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Cessna 172R
Weights
| Aircraft Number |
Empty Weight |
Empty Moment |
Useful Load |
| 2382R |
1685.2 lbs. |
65,905.4 |
764.8.2 lbs. |
Maximum Weights
| |
Normal |
Utility |
| Ramp Weight |
2457 lbs. |
2107 lbs. |
| Takeoff Weight |
2450 lbs. |
2100 lbs. |
| Landing Weight |
2450 lbs. |
2100 lbs. |
| Baggage Weight |
120 lbs. |
empty |
| Area 1 |
120 lbs. |
empty |
| Area 2 |
50 lbs. |
empty |
Powerplant
Engine: Textron Lycoming IO-360, 160 BHP @ 2400 RPM. 4 Cylinders, Direct Drive, horizontally opposed, air cooled, fuel injected.
| Oil: |
Full |
8 qts. |
| |
Min for local flight |
6 qts. |
| |
Min for x-country |
7 qts. |
| |
Grade and type |
Summer-100W50 |
| |
|
Winter- 65W30 |
Fuel System
| Fuel: |
Approved Grades 100LL(blue), 100(green) |
| Total Fuel |
56 gal. |
| Total Usable Fuel |
53 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 nosewheel. Nosewheel 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: |
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 a split primary bus bar, with an essential bus wired between the two primaries to provide power for the master switch and annunciator circiuts. 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.
Speeds
BEST GLIDE SPEED |
|
65 KIAS |
| Stall in landing configuration |
Vso |
33 KIAS |
| Stall in cruise configuration |
Vs1 |
44 KIAS |
| Rotation speed |
Vr |
55 KIAS |
| Best angle of climb speed |
Vx |
60 KIAS |
| Best rate of climb speed |
Vy |
76 KIAS |
| Maneuvering speed |
Va |
|
| |
2450 lbs. |
99 KIAS |
| |
2100 lbs. |
92 KIAS |
| |
1600 lbs |
82 KIAS |
| Flaps extended |
Vfe |
|
| |
0-10° |
110 KIAS |
| |
10-30° |
85 KIAS |
| Max. structural cruising speed |
Vno |
129 KIAS |
| Enroute climb speed |
|
70-85 KIAS |
| Approach Speed |
|
60-70 KIAS |
| Never exceed speed |
Vne |
163 KIAS |
| Demonstrated Crosswind Component |
15 knots |
