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--- courses:201a:systems [2018/05/02 03:45]
evan
+++ courses:201a:systems [2018/05/02 15:33] (current)
evan [Flight Control Systems and Operation]
@@ Line 7: / Line 7: @@
 ===== 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]]
@@ Line 16: / Line 27: @@
 ===== 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
@@ Line 24: / Line 43: @@
 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
-Two types of induction systems are commonly used in small aircraft engines:
+A fuel injection system usually incorporates six basic components: an engine-driven fuel pump, a fuel-air control
-  - The carburetor system mixes the fuel and air in the carburetor before this mixture enters the intake manifold.
+unit, a fuel manifold (fuel distributor), discharge nozzles, an auxiliary fuel pump, and fuel pressure/flow indicators.
-  - The fuel injection system mixes the fuel and air immediately before entry into each cylinder or injects fuel directly into each cylinder.
+{{ :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 =====
@@ Line 36: / Line 73: @@
 ===== 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 =====
@@ Line 41: / Line 82: @@
 ===== 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 =====
@@ Line 50: / Line 110: @@
 ===== 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 =====
@@ Line 65: / Line 159: @@
     * Suction/Vac guage
     * Vacuum loss indications
+{{ :courses:201a:c172_vacuum_system.jpg?linkonly |C172R Vacuum System Diagram}}
 ===== Environmental and Cabin Heating Systems =====
@@ Line 71: / Line 167: @@
   * 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)}}

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