Mechanical engineer Bill Piper, of Los Angeles, California, props the 72 hp McCulloch engine on the Piper-Marriott autogyro as aeronautical engineer Ed Marriott prepares for a flight in early 1964.
The rotor blades have a steel spar and plywood skin.
Engine: 72 hp McCulloch
Rotor diameter: 20 ft
Length: 9 ft 9 in
Empty weight: 225 lb
Gross weight: 450 lb
Top speed: 85 mph
Cruise: 60 mph
Range: 120 mi
Piper Aircraft has received a USAF contract, expected to total about $12 million, to design, develop and test two new prototypes of the Enforcer as a lightweight close support air¬craft. The Enforcer, powered by a 2,445 ehp Lycoming T55 L 9 turboprop, was developed in 1971 as part of the activities of Cavalier Aircraft Corporation, which had produced a batch of updated North American F 51 Mustangs for export and evolved the Turbo Mustang III with a Dart engine. Piper acquired rights in the Enforcer in 1970 after Cavalier had developed the prototype, and for another 8 years Piper lobbied Congress to force the USAF to officially re-evaluate the Enforcer.
The two new prototypes were conversions of existing F 51 airframes, and modified by Piper at its Lakeland, Florida, plant. As well as the T55 installation, they feature wing tip tanks to increase total fuel capacity to 424 US gal (1605 1t), six wing strong points to carry two podded General Electric GAU 8 30 mm four-¬barrel cannon, 2.75 in (7 cm) unguided rockets or bombs, and aerodynamic improvements that include changes in the aileron control system and a 19 in (48 cm) extension of the rear fuselage, with enlarged tailplane and elevators. With a gross weight of 14,000 lb (6 350 kg), the Enforcer was expected to have a max speed of 350 kts (648 km/h). The USAF five month evaluation is expected to be conducted in the late summer of 1983 and completed by February 1984, embracing 98 flights.
In 1971 Piper built two Enforcers by heavily modifying two existing P-51 Mustang aircraft and fitting them with Lycoming T55-L9A turboprop engines (along with numerous other significant modifications). One airframe was single seat (called the PE-1 and FAA registered N201PE) and the other was a dual-control aircraft (called the PE-2, registered N202PE). Prior to the PAVE COIN evaluation, N202PE was lost in a crash off the Florida Coast.
The Piper PA 48 Enforcer flew for the first time on April 9 1971 from the company’s Lakeland, Florida, facility.
The Enforcer that flew is powered by a 2,445 shp Avco Lycoming T55 L 9 turboprop, turning a Skyraider propeller cut down by Piper from 14 feet to 11 feet, 6 inches in diameter. The fuselage has been stretched by 19 inches between the cockpit and fin; the fin area has been increased by nine percent, mostly in chord but slightly in height; the rudder is now equipped with a yaw stability augmentation system; and the tailplane/elevator area has been enlarged by 36 percent. Tip tanks provide 1,900 pounds of fuel capacity, in addition to some wing bending relief and end plate effect.
To ease stick loads at high speed and low level, the Enforcer’s ailerons are equipped with a boost system from a Lockheed T 33. The landing gear embodies Grumman G 1 wheels, T 39 Sabreliner brakes and Mustang type tires, and the tailwheel retracts. With six underwing pylons, the Enforcer’s main armament will be a pair of pod mounted 30mm General Electric four barrel rotary cannons capable of firing at a rate of 2,400 rounds per minute (40 rounds per second). Other weaponry could include miniguns, rockets and cluster bombs.
On the Enforcer’s first flight, the entire mission was flown in the takeoff and landing configuration to examine its stability, controllability and handling. Tests on the second flight included gear retraction, a climb to 20,000 feet and acceleration to 300 knots.
Eventually in the 1979 defense bill $11.9 million was allocated for Piper to build two new prototypes and for the USAF to perform another flight evaluation. Since the Enforcer was never in the Air Force inventory, it was not given an official military designation and did not receive an Air Force serial number. Instead, it carries the Piper designation PA-48 and Federal Aviation Administration (FAA) registration numbers N481PE and N482PE.
By the time the PA-48s were completed, they shared less than ten percent of their structure with the P-51. The two PA-48s were tested during 1983 and 1984 at Eglin AFB, Florida, and Edwards AFB, California. As in the PAVE COIN tests of 1971, the PA-48s were found to perform well in their intended role, but the USAF again decided not to purchase any.
Of the prototype aircraft produced, three of the four still exist. The original PE-1 is disassembled and in storage. One of the PA-48s, N482PE, awaits restoration at Edwards Air Force Base. N481PE has been fully restored and resides in the ‘Prototype Hangar’ at the National Museum of the United States Air Force at Wright-Patterson Air Force Base near Dayton, Ohio.
Engine: 1 x Lycoming T55-L-9 turboprop, 1831kW
Max take-off weight: 6350 kg / 13999 lb
Wingspan: 12.60 m / 41 ft 4 in
Length: 10.40 m / 34 ft 1 in
Height: 4.00 m / 13 ft 1 in
Wing area: 37.9 sq.m / 407.95 sq ft
Max. speed: 650 km/h / 404 mph
Ceiling: 11465 m / 37600 ft
Range: 1480 km / 920 miles
The PA 40 Arapaho was developed and ready to go, but Piper made the decision not to produce this airplane because of its projected high market price. Instead, they un¬dertook the PA 44 Seminole project in order to produce a more cost competitive light twin.
Announced on 21 February 1978, the Seminole is powered by 180-hp Lycomings, and will do 155 knots at 65-percent power and climb at 1,200 feet per minute. Single-engine service ceiling is 3,200 feet. Piper promised first deliveries in June 1978, and a base price of $73,900. A cantilever low-wing monoplane with a T-Tail, retractable tricycle landing gear and power provided by two Avco Lycoming O-360-E1AD counter-rotating engines.
A big help in holding cost down is commonality with existing airplanes. Most of its fuselage is from the Arrow III, from what would be the forward firewall to the aft cabin bulkhead. The T-tail was actually developed on the Seminole first, but introduced on the Lance II. The wings are basically beefed-up versions of the semi-tapered Arrow III to within four feet of the tip. Like the Seneca II and the Navajo C/R, the Seminole uses counter-rotating propellers for balanced thrust, and optional three-blade propellers in 1979 provided a quieter ride. Also in the same year, a propeller synchrophaser further reduced cabin noise levels.
Two 54-gallon fuel tanks are fitted in the engine nacelles, because the engines attach to the wing right where the gas tank is located on four place Piper singles, and placing fuel in the nacelles meant no drastic change in the wing outboard of that point. Piper opted for Lycoming’s new series of engines, which are made on automated equipment at a slightly lower cost. These engines are deeper than previous Lycomings, and thus the nacelles had to be thicker.
At 75% power and 7,000 feet, the Seminole cruises at 191 mph. When leaned to 65%, best-economy power cruise speed is 181 mph, and range is 898 miles with a 45-minute reserve. At 3,800 pounds gross, the Seminole weighs the same as Gulfstream American’s Cougar, which flies between a pair of 160-hp engines; thus, each Seminole horsepower must heft only 10.6 pounds compared to the Cougar’s 11.9 pounds/hp loading. From the beginning, Piper intended the Seminole as a relatively inexpensive alternative to high-performance singles.
408 of the PA-44-180 were built.
