PILOT'S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL

Piper PA-28 Archer III · Training Manual

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Overview

This Pilot's Operating Handbook (POH) is specifically designed for the Piper PA-28-181 Archer III, providing essential information for pilots operating this aircraft. Approved by the FAA for both normal and utility categories, the handbook includes all necessary material required by CAR 3 regulations. It serves as a comprehensive guide for understanding the operational limitations, performance characteristics, and emergency procedures associated with the Archer III. Pilots are advised to familiarize themselves with the handbook to ensure safe and effective flight operations, as it is not a substitute for proper flight training or instruction.

Maximum Ramp Weight: 2558 lbs (Normal), 2138 lbs (Utility)
Maximum Takeoff Weight: 2550 lbs (Normal), 2130 lbs (Utility)
Fuel Capacity: 50 U.S. gallons, Usable Fuel: 48 U.S. gallons
Engine: Lycoming O-360-A4M, 180 BHP at 2700 RPM
Oil Capacity: 8 U.S. quarts, with specific viscosity recommendations based on temperature

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Document details

Type: Training Manual
Year: 1995
Pages: 422
File size: 13 MB
Publisher: independentaviation.training

Documentation completeness

3/7

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

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

More Piper PA-28 Archer IIImanuals & documents

In this document

General

The General section introduces the Pilot's Operating Handbook, emphasizing its role as an operational guide for pilots. It outlines the importance of understanding the aircraft's limitations, performance, and procedures before flight. The section also highlights the pilot's responsibility for ensuring the aircraft's airworthiness and adherence to operational limitations.

Limitations

This section details the operational limitations of the Piper PA-28-181 Archer III, including maximum weights for normal and utility categories. The maximum ramp weight is 2558 lbs for normal operations and 2138 lbs for utility operations. Maximum takeoff and landing weights are both 2550 lbs for normal and 2130 lbs for utility.

Emergency Procedures

Emergency procedures are crucial for ensuring safety during flight. This section provides guidelines for handling various emergency situations, including engine failure, electrical malfunctions, and other critical scenarios that may arise during operation.

Performance

The Performance section outlines the aircraft's capabilities, including takeoff distances, climb rates, and fuel consumption. For instance, the Archer III has a takeoff power of 180 BHP at 2700 RPM, and its fuel capacity is 50 U.S. gallons, with 48 gallons usable.

Weight and Balance

This section provides information on the weight and balance requirements for the Archer III, including maximum ramp weight, takeoff weight, and landing weight. It also discusses the importance of maintaining proper center of gravity (C.G.) limits for safe flight.

Description and Operation of the Airplane and Its Systems

This section describes the various systems of the Archer III, including the engine, fuel system, and electrical system. It provides detailed information on the operation and maintenance of these systems to ensure optimal performance.

Airplane Handling, Servicing and Maintenance

Guidelines for the proper handling, servicing, and maintenance of the Archer III are provided in this section. It emphasizes the importance of regular inspections and adherence to maintenance schedules to ensure the aircraft remains in airworthy condition.

Supplements

The Supplements section includes additional information and updates relevant to the Archer III, such as modifications, equipment changes, and operational tips.

Operating Tips

This section offers practical tips for pilots to enhance their flying experience with the Archer III, including best practices for takeoff, landing, and in-flight operations.

Safety notes

Ensure the handbook is current and applicable to the specific aircraft being operated.
Pilots must familiarize themselves with limitations and emergency procedures before flight.

Full document text

ARCHER III PA-28-181 SN 2843001 AND UP PILOT'S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL FAA APPROVED IN NORMAL AND UTILITY CATEGORIES BASED ON CAR 3. THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY CAR 3 AND CONSTITUTES THE APPROVED AIRPLANE FLIGHT MANUAL AND MUST BE CARRIED IN THE AIRPLANE AT ALL TIMES. AIRPLANE AIRPLANE SERIAL NO. ________________________ REGIST. NO. _____________________ PA-28-181 REPORT: VB-1611 FAA APPROVED BY: PETER E. PECK D.O.A. NO. SO-1 DATE OF APPROVAL: THE NEW PIPER AIRCRAFT, INC. JULY 12, 1995 VERO BEACH, FLORIDA REPORT: VB-1611 ii WARNING EXTREME CARE MUST BE EXERCISED TO LIMIT THE USE OF THIS HANDBOOK TO APPLICABLE AIRCRAFT. THIS HAND- BOOK IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED ON THE FACE OF THE TITLE PAGE. SUBSEQUENT REVISIONS SUPPLIED BY PIPER MUST BE PROPERLY INSERTED. Published by PUBLICATIONS DEPARTMENT Issued: July 12, 1995 © 1995 THE NEW PIPER AIRCRAFT, INC. All Rights Reserved ISSUED: JULY 12, 1995 REPORT: VB-1611 REVISED: JANUARY 5, 2004 iii APPLICABILITY Application of this handbook is limited to the specific Piper PA-28-181 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. WARNING INSPECTION, MAINTENANCE AND PARTS REQUIREMENTS FOR ALL NON-PIPER APPROVED STC INSTALLATIONS ARE NOT INCLUDED IN THIS HANDBOOK. WHEN A NON-PIPER APPROVED STC INSTALLATION IS INCORPORATED ON THE AIRPLANE, THOSE PORTIONS OF THE AIRPLANE AFFECTED BY THE INSTALLATION MUST BE INSPECTED IN ACCORDANCE WITH THE INSPECTION PROGRAM PUBLISHED BY THE OWNER OF THE STC. SINCE NON-PIPER APPROVED STC INSTALLATIONS MAY CHANGE SYSTEMS INTERFACE, OPERATING CHARACTERISTICS AND COMPONENT LOADS OR STRESSES ON ADJACENT STRUCTURES, PIPER PROVIDED INSPECTION CRITERIA MAY NOT BE VALID FOR AIRPLANES WITH NON-PIPER APPROVED STC INSTALLATIONS. REPORT: VB-1611 ISSUED: JULY 12, 1995 iv REVISED: JANUARY 5, 2004 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 airplane 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. Insert page numbers followed by a small letter in direct sequence with the same common numbered page. II. Identification of Revised Material Revised text and illustrations are indicated by a black vertical line located along the outside margin of each revised page opposite the revised, added, or deleted information. A black vertical line next to the page number indicates that an entire page has been changed or added. Black vertical lines indicate current revisions only. Correction of typographical or grammatical errors or the physical relocation of information on a page will not be indicated by a symbol. ORIGINAL PAGES ISSUED The original pages issued for this handbook prior to revision are given below: Title, ii through viii, 1-1 through 1-18, 2-1 through 2-10, 3-1 through 3-16, 4-1 through 4-28, 5-1 through 5-34, 6-1 through 6-12, 7-1 through 7-26, 8-1 through 8-20, 9-1 through 9-14, 10-1 through 10-2. Rev. 1 v Added Rev. 1 to L of R page. (PR961118) 4-27 Revised para. 4.43. 5-3 Revised para. 5.5 (a)(6). 5-7 Revised para. 5.5 (g)(1) 5-26 Revised fig. 5-27. 5-27 Revised fig. 5-27a. 5-28 Revised fig. 5-29. Peter E. Peck 5-29 Revised fig. 5-29a. 8-14 Revised para. 8.21.(c) Nov. 18, 1996 Date Rev. 2 v Added Rev. 2 to L of R page. (PR970403) 5-4 Revised para. 5.5 (b)(5). 5-28 Revised fig. 5-29. 5-29 Revised fig. 5-29a. 5-32 Revised fig. 5-35. 5-33 Revised fig. 5-37. 7-i Rev. TOC. 7-27 Added para. 7.39. 7-28 Added blank page. 9-15 Added Supplement 4 thru Bendix/King KLN89 (B) 9-26 GPS Nav. System 9-27 Added Supplement 5 thru Bendix/King KX 155A 9-38 Comm/Nav System Peter E. Peck 9-39 Added Supplement 6 9-40 Added blank page. APRIL 3, 1997 Date PILOT'S OPERATING HANDBOOK LOG OF REVISIONS REPORT: VB-1611 v Current Revisions to the PA-28-181 ARCHER III Pilot's Operating Handbook, REPORT: VB-1611 issued July 12, 1995. Revision FAA Approval Number and Revised Description of Revisions Signature and Code Pages Date REPORT: VB-1611 ISSUED: JULY 12, 1995 vi REVISED: NOVEMBER 6, 1998 Rev. 3 vi Added Rev. 3 to L of R page. (PR980312) 5-18 Revised fig. 5-15. Peter E. Peck 9-39 Revised header & title. 9-40 Revised header. March 12, 1998 Date Rev. 4 (PR980331) vi Added Rev. 4 to L of R page. 5-14 Revised Fig. 5-7. 5-15 Revised Fig. 5-9. 5-16 Revised Fig. 5-11. 5-17 Revised Fig. 5-13. 5-18 Revised Fig. 5-15. 5-19 Revised Fig. 5-17. 5-20 Revised Fig. 5-19. 5-30 Revised Fig. 5-31. Peter E. Peck 5-32 Revised Fig. 5-35. 5-33 Revised Fig. 5-37. March 31, 1998 Date Rev. 5 vi Added Rev. 5 to L of R page. (PR981106) 4-10 Revised para. 4.5. 4-11 Revised para. 4.5. 4-22 Revised para. 4.23. 5-13 Revised Fig. 5-5. 5-15 Revised Fig. 5-9. 5-17 Revised Fig. 5-13. 5-31 Revised Fig. 5-33. 9-i Revised T of C. 9-41 Added Supplement 7 - Peter E. Peck thru Garmin GNS 430 Nav/Comm. 9-48 Nov. 6, 1998 Date PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Revision FAA Approval Number and Revised Description of Revisions Signature and Code Pages Date Rev. 6 vi-a Added page. (PR981218) vi-b Added page.

