EP's Flashcards
Governor failure
Fuel flow rate down
Same symptoms as eng failure but Ng stabilizes at < 70%
Same symptoms as eng failure but Ng stabilizes at < 70%
Maintain RPM - Auto 65 KIAS
FFC to emergency sector (Ng and T4 should rise)
NG to 70%
If necessary - lower Nr to 350 by increasing collective
Nr to 380 with FFC
Trim Collective and FFC for level flight at Nr 380
- Enter auto
- FFC to Emergency Sector: Ng and T4 should rise
- Control Ng to 70%
- Bump collective to drop Nr to 350
- Increase FFC to Nr 380
- Trim collective and FFC for level flight (at Nr 380)
Governor failure
Excess fuel flow rate
Ng, T4, Nr, and Torque Increase
*Do not reduce collective!*
Reduce FFC till Nr in center of green
Any collective inputs will need corresponding FFC inputs
Landing without governor
Low approach at 65 knots
Nr at 394 with FFC
Final approach - reduce forward speed without touching the FFC
Nr will drop when collective is increased on touchdown
After touchdown, reduce FFC before decreasing collective
Surging
Indications: Hunting of the rpm, torque and t4 indications, jerks in the yaw axis
Reduce collective setting
If persists while fuel and engine pressures are good reduce FFC slightly to leave governed area.
If still persists, land ASAPo
Shut down engine if a tendency for divergence; engine failure procedure
FIRE
RED Light
Engine fire during start
Fuel shut off lever closed
Rotor brake (if necessary)
Booster Pumps off
Crank for 10 seconds
Battery Switch OFF
Extinguishers - fight fire
FIRE
RED LIGHT
Engine fire in flight
Enter auto
Fuel shut off lever closed
Fuel booster pumps OFF
Generator OFF
Master switch OFF if smell burning
Smoke in cabin
Identified source
Shut OFF that system
Fire Extinguisher if necessary
Open front ventilator, ventilation ports, and bad weather windows
Smoke in cabin
Source unidentified
Heating/demisting system OFF
If smoke does not clear:
Master OFF
All switches OFF (including Generator)
Close cabin ventilators
Master On
Generator ON - check voltage and amps
Switch on circuits till source identified
Tail rotor drive failure symptoms
Left yaw: amount depends on A/S and power
Tail rotor drive failure action in hover or low speed
Results in a left yaw. Extent of yaw depends on power and speed
IGE: “Bring aircraft to the ground by reducing collective pitch before the yaw rate is too high.”
- (Hover auto ???)
OGE: Reduce collective moderately to reduce yaw and gain A/S if OGE.
Tail rotor drive failure in forward flight
Results in a left yaw. Extent of yaw depends on power and speed
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
Jamming of pedals or loss of pedal effectiveness
WARNING: LANDING IS MADE EASIER WITH A RH WIND COMPONENT (Helps to control effect of torque). WHEN AIRSPEED IS LESS THAN 20 KT(37 km/h), GO-AROUND IS IMPOSSIBLE DUE TO LOSS OF VERTICAL FIN EFFICIENCY.
Fly 70 KIAS, level flight
HYD TEST button for 5 seconds then back to normal position; depressurizing accumulator
Shallow approach to a clear landing area with a slight side slip to the left (nose right!)
As approaching threshhold, gradually reduce airspeed. As power is slowly applied nose will come left.
Perform a run-on landing; the side slip reduces progressively as power is applied.
Steer with cyclic same as ground track when on the ground!!!
Low Engine Oil Pressure
Gauge Pointer in Red Arc for Ng above 85%
- Test Warning Lights
If light is good and
- TQ is good land ASAPr
- TQ is low, Land ASAPo
If light is bad and
- TQ is good, land ASAPo
- TQ is very low, shut down engine and full down auto
ENG P light OFF when tested (Failed light):
a. TQ very low = shut down engine/autorotation
b. TQ good = land as soon as possible.
ENG P light ON when tested:
a. TQ low = Land ASAPossible
b. TQ good = Land ASAPr and monitor ENG P light.
