Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual

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

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Overview

This Pilot's Operating Handbook (POH) is specifically designed for the Piper PA-28-181 Archer III. It serves as a comprehensive operating guide for pilots, providing essential information required by Federal Aviation Regulations (FAR) and Civil Aviation Regulations (CAR). The handbook includes limitations, emergency procedures, normal procedures, performance data, weight and balance information, and descriptions of the airplane and its systems. It is crucial for pilots to familiarize themselves with the contents to ensure safe and efficient operation of the aircraft. The handbook must be kept current and is required to be on board the aircraft at all times.

Maximum Takeoff Weight: 2550 lbs
Never Exceed Speed (VNE): 154 KIAS
Maximum Structural Cruising Speed (VNO): 125 KIAS
Design Maneuvering Speed (VA) at 2550 lbs: 113 KIAS
Maximum Landing Weight: 2550 lbs
Fuel Capacity: 50 U.S. gallons (total)
Usable Fuel: 48 U.S. gallons

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

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Document details

Type: Pilot's Operating Handbook
Year: 1994
Pages: 212
File size: 5.1 MB
Publisher: www.foxflying.com

Specifications & performance

Extracted from this document.

Specifications

Engine (hp): 180
Propeller: Sensenich
Engine model: O-360-A4M
Fuel capacity (gal): 50
Max takeoff weight (lb): 2,550

Weight & balance

Max ramp weight (lb): 2,558
Baggage allowance (lb): 200
Max landing weight (lb): 2,550
Max takeoff weight (lb): 2,550

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

This section introduces the Pilot's Operating Handbook and outlines its purpose as an operating guide for pilots. It emphasizes the importance of understanding the limitations, performance, and operational handling characteristics of the aircraft before flight.

Limitations

This section details the FAA-approved operating limitations for the Archer III, including airspeed limitations, weight limits, and center of gravity limits. It is essential for pilots to adhere to these limitations to ensure safe operation.

Emergency Procedures

This section provides critical emergency procedures that pilots must follow in various emergency scenarios. It is designed for quick reference during flight to enhance safety.

Normal Procedures

This section outlines standard operating procedures for the Archer III, including preflight checks, engine start, takeoff, and landing procedures.

Performance

This section includes performance data such as takeoff and landing distances, climb rates, and fuel consumption, which are vital for flight planning.

Weight and Balance

This section provides information on the maximum weights for ramp, takeoff, and landing, as well as guidance on calculating weight and balance for safe flight operations.

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, providing pilots with a thorough understanding of the aircraft's operation.

Airplane Handling, Servicing and Maintenance

This section covers the handling, servicing, and maintenance requirements for the Archer III, ensuring pilots are aware of the necessary upkeep for safe operation.

Supplements

This section includes any additional information or updates that supplement the main handbook content.

Operating Tips

This section offers practical tips for operating the Archer III effectively and safely.

Safety notes

Ensure the handbook is current and on board the aircraft at all times.
Adhere to all operating limitations to ensure safety during flight.

Full document text

ARCHER III pA-28-181 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-1563 fAA AppRovEd by: ________________________________ WIllIAm R. moREu d.o.A. no. so-1 dAtE of AppRovAl: pIpER AIRCRAft CoRpoRAtIon August 19, 1994 vERo bEACH, floRIdA PA-28-181, ARCHER III REPORT: VB-1563 ISSUED: AUgUST 19, 1994 ii REVISED: JULY 21, 2015 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: August 19, 1994 © 1994-1995, 1998, 2002, 2009, 2015 Piper Aircraft Corporation All Rights Reserved 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. REVISIONS The information compiled in the Pilot's Operating Handbook, with the exception of the equipment list, will be kept current by revisions distrihuted to the airplane owners. The equipment list was current at the time the air- plane was licensed by the manufacturer IDld thereafter must be maintained by the owner. Revision material will consist of information necessary to update the text of the present handbook andior to add information to cover added airplane equipment. 1. 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 wi th the same page number. 2. Insert all additional pages in proper numerical order within each section. 3. Page numbers followed by a small letter shall be inserted ill direct sequence with the same common numbered page. II. Identification of Revised Material Revised text and illustrations shall be indicated by a black vertical line along the outside margin of the page, opposite revised, added or deleted material. A line along t1le outside margin of the page opposite the page number will indicate that an entire page was added. REPORT: VR-1S63 iii Black lines will indicate only current revisions with changes and additions to or deletions of existing text and illustrations. Changes in capitalization, spelling, punctuation or the physical location of material on ( a page will not be idcntified. ORIGINAL PAGES ISSUED The original pagcs issued [or this handbook prior to revision are given b¢low: Title, ii through vii, 1-1 through 1-18,2-1 through 2-10, 3-1 through 3-16,4-1 Ulrough 4-28,5-1 Ulrough 5-30,6-1 Ulrough 6-12, 7-1 tlu:ough 7-26, 8-1 through 8-20, 9-1 Ulfough 9"14,10-1 through 10-2. REPORT: VB-1563 iv ( ( PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Current Revisions to the PA- 28-181 ARCHER III Pilot's Operating Handhook, REPORT: VB-1563 issued August 19, 1994. Revision FAA Approval Numher and Revised Description of Revisions Signature and Code Pages Date Rev. I (PR950224) 2-2 Revised Para. 2.3 4-22 Revised Para. 4.25 5-4 Revised Para. 5.5 (b) 5-5 Revised Para. 5.5 (c). 5-6 Revised Para. 5.5 (d).& (e) 5-7 Revised Para. 5.5 (e), (f).& (g) 5-9 Revised Para. 5.7 List of Fig. 5-12 Revised Fig. 5-3. 5-13 Revised Fig. 5-5. 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 Remove & Delete Pages thru 5-30 5-19 Added page, Fig. 5-17. 5-20 Added page, Fig. 5-19 .. 5-21 Added page, Fig. 5-20 .. 5-22 Added page, Fig. 5-20a .. 5-23 Added page, Fig. 5-20b .. 5-24 Added Intentional blank page 5-25 Added page, Fig. 5-21.. 5-26 Added page, Fig. 5-27 .. 5-27 Added page, Fig. 5-27a .. 5-28 Added page, Fig. 5-29 .. 5-29 Added page, Fig. 5-29a .. 5-30 Added page, Fig. 5-31 5-31 Added page, Fig. 5-33 REPORT: VB-1563 v PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Revision Number and Revised Code Pages Rev. I (PR950224) (Cont'd) 5-32 5-33 5-34 8-7 Rev. 2 (PR980326) vi 1-12 2-8 4-27 5-4 5-14 5-15 5-16 5-17 5-18 5-19 5-20 5-26 5-27 5-28 5-29 5-30 5-32 5-33 7-i 7-27 7-28 REPORT: VB-lS63 vi FAA Approval Description of Revisions . Signature and Date Added page, Fig. 5-35 ~f.C Added page, Fig. 5-37 Added Intentional blank page PETER E. PECK Added Para. 8.9 (c) & (d) FAAfDOA Coordinator FEB. 24, 1995 Date Added Rev. 2 to L of R. Revised Para. 1.21. Revised Para. 2.25. Revised Para. 4.43. Revised Para. 5.5. Revised Fig. 5-7. Revised Fig. 5-9. Revised Fig. 5-11. Revised Fig. 5-13. Revised Fig. 5-15. Revised Fig. 5-17. Revised Fig. 5-19. Revised Fig. 5-27. Revised Fig. 5-27a. Revised Fig. 5-29. Revised Fig. 5-29a. (v:4) E.GRevised Fig. 5-31. Revised Fig. 5-35. PEtER E. PECK Revised Fig. 5-37. FAA/DO A Revised T of C. Coordinator Added Page & Para. 7.39. Added Page. MAR. 26, 1998 Date ( ( PA-28-181, ARCHER III ISSUED: AUGUST 19, 1994 REPORT: VB-1563 vi-a REVISED: JULY 21, 2015 Rev. 3 vi-a Added page & Rev. 3 to L of R. (PR020415) vi-b Added page. 3-4 Revised Para. 3.5. 4-7 Revised Para. 4.5. 4-8 Revised Para. 4.5. 4-9 Revised Para. 4.5. 4-10 Revised Para. 4.5. 4-11 Revised Para. 4.5. 4-18 Revised Para. 4.13. 4-19 Revised Para. 4.13. 4-22 Revised Para. 4.23. 5-13 Revised Fig. 5-5. 5-15 Revised Fig. 5-9. Albert J. Mill 5-17 Revised Fig. 5-13. 5-31 Revised Fig. 5-33. April 15, 2002 Date Rev. 4 vi-a Added Rev. 4 to L of R. (PR090615) 4-17 Revised Note in Para. 4.9.