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9-i Revised T of C. Peter E. Peck 9-49 Added page. 9-50 Added page. Dec. 18, 1998 Date Rev. 7 vi-a Added Rev. 7 to L of R. (PR991206) 5-23 Revised Fig. 5-20b. 9-i Revised T of C. 9-51 Added pages Christina L. Marsh thru and Supplement 9. 9-52 Dec. 6, 1999 Date Rev. 8 vi-a Added Rev. 8 to L of R. (PR000714) 9-i Revised T of C. 9-47 Revised Section 4. 9-53 Added pages thru and Supplement 10. 9-58 9-59 Added pages thru and Supplement 11. 9-62 9-63 Added pages Christina L. Marsh thru and Supplement 12. 9-70 July 14, 2000 Date Rev. 9 vi-a Added Rev. 9 to L of R. (PR010102) vi-b Added Rev. 9 to L of R. 9-i Revised T of C. 9-71 Added pages thru and Supplement 13. 9-80 PILOT'S OPERATING HANDBOOK LOG OF REVISIONS ISSUED: JULY 12, 1995 REPORT: VB-1611 REVISED: JANUARY 2, 2001 vi-a Revision FAA Approval Number and Revised Description of Revisions Signature and Code Pages Date Rev. 9 9-81 Added pages (PR010102) thru and Supplement 14. continued 9-82 9-83 Added pages thru and Supplement 15. 9-88 9-89 Added pages thru and Supplement 16. 9-94 9-95 Added pages Christina L. Marsh thru and Supplement 17. 9-98 Jan. 2, 2001 Date Rev. 10 vi-b Added Rev. 10 to L of R. (PR020415) 3-4 Revised para. 3.5. 4-7 Revised para. 4.5. 4-8 Revised para. 4.5. 4-9 Revised para. 4.5. Albert J. Mill 4-18 Revised para. 4.13. 4-19 Revised para. 4.13. April 15, 2002 Date Rev. 11 iii Added Warning and moved (PR040105) info. to page iv. iv Moved info. from page iii. vi-b Added Rev. 11 to L of R. vi-c Added page and Rev. 11 to L of R. vi-d Added page. 8-1 Moved info. to page 8-1b and revised para. 8.1. 8-1a Added page and revised para. 8.1. PILOT'S OPERATING HANDBOOK LOG OF REVISIONS REPORT: VB-1611 ISSUED: JULY 12, 1995 vi-b REVISED: JANUARY 5, 2004 Revision FAA Approval Number and Revised Description of Revisions Signature and Code Pages Date Rev. 11 8-1b Added page and moved info. (PR040105) from pages 8-1 and 8-2. continued 8-2 Moved info. to page 8-1b and revised para. 8.3. 9-i Revised T of C. Albert J. Mill 9-99 Added pages thru and Supplement 18. Jan. 5, 2004 9-102 Date Rev. 12 vi-c Added Rev. 12 to L of R. (PR040614) 9-i Revised T of C. 9-103 Added pages thru and Supplement 19. Albert J. Mill 9-110 June 14, 2004 Rev. 13 vi-c Added Rev. 13 to L of R. (PR041007) 9-i Revised T of C. 9-111 Added pages thru and Supplement 20. 9-128 9-129 Added pages thru and Supplement 21. 9-132 Linda J. Dicken October 7, 2004 Rev. 14 vi-c Added Rev. 14 to L of R. (PR050912) 9-i Revised T of C. 9-111 Revised Supplement 20. thru 9-138 9-139 Revised page numbers. thru 9-142 9-143 Added pages thru and Supplement 22. Linda J. Dicken 9-152 Sept. 12, 2005 Revision FAA Approval Number and Revised Description of Revisions Signature Code Pages and Date PILOT'S OPERATING HANDBOOK LOG OF REVISIONS ISSUED: JULY 12, 1995 REPORT: VB-1611 REVISED: SEPTEMBER 12, 2005 vi-c PILOT'S OPERATING HANDBOOK LOG OF REVISIONS REPORT: VB-1611 ISSUED: JULY 12, 1995 vi-d REVISED: APRIL 11, 2008 Revision FAA Approval Number and Revised Description of Revisions Signature Code Pages and Date Rev. 15 vi-d Added Rev. 15 to L of R. (PR051128) 9-116 Revised Section 3. 9-119 Revised Section 3. Linda J. Dicken 9-123 Revised Section 3. Nov. 28, 2005 Rev. 16 vi-d Added Rev. 16 to L of R. (PR060109) 9-i Revised T of C. 9-111 Revised Supplement 20. thru Linda J. Dicken 9-138 Jan. 9, 2006 Rev. 17 vi-d Added Rev. 17 to L of R. (PR060214) 9-ii Revised T of C. 9-116 Revised Section 3. 9-119 Revised Section 3. 9-120 Revised Section 3. 9-123 Revised Section 3. 9-124 Revised Section 3. 9-153 Added pages thru and Supplement 23. Linda J. Dicken 9-188 Feb. 14, 2006 Rev. 18 vi-d Added Rev. 18 to L of R. (PR060411) 9-131 Revised Section 7A. Linda J. Dicken 9-179 Revised Section 7A. April 11, 2006 Rev. 19 vi-d Added Rev. 19 to L of R. (PR070129) 8-20 Revised para. 8.29. Linda J. Dicken Jan. 29, 2007 Rev. 20 vi-d Added Rev. 20 to L of R. (PR080411) 9-155 Revised Supp 23, Section 1. 9-164 Revised Supp 23, Section 3. 9-178 Revised Supp 23, Section 4. 9-186 Revised Supp 23, Section 7B. Albert J. Mill April 11, 2008 PA-28-181Archer III Rev. 21 v-e,f Added new pages to L of R. (PR081015) vi-e Added Rev. 21 to L of R. 9-ii Added Supplements 24 and Albert J. Mill 25 to Section 9 TOC. Oct. 15, 2008 9-189 Added Supplements 24 and thru 25 to Section 9. 9-202 Rev. 22 vi-e Added Rev. 22 to L of R. (PR090615) 4-7 Revise Note in Para. 4.5. 4-17 Revise Note in Para. 4.9. 8-1b Revised text in Para. 8.1. Albert J. Mill 9-112 Revised text in Para. 8.1. June 15, 2009 9-154 Revised text in Para. 8.1. Rev. 23 vi-e Added Rev. 23 to L of R. (PR100205) 4-23 Revised Para. 4.27. 7-13 Revised Para. 7.19. 7-15 Revised callouts for Instrument Panel. 9-ii Added Supplements 26 and 27 to TOC. 9-203 Added pages. thru 9-206 Rev. 24 vi-e,f Added Rev. 24 to L of R. (PR100729) 2-8 Added Note to Para. 2.25. 7-25 Revised Para. 7.37. 7-26 Revised Para. 7.37. 9-ii Revised T.O.C. 9-205 Revised Supplement 27. 9-206 Revised Supplement 27. 9-207 Added pages. Albert J. Mill thru July 29, 2010 9-216 ISSUED: JULY 12, 1995 REPORT: VB-1611 REVISED: JULY 29, 2010 vi-e PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Albert J. Mill February 5, 2010 PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Revision FAA Approved Number and Revised Signature Code Pages Description of Revisions and Date REPORT: VB-1611 ISSUED: JULY 12, 1995 vi-f REVISED: OCTOBER 15, 2008 REPORT: VB-1611 vii 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 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS SECTION 8 AIRPLANE HANDLING, SERVICING AND MAINTENANCE SECTION 9 SUPPLEMENTS SECTION 10 OPERATING TIPS REPORT: VB-1611 viii THIS PAGE INTENTIONALLY LEFT BLANK TABLE OF CONTENTS SECTION 1 GENERAL Paragraph Page No. No. 1.1 Introduction .................................................................................. 1-1 1.3 Engines ......................................................................................... 1-3 1.5 Propellers...................................................................................... 1-3 1.7 Fuel ............................................................................................. 1-3 1.9 Oil ............................................................................................... 1-4 1.11 Maximum Weights ....................................................................... 1-4 1.13 Standard Airplane Weights........................................................... 1-4 1.15 Baggage Space ............................................................................. 1-5 1.17 Specific Loadings ......................................................................... 1-5 1.19 Symbols, Abbreviations and Terminology ................................... 1-6 1.21 Conversion Factors ....................................................................... 1-12 REPORT: VB-1611 1-i REPORT: VB-1611 1-ii THIS PAGE INTENTIONALLY LEFT BLANK 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 F.A.R./C.A.R. 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 responsi- bility 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 and emergency procedures have been placed ahead of the normal proce-dures, performance and other sections to provide easier access to informa-tion 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 intentionally left blank. SECTION 1 PA-28-181, ARCHER III GENERAL ISSUED: JULY 12, 1995 REPORT: VB-1611 1-1 SECTION 1 GENERAL PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 1-2 THREE VIEW 1.3 ENGINES (a) Number of Engines 1 (b) Engine Manufacturer Lycoming (c) Engine Model Number O-360-A4M (d) Takeoff Power (BHP) 180 (e) Takeoff Power Engine Speed (RPM) 2700 (f) Bore (inches) 5.125 (g) Stroke (inches) 4.375 (h) Displacement (cubic inches) 361.0 (i) Compression Ratio 8.5:1 (j) Engine Type Four Cylinder, Direct Drive, Horizontally Opposed, Air Cooled 1.5 PROPELLERS (a) Number of Propellers 1 (b) Propeller Manufacturer Sensenich (c) Model 76EM8S14-0-62 (d) Number of Blades 2 (e) Propeller Diameter (inches) (1) Maximum 76 (2) Minimum 76 (f) Propeller Type Fixed Pitch 1.7 FUEL AVGAS ONLY (a) Fuel Capacity (U.S. gal.) (total) 50 (b) Usable Fuel (U.S. gal.) (total) 48 (c) Fuel (1) Minimum Octane 100 Green or 100LL Blue Aviation Grade (2) Alternate Fuel Refer to latest issue of Lycoming Instruction No. 1070. SECTION 1 PA-28-181, ARCHER III GENERAL ISSUED: JULY 12, 1995 REPORT: VB-1611 1-3 SECTION 1 GENERAL PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 1-4 1.9 OIL (a) Oil Capacity (U.S. quarts) 8 (b) Oil Specification Refer to latest issue of Lycoming Service Instruction 1014. (c) Oil Viscosity per Average Ambient Temp. for Starting Single Multi (1) Above 60°F S.A.E. 50 S.A.E. 40 or 50 (2) 30°F to 90°F S.A.E. 40 S.A.E. 40 (3) 0°F to 70°F S.A.E. 30 S.A.E. 40 or 20W-30 (4) Below 10°F S.A.E. 20 S.A.E. 20W-30 1.11 MAXIMUM WEIGHTS Normal Utility (a) Maximum Ramp Weight (lbs.) 2558 2138 (b) Maximum Takeoff Weight (lbs.) 2550 2130 (c) Maximum Landing Weight (lbs.) 2550 2130 (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) 24 (b) Entry Width (inches) 22 (c) Entry Height (inches) 20 1.17 SPECIFIC LOADINGS (a) Wing Loading (lbs. per sq. ft.) 15.0 (b) Power Loading (lbs. per hp) 14.2 SECTION 1 PA-28-181, ARCHER III GENERAL ISSUED: JULY 12, 1995 REPORT: VB-1611 1-5 SECTION 1 GENERAL PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 1-6 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 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. KCAS Calibrated Airspeed expressed in ``Knots.’’ GS Ground Speed is the speed of an airplane relative to the ground. IAS 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. KIAS Indicated Airspeed expressed in ``Knots.’’ TAS True Airspeed is the airspeed of an airplane relative to undisturbed air which is the CAS corrected for altitude, temperature and compressibility. VA Maneuvering Speed is the maximum speed at which application of full available aerodynamic control will not overstress the airplane. VFE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. Vne/Mne Never Exceed Speed or Mach Number is the speed limit that may not be exceeded at any time. Vno Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution. VS Stalling Speed or the minimum steady flight speed at which the airplane is con- trollable. Vso Stalling Speed or the minimum steady flight speed at which the airplane is con- trollable in the landing configuration. Vx Best Angle-of-Climb Speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance. Vy Best Rate-of-Climb Speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time. (b) Meteorological Terminology ISA 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 -0.00198C (-0.003564°F) per foot and zero above that altitude. OAT Outside Air Temperature is the free air static temperature, obtained either from inflight temperature indications or ground meteorological sources, adjusted for instrument error and compressibility effects. SECTION 1 PA-28-181, ARCHER III GENERAL ISSUED: JULY 12, 1995 REPORT: VB-1611 1-7 SECTION 1 GENERAL PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 1-8 Indicated T h e n u m b e r a c t u a l l y r e a d f r o m a n Pressure Altitude altimeter when the barometric subscale has been set to 29.92 inches of mercury (1013.2 millibars). Pressure Altitude 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. Station Pressure Actual atmospheric pressure at field elevation. Wind 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. (c) Power Terminology Takeoff Power Maximum power permissible for takeoff. Maximum Maximum power permissible continuously Continuous during flight. Power (d) Engine Instruments EGT Gauge Exhaust Gas Temperature Gauge (e) Airplane Performance and Flight Planning Terminology Climb Gradient The demonstrated ratio of the change in height during a portion of a climb, to the horizontal distance traversed in the same time interval. Demonstrated The demonstrated crosswind velocity is the Crosswind velocity of the crosswind component for Velocity which adequate control of the airplane (Demo. X-Wind) during takeoff and landing was actually demonstrated during certification tests. Accelerate-Stop The distance required to accelerate an air- Distance 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. Route Segment 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 An imaginary vertical plane from which all horizontal distances are measured for balance purposes. Station