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.
Cherokee Six 300
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.
Turbo Lance II & Lance II
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.
Embraer EMB-720 Minuano
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.
Embraer EMB-720D Minuano
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.
PT-ROK – Embraer EMB-721D Sertanejo
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
On 30 September 1964 Piper flew the prototype of a new twin-engine executive aircraft which was then the largest built by the company. Identified at first as the Piper PA-31 Inca, the aircraft had been redesignated as the PA-31 Navajo when deliveries began on 17 April 1967.
A six/eight-seat corporate/ commuter transport of cantilever low-wing monoplane configuration with retractable tricycle landing gear, it was powered by two 224kW Avco Lycoming IO-540-K flat-six engines, and was available in optional Standard, Commuter and Executive versions with differing interior layouts.
The internal cabin is 15 ft 10in long and 51.5in high and a nose baggage compartment has 14 cu.ft for 150 lb of luggage, and the aft compartment has 16 cu.ft for 200 lb.
The Standard version has accommodation for six passengers, rear baggage compartment, wardrobe and optional seating arrangements for seven or eight, plus a toilet.
The Executive and VIP version accommodates six passengers, with a pilot/passenger divider, curtained off area, refreshment unit, foldaway tables and a toilet, plus the optional seventh or eighth seat.
The Commuter version accommodates eight passengers, with a curtain divider, foldaway tables, refreshment unit, magazine racks, fasten seatbelts and no smoking signs, plus a luggage capacity of 350 lb.
Made available at the same time was the optional PA-31T Turbo Navajo, which differed only by having two 310 hp /231kW TIO-540-A turbocharged engines.
In 1974 an additional model of the Turbo Navajo was made available, the PA-31-325 Turbo Navajo C/R, which introduced a 242kW version of the counter-rotating engines installed in the Chieftain.
The Turbo Navajo B, cruising at 251 mph at 24,000 feet (404 km/h at 7000 meters); 223 mph at 12,000 feet (359 km/h at 3600 meters), featured new nacelle compartments increased luggage space 42 percent – 62 cubic feet (1.76 cu.m) and hold an additional 300 pounds (136 kg) total 650 pounds (295kg.), seating for up to nine people.
Production of the PA-31 Navajo ended and at the same time the company introduced for 1973 the PA-31-350 Navajo Chieftain which had the fuselage lengthened by 0.61m so an extra pair of seats could be fitted to the cabin, and was powered by two 350 hp / 261kW TIO-540-J2BD turbocharged engines driving counter-rotating propellers.
Piper PA-31-350 Navajo Cheftain
Piper expanded their 1976 medium twin line by offering the Navajo C/R. This airplane has 325 hp engines that eliminate the critical engine characteristics that stem from both propellers rotating in the same direction; the Navajo C/R’s left propeller turns in the conventional clockwise direction, but the right prop rotates counter-clockwise. The Navajo CR had wing lockers.
The basic model remained in production until 1983 by which time 1785 were built. Included in this total were the higher powered (325 hp) models which featured contra-rotating engines.
The engine variations provide the main performance difference among the models. The plain Navajo is a 3500 gross, 2,174 useful airplane, with a 310 hp turbo¬charged but otherwise unfettered TIO 540. The Navajo CR is the same airplane, with the same engine for that matter, except that the horsepower rating has risen to 325, magnetos are pressurized, and the right hand engine turns its propeller inboard, which the left one does anyway. The benefits of counter-rotation are minutely improved single engine performance and speeds, largely theoretical improvement from the neutralization of slipstream and prop wash effects, and the minimization of P factor. Gross weight remains the same, while useful weight drops a tad as a result of the CR’s capacious wing lockers.
The range was extended in 1970 by introduction of the PA-PA-31P Pressurized Navajo (First flying in March 1968) with a fail-safe fuselage structure in the pressurised section and two 317kW Avco Lycoming TIGO-541-E1A engines. The pressurised PA31P seated six was marketed for business high-fliers: 259 were built from 1970 till 1977.
PA-31P
The Chieftain is 24 inches longer than the CR, has a 7,000 gross and a 350 pound greater useful and the same engine. But horsepower has now been boosted to 350 with a tuned induction system and a slightly larger compressor.
One hundred and sixty seven Navajo Chieftains were licence built in Brazil by Embraer circa 1981, as the EMB-820.
Fifty Embraer EMB-820C Navajos were converted to turboprop configuration with Pratt & Whitney Canada PT6A-27 engines flat-rated to 550shp, being named Neiva NE-821 Caraja. The Carajá’s MTOW of 8,003 pounds (3,630 kg) was 1,000 pounds (454 kg) more than that of the Chieftain.
