Arrow PA-28R-201 Pilot'S Operating Handbook And Faa Approved Airplane Flight Manual Download Page 159

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PIPER AIRCRAFT CORPORATION

SECTION 7

PA-28R-201, ARROW

DESCR/OPERATION

ISSUED: SEPTEMBER 15, 1988

REPORT: VB-1365

7-5

7.7 ENGINE CONTROLS (continued)

CONTROL QUADRANT AND CONSOLE

Figure 7-1

Summary of Contents for PA-28R-201

Page 1: ...the manufacturer and constitutes the faa approved airplane flight manual this handbook must be carried in the airplane at all times airplane airplane serial no regist no pa 28r 201 report vb 1365 faa...

Page 2: ...IRPLANE IDENTIFIED ON THE FACE OF THE TITLE PAGE SUBSEQUENT REVISIONS SUPPLIED BY PIPER AIRCRAFT CORPORATION MUST BE PROPERLY INSERTED Published by PUBLICATIONS DEPARTMENT Issued September 15 1988 198...

Page 3: ...ED STC INSTALLATIONS ARE NOT INCLUDED IN THIS HANDBOOK WHEN A NON PIPER APPROVED STC INSTALLATION IS INCORPORATED ON THE AIRPLANE THOSE PORTIONS OF THE AIRPLANE AFFECTED BY THE INSTALLATION MUST BE IN...

Page 4: ...mbers followed by a small letter in direct sequence with the same common numbered page II Identification of Revised Material Each handbook page is dated at the bottom of the page showing the date of o...

Page 5: ...3 14 Revised para 3 1Sa 3 18 Revised para 3 3l 4 S Revised para 4 5a 4 7 Revised para 4 Sc 4 10 Revised para 4 Sh 4 11 4 16 Revised para 4 9c 4 17 Revised para 4 9d 4 18 Revised para 4 13a 4 19 Revise...

Page 6: ...rd Added para 6 9 D H Trompler ec 12 1989 Date Added Revision 4 to Log of Revisions Correct footer Correct footer Correct footer Deleted info Deleted info Moved text from 7 32 I04 Moved text to 7 31 R...

Page 7: ...evision 6 to Log PR950518 of Revisions Peter E Peck vi Corrected Errors on Log vi a of Revisions pages vi vi a May 18 1995 Date Rev 7 iii Added Warning and moved PR040607 info to page iv iv Moved info...

Page 8: ...ved text from Para 4 17 to pg 4 21 4 21 Added text to Para 4 17 from pg 4 20 Changed text in Para 4 19 7 18 Revised text in Para 7 19 Albert J Mill 8 1b Revised text in Para 8 1 May 10 2009 Rev 11 ii...

Page 9: ...SECTION 8 SECTION 9 SECTJON 10 TABLE OF CONTENTS GENERAL LIMITATIONS EMERGENCY PROCEDURES NORMAL PROCEDURES PERFORMANCE WEIGHT AND BALANCE DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS AI...

Page 10: ...SECTION 1 GENERAL Page No I Introduction I I 1 3 Engines 1 3 1 5 Propellers 1 3 1 7 Fuel 1 4 1 9 Oil 1 4 1 11 Maximum Weights 1 5 1 13 Standard Airplane Weights 1 5 1 15 Baggage Space 1 5 1 17 Specifi...

Page 11: ...t The pilot is also responsible for remaining within the opemting limitations as outlined by instrument markings placards and this handbook Although the arrangement of this handbook is intended to inc...

Page 12: ...S 3 00 PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW Wing Area sq ft 170 0 Min Turning Radius ft from pivot point to wing tip 31 0 I t_ G 0 1 10 5 64 1 REPORT VB 136S 1 2 THREE VIEW Figure I I ISSUED S...

Page 13: ...ROPELLERS McCAULEY a Number of Propellers b Propeller Manufacturer c Blade Model d Number of Blades e Hub Model f Propeller Diameter in I Maximum 2 Minimum g Propeller Type ISSUED SEPTEMBER IS 1988 SE...

Page 14: ...ly Actuated a Fuel Cupacity U S gal total 77 b Usable Fuel U S gal total c Fuel Grade Aviation I Minimum Octane 2 Alternate Fuels 1 9 OIL a Oil Capacity U S qts 0 Oil Specification c Oil Viscosity REP...

Page 15: ...ence between the Maximum Takeoff Weight and the Standard Empty Weight 1 15 BAGGAGE SPACE a Compartment Volume cu ft b Entry Width in c Entry Height in 1 17 SPECIFIC LOADINGS a Wing Loading lb per sq f...

Page 16: ...pressed in Knots Ground Speed is the speed of an airplane relative to the ground Indicated Airspeed is the speed of an air craft as shown on the airspeed indicator when corrected for instrument error...

Page 17: ...may not be exceeded at any time Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution Stalling Speed or the minimum steady flight...

Page 18: ...r Temperature is the free air static temperature obtained either from inflight temperature indications or ground meteorological sources adjusted for in strument error and compressibility effects The n...

Page 19: ...op Distance MEA Route Segment The demonstrated ratio of the change in height during a portion of a climb to the horizontal distance traversed in the same time interval The demonstrated crosswind veloc...

Page 20: ...product of the weight ofan item multi plied by its arm Moment divided by a constant is used to simplify balance calcu lations by reducing the number of digits The point at which an airplane would bala...

Page 21: ...ard empty weight plus optional equipment Weight of occupants cargo and baggage Difference between takeoff weight or ramp weight if applicable and basic empty weight Maximum weight approved for ground...

Page 22: ...SECTION I GENERAL PIPER AIRCRAFT CORPORATION PA 28R 20I ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1365 1 12 ISSUED SEPTEMBER IS 1988...

Page 23: ...2 17 2 19 2 21 2 23 General Airspeed Limitations Airspeed Indicator Markings Power Plant Limitations Power Plant Instrument Markings Weight Limits Center of Gravity Limits Maneuver Limits Flight Load...

Page 24: ...S SPEED Never Exceed Speed VNE Do not exceed this speed in any operation Maximum Structural Cruising Speed VNO Do not exceed this speed except in smooth air and then only with caution Design Maneuveri...

Page 25: ...gear 129 130 Maximum Landing Gear Retraction Speed Do not exceed this speed when retracting the landing gear 107 07 Maximum Landing Gear Extended Speed VLE Do not exceed this speed with the landing g...

Page 26: ...lade Model 1 McCauley 2 Hartzell k Propeller Diameter 1 McCauley Minimum Maximum 2 Hartzell Minimum Maximum 1 Blade Angle Limits 1 McCauley Low Pitch Stop High Pitch Stop 2 Hartzell Low Pitch Stop Hig...

Page 27: ...ng Range 75 to 245 F Red Line Maximum 245 F c Oil Pressure Green Arc Normal Operating Range 60 PSI to 90 PSI Yellow Arc Caution Range Idle 25 PSI to 60 PSI Yellow Arc Caution Range Start and Warm up 9...

Page 28: ...ght line variation between points given 91 5 91 5 The datum used is 78 4 inches ahead of the wing leading edge at the intersection of the straight and tapered section It is the responsibility of the a...

Page 29: ...or FAR 135 a Day VF R b Night VF R c Day LF R d Night LF R e Non Icing 2 21 FUEL LIMITATIONS a Total Capacity b Unusable Fuel The unusable fuel for this airplane has been determined as 2 5 gallons in...

Page 30: ...and Landing Checklists will be installed TAKEOFF CHECKLIST Fuel on Proper Tank Electric Fuel Pump On Engine Gauges Checked Alternate Air Closed Seat Backs Erect Mixture Set Propeller Set Fasten Belts...

Page 31: ...IC MANEUVERS INCLUDING SPINS APPROVED On the instrument panel in full view of the pilot GEAR DOWN GEAR UP EXTENDED Near emergency gear lever 129 KIAS MAX 107 KIAS MAX 129 KIAS MAX EMERGENCY DOWN Near...

Page 32: ...NER MUST BE OFF TO INSURE NORMAL TAKEOFF CLIMB PERFORMANCE On inside of baggage compartment door BAGGAGE MAXIMUM 200 LBS SEE WEIGHT AND BALANCE DATA FOR BAGGAGE LOADING BE TWEEN 150 LBS AND 200 LBS Ad...

Page 33: ...ey propeller installations only AVOID CONTINUOUS OPERATION BETWEEN 1500 AND 1950 RPM BELOW 15 MANIFOLD PRESSURE On the aft baggage closeout MAXIMUM BAGGAGE 200 LBS NO HEAVY OBJECTS ON HAT SHELF In ful...

