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.
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 These aircraft were superseded by the six/seven-seat PA-32-301 Saratoga (the basic member of the new related family) in 1980 which had an increased-span tapered wing, reversion to a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
While the Arrow might look like a Cherokee and the design is almost identical, it does differ in being a retractable undercarriage four-seater powered by a 180 or 200 hp engine. First flown on 1 February 1967, sales began slowly in 1967, gaining impetus when the 200 hp version was introduced two years later. In 1969 Piper made available an optional PA-28-200R Cherokee Arrow with a 149kW IO-360-C1C engine.
The 1976 Arrow II evolved from the original 180 hp model built and introduced in 1967 with a useful load of 1120 lbs. 20 more hp were added in 1969, upping the useful load to 1119 lbs. and the service ceiling by 1700 ft. to a maximum of 17,000. Improvements came year by year with significant changes in 1980 (longer fuselage and wider door), 1977 the new wing with tapered outer sections (as the Arrow II) and in 1979 a T-Tail. 2,850 were built.
Although Piper retained the Lycoming IO 360 for the normally aspirated Arrow III (491 built), they redesigned the cowling of the Turbo Arrow III (793 built) to accommodate the Continental TSIO-360 F, a slightly modified version of the Seneca II’s six cylinder engine. The turbocharged Continental brings considerable added performance to the Arrow. In addition to producing full power to 12,000 feet and 75 percent to the aircraft’s maximum approved operating altitude of 20,000 feet, the engine is rated at 200 hp with its exhaust system in place. This additional power allowed Piper to up the Turbo Arrow III’s gross to 2,900 pounds compared with 2,750 pounds for the normally aspirated Arrow III and 2,650 pounds for the Arrow II.
The turbocharged Continental gives the Turbo Arrow III a 10 to 25 knot true airspeed advantage over the normally aspirated Arrow III when both aircraft are operating at their best altitudes at roughly equivalent power settings. Producing approximately 75 percent power at 10,000 feet, the Turbo Arrow will cruise at 154 knots; 143 knots is the best the straight Arrow III can do at 75 percent. Top speed for the turbocharged Piper is 178 knots at 14,000 feet, while for the Arrow III, it’s 152 knots at sea level.
The Turbo Arrow III’s semi tapered wing improves the aircraft’s takeoff, climb and altitude performance. Although the new wing has the same surface area as the wing on older Arrows (170 square feet), the area of the Arrow III’s new mainplane and the lift it generates are distributed over a longer span. Also, more lift is produced along the main portion of the wing, where the adverse effect of the wingtip vortices is not felt. The geometric difference between the old and new Arrow wings is expressed in their aspect ratios: 6.02 for the old Arrow and 7.21 for the Arrow III. The positive effect of the Turbo Arrow III’s longer span and better lift distribution is about 20 percent less induced drag.
The new wing also enhances the Turbo Arrow III’s roll control. The ailerons are long¬er, and the tapered wing responds well to their influence, even though these ailerons are not the nicely balanced Frise type used on the original Warrior wing. In the interest of manufacturing simplicity, and since there was very little deterioration in roll performance, Piper returned to the old simple hinged aileron that they used on the original Cherokee models.
Each of these major developments received a distinctive title such as Arrow IV for the T-tailed version.
Production continued after nearly 7000 Arrows had been delivered by 1988.
The Piper Arrow project was licensed in the 1970s to be manufactured in Brazil by Brazilian manufacturer Embraer and later years later by its subsidiary Neiva and the project was renamed Corisco by Embraer in Brazil. At that time there was a strong interest of the Brazilian Government to stimulate the Brazilian aeronautical industry and executive air transport in Brazil and other Piper projects were also licensed for manufacturing in Brazil.
The Embraer Corisco, in all its versions, managed to establish itself for about two decades in the Brazilian market, with almost 480 units sold.
An improved version of the Embraer Corisco, manufactured from the 1980s by Embraer and Neiva as EMBRAER EMB-711 ST Corisco Turbo was manufactured in Brazil. The Embraer Corisco Turbo is a modernized version of the modest Embraer Corisco, with a few touches of sophistication and refinement, including turbocharger, variable pitch propeller, retractable landing gear, improved sound insulation, leather seats, among other items.
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 960 PA-28 Cherokee.
Chincul-built PA-28 Arrow
PA28-180S Arrow
Engine: 180hp Lycoming O-360-A3A
Length: 23’6
Speed: 152 mph
Range: 845 mi
PA28-180 Cherokee Arrow I
Engine: 180hp Lycoming IO-360-B1E
Useful load: 1120 lb
Max speed: 170 mph
Cruise: 162 mph
Range: 995 mi
Ceiling: 15,000′
PA-28R-200 Arrow
Engine: Lycoming IO-360-C1C6, 200 hp
TBO: 2000 hr
Fuel type: 100/100LL
Propeller: McCauley CS
Landing gear type: Tri/Retr.
Gross weight: 2750 lb
Landing weight: 2750 lb
Empty weight, std: 1790 lb
Useful load, std: 960 lb
Payload, full std. fuel: 572 lb
Usable fuel: 72 USgal
Oil capacity: 8 qt
Wingspan: 35 ft. 5 in
Overall length: 24 ft. 8 in
Height: 7 ft. 10 in
Wing area: 170 sq. ft
Wing loading: 16.18 lbs./sq. ft
Power loading: 13.75 lbs./hp
Wheel base: 7 ft. 10 in
Wheel track: 10 ft. 6 in
Wheel size: 6.00 x 6
Seating capacity: 4
Cabin doors: 1
Cabin width: 41 in
Cabin height: 45 in
Baggage capacity: 200 lb
Cruise speed 75% power @ 6,000 ft.: 137 kt
Max range (w/ res) 55% power @ 9,000 ft: 880 nm
Fuel consumption (.42 lbs./hp/hr. @ sfc) 75% power: 10.5 USgph
Stall speed (flaps up): 60 kt
Stall speed (flaps down): 55 kt
Best rate of climb (SL): 831 fpm
Service ceiling: 16,200 ft
Takeoff over 50-ft. obstacle: 1600 ft
Landing over 50-ft. obstacle: 1520 ft
PA28R-200 Arrow II
Engine: Lycoming IO-360-C1C, 200 hp
Wingspan: 32 ft 0 in / 9.75 m
Length: 24 ft 7.25 in / 7.50 m
Empty weight: 1517 lb / 688 kg
MTOW: 2650 lb / 1202 kg
Useful load: 1133 lb
Equipped payload (750 miles fuel, 75 % power): 730 lb
Cruise (75% pwr): 165 mph / 143 kt / 266 kph
Stall speed (Vso): 64 mph
ROC: 900 fpm / 274 m/min
Service ceiling: 15,000 ft / 4575 m
Range (max fuel, 75% pwr): 740 sm / 642 nm / 1191 km
Seats: 4
Baggage capacity: 200 lb / 90.7 kg
Cabin width (elbow to elbow): 42.0in
PA28R-201 Arrow III
Engine: Lycoming IO 360 C1C6, 200 hp
TBO: 1,600 hr
Prop: constant speed, two blade, 74 in dia
Length: 27 ft
Height: 8 ft 3 in
Wingspan: 35 ft 5 in
Wing area: 170 sq.ft
Max ramp wt: 2,750 lb
Max takeoff wt: 2,750 lb
Std empty wt: 1,627 lb
Max useful load: 1,123 lb
Max landing wt: 2,750 lb
Wing loading: 16.2 lb/sq.ft
Power loading: 13.7 lb/hp
Max usable fuel: 72 USG/432 lb
Max ROC @ SL: 831 fpm
Max ROC @ 8,000 ft: 480 fpm
Max operating alt: 17,000 ft
Max speed: 152 kt
Max cruise, 75 % power (2,400 rpm) at 6,500 ft: 143 kt
Cruise, 65 % pwr at 8,000 ft: 131 kt
Fuel flow 65 % pwr: 9.2 USG/hr
Endurance at 65 % pwr, no res: 7.5 hr
Econ cruise, 55% power at 13,000 ft: 122 kt
Duration at max cruise: 6.7 hr
Duration at econ cruise: 8.5 hr
Stalling speed, clean: 60 kt
Stalling speed, flaps dn: 55 kt
Turbulent air penetration speed: 121 kt.
