Piper ARCHER III Pilot Operating Handbook
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Piper ARCHER III Pilot Operating Handbook

Piper ARCHER III Pilot Operating Handbook

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Table of Contents

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AIRPLANE
SERIAL NO. ________________________
PA-28-181
REPORT: VB-1611 FAA APPROVED BY:
DATE OF APPROVAL:
JULY 12, 1995
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.
ARCHER III
OPERATING
HANDBOOK
AIRPLANE FLIGHT MANUAL
AIRPLANE
REGIST. NO. _____________________
PETER E. PECK
D.O.A. NO. SO-1
THE NEW PIPER AIRCRAFT, INC.
VERO BEACH, FLORIDA
PA-28-181
SN 2843001 AND UP
PILOT'S
AND
FAA APPROVED

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  • Page 1 REPORT: VB-1611 FAA APPROVED BY: PETER E. PECK D.O.A. NO. SO-1 DATE OF APPROVAL: THE NEW PIPER AIRCRAFT, INC. JULY 12, 1995 VERO BEACH, FLORIDA 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.
  • Page 2 THIS HANDBOOK TO APPLICABLE AIRCRAFT. THIS HAND- BOOK IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED ON THE FACE OF THE TITLE PAGE. SUBSEQUENT REVISIONS SUPPLIED BY PIPER MUST BE PROPERLY INSERTED. Published by PUBLICATIONS DEPARTMENT Issued: July 12, 1995 ©...
  • Page 3 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.
  • Page 4 REVISIONS The information compiled in the Pilot’s Operating Handbook, with the exception of the equipment list, will be kept current by revisions distributed to the airplane owners. The equipment list was current at the time the airplane was licensed by the manufacturer and thereafter must be maintained by the owner.
  • Page 5 PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Current Revisions to the PA-28-181 ARCHER III Pilot's Operating Handbook, REPORT: VB-1611 issued July 12, 1995. Revision FAA Approval Number and Revised Description of Revisions Signature and Code Pages Date Rev. 1 Added Rev. 1 to L of R page.
  • Page 6 PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Revision FAA Approval Number and Revised Description of Revisions Signature and Code Pages Date Rev. 3 Added Rev. 3 to L of R page. (PR980312) 5-18 Revised fig. 5-15. Peter E. Peck 9-39 Revised header & title. 9-40 Revised header.
  • Page 7 PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Revision FAA Approval Number and Revised Description of Revisions Signature and Code Pages Date Rev. 6 vi-a Added page. (PR981218) vi-b Added page. Revised T of C. Peter E. Peck 9-49 Added page. 9-50 Added page.
  • Page 8 PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Revision FAA Approval Number and Revised Description of Revisions Signature and Code Pages Date Rev. 9 9-81 Added pages (PR010102) thru and Supplement 14. continued 9-82 9-83 Added pages thru and Supplement 15. 9-88 9-89 Added pages thru...
  • Page 9 PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Revision FAA Approval Number and Revised Description of Revisions Signature Code Pages and Date Rev. 11 8-1b Added page and moved info. (PR040105) from pages 8-1 and 8-2. continued Moved info. to page 8-1b and revised para.
  • Page 10 PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Revision FAA Approval Number and Revised Description of Revisions Signature Code Pages and Date Rev. 15 vi-d Added Rev. 15 to L of R. (PR051128) 9-116 Revised Section 3. 9-119 Revised Section 3. Linda J. Dicken 9-123 Revised Section 3.
  • Page 11 PA-28-181Archer III PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 21 v-e,f Added new pages to L of R. (PR081015) vi-e Added Rev. 21 to L of R. 9-ii Added Supplements 24 and Albert J.
  • Page 12 PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Revision FAA Approved Number and Revised Signature Code Pages Description of Revisions and Date REPORT: VB-1611 ISSUED: JULY 12, 1995 vi-f REVISED: OCTOBER 15, 2008...
  • Page 13 TABLE OF CONTENTS SECTION 1 GENERAL SECTION 2 LIMITATIONS SECTION 3 EMERGENCY PROCEDURES SECTION 4 NORMAL PROCEDURES SECTION 5 PERFORMANCE SECTION 6 WEIGHT AND BALANCE SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS SECTION 8 AIRPLANE HANDLING, SERVICING AND MAINTENANCE SECTION 9 SUPPLEMENTS...
  • Page 14 THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 viii...

  • Page 15: Table Of Contents

    TABLE OF CONTENTS SECTION 1 GENERAL Paragraph Page Introduction .................. Engines ..................Propellers..................Fuel ..................... Oil ....................1.11 Maximum Weights ............... 1.13 Standard Airplane Weights............1.15 Baggage Space ................1.17 Specific Loadings ................. 1.19 Symbols, Abbreviations and Terminology ........1.21 Conversion Factors ............... 1-12 REPORT: VB-1611...
  • Page 16 THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 1-ii...

  • Page 17: Introduction

    SECTION 1 PA-28-181, ARCHER III GENERAL SECTION 1 GENERAL 1.1 INTRODUCTION This Pilot’s Operating Handbook is designed for maximum utilization as an operating guide for the pilot. It includes the material required to be furnished to the pilot by F.A.R./C.A.R. It also contains supplemental data supplied by the airplane manufacturer.
  • Page 18 SECTION 1 GENERAL PA-28-181, ARCHER III THREE VIEW REPORT: VB-1611 ISSUED: JULY 12, 1995...

  • Page 19: Engines

    SECTION 1 PA-28-181, ARCHER III GENERAL 1.3 ENGINES (a) Number of Engines (b) Engine Manufacturer Lycoming (c) Engine Model Number O-360-A4M (d) Takeoff Power (BHP) (e) Takeoff Power Engine Speed (RPM) 2700 (f) Bore (inches) 5.125 (g) Stroke (inches) 4.375 (h) Displacement (cubic inches) 361.0...

  • Page 20: Oil

    SECTION 1 GENERAL PA-28-181, ARCHER III 1.9 OIL (a) Oil Capacity (U.S. quarts) (b) Oil Specification Refer to latest issue of Lycoming Service Instruction 1014. (c) Oil Viscosity per Average Ambient Temp. for Starting Single Multi (1) Above 60°F S.A.E. 50 S.A.E.

  • Page 21: Baggage Space

    SECTION 1 PA-28-181, ARCHER III GENERAL 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.) 15.0 (b) Power Loading (lbs. per hp) 14.2...

  • Page 22: Symbols, Abbreviations And Terminology

    SECTION 1 GENERAL 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 the pilot. (a) General Airspeed Terminology and Symbols...
  • Page 23 SECTION 1 PA-28-181, ARCHER III GENERAL Vne/Mne Never Exceed Speed or Mach Number is the speed limit that may not be exceeded at any time. Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution.
  • Page 24 SECTION 1 GENERAL PA-28-181, ARCHER III Indicated T h e n u m b e r a c t u a l l y r e a d f r o m a n Pressure Altitude altimeter when the barometric subscale has been set to 29.92 inches of mercury (1013.2...
  • Page 25 SECTION 1 PA-28-181, ARCHER III GENERAL (e) Airplane Performance and Flight Planning Terminology Climb Gradient The demonstrated ratio of the change in height during a portion of a climb, to the horizontal distance traversed in the same time interval. Demonstrated...
  • Page 26 SECTION 1 GENERAL PA-28-181, ARCHER III Moment The product of the weight of an item multi- plied by its arm. (Moment divided by a constant is used to simplify balance calcu- lations by reducing the number of digits.) Center of Gravity The point at which an airplane would (C.G.)
  • Page 27 SECTION 1 PA-28-181, ARCHER III GENERAL Maximum Maximum weight approved for the start of Takeoff Weight the takeoff run. Maximum Maximum weight approved for the landing Landing Weight touchdown. Maximum Zero Maximum weight exclusive of usable fuel. Fuel Weight ISSUED: JULY 12, 1995...

  • Page 28: Conversion Factors

    SECTION 1 GENERAL PA-28-181, ARCHER III 1.21 CONVERSION FACTORS MULTIPLY TO OBTAIN centimeters (cm) 0.032808 feet (ft.) 0.3937 inches (in.) 0.01 meters (m) centimeters of 13.3322 hectopascals (hPa) mercury at 0° C .3937 inches of mercury (in. pounds / sq. foot (Ibf./ft 2 ) (cm Hg) 27.85...
  • Page 29 SECTION 1 PA-28-181, ARCHER III GENERAL MULTIPLY TO OBTAIN 3.697x10 -3 drams, fluid (dr. fl.) liters (1) 3.697x10 -6 cubic meters (m 3 ) 0.125 fluid ounces (fl. oz) feet (ft) 30.48 centimeters (cm) inches 0.3048 meters (m) 1.8939x10 -4 miles (mi) 1.6458...
  • Page 30 SECTION 1 GENERAL PA-28-181, ARCHER III MULTIPLY TO OBTAIN cubic centimeters (cm 3 ) gallons, U.S. Liquid 3785.4 cubic feet (ft 3 ) (U.S. gal) 0.1337 0.83268 imperial gallons (imperial gal) cubic inches (in 3 ) 3.785 liters (1) 3.785x10 -3 cubic meters (m 3 ) fluid ounces (fl.
  • Page 31 SECTION 1 PA-28-181, ARCHER III GENERAL MULTIPLY TO OBTAIN lx10 -5 kilometers (km) centimeter (cm) 3280.8 feet (ft) 0.6214 miles (mi) 0.53996 nautical miles (nm) kilometers per hour 58.68 feet per minute (ft / min) 0.9113 feet per second (ft / sec) 0.53996...
  • Page 32 SECTION 1 GENERAL PA-28-181, ARCHER III MULTIPLY TO OBTAIN meters per second (m/sec) 196.8504 feet per minute (ft / min) 3.280840 feet per second (ft / sec) kilometers per hour (km / 1.94384 knots (kt) 2.237 miles per hour (mph)
  • Page 33 SECTION 1 PA-28-181, ARCHER III GENERAL MULTIPLY TO OBTAIN pounds per square inch 68.9475 millibar (mb) (Ibs/ in 2 ) 5.1715 centimeter of mercury (cm Hg) 2.036 inches of mercury (in Hg) cubic inches (in 3 ) quart, U.S. (qt) 57.749...
  • Page 34 SECTION 1 GENERAL PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 1-18...
  • Page 35 TABLE OF CONTENTS SECTION 2 LIMITATIONS Paragraph Page General ..................Airspeed Limitations ..............Airspeed Indicator Markings............Power Plant Limitations ............... Power Plant Instrument Markings ..........2.11 Weight Limits ................2.13 Center of Gravity Limits .............. 2.15 Maneuver Limits ................2.17 Flight Load Factors ..............2.19 Types of Operations..............
  • Page 36 THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 2-ii...

  • Page 37: General

    SECTION 2 PA-28-181, ARCHER III LIMITATIONS SECTION 2 LIMITATIONS 2.1 GENERAL This section provides the ``FAA Approved’’ operating limitations, instrument markings, color coding and basic placards necessary for opera- tion of the airplane and its systems. This airplane must be operated as a normal or utility category airplane in compliance with the operating limitations stated in the form of placards and markings and those given in this section and this complete handbook.

  • Page 38: Airspeed Indicator Markings

    SECTION 2 LIMITATIONS PA-28-181, ARCHER III SPEED KIAS KCAS Design Maneuvering Speed (VA) - Do not make full or abrupt control movements above this speed. At 2550 lbs. G.W. At 1634 lbs. G.W. CAUTION: Maneuvering speed decreases at lighter weight as the effects of aerodynamic forces become more pronounced.

  • Page 39: Power Plant Limitations

    SECTION 2 PA-28-181, ARCHER III LIMITATIONS 2.7 POWER PLANT LIMITATIONS (a) Number of Engines (b) Engine Manufacturer Lycoming (c) Engine Model No. O-360-A4M (d) Engine Operating Limits (1) Takeoff Power limit (BHP) (2) Takeoff Engine Speed (RPM) 2700 (3) Maximum Oil Temperature...

  • Page 40: Power Plant Instrument Markings

    SECTION 2 LIMITATIONS PA-28-181, ARCHER III 2.9 POWER PLANT INSTRUMENT MARKINGS (a) Tachometer Green Arc (Normal Operating Range) 500 to 2700 RPM Red Line (Takeoff Power) 2700 RPM (b) Oil Temperature Green Arc (Normal Operating Range) 100° to 245°F Red Line (Maximum) 245°F...

  • Page 41: Center Of Gravity Limits

    SECTION 2 PA-28-181, ARCHER III LIMITATIONS 2.13 CENTER OF GRAVITY LIMITS (a) Normal Category Weight Forward Limit Rearward Limit Pounds Inches Aft of Datum Inches Aft of Datum 2550 88.6 93.0 2050 (and 82.0 93.0 less) (b) Utility Category Weight...

  • Page 42: Maneuver Limits

    SECTION 2 LIMITATIONS 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°. Entry Speed Steep Turns 113 KIAS Lazy Eights 113 KIAS...

  • Page 43: Placards

    SECTION 2 PA-28-181, ARCHER III LIMITATIONS 2.25 PLACARDS In full view of the pilot: “THIS AIRPLANE MUST BE OPERATED AS A NOR- MAL OR UTILITY CATEGORY AIRPLANE IN COM- PLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS.
  • Page 44 SECTION 2 LIMITATIONS 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 I N S U R E...
  • Page 45 SECTION 2 PA-28-181, ARCHER III LIMITATIONS In full view of the pilot: ``UTILITY CATEGORY OPERATION ONLY.’’ (1) NO AFT PASSENGERS ALLOWED. (2) ACROBATIC MANEUVERS ARE LIMITED TO THE FOLLOWING: ENTRY SPEED SPINS PROHIBITED — STEEP TURNS 113 KIAS LAZY EIGHTS...
  • Page 46 SECTION 2 LIMITATIONS PA-28-181, ARCHER III INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 2-10...
  • Page 47 TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Paragraph Page General ..................Airspeeds for Safe Operation ............Emergency Procedures Checklist ..........Engine Fire During Start ............Engine Power Loss During Takeoff ......... Engine Power Loss In Flight ............ Power Off Landing ..............Fire In Flight................

  • Page 48: Paragraph Page

    TABLE OF CONTENTS (cont) SECTION 3 (cont) Paragraph Page 3.25 Electrical Failures................. 3-14 3.27 Electrical Overload............... 3-14 3.29 Spin Recovery ................3-15 3.31 Open Door ..................3-15 3.33 Carburetor Icing ................3-16 3.35 Engine Roughness ................ 3-16 REPORT: VB-1611 3-ii...

  • Page 49: General

    SECTION 3 PA-28-181, ARCHER III 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.

