Piper WARRIOR III PA-28-161 Pilot Operating Handbook Download

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SECTION 6

PIPER AIRCRAFT CORPORATION

WEIGHT AND BALANCE

PA-28-161, WARRIOR III

SECTION 6

PIPER AIRCRAFT CORPORATION

WEIGHT AND BALANCE

PA-28-161, WARRIOR III

REPORT: VB-1565

ISSUED: JULY 1, 1994

6-14

REPORT: VB-1565

ISSUED: JULY 1, 1994

6-14

C.G. RANGE AND WEIGHT

Figure 6-15

C.G. RANGE AND WEIGHT

Figure 6-15

Summary of Contents for WARRIOR III PA-28-161

Page 1: ...ERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY CAR 3 AND CONStiTUTES THE APPROVED AIRPLANE FLIGHT MANUAL AND MUST BE CARRIED IN THE AIRPLANE AT ALL TIMEs airplane airplane serial no _______________________ regist no ____________________ pa 28 161 report VB 1565 faa approved by WILLIAM R MOREU D O A NO SO 1 date of approval PIPER AIRCRAFT CORPORATION JULY 1 1994 vero beach florida ...

Page 2: ...andbook to applicable aircraft This hand book is valid for use with the airplane identified on the face of the title page Subsequent revisions supplied by Piper AIRCRAFT CORPORATION must be properly inserted Published by PUBLICATIONS DEPARTMENT Issued JULY 1 1994 1994 1995 2015 Piper Aircraft Corporation All Rights Reserved ...

Page 3: ... the text of the present handbook and or to add information to cover added airplane equipment I Revisions Revisions will be distributed whenever necessary as complete page replacements or additions and shall be inserted into the handbook in accordance with the instructions given below 1 Revision pages will replace only pages with the same page number 2 Insert all additional pages in proper numeric...

Page 4: ...hysical location of material on a page will not be identified by symbols ORIGINAL PAGES ISSUED The original pages issued for this handbook prior to revision are given below Title ii through vii 1 1 through 1 10 2 1 through 2 9 3 1 through 3 16 4 1 Uuough 4 25 5 1 U1rough 5 29 6 1 U1rough 6 17 7 1 Uuough 7 26 8 1 through 8 18 9 1 through 9 72 and 10 1 through 10 2 REPORT VB 1565 iv ...

Page 5: ... PETER E PECK 5 22 Added Fig 5 23a FAA DOA 5 23 Added Fig 5 23b Coordinator 5 24 Added Fig 5 25 5 25 Added Fig 5 29 JUNE 9 1995 5 26 Added Fig 5 31 Date Rev 2 ii Added copyright information PR150717 v Added Rev 2 to L of R 2 9 Revised Para 2 25 4 17 Revised Para 4 13 8 1 Revised Para 8 1 Eric A Wright 8 2 Revised Para 8 1 July 17 2015 pilot s operating handbook log of revisions Revision FAA Approv...

Page 6: ...REPORT VB 1565 ISSUED JULY 1 1994 vi Revision FAA Approval Number and Revised Description of Revisions Signature and Code Pages Date pilot s operating handbook log of revisions ...

Page 7: ...8 SECTION 9 SECTION 10 TABLE OF CONTENTS GENERAL LIMITATIONS EMERGENCY PROCEDURES NORMAL PROCEDURES PERFORMANCE WEIGHT AND BALANCE DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS AIRPLANE HANDLING SERVICING AND MAINTENANCE SUPPLEMENTS OPERATING TIPS REI ORT VB 1565 vii ...

Page 8: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1565 viii ...

Page 9: ...Page No No 1 1 Introduction 1 1 1 3 Engines 1 3 1 5 Propellers 1 3 1 7 Fuel 1 3 1 9 Oil 1 4 1 11 Maximum Weights 1 4 1 13 Standard Airplane Weight 1 4 1 15 Baggage Space 1 4 1 17 Specific Loadings 1 4 1 19 Symbols Abbreviations and Terminology 1 5 REPORT VB 1565 1 i 565 1 i ...

Page 10: ...REPORT VB 1565 1 ii THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 11: ...g within the operating limitations as outlined by instrument markings placards and this handbook Although the arrangement of this handbook is intended to increase its in flight capabilities it should not be used solely as an occasional operating reference The pilot should study the entire handbook to familiarize himself with the limitations performance procedures and operational handling character...

Page 12: ...SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA 28 161 WARRIOR III REPORT VB 1565 ISSUED JULY 1 1994 1 2 THREE VIEW Figure 1 1 ...

Page 13: ... Horizontally Opposed Air Cooled 1 5 PROPELLERS a Number of Propellers 1 b Propeller Manufacturer Sensenich c Model 74DM6 0 60 d Number of Blades 2 e Propeller Diameter inches 1 Maximum 74 2 Minimum 72 f Propeller Type Fixed Pitch 1 7 FUEL AVGAS ONLY a Fuel Capacity U S gal total 50 b Usable Fuel U S gal total 48 c Fuel 1 Minimum Octane 100 Green or 100LL Blue Aviation Grade 2 Alternate Fuel Refer...

Page 14: ... S A E 40 S A E 40 3 0 F to 70 F S A E 30 S A E 40 or 20W 30 4 Below 10 F S A E 20 S A E 20W 30 1 11 MAXIMUM WEIGHTS Normal Utility a Maximum Takeoff Weight lbs 2440 2020 b Maximum Ramp Weight lbs 2447 2027 c Maximum Landing Weight lbs 2440 2020 d Maximum Weight in Baggage Compartment lbs 200 0 1 13 STANDARD AIRPLANE WEIGHTS Refer to Figure 6 5 for the Standard Empty Weight and the Useful Load 1 1...

Page 15: ...ve to the ground IAS Indicated Airspeed is the speed of an air craft as shown on the airspeed indicator when corrected for instrument error IAS values published in this handbook assume zero instrument error KIAS Indicated Airspeed expressed in Knots M Mach Number is the ratio of true airspeed to the speed of sound TAS True Airspeed is the airspeed of an airplane relative to undisturbed air which i...

Page 16: ...ed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance VY Best Rate of Climb Speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time b Meteorological Terminology ISA International Standard Atmosphere in which The air is a dry perfect gas The temperature at sea level is 15 Celsius 59 Fahrenheit The pressu...

Page 17: ... be zero Station Pressure Actual atmospheric pressure at field elevation Wind The wind velocities recorded as variables on the charts of this handbook are to be understood as the headwind or tailwind components of the reported winds c Power Terminology Takeoff Power Maximum power permissible for takeoff Maximum Con Maximum power permissible continuously tinuous Power during flight Maximum Climb Ma...

Page 18: ...g certification tests Accelerate Stop The distance required to accelerate an air Distance plane to a specified speed and assuming failure of an engine at the instant that speed is attained to bring the airplane to a stop Route Segment A part of a route Each end of that part is identified by 1 a geographical location or 2 a point at which a definite radio fix can be established f Weight and Balance...

Page 19: ...f gravity locations within which the airplane must be operated at a given weight Usable Fuel Fuel available for flight planning Unusable Fuel Fuel remaining after a runout test has been completed in accordance with govern mental regulations Standard Empty Weight of a standard airplane including Weight unusable fuel full operating fluids and full oil Basic Empty Standard empty weight plus optional ...

Page 20: ...R III REPORT VB 1565 ISSUED JULY 1 1994 1 10 Maximum Maximum weight approved for the start Takeoff Weight of the takeoff run Maximum Maximum weight approved for the landing Landing Weight touchdown Maximum Zero Maximum weight exclusive of usable fuel Fuel Weight ...

Page 21: ... 1 2 5 Airspeed Indicator Markings 2 2 2 7 Power Plant Limitations 2 2 2 9 Power Plant Instrument Markings 2 3 2 11 Weight Limits 2 4 2 13 Center of Gravity Limits 2 5 2 15 Maneuver Limits 2 5 2 17 Flight Load Factors 2 6 2 19 Kinds of Operation Equipment List 2 6 2 21 Fuel Limitations 2 7 2 25 Placards 2 8 REPORT VB 1565 2 i 565 2 i ...

Page 22: ...REPORT VB 1565 2 ii THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 23: ...ven in this section and handbook Limitations associated with those optional systems and equipment which require handbook supplements can be found in Section 9 Supple ments 2 3 AIRSPEED LIMITATIONS SPEED KIAS KCAS Never Exceed Speed VNE Do not exceed this speed in any operation 160 153 Maximum Structural Cruising Speed VNO Do not exceed this speed except in smooth air and then only with caution 126...

Page 24: ...uld not be exceeded while operating in rough air 2 5 AIRSPEED INDICATOR MARKINGS MARKING KIAS Red Radial Line Never Exceed 160 Yellow Arc Caution Range Smooth Air Only 126 to 160 Green Arc Normal Operating Range 50 to 126 White Arc Flap Down 44 to 103 2 7 POWER PLANT LIMITATIONS a Number of Engines 1 b Engine Manufacturer Lycoming c Engine Model No O 320 D3G d Engine Operating Limits 1 Maximum Hor...

