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

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ATRPLANE
SElUAL NO.
DATE OF APPROVAL:
DECEMBER 22, 2017
FAA APPROVED 1N 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 ANDMUST BECARRlEDLN THE AIRPLANE AT ALL TIMES .
•
THIS FLIGHT MANUAL
APPROVED.
VALID FOR THE AFM/POH VB-2749.
ARCHER Ill
AIRPLANE FLIGHT MANUAL
_
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2
8_8_1
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5
5
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__
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IS EASA
THIS
APPROVAL
IS
PA-28-181
SN 2843823, 2881001 AND UP
With Garmin G1000 System
OPERATING
HANDBOOK
FAA APPROVED
AIR PLANE
_ _
RE GI ST .
N O.
ERIC
O.D.A. 510
PTPER AfRCRAFT, INC.
VERO BEACH, FLORIDA
P
.�A..
1per
PILOT'S
AND
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F
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2
3
2
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  • Page 1 ARCHER Ill • PA-28-181 SN 2843823, 2881001 AND UP With Garmin G1000 System PILOT'S OPERATING HANDBOOK FAA APPROVED • AIRPLANE FLIGHT MANUAL ATRPLANE AIR PLANE 8_8_1 RE GI ST . N O. SElUAL NO. ERIC O.D.A. 510 DATE OF APPROVAL: PTPER AfRCRAFT, INC.
  • Page 2 • • • Published by TECHNICAL PUBLICATIONS Piper Aircraft, Inc. Issued: December 22, 2017 Aircraft, © 2017-2021 Piper loc. ghis All Ri Reserved ISSUEU: Uecember 22, 2017 REPORT: VB-2749 REVISED: March 9, 2021...
  • Page 3 PA-28-181, ARCHER ill • 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 PA-28-181, ARCHER ill 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 certified by the manufacturer and thereafter must be maintained by the owner.
  • Page 5 PA-28-181, ARCHER ill PILOT'S OPERA TING HANDBOOK LOG OF REVISIONS • Current Revisions to the PA-28-181 ARCHER ill Pilot's Operating Handbook, REPORT: VB-2749 issued December 22, 2017 . FAA Approval Revision Description of Revisions Signature and Number and Revised Date Code Pages Rev.
  • Page 6 PA-28-181, ARCHER ill • PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (continued) FAA Approval Revision Signature and Number and Revised Description of Revisions Date Code Pages 2-I2a, Added pages for Para. 2.25. Rev. 2 (cont.) 2-l2b 2-13 Revised Para. 2.25. 3-32 Revised Para.
  • Page 7 PA-28-181, ARCHER ill • PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (continued) FAA Approval Revision Description of Revisions Signature and Number and Revised Code Pages Date Rev. 4 Revised Para. 5.5a. (cont.) Revised Para. 5.5e. Revised Para. 7.7. Revised Para. 7.15. 7-9,-10 Revised Para.
  • Page 8 PA-28-181, ARCHER ill • PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (continued) FAA Approval Revision Revised Description of Revisions Signature and Number and Code Pages Date Rev. 6 2-11 Revised Para. 2.25. (cont.) 2-14 -15 Revised Para. 2.29. 3-18 Revised Para. 3.5d. 4-23 Revised Para.
  • Page 9 PA-28-181, ARCHER Ill • PILOT'S OPERA TING HANDBOOK LOG OF REVISIONS (continued) Revision FAA Approval Number and Revised Description of Revisions Signature and Code Pages Date Rev. 8 Revised EASA approval. (PR210309) Updated copyright. vi-c vi-d Added pages to L of R. Added Rev.
  • Page 10 PA-28-181, ARCHER ill • • THIS PAGE INTENTIONALLY LEFT BLANK • REPORT: VB-2749 ISSUED: December 22, 2017 vi-d REVISED: March 9, 2021...
  • Page 11 PA-28-181, ARCHER ill • TABLE OF CONTENTS GENERAL SECTION 1 SECTION 2 LIMITATIONS SECTION 3 EMERGENCY PROCEDURES SECTION 4 NORMAL PROCEDURES SECTION 5 PERFORMANCE WEIGHT AND BALANCE SECTION 6 • SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS SECTION 8 AIRPLANE HANDLING, SERVICING AND MAINTENANCE...
  • Page 12 PA-28-181, ARCHER III • • THIS PAGE INTENTIONALLY LEFT BLANK • ISSUED: December 22, 2017 REPORT: VB-2749 viii...
  • Page 13 SECTION 1 GENERAL PA-28-181, ARCHER ill • TABLE OF CONTENTS SECTION 1 GENERAL Page Paragraph �. �. introduc t ion ................Notations..................Engine..................Propeller..................Fuel 1.11 • 1.13 Max._imum Weights ..............
  • Page 14 SECTION 1 PA-28-181, ARCHER ill GENERAL • • THIS PAGE INTENTIONALLY LEFT BLANK • ISSUED: December 22, 2017 REPORT: VB-2749 I-ii...
  • Page 15 SECTION 1 PA-28-181, ARCHER ill GENERAL • SECTION 1 GENERAL 1.1 INTRODUCTION This Pilot's Operating Handbook is designed for maximum uliljzation 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 16 SECTION 1 GENERAL PA-28-181, ARCHER ill • • THIS PAGE INTENTIONALLY LEFT BLANK • ISSUED: December 22, 2017 REPORT: VB-2749...
  • Page 17 SECTION 1 GENERAL PA-28-181, ARCHER Ill • NOTATIONS \VARNING Operating procedures or techniques which may result in personal injury or loss of life if not carefully followed or a hazard which may require immediate crew recognition and corrective action. CAUTION Operating procedures or techniques which may result in damage to eq1,ipment if not carefully followed or the need for immediate crew awareness and possible need for future...
  • Page 18 SECTION 1 GENERAL PA-28-181, ARCHER ill • 14----12' 10.48'' '-- ---..i 3' 6.2" 0\ / • Min turning radius 30 (ft) (from pivot point to wing tip) 14----------- 35'8'' '-- ---------� • THREE VIEW Figure 1-1 ISSUED: December 22, 2017 REPORT: VB-2749...
  • Page 19 SECTION 1 GENERAL PA-28-181, ARCHER ill • 1.5 ENGINE (a) Number of Engines Lycoming Engine Manufacturer (c) Engine Model Number IO-360-B4A (I) Fuel Injected (d) Takeoff Power (BHP) (e) Takeoff Power Engine 2700 Speed (RPM) 5.125 (f) Bore (inches) 4.375 Stroke (inches) 361.0 Displacement (cubic inches)
  • Page 20 SECTION l GENERAL PA-28-181, ARCHER ill • 1.11 OIL (a) Oil Capacity (U.S. quarts) Refer to latest revision (b) Oil Specification of Lycoming Service Instruction 1014. (c) Oil Viscosity per Average Ambient Refer to latest revision Temperature for Starting of Lycoming Service Instruction 1014.
  • Page 21 SECTION 1 PA-28-181, ARCHER III GENERAL • 1.17 BAGGAGE SPACE (a) Compartment Volume (cubic feet) (b) Entry Width (inches) (c) Entry Height (inches) 1.19 SPECIFIC LOADINGS ft.) Wing Loading (lbs. per sq. 15.0 (lbs. Power Loading 14.2 1.21 G 1000 GNSS (GPS/SBAS) NAVIGATION SYSTEM EQUIPMENT...
  • Page 22 SECTION 1 PA-28-181, ARCHER III GENERAL • 1.21 GlOO0 GNSS (GPS/SBAS) NAVIGATION SYSTEM EQUIPMENT APPROVALS (continued) ICAO Flight Notes Operational Reference Navigation Plan Code Requirements/ Documents Specification Authorizations Item I 8 Item IOa PBN/ Code FAA AC The GPS equipment...
  • Page 23 SECTION 1 PA-28-181, ARCHER ID GENERAL • 1.21 GNSS (GPS/SBAS) NAVIGATION SYSTEM EQUIPMENT GlOOO APPROVALS (continued) Navigation Operational Reference ICAO Flight Notes Specification Requirements/ Documents Plan Code Authorizations Item I0a Item 18 Code PBN/ RNP4 FAA AC The GPS cquipmeni GNSS FDE/RAIM Oceanic and availability must be...
  • Page 24 SECTION I PA-28-181, ARCHER III GENERAL • 1.21 GlO00 GNSS (GPS/SBAS) NAVIGATION SYSTEM EQUIPMENT APPROVALS (continued) Notes Operational Reference !CAO Flight Navigation Requirements/ Documents Plan Code Specification Authorizations Item I0a Item 18 PBN/ Code Includes RNAV Q and T FAA AC...
  • Page 25 SECTION 1 GENERAL PA-28-181, ARCHER ID • 1.21 GlOOO GNSS (GPS/SBAS) NAVIGATION SYSTEM EQUIPMENT APPROVALS (continued) Navigation Operational Reference !CAO Flight Notes Requirements/ Specification Documents Plan Code Authorizations Item I0a Item 18 Code PBN/ RNAV I Must have GNSS/ FAA AC Includes RN AV terminal SSAS capability 20-1380.
  • Page 26 SECTION 1 PA-28-181, ARCHER ill GENERAL • 1.21 GIOOO GNSS (GPS/SBAS) NAVIGATION SYSTEM EQUIPMENT APPROVALS (continued) !CAO Flight Notes Operational Reference Navigation Plan Code Requirements/ Documents Specification Authorizations Item IOa Item 18 Code PBN/ !CAO night plan code FAA AC P-RNAY GNSS receiver is 20-1380.
  • Page 27 SECTION 1 GENERAL PA-28-181, ARCHER Ill • 1.21 GlOOO GNSS (GPS/SBAS) NAVIGATION SYSTEM EQUIPMENT APPROVALS (continued) Notes Reference ICAO Flight Navigation Operational Documents Plan Code S peci ficati on Requirements/ Authorizations Item I0a Item 18 Code PBN/ (cont.) (continued) Pa. rt 91 subpart K. ( continued) (cont.) RNP I...
  • Page 28 SECTION 1 PA-28-181, ARCHER ill GENERAL • 1.21 GlOO-O GNSS (GPS/SBAS) NAVIGATION SYSTEM EQUIPMENT APPROVALS (continued) Reference JCAO Flight Notes Navigation Operational Specification Requirements/ Documents Plan Code Authorizations ILem IOa Item Code PBN/ RNP APCH Procedures containing FAA AC Includes area navigation Radius-co-Fix (RF) LNAV/ 20-1380.
  • Page 29 SECTION 1 GENERAL PA-28-181, ARCHER ill • 1.21 GlOOO GNSS (GPS/SBAS) NAVIGATION SYSTEM EQUIPMENT APPROVALS (continued) Notes Navigation Operational Reference ICAO Flight Requirements/ Documents Plan Code Specification Authorizations Item J0a Item 18 PBN/ Code Includes area navigation RNPAPCH Procedures concaining FAA AC approaches titled LP minima...
  • Page 30 SECTION 1 GENERAL PA-28-181, ARCHER III • 1.21 GlOO0 GNSS (GPS/SBAS) NAVIGATION SYSTEM EQUIPMENT APPROVALS (continued) Navigation Operational Reference ICAO Flight Notes Specification Requirements/ Documents Plan Code Authorizations Item IOa Item Code PBN/ RNP APCH Procedures containing FAA AC Includes area navigation...
  • Page 31 SECTION I GENERAL PA-28-181, ARCHER ill • 1.21 G 1000 GNSS (GPS/SBAS) NAVIGATION SYSTEM EQUIPMENT APPROVALS (continued) Notes ICAO Flight Navigation Operational Reference Plan Code Documents Specification Requirements/ Authorizations Item I0a Item 18 Code PBN/ B�A V Hglding: This does not FAA AC Advanced Supported.
  • Page 32 SECTION 1 GENERAL PA-28-181, ARCHER III • 1.21 GlOOO GNSS (GPS/SBAS) NAVIGATION SYSTEM EQUIPMENT APPROVALS (continued) I. FDE/RAIM availability worldwide can be determined via Lhe following: • Using the Garmin RAJM/Fault Detection and Exclusion Prediction Tool available on the Garmin website lly.garmin.com.
  • Page 33 SECTION 1 GENERAL PA-28-181, ARCHER ill • 1.23 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY The following definitions are of symbols, abbreviations and terminology used throughout the handbook and those which may be of added operational significance to the pilot. (a) General Airspeed Terminology and Symbols Calibrated Airspeed means the indicated speed of an aircraft, corrected for position and instrument error.
  • Page 34 SECTION 1 GENERAL PA-28-181, ARCHER 1.23 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (continued) Never Exceed Speed or Mach Number is the • VNE/MNE speed limit that may not be exceeded al any time. Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution.
  • Page 35 SECTION 1 GENERAL PA-28-181, ARCHER ID • 1.23 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (continued) The n u m b e r a c t u a l l y read f r o m an Indicated Pressure Altitude altimeter when the barometric subscale has been set to 29.92 inches of mercury (1013.2 millibars).
  • Page 36 SECTION 1 GENERAL PA-28-181, ARCHER III • 1.23 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (continued) Avionics System Abbreviations/Terminology Refers to pilot's side (ADAHRS Refers to co-pilot's side (ADAHRS2, ADC2, GPS2) Air Data, Attitude and Heading Reference System ADAHRS Automatic Flight Control System...
  • Page 37 SECTION 1 PA-28-181, ARCHER ill GENERAL • 1.23 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (continued) (f) Airplane Performance and Flight Planning Terminology Accelerate-Stop The distance required to accelerate an airplane to a specified speed and, assuming failure of Distance an engine at the instant that speed is attained, to bring the airplane to a stop.
  • Page 38 SECTION 1 GENERAL PA-28-181, ARCHER 1.23 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (continued) Datum An imaginary vertical plane from which all • horizontal distances are measured for balance purposes. St andard empty weight plus op tional Basic Empty equipment. Weight Maximum Maximum weight approved for the landing Landing Weight touchdown.

  • Page 39: Table Of Contents

    SECTION 2 LIMITATIONS PA-28-181, ARCHER ill • TABLE OF CONTENTS SECTION 2 LIMITATIONS Page Paragraph General ..................Airspeed Limitations ..............Airspeed Indicator Markings ............Powerplant Limitations ............. . Powerplant Instrument Markings ..........2- 4 Systems Limitations ..............2.11 •...
  • Page 40 SECTION 2 PA-28-181, ARCHER ill LIMIT A TIO NS • • THIS PAGE INTENTIONALLY LEFT BLANK • ISSUED: December 22, 2017 REPORT: VB-2749 2-ii...