Neiva NE-821 Caraja
In 1984 a piston-engined version of the turbine Cheyenne I known as the PA31P-350 Mojave was intro-duced but production ceased that same year after only 50 had been completed. It incorporated the Chieftain II wings, pressurised Cheyenne I fuselage, and a Chieftain tail, with the powerplant of the PA-315-350 Chieftain. With increased wingspan and fuel capacity, plus airstairs, production of the PA-31P Pressurized Navajo ended during 1977, at which time a total of 248 had been built.
Schafer Aircraft Modifications Inc was founded 1977, and from 1979 developed modifications for other aircraft. Included were installing turboprop engines to Piper Navajo as the Schafer Comanchero, turboprop engines to Piper Chieftain as the Comanchero 500.
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 Piper PA-31 Navajo.
Production of the PA-31 Navajo started in 1973 and, after 1825 were built, ceased in 1983.
FAA A20SO PA-31 31-1 to 31-659 31-661 to 31-711 31-752 to 31-7612110 31-7712001 to 31-7912124 31-8012001 to 31-8312019
FAA A20SO PA-31-325 31-7300932 to 31-7612110 31-7712001 to 31-7912124
FAA A20SO PA-31-350 31-5000 to 31-7652176 31-7752001 to 31-7952250
FAA A8EA PA-31P 31P-1 to 31-7630019
FAA A8EA PA-31P-350 31P-8414001 to 8414050
Specifications:
PA31-300 Navajo Engine: 2 x Lycoming IO-470-M, 300 hp
PA31-310 Navajo First built: 1967 Engine: 2 x Lycoming TIO-540-A2C, 310 hp TBO: 1800 hrs Fuel; 100/100LL Prop: Hartzell 3 blade, constant speed 80 in Seats: 6/8 Length: 32.6 ft Height: 13 ft Wingspan: 40.7 ft Wing area: 229 sq.ft Wing aspect ratio: 7.2 Max ramp wt: 6536 lbs Max take off wt: 6500 lbs Standard empty wt: 4003 lbs Equipped Weight; 4529 lbs Max useful load: 2533 lbs Max landing wt: 6500 lbs Payload full std Fuel; 1650 lbs Baggage Capacity; 350 lbs Wing loading: 28.4 lbs/sq.ft Power loading: 10.5 lbs/hp Fuel Capacity; 192 US gals Usable Fuel; 187.3 US Gals / 1124 lb Climb rate: 1300 fpm @ 94 kt Climb gradient: 830 ft/nm Rate of climb @ 8000 ft: 1220 fpm Best Angle of Climb; 80 mph Absolute Ceiling; 27,300 ft Certificated ceiling; 24,000 ft SE rate of climb: 245 fpm @ 94 kt SE climb gradient: 157 ft/nm SE ceiling: 15,200 ft Max speed: 227 mph Never exceed ; 236 mph Cruise @ 65% power @ 8,000ft: 176 kts Cruise @ 65% pwr @ 18,000 ft: 192 kts Cruise 75% 22,000 ft Best Power: 213 mph Cruise 75% 22,000 ft Best Economy: 208 mph Cruise 65% 24,000 ft Best Power: 202 mph Cruise 65% 24,000 ft Best Economy: 196 mph Cruise 55% 24,000 ft Best Power: 182 mph Cruise 55% 24,000 ft Best Economy: 171 mph Max Range (with res) 75% 22,000 ft Best Power: 870nm Max Range (with res) 75% 22,000 ft Best Economy: 1005 nm Max Range (with res) 65% 24,000 ft Best Power: 910 nm Max Range (with res) 65% 24,000 ft Best Economy: 1052 nm Max Range (with res) 55% 24,000 ft Best Power: 922 nm Max Range (with res) 55% 24,000 ft Best Economy: 1068 nm Fuel Consumption 75% Best Power: 37.5 US gph Fuel Consumption 75% Best Economy: 29.7 US gph Fuel Consumption 65% Best Power: 33.0 US gph Fuel Consumption 65% Best Economy: 26.0 US gph Fuel Consumption 55% Best Power: 28.7 US gph Fuel Consumption 55% Best Economy: 22.7 US gph Fuel flow @ 65% power @ 18,000ft: 172 pph Endurance @ 65% power @ 18,000ft: 6.3 hr Stalling speed clean: 78 kt Stall speed gear/flaps down: 74 kt Turbulent air penetration speed: 159 kt Retractable undercarriage Trims; Elevator, Rudder, Aileron Min Control (Vmc); 74 mph Take-off Ground Run; 1720 ft Take-off 50ft; 2290 ft Landing 50 ft; 1521 ft Accelerate/stop; 2450 ft
