Piper Cherokee Arrow II PA-28R-200 1973 Pilots Operating Manual
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Piper Cherokee Arrow II PA-28R-200 1973 Pilots Operating Manual

Piper Cherokee Arrow II PA-28R-200 1973 Pilots Operating Manual

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  • Page 2 Airplane Flight Manual approved by the FAA, the Airplane Flight Manual shall be the authority. A complete or partial replacement of this manual, Part No. 761 578, may be obtained only from Piper Customer Services. Published by Piper Aircraft Corporation...
  • Page 3 APPLICABILITY This manual is applicable to Piper Model PA-28R-200 aircraft having serial numbers commencing with 28R-7435001 through 28R-7635545. Contact Piper Customer Services for specific information on the application of this manual. WARNING INSPECTION, MAINTENANCE AND PARTS REQUIlU3MENTS FOR ALL NON-PIPER ARE N W INCLUDED IN THIS HANDBOOK.
  • Page 4 MANUAL PILOT'S OPERATING LOG OF REVISIONS Current Revisions to the PA-28R-200 Arrow I1 Pilot's Operating Manual, 761 578, issued July Description Date Oct. 29,1973 Added Rev. 1 Report: VB-549. Rev. 1 761 578 March 25,1974 Added PAC Approval Form. Rev. 2 761 578 Added Applicability and Item Original...
  • Page 5 MANUAI. LOG OF REVISIONS (cont) Revised Description Revision - - - Pages Added Cruising info; added Mixture Rev 3 (cont) Control Lock and Footnote; relocated Approach and L.anding infb. Added Approach and Landing infb; added Mixture Control Lock and Footnote; relocated Moorings and Weight and Balance infb.
  • Page 6 ARROW I1 THIS PAGE. INTENTIONALLY LEFT BLANK...
  • Page 7 ARROW PILOT'S OPERATING MANUAL LOG OF REVISIONS (cont) Revised Date Description Added info. from page 10-8. 10-9 Revised Service Bulletin info. Feb. 29,1984 Added including serial number. Revised fuel and oil info. Revised para. 2-21 Added Rev. 6 to Report: VB-560. Added Rev.
  • Page 8 OF REVISIONS (cont) Revised Description Revision Pages Revised Oil info. Moved Dimensions and Rev. 12 761 578 Landing Gear to page 1-4. Added page. Relocated Dimensions and Landing Gear from page 1-2. Revised Table of Contents. Revised Oil Requirements. Moved info.. to page 10-8.

  • Page 9: Table Of Contents

    TABLE OF CONTENTS GENERAL SPEClFlCATlONS DESCRIPTION AIRPLANE AND SYSTEMS EMERGENCY PROCEDURES F.A.A. APPROVED EMERGENCY PROCEDURES LOADING INSTRUCTIONS OPERATING INSTRUCTlONS OPERATING TIPS PERFORMANCE CHARTS HANDLING AND SI E WWCI N G...

  • Page 10: General Speclflcatlons

    GENERAL SPECIFlCATlONS Performance Weights Power Plant Baggage Dimensions ..........Landing Gear...
  • Page 11 SPECIFICATIONS PERFORMANCE Published figures are for standard airplanes flown at gross weight under standard conditions at sea level, unless otherwise stated. Performance for a specific airplane may vary from published figures depending upon the equipment installed, the condition of the engine, airplane and equipment, atmospheric conditions and piloting technique.
  • Page 12 ARROW Gmss Weight Obs) Maximum Useful Load (obs) POWER PLANT Engine (Lycoming) Propeller Bore (in) Displacement (cu. i n ) Compression Ratio Dry Weight (lbs) FUEL (AVGAS ONLY) gal.) Fuel, Aviation Grade (min octane) Oil Capacity Refer latest issue of Oil Specification Lycoming Instruction No.
  • Page 13 ARROW GENERAL SPECIFICATIONS ISSUED: JULY 1 3 , I973...
  • Page 14 ARROW Wmg Area (sq Wmg Loading per sq ft) Height (ft) Power Loading Obs per hp) LANDING GEAR Wheel Base (ft) Wheel Tread (ft) Nose M a i n Nose (four-ply rating) Main (four-ply rating) GENERAL SPECIFICATIONS ISSUED: JULY 30,1990...
  • Page 15 ..........Piper External Power...

  • Page 16: Airplane And Systems

    ARROW I1 AIRPLANE. AND SYSTEMS THE AIRPLANE composed entry and exit of tlie spacious interior Four individual seats allow individual comfort for extended cross-country flights Sound proofing has been built into the aircraft t o reduce fatigue and permit restful conversation. Simplicity of operation was designed into the aircraft to allow the aircraft t o operate in VFR or IFR conditions with unhurried en route planning AIRFRAME.

  • Page 17: Engine And Propeller

    ENGINE A N D PROPELLER Arrow I I int:orlinr:rtcs dry alltoniotivc type iliduction air iiltcr The aircraft is equipped with a Hartzell constant speed, controllable pitch propeller. The propeller control is located on the power quadrant between the throttle and mixture controls A mixture control lock* is provided to prevent activation of the mixture control instead of the pitch control, It is coristrtrctcd c~itirely of st;linless steel :,rid is oc111ipli1.d with dilnl muiflcrs...

  • Page 18: Landing Gear

    ARROW LANDING GEAR The Cherokee Arrow 11 is equipped with a retractable tricycle landing gear, wl~icli is selector switch on the instn~ment parlel to tlie left 01' the control quadrant. Tllc landing gear is retracted or extended in about seven seconds Also incorporated in tile system is a pressure sensing device whicll lowets tllc gear regardless of gear sclector position, depending upon airspeed and engine power (propeller slipstream).
  • Page 19 ARROW / + - MIXTURE CONTROL LOCK nor. 7536001 nnd up) Throttle Quadrant OVERRIDE LATCH Console 1974...
  • Page 20 ARROW FILTER LOW PRESSURE COWlROL, DOWN L ROY PRESSURE HEAD OU R S E U E E SIDE NOSE 6EAR HYDRAULIC CYLINDER Landing Gear Hydraulic Schematic AIRPLANE AND SYSTEMS ISSUED: JULY 13,1973...
  • Page 21 ARROW ll Two micro-switches in the throttle quadrant activate a warning horn and a red "Warning Gear tip and power reduced below approximately 14 inches of manifold pressure. Gear extended by back-up gear extender system but gear selector switch "UP," except at full throttle.
  • Page 22 ARROW I1 BRAKE HOUSING Main Wheel Assembly ISSUED: JULY 13,1973...

