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Piper PA-28R-200 “Cherokee Arrow II”
Single-engine four-seat retractable-gear cabin monoplane


Archive Photos¹


Piper PA-28R-200 “Cherokee Arrow II” (N32978, s/n 28R-7535103, 1975) on display at the 2009 Cable Air Show, Cable Airport, Upland, California (John Shupek photos copyright © 2009 Skytamer Images)

Overview²


The “Cherokee Arrow II” is generally similar to the “Cherokee Archer II”, but has a retractable landing gear, more powerful engine, and the untapered wing of the 1975 PA-28-180 “Archer”.

The tricycle landing gear is retracted hydraulically, with an electrically-operated pump supplying the hydraulic pressure. In addition to the usual ‘gear up’ warning horn and red light, the “Cherokee Arrow II” has an automatic extension system which drops the landing gear automatically if power is reduced and airspeed drops below 105 mph (91 knots; 169 km/h). The sensing system consists of a small probe mounted on the port side of the fuselage. Being located in the propeller slipstream, it can differentiate between a climb with power on and an approach to land with power reduced. A free-fall emergency extension system is also fitted. An ‘anti-retraction’ system guards against premature retraction of the landing gear below an airspeed of 85 mph (74 knots, 137 km/h) at take-off, or accidental retraction on the ground. There is also a manual override lever by which the pilot can hold the landing gear retracted as the airspeed falls below 105 mph (91 knots; 169 km/h).

Two groups of optional equipment were available during 1976 for the “Cherokee Arrow II” as basic packages:

Custom — Comprises Piper TruSpeed indicator; instrument panel white Backlighting and overhead red spotlight, cabin dome, navigation, landing/taxi, and radio dimming lights; wheel speed fairings; rotating beacon; sensitive altimeter; assist strap; aircraft step; adding 19.3 lb (8.75 kg) to basic empty weight.

Executive — As Custom package, plus vacuum system with engine-driven pump and advanced instrument panel, comprising 3 in pictorial gyro horizon, 3 in directional gyro, Piper pictorial turn rate indicator, rate of climb indicator, outside air temperature gauge and eight-day clock; adding 35.3 lb (16 kg) to basic empty weight.

The “Cherokee Arrow II” could also be fitted with one of six electronic packages as follows:

Electronic Group N 1-28/32 — Narco Com 11A 360-channel VHF transceiver; Nav 11 200-channel VOR/LOC receiver with converter indicator; AT-50A; M-700A noise-canceling microphone and headset; adding 15 lb (6.8 kg) to basic empty weight.

Electronic Group N 2-28/32 — Dual Narco Com 11A 360-channel VHF transceivers; dual Nav 11 200-channel VOR/LOC receivers with converter indicators; CP-125 audio selector panel; MBT-12R marker beacon receiver; ADF-140; AT-50A transponder; Piper AutoControl IIIB autopilot with VOR/LOC coupling and electric trim; M-700A noise-canceling microphone, headset and two broad band com antennae; adding 49 lb (22.2 kg) to basic empty weight.

Electronic Group NT 3-28/32 — As Group N 2-28/32, except dual Com 11As replaced by dual Com 111B 360-channel VHF transceivers; dual Nav 11s replaced by one Nav 111 200-channel VOR/LOC receiver with converter indicator, including 40 localizer channels, and one Nav 112 200-channel VOR/LOC receiver with converter indicator, including UGR-2A glidescope receiver; adding 55 lb (25 kg) to basic empty weight.

Electronic Group KS 1-28/32 — King KX 170B 720-channel com receiver, with 200-channel nav receiver; KI 201C VOR/LOC indicator; KT-78 transponder; Piper headset and 66C microphone; adding 19 pounds (8.6 kg) to basic empty weight.

Electronic Group KS 2-28/32 — Dual KX 170B 720-channel com receiver, with 200-channel nav receivers; dual KI 201C VOR/LOC converter indicators; KMA 20 audio panel with marker beacon receiver and indicator lights; KR 68 ADF with BFO; KT 78 transponder; Piper AutoControl IIIB autopilot; Piper VOR/LOC coupler; Piper electric trim; Piper static wicks; dual Piper broad band com antennae; and Piper 66C microphone with headset; adding 58 lb (26.3 kg) to basic empty weight.

Electronic Group KTS 3-28/32 — Dual KX 175B nav/com transceivers, with 720-channel transceivers, and 200-channel nav receivers; KNI 520 VOR/LOC/glidescope indicator with to-from indication and appropriate warning flags; KNI 520 VOR/LOC indicator; dual KN 77 VOR/LOC converters; KN 73 glidescope receiver; KR 85 ADF; KT 76 transponder; Piper AutoControl IIIB autopilot; Piper VOR/LOC coupler; Piper electric trim; dual Piper broad ban com antennae; Piper 100T noise-canceling microphone and headset; adding 68 lb (31 kg) to basic empty weight.

