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Flying PNG > DHC-6 Twin Otter > Flashcards

DHC-6 Twin Otter Flashcards

1
Q

How many emergency exits?

A

6 -
2 pilot doors
2 removable exit doors in row 2
2 rear doors

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2
Q

Maximum landing weight?

A

5579kg / 12,300lbs

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3
Q

Starting temp limits?

A

1090° for 2 seconds, then below 980° (925° SOPs)

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4
Q

Takeoff Power/T5/Np/Ng Limits? (300)

A

Torque = 50psi (reduce 1psi for every 1000’ above SL)
T5 = 725°
Np = 96%
Ng = 101.5%

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5
Q

Climb Power/T5/Np/Ng Limits? (300)

A

Torque = 45psi (reduce by 1psi for every 1000’ past 5000’ amsl)
T5 = 695°
Np = 96% (use 85% for noise)
Ng = 101.5%

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6
Q

Cruise Power/T5/Np/Ng Limits?

A

Torque = 40psi (reduce 1psi for every 1000’ past 10,000’)
T5 = 675°
Np = 96% (use 75%)
Ng =??

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7
Q

Minimum battery voltage for start?

A

24V (some docs state 23V)

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8
Q

Flaps are actuated how?

A

Hydraulically by a lever on the cockpit roof

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9
Q

What percentage of air is used for combustion/cooling?

A

25% combustion, 75% cooling/bleed etc

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10
Q

Fuel crossfeeding?

A

No crossfeeding between tanks is available, but one tank can feed both engines

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11
Q

Max takeoff weight?

A

5670kg / 12,500lbs

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12
Q

Front, rear and cabin loading weights/limits?

A

For long nose Hevilift aircraft:

Front locker = 136kg & 45kg/sqft loading
Rear locker = 226kg & 45kg/sqft loading
Rear shelf = 68kg (takes away from the 226kg limit)
Cabin = 91kg/sqft loading

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13
Q

How many turbines? What do they do?

A

2 - power and compressor turbine
*Power turbine runs the reduction gearbox and propeller
*Compressor turbine runs the compressor assembly, accessory gearbox and engine driven fuel pump

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14
Q

How many compressors? What type?

A

4 total, 1 centrifugal compressor and 3 axial compressors with stators in between

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15
Q

What systems does the hydraulic system supply?

A

Wing flaps
Nose wheel steering
Brakes

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16
Q

Hydraulic accumulators function?

A

Stores a small reserve of pressure and absorbers shock in the system from the hydraulic pump.

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17
Q

Hydraulic system location?

A

Underneath cockpit floor, rearward of nose wheel, accessed by panels on exterior of aircraft.

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18
Q

Flap/elevator interconnect tab?

A

Right elevator inner trailing edge tab:
Reduces trim needed when extending flaps beyond 8°

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19
Q

Beta reverse valve?

A

When the CSU is unable to maintain selected prop speed, BRV will restrict oil supply through approx +21° to stop the blade angle going below +17° in flight and +11° at idle in the power lever forward range.

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20
Q

Emergency Equipment Locations:
Oxygen
Fire extinguishers
Torch
First aid kits
Crash axe
Survival kit
Life jackets

A

*Oxygen - cockpit RHS
*Fire extinguishers - cockpit RHS & rear cabin
*Torch - cockpit
*First aid kits - cockpit & rear cabin
*Crash axe - cockpit RHS
*Survival kit - rear cabin
*Life jackets - under each seat

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21
Q

Hydraulic system is powered by what?

A

Left DC bus

22
Q

Minimum oil pressure acceptable to complete a fight is?

A

40psi

23
Q

Battery location and voltage?

A

Under the rear baggage compartment floor, 24V for 28V system.

24
Q

Is the hydraulic reservoir pressurised? What does it do?

A

Non pressurised, supplies fluid to the electric and hand pumps

25
Q

You shouldn’t move the power levers into reverse without the engines running because?

A

It can damage linkages

26
Q

With engines off, battery voltage can be checked by..

