|Aircraft Number||Empty Weight||Empty Moment||Useful Load|
|N35063||1676.2 lbs.||67,731||881.8 lbs.|
|Ramp Weight||2558 lbs.||2208 lbs.|
|Takeoff Weight||2550 lbs.||2200 lbs.|
|Landing Weight||2550 lbs.||2200 lbs.|
|Baggage Weight||120 lbs.||none|
|Area 1||120 lbs.||none|
|Area 2||50 lbs.||none|
Lycoming O-360, 180BHP @ 2700 RPM. Four cylinders, direct drive, horizontally opposed, air-cooled, carburetor-equipped.
|Minimum for Local Flight||6 qt.|
|Minimum for X-Country||7 qt.|
|Grade and Type||Summer - 100W50 wt.|
Winter - 65W30 wt.
|Approved Grades||100LL (blue), 100 (green)|
|Total Fuel||56 Gal.|
|Total Usable||53 Gal.|
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
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.
|Alternator||28 volt, 60 ampere|
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.
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.
|BEST GLIDE SPEED||65 KIAS|
|Stall in Landing Configuration||Vso||40 KIAS|
|Stall in Cruise Configuration||Vs1||48 KIAS|
|Rotate Speed||Vr||55 KIAS|
|Best Angle of Climb||Vx||62 KIAS|
|Best Rate of Climb||Vy||74 KIAS|
|Maneuvering Speed||2550 lbs.||Va||105 KIAS|
|2200 lbs||98 KIAS|
|||1900 lbs||||90 KIAS|
|Flaps Extended||0 - 10°||Vfe||110 KIAS|
|10 - 30°||85 KIAS|
|Max Structural Cruising Speed||Vno||129 KIAS|
|Enroute Climb Speed||75 - 85 KIAS|
|Approach Speed||Vapp||60 - 70 KIAS|
|Never Exceed||Vne||163 KIAS|
|Demonstrated Crosswind Component||15 knots|