Piper PA-28-160 Cherokee 160
Single-engine four-seat low-wing cabin monoplane

Archive Photos ¹

Piper PA-28-160 Cherokee 160 (N5445W, s/n 28-522, 1962) on display at the 2000 Torrance Airshow, Zamperini Field, Torrance, California (Photos by John Shupek)

Piper PA-28 Cherokee Series ²

Circa 1966, the Cherokee was a low-cost all-metal low-wing monoplane with a non-retractable tricycle landing gear. The aircraft was available in 2/4-seat, 4-seat and 6/7-seat versions. A floatplane version was also in production.

Only 1,200 parts went into the manufacture of the Cherokee. Its predecessor, the four-seat high-wing Piper Tri-Pacer used 1,600 parts in its manufacture. The first production Cherokee flew on 10 February 1961, and production was at the rate of 14 aircraft per day in the summer of 1966. A total of 5,219 Cherokees had been built by 1 January 1966.

Models available during 1966 were the Cherokee 140-4 (2/4-seat), Cherokee C 150, 160 and 180 (four-seat), Cherokee 235B (four-seat), and the Cherokee Six (6/7-seat). Descriptions of the PA-28-150, PA-28-160, and the PA-28-180 are presented below.

As part of a continuing research program, Piper tested two Cherokees with a controllable-pitch propeller and retractable landing gear respectively in 1966.

Piper PA-28 Cherokee C Series ²

During 1966, three basic versions of the Piper PA-28 Cherokee C were in production.

• Piper PA-28-150 — 150-hp Lycoming O-320-A2A engine. Prototype flew for the first time on 14 January 1966. FAA type approval 2 June 1961.
• Piper PA-28-160 — 160-hp Lycoming O-320-D2A engine. Prototype flew for the first time on 20 September 1960. FAA Type Approval 31 October 1960.
• Piper PA-28-180 — 180-hp Lycoming O-360-A3A engine. Wheel fairings standard. Prototype flew for the first time on 6 February 1961. FAA Type Approval 3 August 1962.

Each of these basic Cherokee models was available in four different forms, with varying standards of equipment, as follows:

• Standard Cherokee — Basic model with dual controls.
• Custom Cherokee C — As basic model, with addition of Piper TruSpeed Indicator, instrument panel light, cabin dome light, navigation and taxi light, rotating beacon, radio shielding, sensitive altimeter, lighter, coat hooks, step, full flow oil filter and Piper AutoFlite wing stability levelling system, adding 12 lbs (5.5 kg) to basic empty weight.
• Executive Cherokee C — As Custom model, with addition of blind-flying instrumentation, clock, and vacuum pump. Piper AutoControl in place of AutoFlite, adding 25 lbs (11.5 kg) to basic empty weight.
• Sportsman Cherokees C — As Executive model, with addition of Piper electric trim, external power, and course selector on AutoControl, adding 35 lbs (16 kb) to basic empty weight.

Each of the above versions could be fitted with one of four electronic packages, as follows:

• Electronic Group A — Comprises Mk III Omnigator, 90-channel VHF transceiver plus 100-channel VOR/ILS nav indicator, cabin speaker, headset, microphone and antennae, adding 10 lbs (4.5 kg) to basic empty weight.
• Electronic Group B — Same as Group A, with the addition of ADF-31 automatic direction finder, adding 18 lbs (8 kg) to basic empty weight.
• Electronic Group C — Same as Group B, with the addition of Mk 12 series 360-channel VHF transceiver plus 100-channel VOR/ILS nav receiver, VOA-4/ILS localizer converter indicator and Piper marker beacon, adding total of 33 lbs (15 kg) to basic empty weight.
• Electronic Group D — Same as Group C, but with Mk 12 series 90-channel the VHF transceiver instead of Mk III Omnigator, and addition of VOA-5 VOR/ILS localizer converter indicator with glide-slope indication, UGR glide-slope receiver and UDI DME with ground speed indication, adding total of 53 lbs (24 kg) to basic empty weight.

Most items covered under model and electronic group listings were available individually. Other optional extras included Palm Beach external finish, stainless steel control cables, mixture control indicator, T-12 series ADF, KX-160 series radio, fire extinguisher, toe breaks and heated pitot tube.

All versions of the Cherokee could also be fitted with the new Piper AutoFlite automatic stability system. Weighing less than 4 lbs (1.8 kg), this incorporates in the amplifier an electrical rate-gyro with a zero threshold which senses both azimuth changes in wing-down condition, and operates in the ailerons as required for stability. Automatic pitch control is unnecessary on the Cherokee.