The Seminole was complemented on 24 April 1980 by a turbocharged version designated PA-44-180T Turbo Seminole with TO-360-E1AD counter-rotating engines. At 65-percent power economy cruise, the Turbo Seminole can travel at 194 mph over a distance of 920 miles burning fuel at a rate of 19 gph. Standard equipment includes a built-in oxygen system that consists of a rear-mounted bottle with easy-to-reach overhead outlets, night-lighted pressure gauge, oxygen masks, and a control-wheel mike button.
Piper’s financial troubles brought Seminole production to an end in 1990 after 469 were built. Five years later, New Piper Aircraft resumed making the entry-level twin, the only remaining T-tail aircraft in the line, and 29 were delivered over the next three years.
All were certified to FAA A19SO.
PA44-180 Seminole
Engine: 2 x Lycoming O-360-E1AD, 180 hp / 134kW
TBO: 2000 hrs
Prop: Hartzell 2 blade, constant speed 74 in
Seats: 4
Wing area: 183.8 sq.ft
Wingspan: 38 ft. 6.6 in
Overall length: 27 ft. 7.2 in
Height: 8 ft. 6 in
Wing aspect ratio: 8
Max ramp wt: 3816 lb
Max take off wt: 3800 lb
Standard empty wt: 2354 lb
Max useful load: 1462 lb
Max landing wt: 3800 lb
Baggage capacity: 200 lb
Wing loading: 20.7 lbs/sq.ft
Power loading: 10.66 lbs/hp
Max useable fuel: 648 lbs (2×208 lt tanks)
Climb rate: 1340 fpm @ 88 kt
Climb gradient: 913 ft/nm
Rate of climb @ 8000 ft: 740 fpm
Service ceiling; 17,100 ft
SE rate of climb: 217 fpm @ 88 kt
SE climb gradient: 148 f/nm
SE ceiling: 4100 ft
Vne: 202 kt
Vmca: 56 kt
Vfe: 111 kt
Vmo: 169 kt
Cruise speed 75% power: 166 kt
Cruise speed 65% power: 162 kt
Cruise @ 65% power @ 8,000ft: 155 kt
Fuel consumption 75% power: 22.4 USgph
Fuel consumption 65% power: 20.6 USgph
Fuel flow @ 65% power @ 8,000ft: 102 pph
Endurance @ 65% power @ 8,000ft: 6.1 hr
Max range (w/ res) 75% power: 790 nm
Max range (w/ res) 65% power: 850 nm
Stalling speed clean: 57 kt
Stall speed gear/flaps down: 55 kt
Turbulent air penetration speed: 133 kt
Retractable undercarriage
Takeoff distance (50′) 1,400 ft
Landing distance (50′) 1,190 ft
Takeoff ground roll: 880 ft
Landing ground roll: 383 ft
Cabin width: 41.5 in
Cabin height: 49 in
PA44-180T Turbo Seminole
Engine: 2 x Lycoming TO-360-E1A6D, 180 hp
TBO: 1800 hr
Prop: Hartzell 2 blade, constant speed 74 in
Seats: 4
Length: 27.6 ft
Height: 8.5 ft
Wingspan: 38.6 ft
Wing area: 183.8 sq.ft
Wing aspect ratio: 8
Max ramp wt: 3943 lb
Max take off wt: 3925 lb
Standard empty wt: 2430 lb
Max useful load: 1513 lb
Max landing wt: 3800 lb
Wing loading: 21.4 lbs/sq.ft
Power loading: 10.9 lbs/hp
Max useable fuel: 648 lb
Climb rate: 1290 fpm @ 88 kt
Climb gradient: 879 ft/nm
Rate of climb @ 8000 ft: 1140 fpm
Certificated ceiling; 20,000 ft
SE rate of climb: 180 fpm @ 88 kt
SE climb gradient: 123 ft/nm
SE ceiling: 12,500 ft
Max speed: 195 kt
Cruise @ 65% power @ 8,000ft: 154 kt
Cruise @ 65% pwr @ 18,000 ft: 169 kt
Fuel flow @ 65% power @ 18,000ft: 132 pph
Endurance @ 65% power @ 18,000ft: 4.7 hr
Stalling speed clean: 60 kt
Stall speed gear/flaps down: 56 kt
Turbulent air penetration speed: 133 kt
Retractable undercarriage
Takeoff distance (50′) 1,500 ft
Landing distance (50′) 1,190 ft
The Piper PA-40 Arapaho twin-engined cabin monoplane designed by Piper as a replacement for the PA-39 Twin Comanche C/R. The Arapaho was similar in size to the Twin Comanche and had six seats but had a taller main landing gear and larger cabin windows. It had two counter-rotating 160 hp Lycoming IO-320 engines.
The prototype was damaged in June 1972 when the factory at Lock Haven, Pennsylvania, flooded and the prototype, registered N9999P, did not fly until 16 January 1973. It crashed on 21 September 1973 during spin trials when the anti-spin drag chute failed to deploy, and the aircraft was redesigned with a taller tailfin. The second modified prototype with normally aspirated engines first flew in April 1974 and was followed by a third aircraft with turbocharged engines.
The PA-40 was type certified on 18 July 1974, as an amendment to the Twin Comanche type certificate. The Arapaho was scheduled to be launched as a 1975 model, but the company decided not to market the aircraft and the project was cancelled in December 1974. Piper stated that the cancellation was for financial reasons as it did not want to establish a new production line during the 1973–1975 recession.
Following cancellation the two aircraft were used by Piper as company liaison and communication aircraft, one based at Lock Haven, the other at Lakeland, Florida. Later, one aircraft was scrapped by Piper and the third, registered N9997P, was privately owned in Texas, following use by the Purdue University student maintenance program.
28-May-21 Barnstormers advert:
This is the only remaining Piper PA-40 Arapaho out of 3 built. Extensive mechanical restoration completed. (15 SMOH) Original paint and interior. It was rescued from Purdue University in 2018 and is in airworthy condition. Please review the Specs Page for the extensive amount of work that has been completed and other details before calling with any questions. Delivery available. We are taking offers now and will be showing it publicly for the first time at Oshkosh 2021. This is probably the only one of a kind Piper aircraft that is still flyable and airworthy.
**
From the specs page:
1974 Piper PA-40 Arapaho
1270 Total Time Airframe/Engine
15 SMOH both engines and propellers in 2018
Lycoming (L)IO-320-B1A
Condition Inspection due August 2021
Original Engines Installed
Original Airframe and Engine Logbooks
History
The PA-40 Arapaho was designed to be the follow-on aircraft to the PA-39 Twin-Commanche.
The Arapaho differences include leading edge cuffs both inside and outside both nacelles which lower Vmc and stall speeds by approximately 10-15 kts., a single 60 gallon bladder in each wing, 6 inch taller main landing gear, a completely redesigned hydraulic landing gear operating system, strakes on both sides of the rear fuselage as well as above and below the rear fuselage, a redesigned windshield that extends further rearward at the top of the fuselage, redesigned dual pane side windows, as well as other minor changes.
The aircraft has similar cruise speeds to a PA-39 but much lower approach speeds as well as much better pitch authority in the flare which contributes to much nicer landing characteristics.
This aircraft is serial number 3 and is the last remaining Arapaho out of 3 built.
