Evan's CFI Notebook

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====== AF 201A Unit 15 Orientation Lesson 6 - Systems ======


The student will receive instruction on aircraft systems.

The student should have a full understanding of aircraft systems.

===== Flight Control Systems and Operation =====

Cable-controlled alerons, elevators, & rudders.

Elevator trim system

Rudder trim system (if equipped) -- no trim tab, springs on rudder only.

Flaps - Single electric motor in the right wing, cables to operate left flap.

{{ :courses:201a:c172_flaps.png?linkonly |C172 Flap System Diagram}}


  * [[http://4.bp.blogspot.com/-ZuF7zBNesgQ/UqHg_pyNLqI/AAAAAAAAB8Q/Nd3U0Qlesf8/s1600/Forces+acting+on+a+rotating+propeller.jpg|Propeller Aerodynamics]]
    * [[http://media.chiefaircraft.com/media/catalog/product/cache/1/thumbnail/9df78eab33525d08d6e5fb8d27136e95/s/l/sl1010-55003-13-h05-2.jpg|Tach]]
    * [[http://www.boldmethod.com/images/learn-to-fly/aircraft-systems/how-a-constant-speed-prop-works/prop-lever.jpg|Constant Speed Setup]]

===== Four Engine Strokes - Reciprocating Engine =====

===== Ignition Systems =====

Magnetos & function

Spark plugs

===== Induction Systems =====
Two types of induction systems are commonly used in small aircraft engines:
  - The carburetor system mixes the fuel and air in the carburetor before this mixture enters the intake manifold.
  - The fuel injection system mixes the fuel and air immediately before entry into each cylinder or injects fuel directly into each cylinder.

{{:courses:201a:carbeurator.png?linkonly|Carb Diagram}}

   * Induction icing
   * Carburetor  Operation and Carburetor Heat

The use of carburetor heat causes a decrease in engine power, sometimes up to 15 percent, because the heated
air is less dense than the outside air that had been entering the engine. This enriches the mixture. When ice is present in an aircraft with a fixed-pitch propeller and carburetor heat is being used, there is a decrease in rpm, followed by a gradual increase in rpm as the ice melts.

{{:courses:201a:c172-fuel-carb-system.png?linkonly|C172N Fuel System Diagram}}

   * Fuel Injection Systems

A fuel injection system usually incorporates six basic components: an engine-driven fuel pump, a fuel-air control
unit, a fuel manifold (fuel distributor), discharge nozzles, an auxiliary fuel pump, and fuel pressure/flow indicators.

{{ :courses:201a:c172r_fuel_selector.jpg?linkonly |C172R Fuel Selector}}

{{ :courses:201a:c172r_fuel_system.jpg?linkonly |C172R Fuel System}}

The following are advantages of using fuel injection:
  - Reduction in evaporative icing
  - Better fuel flow
  - Faster throttle response
  - Precise control of mixture
  - Better fuel distribution
  - Easier cold weather starts

The following are disadvantages of using fuel injection:
  - Difficulty in starting a hot engine
  - Vapor locks during ground operations on hot days
  - Problems associated with restarting an engine that quits because of fuel starvation

===== Mixture Operation and Leaning Procedures =====

===== Detonation Versus Pre-Ignition =====

===== Exhaust Systems =====

Exhaust from each cylinder passes through a riser to a single muffler and tailpipe.

The muffler is equipped with a shroud for cabin heat.

===== Cooling Systems =====
  * Oil Temp, Oil Cooling

===== Aircraft Landing Gear and Components =====

The  landing  gear  is  of  the  tricycle  type,  with  a  steerable  nose
wheel  and  two  main  wheels.  Wheel  fairings  are  optional  equipment
for both the main and nose wheels. Shock absorption is provided by
the tubular spring steel main landing gear struts and the air/oil nose
gear  shock  strut.  Each  main  gear  wheel  is  equipped  with  a
hydraulically  actuated  disc  type  brake  on  the  inboard  side  of  each
wheel.