  • Page 41: General

    SECTION2 PA- 2 8- 1 81, ARCHER ill LIMITATIONS • SECTION 2 LIMITATIONS 2.1 GENERAL This section provides the FAA Approved operating limitations, instrument markings, color coding and basic placards necessary for operation of the airplane and its systems. This airplane must be operated as a normal or utility category airplane in compliance with the operating limjtations stated in the form of placards and markings and those given in thjs section and trus complete handbook.

  • Page 42: Airspeed Indicator Markings

    SECTION 2 PA-28-181, ARCHER ill LIMITATIONS • 2.3 AIRSPEED LIMITATIONS (continued) CAUTION! Maneuvering speed decreases at lighter weight as the effects of aerodynamic forces become more pronounced. Linear interpolation may be used for intermediate gross weights. Maneuvering speed should not be exceeded while operating in rough air.

  • Page 43: Powerplant Limitations

    SECTION 2 LIMITATIONS PA-28-181, ARCHER ill • 2.7 POWERPLANT LIMITATIONS (a) Number of Engines Lycoming (b) Engine Manufacturer (c) Engine Model No. IO-360-B4A (1) Fuel Injected (d) Engine Operating Limits (I) Rated Horsepower (BHP) 2700 (2) Max. Propeller Speed (RPM) 24 5 °...

  • Page 44: Powerplant Instrument Markings

    SECTION 2 PA-28-181, ARCHER ill LIMIT A TIO NS • 2.9 POWERPLANT INSTRUMENT MARKINGS Tachometer 500 lo 2700 RPM Green Arc (Normal Operating Range) 2700RPM Red Line (Maximum) Oil Temperature ° ° to 245 Green Band (Normal Operating Range) ° Red Line (Maximum) Oil Pressure 55 PSI to 95 PSI...

  • Page 45: Center Of Gravity Limits

    SECTION 2 LIMITATIONS PA-28-181, ARCHER ill • 2.15 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 less) 82.0 93.0 (b) Utjlity Category Weight Forward Lirut Rearward Limit...

  • Page 46: Maneuver Linlits

    SECTION 2 LIMIT A TIO NS PA-28-181, ARCHER III 2.17 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...
  • Page 47 SECTION 2 LIMITATIONS PA-28-181, ARCHER Ill • 2.25 GARMIN GlOOO AVIONICS SYSTEM LIMITATIONS (a) Cockpit Reference & Pilot's Guide Garmin G l 000 Cockpit Reference Guide 190-02131-02 (latest appropriate revision) must be immediately available to the flight crew. Gannin also provides a detailed 01000 Pilot's Guide 190-02130-02 (latest appropriate revision).
  • Page 48 SECTION 2 LIMITATIONS PA-28-181, ARCHER ill • 2.25 GARMIN Gl0OO AVIONICS SYSTEM LIMITATIONS (continued) (c) Databases ( 1) Navigation Database GPS/SBAS based IFR enroute, oceanic and terminal navigation predicated upon the Garmin G 1000 GPS Receiver is prohibited unless the pilot uses a valid, compatible, and current Navigation database or verifies each selected waypoinl for accuracy by reference to current data.
  • Page 49 SECTION 2 PA-28-181, ARCHER ID LIMITATIONS • 2.25 GARMIN GI0OO AVIONICS SYSTEM LIMITATIONS (continued) (d) Flight Planning (continued) For operations within European B-RNA V /RNA V 5 and P-RNA V airspace, if more than one satellite is scheduled to be out of service, then the availability of RAIM/FDE shall be confirmed for the intended flight (route and time).
  • Page 50 SECT1ON2 PA-28-181, ARCHER ill LIMITATIONS • • THIS PAGE INTENTIONALLY LEFT BLANK • ISSUED: December 22, 2017 REPORT: VB-2749 2-8b REVISED: March 27, 2020...
  • Page 51 SECTION 2 LIMITATIONS PA-28-181, ARCHER ill • 2.25 GARMIN GlOOO AVIONICS SYSTEM LIMITATIONS (continued) (e) Enroute Whenever possible, RNP and RNA V routes including Standard Instrument Departures (SIDs) and Obstacle Departure Procedures (ODPs), Standard Terminal Arrival (STAR), and enroute RNA V "Q" and RNA V "T'' routes should be loaded into the flight plan from the database in their entirety, rather than loading route waypoints f om the database into the flight plan...
  • Page 52 SECTION2 PA-28-181, ARCHER ill LIMIT A TIO NS • 2.25 GARMIN G 1000 AVIONICS SYSTEM LIMITATIONS (continued) (f) Approaches (continued) Vertical Guidance (continued) IFR non-precision approach with vertical guidance approval using the GPS/SBAS sensor is limited to published approaches within the U.S. and EASA Airspace Systems.
  • Page 53 SECTION 2 LIMITATIONS PA-28-181, ARCHER UI • 2.25 GARMIN GIOOO AVIONICS SYSTEM LIM1TATIONS (continued) (g) Attitude and Heading Reference System (AHRS) ( I) AHRS Operational Area Operation in the following regions is not authorized due to unsuitability of the magnetic fields near the Earth's poles: °...
  • Page 54 SECTION 2 PA-28-181, ARCHER il l LIMITATIONS • 2.25 GARMlN GIOOO AVIONICS SYSTEM LIMITATIONS (continued) (i) Datalink Weather Display XM weather data is provided by an oplional GDL 69 interface. The weather information display on the MFD is linlited to supplemental use only and may not be used in lieu of an official weather data source.
  • Page 55 SECTION 2 LIMIT ATTONS PA-28-181, ARCHER Ill • 2.25 GARMIN G 1000 AVIONICS SYSTEM LIMIT ATlONS (continued) 0) ChartView, FliteCbarts, and SafeTaxi® (continued) For EASA aircrart (aircraft in compliance with EASA type design TCDS lM.A.234) no EFB airworthiness approval has been obtained. Geo-referenced data (airplane symbol) presented on moving maps and electronic approach charts must be used for situaLional awareness only.
  • Page 56 SECTION2 LIMITATIONS PA-28-181, ARCHER ill 2.25 GARMIN G l0OO AVIONlCS SYSTEM LIMITATIONS (continued) (m) Flight Stream 510 (For EASA aircraft only - aircraft in compliance with EASA type design TCDS IM.A.234) • (I) Da1a Received by Personal Electronic Devices (PED) The PED is not approved as the sole source of information to base tac1ical or strategic decision making and is not approved to replace the information provided by the GI 000 GIFD system.
  • Page 57 SECTION 2 PA-28-181, ARCHER ID LIMITATIONS • 2.25 GARMIN Gl0OO AVIONICS SYSTEM LIMITATIONS (continued) (n) Minimum fully functional equipment required for flight operations: Equipment Number Installed ( I) ADAHRS Magnetometer Standby Instrument - Attitude Standby Instrument - Airspeed Standby Instrument - Altimeter ( 3) Standby Instrument - Heading If the PFD is inoperative during DAY or NIGHT VFR, the MFD...

  • Page 58: Gfc 700 Automatic Flight Control System (Afcs)

    SECTION 2 PA-28-181, ARCHER LIMITATIONS 2.27 GFC 700 AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS) The autopilot must be disengaged during takeoff and landing. • Autopilot minimum engagement heights: 400 feet AGL during takeoff and subsequent climb operations. b. 1000 feel AGL during cruise and descent operations. 200 feet AGL during approach operations.

  • Page 59: Placards

    SECTION 2 LIMITATIONS PA-28-181, ARCHER • 2.29 STANDBY INSTRUMENT LIMITATIONS (continued) 2. Garmin GS Standby Instrument The GS must utilize the following or later FAA approved software versions: Software Version Component GS Standby Instrument 6.40 2.31 PLACARDS • In full view of the pilot: LIMITATIONS THIS AIRPLANE ..iST BE OPERATED AS A NORMAL OR UTILITY CATEGORY AIRPLANE IN COMPLIANCE 11TH THE OPERATING LIMITAT I O N S S TATED IN THE fORN Of PLACARDS.
  • Page 60 SECTION 2 LIMITATIONS PA-28-181, ARCHER III • 2.31 PLACARDS (continued) In fu II view of the pilot: �--------7 113 AT 2550 LBS 98 AT 1917 LBS DEM) X-WNl 17 KTS L __________ NOTE Demonstrated crosswind values are NOT limitations. On the cockpit overhead panel: •...
  • Page 61 SECTION 2 PA-28-181, ARCHER III LIMITATIONS 2.31 PLACARDS (continued) full view the pilot: • WARNING TURN OFF S TROB E LIGHTS WHE N IN CLOSE PROXIMITY G R OUN D O R DUR I N G F L I GHT THROUGH C LOUD, FOG OR HAZE.
  • Page 62 SECTION 2 LIMITATIONS PA-28-181, ARCHER III • 2.31 PLACARDS (continued) On the right side of Lbe fuselage aft of the wing: EXTERNAL POWER 28 VOLTS O.C. TURN MASTER SWITCH AND ALL EQUIP. OFF BEFORE INSERTING OR REMOVING PLUG Adjacent to the filler caps: AVGAS ONLY •...
  • Page 63 SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III • TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Page Paragraph 3- 1 General ..................Crew Alerting System (CAS) Messages ........PFD Annunciations and Alert s ........... Aural Alert s ................

  • Page 64: Paragraph Page

    SECTION3 EMERGENCY PROCEDURES PA-28-181, ARCHER III • TABLE OF CONTENTS (continued) SECTION 3 EMERGENCY PROCEDURES Paragraph Page 3.Se Avionics Failures (continued) ADA HRS Failures ..............3-25 Erroneous or Loss of Engine and Fuel Displays ....3-27 Erroneous or Loss of Warning/Caution CAS Messages ..

  • Page 66: General

    SECTION3 PA-28-181, ARCHER III EMERGENCY PROCEDURES • 3.1 GENERAL (continued) Crew Alerting System (CAS) Messages The following tables show the color and significance of the Warning, Caution and Advisory messages which may appear on the Garmin G l 000 displays.
  • Page 67 SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES • 3.1 GENERAL (continued) Crew Alerting System (CAS) Messages (continued) Warning Messages - Red Checklist CAS Event CAS Message Page Cause CAS Warnings with Text Messages Alternator is turned ON and has Alternator Failure...
  • Page 68 SECTION 3 PA-28-181, ARCHER Ill EMERGENCY PROCEDURES • 3.1 GENERAL (continued) Crew Alerting System (CAS) Messages (continued) Caution Messages - Amber • Checklist CAS Message Page Cause CAS Event CAS Cautions with Text Messages CO level greater than or equal 3-41 CO Level High COLVLHIGH...
  • Page 69 SECTION 3 PA-28-181, ARCHER Ill EMERGENCY PROCEDURES • 3.1 GENERAL (continued) Crew Alerting System (CAS) Messages (continued) Advisory l\lessages - \Vhite Checklist CAS Event Page Cause CAS Message CAS Advisories with Text Messages Avionics Fan Fail 3-31 One or more of the external AV FAN FAIL avionics cooling fans have failed.

  • Page 70: Pfd Annunciations And Alerts

    SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER • 3.1 GENERAL (continued) PFD Annunciations and Alerts The Garmin GI 000 System produces a number of PFD annunciations and alerls in addition to the Crew Alerting System (CAS). PFD annunciations and alerts are not accompanied by Master Warning or Master Caution Indications and are displayed in dedicated areas of the PFD or MFD.

  • Page 71: Aural Alerts

    SECTION 3 PA-28-181, ARCHER ill EMERGENCY PROCEDURES • 3.1 GENERAL (continued) PFD Annunciations and Alerts (continued) Aural Alerts Aural alerts are provided alert the crew and call for their attention: • Master Warning - Repeating triple chime. • Master Caution Non-repeating double chime.

  • Page 72: Fire

    SECTION 3 PA-28-181, ARCHER EMERGENCY PROCEDURES AIRSPEEDS FOR SAFE OPERATION • �5 f;�:: (0 Flaps) ..............50 K.IAS ° 2550 lbs (Full Flaps) .............. 45 KIAS Maximum Operating Maneuvering Speeds 2550 lbs ................. 113 KIAS 1917 lbs ................... 98 KlAS Never Exceed Speed ..............

  • Page 73: Engine Fire In Flight

    SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER ill • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Sa Fire (continued) Engine Fire in Flight FUEL Selector .., ................OFF THROTTLE ................CLOSED MIXTURE ..............IDLE CUT-OFF FUEL PUMP ..................OFF HEAT/DEF (Defroster) ..............lf fire persists: Airspeed ........

  • Page 74: Electrical Fire In Flight

    SECTION 3 ARCHER Ill El\l l ERGENCY PROCEDURES PA-28-181 • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Sa Fire (continued) Electrical Fire In Flight EMERG BATT Switch ............VERIFY ARM BA TT MASTR Switch ................ OFF AL TR Switch ..................OFF Vents ....................OPEN HEAT/DEP (Defroster) ..............

  • Page 75: Engine Power Loss

    SECTION3 PA-28-181, ARCHER III EMERGENCY PROCEDURES • EMERGENCY PROCEDURES CHECK LIST (continued) Engine Power Loss 3.5b Engine Power Loss During Takeoff If sufficient runway remains for a complete stop: Airspeed ........... MAINTAIN SAFE AIRSPEED Landing ........LAND and STOP STRAIGHT AHEAD Brakes ................

  • Page 76: Engine Power Loss In Flight

    SECTION 3 PA-28-181, ARCHER ill EMERGENCY PROCEDURES • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Sb Engine Power Loss (continued) Engine Power Loss In Flight Airspeed ..............MAINTAIN 76 KIAS FUEL Selector......... SWITCH to tank containing fuel FUEL PUMP ..................ON MIXTURE ..................

  • Page 77: Power Off Landing

    SECTION 3 E�1ERGENCY PROCEDURES PA-28-181, ARCHER ill • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Sb Engine Power Loss ( continued) Power Off Landing Airspeed ..............MAINTAIN 76 KIAS Ajr Conditioning (if installed) ............. OFF Landing Pattern ........ESTABLISH 1000 IT ABOVE FIELD AT DOWNWIND POSITION When committed to landing: Airspeed ..................

  • Page 78: Engine Indicating System (Eis)

    SECTION 3 PA-28-181, ARCHER ill EMERGENCY PROCEDURES • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Sc Engine Indicating System (EIS) Oil Pressure Indication: Master Warning, Triple Chime, Flashing Red Oil Pressure Indication Low Oil Pressure: THROTTLE ............MTNTMlJM REQlHRED If accompanied by high oil temperature, land as soon as possible. If accompanied by normal oil temperature, land as soon as practical.

