Production of P.68C by Partenavia

Production of P.68C by Partenavia in Italy started 1978, followed by P.68TC in 1980. Production agreement made with TAAL in 1992; European manufacture ended in 1994 after 400 aircraft.TAAL programme aimed at meeting growing demand for this category of aircraft within India, and to tap export potential to neighbouring countries in Southeast Asia. Initial plans covered two demonstrators (assembled from Italian kits) and up to 30 production aircraft. First TAAL-assembled aircraft, a P.68 Observer 2 (VT-TAA), made its first flight 17 March 1994; second was Viator. Three more assembled from Italian parts: two P.68Cs for Mardia Chemicals and Triveni Sheet Glass; and one P.68TC demonstrator. Last of this kit-built batch completed mid-1996.Local manufacture of the aircraft began as planned on 1 January 1997. Roll-out of first TAAL-built aircraft (a P.68C) took place 20 January 1998; this aircraft due for delivery to an Indian charter operator in March 1998; three more aircraft completed by March 1998. More than 450 P.68C are still flying worldwide.

Power plants  

P.68B - Two 150kW (200hp) Lycoming IO360A1B fuel injected flat four piston engines driving two blade constant speed propellers. P.68TC - Two 155kW (210hp) turbocharged Textron Lycoming TIO360C1A6Ds.

Performance  

P.68B - Max speed 322km/h (174kt), max cruising speed 306km/h (165kt), economical cruising speed 295km/h (160kt). Initial rate of climb 1600ft/min. Service ceiling 20,000ft. Range at economical cruising speed 1700km (920nm). P.68TC - Max speed 352km/h (190kt), max cruising speed 324km/h (175kt), economical cruising speed 278km/h (150kt). Initial rate of climb 1550ft/min. Service ceiling 27,000ft. Range with max payload 555km (300nm), range with max fuel 1924km (1040nm).

Weights  

P.68B - Empty 1200kg (2645lb), max takeoff 1960kg (4321lb). P.68TC - Empty equipped 1300kg (2866lb), max takeoff 1990kg (4387lb).

Dimensions  

P.68B - Wing span 12.00m (39ft 5in), length 9.35m (30ft 8in), height 3.40m (11ft 2in). Wing area 18.6m2 (200.0sq ft). P.68TC - Same except for length 9.55m (31ft 4in).

Capacity  

Standard seating arrangement for seven, comprising one pilot and six passengers, or two pilots and five passengers.

Production  

400 built through to 1994, including 13 preproduction P.68As and 150 P.68B Victors. Six assembled by TAAL in India where licence production is planned.

PIAGGIO P-166 COMMUTER AND UTILITY TRANSPORT

The prototype P-166 first flew on November 16, 1957, and deliveries of the initial P-166AL-1 production model took place from April 1959. Just 23 were built before production switched to the P-166BL-2 Portofino, which featured more powerful 285kW (380hp) engines and an increased max takeoff weight of 3800kg (8377lb). Five Portofinos were built, while several earlier P-166s were converted to that standard with the more powerful engines.

The Italian Air Force received 51 of the military model, the P-166ML-1, for communication and training duties. This had an extra cockpit door, a larger main loading door, and a strengthened floor.

The Piaggio P-166 has been built in only small numbers but has been used in a wide variety of utility missions.

Intended for civil use when designed in the late 1950s, the P-166 features a large cabin which has been put to use in a variety of civil, military and quasi military roles, while its gull wing with tip tanks and pusher engines configuration like that on the P-136 amphibian, ensures it is easily identified.

Powerplants  

P-166 - Two 255kW (340hp) Lycoming GSO-480-B1C6 geared and supercharged flat six piston engines driving three blade constant speed propellers. 

P-166DL-3/SEM - Two 450kW (600shp) AlliedSignal LTP-101-700 turboprops.

Performance  

P-166 - Max speed 357km/h (193kt), max cruising speed 333km/h (180kt), economical cruising speed 280km/h (151kt). Initial rate of climb 1240ft/min. Service ceiling 25,000ft. Max range 1930km (1040nm).

P-166DL-3/SEM - Max speed 400km/h (215kt). Range with max payload 1390km (750nm), range with max fuel 2130km (1150nm).

Weights  

P-166 - Empty 2350kg (5180lb), max takeoff 3680kg (8115lb).

P-166DL-3/SEM - Empty equipped 2688kg (5926lb), max takeoff 4300kg (9480lb).

Dimensions  

P-166 - Wing span (without tip tanks) 14.25m (46ft 9in), length 11.61m (38ft 1in), height 5.00m (16ft 5in). Wing area 26.6m2 (286sq ft). 

