Pilot's Operating Handbook for Piper PA-28 Archer II

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

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Overview

This Pilot's Operating Handbook (POH) is specifically designed for the Piper PA-28 Archer II, providing essential information for pilots operating this aircraft. It includes detailed specifications, operational procedures, and performance data necessary for safe and efficient flight. The handbook serves as a comprehensive reference for both new and experienced pilots, ensuring they have access to critical information regarding the aircraft's systems, limitations, and emergency procedures. The POH is structured to facilitate quick reference during flight operations and ground handling, making it an indispensable tool for effective aircraft management.

Wingspan: 35 ft 10 in (10.92 m)
Maximum Takeoff Weight: 2,550 lbs (1,157 kg)
Maximum Speed: 129 knots (149 mph)
Stall Speed: 54 knots (62 mph)
Climb Rate: 730 fpm at sea level

Document

Source

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

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Document details

Type: Pilot's Operating Handbook
Pages: 328
File size: 4.4 MB
Publisher: www.jerseyaeroclub.com

Documentation completeness

3/7

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

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

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In this document

Aircraft Specifications

The Piper PA-28 Archer II features a low-wing design with a wingspan of 35 feet 10 inches (10.92 meters) and a length of 24 feet 8 inches (7.52 meters). The maximum takeoff weight is 2,550 pounds (1,157 kg), and it is powered by a Lycoming O-360 engine producing 180 horsepower.

Operating Limitations

Pilots must adhere to specific operating limitations, including a maximum speed of 129 knots (149 mph) and a stall speed of 54 knots (62 mph). The aircraft has a service ceiling of 14,000 feet (4,267 meters) and a range of approximately 600 nautical miles (1,111 km) under optimal conditions.

Emergency Procedures

In the event of an engine failure, pilots should follow the emergency checklist, which includes maintaining control of the aircraft, identifying a suitable landing area, and executing a forced landing if necessary. The POH details procedures for various emergency scenarios, including electrical failures and fuel system malfunctions.

Performance Data

The Archer II has a takeoff distance of approximately 1,800 feet (549 meters) at sea level and a landing distance of about 1,600 feet (488 meters) under standard conditions. Climb rate is approximately 730 feet per minute (fpm) at sea level.

Weight and Balance

Proper weight and balance calculations are crucial for safe flight operations. The POH provides tables and guidelines to assist pilots in determining the aircraft's center of gravity and ensuring it remains within the specified limits.

Safety notes

Always refer to the emergency procedures section in case of engine failure.
Ensure weight and balance calculations are completed before flight.