  • Page 23: Flight Controls

    ARROW 11 FLIGHT CONTROLS Dual fligllt controls are provided as standard equipment. A cable system provides actuation of the control surfaces when the flight controls are moved in their respective directions. The horizontal surface (stabilator) is of the flying tail design with a trim tablservo mounted on the trailing edge.

  • Page 24: Fuel System

    ARROW FUEL SYSTEM in each wing containing twenty-five ( 2 5 ) 1J.S. gallons, giving a total of 48 usable gallons. The tanks are attached to the leading edge of the wing with screws and are an integral part of the wing structure.
  • Page 25 ARROW AIRPLANE AND SYSTEMS ISSUED: JULY 13,1973...

  • Page 26: Electrical System

    ARROW 11 provisions :,re made to handle a complete complement of communication and navigational Standard electrical accessories i~lclude alternator, starter, electric fuel pump, stall warning indicator, ammeter, and annunciator panel*. The annunciator panel includes alternator and low oil pressure indicator lights. When the optional gyro system is installed, the annunciator panel aIso includes a low vacuum indicator determine when or if any necessary action is required.
  • Page 27 ARROW I1 1 through Alternator and Starter Schematic (Ser Nos. 743500 7435.33...
  • Page 28 ARROW...
  • Page 29 ARROW AIRPLANE SYSTEMS ISSUED: JUNE 18, 1974...
  • Page 30 ARROW AIRPLANE AND SYfXEhfS ISSUED: JULY 13,1973...
  • Page 31 ARROW Secondary power is provided by a 12-volt, 25..ampere hour battery ammeter will indicate the charging rate of the battery. As each electrical unit is switched on, the ampere value plus amperes for charging the battery will then show on the ammeter, indicating the alternator is fbnctioning properly.
  • Page 32 EXTREME CARE MUST BE EXERCISED TO LIMIT THE USE OF THIS MANUAL. TO APPLICABLE AIRCRAFT THIS MANUAL REVISED AS INDICATED BELOW OR SUBSEQUENTL.Y REVISED IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED BELOW WHEN APPROVED BY PIPER AIRCRAFT CORPORATION SUBSEQUENT REVISIONS SUPPLIED BY PlPER AIRCRAFT CORPORATION MUST BE PROPERLY INSERTED...
  • Page 33 ARROW THIS PACE INTENTIONALLY LEFT BLANK REPORT: VB-560 PAGE 3ii FAA APPROVED MAY 14,1973 MODEL: PA-28R-200...
  • Page 34 Added Item E., AutoControl IIIB to Supplements. Added Gear Light Warning to Item 4. (b); Relocated Items 4. (c) and 4. (d). Added Info from Page 3-7. Added Item E., Installation of Piper AutoControl IIIB. Added pages (AutoControl IIIB Supple- ment info added). Revised Section Title (Supplements to Optional Equipment);...
  • Page 35 ARROW Revised FAA Approved Revision Description and Revision Pages 3-24 Revised Item c (1) Ward Evans Added Lycoming 01-360-C1C6 Engine and McCauley Propeller; added Tach- ometer Green Arc for McCauley prop. Ward Evans Landing Gear Extension). Feb. 28, 1977 Revised item B. Ward Evans Feb.
  • Page 36 ARROW SECTION 1 LIMITATIONS The following limitations must be observed in the operation of this airplane: ENGINE Lycoming 10-360-CIC (Serial Nos. 28R-7435001 through 28R-7635516) Lycoming 10-360-C1C6 (Serial Nos 28R-7635517 and up) ENGINE LIMITS For all operations 2700 RPM 200 HP FUEL (AVGAS ONLY) 1001130 Octane Aviation Gasoline (Minimum) PROPELLER...
  • Page 37 ARROW AIRSPEED LIMITATIONS AND INSTRUMENT MARIUNGS (Calibrated Airspeed) 214 MPH NEVER EXCEED SPEED MAXIMUM STRUCTURAL. CRUISE SPEED 170 MPH MANEUVERING SPEED 1.31 MPH 125 MPH 150 MPH 125 MPH MAXIMUM GEAR RETRACTION SPEED AIRSPEED INSTRUMENT MARICINGS 214 MPH (186 KT) Red Radial Line (Never Exceed) 170 MPH to 214 MPH Yellow Arc (Caution Range)
  • Page 38 ARROW All acrobatic maneuvers including spins prohibited. PLACARDS In full view of the pilot: "THIS AIRCRAFT APPROVE,D FOR NIGHT IFR NON-ICING FLIGHT WHEN EQUIPPED IN ACCORDANCE WITH FAR 91 OR FAR 1.35." "THIS AIRCRAFT MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF...
  • Page 39 ARROW Adjacent to upper door latch: "ENGAGE. LATCH BEFORE FLIGHT." On the inside of the baggage compartment door: Near emergency gear lever: "EMERGENCY DOWN" "OVERRIDE ENGAGED AUTO-EXWFF LOCK PIN ON SIDE TO ENGAGE OVERRIDE: PULL LEVER FULL PUSH LOCK PIN TO RELEASE OVERRIDE: PULL LE,VER FULL RELEASE,"...
  • Page 40 ARROW In full view of the pilot in the area of the air conditioner controls when air conditioner installed: "WARNING AIR CONDITIONER MUST BE OFF TO INSIJRE NORMAL TAKEOFF CLIMB PERFORMANCE." REPORT: VBv560 PAGE 3-5 FAA APPROVED MAY 14,1973 MODEL: PA-28R-200...
  • Page 41 ARROW THIS PA(;II II'TENTIONALLY LEFT 13L.f.NK REPORT: VB-560 PAGE FAA APPROVED MAY .3-6 MODEL.: PA-28R-200...
  • Page 42 ARROW PROCEDURES SYSTEM OPERATIONS The stall-warning system is inoperative with the master switch off. The electric fuel pump must be on for both landing and takeoff. This airplane is equipped with an airspeed power sensing system (back-up gear extender) which extends the landing gear under low airspeed power conditions* even though the pilot may not have selected gear down.
  • Page 43 ARROW he yellow "In Tramit" light on the instrument panel operates whenever any of the t h e e gears is not in either the fully retracted posilian or the fully extended and locked position yellow "Auto Off" light immcdiatcly below the gear sclcctor switcli Takeoff considerations: After takeoff, if the gear selector switch is placed in the gear up position before reaching the airspeed at which the back u p gear extender system no longer commands...
  • Page 44 ARROW THIS PAGE. 1NTE.NTIONALL.Y LEFT BLANK FAA APPROVED MAY 14,1973 REPORT: VB-560 PAGE 3-9 MODEL: PA-28R-200...
  • Page 45 THIS PAGE INTENTIONALLY LE,FT BLANK REPORT: VB-560 PAGE 3-10 FAA APPROVED MAY 14, 1973 MODEL: PA-28R-200...
  • Page 46 . Installation of an Engine Electronic Digital Tachometer, Horizon ode1 P 000, P/N P100070- (Applicability table on continuation sheet) in Piper Aircraft Corp. PA28-140, -150, -151, -160, -161, 180, -181, -235, -236, -201T, R-180, R-200, R-201, R-201T, RT-201, RT-ZOIT, and S-160 Series aircraft, in accordance with Horizon Instruments, Inc.
  • Page 47 (Continuation Sheet) H o r i z o n Tachometer P a r t A i r c r a f t S e r i a l Number Ranse Model 28-20002 PA28-140 28-03, 28-1 PA28-150 28-03, 28-1 28-03, 28-1 F A R 11 PAGE PAGES...
  • Page 48 CONDITIONAL Airplane Flight Manual Supplement for a Piper PA28R-200 This document, by no means, gives the authority to amend or add to any existing Pilot Owners Handbook. This document serves as an example of a Model P-1.000 Electronic Digital Engine Tachometer Flight Manual Supplement, which must be approved by the FAA.
  • Page 49 Horizon Instruments, Inc. St., Unit 92870 Model Digital EngineTadxKneter (714) 5241919 (714) 5245937 TABLE OF CONTENTS Section I . General Page 3 Section 11. Limitations Page Section Emergency Pmcedures Page 3 Section Normal Procedures Page 3 Section Performance Section VI. Weight Balance and Equipment Page 6...
