Page 2 REPORT: VB-2749 FAA APPROVED BY: _______________________________ ERIC A. WRIGHT O.D.A. 510620-CE DATE OF APPROVAL: PIPER AIRCRAFT, INC. DECEMBER 22, 2017 VERO BEACH, FLORIDA FAA APPROVED IN NORMAL AND UTILITY CATEGORIES BASED ON CAR 3. THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY CAR 3 AND CONSTITUTES THE APPROVED AIRPLANE FLIGHT MANUAL AND MUST BE CARRIED IN THE AIRPLANE AT ALL TIMES.
Page 3 PA-28-181, ARCHER III Published by TECHNICAL PUBLICATIONS Issued: December 22, 2017 © 2017–2018 PIPER AIRCRAFT, INC. All Rights Reserved REPORT: VB-2749 ISSUED: December 22, 2017 REVISED: May 7, 2018...
Page 4 PA-28-181, ARCHER III APPLICABILITY Application of this handbook is limited to the specific Piper PA-28-181 model airplane designated by serial number and registration number on the face of the title page of this handbook. This handbook cannot be used for operational purposes unless kept in a current status.
Page 5 PA-28-181, ARCHER III 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 6 PA-28-181, ARCHER III PILOT’S OPERATING HANDBOOK LOG OF REVISIONS Current Revisions to the PA-28-181 ARCHER III Pilot’s Operating Handbook, REPORT: VB-2749 issued December 22, 2017. Revision FAA Approval Number and Revised Description of Revisions Signature and Code Pages Date Rev. 1 Updated copyright.
Page 7 PA-28-181, ARCHER III PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (continued) Revision FAA Approval Number and Revised Description of Revisions Signature and Code Pages Date REPORT: VB-2749 ISSUED: December 22, 2017...
Page 8 PA-28-181, ARCHER III TABLE OF CONTENTS SECTION 1 GENERAL SECTION 2 LIMITATIONS SECTION 3 EMERGENCY PROCEDURES SECTION 4 NORMAL PROCEDURES SECTION 5 PERFORMANCE SECTION 6 WEIGHT AND BALANCE SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS SECTION 8 AIRPLANE HANDLING, SERVICING AND MAINTENANCE SECTION 9...
Page 9 PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-2749 ISSUED: December 22, 2017 viii...
Page 10: Table Of Contents
SECTION 1 PA-28-181, ARCHER III GENERAL TABLE OF CONTENTS SECTION 1 GENERAL Paragraph Page Introduction ................Notations ..................Engine ..................Propeller ..................Fuel ..................1.11 ..................1.13 Maximum Weights ..............1.15 Standard Airplane Weights ............1.17 Baggage Space ................1.19 Specific Loadings ...............
Page 11 SECTION 1 GENERAL PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-2749 ISSUED: December 22, 2017 1-ii...
Page 12: Introduction
SECTION 1 PA-28-181, ARCHER III GENERAL SECTION 1 GENERAL 1.1 INTRODUCTION This Pilot’s Operating Handbook is designed for maximum utilization as an operating guide for the pilot. It includes the material required to be furnished to the pilot by F.A.R./C.A.R. It also contains supplemental data supplied by the airplane manufacturer.
Page 13 SECTION 1 GENERAL PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-2749 ISSUED: December 22, 2017...
Page 14: Notations
SECTION 1 PA-28-181, ARCHER III GENERAL NOTATIONS WARNING 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 equipment if not carefully followed or the need for immediate crew awareness and possible need for future corrective action.
Page 15 SECTION 1 GENERAL PA-28-181, ARCHER III THREE VIEW Figure 1-1 REPORT: VB-2749 ISSUED: December 22, 2017...
Page 16: Engine
SECTION 1 PA-28-181, ARCHER III GENERAL 1.5 ENGINE (a) Number of Engines (b) Engine Manufacturer Lycoming (c) Engine Model Number (1) Fuel Injected IO-360-B4A (d) Takeoff Power (BHP) (e) Takeoff Power Engine Speed (RPM) 2700 (f) Bore (inches) 5.125 (g) Stroke (inches) 4.375 (h) Displacement (cubic inches) 361.0...
Page 17: Oil
SECTION 1 GENERAL PA-28-181, ARCHER III 1.11 OIL (a) Oil Capacity (U.S. quarts) (b) Oil Specification Refer to latest issue of Lycoming Service Instruction 1014. (c) Oil Viscosity per Average Ambient Temp. for Starting Single Multi (1) Above 60°F S.A.E. 50 S.A.E.
Page 18: G1000 Gnss (Gps/Sbas) Navigation System Equipment Approvals
SECTION 1 PA-28-181, ARCHER III GENERAL 1.21 G1000 GNSS (GPS/SBAS) NAVIGATION SYSTEM EqUIPMENT APPROVALS The Garmin G1000 Integrated Avionics GNSS navigation system installed in this aircraft is a GPS system with a Satellite Based Augmentation System (SBAS) comprised of two ETSO-145/TSO-C145d Class 3 approved Garmin GIA 64Ws, ETSO-146/TSO-C146d Class 3 approved Garmin GDU Display Units (1050 and 1054) and two GA36 GPS antennas (one is a GA37 if optional GDL 69 is installed).
Page 19 SECTION 1 GENERAL PA-28-181, ARCHER III 1.21 G1000 GNSS (GPS/SBAS) NAVIGATION SYSTEM EqUIPMENT APPROVALS (continued) The Garmin G1000 Integrated Avionics GNSS navigation system as installed in this aircraft complies with the equipment requirements of AC 90-105A and meets the equipment performance and functional requirements to conduct RNP terminal departure and arrival procedures and RNP approach procedures without RF (radius to fix) legs.
Page 20: Symbols, Abbreviations And Terminology
SECTION 1 PA-28-181, ARCHER III GENERAL 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 21 SECTION 1 GENERAL PA-28-181, ARCHER III 1.23 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (continued) Never Exceed Speed or Mach Number is the speed limit that may not be exceeded at any time. Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution.
Page 22 SECTION 1 PA-28-181, ARCHER III GENERAL 1.23 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (continued) Indicated T h e n u m b e r a c t u a l l y r e a d f r o m a n Pressure Altitude altimeter when the barometric subscale has been set to 29.92 inches of mercury (1013.2...
Page 23 SECTION 1 GENERAL PA-28-181, ARCHER III 1.23 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (continued) (e) Avionics System Abbreviations/Terminology Refers to pilot’s side (ADAHRS1, ADC1, GPS1) Refers to co-pilot’s side (ADAHRS2, ADC2, GPS2) ADAHRS Air Data, Attitude and Heading Reference System AFCS Automatic Flight Control System Crew Alerting System Evolution Backup Display (Aspen standby instrument) Engine Indication System...
Page 24 SECTION 1 PA-28-181, ARCHER III GENERAL 1.23 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (continued) (f) Airplane Performance and Flight Planning Terminology Accelerate-Stop The distance required to accelerate an airplane Distance to a specified speed and, assuming failure of an engine at the instant that speed is attained, to bring the airplane to a stop.
Page 25 SECTION 1 GENERAL PA-28-181, ARCHER III 1.23 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (continued) Datum An imaginary vertical plane from which all horizontal distances are measured for balance purposes. Basic Empty Standard empty weight plus optional Weight equipment. Maximum Maximum weight approved for the landing Landing Weight touchdown.
Page 26 SECTION 2 PA-28-181, ARCHER III LIMITATIONS TABLE OF CONTENTS SECTION 2 LIMITATIONS Paragraph Page General ..................Airspeed Limitations ..............Airspeed Indicator Markings ............Powerplant Limitations .............. Powerplant Instrument Markings ..........2.11 Systems Limitations ..............2.13 Weight Limits ................2.15 Center of Gravity Limits ............2.17 Maneuver Limits ................
Page 27 SECTION 2 LIMITATIONS PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-2749 ISSUED: December 22, 2017 2-ii...
Page 28: General
SECTION 2 PA-28-181, ARCHER III LIMITATIONS SECTION 2 LIMITATIONS 2.1 GENERAL This section provides the FAA Approved operating limitations, instrument markings, color coding and basic placards necessary for operation of the airplane and its systems. This airplane must be operated as a normal or utility category airplane in compliance with the operating limitations stated in the form of placards and markings and those given in this section and this complete handbook.
Page 29: Airspeed Indicator Markings
SECTION 2 LIMITATIONS PA-28-181, ARCHER III 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 30: Powerplant Limitations
SECTION 2 PA-28-181, ARCHER III LIMITATIONS 2.7 POwERPLANT LIMITATIONS (a) Number of Engines (b) Engine Manufacturer Lycoming (c) Engine Model No. (1) Fuel Injected IO-360-B4A (d) Engine Operating Limits (1) Rated Horsepower (BHP) (2) Max. Propeller Speed (RPM) 2700 (3) Max. Oil Temperature 245ºF (4) Oil Pressure Minimum (red line)
Page 31: Powerplant Instrument Markings
SECTION 2 LIMITATIONS PA-28-181, ARCHER III 2.9 POwERPLANT INSTRUMENT MARKINGS (a) Tachometer Green Arc (Normal Operating Range) 500 to 2700 RPM Red Line (Maximum) 2700 RPM (b) Oil Temperature Green Band (Normal Operating Range) 75° to 245°F Red Line (Maximum) 245°F (c) Oil Pressure Green Band (Normal Operating Range)
Page 32: Center Of Gravity Limits
SECTION 2 PA-28-181, ARCHER III LIMITATIONS 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) Utility Category Weight Forward Limit Rearward Limit Pounds...
