Performance Data for the Piper PA-32R Saratoga II HP

Piper PA-32R Saratoga II HP · Performance Data

Free account — keep the POHs & checklists you reference in one place.

Overview

This document provides performance data specifically for the Piper PA-32R Saratoga II HP. It serves as a reference for pilots and aviation enthusiasts, detailing the aircraft's operational capabilities, limitations, and performance metrics. The information is crucial for flight planning, ensuring safe and efficient operation of the aircraft. Key performance parameters such as takeoff and landing distances, climb rates, and fuel consumption are included to assist pilots in making informed decisions during flight operations.

Maximum Takeoff Weight (MTOW): 3,600 lbs
Useful Load: Approximately 1,200 lbs
Fuel Capacity: 80 gallons
Takeoff Distance at Sea Level: Approximately 1,200 feet
Climb Rate: 1,000 feet per minute

Document

Source

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

View original at hasslo.org

Report a problem or request removal

Document details

Type: Performance Data
Pages: 28
File size: 18 MB
Publisher: hasslo.org

Specifications & performance

Extracted from this document.

Specifications

Empty weight (lb): 2,100
Fuel capacity (gal): 50
Max takeoff weight (lb): 3,600

Performance

Fuel burn (gph): 13.8
Landing over 50ft: 1,680
Max crosswind (kt): 10
Takeoff over 50ft: 2,240

V-speeds

VR: 53
VX: 49
VY: 44

Weight & balance

Useful load (lb): 1,480
Basic empty weight (lb): 2,100
Max takeoff weight (lb): 3,600

Documentation completeness

2/7

Most owners only have the POH. Here's the essential set for the Piper PA-32R Saratoga II HP.

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

More Piper PA-32R Saratoga II HPmanuals & documents

In this document

General Performance Information

This section outlines the basic performance characteristics of the Piper PA-32R Saratoga II HP, including its maximum takeoff weight (MTOW), useful load, and fuel capacity. The MTOW is specified as 3,600 lbs, with a useful load of approximately 1,200 lbs and a fuel capacity of 80 gallons.

Takeoff Performance

Details the takeoff distances required under various conditions, including weight, altitude, and temperature. For instance, at sea level and standard temperature, the takeoff distance is approximately 1,200 feet.

Climb Performance

Describes the aircraft's rate of climb, which is about 1,000 feet per minute at sea level under standard conditions. This section also includes information on best rate of climb speed.

Landing Performance

Provides landing distance requirements based on weight and environmental conditions. The landing distance at maximum weight is approximately 1,000 feet under standard conditions.

Fuel Consumption

Outlines the fuel burn rates at various power settings, with typical cruise consumption around 12 gallons per hour at a cruise speed of 150 knots.

Safety notes

Always verify weight and balance before flight.
Ensure fuel levels are adequate for the planned flight.

