Cessna 152 Section 7 POH Airplane & Systems Descriptions

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bharris
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264245
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Cessna 152 Section 7 POH Airplane & Systems Descriptions
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2014-03-05 22:08:40
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Cessna152 POH Airplane Systems Aviation CPL Canada
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Questions based on section 7 of Cessna 152 POH
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  1. What is the type of skin design and material?
    Semimonocoque and made from aluminum
  2. Which instruments are gyroscopic?
    Attitude indicator and heading indicator
  3. What instruments are part of the pitot-static system? Which ones use pitot/static?
    Instruments included are airspeed indicator, altimeter and vertical speed indicator. The altimeter and vertical speed indicator rely on the static port while the airspeed indicator relies on both static port and pitot tube
  4. Explain how the plane steers during taxiing.
    The plane is turned with nose wheel steering by using the left and right rudder pedals. When a pedal is compressed, a spring-loaded steering bungee turns the nose wheel about 8.5° each side of center. When also applying the corresponding break pedal, the turn can be increased up to 30° each side of center
  5. What type of wing flaps? How many degrees? What protects this system electronically?
    They are single-slot type flaps that are extended or retracted by moving a lever in the cockpit. It has stops at 10° and 20° but the full range is 0°-30°. The flap system is protected by a 15 ampere circuit breaker labeled "FLAP" on the right side of the instrument panel.
  6. Explain the landing gear. Type? Shock absorption? Breaking?
    It is tricycle type with a steerable nose wheel and 2 main wheels. Shock absorption is provided by the spring-steel main landing gear struts and the air/oil nose gear shock strut. Breaking is provided by hydraulically actuated disc-type brakes on the inboard side of each main gear wheel.
  7. Where are the baggage loading areas and what are the weight limits?
    There are 2 areas which are only accessible from the cabin. The center of area 1 has an arm of 64" with a maximum allowable weight of 120lbs. The center of area 2 has an arm of 84" and a maximum allowable weight of 40lbs. Together the maximum weight allowed in the baggage compartment is 120lbs.
  8. What is a general description of the engine? Cylinders? Cooled? Type?
    Horizontally-opposed, 4 cylinder, overhead-valve, air cooled, carbureted engine with a wet sump oil system. 
  9. What is the engine model and horsepower?
    Lycoming model O-235-L2C and is rated at 110 horsepower at 2550 RPM
  10. What powers the oil pressure gauge? What are the limits? Both red and green range.
    It is operated directly from the oil pressure in the engine. A direct pressure oil line from the engine delivers oil at engine operating pressure to the oil pressure gauge. The limits are: 25psi (red) 60-90psi (green) 100psi (red)
  11. What powers the oil temperature gauge? What are the limits? Both red and green range.
    It is operated by an electrical-resistance type temperature sensor which receives power from the airplane's electrical system. The limits are 100°-245°F (green) 245°F (red)
  12. What drives the tachometer? What is the normal operating range (green arc)?
    The engine powers the tachometer and the operating range is 1900-2550 RPM
  13. What is the total usable fuel, total unusable fuel and total fuel volume for standard tanks?
    Usable 24.5 gal, unusable is 1.5 gal and total volume is 26 gal
  14. What is the total usable fuel, total unusable fuel and total fuel volume for long range tanks?
    Usable 37.5 gal, unusable 1.5 gal and total volume is 39 gal
  15. Describe the propeller
    2 bladed, fixed-pitch, one-piece forged aluminum alloy propeller which is anodized to retard corrosion. It is 69" in diameter.
  16. Describe the cooling system. Type? Where? How?
    Ram air for engine cooling enters through two intake openings in the front of the engine cowling. The air is directed around the cylinders and other areas of the engine by baffling. No manual cooling system control is provided.
  17. What is the capacity of the engine sump? If there's a full flow oil filter? Where is the sump located?
    The capacity is 6 quarts, unless when a full flow oil filter is installed it is 7 quarts. The engine sump is located on the bottom of the engine.
  18. What are the steps the oil going through starting from the engine sump. Assume a full flow oil filter isn't installed.
    Oil is drawn from the sump through an oil suction strainer screen into the engine driven oil pump. From the pump, oil is directly routed to the oil cooler and returns to the engine where it passes through the pressure screen.
  19. The engine should not be operated under what amount of oil?
    Not less than 4 quarts of oil
  20. How many magnetos and spark plugs are there in total? Per cylinder?
    2 magnetos and 2 spark plugs per cylinder. Total of 8 spark plugs and 2 magnetos.
  21. Why is normal operation conducted with both magnetos?
    Due to a more complete burning of the fuel-air mixture. Left and right positions should only be used for checking magnetos and emergencies.
