Pilot's Operating Handbook
Piper PA-28 Cherokee 180 · Pilot's Operating Handbook
Overview
This document is the Pilot's Operating Handbook (POH) for the Piper PA-28 Cherokee 180. It serves as a comprehensive guide for pilots operating this aircraft model, providing essential information on its performance, systems, and operational procedures. The handbook includes detailed specifications, limitations, and emergency procedures, ensuring that pilots have the necessary knowledge to operate the aircraft safely and efficiently. It is intended for both new and experienced pilots, offering insights into the aircraft's capabilities and operational requirements.
- Maximum takeoff weight: 2,550 lbs
- Cruise speed: 125 knots
- Stall speed (landing configuration): 50 knots
- Maximum altitude: 14,000 feet
- Best glide speed: 70 knots
Document
Source
Originally published by www.odfa.ca. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Pilot's Operating Handbook
- Pages
- 64
- File size
- 565 KB
- Publisher
- www.odfa.ca
Specifications & performance
Extracted from this document.
Specifications
- Engine (hp)
- 180
- Height (ft)
- 7.3
- Length (ft)
- 23.5
- Propeller
- M76EMMS60
- Wingspan (ft)
- 30
- Engine model
- O-360-A4A
- Empty weight (lb)
- 1,294
- Fuel capacity (gal)
- 50
- Rate of climb (fpm)
- 750
- Service ceiling (ft)
- 13,000
- Max takeoff weight (lb)
- 2,400
Performance
- Landing over 50ft
- 1,625
- Takeoff over 50ft
- 720
- Landing distance (ft)
- 600
- Takeoff distance (ft)
- 1,625
Weight & balance
- Useful load (lb)
- 1,106
- Baggage allowance (lb)
- 200
- Basic empty weight (lb)
- 1,294
- Max takeoff weight (lb)
- 2,400
Most owners only have the POH. Here's the essential set for the Piper PA-28 Cherokee 180.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
More Piper PA-28 Cherokee 180manuals & documents
See all 18 →- 2021 Cherokee 180 GuideChecklist
- Airworthiness Concern SheetAirworthiness Directives
- Pilot´s Operating Handbook for the Piper PA-28-140 - Cherokee Cruiser, Piper PA-28-150/160/180 - Cherokee, Piper PA-28-151 - Cherokee Warrior, Piper PA-28-161 - Cadet, Warrior II & III Equipped with TAE 125 InstallationEmergency Procedures
- Piper Cherokee 180 ChecklistChecklist
- CHEROKEE 180 OWNER'S HANDBOOKFlight Manual
- Weight and Balance DataWeight And Balance
- Piper Cherokee Owner's HandbookWeight And Balance
- PIPER CHEROKEE 180 – PA-28-180Specifications
- Pilot's Operating HandbookPilot's Operating Handbook
- Pilot's Operating HandbookPilot's Operating Handbook
- Airplane Flight ManualFlight Manual
- V-Speeds ReferenceV Speeds Reference
In this document
Aircraft Specifications
The Piper PA-28 Cherokee 180 features a maximum takeoff weight of 2,550 lbs and a useful load of approximately 800 lbs. The aircraft is powered by a Lycoming O-360 engine, producing 180 horsepower. The cruise speed is around 125 knots, with a stall speed of 50 knots in landing configuration.
Operating Limitations
Pilots must adhere to specific operating limitations, including a maximum altitude of 14,000 feet and a maximum crosswind component of 15 knots. The aircraft should not be flown in icing conditions, and the maximum flap extension speed is 100 knots.
Emergency Procedures
In the event of an engine failure, pilots should establish best glide speed at 70 knots and identify suitable landing areas. The handbook outlines procedures for electrical failures, fuel emergencies, and other critical situations.
Weight and Balance
Proper weight and balance calculations are crucial for safe flight. The handbook provides charts and formulas to determine the center of gravity and ensure the aircraft is within limits for safe operation.
Performance Data
Takeoff distance over a 50-foot obstacle is approximately 1,600 feet at sea level on a standard day. Landing distance over a 50-foot obstacle is about 1,500 feet. The handbook includes performance charts for various weights and conditions.