  • Page 79: Oil Temperature

    SECTION3 PA-28-181, ARCHER ill EMERGENCY PROCEDURES • EMERGENCY PROCEDURES CHECK LIST (continued) 3.5c Engine Indicating System (EIS) (continued) Oil Temperature Indication: Master Warning, Triple Chime, Flashing Red Oil Temperature Indication THROTILE ......, ....... MINIMUM REQUIRED MIXTURE ................FULL RICH Airspeed ..............

  • Page 80: Loss Of Fuel Flow

    SECTION3 EMERGENCY PROCEDURES PA-28-181, ARCHER Ill • EMERGENCY PROCEDURES CHECK LIST (continued) 3.5c Engine Indicating System (EIS) (continued) Loss of Fuel Flow CAUTION If normal engine operation and fuel flow is not immediately re-established, or if the engine quits, the electric fuel pump should be turned off. The lack of fuel flow indication could indicate a leak in the fuel system, or fuel exhaustion.

  • Page 81: Fuel Quantity Low

    SECTION 3 PA-28-181, A RCHER III EMERGENCY PROCEDURES • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Sc Engine Indicating System (EIS) (continued) Fuel Quantity Low Indication: Master Warning, Triple Chime, LFUELQlY RFUELQTY \VARNING Avoid unusual attitudes such as prolonged slips towards the low quantity tank as this will decrease the time remaining prior to fuel starvation.

  • Page 82: Elect Rical Failures

    SECTION 3 PA-28-181, ARCHER ill EMERGENCY PROCEDURES • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Sd Electrical Failures NOfE The pilot should only reset a tripped circuit breaker if the system/component is considered essential for safety of flight. Prior to resetting the circuit breaker, wait at least one minute and verify there is no smoke or burning smell.
  • Page 83 SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER ill • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Sd Electrical Failures (continued) To ensure 30-minutes of battery life: Battery Discharge ............. - l3 Amps Maximum Pitot Heat............. 14 Minutes Usage Maximum Com Radio ............3 Mins Usage Maximum Fuel Pump ............

  • Page 84: Complet E Elect Rical Failure

    SECTION 3 PA-28-181, ARCHER ill EMERGENCY PROCEDURES • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Sd Electrical Failures (continued) Complete Electrical FaiJure Indication: Single Chime, EMERG BATT ON NOTE The VOLTS indication on the EIS window automatically changes to the emergency bus voltage (E VOLTS) when operating exclusively on the emergency bus.

  • Page 86: Pfd Failure

    SECTION 3 PA-28-181, ARCHER ID EMERGENCY PROCEDURES • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Se Avionics System Failures PFD Failure Indication: PFD display goes blank. Standby Instrument ..........Verify OPERATIONAL Aircraft Control............. Use Standby Instrument DISPLAY BACKUP button on audio panel ..
  • Page 87 SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Se Avionics System Failures (continued) Attitude, heading, airspeed and altitude indications are available on the standby instrument and on the MFD after the DlSPLA Y BACKUP button is pressed.

  • Page 88: Mfd Failure

    SECTION 3 PA-28-181, ARCHER ill EMERGENCY PROCEDURES • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Se Avionics System Failures (continued) MFD Failure Indication: MFD display goes blank. NoTE PFD should automatically rever110 the reversionary display. 111ut.lt: D lSPLA Y BACKUP on audio panel ....PUSH (button ex1ended) Exii and avoid /FR conditions as soon as practical.

  • Page 89: Adahrs Failures

    SECTION 3 PA-28-181, ARCHER ill EMERGENCY PROCEDURES • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Se Avionics System Failures (continued) ADAHRS Failures ADAHRS Total Failure On Ground: Sky/Ground presentation removed, course pointer Indication: straight up, yeUow-x's and amber text on all air data, attitude and heading indicators.
  • Page 90 SECTION 3 PA-28-181, ARCHER ill EMERGENCY PROCEDURES • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Se Avionics System Failures (continued) ADAHRS Failures (continued) ADAHRS Total Failure lo Flieht: Indication; Sky/Ground presentation removed, course pointer straight up, yellow-x's and amber text on all air data, attitude and heading indicators.

  • Page 91: Erroneous Or Loss Of Engine And Fuel Displays

    SECTION 3 PA-28-181, ARCHER ill EMERGENCY PROCEDURES • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Se Avionics System Failures (continued) Erroneous or Loss of Engine and Fuel Displays Indication: Yellow-x over affected engine parameter or fuel display NOTE Erroneous indications may be determined by comparing a display with other system information.

  • Page 92: Erroneous Or Loss Of Warning/Caution Cas Messages

    SECTION3 EMERGENCY PROCEDURES PA-28-181, ARCHER III • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Se Avionics System Failures (continued) Erroneous or Loss of Warning/Caution CAS Messages Indication: Yellow-x is shown over the CAS message window or CAS message present when not expected or CAS message not present when expected.

  • Page 93: Coml And Com2 Failure

    SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III • EMERGENCY PROCEDURES CHECK LIST (continued) Avionics System Failures ( continued) 3.Se COMl and COM2 Failure Indication: Inability to communicate/receive on COM l and COM2. NOTE If power is lost to the audio panel a fail-safe communications path becomes available between the p ilot's headset/microphone and COM I.

  • Page 94: Dual Gps Failure

    SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Se Avionics System Failures (continued) Dual GPS Failure Indication: Amber "DR" annunciation on HSI, Amber "DR" superimposed over airplane symbol on moving map. Navigation ..........Use alternate source of navigation (ILS.

  • Page 95: Avionics Cooljng Fan Failures

    SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER Ill • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Se Avionics System Failures (continued) Loss of Integrity (LO[) Mode -Active when GPS integrity is insufficient for the current phase of flight. Navigation ....... Crosscheck/ use other navigation sources as required.

  • Page 96: Autopilot Or Esp Malfunction

    SECTION 3 El\tlERGENCY PROCEDURES PA-28-181, ARCHER Ill • 3.Se Avionics System Failures (continued) Autopilot or ESP Malfunctions Indication: An unexpected roll or pitch deviation from the desired flight path, possible flight director command deviations from desired aircraft attitudes and possible autopilot disconnect with red AFCS annunciation, amber or red A/P annunciation on PFD.

  • Page 98: Autopilot Overspeed Recovery

    SECTION 3 EMERGENCY PROCEDURES PA-28-1 81 , ARCHER 111 • 3.Se Avionics System Failures (continued) Autopilot Overspeed Recovery MAXSPD Indication: annunciation at the top of the PFD airspeed tape This autopilot mode is active whenever the aircraft actual or projected airspeed exceeds the maximum approved autopilot operating speed of 140 KIAS.

  • Page 99: Autopilot Out-Of-Trim

    SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER Ill • Avionics System Failures ( continued) 3.Se Autopilot Out-Of-Trim ➔ -,1,, Indication: Amber,� AIL, AIL , 1'ELE, or ELE on PFD CAUTION Do not attempt to overpower the autopilot in the event of a mistrim. The autopilot servos will oppose pilot input and will trim opposite the direction of pilot input (pitch axis only).

  • Page 100: Abnormal Flight Director Mode Transitions

    SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III • 3.Se Avionics System Failures ( continued) Abnormal Flight Director Mode Transitions Indication: Flashing lateral or vertical mode annunciations on PFD NOTE Upon loss of a selected mode, the system will revert to the default mode for the affected axis, either ROL or PIT.

  • Page 101: Loss Of Navigation Information

    SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES • Avionics System Failures (continued) 3.Se Loss Of Navigation Information Indication: Amber VOR, VAPP, GPS, BC, LOC or GS flashing on NOTE If a navigation signal is lost while the autopilot is tracking the autopilot will roll U1e aircraft wings level and default to roll mode (ROL).

  • Page 102: Pitot Heat Failure

    SECTION 3 PA-28-181, ARCHER ill EJ\1ERGENCY PROCEDURES • 3.Sf Pitot Heat Failure Pitot Heat Failure Indication: Master Caution, Double Chime, PITOT HEAT FAIL PITOT HEAT Switch ................OFF PITOT HEAT Circuit Breaker (Row 2, Col. 2) ......RESET PITOT HEAT Switch ................ON If Pitot Heat still inoperative: Exit and A void Instrument Meteorological Conditions.

  • Page 103: Spin Recovery

    SECTION3 EMERGENCY PROCEDURES PA-28-181, ARCHER lli • 3.Sh Spin Recovery Spin Recovery Rudder ..............FULL OPPOSITE TO DIRECTION OF ROTATION Control wheel ............FULL FORWARD while NEUTRALIZING AILERONS THROTTLE ..................IDLE slo p s) Rudder ............ NEUTRAL (when rutal.iun Control wheel ..........SMOOTH BACK PRESSURE to recovery from dive Intentional spins are prohibited in this airplane.

  • Page 104: Engine Roughness

    SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER ill 3.Sj Engine Roughness Engine Roughness • ALT AIR ................... OPEN If roughness continues after one minute: MIXTURE ..........Adjust for Maximum Smoothness ALT AIR ......, ............. CLOSE PlJEL PUMP ............, ......... ON Fuel Selector ..............
  • Page 105 SECTION 3 -------------------- EMERGENCY PROCEDURES PA-28-181, ARCHER III 3.Sk Carbon Monoxide CAS Indications CO Detector Warning 1------- • Indication: Master Warning, Triple Chime, COLVLHIGH If the CO Detector Warning or Caution activates in flight: Press the CO RST softkey (on the engine page) lo reset the CO Detector.
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  • Page 107 SECTION 4 PA-28-181, ARCHER ill NORMAL PROCEDURES • TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES Page Paragraph General ................... Airspeeds for Safe Operations ............Normal Procedures Checklist............Preflight Checklist ..............4.5a Engine Start - General ..............4.Sb 4.5c Before Starting Engine ..............
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  • Page 109: General

    4.1 GENERAL This section describes the recommended procedures for conducting normal operations for the Archer III. All of the required ( FAA regulations) procedures necessary for operation of the airplane are presented. This section provides checklists for all normal operating procedures , usin g a simple action - reaction format , with little emphasis on system operation.

  • Page 110: Airspeeds For Safe Operations

    SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER ill 4.3 AIRSPEEDS FOR SAFE OPERATIONS The following airspeeds are significant to the safe operation of the airplane. They are for standard airplanes flown at gross weight under standard conditions • at sea level. Performance for specific airplanes may vary from published figures depending upon the equipment installed, the condition of the engine, airplane and equipment, atmospheric conditions and piloting technique.

  • Page 111: Preflight Checklist

    SECTION 4 PA-28-181, ARCHER ill NORMAL PROCEDURES • 4.5 NORMAL PROCEDURES CHECKLIST (continued) 4.5a Preflight Checklists (continued) CAUTION Thejfop position should be noted before boarding the airplane. The flaps must be placed in the UP position before they will lock and support weight on the step.
  • Page 112 SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER Ill 4.Sa Preflight Checklists (continued) COCKPIT (continued) • FUEL QTY Indications ..........CHECK QUANTITY & IMBALANCE Exterior Lighting Switches ..............ON Exterior Lighting ............ VERIFY OPERATION CAUTION Care should be taken when checking the heated pilot head.
  • Page 113 SECTION 4 PA-28-181, ARCHER ill NORMAL PROCEDURES • 4.5a Preflight Checklists (continued) RIGHT WING Surfac. e Condition ........ CLEAR OF JCE, FROST, SNOW Hap and Hinges .............. NO DAMAGE or INTERFERENCE Aileron and Hinges ............. NO DAMAGE or INTERFERENCE Static Wicks ............CHECK and SECURE \Ving Tip and Lights ..............
  • Page 114 SECTION 4 PA-28-181, ARCHER ill NORMAL PROCEDURES • 4.Sa Preflight Checklists (continued) NOSE SECTION (continued) Chock ..................REMOVE Nose Gear Strut............PROPER INFLATION (3.25 ± .25 in.) Tire ....................CHECK CAUTION When draining any amount of fuel, care should be taken to ensure that no fire hazard exists before starting engine.
  • Page 115 SECTION 4 PA-28-181, ARCHER ill NORMAL PROCEDURES • 4.Sa Preflight Checklists (continued) LEFf WING (continued) Tie Down and Chock ..............REMOVE Fuel Tank ..........CHECK SUPPLY VISUALLY and SECURE CAP Pitot/Static Head ......REMOVE COVER - HOLES CLEAR OAT Probe ..................

  • Page 116: Engine Start- General

    SECTION 4 PA-28-181, ARCHER ill NORl\1AL PROCEDURES 4.Sb Engine Start ENGINE START- GENERAL \VARNING The START ENGD warning CAS message will illuminate after 30 seconds of continuous engine cranking. If the CAS message illuminates after the engine is running, stop the engine and determine the cause.

  • Page 117: Before Starting Engine

    SECTION 4 PA-28-181, ARCHER ID NORMAL PROCEDURES • 4.5c Before Starting Engine Checklists BEFORE STARTING ENGINE Flaps ................... RETRACT Passengers ..................BOARD Door ............... CLOSED and SECURE Seats ........ADJUSTED and LOCKED IN POSffiON Seat Belts and Harness ..........FASTEN/ADJUST CHECK INERTIA REEL FUEL Selector ...............

  • Page 118: Normal Start - Cold Engine

    SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES • 4.Sc Before Starting Engine Checklists ( continued) BEFORE STARTING ENGINE (continued) E VOLTS Indicat. i on .............. 23.3 VOLTS (Minimum) FUEL QTY Indications ........CHECK QUANTITY AND IMBALANCE If che E VOL TS indication is less than 23 .3 VOL TS, thi.:: voltage can be...

  • Page 119: Normal Start - Hot Engine

    SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES • 4.5d Engine Start Checklists (continued) NORMAL START - HOT ENGINE (oil temperature 140 ° F or above) THROTTLE ................1/2 rN. OPEN BA TT MASTR Switch ................. ON AL TR Switch ..................ON LEFf/RIGHT MAG Switches ...............
  • Page 120 SECTION 4 PA-28-181, ARCHER ill NORMAL PROCEDURES • 4.Sd Engine Start Checklists (continued) ENGL'IE START - USING EXTERNAL POWER SOURCE NOTE The EMERG BA TT switch may remain ON while using external power. The emergency bus does not receive power from the external power source due to a relay in the circuit.

  • Page 121: Before Taxiing Checklist

    SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER • 4.5e Before Taxiing Check.list WARM-UP THROITLE ..............800 to 1200 RPM Avoid prolonged idling at low RPM, as this practice may result in fouled spark plugs. BEFORE TAXIING A VJON MASTER Switch ..............ON EMERG BAIT Switch ............