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8-1 Revised text in Para. 8.1. thru 8-2 Albert J. Mill June 15, 2009 Rev. 5 ii Updated copyright. (PR150721) vi-a Added Rev. 5 to L of R. 4-7 Revised Note in Para. 4.5. Eric A. Wright July 21, 2015 PILOT’S OPERATInG HAnDBOOk LOG Of REVISIOnS Revision FAA Approval Number and Revised Description of Revisions Signature and Code Pages Date PA-28-181, ARCHER III REPORT: VB-1563 ISSUED: AUGUST 19, 1994 vi-b REVISED: APRIL 15, 2002 PILOT’S OPERATInG HAnDBOOk LOG Of REVISIOnS Revision FAA Approval Number and Revised Description of Revisions Signature and Code Pages Date SECTION 1 SECTION 2 SECTION 3 SECTION 4 SECTION 5 SECTION 6 SECTION 7 / SECTION 8 SECTION 9 SECTION 10 TABLE OF CONTENTS GENERAL LIMITATIONS EMERGENCY PROCEDURES NORMAL PROCEDURES PERFORMANCE WEIGHT AND BALANCE DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS AIRPLANE HANDLING, SERVICING AND MAINTENANCE SUPPLEMENTS OPERATING TIPS REPORT: VB-lS63 vii .':.. '.,:, THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-lS63 viii ( ( i I Paragraph No. TABLE OF CONTENTS SECTION 1 GENERAL Page 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 Maxitnurn 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-1S63 l-i THIS PAGE INTENTIONALLY LEFl' BLANK REPORT: VB-1563 l-ii ( ( ( PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III 1.1 INTRODUCTION SECTION 1 GENERAL SECTION 1 GENERAL This Pilot's Operating Handbook is designed for maximum utilization as an operating guide for the pilot. It includes the material required to be fUI11ished 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 cutTent 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 ihat tile airplane is ill au airwortilY 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 aITangement 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, perfonnance and other sections to provide easier access to informa- tion that may be required in /light. The "Emcrgcncy Proccdllfcs" Scction has been fUI11ished 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. ISSUED: AUGUST 19, 1994 REPORT: VB-1S63 1-1 SECTION 1 GENERAL Min turning radius 30 (tt) (from pivot point to wing tip) PIPER AIRCRAFT CORPORATION I'A.28·181, AUCHER III ~------- 24' --------IIoi REPORT: VB·1563 1·2 THREEvmw ISSUED: AUGUST 19, 1994 ( ( ( PIPER AmCRAFT CORPORATION PA-28-181, ARCHER TIl 1.3 ENGINES (a) Number of Engines (b) Engine Manufacturer (c) Engine Model Number (d) Takeoff Power (BHP) (e) Takeoff Power Engine Speed (RPM) (f) Bore (inches) (g) Stroke (inches) (h) Displacement (cubic inches) (i) Compression Ratio G) Engine Type 1.5 PROPELLERS (a) Number of Propellers (b) Propeller Manufacturer (c) Model (d) Number of Blades (e) Propeller Diameter (inches) (1) Maximum (2) Minimum (f) Propeller Type 1.7 FUEL AVGASONLY (a) Fuel Capacity (U.S. gal.) (total) (b) Usable Fuel (U.S. gal.) (total) (c) Fuel (1) Minimum Octane (2) Alternate Fuel ISSUED: AUGUST 19, 1994 SECTION 1 GENERAL 1 Lycoming 0-360-A4M 180 2700 5.125 4.375 361.0 8.5:1 Four Cylinder, Direct Drive, Horizontally Opposed, Air Cooled 1 Sensenich 76EM8S14-0-62 2 76 76 Fixed Pitch 50 48 100 Green or 100LL I3ItH~ Aviation Grade Refer to latest issue of Lycoming Instruction No. 1070. REPORT: VR-1563 1-3 SECTION 1 GENERAL PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III 1.9 OIL (a) Oil Capacity (U.S. quarts) (b) Oil Specification (c) Oil Viscosity per Average Ambient 'lcmp. for Starting (1) Above 60°F (2) 30°F to 90°F (3) OaF to 70°F (4) Below 10°F 1.11 MAXIMUM WEIGHTS 8 Refer to latest issue of Lycoming Service Instruction 1014. Single Multi S.A.E.50 S.A.E. 40 or 50 S.A.E.40 S.A.E. 40 S.A.E.30 S.A.E. 40 or 20W-30 S.A.E. 20 S.A.E. 20W-30 Nonnal Utility (a) Maximum Ramp Weight (lbs.) 2558 2138 (b) Maximum Takeoff Weight (Ibs.) 2550 2130 (c) Maximum Landing Weight (Ibs.) 2550 2130 (d) Maximum Weights in Baggage Compartment (ibs.) 200 0 1.13 STANDAIW AIRPLANE WEIGHTS Refer to Figure 6-5 for tile Struldanl Empty Weigllt and the Useful Load. REPORT: VB-1563 1-4 ISSUED: AUGUST 19, 1994 ( ( ( PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III 1.15 BAGGAGE SPACE (a) Compartment Volume (cubic feet) (b) Entry Width (inches) (c) Entry Height (inches) 1.17 SPECIFIC LOADINGS (a) Wing Loading (lbs. per sq. ft.) (b) Power Loading (lbs. per hp) ISSUED: AUGUST 19, 1994 SECTION 1 GENERAL 24 22 20 15.0 14.2 REP OUT: VB·1563 1-5 SECTION 1 GENERAL PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III 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 tile pilot. (a) General Airspeed Terminology and Symbols CAS KCAS GS lAS KIAS TAS VA VFE REPORT: VB-1S63 ,"- 1-6 Calibrated Airspeed means the indicated speed of an aircraft, corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. Calibrated Airspeed expressed in "Knots." Ground Speed is the speed of an airplane relative to tile ground. Indicated Airspeed is tile speed of an air- craft as shown on the airspeed indicator when corrected for instrument error. lAS values published in this handbook assume zero instrument error. Indicated Airspeed expressed in "Knots." True Airspeed is the airspeed of an airplane relati ve to undisturbed air which is the CAS corrected for alLitude, temperature and compressibility. Maneuvering Speed is tile maximum speed at which application of full available aerodynamic control will not overstress tile airplane. ( Maximum Flap Extended Speed is the highest speed permissible WiUl wing flaps in a prescribed extended position. ( ISSUED: AUGUST 19, 1994 PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER m SECTION 1 GENERAL 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 tlle airplane is con- trollable. Vso Stalling Speed or the minimum steady flight speed at which tlle airplane is con- trollable in the landing configuration. Vx Best Angle-or-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 tlle airspeed which delivers tlle greatest gain in altitude in tlle 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 -O.OOI98C (-O.003564°F) per foot and zero above that altitude. OAT Outside Air Temperature is the free air static temperature, obtained eitller from inflight temperature indications or ground meteorological sources, adjusted for instrument error and compressibility effects. ISSUED: AUGUST 19, 1994 REPORT: Vll-1S63 1-7 SECTION 1 GENERAL Indicated Pressure Altitude Pressure Alli!ude Station Pressure Wind (c) Power lcnninology Takeoff Power Maximum Continuous Power (d) Engine Instruments EGTGaugc REPORT: VB-1S63 1-8 PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III The number actually read from an altimeter when the barometric subscale has been set to 29.92 inches of mercury (1013.2 ( millibars). Altitude measured from standard sea-level pressure (29.92 in. Hg) by a pressure or barometric altimeter. It is the indicated pressure altitude corrected for position and instrument error. In Illis handbook, altimeter instrument errors are assumed to be zero. Actual atmospheric pressure at field elevation. The wind velocities recorded as variables on the charts of this handbook are to be understood as the headwind or tailwind components of Ille reported winds. Maximum power permissible for takeoff. ( Maximum power permissible continuously during Hight. Exhaust Gas Temperature Gauge ( ISSUED: AUGUST 19, 1994 PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III SECTION 1 GENERAL (e) Airplane Performance and Flight Planning Terminology Climb Gradient Demonstrated Crosswind Velocity (Demo. X-Wind) Accelerate-S top Distance Route Segment The demonstrated ratio of the change in height during a portion of a climb, to the horizontal distance traversed in the same time interval. The demonstrated crosswind velocity is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during certification tests. The