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Aircraft Rental

 

Cessna 152

Cessna 152

The Cessna 152 is an American built, two seat, fixed tricycle gear general aviation aircraft. It has become synonymous with flight training since the late seventies when production began. Its docile stall characteristics, excellent glide ratio and small power plant make it the perfect trainer for the bulk of pilots flying today. The high wing design affords fantastic visibility of the ground below, providing excellent photo opportunities of the surrounding area.

General Characteristics

  • Crew: 1 pilot
  • Capacity: 1 passenger
  • Length: 24 ft 1 in (7.3 m)
  • Wingspan: 33 ft 4 in (10.2 m)
  • Height: 8 ft 6 in (2.6 m)
  • Wing area: 160 ft² (14.9 m²)
  • Empty weight: 1,081 lb (490 kg)
  • Max takeoff weight: 1,670 lb (757 kg)
  • Powerplant: 1× Lycoming O-235-L2C flat-4 engine, 110 hp (82 kW) driving a 69 in (175 cm), two-blade, fixed-pitch propeller
Performance
  • Maximum speed: 126 mph (110 knots, 204 km/h)
  • Cruise speed: 123 mph (107 knots, 198 km/h)
  • Stall speed: 49 mph (43 knots, 79 km/h) unpowered, flaps down
  • Range: 477 mi (414 nm, 768 km)
  • Extended range 795 mi (690 nm, 1,280 km) with long-range tanks
  • Service ceiling: 14,700 ft (4,480 m)
  • Takeoff roll: 725 ft (221 m)
  • Rate of climb: 715 ft/min (3.6 m/s)
  • Max wing loading: 10.44 lb/ft² (51 kg/m²)
  • Minimum power/mass: .066 hp/lb (108 W/kg)

 

Cessna 172 Skyhawk

The Cessna 172 Skyhawk is a four seat, single engine, high fixed wing aircraft. First flown in 1955 and still in production. More Cessna 172's have been built than any other aircraft.

Early 172's were similar in appearance to the 170, with the same straight aft fuselage and tall gear legs, althought the 172 had a straight vertical tail while the 170 had a rounded fin and rudder. Later 172 versions incorporated revised landing gear and sweptback tail which is still in used today. The final aesthetic development, in the mid 1960s, was a lowered rear deck that allowed an aft window. Cessna advertised this added rear visibility this added rear visibility as "omni-vision." This airframe configuration has remaind almost unchanged since then, except for updates in avionics and engines, including the Garmin G1000 cockpit in 2005. Production had been halted in the mid 1980s, but was resumed in 1996.

General characteristics

  • Crew: 1 pilot
  • Capacity: 3 passengers
  • Length: 27 ft 2 in (8.28 m)
  • Wingspan: 36 ft 1 in (11.0 m)
  • Height: 8 ft 11 in (2.72 m)
  • Wing area: 174 ft² (16.2 m²)
  • Airfoil: NACA 2412 (modified)
  • Empty weight: 1,620 lb (736 kg)
  • Useful load: 830 lb (376 kg)
  • Max takeoff weight: 2,450 lb (1,113 kg)
  • Powerplant: 1× Lycoming IO-360-L2A flat-4 engine, 160 hp (120 kW) at 2,400 rpm
  • Drag area: 5.58 ft² (0.52 m²)
  • Aspect ratio: 7.32
  • Lift-to-drag ratio: 11.6
  • Wing loading: 14.1 lb/ft² (68.8 kg/m²)
  • Power/mass: 15.3 lb/hp (9.25 kg/kW)
Performance
  • Never exceed speed: 163 knots (187 mph, 302 km/h)
  • Maximum speed: 123 knots (141 mph, 228 km/h) at sea level
  • Cruise speed: 122 knots (140mph, 226 km/h)
  • Range: 610 nm (790 mi, 1,272 km) at 55% power at 12,000 ft (3,040 m)
  • Service ceiling: 13,500 ft (4,116 m)
  • Rate of climb: 720 ft/min (3.7 m/s) 

