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Thursday, 28 February 2013

Pilatus PC-6 Porter







The Pilatus PC-6 Porter is a single-engined Short Take-Off and Landing (STOL) utility aircraft designed by Pilatus Aircraft of Switzerland. First flown in 1959, the PC-6 has been built in both piston engine and turboprop powered versions, and has been built both by Pilatus and by Fairchild Hiller in the United States. It remains in production as of August 2011.

Design and development

The first prototype made its maiden flight on 4 May 1959 powered by a 254 kW (340-shp) piston engine. The first Turbo Porter, powered by a turboprop, flew in 1961. The Turbo Porter received an engine upgrade in 1963, which increased its power to its present value of 410 kW (550-shp).
In the United States, the Porter was manufactured under license by Fairchild Hiller. In service with the U.S. Air Force, it received the designation AU-23A Peacemaker. In U.S. Army use, it was designated UV-20 Chiricahua.


Operational history

The PC-6 is noted for its Short Take-off and Landing (STOL) performance on almost any type of terrain - it can take off within a distance of 640 feet (195 m) and land within a distance of 427 feet (130 m) while carrying a payload of 2,646 lbs (1,200 kg). Thanks to its STOL performance, the PC-6 holds the world record for highest landing by a fixed wing aircraft, at 18,865 feet (5,750 m), on the Dhaulagiri glacier in Nepal.
Due to these characteristics, they are frequently used to access short grass mountaintop airstrips in the highlands of Papua Province (Indonesia) and Papua New Guinea.






Variants

PC-6/340 Porter
Initial production version, powered by a 254-kW (340-hp) Lycoming GSO-480-B1A6 flat-six piston engine. Max take-off weight 1,070 kg (2,360 lb).

PC-6/340-H1 Porter
As PC-6/340, but with modified landing gear and increased weight (2,016 kg (4,444 lb)).

PC-6/340-H2 Porter
As for H-2, but with maximum take-off weight increased to 2,200 kg (4,850 lb).

PC-6/350
As PC-6/340, but powered by a 261 kW (350 hp) Lycoming IGO-540-A1A piston engine.

PC-6/350-H1
As for /340 H1 but with O-540 engine.

PC-6/350-H2
As for 340 H2 with O-540 engine.

PC-6/A Turbo-Porter
Initial turboprop powered version, fitted with a 390 kW (523 shp) Turboméca Astazou IIE or IIG turboprop engine.

PC-6/A1 Turbo-Porter
This 1968 version was powered by a 427-kW (573-shp) Turbomeca Astazou XII turboprop engine.

PC-6/A2 Turbo-Porter
This 1971 version was powered by a 427-kW (573-shp) Turbomeca Astazou XIVE turboprop engine.

PC-6/B Turbo-Porter
This version was powered by a 410-kW (550-shp) Pratt & Whitney Canada PT6A-6A turboprop engine.

PC-6/B1 Turbo-Porter
Similar to the PC-6/B, but fitted with a 410-kW (550-shp) Pratt & Whitney Canada PT6A-20 turboprop engine.

PC-6/B2-H2 Turbo-Porter
Fitted with a 507-kW (680-shp) Pratt & Whitney Canada PT6A-27 turboprop engine.

PC-6/B2-H4 Turbo-Porter
The B2-H4 has improved airframe structuring and extended, upturned wingtips.

PC-6/C Turbo-Porter
One prototype built by Fairchild Industries in the USA, powered by a 429-kW (575-shp) Garrett TPE331-25D turboprop engine.

PC-6/C1 Turbo-Porter
Similar to the PC-6/C, but fitted with a 429-kW (575-shp) Garrett TPE 331-1-100 turboprop engine.

PC-6/C2-H2 Porter
Developed by Fairchild Industries in the USA. It was powered by a 485-ekW (650-ehp) Garrett TPE 331-101F turboprop engine.

PC-6/D-H3 Porter
One prototype, fitted with a 373-kW (500-hp) avco Lycoming turbocharged piston engine.

AU-23A Peacemaker
Armed gunship, counter-insurgency, utility transport version for the U.S. Air Force. It was used during the Vietnam War in the early 1970s. 35 were built under licence in the USA by Fairchild Industries. All aircraft were sold to Royal Thai Air Force.

OV-12
Designation for U.S. version, cancelled 1979.

UV-20A Chiricahua
STOL utility transport version for the U.S. Army. Two UV-20As were based in West Berlin during the 1970s and 1980s.

PC-8 Twin Porter
Twin-engined version flown in 1967, but not subsequently developed.






