Cessna 172SP


Aircraft NumberEmpty WeightEmpty MomentUseful Load
N350631676.2 lbs.67,731881.8 lbs.

Maximum Weights

Maximum WeightsNormalUtility
Ramp Weight2558 lbs.2208 lbs.
Takeoff Weight2550 lbs.2200 lbs.
Landing Weight2550 lbs.2200 lbs.
Baggage Weight120 lbs.none
Area 1120 lbs.none
Area 250 lbs.none



Lycoming O-360, 180BHP @ 2700 RPM. Four cylinders, direct drive, horizontally opposed, air-cooled, carburetor-equipped.


Full8 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 Fuel56 Gal.
Total Usable53 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, and auxiliary fuel pump. Fuel flows by gravity from one or both tanks to the fuel selector, through a fuel strainer to the injector manifold. From the injector, the fuel flows to the cylinders and is mixed with air at the intake port. The fuel selector should be in the BOTH position for takeoff, climb, descent, landing, and maneuvers that involve prolonged slips and 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 nose wheel. Nose wheel is steerable and differential braking allows for a tighter turn radius. 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:

Mains38 psi
Nose45 psi

Electrical System

Alternator28 volt, 60 ampere
Battery24 volt

System Description:

Power is supplied to most general electrical items through a split primary bus bar, with an essential bus wired between the two primaries to provide power for the master switch and annunciator circuits. Each primary bus bar is also connected to an avionics bus bar via a single avionics power switch. 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 discharge or a charge 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 two static ports on either side of the nose cowling. The alternate static source is located on the panel above the throttle and supplies static pressure from inside the cockpit.


Stall in Landing ConfigurationVso40 KIAS
Stall in Cruise ConfigurationVs148 KIAS
Rotate SpeedVr55 KIAS
Best Angle of ClimbVx62 KIAS
Best Rate of ClimbVy74 KIAS
Maneuvering Speed2550 lbs.Va105 KIAS

2200 lbs98 KIAS
​1900 lbs​90 KIAS
Flaps Extended0 - 10°Vfe110 KIAS
10 - 30°85 KIAS
Max Structural Cruising SpeedVno129 KIAS
Enroute Climb Speed75 - 85 KIAS
Approach SpeedVapp60 - 70 KIAS
Never ExceedVne163 KIAS
Demonstrated Crosswind Component15 knots