Piper PA-28 Warrior II Pilot's Operating Handbook

Piper PA-28 Warrior II · Pilot's Operating Handbook

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Overview

This Pilot's Operating Handbook (POH) is designed for the Piper PA-28 Warrior II, providing essential information for pilots operating this aircraft. It includes detailed specifications, performance data, operating procedures, and safety information necessary for safe flight operations. The handbook serves as a comprehensive reference for both new and experienced pilots, ensuring they have access to critical information regarding the aircraft's capabilities and limitations. Key sections cover preflight checks, emergency procedures, and performance charts, making it an indispensable tool for flight planning and execution.

Wingspan: 36 ft 1 in (11.00 m)
Maximum Takeoff Weight: 2,550 lbs (1,157 kg)
Cruise Speed: 125 knots (144 mph)
Stall Speed: 54 knots (62 mph)
Service Ceiling: 14,000 ft (4,267 m)

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Document details

Type: Pilot's Operating Handbook
Pages: 171
File size: 5.8 MB
Publisher: bealefss.com

Specifications & performance

Extracted from this document.

Specifications

Engine (hp): 160
Height (ft): 6
Length (ft): 23
Propeller: Sensenich
Wingspan (ft): 35
Engine model: O-320-D2A or O-320-D3G
Fuel capacity (gal): 50
Max takeoff weight (lb): 2,440

Weight & balance

Max ramp weight (lb): 2,447
Baggage allowance (lb): 200
Max landing weight (lb): 2,440
Max takeoff weight (lb): 2,440

Documentation completeness

2/7

Most owners only have the POH. Here's the essential set for the Piper PA-28 Warrior II.

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

More Piper PA-28 Warrior IImanuals & documents

In this document

Aircraft Specifications

The Piper PA-28 Warrior II features a low-wing design with a wingspan of 36 feet 1 inch (11.00 m) and a length of 24 feet 10 inches (7.57 m). The maximum takeoff weight is 2,550 lbs (1,157 kg), and it is powered by a Lycoming O-360 engine producing 180 horsepower.

Performance Data

The aircraft has a maximum cruise speed of 125 knots (144 mph) and a stall speed of 54 knots (62 mph). The service ceiling is 14,000 feet (4,267 m), and the range is approximately 600 nautical miles (1,111 km) with standard fuel reserves.

Operating Procedures

Preflight checks should include a thorough inspection of the aircraft, fuel levels, and control surfaces. The engine start procedure involves ensuring the mixture is rich, the throttle is open 1/4 inch, and the ignition switch is in the 'Both' position.

Emergency Procedures

In the event of an engine failure during takeoff, the recommended action is to maintain control of the aircraft, establish a glide attitude, and select a suitable landing area. Pilots should also be familiar with emergency landing procedures and checklist protocols.

Weight and Balance

Proper weight and balance calculations are crucial for safe flight operations. The handbook provides charts and formulas to determine the center of gravity and ensure the aircraft is within limits for safe operation.

Safety notes

Always perform a thorough preflight inspection before each flight.
Ensure weight and balance calculations are completed prior to departure.
Familiarize yourself with emergency procedures and checklist protocols.