A location along the airplane fuselage usually given in terms of distance from the reference datum. Arm The horizontal distance from the reference datum to the center of gravity (C.G.) of an item. SECTION 1 PA-28-181, ARCHER III GENERAL ISSUED: JULY 12, 1995 REPORT: VB-1611 1-9 SECTION 1 GENERAL PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 1-10 Moment The product of the weight of an item multi- plied by its arm. (Moment divided by a constant is used to simplify balance calcu- lations by reducing the number of digits.) Center of Gravity The point at which an airplane would (C.G.) balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane. C.G. Arm The arm obtained by adding the airplane’s individual moments and dividing the sum by the total weight. C.G. Limits The extreme center of gravity locations within which the airplane must be operated at a given weight. Usable Fuel Fuel available for flight planning. Unusable Fuel Fuel remaining after a runout test has been completed in accordance with govern- mental regulations. Standard Empty Weight of a standard airplane including Weight unusable fuel, full operating fluids and full oil. Basic Empty Standard empty weight plus optional Weight equipment. Payload Weight of occupants, cargo and baggage. Useful Load Difference between takeoff weight, or ramp weight is applicable, and basic empty weight. Maximum Ramp Maximum weight approved for ground Weight maneuver. (It includes weight of start, taxi and run up fuel.) Maximum Maximum weight approved for the start of Takeoff Weight the takeoff run. Maximum Maximum weight approved for the landing Landing Weight touchdown. Maximum Zero Maximum weight exclusive of usable fuel. Fuel Weight SECTION 1 PA-28-181, ARCHER III GENERAL ISSUED: JULY 12, 1995 REPORT: VB-1611 1-11 SECTION 1 GENERAL PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 1-12 1.21 CONVERSION FACTORS MULTIPLY BY TO OBTAIN centimeters (cm) 0.032808 feet (ft.) 0.3937 inches (in.) 0.01 meters (m) centimeters of 13.3322 hectopascals (hPa) mercury at 0° C .3937 inches of mercury (in. Hg) (cm Hg) 27.85 pounds / sq. foot (Ibf./ft2) 0.1934 pounds / sq. inch (Ibf./in2) cubic centimeters (cm3) 3.531x10-5 cubic feet (ft3) 0.06102 cubic inches (in3) 0.001 Liters (1) 0.03381 fluid ounces (fl. oz) 2.642x10-4 U.S. gallons (U.S. gal) cubic feet (ft3) 28317 cubic centimeters (cm3) 7.481 U.S. gallons (U.S. gal) 1728 cubic inches (in3) 28.32 liters (1) 0.028317 cubic meters (m3) cubic inches (in3) 16.39 cubic centimeters (cm3) 5.787x10-4 cubic feet (ft3) 4.329x10-3 U.S. gallons (U.S. gal) 0.01639 liters (1) 1.639x10-5 cubic meters (m3) 0.5541 fluid ounces (fl. oz) 0.01732 U.S. quarts (U.S. qt) cubic meters (m3) 35.3147 cubic feet (ft3) 264.2 U.S. gallons (U.S. gal) 61024 cubic inches (in3) 1000000 liters (1) degrees arc. (deg) 0.01745 radians degrees arc per second 0.01745 radians per second (deg / sec) 0.166667 revolutions per second (rpm) MULTIPLY BY TO OBTAIN drams, fluid (dr. fl.) 3.697x10-3 liters (1) 3.697x10-6 cubic meters (m3) 0.125 fluid ounces (fl. oz) feet (ft) 30.48 centimeters (cm) 12 inches 0.3048 meters (m) 1.8939x10-4 miles (mi) 1.6458 nautical miles (NM) 0.0606061 rods feet per minute (ft / min) 0.01829 kilometers per hour (km / hr) 9.8716x10-3 knots (kt) 0.00508 meters per second (m / s) 0.01136 miles per hour (mph) feet per second (ft / sec) 1.097 kilometers per hour (km / hr) 0.5921 knots (kt) 0.3048 meters per second (m / s) 0.6818 miles per hour (mph) foot-pounds (ft.-lbs.) 3.2383x10-4 kilocalorie (kcal) 1.3558 joules (j) 14.5939 newton-meters (n-m) foot-pound per minute 3.03x10-5 horse power (hp) (ft-lbs/ min) 81.348 joules per minute (j / min) foot-pound per second 1.818x10-5 horse power (hp) (ft-lbs/ sec) 1.3558 joules per second (j / sec) gallons, imperial 4.546x10-3 cubic centimeters (cm3) (imperial gal) 1.201 U.S. gallon (U.S. gal) 277.4 cubic inches (in3) 4.546 liters (l) gallons, U.S. dry 4.405x10-3 cubic meters (m3) (U.S. gal dry) 0.1556 cubic feet (ft3) 1.164 U.S. gallon (U.S. gal) 268.8 cubic inches (in3) 4.405 liters (l) SECTION 1 PA-28-181, ARCHER III GENERAL ISSUED: JULY 12, 1995 REPORT: VB-1611 1-13 SECTION 1 GENERAL PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 1-14 MULTIPLY BY TO OBTAIN gallons, U.S. Liquid 3785.4 cubic centimeters (cm3) (U.S. gal) 0.1337 cubic feet (ft3) 0.83268 imperial gallons (imperial gal) 231 cubic inches (in3) 3.785 liters (1) 3.785x10-3 cubic meters (m3) 128 fluid ounces (fl. oz) hectares (ha) 2.471 acres 107639 square feet (ft2) 10000 square meters (m2) horsepower (hp) 33000 foot-pound per minute (ft-lbs / min) 550 foot-pound per second (ft-lbs / sec) 745.7 joules per second (j / sec) 1.014 metric horsepower (metric hp) 8.026x103 newton-meters per second (n-m / sec) horsepower, metric 0.9863 horsepower (hp) 735.484 joules per second (j / sec) 8.138x103 newton-meters per second (n-m / sec) inches (in) 2.54 centimeters (cm) 0.08333 feet (ft) 0.0254 meters (m) 25.4 millimeters (mm) inches of mercury 0.033421 atmospheres (atm) 2.54 centimeters of mercury (cm Hg) 33.8639 hectopascals (hPa) 70.73 pounds per square foot (Ibf / ft2) 0.4912 pounds per square inch Ibf / in2) 25.4 millimeters mercury (mm Hg) MULTIPLY BY TO OBTAIN kilometers (km) lx10-5 centimeter (cm) 3280.8 feet (ft) 0.6214 miles (mi) 0.53996 nautical miles (nm) kilometers per hour 58.68 feet per minute (ft / min) 0.9113 feet per second (ft / sec) 0.53996 knots (kt) 16.67 meters per minute (m / min) 0.27778 meters per second (m / sec) 0.6214 miles per hour (mph) knots (kt) 1.689 feet per second (ft / sec) 1.852 kilometer per hour (km / hr) 51.48 meter per second (m / sec) 1 nautical mile per hour (nautical mph) statute mile per hour (statute mph) liters (l) 1000 cubic centimeter (cm3) 0.03531 cubic feet (ft3) 0.22 imperial gallons (imperial gal) 0.264172 U.S. gallons (U.S. gal) 61.02 cubic inches (in3) 0.001 cubic meter (m3) 33.814 fluid ounces (fl. oz.) 1.05669 U. S. quart (qt) liters per second (1 / sec) 2.12 cubic feet per minute (ft3 / min) meters (m) 3.28084 feet 39.37 inches 6.214x10-4 miles (mi) 5.3996x10-4 nautical mile (nm) 0.198838 rod meters per minute (m / min) 0.06 kilometers per hour (km / hr) 116.6307 knots (kt) SECTION 1 PA-28-181, ARCHER III GENERAL ISSUED: JULY 12, 1995 REPORT: VB-1611 1-15 SECTION 1 GENERAL PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 1-16 MULTIPLY BY TO OBTAIN meters per second (m/sec) 196.8504 feet per minute (ft / min) 3.280840 feet per second (ft / sec) 3.6 kilometers per hour (km / hr) 1.94384 knots (kt) 2.237 miles per hour (mph) miles, statute(mi) 5280 feet (ft) 1609.3 meters (m) 1.6093 kilometers (km) 0.8684 nautical miles (nm) miles per hour (mph) 88 feet per minute (ft / min) 1.467 feet per second (ft / sec) 0.8684 knots (kt) 0.447 meters per second (m / sec) 1.6093 kilometer per hour miles per hour squared 2.151 feet per second squared (mi / hr2) (ft / sec2) 0.44704 meter per second squared (m / sec2) millibars 1.0 hectopascals (hPa) 0.02953 inches of mercury (in Hg) millimeters of mercury 1.3332 hectopascals (hPa) at 0° C (mm Hg) 0.03937 inches of mercury (in Hg) nautical miles (nm) 6080 feet (ft) 1.852 kilometers (km) 1852 meters (m) 1.1516 statute miles (mi) fluid ounces (fl. oz) 29.57 cubic centimeters (cm3) 8 fluid drams (fl dr) 0.0078 U.S. gallons (U.S. gal) 1.805 cubic inches (in3) 0.0296 liters (1) 2.9574x10-5 cubic meters (m3) pounds per square foot 0.1414 inches of mercury (in Hg) (psf or lbs / ft2) 47.880 newtons per square meter (n / m2) MULTIPLY BY TO OBTAIN pounds per square inch 68.9475 millibar (mb) (Ibs/ in2) 5.1715 centimeter of mercury (cm Hg) 2.036 inches of mercury (in Hg) quart, U.S. (qt) 57.749 cubic inches (in3) 0.94635 liters (1) 9.46353x10-4 cubic meters (m3) radians 57.3 degrees arc (deg) 0.1592 revolutions (rev) radians per second 57.3 degrees per second (deg /sec) 9.549 revolutions per minute (rpm) revolutions 360 degrees (deg) 6.283 radians revolutions per minute (rpm) 6 deg per second (deg / sec) 0.1047 radians per second (r / sec) rod 16.5 feet (ft) 5.029 meters (m) square centimeters (cm2) 0.001076 square feet (ft2) 0.155 square inches (in2) 0.0001 square meters (m2) square feet (ft2) 929 square centimeters (cm2) 144 square inches (in2) 0.092903 square meters (m2) square inches (in2) 6.4516 square centimeters (cm2) 0.006944 square feet (ft2) 6.4516x10-4 square meters (m2) square kilometers (km2) 1000000 square meters (m2) 0.3861 square miles (mi2) square meters (m2) 10.76391 square feet (ft2) 0.0001 hectors (ha) square miles (mi2) 2589988 square meters (m2) 2.59 square kilometers (km2) SECTION 1 PA-28-181, ARCHER III GENERAL ISSUED: JULY 12, 1995 REPORT: VB-1611 1-17 SECTION 1 GENERAL PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 1-18 THIS PAGE INTENTIONALLY LEFT BLANK TABLE OF CONTENTS SECTION 2 LIMITATIONS Paragraph Page No. No. 2.1 General ......................................................................................... 2-1 2.3 Airspeed Limitations .................................................................... 2-1 2.5 Airspeed Indicator Markings........................................................ 2-2 2.7 Power Plant Limitations ............................................................... 2-3 2.9 Power Plant Instrument Markings................................................ 2-4 2.11 Weight Limits ............................................................................... 2-4 2.13 Center of Gravity Limits .............................................................. 2-5 2.15 Maneuver Limits .......................................................................... 2-6 2.17 Flight Load Factors ...................................................................... 2-6 2.19 Types of Operations...................................................................... 2-6 2.21 Fuel Limitations ........................................................................... 2-6 2.25 Placards ........................................................................................ 2-7 REPORT: VB-1611 2-i REPORT: VB-1611 2-ii THIS PAGE INTENTIONALLY LEFT BLANK SECTION 2 LIMITATIONS 2.1 GENERAL This section provides the ``FAA Approved’’ operating limitations, instrument markings, color coding and basic placards necessary for opera- tion of the airplane and its systems. This airplane must be operated as a normal or utility category airplane in compliance with the operating limitations stated in the form of placards and markings and those given in this section and this complete handbook. Limitations associated with those optional systems and equipment which require handbook supplements can be found in Section 9 (Supplements). 2.3 AIRSPEED LIMITATIONS SPEED KIAS KCAS Never Exceed Speed (VNE) - Do not exceed this speed in any operation. 154 148 Maximum Structural Cruising Speed (VNO) - Do not exceed this speed except in smooth air and then only with caution. 125 121 SECTION 2 PA-28-181, ARCHER III LIMITATIONS ISSUED: JULY 12, 1995 REPORT: VB-1611 2-1 SECTION 2 LIMITATIONS PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 2-2 SPEED KIAS KCAS Design Maneuvering Speed (VA) - Do not make full or abrupt control movements above this speed. At 2550 lbs. G.W. 113 111 At 1634 lbs. G.W. 89 89 CAUTION: Maneuvering speed decreases at lighter weight as the effects of aerodynamic forces become more pronounced. Linear interpolation may be used for intermediate gross weights. Maneuver- ing speed should not be exceeded while operating in rough air. Maximum Flaps Extended Speed (VFE) - Do not exceed this speed with the flaps extended. 