Page 25: ...r test procedure to determine approved static rpm under non standard conditions NOTE Refer to the airplane maintenance manual for test procedure to determine approved static rpm under non standard conditions 2 9 POWER PLANT INSTRUMENT MARKINGS a Tachometer Green Arc Normal Operating Range 500 to 2700 RPM Red Line Maximum Continuous Power 2700 RPM b Oil Temperature Green Arc Normal Operating Range ...

Page 26: ...nge Idle 25 to 55 PSI Yellow Arc Ground Warm Up 95 to 115 PSI Red Line Minimum 25 PSI Red Line Maximum 115 PSI d Fuel Pressure Green Arc Normal Operating Range 5 to 8 PSI Red Line Minimum 5 PSI Red Line Maximum 8 PSI 2 11 WEIGHT LIMITS Normal Utility a Maximum Weight 2440 LBS 2020 LBS b Maximum Ramp Weight 2447 LBS 2027 LBS c Maximum Baggage 200 LBS 0 LBS NOTE Refer to Section 5 Performance for ma...

Page 27: ...the wing leading edge at the inboard intersection of the straight and tapered section It is the responsibility of the airplane owner and the pilot to insure that the airplane is properly loaded See Section 6 Weight and Balance for proper loading instructions 2 15 MANEUVER LIMITS a Normal Category All acrobatic maneuvers including spins prohibited b Utility Category Approved Maneuvers for bank angl...

Page 28: ...on indicated However certain operations may be authorized with certain listed equip ment and or systems inoperative under certain conditions and under provisions defined by a current Minimum Equipment List MEL approved by the FAA which is dated concurrently with or after this Pilot s Operating Handbook and FAA Approved Airplane Flight Manual and authorized under an operating regulation which provi...

Page 29: ...navigation equipment required by the FAR Part 91 and 135 operating requirements 2 21 FUEL LIMITATIONS a Total Capacity 50 U S GAL b Unusable Fuel 2 U S GAL The unusable fuel for this airplane has been determined as 1 0 gallon in each wing in critical flight attitudes c Usable Fuel 48 U S GAL The usable fuel in this airplane has been determined as 24 0 gallons in each wing PIPER AIRCRAFT CORPORATIO...

Page 30: ... AS A UTILITY CATEGORY AIRPLANE FOR NORMAL AND UTILITY CATEGORY OPERATION REFER TO THE PILOT S OPERATING HANDBOOK NO ACROBATIC MANEUVERS ARE APPROVED FOR NORMAL CATEGORY OPERATIONS SPINS ARE PROHIBITED FOR NORMAL AND UTILITY CATEGORY In full view of the pilot TAKEOFF CHECKLIST Fuel on proper tank Seat backs erect Electric fuel pump on Fasten belts harness Engine gauges checked Trim tab set Flaps s...

Page 31: ...ECTION FOR BAGGAGE AND AFT PASSENGER LIMITATIONS In full view of the pilot Va 111 KIAS AT 2440 SEE P O H UTILITY CATEGORY OPERATION NO AFT PASSENGERS ALLOWED DEMO X WIND 17 KTS In full view of the pilot when the oil cooler winterization kit is installed OIL COOLER WINTERIZATION PLATE TO BE REMOVED WHEN AMBIENT TEMPERATURE EXCEEDS 50 F PIPER AIRCRAFT CORPORATION SECTION 2 PA 28 161 WARRIOR III LIMI...

Page 32: ...STEEP TURNS 111 KIAS LAZY EIGHTS 111 KIAS CHANDELLES 111 KIAS In full view of the pilot WARNING TURN OFF STROBE LIGHTS WHEN IN CLOSE PROXIMITY TO GROUND OR DURING FLIGHT THROUGH CLOUD FOG OR HAZE Adjacent to fuel filler caps serial numbers 28 8316037 and up SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS PA 28 161 WARRIOR III REPORT VB 1565 ISSUED JULY 1 1994 2 10 ...

Page 33: ...e 3 5 Loss Of Fuel Pressure 3 5 High Oil Temperature 3 5 Electrical Failures 3 5 Electrical Overload 3 5 Spin Recovery 3 6 Open Door 3 6 Engine Roughness 3 7 Carburetor Icing 3 7 3 5 Amplified Emergency Procedures General 3 9 3 7 Engine Fire During Start 3 9 3 9 Engine Power Loss During Takeoff 3 9 3 11 Engine Power Loss In Flight 3 10 3 13 Power Off Landing 3 11 3 15 Fire In Flight 3 11 3 17 Loss...

Page 34: ...REPORT VB 1565 3 ii TABLE OF CONTENTS SECTION 3 cont Paragraph Page No No 3 27 Open Door 3 15 3 29 Carburetor Icing 3 15 3 31 Engine Roughness 3 16 ...

Page 35: ...ified emergency procedures containing additional information to provide the pilot with a more complete understanding of the procedures These procedures are suggested as a course of action for coping with the particular condition described but are not a substitute for sound judgement and common sense Pilots should familiarize themselves with the procedures given in this section and be prepared to t...

Page 36: ...ps 50 KIAS 2440 lbs Full Flaps 44 KIAS 3 2b MANEUVERING SPEEDS 2440 lbs 111 KIAS 1531 lbs 88 KIAS 3 2c NEVER EXCEED SPEED Never Exceed Speed 160 KIAS 3 2c POWER OFF GLIDE SPEED 2325 lbs 0 Flaps 73 KIAS 3 3 EMERGENCY PROCEDURES CHECKLIST ENGINE FIRE DURING START Starter crank engine Mixture idle cut off Throttle open Electric Fuel Pump OFF Fuel Selector OFF Abandon if fire continues ...

Page 37: ...re check RICH Carburetor Heat ON If power is not regained proceed with power off landing ENGINE POWER LOSS IN FLIGHT Fuel Selector switch to tank containing fuel Electric Fuel Pump ON Mixture RICH Carburetor Heat ON Engine Gauges check for indication of cause of power loss If no fuel pressure is indicated check tank selector position to be sure it is on a tank containing fuel When power is restore...

Page 38: ...gnition OFF Battery Master switch OFF ALTR Switch OFF Fuel selector OFF Mixture idle cut off Seat belts and harnesses tight FIRE IN FLIGHT NOTE The posibility of an engine fire in flight is extremely remote The procedure given is general and Pilot judgment should be the determining factor for action in such an emergency Source of fire check Electrical fire smoke in cabin Battery Master switch OFF ...

Page 39: ...iator will be illuminated ALT annunciator light illuminated Ammeter Check to verify inop alt If ammeter shows zero ALT switch OFF Reduce electrical loads to minimum ALT circuit breaker Check and reset as required ALT switch ON If power not restored ALT switch OFF If alternator output cannot be restored reduce electrical loads and land as soon as practical Anticipate complete electrical failure Dur...

Page 40: ...increased system voltage and radio frequency noise operation with ALT switch ON and BATT switch OFF should be made only when required by an electrical system failure If alternator loads are not reduced ALT switch OFF BATT switch As required Land as soon as possible Anticipate complete electrical failure SPIN RECOVERY Rudder full opposite to direction of rotation Control wheel full forward while ne...

Page 41: ...s are open latch side latch then top latch ENGINE ROUGHNESS Carburetor Heat ON If roughness continues after one min Carburetor Heat OFF Mixture adjust for max smoothness Electric Fuel Pump ON Fuel Selector switch tanks Engine Gauges check Magneto Switch L then R then BOTH If operation is satisfactory on either magneto continue on that magneto at reduced power and full RICH mixture to first airport...

Page 42: ...SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA 28 161 WARRIOR III REPORT VB 1565 ISSUED JULY 1 1994 3 8 THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 43: ...inues more than a few seconds the fire should be extinguished by the best available external means The fuel selector valves should be OFF and the mixture at idle cut off if an external fire extingueshing method is to be used 3 9 ENGINE POWER LOSS DURING TAKEOFF The proper action to be taken if loss of power occurs during takeoff will depend on the circumstances of the particular situation If suffi...

Page 44: ... ON Check the engine gauges for an indication of the cause of the power loss If no fuel pressure is indicated check the tank selector position to be sure it is on a tank containing fuel When power is restored move the carburetor heat to the OFF position and turn OFF the electric fuel pump If the preceding steps do not restore power prepare for an emergency landing If time permits turn the magneto ...

Page 45: ...d close the throttle move the mixture to idle cut off and shut OFF the magnetos Turn the battery master and alternator switches OFF Move the fuel selector valve to OFF The seat belts and shoulder harness should be tightened 3 15 FIRE IN FLIGHT The presence of fire is noted through smoke smell and heat in the cabin It is essential that the source of the fire be promptly identified through instrumen...

Page 46: ...oblem is not a pressure gauge malfunction the engine may stop suddenly Maintain altitude until such time as a dead stick landing can be accomplished Don t change power settings unnecessarily as this may hasten complete power loss Depending on the circumstances it may be advisable to make an off airport landing while power is still available particularly if other indications of actual oil pressure ...

Page 47: ...trouble Land at the nearest airport and let a mechanic investigate the problem Watch the oil pressure gauge for an accompanying loss of pressure 3 23 ELECTRICAL FAILURES NOTE Anytime the bus voltage is below 25 Vdc the Low Bus Voltage Annunciator will be illuminated Loss of alternator output is detected through zero reading on the ammeter and alternator inop annunciator Before executing the follow...

