
- Reduce IAS, 70 kts maximum
- Land as soon as PRACTICABLE
- Descent and approach at a low rate of descent
PITOT Light (Pitot heating system not energized)
- Check the push-button (ON)
- Monitor airspeed indicator
FUEL Light ( Fuel quantity less than 15.8 US gal)
Avoid lager attitude changes
Note: Approximately 18 minutes level flight remain at maximum continuous power.
FUEL FILT Light (Fuel filter clogging)
- Reduce engine power
> If light goes out continue flight at reduced power
> If light remains on: Land as soon as POSSIBLE
FUEL P. Light (Fuel pressure lower than 0.2 bar on either or both pumps)
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
AURAL WARNING
Continuous Horn
1. Reduce collective pitch
2. 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 of 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.
Intermittent Horn
- If Nr above 410 RPM
> Slightly increase collective pitch in order to not exceed 430 RPM
