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MEP Theory > BE76 > Flashcards

BE76 Flashcards

1
Q

Vy

A

85kts

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2
Q

Vr

A

71kts

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3
Q

Max oil pressure - red line

A

100psi

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4
Q

Minimum oil pressure

A

25psi

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5
Q

Fuel usable quantity

A

100 USG

378 Litres

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6
Q

Cylinder head temp

A

500 degrees Fahrenheit

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7
Q

Max oil temp

A

245 degrees Fahrenheit

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8
Q

Max continuous RPM

A

2700rpm

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9
Q

Max crosswind limit

A

25kts

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10
Q

Single engine approach speed

A

85kts

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11
Q

Vref

A

75kts normal

80kts flapless

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12
Q

Vat

A

75/76kts

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13
Q

Centre of gravity at 3250lbs

A

106.6 inches aft of datum

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14
Q

Centre of gravity at 3900lbs

A

110.6 inches aft of datum

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15
Q

Vs0

A

60kts

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16
Q

Glide airspeed

A

95kts

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17
Q

Vs1

A

70kts

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18
Q

Vfe

A

120kts

110kts ( full flap)

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19
Q

Vle

A

140kts

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20
Q

Manual gear extension speed

A

100kts

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21
Q

Vne

A

194kts

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22
Q

Vx

A

71kts

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23
Q

Vyse

A

85kts

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24
Q

Vxse

A

85kts

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25
Q

Vtoss

A

75kts (book)

85kts (taught)

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26
Q

Vy

A

85kts

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27
Q

Vno

A

154kts

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28
Q

MTOW

A

3900lbs

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29
Q

MRW

A

3916lbs

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30
Q

Vmca

A

65kts

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31
Q

Va

A

132kts

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32
Q

MLW

A

3900lbs

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33
Q

Turbulent operating speed 3800lbs

A

135kts

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34
Q

Max baggage compartment weight

A

200lbs

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35
Q

Stages of flap

A

4

Up- 10- 20- Down

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36
Q

How is the landing gear system controlled?

A

It’s electrical-hydraulic mechanical system - electric motor drives a hydraulic pump which operates actuators mechanically raising and lowering the landing gear

37
Q

Max tyre pressures

A

Main wheel and nose wheel - 38psi

38
Q

Suction normal operating range (green arc)

A

4.3 - 5.9 inches Hg

39
Q

Minimum fuel in each wing before takeoff

A

9 US Gallons

12 US Gallons - BCFT ops manual

40
Q

What are the 3 main effects of lowering the flap in flight?

A

Nose lowers
Airspeed reduces
Stall speed reduces

41
Q

What is the approximate reduction in climb performance with one engine out?

A

80% reduction

42
Q

What is the propeller to engine drive ratio?

A

Direct drive 1:1

43
Q

On a constant speed prop- RPM is increased by increase in power or nose down attitude, what happens to the blade angle?

A

The CSU moves the propeller to a coarser pitch- to absorb the extra energy
Flyweights spin outwards lifting the landed valve and allow oil to drain away from hub, retreating the piston

44
Q

Power is decreased what happens to the propeller blade angle?

A

It is moved to a finer pitch via the CSU - fly weights spin inwards allowing oil into propeller hub pushing on the piston

45
Q

What does the electrical system consist of?

A

A 28v DC system

Two engine driven alternators and two voltage regulators (regulate load sharing and maintain 28v)

A 24v battery

Two main bus bars supplied by each alternator

46
Q

What is the blade angle in the fully feathered position?

A

81 degrees (+- 1 degree)

47
Q

Where is the C of G reference datum?

A

Located 129.37 inches forward of centre wing spar jack points

48
Q

Propeller diameter

A

76 inches

cut off permitted at 74 inches

49
Q

How many inches aft of datum is the Leading Edge MAC?

A

99.08 inches aft of datum

50
Q

MZFW

A

3500lbs

51
Q

How many inches aft of datum is the Leading Edge MAC?

A

99.08 inches aft of datum

52
Q

Minimum oil capacity for departure?

A

6 US Quartz for departure

53
Q

Max oil capacity

A

8 US Quartz

54
Q

Where is the C of G reference datum?

A

Located 129.37 inches forward of centre of wing spar jack points

55
Q

Manifold Pressure Normal Operating Range ( in.Hg)

A

15-29.6 in.Hg

56
Q

Maximum sideslip duration

A

30 seconds

57
Q

During prop feather checks, why should we avoid RPM dropping below 1000RPM?

A

Below 1000RPM the centrifugal latches engage to feather the propeller. To make sure the propeller feathers past the gates.we dint want it to go this far.

58
Q

With landing gear retraction, after how long with continuous hydraulic pump operation will the time relay disconnect the pump motor from its electrical supply?

A

30 seconds

59
Q

After engine start, oil pressure must rise to what pressure (psi) within how many seconds?

