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EC130B4 > Emergency Procedures > Flashcards

Flashcards in Emergency Procedures Deck (57):
1

Land immediately

Self explanatory

2

Land as soon as possible

Emergency conditions are urgent and require landing at the nearest landing site at which a safe landing can be made.

3

Land as soon as practical

Emergency conditions are less urgent and in the pilots judgement, he may proceed to the nearest airfield where he can expect appropriate assistance

4

Continue flight

Continue flight as planned. Repair at the destination according to the maintenance manual

5

Audio warning System control unit SCU
Horn push button

Used to activate audio warning

6

Audio warning
Gong

A gong is generated each time a red warning appears on the warning panel

7

Audio warning
Continuous tone

Two continuous tones can be heard:
- a 310 hz tone when Nr is below 360 rpm
- a 285 Hz tone when maximum takeoff limitations are exceeded.
*After 1.5 second delay if power remains within transient power limitations
*immediately when transient power limitations are exceeded

In addition, for VEMD after embodiment of MOD. 07-3195 only.
*Immediately when transient limitations are or will be exceeded during fast power increase

1. Collective pitch - reduce to maintain NR in green arc or power within limitations
2. Engine parameters - Check

8

Audio warning
Intermittent tone

An internment tone (310 Hz) is heard when the NR is above 410 rpm.
1. Collective pitch- increase to maintain NR in green arc. (Apply applicable procedure according to the situation)

9

Engine flameout (cruise flight)
Autorotation procedure

Autorotation procedure over land
1. Collective pitch reduce to maintain NR in green arc

2. IAS set to Vy

*If relighting impossible or after tail rotor control failure*

3. Twist grip idle detent

4. Maneuver aircraft into wind on final approach

*At 70 ft.*

5. Cyclic flare

*At 20/25 ft and at consistent attitude*

6. Collective pitch - Gradually increase to reduce rate of descent and forward speed

7. Cyclic - forward to adopt slightly nose up attitude (less than 10 degrees)

8. Pedal adjust to cancel any side slip tendency

9. Collective pitch - increase to cushion touchdown

*After touchdown*

10. Cyclic, collective, pedal - adjust to control ground run

*Once aircraft has stopped*

11. Collective pitch full down

12. Rotor brake apply below 170 rotor rpm

10

Autorotation procedure over water

Apply same procedure as over land, except items 10, 11, and 12, but maneuver to head the aircraft equally between the wind and waves direction on final approach. (Ditch with IAS less than 30 kt’s) and vertical speed. Then apply following checklist items 10, 11, 12.

*After touchdown*

10. Collective pitch maintain

11. Door emergency handles pull up

12. Rotor brake apply

13. Abandon aircraft once rotor has stopped.

11

In-Flight relighting

According to available height and cause of flameout.

1. Starting selector - off position

2. [Fuel Pump] or (Fuel P) - On

3. Starting selector - On position
*The relighting sequence will therefore be automatically carried out as soon as NG less than 17%*

After relighting:

4. [Fuel Pump] or (Fuel P) - Off

*At least 1000’ is necessary to complete relighting procedure after flameout.*

12

Autorotation (hover IGE)

1. Collective - maintain

2. Pedals - Control yaw

3. Collective increase as needed to cushion touchdown

13

Autorotation (hover OGE)

1. Collective pitch - fully down

*When NR stops decreasing*

2. Cyclic - forward to gain airspeed according to available height.

3. Autorotation procedure - Apply

14

Autorotation warning (red)

Safe autorotative landing cannot be warranted Incase of failure in HOGE below the top point of the HV diagram (refer to section 5) or in confined area

15

Tail rotor control failure (Symptom)

The helicopter will yaw to the left with a rotational speed depending on the amount of power and the forward speed set at time of failure.

