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Piper Arrow PA-28R-201 Pilot Operating Handbook

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Airplane Serial:
Airplane Regist. No.:
Revison:
Revision Date:
Creation Date:
Created by:
HB-PQY, Page: 0-0-(0)
ARROW
PA-28R-201
2844120
HB-PQY
27
26.02.2016
24.03.2016
MFGL
Revision: 25, OCTOBER 31, 2012
Pilot's
Operating
Handbook
Cover

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  Summary of Contents for Piper Arrow PA-28R-201

  • Page 1 ARROW PA-28R-201 Pilot’s Operating Handbook Airplane Serial: 2844120 Airplane Regist. No.: HB-PQY Revison: Revision Date: 26.02.2016 Creation Date: 24.03.2016 Created by: MFGL HB-PQY, Page: 0-0-(0) Revision: 25, OCTOBER 31, 2012 Cover...
  • Page 2 AIRPLANE AIRPLANE —J SERIAL REGIST. _______________ PA-28R-201 REPORT: VB-1612 FAA APPROVED __________ PETER E. PECK D.O.A. NO. SO-I DATE OF APPROVAL: PIPER INC. AIRCRAFT, JULY 12, 1995 VERO FLORIDA BEACH, THIS HANDBOOK INCLUDES MATERIAL REQUIRED FURNISHED ADDITIONAL PILOT FEDERAL AVIATION...
  • Page 3 INDICATED SUBSEQUENTLY VALID WITH AIRPLANE REVISED OF THE TITLE IDENTIFIED FACE PAGE. SUBSEQUENT REVISIONS SUPPLIED PIPER MUST PROPERLY INSERTED. Published by TECHNICAL PUBLICATIONS Issued: July 12, 1995 O 1995-1996, 1998, 2000-2001, 2004-2006, 2009-2012, 2016 PIPER INC. AIRCRAFT, All Rights Reserved...
  • Page 4 PA-28R-201, ARROW APPLICABILITY of this handbook is limited to the specific Piper Application airplane designated by serialnumber and registration PA-28R-201 model number on the face of the title page of this handbook. cannot be used for operational purposes unless kept in a This handbook currentstatus.
  • Page 5 ARROW PA-28R-201, REVISIONS The information compiled in the Pilot’s Operating Handbook, with the exception of the equipment list, will be kept current by revisions distributed to the airplane owners. The equipment list was current at the time the airplane was licensed by the manufacturer and thereaftermust be maintained by the owner.
  • Page 6 ARROW PA-28R-201, PILOT’S OPERATING HANDBOOK OF REVISIONS Current Revisions to the PA-28R-201 Arrow Pilot’s Operating Handbook, REPORT: VB-1612 issued July 12, 1995. Revision Approved Revised Description of Revisions Number Signature and Date Code Pages Added Rev. I to L of R page. Rev.
  • Page 7 ARROW PA-28R-201, PILOT’S HANDBOOK OF REVISIONS OPERATING (cont) Revision Approved Number Revised Description of Revisions Signature Code and Date Pages Rev. 5 9-47 Added pages thru and Supplement 8. (PR000914) 9-56 continued 9-57 Added pages thru and Supplement 9. 9-62 9-63 Added pages thru...
  • Page 8 ARROW PA-28R-201, PILOT’S OPERATING HANDBOOK REVISIONS (cont) Revision Approval Number Description of Revisions Revised Signature Code and Date Pages Rev. 9 Added Warning and moved info,to page iv, (PRO4OIO5) Moved info,from page iii. vi-a Added page and Rev. 9 to L of R. vi-b Added page.
  • Page 9 ARROW PA-28R-201, PILOT’S OPERATING HANDBOOK REVISIONS (cont) Revision Approval Number Revised Description of Revisions Signature Code and Date Pages Rev. 11 9-109 Added pages thru and Supplement (PR041007) continued 9-112 Linda J.Dicken October 7, 2004 Rev. 12 vi-b Added Rev. 12 to L of R. Revised and reorganized (PRO5OI 17) thru...
  • Page 10: Added Supplement

    ARROW PA-28R-201, PILOT’S OPERATING HANDBOOK REVISIONS (cont) Revision Approval Description of Revisions Number Revised Signature and Date Code Pages Rev. 16 vi-c Added page and Rev. 16 to LofR. (PR060109) vi-d Added page. Revised T of C. 9-91 Revised Supplement Linda J.Dicken thru 9-118...
  • Page 11: Report: Vb

    ARROW PA-28R-201, PILOT’S HANDBOOK OF REVISIONS OPERATING (cont) Revision Approval Number Revised Description of Revisions Signature Code and Date Pages Rev. 22 vi-d Added Rev. 22 to L of R Added Note to Para. 2.23 (PR100512) Revised TOC. Relocated text to pg.
  • Page 12 ARROW PA-28R-201, PILOT’S OPERATING HANDBOOK REVISIONS Revision Approved Number Revised Description of Revisions Signature and Date Code Pages Rev. 23 Updated copyright dates. vi-e Added Page. Added Rev. 23 (PR1OI 101) to L of R. vi-f Added Albert J.Mill Page. 9-18 1 Revised Section 4.
  • Page 13 ARROW PA-28R-201, PILOT’S OPERATING HANDBOOK REVISIONS (cont) Revision Approved Number Revised Description of Revisions Signature Code and Date Pages REPORT: VB-1612 ISSUED: JULY 12, 1995 vi-f REVISED: NOVEMBER 1, 2010 HB-PQY, Page: 0-0-(12) Revision: 23, NOVEMBER 1, 2010 vi-f...
  • Page 14 ARROW PA-28R-201, TABLE CONTENTS SECTION GENERAL LIMITATIONS SECTION PROCEDURES EMERGENCY SECTION PROCEDURES SECTION NORMAL PERFORMANCE SECTION SECTION BALANCE WEIGHT OPERATION DESCRIPTION SECTION ITS SYSTEMS AIRPLANE SERVICING AIRPLANE HANDLING, SECTION AN]) MAINTENANCE SUPPLEMENTS SECTION OPERATING TIPS SECTION REPORT: VB-1612 12, 1995 ISSUED: JULY HB-PQY, Page: 0-0-(13)
  • Page 15 PA-28R-201, ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT: ‘111-1612 ISSUED: JULY 12, 1995 HB-PQY, Page: 0-0-(14) Issued: JULY 12, 1995 viii...
  • Page 16 SECTION ARROW PA-28R-201, GENERAL TABLE OF CONTENTS SECTION GENERAL ParagTaph Page Introduction Engines Propellers Fuel 1.11 Maximum Weights 1.13 Standard Airplane Weights 1.15 BaggageSpace 1.17 SpecificLoadings 1.19 Symbols, Abbreviations and Terminology REPORT: VB-1612 ISSUED: JULY 12,1995 HB-PQY, Page: 1-0-(1) Issued: JULY 12, 1995...
  • Page 17 SCT1ON PA-28R-201, ARROW GENERAL THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 1-il HB-PQY, Page: 1-0-(2) Issued: JULY 12, 1995 1-ii...
  • Page 18: Introduction

    SECTION ARROW PA-28R-20i, GENERAL SECTION GENERAL 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 the Federal Aviation Regulations and additional information by the manufacturer constitutes the FAA...
  • Page 19 GENERAL ARROW PA-28R-2O, 170.0 31.0 THREE VIEW Figure 1-1 REPORT: VB-1612 ISSUED: JULY 12, 1995 HB-PQY, Page: 1-2-(0) Issued: JULY 12, 1995...
  • Page 20: Engines

    SECTEON ARROW GENERAL PA-28R-201, 1.3 ENGINES (a) Number of Engines (b) Engine Manufacturer Lycoming (c) Engine Model Number IO.360-C1C6 (d) Rated Horsepower 2700 (e) Rated Speed (rpm) 5.125 (I) Bore(in.) 4.375 (g) Stroke (in.) (h) Displacement (cu. in.) 8.7:1 Ratio (I) Compression Four Cylinder, Direct (j) Engine Type...
  • Page 21 SECTION PA-28R-201, ARROW GENERAL 1.5 PROPELLERS (continued) HARTZELL (a) Number of Propellers (b) Propeller Manufacturer Hartzell (c) Blade Model F7666A-2R (d) Number of Blades (e) Hub Model HC-C2YK-1( (f) Propeller Diameter (in.) (1) Maximum (2) Minimum Constant Speed, (g) PropellerType Hydraulically Actuated 1.7 FUEL (a) Fuel Capacity (U.S.
  • Page 22 SECTION GENERAL ARROW PA-28R-201, WEIGHTS 1.11 MAXIMUM 2750 (a) Maximum Takeoff Weight (lb.) (b) Maximum 2750 Landing Weight (lb.) (c) Maximum Weights in Baggage Compartment WEIGHTS* 1.13 STANDARD AIRPLANE (a) Standard Empty Weight (lb.): Weight of a standard airplane including unusable fuel, full operating fluidsand 1603 fulloil.
  • Page 23 SECTION GENERAL ARROW PA-28R-201, 1.19 SYMBOLS, ABBREVIATIONS TERMINOLOGY definitions are of symbols, abbreviations following and those which used throughout the handbook be of terminology 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.Calibrated airspeed is equal...
  • Page 24 SECTION ARROW GENERAL PA-28R-201, TERMINOLOGY 1.19 SYMBOLS, ABBREVIATLONS, (continued) Maximum Landing Gear Extended Speed is speed at which an aircraft can the maximum be safely flown with the landing gear extended. Landing Gear Operating Speed is Maximum the maximum speed at which the landing gear can be safely extended orretracted.
  • Page 25 SECTION GENERAL ARROW PA-28R-201, 1.19 SYMBOLS, AN]) TERMINOLOGY ABBREVIATIONS, (continued) (b) Meteorological Terminology International StandardAtmosphere which: (I) Theairisadiyperfectgas. (2) The temperature at sea level is 15° Celsius Celsius (59° Fahrenheit). (3) The pressure atsea levelis29.92 inches Hg (1013.2mb). (4) The temperature gradient from sea level to the altitude at which the temperature is -56.5°C is 0.00198°C...
  • Page 26 SECTION ARROW GENERAL PA-28R-201, TERMINOLOGY 1.19 SYMBOLS, ABBREVIATIONS, (continued) Cc) Power Terminology power permissible for takeoff. Takeoff Power Maximum Maximum Con- Maximum power permissible continuously tinuous Power during flight. Maximum Maximum Climb power permissible during climb. Power Maximum Maximum Cruise during power permissible...
  • Page 27 GENERAL ARROW PA-28R-201, 1.19 SYMBOLS, TERMINOLOGY ABBREVIATIONS, (continued) (f) Weight and Balance Terminology Reference Datum An imaginary vertical plane from which all horizontal distances are measured balance purposes. Station location along the airplane fuselage usually given in terms of distance from the reference datum.
  • Page 28: Maximum Weights

    SECTION ARROW GENERAL PA-28R-201, 1.19 SYMBOLS, TERMINOLOGY (continued) ABBREVIATIONS, Basic Empty Standard empty weight plus optional Weight equipment Weight of occupants, cargo and baggage. Payload takeoff weight, or Difference between Useful Load ramp weight if applicable, and basic empty weight. for ground MaximumRamp Maximumweight...
  • Page 29: General

    SECTION ARROW GENERAL PA.28R-201, THJS PAGE INTENTIONALLY LEFF BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 1-12 HB-PQY, Page: 1-12-(0) Issued: JULY 12, 1995 1-12...
  • Page 30 SECTION ARROW PA-28R-201, LIMITATIONS TABLE CONTENTS SECTION LIMITATIONS Paragraph Page General Airspeed Limitations Airspeed Indicator Markings Power Plant Limitations Power Plant Insfrument Markings 2J I Weight Limi 2.13 Center of Gravity Limi Limi 2.15 Maneuver Flight Load Factors 2.17 2.19 ‘Ipes of Operations Fuel Limitations 2.21...
  • Page 31: Issued: July

    SECTION ARROW LThIITATIONS PA-28R-201, THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 2-li HB-PQY, Page: 2-0-(2) Issued: JULY 12, 1995 2-ii...
  • Page 32: Airspeed Limitations

    SECTION ARROW LIMITATIONS PA-28R.201, SECTION LIMiTATIONS GENERAL This section provides the FAA limitations, Approved operating instrument markings, color coding and basic placards necessary for the safe operation of the airplane and its systems. and equipment Limitations associated with those optional systems in Section be found which...
  • Page 33: Airspeed Indicator Markings

    SECTION LIMITATIONS ARROW PA-28R-201, AIRSPEED LIMITATIONS (continued) SPEED KIAS KCAS Maximum Flaps Extended Speed (VFE) Do not exceed this speed with the flaps extended. Maximum Landing Gear Extension Speed Do not exceed this speed when extending the landing gear. Maximum Landing Gear Retraction Speed Do not exceed this speed when retracting the landing gear.
  • Page 34 SECTION ARROW LIMITATIONS PA-28R-201, POWER PLANT LIMITATIONS (a) Number of Engines (b) Engine Manufacturer Lycoming (c) Engine Model No. 10-360-C 1C6 (d) Engine Operating Limits (1) Maximum Horsepower 2700 (2) Maximum Rotation Speed (RPM) 245°F (3) Maximum Oil Temperature (e) Oil Pressure 25 PSI Minimum (red line)
  • Page 35 ARROW LIMITATIONS PA-28R-201, POWER PLANT INSTRUMENT MARKINGS (a) Tacbometer Green Arc (Normal Operating Range) 500 to 2700 RPM Red Line (Maximum Continuous 2700 RPM Power) (b) Oil Temperature Green Arc (Normal Operating Range to 245°F Red Line (Maximum) 245°F (c) Oil Pressure Green Arc (Normal Operating Range 60 PSI to90 PSI Yellow Arc (Caution Range) (Idle)
  • Page 36 SECTION ARROW PA-28R-201, LIMITATIONS 2.11 WEIGHT LIMITS (a) Maximum 2750 LBS. Weight (b) Maximum 200 LBS. Baggage NOTE Refer to Section 5 (Performance) for maximum weight as limited by performance. 2.13 CENTER GRAVITY LIMITS Forward Limit Rearward Limit Weight Pounds Inches Aft of Datum Inches Aft of Datum 91.5...
  • Page 37: Fuel Limitations

    ARROW LIMITATIONS PA-28R-201, 2.17 LOAD FACTORS FLIGHT (a) PositiveLoad Factor (Maximum) 3.8 G (b) Negative Load Factor (Maximum) No invertedmaneuve approve.. 2.19 TYPES OPERATIONS The airplane is approved for the following operations when equipped in accordance with FAR 91 or FAR 135.
  • Page 38: Placards

    SECTION ARROW LIMITATIONS PA-28R-201, 2.23 PLACARDS In fullview of the pilot: LMIIAIIU!N5 INFO?? NATION OIL COOLER WINTERIZATION TH1S AIRCRAFT APPROVED NIGHT I.F.R., NON-ICING FLIGHT WINTERIZATION PLATE TO 9? OR FAR WHEN IN ACCORDANCE WITH EQUIPPED REMOVED WHEN AMBIENT ACROBATIC TEMPERATURE EXCEEDS 50’F. INCLUDING MANEUVERS, SPINS,AFPROVED.
  • Page 39 SECTION LIMITATIONS ARROW PA-28R-201, 2.23 PLACARDS (continued) (Serial Numbers 2844001 through 2844021 only) In fullview of the pilot, the following Takeoff and Landing Checklists will be installed: TAKEOFF CHECKLIST Fuel on Proper Tank Fasten Belts/Harness ElectricFuel Pump Flaps Set Checked Trim Tab Set Engine Gauges Alternate Air Closed...
  • Page 40 SECTION ARROW LIMITATIONS PA-28R-201, 2.23 PLACARDS (continued) On the instrument panel in fullview of the pilot in aircraft with McCauley propeller installations only: BETWEEN AVOID CONTINUOUS OPERATIONS 1500 1950 RPM BELOW 15” MANIFOLD PRESSURE. In fullview of pilot: CAUTION COMPASS CAL.
  • Page 41 SECTION ARROW LIMITATIONS PA-28R-201, 2.23 PLACARDS (continued) On the aft baggage closeout: HEAVY MAXIMUM BAGGAGE 200 LBS. NO OBJECTS SHELF. Adjacent to upper door latch: ENGAGE LATCH BEFORE FLIGHT On insideof baggage compartment door: BAGGAGE MAX. LBS. WEIGHT DATA BAGGAGE LOADINGS BALANCE BETWEEN...
  • Page 42 —, ‘i-/ff-’-i’ (HB-2008-135R1) (Lç ATTN: Solomon Engineer, Boston 12 New Executive Hecht, Aerospace ACO, Park, England Burlington, MA fax: (781) 238-7170. Before using any approved 01803; telephone: (781) 238-7159; AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PT) in the FAA Flight Standards District Office (FSDO), or lacking a PT, your local FSDO.
  • Page 43 SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES TABLE CONTENTS SECTION EMERGENCY PROCEDURES Paragraph Page General Airspeeds For Safe Operation Procedures Checklist Emergency 3.5a Engine Fire During Start (3.9) 3.5b Engine Power Loss During Takeoff (3.11) 3.5c Engine Power Loss In Flight (3.13) Power Off Landing (3.15) 3.5d Gear Down...
  • Page 44 SECTION ARROW EMERGENCY PROCEDURES PA-28R-201, TABLE COITENTS SECTION PROCEDURES EMERGENCY (cont) Page Paragraph Procedures (General) 3-11 Amplified Emergency 3-11 Engine Fire During Start (3.5a) 3.11 Engine Power Loss During Takeoff (3.5b) 3-11 3.13 Engine Power Loss In Flight (3.5c) 3-12 3.15 Power Off Landing (3.5d) 3-13...
  • Page 45 SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES SECTION EMERGENCY PROCEDURES 3.1 GENERAL This section provides the recommended for coping with procedures various emergency or criticalsituations.All of the emergency procedures required by the FAA as well as those necessary for operation of the airplane, as determined by the operating and design features of the airplane, are...
  • Page 46 SECTION ARROW EMERGENCY PROCEDURES PA-28R-201, AIRSPEEDS SAFE OPERATION 3.3a STALL SPEEDS 60 KIAS 2750 lbs (Gear Up, 0 Flap) 55 KIAS 2750 lbs (Gear Down, 40 Flap) 3.3b MA1EUVERING SPEEDS 27501bs 118 KIAS 1865 lbs 96KIAS 3.3c NEVER EXCEED SPEED Never Exceed Speed 183 KIAS 3.3d POWER...
  • Page 47 SECTION ARROW EMERGENCY PROCEDURES PA-28R-201, EMERGENCY PROCEDURES CHECKLIST 3.5a ENGINE FIRE DURING START (3.9) CRANK ENGINE Starter Mixture IDLE CUT-OFF OPEN Throttle ElectricFuel Pump Fuel Selector Abandon iffirecontinues. TAKEOFF POWER LOSS DURING 3.5b ENGINE (3.11) If sufficient runway remains for a normal landing, leave gear down and land straight ahead.
  • Page 48 SECTION ARROW EMERGENCY PROCEDURES PA-28R-201, ENGINE POWER LOSS IN FLIGHT 3.5c (3.13)(continued) Electricfuel pump RICH Mixture OPEN AlternateAir CHECK for indication Engine Gauges of cause of power loss Ifno fuel flow/pressure is indicated, check tank selector position to be sure itison a tank containing fuel. When power isrestored: AlternateAir...
  • Page 49 SECTION ARROW EMERGENCY PA-28R-201, PROCEDURES 3.5d POWER LANDING (3.15)(continued) Gear Up Emergency Landing (3.lSb) In the event a gear up landing is required, proceed as follows: AS DESIRED Flaps Throttle CLOSE Mixture IDLE CUT-OFF Ignition BATT MASTR Switch ALTR Switch Fuel Selector Seat Belt and Harness TIGHT...
  • Page 50 SECTION ARROW EMERGENCY PROCEDURES PA-28R-201, 3.5f LOSS PRESSURE (3.19) Land as soon as possible and investigate cause. Prepare for power off landing. 3.5g LOSS FUEL FLOW/PRESSURE (3.21) Electric Fuel Pump CHECK on tank Fuel Selector containing fuel 3.5h HIGH TEMPERATURE (3.23) Land at nearest airport and investigate the problem.
  • Page 51 SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES 3.Sj ELECTRICAL OVERLOAD (Alternator over 20 amps above known electrical load) (3.27)(Continued) Ifammeter reading does NOT decrease; ALTR Switch Land as soon as possible. Use Emergency Gear Extension Landing (3.5m) to lower landing gear. If ammeter reading DOES decrease: BATf...
  • Page 52 SECTION ARROW EMERGENCY PROCEDURES PA-28R-201, 3.5k PROPELLER OVERSPEED (continued) FULL DECREASE PronellerControl rpm, then set if any control available. REDUCE AS REQUIRED Throttle remain below 2700 rpm 3.Sm EMERGENCY LANDING GEAR EXTENSION (3.31) NOTE Refer to paragraph 4.39 for differences when emergency gear extension is being performed for training purposes.
  • Page 53 SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES 3.Sn SPIN RECOVERY (3.33) Rudder FULL OPPOSITE DIRECT[ON of ROTATION Control Wheel FULL FORWARD WHILE NEUTRALIZING AILERONS Throttle IDLE Rudder NEUTRAL (when rotation stops) Control Wheel AS REQUIRED to SMOOTHLY REGAIN LEVEL FLIGHT AlTITUDE 3.5o OPEN DOOR (3.35) If both upper and side latchesare open, the door will trail...
  • Page 54 SECTION ARROW PA-28R-201, PROCEDURES EMERGENCY BLANK LEFT PAGE INTENTIONALLY THIS REPORT: VB-1612 ISSUED: JULY 12,1995 3-10 HB-PQY, Page: 3-10-(0) Issued: JULY 12, 1995 3-10...
  • Page 55 SECTION PA-28R.201, ARROW EMERGENCY PROCEDURES 3.7 AMPLIFIED EMERGENCY PROCEDURES (GENERAL) are presented to supply following additional paragraphs information for the purpose of providing the pilot with a more complete understanding of the recommended course of action and probable cause of an emergency situation.
  • Page 56 SECTION ARROW EMERGENCY PROCEDURES PA-28R-201, DURING TAKEOPF ENGINE POWER LOSS (35b) (continued) will not be If engine failure was caused by fuel exhaustion, power regained after switching fuel tanks untilthe empty fuellines are filled. This may requireup to ten seconds. If power is not regained, proceed with the Power Off Landing procedure (refer to the emergency checklist and paragraph 3.15).
  • Page 57 SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES 3.13 ENGINE POWER LOSS.IN RJGRT (3.Sc)(continued) If engine failure was caused by fuel exhaustion power will not be restored after switching fuel tanks until the empty fuel lines are filled. This may requireup to ten seconds. If power is not regained, proceed with the Power Off Landing procedure (refer to emergency checklistand paragraph 3.15).
  • Page 58 SICE1ON ARROW EMERGENCY PROCEDURES PA-28R-201, 3.15 POWER LANDING (3.Sd)(continzzéd) 3.15a Gear Down (3.Sd) Emergency Landing to a gear down landing, select landing gear When committed emergency Flaps may be used as desired.Close the throttle control and move the DOWN. the ignition, battery master (BATT mixture control to idle cut-off.
  • Page 59 SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES 3.17 FIRE IN FLIGHT (3.Se) The presence of fireis noted through smoke, smell and heat in the cabin. It is essential that the source of the fire be promptly identified through instrument readings, character of the smoke, or other indications since the in each case.
  • Page 60 SECTION ARROW EMERGENCY PROCEDURES PA-28R-201, 3.19 LOSS OF OIL PRESSURE (3.Sf)(continued) be advisable to make an off on the circumstances, it may Depending airportlanding while power is still available, particularly ifother indications of actual oil pressure loss, such as sudden increases in temperatures, or oil smoke, are apparent, and an airport isnot close.
  • Page 61 SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES 3.25 ELECTRICAL FAILURE (3.Si) (continued) If the ammeter continues .to. indicate ZERO output, or if the alternator will not remain reset, turn off the ALTR switch, maintain minimum electrical load and land as soon as practical. All electricalload is being supplied by the battery.
  • Page 62 SECTION PA-28R.201, ARROW PROCEDURES EMERGENCY 3.29 PROPELLER OVERSPEED (3.5k) Propelleroverspeed is caused by a malfunction in the propellergovernor or low oil pressure which allows the propeller blades torotateto fulllow pitch. If propeller overspeed should occur, retard the throttle and check the oil to full DECREASE rpm and pressure.
  • Page 63 SECTION ARROW EMERGENCY PROCEDURES PA-28R-201, 3.33 SPIN RECOVERY (33n) Intentional spins are prohibited in this airplane. If a spin is inadvertently entered, immediately apply fullrudder opposite to the direction of rotation. the control wheel full forward while neutralizing the ailerons. Move Move the rotation stops, neutralizethe rudder and ease the throttle to IDLE.
  • Page 64 SECTION EMERGENCY ARROW PROCEDURES PA-28R-201, 3.37 ENGINE ROUGHNESS (3.Sp) (Continued The magneto switch should then be moved L, then R, then back to• BOTH. If operation is satisfactory on either magneto, proceed on that magneto at reduced power with fullRICH mixture to a landing at the first available airport.
  • Page 65 SECTION ARROW SUPPLEMENTS PA-28R-201, TABLE CONTENTS SECTION NORMAL PROCEDURES Paragraph Page General Airspeeds for Safe Operations Normal Procedures Checklist 4.5a Preflight Checklist (4.9) 4.5b Before StartingEngine Checklist (4.11) 4.5c Engine StartChecklist (4.13) ENGINE START GENERAL NORMAL START COLD ENGINE (4.13a) NORMAL START ENGINE...
  • Page 66 SECTION ARROW PA-28R-201, SUPPLEMENTS TABLE CONTENTS SECTION NORIvIAL PROCEDURES (cont) Paragraph Page 4.5h Takeoff Checklist (4.23) (continued SHORT OBSTACLE CLEARANCE FIELD, 4-11 TECHNIQUE (4.23b) SOFT FIELD 4-il TECHNIQUE (4.23b) 4.5i Climb Checklist (4.25) 4-12 4-12 4.5j CruiseChecklist(4.27) 4.5k Aproach And Landing Checklist (4.29) 4-12 4.5m Stopping Engine Checklist (4.31)
  • Page 67 SECTION ARROW PA-28R-201, SUPPLEMENTS TABLE CONTENTS SECTION NORMAL PROCEDURES (cont) Paragraph Page 4.13a Normal Start Cold Engine (4.5c) 4-18a 4.13b Normal Start Hot Engine (4.5c) 4-19 4.13c Engine StartWhen Flooded (4.5c) 4-19 4.13d Engine StartWith External Power Source (4.5c) 4-19 4.15 WARM-UP 4-20...
  • Page 68 SECTION ARROW SUPPLEMENTS PA-28R-201, TABLE CONTENTS SECTION NORMAL PROCEDURES (cont) Page Paragraph 4-27 GEAR 4.39 LANDING 4-28 4.41 WEIGHT BALANCE 4-28 4.43 NOISE LEVEL REPORT: VB-1612 12, 1995 ISSUED: JULY 4-iv 12, 2010 REVISED: HB-PQY, Page: 4-0-(4) Revision: 22, MAY 12, 2010 4-iv...
  • Page 69 SECTION PA-28R-201, ARROW NORMAL PROCEDURES SECTION NORMAL PROCEDURES GENERAL This section provides the normal operating procedures for the PA-28R- 201, Arrow airplane. All of the normal operating procedures required by the as well as those procedures which have been determined as FAA, necessary for the operation of the airplane, as determined...
  • Page 70 SECTION ARROW PROCEDURES NORMAL PA-28R-201, AIRSPEEDS SAFE OPERATIONS are significant to the safe The following airspeeds are those which operation of the airplane. These figures are for standard airplanes flown at gross weight under standard conditions at sea level. vary from published figures Performance for a specificairplane may the equipment...
  • Page 71: Figure