102 100 2.5 AIRSPEED INDICATOR MARKINGS MARKING IAS Red Radial Line (Never Exceed) 154 KTS Yellow Arc (Caution Range - Smooth 125 KTS to Air Only) 154 KTS Green Arc (Normal Operating Range) 50 KTS to 125 KTS White Arc (Flap Down) 45 KTS to 102 KTS 2.7 POWER PLANT LIMITATIONS (a) Number of Engines 1 (b) Engine Manufacturer Lycoming (c) Engine Model No. O-360-A4M (d) Engine Operating Limits (1) Takeoff Power limit (BHP) 180 (2) Takeoff Engine Speed (RPM) 2700 (3) Maximum Oil Temperature 245F (4) Oil Pressure Minimum (red line) 25 PSI Maximum (red line) 115 PSI (5) Fuel Pressure Minimum (red line) 0.5 PSI Maximum (red line) 8 PSI (6) Fuel (AVGAS ONLY) (minimum grade) 100 or 100LL Aviation Grade (7) Number of Propellers 1 (8) Propeller Manufacturer Sensenich (9) Propeller Model 76EM8S14-0-62 (10) Propeller Diameter Minimum 76 IN. Maximum 76 IN. (11) Propeller Tolerance (static RPM at maximum permissible throttle setting at sea level) Not above 2340 RPM at ISA conditions Not below 2240 RPM NOTE: Reference aircraft maintenance manual for test procedure to determine approved static RPM under non-standard conditions. SECTION 2 PA-28-181, ARCHER III LIMITATIONS ISSUED: JULY 12, 1995 REPORT: VB-1611 2-3 SECTION 2 LIMITATIONS PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 2-4 2.9 POWER PLANT INSTRUMENT MARKINGS (a) Tachometer Green Arc (Normal Operating Range) 500 to 2700 RPM Red Line (Takeoff Power) 2700 RPM (b) Oil Temperature Green Arc (Normal Operating Range) 100° to 245°F Red Line (Maximum) 245°F (c) Oil Pressure Green Arc (Normal Operating Range) 55 PSI to 95 PSI Yellow Arc (Caution Range) (Idle) 25 PSI to 55 PSI Yellow Arc (Ground Warm-Up) 95 PSI to 115 PSI Red Line (Minimum) 25 PSI Red Line (Maximum) 115 PSI (d) Fuel Pressure Green Arc (Normal Operating Range) 0.5 PSI to 8 PSI Red Line (Minimum) 0.5 PSI Red Line (Maximum) 8 PSI (e) Vacuum Gauge Red Line (Minimum) 4.8 in Hg Green Arc (Normal Operating Range) 4.8 in Hg. to 5.2 in Hg Red Line (Maximum) 5.2 in Hg 2.11 WEIGHT LIMITS Normal Utility (a) Maximum Ramp (lbs.) 2558 2138 (b) Maximum Weight (lbs.) 2550 2130 (c) Maximum Baggage (lbs.) 200 0 NOTE Refer to Section 5 (Performance) for maximum weight as limited by performance. SECTION 2 PA-28-181, ARCHER III LIMITATIONS ISSUED: JULY 12, 1995 REPORT: VB-1611 2-5 2.13 CENTER OF GRAVITY LIMITS (a) Normal Category Weight Forward Limit Rearward Limit Pounds Inches Aft of Datum Inches Aft of Datum 2550 88.6 93.0 2050 (and 82.0 93.0 less) (b) Utility Category Weight Forward Limit Rearward Limit Pounds Inches Aft of Datum Inches Aft of Datum 2130 83.0 93.0 2050 (and 82.0 93.0 less) NOTES Straight line variation between points given. The datum used is 78.4 inches ahead of the wing leading edge at the inboard intersection of the straight and tapered section. It is the responsibility of the airplane owner and the pilot to insure that the airplane is properly loaded. See Section 6 (Weight and Balance) for proper loading instructions. SECTION 2 LIMITATIONS PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 2-6 2.15 MANEUVER LIMITS (a) Normal Category - All acrobatic maneuvers including spins prohibited. (b) Utility Category - Approved maneuvers for bank angles exceeding 60°. Entry Speed Steep Turns 113 KIAS Lazy Eights 113 KIAS Chandelles 113 KIAS 2.17 FLIGHT LOAD FACTORS Normal Utility (a) Positive Load Factor (Maximum) 3.8 G 4.4 G (b) Negative Load Factor (Maximum) No inverted maneuvers approved 2.19 TYPES OF OPERATION The airplane is approved for the following operations when equipped in accordance with FAR 91 or FAR 135. (a) Day V.F.R. (b) Night V.F.R. (c) Day I.F.R. (d) Night I.F.R. (e) Non Icing 2.21 FUEL LIMITATIONS (a) Total Capacity 50 U.S. GAL. (b) Unusable Fuel 2 U.S. GAL. The unusable fuel for this airplane has been determined as 1.0 gallon in each wing in critical flight attitudes. (c) Usable Fuel 48 U.S. GAL. The usable fuel in this airplane has been determined as 24.0 gallons in each wing. 2.25 PLACARDS In full view of the pilot: “THIS AIRPLANE MUST BE OPERATED AS A NOR- MAL OR UTILITY CATEGORY AIRPLANE IN COM- PLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS. ALL MARKINGS AND PLACARDS ON THIS AIR- PLANE APPLY TO ITS OPERATION AS A UTILITY CATEGORY AIRPLANE. FOR NORMAL AND UTILITY CATEGORY OPERATION REFER TO THE PILOT’S OPERATING HANDBOOK. NO ACROBATIC MANEUVERS ARE APPROVED FOR NORMAL CATEGORY OPERATIONS. SPINS ARE PROHIBITED FOR NORMAL AND UTILITY CATEGORY.’’ SECTION 2 PA-28-181, ARCHER III LIMITATIONS ISSUED: JULY 12, 1995 REPORT: VB-1611 2-7 SECTION 2 LIMITATIONS PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 2-8 In full view of the pilot, in the area of the air conditioner control panel when the air conditioner is installed: “WARNING’’ AIR CONDITIONER MUST BE OFF TO I N S U R E NORMAL TAKEOFF CLIMB PER- FORMANCE.’’ Adjacent to upper door latch: “ENGAGE LATCH BEFORE FLIGHT.’’ On inside of the baggage compartment door. “BAGGAGE MAXIMUM 200 LBS.’’ “UTILITY CATEGORY OPERATION - NO BAG- GAGE OR AFT PASSENGERS ALLOWED. NOR- M A L C AT E G O RY O P E R AT I O N - S E E P I L OT ’ S O P E R AT I N G H A N D B O O K W E I G H T A N D BA L - ANCE SECTION FOR BAGGAGE AND AFT PAS- SENGER LIMITATIONS.’’ In full view of the pilot: “VA 113 KIAS AT 2550# (SEE P.O.H.)’’ “DEMO. X-WIND 17 KTS.’’ NOTE Demonstrated crosswind values are NOT limitations. REVISED: JULY 29, 2010 In full view of the pilot: ``UTILITY CATEGORY OPERATION ONLY.’’ (1) NO AFT PASSENGERS ALLOWED. (2) ACROBATIC MANEUVERS ARE LIMITED TO THE FOLLOWING: ENTRY SPEED SPINS PROHIBITED — STEEP TURNS 113 KIAS LAZY EIGHTS 113 KIAS CHANDELLES 113 KIAS In full view of the pilot: ``WARNING’’ TURN OFF STROBE LIGHTS WHEN IN CLOSE PROXIMITY TO GROUND OR DURING FLIGHT THROUGH CLOUD, FOG OR HAZE.’’ Adjacent to the filler caps: SECTION 2 PA-28-181, ARCHER III LIMITATIONS ISSUED: JULY 12, 1995 REPORT: VB-1611 2-9 SECTION 2 LIMITATIONS PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 2-10 INTENTIONALLY LEFT BLANK TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Paragraph Page No. No. 3.1 General ........................................................................................ 3-1 3.3 Airspeeds for Safe Operation ....................................................... 3-2 3.5 Emergency Procedures Checklist ................................................. 3-2 Engine Fire During Start .......................................................... 3-2 Engine Power Loss During Takeoff ......................................... 3-2 Engine Power Loss In Flight .................................................... 3-3 Power Off Landing ................................................................... 3-3 Fire In Flight............................................................................. 3-4 Loss of Oil Pressure ................................................................. 3-4 Loss of Fuel Pressure ............................................................... 3-4 High Oil Temperature............................................................... 3-5 Electrical Failures..................................................................... 3-5 Electrical Overload................................................................... 3-6 Spin Recovery .......................................................................... 3-6 Open Door ................................................................................ 3-7 Carburetor Icing ....................................................................... 3-7 Engine Roughness .................................................................... 3-7 3.7 Amplified Emergency Procedures (General) ............................... 3-9 3.9 Engine Fire During Start .............................................................. 3-9 3.11 Engine Power Loss During Takeoff ............................................. 3-9 3.13 Engine Power Loss In Flight ........................................................ 3-10 3.15 Power Off Landing ....................................................................... 3-11 3.17 Fire In Flight................................................................................. 3-11 3.19 Loss of Oil Pressure ..................................................................... 3-12 3.21 Loss of Fuel Pressure ................................................................... 3-13 3.23 High Oil Temperature................................................................... 3-13 REPORT: VB-1611 3-i REPORT: VB-1611 3-ii TABLE OF CONTENTS (cont) SECTION 3 (cont) Paragraph Page No. No. 3.25 Electrical Failures......................................................................... 3-14 3.27 Electrical Overload....................................................................... 3-14 3.29 Spin Recovery .............................................................................. 3-15 3.31 Open Door .................................................................................... 3-15 3.33 Carburetor Icing ........................................................................... 3-16 3.35 Engine Roughness ........................................................................ 3-16 SECTION 3 EMERGENCY PROCEDURES 3.1 GENERAL The recommended procedures for coping with various types of emergencies and critical situations are provided by this section. All of required (FAA regulations) emergency procedures and those necessary for the operation of the airplane as determined by the operating and design features of the airplane are presented. Emergency procedures associated with those optional systems and equipment which require handbook supplements are provided in Section 9 (Supplements). The first portion of this section consists of an abbreviated emergency check list which supplies an action sequence for critical situations with little emphasis on the operation of systems. The remainder of the section is devoted to amplified emergency pro- cedures containing additional information to provide the pilot with a more complete understanding of the procedures. These procedures are suggested as a course of action for coping with the particular condition described, but are not a substitute for sound judgment and common sense. Pilots should familiarize themselves with the procedures given in this section and be prepared to take appropriate action should an emergency arise. Most basic emergency procedures, such as power off landings, are a normal part of pilot training. Although these emergencies are discussed here, this information is not intended to replace such training, but only to provide a source of reference and review, and to provide information on procedures which are not the same for all aircraft. It is suggested that the pilot review standard emergency procedures periodically to remain proficient in them. SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES ISSUED: JULY 12, 1995 REPORT: VB-1611 3-1 SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 3-2 3.3 AIRSPEEDS FOR SAFE OPERATION Stall Speeds 2550 lbs (0° Flaps)...........................................................................50 KIAS 2550 lbs (Full Flaps).......................................................................45 KIAS Maneuvering Speeds 2550 lbs..........................................................................................113 KIAS 1634 lbs............................................................................................89 KIAS Never Exceed Speed .............................................................................154 KIAS Power Off Glide Speed 2550 lbs (0° Flaps)...........................................................................76 KIAS 3.5 EMERGENCY PROCEDURES CHECK LIST ENGINE FIRE DURING START Starter ...............................................................................................crank engine Mixture ................................................................................................idle cut-off Throttle ..........................................................................................................open Electric fuel pump..........................................................................................OFF Fuel selector...................................................................................................OFF Abandon if fire continues. ENGINE POWER LOSS DURING TAKEOFF If sufficient runway remains for a normal landing, land straight ahead. If insufficient runway remains: Maintain safe airspeed. Make only shallow turn to avoid obstructions. Flaps as situation requires. If sufficient altitude has been gained to attempt a restart: Maintain safe airspeed. Fuel selector....................................................................................switch to tank containing fuel Electric fuel pump.................................................................................check ON Mixture ..............................................................................................check RICH Carburetor heat ................................................................................................ON If power is not regained, proceed with power off landing. ENGINE POWER LOSS IN FLIGHT If at low altitude: Airspeed .............................................................................MAINTAIN 76 KIAS Minimum If altitude permits: Fuel selector....................................................................................switch to tank containing fuel Electric fuel pump ...........................................................................................ON Mixture ........................................................................................................RICH Carburetor heat ................................................................................................ON Engine gauges .......................................................................check for indication of cause of power loss If no fuel pressure is indicated, check tank selector position to be sure it is on a tank containing fuel. When power is restored: Carburetor heat ..............................................................................................OFF Electric fuel pump..........................................................................................OFF If power is not restored prepare for power off landing. POWER OFF LANDING Trim for 76 KIAS. Locate suitable field. Establish spiral pattern. 