Data Sheet- Cessna 172SP

 

Data Sheet- Cessna 172SP

Weights

Aircraft Number Empty Weight Empty Moment Useful Load

N*50** 1676.2 lbs 67,731 881.8 lbs

 

Maximum Weights Normal Utility

Ramp Weight 2558 lbs 2208 lbs

Takeoff Weight 2550 lbs 2200 lbs

Landing Weight 2550 lbs 2200 lbs

Baggage Weight 120 lbs. empty

Area 1 120 lbs empty

Area 2 50 lbs empty

 

Powerplant

Engine: Textron Lycoming IO-360, 180 BHP @ 2700 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 38 PSI

Nose 45 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 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.

 

Speeds

BEST GLIDE SPEED 68 KIAS

Stall in landing configuration Vso 40 KIAS

Stall in cruise configuration Vs1 48 KIAS

Rotation speed Vr 55 KIAS

Best angle of climb speed Vx 62 KIAS

Best rate of climb speed Vy 74 KIAS

Maneuvering speed Va

2550 lbs. 105 KIAS

2200 lbs. 98 KIAS

1900 lbs 90 KIAS

Flaps extended Vfe

0-10° 110 KIAS

10-30° 85 KIAS

 

Max. structural cruising speed Vno 129 KIAS

Enroute climb speed 75-85 KIAS

Approach Speed 60-70 KIAS

Never exceed speed Vne 163 KIAS

Demonstrated Crosswind Component 15 knots