Piper Malibu PA-46-310P, Pilot Operating Handbook

Page 1: ...nt 36 Severe Icing Supplement 37 AD 91 07 08 R1 Supplement 39 Section 2 Table of Contents 43 2 1 General 45 2 3 Airspeed Limitations 45 2 5 Airspeed Indicator Markings 46 2 7 Power Plant Limitations 47 2 9 Leaning Limitations 47 2 11 Power Plant Instrument Markings 48 2 13 Weight Limits 48 2 15 Center of Gravity Limits 49 2 17 Maneuver Limits 49 2 19 Flight Load Factors 49 2 21 Kinds of Operation ...

Page 2: ...an 20 amps above known electrical load 84 3 31 Propeller Overspeed 86 3 33 Emergency Landing Gear Extension 86 3 35 Spin Recovery 86 3 37 Engine Roughness 87 3 39 Emergency Descent 87 3 41 Pressurization System Malfunction 88 3 43 Cabin Air Contamination Smoke Evacuation 88 3 45 Gyro Suction Failure Suction below 4 8 in Hg Aircraft not equipped with stand by vacuum pump 89 3 47 Inadvertant Icing E...

Page 3: ...32 Section 5 Performance 133 Section 5 Table of Contents 133 5 1 General 135 5 3 Introduction Performance and Flight Planning 135 5 5 Flight Planning Example 137 5 7 Performance Graphs 143 Airspeed Calibration 145 Angle of Bank vs Stall Speed 146 Wind Components 148 Takeoff Ground Roll 0 Flaps 149 Takeoff Ground Roll 20 Flaps 150 Takeoff Distance Over 50ft Obstacle 0 Flaps 151 Takeoff Distance Ove...

Page 4: ...ty Vacuum Pump Install 337 08 27 2004 196 JPI EDM 700 Install 337 08 04 2003 198 Suspa Door Struts Install 337 04 07 1997 209 Gas Cylinder Install 337 06 15 1995 211 Gas Cylinder Install 337 07 24 1995 213 Loran Install Removal 337 10 31 1993 217 Loran Install 337 10 24 1984 225 6 7 General Loading Recomendations 229 6 9 Weight Balance Determination for Flight 230 Loading Graph 233 CG Range Weight...

Page 5: ...92 8 3 Airplane Inspection Periods 295 8 5 Preventive Maintenance 296 8 7 Airplane Alterations 296 8 9 Ground Handling 297 8 11 Engine Induction Air Filter 299 8 13 Brake Service 300 8 15 Hydraulic System Service 302 8 17 Landing Gear Service 302 8 19 Propeller Service 303 8 21 Oil Requirements 304 8 23 Fuel System 305 8 25 Tire Inflation 309 8 27 Battery Service 309 8 29 Emergency Oxygen System O...

Page 6: ...ion System Supplement 436 Hydraulic Pump Annunciator Light and Motor Control Supplement 452 3M Ryan Stormscope WX 11 Supplement 456 Supplemental Electric Heater Supplement 462 Bendix King RDS Digital Weather Radar Supplement 470 Digital Fuel Management System Operating Manual 472 Hartzell Propeller Supplement 483 Piper SB 1258 496 Section 10 Operating Tips 504 Section 10 Table of Contents 504 10 1...

Page 7: ...Malibu Pilot s Operating Handbook PIPER ...

Page 8: ...ATE OF APPROVAL JANUARY 11 1984 WARD EVANS D O A NO S0 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY THE FEDERAL AVIATION REGULATIONS AND ADDITIONAL INFORMATION PROVIDED BY THE MANUFACTURER AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT MANUAL THIS HANDBOOK MUST BE CARRIED IN THE AIRPLANE AT ALL TIMES REVISED APRIL 1 ...

Page 9: ...RCRAFT 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 PU BU CATIONS DEPARTMENT Piper Aircraft Corporation Issued January 11 1984 REPORT VB 1200 ii ...

Page 10: ... ...

Page 11: ...TALLATIONS 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 INSPECTED IN ACCORDANCE WITH THE INSPECTION PROGRAM PUBLISHED BY THE OWNER OF THE STC SINCE NON PIPER APPROVED STC INSTALLATIONS MAY CHANGE SYSTEMS INTERFACE OPERATING CHARACTERISTICS AND COMPONENT LOADS OR STRES...

Page 12: ...owed by a small letter in direct sequence with the same common numbered page II Identification of Revised Material V Each handbook page is dated at the bottom of the page showing the date of original issue and the date of the latest revision Revised text and illustrations are indicated by a black vertical line located along the outside margin of each revised page opposite the revised added or dele...

Page 13: ...on Signature and Date Revised para 1 7 Revised item g Revised para 3 1 Revised procedure Revised para 3 47 Revised Index Revised procedures Revised procedures relocated text Relocated text Revised procedures added Warning Relocated text Relocated text revised procedures Relocated text revised procedures Relocated text revised procedures Relocated text revised procedures Relocated text revised airs...

Page 14: ...xt revised para 4 21 Relocated text revised para 4 23 Relocated text revised para 4 25 Relocated text Revised airspeed revised para 4 33 Revised para 6 1 Revised para 6 5 Added new para Relocated text Revised para 7 9 Revised para 7 13 Revised para 7 19 Revised Figure 7 17 Revised Figure 7 21 Revised Figure 7 25 Added Caution revised item c 2 Revised Warning moved text Relocated text Relocated tex...

Page 15: ...xt added item d renumbered pg Added new pg Relocated text revised item 6 renumbered pg Relocated text renumbered pg Relocated text revised item 3 renumbered pg Relocated text revised item 7 renumbered pg Relocated text renumbered pg Relocated text renumbered pg Relocated text revised item 3 renumbered pg Relocated and revised text renumbered pg Relocated text renumbered pg Revised Section 6 Revise...

Page 16: ...ion of Revision Signature and Date Revised it m 0 Revised ara 3 47 Revised Table of Contents Relocated text Relocated text Revised para 7 9 Revised para 7 31 Revised Table of Contents Revised Supplement No I KAS 297B Added Section 7 info to Supplement No 7 Added Supplement No 10 Ward Evans July 30 1984 Revised para 2 7 Revised para 2 11 Revised Para 2 25 Added info Added para 3 49 Added note Added...

Page 17: ... January 8 1986 New page Revised figure 7 2 Revised para 3 3 Revised para 3 48 New page New page Revised para 4 23 Revised para 4 31 11 Revised para 7 9 D H Trompler May 29 1986 Relocated figure 7 5 New page Serial numbers added Revised para 3 11 Relocated info from page 3 16 Relocated info to page 3 16 Relocated info to page 3 15 Relocated info from page 3 15 Revised para 3 13 Revised para 3 27 R...

Page 18: ...age 4 23 Revised para 4 19 Relocated info from page 4 22 Relocated info to page 4 24 Relocated info from page 4 23 Relocated info to page 4 24a Relocated info from page 4 24 Revised para 4 25 Revised para 4 27 Relocated info to 4 26 Relocated info from page 4 25 Revised para 4 27 Added Note Revised para 4 27 Added Note and Warning to to para 4 31 Relocated info to 4 30 Relocated info from page 4 2...

Page 19: ... i 9 83 thru 9 86b 9 103 thru 9 106 9 107 thru 9 112 Description of Revision Revised fig 7 15 Revised para 7 21 Revised para 7 31 Revised para 8 21 Revised para 8 23 Revised table of contents Revised page numbering Added Supplement 11 Added Supplement 12 FAA Approval Signature and Date if Ju ne Lt IM7 Date REPORT VB 1200 vi e ...

Page 20: ...evised Caution D H Trompler F b 13 1220 Date Revised Table ofContents Revised fig 7 13 Revised fig 7 15 Revised Table ofContents 1 L Corrected header Added Supplement No 14 D H Tromplcr Ma 14 1220 Date Pages added Revised para 2 7 I Corrected issue date Revised Descent checklist Revised fig 7 13 lists of items operated off Emerg and Main Buses Revised fig 7 15 lists of items operated off Emerg and...

Page 21: ...roval Description of Revisions Signature and Date Renumbered items 7 thru 9 as 8 thru 10 Added new item T MJed Designated it em b 1 a Added item b 1 b Moved info to page 9 7 Relocated info from page 9 6 Moved info to page 9 7a Relocated info from page 9 7 l l Revised items 3 and 4 Added para to Section 4 D H Tropkr A12ril 22 1221 Date V u ...

Page 22: ... to page 4 24a Info relocated from page4 24 Revised Notes Para 7 29 revised and info deleted Info relocated from page7 38 Para 7 29 revised and info deleted Info moved to page 7 37 Revised Section 2 para e D ffl Revised Note Info deleted from para 4 a W R Moreu Revised Note FAA DOA Coordinator w rn11 l Date Para 4 5 revised Note Para 4 21 revised Note Para 4 27 revised Added Para 7 6 Info relocate...

Page 23: ... 5 Revised para 4 21 Eliminated duplicate info Revised T of C Added page Revised para 8 35 Revised para 8 35 Added page para 8 36 Added page para 8 36 Added page Q f k Revised Section 2 Revised Section 4 Peter E Peck Revised Section 4 Revised Section 4 Revised Section 7 Oct 15 1997 Date Added Rev 16 to L of R Added page and Rev 16 to L ofR Added page Revised T ofC Added para 2 32 Relocated info fr...

Page 24: ...ge 3 22 PeterE Peck 4 ii Revised T ofC 4 34 Added page and para 4 49 March 19 1999 Date Rev 17 vi k Added Rev 17 to L ofR PR020325 2 6 Revised para 2 21 AlbertJ Mill March 25 2002 Date Rev 18 iii Added Warning and moved PR021014 info to page iv iv Moved info from page iii vi k Added Rev 18 to L of R 8 1 Moved info to page 8 lB and revised para 8 1 8 lA Added page and revised para 8 1 8 lB Added pa...

Page 25: ...PILOT S OPERATING HANDBOOK LOG OF REVISIONS cont Revision Number and Revised Code Pages REPORT VB 1200 vi I FAA Approval Description of Revisions Signature and Date REVISED MARCH 19 1999 ...

Page 26: ...N 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 REPORT VB 1200 vii ...

Page 27: ... 1 17 1 19 1 21 Introduction Engine Propeller Fuel Oil Maximun1 Weights Standard Airplane Weights Cabin and Entry Dimensions Baggage Space and Entry Dimensions Specific Loading Symbols Abbreviations and Terminology Page No 1 l 1 3 1 3 1 3 1 4 1 4 1 4 1 5 1 5 1 5 1 7 REPORT VB 1200 1 i ...

Page 28: ...ght The pilot is also responsible for remaining 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...

Page 29: ...IOP MALIBU 14 6 4 42 m Wing Arca sq ft 174 9 Min Turning Radius ft from pivot point to wing tip 35 4 43 0 1 3 1 m REPORT VB 1200 1 2 4 7 1 38 m 80 0 DIA 2 03ml l11 3 3 4ml STATIC GROUND LINE THREE VIEW Figure 1 1 4 5 DIHEDRAL __l ISSllED JANUARY II 1984 ...

Page 30: ...anufacturer c Blade Model d Number of Blades e Hub Model 0 Propeller Diameter inches I Minimum 2 Maximum g Propeller Type 1 7 FUEL AVGAS ONLY a Fuel Capacity U S gal total b Usable Fuel U S gal total c Fuel 520 7 5 1 Six Cylinder Direct Drive Horizontally Opposed Air Cooled Turbocharged Fuel Injected Hartzell F8052 2 BHC C2YF 1 BF 78 80 Constant Speed Hydraulically Actuated 122 120 I Minimum Grade...

Page 31: ...15W 50 20W 50 15W 50 20W 50 25W 60 When operating temperatures overlap indicated ranges use the lighter grade oil Multi viscosity oils meeting TCM specification M HS 24A are approved 1 11 MAXIMUM WEIGHTS a Maximum Ramp Weight lbs b Maximum Takeoff Weight lbs c Maximum Landing Weight lbs d Maximum Zero Fuel Weight lbs e Maximum Weights in Baggage Compartments lbs I Forward 2 Aft 1 13 STANDARD AIRPL...

Page 32: ...abin Height max d Entry Width e Entry Height SECTION I GENERAi 49 5 148 47 24 46 1 17 BAGGAGE SPACE AND ENTRY DIMENSIONS a Compartment Volume cu ft I Forward 2 Aft b Entry Dimensions in I Forward 2 Aft 1 19 SPECIFIC LOADING a Wing Loading lbs per sq ft b Power Loading lbs per hp ISSUED JANUARY 11 1984 14 20 9 X 23 24 X 46 23 4 13 2 REPORT VB 1200 1 S ...

Page 33: ...SECTION I GENERAL PIPER AIRCRAFT CORPORATION PA 46 310P MALIBll THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1200 1 6 ISSllED JANllARY 11 1984 ...

Page 34: ...s 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 IAS values published in this handbook assume zero instrument error Indicated Airspeed expressed in Knots Mach Number is the ratio of true airspeed to the speed of sound True Airspeed is the airspeed ofan airplane re...

Page 35: ... 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 speed at which the airplane is controllable Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration Best Angle of Climb Speed is the airspeed w...

Page 36: ... free air static temperature obtained either from inflight temperature indications or ground meteorological sources adjusted for in strument error and compressibility effects The number actually read from an altimeter when the barometric subscale has been set to 29 92 inches of mercury 1013 2 miJlibars Altitude measured from standard sea level pressure 29 92 in Hg by a pressure or barometric altim...

Page 37: ... Route Segment REPORT VB 1200 1 10 The demonstrated ratio of the change in 1 height during a portion of a climb to the horizontal distance traversed in the same time interval The demonstrated crosswind velocity is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during certification tests The distance required t...

Page 38: ... by its arm Moment divided by a constant is used to simplify balance calculations by reducing the number of digits The point at which an airplane would balance if suspended Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane The arm obtained by adding the airplane s individual moments and dividing the sum by the total weight The extreme c...

Page 39: ...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 maneuver It includes weight of start taxi and run up fuel Maximum Weight approved for the start of the takeoff run Maximum weight approved for the landing touchdown Maximum weight exclusive of usable fuel...

Page 40: ...Section 2 Limitations Supplements found inserted before Table of Contents _ l ...

Page 41: ...ly 31 2008 46 350P PA 46R 350T Part Number 761 Section 77 20 00 pages 1 3 876 Chapter 77 Engine Indicating and 4 dated August 28 2007 Section 77 20 00 pages 1 through 4 page 2 dated July 31 2008 1 The Director ofthe Federal Register approved the incorporation by reference of this service information under 5 U S C 552 a and 1 CFR part 51 2 For service information identified in this AD contact Piper...

Page 42: ...es for the Pilot s Operating Handbook POH 1 1ft rbine inlet temperature indication fails or is suspected offailure during takeoff clim escent or landing set power per the POH Section 5 Power Setting Table and then le the approximate POH Power Setting Table fuel flow plus 4 GPH 2 Ifthe turbine inlet temperature cation fails or is suspected offailure after cruise power has been set maintain the powe...

Page 43: ...e is certificated Flight in freezing rain freezing driz zle or mixed icing conditions supercooled liquid water and ice crystals may result in ice build up on protected surfaces exceeding the capability ofthe ice protection system or may result in ice fonning aft ofthe protected surfaces This ice may not be shed using the ice protection systems and may seriously degrade the perfonnance and controll...

Page 44: ... not retract them until the airframe is clear ofice Report these weather conditions to Air Traffic Control b Incorporating the AFM revisions as required by this AD may be perfonned by the owner operator holding at least a private pilot certificate as authorized by section 43 7 of the Federal Aviation Regulations sl l4 CFR 43 7 and must be entered into the aircraft records showing compliance with t...

Page 45: ...rument flight rules or conditions he FAA determined that because of the nature of these accidents rulemaking in this area ould not wait until the investigation program is complete The action required immediate operational limitations on the affected airplanes l hls 1 _ revision changeivt aragraph fat 1 of the AD f rom Flight in instrument flight rule IFR meteorological conditions is prohibited to ...

Page 46: ...into Section 2 Limitations of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual and operate the airplane in accordance with these limitations e Special flight pe r mits may be issued in accordance with FAR 21 197 and 21 199 to operate airplanes to a location where the requirements of this AD can be accomplished f An alternate method of compliance or adjustment of the complianc...

Page 47: ... __ ________ ...

Page 48: ...1 Issued in Kansas City Missouri n April 19 1991 t trong Acting Manager Small Airplane Directorate Aircraft Certification Service 3 t 00 391 f d 001 3Jl I t 11 f l WO 2t 1 16 61 dtt ...

Page 49: ...ions Power Plant Instrument Markings Weight Limits Center of Gravity Limits Maneuver Limits Flight Load Factors Kinds ofOperation Equipment List Fuel Limitations Operating Altitude Limitations Cabin Pressurization Limits Noise Level Maximum Seating Configuration Icing Infomtation Placards Page No 2 1 2 1 2 2 2 3 2 3 2 4 2 4 2 5 2 5 2 5 2 6 2 7 2 8 2 8 2 8 2 8 2 9 I 2 10 ISSUED JANUARY 11 1984 REVI...

Page 50: ... u INTENTIONALLY LEFr BLANK u u ...

Page 51: ...ver Exceed Speed v r Do not exceed this speed in any operation Maximum Structural Cruising Speed V o Do not exceed this speed except in smooth air and then only with caution Design Maneuvering Speed VA Do not make full or abrupt control move ments above this speed At 4100 LBS Gross Weight At 2450 LBS Gross Weight CAUTION KIAS 20 173 135 103 Maneuvering speed decreases at lighter weight as the effe...

