Aero Ae 270 Ibis
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|Ae 270 Ibis|
|Role||Civil utility aircraft|
|National origin||Czech Republic|
|First flight||25 July 2000|
The Aero Ae 270 Ibis was a single-engine turboprop general utility aircraft that was developed by the Czech aircraft company Aero Vodochody. The aircraft's maiden flight took place in 2000. It received Federal Aviation Administration (FAA) type certification in 2006, although production was eventually cancelled (apparently due to a lack of funding).
Design began in the early 1990s. The aircraft's configuration was finalized by 1993. In 1997, Aero signed an agreement with AIDC of Taiwan to jointly manufacture and market the aircraft through Ibis Aerospace. The first prototype (0001, OK-EMA) was completed in 2000, and it first flew on July 25, 2000.
It was projected to have an empty weight of 1,790 kilograms (3,950 lb), a maximum take-off weight of 3,000 kilograms (6,600 lb), and a ceiling of 7,620 metres (25,000 ft). Five prototypes were planned, two for static and dynamic tests and three for flight tests. The requirements changed and the aircraft was redesigned, new equipment added, a new engine variant chosen. The changes added significant weight. The second (partial) prototype was used for static tests, and the fourth for fatigue tests. The third prototype (OK-SAR) first flew in 2002. The fifth prototype (OK-LIB) was finished in 2003, with its first flight in February. The sixth prototype (OK-INA) was also finished in 2003. UCL (Czech Civil Aeronautical Institute) added more requirements, which delayed further tests. The first prototype was not usable for EASA test flights, because the changes were too significant. A seventh prototype (OK-EVA) was built in 2004.
In 2004, AIDC announced that it would not deliver wings for additional airplanes. Aero Vodochody also had issues with money for certification and some members of upper management at Aero were against the program. Deteriorating flight parameters and Aero management interest led to cancellation of preliminary orders. Aero Vodochody was never able to calculate a production price, mostly because the wing was produced in Taiwan and alternate production in Czech Republic was never envisioned.
Airworthiness was certified by the Czech Civil Aviation Authority permitting training and aerial work, including commencement of commercial use. EASA certification completed on December the 12th 2005. The FAA certificate was received on February 24, 2006. During 2006 the program slowed and people from Ae-270 program were moved to other tasks. Despite the issues the eighth prototype (OK-ALE) was finished in 2007, the year the AIDC terminated the program. An agreement between Aero and AIDC divided the know-how and planes - OK-INA (0006) and OK-ALE (0008) are used for Aero Vodochody flights. OK-EMA (0001) is used as a teaching aid in SŠLVT high school, OK-EVA (0007) was dismantled. OK-SAR (0003) and OK-LIB (0005) were transferred to Taiwan - OK-SAR is exposed in Chenfung, OK-LIB flew to Taiwan (14 000 km, 36 hrs. of flight time) with Czech crew in 2008—its current status is unknown.
During 2008 the project was cancelled, jigs and tools removed and 3 unfinished fuselages (including fatigue test prototype 0004) were moved to the Air Park Zruč u Plzně museum.
Aircraft Integrated Solutions based in Manchester UK, is resurrecting the program since August 2016 after its intellectual property and rights as well as European and US type certificates were acquired by its parent, Lebanese investment house COPS.
Specifications (Ae 270HP)
Data from Jane's All The World's Aircraft 2003–2004
- Crew: One or two
- Capacity: Up to 10 passengers or 1,200 kg (2,645 lb) cargo
- Length: 12.23 m (40 ft 1½ in)
- Wingspan: 13.82 m (45 ft 4 in)
- Height: 4.78 m (15 ft 8¼ in)
- Wing area: 21.00 m² (226.0 ft²)
- Airfoil: NASA MS(1)-0316.7 (root), NASA MS(1)-0312 (tip)
- Empty weight: 2,300 kg (5,071 lb)
- Max. takeoff weight: 3,670 kg (8,157 lb)
- Powerplant: 1 × Pratt & Whitney Canada PT6A-66A-42A turboprop engine, 634 kW (850 shp)
- Maximum speed: 500 km/h planned (270 knots, 311 mph) at FL 200, real top speed is 409 km/h (220 kts)
- Cruise speed: 333 km/h, planned 380 km/h
- Stall speed: 123 km/h (66 knots, 76 mph) with flaps down
- Range: 2,981 km (not confirmed - probably 2500-2700 km) (1,610 nmi, 1,852 mi) at 30,000 ft with 30-minute VFR reserve
- Service ceiling: 9,140 m (30,000 ft)
- Rate of climb: 8.7 m/s (1,710 ft/m)
- Aircraft of comparable role, configuration and era
- Related lists
- "History | AERO Vodochody" (Web page). www.aero.cz. AERO Vodochody a.s. 2008. Retrieved 23 March 2012.
- "Ae270 Commercial Flight-Ready", Aviation Week & Space Technology, January 8, 2007.
- "Ztracený duch Ibise posvátného" [Lost Spirit of Sacred Ibis] (in Czech). Magazín Letiště České republiky. Retrieved 17 January 2012.
- "Aero chystá s Běloruskem miliardový kontrakt, chce tam vyrábět Ae 270" [Aero plans a billion-dollar contract with Belarus, wants to produce Ae 270 there] (in Czech). Magazín E15. Retrieved 17 January 2012.
- "UK company to revive Ae270". Flight Global. 9 August 2016.
- Jackson 2003, pp. 262–263.
- The Incomplete Guide to Airfoil Usage
- Jackson, Paul. Jane's All The World's Aircraft 2003–2004. Coulsdon, UK: Jane's Information Group, 2003. ISBN 0-7106-2537-5.
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