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Created Private Pilot Study > Oral Review for Piper Archer > Flashcards

Oral Review for Piper Archer Flashcards

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Charter Pilot (Part 135) - Oral flashcards
1
Q

Recite the V Speeds

A

VSO 45 Stall speed in landing configuration Bottom of White Line
VS 50 Stall speed with zero flaps Bottom of Green Line
VR 60 Rotation speed (start rotation)
VX 64 Best angle of climb
VY 76 Best rate of climb
VG 76 Best glide speed at max weight
VFE 102 Maximum flap extension speed Top of White Line
VNO 125 Max Structural Cruising Speed Top of Green Line
VNE 154 Never exceed speed Red Line
VA 113 Maneuvering speed at 2,550 pounds
VA 89 Maneuvering speed at 1,634 pounds

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2
Q

What is the maximum demonstrated crosswind component?

A

17 KIAS

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3
Q

How many cylinders does the PA-28-181 engine have?

A

4 cylinders

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4
Q

Who manufactures the PA-28-181 engine?

A

Lycoming

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5
Q

What is the horsepower rating for the PA-28-181 engine?

A

180 horsepower

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6
Q

Does the PA-28-181 engine have fuel injector or a carburetor?

A

Carburetor

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7
Q

Is the PA-28-181 engine fuel injected or normally aspirated?

A

Normally Aspirated

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8
Q

How are the cylinders arranged?

A

Horizontally opposed (Pistons oppose each other)

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9
Q

How is ignition provided?

A

Engine ignition is provided through the use of engine driven magnetos, which are independent of the aircrafts electrical system and each other.

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10
Q

What are the minimum and maximum oil capacities?

A

Never below 6 quarts and never above 8 quarts

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11
Q

Describe the propeller system
Who makes the propeller?
How is propeller RPM adjusted?
Define fixed pitch.

A

The Archer III is equipped with a Sensenich two-bladed, fixed pitch metal propeller. Propeller diameter is 76 inches. Maximum RPM (red line) is 2700 RPM.

RPM is adjusted through use of the throttle.

A fixed pitch prop cannot be adjusted or changed. It has one pitch, which is usually a compromise between speed and power.

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12
Q

Describe the Electrical System

A

The Archer III is equipped with a 28-volt DC electrical system and a 24-volt battery. Electrical power is supplied by a 70-amp, engine-driven alternator. A voltage regulator maintains a constant 28-volt output from the alternator. An overvoltage relay is located on the forward left side of the fuselage behind the instrument panel. Alternator output is displayed on a digital ammeter on the
instrument panel.

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13
Q

What are the indications of a failed alternator?

A

The “ALTERNATOR INOP” will illuminate.

Loss of alternator output is detected through zero reading on the ammeter. Before executing the following procedure, ensure that the reading is zero and not merely low by actuating an electrically powered device, such as the landing light. If no increase in the ammeter reading is noted, alternator failure can be assumed.

Electrical load should be kept at minimum and check for popped alternator circuit breaker.

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14
Q

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

A

Yes, through the use of magnetos. However you will be flying dark.

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15
Q

Describe the stall warning system

A

The Archer III is equipped with an electric stall detector located on the leading edge of the left wing. The stall horn emits a continuous sound and is activated between 5 and 10 knots above stall speed.

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16
Q

Describe the fuel system

A

The Archer III, which uses 100 low lead avgas (blue), is equipped with two 25 gallon fuel tanks. One gallon is unusable in each tank. There is one engine-driven and one electrically-driven fuel pump. The electric fuel pump is used for all takeoffs and landings, and when switching tanks.

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17
Q

Explain how to change fuel tanks in cruise flight

A

The aircraft is equipped with a three-position fuel selector control. The positions are “L”, “R”, and “OFF”.
The correct procedure for switching tanks in cruise flight is:
1. Electric fuel pump on
2. Fuel selector from “L” to “R” or from “R” to “L”
3. Check fuel pressure
4. Electric fuel pump off
5. Check fuel pressure

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18
Q

Describe the landing gear system

A

The landing gear is a fixed, tricycle type gear, with oleo (air/oil) struts providing shock absorption for all three wheels.

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19
Q

How is steering accomplished on the ground?

A

The nose wheel is linked to the rudder pedals

by a steering mechanism which turns the nose up to 20 degrees each side of center.

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20
Q

What is the range of travel on the nose wheel?

A

20 degrees each side of center

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21
Q

What type of breaking system is used by the Archer?

A

The Archer III is equipped with hydraulically actuated disc brakes on the main landing gear wheels.

22
Q

Where is the brake fluid reservoir?