Page 52: ...ing Gear Retraction Speed V1 0 Do not exceed this speed when retracting the landing gear Maximum Landing Gear Extended Speed VLE Do not exceed this speed with the landing gear extended 2 5 AIRSPEED INDICATOR MARKINGS MARKING Red Radial Line Never Exceed Yellow Arc Caution Range Smooth Air Only Green Arc Normal Operating Range White Arc Flap Down KIAS 183 170 135 120 170 130 200 IAS KCAS 180 167 13...

Page 53: ...and up g Fuel AVGAS ONLY minimum grade h Number ofPropellers i Propeller Manufacturer j Propeller Hub and Blade Model k Propeller Diameter inches Minimum Maximum I Blade Angle Limits SECTION2 LIMITATIONS 1 Teledyne Continental TSI0 520 BE 2600RPM 240 F 460 F 1750 F 1800 F 38 0 in Hg 35 0in Hg lOPSI lOOPSI 38 5 gal hr 40 0 ga1 hr IOOor IOOLL Aviation Grade 1 Hartzell BHC C2YF IBF F8052 78 80 Low Pi...

Page 54: ...0 PSI 6 gal hr to 38 5 gal hr 38 5 gal hr 6 gal hr to Green Arc Normal Operating Range Red Line Maximum 40 gal hr 4oga1 hr V f Turbine Inlet Temperature Green Arc Normal Operating Range Red Line Maximum 1200 F to 1750 F 1750 F g Cylinder Head Tem rature Green Arc Normal Operating Range 240 F to 420 F Red Line Maximum 460 F Fuel flow gauge P N 548 843 with red line at 40 0 gal hr is also approved f...

Page 55: ...um used is 100 0 inches ahead of the forward pressure bulkhead 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 17 MANEUVER LIMITS No acrobatic maneuvers including spins approved 2 19 FLIGHT LOAD FACTORS a Positive Load Factor Maximum 1 Flaps Up 2 Flaps Down b Negative Load...

Page 56: ...s 4 Tachometer 5 Oil pressure indicator 6 Oil temperature indicator 7 Fuel flow indicator 8 Manifold pressure indicator 9 Cylinder head temperature indicator 10 Turbine inlet temperature indicator 11 Fuel quantity indicator each tank 12 Flap position indicator 13 Elevator rudder trim position indicator 14 Volt ammeter 15 Alternator 16 Gear position indicator lights 17 Gear warning horn 18 Safety r...

Page 57: ...altitude warning light 8 Vacuum pump f Required For Flight Into Known Icing Conditions I Refer to Section 9 Supplement I0 IOTE The above system and c4uipmcnt list docs not include specific flight in trumcnts and commu nication na igation equipment required by the FAR Part 91 and 135 operating requirements 2 23 FUEL LIMITATIONS a Total Capacity 122 U S GAL b Unusable Fuel 2 U S GAL The unusable fue...

Page 58: ...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 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 F A ...

Page 59: ...uest priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the icing conditions Unusually extensive ice accumulation on the airframe and windshield in areas not normally observed to collect ice Accumulation of ice on the upper surface of the wing aft of the protected area Accumulation of ice on the engine cowling and propeller spinner farther aft than norma...

Page 60: ...proved for V F R I F R day and night icing flight when equipped in accordance with the Airplane Flight Manual In full view of the pilot the following takeoff and landing checklists will be installed TAKEOFF CHECKLIST Fuel on Proper Tank Engine Gauges Checked Induction Air Primary Seat Backs Erect Mixture Set Propeller Set Fasten Belts Harnesses Flaps Set Trim Set Controls Free Door Secured Air Con...

Page 61: ...RE RE ENGAGEMENT On the face of the turbine inlet temperature gauge CRUISE MIXTURE SETTING IS 50 LEAN OF PEAK T I T See A F M In full view of the pilot WARNING SECTION2 LIMITATIONS TURN OFF STROBE LIGHTS WHEN IN CLOSE PROXIMITY TO GROUND OR DURING FLIGHT THROUGH CLOUD FOG OR HAZE Near the magnetic compass CAUTION COMPASS CALIBRATION MAY BE IN ERROR WITH ELECTRICAL EQUIPMENT OTHER THAN AVIONICS ON ...

Page 62: ...the inside of the forward baggage door MAXIMUM BAGGAGE THIS COMPART MENT 100 LBS On aft baggage closeout MAXIMUM BAGGAGE THIS COMPART MENT 100 LBS In full view of the pilot PRESSURIZED LANDING NOT APPROVED Adjacent to fuel tank filler caps AVGAS ONLY GRADE 100LL GRADE 100 Over emergency exit handle I REPORT VB 1200 2 12 EMERGENCY EXIT REMOVE GLASS PULL DOOR IN LIFT UP ISSUED JANUARY 11 1984 REVISE...

Page 63: ...te of this AD accomplish the requirements of paragraphs a l and a 2 of this AD NOTE 2 Operators should initiate action to notify and ensure that flight crewmembers are apprised of this change 1 Revise the FAA approved Airplane Flight Manual AFM by incorporating the following into the Limitations Section of the AFM This may be accomplished by inserting a copy of this AD in the AFM WARNING Severe ic...

Page 64: ...aps are extended do not retract them until the airframe is clear of ice Report these weather conditions to Air Traffic Control b Incorporating the AFM revisions as required by this AD may be performed by the owner operator holding at least a private pilot certificate as authorized by section 43 7 of the Federal Aviation Regulations 14 CFR 43 7 and must be entered into the aircraft records showing ...

Page 65: ... 3 5 High Cylinder Head Temperature 3 6 Turbine Inlet Temperature Trn Indicator Failure 3 6 Electrical Failures 3 6 Electrical Overload 3 7 Propeller Overspeed 3 9 Emergency Landing Gear Extension 3 9 Spin Recovery 3 10 Engine Roughness 3 10 Emergency Descent 3 10 Pressurization System Malfunction 3 11 Cabin Air Contamination Smoke Evacuation Pressurized 3 12 Gyro Suction Failure 3 12 Inadvertent ...

Page 66: ...ure TIT Indicator Failure 3 27 Electrical Failures 3 29 Electrical Overload 3 31 Propeller Overspeed 3 33 Emergency Landing Gear Extension 3 35 Spin Recovery 3 37 Engine Roughness 3 39 Emergency Descent 3 41 Pressurization System Malfunction 3 43 Cabin Air Contamination Smoke Evacuation 3 45 Gyro Suction Failure 3 47 Inadvertent Icing Encounter or Flight in Snow 3 48 Hydraulic System Malfunction 3...

Page 67: ...e section is devoted to amplified 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 judgment and common sense Pilots should familiarize themselves with the procedures given in this s...

Page 68: ...ng gear selector UP If sufficient altitude has been gained to attempt a restart Maintain safe airspeed Fuel selector switch to tank containing fuel Induction air ALTERNATE Aux fuel pump HIGH Throttle reduce as necessary approx 75 power Upon restart if normal engine operation is not established promptly select LOW boost pump setting CAUTION If normal engine operation and fuel flow is not immediatel...

Page 69: ...d be turned OFF The lack of fuel flow indication could indicate a leak in the fuel system If power is not restored prepare for power off landing Trim for 90 KIAS POWER OFF LANDING Prop control Full DECREASE Best gliding angle 90 KIAS Locate suitable field Establish spiral pattern 1000 ft above field at downwind position for normal landing approach When field can easily be reached slow to 77 KIAS f...

Page 70: ... switch DUMP Cabin pressurization control PU LL to unpressurize After 5 second delay Battery switch OFF ALTNR switch es OFF Cabin heat OFF CAUTION The dump valve will remain open if activated prior to turning the aircraft electrical system OFF This provides maximum airflow through the cabin for smoke evacuation Do not turn the cabin dump switch OFF The dump valve will close and cannot be reactivat...

Page 71: ...fpower restored Aux fuel pump OFF Mixture as required Ifpower not restored within ten seconds Aux fuel pump HIGH Mixture FULL RICH Throttle approx 75 power ENGINE DRIVEN FUEL PUMP FAILURE Throttle retard Aux fuel pump HIGH Throttle reset as required Mixture reset as required CAUTION If normal engine operation and fuel flow is not immediately re established the auxiliary fuel pumpshouldbe turnedOFF...

Page 72: ...FULL RICH If failure occurs after setting cruise power Mixture 6 GPH fuel flow above value in section 5 Power Setting Table Cylinder Head and Oil Temperatures MONITOR NOTE Repair TIT indicator as soon as possible ELECTRICAL FAILURES CAUTION The alternator output circuit breakers should never be opened manually when the alternators are functioning properly as voltage regulator damage may occur ALTE...

Page 73: ...rative Ifpower not restored dual alternator system ALTR switch affected alternator OFF Electrical loads reduce Ammeter operating alternator monitor I ELECTRICAL OVERLOAD alternator more than 20 amps above known electrical load AIRCRAFT EQUIPPED WITH SINGLE ALTERNATOR Electrical load reduce ALTR No 1 switch ON Battery switch OFF Ifalternator loads are reduced Electrical load reduce to minimum Land ...

Page 74: ...be required AIRCRAFf EQUIPPED WITH DUAL ALTERNATORS Electrical load reduce below 60 amps ALTR No 1switch OFF ALTR No 2 switch ON Battery switch OFF If alternator loads are reduced Electrical load reduce to minimum ALTR No I switch ON Land as soon as practical NOTE Due to increased system voltage and radio noise operation with the ALTR switches ON and the battery switch OFF should be made only when...

Page 75: ...E rpm then set if any control available Airspeed reduce Throttle as required to remain EMERGENCY LANDING GEAR EXTENSION Prior to emergency extension procedure below 2600 rpm Battery switch check ON Circuit breakers check DAY NIGHT dimmer switch DAY in daytime If landing gear does not check down and locked Airspeed below I00 KIAS Hydraulic pump circuit breaker 25 amp PULL Landing gear selector UP E...

Page 76: ...when rotation stops Control wheel as required to smoothly regain level flight attitude ENGINE ROUGHNESS Mixture adjust for maximum smoothness Induction air ALTERNA fE Aux fuel pump LOW Fuel selector select another tank EMERGENCY DESCENT NOTE If pressurized the following procedure will result in an immediate loss of pressurization and the cabin altitude will rise at an uncon trolled rate Seat belts...

Page 77: ...oceed as follows Cabin dump switch DUMP Cabin pressurization control PULL to unpressurize Emergency descent below 12 500 feet NOTE If emergency oxygen is installed don masks activate oxygen generators and check flow Descend below 12 500 feet V Should the aircraft suddenly lose pressurization proceed as follows Cabin dump switch check OFF Cabin pressurization control check IN Emergency descent belo...

Page 78: ...elow 12 500 feet If fumes smoke dissipate land as soon as practical to investigate problem If fumes smoke persist refer to Fire in Flight paragraph 3 15 IGYRO SUCTION FAILURE Suction below 4 8 in Hg Aircraft not equipped with stand by vacuum pump V Unpressurized flight Cabin dump OFF Cabin pressurization control IN Cabin differential pressure above 2 3 PSID Pressurized flight Cabin differential pr...

Page 79: ...LFUNCTION serial numbers 46 8608047 and up and aircraft with Piper Kit No 765 178V 765 179V or 765 197 installed HYD PUMP amber annunciator light illuminates continuously HYD PUMP circuit breaker pull and reset Verify normal hydraulic system operation If HYD PUMP annunciator light illuminates second time HYO PUMP circuit breaker pull Land as soon as possible and investigate cause FLAP SYSTEM MALFU...

Page 80: ... In either case above if fire continues more than a few seconds the fire should be extinguished by the best available external means The fuel selector valve should be OFF and the mixture at idle cut off if an external fire extinguishing 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 ...

Page 81: ...MERG PROCEDURES INADVERTENT ICING ENCOUNTER OR FLIGHT IN SNOW Pitot heat ON Cabin heat full ON Windshield defrost ON Vent Defog Fan ON Change heading and or altitude to exit icing conditions or snow Induction air monitor ISSUED JANUARY 11 1984 REVISED APRIL 30 19 4 ALTERNATE if required REPORT VB 1200 3 13 ...

Page 82: ...LFUNCTION serial numbers 46 8608047 and up and aircraft with Piper Kit No 765 178V 765 179V or 765 197 installed HYD PUMP amber annunciator light illuminates continuously HYD PUMP circuit breaker pull and reset Verify normal hydraulic system operation If HYD PUMP annunciator light illuminates second time HYO PUMP circuit breaker pull Land as soon as possible and investigate cause FLAP SYSTEM MALFU...

Page 83: ...ine power loss is usually caused by fuel flow interruption and power will be restored shortly after fuel flow is restored The first step is to prepare for a power off landing refer to paragraph 3 13 An airspeed of at least 90 KIAS should be maintained If altitude permits switch the fuel selector to another tank containing fuel and turn the auxiliary fuel pump on LOW Reset the mixturecontrol as I r...

Page 84: ...the engine to windmill may restore power Ifpower loss is due to water fuel flow indications will be normal If engine failure was caused by fuel exhaustion power will not be restored after switching fuel tanks until the empty fuel lines are filled This may require up to ten seconds Ifpower is not regained proceed with the Power Off Landing procedureV refer to paragraph 3 13 CAUTION The auxiliary fu...

Page 85: ...e may be lost by widening your pattern using flaps or slipping or a combination of these Whether to attempt a landing with gear up or down depends on many factors If the field chosen is obviously smooth and firm and longenough to bring the plane to a stop the gear should be down If there are stumps or rocks or other large obstacles in the field the gear in the down position will better protect the...

Page 86: ...oke evacuation Do not turn the cabin dump switch OFF The dump valve will close and cannot be reactivated unless electrical power is turned ON An emergency descent should be executed to an altitude of 12 500 feet or less and a landing made as soon as possible WARNING If emergency oxygen is installed use ONLY if flames and heat are not present Ifan engine fire is present close the throttle move the ...

Page 87: ...n the engine may stop suddenly Maintain altitude until such time as a power off landing can be accomplished Do not 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 loss such as sudden increases in tempera...

Page 88: ...ine driven fuel pump failure is indicated retard the throttle and turn the auxiliary fuel pump on HIGH The throttle and mixture should 1 then be reset as required The HIGH position of the auxiliary fuel pump will supply fuel flow for approximately 75 power or less A landing should be made at the nearest appropriate airport as soon as possible and the cause of the failure investigated CAUTION If no...

Page 89: ...e cooling If TIT indication fails after cruise power has been set maintain cruise power setting and lean to 6 GPH fuel flow above that specified in the Power Setting Table in Section 5 of this handbook Continually monitor engine cylinder head and oil temperatures to avoid exceeding limits The TIT indicating system must be repaired as soon as possible after failure has occurred Continued operation ...

Page 90: ...s tum OFF the ALTR switch of the affected alternator insure electrical loads are below 60 amps and continue the flight Monitor the ammeter of the operating alternator since the ALTERNATOR annunciator light will remain on The ammeter is the only indication of the condition of the remaining alternator 3 29 ELECTRICAL OVERLOAD Alternator more than 20 amps above known electrical load If abnormally hig...

Page 91: ...lternator turn the ALTR No 1 switch OFF and the battery switch OFF and turn the EMER BUS switch ON Activation of the emergency bus switch will allow the use of the minimum equipment necessary to operate the aircraft and will provide maximum flight time prior to battery depletion Refer to the Electrical Schematics in Section 7 for a list of equipment supplied by the emergency bus All electrical loa...

Page 92: ...nsure the landing gear selector is in the UP position pull the emergency gear extend control OUT and fishtail the airplane After the landing gear position lights indicate down and locked move the landing gear selector to the DOWN position CAUTION The emergency gear extension procedure will require the pilot to pull the emergency gear extend control knob through a region of high resistance up to 25...

Page 93: ...FF individually and then both turned back ON If operation is satisfactory on either magneto proceed on that magneto at reduced power to a landing at the first available airport If roughness persists prepare for a precautionary landing at pilot s discretion 3 39 EMERGENCY DESCENT NOTE If pressurized the following procedure will result in the immediate loss of pressurization and the cabin altitude w...

Page 94: ... is installed don the oxygen masks activate the oxygen generators and descend to an altitude of 12 500 feet or below I Should the aircraft suddenly lose pressuri1 ation check that the cabin dump switch has not been activated and that the cabin pressurization control is pushed in If the aircraft does not begin to re pressurize and emergency oxygen is not installed execute an emergency descent to 12...

Page 95: ...f a suction system malfunction during unpressurized flight tum the cabin dump switch OFF push the cabin pressurization control IN and select a cabin altitude to maintain at least 2 3 PSID During pressurized flight select a cabin altitude to maintain at least 2 3 PSID Monitor the electrical directional gyro 3 47 INADVERTENT ICING ENCOUNTER OR FLIGHT IN SNOW WARNING Flight into known icing condition...

Page 96: ...ged Pulling and resetting the HYO PUMP circuit breaker will restore electrical power to the hydraulic pump motor and extinguish the annunciator After resetting normal hydraulic system operation should be verified V If normal hydraulic system operation is not restored pull the HYO PUMP circuit breaker and land as soon as possible It may be necessary to lower the landing gear using the emergency ext...

Page 97: ...not regained or the FLAPS annunciator remains illuminated pull the Fl AP MOTOR circuit hreakcr and land as soon as possihle to ascertain the cause of the prohlem The tlaps will remain in the same position as when the malfunction occurred ISSl ED JANVARY 11 1984 REVISED MAY 8 1986 REPORT VB 1200 3 28a ...

Page 98: ...SECTION 3 EMERG PROCEDURES PIPER AIRCRAFT CORPORATION PA 46 310P MALIBU REPORT VB 1200 3 28b Tms PAGE INTENTIONALLY LEFT BLANK ISSUED JANUARY 11 1984 REVISED MAY 8 1986 V V ...

