Piper PA-24-260 Comanche 260 four-seat low-wing monoplane

Piper PA-24-260 Comanche 260
Single-engine (260 hp) four-seat low-wing cabin monoplane

Archive Photos ¹

Piper PA-24-260 Comanche 260 (N8828P, s/n 24-4284, 1965) on display at the 2009 Cable Air Show, Cable Airport, Upland, California (Photos by John Shupek)

Overview ²

The prototype Comanche first flew on 24 May 1956, and the first production aircraft on 21 October 1957. A total of 3,938 had been produced in four versions, with engines of different powers, by 1 January 1965.

The original Comanche had a 180 hp Lycoming engine. The second version, the Comanche 250 with a 250 hp Lycoming engine, received FAA type approval on 7 March 1958. During 1965 the available versions were as follows:

PA-24-260 Comanche 260

Basic model of Comanche 260 which was announced on 28 August 1964, as a replacement for the Comanche 250. Powered by 260 hp Lycoming O-540 or IO-540 engine. Normal fuel capacity 60 US gallons (227 liters), with optional extra 30 US gallons (113.5 liters). Introduced cleaned-up landing gear, with single-fork main legs, which create less drag when retracted. Improved cabin soundproofing, heating and ventilation.

PA-24-260 Comanche 260 Custom 93

Same as standard Comanche 260, with addition of vacuum system, full blind-flying instrumentation, Narco Mk 12 90-channel VHF transceiver with separate 100-channel nav receiver, Narco VOA-6 VOR converter indicator, Bendix ADF-T12, headset, microphone and radio selector panel, Piper TruSpeed Indicator in place of standard ASI, rotating beacon, heated pitot tube, 30 US gallon (113.5 liter) auxiliary fuel tanks.

PA-24-260 Comanche 260 Custom 103

Same as Custom 93, with addition of Piper AutoControl II and V0A-4 VOR/ILS localizer converter instead of the VOA-6.

PA-24-260 Comanche 260 Custom 113

Same as Custom 113, with the addition of Piper Course Selector DG to replace zero heading DG.

PA-24-260 Comanche 260 Custom 123

Same as Custom 113, but with Piper AltiMatic II in place of AutoControl II, plus automatic electric trim, which converts to manual electric tram went AltiMatic II is disengaged.

PA-24-260 Comanche 260 Executive 203

Same as Custom 103, with the addition of Narco Mk 12 360-channel transceiver, second Narco VOA-4 VOR/ILS localizer converter indicator, Piper PM-1 marker beacon, glare ban instrumentation lights and Piper manual electric trim.

PA-24-260 Comanche 260 Executive 213

Same as Executive 203, but with Piper Course Selector DG instead of zero heading DG.

PA-24-260 Comanche 260 Executive 223

Same as Executive 213, but with AltiMatic II automatic electric pitch trim replacing AutoControl II.

PA-24-260 Comanche 260 Sportsman 303

Same as Executive 203, plus Palm Beach interior with leather upholstery, two front seat headrests and rear seat pillow, curtains, and Palm Beach exterior.

PA-24-260 Comanche 260 Sportsman 313

Same as Sportsman 303, but with Piper Course Selector DG instead of zero heading DG.

PA-24-260 Comanche 260 Sportsman 323

Same as Sportsman 313, but with Piper AltiMatic II with automatic electric pitch trim replacing AutoControl II.

PA-24-260 Comanche 260 Professional 403

Same as a Sportsman 303, but with two Narco Mk 12 360-channel transceivers, one Narco VOA-4 VOR/ILS localizer converter indicator, one Narco VOA-5 VOR/ILS localizer converter indicator with glide-scope indication, Narco UGR-1A glide-slope receiver, Narco UDI-3 DME/GSI, Piper external power unit and anti-static antennae.

PA-24-260 Comanche 260 Professional 413

Same as Professional 403, but with new production Piper 3-in gyros in place of re-manufactured 5-in gyros, radio coupling to Omni and Piper course selector DG.

PA-24-260 Comanche 260 Professional 423

Same as Professional 413, but with Piper AltiMatic II replacing AutoControl II.

The following details refer to the basic PA-24-260 Standard Comanche 260, but are generally applicable to the other versions except for the detailed changes listed above.

Specifications and Performance Data (PA-24-260) ²

Type

Four-seat cabin monoplane.

