Systems

Question 1

Describe the Oil System

Answer 1

Wet Sump System- oil is located in tank at base of engine

Oil is supplied from a sump on the bottom of the engine

Capacity: 7quarts

Question 2

Describe how oil flows in the 172

Answer 2

Sump
Strainer
Oil Pump
Bypass Valve
Cooler
Pressure relief valve
Filter
Circulation

Question 3

Describe the carburetor system

Answer 3

Controls fuel to air mixture

Up-draft, float type, fixed jet carburetor mounted on the bottom of the engine.

Question 4

How does the carburetor work?

Answer 4

Fuel arrives at the carburetor and sits in the float chamber

Air passes through the Venturi at high velocity causing a decrease in pressure

A fuel discharge nozzle located in the area of low pressure releases fuel from reservoir

Fuel is mixed with the air

Top of Venturi is the throttle valve that controls how much of the mixture goes to the cylinders

Question 5

What is a primer, how does it work?

Answer 5

A small pump which draws fuel from the fuel strainer when the plunger is pulled out and injects it into the cylinder intake ports when the plunger is pushed back in. Plunger must be locked after use.

Question 6

Describe the propeller

Answer 6

Two-bladed, fixed pitch, one-piece, forged aluminum alloy propeller which is ionized to retard corrosion it is 75” in diameter

Question 7

Describe the fuel system and fuel flow

Answer 7

Gravity fed fuel system two tanks 43 total 40 usable

Fuel Tank
Fuel selector
Fuel strainer
Carburetor
Intake manifold
Cylinders

Question 8

Describe the break system

Answer 8

Single disk hydraulically actuated break on each main landing gear wheel.

Each break is connected by a hydraulic line to a master cylinder attached to each of the pilots rudder pedals.

The breaks are operated by applying pressure to the top of either left or right set of rudder pedals

Question 9

Describe our electrical system

Answer 9

28 volt direct current electrical system
24 volt lead acid battery
60 amp alternator
Power is supplied to circuits through the main bus bar and avionics bus bar which are interconnected by an avionics power switch.

Avionics switch should be of before turning on engine or applying external power source to prevent damage to avionics equipment