PA28R-201 Turbo Arrow III
Engine: Continental TSIO 360 E, 200 hp
TBO: 1,400 hr
Propeller: Hartzell Constant speed, 76 in. diameter
Length: 25 ft
Height: 7 ft. 10 in
Wingspan: 35 ft. 5 in
Airfoil: NACA 652415
Aspect ratio: 7.21
Wing area: 170 sq.ft
Wing loading: 17.1 lb/sq.ft
Power loading: 14.5 lb/hp
Seats: 4
Gross weight: 2,900 lbs
Empty weight: 1,910 lb
Useful load: 990 lb
Payload with full fuel: 528 lb
Fuel capacity: 77 USG/462 lbs
Baggage area: 24 cu.ft
Baggage capacity: 200 lb
Minimum runway requirement: 1,620 ft
Rate of climb: 940 fpm
Service ceiling: 20,000 ft
Maximum level speed: 178 knots
Maximum cruise (75 % @ 18,800 ft.): 172 knots
Economy cruise (55 % @ 20,000 ft.): 154 knots
Range @. maximum cruise (45 min res): 675 nm
Range @ economy cruise (45 min res): 860 nm
Duration @ maximum cruise (no res): 6.5 hr
Duration @.economy cruise (no res): 8.3 hr
Maneuvering speed: 121 knots
Stall speed (clean): 63 knots
Stall speed (gear, flaps down): 58 knots
Engine: Continental TSIO 360 F, 200 hp
TBO: 1,400 hr
Prop: two blade, constant speed, 76 inch diameter
Length: 24 ft. 8in
Height: 7 ft. 10 in
Wingspan: 35 ft. 5 in
Wing area: 170 sq.ft
Wing loading: 17 lb/sq.ft
Power loading: 14.5 lb/hp
Seats: 4
Empty weight: 1,815 lb
Useful load: 1,085 lb
Payload with full fuel: 653 lb
Gross weight: 2,900 lb
Usable fuel capacity: 72 USG/432 lb
Maximum rate of climb: 940 fpm
Service ceiling: 20,000 ft
Maximum speed: 178 kt
Max cruise, 75% power (2,575 rpm) at 19,000 ft: 172 kt
Econ cruise, 55 % power at 20,000 ft: 154 kt
Duration at max cruise: 6.2 hr
Duration at econ cruise: 8.1 hr
Stalling speed, clean: 63 kt
Stalling speed, full flaps: 57 kt
Piper PA-28RT-201T Turbo Arrow
Engine: 1 x Teledyne Continental TSIO-360-FB, 149kW
TBO: 1800 hours / 6 Years
Propeller: HARTZELL PHC-C3YF-1RF
Max take-off weight: 1315 kg / 2899 lb
Empty weight: 767 kg / 1691 lb
Wingspan: 10.8 m / 35 ft 5 in
Length: 8.33 m / 27 ft 4 in
Height: 2.52 m / 8 ft 3 in
Wing area: 15.79 sq.m / 169.96 sq ft
Max. speed: 330 km/h / 205 mph
Ceiling: 6095 m / 20000 ft
Range: 1665 km / 1035 miles
Piper 1978 PA-28R-201T Turbo Arrow III
Engine: Continental TSIO-360F, 200 hp
TBO: 1400 hr
Propeller: Const. spd.
Landing: Tri/Retr.
Gross weight: 2900 lb
Empty weight, std.: 1663 lb
Useful load, std: 1237 lb
Fuel: 72 Usgal
Wingspan: 35 ft
Overall length: 25 ft
Height: 8 ft
Wing area: 170 sq. ft
Seating capacity: 4
Cabin width: 41.5 in
Cabin height: 49 in
Baggage capacity: 200 lb
Cruise speed 75% power: 172kt
Cruise speed 65% power: 167 kt
Max range (w/ res) 75% power: 760 nm
Max range (w/ res) 65% power: 830 nm
Fuel consumption 75% power: 12 USgph
Fuel consumption 65% power: 10.8 USgph
Stall speed (gear, flaps down): 57.5 kt
Best rate of climb: 940 fpm
Service ceiling: 20,000 ft
Takeoff ground roll: 1110 ft
Landing ground roll: 645 ft
PA28R-201 Arrow IV
Engine: 1 x Lycoming IO-360-C1C6, 200 hp
TBO: 1600 hr
Prop: Hartzell 2 blade, constant speed 76 in
Seats: 4
Length: 27 ft
Height: 8.3 ft
Wingspan: 35.4 ft
Wing area: 170 sq.ft
Wing aspect ratio: 7.2
Max ramp wt: 2750 lb
Max take off wt: 2750 lb
Standard empty wt: 1637 lb
Max useful load: 1113 lb
Max landing wt: 2750 lb
Wing loading: 16.2 lbs/sq.ft
Power loading: 13.8 lbs/hp
Max useable fuel: 432 lb
Climb rate: 831 fpm @ 87 kt
Climb gradient: 573 ft/nm
Rate of climb @ 8000 ft: 440 fpm
Service ceiling; 17,000 ft
Max speed: 149 kts
Cruise @ 65% power @ 8,000ft: 131 kt
Fuel flow @ 65% power @ 8,000ft: 58 pph
Endurance @ 65% power @ 8,000ft: 7.2 hr
Stalling speed clean: 58 kt
Stall speed flaps/gear down: 53 kt
Turbulent air penetration speed: 121 kt
Retractable undercarriage
2005 New Piper Arrow IV
Base price: $292,400
Engine: Lycoming IO-360-C1C6, 200 hp
TBO: 2000 hr
Fuel type: 100/100LL
Propeller type: McCauley CS
Landing gear: Tri./Retr
Max ramp weight: 2758 lb
Gross weight: 2750 lb
Landing weight: 2750 lb
Empty weight, std: 1787 lb
Useful load, std: 971 lb
Usable fuel, std: 72 USG
Payload, full std. fuel: 539 lb
Oil capacity: 8 qt
Wingspan: 35 ft. 5 in
Overall length: 24 ft. 8 in
Height: 7 ft. 10 in
Wing area: 170 sq. ft
Wing loading: 16.2 lbs./sq.ft
Power loading: 13.8 lbs./hp
Wheel size: 6.00 x 6
Seating capacity: 4
Cabin doors: 1
Cabin width: 41 in
Cabin height: 45 in
Cruise speed, 75%: 137 kt
Fuel consumption, 75%: 10.6 USgph
Vso: 53 kt
Max range, 55%: 880 nm
Best rate of climb, SL: 831 fpm
Service ceiling: 16,200 ft
Takeoff over 50-ft obstacle: 1600 ft
Landing over 50-ft. obstacle: 1520 ft
PA28RT-201T Turbo Arrow IV
First built: 1978
Engine: 1 x Continental TSIO-360-FB, 200 hp
TBO: 1800 hrs
Fuel; 100 Octane.
Prop: Hartzell 2 blade, constant speed 76 in
Seats: 4
Length: 27.3 ft
Height: 8.3 ft
Wingspan: 35.4 ft
Wing area: 170 sq.ft
Wing aspect ratio: 7.2
Max ramp wt: 2912 lb
Max take off wt: 2900 lb
Standard empty wt: 1896 lb
Max useful load: 1004 lb
Payload (Full std Fuel); 497 lb
Baggage Capacity; 200 lbs / 24 cu.ft.
Max landing wt: 2900 lb
Wing loading: 17 lbs/sq.ft
Power loading: 14.5 lbs/hp
Fuel Capacity (std); 77 US gal
Usable Fuel; 72 US gals. / 432 lb
Climb rate: 940 fpm @ 97 kt
Climb gradient: 581 ft/nm
Rate of climb @ 8000 ft: 850 fpm
Certificated ceiling; 20,000 ft
Max speed: 178 kt
Cruise @ 65% power @ 8,000ft: 140 kts
Cruise @ 65% power @ 18,000ft: 161 kts
Cruise Best Economy Power 75% 19,000 ft: 168 kts
Cruise Best Economy Power 65% 20,000 ft: 164 kts
Cruise Best Economy Power 55% 20,000 ft: 152 kts
Max Range 55% pwr (with res, best economy); 780 nm
Max Range 65% pwr (with res, best economy); 830 nm
Max Range 55% pwr (with res, best economy); 860 nm
Fuel Consumption 75%: 14.0 US Gal/hr
Fuel Consumption 65%: 12.7 US Gal/hr
Fuel Consumption 55%: 11.0 US Gal/hr
Fuel flow @ 65% power @ 18,000ft: 76 pph
Endurance @ 65% power @ 18,000ft: 5.5 hr
Stalling speed clean: 66 kts
Stall speed flaps/gear down: 61 kt
Turbulent air penetration speed: 121 kt
Retractable undercarriage
Wheel base; 7 ft 10 in
Wheel Track; 10 ft 6 in
Wheel Size; 6.00 x 6 in
Cabin Doors; 1
Cabin Width; 42 in
Cabin Height; 46 in
Take-off Ground Roll; 1110 ft
Take-off Over 50ft; 1620 ft
Landing Ground Roll; 645 ft
Landing over 50 ft; 1555 ft
The original concept of a modem, metal, low wing replacement for the high wing, fabric Tri Pacer came from Fred Weick but it was left to John Thorp to design the PA-28.
Piper first flew the prototype of the four-seat Piper PA-28-150 Cherokee sporting/training monoplane on 14 January 1960. The type started life as a cantilever low-wing monoplane of all-metal construction with fixed tricycle landing gear and four-seat accommodation in an enclosed cabin, with power provided by a 150 hp / 112kW Avco Lycoming O-320.
The first production Cherokee was flown on 10 February 1961 (TC 2A13), and the type was available from the beginning in Standard, Custom, Super Custom and AutoFlite models, and a scheme of optional models. 6,442 of the -140 and -140-4 Cherokee were built.
Initial Cherokees were either 150 hp or 160 hp models, with the 160 hp / 119kW O-320-B2B in the PA-28-160 Cherokee.
There are few Cherokee 150s around, since Piper produced only 300 of them. Without a contender in the trainer arena, the solution was a de-rated Cherokee 150. A change of propeller pitch converted it from a 150 hp, 2,700rpm family machine into a 140 hp, 2,450 rpm trainer. The rear seats were removed, and the list price was lowered from $13,700 to $10,700. Thus, the Cherokee 140 was born.