  • Page 122: Taxiing Checklist

    SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES • 4.Sf Taxiing Checklist TAXIING Taxi area ..................CLEAR PARK BRAKE ............... RELEASED Throttle ........, .., ......APPLY SLOWLY Brakes .......... , ..........CHECK Steering ..................CHECK NOT E During taxi, if the VOL TS indication decreases into the warning range, increase engine RPM ( if possible ) to retajn ade q uate battery charging.
  • Page 123 SECTION 4 NORt\1AL PROCEDURES PA-28-181, ARCHER ill • 4.5g Ground Check Checklist GROUND CHECK PARK BRAKE ..................SET THROTTLE ................2000 RPM LETT/RIGHT MAG Check ........MAX. DROP 175 RPM MAX. DIFF. 50 RPM Oil Temperature ................CHECK Oil Pressure ..................CHECK VOLTS Indication ........
  • Page 124 SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER llI • 4.Sh Before Takeoff Checklist BEFORE TA KEO FF BA TI MASTR Switch ............VERIFY ON AL TR Switch ................. VERIFY ON FUEL PUMP ..................ON LEFT/RlGHT MAG Switches ..........VERIFY ON Flight Instruments ................CHECK Standby Flight Instruments ............

  • Page 125: Takeoff

    SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER Ill • 4.Si Takeoff Checklist TAKEOFF NORMAL TECHNIQUE Flaps ......................Trim ....................... SET Brakes ................APPL Y & HOLD THROTTLE ............... FULL POWER Brakes ..................RELEASE Rotation Airspeed ................ 60 KIAS SMOOTHLY ROTATE TO CLIMB A1TITUDE See Flaps Up Takeoff ground roll and Flaps Up Takeoff Performance charts in Section 5 for ground roll/takeoff distances and applicable gross weight vs rotation speed information.

  • Page 126: Climb Checklist

    CRUISING Power ............... SET PER POWER TABLE MIXTURE ..................ADJUST 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 127: Descent C:heck List

    SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER Ill • 4.Sk Cruise Checklist (continued) CRUISING (continued) The electric fuel pump should be turned ON before switching tanks, and should be left ON for a short period thereafter. In order to keep the airplane in best lateral trim during cruising flight the fuel should be used alternately from each tank.
  • Page 128 SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER ID • 4.Sm Approach and Landing Checklist APPROACH AND LANDING NOTE The HSI will auto slew during CDI transitions to LOC, LOC BC, LDA, or SDF approaches if an approach is activated in the G l000 system. The pilot should always double check the inbound course pointer prior to i11itiating a VHF NAV approach.
  • Page 129 SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER ill • 4.Sm Approach and Landing Checklist (continued) APPROACH AND LANDING (continued) Initial Approach Speed ..............75 KIAS ° Final Approach Speed (Flaps 40 ) ..........66 KIAS Touchdown ............... MAIN WHEELS then GENTLY LOWER NOSE Braking ................
  • Page 130 SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER ill • 4.Sn Go-Around Checklist GO-AROUND MIXTURE ................FULL RICH THROTTLE ................FULL OPEN Control Wheel ........BACK PRESSURE TO OBTAIN POSITIVE CLIMB ATTITUDE FLAPS ........... RETRACT INCREMENTALLY ff lilt: ain:raft is t:4uipped with optional Underspeed Protection ( USP ) and an autopilot coupled go-around is desired, press the TO/GA button on the throttle handle followed immediately by the checklist shown above.
  • Page 131 SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III • 4.Sp Stopping Engine Checklist STOPPING ENGINE CAUTION The flaps must be placed in the up position for the flap stop to support weight. Passengers should be cautioned accordingly. PARK BRAKE ..................SET FLAPS ..................

  • Page 132: Mooring Checklist

    SECTION 4 PA-28-181, ARCHER ill NORMAL PROCEDURES • 4.Sq Mooring Checklist MOORING PARK BRAKE ..............AS REQUIRED Flaps ..............VERIFY RETRACTED Control wheel ............ SECURED WITH BELTS Wheel chocks ................IN PLACE Tie downs ..................SECURE If necessary, the airplane should be moved on the ground with the aid of the nose wheel tow bar provided with each airplane and then secure the tow bar on the aft bulkhead of the baggage compartment.

  • Page 133: Stalls

    SECTION4 PA-28-181, ARCHER Ill NORMAL PROCEDURES • 4.7 STALLS The staJI characteristics of the ARCHER Ill are con ventionaJ. An approaching stall is indicated by a stall warning aural annunciation (Stall ..StaJI..Stall) which is activated between five and ten knots above stall speed. Mild airframe buffeting and gentle pitching may also precede the stall.

  • Page 134: Noise Level

    SECTION 4 PA-28-181, ARCHER ill NORMAL PROCEDURES 4.13 NOISE LEVEL (a) 14 CFR Parl 36, Appendix G for aircraft with the standard exhaust • system, the noise level is 73. l dB(A). For aircraft with the optional exhaust system, the noise level is 71.9 dB(A). No determination has been made by the Federal Aviation Administration that the noise levels of this airplane are or should be acceptable or unacceptable for operation at, into, or oul of, any airport.
  • Page 135 SECTION 5 PERFORMANCE PA-28-181, ARCHER III • TABLE OF CONTENTS SECTION 5 PERFORMANCE Paragraph Page General ..................,.. Performance and Flight Planning..........5- 1 Flight Planning Example............. Perfonnance Graphs..............List of Figures................• • REPORT: VB-2749 ISSUED: December 22, 2017...
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  • Page 137 SECTION 5 PERFORMANCE PA-28-181, ARCHER ill • SECTION 5 PERFORMANCE 5.1 GENERAL All of the required (FAA regulalions) and complementary perfonnance information app}jcable to the ARCHER is provided by this section. Perfonnance information associated with those oplionaJ systems and equipment which require handbook supplements is provided by Section 9 (Supplements).
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  • Page 139 SECTIONS PERFORMANCE PA-28-181, ARCHER Ill • S. S 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. The basic empty weight for the airplane as certified at the factory has been entered in Figure 6-5.
  • Page 140 SECTION 5 PERFORMANCE PA-28-181, ARCHER Ill • 5.5 FLIGHT PLANNING EXAMPLE (continued) (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 tlight. Apply the depanure airport conditions and takeoff weight to the appropriate Takeoff Performance graph (Figure 5-7 or 5-9) to determine the barrier distance or (Figure 5-11 or 5-13) to determine...
  • Page 141 SECTION 5 PERFORMANCE PA-28-181, ARCHER Ill • (c) Climb The next step in the tlight 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 considered in determining the climb components from the Time, Distance and Fuel to Climb graph (Figure 5-17).
  • Page 142 SECTION 5 PA-28-181, ARCHER ill PERFORMANCE • 5.5 FLIGHT PLANNING EXAMPLE (continued) (d) Descent The descent data will be determjned prior to the cruise data to provide the descent distance for establishing the total cruise distance. Utilizing the cruise pressure altitude and OAT, determine the basic time, distance and fuel for descent (Figure 5-37).
  • Page 143 SECTION 5 PERFORMANCE PA-28-181, ARCHER III • (e) Cruise Using Lhe total distance to be traveled during the flight, subtract the previously calculated distance to climb and distance Lo descend to establish the total cruise distance. Refer LO the appropriate engine Operator's Manual when selecting the cruise power setting.
  • Page 144 SECTION 5 PA-28-181, ARCHER III PERFORMANCE • 5.5 FLIGHT PLANNING EXAMPLE ( continued) (f) Total Flight Time The total flight time is determined by adding the time to climb, the time to descend and the cruise time. Remember! The time values taken from the climb and descent graphs are in minutes and must be converted to hours before adding them to the cruise time.
  • Page 145 SECTION 5 PA-28-181, ARCHER ill PERFORMANCE 5.7 PERFORMANCE GRAPHS LIST OF FIGURES P age Fi g ure T emperature Con vers ion ............5-11 Airs pee d System Calibration............. 5-12 Stall S peeds ................5-13 Flaps Up Takeoff Performanc e..........
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  • Page 147: Temperature Conversion

    SECTION 5 PA-28-181, ARCHER III PERFORMANCE • • FAHRENHEIT CELSIUS DEGREES DEGREES ·20 • - 3 0 - 4 0 - 4 0 TEMPERATURE CONVERSION Figure 5-1 ISSUED: December 22, 2017 REPORT: VB-2749 5-11...

  • Page 148: Airspeed System Calibration

    SECTION 5 PA-28-181, ARCHER ID PERFORMANCE • AIRSPEED SYSTEM CALIBRATION 2550 LBS. GROSS WEIGHT • 40• 1'1.API • 100 110 120 130 140 1&0 INDICATED AIRSPEED KIAS (ZERO INSTRUMENT ERROR) AIRSPEED SYSTEM CALIBRATION Figure 5-3 ISSUED: December 22, 2017 REPORT: VB-2749 5-12...
  • Page 149 • • • "'O POWER OFF STALL SPEED > � ¥ •rcher Ill ..� ..EXAMPLE ° Flaps � � Aircraft Weight: 2,350 LB. ► � ° - - • 25 Flaps ° Angle of Bank: � ° - - - 40 Flaps �...

  • Page 150: Flaps Up Takeoff Performance

    r:,i lll ,:I FLAPS UP TAKEOFF PERFORMANCE "'0 ei"j ei"j �Q �� ASSOC IA TED CONDITIONS; EXAM LE· FULL THROTTLE BEFORE BRAKE RELEASE 2,000 Ft 0 ..Power: Oepa/1 Airport Pressure Alt: KlAS i� TAKE OFF SPEEDS Conditlooer: LIFTOFF 50FT 23'C Temperature: �...
  • Page 151 • • • FLAPS TAKEOFF PERFORMANCE � ASSOCIATED CONDITIONS 2.000ft El(A MPbE ..Po,,er. A.JLL THROTll.E BEFCRE BRAKE RELEASE J!Jr Conditioner: � Depa-I J!Jrport Pressure Pit TAKE OFF SPEEDS KIAS 2 3' C T efll)eralure: ..PA'va), LEVEL, & CRY �...
  • Page 153 • • • 'JS' FLAPS TAKEOFF GROUND ROLL � ASSOCIATED CONDITIONS EXAMPLE ..Pov-ier: FLU THROTTLE BEFOOE BRA1<E RELEASE � TAJ<EOfF SPEEDS KIAS t!'j 2,000 ft. Depart .Airport Pressure .Alt: .llirCondtiooer: CJ'F _vyJ__ __L.IFTOFF ..T errperatl.1'8: 2-:f PA\1:0, LEva., & DRY 2,550 fur.Nay.

  • Page 154: Climb Performance

    Ul :,:, "'O VJ CLIMB PERFORMANCE EXAMPLE· ASSOCI ATI; Q CQNDIJIONS; ,!.. t'fj t'fj t'fj Gtou W•ght. 2550 LBS 00 "'O Chmb Pressure Alt. 4000 Ft. :,:, (i "r:I ,.., Power: FVLL THROTT1.E Temperature: ° Al��: 0 ..78KlAS :,:, Rate of Climb: FVMln.
  • Page 155 • • • ..TIME, FUEL, DISTANCE TO CLIMB c::: EXAMPLE � ASSOCIATED CONDITIONS Flaps: 23 •c Gross Weight: 255 0 LB Depan Airport Press Aft.: 2000 FT. Temperature: Power. FULL THROTTLE Airspeed: 76 KIAS 1s • c Cruise OAT: Cruise Press Alt.: 8000 ·...

  • Page 157: Engine/Cruise Perform A Nce (55%)

    SECTION 5 PA-28-181, ARCHER ill 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 Knots** Sea Level ISA-15 2245...

  • Page 158: Engine/ C Ruise Performance (65%)

    SECTION 5 PA-28-181, ARCHER ill PERFORMANCE • Engine / Cruise Performance for Non-lSA OAT* RPM for Constant 65 % Power Fue. 1 Flow: Best Economy Mixture, 9.5 GPH True Air Indicated Outside Air Temperature Engine Pressure Speed Speed Altitude Knots** Feet 2385 Sea Level...

  • Page 159: Engine/Cruise Performance (75%)

    SECTION 5 PA-28-181, ARCHER ill PERFORMANCE • Engine / Cruise Performance for Non-ISA OAT* RPM for Constant 75% Power Fuel Flow: Best Economy Mixture, 11.0 GPH Engine Pressure indicated Outside Air Temperature True Air Altitude Speed Speed Feet Knots** Sea Level ISA-15 2485 2515...
  • Page 160 - - - - - - - - - - - - - - - � SECTION 5 PA-28-181, ARCHER 1II PERFORMANCE • • Tms PAGE INTENTIONALLY LEFT BLANK • ISSUED: December 22, 2017 REPORT: VB-2749 5-24...
  • Page 161 • • • "ti ;i.- Fuel Flow Ga l . per Hour SPEED POWER Power Mixture OAT= ISA 2550 LBS GROSS WT..SENSENICH 76EM8S 14-0-62 PROP � � 75 ',I, B�st Econ 11.0 ..I 65 % Best Econ "...
  • Page 162 "'O (J) � g; t-r, t-r, RANGE WITHOUT 45 MIN. RESERVE EXAMPLE; NOTE; QI "'O 6000 Ft. Cruise Pressure All REDUCE RANGE 3% IF �� 48 GAL USA6LE FUEL 2550 LBS GROSS WT. Power 65% Best Economy SENSEWCH 76EM8S14-0-62 PROP WHEEL PANTS ARE ,::, Range wittt No Reserves 547...
  • Page 164 SECTION 5 PERFORMANCE PA-28-181, ARCHER ill cf?Y- � 'o� �\\J� � ... )..-- � �\ �$' � .." .,..,,. � __ ....::::, ..� • lt'i ?,.€. 9. � � ::::, --� • - .. - .. - .. - .. - .. -'- -'- -'- -- -► •...
  • Page 165 SECTION 5 PA-28-181, ARCHER ill PERFORMANCE • � E. 'o'.2-.... ':/--'\J� ..�'{��-- � ..I .,,,,... ll') ..� ., � ., "' ..·•� �E. 9.._ �Q.(O C ..-..-� �,\.} :'( ""\ � � a. w £:_$\ \::.

  • Page 167: Glide Range

    SECTION 5 PA-28-181, ARCHER III PERFORMANCE • � � � � ..-� � �11 ► • (/) 0 <( w � � Z n.: z _ I'-- :s (/) � �� � 0 u.. - u.: ...J u. 0::: (!) 0 (.'.)

  • Page 168: Landing Performance

    Ul ::0 "ti (J') LANDING PERFORMANCE ['!lj r,r, �� ;i:, EXAM PLE: N "'O !� Airport Pressure Attilude: ""1.-, ASSOCIATED CONDITIONS 2,500 ;a:, 21•c ° 0.A. T.: :-:3 Power Off Approach, 40 Flaps, 66 KIAS, Full Stall Gross ◄ Weight SKT.

