Performance Data for the Piper PA-28RT Arrow IV Turbo

Piper PA-28RT Arrow IV Turbo · Performance Data

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Overview

This document provides performance data specifically for the Piper PA-28RT Arrow IV Turbo. It is designed 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 is essential for flight planning and operational efficiency, ensuring that pilots can make informed decisions during flight operations. The document includes various performance charts and tables that outline the aircraft's performance under different conditions, such as weight, altitude, and temperature.

Maximum takeoff weight: 3,600 lbs
Useful load: approximately 1,200 lbs
Climb rate at sea level: approximately 1,000 feet per minute
Cruise speed: 140 knots
Fuel consumption during cruise: around 12 gallons 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: 20
File size: 6.3 MB
Publisher: www.desu.edu

Specifications & performance

Extracted from this document.

Specifications

Cruise speed (kt): 130
Empty weight (lb): 1,890
Fuel capacity (gal): 12.2
Max takeoff weight (lb): 2,750

Performance

Fuel burn (gph): 10.3

V-speeds

VS1: 57

Weight & balance

Useful load (lb): 860
Basic empty weight (lb): 1,890
Max takeoff weight (lb): 2,750

Documentation completeness

3/7

Most owners only have the POH. Here's the essential set for the Piper PA-28RT Arrow IV Turbo.

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

More Piper PA-28RT Arrow IV Turbomanuals & documents

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In this document

Aircraft Specifications

The Piper PA-28RT Arrow IV Turbo features a turbocharged engine, providing enhanced performance at higher altitudes. The aircraft has a maximum takeoff weight of 3,600 lbs and a useful load of approximately 1,200 lbs. It is equipped with a constant speed propeller and has a wingspan of 36 feet.

Performance Charts

The performance charts included in this document detail the aircraft's climb rate, cruise speed, and landing distances under various weight and environmental conditions. For example, at maximum gross weight, the climb rate is approximately 1,000 feet per minute at sea level.

Fuel Consumption

The fuel consumption rates for the Piper PA-28RT Arrow IV Turbo are provided for different phases of flight. During cruise, the aircraft typically consumes around 12 gallons per hour at a cruise speed of 140 knots.

Safety notes

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

Full document text

PA-28R-201, ARROW Paragraph No. TABLE OF CONTENTS SECTION 5 PERFORMANCE SECTION 5 PERFORMANCE Page No. 5.1 General 5-1 5.3 Introduction to Performance and Flight Planning.. 5-1 5.5 Flight Planning Example.. 5-3 5.7 Performance Graphs....... 5-9 List of Figures..... 5-9 ISSUED: JULY 12, 1995 REPORT: VB-1612 5-i PA-28R-201, ARROW SECTION 5 PERFORMANCE SECTION 5 PERFORMANCE 5.1 GENERAL All of the required (FAA regulations) and complementary performance information is provided by this section. Performance information associated with those optional systems and equipment which 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. 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: JULY 12, 1995 REPORT: VB-1612 5-1 SECTION 5 PERFORMANCE PA-28R-201, ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 5-2 ISSUED: JULY 12, 1995 PA-28R-201, ARROW 5.5 FLIGHT PLANNING EXAMPLE (a) Aircraft Loading SECTION 5 PERFORMANCE 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 fac- tory has been entered in Figure 6-5. If any alterations to the air- plane 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 6-11) 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 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 (2 x 170 lbs.) (3) Baggage and Cargo (4) Fuel (6 lb./gal. x 51.3) (5) Engine Start, Taxi, and Run Up (6) Takeoff Weight (7) Landing Weight (a)(6) minus (g)(1), (2600 lbs. minus 73.2 lbs.) 1890 lbs. 340 lbs. 70 lbs. 308 lbs. -8 lbs. 2600 lbs. 2526 lbs. The takeoff weight is below the maximum of 2750 lbs., and the weight and balance calculations have determined the C.G. position to be within approved limits. ISSUED: JULY 12, 1995 REPORT: VB-1612 5-3 SECTION 5 PERFORMANCE 5.5 FLIGHT PLANNING EXAMPLE (continued) (b) Takeoff and Landing PA-28R-201, ARROW Now that the airplane loading has been determined, all aspects of the takeoff and landing must now 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 5-9, 5-11, 5-13 and 5-15) 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 flight have fallen well below the available runway lengths. (1) Pressure Altitude (2) Temperature (3) Wind Component (4) Runway Length Available (5) Runway Required NOTE Departure Airport Destination Airport 1900 ft. 1900 ft. 20°C 20°C 4 KTS 2 KTS 3000 ft. 4600 ft. 2550 ft.* 1490 ft.** 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 5-13 **reference Figure 5-39 REPORT: VB-1612 ISSUED: JULY 12, 1995 5-4 PA-28R-201, ARROW 5.5 FLIGHT PLANNING EXAMPLE (continued) (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 climb components from the Fuel, Time and Distance to Climb graph (Figure 5-21). After the fuel, time and dis- tance for the cruise pressure altitude and outside air temperature values have been established, apply the existing conditions at the departure field to the graph (Figure 5-21). Subtract the values ob- tained from the graph for the field of departure conditions for those for the cruise pressure altitude. The remaining values are the true fuel, time and distance