Engine Oil Temperature Higher than Maximum Specified
In hover
- Land if possible
- Shut down engine
- Check cooler fan
If cannot land
- Fly 80 KIAS or higher & reduce power
* Temp should drop, if not Land ASAPo
Ng indicator failure
Do not exceed max torque and keep T4 as below
OAT <15°C = T4 730°C
OAT >15°C = T4 750°C
Torque Meter Failure
Check ENG P light and engine oil pressure gauge
Check gauge fuse
Ng Limits chart (Mostly 98%)
T4 indicator failure
Comply with Ng limitations (Do not attempt to start engine)
Maximum transient rating (less than 5 seconds)
• Ng = 107.5% - ∆Ng = +6
Maximum takeoff rating (5 minutes)
- without P2 air bleed - ∆Ng = 0
- with P2 air bleed - ∆Ng = –0.6
Maximum continuous rating
• Ng = 98% - ∆Ng = –3.5
Abnormal Nr/Nf Readings
Below Green Arc
If Nr and Nf values agree:
- Excessive power demand
* a. Reduce Collective
- Excessive power demand
Indicator should rise to governed value.
- Governor failure—Refer to Governor Failures
Rotor RPM Indicator Failure
(Complete loss)
Complete loss of Nr indication:
- Maintain above 10% engine torque
Nr reading is then given by the Nf pointer.
- Land ASAPra
Different Nr/Nf readings
- Nr > Nf
- Nr reading is incorrect; (except in autorotation)
- Refer to Rotor RPM Indicator Failure
- 10%+ Torque
- Use Nf
- Land ASAPra
- Nf reading exceeds Nr
On the ground during the starting sequence:
a.Reduce FFC: Check for possible freewheel slippage
Free Turbine RPM (Nf) Indicator Failure
- Check Nr reading
Nr reading should remain within governed range when collective pitch is slowly modified with engine torque above 0%.
- Continue flight.
Yaw Servo Control Slide-valve Seizure
In Hover
- No yaw movement = land normally.
- Yaw movement = HYD OFF
In Cruising Flight
- Reduce A/S, enter into a side-slip, if necessary.
- HYD OFF
Main Servo control Slide-valve Seizure
- Collective HYD switch OFF
- A/S to 60 KIAS
- Proceed as in HYD Light.
Land ASAPo
Load feedback felt immediately; heavy if high speed
a. Collective pitch—44 lb pitch increase load
b. Cyclic—15 to 26 lb left-hand load
c. Cyclic—4 to 9 lb forward load
d. Yaw pedals—Practically no load in cruising flight
Bleed Valve Flag Off
Avoid sudden power variations.
If the flag does not disappear above the specified Ng value, the maximum available engine power is reduced, especially in cold weather.
If the flag does not appear below the specified Ng value, engine surging may result.
Bleed Valve Flag
Flag = Valve open
Normally open when engine is shut down, during start, and low power.
During startup and post-startup acceleration, the airflow is too high and must be reduced to prevent disturbances such as engine stall or surging.
This “airflow reduction” function is automatically performed by a bleed value that compares the pressures P2 (filter outlet pressure) and P0 and closes when NG = 93% approx.
The Ng values at which the bleed valve opens and closes depend on the temperature and altitude specified in the section 4.1 of the RFM.
AURAL WARNING
- Nr between 250 and 360 rpm (continuous)
- Nr above 410 rpm (intermittent)
- Hydraulic pressure drop, below 30 bar (continuous)
- Normal rotor speed when testing the caution panel
It is operative only if the HORN button is pushed in. When this pushbutton is out at nominal rotor speed, the HORN light on the warning–caution–advisory panel is ON.
HYD failure causes
- Failure of the hydraulic pump or belt
- Filter becoming clogged
- Break in a hydraulic line
HYD Light
Loss of hydraulics
IGE hover:
- Land normally
- Lock Collective
- Shutdown
In flight:
- Smoothly establish 40 to 60 KIAS
- Collective HYD switch OFF
LAND AS SOON AS POSSIBLE
Control loads on collective increase and on forward and left cyclic
NOTE: Speed may be increased as necessary but control loads will increase with speed.
– Approach and Landing:
- Shallow apprch to clear, flat area, nose into wind
- Perform run-on landing around 10 knots
– After landing: Lock collective and shutdown
Hydraulic pressure <30 bar
HYD light and the aural alarm, caused by leakage, a broken pump drive belt, etc.