  • Page 50: Engine Fire During Start

    SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III AIRSPEEDS FOR SAFE OPERATION Stall Speeds 2550 lbs (0° Flaps)................50 KIAS 2550 lbs (Full Flaps)...............45 KIAS Maneuvering Speeds 2550 lbs..................113 KIAS 1634 lbs....................89 KIAS Never Exceed Speed ................154 KIAS Power Off Glide Speed 2550 lbs (0°...

  • Page 51: Engine Power Loss In Flight

    SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES ENGINE POWER LOSS IN FLIGHT If at low altitude: Airspeed ................MAINTAIN 76 KIAS Minimum If altitude permits: Fuel selector..................switch to tank containing fuel Electric fuel pump ...................ON Mixture ......................RICH Carburetor heat ....................ON Engine gauges ...............check for indication...

  • Page 52: Fire In Flight

    SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III FIRE IN FLIGHT Source of fire ....................check Electrical fire (smoke in cabin): Batt. Master switch ..................OFF ALTR switch....................OFF Vents ......................open Cabin heat ......................OFF Land as soon as possible. Engine fire: Fuel selector....................OFF Throttle ....................CLOSED Mixture ....................idle cut-off...

  • Page 53: High Oil Temperature

    SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES HIGH OIL TEMPERATURE Land at nearest airport and investigate the problem. Prepare for power off landing. ELECTRICAL FAILURES NOTE: Anytime the bus voltage is below 25 Vdc, the Low Bus Voltage Annunciator will be illuminated.

  • Page 54: Electrical Overload

    SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III ELECTRICAL OVERLOAD (Alternator over 20 amps above known electrical load) ALT switch ......................ON BAT switch.....................OFF If alternator loads are reduced: Electrical load ..............Reduce to Minimum Land as soon as practical. NOTE Due to increased system voltage and radio...

  • Page 55: Open Door

    SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES OPEN DOOR If both upper and side latches are open, the door will trail slightly open and airspeeds will be reduced slightly. To close the door in flight: Slow airplane to 87 KIAS.
  • Page 56 SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995...

  • Page 57: Amplified Emergency Procedures (General)

    SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES 3.7 AMPLIFIED EMERGENCY PROCEDURES (GENERAL) The following paragraphs are presented to supply additional informa-tion for the purpose of providing the pilot with a more complete under-standing of the recommended course of action and probable cause of an emergency situation.

  • Page 58: Engine Power Loss In Flight

    SECTION 3 EMERGENCY PROCEDURES 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 the mixture is RICH.

  • Page 59: Power Off Landing

    SECTION 3 PA-28-181, ARCHER III 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).

  • Page 60: Loss Of Oil Pressure

    SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III If an electrical fire is indicated (smoke in the cabin), the battery master switch should be turned OFF. The cabin vents should be opened and the cabin heat turned OFF. A landing should be made as soon as possible.

  • Page 61: Loss Of Fuel Pressure

    SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES 3.21 LOSS OF FUEL PRESSURE The most probable cause of loss of fuel pressure is either fuel depletion in the fuel tank selected or failure of the engine driven fuel pump. If loss of fuel pressure occurs, turn ON the electric fuel pump and check that the fuel selector is on a tank containing usable fuel.

  • Page 62: Electrical Failures

    SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III 3.25 ELECTRICAL FAILURES NOTE: Anytime the bus voltage is below 25 Vdc, the Low Bus Voltage Annunciator will be illuminated. Loss of alternator output is detected through zero reading on the ammeter. Before executing the following procedure, insure that the reading is zero and not merely low by actuating an electrically powered device, such as the landing light.

  • Page 63: Spin Recovery

    SECTION 3 PA-28-181, ARCHER III 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.

  • Page 64: Carburetor Icing

    SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III 3.33 CARBURETOR ICING Under certain moist atmospheric conditions at temperatures of -5°C to 20°C, it is possible for ice to form in the induction system, even in summer weather. This is due to the high air velocity through the carburetor venturi and the absorption of heat from this air by vaporization of the fuel.
  • Page 65 TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES Paragraph Page General ..................Airspeeds for Safe Operations............Normal Procedures Checklist............Preflight Check................. Engine Start - General .............. Before Starting Engine ............. Normal Start - Cold Engine............Normal Start - Hot Engine ............Engine Start - When Flooded ...........

  • Page 66: Paragraph Page

    TABLE OF CONTENTS (cont) SECTION 4 (cont) Paragraph Page 4.21 Before Takeoff................4-21 4.23 Takeoff..................4-22 4.25 Climb.................... 4-22 4.27 Cruising ..................4-23 4.29 Descent ..................4-24 4.31 Approach and Landing ..............4-24 4.33 Stopping Engine ................4-25 4.35 Mooring..................4-26 4.37 Stalls .....................

  • Page 67: General

    4.1 GENERAL This section describes the recommended procedures for the conduct of normal operations for the Archer III. All of the required (FAA regulations) procedures and those necessary for operation of the airplane as determined by the operating and design features of the airplane are presented.
  • Page 68 SECTION 4 NORMAL PROCEDURES 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...

  • Page 69: Normal Procedures Checklist

    SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES WALK-AROUND Figure 4-1 4.5 NORMAL PROCEDURES CHECK LIST PREFLIGHT CHECK COCKPIT Control wheel ................release restraints Parking brake ....................set Avionics ......................OFF All switches ....................OFF Mixture ....................idle cut-off Magneto switches ..................OFF Battery master switch ..................ON Fuel gauges ..................check quantity...
  • Page 70 SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III Required papers and POH ............check on board Tow bar and baggage ............stow properly - secure Baggage door ................close and secure RIGHT WING Surface condition .............clear of ice, frost, snow Flap and hinges ....................check Aileron and hinges ..................check...
  • Page 71 SECTION 4 PA-28-181, ARCHER III 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...

  • Page 72: Engine Start - General

    SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III MISCELLANEOUS Battery master switch ..................ON Flaps......................retract Interior lighting ................ON and check Pitot heat switch ....................ON Pitot heat OFF/INOP Annunciator ...........extinguished CAUTION: Care should be taken when an operational check of the heated pitot head is being performed. The unit becomes very hot.

  • Page 73: Before Starting Engine

    SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES BEFORE STARTING ENGINE Brakes........................set Circuit breakers ..................check in Alternate static source ..................OFF Carburetor heat ..................full cold Avionics......................OFF Fuel selector ..................desired tank NORMAL START - COLD ENGINE Throttle ....................1/4 in. open Battery master switch..................ON Alternator switch....................ON...

  • Page 74: Starter

    SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III 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...

  • Page 75: Warm-Up

    SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES Proceed with normal start Throttle ................lowest possible RPM Right magneto switch..................ON External power plug ............disconnect from fuselage Battery master switch ..................ON Alternator switch ..............ON - check ammeter Oil pressure ....................check WARM-UP Throttle ..................800 to 1200 RPM TAXIING Taxi area ......................clear...

  • Page 76: Fuel Selector

    SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III BEFORE TAKEOFF 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...

  • Page 77: Short Field, Obstacle Clearance

    SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES SHORT FIELD, OBSTACLE CLEARANCE Flaps ..................25 (second notch) Trim ..................slightly aft of neutral Throttle ..................full power prior to brake release Accelerate to 55 KIAS depending on aircraft weight. Control wheel..............back pressure to rotate to climb attitude After breaking ground, accelerate to 60 KIAS depending on aircraft weight.

  • Page 78: Fuel Selector

    SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III APPROACH AND LANDING Fuel selector..................proper tank Seat backs ......................erect Seats ..............adjusted and locked in position Belts/harness ..................fasten/adjust Electric fuel pump ...................ON Mixture ......................set Flaps ..................set - 102 KIAS max Air conditioner (if installed) ................OFF Initial approach speed ................75 KIAS...
  • Page 79 SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES INTENTIONALLY LEFT BLANK ISSUED: JULY 12, 1995 REPORT: VB-1611 4-13...

  • Page 80: Preflight Check

    SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III PREFLIGHT CHECK The airplane should be given a thorough preflight and walk-around check. The preflight should include a check of the airplane’s operational status, computation of weight and C.G. limits, takeoff distance and in-flight performance.
  • Page 81 SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES Place a container under the quick drain. Drain the fuel tanks through the quick drain prior to the first flight and after refueling, making sure that enough fuel has been drained to verify the proper fuel and insure that all water and sediment is removed.
  • Page 82 SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III Open the fuel cap and visually check the fuel supply. Replace cap securely. The fuel tank vent should be clear of obstructions. Place a container under the quick drain. Drain enough fuel to verify the proper fuel and to insure that all water and sediment has been removed.

  • Page 83: Engine Start - General

    SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES When all passengers are on board, the pilot should check the cabin doors for proper closing and latching procedures. The door should be gently pulled shut, the door handle firmly latched and the overhead latch button turned to the ``LOCK’’...

  • Page 84: Starting Engine

    SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III 4.13 STARTING ENGINE (a) Starting Engine When Cold Open the throttle lever approximately 1/4 inch. Turn ON the battery master switch, alternator switch, left magneto switch and the electric fuel pump. Move the mixture control to full RICH, verify the propeller area is clear and engage the starter.
  • Page 85 SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES (d) Starting Engine 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.

  • Page 86: Warm-Up

    SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III 4.15 WARM-UP Warm-up the engine at 800 to 1200 RPM for not more than two minutes in warm weather and four minutes in cold. Avoid prolonged idling at low RPM, as this practice may result in fouled spark plugs.

  • Page 87: Before Takeoff

    SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES Check the annunciator panel lights with the press-to-test button. Also check the air conditioner. Carburetor heat should also be checked prior to takeff to be sure the control is operating properly and to clear any ice which may have formed during taxiing.

  • Page 88: Takeoff

    SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III Exercise and set the flaps and trim tab. Insure proper flight control movement and response. All doors should be properly secured and latched. On air conditioned models, the air conditioner must be OFF to insure normal takeoff performance.

  • Page 89: Cruising

    PA-28-181, ARCHER III NORMAL PROCEDURES 4.27 CRUISING The cruising speed of the ARCHER III is determined by many factors, including power setting, altitude, temperature, loading and equipment installed in the airplane. The normal maximum cruising power is 75% of the rated horsepower of the engine.

  • Page 90: Descent

    SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III malfunction of the engine driven fuel pump is immediately apparent. If signs of fuel starvation should occur at any time during flight, fuel exhaustion should be suspected, at which time the fuel selector should be immediately positioned to the other tank and the electric fuel pump switched to the ON position.

  • Page 91: Stopping Engine

    SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES The mixture control should be kept in full RICH position to insure maximum acceleration if it should be necessary to open the throttle again. Carburetor heat should not be applied unless there is an indication of carburetor icing, since the use of carburetor heat causes a reduction in power which may be critical in case of a go-around.

  • Page 92: Mooring

    Mild airframe buffeting and gentle pitching may also precede the stall. The gross weight stalling speed of the ARCHER III with power off and full flaps is 45 KIAS. With the flaps up this speed is increased 5 KTS. Loss of altitude during stalls varies from 100 to 350 feet, depending on configuration and power.