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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) Fuel to Climb (4 gal. minus 1.0 gal.) (4) Time to Climb (10 min. minus 3.5 min.) (5) Distance to Climb (17 naut. miles minus 6 naut. miles) (d) Descent 6000 ft. 10°C 3.0 gal.* 6.5 min.* 11 naut. miles* 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 5-35). These figures must be adjusted for the field pressure altitude and temperature 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 5-21 ISSUED: JULY 12, 1995 REPORT: VB-1612 5-5 SECTION 5 PERFORMANCE PA-28R-201. ARROW 5.5 FLIGHT PLANNING EXAMPLE (continued) values from the graph (Figure 5-35). Subtract the values ob- tained from the field conditions from the values obtained from the cruise conditions to find the true fuel, time and distances 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) Fuel to Descend (1.0 gal. minus 0.5 gal.) (2) Time to Descend (7 min. minus 3 min.) (3) Distance to Descend (e) Cruise (18 naut. miles minus 7.5 naut. miles) 0.5 gal.* 4 min.* 10.5 naut. miles* 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 Power Setting Table (Figure 5-23 or 5-23a) 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 appropriate Speed Power graph (Figure 5-25 through 5-27c). For this example, 65% Economy Cruise at 2500 RPM was used. Calculate the cruise flow for the cruise power setting from the information provided by the Best Economy Range chart (Figure 5-31a). 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) Total Distance (2) Cruise Distance (e)(1) minus (c)(5) minus (d)(3), (130 naut. miles minus 11 naut. miles minus 10.5 naut. miles) *reference Figure 5-35 130 naut. miles 108.5 naut. miles REPORT: VB-1612 5-6 ISSUED: JULY 12, 1995 PA-28R-201, ARROW 5.5 FLIGHT PLANNING EXAMPLE (continued) (3) Cruise Power (Best Economy) (4) Cruise Delta OAT from ISA (10° C - 3° C) (5) Cruise Manifold Press. (23.1 + [7/5.5 x .16]) (6) Cruise Speed (7) Cruise Fuel Consumption (8) Cruise Time (e)(2) divided by (e)(6), (108.5 naut. miles divided by 130 KTS) (9) Cruise Fuel (e)(7) multiplied by (e)(8), (10.3 gph mulitiplied by .84 hrs.) (f) Total Flight Time SECTION 5 PERFORMANCE 65% rated power (2500 RPM) 7°C 23.3 in Hg 130 Kts TAS* 10.3 gph* .84 hrs. (51 min.) 8.7 gal. 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)(4) plus (d)(2) plus (e)(8), (.11 hrs. plus .07 hrs. plus .84 hrs.) (6.5 min. plus 4 min. plus 51 min.) (g) Total Fuel Required 1.02 hrs., 61.5 min. 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)(3) plus (d)(1) plus (e)(9), (3.0 gal. plus 0.5 gal. plus 8.7 gal.) (12.2 gal. multiplied by 6 lb./gal.) *reference Figure 5-27c 12.2 gal. 73.2 lbs. ISSUED: JULY 12, 1995 REPORT: VB-1612 5-7 SECTION 5 PERFORMANCE PA-28R-201, ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 5-8 ISSUED: JULY 12, 1995 PA-28R-201, ARROW 5.7 PERFORMANCE GRAPHS SECTION 5 PERFORMANCE LIST OF FIGURES Figure No. Page No. 5-1 5-1a Air Temperatures above & below ISA... Temperature Conversion... 5-10a 5-11 5-3 Airspeed System Calibration. 