A

Looking at the DC voltmeter

27
Q

Describe the fuel tanks

A

Two fuselage tanks, one forward, one aft, both rubber and comprised of 4 cells each, 1 cell per tank is a collector tank which is fed by an ejector pump, the collectors feed the engines via boost pumps

28
Q

Describe the components of each fuel cell

A

Forward tank cells (all have fuel sensor)
1) filler, no flapper, ejector outlet
2) drilled flapper
3) drilled flapper
4) collector, flapper, 2 x boost pumps, fuel low level float switch, fed by ejector pump from other cells

Aft tank cells (all have fuel sensor)
5) collector, flapper, 2 x boost pumps, fuel low level float switch, fed by ejector pump from other cells
6) drilled flapper
7) filler, no flapper
8) drilled flapper, ejector outlet

29
Q

Which tank feeds which engine?

A

Forward tank = right engine
Aft tank = left engine

30
Q

Fuel capacity?

A

1167kg / 2574lb TOTAL
1156kg / 2548lb USABLE

*Forward tank = 691L usable
* Aft tank = 755L usable

31
Q

Fuel burn and endurance?

A

270kg/hr aprrox or 600lb/hr
4.25 hours endurance approx

32
Q

What indicates that a fire bottle has been discharged?

A

One of the two coloured disks will have popped from the side of the engine nacelle, yellow for pilot activation red for thermal activation

33
Q

Main power supply in flight?

A

Two starter-generators

34
Q

How many inverters and how many used at a time?

A

Two inverters, one used at a time (the other remains in standby).

If S.O.O is incorporated or on 310 then both work simultaneously, powering a bus each

35
Q

Pitot static sources, where are the and what do they feed?

A

1 pitot and 2 static either side of fuselage, just forward of cockpit doors.

Left instruments is left pitot and lower static
Right instruments is right pitot and upper static

36
Q

Stall detector locations/details?

A

*Two on leading edge of left wing *Powered by DC bus
*Lower vane operates always
*Upper vane operates when flaps more than 12°
*Sound 4-9kt above stall

37
Q

An illuminated FIRE Pull t-handle indicates?

A

One of the sensors is hot (check this one)

38
Q

If the power (AC) to the fuel gauges is lost, what will they indicate?

A

The level of fuel at the time the power is lost (AC Lies, DC Dies)

39
Q

Fire detection system is powered by which bus?

A

Left DC

40
Q

Describe the two hydraulic leak scenarios

A

Leak upstream of brake system - will lose flaps and nose wheel steering

Leak within brake system - will lose everything

41
Q

Oil dipstick limit?

A

2.5qt below maximum/full

42
Q

What happens if boost pump 1 fails?

A

System will automatically change to boost pump 2, light for 2 will briefly come on then go out

43
Q

Beta backup valve?

A

Prevents the prop from going below +9° whenever the power levers are forward of idle.

Electrically activated via a feedback ring and microswitch, will cut off the oil supply so that the counterweights coursen the blade angle.

Will cycle on and off between +9° and +11°.

Will deactivate for reverse by a microswitch in power level assembly.

44
Q

How does the pitot/static system work when the emergency selector is set to EMER?

A

Both sides of instrument panel will use Co-pilots static source

45
Q

Fire warning is provided by?

A

Illumination of a FIRE PULL handle and sounding of the fire bell

46
Q

Vy
Vx
Vyse
(IAS)

A

Vy = 100kt, flap 0°
Vx = 87kt, flap 0°
Vyse = 80kt, flap 10°

47
Q

Vmo?

A

166kt to 6,700’

Then 3kt reduction per 1000’

48
Q

Vmca
Vmcg
With autofeather and without

A

Vmca = 64kt (68kt without autofeather), flap 10°
Vmcg = 50kt, flap 10°

49
Q

How does autofeather affect takeoff speeds?

A

If autofeather is inop, add 4kt to Vr, V1, V2 and Vmca

50
Q

Vfe Speeds?

A

Vfe 10° = 103kt
Vfe 10°-37.5° = 93kt

51
Q

Take off calls and responses

A

“Autofeather armed”
“Power set”
“40kt” - “checked”
V1
Rotate
400ft & above 91kt/clear of terrain - “terrain clearance” - “flap zero”
“flaps zero” (once retracted)
“set climb power” - “climb power set”

52
Q

Va/Vb

A

132kt

Flying PNG (3 decks)

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