PA31-325 Navajo C/R First built: 1975 Engine: 2 x Lycoming TIO-540-F2BD, 325 hp TBO: 1600 hr Prop: Hartzell 3 blade, constant speed 80 in Seats: 6/8 Length: 32.6 ft Height: 13 ft Wingspan: 40.7 ft Wing area: 229 sq.ft Wing aspect ratio: 7.2 Max ramp wt: 6540 lb Max take off wt: 6500 lb Standard empty wt: 4099 lb Max useful load: 2441 lb Max landing wt: 6500 lb Wing loading: 28.4 lbs/sq.ft Power loading: 10 lbs/hp Max useable fuel: 1425 lb Climb rate: 1220 fpm @ 100 kt Climb gradient: 720 ft/nm Rate of climb @ 8000 ft: 1100 fpm Certificated ceiling; 24,000 ft SE rate of climb: 255 fpm @ 97 kt SE climb gradient: 157 ft/nm SE ceiling: 15,300 ft Max speed: 228 kts Cruise @ 65% power @ 8,000ft: 180 kt Cruise @ 65% pwr @ 18,000 ft: 196 kt Fuel flow @ 65% power @ 18,000ft: 195 pph Endurance @ 65% power @ 18,000ft: 7.1 hr Stalling speed clean: 72 kt Stall speed gear/flaps down: 70 kt Turbulent air penetration speed: 159 kt Retractable undercarriage and counter-rotating prop
PA31-350 Navajo Chieftain Engine: 2 x Lycoming TIO-540-J2BD, 350 hp TBO: 1600 hr Prop: Hartzell 3 blade, constant speed 80 in Seats: 6/10 Length: 34.6 ft Height: 13 ft / 3.96 m Wingspan: 41 ft 8 in / 12.4 m Wing area: 229 sq.ft / 21.27 sq.m Wing aspect ratio: 7.2 Max ramp wt: 7045 lb Max take off wt: 7000 lb / 3175 kg Standard empty wt: 4421 lb Max useful load: 2824 lb Max landing wt: 7000 lb Wing loading: 30.6 lbs/sq.ft Power loading: 10 lbs/hp Max useable fuel: 1416 lb Climb rate: 1120 fpm @ 101 kt Climb gradient: 665 ft/nm Rate of climb @ 8000 ft: 980 fpm Certificated ceiling; 24,000 ft / 7315 m SE rate of climb: 230 fpm @ 106 kt SE climb gradient: 130 ft/nm SE ceiling: 13,700 ft Max speed: 231 kt / 428 km/h / 266 mph Cruise @ 65% power @ 8,000ft: 181 kt Cruise @ 65% pwr @ 18,000 ft: 197 kt Fuel flow @ 65% power @ 18,000ft: 185 pph Endurance @ 65% power @ 18,000ft: 7.4 hr Stalling speed clean: 77 kts Stall speed gear/flaps down: 74 kts Turbulent air penetration speed: 162 kt Retractable undercarriage
PA31P Engines Lycoming TIGO-541 ElA, 425 hp TBO 1,200 hr Propellers Hartzell three blade, constant speed, full feathering, 93 in. dia Length 34 ft. 6 in Height 13 ft. 3 in Wingspan 40 ft. 8 in Wing loading 34.1 lbs./sq.ft Seats 6/8 Empty weight 5,611 lb Useful load 2,189 lb Payload with full fuel 773 lb Gross weight 7,800 lb Power loading 9.18 lbs./hp Fuel capacity, equipped 236 USG/1,416 lb Baggage area 42 cu. Ft Minimum runway requirement 2,700 ft Rate of climb 1,740 fpm Single engine rate of climb 240 fpm Single engine service ceiling 12,100 ft Maximum speed 280 mph/243 kt Endurance, maximum cruise (incl. allowance for climb) 4 hr Normal cruise (@ 24,000 ft.) 244 mph/212 knots Endurance, normal cruise (incl. allowance for climb) 5 hr Long range cruise (@) 24,000 ft.) 222 mph / 193 kt Endurance, long range cruise (incl. allowance for climb) 6.3 hrs Stall speed (clean) 92 mph/80 knots Stall speed (gear, flaps down) 83 mph/72 knots
PA31P-350 Mojave Engines: 2 x Lycoming TIO-540-V2AD, 350 hp Props: Hartzell 3 blade CS 6ft 8in Wingspan: 44 ft 6 in Length: 34 ft 6 in Height: 13 ft 0 in Wing area: 237 sq.ft Max speed: 278 mph Cruise eco: 224 mph Cruise norm: 270 mph Stall: 83 mph ROC: 1220 fpm Service ceiling: 30,400 ft SE service ceiling: 14,300 ft TO run: 1625 ft TO to 50ft: 2469 ft Ldg from 50 ft: 2300 ft Ldg run: 1390 ft Range loaded: 679 mi Range normal: 1280 mi Range econ: 1405 mi Pressure differential: 5.2 lb Empty weight: 5065 lb Loaded weight: 7200 lb Useful load: 2516 lb Fuel capacity: 243 USG Cabin: 14 ft 5.75 in x 50 in x 51.5 in high Left rear cabin door: 46in x 28in Cabin baggage: 22 cu.ft Nose baggage: 22.5 cuf.t Nacelle lockers: 18 cu.ft Seats: 7
The Twin Comanche was a derivative of the single engine Comanche and was introduced in 1963 as a replacement for the Apache H. Little was done to the original Comanche fuselage when it was adapted for use in the Twin Comanche in order to simplify tooling and assembly operations. A cantilver low-wing monoplane with retractable tricycle landing gear and powered by two 160 hp / 119kW Avco Lycoming IO-320-B engines.