    SECTION ARROW PA-28R-201, NORMAL PROCEDURES WALK-AROUND Figure 4-1 NORMAL PROCEDURES CHECKLIST 4.5a Preflight Checklist (4.9) CAUTION 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. COCKPIT (4.9a) Control Wheel...
  • Page 72 SECTION NORMAL PROCEDURES ARROW PA-28R-201, 4.5a Preflight Checklist (4.9)(continued) COCKPIT (4.9a)(continued) Fuel Gauges check QUANTITY CHECK Annunciator Panel BATT MASTR Switch OPERATION Primary Flight Controls PROPER PROPER OPERATION Flaps NEUTRAL Trim Pitot and Static Systems DRAIN Windows check CLEAN Required Papers and POH check ON BOARD Tow Bar and Baggage...
  • Page 73 SECTION ARROW PA-28R-201, NORMAL PROCEDURES 4.5a Preflight Checklist (continued) NOSE SECTION (4.9c) General Condition CHECK SECURE Cowling CHECK QUANTITY Dipstick PROPERLY SEATED Oil Filler Cap SECURE Engine Baffle Seals CHECK Windshield CLEAN Propeller and Spinner CHECK Air Inlets CLEAR AlternatorBelt CHECK TENSION CHECK...
  • Page 74 SECTION NORMAL PROCEDURES ARROW PA-28R-201, 4.5a Preflight Checklist (continued) LEFT WING (4.9d) (continued) DRAIN and CHECK Fuel Tank Sump for water,sediment, and proper fuel Tie Down REMOVE PitotMast REMOVE COVER HOLE CLEAR Wing Tip and Lights CHECK Aileron and Hinges CHECK Flap and Hinges CHECK...
  • Page 75 SECTION ARROW PA-28R-201, NORMAL PROCEDURES 4.5c Engine Start Checklist (4.13) ENGINE START GENERAL (4.13) CAUTION Do not attempt flight if there is no indication of primary alternator output. CAUTION If a positive oil pressure is not indicated within 30 seconds following an engine start, stop the engine and determine the trouble.
  • Page 76 SECTION NORMAL PROCEDURES ARROW PA-28R-201, 4.5c Engine Start Checklist (4.13)(continued) NORMAL START ENGINE (4.13b) Throttle 1/2 INCH OPEN ALTR Switch BATE MASTR Switch ElectricFuel Pump Mixture IDLE CUT-OFF CLEAR Propeller ENGAGE Starter Mixture ADVANCE ADJUST Throttle Oil Pressure CHECK ENGINE START WHEN FLOODED...
  • Page 77 SECTION ARROW PA-28R-201, NORMAL PROCEDURES 4.5c Engine Start Checklist (4.13) (continued) ENGINE START WITH EXTERNAL POWER SOURCE (4.13d) (continued) CAUTION It is possible to use the ship’s battery in parallel by turning only the battery master switch ON. This will give longer cranking capabilities, but will not increase the amperage.
  • Page 78 SECTION NORMAL PROCEDURES ARROW PA-28R-2Ol, 4.51 Ground Check Checklist (4.19) (continued) GROUND CHECK (4.19) (continued) CHECK Magnetos max. drop 175 RPM max. diff. 50 RPM inches Hg Vacuum 105.) CHECK Oil Temperature CHECK Oil Pressure Ammeter CHECK Annunciator Panel PRESS-TO-TEST EXERCISE then Propeller...
  • Page 79 SECTION ARROW PA-28R-201, NORMAL PROCEDURES 4.5h Takeoff Checklist (4.23) NORMAL TECHNIQUE (4.23a) Flaps Trim Accelerate to 65 to 75 KIAS. Control Wheel back pressure to ROTATE smoothly to CLIMB ATTITUDE SHORT OBSTACLE CLEARANCE FIELD, TECHNIQUE (4.23b) 25° (second notch) Flaps Accelerate to 50 to 60 KIAS depending on aircraft weight.
  • Page 80 SECTION NORMAL PROCEDURES ARROW PA-28R-201, 4.51 Climb Checklist (4.25) CLIMB (4.25) Best Rate (2750 lb.)(Gear Up, 90 KIAS flaps Up) Best Rate (2750 lb.)(Gear Down, 78 KIAS Flaps Up) Best Angle (2750 lb.) (Gear Up, 78KIAS flaps Up) Best Angle (2750 lb.) (Gear Down, 72KIAS Flaps Up) En Route...
  • Page 81 SECTION ARROW NORMAL PROCEDURES PA-28R-201, 4.Sm Stopping Engine Checklist (4.31) STOPPiNG ENGINE (4.31) CAUTION The flaps must be placed in the UP position for the flap step to support weight. Passengers should be cautioned accordingly. RETRACT Flaps ElectricFuel Pump Air Conditioner Avionics Electrical Switches FULL...
  • Page 82 SECTION NORMAL PROCEDURES ARROW PA-28R.201, THIS PAGE INTENTIONALLY LEFT BLANK VB-1612 ISSUED: REPORT: JULY 12,1995 4-14 HB-PQY, Page: 4-14-(0) Issued: JULY 12, 1995 4-14...
  • Page 83 SECTION PA-28R-201, ARROW NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES (GENERAL) The following paragraphs are provided to supply detailed information and explanations of the normal procedures necessary for the safe operation of the airplane. PREFLIGHT CHECK (4.5a) airplane should be given a thorough preflight and walk-around check.
  • Page 84 SECTION ARROW NORMAL PROCEDURES PA-28R-201, PREFLIGHT CHECK (4.5a)(continued) 4.9b (4.5a)(continued) Right Wing Open the fuel cap and visually check the fuelcolor. The quantity should match the indicationthatwas on the fuel quantity gauge. Replace cap securely. The fueltank vent should be clear of obstructions. CAUTION When draining any amount of fuel, care should...
  • Page 85 SECTION ARROW NORMAL PROCEDURES PA-28R.201, PREFLIGHT CHECK (4.Sa) (continued) 4.9e Nose Section (4.5a) (continued) CAUTION draining any amount of fuel, care should When be taken to ensure that no fire hazard exists before starting engine. the fuel strainerlocated on the leftside of the firewall long enough Open to remove any accumulation of water and sediment.
  • Page 86 SECTION NORMAL PROCEDURES ARROW PA-28R-201, PREFLIGHT CHECK (4.5a) (continued) 4.9e Fuselage (4.5a) (continued) returning to the cockpit, an operational check of the interior lights, Upon exterior lights, stall warning system, and pitot heat should now be made. Turn the battery master switch and other appropriate switches ON. Check the panel lighting and the overhead flood light.
  • Page 87 SECTION ARROW NORMAL PA.28R-201, PROCEDURES 4.10 ENGINE START GENERAL CAUTION: Do not attempt flight ifthere is no indicationof alternator output. CAUTION: If a positive oil pressure is not indicatedwithin 30 seconds following an engine start, stop the engine and determine the trouble.
  • Page 88 SECTION NORMAL ARROW PROCEDURES PA-28R-201, IHIS PAGE INtENtIONALLY LEFT BLANK 12, 1995 ISSUED: JULY REPORT: VB-1612 12, 2010 REVISED: 4-l8b HB-PQY, Page: 4-18-(2) Revision: 22, MAY 12, 2010 4-18b...
  • Page 89 4.13d Engine Start With External Power Source (4.5c) optional feature called the Piper External Power (PEP) allows the operator to use an external battery to crank the engine without having to gain access to the airplane’s battery. the alternator switch, the battery master...
  • Page 90 SECTION NORMAL PROCEDURES ARROW PA-28R-201, 4.13 ENGINE START (4.Sc)(continued) 4.13d Engine Start With External Power Source (4.5c)(continued) NOTE For all normal the PEP operations using master cables, jumper battery alternatorswitches should be OFF. When the engine is firingevenly, advance the throttle to 800 rpm. If oil pressure is not indicated within thirtyseconds, stop the engine and determine the trouble.
  • Page 91 SECTION PA.28R-201, ARROW NORMAL PROCEDURES 4.17 TAXIING (4.5e)(continued) Observe wing clearances when taxiing near buildings or other stationary objects. If possible, station an observer outsidethe airplane. Avoid holes and rutswhen taxiing over uneven ground. 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: 4.19 GROUND...
  • Page 92 SECTION NORMAL PROCEDU ARROW PA-28R-201, 4.21 BEFORE TAKEOFF (4.5g) After all aspects of the takeoff are considered, a before takeoff check procedure must be performed. Verify that the battery master and alternatorswitches are ON. Check set allof the night instruments as required. Check the fuel selectorto make sure itis on the proper tank (fullest).
  • Page 93 • SECTION PROCEDURES PA-28R-201, ARROW NORMAL 4.25 CLIMB (4.51) On climb-out after takeoff, it is recommended that the best angle of be maintained only if obstacle clearance is a climb speed (78 KIAS) consideration. The best rate of climb speed (90 KIAS) should be maintained with full power on the engine until adequate terrain clearance is obtained.
  • Page 94 SECTION ARROW NORMAL PROCEDURES PA-28R-201, 4.27 CRUISE (4.53) (Continued) To lean the mixture, disengage the lock and pull the mixture control until the engine becomes rough, indicating that the lean mixture limit has been reached in the leaner cylinders. Then enrich the mixture by pushing the control towards the instrument panel until engine operation becomes...
  • Page 95 SECTION ARROW NORMAL PROCEDURES PA.28R-201, 4.29 APPROACH LANDING (4.5k) Check to ensure the fuel selector is on the proper (fullest) tank and that the seat backs are erect.The seat belts and shoulder harness should be fastened and the inertiareelchecked. the electricfuel pump. mixture should be set in the full Turn ON RICH...
  • Page 96 SECTION ARROW NORMAL PROCEDURES PA-28R-201, 4.31 STOPPING ENGINE (4.5w) (continued) The electric fuel pump, air conditioner, radios, and all electrical switches should be turned OFE Set the propeller in the full INCREASE position. Stop the engine by disengaging the mixture control lock and pulling the mixture control back to idle cut-off.The throttleshould be left full aft to avoid...
  • Page 97 SECTION ARROW NORMAL PROCEDURES PA-ZSR.201, 4,37 TURBULENT OPERATION In keeping with good operating practice used in all aircraft, it is recommended that when turbulent airis encountered or expeced, he airspeed be reduced to maneuvering speed to reduce the structural loads caused by gusts and to allow for inadvertent speed build-ups which may occur as a result of the turbulence or of distractionscaused by he conditions.
  • Page 98 SECTION ARROW NORMAL PROCEDURES PA-28R-201, BALANCE 4.41 WEIGHT and pilot to determine that the It is the responsibility of the owner airplane remains within the allowable weight vs. center of gravity envelope while in flight. For weight and balance data, refer to Section 6 (Weight and Balance). 4.43 NOISE LEVEL The noise level of thisaircraft is 75.5 d B(A).
  • Page 99 SECTIONS PA-28R.201, ARROW PERFORMANCE TABLE CONTENTS SECTIONS PERFORMANCE Page Paragraph ,.jenerw Performance and Flight Planning Introduction FlightPlanning Example Performance Graphs Listof Figures REPORT: VB-1612 12, 1995 ISSUED: JULY HB-PQY, Page: 5-0-(1) Issued: JULY 12, 1995...
  • Page 100 SECTION ARROW PERFORMANCE PA-28R-2O1, TilTS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 5-il HB-PQY, Page: 5-0-(2) Issued: JULY 12, 1995 5-ii...
  • Page 101 SECTION PA-28R-201, ARROW PERFORMANCE SECTION PERFORMANCE 5.1 GENERAL All of the required (FAA regulations) and complementary performance informationis provided by thissection. information associated with those optional systems and Performance supplements is provided by Section 9 equipment which require handbook (Supplements). ANt) FLIGHT PLANNING.
  • Page 102 s1c.i.1u1, PA-28R-201, ARROW PERFORMANCE THIS PAGE INTENTIONALLY LEFf BLANK REPORT VB-1612 ISSUED: JULY 12, 1995 HB-PQY, Page: 5-2-(0) Issued: JULY 12, 1995...
  • Page 103 SECTION PA-28R-201, ARROW PERFORMANCE 54 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 thishandbook. The basic empty weight for the airplane as licensed at the factory has been entered in Figure 6-5.
  • Page 104 SECTION ARROW PERFORMANCE PA-28R-2O1, 5.5 FLIGHT PLANNING EXAMPLE (continued) (b) Takeoff and Landing that the airplane loading has been determined, aspects of the takeoff and landing must now be considered. All of the existing conditions at the departure and destination airport must be acquired, evaluated and maintained throughout the flight.
  • Page 105 SECTIONS PA-28R-201, ARROW PERFORMANCE 5.5 FLIGHT PLANNING EXAMPLE (continued) (c) Climb The next step in the flightplan is to determine the necessary climb segment components. The desired cruise pressure altitudeand corresponding cruise outside air temperature values are the firstvariables to be considered considered in determining climb components from the Fuel, Time and...
  • Page 106 SECTION ARROW PA-28R-201, PERFORMtNCE 5.5 FLIGHT PLANNING EXAMPLE (continued) values from the graph (Figure 5-35). Subtract the values obtained obtained from the fieldconditions from the values obtained from the cruise conditions to find the true fuel, time and distances values needed for the flight plan.
  • Page 107 SECTIONS PA-28R-201, AR1OW PERFORMANCE 5.5 FLIGHT PLANNING EXAMPLE (continued) (3) Cruise Power (Best Economy) 65% rated power (2500 RPM) 7°C (4) CruiseDeltaOATfromlSA(10°C-3°C) [7/5.5 x .16]) 23.3 in Hg (5) Cruise Manifold Press. (23.1 130 Kts TAS* (6) Cruise Speed (7) Cruise Fuel Consumption 10.3 gph* (8) Cruise Thme (e)(2) divided by (e)(6), (108.5 naut.
  • Page 108 SECTIONS ARROW PERFORMANCE PA-28R-201, Tills PAGE INTENTIONALLY LEFT BLANK REPORT; VB-1612 ISSUED: JULY 12, 1995 HB-PQY, Page: 5-8-(0) Issued: JULY 12, 1995...
  • Page 109 SECTIONS ARROW PA-28R-201, PERFORMANCE 5.7 PERFORMAIJCE GRAPHS LIST OF FIGURES Figure Page 5-la Air Temperatures above & below ISA 5-lOa Temperature Conversion 5-11 Airspeed System Calibration 5-12 Power Off Stall Speed Vs. Angle of Bank 5-13 Wind Components 5-14 25° Flap Takeoff Performance Over 50 Foot Barrier 5-15 5-11 25°...
  • Page 110 SECTIONS ARROW PERFORMANCE PA-28R-201, 5.7 PERFORMANCE GRAPHS (Cont’d) LIST OF FIGURES (Cont’d) 5-29 Best PowerRange 5-27 (2500 RPM) 5-29a Best PowerRange 5-27a (2200 RPM) 5-31 Best Economy 5-27b (2200RPM) Range 5-3 laBest Economy 5-28 (2500RPM) Range 5-33 Best Power Endurance 5-29 (2500 RPM) 5-33aBest Power Endurance...
  • Page 111 SECTIONS PA-28R-201, ARROW PERFORMANCE Example: Example: 16000 Altitude: 6000 C @6000 ISA + 7 14000 12000 —Zrt Ll0000 8000 “ 6000 \ ‘[4\ ‘ 4000 TEMPERATURE °C ABOVE & BELOW TEMPERATURES Figure 5-la REPORT: VB-1612 ISSUED: JULY 12,1995 5.lOa HB-PQY, Page: 5-10-(1) Issued: JULY 12, 1995 5-10a...
  • Page 112 ULiUI PA-28R-201, ARROW PERFORMANCE BLANK LEFJ THIS PAGE INTENTIONALLY VB-1612 ISSUED: REPORT: JULY 12, 1995 5-lob HB-PQY, Page: 5-10-(2) Issued: JULY 12, 1995 5-10b...
  • Page 113 SECTIONS ARROW PERFORMANCE PA-28R-2O1, —20 CELSIUS FAHRENHEIT DEGREES DEGREES CONVERSION TEMPERATURE Figure 5-1 REPORT: VB-1612 ISSUED: JULY 12,1995 HB-PQY, Page: 5-11-(0) Issued: JULY 12, 1995 5-11...
  • Page 114 SECTIONS ARROW PA-28R-201. PERFORMANCE <: — O•e <‘° >- (1)—U) S*ON G3dSUIV G3LVIOflV AIRSPEED SYSTEM CALIBRATION Figure 5-3 REPORT: VB-1612 ISSUED: JULY 12, 1995 5-12 HB-PQY, Page: 5-12-(0) Issued: JULY 12, 1995 5-12...
  • Page 115 SECTIONS ARROW PA-28R-201, PERFORMANCE £ FLI. LL.>_J •r O3RdS TIVLS OF BANK SPEED VS. ANGLE ST4LL POWER Figure 5-5 VB-1612 REPORT: ISSUED: JULY 12,1995 5-13 HB-PQY, Page: 5-13-(0) Issued: JULY 12, 1995 5-13...
  • Page 116 SECTIONS ARROW PERFORMANCE PA-28R-201, WIND COMPONENTS Example: Wind velocity: 30 knots between wind: Angle flight path knots Headwind component: Crosswind 15 knots components: ‘U CROSSWIND COMPONENT KTS. WIND COMPONENTS Figure 5-7 REPORT: VB-1612 ISSUED: JULY 12, 1995 5-14 HB-PQY, Page: 5-14-(0) Issued: JULY 12, 1995 5-14...
  • Page 117 SECTIONS • PA-28R-201, ARROW PERFORMANCE .L33d 33NVJ.SIO O3)vJ. Ppi:: IJIL <V •< •LL Cl) C4 Ui Wi øbc > •t ;• ...1 ________ ______ V••VV • • • • • • OL& ____ PERFORMANCE 25° 1LAP TAKEOFF Figure 5-9 VB-1612 REPORT: 1995 ISSUED:...
  • Page 118 iL1JI4 PA.28R-201, ARROW PERFORMANCE • iiôu iO3(V dnóe CNIMO iuii +4+i- •.H •IW —I ± ± 2<ot C, z >. ±fb 1Iti im> -ii- ______ —-44— d—’ —I FLAP TAKEOFF GROUND ROLL Figure5-11 REPORT: VB-1612 ISSUED: JULY 12, 1995 5-16 HB-PQY, Page: 5-16-(0) Issued: JULY 12, 1995 5-16...
  • Page 119 SECTIONS ARROW PERFORMANCE PA-28R-201, 33NvsIa 4O3IV.L 1_Qg ‘1w PERFORMANCE TAKEOFF 00 FLAP Figure 5-13 REPORT: VB-112 12, 1995 JULY ISSUED: HB-PQY, Page: 5-17-(0) Issued: JULY 12, 1995 5-17...
  • Page 120 SECTION PA-28R-201, ARROW PERFORMANCE J4 -1IOU CNflOUD O3)IVL aO4Z-Thflu §!ia f— mill > D• uO-D >c rCI. > — (‘41 • 0° FLAP TAKEOFF GROUND ROLL Figure 5-15 REPORT: VB-1612 ISSUED: JULY 12, 1995 5-18 HB-PQY, Page: 5-18-(0) Issued: JULY 12, 1995 5-18...
  • Page 121 PA-28R.201, ARROW PERFORMANCE ______ I— C-’ z-° n_ 0 oII.0 o 34 GEAR UP CLIMB PERFORMANCE Figure 5-17 12, 1995 REPORT: VB-1612 ISSUED: JULY : in HB-PQY, Page: 5-19-(0) Issued: JULY 12, 1995 5-19...
  • Page 122 SECTION PA-28R-201, ARROW PERFORMANCE DOWN CLIMB PERFORMANCE GEAR Figure549 REPORT: VB-1612 ISSUED: JULY 12,1995 5-20 HB-PQY, Page: 5-20-(0) Issued: JULY 12, 1995 5-20...
  • Page 123 SECTION PA-28R-201, ARROW PERFORMANCE Oø ‘;.4E zjj0o ff’ u)• iiiI1t\ CLIMB DISTANCE TIME FUEL, Figure 5-21 REPORT: VB-1612 12, 1995 ISSUED: JULY HB-PQY, Page: 5-21-(0) Issued: JULY 12, 1995 5-21...
  • Page 124 SECTION ARROW PERFORMANCE PA-28R-2O1, THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 5-22 HB-PQY, Page: 5-22-(0) Issued: JULY 12, 1995 5-22...
  • Page 125 SECTIONS PA.28R-201, ARROW PERFORMANCE —“ pD,_ QL.. •as 0... •,m 0•- toc1& p po ,p=_ I— TABLE (Best Power) POWER SETTLNG 5-23 Figure VB-1612 REPORT: 12, 1995 ISSUED: JULY HB-PQY, Page: 5-23-(0) Issued: JULY 12, 1995 5-23...
  • Page 126 SECTIONS ARROW PA-28R-201. PERFORMANCE 0.13 (UQ. I—c Ii” POWER SETI1NG TL4BLE (Best Economy) Figure 5-23a REPORT: VB-1612 ISSUED: JULY 12, 1995 5-24 HB-PQY, Page: 5-24-(0) Issued: JULY 12, 1995 5-24...