5-12 5-5 Power Off Stall Speed Vs. Angle of Bank 5-13 5-7 Wind Components......... 5-14 5-9 25° Flap Takeoff Performance Over 50 Foot Barrier ...... 5-15 5-11 25° Flap Takeoff Ground Roll 5-16 5-13 0° Flap Takeoff Performance Over 50 Foot Barrier. 5-17 5-15 0° Flap Takeoff Ground Roll 5-18 5-17 Gear Up Climb Performance 5-19 5-19 Gear Down Climb Performance..... 5-20 5-21 Fuel, Time and Distance to Climb. 5-21 5-23 Power Setting Table (Best Power). 5-23 5-23a Power Setting Table (Best Economy). 5-24 5-25 Best Power Cruise (75%)..... 5-25 5-25a Best Power Cruise (65%) ..... 5-25a 5-25b Best Power Cruise (55%)......... 5-25b 5-27 Best Economy Cruise (55% 2200 RPM) 5-26 5-26a 5-27a Best Economy Cruise (55% 2500 RPM)... 5-27b Best Economy Cruise (65% 2500 RPM). 5-27c Best Economy Cruise (65% 2500 RPM). 5-26b 5-26c ISSUED: JULY 12, 1995 REPORT: VB-1612 5-9 SECTION 5 PERFORMANCE 5.7 PERFORMANCE GRAPHS (Cont'd) LIST OF FIGURES (Cont'd) PA-28R-201, ARROW 5-29 Best PowerRange (2500 RPM) .. 5-27 5-29a Best PowerRange (2200 RPM).. 5-31 Best Economy Range (2200RPM). 5-31a Best Economy Range (2500RPM) ...... 5-33 Best Power Endurance (2500 RPM).. 5-33a Best Power Endurance (2200 RPM).... 5-33b Best Economy Endurance (2500 RPM). 5-33c Best Economy Endurance (2500 RPM) 5-35 Fuel, Time and Distance to Descend 5-27a 5-27b 5-28 5-29 5-29a 5-29b 5-29c 5-30 5-37 Glide Time and Distance...... 5-31 5-39 Landing Distance Over 50 Foot Barrier 5-32 5-41 Landing Ground Roll Distance 5-33 REPORT: VB-1612 5-10 ISSUED: JULY 12, 1995 PA-28R-201, ARROW 16000 PRESSURE ALTITUDE - FEET 14000 12000 10000 8000 6000 4000 2000 SECTION 5 PERFORMANCE Example: Altitude: 6000 ft. ISA temperature: 3°C Example: 10° C @ 6000 FT: ISA + 7 VISA - 15° C SA +30° C ISA +20° C LISA +10° C ISA S.L. -30 -20 -10 0 0 10 10 20 30 40 50 AIR TEMPERATURE - °C AIR TEMPERATURES ABOVE & BELOW ISA ISSUED: JULY 12, 1995 Figure 5-1a REPORT: VB-1612 5-10a PA-28R-201, ARROW 40 100 90 80 80 30 .70 20 20 60 50 10 40 FAHRENHEIT 30 DEGREES 20 .10 10 0. -20 -10 -20 .30 -30 -40 -40 TEMPERATURE CONVERSION ISSUED: JULY 12, 1995 Figure 5-1 SECTION 5 PERFORMANCE CELSIUS DEGREES REPORT: VB-1612 5-11 REPORT: VB-1612 5-12 200 180 160 440 140 CALIBRATED AIRSPEED - KNOTS AIRSPEED SYSTEM CALIBRATION Figure 5-3 ISSUED: JULY 12, 1995 10 120 AIRSPEED SYSTEM CALIBRATION ASSOCIATED CONDITIONS: GROSS WEIGHT - 2750 LB 80 Exampl KIAS 00 60 YING FLAPS Oº GEAR UP Example: 74 KIAS 73 KCAS 120 140 INDICATED AIRSPEED KNOTS (ZERO INSTRUMENT ERROR) 40 40 80 100 WING FLAPS 40* GEAR DOWN (IAS: ZERO INSTRUMENT ERROR 140 180 200 SECTION 5 PERFORMANCE PA-28R-201. ARROW ISSUED: JULY 12, 1995 POWER OFF STALL SPEED VERSUS ANGLE OF BANK Gross weight: 2750 LB Angle of bank: 20° Flap position: 40° Stall speed indicated: 57 KT Example 06 STALL SPEED - KIAS ŏ POWER OFF STALL SPEED VS. ANGLE OF BANK Figure 5-5 60 REPORT: VB-1612 5-13 PA-28R-201, ARROW FLAPS GEAR DOWN. 140° FLAPH 10 20 30 40 50 ANGLE OF BANK DEGREES 09 SECTION 5 PERFORMANCE

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