distance required to accelerate an air- plane to a specified speed and, assuming failure of an engine at the instant tilat speed is atL:'lined, to bring tile airplane to a stop. A part of a route. Each end of tilat 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 Tenninology 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 tile reference datum. Arm The horizontal distance from the reference datum to the center of gravity (C.G.) of an item. ISSUED: AUGUST 19, 1994 REPORT: VB-1S63 1-9 SECTION 1 GENERAL Moment Center of Gravity (e.G.) C.G.Arm C.G. Limits Usable Fuel Unusable Fuel St.mdanl Empty Weight Basic Empty Weight Payload Useful Load Maximum Ramp Weight REPORT: VB-lS63 1-10 PIPER AIRCRAFT CORPORATION PA·28-181, ARCHER III 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.) The point at which an airplane would balance if suspended. Its distance from tile reference datum is found by dividing the total moment by the total weight of the airplane. The ann obtained by adding tile airplane's individual moments and dividing the sum by tile total weight. The extreme center of gravity locations within which the airplane must be operated at a given weight. Fuel available for flight planning. Fuel remaining after a runout test has been ( completed in accordance with govern- mental regulations. Weight of a standard airplane including unusable fuel, full operating fluids and full oil. Standard empty weight plus optional equipment. Weight of occupants, cargo and baggage. Difference between takeoff weight, or ramp weight is applicable, and basic empty weight. Maximum weight approved for ground maneuver. (It includes weight of start, L:'lxi and run up fuel.) ( ISSUED: AUGUST 19,1994 PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III SECTION 1 GENERAL Maximum Takeoff Weight Maximum Landing Weight Maximum Zero Fuel Weight ISSUED: AUGUST 19, 1994 Maximum weight approved for the start of the takeoff run. Maximum weight approved for the landing touchdown. Maximum weight exclusive of usable fuel. REPORT: VB-lS63 1-11 SECTION 1 GENERAL 1.21 CONVERSION FACTORS MULTIPLY centimeters (cm) centimeters of mercury al 0° C (cm Hg) cubic cenlimeters (cm3) cubic feet (ft3) cubic inches (in3) cubic melers (m3) degrees arc. (deg) degrees arc per second (deg/sec) REPORT: VB-1S63 1-12 PIPER AIRCRAFT CORPORATION BY 0.032808 0.3937 0.01 13.3322 .3937 27.85 0.1934 3.53IxlO-5 0.06102 0.001 0.03381 2.642xlO-4 28317 7.481 1728 28.32 0.028317 16.39 5.787xlO-4 4.329xlO-3 0.01639 I.639x 10- 5 0.5541 0.01732 35.3147 264.2 61024 1000000 0.01745 0.01745 0.166667 PA-28-181, ARCHER III TO OBTAIN feet (ft.) inches (in.) meters (m) hectopascals (hPa) inches of mercury (in. Hg) pounds / sq. foot (lbUft2) pounds / sq. inch (lbUin2) cubic feel (ft3) cubic inches (in3) Liters (I) fluid ounces (fl. oz) U.S. gallons (U.S. gal) cubic centimeters (cm3) U.S. gallons (U.S. gal) cubic inches (in3) liters (1) cubic meters (m 3) cubic centimeters (cm3) cubic feel (ft3) U.S. gallons (U.S. gal) liters (I) cubic meters (m 3) fluid ounces (11 oz) U.S. quarts (U.S. qt) cubic feel (n3) U.S. gallons (U.S. gal) cubic inches (in 3) liters (1) radians radians per second revolutions per second ISSUED: AUGUST 19, 1994 REVISED: MARCH 26, 1998 ( ( ( PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III MULTIPLY drams, fluid (dr. fl.) feet (ft) feet per minute (ft I min) feet per second (ft / sec) foot-pounds (ft.-lbs.) foot-pound per minute (ft-lbs/ min) foot-pound per second (ft-lbs/ sec) gallons, imperial (imperial gal) gallons, U.S. dry (U.S. gal dry) ISSUED: AUGUST 19, 1994 BY 3.697xl0-3 3.697xlo-6 0.125 30.48 12 0.3048 1.8939xlO-4 1.6458 0.0606061 0.01829 9.8716xlO-3 0.00508 0.01136 1.097 0.5921 0.3048 0.6818 3.2383xl0-4 1.3558 14.5939 3.03xl0- 5 81.348 1.818xlo-5 1.3558 4.546xlo-3 1.201 277.4 4.546 4.405xlo-3 0.1556 1.164 268.8 4.405 SECTION 1 GENERAL TO OBTAIN liters (1) cubic meters (m3) fluid ounces (fl. oz) centimeters (cm) inches meters (m) miles (mi) nautical miles (NM) rods kilometers per hour (km / hr) knots (kt) meters per second (m / s) miles per hour (mph) kilometers per hour (km / hI') knots (kt) meters per second (m / s) miles per hour (mph) kilocalorie (kcal) joules U) newton-meters (n-m) horse power (hp) joules per minute G/ min) horse power (hp) joules per second G/ sec) cubic centimeters (cm3) U.S. gallon (U.S. gal) cubic inches (in3) liters (I) cubic meters (m3) cubic feet (ft3) U.S. gallon (U.S. gal) cubic inches (in3) liters (I) REPORT: VB-1S63 1-13 SECTION 1 GENERAL MULTIPLY gallons, U.S. Liquid (U.S. gal) hectares (ha) horsepower (hp) horsepower, metric inches (in) inches of mercury REPORT: VB·1563 1-14 PIPER AIRCRAli'T CORPORATION PA-28·181, ARCHER III BY TO OBTAIN 3785.4 cubic centimeters (cm3) ( " 0.1337 cubic feet (ft3) 0.83268 imperial gallons (imperial gal) 231 cubic inches (in3) 3.785 liters (1) 3.785xl0-3 cubic meters (m3) 128 fluid ounces (fl. oz) 2.471 acres 107639 square feet (ft2) 10000 square meters (m2) 33000 foot-pound per minute (ft-Ibs / min) 550 foot-pound per second (ft-Ibs / sec) 745.7 joules per second U/ sec) 1.014 metric horsepower (metric hp) 8.026x103 newton-meters per second ( (n-m/ sec) 0.9863 horsepower (hp) 735.484 joules per second U/ sec) 8.138x103 newton-meters per second (n-m/ sec) 2.54 centimeters (cm) 0.08333 feet (ft) 0.0254 meters (m) 25.4 millimeters (mm) 0.033421 atmospheres (atm) 2.54 centimeters of mercury (cmHg) 33.8639 hectopascals (hPa) 70.73 pounds per square foot (Ibf / ft2) 0.4912 pounds per square inch rbf / in2) ( 25.4 millimeters mercury (mm I-Ig) ISSUED: AUGUST 19, 1994 PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER In MULTIPLY BY kilometers (km) Ix 10-5 3280.8 0.6214 0.53996 kilometers per hour 58.68 0.9113 0.53996 16.67 0.27778 0.6214 knots (kt) 1.689 1.852 51.48 1 Ii ters (1) 1000 0.03531 0.22 0.264172 61.02 0.001 33.814 1.05669 liters per second (1 1sec) 2.12 meters (m) 3.28084 39.37 6.214xlO-4 5.3996x10-4 0.198838 meters per minute (m 1 min) 0.06 116.6307 ISSUED: AUGUST 19, 1994 TO OBTAIN SECTION 1 GENERAL centimeter (cm) feet (ft) miles (mi) nautical miles (nm) feet per minute (ft 1 min) feet per second (ft 1 sec) knots (kt) meters per minute (m 1 min) meters per second (ml sec) miles per hour (mph) feet per second (ft 1 sec) kilometer per hour (km 1 hr) meier per second (m 1 sec) naulical mile per hour (nautical mph) statute mile per hour (statute mph) cubic centimeter (cm3) cubic feet (ft3) imperial gallons (imperial gal) U.S. gallons (U.S. gal) cubic inches (in3) cubic meter (m3) fluid ounces (fl. oz.) U. S. quart (qt) cubic feet per minute (ft3 1 min) feet inches miles (mi) nautical mile (nm) rod kilometers per hour (km 1 hI') knots (kl) REPORT: Vll·1563 1-15 SECTION 1 GENERAL MULTIPLY meters per second (m/sec) miles, slatute(mi) miles per hour (mph) miles per hour squared (lui / h1'2) mit Ii bars m.illimelers of mercury at 0° C (nun Hg) nautical miles (nm) fluid ounces (fl. oz) pounds per square foot (psf or lbs / ft2) REPORT: VB·1563 1·16 PIPER AIRCRAFT CORPORATION PA·2S·181, ARCHER III BY TO OBTAlN 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 luiles per hour (mph) 5280 feet (ft) 1609.3 meters (m) 1.6093 kilometers (km) 0.8684 nauticalnules (nm) 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 2.151 feet per second squared (ft / sec2) 0.44704 meter per second squared ( (m / sec2) 1.0 hectopascals (hPa) 0.02953 inches of mercury (in Hg) 1.3332 hectopascals (hPa) 0.03937 inches of mercury (in Hg) 6080 feel (ft) 1.852 kilometers (km) 1852 meters (m) 1.1516 statute miles (mi) 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) 2.9574xlO-5 cubic meters (m3) 0.1414 inches of mercury (in Hg) 47.880 newtons per square meter ( (n / m2) ISSUED: AUGUST 19, 1994 PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III MULTIPLY