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🛸 Private Pilot - ATP > Airplane Operations > Flashcards

Airplane Operations Flashcards

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Charter Pilot (Part 135) - Oral flashcards
1
Q

Stall

A

Occurs when the smooth airflow over the wing becomes turbulent, reducing lift. Results from a rapid decrease in lift caused by the separation of airflow from the wing’s surface brought on by exceed the critical AOA.

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2
Q

Attitude indicator

A

The only instrument that provides an instantaneous, direct indication of the airplane’s pitch and bank attitude.

The relationship of the miniature aircraft to the horizon bar is the same as the relationship of the real aircraft to the actual horizon. This instrument gives an instantaneous indication of even the smallest changes in pitch and bank attitude.

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3
Q

If you don’t maintain a constant glide speed in attempting to land in an emergency…

A

It is difficult to judge your gliding distance and landing spot. (Variations of gliding speed nullify all attempts at accuracy in judgment of gliding distance and the landing spot.)

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4
Q

VNO

A

Max structural cruising speed.

Piper Archer - 125 KIAS

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5
Q

VX

A

Best angle of climb.

Piper Archer - 64 KIAS

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6
Q

VY

A

Best rate of climb.

Piper Archer - 76 KIAS

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7
Q

VFE

A

Maximum flap extension speed.

Piper Archer - 102 KIAS

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8
Q

VSO

A

Stall speed in landing configuration.

Piper Archer - 45 KIAS

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9
Q

VA

A

Maneuvering speed.

Piper Archer - 113 KIAS at 2,550lbs; 89 KIAS at 1,634 lbs (G500 a/c)

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10
Q

VNE

A

Never exceed speed.

Piper Archer - 154 KIAS

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11
Q

VR

A

Rotation speed (start rotation)

Piper Archer - 60 KIAS

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12
Q

VS

A

Stall speed w/ zero flaps.

Piper Archer - 50 KIAS

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13
Q

VG

A

Best glide speed at max weight

Piper Archer - 76 KIAS

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14
Q

VLO

A

Maximum landing gear operating speed.

Piper Archer - N/A

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15
Q

Acceleration/Deceleration Error

A

The magnetic dip and the forces of inertia cause magnetic compass errors when accelerating and decelerating on easterly and westerly headings.

When decelerating at either of these headings, the compass indicates a turn towards the south. When accelerating on either of these headings, the compass indicates a turn toward the north.

ANDS - Accelerate = North, Decelerate = South

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16
Q

Effects of Excessive Weight

A

Reduces flight performance in almost every respect. Some of the most important deficiencies are:

  • Higher takeoff speed
  • Longer takeoff run
  • Reduced rate and angle of climb
  • Lower maximum altitude
  • Shorter range
  • Reduced cruising speed
  • Reduced maneuverability
  • Higher stalling speed
  • Higher approach and landing speed
  • Longer landing roll
  • Excessive weight on the nose wheel or tail wheel
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17
Q

White Arc on Airspeed Indicator

A

represents the flap operating range for an aircraft.

Lower limit represents the full flap stall speed, and upper limit provides the maximum flap speed.

Approaches and landings are usually flown at speeds within the white arc.

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18
Q

Green Arc on Airspeed Indicator

A

identifies a normal operating range. Most flying occurs within this range.

Lower limit is the power-off stall speed at the maximum takeoff weight in the clean configuration. Upper limit is the maximum structural cruising speed. (Do not exceed unless in smooth air.)

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19
Q

Yellow Arc on Airspeed Indicator

A

caution range.

Fly within this range only in smooth air and then only with caution.

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20
Q

Red Line on Airspeed Indicator

A

Never exceed speed.

Operating above this speed is prohibited since it may result in damage or structural failure.

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21
Q

Angle of Attack

A

The acute angle between the wing chord line and the direction of the relative wind.

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22
Q

A constant-speed propeller is more efficient than other propellers because:

A

It allows the selection of the most efficient engine RPM for the given conditions.

A constant-speed propeller converts a high percentage of brake horsepower into thrust horsepower over a wide range of RPM and airspeed combinations. Therefore, it is more efficient than other propellers.

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23
Q

Piper Archer max demonstrated crosswind component:

A

17 kts

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24
Q

Describe the PA-28-181 engine:

A

LHAND

Lycoming - manufacturer
Horizontally opposed - pistons oppose each other
Air cooled - engine cooled by air as opposed to liquid cooled
Normally aspirated - no turbo or supercharging to suck air in, air is just captured through intake
Direct drive - crankshaft is connected directly to the propeller

4 cylinder, 180 horsepower, carbureted, 2 magnetos to provide ignition, 8 spark plugs

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25
Q

What are the Piper Archer’s minimum and maximum oil capacities?

A

The maximum oil capacity is 8 quarts and the minimum oil capacity is 2 quarts. According to the POH Section 8.19. ATP policy is not to fly below 6.5 quarts.