Page 99: ...ing Engine 4 7 Starting Engine When Hooded 4 8 Starting With External Power Source 4 8 Warm Up 4 9 Taxiing 4 9 Ground Check 4 10 Before Takeoff 4 10 Takeoff 4 11 TakeoffCliJ nb 4 12 Cruise Climb 4 12 Cruising 4 12 Descent 4 13 Approach And Landing 4 13 Go Around 4 14 Stopping Engine 4 14 Parking 4 14 Amplified Nonnal Procedures General 4 15 Preflight Check 4 15 Before Starting Engine 4 18 Starting...

Page 100: ... 22 Ground Check 4 22 Before Takeoff 4 23 Takeoff 4 24 Climb 4 25 Cruising 4 25 Descent 4 28 Approach and Landing 4 28 Go Around 4 30 Stopping Engine 4 30 Parking 4 30 Stalls 4 30 Turbulent Air Operation 4 31 Landing Gear 4 31 Cabin Pressurization System 4 32 Weight and Balance 4 33 Icing InfOffilation 4 34 REPORT VB 1200 4 ii ISSUED JANUARY 11 1984 REVISED MARCH 19 1999 ...

Page 101: ...iliarize 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 section is devoted to amplified normal procedures which provide deta...

Page 102: ...ane and equipment atmospheric conditions and piloting technique a Best Rate of Climb Speed 110 KIAS b Best Angle of Climb Speed 90 KIAS c Turbulent Air Operating Speed See Subsection 2 3 135 KIAS d Landing Final Approach Speed Full Flaps 77 KIAS e Maximum Demonstrated Crosswind Velocity 17 KTS f Maximum Flaps Extended Speed 10 170 KIAS 20 135 KIAS Full Flaps 36 120 KIAS REPORT VB 1200 4 2 ISSUED J...

Page 103: ...K COCKPIT Control wheel release restraints Parking brake set Gear handle DOWN All switches OFF Avionics OFF Mixture idle cut off Battery switch ON Fuel gauges check quantity Annunciator panel check Oxygen light if installed check Flaps extend Battery switch OFF Primary flight controls proper operation ISSUED JANUA Y 11 1984 REPORT VB 1200 4 3 ...

Page 104: ...ight static port clear RIGHT WING Surface condition clear of ice frost snow Flap and hinges check Aileron and hinges check Static wicks check Wing tip and lights check Fuel tank check supply visually secure cap Fuel tank vent clear Tie down and chock remove Main gear strut proper inflation 2 5 25 in Tire check Brake block and disc check Fuel tank sump drain and check CAUTION for water sediment and...

Page 105: ...tick properly seated Oil filler cap secure Tow bar stow properly secure Bagg gc door close and secure LEFT WING Surface condition clear of ice frost snow Fuel tank sump drain and check CA UT ON for water sediment and proper fuel When draining any amount of fuel care should be taken to ensure that no fire hazard exists before starting engine Tic down and chock remove Main gear strut proper inflatio...

Page 106: ...g performed The unit becomes very hot Ground operation should be limited to three minutes maximum to avoid damaging the heating elements E terior lighting switches ON and check v P1tot check warm Stall warning horn check All lighting switches OFF Pitot heat switch OFF Battery switch OFF Passengers board Doors close and latch Door pins all indicators green WARNING Do not initiate any flight if all ...

Page 107: ...RTING ENGINE Mixture full RICH Throttle full FORWARD Prop control full INCREASE Battery switch ON Mag switches ON Aux fuel pump OFF Primer ON NOTE The amount of prime required depends on engine temperature Familiarity and practice will enable the operator to estimate accurately the amount of prime to use If the engine is hot use prime pump only long enough to purge fuel system of accumulative vapo...

Page 108: ...tion 1 3 minutes will be required when temp is below 20 F Oil press check Alternator s check Gyro suction check STARTING ENGINE WHEN FLOODED Mixture id le cut off Throttle full FORWARD u Prop control full INCREASE U Battery switch ON Aux fuel pump OFF Propeller clear Starter engage When engine fires Throttle rQtard Mixture advance slowly Oil pressure check STARTING WITH EXTERNAL POWER SOURCE Batte...

Page 109: ...attery is at a higher level than the external power supply Throttle lowest possible RPM External power plug disconnect from receptacle Baggage door closed and secure Battery switch ON Altemator s ON check ammeter Oil pressure check WARM UP CAUTION Do not operate engine above 1200 RPM with cabin doors open Throttle 1000 to 1200 RPM Hydraulic pressure check TAXIING Chocks removed Parking brake relea...

Page 110: ...acuum pump check NOTE If flight into icing conditions in visible moisture below 5 C is anticipated conduct a preflight check of the icing systems per Supplement No 10 Ice Protection System Ice protection equipment CHECK AS REQUIRED Volt ammeter check Oil temp check Oil pressure check Propeller exercise then full INCREASE Throttle retard Air conditioner check Annunciator panel press to test Manifol...

Page 111: ...ct Scats adjusted locked in position I Mixture full RICH Prop control full INCREASE Belts harness fastened adjusted Empty seats seat belts snugly fastened J Flaps set Trim set Controls free Door latched Air conditioner OFF Parking brake released TAKEOFF NORMAL Flaps set Trim set Throttle full power WARNING If flight into icing conditions visible moisture below 5 C is anticipated or encountered dur...

Page 112: ...limits at full throttle Limit manifold pressure to 38 in Hg maximum Sec Section 7 Accelerate to 70 KIAS brake release Control wheel back pressure to rotate to climb attitude w After breaking ground accelerate to 74 KIAS Gear UP Accelerate to climb speed Flaps UP TAKEOFF CLIMB NOTE Power should be reduced to cruise climb setting after all obstacles are cleared Mixture full RICH Prop speed 2600 RPM ...

Page 113: ...dure outlined in the amplified procedures of this section Failure to do so will result in excess fuel burn and reduced engine life NOTE Maximum continuous T I T is l 750 F Temporary operation up to 1800 F is permitted in order to define peak T I T In no case should the aircraft be operated more than 30 seconds with a T I T in excess of 1750 F Reference Section 5 power setting table and performance...

Page 114: ...OACH AND LANDING Fuel selector proper tank Seat backs erect Belts harness fasten adjust Aux fuel pump _ OFF Cabin pressure depressurized U Mixture set Prop control set Gear down 170 KIAS max Flaps set Air conditioner OFF Toe brakes depress to check WARNING After pumping several times if one or both toe brakes are inoperative DO NOT attempt landing on a short field NORMAL TECHNIQUE Flaps as require...

Page 115: ...e lO rotate to climb attitude Airspeed 80 KIAS Gear UP Flaps retract slowly Trim as required STOPPING ENGINE Flaps retract Radios and electrical equipment OFF Air conditioner OFF Prop control full INCREASE Throttle CLOSED Mixture idle cut off Magnetos OFF Altemator s OFF Battery switch OFF PARKING Parking brake set Control wheel secured with belts Flaps full up Wheel chocks in place Tie downs secu...

Page 116: ...SECTION4 NORMAL PROCEDURES PIPER AIRCRAFf CORPORATION PA 310P MALIBU THIS PAGE INTENTIONALLY LEFT BLANK I REPORT VB 1200 4 14b ISSUED OCTOBER 14 1991 u V ...

Page 117: ...wer and prevent wear on the units The mixture should be in idle cut off Turn ON the battery switch check the fuel quantity gauges for adequate supply and check that the annunciator panel illuminates If the supplemental oxygen system is installed and its annun ciator is lit the expended canisters must be replaced if oxygen capability is desired for the flight Extend the flaps for the walk around in...

Page 118: ...fuel quantity gauge Replace cap securely The fuel tank vent should be clear of obstructions Remove the tie down and chock Next complete a check of the landing gear Check the gear strut for proper inflation There should be 2 5 25 inches of strut exposure under a 1 normal static load Check the tire for cuts wear and proper inflation Make a visual check of the brake block and disc Drain the fuel tank...

Page 119: ...k Check the main gear strut for proper inflation there should be 2 5 0 25 inches of strut exposure under a normal static load Check the tire and the brake block and disc If installed remove the cover from the pitot head on the underside ofthe wing Make sure the holes are open and clear of obstructions Open the fuel cap and visually check the fuel color The quantity should match the indication that...

Page 120: ...hould be snugly fastened All passengers _ should fasten their seat belts and shoulder harnesses A pull test of the inertia reel locking restraint feature should be performed 4 11 BEFORE STARTING ENGINE WARNING No braking action will occur if aircraft brakes are applied while parking brake handle is pulled and held Before starting the engine the parking brake should be set and the prop control move...

Page 121: ... of prime required depends on engine temperature Familiarity and practice will enable the operator to estimate accurately the amount of prime to use If the engine is hot use prime pump only long enough to purge fuel system of accumulative vapor CAUTION The STARTER ENGAGED annunciator will illuminate during engine cranking Ifthe annun ciator remains lit after the engine is running stop the engine a...

Page 122: ...tion of oil pressure c Starting Engine With External Power Source An optional feature allows the operator to use an external V battery to crank the engine without having to gain access to the airplane s battery Turn the battery and alternator switches OFF and turn all electrical equipment OFF Connect the RED lead of the jumper cable to the POSITIVE terminal of an external 24 volt battery and the B...

Page 123: ... external power supply When the engine is firing evenly advance the throttle to 1000 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 Starter manufacturers recommend that cranking periods be limited to thirty seconds with a two minute rest between cranking periods...

Page 124: ...ith the prop control set to full INCREASE While taxiing make slight turns to ascertain the effectiveness of the steering Observe wing clearances when taxiing near buildings or otherstationary 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 taxiing over ground containing loose stones gravel ...

Page 125: ...ay The propeller control should be moved through its complete range to check for proper operation and then placed in full INCREASE rpm for I takeoff Do not allow a drop of more than 500 RPM during this check In cold weather the propeller control should be cycled from high to low RPM at least three times before takeoff to make sure that warm engine oil has circulated Retard the throttle and check t...

Page 126: ...and the door ajar annunciator light out On air conditioned models the air conditioner must be OFF to ensure normal takeoff climb performance Release the parking brake 4 23 TAKEOFF NORMAL TECHNIQUE Sec Chart Section 5 When the available runway length is well in excess of that required and obstacle clearance is no factor the normal takeoff technique may be used The naps should be set in the retracte...

Page 127: ...uel now indications can exceed their indicated limits at full throttle Limit manifold pressure to 38 in Hg maximum See Section 7 Release the brakes allow the airplane to accelerate to 70 KIAS depending on weight and apply back pressure to rotate for lift off After breaking ground accelerate to 74 KIAS and select gear UP Continue to climb while accelerating to the flaps up best rate of climb speed ...

Page 128: ...SECTION 4 NORMAL PROCEDURES PIPER AIRCRAFf CORPORATION PA 46 JlOP MALIBU THIS PAGE INTENTIONALLY LEFf BLANK I REPORT VB 1200 4 24b ISSUED JANUARY 11 1984 REVISED OCTOBER IS 1997 ...

Page 129: ...ated limits at full throttle See Section 7 It is recommended that this power setting be used only until all obstacles are cleared CRUISE CLIMB Once all obstacles are cleared the power should be reduced to the cruise climb setting of 2500 RPM 35 in Hg and mixture full RICH with an I V airspeed of 125 KIAS below 22 000 ft altitude and 115 KIAS above 22 000ft altitude Use of the auxiliary fuel pump s...

Page 130: ... set the RPM and manifold pressure for the desired cruise power in accordance with the power setting table Using the fuel flow indicator as a reference lean the mixture to Iapproximately 4 gallons per hour above the cruise fuel flow value listed in V the power setting table From this point on use theT I T gage as a reference Slowly lean to peak T I T and continue leaning until the T I T has fallen...

Page 131: ...air should also be selected before entering clouds Manifold pressure may decrease significantly when alternate air is selected depending on altitude power setting and other factors This loss of manifold pressure can exceed 8 inches of Hg when selecting alternate air at cruise power settings during icing conditions If ice is forming on the filter manifold pressure could continue to deteriorate afte...

Page 132: ... the Cabin Altitude Controller to 1000 feet above the pressure altitude of the landing field Adjust the rate control high enough to allow the cabin to descend to the landing setting before the aircraft descends to that altitude For normal letdown the rate knob should be at the nine o clock position A higher setting should be selected for rapid descents so that the aircraft altitude does not catch ...

Page 133: ...ach and landing and the speed of the aircraft at contact with the runway should be varied according to the landing surface conditions of wind and aircraft loading It is generallygood practice to contactthe ground at the minimum possible safe speed consistent with existing conditions As landing distances with this technique will vary performance charts are not furnished SHORT FIELD LANDING APPROACH...

Page 134: ... to idle cut off The throttle should be CLOSED to avoid engine vibration while stopping Then the magneto alternator and battery switches must be turned OFF 4 37 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 in the forward baggage area The aileron and elevator controls should be secured by looping the s...

Page 135: ...ING GEAR WARNING If aircraft electrical power is ON and the landing gear selector is placed in the UP position the landing gear will retract on the ground The pilot should become familiar with the function and significance of the landing gear position indicators and warning lights The red gear warning light on the annunciator panel and the horn operate simultaneously in flight when the throttle is...

Page 136: ...trol cable Ifa cable is broken the air control valve may have failed in either the open or closed position Iffailed open pressurized flight will not be possible but unpressurized flight will be possible Iffailed closed pressurized flight would be possible but should not be attempted as it would not be possible to bring in fresh air should contamination occur Set cabin altitude on the cabin altitud...

Page 137: ...anding field Shortly after letdown is initiated set the cabin altitude to 1000 feet above the pressure altitude of the landing field and adjust the rate control high enough to allow the cabin to descend to the landing setting before the aircraft descends to that altitude For normal letdown the rate knob should be at the normal 9 o clock position A higher setting should be selected for rapid descen...

Page 138: ...wing Immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the severe icing conditions in order to avoid extended exposure to flight conditions more severe than those for which the airplane has been certificated Avoid abrupt and excessive maneuvering that may exacerbate control difficulties Do not engage the autopilot If the autopilot is...

Page 139: ...ENTS SECTION 5 PERFORMANCE Paragraph No 5 1 5 3 5 5 5 7 General Introduction Pcrformann and Flight Planning Flight Planning Example Performance Graphs I isl of 1 igurcs Page No 5 1 5 1 5 3 5 9 5 9 REPORT VB 1200 5 i ...

Page 140: ...r ...

Page 141: ...he various parameters of weight altitude 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 pi...

Page 142: ... Example outlines a detailed flight plan using performance charts in this section Each chart includes its own example to show how it is used WARNING Performance information derived by extrapolation beyond the limits shown on the charts should not be used for flight planning purposes REPORT VB 1200 5 2 ISSUED JANUARY 11 1984 ...

Page 143: ...the Weight and Balance Loading Form Figure 6 11 and the C G Range and Weight graph Figure 6 15 to determine the total weight of the airplane and the center ofgravity position After proper utilization of the information provided the following weights have been determined for consideration in the flight planning example The landing weight cannot be determined until the weight of the fuel to be used ...

Page 144: ...or the takeoff and or the obstacle clearance The 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 flight have fallen well below the available runway lengths Pressure ...

Page 145: ...time for the cruise pressure altitude and outside air temperature values have been established apply the existing conditions at the departure field to graph Figure 5 19 Now subtract the values obtained from the graph for the field of departure conditions from those for the cruise pressure altitude The remaining values are the true fuel distance and time components for the climb segment of the flig...

Page 146: ...nd the true fuel distance and time values needed for the descent segment of the flight plan The values obtained by proper utilization of the graphs for the descent segment of the example are shown below I Time to Descend 18 min minus 3 min 15 min 2 Distance to Descend 60 nautical miles minus 7 nautical miles 53 nautical miles 3 Fuel to Descend 3 5 gal minus 1 0 gal 2 5 gal e Cruise Using the total...

Page 147: ...istance e I minus c 4 minus d 2 400 nautical miles minus 38 nautical miles minus 53 nautical miles 3 Cruise Power 50 lean of peak T I T 4 Cruise Speed 5 Cruise Fuel Consumption 6 Cruise Time e 2 divided by e 4 309 nautical miles divided by 206 KTS 7 Cruise Fuel e 5 multiplied by e 6 15 5 GPH multiplied by 1 5 hrs 0 Total Flight Time 400 nautical miles 309 nautical miles 75 rated power 206 KTS TAS ...

Page 148: ...akeoff 2 7 gal calculated by allowing 5 minutes of fuel flow at takeoff power 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 weight used for the flight The total fuel calculations for the example flight plan are shown below I Total Fuel Required Fuel for Start Taxi and Takeoff plus c...

Page 149: ...laps Takeoff Distance Over 50 Ft Obstacle 0 Flaps Takeoff Distance Over 50 Ft Obstacle 200 Raps Rate of Climb Maximum Continuous Power Time Distance and Fuel to Climb Cruise Climb Time Distance and Fuel to Climb Cruise Speed Vs Altitude Range Endurance Time Distance and Fuel to Descend Glide Time and Distance Balked Landing Climb Landing Distance Over 50 Ft Obstacle Landing Ground Roll Page No 5 1...

Page 150: ...SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA 46 3IOP MAUBl THIS PAGE l IE ll0 1 1 YI EFT HI A K REPORT VB 1200 5 10 ISSUED JANUARY II 1984 ...