Page 33: Maneuver Limits
SECTION 2 LIMITATIONS 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 Lazy Eights 113 KIAS Chandelles 113 KIAS 2.19 FLIGHT LOAD FACTORS...
Page 34: Garmin G1000 Avionics System Limitations
SECTION 2 PA-28-181, ARCHER III LIMITATIONS 2.25 GARMIN G1000 AVIONICS SYSTEM LIMITATIONS (a) Cockpit Reference & Pilot’s Guide The Garmin G1000 Cockpit Reference Guide P/N 190-02131-02 (latest appropriate revision) must be immediately available to the flight crew. Garmin also provides a detailed G1000 Pilot’s Guide P/N 190-02130-02 (latest appropriate revision).
Page 35 SECTION 2 LIMITATIONS PA-28-181, ARCHER III 2.25 GARMIN G1000 AVIONICS SYSTEM LIMITATIONS (continued) (c) Databases (1) Navigation Database GPS/SBAS based IFR enroute, oceanic and terminal navigation predicated upon the Garmin G1000 GPS Receiver is prohibited unless the pilot uses a valid, compatible, and current Navigation database or verifies each selected waypoint for accuracy by reference to current data.
Page 36 SECTION 2 PA-28-181, ARCHER III LIMITATIONS 2.25 GARMIN G1000 AVIONICS SYSTEM LIMITATIONS (continued) (d) Flight Planning (continued) When RAIM is required for GPS integrity (GPS WAAS SBAS not available) during instrument meteorological conditions (IMC), other non- GPS navigation equipment appropriate to the operation, must be available. When using GPS WAAS at an alternate airport, flight planning must be based on the minimums associated with the RNAV (GPS) LNAV, circling, or GPS or conventional approach procedure with “or GPS”...
Page 37 SECTION 2 LIMITATIONS PA-28-181, ARCHER III 2.25 GARMIN G1000 AVIONICS SYSTEM LIMITATIONS (continued) (f) Approaches (1) Vertical Guidance Advisory vertical guidance deviation information is only an aid to help pilots comply with altitude restrictions. When using advisory vertical guidance, the pilot must use the primary barometric altimeter to ensure compliance with all altitude restrictions, particularly during instrument approach operations.
Page 38 SECTION 2 PA-28-181, ARCHER III LIMITATIONS 2.25 GARMIN G1000 AVIONICS SYSTEM LIMITATIONS (continued) (g) Attitude and Heading Reference System (AHRS) (1) AHRS Operational Area Operation in the following regions is not authorized due to unsuitability of the magnetic fields near the Earth’s poles: •...
Page 39 SECTION 2 LIMITATIONS PA-28-181, ARCHER III 2.25 GARMIN G1000 AVIONICS SYSTEM LIMITATIONS (continued) (i) Datalink weather Display XM weather data is provided by an optional GDL 69 interface. The weather information display on the MFD is limited to supplemental use only and may not be used in lieu of an official weather data source.
Page 40 SECTION 2 PA-28-181, ARCHER III LIMITATIONS 2.25 GARMIN G1000 AVIONICS SYSTEM LIMITATIONS (continued) (m) Minimum fully functional equipment required for flight operations: Equipment Number Installed ADAHRS Magnetometer Standby Instrument - Attitude Standby Instrument - Airspeed Standby Instrument - Altimeter Standby Instrument - Heading If the PFD is inoperative during DAY or NIGHT VFR, the MFD must be operative.
Page 41: Gfc 700 Automatic Flight Control System (Afcs)
SECTION 2 LIMITATIONS PA-28-181, ARCHER III 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. 1000 feet AGL during cruise and descent operations. 200 feet AGL during approach operations.
Page 42: Aspen Standby Instrument Limitations
SECTION 2 PA-28-181, ARCHER III LIMITATIONS 2.29 ASPEN STANDBY INSTRUMENT LIMITATIONS The Aspen Evolution Backup Display (EBD) Pilot’s Guide P/N 091-00027-001, Revision A, or later appropriate revision, must be immediately available to the flight crew. Use of the EBD for IFR operations within 750 nautical miles of the magnetic North or South Pole, is NOT AUTHORIZED.
Page 43 SECTION 2 LIMITATIONS PA-28-181, ARCHER III 2.31 PLACARDS (continued) In full view of the pilot: NOTE Demonstrated crosswind values are NOT limitations. On the cockpit overhead panel: On lower left portion of instrument panel: In full view of the pilot, in the area of the air conditioner control panel when the air conditioner is installed: WARNING AIR CONDITIONER MUST BE OFF...
Page 44 SECTION 2 PA-28-181, ARCHER III LIMITATIONS 2.31 PLACARDS (continued) In full view of the pilot: WARNING TURN OFF STROBE L I G H T S W H E N I N CLOSE PROXIMITY G R O U N D D U R I N G F L I G H T T H R O U G H C L O U D , FOG OR HAZE.
Page 45 SECTION 2 LIMITATIONS PA-28-181, ARCHER III 2.31 PLACARDS (continued) On the right side of the fuselage aft of the wing: Adjacent to the filler caps: REPORT: VB-2749 ISSUED: December 22, 2017 2-18...
Page 46: Issued: December
SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Paragraph Page General ..................Crew Alerting System (CAS) Messages ........PFD Annunciations and Alerts ........... Aural Alerts ................Terminology ................Airspeeds for Safe Operation ............Emergency Procedures Checklist ........... 3.5a Fire .....................
Page 47: Issued: December
SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III TABLE OF CONTENTS (continued) SECTION 3 EMERGENCY PROCEDURES Paragraph Page 3.5e Avionics Failures (continued) ADAHRS Failures ..............3-25 Erroneous or Loss of Engine and Fuel Displays ....3-27 Erroneous or Loss of Warning/Caution CAS Messages ..3-28 COM1 and COM2 Failure .............
Page 48: General
The Garmin G1000 Cockpit Reference Guide for the Piper PA-28-181 Archer, Garmin p/n 190-02131-02 Rev. A or later appropriate revision, and the Garmin G1000 Pilot’s Guide for the Piper PA-28-181 Archer, Garmin p/n 190-02130-02 Rev. A or later appropriate revision, contain detailed descriptions of the annunciator system (CAS and Non-CAS) and all warnings, cautions and advisories.
Page 49: Crew Alerting System (Cas) Messages
SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III 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 G1000 displays. REPORT: VB-2749 ISSUED: December 22, 2017...
Page 50 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 Failure 3-18 Alternator is turned ON and has ALTR FAIL failed, as determined by voltage regulator.
Page 51 SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III 3.1 GENERAL (continued) Crew Alerting System (CAS) Messages (continued) Caution Messages - Amber Checklist CAS Event CAS Message Page Cause CAS Cautions with Text Messages CO Level High 3-41 CO level greater than or equal CO LVL HIGH to 50 but less than 200 parts per million (PPM).
Page 52 SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES 3.1 GENERAL (continued) Crew Alerting System (CAS) Messages (continued) Advisory Messages – White Checklist CAS Event CAS Message Page Cause 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 53: Pfd Annunciations And Alerts
Various aural alerts (voice or tone) may accompany PFD annunciations and alerts and no pilot action is required to acknowledge PFD annunciations and alerts. See Garmin G1000 Pilot’s Guide for the Piper PA28-181 Archer G1000 for additional information. Miscellaneous Annunciations...
Page 54: Aural Alerts
SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES 3.1 GENERAL (continued) PFD Annunciations and Alerts (continued) Aural Alerts Aural alerts are provided to alert the crew and call for their attention: • Master Warning - Repeating triple chime. • Master Caution - Non-repeating double chime. •...
Page 55: Fire
SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III AIRSPEEDS FOR SAFE OPERATION Stall Speeds 2550 lbs (0° Flaps) ..............50 KIAS 2550 lbs (Full Flaps) .............. 45 KIAS Maximum Operating Maneuvering Speeds 2550 lbs ................. 113 KIAS 1917 lbs ................... 98 KIAS Never Exceed Speed ..............
Page 56: Engine Fire In Flight
SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES EMERGENCY PROCEDURES ChECk LIST (continued) 3.5a Fire (continued) Engine Fire in Flight FUEL Selector..................OFF THROTTLE ................CLOSED MIXTURE ..............IDLE CUT-OFF FUEL PUMP ..................OFF HEAT/DEF (Defroster) ..............OFF If fire persists: Airspeed ........INCREASE in attempt to blow out fire Proceed with POWER OFF LANDING procedure.
Page 57: Electrical Fire In Flight
SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III EMERGENCY PROCEDURES ChECk LIST (continued) 3.5a Fire (continued) Electrical Fire In Flight EMERG BATT Switch ............VERIFY ARM BATT MASTR Switch ................ OFF ALTR Switch ..................OFF Vents ....................OPEN HEAT/DEF (Defroster) ..............OFF Fire ..................EXTINGUISH Emergency Descent (If needed) ......TO A SAFE ALTITUDE CONSISTENT WITH TERRAIN...
Page 58: Engine Power Loss
SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES EMERGENCY PROCEDURES ChECk LIST (continued) 3.5b Engine Power Loss Engine Power Loss During Takeoff If sufficient runway remains for a complete stop: Airspeed ........... MAINTAIN SAFE AIRSPEED Landing ........LAND and STOP STRAIGHT AHEAD Brakes ................AS REQUIRED If insufficient runway remains: Airspeed ...........
Page 59: Engine Power Loss In Flight
SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III EMERGENCY PROCEDURES ChECk LIST (continued) 3.5b 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 ALTERNATE AIR ................OPEN LEFT/RIGHT MAG Switches ........Turn OFF then ON one at a time When power is restored:...
