Friday, 12 July 2013

Comac ARJ21



Introduction

The Comac ARJ21 Xiangfeng is a twin-engined regional airliner. The design incorporates components from 19 major European and US aerospace suppliers, including General Electric (engine production), Honeywell (fly-by-wire system) and Rockwell Collins (avionics production).

ARJ21 is a  Regional jet manufactured by Comac. Its designer is AVIC I Commercial Aircraft Company (ACAC) and Antonov (derived from McDonnell Douglas MD90). It took its First flight on 28 November 2008. The Unit cost of this is US $20 million as of 2008.

The ARJ21 regional jet is being developed by the AVIC I Commercial Aircraft Company (ACAC), based in Shanghai, which is a consortium of six companies and aerospace research institutes carrying out the development and manufacture of the aircraft. The aircraft performance parameters meet the diverse and demanding conditions in China, including the hot-and-high altitude conditions in Western China. The aircraft has a powerful take-off and climbing performance to allow the use of basic airports with short runways. Final assembly began in March 2007 and the ARJ21-700 aircraft was rolled out in December 2007. The first flight took place in November 2008 at Shanghai's Dachang Airfield. The aircraft obtained CAAC type certification in December 2012. Certification by the Civil Aviation Administration of China (CAAC) was delayed, with entry into service planned by 2014.


The ACAC consortium, formed in 2002, includes the Shanghai Aircraft Research Institute and the Xian Aircraft Design and Research Institute, along with several aerospace companies: Chengdu Aircraft Industry Group, which is responsible for the construction of the nose, Shanghai Aircraft Company, which carries out final assembly, Shenyang Aircraft Corporation, which is manufacturing the empennage (complete tail unit) and the Xian Aircraft Company, which is responsible for manufacturing the aircraft wings and fuselage. The ARJ21 advanced regional jet was awarded State Council approval in 2002. The first phase of the programme is directed to the development of the baseline passenger version with 70 to 80 seats. The development will then progress to the stretched version (95 to 105 seats), standard range and extended range versions, including all passenger, freight and business jet variants.
ACAC consortium was acquired by the Commercial Aircraft Corporation of China (COMAC) in 2009.
ARJ21 underwent cold weather ground and flight testing in the utmost cold of the inner Mongolia autonomous region in January 2011. The cross wind tests of the ARJ21 700 were completed in May 2011. 

ARJ21 regional jet aircraft orders
A launch order was received for 35 aircraft: Shandong Airlines (ten), Shanghai Airlines (five) and Shenzhen Financial Leasing (20). In March 2004, Xiamen Airlines ordered six ARJ21s. In November 2006, Shanghai Electric Leasing (SE Leasing) signed a memorandum of understanding (MoU) for 30 aircraft, and in August 2007, Lao Airlines of Laos signed a MoU for two aircraft. In December 2007, Kunpeng Airlines ordered 50 aircraft (plus 50 options). Henan Airlines and Lao Airlines ordered 100 and two aircraft respectively in December 2007. In June 2007, AVIC I announced an agreement with Bombardier Aerospace to co-develop the ARJ21-900 and promote long-term strategic cooperation in the 90 to 149-seat commercial aircraft market. AVIC I launched the ARJ21-900 in 2009 though service entry is delayed. In March 2008, GE Commercial Aviation Services (GECAS) placed an order for five aircraft (plus 20 options), bringing total firm orders to 90. Also in March 2008, Joy Airlines placed an order for 50 ARJ21 aircraft. Chengdu Airlines became a launch customer by placing an order for 30 ARJ 21s in January 2010. Deliveries will begin in 2014. Merkukh Enterprises signed a memorandum of understanding for nine aircraft in May 2010. Myanmar Airways placed an order for two aircraft in June 2011. COMAC was awarded a $30m contract by the Hebei Aviation Investment Group in November 2011 to supply ten ARJ21 jets. As of November 2011, customer orders for ARJ21 regional jets stand at 340.