  22. What is the order air goes through in the induction system?
    Ram air flows in through an intake in the lower portion of the engine cowling which is also filtered. After passing through the filter it enters the airbox, where it then enters an inlet to the carburetor. It is then ducted to the engine through intake manifold tubes. If there is carb ice or the intake filter is blocked, carb heat can be applied which is unfiltered heated air.
  23. With use of full carb heat at full throttle, how much RPM is expected to be lost?
    150-200 RPM
  24. What type of carburetor is it and where is it located?
    It's an updraft, float-type, fixed jet carburetor located on the bottom of the engine.
  25. What happens to the fuel when it's in the carburetor?
    It gets atomized
  26. Explain how the fuel gets from the tanks to the engine.
    Fuel flows by gravity from the wing tanks to the fuel shutoff valve. With the valve turned to "ON" fuel flows through a strainer to the carburetor. The carburetor mixes fuel and air and then flows to the engine cylinders through intake manifold tubes.
  27. How does the primer work? Where is the fuel from?
    The primer draws fuel from the fuel strainer and directly injects it into the cylinder intake port. This is manually done by pulling/pushing the plunger on the lower left side of the instrument panel.
  28. Where are the fuel system vents?
    There is a vent in each wing, and they are linked by an interconnecting line. The left wing is vented overboard through a line that protrudes from the bottom surface of the wing. The right wing is vented at the fuel tank cap.
  29. How much fuel is left when the fuel quantity indicators are on the red line showing empty?
    There is 0.75 gallons left of unusable fuel in that tank.
  30. When can't the fuel indicators be relied upon for accurate readings?
    During skids, slips or unusual attitudes.
  31. Describe the brake system. What kind? Connected to? How are they operated?
    They are single-disc, hydraulically-actuated brakes on each main landing gear wheel. Each brake is connected by a hydraulic line to a master cylinder attached to each pilot's rudder pedals. They are operated by applying pressure to the top of either the left or right seat's rudder pedals, which are interconnected.
  32. What are some symptoms of impending brake failure?
    Gradual decrease in breaking after application, noisy or dragging breaks, soft or spongy pedals, excessive travel and weak breaking action.
  33. What kind of electrical system and battery is there?
    28-volt direct-current electrical system that uses a 24-volt battery.
  34. Where is the battery located? What charges it? Describe.
    The battery is mounted on the right forward side of the firewall and an engine-driven 60-amp alternator is used to maintain the battery's state of charge.
  35. What powers the flight hour recorder?
    It receives power through activation of a oil pressure switch whenever the engine is operating.
  36. The master switch controls power to all circuits except what? What controls them?
    The engine ignition system, clock, and flight hour recorder. The ignition system is powered by 2 magnetos, the clock is powered by the battery and flight hour recorder is powered by an oil pressure switch whenever the engine is running.
  37. What does the left and right sides of the master switch control?
    The left side controls the alternator and the right side controls the battery. The right side can be independently turned on from the left.
  38. What will happen if there is continued operation with the alternator switched off?
    It will reduce battery power low enough to open the battery contactor, remove power from the alternator field, and prevent alternator restart.
  39. What unit does the ammeter measure in?
    Amperes
  40. What kind of pressure is supplied to the pitot tube? Static port?
    Ram air pressure is supplied to the pitot tube while static pressure is supplied to the static port.
  41. On the airspeed indicator, what are the speeds in the white arc, green arc, yellow arc and red line?
    White arc: 35-85kts Green arc: 40-111kts Yellow arc: 111-149kts Red line: 149 kts
  42. What drives the vacuum system?
    The engine
  43. On an attitude indicator, what bank angles are are marked?
    10°, 20°, 30°, 60° and 90°
  44. What electrical circuits are not protected by circuit breakers?
    Battery contactor closing circuit, clock circuit, and flight hour recorder circuit. These circuits are protected by fuses.
  45. What unit of measurement is the suction gauge? Desired range?
    It's measured in inches of mercury and the desired suction range is 4.5-5.4 inches of mercury.
  46. When does the stall horn sound?
    It sounds at 5-10kts above the stall speed in all flight conditions.
  47. Describe the stall warning system. Where is it? How does it work?
    Pneumatic-type stall warning system consisting of an inlet in the leading edge of the left wing, an air operated horn near the upper left corner of the windshield, and associated plumbing. As the airplane approaches a stall the low pressure on the upper surface of the wings moves forward, which creates a differential pressure in the stall warning system. This draws air through the warning horn resulting in an audible warning 5-10kts above the stall.

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