Page 60: Power Off Landing
SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES EMERGENCY PROCEDURES ChECk LIST (continued) 3.5b Engine Power Loss (continued) Power Off Landing Airspeed ..............MAINTAIN 76 KIAS Air Conditioning (if installed) ............. OFF Landing Pattern ........ESTABLISH 1000 FT ABOVE FIELD AT DOWNWIND POSITION When committed to landing: Airspeed ..................
Page 61: Engine Indicating System (Eis)
SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III EMERGENCY PROCEDURES ChECk LIST (continued) 3.5c Engine Indicating System (EIS) Oil Pressure Indication: Master Warning, Triple Chime, Flashing Red Oil Pressure Indication Low Oil Pressure: THROTTLE ............MINIMUM REQUIRED If accompanied by high oil temperature, land as soon as possible. If accompanied by normal oil temperature, land as soon as practical.
Page 62: Oil Temperature
SECTION 3 PA-28-181, ARCHER III 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 THROTTLE ............MINIMUM REQUIRED MIXTURE................FULL RICH Airspeed ..............INCREASE if practical Land as soon as possible and investigate the problem.
Page 63: Loss Of Fuel Flow
SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III 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 64: Fuel Quantity Low
SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES EMERGENCY PROCEDURES ChECk LIST (continued) 3.5c Engine Indicating System (EIS) (continued) Fuel Quantity Low Indication: Master Warning, Triple Chime, L FUEL QTY R FUEL QTY WARNING Avoid unusual attitudes such as prolonged slips towards the low quantity tank as this will decrease the time remaining prior to fuel starvation.
Page 65: Electrical Failures
SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III EMERGENCY PROCEDURES ChECk LIST (continued) 3.5d Electrical Failures NOTE 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 66 SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES EMERGENCY PROCEDURES ChECk LIST (continued) 3.5d Electrical Failures (continued) To ensure 30-minutes of battery life: Battery Discharge ............. -13 Amps Maximum Pitot Heat............. 14 Minutes Usage Maximum Com Radio ............3 Mins Usage Maximum Fuel Pump ............
Page 67: Complete Electrical Failure
SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III EMERGENCY PROCEDURES ChECk LIST (continued) 3.5d Electrical Failures (continued) Complete Electrical Failure 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 68: Emergency Battery Voltage
SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES EMERGENCY PROCEDURES ChECk LIST (continued) 3.5d Electrical Failures (continued) Emergency Battery Voltage Indication: Master Warning, Triple Chime, Flashing Red E VOLTS Indication WARNING Complete electrical failure is imminent. Land as soon as possible. ISSUED: December 22, 2017 REPORT: VB-2749 3-21...
Page 69: Avionics Failures
SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III EMERGENCY PROCEDURES ChECk LIST (continued) 3.5e 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 ..PUSH (button extended) Aircraft Control ........
Page 70 SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST (continued) 3.5e Avionics System Failures (continued) Attitude, heading, airspeed and altitude indications are available on the standby instrument and on the MFD after the DISPLAY BACKUP button is pressed. It is the pilot’s responsibility to compare these parameters to verify accuracy.
Page 71: Mfd Failure
SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III EMERGENCY PROCEDURES CHECK LIST (continued) 3.5e Avionics System Failures (continued) MFD Failure Indication: MFD display goes blank. NOTE PFD should automatically revert to the reversionary mode display. DISPLAY BACKUP on audio panel ....PUSH (button extended) Exit and avoid IFR conditions as soon as practical.
Page 72: Adahrs Failures
SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES EMERGENCY PROCEDURES ChECk LIST (continued) 3.5e Avionics System Failures (continued) ADAhRS Failures ADAhRS Total Failure On Ground: Indication: Sky/Ground presentation removed, course pointer straight up, yellow-x’s and amber text on all air data, attitude and heading indicators.
Page 73 SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III EMERGENCY PROCEDURES ChECk LIST (continued) 3.5e Avionics System Failures (continued) ADAhRS Failures (continued) ADAhRS Total Failure In Flight: Indication: Sky/Ground presentation removed, course pointer straight up, yellow-x’s and amber text on all air data, attitude and heading indicators.
Page 74: Erroneous Or Loss Of Engine And Fuel Displays
SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES EMERGENCY PROCEDURES ChECk LIST (continued) 3.5e 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 75: Erroneous Or Loss Of Warning/Caution Cas Messages
SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III EMERGENCY PROCEDURES ChECk LIST (continued) 3.5e 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 76: Com1 And Com2 Failure
SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECK LIST (continued) 3.5e Avionics System Failures (continued) COM1 and COM2 Failure Indication: Inability to communicate/receive on COM1 and COM2. NOTE If power is lost to the audio panel a fail-safe communications path becomes available between the pilot’s headset/microphone and COM1.
Page 77: Dual Gps Failure
SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III EMERGENCY PROCEDURES CHECK LIST (continued) 3.5e 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, LOC, VOR, DME, ADF) If no alternate navigation sources are available: Dead Reckoning (DR) Mode - Active when the airplane is greater than...
Page 78: Avionics Cooling Fan Failures
SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES EMERGENCY PROCEDURES ChECk LIST (continued) 3.5e Avionics System Failures (continued) Loss of Integrity (LOI) Mode - Active when GPS integrity is insufficient for the current phase of flight. Navigation ....... Crosscheck / use other navigation sources as required.
Page 79: Autopilot Malfunction
SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III 3.5e Avionics System Failures (continued) Autopilot Malfunction 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 80: Electric Pitchtrim Failure
SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES 3.5e Avionics System Failures (continued) Electric PitchTrim Failure Indication: Red boxed PTRM on PFD NOTE Loss of the electric pitch trim servo will not cause the autopilot to disconnect. Monitor pitch attitude for unusual behavior. Be alert to possible autopilot out-of-trim conditions (see AUTOPILOT OUT OF TRIM procedure this section) and expect residual control forces upon disconnect.
Page 81: Autopilot Overspeed Recovery
SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III 3.5e Avionics System Failures (continued) Autopilot Overspeed Recovery Indication: annunciation at the top of the PFD airspeed MAXSPD tape This autopilot mode is active whenever the aircraft actual or projected airspeed exceeds the maximum approved autopilot operating speed of 140 KIAS.
Page 82: Autopilot Out-Of-Trim
SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES 3.5e Avionics System Failures (continued) Autopilot Out-Of-Trim á Indication: Amber ß AIL, AIL à, ELE, or ELE on PFD â 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 83: Abnormal Flight Director Mode Transitions
SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III 3.5e 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 84: Loss Of Navigation Information
SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES 3.5e Avionics System Failures (continued) 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 it, the autopilot will roll the aircraft wings level and default to roll mode (ROL).
Page 85: Pitot Heat Failure
SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III 3.5f 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 Avoid Instrument Meteorological Conditions.
Page 86: Spin Recovery
SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES 3.5h Spin Recovery Spin Recovery Rudder ..............FULL OPPOSITE TO DIRECTION OF ROTATION Control wheel ............FULL FORWARD while NEUTRALIZING AILERONS THROTTLE ..................IDLE Rudder ............NEUTRAL (when rotation stops) Control wheel ..........SMOOTH BACK PRESSURE to recovery from dive Intentional spins are prohibited in this airplane.
Page 87: Engine Roughness
SECTION 3 EMERGENCY PROCEDURES PA-28-181, ARCHER III 3.5j Engine Roughness Engine Roughness ALTERNATE AIR ................OPEN If roughness continues after one minute: MIXTURE..........Adjust for Maximum Smoothness ALTERNATE AIR ................. CLOSE FUEL PUMP ..................ON Fuel Selector ..............SWITCH TANKS Engine Indicators ................
Page 88: Carbon Monoxide Cas Indications
SECTION 3 PA-28-181, ARCHER III EMERGENCY PROCEDURES 3.5k Carbon Monoxide CAS Indications CO Detector Warning Indication: Master Warning, Triple Chime, CO LVL HIGH Flashing Red If the CO Detector Warning or Caution activates in flight: Press the CO RST softkey (on the engine page) to reset the CO Detector. If the Warning or Caution continues: Shut off the heater, air conditioning or any other opening to the engine compartment.
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Page 90 SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES Paragraph Page General ................... Airspeeds for Safe Operations............Normal Procedures Checklist ............4.5a Preflight Checklist ..............4.5b Engine Start - General ..............4.5c Before Starting Engine ............... 4.5d Engine Start Checklists ..............
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Page 92: General
SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES SECTION 4 NORMAL PROCEDURES 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, using a simple action - reaction format, with little emphasis on system operation.
Page 93: Airspeeds For Safe Operations
SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III 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 94 SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES 4.5 NORMAL PROCEDURES CHECKLIST (continued) 4.5a Preflight Checklists (continued) CAUTION The flap 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 95 SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III 4.5a 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 pitot head. The unit becomes very hot. Ground operation should be limited to three minutes to avoid damaging the heater elements.
Page 96 SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES 4.5a Preflight Checklists (continued) RIGHT WING Surface Condition ........ CLEAR OF ICE, FROST, SNOW Flap and Hinges ..............NO DAMAGE or INTERFERENCE Aileron and Hinges ............. NO DAMAGE or INTERFERENCE Static Wicks ............CHECK and SECURE Wing Tip and Lights ..............