But Piper soon discovered that a substantial number of customers liked the idea of being able to carry two additional passengers. Beginning with the 1965 model, the company returned the 140’s prop pitch to 2,700 rpm and its horsepower to 150, and installed a pair of detachable rear seats. The new airplane, basically a Cherokee 150, was called the 140 4.
As a two place aircraft, the 140 has a maximum gross weight of 1,950 pounds and is licensed in the utility category, which means it can be spun legally. A kit is available from Piper dealers to convert a two-place 140 into a four seater, although the seats themselves were not included in the kit. The conversion includes a prop change, an increase in gross weight to 2,150 pounds and licensing in the normal category (no spins).
The more powerful 180 hp / 134kW O-320-A2A engine model was introduced in 1962 as the Cherokee B. The lower powered models were phased out in 1967 and the Cherokee 180 D made up the middle of the Cherokee range from then on.
Piper launched a new assault on the 150 in 1971 with the Flite Liner, a bare bones Cherokee 140. Out went the frills and most of the options. Instead of 100 hour inspections, the company recommended a progressive maintenance program, which was supposed to halve hourly shop expenses and greatly reduce out of service time. “Instructional cruise” at 60 percent power, Piper said, would further lower operating costs, with little effect on performance, and it marked the appropriate settings on the power pedestal and tachometer. These measures did indeed result in a more economical competitor that cost $2,300 less to buy then the previous model Cherokee 140. Still, the Flite Liner, and other Cherokee 140 models, never caught up with the Cessna’s popularity.
Top of the range was the Cherokee 235 hp version which offered a much better performance and actually had a larger wing than the other models. First flown on 9 May 1962, all told 2822 of these higher-powered Cherokees were built, including 1383 -235 Charger, 712 of the 5 inch longer -235 Charger (re-named Pathfinder in 1974), and 78 of the 235D. The 1963 PA-28-235 had structural strengthening and installation of a 175kW Avco Lycoming O-540-B2B5 flat-six engine for operation at a higher gross weight.
In 1964 Piper introduced the cheap trainer version known as the Cherokee 140 with the 104kW O-320-A2B. 10,089 Cherokee 140s 150s and 160s were sold from 1964 to 1977.
With introduction of the PA-28-180R Cherokee Arrow on 19 June 1967 came a significant change, with retractable tricycle landing gear, fuel-injection engine and a constant-speed propeller as standard; at this time production of the PA-28-150 and PA-28-160 versions came to an end.
In 1971 new models of the PA-28-140 appeared as the Cherokee Flite Liner, a two-seat trainer for use by Piper-sponsored training schools, and the Cherokee Cruiser 2 Plus 2, which was a de luxe two/four-seat version which in the following year became the standard production model. For 1973 the long-standing PA-28-180 was renamed as the Cherokee Challenger, with slight increases in wing span and fuselage length, and improved interior and standards of equipment; at the same time similar changes were introduced on the PA-28-235 which was renamed as the Cherokee Charger.
In 1974 there came a number of changes in the Cherokee line, the Cherokee 2 Plus 2 being renamed Cherokee Cruiser, the Cherokee Challenger the Cherokee Archer, and the PA-28-235 the Cherokee Pathfinder.
In 1974 the PA-28-151 Cherokee Warrior (160 hp / 112kW O-320-E3D) and PA-28-181 Cherokee Archer (180 hp) models were introduced. They had an entirely new wing with tapered outer wing sections and the lower powered Warrior had the lengthened fuselage of the Archer 180 as well. The max fuel payload of the Archer was increased by 105 pounds. By the Spring of 1974 99 production Warrior had been built.
In 1977 Piper ended production of the Cherokee Cruiser and Cherokee Pathfinder, but introduced at the same time the PA-28-236 Dakota which, generally similar to the Archer, was powered by the 175kW O-540-J3A5D flat-six engine and had the new wing of increased span.
New from Piper in 1978 was the Dakota (a Cherokee 235 with a Warrior wing and other improvements). A 235-hp single-engine workhorse that should give the Cessna Skylane some direct competition, replacing the Cherokee 235 in 1979. The Dakota is 11 inches longer than the Archer II, and all of the added length is for¬ward of the firewall. The Lycoming six cylin¬der powerplant takes most of the extra space, with some of the space reserved for the enlarged spinner required for the Hart¬zell constant speed propeller. Standard price 1979: $39,910. A total of 851 were built.
In 1978 a version of this aircraft with a 149kW Continental TSIO-360-FB turbocharged engine became available as the PA-28-201T Turbo Dakota, but only limited demand meant that its production ended in 1980.
Production of the Cherokee family continued in the 1980s with the introduction of the PA-28-161 Warrior II with a 119kW Avco Lycoming O-320-D3G engine, alongside the PA-28-181 Archer II with a 134kW Avco Lycoming O-360-A4M. At the higher performance end of the scale the PA-28RT-201T Turbo Arrow IV in corporated the same powerplant as used in the Turbo Dakota. EMBRAER also continued to build aircraft under licence in Brazil. Financial problems and the crisis of product liability acted as a severe brake on sales, but a trickle of late model aircraft continue to be built. By January 1991 2,985 PA-28-161s had been sold along with 9,894 Cherokee 180/ Archers IIs, and small numbers of Arrows and Turbo Arrows.
Certification of all models is under FAA 2A13.
Embraer EMB-712 Tupi was a livence built Piper PA-28-181 Cherokee, with more than 140 units manufactured in Brazil.
The Embraer EMB-710 “Carioca” is a Piper’s Cherokee 235 Pathfinder produced in Brazil by Embraer and later by its subsidiary Neiva, under license from Piper Aircraft during 1975 – 1983. A total of 288 were manufactured.
Equipped with a semi-tapered wing, the single – engine EMB-710 Carioca can reach the speed of 237 km / h with its engine Lycoming of 235 HP (175 kW).
In July 1964, Sorenson Aircraft Co, Washington, Minnesota, was marketing a spray rig for all Cherokee models. A fibreglass belly tank was on the centre of gravity, holding 110 USG. The ag unit applied a swath width of up to 45 ft. Cost varied with a variety of pumps and nozzles from US$945-1339.
In 1964 Federal Ski & Engineering, Minneapolis, received FAA approval for aircraft skis to replace wheels on new PA-28-180s and 28-235 Cherokees.
1965 Cherokee PA28-140
Engine make/model: Lycoming O320-E2A, 150 hp @2700 rpm
TBO: 2000 hr
Fuel type: 100/100LL
Propeller: Sensenich Fixed / 74 in
Landing: Tri/Fixed
Max ramp weight: 2150 lb
Gross weight: 2150 lb
Landing weight: 2150 lb
Empty weight, std: 1230 lb
Useful load, std: 920 lb
Payload, full std. fuel: 632 lb
Usable fuel: 48 USgal
Oil capacity: 8 qt
Wingspan: 30 ft
Overall length: 23 ft. 3 in
Height: 7 ft. 3 in
Wing area:160 sq. ft
Wing loading: 13.4 lbs./sq. ft
Power loading: 14.3 lbs./hp
Wheel base: 6 ft. 2 in
Wheel track: 10 ft
Wheel size: 6.00 x 6 in
Seating capacity: 2+2
Cabin doors: 1
Cabin width: 42 in
Baggage capacity: 200 lb
Cruise speed 75% power @ 7,800 ft: 115 kt
Cruise speed 65% power @ 10,200 ft: 108 kt
Cruise speed 55% power @ 12,000 ft: 102 kt
Max range (w/ reserve) 75% power: 470 nm
Max range (w/ reserve) 65% power: 522 nm
Max range (w/ reserve) 55% power: 583 nm
Fuel consumption 75% power: 8.4 USgph
Fuel consumption 65% power: 7.3 USgph
Fuel consumption 55% power: 6.2 USgph
Stall speed (flaps up): 52 kt
Stall speed (flaps down):48 kt
Best rate of climb (SL): 660 fpm
Best rate of climb, 8000ft: 350 fpm
Service ceiling (ft.): 14,300
Takeoff ground roll: 800 ft
Takeoff over 50-ft. obstacle: 1700 ft
Landing ground roll: 495 ft
Landing over 50-ft. obstacle: 850 ft
PA28-140 Cruiser
Engine: 1 x Lycoming O-320-E3D, 150 hp
Prop: 6 ft 2 in (1.88 m) dia 2 blade
Wing span: 30 ft 0 in (9.14 m)
Length: 23 ft 6 in (7.16 m)
Wing area: 160 sq ft (14.86 sq.m)
Seats: 2/4
Wing loading: 13.4 lb/sq.ft
Pwr loading: 14.3 lb/hp
Gross wt: 2150 lb (975 kg)
Empty wt: 1275 lb
Equipped useful load: 834 lb
Payload max fuel: 546 lb
Range max fuel/75% pwr: 597nm/5hr
Range max fuel / 55% pwr: 702 nm/ 7 hr
Service ceiling: 10,950 ft
Max cruising speed: 133 mph (214 kph) at 7,000 ft (2,135 m)
75% cruise: 118 kt
55% cruise: 101 kt
Stall: 41-49 kt
1.3 Vso: 53 kt
ROC: 631 fpm
Min field length: 1700 ft
Fuel cap: 288 lb
PA-28-140 Flightliner
PA-28-150 Cherokee B
Engine: 150hp Lycoming O-320E
Wingspan: 30’0″
Length: 23’4″
Useful load: 830 lb
Max speed: 142 mph
Cruise: 133 mph
Stall: 54 mph
Range: 535 mi
Ceiling: 14,300′.