ARJ21 variation models
The variants of the series include the baseline ARJ21 700, the extended ARJ21 900 version, the dedicated freight carrier ARJ21F and the business class aircraft ARJ21B. The ARJ21F is a freighter variant which can carry five LD7 containers or PIP pallets. Its maximum payload capacity is 10,150kg. The ARJ21B is a business jet model built to accommodate 20 passengers. Flight deck and cabin on ACAC's aircraft
The flight deck is fitted with five Rockwell Collins 10in x 8in high-resolution liquid crystal adaptive flight displays. Honeywell is supplying the fly-by-wire flight control system. The avionics suite is based on the Rockwell Collins Pro Line 21 system, including a VHF-4000 voice and data transceiver and an IRU-4000 digital data and audio processor. The system supports current VDL Mode 2 communications and also has the capability to support controlled pilot data link communications.
A Rockwell Collins FMS 4200 flight management system provides multiple wavepoint vertical navigation, flight time and fuel planning and prediction, standard instrument departures and standard terminal arrival routes and approaches (SIDs and STARS). A Kaiser Electroprecision throttle control module interfaces with the Collins autopilot, autothrottle and the engine's FADEC. The avionics suite also includes a fully integrated engine indication and crew alerting system (EICAS).
The navigation systems include Rockwell Collins solid-state weather radar, a Rockwell Collins AHS-3000 attitude heading reference system, a traffic alert and collision avoidance system (TCAS) plus an air data system. The integrated cockpit panel assemblies and the cockpit lighting control are supplied by Eaton Corporation. Sagem is providing the flight deck control system which interfaces with the fly-by-wire system, including columns, pedals and a central console.
The 18.426m-long passenger cabin can be configured for 78 to 90 seats. The advanced broad cabin configuration includes wide seats, broad array pitch, a large space between the aisle seat and sidewall, wide aisles, high ceiling and low cabin noise. The first-class seats are arranged four seats to a row, with a typical 38in pitch. The tourist-class seats are arranged five seats to a row, with a pitch of 32in.

Cargo hold and engines of the Chinese ARJ21 regional jet
The cargo hold capacity is 20.415m². The aircraft is powered by two General Electric CF34-10A engines which are pod mounted at the rear of the fuselage forward of the swept T-tail. The engines are equipped with full authority digital engine control with a Meggitt Vibrometer SA engine control system and engine vibration monitors and Smiths thrust reversal actuators. The relatively thick wing design accommodates large wing tanks of total capacity 12,720l (10,386kg) of fuel. Parker Aerospace is supplying the fuel system. The aircraft has a Kidde Aerospace fully integrated engine and auxiliary power unit fire protection system including cabin fire extinguishers and a bleed air leak detection system. The aircraft is fitted with a Hamilton Sunstrand APS 2300 auxiliary power unit and a back-up ram air turbine generator. The aircraft is fitted with Liebherr Aerospace twin-wheeled tricycle-type landing gear, Goodrich tyres and brakes and a Parker Hannifin hydraulic system. The take-off and landing field lengths are 1,700 m and 1,550 m.

Performance
The 25° sweptback super critical wing is fitted with wing lets for improved cruise performance. The cruise speed is Mach 0.78 (500 kt true air speed) and cruise altitude is 10,668 m. The standard aircraft has a range of 2,225 km and the extended-range version has a range of 3,700 km.

Simulator
In March 2006, ACAC awarded a $13m contract to CAE to develop and provide the first full flight ARJ-21 simulator for ACAC flight training center based in Shanghai. CAE was contracted to supply two additional CAE 7000 Series ARJ21-700 Level D full flight simulators (FFS) for COMAC Shanghai Aircraft Customer Service Company at a cost of C$35m ($32m). Deliveries are expected to conclude in 2012.

Niriha Khajanchi [ MBA Aviation ] 
Project Manager 



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Thursday, 11 July 2013

AASI Jetcruzer

AASI JETCRUZER

Introduction
The AASI Jetcruzer was an American single turboprop light civil transport made by AASI. The Jetcruzer had an unusual configuration, with a single turboprop engine driving a pusher propeller, prominent canards, and fins mounted at the ends of its swept wings. The plane has seating for up to six people including the pilot. The Jetcruzer is noteworthy in being the first aircraft to have achieved a spin resistance certification from the United States FAA.

Development
1) Jetcruzer 450
Work on the Jetcruzer began in March 1983, with the prototype first flying on January 11, 1989. This initial version, designated the Jetcruzer 450 seated six people (including the pilot) and was powered by an Allison 250-C20S. It gained an FAA type certification on June 14, 1994. Three prototypes were built, but AASI chose not to market this aircraft, in order to focus on more advanced versions. A spin recovery system for use in the flight test program was designed for the aircraft by Butler Parachute Systems which also worked on one for the Sino Swearingen SJ-30.