Specifications (PC-6 B2 Turbo-Porter)

General characteristics

Crew:                      one, pilot
Capacity:                 up to ten passengers
Payload:                  1,130 kg (2,491 lb)
Length:                   11.00 m (36 ft 1 in)
Wingspan:               15.87 m (52 ft 0¾ in)
Height:                    3.20 m (10 ft 6 in)
Wing area:               30.15 m² (324.5 sq ft)
Airfoil:                     NACA 64-514
Aspect ratio:             8.4:1
Empty weight:          1,270 kg (2,800 lb)
Max. takeoff weight: 2,800 kg (6,173 lb)
Powerplant:              1 × Pratt & Whitney Canada PT6A-27 turboprop, 410 kW (550 shp)(downrated from 507 kW (680 shp))






Performance

Never exceed speed:          280 km/h (151 knots, 174 mph)
Maximum speed:               232 km/h[15] (125 knots, 144 mph)
Cruise speed:                    213 km/h (115 knots, 132 mph) at 3,050 m (10,000 ft)
Stall speed:                       96 km/h (52 knots, 60 mph) (flaps down, power off)
Range:                             730 km (394 nmi, 453 mi) with maximum payload
Ferry range:                     1,612 km (870 nmi, 1,002 mi) with maximum internal and underwing fuel
Service ceiling:                 8,197 m (25,000 ft)
Rate of climb:                   4.8 m/s (941 ft/min)














Regards,
Heena Mathur[B.Sc(CS)MBA(HR)]
HR Executive


On Line Assistence    :
Gtalk                          :   Heena.aerosoft@gmail.com
Y! Messenger                   :   Heena.aerosoft@yahoo.com
Rediff Bol                     :   Heena.aerosoft@rediffmail.com
MSN                            :   Heena.aerosoft@hotmail.com


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Wednesday, 27 February 2013

Piper PA-46 Malibu








The Piper PA-46 is a family of light aircraft manufactured by Piper Aircraft of the United States. The aircraft is powered by a single engine and has the capacity for one pilot and five passengers. Early Malibus were all piston-engined, but a turboprop version, the Malibu Meridian, is also available.
The PA-46 is the third single-engine piston aircraft with a pressurized cabin to ever reach the market, after the Mooney M22 and Cessna P210Centurion. It is sold mainly to civilian customers.

Piper PA-46 Malibu

Role                      General aviation
National origin      United States of America
Manufacturer      Piper Aircraft
First flight      30 November 1979

Development

Work on the PA-46 began in the late 1970s, with a prototype (the PA-46-300T) first flying on November 30, 1979. The type was announced in November 1982, apparently to compete with Cessna's newest creation of the era, the P210 Centurion. Like the Centurion, the Malibu was to feature cabin pressurization (5.5 psi), a feature not included on the prototype.


Variants

PA-46-310P Malibu

The first example of the initial production version flew in August 1982, and FAA certification was obtained in September 1983. Deliveries started one month later. 404 aircraft with Continental TSIO-520 engines were built before this model was replaced in production by the 350P.
The PA-46-310P is powered by a Teledyne Continental Motors TSIO-520BE engine rated at 310 hp (230 kW). The PA-46-310P has lower fuel consumption, greater range, and the ability to cruise at "lean-of-peak." The PA-46-310P has a maximum cruising range of 1,550 nautical miles (with reserves), while the PA-46-350P initially had a maximum cruising range of only 1,055 nautical miles (1,954 km), although now increased to 1,345 nautical miles (2,491 km).
The PA-46-310P Malibu has set several world speed records: Seattle to New York set November 23, 1987 at 259.27 mph; Detroit to Washington, DC set January 4, 1989 at 395.96 mph; and Chicago to Toronto set on January 8, 1989 at 439.13 mph. All 3 records were set by Steve Stout in his 1986








Malibu N9114B.

The Continental-powered Malibu was discontinued in 1986 following a series of incidents and accidents attributed to engine failures. One such accident resulted in a settlement in which Teledyne Continental Motors paid over US$32,000,000 to a pilot injured in the crash of a Malibu. Some attribute the poor record of the original Malibu to improper engine operation. Unlike virtually every other Continental engine in production at the time, the TSIO-520BE was designed to be operated with mixture set to the lean side of peak TIT ("Lean of Peak"). However, many pilots chose to operate with the mixture on the rich side of peak TIT ("Rich of Peak"), which is how most other airplane engines were operated at the time. On that engine, such operation caused excessively high engine temperatures and cylinder pressures, and led to premature failures.