Full document text

N7669F PILOT'S OPERATING HANDBOOK PIPER CHEROKEE ARCHER II UTILITY FAA APPROVED IN NORMAL AND CATEGORIES BASED ON CAR 3 AND FAR PART 21, SUBPART J. THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY CAR 3 AND FAR PART 21, SUBPART J AND CONSTITUTES THE APPROVED AIRPLANE FLIGHT MANUAL AND MUST BE CARRIED IN THE AIRPLANE AT ALL TIMES. PA-28-181 REPORT: VB-790 FAA APPROVED BY: Ward Evand WARD EVANS D.O.A. NO. SO-1 PIPER AIRCRAFT CORPORATION VERO BEACH, FLORIDA 28-7990124 AIRPLANE SERIAL NO. N2182B AIRPLANE REGISTRATION NO. DATE OF APPROVAL: JUNE 18, 1976 HANDBOOK PART NO. 761 624 PIPER WARNING EXTREME CARE MUST BE EXERCISED TO LIMIT THE USE OF THIS MANUAL TO APPLICABLE AIRCRAFT. THIS MANUAL REVISED AS INDICATED BELOW OR SUBSEQUENTLY REVISED IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED ON THE FACE OF THE TITLE PAGE WHEN OFFICIALLY APPROVED. SUBSEQUENT REVISIONS SUPPLIED BY PIPER AIRCRAFT CORPORATION MUST BE PROPERLY INSERTED. MODEL PA-28-181, CHEROKEE ARCHER II PILOT'S OPERATING HANDBOOK, REPORT: VB-790 REVISION PIPER AIRCRAFT CORPORATION APPROVAL SIGNATURE AND STAMP. Baker REPORT: VB-790 Published by PUBLICATIONS DEPARTMENT Piper Aircraft Corporation Issued: June 18, 1976 LET Q SAFETY WARNING Vacuum/Pressure Gyroscopic Flight Instrument System ATTENTION: ATTENTION: MECHANIC/SERVICE FACILITY This important notice must be given to the Owner/ Operator of the aircraft into which this air pump is installed. FAILURE TO DO SO MAY RESULT IN DEATH, BODILY INJURY, OR PROPERTY DAMAGE. AIRCRAFT OWNER/OPERATOR This important notice must be (1) read and understood and followed before operating the aircraft into which this air pump is installed, (2) distributed to all pilots using the aircraft, and (3) permanently retained in the Pilot's Operating Handbook for this aircraft. FAILURE TO DO SO MAY RESULT IN DEATH, BODILY INJURY, OR PROPERTY DAMAGE. Parker Aerospace Parker Hannifin Corporation Airborne Division 711 Taylor St. P.O. Box 4032 Elyria, Ohio 44036 USA (216) 284-6300 Subject: SAFETY WARNING Instrument Power System. - Vacuum/Pressure Gyroscopic Flight Applicability: This document communicates safety warning information concerning aircraft using air pumps to power gyro flight instruments while flying Instrument Flight Rules (IFR). WARNING: FAILURE TO FOLLOW THE FOLLOWING INSTRUCTIONS MAY RESULT IN DEATH, BODILY INJURY, OR PROPERTY DAMAGE: 1. A BACK-UP PNEUMATIC POWER SOURCE FOR THE AIR DRIVEN GYROS, OR A BACK-UP ELECTRIC ATTITUDE GYRO INSTRUMENT, MUST BE INSTALLED IN ALL AIRCRAFT WHICH FLY IFR. 2. ANY INOPERATIVE AIR PUMP OR OTHER COMPONENT OF THE GYRO SYSTEM, AND ANY INOPERATIVE BACK-UP SYSTEM OR COMPONENT, MUST BE REPLACED PRIOR TO THE NEXT FLIGHT. 3. THIS PILOT SAFETY WARNING MUST BE PERMANENTLY RETAINED IN THE PILOT'S OPERATING HANDBOOK FOR THE AIRCRAFT INTO WHICH THIS AIR PUMP IS INSTALLED. Explanation: Failure of the air pump or any other component of the pneumatic system during IFR flight in Instrument Meteorological Conditions (IMC) can lead to spatial disorientation of the pilot and subsequent loss of aircraft control. This could result in an accident causing death, bodily injury, or property damage. Use of single-engine aircraft in IMC is increasing. Many single-engine aircraft do not have a back-up pneumatic power source or back-up electric attitude gyro instruments. In aircraft without such back-up devices, the pilot due to added workload may not be able to fly the aircraft with only "partial panel" instruments (that is, turn and pap indicator, altimeter, and airspeed indicator) in the event of primary ar pump or pneumatic system failure during IMC. Air pump or pneumatic system failures can and do occur without warning. This can be a result of various factors, including but not limited to normal wear-out of components, improper installation or maintenance, premature failure, or use of substandard overhauled components. It is recommended that an annuciator light or other device be installed to warn the pilot of loss of gyro power so that the pilot can take corrective action prior to the loss of correct gyro information. Since air pump life cannot be accurately predicted and air pumps can fail without warning, the instructions set forth in this document must be followed. Revision Number and Code Revised Pages Description of Revision PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) FAA Approval Signature and Date Rev. 6761 624 (PR 790228) 1-6 Revised para. 1.19. 1-12, 1-13 Revised para. 1.21. 6-1 Revised para. 6.1. 6-33 6-37 Revised item 113. 6-41 Added item 178. 7-10 Revised para. 7.15. 7-11 7-24 Revised para. 7.15. Revised para. 7.37. Rev. 7 761 624 (PR790413) 6-48 6-48a 7-24, 7-25 Rev. 8761.624 iii (PR800523) ✓ 1-3 ✓ 1-4 ✓ 2-2 - 2-3 ✓ 2-4 Renumbered existing items 75, 76, 77 to 74, 75, 76; added new items 77 and 78. Revised item 279. Added item 280. Revised para. 7.37. Revised applicability. Revised para. 1.3. Revised para. 1.11. Revised para. 2.7. Revised para. 2.11. Revised para. 2.13. Ward Evans Ward Evans Feb. 28, 1979 Ward Evens Ward Evans April 13, 1979 ✓ 3-i Added para. 3.28. ✓ 3-4 Added Carburetor Icing. ✓ 3-11 Added para. 3.28. ✓ 4-i ✓ 4-5 ✓ 4-6 Renumbered para.; added para. 4.28. Added descent info.; moved info. to pg. 4-6. Relocated info. from pg. 4-5. ✓ 4-13 Added para. 4.28. ✓ 4-14 ✓ 5-1 ✓5-3-5-6 ✓ 5-18 Conti. para. 4.28. Added warning. Revised para. 5.5. Revised fig. 5-15. Revised fig. 5-23. ✓ 5-25 ✓ 5-26 Revised fig. 5-24. - 5-27 Revised fig. 5-25. 5-28 4 Revised fig. 5-26. ✓ 5-29 Revised fig. 5-27. - 5-30 Revised fig. 5-29. 5-31 ✓ 6-1 ✓ 6-3 ✓ 6-14. Revised fig. 5-31. Revised para. 6.1. Added caution. Revised Fig. 6-15. Revised item 11; added item 17. Added item 122; moved items 129 and 131 to ✓ 6-19 ✓ 6-37 pg. 6-38. REPORT: VB-790 iv-c Description of Revision Relocated items 129 and 131 from pg. 6-37. Relocated items 169 thru 177 from pg. 6-41; Revised items 173 and 175. Revision Number and Revised Code Pages Rev. 8761 624 ✓ 6-38 (PR800523)