First flown in 7 November 1962, then production form flew on 3 May 1963, the PA-30 was superseded in 1965 by an improved four/six-seat PA-30B-160 Twin Comanche, and made available also at the same time was the PA-30B Turbo Twin Comanche with Rayjay-turbocharged IO-320-C1A engines.
In total 2,001 were built.
Delivering the first Twin Comanche to Europe in September 1963, Max Conrad spanned the 2100 miles from Gander to Shannon in 9 hr 21 min averaging 206 mph, at 50% power, burning 11 USG/hr. The co-pilot was Winston S. Churchill, 22 year old grandson of Sir Winston Churchill.
The PA-30 was offered in four models: Standard, Custom, Sportsman, and Turbo. The latter differed in engine power, and the rest contained different interior appointments, electronics, and instrumentation.
Both were replaced in 1970 by generally similar versions which introduced a powerplant with counter-rotating propellers. Designated PA-39 Twin Comanche C/R and PA-39 Turbo Twin Comanche C/R, manufacture of these two models ended in 1972, when total production of all versions amounted to 2,142. Piper announced the end of PA-30 production in 1970 and introduced a new PA-39 line.
Certification was under FAA A1EA.
One of these aircraft was used by Max Conrad to establish a new world class distance record when he flew non-stop from Cape Town, South Africa, to St Petersburg, Florida, during 24-26 December 1964. The distance of 12,678.83km remained a record in its class in 1993.
Its responsive handling earned it an airworthiness directive that raised Vmc from 70 to 78 knots.
The Super Twin Comanche was “Kind of a nice little bomb,” Pug muses, recalling the time he put two 300 hp Lycomings on the little Twin Comanche, almost doubling its horsepower. Even Piper, however, seriously questioned whether an airframe originally developed to hold a single four cylinder, 180 hp engine was quite ready for 12 jugs and 600 horses.
Piper PA-30 1964 Twin Comanche Engine: Lycoming IO-320-B1A, 160 hp TBO: 2000 hr Fuel type: 100LL Propeller: Hartzell two-blade CS Landing gear type: Tri/Retr. Max ramp weight: 3600 lb Max gross weight: 3600 lb Max takeoff weight: 3600 lb Empty weight: 2160 lb Max landing weight: 3600 lb Useful load, std: 1390 lb Payload, full std. fuel: 900 lb Usable fuel, std: 86 USgal Wingspan: 36 ft. 0 in Overall length: 25 ft. 2 in Height: 8 ft. 3 in Wing area:178 sq. ft Wing loading: 19.56 lbs./sq. ft Power loading: 11.25 lbs./hp Wheel base: 7 ft. 4 in Wheel track: 9 ft. 10 in Wheel size, mains: 6.00 x 6 Wheel size, nose: 6.00 x 6 Seating capacity: 4 Cabin doors: 1 Cabin width: 44 in Cabin height: 46 in Baggage capacity: 200-250 lb Cruise speed 75% power @ 8,000 ft: 168 Cruise speed 65% power @ 12,000 ft: 161 kt Cruise speed 55% power @ 14,000 ft: 148 kt Max range (w/ res) 75% power @ 8,000 ft.: 823 nm Max range (w/ res) 65% power @ 12,000 ft.: 890 nm Max range (w/ res) 55% power @ 14,000 ft.: 970 nm Fuel consumption 75% power: 17.2 USgph Fuel consumption 65% power: 15.2 USgph Fuel consumption 55% power: 13.4 USgph Stall speed (gear, flaps down, power off): 66 kt Stall speed (gear, flaps down, power on): 60 kt Best rate of climb: 1460 fpm Service ceiling: 18,600 ft Takeoff ground roll: 950 ft Takeoff over 50-ft. obstacle: 1530 ft Landing ground roll: 1215 ft Landing over 50-ft. obstacle: 1875 ft Service ceiling: 18,600 ft Single-engine service ceiling: 6600 ft Takeoff ground roll: 950 ft Takeoff over 50-ft. obstacle: 1570 ft Landing ground roll: 700 ft Landing over 50-ft. obstacle: 1875 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.
