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Robinson R44 > POH > Flashcards

POH Flashcards

1
Q

MCP and 5 min T/O BH Power

A

Raven I: 205/225

Raven II: 205/245

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2
Q

Max Gross Weight

A

Raven I: 2400 lbs

Raven II: 2500 lbs

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3
Q

Minimum Gross Weight

A

Raven I: 1550 lbs

Raven II: 1600 lbs

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4
Q

Individual seat limits

A

300 lbs including baggage compartment

50 lbs max in baggage compartment

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5
Q

Main Rotor Diameter

A

33’

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6
Q

Vne

A

≤2200 lbs TOGW = 130 KIAS
>2200 lbs TOGW = 120 KIAS

100 KIAS:
Autorotation
Any door(s) removed
MAP > MCP

Do not exceed 110 KIAS except in smooth air (yellow arc on ASI or placard for older ASI)

Vne Chart

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7
Q

Power on/off RPM limits

A

Raven I: 99%-102% (actual RPM 396-408); 90%-108% (actual RPM 360-432)

Raven II: 101%-102% (actual RPM 404-408); 90%-108% (actual RPM 360-432)

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8
Q

Solo Pilot Weight

A

minimum 150 lbs

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9
Q

Fuel capacity

A

Total usable with bladders:
46.5 gal
Main: 29.5
Aux: 17

Total with unusable:
47.7
Main: 30.5
Aux: 17.2

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10
Q

Calculated gallons per hour

A

17

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11
Q

Altitude Limits

A 
14,000 DA
9000 AGL (to allow landing in 5 minutes in case of fire)
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12
Q

Action for hydraulic system failure

A
  1. Verify HYD switch on
  2. If not restored, HYD switch off
  3. Adjust airspeed and flight for comfortable flight
  4. Land as soon as practical

If HYD switch is OFF, try pulling HYD circuit breaker to restore
>Run-on Landing

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13
Q

MAP gauge yellow arc means ….

A

variable MAP limits

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14
Q

Land immediately:

A

Land on the nearest clear area where a safe normal landing can be performed. Be prepared for autorotation during approach, if required.

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15
Q

Land as soon as practical:

A

Landing site is at pilot’s discretion based on nature of problem and available landing areas. Flight beyond nearest airport is not recommended.

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16
Q

What do you do if fuel filter light illuminates?

A

Indicates fuel strainer contamination.
If no other sign of a problem land as soon as practical.
If accompanied by AUX fuel pump warning light or erratic engine operation, land immediately.

School: “Land immediately”

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17
Q

AUX fuel pump light

A

Indicates low AUX fuel pump pressure.
If no other sign of a problem land as soon as practical.
If accompanied by erratic engine operation, land immediately.

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18
Q

3 failed attempts at starting

A

Wait 10 minutes for starter to cool

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19
Q

Why is there an AUX fuel pump?

A

To prime for starting and fuel pump redundancy in flight

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20
Q

Will HYD be lost if ALT and battery are inop?

A

No, runs on HYD pump on main rotor gear box.

On gear box to keep HYD in case of engine failure.

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21
Q

How do we know if the engine driven fuel pump is operational?

A

Normal engine operation when clutch switch is disengaged during startup and shutdown.

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22
Q

What happens if pumps supply too much fuel to engine?

A

Excess returns to tanks

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23
Q

MAP gauge red line

A

Raven I: 26.3” Hg

Raven II: 26.1” Hg

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24
Q

Max Glide configuration:

A

90 KIAS 90%

Increase RPM to a minimum of 97% by 500’ AGL

4.7:1
1 NM per 1300’ AGL

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25
Q

Minimum descent configuration:

A

55 KIAS 90%

Increase RPM to a minimum of 97% by 500’ AGL

4:1
1 NM per 1500’ AGL

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26
Q

How much time left when low fuel light comes on?

A

10 minutes at cruise power. 3 gallons of fuel left.

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27
Q

Why should we fly with doors latched but not locked?

A

To allow for rescue or emergency exits.

28
Q

Amount of blade twist?

A

-6°

29
Q

What will happen if you pull the HYD circuit breaker?

A

Nothing, unless the HYD switch is broken in the OFF position; then pulling circuit breaker would disconnect HYD switch and turn HYD back on if pump is not damaged

30
Q

Operating pressure of HYD?

A

450 to 500 psi

31
Q

Location of pitot-static drain lines?

A

Underside of cabin in frwrd inspection panel

32
Q

Vy

A

best rate of climb

55 KIAS

33
Q

Max range airspeed

A

100 KIAS

Certain conditions may require lower airspeeds

34
Q

Minimum oil for take off?