Page 151: ...IONS WEIGHT 4100 LBS Air speed 140 KIAS 138 KCAS Gear down Flaps down Air speed 110 KIAS 105 KCAS WITH OR WITHOUT DE ICE BOOTS ZERO INSTRUMENT ERROR _ 60 I I I I I I I I I I GEAR UP FLAPS oo I f f T I I I I I I I I I GEAR DOWN FLAPS DOWN Ill II fl Ill i i i i 1 I 1 1 I Ja 80 100 120 140 160 INDICATED AIRSPEED KNOTS AIRSPEED CALIBRATION Figure 5 1 180 200 220 ISSUED JANUARY 11 1984 REPORT VB 1200 S...

Page 152: ...ple Gear up Flaps o0 Stall speed 82 KIAS at 45 angle of bank Gear down Flaps down Stall speed 75 KIAS at 45 angle of bank I I l I I I I l 1 GEAR UP FLAPS 001 I __l J I I I I I I I IL GEAR DOW fLAPS DOWN l rl I Cl I 70 C w w a Cl I _ 60 Cl 50 40 0 _i _ I ill _ I l I I I I I 10 20 30 40 50 ANGLE OF BANK DEGREES ANGLE OF BANK VS STAI L SPEED figure 5 J 11 J 1 60 REPORT VB 1200 5 12 ISSUED JANUARY 11 ...

Page 153: ...TION SECTION 5 PA 46 3IOP MAUBll PERFORMANCE 40 100 90 30 80 70 20 60 50 10 40 FAHRENHEIT 0 CELSIUS 30 DEGREES DEGREES 20 10 10 0 20 10 20 30 30 40 40 TEMPERATURE CONVERSION Figure 5 5 ISSUED JANUARY 11 1984 REPORT VB 1200 S 13 ...

Page 154: ...gle between flight path and wind 30 Headwind component 26 knots Crosswind components 15 knots ANGLE BETWEEN FLIGHT AND WIND DEGREES I 10 _ 20 r 1 I 30 r I J 40 T 1 J b 4 La500 I J 0 1 _ 1 ci i f I r r 60 J I 1 1 1 1 I d Ir 700 I i r I I 1 r 1 I i 1 1 10 i 1 1 _i 20 30 40 CROSSWIND COMPONENT KTS WIND COMPONENTS Figure 5 7 I 80 I I 90 50 REPORT VB 1200 5 14 ISSUED JANUARY 11 1984 ...

Page 155: ... air temperature 15oC Weight 3765 Pounds Wind 10 Kts Headwind Takeoff ground roll 1490 Ft ASSOCIATED CONDITIONS FLAPS o0 600 RPM FULL THROTTLE BEFORE BRAKE RELEASE LIFTOFF SPEED 77 KIAS PAVED LEVEL DRY RUNWAY I I T I 4000 3600 WEIGHT i _ 3200 POUNDS 2800 0 5 10 1 WIND KTS ...

Page 156: ... I _ 0 o A r l o i I JI 0 r ___ c t I I I I 40 20 0 20 40 OUTSIDE AIR TEMPERATURE 11 C ASSOCIATED CONDITIONS FLAPS 20 2600 RPM FULL THROTTLE BEFORE BRAKE RELEASE LIFTOFF SPEED 70 KIAS PAVED LEVEL DRY RUNWAY y I I I p I I I I I or 1 II I _s I X 1 C r I rr Cl m z i i i 0 0 r 0 I z 90 w w z z r l LI i I O w w cc a r I _ I i i I __ 1 I j I I 1 i i I a l o Ila 1 I I 2400 2300 2200 2100 1 UJ 2000 1900 J...

Page 157: ...D r O o r i I r O J i l ii r J o I l 40 20 0 20 40 OUTSIDE AIR TEMPERATURE o C i ASSOCIATED CONDITIONS FLAPS 0 2600 RPM FULL THROTTLE BEFORE BRAKE RELEASE LIFTOFF SPEED 77 KIAS OBSTACLE CLEARANCE SPEED 89 KIAS PAVED LEVEL DRY RUNWAY I I I i I I r 0 0 I w r I I z t a f _ r _ a _ j 1 _ I _ 4000 3600 3200 2800 WEIGHT POUNDS J I Q ll L I Ill I 111 I 1 I s I I I I 111 I 31 I A lil I _ T 4600 4400 w LL ...

Page 158: ...qq l l f cs 1 tll YI oo_ l I 1 I lb 000 _ _ I ooO ooo J di 2 s 1 Jl ASSOCIATED CONDITIONS FLAPS 20 2600 RPM FULL THROTTLE BEFORE BRAKE RELEASE LIFTOFF SPEED 70 KIAS OBSTACLE CLEARANCE SPEED 74 KIAS PAVED LEVEL DRY RUNWAY I I r i j cli C I m i z _ 0 T e i 7o ii st o S w l o w z z u tti w a a i J I _i _ _ 3800 3600 3400 3200 3000 2800 2600 2400 2200 2000 1800 1600 1400 40 20 0 20 40 4000 3600 3200 2...

Page 159: ...itude 4000 ft Outside air temperature 25 C Weight 3500 lbs Rate of climb 1335 FPM _ ASSOCIATED CONDITIONS GEAR UP FLAPS oo 2600 RPM FULL THROTTLE CLIMB SPEED 110 KIAS t ____ 40 20 0 20 40 400 600 800 1000 1200 1400 1600 OUTSIDE AIR TEMPERATURE o C RATE OF CLIMB FPM ...

Page 160: ...in Distance to climb 39 1 38 naut miles o I oo 1 _ pRE 5 f r I 2 oooJL CRUISE i r I O I I J I I 14000 I 12000 0 J I I i 0000 o I I sooo I 6000 I I I I 4000 I 2000 I T S L EtAl T ii 60 40 20 0 20 40 0 ASSOCIATED CONDITIONS GEAR UP FLAPS oo 2600 RPM FULL THROTTLE WEIGHT 4100 LBS CLIMB SPEED 110 KIAS I L J I 1 fT r r o 1 I I I I I I I j i I I r I I JI 1 I II I I 1 T I I I I I V l r 1 71 I r I I 7 I I...

Page 161: ...imb 26 1 25 min WEIGHT 4100 LBS Distance to chmb 63 1 62 naut miles CLIMB SPEED 126 KIAS TO 22 000 FT 116 KIAS ABOVE 22 000 FT I I 1 _ oO I _ _J _ 2 iL i i __ 1 1 PRE _e q I ii 10 002 __ _ __C _UIS _ J _ __ _Q I 11 J v l I I __ e oOJL JI I I I I I j I 4 00 I J I I I 2 000 I I I r c I u I i 1 o ooo I V 0 l r c 0 I _8000 f I J I J I 1 6000 I I I I II I 4000 I J I 2000 I I I I I DEPARTURE i I I SL I ...

Page 162: ... altitude Cruise fuel flow increases one GPH for each 20 C below standard temperature and decreases one GPH for each 20 C above standard temperature The cruise speeds shown are at mid cruise weight 3740 pounds The speed differential for weight is 0 8 knots per 100 pounds faster at lesser weights and slower at heavier weights The leaning procedure to establish 50 lean of peak T l T is discussed in ...

Page 163: ...I I I I I I I I I I I j I II I J I I f I I I J I I I I I J I I I I I I j I I J J I I I I I I j I I I J I 1 f I J I I I I I j I I I I j I I I i j I t r f cul 5 u ti I 0 I C c I iu j C fjl cii r o 5 e 3 r Ji _ I J I I I I I J I j 1 I I 140 160 18 200 220 TRUE AIRSPEED KNOTS CRUISE SPEED VS ALTITUDE Figure 5 21 240 26 35 33 29 25 21 17 0 13 0 9 VI 5 1 3 7 11 15 0 ISSUED JANUARY 11 1984 REPORT VB 1200...

Page 164: ...IPER AIRCRAFT CORPORATION PA 46 310P MALIBU RANGE I I __ f_ I I I I I I I I JI I I j j I I I I I I I I j I I I I I I I I I I J I I I I j I I I I I j I I I J I I I J I I I I I II I i t J f I I J cu J I 51 cu g si l J g I I I I o a __ o I cu J I oe r J f 0 _ 0 C __g e 1 f f g J j I I I I I j I 1 I 1 1100 1200 1300 1400 1500 1600 NAUTICAL MILES RANGE Figure 5 23 ISSUED JANUARY 11 1984 ...

Page 165: ...CE ENDURANCE w 0 25000 _ t 10000 5 c 8000 6000 4000 2000 S L 5 I I I I ID w U Cl 5_ 5 I cc 0 0 I Q_ I w f 0 I z Cl 0 I C1 I I I I I I I Ill I I I 6 7 8 HOURS ENDURANCE Figure 5 25 ISSUED JANUARY 11 1984 I 1i 1 cc 0 w l Z 1 z 9 I 1 l I I I 1 9 10 REPORT VB 1200 S 25 ...

Page 166: ... l 1 iii 8 41 t O Oo i T aa J i CRUISE _ _ __ _ I 1 I ii L 1 II i 14 I i o _i _ c 1 I r _ I r Jl Joo i I I i I J 0000 1 I _ 8000 i I sooo _ __ I i _ Ooo 1 I 1 1 l 2000 DESTINATION l I I I I I I j tfll 111 E LEVE II 60 40 20 0 20 40 0 OUTSIDE AIR TEMPERATURE C J I r 11 11 i I i J II If I I 1111 tfll l oi I I I ASSOCIATED CONDITIONS GEAR UP FLAPS oo 2200 RPM 25 HG MAP DESCENT SPEED 173 KIAS 1 i _ 1 ...

Page 167: ...cal Miles _J I I I I PRess 1 ALT 2 I I J I I P _ooo _1 I I 1eooo I 4000 I _12000 l I I Q_ooo I I _eooo I I 6000 f 1 4000 I I I I 2000 l I SEA LE EL 60 40 20 0 20 40 OUTSIDE AIR TEMPERATURE o C 0 I r I J I ASSOCIATED CONDITIONS I GEAR UPr FLAPS 0 POWER OFF PROPELLER CONTROL FULL DECREASE GLIDE SPEED 90 KIAS I J 2 r1 f o I J I t I j I 1 14 I J I d I J I I I 1 10 20 30 40 50 60 GLIDE TIME AND DISTANC...

Page 168: ... 775 FPM I I I I I I I I A I t Ll ru _i aa _ I Id I L aO l l o I oa II i i ti I l_ ii I a r A l l i o i w o aa i c i ir t r _ c r J i L l 40 20 0 20 40 OUTSIDE AIR TEMPERATURE C C ASSOCIATED CONDITIONS GEAR DOWN WING FLAPS FULL DOWN 2600 RPM FULL THROTTLE CLIMB SPEED 80 KIAS I 1 1 1 I l 1 l l l 1 1 I l l rs i 0 l lt J1 i I I 1 I 1 400 500 600 700 800 900 RATE OF CLIMB FPM ...

Page 169: ...ULL STALL TOUCHDOWN MAXIMUM BRAKING Landing distance over 50 ft obstacle 1770 ft PAVED LEVEL DRY RUNWAY I I I i en CD lo v J 0 l c e C _ 0 I 0 __ M I o i w 00 z o J i ooO li U _ _ i w 0 tfll a roo J I I I I II I _ 2 f 1 d Q _1 3 I 0 I ci i 1 C l T J r I x l o I ct I I I I _ Gj w u i I I _ __ _ _ _ _ L _ _ i u _ _ i 1 i mw 1 i _ _ i 1 1 400S 40 20 0 20 40 3800 3400 3000 2600 0 5 10 15 OUTSIDE AIR T...

Page 170: ...S 1 p s I I I 40 20 0 20 _ 40 OUTSIDE AIR TEMPERATURE o C i ASSOCIATED CONDITIONS GEAR EXTENDED WING FLAPS FULL DOWN THROTTLE CLOSED FULL STALL TOUCHDOWN MAXIMUM BRAKING PAVED LEVEL DRY RUNWAY I 0 2 I Ill w 2 111111 _Ill w Ill a II _ _ _ _ 111 l ci h C II 1 ct Iii 111o r II I I ii I ii 3800 3400 3000 2600 WEIGHT POUNDS C I _ f I 2 4 o 11111 Z 4 I 1600 1500 1400 1300 1200 1 4 II 1100 1000 1 900 I 8...

Page 171: ...6 5 6 7 6 9 6 11 icncral Airplane Weighing Procedure Weight and Balance Data and Record General Loading Recommendations Weight and Balance Determination for Flight Instructions for Using the Weight and Balance Plotter Page No 6 1 6 2 6 5 6 9 6 10 6 15 REPORT VB 1200 6 i ...

Page 172: ...0 ...

Page 173: ...formance 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 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 recove...

Page 174: ...eful 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 each airplane with the basic empty weight and center of gravity location This data is supplied by Figure 6 5 The removal or addition of equipment or airpla...

Page 175: ...urfaces 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 closed building to prevent errors in scale readings due to wind b Leveling I With the airplane on scales insert a 3 4 inch spacer on each of the main gear struts and a 3 0 inch spacer on the nose gear strut 2 Level airplane refer to Figure 6 3 deflating o...

Page 176: ...FORM Figure 6 1 d Basic Empty Weight Center of Gravity I The following geometry applies to the airplane when it is level Refer to Leveling paragraph 6 3 b A 60 50 in B 157 00 in Level Points Centerline of bottom fuselage skin behind fwd pressure bulkhead The datum is 100 0 inches ahead of the forward pressure bulkhead accessible from nose wheel well LEVELING DIAGRAM Figure 6 3 REPORT VB 1200 6 4 r...

Page 177: ...he airplane as licensed at the factory These figures apply 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 ofthe airplane basic empty weight and a complete history of previous modifications Any c...

Page 178: ...ment 292 6 142 9 41818 Basic Empty Weight 2790 6 133 7 373053 The standard empty weight includes full oil capacity and 2 0 gallons of unusable fuel AIRPLANE USEFUL LOAD NORMAL CATEGORY OPERATION Ramp Weight Basic Empty Weight Useful Load 4 11 81bs 2790 6 lbs 4 327 4 lbs TH IS BAS IC EMPTY WE IGHT C G AND USEFU L LOAD ARE FOR THE AIRPLANE AS LI CENSED AT THE FACTORY REFER TO APPROPR IATE A IRCRAFT ...

Page 179: ...r Modificai1ion 9 20 84 As Licensed 10 2 84 avionics installatio Z Rumting Ba ic c I Weight 11 nge Empt wcigJht 1 i g Wt Lb 51 l Arm Moment Wt Moment In 1001 Lb 1 I 790 6 10935 7 r 841 7 373053 383759 9 2 r 3 4 h Jc J J M t C 1 0 3 91 remove Te xas Ins L ran C Syst install Northstar Ml Lora s s m NEW TOTALS USEFU f 2843 8 38 4 136 ...

Page 180: ... 0 E 2 0 _ 2 i C QJ U c e u e s i C z c C 2 U i c i I J oh QJ 0 i paAOWalf pappy QJ C i 0 c i 0 i QJ C e 0 O s g_ z i 0 I QJ 0 QJ CIJ c f oN wau I c QJ I C 0 0 PIPER AIRCRAFT CORPORATION PA 46 3IOP MALIBU i WEIGHT AND BALANCE RECORD cont Figure 6 7 cont REPORT VB 1200 6 8 ISSllED JANUARY 11 1984 V u ...

Page 181: ...spinner 5 7 lbs llnstalled 3 blade prop 62 75 lbs spi1nner 4 9 S lbs New empty weight 2858 516 lbs New a m 135 09 New moments 386175 46 New useful load 1 25 9 44 lbs ARM 135 45 in 311 2 inches 29 0 inches 30 2 inches 28 0 inches Aircraft Services Inc 1160 A1rpor1 lloid Hu1m n tll K 67 I 01l 11 6 f 62066201B MOMENTS 385960 46 1654 0 1165 0 1895 0 139 0 Kevin Mead ...

Page 182: ...0 REG H MO MENT 365844 56 0 00 115 90 0 00 0 00 0 00 0 00 0 00 0 00 o_oo 0 00 0 00 0 00 0 00 0 00 000 0 00 0 00 0 100 0 00 NIEW AIIRCRAFT EMPTY WEIGHT 135 45 385 9 0 W IMAXIIMUM TAKE OFF WEU iHT EMPTY WEIGHT USEFUi LO AD NEW CENTER QIF GRA VITY 4100 00 2849 53 1250 47 135 45 ABOVE EQUIIPMENiT INSTALLED IN ACCORDAINCIE WITH MANUFAC URER S RECOMMENDAT1tONS IIN STAIJLATION M I NUALS A Nll AC 43 1 3 1...

Page 183: ... ...

Page 184: ...844 13 ARM 1135 42 11nches Installed stereo and voltag1e converf er 4 4 lbs 157 0 inches New empty wei ght 2848 53 lbs New airm 11 35 45 New moment 385844 56 New useful oad 1269 47 MOMENTS 385153 76 690 8 Kevin Mead A P 4433641987 1160 Airpori ltoa 1 lut 111 1111 K S67 501 620_728 n 56 f iiic 2 01H ...

Page 185: ...nce dated 6 1 01 WEIGHT 2841 43 Installed JPI indicator 0 9 lbs JPI probes and wires 1 8 lbs New empty weight 2844 13 New arm 135 42 ARM 134 66 inches MOMENTS 384949 2 100 8 New moment 3 153 76 New useful load 1273 87 Keviif Mact _ ______ do 7 __ A PN U36ld ffl c _ rr z ...

Page 186: ... _ _ t _ ...

Page 187: ... Aircraft Sevices Inc 1 U S Certificated Mechanic I Manufacturer AddJass 1180 Aic1221lB Foreign Certificated Mechanic C Certificate No Clly Hutchinson Stale KS Cettificated RepairStation Zip 67501 Coumry USA Cettificaled Maintenance Organization A P 443641987 D I certify that the repair and oralteration made to the unlt s Identified in item 5 above and described on the reverse or attachments heret...