  • Page 127 SECTION PA-28R.201, ARROW PERFORMANCE UJ0c i-u, U2 C1 c,1x: Co x_• 00000000000 000000000000CI) .3cJfllLLlV 3èJflSS3id 133d POWER CRUISE Power) BEST (75% Figure 5-25 VB-1612 REPORT: 12, 1995 JULY ISSUED: HB-PQY, Page: 5-25-(0) Issued: JULY 12, 1995 5.25...
  • Page 128 SECTION PERFORMANCE ARROW PA-28R-201, Ii’ II’IIIJj ULII II’IIIJj Irtf,wIIIn*w II Oø w iu C’1W K+iNJJflj üii z:::ia [J1ii ø I— II’ll E222 OQIpIIIIIIIIIII II’ll III II II Ij) II OQIpIIIIIIIIIII O0000O0Q00 .L33d 3afti.Lnv 3IflSS3eId BEST POWER CRUISE (65% Power) Figure 5-25a REPORT: VB-1612 ISSUED:...
  • Page 129 SECTION PA-28R.201, ARROW PERFORMANCE a_c’ ‘-0 —a-u, ci,g ‘ C)C’1’ COLD CN0O) 3CflJJI1V 3NflSS3d 133d POWER CRUISE BEST (55% Power) Figure 5-25b REPORT: VB-1612 12, 1995 JULY ISSUED: .2ch HB-PQY, Page: 5-25-(2) Issued: JULY 12, 1995 5.25b...
  • Page 130 SECTIONS PERFORMANCE ARROW PA-28R-201, c’J wc’ l.() fl41 EE811W NHLW1LWHJJH1U ‘—LU 0WL1 UJh. o9-& ZLLJCD •di ..ç, <0. a< 1.-I- 000000000 000000000 000000000 Ct)Cs1 ‘- 3anlIl-1v 3iflSS3Id 133d ECONOMY CRUISE Power 2200 RPM) (55% Figure 5-27 REPORT: VB-1612 ISSUED: JULY 12, 1995 5-26 HB-PQY, Page: 5-26-(0)
  • Page 131 SECTIONS PERFORMANCE PA-28R-201, ARROW ‘C1) 1,It1.1i u)rI E 222 11111111111 liii 1.31 II j:.’ 0000000000 t’. 3OfliLL1V NflSS3Nd .L33d (55% Power 2500 RPM) CRUISE ECONOMY Figure 527a REPORT: VB-1612 JULY 12, 1995 ISSUED: 5-26a HB-PQY, Page: 5-26-(1) Issued: JULY 12, 1995 5-26a...
  • Page 132 SECTIONS ARROW PA-28R-201, PERFORMANCE LLCI U,cD U,cD >- 1° .L33d 3QILIJJIV 3IflSS3fd ECONOMY CRUISE Power 2200 RPM) (65% Figure 5-27b REPORT: VB-1612 ISSUED: JULY 12, 1995 S-26b HB-PQY, Page: 5-26-(2) Issued: JULY 12, 1995 5-26b...
  • Page 133 SECTION ARROW PERFORMANCE PA-28R-201, B111FF1 HIIF III1iHI 4444 ‘0 U.tQ anø Iujj >$D 1001 < It’ III! 0 3QflJJJIV 3IflSS3Nd !33d 2500 RPM) Power CRUISE ECONOMY (65% Figure 5-27c VB-1612 REPORT: 12, 1995 ISSUED: JULY 5-26c HB-PQY, Page: 5-26-(3) Issued: JULY 12, 1995 5-26c...
  • Page 134 SECTION PA-28R-201, ARROW PERFORMANCE BLANK LEFT THIS PAGE INTENTIONALLY REPORT: VD-1612 ISSUED: JULY 12,1995 5-26d HB-PQY, Page: 5-26-(4) Issued: JULY 12, 1995 5-26d...
  • Page 135 SECTIONS ARROW PERFORMANCE PA-28R-201, flTfl [i1’irl1r111 lilt I 11111 liii I I II I-ill .i.I.I.1IIIllIIIIl II ) 1l II IL l ILlil IImrrrt-N-.0rl fin r n TI ill 691t11 llI1IIIIIII11 11111 III liii IIIIII liii 11111111 0’ _______ 1B’’ll tilIII I—0 hull 0 U) U) U)
  • Page 136 SECTIONS ARROW PERFORMANCE PA-28R-201, •g 30n.LJJIV ] flSSNd • BEST POWER RANGE (2200 RPM) Figure 5-29a REPORT: VB-1612 ISSUED: JULY 12, 1995 5-27a HB-PQY, Page: 5-27-(1) Issued: JULY 12, 1995 5-27a...
  • Page 137 SECTION PA-28R-201, ARROW PERFORMANCE rnrr IiI II II1lIIII I.IEB+I±H E1L I[{ II II ±uIIn 111(1111—I I11’’li U.L! •—•i••ii liii +EEUFFBL1IIW]FB I UUi Ii’ IIIIII I 111111111 lljjflniuijUj ______ fflTflrr• tillIELtIlIllil I11)]I[1J]1i)1 ]II1)]IUL1J i 111I1iiIiIl)IiH § ]afUUiv ISSd RANGE ECONOMY (2200 RPM) BEST Figure 5-31 VB-1612...
  • Page 138 SECTIONS PA-28R-201, ARROW PERFORMANCE 11111)11 1111111 1IJ1—lllllllilIllIlll hIll’’’’ llll g ‘.1 11)11 • irrrr iilimwUiI1 lull l iii I iii1Fff1 1111111 11 [11i4!.1 Ii’ If F[flHfl1fl1Tfl I[IlI1 IliRilin 11441I1I 11W W 11111 >- 1.[II 11111 1111 l11i44.U.i Iou.I C 1111111 II 111111 IiEIEt1 11.l.1i11tt11Il1U...
  • Page 139 SECUON PA-28R.201, ARROW PERFORMANCE IlIIIIIIIIIIIIIIIIIIIIIIIII1Il1’ ‘ ‘U 1It11rje ‘U C40Q ‘U CD ID ‘‘I iiiiil ll_ii ¶fl1’ III l iii ii’ IILII If II Ullill HHfH LIiiLH0LUfUi1 -ö aniu.v ENDURANCE (2500 RPM) BEST POWER Figure 5-33 REPORT: VB-1612 12, 1995 ISSUED: JULY 5.29...
  • Page 140 SECTIONS ARROW PA-28R-201, PERFORMANCE 111111 i1II11I 11111111111) ‘U WI I c’i OIQ.— I II’ III’’’ c_o_ “ I liii ITI III II I I IIIIIII(I[[lIII1 §-. 88888 — .L]d aofl.LLLW flSSd BEST POWER ENDURANCE (2200 RPM) Figure 5-33a REPORT: VB-1612 JISSUED: JULY 12, 1995...
  • Page 141 SECTION PERFORMANCE PA-28R-201. ARROW ____ III UhiuiNiliii)) lb ‘I’ll a’ II III l1lII) IIIjI III.. L T i{TffiIu u-Io u-Io —I ° § § § § § § § 3Cfl.LLflY flSSId (2200 RPM) ENDURANCE BEST ECONOMY Figure 5-33b VB-1612 REPORT: 12, 1995 JuLY ISSUED...
  • Page 142 SECTION ARROW PA-28R-201, PERFORMANCE §8888888 QftLLLY NflSS9d BEST ECONOMY ENDURANCE (2500 RPM) Figure 5-33c REPORT: VB-1612 ISSUED: JULY 12,1995 5-29c HB-PQY, Page: 5-29-(3) Issued: JULY 12, 1995 5-29c...
  • Page 143 SECTIONS ARkOW PERFORMANCE PA-ZSR-2O1, LEFT BLANK TifiS PAGE INTENTIONALLY • VB-1612 REPORT: ISSUED: JULY 12,1995 HB-PQY, Page: 5-29-(4) Issued: JULY 12, 1995 5-29d...
  • Page 144 SECTIONS PERFORMANCE ARROW PA-28R-201, ..Zw øui O< I— Iiiui1i TIME FUEL, DISTANCE DESCEND Figure 5-35 REPORT: VB-1612 ISSUED: 1995 JULY12, 5-30 HB-PQY, Page: 5-30-(0) Issued: JULY 12, 1995 5-30...
  • Page 145 SECTIONS PERFORMANCE A1UOW PA-28R-201, g;1lfi1h_-.LiHItIIi 4--f--- f I— 1111111 tl1-H-H1-I1I1ItI-N-14 1iItU ____ !JJHfHf±iH Ectthttjfttf±th±1 <0 _________ ZDC00 OgomZ_ UJ0O I—C)u. IIt1 ______ PFi ; DISTANCE GLIDE TIME Figure 5-37 REPORT: VB-1612 ISSUED: JULY 12,1995 c.ii HB-PQY, Page: 5-31-(0) Issued: JULY 12, 1995 5-31...
  • Page 146 SECTION ARROW PA-28R-201, PERFORMANCE ONION Vi .14 )NVSIO !L1i1. J[IIIJ > 0< hJbffi ii____ ____ LANDING DISTANCE OVER 50 FOOT BARRIER Figure 5-39 REPORT: VB4612 ISSUED: JULY 12, 1995 5.32 HB-PQY, Page: 5-32-(0) Issued: JULY 12, 1995 5-32...
  • Page 147 SECTION ARROW PA-28R-201, PERFORMANCE TiOll aNnoI9 NIONV1 • ] .<: C’ _______ _______ ___, •_______ • ROLL DISTANCE GROUND LANDING Figure 5-41 VB-1612 REPORT: 12, 1995 ISSUED: JULY HB-PQY, Page: 5-33-(0) Issued: JULY 12, 1995 5-33...
  • Page 148 SECTION ARROW PA-28R-201, PERFORMANCE LEFT BLANK THIS PAGE INTENTIONALLY REPORT; VB-1612 ISSUED: JULY 12, 1995 5-34 HB-PQY, Page: 5-34-(0) Issued: JULY 12, 1995 5-34...
  • Page 149 SECTION PA-28R-201, ARROW BALANCE WEIGHT TABLE OF CONTENTS. SECTION WEIGHT BALANCE Page Paragraph General Airplane Weighing Procedure Weight and Balance Data and Record Weight and Balance Determination for Flight Supplied with List (Form 240-0129) Equipment aircraft paperwork VB-1612 REPORT: 12, 1995 ISSUED: JULY HB-PQY, Page: 6-0-(1)
  • Page 150 SECTION ARROW PA-28R-201, BALANCE WEIGkIT LEFt’ BLANK THIS PAGE INTENTIONALLY REPORT: VB-1612 ISSUED: JULY 12, 1995 6-li HB-PQY, Page: 6-0-(2) Issued: JULY 12, 1995 6-ii...
  • Page 151 SECTION AN]) BALANCE PA-28R-201, ARROW WEIGHT SECTION WEIGHT BALANCE 6.1 GENERAL In order to achieve the performance and flying characteristics which are center of designed into the airplane, it must be flown with the weight and gravity (C.G.) position within the approved operating range (envelope).
  • Page 152 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. The removal or addition of equipment or airplane modifications can affect the basic empty weight and center of gravity.
  • Page 153 SECTION PA-28R-201, ARROW WEIGHT 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 engines for a minimum of 3 minutes at 1000 rpm on each tank to insure no air exists in the fuel supply lines.
  • Page 154 SECTION WEIGHT AN]) BALANCE ARROW PA.28R-201, 6.3 AIRPLANE WEIGHING PROCEDURE (continued) Scale Tare Scale Positionand Symbol Reading Weight Nose Wheel Right Main Wheel Left Main Wheel Basic Empty Weight, as Weighed (‘I) WEIGHING FORM Figure 6-1 (d) Basic Empty Weight Center of Gravity (1) The applies to the PA-28R-201 following...
  • Page 155 SECTION ARROW WEIGHT PA-28R-201, BALANCE 6.3 AIRPLANE WEIGHING PROCEDURE (continued) (2) The basic empty center of gravity (as weighed weight full oil and unusable fuel) including optional equipment, can be detenitined by the following formula: inches C.GArm=N(A)+(R+L)(B) T=N+R+L Where: 6.5 WEIGHT BALANCE DATA RECORD...
  • Page 156 SECTION WEIGHT BALANCE PA-28R-201, ARROW 6.5 WEIGHT DATA BALANCE RECORD (continued) MODEL PA-28R-201 ARROW Airplane SerialNumber 2844120 ‘f Registration Number Date 04!28/05 AIRPLANE BASIC EMPTY WEIGHT C.G.Arm x (Inches Aft Moment Weight Item of Datum) (Lbs) (In-Lbs) Actual 1797.0 85.8819 154329.8 Standard Empty Weight*...
  • Page 157 SECTION PA-28R-201, ARRO WEIGHT BALANCE (continued) •-o pow’>J pppv UI.0fl WEIGHT BALANCE RECORD Figun 6-7 ISSUED: JULY 12, 1995 REPORT: VB-1612 HB-PQY, Page: 6-7-(0) Issued: JUNE 5, 2009...
  • Page 158 SECTION WEIGHT P ND BALANCE ARROW PA-28R-201, 6.5 WEIGHT DATA BALANCE RECORD (continued) •P a’ —: <ti. <ti. pAOUIJ poppy — r’ WEIGHT BALANCE RECORD (cont) Figure 6-7 (cont) REPORT: VB-1612 ISSUED: JULY 12, 1995 HB-PQY, Page: 6-8-(0) Issued: JULY 12, 1995...
  • Page 159 SECTION PA-28R-201, ARROW WEIGHT BALANCE 6.7 WEIGHT BALANCE DETERMNATJON 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 allitems to be carriedin the airplane. (c) Add the moment of allitems to be loaded to the basic empty weight moment.
  • Page 160 SECTION ARROW WEIGHT BALANCE PA28R-201, FLIGHT 6.7 WEIGHT BALANCE DETERMINATION (continued) Datum Moment Weight (Inches) (In-Lbs) (Lbs) Basic Empty Weight Pilotand Front Passenger 80.5 118.1 Passengers (Rear Seats) Fuel (72 Gallons Maximum) 95.0 Baggage (200 Lbs. Maximum) 142.8 Weight (2758 Lbs. Ramp Maximum) Fuel Allowance For Engine...
  • Page 161 SECTION ARROW WEIGHT BALANCE PA-28R-201, 6.7 WEIGHT BALANCE DETERMINATION FLIGHT (continued) GRAPH LOADING Figure 6-13 REPORT: VB-1612 12, 1995 ISSUED: JULY HB-PQY, Page: 6-11-(0) Issued: JULY 12, 1995 6-11...
  • Page 162 SECTION WEIGHT BALANCE ARROW PA-28R-201, 6.7 WEIGHT DETERMINATION FLIGHT BALANCE (continued) 2600 2400 1600 1400 INCHES AFT OF DATUM C. G RANGE WEIGHT Figure 6-15 REPORT: VB-1612 ISSUED: JULY 12, 1995 6-12 HB-PQY, Page: 6-12-(0) Issued: JULY 12, 1995 6-12...
  • Page 163 The following isa list o f standardand optional equipment forthePA-28R-20l Arrow. Optionalequipment itemsmarked with an X are installed on the airplane. All itemsare as described below at thetime of licensing b y themanufacturer. T he New Piper Aircraft, Inc.willnot revise this equipment list o nce theaircraft islicensed. I tistheowner’s responsibility to retain nod amend this equipment list t oreflect changes in equipment installed in this airplane.
  • Page 164 Piper PIPER AIRCRAFT, PA-28R-201, ARROV LIST EQUIPMENT SIN 2844116 and UP Item Arm (In.) Moment Weight Item (Pounds) Aft Datum (Lb-In.) (d) Miscellaneoas-continued Tow Bar, Piperdrawing 67336-0 2.20 156.00 343.20 OF STANDARD EQUIPMENT ISSUED: 02/27/04 240-0129 REVISED: 10/12/2004 2 of 17...
  • Page 165 0.068 273.04 18.65 Tail Light installation total weight 278.313 57.78 TailStrobe installation, Piperdrawing 104296-005, (MarketingOption 355) a. Strobe Light, Whelen 01-0790111-02, Piper code number 683-504 0.24 243.79 58.63 b. Cables/harnesses and hardware, Piperdrawing 104296-005 194.95 251.92 1.29 Tail Strobeinstallation 202.61 310.55...
  • Page 166 45tt64 S-FEC System 55X Autopilot with Compass STS- I80/HSl and Flight Director (AOl), Piperdrawing 104581-003or 104581-006,(MarketingOption 510 requires M arketing Option 595) a.) 5-TEC System 55 Autopilot with Compass STS-I 80/HSI. Piper drass ing 36.12 1t3.66 4506.48 104581-002 or 104511-005 (delta) b.) S-TEC 901415-11 Autopilot Cables...
  • Page 167 11.57 number 683-724 3.) Harness, and hardware, Piperdrawing 105329-003 1.29 53.19 68.59 c.) Altitude Reporterinstallation, Piperdrawing 101415-002 I.) Attitude Reporter, Amen-King Corporation Model AK-350, Piper code 0.57 51.04 29.04 number 602-290 2.) Altitude Reporterassembly and hardware, Piperdrawing 101415-002 0.34 53.52 18.17...
  • Page 168 Marker Beacon Cable and hardware, Piperdrasving 104253-003 0.70 136.26 94.99 6.) GPS Antenna #1 installation, Piperdrawing 104253-003 a.) Garmin Antenna Kit. Partnumber 010-10040-1)1, Piper code numbe: sA72 sA72 I.) Ganssn GA56 Antenna, Partnumber 011-00 34-00. Piper code number 0.24 it6.l 28.11 65 t-72j b.) Coax Cable with hardware, Piperdrawing 104253-003...
  • Page 169 Deluxe Avionics System without Autopilot weight 21.11 99.30 2120.18 Deluse Avionics package-DunI GNS 430 with Honeywell KCS -55A HSI, Piper drawing CA-28-44l 10, (MarketingOption 595-Non Autopilot) a.) Garmin Dual GNS 430 GPS/Nav/Com, Piperdrawing 105327-002 I.) Gui-rain GNS43O (11-33 Vdc) #1 with mount, connectorsand data curd, 6.56...
  • Page 170 Option (Lb-In.) Installed (g)Optional Avionics Equipment-continued Deluxe Avionics package-Dual GNS 430 with Honeywell KCS -55A HSI, Piper drawing CA-28-44l 10, (MarketingOption 595 Non Autopilot-contittued c.) Attitude Ret’orter i nstallation, Piperdrawing 101415-002-continued 1.) Altitude Reporter, Amen-King Corporation Model AK-350, Piper code 0.57...
  • Page 171 58.14 381.18 Piper PS50040-40-4, Piper code number 601-229 60.23 61.43 3.) GarusinGI-lO6A Indicator # 1,Piper code number 602-239 1.02 4.) Garmin GI-lO6A Indicator # 2,Piper code number 602-239 1.02 60.23 61.43 5.) Cables/Harnesses a nd Hardware, Piperdrawing 105325-003 3.32 55.62 184.59...
  • Page 172 451 with /450 Indicator installation, Piper drawing 104257-003, (MarketingOption 575 requires Marketingoption 595,(Include itemsIII or 113))) a.) S-TEC DME installation kit. Piper PS50040-3 1-26, Piper cede number 601- I.) S-TEC Transceiver TCR-451, Partnumber 690109 4.80 200.70 963.36 2.) S-TEC Transceiver installation kit, P artnumber 690224 0.69...
  • Page 173 381.18 PiperPS50040-40-4, Piper drawing 101901-100 Piper code number 601-229 2.) Hardware Piperdrawiitgs 101901-100 0.07 62.95 4.17 3.) ‘lAy receising AV I 2-PPR nIentsa Piper code number 451-802 Piper 0.40 264.90 105.96 drawing 101901-100 Antenna Cable assembly par’ hardware Piperdrawind 101901-100 1.55...
  • Page 174 1.) Truspeed Indicator, Piper PS50049-32T United Instruments Piper code c’ 0 72 61 85 44 22 number 548-167, Cert. Basis TSO C2b 2.) Altimeter, Piper PS50008- I0-2D —United U15934PD-3A. 134, Piper code 60 89 52 33 0 86 number 599-549 Cert.Basis TSO CIOb ISSUED: 02/27/04...
  • Page 175 Standby Flight instruments installation, Piper drawings 38453-007-continued 3.) Standby attitude I ndicator w ith battety pack option, Mid-Continent Part 3.67 58.64 215.20 MD4300-41 I, Piper code number 602-319 4.) Standby flight instruments i nstallation hardware Piperdrawings 38453-007 0.88 64.40 56.39...
  • Page 176 1.20 51.069 61.28 Gartn Gl-106A System installation, Piperdrawing 101901-101. .%.idyne Entegrasystem (only), (Marketing option 225) a.) Darwin Gttt!6A Indicator, Piper PS 50040-40-2, Piper code cumbcc 602.-,--, 23° b.) Cables/harnesses and hardware,POser drewing 0l%0l-iOlnitd 101000-104 tL54 50.01 3l.iS (JonuinGO-I06A ‘4ysteis: installation 59.21...
  • Page 177 (It) A vidyne Etttcgra Avionics (Optional Equipment) S-TEC ADF RCR 650D installation, Avidyne Etttegra S ystem (only), P iper drawing 101901-112 (Marketingoption 525) a.) S-TEC ADF Kit (RCR 6500), Piper PS50040-3 1-32, Piper code number 652-167 I.) S-TEC ReceiverRCR 6500, Partnumberô9OIO8-4 2.484 58.038...
  • Page 178 ç74 6 denial I.) Evapt Moe Ontokampa i-le-itcraft, Inc. part number HR. ;,/120411 l’;par tot ti drawing 99640- 002, Piper rode itamber 552-200 3 Lull eat 42 2.) Blower assembly.Pipertlrsteing 09642-007 747? 3.) Receiver-Hydrator. Pnrker Aerospace PartuuntberPAll 249099-It’. Piper I 4.
  • Page 179 Piper i’IIENEW PIPER AIRCRAFT, PA-28R-20I, ARROW LIST EQUIPMENT SIN 2644116 and UP Mark if Arm (In.) Moment Item Weight (Pounds) Aft Datum Item Option (Lb-In.) Installed ENI) FACTORY INSTALIEI) OPTIONS 65.5 124.3695 TOTAl. OPTIONAl. EQUIPMENT END OF ORIGINAl, INSTALLATION EQUIPMENT 2.40...
  • Page 180 7-24 Heating, Ventilating and Defrosting System 7-25 7.29 7.31 Stall Warning 7-27 Finish 7-27 7.33 Air Conditioning 7-27 7.35 Piper External Power 7.37 7-29 Locator Transmitter 7-29 7.39 Emergency 12, 1995 REPORT: VB-16t2 ISSUED: JULY HB-PQY, Page: 7-0-(1) Issued: JULY 12, 1995...
  • Page 181 SECTION ARROW DESCRIOPERATJON PA-28R-2O1, THIS PAGE INTENTIONALLY LEVI’ BLANK REPORT: VB-1612 ISSUED: SULY 12,1995 HB-PQY, Page: 7-0-(2) Issued: JULY 12, 1995 7-ii...
  • Page 182 SECTION ARROW PA-28R.201, DESCRIOPERATION SECTION DESCRIPTION OPERATION OF THE AIRPLANE ITS SYTEMS AIRPLANE The PA-28R-201, Arrow is a single engine, retractable landing gear, all metal airplane. It has seating for up to four occupants, a 200 pound luggage compartment, and a 200 HP engine. AIRFRAME the exception With...
  • Page 183 Since Lycoming from time to time revises the recommended overhaul period, the owner should check the latest Lycoming Service InstructionNo. 1009 at his Piper dealer for the latest recommended overhaul period and for any additional information.
  • Page 184 SECTION ARROW PA-28R-201, DESCRJOPERATION INDUCTION SYSTEM induction system incorporates a Bendix 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 makes the fuel flow proportional...