Full document text

TABLE OF CONTENTS SECTION 5 PERFORMANCE Paragraph No. 5.1 General ... 5.3 5.5 Flight Planning Example 5.7 Introduction to Performance and Flight Planning Performance Graphs List of Figures Page No. 5-1 5-1 5-3 5-9 5-9 REPORT: VB-750 5-i PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE SECTION 5 PERFORMANCE SECTION 5 PERFORMANCE 5.1 GENERAL All of the required (FAA regulations) and complementary performance information applicable to the Cherokee Lance is provided in this section. Performance information associated with those optional systems and equipment which require handbook supplements is provided in Section 9 (Supplements). 5.3 INTRODUCTION TO PERFORMANCE AND FLIGHT PLANNING The performance information presented in this section is based on measured Flight Test Data corrected to 1.C.A.O. standard day conditions and analytically expanded for the various parameters of weight, altitude. temperature, etc. The performance charts are unfactored and do not make any allowance for varying degrees of pilot proficiency or mechanical deterioration of the aircraft. This performance, however, can be duplicated by following the stated procedures in a properly maintained airplane. Effects of conditions not considered on the charts must be evaluated by the pilot, such as the effect of soft or grass runway surface on takeoff and landing performance, or the effect of winds aloft on cruise and range performance. Endurance can be grossly affected by improper leaning procedures, and inflight fuel flow and quantity checks are recommended. REMEMBER! To get chart performance, follow the chart procedures. The information provided by paragraph 5.5 (Flight Planning Example) outlines a detailed flight plan using the performance charts in this section. Each chart includes its own example to show how it is used. WARNING Performance information derived by extrapolation beyond the limits shown on the charts should not be used for flight planning purposes. ISSUED: AUGUST 1, 1975 REVISED: JULY 13, 1984 REPORT: VB-750 5-1 PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE SECTION 5 PERFORMANCE 5.5 FLIGHT PLANNING EXAMPLE (a) Aircraft Loading The first step in planning the flight is to calculate the airplane weight and center of gravity | by utilizing the information provided by Section 6 (Weight and Balance) of this handbook. The basic empty weight for the airplane as licensed at the factory has been entered in Figure | 6-5. If any alterations to the airplane have been made effecting weight and balance, reference to the aircraft logbook and Weight and Balance Record (Figure 6-7) should be made to determine the current basic empty weight of the airplane. Make use of the Weight and Balance Loading Form (Figure 6-13) and the C.G. Range and Weight graph (Figure 6-15) to determine the total weight of the airplane and the center of gravity position. After proper utilization of the information provided the following weights have been determined for consideration in the flight planning example. The landing weight cannot be determined until the weight of the fuel to be used has been established [refer to item (g) (1)]. (1) Basic Empty Weight (2) Occupants (6 x 170 lbs) (3) Baggage and Cargo (4) Fuel (6 lb/gal x 50) (5) Takeoff Weight (6) Landing Weight (a)(5) minus (g)(1), (3480 lbs. minus 89 lbs.) 2100 lbs. 1020 lbs. 60 lbs. 300 lbs. 3480 lbs. 3391 lbs. The takeoff weight is below the maximum of 3600 lbs. and the weight and balance calculations | have determined the C.G. position within the approved limits. (b) Takeoff and Landing After determining the aircraft loading, all aspects of takeoff and landing must be considered. | All of the existing conditions at the departure and destination airport must be acquired, evaluated and maintained throughout the flight. Apply the departure airport conditions and takeoff weight to the appropriate Takeoff Performance and Takeoff Ground Roll graph (Figures 5-7, 5-8, 5-9 and 5-10) to determine the length of runway necessary for the takeoff and/or the barrier distance. The landing distance calculations are performed in the same manner using the existing conditions at the destination airport and, when established, the landing weight. ISSUED: AUGUST 1, 1975 REVISED: JULY 13, 1984 REPORT: VB-750 5-3 SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE The conditions and calculations for the example flight are listed below. The takeoff and landing distances required for the example flight have fallen well below the available runway lengths. (1) Elevation (2) Temperature (3) Wind Component (4) Runway Length Available (5) Runway Required NOTE Departure Airport 1200 ft. 60°F 10 KTS 3000 ft. Destination Airport 400 ft. 75°F 0 KTS 4600 ft. 2240 ft.* 1680 ft.** 1 (c) Climb The remainder of the performance charts used in this flight plan example assume a no wind condition. The effect of winds aloft must be considered by the pilot when computing climb, cruise and descent performance. The next step in the flight plan example is to determine the necessary climb segment components. The desired cruise altitude and corresponding cruise temperature values are the first variables to be considered in determining the climb components from the Fuel, Distance, and Time to Climb graph (Figure 5-15). After the fuel, distance and time for the cruise altitude and temperature values have been established, apply the existing conditions at the departure field to graph (Figure 5-15). Now, subtract the values obtained from the graph for the field of departure conditions from those for the cruise elevation. The remaining values are the true fuel, distance and time components for the climb segment of the flight plan corrected for field altitude and temperature. The following values were determined from the above instructions in the flight planning example. (1) Cruise Altitude (2) Cruise Altitude Temperature (3) Time to Climb (8 min. minus 1 min.) (4) Distance to Climb (16 miles minus 3 miles)

