Piper PA-32-300 Cherokee Six
Single-engine 6/7-seat fixed-gear low-wing cabin monoplane

Archive Photos¹

Piper PA-32-300 Cherokee Six (N94JC, s/n 32-73440107, 1973) on display at the 2000 Torrance Airshow, Zamperini Field, Torrance, California (Photos by John Shupek)

Overview²

The prototype of the PA-32 Cherokee Six (N9999W) was flown for the first time on 6 December 1963, followed by the first production model (N9998W) on 17 September 1964. FAA Type Approval was received on 4 March 1965.

The original version was a six-seater, but the model introduced in October 1966 offered an optional seventh seat. The 1969 Cherokee Six B introduced increased cabin space, achieved by moving the instrument panel forward. Additional shoulder, hip and legroom was provided by moving the seats one inch away from the fuselage walls. The new features incorporated in the 1973 Cherokee Cruiser apply also to the Cherokee Six. In addition, the Cherokee Six 260 incorporated a two-blade constant-speed propeller as standard.

The 1973 Piper PA-32 was available with two alternate power plants, as follows:

Cherokee Six 260 — Basic version with 260 hp Lycoming O-540-E six-cylinder horizontally-opposed air-cooled engine, driving a two-blade constant-speed propeller. Carburetor heat control and engine primer standard.

Cherokee Six 300 — More powerful version with 300 hp Lycoming IO-540-K six-cylinder horizontally-opposed air-cooled engine, driving a two-blade constant-speed propeller. available also has a floatplane, on the Edo 3430 floats and with propeller of 7 ft 0 in (2.13 m) diameter. Two oil coolers and alternate air source (automatic with manual override) were standard.

The Cherokee Six could be fitted with one of four electronic packages as follows:

Electronic Group A — Mark 12 series 360-channel VHF transceiver plus 100-channel VOR/ILS receiver; VOR/ILS localizer converter indicator; Piper AutoFlite II; cabin speaker, headset and microphone with jacks, antennae and wiring, adding 15 lb (6 kg) to basic empty weight.

Electronic Group B — As Electronic Group A, with the addition of ADF-31 series automatic direction finder, with BFO and tuning meter; and Piper Nav Tracker II to AutoFlite II, adding 20 lb (9.1 kg) to basic empty weight.

Electronic Group C — As Electronic Group B, plus additional Mark 12 series 360-channel VHF transceiver with 100-channel VOR/ILS nav receiver and VOR/ILS localizer converter indicator; Piper marker beacon indicator; Piper audio selector panel; and Piper Electric Trim, adding 36 lb (16.3 kg) to basic empty weight.

Electronic Group D — As Electronic Group C, with deletion of one VOA-40 VOR/ILS localizer converter indicator and Piper marker beacon indicator; and addition of VOA/50M VOR/ILS localizer converter indicator with glidescope and marker beacon indication; UGR series glidescope receiver; and UDI series DME with ground speed indication.

Specifications and Performance Data (PA-32-300)²

Type

• Six/seven-seat cabin monoplane.

Wings

• Cantilever low-wing monoplane
• Wing section NACA 65₂-415
• Dihedral 7°
• Incidence 2°
• Single-spar wings, plain ailerons and slotted flaps made of aluminum alloy, except for glassfiber wingtips.
• Ailerons and four-position flaps have corrugated skin.
• Ground adjustable tab in port aileron.

Fuselage

• Aluminum alloy semi-monocoque structure.
• Glassfiber engine cowling.

Tail Unit

• Cantilever structure of aluminum alloy, except for glassfiber tips on fin and tailplane.
• Fin and rudder have corrugated metal skin.
• One-piece all-moving horizontal surface with combined anti-balance and trim tab.
• Trim-tab in rudder.

Landing Gear

• Non-retractable tricycle type.
• Steerable nose-wheel.
• Piper oleo-pneumatic shock-absorbers.
• Cleveland wheels and Schenuit tires, size 6.00-6, on all three wheels.
• Cleveland disc brakes.
• Parking brake.
• Toe brakes optional.
• Wheel fairings standard.

