Piper Arrow PA-28R-201 Pilot Operating Handbook
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Piper Arrow PA-28R-201 Pilot Operating Handbook

Piper Arrow PA-28R-201 Pilot Operating Handbook

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Table of Contents

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See also: Pilot Operating Handbook , Information Manual
AIRPLANE
SERIAL
PA-28R-201
REPORT:
DATE
JULY 12, 1995
THIS
PILOT
PROVIDED
AIRPLANE
AT ALL TIM ES.
Page: 0-0-(1)
NO. ________________
VB-1612
FAA APPROVED
OF APPROVAL:
HANDBOOK
INCLUDES
BY THE
FEDERAL
AVIATION
BY
THE
MANUFACTURER
FLIGHT
MANUAL
Issued: JULY 12, 1995
ARROW
PA-28R-201
AIRPLANE
AIRPLANE
REGIST. NO. _____________
BY:
PETER
D.O.A. NO. SO-I
THE NEW
VERO
THE
MATERIAL
REQUIRED
REGULATIONS
AND
CONSTITUTES
THIS HANDBOOK
MUST
SN 2844001 AND
PILOT'S
OPERATING
HANDBOOK
AND
FAA APPROVED

FLIGHT MANUAL

E. PECK
PIPER AIRCRAFT,
FLORIDA
BEACH,
TO BE
FURNISHED
AND
ADDITIONAL
INFORMATION
THE
FAA
APPROVED
BE CARRIED
IN THE
—
Piper
UP
INC.
TO THE
AIRPLANE
i

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  • Page 1: Flight Manual

    NO. ________________ SERIAL REGIST. NO. _____________ PA-28R-201 REPORT: VB-1612 FAA APPROVED PETER E. PECK D.O.A. NO. SO-I DATE OF APPROVAL: THE NEW PIPER AIRCRAFT, INC. JULY 12, 1995 VERO FLORIDA BEACH, THIS HANDBOOK INCLUDES MATERIAL REQUIRED TO BE FURNISHED TO THE...
  • Page 2 REVISIONS SUBSEQUENT SUPPLIED PIPER MUST PROPERLY INSERTED. Published by PUBLICATIONS DEPARTMENT Issued: July 12, 1995 © 1995-1996, 1998, 2000-2001, 2004-2006, 2009-2011 PIPER AIRCRAFT, INC. All Rights Reserved REPORT: VB-1612 ISSUED: JULY 12, 1995 REVISED: OCTOBER 24, 2011 Page: 0-0-(2) Revision: 24, OCTOBER 24, 2011...
  • Page 3 PA-28R-201, ARROW APPLICABILITY of this handbook is limited to the specific Piper Application PA-28R-201 model airplane designated by serialnumber and registration number on the face of the title page of this handbook. This handbook cannot be used for operational purposes unless kept in a current status.
  • Page 4 PA-28R-201, ARROW REVISIONS The information compiled in the Pilot’s Operating Handbook, with the exception of the equipment list, w ill be kept current by revisions distributed to the airplane owners. The equipment list was currentat the time the airplane was licensed by the manufacturer and thereafter must be maintained by the owner.

  • Page 5: Table Of Contents

    PA-28R-201, ARROW 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 FAA Approved Number and Revised Description of Revisions Signature Code and Date Pages Added Rev. 1 to L of R page. Rev.

  • Page 6: Added Pages And Supplement

    ARROW PA-28R-201, PILOT’S OPERATING HANDBOOK REVISIONS (cont) FAA Approved Revision Number and Revised Description ofRevisions Signature Code and Date Pages Rev. 5 9-47 Added pages thru and Supplement 8. (PR0009 14) continued 9-56 9-57 Added pages thru and Supplement 9. 9-62 9-63 Added pages...

  • Page 7: Revision

    PA-28R-201, ARROW OF REVISIONS PILOT’S OPERATING HANDBOOK (cont) Revision Approval Number Revised Description of Revisions Signature and Date Code Pages Rev. 9 Added Warning and moved info,to page iv. (PRO4O 105) Moved info, from page iii. vi-a Added page and Rev. 9 toL of R. vi-b Added page.
  • Page 8 PA-28R-201, ARROW PILOT’S OPERATING HANDBOOK OF REVISIONS (cont) Revision FAA Approval Number Revised Description of Revisions Signature Code and Date Pages Rev. 11 9-109 Added pages thru and Supplement 17. (PR041007) continued 9-112 Linda J. Dicken October 7, 2004 Rev. 12 vi-b Added Rev.

  • Page 9: (Pr000914) 9-I

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

  • Page 10: Added Supplement 21

    PA-28R-201, ARROW PILOT’S OPERATING HANDBOOK OF REVISIONS (cont) Revision FAA Approval Number Revised Description of Revisions Signature Code and Date Pages Rev. 22 vi-d Added Rev. 22 toL of R Added Note to Para.2.23 (PR100512) Revised TOC. Relocated text 4-u. to pg.

  • Page 11: Revised T Of C

    PA-28R-201, ARROW PILOTS OPERATING HANDBOOK OF REVISIONS (cont) Revision Approved Number and Revised Description of Revisions Signature Code and Date Pages Rev. 23 Updated copyright dates. (PR 10 110 1) vi-e Added Page. Added Rev. 23 to L of R. vi-f Added Page.
  • Page 12 PA-28R-201, ARROW PILOT’S OPERATING HANDBOOK OF REVISIONS (cont) Revision FAA Approved Number Revised Description of Revisions Signature Code and Date Pages REPORT: VB-1612 ISSUED: 12, 1995 JULY vi-f REVISED: NOVEMBER 1, 2010 Page: 0-0-(12) Revision: 23, NOVEMBER 1, 2010 vi-f...
  • Page 13 PA-28R-201, ARROW OF CONTENTS TABLE GENERAL SECTION LIMITATIONS SECTION PROCEDURES EMERGENCY SECTION PROCEDURES NORMAL SECTION PERFORMANCE SECTION AND BALANCE WEIGHT SECTION OPERATION DESCRIPTION SECTION AN]) ITS SYSTEMS THE AIRPLANE SERVICING AIRPLANE HANDLING, SECTION AN]) MAINTENANCE SUPPLEMENTS SECTION TIPS OPERATING SECTION VB-1612 REPORT: 12, 1995...
  • Page 14 PA-28R-201, ARROW THIS PAGE LEFT INTENTIONALLY BLANK REPORT: VB-1612 ISSUED: JULY 12,1995 vu’ Page: 0-0-(14) Issued: JULY 12, 1995 viii...
  • Page 15 SECTION GENERAL PA-28R-201, ARROW TABLE OF CONTENTS SECTION GENERAL Page Paragraph Introduction Engines Propellers Fuel 1.11 Maximum Weights 1.13 Standard Airplane Weights 1.15 BaggageSpace 1.17 Specific Loadings Symbols, Abbreviations and Terminology 1.19 VB-1612 REPORT: l2, 1995 ISSUED: JULY Page: 1-0-(1) Issued: JULY 12, 1995...
  • Page 16 SECTION PA-28R-201, ARROW GENERAL THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 1-il Page: 1-0-(2) Issued: JULY 12, 1995 1-ii...
  • Page 17 SECTION PA-28R-201, ARROW GENERAL SECTION GENERAL 1.1 INTRODUCTION is designed for maximum utilization This Pilot’s Operating Handbook as an operating guide for the pilot. Itincludes the material required to be furnished to the pilotby the Federal Aviation Regulations and additional and constitutes the FAA information provided by the manufacturer Approved Airplane Flight Manual.
  • Page 18 GENERAL PA-28R-201, ARROW 1.00 170.0 Wing Area (sq. f t.) Mi,,. T urning Radius (ft) (from pivot p oint to wing tip) 31.0 THREE VIEW Figure 1-1 REPORT: VB-1612 ISSUED: JULY 12, 1995 Page: 1-2-(0) Issued: JULY 12, 1995...
  • Page 19 SECTION GENERAL PA-28R-201, ARROW 1.3 ENGINES Number of Engines (b) Engine Manufacturer Lycoming (c) Engine Model Number 10-360-C 1C6 (d) Rated Horsepower 2700 Ce) Rated Speed (rpm) 5.125 (I) Bore(in.) 4.375 (g) Stroke (in.) (h) Displacement (Cu. in.) 8.7:1 (1) Compression Ratio Four Cylinder, Direct (j) Engine Type Drive, Horizontally...
  • Page 20 SECTION GENERAL PA-28R-201, ARROW 1.5 PROPELLERS (continued) HARTZBLL (a) Number of Propellers (b) Propeller Manufacturer Hartzell (c) Blade Model F7666A-2R (d) Number ofBlades (e) Hub Model HC-C2YK-1( (f) Propeller Diameter (in.) (1) Ma2dmum (2) Minimum Constant Speed, (g) Propeller Iype Hydraulically Actuated 1.7 FUEL (a) Fuel Capacity(U.S.gal.) (total)
  • Page 21 SECTION PA-28R-201, ARROW GENERAL 1.11 MAXIMUM WEIGHTS (a) Maximum Takeoff Weight (lb.) 2750 (b) Maximum 2750 Landing Weight (lb.) (c) Maximum Weights in Baggage Compartment 1.13 STANDARD AIRPLANE WEIGHTS* (a) Standard Empty Weight (lb.): Weight of a standard airplane including unusable fueL full operating fluids and 1603 full oil.
  • Page 22 SECTION GENERAL PA-28R-201, ARROW 1.19 SYMBOLS, ABBREVIATIONS TERMINOLOGY definitions are of symbols, abbreviations following and those which may terminology used throughout the handbook be of added operational significance to the pilot. (a) General Airspeed Terminology and Symbols Calibrated Airspeed means the indicated speed of an aircraft, correctedfor position and instrument error.Calibrated airspeed is equal to true airspeed in standard...
  • Page 23 SECTION PA-28R-201, ARROW GENERAL 1.19 SYMBOLS, TERM]NOLOGY ABBREVIATIONS, (continued) Maximum Landing Gear Extended Speed is speed at which an aircraft c an the maximum be safely flown with the landing gear extended. VI.o Maximum Landing Gear Operating Speed is speed at which the landing the maximum gear can be safely extended or retracted.
  • Page 24 SECTION PA-28R-201, ARROW GENERAL TERMINOLOGY 1.19 SYMBOLS, (continued) ABBREVIATIONS, (b) Meteorological Terminology International Standard Atmosphere which: (1) Theairisadryperfectgas. (2) The temperature atsea level is15°Celsius Celsius (59°Fahrenheit). (3) The pressure atsea level is29.92 inches Hg (1013.2mb). (4) The temperature gradient from sea level to the altitude atwhich the temperature is -56.5°C (-69.7°F) is 0.00198°C...
  • Page 25 SECTION PA.28R-201, ARROW GENERAL AN]) TERMINOLOGY 1.19 SYMBOLS, ABBREVIATIONS, (continued) (c) Power Terminology power permissible fortakeoff. Takeoff Power Maximum Con- Maximum Maximum power permissible continuously tinuousPower during flight. Maximum Climb Maximum power permissible during climb. Power Maximum Maximum Cruise during power permissible cruise.
  • Page 26 GENERAL PA-28R-201, ARROW 1.19 SYMBOLS, TERMINOLOGY ABBREVIATIONS, (continued) (f) Weight and Balance Terminology An imaginary vertical p lane from which all Reference Datum horizontal distances are measured balance purposes. Station A location along the airplane fuselage usuallygiven in terms of distancefrom the reference datum.
  • Page 27 SECTION PA-28R-201, ARROW GENERAL 1.19 SYMBOLS, TERMINOLOGY ABBREVIATIONS, (continued) 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 Maximum weight approved...
  • Page 28 SECTION PA-28R-201, ARROW GENERAL THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12,1995 1-12 Page: 1-12-(0) Issued: JULY 12, 1995 1-12...
  • Page 29 SECTION PA-28R-201, ARROW LIMITATIONS TABLE OF CONTENTS SECTION LiMITATIONS Paragraph Page General Airspeed Limitations Airspeed Indicator Markings Power Plant Limitations Power Plant Instrument Markings 2.11 Weight Lmii 2.13 Center of Gravity Lum 2.15 Maneuver Lami Flight Load Factors 2.17 I,pes of Operations 2.19 2.21 Fuel Limitations...
  • Page 30 SECTION PA-28R-201, ARROW LIMiTATIONS TElLS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 2-li Page: 2-0-(2) Issued: JULY 12, 1995 2-ii...
  • Page 31 SECTION PA-28R-201, ARROW LIMITATIONS SECTION LIMiTATIONS GENERAL This section provides the FAA operating limitations, Approved instrument markings, color coding and basic placardsnecessary for the safe operation of the airplane and its systems. Limitations associated with those optional systems and equipment can be found in Section 9 which...
  • Page 32 SECTION LTh1ITATIONS PA-28R-201, ARROW AIRSPEED LIMITATIONS (continued) SPEED KIAS KCAS Maximum Flaps Extended Speed (Vin) Do not exceed this speed withthe flaps extended. Maximum Landing Gear Extension Speed Do not exceed this speed when extending the landinggear. Maximum Landing Gear Retraction Speed Do not exceed this speed when retracting the landinggear.
  • Page 33 SECTION LIMITATIONS PA-28R-201, ARROW POWER PLANT LIMITATIONS (a) Number of Engines (b) Engine Manufacturer Lycoming IO-360-C1C6 (c) Engine Model No. (d) Engine Operating Limits (1) Maximum Horsepower 2700 (2) Maximum Rotation Speed (RPM) Oil Temperature 245°F (3) Maximum (e) Oil Pressure 25 PSI Minimum (red line)
  • Page 34 JI.L1UJN LIMITATIONS PA-28R-201, ARROW POWER PLANT INSTRUMENT MARKINGS (a) Tacbometer Green Arc (Normal OperatingRange) 500 to 2700 RPM Red Line (Maximum Continuous 2700 RPM Power) (b) Oil Temperature Green Arc (Normal OperatingRange 75° to 245°F Red Line (Maximum) 245°F (c) Oil Pressure Green Arc (Normal OperatingRange 60 PSI to90 PSI Yellow Arc (CautionRange) (Idle)
  • Page 35 SECTION PA-28R-201, ARROW 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 OF GRAVITY LIMITS Forward Limit Rearward Limit Weight Pounds Inches Aft of Datum Inches Aft of Datum...

  • Page 36: Fuel Limitations

    • PA-28R-201, ARROW LIMITATIONS 2.17 FLIGHT LOAD FACTORS (a) Positive Load Factor (Maximum) 3.8 0 No inverted maneuve (b) Negative Load Factor (Maximum) approve 2.19 TYPES OF OPERATIONS The airplane is approved for the following operations when equipped in accordance with FAR 91 or FAR 135.

  • Page 37: Placards

    SECTION PA-28R-201, ARROW LIMITATIONS 2.23 PLACARDS In full view of the pilot: LIMITATIONS INFORMATION —4 OIL COOLER THISAIRCRAFT APPROVED FOR NIGHT I.F.R., WINTER HON-ICING FLIGHT IZATTON PLATE TO BE WHEN EQUIPPED IN ACCORDANCE WITH FAR St OR FAR 135. REMOVED WHEN AMBIENT NO ACROBATIC MANEUVERS, INCLUDING SPINS,APPROVED.
  • Page 38 SECTION LIMITATIONS PA-28R-201, ARROW 2.23 PLACARDS (continued) (Serial Numbers 2844001 through 2844021 only) In full view of the pilot, the following Takeoff and Landing Checklists will be installed: TAKEOFF CHECKLIST Fuel on Proper Tank Fasten Belts/Harness Electric Fuel Pump Flaps Set Checked Trim Tab Set Engine Gauges...
  • Page 39 SECTION PA-28R-201, ARROW LIMITATIONS 2.23 PLACARDS (continued) On the instrument panel in full view of the pilot inaircraft with McCauley propeller installations only: AVOID CONTINUOUS OPERATIONS BETWEEN 1500 AND 1950 RPM BELOW 15” MANIFOLD PRESSURE. In full view of pilot: CAUTION COMPASS CAL.
  • Page 40 SECTION PA-28R-201, ARROW LIMITATIONS 2.23 PLACARDS (continued) On theaft baggage closeout: MAXIMUM BAGGAGE 200 LBS. NO HEAVY OBJECTS ON HAT SHELF. Adjacent to upper door latch: ENGAGE LATCH BEFORE FLIGHT On inside of baggage compartment door: BAGGAGE MAX. LBS. WEIGHT BALANCE DATA BAGGAGE...

  • Page 41: Engines

    /?J?-f (HB-2008-135R1) ,;74:;t.1 (tef.. ATTN: Solomon Hecht, Aerospace Engineer, Boston ACO, 12 New England Executive Park, Burlington, MA 01803; telephone: ( 781)238-7159; fax: (781) 238-7170. Before usingany approved AMOC on any airplane to which theAMOC applies, notify your appropriate principal inspector (P1) intheFAA Flight Standards District Office (FSDO), or lacking a PT,your local FSDO.
  • Page 42 SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES TABLE OF CONTENTS SECTION EMERGENCY PROCEDURES Page Paragraph General Airspeeds For Safe Operation Emergency Procedures Checklist Engine Fire During Start (3.9) 3.5a Engine Power Loss During Takeoff (3.11) 3.5b Engine Power Loss In Flight (3.13) 3.5c Power Off Landing (3.15) 3.Sd...
  • Page 43 SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES OF CONTENTS TABLE SECTION PROCEDURES EMERGENCY (cont) Page Paragraph 3-11 Amplified Emergency Procedures (General) 3-11 Engine Fire During Start (3.5a) 3-11 3.11 Engine Power Loss During Takeoff (3.5b) 3-12 3.13 Engine Power Loss In Flight(3.5c) 3-13 3.15 PowerOffLanding(3.5d)
  • Page 44 SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES SECTION EMERGENCY PROCEDURES 3.1 GENERAL This section provides the recommended procedures for coping with vanous emergency or critical situations. A ll of the emergency procedures requiredby the FAA as well as those necessary for operation of the airplane, as determined by the operating and design features of the airplane, are presented.
  • Page 45 SECTION EMERGENCY PA-28R.201, ARROW PROCEDURES AIRSPEEDS SAFE OPERATION 3.3a STALL SPEEDS 60 KIAS 2750 lbs (Gear Up, 0 Flap) 2750 lbs (Gear Down, 40 Flap) 55 KIAS 3.3b MANEUVERING SPEEDS 118 KIAS 27501bs 1865 lbs 96KIAS 3.3c NEVER EXCEED SPEED Never Exceed Speed 183 KIAS 3.3c1POWER...
  • Page 46 SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES EMERGENCY PROCEDURES CHECKLIST 3.5a ENGINE FIRE DURING START (3.9) ENGINE Starter CRANK Mixture IDLE CUT-OFF Throttle OPEN Electric Fuel Pump Fuel Selector Abandon if fire continues. DURING TAKEOFF 3.5b ENGINE POWER LOSS (3.11) If sufficient runway remains for a normal landing, leave gear down and land straight a head.
  • Page 47 SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES POWER LOSS IN FLIGHT 3.5c ENGINE (3.13)(continued) Electric f uel pump RICH Mixture OPEN Alternate Air CHECK forindication Engine Gauges of cause of power loss Ifno fuel flow/pressure is indicated, c heck tank selector p osition tobe sureitison a tank containing fuel.
  • Page 48 SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES 3.5d POWER LANDING (3.15) (continued) Gear Up Emergency Landing (3.15b) In theeventa gear up landing is required, p roceed as follows: AS DESIRED Flaps Throttle CLOSE Mixture IDLE CUT-OFF Ignition BATT MASTR Switch ALTR Switch Fuel Selector SeatBeltand Harness TIGHT...
  • Page 49 SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES OF OIL PRESSURE 3.5f LOSS (3.19) Land as soon as possible and investigate cause. Prepare for power off landing. OF FUEL FLOW/PRESSURE 3.5g LOSS (3.21) Electric Fuel Pump CHECK on tank Fuel Selector containing fuel 3.5h HIGH OIL TEMPERATURE (3.23)

  • Page 50: Propellers

    SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES 3.Sj ELECTRICAL OVERLOAD (Alternator over 20 amps above knoi electrical load) (3.27)(Continued) Ifammeter reading does NOT decrease: LTh Switch Land as soon as possible. Use Emergency Landing Gear Extension (3.5m) to lower landinggear. Ifammeter reading DOES decrease: BAIT MASTR...
  • Page 51 SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES 3.5k PROPELLER OVERSPEED (continued) FULL DECREASE Propeller Control rpm, thenset if any control available. REDUCE Airspeed Throttle AS REQUIRED remain below 2700 rpm 3.Sm EMERGENCY LANDING GEAR EXTENSION (3.31) NOTE Refer to paragraph 4.39 for differenceswhen emergency gear extensionis being performed for training purposes.