1000 ft. above field at downwind position for normal landing approach. When field can easily be reached, slow to 66 KIAS for shortest landing. Touchdowns should normally be made at lowest possible airspeed with full flaps. When committed to landing: Flaps .....................................................................................................As desired Throttle.........................................................................................................Close Mixture ................................................................................................idle cut-off Magnetos........................................................................................................OFF Battery Master switch ....................................................................................OFF ALTR Switch .................................................................................................OFF Fuel selector...................................................................................................OFF Seat belt and harness......................................................................................tight SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES ISSUED: JULY 12, 1995 REPORT: VB-1611 3-3 SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 3-4 REVISED: APRIL 15, 2002 FIRE IN FLIGHT Source of fire ...............................................................................................check Electrical fire (smoke in cabin): Batt. Master switch ........................................................................................OFF ALTR switch..................................................................................................OFF Vents ..............................................................................................................open Cabin heat ......................................................................................................OFF Land as soon as possible. Engine fire: Fuel selector...................................................................................................OFF Throttle ..................................................................................................CLOSED Mixture ................................................................................................idle cut-off Electric fuel pump ...............................................................................check OFF Heater and defroster.......................................................................................OFF Proceed with power off landing procedure. NOTE: The possibility of an engine fire in flight is extremely remote. The procedure given is general and Pilot judgment should be the determining factor for action in such an emergency. LOSS OF OIL PRESSURE Land as soon as possible and investigate cause. Prepare for power off landing. LOSS OF FUEL PRESSURE Electric fuel pump ...........................................................................................ON Fuel selector .............................................................................check on full tank HIGH OIL TEMPERATURE Land at nearest airport and investigate the problem. Prepare for power off landing. ELECTRICAL FAILURES NOTE: Anytime the bus voltage is below 25 Vdc, the Low Bus Voltage Annunciator will be illuminated. ALT annunciator light illuminated: Ammeter........................................................................Check to verify inop. alt. If ammeter shows zero: ALT switch.....................................................................................................OFF Reduce electrical loads to minimum: ALT circuit breaker......................................................................Check and reset as required ALT switch ......................................................................................................ON If power not restored: ALT switch.....................................................................................................OFF If alternator output cannot be restored, reduce electrical loads and land as soon as practical. Anticipate complete electrical failure. Duration of battery power will be dependent on electrical load and battery condition prior to failure. NOTE: Low Bus Voltage Annunciator will be illuminated. SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES ISSUED: JULY 12, 1995 REPORT: VB-1611 3-5 SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 3-6 ELECTRICAL OVERLOAD (Alternator over 20 amps above known electrical load) ALT switch ......................................................................................................ON BAT switch.....................................................................................................OFF If alternator loads are reduced: Electrical load ......................................................................Reduce to Minimum Land as soon as practical. NOTE Due to increased system voltage and radio frequency noise, operation with ALT switch ON and BAT switch OFF should be made only when required by an electrical system failure. If alternator loads are not reduced: ALT switch.....................................................................................................OFF BAT switch .........................................................................................As required Land as soon as possible. Anticipate complete electrical failure. SPIN RECOVERY Rudder...........................................................................................full opposite to direction of rotation Control wheel...........................................................................full forward while neutralizing ailerons Throttle............................................................................................................idle Rudder.....................................................................neutral (when rotation stops) Control wheel ..................................................................as required to smoothly regain level flight attitude OPEN DOOR If both upper and side latches are open, the door will trail slightly open and airspeeds will be reduced slightly. To close the door in flight: Slow airplane to 87 KIAS. Cabin vents....................................................................................................close Storm window ...............................................................................................open If upper latch is open .....................................................................................latch If side latch is open .............................................................pull on armrest while moving latch handle to latched position If both latches are open .................................................................latch side latch then top latch CARBURETOR ICING Carburetor heat ................................................................................................ON Mixture .................................................................................adjust for maximum smoothness ENGINE ROUGHNESS Carburetor heat ................................................................................................ON If roughness continues after one min: Carburetor heat ..............................................................................................OFF Mixture .................................................................................adjust for maximum smoothness Electric fuel pump ...........................................................................................ON Fuel selector ......................................................................................switch tanks Engine gauges ..............................................................................................check Magneto switches ..............................................................Check Left then Right If operation is satisfactory on either one, continue on that magneto at reduced power and full RICH mixture to first airport. Prepare for power off landing. SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES ISSUED: JULY 12, 1995 REPORT: VB-1611 3-7 SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 3-8 THIS PAGE INTENTIONALLY LEFT BLANK 3.7 AMPLIFIED EMERGENCY PROCEDURES (GENERAL) The following paragraphs are presented to supply additional informa-tion for the purpose of providing the pilot with a more complete under-standing of the recommended course of action and probable cause of an emergency situation. 3.9 ENGINE FIRE DURING START Engine fires during start are usually the result of overpriming. The first attempt to extinguish the fire is to try to start the engine and draw the excess fuel back into the induction system. If a fire is present before the engine has started, move the mixture control to idle cut-off, open the throttle and crank the engine. This is an attempt to draw the fire back into the engine. If the engine has started, continue operating to try to pull the fire into the engine. In either case (above), if fire continues more than a few seconds, the fire should be extinguished by the best available external means. The fuel selector valves should be OFF and the mixture at idle cut-off if an external fire extinguishing method is to be used. 3.11 ENGINE POWER LOSS DURING TAKEOFF The proper action to be taken if loss of power occurs during takeoff will depend on the circumstances of the particular situation. If sufficient runway remains to complete a normal landing, land straight ahead. If insufficient runway remains, maintain a safe airspeed and make only a shallow turn if necessary to avoid obstructions. Use of flaps depends on the circumstances. Normally, flaps should be fully extended for touchdown. SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES ISSUED: JULY 12, 1995 REPORT: VB-1611 3-9 SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 3-10 If sufficient altitude has been gained to attempt a restart, maintain a safe airspeed and switch the fuel selector to another tank containing fuel. Check the electric fuel pump to insure that it is ON and that the mixture is RICH. The carburetor heat should be ON . If engine failure was caused by fuel exhaustion, power will not be re- gained after switching fuel tanks until the empty fuel lines are filled. This may require up to ten seconds. If power is not regained, proceed with the Power Off Landing procedure (refer to the emergency check list and Paragraph 3.15). 3.13 ENGINE POWER LOSS IN FLIGHT Complete engine power loss is usually caused by fuel flow interruption and power will be restored shortly after fuel flow is restored. If power loss occurs at a low altitude, the first step is to prepare for an emergency landing (refer to Paragraph 3.15). An airspeed of at least 76 KIAS should be main- tained. If altitude permits, switch the fuel selector to another tank containing fuel and turn the electric fuel pump ON. Move the mixture control to RICH and the carburetor heat to ON. Check the engine gauges for an indication of the cause of the power loss. If no fuel pressure is indicated, check the tank selector position to be sure it is on a tank containing fuel. When power is restored move the carburetor heat to the OFF position and turn OFF the electric fuel pump. If the preceding steps do not restore power, prepare for an emergency landing. If time permits, turn the Left and Right magneto switches OFF then ON one at a time. Move the throttle and mixture control levers to different settings. This may restore power if the problem is too rich or too lean a mixture or if there is a partial fuel system restriction. Try other fuel tanks. Water in the fuel could take some time to be used up, and allowing the engine to windmill may restore power. If power loss is due to water, fuel pressure indications will be normal. If engine failure was caused by fuel exhaustion, power will not be re- stored after switching fuel tanks until the empty fuel lines are filled. This may require up to ten seconds. If power is not regained, proceed with the Power Off Landing procedure (refer to the emergency check list and Paragraph 3.15). 