Cessna 172 G430
|Aircraft Number||Empty Weight||Empty Moment||Useful Load|
|63366||1481.1 lbs.||57777.7||918.9 lbs.|
|51204||1482.9 lbs.||57760.2||917.1 lbs.|
|54971||1487.1 lbs.||57476.6||912.9 lbs.|
|Ramp Weight||2407 lbs.||2107 lbs.|
|Takeoff Weight||2400 lbs.||2100 lbs.|
|Landing Weight||2400 lbs.||2100 lbs.|
|Baggage Weight||120 lbs.||none|
|Area 1||120 lbs.||none|
|Area 2||50 lbs.||none|
Lycoming O-320, 160BHP @ 2700 RPM. Four cylinders, direct drive, horizontally opposed, air-cooled, carburetor-equipped.
|Minimum for Local Flight||6 qt.|
|Minimum for X-Country||7 qt.|
|Grade and Type||Summer - 100W50 wt.|
Winter - 65W30 wt.
|Approved Grades||100LL (blue), 100 (green)|
|Total Fuel||43.0 Gal.|
|Total Usable||40.0 Gal.|
The airplane is equipped with a standard fuel system consisting of two vented fuel tanks, a fuel tank selector valve, fuel strainer, manual primer, and carburetor. Fuel flows by gravity form one or both tanks to the fuel selector, through a fuel strainer to the carburetor. From the carburetor, the fuel/air mixture flows to the cylinders. The fuel selector should be in the BOTH position for takeoff, climb, descent, landing, and maneuvers that involve prolonged slips or skids. Operation from either the LEFT or RIGHT position is reserved for level cruising flight only.
Landing Gear and Brakes
Landing gear is fixed in the tricycle configuration with a steerable nosewheel. Nosewheel is steerable through a 10 degree arc each side of center. Differential braking increases the turning arc to 30 degrees of center. Nose strut is an air-oil type shock. Each main gear is equipped with a hydraulically activated single disk brake on the inboard side of each wheel.
|Alternator||28 volt, 60 ampere|
Power is supplied to most general electrical items through the primary bus. All avionics are powered by the avionics bus. The two busses are tied together through the avionics power switch, which also functions as a circuit breaker for the avionics bus. The avionics power switch should be turned off prior to starting the engine to prevent harmful transient voltages from damaging the avionics equipment. The ammeter shows a charge or discharge on the battery and should remain at or near the zero indication after a brief charging period.
The system is standard with a heated pitot head under the left wing and a static port on the left nose cowling. The alternate static source is located on the panel below the throttle and supplies static pressure from inside the cockpit
|BEST GLIDE SPEED||65 KIAS|
|Stall in Landing Configuration||Vso||33 KIAS|
|Stall in Cruise Configuration||Vs1||44 KIAS|
|Rotate Speed||Vr||55 KIAS|
|Best Angle of Climb||Vx||60 KIAS|
|Best Rate of Climb||Vy||76 KIAS|
|Maneuvering Speed||1600 lbs.||Va||82 KIAS|
|2400 lbs||99 KIAS|
|Flaps Extended||0 - 10°||Vfe||110 KIAS|
|10 - 30°||85 KIAS|
|Max Structural Cruising Speed||Vno||127 KIAS|
|Enroute Climb Speed||75 - 85 KIAS|
|Approach Speed||Vapp||60 - 70 KIAS|
|Never Exceed||Vne||158 KIAS|
|Demonstrated Crosswind Component||15 knots|