Page 97 SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III 4.5a 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 98 SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES 4.5a Preflight Checklists (continued) LEFT WING (continued) Tie Down and Chock ..............REMOVE Fuel Tank ..........CHECK SUPPLY VISUALLY and SECURE CAP Pitot/Static Head ......REMOVE COVER - HOLES CLEAR OAT Probe ..................CHECK Wing Tip and Lights ..............CHECK Aileron and Hinges ......
Page 99: Engine Start - General
SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III 4.5b Engine Start ENGINE START - GENERAL WARNING 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 100: Before Starting Engine
SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES 4.5c Before Starting Engine Checklists BEFORE STARTING ENGINE Flaps ...................RETRACT Passengers ..................BOARD Door...............CLOSED and SECURE Seats ........ADJUSTED and LOCKED IN POSITION Seat Belts and Harness ..........FASTEN/ADJUST CHECK INERTIA REEL FUEL Selector ...............DESIRED TANK PARK BRAKE ..................SET Circuit Breakers ...............CHECK IN ALTERNATE AIR .................
Page 101: Engine Start Checklists
SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III 4.5c Before Starting Engine Checklists (continued) BEFORE STARTING ENGINE (continued) E VOLTS Indication ...............23.3 VOLTS (Minimum) FUEL QTY Indications ........CHECK QUANTITY AND IMBALANCE If the E VOLTS indication is less than 23.3 VOLTS, the voltage can be checked again at the end of the GROUND CHECK checklist (after being charged by the primary electrical system) or can be conditioning charged by ground personnel prior to further checks.
Page 102: Normal Start - Hot Engine
SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES 4.5d Engine Start Checklists (continued) NORMAL START - HOT ENGINE THROTTLE ................1/2 IN. OPEN BATT MASTR Switch ................ON ALTR Switch ..................ON LEFT/RIGHT MAG Switches ............... ON FUEL PUMP ..................ON MIXTURE.................IDLE CUT-OFF CAS Messages .........
Page 103: Engine Start Using External Power Source
SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III 4.5d Engine Start Checklists (continued) ENGINE START - USING ExTERNAL POWER SOURCE NOTE The EMERG BATT 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 104: Before Taxiing Checklist
SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES 4.5e Before Taxiing Checklist WARM-UP THROTTLE ..............800 to 1200 RPM Avoid prolonged idling at low RPM, as this practice may result in fouled spark plugs. BEFORE TAxIING AVION MASTER Switch ..............ON EMERG BATT Switch ............VERIFY ARM Multi-Function Display (MFD) ......VERIFY DATABASE CURRENCY MFD Aux-Weight Planning .........
Page 105: Taxiing Checklist
SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III 4.5f Taxiing Checklist TAxIING Taxi area ..................CLEAR PARK BRAKE ............... RELEASED Throttle ................APPLY SLOWLY Brakes ..................... CHECK Steering ..................CHECK NOTE During taxi, if the VOLTS indication decreases into the warning range, increase engine RPM (if possible) to retain adequate battery charging.
Page 106 SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES 4.5g 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 Indication........CHECK BUS (28 +/- 1 VOLT) ALTR AMPS Indication ..........CHECK NORMAL ALTERNATE AIR ...........APPROX.
Page 107: Before Takeoff Checklist
SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III 4.5h Before Takeoff Checklist BEFORE TAKEOFF BATT MASTR Switch ............VERIFY ON ALTR Switch ................. VERIFY ON FUEL PUMP ..................ON LEFT/RIGHT MAG Switches ..........VERIFY ON Flight Instruments ................CHECK Standby Flight Instruments ............CHECK CAS Messages ........
Page 108: Takeoff Checklist
SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES 4.5i Takeoff Checklist TAKEOFF NORMAL TECHNIQUE Flaps ......................Up Trim .......................SET Brakes ................APPLY & HOLD THROTTLE ...............FULL POWER Brakes ..................RELEASE Rotation Airspeed ................ 60 KIAS SMOOTHLY ROTATE TO CLIMB ATTITUDE 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 109: Climb Checklist
SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III 4.5j Climb Checklist CLIMB Best rate (flaps up) ................ 76 KIAS Best angle (flaps up) ..............64 KIAS Enroute ..................87 KIAS FUEL PUMP ............OFF at desired altitude For climbing enroute, a speed of 87 KIAS is recommended. This will produce better forward speed and increased visibility over the nose during the climb.
Page 110: Descent Checklist
SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES 4.5k 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 111: Approach And Landing Checklist
SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III 4.5m 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 G1000 system. The pilot should always double check the inbound course pointer prior to initiating a VHF NAV approach.
Page 112 SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES 4.5m 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 ................AS REQUIRED NOTE TAS aural alerts will be muted when GPS altitude is lower than ~ 400 FT AGL.
Page 113: Go-Around Checklist
SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III 4.5n Go-Around Checklist GO-AROUND MIXTURE................FULL RICH THROTTLE ................FULL OPEN Control Wheel ........BACK PRESSURE TO OBTAIN POSITIVE CLIMB ATTITUDE FLAPS ........... RETRACT INCREMENTALLY If the aircraft is equipped 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 114: Stopping Engine Checklist
SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES 4.5p 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 ..................RETRACT FUEL PUMP ..................
Page 115: Mooring Checklist
SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III 4.5q 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 116: Stalls
SECTION 4 PA-28-181, ARCHER III NORMAL PROCEDURES 4.7 STALLS The stall characteristics of the ARCHER III are conventional. An approaching stall is indicated by a stall warning aural annunciation (Stall..Stall..Stall) which is activated between five and ten knots above stall speed. Mild airframe buffeting and gentle pitching may also precede the stall.
Page 117: Noise Level
SECTION 4 NORMAL PROCEDURES PA-28-181, ARCHER III 4.13 NOISE LEVEL (a) FAR 36 Appendix G for aircraft with the standard exhaust system, the noise level is 73.1 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,...
Page 118 SECTION 5 PA-28-181, ARCHER III PERFORMANCE TABLE OF CONTENTS SECTION 5 PERFORMANCE Paragraph Page General ..................Performance and Flight Planning ..........Flight Planning Example ............. Performance Graphs ..............List of Figures ................ISSUED: December 22, 2017 REPORT: VB-2749...
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Page 120 SECTION 5 PA-28-181, ARCHER III PERFORMANCE SECTION 5 PERFORMANCE 5.1 GENERAL All of the required (FAA regulations) and complementary performance information applicable to the ARCHER III is provided by this section. Performance information associated with those optional systems and equipment which require handbook supplements is provided by Section 9 (Supplements).
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Page 122 SECTION 5 PA-28-181, ARCHER III PERFORMANCE 5.5 FlIghT PlannIng ExamPlE (a) Aircraft Loading The first step in planning the flight is to calculate the airplane weight and center of gravity by utilizing the information provided by Section 6 (Weight and Balance) of this handbook. The basic empty weight for the airplane as certified at the factory has been entered in Figure 6-5.
Page 123 SECTION 5 PERFORMANCE PA-28-181, ARCHER III 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 flight. Apply the departure 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 124 SECTION 5 PA-28-181, ARCHER III PERFORMANCE (c) Climb The next step in the flight plan is to determine the necessary climb segment components. The desired cruise pressure altitude and corresponding cruise outside air temperature values are the first variables to be considered in determining the climb components from the Time, Distance and Fuel to Climb graph (Figure 5-17).
Page 125 SECTION 5 PERFORMANCE PA-28-181, ARCHER III 5.5 FLIGHT PLANNING ExAMPLE (continued) (d) Descent The descent data will be determined 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 126 SECTION 5 PA-28-181, ARCHER III PERFORMANCE (e) Cruise Using the total distance to be traveled during the flight, subtract the previously calculated distance to climb and distance to descend to establish the total cruise distance. Refer to the appropriate Lycoming Operator’s Manual when selecting the cruise power setting.
Page 127 SECTION 5 PERFORMANCE PA-28-181, ARCHER III 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 128 SECTION 5 PA-28-181, ARCHER III PERFORMANCE 5.7 PERFORMANCE GRAPHS LIST OF FIGURES Figure Page Temperature Conversion ............5-11 Airspeed System Calibration ............. 5-12 Stall Speeds ................5-13 Flaps Up Takeoff Performance ..........5-14 25° Flaps Takeoff Performance ..........5-15 5-11 Flaps Up Takeoff Ground Roll ..........
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Page 130 SECTION 5 PA-28-181, ARCHER III PERFORMANCE TEMPERATURE CONVERSION Figure 5-1 ISSUED: December 22, 2017 REPORT: VB-2749 5-11...
Page 131 SECTION 5 PERFORMANCE PA-28-181, ARCHER III INDICATED AIRSPEED KIAS (ZERO INSTRUMENT ERROR) AIRSPEED SYSTEM CALIBRATION Figure 5-3 REPORT: VB-2749 ISSUED: December 22, 2017 5-12...
Page 132 SECTION 5 PA-28-181, ARCHER III PERFORMANCE STALL SPEEDS Figure 5-5 ISSUED: December 22, 2017 REPORT: VB-2749 5-13...
Page 133 SECTION 5 PERFORMANCE PA-28-181, ARCHER III FLAPS UP TAKEOFF PERFORMANCE Figure 5-7 REPORT: VB-2749 ISSUED: December 22, 2017 5-14...
Page 134 SECTION 5 PA-28-181, ARCHER III PERFORMANCE 25° FLAPS TAKEOFF PERFORMANCE Figure 5-9 ISSUED: December 22, 2017 REPORT: VB-2749 5-15...
Page 135 SECTION 5 PERFORMANCE PA-28-181, ARCHER III FLAPS UP TAKEOFF GROUND ROLL Figure 5-11 REPORT: VB-2749 ISSUED: December 22, 2017 5-16...
