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Piper Archer > Piper Archer > Flashcards

Piper Archer Flashcards

1
Q

Manufacturer

A

Piper Aircraft

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2
Q

Model

A

PA-28-181

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3
Q

Identifier

A

P28A

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4
Q

Max Gross weight

A

2550

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5
Q

Primary Flight Controls

A

Differential Ailerons
Elevator
Rudder

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6
Q

Secondary Flight controls

A

Single slot wing flaps
Manually actuated
0,10,25,40

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7
Q

Trim

A

Stabilator
Manual: located between front seats
Electric: located on both yokes

Rudder trim:

Located by copilot left leg

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8
Q

Propeller

A

Sensenich
Fixed pitch
76 diameters
2 metal blades

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9
Q

Power plant

A

Lycoming IO-360-B4A
I=Fuel injected
O= Horizontally opposed
360= cubic inches of displacement
B4A- Accessories we have in the plane
4 cylinders horizontally opposed
Direct propeller drive
Air cooled
Naturally aspirated
180hp @2700 rpm
Dual magneto ignition
Fuel air mixture control (manual)

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10
Q

Oil

A

Wet sump
5-8quarts
School:6 quarts
Phillips X/C 20W-50

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11
Q

Fuel system

A

Mechanical and Electrical fuel pump
50 gal capacity
48 gal usable capacity

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12
Q

Hydraulic System

A

MIL 5606H
External Reservoir located on firewall
Hydraulically actuated external caliper disk brakes (on main wheels only)

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13
Q

Landing gear

A

Tricycle configuration
Differential toe brakes
Nose gear: Steerable Air/oil shock strut
Main gear: same nose

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14
Q

Electrical system

A

28 volts
70A alternator
24v main battery
1 emergency battery (24V approx 30 min power to emergency bus, and 30 minutes of power on main battery once alternator fails)
Section 7
Standby instrument is on a battery

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15
Q

Avionics

A

Transponder: A,C, and S functions
Garmin G1000 display PFD and MFD
ADAHRS flight instruments
Garmin G5 standby instrument
Auto pilot: Garmin-GFC 700 2-axis integrated with auto pitch trims
IFR Navigator: 2x Garmin GPS

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16
Q

De-Ice/Anti-ice

A

Pitot heat
Windscreen defroster
Heated static port on pitot mast
Alternate static source
Alternate air

17
Q

Va

A

98-113

18
Q

VSO

A

45

19
Q

VS1

A

50

20
Q

Vfe

A

102

21
Q

Vg

A

76

22
Q

Vx

A

64

23
Q

Vy

A

76

24
Q

Vno

A

125

25
Q

Vne

A

154

26
Q

AHRS Flight Support Systems

A

AHRS for aviation and general aviation are small solid-state systems integrating a variety of technology such as low cost inertial sensors, rate gyros, and magnetometers, and have capability for satellite signal reception.

27
Q

Air Data Computer

A

An aircraft computer that receives and processes pitot pressure, static pressure, and temperature to calculate very precise altitude IAS, TAS, and air temperature.

•Computes the difference between the total pressure and the attic pressure and generates the information necessary to display the airspeed on the PFD.
•Outside air temperatures are also monitored and introduced into various components within the system.
•Altitude information is derived from the static pressure port just as an analogue system does.
•However the static pressure does not entered a diaphragm.
• The ADC computes received barometric pressure and sends a digital signal to the PFD to display the proper altitude readout.

28
Q

Magnetometer

A

Heading information is derived from a magnetometer that senses the earths lines of magnetic flux. This information is then processed and sent out to the PFD to generate heading display.

29
Q

How Does A fuel Injected System Work?

A

•The auxiliary fuel pump provides fuel under pressure to the fuel-air control unit for engine starting and/or emergency use.
•After starting, the engine driven pump provides fuel under pressure from the fuel tank to the fuel-air control unit.
•This control unit meters fuel based on the mixture control setting and sends it to the fuel manifold valve at a rate controlled by the throttle.
•After reaching the fuel manifold valve, the fuel is distributed to the individual fuel discharge nozzles.
•The discharge nozzles which are located in each cylinder head, inject the fuel-air mixture directly into each cylinder intake port.

Piper Archer (2 decks)

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