===== Brake and Other Hydraulic Systems =====
  * How disc brakes work

The  airplane  has  a  single-disc,  hydraulically  actuated  brake  on
each  main  landing  gear  wheel.  Each  brake  is  connected,  by  a
hydraulic  line,  to  a  master  cylinder  attached  to  each  of  the  pilot's
rudder pedals. The brakes are operated by applying pressure to the
top of either the left (pilot's) or right (copilot's) set of rudder pedals,
which  are  interconnected.  When  the  airplane  is  parked,  both  main
wheel  brakes  may  be  set  by  utilizing  the  parking  brake  which  is
operated by a handle under the left side of the instrument panel. To
apply the parking brake, set the brakes with the rudder pedals, pull
the handle aft, and rotate it 90° down.

===== Fuel Systems =====
  * Carburetor
  * Fuel Injection (Fuel pumps, fuel distribution manifold)

===== Oil Systems =====

From C172R POH:

The engine utilizes a full pressure, wet sump-type lubrication
system with aviation grade oil used as the lubricant. The capacity of
the engine sump (located on the bottom of the engine) is eight
quarts. Oil is drawn from the sump through an oil suction strainer
screen into the engine-driven oil pump. From the pump, oil is routed
to a bypass valve. If the oil is cold, the bypass valve allows the oil
to bypass the oil cooler and go directly from the pump to the full
flow oil filter. If the oil is hot, the bypass valve routes the oil out of
the accessory housing and into a flexible hose leading to the oil
cooler on the right, rear engine baffle. Pressure oil from the cooler
returns to the accessory housing where it passes through the full
flow oil filter. The filter oil then enters a pressure relief valve which
regulates engine oil pressure by allowing excessive oil to return to
the sump while the balance of the oil is circulated to various engine
parts for lubrication. Residual oil is returned to the sump by gravity
flow.

An oil filler cap/oil dipstick is located at the right rear of the
engine. The filler cap/ dipstick is accessible through an access door
on the top right side of the engine cowling. The engine should not
be operated on less than five quarts of oil. For extended flight, fill to
eight quarts (dipstick indication only). For engine oil grade and
specifications, refer to Section 8 of this handbook.

===== Electrical Systems =====

{{ :courses:201a:c172p_electrical.jpg?direct&400 |C172P Electrical Diagram}}

{{ :courses:201a:c172p_electrical_diagram.png?linkonly |C172P Electrical Bus}}

{{ :courses:201a:c172r_electrical_1.png?linkonly |C172R Electrical Diagram 1}}

**Alternator Control Unit** -- Automatically disconnects the alternator in the event of an over-voltage situation. In this instance, the battery will then power the airplane's electrical system. (C172P POH pg 7-27)

===== Avionics =====

  * Antennas
  * Transponder / ADS-B

===== Flight Instrument Systems =====

  * {{ :courses:201a:pitot-staticsyslg.jpg?linkonly |Pitot/Static System}}
  * Electric instruments
  * Vacuum system & instruments
    * Suction/Vac guage
    * Vacuum loss indications

{{ :courses:201a:c172_vacuum_system.jpg?linkonly |C172R Vacuum System Diagram}}

===== Environmental and Cabin Heating Systems =====
  * Cabin Heat -- exhaust manifold similar to a car
  * Overhead vents
  * Cabin air vent (right side)

{{ :courses:201a:c172p_ventilation.png?linkonly |C172P Ventilation Diagram}}

{{ :courses:201a:c172_ventilation.jpg?linkonly |C172R Ventilation Diagram}}

-----

{{ :courses:201a:cessna_172_c172p-1982-poh.pdf |Cessna 172P POH (Sample)}}

{{ :courses:201a:cessna_172sp_systems.pdf |C172SP Systems}}
Evan's CFI Notebook

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