  • Page 169: Landing Ground Roll

    SECTION 5 PA-28-181, ARCHER Ill PERFORMANCE • l.33.:1 -110� aNnO�D DNION'v'1 ....(") <O ,.._ <D� � I I I �(' " 9� •� -�✓ • ..w r.,w . I • • � 711,- \0 � '�...
  • Page 170 SECTION 5 PERFORMANCE PA-28-181, ARCHER ill • • THIS PAGE INTENTIONALLY LEFT BLANK • REPORT: VB-2749 ISSUED: December 22, 2017 5-34...
  • Page 171 SECTION6 WEIGHT AND BALANCE PA-28-181, ARCHER ill • TABLE OF CONTENTS SECTION 6 WEIGHT AND BALANCE Page Paragraph General ..................Airplane Weighing Procedure ..........6.
  • Page 172 SECTION 6 WEIGHT AND BALANCE PA-28-181, ARCHER III • • THIS PAGE INTENTIONALLY LEFT BLANK • REPORT: VB-2749 ISSUED: December 22, 2017 6-ii...
  • Page 173 SECTION6 WEIGHT AND BALANCE PA-28-181, ARCHER ill • 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 174 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 175 SECTION 6 WEIGHT AND BALANCE PA-28-181, ARCHER ill • 6.3 AlRPLANE WEIGHJNG PROCEDURE (continued) 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.
  • Page 176 SECTION 6 PA-28-181, ARCHER WEIGHT AND BALANCE • 6.3 AIRPLANE WEIGHING PROCEDURE (continued) (d) Basic Empty Weight Center of Gravity (1) The following geometry applies to the PA-28-181 airplane when it is level. Refer to Leveling paragraph 6.3 (b). (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: inches...
  • Page 178 SECTION 6 WEIGHT AND BALANCE PA-28-181, ARCHER III • MODEL P A-28-181 ARCHER ill Airplane Serial Number _ _ 2_8_8�1-55_ 0 _ _ _ _ .,,. ._._. Registration Number _ _ _ ..O /2_0 Date _ _ _ _ _ _ _ c..
  • Page 179 • • • "' >- 2881550 N232TF Page Number Registration Number PA-28-181 Se1ial Number � ..,,..Running Basic ,,..._ ' ..+ ..__, Weight Change � Empty Weight ..__,"O > Description of Article II> -0 (l) > Date :,::, -0 0 or Modification Moment...
  • Page 180 SECTION 6 PA-28-181, ARCHER HI WEIGHT AND BALANCE • ....c:: "'·- ::E -... (:Q Q) bl)� § -� � ,-.. ::, E ...; ..0 "' 0::: �..l '--' 0 ..::E -..� ..c:: ..., <'i: 8 ..c:: ..
  • Page 181 SECTION 6 WEIGHT AND BALANCE PA-28-181, ARCHER III • 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 182 SECTION6 PA-28-181, ARCHER III WEIGHT AND BALANCE • Arm Aft Datum Weight Moment (Lbs) (Inches) (In-Lbs) Basic Empty Weight 80.5 Pilot and Front Passenger 118.1 Passengers (Rear Seats)* Fuel (48 Gallon Maximum) 95.0 142.8 Baggage (200 Lbs. Maximum)* Ramp Weight (2558 Lbs. Normal, 2138 Lbs.
  • Page 183 SECTION6 WEIGHT AND BALANCE PA-28-181, ARCHER III • �.,.?' '</ r1 · - , l ' .�o ·/ �' �-Ii 'I--� � '<,S ,,, � V � # � "' • " )½ t:," MOMENT/1000 (POUNDS - INCHES) • LOADrNG GRAPH...
  • Page 184 SECTION6 PA-28-181, ARCHER III WEIGHT AND BALANCE • WEIG HT vs . C.G. ENVELOPE 2660 LBS. MAX. GROSS WT.· es., NORMAL CATEGORY 26 00 2400 2300 8 4 / -1- - -1 22 00 • --UTILITY CATEGORY-- 2100 2000 •...
  • Page 185 SECTION7 DESCRIPTION & OPERATION PA-28-1 8 1 , ARCHER III • TABLE OF CONTENTS SECTION 7 DESCRIPTION AND OPERA TION OF THE AIRPLANE AND ITS SYSTEMS Page Paragraph The Airplane ................7- 1 Airframe ..................Engine and Propeller ..............
  • Page 186 SECTION7 DESCRIPTION & OPERATION PA-28-181, ARCHER III • • THIS PAGE INTENTIONALLY LEFT BLANK • REPORT: VB-2749 ISSUED: December 22, 2017 7-ii...
  • Page 187 7.5 ENGINE AND PROPELLER The ARCHER III is powered by a four-cylinder, direct drive, horizontally opposed fuel injected engine rated at 180 horsepower at 2700 rpm. It is furnished with a starter, 70 ampere 28-volt alt. e rnator, shielded ignition wires, a fuel pump, and a dry, automotive type induction air filter.
  • Page 188 SECTION7 PA-28-181, ARCHER ill DESCRIPTION & OPERATION INDUCTION SYSTEM The induction system incorporates an Avstar RSA-SAD I type fuel injector. • The injector is based on the principle of differential pressure, which balances air pressure against fuel pressure. The regulated fuel pressure established by the servo valve when applied across a fuel control (jett i ng system) makes the fuel flow proportional to airflow.
  • Page 189 SECTION7 DESCRIPTION & OPERATION PA-28-181, ARCHER ill • • � t y · __.,,-· • CONTROL QUADRANT AND CONSOLE Figure 7-1 REPORT: VB-2749 ISSUED: December 22, 2017...
  • Page 190 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION • 7.9 ENGINE CONTROLS (continued) The friction on the throttle and mixture controls can be adjusted by using the friction adjustment lever on the right side of the control quadrant. An alternate air control is located on the instrument panel right of the contJol quadrant.
  • Page 192 SECTION7 PA-28-181, ARCHER 111 DESCRIPTION & OPERATION • /'fl • • MAIN WHEEL ASSEMBLY Figure 7-3 (Wheel fairing removed for clarity.) ISSUED: December 22, 2017 REPORT: VB-2749 7 -6...
  • Page 193 SECTION7 DESCRIPTION & OPERATION PA-28-181, ARCHER ID • 7.13 LANDING GEAR Three landing gear use Parker 6.00 x 6 wheels. Each main gear are equipped with a single hydraulically operated external caliper & disc brake assembly. All three wheels use 6.00 x 6, four-ply rating, Type HI tires with tubes. A spring device is incorporated in the rudder pedal torque tube assembly to provide rudder trim.
  • Page 194 The latest appropriate rev1s1on of the Garmin G 1000 Cockpit Reference Guide for the Piper PA-28-181 Archer (Garmin PIN 190-02131-02), and the Garmin G 1000 Pilot's Guide for the Piper PA-28-181 Archer (Garmin PIN 190-02130-02), contain operational information and detailed...
  • Page 195 SECTION 7 PA-28-181, ARCHER ill DESCRIPTION & OPERATION • 7.15 GARMIN GlOOO AVIONICS SYSTEM (continued) Primary Flight Display The Primary Flight Display (PFD) displays ajrspeed, attitude, altitude, and heading information in a traditional format. Slip information is shown as a trapezoid under the bank pointer.
  • Page 196 SECTION 7 PA-28-181, ARCHER Ill DESCRIPTION & OPERATION • Primary Flight Display (continued) real-time to obtain the user's position, velocity, and time. These GPS SBAS receivers are certified under TSO C l46a and therefore is qualified as a primary navigation system. The PFD also displays autopilot status and mode annunciation, at the top, center of the display.
  • Page 197 SECTION7 PA-28-181, ARCHER DESCRIPTION & OPERATION • Primary Flight Display (continued) Reversionary Mode - PFD The PFD will automatically be displayed in a composite fonnat (Reversionary mode) for emergency use if the MFD display fails. The DISPLAY BACKUP button on the audio panel should also be pressed. In the composite mode, the PFD will display the engine parameters typically reserved for the MFD, including the full crew alerting system and autopilot annunciations.
  • Page 198 SECTION 7 PA-28-181, ARCHER ill DESCRIPTION & OPERATION • Synthetic Vision System (SVS) - Optional The Synthetic Vision System (SVS) is a visual enhancement to lhe GlOOO . Terrain-SYS is displayed on the PFD as a forward-looking depiction of the topography immediately in front of the aircraft.
  • Page 199 SECTION 7 PA-28-181, ARCHER ill DESCRIPTION & OPERATION • Multi-Function Display The Multi-Function Display (MFD) is located in the center of the instrument panel. The primary functions of the MFD include the display of: • Engine parameters • Aircraft system parameters •...
  • Page 200 SECTION7 PA-28-181, A RCHER III DESCRIPTION & OPERATION • Multi-Function Display (continued) • EIS PAGE (TYPICAL) Figure 7-4 • ISSUED: December 22, 2017 REPORT: VB-2749 7-14...
  • Page 201 SEC TION7 DESCRIPTION & OPERATION PA-28-181, ARCHER Ill • Multi-Function Display (continued) Crew Alerting System (CAS) Messages The Crew Alerting System (CAS) consists of a Master Warning and Caution softkey on the lower right side of the PFD operating in conjunction with CAS text messages.
  • Page 202 SECTION7 PA-28-181, ARCHER III DESCRIPTION & OPERATION • Multi-Function Display (continued) Crew Alerting System (CAS) Messages (continued) Amber Caution Messages Caution messages consist of a !lashing amber Master CAUTION softkey, and a flashing (inversely black on amber) CAS Caution text message located in the lower right area of the PFD.
  • Page 203 SECTION? PA-28-181, ARCHER ill DESCRIPTION & OPERATION • Multi-Function Display (continued) Crew Alerting System (CAS) Messages (continued) Reversionary Mode - MFD Should the PFD become inoperative, the MFD can be selected into reversionary mode by pressing the red DISPLAY BACKUP on the audio panel. The MFD will then show typical PFD information, including the horizon with airplane symbol, rotating compass card with heading and course deviation, the pilot selectable data fields, transponder information and G l000 system...
  • Page 204 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION • Multi-Function Display (continued) Traffic Information Service (TIS) NOTE If the G I 000 system is configured to use the optionaJ Traffic Advisory System (T AS), TIS will not be available for use.
  • Page 205 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER • Multi-Function Display (continued) Traffic Information Service (TIS) (continued) Traffic Map Page (Continued) Traffic is overlaid on the following pages: • Navigation Map Page • Traffic Map Page • Trip Planning Page • Nearest Pages •...
  • Page 206 SECTION7 PA-28-181, ARCHER III DESCRIPTION & OPERATION • Multi-Function Display (continued) Traffic Information Service (TIS) (continued) TIS Alerts (continued) TIS customization options are available to the pilot by depressing the MENU key while on the Navigation Map Page, and then selecting "Map Setup" then "Traffic"...
  • Page 207 SECTION? PA-28-181, ARCHER ill DESCRIPTION & OPERATION • Multi-Function Display (continued) Traffic Advisory System (TAS) - Optional (continued) Traffic Map Page The Traffic Map page, located in the Map Group on the MFD, is selectable from 2 nm to 12 nm. The GTS 800 is capable of tracking up to 45 intruding aircraft equipped with Mode A or C transponders, and up to 30 intruding aircraft equipped with Mode S transponders.
  • Page 208 SECTION 7 PA-28-181, ARCHER ID DESCRIPTION & OPERATION • Multi-Function Display (continued) Traffic Advisory System (TAS) - Optional (continued) TAS Alerts: Traffic is displayed according to TCAS symbology using four different symbols. l. Non-Threat Traf ic - An open white diamond with black center that indicates traffic is beyond a 6 nm range and greater than ±...
  • Page 209 SECTION7 DESCRIPTION & OPERATION PA-28-181, A RCHER III • Multi-Function Display (continued) Terrain Proxin1ity NOTE If the GI 000 system is configured to use the optional Terrain Awareness and Warning System (TA WS), Terrain Proximity will not be available for use. G LOO0 Terrain Proximity is a terrain awareness system Lhat increases situational awareness and aids in preventing controlled flight into terrain (CFIT).
  • Page 210 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION • Multi-Function Display (continued) Terrain Proximity (continued) OPS alLitude, whicb is derived from satellite position and therefore may differ from baro-corrected altitude read from the altimeter, is converted to mean sea level (MSL)-based altitude (GPS-MSL altitude) and is used in conjunction with OPS position to calculate and predict the aircraft's flight path in relation to the surrounding terrain and obstacles, whose altitudes are also referenced to MSL.
  • Page 211 SECTION7 DESCRIPTION & OPERATION PA-28-181, ARCHER • Multi-Function Display (continued) Terrain Proximity (continued) Tenain customization options are available by pressing the MENU key while on the Navigation Map Page, and then selecting "Map Setup" then "Map" group. Options selected on the Navigation Map page will be used on other map pages (less the Terrain Proximity Page itself) that display terrain information.
  • Page 212 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER IH • Multi-Function Display (continued) Terrain Awareness and Warning System (TA WS -B) - Optional NOTE the G l0O0 system is configured to use the optional Terrain Awareness and Warning System (TA WS), Terrain Proximity will not be available for use.
  • Page 213 SECTION7 PA-28-181, ARCHER DI DESCRIPTION & OPERATION • Multi-Function Display (continued) Terrain Awareness and Warning System (TA WS-B)- Optional (continued) System Status: During G 1000 power-up, TA WS-B conducts a self-test of its aural and visual annunciations. The system test can also be manually initiated by selecting the TA WS-B Page then depress the MENU key, then select the "Test TA WS"...
  • Page 214 SECTION 7 PA-28-181, ARCHER Ill DESCRIPTION & OPERATION • Multi-Function Display (continued) Terrain Awareness and Warning System (TAWS-B)- Optional (continued) Operation of TA WS-B (continued) Terrain customization options are available by pressing the MENU key while on the Navigation Map Page, and then selecting "Map Setup" then "Map"...
  • Page 215 SECTION7 DESCRIPTION & OPERATION PA-28-181, ARCHER Ill • Multi-Function Displa y (continued) Terrain Awareness and Warning System (TA WS-B)-Optional (continued) TAWS-B Page: The TAWS-B Page is located in the Map Page Group on the MFD. The TA WS Page is specialized to show terrain, obstacle, and potential impact point data in relation to the aircraft's current altitude, without clutter from the base map.
  • Page 216 SECTION7 PA-28-181, ARCHER III DESCRIPTION & OPERATION • THIS PAGE INTENTIONALLY LEFT BLANK • Reserved Table 7-1 REPORT: VB-2749 ISSUED: December 22, 2017 7-30 REVISED: June 17, 2019...
  • Page 217 SECTlON 7 PA-28-181, ARCHER TII DESCRIPTION & OPERATION • Multi-Function Display (continued) Terrain Awareness and Warning System (TA WS-B)- Optional (continued) TA WS-B Alerts (continued) RCStJOnsc Technique WARNING: I. Level the wings while simultaneously adding maximum power. ° ° 2. Smoothly pi1ch up at a rate of2 to 3 per second towards an initial target °...
  • Page 218 SECTIO 7 PA-28-181, ARCHER Ill DESCRIPTIO & OPERATION • Multi-Function Display (continued) Garmin Datalink (GDL)- Optional SiriusXM Weather services is provided through Lhe optional GDL 69eA. a remote-mounted data-link satellite receiver. SiriusXM Satellite Weather services, available by subscription, have coded IDs unique the installed GDL 69eA.
  • Page 219 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER Ill • Multi-Function Display (continued) Garmin Datalink (GDL) - Optional (continued) SiriusXM Satellite Weather (continued) NOTE Echo Tops and Cloud Tops are not selectable at the same time due to their color similarities. The following pages can display various portions of XM Weather data: •...
  • Page 220 SECTION7 PA-28-181, A RCHER III DESCRIPTION & OPERATION • Multi-Function Display (continued) Garmin Datalink (GDL) - Optional (continued) SirusXM Satellite Weather (continued) Expiration Time Broadcast Rate Weather Product Symbol (minutes) (minutes) 5 (U.S.) NEXRAD � tr., .;;a Cloud Top CLO TOP) liiiil ■...
  • Page 221 SECTION7 PA-28-181, ARCHER ill DESCRIPTION & OPERATION • Multi-Function Display (continued) Garmin Datalink (GDL) - Optional (continued) SirusXM Satellite Weather (continued) Table 7-2 shows the weather product symbols, the expiration time and the broadcast rate. The broadcast rate represents the interval at which SiriusXM weather service transmits new signals that may or may not contain updated weather products.
  • Page 222 SECTION 7 PA-28-181, ARCHER ID DESCRIPTION & OPERATION • Databases The GI 000 utilizes several databases. Database titles display in yellow if they have expired or are in question. Database cycle information is displayed at power up on the MFD screen, but more detailed information is available on the AUX pages.
  • Page 223 SECTION7 DESCRIPTION & OPERATION PA-28-181, ARCHER ill • Databases (continued) FliteCharts Database The Garmin FliteCharts database contains procedure charts for the coverage area purchased. This database is updated on a 28-day cycle. If not updated within 180 days of the expiration date, FliteCharts will no longer function.
  • Page 224 SECTION7 PA-28-181, ARCHER ill DESCRIPTION & OPERATION • Autopilot (Optional) AUTOPILOT CONTROLS Controls for selecting lateral and vertical flight director modes and for engaging/ disengaging autopilot and flight director, are located on the MFD bezel. Additional autopilot related functions are controlled by the following: A/P DISC TR1M INTER Switch Autopilot Disconnect and Trim Interrupt...
  • Page 225 SECTION7 PA-28-181, ARCHER ill DESCRIPTION & OPERATION • Autopilot (Optional} (continued) AUTOPILOT OPERATION When the A VION MASTER switch is selected ON, the GFC700 automatically conducts a self-test, as indicated by a white boxed PFT on the PFD. Successful completion of this self-test is indicated by extinguishing the PFf with no AP failure indications and an autopilot "warble"...
  • Page 226 SECTION7 PA-28-181, ARCHER ill DESCRIPTION & OPERATION • Autopilot (Optional) (continued) Autopilot Disengagement Methods: The autopilot can be disengaged manually by the following "normal" methods which are indicated by a yellow flashing AP annunciation: • Pressing the A/P DISC I TRIM INTER switch on the control wheel •...
  • Page 227 SECTION? PA-28-181, ARCHER DESCRIPTION & OPERATION • Autopilot {Optional) (continued) AUTOPILOT FEATURES (continued) Overspeed Recovery Mode (continued) is not active in ALT or GS modes and the airspeed reference (FLC) cannot be adjusted while in Overspeed Recovery mode. Takeoff Mode {Optional) Takeoff Mode allows the pilot to manually follow the flight director command bars a[Lc::r 1akc::uf rutaLiun.
  • Page 228 SECTION7 DESCRIPTION & OPERATION PA-28-181, ARCHER ill • Autopilot (Optional) (continued) AUTOPILOT FEATURES (continued) Level Mode (Optional) Level Mode commands the airplane to wings level and zero vertical speed. It is activated by pressing the blue switch (labeled LVL) at the top center of the instrument p anel.
  • Page 229 SECTION 7 PA-28-181, A RCHER ill DESCRIPTION & OPERATION • Autopilot (Optional) (continued) A UTOPILOT FEATURES (continued) Expanded Engagement Envelope (Optional) Expanded engagement envelope allows autopilot engagement up to the pitch and roll attitudes shown in the autopilot limitations of Section 2. If the autopilot is engaged at a pitch or roll attitude within the expanded engagement envelope but beyond the maximum autopilot command limits, the airplane will be pitched or rolled to the maximum autopilot command limits.
  • Page 230 SECTION7 PA-28-181, ARCHER III DESCRIPTION & OPERATION • GTX 33SR Transponder (Extended Squitter) The GTX 335R Transponder provides Mode A, C, and S altitude and position reporting information for the GI 000 system as well as TIS-A and ADS-B OUT (1090 ES).
  • Page 231 SECTION 7 PA-28-181, ARCHER ill DESCRIPTION & OPERATION • GTX 345R Transponder (Option) (continued) Traffic information will be displayed as a combination of two systems: • ADS-B traffic information from other ADS-B equipped aircraft • GTS 800 Traffic Advisory System (TAS) NOTE ADS-B traffic information will be available on the normal GI 000 traffic display maps/pages.
  • Page 232 SECTION7 PA-28-181, ARCHER Ill DESCRIPTION & OPERATION • 7.17 STANDBY INSTRUMENT (continued) Aspen Standby Instrument In the event of a complete electrical failure of the alternator, primary and emergency batteries; the Aspen standby instrument will revert to its internal battery allowing approximately 30 additional minutes of operation. ln this occurrence the Aspen standby instrument will illuminate an "ON BAT"...
  • Page 233 SECTION7 PA-28-181, ARCHER III DESCRIPTION & OPERATION • 7.17 S TANDBY INSTRUMENT (continued) BackUght Intensity Adjustment: The Garmin GS powers up in lhe Auto adjustment mode. To adjust the backlighting: To select Manual mode from Auto mode: I. While the unit is turned on, press the Power button.
  • Page 234 SECTION7 PA-28-181, ARCHER ill DESCRIPTION & OPERATION 7.17 STANDBY INSTRUMENT (continued): Refer to Garmin 05 Electronic Flight instrument Pilot's Guide for Certified • Aircraft, part number 190-01112-12 Rev D (or later approved revisions), for a list of system messages and description of the Garmin 05 standby flight instrument This reference material is not required to be on board the aircraft but does contain a more in depth description of all the functions and capabilities of the Garmin GS standby instrument.
  • Page 235 SECTION 7 PA-28-181, ARCHER ill DESCRIPTION & OPERATION • 7.19 FUEL SYSTEM (continued) � ;::;,-:_ � 7_;..,- ..---- ----- './"'l -� � • �J �\ -::::--- ---- � -· ,;,- ,--- � ,---_,..;:-� ::::---- FUEL SELECTOR Figure 7-5 An auxiliary electric fuel pump is provided in case of failure of the engine driven pump.
  • Page 236 SECTION 7 PA-28-181, ARCHER ill DESCRIPTION & OPERATION • 7.19 FUEL SYSTEM (continued) FUEL NOZZLE FUEL otSTRIBUTOR ,..,.,_,.,...,.._ FUEL INJECTOR MUt. TI fUNC'Tl01$ Oll,U't ►---SERVO REGULATOR NMAAYPI.Off Ollft\Al Hit.�--� • ...,_---ELECTRIC FUEL PUMP FIREWALL--✓ f.., ____ FUEL SELECTOR VAJ..VE LEFT TANK RIGHT TANK DRAIN DRAIN...
  • Page 237 SECTION7 DESCRIPTION & OPERATION PA-28-181, ARCHER ill • 7.21 ELECTRICAL SYSTEM The 28 volt electrical system includes a 24 volt primary battery, a 70 ampere 28 volt alternator, a single external power connector and an isolated 24 volt emergency battery. The electrical system is capable of supplying sufficient current to all the required equipment for day/night IFR and day/night VFR operations.
  • Page 238 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER ill • 7.21 ELECTRICAL SYSTEM (continued) CAUTION J O - m inutes of power from the emergency battery is on.Ly available if its voltage is greater than 23.3 volts prior to flight. Ensure that a minimum of 23. 3 volts is available prior to jligh1.
  • Page 239 SECTION7 DESCRIPTION & OPERATION PA- 2 8-181, ARCHER Ill • 7.21 ELECTRICAL SYSTEM (continued) • • ALTERNATOR AND STARTER SCHEMATIC Figure 7-7 Sheet 1 of 2 REPORT: VB-2749 ISSUED: December 22, 2017 7-51...