Page 48: ...gh alternator output is observed more than 20 amps above known electrical load for the operating conditions it may be caused by a low battery a battery fault or other abnormal electrical load If the cause is a low battery the indication should begin to decrease toward normal within 5 minutes If the overload condition persists attempt to reduce the load by turning off non essential equipment Turn t...

Page 49: ...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 door in flight slow the airplane to 89 KIAS close the cabin vents and open the storm window If the top latch is open latch it If the side latch is open pull on the arm rest while moving the latch handle to the latched position If both l...

Page 50: ...adjust the mixture for maximum smoothness The engine will run rough if the mixture is too rich or too lean The electric fuel pump should be switched to ON and the fuel selector switched to the other tank to see if fuel contamination is the problem Check the engine gauges for abnormal readings If any gauge readings are abnormal proceed accordingly Move the magneto switch to L then to R then back to...

Page 51: ...Engine When Cold 4 6 Starting Engine When Hot 4 6 Starting Engine When Flooded 4 7 Starting With External Power Source 4 7 Warm Up 4 7 Taxiing 4 7 Ground Check 4 8 Before Takeoff 4 8 Takeoff 4 9 Climb 4 10 Cruising 4 10 Descent 4 10 Approach And Landing 4 11 Stopping Engine 4 11 Parking 4 11 4 7 Amplified Normal Procedures General 4 12 4 9 Preflight Check 4 12 4 11 Before Starting Engine 4 15 4 13...

Page 52: ... 4 21 Before Takeoff 4 19 4 23 Takeoff 4 20 4 25 Climb 4 21 4 27 Cruising 4 21 4 29 Descent 4 22 4 31 Approach And Landing 4 23 4 33 Stopping Engine 4 24 4 35 Parking 4 24 4 37 Stalls 4 25 4 39 Turbulent Air Operation 4 25 4 41 Weight And Balance 4 25 4 43 Noise Levels 4 26 ...

Page 53: ... procedures which are not the same for all aircraft Pilots should familiarize themselves with the procedures given in this section in order to become proficient in the normal operations of the airplane The first portion of this section consists of a short form checklist which supplies an action sequence for normal operations with little emphasis on the operation of the systems The remainder of the...

Page 54: ... under standard conditions at sea level Performance for a specific airplane may vary from published figures depending upon the equipment installed the condition of the engine air plane and equipment atmospheric conditions and piloting technique a Best Rate of Climb Speed 79 KIAS b Best Angle of Climb Speed 63 KIAS c Turbulent Air Operating Speed See Subsection 2 3 111 KIAS d Maximum Flap Speed 103...

Page 55: ...1565 4 3 oard able tied mits nned oard safe WALK AROUND Figure 4 1 4 5 NORMAL PROCEDURES CHECKLIST PREPARATION Airplane status airworthy papers on board Weather suitable Baggage weighed stowed tied Weight and C G within limits Navigation planned Charts and navigation equipment on board Performance and range computed and safe ...

Page 56: ...heck Trim check set neutral Pitot drain DRAIN close Static drain DRAIN close Windows check clean Tow bar stow Baggage secure Baggage door close secure RIGHT WING Wing free of ice snow frost Control surfaces check for interference free of ice snow frost Hinges check for interference Static wicks check Wing tip and lights check Fuel tank check supply visually secure caps Fuel tank sump drain check f...

Page 57: ...water sediment and proper fuel LEFT WING Wing free of ice snow frost Fresh air inlet clear Main gear strut proper inflation 4 50 in Tire check Brake block and discs check Fuel tanks check supply visually secure caps Fuel tank sumps drain check for water sediment and proper fuel Fuel vents open Tie down and chock remove Pitot head remove cover holes clear Wing tip and lights check Control surfaces ...

Page 58: ...ngers board Cabin door close and secure Seat belts and harnesses fasten check interia reel BEFORE STARTING ENGINE Brakes set Carburetor Heat full OFF Fuel Selector desired tank Radios OFF STARTING ENGINE WHEN COLD Throttle 1 4 open Master switch ON Electric fuel pump ON Mixture full RICH Starter engage Throttle adjust Oil Pressure check If engine does not start within 10 sec prime and repeat start...

Page 59: ...INE WITH EXTERNAL POWER SOURCE Master switch OFF All electrical equipment OFF Terminals connect External power plug insert in fuselage Proceed with normal start Throttle lowest possible RPM External power plug disconnect from fuselage Master switch ON check ammeter Oil Pressure check WARM UP Throttle 800 to 1200 RPM TAXIING Chocks removed Taxi area clear Throttle apply slowly Brakes check Steering...

Page 60: ...Carburetor Heat check Observe approx 75 RPM drop Engine is warm for takeoff when throttle can be opened without engine faltering Electric fuel pump OFF Fuel pressure check Throttle RETARD BEFORE TAKEOFF Master switch ON Flight instruments check Fuel selector proper tank Electric fuel pump ON Engine gauges check Carburetor heat OFF Seat backs erect Mixture set Belts harness fastened check Empty sea...

Page 61: ...second notch Accelerate to 40 52 KIAS depending on weight Control Wheel back pressure to rotate to climb attitude Accelerate to and maintain 44 to 57 KIAS depending on weight until obstacle clearance is achieved and climb out at 79 KIAS Flaps retract slowly SOFT FIELD OBSTACLE CLEARANCE Flaps 25 second notch Accelerate and lift off nose gear as soon as possible Lift off at lowest possible airspeed...

Page 62: ...IAS Flaps retract slowly CLIMB Best rate flaps up 79 KIAS Best angle flaps up 63 KIAS En route 87 KIAS Electric fuel pump OFF at desired altitude CRUISING Reference performance charts and Avco Lycoming Operators Manual Normal max power 75 Power set per power table Mixture adjust DESCENT NORMAL Throttle 2500 rpm Airspeed 126 KIAS Mixture rich Carburetor heat ON if required POWER OFF Carburetor heat...

Page 63: ...OFF Trim to 70 KIAS Final approach speed flaps 40 63 KIAS STOPPING ENGINE Flaps retract Electric fuel pump OFF Air Conditioner OFF Radios OFF Throttle full aft Mixture idle cut off Magnetos OFF Master switch OFF PARKING Parking brake set Control wheel secure with belts Flaps full up Wheel chocks in place Tie downs secure PIPER AIRCRAFT CORPORATION SECTION 4 PA 28 161 WARRIOR III NORMAL PROCEDURES ...

Page 64: ... flight should be checked before takeoff CAUTION The flap position should be noted before boarding the airplane The flaps must be placed in the UP position before they will lock and support weight on the step COCKPIT Upon entering the cockpit release the seat belts securing the control wheel turn OFF all avionics equipment and set the parking brake Insure that all electrical switches and the magne...

Page 65: ... daily prior to the first flight and after each refueling and checked for proper fuel CAUTION When draining any amount of fuel care should be taken to insure that no fire hazard exists before starting engine Remove the tie down and chock Next a check of the landing gear Check the gear strut for proper inflation there should be 4 50 25 inches of strut exposure under a normal static load Check the t...

Page 66: ...ly The fuel tank vent should be clear of obstructions Drain enough fuel to insure that all water and sediment has been removed and check for proper fuel Remove tie down and chock Remove the cover from the pitot static head on the underside of the wing Make sure the holes are open and clear of obstructions Check the wing tip and lights for damage Check the aileron flap and hinges for damage and ope...

Page 67: ...ition The fuel selector should then be moved to the desired tank Check to make sure that all the radios are OFF 4 13 STARTING ENGINE a Starting Engine When Cold Open the throttle lever approximately 1 4 inch Turn ON the master switch and the electric fuel pump Move the mixture control to full RICH and engage the starter by rotating the magneto switch clockwise When the engine fires release the mag...

Page 68: ...switch clockwise When the engine fires release the magneto switch advance the mixture and retard the throttle d Starting Engine With External Power Source An External Power receptacle allows the operator to use an external battery to crank the engine without having to gain access to the airplane s battery Turn the master switch OFF and turn all electrical equipment OFF Insert the plug of a 28 volt...

Page 69: ... throttle to 800 rpm If oil pressure is not indicated within thirty seconds stop the engine and determine the trouble In cold weather it will take a few seconds longer to get an oil pressure indication If the engine has failed to start refer to the Lycoming Operating Handbook Engine Troubles and Their Remedies NOTE Starter manufacturer recommends starter cranking periods be limited to 10 seconds w...

Page 70: ... taxiing near buildings or other stationary objects If possible station an observer outside the airplane Avoid holes and ruts when taxiing over uneven ground Do not operate the engine at high rpm when running up or taxiing over ground containing loose stones gravel or any loose material that may cause damage to the propeller blades 4 19 GROUND CHECK The magnetos should be checked at 2000 rpm Drop ...

Page 71: ...e it is on the proper tank fullest Turn ON the electric fuel pump to prevent loss of power should the engine driven pump fail during takeoff and check the engine gauges The carburetor heat should be in the OFF position All seat backs should be erect and the seat belts and shoulder harness should be fastened Pull test the locking restraint feature of the shoulder harness inertia reel Fasten the sea...