Wings

Cantilever low-wing monoplane.
NACA 64₂A215 laminar-flow wing section.
Aspect ratio 7.28
Wing chord: 7 ft 1 in (2.16 m) at root, 3 ft 3 in (0.99 m) at tip.
Wing dihedral: 5°
Wing incidence: 2°
Wing swept-forward at quarter-chord 2° 30’.
Three-spar aluminum stressed-skin structure.
Plastic wingtips.
Plain aluminum ailerons.
Electrically-actuated single-slotted aluminum flaps.

Fuselage

Aluminum semi-monocoque structure.

Tail Unit

Cantilever stressed-skin structure, made entirely of aluminum except for steel-tube stub spar.
SweptBack vertical surfaces.
All-moving one-piece tailplane or stabilator, with anti-servo tab.

Landing Gear

Electrically-retractable tricycle type, with emergency manual extension.
nosewheel retracts rearward, main units inward.
Piper oleo-pneumatic shock absorbers.
Cleveland wheels, size 600 × 6, tire pressure 42 psi (2.95 kg/cm²)
Cleveland single-disc hydraulic brakes.
Parking brake.
Edo type 289-2700 amphibious floats can be fitted.

Power Plant

One 260 hp Lycoming O-540 or IO-540 six-cylinder horizontally-oppose air-cooled engine.
Hartzell HC82XK1D two-blade metal constant-speed propeller.
Two rubber fuel tanks in wings with total capacity of 60 US gallons (227 liters).
Two optional auxiliary tanks in wings with total capacity of 30 US gallons (113.5 liters).
Refueling points above wings.
Oil capacity 3 US gallons (11.4 liters).

Accommodation

Enclosed cabin seating four in two pairs.
Dual controls.
Rear seat quickly removable to provide space for stretcher, camera or freight.
Forward-opening door at front of cabin on starboard side.
Baggage compartment, capacity 200 lb (90 kg), aft of cabin, with door on starboard side.

Electronics and Equipment

Standard equipment includes heater and defroster, ventilators, navigation and landing lights.
Optional equipment as detailed above under individual models.

Dimensions, External

Wing span: 36 ft 0 in (10.97 m)
Length overall: 25 ft 0 in (7.62 m)
Height overall: 7 ft 5½ in (2.27 m)
Tailplane span: 12 ft 6 in (3.81 m)
Wheel track: 9 ft 8 in (2.94 m)
Wheelbase: 6 ft 6^5/8 in (1.99 m)

Areas

Wings, gross: 1789 ft² (16.53 m²)
Ailerons (total): 14.0 ft² (1.30 m²)
Trailing-edge flaps (total): 20.2 ft² (1.87 m²)
Fin: 8.0 ft² (0.74 m²)
Rudder: 5.4 ft² (0.52 m²)
Tailplane, including tab: 32.5 ft² (3.04 m²)

Weights

Weight empty: 1,700 lb (771 kg)
Maximum T-O and landing weight: 2,900 lb (1,315 kg)

Loadings

Maximum wing loading: 16.3 lb/ft² (79.6 kg/m²)
Maximum power loading: 11.15 lb/hp (5.06 kg/hp)

Performance at Maximum Takeoff Weight

Maximum speed at sea level: 195 mph (314 kmh)
Maximum cruising speed, 75% power, 7,000 ft (2,135 m): 185 mph (298 kmh)
Stalling speed, flaps down: 61 mph (98 kmh)
Rate of climb at sea level: 1,500 ft/min (457 m/min)
Service ceiling: 20,600 ft (6,280 m)
T-O run: 660 ft (200 m)
T-O to 50 ft (15 m): 1,540 ft (470 m)
Landing from 50 ft (15 m): 1,420 ft (433 m)
Landing run: 650 ft (198 m)
Range (75% power), standard fuel: 730 miles (1,175 km)
Range (75% power), auxiliary fuel: 1,120 miles (1,800 km)
Maximum range, 55% power, standard fuel: 825 miles (1,325 km)
Maximum range, 55% power, auxiliary fuel: 1,265 miles (2,035 km)

References

Photos: John Shupek
Taylor, John W.R. (editor). Piper PA-24 Comanche, Jane’s All The World’s Aircraft 1965-1966, McGraw-Hill Book Company, New York, 1965, pages 288-290