  • Page 240: Fi G Ure

    SECTION7 DESCRIPTION & OPERATION PA-28-181, ARCHER Ill • 7.21 ELECTRICAL SYSTEM (continued) • � � • Sl18 1WN3SS3 ALTERNATOR AND STARTER SCHEMATIC Figure 7-7 Sheet 2 of2 REPORT: VB-2749 ISSUED: December 22, 2017 7-52...
  • Page 242 SECTION7 DESCRIPTION & OPERATION PA-28-181, ARCHER Ill • �� �s Ci� __;;;o I'-. 0 0 2._ 2..,0 <'I �@ • ,.,. • .. ca □• 0 0 0 0 0 0 0 ..00000000000 �o ..<2... "O � (") �- §...
  • Page 243 • • • "tl > �� <� I. Standby instrument Electrical accessories (L to � 0 � . . 0 a) Aspen EBD-1000 a) Flight director/ autopilot switch (option) " > ::: lll b) Gannin G5 b) Pirot heat ., :l ::i:, 2.
  • Page 244 SECTION7 PA-28-181, ARCHER ill DESCRIPTION & OPERATION • 7.23 INSTRUMENT PANEL (continued) l [N] I liHI] ◊ ..c: � •§ I • [I[] 1 §_ [Jill [ill] • � 0 OVERHEAD SWITCH PANEL Figure 7-10 REPORT: VB-2749 ISSUED: December 22, 2017 7-56...
  • Page 245 SEC TION7 DESCRIPTION & OPERATION PA-28 - 1 81, ARCHER Ill • • THIS PAGE INTENTIONALLY LEFT BLANK • REPORT: VB- 2 749 ISSUED: December 22, 2017 7-57...
  • Page 246 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 7.25 PITOT-ST ATIC SYSTEM Dynamic and static pressures are both supplied by a single pitot head • installed on the bottom of the left wing. Independent pressure lines plumbed from the pitot mast through the wing and fuselage connect to the Garmin air data computer and the standby instrument (Figure 7-1 I) located on the instrument panel.
  • Page 247 SECTION7 DESCRIPTION & OPERATION PA-28-181, ARCHER ill • • STATIC LINE STATIC LINE --·J PITOTLINE • 1. Standby Instrument Display 2. Alternate Static Valve 3. PitoVStatic Drain Valves 4. Air Data Attitude and Heading Reference System (ADAHRS) 5. Pilot Head PITOT-STATIC SYSTEM Figure 7-11 REPORT: VB-2749...
  • Page 248 SECTION7 DESCRIPTION & OPERATION PA-28-181, ARCHER ill � • • HEATING AND VENTILATING SYSTEM Figure 7-12 REPORT: VB-2749 ISSUED: December 22, 2017 7-60...
  • Page 249 SECTION7 DESCRIPTION & OPERATION PA- 2 8-181, ARCHER ill • 7. 2 7 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 7-12). The amount of heat desired can be regulated with the controls located on the far right side of the instrument panel.
  • Page 250 SECTION7 PA-28-181, ARCHER ill DESCRIPTION & OPERATION • 7.29 CABIN FEATURES (continued) I CAUTION! Ensure all occupied seat backrests are in their full upright position for all taxi, take-off and landing operations. A cabin interior includes a pilot storm window, two sun visors, two map pockets, and pockets on the backs of each front seat.
  • Page 251 SECTION7 DESCRIPTION & OPERATION PA- 2 8- 181, ARCHER Ill • 7. 3 3 STALL WARNING An approaching stall is indicated by a stall warning aural alert which is activated between five and ten knots above stall speed. Mild airframe buffeting and gentle pitching may also precede the stall.
  • Page 252 SECTION7 PA-28-181, ARCHER ill DESCRIPTION & OPERATION • 7.39 EMERGENCY LOCATOR TRANSMITTER (continued) NOTE If for any reason a test transmission is necessary, the test transmission should be conducted only in the first five minutes of any hour and limited to three audio sweeps.
  • Page 253 SECTION? PA-28-181, ARCHER DI DESCRIPTION & OPERATION • 7.39 EMERGENCY LOCATOR TRANSMITTER (continued) ARTEX ELT 1000 OPERATION (continued) The transmjtter can be activated manually at any time by placing either the remote switch or the EL T switch to the ON position. A monthly functional check is recommended to verify operational status of the ELT.
  • Page 254 SEC TION 7 PA-28-181, ARCHER ill DE SCRIPTION & OPERATION • • THIS PAGE INTENTIONALLY LEFT BLANK • ISSUED: December 22, 2017 REPORT: VB-2749 7-66...
  • Page 255 SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER ill • TABLE OF CONTENTS SECTION 8 AIRPLANE HANDLING, SERVICING AND MAINTENANCE Page Paragraph 8. 1 General ................... Airplane Inspection Periods ........... . 8. 5 Preventive Maintenance ............Airplane Alterations ..............Ground Handling ..............
  • Page 256 SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER ill • THIS PAGE INTENTIONALLY LEFT BLANK • REPORT: VB-2749 ISSUED: December 22, 2017 8-ii...
  • Page 257 STC installations. \\' A RNING Modifications must be approved in writing by PIPER prior to installation. Any and all other installations, whatsoever, of any kind will void • this warranty in it's entirety . ISSUED: December 22, 2017...
  • Page 258 HANDLING, SERV & MAINT PA-28-181, ARCHER III • GENERAL (continued) \VARNI�G 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...
  • Page 259 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 260 PIPER'S maintenance/service manuals and parts catalogs are no longer applicable and the purchaser is warned not to rely on such data for non-PIPER parts. All inspection intervaJs, replacement time limits, overhaul time limits, the method of inspection, life limits, cycle limits, etc., for such non-PIPER parts must be obtained from the...
  • Page 261 SECTIONS HANDLING, SERV & MAINT PA-28-181, ARCHER III • 8.3 AIRPLANE INSPECTION PERIODS (continued) 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 262 SECTIONS PA-28-181, ARCHER ID HANDLING, SERV & MAINT 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. I 3-2, when performed by an A & P mechanic, may be approved by the local FAA office.
  • Page 263 SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER ID • 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 264 SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER Ill • 8.9 GROUND HANDLING (continued) (b) Taxiing (continued) (4) When taxiing over uneven ground, avoid holes and ruts. (5) Do not operate the engine at high RPM when running up or taxiing over ground containing loose stones, gravel, or any loose material that may cause damage to the propeller blades.
  • Page 265 SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER III • 8.9 GROUND HANDLING (continued) (d) Mooring The airplane should be moored for immovability, security and protection. The following procedures should be used for the proper mooring of the airplane: (I) Head the airplane into the wind if possible.
  • Page 266 SECTION 8 PA-28-181, ARCHER Ill HANDLING, SERV & MAINT 8.11 ENGINE AIR FILTER Inspect inlet f o r f o reign particles and obstructions. Engine Air Filter should . ­ be removed and inspected or replaced at intervals as outlined in the aircraft Maintenance Manual.
  • Page 267 SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER III ,,,,..- • • 1. BRAKE RESERVOIR 2. RIGHT BRAKE AND RUDDER PEDAL 3. LEFT BRAKE AND RUDDER PEDAL 4. RIGHT BRAKE CYLINDER 5. LEFT BRAKE CYLINDER 6. BRAKE HANDLE 7. HANDLE RELEASE BUTTON 8.
  • Page 268 SECTIONS PA-28-181, ARCHER III HANDLING, SERV & MAINT 8.15 LANDING GEAR SERVICE The three landing gears use Cleveland Aircraft Products 6.00 x 6, four-ply • rating, type III tires with tubes. (Refer to paragraph 8.23). Landing gear oleos on the ARCHER should be serviced according to the instructions on the units.
  • Page 269 SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER • 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 270 SECTION 8 PA-28-181, ARCHER ill HANDLING, SERV & MA INT • 8.21 FUEL SYSTEM (continued) (c) Filling Fuel Tanks Observe all required precautions for handling gasoline. Fill the fuel tanks through the filler located on the forward slope of the wing. Each wing holds a maximum of 25 U.S.
  • Page 271 SECTIONS PA-28-181, ARCHER ill HANDLING, SERV & MAINT • 8.21 FUEL SYSTEM (continued) �..___, �� • 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 272 SECTION 8 PA-28-181, ARCHER III HANDLING, SERV & MAINT 8.23 TIRE INFLATION For maximum service from the tires, keep them inflated to the proper • pressures - 18 psi f o r the nose gear and 24 psi f o r 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 273 SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER Ill • 8.27 CLEANING (a) Cleaning Landing Gear Before cleaning the landing gear, place a plastic cover or similar material over the wheel and brake assembly. (I) Place a pan under the gear to catch waste. (2) Spray or brush the gear area with solvent or a mixture of solvent and degreaser, as desired.
  • Page 274 SECTION 8 HANDLING, SERV & MA INT PA-28-181, ARCHER ill • 8.27 CLEANING (continued) (c) 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.
  • Page 275 SECTION 8 PA-28-181, ARCHER ID HANDLING, SERV & MAINT • 8.27 CLEANING (continued) (e) Cleaning Carpets To clean carpels, 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 276 SECTION 8 PA-28-181, ARCHER ill HANDLING, SERV & MAINT • • THIS PAGE INTENTIONALLY LEFT BLANK • REPORT: VB-2749 ISSUED: December 22, 2017 8-20...
  • Page 277 SECTION 9 SUPPLEMENTS PA-28-181, ARCHER III • TABLE OF CONTENTS SECTION 9 SUPPLEMENTS Page Paragraph General ..................
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  • Page 279: General