Page 34: ...ing Takeoff 3 11 Engine Power Loss In Flight 3 13 Power Off Landing 3 15 Gear Down Emergency Landing 3 15a Gear Up Emergency Landing 3 15b Fire In Flight 3 17 Loss Of Oil Pressure 3 19 Loss Of Fuel Fl...

Page 35: ...5c Power Off Landing 3 5d Gear Down Emergency Landing 3 5d Gear Up Emergency Landing 3 5d Fire In Flight 3 5e 3 11 3 12 3 13 3 14 3 14 3 15 3 19 Loss of Oil Pressure 3 5f 3 15 3 21 Loss of Fuel Flow...

Page 36: ...ond part of the section provides amplified emergency procedures corresponding to the emergency procedures checklist items These amplified emergency procedures contain additional information to provide...

Page 37: ...ION 3 3a STALL SPEEDS 2750 Ibs Gear Up 0 Flap 60 KIAS 2750 lbs Gear Down 400 Flap 55 KIAS 3 3b MANEUVERING SPEEDS 2750 Ibs 118 KIAS 1865 Ibs 96 KIAS 3 3c NEVER EXCEED SPEED Never Exceed Speed 183 KIAS...

Page 38: ...ahead is rough or if it is necessary to clear obstructions Gear Selector Switch UP Ifsufficient altitude has been gained to attempt a restart Maintain safe airsp d Fuel Selector SWITCH to tank contai...

Page 39: ...OWER OFF LANDING 3 15 Trim for 79 KIAS Locate suitable field Establish spiral pattern 1000 ft above field at downwind position for normal landing approach When field can be easily reached slow to 72 K...

Page 40: ...rspeed 3 Se FIRE IN FLIGHT 3 17 Source of Fire ClIECK Electrical Fire Smoke in Cabin BAIT MASTR Switch OFF I ALTR Switch OFF Vents OPEN Cabin Heat OFF Land as soon as practical Engine Fire Fuel Select...

Page 41: ...ECTRICAL FAILURE 3 25 ALT annunciator light illuminated containing fuel Ammeter CHECK to VERI FY inop alt If ammeter shows zero ALTR Switch OFF Reduce electrical loads to minimum ALTNTR FIELD Circuit...

Page 42: ...decrease within five minutes BATT MASTR Switch OFF Land as soon as possible CAUTION If the battery is depleted the landing gear must be lowered using the emergency extension procedure The gear positio...

Page 43: ...tor Bulbs CHECK Iflanding gear does not check down and locked Airspeed REDUCE BELOW 87 KIAS Landing Gear Selector Switch GEAR DOWN POSITION If gear has still failed to lock down move and hold the emer...

Page 44: ...ght Slow airplane to 87 KIAS Cabin Vents CLOSE Storm Window OPEN If upper latch is open LATCH If side latch is open PULL on ARMREST while moving Latch Handle to LATCH position If both latches are open...

Page 45: ...SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA 28R 201 ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1365 3 10 ISSUED SEPTEMBER IS 1988...

Page 46: ...ng to try to pull the fire into the engine In either of the above cases if fire continues for more than a few seconds the fire should be extinguished by the best available external means The fuel sele...

Page 47: ...o another tank containing fuel and turn the electric fuel pump to ON Move the mixture control to RICH and the alternate air to OPEN Check the engine gauges for an indication of the cause of the power...

Page 48: ...nd feet of altitude If possible notify the FAA by radio of your difficulty and intentions If another pilot or passenger is aboard let him help When you have located a suitable field establish a spiral...

Page 49: ...The seat belts and shoulder harness should he tightened Touchdown should normally be made at the lowest possible airspeed NOTE If the battery master switch is OFF the landing gear cannot be retracted...

Page 50: ...select the battery master BAIT MASTR and alternator ALTR switches OFF If the terrain permits a landing should be made immediately NOTE The possibility of an engine fire in flight is extremely remote...

Page 51: ...aybe caused bya low oil level an obstruction in the oil cooler damaged or improper baffle seals a defective gauge or other causes Land as soon as practical atan appropriate airport and have the cause...

Page 52: ...d as soon as possible The landing gear must be lowered using the Emergency Landing Gear Extension procedure 3 33 If after turning the BATT MASTR switch OFF the ammeter reading DOES decrease turn the B...

Page 53: ...alternator ALTR switches are ON and that the circuit breakers have not opened If it is in daytime the NAV LIGHT switch should be turned OFF Check the landing gear indicators for faulty bulbs If the l...

Page 54: ...a racteristics and a normal landing can be made with the door open If both upper and side latches are open the door will trail slightly open and airspeed will be reduced slightly _To close the doorin...

Page 55: ...h should then be moved L then R then back to ROTH If operation is satisfactory on either magneto proceed on that magneto at reduced power with full RICH mixture to a landing at the first available air...

Page 56: ...cklist 4 13 4 7 NORMAL START COLD ENGINE 4 13a 4 7 NORMAL START HOT ENGINE 4 13b 4 7 ENGINE START WHEN FLOODED 4 13c 4 7 ENGINE START WITH EXTERNAL POWER SOURCE 4 13d 4 7 4 5d Warm Up Checklist 4 IS 4...

Page 57: ...Cockpit 4 5a 4 9b Right Wing 4 5a 4 9c Nose Section 4 5a 4 9d Left Wing 4 5a 4 ge Fuselage 4 5a 4 11 BEFORE STARTING ENGINE 4 Sb 4 13 ENGINE START 4 5c 4 13a Normal Start Cold Engine 4 5c 4 13b Norma...

Page 58: ...4 43 BEFORE TAKEOFF 4 5g TAKEOFF 4 Sh Normal Technique 4 5h Short Field Obstacle Clearance And Soft Field Techniques 4 5h CLIMB 4 5i CRUISE 4 5j APPROACH AND LANDING 4 5k STOPPING ENGINE 4 5m MOORING...

Page 59: ...SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA 28R 201 ARROW REPORT VB 1365 ISSUED SEPTEMBER 15 1988 4 iv THIS PAGE INTENTIONALLY LEFT BLANK...

Page 60: ...Pilots should familiarize themselves with these procedures to become proficient in the normal operation of the airplane This section is divided into two parts The first part is a short form checklist...

Page 61: ...rom published figures depending upon the equipment installed the condition of the engine airplane and equipment atmospheric conditions and piloting technique a Best Rate of Climb Speed gear up flaps u...

Page 62: ...ION The flap position should be noted before boarding the airplane The flaps must be placed in the UP position before they will lock and support weight on the step COCKPIT 4 9a Control Wheel release r...

Page 63: ...or CLOSE and SECURE RIGHT WING 4 9b Surface Condition CLEAR of ICE FROST SNOW Flap and Hinges CHECK Aileron and Hinges CHECK Static Wicks CHECK SECURE Wing Tip and Lights CHECK Fuel Tank CHECK supply...

Page 64: ...5 in Nose Wheel Tire CHECK CAUTION When draining any amount of fuel care should be taken to ensure that no fire hazard exists before starting engine Fuel Strainer DRAIN LEFT WING 4 9d Surface Conditio...

Page 65: ...t CLEAR Empennage CLEAR of ICE FROST SNOW Stabilator and Trim Tab CHECK Tie Down REMOVE Right Static Vent CLEAR BATT MASTR Switch ON Cockpit Lighting CHECK Navigation and Strobe Lights CHECK Landing L...

Page 66: ...1 2 INCH OPEN AL1R Switch ON BAIT MASTR Switch ON Electric Fuel Pump ON Mixture IDLE CUT OFF Propeller CLEAR I Starter ENGAGE Mixture ADVANCE Throttle ADJUST Oil Pressure CHECK ENGINE START WHEN FLOO...

Page 67: ...tery master switch ON This will give longer cranking capabilities but will not increase the amperage Care should be exercised because if the ship s battery has been depleted the external power supply...

Page 68: ...Parking Brake SET Propeller FULL INCREASE Throttle 2000 RPM Magnetos CHECK max drop 175 RPM max diff 50 RPM Vacuum 4 8 to 5 2 inches Hg Oil Temperature CHECK Oil Pressure CHECK Ammeter CHECK Annunciat...

Page 69: ...ever UP POSITION Controls FREE Doors LATCHED Air Conditioner OFF 4 5h Takeoff Checklist 4 23 NORMAL TECHNIQUE 4 23a Flaps SET Trim SET Accelerate to 65 to 75 KIAS Control Wheel back pressure to ROTATE...

Page 70: ...KIAS depending on aircraft weight Gear UP Accelerate to best gear up rate of climb speed 90 KIAS Flaps RETRACT SLOWLY 4 5i Climb Checklist 4 25 CLIMB 4 25 Best Rate 2750 lb Gear Up Flaps Up 90 KIAS B...