The Piper PA-28-180 Cherokee was also available in seaplane form as the PA-28S-180 with Edo Model 89-2000 floats, having received FAA Type Approval in this form on 10 May 1963.

All versions of the Cherokee could be fitted with low-drag quickly-detachable Sorensen spray-gear for agricultural duties. Available in kit form, the spray-gear consists of 110 US gallon (416 liter) glass-fiber belly tank, ½-in pump, pipes and boom with openings for 17 nozzles of five different types.

Specifications and Performance Data (PA-28-160) ²

Type

• Four-seat cabin monoplane.

Wings

• Cantilever low-wing monoplane
• Wing section NACA 65₂-415
• Aspect ratio 5-63
• Constant chord of 5 ft 3 in (1.60 m)
• Dihedral 7°
• Incidence 2°
• Single-spar wings, plain ailerons and slotted flaps made of aluminum alloy, except for glass-fiber wing-tips.
• Ailerons and flaps have corrugated skin.
• Ground adjustable tab in port aileron.

Fuselage

• Aluminum alloy semi-monocoque structure.
• Glass-fiber engine cowling.

Tail Unit

• Cantilever structure of aluminum alloy, except for glass-fiber 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 optional.
• Approved for operation on skis.

Power Plant

• One Lycoming four-cylinder horizontally-opposed air-cooled engine (details under descriptions of individual models).
• Sensenich two-blade fixed-pitch propeller, diameter 6 ft 2 in (1.88 m).
• Fuel in two tanks in wing leading-edges.
• Standard fuel capacity of 38 US gallons (136 liters), the remaining tankage of 14 US gallons (53 liters) being regarded as reserve.

Accommodation

• Four persons in pairs in enclosed cabin.
• Individual front seats; bench type rear seat.
• Large door on starboard side.
• Heater and ventilation.
• Baggage compartment aft of cabin, with capacity of 200 lb (90 kg), door on starboard side.
• Rear seat removable to provide 44 ft³ (1.25 m³) cargo space.
• Provision for carrying stretcher.

Electronics and Equipment

• Details under model and electronic group listed above.

Dimensions, external

• Wing span: 30 ft 0 in (9.14 m)
• Length overall: 23 ft 6 in (7.16 m)
• Height overall (landplane): 7 ft 3½ in (2.22 m)
• Tailplane span: 10 ft 0 in (3.05 m)
• Wheel track: 10 ft 0 in (3.05 m)
• Wheelbase: 6 ft 2½ in (1.89 m)

Areas

• Wings, gross: 160 ft² (14.86 m²)
• Ailerons (total): 10.60 ft² (0.99 m²)
• Trailing edge flaps: 14.60 ft² (1.36 m²0
• Fin: 7.5 ft² (0.70 m²)
• Rudder: 4.10 ft² (0.38 m²)
• Tailplane: 24.40 ft² (2.26 m²)

Weights and Loadings

• Weight empty (standard): 1,255 lbs (569 kg)
• Max. T/O weight: 2,200 lbs (998 kg)
• Maximum wing loading: 13.8 lb/ft² (67.4 kg/m²)
• Maximum power loading: 13.8 lb/hp (6.26 kg/hp)

Performance

• Maximum speed at S/L: 146 mph (235 kmh)
• Maximum cruising speed at 75% power at 7,000 ft (2,135 m): 137 mph (220 kmh)
• Stalling speed, flaps down: 55 mph (88.5 kmh)
• Rate of climb at S/L: 730 ft/min (223 m/min)
• Service ceiling: 15,800 ft (4,815 m)
• T/O run: 740 ft (226 m)
• Landing run: 550 ft (168 m)
• Range at 75% power at 7,000 ft (2,130 m) with 36 US gallons fuel): 545 miles (875 km)
• Range at 55% power at 10,000 ft (3,050 m) with 36 US gallons fuel): 590 miles (950 km)
• Range at 75% power at 7,000 ft (2,130 m) with 50 US gallons fuel): 735 miles (1,183 km)
• Range at 55% power at 10,000 ft (3,050 m) with 50 US gallons fuel): 815 miles (1,310 km)

References

1. Photos: John Shupek
2. Taylor, John W. R. (editor). Jane’s All The World’s Aircraft 1966-1967, McGraw-Hill Book Company, New York, pages 310-311