3.15 POWER OFF LANDING If loss of power occurs at altitude, trim the aircraft for best gliding angle 76 KIAS (Air Cond. off) and look for a suitable field. If measures taken to restore power are not effective, and if time permits, check your charts for airports in the immediate vicinity; it may be possible to land at one if you have sufficient altitude. If possible, notify the FAA by radio of your diffi- culty and intentions. If another pilot or passenger is aboard, let him help. When you have located a suitable field, establish a spiral pattern around this field. Try to be at 1000 feet above the field at the downwind position, to make a normal landing approach. When the field can easily be reached, slow to 66 KIAS with flaps down for the shortest landing. Excess altitude may be lost by widening your pattern, using flaps or slipping, or a combination of these. Touchdown should normally be made at the lowest possible airspeed. When committed to a landing,lower the flaps as desired, close the throttle, move the mixture to idle cut-off, and shut OFF the magnetos. Turn the battery master and alternator switches OFF. Move the fuel selector valve to OFF. The seat belts and shoulder harness should be tightened. 3.17 FIRE IN FLIGHT The presence of fire is noted through smoke, smell and heat in the cabin. It is essential that the source of the fire be promptly identified through instrument readings, character of the smoke, or other indications since the action to be taken differs somewhat in each case. Check for the source of the fire first. SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES ISSUED: JULY 12, 1995 REPORT: VB-1611 3-11 SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 3-12 If an electrical fire is indicated (smoke in the cabin), the battery master switch should be turned OFF. The cabin vents should be opened and the cabin heat turned OFF. A landing should be made as soon as possible. If an engine fire is present, switch the fuel selector to OFF and close the throttle. The mixture should be at idle cut-off. Turn the electric fuel pump OFF. In all cases, the heater and defroster should be OFF. If radio com-munication is not required, select battery master and alternator switchs OFF. Proceed with power off landing procedure. NOTE The possibility of an engine fire in flight is extremely remote. The procedure given is general and pilot judgment should be the deter- mining factor for action in such an emergency. 3.19 LOSS OF OIL PRESSURE Loss of oil pressure may be either partial or complete. A partial loss of oil pressure usually indicates a malfunction in the oil pressure regulating system, and a landing should be made as soon as possible to investigate the cause and prevent engine damage. A complete loss of oil pressure indication may signify oil exhaustion or may be the result of a faulty gauge. In either case, proceed toward the nearest airport, and be prepared for a forced landing. If the problem is not a pressure gauge malfunction, the engine may stop suddenly. Maintain altitude until such time as a dead stick landing can be accomplished. Don’t change power settings unnecessarily, as this may hasten complete power loss. Depending on the circumstances, it may be advisable to make an off airport landing while power is still available, particularly if other indications of actual oil pressure loss, such as sudden increases in temperatures, or oil smoke, are apparent, and an airport is not close. If engine stoppage occurs, proceed with Power Off Landing. 3.21 LOSS OF FUEL PRESSURE The most probable cause of loss of fuel pressure is either fuel depletion in the fuel tank selected or failure of the engine driven fuel pump. If loss of fuel pressure occurs, turn ON the electric fuel pump and check that the fuel selector is on a tank containing usable fuel. If loss of fuel pressure is due to failure of the engine driven fuel pump the electric fuel pump will supply sufficient fuel pressure. After fuel pressure and power are regained, turn the electric fuel pump OFF. If fuel pressure starts to drop, turn the electric fuel pump ON and land at the nearest suitable airport as soon as possible and have the cause investigated. CAUTION If normal engine operation and fuel pressure is not immediately re-established, the electric fuel pump should be turned off. The lack of fuel pressure indication could indicate a leak in the fuel system, or fuel exhaustion. 3.23 HIGH OIL TEMPERATURE An abnormally high oil temperature indication may be caused by a low oil level, an obstruction in the oil cooler, damaged or improper baffle seals, a defective gauge, or other causes. Land as soon as practical at an appro- priate airport and have the cause investigated. A steady, rapid rise in oil temperature is a sign of trouble. Land at the nearest airport and let a mechanic investigate the problem. Watch the oil pressure gauge for an accompanying loss of pressure. SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES ISSUED: JULY 12, 1995 REPORT: VB-1611 3-13 SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 3-14 3.25 ELECTRICAL FAILURES NOTE: Anytime the bus voltage is below 25 Vdc, the Low Bus Voltage Annunciator will be illuminated. Loss of alternator output is detected through zero reading on the ammeter. Before executing the following procedure, insure that the reading is zero and not merely low by actuating an electrically powered device, such as the landing light. If no increase in the ammeter reading is noted, alternator failure can be assumed. The electrical load should be reduced as much as possible. Check the alternator circuit breakers for a popped circuit. The next step is to attempt to reset the overvoltage relay. This is accomplished by moving the ALT switch to OFF for one second and then to ON. If the trouble was caused by a momentary overvoltage condition (30.5 volts and up) this procedure should return the ammeter to a normal reading. NOTE: Low Bus Voltage Annunciator will be illuminated. If the ammeter continues to indicate ``0’’ output, or if the alternator will not remain reset, turn off the ALT switch, maintain minimum electrical load and land as soon as practical. Anticipate complete electrical failure. Duration of battery power will be dependent on electrical load and battery condition prior to failure. 3.27 ELECTRICAL OVERLOAD (Alternator over 20 amps above known electrical load) If abnormally high alternator output is observed (more than 20 amps above known electrical load for the operating conditions) it may be caused by a low battery, a battery fault or other abnormal electrical load. If the cause is a low battery, the indication should begin to decrease toward normal within 5 minutes. If the overload condition persists attempt to reduce the load by turning off non-essential equipment. Turn the BAT switch OFF and the ammeter should decrease. Turn the BAT switch ON and continue to monitor the ammeter. If the alternator output does not decrease within 5 minutes, turn the BAT switch OFF and land as soon as practical. All electrical loads are being supplied by the alternator. NOTE Due to higher voltage and radio frequency noise, operation with the ALT switch ON and the BAT switch OFF should be made only when required by an electrical failure. 3.29 SPIN RECOVERY Intentional spins are prohibited in this airplane. If a spin is inadvertently entered, immediately apply full rudder opposite to the direction of rotation. Move the control wheel full forward while neutralizing the ailerons. Move the throttle to IDLE. When the rotation stops, neutralize the rudder and ease back on the control wheel as required to smoothly regain a level flight attitude. 3.31 OPEN DOOR The cabin door is double latched, so the chances of its springing open in flight at both the top and side are remote. However, should you forget the upper latch, or not fully engage the side latch, the door may spring partially open. This will usually happen at takeoff or soon afterward. A partially open door will not affect normal flight characteristics, and a normal landing can be made with the door open. If both upper and side latches are open, the door will trail slightly open, and airspeed will be reduced slightly. To close the door in flight, slow the airplane to 87 KIAS, close the cabin vents and open the storm window. If the top latch is open, latch it. If the side latch is open, pull on the armrest while moving the latch handle to the latched position. If both latches are open, close the side latch then the top latch. SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES ISSUED: JULY 12, 1995 REPORT: VB-1611 3-15 SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 3-16 3.33 CARBURETOR ICING Under certain moist atmospheric conditions at temperatures of -5°C to 20°C, it is possible for ice to form in the induction system, even in summer weather. This is due to the high air velocity through the carburetor venturi and the absorption of heat from this air by vaporization of the fuel. To avoid this, carburetor preheat is provided to replace the heat lost by vaporization. Carburetor heat should be full on when carburetor ice is encountered. Adjust mixture for maximum smoothness. 3.35 ENGINE ROUGHNESS Engine roughness is usually due to carburetor icing which is indicated by a drop in RPM, and may be accompanied by a slight loss of airspeed or altitude. If too much ice is allowed to accumulate, restoration of full power may not be possible; therefore, prompt action is required. Turn carburetor heat on (See Note). RPM will decrease slightly and roughness will increase. Wait for a decrease in engine roughness or an increase in RPM, indicating ice removal. If no change in approximately one minute, return the carburetor heat to OFF. If the engine is still rough, adjust the mixture for maximum smoothness. The engine will run rough if too rich or too lean. The electric fuel pump should be switched to ON and the fuel selector switched to the other tank to see if fuel contamination is the problem. Check the engine gauges for abnormal readings. If any gauge readings are abnormal, proceed accord- ingly. Select the Left magneto switch OFF then ON and repeat with the Right magneto switch. If operation is satisfactory on either magneto, proceed on that magneto at reduced power, with mixture full RICH, to a landing at the first available airport. If roughness persists, prepare for a precautionary landing at pilot’s discretion. NOTE Partial carburetor heat may be worse than no heat at all, since it may melt part of the ice, which will refreeze in the intake system. When using carburetor heat, therefore, always use full heat, and when ice is removed return the con- trol to the full cold position. TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES Paragraph Page No. No. 4.1 General ......................................................................................... 4-1 4.3 Airspeeds for Safe Operations...................................................... 4-1 4.5 Normal Procedures Checklist....................................................... 4-3 Preflight Check......................................................................... 4-3 Engine Start - General .............................................................. 4-6 Before Starting Engine ............................................................. 4-7 Normal Start - Cold Engine...................................................... 4-7 Normal Start - Hot Engine ....................................................... 4-7 Engine Start - When Flooded ................................................... 4-8 Starting With External Power Source....................................... 4-8 Warm-Up .................................................................................. 