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--- courses:201a:systems [2018/05/02 03:58]
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 24: / Line 35: @@
   - 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
@@ Line 38: / Line 52: @@
 {{ :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 45: / 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 50: / 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 59: / 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 74: / 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 80: / 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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