Page 71: ...REASE Emergency Gear Extension Lever UP POSITION Gear DOWN 129 KIAS max Flaps SET 103 KIAS max Air Conditioner OFF Trim to 75 KIAS 4 5m Stopping Engine Checklist 4 31 STOPPING ENGINE 4 31 CAUTION The...

Page 72: ...8R lOI ARROW 4 5n Mooring Checklist 4 33 MOORING 4 33 SECTION 4 NORMAL PROCEDllRES Parking Brake SET Flaps FULL UP Control Wheel SECURED with belts Wheel Chocks IN PLACE Tie Downs SECURE ISSUED SEPTEM...

Page 73: ...SECTION 4 NORMAL PROCEDURES PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW THIS PAGE INTENTIONAI LY LEFT BLANK REPORT VB 1365 4 14 ISSllED SEPTEMBER 15 1988...

Page 74: ...ing gear selector handle is in the DOWN position and set the parking brake Ensure that all avionics and electrical switches are OFF Check that the mixture is in the idle cut off and the magneto switch...

Page 75: ...e gear strut for proper inflation there should be 2 0 0 25 inches of strut exposure under a nonnal static load Check the tire for cuts wear and proper inflation Make a visual check of the brake block...

Page 76: ...brake block and disc CAUTION When draining any amount of fuel care should be taken to ensure that no fire hazard exists before starting engine The fuel tank vent should be clear of obstructions Drain...

Page 77: ...ly on the str p Fasten seat belts on empty seats 4 11 BEFORE STARTING ENGINE 4 Sb Before stardng the engine set the parking brake ON Check that all circuit breakers are in and that the alternate air i...

Page 78: ...l than the external power supply ISSUED SEPTEMBER 15 1988 REPORT VB 1365 REVISED MARCH 10 1989 4 19 PIPER AIRCRAFT CORPORATION SECTION 4 PA 28R 201 ARROW NORMAL PROCEDURES 4 13 ENGINE START 4 5c conti...

Page 79: ...ied person authorized by the owner Ascertain that the propeller back blast and taxi areas are clear SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA 28R 201 ARROW REPORT VB 1365 ISSUED SEPTEM...

Page 80: ...ration on one magneto should not exceed 10 seconds Check the vacuum gauge the indicator should read between 4 8 and 5 2 inches Hg at 2000 rpm Retard the throttle Check both oil temperature and oil pre...

Page 81: ...and response of all flight controls All doors should be properly secured and latched On air conditioned models the air conditioner must be OFF to ensure normal takeoff performance 4 23 TAKEOFF 4 5h 4...

Page 82: ...full throttle and 2700 rpm must be used 4 27 CRUISE 4 5j Following level off for cruise the airplane should be trimmed The cruising speed of the Arrow is determined by many factors including power set...

Page 83: ...fuel flow indication is considerably higher than the fuel actually being consumed a fuel nozzle may be clogged and require cleaning There are no mechanical uplocks in the landing gearsystem In the eve...

Page 84: ...amount of flap used during landings and the speed of the aircraft at contact with the runway should be varied according to the landing surface and conditions of wind and airplane loading It is genera...

Page 85: ...belt through the control wheel and pulling it snug Tiedowns can be secured to rings provided under each wing and to the tail skid The rudder is held in position by its connections to the nose wheel st...

Page 86: ...l automatically dim The red gear warning light on the instrument panel and the gear warning horn operate simultaneously in flight when the throttle is reduced to where the manifold pressure is approxi...

Page 87: ...e level of this aircraft is 75 5 d B A No determination has been made by the Federal Aviation Administration that the noise levels of this airplane are or should be acceptable or unacceptable for oper...

Page 88: ...E OF CONTENTS SECTION 5 PERFORMANCE SECTION 5 PERFORMANCE Page No 5 1 General 5 1 5 3 Introduction to Performance and Flight Planning 5 1 5 5 Flight Planning Example 5 3 5 7 Performance Graphs 5 9 Lis...

Page 89: ...cal deterioration of the aircraft This performance however can be duplicated by following the stated procedures in a properly maintained airplane Effects ofconditions not considered on the charts must...

Page 90: ...SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA 28R 20I ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1365 5 2 ISSUED SEPTEMBER 15 1988...

Page 91: ...Form Figure 6 11 and the C G Range and Weight graph Figure 6 15 to deter mine the total weight of the airplane and the center of gravity position After proper utilization of the information provided t...

Page 92: ...ce calculations are performed in the same manner using the existing conditions at the destination airport and when established the landing weight The conditions and calculations for the example flight...

Page 93: ...onents for the climb segment of the flight plan corrected for field pressure altitude and temperature The following values were determined from the above instruc tions in theflight planning example 1...

Page 94: ...r to the Power Setting Table Figure 5 23 or 5 23a when selecting the cruise power setting The established pressure altitude and temperature values and the selected cruise power should now be utilized...

Page 95: ...and descent graphs are in minutes and must be converted to hours before adding them to the cruise time The following flight time is required for the flight planning example 1 Total Flight Time c 4 plu...

Page 96: ...SECTIONS PERFORMANCE PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1365 5 8 ISSUED SEPTEMBER 15 1988...

Page 97: ...akeoff Performance Over 50 Foot Barrier 5 17 5 15 0 Flap Takeoff Ground Roll 5 18 5 17 Gear Up Climb Performance 5 19 5 19 Gear Down Climb Performance 5 20 5 21 Fuel Time and Distance to Climb 5 21 5...

Page 98: ...1aBest Economy Range 25OORPM 5 28 5 33 Best Power Endurance 2500 RPM 5 29 5 33aBest Power Endurance 2200 RPM 5 29a 5 33bBest Economy Endurance 2500 RPM 5 29b 5 33cBest Economy Endurance 2500 RPM 5 29c...

Page 99: ...w c w c a 6000 4000 2000 S L Example Altitude 6000 ft ISA temperature 3 0 C 30 20 10 o SECTIONS PERFORMANCE _ Example r 100 C 6000FT ISA 7 10 20 30 40 50 AIR TEMPERATURE 0 C AIR TEMPERATURES ABOVE BEL...

Page 100: ...PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW SECTION 5 PERFORMANCE THIS PAGE INTENTIONALLY LEFT BLANK I REPORT VB 1365 5 10b ISSUED SEPTEMBER 15 1988 REVISED MAY 8 1995...

Page 101: ...N PA 28R 201 ARROW 100 90 80 70 60 50 40 FAHRENHEIT DEGREES 30 20 10 0 10 20 30 40 40 30 20 10 0 10 20 30 40 SECTION 5 PERFORMANCE CELSIUS DEGREES TEMPERATURE CONVERSION Figure 5 1 ISSUED SEPTEMBER 15...

Page 102: ...II tl 0 E i 0 0 0 0 SilO CD mal Z J b III i 0 osg 0 0 1 1 0 Z a t a ON 0 Z I 01 z 01 i 011 1 W OX Na I I cS2 CIJ WW o III I z m 0 0 CIJ oua 0 1 oa w II C 0 0 1 0 u W I W t D 0 CIJ II a E_ 11 0 w 0 0 0...

Page 103: ...2 3 2 o g CiJII Q 0 8 EE gCl J Cu B w m o en i lto oS 0 a i iii o CD F SECTION 5 PERFORMANCE o II o o It om II l w C 0 I lZ ot CD II o O l NZ o o III SImi 033dS lWJ S POWER OFF STALL SPEED VS ANGLE O...

Page 104: ...N FLIGHT AND WIND DEGREES l I I 50 O 10 I iii 40 I I I Z 30 w Z 0 II 1 to II D 2 II II 0 U 20 0 Z 1 rl ll II r 0 II if V 10 W t IJ I l V V 1 0 o 10 REPORT VB 136S 5 14 20 rI 30 J II 40 H 7r Vi l O I 1...

Page 105: ...off speed 57 KIAS _ _ __ _ _ Speed al 50 FT 60 KIAS Takeoff dislance 1850 F T _ l ft iitl j i l r I tt tf j I tH LIFTOFF SPEED KIAS 59 57 55 S 3 51 i I H H_ Rmmt f PEED AT 50 FT KIAS 62 60 58 56 54 H...

Page 106: ...ELEASE 40 20 0 20 40 OUTSfDE AIR TEMP C WING FLAPS 25 PAVED LEVEL DRY RUNWAY T1 M 1 Tn 1 1 LI t 69 LfFTOFF SPEED KIAS 5i l l l 55 3 2600 2400 2200 WEIGHT LBS EXilmple Pressure altitude 1900 FT iii Out...

Page 107: ...69 KIAS Speed alSO FT 69 KIAS Takeoff d slance 2550 FT q iJ POWER 2700 RPM AND FULL THROTTLE BEFORE BRAKE RELEASE PAVED LEVEL DRY RUNWAY r J 0 r flO s s WING FLAPS 0 w Z w II III o II II LIFTOFF AND 6...

