I'll describe the little Cessna 152 II I fly hehe. I'll be taking the information from the POH (Pilot Operating Handbook)
Airplane and Systems Descriptions
The airplane is an all-metal, two-place, high-wing, single-engine airplane equipped with tricycle landing gear and designed for general utility purposes.
The airplane's flight control system consists of conventional aileron, rudder, and elevator control surfaces. The control surfaces are manually operated through mechanical linkage using a control wheel for the ailerons and elevator, and rudder/brake pedals for the rudder.
The instrument panel is designed to place the primary flight instruments directly in front of the pilot. The gyro-operated flight instruments are arranged one above the other, slightly to the left of the control column. To the left of these instruments is the airspeed indicator, turn coordinator, and suction gage. The clock, altimeter, rate-of-climb indicator, and navigation instruments are above and/or to the right of the control column. Avionics equipment is stacked approximately on the centerline of the panel, with space for additional equipment on the lower right side of the instrument panel. The right side of the panel also contains the tachometer, ammeter, low-voltage light, and additional instruments such as a flight hour recorder. The left switch and control panel, under the primary instrument panel, contains the fuel quantity indicators, cigar lighter, and engine instruments positioned below the pilot's control wheel.
The electrical switches, panel and radio light rheostat knob, ignition and master switches, primer, and parking brake control are located around these instruments. The engine controls, wing flap switch, and cabin air and heat control knobs are to the right of the pilot, at the center of the switch and control panel. Directly below these controls are the elevator trim control wheel, trim position indicator, microphone, and circuit breakers. A map compartment is on the extreme right side of the switch and control panel.
Effective ground control while taxiing is accomplished through nose wheel steering by using the rudder pedals; left rudder pedal to steer left and right rudder pedal to steer right. When a rudder pedal is depressed, a spring-loaded steering bungee (which is connected to the nose gear and to the rudder bars) will turn the nose wheel through an arc of approximately 8.5º each side of center. By applying either left or right brake, the degree of turn may be increased up to 30º each side of center.
WING FLAP SYSTEM
The wing flaps are of the single-slot type, and are extended or retracted by positioning the wing flap switch lever on the instrument panel to the desired flap deflection position. The switch lever is moved up or down in a slot in the instrument panel that provides mechanical stops at the 10º and 20º positions. For flap settings greater than 10º, move the switch lever to the right to clear the stop and position it as desired.
LANDING GEAR SYSTEM
The landing gear is of the tricycle type with a steerable nose wheel and two main wheels. The landing gear may be equipped with wheel fairings. 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. When wheel fairings are installed an aerodynamic fairing covers each brake.
The airplane is powered by a horizontally-opposed, four-cylinder, overhead-valve, air-cooled, carbureted engine with a wet sump oil system.
The engine is a Lycoming Model 0-235-L2C and is rated at 110 horsepower at 2550 RPM. Major engine accessories include a starter, a belt-driven alternator, and an oil cooler. Dual magnetos are mounted on an accessory drive pad on the rear of the engine. Provisions are also made for a vacuum pump and full flow oil filter.
The airplane is equipped with a two-bladed, fixed-pitch, one-piece forged aluminum alloy propeller which is anodized to retard corrosion. The propeller is 69 inches in diameter.
The airplane is equipped with either a standard fuel system. The system consists of two vented fuel tanks (one in each wing), a fuel shutoff valve, fuel strainer, manual primer, and carburetor.
TOTAL FUEL VOLUME: 26 Gallons
TOTAL USABLE FUEL ALL FLIGHT CONDITIONS: 24.5 Gallons
The airplane is equipped with a 28-volt, direct-current electrical system. This system uses a 24-volt battery mounted on the right forward side of the firewall as the source of electrical energy and an engine-driven 60-amp alternator to maintain the battery's state of charge. Power is supplied to a bus bar, and a master switch controls this power to all circuits, except the engine ignition system, clock, and flight hour recorder (if installed). The flight hour recorder receives power through activation of an oil pressure switch whenever the engine is operating, and the clock is supplied with current at all times. All avionics equipment should be turned off prior to starting the engine or using an external power source to prevent harmful transient voltages from damaging the transistors in this equipment.
Performance and Speeds (KIAS)
Maximum at Sea Level: 110 knots
RATE OF CLIMB AT SEA LEVEL: 715 FPM
SERVICE CEILING: 14,700 FT
Ground Roll: 725 ft
Total Distance over 50 ft obstacle: 1340 ft
Ground roll: 475 ft
Total Distance over 51 ft obstacle: 1200 ft
STALL SPEED (CAS)
Flaps up, power off: 48 knots
Flaps down, power off: 43 knots
Ramp: 1675 lbs
Takeoff or landing: 1670 lbs
STANDARD EMPTY WEIGHT
152 II: 1133 lbs
MAXIMUM USEFUL LOAD
152 II: 542 lbs
BAGGAGE ALLOWANCE: 120 LBS
SPEEDS FOR NORMAL OPERATION (KIAS)
Normal Climb Out: 65-75
Short Field Takeoff. Flaps 101, Speed at 50 Feet: 54
Climb, Flaps Up:
Best Rate of Climb, Sea Level: 67
Best Rate of Climb, 10,000 Feet: 61
Best Angle of Climb, Sea Level thru 10,000 Feet: 55
Normal Approach, Flaps Up: 60-70
Normal Approach, Flaps 30: 55-65
Short Field Approach, Flaps 30: 54
Maximum Power, Flaps 20: 55
Maximum Recommended Turbulent Air Penetration Speed:
1670 Lbs: 104
1500 Lbs: 98
1350 Lbs: 93
Maximum Demonstrated Crosswind Velocity: 12 knots
Next one: emergency procedures.