PA-46-350P Malibu Mirage

Production of the Malibu Mirage commenced in October 1988. New features included a more powerful Textron Lycoming TIO-540-AE2A 350 hp (260 kW) engine and a new wing. This model remains in production as of 2011. Various changes have occurred over the model years. Earlier models had an all King panel and later this became largely Garmin. The Avidyne Entegra glass cockpit is now standard in the Mirage with the Garmin G1000 optional. In 1995, the pilot's windshield became a glass assembly (earlier it had been acrylic glass with a heat strip overlay). In 1996, numerous switches were moved to an overhead console. In 1999, the Mirage gained the strengthened wing designed for the turboprop Meridian. The base price for a 2011 Malibu Mirage is US$997,500

PA-46-500TP Malibu Meridian

In 1997, Piper announced its intention to market a turboprop-powered version of the Malibu, and flew a prototype the following year powered by a Pratt & Whitney Canada PT6A-42A of 500 shp (370 kW). Certification was achieved in September 2000 and deliveries began in November that year. Changes made to allow for turboprop power include larger wings and tail surfaces. In 2009, Piper began offering the Meridian with a three screen version of the Garmin G1000 including the Garmin GFC 700 autopilot as a replacement for the Avidyne Entegra system.
The Meridian's base price in 2012 was $2.13 million.



PA-46R-350T Matrix

In October 2007 Piper announced the Matrix, an unpressurized version of the Mirage. It seats six and its base price is $819,000 (2010 USD). The new model has been designated as the PA-46R-350T, indicating retractable landing gear, 350 horsepower (260 kW), and turbocharging.
Piper Aircraft is marketing the Matrix as a cabin-class aircraft for Cirrus SR-22 and Cessna 400 owners to step up to.
Standard equipment on the Matrix includes a built-in oxygen system, Avidyne Entegra glass cockpit, S-Tec 55X autopilot and air conditioning.
Major options on the Matrix are a de-ice system, an "Enhanced Situational Awareness Package", speed brakes, an avionics package featuring the Avidyne TAS610 dual antenna traffic advisory system, GWX-68 Weather Radar, and, beginning in 2010, the Garmin G1000 avionics system with twin 10" PFD's and a 15" MFD.
The Matrix's powerplant is a turbocharged Lycoming TI0-540-AE2A producing 350 hp (260 kW). The aircraft's performance includes a cruise speed of 215 knots at 25,000 feet (7,600 m), 215 knots (398 km/h) at 17,500 feet (5,300 m) and 188 knots (348 km/h) at 12,000 feet (3,700 m). Maximum take-off weight is 4,340 lb (1,970 kg) and an empty weight of 2,937 lb (1,332 kg) giving a standard useful load of 1,421 lb (645 kg).
Matrix deliveries began in early 2008.







JetPROP

The JetPROP DLX is an aftermarket turbine engine conversion for the PA-46-310P Malibu and PA-46-350P Malibu Mirage. Originally certified in August 1998 with a Pratt & Whitney PT6A-34, conversions 90 and above used the P&W PT6A-35 when the -34 was discontinued. A lower cost JetPROP DL conversion became available in October 2003 utilizing the P&W PT6A-21. As of September 2008, 233 JetPROP conversions had been completed and delivered by Rocket Engineering of Spokane, WA. Twenty percent of the entire PA-46 fleet have been converted.

Specifications (PA-46-310P Malibu)

General characteristics

Crew:                  one
Capacity:             five passengers
Length:               28 ft 4 3⁄4 in (8.655 m)
Wingspan:           43 ft 0 in (13.11 m)
Height:                11 ft 3 1⁄2 in (3.442 m)
Wing area:           175 sq ft (16.3 m2)
Empty weight:      2,354 lb (1,068 kg)
Gross weight:       4,100 lb (1,860 kg)
Fuel capacity:       120 U.S. gallons (450 L; 100 imp gal)
Powerplant:         1 × Continental TSIO-520-BE 6-cylinder, turbocharged, fuel-injected, horizontally  opposed aircraft engine, 310 hp (230 kW)







Performance

Maximum speed:           234 kn (269 mph; 433 km/h)
Cruise speed:                196 kn (226 mph; 363 km/h) at 55% power
Stall speed:                   58 kn (67 mph; 107 km/h)
Range:                         1,555 nmi (1,789 mi; 2,880 km)
Service ceiling:             25,000 ft (7,600 m)
Rate of climb:               1,143 ft/min (5.81 m/s)
Wing loading:                24.3 lb/sq ft (119 kg/m²)















Regards,
Heena Mathur[B.Sc(CS)MBA(HR)]
HR Executive




On Line Assistence    :

Gtalk                          :   Heena.aerosoft@gmail.com

Y! Messenger                   :   Heena.aerosoft@yahoo.com

Rediff Bol                     :   Heena.aerosoft@rediffmail.com

MSN                            :   Heena.aerosoft@hotmail.com


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Tuesday, 26 February 2013

Piper Aerostar








The Piper Aerostar (formerly Ted Smith Aerostar) is an American twin-engined propeller-driven executive or light transport aircraft, designed by Ted R. Smith. It was originally built by Ted Smith Aircraft Company, which after 1978 became part of the Piper Aircraft Corporation.

