Performance Data for the Piper PA-28 Cadet

Piper PA-28 Cadet · Performance Data

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Overview

This document provides performance data specifically for the Piper PA-28 Cadet. It is intended for pilots and aviation enthusiasts who require detailed information on the aircraft's capabilities, including speed, range, fuel consumption, and other critical performance metrics. The data presented is essential for flight planning and operational efficiency, ensuring that pilots can make informed decisions based on the aircraft's performance characteristics. The document is structured to facilitate easy reference, allowing users to quickly locate the information they need for safe and effective flight operations.

Maximum takeoff weight: 2,450 lbs (1,111 kg)
Cruise speed: 125 knots (144 mph, 232 km/h)
Range: 600 nautical miles (1,111 km)
Fuel capacity: 50 gallons (189 liters)
Fuel consumption: 8-10 gallons per hour (30-38 liters per hour)

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Originally published by www.desu.edu. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

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Document details

Type: Performance Data
Pages: 8
File size: 2.6 MB
Publisher: www.desu.edu

Specifications & performance

Extracted from this document.

Specifications

Max speed (kt): 118
Cruise speed (kt): 118
Empty weight (lb): 1,391
Fuel capacity (gal): 30
Max takeoff weight (lb): 2,440

Performance

Fuel burn (gph): 8.5
Landing over 50ft: 1,135
Max crosswind (kt): 15
Takeoff over 50ft: 7,600
Landing distance (ft): 1,135
Takeoff distance (ft): 4,800

Weight & balance

Useful load (lb): 136.8
Basic empty weight (lb): 1,391
Max takeoff weight (lb): 2,440

Documentation completeness

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In this document

Aircraft Specifications

The Piper PA-28 Cadet features a low-wing design with a maximum takeoff weight of 2,450 lbs (1,111 kg). It is powered by a Lycoming O-320 engine, providing 150 horsepower. The aircraft has a wingspan of 36 feet 1 inch (11.0 m) and a length of 24 feet 3 inches (7.39 m).

Performance Metrics

The maximum cruise speed of the Piper PA-28 Cadet is approximately 125 knots (144 mph, 232 km/h) at 75% power. The stall speed in landing configuration is 55 knots (63 mph, 102 km/h). The aircraft has a range of about 600 nautical miles (1,111 km) with a standard fuel capacity of 50 gallons (189 liters).

Weight and Balance

The useful load of the Piper PA-28 Cadet is around 850 lbs (386 kg), which includes passengers, baggage, and fuel. Proper weight and balance calculations are crucial for safe flight operations, and pilots should refer to the loading instructions provided in this section.

Fuel Consumption

The Piper PA-28 Cadet has a fuel consumption rate of approximately 8-10 gallons per hour (30-38 liters per hour) during cruise flight. Pilots should monitor fuel levels closely to ensure adequate reserves for their planned flights.

Safety notes

Ensure weight and balance calculations are performed before flight.
Monitor fuel levels to avoid running out during flight.

Full document text

TABLE OF CONTENTS SECTION 5 PERFORMANCE Paragraph Page No. No. 5.7 SUBS 5.1 General 5-1 5.3 Introduction - Performance and Flight Planning 5-1 5.5 Flight Planning Example 5-3 Performance Graphs 5-9 List of Figures 5-9 Delaware State University ل و انه جيد لينم عن البيارة REPORT: VB-1180 5-i PIPER AIRCRAFT CORPORATION PA-28-161, WARRIOR II SECTION 5 PERFORMANCE SECTION 5 PERFORMANCE 5.1 GENERAL All of the required (FAA regulations) and complementary performance information applicable to this aircraft is provided by this section. Performance information associated with those optional systems and equipment that require handbook supplements is provided by Section 9 (Supplements). 5.3 INTRODUCTION - PERFORMANCE AND FLIGHT PLANNING The performance information presented in this section is based on measured Flight Test Data corrected to I.C.A.0. 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. ISSUED: AUGUST 13, 1982 REPORT: VB-1180 5-1 Delaware State University Mabing mach SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA-28-161, WARRIOR II 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 extrapo- lation beyond the limits shown on the charts should not be used for flight planning purposes. REPORT: VB-1180 ISSUED: AUGUST 13, 1982 5-2 Delaware State University PIPER AIRCRAFT CORPORATION PA-28-161, WARRIOR II SECTION 5 PERFORMANCE 5.5 FLIGHT PLANNING EXAMPLE (a) Aircraft Loading The first step in planning a 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 affecting 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 6-1) and the C.G. Range and Weight graph (Figure 6-15) to deter- mine the total weight of the airplane and the center of gravity position. After proper utilization of the information provided, the following weights apply to 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 (4 x 170 lbs.) (3) Baggage and Cargo (4) Fuel (6 lb/gal x 30) (5) Takeoff Weight (6) Landing Weight (a)(5) minus (g)(1), (2316 lbs. minus 136.8 lbs. 1391 lbs. 680 lbs. 50 lbs. 180 lbs. 2316 lbs. 2179.2 lbs. The takeoff weight is below the maximum of 2440 lbs., and the weight and balance calculations have determined that the C.G. position is within the approved limits. ISSUED: AUGUST 13, 1982, REPORT: VB-1180 5-3 --- Delaware State University king SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA-28-161, WARRIOR II (b) Takeoff and Landing. Now that the aircraft loading has been determined, all aspects of the 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 graph (Figures 5-7 and 5-9 or 5-11 and 5-13) 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. 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) Pressure Altitude (2) Temperature (3) Wind Component Departure Airport Destination Airport 1500 ft. 2500 ft. 27°C 15 KTS 24°C 0 KTS (Headwind) 4800 ft. 2100 ft.* 7600 ft. 1135 ft.** (4) Runway Length Available (5) Runway Required NOTE The remainder of the performance charts used in this flight planning example assume a no wind condition. The effect of winds aloft must be considered by the pilot when computing climb, cruise and descent performance, *reference Figure 5-9 **reference Figure 5-35 REPORT: VB-1180 5-4 ISSUED: AUGUST 13, 1982 Delaware State University Ев PIPER AIRCRAFT CORPORATION PA-28-161, WARRIOR II (c) Climb SECTION 5 PERFORMANCE The next step in the flight plan is to determine the necessary climb segment components. The desired cruise pressure altitude and corresponding cruise outside air temperature values are the first variables to be con- sidered in determining the climb components from the Fuel, Time and Distance to Climb graph (Figure 5-19). After the fuel, time and distance for the cruise pressure altitude and outside air temperature values have been established, apply the existing conditions at the departure field to graph (Figure 5-19). Now, subtract the values obtained from the graph for the field of departure conditions from

