Performance Data for the Piper PA-28 Dakota

Piper PA-28 Dakota · Performance Data

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Overview

This document provides performance data for the Piper PA-28 Dakota, a six-cylinder aircraft powered by a Lycoming engine. It includes specifications on engine performance, weights, dimensions, fuel capacity, and various performance metrics such as speed, climb rate, and takeoff distances. The information is crucial for pilots and aviation enthusiasts to understand the aircraft's capabilities and limitations. The document serves as a reference for flight planning and operational procedures, ensuring safe and efficient flight operations.

Engine: Lycoming 0-540-J3A5D, 235 hp @ 2400 RPM
Gross Weight: 3000 lbs (1361 kg), Useful Load: 1392 lbs (631 kg)
Maximum Speed: 148 knots (274 km/h)
Takeoff Distance: 825 ft (251 m) ground run, 1725 ft (526 m) over 50 ft obstacle
Service Ceiling: 17,500 ft (5334 m)

Document

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Document details

Type: Performance Data
Pages: 2
File size: 618 KB
Publisher: airmart.com

Specifications & performance

Extracted from this document.

Specifications

Engine (hp): 235
Height (ft): 8.5
Length (ft): 24.7
Propeller: Hartzell
Wingspan (ft): 36
Engine model: 0-540-J3A5D
Max speed (kt): 148
Cruise speed (kt): 139
Empty weight (lb): 1,608
Fuel capacity (gal): 77
Rate of climb (fpm): 1,000
Service ceiling (ft): 17,500
Max takeoff weight (lb): 3,000

Performance

Fuel burn (gph): 13.6
Landing over 50ft: 640
Takeoff over 50ft: 825
Landing distance (ft): 640
Takeoff distance (ft): 825
Stall speed clean (kt): 56
Stall speed landing (kt): 65

V-speeds

VS1: 56
VSO: 65

Weight & balance

Useful load (lb): 1,392
Basic empty weight (lb): 1,608
Max takeoff weight (lb): 3,000

Documentation completeness

4/7

Most owners only have the POH. Here's the essential set for the Piper PA-28 Dakota.

Pilot's Operating Handbook / AFM
Checklist
Maintenance Manual
Parts Catalog (IPC)
Systems & Wiring
Service Bulletins
Type Certificate (TCDS)

More Piper PA-28 Dakotamanuals & documents

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In this document

Engine Specifications

The Piper PA-28 Dakota is equipped with a Lycoming 0-540-J3A5D engine, rated at 235 horsepower at 2400 RPM. It has six cylinders and a recommended time between overhauls (TBO) of 2000 hours.

Weights and Capacities

The aircraft has a gross weight of 3000 lbs (1361 kg) and a standard empty weight of 1608 lbs (730 kg), resulting in a useful load of 1392 lbs (631 kg). Fuel capacity is two 38.5-gallon tanks, providing a usable fuel amount of 77 gallons (292 liters).

Performance Metrics

Maximum speed at gross weight is 148 knots (274 km/h). Cruising speeds vary with power settings: at 75% power, the speed is 139 knots (257 km/h), while at 65% power, it is 134 knots (248 km/h). The aircraft has a service ceiling of 17,500 feet (5334 m) and a rate of climb at sea level of 860 feet per minute (262 m/min).

Takeoff and Landing Distances

Takeoff distance at sea level with zero wind and standard temperature is 825 feet (251 m) for the ground run and 1725 feet (526 m) over a 50-foot obstacle. Landing distances are 640 feet (195 m) for the ground roll and 1530 feet (466 m) over a 50-foot obstacle.

Standard Equipment

Standard equipment includes a dual ignition Lycoming engine, Hartzell constant speed propeller, and various flight instruments such as an airspeed indicator, altimeter, and fuel quantity gauges. The aircraft also features dual flight controls and provisions for a vacuum pump.