Page 72: ...lift off at 40 52 KIAS depending on weight and accelerate to and maintain 44 57 KIAS depending on weight past obstacle and climb out at 79 KIAS A short field takeoff with an obstacle clearance is accomplished by first lowering the flaps to 25 Apply full power before brake release and accel erate to 40 52 KIAS depending on weight and rotate Accelerate to and maintain 44 57 KIAS depending on weight ...

Page 73: ... when alternate fuels are used The mixture should be full rich when operating above 75 power and leaned during cruising operation when 75 power or less is being used To lean the mixture for best power cruise performance place the mixture control full forward and set the throttle slightly below approximately 35 RPM the desired cruise power setting and lean the mixture to peak RPM Adjust the throttl...

Page 74: ...approximately one half hour of fuel Do not run tanks completely dry in flight The electric fuel pump should be normally OFF so that any malfunction of the engine driven fuel pump is immediately apparent If signs of fuel starvation should occur at any time during flight fuel exhaustion should be suspected at which time the fuel selector should be immediately positioned to the other tank and the ele...

Page 75: ...cause detonation The 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 generally good practice to contact the ground at the minimum possible safe speed consistent with existing conditions Normally the best technique for short and slow landings is to use ful...

Page 76: ... to 1200 RPM for one minute prior to shutdown to clean out any unburned fuel NOTE The flaps must be placed in the UP position for the flap step to support weight Passengers should be cautioned accordingly 4 35 PARKING If necessary the airplane should be moved on the ground with the aid of the nose wheel tow bar provided with each airplane and secured behind the rear seats The aileron and stabilato...

Page 77: ...ecking to determine if the horn is actuated The master switch should be returned to the OFF position after the check is complete 4 39 TURBULENT AIR OPERATION In keeping with good operating practice used in all aircraft it is rec ommended that when turbulent air is encountered or expected the airspeed be reduced to maneuvering speed to reduce the structural loads caused by gusts and to allow for in...

Page 78: ...evels of this airplane are or should be acceptable or unacceptable for operation at into or out of any airport The above statement notwithstanding the noise level stated above has been verified by and approved by the Federal Aviation Administration in noise level test flights conducted in accordance with FAR 36 Noise Standards Aircraft Type and Airworthiness Certification This aircraft model is in...

Page 79: ... CONTENTS SECTION 5 PERFORMANCE Paragraph Page No No 5 1 General 5 1 5 3 Introduction Performance and Flight Planning 5 1 5 5 Flight Planning Example 5 3 5 7 Performance Graphs 5 9 List of Figures 5 9 REPORT VB 1565 5 i 565 5 i ...

Page 80: ...REPORT VB 1565 5 ii THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 81: ...ltitude temperature etc The performance charts are unfactored and do not make any allowance for varying degrees of pilot proficiency or mechanical deterioration of the aircraft This performance however can be duplicated by following the stated procedures in a properly maintained airplane Effects of conditions not considered on the charts must be evaluated by the pilot such as the effect of soft or...

Page 82: ...rovided by paragraph 5 5 Flight Planning Example outlines a detailed flight plan using the performance charts in this section Each chart includes its own example to show how it is used WARNING Performance information derived by extrapo lation beyond the limits shown on the charts should not be used for flight planning purposes ...

Page 83: ...ake use of the Weight and Balance Loading 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 the following weights apply to the flight planning example The landing weight cannot be determined until the weight of the fuel to be used has been established...

Page 84: ...e landing distance 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 are listed below The takeoff and landing distances required for the example flight have fallen well below the available runway lengths Departure Destination Airport Airport 1 Pressure...

Page 85: ...plan corrected for field pressure altitude and temperature The following values were determined from the above instruc tions in the flight planning example 1 Cruise Pressure Altitude 5000 ft 2 Cruise OAT 16 C 3 Time to Climb 11 0 min minus 3 0 min 8 0 min 4 Distance to Climb 16 0 miles minus 3 0 miles 13 0 miles 5 Fuel to Climb 3 gal minus 1 0 gal 2 0 gal d Descent The descent data will be determi...

Page 86: ...istance to climb and distance to descend to establish the total cruise distance Refer to the appropriate Avco Lycoming Operator s Manual when selecting the cruise power setting The established pressure altitude and temperature values and the selected cruise power should now be utilized to determine the true airspeed from the Cruise Performance graph Figure 5 21 or 5 23 Calculate the cruise fuel co...

Page 87: ... the cruise time The following flight time is required for our flight planning example 1 Total Flight Time c 3 plus d 1 plus e 6 13 hrs plus 07 hrs plus 2 44 hrs 2 64 hrs g Total Fuel Required Determine the total fuel required by adding the fuel to climb the fuel to descend and the cruise fuel When the total fuel in gallons is determined multiply this value by 6 lb gal to determine the total fuel ...

Page 88: ...SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 28 161 WARRIOR III REPORT VB 1565 ISSUED JULY 1 1994 5 8 THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 89: ...rmance 5 18 5 17 Climb Performance 5 19 5 19 Fuel Time and Distance to Climb 5 20 5 21 Cruise Performance Speed Power 5 20b 5 23 Engine Cruise Performance 55 Power 5 21 5 23a Engine Cruise Performance 65 Power 5 21 5 23b Engine Cruise Performance 75 Best Power 5 23 5 25 Range 5 24 5 29 Endurance 5 25 5 31 Fuel Time and Distance to Descend 5 26 5 33 Glide Performance 5 27 5 35 Landing Distance 5 28...

Page 90: ...SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 28 161 WARRIOR III REPORT VB 1565 ISSUED JULY 1 1994 5 10 THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 91: ... WARRIOR III PERFORMANCE ON 5 NCE ISSUED JULY 1 1994 REPORT VB 1565 5 11 565 5 11 TEMPERATURE CONVERSION Figure 5 1 40 100 90 30 80 70 20 60 Sea LeveiiSA Standard Day 50 10 40 30 0 FAHRENHEIT CELSIUS DEGREES 20 DEGREES 10 10 0 20 10 20 30 30 40 40 ...

Page 92: ... III REPORT VB 1565 ISSUED JULY 1 1994 5 12 AIRSPEED SYSTEM CALIBRATION Figure 5 3 II 1 0 z I c L1J L1J 0 II a c L1J 1 a Ill i u 160 140 120 100 80 60 40 40 PA 28 161 AIRSPEED SYSTEM CALIBRATION FLAPS UP WING FLAPS 40 60 80 100 120 140 160 180 INDICATED AIRSPEED KNOTS ...

Page 93: ...L SPEED igure 5 5 STALL SPEED Figure 5 5 Example Gross Weight 2170 lbs Angle of bank 20 Flap position 40 PA 28 161 STALL SPEED Stall speed indicated 44 KTS ui 0 N I 1 w 3 x c 2400 ________ CALIBRATED STALL SPEED INDICATED STALL SPEED 2200 2000 1800 GROSS WEIGHT LBS oo FLAPS 1600 40 FLAPS 60 ui 1 so I c w w c en 40 l l en 30 0 20 40 60 ANGLE OF BANK DEGREES ...

Page 94: ...arture a1rport pressure alt1tud 1500 ft tFULL POWER BEFORE BRAKE RELEASE Departure a1rport temperature 27 C FLAPS 0 o fff We1ght 2316 lbs tnrrtTTfT J ttrmr 111111111111 J H Wind 15 KTS headwind Ground roll 1150 ft Lift off speed 50 KIAS 52 48 liFT OFF SPEED KIA oSmmtttrn m tttmt t nr r r t t H i t 1 1jtr tt 1 u ntt p f H t t H H tffi 2000 j t roooo 0 _ I 40 30 20 10 0 10 20 30 40 OUTSIDE AIR TEMP ...

Page 95: ...KE RELEASE FLAPS oo t57 52 u UJ a 50 FT BARRIER SPEED KIAS H 5 5 oj j j bt47 4BmiW4 s miW43 1 1 1 1 1 1 1 LIFT OFF SPEED KIAS Example Departure airport pressure alt1tude 1500 ft Departure airport temperature 27 C Weight 2316 lbs Wind 15 KTS headwind Distance over 50 ft barrier 2100 ft Lift off speed 50 KIAS Barrier speed 55 KIAS 44 3500 3000 2500 _ a UJ a a al _ 0 Ltl a UJ 0 2000 1500 1000 z 1 m 0...

Page 96: ...ASSOCIATED CONDITIONS PAVED LEVEL DRY RUNWAY FULL POWER BEFORE BRAKE RELEASE FLAPS 25 0 Q t b Oor l i 1 52 Ill J 0 N w z w 0 48 46 43 LIFT OFF SPEED KIAS 40 30 20 10 0 10 20 30 OUTSIDE AIR TEMP oc 40 2400 2300 2200 21 00 2000 1900 1800 1700 WEIGHT LBS Example Departure airport pressure altitude 1500 Departure airport tE Weight 2175 lbs Wind 15 KTS headwind Ground roll 975ft Lift off speed 48 KIAS ...