  • Page 50 Horizon Instruments, Inc. 600 5 . IeffeMn S t . , Unit C, Placentia, Model P-1000 ElechDnic Ph. (714) 5241919 (714) 524-5937 Section I. General: No Change Section Limitations: This table lists each engine operating range by the lowest RPM within the operating range.
  • Page 51 Horizon Instruments, Inc. 600 5. Jefferson St., Unit 92870 Model P-1000 Elecbonic Digital Engine Tachometer Ph. (714) 524-1919 Fx. (714) 524-5937 be individually enabledldisabled via buttons on the face of the Tachometer, refer to items K and I on page 5 of 7. Engine operating ranges are indicated on the large green, yellow, and red LED magneto system alert indicator lights are located within the "Status"...
  • Page 52 Horizon Instruments, Inc. 600 5 . S t . , 92870 Model P-1000 (714) 524-1919 (714) 524-5937 PRESS AND HOLD OPERATIONS The left button, K, upon depression, will cause the Tachometer to display the non-fractional portion (0000.) of the current accumt~lated engine hours.
  • Page 53 Horizon ]instruments, Inc. 600 S. Jefferson St., Unit Model P-1000 Digital Engine Tachometer (714) 524-1919 (714) 524-5937 green, yellow, and small red and yellow LEDS are dim-able. 'The large red LED still operates a t full intensity to maximize the possibility of gaining pilot attention during excursion into restricted rprn ranges.
  • Page 54 Horizon Instruments, Inc. 600 S. Jeffemn St., Unit C, Plawtia, C A 92870 Modei Ph. (714) 524-1919 Fx. (714) 524-5937 P-1000 Eiectmnic Digital Engine Tachometer Right Magneto Signal Loss Indicator RPM Sync Loss Indicator Left Magneto Signal Loss Indicator Normal Operating Green RPM Mark Cautionary Yellow RPM Arc Indicator Restricted Red RPM Arc Indicator Placard Area...
  • Page 55 East Haddam, Connecticut 06423-0415 APPROVED Aircraft Flight Manuai Siipplement For: Piper PA-28R-200, PA-28R-201, PA-28RT-201 Make &Model of Aircraft Registration. No.: Serial No.: This supplement must be atfached to FAA Approved Aircraft Flight Manual for the Piper PA-28R-201 PA-28RT-201, when Propeller Model &...
  • Page 56 US PROPELLER SERVICE of CONNECTICUT PO BOX 415 GOOUSPEED AIRPORT EAST HAUDAM, Limitations: (continued): Placard: On the instrument panel, between tachometer and manifold pressure guages station: "Avoid continuous operation below 15 inches HG between 1900 RPM and 2350 RPM." Procedures No changes.
  • Page 61 ARROW EMERGENCY PROCEDURES Emergency landing gear extension instructions: Accomplish the following check prior to initiation of the emergency extension procedures: (a) Master Switch Check On (b) Circuit Breakers Check Off (in daytime) Check If landing gear does not check down and locked: extender, raise emergency gear lever to "Override Engaged"...
  • Page 62 ARROW BLANK THIS PAGE INTENTIONALLY LEFT FAA APPROVED MAY 14,1973 MODEL: PA-28R-U)O...
  • Page 63 ARROW SECTION I n PERFORMANCE STALLS The following performance figures were obtained during FAA type tests and may be realized under conditions indicated with the airplane and engine in good condition and with average piloting technique. All performance is given for 2650 pounds. Loss of altitude during stalls varied from 100 t o 300 feet, depending on configuration and power.
  • Page 64 ARROW FAA APPROVED MAY 14,1973 MODEL: PA-28R-200...
  • Page 65 AIRPLANE FLIGHT MANUAL ONLY IF THE EQUIPMENT WHICH I S T H E SUBJECT O F THE Electric Pitch Trim Installation Air Conditioner Installation Installation of Piper AutoControl lIlB FAA APPROVED MAY 14,1973 REPORT: VB-560 PAGE 3-1 5 JUNE 18,1974 MODEL: PA-28R-200...
  • Page 66 ARROW THIS PAGE INTENTIONALLY LEFT BLANK FAA APPROVED MAY 14,1973...
  • Page 67 ARROW LIMITATIONS PROCEDURES Preflight (2) Operate rocker switch (3) Manually override electric trim (4) Clieck manual trim operation (5) If trim fails preflight, disengage electric trim by operating push button trim switch on instrument panel until repaired. If trim does not disengage liave unit repaired before further flight.
  • Page 68 ARROW AUTOCONTROL I11 INSTALLATION Autopilot use is prohibited above 200 MPH-CAS Autopilot "OFF" for takeoff and landing Normal Operation Refer to the current AutoControl 111 Owner's Handbook. Emergency Operation (a) Pushing the roll "ON-OFF" switch t o "OFF." (b) Turning aircraft Master Switch "OFF." The AutoControl 111 can be overpowered at either control wheel., (3) An autopilot runaway, with a 3 second delay in the initiation of recovery, while operating in a climb, cruise or descending flight could...
  • Page 69 ARROW INSTALLATION Autopilot use is proliibited above 200 MPH-CAS PROCEDURES Normal Operation Refer to the current AutoFlite I1 Owner's Handbook Emergency Operation Pressing disconnect switch on pilot's control wheel. (b) Rocker switch on instrument panel O F F (2) Unit may be overpowered manually at either control wheel. An autopilot runaway, with a 3 second delay in the initiation of recovery, while operating in a climb, cruise or descending flight cotild bank and a 190 foot altitude loss.
  • Page 70 ARROW AIR CONDITIONER INSTALLATION LIMITATIONS Air Conditioncr "OFF" for takeoff and landing. Prior t o takeotf, the air coliditioncr should be checkcd lor proper operation as follows: Check aircraft master switch on Turn the air conditioner control switch t o "ON" and the fan switch t o one of the operating positions the "AIR COND DOOR OPEN"...
  • Page 71 ARROW PIPER AUTOCONTROL llIB LIMITATIONS Autopilot OFF during takeoff and landing Autopilot use prohibited above 200 MPH CAS PROCEDIJRES PREFLIGHT (a) Place Radio Coupler in "Heading" inodc and place A/P Rotate roll command knob Left and Right and observc control wheel describes a corresponding Left and Right turn, then center knob.
  • Page 72 ARROW (4) VOR (a) T o Intercept: Using OMNI Bearing Selector, dial desired course, inbound or outbound. Set identical heading on Course Selector D.G. After aircraft has stabilized, position coupler mode selector knob to OMNI mode. As aircraft nears selected radial, interception and crosswind correction will be automatically accomplished without further switching.
  • Page 73 ARROW NOTE For precise tracking over OMNI station, without "S" turn, position coupler mode selector to HDG mode just prior to station passage. If holding pattern is desired, position coupler mode selector to HDG mode at station passage inbound and select outbound heading in direction of turn.
  • Page 74 ARROW EMERGENCY OPERATION (1) In an emergency t l ~ e AutoControl can be disconnected by: (a) Placing the A/P ON/OFF switch to the "OFF" position. (b) Pulling the Autopilot circuit breaker (aircraft S/N 28-7635001 and up). (2) The AutoControl can be overpowered at either control wheel. (3) An Autopilot runaway, with a 3 second delay in the initiation of recovery, while operating in a climb, cruise or descending flight could...
  • Page 75 EMERGENCY PROCEDURE ..........Introduction .