Page 136 SECTION 5 PA-28-181, ARCHER III PERFORMANCE 25° FLAPS TAKEOFF GROUND ROLL Figure 5-13 ISSUED: December 22, 2017 REPORT: VB-2749 5-17...
Page 137 SECTION 5 PERFORMANCE PA-28-181, ARCHER III CLIMB PERFORMANCE Figure 5-15 REPORT: VB-2749 ISSUED: December 22, 2017 5-18...
Page 138 SECTION 5 PA-28-181, ARCHER III PERFORMANCE TIME, DISTANCE AND FUEL TO CLIMB Figure 5-17 ISSUED: December 22, 2017 REPORT: VB-2749 5-19...
Page 139 SECTION 5 PERFORMANCE PA-28-181, ARCHER III ENGINE PERFORMANCE Figure 5-19 REPORT: VB-2749 ISSUED: December 22, 2017 5-20...
Page 140 SECTION 5 PA-28-181, ARCHER III PERFORMANCE Engine / Cruise Performance for Non-ISA OAT* RPM for Constant 55% Power Fuel Flow: Best Economy Mixture, 8.2 GPH Pressure Indicated Outside Air Temperature Engine True Air Altitude Speed Speed Feet °C °C °F Knots ** Sea Level ISA-15...
Page 141 SECTION 5 PERFORMANCE PA-28-181, ARCHER III Engine / Cruise Performance for Non-ISA OAT* RPM for Constant 65% Power Fuel Flow: Best Economy Mixture, 9.5 GPH Pressure Indicated Outside Air Temperature Engine True Air Altitude Speed Speed Feet °C °C °F Knots ** Sea Level ISA-15...
Page 142 SECTION 5 PA-28-181, ARCHER III PERFORMANCE Engine / Cruise Performance for Non-ISA OAT* RPM for Constant 75% Power Fuel Flow: Best Economy Mixture, 11.0 GPH Pressure Indicated Outside Air Temperature Engine True Air Altitude Speed Speed Feet °C °C °F Knots ** Sea Level ISA-15...
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Page 144 SECTION 5 PA-28-181, ARCHER III PERFORMANCE SPEED POWER Figure 5-27 ISSUED: December 22, 2017 REPORT: VB-2749 5-25...
Page 145 SECTION 5 PERFORMANCE PA-28-181, ARCHER III RANGE (NO RESERVE) Figure 5-29 REPORT: VB-2749 ISSUED: December 22, 2017 5-26...
Page 146 SECTION 5 PA-28-181, ARCHER III PERFORMANCE RANGE (45 MIN. RESERVE) Figure 5-31 ISSUED: December 22, 2017 REPORT: VB-2749 5-27...
Page 147 SECTION 5 PERFORMANCE PA-28-181, ARCHER III ENDURANCE (NO RESERVE) Figure 5-33 REPORT: VB-2749 ISSUED: December 22, 2017 5-28...
Page 148 SECTION 5 PA-28-181, ARCHER III PERFORMANCE ENDURANCE (45 MIN. RESERVE) Figure 5-35 ISSUED: December 22, 2017 REPORT: VB-2749 5-29...
Page 149 SECTION 5 PERFORMANCE PA-28-181, ARCHER III TIME, DISTANCE AND FUEL TO DESCEND Figure 5-37 REPORT: VB-2749 ISSUED: December 22, 2017 5-30...
Page 150 SECTION 5 PA-28-181, ARCHER III PERFORMANCE GLIDE RANGE Figure 5-39 ISSUED: December 22, 2017 REPORT: VB-2749 5-31...
Page 151 SECTION 5 PERFORMANCE PA-28-181, ARCHER III LANDING PERFORMANCE Figure 5-41 REPORT: VB-2749 ISSUED: December 22, 2017 5-32...
Page 152 SECTION 5 PA-28-181, ARCHER III PERFORMANCE LANDING GROUND ROLL Figure 5-43 ISSUED: December 22, 2017 REPORT: VB-2749 5-33...
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Page 154 SECTION 6 PA-28-181, ARCHER III WEIGHT AND BALANCE TABLE OF CONTENTS SECTION 6 WEIGHT AND BALANCE Paragraph Page General ..................Airplane Weighing Procedure ..........Weight and Balance Data and Record ........Weight and Balance Determination for Flight ......Equipment List ..............upplied with aircraft paperwork.
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Page 156 SECTION 6 PA-28-181, ARCHER III WEIGHT AND BALANCE SECTION 6 WEIGHT AND BALANCE 6.1 GENERAL In order to achieve the performance and flying characteristics which are designed into the airplane, it must be flown with the weight and center of gravity (C.G.) position within the approved operating range (envelope).
Page 157 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 158 SECTION 6 PA-28-181, ARCHER III WEIGHT AND BALANCE 6.3 AIRPLANE WEIGHING 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 the fuel supply lines.
Page 159 SECTION 6 WEIGHT AND BALANCE PA-28-181, ARCHER III 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: C.G.
Page 160 SECTION 6 PA-28-181, ARCHER III WEIGHT AND BALANCE 6.5 WEIGHT AND BALANCE DATA AND RECORD The Basic Empty Weight, Center of Gravity Location and Useful Load listed in Figure 6-5 are for the airplane as certified at the factory. These figures apply only to the specific airplane serial number and registration number shown.
Page 161 SECTION 6 WEIGHT AND BALANCE PA-28-181, ARCHER III MODEL PA-28-181 ARCHER III Airplane Serial Number _____________________ Registration Number ________________________ Date _____________________________________ AIRPLANE BASIC EMPTY WEIGHT C.G. Arm Weight x (Inches Aft = Moment Item (Lbs) of Datum) (In-Lbs) Actual Standard Empty Weight* Computed Optional Equipment Basic Empty Weight *The standard empty weight includes full oil capacity and 2.0 gallons of unus-...
Page 162 SECTION 6 PA-28-181, ARCHER III WEIGHT AND BALANCE WEIGHT AND BALANCE RECORD Figure 6-7 ISSUED: December 22, 2017 REPORT: VB-2749...
Page 163 SECTION 6 WEIGHT AND BALANCE PA-28-181, ARCHER III WEIGHT AND BALANCE RECORD (cont) Figure 6-7 (cont) REPORT: VB-2749 ISSUED: December 22, 2017...
Page 164 SECTION 6 PA-28-181, ARCHER III WEIGHT AND BALANCE 6.7 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT (a) Add the weight of all items to be loaded to the basic empty weight. (b) Use the Loading Graph (Figure 6-13) to determine the moment of all items to be carried in the airplane.
Page 165 SECTION 6 WEIGHT AND BALANCE PA-28-181, ARCHER III Arm Aft Weight Datum Moment (Lbs) (Inches) (In-Lbs) Basic Empty Weight Pilot and Front Passenger 80.5 Passengers (Rear Seats)* 118.1 Fuel (48 Gallon Maximum) 95.0 Baggage (200 Lbs. Maximum)* 142.8 Ramp Weight (2558 Lbs. Normal, 2138 Lbs.
Page 166 SECTION 6 PA-28-181, ARCHER III WEIGHT AND BALANCE LOADING GRAPH Figure 6-13 ISSUED: December 22, 2017 REPORT: VB-2749 6-11...
Page 167 SECTION 6 WEIGHT AND BALANCE PA-28-181, ARCHER III C.G. RANGE AND WEIGHT Figure 6-15 REPORT: VB-2749 ISSUED: December 22, 2017 6-12...
Page 168 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION TABLE OF CONTENTS SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS Paragraph Page The Airplane ................Airframe ..................Engine and Propeller ..............Induction System ................. Engine Controls ................7.11 Flight Controls ................7.13 Landing Gear ................
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Page 170: The Airplane
SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS 7.1 THE AIRPLANE The PA-28-181 ARCHER III is a single-engine, low-wing monoplane of all metal construction. It has four-place seating, two hundred pound baggage capacity, and a 180 horsepower engine.
Page 171: Induction System
SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III INDUCTION SYSTEM The induction system incorporates an Avstar RSA-5AD1 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 (jetting system) makes the fuel flow proportional to airflow.
Page 172 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION CONTROL QUADRANT AND CONSOLE Figure 7-1 ISSUED: December 22, 2017 REPORT: VB-2749...
Page 173 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III 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 control quadrant.
Page 174: Flight Controls
SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 7.11 FLIGHT CONTROLS Dual controls are provided as standard equipment, with a cable system used between the controls and the surfaces. The horizontal tail (stabilator) is of the all- movable slab type with a trim tab mounted on the trailing edge of the stabilator to reduce the control system forces.
Page 175 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III MAIN WHEEL ASSEMBLY Figure 7-3 (Wheel fairing removed for clarity.) REPORT: VB-2749 ISSUED: December 22, 2017...
Page 176: Landing Gear
SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 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 III tires with tubes. A spring device is incorporated in the rudder pedal torque tube assembly to provide rudder trim.
Page 177: Garmin G1000 Avionics System
The latest appropriate revision of the Garmin G1000 Cockpit Reference Guide for the Piper PA-28-181 Archer (Garmin P/N 190-02131-02), and the Garmin G1000 Pilot’s Guide for the Piper PA-28-181 Archer (Garmin P/N 190-02130-02), contain operational information and detailed descriptions of the Garmin G1000 avionics system, the annunciator system (CAS and Non-CAS) and all warnings, cautions and advisories.