PA-40 Arapaho
1973
Engines: two 160hp Lycoming IO-320
Wing span: 36’5″
Length: 25’2″
Useful load: 1460 lb
Max speed: 201 mph
Cruise: 181 mpj
Stall: 69 mph
Range: 1115 mi
Seats: 6
Piper announced the end of PA-30 production in 1970 and introduced a new PA-39 line. Basically a PA30, the PA-39 featured contra-rotating engines and a slight modification to the wings.
Three models were available:
Standard Model
Custom
As Standard Model, with Piper Truespeed Indicator, vacuum system with dual engine driven vacuum pumps (dry), dual vacuum gauge, dual 70A engine driven alternators, heated pitot tube and full flow oil filters.
Advanced instrument panel with 3in pictorial gyro horizon, 3in directional gyro, rate of climb indicator, OAT gauge, gyro air filter, inertial shoulder harness for two front seats, Piper pictorial turn rate indicator + 47 lb.
Sportsman
As Custom Model, with Piper External Power, glare ban instrument lights, fifth & sixth family seats, Palm Beach interior with leather upholstery, four headrests and window curtains + 83 lb.
The 160 hp Lycoming IO-320 B version of the Twin Comanche was produced in limited numbers, all models were certified under FAA A1EA.
Some 155 were built before the 1972 flood at Lock Haven when it was decided not to build any more.
PA-39
Engines: 2 x Lycoming IO-320 B1A, 160 hp
Props: Hartzell, Constant speed, full feathering, counter rotating
Wingspan: 35 ft 11 in / 35 ft 9.5 in o/tip tanks
Length: 25 ft 2 in
Height: 8 ft 3 in
Wing area: 178 sq.ft
Tailplane span: 12 ft 6 in
Fuel capacity: 90 USG / 120 USG w/tip tanks
Stall: 69-70 mph
Baggage: 200 lb
Loaded weight: 3725 lb
PA-39 C/R
Engines: 2 x Lycoming IO-320 B1A, 160 hp / 119kW
Props: Hartzell, Constant speed, full feathering, counter rotating
Wingspan: 35 ft 11 in (19.97m) / 36 ft 9.5 (11.22m) in o/tip tanks
Wing area: 178 sq.ft
Length: 25 ft 2 in (7.67m)
Height: 8 ft 3 in / 2.51 m
Tailplane span: 12 ft 6 in
Empty weight: 2270 lb (1029kg)
MTOW norm: 3600 lb (1633kg)
MTOW w/tip tanks: 3725 lb (1690kg)
Fuel capacity: 90 USG / 120 USG w/tip tanks
Baggage: 250 lb / 113 kg
Max speed SL: 205 mph
Cruise speed SL eco: 181-188 mph
Cruise speed SL norm: 198 mph / 172 kt / 319 kph
Cruise speed 8000ft: 194 mph
Cruise speed 10,000ft eco: 166 mph
Stall: 69-70 mph
Climb rate: 1460 ft/min / 445 m/min
SE Climb rate: 260 ft/min
Service ceiling: 20,000 ft / 6095 m
SE service ceiling: 7100 ft
Takeoff run: 940 ft
Takeoff run to 50ft: 1530 ft
Landing run from 50ft: 1870 ft
Landing run: 700 ft
Range norm fuel: 830 mi / 720 nm / 1335 km
Range eco: 1110 mi
Range max: 1200 mi / 1042 nm / 1930 km
Baggage compartment: 20 cu.ft (0.57cu.m)
Seats: 4-6
39 Turbo
Cruise 12,000ft: 228 mph
Cruise 12,000ft eco: 186-193 mph
Stall: 69-70 mph
Climb rate: 1290 ft/min
SE Climb rate: 225 ft/min
Service ceiling: 25,000 ft
SE service ceiling: 12,600 ft
Takeoff run: 990 ft
Takeoff run to 50ft: 1590 ft
Landing run from 50ft: 1900 ft
Landing run: 725 ft
Range 12,000ft: 1090 mi
Range 12,000ft eco: 1485 mi
Range 12,000ft max: 1535 mi
Range 24,000ft: 1270 mi
Range 24,000ft eco: 1670 mi
Range 24,000ft max: 1710 mi
Empty weight: 2416 lb
Baggage: 250 lb
Loaded weight: 3725 lb
PA-39 B Turbo
Engines: 2 x Lycoming IO-320 B1A, 160 hp
Props: Hartzell, Constant speed, full feathering, counter rotating
Wingspan: 35 ft 11 in
Length: 25 ft 2 in
Height: 8 ft 3 in
Wing area: 178 sq.ft
Tailplane span: 12 ft 6 in
Max speed SL: 240 mph
Service ceiling: 30,000 ft
SE service ceiling: 19,000 ft
Range norm: 1090 mi
Range w/tip tanks: 1360 mi
Empty weight: 2408 lb
Baggage: 250 lb
Loaded weight: 3725 lb
Piper announced in 1972 a completely new version of the PA-25 Pawnee agricultural aircraft which introduced a more powerful Continental Tiara 6-285 flat-six engine of 213kW, a new cantilever wing, new safety features, filtration of the air entering the pilot’s ventilated and heated cockpit, and a larger standard chemical hopper of 0.85cu.m or, optionally, 1.08cu.m capacity. First introduced in Piper’s 1973 model year, over 350 were built up till 1977, all powered by a 285 hp Conti¬nental Tiara engine.
The Brave has a number of innovations to distinguish it from the earlier models of the type. One of the first differences evident is the lack of wing struts, fibreglass leading edges, and the fuel tanks are filled with a plastic foam like “infinite baffle” which is intended to reduce fuel movement and reduce the potential of fire. For the same reason the fuel lines are located behind the main spar. The rear fuselage is “pressurised” from a vent on the tail fin which acts to “push” the super out of the rear fuselage. The system is designed to keep 90% of the dust and dirt out of the fuselage and the easily removable panels make the remaining 10 per cent easy to get at.
A much larger ag aircraft than the original Pawnee, the Pawnee Brave was underpowered in its original 285 hp version. A 300 hp model was introduced in 1977. Designated Piper PA-36 Pawnee Brave, the new model began to enter service in 1973, and in 1977 an additional version with a 300 hp / 224kW Avco Lycoming IO-540-K1G5 engine became available, the designations of these two aircraft then becoming PA-36 Pawnee Brave 285 and PA-36 Pawnee Brave 300.
In 1978 the 300 hp aircraft became the standard model, and a new PA-36 Pawnee Brave 375 being introduced with a 280kW Avco Lycoming IO-720-D1CD flat-eight engine, equipped with the larger of the two chemical hoppers as standard. The engine was a detuned 400 hp Lycoming
These were to remain in production with Piper until rights for both versions of the PA-36 were acquired by WTA Inc. in 1981. This latter company was marketing this agricultural aircraft in two versions, the version with the 280kW engine now being the basic model and redesignated PA-36 New Brave 375. It was available optionally with a 298kW IO-720-D1C engine under the designation PA-36 New Brave 400.
WTA Inc received from Piper rights to PA-18-150 Super Cub lightplane and PA-36 Brave agricultural aircraft; 250 Super Cubs built before becoming once again Piper type, while PA-36 produced as New Brave.
