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Learjet 24
NASA Learjet 24
Role Business jet
Manufacturer Learjet
First flight January 24, 1966
Primary users Private
Military
NASA
Number built 210

The Learjet 24 is an American six to eight seat (two crew and four to six passengers) twin-engined, high speed business jet. Manufactured by Learjet as the successor to the Lear Jet 23.

Contents

History

The Learjet 24 was designed as an improved version of the Learjet 23, which was limited to 12,500 pounds (5,700 kg) gross weight. Engineers designed the model 24 to accept up to the full 13,500 pounds (6,100 kg) gross weight permitted by FAR-25 standards.

Other improvements introduced in the Learjet 24 included:

  • increased cabin pressurization, to allow a higher operating altitude
  • the addition of one extra window on each side of the cabin
  • more powerful engines
  • a new windshield
  • auxiliary fuel in wing tip tanks
  • a fire-extinguishing system for the engines

With these changes, the LJ24 became the first business jet to be certified under FAR-25.[1]

The first flight of a Learjet 24 took place on January 24, 1966. From May 23 to 26, 1966, a Learjet 24 flew around the world in 50 hours, 20 minutes flying time as a demonstration of its capabilities.[1]

Different variants were the 24A, B, C, D, E and F, with changes of takeoff weight, range, cabin and engines.

Altogether 259 Model 24s were built, and in 2001, there were still 210 Learjet 24s in use. Altogether 39 LJ24s had been lost through accidents.

Variants

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Learjet 24A

Standard version. Converted from existing Learjet 23. Takeoff weight 5,902 pounds (2,677 kg). FAA certified on November 9, 1966. 81 aircraft built.

Learjet 24B

Improved variant, powered by two 2,950-pound (1,340 kg) thrust General Electric CJ610-6 turbojet engines, and 6,129 pounds (2,780 kg) maximum take-off weight. FAA certified December 17, 1968. 49 aircraft built.

Learjet 24C

A light-weight version of the 24B, fuselage tank not fitted which would have caused a reduction in range. The Learjet 24C project was abandoned in December 1970. Take-off weight 5,675 pounds (2,574 kg). None built.

Learjet 24D

Similar to Learjet 24C, however by changing surface tanks range and takeoff weight were increased to 6,129 pounds (2,780 kg). Round cabin windows replaced by angular. FAA certified July 17, 1970. Replaced the 24B in production.[1] A reduced gross weight (restricted to 12,500 pounds (5,700 kg) version was also available (the 24D/A). 99 built.

Learjet 24D/A

Light-weight version with a retricted take-off weight of 5669-kg (12,500-lb),

Learjet 24E and 24F

Two new versions were announced in 1976 the 24E and 24F, they introduced a new cambered wing and aerodynamic improvements to reduce stall and approach speed (Century III wing). The 24E did not have a fuselage fuel tank for higher payload but shorter range. Some 24E models had the fuselage tank installed later to restore range. Powered by two 2,950-lb thrust General Electric CJ610-8A turbojet engines. On April 15, 1977, the FAA approved extended ceiling to 51,000 feet (16,000 m), the highest level then achieved in civilian aviation.[1] 29 aircraft built.

Survivors

Operators

 United States

Former Operators

 United States

Specifications (Learjet 24D)

Data from {name of first source}

General characteristics

  • Crew: Two (pilot & co-pilot)
  • Capacity: 5 passengers
  • Length: ()
  • Wingspan: 35ft 7in ()
  • Height: 12ft 3in ()
  • Loaded weight: 7,830 lb (3,600 kg)
  • Max takeoff weight: 13,500 lb (6,136 kg)
  • Powerplant:General Electric CJ610-6 turbojet engines
  • * Cabin Height: 4 feet 4 inches (1.3 m)
  • Cabin Width: 4 feet 10 inches (1.5 m)
  • Cabin Length: 9 feet (2.7 m)
  • Cabin Volume: 192 square feet (17.8 m2)
  • Door Height: 4 feet 3 inches (1.3 m)
  • Door Width: 3 feet (0.91 m)
  • Baggage Volume Internal: 40 square feet (3.7 m2)

Performance

  • Maximum speed: 475 knots (565 mph, 886 km/h)
  • Cruise speed: 439 knots (534 mph (859 km/h))
  • Range: 1,100 NM (1,266 miles (2,037 km))
  • Service ceiling: 45,000 ft at Maximum Weight (13,720 m)
  • Rate of climb: 6,800 ft/min (2,073 m/min)
  • Long Range Cruise Speed: 410 knots (472 mph, 765 km/h)
  • Range - Seats Full: 850 NM (978 mi, 1,585 km)
  • One Engine Inoperative Service Ceiling at Maximum Weight: 28,500 feet (8,700 m)
  • Rate of Climb - One Engine Out: 2,100 ft/min (640 m/min)
  • Balance Field Length: 4,300 feet (1,300 m)
  • Landing Distance (Factored): 5,325 feet (1,623 m)
  • Maximum Landing Weight: 11,880 pounds (5,389 kg)
  • Usable Fuel: 5,628 pounds (2,553 kg)
  • Payload with Full Fuel: 342 pounds (155 kg)
  • Maximum Payload: 3,570 pounds (1,619 kg)

See also

References

External links

Related content

Related lists

List of aircraft


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