PA-28-150 Cherokee C
1961-67
Engine: 150hp Lycoming O-320E
Wingspan: 30’0″
Length: 23’4″
Useful load: 830 lb
Max speed: 142 mph
Cruise: 133 mph
Stall: 54 mph
Range: 535 mi
Ceiling: 14,300′.
1900 built
PA-28-150 Cherokee
Engine: 150hp Lycoming O-320-A2A
300 built
PA-28-160 Cherokee C
1970
Engine: 160hp Lycoming O-320-D2A
810 built
PA28-151 Warrior
Engine: 1 x Lycoming O-320-E3D, 150 hp
Wingspan: 35 ft 0 in / 10.67 m
Length: 23 ft 10 in / 7.26 m
Wing loading: 13.7 lb/sq.ft
Pwr loading: 15.5 lb/hp
MTOW: 2325 lb / 1054 kg
Empty wt: 1301 lb / 590 kg
Equipped useful load: 882 lb
Payload max fuel: 594 lb
Fuel cap: 288 lb
Range max fuel/75% pwr: 583nm / 5hr
Range max fuel / 55% pwr: 667 nm/ 7 hr
Service ceiling: 12,700 ft / 3870 m
75% cruise: 115 kt
55% cruise: 96 kt
Stall: 44-51 kt
1.3 Vso: 57 kt
ROC: 649 fpm / 198 m/min
Min field length: 1760 ft
Seats: 4
Cabin length: 9 ft 0 in / 2.74 m
Cabin width: 3 ft 6 in / 1.07 m
Cabin height: 4 ft 0 in / 1.22 m
Cabin volume: 92 cu.ft / 2.61 cu.m
Baggage compartment: 15 cu ft / 0.42 cu.m
PA28-161 Warrior II
First built: 1973
Engine: 1 x Lycoming O-320-D3G, 160 hp
Fuel: 100 Octane
TBO: 2000 hrs
Prop: Sensenich 2 blade, fixed pitch 74 in DM-0-60
Seats: 4
Length: 23.8 ft
Height: 7.3 ft
Wingspan: 35 ft
Wing area: 170 sq.ft
Wing aspect ratio: 7.2
Max ramp wt: 2325 lb
Max take off wt: 2325 lb
Standard empty wt: 1348 lb
Max useful load: 977 lb
Max landing wt: 2325 lb
Wing loading: 13.7 lbs/sq.ft
Power loading: 14.5 lbs/hp
Max useable fuel: 48 USG / 288 lb
Climb rate: 710 fpm @ 75 kt
Climb gradient: 568 ft/nm
Rate of climb @ 8000 ft: 338 fpm
Best angle of climb: 63 kt
Service ceiling; 13,000 ft
Max level speed: 127 kt
Never exceed speed: 160 kt
Cruise speed 75% pwr 9000 ft Best pwr: 127kts
Cruise speed 75% pwr 9000 ft Best econ: 123kts
Cruise speed 65% pwr 12,500 ft Best pwr: 118kts
Cruise speed 65% pwr 12,500 ft Best econ: 116kts
Cruise speed 55% pwr 12,500 ft Best pwr: 107kts
Cruise speed 55% pwr 12,500 ft Best econ: 103kts
Max range (with 45 min res) 75% pwr 9000 ft Best pwr: 525nm
Max range (with 45 min res) 75% pwr 9000 ft Best econ: 590nm
Max range (with 45 min res) 65% pwr 12,500 ft Best pwr: 553nm
Max range (with 45 min res) 65% pwr 12,500 ft Best econ: 633nm
Max range (with 45 min res) 55% pwr 12,500 ft: Best pwr 565nm
Max range (with 45 min res) 55% pwr 12,500 ft Best econ: 640nm
Fuel consumption 75% pwr 9000 ft Best pwr: 10.0 US Gal/hr
Fuel consumption 75% pwr 9000 ft Best econ: 8.5 US Gal/hr
Fuel consumption 75% pwr 9000 ft Best pwr: 10.0 US Gal/hr
Fuel consumption 65% pwr 12,500 ft Best econ: 7.5 US Gal/hr
Fuel consumption 55% pwr 12,500 ft Best pwr: 7.8 US Gal/hr
Fuel consumption 55% pwr 12,500 ft Best econ: 6.6 US Gal/hr
Endurance @ 65% power @ 8,000ft: 6.1 hr
Stalling speed clean: 56 kts
Stall speed flaps down: 50 kts
Turbulent air penetration speed: 108 kt
Take-off ground run: 975 ft
Take-off over 50 ft obstacle: 1490 ft
Landing ground roll: 595 ft
Landing over ft obstacle: 1115 ft
Fixed undercarriage
Wheel base: 6 ft 8 in
Wheel track. 10 ft
Wheel size mains: 6.00×6 / nose 5.00×5
Cabin doors: 1
Cabin length: 97 in
Cabin width: 41.5 in
Cabin height: 49 in
Baggage capacity: 200 lbs / 24 cu.ft
Trims: Elevator/ Rudder
PA28-161 Warrior III
Engine: Lycoming O-320-D3G, 160 hp
Length: 23.786 ft / 7.25 m
Height: 7.316 ft / 2.23 m
Wingspan: 35.007 ft / 10.67 m
Wing area: 169.964 sq.ft / 15.79 sq.m
Max take off weight: 2447.6 lb / 1110.0 kg
Weight empty: 1490.6 lb / 676.0 kg
Max. payload weight: 957.0 lb / 434.0 kg
Wing loading: 14.35 lb/sq.ft / 70.0 kg/sq.m
Max speed: 127 kts / 235 km/h
Max cruising speed: 126 kts / 233 km/h
Cruise: 115 kt
Service ceiling: 11,000 ft / 3353 m
Endurance: 5.8 hr
Landing speed: 44 kts / 82 km/h
Take off distance: 1650 ft / 503 m
Landing distance: 1161 ft / 354 m
Range: 520 nm / 963 km
Crew: 2+2
PA-28-180 Cherokee C
1962-67
Engine: 180hp Lycoming O-360-A3A
Length: 23’6
speed: 152 mph
Range: 845 mi
No built: 1,118
PA28-181 Archer II
Engine: 1 x Lycoming O-360-A4M, 180 hp
TBO: 2000 hrs
Fuel: 100 Octane
Prop: Sensenich 2 blade, fixed pitch 76 in
Seats: 4
Length: 23.8 ft
Height: 7.3 ft
Wingspan: 35 ft
Wing area: 170 sq.ft
Wing aspect ratio: 7.2
Max ramp wt: 2550 lb
Max take off wt: 2550 lb
Standard empty wt: 1413 lb
Max useful load: 1137 lb
Payload full std fuel; 690 lb
Max landing wt: 2550 lb
Wing loading: 15 lbs/sq.ft
Power loading: 14.2 lbs/hp
Fuel Capacity std; 50 US Gal
Max useable fuel: 48 US Gals / 288 lb
Climb rate: 735 fpm @ 76 kt
Climb gradient: 580 ft/nm
Rate of climb @ 8000 ft: 370 fpm
Service ceiling; 13,650 ft
Max Level speed: 129 kt
Take-off Ground Run; 870 ft
Take-off 50 ft; 1625 ft
Landing Ground Roll; 925 ft
Landing 50 ft; 1390 ft
Cruise @ 65% power @ 8,000ft: 118 kts.
Cruise Speed 75% 8,000 ft Best Power: 129 kt /148 mph
Cruise Speed 75% 8,000 ft Best Economy: 126 kt /145 mph
Cruise Speed 65% 12,000 ft Best Power: 125 kt /143 mph
Cruise Speed 65% 12,000 ft Best Economy: 122 kt /140 mph
Cruise Speed 55% 12,500 ft Best Power: 111 kt /128 mph
Cruise Speed 55% 12,500 ft Best Economy: 107 kt /123 mph
Max Range (with res) 75% 8,000 ft Best Power: 520 nm /598 sm
Max Range (with res) 75% 8,000 ft Best Economy: 600 nm /690 sm
Max Range (with res) 65% 12,000 ft Best Power: 565 nm /650 sm
Max Range (with res) 65% 12,000 ft Best Economy: 645 nm /742 sm
Max Range (with res) 55% 12,500 ft Best Power: 580 nm /667 sm
Max Range (with res) 55% 12,500 ft Best Economy: 670 nm /771 sm
Fuel Consumption 75% Best Power: 10.5 US Gal/hr
Fuel Consumption 75% Best Economy: 8.8 US Gal/hr
Fuel Consumption 65% Best Power: 9.0 US Gal/hr
Fuel Consumption 65% Best Economy: 7.6 US Gal/hr
Fuel Consumption 55% Best Power: 7.8 US Gal/hr
Fuel Consumption 55% Best Economy: 6.3 US Gal/hr
Fuel flow @ 65% power @ 8,000ft: 46 pph
Endurance @ 65% power @ 8,000ft: 6 hr
Stalling speed clean: 59 kts
Stall speed flaps down: 53 kts
Turbulent air penetration speed: 111 kts
Fixed undercarriage
Wheel base; 6.6 ft
Wheel Track; 10.0 ft
Wheel Size; 6.00 x 6
Cabin Doors; 1
Cabin Length; 97 in
Cabin Width; 41.5 in
Cabin Height; 49 in
Baggage Capacity; 200 lbs / 26 cu ft
Trim; Elevator / Rudder
1978 Piper PA-28-181 Archer II
Engine: Lycoming O-360-A4M, 180 hp @ 2700 rpm
TBO: 2000 hr
Fuel type: 100LL
Propeller: Sensenich metal, FP/76 in
Landing gear: Tri./Fixed
Max ramp weight: 2550 lb
Gross weight: 2550 lb
Landing weight: 2550 lb
Empty weight, std: 1416 lb
Useful load, std: 1134 lb
Payload, full std. fuel: 637.5 lb
Useful fuel, std: 48 USG
Oil capacity: 8 qt
Wingspan: 35 ft. 5 in.