Power Plant

• One 300 hp Lycoming six-cylinder horizontally-opposed air-cooled engine, driving a two-blade propeller.
• Two fuel tanks in inner wings, total capacity 50 US gallons (189 liters).
• Two auxiliary tanks in glassfiber wingtips, with total capacity of 34 US gallons (129 liters).
• Total standard fuel capacity, with auxiliary tanks, 84 US gallons (318 liters) of which 83.3 US gallons (315 liters) are usable.
• Refueling point above each tank.
• Oil capacity 3 US gallons (11.5 liters)

Accommodation

• Enclosed cabin, seating six people in pairs.
• Optional seventh seat between two center seats.
• Dual controls standard.
• Two forward-hinged doors, one on starboard side at front and the other on portside and rear.
• Space for 100 lb (45 kg) bang each at rear of cabin, and another 100 lb (45 kg) forward, between engine and instrument panel.
• A set of four pieces of matched luggage to fit the nose baggage compartment is provided as standard.
• Passenger seats easily removable to provide up to 110 ft³ (3.11 m³) of cargo space inside cabin, or room for stretcher and one or two attendants.
• Large optional upward hinged utility door adjacent to rear door provides loading entrance nearly 5 ft (1.5 m) wide.
• Ten silent fresh air outlets, cabin heater with eight warm air outlets, including two defrosters, and two cabin air exhaust vents are standard.

Dimensions, external

• Wing span: 32 ft 9½ in (9.99 m)
• Length overall: 27 ft 8¾ (8.45 m)
• Height overall: 7 ft 11 in (2.41 m)
• Tailplane span: 12 ft 10½ in (3.92 m)
• Wheel track: 10 ft 7 in (3.22 m)
• Wheelbase: 7 ft 10 in (2.39 m)
• Propeller diameter: 6 ft 8 in (2.03 m)
• Cabin door height (rear, port): 2 ft 10 in (0.86 m)
• Cabin door width (rear, port): 3 ft 1 in (0.94 m)

Dimensions, internal

• Cabin length, panel to rear wall: 9 ft 11 in (3.02 m)
• Cabin max width: 4 ft 1 in (1.24 m)
• Cabin max height: 4 ft 0½ in (1.23 m)
• Baggage forward compartment volume: 8 ft³ (0.23 m³)
• Baggage aft compartment volume: 22 ft³ (0.62 m³)

Areas

• Wings, gross: 174.5 ft² (16.21 m³)

Weights and Loadings

• Weight empty, equipped: 1,799 lb (816 kg)
• Maximum T-O weight: 3,400 lb (1,542 kg)
• Maximum wing loading: 19.5 lb/ft² (95 kg/m²)
• Maximum power loading: 11.3 lb/hp (5.1 kg/hp)

Performance at max T-O weight

• Maximum level speed: 174 mph (151 knots; 279 km/h)
• Maximum cruising speed, 75% power at optimum altitude: 168 mph (146 knots; 270 km/h)
• Stalling speed, flaps down: 63 mph (55 knots; 102 km/h)
• Rate of climb at S/L: 1,050 ft/min (320 m/min)
• Service ceiling: 16,250 ft (4,950 m)
• Absolute ceiling: 18,000 ft (5,485 m)
• T-O run: 700 ft (213 m)
• T-O run to 50 ft (15 m): 1,140 ft (348 m)
• Landing from 50 ft (15 m): 1,000 ft (305 m)
• Landing run: 630 ft (192 m)
• Range at 75% power, basic fuel: 525 miles (456 nm; 845 km)
• Range at 75% power, with auxiliary fuel: 880 miles (764 nm; 1,415 km)
• Range at 55% power, basic fuel: 630 miles (547 nm; 1.015 km)
• Range at 55% power, with auxiliary fuel: 1,060 miles (920 nm; 1,705 km)

References

1. Photos: John Shupek
2. Taylor, John W. R. (editor). Jane’s All The World’s Aircraft 1973-74, Jane’s Yearbooks, McGraw-Hill Book Company, New York, 1973, ISBN 07-032021-7, pages 403-405