Airplane Parts Flashcards
Archer
Max Gross Weight (lbs)
2550
Primary Flight Controls
Differential Ailerons
Stabilator
Rudder
Secondary flight controls
Single-slot type wing flaps
-Manually Actuated
-0°,10°,25°,40°
Flight controls
Trim
Elevator
Manually and electronically
Propeller
Sensenich
Fixed pitch
76 in
2 blades
Metal
Powerplant
Lycoming
IO-360-B4A
I = Fuel Injected
O = Horizontally Opposed Cylinders
360 = Cubic inches of displacement
- _____ = accessory configuration
4 cylinder configuration
Direct propeller drive
Air cooling
Dual magnetos
Power plant
Horsepower
180 @ 2700rpm
Oil System
Wet sump
8 qt capacity
6 qt min for school
Phillips X/C 20W-50
Fuel System
2 fuel pumps
Mechanical and engine driven
50 gal capacity
48 gal usable
Hydraulic System
MIL 5606H
Landing Gear
Fixed tricycle
Steerable Air / Oil Shock Strut (OLEO)
Brake fluid is red
Electrical System
System- 28 volt
Main battery - 24 volt
Emergency battery- 24 volt
Alternator- 70 amp
Electrical system
Additional Batteries
1x Emergency (24V approx 30min power to 30min Emergency Bus)
1x Battery for G5 (approx 4 hrs)
Deicing and Anti-Icing
Pitot heat
Windscreen defroster
Heated Static Port on Pitot Mast
Alternate static source
Alternate induction air
Avionics
Transponder
Mode S with A, C and S functions
Avionics
Displays
Garmin G1000 PFD & MFD
Avionics
1: Air Data Computer (ADC) + Attitude & Heading Reference System (AHRS) (see 2 for more information)
2: AHRS for gyroscopic instruments uses rate sensors, inclinometers, accelerometers. In conjunction with a magnetometer located in the wing or tail (see POH). ADC provides information for the pitot static instruments via conventional pitot static tubing and translates them to the displays using pressure sensors.
3: The conventional standby instruments include altimeter, airspeed indicator, and attitude indicator with suction provided by an engine driven vacuum pump. 4: G1000 magnetometer in the left wing, G5 in the right
Spark plugs
8 spark plugs
2 per cylinder
Weight limits
Empty weight ~ 1730lbs
Max weight ~ 2550lbs
Baggage weight~ 200lbs
gyroscopic instruments
rigidity in space
precession
attitude indicator
rigidity in space
vacuum driven
-bank/pitch
heading indicator
rigidity in space
vacuum system
turn indicators
precession
*turn coordinators: rate of turn\rate and roll
*turn-and-slip indicators: rate of turn only
vertical speed indicator
rate of climb and rate trend
diaphragm to static source
static pressure via calibrated leak
responds to pressure change over time
expands and contracts
altimeter
-height above given pressure level
based on standard pressure lapse rate of 1000 per in of mercury
-aneroid wafers expand and contract with changes in pressure received from static port
mechanical linkage between aneroid wafers and display translates the sensed pressure to altitude indication
VSI
vertical speed indicator
rate of climb in fpm
rate trend
diaphragm connected to static source
outside diaphragm receives static pressure via calibrated leak
static pressure over time
static port blockages
airspeed indicator
indicates correctly only at blockage altitude
lower altitudes- airspeed indicates lower than it should
low altitudes- indicates higher than it should
static port blockages
altimeter
will freeze on the altitude where it was blocked
static port blockages
VSI
freezes on zero
static port blockages
alt air
airspeed indicator- indicate faster airspeed
altimeter- indicate higher
VSI- momentarily show a climb, then to 0