  • Page 185 SECTION ARROW DESCR1OPERATION PA-28R-201, ENGINE CONTROLS Engine controls consist of a throttle control, a propeller control and a mixture control lever.These controls are located on the control quadrant on panel (Figure 7-1) where they are the lower center of the instrument accessibleto both the pilot and the copilot.
  • Page 186 SECTION PA-28R-201, ARROW DESCRIOPERATION ENGINE CONTROLS (continued) CONSOLE CONTROL QUADRANT Figure 7-1 REPORT: VB-1612 JULY 12,1995 ISSUED: ‘7-c HB-PQY, Page: 7-5-(0) Issued: JULY 12, 1995...
  • Page 187 SECTION ARROW DESCRIOPERATION PA-28R-201, TEMP • ‘oo LANDING GEAR SELECTOR Figure 7-3 7.11 LANDING GEAR Arrow is equipped with a retractable tricycle landing gear, which is hydraulically actuated by an electricallypowered reversible pump. is controlled by a selectorswitch on the Instrument panel to the leftof pump the control quadrant (Figure 7-3).
  • Page 188 SECTION PA-28R.201, ARROW DESCRIOPERATION 7.11 LANDING GEAR (continued) The main landing gear uses 6.00 x 6 wheels. The main gear incorporate brake drums and Cleveland single disc hydraulic brake assemblies. The nose wheel carriesa 5.00 x 5 four ply tireand the main gear use 6.00 x 6 six ply tires.
  • Page 189 Ci1UIN PA-28R-201, ARROW DESCRIOPERATION 7.11 LANDING GEAR (continued) LANDING GEAR ELECTRICAL SCHEMATIC Figure 7-5 REPORT: VB-1612 ISSUED: JULY 12, 1995 HB-PQY, Page: 7-8-(0) Issued: JULY 12, 1995...
  • Page 190 SECTION ARROW DESCRIOPERATION PA-28R.201, 7.il LANDING GEAR (continuea) SHUItt.EVALVE LOW PRESSURE CONTROL IMOUNTING BASE EMERGENCY FREE FAU. MAIN GEAR GEAR VALVE HYDRAUIJCCYUNDER SCHEMATIC GEAR HYDRAULIC LANDING Figure 7-7 VE-1612 REPORT: ISSUED: JULY 12,1995 HB-PQY, Page: 7-9-(0) Issued: JULY 12, 1995...
  • Page 191 SECTION PA-28k-201, ARROW DESCR/OPERATION EMERGENCYGEAR LEVER EXTENSION PITCHTRIM CONTROL FLAP HANDLE • FLIGHT CONTROL CONSOLE Figure 7-9 CONTROLS 7.13 FLIGHT Dual flight controls are provided as standard equipment. A cable system provides actuation of the controlsurfaces when the flight controls are moved in their respective directions.
  • Page 192 SECTION PA-28R-201, ARROW DESCRJOPERATION 7.13 FLIGHT CONTROLS (continued) Manually controlled flaps are provided. They are extended by a control cable and are spring-loaded to the retracted (up) position. The control is located between the two front seats on the control console (Figure 7-9).
  • Page 193 SECTION ARROW DESCRIOPERATION PA-28R-201, SYSTEM 7.15 FUEL (continued) 4OflLE )REGUlATOR SUPI’IV LJNE FIPWAa QUANTITY GAUGES FUEL SYSTEM SCHEMATIC Figure 7-11 REPORT: VB.1612 ISSUED: JULY 12, 1995 7-12 HB-PQY, Page: 7-12-(0) Issued: JULY 12, 1995 7-12...
  • Page 194 SECTION PA-28R-201, ARROW DESCRIOPERAT[cj 7.15 FUEL SYSTEM (continued) FUEL SELECTOR Figure 7-13 CAUTION When draining fuel, care should be taken to ensure that no firehazard exists before starting the engine. A fuel tank selector allows the pilot to control the flow of fuel to the engine, and is located on the leftside wall below the instrument panel.
  • Page 195 SECTION PA-28R-201, ARROW DESCRIOPERATION 7.17 ELECTRICAL SYSTEM All switches are grouped in a switch panel above the power quadrant. The circuitbreaker panel is located on the lower right side of the instrument panel. Each breaker is clearly marked to show which circuit it protects. Also, circuit provisions are made to handle the addition of communications navigationalequipment.
  • Page 196 SECTION PA-28R-201, ARROW DESCRIOPERATJON 7.17 ELECTRICAL SYSTEM (continued) ALTERNATOR SCHEMATIC STARTER Figure 7-15 12, 1995 ISSUED: JULY REPORT:VB-1612 7-15 HB-PQY, Page: 7-15-(0) Issued: JULY 12, 1995 7-15...
  • Page 197 SECTION DESCRIOPERATION PA-28R-201. ARROW 7.17 ELECTRICAL SYSTEM (continued) ®®®®c®®®O®®®® ® ®® ®®®®®®®QO®®® CIRCUIT BREAKER PANEL Figure 7-17 WAR1VING Strobe lights should not be operating when overcast and clouds flying through since reflected light produce spacial disorientation. Do not operate strobe lights in close proximity to ground, during takeoff and landing.
  • Page 198 SECTION PA-28R-201, ARROW DESCRIOPERATION 7.17 ELECTRICAL SYSTEM (continued) Secondary power is provided by a 12-volt, 35-ampere-hour battery. The ammeter as installed does not show battery discharge; rather it shows the electrical load placed on the system. With all the electrical off, and the battery master (BATT equipment and alternator...
  • Page 199 SECTION PA-28R-201, ARROW DESCRIOPERATION 7.19 VACUUM SYSTEM (continued) regulator is provided in the system to protect the gyros. A vacuum valve isset so the normal vacuum reads 4.8 to 5.1 inches of mercury, a setting to operate allthe gyros at theirrated rpm. which provides sufficient vacuum the gyros and with a low setting the gyros will be Higher settings will damage...
  • Page 200 SECTION ARROW DESCRIOPERATION PA-28R-201, 7.21 PITOT-STATIC SYSTEM (continued) SYSTEM PITOT-STATIC Figure 7-19 REPORT: VB-1612 12, 1995 JULY ISSUED: 7.19 HB-PQY, Page: 7-19-(0) Issued: JULY 12, 1995 7-19...
  • Page 201 SECTION DESCR!OPERATION PA-28R-201, ARROW 7.23 INSThUMENT PANEL INSTRUMENT PANEL Figure 7-21 REPORT: VB-1612 ISSUED: JVIY 12,1995 7-20 HB-PQY, Page: 7-20-(0) Issued: JULY 12, 1995 7-20...
  • Page 202 SECTION A1NZOW PA2SI-7O1! <0 oz<0 E< CD0Z 0t09 _øO0 Lz:.)<Lrz o<ocr22 <<Ci < o’- cor-.a: PANEL INSTRUMENT Figure 7-21 VB-1612 REPORT: 12, 1995 JULY ISSUED: 7-21 2004 OCTOBER REVISED: HB-PQY, Page: 7-21-(0) Revision: 11, OCTOBER 7, 2004 7-21...
  • Page 203 SECTION ARROW DESCRIOPERATION PA-28R-201, 7.23 INSTRUMENT PANEL (continued) the customary to accommodate The instrument panel is designed advanced flight instruments and the normally required power plant instruments. The altitudeand directional gyros, located in the center of the vacuum gauge, is lefthand instrument panel, are vacuum operated.
  • Page 204 SECTION PA-28R-201. ARROW DESCRIOPERATION CABIN DOOR LATCH Figure 7-23 7.25 CABIN FEATURES All seat backs have three positions:normal, intennediateand recline. The adjustment lever islocated at the base of the seat back on the outboard side of the seat.The front seats adjust fore and aft for ease of entry and occupant comfort.
  • Page 205 SECTION ARROW DESCRIOPERATION PA-28R-201, 7,25 CABIN FEATURES (continued) the strap will normal movement and holds the occupant in place. Under extend and retractas required. Shoulder harnesses should be routinely worn situation during takeoff, landing and whenever an in-flight emergency occurs. two sun visors, ash Additional features include pilot storm window, trays for each occupant, map pockets located on the side panels below the...
  • Page 206 SECTION PA-28R-201, ARROW DESCRIOPERATION 7.29 BEATING, DEFROSTING VENTILATING, SYSTEM The heating system is designed to provide maximum comfort for the occupants during winter and cool weather flights. T he system includes a heat shroud, heat ducts, defroster outlets, heat and defroster controls. CAUTION When cabin heat is operated, heat duct surface...
  • Page 207 SECTION ARROW PA-28R-201, DESCRIOPERATION SYSTEM DEFROSTING 7.29 HEATING, VENTILATING, (continued) • VENTILATING DEFROSTING SYSTEM HEATING, Figure 7-25 REPORT: VB-1612 ISSUED: JULY 12, 1995 7-26 HB-PQY, Page: 7-26-(0) Issued: JULY 12, 1995 7-26...
  • Page 208 All exterior surfaces are primed with etching primer and finished with acrylic lacquer. To keep the finish attractive looking, economy size spray cans of touchup paint are availablefrom Piper Dealers. 7,35 AIR CONDITIONING* The air conditioning system is a recirculating air system. The major...
  • Page 209 SECTION PA-28R-201, ARROW DESCRIOPERATION 7.35 AIR CONDITION]NG* (continued) The switches and temperature control arc located on the lower right side of the instrument panel in the climate control center panel. The temperature control regulates the temperature of the cabin. Turning the control clockwise increases cooling;...
  • Page 210 DESCRJOPERATION PA-28R-201, 7.37 PIPER EXTERNAL POWER* An optional starting installationknown as Piper External Power (PEP) is accessible through a receptacle located on the right side of the fuselage aft of the baggage door. An external battery can be connected compartment the socket, thus allowing the operator to crank the engine without having to gain access to the airplane’sbattery.
  • Page 211 SECTION DESCRJOPERATION ARROW PA-28R-201, 7.39 EMERGENCY LOCATOR TRANSMITTER* (continued) NARCO 10 OPERATION (continued) as a portable unit in an emergency, remove the cover and To use the ELT base. The antenna cable is disconnected unlatch the unit from its mounting by a left quarter-turn of the knurled nut and a pull.
  • Page 212 SECTION ARROW DESCRJOPERATION PA-28R-201, 7.39 EMERGENCY LOCATOR TRANSMITTER* (continued) NARCO ELT 910 OPERATION On the ELT unit itself is a three position switch placarded ON, ARM. position sets the ELT The ARM so thatitwill transmit after impact and will continue to transmit until its battery is drained. The ARM position is selectedwhen the ELT is installedin the airplane and itshould remain in that...
  • Page 213 SECTION DESCRJOPERATION ARROW PA-28R-201, 7.39 EMERGENCY LOCATOR TRANSMITTER* (continued) ARTEX OPERATION On the ELT unit itself is a two position switch placarded ON and OFF. The OFF position isselected when the transmitter is installed at the factory and the switch should remain in that position whenever the unit is installedin the airplane.
  • Page 214 SECTION ARROW PA-28R-201, HAND/SERV!MAINT TABLE CONTENTS SECTION AIRPLANE MAINTENANCE HANDLING, SERVICING, Paragraph Page General Airplane Inspection Periods Preventive Maintenance Airplane Alterations Ground Handling 8.11 Engine Air Filter 8.13 Brake Service Landing Gear Service 8.15 8-10 8.17 Propeller Service 8-10 8.19 Oil Requirements 8-10 8.21...
  • Page 215 PA-28R-201, ARROW UAND/SERVIMAINT THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 8-il HB-PQY, Page: 8-0-(2) Issued: JULY 12, 1995 8-ii...
  • Page 216 WARNING in writing by PIPER prior to Modifications must be approved and all other installations, whatsoever, of any installation. Any kind willvoid this warranty in it’s entirety. REPORT: VB-1612...
  • Page 217 PIPER parts or PIPER only genuine parts approved obtained from PIPER sources, in connection with the approved maintenance and repair of PIPER airplanes. Genuine PIPER under parts are produced inspected to insure airworthiness and suitability for rigorous procedures use in PIPER airplane applications.
  • Page 218 Piper Every Service Center or Piper’s Customer Service Department to obtain the latest information pertaining to their airplane, and to avail themselves of Piper’s support systems. Piper takes a continuing interestin having owners get the most efficient their airplane and it in the best mechanical condition.
  • Page 219 Manual complied with by a properly trained, knowledgeable, and qualified mechanic at a Piper Authorized Service Center or a reputable repairshop. Piper cannot accept responsibility for the continued airworthiness of any aircraft not maintained to these standards, andlor not brought into compliance...
  • Page 220 SECTION PA-28R-201, ARROW HAND/SERV/MAINT 8.5 PREVENTIVE MAINTENANCE The holder of a PilotCertificateissued under FAR Part 61 may perform certain preventive maintenance described in FAR Part 43. This maintenance be performed only on an aircraft which the pilot owns or operates and which isnot used to carry persons or property for hire, except as provided in applicable FAR’s.
  • Page 221 SECTION HANDISERVIMAINT ARROW PA-28R-201, ALTERATIONS 8.7 AIRPLANE (continued) (b) Tobecarriedintheaircraftatalltimes: (1) Pilot’s Operating Handbook. (2) Weight and Balance data plus a copy of the latest Repair if applicable. aridAlterationForm FAA-337, (3) Aircraft equipment list. Although the aircraft arid engine logbooks are not required to be in the aircraft, they should be made available upon request.
  • Page 222 SECTION ARROW HAND/SERV/MAINT PA-28R-201, 8.9 GROUND RANDLING (continued) (b) Taxiing Before attempting to taxi the airplane,ground personnel should be instructed and approved by a qualified person authorized by the owner. Engine starting and shutdown procedures as well as taxi should be covered. When it is ascertained that the techniques...
  • Page 223 SECTION ARROW HA1b4DISERV/MA1NT PA-28R-201, 8.9 GROUND HANDLING (continued) (3) Aileron and stabilator controls should be secured with the front seat belt and chocks used to properly block the wheels. (d) Mooring The airplane should be moored for immovability, security, and protection.
  • Page 224 SECTIONS ARROW HANDISERVIMAINT PA-28R-201, 8.11 ENGINE FILTER Engine Air Filter (a) Removing the upper cowl. (1) Remove the wing nuts securing the filler box cover. Remove (2) Remove Remove the filter. (b) Cleaning Engine Air Filter The induction air filter must be cleaned at leastonce every 50 hours, and more often, even daily, when operating in dusty conditions.
  • Page 225 SECTION ARROW PA-28R-201, ELAND/SERVIMAINT SERVICE 8.13 BRAKE (continued) BRAKE SYSTEM Figure 8-1 REPORT: VB-1612 ISSUED: .JULY 12,1995 HB-PQY, Page: 8-8-(0) Issued: JULY 12, 1995...
  • Page 226 SECTION ARROW PA-28R-201, HAND/SERY/MAINT 8.15 LAND]NG GEAR SERVICE The main landing gear uses 6.00 x 6 wheels with 6.00 x 6, six-ply rating tiresand tubes.The nose wheel uses a 5.00 x 5 wheel with a 5.00 x 5 four-ply tireand tube. (Refer to Paragraph 8.23.) rating, type Wheels are removed...
  • Page 227 HAND/SERV/MAINT ARROW PA-28R-201, 8.17 PROPELLER SERVICE The spinner and backing plate should be cleaned and inspected for cracks frequently. Before each flight the propeller should be inspected for nicks,scratches, and corrosion. If found, they should be repaired as soon as possible by a rated mechanic, since a nick or scratch causes an area of increased stresswhich can lead to seriouscracks or the loss of a propellertip.
  • Page 228 SECTION ARROW PA-28R-201, RAND/SERVIMAINT 8.21 FUEL SYSTEM (continued) (a) Servicing Fuel System (continued) of the firewall. It is accessible by removing the lower cowling. After cleaning, a small amount of grease applied to the gasket will facilitate facilitate reassembly. (b) Fuel Requirements (AVOAS ONLY) Aviation grade fuel with a minimum octane of 100/130...
  • Page 229 SECTION ARROW HAND/SERV/MAINT PA.28R-201, 8.21 FUEL SYSTEM (continued) (b) Fuel Requirements (AVGAS ONLY) (continued) The operation of the aircraft is approved with an anti-icing additive additive in the fuel.When anti-icing additive is used, itmust meet the specification MIL-I-27686, must be uniformly blended with the fuel while refueling, must not exceed 0.15% of the refueled by volume...
  • Page 230 SECTIONS ARROW HAND/SERVIMAINr PA-28R-201, FUEL SYSTEM (continued) Filling Fuel Tanks (continued) Observe all safety precautions required when handling gasoline. gasoline. Fill the fuel tanks through the filler located on the forward of 38.5 U.S. gaflons. slope of the wing. Each wing holds a maximum using lessthan the standard 77 gallon capacity, fuel should be When distributed equally between each side.
  • Page 231 SECTION ARROW PA-28R-201, HANDISERVIMAINT 8.21 FUEL SYSTEM (continued) (d) Draining Fuel Strainer, Sumps and Lines (continued) The fuelstrainer, l ocated on the lower left side of the firewall, is drained before the first provided with a quick drain which should be contamination.
  • Page 232 SECTION ARROW PA-28R-201, HAND/SERVIMAINT BATTERY SERVICE The 12-volt, 35-ampere-hour battery is located just behind the aft close out panel. Access is gained through the baggage compartment. The battery container has a plastic drain tube which is normally closed off with a cap. The cap should be opened periodically to remove battery acid which may have collectedin the tube.
  • Page 233 slCT1Uf’ PA-28R-201, ARROW IIAND/SERVIMAINT 8.27 CLEANING (continued) (continued) (a) Cleaning Engine Comparunent the engine from five to ten (3) Allow the solvent to remain on clean with additional rinse the engine minutes. Then solvent and allow itto dry. CAUTION not operate the engine until excess solvent has evaporated or otherwise been removed.
  • Page 234 SECTION ARROW IIAND!SERVIMAINT PA-28R-201, CLEANING (continued) (c) Cleaning ExteriorSurfaces (continued) (2) Apply cleaning solution with a soft cloth, a sponge or a softbristle brush. exhaust stains, allow the solution to remain (3) To remove on the surface longer. stubborn oil and grease, use a cloth dampened (4) To remove with napbtha.
  • Page 235 SECTION ARROW PA-28R-201, HAND/SERV/MAINT 8.27 CLEANING (continued) (e) Cleaning Headliner, Side Panels and Seats with a stiffbristle (1) Clean headliner, side panels, and seats brush, and vacuum where necessary. be cleaned with a (2) Soiled upholstery, except leather, may good upholstery cleaner suitable for the material. Carefully follow the manufacturer’s instructions.
  • Page 236: Garmin Gns