Role                           light transport aircraft
National origin          United States
Manufacturer          Ted Smith Aircraft Company
                                 Piper Aircraft Corporation
Designer                  Ted R. Smith
First flight                  1967
Status                  Out of production Active service
Produced                  1967-1984
Number built          1010

Development

Ted Smith flew the first Aerostar 600 in October 1967. It was a mid-wing cantilever monoplane powered by two wing-mounted Avco Lycoming piston engines, with a tricycle landing gear. It was fitted with luxury accommodation for six. Also produced, and the base of most of the subsequent models, was a version with a turbocharged engine, the Aerostar 601.






Performance

The Aerostar is one of the fastest twin piston engine aircraft produced, with cruise speeds from 220 kt (408 kph) for the earliest 600 models to 261 kt (483 kph) for the later 700 models. Light construction, low drag and high powered engines also contribute to fast climb rates.

History

The aircraft were originally built at Van Nuys in California, when in 1968 the company was bought by the American Cement Company. The acquisition was not a success and in 1969 the company was sold again to Butler Aviation, owners of Mooney Airplane Company. The new company was named Aerostar Aircraft Corporation and it was intended to move production to a Mooney plant at Kerrville, Texas. In 1972 Ted Smith bought back all the rights to the aircraft and continue to manufacture Aerostars in Santa Maria, California. He also introduced the pressurized Aerostar 601P. The 601P had engines with higher-rate turbochargers to feed a cabin pressurisation system. Another variant was the stretched Aerostar 700 Superstar. In 1976 the company name was changed to the Ted Smith Aerostar Corporation. Ted Smith died in 1976.

Variants

600
Initial production model with two 290hp Lycoming IO-540-K engines, 282 produced under four different company names.

600A
Model 600 with some minor detail changes.

600E
Designation used for aircraft sold in Europe.

601 (later PA-61) 
This aircraft still holds the land closed speed record for a production piston twin
Model 600 with turbocharged engines, 117 built.

601B (later PA-61)
Model 601 with increased wingspan, 44 built.

601P (later PA-61P)
Pressurised version of the 601 with increased gross weight, 492 built

602P Sequoia (later PA-60)
Piper developed version of the 601P with the 290 hp Lycoming TIO-540-AA1A5 engines, 124 built.

620
A pressurised Aerostar with 310 hp TIO-540 engines, one built.

700 Superstar
Prototype of stretched fuselage variant with two IO-540M engines.

700P
602P with counter-rotating Lycoming TIO-540-U2A engines, 26 built, also designated the PA-60

702P
New modification of 700P with a reinforced nose gear allowing for higher takeoff weight

800
601P with stretched fuselage, enlarged tail and two 400 hp Lycoming engines, one built.

Speedstar 850
A modification to replace the twin piston engines with a single nose mounted turboprop.






Specifications (700P)

General characteristics

Crew:                    1
Capacity:               5 passengers
Length:                 34 ft 9¾ in (10.61 m)
Wingspan:             36 ft 8 in (11.18 m)
Height:                 12 ft 1 in (3.68 m)
Wing area:            178.2 ft2 (16.56 m2)
Empty weight:      4,275 lb (1,939 kg)
Gross weight:       6,315 lb (2,864 kg)
Powerplant:         2 × Avco Lycoming TIO-540-U2A flat six counter-rotating piston, 350 hp (261  kW) each each






Performance

Maximum speed:          306 mph (492 km/h)
Cruise speed:               242 mph (390[3] km/h)
Range:                        1,024 miles (1,648 km)
Service ceiling:            25,000 ft (7,620 m)
Rate of climb:             1,840 ft/min (9.4 m/s)












Regards,
Heena Mathur[B.Sc(CS)MBA(HR)]
HR Executive


On Line Assistence    :
Gtalk                          :   Heena.aerosoft@gmail.com
Y! Messenger                   :   Heena.aerosoft@yahoo.com
Rediff Bol                     :   Heena.aerosoft@rediffmail.com
MSN                            :   Heena.aerosoft@hotmail.com

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