4-9 Taxiing...................................................................................... 4-9 Ground Check .......................................................................... 4-9 Before Takeoff.......................................................................... 4-10 Takeoff...................................................................................... 4-10 Short Field, Obstacle Clearance ............................................... 4-11 Climb........................................................................................ 4-11 Cruising .................................................................................... 4-11 Descent ..................................................................................... 4-11 Approach and Landing ............................................................. 4-12 Stopping Engine ....................................................................... 4-12 Mooring.................................................................................... 4-12 4.7 Preflight Check............................................................................. 4-14 4.9 Engine Start - General .................................................................. 4-17 4.11 Before Starting Engine ................................................................. 4-17 4.13 Starting Engine............................................................................. 4-18 4.15 Warm-Up ...................................................................................... 4-20 4.17 Taxiing.......................................................................................... 4-20 4.19 Ground Check .............................................................................. 4-20 REPORT: VB-1611 4-i REPORT: VB-1611 4-ii TABLE OF CONTENTS (cont) SECTION 4 (cont) Paragraph Page No. No. 4.21 Before Takeoff.............................................................................. 4-21 4.23 Takeoff.......................................................................................... 4-22 4.25 Climb............................................................................................ 4-22 4.27 Cruising ........................................................................................ 4-23 4.29 Descent ......................................................................................... 4-24 4.31 Approach and Landing ................................................................. 4-24 4.33 Stopping Engine ........................................................................... 4-25 4.35 Mooring........................................................................................ 4-26 4.37 Stalls ............................................................................................. 4-26 4.39 Turbulent Air Operation ............................................................... 4-27 4.41 Weight and Balance...................................................................... 4-27 4.43 Noise Level................................................................................... 4-27 SECTION 4 NORMAL PROCEDURES 4.1 GENERAL This section describes the recommended procedures for the conduct of normal operations for the Archer III. All of the required (FAA regulations) procedures and those necessary for operation of the airplane as determined by the operating and design features of the airplane are presented. Normal procedures associated with those optional systems and equip- ment which require handbook supplements are provided by Section 9 (Supplements). These procedures are provided to present a source of reference and review and to supply information on procedures which are not the same for all aircraft. Pilots should familiarize themselves with the procedures given in this section in order to become proficient in the normal operations of the airplane. The first portion of this section consists of a short form check list which supplies an action sequence for normal operations with little emphasis on the operation of the systems. The remainder of the section is devoted to amplified normal procedures which provide detailed information and explanations of the procedures and how to perform them. This portion of the section is not intended for use as an in-flight reference due to the lengthly explanations. The short form check list should be used for this purpose. 4.3 AIRSPEEDS FOR SAFE OPERATIONS The following airspeeds are those which are significant to the safe operation of the airplane. These figures are for standard airplanes flown at gross weight under standard conditions at sea level. SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES ISSUED: JULY 12, 1995 REPORT: VB-1611 4-1 SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 4-2 Performance for a specific airplane may vary from published figures depending upon the equipment installed, the condition of the engine, airplane and equipment, atmospheric conditions and piloting technique. (a) Best Rate of Climb Speed 76 KIAS (b) Best Angle of Climb Speed 64 KIAS (c) Turbulent Air Operating Speed (See Subsection 2.3) 113 KIAS (d) Maximum Flap Speed 102 KIAS (e) Landing Final Approach Speed (Flaps 40) 66 KIAS (f) Maximum Demonstrated Crosswind Velocity 17 KTS 4.5 NORMAL PROCEDURES CHECK LIST PREFLIGHT CHECK COCKPIT Control wheel .............................................................................release restraints Parking brake ....................................................................................................set Avionics .........................................................................................................OFF All switches ...................................................................................................OFF Mixture ................................................................................................idle cut-off Magneto switches ..........................................................................................OFF Battery master switch ......................................................................................ON Fuel gauges ....................................................................................check quantity Annunciator panel........................................................................................check Battery master switch ....................................................................................OFF Flaps ...........................................................................................................extend Primary flight controls................................................................proper operation Trim............................................................................................................neutral Pitot and static systems .....................................................................................drain Windows.................................................................................................check clean SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES ISSUED: JULY 12, 1995 REPORT: VB-1611 4-3 WALK-AROUND Figure 4-1 SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 4-4 Required papers and POH ............................................................check on board Tow bar and baggage .........................................................stow properly - secure Baggage door ..............................................................................close and secure RIGHT WING Surface condition .............................................................clear of ice, frost, snow Flap and hinges ............................................................................................check Aileron and hinges .......................................................................................check Static wicks ....................................................................................check - secure Wing tip and lights.......................................................................................check Fuel tank...........................................................................................check supply visually - secure cap Fuel tank vent ................................................................................................clear CAUTION: When draining any amount of fuel, care should be taken to ensure that no fire hazard exists before starting engine. Fuel tank sumps .....................................................................drain and check for water, sediment and proper fuel Tie down and chock...................................................................................remove Main gear strut............................................................................................proper inflation (4.5 ± .25 in.) Tire ..............................................................................................................check Brake block and disc....................................................................................check Fresh air inlet.................................................................................................clear NOSE SECTION General condition.........................................................................................check Cowling.......................................................................................................secure Windshield ....................................................................................................clean Propeller and spinner ...................................................................................check Air inlets ........................................................................................................clear Engine baffle seals .......................................................................................check Chock ........................................................................................................remove Nose gear strut ............................................................................................proper inflation (3.25 ± .25 in.) Nose wheel tire ............................................................................................check Oil ................................................................................................check quantity Dipstick.........................................................................................properly seated Oil filler cap ................................................................................................secure CAUTION: When draining any amount of fuel, care should be taken to ensure that no fire hazard exists before starting engine. Fuel strainer ..................................................................................................drain LEFT WING Surface condition .............................................................clear of ice, frost, snow Fresh air inlet.................................................................................................clear CAUTION: When draining any amount of fuel, care should be taken to ensure that no fire hazard exists before starting engine. Fuel tank sump .......................................................................drain and check for water, sediment and proper fuel Fuel tank vent ................................................................................................clear Main gear strut............................................................................................proper inflation (4.5 ± .25 in.) Tire ..............................................................................................................check Brake block and disc....................................................................................check Tie down and chock...................................................................................remove Fuel tank...........................................................................................check supply visually - secure cap Pitot/static head...........................................................remove cover - holes clear Wing tip and lights.......................................................................................check Aileron and hinges .......................................................................................check Flap and hinges ............................................................................................check