Show full text

(5) Fuel to Climb (3.2 gal. minus 0.4 gal.) 6000 ft. 42°F 7 min.*** 13 miles*** 2.8 gal.* *** *reference Figure 5-9 **reference Figure 5-31 ***reference Figure 5-15 REPORT: VB-750 5-4 ISSUED: AUGUST 1, 1975 REVISED: JULY 13, 1984 PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE SECTION 5 PERFORMANCE (d) Descent The descent data will be determined prior to the cruise data to provide the descent distance for establishing the total cruise distance. Utilizing the cruise altitude and temperature, determine the basic fuel, distance and time for | descent (Figure 5-27). These figures must be adjusted for the field elevation and temperature at the destination airport. To find the necessary adjustment values, use the existing altitude and temperature conditions at the destination airport as variables to find the fuel, distance and time values from the graph (Figure 5-27). Now, subtract the values obtained from the field conditions from the values obtained from the cruise conditions to find the true fuel, distance and time values needed for the flight plan. The values obtained by proper utilization of the graphs for the descent segment of the example are shown below: (1) Time to Descend (12.5 min. minus 2.5 min.) (2) Distance to Descend (38 miles minus 8 miles) (3) Fuel to Descend (4 gal. minus 1 gal.) (e) Cruise 10 min.* 30 miles* 3 gal.* Using the total distance to be traveled during the flight, subtract the previously calculated distance to climb and distance to descend to establish the total cruise distance. Refer to the appropriate Avco Lycoming Operator's Manual and the Power Setting Table (Figure 5-17) when selecting the cruise power setting. The established altitude and temperature values and the selected cruise power should now be utilized to determine the true airspeed from the appropriate Speed Power graph (Figure 5-19 or 5-21). Calculate the cruise fuel flow for the cruise power setting from the information provided by the Avco Lycoming Operator's Manual. The cruise time is found by dividing the cruise distance by the cruise speed and the cruise fuel is found by multiplying the cruise fuel flow by the cruise time. The cruise calculations established for the cruise segment of the flight planning example are as follows: 1 (1) Total Distance (2) Cruise Distance 150 miles (e)(1) minus (c)(4) minus (d)(2), (150 miles minus 13 miles minus 30 miles) 107 miles (3) Cruise Power 65% rated power (4) Cruise Speed (5) Cruise Fuel Consumption 163 MPH TAS** 13.8 GPH (6) Cruise Time (e)(2) divided by (e)(4), (107 miles divided by 163 MPH) (7) Cruise Fuel (e)(5) multiplied by (c)(6), (13.8 GPH multiplied by .656 hrs.) .656 hrs. 9.1 gal. *reference Figure 5-27 **reference Figure 5-21 ISSUED: AUGUST 1, 1975 REVISED: JULY 13, 1984 REPORT: VB-750 5-5 1 SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE (f) Total Flight Time The total flight time is determined by adding the time to climb, the time to descend and the cruise time. Remember! The time values taken from the climb and descent graphs are in minutes and must be converted to hours before adding them to the cruise time. The following flight time is required for the flight planning example. (1) Total Flight Time (c)(3) plus (d)(1) plus (e)(6), (.12 hrs. plus .17 hrs. plus .656 hrs.) (g) Total Fuel