Pawnee Brave
Engines: Continental 6-285-C, 285 hp
Wingspan: 39 ft 0 in / 11.89 m
Length: 27 ft 4.25 in / 8.34 m
Empty weight standard: 2050 lb / 930 kg
Empty weight sprayer: 2170 lb / 984 kg
MTOW weight normal: 3900 lb / 1769 kg
MTOW weight restricted: 4400 lb / 1996 kg
Wing loading: 17.3 lb/sq.ft
Pwr loading: 13.68 lb/hp
Equipped useful load: 1803 lb
Fuel cap: 522 lb
Payload max fuel: 1281 lb
Working speed: 117 kt / 135 mph / 217 kph
75% cruise: 128 kt
Range max fuel 75% pwr: 531 nm/ 4.2 hr
Service ceiling: 13,000 ft
Working endurance: 5 hr
Stall: 54-62 kt
ROC: 790 fpm
Min field length: 1650 ft
Hopper cap: 225 USG / 30 cu.ft / 0.85 cu.m / 852 lt
Opt hopper cap: 275 USG / 38 cu.ft / 1.08 cu.m / 1041 lt / 1900 lb / 862 kg
Cockpit width: 3 ft 2 in / 0.97 m
Seats: 1
PA36-300 Brave 300
Engine: Lycoming I0-540-KIGS, 300 hp / 224kW
Wingspan: 11.89 m / 39 ft 0 in
Length: 8.34 m / 27 ft 4 in
Height: 2.29 m / 8 ft 6 in
Wing area: 20.96 sq.m / 225.61 sq ft
Hopper Cap: 30 or 38 cu.ft
Wing loading: 17.3 lb/sq.ft
Pwr loading: 13 lb/hp
Max TO wt: 3900 lb
Empty wt: 2180 lb
Equipped useful load: 1673 lb
Payload max fuel: 1157 lb
Range max fuel/ 75% pwr: 480 nm/ 3.9 hr
Service ceiling: 12,000 ft
75% cruise: 123 kt / 229 km/h / 142 mph
Working speed: 103 kt
Stall: 54-63 kt
ROC: 770 fpm
Min field length: 1650 ft
Fuel cap: 516 lb
Seats: 1
PA36-375
Engine: Lycoming I0-720, 375 hp
Prop: Hartzell 86in
Useful load: 2285 lb
Hopper cap: 38 cu.ft
For 1972 Piper introduced the six/seven-seat Piper PA-34 Seneca which, basically, was a twin-engine version of the Cherokee SIX with retractable tricycle landing gear, a new fuselage structure and power provided by two 200 hp / 149kW Avco Lycoming IO-360 flat-four engines.
Early models, the Seneca I, handled awkwardly and were slower than expected and the Seneca II incorporated improvements including: turbo-charging, larger and redesigned ailerons and improved stick forces. For 1975 149kW Continental TSIO-360-E turbocharged and counter-rotating engines were introduced and the landing gear was strengthened for operation at higher gross weight, the designation then changing to PA-34-200T Seneca II.
Many Seneca I have been upgraded to Seneca II standard featuring turbo-charged engines and improvements to ailer¬ons, rudder and the stabilator to improve handling.
In 1982 the Seneca II was superseded by an improved PA-34-220T Seneca III. A total of 28 improvements changed the II into the III, and while most of these are cosmetic, the two most significant are further increases in available power, and weight – most of which means useful load. A five minute take-off power rating increases 20 hp to 220, an rpm increase from 2575 to 2800, and an increase in MTOW of 180 lbs. This translates to a 190 lbs increase in useful load. The Seneca III has Continental TSIO-360-KB turbocharged and counter-rotating engines.
The PA-34-220T Seneca III remained in production in 1984.
During 1976-77 Piper signed an agreement with the Polish foreign trade association Pezetel under which P.Z.L. Mielec will assemble/manufacture the Seneca for sale in eastern Europe. Designated in Poland as the P.Z.L. Mielec M-20 Mewa (Gull), the first Polish-built prototype was flown on 25 July 1979. The production version M-20 03 was one of the very few light-twins on the market.
It was reported in February 1981 that the Forca Aerea Brasileira had placed an order for a follow-on batch of 20 EMB-810 (Seneca II) for liaison work, 11 having the Robertson STOL modifications. The EMB-810 is designated U-7 by the FAB, the initial order having called for 12 aircraft.
In 1994, the “new” Piper Aircraft company introduced the Seneca IV, having acquired its license on November 17, 1993. This model is similar to the Seneca III offering small improvements such as modifying the engine hood for better cruise performance. It still continued to use the counter-rotating technique with the Continental IO-360 and Continental TSIO-360-KB engines and the maximum weights remained the same.
In Brazil, versions with the economical Continental IO 360 aspirated Seneca II (two-bladed propeller) and Seneca III (three-bladed propeller) were a major selling success in the 1970s and 1980s, leading to a licensing agreement between Piper and Brazilian manufacturer Embraer, on a new EMB-810 D and Cuesta designation for the same basic design. Subsequently, the manufacture of the aircraft was transferred to the subsidiary of Embraer, Indústria Aeronáutica Neiva.
The Seneca IV was the last Piper produced under license by Embraer and that agreement terminated in 1996.
A total of 4,464 Seneca were delivered by 1 January 1991.
New Piper continued production of the Seneca V.
Certification was under FAA A7SO for:
PA-34-200
34-7250001 to 34-7250189 when kit number 760607 is installed.
34-7250190 to 34-7250214 when kit number 760611 is installed.
34-7250215 to 34-7350353
34-7450001 to 34-7450220
PA-34-200T Seneca II
All, except with kit number 764-048V or 765-110 installed.
