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The construction of the fuselage is a conventional formed sheet metal bulkhead, stringer, and skin design referred to as semi-monocoque. Major items of structure are the front and rear carry-through spars to which the wings are attached, a bulkhead and forgings for main landing gear attachment at the base of the rear door posts, and a bulkhead with attaching plates at the base of the forward door posts for the lower attachment of the wing struts. Four engine mount stringers are also attached to the forward door posts and extend forward to the firewall.
The externally braced wings, containing the fuel tanks, are construced of a front and rear spar with formed sheet metal ribs, doublers, and stringers. The entire structure is covered with aluminum skin. The front spars are equipped with wing-to-fuselage and wing-to-strut attach fittings. The aft spars are equipped with wing-to-fuselage attach fittings, and are partial-span spars. Conventional hinged ailerons and single-slotted flaps are attached to the trailing edge of the wings. The ailerons are constructed of a forward spar containing a balance weight, formed sheet metal ribs and "V" type corrugated aluminum skin joined together at the trailing edge. The flaps are constructed basically the same as the ailerons, with the exception of balance weight and the addition of a formed sheet metal leading edge section.
The empennage (tail assembly) consists of a conventional vertical stabilizer, rudder, horizontal stabilizer, and elevator. The vertical stabilizer consists of a spar, formed sheet metal ribs and reinforcements, a wrap-around skin panel, formed leading edge skin and a dorsal. The rudder is constructed of a formed leading edge skin containing hinge halves, a wrap-around skin panel and ribs, and a formed trailing edge skin with a ground adjustable trim tab at its base. The top of the rudder incorporates a leading edge extension which contains a balance weight. The horizontal stabilizer is constructed of a forward spar, main spar, formed sheet metal ribs and stiffeners, a wrap-around skin panel, and formed leading edge skins. The horizontal stabilizer also contains the elevator trim tab actuator. Construction of the elevator consists of a main spar and bellcrank, left and right wrap-around skin panels, and a formed trailing edge skin on the left half of the elevator; the entire trail-
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👉 TAXIING
👉 TAKEOFF
👉 CRUISE
👉 LANDING
👉 ENGINE
👉 MAXIMUM CERTIFICATED WEIGHTS
👉 AIRSPEEDS FOR EMERGENCY OPERATION
👉 ENGINE FAILURE DURING TAKEOFF RUN
👉 ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF
👉 ENGINE FAILURE DURING FLIGHT
👉 EMERGENCY LANDING WITHOUT ENGINE POWER
👉 PRECAUTIONARY LANDING WITH ENGINE POWER
👉 DITCHING
👉 FIRES DURING START ON GROUND
👉 LANDING WITH A FLAT MAIN TIRE
👉 ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS
👉 LANDING WITHOUT ELEVATOR CONTROL
👉 FIRES
👉 EMERGENCY OPERATION IN CLOUDS
👉 EXECUTING A 180° TURN IN CLOUDS
👉 EMERGENCY DESCENT THROU GH CLOUDS
👉 SPINS
👉 ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS
👉 AIRFRAME
👉 SEATS
👉 SEAT BELTS AND SHOULDER HARNESSES
👉 ENTRANCE DOORS AND CABIN WINDOWS
👉 NEW ENGINE BREAK-IN AND OPERATION
👉 CARBURETOR AND PRIMING SYSTEM
👉 OVER-VOLTAGE SENSOR AND WARNING LIGHT
👉 GROUND SERVICE PLUG RECEPTACLE
👉 PITOT-STATIC SYSTEM AND INSTRUMENTS
👉 VACUUM SYSTEM AND INSTRUMENTS
👉 CESSNA CUSTOMER CARE PROGRAM
👉 PARKING
👉 TIE-DOWN
👉 JACKING
👉 LEVELING
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