Specifications and Performance (1976 PA-28R-200 “Arrow II”)²


Type

  • Four-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 of light allow construction.
  • Glassfiber wingtips.
  • Ailerons and four-position 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-servo and trim tab.
  • Trim-tab in rudder.

Landing Gear

  • Retractable tricycle type, with single wheel on each unit.
  • Hydraulic retraction, main units inward into wings, nose unit rearward.
  • All units fitted with oleo-pneumatic shock-absorbers.
  • Main wheels and tires, size 6.00-6, 4-ply rating.
  • Nosewheel and tire size 5.00-6, 4-ply rating.
  • High-capacity dual hydraulic brakes and parking brake.

Power Plant

  • One 200-hp (149 kW) Lycoming IO-360-C1C flat-four engine.
  • Two-blade constant speed propeller with spinner.
  • Fuel in two tanks in wing leading-edges, with total capacity of 50 U.S. gallons (189 liters), of which 48 US gallons (181.5 liters) are usable.

Accommodation

  • Four persons in pairs in enclosed cabin.
  • Individual adjustable front seats, with dual controls.
  • Individual rear seats.
  • Large door on starboard side.
  • Heater and ventilation.
  • Windscreen defrosting.
  • Baggage compartment aft of cabin, with volume of 24 ft³ (0.68 m³) and capacity of 200 lb (90 kg), door on starboard side.
  • Rear seats removable to provide 44 ft³ (1.25 m³) cargo space.

Systems

  • Optional Piper Aire air-conditioning system.
  • Electrical system includes 60A alternator and 12V 25Ah battery.
  • Hydraulic system for brakes only.
  • Vacuum system optional.

Electronics and Equipment

  • Details of the available electronics packages are noted above.
  • Standard equipment includes external tie-town points, wing jack points and Piper automatic locator.
  • Optional equipment available includes fire extinguisher, 35Ah battery, external power socket, Inertia-reel shoulder harness for rear seats, adjustable front seats, alternate static source, overhead vent system, ventilation fan for air vent system, super soundproofing, outside air temperature gauge, heated pitot, Piper mixture control indicator, headrests, solar control windows, white wingtip strobe lights, zinc chromate application, and stainless steel control cables.

Dimensions, external:

  • Wingspan: 32 ft 2½ in (9.82 m)
  • Length overall: 24 ft 7¼ in (5.50 m)
  • Height overall: 8 ft 0 in (2.44 m)
  • Wheel track: 10 ft 6 in (3.20 m)
  • Wheelbase: 7 ft 10½ in (3.20 m)
  • Propeller diameter: 6 ft 2 in (1.88 m)

Areas

  • Wings, gross: 170 ft² (15.79 m²)
  • Ailerons (total): 13.20 ft² (1.23 m²)
  • Trailing-edge flaps (total): 14.60 ft² (13.16 m²)
  • Fin: 7.50 ft² (0.70 m²)
  • Rudder: 4.10 ft² (0.38 m²)
  • Tailplane: 26.50 ft² (2.46 m²)

Weights

  • Weight empty, equipped (standard): 1,513 lb (694 kg)
  • Maximum T-O weight: 2,650 lb (1,202 kg)

Loadings

  • Maximum wing loading: 15.6 lb/ft² (76.17 kg/m²)
  • Maximum power loading: 13.25 lb/hp (6.01 kg/hp)

Performance at Maximum T-O weight

  • Maximum level speed: 175 mph (152 knots; 282 km/h)
  • Maximum cruising speed, 75% power at optimum altitude: 165 mph (143 knots; 266 km/h)
  • Stalling speed with flaps down: 64 mph (56 knots; 103 km/h)
  • Maximum rate of climb at S/L: 900 ft/min (274 m/min)
  • Service ceiling: 15,000 ft (4,575 m)
  • Absolute ceiling: 17,000 ft (5,181 m)
  • T-O run: 1,025 ft (312 m)
  • Landing run: 780 ft (238 m)
  • Range with maximum fuel, 75% power at optimum altitude: 740 miles (642 nm; 1,191 km)
  • Range with maximum fuel, 55% power at optimum altitude: 850 miles (738 nm; 1,368 km)

References


  1. Photos, John Shupek, Copyright © 2009 Skytamer Images. ALL RIGHTS RESERVED
  2. Taylor, John W. R. (editor). Jane's All The World’s Aircraft 1976-77, Jane's Yearbooks, Franklin Watts Inc., New York, 1976, ISBN 0-531-03260-4, pages 350-353

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