Systems Flashcards

1
Q

What are the conditions that certificated Vmc? 23.149

SMACFUM

A

Vmc certification requirements 23.149

S - Standard day at sea level

M - Max power w/ one engine opertating

A - Aft CG

C - Critical engine windmilling

F - Flaps up/gear up

U - Up to 5° bank

M - Most unfavorable weight

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2
Q

S - Standard day at sea level

A

air is more dense, allowing for engine to perform better, increasing thrust, causing a greater force toward the dead engine, requiring more rudder to overcome that force.

(BAD for VMC)

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3
Q

M - Max power w/ one engine opertating

A

Max power means more performance & more yaw towards inoperative engine. This requires more rudder input, to counteract yaw. This increases VMC, which is bad b/c we want to maintain control at lowest speeds

(BAD for VMC)

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4
Q

A - Aft CG

A

Aft CG means less arm, less arm means less leverage for rudder to counteract yaw. Less rudder authority means VMC increases.

(BAD for VMC)

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5
Q

C - Critical engine windmilling

A

Critical engine windmilling causes more drag than if it was feathered. More drag on the inoperative engine means more yaw toward the inop engine. Therefore more rudder is needed to counteract this yaw. Therefore VMC increases

(BAD for VMC)

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6
Q

F - Flaps up/gear up

A

Flaps up/Gear up means less drag, which you would think is good for VMC, but really it is bad for VMC. Flaps help stabilize a/c and reduce stalling speeds. Gear down gives the a/c a
“keel effect”, which helps keep it straight, just like a kayak in the water. Therefore flaps up & gear up negatively affects our vmc speed

(BAD for VMC)

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7
Q

U - Up to 5° bank

A

provides a zero side slip condition, a/c creates less drag when banked into the operative engine.

(split the ball and bank 5° into operating engine). This brings VMC down which is GOOD

(GOOD for VMC)

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8
Q

M - Most unfavorable weight

A

Vmc increases as weight decreases, therefore the lightest legal weight is unfavorable.

(BAD for VMC)

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9
Q

What is the critical engine?

A

the engine that if failed, would cause the most trouble to the pilot. The engine that if failed, adversely affects the aircraft the most. For a conventional twin, the LEFT is the most critical.

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10
Q

What is the critical engine for the C-130H?

A

The furthest LEFT engine

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11
Q

PAST: Understanding which engine is critical and understand which engine creates the most adverse effect and why.

A

P - P factor (yaw)

A - Accelerated Slipstream (roll)

S - Spiraling Slipstream (yaw)

T - Torque (roll)

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12
Q

P - P factor

A

failure of the left engine will cause MORE loss of directional control, than the loss of the right engine b/c of the LONGER ARM of the right (operative) engines arm’s thrust causing a/c to yaw.

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13
Q

A - Accelerated Slipstream

A

propwash from the descending blade going over the wing results in lift, causing a/c to roll; bigger roll from right engine.

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14
Q

S - Spiraling Slipstream (yaw)

A

Descending blade causes more thrustin turn causing LOW PRESSURE,

Ascending blade causes high pressure; High pressure always wants to go to low pressure.

Spiraling slipstream goes towards the right b/c high to low pressure.

Spiraling slipstream on the left engine contacts the rudder which gives us more rudder authority,

counteracting yaw towards inoperative engine.

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15
Q

T - Torque (roll)

A

Newton’s third law: for every action, there is an equal and opposite reaction.

If the right engine fails, this left roll tendency will help us maintain control and resist the roll towards the right, inoperative engine, caused by asymmetric thrust. If the left engine fails, the left roll tendency by torque will add to the left turning force caused by asymmetric thrust into the inoperative engine. This makes it much more difficult to maintain directional control, making the left engine the critical engine.

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16
Q

PA 44-180 Seminole Engine (LHAND)

A

L - Lycoming (O-360, 4 cylinder, 360 cubic inch)

H - Horizontally opposed (pistons oppose each other)

A - Air cooled

N - Normally Aspirated (No turbo or supercharger)

D - Direct Drive (crank shaft connected directly to the propeller)

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17
Q

When does Carburetor Icing occur?

A

1) Visible moisture (clouds)
2) -5° to 20° C or (20° to 70° F)

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18
Q

What causes carburetor icing and what is the solution?

A

Cause = high air velocity through the venturi and the absorption of the heat from this air by vaporization of the fuel

Solution = turn on carburetor heat and adjust mixture for maximum smoothness

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19
Q

PA44-180 Propeller type

A

1) Hartzell two bladed controllable pitch
2) Constant speed
3) Full feathering metal propellers

20
Q

What is controllable pitch?

A

ability to control engine RPM by varying the pitch of the propeller blades regulated by the propeller governor.

21
Q

Blue handle forward/aft does what?

A

Blue handle forward = oil pressure regulated by the prop governor, drives a piston, which moves the blades to a low pitch-high RPM (unfeathered) position.

Blue handle aft = oil pressure is reduced by the prop governor. This allows a nitrogen-charged cylinder, spring, and centrifugal counterweights to drive the blades to a high pitch-low RPM (feathered) position

22
Q

What is a full feathering prop?

A

allows propeller to be in alignment with the relative wind (feathered), this reduces the drage caused by the blade area exposed to the wind.

To feather, move blue propeller control AFT.

Seminole is equipped wiht cenrifugal stop pin that prevents the propeller from feathering below 950 rpm. This allows the propeller to remain in a low pitch upon engine shutdown, which prevents excessive loads on the engine starter during the next engine start.

23
Q

What is propeller underspeed?