  • Page 52: Issued: July

    SECTION PA-28R-2o1, ARROW EMERGENCY PROCEDURES 3.5n SPIN RECOVERY (3.33) Rudder FULL OPPOSITE DIRECTION ofROTATION Control Wheel FULL FORWARD WHILE NEUTRALIZING AILERONS Throttle Rudder NEUTRAL (when rotation stops) ControlWheel AS REQUIRED to SMOOTHJX REGAiN LEVEL FLIGHT ATrITUD 3.So OPEN DOOR (3.35) Ifboth upper and sidelatches are open, the door willtrail slightly open and airspeeds will be reduced slightly.

  • Page 53: Issued: July

    SECTION PA-28R-201, ARROW PROCEDURES EMERGENCY THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 3-10 Page: 3-10-(0) Issued: JULY 12, 1995 3-10...
  • Page 54 SECTION PROCEDURES PA-28R-201, ARROW EMERGENCY 3.7 AMPLIFIED EMERGENCY PROCEDURES (GENERAL) to supply additional are presented following paragraphs information for the purpose of providing the pilot with a more complete course of actionand probable cause of understanding of the recommended an emergency situation. FIRE DURING START 3.9 ENGINE...
  • Page 55 SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES TAKEOff 3.li ENGINE POWER LOSS DURING (35b) (continued) If engine failurewas caused by fuel exhaustion power will not be regained after switching fueltanks until the empty fuellinesare filled. This may require up toten seconds. If power isnot regained, proceed with the Power Off Landing procedure (refer t o the emergency checklist and paragraph 3.15).
  • Page 56 SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES 3.13 ENGINE POWER LOSSIN FlIGHT (3.Sc) (continued) If engine failurewas caused by fuel exhaustion power will not be restoredafter switching fueltanks untilthe empty fuellinesare filled. T his may requireup to tenseconds. If power isnot regained,proceed with the Power Off Landing procedure (refer to emergency checklist and paragraph 3.15).
  • Page 57 SICELON PA-28R-201, ARROW EMERGENCY PROCEDURES 3.15 POWER OFF LANDING (3Sd) (continued) 3.lSa Gear Down Emergency Landing (3.Sd) When committed to a gear down emergency landing, select landinggear DOWN. Flaps may be used as desired. Close the throttle control and move the mixture controlto idlecut-off.
  • Page 58 SECTION PA-28R.201, ARROW EMERGENCY PROCEDURES 3.17 FERE IN FIJGRT (3.5e) The presence of fireis noted through smoke, smell and heat in the cabin. It is essentialthat the source of the firebe promptly identified through instrument readings1 characterof the smoke, or other indicationssince the actionto be takendiffers s omewhat ineach case.
  • Page 59 SECTION PA-28R.201, ARROW EMERGENCY PROCEDURES 3.19 LOSS OF OIL PRESSURE (3.Sf) (continued) an off Depending on the circumstances, it may be advisable to make airport landing while power is still a vailable, p articularly if other indications of actualoil pressure loss, such as sudden increasesin temperatures, or oil smoke, are apparent, and an airport isnot close.
  • Page 60 SECTION PA-28R-201, ARROW EMERGENCY PROCEDURES 3.25 ELECTRICAL FAILURE (3.51) (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 electrical load is being suppliedby the battery.
  • Page 61 SECTION PA.28R-201, ARROW EMERGENCY PROCEDURES 3.29 PROPELLER OVERSPEED (3.5k) Propeller overspeed iscaused by a malfunction in the propeller governor or low oil pressure which allowsthe propeller bladestorotate tofull low pitch. If propeller overspeed should occur,retard the throttle and check the oil pressure.
  • Page 62 SECTION PA-28R-201, ARROW EMERGENCY PROCEDU1ES 3.33 SPIN RECOVERY (3.5n) Intentional spins are prohibited in this airplane. If a spin is inadvertently entered, immediately apply fullrudder opposite to the direction of rotation. Move the controlwheel fullforward while neutralizing the ailerons. Move the throttle t o IDLE.
  • Page 63 SECTION EMERGENCY PROCEDURES PA-28R-201, ARROW 3.37 ENGINE ROUGHNESS (3.5p) (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 64 SECTION PA-28R-201, ARROW SUPPLEMENTS TABLE CONTENTS SECTION NORMAL PROCEDURES Paragraph Page General Airspeeds forSafe Operations Normal Procedures Checklist Preflight Checklist (4.9) 4.5a 4.5b Before Starting Engine Checklist (4.11) 4.5c Engine Start Checklist (4.13) GENERAL ENGINE START NORMAL START COLD ENGINE (4.13a) ENGINE NORMAL...
  • Page 65 SECTION PA-28R-201, ARROW SUPPLEMENTS TABLE OF CONTENTS SECTION NORMAL PROCEDURES (cont) Paragraph Page 4 5h Takeoff Checklist (4 23) (continued SHORT FIELD, OBSTACLE CLEARANCE 4-11 TECHNIQUE (4.23b) FIELD TECHNIQUE 4-11 SOFT (4.23b) 4.5i Climb Checklist (4.25) 4-12 Cruise Checklist (4.27) 4-12 4.5j 4.5k...
  • Page 66 SECTION PA-28R-201, ARROW SUPPLEMENTS TABLE OF 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 Start When Flooded (4.5c) 4-19 4.13d Engine Start With ExternalPower Source (4.5c) 4-19 4.15 WARM-UP...
  • Page 67 SECTION PA-28R-201, ARROW SUPPLEMENTS TABLE OF CONTENTS SECTION NORMAL PROCEDURES (cont) Page Paragraph 4-27 4.39 LANDING GEAR 4-28 BALANCE 4.41 WEIGHT 4-28 4.43 LEVEL NOISE VB-1612 REPORT: 12, 1995 ISSUED: JULY 4-iv 12, 2010 REVISED: Page: 4-0-(4) Revision: 22, MAY 12, 2010 4-iv...
  • Page 68 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 operatingprocedures requiredby the FAA, as well as those procedures which have been determined as necessary for the operation of the airplane, as determined by the operating and designed featuresof the airplane, are presented.
  • Page 69 SECTION NORMAL PROCEDURES PA-28R-201, ARROW AIRSPEEDS SAFE OPERATIONS The following airspeeds are those which are significant to the safe operation of the airplane. These figures are for standard airplanes flown at grossweight under standardconditions at sea level. Performance for a specificairplane may vary from published figures depending upon the equipment installed, the condition of the engine, airplane and equipment, atmospheric conditionsand piloting technique.

  • Page 70: Figure

    SECTION PA-28R-201, ARROW 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 supportweight on the step. COCKPIT (4.9a) ControlWheel...
  • Page 71 SECTION NORMAL PROCEDURES PA-28R-201, ARROW 4.5a Preflight Checklist (4.9) (continued) COCKPIT (4.9a)(continued) check QUANTITY Fuel Gauges AnnunciatorPanel CHECK BATT MASTR Switch Primary Flight Controls PROPER OPERATION PROPER OPERATION Flaps NEUTRAL Trim Pitot and Static Systems DRAIN Windows check CLEAN check ON BOARD Required Papers and POH Tow Bar and Baggage STOW...
  • Page 72 SECTION PA-28R-201, ARROW NORMAL PROCEDURES 4.5a Preflight Checklist (continued) NOSE SECTION (4.9c) General Condition CHECK SECURE Cowling CHECK QUANTITY PROPERLY SEATED Dipstick OilFiller Cap SECURE Engine BaffleSeals CHECK Windshield CLEAN Propeller and Spinner CHECK CLEAR Air Inlets CHECK Alternator Belt TENSION CHECK Landing Light...
  • Page 73 SECTION PA-28R-201, ARROW NORMAL PROCEDURES 4.Sa Preflight Checklist (continued) LEFT WING (4.9d)(continued) Fuel Tank Sump DRAIN and CHECK for water,sediment, and proper fuel REMOVE Tie Down Pitot Mast REMOVE COVER HOLE CLEAR Wing Tip and Lights CHECK Aileron and Hinges CHECK Flap and Hinges CHECK...
  • Page 74 SECTION PA-28R-201, ARROW NORMAL PROCEDURES 4.5c Engine Start Checklist (4.13) ENGINE START GENERAL (4.13) CAUTION Do not attempt flight ifthere is no indicationof 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 75 SECTION NORMAL PROCEDURES PA-28R-201, ARROW 4.5c Engine Start Checklist (4.13)(continued) NORMAL START ENGINE (4.13b) Throttle 1/2 INCH OPEN ALTR Switch BAIT MASTR Switch Electric Fuel Pump Mixture IDLE CUT-OFF CLEAR Propeller Starter ENGAGE Mixture ADVANCE ADJUST Throttle Oil Pressure CHECK ENGINE START WHEN...
  • Page 76 SECTION PA-28R-201, ARROW 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 77: Flight Instruments

    SECTION NORMAL PROCEDURES PA-28R-201, ARROW 4.5f Ground Check Checklist (4.19)(continued) GROUND CHECK (4.19)(continued) CHECK Magnetos max. drop 175 RPM -max.diff.50 RPM 4.8 to 5.1 inches Hg Vacuum Oil Temperature CHECK Oil Pressure CHECK CHECK Ammeter Annunciator Panel PRESS-TO-TEST EXERCISE then Propeller FULL INCREASE...
  • Page 78 SECTION PA-28R-201, ARROW NORMAL PROCEDURES 4.5h Takeoff Checklist (4.23) NORMAL (4.23a) TECHNIQUE Flaps Trim Accelerateto 65 to 75 KIAS. Control Wheel back pressure to ROTATE smoothly toCLIMB ATI’ITLJDE SHORT CLEARANCE OBSTACLE FIELD, (4.23b) TECHNIQUE 25° (second notch) Flaps Accelerateto 50 to 60 KIAS depending on aircraft weight. ControlWheel back pressure to ROTATE to CLIMB...
  • Page 79 SECTION NORMAL PROCEDURES PA-28R-201, ARROW 4.51 Climb Checklist (4.25) CLIMB (4.25) Best Rate (2750 lb.) (Gear Flaps Up) 9OKIAS 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, 72 KIAS Flaps Up) En Route...
  • Page 80 SECTION PA-28R-201, ARROW NORMAL PROCEDURES 4.5m 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 Electric Fuel Pump Air Conditioner Avionics Electrical S witches...
  • Page 81 SECTION NORMAL PROCEDURES .PA-28R-201, ARROW THIS PAGE INTENTIONALLY LEFT BLANI( ISSUED: JULY VB-1612 12,1995 REPORT: Page: 4-14-(0) Issued: JULY 12, 1995 4-14...
  • Page 82 SECTION PA-28R-201, ARROW NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES (GENERAL) The following paragraphs are provided to supply detailedinformation and explanations of the normal procedures necessary for the safe operation of the airplane. PREFLIGHT CHECK (4.Sa) The airplane should be given a thorough preflight and walk-around check.
  • Page 83 SECTION PA-28R-201, ARROW NORMAL PROCEDURES PREFLIGHT CHECK (4.5a)(continued) 4.9b Right Wing (4.Sa) (continued) Open the fuel cap and visually check the fuelcolor. The quantity should match theindication t hat was on the fuel quantity gauge. Replace cap securely. The fueltank ventshould be clear of obstructions. CAUTION drainingany amount of fuel, care should When...
  • Page 84 SECTION PA.28R-201, ARROW NORMAL PROCEDURES PREFLIGHT CHECK (4.Sa)(continued) 4.9c Nose Section (4.Sa)(continued) CAUTION When draining any amount of fuel, care should be taken to ensure that no fire hazard exists before starting engine. Open the fuel strainer l ocated on the left side of the firewall long enough to remove any accumulation of water and sediment.
  • Page 85 SECTION PA-28R-201, ARROW NORMAL PROCEDURES PREFLIGHT CHECK (4.5a)(continued) 4.9e Fuselage (4.5a)(continued) Upon returning to the cockpit, an operational check of the interior lights, 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 Visually confirm thatexterior lights are operational.
  • Page 86 SECTION PA-28R-201, ARROW NORMAL PROCEDURES 4.10 ENGINE START GENERAL CAUTION: Do not attempt flight ifthereisno indication of alternator output. CAUTION: If a positive oil pressure is not indicated within 30 seconds following an engine start, s top the engine and determine the trouble.
  • Page 87 SECTION NORMAL PROCEDURES PA-28R-201, ARROW LEFT BLANK THIS PAGE INTENTIONALLY 12, 1995 ISSUED: JULY VB-1612 REPORT: 12, 2010 REVISED: 4-18b Page: 4-18-(2) Revision: 22, MAY 12, 2010 4-18b...
  • Page 88 Check the oil pressure. 4.13d Engine Start With External Power Source (4.5c) An 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 b attery.
  • Page 89 SECTION NORMAL PROCEDURES PA-28R-201, ARROW 4.13 ENGINE START (4.5c) (continued) 4.13d Engine Start With External Power Source (4.5c) (continued) NOTE using the PEP For all normal operations master cables, battery jumper alternator switches should be OFF. When the engine is firing evenly, advance the throttle t o 800 rpm. If oil pressure is not indicatedwithin thirty seconds, stop the engine and determine the trouble.In cold weather, it will take a few seconds longer to get an oil pressure indication.
  • Page 90 SECTION PA-28R-201, ARROW NORMAL PROCEDURES 4.17 TAXIING (4.5e) (continued) Observe wing clearances when taxiing near buildings or other stationary objects. I f possible, s tation an observeroutsidethe airplane. Avoid holes and rutswhen taxiing over uneven ground. Do not operate the engine at high rpm when running up or taxiing over ground containing loose stones, gravel or any loose materialthat may cause damage to the propeller blades;...
  • Page 91 SECTION PA-28R-201, ARROW NORMAL PROCEDURES 4.21 BEFORE TAKEOFF (4.Sg) After all aspects of the takeoffare considered, a before takeoffcheck procedure must be performed. Verify thatthe battery master and alternator s witches areON. Check and setallof the night instrumentsas required. Check the fuelselector to make sureitison the proper tank (fullest).
  • Page 92 • SECTION PA-28R-201, ARROW NORMAL PROCEDURES 4.25 CLIMB (4.51) On climb-out after takeoff, itis recommended thatthe best angle of climb speed (78 KIAS) be maintained only if obstacle clearance is a consideration. T he best rateof climb speed (90 KIAS) should be maintained with full power on the engine until adequate terrain clearanceisobtained.At lighter than gross weight these speeds are reduced somewhat.
  • Page 93 SECTION PA-28R-201, ARROW PROCEDURES NORMAL 4.27 CRUISE (4.53) (Continued) To lean the mixture, disengage the lock and pull the mixture control untilthe engine becomes rough, indicating that the lean mixture limithas been reached in the leaner cylinders. Then enrichthe mixture by pushing the control towards the instrument panel until engine operation becomes smooth.
  • Page 94 SEC[[ON PA-28R-201, ARROW NORMAL PROCEDURES 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 fastenedand the inertia r eel checked. Turn ON the electhc fuel pump.
  • Page 95 SECTION PA-28R-201, ARROW NORMAL PROCEDURES 4.31 STOPPING ENGINE (4.Sni) (continued) air conditioner, radios, and all electrical The electnc fuel pump, Set the propeller in the fulliNCREASE switches should be turned OFR position.Stop the engine by disengaging the mixture control lock and pulling the mixture controlback to idlecutoff.
  • Page 96 SECTION PA-28R.201, ARROW NORMAL PROCEDURES 4.37 TURBULENT AIR OPERATION In keeping with good operating practice used in all aircraft, it is recommended that when turbulent air is encountered or expected, the airspeed be reduced to maneuvering speed to reduce the structural loads caused by gusts and to allow for inadvertent speed build-ups which may occur as a result of theturbulenceor of distractions caused by the conditions.
  • Page 97 SECTION PA-28R-201, ARROW NORMAL PROCEDURES BALANCE 4.41 WEIGHT Itis the responsibility of the owner and pilot to determine that the airplane remains within the allowable weight vs. centerof gravityenvelope while in flight. For weight and balance data, refertoSection6 (Weight and Balance). 4.43 NOISE LEVEL The noise levelof thisaircraft i s75.5 d B(A).

  • Page 98: Introduction

    SECTIONS PA-28R-201, ARROW PERFORMANCE TABLE OF CONTENTS SECTION PERFORMANCE Page Paragraph General Introduction toPerformance and FlightPlanning Flight Planning Example Performance Graphs List of Figures VB-1612 REPORT: 12, 1995 JULY ISSUED: Page: 5-0-(1) Issued: JULY 12, 1995...
  • Page 99 SECTION PA-28R-2O1, ARROW PERFORMANCE THIS PAGE INTENTIONALLY LEFt’ BLANK REPORT VB-1612 ISSUED: JULY 12, 1995 Page: 5-0-(2) Issued: JULY 12, 1995 5-ii...
  • Page 100 SECTION PA-28R-201, ARROW PERFORMANCE SECTION PERFORMANCE 5.1 GENERAL All of the required (FAA regulations) and complementay performance information is provided by thissection. Performance information associated with those optional systems and equipment which require handbook supplements is provided by Section 9 (Supplements).
  • Page 101 PA-28R-201, ARROW PERFORMANCE LEFT THIS PAGE INTENTIONALLY BLANK REPORT VB-1612 ISSUED: JULY 12, 1995 Page: 5-2-(0) Issued: JULY 12, 1995...
  • Page 102 SECTION PA-28R-201, ARROW PERFORMANCE 5.5FLIGHT PLANNING EXAMPLE (a) Aircraft Loading The first step in planning the flight is to calculate the airplane weight and center of gravityby utilizing t he information provided by Section 6 (Weight and Balance) of this handbook. The basic empty weight for the airplane as licensedat the factory has been entered in Figure 6-5.
  • Page 103 SECTION PA-28R-201, ARROW PERFORMANCE 5.5 FLIGHT PLANNING EXAMPLE (continued) (b) Takeoffand Landing that the airplane loading has been determined, aspects of the takeoffand landing must now be considered. All of the existing conditionsat the departure and destination airport must be acquired, evaluated and maintained throughout the flight.
  • Page 104 SECTIONS PA-28R-201, ARROW PERFORMANCE 5.5 FLIGHT PLANMNG EXAMPLE (continued) (c) Climb The next step in the flightplan is to determine the necessary climb segment components. The desired cruise pressure altitude and corresponding cruise outside air temperature values are the first variables to be considered considered in determining climb components from the Fuel, Time and Distance to Climb graph (Figure 5-21).
  • Page 105 SECTION PA-28R-201, ARROW PERFORMANCE 5.5 FLIGHT PLANNING EXAMPLE (conthiued) values from the graph (Figure 5-35). Subtract the values obtained obtained from the field conditionsfrom the valuesobtained from the cruise conditions to find the true fuel, time and distancesvalues needed forthe ifight p lan. The values obtained by proper utilization o the graphs for the descent segment of the example areshown below: (1) Fuel toDescend...
  • Page 106 SECTION PA-28R-201, ARROW PERFORMANCE 5.5 FLIGHT PLANNING EXAMPLE (continued) (3) CruisePower (Best Economy) 65% rated power (2500 RPM) 7°C (4) CruiseDeltaOATfromlSA(10°C-3°C) 23.3 in Hg (5) CruiseManifold Press. (23.1 [7/5.5 x .16]) 130 Kts TAS* (6) Cruise Speed 10.3 gph* (7) CruiseFuel Consumption (8) CruiseTime (e)(2) divided by (e)(6), ( 108.5 naut.
  • Page 107 SECTIONS PA-28R-201, ARROW PERFORMANCE rars PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 Page: 5-8-(0) Issued: JULY 12, 1995...
  • Page 108 SECTION PA-28R-201, ARROW PERFORMANCE 5.7 PERFORMANCE 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 TakeoffPerformance Over 50 Foot Barrier 5-15 Flap TakeoffGround Roll 5-16...
  • Page 109 SECTIONS PA-28R-201, ARROW PERFORMANCE GRAPHS 5.7 PERFORMANCE (Cont’d) LIST OF FIGURES (Cont’d) 5-27 5-29 Best PowerRange (2500 RPM) 5-27a 5-29aBest PowerRange (2200 RPM) 5-27b 5-31 Best Economy Range (2200RPM) 5-28 5-3laBest Economy Range (2500RPM) 5-29 5-33 Best Power Endurance (2500 RPM) 5-29a 5-33aBest Power Endurance (2200 RPM) 5-29b...
  • Page 110 SECTION PA-28R-201, ARROW PERFORMANCE Example: Example: 16000 Altitude: 6000 ft. @ 6000 FT: ISA + 100 C ISA temperature: 3°C 14000 12000 *1f1L 10000 8000 6000 -‘ 4000 2000 S.L. AIR TEMPERATURE ABOVE & BELOW AIR TEMPERATURES Figure 5-la REPORT: VB-1612 ISSUED: JULY...
  • Page 111 tUIIU1N PA-28R-201, ARROW PERFORMANCE TEIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 5-lob Page: 5-10-(2) Issued: JULY 12, 1995 5-10b...