PA-34-220T Seneca III
All, except with kit number 764-099V or 766-203 installed
PA-34-220T Seneca V
3440991 and up, except with kit number 766-632 installed or Avidyne Entegra System installed
Specifications:
PA-34-200
Engines: Two 200hp Lycoming IO-360
Wingspan: 38’11”
Length: 28’6″
Useful load: 1600 lb
Max speed: 198 mph
Cruise:183 mph
Range: 940-1130 mi
Ceiling: 20,000′
Seats: 6-7
No. built: 933
PA34-200T Seneca II
Engines: 2 x Continental TSIO-360-E, 200 hp at sea level, 215 hp at 12,000 ft
Seats: 6/7
Wing loading: 22 lb/sq.ft
Pwr loading: 11.4 lb/hp
Gross wt: 4570 lb
Empty wt: 2788 lb
Equipped useful load: 1654 lb
Payload max fuel: 916 lb
Range max fuel/ 75% pwr: 864 nm/4.5 hr
Range max fuel / 55% pwr: 998 nm/ 6.1 hr
Service ceiling: 25,000 ft
Cruise 75%: 190 kts @ 20,000 ft
55% cruise: 165 kt
Vmc: 70 kt
Stall: 61-63 kt
1.3 Vso: 79 kt
ROC: 1340 fpm
SE ROC: 225 fpm @ 90 kt
SE Service ceiling: 13,400 ft
Min field length: 1568 ft
Fuel cap: 588/738 lb
Undercarriage: retractable
T/O dist (50 ft): 1240 ft
Ldg dist (50 ft): 1860 ft
Number built: 2588
PA34-220T Seneca III
Engine: 2 x Continental, TSIO-360KB & LTSIO-360KB, 220 hp @ 2800 rpm (5 min), 200 hp @ 2600 rpm continuous
TBO: 1800 hr
Prop: Hartzell 2 blade, constant speed 76 in
Seats: 6/7
Length: 28.5 ft
Height: 9.9 ft
Wingspan: 11.86 m / 39 ft 11 in
Wing area: 209 sq.ft
Wing aspect ratio: 7.4
Max ramp wt: 4773 lb
Max take off wt: 4750 lb / 2155 kg
Standard empty wt: 2875 lb
Max useful load: 1898 lb
Max landing wt: 4513 lb
Wing loading: 22 lbs/sq.ft
Power loading: 11.4 lbs/hp
Max useable fuel: 738 lb
Climb rate: 1400 fpm @ 89 kt
Climb gradient: 903 ft/nm
Rate of climb @ 8000 ft: 1275 fpm
Certificated ceiling; 25,000 ft / 7620 m
SE rate of climb: 240 fpm @ 92 kt
SE climb gradient: 157 ft/nm
SE ceiling: 12,300 ft
Max speed: 196 kt
Cruise @ 65% power @ 8,000ft: 164 kt
Cruise @ 65% pwr @ 18,000 ft: 180 kt
Fuel flow @ 65% power @ 18,000ft: 121 pph
Endurance @ 65% power @ 18,000ft: 5.8 hr
Stalling speed clean: 65 kt
Stall speed gear/flaps down: 62 kt
Turbulent air penetration speed: 140 kt
Retractable undercarriage
Cabin length: 125 in
Cabin height: 49 in
Cabin volume: 195.3 cu.ft
Fuel capacity: Std: 371 lt, Optional: 484 lt
TO dist: 920 ft
Landing dist: 1218 ft
Piper PA34 – 220T Seneca IV
Engines: 2 x Teledyne Continental TSIO / LTSIO 360 KB, 232 hp
Length: 28.576 ft / 8.71 m
Height: 9.908 ft / 3.02 m
Wingspan: 38.911 ft / 11.86 m
Wing area: 208.714 sq.ft / 19.39 sq.m
Max take off weight: 4749.6 lb / 2154.0 kg
Weight empty: 2853.3 lb / 1294.0 kg
Max. payload weight: 1920.6 lb / 871.0 kg
Max. speed: 196 kt / 363 km/h
Landing speed: 64 kt / 119 km/h
Cruising speed: 193 kt / 357 km/h
Take off distance: 1211 ft / 369 m
Landing distance: 1978 ft / 603 m
Service ceiling: 25000 ft / 7620 m
Wing loading: 22.76 lb/sq.ft / 111.0 kg/sq.m
Range: 990 nm / 1833 km
Crew: 2+4
2007 Piper PA34-220T Seneca V
Engines: Continental TSIO-360-RB, 220 hp
TBO: 1800 hr
Fuel type: 100/100LL
Propeller: Hartzell CS/2-blade
Landing gear: Tri./Retr.
Max ramp weight: 4773 lb
Gross weight: 4750 lb
Landing weight: 4513 lb
Empty weight, std: 3393 lb
Useful load, std: 1380 lb
Usable fuel, std: 122 USgal
Payload, full std. fuel: 648 lb
Wingspan: 38 ft. 10 in
Overall length: 28 ft. 7 in
Height: 9 ft. 11 in
Wing area: 208.7 sq. ft
Wing loading: 22.8 lbs./sq. ft
Power loading: 10.8 lbs./hp
Wheel size: 6.00 x 6
Seating capacity: 6
Cabin doors: 2/3
Cabin width: 49 in
Cabin height: 42 in
Cruise speed 75% power: 197 kt
Cruise speed 65% power: 190 kt
Fuel consumption 75% power: 26.4 USgph
Fuel consumption 65% power: 22.8 USgph
Cruising range: 828+ nm
Vso: 64 kt
Best rate of climb (SL): 1462 fpm
Service ceiling: 25,000 ft
Service ceiling, SE: 16,500 ft
Takeoff ground roll: 1143 ft
Takeoff over 50 ft. obstacle: 1707 ft
Landing ground roll: 1400 ft
Landing over 50 ft. obstacle: 2180 ft
PZL Mielec M 20 Mewa
Engines: 2 x Teledyne Continental TSIO 360 KB, 217 hp
Length: 28.609 ft / 8.72 m
Height: 9.908 ft / 3.02 m
Wingspan: 38.911 ft / 11.86 m
Wing area: 206.454 sq.ft / 19.18 sq.m
Max take off weight: 4564.4 lb / 2070.0 kg
Weight empty: 2910.6 lb / 1320.0 kg
Max. speed: 194 kts / 360 km/h
Landing speed: 60 kts / 112 km/h
Cruising speed: 168 kts / 311 km/h
Initial climb rate: 1496.06 ft/min / 7.60 m/s
Service ceiling: 25000 ft / 7620 m
Wing loading: 22.14 lb/sq.ft / 108.0 kg/sq.m
Maximum range: 990 nm / 1833 km
Range: 670 nm / 1240 km
Crew: 1+6
In 1967 a single Comanche, N4600Y, was modified by Swearingen with a pressurised cabin.
The prototype, powered by a 260-hp Lycoming TIO-540 engine and equipped with Twin Comanche landing gear, tail and wings and a new fuselage, was first flown on 11 March 1967.
The Comanche crashed on takeoff from Lock Haven 23 March 1967 when the pilot had problems with the electric nosewheel. The project was then cancelled and removed from the Register in 1969.
The Piper PA-32-3M was basically a PA-32 Cherokee based prototype modified as a Trimotor aircraft with two 115-hp Lycoming O-235 engines fitted to the wings, for development of the PA-34 Seneca at Vero Beach FL. in the early ’70s. This prototype significantly helped many other development projects at Piper.
It was an early attempt to convert the PA-32-260 Cherokee 6 into a simple, low-cost trimotor, retaining the fixed gear and using fixed-pitch props. This was actually tested by adding two 115 hp engines to the wings and throttling the Cherokee 6’s 260 hp engine back to simulate a third O-235 for a total of 345 hp.
Performance on all three engines was fine, but engine out performance was not. Switching the 115 hp engines for 150 hp units solved that problem, but speed was now so high on 450 hp that controllable-pitch props were needed, defeating the original purpose. That model eventually became the Seneca, but with two larger engines, variable-pitch props and retractable gear.
On 6 December 1963 Piper flew the prototype of a six-seat version of the PA-28 Cherokee, retaining the same general configuration but differing primarily by having a slight increase in wing span, the fuselage lengthened by 1.35m, and the installation of the 194kW Avco Lycoming O-540-E4B5 engine. These were the wings, rear fuselage and tail of the Cherokee 235. Designated Piper PA-32-260-6 Cherokee Six, it was available initially in Standard, Custom, Executive and Sportsman versions with differing standards of installed equipment. By 1966 the company designation had changed to PA-32-260 and the Cherokee Six was then available as an optional six/seven-seat aircraft and, as the PA-32-300, with an optional 224kW IO-540-K engine.
In 1971 Piper restyled the name to Cherokee SIX, but apart from annual product improvement, there were no changes until 1975 when a new version designated PA-32R-300 Cherokee Lance entered production to complement the Cherokee SIX, differing by introduction of a new fuselage structure and retractable tricycle landing gear. The Lance carries 66 pounds more fuel than the similarly powered but fixed gear Cherokee Six, yet it has a 48 pound higher max fuel useful load, and it can produce nearly nine percent more nmpg than the Six at 75 percent power in spite of its 200 pound ¬higher gross weight.