    SECTION ARROW SUPPLEMENTS PA-28R-201, 1BLE CONTENTS SECTION SUPPLEMENTS Page Paragraph/Supplement General Auxiliary Vacuum (6 pages) System King 100 Series Flight Control System (Deleted) (I page) 9-11 King 150 Series Flight Control System (Deleted) (1 page) 9-13 89B GPS (12 pages) Navigation System Bendix/King 9-25...
  • Page 237: Table Of Contents

    SECTION ARROW SUPPLEMENTS PA-28R-201, TABLE CONTENTS SECTION SUPPLEMENTS (continued) Page Paragraph/Supplement KR-87 Digital ADF with Bendix/King 9-159 KI-227 Indicator (10 pages) 9-169 KN-63 (4 pages) Bendix/King Garmin 430W Conmrnnication Receiver/GPS Receiver 9-173 TransceiverIVORllLS (12 pages) Primary Flight and Multifunction Garmin G500 9-185 (1 page)
  • Page 238 SECTION ARROW SUPPLEMENTS PA-28R-201, SECTION SUPPLEMENTS GENERAL This section provides information in the form of Supplements which are necessary for efficient operation of the airplane when equipped with one or not provided with the more of the various optional systems and equipment standard airplane.
  • Page 239 SECHON ARROW PA-28R-2O1, SUPPLEMENTS LEFT BLANK TilES PAGE INTENTIONALLY REPORT: VB-1612 ISSUED: 12, 1995 JULY HB-PQY, Page: 9-2-(0) Issued: JULY 12, 1995...
  • Page 240 For information not contained in this supplement, consult the basic Pilot’s Operating Handbook and FAA Airplane Flight Manual. Approved APPROVED PETER E. PECK D.O.A. NO. SO-i INC. PIPER AIRCRAFT, FLORIDA VERO BEACH, DATE OF APPROVAL SEPTEMBER 19. 1999 REPORT:...
  • Page 241 SUPPLEMENT ARROW PA-28R-201, THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1733 ISSUED: SEPTEMBER 19, 1999 HB-PQY, Page: 9-2-(2) Issued: SEPTEMBER 19, 1999 UK i...
  • Page 242 UNITED KINGDOM ARROW SUPPLEMENT PA-28R-201, PILOT’S OPERATING HANDBOOK REVISIONS Current Revisions to the PA-28R-201 Arrow, UK VB-1733, Supplement, issued September 19, 1999. Revision Number Revised Description of Revisions Code Pages Rev. I Revised page. Revised page. (PR010417) Revised Limitations. REPORT: VB-1733 19, 1999 ISSUED:...
  • Page 243 ARROW SUPPLEMENT PA-28R-201, Revision Description of Revisions REPORT VB-1733 ISSUED: SEPTEMBER 19, 1999 ‘Ii REVISED: APRIL 17, 2001 HB-PQY, Page: 9-2-(4) Issued: APRIL 17, 2001 UK iii...
  • Page 244 UNITED KINGDOM ARROW PA-28R-201, SUPPLEMENT INTRODUCTION data in this supplement must in the included Pilot’s Operating Handbook when (P.O.H.) operating United register. In cases of conflicting Kingdom information, the data in this supplement information supercedes published inVB-1612. LIMITATIONS Category: Aircraft of this type are eligible for certification in the this aeroplane...
  • Page 245 ARROW SUPPLEMENT PA-28R-201, LIMITATIONS (Cont’d.) Performance (Cont’d.) from short dry grass fields with For take off operations take off distance 20%. take off firm subsoil, increase from short fields, with firm subsoil, operations grass 25%. factors apply to take increase take off distance These off distance...
  • Page 246 UNITED KINGDOM ARROW PA-28R-201, SUPPLEMENT LIMITATIONS (Cont’d.) Number of Occupants: number of persons carried must not exceed four, nor exceed the number of seats installed. Children under the age of 2, carried in the arms of passengers, are excluded from this count.
  • Page 247 SUPPLEMENT ARROW PA-28R-201, LIMITATIONS (Cont’d.) Autopilots: When a Bendix/King series autopilot, or an S-TEC 55/55X is installed, it shall remain System autopilot at heights below 1000 feet above the terrain. When engaged to an ILS glide slope, it shall not remain coupled engaged heights below...
  • Page 248 UNITED KINGDOM ARROW SUPPLEMENT PA-28R-201, PROCEDURES (Cont’d.) Starter Engaged (Cont’d) Warning Light: light remain illuminated after the Should the warning turn the BATTERY MASTER starter switch is disengaged, SWITCH have the fault corrected before attempting to start the engine. Monitor Light Voltage Pre Flight Check:...
  • Page 249 SUPPLEMENT ARROW PA-28R-201, PROCEDURES (Cont’d.) Notes: should be made as soon as possible. Under landing the alternator failure conditions the battery endurance should be 30 minutes. communication transmission should be restricted to maximum of 3 minutes total flight. during Other electrical services be used...
  • Page 250 Pilot’s Operating Handbook and FAA Airplane Flight Manual when the Piper Auxiliary Approved Vacuum System is installed in accordance with Piper Drawing No. 89311-2. contained herein supplements or supersedes the basic The information and FAA Pilot’s Operating...
  • Page 251 GENERAL This supplement supplies information necessary for the operation of the System is installed. T he airplane when the optional Piper Auxiliary Vacuum information contained within this supplement is to be used in conjunction with the complete handbook. SECTION 2- LIMiTATIONS...
  • Page 252 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 4-NORMAL PROCEDURES (a) Preflight Check. (1) Turn battery master (BATT switch ON and verify MASTR) thatthe VAC OFF light isilluminated. NOTE to the electrical power requirement of the auxiliary vacuum itis suggested that the pump engine be operating while making the following checks.
  • Page 253 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION PERFORMANCE No change. & BALANCE SECTION 6- WEIGHT is included in the licensed weight Factory installed optional equipment and balance data in Section 6 of the Basic Pilot’s Operating Handbook. SECTION 7- DESCRIPTION OPERATION system provides an independent The auxiliary dry air pump back-up source of pneumatic power to operate the gyro flight instruments in the event...
  • Page 254 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 7-DESCRIPTION OPERATION (coat) The annunciator lights do not incorporate a press-to-test feature.If the lights do not illuminate as expected, check for burned out lamps,,replace with MS 25237-330 bulbs and retestthe system. motor electrical c ircuitis protected by a 20 amp AUX The pump breaker installedin the circuit breaker panel.
  • Page 255 SECTION ARROW SUPPLEMENT PA-28R-201, ‘3 VACUUM SYSTEM SCHEMATIC REPORT: VB-1612 ISSUED: 12, 1995 JULY 6of6 HB-PQY, Page: 9-8-(0) Issued: JULY 12, 1995...
  • Page 256 SECTION ARROW PA-28R-201, SUPPLEMENT PILOT’S OPERATING HANDBOOK APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO.2 KING 100 SERIES FLIGHT CONTROL SYSTEM The FAA to the Bendix/King Approved Operational Supplement Series Flight Control System as installed per STC SA1563CE-D is supplied by the autopilot manufacturer. will be responsible to supply BendixfKing and revise the operational supplement.
  • Page 257 SECTION ARROW SUPPLEMENT PA-28R-201, THIS BLANK PAGE INTENTIONALLY LEFT ISSUED: JULY 12,1995 REPORT: VB-1612 9-10 HB-PQY, Page: 9-10-(0) Issued: JULY 12, 1995 9-10...
  • Page 258 SECTION ARROW PA-28R201, SUPPLEMENT PILOT’S OPERATING HANDBOOK APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO.3 KING 150 SERIES FLIGHT CONTROL SYSTEM The FAA to the BendixlKing Approved Operational Supplement Series Flight Control System as installed per STC SA1563CE-D is supplied by the autopilot manufacturer. will be responsible to supply Bendix/King and revise the operational supplement.
  • Page 259 SECTION ARROW SUPPLEMENT PA-ZSR-201, THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: JULY 12, 1995 REPOR1’ VB-1612 9-12 HB-PQY, Page: 9-12-(0) Issued: JULY 12, 1995 9-12...
  • Page 260 For limitations, procedures and performance information contained in this supplement, consult the Pilots Operating Handbook Airplane Flight Manual. Approved APPRO: PETER E. PECK D.O.A. NO. SO-i PIPER AIRCRAFT,]NC. VERO FLORIDA BEACH, DAlE OF APPROVAL: December 11. 1995 12, 1995 REPORT:...
  • Page 261 SECTION ARROW SUPPLEMENT PA-28R-201, 1 GENERAL SECTION The KLN unit contains the GPS sensor, the panel mounted display, and allcontrols required to operate the navigation computer, a Cl unit. Italso houses the data base card which plugs directly into the front of the unit.
  • Page 262 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 2- LIMiTATIONS The KLN 89B GPS Pilot’s Guide, P/N 006-08786-0000, dated May, 1995 (or later applicablerevision) must be immediately availableto the flight crew whenever navigation is predicated on the use of the system. The Operational Revision Status (ORS) of the Pilot’s Guide must...
  • Page 263 SECTION ARROW PA-28R-201, SUPPLEMENT ABNORMAL 3-EMERGENCY PROCEDURES SECTION PROCEDURES infonnation is not available or invalid, utilize If the K.LN 89B GPS remaining operationalnavigation equipment as required. message is displayed while conducting If a “RAIM AVAILABLE’ an instrument approach, terminate the approach. Execute a missed approach if required.
  • Page 264 SECTION SUPPLEMENT PA-28R-201, ARROW NORMAL PROCEDURES Will flash to alert the pilot of a annunciator (MSG) Message situation that requires attention. Press the MSG button on the KLN 89B GPS to view the message. (Appendix B of the KLN 89B Pilot’s Guide contains a list of allof the message page messages and their meanings).
  • Page 265 SECTION ARROW SUPPLEMENT PA-28R-201, NORMAL PROCEDURES CII’S approach (GPS switch/annunciator ARM/ACTV) Used to (a) manuaily select or deselect approach deselect approach and (b) annunciate the stage of ACTV) approach operation either armed (ARM) or activated (ACTV). Sequential button pushes if in ACTV would first result in approach ARM...
  • Page 266: (1 Page)