P-166DL-3/SEM - Same except for wing span over tip tanks 14.69m (48ft 3in), length (including chin mounted radar) 11.88m (39ft 0in).

Capacity  

Flightcrew of one or two and standard seating for eight or nine in main cabin in airliner configuration. Max seating for 12 in P-166C. Executive configuration seats five or six with toilet and bar. Air ambulance can carry two stretchers and two medical attendants.

Production  

Approximately 145 P-166s of all models built, including many for government and military customers. New production aircraft built on demand.

PIAGGIO P-180 AVANTI TWIN TURBOPROP EXECUTIVE TRANSPORT

The innovative Avanti has been a slow seller despite its modern features, and jet like performance but turboprop operating costs.

Development of the Avanti dates back to program launch in 1981. Gates Learjet participated in Avanti development from 1983 and would have built the Avanti's forward fuselage, but instead withdrew from the program in January 1986. Not deterred by Gates' withdrawal, Piaggio assumed total control of the program, and all tooling and three forward fuselages for what would have been the Learjet P.180 were transferred to Italy.

Piaggio flew the first of two P.180 prototypes on September 23 1986, the second flew in May 1987. Italian certification was granted in March 1990, the first production Avanti flew that May and the first customer delivery took place in September 1990.

Powerplants  

Two 635kW (850shp) Pratt & Whitney Canada PT6A66 turboprops driving five blade constant speed Hartzell props.

Performance  

Max speed 732km/h (395kt), max cruising speed 644km/h (348kt). Initial rate of climb 2950ft/min. Service ceiling 41,000ft. Range with one pilot, six passengers and IFR reserves 2595km (1400nm).

Weights  

Empty equipped 3400kg (7500lb), max takeoff 5240kg (11,550lb).

Dimensions  

Wing span 14.03m (46ft 1in), length 14.41m (47ft 4in), height 3.94m (12ft 11in). Wing area 16.0m2 (172.2sq ft).

Capacity  

Flightcrew of one or two (certificated for single pilot operation). Max seating in main cabin for nine in high density airliner configuration. Standard seating for seven in individual seats. Executive/VIP seating for five.

Production  

Orders placed for approximately 42 Avantis (including three for the Italian air force for use as regional transports), with 30 built by early 1995. Production restarting against an Italian air force order for 12.

PILATUS PC-12 UTILITY,REGIONAL AIRLINE AND CORPORATE TURBO

The PC-12 is a King Air class and size turboprop originated at Switzerland, aimed at corporate transport and regional airliner operators. It is the latest in a line of single engined PT6 powered Pilatus products.

Pilatus announced it was developing the PC-12 at the National Business Aircraft Association's annual convention in October 1989. First flight of the first of two prototypes occurred on May 31 1991. Certification was originally planned for mid 1993 but a redesign of the wings with the addition of winglets to ensure performance guarantees were met pushed this back, with Swiss certification awarded on March 30 1994 and US FAA FAR Part 23 approval following on July 15 1994.

Powerplants  

One 895kW (1200shp) takeoff rated Pratt & Whitney Canada PT6A67B turboprop driving a four blade constant speed Hartzell propeller.

Performance  

Max cruising speed at 25,000ft 500km/h (270kt), economical cruising speed 430km/h (232kt). Initial rate of climb 1680ft/min. Max operating altitude 30,000ft. Max range at economical cruising speed with VFR reserves 4187km (2260nm). Range at max cruising speed with IFR reserves 2965km (1600nm).

Weights  

PC12 - Standard empty 2600kg (5732lb), max takeoff 4500kg (9920lb).

Dimensions  

Wing span 16.23m (52ft 3in), length 14.40m (47ft 3in), height 4.27m (14ft 0in). Wing area 25.8m2 (277.8sq ft).

Capacity  

Flightcrew of one or two pilots (certificated for single pilot). Seating for nine in main cabin in regional airliner configuration. Corporate/executive transport configurations typically seat six in main cabin. Combi passenger/freight version seats four passengers in main cabin plus freight pallet.

Production  

Over 280 PC-12s delivered by end of April.

PILATUS PC-6 PORTER AND TURBO PORTER STOL UTILITY TRANSPORT PIPER

The Pilatus Porter and Turbo Porter STOL utilities are renowned for their exceptional STOL performance and low speed handling and have sold strongly on the strength of their performance.

The high wing taildragger Porter was designed to perform a range of utility roles, and flew for the first time on May 4 1959. The first production aircraft built were delivered from 1960 and were powered by a six cylinder GSO480 piston engine, but it was not long after that a turboprop powered development flew.

