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Private Pilot Ground > Piper Warrior > Flashcards

Piper Warrior Flashcards

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Charter Pilot (Part 135) - Oral flashcards
1
Q

Number of Engines

A

1

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2
Q

Engine Manufacturer

A

Lycoming

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3
Q

Engine Model Number

A

O-320-D3G

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4
Q

Rated Horsepower

A

160

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5
Q

Rated speed (rpm)

A

2700 RPM

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6
Q

Engine Type

A

Four Cylinder, Direct Drive, Horizontally Opposed, Air Cooled

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7
Q

Number of Propellers

A

1

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8
Q

Propeller Manufacturer

A

Sensenich

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9
Q

Propeller Model

A

74DM6-0-60

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10
Q

Number of Propeller Blades

A

2

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11
Q

Propeller Diameter (Inches)

A

Maximum 74 inch, Minimum 72 inch

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12
Q

Propeller Type

A

Fixed Pitch

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13
Q

Fuel Capacity (U.S. gal) (total)

A

50

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14
Q

Usable fuel (US gal.) (total)

A

48

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15
Q

Minimum Octane

A

100 Green or 100LL Blue Aviation Grade

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16
Q

Alternate Fuel

A

commercial
grade 100/130

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17
Q

Oil Capacity (U.S. quarts)

A

8

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18
Q

Oil Specification

A

SAE J1966 and SAE J1899 are specifications which establish the requirements for lubricating oils to be used
in four-stroke piston aircraft engines.

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19
Q

Maximum Takeoff Weight (lbs)

A

(Normal 2440),

(Utility 2020)

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20
Q

Maximum Ramp Weight (lbs)

A

(Normal 2447)

(Utility 2027)

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21
Q

Maximum Landing Weight (lbs)

A

(Normal 2440)

(Utility 2020)

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22
Q

Maximum Weight in Baggage Compartment (lbs)

A

(Normal 200)

(Utility 0)

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23
Q

Baggage Space

A

24

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24
Q

Wing Loading (lbs per sq ft)

A

14.4

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25
Q

Power Loading (lbs per)

A

15.3

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26
Q

Calibrated Airspeed (CAS)

A

Indicated airspeed corrected for position and instrument error. Equal to True airspeed in atmosphere at sea level

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27
Q

KCAS

A

Calibrated airspeed in knots

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28
Q

GS (Ground Speed )

A

is the speed of an airplane relative to the ground

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29
Q

IAS

A

is the speed of an aircraft as shown on the airspeed indicator when corrected for instrument error.

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30
Q

KIAS

A

Indicated Airspeed expressed in Knots

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31
Q

TAS

A

true air speed, speed moving relative to air that surrounds it

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32
Q

Va

A

Maneuvering Speed is the maximum speed at which application of full available aerodynamic control will not overstress the airplane.

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33
Q

Vfe

A

Maximum flap extended speed

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34
Q

Vne/Mne

A

Never Exceed Speed or Mach Number is the speed limit that may not be exceeded at any time

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35
Q

Vno

A

Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air, then only with caution.

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36
Q

Vs

A

Stalling speed or minimum steady flight speed at which the airplane is controllable

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37
Q

Vso

A

Stalling speed or minimum steady flight speed in the landing configuration.

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38
Q

Vx

A

Best angle of climb speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance

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39
Q

Vy

A

Best rate of climb speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time

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40
Q

ISA

A

International Standard Atmosphere in

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41
Q

OAT

A

Outside Air Temperature

42
Q

Vne

A

(KIAS 160)

(KCAS 153)

43
Q

Vno

A

(KIAS 126)

(KCAS 122)

44
Q

Vfe

A

(KIAS 103)

(KCAS 100)

45
Q

Va

A

2440 LBS(KIAS 111) 1531 LBS (KIAS 88)

2440 (KCAS 108) 1531 (KCAS 89)

46
Q

Red radial line (Never exceed)

A

160 KIAS

47
Q

Yellow Arc (Caution Range - Smooth Air Only)

A

126-160 KIAS

48
Q

Green Arc (Normal Operating Range)

A

50-126 KIAS

49
Q

White Arc (Flap Down)

A

44-103 KIAS

50
Q

Number of Engines

A

1

51
Q

Engine Manufacturer

A

Lycoming

52
Q

Engine Model No.

A

O-320-D3G

53
Q

Maximum Horsepower

A

160

54
Q

Maximum Rotation Speed (RPM)

A

2700

55
Q

Maximum Oil Temperature

A

245 degrees F

56
Q

Minimum Oil pressure (Red Line)

A

25 psi

57
Q

Maximum (Red line)

A

115 PSI

58
Q

Minimum fuel pressure (red line)

A

.5 PSI

59
Q

Maximum fuel pressure (red line)

A

8 PSI

60
Q

Fuel Minimum Grade

A

100 or 100LL Aviation Grade

61
Q

Center of Gravity Limits: Weight 2440: Forward Limit

A

88.3

62
Q

Center of Gravity Limits: Weight 1950 (and less)

A

83.0

63
Q

Normal category: Weight 2440 Rearward Limit

A

93.0

64
Q

Normal category: Weight 1950 (and less)

