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Specifications/Performance Standard Equipment Saratoga/Turbo Saratoga PA 32-301/301T

Piper PA-32R Saratoga II HP · Specifications

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Overview

This document provides detailed specifications and performance data for the Piper PA-32R Saratoga II HP and its turbocharged variant, the PA-32R Turbo Saratoga II HP. It is intended for pilots, aviation enthusiasts, and maintenance personnel who require precise information about the aircraft's capabilities, dimensions, weights, and standard equipment. The specifications include engine details, performance metrics, weight and balance information, and cockpit features, ensuring users have a comprehensive understanding of the aircraft's operational parameters and equipment.

  • Engine: Lycoming IO-540-K1G5, 300 hp @ 2700 rpm
  • Maximum speed: 152 knots (282 km/h)
  • Cruise range: 745 nm (1380 km) at 75% power
  • Total fuel capacity: 107 gallons (405 L), usable: 102 gallons (386 L)
  • Standard empty weight: 1935 lbs (878 kg)

Document

Source

Originally published by brantaero.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

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Document details

Type
Specifications
Year
1983
Pages
4
File size
1.2 MB
Publisher
brantaero.com

Specifications & performance

Extracted from this document.

Specifications

Range (nm)
745
Engine (hp)
300
Height (ft)
8.2
Length (ft)
27.7
Propeller
Hartzell
Wingspan (ft)
36.2
Engine model
TIO-540-S1 AD
Max speed (kt)
178
Cruise speed (kt)
152
Empty weight (lb)
1,998
Fuel capacity (gal)
107
Rate of climb (fpm)
1,075
Service ceiling (ft)
20,000
Max takeoff weight (lb)
3,600

Performance

Fuel burn (gph)
18
Landing over 50ft
1,612
Takeoff over 50ft
1,759
Landing distance (ft)
732
Takeoff distance (ft)
1,183
Stall speed clean (kt)
62
Stall speed landing (kt)
58

V-speeds

VS1
62
VSO
58

Weight & balance

Useful load (lb)
1,619
Max ramp weight (lb)
3,617
Baggage allowance (lb)
100
Basic empty weight (lb)
1,998
Max landing weight (lb)
3,600
Max takeoff weight (lb)
3,600
Documentation completeness
2/7

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In this document

Engine Specifications

The Piper PA-32R Saratoga II HP is powered by a Lycoming IO-540-K1G5 engine, rated at 300 hp at 2700 rpm. The turbocharged variant, the PA-32R Turbo Saratoga II HP, uses a Lycoming TIO-540-S1AD engine, also rated at 300 hp at 2700 rpm. Both engines have a recommended TBO of 2000 hours for the Saratoga and 1800 hours for the Turbo Saratoga.

Weights and Dimensions

The ramp weight for the PA-32R Saratoga II HP is 3615 lbs (1639 kg), with a gross weight of 3600 lbs (1633 kg) and a standard empty weight of 1935 lbs (878 kg). The aircraft has a wingspan of 36.2 ft (11.0 m), a length of 27.7 ft (8.4 m), and a height of 8.2 ft (2.5 m). The cabin dimensions include a width of 49 in (124.5 cm) and a height of 42 in (106.7 cm).

Performance Data

The maximum speed of the Saratoga II HP is 152 knots (282 km/h) at gross weight. The aircraft achieves a cruise range of 745 nautical miles (1380 km) at 75% power and 805 nautical miles (1491 km) at 65% power. The stall speed with flaps down is 58 knots (107 km/h), and the service ceiling is 16,000 ft (4877 m), with the Turbo variant capable of exceeding 20,000 ft.

Fuel Capacity and Consumption

The total fuel capacity for both variants is 107 gallons (405 L), with 102 gallons (386 L) usable. Fuel consumption at 75% power is 18.0 gph (68 L/h) for the Saratoga and 19.9 gph (75.2 L/h) for the Turbo Saratoga.

Standard Equipment

Standard equipment includes a Lycoming engine, Hartzell constant speed propeller, dual flight controls, and a variety of flight instruments such as an airspeed indicator, altimeter, and fuel quantity gauges. The aircraft also features a cabin heater, defroster, and provisions for optional avionics.