The first PC6/A Turbo Porter flew in May 1961, powered by a 390kW (523shp) Turboméca Astazou II turboprop. The majority of PC6s are PC6/Bs, powered by the Pratt & Whitney Canada PT6A. PC6/Cs were powered by a 310kW (575shp) AiResearch TPE331, and were first delivered in 1965.

Powerplants  

PC6H2 - One 255kW (340hp) Lycoming GSO480B1A6 geared and supercharged six cylinder piston engine driving a three blade constant speed propeller. PC6/B2H4 - One 410kW (550shp) Pratt & Whitney Canada PT6A27 turboprop.

Performance  

PC6H2 - Max speed 233km/h (126kt), max cruising speed 216km/h (117kt), economical cruising speed 190km/h (103kt). Initial rate of climb 550ft/min. Service ceiling 17,400ft. Max range with no reserves 1500km (810nm). PC6/B2H4 (Utility version) - Economical cruising speed 213km/h (115kt). Initial rate of climb 940ft/min. Max operating ceiling 25,000ft. Range with max payload at economical cruising speed and no reserves 730km (395nm), range with max internal fuel 925km (500nm), with external fuel 1610km (870nm).

Weights  

PC6H2 - Empty 1250kg (2755lb), max takeoff 2200kg (4850lb). PC6/B2H4 - Empty 1130kg (2491lb), max takeoff 2800kg (6173lb).

Dimensions  

PC6H2 - Wing span 15.14m (49ft 8in), length 10.20m (33ft 6in), height tail down 3.20m (10ft 6in). Wing area 28.8m2 (310sq ft). PC6/B2H4 - Wing span 15.87m (52ft 1in), length 10.90m (35ft 9in), height 3.20m (10ft 6in). Wing area 30.2m2 (324.5sq ft).

Capacity  

Pilot and passenger on flightdeck, with standard seating for six in main cabin. Max seating for 11 including pilot. Alternative layouts include two stretchers and three medical attendants, or 10 skydivers. Some equipped for agricultural spraying.

Production  

Over 500 Porters of all versions have been built, including 100 under licence in the USA and against various military orders.

PIPER AEROSTAR SIX SEAT HIGH PERFORMANCE LIGHT TWIN

The Aerostar - which in its higher powered forms can lay claim to being the fastest piston twin GA aircraft built - was designed by Ted Smith, who was also responsible for the Aero Commander twins.

Smith's original intention in designing the Aerostar was to develop a family of single and piston twins, twin turboprop and even twin jet powered versions of the same basic aircraft. However the Aerostar appeared in piston twin form only. Smith began design work on the Aerostar in late 1964, with a prototype making its first flight two years later in November 1966.

The prototype was powered by 120kW (160hp) Lycoming IO-320s, but the Aerostar was placed into production from 1968 as the Aerostar 600 with 215kW (290hp) IO-540s.

Powerplants  

600A - Two 215kW (290hp) Lycoming IO-540-K1J5 fuel injected flat six piston engines driving three blade constant speed Hartzell propellers. 

PA-60-700P - Two 260kW (350hp) turbocharged and counter rotating TIO-540-U2As.

Performance  

600A - Max speed 418km/h (226kt), long range cruising speed 357km/h (193kt). Initial rate of climb 1800ft/min. Service ceiling 21,200ft. Max range with reserves 2225km (1200nm). 

PA-60-700P - Max speed 490km/h (264kt), max cruising speed 484km/h (261kt), economical cruising speed 390km/h (211kt). Initial rate of climb 1755ft/min. Service ceiling 25,000ft. Range at max cruising speed 1250km (675nm), at economical cruising speed with max fuel 2150km (1160nm).

Weights  

600A - Empty 1695kg (3757lb), max takeoff 2495kg (5500lb).

PA-60-700P - Empty 1940kg (4275lb), max takeoff 2864kg (6315lb).

Dimensions  

600A - Wing span 10.41m (34ft 2in), length 10.61m (34ft 10in), height 3.89m (12ft 1in). Wing area 15.8m2 (170sq ft).

PA-60-700P - Same except for wing span 11.18m (36ft 8in). Wing area 16.6m2 (178.2sq ft).

Capacity  

Typical seating for six.

Production  

1010 Aerostars built, including 491 by Ted Smith and 519 by Piper.

PIPER CLUB TWO-SEAT LIGHT AIRCRAFT

The simple and economical Cub is one of the most well loved light aircraft of all time, and helped make flying an affordable pastime for thousands of pilots in the years surrounding World War 2.