A

93.0

65
Q

Utility Category: Weight 1950 (and less) Forward Limit

A

83.0

66
Q

Utility Category Weight 2020 forward limit

A

83.8

67
Q

Utility Category weight 1950 (and less) rearward limit

A

93.0

68
Q

Utility Category weight 2020 rearward limit

A

93.0

69
Q

Steep Turns Maneuver limits

A

111 KIAS

70
Q

Lazy

A

111 KIAS

71
Q

Chandelles

A

111 KIAS

72
Q

Positive Load Factor (Maximum)

A

Normal 3.8 G

Utility 4.4 G

73
Q

Day VFR Required Equipment

A

(1) Airspeed indicator

(2) Altimeter

(3) Magnetic compass

(4) Tachometer (5) Oil pressure indicator

(6) Oil temperature indicator

(7) Fuel pressure indicator

(8) Fuel quantity indicator - each tank

(9) Volt-ammeter

(10) Elevator/rudder trim indicator (11) Alternator (12) Safety restraint - each occupant

74
Q

Night VFR

A

1) All equipment required for Day VFR

(2) Position lights

(3) Instrument lights

(4) Anti-collision (strobe) lights

75
Q

Unusable

A

2 U.S. GAL

The unusable fuel for this airplane has been determined as 1.0 gallon in each wing in critical flight attitudes

76
Q

Takeoff Checklist

A

Fuel on proper tank, Electric fuel pump on, Engine gauges checked, Flaps-set, Carb. heat off, Mixture set, Seat backs erect, Fasten belts/harness, trim tab-set, Controls-free, Door-latched

77
Q

Landing Checklist

A

Fuel on proper tank, mixture rich, Electric fuel pump on, Seat backs erect, Flaps-set (White Arc), Fasten belts/harness

78
Q

auxiliary vacuum system

A

is limited to standby function only. Take off with the engine driven dry air pump inoperative is not approved

79
Q

Vacuum pressure limitations

A

Discontinue flight in instrument meteorological conditions (IMC) if vacuum pressure falls below 4.8 In. Hg.

80
Q

The auxiliary pump/motor

A

Auxiliary pump/motor assembly and elapsed time indicator must be removed from service after 500 hours accumulated operating time or 10 years, whichever occurs first

81
Q

ELT

A

The Emergency Locator Transmitter (ELT), when installed, is located in the aft portion of the fuselage just below the stabilator leading edge and is accessible through a plate on the right side of the fuselage. This plate is attached with slotted-head nylon screws for ease of removal; these screws may be readily removed with a variety of common items such as a dime, a key, a knife blade, etc. If there are no tools available in an emergency, the screw heads may be broken off by any means. The ELT meets the requirements of FAR 91.52.

82
Q

alternate fuel

A

100/130 commercial grade

83
Q

Wing tip to tip

A

35 feet

84
Q

Plane length

A

23 feet and 9.6 inches

85
Q

Landing wheel length

A

10 feet

86
Q

Stabilizer to ground

A

7 feet and 3.6 inches

87
Q

Indicated Pressure Altitude

A

T h e n umber actually read from an
Altitude altimeter when the barometric subscale has
been set to 29.92 inches of mercury (1013.2
millibars)

88
Q

Pressure Altitude

A

Altitude measured from standard sea-level
pressure (29.92 in. Hg) by a pressure or
barometric altimeter. It is the indicated
pressure altitude corrected for position and
instrument error. In this handbook,
altimeter instrument errors are assumed to
be zero.

89
Q

Station Pressure

A

Actual atmospheric pressure at field

90
Q

Reference Datum

A

An imaginary vertical plane from which all
horizontal distances are measured for
balance purposes

91
Q

Station

A

A location along the airplane fuselage usually given in terms of distance from the reference datum

92
Q

Arm

A

The horizontal distance from the reference
datum to the center of gravity (C.G.) of an item.

93
Q

Moment

A

The product of the weight of an item
multiplied by its arm. (Moment divided by
a constant is used to simplify balance
calculations by reducing the number of
digits.

94
Q

Center of Gravity (C.G.)

A

The point at which an airplane would balance if suspended. Its distance from the
reference datum is found by dividing the
total moment by the total weight of the
airplane.

95
Q

C.G. Arm

A

The arm obtained by adding the airplane’s individual moments and dividing the sum by the total weight

96
Q

C.G. Limits

A

The extreme center of gravity locations within which the airplane must operated at a given weight

97
Q

Standard Empty Weight

A

Weight of a standard airplane including unusable fuel, full operating fluids and full oil.

98
Q

Payload

A

Weight of occupants, cargo and baggage

99
Q

Maximum Ramp Weight

A

Maximum weight approved for ground
maneuver. (It includes weight of start, taxi
and run up fuel.)

100
Q

Maximum Takeoff weight

A

Maximum weight approved for the start of the takeoff run

101
Q

Maximum Landing Weight

A

Maximum weight approved for the landing touchdown

102
Q

Maximum Zero Fuel Weight

A

Maximum weight exclusive of usable fuel

Private Pilot Ground (12 decks)

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