  • Page 93: Turbulent Air Operation

    SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES 4.39 TURBULENT AIR OPERATION In keeping with good operating practice used in all aircraft, it is recom- mended that when turbulent air is encountered or expected, the airspeed be reduced to maneuvering speed to reduce the structural loads caused by gusts and to allow for inadvertent speed build-ups which may occur as a result of the turbulence or of distractions caused by the conditions.
  • Page 94 SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 4-28...
  • Page 95 TABLE OF CONTENTS SECTION 5 PERFORMANCE Paragraph Page General ..................Introduction to Performance and Flight Planning ......Flight Planning Example .............. Performance Graphs ..............List of Figures ................REPORT: VB-1611...
  • Page 96 THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 5-ii...
  • Page 97 5.1 GENERAL All of the required (FAA regulations) and complementary performance information applicable to the ARCHER III is provided by this section. Performance information associated with those optional systems and equipment which require handbook supplements is provided by Section 9 (Supplements).
  • Page 98 SECTION 5 PERFORMANCE PA-28-181, ARCHER III The information provided by paragraph 5.5 (Flight Planning Example) outlines a detailed flight plan using the performance charts in this section. Each chart includes its own example to show how it is used. WARNING...
  • Page 99 SECTION 5 PA-28-181, ARCHER III PERFORMANCE 5.5 FLIGHT PLANNING EXAMPLE (a) Aircraft Loading The first step in planning the flight is to calculate the airplane weight and center of gravity by utilizing the information provided by Section 6 (Weight and Balance) of this handbook.
  • Page 100 SECTION 5 PERFORMANCE PA-28-181, ARCHER III (b) Takeoff and Landing After determining the aircraft loading, all aspects of takeoff and landing must be considered. Conditions of the departure and destination airport must be acquired, evaluated and maintained throughout the flight.
  • Page 101 SECTION 5 PA-28-181, ARCHER III PERFORMANCE (c) Climb The next step in the flight plan is to determine the necessary climb segment components. The desired cruise pressure altitude and corresponding cruise outside air temperature values are the first variables to be con- sidered in determining the climb components from the Time, Distance and Fuel to Climb graph (Figure 5-17).
  • Page 102 SECTION 5 PERFORMANCE PA-28-181, ARCHER III the graph (Figure 5-31). Now, subtract the values obtained from the field conditions from the values obtained from the cruise conditions to find the true time, distance and fuel values needed for the flight plan.
  • Page 103 SECTION 5 PA-28-181, ARCHER III PERFORMANCE (3) Cruise Power (4) Cruise Speed 117 Kts.* (5) Cruise Fuel Consumption 9.5 gal./hr. (6) Cruise Time (e)(2) divided by (e)(4), (282 nm divided by 117 kts) 2.4 hrs. (7) Cruise Fuel (e)(5) multiplied by (e)(6), (9.5 gal./hr multiplied by 2.4 hrs)
  • Page 104 SECTION 5 PERFORMANCE PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995...
  • Page 105 SECTION 5 PA-28-181, ARCHER III PERFORMANCE 5.7 PERFORMANCE GRAPHS LIST OF FIGURES Figure Page Temperature Conversion ............5-11 Airspeed System Calibration............5-12 Stall Speeds ................5-13 Flaps Up Takeoff Performance........... 5-14 25 Flaps Takeoff Performance............ 5-15 5-11 Flaps Up Takeoff Ground Roll ...........
  • Page 106 SECTION 5 PERFORMANCE PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 5-10...
  • Page 107 SECTION 5 PA-28-181, ARCHER III PERFORMANCE TEMPERATURE CONVERSION Figure 5-1 ISSUED: JULY 12, 1995 REPORT: VB-1611 5-11...
  • Page 108 SECTION 5 PERFORMANCE PA-28-181, ARCHER III INDICATED AIRSPEED KIAS (ZERO INSTRUMENT ERROR) AIRSPEED SYSTEM CALIBRATION Figure 5-3 REPORT: VB-1611 ISSUED: JULY 12, 1995 5-12...
  • Page 109 SECTION 5 PA-28-181, ARCHER III PERFORMANCE STALL SPEEDS Figure 5-5 ISSUED: JULY 12, 1995 REPORT: VB-1611 REVISED: NOVEMBER 6, 1998 5-13...
  • Page 110 SECTION 5 PERFORMANCE PA-28-181, ARCHER III FLAPS UP TAKEOFF PERFORMANCE Figure 5-7 REPORT: VB-1611 ISSUED: JULY 12, 1995 5-14 REVISED: MARCH 31, 1998...
  • Page 111 SECTION 5 PA-28-181, ARCHER III PERFORMANCE 25° FLAPS TAKEOFF PERFORMANCE Figure 5-9 ISSUED: JULY 12, 1995 REPORT: VB-1611 REVISED: NOVEMBER 6, 1998 5-15...
  • Page 112 SECTION 5 PERFORMANCE PA-28-181, ARCHER III FLAPS UP TAKEOFF GROUND ROLL Figure 5-11 REPORT: VB-1611 ISSUED: JULY 12, 1995 5-16 REVISED: MARCH 31, 1998...
  • Page 113 SECTION 5 PA-28-181, ARCHER III PERFORMANCE 25° FLAPS TAKEOFF GROUND ROLL Figure 5-13 ISSUED: JULY 12, 1995 REPORT: VB-1611 REVISED: NOVEMBER 6, 1998 5-17...
  • Page 114 SECTION 5 PERFORMANCE PA-28-181, ARCHER III CLIMB PERFORMANCE Figure 5-15 REPORT: VB-1611 ISSUED: JULY 12, 1995 5-18 REVISED: MARCH 31, 1998...
  • Page 115 SECTION 5 PA-28-181, ARCHER III PERFORMANCE TIME, DISTANCE AND FUEL TO CLIMB Figure 5-17 ISSUED: JULY 12, 1995 REPORT: VB-1611 REVISED: MARCH 31, 1998 5-19...
  • Page 116 SECTION 5 PERFORMANCE PA-28-181, ARCHER III ENGINE PERFORMANCE Figure 5-19 REPORT: VB-1611 ISSUED: JULY 12, 1995 5-20 REVISED: MARCH 31, 1998...
  • Page 117 SECTION 5 PA-28-181, ARCHER III PERFORMANCE Engine / Cruise Performance for Non-ISA OAT* RPM for Constant 55% Power Fuel Flow: Best Economy Mixture, 8.2 GPH Pressure Indicated Outside Air Temperature Engine True Air Altitude Speed Speed Feet °C °C °F...
  • Page 118 SECTION 5 PERFORMANCE PA-28-181, ARCHER III Engine / Cruise Performance for Non-ISA OAT* RPM for Constant 65% Power Fuel Flow: Best Economy Mixture, 9.5 GPH Pressure Indicated Outside Air Temperature Engine True Air Altitude Speed Speed Feet °C °C °F...
  • Page 119 SECTION 5 PA-28-181, ARCHER III PERFORMANCE Engine / Cruise Performance for Non-ISA OAT* RPM for Constant 75% Power Fuel Flow: Best Economy Mixture, 11.0 GPH Pressure Indicated Outside Air Temperature Engine True Air Altitude Speed Speed Feet °C °C °F...
  • Page 120 SECTION 5 PERFORMANCE PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 5-24...
  • Page 121 SECTION 5 PA-28-181, ARCHER III PERFORMANCE SPEED POWER Figure 5-21 ISSUED: JULY 12, 1995 REPORT: VB-1611 5-25...
  • Page 122 SECTION 5 PERFORMANCE PA-28-181, ARCHER III RANGE (NO RESERVE) FIGURE 5-27 REPORT: VB-1611 ISSUED: JULY 12, 1995 5-26 REVISED: NOVEMBER 18, 1996...
  • Page 123 SECTION 5 PA-28-181, ARCHER III PERFORMANCE RANGE (45 MIN. RESERVE) FIGURE 5-27a ISSUED: JULY 12, 1995 REPORT: VB-1611 REVISED: NOVEMBER 18, 1996 5-27...
  • Page 124 SECTION 5 PERFORMANCE PA-28-181, ARCHER III ENDURANCE (45 MIN. RESERVE) FIGURE 5-29 REPORT: VB-1611 ISSUED: JULY 12, 1995 5-28 REVISED: APRIL 3, 1997...
  • Page 125 SECTION 5 PA-28-181, ARCHER III PERFORMANCE ENDURANCE (NO RESERVE) Figure 5-29a ISSUED: JULY 12, 1995 REPORT: VB-1611 REVISED: APRIL 3, 1997 5-29...
  • Page 126 SECTION 5 PERFORMANCE PA-28-181, ARCHER III TIME, DISTANCE AND FUEL TO DESCEND Figure 5-31 REPORT: VB-1611 ISSUED: JULY 12, 1995 5-30 REVISED: MARCH 31, 1998...
  • Page 127 SECTION 5 PA-28-181, ARCHER III PERFORMANCE GLIDE RANGE Figure 5-33 ISSUED: JULY 12, 1995 REPORT: VB-1611 REVISED: NOVEMBER 6, 1998 5-31...
  • Page 128 SECTION 5 PERFORMANCE PA-28-181, ARCHER III LANDING PERFORMANCE Figure 5-35 REPORT: VB-1611 ISSUED: JULY 12, 1995 5-32 REVISED: MARCH 31, 1998...
  • Page 129 SECTION 5 PA-28-181, ARCHER III PERFORMANCE LANDING GROUND ROLL Figure 5-37 ISSUED: JULY 12, 1995 REPORT: VB-1611 REVISED: MARCH 31, 1998 5-33...
  • Page 130 SECTION 5 PERFORMANCE PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 5-34...
  • Page 131 TABLE OF CONTENTS SECTION 6 WEIGHT AND BALANCE Paragraph Page General ..................Airplane Weighing Procedure ..........Weight and Balance Data and Record ........Weight and Balance Determination for Flight ......** Equipment List (Form 240-0177)......ENCLOSED WITH THIS HANDBOOK REPORT: VB-1611...
  • Page 132 THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 6-ii...
  • Page 133 SECTION 6 PA-28-181, ARCHER III WEIGHT AND BALANCE SECTION 6 WEIGHT AND BALANCE 6.1 GENERAL In order to achieve the performance and flying characteristics which are designed into the airplane, it must be flown with the weight and center of gravity (C.G.) position within the approved operating range (envelope).
  • Page 134 Following this is the method for computing takeoff weight and C.G. 6.3 AIRPLANE WEIGHING PROCEDURE At the time of licensing, Piper provides each airplane with the basic empty weight and center of gravity location. This data is supplied by Figure 6-5.
  • Page 135 SECTION 6 PA-28-181, ARCHER III WEIGHT AND BALANCE CAUTION Whenever the fuel system is completely drained and fuel is replenished it will be necessary to run the engine for a minimum of 3 minutes at 1000 RPM on each tank to ensure no air exists in the fuel supply lines.
  • Page 136 SECTION 6 WEIGHT AND BALANCE PA-28-181, ARCHER III Scale Scale Position and Symbol Reading Tare Weight Nose Wheel Right Main Wheel (R) Left Main Wheel Basic Empty Weight, as Weighed (T) WEIGHING FORM Figure 6-1 (d) Basic Empty Weight Center of Gravity (1) The following geometry applies to the PA-28-181 airplane when it is level.
  • Page 137 SECTION 6 PA-28-181, ARCHER III WEIGHT AND BALANCE (2) The basic empty weight center of gravity (as weighed including optional equipment, full oil and unusable fuel) can be determined by the following formula: C.G. Arm = N (A) + (R + L) (B)
  • Page 138 SECTION 6 WEIGHT AND BALANCE PA-28-181, ARCHER III MODEL PA-28-181 ARCHER III Airplane Serial Number _____________________ Registration Number ________________________ Date _____________________________________ AIRPLANE BASIC EMPTY WEIGHT C.G. Arm Weight x (Inches Aft = Moment Item (Lbs) of Datum) (In-Lbs) Actual Standard Empty Weight* Computed...
  • Page 139 SECTION 6 PA-28-181, ARCHER III WEIGHT AND BALANCE WEIGHT AND BALANCE RECORD Figure 6-7 ISSUED: JULY 12, 1995 REPORT: VB-1611...
  • Page 140 SECTION 6 WEIGHT AND BALANCE PA-28-181, ARCHER III WEIGHT AND BALANCE RECORD (cont) Figure 6-7 (cont) REPORT: VB-1611 ISSUED: JULY 12, 1995...
  • Page 141 SECTION 6 PA-28-181, ARCHER III WEIGHT AND BALANCE 6.7 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT (a) Add the weight of all items to be loaded to the basic empty weight. (b) Use the Loading Graph (Figure 6-13) to determine the moment of all items to be carried in the airplane.
  • Page 142 SECTION 6 WEIGHT AND BALANCE PA-28-181, ARCHER III Arm Aft Weight Datum Moment (Lbs) (Inches) (In-Lbs) Basic Empty Weight Pilot and Front Passenger 80.5 Passengers (Rear Seats)* 118.1 Fuel (48 Gallon Maximum) 95.0 Baggage (200 Lbs. Maximum)* 142.8 Ramp Weight (2558 Lbs. Normal, 2138 Lbs.
  • Page 143 SECTION 6 PA-28-181, ARCHER III WEIGHT AND BALANCE LOADING GRAPH Figure 6-13 ISSUED: JULY 12, 1995 REPORT: VB-1611 6-11...
  • Page 144 SECTION 6 WEIGHT AND BALANCE PA-28-181, ARCHER III C.G. RANGE AND WEIGHT Figure 6-15 REPORT: VB-1611 ISSUED: JULY 12, 1995 6-12...
  • Page 145 TABLE OF CONTENTS SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS Paragraph Page The Airplane................. Airframe ..................Engine and Propeller ..............Landing Gear................Flight Controls................7.11 Engine Controls................7.13 Fuel System .................. 7.15 Electrical System................7.17 Vacuum System ................7-12 7.19 Instrument Panel................
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  • Page 147: The Airplane

    7.5 ENGINE AND PROPELLER The ARCHER III is powered by a four cylinder, direct drive, horizontally opposed engine rated at 180 horsepower at 2700 rpm. It is furnished with a starter, a 70 ampere, 28 volt alternator, a shielded ignition, vacuum pump drive, a fuel pump, and a dry, automotive type carburetor air filter.
  • Page 148 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III MAIN WHEEL ASSEMBLY Figure 7-1 (Wheel fairing removed for clarity.) REPORT: VB-1611 ISSUED: JULY 12, 1995...

  • Page 149: Landing Gear

    SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 7.7 LANDING GEAR The three landing gears use Cleveland 6.00 x 6 wheels, the main gear wheels (Figure 7-1) being provided with brake drums and Cleveland single disc hydraulic brake assemblies. All three wheels use 6.00 x 6, four-ply rating, Type III tires with tubes.
  • Page 150 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995...

  • Page 151: Flight Controls

    SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION FLIGHT CONTROL CONSOLE Figure 7-3 7.9 FLIGHT CONTROLS Dual controls are provided as standard equipment, with a cable system used between the controls and the surfaces. The horizontal tail (stabilator) is of the all-movable slab type with a trim tab mounted on the trailing edge of the stabilator to reduce the control system forces.
  • Page 152 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III CONTROL QUADRANT AND CONSOLE Figure 7-5 REPORT: VB-1611 ISSUED: JULY 12, 1995...

  • Page 153: Engine Controls

    SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 7.11 ENGINE CONTROLS Engine controls consist of a throttle control and a mixture control lever. These controls are located on the control quadrant on the lower center of the instrument panel (Figure 7-5) where they are accessible to both the pilot and the copilot.
  • Page 154 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III FUEL SELECTOR Figure 7-7 The fuel drains should be opened daily prior to first flight to check for water or sediment and proper fuel. Each tank has an individual drain at the bottom, inboard rear corner.

  • Page 155: Electrical System

    SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION FUEL SYSTEM SCHEMATIC Figure 7-9 7.15 ELECTRICAL SYSTEM The 28-volt electrical system includes a 24-volt battery for starting and to back up alternator output. Electrical power is supplied by a 70 ampere alternator.The battery is mounted in a box on the battery shelf located in the...
  • Page 156 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III All powerplant and exterior lighting switches are grouped in a overhead switch panel, with all avionics switches grouped in a switch panel just above the throttle quadrant (figure 7-15). The circuit breaker panel is located on the lower right side of the instrument panel (figure 7-15).
  • Page 157 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION ALTERNATOR AND STARTER SCHEMATIC Figure 7-11 ISSUED: JULY 12, 1995 REPORT: VB-1611 7-11...

  • Page 158: Vacuum System

    SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III CAUTION: Do not use cigar lighter receptacles as power sources for any devices other than the cigar lighters supplied with the airplane. Any other device plugged into these receptacles may be damaged.

  • Page 159: Instrument Panel

    SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION A vacuum regulator is provided in the system to protect the gyros. The valve is set so the normal vacuum reads 4.8 to 5.2 inches of mercury, a setting which provides sufficient vacuum to operate all the gyros at their rated RPM.
  • Page 160 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III INSTRUMENT PANEL Figure 7-15 REPORT: VB-1611 ISSUED: JULY 12, 1995 7-14...
  • Page 161 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION ISSUED: JULY 12, 1995 REPORT: VB-1611 REVISED: FEBRUARY 5, 2010 7-15...
  • Page 162 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III OVERHEAD SWITCH PANEL Figure 7-15A Overhead switches: (left to right) Left Panel Flood Light Control Engine Primer Engine Starter Battery Master Alternator Fuel Pump Left Magneto Right Magneto Landing Light / Taxi Light...
  • Page 163 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: JULY 12, 1995 REPORT: VB-1611 7-17...

  • Page 164: Pitot-Static System

    SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III 7.21 PITOT-STATIC SYSTEM The system supplies both pitot and static pressure for the airspeed indicator, altimeter and the vertical speed indicator (Figure 7-17). Pitot and static pressure are picked up by a pitot head installed on the bottom of the left wing and carried through pitot and static lines within the wing and fuselage to the gauges on the instrument panel.
  • Page 165 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION PITOT-STATIC SYSTEM Figure 7-17 ISSUED: JULY 12, 1995 REPORT: VB-1611 7-19...

  • Page 166: Heating And Ventilating System

    SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III HEATING AND VENTILATING SYSTEM Figure 7-19 REPORT: VB-1611 ISSUED: JULY 12, 1995 7-20...

  • Page 167: Cabin Features

    SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 7.23 HEATING AND VENTILATING SYSTEM Heat for the cabin interior and the defroster system is provided by a heater muff attached to the exhaust system (Figure 7-19). The amount of heat desired can be regulated with the controls located on the far right side of the instrument panel.