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those for the cruise pressure altitude. The remaining values are the true fuel, time and distance components for the climb segment of the flight plan corrected for field pressure altitude and temperature. The following values were determined from the above instruc- tions in the flight planning example. (1) Cruise Pressure Altitude (2) Cruise OAT (3) Time to Climb (12.0 min, minus 3.0 min.) (4) Distance to Climb (16.0 miles minus 4.0 miles) (5) Fuel to Climb (3 gal. minus 1.0 gal.) (d) Descent 5000 ft. 16°C 9.0 min.* 12.0 miles* 2.0 gal.* 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 pressure altitude and OAT, determine the basic fuel, time and distance for descent (Figure 5-31). These figures must be adjusted for the field pressure altitude and temperaturé at the destination airport. To find the necessary adjustment values, use the existing pressure altitude and temperature conditions at the destination airport as variables to find the fuel, time and distance *reference Figure 5-19 ISSUED: AUGUST 13, 1982 Delaware State University Boken REPORT: VB-1180 5-5 SECTION S PERFORMANCE PIPER AIRCRAFT CORPORATION PA-28-161, WARRRIOR II values from the graph (Figure 5-31). Now, subtract the values obtained from the field conditions from the values obtained from the cruise conditions to find the true fuel, time and distance 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 (7.5 min. minus 4.5 min.) (2) Distance to Descend (13.5 miles minus 8.0 miles) (3) Fuel to Descend (e) Cruise (1.0 gal. minus .5 gal.). 3.0 min.* 5.5 miles* .5 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 when selecting the cruise power setting. The established pressure altitude and temperature values and the selected cruise power should now be utilized to determine the true airspeed from the Cruise Performance graph (Figure 5-21 or 5-23). Calculate the cruise fuel consumption 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 consumption by the cruise time, The cruise calculations established for the cruise segment of the flight planning example are as follows: (1) Total Distance (2) Cruise Distance 300 miles (e) (1) minus (c)(4) minus (d)(2), (300 minus 12 miles minus 5.5 miles) 282.5 miles *reference Figure 5-31 REPORT: VB-1180 5-6 ISSUED: AUGUST 13, 1982 Delaware State University halten aband PIPER AIRCRAFT CORPORATION PA-28-161, WARRIOR II SECTION 5 PERFORMANCE (3) Cruise Power Best Economy Mixture 75% rated power (4) Cruise Speed (5) Cruise Fuel Consumption (6) Cruise Time (e)(2) divided by (e)(4), (283.5 (2625 RPM) 118 KTS TAS* 8.5 GPH miles divided by 118 KTS) 2,39 hrs. (7) Cruise Fuel (c)(5) multiplied by (e)(6), (8.5 GPH mulitiplied by 2.40 hrs.) 20.3 gal. (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 our flight planning example. (1) Total Flight Time (c)(3) plus (d)(1) plus (e)(6), (.15 hrs. plus .05 hrs. plus 2.39 hrs.) 2.59 hrs. (g) Total Fuel Required 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 (c)(7), (2.0 gal. plus .5 gal. plus 20.3 gal.) (22.8 gal. multiplied by 6 lb/gal.) 22.8 gal. 136.8 lbs. *reference Figure 5-23 ISSUED: AUGUST 13, 1982 REPORT: VB-1180 5-7 Delaware State University Making mon

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