Overall length: 24 ft.
Height: 7 ft. 3 in
Wing area: 170 sq. ft
Wing loading: 15 lb/sq. ft
Power loading: 14.2 lbs./hp
Wheel size: 6 ft. 7 in
Seating capacity: 4
Cabin doors: 1
Baggage capacity: 200 lb
Cruise speed 75% power: 125kt
Cruise speed 65% power: 116 kt
Cruise speed 55% power: 102 kt
Range (w/ res) 75% power: 565 nm
Range (w/ res) 65% power: 600 nm
Range (w/ res) 55% power: 670 nm
Fuel consumption 75% power: 10.5 USgph
Fuel consumption 65% power: 9.0 USgph
Fuel consumption 55% power: 7.8 USgph
Vs: 55 kt
Vso: 49 kt
Best rate of climb: 667 fpm
Best rate of climb, 8,000 ft: 280 fpm
Service ceiling: 13,236 ft
Takeoff ground roll: 870 ft
Takeoff over 50-ft. obstacle: 1210 ft
Landing ground roll: 925 ft
Landing over 50-ft. obstacle: 1390 ft
PA28-181 Archer III
Engine: Lycoming IO-360-A4M, 180 hp
TBO: 2000 hr
Fuel type: 100/100LL
Propeller: Sensenich FP
Landing gear: Tri/Fixed
Max ramp weight: 2558 lb
Gross weight: 2550 lb
Landing weight: 2550 lb
Empty weight, std: 1703 lb
Zero fuel wt: 2364 lb
Useful load, std: 847 lb
Payload, full std. fuel: 559 lb
Usable fuel: 48 USG
Fuel cap: 194 lbs
Oil capacity: 8 qt
Wingspan: 25 ft. 6 in
Overall length: 24 ft
Height: 7 ft. 4 in
Wing area: 171.8 sq. ft
Wing loading: 14.8 lbs./sq. ft
Power loading: 14.2 lbs./hp
Wheel base: 6 ft. 7 in
Wheel track: 10 ft
Wheel size: 6.00 x 6
Seating capacity: 4
Cabin doors: 1
Cabin width: 42 in
Cabin height: 45 in
Baggage capacity: 200 lb /26 cu. ft
Cruise speed 75% power @ 7,900 ft: 128 kt
Cruise speed 65% power @ 12,000 ft: 125 kt
Cruise speed 55% power @ 12,500 ft: 111 kt
Max range (w/ res) 75% power: 444 nm
Max range (w/ res) 65% power: 487 nm
Max range (w/ res) 55% power: 522 nm
Fuel consumption 75% power: 10.0 USgph
Fuel consumption 65% power: 8.6 USgph
Fuel consumption 55% power: 7.3 USgph
Endurance: 5.7 hr
Vs: 46 kt
Vso: 45 kt
Best rate of climb (SL): 667 fpm
Service ceiling: 13,240 ft
Takeoff ground roll: 1135 ft
Takeoff over 50-ft. obstacle: 1608 ft
Landing ground roll: 920 ft
Landing over 50-ft. obstacle: 1400 ft
PA28-235 Pathfinder
Engine: 1 x Lycoming O-540-B4B5, 235 hp
TBO: 2000 hr
Fuel type: 100/100LL
Propeller: Hartzell CS
Landing gear type: Tri/Fixed
Wingspan: 32 ft
Overall length: 24 ft
Height: 7 ft. 10 in
Wing area:170 sq. ft
Seats: 4
Pwr loading: 12.8 lb/hp
MTOW: 3000 lb
Empty wt: 1565 lb
Max ramp weight: 3000 lb
Landing weight: 3000 lb
Equipped useful load: 1359 lb
Payload max fuel: 867 lb
Wing loading: 17.6 lb/sq.ft
Wheel size: 6.00 x 6
Cabin doors: 1
Cabin width: 44 in
Cabin height: 47 in
Baggage capacity: 200 lb
Range max fuel/75% pwr: 748nm/5.6hr
Range max fuel / 55% pwr: 930 nm/ 7.8 hr
Service ceiling: 13,550 ft
75% cruise: 133 kt
55% cruise: 120 kt
Stall: 53-57 kt
1.3 Vso: 69 kt
ROC: 800 fpm
Takeoff ground roll: 850 ft
Takeoff over 50-ft. obstacle: 1410 ft
Landing ground roll: 1040 ft
Landing over 50-ft. obstacle: 1740 ft
Min field length: 1740 ft.
Fuel cap: 492 lb / 82 USG
Oil capacity: 12qt
PA28-235 Charger
Useful load: 1340 lbs
Cruise @ 75% pwr: 130 kts
Fuel cap: 319 lt
Seats: 5
1968 Piper Cherokee 235C
Engine: Lycoming O-540-B4B5, 235 hp
TBO: 2000 hr
Fuel type: 100/100LL
Propeller: Hartzell CS
Landing: Tri/Fixed
Max ramp weight: 2900 lb
Gross weight: 2900 lb
Landing weight: 2900 lb
Empty weight, std: 1467 lb
Useful load, std: 1433 lb
Payload, full std. fuel: 929 lb
Usable fuel, std: 84 USG
Oil capacity: 12 qt
Wingspan: 32 ft
Overall length: 23 ft. 9 in
Height: 7 ft. 1 in
Wing area: 171.6 sq. ft
Wing loading: 17 lbs./sq. ft
Power loading: 12.4 lbs./hp
Wheel size: 6.00 x 6
Seating capacity: 4
Cabin doors: 1
Cabin width: 44 in
Cabin height: 47 in
Baggage capacity: 200 lb
Cruise speed 75% power @ 8,000 ft: 136 kt
Cruise speed 65% power @ 8,000 ft: 130 kt
Cruise speed 55% power @ 8,000 ft: 122 kt
Stall speed (flaps up): 57 kt
Stall speed (flaps down): 52 kt
Best rate of climb (SL): 825 fpm
Service ceiling: 14,500 ft
Takeoff ground roll: 800 ft
Takeoff over 50-ft. obstacle: 1360 ft
Landing ground roll: 680 ft
Landing over 50-ft. obstacle: 1300 ft
PA28-235D
1970
PA28-235E
1971
PA28-236 Dakota
First built: 1978
Engine: 1 x Lycoming O-540-J3A5D, 235 hp
TBO: 2000 hrs
Prop: Hartzell 2 blade, constant speed 80 in
Seats: 4
Length: 25 ft / 7.52 m
Height: 7.4 ft / 2.18 m
Wingspan: 35 ft / 10.8 m
Wing area: 170 sq.ft / 15.79 sq.m
Wing aspect ratio: 7.2
Max ramp wt: 3000 lb / 1361.0 kg
Max take off wt: 3000 lb/ 1361.0 kg
Standard empty wt: 1608 lb / 730.0 kg
Max useful load: 1392 lb
Max landing wt: 3000 lb
Wing loading: 17.6 lbs/sq.ft
Power loading: 12.8 lbs/hp
Max useable fuel: 432 lb
Climb rate: 1110 fpm @ 85 kt
Climb gradient: 784 ft/nm
Rate of climb @ 8000 ft: 550 fpm
Service ceiling; 17,500 ft / 5334 m
Max speed: 148 kt / 274 km/h
Cruise @ 65% power @ 8,000ft: 137 kt
Fuel flow @ 65% power @ 8,000ft: 65 pph
Endurance @ 65% power @ 8,000ft: 6.3 hr
Range: 750 nm / 1389 km
Stalling speed clean: 63 kts
Stall speed flaps down: 56 kt
Turbulent air penetration speed: 122 kt
Fixed undercarriage
Take off distance: 1217 ft / 371 m
Landing distance: 1726 ft / 526 m
Landing speed: 56 kts / 104 km/h
Piper 1979 PA-28-201T Turbo Dakota
Engine: Continental TSIO 360 FB, 200 hp
TBO: 1,800 hrs
Prop: two blade, constant speed, 76 in. dia
Length: 25 ft
Height: 7 ft 7 in
Wingspan: 35 ft. 5 in
Wing area: 170 sq.ft
Max ramp wt: 2,900 lb
Max takeoff wt: 2,900 lb
Standard empty wt: 1,563 lb
Max useful load: 1,337 lbs
Max landing wt: 12,900 lb
Baggage capacity: 200lb
Wing loading: 17 lbs. per sq.ft
Power loading: 14.5 lb/hp
Max usable fuel: 72 USG/432 lb
Max rate of climb, sea level: 880 fpm
Max rate of climb, 8,000 ft: 820 fpm
Max operating altitude: 20,000 ft
Max speed (15,000): 162 kts
Cruise, 65% power at 8,000 ft: 132 kt
Cruise, 65% power at 18,000 ft: 148 kt
Max range (w/ res) 75% power: 729 nm
Max range (w/ res) 65% power: 766 nm
Fuel consumption 75% power: 12.0 US gph
Fuel flow at 65% power: 10.8 USG/hr
Endurance at 65% power, no res: 7 hrs
Stalling speed, clean: 67 kt
Stalling speed, flaps down: 59 kt
Turbulent air penetration speed: 122 kt
Seats: 4
U/C: fixed.