BY pounds per square inch 68.9475 (llis! in2) 5.1715 2.036 quart, U.S. (qt) 57.749 0.94635 9 .46353x 10-4 radians 57.3 0.1592 radians per second 57.3 9.549 revolutions 360 6.283 revolutions per minute (rpm) 6 0.1047 rod 16.5 5.029 square centimeters (cm2) 0.001076 0.155 0.0001 square feet (ft2) 929 144 0.092903 square inches (in2) 6.4516 0.006944 6.4516xlO-4 square kilometers (km2) 1000000 0.3861 square meters (m2) 10.76391 0.0001 square miles (nu2) 2589988 2.59 ISSUED: AUGUST 19, 1994 SECTION 1 GENERAL TO OBTAIN millibar (mb) centimeter of mercury (cmHg) inches of mercury (in Hg) cubic inches (in3) liters (1) cubic meters (m3) degrees arc (deg) revolutions (rev) degrees per second (deg !sec) revolutions per minute (rpm) degrees (deg) radians deg per second (deg! sec) radians per second (r! sec) feet (ft) meters (m) square feet (ft2) square inches (in2) square meters (m2) square centimeters (cm2) square inches (in2) square meters (m2) square centimeters (cm2) square feet (ft2) square meters (m2) square meters (m2) square miles (mi2) square feet (ft2) hectors (ha) square meters (m2) square kilometers (km2) REPORT: VH-1S63 1-17 SECTION 1 GENERAL PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT ULANK REPORT: VB-1S63 1-18 ISSUED: AUGUST 19, 1994 ( ( ( Paragraph No. TABLE OF CONTENTS SECTION 2 LIMITATIONS Page No. 2.1 General......................................................................................... 2-1 2.3 Airspr.ed LiInitations .............. ............ ............ .......... ............ ........ 2-1 2.5 Airspeed Indicator Markings........................................................ 2-2 2.7 Power Plant LiInitations ............................................................... 2-3 2.9 Power Plant Instrument Markings................................................ 2-4 2.11 Weight LiInits ....................................................................... ........ 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 UEPOUT: VU-lS63 2-i THIS PAGE INTENTIONALLY LEFT ULANK REPORT: VB-1563 2-ii ( ( ( PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III SECTION 2 LIMITATIONS 2.1 GENERAL SECTION 2 LIMITATIONS 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 lltility 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 Never Exceed Speed (VNE) - Do not exceed this speed in any operation. Maximum Structural Cruising Speed (VNO) - Do not exceed this speed except in smooth air and then only with caution. ISSUED: AUGUST 19, 1994 KIAS KCAS 154 148 125 121 REPORT: Vll-1S63 2-1 SECTION 2 LIMITATIONS PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III SPEED KIAS Design Maneuvering Speed (VA) - Do not make full or abrupt control Illovements above this speed. At 2550 lbs. G.W. 113 At 16341bs. G.w. 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 nOL Gxcecd this speed with the flaps cxlceded. 2.5 AIRSPEED INDICATOR MARKINGS MARKING Red Radial Line (Never Exceed) Yellow Arc (Caution Range - Smooth Air Only) Green Arc (Normal Operating Range) White Arc (Flap Down) 102 KCAS 111 89 100 lAS 154 KTS 125 KTS to 154 KTS 50 KTS to 125 KTS 45 KTS to 102KTS REPORT: VB-1S63 2·2 ISSUED: AUGUST 19, 1994 REVISED: FEBRUARY 24, 1995 ( ( ( PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER ill 2.7 POWER PLANT LIMITATIONS (a) Number of Engines (b) Engine Manufacturer (c) Engine Model No. (d) Engine Operating Limits (1) Takeoff Power limit (BHP) (2) Takeoff Engine Speed (RPM) (3) Maximum Oil Temperature (4) Oil Pressure Minimum (red line) Maximum (red line) (5) Fuel Pressure Minimum (red line) Maximum (red line) (6) Fuel (AVGAS ONLY) (minimum grade) (7) Number of Propellers (8) Propeller Manufacturer (9) Propeller Model (10) Propeller Diameter Minimum Maximum (11) Propeller Tolerance (static RPM at maximum permissible throttle setting at sea level) at ISA conditions SECTION 2 LIMITATIONS 1 Lycoming 0-360-A4M 180 2700 245F 25 PSI 115 PSI 0.5 PSI 8 PSI 100 or lOOLL Aviation Grade 1 Sensenich 7 6EM8S 14-0-62 76 IN. 76 IN. Not above 2340 RPM Not below 2240 RPM NOTE: Reference aircraft maintenance manual for test procedure to determine approved static RPM under non-standard conditions. ISSUED: AUGUST 19, 1994 REPORT: Vll-1563 2-3 SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATION;.:;S_________.__~P~'A:...;-2::..:8;...-::..:18:...;1;.:.,::..:A:;;:R..:..C.;..;;F:;;:IE::..:'::..:R;,.:I=II 2.9 POWER PLANT INSTRUMENT MARKINGS (a) Tachometer Green Arc (Nonnal Operating Range) Red Line (Takeoff Power) (b) Oil Temperature Green Arc (Normal Operating Range) Red Line (Maximum) (c) Oil Pressure Green Arc (Normal Operating Range) Yellow Arc (Caution Range) (Idle) Yellow Arc (Ground Warm-Up) Red Line (Minimum) Red Line (Maximum) (d) Fuel Pressure Green Arc (N01mal Operating Range) Red Line (Minimum) Red Line (Maximum) (e) Vacuum Gauge Red Line (Minimum) Green Arc (Normal Operating Range) Red Line (Maximum) 2.11 'VEIGHT LIlVIITS (a) Maximulll Ramp (Ibs.) (b) Maximum Weight (lbs.) (c) Maximum Baggage (lbs.) NOTE 500 to 2700 RPM 2700 RPM 100° to 245°F 245°F 55 PSI to 95 PSI 25 PSI to 55 PSI 95 PSI to 115 PSI 25 PSI 115 PSI 0.5 PSI to 8 PSI 0.5 PSI 8 PSI 4.8 in Hg 4.8 in Hg. to 5.2 in Hg Nonnal 2558 2550 200 S.2in Hg Utility 2138 2130 o Refer to Section 5 (Performance) for maximum weight as limited by performmlce. REPORT: VJl-lS63 2-4 ISSUED: AUGUST 19, 1994 ( ( PIPER AIRCRAFT CORPORATION PA-28·181, ARCHER ill SECTION 2 LIMITATIONS 2.13 CENTER OF GRAVITY LIMITS (a) Nannal 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 Pounds 2130 2050 (and less) Forward Limit Rearward Limit Inches Aft of Datum Inches Aft of Datum 83.0 93.0 82.0 93.0 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. ISSUED: AUGUST ]9, 1994 REPORT: VB-1S63 2-5 SECTION 2 LIMITATIONS PIPER AIRCRAFT CORPORATION PA.28·181, ARCHER III 2.15 MANEUVER LIMITS (a) Normal Category· All acrobatic maneuvers including spins prohibited. ( (b) Utility Category - Approved maneuvers for bank angles exceeding 60°. Steep Tums Lazy Eights Chandelles 2.17 FLIGHT LOAD FACTOnS (a) Positive Load Factor (Maximum) (b) Negative Load Factor (Maximum) 2.19 TYPES OF O1)ERATION Entry Speed 113 KIAS 113 KIAS 113 KIAS Normal 3.8G Utility 4.4 G No inverted maneuvers approved The airplane is approved for tile following operations when equipped in ( accordance with FAR 91 or FAR l35. (a) Day Y.ER. (b) Night V.ER. (c) Day I.F.R. (d) Night LF.R. (e) Non Icing 2.21 FUEL LIMITATIONS (a) Total Capacity (b) Unusable Fuel The unusable fuel for this airplane has been determined as 1.0 gallon in each wing in critical flight attitudes. (c) Usable Fuel The usable fuel in this airplane has been detennined as 24.0 gallons in each wing. 50 U.S. GAL. 2U.S. GAL. 48 U.S. GAL. ( REPORT: VB·1563 2·6 ISSUED: AUGUST 19, 1994 PIPER AIRCRAFT CORPORATION PA-28-18J, ARCHER III 2.25 PLACARDS In full view of the pilot: SECTION 2 LIMITATIONS "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. " ISSUED: AUGUST 19, 1994 REPORT: VB-1563 2-7 SECTION 2 LIMITATIONS PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III 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 INSURE 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- MAL CATEGORY OPERATION - SEE PILOT'S OPERATING HANDBOOK WEIGHT AND BAL- 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." In full view of the pilot: "OIL COOLER WINTERIZATION PLATE TO BE REMOVED WHEN AMBIENT TEMPERATURE EXCEEDS 50° F." REPORT: VB-1S63 2-8 ISSUED: AUGUST 19, 1994 REVISED: MARCH 26, 1998 ( PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III In full view of the pilot: SECTION 2 LThHTATIONS "UTILITY CATEGORY OPERATION ONLY." (1) NO AFT PASSENGERS ALLOWED. (2) ACROBATIC MANEUVERS ARE LIMITED TO THE FOLLOWING: SPINS PROHIBITED STEEP TURNS LAZY EIGHTS CHANDELLES In full view of the pilot: ENfRYSPEED 113 KIAS 113 KIAS 113 KIAS "WARNING" TURN 0l<""'F STROBE LIGHTS WHEN IN CLOSE PROXIMITY TO GROUND OR DURING FLIGHT THROUGH CLOUD, FOG OR HAZE." Adjacent to the filler caps: AVGAS ONLY "GRADII 100LL GRADI! 