Cessna 172


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.
62085 1489.7 lbs. 57133.0 917.2 lbs.

Maximum Weights

Maximum Weights Normal Utility
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.


Full 7 qt.
Minimum for Local Flight 6 qt.
Minimum for X-Country 7 qt.
Grade and Type Summer - 100W50 wt.
Winter - 65W30 wt.

Fuel System


Approved Grades 100LL (blue), 100 (green)
Total Fuel 43.0 Gal.
Total Usable 40.0 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:

Mains 28 psi
Nose 34 psi

Electrical System

Alternator 28 volt, 60 ampere
Battery 24 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 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