16

Tail rotor control failure
(Hover IGE or OGE in HV diagram)

LAND IMMEDIATELY
1. Twist grip - Idle detent
2. Collective - increase to cushion touch-down

17

Tail rotor control failure
(Hover OGE) (clear area, outside of HV diagram)

Simultaneously
1. Collective - reduce depending on available height

2. Cyclic - forward to gain speed

3. Cyclic - adjust to set IAS to Vy and control yaw

Land as soon as possible

*If a go around has been preformed, carry out an autorotative landing on a suitable area as landing procedure.*

18

Tail rotor control failure
(In cruise flight)

1. Cyclic - Adjust to set IAS to Vy and control yaw

2. Collective - reduce to avoid sideslip

Land as soon as possible

*Approach and landing*
Carryout and autorotative landing on a suitable area as landing procedure

19

Smoke in cockpit/cargo area
(Source not identified)

Heating demisting off
Smoke clears: yes continue flight (depending on weather conditions
No -
1. Master switch or EMER SW - shutoff
2. (Direct batt) or (DCT BAT) - Off
3. (EXT PWR BATT) or (BAT/EPU) - Off
4. (GEN) or (GENE) - Off
5. Master avionic or avionic - Off
6. Ventilate the cabin

*when smoke clears*
1. All consumers - Off (Visually or via SCU TST)
2. (Master switch) or (EMER SW) - On
3. EXT PWR BATT or (BAT/EPU) - On Check DC parameters
4. (Direct BAT) or (DCT BAT) - On Check DC parameters
5. (GEN) or (GENE) - On Check DC parameters

If DC parameters not correct:
6. (GEN) or (GENE) - Off
7. Unnecessary equipment - Off
Land as soon as practicable

If DC parameters correct and no smoke detected:
6. (Master Avionic) or (Avionic) - On
7. All consumers - On, one by one to identify the failed system then keep Off.

CAUTION (AMBER)
When battery or generator are off line, the VEMD goes out and only the NR gauge remains. Apply both screen failure procedure (VEMD screen failure section 3)

20

Smoke in cockpit/cargo
(Source Identified)

1. Corresponding systems - Off
2. Ventilate the cabin

Continue flight depending on failed system

Note:
After DC had been switched off and on in flight, GOV light will remain on until the next normal full engine and battery switch-Off on the ground.

21

VEMD Screen failure (one screen)

Failed screen - Off

Read all available informations on the other screen

Informations Are available using the (Scroll) push button on either the VEMD or the collective pitch lever.

If top screen fails, the 3 parameters engine will be automatically displayed on the lower screen but with Tq and Delta (🔺)NG offline. Only T4 and digital NG will be available. Refer to 3.5.4 for compliance with limitations

22

VEMD Screen failure (failure of both screens)

Can be a single failure when battery and DC generator are in off position (fire and smoke detection procedure)
In this case, to avoid any power over limit, the maximum authorized power will be the power needed to establish level flight with the following law: IAS = 100 kt’s (2 kt’s/ per 1000ft hp)

Land as soon as practicable

Landing procedure: carryout no hover landing

23

Caution message on VEMD

When a parameter is offline, the parameter is not displayed on VEMD upper screen and the parameter scale symbology is displayed in yellow. Caution messages are self explanatory and the pilot shall comply with the action requested. If no light is lit on the caution and warning panel, no other action is required by the pilot.

24

Abnormal NR indication failure

Collective maintain tq greater than 10%
(NR reading given by Nf pointer

Land as soon as practicable

25

Abnormal Nf indication failure

NR gauge - Check in green range greater than 0%

Continue flight

Note 1:
The Nf value can be read on the VEMD screen. Press (select) then (+) as many times as required to display the parameter in the rectangular window at the bottom of the FLI or 3 data screen.

Note 2:
Incase of Nf indication failure, the EBCAU may not be available

26

Abnormal engine parameter indication

Engine oil temperature over 115C
Airspeed set to 80kt’s

Temperature reduces: (Yes)
Land as soon as practicable

Temperature reduces: (No)
Land as soon as possible (check cooler fan operation)

27

Low engine oil pressure

Caution and warning panel - Check ENG P

Check ENG P: (No)
CWP light test completed (ENG P white) land immediately autorotation procedure apply shut down engine time permitting
(ENG P red) land as soon as practicable

Check ENG P: (Yes)
Land immediately autorotation procedure apply shutdown engine time permitting

28

Loss of Ng, tq, or t4 parameters

When a parameter is offline, the parameter value is not displayed on the VEMD upper screen and the parameter scale symbology is displayed in yellow.
The first limits indicator (FLI) is replaced by the 3 data symbology (NG, delta (🔺) NG, T4, and Tq) and a failure message is displayed.

29

NG, Delta (🔺) NG indicator failure

Respect the maximum Tq value and T4 below 810C

Note:
T4 limitations displayed are starting limitations

30

Torquemeter failure

Respect the NG given in the following table.