Page 108: ...LEVEL DRY RUNWAY 00 II 0 I s rV 20 40 Example Pressure altitude 1900 FT Outside air temperature 20G e Weight 2600 LB Surface wind 4 KT headwind Liftoff speed 66 KIAS Takeoff distance 1950 FT CI CI LIF...

Page 109: ...PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW b 0 SECTION 5 PERFORMANCE o g o GEAR UP CLIMB PERFORMANCE Figure 5 17 ISSUED SEPTEMBER 15 1988 REPORT VB 1365 5 19...

Page 110: ...SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW b o o o CD o o N J II 011 i o 0 I o f GEAR DOWN CLIMB PERFORMANCE Figure 5 19 REPORT VB 1365 5 20 ISSUED SEPTEMBER IS 1988...

Page 111: ...Tl Example Depanure pressure altitude 1900 FT Departure outside air temperature 200 e Cruise pressure altitude 6000 FT Cruise outside air temperature 10 C Fuel to climb 4 gal minus 1 gal 3 gal Time t...

Page 112: ...SECTION S PERFORMANCE PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1365 5 22 ISSUED SEPTEMBER 15 1988...

Page 113: ...48 9 22 6 20 8 25 1 23 1 25 3 3000 4000 45 7 22 3 20 5 24 7 22 8 24 9 4000 5000 41 5 21 9 20 2 24 3 22 4 24 6 5000 6000 38 3 21 6 19 9 24 0 22 1 24 3 6000 6800 35 2 21 3 19 7 23 7 21 9 F T 6800 7000...

Page 114: ...1 24 0 21 8 26 7 24 1 48 9 23 7 21 5 26 3 23 8 45 7 23 3 21 3 26 0 23 6 41 5 22 9 21 1 25 6 23 3 40 4 22 8 21 0 F T 23 2 38 3 22 5 20 8 23 1 34 1 22 1 20 6 22 8 30 1 21 8 20 4 22 6 28 2 21 5 20 2 F T...

Page 115: ...CTION 5 PERFORMANCE O O O O O O O O O O O O J 0 0 0 0 0 0 0 0 0 0 a 0 o 0 0 0 0 0 0 0 0 a a 0 CI N a m ro w V M N 133 1 3an 1I 11 v 3t1nSS3t1d BEST POWER CRUISE 75 Power Figure 5 25 ISSUED SEPTEMBER 1...

Page 116: ...mm mm mm mm mm r 10 r r 0 0 0 0 0 0 0 0 0 0 0 0 J 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 CI C I r 0 0 ex t 0 10 V f C I r r r r 133 1 30n1111V 3HnSS3Hd BEST POWER CRUISE 65 Power REPORT VB 13...

Page 117: ...QI C II c QI II E QI I QI c a I l i3 3 c QI E 2 2 2 OOI o 0 0 0 0 0 0 0 o 0 0 0 0 0 0 0 o 0 0 0 0 0 0 0 C I T 0 J CO CD LO 0 0 0 0 0 0 0 0 0 t C C I 133 1 30n 1I 11 f 3 JnSS3 Jd BEST POWER CRUISE 55 P...

Page 118: ...u a M 5l Q Q Q II II a 2 2 l E 2 U S 0 a a a a a a a 0 0 0 a C I 0 0 a a 0 co h O0A a a a PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW LO C I 0 C I 00 t V oa LOen 0 1 0 0 U Z ol 1 0 oW W a 0 en 0 W LO...

Page 119: ...CJ E 2 m a 0 u 2 I J 8 Qj III J III E 41 LL 2 n l 41 QI III III 0 2 2 E 2 u uu W 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 C I 0 J ex 0 Yo h oOd Ol 0 0 0 0 0 0 0 0 0 LO V I SECTIONS PERFORMANCE 0 I LO...

Page 120: ...0 z l 1 Cl W 0 w G X W c e 10 5 L5 J 0 0 0 a 0 cu a co 0 0 32 Q 0 Z Iii qo Uw W 0 0 0 N J 8 0 0 J J I 0 a C W t Q Q Q l 0 e e C l 8 a III III E Q e G D a 9i 51 51 51 l 0 u E 2 2 2 uuu W 10 a a a a a a...

Page 121: ...PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW SECTIONS PERFORMANCE...

Page 122: ...SECTIONS PERFORMANCE PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW TillS PAGE INTENTIONALLY LEFT BLANK I REPORT VB 1365 5 26d ISSUED SEPTEMBER 15 1988 REVISED MAY 8 1995...

Page 123: ...ONDITIONS Total Range With Reserve 684 NM approx Total Range Without Reserve 770 NM approx 1 1 2750LBS I S A NO WIND EI RangeiJtII Iudes fuel required for takeolif climb powered descent In CD 45 Min R...

Page 124: ...SE RPM 2200 FUEL 72 GALS USABLE ASSOCIATED CONDITIONS 2750 LBS I S A NO WIND Range includes fuel required for 45 Min Reserve 1m takeoff climb powered descent 55 Power FUEL FLOWS Power GPH 65 11 0 ti o...

Page 125: ...Total Range Without Reserve 955 NM FUEL FLOWS It 45 Min Reserve Power GPH I 55 Power 65 9 8 55 8 5 J i 0 MIXTURE PEAK EGT CRUISE RPM 2200 FUEL 72 GALS USABLE ASSOCIATED CONDITIONS 1 1 2750 LBS I S A N...

Page 126: ...FUEL 72 GALS USABLE ASSOCIATED CONDITIONS 2750 LBS I S A NO WIND Range includes fuel required for takeoff climb powered descent 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 I FUELFLOWS Power GP...

Page 127: ...SECTIONS PERFORMANCE PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW 133 1 30ml1 lV 3 nSS3 d BEST POWER ENDURANCE 2500 RPM Figure 5 33 ISSUED SEPTEMBER 15 1988 REVISED MAY 8 1995 REPORT VB 1365I 5 29...

Page 128: ...PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW SECTIONS PERFORMANCE 133 1 3Cn111 1 1 3 nSS3 d BEST POWER ENDURANCE 2200 RPM Figure 5 33a I REPORT VB 1365 5 29a ISSUED SEPTEMBER 15 1988 REVISED MAY 8 1995...

Page 129: ...SECTIONS PERFORMANCE PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW 33 1 30ml 9 3HnSS3Hd BEST ECONOMY ENDURANCE 2200 RPM Figure 5 33b ISSUED SEPTEMBER 15 1988 REVISED MAY 8 1995 REPORT VB 1365 5 29b...

Page 130: ...PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW SECTIONS PERFORMANCE 33 1 3an l 1 9 3 nSS3 d BEST ECONOMY ENDURANCE 2500 RPM Figure 5 33c REPORT VB 1365 5 29c ISSUED SEPTEMBER 15 1988 REVISED MAY 8 1995...

Page 131: ...SECTIONS PERFORMANCE PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW TIDS PAGE INTENTIONALLY LEFT BLANK ISSUED SEPTEMBER 15 1988 REVISED MAY 8 1995 REPORT VB 1365 5 29d...

Page 132: ...W 0 0 C EZ E 2 2 cP ILl uuaau a C UCl a Z O a Cl i2 0 t Cl CD W otN E a i W 3 0 J a W l ll o PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW 0 ID 0 IS w 0 Z 7 OUI M e 4 e z Q w 0 E Ni J W 1It lIi 1 u i1 J...

Page 133: ...ROPELLER FULL DECREASE Example Cruise pressure altitude 6000 FT Cruise outside air temperature 10 C Terrain pressure altitude 2000 FT Terrain outside air temperature 200 e Glide time 7 5 min minus 3 5...

Page 134: ...ind 2 KTS headwind Approach speed 69 KIAS Landing Oistance 1490 FT e fI fl S POWER OFF APPROACH WING FLAPS 400 FULL STALL TOUCHDOWN MAXIMUM BRAKING PAVED LEVEL DRY RUNWAY 0 l 00 APPROACH SPEED KIAS 72...

Page 135: ...lNIONlf1 0 0 II O 41 1 V l C1NIM Oll3Z 3NI1 I11 3NI1 BII B109Le to b lb IP b o o 0 i 1II f 0 LANDING GROUND ROLL DISTANCE Figure 5 41 0 II I 0 ItIItI I Z W oZ O II 0 IJ 0 o 0 0 0 N 0 0 N N 01 8 S iii...

Page 136: ...SECTION S PERFORMANCE PIPER AIRCRAFT CORPORATION PA 28R l01 ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1365 S 34 ISSUED SEPTEMBER IS 1988...