  • Page 112: Temperature Conversion

    SECTION PA-28R-201, ARROW PERFORMANCE • ______ CELSIUS FAHRENHEIT DEGREES DEGREES •1O ____ CONVERSION TEMPERATURE Figure 5-1 VB-1612 REPORT: 12, 1995 ISSUED: JULY Page: 5-11-(0) Issued: JULY 12, 1995 5-11...

  • Page 113: Airspeed System Calibration

    SECTIONS PA-28R-201, ARROW PERFORMANCE Q7WIU COO______ S1ON GJ3dWV G.LVOflV AIRSPEED SYSTEM CALIBRATION Figure 5-3 REPORT: VB-1612 ISSUED: 12, 1995 JULY 5-12 Page: 5-12-(0) Issued: JULY 12, 1995 5-12...

  • Page 114: Power Off Stall Speed Vs. Angle Of Bank

    SECTIONS PA-28R-201, ARROW PERFORMANCE <Ci) cooIw H-LuuJ41114 Zjj114 .rrrrl 033dS TIVJ.S OF BANK VS. ANGLE STALL SPEED POWER Figure VB-1612 REPORT: 12, 1995 ISSUED: JULY 5-13 Page: 5-13-(0) Issued: JULY 12, 1995 5-13...

  • Page 115: Wind Components

    SECTION PERFORMANCE PA-28R-201, ARROW WIND COMPONENTS Example: Wind velocity: 30 knots Angle between flight p ath and wind: 30° Headwind component: 26 knots Crosswind components: 15 knots •..I 1..-.- .,I, FliGHT AND WIND ANGLE BETWEEN DEGREES i’I1’iji 1Iii t:1:tT:r*t: :ii: ‘F ::::::::: 41#!I1...
  • Page 116 SECTION PA-28R-201, ARROW PERFORMANCE NV.LSIC O3w.L ° < < I—cl) iIIiI r*141 _______ _____ > —4.A ‘H _____ ‘ 1IV!11i1i1Ii ,fFr ______ PERFORMANCE TAKEOFF 25° FLAP Figure 5-9 VB-1612 REPORT: 12, 1995 ISSUED: JULY Page: 5-15-(0) Issued: JULY 12, 1995 5-15...
  • Page 117 _L1Ui PA-28R-201, ARROW PERFORMANCE J.I 11OH ONflOO O)IV.L ________ ONIM ONZ Nfl 3 — FLAP TAKEOFF GROUND ROLL Figure5-11 REPORT: VB-1612 ISSUED: JULY 12, 1995 5-16 Page: 5-16-(0) Issued: JULY 12, 1995 5-16...
  • Page 118 SECTIONS PA-28R-2O1, ARROW PERFORMANCE .14 NLSIO ilO34V § WLI.O1” SS1 C,.LZ PERFORMANCE TAKEOFF 00 FLAP Figure 5-13 REPORTS VB-1Ø1Z 12, 1995 JULY ISSUETh Page: 5-17-(0) Issued: JULY 12, 1995 5-17...
  • Page 119 SECTIONS PA-28R-201, ARROW PERFORMANCE fl014 CNflO dO3)(VL --I-1-,-rr +,÷1 — ‘U ‘U (nfj< 0> ‘U cIo. > ‘U FLAP T4KEOFT GROUND ROLL 5-15 Figure REPORT: VB-1612 ISSUED: JULY 12, 1995 5-18 Page: 5-18-(0) Issued: JULY 12, 1995 5-18...
  • Page 120 ARROW PA-28R2O1, PERFORMA1’4CE WUJW 14:t: tIIto_J tIIto_J UP CLIMB PERFORMANCE GEAR Figure 5-17 REPORT: ‘1B-1612 12, 1995 JULY ISSUED: : in Page: 5-19-(0) Issued: JULY 12, 1995 5-19...

  • Page 121: Gear Down Climb Performance

    SECTION PA-28R-201, ARROW PERFORMANCE < XQOø ..tjW %Cl) ‘- GEAR DOWN CLIMB PERFORMANCE Figure 5-19 REPORT: VB-1612 ISSUED: JULY 12,1995 5-20 Page: 5-20-(0) Issued: JULY 12, 1995 5-20...

  • Page 122: Fuel, Time And Distanceto Climb

    SECTION PA-28R-201, ARROW PERFORMANCE tHit-ittltH rrriIT rn-I rrni I C) I— rl—,—,1?,—,—1It,rr,—tlrrt-11 f%_6 ° LU co 1— TO CLIMB DISTANCE TIME FUEL, Figure 5-21 VB4612 REPORT: 12, 1995 ISSUED: JULY Page: 5-21-(0) Issued: JULY 12, 1995 5-21...
  • Page 123 SECTIONS PA-28R-201, ARROW PERFORMANCE LEFT THIS PAGE INTENTIONALLY BLANK REPORT: VB-I12 ISSUED: JULY 12, 1995 5.22 Page: 5-22-(0) Issued: JULY 12, 1995 5-22...

  • Page 124: Power Setting Table (Bestpower)

