Piper Warrior Flashcards
(102 cards)
1
Q
Number of Engines
A
1
2
Q
Engine Manufacturer
A
Lycoming
3
Q
Engine Model Number
A
O-320-D3G
4
Q
Rated Horsepower
A
160
5
Q
Rated speed (rpm)
A
2700 RPM
6
Q
Engine Type
A
Four Cylinder, Direct Drive, Horizontally Opposed, Air Cooled
7
Q
Number of Propellers
A
1
8
Q
Propeller Manufacturer
A
Sensenich
9
Q
Propeller Model
A
74DM6-0-60
10
Q
Number of Propeller Blades
A
2
11
Q
Propeller Diameter (Inches)
A
Maximum 74 inch, Minimum 72 inch
12
Q
Propeller Type
A
Fixed Pitch
13
Q
Fuel Capacity (U.S. gal) (total)
A
50
14
Q
Usable fuel (US gal.) (total)
A
48
15
Q
Minimum Octane
A
100 Green or 100LL Blue Aviation Grade
16
Q
Alternate Fuel
A
commercial
grade 100/130
17
Q
Oil Capacity (U.S. quarts)
A
8
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.
19
Q
Maximum Takeoff Weight (lbs)
A
(Normal 2440),
(Utility 2020)
20
Q
Maximum Ramp Weight (lbs)
A
(Normal 2447)
(Utility 2027)
21
Q
Maximum Landing Weight (lbs)
A
(Normal 2440)
(Utility 2020)
22
Q
Maximum Weight in Baggage Compartment (lbs)
A
(Normal 200)
(Utility 0)
23
Q
Baggage Space
A
24
24
Q
Wing Loading (lbs per sq ft)
A
14.4
25
Power Loading (lbs per)
15.3
26
Calibrated Airspeed (CAS)
Indicated airspeed corrected for position and instrument error. Equal to True airspeed in atmosphere at sea level
27
KCAS
Calibrated airspeed in knots
28
GS (Ground Speed )
is the speed of an airplane relative to the ground
29
IAS
is the speed of an aircraft as shown on the airspeed indicator when corrected for instrument error.
30
KIAS
Indicated Airspeed expressed in Knots
31
TAS
true air speed, speed moving relative to air that surrounds it
32
Va
Maneuvering Speed is the maximum speed at which application of full available aerodynamic control will not overstress the airplane.
33
Vfe
Maximum flap extended speed
34
Vne/Mne
Never Exceed Speed or Mach Number is the speed limit that may not be exceeded at any time
35
Vno
Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air, then only with caution.
36
Vs
Stalling speed or minimum steady flight speed at which the airplane is controllable
37
Vso
Stalling speed or minimum steady flight speed in the landing configuration.
38
Vx
Best angle of climb speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance
39
Vy
Best rate of climb speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time
40
ISA
International Standard Atmosphere in
41
OAT
Outside Air Temperature
42
Vne
(KIAS 160)
(KCAS 153)
43
Vno
(KIAS 126)
(KCAS 122)
44
Vfe
(KIAS 103)
(KCAS 100)
45
Va
2440 LBS(KIAS 111) 1531 LBS (KIAS 88)
2440 (KCAS 108) 1531 (KCAS 89)
46
Red radial line (Never exceed)
160 KIAS
47
Yellow Arc (Caution Range - Smooth Air Only)
126-160 KIAS
48
Green Arc (Normal Operating Range)
50-126 KIAS
49
White Arc (Flap Down)
44-103 KIAS
50
Number of Engines
1
51
Engine Manufacturer
Lycoming
52
Engine Model No.
O-320-D3G
53
Maximum Horsepower
160
54
Maximum Rotation Speed (RPM)
2700
55
Maximum Oil Temperature
245 degrees F
56
Minimum Oil pressure (Red Line)
25 psi
57
Maximum (Red line)
115 PSI
58
Minimum fuel pressure (red line)
.5 PSI
59
Maximum fuel pressure (red line)
8 PSI
60
Fuel Minimum Grade
100 or 100LL Aviation Grade
61
Center of Gravity Limits: Weight 2440: Forward Limit
88.3
62
Center of Gravity Limits: Weight 1950 (and less)
83.0
63
Normal category: Weight 2440 Rearward Limit
93.0
64
Normal category: Weight 1950 (and less)
93.0
65
Utility Category: Weight 1950 (and less) Forward Limit
83.0
66
Utility Category Weight 2020 forward limit
83.8
67
Utility Category weight 1950 (and less) rearward limit
93.0
68
Utility Category weight 2020 rearward limit
93.0
69
Steep Turns Maneuver limits
111 KIAS
70
Lazy
111 KIAS
71
Chandelles
111 KIAS
72
Positive Load Factor (Maximum)
Normal 3.8 G
Utility 4.4 G
73
Day VFR Required Equipment
(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
Night VFR
1) All equipment required for Day VFR
(2) Position lights
(3) Instrument lights
(4) Anti-collision (strobe) lights
75
Unusable
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
Takeoff Checklist
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
Landing Checklist
Fuel on proper tank, mixture rich, Electric fuel pump on, Seat backs erect, Flaps-set (White Arc), Fasten belts/harness
78
auxiliary vacuum system
is limited to standby function only. Take off with the engine driven dry air pump inoperative is not approved
79
Vacuum pressure limitations
Discontinue flight in instrument meteorological conditions (IMC) if vacuum pressure falls below 4.8 In. Hg.
80
The auxiliary pump/motor
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
ELT
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
alternate fuel
100/130 commercial grade
83
Wing tip to tip
35 feet
84
Plane length
23 feet and 9.6 inches
85
Landing wheel length
10 feet
86
Stabilizer to ground
7 feet and 3.6 inches
87
Indicated Pressure Altitude
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
Pressure Altitude
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
Station Pressure
Actual atmospheric pressure at field
90
Reference Datum
An imaginary vertical plane from which all
horizontal distances are measured for
balance purposes
91
Station
A location along the airplane fuselage usually given in terms of distance from the reference datum
92
Arm
The horizontal distance from the reference
datum to the center of gravity (C.G.) of an item.
93
Moment
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
Center of Gravity (C.G.)
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
C.G. Arm
The arm obtained by adding the airplane's individual moments and dividing the sum by the total weight
96
C.G. Limits
The extreme center of gravity locations within which the airplane must operated at a given weight
97
Standard Empty Weight
Weight of a standard airplane including unusable fuel, full operating fluids and full oil.
98
Payload
Weight of occupants, cargo and baggage
99
Maximum Ramp Weight
Maximum weight approved for ground
maneuver. (It includes weight of start, taxi
and run up fuel.)
100
Maximum Takeoff weight
Maximum weight approved for the start of the takeoff run
101
Maximum Landing Weight
Maximum weight approved for the landing touchdown
102
Maximum Zero Fuel Weight
Maximum weight exclusive of usable fuel