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(cont) ✓ 6-40 ✓ 6-41 ✓ 6-42 7-1 ✓ 7-10 ✓ 8-11 Revised para. 7.13. 10-2 V Revised para. 8.19. Added para. (j). Moved items 169 thru 177 to pg. 6-40; added item 180; relocated item 183 from pg. 6-42. Moved item 183 to pg. 6-41. Revised para. 7.5. FAA Approval Signature and Date Ward Evans Ward Evans May 23, 1980 REPORT: VB-790 iv-d Revision Number and Revised Pages Code PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) Description of Revision FAA Approval Signature and Date Rev. 4761 624 1-3 (PR770712) 1-11, 1-12, Added new propeller to 1.5 and added footnote. Revised section 1.21, Conversion Factors. 1-13, 1-14 2-2 Added new propeller to 2.7, item (j) and added footnote. 4-4 4-9 4-10 5-9 5-19 5-20 5-21 5-22 5-23 5-24 5-25 5-26 5-27 5-28 5-29 5-30 5-31 5-32 5-33 5-34 Revised Starting With External Power Source. Revised item 4.13 (d) Starting Engine With External Power Source. Added CAUTION. Revised page nos.; revised titles; added pages; added figures. Added ser. nos. Relocated Fig. 5-19 to page 5-21; added new chart (Fig. 5-18). Relocated Fig. 5-21 to page 5-23; added re- located Fig. 5-19; added ser. nos. Relocated Fig. 5-23 to page 5-25; added new chart (Fig. 5-20). Relocated Fig. 5-25 to page 5-27; added re- located Fig. 5-21; added ser. nos. Relocated Fig. 5-27 to page 5-29; added new chart (Fig. 5-22). Relocated Fig. 5-29 to page 5-30; added re- located Fig. 5-23; added ser. nos. Relocated Fig. 5-31 to page 5-31; added new chart (Fig. 5-24). Relocated Fig. 5-33 to page 5-32; added re- located Fig. 5-25; added ser. nos. Relocated Fig. 5-35 to page 5-33; added new chart (Fig. 5-26). Added page (added relocated Fig. 5-27). Added page (added relocated Fig. 5-29). Added page (added relocated Fig. 5-31). Added page (added relocated Fig. 5-33). Added page (added relocated Fig. 5-35). Added page (int. blank). 6-17 Added item 3. 6-33 Added items 76 and 77. 6-45 6-46 6-47 Added item 223; renumbered items; re- located item. Added relocated items; renumbered items; added new items; relocated items; removed footnotes; added footnote. Added relocated items; renumbered items: added new items; relocated items; added footnote. REPORT: VB-790 iv-a Revision Number and Code Revised Pages PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) FAA Approval Signature and Date Description of Revision Rev. 4 761 624 (PR770712) (cont) 6-48 Added relocated items; renumbered items; added new items; revised item 277; relocated items; added footnotes. 6-48a 6-48b 6-49 6-50 7-1 7-18 Added page (added relocated items and new item). Added page. Renumbered items; revised items 325 and 329. Renumbered items; revised item 349. Added new propeller model to para. 7.5. Revised alternate static source description in para. 7.21. Ward Evans Ward Evans July 12, 1977 Rev. 5761 624 (PR780703) REPORT: VB-790 iv-b 1-4 Revised note. Revised propeller tolerance RPM. 2-7 3-3 3-7 1223 2 7F I 4-5 4-9 Added additional Takeoff Check List. Added Primer information to “Engine Power Loss During Takeoff” check list. Added Primer information to "Engine Power Loss During Takeoff." Added Primer information to "Before Takeoff" check list. Deleted "pressing in" of magneto switch as necessary. Added Primer checked information to para- graph. 