A

Above red radial and into normal operating range (60-100psi) within 30 seconds (25psi minimum)

60
Q

Min/max Fuel pressures (psi)

A

Min 0.5 psi

Max 8.0 psi

61
Q

Which cylinders are connected to the engine priming system?

A

Cylinders 1,2 and 4 for each engine

62
Q

What in volts and amperes is the electrical power supplied to the bus bars by the alternators?

A

28V

55 Amperes supplied by each alternator

63
Q

What is the aft C of G limit with landing gear extended at MAUW?

A

117.5 inches aft of datum

64
Q

In what flap configuration will port wing stall sensing vane trigger if aircraft approaches a stall?

A

When the flaps are above 16 degrees ( 16 degrees or less)

65
Q

In what flap configuration will the starboard wing stalling sense vane trigger an alert if the aircraft approaches a stall?

A

When the wing flaps are below 16 degrees ( 16 degrees or more)

66
Q

What devices are fitted between the battery bus bar and main left and right busbars?

A

One main isolating circuit breaker/ isolator each

67
Q

What is the maximum alternator load capacity and at what engine RPM?

A

80% at approx 2300RPM

68
Q

What performance class is the BE76?

A

Class B

69
Q

How is the alternate static air source operated?

A

Pushing lever to ON position (lower side well adjacent P1) open valve- used when normal static has been obstructed

70
Q

Following an engine failure, the cause of which cannot be determined, at what point would you consider using the cross feed capability?

A

After dead engine secured and live engine checked- phase 2 checks

71
Q

Assuming all mandatory inspection requirements what is the life expectancy of basic wing structure (hours)

A

20,000 flight hours

72
Q

If the Janitrol heater trips out in flight, can it be reset?

A

No, it can only be reset on ground by an engineer

73
Q

Self excitation of alternators load

A

Linked to engine RPM , feature not come on until approx 1200-1400RPM with load capability of approx 50%

74
Q

Describe the system to prevent inadvertent gear retraction on the ground

A

Safety pressure switch measures dynamic pressure.

When dynamic pressure is between 59-63kts deactivates the hydraulic pressure pump

75
Q

Describe the Janitrol heating system on the BE76

A

The Janitrol heater is a fuel combustion air heater located on front right of aircraft nose. It is used for cabin heating and windshield defrosting

Uses approx 2/3 USG per hour from right wing fuel system

76
Q

What are the maximum positive and negative load factors at MAUW?

A

Positive 2.0G ( flaps down)
3.8G (flaps up)

Negative -1.52G ( flaps up)

77
Q

What is the minimum height of occupants in either of the front seats?

A

4’ 7” to be able to access rudder pedals with chair forward

78
Q

What is the checklist drill for Crossfeed?

A 
Aux pump (live engine) - On 
Fuel cock (dead engine)- Off 
Fuel cock (live engine) - Crossfeed ( level flight, cruise only) 
Aux pump (dead engine) - Off

From Phase 2 checks

79
Q

How is the engine oil pressure boosted to operate the CSU propeller system?

A

A supplementary pump is found in the CSU unit- liked gear driven

80
Q

What gases are produced by a lead-acid battery when it is being charged?

A

Hydrogen gas can be produced when the lead acid battery is being charged

81
Q

Below what RPM will the propeller fine pitch latches engage?

A

Below 700-800RPM

82
Q

What types of fuel can be used and appropriate colours?

A

100LL Blue Avgas

100 Green Avgas

83
Q

When we check the propeller function of the ground during engine run ups, what indications might we expect to see on the instruments?

A

MP increase as Prop RPM is reduced- MP relationship with torque
Coarse blade - torques goes up - RPM reduced - slight variation of MP maybe.

84
Q

What would be the significance of the red gear ‘in transit’ light remains on following gear retraction after takeoff, what subsequent actions might be required?

A

This could indicate the gear is in an intermediate position- potentially unretracted and not locked and safe - recycle gear

85
Q

How is the undercarriage held in the up/ retracted position?

A

Hydraulic pressure- it is held in place via hydraulic pressure which is maintained in the actuator

86
Q

How is the undercarriage locked in the down/extended position?

A

Retraction of the actuator moves the gear A frame - gear locks at elbow of gear brace into overcentered position

87
Q

What does the fuel system consist of?

A

Each fuel tank (51.5 USG capacity)
Fuel flow -
Tank-fuel strainer-fuel selector- check valve- engine driver fuel pump -carburettor

88
Q

What is the emergency descent checkist drill?

A

Props - 2700rpm
Throttles- Idle
Airspeed- 140kts
Undercarriage- Down

89
Q

With regard to the red ‘gear in transit’ warning light, what is the significance of this light illuminating momentarily in flight?

A

It signifies a drop in system pressure, re-pressurisation occurs, if it keeps happening it could signify a leak.
Pull gear motor CB to avoid overheating

MEP Theory (4 decks)

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