A

when climbing, if you don’t adjust your engine controls, and you pitch the airplane up, your engine has to work harder and it will start to slow down. This situation is called underspeed.

But you’re airplane is smart. As soon as this happens, the flyweights begin to wall inward b/c they slow down as well. When this happens, the pilot valve moves down and oil flows out of the propeller hub, reducing the pitch of the blades.

24
Q

What is propeller overspeed?

A

When you pitch the airplane down, the governor takes over again. By pitching down and not touching the engine controls, the engine will start to speed up, and the flyweights will fly outward, due to centrifugal force. As soon as that happens, the pilot valve will raise, oil will flow into the prop hub, and the pitch of the blades will increase, slowing the engine to your set speed.

25
Q

What happens when you go FULL FWD on the Blue prop lever?

For example when you’re coming in to land

A

Low pitch/High RPM setting

By moving the lever forward,it turns the screw to the right and increases the pressure on the speeder spring, thus causing the flyweights to fall in and raise the pilot valve, allowing oil to escape the prop hub and go back into the sump, allowing prop to go into the low pitch/High RPM setting.

Practically, you give yourself more ‘instantaneous’ power, because the engine doesn’t need to work as hard to turn the prop, it takes smaller “bites” of air. That’s something that’s useful if you need to go-around.

26
Q

What happens when you bring the the Blue prop lever aft?

For example when you’re at cruise altitude prop goes to 2300 rpm

A

High pitch/Low RPM setting

When you bring the prop lever aft, the screw will turn left, releasing tension on the speeder spring. This will cause the flyweights to fly out b/c of the less spring tension, lifting the valve and pumping oil into the prop hub, allowing prop to go into the High pitch/Low RPM setting

Practically, you adjust to prop to take a bigger ‘bite’ of air, in turn, increasing the torque required of the engine to swing the prop around.

With that increase in torque, the engine slows down, which in cruise flight is a good thing. It means your engine isn’t spinning as fast, your fuel efficiency is increased, and the engine parts won’t wear down as quickly. Think of it kind of like switching to a higher gear on your bike. You need to push a little harder with your legs, but you don’t need to pedal nearly as fast.

27
Q

PA44-180 Landing Gear?

A

Hydraulically actuacted

Fully retractable

Tricycle type landing gear

28
Q

How does the PA44-180 Landing Gear work?

A

An electrically powered reversible hydraulic pump, provides hydraulic pressure.

29
Q

What keeps the gear up?

A

Hydraulic pressure

30
Q

What keeps the gear down?

A

Springs, downlock hooks, and gravity

31
Q

What does the squat switch do?

A

1) Prevents gear retraction on the ground
2) When squat switch is engaged, it prevents electrical current from reaching the hydraulic pump
3) When airborne the strut is fully extended, closing the siwtch that allows current to reach the hydraulic pump

32
Q

What to do if gear won’t come down?

A

1) Pull landing gear emergency extension (releases hydraulic pressure holding it up)
2) Do a “G Load” maneuver to knock it down
3) If it still does not want to come down, try to secure engine before doing a belly up landing

33
Q

Landing gear lights does not show 3 green?

A

1) Switch the light knobs
2) Manifold pressure to below 15”
3) Flaps 25-40 deg
4) On the ground put gear in “UP” position (maintenance personnel only)

34
Q

What kind of brakes does the PA44-180 have?

A

Hydraulically actuated disk brakes, independent from the landing gear

35
Q

PA-44-180 Flaps

A

Manual flap system with settings of 0,10,25,40. spring loaded to return to 0 deg position

36
Q

Vacuum System

A

(2) Engine drive vacuum pumps that operates the attitude gyro & HSI.

Suction limits are 4.8-5.2” HG.

Failure of the vacuum pump is indicated by an annunciator panel light and a red light on the vacuum gauge itself. Failure of (1) pump should not cause the loss of any instruments b/c the remaining pump should handle the enitre vaccum demand

37
Q

Pitot Mast

A

combines the pitot tube and static port located under the left wing.

alternatic static source is located in the cabin under the left instrument panel, when using it, make sure the storm window, and cabin vents are closed, heater and defroster must be turned on, this will reduce the pressure differential btwn the cockpit and the atmosphere, reducing the pitot static error. Pitot static instruments are (Airspeed indicator, Altimeter, & VSI)

38
Q

How many Fuel pumps does the PA44-180 have?

A

4 total.

(2) Engine driven
(2) Electrically driven

39
Q

What are the (2) electrical fuel pumps used for?

A

engine start, takeoff, landing, and fuel selector changes

40
Q

Fuel System

A

100LL (blue) avgas, two tanks (one in ea engine), 55gal per tank, 1gal nonusable.

Total fuel 110gal, 108 usable.

Fuel selector, ON, OFF, X-FEED, when X-FEED is on, engine draws fuel from opposite tank. Fuel is NOT transferred from one tank to another.

41
Q

PA-44-180 Fuel diagram

A
42
Q

Electrical system

A
  • (2) Alternators @ 70 amps & 14 volts; push pull type circuit breakers
  • 12 volt 35 amp battery
43
Q

PA-44-180 Electrical Diagram

A
44
Q

PA44-180 Electrical System

A
45
Q

How does the vacuum system work?

A

Outside air is brought in through the filter, passes through the gyroscopic instruments, passes through the manifold check valve (pressure is measured at this time w/ the vac indicator), then moves down through the regulator (if pump is pulling too much suction, regulator will pull in air to keep pressure at 4.8-5.2” Hg), then through the pump and out.