  • Page 76: Emergency Procedures

    ARROW INTRODUCTION This section contains procedures that are recommended if an emergency condition should occur during grottnd operation, take-off, or in-flight. These procedures are suggested as the best course of action for coping with the particular condition described, but are not a substitute for sound judgment and common sense.
  • Page 77 emergency procedures circumstances. If sufficient runway remains for a normal landing, leave the gear down and land straight ahead. If the area ahead is rough, or if it is necessary to clear obstructions, put gear selector switch in the position, and latch the gear lever in the override position. restart, proceed as follows: CHECK ON AS REQUIRED...

  • Page 78: Engine Power Loss In Flight

    ARROW 11 ENGINE POWER LOSS IN FLIGHT Complete engine power loss is usually caused by fuel flow interruption, and power will be restored shortly after ft~el flow is restored. If power loss occurs a t low altitude, the first step is to prepare for an emergency landing (See POWER O F F LANDING).
  • Page 79 Wliethcr to attempt a landing with gear u p or down depends on msny f?r+crr the field chosen is obviously smooth and firm, and long enough to bring the plane t o a stop, the gear down position will better protect the occupants of the aircraft. If, however, the field is suspected to be excessively soft or short, or when landing in water of any depth, a wheels-up landing will normally be safer and do less damage to the airplane.

  • Page 80: Propeller Overspeed

    ARROW PROPELLER OVERSPEED Propeller overspeed is caused by a malfunction in the propeller governor, or low oil pressure, which allows the propeller blades to rotate to full low pitch. If this should occur, proceed as follows: 1. THRO'ITLE RETARD. OIL PRESSURE CHECK.

  • Page 81: Spins

    ARROW I1 SPINS Intentional spins are prohibited in this aircraft. If a spin is inadvertently entered, immediately use the following n IDLE. FULL OPPOSITE TO DIRECTION OF ROTATION. REGAIN LEVEL FLIGHT NOTE On aircraft equipped with the backup gear extender, the landing gear will extend in this flight condition, but will retract during OPEN DOOR The cabin door on the Cherokee Arrow I1 is latched at four points so the chances of its...

  • Page 82: Fire

    ARROW ll smoke. o r other indications, since the action to be taken differs somewhat in eaclt case. Source of Fire Check Electrical Fire (Smoke in Cabin): (2) Vents Open (3) Cabin Heat (4) Land as soon as practicable. Engine Fire: (a) Fuel Selector O F F Mixture...

  • Page 83: Loss Of Fuel Pressure

    ARROW 11 change power settings unnecessarily, as this may hasten complete power loss Depending on the circumstances, it may bc advisable to make an off airport landing while power is still available, particularly if other indications of actual oil pressure loss, such as sudden increase in temperatures, or oil smoke, are apparent, and an airport is not close.
  • Page 84 EXTREME CARE MUST BE EXERCISED TO LIMIT THE USE O F THIS REPORT TO SUBSEQUENTLY REVISED IS VALID FOR USE WITH THE AIRPL.ANE IDENTIFIED BELOW WHEN APPROVED BY PIPER AIRCRAFT CORPORATION. SUBSEQUENT REVISIONS SUPPLIED BY PIPER AIRCRAFT CORPORATION MUST BE PROPERLY INSERTED.