 2) Jetcruzer 500
The first version developed from the 450 was the Jetcruzer 500, a slightly stretched version powered by a Pratt & Whitney Canada PT6A-66A and featuring cabin pressurization. Two of the 450 prototypes were converted to this configuration, and first flew in this form on August 22, 1997. This was the version selected for production, and at one point, AASI had orders for some 200 aircraft at $US 1.6 million each. A military version, the ML-2 had also been offered, as well as a UAV, the ML-1. None of these orders would be filled, however, as the Jetcruzer 500 remained uncertified and its development slowly stagnated. Specific problems with the aircraft's noise, high stall speed, and center of gravity were not overcome before all work on it was suspended in 2002. Nearly 20 years of work had still not resulted in a marketable aircraft
 3) Jetcruzer 650
In December 1992, construction work began on the prototype of an even larger variant, the Jetcruzer 650, which was to seat up to thirteen. This was quickly abandoned as the company's financial problems required resources to be focused on the 500. A military version would have been the ML-4.
 4) Stratocruzer 1250
Similarly, a turbofan-powered version was planned as the Stratocruzer 1250, but never left the drawing board. Design work had started in September 1991 to provide a business jet with intercontinental range. A military version, the ML-5 intended for surveillance duties, was also planned. Work was abandoned after AASI failed to attract financial backers for the project in 1995.
 Powerplant
One rear mounted 1172kW (1572shp) Pratt & Whitney Canada PT6A-66A turboprop driving a five blade constant speed Hartzell propeller.

Specifications (Jetcruzer 500)
1 General characteristics
Crew: 1
Capacity: 5 passengers
Length: 28 ft 2 in (8.59 m)
Wingspan: 42 ft 2 in (12.85 m)
Height: 10 ft 5 in (3.17 m)
Wing area: 193 ft² (18 m²)
Empty weight: 2,950 lb (1,338 kg)
Max. takeoff weight: 5,500 lb (2,495 kg)
Powerplant: 1 × Pratt & Whitney Canada PT6A-66 turboprop, 850 shp (635 kW)
 Capacity
Typical accommodation for six including pilot. Can be configured for ambulance, cargo and other utility work. Optional aft lavatory
 Production 
450 - 3 were built.
500 - by November 2001, 2 had been converted from 450s, 1 new one was built, and 197 were on order.
Basic unit price (2001) $US1.495.000
 2) Performance
Maximum speed: 300 knots (345 mph, 556 km/h)
Range: 1,579 nm (1,818 mi, 2,936 km)
Service ceiling: 30,000 ft (9,100 m)
Rate of climb: ft/min (m/s)



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Friday, 5 July 2013

Weatherly 201 / 620 Agricultural Aircraft

Agricultural aircraft

History:  

The Weatherly 201 / 620 Agricultural Aircraft were built in relatively small numbers from the late 1960s.
The Weatherly 201 and its successors date back to the Weatherly WM-62C agricultural aircraft, 19 of which were built between January 1961 and late 1965. The WM-62s were agricultural conversions of the basic Fairchild M-62 airframe, fitted with a chemical hopper, spray booms and either a Wright W-670 or Pratt & Whitney R-985 radial engine.
Weatherly used its experience in designing and converting the WM-62s in developing its own agricultural aircraft design. The resulting Model 201 was a larger aircraft overall of conventional ag aircraft configuration, with a low wing, a Pratt & Whitney R-985 radial, integral chemical hopper and spray booms and an enclosed cockpit for the pilot. The initial production 201, the 201A, was certificated in 1967, followed by the 201B, and the improved 201C was granted its type certificate in 1975. A unique feature was the use of wingtip vanes which were developed to increase the effective swath width, while reducing the amount of chemicals lost from the spraying swath (they could be folded back beneath the wings for hangar storage.
                  The Model 620 replaced the 201C in production from 1980. The 620 featured a longer span wing with optional wingtip vanes and a larger chemical hopper, but the same R-985 engine. The 620A had a 65USgal fuel capacity, the 620B had a 4in stretched fuselage to give a 88USgal capacity.
The Pratt & Whitney Canada PT6A-11AG turboprop powered 620TP joined the 620 in production in 1980, and featured a longer nose and a slightly larger chemical hopper. This 620TP was available as the 620A-TP and 620B-TP.
The 620B-TP was replaced by the 620B-TG which is powered by a 496kW (665shp) Honeywell TPE331-1 turboprop. The 620B and 620B-TG are still in low-rate production.