Cabin width: 42 in
Cabin height: 49 in
Takeoff ground roll: 963 ft
Landing ground roll: 861 ft
Avcon Cherokee 140 / 180
Engines: 1 x Lycoming O-360-A1A, 180 hp
Seats: 4
Wing loading: 12.9 lb/sq.ft
Pwr loading: 12.2 lb/hp
Max TO wt: 2200 lb
Empty wt: 1367 lb
Equipped useful load: 768 lb
Payload max fuel: 468 lb
Range max fuel/ 75% cruise: 592 nm/4.4 hr
Service ceiling: 17,300 ft
75% cruise: 116 kt
Stall: 48-54 kt
1.3 Vso: 62 kt
ROC: 950 fpm
Min field length: 550 ft
Fuel cap: 300 lb
The rapid expansion of Piper’s operations in the 1950s meant that new facilities were soon required, and in 1957 the company opened a new aircraft development centre at Vero Beach, Florida, to be responsible for design, development and testing of new projects. The Vero Beach facility began its operations on a new specialised agricultural aircraft, designated Piper PA-25 Pawnee, for experience with the PA-18A configured for agricultural use had shown the active market for this category of aeroplane. Designed by Fred Weick and a development of a specialised ag-aeroplane called the AG-1, the Pawnee entered produc-tion in 1959 powered by the same 150 hp engine as in the Super Cub, Tri-Pacer and Apache.
A braced low-wing monoplane with fixed tailwheel landing gear, the PA-25 was powered initially by a 112kW Avco Lycoming O-320 flat-four engine, and this version was later redesignated PA-25-150 Pawnee. It had a glass-fibre chemical hopper installed forward of the cockpit, this having a volume of 0.57 cu.m, and the dust/spray distribution system was the same as that which had been proven on the PA-18A. Further forward of that again was a compartment for the loader driver that had a pop-up canopy. The passenger got in through the starboard side and sat in the compartment between the hopper and the firewall.
Advanced design features were intended to reduce the likelihood of an accident and to give the pilot a far better chance of survival in a crash; thus he was given a high sitting position to ensure an excellent all-round view, above average strength seat restraints, and a specially designed structure that was installed to leave the cockpit substantially undamaged in the usual type of low-speed crash associated with agricultural dusting/spraying operations.
In all, seven hundred and thirty one Pawnee 150s, plus two prototypes, were built between 1957 and 1963. To improve the 150 hp Pawnee’s performance Airwork installed the larger Lycoming 0 360 A2A engine of 180 horsepower. On the advice of Civil Aviation of New Zealand, the Pawnee fuel system was rede¬signed by Airwork and the fuel tanks situated far out in the wings. This mod proved to be excellent and no further troubles were encountered.
The 235 hp / 175kW Avco Lycoming O-540-B2B5 Pawnee with structural strengthening came on the market in 1962, including some with the more powerful 260 hp / 194kW O-540-E engine. Its hopper/ lank can carry 150 US gallons (568 litres) of liquid or 1,200 lb (544 kg) of dry chemi¬cal, and it can be changed over from dus¬ter to sprayer (or vice versa) in less than five minutes.
Some 235 hp models were converted by Airwork to have a 250 hp engine.
In 1965, Hazair at Orange modified a Pawnee 235 to incorporate side by side seating within he existing cockpit by widening the fuselage it several stations. A number of Pawnee 235s were converted in a similar fashion and other operators made comparable conversions.
The PA 25¬-235A/1 series was modified by widening the fuselage at the rear of the cockpit. Added to the top of the rear fuselage was the shaped turtledeck. The cockpit was fitted with dual controls and new side doors were “bulged” to provide more shoulder room. The hopper was removed and glider towing attachments and a release mecha¬nism were fitted. Air Express was responsible for the conversion and the company had the aircraft certified in 5 June 1970. VH KLA was then listed as a Piper PA 25 180A/1 and was re registered to the Gliding Club of Victoria and Benella, Australia.
A total of 5167 Pawnees of all types were built from 1959 to early 1982.
PA-25-150 – 731
PA-25-235 – 2,906
PA-25-260 – 251
Certification for the PA-25, 25-3 to 25-731, and all PA-25-235 was under FAA 2A10.
In 1998 Laviasa acquired from the New Piper Aircraft Company of the USA the Type Certificates (CCTT’S) No. 2 A 8 and 2 A 10 issued by the Federal Aviation Administration of the USA (FAA) in 1998 and the Certificates of Type No. AV-0004, AV-9901 and Production Certificate No. A-0801 issued by the National Civil Aviation Administration of Argentina (ANAC). These documents gave Laviasa the exclusive rights for the manufacture of PA-25-235 / 260 (formerly called “Pawnee” and renamed “Puelche”) and its parts.
Derivatives:
Gippsland Aeronautics GA-200 Fatman
Specifications:
PA25-150
Engine: Ly¬coming O-320
PA25-235
Engine: Ly¬coming O 540 B2B5, 235 hp / 175kW
Prop: 7 ft 0 in (2.13 m) dia 2 blade
Wing span: 36 ft 2 in (11.02 m)
Length: 24 ft 8.5in (7.53 m)
Height: 2.21 m / 7 ft 3 in
Wing area: 183 sq ft (17.0 sq.m)
Gross weight: 2,900 lb (1,315 kg)
Empty weight: 725 kg / 1598 lb
Max cruising speed (duster/sprayer): 100/105 mph (161/169 kph)
Max range (duster/sprayer): 255/270 miles (410/434 km)
Accommodation: Crew 1
Pawnee B
1965
Improved -235 with larger hopper
Pawnee C
1966
Engine: optional Lycoming O-540-E from 1968
Oleo shock absorbers
PA25-235D
Engines: Lycoming O-540-B2C5, 235 hp
Wing loading: 15.8 lb/sq.ft
Pwr loading: 12.3 lb/hp
Max TO wt: 2900 lb
Empty wt: 1420 lb
Equipped useful load: 1433 lb
Payload max fuel: 1202 lb
Range max fuel/ 75% pwr: 203 nm/ 2.1 hr
Service ceiling: 13,000 ft
Hopper cap: 150 USG
75% cruise: 99 kt
Working speed: 75 kt
Working endurance: 2.8 hr
Stall: 53 kt
ROC: 700 fpm
Min field length: 1350 ft
Fuel cap: 231 lb
Seats: 1
PA25-260 Pawnee C
Engine: 260 hp
Prop: CSU
Hopper cap: 145 USG
PA25-260D
Engines: Lycoming O-540-G1A, 260 hp
Seats: 1
Wing loading: 15.8 lb/sq.ft
Pwr loading: 11.2 lb/hp
Max TO wt: 2900 lb
Empty wt: 1472 lb
Equipped useful load: 1381 lb
Payload max fuel: 1150 lb
Range max fuel/ 75% pwr: 195 nm/ 2.0 hr
Service ceiling: 14,000 ft
Hopper cap: 150 USG
75% cruise: 100 kt
Working speed: 75 kt
Working endurance: 2.7 hr
Stall: 53 kt
ROC: 755 fpm
Min field length: 1250 ft
Fuel cap: 231 lb
On 24 May 1956 Piper flew the prototype of a new single-engine four-seat cabin monoplane that it designated initially Piper PA-24 Comanche, but which later became known as the PA-24-180 Comanche. A cantilever low-wing monoplane of all-metal construction, this very clean looking aircraft had such features as retractable tricycle landing gear, an all-moving tailplane and a 180 hp / 134kW Avco Lycoming O-360-A1A engine. The first production aircraft was flown on 21 October 1957, and from the outset it was available in four versions, the Standard with basic essential equipment, the Custom, Super Custom and AutoFlite having progressively more sophisticated equipment, the last of them introducing a two-axis autopilot.
The capability of the PA-24-180 Comanche was demonstrated by American pilot Max Conrad in establishing FAI-accredited world class distance records of 11211.83km in a straight line and 11138.72km in a closed circuit during 1959 and 1960 respectively. And flying a PA-24-250 Comanche in 1959 over a straight-line distance of 12341.26km; these records remained unbroken in 1983.
The PA-24-250 Comanche which soon supplemented the PA-24-180 (1,143 built) and while basically similar differed by having the 186kW O-540-A1A engine; this variant was built to a total of 2,537.
This was followed in 1964 by the PA-24-260 Comanche B with a 194kW version of the O-540 engine increasing performance, cleaned up landing gear, and a single-fork main gear was used. This model was used by the UK’s Sheila Scott between 18 May and 20 June 1966 to establish a new round-the-world class speed record, covering a distance of 46759km.
The pressurized Comanche design may be Piper’s most lamented failure. The sole prototype was destroyed in a freak takeoff roll accident in 1966, when the pilot got out of synch with the touchy electric nosewheel steering. But the heavy single had already run into problems meeting certification requirements that demanded a 61 knot stalling speed.
