Performance Data for the Piper PA-28 Cherokee 160
Piper PA-28 Cherokee 160 · Performance Data
Overview
This document provides performance data specifically for the Piper PA-28 Cherokee 160. It is intended for pilots and aviation enthusiasts who require detailed information about the aircraft's capabilities. The data includes critical performance metrics such as takeoff and landing distances, climb rates, and fuel consumption under various conditions. Understanding this information is essential for safe and efficient flight operations. The document serves as a reference for flight planning and operational decision-making, ensuring that pilots can maximize the aircraft's performance while adhering to safety standards.
- Takeoff distance at sea level: 1,600 feet
- Climb rate: 730 feet per minute
- Landing distance on dry runway: 1,500 feet
- Cruise fuel consumption: 8.5 gallons per hour
- Maximum takeoff weight: 2,550 pounds
Document
Source
Originally published by floridaaviationprofessionals.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Performance Data
- Pages
- 8
- File size
- 7.0 MB
- Publisher
- floridaaviationprofessionals.com
Specifications & performance
Extracted from this document.
Specifications
- Engine (hp)
- 112
- Fuel capacity (gal)
- 36
- Max takeoff weight (lb)
- 2,150
Performance
- Fuel burn (gph)
- 8.4
- Landing over 50ft
- 1,400
- Landing distance (ft)
- 1,400
Weight & balance
- Max takeoff weight (lb)
- 2,150
Most owners only have the POH. Here's the essential set for the Piper PA-28 Cherokee 160.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
More Piper PA-28 Cherokee 160manuals & documents
- N5470W Weight and Balance SheetWeight And Balance
- Piper PA-28 Cherokee Systems DescriptionSystems Description
- 50 HOUR PROGRESSIVE INSPECTION MANUALService Manual
- SCHEDULE OF AIRWORTHINESS DIRECTIVESAirworthiness Directives
- PIPER PA-28 STRAIGHT WING MODEL GAP SEALS STC No. SA603GLSupplemental Type Certificate
- SCHEDULE OF AIRWORTHINESS DIRECTIVESAirworthiness Directives
- Airplane Flight Manual for the Piper PA-28 Cherokee 160Flight Manual
In this document
Takeoff Performance
The takeoff performance section outlines the required distances for takeoff under various weight and environmental conditions. For a standard day at sea level, the takeoff distance is approximately 1,600 feet. This distance increases with higher elevations and temperatures.
Climb Performance
Climb performance data indicates a rate of climb of about 730 feet per minute at sea level under standard conditions. This rate may vary based on aircraft weight and atmospheric conditions.
Landing Performance
Landing performance details the required landing distance, which is approximately 1,500 feet on a dry runway. Factors such as weight, wind, and runway conditions can affect this distance.
Fuel Consumption
Fuel consumption rates are provided for various phases of flight. During cruise at 75% power, the aircraft consumes about 8.5 gallons per hour.
Weight and Balance
The weight and balance section provides guidelines for loading the aircraft to ensure safe operations. The maximum takeoff weight is 2,550 pounds, and pilots must calculate weight distribution to maintain balance.
Safety notes
- Ensure weight and balance calculations are performed before flight.
- Monitor fuel levels to avoid running out during flight.