Powerplants:  

201C - One 335kW (450hp) Pratt & Whitney R-985 nine cylinder radial piston engine driving a two blade constant speed Hartzell propeller. 
620 - Same except for a three blade constant speed prop. 
620TP - One 375kW (500shp) Pratt & Whitney Canada PT6A-11AG turboprop.

Performance:  

201C - Typical cruising speed 170km/h (91kt). Initial rate of climb 960ft/min.
620 - Endurance 2hr 30min. 
620TP - Endurance 2hr 0min.

Weights:  

201C - Empty 1157kg (2550lb), max takeoff restricted category 2177kg (4800lb). 
620 - Empty 1270kg (2800lb), max takeoff restricted category 2495kg (5500lb), design takeoff 1815kg (4000lb). 
620TP - Empty 1135kg (2500lb), max takeoff restricted category 2450kg (5400lb), design takeoff 1815kg (4000lb).

Dimensions:  

201C - Wing span 11.89m (39ft 0in), length 8.29m (27ft 3in), height 2.48m (8ft 2in). Wing area 23.3m2 (251.5sq ft). 
620 & 620TP - Wing span 12.50m (41ft 0in), or 14.33m (47ft 0in) with optional wingtip guide vanes.

Capacity:  

Pilot only in all models. 
Hopper capacity in 201C is 1022 litres (270US gal/225Imp gal); 
Hopper capacity in 620 is 1268 litres (335US gal/280Imp gal); 
Hopper capacity in 620TP is 1287 litres (340US gal/283Imp gal).

Production:  

The three model types were built in relatively small numbers (including more than 100 Model 201s). By mid 2000 at least 155 Model 620/620TPs had been built.





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P - Productivity S - Speed R - Relevancy    
Price: $20.00 USD. Approx. 22,870 words. Language: English. Published on August 23, 2013. Category: Essay. 
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is a story of Pilots in Aviation who are unable to cope. This is not a book to teach you how to get into an Aviation School or even how to live like a Pilot. In fact, it describes how one can become a Successfull Aviator not just an Airplane Driver [ So called Pilot ] with very small changes in life. Also Why abroad trained Pilots are better Aviator and Why FAA, CASA, CAAP, CAA are better civil Aviation Authority then DGCA.
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Cabin Crew Career Guide


Published: Aug. 26, 2013 
Words: 2,160 (approximate)
Language: English
ISBN: 9781301001965

SU-31


SU-31 SINGLE and TWO SEAT AEROBATIC LIGHT AIRCRAFT:
TYPE:  

Single and Two Seat Aerobatic Light Aircraft


HISTORY:

Sukhoi's highly regarded aerobatic aircraft have won numerous international aerobatic events.
Sukhoi is perhaps better known as one of the two preeminent Russian high performance combat aircraft designers, but it turned its attention to design and flying a single seat aircraft for unlimited aerobatics competitions in the early 1980s. The prototype of the single seat Su26, the originator of the series, flew for the first time in June 1984, and remarkably competed in the World Aerobatic Championships held in Hungary only two months later.
Features introduced on the initial Su26 include the Vedneyev, now VOKBM, M14 nine cylinder piston radial engine, which is highly regarded for its simplicity, power to weight ratio, fuel economy and low oil consumption. The airframe itself is extremely strong, capable of withstanding +11 and 9g, while the wing's aerofoil section is symmetrical and attached to the airframe at zero incidence and dihedral for similar positive and negative angle of attack flight characteristics.
Modifications to the Su26 including a squared off vertical tail and less glass led to the Su26M, which participated in the 1986 World Aerobatic Championships in the UK. The Su26MX is an export version. The success of the Su26 led Sukhoi to design a two seat, dual control development, the Su29, which first flew during 1991. Differences include the second seat, greater span wing and increased length. The Su-29M has lightweight ejection seats.
The ultimate development is the Su31, which first flew in June 1992 as the Su29T. The Su31 is a single seater based on the Su29 but with a more powerful engine. The basic version is the Su31T, the Su-31X is for export and the Su31U has retractable undercarriage. Production began in 1994.

                   The main features of the new aeroplane were:
high power-to-weight ratio achieved through a rugged design, the weight of the airframe being kept down to a minimum;
special aerodynamic symmetric-profile wing configuration to enable superior piloting performance;
a robust airframe structure capable of sustaining +12/-10 G loads;
extensive use of composite materials in the design;
ergonomic cockpit configuration.
The design work involved revision of the existing strength standards for highly-manoeuvrable aerobatic sports aircraft to support a new level of pilot performance and to confirm, using unbiased monitoring systems, that the pilot can safely perform an entire range of aerial stunts under forward acceleration up to +12g. The design of the new plane incorporated the requests and comments of sports pilots from the USSR national team, as well as modern trends in the development of aerobatics. As a result, the design was based on new guidelines for developing a highly-manoeuvrable aerobatic Aeroplane.