Page 97: ...arture airport temperature 2rc Weight 2175 lbs Wind 15 KTS headwind Dista nee over 50 ft barrier 1500 ft Lift off speed 48 KIAS Barrier speed 53 KIAS ASSOCIATED CONDITIONS PAVED LEVEL DRY RUNWAY FULL POWER BEFORE BRAKE RELEASE FLAPS 25 en 0 3 N I w z u w a KIAS 47 43 44 lJ W zg f 4000 lo w 0 3500 3000 2500 2000 1500 1000 500 l l l l l l l l l l l 111 1111 I I I 40 30 20 10 0 10 20 30 40 2400 2300 ...

Page 98: ... 15 10000 9000 8000 7000 L 6000 1 5 5000 w f t 0 4000 w g 3000 2000 1000 c S L 5 I i c I 0 ENGINE PERFORMANCE POWER vs RPM OAT ISA PROPELLER Sensenich 74DM6 0 60 Example f r Powers are percent of 160 BHP Pressure Altitude 5000 It f RPM applicable to both best f Power 75 f power best economy mixture f Engine Speed 2630 RPM i It s l Q o 1 o o 3 I i o i I q f f f 7 r f f ff f I I I 5 10 15 2300 2400 ...

Page 99: ...9 KIAS MAXIMUM RATE OF CLIMB EXAMPLE PRESSURE ALTITUDE 5000FT OAT 16 C ISA 11 C MAX RATE OF CLIMB 374 FPM PRESSURE OUTSIDE AIR TEMPERATURE ALTITUDE ISA 15 C ISA ISA 10 C ISA 20 C ISA 30 C FEET S L 677 644 624 604 585 1000 628 595 574 554 534 2000 578 545 524 504 485 3000 528 495 475 455 436 4000 478 446 425 405 386 5000 429 396 376 356 337 6000 379 346 326 306 287 7000 330 298 277 257 238 8000 280...

Page 100: ...RE FLAPS AIRSPEED 2440LBS FULL THROTTLE FULL RICH UP 79 KIAS Ui Jl r 00 S L PRESSURE ALTITUD fEET Distance shown based on zero wind Propeller Sensenich 74DM6 0 60 ff Departure Altitude Pressure Altitude 1500 fl Departure Airport Temperature 27 C Cruise Pressure Altitude 5000 fl Cruise OAT 16 C Time to climb 11 min minus 3 min 8 min Distance to climb 16 0 miles minus 3 0 miles 13 NM Fuel to Climb 3...

Page 101: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT CORPORATION SECTION 5 PA 28 161 WARRIOR III PERFORMANCE ON 5 NCE ISSUED JULY 1 1994 REPORT VB 1565 REVISED JUNE 9 1995 5 20a 565 20a ...

Page 102: ...CRUISE PERFORMANCE SPEED POWER Figure 5 21 CRUISE PERFORMANCE SPEED POWER OAT ISA Mid Cruise Weight 2300 Lbs Propeller Sensenich 74DM6 0 60 10000 9000 8000 f w 7000 I 6000 J f i 5000 _J w 4000 0 J 3000 w 0 a 2000 1000 0 5 I j I Example Pressure Altitude 5000 ft 1 Power 75 True Airspeed 114 kt s n 1 i cf 8 1 f f8 t r t I m CD I I I 0 I I g I I g I f 1 r f I 0 5 10 15 95 100 105 110 115 120 OUTSIDE ...

Page 103: ...10 ISA 15 59 2250 ISA 10 25 77 2280 ISA 20 35 95 2300 ISA 30 45 113 2330 ISA 15 4 25 2260 ISA 11 52 2300 ISA 10 21 70 2320 ISA 20 31 88 2350 ISA 30 41 106 2370 ISA 15 8 18 2300 ISA 7 45 2340 ISA 10 17 63 2370 ISA 20 27 81 2400 ISA 30 37 99 2420 ISA 15 12 10 2350 ISA 3 37 2390 ISA 10 13 55 2410 ISA 20 23 73 2440 ISA 30 33 91 2460 ISA 15 16 4 2390 ISA 1 31 2430 ISA 10 9 49 2460 ISA 17 5 16 5 62 2475...

Page 104: ...ISA 15 59 2390 ISA 10 25 77 2420 ISA 20 35 95 2440 ISA 30 45 113 2470 ISA 15 4 25 2390 ISA 11 52 2440 ISA 10 21 70 2460 ISA 20 31 88 2490 ISA 30 41 106 2520 ISA 15 8 18 2440 ISA 7 45 2480 ISA 10 17 63 2510 ISA 20 27 81 2540 ISA 30 37 99 2560 ISA 15 12 10 2490 ISA 3 37 2530 ISA 10 13 55 2560 ISA 20 23 73 2580 ISA 30 33 91 2600 ISA 15 16 4 2530 ISA 1 31 2580 ISA 10 9 49 2610 ISA 17 5 16 5 62 2630 IS...

Page 105: ... 2460 ISA 15 59 2510 ISA 10 25 77 2540 ISA 20 35 95 2560 ISA 30 45 113 2590 ISA 15 4 25 2510 ISA 11 52 2560 ISA 10 21 70 2590 ISA 20 31 88 2620 ISA 30 41 106 2640 ISA 15 6 21 2540 ISA 9 48 2580 ISA 10 19 66 2610 ISA 20 29 84 2640 ISA 30 39 102 2670 ISA 15 8 18 2560 ISA 7 45 2610 ISA 10 17 63 2640 ISA 20 27 81 2670 ISA 30 37 99 2690 ISA 15 10 14 2590 ISA 5 41 2630 ISA 10 15 59 2660 ISA 20 25 77 269...

Page 106: ...ltitude 5000 ft I L 75 BEST POWER Cruise power 75 Best power mixture I Note See Section 4 27 for 12000 Range w 45 min reserve 55 power 414 NM I mixture setting procedure Range w o reserve 474 NM i i 45 MIN RESERVE AT 55 POWER NO RESERVE I 10000 1 w w L I i i I I II J u I w 8000 0 J 1 _J w 6000 c o l 0 I I LU 0 a i I let 81 1 e 1 1 I 1 J f f w c 4000 ll 11 1 I I I I I I i 1 I I J L I I I I I 1 I I ...

Page 107: ...Endurance w 45 min reserve 55 48 GAL USABLE FUEL 2440 LBS GROSS WT 55 BEST ECONOMY power 3 65 hrs PROPELLER SENSENICH 74DM6 0 60 65 BEST ECONOMY Endurance w o reserve 4 17 75 BEST POWER 11000 10000 9000 LL 8000 w 0 7000 1 i 6000 _J w 5000 0 w 0 a 4000 3000 2000 1000 S L 3 0 45 MIN RESERVE AT 55 POWER 3 5 J 0 1 0 U 0 u 4 0 H f 0 4 5 CJ CJ 0 5 0 r 5 5 1 4 0 NO RESERVE J 0 1 if U m u t FJ f F t i l 4...

Page 108: ...Temperature 16 C ISA 11 C Time To Descend 8 8 min By Interpolation Fuel To Descend 1 9 gal By Interpolation Distance To Descend 19 6 miles By Interpolation Destination Airport Pressure Altitude 2500 ft Destination Airport Temperature 24 C ISA 14 C ISA 10 C ISA 20 C DIST TIME FUEL DIST TIME FUEL NM MIN GAL NM MIN GAL 0 0 0 0 0 0 10 3 1 6 2 1 17 5 1 10 3 1 22 6 1 14 5 1 26 8 2 17 6 1 29 9 2 20 7 1 3...

Page 109: ...DE PERFORMANCE ASSOCIATED CONDITIONS WEIGHT 2440 LBS PROP WINDMILLING FLAPS 0 NO WIND 73 KIAS Example 12000 10000 1 w w u 8000 w c 1 i 6000 1 1 w a U U w 4000 a a TEA 2000 SEA lEVEl 0 Cruise pressure altitude 5000 ft Terrain pressure altitude 2000 ft Glide distance 9 5 miles minus 3 9 miles 5 6 nautical miles CRUISE I II 5 10 15 20 25 GLIDE RANGE NAUTICAL MILES ...

Page 110: ...S POWER OFF FLAPS 40 o PAVED LEVEL DRY RUNWAY MAXIMUM BRAKING Example Destination airport altitude 2500 ft Destination airport temperature 24 C Destination airport wind 0 KTS Landing Weight 2179 lbs Distance over 50 ft barrier E 1 iuoE I E ss u 40 30 20 10 0 10 20 OUTSIDE AIR TEMP o 30 65 n 45 ui 0 0 t N I w z u w a I I 40 2400 2300 2200 2100 2000 19 00 1aoo 17 00 WEIGHT LBS 49 37 0 Z 1 3 1400 0 s...

Page 111: ...ple I lllllllllll lllllll ASSOCIATED CONDITIONS Destination airport pressure altitude 2500 ft POWER OFF FLAPS 40 Destination airport temperature 24 C PAVED LEVEL DRY RUN 1 o Destination airport wind 0 KTS Landing Weight 2179 lbs Ground Roll 625ft 45 ui t w z u w a TOUCH DOWN SPEED KIAS 0 z 3E 0 z I w z tti i a 40 30 20 10 0 10 20 30 40 2400 2200 2000 1800 0 5 10 15 2300 2100 1900 1700 OUTSIDE AIR ...