26
Q

Describe the Piper Archer propeller:

A

Sensenich, fixed pitch (propeller’s blades pitch cannot be adjusted, therefore it will perform differently at different phases of flight), 76-inch,

RPM is adjusted by the throttle which controls how much fuel-air mixture is sent from the carburetor to cylinders

27
Q

Describe the Piper Archer electrical system:

A

28-volt DC electrical system and 24-volt lead-acid main battery. Electrical power is given by a 70-amp, engine driven alternator. Voltage regulator maintains a constant 28-volt output from alternator. Alternator output is displayed on a digital ammeter.

28
Q

Indications of a failed alternator in PA-28-181?

A

Zero reading on the ammeter, low bus voltage annunciator light will be illuminated.

29
Q

Describe PA-28-181 braking system:

A

Toe brakes on top of rudder pedals. Hydraulically-actuated disc brakes on main landing gear wheels. Both toe brakes and the parking brake have separate braking cylinders but share a hydraulic reservoir. Brake fluid reservoir is installed on the top left front face of firewall.

30
Q

Piper Archer flaps:

A

Slotted. Manual system.
Settings: 0, 10, 25, 40
Lever in center of the cockpit floor controls them.

31
Q

Piper Archer maximum takeoff, taxi, and landing weights?

A

Takeoff/landing: 2550 lbs
Taxiing: 2558 lbs

32
Q

Piper Archer maximum baggage capacity?

A

200 lbs

33
Q

Define Vx and Vy:

A

Vx - 64 KIAS, best angle of climb to get higher over a shorter distance if needed to clear obstacles
Vy - 76 KIAS, best rate of climb over a given time

34
Q

Aircraft equipment checks under FAR part 91?

A

AV1ATE

Annual Inspection - every 12 calendar months (A&P, IA)
VOR Check - every 30 days (for IFR)
100 Hour Inspection - every 100 flight hours (if for hire)
Altimeter/Static Encoder - every 24 calendar months (for IFR)
Transponder - every 24 calendar months
ELT - inspection every 12 calendar months, replace after 1 hour of cumulative use or after 50% of battery life

35
Q

Aircraft documents required?

A

SPARROWED

Supplements - manuals for additional equipment updates like avionics
Placards - list can be found in POH Section 2 Limitations
Airworthiness Certificate - doesn’t expire unless required equipment checks are not completed or ADs are not complied with
Registration - expires after 7 years as of January 2023 (before it was 3 years)
Radio Station License - needed if traveling internationally
Operations Manual - POH or AFM, tail-number specific
Weight and Balance Data - found in the POH
External Data Plate
Magnetic Compass Deviation Card

36
Q

Lost comms procedures?

A
  • Troubleshoot first. Check volume, headset ports, check frequency. If using Comm 1, see if Comm 2 will function instead and vice versa.
  • If none of these options work, continue transmitting. You may not be able to receive, but you might be able to transmit for other people to hear you.
  • Squawk 7600
  • Remain VFR.
  • Head to nearest uncontrolled airport. Overfly the field to see if there is anyone in the pattern.
  • Follow the flow of traffic and enter the pattern.
  • Land normally.
37
Q

Describe the pitot-static system.

A

Data is received through the pitot-static mast. The mast has three holes: the front collects RAM air, the bottom and back collect static air, while the bottom hole can also be used as a drain hole. In the Archer, this data is given to the Air Data Computer. These contribute to the Airspeed Indicator, the Vertical Speed Indicator, and the Altitude Indicator. Each of these gauges have an inner chamber made of lightweight, wafer-like movable material, and an outer chamber that surrounds the wafer.

In the Airspeed Indicator, RAM air is compared to static air. The static air fills the outer chamber, and the RAM air fills the inner chamber. As the airplane’s airspeed increases, more RAM air is collected by the pitot hole. The inner chamber expands as more RAM air fills it. As the inner chamber expands, the airspeed indicator increases and vice versa.

In the Vertical Speed Indicator, the static air is used. Static air fills the outer chamber, and a calibrated leak into the inner chamber causes the air in there to be about 3 seconds behind. So the gauge compares current static air to the static air 3 seconds before it. An increase in pressure indicates a downward trend, and a decrease in pressure indicates an upward trend.

In the Altitude Indicator, static air is compared to standard air pressure 29.92 in Hg. The inner chamber is set to 29.92 in Hg, and the outer chamber collects the static air to compare the two. As the static air pressure lowers, the Altitude Indicator indicates a higher altitude.

38
Q

Where is the alternate static source in the PA-28?

A

In front of the left pilot’s seat under the yoke. In the off position, the lever points to the right side of the cockpit (the right seat passenger). The pressure inside the cabin is lower than outside, so the altitude indicator will read slightly higher if on.

When using alternate static source, verify that storm window and cabin vents are closed. Turn cabin heater and defroster on.