The 1978 version of the Lance had the conventional tail unit replaced by a T-tail, the designation then changing to PA-32RT-300 Lance II and, at the same time, a model with 224kW TIO-540-S1AD turbocharged engines became available under the designation PA-32RT-300T Turbo Lance II.
Production of PA-32-260 Cherokee SIX ended in late 1978, the remaining version then being redesignated PA-32-300 SIX 300, but in the following year this also disappeared, together with the Lance II and Turbo Lance II. These aircraft were superseded by the six/seven-seat PA-32-301 Saratoga (the basic member of the new related family) in 1980 which had an increased-span tapered wing, reversion to a conventional tail unit, fixed tricycle landing gear, and a 224kW IO-540-K1G5D engine driving a constant-speed propeller.
Made available simultaneously was the generally similar PA-32-301T Turbo Saratoga, which had a turbocharged version of the same engine, and the corresponding PA-32R-301 Saratoga SP and PA-32R-301T Turbo Saratoga SP which differed by having retractable tricycle landing gear. Only very low volume production continued into the early 1990s.
The Embraer EMB-720 “Minuano” is the Piper PA-32 Cherokee Six produced in Brazil by Embraer and later by its subsidiary Neiva, under license from Piper Aircraft. Equipped with Lycoming engine with direct injection of fuel and 300 HP of power, it develops 270 km / h. Its electronic communication and radionavigation system was considered modern for the time. It can carry up to six people (1 pilot + 5 passengers) with ample luggage space.
293 Minuano aircraft were marketed between 1975 and 1996. Designed to operate in regions with short and unpaved runways, it was widely used to link cities to farms and remote regions, such as garimpo areas.
The Embraer EMB-721 “Sertanejo” is a PA-32R, produced in Brazil by Embraer and later by its subsidiary Neiva, under license from Piper Aircraft.
Chincul SACAIFI manufactured aircraft under license from Piper Aircraft Corporation. The company was a wholly owned subsidiary of “La Macarena S.A.”, Piper’s Argentine agent. Production included 26 Piper PA-32R.
Produced from 1975 to 2000, 208 Sertanejo were built by Embraer in Brasil.
Certification is under FAA A3SO for models:
PA-32-260
32-1111 to 32-7200045
32-740001 to 32-7600024
32-770001 to 32-7800008
PA-32-300
All
PA-32R-300
32R-7780001 to 32R-7880066
PA-32R-301
Up to 3213041
PA-32-301T
Up to 32-8424002
PA-32R-301T
Up to 3229003
PA-32S-300
32S-40566 to 32S-7240137
Specifications:
PA32-260
Engine: 1 x Lycoming O-540-E4B5, 260 hp
Seats: 6/7
Wing loading: 19.5 lb/sq.ft
Pwr loading: 13 lb/hp
Gross wt: 3400 lb
Empty wt: 1767 lb
Equipped useful load: 1556 lb
Payload max fuel: 1054 lb
Range max fuel/75% pwr: 712nm/5.3hr
Range max fuel / 55% pwr: 834 nm/ 7.3 hr
Service ceiling: 12,800 ft
75% cruise: 133 kt
55% cruise: 115 kt
Stall: 47-54 kt
1.3 Vso: 61 kt
ROC: 775 fpm
Min field length: 1800 ft
Fuel cap: 502 lb
PA 32 Cherokee Six D
Engine: Lycoming O 540 E, 260 hp
Length: 27 ft 8.75 in
Wingspan: 32 ft 9.5 in
Speed: 166 mph
Ceiling: 14,500 ft
Range: 550 mls
Seats: 6
PA32-300
Engine: 1 x Lycoming O-540-K1G5, 300 hp
Seats: 6/7
Wing loading: 19.5 lb/sq.ft
Pwr loading: 11.3 lb/hp
Gross wt: 3400 lb
Empty wt: 1824 lb
Equipped useful load: 1509 lb
Baggage cap: 28 cu.ft
Payload max fuel: 1007 lb
Range max fuel/75% pwr: 658nm/4.5hr
Range max fuel / 55% pwr: 844 nm/ 6.3 hr
Service ceiling: 16,250 ft
75% cruise: 146 kt
55% cruise: 135 kt
Stall: 47-54 kt
1.3 Vso: 61 kt
ROC: 1050 fpm
Min field length: 1350 ft
Fuel cap: 502 lb
1977 Piper Cherokee Six 300
Engine: Lycoming IO-540K, 300 hp @2700 rpm
TBO: 2000 hr
Fuel type: 100/100LL
Propeller: CS two-blade
Landing gear: Tri/Fixed
Max ramp weight: 3400 lb
Gross weight: 3400 lb
Landing weight: 3400 lb
Empty weight, std: 1822 lb
Useful load, std: 1578 lb
Payload, full std. fuel: 1080 lb
Usable fuel: 84 USG
Oil capacity: 12 qt
Wingspan: 32 ft. 9 in
Overall length: 27 ft. 9 in
Height: 8 ft. 3 in
Wing area: 174.5 sq. ft
Wing loading: 19.5 lbs./sq. ft
Power loading: 11.3 lbs./hp
Wheel base: 6 ft. 10 in
Wheel track: 10 ft. 7 in
Wheel size: 6.00 x 6 in
Seating capacity: 6-7
Cabin doors: 2-3
Cabin width: 49 in
Cabin height: 49 in
Baggage capacity (nose): 100 lb
Baggage capacity (rear): 100 lb
Cruise speed 75% power @ 8,000 ft.: 146 kt
Cruise speed 65% power @ 11,300 ft.: 142 kt
Cruise speed 55% power @ 14,000 ft.: 134 kt
Fuel consumption 75% power: 16.0 USGph
Fuel consumption 65% power: 13.8 USGph
Fuel consumption 55% power: 11.9 USGph
Stall speed (flaps up): 61 kt
Stall speed (flaps down): 55 kt
Best rate of climb: 1225 fpm
Best rate of climb (8,000 ft): 680 fpm
Service ceiling: 16,250 ft
Takeoff ground roll: 1050 ft
Takeoff over 50-ft. obstacle: 1500 ft
Landing ground roll: 630 ft
Landing over 50-ft. obstacle: 1000 ft
Cherokee Six 300
Engine: Lycoming IO-540-K, 300 hp
Wingspan: 32 ft 9.5 in / 9.99 m
Length: 27 ft 8.25 in / 8.45 m
Empty weight: 1818 lb / 824 kg
MTOW: 3400 lb / 1542 kg
Max cruise 75%: 145 kt / 168 mph / 270 kph
ROC SL: 1050 fpm / 320 m/min
Service ceiling: 16,250 ft / 4950 m
Cruise range 65%: 738 nm / 850 mi / 1368 km
Cruise range 55%: 894 nm / 1030 mi / 1658 km
Seats: 6
Cabin length: 9 ft 11 in / 3.02 m
Cabin width: 4 ft 1 in / 1.24 m
Cabin max height: 4 ft 0.5 in / 1.23 m
Cabin volume: 110 cu.ft / 3.11 cu.m
Forward baggage compartment: 8 cu.ft / 0.23 cu.m
Rear baggage compartment: 22 cu.ft / 0.62 cu.m / 100 lb / 45 kg
PA-32-300 B Cherokee Six
Engine: Lycoming IO-540-K1A5, 300 hp
Prop diameter: 80 in
Wingspan: 32.8 ft
Wing area: 174.5 sq.ft
Wing loading: 19.5 lb/sq.ft
Length: 27.7 ft
Height: 7.9 ft
Power loading: 11.3 lb/hp
Empty weight: 1777 lb
Useful load: 1623 lb
Empty weight seats out: 1707 lb
Useful load seats out: 1693 lb
Fuel capacity inboard: 50 USG
Std Aux fuel: 34 USG
Fuel: 100/130 Octane
Max baggage fwd/aft: 100/100 lb
Baggage space: fwd/aft: 8/20 cu.ft
Door size: 16in x 22in
TO run: 700 ft
TO 50 ft: 1140 ft
ROC speed: 105 mph
ROC: 1050 fpm
Service ceiling: 16,250 ft
Absolute ceiling: 18,000 ft
Top speed: 174 mph
Cruise 75% 7000ft: 168 mph
Cruise range 55% std fuel: 630 mi
Cruise range 55% Aux fuel: 1060 mi
Cruise range 75% std fuel: 525 mi
Cruise range 75% aux fuel: 880 mi
Stall 40deg flap: 63 mph
Stall flap up: 70 mph
Landing roll: 630 ft
Landing dist 50 ft: 1000 ft
Piper 1976 PA-32-300 Lance
Engine: Lycoming IO-540-K1A5D, 300 hp
TBO: 2000 hr
Propeller: Const. spd.