100 , ." or _,' ~ ,. " ~.... " 'r 1._ ',,4 ...... " "" .... '.... _, >._ - , __ . (,~ ..... ,,~, ..' ~ '-.0.' ISSUED: AUGUST 19, 1994 REPORT: Vn-1S63 2-9 SECTION 2 PIPER AIRCRAFf CORPORATION LIMITATIONS PA·28·181, ARCHER III ------------------------'----- REPORT: VB·1563 2·10 L1\1TENTIONALLY LEFT BLANK ISSUED: AUGUST 19, 1994 ( ( Paragraph No. TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Page No. 3.1 General ........................................................................................ 3-1 3.3 Airspeeds for Safe Operation ....................................................... 3-2 3.5 Emergency Procedures Checklist................................................. 3-2 Engine Fire l)uring 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 Amplit1ed 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-lS63 3-i Paragraph No. TARLE OF CONTENTS (cont) SECTION 3 (cont) 3.25 Electrical Failures ........................................................................ . 3.27 Electrical Overload ..................................................................... .. 3.29 Spin Recovery ............................................................................. . 3.31 Open Door ................................................................................... . 3.33 Carburetor Icing ......................................................................... .. 3.35 Engine Roughness ....................................................................... . REPORT: VB·1563 3·jj Page No. 3-14 3-14 3-15 3-15 3-16 3-16 ( ( ( PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III SECTION 3 EMERGENCY PROCEDURES 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 tile 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. Pilot.s shouldJamiliarize 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 infonnalion on procedures which are not the smne for all aircraft. It is suggested tllat the pilot review standard emergency procedures periodically to remain proficient in iliem. ISSUED: AUGUST 19, 1994 ImpORT: Vll-1S63 3-1 SECTION 3 EMERGENCY PROCEDURES PIPER AIRCRAFT CORPORATION PA·28·181, ARCUER III 3.3 AIRSPEEDS FOR SAFE OPERATION SlalI2~~e?bs (00 Flaps) ........................................................................... 50 KIAS 25501bs (Full Flaps) ..................................................................... ..45 KIAS MlUleuvering Speeds 2550 Ibs .......................................................................................... 113 KIAS 16341bs ............................................................................................ 89 KIAS Never Exceed Speed ............................................................................. 154 KIAS Power Ofr Glide Speed 2550 Ibs (0° Flaps) ........................................................................... 76 KIAS 3.5 EMERGENCY PROCEDURES CHECK LIST ENGINE I?IRE DURING STAnT Starter ............................................... ., .............................................. crank engine Mixture ............................................................................................... .idle cut-off Throttle .......................................................................................................... open Electric fuel PUlnp .......................................................................................... OFF Fuel selector ................................................................................................... OFF ( Abandon if fire continues. ( ENGINE POWER LOSS DUnING TAKEOFF If sufficient runway remains for a nonnallanding, 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 hmding. REPORT: VB·1563 3-2 ISSUED: AUGUST 19, 1994 PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER ill ENGINE POWER LOSS IN FLIGHT If at low altitude: SECTION 3 EMERGENCY PROCEDURES 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 ISSUED: AUGUST 19, 1994 REPORT: VB-1563 3-3 SECTION 3 EMERGENCY PROCEDURES PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER ill FIRE IN FLIGHT Source of fire ............................................................................................... check Electrical fire (smoke in cabin): Batt. Master switch ........................................................................................ OFF ALTR switch .................................................................................................. OFF Vents .............................................................................................................. open Cabin heat ...................................................................................................... OFF ILand 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 REPORT: VB-1563 3-4 ISSUED: AUGUST 19, 1994 REVISED: APRIL 15, 2002 ( ( ( PIPER AIRCRAFT CORPORATION PA-2S-1S1, ARCHER III SECTION 3 EMERGENCY PROCEDURES HIGH OIL lEMPERATURE Land at nearest airport and investigate the problem. Prepare for power off landing. ELECTRICAL FAILURES NOlE: 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: Al:T 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. NOlE: Low Bus Voltage Annunciator will be illuminated. ISSUED: AUGUST 19, 1994 REPORT: Vn-1563 3-5 SECTION 3 ErvIERGENCY PROCEDURES PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER TIl ELECTRICAL OVERLOAD (Alternator over 20 amps above known eJectricalload) ALT switch ...................................................................................................... ON ( DAT switch ........................................................ ............................................ 01'1' 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 DAT switch OFF should be made only when required by an electrical system failure. If alternator loads are not reduced: ALT switch ..................................................................................................... OFF DAr switch ......................................................................................... As required ( Land as soon as possible. Anticipate complete electrical failure. SPIN Rl<:COVERY Rudder ........................................................................................... full opposite to direction of rotation ContJOI wheel .......................................................................... .full forward while neutralizing ailerons Throttle ........................................................................................................... .idle Rudder ..................................................................... neutral (when rotation stops) Cont.rol wheel .................................................................. as required to smoothly REPORT: VB-1563 3-6 regain level flight attitude ISSUED: AUGUST 19, 1994 ( PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER ill OPEN DOOR SECTION 3 EMERGENCY PROCEDURES 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 Stonn window ............................................................................................... open If upper latch is open .................................................................................... .latch If side latch is open ............................................................. pull on rumrest 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 nlaxunUln " smoothness ENGINE ROUGHNESS Carburetor heat ................................................................................................ ON If roughness continues after one min: Carburetor heat ..............................................................................................OFF