Page 178: Primary Flight Display
SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 7.15 GARMIN G1000 AVIONICS SYSTEM (continued) Primary Flight Display The Primary Flight Display (PFD) displays airspeed, attitude, altitude, and heading information in a traditional format. Slip information is shown as a trapezoid under the bank pointer. One width of the trapezoid is equal to a one ball width slip.
Page 179 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III Primary Flight Display (continued) real-time to obtain the user’s position, velocity, and time. This GPS WAAS is certified under TSO C146a 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 180 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION Primary Flight Display (continued) Reversionary Mode - PFD The PFD will automatically be displayed in a composite format (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 181 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III Synthetic Vision System (SVS) - Optional The Synthetic Vision System (SVS) is a visual enhancement to the G1000. Terrain-SVS is displayed on the PFD as a forward-looking depiction of the topography immediately in front of the aircraft. The depicted imagery is derived from the aircraft attitude, heading, GPS three-dimensional position, and a database of terrain, obstacles, and other relevant features.
Page 182: Multi-Function Display
SECTION 7 PA-28-181, ARCHER III 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 183 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III Multi-Function Display (continued) EIS PAGE (TYPICAL) Figure 7-4 REPORT: VB-2749 ISSUED: December 22, 2017 7-14...
Page 184 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 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 185 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III Multi-Function Display (continued) Crew Alerting System (CAS) Messages (continued) Amber Caution Messages Caution messages consist of a flashing 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 186 SECTION 7 PA-28-181, ARCHER III 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 G1000 system...
Page 187 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III Multi-Function Display (continued) Traffic Information Service (TIS) NOTE If the G1000 system is configured to use the optional Traffic Advisory System (TAS), TIS will not be available for use. Traffic Information Service (TIS) provides a graphic display of traffic advisory information to the pilot.
Page 188 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 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 189 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III 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 190 SECTION 7 PA-28-181, ARCHER III 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 191 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III Multi-Function Display (continued) Traffic Advisory System (TAS) – Optional (continued) TAS Alerts: Traffic is displayed according to TCAS symbology using four different symbols. 1. Non-Threat Traffic – An open white diamond with black center that indicates traffic is beyond a 6 nm range and greater than ±...
Page 192 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION Multi-Function Display (continued) Terrain Proximity NOTE If the G1000 system is configured to use the optional Terrain Awareness and Warning System (TAWS), Terrain Proximity will not be available for use. G1000 Terrain Proximity is a terrain awareness system that increases situational awareness and aids in preventing controlled flight into terrain (CFIT).
Page 193 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III Multi-Function Display (continued) Terrain Proximity (continued) GPS altitude, which 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 GPS 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 194 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION Multi-Function Display (continued) Terrain Proximity (continued) Terrain 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 195 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III Multi-Function Display (continued) Terrain Awareness and Warning System (TAWS -B) – Optional NOTE If the G1000 system is configured to use the optional Terrain Awareness and Warning System (TAWS), Terrain Proximity will not be available for use.
Page 196 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION Multi-Function Display (continued) Terrain Awareness and Warning System (TAWS-B) – Optional (continued) System Status (continued) TAWS-B requires the following to operate properly: • A valid terrain/obstacle/airport terrain database • A valid 3-D GPS position solution If a valid 3-D GPS position solution and vertical accuracy requirements are not attained or the aircraft is out of the database coverage area, a TAWS N/A annunciation will appear on the TAWS-B Page and the aural annunciation...
Page 197 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III Multi-Function Display (continued) Terrain Awareness and Warning System (TAWS-B) – Optional (continued) Operation of TAWS (continued) To inhibit the aural and visual Premature Descent Alert (PDA) and Forward Looking Terrain Awareness (FLTA) alerts (RTC, ITI, ROC and IOI), press the INHIBIT softkey on the TAWS-B Page or depress the MENU key then select “Inhibit TAWS”...
Page 198 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION PFD/MFD Alert Response Alert Type Annunciation MFD Pop-Up Alert Aural Message Technique Excessive Descent PULL-UP “Pull Up” WARNING PULL-UP Rate Warning (EDR) Reduced Required “Terrain, Terrain; PULL-UP Terrain Clearance WARNING TERRAIN - PULL-UP Pull Up, Pull Up”...
Page 199 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III Multi-Function Display (continued) Terrain Awareness and Warning System (TAWS-B) – Optional (continued) TAWS-B Page (continued) On all pages that display terrain data, the obstacles and terrain are depicted with the following colors: •...
Page 200 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION Multi-Function Display (continued) Terrain Awareness and Warning System (TAWS-B) – Optional (continued) TAWS-B Alerts (continued) Response Technique - CAUTION: 1. Take positive corrective action until the alert ceases. 2. Based on analysis of all available instruments and information: •...
Page 201 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III Multi-Function Display (continued) Garmin Datalink (GDL) – Optional SiriusXM Weather services is provided through the optional GDL 69eA, a remote-mounted data-link satellite receiver. SiriusXM Satellite Weather services, available by subscription, have coded IDs unique to the installed GDL 69eA.
Page 202 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 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 203 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III 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 10 (Canada) Cloud Top (CLD TOP) Echo Top (ECHO TOP) SirusXM Lightning (XM LTNG)
Page 204 SECTION 7 PA-28-181, ARCHER III 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 205 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III Databases The G1000 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 206 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 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 207: Autopilot (Optional)
SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III 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 / TRIM INTER Switch –...
Page 208 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION Autopilot (Optional) (continued) AUTOPILOT OPERATION When the AVION 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 PFT with no AP failure indications and an autopilot “warble”...
Page 209 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III 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 / TRIM INTER switch on the control wheel •...
Page 210 SECTION 7 PA-28-181, ARCHER III 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 after takeoff rotation.
Page 211 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III 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 panel.
Page 212: Audio Panel
SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION Autopilot (Optional) (continued) AUTOPILOT 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 213: Gtx 335R Transponder (Extended Squitter)
SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III GTX 335R Transponder (Extended Squitter) The GTX 335R Transponder provides Mode A, C, and S altitude and position reporting information for the G1000 system as well as TIS-A and ADS-B OUT (1090 ES). It includes the following features: •...
Page 214: Standby Instrument
SECTION 7 PA-28-181, ARCHER III 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 G1000 traffic display maps/pages.
Page 215: Fuel System
SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III STANDBY INSTRUMENT (continued): In the event of a complete electrical failure of the alternator, primary and emergency batteries; the EBD will revert to its internal battery allowing approximately 30 additional minutes of operation. In this occurrence the EBD will illuminate an “ON BAT”...
Page 216 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 7.19 FUEL SYSTEM (continued) FUEL SELECTOR Figure 7-5 An auxiliary electric fuel pump is provided in case of failure of the engine driven pump. The electric pump should be on for all takeoffs and landings, and when switching tanks.
Page 217 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III 7.19 FUEL SYSTEM (continued) FUEL SYSTEM SCHEMATIC - Fuel Injected Engine - Figure 7-6 REPORT: VB-2749 ISSUED: December 22, 2017 7-48...
Page 218: Electrical System
SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 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 219 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III 7.21 ELECTRICAL SYSTEM (continued) CAUTION 30-minutes of power from the emergency battery is only 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 flight.
Page 220 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 7.21 ELECTRICAL SYSTEM (continued) ALTERNATOR AND STARTER SCHEMATIC Figure 7-7 Sheet 1 of 2 ISSUED: December 22, 2017 REPORT: VB-2749 7-51...
Page 221 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III 7.21 ELECTRICAL SYSTEM (continued) ALTERNATOR AND STARTER SCHEMATIC Figure 7-7 Sheet 2 of 2 REPORT: VB-2749 ISSUED: December 22, 2017 7-52...
Page 222: Instrument Panel
SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 7.21 ELECTRICAL SYSTEM (continued) CIRCUIT BREAKER PANEL Figure 7-8 7.23 INSTRUMENT PANEL The instrument panel is designed to accommodate the Garmin G1000 system, the Aspen EBD standby instrument, required switches, and remaining avionics/options (See Figure 7-9 and Figure 7-10 for location of each item/ details).
Page 223 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III INSTRUMENT PANEL Figure 7-9 REPORT: VB-2749 ISSUED: December 22, 2017 7-54 REVISED: May 7, 2018...
Page 224 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION ISSUED: December 22, 2017 REPORT: VB-2749 7-55 REVISED: May 7, 2018...
Page 225 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III 7.23 INSTRUMENT PANEL (continued) OVERHEAD SWITCH PANEL Figure 7-10 REPORT: VB-2749 ISSUED: December 22, 2017 7-56...
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Page 227: Pitot-Static System
SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III 7.25 PITOT-STATIC 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 Aspen EBD standby instrument (refer Figure 7-11) located on the instrument panel.
Page 228 SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 106980 C PITOT LINE STATIC LINE GARMIN G1000 NXi INSTALLATION 1. EBD (Standby Instrument Display) 2. Alternate Static Valve 3. Pitot/Static Drain Valves 4. Air Data Attitude and Heading Reference System (ADAHRS) 5.
Page 229: Heating And Ventilating System
SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III HEATING AND VENTILATING SYSTEM Figure 7-12 REPORT: VB-2749 ISSUED: December 22, 2017 7-60...
Page 230: Cabin Features
SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 7.27 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 231: Baggage Area
SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III 7.29 CABIN FEATURES (continued) 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 232: Stall Warning
SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 7.33 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. Stall speeds are shown on the Stall Speed graph in Section 5.