  • Page 85: Weight And Balance

    ......... . . Log of Revisions Weight and Balance Data Weighing Procedure...
  • Page 86 ARROW WEIGHT AND BALANCE INDEX ..........Log of' Revisions 5-iii .
  • Page 87 ARROW THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: MAY 14,1973 REPORT: VB-549 PAGE 5-ii MODEL: PA-28R-200...
  • Page 88 BALANCE LOG OF WEIGHT AND REVISIONS Revised Pages Description and Revision Revised Fuel Capacity on Sample Problem. Revised Battery and Voltage Regulator Weights and Moments. Revised Toe Brake Weight and Moment. Revised Battery Weights and Moment. Revised Selector Panel and Marker Beacon Weights, Arms and Moments.
  • Page 89 Added Right Front Seat from page 5-.31; added 79591-1 Right Front Seat; added added Stainless Steel Control Cables; added footnote. Revised Electric Trim System to Piper Pitch Trim 67469-7; added Piper Pitch Trim 67469-3; added footnote. Added King KN61 DME and King KN65A Added Dwg.
  • Page 90 ARROW WEIGHT AND BALANCE LOG REVISIONS (cont) Revision Revised Pages Description and Revision Added McCauley Propeller and Spinner; added footnotes. Added Lycoming I@36@C1 C6 Engine and footnotes. Added Tachometer and footnotes. Revised Attitude and Directional Gyro dash nos. Revised Weight and Balance info. Added Caution;...
  • Page 91 ARROW THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: FEBRUARY 2 8 , 1 9 7 7 MODEL: PA-28R-200...
  • Page 92 ARROW WEIGHT A N D BALANCE In order to achieve the performance and flying characteristics which are designed into the aircraft. the Arrow must be flown with the weight and center of gravity (C.G.) position within the approved envelope. The aircraft offers flexibility of loading. However, youcannot fill theaircraft, with four adults.
  • Page 93 ARROW THIS PAGE 1NTENTIONALL;Y LEFT BLANK ISSUED: MAY REPORT: PAGE 14,1973...
  • Page 94 ARROW WEIGHT AND BALANCE DATA WEIGHING PROCEDURE At the timeof 1icensing.Piper Aircraft Corporation provides each airplane with the licensed Thii 5-7. empty weight and center of gravity location. data is on Page The removal o r addition of an excessive amount of equipment or excessive airplane modifications can affect the licensed empty weight and empty weight center of gravity.
  • Page 95 ARROW Level airplane (see diagram) deflating nose wheel tire, to center bubble on level. WEIGHING AIRPLANE E,MPTY WEIGHT With the airplane level and brakes released, record the weight shown on each scale. Deduct the tare, if any, from each reading. Scale Tare Weight...
  • Page 96 ARROW Obtain measurement "A" by measuring from a plumb bob dropped from the wing leading edge, at the intersection of the straight and tapered section, horizontally and parallel t o the airplane centerline, t o the main wheel centerline. Obtain measurement "B" by measuring the distance from the main wheel centerline, horizontally and parallel to the airplane centerline, t o each side of the nose wheel axle.
  • Page 97 ARROW THIS PAGE INTENTIONALLY L.EFT BLANK REPORT: VB-549 PAGE 5 6 ISSUED: MAY 14,1973 MODEL: PA-28R-200...
  • Page 98 ARROW WEIGHT AND BALANCE DATA MODEL PA-28R-200 CHEROKEE Aiilane Serial Number Registration Number Date AIRPLANE EMITY WEIGHT C. G. Arm (Inches Aft Moment Weight (In-Lbs) of Datum) I tem Actual *Empty Weight Computed 103.0 1030 10.0 Standard Empty Weight Optional Equipment Licensed Empty Weight dry empty weight (including paint and hydraulic fluid) plus 1.8 ibs undrainable engine oil.
  • Page 99 INSTRUCTIONS RANGE WEIGHT Add the weight of all items to be loaded t o the licensed empty weight. Use the loading graph to determine the moment Add the moment of all items to be loaded to the licensed empty weight moment. Divide the total moment by the total weight t o determine the C.G.
  • Page 100 ARROW LOADING GRAPH INCHES) ISSUED: MAY 14.1973 REPORT: VB-549 PAGE 5-9 MODEL: PA-28R-200...
  • Page 101 ARROW IT IS THE RESPONSIBILITY OF THE OWNER AND PILOT 1 0 ASCERTAIN THAT THE AIRPLANE ALWAYS REMAINS WITHIN THE ALL.OWAB1.F WEIGHT VS CENTER OF GRAVITY ENVELOPE WHILE IN FLIGHT C. 6. RANGE AND WEIGHT INCHES AFT OF DATUM MOMENT DUE TO RETRACTING LANDING GEAR = +819 I N . LBS ISSIJED: MAY 14.
  • Page 102 ARROW EQUIPMENT LIST The following is a list of' eq~lipment which may be installed in the PA-28R-200. Items marked with an are items installed when the airplane was delivered by the manufacturer. Weight Ann Aft Cert. Lbs. Datum Moment Basis Item Item A.
  • Page 103 ARROW Weight Arm Aft Datum Moment Basis Item Item Fuel and Oil Systenls Engine Lycoming Model Fuel Pump Electric Auxiliary Induction Air Filter Fuel Pump Engine Driven Lycoming 75247 Alternator 12V 60 Amp Starter Prestolite Model MZ-4206 Lycoming 7621 1 Oil Cooler, PAC 67848 Oil Filter with Adapter AC OF5578770 (3 3 lbs each)
  • Page 104 Weight Arm Aft Cert Lbs. Datum Moment Basis ltem Item Main Wheel Brake Assemblies 40-86 Wheel Assemblv (Cleveland) Main 4 Ply Rating Tires 34.4 109.8 3777 One Nose Wheel Assembly 40-77 Wheel Assembly (Cleveland) (less brake drum) One 4 Ply Rating Tire 5.00-5 Regular Tube ISSIJED: MAY 14, 1973 REPORT: VB-549 PAGE 5-13...
  • Page 105 Cutler Hammer 8906-K 1736 Voltage Regulator Wico Electric No. X-16300B Overvoltage Relay Wico Electric No. X-167998 Starter Relay Piper Dwg. 991 30-2 Landing Gear Motor Contactor (2) 8 lbs, each Annunciator Lights *Serial nos. 75.35001 and up REPORT: VB-549 PAGE 5-14...
  • Page 106 -3 TC 2.413 Tachometer Piper 62177-6 Engine Cluster Piper 95241-2 TC 2A13 Engine Cluster Piper 95241-3 Altimeter Piper PS50008-2, -3, TSO Cl Ob or -5 Manifold Pressure and Fuel TSO C45 Flow Piper PS5003 1-6 Airspeed Indicator Piper TSO C2b...
