Discuss V-speeds (PHAK 10-17) (POH section 2)
68 KIAS - Best Glide Speed
Vso 40KIAS - Stall in landing configuration
Vs1 48KIAS - Stall in cruise configuration
Vr 55 KIAS - Rotation speed
Vx 62 KIAS - Best angle of climb speed (greatest altitude gain per distance over the ground)
Vy 74 KIAS - Best rate of climb speed (greatest altitude gain per unit of time)
Va - Maneuvering speed
105 KIAS 2550 lbs.
98 KIAS 2200 lbs.
90 KIAS 1900 lbs
Vfe - Flaps extended
110 KIAS 0-10°
85 KIAS 10-30°
Vno 129 KIAS - Max. structural cruising speed (flight above this speed only permissible in smooth air)
75-85 KIAS - Enroute climb speed
60-70 KIAS - Approach Speed
Vne 163 KIAS - Never exceed speed
Demonstrated Crosswind Component 15 knots
Weights
Aircraft Number Empty Weight Empty Moment Useful Load
N3506X 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 20 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
- A - Airspeed - (best glide)
- B - Best Landing Site
- C - Checklist - (a quick flow before even touching the checklist: mixture full in, gas on fullest tank mag switch to one and/or two
- D - Declare - (7700/ATC)
- E - Egress - (ensure seat belts are secure, open door so it doesn’t get jammed, if available, use soft objects for protection.
Aircraft Performance
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