Safety notes
- Do not operate in icing conditions
- Adhere to maximum crosswind component of 15 knots
Full document text
CHEROKEE D PA-28-180 Owner's Handbook PIPER Piper Aircraft Corporation, Vero Beach, Florida U.S. A. REFERENCE ONLY THIS ELECTRONIC VERSION OF THE AOH IS NOT APPROVED TO REPLACE ANY OPERATING INFORMATION REQUIRED BY THE REGULATIONS. NOTICE THIS HANDBOOK IS NOT DESIGNED, NOR CAN ANY HANDBOOK SERVE, AS A SUBSTITUTE FOR ADEQUATE AND COMPETENT FLIGHT INSTRUCTION, OR KNOWLEDGE OF THE CURRENT AIRWORTHINESS DIRECTIVES, THE APPLICABLE FEDERAL AIR REGULATIONS, AND ADVISORY CIRCULARS. IT IS NOT INTENDED TO BE A GUIDE OF BASIC FLIGHT INSTRUCTION, NOR A TRAINING MANUAL. THE HANDBOOK IS DESIGNED: 1. TO HELP YOU OPERATE YOUR CHEROKEE WITH SAFETY AND CONFIDENCE. 2. TO MORE FULLY ACQUAINT YOU WITH THE BASIC PERFORMANCE AND HANDLING CHARACTERISTICS OF THE AIRPLANE. 3. TO MORE FULLY EXPLAIN YOUR CHEROKEE'S OPERATION THAN IS PERMISSIBLE TO SET FORTH IN THE AIRPLANE FLIGHT MANUAL. IF THERE IS ANY INCONSISTENCY BETWEEN THIS HANDBOOK AND THE AIRPLANE FLIGHT MANUAL APPROVED BY THE F.A.A., THE FLIGHT MANUAL SHALL GOVERN. Revised text and illustrations shall be indicated by a black vertical line in the margin opposite the change. Additional copies of this manual, Part No. 753 765 may be obtained from your Piper Dealer. Published by PUBLICATIONS DEPARTMENT Piper Aircraft Corporation 753 765 Issued: November 1967 Revised: January 1973 Performance Weights. Power Plant Fuel and Oil . Baggage Dimensions Landing Gear. 671101 SECTION I SPECIFICATIONS 1 2 2 2 2 3 3 CHEROKEE “D” SECTION I SPECIFICATIONS SECTION I PERFORMANCE Performance figures are for airplanes equipped for cross- country transportation and flown at gross weight under standard conditions at sea level or stated altitude. Any changes in equip- ment may result in changes in performance. Take-off Run (maximum effort, 25° flap) (ft) Take-off over 50-ft barrier (maximum effort, 25° flap) (ft) Best Rate of Climb Speed (mph) Rate of Climb (ft per min) 720 1625 85 750 Service Ceiling (ft) 13,000 Absolute Ceiling (ft) 15,000 Top Speed (mph) 152 Optimum Cruising Speed (75% power, optimum altitude) (mph) 143 Cruising Range (75% power, optimum altitude) (mi) 725 Optimum Cruising Range (55% power, optimum altitude) (mi) 845 Stalling Speed (flaps down) (mph) 57 Stalling Speed (flaps up) (mph) 67 Landing Roll (flaps down) (ft) Landing Roll over 50-ft barrier (ft) 600 .1150 681115 1 SECTION I SPECIFICATIONS (cont): WEIGHTS Gross Weight (lbs) CHEROKEE “D” 2400 Empty Weight (Standard) (lbs) USEFUL LOAD (Standard) (lbs) 1294 1106 POWER PLANT Engine (Lycoming) Rated Horsepower Rated Speed (rpm) Bore (in.) Stroke (in.) Displacement (cu in.) Compression Ratio Dry Weight (lbs) Propeller FUEL AND OIL Fuel Capacity (U.S. gal) Oil Capacity (qts) Fuel, Aviation Grade (min octane) BAGGAGE Maximum Baggage (lbs) Baggage Space (cu ft) Baggage Door Size (in.) 2 O-360-A4A 180 2700 5.125 4.375 361.0 8.5:1 285 M76EMMS60 50 8 91/96 200 17 20 x 22 671101 CHEROKEE “D” SPECIFICATIONS (cont): DIMENSIONS SECTION I Wing Span (ft) 30 Wing Area (sq ft) 160 Wing Loading (lbs per sq ft). 15.0 Length (ft) 23.5 Height (ft) 7.3 Power Loading (lbs per hp) 13.3 LANDING GEAR Wheel Base (ft) 6.2 Wheel Tread (ft) 10 Tire Pressure (psi) Nose 24 Main 24 Tire Size Nose (4 ply rating) Main (4 ply rating) 6.00 x 6 6.00 x 6 671101 3 4 SECTION I 6' 2.65" L 30' 10' 23' 7.03" ·10' 30" CHEROKEE “D” 7' 3.30" 671101 63" 671101 SECTION II DESIGN INFORMATION Engine and Propeller Structures. Landing Gear. 6 Control Systems . 7 Fuel System 7 Electrical System 9 Heating and Ventilating System . 13 Cabin Features 13 20 5 5 сл CHEROKEE "D" SECTION II DESIGN INFORMATION SECTION II ENGINE AND PROPELLER The Cherokee “D” is powered by a Lycoming 0-360-A4A four cylinder, direct drive, horizontally opposed engine rated at 180 HP at 2700 RPM. It is furnished with a starter, 60 ampere 12 volt alternator, shielded ignition, vacuum pump drive, fuel pump, and a dry, automotive type carburetor air filter. The exhaust system is of the cross-over type to reduce back pressure and improve performance. It is made entirely from stain- less steel and is equipped with dual mufflers. A heater shroud around the mufflers is provided to supply heat for the cabin