    SECTION PA-28R-201, ARROW PERFORMANCE 0w-. ‘Cu POWER SETTING TABLE (BestPower) Figure 5-23 ISSUED: 12, 1995 REPORT: VB-1612 JULY r ‘v Page: 5-23-(0) Issued: JULY 12, 1995 5-23...
  • Page 125 SECTIONS PA-28R-201, ARROW PERFORMANCE CCuCu > 0’- ‘Ii — Cu Cu POWER SETTING TABLE (Best Economy) Figure 5-23a REPORT: VB-1612 ISSUED: JULY 12,1995 5-24 Page: 5-24-(0) Issued: JULY 12, 1995 5-24...
  • Page 126 SECTION ARROW ‘—IPA-28R-201, PERFORMANCE ‘-‘ 0 ‘0 ‘—IPA-28R-201, 000000000000 133d 3OflJJJIV 3èJflSS3Nd BEST POWER CRUISE (75% Power) Figure 5-25 ISSUED: JULY REPORT: VB-1612 12,1995 Page: 5-25-(0) Issued: JULY 12, 1995 5.25...
  • Page 127 SECTIONS PERFORMANCE PA-28R-201, ARROW LZJ0 CD Ui c4 1Ucf. ø.o_ 0000000000 0000000000 0000000000 !33d-aaftLLflv3Nnss3eJd BEST POWER CRUISE(65% Power) Figure 5-25a REPORT: VB-1612 ISSUED: JULY 12, 1995 5.2Sa Page: 5-25-(1) Issued: JULY 12, 1995 5.25a...
  • Page 128 SECTION PA-28R-201, ARROW PERFORMANCE ‘0 ‘-0 0•’ 000000000000 00000000000CI) 133d 3Cfl!LIIV 3flSS3d BEST POWER CRUISE (55% Power) Figure 5-25b ISSUED: JULY REPORT: VB-1612 12,1995 Page: 5-25-(2) Issued: JULY 12, 1995 5.25b...
  • Page 129 SECTION PA-28R-201, ARROW PERFORMANCE wc’ %UJI ‘0-I >- ooo.oooooeoooj 0’O (‘9 aniinv 133d 3NflSS3Id (55% Power 2200 RPM) ECONOMY CRUISE 5-27 Figure REPORT: VB-1612 ISSUED: JULY 12, 1995 5-26 Page: 5-26-(0) Issued: JULY 12, 1995 5-26...
  • Page 130 SECTION PA-28R-201, ARROW PERFORMANCE C’) C’) (55% Power 2500 RPM) CRUISE ECONOMY Figure 5.27a VB-1612 REPORT: 12, 1995 JULY ISSUED: S-26a Page: 5-26-(1) Issued: JULY 12, 1995 5-26a...
  • Page 131 SECTIONS PA-28R-201, ARROW PERFORMANCE WC%4 Oøo rb’ ZLUCD 133d 3GflJJJ.1V 3èflSS3d ECONOMY CRUISE (65% Power 2200 RPM) 5-27b Figure REPORT: VB-1612 ISSUED: JULY 12, 1995 5-26b Page: 5-26-(2) Issued: JULY 12, 1995 5-26b...
  • Page 132 SECTION PA-28R-201, ARROW PERFORMANCE +4-4--4-4444-4--l-F-4l L)CI) (‘41- ‘0 4444-4-4- 4 ’1 C’4W ‘-aC ‘-aC >- ‘S (DOo ‘—I0 ØQ) .-a) zo-. ‘—I0 n-I-pä5 n-I-pä5 -Dwd) p222 OOC.) (‘5 ‘D 3GflhILlY 3NflSS3Nd ECONOMY CRUISE (65% Power 2500 RPM) Figure 5-27c 12, 1995 REPORT: VB-1612 ISSUED:...
  • Page 133 PA-28R-201, ARROW PERFORMANCE THIS PAGE INTENTIONALLY LEIT BLANK REPORT: VB-1612 ISSUED: JULY 12,1995 5.26d Page: 5-26-(4) Issued: JULY 12, 1995 5-26d...
  • Page 134 SECTIONS PA.28R.201, ARROW PERFORMANCE 0>’ ‘I — I-.0 UI o .-J. 0< < DC!) 0000000000 C’1 C’) i’- ‘0 9OftLIJIY NflSS9Nd RANGE POWER (2500 RPM) BEST Figure 5-29 VB-1612 REPORT: 12, 1995 ISSUED: JULY c.2’7 Page: 5-27-(0) Issued: JULY 12, 1995 5-27...
  • Page 135 SECTION PA-28R-201, ARROW PERFORMANCE ø 0’ .r-.6< 3anJJ.L,V 3flSSd • BEST POWER RAGE (2200 RPM) Figu±e 5-29a REPORT: VB-1612 ISSUED: JULY 12, 1995 5-27a Page: 5-27-(1) Issued: JULY 12, 1995 5-27a...
  • Page 136 SECTION PA-28R-201, ARROW PERFORMANCE Ø C’0 C’0 • 0080 C’4 C’- ]an.wiv 3 flSS1cI ECONOMY RANGE BEST (2200 RPM) Figure 5-31 REPORT: VB-1612 ISSUED: JULY 12,1995 5-2Th Page: 5-27-(2) Issued: JULY 12, 1995 5-27b...
  • Page 137 SECTION PA-28R-201, ARROW PERFORMANCE ‘Is’’’’ IIIII!III ‘‘I’ll’’ till II I •0 IIII 11iHii lililiti 111111 liii 111111 1i1ITt1fl F11i14..[I I III iuiiirl Iii’ li+1141Ji 11111 liii I II 11111111111111111 IccI) IccI) I III ‘‘—‘II111f..11iI1IlIlliIliIIlIi ilii (flcu [[[U1Ii >- lIiTh+U1iHIIlI l ilt liii .Tii4ti flttfl1t1t1trl IFillil...
  • Page 138 SECTIONS PERFORMANCE PA-28R-201, ARROW I— IflZ Oflh1J.W 2flSSNd ENDURANCE (2500 RPM) BEST POWER Figure 5-33 REPORT: VB-1612 12, 1995 ISSUED: JULY 5-29 Page: 5-29-(0) Issued: JULY 12, 1995 5-29...
  • Page 139 SECTION PA-28R-201, ARROW PERFORMANCE II Ill Ill Ill II 1111111111111 ‘U 111111 N1Je Liii iiiIl ‘‘‘‘I’ll’ I1III1iI I’I’l ‘lilt Iii l iii § U.LLIflI! tnl I •Ii WI l C4 <(fl ‘I OIø1 IIII ‘‘I It’ll ______ ImlllIlHlln’ ‘C VIfttffhfff •...
  • Page 140 SECTION PA-28R-201, ARROW PERFORMANCE iI1(HhII iI1(HhII I lii 11111W ____ ir4U 1111 _flUiILWUIWUJJ llIIiiii .iIIFI uwtz fflhiEtU1 IIIII[1fIIIIIIIIIIIIIII g’h. llI1PI is-I IiiIFHhI1li..UW’PU It! liii IiLIII ji4.4 EEII III I 1)11 1111 nriiii’ c4-4-44 eset:111 .l11I 0_c_ u-& ‘-1 1111 a LU •az a B EU E U 5 3 •a...
  • Page 141 SECTION PA-28R-201, ARROW PERFORMANCE F.---’ I.•0 I.•0 I— ø aflhLL1v NflSS]d BEST ECONOMY ENDURANCE (2500 RPM) Figure 5-33c REPORT: VB-1612 ISSUED: JULY 12, 1995 5-29c Page: 5-29-(3) Issued: JULY 12, 1995 5-29c...
  • Page 142 SCT1ON PA-28R-201, ARROW PERFORMANCE LEFT BLANK ThIS PAGE INTENTIONALLY REPORT: VB-J,612 12,1995 ISSUED: JULY Page: 5-29-(4) Issued: JULY 12, 1995 5-29d...
  • Page 143 SECTION PERFORMANCE PA-28R-201, ARROW llll ZeII :zih I—uj ‘ w< Jltt [Th±H TIME DISTANCE FUEL, TO DESCEND Figure 5-35 REPORT: VB-1612 ISSUED: JULY 12, 1995 5-30 Page: 5-30-(0) Issued: JULY 12, 1995 5-30...
  • Page 144 SECTION PA-28R-201, ARR PERFORMANCE irSb <0 — ——a. ‘4. AN]) DISTANCE TIME GLIDE Figure 5-37 REPORT: VB-1612 12, 1995 ISSUED: JULY Page: 5-31-(0) Issued: JULY 12, 1995 5-31...
  • Page 145 SECTIONS PA-28R-201, ARROW PERFORMANCE 3ONVISK3 DNtONV1 444-4 Ifi-f+f4 4+H > ElOgL’ r.< LANDING DISTANCE OVER 50 FOOT BARRIER Figure 5-39 REPORT: VB4612 ISSUED: JULY 12,1995 5-32 Page: 5-32-(0) Issued: JULY 12, 1995 5-32...
  • Page 146 SECTIONS PA-28R-201, ARROW PERFORMANCE TIOU GNflOID DNIaNV1 u’ flttl:t ri-li rrr, 0” ____o __(Li. -II b ROLL DISTANCE GROUND LANDING Figure 5-41 VB-1612 REPORT: 12, 1995 ISSUED: JULY Page: 5-33-(0) Issued: JULY 12, 1995 5-33...
  • Page 147 SECTEON PA-28R-201, ARROW PERFORMANCE THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12, 1.995 5-34 Page: 5-34-(0) Issued: JULY 12, 1995 5-34...
  • Page 148 SECTION PA-28R-201, ARROW WEIGifF BALANCE TABLE OF CONTENTS. SECTION WEIGHT BALANCE Paragraph Page General AirplaneWeighing Procedure Weight and Balance Data and Record Weight and Balance Detenninationfor Flight Supplied with Equipment List (Form 240-0129) aircraft paperwork REPORT: VB-1612 12, 1995 ISSUED: JULY Page: 6-0-(1) Issued: JULY 12, 1995...
  • Page 149 SECTION PA-28R-201, ARROW WEIGHT BALANCE THIS PAGE LEFT INTENTIONALLY BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 6.11 Page: 6-0-(2) Issued: JULY 12, 1995 6-ii...
  • Page 150 SECTION PA-28R-201, ARROW WEIGHT AN]) BALANCE SECTION WEIGHT BALANCE 6.1 GENERAL In order to achieve the performance and flying characteristics which are designed into the airplane, it must be flown with the weight and centerof gravity (C.G.) position within the approved operating range (envelope). Although the airplane offersa tremendous flexibility of loading, itcannot be flown with the maximum number of adult passengers, fullfuel tanks and...
  • Page 151 C.G. 6.3 AIRPLANE WEIGHING PROCEDURE At the time of licensing, Piper provides each airplane with the basic empty weight and centerof gravity location. This data is suppliedby Figure 6-5. The removal or addition of equipment or airplane modifications can affectthe basic empty weight and center of gravity. The following is a...
  • Page 152 SECTION PA-28R-201, ARROW WEIGHT BALANCE 6.3 AIRPLANE WEIGHING PROCEDURE (continued) CAUTION Whenever the fuel system is completely drained and fuelis replenished it will be necessary to run the engines fora minimum of 3 minutes at 1000 rpm on each tank to insureno air exists in the fuel supply lines.
  • Page 153 SECTION PA-28R-201, ARROW WEIGHT BALANCE 63 AIRPLANE WEIGHING PROCEDURE (continued) Scale Tare Scale Position and Symbol Reading Weight Nose Wheel Right Main Wheel LeftMain Wheel Basic Empty Weight, as Weighed (‘I) WEIGHING FORM Figure 6-1 Cd) Basic Empty Weight Center of Gravity (1) The following applies to the PA-28R-201 geometry...
  • Page 154 SECTION PA-28R-201, ARROW WEIGHT BALANCE 6.3 AIRPLANE WEIGHING PROCEDURE (continued) (2) The basic empty weight center of gravity (as weighed including optional equipment, fulloil and unusable fuel) can be detennined by the following formula: C.G Ann N (A) L) (B) inches Where: T=N+R+L...
  • Page 155 SECTION PA-28R-201, ARROW WEIGHT BALANCE BALANCE DATA RECORD 6.5 WEIGHT (continued) PA-28R-201 ARROW MODEL 2844120 Airplane Serial Number 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* Computcd...
  • Page 156 Figwe Page: 6-7-(0) Issued: JUNE 5, 2009...
  • Page 157 SECTION WEIGHT P ND BALANCE PA-28R-201, ARROW 6.5 WEIGHT BALANCE DATA RECORD (continued) £b (-) P”I (+) poppy <c uI1I WEIGHT BALANCE RECORD (cont) Figure 6-7 (cont) REPORT: VB-1612 ISSUED: JULY 12, 1995 Page: 6-8-(0) Issued: JULY 12, 1995...
  • Page 158 SECTION PA-28R-201, ARROW WEIGHT BALANCE 6.7 WEIGHT BALANCE DETERMINATION FLIGHT (a) Add the weight of all items tobe loadedto the basic empty weight. (b) Use the Loading Graph (Figure 6-13) to determine the moment all items tobe carried in the airplane. (c) Add the moment of all items to be loaded to the basic empty weight moment.
  • Page 159 SECTION ARROW WEIGHT BALANCE PA..28R-201, FLIGHT WEIGHT BALANCE DETERMINATION (continued) ArmAft Moment Datum Weight (Lbs) (Inches) (In-Lbs) Basic Empty Weighi Pilot and Front Passenger 80.5 118.1 Passengers (Rear Seats) Fuel (72 Gallons Maximum) 95.0 Baggage (200 Lbs. Maximum) 142.8 Ramp Weight (2758 Lbs. Maximum) Fuel Allowance For Engine Start, T axi, and Run-Up...
  • Page 160 SECTION PA-28R-201, ARROW WEIGHT BALANCE 6.7 WEIGHT BALANCE DETERMINATION FLIGHT (continued) IS’ MQMENT/0OO (INCN. POUNDS) GRAPH LOADING Figure 6-13 VB-1612 REPORT 12, 1995 ISSUED: JULY _1 I Page: 6-11-(0) Issued: JULY 12, 1995 6-11...
  • Page 161 SECTION PA-28R-201, ARROW WEIGHT BALANCE 6.7 WEIGHT FLIGHT BALANCE DETERMINATION (continued) 3000 P.S. 88.9 2800 wirr 2400 234LU 2000 1800 1600 1400 INCHES AFT OF DATUM C. G RANGE WEIGHT Figure 6-15 REPORT: VB4612 ISSUED: JULY 12, 1995 Page: 6-12-(0) Issued: JULY 12, 1995 6-12...
  • Page 162 19.35 b.) Telex Holder 64022-000 and Hardware, Piper drawing 79036-024 0.03 74.13 2.34 Pilot’s H eadset, Piper drawing 79036-024 a.) Telex 5161A Airman 760 Headset, Piper code number 692-205 16.34 0.20 80.5 (d) Miscellaneous Fire Extinguisher installation, Piper drawing 8223 5-2 a.) Saber part number 1211-1301 Halon Model RTA600,...
  • Page 163 PipEr PIPER PA-28R-201, ARROW AIRCRAFT, LIST EQUIPMENT SIN 2844116 and UP Item Arm (In.) Moment Weight Item Aft Datum (Pounds) (Lb-In.) (d) Miscellaneous-continued Tow Bar, Piperdrawing 67336-0 343.20 2.20 156.00 OF STANDARD EQUIPMENT ISSUED: 02/27/04 240-0129 Page: 6-13-(2) Issued: DECEMBER 10, 2004...
  • Page 164 S-TEC System 55X Autopilot with Compass STS-180/HSI, Piper drawing 104581-002 or 104581-005, (Marketing Option 594— requiresMarketing Option 595) a.) S-TEC Turn Coordinator, Partnumber 6405-14L 1.62 60.4 97.546 b.) Turn Coordinator hardware, Piper drawing 10458 1-002 or 10458 1-005 0.01 62.99 0.89 c.) S-TEC Programmer/Computer, Partnumber 01192-1 -46TP 2.700 58.20...
  • Page 165 104581-002 or 104581-005 60.92 Removed Standard Directional Gyro, Sigma -Tek, Partnumber Ilj262-001-37, 59 75 -148 ‘7 Piper PS 50126-5, Piper code number 548-435, Cert.Basis TSC> C5c Removed Standard Turn Coordinator, Piper PS50030-3-5, Piper code number 1 04 59 70 548-190 Delta System weight 36.12...
  • Page 166 Antenna, Piper code number 45 1-802 0.40 264.90 105.96 1.11 180.39 200.15 a.) Nay Antenna Cable assembly and hardware, Piper drawing 104253-003 0.19 54.94 10.47 2.) Comant Cl-i 125 Antenna Coupler, Piper code number 556-753 3.) VHF Comm #1 Comant CI-121 Antenna, Piper PS50040-18-2, Piper code...
  • Page 167 Antenna installations, Navigation, VHF Cornms #1 and 2, Marker beacon and GPS #1 and 2,Piper drawing 104253-003-continued Comm #2 Antenna Cable assembly and hardware, Piper drawing 104253- 84.18 71.98 5.) Marker Beacon Antenna installation, Piper drawing 104253-003 a.) Marker Beacon Antenna Comant CI-102, PiperPS50040-15-l0, Piper code...
  • Page 168 0.10 60.94 104 06 .594 iiu S.nsor rt nbrnoer 644o per code ianbei o2-164 iS-ThC 5.) S-TEC Hardware installation kit, Part number 90480-1, Piper code number 37 13 0 63 58 94 652-164 5.37 124.32 666.98 &) Harnesses, Brackets and Hardware, Piper drawing 104.253-003...
  • Page 169 050-2020-02. Flux mounting brackets, Gyro leveling bracket,hardware,Piper drawing 87455-003. Piper code number 0.68 173.42 18 46 599-232 6.) Harnesses, Brackets and Hardware, Piper drawings CA-28-2-206 and 87455- 4.27 118.22 504.34 Removed Standard Directional Gyro, Sigma -Tek, Partnumber IU 262-001-37, -2.48...
  • Page 170 (11-33 Vdc) #2 with mount, connectorsand data card, 58 14 381 18 Piper PS50040-40-4, Piper code number 60 1-229 61.43 3.) Garmin GI-106A Indicator #1, Piper code number 602-239 1.02 60.23 4.) Garmin GI-106A Indicator #2, Piper code number 602-239 1.02 60.23...
  • Page 171 S-TEC Trim Servo installation kit-Hardware.Pertnumber 9O4O3-, Piper 0.93 15.27 147 70 code number 65 1-658 e. S-TiC Trim Switch and Cable installation kit, Partnumber 90403-2, Piper Q0.9(’ 0.88 102.73 code number 651-657 f. S-TEC Monitor/Sonalertinstallation kit Hardware, Part number 90403-3,...
  • Page 172 Page: 6-13-(11) Issued: DECEMBER 10, 2004 240-0129 11 of 17...
  • Page 173 4.13 3.) Marker Beacou Antenna Comant, Partnumber CI-102, Piper drawing 0.45 217.17 101901-102, Piper PS50040- 15-10,Paper code number 597-893 4.) Marker Beacon antenna cable and hardware Piper dra.wig 1O19ii. 102 10:. dyne 1Znteg a Pramdry Flight Displa” LXP Pipaa drawin 101901-103 Entegrn Paimary FlightDisplay FXP S000.Aviciye part ounher...
  • Page 174 Aft Datum (Pounds) (Lb-In.) Option Installed (h) Avidyne Entegra Avionics (Optional Equipment) Standard Entegra Avionics Package, Piper drawings 101901-003, 101901-100, 101901-101, 101901-102, 101901-103, 101901-104, 101901-109, and 101901- 111, and 101901-115 (Marketingoption AVI)-continued m.) Standby Flight instruments installation, Piper drawings 38453-007-continued 3.) Standby attitude Indicator with battery pack option, Mid-Continent Part...
  • Page 175 61.28 Deltasystemweight Garrn G1-106A System installation, Piper drawing 101901-101. Aidyne Entegra system (only),(Marketing option 225) a.) Girmin G1-106A Indicator, P iper PS 50040-40-2, Piper code umii 59?4 11’ b.) Cahles/harnessesandhardware, Piper drving ‘01901-1 OLandi 01900-104 0.54 Grinin Gl-iC6A Systeiiiinstallation 1.56 9.21...
  • Page 176 Piper 90oo.oou. Moo,. Page: 6-13-(15) Issued: DECEMBER 10, 2004 240-0129 15 of 17...
  • Page 177 Avidyne Entegra System (only)). Piperdrawing 10 Y9(C-105 a.) Shelf assembly Piper drawing 101253-002 0.69 201.60 138.43 (i) Miscellaneous Optional Equipment nditic.nei installation (P.—2’. Piper diwine L)Q50.. )J7. (i)itin’, Opn’0l) Coidenscr iiialJatiop. P ic: drawing 9985 5-OOC I C.-mderser-Enviro Systems Partnumbe l25034, Pine de 557- IU1±...
  • Page 178 Piper Page: 6-13-(17) Issued: DECEMBER 10, 2004 240-0129 17 of 17...
  • Page 179 7.27 Heating, Ventilating and DefrostingSystem 7-25 7.29 Stall Warning 7-27 7.31 7-27 Finish 7.33 7-27 Air Conditioning 7.35 Piper External Power 7-29 7.37 7-29 Emergency Locator Transmitter 7.39 REPORT: VB-1612 12, 1995 ISSUED: JULY ‘7-i Page: 7-0-(1) Issued: JULY 12, 1995...
  • Page 180 SECTION PA-28R-2O1, ARROW DESCRIOPERATION LEFT BLANK • THIS PAGE INTENTIONALLY ISSUED: 12, 1995 REPORT: VB-1612 JULY Page: 7-0-(2) Issued: JULY 12, 1995 7-ii...
  • Page 181 SECTION PA-28R-201, ARROW 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. Ithas seating for up to four occupants, a 200 pound luggage compartment, and a 200 HP engine. AIRFRAME With the exception of the steel engine mount, the landing gear,...
  • Page 182 Since Lyconting from time to time revisesthe recommended overhaul period, the owner should check the latest Lycoming Service Instruction No. 1009 at his Piper dealer for the latest recommended overhaul period and for any additional information.
  • Page 183 SECTION PA-28R-201, ARROW DESCRIOPERATION INDUCTION SYSTEM The 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 the fuel flow proportional to airflow.
  • Page 184 SECTION PA-28R-201, ARROW DESCR]OPERATION ENGIIbE CONTROLS Engine controlsconsistof a throttle control, a propeller controland a mixture controllever. These controlsare located on the control quadrant on the lower center of the instrument panel (Figure 7-1) where they are accessible to both the pilot and the copilot. The controlsutilize teflon-lined control cables to reduce friction and binding.
  • Page 185 SECTION DESC1VOPERATION PA-28R-2O1, ARROW ENGINE CONTROLS (continued) TRIM CONTROL CONSOLE CONTROL QUADRANT Figure 7.1 VB-1612 REPORT: 12, 1995 JULY ISSUED: .7-c Page: 7-5-(0) Issued: JULY 12, 1995...
  • Page 186 SECTION PA-28R-201, ARROW DESCR!OPERATION 150 245 &T!MP GEAi %Id] AMPS1 • LANDING GEAR SELECTOR Figure 7-3 7.11 LANDING GEAR The Arrow is equipped with a retractable tricycle landinggear, which is hydraulically actuated by an electrically powered reversible pump. The pump iscontrolled by a selector switch on theinstrument panel tothe left of the control quadrant (Figure7-3).
  • Page 187 SECt[ON PA-28R-201, ARROW DESCRIOPERATION 7.11 LAIQD]NG 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 carries a 5.00 x 5 four ply tire and the main gear use 6.00 x 6 six ply tires.
  • Page 188 J,u11UIN PA-28R-201. ARROW DESCRIOPERATION 7.11 LANDING GEAR (continued) LANDING GEAR ELECTRICAL SCHEMATIC Figure 7-5 REPORT: VB-1612 ISSUED: JULY 12, 1995 Page: 7-8-(0) Issued: JULY 12, 1995...
  • Page 189 SECTION PA-28R-201, ARROW DESCRIOPERATION 7.11 LAD]NG GEAR (continued) •SHUTtLE VALVE LOW PfiESSUflE cONtROL. IMOUNTING BASE MAINGEAR NTDEAUUCCYUND!R SChEMATIC GEAR hYDRAULIC LANDING Figure 7-7 REPORT: VB-1612 12, 1995 ISSUED: JULY ,7-Q Page: 7-9-(0) Issued: JULY 12, 1995...
  • Page 190 SECTION PA-28R-201, ARROW DESCRIOPERATION EMERGENCYGEAR LEVER EXTENSION PITCHTRIM CONTROL FLAP HANDLE FLIGHT CONTROL CONSOLE Figure 7-9 7.13 FLIGHT CONTROLS Dual flight controlsare provided as standard equipment. A cable system provides actuationof the control surfaces when the flight controls are moved intheir respective directions.
  • Page 191 SECTION PA-28R-201, ARROW DESCR/OPERATION 7.13 LIGRT 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 frontseats on the control console (Figure 7-9).
  • Page 192 SECTION PA-28R-201, ARROW DESCRIOPERATION 7.15 FUEL SYSTEM (continued) • NOZ2LE FUEL DISTRISIJTOR FUELFUMP supply L INE OUANT1TY GAUGES. FUEL SYSTEM SCHEMATIC Figure 7-11 REPORT: VB-1612 ISSUED: JULY 12, 1995 7-12 Page: 7-12-(0) Issued: JULY 12, 1995 7-12...
  • Page 193 • SECTION PA-28R-201, ARROW DESCRJOPERATION 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 selectorallows the pilot to controlthe flow of fuel to the engine, and islocatedon the leftside wall below the instrument panel.
  • Page 194 SECTION DESCR/OPERATION PA-28R-201, ARROW ELECTRICAL SYSTEM All switches are grouped in a switch panel above the power quadrant. The circuit breaker panel islocatedon the lower right sideof the instrument panel. Each breakeris clearly marked to show which circuit i t protects. A lso, circuit provisions are made to handle the addition of communications and navigational e quipment.
  • Page 195 SECTION PA-28R-201, ARROW DESCWOPERATION 7.17 ELECTRICAL SYSTEM (continued) SCEEMATIC ALTERNATOR STARTER Figure 7-15 REPORT: VB-1612 ISSUED: JULY 12,1995 7-15 Page: 7-15-(0) Issued: JULY 12, 1995 7-15...
  • Page 196 SECTION DESCR!OPERATION PA-28R-201, ARROW 7.17 ELECTRICAL SYSTEM (continued) ®®®®®®®®o®®®® ® as.. •ptQ ®® ®@®®®®®OO®®® CIRCUIT BREAKER PANEL Figure 7-17 WARNING Strobe lights should not be operating when flying through overcast and clouds since reflected light produce spacial disorientation. Do not operate strobe lights in close proximity to ground, during takeoffand landing.
  • Page 197 SECTION PA-28R-201, ARROW DESCRIOPERATJCjN 7.17 ELECTIUCAL SYSTEM (continued) Secondary power is provided by a 12-volt, 35-ampere-hour battery. The ammeter as installeddoes not show battery discharge; ratherit shows the electrical load placed on the system. With all the electrical equipment off, and the battery master (BATT and alternator MASTR) (ALT.R) switches on, the anmieter will indicate the charging rate of the...
  • Page 198 SECTION PA-28R-201, ARROW DESCRIOPERATION VACUUM SYSTEM (continued) regulator is provided in the system to protect the gyros. The A vacuum valve issetso thenormal vacuum reads 4.8to 5.1 inches of mercury, a setting which provides sufficient v acuum to operate allthe gyros attheirrated rpm. Higher settings will damage the gyros and with a low setting the gyros willbe unreliable.
  • Page 199 SECTION PA-28R-201, ARROW DESCRIOPERATION 7,21 PITOT-STATIC SYSTEM (continued) SYSTEM PITOT-STATIC Figure 7-19 REPORT VE-16j2 12, 1995 JULY ISSUED: Page: 7-19-(0) Issued: JULY 12, 1995 7-19...
  • Page 200 SECTION PA-28R-201, ARROW DESCRIOPERATION 7.23 INSTRUMENT PANEL INSTRUMENT PANEL Figure 7-21 REPORT: VB-1612 ISSUED: 12, 1995 JULY 7-20 Page: 7-20-(0) Issued: JULY 12, 1995 7-20...
  • Page 201 SECTION ARNOW WSCP /OPER ATION I-i- 0z<e, < U)LL cj< cr°l-<o.C WUJ(< .c0fl..LUØgOQzOO oe-a 0—N CCCC) <I- øO0 z<-1 a_U) 0— C..) < DDOWW<0<>DO.J-J <<cjo<aZI<zCJOXCJw< Oc.lc.4 ncór 0< i—1- < <Ui < 0... Dcl) < 0W-i < < -so—— C.)0 _o<01-o.JL)t ZWOU.LLZZ <UU—...
  • Page 202 SECTION PA.28R-201, ARROW DESCRIOPERATION (continued) 7.23 INSTRUMENT PANEL the customary The instrument panel is designed to accommodate advanced flight instruments and the normally plant required power instruments. The altitude and directional gyros, locatedin the centerof the operated. The vacuum gauge. is lefthand instrument panel, are vacuum located on the right hand instrument panel.
  • Page 203 SECTION PA-28R..201, ARROW DESCRJOPERA’rIoN CABIN DOOR LATCH Figure 7-23 7.25 CABIN FEATURES All seatbacks have three positions: n ormal, intermediate and recline. T he adjustment leverislocatedatthe base of the seatback on the outboard sideof the seat.The frontseats adjust fore and aftfor ease of entry and occupant comfort.An armrestislocatedon the side panelsadjacent to the frontseat.
  • Page 204 SECTION PA-28R-201, ARROW DESCRIOPERATION 7,25 CABIN FEATURES (continued) the strap will and holds the occupant in place. Under normal movement extend and retract as required. Shoulder harnesses should be routinely worn during takeoff, landing and whenever an in-flightemergency situation occurs. Additional features include pilot storm window, two sun visors, ash trays for each occupant, map pockets located on the side panels below the instrument panel, miscellaneous pockets on the rear of thefront seat backs,...
  • Page 205 SECTION PA-28R-201, ARROW DESCRIOPERATION 7.29 BEATING, DEFROSTING SYSTEM VENTILATING, The heating system is designed to provide maximum comfort for the occupants during winter and cool weather flights. The system includes a heat shroud1 heat ducts, defroster outlets, h eatand defroster c ontrols. CAUTION When cabin heat is operated, heat duct surface...
  • Page 206 SECTION PA-28R-201, ARROW DESCR!OPERATION 7.29 HEATING, SYSTEM DEFROSTING VENTILATING, (continued) VENTILATING HEATING, DEFROSTING SYSTEM Figure 7-25 REPORT: VB-1612 ISSUED: JULY 12, 1995 7-26 Page: 7-26-(0) Issued: JULY 12, 1995 7-26...
  • Page 207 All exterior surfacesare primed with etching primer and finishedwith acryliclacquer. To keep the finish attractive looking, economy size spray cans of touchup paint areavailable from Piper Dealers. 7.35 AIR CONDITIONING* The air conditioning system is a recirculating air system. The major components include an evaporator, a condenser, a compressor, a blower, switches and temperature controls.
  • Page 208 SECTION DESCR!OPERATION PA-28R-201, ARROW 7.35 AIR CONDITION1NG (continued) The switchesand temperature controlarelocatedon the lower right side of the instrument panel in the climate controlcenter panel. The temperature control regulates the temperature of the cabin. Turning the control clockwise increases cooling; counterclockwisedecreases cooling. The fan speed switch and the air conditioning ON-OFF switch are inboard of the temperature control.
  • Page 209 EXTERNAL POWER An optional starting installation k nown as Piper External Power (PEP) is accessible through a receptacle located on the right sideof the fuselage aft of the baggage compartment door. An external battery can be connected to the socket, thus allowing the operator to crank the engine without having to gain access to the airplane’s battery.
  • Page 210 SECTION DESCRJOPERATION PA-28R-201, ARROW 7.39 EMERGENCY LOCATOR TRANSMITTER* (continued) NARCO ELT 10 OPERATION (continued) To use the ELT as a portable unitin an emergency, remove the cover and unlatch the unit from its mounting base. The antenna cable is disconnected by a left quarter-turn of the knurled nut and a pull.
  • Page 211 SECTION PA-28R-201, ARROW DESCRJOPERATION 7.39 EMERGENCY LOCATOR TRANSMITTER* (continued) NARCO ELT 910 OPERATION On the ELT unit itself i s a three position switch placarded ON, OFF ARM. The ARM position setsthe LILT so thatitwilltransmitafter impact and will continue to transmit until its battery is drained. The ARM position is selected when the LILT is installed in the airplane and itshould remain in that position.
  • Page 212 SECTION DESCRJOPERATION PA-28R-201, ARROW 7,39 EMERGENCY LOCATOR TRANSMITTER* (continued) ARTEX ELT OPERATION On the ELT unit itself is a two position switch placarded ON and OFF. The OFF position is selectedwhen the transmitter i sinstalled a t the factory and the switch should remain in that position whenever the unit is installed in the airplane.
  • Page 213 SECTION PA-28R-201, ARROW HANDISERV!MAINT TABLE OF CONTENTS SECTION MAiNTENANCE AIRPLANE HANDLING, SERVICING, Page Paragraph General AirplaneInspection Period.s Preventive Maintenance Airplane Alterations Ground Handling Engine Air Filter 8.11 Brake Service 8.13 Landing Gear Service 8.15 8-10 Propefler Service 8.17 8-10 8.19 Oil Requirements 8-10 Fuel System...
  • Page 214 I!A11V1’ ö PA-28R-201, ARROW HAND/SERVIMAINT • THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: 12, 1995 JULY 8-li Page: 8-0-(2) Issued: JULY 12, 1995 8-ii...
  • Page 215 STC installations. non-PIPER WARNING Modifications must be approved in writing by PIPER prior to installation. Any and allother installations, whatsoever, of any kind willvoid this warranty in it’s entirety. REPORT:...
  • Page 216 PIPER airplane applications. Parts purchased from sources other than PIPER, even though identical in appearance, may not have had the required tests and inspections performed, be differentin fabrication techniques and materials, and may be dangerous when installed in an airplane.
  • Page 217 Piper’s support systems. Piper takes a continuing interest in having owners get the most efficient use from their airplane and keeping it in the best mechanical condition. Consequently, Piper, from time to time, issues service releases including Service Bulletins, Service Letters, Service Spares Letters, and others relating to the airplane.
  • Page 218 Manual contains appropriate forms, and all inspectionprocedures should be complied with by a properly trained, knowledgeable, and qualified mechanic at a Piper Authorized ServiceCenter or a reputable repair shop. Piper cannot accept responsibility for the continued airworthinessof any aircraft not maintained to...
  • Page 219 SECTION PA-28R-201, ARROW RAND/SERVIMA1NT 85 PREVENTIVE MAINTENANCE The holder of a Pilot Certificate i ssued under FAR Part 61 may perform certain preventive maintenance describedin FAR Part 43. This maintenance may be performed only on an aircraft w hich the pilot owns or operates and which isnot used to carry persons or property for hire, except as provided in applicable FAR’s.
  • Page 220 SECTION PA-28R-201, ARROW ELANDISERVIMAINT 8.7 AIRPLANE ALTERATIONS (continued) (b) Tobecaniedintheaircraftatailtimes: (I) Pilot’s Operating Handbook. (2) Weight and Balance data plus a copy of the latest Repair and Alteration F orm FAA-337, if applicable. (3) Aircraft equipment list. Although the aircraft a nd engine logbooks are not required to be in the aircraft, t hey should be made available upon request.Logbooks should be complete and up to date.Good records will reduce maintenance cost by...
  • Page 221 SECTION IIAND/SERVIMAINT PA-28R-201, ARROW 8.9 GROUND BANDLING (confinued) (b) Taxiing Before attempting to taxithe airplane, ground personnel should be instructed and approved by a qualified person authorized by the procedures as well as taxi owner. Engine starting and shutdown it is ascertained that the techniques should be covered.
  • Page 222 SECTION PA-28R-201, ARROW HANDISERVIMAJNT 8.9 GROUND HANDLING (continued) (3) Aileron and stabilator c ontrols 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 223 SECTION PA-28R-201, ARROW HAND/SERVIMAJNT 8.11 ENGINE AIR FILTER (a) Removing Engine Air Filter (1) Remove the upper cowl. (2) Remove the wing nuts securing the filter box cover. Remove Remove the filter. (b) Cleaning Engine Air Filter The inductionairfilter m ust be cleaned at leastonce every SO hours, and more often, even daily, when operating in dusty conditions.
  • Page 224 SECTION PA.28R-201, ARROW HAND/SERY/MAINT SERVICE 8.13 BRAKE (continued) I!IIII BRAKE SYSTEM Figure 8-1 REPORT: VB-1612 ISSUED: JULY 12,1995 Page: 8-8-(0) Issued: JULY 12, 1995...
  • Page 225 SECTION PA-28R-201, ARROW EIAND/SERVIMAINT 8.15 LANDING GEAR SERVICE The main landinggear uses 6.00 x 6 wheels with 6.00 x 6, six-ply rating tires and tubes.The nose wheel uses a 5.00 x 5 wheel with a 5.00 x 5 four-ply rating, t ype ifi tire and tube. (Refer to Paragraph 8.23.) Wheels are removed by taking off the hub cap, cotter pin, axle nut, and the two bolts holding the brake segment in place.
  • Page 226 SJCTION PA-28R-201, ARROW HANDISERVIMAINT 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 stress which can lead to serious cracks or the lossof a propeller tip.
  • Page 227 SECTION PA-28R-201, ARROW HANDISERVIMA1I4T SYSTEM FUEL (continued) (a) Servicing Fuel System (continued) of the firewall. I tis accessible by removing the lower cowling. After cleaning, a small amount of grease applied to the gasket willfacilitate facilitate reassembly. (1,) Fuel Requirements (AVOAS ONLY) Aviation grade fuel with a minimum octane of 100/130 is...
  • Page 228 SECTION HAND/SERV?MAINT PA-28R-201, ARROW 8.21 FUEL SYSTEM (continued) (b) Fuel Requirements (AVGAS ONLY) (continued) The operation of the aircraft i s approved with an anti-icing addithe anti-icing additive is used, itmust meet the addithe in the fuel.When specification MIL-I-27686, must be uniformly blended with the fuel while refueling, m ust not exceed 0.15% by volume of the refueled quantity, and to ensure itseffectiveness should be blended at not Less than 0.10% by volume.
  • Page 229 SECTION BAND/SERVJMA]NT PA-28R-201, ARROW FUEL SYSTEM (continued) (c) Filling Fuel Tanks (continued) Observe all safety precautions required when handling gasoline. Fillthe fuel tanks through the filler located on the forward gasoline. U.S. slope of the wing. Each wing holds a maximum of 38.5 gallons.
  • Page 230 SECTION PA-28R-201, ARROW IIAND/SERV/MAINT FUEL SYSTEM (continued) (d) Draining Fuel Strainer, Sumps and Lines (continued) The fuel strainer, locatedon the lower left side of the firewall, i s before the first provided with a quick drainwhich should be drained flight of the day or after refueling, to check for fuel contamination. If contamination is found, fuel should be drained untilthe contamination stops.
  • Page 231 SECTION PA-28R-291, ARROW BAND/SERVIMAINT IATTERY SERVICE The 12-volt, 35-ampere-hour battery is located just behind the aftclose out panel. Access is gained through the baggage compartment. The battery containerhas 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 collected in the tube.
  • Page 232 S1!CTIUIN PA-28R-201, ARROW HAND/SERVIMAINT 8.27 CLEANING (continued) (a) Cleaning Engine Compartment (continued) (3) Allow the solventto remain on the engine from fiveto ten rinse the engine clean with additional minutes. Then solvent and allow itto dry. CAUTION Do not operate the engine untilexcess solvent has evaporated or otherwise been removed.
  • Page 233 SECTION PA-28R-201, ARROW HAND/SERVIMAINT 8.27 CLEANING (continued) (c) Cleaning Exterior Surfaces (continued) (2) Apply cleaning solutionwith a soft cloth, a sponge or a softbristle b rash. exhaust stains, allow the solution to remain (3) To remove on the surface longer. (4) To remove stubborn oiland grease, use a cloth dampened with naphtha.
  • Page 234 SECTION PA-28R-201, ARROW BANDISERVIMAINT 8.27 CLEANING (continued) (e) Cleaning Headliner, Side Panelsand Seats (1) Clean headliner, side panels, and seats with a stiff bristle brush, and vacuum where necessary. (2) Soiled upholstery, except leather, may be cleaned with a good upholstery cleaner suitablefor the material.Carefully follow the manufacturer’s instructions.
  • Page 235 SECTION PA-28R-201, ARROW SUPPLEMENTS TABLE OF CONTENTS SECTION SUPPLEMENTS Page Paragraph/Supplement General Auxiliary Vacuum System (6 pages) King 100 Series Flight Control System (Deleted) (1 page) 9-11 King 150 Series Flight Control System (Deleted) (1 page) 9-13 89B GPS Navigation System Bendix/King KLN (12 pages) 9-25...
  • Page 236 SECTION PA-28R-201, ARROW SUPPLEMENTS TABLE OF CONTENTS SECTION SUPPLEMENTS (continued) Paragraph/Supplement Page Bendix/King KR-87 Digital ADF with KI-227 Indicator 9-159 (10 pages) Bendix/King KN-63 DME 9-169 (4 pages) Garmin GNS 430W Communication Transceiver/VORJILS Receiver/GPS Receiver 12 pages) 9-173 Garmin G500 Primary Flight and Multifunction 9-185 (1 page) Display System...
  • Page 237 SECTION PA-28R-201, ARROW SUPPLEMENTS SECTION SUPPLEMENTS GENERAL This section provides informationin the form of Supplements which are necessary for efficient o peration of the airplane when equipped with one or more of the various optionalsystems and equipment not provided with the standard airplane.
  • Page 238 SECTION SUPPLEMENTS PA-28R-201, ARROW TRIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: 12, 1995 JULY Page: 9-2-(0) Issued: JULY 12, 1995...
  • Page 239 Airplane Flight Manual only in those areaslisted herein.For informationnot contained in this supplement, consultthe basic Pilot’s Operating Handbook Approved Airplane Flight Manual. and FAA APPROVED E. PECK PETER D.O.A. NO. SO-i INC. PIPER AIRCRAFT, VERO FLORIDA BEACH, OF APPROVAL SEPTEMBER 19. 1999 DATE REPORT:...
  • Page 240 PA-28R-201, ARROW SUPPLEMENT THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1733 ISSUED: SEPTEMBER 19, 1999 Page: 9-2-(2) Issued: SEPTEMBER 19, 1999 UK i...

