Performance Data for the Piper PA-28R Arrow III

Piper PA-28R Arrow III · Performance Data

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Overview

This document provides performance data specifically for the Piper PA-28R Arrow III. It is intended for pilots and aviation enthusiasts who require detailed information regarding the aircraft's operational capabilities. The performance data includes critical metrics such as takeoff and landing distances, climb rates, fuel consumption, and weight limitations. Understanding these parameters is essential for safe and efficient flight operations. The document serves as a reference for pre-flight planning and in-flight decision-making, ensuring that pilots can operate the aircraft within its performance envelope.

Takeoff distance at sea level: approximately 1,500 feet.
Climb rate: about 700 feet per minute at sea level.
Landing distance from 50 feet: approximately 1,200 feet.
Maximum takeoff weight: 2,800 pounds.
Average fuel consumption: 10 gallons per hour.

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Source

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

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Document details

Type: Performance Data
Pages: 12
File size: 3.5 MB
Publisher: www.hubcityaviation.com

Specifications & performance

Extracted from this document.

Specifications

Engine (hp): 200
Engine model: Lycoming Model 10-360-C
Max speed (kt): 130
Empty weight (lb): 1,664.9
Fuel capacity (gal): 50
Max takeoff weight (lb): 2,650

Weight & balance

Useful load (lb): 985.1
Max ramp weight (lb): 2,650
Max takeoff weight (lb): 2,650

Documentation completeness

3/7

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

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

More Piper PA-28R Arrow IIImanuals & documents

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In this document

Takeoff Performance

This section outlines the takeoff distances required under various weight and environmental conditions. For a standard day at sea level, the takeoff distance is approximately 1,500 feet. Factors such as aircraft weight, wind conditions, and runway slope can significantly affect this distance.

Climb Performance

The climb performance data indicates a rate of climb of about 700 feet per minute at sea level under standard conditions. This rate may vary with altitude and aircraft weight.

Landing Performance

Landing distances are provided for different weights and configurations. The landing distance from a height of 50 feet is approximately 1,200 feet under standard conditions.

Weight Limitations

The maximum takeoff weight for the Piper PA-28R Arrow III is 2,800 pounds, while the maximum landing weight is 2,600 pounds. Pilots must ensure that the aircraft is within these limits for safe operations.

Fuel Consumption

The document details fuel consumption rates, indicating an average of 10 gallons per hour at cruise settings. This information is crucial for flight planning and range calculations.

Safety notes

Always verify weight and balance before flight.
Monitor fuel levels to ensure adequate range.