31

Delta (🔺) NG and torquemeter indicator failure

Red GOV warning can also cause loss of Delta (🔺) NG and TQ indications.
The VEMD switches to 3 data symbology with only T4 and numeric NG as valid parameter. Comply with NG limitations in the above table, substituting the Delta (🔺) NG = -4 by a T4 limit of 810C

32

T4 indicator failure

Respect NG and TQ limitations
On ground do not try and start engine

For all these failures land as soon as practicable (All indicator failures)

33

Engine emergency (warning panel)

(Engine fire) at start up (ENG FIRE red)

1. Starting selector - off position
2. Emergency fuel shutoff handle - aft
3. Booster pump - Off
4. (Crank) - Depress 10 seconds
5. (Master SW) or (EMER SW) - Shut Off
6. Rotor brake apply less than or = to 170 rpm
7. Evacuate and fight fire from outside

Hover, take off, final
Land immediately (carryout no hover powered landing then once on the ground apply same procedure as above

34

Engine emergency (warning panel)

(Engine fire) in flight (ENG FIRE red)

Land immediately
1. Collective pitch reduce
2. IAS -Vy
3. Autorotation procedure - Apply
4. Emergency fuel - shutoff handle (aft)
5. Starting selector- off position

After landing
6. (Master SW) or (EMER SW) - shutoff
7. Rotor break - apply less than or = to 170 rpm
8. Evacuate aircraft fight fire from outside

35

Warning panel (GOV red) (Major gov failure- emergency mode engaged)
(In-Flight)

1. Flight parameters - check (emergency mode self engages yellow GOV illuminates)
2. Collective pitch - avoid abrupt changes (maintain NG greater than 80% hp less than 20000ft)(maintain NG greater than 85% hp greater than or equal to 20000’
Land as soon as practicable

Approach and landing:
Make powered approach avoid steep angle

After touchdown, shutdown:
Collective pitch - slowly down to low pitch
Starting selector - off

Note:
This failure can also result in loss of Delta (🔺) NG and torque parameters on the VEMD

During engine start
Starting selector - off position immediately

36

Warning panel (GOV Yellow) (minor FADEC failure)
(Permanently lighted)
(Flashing at idle, or during starting and shutdown)

Permanently lighted:
Governing function degraded
1. Collective - Avoid abrupt power changes
2. IAS - maintain below VNE Power Off
Land as soon as practicable
On ground do not start engine

Flashing at idle or during start or shutdown:
Governor redundancy failure, no impact on governing function.
Start up procedure abort - report to maintenance manual
Autorotation training - cancel training return to base

37

Warning panel (ENG P Amber)

Engine oil pressure less than 1, 1 bar

Oil pressure - check gauge
Low or nil: land immediately
Autorotation procedure- Apply
Shutdown engine time permitting

Normal: land as soon as practicable

38

Warning panel (TWT Grip amber)

Twist grip outside flight detent

Twist grip increase to flight detent

Continue flight

39

Warning panel (ENG CHIP yellow)

Metal particles in oil circuit

Collective pitch - reduce power
Land as soon as possible

Low power approach and landing
Be prepared Incase loss of engine power

Note:
Takeoff is prohibited until specified checks in TURBOMECA maintenance manual have been preformed

40

Warning panel (MGB P red)
(Main gearbox low oil pressure less than 1 bar)

Collective - reduce power

Land as soon as possible

If a safe landing is not possible, continue flight to the nearest appropriate landing site, reduce power to fly at minimum power speed (Vy)

*At low power Vy, a maximum of 55 minutes of simulated flight time has been demonstrated during bench test*

41

Warning panel (MGB TEMP yellow)
(Main gearbox oil over heating greater than 115C)

IAS - set to Vy
CWP - Check (MGB TEMP)

MGB TEMP grey
Land as soon as practicable

MGB TEMP yellow
Land as soon as possible

42

Warning Panel (MGB CHIP yellow)
(Metal particles in MGB oil circuit)

Collective - Reduce Power

MGB P and MGB TEMP - monitor

Land as soon as possible

43

Warning panel (TGB CHIP yellow)
(Metal particles in TGB oil circuit)

Avoid prolonged hovering

Continue flight

44

Warning panel (HYDR + SERVO yellow)
(Loss of hydraulic pressure in one circuit)