Mixture ................................................................................. adjust for InaxiInum 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. ISSUED: AUGUST 19, 1994 REPORT: VB-1S63 3-7 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA.28·181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB·1563 3·8 ISSUED: AUGUST 19, 1994 ( ( ( PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III . SECTION 3 EMERGENCY PROCEDURES 3.7 AMPLIFIED EMERGENCY PROCEDURES (GENERAL) The following paragraphs are presented to supply additional infonna- 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 fue continues more than a few seconds, the fire should be extinguished by the best available extemal 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 nonnal landing, lanel straight ahead. If insufficient runway remains, maintain a safe airspeed and make only a shallow tum if necessary to avoid obstructions. Use of naps depends on the circumstances. NOImally, naps should be fully extended for touchdown. ISSUED: AUGUST 19, 1994 REPORT: VB-lS63 3-9 SECTION 3 EMERGENCY PROCEDURES PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III 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 tlIe 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 arc filled. This may require up to ten seconds. If power is not regained, proceed with the Power Off Landing procedure (refer to Ole emergency check list and Paragraph 3.15). 3.13 ENGINE POWER LOSS IN FLIGHT Complete engine power loss is usually caused by fuel flow intelTuption 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). Au airspeed of at least 76 KIAS should be main- tained. ( If altitude permits, switch the fuel selector to another tank containing fuel and tum the electric fuel pump ON. Move tlle mixture control to RICH ( and tlle carburetor heat to ON. Check the engine gauges for an indication of the cause of tlIe power loss. If no fuel pressure is indicated, check Ole tank selector position to be sure it is on a tank containing fuel. When power is restored move tlle carburetor heat to tlle OFF position and tum OfF the electric fuel pump. If tlle preceding steps do not restore power, prepare for an emergency landing. If time pennits, 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 tlle problem is too rich or too lean a mixture or if tlIere is a partial fuel system restriction. Try other fuel tanks. Water in the fuel could take some time to be used up, and allowing tlIe engine to windmill may restore power. If power loss is due to water, fuel pressure indications will be nonnal. REPORT: VB-1S63 3-10 ISSUED: AUGUST 19, 1994 ( PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III SECTION 3 EMERGENCY PROCEDURES 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 Condo 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 hy radio of your diffi- culty and intentions. If anoUler 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 wiqening your paltern, using flaps or stipping, or a combination of these. 0" Touchdown should nonnally 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. Tum Ule battery master and alternator switches OFF. Move the fuel selector valve to OFF. The seat belts and shoulder harness should be lightened. 3.17 FIRE IN Il'LIGHT 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. ISSUED: AUGUST 19, 1994 REPonT: VB-1S63 3-11 SECTION 3 EMERGENCY PROCEDURES PIPER AIRCRAli'T CORPORATION PA w 2S·1S1, ARCHER III If an electrical fire is indicated (smoke in the cabin), the battery master switch should be tumed OFF. The cabin vents should be opened and the cabin heat tumed 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. Tum 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 bc tilC rcsult of a faulty gauge. In eiUler case, proceed toward tilC ncarest airport, and be prepmed for a forced landing. If the problem is not a pressure gauge malfunction,thc cngine may stop suddenly. Maintain altitude until such time as a dead stick landing can be accomplished. Don't change power settings unnecessarily, as tllis may hasten complete power loss. Depending on the circumstances, it may be advisable to make an off ailport landing while power is still available, particularly if otiler 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. REPORT: VB·1563 3·12 ISSUED: AUGUST 19, 1994 PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER HI 3.21 LOSS OF FUEL PRESSURE SECTION 3 EMERGENCY PROCEDURES 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 Ule electric fuel pump OFF. If fuel pressure starts to drop, turn Ule electric fuel pump ON and land at the nearest suitable airport as soon as possible and have the cause investigated. CAUTION If nonnal engine operation and fuel pressure is not immediately re-establish ed, 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. ISSUED: AUGUST 19, 1994 REPORT: VB-1S63 3-13 SECTION 3 EMERGENCY PROCEDURES 3.25 ELECTRICAL FAILURES PIPER AIRCRAFT CORI'ORATION PA.28·181, ARCHER III 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 ~Ullmeter. 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, altemator failure Crul be assumed. The electrical load should be reduced as much as possible. Check tile 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 tile trouble was caused by a momentary overvoltage condition (30.5 volts and up) this procedure should retum the runmeter to a normal reading. NOTE: Low Bus Voltage Annunciator will be illuminated. If tile ammeter continues to indicate "0" output, or if the altemator will not remain reset, tum off the ALT switch, maintain minimum electrical load and land as soon as practical. Anticipate complete elecLIical failure. Duration of ballery 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 runps above known electrical load for ilie operating conditions) it may be caused by a low battery, a battery fault or oilier abnormal electrical load. If the cause is a low battery, tile indication should begin to decrease toward normal within 5 minutes. If the overload condition persists attempt to reduce ilie load by turning off non-essential equipment. REPORT: VB·1563 3·14 ISSUED: AUGUST 19, 1994 ( ( ( . ' \ ~ PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER HI SECTION 3 EMERGENCY PROCEDURES 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 tlle chances of its springing open in flight at both the top and side are remote. However, should you forget tlle 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, tlle door will trail slightly open, and airspeed will be reduced slightly. To close the door in flight, slow the alrplane to 87 KIAS, close the cabin vents and open the storm window. If the top latch is open, latch it. If tlle side latch is open, pull on the armrest while moving the latch handle to the latched position. If both latches are open, close tlle side latch then the top latch. ISSUED: AUGUST 19, 1994 REPORT: VH-1563 3-15 SECTION 3 EMERGENCY PROCEDURES 3.33 CARUURETOR ICING PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III 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 Illis air by vaporization of tile fuel. To avoid Illis, carburetor preheat is provided to replace tile heat lost by vaporization. Carburetor heat should be full on when carburetor ice is encountered. Adjust mixture for maximum smoollmess. 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 al tiLu de. 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, retum Ille 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 he switched to ON amI 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 m:.'f' !lIen ON and repeat with !lIe Right magneto swiLch. If operation is satisfactory on either magneto, proceed on that magneto at reduced power, with mixture full RICH, to a landing at !lIe 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 retum the con- trol to !lIe full cold position. REPORT: Vll-1563 3-16 ISSUED: AUGUST 19, 1994 ( ( Paragraph No. TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES 4.1 General ....................................................................................... .. 