  • Page 107 ARROW THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: MAY 14,1973 MODEL: PA-28R-200...
  • Page 108 Cett. Item Item Lbs. Datum Moment Basis Cylinder Hydraulic Nose Gear Piper 67504 Cylinder Hydraulic (2) Main Gear Piper 67505 (0.9 lbs. each) Pump Assembly Piper 67500-2 Switch, Pressure Consolidated Controls *2 1 1 C243-.3 Valve Free Fall Piper 67522-2...
  • Page 109 Toe Brakes (Dual) Piper Dwg. 67018-3 Right Front Seat Piper Dwg. 76171-1 Individual Rear Seats (2) Piper Dwg. 997300 and -1 (13.5 lbs. each) Flight Manual and Logs Tow Bar, Piper Dwg. 67.336-0 REPORT: VB-549 PAGE 5-1 8 ISSUED: MAY 14,1973...
  • Page 110 ARRQW THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: MAY 14.1973 REPORT: VB-549 PAGE 5-19 MODEL: PA-28R-200...
  • Page 111 ARROW Weight Arm Aft Item Datum Moment Basis H. 'ngine and Engine Accessories Fuel and Oil System (Optional Equipment) Vacuum Pump Airborne Manufacturing Co Model 200 CC AC OF5578770 (3.3 lbs. each) 33.1 TC 2A13 Oil Filter, Lycoming LW-1374.3 (Champion Vacuum Pump, Airborne Mfg.
  • Page 112 Navigation Light Wing) (2) Grimes A1 2854-1 2 A1 285-R-12 (0.2 lbs. each) 106.6 TSO C30b Auxiliary Power Receptacle Piper 65647 External Power Cable Piper 62355-2 Cabin Speaker Quincy Spkr. Co. 8B-15052 or Oaktron Ind. GEV 1937 Cabin Light Rotating Beacon Battery 12V, 35 A.H.
  • Page 113 Electrical Equipment (Optional Equipment) (cont) Heated Pitot Head Piper 67477-0 Anti-Collision Lights Whelen Engineering Co. Piper Dwg. 99030-2 or Power Supply, Model HS, No. 198.0 TC 2A1.3 Power Supply, Model HD, T3 No. A413 (with fin and wing TC 2.413 lights) 198.0...
  • Page 114 ARROW Ann Alt Cert Datum Moment Basis Roll Servo "lC363-1-183~ 122.2 STC SA I40hSW Console 60.1 STC SA 1406SW Cables 95.5 STC SA 1406SW Attitude Gyro " 5 2 ~ 6 6 59.4 Directional Gyro " 5 2 ~ 5 4 59.0 STC SA 1406SW Omni Coupler ' 1 C 8 8...
  • Page 115 ARROW THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: MAY 14,1973 REPORT: VB-549 PAGE 5-24 MODEL: PA-28R-2.00...
  • Page 116 ARROW Cert. Weight Moment Basis Datum Lbs. ltem Narco Mark I 6 Transceiver, Single Narco Mark 16 Transceiver, ~ u a l 15.0 Narco VOA-50M Omni Converter* Narco VOA-40M Omni Converter Narco VOA-40 Omni Converter Cable, Nav. Antenna 1 VHF Comm. Antenna Cable, 1 VHF Comm.
  • Page 117 ARROW Weight Arm Aft Cert. Item Item Lbs. Moment Basis Equipment) (con Bendix ADF-T-I 2C or D Receiver Model 20 1 F Receiver Model 201 C or D Audio Amplifier 102A Servo Indicator 55 1 A Loop Antenna 2321 E Cable, Interconnecting Sense Antenna and Cable Narco Comm 10...
  • Page 118 Weight Arm Aft Lbs. Datum Moment Basis K. Radio Equipment (Optional Equipment) (cont) King KR-85 Receiver Servo Indicator Loop Antenna Loop Cable Audio Amplifier Sense Antenna and Cable Narco CP-25B/125 Selector Panel Narco MBT-12-R Marker Beacon Narco Comm 110" Narco Comm 11 1 Narco Nav 110"...
  • Page 119 Antenna &Cable Narco AT-5OA Transponder (Includes Antenna &Cable) King KMA-20 Audio Panel Antenna Cable Audio Selector Panel -Piper 99395-0, -2, or -3 Microphone (Carbon) Piper Dwg. 68856-1 0 Microphone (Dynamic) Piper Dwg. 68856-1 2 "Serial nos. 7435001 through 74.3533 1...
  • Page 120 ARROW Arm Aft Cert. Item Item Datum Moment Basis Equipment) (cant) King KE21.3 VOR/L,OC/CS Indicator 60.4 161.5 105.5 TC 2A13 Audio Amplifier 51.0 King KR-86 ADF (2nd) 59.4 2.32 Receiver 150.7 TC 2A1.3 Loop Antenna 105.0 Loop Cable Sense Antenna &Cable 147.5 King KN-73 Glide Slope Receiver...
  • Page 121 ARROW Weight Arm Aft Item Datum Moment Basis K. Radio Equipment (Optional Equipment) (cont) Narco Comrn 1 1 B VHF Transceiver Narco Dual Comm 1 1 B VHF Transceiver Narco Dual Comm 11 1 VHF Transceiver Narco Comm 11 1B VHF Transceiver Narco Dual Comm I 1 1B VHF Transceiver...
  • Page 122 Cable, Loop Sense Antenna and Cable Loop Antenna Cable, Loop Sense Antema and Cable Remote fbr Dual Ind. Narco DME-190 Receiver Antenna Cable, Antenna Microphone (Dynamic)* Piper Dwg. 68856-1 'Serial nos. 75.35001 and up REPORT: VB-549 PAGE 5-28c MODEL: PA-28R-200...
  • Page 123 ARROW THIS PAGE 1NTENTIONALL.Y LEFT BLANK REPORT: VB-549 PAGE 5-28d ISSUED: JUNE 1 8 , 1 9 7 4...
  • Page 124 Instruments (Optional Equipment) Suction Gauge Piper 99480-0 or-2 Vacuum Filter, Piper 66673 Indicator Rate of Climb TSO C8b Piper 99010-2, -4, or -5 Indicator Rate of Climb TSO C8b Piper 99010-3 Attitude Gyro Piper 99002-2, TSO C4c -3, -4, or -5...
  • Page 125 Lbs. I tem I tem Datum Moment Basis Instruments (Optional Equipment) (cont) Engine Hour Meter* Piper Dwg.. 79548-0 Piper Dwg. 37693-2 NSD-360 Gyro* 59.0 24 1 TSO C5c Narco OC-1 10* Converter and Mount *Serial nos. 28R-7635001 and up. ISSUED: MAY...
  • Page 126 Lbs. Datum Moment Assist Step Piper 653844 Assist Strap and Coat Hook Piper 62353-5 Assist Strap Piper Dwg. 79455 Inertia Safety Belts, Rear Seats (2) PS50039-4-14 Lighter 200462 Fire Extinguisher, Scott Aviation 4221 1 4 0 Piper Dwg. 76 167-2 Headrests, Front (2) 99255-3 1 .O lbs.
  • Page 127 ARROW Weight Arm Aft Cert I tem Lbs. Datum Moment Basis M. Miscellaneous (Optional Equipment) (cont) Piper Dwg. 790304 18.1 86.8 1571 TC 2A13 Cabin Overhead Vent System Piper Dwg. 76304-3 1022 159.6 Cabin Overhead Vent System With Ground Ventilating Blower Piper Dwg..
  • Page 128 OPERATING INSTRUCTIONS ........Preflight ..........Starting Engine .
  • Page 129 ARROW I1 OPERATING INSTRUCTIONS PREFLIGHT The airplane should be given a thorough visual inspection prior to each flight. Particular attention should be given t o the following items: Master switch and ignition OFF; landing gear switch DOWN; remove seat belt securing control wheel.

