Cessna 172 G430


Aircraft NumberEmpty WeightEmpty MomentUseful Load
633661481.1 lbs.57777.7918.9 lbs.
512041482.9 lbs.57760.2917.1 lbs.
549711487.1 lbs.57476.6912.9 lbs.

Maximum Weights

Maximum WeightsNormalUtility
Ramp Weight2407 lbs.2107 lbs.
Takeoff Weight2400 lbs.2100 lbs.
Landing Weight2400 lbs.2100 lbs.
Baggage Weight120 lbs.none
Area 1120 lbs.none
Area 250 lbs.none



Lycoming O-320, 160BHP @ 2700 RPM. Four cylinders, direct drive, horizontally opposed, air-cooled, carburetor-equipped.


Full7 qt.
Minimum for Local Flight6 qt.
Minimum for X-Country7 qt.
Grade and TypeSummer - 100W50 wt.
Winter - 65W30 wt.

Fuel System


Approved Grades100LL (blue), 100 (green)
Total Fuel43.0 Gal.
Total Usable40.0 Gal.

System Description:

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

System Description:

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.

Tire Inflation:

Mains28 psi
Nose34 psi

Electrical System

Alternator28 volt, 60 ampere
Battery24 volt

System Description:

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.

Pitot-Static System

System Description:

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


Stall in Landing ConfigurationVso33 KIAS
Stall in Cruise ConfigurationVs144 KIAS
Rotate SpeedVr55 KIAS
Best Angle of ClimbVx60 KIAS
Best Rate of ClimbVy76 KIAS
Maneuvering Speed1600 lbs.Va82 KIAS

2400 lbs99 KIAS
Flaps Extended0 - 10°Vfe110 KIAS
10 - 30°85 KIAS
Max Structural Cruising SpeedVno127 KIAS
Enroute Climb Speed75 - 85 KIAS
Approach SpeedVapp60 - 70 KIAS
Never ExceedVne158 KIAS
Demonstrated Crosswind Component15 knots