Piper “Cherokee Archer II”
Single-engine four-seat low-wing cabin monoplane
Piper PA-28-181 “Cherokee Archer II” (N2429T, s/n 28-7690390, 1976) c.1990s on display at the MCAS El Toro Airshow, MCAS El Toro, California (John Shupek photo copyright © 2001 Skytamer Images)
Piper PA-28-181 “Cherokee Archer II” (N4410X, s/n 28-7690012, 1975) on display at the 2009 Cable Air Show, Cable Airport, Upland, California (John Shupek photos copyright © 2009 Skytamer Images)
Piper PA-28-181 “Cherokee Archer II” (N8788E, s/n 28-7690204, 1976) on display at the 2009 Cable Air Show, Cable Airport, Upland, California (John Shupek photos copyright © 2009 Skytamer Images)
Piper PA-28-181 “Cherokee Archer II” ²
On 9 October 1972 Piper introduced the “Cherokee Challenger” as its successor to the “Cherokee 180”. In 1974 this was superseded by the “Cherokee Archer”, with the same basic airframe and powerplant, but introducing many new equipment and electronic options. For 1976 this aircraft was designated PA-28-181 “Cherokee Archer II”, and had the tapered wings of the “Cherokee Warrior”.
Two groups of optional equipment were available during 1966 for the “Cherokee Archer 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 Archer 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-28-181)²
- Four-seat cabin monoplane.
- Cantilever low-wing monoplane
- Wing section NACA 652-415 on inboard panels
- Outboard leading-edge has modification No. 5 of NACA TN 2228.
- Dihedral 7°
- Incidence 2° at root, -1° at tip.
- SweepBack at quarter-chord 5°
- Light alloy single-spar structure with glass-fiber wing-tips.
- Plain ailerons of light alloy construction.
- Trailing-edge flaps constructed of light alloy with ribbed skins.
- Aluminum alloy semi-monocoque structure.
- Glass-fiber engine cowling.
- 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.
- Non-retractable tricycle type.
- Steerable nose-wheel.
- Piper oleo-pneumatic shock-absorbers.
- Cleveland wheels and Schenuit tires, size 6.00 × 6, 4-ply rating, on all three wheels.
- Cleveland disc brakes.
- Parking brake
- One 180-hp (134 kW) Lycoming O-360-A3A flat-four engine.
- Sensenich two-blade fixed-pitch 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.
- 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.
- 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.
- Wingspan: 35 ft 0 in (10.67 m)
- Wing chord at root: 5 ft 3 in (1.6 m)
- Wing chord at tip: 3 ft 6¼ in (1.07 m)
- Length overall: 23 ft 9½ in (7.25 m)
- Height overall: 7 ft 3½ in (2.23 m)
- Tailplane span: 12 ft 10½ in (3.92 m)
- Wheel track: 10 ft 0 in (3.05 m)
- Wheelbase: 6 ft 7 in (2.00 m)
- Propeller diameter: 6 ft 4 in (1.93 m)
- 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)
- Weight empty, equipped (standard): 1,416 pounds (642 kg)
- Maximum T-O and landing weight: 2,550 pounds (1,156 kg)
- Maximum wing loading: 15.0 lb/ft² (73.2 kg/m²)
- Maximum power loading: 14.17 lb/hp (8.63 kg/kW)
Performance at Maximum T-O weight
- Never exceed speed: 171 mph (148 knots, 275 km/h) CAS
- Maximum level speed at S/L: 147 mph (128 knots, 237 km/h) CAS
- Maximum cruising speed at 75% power at 9000 ft (2,745 m): 143 mph (124 knots, 230 km/h) TAS
- Econ cruising speed at 65% power at 12,500 ft (3,810 m): 133 mph (115 knots, 214 km/h) TAS
- Stalling speed with flaps up: 67 mph (58.5 knots, 108 km/h) CAS
- Stalling speed with flaps down: 60 mph (52.5 knots, 97 km/h)
- Maximum rate of climb at S/L: 740 ft/min (226 m/min)
- Service ceiling: 13,700 ft (4,175 m)
- T-O run, S/L, ISA, 25° flap: 870 ft (265 m)
- T-O to 50 ft (15 m), S/L, ISA, 25° flap: 1,600 ft (488 m)
- Landing from 50 ft (15 m), S/L, ISA, 40° flap, max braking on paved dry runway: 1,390 ft (424 m)
- Landing run, conditions as above: 925 ft (282 m)
- Range with 48 US gallons (181.5 liters) usable fuel, 65% power at 12,500 ft (3,810 m), no reserves: 810 miles (703 nm, 1,303 km)
- Range, conditions as above, with max payload: 705 miles (612 nm, 1,134 km)
- Range with 48 US gallons (181.5 liters) usable fuel, 55% power at 12,500 ft (3,810 m) and 45 minute reserves: 685 miles (595 nm, 1,102 km)
- Photos, John Shupek, Copyright © 2001-2009 Skytamer Images. ALL RIGHTS RESERVED
- Taylor, John W. R. (editor). Jane's All The World’s Aircraft 1976-77, Jane's Yearbooks, Franklin Watts Inc., New York, 1776, ISBN 0-531 03260 4, pages 350-352
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