Keep aircraft to a level attitude.
Avoid abrupt maneuvers.
CAUTION: DO NOT PUSH HYD TEST BUTTON AS THIS WILL DEPRESSURIZE THE YAW LOAD COMPENSATOR, RESULTING IN HEAVY PEDALS CONTROL LOADS.
NOTE 1: Pressure in accumulators allows enough time to secure flight and to establish safe speed.
NOTE 2: Do not silence the HORN by using the HORN switch.
HORN will be off when HYD cut-off switch is OFF.
HYD TEST
Button
- Pressed only in flight if suspected tail rotor control problem and need TR somewhat near neutral (lower TQ settings)
- After Start Test:
- Press Button - HYD/HORN lights ON
- Cyclic movemernts (fore/aft & lateral) - No increase in load
- Check pedals - should become stiff
- Press Button again - HYD/HORN lights OFF
Any control feedback on cyclic - accumulators need checking
Tests MR & TR accumulators’ pressurization
Tests for an asymmetric problem if HYD failure
Opens test and TR servo solenoids, allowing accumulators to depressurize
On the ground with the rotor spinning, pressing “HYD TEST” button:
Pilot should be able to move the cyclic stick without any effort until a resistance is subsequently felt, indicating the accumulators have discharged.
Pedals become stiff. HYD TEST opens solenoids 13 & 14. HYD cutoff switch only opens solenoid 13. (8.14 & 8.15)
With rotor stopped alows pilot to operate or center the yaw pedals on the ground.
HYD TEST
Pushing button in flight
DONT DO IT!
Unless a suspected tail rotor control failure
HYD cut-off swtich
After start check
- Secure collective
- Switch OFF - HYD light ON, Load increases
- Pedals are partially boosted
After start test: tests system can be disabled if HYD failure or slide valve seizure; proper operation of isolation solenoids, and yaw accumulator check
Used in case of hydraulic failure or seizure of a servo actuator distributor to route the servo pressure inlet line back into the reservoir
This eliminates back pressure in manual control and reduces the control loads.
With the rotor spinning, turning off HYD switch opens solenoids.
The pressure then drops, the “HYD” light illuminates and the control operating loads are instantaneously felt, except on the yaw pedals where they remain low due to the action of the accumulator.
HYD cut-off switch back on after test
After HYD switch back ON
Horn < 2 seconds = accumulators overcharged
Horn > 3 seconds = accumulators undercharged.
MGB P
RED LIGHT
- Reduce power
- Land ASAPo
NOTE: The MGB has successfully passed a bench test consisting in running the gearbox for 45 min. with zero oil pressure at the power cor-responding to minimum power in level flight (at 55 kt).
MGB T
RED LIGHT
Test MGB P light
- No light = proceed as for MGB P (Reduce Power & Land ASAPo)
- Light = land and check the MGB oil level.
- If oil level is normal, fly to nearest base.
CHIP MGB
Amber light
Reduce engine power.
Monitor MGB P and MGB T lights.
Should either or both lights illuminate refer to illumination of relevant light(s), in LIGHT column.
- MGB P: Reduce power, Land ASAPo
- MGB T: Test MGB P light
No light = proceed as for MGB P
Light = land and check the MGB oil level.
If oil level is normal, fly to nearest base.
CHIP TGB
Amber light
Continue flight avoiding prolonged hovering
BAT T
RED LIGHT
Isolate battery (push button OFF) and land as soon as possible.
BAT
Amber Light
Battery isolated from the DC network; no longer charging
– Check the pushbutton (ON)
If OFF, push ON; continue flight, according to circumstances
If ON:
– Monitor voltage (22 Minimum) and Land ASAPr
ENG CHIP
Amber light
Land as soon as possible
It is prohibited to take off again as long as the checks scheduled in TURBOMECA Maintenance Manual have not been performed.
In addition to Pilot Action, apply the fire-in flight procedure specified in paragraph 5.2 of Section 3.1 if the following occurs
- Smoke in assumed engine area and/or
- Smell of burning in cabin and/or
- Hunting of engine oil pressure indicator pointer.
ENG P
RED LIGHT
- Reduce power.