and windshield defrosting. The Sensenich M76EMMS60 fixed-pitch propeller is made from a one-piece alloy forging. STRUCTURES All structures are of aluminum alloy construction and are designed to ultimate load factors well in excess of normal re- quirements. All exterior surfaces are primed with etching primer and painted with acrylic enamel. The wings are attached to each side of the fuselage by in- serting the butt ends of the respective main spars into a spar box carry-through which is an integral part of the fuselage structure, providing in effect a continuous main spar with splices at each side of the fuselage. There are also fore and aft attachments at 671101 5 SECTION II CHEROKEE "D" the rear spar and at an auxiliary front spar. The wing airfoil section is a laminar flow type, NACA652- 415 with the maximum thickness about 40% aft of the leading edge. This permits the main spar carry-through structure to be located under the rear seat providing unobstructed cabin floor space ahead of the rear seat. LANDING GEAR The three landing gears use a Cleveland 6.00 x 6 wheel, the main wheels being provided with Cleveland single disc hydraulic brake assemblies, No. 30-55. All wheels use 6.00 x 6 four ply tires with tubes. The nose gear is steerable through a 44 degree arc by use of the rudder pedals. A spring device is incorporated in the rudder pedal torque tube assembly to aid in rudder centering and to provide rudder trim. The nose gear steering mechanism also in- corporates a hydraulic shimmy dampener. The three struts are of the air-oil type, with the normal extension being 3.25 inches for the nose gear and 4.50 inches for the main gear. The standard brake system for the Cherokee consists of a hand lever and master cylinder which is located below and behind
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the left center of the instrument sub-panel. The brake uid reservoir is installed on the top left front face of the firewall. The parking brake is incorporated in the master cylinder and is actuated by pulling back on the brake lever, depressing the knob attached to the handle and releasing the brake lever. To release the parking brake, pull back on the lever to disengage the catch mechanism and allow the handle to swing forward. Optional toe brakes are available to supplement the standard hand lever and parking brake system. 671101 CHEROKEE “D” SECTION II CONTROL SYSTEMS Dual controls are provided as standard equipment with a cable system used between the controls and the surfaces. The horizontal tail is of the Flying Tail type (stabilator), with a trim tab mounted on the trailing edge of the stabilator to reduce the control system forces. This tab is actuated by a control wheel on the floor between the front seats. The stabilator provides extra stability and controllability with less size, drag and weight than conventional tail surfaces. The ailerons are provided with a differential action which tends to reduce adverse yaw in turning maneuvers, and which also reduces the amount of coordination required in normal turns. A rudder trim adjustment is mounted on the right side of the pedestal below the throttle quadrant and permits directional trim as needed in flight. The flaps are manually operated, balanced for light operating forces and spring-loaded to return to the up position. A past- center lock incorporated in the actuating linkage holds the flap when it is in the up position so that it may be used as a step on the right side. The flap will not support a step load except when in the full up position, so it must be completely retracted when used as a step. The flaps have three extended positions: 10, 25 and 40 degrees. FUEL SYSTEM Fuel is stored in two twenty-five gallon tanks which are secured to the leading edge structure of each wing by screws and nut plates. This allows easy removal for service or inspection. The fuel selector control is located on the left side-panel, forward of the pilot's seat. If a modified selector valve cover has been installed, the button on the selector cover must be depressed and held while the handle is moved to the OFF position. The button releases automatically when the handle is moved into the ON position. An auxiliary electric fuel pump is provided in case of failure 730130 7