Piper Cherokee 180R N4646J
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.
1978 Piper Arrow 3
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.
1978 Piper Arrow 3
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.
Piper Arrow IV
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.
Embraer EMB-711 Corisco
The Embraer Corisco, in all its versions, managed to establish itself for about two decades in the Brazilian market, with almost 480 units sold.
Embraer EMB-711 Corisco
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.
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.
PA28-140
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.
Piper Charger N2673T
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.
Piper Cherokee 235B N8500W
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.
PA28-151 Cherokee Warrior
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.
Embraer EMB-710C Carioca
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.
Sorenson Aircraft spray rig
In 1964 Federal Ski & Engineering, Minneapolis, received FAA approval for aircraft skis to replace wheels on new PA-28-180s and 28-235 Cherokees.
Federal Ski & Engineering equipped PA-28-180
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
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
Basically an improved Apache, the Aztec was a full six-seater and had more powerful engines (250 hp) than the Apache. The first models were later named Aztec A. A major change came in 1962 with the introduction of the Aztec B, which had a lengthened nose giving the Aztec a completely different look from its Apache fore¬runner. Improvements were made year by year and the models were given letters until 1976 when the Aztec F was marketed. By then the Aztec had longer “tiger shark” shaped engine nacelles and an even longer and sharper nose. When production ceased in 1981 a total of 4929 Aztecs had been built.
Aztec F Engines: Lycoming TIO 540 ClA, 250 hp Props: two blade, constant speed, full feathering 77 in dia Length: 31 ft. 3 in Height: 10ft. 1 in Wingspan: 37 ft. 4 in Wing area: 207 sq. ft Max takeoff weight: 5,200 lb Standard empty weight: 3,319 lb Max useful load: 1881 lb Max landing weight: 4,940 lb Max zero fuel weight: 4,500 lb Power loading: 10.4 lbs/hp Wing loading: 25.1 lbs/sq.ft Max usable fuel: 177 gals./ 1,062 lb Max rate of climb, sea level: 1,480 fpm Max rate of climb, 8,000 feet: 1,330 fpm Certificated ceiling: 24,000 ft Single engine rate of climb, sea level: 226 fpm Single engine climb gradient: 154 ft. per nm Single engine service ceiling: 13,250 ft Max speed: 210 kts Cruise, normal at 8,000 ft: 116 kts Cruise, normal at 18,000 ft: 191 kts Fuel flow at normal cruise: 29.3 gph Endurance at normal cruise, no res: 5.8hrs Stalling speed, clean, power off: 60 kts Stalling speed, flaps down, power off: 67 kts Turbulent air penetration speed: 131 kts
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.
PA25-160
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.
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.
PA-24-250 – 1960
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.
Turbo Comanche C
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
It all began in 1952 with the introduction of the Twin-Stinson, the first Piper of Stinson lineage to be produced since the Piper/Stinson Flying Station Wagon. It was powered by twin 125-hp Lycoming engines. The following year Piper introduced the PA-23 Apache, a vast improvement on the Twin-Stinson concept.The Apache featured a conventional single rudder tail unit rather than the Twin-Stinson’s twin-tail configuration, and power was boosted with the use of 150-hp Lycomings. The new Piper also utilized all-metal construction and retractable landing gear.
On 2 March 1952 Piper flew the prototype N1953A of a new twin-engine aircraft which it then identified as the Piper PA-23 Twin-Stinson. A cantilever low-wing monoplane of all-metal construction, it had a tailplane set high on the fuselage and mounting endplate fins and rudders, retractable tricycle landing gear and an enclosed cabin seating four in two pairs. The Stinson’s fabric covering was replaced by metal and there was a major redesign from the cabin aft, including a single tail. Power was upgraded to two 150hp Lycoming 0-320-A, and prototype N23P c/n 23-1 took wing on 29 July 1953. There followed a second prototype [N1000P] c/n 23-2, and issuance of a TC1A10 on 29 January 1954.