- Check engine oil pressure indicator:
- If pressure and torquemeter readings are correct, land as soon as possible
- If pressure is low or zero read torquemeter:
° If correct land immediately
° If very low shut down engine; Land or Autorotation???
GEN
Light
– DC power supply failure or overvoltage detected
– Check:
- D.C. voltage.
- GEN push button
- Attempt reset
– If unsuccessful:
- Shed non-essential circuits:
- Continue flight, according to circumstances, keeping a close check on voltage (22 volts minimum).
–Land as soon as practicable.
See altitude limits after booster pumps have been switched off.
HORN
Amber light
Horn not set
– Set the horn by actuating the push-button situated on the control pedestal panel.
No fuel pressure
Failure confirmed if Fuel P light is on.
If no light then gauge is faulty.
Continue flight.
If light is on both pumps faulty:
Flight may be continued lower than 5,000 ft (1,524 m).
Fuel pressure lower than 0.2 bar on either or both pumps
Low Fuel Pressure
Failure confirmed if F FILT light is on.
If no light then gauge is faulty
If light on: Filter is clogging
Reduce power
—-if light goes out continue flight
—-if light stays on, Land ASAPo
Pressure is negative in fuel lines
Avoid flying at high altitude especially at high OAT in order to prevent vapor lock. (THM 10.3)
Note: fuel pressure gauge located post filters
FUEL
Amber Light
Fuel quantity less than 15.8 gal (60 liters)
– Avoid large attitude changes.
NOTE: Remaining usable fuel allows approximately 18 minutes level flight at maximum continuous power.
FUEL P
Amber light
Check fuel pressure:
- Pressure normal = only one pump is faulty:
- Continue flight
- Pressure is zero = both pumps faulty:
- Flight may be continued lower than 5,000 ft (1,524 m).
Fuel pressure lower than 0.2 bar on either or both pumps
F FILTER
Amber light
Filter is Clogged
- Reduce engine power
- Light goes out = continue flight at reduced power.
- Light stays on = land as soon as possible.
PITOT
Amber light
Pitot heat not energized
– Check the pushbutton (ON).
– Monitor airspeed indicator.
DOORS
Amber light
One or both baggage hold side doors unlocked
– Reduce airspeed 120 KIAS max
– Check visually that doors are closed.
– If one or both doors are open, or if checking is impossible:
Land if possible, or continue flight at reduced speed
– Maintain low sink rate and shallow approach.
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 after engine failure
Enter auto and pick LZ
Stabilize RPM 65 KIAS
FFC to shutdown position
Relight possible? If not: Close fuel shut off lever
Switch OFF:
Booster pumps
Generator
Master (if smell burning)
Head into wind on final
Flare approx 65’
20-25’: apply collective to reduce descent
Resume level attitude before touchdown
Lower collective after touchdown
In flight Flameout indications
- Jerk in the yaw axis (only in high-power flight)
- Drop in rotor speed (Horn below 360 rpm)
- Torque at zero
- Ng falling off to zero
- Generator (GEN) warning light illuminates
- Engine oil pressure (ENG P) warning light illuminates
Relighting Engine in Flight
<13,000 ft
- Fuel booster pumps ON
- Generator ON
- Wait until Ng < 30% (“to blowout unburnt fuel”)
- Carry out normal starting procedure.
To avoid any jerk on resynchronization, accelerate the engine progressively when free turbine speed approaches rotor speed.
Flight time on battery only
Day = 50 min
Night = 20 min
High T4 abort
(Under Normal Procedures in RFM)
- Check battery voltage >15 Volts
- If ok, CRANK about 15 seconds
- Immediately Reattempt Start
- Increase FFC gradually; do not let Ng drop between CRANK and 2nd start attempt
- If voltage <15 volts during the start, it may be impossible to obtain lightup.
Aborting Start
- Close FFC
- Fuel pumps & GEN OFF
- CRANK engine (10 seconds)
If the starting cycle has to be aborted return the fuel flow control to the closed position and switch off the fuel pump and generator.
List of battery functions which must remain ON when flying on the battery only
- Day
: Battery, fuel pumps, VHF, Radio-Nav.
- Night
: Same as day plus : Instrument lighting (1 and 2), horizon, position lights, anticollision light.
