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Flight Study > EC130B4 > Flashcards

EC130B4 Flashcards

1
Q

CRUISE FLIGHT – Autorotation procedure over land:

A

-Collective pitch – REDUCE to maintain NR.
-IAS – SET to VY.
If no relighting or tail rotor control failure:
-Twist grip – IDLE detent.
-Maneuver into the wind on final.
-At ≈ 70 feet: Cyclic – FLARE
-At 20/25: Collective pitch – GRADUALLY INCREASE
-Cyclic – FORWARD for slightly nose-up landing attitude

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2
Q

IN FLIGHT RELIGHTING:

A

According to available height and cause of flame-out:

  1. Starting selector – OFF position.
  2. [FUEL PUMP] – ON.
  3. Starting selector – ON position.
    - The relighting sequence will therefore be automatically carried out as soon as NG
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3
Q

HOVERING AUTO- IGE:

A
  1. Collective – MAINTAIN.
  2. Pedals – CONTROL YAW.
  3. Collective – INCREASE as needed to cushion touch-down.
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4
Q

HOVERING AUTO- OGE:

A
  1. Collective pitch – FULLY DOWN.
    When NR stops decreasing:
  2. Cyclic – FORWARD to gain airspeed according to available height.
  3. Autorotation procedure – APPLY.
    -WARNING: SAFE AUTOROTATIVE LANDING CAN NOT BE WARRANTED IN CASE OF A FAILURE IN HOGE BELOW THE TOP POINT OF THE HV DIAGRAM.
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5
Q

TAIL ROTOR CONTROL FAILURE- IGE or OGE in HV diagram:

A
  1. LAND IMMEDIATELY
  2. Twist grip – IDLE detent.
  3. Collective – INCREASE to cushion touch-down
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6
Q

TAIL ROTOR CONTROL FAILURE- OGE (Clear area, out of HV diagram):

A

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.
  4. LAND AS SOON AS POSSIBLE
    - If a go-around has been performed, carry out an autorotative landing.

WARNING: SAFE AUTOROTATIVE LANDING CAN NOT BE WARRANTED IN CASE OF A FAILURE IN HOGE BELOW THE TOP POINT OF THE HV DIAGRAM OR IN CONFINED AREA.

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7
Q

TAIL ROTOR CONTROL FAILURE- CRUISE FLIGHT:

A
  1. Cyclic – ADJUST to set IAS to VY and control yaw.
  2. Collective – REDUCE to avoid sideslip.
  3. LAND AS SOON AS POSSIBLE
    - Approach and landing: Carry out an autorotative landing to a suitable area as landing procedure.
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8
Q

SMOKE IN THE CABIN- SOURCE NOT IDENTIFIED:

A

Heating, demisting – OFF
-If smoke clears CONTINUE FLIGHT
-If smoke does not clear:
1. [MASTER SWITCH – SHUT OFF.
2. [DIRECT BATT] – OFF.
3. EXT PWR BATT] – OFF.
4. [GENE] – OFF.
5. [MASTER AVIONIC] – OFF.
6. Ventilate the cabin.
-When smoke clears:
1. All consumers – OFF; visually or via [SCU TST]
2. [MASTER SWITCH] – ON.
3. [EXT PWR BATT] – ON, check DC parameters.
4. [DIRECT BATT] – ON, check DC parameters.
5. [GENE] – ON, check DC parameters.
-If DC parameters correct and no smoke detected:
6. [MASTER AVIONIC] – ON.
7. All consumers – ON, one by one to identify the failed system; then keep it off.
-If DC parameters not correct:
8. [GENE] – OFF.
9. Unnecessary equipment – OFF.
10. LAND AS SOON AS PRACTICABLE.
CAUTION: When battery and generator are off line, the VEMD goes out and only the NR gauge remains. Apply both screen failure procedure.

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9
Q

SMOKE IN THE CABIN- SOURCE IDENTIFIED:

A
  1. Corresponding system – OFF.
  2. Ventilate the cabin
  3. CONTINUE FLIGHT depending on system failed.
    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.
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10
Q

VEMD SCREEN FAILURE:

A
  1. IAS kt = 100 kt at sea level – (2 kt / 1,000 ft HP)
  2. LAND AS SOON AS PRACTICABLE.
  3. Landing procedure – Carry out a no hover landing.
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11
Q

NR INDICATION FAILURE:

A
  1. Collective – MAINTAIN Tq > 10%.
    - NR reading is given by NF pointer.
  2. LAND AS SOON AS PRACTICABLE
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12
Q

NF INDICATION FAILURE:

A
  1. NR gauge – CHECK in green range with Tq > 0.
  2. CONTINUE FLIGHT

NOTES:

  • 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.
  • In the case of NF indication failure, the EBCAU may not be available.
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13
Q

ENGINE OIL TEMPERATURE OVER 115°C:

A
  1. Airspeed – SET to 80 kts.
    - If temperature reduces:
  2. LAND AS SOON AS PRACTICABLE.
    - If temperature does NOT reduce:
  3. LAND AS SOON AS POSSIBLE.
  4. Check cooler fan operation.
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14
Q

LOW ENGINE OIL PRESSURE:

A
  1. Caution and warning panel – CHECK ENG P light.
    - If illuminated:
  2. LAND IMMEDIATELY
  3. Autorotation procedure – Apply.
  4. Shutdown engine time permitting.
    - If NOT illuminated:
  5. CWP light test – COMPLETED.
    - If still NOT illuminated:
  6. LAND IMMEDIATELY.
  7. Autorotation procedure – APPLY.
  8. Shutdown engine time permitting
    - If illuminated AFTER CWP light test completed:
  9. LAND AS SOON AS PRACTICABLE
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15
Q
  • ENGINE FIRE- AT START-UP:

- ENGINE FIRE- HOVER, TAKEOFF, FINAL:

A
  1. Starting selector – OFF position.
  2. Emergency fuel shut-off handle – AFT.
  3. Booster pump – OFF.
  4. [CRANK] – DEPRESS (10 seconds).
  5. [MASTER SW] – SHUT OFF.
  6. Rotor brake – APPLY (≤ 170 RPM).
  7. Evacuate aircraft and fight fire from outside.
  8. LAND IMMEDIATELY.
  9. Carry out a no hover, powered landing then, once on ground, apply same procedure as above
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16
Q

ENGINE FIRE- IN FLIGHT:

A
  1. LAND IMMEDIATELY.
  2. Collective pitch – REDUCE.
  3. IAS – VY.
  4. Autorotation procedure – APPLY.
  5. Emergency fuel shut-off handle – AFT.
  6. Starting selector – OFF position.
    - After landing:
  7. [MASTER SW] – SHUT OFF.
  8. Rotor brake – APPLY (≤ 170 RPM).
  9. Evacuate aircraft and fight fire from outside.
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17
Q

GOV (red)- IN FLIGHT:

GOV (red)- DURING ENGINE STARTING:

A
  1. Flight parameters – CHECK.
    - Emergency mode automatically self engages; GOV caution illuminates.
  2. Collective pitch – AVOID abrupt changes
  3. Maintain NG > 80%
  4. Land as soon as practicable.
    - make a shallow approach and landing lowering the collective slowly and start selector off.

1.Start selector- OFF immediately.

18
Q

GOV (yellow)- PERMANENTLY LIGHTED:

GOV (yellow)- BEFORE START:

GOV (yellow)- FLASHING AT IDLE/START-UP/S-DOWN

A
  1. Collective – AVOID abrupt power changes.
  2. IAS – MAINTAIN below VNE power off.
  3. LAND AS SOON AS PRACTICABLE
  4. Do not Attempt Start.

Redundancy loss. Abort start. Cancel autorotation training.

19
Q

ENG P (red):

A
  1. Check oil pressure gauge.

If Low or Nil:

  1. Land Immediately.
  2. Autorotate.
  3. Shutdown engine time permitting.

If Normal:
5. Land as soon as practical.

20
Q

ENG CHIP (yellow):

A
  1. Collective pitch – REDUCE power.
  2. LAND AS SOON AS POSSIBLE.
  3. Low power approach and landing.
  4. Be prepared in case of an engine loss of power.

NOTE: Takeoff is prohibited until specified checks in TURBOMECA Maintenance Manual have been performed

21
Q

MGB P (red):

A
  1. Collective- Reduce
  2. Land as soon as possible.

Warning: Simulated runtime is 55 mins at Vy.

22
Q

MGB TEMP (yellow):

A
  • Main gearbox oil overheating (> 115°C).
  1. IAS – SET TO VY.
  2. CWP – CHECK MGB P light.

If MGB TEMP illuminated:
3. LAND AS SOON AS POSSIBLE.

If MGB TEMP extinguished:
4. LAND AS SOON AS PRACTICABLE.

23
Q

MGB CHIP (yellow):

A
  1. Collective – REDUCE power.
  2. MGB P and MGB TEMP lights – MONITOR.
  3. LAND AS SOON AS POSSIBLE.
24
Q

TGB CHIP (yellow):

A
  1. Avoid prolonged hovering.