Page 112: ...SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 28 161 WARRIOR III REPORT VB 1565 ISSUED JULY 1 1994 5 30 THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 113: ... 1 General 6 1 6 3 Airplane Weighing Procedure 6 2 6 5 Weight and Balance Data and Record 6 6 6 7 Weight and Balance Determination for Flight 6 11 6 9 Instructions for Using the Weight and Balance Plotter 6 15 Equipment List Form 240 0009 Supplied with aircraft paperwork REPORT VB 1565 6 i 565 6 i ...

Page 114: ...REPORT VB 1565 6 ii THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 115: ...ity 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 C G is too far aft the airplane may rotate prematurely on takeoff or tend to pitch up during climb Longitudinal stability will be reduced This can lead to inadvertent stalls and even spins and spin recovery becomes more difficult as the cen...

Page 116: ...against improper loading The following pages are forms used in weighing an airplane in production and in computing basic empty weight C G position 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 C G 6 3 AIRPLANE WEIGHING PROCEDURE At the time of licensing Piper Aircraft Corporation provides ea...

Page 117: ...with oil to full capacity 5 Place pilot and copilot seats in fourth 4th notch aft of forward position Put flaps in 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 should be closed 6 Weigh the airplane inside a closed building to prevent errors in the scale readings due to wind b Leveling 1 With ai...

Page 118: ...eighing Airplane Basic Empty Weight With the airplane level and brakes released record the weight shown on each scale Deduct the tare if any from each reading WEIGHING FORM Figure 6 1 Scale Net Scale Position and Symbol Reading Tare Weight Nose Wheel N Right Main Wheel R Left Main Wheel L Basic Empty Weight as Weighed T ...

Page 119: ...ty Weight Center of Gravity 1 The following geometry applies to the PA 28 161 airplane when it is level Refer to Leveling paragraph 6 3 b LEVELING DIAGRAM Figure 6 3 2 The basic empty weight center of gravity as weighed including optional equipment full oil and unusable fuel can be determined by the following formula C G Arm N A R L B inches T Where T N R L ...

Page 120: ...ply only to the specific airplane serial number and registration number shown The basic empty weight of the airplane as licensed at the factory has been entered in the Weight and Balance Record Figure 6 7 This form is provided to present the current status of the airplane basic empty weight and a complete history of previous modifications Any change to the per manently installed equipment or modif...

Page 121: ...ERATION Ramp Weight Basic Empty Weight Useful Load Normal Category 2447 lbs lbs lbs Utility Category 2027 lbs lbs lbs THIS BASIC EMPTY WEIGHT C G AND USEFUL LOAD ARE FOR THE AIRPLANE AS LICENSED AT THE FACTORY REFER TO APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE WEIGHT AND BALANCE DATA FORM Figure 6 5 AIRPLANE BASIC EMPTY WEIGHT C G Arm Weight x Inches Aft Moment Item Lbs of Datum ...

Page 122: ...SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 28 161 WARRIOR III REPORT VB 1565 ISSUED JULY 1 1994 6 8 THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 123: ...LY 1 1994 REPORT VB 1565 6 9 REPORT VB 1565 6 9 D BALANCE RECORD Figure 6 7 WEIGHT AND BALANCE RECORD Figure 6 7 PA 28 161 Serial Number Registration Number Page Number Running Basic I Weight Change 0 0 Empty Weight z Description of Article 0 Date s or Modification g Wt Arm Moment Wt Moment B Lb ln 100 Lb 100 As licensed ...

Page 124: ...II REPORT VB 1565 ISSUED JULY 1 1994 6 10 ISSUED JULY 1 1994 CE RECORD cont cont WEIGHT AND BALANCE RECORD cont Figure 6 7 cont PA 28 161 Serial Number Registration Number Page Number Running Basic Weight Change Empty Weight 13 Date Description of Article 13 5 or Modification Co Wt Arm Moment Wt Moment 5 Lb ln 100 Lb 100 ...

Page 125: ...g meets the weight and balance requirements The center of gravity C G of this sample loading problem is at 90 6 inches aft of the datum line Locate this point 90 6 on the C G range and weight graph Since this point falls within the weight C G envelope this loading meets the weight and balance requirements IT IS THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNER TO INSURE THAT THE AIRPLANE IS LOADE...

Page 126: ...re 6 5 If the airplane has been altered refer to the Weight and Balance Record for this information Utility Category Operation No baggage or aft passengers allowed WEIGHT AND BALANCE LOADING FORM Figure 6 11 Arm Aft Weight Datum Moment Lbs Inches In Lbs Basic Empty Weight Pilot and Front Passenger 80 5 Passengers Rear Seats 118 1 Fuel 48 Gallon Maximum 95 0 Baggage 200 Lbs Maximum 142 8 Ramp Weigh...

Page 127: ...WARRIOR III WEIGHT AND BALANCE ON 6 NCE ISSUED JULY 1 1994 REPORT VB 1565 6 13 565 6 13 LOADING GRAPH Figure 6 13 450 400 q l J 350 q_ o r q 300 Vi c z 250 0 1 I fl l b J jjj 200 1 c 0 150 100 50 0 0 5 10 15 20 25 30 35 40 MOMENT 1000 POUNDS INCHES ...

Page 128: ...REPORT VB 1565 ISSUED JULY 1 1994 6 14 C G RANGE AND WEIGHT Figure 6 15 WEIGHT vs C G ENVELOPE 2440 MAX GROSS WT NORMAL CATEGORY 86 89 90 I en 0 1800 r r 1 J 1 1 S 1700 w 3 r r r t 1600 1 0 r r 1500 1 8 3 8 4 8 5 8 6 8 7 8 8 8 9 9 0 9 1 9 2 9 3 1200 C G LOCATION INCHES AFT DATUM ...

Page 129: ...t Controls 7 5 7 11 Engine Controls 7 6 7 13 Fuel System 7 8 7 15 Electrical System 7 10 7 17 Vacuum System 7 13 7 19 Instrument Panel 7 15 7 21 Pitot Static System 7 18 7 23 Heating and Ventilating System 7 21 7 25 Cabin Features 7 21 7 27 Baggage Area 7 22 7 29 Stall Warning 7 22 7 31 Finish 7 22 7 33 Piper External Power 7 23 7 35 Emergency Locator Transmitter 7 23 7 37 Air Conditioning 7 25 7 ...

Page 130: ...REPORT VB 1565 7 ii THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 131: ...ggage door is installed aft of the rear seat The wing is of a conventional semi tapered design incorporating a laminar flow NACA 652415 airfoil section The cantilever wings are attached to each side of the fuselage by insertion of the butt ends of the main spars into a spar box carry through which is an integral part of the fuselage structure The spar box carry through structure located under the ...

Page 132: ...heated air for the cabin the defroster system and the carburetor deicing system An oil cooler is located on the left rear of the engine mounted to the engine baffling Engine cooling air which is picked up in the nose section of the engine cowling and carried through the baffling is utilized on the left side for the oil cooler A winterization plate is provided to restrict air during winter operatio...

Page 133: ...PIPER AIRCRAFT CORPORATION SECTION 7 PA 28 161 WARRIOR III DESCRIPTION OPERATION ON 7 ON ISSUED JULY 1 1994 REPORT VB 1565 7 3 565 7 3 MAIN WHEEL ASSEMBLY Figure 7 1 I bi l ...

Page 134: ... through a 30 degree arc each side of center Later aircraft have the bungee removed from the nose gear steering mechanism and are steerable through a 20 degree arc each side of center A shimmy dampener is also included in the nose gear The three struts are of the air oil type with the normal static load extension being 3 25 inches for the nose gear and 4 50 inches for the main gear The brakes are ...

Page 135: ...he control console between the front seats Figure 7 3 Forward rotation of the wheel gives nose down trim and aft rotation gives nose up trim The rudder is conventional in design and incorporates a rudder trim The trim mechanism is a spring loaded recentering device The trim control is located on the right side of the pedestal below the throttle quadrant refer to Figure 7 5 Turning the trim control...

Page 136: ...lly retracted up position When the flap is to be used as a step make sure the flaps are in the retracted up position 7 11 ENGINE CONTROLS Engine controls consist of a throttle control and a mixture control lever These controls are located on the control quadrant on the lower center of the instrument panel Figure 7 5 where they are accessible to both the pilot and the copilot The controls utilize t...

Page 137: ...PIPER AIRCRAFT CORPORATION SECTION 7 PA 28 161 WARRIOR III DESCRIPTION OPERATION ON 7 ON ISSUED JULY 1 1994 REPORT VB 1565 7 7 565 7 7 CONTROL QUADRANT AND CONSOLE Figure 7 5 1 I I ___ ...

Page 138: ...red to the leading edge of each wing with screws and nut plates This allows removal for service or inspection The fuel tank selector control Figure 7 7 is located on the left side panel forward of the pilot s seat The button on the selector cover must be depressed and held while the handle is moved to the OFF position The button releases automatically when the handle is moved back to the ON positi...

Page 139: ...ARRIOR III DESCRIPTION OPERATION ON 7 ON ISSUED JULY 1 1994 REPORT VB 1565 7 9 565 7 9 FUEL SYSTEM SCHEMATIC Figure 7 9 ENGINE FUEl PUivP ELECTRIC FUEL PUMP LEFT MAIN TANK CARBURETOR TRANSDUCER FUEL QUANTITY GAUGE FUEL PRESSURE GAUGE RIGHT MAIN TANK ...