    SECTION PA-28R-2O1, A1ROW SUPPLEMENT NORMAL PROCEDURES ALERT AURAL ‘lONES ALTITUDE • 1000 feet prior to reaching the selected altitude threeshorttones. • reaching the selected altitude two shorttones. Upon • Deviating above or below the selectedaltitude by more than the warn altitude four shorttones. PREDICYION RAJM APPROACH...
  • Page 267 JUiiULN ARROW SUPPLEMENT PA-28R-201, NORMAL PROCEDURES At30nmfromtheairport Verify automatic annunciation of APR ARM. Note automatic dbar scaling change from ± 5.0 urn to ±1.0 nsa over the next 30 seconds. Update the KLN 89B altimeter baro setting as required. 89B will transition from en route to Internally the KLN terminal integrity monitoring.
  • Page 268: (4 Pages)

    SECTION PA-28R-2O1, ARROW SUPPLEMENT NORMAL PROCEDURES Approaching the FAF inbound (within 2 urn.): ACTV. Verify APR Note automatic dbar scalingchange from ±1.0 am to ± 03 urn over the 2 am inbound to the FAR Internally the ICLN 89B willtransition f rom terminal to approach integrity monitoring.
  • Page 269 SECTION ARROW SUPPLEMENT PA-28R-ZO1, NORMAL PROCEDURES Waypoint suffixes in the flight plan: I4AF f- FAF rn-MAP h missed approach holding fix. arc lAP (arc intercept waypoint) will be a) on your present position radial off the arc VOR when you load the lAP into the flight plan, of the arc if or b) the beginning currently on a zadial beyond the arc...
  • Page 270 PA-28R.201, ARROW SUPPLEMENT NORMAL PROCEDURES • to APR ACTV automatic provide& a. You are in APR (normally automatic). b. Ycaiare in LEG mode! c. The FAF is the active wavpoint! d. Within 2nm.oftheFAE e.Outside of the FAR f. InboundtotheFAE g. RAIM isavailable.
  • Page 271 SICIION ARROW SUPPLEMENT PA-28R-201, \•_j TUJS PAGE LEFf BLANK INTENTIONALLY REPORT: VB-1612 ISSUED: 12, 1995 JULY 9-24 12 of 12 REVISED: DECEMBER 11, 1995 HB-PQY, Page: 9-24-(0) Revision: 1, DECEMBER 11, 1995 9-24...
  • Page 272 FAA Airplane Flight Manual when the KX 155A Comm/Nay Approved is installed per the Piper Drawings. information contained System herein supplements or supersedes the Pilots Operating Handbook and FAA Airplane Flight Manual only in those areas listed herein. For...
  • Page 273 1 GENERAL SECTION supplies information necessary for the operation of the This supplement System is installed in airplane when the BendixiKing 155A Comm/Nay accordance with FAA approved Piper data. SECTION 2 LIMITATIONS No change. .3- EMERGENCY PROCEDURES SECTION No change. SECTION...
  • Page 274 SECTION PA-28R.201, ARROW SUPPLEMENT SECTION 7 DESCRIPTION & OPERATION GENERAL are located on the Al) controls required to operate the KX 155A/165A unitfront panel. (See Figure 3-1.) AmiCa.w — FIGURE FUNCTIONS 155A CONTROL COMM TRANSCEIVER knob out knob clockwise from the OFF position. Pull the VOL Rotate the VOL knob back in to actuate the and adjust for desired listening level.
  • Page 275 SECTION ARROW SUPPLEMENTS PA-28R-201, COMM TRANSCEIVER (CONTD) portion of the standby display. At one The outer knob will change the MHz change will wrap around to band-edge (118 or 136 MHz) the following 1 MHz the other band-edge. The inner knob will change the kHz portion of the standby display.
  • Page 276 SECTION ARROW SUPPLEMENT PA-28R401, J.55A also has provision to program 32 channels. Pressing the CHAN The KX button for 2 or more seconds will cause the unit to enter the channel program is displayed next to the entering the channel program mode,”PG” mode.
  • Page 277 1!CL ION 9 ARROW SUPPLEMENTS PA-28R-201, RECEIVER (CONTD) receiver’s lower and upper The inner knob operates in 50 kHz steps. The NAy and 117.95 MHz. the upper limit frequency limitsare 108.00 MHz Exceeding of frequency band will automatically return to the lower limitand vice versa. frequency transfer button for 2 seconds or more will cause Depressing the NAV the display to go in to the ACTIVE...
  • Page 278 SECTION ARROW SUPPLEMENTS PA-28R-201, i-itLJL. i-itLJL. IU..JLJ +--—--( FIGURE FORMAT ACTIVE LOCALIZER FREQUENCY/CDI DISPLAY; the received signal istoo weak to ensure accuracy the display will When “flag”. See Figure 3-4. E109. fl3fl E109. FLAG DISPLAY FIGURE 3-4 VOR REPORT: VB-1612 12, 1995 ISSUED: JULY...
  • Page 279 SECTION ARROW PA-28R-201, SUPPLEMENT RECEIVER (CONT’D) display to go from the button will cause the NAV the mode Depressing format. In the BEARING format to the ACTIVE/BEARING ACTIVEICDI frequency window the ACTIVE mode, the increment/decrement knob channels and depressing the frequency transfer button will cause the ACTIVE frequency frequency (in blind storage) to be placed in blind storage and the STANDBY...
  • Page 280 SECTION ARROW PA.28R.201, SUPPLEMENT Another push of the mode button will cause the NAV display to go from the ACTIVE/BEARING format to the ACTIVE/RADIAL format as shown Figure 3-7. In the RADIAL mode, the increment/decrement knob channels the ACTIVE frequency window and depressing the frequency transfer button will cause the ACTIVE frequency to be placed in blind storage and the STANDBY...
  • Page 281 SECTION ARROW SUPPLEMENT PA-28R-201, RECEIVER (CONTD) button will cause the unit to go into the TIMER Another push of the mode the unit is turned on the elapsed timer begins mode. See Figure 3-9. When counting upwards from zero. The timer can be stopped and reset to zero by pushing the NAV frequency transfer button for 2 seconds or more causing the ET on the display to flash.
  • Page 282 SECTION ARROW SUPPLEMENT PA-28R-201, PILOT CONFIGURATION can be accessed by pressing and holding the Nay Mode This mode Button for more than 2 seconds and then pressing the Nay Frequency Transfer Button for an additional2 seconds, while continuing to hold the Nay Mode Button.
  • Page 283 SECTION SUPPLEMENT ARROW PA-28R-201, THIS LEFT BLANK PAGE INTENTIONALLY REPORT: VB-1612 ISSUED: JULY 12, 1995 12 of 12 9-36, REVISED: NOVEMBER 16,1998 HB-PQY, Page: 9-36-(0) Revision: 3, NOVEMBER 16, 1998 9-36...
  • Page 284 SECTION PA.28R-201, ARROW SUPPLEMENT PILOT’S OPERATING HANDBOOK MANUAL APPROVED AIRPLANE FLIGHT SUPPLEMENT NO.6 TRIM SYSTEM MAWUAL ELECTRIC S-TEC TRIM MONITOR WITH 2844010 and up) (Serial numbers Manual for the S-TEC The FAA operational supplement approved Electric Trim System, Installedin accordance with STC SA78O5SW-D, will be responsible to supply S-TEC...
  • Page 285 ARROW SUPPLEMENT PA-28R-201, LEFT BLANK THIS PAGE INTENTIONALLY REPORT: VB.1612 ISSUED: JULY 12,1995 9-38 REVISED: JANUARY 31,2000 HB-PQY, Page: 9-38-(0) Revision: 4, JANUARY 31, 2000 9-38...
  • Page 286 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. APPROVED: (kAA1lkAa 1hlLA.Wç CF]IUSTINA L. MARSH D.O.A. NO. SO-i PiPER INC. AIRCRAFT, VERO FLORIDA BEACH, 14.2000 DATE OF APPROVAL: SEPTEMBER VB-1612 REPORT:...
  • Page 287 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION GENERAL instrument, which The GNS 430 System is a fullyintegrated, panel mounted Transceiver, a VORJILS receiver, and a contains a VHF Communications Global PositioningSystem (GPS) Navigation computer. The system consistsof a GPS antenna, GPS receiver, VHF VORJLOC/GS antenna, VORIILS receiver,...
  • Page 288 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION LIMITATIONS The GARMIN 430 Pilot’s Guide, p/n 190-00140-00, Rev. A, dated October 1998, or later appropriate revision, must be immediately available to the flight crew whenever navigation is predicated on the use of the system. The GNS 430 must utilize the following or later FAA approved software...
  • Page 289 SUPPLEMENT PA-28R-201, ARROW SECTION 2- LIMITATIONS (continued) of ILS, LOC, SDF, MLS or any LOC-BC, LDA, Accomplishment other type of approach not approved for GPS overlay with the GNS 430’s GPS receiverisnot authorized. Use of the GNS 430 VOR/ILS receiver to fly approaches approved for GPS require VOR/ILS navigation data to be present on...
  • Page 290 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 3-EMERGENCY PROCEDURES ABNORMAL PROCEDURES If GARMIN 430 navigation information is not availableor invalid, utilize remaining operationalnavigation equipment as required. If “RAIM POSITION WARNING” message is displayed the system will flag and no longer provide GPS based navigational guidance.
  • Page 291 ARROW PA-28R-201, SUPPLEMENT 4- NORMAL SECTION PROCEDURES WARNING Familiarity with the enroute operation of the 430 does not constitute proficiency in approach operations. Do not attempt approach operations in IMC prior to attainingproficiency 430 approach feature. in the use of the ONS DETAILED OPERATING PROCEDURES...
  • Page 292 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 4-NORMAL PROCEDURES (continued) AUTOMATIC LOCALIZER COURSE CAPTURE 430 automatic localizercourse capture feature is By default, the ONS enabled. This feature provides a method for system navigation data present on the externalindicators to be switched automatically from OPS guidance to localizer I glide slope guidance at the point of course intercept on a derived course deviation equals localizer derived...
  • Page 293 ARROW SUPPLEMENT PA-28R-201, THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12,1995 8 of 8 REVISED: SEPTEMBER 14,2000 HB-PQY, Page: 9-46-(0) Revision: 5, SEPTEMBER 14, 2000 9-46...
  • Page 294 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. APPROVED: CHRISTINA L. MARSH D.O.A. NO. SO-I INC. PIPER AJRCRAFr, FLORIDA VERO BEACH, September 14. 2000 DATE OF APPROVAL: REPORT: VB-1612 12, 1995...
  • Page 295 1- GENERAL SECTION This supplement supplies information necessary for the operation of the airplane when the Garmin 327 Transponder is installedin accordance with FAA approved Piper data. SECTION 2- LIMITATIONS No change. 3- EMERGENCY SECTION PROCEDURES To transmit an emergency signal: •...
  • Page 296 SECTION ARROW SUPPLEMENTS PA-28R-201, SECTION 4-NORMAL PROCEDURES BEFORE TAKEOFF: • To transmitMode C (Altitude Reporting) code in flight: • Mode Selection Key • Code Selector SELECT assigned code. Keys A (Aircraft I dentification) code in flight: To transmitMode • Mode Selector Key •...
  • Page 297 SUPPLEMENT PA-28R-201. ARROW SECTION 7. DESCRIPTION OPERATION The GTX 327 transponder is powered on by pressing the STBY, or ON keys, or by a remote avionics master switch (if applicable). After power on, a start-up page willbe displayed while the unit performs a selftest. Mode Selection Keys Powers off the GTX...
  • Page 298 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 7-DESCRIPTION AN]) OPERATION (continued) 327 Configuration Mode (continued) To use the GTX 327 Configuration Mode: 1: Press and hold the FtJNC key while powering on the unit using the ON, or ALT key (or using an avionicsmaster switch). STRY, 2.
  • Page 299 ARROW SUPPLEMENT PA-28R-201, 7- DESCRIPTION OPERATION SECTION (continued) Code Selection (continued) Codes: Important (Refer to ICAO standards The VFR code for any altitude in the US 1200 elsewhere) 7000- The VFR code commonly used in Europe (Refer to ICAO standards) Hijack code (Aircraft is subject to unlawful interference) 7500 7600...
  • Page 300 SECTION ARROW SUPPLEMENT PA-28R201, SECTION 7-DESCRIPTION OPERATION (continued) Keys for Other GTX 327 Functions (continued) ALT: Displays the altitudedata supplied to the ___________PRESSURE 327 in feet, hundreds of feet (i.e., f lightlevel), or meters, depending on configuration. Displays the Flight Time, which is controlled FLIGHT TIME;...
  • Page 301 SUPPLEMENT ARROW PA-28R-201, SECTION 7- DESCRIPTION OPERATION (continued) Altitude Trend Indicator When the “PRESSURE ALT” page is displayed, an arrow may be displayed to the right of the altitude, indicating thatthe altitude is increasing or decreasing. on the rate of of two sizes of arrows may be displayed depending sensitivity of these arrows...
  • Page 302 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7-DESCRIPTION AN]) OPERATION (continued) Automatic ALT/STRY Mode Switching 327 is configured for automatic standby switching, the mode will If the GTX a squat switch senses thatthe aircraft has automaticallychange to ALT when automatically when a will change to STBY airborne.
  • Page 303 ARROW SUPPLEMENT PA-28R-201, THIS PAGE INTENTIONALLY LEFf BLANK REPORT: VB-1612 ISSUED: JULY 12,1995 9-56 10 of 10 REVISED: SEPTEMBER 14,2000 HB-PQY, Page: 9-56-(0) Revision: 5, SEPTEMBER 14, 2000 9-56...
  • Page 304 FAA consult the Pilot’s Operating Handbook Airplane Flight Approved Manual. APPROVED; L. MARSH CHRISTINA D.O.A. NO. SO- I INC. PIPER AIRCRAFI’, FLORIDA VERO BEACH, September 14. 2000 OF APPROVAL: DATE VB-1612 REPORT: ISSUED:...
  • Page 305 PA-28R-201, SECTION 1. GENERAL This supplement supplies information necessary for the operation of the airplane when the S-TEC ADF-650 System is installedin accordance with approved Piper data. 2. LIMITATIONS SECTION No change. SECTION 3- EMERGENCY PROCEDIJIES No change. REPORT: VB-1612...
  • Page 306 SECTION PA.28R-201, ARROW SUPPLEMENT SECTION 4- NORMAL PROCEDURES To operate as an Automatic Direction Finder: • OFF/VOL Control • Frequency SelectorKnobs SELECT desired frequency. • ADF SPEAKERJPHONE SelectorSwitch (on audio control panel) SELECT as desired. • OFF/VOL Control SET to desired volume level. •...
  • Page 307 PA-28R.201. ARROW SUPPLEMENT ANI) OPERATION SECTION 7-DESCRIPTION System operates over a frequency range of 200 through The S-TEC ADF-650 1799 kHz in l-kHz increments. Three operating modes are included as part of the ADF-650 System. •ANT • ADF CONTROL ADF-650 Receiver, Controls, and Indicators Figure 1 Mode...
  • Page 308 SECTION PA-28R.201, ARROW SUPPLEMENT SECTION 7-DESCRIPTION OPERATION (continued) (Antenna) Mode The ANT (antenna) mode cannot be used for navigation; thismode enhances audio reception clarity and is normally used for station identification. Mode is used for navigation. This mode Automatic Direction Finder (ADF) mode activates the bearing pointer.
  • Page 309: Issued: July