  • Page 168: Baggage Area

    SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III Shoulder harnesses with inertia reels are provided as standard equipment for the occupants of both front and rear seats. A check of the inertia reel mechanism can be made by pulling sharply on the strap and checking that the reel will lock in place under sudden stress.

  • Page 169: Finish

    SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 7.31 FINISH All exterior surfaces are primed with etching primer and finished with a polyurethane finish. 7.33 AIR CONDITIONING* The air conditioning system is a recirculating air system. The major items include: evaporator, condenser, compressor, blower, switches and temperature controls.

  • Page 170: External Power

    SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III Located inboard of the temperature control is the fan speed switch and the air conditioning ON-OFF switch. The fan can be operated independently of the air conditioning. However, it must be on for air conditioner operation. Turning either switch off will disengage the compressor clutch and retract the condenser door.

  • Page 171: Emergency Locator Transmitter

    SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 7.37 EMERGENCY LOCATOR TRANSMITTER* The Emergency Locator Transmitter (ELT), is located in the aft portion of the fuselage just below the stabilator leading edge and is accessible through a plate on the right side of the fuselage. This plate is attached with slotted-head nylon screws for ease of removal;...
  • Page 172 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III ARTEX ELT OPERATION On the ELT unit itself is a two position switch placarded ON and OFF. The OFF position is selected when the transmitter is installed at the factory and the switch should remain in that position whenever the unit is installed in the airplane.

  • Page 173: Carburetor Ice Detection System

    SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 7.39 *CARBURETOR ICE DETECTION SYSTEM A carburetor ice detection system is available as optional equipment. The system consists of a control box mounted on the instrument panel, a probe sensor mounted in the carburetor and a red warning light to indicate the presence of ice in the carburetor.
  • Page 174 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 7-28 REVISED: APRIL 3, 1997...
  • Page 175 TABLE OF CONTENTS SECTION 8 AIRPLANE HANDLING, SERVICING AND MAINTENANCE Paragraph Page General ..................Airplane Inspection Periods ............Preventive Maintenance ............... Airplane Alterations ..............Ground Handling................8.11 Engine Air Filter................8.13 Brake Service ................8.15 Landing Gear Service..............8-10 8.17 Propeller Service ................8-11 8.19 Oil Requirements................
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  • Page 177: General

    SECTION 8 AIRPLANE HANDLING, SERVICING, AND MAINTENANCE GENERAL This section provides guidelines relating to the handling, servicing, and maintenance of the ARCHER III. For complete maintenance instructions, refer to the PA-28-181 Maintenance Manual. WARNING Inspection, maintenance and parts requirements for all non-PIPER approved STC installations are not included in this handbook.
  • Page 178 HANDLING, SERV & MAINT PA-28-181, ARCHER III 8.1 GENERAL (CONTINUED) WARNING Use only genuine PIPER parts or PIPER approved parts obtained from PIPER approved sources, in connection with the maintenance and repair of PIPER airplanes. Genuine PIPER parts are produced and inspected under rigorous procedures to insure airworthiness and suitability for use in PIPER airplane applications.
  • Page 179 Piper’s support systems. Piper takes a continuing interest in having owners get the most efficient use from their airplane and keeping it in the best mechanical condition. Consequently, Piper, from time to time, issues service releases including Service Bulletins, Service Letters, Service Spares Letters, and others relating to the airplane.

  • Page 180: Airplane Inspection Periods

    Piper Authorized Service Center or a reputable repair shop. Piper cannot accept responsibility for the continued airworthiness of any aircraft not maintained to these standards,...

  • Page 181: Preventive Maintenance

    SECTION 8 PA-28-181, ARCHER III HANDLING, SERV & MAINT A spectrographic analysis of the engine oil is available from several sources. This inspection, if performed properly, provides a good check of the internal condition of the engine. To be accurate, induction air filters must be cleaned or changed regularly, and oil samples must be taken and sent in at regular intervals.

  • Page 182: Airplane Alterations

    SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER III 8.7 AIRPLANE ALTERATIONS If the owner desires to have his aircraft modified, he must obtain FAA approval for the alteration. Major alterations accomplished in accordance with Advisory Circular 43.13-2, when performed by an A & P mechanic, may be approved by the local FAA office.

  • Page 183: Ground Handling

    SECTION 8 PA-28-181, ARCHER III HANDLING, SERV & MAINT 8.9 GROUND HANDLING (a) Towing The airplane may be moved on the ground by the use of the nose wheel steering bar that is stowed below the forward ledge of the baggage compartment or by power equipment that will not damage or excessively strain the nose gear steering assembly.
  • Page 184 SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER III (b) Taxiing Before attempting to taxi the airplane, ground personnel should be instructed and approved by a qualified person authorized by the owner. Engine starting and shut-down procedures as well as taxi techniques should be covered. When it...
  • Page 185 SECTION 8 PA-28-181, ARCHER III HANDLING, SERV & MAINT (3) Aileron and stabilator controls should be secured with the front seat belt and chocks used to properly block the wheels. (d) Mooring The airplane should be moored for immovability, security and protection.

  • Page 186: Engine Air Filter

    SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER III 8.11 ENGINE AIR FILTER Inspect inlet for foreign particles and obstructions. Engine Air Filter should be removed and inspected or replaced at intervals as outlined in the aircraft Maintenance Manual. Operations in sever environments may require more frequent attention.
  • Page 187 SECTION 8 PA-28-181, ARCHER III HANDLING, SERV & MAINT BRAKE SYSTEM Figure 8-1 ISSUED: JULY 12, 1995 REPORT: VB-1611...

  • Page 188: Landing Gear Service

    Landing gear oleos on the ARCHER III should be serviced according to the instructions on the units. The main oleos should be extended under normal static load until 4.50 ±...

  • Page 189: Propeller Service

    SECTION 8 PA-28-181, ARCHER III HANDLING, SERV & MAINT In jacking the aircraft for landing gear or other service, two hydraulic jacks and a tail stand should be used. At least 250 pounds of ballast should be placed on the base of the tail stand before the airplane is jacked up. The hydraulic...

  • Page 190: Oil Requirements

    SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER III 8.19 OIL REQUIREMENTS The oil capacity of the engine is 8 quarts and the minimum safe quantity is 2 quarts. It is recommended that the oil be drained and renewed, and the screen cleaned, every 25 hours.
  • Page 191 SECTION 8 PA-28-181, ARCHER III HANDLING, SERV & MAINT A summary of the current grades as well as the previous fuel designations is shown in the following chart: FUEL GRADE COMPARISON CHART Previous Commercial Current Commercial Current Military Fuel Grades (ASTM-D910)
  • Page 192 SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER III CAUTIONS Some fuels have anti-icing additives pre- blended in the fuel at the refinery, so no further blending should be performed. Fuel additive can not be used as a substitute for preflight draining of the the fuel system drains.
  • Page 193 SECTION 8 PA-28-181, ARCHER III HANDLING, SERV & MAINT FUEL DRAIN Figure 8-3 (e) Draining Fuel System The bulk of the fuel may be drained from the system by opening the valve at the inboard end of each fuel tank. Push up on the arms of the drain valve and turn counterclockwise to hold the drain open.

  • Page 194: Tire Inflation

    SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER III 8.23 TIRE INFLATION For maximum service from the tires, keep them inflated to the proper pressures - 18 psi for the nose gear and 24 psi for the main gear. All wheels and tires are balanced before original installation, and the relationship of tire, tube and wheel should be maintained upon reinstallation.

  • Page 195: Cleaning

    SECTION 8 PA-28-181, ARCHER III HANDLING, SERV & MAINT 8.27 CLEANING (a) Cleaning Engine Compartment Before cleaning the engine compartment, place a strip of tape on the magneto vents to prevent any solvent from entering these units. (1) Place a large pan under the engine to catch waste.
  • Page 196 SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER III (b) Cleaning Landing Gear Before cleaning the landing gear, place a plastic cover or similar material over the wheel and brake assembly. (1) Place a pan under the gear to catch waste.
  • Page 197 SECTION 8 PA-28-181, ARCHER III HANDLING, SERV & MAINT (d) Cleaning Windshield and Windows (1) Remove dirt, mud and other loose particles from exterior surfaces with clean water. (2) Wash with mild soap and warm water or with aircraft plastic cleaner. Use a soft cloth or sponge in a straight back and forth motion.

  • Page 198: Cold Weather Operation

    SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER III (f) Cleaning Carpets To clean carpets, first remove loose dirt with a whisk broom or vacuum. For soiled spots and stubborn stains use a non-flammable dry cleaning fluid. Floor carpets may be removed and cleaned like any household carpet.
  • Page 199 TABLE OF CONTENTS SECTION 9 SUPPLEMENTS Paragraph Page General ..................Air Conditioning Installation ............Bendix/King KAP 100 Series Flight Control System....Auxiliary Vacuum System ............Bendix/King KLN 89 (B) GPS Navigation System..(12 Pages) 9-15 Bendix/King KX 155A Comm/Nav System ....(12 Pages) 9-27 Bendix/King KAP 140 Series Flight Control System....
  • Page 200 TABLE OF CONTENTS SECTION 9 SUPPLEMENTS (continued) Paragraph/Supplement Page Avidyne FlightMax Entegra Primary Flight/ Multi-Function Displays With The B&C Specialties BC410 Standby Alternator .....(36 pages) 9-153 Bendix/King KR-87 Digital ADF with KI-227 Indicator ............(10 pages) 9-189 Bendix/King KN-63 DME ..........(4 pages) 9-199 Garmin G500 Primary Flight and Multifunction Display System ................(2 pages)
  • Page 201 SECTION 9 PA-28-181, ARCHER III SUPPLEMENTS SECTION 9 SUPPLEMENTS 9.1 GENERAL This section provides information in the form of Supplements which are necessary for efficient operation of the airplane when equipped with one or more of the various optional systems and equipment not approved with the standard airplane.
  • Page 202 SECTION 9 SUPPLEMENTS PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995...
  • Page 203 This supplement must be attached to the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual when the optional air conditioning system is installed in accordance with Piper Drawing 99575-10. The information contained herein supplements or supersedes the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein.

  • Page 204: General

    SECTION 9 SUPPLEMENT 1 PA-28-181, ARCHER III SECTION 1 - GENERAL This supplement supplies information necessary for the efficient opera- tion of the airplane when the optional air conditioning system is installed. The information contained within this supplement is to be used ``as described’’...
  • Page 205 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 1 (a) Check aircraft master switch ON. (b) Turn the air conditioner control switch to ON and the fan switch to one of the operating positions - the ``AIR COND DOOR’’ warning light will turn on, thereby indicating proper air conditioner condenser door actuation.
  • Page 206 SECTION 9 SUPPLEMENT 1 PA-28-181, ARCHER III Although the cruise speed and range are only slightly affected by the air conditioner operation, these changes should be considered in preflight planning. To be conservative, the following figures assume that the com- pressor is operating continuously while the airplane is airborne.

  • Page 207: Bendix/King Kap 100 Series Flight Control System

    SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 2 PILOT'S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 2 KING KAP 100 SERIES FLIGHT CONTROL SYSTEM The FAA Approved Operational Supplement to the Bendix/King 100 Series Flight Control System as installed per STC SA1565CE-D is supplied by the autopilot manufacturer.
  • Page 208 SECTION 9 SUPPLEMENT 2 PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995...

  • Page 209: Auxiliary Vacuum System

    AUXILIARY VACUUM SYSTEM This supplement must be attached to the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual when the Piper Auxiliary Vacuum System is installed in accordance with Piper Drawing 85387-2. The information contained herein supplements or supersedes the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein.
  • Page 210 SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Piper Auxiliary Vacuum System is installed. The information contained within this supplement is to be used in conjunction with the complete handbook.
  • Page 211 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 3 SECTION 4 - NORMAL PROCEDURES A. Preflight Check. 1. Turn on battery master switch on and verify that VAC OFF lamp lights. NOTE Due to electrical power requirement of the auxiliary vacuum pump it is suggested that the engine be operating while making the following checks.
  • Page 212 SECTION 9 SUPPLEMENT 3 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION The auxiliary dry air pump system provides an independent back-up source of pneumatic power to operate the gyro flight instruments in the event the engine driven air pump fails.
  • Page 213 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 3 ISSUED: JULY 12, 1995 REPORT: VB-1611 9-13...
  • Page 214 SECTION 9 SUPPLEMENT 3 PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 9-14...

  • Page 215: Bendix/King Kln 89(B) Gps Navigation System

    Pilot's O p erating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: PETER E. PECK D.O.A. NO. SO-1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: APRIL 3, 1997 ____ ISSUED: JULY 12, 1995...
  • Page 216 SECTION 9 SUPPLEMENT 4 PA-28-181, ARCHER III SECTION 1 GENERAL NOTE This supplement covers both the KLN 89 (VFR) only and the KLN 89B (IFR approved for Enroute, Terminal and non-precision approach phases of flight). There are numerous places throughout this supplement...
  • Page 217 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 4 SECTION 1 GENERAL (Cont'd) VFR/IFR en route oceanic and remote, en route domestic, terminal, and instrument approach (GPS, VOR, VOR-DME, TACAN, NDB, NDB-DME, RNAV) operation within the U.S. National Airspace System, North Atlantic Minimum Navigation Performance Specifications (MNPS) Airspace and latitudes bounded by 74°...
  • Page 218 SECTION 9 SUPPLEMENT 4 PA-28-181, ARCHER III SECTION 2- LIMITATIONS The KLN 89 (B) GPS Pilot’s Guide, P/N 006-08786-0000, dated May, 1995 (or later applicable revision) must be immediately available to the flight crew whenever navigation is predicated on the use of the system. The Operational Revision Status (ORS) of the Pilot’s Guide must match the ORS...
  • Page 219 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 4 SECTION 3- EMERGENCY PROCEDURES ABNORMAL PROCEDURES If the KLN 89 (B) GPS information is not available or invalid, utilize remaining operational navigation equipment as required. If a “RAIM NOT AVAILABLE” message is displayed while conducting an instrument approach, terminate the approach.
  • Page 220 SECTION 9 SUPPLEMENT 4 PA-28-181, ARCHER III NORMAL PROCEDURES Message (MSG) annunciator - Will flash to alert the pilot of a situation that requires attention. Press the MSG button on the KLN 89 (B) GPS to view the message. (Appendix B of the KLN 89 (B) Pilot’s Guide contains a list of all of the message page messages and their meanings).
  • Page 221 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 4 NORMAL PROCEDURES GPS approach (GPS APR ARM/ACTV) switch/annunciator - (KLN 89B only) used to (a) manually select or deselect approach ARM (or deselect approach ACTV) and (b) annunciate the stage of approach operation either armed (ARM) or activated (ACTV).
  • Page 222 SECTION 9 SUPPLEMENT 4 PA-28-181, ARCHER III NORMAL PROCEDURES ALTITUDE ALERT AURAL TONES 1000 feet prior to reaching the selected altitude - three short tones. Upon reaching the selected altitude - two short tones. Deviating above or below the selected altitude by more than the warn altitude - four short tones.
  • Page 223 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 4 NORMAL PROCEDURES At 30 nm from the airport: Verify automatic annunciation of APR ARM. Note automatic dbar scaling change from ± 5.0 nm to ±1.0 nm over the next 30 seconds. Update the KLN 89B altimeter baro setting as required.
  • Page 224 SECTION 9 SUPPLEMENT 4 PA-28-181, ARCHER III NORMAL PROCEDURES Approaching the FAF inbound (within 2 nm.): Verify APR ACTV. Note automatic dbar scaling change from ±1.0 nm to ± 0.3 nm over the 2 nm inbound to the FAF. Internally the KLN 89B will transition from terminal to approach integrity monitoring.
  • Page 225 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 4 NORMAL PROCEDURES • Waypoint suffixes in the flight plan: i - IAF f- FAF m - MAP h missed approach holding fix. • The DME arc IAF (arc intercept waypoint) will be a) on your present...
  • Page 226 SECTION 9 SUPPLEMENT 4 PA-28-181, ARCHER III NORMAL PROCEDURES APR ARM to APR ACTV is automatic provided: a. You are in APR ARM (normally automatic). b. You are in LEG mode! c. The FAF is the active waypoint! d. Within 2 n.m. of the FAF.