Safety notes

  • Actual performance depends on pilot techniques and operating surfaces.
  • It is the pilot's responsibility to operate within approved limits of design gross weight and center of gravity.

Full document text

Piper Aircraft Corporation 1983 Specifications/Performance Standard Equipment Saratoga/Turbo Saratoga PA 32-301/301T Piper Aircraft Corporation Saratoga/Turbo Saratoga PA 32-301/301T Specifications Turbo Saratoga Saratoga ENGINE Manufacturer Lycoming Lycoming Model IO-540-K1 G5 TIO-540-S1 AD Rating (hp @ rpm) (Take-Off) 300@ 2700 300@2700 Rating (hp @ rpm) Continuous - 2 - B lade Prop 294@ 2600 294 @ 2575 Rating (hp @ rpm) Continuous- 3 - Blade Prop 300@ 2700 300 @2700 Number of Cylinders 6 6 Recommended TBO (hrs.) 2000 1800 PROPELLER Manufacturer Hartzell Hartzell Number of Blades 2 2 Type Constant Speed Constant Speed Diameter (in.!cm.) 801203 80/203 WEIGHTS Ramp Weight (Ibs.!kg) 3615/1639 3617/1640 Gross Weight (Ibs.!kg) 3600/1633 3600/1633 Standard Empty Weight (lbs.!kg) 1935/878 1998/906 (Includes unusable fuel. full oil and full operating fluids) (Ibs.!kg) Standard Useful Load (lbs.!kg) 1680/762 16191734 Zero Fuel Weight (lbs.!kg) 3600/1633 3600/1633 WING AREA AND LOADINGS Wing Area (ft.2lm2) 178.3/16.6 178.3/16.6 Wing Loading (lbs.!ft.2)1(kg/m2) 20.2/98.7 20.2/98.7 Power Loading (Ibs.!hp)/(kg/hp) 12.0/5.5 12.0/5.5 DIMENSIONS Wing Span (ft.!m) 36.2/11.0 36.2/11.0 Length (ft.!m) 27.7/8.4 28.2/8.6 Height (ft.!m) 8.212.5 8.212.5 Cabin Length (Instrument panel to rear bulkhead) (in.!cm.) 124.25/315.6 124.25/315.6 Cabin Width (in.!cm) 49/124.5 49/124.5 Cabin Height (in.!cm) 42/106.7 421106.7 Headroom (Seat to Ceiling) Front Seats (in.!cm.) 38/96.5 38/96.5 Middle Seats (in.!cm) 35.75/90.8 35.75/90.8 Rear Seats (in.!cm) 34.5/87.6 34.5/87.6 Forward Baggage Door Size (in.!cm) 16/40.6 x 22/55.9 16/40.6 x 22/55.9 Aft Baggage/Utility Door Size (in.! cm) 20.5/52.1 x 26/66.0 20.5/52.1 x 26/66.0 Forward Cabin Door Size (in.!cm) 35/88.9 x 36/91.4 35/88.9 x 36/91.4 Aft Cabin Door Size (in.! em) 28.5/72.4 x 28/71.1 28.5/72.4 x 28/71 .1 Wheel Base (ft.!m) 7.7512.4 7.75/2.4 Wheel Tread (ft.!m) 10.6/3.2 10.6/3.2 FUEL CAPACITY Total Capacity (gal./L) 107/405 107/405 Usable Fuel (gal./L) 102/386 102/386 OIL CAPACITY (qts.!L) 12/11.35 12111.35 BAGGAGE Volume (ft.3/m3) Forward Compartment 8/.23 8/.23 Aft Compartment 17.3/.49 17.3/.49 Capacity (Ibs.!kg) Forward Compartment 100/45.4 100/45.4 Aft Compartment 100/45.4 100/45.4 150/278 146/270 136/252 148/274 144/266 133/246 165/306 154/285 139/258 160/296 148/274 132/245 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) CRUISE RANGE (Cruising range includes 45 minute 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) 152/282 Turbo Saratoga 178/329 (1) 182/336 (2) Saratoga Best Power Best Economy Best Power Best Economy Best Power Best Eco