Page 137: ...ALANCE TABLE OF CONTENTS SECTION 6 WEIGHT AND BALANCE Paragraph No 6 1 6 3 6 5 6 7 General Airplane Weighing Procedure Weight and Balance Data and Record Weight and Balance Determination for Flight Pa...

Page 138: ...rformance it will have Center of gravity is a determining factor in flight characteristics If the C G is too far forward in any airplane it may be difficult to rotate for takeoff or landing If the e G...

Page 139: ...and useful load Note that the useful load includes usable fuel baggage cargo and passengers Following this is the method for computing takeoff weight and CO 6 3 AIRPLANE WEIGHING PROCEDURE At the tim...

Page 140: ...in the fully retracted position and all control surfaces in the neutral position Tow bar should be in the proper location and all entrance and baggage doors closed 6 Weigh the airplane inside a close...

Page 141: ...ighed T E a Ol 0 WEIGHING FORM Figure 6 1 d Basic Empty Weight Center of Gravity I The following geometry applies to the PA 28R 201 airplane when it is level Refer to leveling paragraph 6 3 b N Level...

Page 142: ...listed in Figure 6 5 are for the airplane as licensed at the factory These figures apply only to the specific airplane serial number and registration number shown The basicempty weight ofthe airplane...

Page 143: ...bs Actual Standard Empty Weight Computed Optional Equipment Basic Empty Weight The standard empty weight includes full oil capacity and 5 0 gallons of unusable fuel AIRPLANE USEFUL LOAD NORMAL CATEGOR...

Page 144: ...E I Z U 01 ell Q f III E I Z c II 00 III IX f U E I z c U 0 00 0 Q c u uO c E 11101 eII _ 0 t Qu OI 5 C cc I E 0 IXUJ 2 C uo e 0 0 01 C ell c U E c c 01 0 0 J p AOW M p ppv 0 u c 9 0 U U 0 III c C 0...

Page 145: ...ORD continued v 0 E I Z v OIJ t 1 a U 0 E I Z c 2 bh u 0 f u 0 E I Z ca U 00 a u E vO E t 1 _ 0 COv OIJ c C co I E 0 0 u J J C vO E 0 IJ OJ c t 1 r U E c c u 0 P OW lI P PPV v c g 9 u 0 C 0 2 0 o u 0...

Page 146: ...t Lbs Inches In Lbs Basic Empty Weight 1890 84 8 160272 Pilot and Front Passenger 340 0 80 5 27370 Passengers Rear Seats 170 0 118 1 20077 Fuel 72 Gallons Maximum 294 95 0 27930 Baggage 200 Lbs Maximu...

Page 147: ...lowance For Engine Start Taxi and Run Up 8 95 0 760 Moment due to Retraction of Landing Gear 819 Takeoff Weight 2750 Lbs Maximum Totals must be within approved weight and e G limits It is the responsi...

Page 148: ...ORPORATION PA 28R 201 ARROW SECTION 6 WEIGHT AND BALANCE 6 7 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT continued 100 MOMENT 10oo lINCH POUNDS I LOADING GRAPH Figure 6 13 ISSUED SEPTEMBER 15 1988 REP...

Page 149: ...HT AND BALANCE DETERMINATION FOR FLIGHT continued 3000 2800 2800 2400 2375 LB as C 2200 c J i 2000 1800 1600 1400 REPORT VB 1365 6 12 g Q F s 88 8 2750LB MAX WEIGHT 82 84 II II INCHES AFT OF DATUM C G...

Page 150: ...position the zero weight end of anyone of the loading slots over this point Using a pencil draw a line along the slot to the weight which will be carried in that location Then position the zero weigh...

Page 151: ...dot is under the slot for the forward seats pilot and front passenger at zero weight 3 Draw a line up the slot to the 340 pound position 170 170 and place a dol 4 Slide the slotted plastic into positi...

Page 152: ...R USING THE WEIGHT AND BALANCE PLOTTER continued RAMP WEIGHT ANDC G 2750 LBS MAX GROSS WT w G r IS C G C G LOCATION INCHES AFT DATUMI In III SAMPLE PROBLEM Figure 6 17 ISSUED NOVEMBER 8 1989 2750 2700...

Page 153: ...COIISIOIIS TIllS uml 111 AlD IND MDT I SIISTnUTI fat TM CU UTATIOMIIUHOD TO IlTUMIlI THAl TIl WIIMT UI UlAlICI If AN IIIUIFT IS nHUlITS II1OWlII I IIlinS fOI JLI Hf OPlIATiDII 2nD LIS MAX GRO S WI r...

Page 154: ...e Controls 7 4 7 11 Landing Gear 7 6 7 13 Flight Controls 7 10 7 15 Fuel System 7 11 7 17 Electrical System 7 14 7 19 Vacuum System 7 17 7 21 Pitot Static System 7 18 7 23 Instrument Panel 7 20 7 25 C...

Page 155: ...the rear seat The wing is of a conventional design semi tapered and employs a laminar flow NACA 652 415 airfoil section The main spar is located at approximately 40 of the chord aft of the leading edg...

Page 156: ...from time to time revises the 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...

Page 157: ...rs fuel flow proportionally with airflow and maintains the mixture as manually set for all engine speeds The fuel flow divider receives metered fuel and distributes fuel to each cylinderfuel nozzle Th...

Page 158: ...advertent gear up landing The propeller control lever is used to adjust the propeller speed from high rpm to low rpm The mixture control lever is used to adjust the air to fuel ratio The engine is shu...

Page 159: ...PER AIRCRAFT CORPORATION SECTION 7 PA 28R 201 ARROW DESCR OPERATION ISSUED SEPTEMBER 15 1988 REPORT VB 1365 7 5 7 7 ENGINE CONTROLS continued CONTROL QUADRANT AND CONSOLE Figure 7 1 RUDDER TRIM CONTRO...

Page 160: ...to the left of the flap handle figure 7 9 should be in the up position to permit proper gear retraction operation To perform an emergency gear extension the emergency gear lever must be held in the d...

Page 161: ...of center through the use of the rudder pedals As the nose wheel retracts the steering linkage disengages to reduce rudder pedal loads in flight The nose wheel is equipped with a hydraulic shimmy dam...

Page 162: ...D POSITION WITH STRUTS COMPftE l5 D AND THROTTLE CLOSED 2 LIGHT LEGEND R REDltGHT G GRlEN LIGHT 3 SWITCH LEGEND C COMMON NC NORMAllY CLOSED NO MCANALLY OPEN 5AMP TERMINAL 1 1 TO HA I LIGHT SWITCH GEAR...

Page 163: ...IlIERIlAL REUEF lOW PRESSURE CONTROL MAINGI AR HYDRAULIC CYLINOER MANUAL FREE FALL EMERGENCY EXTEND ORIFICE NOSE GEAR HYDRAULIC CYLINDER SHUTTLE VALVI GEAR DOWN 9NUIIIIER ORIFICE EMERGENCY FREE FALL G...

Page 164: ...oviding trim control and pitch control forces The trim function is controlled by a trim control wheel located on the control console between the two front seats Figure 7 9 Rotating the wheel forward g...

Page 165: ...allon tanks one in each wing Of the total 77 gallon capacity Qnly 72 gallons are usable Each tank is equipped with a filler neck indicator tab to aid in determining fuel remaining when the tanks are n...

Page 166: ...EL SYSTEM continued FUEL NOZZLE FUEL DISTRIBUTOR SERVO REGULATOR It ENGINE DRIVEN FUEL PUMP t ELECTRIC FUEL PUMP FILTER AND DRAIN SUPPLY LINE 0 I FUEL SELECTOR I FUEL SELECTOR VALVE QUANTITY GAUGES RE...

Page 167: ...tor points to the tank which is supplying fuel to the engine The valve also incorporates a safety latch which prevents inadvertently selecting the OFF position Normally fuel is supplied to the engine...

Page 168: ...ation ground recognition anti collision landing instrument panel and cabin dome lights The navigation lights are controlled by a rocker switch on the main switch panel Radio panel and switch lights ar...

Page 169: ...INSTR LTS PANEL CLOCK OPTlONS J OIL t PRESSURE SWITCH ANNUNCIATOR LIGHTS AMMETER TO ENGINE S MAGNETOS o _ E TI A VACUUM OIL PRESS SENSOR IISENSOR BATTERY CONTACTOR TOUGHT OI WH STARTER CONTACT OR OPT...

Page 170: ...ercast and clouds since reflected light can produce spacial disorientation Do not operate strobe lights in close proximity to ground during takeoff and landing The primary electrical power source is a...