Full document text

WARRIOR II INFORMATION MANUAL Warrior II PA-28-161 HANDBOOK PART NO. 781 780 Π PIPER ✓ A LEAR SIEGLER COMPANY Piper APPLICABILITY Application of this handbook is limited to the specific Piper PA-28-161 model airplane designated by serial number and registration number on the face of the title page of this handbook. This handbook cannot be used for operational purposes unless kept in a current status. REVISIONS The information compiled in the Pilot's Operating Handbook, with the exception of the equipment list, will be kept current by revisions distributed to the airplane owners. The equipment list was current at the time the air- plane was licensed by the manufacturer and thereafter must be maintained by the owner. Revision material will consist of information necessary to update the text of the present handbook and/or to add information to cover added airplane equipment. I. Revisions Revisions will be distributed whenever necessary as complete page replacements or additions and shall be inserted into the handbook in accordance with the instructions given below: 1. Revision pages will replace only pages with the same page number. 2. Insert all additional pages in proper numerical order within each section. 3. Page numbers followed by a small letter shall be inserted in direct sequence with the same common numbered page. II. Identification of Revised Material Revised text and illustrations shall be indicated by a black vertical line along the outside margin of the page, opposite revised, added or deleted material. A line along the outside margin of the page opposite the page number will indicate that an entire page was added. REPORT: VB-1180 iii Black lines will indicate only current revisions with changes and additions to or deletions of existing text and illustrations. Changes in capitalization, spelling, punctuation or the physical location of material on a page will not be identified by symbols. ORIGINAL PAGES ISSUED The original pages issued for this handbook prior to revision are given below: Title, ii through vii, 1-1 through 1-10, 2-1 through 2-9, 3-1 through 3-16, 4-1 through 4-25, 5-1 through 5-29, 6-1 through 6-17, 7-1 through 7-26, 8-1 through 8-18, 9-1 through 9-72 and 10-1 through 10-2. REPORT: VB-1180 iv PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Current Revisions to the PA-28-161 Warrior 11 Pilot's Operating Hand- book, REPORT: VB-1180 issued August 13, 1982. Revision Number and Code Revised Pages Description of Revision Rev. I 4-21, Revised para. 4.27. (PR821015) 4-22 5-18 Revised fig. 5-15. 6-5 Revised fig. 6-3. 7-10 Revised para. 7.15. FAA Approval Signature and Date Ward Evans Oct. 15, 1982 Ward Evans Rev. 2 1-8 Deleted MEA. (PR830715) 2-9 Added GAMA placard. 6-11 Revised para. 6.7. 6-16 Revised page top. 7-23 Revised para. 7.33. 8-2 Revised para. 8.3. Ward Evans 8-3. Revised para. 8.5. July 15, 1983 8-4 Ward Evans Rev. 3 1-3 Revised para. 1.7. (PR840628) 1-6, Revised para. 1.19 (b). 1-7 2-2 Revised para. 2.7. 2-6 Revised para. 2.23. 3-1 Revised para. 3.1. 4-4 Revised procedures. 4-5 Revised procedure; moved 4-6 4-13 4-14 4-15 info. to pg. 4-6. Relocated info. from pg. 4-5. Revised para. 4.9. Revised para. 4.9; moved info. to pg. 4-15. Relocated info. from pg. 4-14. REPORT: VB-1180 Revision Number and Code Revised Pages PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) FAA Approval Signature and Date Description of Revision Rev. 3 (cont) 7-4 Revised para. 7.7. 7-10 Revised para. 7.13. 7-11 Revised para. 7.15. 8-11, Revised para. 8.21. Ward Evans 8-13, 8-14 June 28, 1984 Ward Evans Rev. 4 (PR850712) 7-11 Revised para. 7.15. 7-22 Revised para. 7.26. 9-73 Added Supplement 8 thru (Aux. Vacuum System). 9-77 D.H.Trompler Sept. 23, 1985 REPORT: VB-1180 vi TABLE OF CONTENTS SECTION 1 GENERAL SECTION 2 LIMITATIONS SECTION 3 EMERGENCY PROCEDURES SECTION 4 NORMAL PROCEDURES SECTION 5 PERFORMANCE SECTION 6 WEIGHT AND BALANCE SECTION 7 SECTION 8 SECTION 9 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS AIRPLANE HANDLING, SERVICING AND MAINTENANCE SUPPLEMENTS SECTION 10 OPERATING TIPS REPORT: VB-1180- vii TABLE OF CONTENTS SECTION 1 GENERAL Paragraph No. 1.1 Introduction 1.3 Engines 1.5 Propellers 1.7 Fuel 1.9 Oil... 1.11 Maximum Weights Page No. 1-1 1-3 1-3 1-3 1-4 1-4 1.13 Standard Airplane Weight 1-4 1.15 Baggage Space 1-4 1.17 Specific Loadings 1-4 1.19 Symbols, Abbreviations and Terminology. 1-5 REPORT: VB-1180 1-i PIPER AIRCRAFT CORPORATION PA-28-161, WARRIOR II SECTION 1 GENERAL SECTION 1 GENERAL 1.1 INTRODUCTION This Pilot's Operating Handbook is designed for maximum utilization as an operating guide for the pilot. It includes the material required to be furnished to the pilot by C.A.R. 3 and FAR Part 21, Subpart J. It also contains supplemental data supplied by the airplane manufacturer. This handbook is not designed as a substitute for adequate and competent flight instruction, knowledge of current airworthiness directives, applicable federal air regulations or advisory circulars. It is not intended to be a guide for basic flight instruction or a training manual and should not be used for operational purposes unless kept in a current status. Assurance that the airplane is in an airworthy condition is the responsibility of the owner. The pilot in command is responsible for determining that the airplane is safe for flight. The pilot is also responsible for remaining within the operating limitations as outlined by instrument markings, placards, and this handbook. Although the arrangement of this handbook is intended to increase its in-flight capabilities, it should not be used solely as an occasional operating reference. The pilot should study the entire handbook to familiarize himself with the limitations, performance, procedures and operational handling characteristics of the airplane before flight. The handbook has been divided into numbered (arabic) sections, each provided with a "finger-tip" tab divider for quick reference. The limitations

