Cessna 172RG


Aircraft Number Empty Weight Empty Moment Useful Load
9584B 1692.5 lbs. 64803.0 965.0 lbs.

Maximum Weights

Maximum Weights
Ramp Weight 2658 lbs.
Takeoff Weight 2650 lbs.
Landing Weight 2650 lbs.
Baggage Weight 200 lbs.
Area 1 200 lbs.
Area 2 50 lbs.



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


Full 8 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 66.0 Gal.
Total Usable 62.0 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, engine driven fuel pump, auxiliary electric fuel pump, and carburetor. Fuel flows by gravity from one or both tanks, through a fuel strainer to the auxiliary pump and engine driven pump to the carburetor. From the carburetor, the fuel/air mixture flows to the cylinders. The auxiliary fuel pump should be used whenever fuel pressure falls below .5 psi. 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 a retractable tricycle type with a steerable nose wheel. Shock absorption is accomplished through tubular spring steel main gear struts and an air/oil nose gear strut. Nose wheel steering will turn the nose wheel through a 15 degree arc each side of center. Differential braking will increase the turning arc up to 30 degrees each side of center. Each main gear is equipped with a hydraulically actuated disc type brake. When the gear lever is moved up or down, it creates a pressure change which electrically activates the hydraulic power pack which then hydraulically raises or lowers the gear. The gear is held in the UP position by hydraulic pressure and in the DOWN position by mechanical locks. A squat switch on the nose gear prevents inadvertent raising of the gear while on the ground. A hand operated hydraulic pump is provided for manual extension of the landing gear in the event of a hydraulic power pack failure. A gear warning horn sounds when the one or all of the gear are not locked down and the manifold pressure drops below 12 inches or flaps are extended beyond 20 degrees. A green gear light indicates all three gear are down and locked. An amber light indicates that all of the gear are up and locked. No lights illuminated indicates gear in transition.

Tire Inflation:

Mains 40 - 50 psi
Nose 60 - 68 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 ammeter is connected to the battery and shows whether the battery is charging or discharging. 

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


​1850 lbs. ​61 KIAS
Stall in Landing Configuration Vso 42 KIAS
Stall in Cruise Configuration Vs1 50 KIAS
Rotate Speed Vr 55 KIAS
Best Angle of Climb Vx 67 KIAS
Best Rate of Climb Vy 84 KIAS
Maneuvering Speed 2350 lbs. Va 106 KIAS

1850 lbs 89 KIAS
Flaps Extended 0 - 10° Vfe 130 KIAS
10 - 30° 100 KIAS
​Max Landing Gear Operating Speed ​Vlo ​140 KIAS
​Max Landing Gear Extended Speed ​Vle ​164 KIAS
Max Structural Cruising Speed Vno 145 KIAS
Enroute Climb Speed 85 - 95 KIAS
Approach Speed Vapp 60 - 70 KIAS
Never Exceed Vne 164 KIAS
Demonstrated Crosswind Component 15 knots