  • Page 227: Bendix/King Kx 155A Comm/Nav System

    This supplement must be attached to the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual when the KX 155A Comm/Nav System is installed per the Piper Drawings. The information contained herein supplements or supersedes the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein.
  • Page 228 PA-28-181, ARCHER III SECTION 1 GENERAL This supplement supplies information necessary for the operation of the airplane when the Bendix/King KX 155A Comm/Nav System is installed in accordance with FAA approved Piper data. SECTION 2 LIMITATIONS No change. SECTION 3- EMERGENCY PROCEDURES No change.
  • Page 229 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 5 SECTION 7 DESCRIPTION & OPERATION GENERAL All controls required to operate the KX 155A/165A are located on the unit front panel. (See Figure 3-1.) FIGURE 3-1 KX 155A CONTROL FUNCTIONS COMM TRANSCEIVER Rotate the VOL knob clockwise from the OFF position. Pull the VOL knob out and adjust for desired listening level.
  • Page 230 SECTION 9 SUPPLEMENT 5 PA-28-181, ARCHER III COMM TRANSCEIVER (CONT'D) The outer knob will change the MHz portion of the standby display. At one band-edge (118 or 136 MHz) the following 1 MHz change will wrap around to the other band-edge. The inner knob will change the kHz portion of the standby display.
  • Page 231 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 5 The KX 155A also has provision to program 32 channels. Pressing the CHAN button for 2 or more seconds will cause the unit to enter the channel program mode. Upon entering the channel program mode,”PG” is displayed next to the channel number and the channel number will flash indicating that it can be programmed.
  • Page 232 SECTION 9 SUPPLEMENT 5 PA-28-181, ARCHER III NAV RECEIVER (CONT'D) The inner knob operates in 50 kHz steps. The NAV receiver’s lower and upper frequency limits are 108.00 MHz and 117.95 MHz. Exceeding the upper limit of frequency band will automatically return to the lower limit and vice versa.
  • Page 233 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 5 FIGURE 3-3 NAV DISPLAY; ACTIVE LOCALIZER FREQUENCY/CDI FORMAT When the received signal is too weak to ensure accuracy the display will “flag”. See Figure 3-4. FIGURE 3-4 VOR FLAG DISPLAY ISSUED: JULY 12, 1995...
  • Page 234 SECTION 9 SUPPLEMENT 5 PA-28-181, ARCHER III NAV RECEIVER (CONT'D) Depressing the mode button will cause the NAV display to go from the ACTIVE/CDI format to the ACTIVE/BEARING format. In the BEARING mode, the increment/decrement knob channels the ACTIVE frequency...
  • Page 235 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 5 Another push of the mode button will cause the NAV display to go from the ACTIVE/BEARING format to the ACTIVE/RADIAL format as shown in Figure 3-7. In the RADIAL mode, the increment/decrement knob channels the...
  • Page 236 SECTION 9 SUPPLEMENT 5 PA-28-181, ARCHER III NAV RECEIVER (CONT'D) Another push of the mode button will cause the unit to go into the TIMER mode. See Figure 3-9. When the unit is turned on the elapsed timer begins counting upwards from zero. The timer can be stopped and reset to zero by pushing the NAV frequency transfer button for 2 seconds or more causing the ET on the display to flash.
  • Page 237 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 5 PILOT CONFIGURATION This mode can be accessed by pressing and holding the Nav Mode Button for more than 2 seconds and then pressing the Nav Frequency Transfer Button for an additional 2 seconds, while continuing to hold the Nav Mode Button. When the Pilot Config Mode is entered the unit will show the “SWRV”...
  • Page 238 SECTION 9 SUPPLEMENT 5 PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 9-38 REVISED: APRIL 3, 1997...

  • Page 239: Bendix/King Kap 140 Series Flight Control System

    SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 6 PILOT'S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 6 KING KAP 140 SERIES FLIGHT CONTROL SYSTEM The FAA Approved Operational Supplement to the Bendix/King 100 Series Flight Control System as installed per STC SA00444WI-D is supplied by the autopilot manufacturer.
  • Page 240 SECTION 9 SUPPLEMENT 6 PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 9-40 REVISED: MARCH 12, 1998...
  • Page 241 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: PETER E. PECK D.O.A. NO. SO-1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: NOVEMBER 6, 1998 ISSUED: JULY 12, 1995 REPORT: VB-1611...
  • Page 242 SECTION 9 SUPPLEMENT 7 PA-28-181, ARCHER III SECTION 1 - GENERAL The GNS 430 System is a fully integrated, panel mounted instrument, which contains a VHF Communications Transceiver, a VOR/ILS receiver, and a Global Positioning System (GPS) Navigation computer. The system consists of a GPS antenna, GPS receiver, VHF VOR/LOC/GS antenna, VOR/ILS receiver, VHF COMM antenna and a VHF Communications transceiver.
  • Page 243 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 7 SECTION 2 - LIMITATIONS A. The GARMIN GNS 430 Pilot’s Guide, p/n 190-00140-00, Rev. A, dated October 1998, or later appropriate revision, must be immediately available to the flight crew whenever navigation is predicated on the use of the system.
  • Page 244 SECTION 9 SUPPLEMENT 7 PA-28-181, ARCHER III SECTION 2 - LIMITATIONS (continued) Accomplishment of ILS, LOC, LOC-BC, LDA, SDF, MLS or any other type of approach not approved for GPS overlay with the GNS 430’s GPS receiver is not authorized.
  • Page 245 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 7 SECTION 3 - EMERGENCY PROCEDURES ABNORMAL PROCEDURES A. If GARMIN GNS 430 navigation information is not available or invalid, utilize remaining operational navigation equipment as required. B. If “RAIM POSITION WARNING” message is displayed the system will flag and no longer provide GPS based navigational guidance.
  • Page 246 SECTION 9 SUPPLEMENT 7 PA-28-181, ARCHER III SECTION 4 - NORMAL PROCEDURES WARNING Familiarity with the enroute operation of the GNS 430 does not constitute proficiency in approach operations. Do not attempt approach operations in IMC prior to attaining proficiency in the use of the GNS 430 approach feature.
  • Page 247 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 7 SECTION 4 - NORMAL PROCEDURES (continued) D. AUTOMATIC LOCALIZER COURSE CAPTURE By default, the GNS 430 automatic localizer course capture feature is enabled. This feature provides a method for system navigation data present...
  • Page 248 SECTION 9 SUPPLEMENT 7 PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 9-48 REVISED: NOVEMBER 6, 1998...
  • Page 249 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: PETER E. PECK D.O.A. NO. SO-1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: DECEMBER 18, 1998 ISSUED: JULY 12, 1995 REPORT: VB-1611...
  • Page 250 SECTION 9 SUPPLEMENT 8 PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 9-50 REVISED: DECEMBER 18, 1998...

  • Page 251: S-Tec Manual Electric Trim System

    SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 9 PILOT'S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 9 S-TEC MANUAL ELECTRIC TRIM SYSTEM WITH TRIM MONITOR (Serial numbers 2843058 and up) The FAA approved operational supplement for the S-TEC Manual Electric Trim System, installed in accordance with STC SA8388SW-D, is required for operation of this system.
  • Page 252 SECTION 9 SUPPLEMENT 9 PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 9-52 REVISED: DECEMBER 6, 1999...

  • Page 253: Model Sky497

    Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: CHRISTINA L. MARSH D.O.A. NO. SO- I THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: July 14, 2000 ISSUED: JULY 12, 1995 REPORT: VB-1611...
  • Page 254 SECTION 9 SUPPLEMENT 10 PA-28-181, ARCHER III SECTION 1 - GENERAL The SKYWATCH system is an on-board traffic advisory system which monitors a radius of 10 nautical miles, of which a maximum of 6 nautical miles are displayed, about the aircraft by interrogating any “intruding”...
  • Page 255 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 10 SECTION 2 - LIMITATIONS Information shown on the display is provided to the pilot as an aid to visually acquiring traffic. Pilot’s should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic.
  • Page 256 SECTION 9 SUPPLEMENT 10 SECTION 4 - NORMAL PROCEDURES (continued) SELF TEST (continued) If “TRAFFIC ADVISORY SYSTEM TEST FAILED” is heard or the SKY497 FAILED screen appears, the SKYWATCH system should be turned OFF. NOTE The operator initiated Self-Test can only be performed when in standby or failed mode.
  • Page 257 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 10 SECTION 4 - NORMAL PROCEDURES (continued) ABNORMAL PROCEDURES If “TRAFFIC ADVISORY SYSTEM TEST FAILED” is heard or the SKY497 FAILED screen appears, the SKYWATCH system should be turned OFF. If the barometric altimeter fails in flight and is the altitude source for the transponder, turn SKYWATCH OFF.
  • Page 258 SECTION 9 SUPPLEMENT 10 PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 9-58, 6 of 6 REVISED: JULY 14, 2000...
  • Page 259 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: CHRISTINA L. MARSH D.O.A. NO. SO- I THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: July 14, 2000 ISSUED: JULY 12, 1995 REPORT: VB-1611...
  • Page 260 SECTION 9 SUPPLEMENT 11 PA-28-181, ARCHER III SECTION 1 - GENERAL This supplement provides information necessary for the operation of the aircraft with the BF Goodrich WX-500 Stormscope. WARNING Never use your Stormscope system to attempt a thunderstorm. The FAA Advisory Circular, Subject: Thunderstorms, and the Airman’s...
  • Page 261 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 11 SECTION 4 - NORMAL PROCEDURES Normal operating procedures are described in the BF Goodrich Aerospace WX-500 Stormscope Users Guide, p/n 009-11501-001, Rev. A, dated September 10, 1997, or later appropriate revision. SECTION 5 - PERFORMANCE No change.
  • Page 262 SECTION 9 SUPPLEMENT 11 PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 9-62, 4 of 4 REVISED: JULY 14, 2000...
  • Page 263 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVE: CHRISTINA L. MARSH D.O.A. NO. SO- I THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: July 14, 2000 ISSUED: JULY 12, 1995 REPORT: VB-1611...
  • Page 264 SECTION 9 SUPPLEMENT 12 PA-28-181, ARCHER III SECTION 1 - GENERAL The GNS 430 System is a fully integrated, panel mounted instrument, which contains a VHF Communications Transceiver, a VOR/ILS Receiver, and a Global Positioning System (GPS) Navigation computer. The system consists of a GPS Antenna, GPS Receiver, VHF VOR/LOC/GS Antenna, VOR/ILS Receiver, VHF COMM Antenna and a VHF Communications Transceiver.
  • Page 265 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 12 SECTION 2 - LIMITATIONS A. The GARMIN GNS 430 Pilot’s Guide, p/n 190-00140-00, Rev. A, dated October 1998, or later appropriate revision, must be immediately available to the flight crew whenever navigation is predicated on the use of the system.
  • Page 266 SECTION 9 SUPPLEMENT 12 PA-28-181, ARCHER III SECTION 2 - LIMITATIONS (continued) C. IFR enroute and terminal navigation predicated upon the GNS 430’s GPS Receiver is prohibited unless the pilot verifies the currency of the data base or verifies each selected waypoint for accuracy by reference to current approved data.
  • Page 267 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 12 SECTION 2 - LIMITATIONS (continued) If not previously defined, the following default settings must be made in the “SETUP 1” menu of the GNS 430 prior to operation (refer to Pilot’s Guide for procedure if necessary): 1.
  • Page 268 SECTION 9 SUPPLEMENT 12 PA-28-181, ARCHER III SECTION 3 - EMERGENCY PROCEDURES ABNORMAL PROCEDURES A. If GARMIN GNS 430 navigation information is not available or invalid, utilize remaining operational navigation equipment as required. B. If “RAIM POSITION WARNING” message is displayed the system will flag and no longer provide GPS based navigational guidance.
  • Page 269 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 12 SECTION 4 - NORMAL PROCEDURES CAUTION Familiarity with the enroute operation of the GNS 430 does not constitute proficiency in approach operations. Do not attempt approach operations in IMC prior to attaining proficiency in the use of the GNS 430 approach feature.
  • Page 270 SECTION 9 SUPPLEMENT 12 PA-28-181, ARCHER III SECTION 4 - NORMAL PROCEDURES (continued) E. DISPLAY OF LIGHTNING STRIKE DATA Lightning strike data detected by the BF Goodrich WX-500 Stormscope will appear on the moving map and weather pages of the GNS 430. For detailed operating instructions regarding the interface of the GNS 430 with the WX-500, refer to the WX-500 Pilot’s Guide and the GNS 430...