4-12 5-5 Changed item 5 from Cruise Fuel to Cruise Fuel Consumption. 5-25 Added note to graph. 5-26 Added note to graph. 5-27 Added note to graph. 5-28 Added note to graph. 6-1 Changed paragraph. 6-35 Changed item 93. 6-41 Added Collins VHF-250 to item 169, added Collins VIR-350 to item 171. 6-42 Relocated item 187, 189 and 191; added items to 189 and 191. 6-43 6-44 6-50 Relocated item 187, 189 and 191, added items 194 and 195, changed item 195 to 196. Relocated items 201, 203 and 205, revised item 211. Added vendor information to item 349. 7-21 Added "Caution" to 7.23. 7-24 Removed ELT information from 7.37. 8-i Added 8.29 Cold Weather Operation to table of Ward Evans contents. 8-15 Added 8.29 Cold Weather Operation. July 3, 1978 TABLE OF CONTENTS SECTION 1 SECTION 2 GENERAL LIMITATIONS EMERGENCY PROCEDURES PERFORMANCE SECTION 3 SECTION 4 NORMAL PROCEDURES SECTION 5 SECTION 6 SECTION 7 SECTION 8 WEIGHT AND BALANCE DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS AIRPLANE HANDLING, SERVICING AND MAINTENANCE SUPPLEMENTS SECTION 9 SECTION 10 SAFETY TIPS REPORT: VB-790 V I Paragraph No. 1.1 Introduction 1.3 Engines. 1.5 Propellers 1.7 Fuel 1.9 Oil 1.11 TABLE OF CONTENTS SECTION 1 GENERAL Maximum Weights 1.13 Standard Airplane Weights 1.15 Baggage Space 1.17 Specific Loadings 1.19 Symbols, Abbreviations and Terminology 1.21 Conversion Factors 1-1 1-3 1-3 1-3 1-3 1-4 1-4 1-4 1-4 IIIII ZA Page No. 1-5 1-11 REPORT: VB-790 1-i PIPER AIRCRAFT CORPORATION PA-28-181, CHEROKEE ARCHER 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 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 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, figure numbers, item numbers and pages noted as being left blank intentionally. ISSUED: JUNE 18, 1976 REPORT: VB-790 1-1 SECTION 1 GENERAL REPORT: VB-790 1-2 5' 3.00" 12' 10.48" 35' 0.00" -23' 9.60" ล 10' 0.00" PIPER AIRCRAFT CORPORATION PA-28-181, CHEROKEE ARCHER II 2' 6.00" Wing Area (sq. ft.) Min. Turning Radius (ft.) (from pivot point to wingtip) STATIC GROUND LINE 6' 6.91" THREE VIEW Figure 1-1 7' 3.68" 170.0 30.0 3' 6.20" ISSUED: JUNE 18, 1976 PIPER AIRCRAFT CORPORATION PA-28-181, CHEROKEE ARCHER 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 1 Lycoming 0-360-A4A or 0-360-A4M | 180 2700 5.125 4.375 361.0 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 1 Sensenich 76EM8S5-0-60* or 76EM8S5-0-62 ** 2 76 76 Fixed Pitch 1.7 FUEL (a) Fuel Capacity (U.S. gal) (total) (b) Usable Fuel (U.S. gal) (total) (c) Fuel Grade, Aviation (1) Minimum Octane (2) Specified Octane (3) Alternate Fuel 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 *Serial nos. 28-7790001 through 28-7790607. **Serial nos. 28-7890001 and up. ISSUED: JUNE 18, 1976 REVISED: MAY 23, 1980 48 000 50 100/130 Green 100/130 Green Refer to latest issue of Lycoming Instruction No. 1070. .8 Refer to latest issue of Lycoming Service Instruction 1014. SINGLE S.A.E. 50 S.A.E. 40 MULTI S.A.E. 40 or 50 S.A.E. 40 S.A.E. 30 S.A.E. 40 or 20W-30 S.A.E. 20 S.A.E. 20W-30 REPORT: VB-790 1-3

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