    PA-28R-201, ARROW SUPPLEMENT THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 6 of 6 REVISED: SEPTEMBER 14,2000 HB-PQY, Page: 9-62-(0) Revision: 5, SEPTEMBER 14, 2000 9-62...
  • Page 310 Pilot’s information Flight Manual. Operating Handbook and FAA Approved Airplane &lFJ-W,)e APPROVED CHRISTINA L. MARSH D.O.A. NO. SO-i PIPER INC. AIRCRAFr, VERO FLORiDA BEACH, September 14.2000 DATE OF APPROVAL VB-1612 REPORT: ISSUED: JULY...
  • Page 311 SUPPLEMENT PA-28R-201, 1- GENERAL SECTION This supplement supplies information necessary for the operation of the 340 audio panel isinstalled in accordance airplane when the Garmin GMA approved Piper data. with FAA SECTION 2- LIMITATiONS No change. 3- EMERGENCY PROCEDURES SECTION No change.
  • Page 312 SECTION PA-28R.201, ARROW SUPPLEMENT SECTION 5- PERFORMANCE No change. SECTION 6- WEIGHT AN]) BALANCE Factory installed optionalequipment isincluded in the licensed weight and balance data in section6 of the Airplane Flight Manual. SECTION 7-DESCRIPTION AN]) OPERATION 1. Marker Beacon Lamps 2.
  • Page 313 SIUTIOiN SUPPLEMENT ARROW PA-28R-201, SECTION 7-DESCRIPTION OPERATION (continued) Pilot Intercom System (ICS) Volume Control ON/OFF, The OMA 340 is powered OFF when the leftsmall knob (5) is rotated fully into the detent.To turn the unit ON, rotate the knob clockwise past the click.The knob then functions as the pilot ICS volume control.
  • Page 314 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7-DESCRIPTION OPERATION (continued) Aircraft Radios and Navigation (16) or MRK Pressing NAV1, NAV2, (2) selects each audio DME, source.A second button press deselectsthe audio. Speaker Output Pressing the SPKR button (12) selects the aircraftradios over the cabin speaker.
  • Page 315 PA-28R-201, ARROW SUPPLEMENT SECTION 7-DESCRIPTION OPERATION (continued) Marker Beacon Receiver 340’s marker beacon receivercontrols are locatedon the left side of The GMA button selectseither high or low sensitivity the front panel (1 4). The SENS as indicated by the HI or LO LED being lit.
  • Page 316 SECTION ARROW PA.28R-201, SUPPLEMENT PILOT’S.OPERATING HANDBOOK APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO.11 S-TEC DME-450 This supplement must be attached to the Pilot’s Operating Handbook Approved Airplane Flight Manual when the S-TEC DME-450 isinstalled per the Equipment List. The information contained herein supplements supersedes the Pilot’s Operating Handbook and FAA Airplane...
  • Page 317 SUPPLEMENT ARROW PA.28R-201, 1- GENERAL SECTION The S-TEC system is a full feature, solid state, remote mounted DME-450 system with full 200 channel capability. For long distance operation, it provides a full100 watts maximum pulse power transmitter output. The IND-450 indicator (see figure 1) provides selectable read-out of distance to/from the station, ground speed, and time to/from the station.
  • Page 318 SECTION ARROW PA-28R-201, SUPPLEMENT SECTION 6. WEIGHT AN]) BALANCE Factory installed optional equipment is included in the licensed weight and balance data in Section 6 of the Pilot’s Operating Handbook and Airplane Flight Manual. SECTION 7- DESCRIPTION OPERATION IND.450 Figure 1 1.
  • Page 319 PA-28R-201, ARROW SUPPLEMENT 7- DESCRIPTION OPERATiON (continued) Turns DME power on or off. 4. DME ON/OFF SWITCH HOLD NAV I SELECT Mode Selector Switch Figure 2 5. DME MODE SELECTOR SWITCH Selects 1, HOLD, (NAV operating mode as follows: SelectsDME operation with NO.
  • Page 320 SECTION ARROW PA-28R-201, SUPPLEMENT PILOT’S OPERATING HANDBOOK APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO.12 S-TEC SYSTEM 55 TWO AXIS AUTOMATIC FLIGHT GUIDANCE SYSTEM The FAA for the S-TEC approved operational supplement System Autopilot, installed in accordance with STC is required for SAO9129AC-D, operation of this system.
  • Page 321 ARROW SUPPLEMENT PA-28R-201, THIS PAGE LEFT BLANK INTENTIONALLY REPORT: VB-1612 ISSUED: JULY 12,1995 9-74 REVISED: SEPTEMBER 14,2000 HB-PQY, Page: 9-74-(0) Revision: 5, SEPTEMBER 14, 2000 9-74...
  • Page 322 SECTION PA-28R-201, ARROW SUPPLEMENT PILOT’S OPERATING HANDBOOK APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO.13 S-TEC SYSTEM 55X TWO AXIS AUTOMATIC FLIGHT GUIDANCE SYSTEM The FAA approved operational supplement for the S-TEC System Autopilot, installedin accordance with STC is required for SAO9129AC-D, operation of this system.
  • Page 323 PA-28R-201, ARROW SUPPLEMENT TillS PAGE LEFT BLANK INTENTIONALLY REPORT: VB-1612 ISSUED: JULY 12, 1995 9.76 REVISED: 2000 DECEMBER21, HB-PQY, Page: 9-76-(0) Revision: 6, DECEMBER 21, 2000 9-76...
  • Page 324 S-TEC CORPORATION MINERAL TEXAS 76O7 WELLS, FAA/DAS APPROVED PILOTS OPERATING HANDBOOK AND/OR AIRPLANE FLIGHT MANUAL SUPPLEMENT PIPER PA-28R-201 MODELS PA-28R-201T WITH S-TEC SYSTEM 55/55X TWO AXIS AUTOMATIC FLIGHT GUIDANCE SYSTEM WITH TRIM MONITOR (14 Volt System) REG. N30645 SER.NO. 2844120...
  • Page 325 CORPORATION MINERAL TEXAS 76067 WELLS, FAA/DAS APPROVED HANDBOOK AND/OR PILOTS OPERATING AIRPLANE MANUAL SUPPLEMENT FLIGHT and PA..28R-201T Piper models PA-28R-201 OF REVISIONS REV. PAGES APPROVED DATE AFFECTED DESCRIPTION Added 1,3, 5, 10, System 11, 12 information. Removed Optional Equipment Section.
  • Page 326 APPROVED PILOT’S OPERATING HANDBOOK AND/OR AIRPLANE FLIGHT MANUAL SUPPLEMENT Piper models PA-28R-20l and PA-28R-201T SECTION OPERATING LIMITATIONS Autopilot operation not authorized above 165 KIAS. Flap extension limited to two (2) notches (25°) or less during autopilotoperations. around or missed approach maneuvers not authorized during autopilotoperation.
  • Page 327 OPERATING HANDBOOK SUPPLEMENT AIRPLANE FLIGHT MANUAL Piper models PA-28R-20l and PA-28R-201T The autopilotmay be disconnected by: Depressing the “AP Disconnect” Switch on the left horn of the pilot’s control wheel. Placing the “AP Master Switch” in the “OFF” position. interrupting aircraftelectrical power...
  • Page 328 WELLS, FAA/DAS APPROVED PILOT’S OPERATING HANDBOOK AND/OR AIRPLANE FLIGHT MANUAL SUPPLEMENT Piper models PA-28R-201 and PA-28R-201T following altitude losses and bank angles were recorded after a malfunction with a I second recovery delay: Bank Angle/Altitude Loss Configuration 18°/-40’ Maneuvering (Coupled or Approach 20°/-20’...
  • Page 329 WELLS, FAAIDAS APPROVED PILOT’S OPERATING HANDBOOK AND/OR AIRPLANE FLIGHT MANUAL SUPPLEMENT Piper models PA-28R-201 and PA-28R-201T CONTROL WHEEL SWITCHES The left grip of the pilot’s control wheel will normally contain the following autopilot switches: • Manual ElectricTrim • Trim Interrupt/A/P Disconnect Switch...
  • Page 330 S-TEC CORPORATION MINERAL TEXAS 76067 WELLS, FAAJDAS APPROVED PILOT’S OPERATING HANDBOOK AND/OR AIRPLANE FLIGHT MANUAL SUPPLEMENT Piper models PA-28R-201 and PA-28R-201T TRIM SYSTEM WITH TRIM MONITOR TRIM TRIM TRIM ELEV. TRIM INTRPT ILPIMfi PUSH ti’: ON/OFF HORN C.B. FIGURE SYSTEM...
  • Page 331 PILOTS OPERATING HANDBOOK AND/OR AIRPLANE FLIGHT MANUAL SUPPLEMENT Piper models PA-28R-20l and PA-28R-201T AlP master switch Operate trim switch (both knob sections) NOSE Check that trim moves nàse down and yellow trim light in trim master switch flasheswhile trim is in motion. The trim “in motion” indicatorin should flash “TRIM”...
  • Page 332 FAAIDAS APPROVED PILOT’S OPERATING HANDBOOK AND/OR AIRPLANE FLIGHT MANUAL SUPPLEMENT Piper models PA-28R-201 and PA-28R-201T will disconnect A/P only when a pitch mode is engaged.) autopilot HDG and ALT modes Press trim interruptlAP Reengage disconnect switch Autopilot should disconnect: Retrim aircraft for take off- Check all controls for freedom of motion and determine that autopilot and trim have disconnected.
  • Page 333 OPERATING HANDBOOK AND/OR AIRPLANE FLIGHT MANUAL SUPPLEMENT • • and PA-28R-201T Piper models PA-28R-201 NOTE: be lowered at 129 KIAS to slow the landing gear may aircraft to the flap speed of 103 KIAS. in any case, the aircraft should...
  • Page 334 APPROVED PILOTS OPERATING HANDBOOK AND/OR AIRPLANE FLIGHT MANUAL SUPPLEMENT and PA-28R-201T Piper models PA-28R-201 SECTION SUPPLEMENTS Refer to contents of this supplement for operation for System 55/55X Automatic Flight Control System. SECTION OPERATING TIPS The textof thisSection not affected by installation o f this equipment.
  • Page 335 Pilot’s Operating Handbook Airplane Flight Manual. Approved APPROVED: ALBERT 3.MILL D.O.A. NO. SO- 1 PIPER AIRCRAFT, INC. VERO FLORIDA BEACH, 20. 2001 OF APPROVAL: DECEMBER DATE REPORT:...
  • Page 336 SECTION 1- GENERAL This supplement supplies information necessary for the operation of the airplane when the S-TEC ADF-650D is installed in accordance System with FAA approved Piper data. SECTION 2- LIMITATIONS No change. SECTION 3- EMERGENCY PROCEDURES No change. REPORT:...
  • Page 337 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 4- NORMAL PROCEDURES To turn on the ADF-650D System: • Depress the PWR button momentarily and release. NOTE button is pressed for longer than 3 If the PWR seconds, the receiverwill immediately shut off. • After successfulself test, input desired station frequency and selectANT mode.
  • Page 338 SECTION ARROW SUPPLEMENT PA-28R-201, 4- NORMAL SECTION PROCEDURES (continued) To perform the preflight checklistand selftest: After successful self test, press the mode control until ANT is displayed and input a predetermined frequency to selecta station in the immediate area. Adjust the volume control as necessary to provide a comfortable listening level.
  • Page 339 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 7- DESCRIPTION OPERATION System operates over a frequency range of 200 through The S-TEC ADF-650D 1799 kHz in l-kHz increments. Three operating modes are included as part of the ADF-650D System. • BFO • ADF •ANT VOLUME CONTROL...
  • Page 340 SECTION SUPPLEMENT ARROW PA-28R-201, 7- DESCRIPTION SECTION OPERATION (continued) Automatic Direction Finder (ADF) Mode Automatic Direction Finder mode uses conventional (ADF) nondirectional beacons and AM broadcast stations for navigation. This mode activates the bearing pointer. The bearing pointer will point in the directionof the station relative to the aircraft heading.
  • Page 341 SECTION ARROW PA-28R-201, SUPPLEMENT 7- DESCRIPTION SECTION OPERATION (continued) Clear (CLR) The clearfunction offersseveral options for the operator. • If the entire frequency isentered and the CLR button is pushed, all the numbers willbecome dashes. An additional push on the CLR button will restoreand display the priorfrequency entry.
  • Page 342 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 7- DESCRIPTION OPERATION (continued) Function (FUNC) Selector The function selectorenables the user to selectbetween contrastand volume display functions (on power-up, the RCR-650D will be in the volume display function). The first t ime the function selector is pressed, the receiverentersthe contrastfunction.
  • Page 343 SECTION ARROW PA-28R-201, SUPPLEMENT SECTION 7- DESCRIPTION OPERATION (continued) Function (FUNC) Selector continued Keypad Light Brightness The keypad lightbrightness setting isused to adjust the brightness of all legends on the display face.When the display is setup in the manual mode, press the FUNC selector untilthe keypad function isselected.
  • Page 344 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 7- DESCRIPTION OPERATION (continued) Test Mode 2OrviHz Press the TEST button to start the test mode. The text “TEST” will be displayed in the bottom right corner of the display for approximately seconds. this time, the IND-650A Indicator pointer will...
  • Page 345 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. APPROVED: ALBERT 3.MilL D.O.A. NO. SO -1 PIPER INC. AIRCRAFT, VERO FLORIDA BEACH, DATE OF APPROVAL: January 5, 2004 REPORT: VB-1612...
  • Page 346 This supplement supplies information necessary for the operation of the airplane when the Garmin 330 Transponder is installed in accordance with FAA approved Piper data. 2- LIMITATIONS SECTION A. Display of TIS traffic information is advisory only and does not relievethe pilotresponsibility to “see and avoid”...
  • Page 347 SECTION ARROW PA-28R-201, SUPPLEMENT SECTION 4- NORMAL PROCEDURES BEFORE TAKEOFF: • To transmitMode C (Altitude Reporting) code in flight: • Mode Selection Key • Code Selector SELECT assigned code. Keys To transmit Mode A (Aircraft Identification) code in flight: • Mode Selector Key •...
  • Page 348 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 5- PERFORMANCE No change. SECTION 6- WEIGHT BALANCE Factory installed optional equipment is included in the licensed weight and balance data in section6 of the Airplane Flight Manual. SECTION 7- DESCRIPTION OPERATION See the 400/500 Series Garmin Display Interfaces (Pilot’s Guide Addendum), 190-00140-13, and GTX 330 Pilot’s Guide, P/N for a...
  • Page 349 (JManual information not contained in this supplement, consult the Pilot’s performance Operating Handbook and FAA Airplane Flight Manual. Approved APPROVED: LINDA J. DICKEN DOA-5 10620-CE PIPER INC. AIRCRAFT, VERO FLORIDA BEACH, OCTOBER 7, 2004 DATE OF APPROVAL: REPORT: VB-1612 ISSUED:...
  • Page 350 SECTION SUPPLEMENT ARROW PA-28R.201, SECTION 1- GENERAL This airplane is equipped with the Avidyne FlightMax Entegra EXP5000 series Primary Flight Display with software to the latest approved 700-00006-OXX-( site and EX5000 series 700-00004-OXX-( Multi- revision per Avidyne Function Display with software to the latest approved revision per Avidyne web site, herein referredto as the “PFD”...
  • Page 351 SECTION SUPPLEMENT ARROW PA-28R.201, SECTION GENERAL (continued) The MFD is intended to be a supplemental display of situational and navigation information to the pilot. Its primary function is to provide a moving map display to the pilot for increased situational awareness. The MFD is capable of accepting data from a variety of GPS sensors, the BFG...
  • Page 352 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 2- LIMITATIONS Limitations A. PFD the PFD or any standby instrument is 1. IFR flight is prohibited when inoperative (altimeter, airspeed indicator, artificial horizon, or whiskey compass). aircrafttotal loss of essential engine 2. IFR flight is prohibited upon parameter display (manifold pressure, tachometer, fuel flow).
  • Page 353 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION LIMITATIONS (continued) B. MFD Limitations (continued) 4. Aircraft dispatch is prohibited when the MFD is inoperative. 5. Selecting “Lightning Display OFF’ for the Lightning overlay of the Map page will prevent current heading values from being sent to the WX500 sensor from the EX5000.
  • Page 354 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION LIMITATIONS (continued) C. CMAX CHART PAGE Limitations The geographic referenced aircraft symbol must not be used for navigation. NOTE aircraft symbol displayed provides supplemental aircraft situational awareness information.It is not intended as a means for navigation or flightguidance. The airplane is not to be used for conducting...
  • Page 355 SECTION ARROW SUPPLEMENT PA-28R-201, PAGE INTENTIONALLY LEFT BLANK THIS VB-1612 REPORT: 12, 1995 ISSUED: JULY 9-95 9, 2006 REVISED: JANUARY HB-PQY, Page: 9-95-(0) Revision: 16, JANUARY 9, 2006 9-95...
  • Page 356 SIU1’l(JN ARROW SUPPLEMENT PA-28R-201, SECTION 3- EMERGENCY PROCEDURES Failure of Pilot’sElectronic Attitude Direction Display Screen (PFD) Indication: PFD Display goes blank. Standby Attitude Gyro VERIFY flag is pulled on gyro Maintain attitude control using standby gyro and establishthe aircraft in straight and level unaccelerated flight.
  • Page 357 SECTION ARROW SUPPLEMENT PA-28R-201, 3- EMERGENCY SECTION PROCEDURES (continued) Loss of PFD Engine Data needle removed from dial and digital readout Indication: Indicator replaced with white dashes. Engine Instruments Refer to Engine page of MFD Land as soon as practical. Invalid Air Data data replaced with...
  • Page 358 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 3- EMERGENCY PROCEDURES (continued) Invalid Attitude and Heading Data Indication: Attitude and Heading Data removed and replaced with Red X’s. Standby Attitude Gyro VERIFY flag is pulled on gyro. Maintain attitudecontrol using standby gyro. If time and conditions permit: CircuitBreaker PULL and RESET...
  • Page 359 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 3- EMERGENCY PROCEDURES (continued) Failure of Attitude, Airspeed and Heading Reference System (ADAHRS) Indication: Airspeed, Altitude with Attitude, Heading replaced Red X’s. VERIFY Standby Attitude Gyro flag is pulled on gyro Maintain attitude control using standby gyro. If time and conditions permit: CircuitBreaker PULL...
  • Page 360 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 3- EMERGENCY PROCEDURES (continued) Cross Check Monitor on PFD. Indication: Yellow Crosscheck Attitude Annunciator Establish aircraft in straight and levelunaccelerated flight. AircraftAttitude Crosscheck aircraft attitude with standby attitude gyro Total Loss of Engine Instruments Indication: Indicator needle removed from...
  • Page 361 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 3- EMERGENCY PROCEDURES (continued) Alternator Failure Indication: Alternator annunciator light illuminated zero current on MFD alternator indication source. displayed NOTE the bus voltage is below 25 Vdc, the Low Anytime Voltage annunciator will be illuminated. Check ammeter Verify Failure If ammeter...
  • Page 362 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 3- EMERGENCY PROCEDURES (continued) Alternator Failure (continued) If power is not restored: ALTR Switch Reduce electricalloads by switching OFF or pulling circuitbreakers for all non-essential equipment to include the following: • Reduce PFD and MFD brightness as part of overallelectrical system management •...
  • Page 363 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 3- EMERGENCY PROCEDURES (continued) Electrical Failure Complete ‘N Standby Attitude Gyro SELECT power button Standby (STBY) CAUTION STBY annunciator will rapidly flash for minute when aircraft power is lost. approximately STBY must be selected, otherwise the gyro will auto shutdown after approximately one minute.
  • Page 364 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 3- EMERGENCY PROCEDURES (continued) Fire in Flight ElectricalFire Fire Extinguish VERIFY Standby Attitude Gyro flag is pulled on gyro Maintain aircraft control with reference to the standby airspeed, altimeter, and attitude gyro indicators. Battery Master Switch ALTR Switch Ground...
  • Page 365 SECTION ARROW PA-28R-201, SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES (continued) Aircraft Engine Power Loss During an engine failure the pilot may electto attempt an engine restart. During thistime large voltage drops may cause the PFD to lose power and reinitialize. During this initialization process the PFD not be able to complete a fast alignment during flight and therefore the pilot may have to obtain aircraft...
  • Page 366 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 3- EMERGENCY PROCEDURES (continued) Loss of Heading Accuracy Indication: • or GPS. Difficulty maintaining course while using VOR • Excessive difference between heading and track required maintaining a or GPS course. • ATC indicatesthe aircraft is on a wrong heading.
  • Page 367 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 4- NORMAL PROCEDURES Engine Start General CAUTION Do not attempt flight ifthere is no indication of alternator output. CAUTION If a positive oil pressure is not indicatedwithin 30 seconds following an engine start, stop the engine and determine the trouble.
  • Page 368 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 4- NORMAL PROCEDURES (continued) Normal Start Cold Engine Throttle ½ inch open Battery Master Switch Verify correctaircraft Primary Flight Display (PFD) model software Alternator Switch ElectricFuel Pump Mixture Prime then idle cut-off CLEAR Propeller Starter ENGAGE Mixture Full RICH...
  • Page 369 SECTION ARROW PA-28R-201, SUPPLEMENT 4- NORMAL SECTION PROCEDURES (continued) Engine Start When Flooded Throttle full Open Battery Master Switch Verify correct aircraft Primary Flight Display (PFD) model software Alternator Switch ElectricFuel Pump Mixture Idle cut-off CLEAR Propeller Starter ENGAGE Mixture Full rich Throttle RETARD...
  • Page 370 SECTION ARROW SUPPLEMENT PA.2R2OI, SECTION 4. NORMAL PROCEDURES continued) Starting With External Power Source CAUTION It is possible to use the ship’s battery in parallel by turning only the battery master switch ON. This will give longer cranking capabilities, but will not increase the amperage. Care should be exercised because if the ship’s battery has been depleted, the external power supply can be reduced to the levelof the ship’sbattery.
  • Page 371 SECTION ARROW PA-28R.201, SUPPLEMENT SECTION 7- DESCRIPTION OPERATION A. PFD Systems Description NOTE This supplement provides a general description of the Series 700-00006-OXX-( Avidyne FlighiMax Entegra its operation, and aircraft systems interfaces. For a PFD, detailed description of PFD operation, refer to the Avidyne Entegra Series Primary Flight Display Pilot’s FlightMax Guide, p/n 600-00104-000...
  • Page 372 ARROW PA-28R-201, SUPPLEMENT OPERATION SECTION 7- DESCRIPTION (continued) A. PFD Systems Description (continued) Horizontal Situation Indicator (HSI) Heading Data digital form at the top of the is represented in a boxed Magnetic heading rate (Rate of Turn Indicator) takes the form of a blue rose.
  • Page 373 SECTION ARROW SUPPLEMENT PA.28R-201, SECTION DESCRIPTION OPERATION (continued) A. PFD Description (continued) Systems Autopilot Integration The Entegra PFD is fully integrated with the S-TEC System Autopilot. Reference bugs for Heading, Altitude, and Vertical Speed are provided on the to control the autopilot and aid pilot situational awareness. These bugs are depending on the autopilot status.If displayed with solidor hollow symbology the autopilot is engaged in that mode, the bug is solid to indicatethe autopilot is...
  • Page 374 SECTION ARROW PA-28R-201, SUPPLEMENT OPERATION 7- DESCRIPTION (continued) SECTION A. PFD Systems Description (continued) Autopilot Integration (continued) are supported by the PFD: The following autopilot modes using the heading 1. HDG bug) (Heading, (Nay, using the course pointer and course deviation indicator) 2.
  • Page 375 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 7- DESCRIPTION OPERATION (continued) A. PFD Systems Description (continued) Instruments Back-up system installation includes redundant means of display of The Entegra PFD certain aircraft flight and systems Altimeter, Airspeed parameters. Back-up and Attitude instruments are provided to facilitate pilot cross-checking of display flight parameters.
  • Page 376 SECTION PA-28R..201, ARROW SUPPLEMENT SECTION 7. DESCRIPTION OPERATION (continued) B. MFD Systems Description NOTE provides a general description of the This supplement EX5000 Series 700-00004-OXX-( ) MFD, Avidyne operation and aircraft interface. For a detailed description of refer to the Avidyne EX5000 Series the MFD,...
  • Page 377 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 7- DESCRIPTION OPERATION (continued) B. MFD Systems Description (continued) (continued) Navigation data and the GPS-supplied present position, the Using the Jeppesen NavData can provide the pilot with the nearest 25 airports or navaids, depending on pilot selection, within 100 nm. This information is presented on Nearest page.
  • Page 378 IiI1U1N ARROW SUPPLEMENT PA-28R-201, OPERATION SECTION 7- DESCRIPTION (continued) B. MFD Systems Description (continued) Setup (continued) Airport Settings page provides selections for displaying airporttype, runway surface type and minimum lengths on the moving map. Declutter runway Settings page allows the pilot to select settings for defining the base map detail Time page provides an opportunity to when...
  • Page 379 HB-PQY, Page: 9-119-(0) Issued: JULY 12, 1995 9-119...
  • Page 380 For limitations, procedures and performance information not contained in this supplement, consult the Pilot’s Operating Handbook and FAA Airplane Flight Manual. Approved APPROVED: J. DICKEN LINDA DOA-5 10620-CE INC. PIPER AIRCRAFT, VERO FLORIDA BEACH, DATE OF APPROVAL: 22. 2006 REPORT: VB-1612 12, 1995 ISSUED:...
  • Page 381 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION GENERAL This airplane is equipped with the Avidyne FlightMax Entegra EXP5000 series Primary Flight Display with software to the latest approved 700-00006-OXX-( site and EX5000 series 700-00004-OXX-( Multi- revision per Avidyne Function Display with software to the latest approved revision per Avidyne web The PFD is intended to be the site, herein referredto as the “PFD”...
  • Page 382 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION GENERAL (continued) The MFD is intended to be a supplemental display of situational and navigation information to the pilot. Its primary function isto provide a moving map display to the pilot forincreased situational awareness. The MFD is capable of accepting data from a variety of GPS sensors, the BFG...
  • Page 383 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION GENERAL (continued) A B&C Specialties, BC4IO standby alternator, when will replace the primary alternator function, but will not supplement its output. The alternator is gear driven through the engine vacuum drive pad. pump The standby alternator isratedfor 20 amperes of maximum load.The actual load availablefor use is dependent on engine rpm and current operating conditions.
  • Page 384 SECTION ARROW PA-28R-201, SUPPLEMENT SECTION 2- LIMITATIONS A. PFD Limitations I. IFR flight is prohibited when the PFD oi any standby instrument is inoperative (altimeter, airspeed indicator, artificial horizon, or whiskey compass). 2. IFR flight is prohibited upon aircrafttotal loss of essential engine parameter display (manifold pressure, tachometer, fuel flow).
  • Page 385 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION LIMITATIONS (continued) B. MFD Limitations (continued) 4. Aircraft dispatch is prohibited when the MFD is inoperative. 5. Selecting “Lightning Display OFF” for the Lightning overlay of the Map page will prevent current heading values from being sent to the WX500 sensor from the EX5000.
  • Page 386 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION LIMITATIONS (continued) C. CMAX CHART PAGE Limitations The geographic referenced aircraft symbol must not be used for navigation. NOTE aircraft symbol provides supplemental displayed aircraft situational awareness information. Itis not intended as a means for navigation or flight guidance. The airplane is not to be used for conducting...
  • Page 387 SECTION ARROW SUPPLEMENT FA-28R-201, SECTION 3- EMERGENCY PROCEDURES Failure of Pilot’sElectronic Attitude Direction Display Screen (PFD) Indication: PFD Display goes blank. VERIFY Standby Attitude Gyro flag is pulled on gyro Maintain attitude control using standby gyro and establishthe aircraft in straight and levelunaccelerated flight.
  • Page 388 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 3- EMERGENCY PROCEDURES (continued) Loss of PFD Engine Data Indication: Indicator needle removed from dial and digital readout replaced with white dashes. Engine Instruments Refer to Engine page of MFD Land as soon as practical. Invalid Air Data Indication: Airspeed, Altimeter, and Vertical Speed...
  • Page 389 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 3- EMERGENCY PROCEDURES (continued) Data Invalid Attitude and Heading Indication: Attitude and Heading Data removed and replaced with Red X’s. VERIFY Standby Attitude Gyro flag is pulled on gyro. Maintain attitude control using standby gyro. If time and conditions permit: PFD Circuit Breaker PULL...
  • Page 390 SECTION ARROW PA-28R-201, SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES (continued) Failure of Attitude, Airspeed and Heading Reference System (ADAHRS) Indication: Airspeed, Altitude Attitude, with Heading replaced Red X’s. Standby Attitude Gyro VERIFY flag is pulled on gyro Maintain attitude control using standby gyro. If time and conditions permit: Circuit Breaker PULL...
  • Page 391 SECTION ARROW PA-28R-201, SUPPLEMENT PROCEDURES 3- EMERGENCY (continued) SECTION Cross Check Monitor on PFD. Attitude Annunciator Indication: Yellow Crosscheck Establish aircraft in straight and levelunaccelerated flight. Crosscheck aircraft attitude AircraftAttitude with standby attitude gyro Instruments Total Loss of Engine dial and digital readout removed from...
  • Page 392 SECTION ARROW PA-28R-201, SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES (continued) ALTERNATOR FAILURE Failure of Primary Alternator Indication: Alternator annunciator light illuminated zero current displayed on MFD alternator indication source. WARNING error may exceed 10 degrees with alternator Compass inoperative. CAUTION A power interruption greater than 20 seconds will result in loss of attitude information from the PFD untilthe unit...
  • Page 393 SECTION ARROW SUPPLEMENT PA-28R-201, PROCEDURES SECTION 3- EMERGENCY (continued) ALTERNATOR FAILURE (continued) Failure of Standby Alternator If STBY ALTR is not illuminated: VERIFY correct position Day/Night Switch STBYALTR STBY ALTR FIELD circuitbreaker Check and resetas required STBY ALTR SENSE circuitbreaker Check and reset as required ALTR STBY...
  • Page 394 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 3- EMERGENCY PROCEDURES (continued) ALTERNATOR FAILURE (continued) Reduce electricalloads by switching OFF or pulling circuitbreakers for all non-essential equipment to include the following: • Reduce and MFD brightness as part of overall electrical system management •...
  • Page 395 SECTION ARROW SUPPLEMENT PA-28R-201, 3- EMERGENCY PROCEDURES SECTION (continued) (Alternator over 20 amps above known electrical load) ElectricalOverload ALTR BATTMASTR If alternator loads are reduced: Reduce to minimum Electrical load NOTE Due to increased system voltage and radio frequency noise, operation with ALTR and BATE MASTR...
  • Page 396 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 3- EMERGENCY PROCEDURES (continued) Electrical Overload (Alternator over 20 amps above known electrical load) (continued) electrical loads by switching OFF or pulling circuitbreakers for all Reduce non-essential equipment to include the following: • Reduce and MFD brightness as part of overall electrical system management •...
  • Page 397 SECTION ARROW SUPPLEMENT PA-28R-201, PROCEDURES SECTION 3- EMERGENCY (continued) Electrical Failure Complete SELECT power button Standby Attitude Gyro Standby (STBY) CAUTION STBY annunciator will rapidly flash for one minute when aircraft power is lost. approximately must be selected, otherwise the gyro will auto STBY shutdown after approximately one minute.
  • Page 398 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 3- EMERGENCY PROCEDURES (continued) Fire in Flight ElectricalFire Fire Extinguish Battery Master Switch ALTR Switch STBY ALTR Switch SELECT power button Standby Attitude Gyro Standby (STBY) CAUTION flash for annunciator will rapidly STBY is lost. minute when aircraft power...
  • Page 399 SECTION ARROW SUPPLEMENT PA-28R-201, PROCEDURES SECTION 3- EMERGENCY (continued) Aircraft Engine Power Loss During an engine failure the pilot may electto attempt an engine restart. During to lose power and reinitialize. thistime large voltage drops may cause the PFD not be able to complete a fast During this initialization process the PFD have to obtain aircraft alignment during flight and therefore the pilot may...
  • Page 400 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 3- EMERGENCY PROCEDURES (continued) Loss of Heading Accuracy Indication: • Difficultymaintaining course while using VOR or GPS. • Excessive difference between heading and track required maintaining a or GPS course. • ATC indicatesthe aircraft is on a wrong heading. •...
  • Page 401 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 4- NORMAL PROCEDURES Engine Start General CAUTiON not attempt flight if there is no indication of primary alternator output. CAUTION If a positive oil pressure is not indicated within 30 seconds following an engine start, stop the engine and determine the trouble.
  • Page 402 SECTION ARROW PA-28R-201, SUPPLEMENT SECTION 4- NORMAL PROCEDURES (continued) Normal Start Cold Engine Throttle ½ inch open Battery Master Switch Primary Flight Display (PFD) Verify correct aircraft model software Alternator Switch Standby Alternator Switch Electric Fuel Pump Mixture RICH then IDLE CUT-OFF Propeller CLEAR...
  • Page 403 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 4- NORMAL PROCEDURES (continued) Engine Start When Flooded full Throttle Open Battery Master Switch Verify conect aircraft Primary Flight Display (PFD) model software Atternator Switch Standby Alternator Switch ElectricFuel Pump Mixture IDLE CUT-OFF CLEAR Propeller Starter ENGAGE Mixture...
  • Page 404 SECTION ARROW PA-28R-201, SUPPLEMENT SECTION 4- NORMAL PROCEDURES (continued) Starting With External Power Source CAUTION It is possible to use the ship’s battery in parallel by turning only the battery master switch ON. This will give longer cranking capabilities, but will not increase the amperage. Care should be exercised because if the ship’s battery has been depleted, the external power supply can be reduced to the levelof the ship’s battery.
  • Page 405 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 4- NORMAL PROCEDURES (continued) Ground Check Throttle 2300 RPM ALTR switch STBY ALTR switch STBY ALTR annunciator verify ON Increase electrical l oad to over 20 amps. STBYALTR annunciator verify flashing Decrease electrical l oad to lessthan 20 amps. STBY ALTR annunciator...
  • Page 406 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 7- DESCRIPTION OPERATION A. PFD Systems Description NOTE This supplement provides a general description of the Series 700-00006-OXX-( Avidyne FlightMax Entegra its operation, and aircraft systems interfaces.For a PFD, detailed description of PFD operation, refer to the Avidyne Entegra Series Primary Flight Display Pilot’s FlightMax revision 00 or appropriate later...
  • Page 407 SECTION ARROW SUPPLEMENT PA-28R-201, OPERATION SECTION 7- DESCRIPTION (continued) A. PFD Systems Description (continued) Horizontal Situation Indicator (HSI) Heading Data at the top of the heading is represented in a boxed digital form Magnetic rate (Rate of Turn Indicator) takes the form of a blue rose.
  • Page 408 SECTION ARROW PA-28R-201, SUPPLEMENT SECTION 7- DESCRIPTION OPERATION (continued) A. PFD Systems Description (continued) Autopilot Integration The Entegra PFD is fully integrated with the S-TEC System Autopilot. Reference bugs for Heading, Altitude, and Vertical Speed are provided on the to control the autopilot and aid pilot situational awareness. These bugs are displayed with solidor hollow symbology depending on the autopilot status.
  • Page 409 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 7- DESCRIPTION OPERATION (continued) A. PFD Systems Description (continued) Autopilot Integration (continued) The following autopilot modes are supported by the PFD: I. HDG using the heading (Heading, bug) 2. NAV (Nay, using the course pointer and course deviation indicator) 3.
  • Page 410 SECTION ARROW SUPPLEMENT PA-28R-201, 7- DESCRIPTION SECTION OPERATION (continued) A. PFD Systems Description (continued) Engine Instruments The Entegra PFD provides a display Pressure, Tachometer Manifold Engine Oil Pressure (OP), and Fuel Flow (FF) in the upper left hand corner of (RPM), the display.
  • Page 411 SECTION ARROW SUPPLEMENT PA-28R-201, 7- DESCRIPTION OPERATION SECTION (continued) B. MFD Systems Description NOTE provides a general description of the This supplement EX5000 Series 700-00004-OXX-( ) MFD, Avidyne operation and aircraft interface. For a detailed description of the MFD, refer to the Avidyne FlightMax EX5000 Series revision 00...
  • Page 412 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 7- DESCRIPTION OPERATION (continued) B. MFD Systems Description (continued) (continued) Navigation Using the Jeppesen NavData data and the GPS-supplied present position, the can provide the pilot with the nearest 25 airports or navaids, depending is presented on the pilot selection, within 100 nm.
  • Page 413 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 7- DESCRIPTION OPERATION (continued) B. MFD Description (continued) Systems Setup (continued) Airport Settings page provides selections for displaying airporttype, runway surface type and minimum lengths on the moving map. Declutter runway Settings page allows the pilot to select settings for defining the base map detail when page provides an opportunity to Time...
  • Page 414 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 7- DESCRIPTION OPERATION (continued) C. STANDBY ALTERNATOR System Description B&C Specialty Products Standby Alternator system delivers electrical power to the aircraft electrical power bus in the event of failure of the primary alternator. Powering the bus allows the pilotflexibility to choose equipment suitableto the current flight conditions.
  • Page 415 SECTION ARROW SUPPLEMENT PA-28R-201, ( ,) THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: 12, 1995 JULY 36 of 36 REVISED: 9-158, 22, 2006 HB-PQY, Page: 9-158-(0) Revision: 18, MAY 22, 2006 9-158...
  • Page 416: January 21. 2009