Landing gear: Tri/Retr.
Gross weight: 3600 lb
Empty weight, std: 1973 lb
Useful load, std: 1627 lb
Fuel: 94 USG
Wingspan: 32 ft. 8 in
Overall length: 27 ft. 7 in
Height: 7 ft. 9 in
Wing area: 174.5 sq. ft
Seating capacity: 6-7
Cabin width: 49 in
Cabin height: 48.5 in
Baggage capacity: 200 lb
Cruise speed 75% power: 158 kt
Cruise speed 65% power: 148 kt
Max range (w/ res) 75% power: 700 nm
Max range (w/ res) 65% power: 800 nm
Fuel consumption 75% power: 16.5 USgph
Fuel consumption 65% power: 14.0 USgph
Stall speed (gear, flaps down): 61 kt
Best rate of climb: 1000 fpm
Service ceilin): 14,600 ft
Takeoff ground roll: 970 ft
Landing ground roll: 870 ft
Cherokee Lance
Engine: 1 x Lycoming IO-540-K1G5D, 300 hp
TBO: 2,000 hr
Prop: constant speed, two blade, 80 in dia
Seats: 6/7
Length: 27 ft. 9 in
Height: 8 ft. 2 in
Wingspan: 32 ft. 10 in
Wing area: 174 ft. 6 in
Wing loading: 20.6 lb/sq.ft
Pwr loading: 12 lb/hp
Gross wt: 3600 lb
Empty wt: 1910 lb
Equipped useful load: 1623 lb
Payload max fuel: 1059 lb
Range max fuel/75% pwr: 828 nm/5.2 hr
Range max fuel / 55% pwr: 994 nm/ 7.2 hr
Range at max cruise (45 min res): 780 nm
Range at economy cruise (45 min res): 880 nm
Service ceiling: 14,600 ft
Maximum speed: 165 kt
Max cruise (best economy): 156 kt
Economy cruise (55 % power @ 10,000 ft.): 134 kt
Duration max cruise, no reserve: 5.75 hrs
Stall speed (clean): 66 kt
Stall speed flaps, gear down: 61 kt
1.3 Vso: 68 kt
ROC: 1000 fpm
Min field length: 1708 ft
Fuel cap: 94 USG/564 lb
Undercarriage: Retractable nose
Lance II
Engine: Lycoming IO 540, 300 hp
Prop: 80 inch, two blade, constant speed
TBO: 2,000 hr
Length: 27 ft. 8 in
Height: 9 ft. 6 in
Wingspan: 32 ft. 10 in
Wing area: 174.5 sq. ft
Wing loading: 20.6 lb/sq.ft
Power loading: 12 lb/hp
Seats: 6
Empty wt: 2,228 lb
Useful load: 1,372 lb
Payload with full fuel: 808 lb
Gross weight: 3,600 lb
Usable fuel cap: 94 USG/564 lb
Max rate of climb: 1,000 fpm
Service ceiling: 14,600 ft
Certificated ceiling: 16,200 ft
Max speed: 165 kt
Max cruise, 75% power (2,400 rpm) at 7,500 ft: 158 kt
Econ cruise, 55% power at 13,500 ft: 138 kt
Duration at max cruise: 5.2 hr
Duration at econ cruise: 7.9 hr
Stalling speed, clean: 77 kt
Stalling speed, full flaps: 70 kt
Turbo Lance
Engine Lycoming TIO 540 S1AD, 300 hp
TBO 1,800 hr
Prop Hartzell, constant speed, 80 in
Length 29 ft
Height 9 ft. 6 in
Wingspan: 32 ft 9 in
Wing area 175.4 sq.ft
Wing loading 20.6 lb/sq.ft
Power loading 12 lb/hp
Seats 6
Empty weight 2,382 lb
Useful load 1,217 lb
Payload with full fuel 653 lb
Gross weight 3,600 lb
Usable fuel capacity 94 USG/564 lb
Maximum landing weight 3,600 lb
Maximum rate of climb 1,000 fpm
Service ceiling 20,000 ft
Certificated ceiling 20,000 ft
Maximum speed 193 kt
Max cruise, 75% power (2,400 rpm) at 20,000 ft 176 kt
Econ cruise, 55 % power 142 kt
Duration at max cruise 3.45 hr
Duration at econ cruise 4.3 hr
Stalling speed, clean 57 kt
Stalling speed, full flaps 52 kt
Turbo Lance II
Engine: turbocharged, 300 hp
Seats: 6/7
Cruise: 158 kts
Range: 864 nm
PA32-301 Saratoga
First built: 1980
Engine: 1 x Lycoming IO-540-K1G5D, 300 hp
TBO: 2000 hrs
Prop: Hartzell 2 blade, constant speed 80 in
Seats: 6/7
Length: 28.3 ft
Height: 9 ft
Wingspan: 36 ft
Wing area: 178 sq.ft
Wing aspect ratio: 7.3
Max ramp wt: 3615 lb
Max take off wt: 3600 lb
Standard empty wt: 1940 lb
Max useful load: 1675 lb
Max landing wt: 3600 lb
Wing loading: 20.2 lbs/sq.ft
Power loading: 12 lbs/hp
Max useable fuel: 612 lb
Climb rate: 990 fpm @ 90 kt
Climb gradient: 660 ft/nm
Rate of climb @ 8000 ft: 535 fpm
Service ceiling; 14,100 ft
Max speed: 152 kt
Cruise @ 65% power @ 8,000ft: 140 kt
Fuel flow @ 65% power @ 8,000ft: 96 pph
Endurance @ 65% power @ 8,000ft: 6.2 hr
Stalling speed clean: 66 kt
Stall speed flaps down: 60 kt
Turbulent air penetration speed: 132 kt
Fixed undercarriage
PA-32-301T Turbo Saratoga
Engine: 1 x Avco Lycoming TIO-540-S1AD, 224kW / 300 hp
TBO: 1800 hr
Prop: Hartzell 2 blade, constant speed 80 in
Length: 29 ft
Height: 9 ft
Wingspan: 36 ft
Wing aspect ratio: 7.3
Wing area: 16.56 sq.m / 178.25 sq ft
Max ramp wt: 3617 lb
Max take off wt: 3600 lb
Standard empty wt: 2003 lb
Max useful load: 1614 lb
Max landing wt: 3600 lb
Wing loading: 20.2 lbs/sq.ft
Power loading: 12 lbs/hp
Max useable fuel: 612 lb
Max. speed: 330 km/h / 205 mph / 182 kt
Climb rate: 1075 fpm @ 90 kts
Climb gradient: 717 ft/nm
Rate of climb @ 8000 ft: 950 fpm
Cruise @ 65% power @ 8,000ft: 140 kt
Cruise @ 65% pwr @ 18,000 ft: 152 kt
Fuel flow @ 65% power @ 18,000ft: 103 pph
Endurance @ 65% power @ 18,000ft: 5.7 hr
Stalling speed clean: 67 kt
Stall speed flaps down: 60 kt
Turbulent air penetration speed: 132 kt
Certificated ceiling: 6095 m / 20,000 ft
Range: 1593 km / 990 miles
Seats: 6/7
Retractable undercarriage.