Full document text
FEET DENSITY ALTITUDE 730115 THE PIPER CHEROKEE 7000 PIPER CHEROKEE PA-28-140 TAKE-OFF DISTANCE VS. T T DENSITY ALTITUDE- 1950 LBS. GROSS WEIGHT 2150 LBS. GROSS WEIGHT -EXTRAPOLATION OF CHART ABOVE 7000 FT. IS INVALID 6000 5000 4000 3000 2000 1800 GROUND- Mar OVER SOFT OBSTACLE 0 500 1000 1500 2000 2500 3000 3500 4800 TAKE OFF DISTANCE . FEET • 20 20 SECTION IV DENSITY ALTITUDE, FEET SECTION IV THE PIPER CHEROKEE 18000 16000 14000 12000 10000 8000 6000 4000 2000 21 PIPER CHEROKEE PA-28-140 RATE OF CLIMB VS DENSITY ALTITUDE 1950 LBS. GROSS WT. 2150 LBS. GROSS WT. 100 200 300 400 500 600 700 800 900 1000 RATE OF CLIMB - FEET PER MINUTE 730115 DENSITY ALTITUDE, FEET SECTION IV THE PIPER CHEROKEE 14000 12000 10000 8000 6000 4000 2000 23 23 PIPER CHEROKEE PA-28-140 TRUE AIRSPEED VS DENSITY ALTITUDE --- + +++ 2150 LBS. GROSS WT. FULL THROTTLE 50% POWER 55% POWER 60% POWER 65% POWER 70% POWER 75% POWER O 100 110 120 130 140 150 160 TRUE AIRSPEED, M.P.H. 650630 23b SECTION IV THE PIPER CHEROKEE 14000 PIPER CHEROKEE PA-28-140 RANGE VS DENSITY ALTITUDE 2150 LBS. GROSS WT. 36 GAL. FUEL (standard) 50 GAL. FUEL (with reserve) 12000 10000 DENSITY ALTITUDE, FEET 8000 6000 4000 2000 0 75% POWER 70% 65% 60%. 55% -50% -70% -65% +60% 75% POWER- 1 500 600 700 800 900 1000 RANGE, MILES 1100 730115 55% 50% DENSITY ALTITUDE, FEET SECTION IV THE PIPER CHEROKEE PA-28-140 PIPER CHEROKEE POWER VS ALTITUDE 14000 2150 LBS. GROSS WT.. 12000 10000 8000 0009 4000 2000 25 25 2000 50% POWER 55% POWER 75 H.P. 5.6 G.P.H. 60% POWER 82 H.P 6.2 6. P. H. 90 H.P. 6.7 G.P.H. TX POWER 97 H.P. 7.3 G.P.H. XXX +オ 70% POWER 105 H.P 7.9 G.PH 75% POWER 112 H.P 8.4 G.P.H. 2100 2200 2300 2400 2500 2600 2700 ENGINE SPEED - R.P.M. 730115 DENSITY ALTITUDE, FEET 7000 6000 5000 4000 3000 2000 1000 730115 THE PIPER CHEROKEE SECTION IV PIPER CHEROKEE PA-28-140 LANDING DISTANCE VS DENSITY ALTITUDE FLAPS 40° POWER OFF PAVED LEVEL DRY RUNWAY NO WIND MAXIMUM BRAKING SHORT FIELD EFFORT -- 1950 LBS. GROSS WT. 2150 LBS. GROSS WT. GROUND ROLL OUT OVER 50 FT. OBSTACLE 200 400 600 800 1000 1200 1400 LANDING DISTANCE, FEET 25a ALTITUDE ABOVE TERRAIN, FEET 25b THE PIPER CHEROKEE 14000 12800 10090 6000 4006 2008 PA-28-140 PIPER CHEROKEE T GLIDE DISTANCE VS ALTITUDE 2150 LBS. 03 M.P.N. PROP WHDHALING 0° FLAPS NO WIND - 10 15 20 25 30 CLIDE RANGE, MILES SECTION IV 730115 THE PIPER CHEROKEE DENSITY ALTITUDE - FT. 24000 20000 SECTION IV PIPER CHEROKEE PA-28-140 ALTITUDE CONVERSION CHART THIS CHART SHOULD BE USED TO DETERMINE DENSITY ALTITUDE FROM EXISTING TEMPERATURE AND PRESSURE ALTITUDE CONDITIONS FOR USE WITH PERFORMANCE CHARTS. STD. TEMP. 16000 12000 3000 4000 SL -40 730115 20 .20 0 16000 FT. PRESSORE ALTITUDE 14000 12000 10000 8809 6000 4000 2000 20 10 00 40 60 88 TEMPERATURE °F 100 26 16