A

7 quarts

35
Q

Where is the CO sensor located?

A

Above pilot’s heater outlet

36
Q

How is engine fire light actuated?

A

By a temperature switch at the forward end of horizontal firewall

37
Q

Loss of HYD fluid indications?

A

May cause intermittent and/or vibrating feedback in controls

38
Q

Vh?

A

Stabilized level flight at MCP

39
Q

Vne with pop-out floats inflated

A

80 KIAS

40
Q

If CO light illuminates:

A

Shut off heater
Open door and nose vents
If hovering, transition to forward flight

41
Q

Hydraulic system consists of:

A

Pump, 3 servos (1 for each push-pull tube), a reservoir, and connecting lines

Reservoir behind MR gear box on steel tube frame includes a filter, pressure relief valve, and pilot controlled pressure shut-off valve.

42
Q

Fuel sample locations

A

Main and AUX tanks in right side cowl door.

Gascolator lower right side of firewall.

43
Q

Electrical system

A

28 volt 70 amp ALT
24 volt sealed lead-acid battery
Battery relay
Alternator control Unit

44
Q

Air restart

A
  1. Mixture off
  2. Throttle closed
  3. Starter - enage
  4. Mixture - move slowly rich while cranking

Not recommended below 2000’ AGL
Do not attempt if:
not in stabilized autorotation or engine malfunction is suspected

45
Q

How long to prime?

A

First flight: 3-5 seconds

Other: 2 seconds

46
Q

CO monitor should flash how many times when master is turned on?

A

2

47
Q

What is critical altitude?

A

Max altitude which an engine can maintain it’s full rated HP

48
Q

Approved fuel grades?

A

100 LL 100/130

49
Q

Other locations battery could be found

A

Under front left seat

Beneath instrument console

50
Q

Powerplant

A 
Raven I: 
Lycoming O-540-F1B5
6 cylinder, horizontally opposed, direct drive, air cooled, carbureted, normally aspirated
Normal rating: 260 BHP
MCP: 205 BHP
5 min T/O: 225 BHP
2718 Max RPM @ 102%

Raven II:
Lycoming IO-540-AE1A5
6 cylinder, horizontally opposed, direct drive, air cooled, fuel injected, normally aspirated
Capable of 300 HP, normally rated at 260 HP
MCP: 205 BHP
5 min T/O: 245 BHP
2718 Max RPM @ 102%

51
Q

Blade Diameter

A

Main rotor = 33’

Tail rotor = 4’ 10”

52
Q

Oil Pressures

A

Min during idle = 25 psi
Min during flight = 55 psi
Max during flight = 95 psi
Max during start and warm up = 115 psi

53
Q

When collective is lowered at high airspeed….

A

aft cyclic is required.

54
Q

T/O, climb, and approach A/S

A

60 KIAS

55
Q

Max climb A/S

A

55 KIAS

56
Q

Max range A/S

A

100 KIAS

57
Q

Max cruise A/S

A

110 KIAS ( do not exceed except in smooth air, and then only with caution)

58
Q

Significant turbulence A/S

A

60 to 70 KIAS

59
Q

If engine doesnt fire after 5 to 7 seconds of cranking…

A

repeat priming sequence and reattempt start.

If fails to start after 3 attempts, allow starter to cool 10 minutes.

60
Q

If engine fires momentarily but dies before or while moving mixture to rich…

A

pull mixture off, engage starter, and push mixture slowly rich while cranking

61
Q

Avoid blade slap

A

Generally occurs at airspeeds <100 KIAS.

Avoid by maintaining 100 KIAS until rate of descent is over 1000 fpm, then using a fairly steep approach until A/S is below 65 KIAS

62
Q

HYD off effects on controls

A

Collective inputs cause longitudinal cyclic forces.

Any cyclic input will cause the collective to lower.

63
Q

Clutch fuse

A

Prevents actuator motor from overload tripping the clutch circuit breaker.
An open circuit breaker removes power from clutch motor and LIGHT.

64
Q

What is the AUX fuel pump?

A

Used for priming.
Runs after start up for redundancy, and as long as the engine has oil pressure and the clutch switch is in the engage position.

65
Q

What illuminates the fuel filter caution light?

A

A pressure switch on the gascolator if the strainer becomes contaminated

66
Q

What illuminates the AUX Fuel Pump light?

A

A pressure switch downstream of the aux fuel pump when the aux fuel pump output pressure is low.

Robinson R44 (5 decks)

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