Keep aircraft to more or less level attitude

Avoid abrupt maneuvers
Maintain angle of bank lower than 30 degrees
Maintain IAS below 110kt (or VNE if lower)
Normal approach and landing

Note:
LIMIT light may be on if LH circuit failed or during load factor maneuvers one remaining circuit allows continued safe flight and landing

Land as soon as practicable

Caution:
Under high load factor, servo control reversibility can be encountered

45

Warning panel (SERVO yellow)
(Jamming of a distributor valve on a main servo unit)

Continue flight

46

Warning panel (BATT TEMP red)
(Maximum battery temperature)

1. (EXT PWR BATT) or (BAT/EPU) - Off
2. U bus voltage - Check

Normal:
Land as soon as practicable

Above U max:
1. EXT PWR BATT or BAT/EPU - On
2. GEN or GENE - Off
3. Unnecessary equipment - Off
Land as soon as practicable

47

Warning panel (BATT yellow)
(Battery offline)

(EXT PWR BATT) or (BAT/EPU) - Check On

Yes:
Check voltage on VEMD
Land as soon as practicable

No:
EXT PWR BATT or BAT/EPU - On
Continue flight

48

Warning panel (GENE yellow)
(DC generator offline)

U Bus on VEMD- Check
GEN or GENE - Check On

Yes:
(GENE reset) or (GENE RST) - On
GENE light off continue flight

GENE light stays on:
Unnecessary equipment off
Land as soon as practicable

No:
GEN or GENE - On

Caution:
If the battery fails, the VEMD will go out and only the analog NR gauge will remain

Maximum flight time on battery:
Day - 50 minutes (1 vhf 1 vor)
Night - 20 minutes (same as day plus instrument lighting and external lights)

49

Warning panel (FUEL yellow)
(Less than 48 kg 106 lbs)

Land as soon as possible

Note:
15 minutes of flight time remain at MCP

Warning:
Avoid large attitude changes

50

Warning panel (FUEL P yellow)
(Low fuel pressure)

In flight:
1. Collective pitch - reduce power
2. Booster pump - On

Land as soon as possible

Lower power approach and landing

Warning:
Be prepared Incase of engine flameout

51

Warning panel (FUEL FILT yellow)
(Fuel filter clogged)

Warning:
Fuel filter BY-PASS opening drives pollution into the fuel line, and the governor, introducing oscillations, limited power or eventually flameout.

Collective Pitch - reduce power
FUEL FILT light out - continue flight at reduced power -
Land as soon as practicable
Monitor NG - if NG oscillation occurs (Land immediately) autorotation procedure apply

FUEL FILT Remains On:
Land as soon as possible
Monitor NG - if NG oscillation occurs (Land immediately) autorotation procedure apply

52

Warning panel (PITOT yellow)
(PITOT heating not operative)

PITOT or PITOTS - On

Yes:
Monitor airspeed indicator

No:
PITOT or PITOTS - On
Continue flight

53

Warning panel (HORN yellow)
(Aural warning not operative)

Horn - Check On

Yes:
Aural warning failure
Continue flight

No:
Horn - On
Continue flight

54

Warning panel (DOOR yellow)
(On or both cargo hold unlocked)

Airspeed - reduce to 70kt max

Land as soon as practicable

Descent and approach at low sink rate

55

Warning panel (LIMIT yellow)
(Main servo unit max load reached or max rotor head stressed reached)

In high speed cruise flight or steep maneuvers:
1. Collective - reduce power
2. Cyclic - reduce speed or load factor

At rearward speed or hovering in high tailwind:
1. Cyclic - reduce rearward speed reduce tailwind component

Continue flight

56

Rotor break inoperative

If wind operation:
1. Aircraft headwind
2. Cyclic stick slightly into wind

Warning:
Wait for full rotor shutdown before leaving the aircraft

57

Bleed valve failure

The bleed valve open flag above the FLI (Green cross hash marks) disappears when bleed valve closes
The bleed valve is normally open when the engine is shutdown during starting and low power settings

- If the flag is not displayed when the engine is shutdown, Check GOV SIGNAL fuse or breaker 30a panel. Do not start engine

- if flag does not disappear at high power setting (near MCP or above), the maximum engine power is reduced, specifically in cold weather.

- if the flag does not reappear at low power settings, the engine may surge. Avoid abrupt changes in power settings.

- bleed valve failure results in GOV illumination

Land as soon as practicable