C150 Flashcards
Engine Specs
horizontally opposed 4-cylinder carbureted continental 0-200-A Air cooled engine.
100hp @ 2750 RPM
Vacuum pump is located at front of engine and a starter ,gear driven alternator and dual Mags are mounted at the rear of the engine.
Oil system location and specs
Located at the bottom of the engine with total capacity of 6 quarts.
oil drawn from sump through filter screen@ end of pick up tube to the engine-driven oil pump.
Propeller type
fixed pitch
69 inches
Landing gear
tricycle type
shock absorption- tubular spring-steel main landing gear struts and air/oil nose gear shock strut.
brakes= hydraulically actuated disc type
Brakes
Single-disc hydraulically actuated brake on each main.
connected by hydraulic line to the master cylinder.
Fuel system
two tanks ( 13 each) 22.5 useable-135lbs
vented tanks, fuel shut off, strainer, manual primer, and carburetor.
fuel goes thru strainer to carb(mixes w/ air) to cylinders through intake manifold tubes.
* primer draws from STRAINER directly to intake manifold.
How does the fuel system vent
interconnecting line from the right to left tank.left tank is vented overbroad thru vent line which has a check valve. sticks out from the bottom of the left wing
right tank cap is vented.
How much unusable fuel is stored
3.5 gal
because the fuel lines sit higher then bottom of tanks
How is fuel quantity measured
2 float type transmitters and indicated by 2 electrically operated fuel quantity indicators on the lower portion of the panel.
Where is the fuel strainer drain located
under access panel on right side of cowling
tanks should be filled each flight to prevent condensation
How is electricity powered to the airplane
by a 14 volt DC system powered by engine driven Go-amp alternator.
12V/25Amp hour battery located right forward side of firewall.
power is supplied to a single bus bar, master switch controls all circuits except ignition system, optional clock and flight recorder.
Describe the bus bar
like a power strip
Single bus
Master switch controls power to all circuits except engine ignition system, flight hour recorder and clock.
Flight hour recorder
receives power through activation of oil pressure switch whenever engine is operating
what happens when Alternator malfunctions
Electrical load exceeds the output of the alternator, the ammeter will indicate battery discharge rate
explain over voltage condition in electrical system
the sensor will automatically remove the alternator field current and shuts down the alternator. the red warning light will then turn on.
can be reset by cycling master switch.
which components are powered by fuses not circuit breakers
battery contactor closing(external power) circuit, flight hour recorder circuits which have fuses mounted by the battery.
explain the vacuum system
engine driven system provides suction to operate the attitude indicator and directional indicator.
pump is mounted on engine , vacuum relief valve and air filter on aft side of firewall.
describe suction gauge
indicates the measure of mercury and amount of suction available for the attitude/directional indicator.
desired rate is 4.6 to 5.4 inches.
describe the pitot static system
supplies ram pressure to the airspeed indicator and static pressure to the airspeed indicator, rate of climb indicator and altimeter.
has a heating element on a 10amp ck breaker.
describe airspeed indicator
flaps white arc 49-100mph
normal operating range green arc 56-120mph
caution yellow arc 120-162mph
never exceed red line - 162 mph
Stall warning horn
pneumatic type
inlet is in the leading edge of the wing.
air operated horn sounds 5 to 10 kts above stall speed.
low pressure over the wing creates a differential pressure (vacuum) which draws air to thru the horn.
gross weight
max allowable weight of both airplane and its contents
1600lbs
useful load
weight of the pilot, passengers,cargo,fuel and other equipment and drainable oil
625lbs
wing loading
10.2 pounds per sqft