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and emergency procedures have been placed ahead of the normal procedures, performance and other sections to provide easier access to information that may be required in flight. The "Emergency Procedures" Section has been furnished with a red tab divider to present an instant reference to the section. Provisions for expansion of the handbook have been made by the deliberate omission of certain paragraph numbers, ligure numbers, item numbers and pages noted as being intentionally left blank. ISSUED: AUGUST 13, 1982 REPORT: VB-1180 1-1 SECTION 1 GENERAL PIPER AIRCRAFT CORPORATION PA-28-161, WARRIOR II REPORT: VB-1180 1-2 5'3" 12' 11.75" ·35° -10° 23' 9.6" 76" -STATIC GROUND LINE- 6' 0" 7' 3.6" 3'6.2" THREE VIEW Figure 1-1 ISSUED: AUGUST 13, 1982 PIPER AIRCRAFT CORPORATION PA-28-161, WARRIOR II SECTION 1 GENERAL 1.3 ENGINES (a) Number of Engines (b) Engine Manufacturer (c) Engine Model Number (d) Rated Horsepower (e) Rated Speed (rpm) (f) Bore (inches) (g) Stroke (inches) (h) Displacement (cubic inches) (i) Compression Ratio (j) Engine Type Lycoming O-320-D2A or O-320-D3G 160 2700 5.125 3.875 319.8 8.5:1 Four Cylinder, Direct Drive, Horizontally Opposed. Air Cooled 1.5 PROPELLERS (a) Number of Propellers (b) Propeller Manufacturer (c) Model (d) Number of Blades (e) Propeller Diameter (inches) (1) Maximum (2) Minimum (f) Propeller Type Sensenich 74DM6-0-60 2 74 72 Fixed Pitch 1.7 FUEL AVGAS ONLY (a) Fuel Capacity (U.S. gal) (total) (b) Usable Fuel (U.S. gal) (total) (c) Fuel (1) Minimum Octane (2) Alternate Fuel 50 48 80 100 Green or 100LL Blue Aviation Grade Refer to Fuel Requirements, Handling. Servicing Section 8 and Maintenance. ISSUED: AUGUST 13, 1982 REVISED: JUNE 28, 1984 REPORT: VB-1180 1-3 SECTION 1 GENERAL PIPER AIRCRAFT CORPORATION PA-28-161, WARRIOR II 1.9 OIL (a) Oil Capacity (U.S. quarts) (b) Oil Specification (c) Oil Viscosity per Average Ambient Temp. for Starting (1) Above 60°F (2) 30° F to 90° F (3) 0° F to 70°F (4) Below 10°F 1.11 MAXIMUM WEIGHTS 8 Refer to latest issue of Lycoming Service Instruction 1014. Single Multi S.A.E. 50 S.A.E. 40 or 50 S.A.E. 40 S.A.E. 40 S.A.E. 30 S.A.E. 40 or 20W-30 S.A.E. 20 S.A.E. 20W-30 Normal Utility (a) Maximum Takeoff Weight (lbs) 2440 2020 (b) Maximum Ramp Weight (lbs) 2447 2027 (c) Maximum Landing Weight (lbs) 2440 2020 (d) Maximum Weights in Baggage Compartment (lbs) 200 0 1.13 STANDARD AIRPLANE WEIGHTS Refer to Figure 6-5 for the Standard Empty Weight and the Useful Load. 1.15 BAGGAGE SPACE (a) Compartment Volume (cubic feet) (b) Entry Width (inches) (c) Entry Height (inches) 1.17 SPECIFIC LOADINGS (a) Wing Loading (lbs per sq ft) (b) Power Loading (lbs per hp) REPORT: VB-1180 1-4 222 24 22 20 14.4 15.3 ISSUED: AUGUST 13, 1982 PIPER AIRCRAFT CORPORATION PA-28-161, WARRIOR II SECTION 1 GENERAL 1.19 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY The following definitions are of symbols, abbreviations and termi- nology used throughout the handbook and those which may be of added operational significance to the pilot. (a) General Airspeed Terminology and Symbols CAS KCAS GS IAS KIAS M TAS VA VFE Calibrated Airspeed means the indicated speed of an aircraft, corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. Calibrated Airspeed expressed in Knots. Ground Speed is the speed of an airplane relative to the ground. Indicated Airspeed is the speed of an air- craft as shown on the airspeed indicator when corrected for instrument error. IAS values published in this handbook assume zero instrument error. Indicated Airspeed expressed in Knots. Mach Number is the ratio of true airspeed to the speed of sound. True Airspeed is the airspeed of an airplane relative to undisturbed air which is the CAS corrected for altitude, temperature and compressibility. Maneuvering Speed is the maximum speed at which application of full available aerodynamic control will not overstress the airplane. Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. ISSUED: AUGUST 13, 1982 REPORT: VB-1180 1-5 SECTION 1 GENERAL VNE MNE V\O V's Vso Vx Vy PIPER AIRCRAFT CORPORATION PA-28-161, WARRIOR II Never Exceed Speed or Mach Number is the speed limit that should not be exceeded at any time. Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution. Stalling Speed or the minimum steady flight speed at which the airplane is controllable. Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration. Best Angle-of-Climb Speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance. Best Rate-of-Climb Speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time. (b) Meteorological Terminology ISA OAT International Standard Atmosphere in which: The air is a dry perfect gas; The temperature at sea level is 15° Celsius (59° Fahrenheit); The pressure at sea level is 29.92 inches Hg (1013.2 mb): The tempera- ture gradient from sea level to the altitude at which the temperature is -56.5°C (-69.7° F) is -0.00198° C (-0.003564° F) per fool and zero above that altitude. Outside Air Temperature is the free air static temperature obtained either from inflight temperature indications or ground meteorological sources, adjusted for in- strument error and compressibility effects. REPORT: VB-1180 1-6 ISSUED: AUGUST 13, 1982 REVISED: JUNE 28, 1984 PIPER AIRCRAFT CORPORATION PA-28-161, WARRIOR II SECTION 1 GENERAL Indicated Pressure Altitude Pressure Altitude Station Pressure Wind (c) Power Terminology Takeoff Power Maximum Con- tinuous Power Maximum Climb Power Maximum Cruise Power The number actually read from an altimeter when the barometric subscale has been set to 29.92 inches of mercury (1013.2 millibars). Altitude measured from standard sea-level pressure (29.92 in. Hg) by a pressure or barometric altimeter. It is the indicated pressure altitude corrected for position and instrument error. In this handbook. altimeter instrument errors are assumed to be zero. Actual atmospheric pressure at field elevation. The wind velocities recorded as variables on the charts of this handbook are to be understood as the headwind or tailwind components of the reported winds. Maximum power permissible for takeoff. Maximum power permissible continuously during flight. Maximum power permissible during climb. Maximum power permissible during cruise. (d) Engine Instruments EGT Gauge Exhaust Gas Temperature Gauge ISSUED: AUGUST 13, 1982 REVISED: JUNE 28, 1984 REPORT: VB-1180 1-7 SECTION 1 GENERAL PIPER AIRCRAFT CORPORATION PA-28-161, WARRIOR II (e) Airplane Performance and Flight Planning Terminology Climb Gradient Demonstrated Crosswind Velocity Accelerate-Stop Distance Route Segment The demonstrated ratio of the change in height during a portion of a climb, to the horizontal distance traversed in the same time interval. The demonstrated crosswind velocity is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during certification tests. The distance required to accelerate an air- plane to a specified speed and, assuming failure of an engine at the instant that speed is attained, to bring the airplane to a stop. A part of a route. Each end of that part is identified by (1) a geographical location or (2) a point at which a definite radio fix can be established. (f) Weight and Balance Terminology Reference Datum Station Arm An imaginary vertical plane from which all horizontal distances are measured for balance purposes. A location along the airplane fuselage usually given in terms of distance from the reference datum. The horizontal distance from the reference datum to the center of gravity (C.G.) of an item. REPORT: VB-1180 1-8 ISSUED: AUGUST 13, 1982 REVISED: JULY 15, 1983

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