Page 171: ...he system components or eventual failure of the system ISSUED SEPTEMBER 15 1988 REPORT VB 1365 7 17 PIPER AIRCRAFT CORPORATION SECTION 7 PA 28R 201 ARROW DESCR OPERATION 7 17 ELECTRICAL SYSTEM continu...

Page 172: ...ero readings on the instruments NOTE During preflight check to make sure the pitot cover is removed SECTION 7 PIPER AIRCRAFT CORPORATION DESCR OPERATION PA 28R 201 ARROW REPORT VB 1365 ISSUED SEPTEMBE...

Page 173: ...PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW 7 21 PITOT STATIC SYSTEM continued SECTION 7 DESCR OPERA TION PITOT STATIC SYSTEM Figure 7 19 ISSUED SEPTEMBER 15 1988 REPORT V8 1365 7 19...

Page 174: ...en r ca PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW 0 N e m il r is i ell u t J l e i J r 1 c i O j Ell a Ol i i 0 r i Ii 8 Ij 1 0 I U e eli 1 Ii Ii fl ell eii i 0 r j CI CO CD r eo m 0 1ft INSTRUMEN...

Page 175: ...OLS QUADRANT 17 COMMUNICATIONS TRANS 31 AIR CONDITIONER DOOR UGHT CEIVER 32 E G T GAUGE 18 AREA NAVIGATION 33 LANDING GEAR SELECTOR RECEIVER 34 LANDING GEAR POSITION 19 NAVIGATION COMMUNICATIONS 35 LE...

Page 176: ...d on the bottom row of the main switch panel When the battery master BATT MASTR switch is turned ON power is supplied to the avionics master relay switch opening the contactors and preventing current...

Page 177: ...echanisms which must be released before the rear seats can be removed Releasing the retainers is accomplished by depressing the plunger behind each rear leg Optional headrests are available Seat occup...

Page 178: ...occupants cabin or baggage door locks and ignition lock The Arrow cabin door is double locked To close the cabin door hold the door closed with the armrest while moving the side door latch to the LATC...

Page 179: ...control located on the right side of the instrument panel Defrosting is accomplished by heat outlets located on the right and left side of the cowl cover Heated air is ducted directly to defroster shu...

Page 180: ...OPERATION PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW 7 29 HEATING VENTILATING AND DEFROSTING SYSTEM continued a j I HEATING VENTILATING AND DEFROSTING SYSTEM Figure 7 25 REPORT VB 1365 7 26 ISSUED SE...

Page 181: ...conomy size spray cans of touchup paint are available from Piper Dealers 7 35 AIR CONDITIONING The air conditioning system is a recirculating air system The major components include an evaporator a co...

Page 182: ...n the system OFF until the fault is corrected The fan switch allows operation of the fan with the air conditioner turned OFF to aid in cabin air circulation LOWor HIGH can be selected to direct a flow...

Page 183: ...ter To comply with FAA regulations the battery must be replaced on or before this date The battery must also be replaced if the transmitter has been used in an emergency situation or if the accumulate...

Page 184: ...ace of the ELT and then moving the switch to ARM A pilot s remote switch located on the left side panel is provided to allow the transmitter to be turned on from inside the cabin The pilot s remote sw...

Page 185: ...lines Should the ELT be activated inadvertently it can be reset by either positioning the remote switch to the ON position for two seconds and then relocating it to the ARM position or by setting the...

Page 186: ...SECTION 7 DESCRIOPERATION PIPER AIRCRAFf CORPORATION PA 28R 201 ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 136S 7 32 ISSUED SEPTEMBER 15 1988 REVISED APRIL 9 1990...

Page 187: ...tion Periods 8 2 8 5 Preventive Maintenance 8 3 8 7 Airplane Alterations 8 3 8 9 Ground Handling 8 4 8 11 Engine Air Filter 8 7 8 13 Brake Service 8 7 8 15 Landing Gear Service 8 9 8 17 Propeller Serv...

Page 188: ...ion is incorporated on the airplane those portions of the airplane affected by the installation must be inspected in accordance with the inspection program published by the owner of the STC Since non...

Page 189: ...rent in fabrication techniques and materials and may be dangerous when installed in an airplane Additionally reworked or salvaged parts or those parts obtained from non PIPER approved sources may have...

Page 190: ...egarding the airplane should include the airplane model and serial number to ensure proper response PIPER AIRCRAFT CORPORATION SECTION 8 PA 28R 201 ARROW HAND SERV MAINT ISSUED SEPTEMBER 15 1988 REPOR...

Page 191: ...uthorized Service Center or a reputable repair shop Piper cannot accept responsibility for the continued airworthiness of any aircraft not maintained to these standards and or not brought into complia...

Page 192: ...ain a The date the work was accomplished b Description of the work c Number of hours on the aircraft d The certificate number of pilot performing the work e Signature of the individual doing the work...

Page 193: ...ground by the use ofthe nose wheel steering bar that is stowed in the rear baggage compartment or by power equipment that will not damage or excessively strain the nose gear steering assembly The ste...

Page 194: ...If possible station an observer outside the airplane 5 When taxiing over uneven ground avoid holes and ruts 6 Do not operate the engine at high rpm when mnning up or taxiing over ground containing loo...

Page 195: ...he control wheel and pulling it snug 4 Block the wheels 5 Secure tiedown ropes to the wing tiedown rings and to the tail skid at approximately 45 degree angles to the ground When using rope of non syn...

Page 196: ...ge re place it immediately 3 Wipe the filter housing with a clean cloth soaked in un leaded gasoline When the housing is clean and dry install the filter c Installation of Engine Air Filter After clea...

Page 197: ...SECTION 8 HAND SERV MAINT PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW 8 13 BRAKE SERVICE continued I I REPORT VB 1365 8 8 BRAKE SYSTEM Figure 8 1 ISSUED SEPTEMBER IS 1988...

Page 198: ...excess air and oil to escape With the strut still compressed reinsert the valve stem and pump up the strut as mentioned above In jacking the aircraft for landing gear or other service two hydraulic ja...

Page 199: ...ded that the oil be drained and renewed and oil filter be changed every 50 hours or sooner under unfavorable operating conditions The interval between oil and oil filter change is not to exceed four 4...

Page 200: ...Chart Refer to the latest issue of Lycoming Service Instruction No 1070 Avco Lycoming Specifted Fuels A summary of the current grades as well as the previous fuel designations is shown in the followin...

Page 201: ...should be carefully followed CAUTIONS Assure that the additive is directed into the flowing fuel stream The additive flow should start after and stop before the fuel flow Do not permit the concentrate...

Page 202: ...orward slope of the wing Each wing holds a maximum of38 5 U S gallons When using less than the standa d 77 gallon capacity fuel should be distributed equally between each side NOTE Aircraft should be...

Page 203: ...ning Fuel System The bulk of the fuel may be drained from the fuel cells by the use of a siphon hose placed in the cell or tank through the filler neck The remainder of the fuel may be drained by open...

Page 204: ...r amperes and finishing with a rate oftwo amperes The battery should be removed from the airplane for charging and quick charges are not recommended The external power receptacle if installed is locat...

Page 205: ...h the gear area with solvent or a mixture of solvent and degreaser as desired Where heavy grease and dirt deposits have collected it may be necessary to brush areas that were sprayed in order to clean...

Page 206: ...s will reduce the abrasion problems in these areas d Cleaning Windshield and Windows I Remove dirt mud and other loose particles from exterior surfaces with clean water 2 Wash with mild soap and warm...

Page 207: ...be cleaned with saddle soap or a mild hand soap and water 0 Cleaning Carpets To clean carpets first remove loose dirt with a whisk broom or vacuum For soiled spots and stubborn stains use a nonflam m...

Page 208: ...Piper Electric Pitch Trim 4 pages 9 7 3 Auxiliary Vacuum System 6 pages 9 11 4 Piper Control Wheel Clock Installation 4 pages 9 17 5 King KNS 80 Area Navigation System 14 pages 9 21 6 King 100 Series...

Page 209: ...irplane when equipped with one or more of the various optional systems and equipment not provided with the standard airplane All of the Supplements provided by this section are FAA Approved and consec...

Page 210: ...SECTION 9 SUPPLEMENTS PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 136S 9 2 ISSUED SEPTEMBER IS 1988...

Page 211: ...per Drawing No 99598 2 The information contained herein supplements or supersedes the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein For lim...

Page 212: ...com pressor and retract the condenser door Also the air conditioner must be turned OFF manually before the landing approach in preparation for a possible go around b Placards In full view of the pilo...

Page 213: ...d prior to flight The above operational check may be performed during flight if an in flight failure is suspected The condenser door light is located to the right of the tachometer in front of the pil...

Page 214: ...al miles for the 72 gallon usable fuel capacity The climb performance is not compromised measurably with the air conditioner operating since the compressor is declutched and the condenser door is retr...