One day, Pug Piper was sitting in a friend’s 450 hp Staggerwing, and thought, ‘Gee, we can do better than this by putting a 400 Lycoming in the nose of the Comanche.’ Delayed by engine problems, the Comanche 400 went on sale just as the Twin Comanche became available for not much more money. The Interceptor 400 was a PA-24 Commanche with a six cylinder Lycoming engine built in 1964-65.
Last of the single-engine Comanches was the PA-24T-260 Turbo Comanche which introduced an IO-540 engine with a Rayjay turbo-charger to give considerably improved performance, and when production of the PA-24-260s ended in 1972 a total of 1,028 had been built, giving a Comanche grand total of 4,708. Production ended in 1972 due to the floods at Piper’s factory, Lock Haven. Certification for the PA-24, 24-2 to 24-3687 and PA-24-260, 24-4247 and 24-4300 to 24-5034, was under FAA 1A15.
A Commanche 400 owned by Garrett-AiResearch, powered by their TPE 331 turboprop engine, was flown to a new altitude record for light turboprops by company pilot Jack Womack, reaching 41,320 ft in 70 minutes.
Comanche 180
Engine: Lycoming O-360-A1A, 180 hp
TBO: 2000 hr
Fuel type: 80/87
Propeller: Hartzell CS
Landing gear: Tri/Retr.
Max ramp weight: 2550 lb
Gross weight: 2550 lb
Max landing weight:2550 lb
Empty weight: 1530 lb
Useful load: 1020 lb
Payload, full std. fuel: 660 lb
Wingspan: 36 ft. 11 in
Overall length: 24 ft. 9 in
Height: 7 ft. 4 in
Wing area:178 sq. ft
Wing loading: 14.3 lbs./sq. ft
Power loading: 14.2 lbs./hp
Wheel base: 6 ft. 7 in
Wheel track: 9 ft. 8 in
Wheel size: 6.00 x 6 in
Seating capacity: 4
Cabin doors: 1
Cabin width: 44 in
Cabin height: 45 in
Baggage capacity: 100 lb
Cruise speed 75% power @ 8,000 ft: 139 kt
Cruise speed 65% power @ 11,500 ft: 133 kt
Cruise speed 55% power @ 14,000 ft: 122 kt
Max range (w/ reserve) 75% power: 682 nm
Max range (w/ reserve) 65% power: 771 nm
Max range (w/ reserve) 55% power: 860 nm
Fuel consumption 75% power: 9.5 USgph
Fuel consumption 65% power: 8.2 USgph
Fuel consumption 55% power: 6.9 USgph
Stall speed (flaps up): 53 kt
Best rate of climb: 910 fpm
Service ceiling: 18,500 ft
Takeoff ground roll: 750 ft
Takeoff over 50-ft. obstacle: 2240 ft
Landing ground roll: 600 ft
Landing over 50-ft. obstacle: 1025 ft
1964 Piper Comanche 250 PA-24-250
Engine: Lycoming IO-540-C, 250 hp
TBO: 2000 hr
Fuel type: 100LL
Propeller: Hartzell two-blade CS / 77 in
Landing gear: Tri/Retr.
Gross weight: 2900 lb
Max landing weight: 2900 lb
Empty weight, std: 1690 lb
Useful load, std: 1210 lb
Useful load – equipped: 1073 lb
Payload, full std. fuel, 60 USgals: 850 lb
Payload – full opt. fuel, 90 gals: 670 lb
Usable fuel: 37 USgal
Oil capacity: 12 qt
Wingspan: 36 ft
Overall length: 24 ft. 10 in
Height: 7 ft. 5 in
Wing area: 178 sq. ft
Wing loading: 16.3 lbs./sq. ft
Power loading: 11.6 lbs./hp
Wheel base: 6 ft. 6 in
Wheel track: 9 ft. 10 in
Wheel size mains: 6.00 x 6 in
Wheel size nose: 6.00 x 6 in
Seating capacity: 4
Cabin doors: 1
Cabin length: 108 in
Cabin width: 45 in
Cabin height: 47 in
Baggage capacity: 200 lb /20 cu. ft
Max level speed: 165 kt /190 mph
Cruise speed 75% power: 157 kt / 181 mph
Cruise speed 65% power: 154 kt / 177 mph
Cruise speed 55% power: 142 kt /164 mph
Max. range opt. fuel, 45-min. res 75% power: 928 nm / 1068 sm
Max. range opt. fuel, 45-min. res 65% power: 1000 nm / 1151 sm
Max. range opt. fuel, 45-min. res 55% power: 1040 nm / 1197 sm
Max. range opt. fuel, 45-min. res 45% power: 1108 nm / 1275 sm
Fuel consumption 75% power: 13.7 USgph
Fuel consumption 65% power: 12.3 USgph
Fuel consumption 55% power: 11.0 USgph
Fuel consumption 45% power: 9.5 USgph
Stall speed (gear, flaps up): 61 kt / 70 mph
Stall speed (gear, flaps down): 55 kt/63 mph
Best rate of climb (SL): 1350 fpm
Service ceiling: 20,000 ft
Takeoff ground roll: 750 ft
Takeoff over 50-ft. obstacle: 1650 ft
Turbo Comanche C
Engine: Lycoming TIO 540 RIA5, 260 hp
TBO: 1,500 hrs
Prop: 77 in Hartzell constant speed
Wing span: 35 ft. 11.75in
Airfoil: NACA 642A215
Aspect ratio: 7.28:1
Wing area: 178 sq. ft
Wing loading: 18 lb/sq.ft
Seats: 6
Empty weight: 1,894 lbs
Useful load: 1,306 lbs
Payload with full opt fuel: 702 lbs
Gross weight: 3,200 lbs
Power loading: 12.3 lb/hp
Fuel capacity (std.): 60 USG
Fuel capacity (opt): 90 USG
Baggage capacity: 250 lbs
Baggage area: 20 cu.ft
Takeoff dist over 50 ft: 1,800 ft
Rate of climb: 1,320 fpm
Service ceiling: 25,000 ft
Max speed: 242 mph/210 kts
Cruise (75% @ 25,000ft): 228 mph/198 kts
Econ cruise (55% @ 25,000ft): 209 mph/182 kts
Range @ max cruise (45 min. res, opt tanks): 1,120 sm/970 nm
Range (@ econ cruise (45.min. res, opt tanks): 1,330 sm/1,155 nm
Duration @ max cruise (opt tanks): 5 hr 40 min
Stall speed (gear & flaps down): 67 mph/58 kts
Landing dist over 50 ft: 1,200 ft.
PA-24T-260
Engine: 1 x Avco Lycoming IO-540 turbocharged, 194kW
Wingspan: 10.97 m / 36 ft 0 in
Length: 7.62 m / 25 ft 0 in
Height: 2.29 m / 8 ft 6 in
Wing area: 16.54 sq.m / 178.03 sq ft
Max take-off weight: 1451 kg / 3199 lb
Empty weight: 859 kg / 1894 lb
Max. speed: 389 km/h / 242 mph
Ceiling: 7620 m / 25000 ft
Range: 2398 km / 1490 miles
PA24 Interceptor 400
Engine: Lycoming IO-720, 400 hp
Top speed: 233 mph
Cruise: 202 mph
1964 Piper Comanche 400
New price (1964): $36,890
Engine: Lycoming IO-720 A1A, 400 hp
TBO: 1800 hr
Fuel type: 100
Propeller type: CS
Landing gear: Tri./Retr
Max ramp weight: 3600 lb
Gross weight: 3600 lb
Landing weight: 3600 lb
Empty weight, std: 2110 lb
Useful load, std: 1490 lb
Useful fuel, std: 130 USG
Payload, full std. fuel: 710 lb
Wingspan: 36 ft
Overall length: 25 ft. 8 in
Height: 7 ft. 10 in
Wing area: 178 sq. ft
Wing loading: 20.2 lbs./sq.ft
Power loading: 9.0 lbs./hp
Wheel size: 6.00 x 6 in
Seating capacity: 4
Cabin doors: 1
Cabin width: 44 in
Cabin height: 45 in
Cruise speed 75% power: 185 kt
Cruise speed 65% power: 180 kt
Cruise speed 55% power: 171 kt
Fuel consumption 75% power: 22 USgph
Fuel consumption 65% power: 19 USgph
Fuel consumption 55% power: 16 Usgph
Vso: 59 kt
Best rate of climb, SL: 1600 fpm
Service ceiling: 19,500 ft
Takeoff ground roll: 980 ft
Takeoff over 50-ft obstacle: 1500 ft
Landing ground roll: 1180 ft
Landing over 50-ft. obstacle: 1820 ft
Piper had nothing to compete with the Cessna 150, so Piper made use of its Tri Pacer tooling and brought forth a two seat, 108 hp version of the PA 22. A nose-wheel development of the PA-20. This was the final high-wing design to come from Piper. It differed from the PA-20 by having an interconnected aileron and rudder pedal control system, enabling the Tri-Pacer to be flown entirely by the control column without the need to have an input from the rudder pedals during turns. This system was easily disconnected, however, to permit independent use of the ailerons, elevator and rudder. Basically, an updated PA-20 Pacer with tricycle undercarriage, the PA-22 Tri-Pacer (TC 1A6) appeared in 1950 and sold in large numbers at $4,995-6,995 for Standard, Custom, and Super Custom models in 1962. 1,822 Colt were sold.
The Tri-Pacer was introduced as four-seat PA22-125 (125 hp) and PA22-135 (135 hp), the -135 being standard from 1953.