It entered production in early 1954 as the PA-23 Apache, later designated PA-23 Apache 150. A total of 1,231 were built, priced at $32,000.
Piper Apache 160 N3454P
Powered by two Lycoming O-320 engines, each of 150 h.p. with Hartzell constant-speed airscrews, the Apache has comprehensive instruments and radio equipment included to remove the limitation of “daylight, V.F.R. only” flying, and the selling price of the new machine was $32,500, or approximately £11,600, in 1954.
Maximum all-up weight of the Apache is 3,500 lb which, with full tanks, four passengers, full instrumentation aria radio, enables 198 lb of baggage or extra equipment to be carried. Maximum sea-level cruising speed is 160 m.p.h. Single-engined ceiling at top weight is 5,000 ft, and at 3,100 lb is 8,000 ft.
The aircraft is of all-metal construction, and has an empty weight (completely equipped) of 2,170 lb. The “Custom” model is fitted with the three radio installations shown in the cockpit photograph; an autopilot can be fitted. The baggage compartment behind the cabin has a volume of 25 cu ft, and the rear passenger seats can be easily removed to increase the available cargo space to 80 cu ft.
The dual controls are conventional, with toe brakes on the left rudder pedals, and with connections to the steerable nosewheel. Rudder and elevator trim controls are located centrally in the cabin roof. The “Electrol” tricycle landing gear is hydraulically retractable and is fitted with Goodrich wheels, tyres and brakes. Two 36-gallon rubber fuel tanks are installed in the wing, outboard of the engines. The span of the Apache is 37ft; length 27ft lin; and wing area 204 sq ft.
The Apache achieved FAA 1A10 certification on January 29, 1954, with Lycoming 150hp. This ended up covering all PA-23, PA-23-160, and PA-23-250 27-1 to 27-1999 and 27-2505 to 27-8154030.
In 1958, O-320-B 160-hp engines were added as the PA-23 Apache 160, and with some interior revisions so that it was classed as a four/ five-seat aircraft (816 built), and in 1963, the 175kW / 235-hp Lycoming O-540-B1A5 became the standard powerplant to meet requirements for better single-engine performance (119 built). This later model was the first to sport swept tail surfaces and was quite similar to the Aztec of the same vintage, except for the Apache’s smaller engines and shorter nose. 816 were built.
Piper PA-23-160 Apache ZK-BYB
The optional fifth seat became available in 1956, retrofitable to earlier models, though baggage capacity was reduced from 200 lbs to 30 lbs when the seat was occupied, and two 18 USG aux tanks in the outboard wings were installed. Introduced in 1958 were the 160 hp Lycomings along with an increase in MTOW from 3500 lbs to 3800 lbs.
The Apache 235 (later becoming the Aztec 235) featured a swept tail and two Lycoming 235hp O-540-B1A5 engines. 119 were built.
A total of 481 of the 1959 Aztec 250 were sold.
584 of the 1960 Aztec B were sold, plus 20 to the USN as UO-1.
Piper Aztec B N5000Y
1357 of the 1962 Aztec C were built.
Introduced in 1968, the Aztec D featured a long nose with baggage compartment. 492 were built with an export model to South America and Africa.
1,020 of the 1970 introduce Aztec E were built.
Introduced in 1975, the Aztec F was powered with two 250hp Lycoming IO-540-C4B5 engines. Priced at $141,415 (1977), 714 were built, including Turbo Aztec F with TIO-540-C1A engines.
PA-23-250 Apache F ZK-EVP
The 1960 Apache G began the third side window. Some 170 of the 1961 Apache H model were built.
Piper’s 1964 Aztec had streamlined nacelles, flush wing flaps and fully enclosed wheel doors raising the max cruise to 208 mph. Lycoming 250 hp engines have fuel injection and lightweight Hartzell props. The price was $54,990.
From 1962 to 1965, built 117 Apache 235s. More than 2000 150- to 160-hp Apaches were built between 1954 and 1962 until production was replaced by the Twin Commanche (introduced in 1963).
The type continued in production as the Apache until 1965, by which time 2,166 had been built, including 1,231 examples of the first production version.
PA23-250C Aztec
With sales of the Apache 235 declining, Piper developed an improved version of this aircraft in 1960 which introduced a 250 hp / 186kW O-540 engine and provided six-seat capacity. The Aztec introduced a longer fuselage, longer nose, squared tail, and 5-6 seats instead of the Apache’s four.
This entered production under the designation PA-23-250 Aztec in 1959-60, the US Navy acquiring 20 of these aircraft, 149050 to 149069, for use in a utility role, designating them UO-1, changed to U-11A in 1962.