4.3 Airspeeds for Safe Operations ..................................................... . 4.5 Nonnal Procedures Checklist.. ................................................... .. Preflight Check ........................................................................ . Engine Start - General ............................................................ .. Before Starting Engine ........................................................... .. Nonnal Start - Cold Engine ..................................................... . Nonna! Start - Hot Engine ..................................................... .. Engine Start - When Flooded .................................................. . Starting With External Power Source ..................................... .. Wann-Up ................................................................................ .. Taxiing .................................................................................... .. Ground Check ........................................ :............................... .. Before Takeoff ........................................................................ .. Takeoff.................................................................................... .. Short Field, Obstacle Clearance ............................................. .. CliInb ...................................................................................... .. Cruising .................................................................................. .. Descent ................................................................................... .. Approach and Landing ........................................................... .. Stopping Engine ..................................................................... .. Mooring .................................................................................. .. 4.7 Preflight Check ........................................................................... .. 4.9 Engine Start - General ................................................................ .. 4.11 Before Starting Engine ............................................................... .. 4.13 Starling Engine ........................................................................... .. 4.15 Wann-Up .................................................................................... .. 4.17 Taxiing ........................................................................................ .. 4.19 Ground Check ............................................................................ .. Page No. 4-1 4-1 4-3 4-3 4-6 4-7 4-7 4-7 4-8 4-8 4-9 4-9 4-9 4-10 4-10 4-11 4-11 4-11 4-11 4-12 4-12 4-12 4-14 4-17 4-17 4-18 4-20 4-20 4-20 REPORT: VB-1S63 4-i Paragraph No. TABLE Ol~ CONTENTS (cont) SECTION 4 (cont) Page No. 4.21 Before Takeoff.............................................................................. 4-21 4.23 lakeoff.......................................................................................... 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 Enginc ........................................................................... 4-25 4.35 Mooring ........................................................................................ 4-26 4.37 Stalls ............................................................................................. 4-26 4.39 Turbulcnt Air Opcration .............................. ................................. 4-27 4.41 Weight and l3alancc...................................................................... 4-27 4.43 Noise Level.................................................................................. 4-27 REPORT: VB-lS63 4-ii PIPER AIRCRAFT CORPORATION PA·28·181, ARCHER III SECTION 4 SECTION 4 NORMAL PROCEDURES 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 tile airplane are presented. Normal procedures associated wiLh 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 [or 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 I?OR 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. ISSUED: AUGUST 19, 1994 REP OUT: VB·1563 4·1 SECTION 4 NORMAL PROCEDURES PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III 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 (b) Best Angle of Climb Speed (c) Turbulent Air Operating Speed (See Subsection 2.3) (d) Maximum Flap Speed (c) Landing Final Approach Speed (Flaps 40) (0 Maximulll Delllonstrated Crosswind Velocity 76KIAS 64KIAS 113 KIAS 102 KIAS 66KIAS 17KTS REPORT: VB-1S63 4-2 ISSUED: AUGUST 19, 1994 ( ( PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III SECTION 4 NORMAL PROCEDURES ....................................... . .".., ........................................ . . . ............................................ WALK·AROUND Figure 4·1 4.5 NORMAL PUOCEDURES CHECK LIST PREFLIGHT CHECK COCKPIT Control wheel .............................................................................release restraints Parking brake .................................................................................................... set Avionics ......................................................................................................... OFF All switches ................................................................................................... OFF Mixture ............................................................................................... .itlle cut-off Magneto switches ........................................................................................... OFF Battery master switch ...................................................................................... ON Fuel gauges .................................................................................... check quantity Annunciator panel ........................................................................................ check Battery master switch .................................................................................... OFI' Flaps ........................................................................................................... extentl Primary flight contro\s ................................................................ proper operation TriIn ............................................................................................................neutral Pi tot and static systems ..................................................................................... drain Windows ................................................................................................. check clean ISSUED: AUGUST 19, 1994 UEPonT: VB·]563 4-3 SECTION 4 NORMAL PROCEDURES PIPER AIRCRAFr CORPORATION PA-28-181, ARCHER III Required papers and POll ............................................................ check on board Tow bar and baggage ......................................................... stow properly - secure Baggage door .............................................................................. close and secure RIGHT WING Surfacc condition ............................................................. clcar of ice, frost, snow Flap and hinges ............................................................................................ check Aileron and hinges ....................................................................................... check Static wicks .................................................................................... check - secure Wing tip and lights ....................................................................................... check Fuel t~U1k ........................................................................................... 