  • Page 271: Garmin Gtx 327 Transponder

    Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: CHRISTINA L. MARSH D.O.A. NO. SO- 1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: January 2, 2001 ISSUED: JULY 12, 1995 REPORT: VB-1611...
  • Page 272 SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the Garmin GTX 327 Transponder is installed in accordance with FAA approved Piper data. SECTION 2 - LIMITATIONS No change. SECTION 3 - EMERGENCY PROCEDURES To transmit an emergency signal: •...
  • Page 273 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 13 SECTION 4 - NORMAL PROCEDURES BEFORE TAKEOFF: • To transmit Mode C (Altitude Reporting) code in flight: • Mode Selection Key - ALT • Code Selector Keys - SELECT assigned code. To transmit Mode A (Aircraft Identification) code in flight: •...
  • Page 274 SECTION 9 SUPPLEMENT 13 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION The GTX 327 transponder is powered on by pressing the STBY, ALT or ON keys, or by a remote avionics master switch (if applicable). After power on, a start-up page will be displayed while the unit performs a self test.
  • Page 275 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 13 SECTION 7 - DESCRIPTION AND OPERATION (continued) GTX 327 Configuration Mode (continued) To use the GTX 327 Configuration Mode: 1. Press and hold the FUNC key while powering on the unit using the STBY, ON, or ALT key (or using an avionics master switch).
  • Page 276 SECTION 9 SUPPLEMENT 13 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) Code Selection (continued) Important Codes: 1200 - The VFR code for any altitude in the US (Refer to ICAO standards elsewhere) 7000 - The VFR code commonly used in Europe (Refer to ICAO standards)
  • Page 277 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 13 SECTION 7 - DESCRIPTION AND OPERATION (continued) Keys for Other GTX 327 Functions (continued) PRESSURE ALT: Displays the altitude data supplied to the GTX 327 in feet, hundreds of feet (i.e., flight level), or meters, depending on configuration.
  • Page 278 SECTION 9 SUPPLEMENT 13 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) Altitude Trend Indicator When the “PRESSURE ALT” page is displayed, an arrow may be displayed to the right of the altitude, indicating that the altitude is increasing or decreasing.
  • Page 279 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 13 SECTION 7 - DESCRIPTION AND OPERATION (continued) Automatic ALT/STBY Mode Switching If the GTX 327 is configured for automatic standby switching, the mode will automatically change to ALT when a squat switch senses that the aircraft has become airborne.
  • Page 280 SECTION 9 SUPPLEMENT 13 PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 9-80, 10 of 10 REVISED: JANUARY 2, 2001...
  • Page 281 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 14 PILOT'S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 14 S-TEC SYSTEM 55X TWO AXIS AUTOMATIC FLIGHT GUIDANCE SYSTEM The FAA approved operational supplement for the S-TEC System 55X Autopilot, installed in accordance with STC SA8402-SW-D, is required for operation of this system.
  • Page 282 SECTION 9 SUPPLEMENT 14 PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 9-82 REVISED: JANUARY 2, 2001...

  • Page 283: S-Tec Adf 650A System

    Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: CHRISTINA L. MARSH D.O.A. NO. SO- 1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: January 2, 2001 ISSUED: JULY 12, 1995 REPORT: VB-1611...
  • Page 284 SECTION 9 SUPPLEMENT 15 PA-28-181, ARCHER III SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the S-TEC ADF-650A System is installed in accordance with FAA approved Piper data. SECTION 2 - LIMITATIONS No change.
  • Page 285 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 15 SECTION 4 - NORMAL PROCEDURES To operate as an Automatic Direction Finder: • OFF/VOL Control - ON • Frequency Selector Knobs - SELECT desired frequency. • ADF SPEAKER/PHONE Selector Switch (on audio control panel) - SELECT as desired.
  • Page 286 SECTION 9 SUPPLEMENT 15 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION The S-TEC ADF-650A System operates over a frequency range of 200 through 1799 kHz in 1-kHz increments. Three operating modes are included as part of the ADF-650 System.
  • Page 287 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 15 SECTION 7 - DESCRIPTION AND OPERATION (continued) ANT (Antenna) Mode The ANT (antenna) mode cannot be used for navigation; this mode enhances audio reception clarity and is normally used for station identification. ADF Mode Automatic Direction Finder (ADF) mode is used for navigation.
  • Page 288 SECTION 9 SUPPLEMENT 15 PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 9-88 6 of 6 REVISED: JANUARY 2, 2001...

  • Page 289: Garmin Gma 340 Audio Panel

    Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED CHRISTINA L. MARSH D.O.A. NO. SO-1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL January 2, 2001 ISSUED: JULY 12, 1995...
  • Page 290 SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the Garmin GMA 340 audio panel is installed in accordance with FAA approved Piper data. SECTION 2 - LIMITATIONS No change. SECTION 3 - EMERGENCY PROCEDURES No change.
  • Page 291 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 16 SECTION 5 - PERFORMANCE No change. SECTION 6 - WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance data in section 6 of the Airplane Flight Manual.
  • Page 292 SECTION 9 SUPPLEMENT 16 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) ON/OFF, Pilot Intercom System (ICS) Volume Control The GMA 340 is powered OFF when the left small knob (5) is rotated fully CCW into the detent. To turn the unit ON, rotate the knob clockwise past the click.
  • Page 293 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 16 SECTION 7 - DESCRIPTION AND OPERATION (continued) Aircraft Radios and Navigation Pressing NAV1, NAV2, DME, ADF (16) or MRK (2) selects each audio source. A second button press deselects the audio. Speaker Output Pressing the SPKR button (12) selects the aircraft radios over the cabin speaker.
  • Page 294 SECTION 9 SUPPLEMENT 16 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) Marker Beacon Receiver The GMA 340’s marker beacon receiver controls are located on the left side of the front panel (1 - 4). The SENS button selects either high or low sensitivity as indicated by the HI or LO LED being lit.

  • Page 295: S-Tec Dme 450

    Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: CHRISTINA L. MARSH D.O.A. NO. SO- 1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: January 2, 2001 ISSUED: JULY 12, 1995 REPORT: VB-1611...
  • Page 296 SECTION 9 SUPPLEMENT 17 PA-28-181, ARCHER III SECTION 1 - GENERAL The S-TEC DME-450 system is a full feature, solid state, remote mounted system with full 200 channel capability. For long distance operation, it provides a full 100 watts maximum pulse power transmitter output.
  • Page 297 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 17 SECTION 6 - WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance data in Section 6 of the Pilot’s Operating Handbook and Airplane Flight Manual. SECTION 7 - DESCRIPTION AND OPERATION...
  • Page 298 SECTION 9 SUPPLEMENT 17 PA-28-181, ARCHER III 7 - DESCRIPTION AND OPERATION (continued) 4. DME ON/OFF SWITCH - Turns DME power on or off. Mode Selector Switch Figure 2 5. DME MODE SELECTOR SWITCH (NAV 1, HOLD, NAV 2) - Selects DME operating mode as follows: NAV 1 - Selects DME operation with NO.

  • Page 299: Garmin Gtx 330 Transponder

    Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: ALBERT J. MILL D.O.A. NO. SO - 1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: January 5, 2004 ISSUED: JULY 12, 1995 REPORT: VB-1611...
  • Page 300 SECTION 9 SUPPLEMENT 18 PA-28-181, ARCHER III SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the Garmin GTX 330 Transponder is installed in accordance with FAA approved Piper data. SECTION 2 - LIMITATIONS A.
  • Page 301 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 18 SECTION 4 - NORMAL PROCEDURES BEFORE TAKEOFF: • To transmit Mode C (Altitude Reporting) code in flight: • Mode Selection Key - ALT • Code Selector Keys - SELECT assigned code. To transmit Mode A (Aircraft Identification) code in flight: •...
  • Page 302 SECTION 9 SUPPLEMENT 18 PA-28-181, ARCHER III SECTION 5 - PERFORMANCE No change. SECTION 6 - WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance data in section 6 of the Airplane Flight Manual.
  • Page 303 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: ALBERT J. MILL DOA-510620-CE THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: June 14, 2004 ISSUED: JULY 12, 1995 REPORT: VB-1611...
  • Page 304 SECTION 9 SUPPLEMENT 19 PA-28-181, ARCHER III SECTION 1 - GENERAL The GNS 530 System is a fully integrated, panel mounted instrument, which contains a VHF Communications Transceiver, a VOR/ILS Receiver, and a Global Positioning System (GPS) Navigation computer. The system consists of a GPS Antenna, GPS Receiver, VHF VOR/LOC/GS Antenna, VOR/ILS Receiver, VHF COMM Antenna and a VHF Communications Transceiver.
  • Page 305 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 19 SECTION 2 - LIMITATIONS A. The GARMIN GNS 530 Pilot’s Guide, p/n 190-00181-00, Rev. A, dated November 1999, or later appropriate revision, must be immediately available to the flight crew whenever navigation is predicated on the use of the system.
  • Page 306 SECTION 9 SUPPLEMENT 19 PA-28-181, ARCHER III SECTION 2 - LIMITATIONS (continued) 2. Accomplishment of ILS, LOC, LOC-BC, LDA, SDF, MLS or any other type of approach not approved for GPS overlay with the GNS 530’s GPS receiver is not authorized.
  • Page 307 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 19 SECTION 3 - EMERGENCY PROCEDURES ABNORMAL PROCEDURES A. If GARMIN GNS 530 navigation information is not available or invalid, utilize remaining operational navigation equipment as required. B. If “RAIM POSITION WARNING” message is displayed the system will flag and no longer provide GPS based navigational guidance.
  • Page 308 SECTION 9 SUPPLEMENT 19 PA-28-181, ARCHER III SECTION 4 - NORMAL PROCEDURES CAUTION Familiarity with the enroute operation of the GNS 530 does not constitute proficiency in approach operations. Do not attempt approach operations in IMC prior to attaining proficiency in the use of the GNS 530 approach features.
  • Page 309 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 19 SECTION 4 - NORMAL PROCEDURES (continued) E. AUTOMATIC LOCALIZER COURSE CAPTURE By default, the GNS 530 automatic localizer course capture feature is enabled. This feature provides a method for system navigation data present...
  • Page 310 SECTION 9 SUPPLEMENT 19 PA-28-181, ARCHER III SECTION 5 - PERFORMANCE There is no change to aircraft performance with this equipment installed. SECTION 6 - WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance data in Section 6 of the basic Pilot’s Operating Handbook.

  • Page 311: Avidyne Flightmax Entegra Primary Flight/Multi-Function Displays

    Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: LINDA J. DICKEN DOA-510620-CE THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: OCTOBER 7, 2004 ISSUED: JULY 12, 1995...
  • Page 312 SECTION 9 SUPPLEMENT 20 PA-28-181, ARCHER III SECTION 1 - GENERAL This airplane is equipped with the Avidyne FlightMax Entegra EXP5000 series 700-00006-0XX-( ) Primary Flight Display with software to the latest revision per Avidyne website and EX5000 series 700-00004-0XX-( ) Multi-Function Display with software to the latest revision per Avidyne website, herein referred to as the “PFD”...
  • Page 313 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 20 SECTION 1 - GENERAL (continued) The MFD is intended to be a supplemental display of situational and navigation information to the pilot. Its primary function is to provide a moving map display to the pilot for increased situational awareness. The MFD is capable of accepting...
  • Page 314 SECTION 9 SUPPLEMENT 20 PA-28-181, ARCHER III SECTION 2 - LIMITATIONS A. PFD Limitations 1. IFR flight is prohibited when the PFD or any standby instrument is inoperative (altimeter, airspeed indicator, artificial horizon, or whiskey compass). 2. IFR flight is prohibited upon aircraft total loss of essential engine parameter display (manifold pressure, tachometer, fuel flow).
  • Page 315 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 20 SECTION 2 - LIMITATIONS (continued) B. MFD Limitations (continued) 4. Aircraft dispatch is prohibited when the MFD is inoperative. 5. Selecting “Lightning Display OFF” for the Lightning overlay of the Map page will prevent current heading values from being sent to the WX500 sensor from the EX5000.
  • Page 316 SECTION 9 SUPPLEMENT 20 PA-28-181, ARCHER III SECTION 2 - LIMITATIONS (continued) C. CMAX CHART PAGE Limitations The geographic referenced aircraft symbol must not be used for navigation. NOTE The aircraft symbol displayed provides supplemental aircraft situational awareness information. It is not intended as a means for navigation or flight guidance.
  • Page 317 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 20 THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: JULY 12, 1995 REPORT: VB-1611 REVISED: JANUARY 9, 2006 7 of 30, 9-115...
  • Page 318 SECTION 9 SUPPLEMENT 20 PA-28-181, ARCHER III SECTION 3 - EMERGENCY PROCEDURES Failure of Pilot’s Electronic Attitude Direction Display Screen (PFD) Indication: PFD Display goes blank. Standby Attitude Gyro ..............VERIFY ON and flag is pulled on gyro Maintain attitude control using standby gyro and establish the aircraft in straight and level unaccelerated flight.
  • Page 319 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 20 SECTION 3 - EMERGENCY PROCEDURES (continued) Loss of PFD Engine Data Indication: Indicator needle removed from dial and digital readout replaced with white dashes. Engine Instruments..........Refer to Engine page of MFD Land as soon as practical.
  • Page 320 SECTION 9 SUPPLEMENT 20 PA-28-181, ARCHER III SECTION 3 - EMERGENCY PROCEDURES (continued) Invalid Attitude and Heading Data Indication: Attitude and Heading Data removed and replaced with Red X’s. Standby Attitude Gyro ..............VERIFY ON and flag is pulled on gyro.
  • Page 321 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 20 SECTION 3 - EMERGENCY PROCEDURES (continued) Failure of Attitude, Airspeed and Heading Reference System (ADAHRS) Indication: Airspeed, Attitude, Heading and Altitude replaced with Red X’s. Standby Attitude Gyro ..............VERIFY ON and flag is pulled on gyro Maintain attitude control using standby gyro.
  • Page 322 SECTION 9 SUPPLEMENT 20 PA-28-181, ARCHER III SECTION 3 - EMERGENCY PROCEDURES (continued) Cross Check Monitor Indication: Yellow Crosscheck Attitude Annunciator on PFD. Establish aircraft in straight and level unaccelerated flight. Aircraft Attitude ............Crosscheck aircraft attitude with standby attitude gyro...
  • Page 323 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 20 SECTION 3 - EMERGENCY PROCEDURES (continued) Alternator Failure Indication: Alternator Inop annunciator light illuminated and zero current displayed on MFD alternator indication source. NOTE Anytime the bus voltage is below 25 Vdc, the Low Bus Voltage annunciator will be illuminated.
  • Page 324 SECTION 9 SUPPLEMENT 20 PA-28-181, ARCHER III SECTION 3 - EMERGENCY PROCEDURES (continued) Alternator Failure (continued) If power is not restored: ALTR Switch....................OFF Reduce electrical loads by switching OFF or pulling circuit breakers for all non-essential equipment to include the following: •...
  • Page 325 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 20 SECTION 3 - EMERGENCY PROCEDURES (continued) Complete Electrical Failure Standby Attitude Gyro ......SELECT Standby (STBY) power button CAUTION The STBY PWR annunciator will rapidly flash for approximately one minute when aircraft power is lost.
  • Page 326 SECTION 9 SUPPLEMENT 20 PA-28-181, ARCHER III SECTION 3 - EMERGENCY PROCEDURES (continued) Fire in Flight Electrical Fire Fire......................Extinguish Standby Attitude Gyro ..............VERIFY ON and flag is pulled on gyro Maintain aircraft control with reference to the standby airspeed, altimeter, and attitude gyro indicators.
  • Page 327 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 20 SECTION 3 - EMERGENCY PROCEDURES (continued) Aircraft Engine Power Loss During an engine failure the pilot may elect to attempt an engine restart. During this time large voltage drops may cause the PFD to lose power and reinitialize.
  • Page 328 SECTION 9 SUPPLEMENT 20 PA-28-181, ARCHER III SECTION 3 - EMERGENCY PROCEDURES (continued) Loss of Heading Accuracy Indication: • Difficulty maintaining course while using VOR or GPS. • Excessive difference between heading and track required maintaining a VOR or GPS course.
  • Page 329 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 20 SECTION 4 - NORMAL PROCEDURES Engine Start - General CAUTION Do not attempt flight if there is no indication of alternator output. CAUTION If a positive oil pressure is not indicated within 30 seconds following an engine start, stop the engine and determine the trouble.
  • Page 330 SECTION 9 SUPPLEMENT 20 PA-28-181, ARCHER III SECTION 4 - NORMAL PROCEDURES (continued) Normal Start - Cold Engine Throttle ....................½ inch open Battery Master Switch..................ON Primary Flight Display (PFD) ..........Verify correct aircraft model software Alternator Switch ....................ON Electric Fuel Pump ..................ON Magneto Switches ....................ON...
  • Page 331 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 20 SECTION 4 - NORMAL PROCEDURES (continued) Engine Start When Flooded Throttle ....................Open full Battery Master Switch..................ON Primary Flight Display (PFD) ..........Verify correct aircraft model software Alternator Switch ....................ON Electric Fuel Pump ..................OFF Magneto Switches ....................ON Mixture ....................Idle cut-off...
  • Page 332 SECTION 9 SUPPLEMENT 20 PA-28-181, ARCHER III SECTION 4 - NORMAL PROCEDURES (continued) 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.
  • Page 333 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 20 SECTION 7 - DESCRIPTION AND OPERATION A. PFD Systems Description NOTE This supplement provides a general description of the Avidyne FlightMax Entegra Series 700-00006-0XX-( ) PFD, its operation, and aircraft systems interfaces. For a detailed description of PFD operation, refer to the Avidyne FlightMax Entegra Series Primary Flight Display Pilot’s...
  • Page 334 SECTION 9 SUPPLEMENT 20 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) A. PFD Systems Description (continued) Horizontal Situation Indicator (HSI) Heading Data Magnetic heading is represented in a boxed digital form at the top of the compass rose. Heading rate (Rate of Turn Indicator) takes the form of a blue arcing arrow that begins behind the magnetic heading indicator and moves left or right accordingly.
  • Page 335 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 20 SECTION 7 - DESCRIPTION AND OPERATION (continued) A. PFD Systems Description (continued) Autopilot Integration The Entegra PFD is fully integrated with the S-TEC System 55X Autopilot. Reference bugs for Heading, Altitude, and Vertical Speed are provided on the PFD to control the autopilot and aid pilot situational awareness.
  • Page 336 SECTION 9 SUPPLEMENT 20 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) A. PFD Systems Description (continued) Autopilot Integration (continued) The following autopilot modes are supported by the PFD: 1. HDG (Heading, using the heading bug) 2. NAV (Nav, using the course pointer and course deviation indicator) 3.
  • Page 337 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 20 SECTION 7 - DESCRIPTION AND OPERATION (continued) A. PFD Systems Description (continued) Back-up Instruments The Entegra PFD system installation includes redundant means of display of certain aircraft flight and systems parameters. Back-up Altimeter, Airspeed and Attitude instruments are provided to facilitate pilot cross-checking of PFD display flight parameters.
  • Page 338 SECTION 9 SUPPLEMENT 20 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) B. MFD Systems Description NOTE This supplement provides a general description of the Avidyne EX5000 Series 700-00004-0XX-( ) MFD, its operation and aircraft interface. For a detailed description of the MFD, refer to the Avidyne FlightMax EX5000 Series Pilot’s Guide and Reference, p/n 600-00105-000 revision 00...
  • Page 339 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 20 SECTION 7 - DESCRIPTION AND OPERATION (continued) B. MFD Systems Description (continued) Navigation (continued) Using the Jeppesen NavData data and the GPS-supplied present position, the MFD can provide the pilot with the nearest 25 airports or navaids, depending on pilot selection, within 100 nm.
  • Page 340 SECTION 9 SUPPLEMENT 20 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) B. MFD Systems Description (continued) Setup (continued) Airport Settings page provides selections for displaying airport type, runway surface type and minimum runway lengths on the moving map. Declutter Settings page allows the pilot to select settings for defining the base map detail when changing display range.