  • Page 241: Current Revisions To The Pa-28R

    UNITED KINGDOM PA-28R-201, ARROW SUPPLEMENT PILOT’S OPERATING HANDBOOK OF REVISIONS Current Revisions to the PA-28R-201 Arrow, UK Supplement, VB.-1733, issued September 19, 1999. Revision Revised Description of Revisions Number Code Pages Rev. 1 Revised page. Revised page. (PR010417) Revised Limitations. REPORT: VB-1733 19, 1999...

  • Page 242: Report: Vb

    SUPPLEMENT ARROW PA-28R-201, Revision Number Revised Description of Revisions Code Pages REPORT: VB-1733 ISSUED: SEPTEMBER 19, 1999 REVISED: APRIL 17, 2001 Page: 9-2-(4) Issued: APRIL 17, 2001 UK iii...
  • Page 243 UNITED KINGDOM SUPPLEMENT PA-28R-201, ARROW INTRODUCTION The data in this supplement must be includedin the Pilot’s Operating Handbook (P.O.H.) when operating on the United Kingdom register. In cases of conflicting information, thedatain this supplementsupercedes information published inVB-1612. LIMITATIONS Category: in the Aircraft o f this type are eligible forcertification However, this aeroplane m ay Transport Category(Passenger).
  • Page 244 SUPPLEMENT PA-28R-201, ARROW LIMITATIONS (Cont’d.) Performance (Cont’d.) For takeoff operations from short dry grass fields w ith firm subsoil, increase t akeoffdistance by 20%. For takeoff operations from shortwet grass fields, with firm subsoil, increase t akeoffdistance by 25%. These factors apply totake offdistance t o50 feet theeffect o n the ground roll will be greater.
  • Page 245 UNITED KINGDOM PA-28R-201, ARROW SUPPLEMENT LIMITATIONS (Cont’d.) Number of Occupants: The number of persons carried m ust notexceed four, n or exceedthenumber of seats installed. Children underthe age of 2, carried i nthearms of passengers, areexcluded from this count. Climatic Conditions: The operating suitability of the aeroplane has been established for temperatures up tothe range defined by I.S.A.
  • Page 246 PA-28R-201, ARROW SUPPLEMENT LIMITATIONS (Cont’d.) Autopilots: When a Bendix/King 150 series autopilot, or an S-TEC System 55155X autopilot is installed, it shallnot remain engaged at heights below 1000 feet above theterrain. When coupled to an ILS glide slope, itshall n ot remain engaged at heights below 200 ftabovetheterrain.
  • Page 247 UNITED KINGDOM PA-28R-201, ARROW SUPPLEMENT PROCEDURES (Cont’d.) Starter Engaged Warning Light: (Cont’d) Should the warning light remain illuminated after the MASTER starter switchis disengaged, turnthe BATTERY OFF and have thefault corrected b efore attempting SWITCH tostart t he engine. Low Voltage Monitor Light Pre Flight Check: Before Engine Start Alternator...
  • Page 248 SUPPLEMENT PA-28R-201, ARROW PROCEDURES (Cont’d.) Notes: A landing shouldbe made assoon as possible. Under the alternator failure conditions the battery endurance shouldbe 30 minutes. VHF communication transmission should be restricted tomaximum of3 minutes during total flight. Other electrical services may be used atthe pilot discretion but the battery endurance will be reduced prorata.
  • Page 249 This supplement must be attached to the Pilot’s Operating Handbook and FAA Airplane Flight Manual when the Piper Auxiliary Approved Vacuum System isinstalled i n accordance with Piper Drawing No. 89311-2. or supersedes the basic The information contained herein supplements Pilot’s Operating Handbook and FAA Airplane Flight Manual Approved only in those areas listed herein.
  • Page 250 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 1- GENERAL This supplement supplies information necessary for the operation of the airplane when the optionalPiper Auxiliary Vacuum System isinstalled. The informationcontained within this supplement is to be used in conjunction with the complete handbook. SECTION LIMITATIONS (a) The auxiliary vacuum...
  • Page 251 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 4- NORMAL PROCEDURES (a) Preflight C heck. switch ON and verify (I) Turn battery master (BAT1’ MASTR) OFF light is illuminated. thatthe VAC NOTE Due to the electrical p ower requirement of the pump itis suggested thatthe auxiliary vacuum engine be operating while making the following checks,...
  • Page 252 SECTION PA-28R-201, ARROW SUPPLEMENT SECTIONS- PERFORMANCE No change. SECTION 6- WEIGhT & BALANCE Factory installed optionalequipment is included in the licensed weight and balancedatain Section6 of the Basic Pilot’s Operating Handbook. 7- DESCRIPTION SECTION AN]) OPERATION The auxiliary dry air pump system provides an independent back-up sourceof pneumatic power to operate the gyro flight instruments in theevent the engine drivenair pump fails.
  • Page 253 SECTION PA-28R-201, ARROW SUPPLEMENT OPERATION SECTION 7- DESCR]PT[ON (cont) The annunciator lights do not incorporate a press-to-test feature. If the lights do not illuminateas expected, check for burned out lamps,,replace 25237-330 bulbs and retest the system. with MS motor electrical circuit is protectedby a 20 amp AUX The pump breaker installed in the circuit breakr panel.
  • Page 254 SECTION PA.28R-2O1, ARROW SUPPLEMENT <cOu. VACUUM SYSTEM SCHEMATIC REPORT: VB-1612 ISSUED: 12, 1995 JULY 6of6 Page: 9-8-(0) Issued: JULY 12, 1995...
  • Page 255 SECTION PA-28R-201, ARROW SUPPLEMENT PILOT’S OPERATING HANDBOOK APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO.2 KING 100 SERiES FLIGHT CONTROL SYSTEM The FAA to the Bendix/King 100 Approved Operational Supplement Series Flight Control System as installed per STC is supplied SA1563CE-D by the autopilot manufacturer. Bendix/King will be responsible to supply and revise the operational supplement.
  • Page 256 SECTION PA-28R-201, ARROW SUPPLEMENT THIS PAGE LEFF BLANK INTENTIONALLY ISStJED: JULY 12, 1995 REPORT VB-1612 9-10 Page: 9-10-(0) Issued: JULY 12, 1995 9-10...
  • Page 257 SECTION PA-28R-201, ARROW SUPPLEMENT PILOT’S OPERATING HANDBOOK MANUAL APPROVED AIRPLANE FLIGHT NO.3 SUPPLEMENT SYSTEM 150 SERIES FLIGHT CONTROL KING Operational Supplement to the Bendix/King 150 The FAA Approved SAI563CE-D is supplied Series Flight Control System as installed per STC to supply by the autopilot manufacturer.
  • Page 258 SECTION SUPPLEMENT PA.28R-201, ARROW TifIS PAGE INTENTIONALLY BLANK LEFT ISSUED: JULY 12, 1995 REPOR VB-1612 9.12 Page: 9-12-(0) Issued: JULY 12, 1995 9-12...
  • Page 259 For limitations, procedures and performance information not containedin this supplement, consultthe Pilot’s Operating Handbook Approved Airplane Flight Manual. FAA APPRO: PETER E. PECK D.O.A. NO. SO-i PIPER AIRCRAFT, INC. THE NEW VERO FLORIDA BEACH, DATE OF APPROVAL: December 11.1995...
  • Page 260 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 1 GENERAL sensor, the The KLN panel mounted unit contains the GPS display, and allcontrols required to navigationcomputer, a CRT operate unit. Italsohouses the database card which plugs directly intothe frontof the unit. The data base card isan electronic informationon airports, memorycontaining navaids, intersections, S 1D’s, STAR’s, instrument approaches, special use...
  • Page 261 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 2- LIMifATIONS Pilot’s The KLN 89B GPS Guide, PIN 006-08786-0000, dated May, 1995 (or later applicable revision) must be immediately available to the flight crew whenever navigation is predicated on the use of the system. The Operational Revision States (ORS) of the Pilot’sGuide must match the ORS level...
  • Page 262 SECTION PA-28R-201, ARROW SUPPLEMENT ABNORMAL SECTION 3-EMERGENCY PROCEDURES PROCEDURES Invalid, utilize If the KLN 89B GPS information is not availableor remaining operational n avigationequipment as required. AVAILABLE’ Ifa “RA]M message is displayed while conducting an instrument approach, terminate the approach. Execute a missed approach if required.
  • Page 263 SECTION PA-28R-201, ARROW SUPPLEMENT NORMAL PROCEDURES Will flashto alertthe pilot of a annunciator Message (MSG) situation that requires attention. Pressthe MSG button on the KLN 89B GPS toview the message. (Appendix B of theKLN 89B Pilot’s Guide containsa list of allof the message page messages and their meanings).
  • Page 264 SECTION PA-28R-201, ARROW SUPPLEMENT NORMAL PROCEDURES switch/annunciator approach (GPS ARMIACTV) Used to (a) manually select or deselect approach ARM and (b) annunciate the stage of deselect approach ACTV) or activated (ACTV). approach operation eitherarmed (ARM) would firstresult in Sequential button pushes if in ACTV approach ARM and then approach arm canceled.
  • Page 265 SECTION PA-28R-201, ARROW SUPPLEMENT NORMAL PROCEDURES ALTITUDE ALERT AURAL lONES • 1000 feet prior to reaching the selected a ltitudethreeshort tones. • Upon reaching theselected altitude two shorttones. • Deviating above or below the selected altitude by more thanthe warn altitudefourshort tones. APPROACH MODE RAiM...
  • Page 266 JU1iULN SUPPLEMENT PA-28R-201, ARROW NORMAL PROCEDURES At30nmfromtheairport APR ARM. Verify automaticannunciation Note automatic dbar scalingchange from ± 5.0 urn to ±10 ran over the next 30 seconds. Update theKLN 89B altimeter b aro setting as required. Internally the KLN 89B will transition from en route to terminal integrity m onitoring.
  • Page 267 SECTION PA-28R-201, ARROW SUPPLEMENT NORMAL PROCEDURES Approaching theFAF inbound (within 2 mu.): Verify APR ACTV. Note automaticdbar scaling change from ±1.0 tim to ± 03 nmoverthe2mninboundtotheFAE 89B willtransition from terminalto Internally t heKLN approach integrity monitoring. Crossing theFAF and APR ACPI is pti annunciate&...
  • Page 268 SECTION PA-28R-2OI, ARROW SUPPLEMENT PROCEDURES NORMAL • suffixes the flight plan: Waypoint i-lAP f-FAF rn-MAP h missed approach holding fix. • The DME arc lAP (arc intercept waypoint) willbe a) on your present position radialoff the arc VOR when you load the lAP into the flight plan, or b) the beginning of the arc if currently on a radial beyond the arc limit To adjust the arc intercept to be...
  • Page 269 SECTION ARROW SUPPLEMENT PA-28R401, NORMAL PROCEDURES • to APR ACTV automatic provide& a. You are in APR (normally automatic). b. You areinLEG mode! c. The FAF istheactive wavpoiut! d. Within 2 n.m. of theFAR e. Outside of theFAR f. Inbound to theFAR g.
  • Page 270 SECTION PA-28R-201, ARROW SUPPLEMENT LEFT BLANK THJS PAGE INTENTIONALLY REPORT: VB-1612 ISSUED: JULY 12, 1995 9.24 12 of 12 REVISED: 11, 1995 DECEMBER Page: 9-24-(0) Revision: 1, DECEMBER 11, 1995 9-24...
  • Page 271 KX 155A Comm/Nay Approved Airplane Flight Manual and FAA contained System is installed per the Piper Drawings. The information and FAA herein supplements or supersedes the Pilot’s Operating Handbook only in those areas listedherein. For Airplane Flight Manual...
  • Page 272 SUPPLEMENT SECTION 1 GENERAL This supplement supplies information necessary for the operation of the System is installed in airplane when the Bendix/King KX 155A Comm/Nay accordance with FAA approved Piper data. SECTiON 2 LIMiTATIONS No change. SECTION 3- EMERGENCY PROCEDURES No change.
  • Page 273 SECTION PA-28R-201, ARROW SUPPLEMENT 7 DESCRIPTION SECTION & OPERATION GENERAL Allcontrols required to operate the KX 155A1165A arelocated on the unitfront panel. (See Figure3-1.) t$Iat OJlobTR.ahld SlzsI AdlV.COIIm *dIi,$ie FtI$.cV Flqc DVDSCmm A.,*dkSqIc. p,1I A,,g1e qwk. Hl fteSy Co,,m Fnqy ia F,qac iIncês a.c1Kne,...
  • Page 274 SECTION PA-28R-201, ARROW SUPPLEMENT COMM TRANSCEIVER (CONTD) The outer knob will change the MHz portion of the standby display. At one band-edge (118 or 136 MHz). the following 1 MHz change will wrap around to the other band-edge. The inner knob will change the kHz portion of the standby display.
  • Page 275 SECTION PA-28R-201, ARROW SUPPLEMENT The KX 155A alsohas provision to program 32 channels. Pressing the CHAN buttonfor2 or more seconds willcause the unittoenterthe channel program mode. Upon entering the channel program mode,”PG” is displayed next to the channel number and the channel number will flash indicating thatitcan be programmed.
  • Page 276 S1C11ON PA-28R-201, ARROW SUPPLEMENT RECEIVER (CONTO) receiver’s l ower and upper The innerknob operates in 50 kHz steps. The NAV and 117.95 MHz. Exceeding the upper limit frequency limits are 108.00 MHz of frequency band will automatically return to the lower limit and vice versa. frequency transfer b uttonfor 2 seconds or more willcause Depressing the NAV the display to go in to the ACTIVE...
  • Page 277 SECTION PA-28R-201, ARROW SUPPLEMENT 41U. -+-- FIGURE ACTiVE LOCALIZER FORMAT DISPLAY; FREQUENCY/CDI When thereceived signal istoo weak toensure accuracy the display will “flag”. See Figure 3-4. flfl L-IU9 FLR[ L-IU9 DISPLAY FIGURE 3-4 VOR FLAG REPORT: VB-1612 12, 1995 ISSUED: JULY 12, 9-31 16, 1998...
  • Page 278 SECTION SUPPLEMENT PA-28R-201, ARROW RECEIVER (CONTD) Depressing the mode button will cause the NAV display to go from the ACTIVE/CDT format to the ACTIVE/BEARING format. In the BEARING mode, theincrement/decrement knob channelsthe ACTIVE frequency window and depressing the frequency transfer b uttonwillcause theACTIVE frequency to be placed inblind storage and theSTANDBY frequency (in blind storage) to...
  • Page 279 SECTION PA-28R-201, ARROW SUPPLEMENT Another push of the mode button willcause the NAV display to go from the ACTIVE/BEARING format to the ACTIVE/RADIAL format as shown in Figure 3-7.In theRADIAL mode, theincrementldecrementknob channelsthe ACTIVE frequency window and depressing the frequency transfer buttonwill cause theACTIVE frequency tobe placed in blind storage and the STANDBY frequency (in blind storage) tobe displayed in theACTIVE...
  • Page 280 SECTION PA-28R-201, ARROW SUPPLEMENT NAV RECEIVER (CONTO) Another push of the mode button will cause the unit to go into the TIMER the unitis turned on the elapsed timer begins mode. See Figure 3-9. When counting upwards from zero.The timer can be stopped and resetto zero by frequency transfer button for 2 seconds or more causing the pushing the NAV ET on the display to flash.In thisstatethe timer can be set as a countdown...
  • Page 281 SECTION SUPPLEMENT PA-28R-201, ARROW PILOT CONFIGURATION This mode can be accessed by pressing and holding the Nay Mode Button for more than 2 seconds and then pressing the Nay Frequency TransferButton for an additional 2 seconds, while continuing to hold the Nay Mode Button.When is entered the unit will show the “SWRV”...
  • Page 282 SECTION PA-28R-201, ARROW SUPPLEMENT THIS PAGE LEFT BLANK INTENTIONALLY REPORT: VB-1612 ISSUED: JULY 12,1995 9-36, 12 of 12 REVISED: NOVEMBER 16, 1998 Page: 9-36-(0) Revision: 3, NOVEMBER 16, 1998 9-36...
  • Page 283 SECTION PA-28R-201, ARROW SUPPLEMENT PILOT’S OPERATING HANDBOOK APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO.6 S-TEC MANUAL TRIM ELECTRIC SYSTEM WITH TRIM MONITOR (Serial numbers 2844010 and up) The FAA for the S-TEC Manual approved operational supplement ElectricTrim System, installed in accordance with STC SA78O5SW-D, required for operation of this system.
  • Page 284 PA-28R-201, ARROW SUPPLEMENT THIS PAGE LEFT BLANK INTENTIONALLY REPORT: VB-1612 ISSUED: JULY 12,1995 9-38 REVISED: JANUARY 31, 2000 Page: 9-38-(0) Revision: 4, JANUARY 31, 2000 9-38...
  • Page 285 FAA supplement, consult the Pilot’s Operating Handbook Approved Airplane Flight Manual. APPROVED: pJAk. L. MARSH CHRISTINA D.O.A. NO. SO-i INC. THE NEW PIPER AIRCRAFT, VERO FLORIDA BEACH, 14.2000 DATE OF APPROVAL: SEPTEMBER VB-1612 REPORT: ISSUED: JULY...
  • Page 286 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION GENERAL 430 System isa fullyintegrated, panel mounted instrument, which The GNS receiver, and a contains a VHF Communications Transceiver, a VORIILS Global Positioning System (GPS) Navigation computer. The system consists of antenna, VORJILS a GPS antenna, GPS receiver, VHF VORJLOC/GS receiver, Communications transceiver.
  • Page 287 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION LIMITATIONS A. The GARMIN 430 Pilot’s Guide, p/n 190-00140-00, Rev. A, dated October 1998, or later appropriate revision, m ust be immediately available to the flight crew whenever navigation is predicated on the use of the system.
  • Page 288 PA-28R-201, ARROW SUPPLEMENT SECTION 2- LIMITATIONS (continued) SDF, MLS or any of US, LOC, LOC-BC, LDA, Accomplishment overlay with the GNS other type of approach not approved for GPS 430’s GPS receiver isnot authorized. receiver to fly approaches not Use of the GNS 430 VOR/ILS approved for GPS require VOR/ILS navigation datato be present on...
  • Page 289 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES ABNORMAL PROCEDURES A. If GARMIN 430 navigation informationisnot available or invalid, utilize remaining operational navigation equipment as required. If“RAIM POSITION WARNING” message is displayed the system will flag and no longer provide GPS based navigational guidance.
  • Page 290 PA-28R-201, ARROW SUPPLEMENT 4- NORMAL PROCEDURES SECTION 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 attaining proficiency 430 approach feature. intheuse of theONS PROCEDURES DETAILED OPERATING...
  • Page 291 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 4- NORMAL PROCEDURES (continued) AUTOMATIC LOCALIZER COURSE CAPTURE By default, the GNS 430 automatic localizer course capture featureis enabled. This feature provides a method for system navigation data present on the external indicators t obe switched automatically f rom GE’S guidance to localizer! glide slope guidance at the point of course intercept on a localizer a t which GE’S derivedcourse deviation equals localizer derived course deviation.
  • Page 292 PA-28R-201, ARROW SUPPLEMENT THIS PAGE INTENTIONALLY LEFf BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 8 of 8 REVISED: SEPTEMBER 14, 2000 Page: 9-46-(0) Revision: 5, SEPTEMBER 14, 2000 9-46...
  • Page 293 Pilot’s Operating Handbook aad FAA Approved AirplaneFlight Manual. )1ttAJ,.k APPROVED: (jv.dL31o.. CBRIST1NA L. MARSH D.O.A. NO. SO- 1 INC. PIPER AIRCRAFr, FLORIDA VERO BEACH, September 14.2000 DATE OF APPROVAL: REPORT: VB-1612 ISSUED: JULY 12,1995...
  • Page 294 SUPPLEMENT SECTION 1. GENERAL This supplement supplies information necessary for the operation of the airplane when the Garmin GTX 327 Transponder is installed in accordance withFAA approved Piper data. SECTION 2- LIMITATIONS No change. SECTION 3- EMERGENCY PROCEDURES To transmit an emergency signal: •...
  • Page 295 SECTION PA-28R-201, ARROW SUPPLEMENT 4- NORMAL SECTION PROCEDURES BEFORE TAKEOFF: • To transmit Mode C (Altitude R eporting) code in flight: • Mode Selection Key- ALT • Code Selector assigned code. SELECT Keys code in flight: To transmit Mode A (Aircraft Identification) •...
  • Page 296 PA-28R-20L ARROW SUPPLEMENT 7. DESCRIPTION SECTION OPERATION GiiRNIN Crporticn t3TX 327 transponder is powered on by pressing the STBY, ALT or. ON The GTX keys, or by a remote avionicsmaster switch (if applicable). After power on, a start-up p age will be displayed while theunit performs a self test. Mode Selection Keys Powers offtheGTX 327.
  • Page 297 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION (continued) 327 Configuration Mode (continued) To use the GTX 327 Configuration Mode: 1: Press and hold the FUNC key while powering on the unit using the key (orusing an avionics master switch). STBY, ON, or ALT 2.
  • Page 298 1&_ I I.Ji PA-28R-201, ARROW SUPPLEMENT 7- DESCRIPTION ANI) OPERATION SECTION (continued) Code Selection (continued) Important Codes: code for any altitude in the US (Refer to ICAO standards The VFR 1200 elsewhere) used in Europe (Refer to ICAO 7000- The VFR code commonly standards) 7500...
  • Page 299 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION OPERATION 7-DESCRIPTION (continued) Keys for Other GTX 327 Functions (continued) PRESSURE ALT: Displays the altitude data supplied to the Li123 .1;0];1] 327 in feet, hundreds of feet (i.e., flight level), o r meters, depending on configuration. Displays the Flight Time, which iscontrolled FLIGHT TIME:...
  • Page 300 PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION (continued) AltitudeTrend Indicator “PRESSURE When the ALT” page is displayed, an arrow may be displayed to the right of the altitude, indicating thatthealtitude i s increasing or decreasing. One of two sizes of arrows may be displayed depending on the rate of climb/descent.
  • Page 301 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION AN]) OPERATION (continued) Automatic ALT1STBY Mode Switching 327 is configured for automatic standby switching, the mode will Ifthe GTX when a squat switch senses thatthe aircraft has automatically change to ALT automatically when a become airborne.
  • Page 302 PA-28R.2O1, ARROW SUPPLEMENT THIS PAGE LEFT BLANK INTENTIONALLY REPORT: VB-1612 ISSUED: JULY 12, 1995 9.56 10 of 10 REVISED: SEPTEMBER 14, 2000 Page: 9-56-(0) Revision: 5, SEPTEMBER 14, 2000 9-56...
  • Page 303 Pilot’s Operating Handbook aridFAA Approved Airplane Flight Manual. APPROVED:_____________________ CHRJS11NA L. MARSH D.O.A. NO. SO- I INC. THE NEW PIPER AIRCRAFT, VERO FLORIDA BEACH, September 14. 2000 OF APPROVAL: DATE VB-1612 REPORT: 12, 1995 ISSUED:...
  • Page 304 PA-28R-201, ARROW 1- GENERAL SECTION This supplement supplies information necessary for the operation of the airplane when the S-TEC ADF-650 System is installed in accordance with FAA approved Piper data. SECTION LIMITATIONS No change. SECTION 3- EMERGENCY PROCEDURES No change.
  • Page 305 SECTION PA.28R-201, ARROW SUPPLEMENT9 4- NORMAL SECTION PROCEDURES To operate as an Automatic DirectionFinder: • OFF/VOL Control- ON • Frequency Selector Knobs SELECT desired frequency. • ADF SPEAKER/PHONE SelectorSwitch (on audio control panel) as desired. SELECT • OFF/VOL Control SET todesiredvolume level. •...
  • Page 306 PA-28R-201. ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION System operates over a frequency range of 200 through The S-TEC ADF-650 1799 kHz in 1-kHz increments. Three operating modes are includedas part of theADF-650 System. •ANT • ADF 10kHz Control 100kHz/i CONTROL CONTROL ADF-650 Receiver,Controls, and Indicators...
  • Page 307 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 forstation identification. Mode Automatic Direction Finder (ADF) mode is used for navigation. This mode activates t he bearingpointer.
  • Page 308 PA-28R-201, ARROW SUPPLEMENT BLANK THIS PAGE INTENTIONALLY LEFJ REPORT: VB-1612 ISSUED: JULY 12,1995 9.62 6 of 6 REVISED: SEPTEMBER 14,2000 Page: 9-62-(0) Revision: 5, SEPTEMBER 14, 2000 9-62...
  • Page 309 Pilot’s Airplane Flight Manual. Operating Handbook and FAA Approved FAA APPROVED L. MARSH CHRISTINA D.O.A. NO. SO-i INC. PIPER AIRCRAFr, FLORIDA VERO BEACH, September 14.2000 OF APPROVAL OATH VB-1612 REPORT: 12, 1995...
  • Page 310 SUPPLEMENT 1- GENERAL SECTION This supplement supplies information necessary forthe operation of the airplane when the Garmin OMA 340 audio panel isinstalled in accordance with FAA approved Piper data. SECTION 2- LIMITATIONS No change. 3- EMERGENCY SECTION PROCEDURES No change.
  • Page 311 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 5- PERFORMANCE No change. 6- WEIGHT SECTION BALANCE Factory installed optional equipment isincludedinthe licensed weight and balance data in section 6 of the AirplaneFlight Manual. SECTION 7- DESCRIPTION OPERATION 1, Marker Beacon Lamps 2. Marker Beacon ReceiverAudio SelectiMuteButton 3.
  • Page 312 SICiIUI SUPPLEMENT PA-28R-201, ARROW SECTION 7- DESCRIPTION OPERATION (continued) PilotIntercom System (ICS) Volume Control ON/OFF, The GMA 340 is powered OFF when the leftsmall knob (5) is rotated fully intothe detent. To turn the unit ON, rotatethe knob clockwise past the click.The knob then functionsas the pilot ICS volume control.
  • Page 313 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION (continued) Aircraft Radios and Navigation Pressing NAV1, NAV2, DME, (16) or MRK (2) selects each audio source. A second button press deselects t he audio. Speaker Output Pressing the SPKR button (12) selectsthe aircraft radios over the cabin speaker.
  • Page 314 PA.28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION (continued) Marker Beacon Receiver 340’smarker beacon receiver controlsare locatedon the left sideof The GMA the front panel (1 4). The SENS button selects either high or low sensitivity sensitivity is used on ILS as indicated by the HI or LO LED being lit.