Piper U-11A
The Aztec was built until early 1982 when production was suspended. In final production form the type had the designation PA-23-250 Aztec F, and was available also as the generally similar PA-23T-250 Turbo Aztec F which differed by having Avco Lycoming TIO-540 engines with a Garrett turbo-charging system. The first F model, introduced in 1976, offered optional fuel capacity increase.
Both Apache and Aztec were available until the Apache line was dropped. A total of 2047 were built from 1954 to 1962.
Aztec Nomad Inc of Canada, produced the Aztec Nomad conversion of six-place Piper Aztec to twin EDO floats. The useful load was 2200 lb, reducing to 1800 lb as optional amphibian.
1954 Piper Apache 150 Engines: 2 x Lycoming O-320-A1A, 150 hp TBO: 2200 hr Fuel type: 100LL Props: Hartzell HC-82VL-2C, 2 blade CS, 72 in.. Landing gear: hydraulic Tri/Retr. Max ramp weight: 3800lb Gross weight: 3800 lb Landing weight: 3800 lb Empty weight, std: 2215 lb Useful load, std: 1585 lb Payload, full std. fuel: 1153 lb Usable fuel: 72 USG Optional fuel: 108 USG Oil capacity: 8 qt Wingspan: 37 ft Overall length: 27 ft. 1 in Height: 9 ft. 6 in Wing area: 208 sq. ft Wing loading: 12.7 lbs./sq. ft Power loading: 12.7 lbs./hp Wheel base: 7 ft. 4 in Wheel track: 11 ft. 4 in Wheel size: 6.00 x 6 in Seating capacity: 4 std, 5 opt Cabin doors: 1 Cabin width: 48 in Cabin height: 50 in Baggage capacity: 200 lb /25 cu. ft Maximum speed: 180 mph Cruise speed 75% power @ 6,000 ft: 146 kt / 170 mph Cruise speed 65% power @ 9,000 ft: 139 kt / 162 mph Cruise speed 55% power @ 12,000 ft: 128 kt Range at 75% pwr no reserve (72 USgal): 620 sm Range at 65% pwr no reserve (72 USgal): 710 s.m Maximum range no reserve (72 USgal): 840 sm Fuel consumption 75% power: 18.0 USgph Fuel consumption 65% power: 16.0 USgph Fuel consumption 55% power: 14.0 USgph Vs: 59 kt Vso: 51 kt Stall speed, gear and flaps up: 66mph. Stall speed, gear and flaps down: 59 mph Best rate of climb (SL): 1150 fpm Best rate of climb, 8000 ft: 600 fpm Service ceiling: 15,500 ft Single-engine absolute ceiling: 6750 ft Rate of climb, SE SL: 240 fpm Takeoff ground roll: 1290 ft Takeoff over 50-ft. obstacle (ft.): 1600 ft Landing ground roll: 750 ft Landing over 50-ft. obstacle: 1360 ft
PA23-160 Apache Engines: 2 x Lycoming O-320-B, 160 hp. Gross wt: 3,800 lb Empty wt. 2,280 lb Total fuel cap: 108 USG Max speed 3,000 ft: 152 kt / 183 mph Vmc: 70 kt Initial climb rate 1,260 fpm Best SE climb speed: 83kt SE ceiling: 5,500 ft Cruise 23×23: 130 kt / 173 mph Stall 61 mph Range 1,260 sm Ceiling 17,000 ft Takeoff run 1,190 ft Landing roll 750 ft Seats 4-5
PA23-235 Apache / Aztec 235 Lycoming: 2 x Lycoming O-540-B1A5, 235 hp Wingspan: 37 ft 1.75 in / 11.33 m Length: 27 ft 7 in / 8.41 m Empty wt. 2,735 lb / 1240 kg MTOW: 4,800 lb / 2177 kg Fuel capacity 144 USG Top speed 202 mph Cruise 75% 7000ft/2135m: 166 kt / 191 mph / 307 km Stall mph 62 Initial climb rate: 1,450 fpm / 442 m/min Service Ceiling: 17,200 ft / 5240 m Range 75%: 851 nm / 980 sm / 1575 km Takeoff run: 830 ft Landing roll: 880 ft Seats 4-5
Aztec A 1959 Engines: 2 x Lycoming IO 540 A1D5, 250 hp Seats: 5
Aztec B 1962 Seats: 6
Aztec C 1964 Engines: 2 x Lycoming IO 540 C4B5, 250 hp
Turbo Aztec C 1964 Engines: 2 x Lycoming TIO 540 C1A, 250 hp
Aztec D Engines: 2 x Lycoming IO 540 C41B5, 250 hp Prop: 6 ft 5 in (1.96 m) dia 2 blade metal Wing span: 37 ft 2.5 in (11,34 m) Length: 30 ft 21 in (9,21 m) Wing area: 207.56 sq ft (19.28 sq.m) Gross weight: 5,200 lb (2,360 kg) Normal cruising speed: 210 mph (338 km/h) at 4,000 ft (1,220 m) Range: 830 miles (1,335 km) at normal cruising speed Seats: 6.
