C172 Skyhawk Flashcards
Engine
Lycoming Model IO-360-L2A,
air cooled, horizontally opposed 4-cylinder, fuel-injected engine
Rated to 180 HP at 2700 rpm
Controlled with throttle for engine rpm, and mixture control for leaning/enrichening fuel flow to the engine.
Flap System
Single slot type wing flaps, electrically controlled with a switch in the cockpit with markings for the 10, 20, and 30 degree positions.
Air Induction System
Recieves ram air at the front of the aircraft, below the spinner. This ram air passes through a filter before entering an air box. The air box has a spring-loaded alternate air door. If the filter is obstructed, the alternate door opens, drawing unfiltered air from the lower cowl area. An open alternate air foor will result in a 10% loss of engine power at full throttle.
Propellor
2 bladed, fixed pitch, 76 inch aluminum alloy
Fuel system
28.0 total gallons in each tank, 1.5 unusable in each tank, for a total of 56 gallons or 53.0 usable gallons.
Electrical system
28 volt, DC current. Powered by a 60 amp alternator and 24 volt battery. Electrical power is needed to start the engine, but total loss of power will not turn off engine. Annunciator VOLTS indication if voltage ever falls below 24.5. Usual cause is alternator failure. In the event this occurs, turn off all non-essential electrical equipment.
Lighting System (exterior)
Red nav light on left, green nav on right. Flashing beacon on rudder, strobes on each wingtip. Landing and taxi light on left wing leading edge. Controlled by switches below left seat yoke.
Cabin Heating/Defrost
For cabin ventilation, pull CABIN AIR out. For heat, pull CABIN HT out 1/4 to 1/2 inch for a small amount, more by pulling further. Heated air flows around the muffler to warm up before being directed into cabin. Pitot heat switch activated an electrical heater in the ptiot tube, to combat icing. Though many other methods of defeating ice exist, our Cessnas have almost nothing, which is why we are not permitted to fly into known visible moisture in icing conditions.
Pitot static system
Supplies ram air pressure to the ASI, and static pressure to the Airspeed Indicator, Altimeter and VSI. Composed of a pitot tube under left wing and external static port on left side of forward fuselage. Alternate static source recieves static pressure from inside the cabin.
Vacuum System
Provides suction for AI and HI gyros by means of two engine driven vacuum pumps, a vacuum gauge, low vacuum warning, and a manifold with check valves to allow normal operation if one pump fails.
Stall Warning
Pneumatic type, provides audible warning 5-10 kts above stall speed in all flight conditions.
Static dischargers
AKA Static Wicks, these carry static charges away from the aircraft to prevent disruption of radio communication. Deteriorate with age.
Anti-ice additives
It is permissible to add either isopropyl alcohol or dieththylene glycol monomethyl ether (DiEGME) compound to the fuek supply (8-16), with charts for concentration per gallon of fuel.