  • Page 315 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. (24L4 APPROVED: L. MARSH CHRISTINA D.O.A. NO. SO- 1 THE NEW PIPER AIRCRAFr, INC. VERO FLORiDA BEACH, September 14. 2000 DATE OF APPROVAL: REPORT:...
  • Page 316 PA-28R-201, ARROW SUPPLEMENT 1- GENERAL SECTION The S-TEC DME-450 system is a full feature, solid state, remote mounted system with full200 channel capability. For long distance operation, it provides a full100 wattsmaximum pulse power transmitter o utput. The IND-450 indicator (see figure 1) provides selectable read-outof distance to/fromthe station, g round speed, and time to/from the station.
  • Page 317 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 6- WEIGHT 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 AN]) OPERATION IND-450 Figure 1 1.
  • Page 318 PA-28R-201. ARROW SUPPLEMENT 7- DESCRIPTION OPERATION (continued) power on or off. Turns DME 4. DME ON/OFF SWiTCH HOLD NAV2 NAVI SELECT Selector Switch Mode Figure 2 5. DME SELECTOR SWiTCH 2) Selects MODE 1, HOLD, (NAY operating mode as follows: Selects DME operation with NO.
  • Page 319 SECTION PA-28R-201, ARROW SUPPLEMENT PILOT’S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO.12 S-TEC SYSTEM 55 TWO AXIS AUTOMATIC FLIGHT GUIDANCE SYSTEM The FAA approved operationalsupplement for the S-TEC System 55 Autopilot, installed i n accordance with STC is required for SAO9I29AC-D, willbe responsible to supply and revisethe operation of this system.
  • Page 320 PA-28R-201, ARROW SUPPLEMENT THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12,1995 9-74 REVISED: SEPTEMBER 14,2000 Page: 9-74-(0) Revision: 5, SEPTEMBER 14, 2000 9-74...
  • Page 321 SECTION PA-28R-201, ARROW SUPPLEMENT PILOT’S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO.13 S-TEC SYSTEM SSX TWO AXIS AUTOMATIC FLIGHT GUIDANCE SYSTEM The FAA approved operational supplement for the S-TEC System 55X Autopilot, installed i n accordance with STC SAO9129AC-D, is required for operation of this system.
  • Page 322 PA-28R-201, ARROW SUPPLEMENT LEFT BLANK THIS PAGE INTENTIONALLY REPORT: VB-1612 ISSUED: 12, 1995 JULY REVISED: 2000 DECEMBER21, Page: 9-76-(0) Revision: 6, DECEMBER 21, 2000 9-76...
  • Page 323 S-TEC CORPORATION MiNERAL TEXAS 76067 WELLS, FAA/DAS APPROVED PILOT’S OPERATING HANDBOOK AND/OR AIRPLANE FLIGHT MANUAL SUPPLEMENT PIPER MODELS PA-28R-201 AND PA-28R-201T WITH S-TEC SYSTEM 55155X TWO AXIS AUTOMATIC FLIGHT GUIDANCE SYSTEM WITH TRIM MONITOR (14 Volt System) KEG. NO. N30645 SER.NO.
  • Page 324 CORPORATION MINERAL TEXAS 76067 WELLS, FAA/DAS APPROVED PILOTS OPERATING HANDBOOK AND/OR AIRPLANE FLIGHT MANUAL SUPPLEMENT Piper models PA-28R-201 and PA-28R-201T OF REVISIONS REV. PAGES AFFECTED DESCRIPTION APPROVED DATE Added 1,3, 5, 10, System 11, 12 information. Removed Optional Equipment Section.
  • Page 325 APPROVED PILOT’S OPERATING HANDBOOK AND/OR AIRPLANE FLIGHT MANUAL SUPPLEMENT Piper models PA-28R-201 and PA-28R-201T SECTION OPERATiNG LIMITATIONS Autopilotoperation not authorizedabove 165 KIAS. Flap extension limited to two (2) notches (25°) or less during autopilot operations. Go around or missed approach maneuvers not authorized during autopilot operation.
  • Page 326 SUPPLEMENT AIRPLANE FLIGHT MANUAL and PA-28R-201T Piper models PA-28R-201 The autopilot may be disconnected by: Depressing the “AP Disconnect” Switch on the left horn of the pilot’s controlwheel. Placing the “AP Master Switch” in the “OFF” position. Momentarily interrupting aircraft electrical p ower at the battery master switch.
  • Page 327 FAA/DAS APPROVED PILOT’S OPERATING HANDBOOK AND/OR AIRPLANE FLIGHT MANUAL SUPPLEMENT Piper models PA-28R-201 and PA-28R-2OlT following altitudelosses and bank angles were recorded after a malfunction with a 1 second recovery delay: Bank Angle/Altitude Loss Configuration 18°/-40’ Maneuvering Approach (Coupled or 20°/-20’...
  • Page 328 WELLS, FAAJDAS APPROVED PILOT’S OPERATING HANDBOOK AND/OR FLIGHT AIRPLANE MANUAL SUPPLEMENT Piper models PA-28R-201 and PA-28R-201T CONTROL WHEEL SWITCHES The left grip of the pilot’s controlwheel will normally containthe following autopilot switches: Manual Electric Trim • Trim Interrupt/A/P Disconnect Switch •...
  • Page 329 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 ELEV, TRIM TRIM TRIM INTRPT _______ JELfi PUSH ON/OFF HORN {ICO FIGURE SYSTEM...
  • Page 330 HANDBOOK AND/OR MANUAL SUPPLEMENT AIRPLANE FLIGHT Piper models PA-28R-20l and PA-28R-201T A/P master switch ON Check that Operate trim switch (both knob sections) NOSE trim moves nose down and yellow trim light in trim master switch flashes while trim is in motion. The trim“in motion” indicator in the autopilot programmer should flash“TRIM”...
  • Page 331 OPERATING HANDBOOK AND/OR AIRPLANE FLIGHT MANUAL SUPPLEMENT Piper models PA-28R-201 and PA-28R-201T willdisconnectA/P only when a pitch mode is engaged.) and ALT modes Presstrim interrupt/AP Reengage autopilot HDG disconnect switch Autopilot should disconnect: Retrim aircraft f ortake off Check all controlsforfreedom of motion and determine that autopilot and trim have disconnected.
  • Page 332 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. But in any case, the aircraft should be configured and stabilizedin altitude hold mode before reaching glideslope intercept, for optimum results.
  • Page 333 FAA/DAS APPROVED PILOT’S OPERATING HANDBOOK AND/OR AIRPLANE FLIGHT MANUAL SUPPLEMENT Piper models PA-28R-201 and PA-28R-201T SECTION SUPPLEMENTS Refer to contents of this supplement for operation for System 55/55X Automatic Flight Control System. SECTION OPERATING TIPS The textof thisSectionnot affected by installation of this equipment.
  • Page 334 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: J.MILL ALBERT D.O.A. NO. SO-i INC. PIPER AIRCRAFT, VERO FLORIDA BEACH, 20, 2001 DECEMBER DATE OF APPROVAL: VB-1612...
  • Page 335 PA-28R-201, ARROW SECTION 1- GENERAL This supplement supplies information necessary for the operation of the airplane when the S-TEC ADF-650D System is installed in accordance with FAA approved Piper data. SECTION LIMITATIONS No change. SECTION 3- EMERGENCY PROCEDURES No change.
  • Page 336 SECTION PA-28R-201, ARROW SUPPLEMENT 4- NORMAL SECTION PROCEDURES To turn on theADF-650D System: • button momentarily and release. Depress the PWR NOTE Ifthe PWR button is pressed for longer than 3 seconds, the receiver will immediately shutoff. • After successful self test, i nput desiredstation frequency and select ANT mode.
  • Page 337 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 4- NORMAL PROCEDURES (continued) To perform the preflight checklist and self test: • After successful self test, p ress the mode controluntil ANT is displayed and input a predeterminedfrequency to select a station in the immediate area.
  • Page 338 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION The S-TEC ADF-650D System operates over a frequencyrange of 200 through 1799 kHz in 1-kHz increments. Three operating modes areincluded as part of theADF-650D System. • BFO • ADF • ANT VOLUME MODE FUNCTION CONTROL...
  • Page 339 SECTION SUPPLEMENT PA-28R-201, ARROW 7- DESCRIPTION SECTION OPERATION (continued) Automatic DirectionFinder (ADF) Mode Automatic Direction Finder mode uses conventional (ADF) nondirectionalbeacons and AM broadcaststations f or navigation. This mode activates the bearing pointer. The bearingpointer will point inthedirection of thestation r elative t o the aircraft heading. Antenna (ANT) Mode The ANT (antenna) mode cannot be used for navigation;...
  • Page 340 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION (continued) Clear (CLR) The clearfunctionoffers several options forthe operator. • If the entire frequency isenteredand the CLR buttonis pushed, allthe numbers willbecome dashes. An additional push on the CLR buttonwill restore and display the priorfrequencyentry. •...
  • Page 341 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION 7- DESCRIPTION OPERATION (continued) Function (FUNC) Selector The functionselector enablesthe user to select between contrast and volume display functions (on power-up, the RCR-650D willbe in thevolume display function). The first t ime thefunction selector is pressed, thereceiver entersthe contrast function.
  • Page 342 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION (continued) Function (FUNC) Selector continued Keypad Light Brightness 21iI1 The keypad light brightness setting isused to adjust the brightness of all legends on the display face. When the display is setup inthemanual mode, press the FUNC selector until the keypad function isselected.
  • Page 343 SECTION PA-28R-201, ARROW SUPPLEMENT OPERATION SECTION 7- DESCRIPTION (continued) Test Mode OMHzTESr] Press the TEST button to start the testmode. The text“TEST” will be displayed in the bottom right corner of the display for approximately 15 seconds. During this time, the IND-650A Indicator pointer will incrementally rotate PresstheTEST button again tocancelthetest while...
  • Page 344 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: J.MILL ALBERT D.O.A. NO. SO INC. PIPER AIRCRAFT, FLORIDA VERO BEACH, January 5, 2004 OF APPROVAL: DATE REPORT: VB-1612 12, 1995...
  • Page 345 This supplement supplies information necessary forthe operation of the airplane 330 Transponder is installed i n accordance with FAA when the Garmin GTX approved Piper data. SECTION 2- LIMITATIONS A. Display of TIS traffic i nformationis advisoryonly and does not relieve the Aircraft maneuvers shall pilot responsibility to “seeand avoid”...
  • Page 346 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 4- NORMAL PROCEDURES BEFORE TAKEOFF: • To transmitMode C (Altitude Reporting) code in flight: • Mode Selection • Code Selector SELECT assigned code. Keys To transmit Mode A (Aircraft I dentification) code in flight: • Mode Selector •...
  • Page 347 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 5- PERFORMANCE No change. SECTION 6- WEIGHT BALANCE Factory installed optionalequipment is included in the licensed weight and balance datain section 6 of the AirplaneFlight Manual. SECTION 7- DESCRIPTION OPERATION See the 400/500 SeriesGarmin Display Interfaces (Pilot’s Guide Addendum), P/N 190-00140-13, and GTX 330 Pilot’s Guide, P/N 190-00207-00, for a complete description of the GTX...
  • Page 348 Manual consultthe Pilot’s performance information not contained in this supplement, and FAA Approved Airplane Flight Manual. Operating Handbook FAA APPROVED: LINDA J.DICKEN DOA-5 10620-CE INC. PIPER AIRCRAFT, FLORIDA VERO BEACH, 7, 2004 OCTOBER DATE OF APPROVAL: VB-1612 REPORT: 12, 1995...
  • Page 349 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION 1- GENERAL This airplane is equipped with the Avidyne FlightMax Entegra EXP5000 series Primary FlightDisplay with softwareto the latest approved 700-00006-OXX-( revision per Avidyne web siteand EX5000 series 700-00004-OXX-( Multi- Function Display with software to the latest approved revision per Avidyne web site, h ereinreferred to as the “PFD”...
  • Page 350 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION GENERAL (continued) The MFD is intendedto be a supplemental display of situational and navigation information to the pilot. Its primary function isto provide a moving map display to the pilot forincreasedsituational awareness.The MFD is capable of accepting data from a variety of GPS sensors, the BFG WX-500...
  • Page 351 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 2- LIMITATIONS A. PFD Limitations I. IFR flight is prohibited when the PFD or any standby instrument is inoperative (altimeter, airspeed indicator, a rtificial horizon, or whiskey compass). 2. IFR flight is prohibited upon aircraft totalloss of essential engine parameter display (manifold pressure, tachometer, fuel flow).
  • Page 352 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION LIMITATIONS (continued) B. MFD Limitations (continued) 4. Aircraft dispatch is prohibited when the MFD is inoperative. 5. Selecting“Lightning Display OFF” forthe Lightningoverlay of the Map page will prevent current heading values from being sent to the WX500 sensor from the EX5000.
  • Page 353 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION LIMITATIONS (continued) C. CMAX CHART PAGE Limitations The geographic referencedaircraft symbol must not be used for navigation. NOTE The aircraft symbol displayed provides supplemental aircraft s ituational a wareness information. Itisnot intended as a means for navigation or flight guidance. The airplane is not to be used for conducting instrument symbol approaches or departures.
  • Page 354 SECTION PA-28R-201, ARROW SUPPLEMENT THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: 12, 1995 JULY 7 of 30, 9-95 9, 2006 REVISED: JANUARY Page: 9-95-(0) Revision: 16, JANUARY 9, 2006 9-95...
  • Page 355 S1CI1(JIN 9 PA-28R-201, ARROW SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES Failure of Pilot’s ElectronicAttitude 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 establish the aircraft i n straight and levelunaccelerated flight.
  • Page 356 SECTION PA-28R-201, ARROW SUPPLEMENT 3- EMERGENCY SECTION 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. InvalidAir Data Indication: Airspeed, Altimeter, and Vertical Speed data replaced with Red X’s.
  • Page 357 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION 3- EMERGENCY PROCEDURES (continued) InvalidAttitude and Heading Data Indication:Attitude and Heading Data removed and replaced with Red X’s. Standby Attitude Gyro VERIFY ON and flag is pulled on gyro. Maintain attitude c ontrol using standby gyro. If time and conditions permit: PFD CircuitBreaker PULL...
  • Page 358 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES (continued) Failure of Attitude,Airspeed and Heading Reference System (ADAHRS) Indication: Airspeed, Altitude replaced with Attitude, Heading Red X’s. Standby Attitude Gyro VERIFY ON and flag is pulled on gyro Maintain attitude control using standby gyro. If time and conditions permit: PFD CircuitBreaker PULL...
  • Page 359 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES (continued) Cross Check Monitor on PFD. Attitude Annunciator Indication:Yellow Crosscheck Establishaircraft i n straight and levelunaccelerated flight. Crosscheck aircraft a ttitude Aircraft Attitude with standby attitude gyro Total Loss of Engine Instruments Indication:Indicator needle removed from dial and...
  • Page 360 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES (continued) Alternator Failure Indication:Alternator annunciator light illuminated zero alternator indication source. current displayed on MFD NOTE Anytime the bus voltage is below 25 Vdc, the Low Voltage annunciatorwillbe illuminated. Check ammeter Verify Failure shows zero: If ammeter ALTR...
  • Page 361 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES (continued) Alternator Failure (continued) If power is not restored: ALTR Switch Reduce electrical loads by switching OFF or pulling circuit breakers for all non-essential equipment to includethe following: • Reduce PFD and MFD brightness as part of overallelectrical system management •...
  • Page 362 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES (continued) Complete Electrical Failure SELECT Standby (STBY) power button Standby Attitude Gyro CAUTION annunciator will rapidly flash for STBY approximately one minute when aircraft power is lost. must be selected, otherwise the gyro willauto STBY shutdown after approximately one minute.
  • Page 363 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES (continued) Fire in Flight Electrical Fire Fire Extinguish Standby Attitude Gyro VERIFY ON and flag is pulled on gyro Maintain aircraft c ontrolwith referenceto the standby airspeed, altimeter, and attitude gyro indicators. Battery Master Switch ALTR Switch...
  • Page 364 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES (continued) Aircraft Engine Power Loss During an engine failure the pilot may electto attempt an engine restart. During thistime largevoltagedrops may cause the PFD to lose power and reinitialize. During thisinitialization process the PFD may not be able to complete a fast alignment during flight and thereforethe pilotmay have to obtain aircraft attitude a nd aircraft c ontrol using the standby instruments.
  • Page 365 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION 3- EMERGENCY PROCEDURES (continued) Loss of Heading Accuracy Indication: Difficulty m aintaining course while using VOR or GPS. • Excessive differencebetween heading and track required maintaining a or GPS course. • ATC indicates the aircraft i s on a wrong heading.
  • Page 366 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 4- NORMAL PROCEDURES Engine Start General CAUTION Do not attempt flight if thereis 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.In cold weather it will take a few seconds longer to get a positive oil pressure indication.
  • Page 367 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION 4- NORMAL PROCEDURES (continued) Normal Start Cold Engine Throttle ½ inch open Battery Master Switch Verify correctaircraft Primary FlightDisplay (PFD) model software Alternator Switch Electric Fuel Pump Mixture Prime then idle cut-off CLEAR Propeller Starter ENGAGE Mixture FullRICH...
  • Page 368 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 4- NORMAL PROCEDURES (continued) Engine Start When Flooded Throttle Open full Battery Master Switch Verify correctaircraft Primary FlightDisplay (PFD) model software AlternatorSwitch Electric Fuel Pump Mixture Idlecut-off CLEAR Propeller Starter ENGAGE Mixture Fullrich RETARD Throttle Oil Pressure CHECK VB-1612...
  • Page 369 SECTION 9 PA 28R 2O1 ARROW F 16 SUPPLEMEN 4- NORMAL PROCEDURES coñtinued) SECTION Starting With External Power Source CAUTION Itis 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 increasethe amperage.
  • Page 370 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION A. PFD Systems Description NOTE This supplement provides a general description of the FlightMax Entegra Series 700-00006-OXX-( Avidyne PFD, its operation, and aircraft systems interfaces. F or a detailed description of PFD operation, referto the Avidyne FlightMax Entegra Series Primary Flight Display Pilot’s Guide, p/n 600-00104-000 revision00 or appropriate later revision, or 600-00143-000 revision 01 (EXP 5000 R6) or...
  • Page 371 PA-28R-201, ARROW SUPPLEMENT 7- DESCRIPTION OPERATION SECTION (continued) A. PFD Systems Description (continued) Horizontal SituationIndicator (HSI) Heading Data Magnetic heading is represented in a boxed digital form at the top of the compass rose. Heading rate (Rate of Turn Indicator) takes the form of a blue arcing arrow that begins behind the magnetic heading indicator and moves left or rightaccordingly.
  • Page 372 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION (continued) A. PFD Systems Description (continued) Autopilot Integration The Entegra PFD is fullyintegrated with the S-TEC System 55X Autopilot. Reference bugs for Heading, Altitude, and Vertical Speed are provided on the PFD to control the autopilot and aid pilot situational awareness.These bugs are displayed with solidor hollow symbology depending on the autopilot status.
  • Page 373 SECTION PA-28R-201, ARROW SUPPLEMENT 7- DESCRIPTION OPERATION (continued) SECTION A. PFD Systems Description (continued) Autopilot Integration (continued) The following autopilot modes are supported by the PFD: (Heading, using the heading bug) 1. HDG (Nay, using the course pointer and course deviation indicator) 2.
  • Page 374 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION (continued) A. PFD Systems Description (continued) Back-up Instruments The Entegra PFD system installation includes redundant means of display of certain aircraft flight and systems parameters. Back-up Altimeter,Airspeed and Attitude instruments are provided to facilitate pilot cross-checking of PFD display flightparameters.
  • Page 375 SECTION PA.28R..201, ARROW SUPPLEMENT SECTION 7. DESCRIPTION OPERATION (continued) B. MFD Systems Description NOTE This supplement provides a general description of the EX5000 Series 700-00004-OXX-( ) MFD, Avidyne operation and aircraft i nterface. For a detailed description of referto the Avidyne FlightMax EX5000 Series the MFD, Pilot’s Guide and Reference, p/n 600-00105-000 revision 00...
  • Page 376 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION 7- DESCRIPTION OPERATION (continued) B. MFD Systems Description (continued) Navigation (continued) Using the Jeppesen NavData data and the GPS-supplied present position, the can provide the pilot with the nearest25 airports or navaids, depending on pilot selection, within 100 nm. This information is presented on the Nearest page.
  • Page 377 r&iiiJr PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION (continued) B. MFD Systems Description (continued) Setup (continued) Airport Settings page provides selections for displayingairport type,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 changing display range.
  • Page 378 Page: 9-119-(0) Issued: JULY 12, 1995 9-119...
  • Page 379 For limitations, procedures and performance information not contained in this supplement, consultthe Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: LINDA J.DICKEN DOA-5 10620-CE PIPER AIRCRAFT, INC. VERO FLORIDA BEACH, 22. 2006 DATE OF APPROVAL: REPORT:...
  • Page 380 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION GENERAL This airplane is equipped with the Avidyne FlightMax Entegra EXP5000 series Primary FlightDisplay with software to the latest approved 700-00006-OXX-( revision per Avidyne web siteand EX5000 series 700-00004-OXX-( Multi- Function Display with software to the latest approved revision per Avidyne web Site, h ereinreferred to as the “PFD”...
  • Page 381 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION GENERAL (continued) The MFD is intended to be a supplemental display of situational and navigation informationto the pilot. Its primary functionisto provide a moving map display to the pilot forincreasedsituational awareness.The MFD is capable of accepting sensors, the BFG WX-500 data from a variety of GPS...
  • Page 382 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION GENERAL (continued) A B&C Specialties, BC4IO standby alternator, when ON, will replace the primary alternator function, but will not supplement its output. The alternator i s gear driven through the engine vacuum pump drive pad. The standby alternator i sratedfor20 amperes of maximum load.The actualload available for use is dependent on engine rpm and current operating conditions.
  • Page 383 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 2- LIMITATIONS A. PFD Limitations I. IFR flight is prohibited when the PFD or any standby instrument is inoperative(altimeter, a irspeed indicator, artificial horizon, or whiskey compass). 2. IFR flight is prohibited upon aircraft total loss of essential engine parameter display (manifold pressure, tachometer, fuel flow).
  • Page 384 SECTION PA-28R-201, ARROW SUPPLEMENT LIMITATIONS SECTION (continued) B. MFD Limitations (continued) 4. Aircraft dispatch is prohibited when the MFD is inoperative. 5. Selecting“LightningDisplay OFF” forthe Lightning overlay of the Map page will prevent current heading valuesfrom being sent to the WX500 sensor from the EX5000.
  • Page 385 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION LIMITATIONS (continued) C. CMAX CHART PAGE Limitations The geographic relèrencedaircraft symbol must not be used for navigation. NOTE aircraft symbol displayed provides supplemental aircraft s ituational awareness information. Itisnot intended as a means for navigation or flight guidance. The airplane is not to be used for conducting instrument symbol approaches or departures.
  • Page 386 SECTION FA-28R-201, ARROW SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES Failure of Pilot’s ElectronicAttitude Direction Display Screen (PFD) Indication:PFD Display goes blank. VERIFY ON and Standby Attitude Gyro flag is pulled on gyro Maintain attitude control using standby gyro and establish the aircraft i n straight and level unaccelerated flight.
  • Page 387 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES (continued) Loss of PFD Engine Data Indication:Indicator needle removed from dial and digital readout replaced with white dashes. Refer to Engine page of MFD Engine Instruments Land as soon as practical. Invalid Air Data Indication: Airspeed, Altimeter, and Vertical Speed data replaced with Red X’s.
