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Beech 76 Duchess > Systems > Flashcards

Systems Flashcards

1
Q

Vne

A

194 Kts

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2
Q

Vno

A

154 kts

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3
Q

Va

A

132 kts @ 3900 lbs
116 kts @ 3000 lbs

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4
Q

Vfe

A

120 kts up to 20 degrees
110 kts for full flaps

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5
Q

Vle

A

140 kts

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6
Q

Vlo

A

112 kts

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7
Q

Vmc

A

65 kts

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8
Q

Vso

A

60 kts

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9
Q

Vsi

A

70 kts

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10
Q

Blue radial

A

85 kts

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11
Q

Vyse

A

85 kts

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12
Q

Vxse

A

85 kts

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13
Q

Vrotation

A

71 kts

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14
Q

Vsse

A

71 kts

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15
Q

Max Zero Fuel weight

A

3500 lbs

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16
Q

Max Ramp weight

A

3916 lbs

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17
Q

Max takeoff weight

A

3900 lbs

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18
Q

Max landing weight

A

3900 lbs

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19
Q

Max Baggage in Baggage Compartment

A

200 lbs

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20
Q

Max load factors, flaps up

A

-1.52G to 3.8G

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21
Q

Max load factor flaps down

A

2 G

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22
Q

Total fuel

A

103 g

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23
Q

Total usable fuel

A

100 g

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24
Q

Fuel grades usable

A

100 or 100LL

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25
Q

Fuel flow

A

9g @ 23 / 2300 rpm
11g @ 25 / 2500 rpm

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26
Q

Max slip duration

A

30 seconds

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27
Q

Max starter duty time

A

30 Seconds on, 2 mins off

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28
Q

Service Ceiling - ISA, both engines

A

19 600 ft @ 3900 lbs

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29
Q

Service Ceiling ISA single engine

A

6200 @ 3900 lbs
10 300 @ 3400 lbs

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30
Q

Oil capacity

A

8 qts max

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31
Q

Engine type

A

Lycoming O-360 and LO-360

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32
Q

engine horsepower

A

180 hp @ 2700 rpm

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33
Q

Propeller

A

Full feathering
Constant speed
Adjustable pitch
76 inch
2 blade Hartzell
counter rotating

34
Q

Brake system

A

Hydraulic disc brakes on main wheels
Hydraulic fluid MIL-H-5606 (red)
Toe pedal operated

35
Q

Brake fluid reservoir location

A

left side of forward cabin bulkhead

36
Q

Landing gear description

A

Tricycle
Retractable
Electrically driven hydraulically actuated

37
Q

Landing gear safety switch

A

located in pitot sytem
speeds less than 59-63 kts open landing gear circuit to prevent inadvertent gear retraction

38
Q

Landing gear CB

A

2 - one for the motor and one for the control

39
Q

Gear retraction process

A

Electric motor rotates pump CW
Forces hydraulic fluid through manifold to the retract side of the system
Pressure switch automatically shuts off motor when system reaches 1550 psi +/- 100
If pressure drops to 1250 or less the pressure turns the motor back on until it reaches 1550 psi
Uplock check valve in the pump retains pressure to hold gear up

40
Q

Gear Extend process

A

Electric motor rotates CCW
Forces hydraulic fluid through manifold to extend side of the system
Main gear downlock accomplished by overcenter travel of spring held side brace
Nose gear downlock accomplished by overcenter travel of drag link and mechanically actuated downlock

41
Q

Emergency landing gear process

A

Pop Gear Motor CB
Put gear handle in down position
Slow down below 100 kts
release hydraulic pressure in bypass valve by turning it 90 degress CCW

42
Q

Throttle warning system

A

If MP less than 12 (POH says 16-18), gear horn will sound

43
Q

Landing gear warning horn

A

If MP < 12”
Flaps > 16 degrees
Use same landing gear warning horn

44
Q

Landing gear time delay relay

A

30 seconds
Incorporated into the electric circuitry of gear system to prevent continuous operation
De-energizes gear up relay only
Reset by putting gear handle down then up

45
Q

Tire pressures

A

38 psi (all)

46
Q

Landing gear shock struts

A

Oleo on nose
Shock absorbers on mains

47
Q

Stall warning vanes

A

2
Left wing 0 - 16 degree flaps
Right wing 17-35 degree flaps

48
Q

Flaps

A

Single slotted fowler flaps
0-35 degrees
Electrically operated / actuated
Single flap motor located underneath rear pax compartment
Flaps connected via hollow interconnect torque tube through fuselage

49
Q

Fuel quantity indicators

A

Each tank has 2 float type fuel quantity sensors to transmit fuel quantity to fuel gauges in cockpit

50
Q

Min fuel required for takeoff

A

18 g (9g / tank)