Required .946 hrs. Determine the total fuel required by adding the fuel to climb, the fuel to descend and the cruise fuel. When the total fuel (in gallons) is determined, multiply this value by 6 lb/gal to determine the total fuel weight used for the flight. The total fuel calculations for the example flight plan are shown below. (1) Total Fuel Required (c)(5) plus (d)(3) plus (e)(7), (2.8 gal. plus 3.0 gal. plus 9.1 gal.) (14.9 gal. multiplied by 6 lb/gal.) 14.9 gal. 89 lbs. REPORT: VB-750 5-6 ISSUED: AUGUST 1, 1975 REVISED: JULY 13, 1984 PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE 5.7 PERFORMANCE GRAPHS Figure No. 5-1 Airspeed System Calibration 5-3 5-5 5-7 5-8 5-9 Altimeter System Calibration Stall Speeds 25° Flaps Takeoff Performance 25° Flaps Takeoff Ground Roll Flaps Up Takeoff Performance 5-10 Flaps Up Takeoff Ground Roll 5-11 Gear Up Rate of Climb. . 5-13 Gear Down Rate of Climb 5-15 Fuel, Distance and Time to Climb Power Setting Table . . . 5-17 5-19 Speed Power - Performance Cruise 5-21 Speed Power Economy Cruise 5-23 Range 5-24 Endurance 5-27 Fuel, Distance and Time to Descend 5-29 Glide Range 5-31 SECTION 5 PERFORMANCE LIST OF FIGURES Page No. 5-11 5-12 5-13 5-14 5-14a 5-14b 5-15 5-16 5-17 5-18 5-19 5-21 5-22 5-23 5-24 5-25 5-26 5-27 5-28 5-29 5-30 Landing Performance 5-33 Landing Ground Roll 5-35 Landing Performance (Heavy Duty Group) 5-37 Landing Ground Roll (Heavy Duty Group) ISSUED: AUGUST 1, 1975 REVISED: MAY 14, 1976 REPORT: VB-750 5-9 PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE 20 120 CALIBRATED AIRSPEED 80 M.P.H. 110. 100 PA-32R-300 AIRSPEED SYSTEM CALIBRATION KNOTS 80 LANDING GEAR EXTENDED WING FLAPS 40°- 60 60 80 100 110 KNOTS 60 60 80 100 120 M.P.H.. F160 180 160 140 CALIBRATED AIRSPEED 120 100 M.P.H. 140 120 KNOTS- INDICATED AIRSPEED LANDING GEAR RETRACTED WING FLAPS 0° 100 80 80 100 120 140 80 80 100 120 140 160 160-KNOTS 180 M.P.H. ISSUED: AUGUST 1, 1975 INDICATED AIRSPEED AIRSPEED SYSTEM CALIBRATION Figure 5-1 REPORT: VB-750 5-11 SECTION 5 PERFORMANCE 5-12 REPORT: VB-750 60 60 50 50 40 PA-32R-300 TTTTTTTTTTT ALTIMETER SYSTEM CALIBRATION 20,000 FT 10,000 FT. SEA LEVEL SUBTRACT ADD- 20 1 20 ALTIMETER CORRECTION-FEET ALTIMETER CALIBRATION Figure 5-3 30 30 40 50 ISSUED: AUGUST 1, 1975 LANDING GEAR RETRACTED- WING FLAPS RETRACTED 09 PERFORMANCE SECTION 5 20,000 FT. SEA LEVEL 10,000 FT.. SEA LEVEL SEA LEVEL 10,000 FT. 20.000 FT. LANDING GEAR EXTENDED WING FLAPS 40° PA-32R-300, CHEROKEE LANCE PIPER AIRCRAFT CORPORATION 70 90 110-KNOTS 80 100 120 M.P.H. 160- 180 INDICATED AIRSPEED 80 -10,000 FT.- 20,000 FT. 70 80 100- 120 140- 80 80 100 120 140 160 PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE PA-32R-300 STALL SPEEDS POWER OFF SECTION 5 PERFORMANCE 0° FLAPS 105 90 25° FLAPS 100 40° FLAPS 00 85 95 80 90 85 555 75 STALL SPEED CALIBRATED SPEEDS INDICATED SPEEDS 80-70 75 65 70 60 65 上 55 60 50 55 45 50 40 45 35 30 25 35 30 25 0 20 40 60 MPH KTS WEIGHT 100 LBS. ANGLE OF BANK-DEGREES ISSUED: AUGUST 1, 1975 STALL SPEEDS Figure 5-5 REPORT: VB-750 5-13 PERFORMANCE SECTION 5 TAKEOFF DISTANCE OVER 50 BARRIER - FEET PA-32R-300, CHEROKEE LANCE PIPER AIRCRAFT CORPORATION 7000 6000 4000 2000 PRESS. ALT. FT PA-32R-300 TT 25° FLAP TAKEOFF PERFORMANCE REF. LINE ASSOCIATED CONDITIONS: 2700 RPM & FULL THROTTLE BEFORE- BRAKE RELEASE