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 .................................................................................. rernove ( Main gear strut· ...... ·...... ··· .. · .. ·· .. · .. ·...... ·.. ·· .. · ...... ·.. ·.. ·· .... ·.. ·;~fl~~i·~·1~··(4:5·±·:~~0fn~~ ( Tire .............................................................................................................. check Brake block and disc .................................................................................... check Fresh air inlet. ................................................................................................ clear NOSE SECTION Gcneral conditioll ......................................................................................... chcck 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 REPORT: VB-1563 4-4 ISSUED: AUGUST 19, 1994 PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III SECTION 4 NORMAL PROCEDURES 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 .................................................................................................... relnove ISSUED: AUGUST 19,1994 REPORT: Vn-1563 4-5 SECTION 4 NORMAL PROCEDURES l\USCELLANEOUS PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER ITI Battery master switch ...................................................................................... ON (' Flaps ............................................................................................................ retract Interior lighting .............................................................................. ON and check Pitot heat switch .............................................................................................. ON Pitot heat OFF/INOP Anllullciator ................................................... extinguished CAUTION: Care should be taken when an operational check of the heated pitot head is being perfonned. The ullit becomes very hol. Ground operation should be limited to three minutes to avoid damaging tile heater elements. NOTE: Secure and adjust all unused seat belts and shoulder hamess to prevent control interference or passenger injury during flight in turbulent air. Exterior lighting switches ............................................................... ON and check Pitot ................................................................................................. check - warm Stall warning hom ........................................................................................ check ( All lighting switches ...................................................................................... OFF Pitot heat switch ............................................................................................. OFF Pilot heat OFF/lNOP Annunciator .................................................... .illuminated BattelY master switch .................................................................................... OFF Passengers .................................................................................................... board l)oor ......................................................................................... Closed and secure Scats ................................................................... adjustcd and /locked in position Scat belts and harness ...................................................................... .fasten/adjust check inertia reel ENGINE START - GENERAL CAUTION: Do not attempt flight if tilere is no indication of alternator output. CAUTION: If a positive oil pressure is not indicated wiUlin 30 seconds following an engine start, stop Ule engine and detennine tile trouble. In cold weallier it will take a few seconds longer to ( get a positive oil pressure indication. REPORT: VU-1S63 4-6 ISSUED: AUGUST 19, 1994 PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES ISSUED: AUGUST 19, 1994 REPORT: VB-1563 4-7 REVISED: JULY 21, 2015 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 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-181, ARCHER III REPORT: VB-1563 ISSUED: AUGUST 19, 1994 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 PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III Proceed with normal start SECTION 4 NORMAL PROCEDURES Throttle ............................................................................... .lowest possible RPM Right magneto switch ...................................................................................... ON I 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. ............................................................................. press-to-test Carburetor heat ................................................................... approx. 75 RPM drop Engine is warm for takeoff when throttle can be opened without engine faltering. Electric fuel pump .......................................................................................... OFF Fuel pressure ................................................................................................ check Throttle ........................................................................................................ retard ISSUED: AUGUST 19, 1994 REVISED: APRIL 15, 2002 REPORT: VB-1563 4-9 SECTION 4 NORMAL PROCEDURES BEFORE TAKEOFF PIPER AIRCRAFT CORPORATION PA-28-181, ARCHER III Battery master switch ............................................................................ verify ON ( Alternator switch ................................................................................... verify ON , Magnetos ............................................................................................... verify ON Flight instruments ........................................................................................ check Fuel selector ........................................................................................ proper tank Electric fuel pump ........................................................................................... ON Engine gauges .............................................................................................. check Carburetor heat .............................................................................................. OFF Mixture ............................................................................................................. set Seat backs ...................................................................................................... erect Seats .................................................................... adjusted and locked in position Belts/harness .................................................................................. fastened/check Empty seats ................................................................ seat belts securely fastened Flaps .................................................................................................................. set Trim .................................................................................................................. set Controls.: ......................................................................................................... free Door .......................................................................................................... .latched Air conditioner (if installed) .......................................................................... OFF ( TAKEOFF NORMAL TECHNIQUE Flaps .................................................................................................................. set Trim ......................

All Piper PA-28 Archer III pilot's operating handbook