  • Page 130: Starting Engine

    ARROW I1 Check tires for cuts, wear and proper inflation. Check brake blocks and discs for wear and damage. Check windshield for cleanliness. Check propeller and spinner for defects or nicks. Check for obvio~ls fuel or oil leaks. Check oil level. (Insure dipstick is properly seated.) Check cowling and inspection covers for security.

  • Page 131: Starting Engine When Flooded

    Longer cranking periods will shorten the life of the starter. STARTING WITH EXTERNAL POWER* An optional feature known as Piper External Power (PEP) allows the operator to use an external battery to crank the engine without having to access to the aircraft gain battery.

  • Page 132: Takeoff

    ARROW 11 RPM. Check vacuum gauge. Indicator should read 5" Hg .I" Hg at 2000 Check both the oil temperature and pressure. The temperature may be low for some time if the engine is being run for the first time of the day, but as long as the pressure is within limits the engine is ready for takeoff.

  • Page 133: Climb

    ARROW I1 Short Field, Obstacle Clearance: Lower flaps t o 25" (second notch), accelerate aircraft to 60-65 MPH and ease back on the wheel to rotate. After breaking ground, accelerate to best angle of climb speed, 8 5 MPH, select gear "up"* and continue climb while accelerating to best rate of climb speed, 104 MPH, and slowly retract the flaps while climbing out.

  • Page 134: Cruising

    ARROW Il CRUISING The cntising speed of the Cherokee Arrow I1 is determined by many factors, including power setting, altitude, temperature, loading, and equipment installed on the airplane. The normal cniising power is of the rated horsepower of the engine True airspeeds which may be obtained at various altitudes and po*er settings can be determined from the charts in "Section XIII"...

  • Page 135: Approach And Landing

    ARROW I1 APPROACH AND LANDING Before landing check list: Seat backs -erect Fasten beltslharness Fuel on proper tank Fuel pump Mixture Propeller - DOWN Gear Flaps set (1 25 MPH) Air conditioner The airplane should be trimmed t o an approach speed of about 9 0 MPH with the flaps and gear extended.

  • Page 136: Airspeed Data

    ARROW 11 AIRSPEED DATA All airspeeds quoted in this manual are calibrated unless otherwise noted. Calibrated airspeed is indicated airspeed corrected for instrument and pos~tion errors. The following table gives the correlation between indicated airspeed and calibrated airspeed if zero instrument error is assumed This calibration is valid only when flown at maximum gross weight in level flight.
  • Page 137 ARROW 11 activated by a longitudinal force of 5 g's and transmits a distress signal on both 121.5 MHz and for a period of from 48 hours in low temperature areas up to 100 llours in kigh 243.0 temperature areas. The unit operates on a self-contained battery. The replacement date as required by FAA regulations is marked on the transmitter label.

  • Page 138: Air Conditioner Operational Check Procedure

    ARROW I1 NOTE If fbr any reason a test transmission is necessary, the operator must first obtain permission from local representative (or other applicable Authority). Test transmission should be kept to a minimal duration. AIR CONDITIONMG To operate the air conditioning system either on the ground or in flight: Start the engine (ground operation).
  • Page 139 ARROW I1 Although the cruise speed and range are only slightly affected by the air conditioner operation, these changes should be considered in preflight planning. To be conservative, the following figures assume that the compressor is operating continuously while the airplane is airborne.

  • Page 140: Operating Tips

    OPERATING TIPS ....Operating Tips...
  • Page 142 ARROW I1 OPERATING T I P S The following Operating Tips are of particular value in the operation of the Cherokee Arrow 11. Learn t o trim for take-off so that only a very light back pressure on the wheel is required t o lift the airplane off the ground.
  • Page 143 ARROW operating speed of the vacuum-driven gyroscopic flight instruments. It also monitors the condition of the commom air filter by measuring the flow of air through the filter. If the vacuum gauge does not register 5" Hg f .lo" Hg a t 2000 RPM, following items ahould be checked before flight: Common air filter, could be dirty o r restricted.