Page 140: ...facilitate starting Pressing the momentary primer switch on automatically activates the electric fuel pump and opens a solenoid valve which then supplies fuel to the fuel primer lines 7 15 ELECTRICAL SYSTEM The electrical system includes a 28 volt 60 amp alternator a 24 volt battery a voltage regulator and a master switch relay Figure 7 11 The battery is in a box mounted on the forward right face ...

Page 141: ...ying through cloud fog or haze since the reflected light can produce spatial dis orientation Strobe lights should not be used in close proximity to the ground such as during taxiing takeoff or landing Unlike previous generator systems the ammeter as installed does not show battery discharge rather it indicates the electrical load on the alternator in amperes With all the electrical equipment off a...

Page 142: ...61 WARRIOR III REPORT VB 1565 ISSUED JULY 1 1994 7 12 ALTERNATOR AND STARTER SCHEMATIC Figure 7 11 ALTERNATOR FIELD TO LIGHT DIMMING ALTERNATOR SWITCH EXTERNAL POWER RECEPTICAL ELECTRIC CLOCK _ I c ___ AMMETER sa OIL PRESSURE SWITCH BATIERY FEEDER STARTER ACC STARTER ...

Page 143: ...ome inoperative A vacuum gauge mounted on the far left instrument panel provides a pilot check for the system during operation A decrease in pressure in a system that remained constant over an extended period may indicate a dirty filter dirty screens possibly a sticky vacuum regulator or leak in the system a low vacuum indicator light is provided in the annunciator panel Zero pressure would indica...

Page 144: ... in the system to protect the gyros The valve is set so the normal vacuum reads 4 8 to 5 2 inches of mercury a setting which provides sufficient vacuum to operate all the gyros at their rated RPM Higher settings will damage the gyros and with a low setting the gyros will be unreliable The regulator is located behind the instrument panel Vacuum pressure even though set correctly can read lower at v...

Page 145: ...ument panel The turn indicator on the left side is electrically operated The radios are located in the center section of the panel and the circuit breakers are in the lower right corner of the panel Standard instruments include a compass an airspeed indicator a tachometer altimeter ammeter engine cluster gauge fuel quantity gauge and an annunciator panel The compass is mounted on the windshield bo...

Page 146: ... AIRCRAFT CORPORATION DESCRIPTION OPERATION PA 28 161 WARRIOR III REPORT VB 1565 ISSUED JULY 1 1994 7 16 ISSUED JULY 1 1994 MENT PANEL 15 TYPICAL INSTRUMENT PANEL Figure 7 15 0 0 Q Qr IJ m 9 e IS e si 0 0 82 i 0 ei E i 0 e et ei I i e 0 d 0 N N N 0 I 8 I I _ 0 _ ...

Page 147: ...R ELECTRIC TYPICAL INSTRUMENT PANEL Figure 7 15 cont 1 CLOCK ELECTRIC OPTIONAL 2 AIRSPEED INDICATOR 3 ATTITUDE GYRO 4 ALTIMETER 5 DAY NIGHT SWITCH 6 ANNUNCIATOR PANEL 7 COMPASS MAGNETIC 7a COMPASS CORRECTION CARD 8 COMM NAV RADIO 9 TRANSPONDER 10 AMMETER DIGITAL 11 HOUR METER 12 TACHOMETER RPM 13 FUEL QUANTITY 14 DIRECTIONAL GYRO 15 TURN BANK 16 VACUUM GAUGE 17 CABIN AIR CONTROL WINDSHIELD DEFROST...

Page 148: ...er and defroster must be on during alternate static source operation The altimeter error is less than 50 feet unless otherwise placarded Both the pitot and static lines can be drained through separate drain valves located on the left lower side of the fuselage interior A heated pitot head which alleviates problems with icing and heavy rain is available as optional equipment The switch for the heat...

Page 149: ... 7 DESCRIPTION OPERATION ISSUED JULY 1 1994 REPORT VB 1565 7 19 REPORT VB 1565 7 19 TATIC SYSTEM gure 7 17 PITOT STATIC SYSTEM Figure 7 17 r 1i I 1 ___ 1 ALTIMETER 2 AIRSPEED INDICATOR 3 PITOT HEAT SWITCH OPTIONAL 4 VERTICAL SPEEO INDICATOR PITOT HEAD 6 DRAIN VALVES 7 ALTERNATE STATIC SOURCE 5 ...

Page 150: ...5 ISSUED JULY 1 1994 7 20 ISSUED JULY 1 1994 LATING SYSTEM 19 HEATING AND VENTILATING SYSTEM Figure 7 19 __ I l 1 FRESH AIR INLET 2 CABIN EXHAUST OUTLET 3 DEFROSTER OUTLETS 4 BLOWER SWITCH PANEL 5 DEFROSTER CONTROL 6 HEATER CONTROL 7 CABIN HEAT DIVERSICN CONTROL 8 FRESH AIR CONTROL COCKPIT 9 FRESH AIR CONTROL PASSENGER CABIN HEAT FRESH AIR ...

Page 151: ...lets or surface Fresh air inlets are located in the leading edges of the wings near the fuselage At each front seat location there is an adjustable fresh air outlet on the side of the cabin near the floor Cabin air is exhausted through an outlet located below the rear seat 7 25 CABIN FEATURES For ease of entry and exit and for pilot passenger comfort the front seats are adjustable fore and aft The...

Page 152: ...enever an inflight emergency situation occurs 7 27 BAGGAGE AREA A 24 cubic foot baggage area located behind the rear seat is accessible from the cabin or loaded through a large 20 x 22 inch outside baggage door on the right side of the fuselage Maximum capacity is 200 pounds Tie down straps are available and they should be used at all times NOTE It is the pilot s responsibility to be sure when the...

Page 153: ...tted head nylon screws for ease of removal these screws may be readily removed with a variety of common items such as a dime a key a knife blade etc If there are no tools available in an emergency the screw heads may be broken off by any means The ELT meets the requirements of FAR 91 52 A battery replacement date is marked on the transmitter to comply with FAA regulations the battery must be repla...

Page 154: ... back to OFF In the event the transmitter is activated by an impact it can be turned off by moving the ELT switch OFF Normal operation can then be restored by resetting the switch to ARM It may also be turned off and reset by positioning the remote switch to the ON and then immediately to the ARM position The transmitter can be activated manually at any time by placing either the remote switch or ...

Page 155: ...riods 8 2 8 5 Preventive Maintenance 8 3 8 7 Airplane Alterations 8 4 8 9 Ground Handling 8 5 8 11 Engine Air Filter 8 7 8 13 Brake Service 8 8 8 15 Landing Gear Service 8 9 8 17 Propeller Service 8 11 8 19 Oil Requirements 8 12 8 21 Fuel System 8 12 8 23 Tire Inflation 8 15 8 25 Battery Service 8 16 8 27 Cleaning 8 16 8 29 Cold Weather Operation 8 19 REPORT VB 1565 8 i 565 8 i ...

Page 156: ...REPORT VB 1565 8 ii THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 157: ...ficient use from their airplane and keeping it in the best mechanical condition Consequently Piper from time to time issues service releases including Service Bulletins Service Letters Service Spares Letters and others relating to the airplane Piper Service Bulletins are of special importance and Piper considers compliance mandatory These are available on the Piper com website Depending on the nat...

Page 158: ...per Aircraft Corporation cannot accept responsibility for the continued airworthiness of any aircraft not maintained to these standards and or not brought into compliance with applicable Service Bulletins issued by Piper Aircraft Corporation instructions issued by the engine propeller or accessory manufacturers or Airworthiness Directives issued by the FAA A programmed inspection approved by the F...

Page 159: ...nder Federal Aviation Regulations FAR Part 61 may perform certain preventive maintenance as defined in the FARs This maintenance may be performed only on an aircraft which the pilot owns and operates and which is not used in air carrier or air taxi commercial operations service All other aircraft maintenance must be accomplished by a person or facility appropriately certificated by the Federal Avi...

Page 160: ...ollowing Aircraft Papers are in order and in the aircraft a To be displayed in the aircraft at all times 1 Aircraft Airworthiness Certificate Form FAA 8100 2 2 Aircraft Registration Certificate Form FAA 8050 3 3 Aircraft Radio Station License if transmitters are installed b To be carried in the aircraft at all times 1 Pilot s Operating Handbook 2 Weight and Balance data plus a copy of the latest R...

Page 161: ...e long enough to clear the nose and or tail by not less than fifteen feet and a qualified person should ride in the pilot s seat to maintain control by use of the brakes b Taxiing Before attempting to taxi the airplane ground personnel should be instructed and approved by a qualified person authorized by the owner Engine starting and shut down procedures as well as taxi techniques should be covere...

Page 162: ...the wind if possible 2 Set the parking brake by pulling back on the brake lever and depressing the knob on the handle To release the parking brake pull back on the handle until the catch disengages then allow the handle to swing forward CAUTION Care should be taken when setting brakes that are overheated or during cold weather when accumulated moisture may freeze a brake 3 Aileron and stabilator c...