 

Piper Warrior

Warrior The Piper A-28 Cherokee is a family of light aircraft designed for flight training, air taxi and personal use, built by Piper Aircraft. All members of the PA-28 family are all-metal, unpressurized, four-seat, single-engine piston-powered airplanes with low-mounted wings and tricycle landing gear. All PA-28 aircraft have a single door on the co-pilot side, which is entered by stepping on the wing.  Piper has created variations within the Cherokee family by installing engines ranging from 140 to 300 horsepower.  In 1978, Piper upgraded the Warrior to 160 horsepower (119 kW) PA-28-161, changing its name to Cherokee Warrior II.

General Characteristics

  • Crew: 1 pilot
  • Capacity: 3 passengers
  • Length: 23.3 feet (7.16 m)
  • Wingspan: 30.0 feet (9.2 m)
  • Height: 7.3 feet (2.25 m)
  • Wing area: 160 sq ft (15.14 m²)
  • Airfoil: NACA 652-415
  • Empty weight: 1201 lb (544 kg)
  • Loaded weight: 2150 lb (975 kg)
  • Useful load: 949 lb (430 kg)
  • Max takeoff weight: 2150 lb (975 kg)
  • Powerplant: 1× Lycoming O-320-E2A Sensenich M74DM, 150 hp (113 kW)
  • Propeller diameter: 74 inches (1.9 m)
Performance
  • Maximum speed: 123 knots (142 mph, 230 km/h)
  • Cruise speed: 108 knots (124 mph (200 km/h), 201 km/h)
  • Stall speed: 47 knots (54 mph, 87 km/h)
  • Range: 465 nm (535 sm, 867 km)
  • Service ceiling: 14,300 feet (4400 m)
  • Rate of climb: 660 ft/min (3.4 m/s)
  • Wing loading: 13.4 lb/sq ft (64.4 kg/sq m)
  • Power/mass: 14.3 lb/hp (0.116 kW/kg) 

 

Piper Arrow

In 1967, Piper introduced the PA-28-180 Arrow. This aircraft featured a constant-speed propeller and retractable landing gear and was powered by a 180 horsepower (134 kW) Lycoming IO-360-B1E engine. The engine was upgraded to a Lycoming IO-360-C1C of 200 horsepower (149 kW) in 1971 and the designation was changed to PA-28R-200.  In 1968, the cockpit was modified to replace the "push-pull" style engine controls with levers. In addition, a third window was added to each side, giving the fuselage the more modern look seen in current production.

General Characteristics
  • Crew: 1 pilot
  • Capacity: 3 passengers
  • Length: 23.3 feet (7.16 m)
  • Wingspan: 30.0 feet (9.2 m)
  • Height: 7.3 feet (2.25 m)
  • Wing area: 160 sq ft (15.14 m²)
  • Airfoil: NACA 652-415
  • Empty weight: 1201 lb (544 kg)
  • Loaded weight: 2150 lb (975 kg)
  • Useful load: 949 lb (430 kg)
  • Max takeoff weight: 2150 lb (975 kg)
  • Powerplant: 1× Lycoming IO-360-C1C flat-4 engine, 200 hp (149 kW)
  • Propeller diameter: 74 inches (1.9 m)

Performance

  • Maximum speed: 123 knots (142 mph, 230 km/h)
  • Cruise speed: 108 knots (124 mph, 201 km/h)
  • Stall speed: 47 knots (54 mph, 87 km/h)
  • Range: 465 nm (535 sm, 867 km)
  • Service ceiling: 14,300 feet (4400 m)
  • Rate of climb: 660 ft/min (3.4 m/s)
  • Wing loading: 13.4 lb/sq ft (64.4 kg/sq m)
  • Power/mass: 14.3 lb/hp (0.116 kW/kg)

 