Aztec E Engine: 2 x Lycoming IO-540-C4B5, 250 hp Wingspan: 37 ft 2.5 in / 11.34 m Length: 31 ft 2.75 in / 9.52 m Empty weight: 3042 lb / 1379 kg MTOW: 5200 lb / 2360 kg Cruise 4000ft/1220m: 182 kt / 210 mph / 338 kph Range cruise 10200ft/3110m: 169 kt / 195 mph / 314 kph ROC SL: 1490 fpm / 455 m/min Absolute ceiling: 21,100 ft / 6430 m Norm max fuel range: 720 nm / 830 mi / 1335 km Max range cruise: 1050 nm / 1210 mi / 1947 km Seats: 6 Cabin capacity: 1700 lb / 725 kg Rear cabin capacity: 150 lb / 68 kg Nose compartment capacity: 150 lb / 68 kg Max cargo capacity: 122 cu.ft / 3.45cu.m
Turbo Aztec E 1964 Engines: 2 x Lycoming TIO 540 C1A, 250 hp
PA23-250F Aztec F Engines: 2 x Lycoming IO 540 C4B5, 250 hp TBO: 2,000 hrs Props: 2 blade, constant speed, 77 in dia Max wt: 5200 lbs Max ldg wt: 4940 lbs Empty wt: 3221 lbs Useful load: 1979 lbs Payload with full fuel: 759 lb Wing area: 207 sq.ft Wing loading: 25.1 lb/sq.ft Pwr loading: 10.4 lb/hp Wing span: 37.3 ft Length: 31.2 ft Height: 10.1 ft Cabin length: 8.5 ft Cabin width: 45 in Cabin height: 50.5 in Useable fuel: Std: 137.2 USG, Optional: 177.2 USG/1,063 lbs Baggage capacity: Nose: 17.4 cu.ft, 150 lbs, Rear: 23 cu.ft, 150 lbs Seats: 6 Maximum speed: 178 kts Normal cruise: 179 kts @ 3850 ft Economy cruise (range, std fuel): 170 kts @ 6250 ft (830 nm) Long range cruise: (162 kts @ 10,800 ft: 985 nm Max cruise, 75% power (2,300 rpm) at 4,000 ft: 177 kts Econ cruise, 55% power at 10.000 ft: 152 kts Duration at max cruise: 5 hrs Duration at econ cruise: 8.6 hrs ROC: 1400 fpm SE ROC: 235 fpm Single engine climb gradient at 88 knots (Vy): 1.5 degrees Stall (5200 lbs), clean: 61 kts, Flap dn: 54.5 kts Service ceiling (5200 lbs): 17,600 ft Service ceiling SE: 4800 ft. T/O (50ft): 1980 ft Ldg dist (50ft): 1585 ft
PA23-250F Turbo Aztec F Engines: 2 x Lycoming TIO-540-C1A, 250 hp / 186kW Max wt: 5200 lb / 2359 kg Max ldg wt: 4940 lbs Empty wt: 3358 lb Useful load: 1842 lb Wing area: 207 sq.ft / 19.23 sq.m Wing loading: 25.1 lb/sq.ft Pwr loading: 10.4 lb/hp Wing span: 37 ft 4 in / 11.37 m Length: 31 ft 3 in / 9.52 m Height: 10 ft 1 in / 3.07 m Cabin length: 8.5 ft Cabin width: 45 in Cabin height: 50.5 in Useable fuel: Std: 137.2 USG Optional fuel: 177.2 USG Baggage capacity: Nose: 17.4 cu.ft, 150 lbs, Rear: 23 cu.ft, 150 lbs Max. speed: 407 km/h / 253 mph Economy cruise (range, std fuel): 193 kts @ 24,000 ft (780 nm) Long range cruise (range, std fuel): 165 kts @ 20,000 ft: 835 nm ROC: 1470 fpm ROC SE: 225 fpm Stall (5200 lbs), clean: 61 kts, Flap dn: 54.5 kts. Service ceiling (5200 lbs): 24,000 ft/7315 m, SE: 17,000 ft T/O (50ft): 1980 ft Ldg dist (50ft): 1585 ft.
All Aero 