nomy Best Power Best Economy 75% power (nm/km) 745/1380 823/1524 684/1267 780/1445 65% power (nm/km) 805/1491 911/1687 730/1353 845/1566 55% power (nm/km) 849/1572 960/1778 772/1431 860/1594 FUEL CONSUMPTION Best Power Best Economy Best Power Best Economy 75% power (gph/Lph) 18.0/68 16.0/61 19.9/75.2 16.5/62.5 65% power (gph/Lph) 16.0/61 13.8/52 17.2/65.2 14.0/52.9 55% power (gph/Lph) 14.0/53 11.9/45 14.6/55.3 12.3/46.6 RATE OF CLIMB (At Sea Level and Gross Wt.) Full Throttle (fpm/mpm) 990/302 1075/328 STALL SPEED IAS CAS IAS CAS Flaps Down Full 40° (kts./kmh) 58/107 60/111 58/107 60/111 Flaps Up (kts'/kmh) 62/114 66/122 62/115 67/124 SERVICE CEILING (100 fpm) (ft./m) 16,000/4877 *20,000+/6096+ TAKE-OFF DISTANCE 2-Blade 3-Blade 2-Blade 3-8 lade (Sea Level, zero wind, standard temperature) Ground Run (ft./m) 1183/361 1013/309 1110/338 960/293 Total over 50 ft. Obstacle (ft./m) 1759/536 1573/479 1590/485 1420/433 LANDING DISTANCE Std. Brakes H.D. Brakes Std. Brakes H.D. Brakes (Sea Level, zero wind, standard temperature) Ground Roll (ft./m) 732/223 650/198 732/223 650/198 Total over 50 ft. Obstacle (ft./m) 1612/491 1530/466 1725/526 1640/500 *20,000 feet is maximum approved altitude for Turbo Saratoga Standard Equipment (1) 2-Blade Prop. (2) 3-Blade Prop. POWER PLANT AND PROPELLER Engine - Lycoming 300 hp at 2700 rpm, direct drive, six cylinders, fuel injection, dual ignition with shielding (1) Lycoming 300 hp at 2700 rprn, turbocharged, fuel injection, six cylinders, direct drive, dual ignition with shielding (2) Engine Mounts - Dynafocal with internal dampers Propeller - Hartzell, 2 blade, constant speed Propeller Spinner Geared Starter, 12 volt Air Filter, dry type Oil Filter, full flow Oil Cooler with thermostatic control - two (1), one (2) Engine machined for vacuum pump (no drive installed) Muffler and Exhaust System Alternate Air with manual control Oil Ouick Drain FLIGHT INSTRUMENTS 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 vacuum low (with pump installed) Over boost (2) Tachometer, recording Fuel Ouantity Gauges, two Fuel Pressure Gauge (1) Manifold/Fuel Flow Gauge Oil Temperature Gauge Oil Pressure Gauge Cylinder Head Temperature Gauge (2) Exhaust Gas Temperature Gauges (EGT) (2) Stabilator Trim Position Indicator Rudder Trim Position Indicator Power Setting Table on Sun Visor Compass Card Compass Card Holder Weight and Balance Plotter Takeoff/Landing Check Lists on Sun Visor Pilot's Operating Handbook Aircraft Log Book Engine Log Book Certificate of Airworthiness Standard Equipment Continued 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, with' lock Alternate air Engine Controls Friction Lock Dual Flight Controls Stall Warning Horn Cabin Heater and Defroster Controls Steerable Nosewheel Brakes Pilot's toe brakes Copilot's toe brakes Parking brake Landing Gear, fixed