  • Page 144: Performance Charts

    PERFORMANCE CHARTS Altitude Conversion Chart ..........Takeoff Pexformance Climb Performance Cruise Performance...
  • Page 146 ARROW 11 THIS CHART SHOULD BE USED TO DETERMINE DENSITY ALTITUDE FROM EXISTING TEMPERATURE FOR USE WITH PERFORMANCE CHARTS. TEMPERATURE PERFORMANCE CHARTS ISSUED: JULY 13,1973...
  • Page 147 ARROW TAKE-OFF DISTANCE (FT.) NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING INSTALLATION ON PERFORMANCE.
  • Page 148 ARROW POWER FULL THROTTLE GEAR AND FUPS RETRACTED GROSS WT. 2650 LBS. RATE OF CLIMB (FT./MIN.) NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING INSTALLATION ON PERFORMANCE. PERFORMANCE CHARTS REVISED: JUNE 18,1974...
  • Page 149 ARROW I1 TRUE AIRSPEED IMPHj NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING INSTALLATION ON PERFORMANCE. PERFORMANCE CHARTS JUNE 18, 1974...
  • Page 152 ARROW 1600 1800 2000 2200 2400 2600 GROSS WEIGHT POUNDS PERFORMANCE CHARTS ISSUED: JULY 1 3 , 1 9 7 3...
  • Page 153 ARROW Il GLIDE RANGE MILES PERFORMANCE CHARTS 18,1974...
  • Page 154 ARROW NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING INSTALLATION ON PERFORMANCE. PERFORMANCE CHARTS REVISED: JIME 18, 1974...

  • Page 156: Handling And Si E Wwci N G

    Ground Handling Towing ..........................Taxiing Parking Mooring Cleaning Cleaning Engine Compartment Cleaning Landing Gear ......................Cleaning Exterior Surfaces . . . Cleaning Windshield and Windows ..............Cleaning Headliner, Side Panels and Seats Cleaning Carpets Power Plant Induction Air Filter Removal of Induction Air Filter Cleaning Induction h r Ftlter Installation of Induction Air Filter ........................
  • Page 157 PIPER provided inspection criteria may not be valid for airplanes with non-PIPER approved STC installations. WARNING Modifications must be approved in writing by PIPER prior to installation. Any and other installations, whatsoever, of any kind will void this warranty in it's entirety. WARNING approved sources, in connection with the maintenance and repair of PIPER airplanes.
  • Page 158 ARROW Before attempting to taxi the airplane, ground personnel should be checked out by a qualified pilot or other responsible person. Engine starting and shut-down procedures should be covered as well as taxi techniques. When it is ascertained that the propeller back blast and taxi areas are clear, power should be applied to start the taxi roll and the following checks should be performed.
  • Page 159 ARROW CLEANING CLEANING ENGINE COMPARTMENT Before cleaning the engine compatment, place a strip of tape on the magneto vents to prevent solvent from entering these units. Place a large pan under the engine to catch waste. With the engine cowling removed, spray or brush the engine with solvent or a mixture of solvent and degreaser, as desired.
  • Page 160 ARROW 11 The airplane should be washed with a mild soap and water. Harsh abrasive or alkaline soaps or detergents used on painted or plastic surfaces could make scratches or cause corrosion of metal surfaces. Cover areas where cleaning solution could cause damage. To wash the airplane, the following procedure may be used: Flush away loose dirt with water.
  • Page 161 ARROW I1 POWER PLANT INDUCTION AIR FILTER The induction air filters must be cleaned at least once every 50 hours. Depending on the type of condition existing, it may be necessary to clean the filters more often. REMOVAL OF INDUCTION AIR FILTER Remove top cowl.
  • Page 162 ARROW 11 LANDING GEAR SERVICE The main lmding gear uses Cleveland Aircraft Products wheels and Cleveland single disc tubes. The nose wheel uses a Cleveland Aircraft Products 5.00 wheel with a 5.00 5, four-ply rating, type 111 tire with tube Wheels are removed by taking off the hub cap, cotter pin, axle nut, and the two bolts holding the brake segment in place.
  • Page 163 ARROW The spinner and backing plate should be cleaned and inspected frequently for cracks. The propeller should be inspected before each flight for nicks, scratches, and corrosion. If found, they should be taken care of as soon as possible by a rated mechanic, because nicks and scratches cause areas of increased stress which can cause serious damage or loss of propeller tip.
  • Page 164 ARROW The operation of the aircraft is approved with anti-icing additive in the fuel. When an anti-icing additive is used, it must meet the specification MIL-1-27686, must be uniformly blended with the fuel while refueling, must not exceed .IS% by volume of the refueled quantity, and to ensure its effectiveness, should be blended at not less than .lo% by volume.
  • Page 165 ARROW I1 TIRE M n A T I O N For maximum service from the tires, keep them inflated to the proper pressure of 30 psi for nose tire and 27 psi for main tires. Interchange the tires periodically for even wear. All wheels and tires are balanced before original installation, and the relationship of tire, tube and wheel should be maintained upon reinstallation.
  • Page 166 BLANK THIS PAGE JNTENTIONALLY LEFT HANDLING SERVICING ISSUED: JlJLY 13,1973...
  • Page 167 Piper Service Bulletins are of special imponance and Piper considers compliance mandatory. These are sent directly to the latest FAA-registered owners in the United States (U.S.) and Piper Service Centers worldwide. Depending on the nature of the release, material and labor allowances may apply.
  • Page 168 ARROW The owner or pilot is required to ascertain that the following Aircraft Papers are in order and in the aircraft. be displayed in the aircraft at all times: Aircraft Airworthiness Certificate Form FAA-1362B. Aircraft Registration Certificate Form FAA-SMIA. Aircraft Radio Station License Form FCC-4DQA, if transmitters are installed. be canied on the aircraft at all times: Aircraft Flight Manual.
  • Page 169 The Owner Service Agreement which the owner receives upon delivery of the aircraft should be kept in the aircraft at all times. This identifies him to authorized Piper dealers and entitles the owner to receive service in accordance with the regular service agreement terms. This agreement also entitles the transient owner full warranty by any Piper dealer in the world.
  • Page 171 ARROW I1 HANDLING SERVICING ISSUED: JULY 13,1973...

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