Page 188: ...picable airworthiness requirements lusA I 11 11 10 I 8 Description of Work Accomplished Nationality and Registration Mark Date Replaced original Piper engine mount with modified engine mount supplied by Kosola and Associates per STC SA 02779AT Modification was performed per drawing K84010 dated 4 30 03 Instructions for continued airworthiness are attached to form 337 END r 1 I AAitlnn02I C hnntc l...

Page 189: ... June 28 2005 or later FAA approved revision is a required part ofthis STC The ICA specifics the engine mount inspection requirements for the Piper Aircraft Models listed on this STC The compati bility ofthis design change with other previously approved modifications must be determined by the installer Ifthe holder ofthis STC agrees to permit another pcrnon to use this certificate to alter the pro...

Page 190: ...nd stronger attachment tubes so to reduce the stresses in this area 89137 engine mount shown 84010 02 and 102460 02 engine JJ LOunt modification area is the same identical similar as the 89137 engine IIi eunt Typlc 21 Engine Mount A rrcw s indlc rto E nglne Mount Ac tuatcr J tuc h Fe t Figu A Inspections Inspection intervals ofthe actuator attach feet Fig A shall be in intervals as determined by t...

Page 191: ...v 5 Unit Identification Make Model Serial No As described in Item 1 above 6 Conformity Statement B Kind ofAgency I U S Certlficated Mechanic I Manufacture Foreign Certificated Mechanic C Certificate No Certificated Repair Station Certificated Maintenance Organization 594203699 D I certify that the repair and or alteration made to the unit s identified in item 5 above and described on the reverse o...

Page 192: ... STC SA02779AT In Accordance with Kosola And Associates Drawing Number K84010 Dated April 30 2003 or Later FAA Approved Revisions Engine Mount Part Number Has Changed to K84010 01 As per Drawing Kosola And Associates Instructions For Continued Aiiworthiness ICA Document Number ICA 1 Dated June 28 2005 or Later FAA Approved Revision is required part of this STC The ICA Specifies the Engine Mount In...

Page 193: ...al No As describedIn Item 1 above 6 Confonnny Statement B Kind ofAgency 1 U S Certificated Mechanic I Manufacturer Foreign Certificated Mechanic C Certificate No Certificated RepairStation Certificated Maintenance Organization A P 443641987 D I certify that the repair and oralteration made to the unlt s Identified in item 5 above and described on the reverse or attachments hereto have been made in...

Page 194: ...shed Nationality and Registration Mark Date I Removed original TS10520BE engine Installed engine TS10550C1 B and M5 cooling kit per STC SA01770CH using instruction manual M5 D3000 rev A dated 1 16 03 Propeller model PHC G3YF 1E 7890K and spinner p C 3535 3P previously installed Equipment list revised Performed functional checks Operations satisfactory No electrical interference noted Instructions ...

Page 195: ...y 6 2003 or later FAA Approved revision is required Q 3 This modification did not increase the noise level and was not considered an acoustical change as defined in Title I C Federal Regulations Section 21 93 b 4 lfthe holder agrees to permit another person to use this certificate to alter the product the holder must give the other pers o ___ written evidence ofthat permission End YZ r e nak Ju vv...

Page 196: ...and Address B Kind ofAgency C Certificate No Mead Aircraft Services Inc X U S Certificated Mechanic A P 443641987 648 Arrowhead Rd Foreian Certificated Mechanic Inman KS 67546 Certifica1ed Reoalr Station Manufacturer D I certify that the repair and or alteration made to 1he unit s identified in item 4 above and desaibed on the reverse or attachments hereto have been made in accordance with the req...

Page 197: ...uctions Installation conforms to ACCf ptable Methods Techniques and Practices of AC 43 13 1A Chapter 5 section 1 pars 227 228 230 231 Chapter 11 section 1 pars 406 407 410 section 2 pars 424 428 430 section 3 pars 442 445 447 451 section 7 pars 514 520 AC 43 13 Chapter 2 pars 21 27 Chapter 3 pars 36 38 42 44 Chapter 11 pars 211 214 Chapter 13 pars 261 263 Ground checks made and CD player exhibits ...

Page 198: ... y U S Certificated Mechanic I Manufacturer Addrass i J Acco 1 r e f M Foreign Certificated Mechanic C Certificate No City r k l I IC State 1 lS Certificated Repair Station Zip t2 1 9 Country Certificated Maintenance Organization A P 443641987 D I certify that the repair and or alteration made to the unit s identified in item 5 above and described on the reverse or attachments hereto have been mad...

Page 199: ...hiness requirements USA 8 Description of Work Accomplished Nationality and Registration Mark Date Removed original 2 blade propeller Installed propeller model PHC G3YF 1 E 7890K spinner p C 3535 3P using instruction manual HP46 310 NST dated 1 14 02 Weight balance and equipment list revised Performed functional checks Operations satisfactory No electrical interference noted Instructions for contin...

Page 200: ...ler 2 FAA Approved Airplane Flight Manual Supplement HP46 310 AFMS dated December 20 2001 or later FAA Approved revision is required 3 This modification did not increase the noise level and was not considered an acoustical change as defined in paragraph 21 93 b of the Federal Aviation Regulations 4 If the holder agrees to permit another person to use this certificate to alter the product the holde...

Page 201: ...beyond the aircraft specified below is a violation of proprietary laws and is subject to legal action Please keep the STC installation instructions Flight Manual Supplement and this authorization sheet in a secure location There will be a charge for issuing replacement documents STC Number Aircraft Model Serial Number Aircraft Registration Date Issued Issued by IU nnbkn 1 uJcf SA01616CH PA46 31 OP...

Page 202: ...whead Rd Irunan KS 67546 6 Confonnity Statement B Kind ofAgency C Certificate No U S Certificated Mechanic A P 443641987 Foreian Certificated Mechanic Certiflca1ed Renair Station Manufacturer D I certify that the repair and or atteration made to the unit s identified in item 4 above and desaibed on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 ofth...

Page 203: ...onalilyandregistration mark and date work completed Completed Malibu Power Propeller LLC Replacement Installation of Standby Vacuum Pump with Continuous Duty Vacuum Pump per instructions drawings and photos included in Document No M5 D2101 dated 9 29 03 as contained in FAA Form 8110 3 Performed functional checks operations satisfadory No eledrical interference noted Weight balance changes negligib...

Page 204: ...ess B Kind ofAgency C Certificate No Mead Aircraft Services Inc X U S Certificated Mechanic 443641987 648 Arrowhead Rd Fonmn Certificated Medlanic Inman KS 67546 Certificated Renalr Station Manufadurer 0 I certify that1he repair and or alteration made to the unit s identified in item 4 above and desaibed on the mve se or attachments hereto have been made in accordance with the requirements of Part...

Page 205: ...iretaftnationalityand registration mark and date work completed Installed JPI EDM 700 EGT 701 engine monitor per STC SA2586NM using installation manual 103 rev C Routed harness along existing engine electrical harness Attached LH RH TIT probe options Performed functional checks operations are satisfactory No electrical interference noted Electrical load does not excede 80 of total capacity Instruc...

Page 206: ...THE EGT 100 200 SERIES AND 701 SERIES TEMPERATURE INDICATORS FOR EXHAUST GAS CYLINDER HEAD TEMPERATURE MONITORING SYSTEM STC NUMBER SA2586NM DATE AUGUST 14 1985 REV 13 DATE February Last pril ICd OS 30Al3 2 22 PM fAA lPPpn m APR 182093 611 CAAFT C flCATION QFFtCE LOS JNlTI IJ S r p1 ...

Page 207: ...1 Addition of RPM MAP to identification list for EGT 701 Sheet ALL Addition of American Champ 8KCAB 7GCBC 7ECA 7GCBA 7GCAA 7KCAB Beech 95 58 Cessna T206H Gulfstream American 114 8 TC Maule MXT 7 180 A B Mooney Rocket Conv Per STC SA 00472SE STC SA 5691NM M20K M20J Pitts Avlat S 1S S 1T S 2 S 2A Christen Avail A 1 S 2B Mooney M 22 M20S Jobmastcr Comp DGA 15P V Jeatherly 620 A B Thompson Navion C Ce...

Page 208: ...A1A ABWE 8 0 100 180 ABWE 4 A BKCAB A21CE 4 A 7GCBC 7ECA 7GCBA 7GCAA 7KCAB A 759 4 A GA 7Twin A17S0 ST BT 018S 018C E18S C 45G TC 45G C 45H TC 45H TC A 765 9 E 45J or UC 45J SNB 5 RC 45J SNB 5P E182 9700 G1BS JRB 6 3N 3NM 3TM P7WWesps Jr Model 017S S017S 017R A 649 9 E 017A ATC 713 9 E C17R Army UC 43E ATC 604 9 E G17S ATC 779 9 E 23 A23 A23A A23 19 19A A1CE 4 A B19 M19A A23 24 823 C23 A24 A24R 82...

Page 209: ...charged engines Part number Series 4 4 6 6 4 Cylinder with 4 Cylinder 6 Cylinder with 6 Cylinder RPM MAP RPM MAP EGT 701 EGT 701 EGT 701 EGT 701 4C RIM 4C SCRIM SC 4CORIM 4CO 6CORIM SCO 4CA RIM 4CA 6CARIM SCA 4CT RIM 4CT 6CT RIM 6CT 4CI RIM 4CI 6CIRIM 6CI 4CF RIM 4CF 6CF RIM SCF 4COARIM 4COA SCOARIM 6COA 4COTRIM 4COT 6COT RIM 6COT co RIM 4COI SCOI RIM 6COI 4COF RIM 4COF 6COF RIM 6COF 4COATRIM 4COA...

Page 210: ...ldina Co 64 Gulfstream 65 Gulfstream American 66 Gulfstream American 67 Helio Alliance Aircraft 68 Huahes Helioooter 69 Jobmaster Comoanv 70 Lancair 71 Maule 72 Maule J Mooney 74 Moonev 1S Mooney Rocket Ena Conv MASTER EUGIB1Ll1Y UST J P INSTRUMENTS REPORT SA 2686NM SHEETS Part Number AIRCRAFT MODEL T C D S See P 9 for Series 411 411A 414 414A 421 421A 421B 421C SR 20 A00009CH 6 B SR 22 A00009CH 1...

Page 211: ...n can PA 31P 31P 350 A8EA CST BT PA 32 260 32 300 32S 300 A3SO 6 B PA 32R 300 0 32RT 300 32RT 300T PA 32R 301 32R 301T PA 32 301 32 301T PA 34 200 A7S0 4T AT PA 34 200T 220T A7S0 ST BT PA 38 112 A1BS0 4 CA FAA approved AFM Supplement is required with the EGT 701 The EGT 701 is applicable to all EGT 100 200 series RPM and MAP applicable to the P N EGT 701 4 end 6 cylinder engines only Revision 13 F...

Page 212: ...ce dated 5 6 98 w 2850 73 lbs Removed Wulfsberg flight phone transceiver 7 3 lb mount 0 4 lb cabin control 1 6 lb New empty weight New arm 134 66 incMes New momen 382621 48 New useful load 1276 57 lbs Kevin Mead P 443641987 1969 5 107 9 250 4 648 Arrowhead Rd Inman KS 67546 Phone I Fax 316 585 2180 ...

Page 213: ......

Page 214: ...ORAN RELAY Items Installed ALLIED SIGNAL KLN 908 GP ____ A LLIED SIGNAL KA 92 GPS ANTENNA MID CONTINENT MD 43 ANNUNCIATOR RELAY I New Em New Empty Weight New C G New Useful Load At Gross Weight of 2850 73 135 04 1267 27 4 118 00 Authorized Signature _ Prepared By Peter Wagn CRS LF1 R294K erial 98 Weight 2 843 68 0 50 6 30 0 50 0 75 Arm 135 10 115 90 113 00 143 00 116 00 Moment 384 136 83 57 95 0 0...

Page 215: ... Kind of Agency C Certificate No Skytech Inc U S Certificated Mechar P O Box 4942 Foreign Certificated Mechanic Baltimore 21220 X Certificated Repair Station LF1R294K MD Manufacturer D I certify that the repair and or alteration made to the unit s identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U S F...

Page 216: ...1 Piper upper cabin door strut PIN 980162 502 and baggage door strut PIN 585 231 Units are used to hold doors in open position B Installed the following 1 Suspa Inc cabin door strut PIN 820162 502 SK 2 Suspa Inc baggage door strut PIN 585 231 SK 3 Suspa Inc gas cylinders are manufactured to some weight and outside dimensions as original units supplied by Piper 4 Suspa Inc gas cylinders are attache...

Page 217: ..._ X POWERPLANT PROPELLER Type APPLIANCE Manufacturer 6 Conformity Statement A Agency s Name and Address B Kind of Agency C Certificate No Skytech Inc U S Certificated Mechanic Foreign Certificated Mechanic P o Box 4942 LF1R294K Baltimore MD 21220 X Certificated Repair Station Manufacturer D I certify that the repair and or alteration made to the unit s identified in item 4 above and described on t...

Page 218: ...fy with airer 1ft nationality and rer stration mark and date work completed 1 Removed the following a Piper aircraft supplied gas cylinder PIN 980162 502 that is installed to hold upper cab n door in open position 2 Installed the following a b c l i SUSPA Inc gas cylirider J N 820162 502 SK SUSPA Inc gas cyllnder 1 manufactured to s om e v eight and outside dimensions as orir nal unit supplied by ...

Page 219: ...Identification Model Serial No As described in Item 1 above Type Manufacturer 6 Conformity Statement 5 Type Repair A Agency s Name and Address B Kind of Agency C Certificate No Skytech Inc P O Box 4942 Baltimore MD 21220 U S Certificated Mechanic Foreign Certificated Mechanic LF1R294K X Certificated Repair Station Manufacturer Alteration X D 1 certify that the repair and or alteration made to the ...

Page 220: ...lied gas cylinder PIN 585 231 that is installed to hold Baggage door in open position B Installed the following 1 2 3 SUSPA Inc gas cylinder P N 585 231 SK SUSPA Inc gas cylinder is manufactured to same weight and outside dimensions as original unit supplied by Piper SUSPA Inc gas cylinder is attached to aircraft and door in same configuration as original unit C No Weight and Balance change END __...

Page 221: ... Loran Antenna INSTALLED Northstar Loran NEW TOTAL 10 31 19 y We ght Ne C G Ne Useful G css Weight Weight 2847 4 6 7 7 1 2 2843 68 115 9 252 6 252 6 115 9 252 6 252 6 135 1 Utility Category E npty Weis Ne r C G New t seful Load Gross eight Mo ent 384734 35 776 5 176 8 303 1 I 486 78 101 4 70 7 384136 83 A No N Model Date 10 31 93 Serial No PreFafedBy S David E Conover SkyTech I r artin Sta e A1rpo...

Page 222: ...__ ...

Page 223: ... Kind of Agency C Certificate No U S Certificated Mechanic Foreign Certificated Mechanic X Certificated Repair Station LF1R294K Manufacturer Alteration xx D I certify that the repair and or alteration made to the unit s identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U S Federal Aviation Regulations ...

Page 224: ...M1A receiver s n 19542 Antenna coupler 2010 Loran antenna s n 9334 Loran system functionally tested and installed IAW mfrs instructions p n GM295 rev M System installed IAW AC20 121A App 1 par A F System placarded for VFR USE ONLY System ramp tested and flight tested with no EMI or other interference noted Pilor b e _ Date f 3 REFERENCES AC43 13 1A Chap 11 Chap 13 Chap 15 Sec 1 par 406 407 Sec 2 p...

Page 225: ...bsequent FAA Approved Revision _ C nd This approval should not be extended to other airplanes of this model that incorporate any other previously approved modification unless it is detennined that the interrelationship between this change and any other previously approved modification will introduce no adverse effect on the airworthiness of these airplanes Yk a 1 k l t u nh Mt _ u u n U at al k n ...

Page 226: ... t _ t _ t __ _ ...

Page 227: ...stem 1 1 120 5 132 5 5 2 Inside W i ndow Installation 4 0 200 2 801 0 3 Engine Heat Shield 6 69 0 41 4 New Weight Balance 284 7 4 13 5 1 384734 35 N l Cate ory Utility Category E y Weight 28 4 7 4 lbs E npty We i c Ne C G 135 1 inches Ne C G Ne Useful Loaa 12 70 6 lb s New Useful Load G oss Weight 411 8 0 lbs Gross e ight A ft Make Piper Registra ion No Model PA46 310P Date __ 9_ _2_4_ _9_3_ _ Ser...

Page 228: ...3 2 4 252 6 606 2 7 3 269 8 1969 5 Wul fsberg Rl 18B Transceiver u 2a11 w AT 461 Antenna 4 26 8 C 1 07 r WH 5 102 Cabin Control Ryan 3M WX 11 Processor and rrount CDU Antenna King KAS 297B Altitude Selector Kffi 331 Rate Gyro KC 296 Yaw Coupl er KS 271A Servo and rrount Shadin Digiflo Fuel FlCM Indicat or Ryan 3M Installation Cable s Upper rear avionics shel f Misc Installation Hardware King KEA 1...

Page 229: ... I 1 ___ _ ...

Page 230: ...EIGN CERTIFICATED MECHAN IC 5605 Portage Road X CERTIFICATED ll PAlll STATION CRS 3240 Kal amazoo MI 49002 MANUfACTUllfll D I certify that the repair and or alteration made to the unit s identified in item 4 aboye and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U S Federal Aviation Regulation and that the information furnished...