Full document text

26/.74 Piper Aircraft Corporation Dakota PA 28-236 Specifications ENGINE Manufacturer Model Rating (hp @ rpm) Number of Cylinders Recommended TBO (hrs.) PROPELLER Manufacturer Number of Blades Type Diameter Lycoming 0-540-J3A5D 235 @ 2400 6 2000 Hartzell 2 Constant Speed 801203 WEIGHTS Gross Weight (Ibs'/kg) Standard Empty Weight (Ibs'/kg) (Includes unusable fuel, full oil and full operating fluids) Standard Useful Load (lbs'/kg) WING AREA AND LOADINGS Wing Area (ft.2/m2) Wing Loading (lbs'/ft.2)/(kg/m2) Power Loading (Ibs'/hp)/(kg/hp) DIMENSIONS Wing Span (ft./m) Length (ft.lm) Height (ft./m) Cabin Length (Instrument Panel to Rear Bulkhead) (in./cm.) Cabin Width (in./cm.) Cabin Height (in./cm.) Cabin Volume (ft.3/m3) (including luggage area) Headroom (seat to ceiling) Front Seats (in./cm.) Rear Seats (in./cm.) Baggage Door Size (in./cm) Cabin Door Size (in./cm) Wheel Base (ft./m) Wheel Tread (ft./m) FUEL CAPACITY Two 38.5 gal. tanks (gal./L) Usable Fuel (gal./L) OIL CAPACITY (qts./L) BAGGAGE Volume (ft.3/m3) (with 2 cu. ft. hat shelf) Capacity (Ibs'/kg) 3000/1361 16081730 1392/631 170/15.8 17.6/86.1 12.8/5.8 35.4/10.8 24.717.5 7.212.2 97.01246.4 41.5/105.4 49.0/124.5 106/3.0 36/91.4 36/91.4 22/55.9 x 20/50.8 36/91.4 x 35/88.9 6.5/1.98 10/3.05 771291 721273 12/11.36 200/91 Performance MAXIMUM SPEED (kts/kmh) (TAS at Gross Weight) CRUISING SPEEDS (TAS at Gross Weight) Optimum Altitude 75% power (kts./kmh) 65% power (kts./kmh) 55% power (kts./kmh) , 1481274 Best Power Best Economy 1441267 1381255 1301240 1391257 1341248 126/233 Best Power Best Economy 650/1204 710/1315 710/1315 770/1426 750/1390 810/1500 Best Power Best Economy 13.6/51.5 12.7/47.9 11.8/44.7 10.9/41.3 10.1/38.2 9.3/35.2 1110/338 IAS CAS 56/104 56/104 65/120 63/117 17,500/5334 Performance Continued CRUISE RANGE (Cruising range includes 45 minutes fuel reserve at maximum range power plus allowance for fuel used during taxi, take-off, climb at MCP, cruise at optimum altitude and stated mixture plus descent) 75% power (nm/km) 65% power (nm/km) 55% power (nm/km) FUEL CONSUMPTION 75% power (gph/lph) 65% power (gph/lph) 55% power (gph/lph) RATE OF CLIMB (At Sea Level and Gross Wt.) Full Throttle (fpm/mpm) STALL SPEED Flaps Down Full 40° (kts./kmh) Flaps Up (kts./kmh) SERVICE CEILING (100 fpm) (ft.lm) TAKE-OFF DISTANCE (Sea Level, zero wind, standard temperature) Ground Run (ft./m) Total over 50 ft. obstacle (ft./m) LANDING DISTANCE (Sea Level zero wind, standard temperature) Ground Roll (ft./m) Total over 50 ft. obstacle (ft./m) Standard Equipment POWER PLANT AND PROPELLER Engine - Lycoming 235 hp at 2400 rpm, direct drive, 6 cylinders dual ignition with radio shielding Engine Mount - Dynafocal with internal dampers Propeller - 1 Hartzell, 2 blade, constant speed Propeller Spinner Geared Starter, 12 volt Air Filter, dry type Oil Filter, full flow Oil Cooler Engine machined for vacuum pump (no drive installed) Dual Mufflers Cross-over Exhaust System Carburetor Heat with manual control Oil Quick Drain FLIGHT INSTRUMENT AND INDICATORS Piper Airspeed Indicator Magnetic Compass Sensitive Altimeter (in. and mb.) Ammeter Annunciator Panel with push-to-test Alternator inoperative Oil pressure low Gyro pressure low (with pump installed) Tachometer, recording Fuel Quantity Gauges, two Fuel Pressure Gauge Manifold Pressure Gauge Oil Temperature Gauge Oil Pressure Gauge Stabilator Trim Position Indicator Rudder Trim Position Indicator 8861270 1216/371 Std. Brakes H.D. Brakes 8251251 1725/526 640/195 1530/466 COCKPIT, FLIGHT AND GROUND CONTROLS Flight Primary - dual with rams horn type wheels. Provisions for elevator trim and mike button Flight Trim - lower floor Rudder Stabilator Engine Controls - pedestal Throttle Propeller Mixture Carburetor heat Engine Controls Friction Lock Dual Flight Controls Stall Warning Horn Cabin Heater and Defroster Controls Steerable Nosewheel, cushioned Brakes Pilot's toe brakes Co-pilot's toe brakes Parking brake Landing gear, fixed Landing Gear Strut Fairings Provisions for high speed wheel fairings Wing Flaps, four positions (0°, 10°,25° and 40°) Wing Flap Control, manual Fuel Control Selector - OFF, LEFT, RIGHT Engine Fuel Primer Cabin Fresh Air Vent Controls, four - individually controlled

All Piper PA-28 Dakota performance data