  • Page 341: Mid-Continent 4300-4Xx Series Electric Attitude Indicator

    Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: LINDA J. DICKEN DOA-510620-CE THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: OCTOBER 7, 2004 ISSUED: JULY 12, 1995...
  • Page 342 This supplement supplies information necessary for the operation of the airplane when the optional Mid-Continent model 4300-XXX Electric Attitude Indicator is installed in accordance with FAA Approved Piper data. For additional information refer to the Mid-Continent Instruments Pilot’s Guide, manual number 9015834, revision NR, or later revision.
  • Page 343 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 21 SECTION 4 - NORMAL PROCEDURES Preflight Check 1. Apply aircraft power and allow the gyro to spin up for approximately 2 minutes. 2. Press and hold the STBY PWR button. 3. Verify that after several seconds the amber LED has started to flash. This indicates that the unit has latched into the Battery Test Mode.
  • Page 344 SECTION 9 SUPPLEMENT 21 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION The Model 4300-4XX Electric Attitude Indicator incorporates a moving display that simulates the earth's horizon and provides the pilot with a real time visual indication of the aircraft pitch and roll attitude relative to the indicator symbolic airplane.

  • Page 345: S-Tec Adf-650D System

    Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: LINDA J. DICKEN DOA-510620-CE THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: SEPTEMBER 12, 2005 ISSUED: JULY 12, 1995 REPORT: VB-1611...
  • Page 346 SECTION 9 SUPPLEMENT 22 PA-28-181, ARCHER III SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the S-TEC ADF-650D System is installed in accordance with FAA approved Piper data. SECTION 2 - LIMITATIONS No change.
  • Page 347 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 22 SECTION 4 - NORMAL PROCEDURES To turn on the ADF-650D System: • Depress the PWR button momentarily and release. NOTE If the PWR button is pressed for longer than 3 sec- onds, the receiver will immediately shut off.

  • Page 348: Section 4 - Normal Procedures (Continued)

    SECTION 9 SUPPLEMENT 22 PA-28-181, ARCHER III SECTION 4 - NORMAL PROCEDURES (continued) To perform the preflight checklist and self test: • After successful self test, press the mode control until ANT is displayed and input a predetermined frequency to select a station in the immediate area.
  • Page 349 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 22 SECTION 7 - DESCRIPTION AND OPERATION The S-TEC ADF-650D System operates over a frequency range of 200 through 1799 kHz in 1-kHz increments. Three operating modes are included as part of the ADF-650D System.
  • Page 350 SECTION 9 SUPPLEMENT 22 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) Automatic Direction Finder (ADF) Mode The Automatic Direction Finder (ADF) mode uses conventional nondirectional beacons and AM broadcast stations for navigation. This mode activates the bearing pointer. The bearing pointer will point in the direction of the station relative to the aircraft heading.
  • Page 351 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 22 SECTION 7 - DESCRIPTION AND OPERATION (continued) Clear (CLR) The clear function offers several options for the operator. • If the entire frequency is entered and the CLR button is pushed, all the numbers will become dashes.
  • Page 352 SECTION 9 SUPPLEMENT 22 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) Function (FUNC) Selector The function selector enables the user to select between contrast and volume display functions (on power-up, the RCR-650D will be in the volume display function).
  • Page 353 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 22 SECTION 7 - DESCRIPTION AND OPERATION (continued) Function (FUNC) Selector - continued • Keypad Light Brightness The keypad light brightness setting is used to adjust the brightness of all legends on the display face. When the display is setup in the manual mode, press the FUNC selector until the keypad function is selected.
  • Page 354 SECTION 9 SUPPLEMENT 22 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) Test Mode Press the TEST button to start the test mode. The text “TEST” will be displayed in the bottom right corner of the display for approximately 15 seconds.
  • Page 355 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: LINDA J. DICKEN DOA-510620-CE THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: FEBRUARY 14, 2006 ISSUED: JULY 12, 1995 REPORT: VB-1611...
  • Page 356 SECTION 9 SUPPLEMENT 23 PA-28-181, ARCHER III SECTION 1 - GENERAL This airplane is equipped with the Avidyne FlightMax Entegra EXP5000 series 700-00006-0XX-( ) Primary Flight Display with software to the latest revision per Avidyne website and EX5000 series 700-00004-0XX-( ) Multi-Function Display with software to the latest revision per Avidyne website, herein referred to as the “PFD”...
  • Page 357 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 23 SECTION 1 - GENERAL (continued) The MFD is intended to be a supplemental display of situational and navigation information to the pilot. Its primary function is to provide a moving map display to the pilot for increased situational awareness. The MFD is capable of accepting...
  • Page 358 SECTION 9 SUPPLEMENT 23 PA-28-181, ARCHER III SECTION 1 - GENERAL (continued) A B&C Specialties, BC410 standby alternator, when ON, will automatically activate in the event of a failure in the primary alternator, therefore replacing the primary alternator function, but not supplementing its output. The alternator is gear driven through the engine vacuum pump drive pad.
  • Page 359 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 23 SECTION 2 - LIMITATIONS A. PFD Limitations 1. IFR flight is prohibited when the PFD or any standby instrument is inoperative (altimeter, airspeed indicator, artificial horizon, or whiskey compass). 2. IFR flight is prohibited upon aircraft total loss of essential engine parameter display (manifold pressure, tachometer, fuel flow).
  • Page 360 SECTION 9 SUPPLEMENT 23 PA-28-181, ARCHER III SECTION 2 - LIMITATIONS (continued) B. MFD Limitations (continued) 4. Aircraft dispatch is prohibited when the MFD is inoperative. 5. Selecting “Lightning Display OFF” for the Lightning overlay of the Map page will prevent current heading values from being sent to the WX500 sensor from the EX5000.
  • Page 361 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 23 SECTION 2 - LIMITATIONS (continued) C. CMAX CHART PAGE Limitations The geographic referenced aircraft symbol must not be used for navigation. NOTE The aircraft symbol displayed provides supplemental aircraft situational awareness information. It is not intended as a means for navigation or flight guidance.
  • Page 362 SECTION 9 SUPPLEMENT 23 PA-28-181, ARCHER III SECTION 3 - EMERGENCY PROCEDURES Failure of Pilot’s Electronic Attitude Direction Display Screen (PFD) Indication: PFD Display goes blank. Standby Attitude Gyro ..............VERIFY ON and flag is pulled on gyro Maintain attitude control using standby gyro and establish the aircraft in straight and level unaccelerated flight.
  • Page 363 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 23 SECTION 3 - EMERGENCY PROCEDURES (continued) Loss of PFD Engine Data Indication: Indicator needle removed from dial and digital readout replaced with white dashes. Engine Instruments..........Refer to Engine page of MFD Land as soon as practical.
  • Page 364 SECTION 9 SUPPLEMENT 23 PA-28-181, ARCHER III SECTION 3 - EMERGENCY PROCEDURES (continued) Invalid Attitude and Heading Data Indication: Attitude and Heading Data removed and replaced with Red X’s. Standby Attitude Gyro ..............VERIFY ON and flag is pulled on gyro.
  • Page 365 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 23 SECTION 3 - EMERGENCY PROCEDURES (continued) Failure of Attitude, Airspeed and Heading Reference System (ADAHRS) Indication: Airspeed, Attitude, Heading and Altitude replaced with Red X’s. Standby Attitude Gyro ..............VERIFY ON and flag is pulled on gyro Maintain attitude control using standby gyro.
  • Page 366 SECTION 9 SUPPLEMENT 23 PA-28-181, ARCHER III SECTION 3 - EMERGENCY PROCEDURES (continued) Cross Check Monitor Indication: Yellow Crosscheck Attitude Annunciator on PFD. Establish aircraft in straight and level unaccelerated flight. Aircraft Attitude ............Crosscheck aircraft attitude with standby attitude gyro...
  • Page 367 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 23 SECTION 3 - EMERGENCY PROCEDURES (continued) ALTERNATOR FAILURE Failure of Primary Alternator Indication: Alternator Inop annunciator light illuminated and Standby Alternator ON annunciator light illuminated or zero current displayed on MFD alternator indication source.
  • Page 368 SECTION 9 SUPPLEMENT 23 PA-28-181, ARCHER III SECTION 3 - EMERGENCY PROCEDURES (continued) ALTERNATOR FAILURE (continued) Failure of Standby Alternator If STBY ALTR ON is not illuminated: STBY ALTR ....................OFF STBY ALTR FIELD circuit breaker......check and reset as required STBY ALTR SENSE circuit breaker ......check and reset as required STBY ALTR ....................ON...
  • Page 369 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 23 SECTION 3 - EMERGENCY PROCEDURES (continued) ALTERNATOR FAILURE (continued) Reduce electrical loads by switching OFF or pulling circuit breakers for all non-essential equipment to include the following: • Reduce PFD and MFD brightness as part of overall electrical system management •...
  • Page 370 SECTION 9 SUPPLEMENT 23 PA-28-181, ARCHER III SECTION 3 - EMERGENCY PROCEDURES (continued) Electrical Overload (Alternator over 20 amps above known electrical load) ALTR........................ON BATT MASTR ....................OFF If alternator loads are reduced: Electrical load ................reduce to minimum NOTE Due to increased system voltage and radio frequency noise,...
  • Page 371 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 23 SECTION 3 - EMERGENCY PROCEDURES (continued) Reduce electrical loads by switching OFF or pulling circuit breakers for all non-essential equipment to include the following: • Reduce PFD and MFD brightness as part of overall electrical system management •...
  • Page 372 SECTION 9 SUPPLEMENT 23 PA-28-181, ARCHER III SECTION 3 - EMERGENCY PROCEDURES (continued) Complete Electrical Failure Standby Attitude Gyro ......SELECT Standby (STBY) power button CAUTION The STBY PWR annunciator will rapidly flash for approximately one minute when aircraft power is lost.
  • Page 373 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 23 SECTION 3 - EMERGENCY PROCEDURES (continued) Fire in Flight Electrical Fire Fire......................Extinguish Battery Master Switch ..................OFF ALTR Switch....................OFF STBY ALTR Switch ..................OFF Standby Attitude Gyro ......SELECT Standby (STBY) power button CAUTION The STBY PWR annunciator will rapidly flash for approximately one minute when aircraft power is lost.