                    The Su-31 differed from its predecessor in more extensive use of composite materials, whose share in the airframe design was 65%, which made it possible to achieve a dramatic reduction in weight while keeping the strength and durability of the structure. The pilot obtained a more congenial cockpit environment. Fitted with a boosted M-14PF engine, the Su-31's thrust-to-weight ratio reached unity. This meant that the Su-31 gave the pilot an option to perform “helicopter-like" manoeuvres.
The Su-31 has been in series production since 1994.
In 1992, at the World Championships in aerobatics, which took place in France, pilot Yurgis Kairis won bronze; in the autumn, at the air show in Farnborough, he took the Su-31 to heights of breathtaking aerobatics that had never before been possible for any pilot of a sports aeroplane.
The export version, theSu-31Kh, differs from the Su-31 in that it has additional fuel tanks installed in the wing to increase its ferry range. The 16 Su-31Kh aeroplanes produced were delivered to users in the USA, UK, Spain, Australia, Italy and elsewhere.
                     The Sukhoi aerobatic aircraft has emerged as a family of superior aerobatic aeroplanes, allowing pilots to use them for training and world class aerobatics competitions and exhibition shows. Since 1996, a majority of international contestants have been entering competitions with Sukhoi aeroplanes.

POWERPLANT:
Su29 - One 265kW VOKBM M-14PT nine cylinder radial piston engine driving a constant speed three blade propeller. Su31T - One 295kW M14PF driving a three blade constant speed prop.

PERFORMANCE:
Su29 - Max speed 325km/h. Initial rate of climb 3150ft/min. Service ceiling 13,120ft. Range with max fuel 1200km. Su31T - Max speed 330km/h. Initial rate of climb 4725ft/min. Service ceiling 13,125ft. Range with internal fuel 290km, max ferry range up to 1200km.

WEIGHT:
Su29 - Empty 735kg, MTOW 1204kg. Su31T - Empty equipped 670kg, MTOW 968kg.

DIMENSIONS:
Su26M - Wing span 8.20m, length 7.29m, height 2.89m, Wing area 12.2m2, Su31T - Wing span 7.80m , length 6.90m, height 2.76m, Wing area 11.8m2.

CAPACITY:
Accommodation for pilot only in Su26, Su26M, Su31T and Su31U. Seating for two in tandem in Su29.

PRODUCTION:

Production includes approximately 60 Su29s, 70 Su26s and 25 Su-31s.






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Wednesday, 3 July 2013

Cessna 182 Skylane

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Cessna182

The Cessna 182 Skylane is an American Four-Seat, Single-Engine, Light Airplane, built by Cessna of Wichita, Kansas. It has the option of adding two child seats, installed in the baggage area.

Introduced in 1956, the 182 has been produced in a number of variants, including a version with retractable landing gear, and is ...


General characteristics

Min Crew: 1 
Capacity: 3 passengers
Total : 4 Pax
Length: 29 ft 0 in (8.84 m)
Wingspan: 36 ft 0 in (11.0 m)
Height: 9 ft 4 in (2.8 m)
Wing area: 174 sq ft (16.2 m²)
Airfoil: NACA 2412
Empty weight: 1,970 lb (894 kg)
Loaded weight: 3,110 lb (1,411 kg)
Useful load: 1,140 lb (517 kg)
Max. takeoff weight: 3,100 lb (1406 kg)
Powerplant: 1 × Lycoming IO-540-AB1A5 3-Bladed Constant Speed, 230 hp (172 kW)
Performance

Never exceed speed: 175 knots (201 mph, 324 km/h)
Maximum speed: 150 knots (173 mph, 278 km/h)
Cruise speed: 145 knots (167 mph, 269 km/h)
Stall speed: 49 knots (56 mph, 91 km/h)
Range: 930 nmi (1,070 mi, 1,722 km)
Service ceiling: 18,100 ft (5,517 m)
Rate of climb: 924 ft/min (4.7 m/s)
Wing loading: 17.8 lb/sq ft (87 kg/m²)
Power/mass: 0.074 hp/lb (122 W/kg)







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