Static wicks.......................................................................................check secure FUSELAGE Antennas ......................................................................................................check Empennage ......................................................................clear of ice, frost, snow Stabilator and trim tab .................................................................................check Tie down....................................................................................................remove SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES ISSUED: JULY 12, 1995 REPORT: VB-1611 4-5 SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 4-6 MISCELLANEOUS Battery master switch ......................................................................................ON Flaps............................................................................................................retract Interior lighting ..............................................................................ON and check Pitot heat switch ..............................................................................................ON Pitot heat OFF/INOP Annunciator ...................................................extinguished CAUTION: Care should be taken when an operational check of the heated pitot head is being performed. The unit becomes very hot. Ground operation should be limited to three minutes to avoid damaging the heater elements. NOTE: Secure and adjust all unused seat belts and shoulder harness to prevent control interference or passenger injury during flight in turbulent air. Exterior lighting switches...............................................................ON and check Pitot .................................................................................................check - warm Stall warning horn........................................................................................check All lighting switches ......................................................................................OFF Pitot heat switch.............................................................................................OFF Pitot heat OFF/INOP Annunciator .....................................................illuminated Battery master switch ....................................................................................OFF Passengers ....................................................................................................board Door .........................................................................................Closed and secure Seats ...................................................................adjusted and /locked in position Seat belts and harness .......................................................................fasten/adjust check inertia reel ENGINE START - GENERAL CAUTION: Do not attempt flight if there is no indication of alternator output. CAUTION: If a positive oil pressure is not indicated within 30 seconds following an engine start, stop the engine and determine the trouble. In cold weather it will take a few seconds longer to get a positive oil pressure indication. SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES BEFORE STARTING ENGINE Brakes..................................................................................................................set Circuit breakers ..........................................................................................check in Alternate static source ......................................................................................OFF Carburetor heat ........................................................................................full cold Avionics............................................................................................................OFF Fuel selector .........................................................................................desired tank NORMAL START - COLD ENGINE Throttle .................................................................................................1/4 in. open Battery master switch.........................................................................................ON Alternator switch................................................................................................ON Left magneto switch ........................................................................................ON Electric fuel pump..............................................................................................ON Mixture ....................................................................................................full RICH Propeller...........................................................................................................clear Starter ...........................................................................................................engage Throttle...........................................................................................................adjust Right magneto switch ........................................................................................ON Oil pressure.....................................................................................................check NOTE: If engine does not start within 10 seconds, prime and repeat starting procedure. Starter manufacturer recommends starter cranking periods be limited to 10 seconds with a 2 minute rest period between cranking periods. Maximum of 5 start periods allowed. If start is not achieved on fifth attempt allow starter to cool for 30 minutes before attempting additional starts. NORMAL START - HOT ENGINE Throttle .................................................................................................1/2 in. open Battery master switch.........................................................................................ON Alternator switch................................................................................................ON Left magneto switch ........................................................................................ON Electric fuel pump..............................................................................................ON Mixture ....................................................................................................full RICH Propeller...........................................................................................................clear Starter ...........................................................................................................engage Throttle...........................................................................................................adjust Right magneto switch ........................................................................................ON Oil pressure.....................................................................................................check ISSUED: JULY 12, 1995 REPORT: VB-1611 REVISED: June 15, 2009 4-7 SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III REPORT: VB-1611 ISSUED: JULY 12, 1995 4-8 REVISED: APRIL 15, 2002 ENGINE START WHEN FLOODED Throttle ......................................................................................................open full Battery master switch.........................................................................................ON Alternator switch................................................................................................ON Left magneto switch ........................................................................................ON Electric fuel pump ............................................................................................OFF Mixture...................................................................................................idle cut-off Propeller...........................................................................................................clear Starter ...........................................................................................................engage Mixture .......................................................................................................advance Throttle ...........................................................................................................retard Right magneto switch ........................................................................................ON Oil Pressure ....................................................................................................check STARTING WITH EXTERNAL POWER SOURCE CAUTION: It is possible to use the ship's battery in parallel by turning only the battery master switch ON. This will give longer cranking capabilities, but will not increase the amperage. Care should be exercised if the ship's battery has been depleted. The external power supply can be be reduced to the level of the ship's battery. This can be tested by turning only the battery master switch on momentarily while the starter is engaged. If cranking speed increases, the ship's battery is at a higher level than the external power supply. If the battery is at a lower level than the external power supply, continue starting with the battery master switch off. Battery master switch ....................................................................................OFF Alternator switch ...........................................................................................OFF Left magneto switch ........................................................................................ON All electrical equipment.................................................................................OFF Terminals ..................................................................................................connect External power plug...................................................................insert in fuselage SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES Proceed with normal start Throttle ................................................................................lowest possible RPM Right magneto switch......................................................................................ON External power plug ......................................................disconnect from fuselage Battery master switch ......................................................................................ON Alternator switch .................................................................ON - check ammeter Oil pressure ..................................................................................................check WARM-UP Throttle .....................................................................................800 to 1200 RPM TAXIING Taxi area ........................................................................................................clear Parking brake ...........................................................................................released Throttle .............................................................................................apply slowly Brakes ..........................................................................................................check Steering ........................................................................................................check GROUND CHECK Parking brake ....................................................................................................set Throttle ................................................................................................2000 RPM Magnetos ..............................................................................max. drop 175 RPM max. diff. 50 RPM Vacuum ......................................................................................4.8 to 5.2 in. Hg. Oil temperature ............................................................................................check Oil pressure ..................................................................................................check Air conditioner (if installed) ........................................................................check Ammeter ......................................................................................................check Annunciator panel............................................................................

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