Page 215: ...No 67496 3 The I information contained herein supplements or supersedes the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein For limitations...

Page 216: ...y activating pitch trim switch on pilot s control yoke to OFF position b In case of emergency electric pitch trim may be overpowered using manual pitch trim and or control wheel pressure c In cruise c...

Page 217: ...lOI ARROW SECTION S PERFORMANCE SECTION 9 SUPPLEMENT 1 No changes to the basic performance provided by Section 5 of this Pilot s Operating Handbook are necessary for this supplement ISSUED SEPTEMBER...

Page 218: ...SECTION 9 SUPPLEMENT 2 PIPER AIRCRAFT CORPORATION PA 28R 20I ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1365 ISSUED SEPTEMBER 15 1988 9 10 4 of 4...

Page 219: ...Piper Drawing No 89311 2 The information contained herein supplements or supersedes the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein For...

Page 220: ...s below 4 8 In Hg c The auxiliary pump motor assembly and elapsed time indicator must be removed from service after 500 hours accumulated operating time or to years whichever occurs first SECTION 3 EM...

Page 221: ...lectrical load increase of approximately 15 amps on the ammeter 3 Turn off the auxiliary vacuum pump and verify that the AUX ON light has extinguished b Inflight Check 1 Turn off non essential electri...

Page 222: ...VAC for the auxiliary pump system is located on the main electrical switch panel in the center of the instrument panel above the throttle quadrant The control switch operating modes are push for on a...

Page 223: ...feature If the lights do not illuminate as expected check for burned out lamps replace with MS 25237 330 bulbs and retest the system The pump motor electrical circuit is protected by a 20 amp AUX VAC...

Page 224: ...SECTION 9 SUPPLEMENT 3 I PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW V ACUUM SYSTEM SCHEMA TIC REPORT VB 1365 ISSUED SEPTEMBER IS 1988 9 16 6 of 6...

Page 225: ...87347 2 The information contained herein supplements or supersedes the information in the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein For...

Page 226: ...ons provided by Section 2 of this Pilot s Operating Handbook are necessary for this supplement SECTION 3 EMERGENCY PROCEDURES No changes to the basic Emergency Procedures provided by Section 3of this...

Page 227: ...are flashing in the set mode pressing the RST button will return the clock to the normal tim keeping mode without altering the minutes timing This feature is useful when changing timeIzones when only...

Page 228: ...SECTION 9 SUPPLEMENT 4 PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1365 ISSUED SEPTEMBER 15 1988 9 20 4 of 4...

Page 229: ...64 2 The information contained herein supplements or supersedes the information in the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein For li...

Page 230: ...EDURES The following test can be used to determine if the system is operating properly a Tune the KNS 80 to a VORTAC VOR DME within 25 NM of the airplane b Place the KNS 80 in VOR mode and rotate the...

Page 231: ...y 3 Select a waypoint I radial by first depressing the DATA button This will cause the radial for the previous waypoint I to appear in the data display over the annunciation RAD Select the radial with...

Page 232: ...off check to be sure that RNV ENR is still the active mode then depress the DSP button to place waypoint I in the DSP position The selected waypoint I frequency will automatically appear in the data d...

Page 233: ...t if desired waypoint 2 radial and distance data may be rechecked by depressing the DATA button for each I When satisfied depress the USE button to put waypoint 2 data in use The number 2 will appear...

Page 234: ...e VORTAC and VORl PAR function will remain annunciated along with the active ILS function Now reselect the same VOR and the ILS annunciation will cancel and it will revert back to VORl PAR mode HLD wi...

Page 235: ...ows to reduce pilot workload during the final approach segment Waypoint Number Use repetitively for initial and intermediate fixes See note below 2 Final Approach Fix FAF Coordinates 3 Missed Approach...

Page 236: ...UM LENGTH OF FINAL APPROACH SEGMENT IN NAUTICAL MILES Approach Category Approach Magnitude of Turn Over Final Category S peed Requirements Approach Waypoint Intercept Angle 10 20 30 40 50 600 A Less t...

Page 237: ...hen switched out of an ILS frequency the system will revert back to the mode in which it was at the time the ILS frequency was selected When energized the system will go to the mode in which it was wh...

Page 238: ...t oto 999 knots in I knot steps Update rate is once per second Most significant digit is zero blanked Displays dashes whenever DME goes into search c ILS Display Indicates that the frequency in use is...

Page 239: ...o blanked 10 NM digit overflows into or underflows from 100 NM digit The two most significant digits roll over from 190 to 0 NM and vice versa f USE Display Displays waypoint number of data actually b...

Page 240: ...ty Flagged if localil er data is invalid CONTROLS a VOR Button Momentary pushbutton When pushed while system is in either RNV mode causes system to go to VOR mode When pushed while system is in either...

Page 241: ...ob has IN and OUT positions I Frequency Data Outer knob varies I MHz digit A carry occurs from units to tens position Rollover occurs from 117 to 108 Center knob varies frequency in 50 KHz steps 2 Rad...

Page 242: ...SECTION 9 SUPPLEMENT 5 PIPER AIRCRAFT CORPORATION PA 18R 10l ARROW For additional information consult the King KNS 80 Pilot s Guide REPORT VB 1365 ISSUED SEPTEMBER 15 1988 9 34 14 of 14...

Page 243: ...th STC SA 1563CE D The information contained herein supplements or supersedes the information in the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed...

Page 244: ...t Control System is installed SECTION 2 LIMITATIONS A The autopilot must be OFF during takeoff and landing SECTION 3 EMERGENCY PROCEDURES A SYSTEM WITH AUTOPILOT ONLY I In casc of Autopilot malfunctio...

Page 245: ...nnunciator lights on TRIM annunciator flashing b After approximately 5 seconds all annunciator lights off except AP which will flash approximately 12 times and then remain off NOTE If TRI M warning li...

Page 246: ...ing Changes with optional CWS Button only a Manual Heading Changes with optional CWS Button only I CWS button PRESS and MANEUVER airplane to the desired heading 2 CWS button RELEASE Autopilot will mai...

Page 247: ...re track sequency will automatically begin b When equipped with DG I OBS Knob SELECT desired course 2 NAV Mode Selector Button PRESS 3 Heading Selector Knob ROTATE BUG to agree with OBS course NOTE Wh...

Page 248: ...t is reached the HDG will disengage the APR annunciator will illuminate steady and the selected course will be automatically captured and tracked b If the D Bar is less than 2 to 3 dots the HDG mode w...

Page 249: ...AV 2 switching and NAV 2 is selected set OBS to the ILS front course inbound heading 2 HEADING Selector Knob SET BUG to provide desired intercept angle 3 BC Mode Selector Button PRESS a Irthe Course D...

Page 250: ...will be automatically captured and tracked b If the D Bar is less than 2 to 3 dots the HDG mode will disengage upon selecting BC mode the BC and APR annunciators will illuminate steady and the capture...

Page 251: ...nd aurally annunciated A lockout device prevents autopilot engagement until the system has been successfully preflight tested The following conditions will cause the Autopilot to automatically disenga...

Page 252: ...T TRIM Illuminates continuously whenever trim power is not on or the system has not been pre flight tested The TRIM warning light will flash and be accompa nied by an audible warning whenever a manual...

Page 253: ...will select the Approach mode This mode provides all angle intercept with HSl or a fixed angle intercept of 45 with DG automatic beam capture and tracking of VOR RNAV or LOC signals The tracking gain...

Page 254: ...olic airplane to present pitch attitude Scale graduated at 0 5 0 15 20 and 25 degrees 5 SYMBOLIC AIRPLANE Serves as a stationary symbol of the aircraft Aircraft pitch and roll attitudes are displayed...

Page 255: ...en a NAV flag is present in the navigation indicator CDI or KI 525A the autopilot operation is not affected The pilot must monitor the navigation indicators for NAV flags to ensure that the Autopilot...

Page 256: ...ope beam centerline 9 RECIPROCAL COURSE INDEX Indicates reciprocal of se lected VOR course 10 OMNI BEARING SELECTOR OBS KNOB Rotates course card to selected course I COURSE DEVIATION NEEDLE Indicates...

Page 257: ...ss card 10 The selected VOR radial or localizer heading remains set on the compass card when the compass card 10 rotates 6 TO FROM INDICATOR FLAG Indicates direction of VOR station relative to selecte...

Page 258: ...A course deviation bar displace ment ofSdots represents full scale VOR 10 LOC 21 2 RNAV SNM RNAV APR 1 1 4NM deviationfrom beam centerline 14 HEADING BUG Moved by Q knob 9 to select desired heading 1...