PA32 Saratoga SP
Engine: 1 x 300 hp Lycoming
Seats: 6
Empty Wt: 1999 lbs
Gross wt: 3600 lb
Useful load: 1601 lb
Max Cruise: 190 mph
Max range: 996 sm
1998 Piper PA-32R-301 Saratoga HP
Price: $378,900
Engine: Lycoming IO-540-K1G5, 300 hp @2500 rpm
TBO: 2000 hr
Fuel type: 100/100LL
Propeller: Hartzell 2 blade, constant speed 80 in
Landing gear: Tri/Retr
Max ramp weight: 3615 lb
Gross weight: 3600 lb
Max landing weight: 3600 lb
Empty weight: 2407 lb
Useful load, std: 1208 lb
Payload, full std. fuel: 596 lb
Usable fuel: 102 USG / 612 lb
Oil capacity: 12 qt
Wingspan: 36 ft. 2 in
Overall length: 27 ft. 10 in
Height: 8 ft. 6 in
Wing area: 178.3 sq. ft
Wing aspect ratio: 7.3
Wing loading: 20.2 lbs./sq. ft
Power loading: 12.0 lbs./hp
Wheel base: 7 ft. 11 in
Wheel track: 11 ft. 1 in
Wheel size: 6.00 x 6
Seating capacity: 5/6
Cabin doors: 2
Cabin width: 49 in
Cabin height: 42 in
Baggage capacity: 200 lb /24.3 cu.ft
Cruise speed 75% power @ 6,000 ft.: 163 kt
Cruise speed 65% power @ 9,000 ft.: 158 kt
Cruise @ 65% power @ 8,000ft: 149 kts
Cruise speed 55% power @ 11,000 ft.: 154 kt
Max range (w/ res) 75% power: 740 nm
Max range (w/ res) 65% power: 800 nm
Max range (w/ res) 55% power: 860 nm
Fuel consumption 75% power: 18.5 USgph
Fuel consumption 65% power: 16.5 USgph
Fuel flow @ 65% power @ 8,000ft: 96 pph
Fuel consumption 55% power: 14.5 USgph
Endurance @ 65% power @ 8,000ft: 6.2 hr
Climb rate: 1010 fpm @ 91 kt
Climb gradient: 666 ft/nm
Rate of climb @ 8000 ft: 540 fpm
Service ceiling: 15,588 ft
Stalling speed clean: 65 kt
Stall speed gear/flaps down: 59 kt
Turbulent air penetration speed: 132 kt
Takeoff ground roll: 1200 ft
Takeoff over 50-ft. obstacle: 1800 ft
Landing ground roll: 640 ft
Landing over 50-ft. obstacle: 1520 ft
1983 Piper PA-32-301T Saratoga SP
Engine: Lycoming TIO-540-S1AD, 300 hp
TBO: 1800 hr
Propeller: Hartzell 2 blade, constant speed 80 in
Landing gear: Tri/Retr.
Max ramp wt: 3617 lb
Max take off wt: 3600 lb
Standard empty wt: 2066 lb
Max useful load: 1551 lb
Max landing wt: 3600 lb
Wing loading: 20.2 lbs/sq.ft
Power loading: 12 lbs/hp
Fuel: 102 USG / 612 lb
Wingspan: 36 ft. 2 in
Overall length: 28 ft. 4 in
Height: 8 ft. 6 in
Wing area: 178 sq. ft
Wing aspect ratio: 7.3
Seating capacity: 6-7
Cabin width: 49 in
Cabin height: 49 in
Baggage capacity: 200 lb
Max speed: 191 kts
Cruise speed 75% power: 172 kt
Cruise @ 65% power @ 8,000ft: 149 kt
Cruise @ 65% pwr @ 18,000 ft: 164 kt
Max range (w/ res) 75% power: 845 nm
Max range (w/ res) 65% power: 920 nm
Fuel consumption 75% power: 16.5 USgph
Fuel consumption 65% power: 14.0 USgph
Fuel flow @ 65% power @ 18,000ft: 103 pph
Endurance @ 65% power @ 18,000ft: 5.8 hr
Climb rate: 1120 fpm @ 92 kt
Climb gradient: 730 ft/nm
Rate of climb @ 8000 ft: 1000 fpm
Stalling speed clean: 63 kt
Stall speed gear/flaps down: 60 kt
Turbulent air penetration speed: 132 kt
Service ceiling: 20,000 ft
Takeoff ground roll: 1110 ft
Landing ground roll: 732 ft
Saratoga II HP
Engine: Lycoming IO-540-K1G5
Useful load: 546 kg
Endurance: 6.3 hr
Cruise: 166 kt
2007 Piper PA32-301T Saratoga II TC
Engine: Lycoming TIO-540-AH1A, 300 hp @SL to 18,000 ft
TBO: 2000 hr
Fuel type: 100/100LL
Propeller: Hartzell CS/3-blade
Landing gear type: Tri./Retr.
Max ramp weight: 3615 lb
Gross weight: 3600 lb
Empty weight, std: 2475 lb
Useful load, std: 1140 lb
Payload, full std. fuel: 513 lb
Useable fuel, std: 102 USG
Wingspan: 36.2 ft
Overall length: 27.9 ft
Height: 8.5 ft
Wing area: 178.3 sq. ft
Wing loading: 20.2 lbs./sq. ft
Power loading: 12 lbs./hp
Wheel size: 6.00 x 6
Seating capacity: 6/7
Cabin doors: 2/3
Cabin width: 48.75 in
Cabin height: 42 in
Baggage capacity: 200 lb
Cruise speed (kts.): 75% power: 185
Fuel consumption 75% power: 18.5 USgph
Fuel consumption 65% power: 16.5 USgph
Range 55% power: 950 nm
Vso: 63 kt
Best rate of climb, SL: 1120 fpm
Service ceiling: 20,000 ft
Takeoff ground roll: 1110 ft
Takeoff over 50 ft obstacle: 1810 ft
Landing ground roll: 880 ft
Landing over 50 ft obstacle: 1700 ft
All Aero 