Page 231: ...fran 063 Alclad 2024 T3 aluminum Br acket mounted to structure above baggage ccrnpa rtrrent Power supplied through anp circuit breaker mounted in the lefthand breaker panel System installed according to procedures specified in Texas InstrurrEnt s manual 2788127 0002 FAA AC 90 45A appendix A paragraph 26 FAA AC 43 13 lA chapter 15 sections 1 6 and FAA AC 43 13 2A chapter 1 paragraphs 1 2 chapter 2 ...

Page 232: ...aircraft consisting of the following WX 11 Processor Control Display Unit Mounting Tray Antenna p n 78 8047 0958 8 p n 78 8047 0966 1 p n 78 8041 7628 3 p n 78 8041 7950 1 The coo was mounted in the lower lefthand side of the instrument panel The processor was mounted on the upper rear avionics shelf The antenna was belly nounted aft of the entrance door Installation caaplies with Ryan 31VrinSta L...

Page 233: ... _ J _ __ J r ...

Page 234: ... to Shadin manual 4067 and STC 824GL 7 Removed existing Alt ineter and replaced with King Radio Corporation KFA 130A Enccx ling Altilreter 8 Removed existing Vertical Speed Indicator and replaced with IVS s 9 Aircraft weight and balance revised and entered into the log book 10 Electrical load analysis perfomed to ensure adequate power capabilities 11 FAA approved Flight Manual Supplements for the ...

Page 235: ...ad rear baggage compartment first Without aft baggage fuel load may be limited by forward envelope for some combinations of optional equipment c 3 Occupants 2 in front I in rear Baggage in nose may be limited by forward envelope d 4 Occupants 2 in front 2 in rear Fuel may be limited for some combinations of optional equipment e 5 Occupants 2 in front I in middle 2 in rear Investigation is required...

Page 236: ...ment of all items to be loaded to the basic empty weight moment d Divide the total moment by the total weight to determine the C G location e By using the figures of item a and item d above locate a point on the C G range and weight graph Figure 6 1 5 If the point falls within the C G envelope thl loading meets the weight and balance requirements f Add the fuel allowance 18 lbs for engine start ta...

Page 237: ...t of this sample loading problem is at 146 43 inches aft of the datum line Locate this point 146 43 on the C G range and weight graph Figure6 15 Since this point falls with in the weight C G envelope this loadin g meets the weight and balance requirements Takeoff Weight 4100 146 43 600364 Minus Estimated Fuel Burn off climb cruise 6 0 Lbs Gal 350 150 31 52609 Landing Weight 3750 146 07 547755 Loca...

Page 238: ... problem is at inches aft of the datum line Locate this point on the C G range and weight graph Figure 6 15 If this point falls within the weight C G envelope this loading meets the weight and balance require ments Takeoff Weight Minus Estimated Fuel Burn off climb cruise 6 0 Lbs Gal 150 31 Landing Weight Locate the center of gravity of the landing weight on the C G range and weight graph Figure 6...

Page 239: ...PIPER AIRCRAFT CORPORATION PA 46 310P MALIBU SECTION 6 WEIGHT AND BALANCE 0 ID g u 0 0 ID SONnOd l HE 13M 0 101 LOADING GRAPH Figure 6 13 ISSUED JANUARY 11 1984 0 2 g 0 0 0 0 N REPORT VB 1200 6 13 ...

Page 240: ...L S a 0 a 2800 2600 J g 2400 i Q II 2200 130 C G RANGE WEIGHT F S 143 3 I I I I I I I I I I I I I I 4100 LBS MAX GROSS WT 1 11 F S 136 1 I I I I 3680 LBS J J I I I J I I 132 134 136 138 140 142 144 C G LOCATION INCHES AFT DATUM C G RANCa AND WEIGHT GRAPH hg un 6 15 _ t _ _ II t 146 148 REPORT VB 1200 6 14 ISSUED JANUARY 11 1984 ...

Page 241: ...ther than on the seats or in the baggage compartments Brief instructions are given on the plotter itself To use it first plot a point on the grid to locate the basic weight and C G location This can be put on more or less permanently because it will not change until the airplane is modified Next position the zero weight end of any one of the loading slots over this point Using a pencil draw a line...

Page 242: ... 2 Slide the slotted plastic into position so that the dot is under the slot for the forward scats at zero weight 3 Draw a line up the slot to the 340 pound position 170 170 and put a dot 4 Move the slotted plastic again to getthe zero end ofthe rear seat slot over this dot 5 Draw a line up this slot to the 340 pound position 170 170 and place the third dot 6 Continue moving the plastic and plotti...

Page 243: ... 3900 LBS MAX LANDING _ MAX ZERO FUEL WEIGHT WEIGHT vs CG ENVELOPE 138 130 132 134 136 138 140 142 144 146 148 150 C G LOCATION INCHES AFT DATUM SAMPLE PROBLEM Figure 6 17 ISSUED JANUARY 11 1984 146 147 3000 ui ID _J I l Q 2800 w 3 I u l a V 2600 a 2400 2200 REPORT VB 1200 6 17 ...

Page 244: ...OCATION 2 ZERO DESIRED LOADING SLOT OVER THE BASIC EMPTY WEIGHT POINT ESTABLISH A NEW POINT AT TkE WEIGHT CORRESPONDING TO THE LOADING SELECTED 3 CONTINUE TO SELECT AND PLOT LOADINGS DESIRED UNLESS A SLOT LEAVES THE WEIGHT VS C G ENVELOPE ANY POINT OF EXIT INDICATES MAXIMUM ALLOWABLE FOR THE LOADING SELECTED 144 146 147 PA461 3 I I I I I I I I I CG LOCATIO INCHES DATUM WEIGHT AND BALANCE PLOTTER 1...

Page 245: ...G ON HORIZONTALLY ADJUSTABLE SEATS POSITIONED FOR AVERAGE OCCUPANT NUMBERS IN PARENTHESES INDI CATE FORWARD AND AFT LIMITS OF OCCUPANT C G 3 C G OF CENTER OCCUPANTS 4 C G OF REAR OCCUPANTS 5 CENTROID OF REAR BAGGAGE AREA I I w a u 79 00 T I w z Q a 100 00 T 1 00 88 60 135 50 5TH NOTCH 130 90 139 00 D ci 21 75 c I 1 t r J _ ID Cl I w a Q ci __ _ __ j 7 ...

Page 246: ... 2 Air Induction System 7 6 Engine Controls 7 7 Hydraulic System 7 9 Landing Gear 7 9 Brake System 7 14 Flight Control System 7 14 Fuel System 7 15 Electrical System 7 20 Instrument Panel 7 26 Pilot Static System 7 30 Environmental System 7 32 Bleed Air Conditioning Pressurization System 7 34 Vacuum System Standard 7 37 Cabin Features 7 41 Baggage Area 7 43 Finish 7 43 Stall Wanting 7 43 Emergency...

Page 247: ... o ...

Page 248: ...ction There arc three basic fuselage sections the forward baggage section the pressurized cabin section and the tail cone section The cabin section is sealed to maintain pressurization The seating arrangement includes two crew seats and four passenger seats The forward passenger seats face aft and all passenger seats have adjustable backs with built in headrests An inside baggage area is provided ...

Page 249: ...he all metal ailerons are mass balanced and operated by a cable system mounted on the aft wing spar The empennage is of conventional fin and rudder stabilizer and elevator design with aerodynamic and mass balanced control surfaces Surfaces are ofall metal construction and the single pieceelevator assembly V carries a center mounted trim tab This tab operates to combine anti servo and trim function...

Page 250: ...sed Pressure increases air density making a greater mass of air available to d1e engine cylinders on each intake stroke Air then flows through an aftercoole here air temperature is reduced further increasing the density of air avml able to each cylinder Downstream the aftercoolers air flow joins at the y junction of intake tubes on the top front of the engine then passes the throttle butterfly val...

Page 251: ...RBOCHARGER 5 EXHAUST 6 WASTE GATE 7 CROSSOVER TUBE PIPER AIRCRAFT CORPORATION PA 46 JIOP MAUBll 8 INJECTOR 9 NOZZLE 10 MANIFOLD PRESSURE 11 THROTILE 12 DECK PRESSURE 13 PRESSURE RELIEF VALVE 14 SONIC NOZZLES TURBO INDUCTION SYSTEM Figure 7 1 REPORT VB 1200 7 4 ISSUED JANUARY II 1984 ...

Page 252: ...ivides metered fuel flow equally between the six nozzles in the system The nozzles continuously I spray and atomize metered fuel into the intake valve port of the engine cylinder head Fuel is supplied to the engine driven pump at a greater rate than required The excess is returned to the wing tank selected To assist engine starting an injection primer button can be found to the right of the starte...

Page 253: ...interaction of these and other forces to maintain a constant RPM is provided by the propeller control lever in the cockpit The propeller control lever linked by cable to the propeller governor detennines a wide range of in flight RPM Governor range is more limited u during ground operation Pushing the lever forward selects increased or V higher RPM Pulling the lever aft selects decreased or lower ...

Page 254: ... AffiCRAFT CORPORATION PA 46 310P MALIBU 0 i 1 f t J l T T r t X I M E i i l IIOOUCYIOQ It tt T I U II ALfOUl l CONTROL PEDESTAL Figure 7 3 ISSUED JANUARY 11 1984 SECTION7 DESCR OPERATION REPORT VB 1200 7 7 ...

Page 255: ... of manifold pressure when operating with a combination of high altitude and low RPM where the turbocharger wastegate is closed Loss of manifold pressure of up to 8 inches Hg can result at maximum continious power with a possible greater reduction resulting at cruise power settings Some of this manifold pressure loss may be recovered with tJuottle and I or RPM adjusunent V 7 7 ENGINE CONTROLS The ...

Page 256: ... 46 8408001 through 46 8508109 using an electrically driven hydraulic pump operating at 1425 1575 psi On aircraft with serial numbers 46 8508036 46 8508040 and up the hydraulic pump assembly includes an accumulator with a nitrogen gas charge of 1200 psi The accumulator incorporates a valve for V servicing on the gas end CAUTION Serial numbers 46 8408001 through 46 8608046 unless Piper Kit No 765 1...

Page 257: ...ween the ammeter and the flap indicator on aircraft with serial numbers 46 8408001 Uuough 46 8508109 The hydraulic pump is located aft of the baggage compartment and is accessible through the baggage compartment aft closeout panel The pump has the fluid reservoir V which is transparent for ease of checking fluid level as an integral part of the unit The landing gear selector is a mechanically actu...

Page 258: ...EAR ACTUATOR FLAP SELECTOR CONTROL FLAP SELECTOR VALVE FLAP ACTUATOR HYD PUMP PRESS PORT RETURN PORT ACCUMULATOR SERVICE VALVE JS I L __ Jl 1s1 Nnrn uPPOS1T ONl _ ________ __ _ 0 0 SECTIO 7 DESCR OPEH TIO SERIAL NUM8 RS I 46 8408001 THROUGH 46 8 8109 r F 3 _ 2 _ I SERIAL r uMBERS 46 8508036 46 8508040 tJ j uP 1 1 1 J 13 0 0 SERIAL NUMBERS 46 840 8001 THROUGH 46 8508109 HYDRAU IC SYSTEM ISSl ED JA ...

Page 259: ...SECTION 7 DESCR OPERATION PIPER AIRCRAFT CORPORATION PA 46 JIOP MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1200 7 tOb ISSUED JANUARY 11 1984 REVISED MAY 8 1986 u ...

Page 260: ... sure that the landing gear selector is in the DOWN position and that the three green gear indicator lights are illuminated On takeoff the gear should be retracted before an airspeed of 130 KIAS is exceeded The landing gear may be lowered at any speed up to 170 KIAS The nose gear retracts aft turning 90 sideways and is fully enclosed by doors A nose gear door actuating cylinder is located in the n...

Page 261: ...being used for training purposes or a pilot check out flight and the emergency gear extension knob has been pulled out it may be pushed in again when desired if there has not been any apparent malfunction of the landing gear system FUEL SELECTOR O F F L LNR I g R T E T EMERGENCYGEARFXTENSIDN PULL TORELEASE SFF AFM c EFORE RE ElloGAGfl wlENT e LANDING GEAR SELECTOR Figure 7 7 The hydraulic reservoi...

Page 262: ... DET HEAT R LAY GEAR HORN PRESSURE SWITCH THROTTLE SWITCH FLAP SWITCH GEAR SHOWN DOWN AND LOCKED RIGHT MAIN UP SWITCH SECTION 7 DESCR OPERATION NOSE UPSW EMERGENCY BUS LEFT MAIN UP SWITCH LAHDING GEAR WARNING LANDING GEAR ELECTRICAL DIAGRAM Figure 7 9 ISSUED JANUARY 11 1984 REPORT VB 1200 7 13 ...

Page 263: ...t access panel in the forward baggage compartment Brake fluid should be maintained at the level marked on the reservoir For further information see Brake Service in Section 8 of this handbook The parking brake knob is located just below the left control column To set the parking brake first depress and hold the toe brake pedals and then pull the parking brake knob To release the parking brake firs...

Page 264: ...nsion is limited to airspeeds below 120 KIAS On aircraft sn 46 8608001 and up the flaps are electrically operated Flap positions airspeeds and operation have not changed from those indicated in the above paragraph Inaddition a FLAPS annunciator light is provided as part oftheannunciator panel located in the upper portion ofthe pilots instrument panel If the annunciator light illuminates it is indi...

Page 265: ...Each tank separately vents air in and fumes out to equalize pressure with ambient conditions This is accomplished through combination valves in non icing fuel tank vents located at the most outboard forward tank access panels NOTE When opening the fuel tank filler cap a rush of air will normally be heard and felt This is caused by the large volume of vapor space in the wing tank which is under a s...

Page 266: ...ng 2 speed selections available through a switch on the instrument panel LOW speed is intended for vapor suppression at altitude and may be used during normal engine operation both on the ground and in flight Unstable engine operation or fluctuating fuel flow indications are signs of vapor in the fuel lines The HIGH pump speed selection on the instrument panel should be used only in the event of e...

Page 267: ...E AND FLOW GAUGE VAPOR RflUJIN UNI PIPER AIRCRAFT CORPORATION PA 46 310P MALIBU FIJEL QIJANTIJY GAUSE SAUSE Alll lllZZUS VDITDI Til D CK PRISSllil run lllZZL lWCIOLD YA1Y Ft EL SYSTEM SCHEMATIC Figure 7 11 REPORT VB 1200 7 18 ISSl ED JANllARY 11 1984 u u ...

Page 268: ...e baggage floor on the right side The filter drain is a nylon tube located on the right side of the aircraft forward ofthe wing To drain fuel simply push in the nylon tube If contaminants clog the filter an internal relief valve will allow fuel to bypass the filter This will allow unfiltered fuel to reach the engine and could contaminate the fuel distribution system in the engine NOTE Regular serv...

Page 269: ... is one gallon each side Fuel quantity gauges are calibrated to indicate usable fuel 7 19 ELECTRICAL SYSTEM The standard electrical power system refer to Figure 7 13 is 28 V D C negative ground single main bus with a 15 5 amp hr lead acid battery located in the lower left area of the forward baggage compartment beneath the floor The manifold type battery is vented with an acid recovery system prov...

Page 270: ... H 1 N 48 809CM9 911d Up 2 NAY T SIN 48 II08048 911d Up J 1 N 41 1801001 alld Up I I SECTION 7 DESCR OPERATION lMiRGlNCY BUS PANO UO fllltQ PlfOT NIAi ANDINO GUii l OIITION UIIINfl tUIIIIIIIIICIATOII l AIIIIL COMM I NAY 118 Note Tl IPIAlllll AUOOO AMI ANDINO LIGHT PIUITI TUIIN COOtlOINATOII IITAU WAIINIIIO lfAIIDft VACUUM PUMP DIERGEHCY BVS SWITCH TI TO RADIO EMEAGElfCl 8US MASTER RELAY AVIONICS I...

Page 271: ...S 4 CTION7 DESCR OPERATION PIPER AIRCRAFf CORPORATION PA 46 310P MALIBU THIS PAGE INTENTIONALLY LEFf BLANK REPORT VB 1200 7 22 ISSUED JANUARY 11 1984 V ...

Page 272: ...ONICIIUI COMllel _ TIIAllll OIIOIII AUDIOIM 11 A ICS LIGNTIIDtMMfll CONTl Dt AYIOIIICS COOUNO DMI PffCN 111M AUTOPII Of COMl MI IIADAII AlnMITIII SECTION7 DESCR OPERATION MAIN fMfAOl NCY IUS P UCUllGNTIIIQ lAN OIM P091110tC UOMrl _UltCIATOII PANIL co t NAV tl 11 P AUII AUDIO I AltD UGMT PILOr YUAN COOIIOINA1011 91AU WAIINIIIO AUtllNAl OllN I WINO lOIIIA DPIIIUHU 1 PffOf tCAT un OITtCTOII NU T IUII...

Page 273: ...or The optional electrical power system adds a Ford 60 amp alternator providing alternator paralleling The standard single alternator feeds its positive output to the single main power distribution bus via the shunt resistor and the 80 amp main bus current limiter The shunt resistor taps feed the ammeter therefore ammeter indications represent total system current now The optional electrical power...

Page 274: ...PIPER AIRCRAFT CORPORATION PA 46 310P MALIBU TYPICAL C 8 PANEL Figure 7 19 ISSUED JANUARY II 1984 SECTION 7 DESCR OPERATION REPORT VB 1200 7 25 ...

Page 275: ...ruments and the normally required power plant instruments The artificial horizon is vacuum operated and located in the center of the left instrument panel The vacuum gauge is located on the left V side of the pilot s instrument panel The directional gyro located in the center of the left instrument panel and the turn and bank indicator on the left side are electrically operated The heat defrost pr...