    SECTION9 SUPPLEMENTS PA-28-181, ARCHER III • SECTION 9 SUPPLEMENTS 9.1 GENERAL This section provides information in the form of Supplements which are necessary for ef icient operation of the airplane when equipped with one or more of the various optional systems and equipment not approved with the standard airplane.
  • Page 280 SECTION 9 SUPPLEMENTS PA-28-181, ARCHER Ill • THIS PAGE INTENTIONALLY LEFT BLANK • REPORT: VB-2749 ISSUED: December 22, 2017...

  • Page 281: Air Conditioning Installation

    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 99575-13. 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 282 SECTION9 SUPPLEMENT 1 PA-28-181, ARCHER ill SECTION 1 - GENERAL This supplement supplies information necessary for the efficient opera- • lion of the airplane when the optional air conditioning system is installed. The information contained· within this supplement is to be used "as described" in conjunction with the complete handbook.
  • Page 283 SECTION 9 PA-28-181, ARCHER ill SUPPLEMENT 1 Advisory Messages - White Checklist • CAS Event CAS Message Page Cause Non-hidden CAS Messa es Air Conditioning Air conditioning condenser AC DOOR OPEN door is open Door Open 3.5 EMERGENCY PROCEDURES CHECK LIST Air Conditioning Door Open Indication: Master Caution, Double Chime, AC DOOR OPEN...
  • Page 284 SECTION 9 PA-28-181, ARCHER Ill SUPPLEMENT 1 SECTION 5 • PERFORMANCE Operation of the air conditioner will cause slight decreases in cruise speed • and range. Power from the engine is required to run the compressor, and the condenser door, when extended, causes a slight increase in drag. When the air conditioner is turned off there is normally no measurable difference in climb, cruise or range performance of the airplane.
  • Page 285 SECTION9 SUPPLEMENT 1 PA-28-181, ARCHER Ill • SECTION 7 - DESCRIPTION AND OPERATION The air conditioning system is a recirculating air system. The major items include: evaporator, condenser, compressor, blower, switches and temperature controls. The evaporator is located behind the left rear side of the baggage com­ partment.
  • Page 286 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 1 • SECTION 7 - DESCRIPTION AND OPERATION (continued) An "AC DOOR OPEN" CAS advisory alert will appear on the PFD whenever the condenser door is open and remains on until the door is closed.
  • Page 287 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVE! � Eric � W •• ODA-5I0620-CE Piper Aircraft, Inc. Vero Beach, Florida • DATE OF APPROVAL: May 7. 2018 REPORT: VB-2749 ISSUED: December 22, 2017...
  • Page 288 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 2 SECTION 1 - GENERAL The Bendix/King Digital ADF is a panel mounted, digitally tuned, automatic • direction finder. lt is designed to provide continuous I kHz digital tuning in the frequency range of200 kHz to 1799 kHz and eliminates the need for mechanical band switching.
  • Page 289 SECTION 9 PA-28-181, ARCHER lll SUPPLEMENT 2 • SECTION 4 - NORMAL PROCEDURES To Operate as an Automatic Direction Finder: l. OFF/VOL Control 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 290 SECTION 9 SUPPLEMENT 2 PA-28-181, ARCHER • 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 bullon, then transferred to active use by pressing the FRQ button again.
  • Page 291 SECTION 9 PA-28-181, ARCHER Ill SUPPLEMENT 2 • SECTION 4 - NORMAL PROCEDURES (continued) ADF Operation NOTES: Erroneous ADF Bearing D11e Radio Frequenc,· 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 condi­ tions, such as Night Effect, may cause signals from such stations to overlap.
  • Page 292 SECTION 9 PA-28-181, ARCHER ID SUPPLEJ\ilENT 2 • SECTION 5 - PERFOR1\1ANCE No change. SECTION 6 - WEICHT AND BALANCE Factory installed optional equipment is included in the certified weight and balance data in Section 6 or the Pilot's Operating Handbook and Airplane Flight Manual.
  • Page 293 SECTION 9 SUPPLEMENT 2 PA-28-181, ARCHER • SECTION 7 - DESCRIPTION AND OPERATION KR-87 Digital ADF • T�/REF �T • ADF Displays on Garmin PFD DigiLal ADF Operating Controls and PFD Indicator Figure I REPORT: VD-2749 ISSUED: 22, 2017 December REVISED: May 7, 2018 7 of 10 9-15...
  • Page 294 SECTION9 SUPPLEMENT 2 PA-28-181, ARCHER Ill SECTION 7 - DESCRIPTION AND OPERATION (continued) Legend - Figure I • I. Mode Annunciation Antenna (ANT) is selected by the "out" position the ADF button. This mode improves the aural reception and is usually used for station idcntil' i cation.
  • Page 295 SECTION 9 SUPPLEMENT 2 PA-28-181, ARCHER ill • SECTION 7 · DESCRIPTION AND OPERATION (continued) Legend • Figure I (continued) 6. Timer Mode AnnunciaLion EiLher Lhe elapsed time (ET) or flight time (FLT) mode is annunciated here. 7. Frequency Selector Knobs - Selects the standby frequency when FRQ is displayed and directly selects the active f equency whenever either of the timer functions is selected.
  • Page 296 SECTION 9 PA-28-181, ARCHER ill SUPPLEMENT 2 • • THIS PAGE INTENTIONALLY LEFT BLANK • .REPORT: VB-2749 ISSUED: December 22, 2017 I0ofl0 REVISED: May 7, 2018 :9-18,...

  • Page 297: Bendix/King Kn-63 Dme

    Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVEf � r· g ht ODA-510620-CE Piper Aircraft, Inc. Yero Beach, Florida • DATE OF APPROVAL: Dccember22, 2017 REPORT: VB-2749 ISSUED: December 22, 2017 lof4...
  • Page 298 SECTION 9 PA-28-181, ARCHER HI SUPPLEMENT SECTIO 1 - GENERAL The Bendix/King KN-63 DME supplies continuous slant range distance infor- mation from a lixed ground station to an aircraft in llighl. • The equipment consists of a Garmin Primary Flight Display (PFD) which con­ tains all the operating controls and displays, and a remotely mounted KN-63 Recei vcr-Transm iller.
  • Page 299 SECTION9 SUPPLEMENT 3 PA-28-181, ARCHER ill • SECTION 7 - DESCRIPTION AND OPERATION DME Display on Garmin PFD Figure 1 Legend - Figure 1 I. DME Information Window 2. DME MODE ANNUNCIATOR j I.' , l'�H ·,· 17.3[; Displays the DME operating mode; NA V I or NA V 2 4.6NH or HOLD selected in the DME TUNING window.
  • Page 300 SECTION 9 SUPPLEMENT 3 PA-28-181, ARCHER III • SECTION 7 - DE SCRIPTION AND OPERATION (continued) Legend - Figure 1 (continued) 5. DME TUNING Window (NA VI, NA V2, HOLD) Allows access to the DME operating mode as follows: NA V 1 Selects DME operation with No.

  • Page 301: Appareo Vision 1000 Unit

    • FAA Approved Airplane Flight Manual when the optional Appareo Vision 1000 unit is installed in accordance wilh Piper Drawing I 07420. 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 302 SECTION9 SUPPLEMENT 4 PA-28-181, ARCHER ID SECTION I -GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Appareo Vision 1000 unit is installed. The • information contained within this supplement is to be used "as described" in conjunction with the complete handbook.
  • Page 303 SECTION9 SUPPLEMENT 4 PA-28-181, ARCHER ITT SECTION 4 - NORMAL PROCEDURES (continued) • Status Indicators: Tuble 1: LED Status LEDStatus Configuralion Item Fault detected: Refer to ICA Blue Booting Operating Green SD card not inserted: insert SD card and verify Green LED Yellow SD card not format ed correctly: format SD to NTSF, verify...
  • Page 304 SECTION9 PA-28-181, ARCHER III SUPPLElVIENT 4 SECTION 7- DESCRIPTION AND OPERATION The Vision I 000 system is a data gathering system utilizing global positioning, image capturing, flight attitude acquisition, and ambient audio recording. It • will record the aircraft's airf ame attitudes, rates, accelerations, GPS position, and record cockpit audio and images.