The Piper Cub began life as the Taylor E-2, designed by C.G. Taylor. In the middle of 1930, his company, Taylor Brothers Aircraft Corporation, went bankrupt. Businessman William Piper, who had made large profits from the oil industry, purchased the assets of the company and formed Taylor Aircraft Company with C.G. Taylor as the Chief Engineer.

Powerplants  

J-3C-65 - One 50kW (65hp) Continental A-65-1 flat four piston engine driving a two blade fixed pitch propeller.

PA-12 - One 75kW (100hp) Lycoming O-235 flat four.

Performance  

J-3C-65 - Max speed 148km/h (80kt), typical cruising speed 132km/h (71kt). Initial rate of climb 450ft/min. Service ceiling 12,000ft. Range 402km (217nm). 

PA-12 - Max speed 183km/h (99kt), normal cruising speed 170km/h (90kt). Service ceiling 12,600ft. Range 580km (313nm).

Weights  

J-3C-65 - Empty 290kg (640lb), max takeoff 500kg (1100lb).

PA-12 - Empty 430kg (950lb), max takeoff 795kg (1750lb).

Dimensions  

J-3C-65 - Wing span 10.75m (35ft 3in), length 6.79m (22ft 3in), height 2.03m (6ft 8in). Wing area 16.6m2 (178.5sq ft). 

PA-12 - Wing span 10.83m (35ft 6in), length 6.74m (22ft 1in), height 2.08m (6ft 10in). Wing area 16.7m2 (179.3sq ft).

Capacity  

Typical seating for two in tandem in the J-2 and J-3 Cub, J-4 Cub Coupe and PA-11 Cub Special, three in the J-5 Cub Cruiser and PA-12 Super Cruiser, and four in the PA-14 Family Cruiser.

Production  

Production includes 348 E-2s, 1169 J-2s, 20056 J-3s (including 5677 military O-59, L-4 and NE), 1251 J-4 Cub Coupes, 1506 J-5 Cub Cruisers, 1541 PA-11 Cub Specials, 3759 PA-12 Super Cruisers and 238 PA-14 Family Cruisers.

PIPER PA-18 SUPER CLUB TWO SEAT UTILITY LIGHT AIRCRAFT

The Super Cub is one of Piper's most successful and long lived aircraft programs, with production spanning over four decades.

The PA-18 Super Cub was the ultimate development of Piper's original aircraft, the J-3 Cub (described separately). The four seat development of the Cub, the PA-14 Family Cruiser, was the basis for the Super Cub, but the later differed in having seating for two in tandem (as on the Cub), all metal wings and, in its initial form, a 65kW (90hp) Continental C-90 in the PA-18-90 or a 80kW (108hp) Lycoming O-235 engine in the PA-18-105. The Super Cub flew for the first time in 1949, and certification was awarded on November 18 that year. The first production Super Cubs were delivered from late 1949, the type replacing the PA-11 Cub Special on Piper's production lines.

Powerplants  

PA-18-95 - One 65kW (90hp) Continental C-90-12F or 8F flat four piston engine driving a two blade fixed pitch propeller. 

PA-18-150 - One 110kW (150hp) Lycoming O-320.

Performance  

PA-18-95 - Max speed 180km/h (97kt), max cruising speed 161km/h (87kt). Initial rate of climb 710ft/min. Service ceiling 15,750ft. Max range with no reserves 580km (313nm). PA-18-150 - Max speed 210km/h (113kt), max cruising speed 185km/h (100kt), economical cruising speed 170km/h (90kt). Initial rate of climb 960ft/min. Service ceiling 19,000ft. Range at max cruising speed and no reserves 740km (400nm).

Weights  

PA-18-95 - Empty 367kg (910lb), max takeoff 680kg (1500lb).

PA-18-150 - Empty 429kg (946lb), max takeoff 794kg (1750lb).

Dimensions  

PA-18-95 - Wing span 10.73m (35ft 3in), length 6.83m (22ft 5in), height 2.02m (6ft 9in). Wing area 16.6m2 (178.5sq ft).

PA-18-150 - Same except for length 6.88m (22ft 7in).

Capacity  

Typical seating for two in tandem.

Production  

Almost 7500 Super Cubs (including 1700 military) built until 1981 when production originally ceased. Piper production for WTA between 1982 and 1988 totalled 250. Piper production between 1988 and 1994 approximately 100.

Er. Aakanksha Saxena [B.Tech-EE]

Software Trainee/Blog Master

Aakanksha.aerosoft@gmail.com