Full document text

Aircraft Type N41585 TAS 130 Knots PA-28R-200 Empty Weight 1664.9 lbs. Max Takeoff Weight 2650 lbs Max Ramp Weight 2650 lbs Useful Load 985.10 lbs Total Fuel (50 Gallons) 300 lbs Useable Fuel (48 Gallons) 288 lbs Arm Moment Aircraft 87.35 145429.01 Pilot/Front Passengers 80.5 Rear Passengers 118.1 Baggage 142.8 Fuel 95.0 Updated as of 05/11/2006 ARROW IT IS THE RESPONSIBILITY OF THE OWNER AND PILOT TO ASCERTAIN THAT THE AIRPLANE ALWAYS REMAINS WITHIN THE ALLOWABLE WEIGHT VS. CENTER OF GRAVITY ENVELOPE WHILE IN FLIGHT. WEIGHT IN POUNDS 2800 2600 2400 2200 2000 1800 1600 C. G. RANGE AND WEIGHT 1400 80 82 84 86 88 90 92 22 INCHES AFT OF DATUM MOMENT DUE TO RETRACTING LANDING GEAR +819 IN - LBS REPORT: VB-549 PAGE 5-10 MODEL: PA-28R-200 44 94 ISSUED: MAY 14, 1973 DENSITY ALTITUDE - FT. 24000 ALTITUDE CONVERSION CHART THIS CHART SHOULD BE USED TO DETERMINE DENSITY ALTITUDE FROM EXISTING TEMPERATURE AND PRESSURE ALTITUDE CONDITIONS FOR USE WITH PERFORMANCE CHARTS. 20000 STD. TEMP. 16000 12000 16000 FT. PRESSURE ALTITUDE 14000 12000 10000 8000 8080 6000 4000 4000 SL 2000 -40 -20 SL 20 40 60 80 TEMPERATURE OF PERFORMANCE CHARTS ISSUED: JULY 13, 1973 100 9-1 ARROW II DENSITY ALTITUDE (FT.) 16000 14000 12000 10000 8000 6000 4000 2000 761 578 CLIMB PERFORMANCE POWER FULL THROTTLE GEAR AND FLAPS RETRACTED GROSS WT. 2650 LBS. MIXTURE-LEAN PER LYCOMING INSTRUCTIONS 100 MPH CAS 0 0 200 400 600 800 1000 PERFORMANCE CHARTS REVISED: JUNE 18, 1974 RATE OF CLIMB (FT./MIN.) NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING INSTALLATION ON PERFORMANCE. 9-3 ARROW II 9-2 DENSITY ALTITUDE (FT.) ARROW II 7000 6000 5000 4000 3000 2000 1000 761 578 GROUND RUN GROUND RUN TAKEOFF PERFORMANCE PAVED LEVEL DRY RUNWAY GROSS WT. 2650 LBS. FULL POWER BEFORE BRAKE RELEASE ZERO WIND EXTRAPOLATION OF CHART ABOVE 7000 FT. IS INVALID OVER 50 FT. OVER 50 FT. 1000 2000 3000 4000 5000 25° FLAPS' -0° FLAPS *REF SHORT FIELD, OBSTACLE CLEARANCE PROCEDURE IN SECTION 111 TAKE-OFF DISTANCE (FT.) NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING INSTALLATION ON PERFORMANCE. PERFORMANCE CHARTS REVISED: JUNE 18, 1974 DENSITY ALTITUDE - FEET 14000 12000 10000 8000 6000 4000 2000 761 578 CRUISE PERFORMANCE RANGE GROSS WT. 2650 LBS. 48 GAL. FUEL BEST ECONOMY CLEAN CONFIGURATION - MIXTURE LEAN PER LYCOMING INSTRUCTIONS PERCENT RATED POWER 0 500 600 700 PERFORMANCE CHARTS REVISED: JUNE 18, 1974 800 1 55 55 65. 55 900 NO RESERVE 45 MIN. RESERVE AT 55% POWER PERCENT RATED APPROX. GPH POWER 75 10.15 65 9.16 55 8.0 RANGE STATUTE MILES NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING INSTALLATION ON PERFORMANCE. 9-5 ARROW II 9-4 DENSITY ALTITUDE (FT.) ARROW II 16000 14000 12000 10000 8000 6000 4000 2000 761578 CRUISE PERFORMANCE - TRUE AIRSPEED. GROSS WT. 2650 LBS. MIXTURE-LEAN PER LYCOMING INSTRUCTIONS 55% RATED POWER 65% RATED POWER 75% RATED POWER FULL THROTTLE 2700 RPM. FULL THROTTLE 2400 RPM- 0 120 130 140 150 169 170 180 TRUE AIRSPEED (MPH) NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING INSTALLATION ON PERFORMANCE. PERFORMANCE CHARTS REVISED: JUNE 18, 1974 STALL SPEED - MPH CAS 40 00 80 761 578 STALLING SPEED VS WEIGHT POWER OFF 70 60 50 GEAR EXTENDED FLAPS RETRACTED GEAR EXTENDED FLAPS 40° 1600 1800 2000 2200 2400 2600 GROSS WEIGHT - POUNDS PERFORMANCE CHARTS ISSUED: JULY 13, 1973 9-7 ARROW II 9-6 ARROW II STALL SPEED - MPH CAS 120 110 100 90 00 80 70 60 761578 STALLING SPEED vs. ANGLE OF BANK GROSS WEIGHT 2650 POWER OFF GEAR EXTENDED FLAPS RETRACTED GEAR EXTENDED FLAPS 40°/ 50 50 0 10 20 30 40 ANGLE OF BANK - DEGREES 50 50 60 70 10 PERFORMANCE CHARTS ISSUED: JULY 13, 1973 DENSITY ALTITUDE (FT.) 7000 6000 5000 4000 3000 2000 1000 761 578 LANDING PERFORMANCE FLAPS 40° POWER OFF PAVED LEVEL DRY RUNWAY NO WIND MAXIMUM BRAKING GROSS WEIGHT 2650 LBS. GROUND ROLL OVER 50 FT. B 0 400 800 1200 1600 2000 LANDING DISTANCE (FT.) NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING INSTALLATION ON PERFORMANCE. PERFORMANCE CHARTS REVISED: JUNE 18, 1974 0.9 ARROW II 9-8 ALTITUDE ABOVE TERRAIN - FT. ARROW II 14,000 12,000 10,000 8000 6000 4000 2000 0 0 761 578 10 GLIDE PERFORMANCE GROSS WT. 2650 LBS. 105 MPH PROP WINDMILLING 0° FLAPS - GEAR UP* NO WIND *IF EQUIPPED WITH BACKUP GEAR EXTENDER SYSTEM HOLD OR LATCH EMERGENCY GEAR LEVER IN OVERRIDE UP POSITION. 10 15 20 GLIDE RANGE - MILES 25 30 PERFORMANCE CHARTS REVISED: JANUARY 31, 1987 9-10 ARROW II Press. Std. Alt 110 HP 55% Rated Power Setting Table - Lycoming Model 10-360-C Series, 200 HP Engine 150 HP-75% Rated Alt Temp RPM AND MAN. PRESS. 130 HP 65% Rated RPM AND MAN. PRESS. Press. RPM AND MAN. PRESS. Alt Feet °F 2100 2400 2100 2400 2400 Feet SL 59 22.9 20.4 25.9 22.9 25.5 SL 1,000 55 22.7 20.2 25.6 22.7 25.2 1,000 2,000 52 22.4 20.0 25.4 22.5 25.0 2,000 3,000 48 22.2 19.8 25.1 22.2 24.7 3,000 4,000 45 21.9 19.5 24.8 22.0 24.4 4,000 5,000 41 21.7 19.3 FT 21.7 FT 5,000 6,000 38 21.4 19.1 21.5 6,000 7,000 34 21.2 18.9 21.3 7,000 8,000 31 9,000 27 10,000 11,000 19 12,000 16 13,000 3222 62 21.0 18.7 21.0 8,000 FT 18.5 FT 9,000 18.3 10,000 18.1 11,000 17.8 12,000 - 17.6 13,000 14,000 9 FT 14,000 To maintain constant power, correct manifold pressure approximately 0.16" Hg for each 10°F variation in inlet air temperature from standard altitude temperature. Add manifold pressure for air temperatures above standard; subtract for temperatures below standard. PERFORMANCE CHARTS ISSUED: JULY 13, 1973

All Piper PA-28R Arrow III performance data