The original wooden wing Extra 230 was designed by company founder Walter Extra to meet the requirements of competition pilots with the Swiss Aero Club. First flight occurred during 1983. Unusually for an aircraft of its type the Extra 230 features a wooden wing with Dacron covering, while as on other aerobatic competition aircraft the 230′s wing has 0° incidence for sustained inverted flight. Production ceased in 1990 when Extra was experiencing difficulties in sourcing the correct type of wood.
|Production line:||Flugplatz Schwarze Heide.|
|Type aircraft:||unlimited aerobatic competition aircraft.|
|Wing span||7,40 m.|
|Fuselage length:||5,82 m.|
|Engines:||one Textron Lycoming AEIO360 flat four piston engine rated 150 kW.|
|Propeller:||two blade c/s Mühlbauer propeller.|
|Max. take off weight:||560 Kg.|
|Max. speed:||352 km/h.|
|Max rate of roll:|
|G-limits:||+ 10/-10 g.|
The A400M program is a direct result of a commonly expressed need by 8 European air forces for a new generation military airlifter.
Airbus A400M timeline:
- The Airbus A400M development started in the seventies as the Future Large Aircraft project. Request for Proposal August 1997.
- Memorandum of Understanding is signed June 19, 2001 at the Le Bourget Air show.
- On May 27, 2003, a contract was signed between Airbus Military and OCCAR (Organization Conjointe de Cooporation en Matire d’Armement), representing Belgium, France, Germany, Luxembourg, Spain, Turkey, and United Kingdom for a total of 180 aircraft.
- The industrial program was formally launched on May 31, 2003.
- Start production January 2005.
- First Roll out: June 26, 2008
- First Flight December 11, 2009, and the first deliverywill be in 2012.
First Flight December 11, 2009
The A400M Common Standard Aircraft (CSA) is capable of performing:
- strategic operations (long range, large capacity, high cruise speed).
- tactical missions (soft-field performance, autonomous ground operation, low speed / low level operations, aerial delivery).
- “in-theatre” tanking operations (receiving as well as dispensing fuel).
The A400M is designed to civil certification standards complemented where appropriate by specific military requirements. The aircraft design incorporates leading state-of-the-art technology including:
- Fly-by-wire Flight Control System with side stick controllers.
- Flight envelope protection system, already proven in Airbus commercial aircraft.
- Advanced structural design incorporating extensive use of composite materials.
- High performance turboprop engines, allowing operation in civil air traffic control environment.
- High flotation landing gear, allowing operation from short, unpaved airfields.
The Airbus A400M will play an essential role in enhancing Europe’s airlift capabilities, whilst enabling the establishment of common support, training and operational procedures and greater interoperability in multi-national humanitarian and peace-keeping missions.
The A400M is also quickly convertible into a tactical tanker. The flight envelope of the A400M allows it to refuel a wide range of aircraft and helicopters, at the altitudes appropriate to their missions.
- A two-point trailing drogue system can be installed within two hours by fitting two standard air-to-air refueling pods (optional) to the multi-role attachment points on the wings. Each pod provides a fuel flow of up to 1200kg/min.
- A centre-line pallet-mounted hose drum unit can be fitted in the rear cargo bay. It provides a fuel flow of 1800kg/min.
|Developing nation:||European Nations.|
|Production line:||Sevilla, Spain|
|Type aircraft:||Military transporter.|
|First flight:||December 11, 2009|
|Cockpit crew:||2 pilots, 1 loadmaster|
|Cabin length:||17,71 m.|
|Cabin diameter:||4,00 m.|
|Cabin height:||3,85 m.|
|Ramp length:||5,40 m.|
|Cargo volume:||356 m³.|
|Wing span:||42,4 m|
|Wing area:||221,5 m².|
|Fuselage length:||43,8 m.|
|Fuselage diameter:||4,10 m.|
|Engines:||- four Europrop International TP400-D6?each rated 11.000 Hp.|
|Propeller:||Ratier FH386 eight blades 5,33 m diameter.|
|Weight:||- empty: 70.000 Kg.
- fuel: 46.700 kg.
- max. payload: 37.000 Kg.
|Max. take off weight:||130.000 Kg.|
|Max. landing weight:||114.000 Kg.|
|Cruise speed:||mach 0,68.|
|Max. speed:||mach 0,72.|
|Service ceiling:||8.840 m.|
|Max. ceiling:||12.190 m.|
|Max. range:||9.260 km.|
|Performance:||- take-off run 940 m at max. take-off weight.- landing run 625 m at max. landing weight.|
|Airbus A400M order book:|
Grob launched its first business jet project in complete secrecy in January 2004. Prototype assembly took place between October 2004 and January 2005.
Rumors that Grob was working on a business jet began to circulate in the spring of 2005, pointing to a very light jet. Surprise was therefore great when Grob presented its SPn Utility Jet at the Paris Air Show on 13 June 2005, not only showing a cabin mock up but the real prototype.
Grob Aerospace’s new SPn Utility Jet completed its maiden flight on July 20, 2005. It departed Allgu Airport (EDJA) near Memmingen in southern Germany at 11:14 am. The aircraft was commanded by Capt. Gerard Guillaumaud and co-test pilot Tore Reimers. It landed 66 minutes later after performing initial handling tests and system checks. Previously, a test airframe had successfully passed a program of full strength testing on the fuselage and wing required for certification.
As the largest private jet to be certified for single-pilot operations, the Grob SPn is equipped with the state of the art and newly improved Honeywell APEX integrated all glass cockpit which sets new standards for simplicity, reliability and technology. Propulsion consists of two rear mounted FADEC controlled Williams J44-3A engines with 1.270 kg of thrust, and a proven track record from use in many of today’s leading light jets.
A fully-equipped pre-production aircraft will enter service at the beginning of 2007 and will be used to complete final certification and reliability testing. It will be fitted with a full interior and major avionics options.
- Crew: 1 pilot
- Capacity: 9 passengers
- Length: 14.81 m (48 ft 7 in)
- Wingspan: 14.86 m (48 ft 9 in)
- Height: 5.12 m (16 ft 10 in)
- Gross weight: 6,300 kg (13,889 lb)
- Powerplant: 2 × Williams FJ44-3A turbofans, 12.44 kN (2,800 lbf) thrust each
- Maximum speed: 753 km/h (468 mph)
- Maximum speed: Mach 0.7
- Stall speed: 143 km/h (89 mph)
- Range: 3,425 km (2,128 miles)
- Service ceiling: 12,500 m (41,000 ft