By 1955 the Tri-Pacer (TC 1A6) had been updated and fitted with a 150 hp / 112kW Avco Lycoming O-320 engine, as installed in the PA-18 Super Cub. A more powerful version powered by a 160 hp engine was marketed in 1957 and the following year the 150 hp version became the Caribbean $8,395 (1959). 7,668 were built. EDO floats were an option for $2,435.
The final PA-22 version was the simplified two-place Colt built from 1960 to 1964. The Colt utilized the Tri-Pacer undercarriage, engine mounts, windshield, door, tail surfaces, struts, seats and instrument panel. Selected as the standard aero club trainer by Sweden, nearly 1800 of the type had been delivered by the beginning of 1964.
The 125-hp Pacers, fully equipped, sold for $5,170, and the 135-hp models were priced at $6,275, which included an Aeromatic or Sensenich controllable-pitch propeller.
The Colt never had a chance. Despite its eight horsepower edge over the Cessna 150, it was a stocky, ragwing, flapless loser with a poor glide ratio; slow sales prompted Piper to axe the program after just three years.
The Tri Pacer Twin had two 100 hp Continentals in its nose, one atop the other, driving a pair of props on concentric shafts. The concept led to a similar sandwich engine Comanche study, after Bill Lear assured Piper that the first company to develop a conventionally configured “single” with engine out capability would get rich quick. Ed Swearingen, however, who did the feasibility study, convinced Piper that the Comanche would never work.
The PA-22-108, -150, and –16 were certified under FAA 1A6 and by the end of production a total of 9490 had been produced.
PA22-125 Tri-Pacer
Engine: Lycoming O-290-D2, 125 hp
Seats: 4
PA22-135 Tri-Pacer
Engine: Lycoming O-290-D2, 135 hp
Seats: 4
PA22-108 Colt
Engine: Lycoming O-235-C1B, 108 hp
Wingspan: 30 ft 0 in / 9.14 m
Length: 20 ft 0 in / 6.10 m
Height: 6 ft 3 in
Wing area: 147 sq.ft
Empty weight: 940 lb / 426 kg
MTOW: 1650 lb / 748 kg
Max option fuel: 36 USG / 136 lt
Max speed: 120 mph at SL
Max cruise 75% 7000ft/2135m: 100 kt / 115 mph / 185 kph
ROC SL: 610 fpm / 186 m/min
Service ceiling: 12,000 ft / 3660 m
Range std fuel: 281 nm / 324 mi / 554 km
Range max opt fuel 7000ft/2135m: 599 nm / 690 mi / 1110 km
U/C: Nose wheel
Seats: 2
PA-22 Tri-Pacer
Engine: Lycoming O-320, 160 hp
TBO: 2000 hr
Fuel type: 100
Propeller type: 62-inch, FP Sensenich
Landing gear type: Conv./Fixed
Gross weight: 2000 lb / 908 kg
Empty weight, std: 1150 lb
Useful load, std: 850 lb
Usable fuel, std: 66 Usgals /396 lb
Payload, full std. fuel: 454 lb
Wingspan: 29 ft. 4 in / 8.9 m
Overall length: 20 ft. 4 in / 6.28 m
Height: 6 ft. 1 in
Wing area: 147.5 sq. ft
Wing loading: 13.6 lbs./sq. ft
Power loading: 12.5 lbs./hp
Seating capacity: 2+2
Cabin doors: 2
Cabin width: 40 in
Cabin height: 45 in
Wheel size: 6 x 6 in
Max level speed: 141 mph (226 kph)
Cruise speed, 75% power: 120 kts
Fuel consumption, 75% power: 8 gph
Vso: 42 kt
Best rate of climb, SL: 1000 fpm
Service ceiling: 15,500+ ft
Takeoff ground roll: 1120 ft
Takeoff over 50 ft obstacle: 1600 ft
Landing ground roll: 780 ft
Landing over 50 ft obstacle: 1280 ft
1958 PA-22 Tri-Pacer
Engine: Lycoming O-320-B, 160 hp
TBO: 2000 hr
Propeller: Fixed
Landing gear: Tri/Fixed
Gross weight: 2000 lb
Empty weight, std: 1110 lb
Useful load, std: 890 lb
Fuel: 36 USgal
Wingspan: 29 ft. 3 in
Overall length: 20 ft. 6 in
Height: 8 ft. 4 in.
Wing area: 147.5 sq. ft
Seating capacity: 4
Cabin width: 40 in
Cabin height: 36 in
Baggage capacity: 100 lb
Cruise speed 75% power: 113 kt
Max range (w/ reserve) 75% power: 435 nm
Fuel consumption 75% power: 8 US gph
Stall speed (gear, flaps down): 49 kt
Best rate of climb: 800 fpm
Service ceiling: 16,500 ft
Takeoff ground roll: 1120 ft
Landing ground roll: 500 ft
PA-22-150
Engine: 1 x Avco Lycoming O-320-B, 119kW
Max take-off weight: 907 kg / 2000 lb
Empty weight: 503 kg / 1109 lb
Wingspan: 8.92 m / 29 ft 3 in
Length: 6.28 m / 21 ft 7 in
Height: 2.54 m / 8 ft 4 in
Wing area: 13.7 sq.m / 147.47 sq ft
Max. speed: 227 km/h / 141 mph
Ceiling: 5030 m / 16500 ft
Range: 1054 km / 655 miles
PA22 Caribbean
Seats: 4
Originally called ‘Clipper’ but changed to Pacer as PanAm had threatened as lawsuit as the name ‘Clipper’ was registered to them. The Piper Pacer, built 1950-1953 inclusive, evolved from the two-place Vagabond of 1948. As the post-war market developed, Piper recognized the need for a minimum-cost four-placer, and the initial result was the PA-16 Clipper in 1949, which in turn spawned the PA-20 Pacer in 1950.
The Pacer is typical Piper for that period: metal-framed, fabric covered, and easy to fly. It introduced a number of improvements, including a larger area tailplane with balanced elevators, increased fuel capacity, redesigned landing gear and several interior refinements.
The Pacers are taildraggers, and the first ones were powered with the Lycoming O-235-C1 Lycoming of 81kW / 115-hp, designated PA-20 Pacer 115 (TC 1A4), and priced at $3,795. Since this was during the pre-avionics age, not much, if anything, was added to that for radios.
Few of the 115-hp models were produced, however, before the 93kW / 125-hp (Lycoming O-290-D) Pacer 125 was offered, and most Pacer production is accounted for by this model.
The 1952 Pacer 135 introduced a variable-pitch propeller and were fitted with the O-290-D2 rated at 135-hp, but sales dwindled and production was halted in 1953, because the tri-gear version of the Pacer, the PA-22 Tri-Pacer, introduced in 1952, was claiming most of the customers.
In May 1951 Max Conrad set a Transcontinental, non-stop lightplane record of 23h:4m:31s
in a PA-20.
When production ended in 1954 a total of 1,119 had been built, and the PA-20 Pacer 135 could demonstrate a maximum speed of 225km/h and had a range of 933km.
Engine: 1 x 93kW Lycoming O-290-D
Max take-off weight: 816 kg / 1799 lb
Wingspan: 8.93 m / 29 ft 4 in
Length: 6.21 m / 20 ft 4 in
Cruise speed: 180 km/h / 112 mph
Range: 933 km / 580 miles
Crew: 1
Passengers: 3
This little bubbletop trainer was the world’s first fiberglass airplane. It bore a deceptive similarity to the Tomahawk, with which it has nothing in common. Heralded as Piper’s next generation trainer when it was previewed by the press in 1962, the airplane was quietly dropped: the potential profits weren’t worth the risks of being a plastics pioneer.
Only the one was built, N2900M, first flying on 30 April 1962.
A side by side two seat training aircraft, construction was all plastic / glassfibre honeycomb construction and fitted with a fixed tricycle undercarriage. The aircraft is fitted with one piece full span flaperons and the canopy slides rearwards.
The aircraft is now preserved at the Piper Aviation Museum at Lock Haven.
Engine: Lycoming O-235-C1B, 108 hp
Wingspan: 25 ft 0 in
Length: 21 ft 6 in
Height: 7 ft 0 in
Empty weight: 803 lb
Loaded weight: 1500 lb
Seats: 2
Early in 1948 Piper was developing the PA-19, which was a version of the PA-11 Cub Special for the U.S. Army. Only three were built and the first of them, N5011H (Ser. No. 19-1), would serve as the certification test bed for the installation of the Continental C-90-12F, Lycoming O-235-C1 and O-290-D.
The PA-11 airframe was unchanged, except for a revised center section and the use of the more rounded rudder that was first used on the J-4 Cub Coupe. A sporty 90hp Continental-powered version of the Vagabond with Clipper wings, which was to be a mate with the 90hp PA-11 for the 1949 model year.
Military orders for the PA-19 that Piper Aircraft hoped for did not immediately materialize, so the company decided to ”civilianize” the design and market it as the Super Cub. Rather than advancing to the next model designation, which would have been PA-20, Piper chose to go backward and assign the unused PA-18 designation to the Super Cub.
Ot the three PA-19s were built: the first became the test bed for the PA-18-90 and -105 models; the second example became the test bed for the PA-18-125 and -135; and the third was built and sold to the Department of the Interior and used by the Fish and Game Commission. This PA-19 existed in 2009 and was flying in Alaska.
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