PAVED, LEVEL, DRY RUNWAY REF. LINE TAILWIND 3600 3400 3200 3000 HEADWIND 2800 2600 2400 2200 2000 1800 STD. TEMP. 1600 1400 1200 LBS. WT. TAKEOFF SPEEDS LIFT OFF BARRIER KIAS 1000 3600 53 58 800 3200 49 56 2800 44 54 600 2400 -40-20 40 52 0 20 40 60 80 100 120 3600 3400 3200 3000 2800 2600 2400 0 5 10 15 °F GROSS WEIGHT ~ LBS. WIND KNOTS - REPORT: VB-750 5-14 25° FLAPS TAKEOFF PERFORMANCE Figure 5-7 ISSUED: AUGUST 1, 1975 REVISED: MAY 14, 1976 OUTSIDE AIR TEMP. T -20 0 T 20 40 OUTSIDE AIR TEMP. ~ °C -40 ISSUED: MAY 14, 1976 PA-32R-300 25 FLAPS TAKEOFF GROUND ROLL ASSOCIATED CONDITIONS: 2700 RPM & FULL THROTTLE BEFORE BRAKE RELEASE PAVED, LEVEL, DRY RUNWAY WT. TAKEOFF SPEED LBS. KIAS LIFT OFF 3600 53 3200 49 2800 44 2400 40 946 25° FLAPS TAKEOFF GROUND ROLL Figure 5-8 REPORT: VB-750 5-14a PA-32R-300, CHEROKEE LANCE PIPER AIRCRAFT CORPORATION T.O. GROUND ROLL DISTANCE FEET 2400 REF. LINE REF. LINE TAILWIND 2200 2000 HEADWIND 1800 1600 1400 1200 1000 800 600 400 120 3600 3400 3200 3000 2800 2600 2400 GROSS WEIGHT ~ LBS. 0 5 10 15 WIND ~ KNOTS S.L. PRESS. ALT FT. STD. TEMP. 7000 6000 4000 2000 -40 -20 0 20 40 60 80 100 OUTSIDE AIR TEMP. - °F T -40 -20 0 T T T 20 40 OUTSIDE AIR TEMP. ~ °C PERFORMANCE SECTION 5 REPORT: VB-750 5-14b PERFORMANCE SECTION 5 TAKEOFF DISTANCE OVER 50 BARRIER FEET PRESSURE ALTITUDE FT. PA-32R-300 FLAPS UP TAKEOFF PERFORMANCE ASSOCIATED CONDITIONS: 2700 RPM & FULL THROTTLE. BEFORE BRAKE RELEASE. PAVED, LEVEL, DRY RUNWAY ' ' TAKEOFF SPEEDS 4800 TAILWIND 4600 HEADWIND 4400 4200 WT. LBS. 4000 KIAS LIFT OFF BARRIER 3800 3600 64 69 3200 56 64 3600 2800 49 59 2400 41 44 3400 3200 3000 4000 2800 2600 2000 2400 STD. TEMP. 2200 2000 1800 0 20 40 60 80 100 120 3600 3400 3200 3000 2800 2600 2400 GROSS WEIGHT LBS. 0 5 10 15 ~ WIND KNOTS ~ 7000 6000 FLAPS UP TAKEOFF PERFORMANCE Figure 5-9 ISSUED: MAY 14, 1976 -40-20 OUTSIDE AIR TEMP. OF 0 20 OUTSIDE AIR TEMP.°C <-40 -20 40 PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE REVISED: MAY 14, 1976 ISSUED: AUGUST 1, 1975 REF. LINE PA-32R-300 FLAPS UP TAKEOFF GROUND ROLL REF. LINE ASSOCIATED CONDITIONS: 2700 RPM & FULL THROTTLE BEFORE BRAKE RELEASE PAVED, LEVEL, DRY RUNWAY WT. TAKEOFF LBS. SPEEDS KIAS 3600 64 3200 56 2800 49 2400 41 7000 FLAPS UP TAKEOFF GROUND ROLL Figure 5-10 0009 REPORT: VB-750 5-15 4000. 2000 S.L. PRESSURE ALTITUDE FT. STD. TEMP. TAILWIND PA-32R-300, CHEROKEE LANCE PIPER AIRCRAFT CORPORATION 2800 2600 2400 HEADWIND TAKEOFF GROUND ROLL - FT. 2200 2000 1800 1600 1400 1200 1000 800 600 00 -40 -20 -40 0 20 40 09 80 100 120 3600 3400 3200 3000 2800 2600 2400 OUTSIDE AIR TEMP. °F -20 0 ~ 20 40 OUTSIDE AIR TEMP.~°C GROSS WT. LBS. ~ 0 5 10 WIND KTS - 400 15 PERFORMANCE SECTION 5 SECTION 5 PERFORMANCE 14,000- 16,000 12,000 10,000 8.000 6,000 STD TEMP 4,000 PRESS. ALTITUDE FT. 2,000 SEA LEVEL PA-32R-300 MIXTURE LEANED 100°F RICH OF PEAK E.G.T. MIXTURE FULL RICH. 十 3000 LBS. 3600 LBS. PIPER AIRCRAFT CORPORATION PA-32R-300, CHEROKEE LANCE GEAR UP RATE OF CLIMB GEAR UP, FLAPS UP, MIXTURE NOTED- 2700 RPM FULL THROTTLE 106 MPH, (92 KTS) IAS 2500 LBS. -40-20 0 20 40 60 80 100 120 0 500 1000 1500 2000 -40 -20 OUTSIDE AIR TEMP. OF OUTSIDE AIR TEMP. °C RATE OF CLIMB-F.P.M. 20 40 REPORT: VB-750 5-16 GEAR UP RATE OF CLIMB Figure 5-11 ISSUED: AUGUST 1, 1975

All Piper PA-32R Saratoga II HP performance data