  • Page 388 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION 3- EMERGENCY PROCEDURES (continued) InvalidAttitude 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 attitude c ontrol using standby gyro. If time and conditions permit: PFD CircuitBreaker PULL and RESET...
  • Page 389 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES (continued) Failure of Attitude, Airspeed and Heading Reference System (ADAHRS) Indication: Airspeed, Altitude replaced with Attitude, Heading Red X’s. VERIFY ON and Standby Attitude Gyro flag is pulled on gyro Maintain attitude c ontrol using standby gyro. If time and conditions permit: PULL and RESET...
  • Page 390 SECTION PA-28R-201, ARROW SUPPLEMENT 3- EMERGENCY PROCEDURES SECTION (continued) Cross Check Monitor on PFD. Attitude Annunciator Indication:Yellow Crosscheck Establishaircraft i n straight and levelunaccelerated flight. Crosscheck aircraft a ttitude Aircraft Attitude with standby attitude gyro Total Loss of Engine Instruments dial and digital readout Indication:Indicator needle removed...
  • Page 391 SECTION PA-28R-201, ARROW 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 interruptiongreater than 20 seconds will result in loss of attitude information from the PFD untilthe unit can be reinstated on the ground.
  • Page 392 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES (continued) ALTERNATOR FAILURE (continued) Failure of Standby Alternator If STBY ALTR ON is not illuminated: Day/Night Switch VERIFY correct position STBY ALTR STBY ALTR FIELD circuit breaker Check and resetas required STBY ALTR SENSE circuit breaker...
  • Page 393 SECTION SUPPLEMENT PA-28R-201, ARROW 3- EMERGENCY SECTION PROCEDURES (continued) ALTERNATOR FAILURE (continued) or pulling circuit breakers for all Reduce electrical loads by switching OFF non-essential equipment to include the following: • Reduce PFD and MFD brightness as part of overallelectrical system management •...
  • Page 394 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES (continued) ElectricalOverload (Alternator over 20 amps above known electrical load) ALTR BATT MASTR If alternatorloads are reduced: Reduce to minimum Electrical l oad NOTE Due to increased system voltage and radio frequency noise, switch ON and BATT MASTR switch...
  • Page 395 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES (continued) ElectricalOverload (Alternator over 20 amps above known electrical load) (continued) or pulling circuitbreakers for all Reduce electrical loads by switching OFF non-essential equipment to include the following: • Reduce PFD and MFD brightness as part of overall electrical system management •...
  • Page 396 SECTION PA-28R-201, ARROW SUPPLEMENT 3- EMERGENCY PROCEDURES SECTION (continued) Complete ElectricalFailure Standby (STBY) power button Standby Attitude Gyro SELECT CAUTION STBY annunciator will rapidly flash for approximately one minute when aircraft power is lost. STBY must be selected, otherwise the gyro willauto shutdown after approximately one minute.
  • Page 397 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES (continued) Fire in Flight Electrical Fire Fire Extinguish Battery Master Switch ALTR Switch STBY ALTR Switch SELECT Standby (STBY) power button Standby Attitude Gyro CAUTION annunciator will rapidly flash for STBY aircraft power is lost. approximately one minute when must be selected, otherwise the gyro will auto STBY...
  • Page 398 SECTION PA-28R-201, ARROW SUPPLEMENT 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. this time largevoltagedrops may cause the PFD may not be able to complete a fast During this initialization process the PFD have to obtain aircraft...
  • Page 399 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 3- EMERGENCY PROCEDURES (continued) Loss of Heading Accuracy Indication: • Difficulty maintaining course while using VOR or GPS. • Excessive differencebetween heading and track required maintaining a or GPS course. • ATC indicates the aircraft i son a wrong heading. •...
  • Page 400 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION 4- NORMAL PROCEDURES Engine Start General CAUTION Do not attempt flight if there is no indicationof primary alternator output. CAUTION If a positive oil pressure isnot indicatedwithin 30 seconds following an engine start, stop the engine and determine the trouble.In cold weather it will take a few seconds longer to get a positive oil pressure indication.
  • Page 401 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 4- NORMAL PROCEDURES (continued) Normal Start Cold Engine Throttle ½ inch open Battery Master Switch Verify correctaircraft Primary FlightDisplay (PFD) model software AlternatorSwitch Standby AlternatorSwitch Electric Fuel Pump Mixture RICH then IDLE CUT-OFF CLEAR Propeller Starter ENGAGE Mixture...
  • Page 402 SECTION SUPPLEMENT PA-28R-201, ARROW 4- NORMAL SECTION PROCEDURES (continued) Engine Start When Flooded Throttlu Open full Battery Master Switch Verify correctaircraft Primary FlightDisplay (PFD) model software Alternator Switch Standby AlternatorSwitch Electric Fuel Pump Mixture IDLE CUT-OFF CLEAR Propeller Starter ENGAGE Mixture Full rich Throttle...
  • Page 403 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 4- NORMAL PROCEDURES (continued) Starting With External Power Source CAUTION Itis possible to use the ship’sbattery 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 ifthe ship’s battery has been depleted, the external power supply can be reduced to the levelof the ship’sbattery.
  • Page 404 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION 4- NORMAL PROCEDURES (continued) Ground Check Throttle 2300 RPM ALTR switch STBY ALTR switch ALTR STBY ON annunciator verify ON Increaseelectrical load to over 20 amps. STBY ALTR annunciator verify flashing Decrease electrical load to lessthan 20 amps. STBY ALTR annunciator...
  • Page 405 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION A. PFD Systems Description NOTE This supplement provides a general description of the FlightMax Entegra Series 700-00006-OXX-( Avidyne PFD, its operation, and aircraft systems interfaces. F or a detailed description of PFD operation, referto the Avidyne FlightMax Entegra Series Primary Flight Display Pilot’s Guide, p/n 600-00104-000 revision00 or appropriate later revision, or 600-00143-000 revision01 (EXP 5000 R6) or...
  • Page 406 SECTION PA-28R-201, ARROW SUPPLEMENT OPERATION SECTION 7- DESCRIPTION (continued) A. PFD Systems Description (continued) Horizontal Situation Indicator (HSI) Heading Data Magnetic heading is represented in a boxed digital form at the top of the compass rose. Heading rate (Rate of Turn Indicator) takes the form of a blue arcing arrow that begins behind the magnetic heading indicator and moves left or rightaccordingly.
  • Page 407 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION (continued) A. PFD Systems Description (continued) Autopilot Integration The Entegra PFD is fullyintegrated with the S-TEC System 55X Autopilot. Reference bugs for Heading, Altitude, and Vertical Speed are provided on the PFD to controlthe autopilot and aid pilot situational awareness. These bugs are displayed with solidor hollow symbology depending on the autopilot status.
  • Page 408 SECTION PA-28R-201, ARROW SUPPLEMENT 7- DESCRIPTION OPERATION SECTION (continued) A. PFD Systems Description (continued) Autopilot Integration (continued) The following autopilot modes are supported by the PFD: 1. HDG (Heading, using the heading bug) 2. NAV (Nay, using the course pointer and course deviation indicator) 3.
  • Page 409 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION (continued) A. PFD Systems Description (continued) Engine Instruments The Entegra PFD provides a display of Engine Manifold Pressure, Tachometer (RPM), Oil Pressure (OP), and Fuel Flow (FF) in the upper left hand corner of the display.
  • Page 410 SECTION PA-28R-201, ARROW SUPPLEMENT OPERATION SECTION 7- DESCRIPTION (continued) B. MFD Systems Description NOTE This supplement provides a general description of the EX5000 Series 700-00004-OXX-( MFD, Avidyne operation and aircraft i nterface. For a detailed description of refer to the Avidyne FlightMax EX5000 Series the MFD, Pilot’s G uide and Reference, p/n 600-00105-000 revision 00...
  • Page 411 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION (continued) B. MFD Systems Description (continued) Navigation (continued) Using the Jeppesen NavData data and the GPS-supplied present position, the can provide the pilot with the nearest25 airports or navaids, depending on pilot selection, within 100 nm. This information is presented on the Nearest page.
  • Page 412 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION 7- DESCRIPTION OPERATION (continued) B. MFD Systems Description (continued) Setup (continued) Airport Settings page provides selections for displayingairporttype,runway surface type and minimum runway lengths on the moving map. Declutter Settingspage allows the pilot to select settings for defining the base map detail when changing display range.
  • Page 413 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION (continued) C. STANDBY ALTERNATOR System Description The B&C Specialty Products Standby Alternator system deliverselectrical power to the aircraft e lectrical power bus in the event of failure of the primary alternator. Powering the bus allows the pilotflexibility to choose equipment suitable to the current flight conditions.
  • Page 414 SECTION PA-28R-201, ARROW SUPPLEMENT LEFT BLANK THIS PAGE INTENTIONALLY REPORT: VB-1612 ISSUED: 12, 1995 JULY 36 of 36 REVISED: 22, 2006 9-158, Page: 9-158-(0) Revision: 18, MAY 22, 2006 9-158...
  • Page 415 For limitations, procedures and performance information not contained in this supplement, consultthePilot’s Operating Handbook and FAA Approved AirplaneFlight Manual. FAA APPROVED: Albef’t J .Mill DOA-5 10620-CE Piper Aircraft, Inc. Vero Beach, Florida DATE OF APPROVAL: January 21. 2009 12, 1995...
  • Page 416 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION 1- GENERAL The Bendix/King Digital ADF is a panel mounted, digitally t uned, automatic direction f inder. Itis designed to provide Continuous 1 kHz digital tuning in the frequencyrange of 200 kHz to 1799 kHz and eliminates the need formechanical band switching.
  • Page 417 SECTION PA-28R-201, ARROW SUPPLEMENT 4- NORMAL SECTION PROCEDURES To Operate as an Automatic DirectionFinder: 1. OFF/VOL Control ON. desired frequency in the standby 2. Frequency SelectorKnobs SELECT frequencydisplay. 3. FRQ Button PRESS to move the desired frequency from the standby to theactive position.
  • Page 418 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION 4- NORMAL PROCEDURES (continued) NOTE The Standby Frequency which isin memory while Flight Time or Elapsed Time modes are being displayed may be called back by pressing the FRQ button, then transferred t o activeuse by pressing the FRQ button again.
  • Page 419 SECTION PA-28R-201, ARROW SUPPLEMENT 4- NORMAL SECTION PROCEDURES (continued) Operation NOTES: Erroneous ADF Bearing Due to Radio Frequency Phenomena: In the U.S., the FCC, which assigns AM radio frequencies, o ccasionally will assign thesame frequency tomore thanone station in an area. Certain conditions, such as Night Effect, may cause signals from such stations to overlap.
  • Page 420 SECTION SUPPLEMENT PA-28R-201, ARROW 5- PERFORMANCE SECTION No change. SECTION 6- WEIGHT BALANCE Factory installed optionalequipment is included in the licensed weight and balance datain Section6 of the Pilot’s Operating Handbook and AirplaneFlight Manual. 12, 1995 ISSUED: VB-1612 JULY REPORT: 21, 2009 REVISED: JANUARY...
  • Page 421 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION KR-87 Digital ADF KI-227 Indicator Operating Controls and Indicators King Digital ADF Figure 1 REPORT: VB-1612 12, 1995 ISSUED: JULY 21, 2009 REVISED: 9-165 JANUARY Page7ofl0 Page: 9-165-(0) Revision: 19, JANUARY 21, 2009 9-165...
  • Page 422 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION 7- DESCRIPTION OPERATION (continued) Figure 1 Legend 1. Mode Annunciation Antenna (AN1D isselected by the “out” position of the ADF button.This mode improves the aural reception and is usually used forstation identification. The bearingpointer isdeactivated and will park in the relative position.
  • Page 423 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 7- DESCRIPTION OPERATION (continued) Figure 1 (continued) Legend 6. Timer Mode Annunciation Eitherthe elapsed time (ET) or flight time (FLT) mode isannunciatedhere. 7. Frequency SelectorKnobs Selectsthe standby frequency when FRO is displayed and directly selects the active frequency whenever either of the timerfunctions is selected.
  • Page 424 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION 7- DESCRIPTION OPERATION (continued) Figure 1 (continued) Legend 15.Pointer Indicates station bearing in degrees of azimuth, relative t o the nose of the aircraft. When heading controlis adjusted, indicates r elative, magnetic, or true bearing of radio signal. 16.
  • Page 425 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: A1bextJ.Mill DOA-5 10620-CE Piper Aircraft, I nc. Vero Beach, Florida January 21, 2009 DATE OF APPROVAL: REPORT: VB-1612 ISSUED:...
  • Page 426 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION 1- GENERAL The Bendix/King KN-63 supplies continuous slant range distance informationfrom a fixed ground station to an aircraft i n flight. The equipment consistsof a KDI-572 Panel Display which contains all the operating controlsand displays, and a remotely mounted KN-63 Receiver- Transmitter.
  • Page 427 SECTION PA-28R-201, ARROW SUPPLEMENT 7- DESCRIPTION SECTION OPERATION E/JI Bendix/King KN-63 DME Figure 1 Figure 1 Legend 1. DISTANCE distance to VORTAC/WAYPOINT DISPLAY (NM) displayed in .1 nautical mile increments up to 99.9 NM, then in increments of one nautical mile to 389 NM. 2.
  • Page 428 SECTION PA-28R-201, ARROW SUPPLEMENT 7- DESCRIPTION SECTION OPERATION (continued) Figure 1 (continued) Legend 6. DME MODE SELECTOR SWITCH (OFF, Ni, HLD, Applies power to theDME and selects DME operating mode as follows: Turns DME power off. OFF: NAV1 operation with No. i VHF navigation set;...
  • Page 429 Pilot’s Operating Handbook and FAA consult Approved Airplane Flight Manual. APPROVED: Wayne E. Gaulzetti ODA-5 10620-CE Piper Aircraft, I nc. Vero Beach, Florida 12, 2010 OF APPROVAL: DATE REPORT: VB-1612 12, 1995 ISSUED: JULY •...
  • Page 430 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION 1- GENERAL System isa fullyintegrated, panel mounted instrument, which The GNS43OW Transceiver, a VOR/ILS receiver, and a contains a VHF Communications Global PositioningSystem (GPS) Navigation computer. The WAAS—enabled antenna, GPS/WAAS receiver, VHF VOR/LOC/GS system consistsof a GPS COMM antenna VOR/ILS...
  • Page 431 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 1- GENERAL (continued) Class II Oceanic, Remote, and other operations The Garmin 430W has been found to comply with the requirements for GPS primary means of Class II navigation in oceanic and remote airspace when used in conjunction with Garmin Prediction Program part number 006-A0 154- 03.
  • Page 432 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION 2- LIMITATIONS Pilot’s Guide The Garmin 400W SeriesPilot’s Guide, part number and revisionlisted below (or later revisions), must be immediately available forthe flight crew whenever whenever navigation is predicated on the use of the GNS43OW unit.
  • Page 433 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION LIMITATIONS (continued) Navigation Data Base (continued) GPS instrument approaches using the GNS43OW are prohibited, unlessthe GNS43OW’s approach data is verified by the pilot or crew to be current. Instrument approaches must be accomplished in accordance with an instrument approach that is loaded from approved...
  • Page 434 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION LIMITATIONS (continued) Terrain Data Base The GNS43OW supports Terrain and requires a Terrain database card to be installed i n order for the featureto operate. The tablebelow lists compatible database cards for the GNS43OW. Each of the database cards contains the following data: •...
  • Page 435 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION LIMITATIONS (continued) Approaches • During GPS approaches, the pilot must verify the GNS43OW unit is operating in the approach mode. (LNAV, LNAV+V or LPV.) L/VNAV • When conducting approaches referencedto true North, the heading selection selection on the AUX pages must be adjusted to TRUE.
  • Page 436 SECTION SUPPLEMENT PA-28R-201, ARROW SECTION 3- EMERGENCY PROCEDURES Procedures Emergency No change. Abnormal Procedures IftheGarmin GNS430W GPS navigation informationisnot available, or is invalid, utilize other remaining operational navigationequipment installed in the airplane as appropriate, If the430W losesOPS position and reverts to Dead Reckoning mode (indicated by the annunciation of “DR”...
  • Page 437 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 4- NORMAL PROCEDURES Refer to the400W Series unitPilot’s Guide defined in Section2 Limitations of this supplement for normal operating procedures. This includes allGPS and NAV, and Multi-Function Display (optional) information. operations, VHF information. Although intuitive a nd user friendly, the GNS43OW requires a reasonable degree of familiarity to prevent Operations without becoming too engrossed at the expense of basic instrument flying in IMC...
  • Page 438 A AJL PA-28R-201, ARROW SUPPLEMENT SECTION 4- NORMAL PROCEDURES (continued) Autopilot Operation 55X Autopilot when The Garmin GNS43OW may 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 55X Autopilot may Steering in lieuof the analog deviationinformation.
  • Page 439 SECTION PA-28R-201, ARROW SUPPLEMENT SECTION 4- NORMAL PROCEDURES (continued) WFDE Prediction Program Garmin WAAS Fault Detection and Exclusion (WFDE) Prediction Program is required forRemote/Oceanic operations. should be used in conjunction with the Garmin The Prediction Program Simulator.After entering the intended route of flight in the 400W/500W Prediction Program under the Simulator flight plan, the pilot selectsthe FDE...
  • Page 440 SECTION SUPPLEMENT PA-28R-201, ARROW INTENTIONALLY LEFT BLANK THIS PAGE 12, 1995 ISSUED: REPORT: VB-1612 JULY REVISED: 12,2010 9-184 Page 12 of 12 Page: 9-184-(0) Revision: 22, MAY 12, 2010 9-184...
  • Page 441 SECTION ARROW SUPPLEMENT PA-28R-201, HANDBOOK PILOT’S OIERATING APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO.22 GARMIN G500 PRIMARY FLIGHT MULTIFUNCTION DISPLAY SYSTEM The FAA approved operationalsupplement for the Garmin G500 PFD/ System, installed in accordance with STC is required SAO2OI5SE-D, for operation of this system. Garmin will be responsible to supply and revise the operational supplement.
  • Page 442 SECTION PA-28R-201, ARROW SUPPLEMENT THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1612 ISSUED: JULY 12, 1995 9-186 REVISED: OCTOBER 24, 2011 Page: 9-186-(0) Revision: 24, OCTOBER 24, 2011 9-186...
  • Page 443 Airplane Flight Manual Supplement NoE-362-E forthe 3-Blade Constant Speed Propeller System MTV-1 2-B/I 80-17 installed on the Airplane (all Serial Numbers) PIPER PA28R-180 with 200 HP-Engine PA 28R-200 PIPER PIPER PA 28R-201 PIPER PA 28RT-201 available Mufflerconfigurations: 1. without muffler 2.
  • Page 444 Page 1of 4 Manual S upplement Airplane No.E-362 E Flight PA-28R-180 PA28R-2001 PA2BRT-201 (200HP), Edition Jan. 1 6,2004 Revision 2— April 21, 2006 This Manual S appternent to the aircraft: Flight belongs /4’E )‘ r7’ Aircraft registration SedaiNs.: Year of masufaclure: TCDS Na.
  • Page 445 2500 RPM and 2700 RPM red radialline at 2700 RPM Markings and placards concerning other propellers, are obsolete. According to Piper equipment list Propeller-Governor: MT-Propeller No. P-391 Propeller-Spinner: The aircraft may be operated without spinner as well.
  • Page 446 Page3of4 Airplane Flight Manual Supplement No. E-362 E PA-28R-i 80 (200HP), PA28R-2001-20 1, PA28RT-201 EditionJan. 16, 2004 5. PERFORMANCE Max. continous speed with MTV-12-B/180-17 2500 RPM propeller: Max take off speed (5 mm) with MTV-12-B/180-17 2700 RPM propeller: information given in the charts of the Original POHIAFM concerning take off performance (landing gear extended or retracted), time, distance and fuel consumption...
  • Page 447 Page4of4 ‘J Airplane Flight Manual Supplement No. E-362 E PA-28R-1 80 (200H P), 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) related to max. engine (%-performance max. take off weight...
  • Page 448 Nach -iolzig Flugzeug- att: alldampfer-Anlage uno Maschinenbau GmbH von: “SystemGomolzig” Höfen 84 a 5600 Wuppertal 2 PA28 606504 LBA Nr.: I-C 39, lI-A 226 Ausgabe: 02.93 Umrustanweisung Anhang Flughandbuch mit Nachschalldämpfer-Anlage”system PA28 606504 Gomoizig” Dieser Anhang zum Flughandbuch g ehört zum Flugzeug: Baureihe: Kennzeichen: Werk-Nr.:...
  • Page 449 fJifn AIRCRAFT FLIGHT MANUAL SUPPLEMENT Technology LARM FOCA APPROVED AIRCRAFT FLIGHT MANUAL SUPPLEMENT FLARM COLLISION WARNING DEVICE Aircraft Registration: AircraftMake: __________________________________ A-trov —20-1 Aircraft Model: Z’L414 AircraftSerial Number: 2.øU 00AO04 Approval Reference & Date: This document must be carriedin the aircraft a t all the times. It describes the operating procedures for a fixinstalled FLARM Collision Warning System and its interfacesin accordance withthe FLARM Installation FOCA...
  • Page 450 AIRCRAFT FLIGHT MANUAL SUPPLEMENT FLARM Technology OF CONTENTS TABLE SECTION GENERAL SECTION OPERATING LIMITATIONS SECTION EMERGENCY PROCEDURES SECTION NORMAL OPERATING PROCEDURES SECTION PERFORMANCE SECTION WEIGHT BALANCE SECTION SYSTEM DESCRIPTION OF REVISIONS REVISION Date FOCA Description Page AppyI,. Original release 15.03.2006 Original ““‘...
  • Page 451 AIRCRAFT FLIGHT MANUAL SUPPLEMENT Technology LARM —GENERAL SECTOONI The gliding scene has been confronted since years to dramatic mid air collision accidents.With the extreme fine shape and relatively high cruise speed of modern gliders, the human visionhas reached its limit of detection.Another aspect isthe airspace restrictions to VFR thatcreates an augmentation of traffic density in certainareas and the associated airspace complexity that request more pilot attention on the navigation material.These have a direct impact on the probability of collision a lso affectingpowered aircraft or rotorcraft...
  • Page 452 AIRCRAFT FLIGHT MANUAL SUPPLEMENT fffj MTechnolov SECTION OPERAfiNG UMITATONS 1. This FLARP installation is compliant for “situationawareness only”. The followingplacard must be installed on the instrumental panel, at the proximity of the display: For Situation Awareness only 2. Maneuvering must not be based solely on the use of the information presented on the FLARM displays or aural annunciations.
  • Page 453 MANUAL FLARM AIRCRAFT FLiGHT Technology SUPPLEMEJ SECTOON EMERGENCY PROCEDURES In case of Fire,Smoke, electrical burning smells or Electromagnetic Interferences followthe procedure of the basic AFM. Emergency FLARM is normally installed o n a non-essentialbus. But on ancient aircraft i tis possible that only an avionics bus or even only a main bus is available forall electrical consumers.
  • Page 454 FLIGHT MANUAL SUPPLEMENT FLARM AIRCRAFT Technology SEC11ON NORMAL OPERATING PROCEDURES 4.1 Genera Itisrecommended to carry the FLARM Operating Manual version 3 or later on board the aircraft. To make good use of the informationcontains in this manual the pilot should know the hardware version, the software version, the serial number and the obstacle database name currently installed inthe FLARM.
  • Page 455 4.5Line of sight Compatible FLARM unitsmust be within range in order to provide a warning. The range is very much determined by the type, installation and position of the radio antennae, plus the relative p ositions of the two aircraft. Under optimum conditionsthe internal antennae can give a head-on range of up to 5 km; normally, range isabout 2 km.