Page 233 SECTION 7 DESCRIPTION & OPERATION PA-28-181, ARCHER III 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 234: Flap Position Sensor (Optional)
SECTION 7 PA-28-181, ARCHER III DESCRIPTION & OPERATION 7.39 EMERGENCY LOCATOR TRANSMITTER (continued) ARTEX ELT 1000 OPERATION (continued) The transmitter can be activated manually at any time by placing either the remote switch or the ELT switch to the ON position. NOTE A monthly functional check is recommended to verify operational status of the ELT.
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Page 236 SECTION 8 PA-28-181, ARCHER III HANDLING, SERV & MAINT TABLE OF CONTENTS SECTION 8 AIRPLANE HANDLING, SERVICING AND MAINTENANCE Paragraph Page General ..................Airplane Inspection Periods ............ Preventive Maintenance ............Airplane Alterations ..............Ground Handling ..............8.11 Engine Air Filter ..............8-10 8.13 Brake Service ................
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Page 238: General
STC installations. WARNING 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 239 HANDLING, SERV & MAINT PA-28-181, ARCHER III GENERAL (continued) WARNING Use only genuine PIPER parts or PIPER approved parts obtained from PIPER approved sources, in connection with the maintenance and repair of PIPER airplanes. Genuine PIPER parts are produced and...
Page 240 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 241: Airplane Inspection Periods
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 intervals, 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 242: Preventive Maintenance
SECTION 8 PA-28-181, ARCHER III HANDLING, SERV & MAINT 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 243: Airplane Alterations
SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER III 8.7 AIRPLANE ALTERATIONS If the owner desires to have his aircraft modified, he must obtain FAA approval for the alteration. Major alterations accomplished in accordance with Advisory Circular 43.13-2, when performed by an A & P mechanic, may be approved by the local FAA office.
Page 244: Ground Handling
SECTION 8 PA-28-181, ARCHER III HANDLING, SERV & MAINT 8.9 GROUND HANDLING (a) Towing The airplane may be moved on the ground by the use of the nose wheel steering bar that is stowed below the forward ledge of the baggage compartment or by power equipment that will not damage or excessively strain the nose gear steering assembly.
Page 245 SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER III 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 246 SECTION 8 PA-28-181, ARCHER III HANDLING, SERV & MAINT 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: (1) Head the airplane into the wind if possible. (2) Retract the flaps.
Page 247: Engine Air Filter
SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER III 8.11 ENGINE AIR FILTER Inspect inlet for foreign particles and obstructions. Engine Air Filter should be removed and inspected or replaced at intervals as outlined in the aircraft Maintenance Manual. Operations in severe environments may require more frequent attention.
Page 248 SECTION 8 PA-28-181, ARCHER III HANDLING, SERV & MAINT BRAKE SYSTEM Figure 8-1 ISSUED: December 22, 2017 REPORT: VB-2749 8-11...
Page 249: Landing Gear Service
SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER III 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 III should be serviced according to the instructions on the units.
Page 250: Oil Requirements
SECTION 8 PA-28-181, ARCHER III HANDLING, SERV & MAINT 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 251 SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER III 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. gallons. When using less than the standard 50 gallon capacity, fuel should be distributed equally between each tank.
Page 252 SECTION 8 PA-28-181, ARCHER III 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 253: Tire Inflation
SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER III 8.23 TIRE INFLATION For maximum service from the tires, keep them inflated to the proper pressures - 18 psi for the nose gear and 24 psi for the main gear. All wheels and tires are balanced before original installation, and the relationship of tire, tube and wheel should be maintained upon reinstallation.
Page 254: Cleaning
SECTION 8 PA-28-181, ARCHER III HANDLING, SERV & MAINT 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. (1) 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 255 SECTION 8 HANDLING, SERV & MAINT PA-28-181, ARCHER III 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 256: Cold Weather Operation
SECTION 8 PA-28-181, ARCHER III HANDLING, SERV & MAINT 8.27 CLEANING (continued) (e) Cleaning Carpets To clean carpets, first remove loose dirt with a whisk broom or vacuum. For soiled spots and stubborn stains use a non-flammable dry cleaning fluid. Floor carpets may be removed and cleaned like any household carpet.
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Page 258 SECTION 9 SECTION 9 PA-28-181, ARCHER III PA-28-181, ARCHER III SUPPLEMENTS SUPPLEMENTS TABLE OF CONTENTS SECTION 9 SUPPLEMENTS Paragraph Page General ..................Air Conditioning Installation ........(6 pages) Bendix/King KR-87 Digital ADF with Garmin PFD Indicator ..........(10 pages) Bendix/King KN-63 DME ..........(4 pages) 9-19 Appareo Vision 1000 Unit ..........
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Page 260: General
SECTION 9 SECTION 9 PA-28-181, ARCHER III PA-28-181, ARCHER III SUPPLEMENTS SUPPLEMENTS SECTION 9 SUPPLEMENTS 9.1 GENERAL This section provides information in the form of Supplements which are necessary for efficient operation of the airplane when equipped with one or more of the various optional systems and equipment not approved with the standard airplane.
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Page 262: 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 263 SECTION 9 SUPPLEMENT 1 PA-28-181, ARCHER III SECTION 1 - GENERAL This supplement supplies information necessary for the efficient opera- tion of the airplane when the optional air conditioning system is installed. The information contained within this supplement is to be used ``as described’’ in conjunction with the complete handbook.
Page 264 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 1 Advisory Messages – White Checklist CAS Event CAS Message Page Cause Non-hidden CAS Messages 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 CAUTION...
Page 265 SECTION 9 SUPPLEMENT 1 PA-28-181, ARCHER III 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 266 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 1 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 267 SECTION 9 SUPPLEMENT 1 PA-28-181, ARCHER III 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. The “AC DOOR OPEN”...
Page 268: Bendix/King Kr-87 Digital Adf With Garmin Pfd Indicator
Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: _________________ Eric A. Wright ODA-510620-CE Piper Aircraft, Inc. Vero Beach, Florida DATE OF APPROVAL: May 7, 2018 Bendix/King KR-87 Digital ADF with Garmin PFD Indicator ( 1 0...
Page 269 SECTION 9 SUPPLEMENT 2 PA-28-181, ARCHER III SECTION 1 - GENERAL The Bendix/King Digital ADF is a panel mounted, digitally tuned, automatic direction finder. It is designed to provide continuous 1 kHz digital tuning in the frequency range of 200 kHz to 1799 kHz and eliminates the need for mechanical band switching.
Page 270 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 2 SECTION 4 - NORMAL PROCEDURES To Operate as an Automatic Direction Finder: 1. OFF/VOL Control - ON. 2. Frequency Selector Knobs - SELECT desired frequency in the standby frequency display. 3. FRQ Button - PRESS to move the desired frequency from the standby to the active position.
Page 271 SECTION 9 SUPPLEMENT 2 PA-28-181, ARCHER III SECTION 4 - NORMAL PROCEDURES (continued) NOTE The Standby Frequency which is in memory while Flight Time or Elapsed Time modes are being displayed may be called back by pressing the FRQ button, then transferred to active use by pressing the FRQ button again.
Page 272 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 2 SECTION 4 - NORMAL PROCEDURES (continued) ADF Operation NOTES: Erroneous ADF Bearing Due to Radio Frequency Phenomena: In the U.S., the FCC, which assigns AM radio frequencies, occasionally will assign the same frequency to more than one station in an area. Certain condi- tions, such as Night Effect, may cause signals from such stations to overlap.
Page 273 SECTION 9 SUPPLEMENT 2 PA-28-181, ARCHER III 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 274 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 2 SECTION 7 - DESCRIPTION AND OPERATION KR-87 Digital ADF ADF Displays on Garmin PFD Digital ADF Operating Controls and PFD Indicator Figure 1 ISSUED: December 22, 2017 ISSUED: December 22, 2017 REPORT: VB-2749 REPORT: VB-2749 REVISED: May 7, 2018 1 of 10...
Page 275 SECTION 9 SUPPLEMENT 2 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) Legend - Figure 1 1. Mode Annunciation - Antenna (ANT) is selected by the “out” position of the ADF button. This mode improves the aural reception and is usually used for station identification.
Page 276 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 2 SECTION 7 - DESCRIPTION AND OPERATION (continued) Legend - Figure 1 (continued) 6. Timer Mode Annunciation - Either the elapsed time (ET) or flight time (FLT) mode is annunciated here. 7. Frequency Selector Knobs - Selects the standby frequency when FRQ is displayed and directly selects the active frequency whenever either of the timer functions is selected.
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Page 278: Bendix/King Kn-63 Dme
Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: _________________ Eric A. Wright ODA-510620-CE Piper Aircraft, Inc. Vero Beach, Florida DATE OF APPROVAL: December 22, 2017 Bendix/King KN-63 DME (4 pages) ISSUED: December 22, 2017...
Page 279 SECTION 9 SUPPLEMENT 3 PA-28-181, ARCHER III SECTION 1 - GENERAL The Bendix/King KN-63 DME supplies continuous slant range distance infor- mation from a fixed ground station to an aircraft in flight. 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 Receiver-Transmitter.
Page 280 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 3 SECTION 7 - DESCRIPTION AND OPERATION DME Display on Garmin PFD Figure 1 Legend - Figure 1 1. DME Information Window 2. DME MODE ANNUNCIATOR Displays the DME operating mode; NAV 1 or NAV 2 or HOLD as selected in the DME TUNING window.
Page 281 SECTION 9 SUPPLEMENT 3 PA-28-181, ARCHER III SECTION 7 - DESCRIPTION AND OPERATION (continued) Legend - Figure 1 (continued) 5. DME TUNING Window (NAV1, NAV2, HOLD) Allows access to the DME operating mode as follows: NAV 1 Selects DME operation with No.