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Landing Gear Strut Fairings Wing Flaps, four positions (0°,10°,25° and 40°) Wing Flap Control, manual Fuel Control Selectors with OFF/LEFT/RIGHT Cabin Fresh Air Vent Controls, six - individually controlled, overhead ELECTRICAL PROVISIONS 14 volt, Alternator ~ 60 amp 12 volt, 25 amp Hour Battery Master Switch Relay Voltage Regulator Overvoltage Relay Resettable-type Circuit Breakers Basic Wiring Rocker Switches, conveniently grouped on pilot's 'waterfall' panel Ammeter, shunted type Provision for External Power Supply Receptacle Circuit Breaker Panel AVIONICS PROVISIONS Circuit Breaker Panel Provisions for Automatic Locator Beacon Wide selection of Optional Avionics available FUEL SYSTEM Four Fuel Tanks with 107 gallons total capacity, 102 gallons usable, mechanically interconnected per side Engine Driven Fuel Pump Electric Auxiliary Fuel Pump Fuel Quantity Sight Gauge, inboard tanks - two Fuel Tank Quick Drains, four Fuel System Central Drain Fuel Sampling Bottle LIGHTING PROVISIONS Large selection of optional internal and external lighting has been made available CABIN COMFORT SYSTEM Heater Muff provides heat to cabin area regulated by control on copilot instrument panel with six floor heat outlets Heat Regulating Levers - located at each passenger seat Windshield Defrosters Cabin Air Exhaust Vents, two Cabin Fresh Air Vents, six - individually controlled, overhead and four - individually controlled, floor mounted EXTERNAL FEATURES Three Tone Exterior Paint Design, in a wide choice of color combinations 12" registration number Cabin Doors, two - right forward and left rear Main Wheels, 6.00 x 6 with 6.00 x 6 tires with tubes, 8 ply rating Nose Wheel, 5.00 x 5 with 5.00 x 5 tire with tube, 6 ply rating Aircraft Brakes Stowable Towbar Tie Down Rings, three Jack Pads Meets FAR Part 36 noise requirements Cabin and Rear Cabin Door Locks with keys Nose Baggage Door with flush lock with key Utility Door, rear baggage access and cargo loading COCKPIT AND CABIN APPOINTMENTS AND PROVISIONS Choice of five interior colors, which includes: fabric and vinyl seats, vinyl side panels, wall to wall carpeting and headliner Upholstery - all seats of Scotchguarded, nylon fabrics with side paneling of 'soft hand' vinyls Pilot/Copilot Seats - fabric and vinyl with magazine storage pockets on back of each seat - seats adjust fore and aft and reclining, with inertia reel shoulder and safety belts Armrests - crew area, two Ash Trays - crew area, two Map Pockets, two Storm Window, pilot Glove Compartment with rollaway door Scuff Pads, pilot and copilot Two Piece Windshield Sun Visors, two Door Closing Straps, two (fore and aft cabin doors) Four Rear Passenger Seats - fabric and vinyl with reclining feature, seat belts, side panel ash trays - incorporates quick release feature for easy removal Provisions for Vertically Adjustable Pilot and Copilot Seats Soundproofing Ignition Lock with key Locks with keys, fore and aft cabin and nose baggage Luggage Compartments with security straps Rear cabin and hat shelf area, 17.3 cu. ft. - 100 Ibs. Fuselage nose, 8.0 cu. ft. - 100 Ibs. The performance information is based on an airplane flown at gross weight under standard sea level atmospheric conditions except as noted and based on the latest data available at the time of publication approval. Take-off and landing performance is optimum. Actual performance depends on pilot techniques, operating surfaces and other factors. It is the responsibility of the pilot to determine that all operations are conducted within approved limits of design gross weight, center of gravity, and in accordance with the FAA-approved Airplane Flight Manual which is the only official source of operating parameters and performance information. In accordance with GAMA format, range provides for taxi, take-off, climb at MCP, cruise at stated mixture and descent with 45-minute reserve at maximum range power, Empty weight in- cludes unusable fuel, full operating fluids and full oil. Piper Aircraft Corporation reserves the right to make changes in specifications, materials, equipment or prices at any time without prior notice or to discontinue models as required. Your Piper Dealer has listings of a wide variety of optional equipment and avionics. Items most frequently chosen by owners are packaged for factory installation at substantial price savings. 995-3-227 10/1/82 Printed in USA PRODUCT SUPPORT Piper Warranty Form Piper Service Center Directory Inspection Forms (1) SARATOGA (2) TURBO SARATOGA MORE AIRPLANE FOR THE DOLLAR 111I PIPER AIRCRAFT CORPORATION LOCK HAVEN, PENNSYLVANIA 17745 @ a BA,!GOR PUNTA Company e MEMBER OF GAMA