Page 163: ...cover if available Be sure to remove the pitot head cover before flight 7 Cabin and baggage doors should be locked when the airplane is unattended 8 11 ENGINE AIR FILTER The wet type polyurethane foam air filter must be inspected at least once every fifty hours Under extremely adverse operating conditions it may be necessary to inspect the filter more frequently The filter is disposable and inexpe...

Page 164: ...t immediately 3 Wipe the filter housing with a clean cloth soaked in unleaded gasoline When the filter housing is clean and dry install the filter c Installation Of Engine Air Filter When replacing the filter install the filter in the reverse order of removal 8 13 BRAKE SERVICE The brake system is filled with MIL H 5606 petroleum base hydraulic brake fluid The fluid level should be checked periodi...

Page 165: ...jacks Depress the valve core to allow air to escape from the strut housing chamber Remove the filler plug and slowly raise the strut to full compression If the strut has sufficient fluid it will be visible up to the bottom of the filler plug hole and will then require only proper inflation Should hydraulic fluid be below the bottom of the filler plug hole fluid should be added Replace the plug wit...

Page 166: ...re 8 1 1 BRAKE RESERVOIR 2 RIGHT BRAKE AND RUDDER PEDAL 3 LEFT BRAKE AND RUDDER PEDAL 4 RIGHT BRAKE CYLINDER 5 LEFT BRAKE CYLINDER 6 BRAKE HANDLE 7 HANDLE RELEASE BUTTON 8 LINE INLET 9 CLEVIS PIN 10 MASTER CYLINDER ASSEMBLY 11 BOLT ASSEMBLY 12 TORQUE TUBE 13 COPILOrS RIGHT BRAKE AND RUDDER PEDAL 14 COPILOrS LEFT BRAKE AND RUDDER PEDAL ...

Page 167: ...until the airplane is at the height desired 8 17 PROPELLER SERVICE The spinner and backing plate should be frequently cleaned and inspected for cracks Before each flight the propeller should be inspected for nicks scratches and corrosion If found they should be repaired as soon as possible by a rated mechanic since a nick or scratch causes an area of increased stress which can lead to serious crac...

Page 168: ...60 F 50 40 or 50 30 F to 90 F 40 40 0 F to 70 F 30 30 40 or 20W 40 Below 10 F 20 30 or 20W 30 When operating temperatures overlap indicated ranges use the lighter grade oil NOTE Refer to the latest issue of Lycoming Service Instruction 1014 Lubricating Oil Recom mendations for further information 8 21 FUEL SYSTEM a Servicing Fuel System At every 50 hour inspection the fuel screens in the strainer ...

Page 169: ...dditive is directed into the flowing fuel stream The additive flow should start after and stop before the fuel flow Do not permit the concentrated additive to come in contact with the aircraft painted surfaces or the interior surfaces of the tanks Some fuels have anti icing additives pre blended in the fuel at the refinery so no further blending should be performed Fuel additive cannot be used as ...

Page 170: ...ximum of 25 U S Gallons When using less than the standard 50 gallon capacity fuel should be distributed equally between each tank There is approximately 17 gallons in the fuel tank when fuel level is even with bottom of filler neck indicator d Draining Fuel Strainer Sumps and Lines The fuel tank sumps and strainer should be drained daily prior to the first flight and after refueling to avoid the a...

Page 171: ...king e Draining Fuel System The bulk of the fuel may be drained from the system by opening valve at the inboard end of each fuel tank Push up on the arms of the drain valve and turn counterclockwise to hold the drain open The remaining fuel in the system may be drained through the filter bowl Any individual tank may be drained by closing the selector valve and then draining the desired tank 8 23 T...

Page 172: ...p to charge recharge starting at a 4 amp rate and finishing with a 2 amp rate Quick charges are not recommended 8 27 CLEANING a Cleaning Engine Compartment Before cleaning the engine compartment place a strip of tape on the magneto vents to prevent any solvent from entering these units 1 Place a large pan under the engine to catch waste 2 With the engine cowling removed spray or brush the engine w...

Page 173: ...e gear with additional solvent and allow to dry 4 Remove the cover from the wheel and remove the catch pan 5 Lubricate the gear in accordance with the Lubrication Chart in the PA 28 161 Service Manual c Cleaning Exterior Surfaces The airplane should be washed with a mild soap and water Harsh abrasives or alkaline soaps or detergents could make scratches on painted or plastic surfaces or could caus...

Page 174: ...t cloth Do not use a circular motion 5 A severe scratch or mar in plastic can be removed by rubbing out the scratch with jeweler s rouge Smooth both sides and apply wax e Cleaning Headliner Side Panels and Seats 1 Clean headliner side panels and seats with a stiff bristle brush and vacuum where necessary 2 Soiled upholstery except leather may be cleaned with a good upholstery cleaner suitable for ...

Page 175: ...erization plate is installed on the inlet opening of the oil cooler This plate should be installed whenever the ambient temperature reaches 50 F or less The plate should be removed and stored in the cockpit when the ambient temperature exceeds 50 F It is recommended that an optional Engine Breather Tube Winterization Kit be installed for cold weather operation This kit is available through your Pi...

Page 176: ...SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING SERV MAINT PA 28 161 WARRIOR III REPORT VB 1565 ISSUED JULY 1 1994 8 20 THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 177: ...age No 1 3 TABLE OF CONTENTS SECTION 9 SUPPLEMENTS Paragraph Page No No 9 1 General 9 1 1 Auxiliary Vacuum System 4 pages 9 3 REPORT VB 1565 9 i 565 9 i ...

Page 178: ...REPORT VB 1565 9 ii THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 179: ...nal systems and equipment not provided with the standard airplane All of the Supplements provided by this section are FAA Approved and consecutively numbered as a permanent part of this Handbook The information contained in each Supplement applies only when the related equipment is installed in the airplane PIPER AIRCRAFT CORPORATION SECTION 9 PA 28 161 WARRIOR III SUPPLEMENTS ON 9 NTS ISSUED JULY...

Page 180: ...SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA 28 161 WARRIOR III REPORT VB 1565 ISSUED JULY 1 1994 9 2 THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 181: ... Airplane Flight Manual when the Piper Auxiliary Vacuum System is installed in accordance with Piper Drawing 87774 2 The information contained herein supplements or supersedes the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein For limitations procedures and performance information not contained in this supplement consult the Pilot s Operating H...

Page 182: ...ons IMC if vacuum pressure falls below 4 8 In Hg 3 The auxiliary pump motor assembly and elapsed time indicator must be removed from service after 500 hours accumulated operating time or 10 years whichever occurs first SECTION 3 EMERGENCY PROCEDURES LOSS OF VACUUM SUCTION Vacuum inop VAC annunciator and VAC OFF warning lamp lit 1 Vacuum gauge Check to verify inoperative pump If vacuum gauge reads ...

Page 183: ...rior to entering instrument flight conditions 1 Turn off non essential electrical equipment 2 Turn on auxiliary vacuum pump and verify AUX ON light illuminated and electrical load is approximately 11 amps on ammeter 3 Turn off auxiliary vacuum pump and verify AUX ON light goes out NOTE For maximum service life avoid continuous non emergency operation of the auxiliary vacuum pump SECTION 5 PERFORMA...

Page 184: ...sections labeled VAC OFF and AUX ON The VAC OFF section is controlled by a vacuum switch in the primary pneumatic system and illuminates an amber light when the engine driven pump is inoperative or when the system vacuum falls below the switch activation level The AUX ON section is controlled by a vacuum switch on the manifold and illuminates a blue light when the auxiliary pump is operating and c...

Page 185: ... 9 7 REPORT VB 1565 9 7 2 3 10 PRIMARY SYSTEM 17777 7777A AUXILIARY SYSTEM 1 ENGINE DRIVEN DRY AIR PUMP 2 MANIFOLD CHECK VALVE ASSY 3 AUX ELECTRICALLY DRIVEN DRY AIR PUMP 7 ATTITUDE GYRO 8 DIRECTIONAL GYRO 9 FILTER 4 PRESSURE SENSING SWITCH 10 OVERBOARD VENT 5 SYSTEM REGULATOR PRESS SENSING SWITCH 11 FIREWALL 6 VACUUM SUCTION GAUGE ...

Page 186: ...SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 1 PA 28 161 WARRIOR III REPORT VB 1565 ISSUED JULY 1 1994 9 8 THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 187: ...age No 1 1 TABLE OF CONTENTS SECTION 10 OPERATING TIPS Paragraph Page No No 10 1 General 10 1 10 3 Operating Tips 10 1 REPORT VB 1565 10 i 565 10 i ...

Page 188: ...REPORT VB 1565 10 ii THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 189: ...t a slower speed 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 UP position before they will lock and support weight on the step d Before attempting to reset any circuit breaker allow a two to five minute cooling off period e Before starting the engine check that all radio switches light switches and the pi...

Page 190: ...vailable in FAA publications such as regulations advisory circulars Aviation News AIM and safety aids i Prolonged slips and skids which result in excess of 2000 ft of altitude loss or other radical or extreme maneuvers which could cause uncovering of the fuel outlet must be avoided as fuel flow inter ruption may occur when the tank being used is not full j Hand starting of the engine is not recomm...

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