A

The brake fluid reservoir is installed on the top left front face of the firewall.

23
Q

What type of flaps does the Archer have?

A

Manuel Flaps

24
Q

What are the flap settings on the Archer?

A

0, 10, 25, 40 degrees

25
Q

What are the maximum taxi, takeoff, and landing weights?

A

Taxi- 2,558 lbs

Takeoff- 2,550 lbs

Landing- 2,550 lbs

26
Q

Define Vx

A

Best Angle-of-Climb Speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance.

27
Q

Define Vy

A

Best Rate-of-Climb Speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time.

28
Q

What aircraft equipment checks are required under FAR part 91?

A 
A TOMATO FLAMES
Anti-collision light system
Tachometer
Oil pressure gauge for each engine
Manifold pressure gauge
Airspeed indicator
Temp gauge (For each liquid cooled engine)
Oil Temperature gauge (for each air cooled engine)
Fuel quantity indicator
Landing gear position indicators (if retractable gear)
Altimeter
Magnetic compass
ELT
Safety Belts
29
Q

What documents are required to be on the aircraft?

A
  1. Current Air Worthiness Certificate
  2. Current Registration Certificate
  3. Current Airplane Flight Manuel or Pilot’s Operating Handbook
30
Q

Explain lost communication procedures

A

If in VFR conditions, or if VFR conditions are encountered, squawk 7600, remain VFR and land as soon as practicable.

31
Q

Explain the pitot-static system

A

Pitot and static pressure are both received from a pitot head installed on the bottom of the left wing.

32
Q

Does the PA-28 have an alternate static source? If so, how is it activated and what actions are necessary to acquire the most accurate reading?

A

Yes!
An alternate static source is located inside the cabin
under the left side of the instrument panel, for use in the event of static port blockage. When using the alternate static source, the storm window and cabin vents must be closed and the cabin heater and defroster must be on. This will reduce the pressure differential between the cockpit and the atmosphere, reducing pitot-static error. The pitot-static instruments are the airspeed indicator, altimeter, and vertical speed indicator.
Both the pitot and static lines can be drained through separate drain valves located on the left lower side of the fuselage interior.

33
Q

What instruments are pitot static?

A
  1. Airspeed indicator
  2. Altimeter
  3. Vertical Speed Indicator
34
Q

Where is the pitot-static port located?

A

Left lower side of the fuselage interior

35
Q

What is the fuel capacity?

A

50 gallons (48 usable gallons)

36
Q

How many unusable gallons of fuel?

A

2 gallons

37
Q

What grade of fuel is used in the PA-28?

A

100 LL AVGAS (blue)

38
Q

How many fuel pumps are on the aircraft?

A

2 fuel pumps, one engine driven and one electrically driven

39
Q

When is the electric fuel pump to be used?

A

The electric fuel pump is used for all take offs and landings, and when switching tanks.

40
Q

What are the various positions of the fuel selector control?

A

Left, Right, and OFF

41
Q

Explain the procedure for for changing fuel tanks in cruise flight

A
  1. Electric fuel pump on
  2. Fuel selector from “L” to “R” or Visa Versa
  3. Check Fuel Pressure
  4. Electric Fuel Pump off
  5. Check Fuel Pressure
42
Q

In the event of electrical failure, what pilot actions are necessary to ensure continued operation of the standby attitude indicator?

A

If battery is dead and there is complete electrical failure. Reset the circuit breaker only one time.

43
Q

How do you determine a standard rate turn on an aircraft with a G500 system?

A

Use the reference lines and the magenta line that appears

above the heading indicator to identify a standard rate or half-standard rate turn.

44
Q

In the event of an AHRS failure, which indications will no longer be displayed on the PFD? Which indications will still be visible?

A

No Longer Visible: Sky/Ground ADI, Rate of turn is lost

Still Visible: The PFD continues displaying airspeed, altitude, vertical speed, compass rose and ground track.

45
Q

Which approaches can be accomplished with an AHRS failure?

A

All precision and non-precision

46
Q

What instrument approaches are available with the PFD inoperative?

A

GPS approach only

47
Q

What instrument approaches are available with MFD inoperative?

A

All precision and non-precision

48
Q

What instrument approaches are available with total PFD/MFD failure?

A

None

49
Q

How long does the internal battery last when providing power to the standby attitude indicator?

A

Up to 1 hour

50
Q

With the loss of the ADC, which lost instrument does not have a backup?

A

No backup for the VSI

51
Q

What should you do to compensate for lack of VSI information?

A

Use the known pitch attitudes, power settings, and air speeds.

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