2. CONTINUE FLIGHT.

25
Q

HYDR (yellow) and SERVO (yellow):

A
  • Loss of hydraulic pressure in a circuit.
    1. Avoid abrupt maneuvers.
    2. Maintain angle of bank lower than 30°.
    3. Maintain IAS below 110 kt (or VNE if lower).
    4. 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.

  1. LAND AS SOON AS PRACTICAL.

CAUTION: Under high load factor, servocontrol reversibility can be encountered.

26
Q

SERVO (yellow):

A
  • Jamming of a distributor valve.

1. LAND AS SOON AS PRACTICAL

27
Q

GENE (yellow):

A
  1. U bus on VEMD – CHECK.
  2. [GENE] – CHECK. If OFF:
  3. [GENE] – ON. If ON:
  4. [GENE RESET] – ON.

If GENE light extinguishes:
5. CONTINUE FLIGHT.

If GENE light remains illuminated:

  1. Unnecessary equipment – OFF.
  2. LAND AS SOON AS PRACTICABLE.

CAUTIONS:

  • 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).
28
Q

FUEL (yellow):

A

Less than 15.8 gal or 15 mins at MCP

  1. Land as soon as possible.
29
Q

FUEL P (yellow):

A

IN FLIGHT:

  1. Collective pitch – REDUCE POWER.
  2. Booster pump – ON.
  3. LAND AS SOON AS POSSIBLE.
  4. Low power approach and landing.

WARNING: BE PREPARED IN CASE OF AN ENGINE FLAME-OUT.

30
Q

FUEL FILT (yellow):

A

WARNING: FUEL FILTER BY-PASS ALLOWS POLLUTION INTO THE FUEL LINE AND THE GOVERNOR INTRODUCING OSCILLATIONS, LIMITED POWER OR EVEN FLAME-OUT.

  1. Collective pitch – REDUCE POWER.
    - FUEL FILT light extinguishes:
  2. Continue flight at reduced power.
  3. LAND AS SOON AS PRACTICABLE
  4. MONITOR NG
    - If at any time NG oscillations occur:
  5. LAND IMMEDIATELY
  6. Autorotation procedure – APPLY.
    - FUEL FILT light remains illuminated:
  7. LAND AS SOON AS POSSIBLE.
  8. MONITOR NG
31
Q

PITOT (yellow):

A
  1. [PITOT] – CHECK ON.

If ON:

  1. Monitor airspeed indicator.
  2. CONTINUE FLIGHT.

If OFF:

  1. [PITOT] – ON.
  2. CONTINUE FLIGHT
32
Q

HORN (yellow):

A
  1. [HORN] – CHECK ON.

If ON:

  1. Aural warning failure.
  2. CONTINUE FLIGHT.

If OFF:

  1. [HORN] – ON.
  2. CONTINUE FLIGHT.
33
Q

DOOR (yellow):

A
  1. Airspeed – REDUCE to 70 kt max.
  2. LAND AS SOON AS PRACTICABLE.
  3. Descent and approach at low sink rate.
34
Q

LIMIT (yellow):

A
  • Main servo unit max load reached OR Max rotor head stress reached.

In high speed cruise flight or steep maneuvers:

  1. Collective – Reduce power.
  2. Cyclic – Reduce speed or load factor.
  3. CONTINUE FLIGHT.

At rearward speed or hovering in high tail wind:

  1. Cyclic – Reduce rearward speed; reduce tailwind component.
  2. CONTINUE FLIGHT
35
Q

RTR BRAKE INOP:

A
  1. Aircraft – HEADWIND.
  2. Cyclic stick – Slightly into wind.

WARNING: WAIT FOR FULL ROTOR SHUTDOWN BEFORE LEAVING THE AIRCRAFT.

36
Q

Max. Gross Weight (Internal):

A

5350 lbs

37
Q

Temperature Limits:

A

Minimum: -40º C
Maximum: ISA +35º C limited to +50º C

38
Q

Airspeed:

A

Power ON VNE: 155 kts - 3 kts/1000’

Power OFF VNE: 125 kts - 3 kts/1000’

39
Q

Slopes:

A

Nose Up: 6º
Nose Down: 6º
Lateral: 8º

Maneuvering - Do not exceed load factor causing the LIMIT light to illuminate.

40
Q

FLI limits: Yellow arc and Transient.

A

Yellow Arc: max 40 kts (Tq) or 5 min (T4/Ng).

Transient triangle: 5 sec.

41
Q

T4 Starting:

A

750˚ C: Max continuous

865˚ C: Max transient (10 sec)

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