Robinson R-22

The Robinson R-22 is a two-bladed, single-engine light utility helicopter manufactured by Robinson Helicopter. The two-seat R-22 was designed in 1973 by Frank Robinson and has been in production since 1979.  Due to relatively low acquisition and operating costs, the R-22 has been popular as a primary rotorcraft trainer around the world, and as a livestock management tool on large ranches in North America and cattle stations in Australia. The R-22 has a very low inertia rotor system and the control inputs are operated directly by push rods with no hydraulic assistance. Thus, the flight controls are very sensitive and require a light touch to avoid over correcting. A student that masters an R-22 generally does not have a problem transitioning to a heavier helicopter.

General Characteristics

  • Crew: 1 pilot
  • Capacity: 1 passenger
  • Length: 28 ft 8 in (8.7 m)
  • Rotor diameter: 25 ft 4 in (7.7 m)
  • Height: 8 ft 11 in (2.7 m)
  • Disc area: 497 ft² (46.2 m²)
  • Empty weight: 796 lb (389 kg)
  • Loaded weight: 920 lb (417 kg)
  • Max takeoff weight: 1,370 lb (635 kg)
  • Powerplant: 1× Lycoming O-320-A2B or -A2C flat 4 piston engine, 124 hp (93 kW)
  • Main tank total capacity: 19.8 US gallons (75 liters)
  • Main tank usable capacity: 19.2 US gallons (73 liters)
  • Optional aux tank total capacity: 10.9 US gallons (41 liters)
  • Optional aux tank usable capacity: 10.5 US gallons (40 liters)
Performance
  • Never exceed speed: 117 mph, 189 km/h, 102 kts
  • Cruise speed: 99 mph, 160 km/h, 86 kts
  • Range: 240 mi (386 km)
  • Service ceiling: 14,000 ft (4,267 m)
  • Rate of climb: 1,200 ft/min (6.1 m/s)
  • Disc loading: 2.61 lb/ft² (13.7 kg/m²)
  • Power/mass: 0.095 hp/lb (0.147 kW/kg)
  • Endurance: approx. 2 hours, with 30-minute reserve

Robinson R-44

R-44The Robinson R-44 is a small American, four seat piston driven civilian helicopter produced by the Robinson Helicopter Company since 1992.

While resembling the company's earlier Robinson R-22, the R-44 is larger and faster than its predecessor. It also features boosted flight controls, a feature not found on the R-22. The Raven models have hydraulically assisted cyclic and collective controls. The Raven II model (2002 onwards) uses a fuel injected engine, tuned induction, optional night VFR 28-volt electrical system, and extended chord blades for increased performance. 

The R-44 is a single engine helicopter with a semi rigid two bladed main rotor and a two bladed tail rotor and skid landing gear. The enclosed cabin has two rows of side-by-side seating to accommodate the pilot and three passengers. Tail rotor direction of rotation on the R-44 is reversed compared to the R-22 for improved yaw control authority. On the R-44 the advancing blade is on the bottom. 

General Characteristics

  • Crew: 1 (pilot)
  • Capacity: 3 (passengers)
  • Payload: 900 lb (408 kg)
  • Length: (body only) 21 ft 5 in (9.0 m)
  • Rotor diameter: 33 ft (10.1 m)
  • Height: 10 ft 9 in (3.3 m)
  • Empty weight: 1450 lb (657.7 kg)
  • Loaded weight: 2500 lb (1134 kg)
  • Powerplant: 1× Lycoming IO-540-AE1A5 6 cylinder, horizontally opposed, direct drive, air cooled, fuel injected, normally aspirated, 5 minute max of 245 bhp (183 kW), max continuous power of 205 bhp (153 kW) ()
  • Main tank total capacity: 31.6 US gallons (120 liters)
  • Main tank usable capacity: 30.6 US gallons (116 liters)
  • Optional aux tank total capacity: 18.5 US gallons (70 liters)
  • Optional aux tank usable capacity: 18.3 US gallons (69 liters)