39
Q

PA-28 fuel capacity? Unusable fuel? Fuel grade?

A

Fuel capacity - 50 gallons
Unusable fuel - 2 gallons
Fuel grade - Avgas 100LL (blue) or 100 (green)

40
Q

How many fuel pumps in PA-28?

A
  1. 1 engine-driven fuel pump and 1 electric fuel pump.
41
Q

When to use electric fuel pump?

A

During takeoff, taxiing, landing, and when switching tanks in cruise.

42
Q

Positions on fuel selector control?

A

R, L, and Off.

43
Q

PA-28 with G500, in the event of an electrical power failure, how to use standby attitude indicator?

A

Press power button and release once.

44
Q

PA-28 with G500, if the standby attitude indicator isn’t pressed within 60 seconds after battery failure?

A

A red flag will appear and the unit will shut down. Press and release power button once to power the unit.

45
Q

PA-28 with G500, where is the indication for a standard rate of turn?

A

Pink line will extend toward the inside of the turn near the heading indicator. Two tick marks on either side of the heading indicator represent varying degrees of standard rate turn. An arrow will appear if the rate of turn goes beyond standard.

46
Q

If AHRS failure, which indications will be no longer displayed on PFD? Which will still be visible?

A
  • Sky/ground representation is removed
  • Red X appears across attitude direction indicator.
  • Yellow “Attitude Fail” and “HDG” alert messages will appear on PFD.
  • A “TRK” message appears to the right of ground track at the top of the compass rose.
  • Rate of turn info is unavailable.
  • “HDG Lost” “HDG Fault” and “TRK Traffic” alert messages appear on MFD.

Airspeed Indicator, Altitude Indicator, and Vertical Speed Indicator will still be visible.

47
Q

How long does standby battery last in standby attitude indicator?

A

If fully charged, up to 1 hour.

48
Q

With loss of ADC, which instrument doesn’t have a back up?

A

Vertical Speed Indicator. Use known pitch attitudes with attitude indicator, power settings, and airspeeds to produce consistent rates.

49
Q

Will the engine continue to run with alternator and battery master switches off?

A

Yes, after start, the magnetos power the engine continuously independently of the alternator and battery.

50
Q

Describe the stall warning system:

A

A small tab on the leading edge of the left wing that activates within 5-10 knots above stall speed, causing the stall horn to emit a continuous sound.

51
Q

Describe the fuel system:

A

Two 25 gallon tanks (one gallon in each is unusable) on each wing, low wing structure requires a fuel pump to transfer fuel to engine. There is 1 engine-driven pump and 1 electric pump. Fuel tank selector rotates between selected fuel tanks. 100LL Avgas (blue). Electric fuel pump is used for all takeoffs and landings and when switching tanks during cruise flight.

52
Q

Explain how to change fuel tanks in cruise.

A

Check messages, if “switch tanks,” then turn fuel pump ON, rotate selector to next tank, check fuel pressure, fuel pump OFF, check fuel pressure.

53
Q

Describe landing gear system.

A

Fixed, tri-cycle type gear, with oleo struts providing shock absorption on all 3 wheels. Nose wheel damps nose wheel vibrations during ground ops and center nose wheel in air. Nose wheel is linked to rudder pedals by steering mechanism that turns nosewheel up to 20 degrees on each side of center.

54
Q

Piper Archer horsepower

A

180

55
Q

Piper Archer, fuel injected or carburetor?

A

Carburetor. As denoted by the absence of the “I” from the engine name O-360.

56
Q

Piper Archer, turbo-charged or normally aspirated?

A

Normally aspirated. Uses simple vent holes to funnel air into the engine, as opposed to a turbo charged engine that sucks more air in.

57
Q

Piper Archer, how are cylinders arranged?

A

Horizontally opposed.

58
Q

How is ignition provided?

A

The battery provides the power to start the engine. A gear pops out and rotates the flywheel which rotates the propeller and starts the four-stroke cycle in the cylinders. An impulse coupler in the left magneto, similar to a wound-up spring, provides extra power to the starter in this process.

59
Q

Pitot-static system failures, RAM air clogged, drain hole opened:

A

ASI reads 0.

60
Q

Pitot-static system failures, RAM air clogged, drain hole clogged:

A

ASI will act as an altimeter.

61
Q

Static port blockage:

A
  • ASI reads correctly at the same altitude blockage occurred
  • Altimeter freezes indication on the altitude it was blocked
  • VSI freezes on zero
  • Use alternate static source
62
Q

Alternate static source in use:

A

When the valve is set in the alternate position, the altimeter, vertical speed indicator and airspeed indicator will be using cabin air for static pressure. The storm window and cabin vents must be closed and the cabin heater and defroster must be on during alternate static source operation. The altimeter error is less than 50 feet unless otherwise placarded.

🛸 Private Pilot - ATP (8 decks)

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