  • Page 374: Throttle

    SECTION 9 SUPPLEMENT 23 PA-28-181, ARCHER III SECTION 3 - EMERGENCY PROCEDURES (continued) Aircraft Engine Power Loss During an engine failure the pilot may elect to attempt an engine restart. During this time large voltage drops may cause the PFD to lose power and reinitialize.
  • Page 375 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 23 Loss of Heading Accuracy Indication: • Difficulty maintaining course while using VOR or GPS. • Excessive difference between heading and track required maintaining a VOR or GPS course. • ATC indicates the aircraft is on a wrong heading.
  • Page 376 SECTION 9 SUPPLEMENT 23 PA-28-181, ARCHER III SECTION 4 - NORMAL PROCEDURES Engine Start - General CAUTION Do not attempt flight if there is no indication of primary alternator output. CAUTION If a positive oil pressure is not indicated within 30 seconds following an engine start, stop the engine and determine the trouble.

  • Page 377: Primary Flight Display (Pfd)

    SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 23 SECTION 4 - NORMAL PROCEDURES (continued) Normal Start - Cold Engine Throttle ....................¼ inch open Battery Master Switch..................ON Primary Flight Display (PFD) ..........Verify correct aircraft model software Alternator Switch ....................ON Standby Alternator Switch ................ON Electric Fuel Pump ..................ON...
  • Page 378 SECTION 9 SUPPLEMENT 23 PA-28-181, ARCHER III SECTION 4 - NORMAL PROCEDURES (continued) Engine Start When Flooded Throttle ....................Open full Battery Master Switch..................ON Primary Flight Display (PFD) ..........Verify correct aircraft model software Alternator Switch ....................ON Standby Alternator Switch ................ON Electric Fuel Pump ..................OFF Left Magneto Switch..................ON...
  • Page 379 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 23 SECTION 4 - NORMAL PROCEDURES (continued) 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.
  • Page 380 SECTION 9 SUPPLEMENT 23 PA-28-181, ARCHER III SECTION 4 - NORMAL PROCEDURES (continued) Ground Check Throttle................maximum power/RPM ALTR switch ....................OFF STBY ALTR ON annunciator ..............verify ON Increase electrical load to over 20 amps. STBY ALTR ON annunciator ............verify flashing Decrease electrical load to less than 20 amps.
  • Page 381 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 23 SECTION 7 - DESCRIPTION AND OPERATION A. PFD Systems Description NOTE This supplement provides a general description of the Avidyne FlightMax Entegra Series 700-00006-0XX-( ) PFD, its operation, and aircraft systems interfaces. For a detailed description of PFD operation, refer to the Avidyne FlightMax Entegra Series Primary Flight Display Pilot’s...
  • Page 382 SECTION 9 SUPPLEMENT 23 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) A. PFD Systems Description (continued) Horizontal Situation Indicator (HSI) Heading Data Magnetic heading is represented in a boxed digital form at the top of the compass rose. Heading rate (Rate of Turn Indicator) takes the form of a blue arcing arrow that begins behind the magnetic heading indicator and moves left or right accordingly.
  • Page 383 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 23 SECTION 7 - DESCRIPTION AND OPERATION (continued) A. PFD Systems Description (continued) Autopilot Integration The Entegra PFD is fully integrated with the S-TEC System 55X Autopilot. Reference bugs for Heading, Altitude, and Vertical Speed are provided on the PFD to control the autopilot and aid pilot situational awareness.
  • Page 384 SECTION 9 SUPPLEMENT 23 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) A. PFD Systems Description (continued) Autopilot Integration (continued) The following autopilot modes are supported by the PFD: 1. HDG (Heading, using the heading bug) 2. NAV (Nav, using the course pointer and course deviation indicator) 3.
  • Page 385 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 23 SECTION 7 - DESCRIPTION AND OPERATION (continued) A. PFD Systems Description (continued) Back-up Instruments The Entegra PFD system installation includes redundant means of display of certain aircraft flight and systems parameters. Back-up Altimeter, Airspeed and Attitude instruments are provided to facilitate pilot cross-checking of PFD display flight parameters.
  • Page 386 SECTION 9 SUPPLEMENT 23 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) B. MFD Systems Description NOTE This supplement provides a general description of the Avidyne EX5000 Series 700-00004-0XX-( ) MFD, its operation and aircraft interface. For a detailed description of the MFD, refer to the Avidyne FlightMax EX5000 Series Pilot’s Guide and Reference, p/n 600-00105-000 revision 00...
  • Page 387 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 23 SECTION 7 - DESCRIPTION AND OPERATION (continued) B. MFD Systems Description (continued) Navigation (continued) Using the Jeppesen NavData data and the GPS-supplied present position, the MFD can provide the pilot with the nearest 25 airports or navaids, depending on pilot selection, within 100 nm.
  • Page 388 SECTION 9 SUPPLEMENT 23 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) B. MFD Systems Description (continued) Setup (continued) Airport Settings page provides selections for displaying airport type, runway surface type and minimum runway lengths on the moving map. Declutter Settings page allows the pilot to select settings for defining the base map detail when changing display range.
  • Page 389 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 23 SECTION 7 - DESCRIPTION AND OPERATION (continued) C. STANDBY ALTERNATOR System Description The B&C Specialty Products Standby Alternator system automatically delivers electrical power to the aircraft electrical power bus in the event of failure of the primary alternator, provided the STBY ALTR switch is in the ON position.
  • Page 390 SECTION 9 SUPPLEMENT 23 PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 9-188, 36 of 36 REVISED: FEBRUARY 14, 2006...
  • Page 391 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 24 PILOT’S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 24 BENDIX/KING KR-87 DIGITAL ADF WITH KI-227 INDICATOR This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when the Bendix/King KR-87 Digital ADF with the KI-227 Indicator is installed per the Equipment List.
  • Page 392 SECTION 9 SUPPLEMENT 24 PA-28-181, ARCHER III SECTION 1 - GENERAL The Bendix/King Digital ADF is a panel mounted, digitally tuned, automatic direction finder. It is designed to provide continuous 1 kHz digital tuning in the frequency range of 200 kHz to 1799 kHz and eliminates the need for mechanical band switching.
  • Page 393 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 24 SECTION 4 - NORMAL PROCEDURES To Operate as an Automatic Direction Finder: 1. OFF/VOL Control - ON. 2. Frequency Selector Knobs - SELECT desired frequency in the standby frequency display. 3. FRQ Button - PRESS to move the desired frequency from the standby to the active position.
  • Page 394 SECTION 9 SUPPLEMENT 24 PA-28-181, ARCHER III SECTION 4 - NORMAL PROCEDURES (continued) NOTE The Standby Frequency which is in memory while Flight Time or Elapsed Time modes are being displayed may be called back by pressing the FRQ button, then transferred to active use by pressing the FRQ button again.
  • Page 395 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 24 SECTION 4 - NORMAL PROCEDURES (continued) ADF Operation NOTES: Erroneous ADF Bearing Due to Radio Frequency Phenomena: In the U.S., the FCC, which assigns AM radio frequencies, occasionally will assign the same frequency to more than one station in an area. Certain conditions, such as Night Effect, may cause signals from such stations to overlap.
  • Page 396 SECTION 9 SUPPLEMENT 24 PA-28-181, ARCHER III SECTION 5 - PERFORMANCE No change. SECTION 6 - WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance data in Section 6 of the Pilot’s Operating Handbook and Airplane Flight Manual.
  • Page 397 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 24 SECTION 7 - DESCRIPTION AND OPERATION KR-87 Digital ADF KI-227 Indicator King Digital ADF Operating Controls and Indicators Figure 1 ISSUED: JULY 12, 1995 REPORT: VB-1611 Page 7 of 10 • REVISED: OCTOBER 15, 2008...
  • Page 398 SECTION 9 SUPPLEMENT 24 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) Legend - Figure 1 1. Mode Annunciation - Antenna (ANT) is selected by the “out” position of the ADF button. This mode improves the aural reception and is usually used for station identification.
  • Page 399 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 24 SECTION 7 - DESCRIPTION AND OPERATION (continued) Legend - Figure 1 (continued) 6. Timer Mode Annunciation - Either the elapsed time (ET) or flight time (FLT) mode is annunciated here. 7. Frequency Selector Knobs - Selects the standby frequency when FRO is displayed and directly selects the active frequency whenever either of the timer functions is selected.
  • Page 400 SECTION 9 SUPPLEMENT 24 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) Legend - Figure 1 (continued) 15. Pointer - Indicates station bearing in degrees of azimuth, relative to the nose of the aircraft. When heading control is adjusted, indicates relative, magnetic, or true bearing of radio signal.
  • Page 401 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 25 PILOT’S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 25 BENDIX/KING KN-63 DME This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when the Bendix/King KN-63 DME is installed per the Equipment List.
  • Page 402 SECTION 9 SUPPLEMENT 25 PA-28-181, ARCHER III SECTION 1 - GENERAL The Bendix/King KN-63 DME supplies continuous slant range distance information from a fixed ground station to an aircraft in flight. The equipment consists of a KDI-572 Panel Display which contains all the operating controls and displays, and a remotely mounted KN-63 Receiver- Transmitter.
  • Page 403 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 25 SECTION 7 - DESCRIPTION AND OPERATION Bendix/King KN-63 DME Figure 1 Legend - Figure 1 1. DISTANCE DISPLAY (NM) - DME distance to VORTAC/WAYPOINT displayed in .1 nautical mile increments up to 99.9 NM, then in increments of one nautical mile to 389 NM.
  • Page 404 SECTION 9 SUPPLEMENT 25 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) Legend - Figure 1 (continued) 6. DME MODE SELECTOR SWITCH (OFF, N1, HLD, N2) - Applies power to the DME and selects DME operating mode as follows: OFF: Turns DME power off.
  • Page 405 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 26 PILOT'S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 26 GARMIN G500 PRIMARY FLIGHT AND MULTIFUNCTION DISPLAY SYSTEM The FAA approved operational supplement for the Garmin G500 PFD/MFD System, installed in accordance with STC SA02015SE-D, is required for operation of this system.
  • Page 406 SECTION 9 SUPPLEMENT 26 PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 9-204 REVISED: FEBRUARY 5, 2010...
  • Page 407 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 27 PILOT'S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 27 GARMIN GNS 430W VHF COMMUNICATION TRANSCEIVER/VOR/ILS RECEIVER/GPS RECEIVER This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when the Garmin GNS 430W VHF Communication Transceiver/VOR/ILS Receiver/Global Positioning System is installed per the Equipment List.
  • Page 408 SECTION 9 SUPPLEMENT 27 PA-28-181, ARCHER III SECTION 1 – GENERAL The GNS430W System is a fully integrated, panel mounted instrument, which contains a VHF Communications Transceiver, a VOR/ILS receiver, and a WAAS–enabled Global Positioning System (GPS) Navigation computer. The...
  • Page 409 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 27 SECTION 1 - GENERAL (continued) Class II Oceanic, Remote, and other operations The Garmin 430W has been found to comply with the requirements for GPS primary means of Class II navigation in oceanic and remote airspace when used in conjunction with Garmin Prediction Program part number 006-A0154- 03.
  • Page 410 SECTION 9 SUPPLEMENT 27 PA-28-181, ARCHER III SECTION 2 – LIMITATIONS Pilot’s Guide The Garmin 400W Series Pilot’s Guide, part number and revision listed below (or later revisions), must be immediately available for the flight crew whenever navigation is predicated on the use of the GNS430W unit.
  • Page 411 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 27 SECTION 2 - LIMITATIONS (continued) Navigation Data Base (continued) • GPS instrument approaches using the GNS430W are prohibited, unless the GNS430W’s approach data is verified by the pilot or crew to be current.
  • Page 412 SECTION 9 SUPPLEMENT 27 PA-28-181, ARCHER III SECTION 2 - LIMITATIONS (continued) Terrain Data Base The GNS430W supports Terrain and requires a Terrain database card to be installed in order for the feature to operate. The table below lists compatible database cards for the GNS430W.
  • Page 413 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 27 SECTION 2 - LIMITATIONS (continued) Approaches • During GPS approaches, the pilot must verify the GNS430W unit is operating in the approach mode. (LNAV, LNAV+V, L/VNAV, or LPV.) • When conducting approaches referenced to true North, the heading selection on the AUX pages must be adjusted to TRUE.
  • Page 414 SECTION 9 SUPPLEMENT 27 PA-28-181, ARCHER III SECTION 3 - EMERGENCY PROCEDURES Emergency Procedures No change. Abnormal Procedures • If the Garmin GNS430W GPS navigation information is not available, or is invalid, utilize other remaining operational navigation equipment installed in the airplane as appropriate. If the 430W loses GPS position and reverts to Dead Reckoning mode (indicated by the annunciation of “DR”...
  • Page 415 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 27 SECTION 4 - NORMAL PROCEDURES Refer to the 400W Series unit Pilot’s Guide defined in Section 2 - Limitations of this supplement for normal operating procedures. This includes all GPS operations, VHF COM and NAV, and Multi-Function Display (optional) information.
  • Page 416 SECTION 9 SUPPLEMENT 27 PA-28-181, ARCHER III SECTION 4 - NORMAL PROCEDURES (continued) Autopilot Operation The Garmin GNS430W may be coupled to the STEC 55X Autopilot when operating as prescribed in the LIMITATIONS section of this supplement. For lateral guidance, the STEC 55X Autopilot may utilize GPSS or GPS Roll Steering in lieu of the analog deviation information.
  • Page 417 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 27 SECTION 4 - NORMAL PROCEDURES (continued) WFDE Prediction Program The Garmin WAAS Fault Detection and Exclusion (WFDE) Prediction Program is required for Remote/Oceanic operations. The Prediction Program should be used in conjunction with the Garmin 400W/500W Simulator.
  • Page 418 SECTION 9 SUPPLEMENT 27 PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 ISSUED: JULY 12, 1995 • Page 12 of 12 REVISED: JULY 29, 2010 9-216...
  • Page 419 TABLE OF CONTENTS SECTION 10 OPERATING TIPS Paragraph Page 10.1 General ..................10-1 10.3 Operating Tips ................10-1 REPORT: VB-1611 10-i...
  • Page 420 THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1611 10-ii...
  • Page 421 SECTION 10 PA-28-181, ARCHER III OPERATING TIPS SECTION 10 OPERATING TIPS 10.1 GENERAL This section provides operating tips of particular value in the operation of Archer III. 10.3 OPERATING TIPS (a) Learn to trim for takeoff so that only a very light back pressure on the control wheel is required to lift the airplane off the ground.
  • Page 422 SECTION 10 OPERATING TIPS PA-28-181, ARCHER III (g) The rudder pedals are suspended from a torque tube which extends across the fuselage. The pilot should become familiar with the proper positioning of his feet on the rudder pedals so as to avoid interference with the torque tube when moving the rudder pedals or operating the toe brakes.

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