    For limitations,procedures and performance information not contained in this supplement, consult the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. APPROVED: Albeit J. Mill DOA-5 10620-CE Piper Aircraft, Inc. Vero Beach, Florida DATE OF APPROVAL: January 21. 2009 REPORT: VB-1612 ISSUED:...
  • Page 417 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION GENERAL The BendixlKing Digital ADF is a panel mounted, digitally tuned, automatic directionfinder. Itis designed to provide continuous 1 kHz digital tuning in the frequency range of 200 kHz to 1799 kHz and eliminatesthe need for mechanical band switching.
  • Page 418 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 4- NORMAL PROCEDURES To Operate as an Automatic Direction Finder: 1. OFF/VOL Control 2. Frequency Selector Knobs SELECT desired frequency in the standby frequency display. 3. FRQ Button PRESS to move the desired frequency from the standby to the active position.
  • Page 419 SECTION SUPPLEMENT ARROW PA-28R-201, 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 calledback by pressing the FRQ button, then transferred to active use by pressing the FRQ button again.
  • Page 420 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 4- NORMAL PROCEDURES (continued) 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 tomore than one station in an area. Certain conditions, such as Night Effect, may cause signals from such stationsto overlap.
  • Page 421 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 5- PERFORMANCE No change. 6- WEIGHT SECTION BALANCE is included in the licensed weight and Factory installed optional equipment balance data in Section 6 of the Pilot’s Operating Handbook and Airplane Flight Manual. ISSUED: 12, 1995 VB-1612 JULY REPORT:...
  • Page 422 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION KR-87 Digital ADE KI-227 Indicator Operating Controls and Indicators King Digital ADF Figure 1 VB-1612 .JULY 12, 1995 REPORT: ISSUED: REVISED: 21, 2009 9-165 JANUARY Page7oflO HB-PQY, Page: 9-165-(0) Revision: 19, JANUARY 21, 2009 9-165...
  • Page 423 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 7- DESCRIPTION OPERATION (continued) Figure 1 Legend 1. Mode Annunciation Antenna (ANT) isselected by the “out” position of the ADF button. This mode improves the aural reception and is usually used for station identification. The bearing pointer isdeactivatedand will park in the 90°...
  • Page 424 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION (continued) Figure 1 (continued) Legend 6. Timer Mode Annunciation Either the elapsed time (ET) or flight time (FLT) mode is annunciated here. 7. Frequency SelectorKnobs Selectsthe standby frequency when FRO displayed and directly selectsthe active frequency whenever eitherof the timer functions is selected.
  • Page 425 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 7- DESCRIPTION OPERATION (continued) Figure 1 (continued) Legend 15. Pointer Indicatesstation bearing in degrees of azimuth, relative to the nose of the aircraft. When heading controlis adjusted, indicates relative, magnetic, or true bearing of radio signal. 16.
  • Page 426 FAA consult the Pilot’s Operating Handbook Approved Airplane Flight Manual. APPROVED: A1bet J.Mill DOA-5 10620-CE Piper Aircraft, Inc. Vero Beach, Florida January 21. 2009 DATE OF APPROVAL: REPORT: VB-1612 ISSUED: JULY 1995 Page 1 of 4...
  • Page 427 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION GENERAL KN-63 supplies Continuous slant range distance Bendix/King information from a fixed ground stationto an aircraft in flight. The equipment consists of a KDI-572 Panel Display which contains all the operating controls and displays, and a remotely mounted KN-63 Receiver- Transmitter.
  • Page 428 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION KN-63 Bendix/King Figure 1 Figure 1 Legend I. DISTANCE DISPLAY distanceto VORTAC/WAYPOINT (NM) displayed in .1 nautical mile increments up to 99.9 NM, then in increments of one nauticalmile to 389 NM. 2.
  • Page 429 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 7- DESCRIPTION OPERATION (continued) Figure 1 (continued) Legend 6. DME MODE SELECTOR SWITCH (OFF, Ni, HLD, Applies power to the DME and selects DME operating mode as follows: OFF: Turns DME power off. SelectsDME operation with No. 1 VHF navigation set;...
  • Page 430 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. APPROVED: E. Gaulzetti Wayne ODA-5 I0620-CE Piper Aircraft, Inc. Vero Beach, Florida 12, 2010 DATE OF APPROVAL: REPORT: VB-1612 ISSUED: 12, 1995 JULY •...
  • Page 431 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION GENERAL The GNS43OW System is a fullyintegrated, panel mounted instrument, which contains a VHF Communications Transceiver, a VOR/ILS receiver, and a WAAS—enabled Global Positioning System (OPS) Navigation computer. The system consists of a GPS antenna, GPS/WAAS receiver, VHF VORILOC/GS VOR/ILS...
  • Page 432 SECTION ARROW PA-28R-201, SUPPLEMENT SECTION GENERAL (continued) Class II Oceanic, Remote, and other operations with the requirements for GPS The Garmin 430W has been found to comply of Class II navigation in oceanic and remote airspace when primary means used in conjunction with Garmin Prediction Program part number 006-A0 154- 03.
  • Page 433 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 2- LIMITATIONS Pilot’s Guide The Garmin 400W Series Pilot’s Guide, part number and revisionlisted below (or later revisions), must be immediately availablefor the flight crew whenever whenever navigation is predicated on the use of the GNS430W unit.
  • Page 434 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION LIMITATIONS (continued) Navigation Data Base (continued) instrument approaches using the GNS43OW are prohibited, unless the GNS43OW’s approach data is verified by the pilot or crew to be current. Instrument approaches must be accomplished in accordance with an instrument that is loaded...
  • Page 435 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION LIMITATIONS (continued) Terrain Data Base The GNS43OW supports Terrain and requires a Terrain database card to be installed in order for the feature to operate. The table below lists compatible database cards for the GNS43OW. Each of the database cards contains the following data: •...
  • Page 436 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION LIMITATIONS (continued) Approaches • approaches, the pilot must verify the GNS43OW unit is During or LPV.) operating in the approach mode. (LNAV, LNAV+V, L/VNAV, • When conducting approaches referenced to true North, the heading selection selection on the AUX pages must be adjusted to TRUE.
  • Page 437 SECTION SUPPLEMENT ARROW PA-28R-201, SECTION 3- EMERGENCY PROCEDURES Procedures Emergency No change. Abnormal Procedures Ifthe Garmin GNS43OW navigation information isnot available, or is invalid, utilize other remaining operational navigation equipment installed in the airplane as appropriate. If the 430W loses GPS position and reverts (indicated by the annunciation of “DR”...
  • Page 438 SECTION ARROW SUPPLEMENT PA-28R-291, SECTION 4- NORMAL PROCEDURES Series unit Pilot’s Guide defined in Section 2 Refer to the 400W Limitations of this supplement for normal operating procedures. This includes allGPS operations, VHF and NAy, and Multi-Function Display (optional) infermatipn. infermatipn.
  • Page 439 ARROW SUPPLEMENT PA-28R-201, 4- NORMAL PROCEDURES SECTION (continued) Autopilot Operation Autopilot when The Garmin GNS43OW be coupled to the STEC section of this supplement. For operating as prescribed in the LIMITATIONS utilize GPSS or GPS Roll lateral guidance, the STEC Autopilot may Steering in lieuof the analog deviation information, For autopilotoperational instructions, refer to the FAA...
  • Page 440 SECTION SUPPLEMENT ARROW PA-28R-201, 4- NORMAL PROCEDURES SECTION (continued) WFDE Prediction Program Garmin WAAS Fault Detection and Exclusion Prediction (WFDE) Program is required for Remote/Oceanic operations. Prediction Program should be used in conjunction with the Garmin 400W/500W Simulator. After entering the intended route of flight in the Simulator flight plan, the pilot selectsthe FDE Prediction Program under the...
  • Page 441 SECTION ARROW SUPPLEMENT PA-28R-201, INTENTIONALLY LEFT BLANK THIS PAGE 12, 1995 ISSUED: VB-1612 JULY REPORT; 12. 2010 REVISED: Page 12 of 12 9-184. HB-PQY, Page: 9-184-(0) Revision: 22, MAY 12, 2010 9-184...
  • Page 442 SECTION PA -28R-201, ARROW SUPPLEMENT PILOT’S OPERATING HANDBOOK APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO.22 GARMIN G500 PRIMARY FLIGHT MULTIFUNCTION DISPLAY SYSTEM The FAA for the Garmin PFD/ G500 approved operational supplement installedin accordance with STC is required SAO2O15SE-D, System, for operation of this system. Garmin will be responsible to supply and revise the operational supplement.
  • Page 443 SECTION SUPPLEMENT ARROW PAs2SR.201, THIS PAGE INThNONALLY LEFT BLANK REPORT: VB-1612 iSSUED: 12, 1995 JULY 9-186 REVISED: OCTOBER 24, 2011 HB-PQY, Page: 9-186-(0) Revision: 24, OCTOBER 24, 2011 9-186...
  • Page 444 This supplement must be attached to the Pilot’s Operating Handbook Airplane Flight Manual when the optional Flightcom model Approved intercom is installed in accordance with Piper Drawing 107421. information contained herein supplements or supersedes the Pilot’s Operating Handbook and FAA Airplane Flight Manual...
  • Page 445 SECTION SUPPLEMENT ARROW PA-28R-201, 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. SECTION LIMITATIONS No change.
  • Page 446 SECTION ARROW SUPPLEMENT PA-28R-201, SECTION 4- NORMAL PROCEDURES (Continued) Adjusting the Intercom and Headsets (Continued) NOTE Noise will not operate canceling microphones correctly if they are more than 1/8” from mouth. While speaking loudly, adjust the ICS volume controls on the Garmin audio panel to setthe pilot and copilot volumes to a comfortable level.
  • Page 447 SECTION ARROW SUPPLEMENT PA-28R-201, 4- NORMAL PROCEDURES SECTION (Continued) Isolate Switch and transmit operations, place the Isolate switch in For normal intercom position. To isolate the passengers from transmitting and receiving place the Flightcom 403 Isolate switch in the Isolate radio communications, position.
  • Page 448 SECTION ARROW SUPPLEMENT PA-28R.201, PILOT’S OPERATING HANDBOOK APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO.24 650 NAVIGATION SYSTEM GARMIN for the Garmin approved operational supplement installed in accordance with STC SAO2OI9SE-D, Navigation System, required for operation of this system. Garmin will be responsible to supply and revise the operational supplement.
  • Page 449 SECTION SUPPLEMENT ARROW PA-28R-201, THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12,1995 9-192 12, 2016 REVISED: JANUARY HB-PQY, Page: 9-192-(0) Revision: 26, JANUARY 12, 2016 9-192...
  • Page 450 SECTION ARROW SUPPLEMENT PA-28R-201, PILOT’S OPERATING HANDBOOK APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO.25 GARMIN 88 TRANSCEIVER SYSTEM for the Garmin approved operational supplement Transceiver System, installedin accordance with STC SAO21 19SE, is required for operation of this system. Garmin will be responsible to supply and revise the operational supplement.
  • Page 451 SECTION ARROW SUPPLEMENT PA-28R-201, PAGE INTENTIONALLY LEFT BLANK THIS REPORT: VB-1612 ISSUED: 12, 1995 JULY 9-194 REVISED: 12, 2016 JANUARY HB-PQY, Page: 9-194-(0) Revision: 26, JANUARY 12, 2016 9-194...
  • Page 452 No.E-362-E for the 3-Blade Constant Speed PropellerSystem MTV-I 2-B/I 80-17 installed o n the Airplane (all Serial Numbers) PIPER PA28R-180 with 200 HP-Engine PIPER PA 28R-200 PIPER PA 28R-201 PIPER PA 28RT-201 avstlsble Mufflerconfigurations: 1.without muffler 2. Muffler Gomoizig PA28-606504 3.
  • Page 453 Page 1 of 4 Airplane Flight Manual Supplement No. E-362 E PA-28R-1 80 (200HP), PA28R-200/-201, PA28RT-201 EditionJan. 16, 2004 Revision 2 April 21 2006 This Airplane Flight Manual Supplement belongs tothe aircraft: Aircraft regiatration No: SerialNo.: zct.c Year of manufacture: TCDS No.
  • Page 454 2700 RPM red radial line at 2700 RPM Markings and placards concerning other propellers, are obsolete. Propeller-Governor: According to Piper equipment list Propeller-Spinner: MT-Propeller No. P-391 The aircraft may be operated without spinner as well. In thiscase remove tiller plates.
  • Page 455 i-’.. Page 3 of4 Airplane Flight Manual Supplement No. E-362 E PA-28R-1 80 (200HP), PA28R-200/-201 PA28RT-201 EditionJan. 16, 2004 5. PERFORMANCE Max. continous speed with MTV-12-B/180-17 2500 RPM propeller: Max take off speed with MW-12-B/180-17 2700 RPM (5mm) propeller: information given in the charts of the Original POHIAFM concerning take off performance (landing gear extended or retracted), t ime, distance and fuel consumption attake offare validfurtherwhen the...
  • Page 456 Page4of4 Airplane Flight Manual Supplement No. E-362 E PA-28R-1 80 (200HP), PA28R-200/-201, PA28RT-201 EditionJan. 16, 2004 PA28RT-201 Cruisespeed Piper PA28R-201, PA-28R-180 PA28R-200, (200HP), :onditions: Peak-50°F LYC. 10-360-C Engine: (on the rich side) (%-perforrnance relatedto max. engine max. take off weight...
  • Page 457 Nach iolzig Flugzeug- alldampfer-Anlage unci Maschinenbau GmbH von: “System Gomoizig’ Häfen 84 a, 5600 PA28 606504 Wuppertal Nr.: I-C 39, Il-A 226 Ausgabe: 02.93 Umrustanweisung Anhang Flughandbuch mit Nachschalldampfer-Anlage”System PA28 606504 Gomolzig’ Dieser Anhang gehort zum Flughandbuch Flugzeug: ‘ ...‘-::?Y i”...
  • Page 458 1’ AIRCRAFT FLIGHT MANUAL FLARM Technology f%#jj. SUPPLEMH FOCA APPROVED AIRCRAFT FLIGHT MANUAL SUPPLEMENT FLARM COLLISION WARNING DEVICE Aircraft Registration: AircraftMake: __________________________________ .—20A AircraftModel: ZC4LI AircraftSerialNumber: €ASA OOAO04ZO9 Approval Reference & Date: /OcJ-215.M This document must be carried in the aircraft atall the times.It describes the operatingprocedures for a fix installed F LARM Collision Warning System aridits interfaces inaccordance with the FLARM Installation F OCA...
  • Page 459 AIRCRAFT FLIGHT MANUAL SUPPLEMENT FLARM Technology fIAj’jn TABLE OF CONTENTS SECTION GENERAL SECTION OPERATING LIMITATIONS SECTION EMERGENCY PROCEDURES.. SECTION NORMAL OPERATING PROCI SECTION PERFORMANCE SECTION WEIGHT BALANCE SECTION SYSTEM DESCRIPTION OF REVISIONS REVISION Date FOCA Approval Page Description Original release 15.03.2006 Original Note:...
  • Page 460 AIRCRAFT FLIGHT MANUAL FLARM Technology flirn SUPPLE SECTON GENERAL The gliding scene has been confrontedsince years to dramaticmid air collision a ccidents. With the extreme tine shape and relatively high cruise speed of modern gliders, thehuman vision has reached its limit o f detection.
  • Page 461 AIRCRAFT FLIGHT MANUAL SUPPLEMENT Technology fIAn SEC1ION OPERA11NG LIMATIONS 1. This FLARM installation i s compliant for “situationawareness only”. The following placard must be installed on the instrumental panel, at the proximity ofthe display: For Situation Awareness only must not be based solely on the use of the information presented on the FLARM Maneuvering displays or aural annunciations.
  • Page 462 AIRCRAFT FLIGHT MANUAL FLARM Technology fJAi4n SUPPLEMEJ SEC11ON EMERGENCY PROCEDURES Incase of Fire,Smoke, electrical burning smells or Electromagnetic Interferencesfollow the Emergency procedure ofthe basic AFM. FLARM is normally installed o n a non-essential bus. But on ancientaircraft itis possible lhat only an avionics bus oreven only a main bus isavailable forall electrical consumers.
  • Page 463 AIRCRAFT FLIGHT MANUAL SUPPLEMENT Technology fIAtn LFLARM SECTION NORMAL OPERATING PROCEDURES 4.1 General Itisrecommended to carry the FLARM Operating Manual version3 or later on board the aircraft. To make good use of the informationcontains in this manual the pilot should knom the hardware version, the software version, the serial number and the obstacledatabase name currently installed i nthe FLARM.
  • Page 464 AIRCRAFT FLIGHT MANUAL SUPPLEMENT Technology 4.5 Line of sight Compatible FLARM unitsmust be within range inorder to provide a warning. The range is very much and position of the radio antennae, plus the relative p ositions o f the two determined by the type, installation aircraft.
  • Page 465 AIRCRAFT FLIGHT MANUAL SUPPLEMENT Technology fIAfrn [FLARM SEC11ON PERFORMANCE No Change to basic flight m anual SECTION WEIGHT BALANCE No Change to basic flight m anual SECTION SYSTEM DESCRIPTION 7.1 System description receives position and movement information from an internal G PS FLARM receiverwithan externalGPS antenna.
  • Page 466 AIRCRAFT FLIGHT MANUAL SUPPLEMENT FLARM Technology fIArs 7.3 In-flight software scheme 7.4 Radio transmission The FLARM system uses a data communication frequency in thefree Non-Specific Short Range Device (SRD), sub band f, between 868.0— 868.6 MHz and with an ERP power ofless than 10 mW (dutycycle 1%).
  • Page 467 SECTION ARROW OPERATING PA-28R-201, TIPS TABLE CONTENTS SECTION OPERATING TIPS Paragraph Page 10.1 General 10-1 10.3 10-1 Operating ‘lips ISSUED: 12, 1995 REPORT: VB-1612 JULY 10-i HB-PQY, Page: 10-0-(1) Issued: JULY 12, 1995 10-i...
  • Page 468 SECTION ARROW TIPS OPERATING PA-2SR-201, ‘i.’ LEFT BLANK THIS PAGE INTENTIONALLY REPORT: VB-1612 ISSUED: 12, 1995 JULY 10-il HB-PQY, Page: 10-0-(2) Issued: JULY 12, 1995 10-ii...
  • Page 469 SECTION ARROW OPERATING TIPS PA-28R-201, SECTION OPERATiNG TIPS 10.1 GENERAL This section provides operating tips of particular value in the operation of the Arrow. 10.3 OPERATING TIPS (a) Learn to trim for takeoff so that only a very light back pressure on the control wheeJ is required to lift the airplane offthe ground.
  • Page 470 OPERATING PA-28R-201, ARROW 10.3 OPERATING TIPS (continued) (g) The rudder pedals are suspendçd from a torque tube which extends across the fuselage. The pilot should become miliar. with the proper positioning of his feet on the rudder pedals so as to avoid interference with the torque tube when the rudder pedals moving...