Learjet 24
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| Learjet 24 | |
|---|---|
 NASA Learjet 24 |
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| Type | Business jet |
| Manufacturer | Learjet |
| Maiden 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.
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[edit] History
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The original Lear Jet 23 was designed not to exceed a gross weight of 12,500lb (5670 kg) and it was soon realised that this limit was not needed and a higher gross weight version was developed as the Learjet 24. The aircraft was designed to meet FAR Part 25 Regulations with a gross weight of 13,500 lb (6123 kg). It was announced in October 1965. It also introduced other improvements including increased cabin pressurisation (to allow a higher operating altitude). One of the obvious differences is the addition of one extra window on each side of the cabin. Improved engines were installed and some small changes were made, in order to meet the requirements of FAR Part 25 regulations (the LJ24 was the first business jet to be certified under Part 25).[1] In addition there was a new windshield, the auxiliary fuel in wing tip tanks and a fire-extinguishing system for the engines. The first flight of a Learjet 24 took place on January 24, 1966. Different variants were the 24A, B, C, D, E and F, with changes of takeoff weight, range, cabin and engines.
From May 23 to May 26, 1966, a Learjet 24 flew around the world in 50 hours, 20 minutes' flying time as a demonstration of its capabilities.[1]
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.
[edit] Variants
[edit] Learjet 24A
Standard version. Converted from existing Learjet 23. Takeoff weight 5902 kg. FAA certified on November 9, 1966. 81 aircraft built.
[edit] Learjet 24B
Improved variant with 2x General Electric CJ610-6 and 6129 kg maximum takeoff weight. FAA certified December 17, 1968. 49 aircraft built.
[edit] Learjet 24C
A light-weight version of the 24B, fuselage tank not fitted which would have caused a reduction in range. Takeoff weight 5675 kg. None built.
[edit] Learjet 24D
Similar to Learjet 24C, however by changing surface tanks range and takeoff weight were increased 6129 kg. Round cabin windows replaced by angular. FAA certified July 17, 1970. Replaced the 24B in production.[1] A reduced gross weight (restricted to 12,500lb (5669 kg) version was also available (the 24D/A). 99 built.
[edit] Learjet 24E/F
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. The 24E was had an additional fuel tank to give an 18% greater fuel capacity. Powered by two General Electric CJ610-8A. On April 15, 1977, the FAA approves extended ceiling to 51,000 feet (15,545 m), the highest level then achieved in civilian aviation.[1] 29 aircraft built.
[edit] Specifications (Learjet 24E)
This aircraft article is missing some (or all) of its specifications. If you have a source, you can help Wikipedia by adding them.Data from {name of first source}
General characteristics
- Crew: Two (pilot & co-pilot)
- Capacity: 5 passengers
- Length: ()
- Wingspan: ()
- Height: ()
- Loaded weight: 7,830 lb (3,600 kg)
- Max takeoff weight: 13,500 lb (6,136 kg)
- Powerplant: 2× General Electric CJ610-6 turbojet engines
- * Cabin Height: 4 ft 4 in (1.32 m)
- Cabin Width: 4 ft 10 in (1.47 m)
- Cabin Length: 9 ft (2.74 m)
- Cabin Volume: 192 ft³ (5.4 m³)
- Door Height: 4 ft 3 in (1.3 m)
- Door Width: 3 ft (0.91 m)
- Baggage Volume Internal: 40 ft³ (1.13 m³)
Performance
- Maximum speed: 475 knots (546 mph, 886 km/h)
- Cruise speed: 439 knots (505 mph, 819 km/h)
- Range: 1,100 NM (1,266 mi, 2,052 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 ft (8,690 m)
- Rate of Climb - One Engine Out: 2,100 ft/min (640 m/min)
- Balance Field Length: 4,300 ft (1,311 m)
- Landing Distance (Factored): 5,325 ft (1,623 m)
- Maximum Landing Weight: 11,880 lb (5,400 kg)
- Usable Fuel: 5,628 lb (2,558 kg)
- Payload with Full Fuel: 342 lb (155 kg)
- Maximum Payload: 3,570 lb (1,622 kg)
[edit] References
[edit] External links
- A history of the LJ23-LJ29 series on Airliners.net
- Listing of LJ24 accidents in ASN Aviation Safety Database
[edit] See also
[edit] Related content
Related lists
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