Page 276: ...rain valve located on the left side of the center console below and forward of the instrument panel normally above the pilot s right knee This allows any moisture which may have collected from condensation to be pulled into the engine This is accom plished by depressing the valve for 5 seconds while operating the engine at 1000 RPM NOTE Do not depress the valve when manifold pressure exceeds 25 in...

Page 277: ...RAFT CORPORATION PA 46 310P MALIBU en ii I I lel lell U II E e 0 i Ci e e I rnm I 1ft REPORT VB 1200 7 28 _ _ r m 1 id I IJ l co I l 1 O lf s z S I 1 11 77 N INSTRUMENT PANEL Figure 7 21 co ISSUED JANUARY 11 1984 REVISED APRIL 30 1984 V V ...

Page 278: ...ER 18 VERTICAL SPEED INDICATOR 19 RADAR ALTIMETER 20 FUEL GAUGE 21 RPM 22 MANIFOLD PRESSURE FUEL FLOW 23 T I T GAUGE SECTION 7 DESCR OPERATION 24 OIL PRESSURE OIL TEMP CYLINDER HEAD TEMP 25 COMPASS 26 AVIONICS SWITCHES 27 AVIONICS INSTALLATION 28 RADAR 29 COPILOT S INSTRUMENTS 30 HOBBS METER 31 DEICE PANEL 32 FLAP SELECTOR 33 FLAP INDICATOR 34 HYDRAULIC PRESS GAUGE 35 VOLT AMMETER 36 GEAR HANDLE 3...

Page 279: ...atic source is selected the airspeed and altimeter and vertical speed indicator are vented to the alternate static pad on the bottom aft fuse lage During alternate static source operation these instruments may give slightly different readings The pilot can determine the effects ofthe alternate static source on instrument readings by switching from standard to alternate sources at different airspee...

Page 280: ...z 8 w a m 0 0 f3 i a ffl CO ffi Ya a g u o t3z OQ 5 Yffiw wiS ia gc I w 0 w w c ffi c 5 I ozl ii tfic J c czo a a zY1 1 Y1 a i I 5ffi t gg Sg 0 i 1 O oo0a a 0a 1 d Nt ht in 1 1 r a O I 1 1 I I i I PITOT STATIC SYSTEM Figure 7 23 ISSUED JANUARY 11 1984 REVISED MARCH 20 1991 REPORT VH 1200 7 31 ...

Page 281: ... to be diverted to the windshield defrost outlet Separate and individual controls for the two footwarmcr outlets are also provided The outlets are located between the rudder pedals on each side of the cockpit The ventilation blowers supply V airflow to the portion of the side wall ducts containing the individual seat outlets eyeballs The cabin pressurization and control system consist of an outflo...

Page 282: ...TOFF VALVE 10 HEAT MUFF 11 FIRE WALL 12 PRESSURE BULKHEAD 13 CONDmONED AIR 14 OUTFLOW VALVE 15 SAFETY VALVE 16 RECIRCULATION BLOWERS OPTIONAL EVAPORATORS 17 EYEBALLS 6 18 DEFROSTER 19 FOOT WARMERS 20 FLOW RESTRICTOR 21 GROUND BLOWER 22 DEFROST CONTROL 23 FOOT WARMER CONTROL 24 CABIN TEMP CONTROL 25 CABIN PRESSURE CONTROL 23 26 CHECK VALVE ENVIRONMENTAL SYSTEM Figure 7 25 ISSUED JANUARY 11 1984 REV...

Page 283: ...alve and the ram airselector valve When fully in the fire wall shut off valve is open the bleed air dump valve is closed and the ram air selector valve is positioned to route ambient air across the bleed air heat exchanger When the control is fully out pull the fire wall shut off valve is closed the bleed air dump valve is open anci the ram air selector valve is posi tioned to route ambient air in...

Page 284: ...n the annunciator display warns the pilot when the cabin altitude is above I0 000 feet Cabin pressure is auto matically regulated to a maximum of5 5 psi pressure differential Should the cabin outflow valve malfunction the cabin safety valve will maintain a maximum of 5 6 cabin differential pressure The landing gear squat switch on the left main landing gear prevents the cabin from being pressurize...

Page 285: ...oo w 0 4000 z ii c 0 2000 0 PIPER AIRCRAFT CORPORATION PA 46 JlOP MALIBU v it I Q q o o I l t l t 0 6000 10 000 16 000 20 000 26 000 AIRPLANE ALTITUDE FT CABIN ALTITUDE VS AIRPLANE ALTITUDE Figure 7 29 REPORT VB 1200 7 36 ISSUED JANUARY 11 1984 ...

Page 286: ...filter dirty screens possibly a sticking vacuum regulator or a leak in the system Zero V gauge reading indicates either a sheared pump drive defect in pump possibly a defective gauge or a collapsed line In the event of any gauge variation from the norm the pilot should have a mechanic check the system to prevent possible damage to the system components or eventual failure of the system The vacuum ...

Page 287: ...d on the forward pressure bulkhead inside the cabin The vacuum in the system is regulated between 4 8 and 5 2 Iinches of mercury as shown on the vacuum gauge The standby vacuum pump is operated by the STANDBY VAC PUMP switch located on the main switch panel on the left side of the pilot s instrument panel For normal operations the standby pump is OFF and the right side red flow button will be visi...

Page 288: ...ALL 1tl PRESSURE IIUUOtEAD r J I I ___J___ I 5 6 I Ii_ AIRCRAFT I 1 VACUUM PUMP 2 VACUUM REGULATOR 3 VACUUM PRESSURE SWITCH 4 INLINE FILTER 5 CABIN PRESSURE CONTROLLER 6 VACUUM GAUGE 7 PILOT S ATTITUDE GYRO VACUUM SYSTEM STANDARD Figure 7 31 INSTRUMENT PANEL ISSUED JANUARY 11 1984 REPORT VB 1200 7 39 ...

Page 289: ...UTCH DRIVEN STANO BY PUMP 3 VACUUM REGULATOR 4 VACUUM MANIFOLD CHECK VALVE 5 VACUUM PRESSURE SWITCH 6 INLINE FILTER 7 CABIN PRESSURE CONTROLLER 8 VACUUM GAUGE 9 PILOT S ATTITUDE GYRO 10 COPILOT S AIR DRIVEN GYROS FIREWALL PRESSURE BULKHEAD INSTRUMENT PANEL i VACUUM SYSTEM WITH STAND BY PUMP Figure 7 33 REPORT VB 1200 7 40 ISSUED JANUARY 11 1984 ...

Page 290: ...el flood map u hts are provided forward and four passenger reading lights are provided aft A cabin entranceflood light is located above the door The four passenger seats with folding annrests and headrests are positioned in a club seating arrangement The center seats face aft The seat I ba ks recline by pushing a button mounted in the outboard armrest An optional conference table located between t...

Page 291: ...tors have been activated The light remains illuminated with the battery switch ON until the system is serviced An optional fire extinguisher is available and if installed is located either behind the spar or on top of the right cabinet The emergency exit is located on the right side of the fuselage adjacent to the aft facing seat Instructions for opening the emergency exit are placarded on the cov...

Page 292: ... the airplane s C G falls within the allowable C G range refer to Section 6 Weight and Balance All exterior surfaces are primed and finished with polyurethane To keep the finish attr ctive looking polyurethane touch up paint is available from Piper Dealers 7 37 STALL WARNING An approaching stal is indicated by a stall warning horn which is activated between five and ten knots above stall speed Mil...

Page 293: ... nearest FAA tower or flight service station NARCO ELT IO OPERATION On the ELT unit itself is a three position switch placarded ON OFF and ARM The ARM position sets the ELT so that it will transmit after impact and will continue to transmit until its battery is drained The ARM position is selected when the ELT is installed in the airplane and it should remain in that position To use the ELTas a po...

Page 294: ...return the switch to ARM Recheck with the receiver to ascertain the transmitter is silent 7 41 EXTERNAL POWER An optional external power receptacle allows the airplane engine to be started from an external battery without the necessity of gaining access to the airplane battery The cable from the external battery can be attached to a receptacle located on the aft side of the forward baggage compart...

Page 295: ...n effects of radar can cause serious damage to the eyes and tender organs of the body Personnel should not be allowed within fifteen feet of the area being scanned by the antenna while the system is transmitting Do not operate the radar during refueling or in the vicinity of trucks or containers accommodating explosives or flammables Flashbulbs can be exploded by radar energy Before operating the ...

Page 296: ...ce 8 3 Airplane Alterations 8 3 Ground Handling 8 4 Engine Induction Air Filter 8 7 Brake Service 8 7 Hydraulic System Service 8 9 Landing Gear Service 8 9 Propeller Service 8 10 Oil Requirements 8 11 Fuel System 8 J2 Tire Inflation 8 16 Battery Service 8 16 Emergency Oxygen System Optional 8 16 Pressurization System 8 16 Lubrication 8 17 Cleaning 8 17 Cleaning and Maintenance of ReliefTube System...

Page 297: ...u THIS PAGE INTENTIONALLY LEFT BLANK u I REPORT VB 1200 8 ii REVISED OCTOBER 15 1997 ...

Page 298: ...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 PIPER approved STC installations may change systems interface operating characteristics and component loads or stresses on adjacent structures PIPER provided inspection criteria may not be valid for a...

Page 299: ...ent 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 service histories which are unknown or cannot be authenticated may have been subjected to unacceptable stresses or temperatures or may have other hidden damage not discernible through routine visual o...

Page 300: ...s may apply This information is provided to all authorized Piper Service Centers Service Letters deal with product improvements and servicing techniques pertaining to the airplane They are sent to Piper Service Centers and if I necessary to the latest FAA registered owners in the U S Owners should give careful attention to Service Letter information Service Spares Letters offer improved parts kits...

Page 301: ... Manual and should be complied with by a properly trained knowledgeable and qualified mechanic at a Piper authorized Service Center or a reputable repair shop Piper Aircraft Corporation cannot accept responsibility for the continued airworthiness of any aircraft not maintained to these standards and or not hr ought into compliance with applicable Service Bulletins issued by Piper Aircraft Corporat...

Page 302: ...r aircraft maintenance must be accomplished by a person or facility appropriately certificated by the Federal Aviation Administration FAA to perform that work Anytime maintenance is accomplished an entry must be made in the appropriate aircraft maintenance records The entty shall include a The date the work was accomplished b Description of the work c Number of hours on the aircraft d The certific...

Page 303: ...ilable upon request Logbooks should be complete and up to date Good records will reduce maintenance cost by giving the mechanic information about what has or has not been accomplished 8 9 GROUND HANDLING a Towing The airplane may be moved on the ground by the use of the nose wheel steering bar that is stowed in the forward baggage compartment or by power equipment that will not damage or excessive...

Page 304: ...ectiveness of the stee ring 4 Observe wing clearance when taxiing near buildings or other stationary objects If possible station an observer outside the irplane 5 When taxiing over uneven ground avoid holes and ruts 6 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 c Park...

Page 305: ...d for the proper mooring of the airplane I Head the airplane into the wind if possible 2 Retract the flaps 3 Immobilize the ailerons and elevator by looping the seat belt through the control wheel and pulling it snug 4 Block the wheels 5 Secure tie down ropes to the main gear assemblies and to the tail ring at approximately 45 degree angles to the ground When using rope of non synthetic material l...

Page 306: ...re should be kept on hand for use as a rapid replacement To clean the filter I Tap filter gently to remove dirt particles Do not use compressed air or cleaning solvents 2 Inspect filter If paper element is torn or ruptured or gasket is damaged the filter should be replaced The usable life of the filter should be restricted to one year or 500 hours whichever comes first 3 After cleaning check all c...

Page 307: ...SECTION 8 HAND SERV MAINT PIPER AIRCRAFT CORPORATION PA 46 310P MALIBU I REPORT VB 1200 8 8 BRAKE SYSTEM Figure 8 1 ISSUED JANUARY II 1984 ...

Page 308: ...0 x 6 wheels with 6 00 x 6 eight ply rating tires and tubes The nose wheel uses a McCauley or a Cleveland Aircraft Products 5 00 x 5 wheel with a 5 00 x 5 six ply rating type III tire and tube Refer to paragraph 8 25 Wheels are removed by taking off the hub cap cotter pin axle nut and the two bolts holding the brake segment in place Mark tire and wheel for reinstallation then dismount by deflating...

Page 309: ... the fore and aft axis of the plane when the rudder pedals are centered Alignment of the nose wheel can be checked by pushing the airplane back and forth with the rudder two degrees to the right to determine that the plane follows a straight line The turning arc of the nose wheel is 30 1 in either direction and is limited by stops at the trunnion forging or the forward steering contact arm mounted...

Page 310: ...that oil be added if the quantity falls to 7 quarts It is recommended that engine oil be drained and renewed every I00 hours or sooner under unfavorable conditions Full flow cartridge type oil filters should be replaced each 50 hours of operation Teledyne Continental recommends that only the larger approximately 5 8 inch high full flow oil filter be used on the TSI0520BE engine The following grade...

Page 311: ...com mended Fuel and Oil Grades A summary of the current grades as well as the previous fuel designation is shown in the following chart FUEL GRADE COMPARISON CHART Current Military Previous Commercial Current Commercial Fuel Grades MIL G 5572E Fuel Grades ASTM 0910 Fuel Grades ASTM 0910 75 Amendment No 3 Max TEL Max TEL Max TEL Grade Color mVU S Gal Grade Color mVU S Gal Grade Color ml U S Gal 80 ...

Page 312: ...NS 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 concentrated additive to come in contact with the aircraft painted surfaces or the interior surfaces of the fuel tanks Some fuels have anti icing additives pre blended in the fuel at the refinery so no further blending should be performed Fuel ad...

Page 313: ... selector on left or right tank before draining The fuel collector sump tanks located at the root of each wing are the lowest points in the system Each tank drain is accessible through a hole in the bottom wing skin adjacent to the wheel well The fuel filter drain is located on the right hand side of the fuselage several feet forward of the wing Sumps and filter should be drained until sufficient ...

Page 314: ... drain valves and twist Y a turn to lock open Remaining fuel may be drained through the filter drain Close sump drain valves before refueling CAUTION Whenever the fuel system is completely drained and fuel is replenished it will be necessary to run the engine for a minimum of three minutes at IOOO RPM on each tank to insure that no air exists in the fuel supply lines ISSUED JANUARY 11 1984 REPORT ...

Page 315: ...T fill the battery above the baffle plates DO NOT fill the battery with acid use water only A hydrometer check will determine the percent of charge in the battery Inspect overflow sump for presence of battery fluid Fluid in the sump is not a normal condition and indicates either a battery or charging system problem If fluid is present the electrical system must be serviced to eliminate cause and t...

Page 316: ...sh areas that were sprayed CAUTION Do not spray solvent into the alternator vacuum pump starter or air intakes 3 Allow the solvent to remain on the engine from five to ten minutes Then rinse the engine clean with additional solvent and al1ow it to dry CAUTION Do not operate the engine until excess solvent has evaporated or otherwise been removed 4 Lubricate the controls bearing surfaces etc in acc...

Page 317: ...ap and water Harsh abrasives or alkaline soaps or detergents could make scratches on painted or plastic surfaces or could cause corrosion of metal Cover areas where cleaning solutions could cause I damage To wash the airplane use the following procedure CAUTION Do not direct any stream of water or cleaning solutions at the openings in the pilot head static ports alternate static ports or fuselage ...

Page 318: ...t of hard polishing wax Rub lightly with a soft cloth Do not use a circular motion 5 A minor scratch or mar in plastic can be removed by rubbing out the scratch with jeweler s rouge Smooth both sides and apply wax Deep scratches may lead to failure when pressurized 6 Ifa deep scratch or crack is found in any ofthe windshields or windows do not pressurize cabin until serviced at authorized repair s...

Page 319: ... saddle soap or a mild hand soap and water f Cleaning Carpets To clean carpets first remove loose dirt with a whisk broom or vacuum For soiled spots and stubborn stains use a noninflammable dry cleaning fluid Floor carpets may be cleaned like any household carpet g Cleaning Oxygen Equipment I Clean the mask assemblies with a suitable oil free disinfectant 2 Wipe dirt and foreign particles from the...

Page 320: ...eaner does not have time to soak into the rubber Petroleum products such as these are injurious to rubber and therefore should be used sparingly if at all With the deicer boots properly cleaned a coating of Agemaster No I should be applied as described in the PA 46 3 IOP Service Manual This treatment helps protect the boot rubber from ozone attack aging and weathering After the Agemaster coating i...

Page 321: ...r even one day a Interior After each use of the relief tube the area surrounding the relief tube should be examined for spillage and cleaned according to the cleaning procedures listed in paragraphs 8 35 e and t above Clean area inside the box and access door funnel and tube using mild soap and water After cleaning assure that no soapy residue remains by flushing with clean water Dry system thorou...

Page 322: ... relief tube system has been used Cleaning should occur in accordance with paragraph 8 35 c with the following exception After completion of washing a solution of baking soda I0 and water should be applied to the entire area and allowed lo remain for a few minutes The area then must he thoroughly rinsed with clean water The area should be thoroughly dried and ohserved for paint chips and corrosion...

Page 323: ...SECTIONS HAND SERV MAINT PIPER AIRCRAFT CORPORATION PA 46 JlOP MALIBU THIS PAGE INTENTIONALLY LEFf BLANK REPORT VB 1200 8 24 REVISED OCTOBER 15 1997 ...