Page 282: Appareo Vision 1000 Unit
This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when the optional Appareo Vision 1000 unit is installed in accordance with Piper Drawing 107420. 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 283 SECTION 9 SUPPLEMENT 4 PA-28-181, ARCHER III SECTION 1 - 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 284 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 4 SECTION 4 - NORMAL PROCEDURES (continued) Status Indicators: Table 1: LED Status Item LED Status Configuration Fault detected: Refer to ICA Blue Booting Green Operating Yellow SD card not inserted: insert SD card and verify Green LED SD card not formatted correctly: format SD to NTSF, verify Green LED GPS lock not received: Allow 15 minutes to clear, if problem...
Page 285 SECTION 9 SUPPLEMENT 4 PA-28-181, ARCHER III SECTION 7- DESCRIPTION AND OPERATION The Vision 1000 system is a data gathering system utilizing global positioning, image capturing, flight attitude acquisition, and ambient audio recording. It will record the aircraft’s airframe attitudes, rates, accelerations, GPS position, and record cockpit audio and images.
Page 286: Flightcom Model 403 Intercom
This supplement must be attached to the Pilot’s Operating Handbook and 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 287 SECTION 9 SUPPLEMENT 5 PA-28-181, ARCHER III 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 288 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 5 SEcTION 4 - NORMAL PROcEDURES (continued) Adjusting the Intercom and Headsets (continued) NOTE Noise canceling microphones will not operate correctly if they are more than 1/8” 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 289 SECTION 9 SUPPLEMENT 5 PA-28-181, ARCHER III 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 290: Carbureted O-360 Engine Installation
This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when the Carbureted O-360 Engine is installed in accordance with Piper Drawing 109002-001. 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 291 SECTION 9 SUPPLEMENT 6 PA-28-181, ARCHER III SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the Carbureted O-360 Engine is installed. The information contained within this supplement is to be used “as described” in conjunction with the complete handbook.
Page 292 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 6 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 Power Loss Engine Power Loss During Takeoff If sufficient runway remains for a complete stop:...
Page 293 SECTION 9 SUPPLEMENT 6 PA-28-181, ARCHER III EMERGENCY PROCEDURES CHECK LIST (continued) 3.5b 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 294 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 6 EMERGENCY PROCEDURES CHECK LIST (continued) 3.5j Carburetor Icing Carburetor Icing CARB HEAT ..................ON MIXTURE..............Adjust for Maximum Smoothness Under certain moist atmospheric conditions at temperatures of -5°C to 20°C, it is possible for ice to form in the induction system. This is due to the high air velocity through the carburetor venturi and the absorption of heat from this air by vaporization of the fuel.
Page 295 SECTION 9 SUPPLEMENT 6 PA-28-181, ARCHER III EMERGENCY PROCEDURES CHECK LIST (continued) 3.5k 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 carburetor heat, always use full ON, and when ice is removed return the control to the full OFF position.
Page 296 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 6 SECTION 4 - NORMAL PROCEDURES NOTE Only those Normal Procedures that are specific to a Carbureted engine, are provided in this supplement. Refer to Pilot Operating Handbook Section 4 for all Normal Procedures. ISSUED: December 22, 2017 ISSUED: December 22, 2017 REPORT: VB-2749...
Page 297 SECTION 9 SUPPLEMENT 6 PA-28-181, ARCHER III SECTION 4 - NORMAL PROCEDURES (continued) 4.5c Before Starting Engine Checklists BEFORE STARTING ENGINE Flaps ...................RETRACT Passengers ..................BOARD Door...............CLOSED and SECURE Seats ........ADJUSTED and LOCKED IN POSITION Seat Belts and Harness ..........FASTEN/ADJUST CHECK INERTIA REEL FUEL Selector ...............DESIRED TANK PARK BRAKE ..................SET Circuit Breakers ...............CHECK IN...
Page 298 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 6 4.5c Before Starting Engine Checklists (continued) If the E VOLTS indication is less than 23.3 VOLTS, the voltage should be checked again at the end of the GROUND CHECK checklist (after being charged for some time by the primary electrical system). If E VOLTS is still less than 23.3 volts, determine the cause and correct the issue prior to flight.
Page 299 SECTION 9 SUPPLEMENT 6 PA-28-181, ARCHER III 4.5d Engine Start Checklists (continued) NORMAL START - HOT ENGINE THROTTLE ................1/2 IN. OPEN BATT MASTR Switch ................ON ALTR Switch ..................ON LEFT MAG Switch ................ON FUEL PUMP ..................ON MIXTURE................FULL RICH CAS Messages .........
Page 300 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 6 4.5d Engine Start Checklists (continued) ENGINE START - USING ExTERNAL POWER SOURCE NOTE The EMERG BATT 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 301 SECTION 9 SUPPLEMENT 6 PA-28-181, ARCHER III 4.5g 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 Indication........CHECK BUS (28 +/- 1 VOLT) ALTR AMPS Indication ..........CHECK NORMAL CARB HEAT ............APPROX.
Page 302 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 6 4.5h Before Takeoff Checklist BEFORE TAKEOFF BATT MASTR Switch ............VERIFY ON ALTR Switch ................. VERIFY ON FUEL PUMP ..................ON LEFT/RIGHT MAG Switches ..........VERIFY ON Flight Instruments ................CHECK Standby Flight Instruments .............CHECK CAS Messages..
Page 303 SECTION 9 SUPPLEMENT 6 PA-28-181, ARCHER III 4.5l Descent Checklist DESCENT Normal Descent: THROTTLE ................2500 RPM Airspeed ..................122 KIAS MIXTURE..................RICH CARB HEAT ............... ON IF REQUIRED Power Off Descent: CARB HEAT ............... ON IF REQUIRED THROTTLE ................. CLOSED Airspeed ................
Page 304 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 6 SECTION 5 - PERFORMANCE No change. SECTION 6 - WEIGHT AND BALANCE No change. SECTION 7 - DESCRIPTION AND OPERATION 7.5 ENGINE AND PROPELLER The ARCHER III is powered by a four cylinder, direct drive, horizontally opposed engine rated at 180 horsepower at 2700 rpm.
Page 305 SECTION 9 SUPPLEMENT 6 PA-28-181, ARCHER III 7.7 ENGINE CONTROLS A carburetor heat control is located on the instrument panel right of the control quadrant. The control displays two positions: ON (down), OFF (up). 7.15 FUEL SYSTEM An electric engine priming system is provided to facilitate starting. The primer switch is located right of the starter switch in the overhead switch panel (see Fig.
Page 306 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 6 7.15 FUEL SYSTEM (continued) FUEL SYSTEM SCHEMATIC - Carbureted Engine - Figure 7-6 7.19 INSTRUMENT PANEL The instrument panel is designed to accommodate the Garmin G1000 system, the Aspen EBD standby instrument, required switches, and remaining avionics/options (See Figures 7-9 and 7-10 for location of each item/details).
Page 307 SECTION 9 SUPPLEMENT 6 PA-28-181, ARCHER III INSTRUMENT PANEL Figure 7-9 REPORT: VB-2749 ISSUED: December 22, 2017 9-48, 18 of 22 REVISED: May 7, 2018...
Page 308 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 6 ISSUED: December 22, 2017 REPORT: VB-2749 REVISED: May 7, 2018 19 of 22 9-49...
Page 309 SECTION 9 SUPPLEMENT 6 PA-28-181, ARCHER III 7.19 INSTRUMENT PANEL (continued) OVERHEAD SWITCH PANEL Figure 7-10 REPORT: VB-2749 REPORT: VB-2749 ISSUED: December 22, 2017 ISSUED: December 22, 2017 9-50, 9-50, 2 of 22 20 of 22...
Page 310 SECTION 9 PA-28-181, ARCHER III SUPPLEMENT 6 SECTION 8 - HANDLING, SERVICING, 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. ISSUED: December 22, 2017 ISSUED: December 22, 2017 REPORT: VB-2749...
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Page 312: Amsafe Inflatable Seat Restraints (Stc Sa02276Ak)
SECTION 9 SECTION 9 PA-28-181, ARCHER III PA-28-181, ARCHER III SUPPLEMENT 7 SUPPLEMENTS PILOT’S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 7 AMSAFE INFLATABLE SEAT RESTRAINTS (STC SA02276AK) The FAA approved operational supplement for the AMSAFE Inflatable Seat Restraints, installed in accordance with STC SA02276AK, is required for operation of this system.
Page 313 SECTION 9 SECTION 9 SUPPLEMENTS SUPPLEMENT 7 PA-28-181, ARCHER III PA-28-181, ARCHER III THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-2749 ISSUED: December 22, 2017 9-54...
Page 314 SECTION 10 PA-28-181, ARCHER III OPERATING TIPS TABLE OF CONTENTS SECTION 10 OPERATING TIPS Paragraph Page 10.1 General ..................10-1 10.3 Operating Tips ................10-1 ISSUED: December 22, 2017 REPORT: VB-2749 10-i...
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Page 316 SECTION 10 PA-28-181, ARCHER III OPERATING TIPS SECTION 10 OPERATING TIPS 10.1 GENERAL This section provides operating tips of particular value in the operation of Archer III. 10.3 OPERATING TIPS (a) Learn to trim for takeoff so that only a very light back pressure on the control wheel is required to lift the airplane off the ground.
Page 317 SECTION 10 OPERATING TIPS PA-28-181, ARCHER III 10.3 OPERATING TIPS (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, takeoff or landing.

Piper Archer III PA-28-181 Handbook

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