Page 259: ...s to display heading of airplane with reference to lubber line 4 on HSI or DG S HEADING SELECTOR KNOB Positions heading Bug 3 on compass card 4 by rotating tile heading selector knob The Bug rotates w...

Page 260: ...e right half to control the direction of motion of the trim servo motor Both halves of the split trim switch must be actuated in order for the manual trim to operate in the desired direction 3 CONTROL...

Page 261: ...avionics bus bar of the radio circuit breakers and the autopilot circuit breaker The following circuit breakers are used to protect the following elements of the King KA P 100 Autopilot AUTOPILOT Sup...

Page 262: ...SECTION 9 SUPPLEMENT 6 PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 136S ISSUED SEPTEMBER 15 1988 9 54 20 of 20...

Page 263: ...ce with STC SAI563CE D The information contained herein supplements or supersedes the infor mation in the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas l...

Page 264: ...tem is installed SECTION 2 LIMITATlONS A During autopilot operation a pilot with scat belt fastened must be seated at the left pilot position R The autopilot must be OFF during takeoff and landing C T...

Page 265: ...n Configuration Cruise Climb Descent Maneuvering APPR SECTION 4 NORMAL PROCEDURES A PREFLIGHT Perform prior to each flight ALT Loss 550 100 100 I GYROS Allow 34 minutes for gyros to come up to speed 2...

Page 266: ...s to engage autopilot 7 CONTROL WHEEL MOVE fore aft left and right to verify that the autopilot can be overpowered 8 AP DISC TRIM INTER Switch PRESS Verify that the autopilot disconnects and all light...

Page 267: ...y airplane to desired pressure altitude b CWS Button RELEASE when desired pressure altitude is reached The autopilot will maintain the desired pressure altitude 2 Using Vertical Trim Recommended for a...

Page 268: ...BS to the desired course 2 HEADING Selector Knob SET BUG to provide desired intercept angle 3 NAV Mode Selector Button PRESS a If the Course Deviation Bar is greater than 2 to 3 dots the aircraft will...

Page 269: ...less than 2 to 3dots the HOG mode will disengage upon selecting NAV mode the NAV annunciator will illuminate steady and the capture track sequence will automatically begin 7 Approach APR Coupling a Wh...

Page 270: ...osition of the bug a If the O Bar is greater than 2 to 3 dots the auto pilot will annunciate HOG mode unless HOG not selected and APR flashing when the computed capture point is reached the HOG annunc...

Page 271: ...nnunciators will illuminate steady and the capture track sequence will automatically begin b When equipped with DG I OBS Knob SELECT the ILS front course inbound heading 2 BC Mode Selector Button PRES...

Page 272: ...Jideslope centering NOTE GS annunciator ON NOTE Autopilot can capture glideslope from above or below the beam while operating in either pitch attitude hold or ALT hold modes 10 Missed Approach a AP DI...

Page 273: ...and balance data in Section 6 of the basic Pilot s Operating Handbook SECTION 7 DESCRIPTION AND OPERATION The 150 Series AFCS is certified in this airplane with 2 axis control pitch and roll The vario...

Page 274: ...cess of 16 per second will cause the autopilot to disengage except when the CWS switch is held depressed E Pitch rates in excess of 6 per second will cause the autopilot to disengage except when the C...

Page 275: ...one whenever an autolrim failure occurs The autotrim system is monitored for the following failures trim servo running without a command trim servo not running when commanded to run trim servo running...

Page 276: ...racking of VOR RNAV or LOC signals The NAV annunciator will flash until the automatic capture sequence is initiated On the KA 185 Remote Mode Annunciator NAV ARM will annunciate until the automatic ca...

Page 277: ...R _ Complete Autopilot computer including system mode annun ciators and system controls 2 VERTICAL TRIM CONTROL A spring loaded to center rocker switch which will provide up or down pitch command chan...

Page 278: ...im circuit breaker may be cycled off to silence the continuous tone but the trim fail light will remain on The manual electric trim may be used but the autopilot should not be engaged 6 AUTOPILOT ANNU...

Page 279: ...eam capture and tracking of VOR RNAV or LOC signals The NAV annunciator will flash until the automatic capture sequence is initiated On the KA 185 Remote Mode Annunciator NA V ARM will annunciate unti...

Page 280: ...ignal returns within six seconds the autopilot will automatically recouple in the GS mode If the valid signal does not return within six seconds the auto pilot will remain in pitch attitude hold mode...

Page 281: ...2 seconds 7 ARMED ARM ANNUNCIATOR Illuminates continuously along with NAV or APR when either the NAV or APR mode selector button is depressed The ARM annunciator will continue to illuminate until the...

Page 282: ...Scale graduated at 0 5 10 15 20 and 25 degrees 5 COMMAND BAR Displays computed steering commands referenced to the symbolic airplane The command bar is visible only when FD mode is selected The comman...

Page 283: ...lic airplane to present pitch attitude Scale graduated at 0 5 10 15 20 and 25 degrees 5 SYMBOLIC AIRPLANE Serves as a stationary symbol of the airplane Airplane pitch and roll attitudes are displayed...

Page 284: ...ndicator CDI or KI 525A the autopilot operation is not affected The pilot must monitor the navigation indicators for NAVflags to ensure that the Autopilot and or Flight Director are tracking valid nav...

Page 285: ...m centerline 9 HEADING SELECTOR KNOB Positions heading bug 14 on compass card 10 by rotating the heading selector knob The Bug rotates with the compass card to COMPASS CARD Rotates to display heading...

Page 286: ...PASS CARD Rotates to display heading of airplane with reference to lubber line 2 on HSI or DG S HEADING SELECTOR KNOB Q Positions heading bug 3 on compass card 4 by rotating the heading selector knob...

Page 287: ...sent in the navigation indicator CDI or KI 525A the autopilot operation is not affected The pilot must monitor the navigation indicators for NAV flags to ensure that the Autopilot and or Flight Direct...

Page 288: ...lideslope beam centerline 9 RECIPROCAL COURSE INDEX Indicates reciprocal of selected VOR course 10 OMNI BEARING SELECTOR OBS KNOB Rotates course card to selected course II COURSE DEVIATION NEEDLE Indi...

Page 289: ...n depressed allows pilot to manually control the aircraft disengages the pitch and roll servos without cancellation of any of the selected modes Will engage the Flight Director mode if not previously...

Page 290: ...the radio circuit breakers and the autopilot circuit breaker The following circuit breakersare used to protect the following elements of the King 150 Series Autopilot AUTOPILOT Supplies power to the...

Page 291: ...s installed per STC SAI563CE D The information contained herein supplements or supersedes the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein...

Page 292: ...handbook and must remain in this handbook at all times when the optional King KAS 297B Vertical Speed And Altitude Selector is installed SECTION 2 LIMITATIONS Altitude select captures below 800 feet...

Page 293: ...e back side of the power curve a decrease in airspeed results in a reduced rate of climb Continued operation on the back side ofthe power curve in vertical speed hold mode will result in a stall CAUTI...

Page 294: ...k SECTION 7 DESCRIPTION AND OPERATION The KAS 2978 provides the pilot with the following features ability to select vertical speed hold ability to select arm and upon approaching the selected altitude...

Page 295: ...tarily when the selected altitude is reached Once the selected altitude is reached the light signified that the 300 feet safe band has been exceed and will remain on until 1000 feet from the selected...

Page 296: ...If altitude select ARM mode is present when GS couple occurs the GS mode will cancel altitude select ARM mode The engagement of ALT by the pilot s use of the ALT switch will cancel the altitude selec...

Page 297: ...FUNCTION Supplies power to the KC 192 or the KC 191 computer the autopilot pitch and roll servos the ELV TRI M circuit breaker and the KAS 297B Supplies power to the King KEA 130AjKEA 346 Altimeter N...

Page 298: ...SECTION 9 SUPPLEMENT 8 PIPER AIRCRAFT CORPORATION PA 28R 201 ARROW THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1365 ISSUED SEPTEMBER 15 1988 9 90 8 of 8...

Page 299: ...AFT CORPORATION PA 28R 201 ARROW Paragraph No 10 1 General TABLE OF CONTENTS SECTION 10 OPERATING TIPS SECTION 10 OPERATING TIPS Page No 10 1 10 3 Operating Tips 10 1 ISSUED SEPTEMBER 15 1988 REPORT V...

Page 300: ...loads it is desirable to have the airplane at a slowerspeed before extending the flaps The flap step will not support weight if the flaps are in any extended position The flaps must be placed in the U...

Page 301: ...he rudder pedals or operating the toe brakes h In an effort to avoid accidents pilots should obtain and study the safety related information made available in FAA publications such as regulations advi...

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Arrow PA-28R-201, Pilot'S Operating Handbook And Faa Approved Airplane Flight Manual

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