51
Q

Which cylinders are primed w/ primer

A

1, 2, 4

52
Q

What cylinder has manifold pressure gauge

A

3

53
Q

What cylinder has CHT gauge

A

3

54
Q

Carburetor type

A

float type

55
Q

Primer solenoid

A

Electrically operated
Actuated by push to prime
Battery a fuel pump must be on

56
Q

Fuel tank vents

A

caps
fuel vents under wing

57
Q

How many fuel pumps

A

4
2 engine driven
2 electric driven

58
Q

Aux fuel pumps use

A

Start, taxi, takeoff, landing, emergency ops

59
Q

When can fuel cross feed be used

A

level flight only in emergency situations
either engine can consume fuel from the opposite tank

60
Q

Fuel drains

A

8, 4 per wing

61
Q

Battery

A

1 x 24V 15.5 amp battery

62
Q

When is battery used

A

Start, to power bus bar before alternators online
Emergency in event alternator failure

63
Q

Alternators

A

2 x 28V 55 amp alternator AC current rectified to DC current in electrical system

64
Q

Self excitation

A

Normally, alternator field is stimulated by current drawn from battery HOWEVER
Alternators in BE-76 have self excitation, meaning the provide current to the electrical system without external power (battery) to stimulate the alternator field
Comes on at 1200-1400 rpm, battery is then no longer needed
Important if complete electric failure and need to isolate battery, alternators will cont to function as usual and power their respective busses
Load carrying ability will be lower though - up to 80% at 2300 rpm, 50% @ 12-1400 rpm

65
Q

Loadmeters

A

2
Marked in percentage to show portion of max current available (55 amps) being drawn from each alternator

66
Q

Loadsharing

A
  • Bus tie fuse
  • Battery bus bar
  • Paralleling circuit between voltage regulators

bus tie and battery bus bar allow a single operating alternator to support the load of both alternator bus bars

67
Q

Most direct tie between left and right alternator bus bars

A

Bus tie fuse
30 amp
establishes limitation on the amount of electrical load we can carry on the alternator out bus bars (less than 30 amp)
Minimal electrical load should be imposed so that bus tie fuse doesn’t blow

68
Q

Battery bus bar

A

Also ties together left and right alternator bus bars though independent bus isolation CB (50 amp)
In the event of a bus tie failure, battery bus bar is now our last tie between left and right alternator bus bars
Must ensure load is less than 50 amp

69
Q

Undervoltage

A

Alternator output drops 4 +/- 0.1 below bus voltage
Undervoltage light will come on
Loadmeter will be zero
Affected alternator become an additional load for working alternator until the failed alternator field switch is turned off

70
Q

Overvoltage

A

Alternator output exceeds bus voltage by 4 +/- 0.1
Overvoltage relay will open the circuit to affected alternator
Voltage will drop to zero
Alternator is effectively switched off

71
Q

Lock pins

A

prevent engine from feathering during ground ops below 1000 rpm

72
Q

Propeller pitch settings

A

Feathered = 81 degrees
Low 12.1
High 17

73
Q

Feathering

A

Release gov oil pressure to drain oil back into engine as well as accumulator
Springs, nitrogen and counterweights help bring propeller to feather
3-10 seconds

74
Q

Unfeathering

A

Repositioning the governor to normal flight range
Closes lock valve to oil sump and opens lock valve from the accumulator, releasing trapped oil pressure from accumulator to bring prop to lower pitch higher rpm setting

75
Q

Underspeed condition

A

Level flight to a climb
Engine rpm drops, fly weights drop in, opening pilot valve, letting oil into the system pushing piston forwards resulting in engine increasing rpm to original rpm setting

76
Q

Overspeed condition

A

Level flight to a dive
Engine rpm increases, fly weights out, lifting pilot valve allowing oil out, piston assisted by feathering spring, nitrogen and counterweights pushes blades to higher pitch, lower rpm

77
Q

Speeder spring

A

set by pilot for rpm desired - increases / decreases tension on fly weights

78
Q

Accumulator

A

Air side charged with nitrogen
Oil side is charged by prop governor and stores oil at governor pressure of 290 psi
When prop unfeathered, oil is released from the accumulator to the prop hub to move blades to low pitch
Windmilling engine causes governor oil pressure to rise again, completing unfeathering

79
Q

Heater

A

45 000 btu janitrol combustion heater
Located in right nose compartment
Use 2/3 g of fuel / hour from right tank / hour

80
Q

Heater temp limit

A

300 F
Overtemp Switch shuts off the heater when this temp is exceeded
Not resettable in flight
Cabin air should be open only 1/2 way with heater on or else heater will be deactivated to prevent overtemp

81
Q

Cabin air blower

A

Shuts off when gear is retracted due to connection with nose gear down limit switch
Should be off in flight
Heater should be put to blower only after landing to cool heater before shutting it down

Beech 76 Duchess (1 decks)

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