  • Page 456: System Description

    AIRCRAFT FLIGHT MANUAL SUPPLEMENT flAn Technology SECTION 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 FLARM receives position and movement informationfrom an internal GPS receiverwith an external GPS antenna.
  • Page 457 AIRCRAFT FLIGHT MANUAL FLARM Technology SUPPLEMENT1 7.3n-fIight softwarescheme 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 and with an ERP power of less than 10 mW (duty cycle 1%).
  • Page 458 SECTION PA-28R-201, ARkOW OPERATING TIPS TABLE OF CONTENTS SECTION OPERATING TIPS Paragraph Page 10.1 General 10-1 10-1 10.3 OperatingTips REPORT: VB-1612 ISSUED: 12, 1995 JULY 10-i Page: 10-0-(1) Issued: JULY 12, 1995 10-i...
  • Page 459 SECTION ARROW OPERATING PA-2R.201, TiUS PAGE INTENTIONALLY LEFT BLANK REPORT: VB4612 ISSUED: JULY 12, 1995 10-il Page: 10-0-(2) Issued: JULY 12, 1995 10-ii...
  • Page 460 SECTION PA-28R-201, AIROW OPERATING TIPS SECTION OPERATING TIPS 10.1 GENERAL This section provides operatingtips of particular value in the operation of theArrow. 10.3 OPERATING TIPS (a) Learn to trim for takeoffso that only a very light back pressure on thecontrol whee) is required tolift t he airplane offthe ground. under normal conditions.
  • Page 461 PA-28R-201, ARROW OPERAT[NG 10.3 OPERATING TIPS (continued) (g) The rudder pedals are suspended from a torque tube which extends across the fuselage. The pilot should become miiiar. with the proper positioning of his feet on the rudder pedals so as to avoid interferencewith the torque tube when moving the rudder pedals or operating the toebrakes.

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