  • Page 305: Flightcom Model 403 Intercom

    • FAA Approved Airplane Flight Manual when the optional Flightcom model 403 intercom is installed in accordance with Piper Drawing 107421. 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 306 SECTION9 PA-28-181, ARCHER III SUPPLEMENT S • SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Flightcom model 403 intercom is installed. The information contained within this supplement is to be used in conjunction with the complete handbook.
  • Page 307 SECTION9 SUPPLEMENT 5 PA-28-1 8 1 , ARCHER ID • SECTION 4 - NORMAL PROCEDURES (continued) Adjusting the Intercom and Headsets (continued) NOTE Noise canceling microphones will not operate correctly if they are more than l/8" from the mouth. While speaking loudly, adjust the ICS volume controls on the Garmin audio panel to set the pilot and copilot volumes to a comfortable level.
  • Page 308 SECTION 9 SUPPLEMENT 5 PA-28-181, ARCHER ill • SECTION 4 - NORMAL PROCEDURES (continued) Isolate Switch For normal intercom and transmit operations, place the Isolate switch in the ICS position. To isolate the passengers from transmitting and receiving radio communications, place the Flightcom 403 Isolate switch in the Isolate position. Placing the Isolate switch in this position will allow continued use of the intercom between copilot and passengers.
  • Page 309 This supplement must be allached to the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual when the Carbureted 0-360 Engine is installed in accordance with Piper Drawing l09002-00 I. 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 310 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 6 SECTION 1 • GENERAL This supplement supplies information necessary for the operation of the • airplane when the Carbureted 0-360 Engine is installed. The information contained within this supplement is to be used "as described" in conjunction with the complete handbook.
  • Page 311 SECTION9 SUPPLEMENT 6 PA-28-181, A RCHER Ill • SECTION 3 - EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST NOTE Only those Emergency Procedures that are specific to a Carbureted engine, are provided in this supplement. Refer to Pilot Operating Handbook Section 3 for all Emergency Procedures. 3.5b Engine Powe1- Loss Engine Power Loss During Takeoff If sufficient runway remains for a complete stop:...
  • Page 312 SECTION9 PA-28-181, ARCHER III SUPPLEMENT 6 • EMERGENCY PROCEDURES CHECK LIST (continued) 3.Sb Engine Power Loss (continued) Engine Power Loss In Flight Airspeed ..............MAINTAIN 76 KIAS FUEL Selector..............SWITCH to tank containing fuel FUEL PUMP ..................ON MIXTURE ..................RICH CARB HEAT ..................
  • Page 313 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 6 • EMERGENCY PROCEDURES CHECK LIST (continued) 3.5j Carburetor Icing Carburetor Icing CARB HEAT ..................ON MDCTURE ..............Adjust for Maximum Smoothness Under certain moist atmospheric conditions at temperatures of -5 C to °...
  • Page 314 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 6 • El\ilERGENCY PROCEDURES CHECK LIST (continued) 3.Sk Engine Roughness ENGINE ROUGHNESS NOTE Partial carburetor heat may be worse than no heat at all, since it may melt part of the ice, which will refreeze in the intake system. When using...
  • Page 315 SECTION9 SUPPLEMENT 6 PA-28-181, ARCHER III • SECTION 4 - NORMAL PROCEDURES NOTE Only those Normal Procedures that are specific to a Carbureted en g ine, are provided in this supplement. Refer to Pilot Operating Handbook Section 4 for all Normal Procedures.
  • Page 316 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 6 • 4.5c Before Starting Engine Checklists (continued) E VOLTS lndication ........... 23.3 VOLTS (Minimum) Verify operation of: • PFD with no red-x's on: • Altitude • Airspeed • Altitude • Vertical Speed • Audio Panel •COMl...
  • Page 317 SECTION9 PA-28-181, ARCHER Ill SUPPLEMENT 6 • 4.Sd Engine Start Checklists (continued) NORMAL START - HOT ENGINE THROTILE ................1/2 IN. OPEN BA TI MASTR Switch ................ON AL TR Switch ..................ON LEFf MAG Switch ................ON FUEL PUMP ..................ON MIXTURE ................
  • Page 318 SECTION 9 PA-28-181, AR CHER III SUPPLEMENT 6 • 4.Sd Engine Start Checklists (continued) ENGINE START - FLOODED CAUTION If engine does not start and/or any indication of fire or smoke is present, immediately execute the emergency procedure for Engine Fire During Start.
  • Page 319 SECTION9 SUPPLEMENT 6 PA- 2 8-181, ARCHER ill • 4.Sd Engine Start Checklists (continued) ENGINE START - USING EXTERNAL POWER SOURCE N OTE The EMERG BA TT switch may remain ON while using external power. The emergenc y bus does not receive power from the external power source due to a relay in the circuit.
  • Page 320 SECTION 9 PA-28-181, ARCHER ill SUPPLEMENT 6 • 4.Sg Ground Check Checklist GROUND CHECK PARK BRAKE ..................SET THROTTLE ................2000 RPM LEFT/RIGHT MAG Check ........MAX. DROP 175 RPM MAX. DIFF. 50 RPM Oil Temperature ................CHECK Oil Pressure ..................CHECK VOLTS lndication ........
  • Page 321 SECTION 9 SUPPLEMENT 6 PA-28-181, ARCHER Ill • 4.Sh Before Takeoff Checklist BEFORE TAKEOFF BA TI MASTR Switch ............VERIFY ON AL TR Switch ................. VERIFY ON FUEL PUMP ..................ON LEFT/RIGHT MAG Switches ...... , ......VERIFY ON Flight Instruments ................CHECK Standby Flight Instruments ............
  • Page 322 SECTION9 SUPPLEMENT 6 PA-28-181, ARCHER III • 4.51 Descent Checklist DESCENT Normal Descent: THROTTLE ................2500 RPM Airspeed ..................I 22 KTAS MIXTURE ..................RICH CARB HEAT ............... ON IF REQUIRED Power Off Descent: CARB HEAT ............... ON IF REQUIRED THROTTLE .................
  • Page 323 SECTION9 SUPPLEMENT 6 PA-28-181, ARCHER III • SECTION 5 - PERFORMANCE No change. SECTION 6 - WEIGHT AND BALANCE No change. SECTION 7 - DESCRIPTION AND OPERATION 7. 5 ENGINE AND PROPELLER The ARCHER Ill is powered by a four cylinder, direct drive, horizontally opposed engine rated at 180 horsepower at 2700 rpm.
  • Page 324 SECTION 9 SUPPLEMENT 6 PA-28-181, ARCHER III 7.9 ENGINE CONTROLS A carburetor heat control is located on the insu·ument panel right of the conLrol quadrant. The conLrol displays two positions: ON (down), OFF (up). • 7.19 FUEL SYSTEM An electric engine priming system is provided to facilitate starting. The primer switch is located right of tbe starter switch in the overhead switch panel (see Fig.
  • Page 325 SECTION 9 SUPPLEMENT 6 PA-28-181, ARCHER III • 7.19 FUEL SYSTEM (continued) CARBURETOR ,UIIRow ,,._.ton MUL Tl FIJMCTIOM 0'.$P\.AY PRIMARY FllGKT FUEL 00$1'1.AY (R•viMClnWVMode Onttl -PRIMER SOLENOID ENGINE FUEL PUMP • ELECTRIC FUEL PUMP RELAY � PRIMER SWITCH ELECTRIC FUEL PUMP...
  • Page 326 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 6 • �� �s • • • ,-.. <D o �� o <O ..• � I» • • ,-.. • ..• 0 000000 ·- "O � �� .., C") ..·- §...
  • Page 327 • • • "'C ► �� �� 13. Electrical accessories (L to R) l. Standby instrument V'J� � a) Flight director/ autopilot switch (option) a) Aspen EBD-1000 .. 0 3:: � b) Pitot heat b)Garmin G5 � � n O" =- �...
  • Page 328 SECTION9 PA-28-181, ARCHER III SUPPLEMENT 6 • I 7.23 INSTRUMENT PANEL (continued) 1 m 1 � ·oo ,::;­ ..• .., [Jill • OVERHEAD SWITCH PANEL Figure 7-10 REPORT: VB-2749 ISSUED: December 22, 2017 9-50, 20 of 22 REVISED: July 31, 2018...
  • Page 329 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 6 • SECTION 8 - HANDLING, SERVIClNG, AND MAINTENANCE 8.21 FUEL SYSTEM (a) Servicing Fuel System At every 50 hour inspection, the fuel screens in the strainer, in the electric fuel pump, and at the carburetor inlet must be cleaned .
  • Page 330 SECTION 9 PA-28-181, ARCHER ill SUPPLEMENT 6 • • THIS PAGE INTENTIONALLY LEFT BLANK • REPORT: VB-2749 ISSUED: December 22, 2017 9-52, 22 of 22...
  • Page 331 SECTION 9 SUPPLEMENT 7 PA-28-181, ARCHER Ill • PILOT'S OPERA TING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 7 AMSAFE INFLATABLE SEAT RESTRAINTS (FAA STC SA02276AK) (EASA STC 10031010) The FAA approved operational supplement for the AMSAFE Inflatable Seat Restraints, installed in accordance with STC SA02276AK, is required for •...
  • Page 332 SECTION PA-28-181, AR CHER Ill SUPPLEMENT 7 • • THIS PAGE INTENTIONALLY LEFT BLANK • REPORT: VB-2749 ISSUED: December 22, 2017 9-54...
  • Page 333 SECTION 9 SUPPLEMENT 8 PA-28-181, ARCHER ill • PILOT'S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 8 CONTINENTAL AEROSPACE TECHNOLOGIES DIESEL ENGINE (TAE 125-02-114) INSTALLATION (FAA STC SA03303A T) (EASA STC 10014364) The FAA approved operational supplement for the Continental Aerospace Technologies diesel engine (T AE 125-02-114) installation, installed in •...
  • Page 334 SECTION9 PA-28-181, ARCHER III SUPPLEMENT 8 • • TIDS PAGE INTENTIONALLY LEFT BLANK • REPORT: VB-274 9 ISSUED: December 22, 201 7 I 9-56 REVISED: August 29, 2019...
  • Page 335 Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein. For limitations, procedures and performance information not contained in this supplement, consult the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: PIPER AIRCRAFT, INC. • VERO BEACH, FLORIDA DATE OF APPROVAL: -�M�...
  • Page 336 SECTION9 SUPPLEMENT 9 PA-28-181, ARCHER III SECTION 1 - GENERAL The Safe Flight Angle of Attack (AoA) Indexer, referred to as the "AoA Indicator" or simply "display" in this supplement, is a system that receives and • displays angle of attack information from the lift transducer vane installed in the right wing of the aircraft.
  • Page 337 SECTION9 PA-28-181, ARCHER SUPPLEMENT 9 • SECTION 4 - NORMAL PROCEDURES 4.Se BEFORE T AXllNG A VION MASTER Switch .., ... , ............ON Ao A Indicator......, ....... VERIFY SELF TEST AoA Indication ..........lights illuminated (not blank) NOTE If AoA indications are suspected to not be accurate, discontinue use of the AoA Indicator.
  • Page 338 SECTION 9 PA-28-181, ARCHER ill SUPPLEMENT 9 • 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 339 SECTION 9 SUPPLEMENT 9 PA-28-181, ARCHER ill • SECTION 7 - DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS (continued) The lights on the display shown in Figure 7-1 are a general representation of angle of attack. l. Stall is imminent or stall is occurring. 2.
  • Page 340 SECTION9 PA-28-181, ARCHER III SUPPLEMENT 9 • SECTION 7 - DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS (continued) NOTE If AoA indications are suspected to not be accurate, discontinue use of the AoA Indicator. The reference marker can be set to a target angle of attack f o r the desired phase of flight.
  • Page 341 SECTION9 SUPPLEMENT PA-28-181, ARCHER ill • SECTION 8 - AIRPLANE HANDLING, SERVICING, AND MAINTENANCE The Safe Flight AoA indicating system is not field repairable. If the operation of the system is in doubt, apply power to the system and verify that the power-on self-test has completed properly.
  • Page 342 SECTION9 SUPPLEMENT 9 PA-28-181, ARCHER lil • • THIS PAGE INTENTIONALLY LEFT BLANK • ISSUED: December 22, 2017 REPORT: VB-2749 9-64, REVISED: March 27, 2020 s ors...
  • Page 343 SECTION9 SUPPLEMENT 10 PA-28-181, ARCHER III • PILOT'S OPERA TING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. IO SECOND OIL COOLER 171is supplement must be attached to the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual when a second oil cooler system is •...
  • Page 344 SECTION9 SUPPLEMENT 10 PA-28-181, ARCHER ill SECTION 1 - GENERAL An optional second oil cooler is intended co increase the operational flexibility of the aircraft in extreme high temperature environments. • 1.11 OIL (a) Oil Capacity (U.S. quarts) NOTE With the addition of the second oil cooler and associated hoses, the total capacity of the oil system will be approximately 9 quarts.
  • Page 345 SECTION9 SUPPLEMENT 10 PA-28-181, ARCHER Ill • 2. 9 POWERPLANT INSTRUMENT MARKINGS (d) Cylinder Head ° Green Band (Normal Operating Range) Cp to 490 ° Yellow Band (Caution Range) p to 500 ° Red Band (Maximum) Above 500 SECTION 3 - EMERGENCY PROCEDURES 3.1 GENRRAL Crew Alerting System (CAS) : M essages Warning Messages - Red...
  • Page 346 SECTION9 PA-28-181, ARCHER III SUPPLEMENT 10 • EMERGENCY PROCEDURES CHECKLIST 3.5l Cylinder Head Temperature Cylinder Head Temperature Indication: Master Caution, Double Chime, CYLHDTEMP ENGINE PAGE ................SELECT Cylinder Head Temperatures ............ MONITOR THROTTLE ............. Consider REDUCING MIXTURE ............Consider ENRICHENING Airspeed ...............
  • Page 347 SECTION9 SUPPLEMENT 10 PA-28-181, ARCHER III • SECTION 4 - NORMAL PROCEDURES No change . SECTION 5 - PERFORMANCE No change. SECTION 6 - WEIGHT AND BALANCE Factory installed optional equipment is included in the certified weight and balance data in Section 6 of the Pilot's Operating Handbook and Airplane Flight Manual.
  • Page 348 SECTION9 PA-28-181, ARCHER III SUPPLEMENT 10 • SECTION 8 - AIRPLANE HANDLlNG, SERVIClNG, AND MAINTENANCE 8.19 OIL REQUIREMENTS NOTE With the addition of the second oil cooler and associated hoses, the total capacity of the oil system will be approximately 9 quarts. However,...
  • Page 349 For limitations, procedures and performance information not contained in this supplement, consult the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: SCOTT EDWARDS ODA-510620-CE PIPER AIRCRAFT, INC. • VERO BEACH, FLORIDA DA TE OF APPROVAL: --=-Ju= l 1= 5 ,c..:2= 0 =20 ..,,...
  • Page 350 SECTION9 PA-28-181, ARCHER III SUPPLEMENT 11 • SECTION 1 - GENERAL No change. SECTION 2 - LIMIT A TIO NS No change. SECTION 3 - EMERGENCY PROCEDURES No change. SECTION 4 - NORMAL PROCEDURES No change. SECTION 5 - PERFORMANCE •...
  • Page 351 SECTION9 SUPPLEMENT 11 PA- 2 8- 1 81, ARCHER III • SECTION 7 - DESCRIPTION AND OPERATION 7. 1 9 FUEL SYSTEM The fuel system is modified by the addition of a fuel return system, including a different fuel selector valve. Unused excess fuel is returned from the...
  • Page 352 SECTION 9 SUPPLEMENT 11 PA-28-181, ARCHER III • FUEL NOZZLE FUEL FLOW DISPLAY . .• ---· GAAM-NfNOOE · .. FLOW METER A�AAME INTERfACE COEA 11) FUEL INJECTION SERVO _.,.- ,,,,.,-- ENGINE DRIVEN OPTIONAL: VAPOR RETURN LINE .,,,,,,- FUEL PUMP NOTC 1: rucL rLOW l:l rROM Tl IC rucL INJECTION SERVO TO THE LORR TANK.
  • Page 353 SECTION 10 OPERATING TIPS PA-28-181, ARCHER III • TABLE OF CONTENTS SECTION 10 OPERA TING TIPS Page Paragraph 10-1 L0.l General..................I 0.3 Operating Tips................I 0-1 • • REPORT: VB-2749 ISSUED: December 22, 2017 10-i...
  • Page 354 SECTION 10 PA-28-181, ARCHER Ill OPERA TING TIPS • TIDS PAGE INTENTIONALLY LEFf BLANK • ISSUED: December 22, 2017 REPORT: VB-2749 10-ii...
  • Page 355 SECTION 10 PA-28-181, ARCHER III OPERA TING TIPS • SECTION 10 OPERA TING 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 356 SECTION 10 OPERATING TIPS PA-28-181, ARCHER III 10.3 OPERA TING TlPS (continued) (f) Anti-collision lights should not be operating when flying through cloud, • fog or haze, since reflected light can produce spacial disorientation. Strobe lights should not be used in close proximity to the ground such as during taxiing, takeof or landing.

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Pa-28-181

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