Page 324: ...r Radar System 6 Pages 9 55 Emergency Oxygen 6 Pages 9 61 Air Conditioning System 4 Pages 9 67 3M Ryan Stomscope WX IOA 6 Pages 9 71 Prop Heat Heated Windshield Panel and Wing Ice Detection Light 6 Pages 9 77 TI 9100 Loran C Navigator With KAP KFC 150 Autopilot System 6 Pages 9 83 Ice Protection System 16 Pages 9 87 Hydraulic Pump Annunciator Light 4 Pages 9 103 3M Ryan Stonnscope WX 11 6 Pages 9 ...

Page 325: ...as the FAA Approved Operational Supplement to the Bendix King 150 Series Flight Control System as installed per STC SA1778CE D Effective this revision Bendix King will be responsible to supply and revise the operational supplement It is permitted to include the Bendix King supplement in this location of the Pilots I Operating Handbook unless otherwise stated by Bendix King pages 9 4 through 9 28 D...

Page 326: ...u PAGES 94 TI IROUGH 9 28 IN1ENTIONALLY DELETED U u ...

Page 327: ...TION 4 NORMAL PROCEDURES a PREFLIGHT PERFORM PRIOR TO EACH FLIGHT Alt Loss 480 ft 80 ft 80 ft 1 GYROS Allow 3 4 minutes for gyros to come up to speed 2 RADIO POWER AVIONICS MASTER ON 3 PREFLIGHT TEST BUTTON PRESS momentarily and NOTE a All annunciator lights on TRIM annunciator flashing b When equipped with KAS 297B all legends and digits are displayed on the KAS 297B c After approximately 5 secon...

Page 328: ...e up direction after approximately four seconds Depress and hold control wheel steering switch CWS and verify that autotrim stops then release vertical trim and CWS switches Use the vertical trim switch on the Mode Controller to command a pitch DN Observe that the autotrim runs in the nose down direction after approximately four seconds Release Mode Controller vertical trim switch and control whee...

Page 329: ...mation contained in this manual is FAA Approved material which along with the FAA Approved Airplane Flight Manual placards and instrument 11arkings is applicable to the operation of the airplane when modified by the installation of the King 150 Series Automatic Flight Control System as per STC SA1778CE D Revision 4 FAA Appcoved 11 RALPH V COLE DAS Coordinator Ki ng Radio Corporation DAS4CE Date Oc...

Page 330: ...ation aection froa front of aanual to baclc of aanual Entire aanual reforaatted KAS 297B Altitude Vertical Speed Selector suppleaent incorporated into thi aanual Added limitations r G H J and L Liaitations I and K added with inclusion of altitude vertical P d selector operation to aanual neviaed entire Eaergency Procedure section Chan9ed Caution not to Warning Added warnin9 Turbulerice note added ...

Page 331: ...G PIPER MODELS PA 46 310P AND PA 46 350P FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT TABLE OF CONTENTS General Limitations Emergency Procedures Normal Procedures Performance System Description and Operation i PAGE 1 3 4 7 21 22 006 0428 01 ...

Page 332: ...a KFC 150 or a KAP 150 Flight Control System provides the pilot with the following features ability to select vertical speed hold ability to select arm and upon approaching the selected altitude automatically transfer into Altitude Bold altitude alerting as specified by F A R 91 51 The 150 Series AFCS has an electric pitch trim system which provides autotrim during autopilot operation and manual e...

Page 333: ...used to protect the following elements of the King 150 Series Autopilot LABEL AUTOPILOT PITCH TRIM COMPASS FUNCTION Supplies power to the KC 192 or the KC 191 Computer the autopilot pitch and roll servos the optional KA 185 Annunciator and the Pitch Trim Circuit Breaker It also applies power to the KC 296 Yaw Computer the Yaw Servo and the KAS 2978 Altitude Vertical Speed Selector when installed S...

Page 334: ...system is prohibited prior to completion of these tests 8 The PITCH TRIM circuit breaker must be pulled following any inflight illumination of the red TRIM warning light but only after first completing the Emergency Procedures Section 3 paragraph A The manual electric trim and autopilot autotrim systems will be disabled with the PITCH TRIM circuit breaker pulled I Altitude Select captures below 80...

Page 335: ...DIO KASTR SVITCH HAY BE USED AS AN ALTERNATE MEANS OF REMOVING ALL POVER FROM THE AUTOPILOT AND ELECTRIC TRIM SYSTEMS IF NECESSARY PERFORM STEPS 1 THROUGH 3 ABOVE THEN TURN THE _ I RADIO HASTll SVITCH OFF BEFORE LOCATING AND PULLING THE AUTOPILOT AND PITCH TRIM CIRCUIT BREAKERS TURN THE RADIO KASTR SVITCH ON AS SOON AS POSSIBLE TO RESTORE POVER TO ALL OTHER AVIONICS EQUIPMENT PRIMARY ATTITUDE AIRS...

Page 336: ...utopilot or autopilot trim malfunction or to an automatic disconnect of the autopilot is in maintaining control of the airplane Immediately grasp the control wheel and press and hold down the A P DISC TRIM INTER switch throughout the recovery Manipulate the controls as required to safely maintain operation of the airplane within all of its operating limitations Elevator trim should be used as need...

Page 337: ...ents will remain operational however communications navigation and identification equipment will be inoperable VARNING k DO NOT ATIEMPT TO RE ENGAGE THE AUTOPILOT OR TO USE THE MANUAL ELECTRIC TRIM SYSTEM POLLOVING A MANUAL ELECTRIC TRIH MALFUNCTION UNTIL CORRECTIVE SERVICE ACTION HAS BEEN PERFORMED ON THE SYSTEM 3 Note that the emergency procedure for any malfunction is essentially the same immed...

Page 338: ...RIM DID NOT PASS PREFLIGHT TBST TBB AtrrOPILOT CIRCUIT BRBAKBR HUST BB PULLED MANUAL ELECTRIC TRIM CAN NOT BB USED 4 MANUAL ELECTRIC TRIM TEST as follows a Actuate left side of split switch unit to the fore and aft positions The trim wheel should not move on its ovn b Actuate right side of split switch unit to the fore and aft positions Trim wheel should not move on its own and normal trim wheel f...

Page 339: ... PRESS Verify that the autopilot and yaw damper disconnects and all flight director modes are canceled 10 TRIM SET to take off position manually B AUTOPILOT OPERATION VARNING TBB PILOT IN COHKAND HUST CONTINUOUSLY MONITOR THB AUTOPILOT VIIBN IT IS ENGAGED AND BE PREPARED TO DISCONNBcr TBB AUTOPILOT AND TAKE IMMEDIATE CORRBClIVB AcrION INCLUDING MANUAL CONTROL OF THE AIRPLANE AND OR PERFORMANCE OF ...

Page 340: ...ATES THE CONTROL VBBEL MANUALLY VBILE THE AUTOPILOT IS ENGAGED 3 Climb or Descent a Using CVS 1 CVS Button PRESS and HOVE aircraft nose to the desired attitude 2 CVS Button RELEASE Autopilot will maintain aircraft pitch attitude up to the pitch limits of 15 or 10 b Using Vertical Trim 1 VERTICAL TRIK Control PRESS either up or down to modify aircraft attitude at a rate of 7 deg sec up to the pitch...

Page 341: ...ly begin b Vhen equipped with DGR 1 OBS Knob SELECT desired course 2 NAV Mode Selector Button PRESS 3 Heading Selector Knob ROTATB BUG to agree with OBS course NOTE VHEN NAV IS SELECTED THE LATERAL OPERATING MODE VILL CHANGE FROM HDG IF SELECTED TO VINGS LEVEL FOR 5 SECONDS A 450 INTERCEPT ANGLE VILL THEN BE AUTOMATICALLY ESTABLISHED BASED ON THE POSITION OF THE BUG a If the D Bar is greater than ...

Page 342: ...e Deviation Bar is greater than 2 to 3 dots the aircraft will continue in BOG mode or wings level if BOG not selected with the APR annunciator flashing when the computed capture point is reached the BOG mode 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 HOG mode will disengage...

Page 343: ... 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 HOG mode will disengage upon selecting APR mode the APR annunciator will illuminate steady and the capture track sequence will automatically begin 8 BC Approach Coupling a Vhen equipped with HSI 1 Course Bearing Pointer SET to the ILS front course inbound heading NOTE V...

Page 344: ...equipped with DG 1 OBS Knob SBLBCT the ILS front course inbound heading 2 BC Mode Selector Button PRESS 3 Beading Selector Knob ROTATE Bug to the ILS front course inbound heading NOTE VHEN BC IS SELECTED THE LATERAL OPERATING MODE VILL CHANGE FROM BDG IF SELECTED TO VINGS LEVEL FOR 5 SECONDS A 45 INTERCEPT ANGLE VILL THEN BE ESTABLISHED BASED ON THE POSITION OF THE BUG FAA Approved Revision 4 a If...

Page 345: ...R Mode ENGAGED b At glideslope centering HOTB GS annunciator ON NOTE AUTOPILOT CAN CAPTURE GLIDESLOPE FROM ABOVE OR BELOV THE BEAM VRILE OPERATING IN EITHER PITCH ATTITUDE HOLD OR ALT BOLD HODES I 10 Missed Approach a A P DISC TRIM INTER Switch PRESS to disengage AP and YD b HISSED APPROACH EXECUTE c CVS Button PRESS KFC 150 only as desired to activate FD mode during go around maneuver d AP ENG Bu...

Page 346: ...is not engaged and the pilot must maneuver the aircraft to satisfy the flight director commands D YAV DAMPER OPERATION 1 Vith Yaw Damper Switch Installed a Before Take off 1 A P DISC TRIM INTER Switch Press to disengage AP and YD b Yaw Damper Engagement 1 YD Switch PRESS Note YD Annunciator on NOTE YAV DAMPER ENGAGEMENT VILL OCCUR AUTOMATICALLY VITH AUTOPILOT ENGAGEMENT THE YAV DAMPER HAY BE DISEN...

Page 347: ... Only Press 2 AP ENG Button Press Note AP and YD annunciators on NOTE FOR YAV DAMPER OPERATION VITBOUT THE AUTOPILOT DISENGAGE THE AUTOPILOT BY PRESSING THE AP ENG BUTTON OR MANUAL ELECTRIC TRIH CONTROL SVITCBES c Before Landing 1 A P DISC TRIM INTER Switch PRESS to 1 disengage AP and YD Piper Models PA 46 310P and PA 46 350P Airplane Flight Manual Supplement 006 0428 01 Page 18 of 39 FAA Approved...

Page 348: ...sired vertical speed is displayed c VERTICAL SPEED MODE ENG button PUSH to engage the Vertical Speed Bold mode 2 Changing Vertical Speed a Using CVS 1 CVS Button PRESS and BOLD 2 Airplane Establish desired vertical speed 3 CVS Button REI BASE b Using Vertical Trim Control FAA Approved Revision 4 1 VERTICAL TRIM CONTROL PRESS either up or down to increase or decrease the vertical speed Displayed ve...

Page 349: ...SAR Y TO REDUCE POVER IN ORDBR TO MAINTAIN TBB DBSIR BD RATE OP DBSCBN 1 AND NOT BXCIBD TBB NilIMUM AUTOPILOT SPBBD 3 ALTITUDE PRESELECT a ALTITUDE SELECT knob PUSH small knob to the IN position VARNING VERIFY UNIT IS DISPLAYING ALTITUDE SELECT VINDOV PRIOR TO INITIATING ANY CBANGB IN TBB SBLBCTBD ALTITUDE VALUE b ALTITUDE SBLBCT knob ROTATE until the desired altitude is displayed c ALTITUDE SELEC...

Page 350: ...0 BENDIX KING SECTION 5 PERFORMANCE No change FAA Approved Revision 4 Piper Models PA 46 JlOP and PA 46 JSOP Airplane Plight Manual Supplement 006 0428 01 Page 21 of 39 ...

Page 351: ... PLIGHT DIRECTOR COMPUTER G YD ALT HD GS NAV APR BC mn ill fil ill KC 191 AUTOPILOT COMPUTER FIGURE 1 KING KAP 150 AUTOPILOT SYSTEM CONTROLS AND INDICATORS piper Models PA 46 310P and PA 46 350P Airplane Plight Manual Supplement 006 0428 01 Page 22 of 39 cp q t filMl AP TEST 0 PAA Approved Revision 4 ...

Page 352: ...IPTION AND OPERATION KA 185 REMOTE HODB ANNUNCIATOR OPTIONAL YAW DAMP YAV DAMPER SVITCB OPTIONAL FIGURE 1 KING KAP 150 AtrrOPILOT SYSTEM CONTROLS AND INDICATORS Piper Models PA 46 310P and PA 46 350P Airplane Plight Manual Supplement 006 0428 01 Page 23 of 39 ...

Page 353: ...l such time that a valid glideslope returns and the aircraft passes thru the glideslope At that point i s couple will re occur S TRIM VARNING LIGHT TRIM Illuminates continuously whenever trim power is not on or the system has not been preflight tested THE TRIM warning light illuminates and is accompanied by an audible warning whenever a manual trim fault is detected The Manual Trim System is monit...

Page 354: ...T TEST TEST BUTTON Vhen momentarily pushed initiates preflight test sequence which automatically turns on all annunciator lights tests the roll and pitch rate monitors tests the autotrim fault monitor checks the manual trim drive voltage and tests all autopilot valid and dump logic If the preflight is successfully passed the AP annunciator light will flash for approximately 6 seconds an aural tone...

Page 355: ...ot Computer will flash until the automatic capture sequence is initiated On the KA 185 Remote Mode Annunciator NAV ARM will annunciate until the automatic capture sequence is initiated At beam capture NAV CPLD will annunciate 12 BEADING BOG MODE SELECTOR BUTTON Vhen pushed will select the Beading mode which commands the airplane to turn to and maintain the heading selected by the heading bug on th...

Page 356: ...em mode annunciators and system controls 17 KA 185 REMOTE MODE ANNUNCIATOR OPTIONAL Provides mode annunciation in the pilots primary scan area as well as three Harker Beacon lights 18 ARMED ARM ANNUNCIATOR Illuminates continuously along with NAV or APR when either the NAV or APR mode selector button is depressed The ARM annunciator vill continue to illuminate until the automatic capture sequence i...

Page 357: ...ressed and held will interrupt all electric trim power stop trim motion disengage the autopilot and yaw damper and cancel all operating Flight Director modes 24 CONTROL VHEEL STEERING CVS BUTTON Vhen depressed allows pilot to manually control the aircraft disengages the pitch and roll servos without cancellation of any of the selected modes Vill engage the Flight Director mode if not previously en...

Page 358: ...in order for the manual trim to operate in the desired direction Vhen the autopilot is engaged operation of the manual electric trim will automatically disconnect the autopilot but not the yav damper 26 KI 256 FLIGHT COMMAND INDICATOR FCI Displays airplane attitude as a conventional attitude gyro and displays commands for flight director operation The gyro is air driven FAA Approved Revision 4 FIG...

Page 359: ...ERATION IC 256 FLIGHT COMMAND INDICATOR ICG 258 VERTICAL GYRO FIGURB 1 ltING ICAP 150 AUTOPILOT SYSTEM CONTROLS AND INDICATORS Piper Models PA 46 310P and PA 46 350P Airplane Plight Manual Supplement 006 0428 01 Page 30 of 39 FAA Approved Revision 4 ...

Page 360: ...X RING SECTION 6 SYSTEM DESCRIPTION AND OPERATION KI 525A BSI KG 107 DG FIGURE 1 KING KAP 150 AUTOPILOT SYSTEM CONTROLS AND INDICATORS Piper Models PA 46 310P and PA 46 350P Airplane Flight Manual Supplement 006 0428 01 Page 31 of 39 ...

Page 361: ...ITUDE SCALE Moves with respect to the symbolic airplane to present pitch attitude Scale graduated at O 5 10 15 20 and 25 degrees 31 COMMAND BAR Displays computed steering commands referenced to the symbolic airplane The command bar is visible only when FD mode is selected The command bar will be biased out of view whenever the system is invalid or a Flight Director mode is not engaged PIGURB 1 KIN...

Page 362: ...ning of the symbolic aircraft for level flight under various load conditions 36 KI 525A HORIZONTAL SITUATION INDICATOR HSI Provides a pictorial presentation of aircraft deviation relative to VOR radials or localizer beams It also displays glideslope deviations and gives heading reference with respect to magnetic north 37 NAV FLAG Flag is in view when the NAV receiver signal is inadequate Vhen a NA...

Page 363: ...POINTERS Indicate on glideslope scale 43 aircraft displacement from glideslope beam center Glideslope pointers in view indicate a usable glideslope signal is being received 43 GLIDESLOPE SCALES Indicate displacement from glideslope beam center A glideslope deviation bar displacement of 2 dots represents full scale 0 7 deviation above or belov glideslope beam centerline 44 HEADING SELECTOR KNOB Pos...

Page 364: ...ble visual indication of aircraft heading to the pilot The gyro is air driven 51 GYRO ADJUSTMENT KNOB PUSH Vhen pushed in allows the pilot to manually rotate the gyro compass card 45 to correspond with the magnetic heading indicated by the magnetic compass The unslaved compass card must be manually reset periodically to compensate for precessional errors in the gyro 52 KI 204 206 VOR LOC GLIDESLOP...

Page 365: ... outer selects altitude in 1000 foot increments vith roll over into the 10 000 digits Vertical speed is displayed and selected when the small knob is in the out position Vhen rotated the small knob selects vertical speed in 100 fpm increments The larger knob selects vertical speed in 1000 fpm increments up to a maximum of 3000 fpm 68 MODE FT or FT MIN ANNUNCIATOR Indicates FT HIN when in the Verti...

Page 366: ...N Not shown Vhen pressed in addition to the normal autopilot functions the CVS also interfaces with the KAS 297B Vhen operating in the Vertical Speed Bold mode the CVS will re sync the Vertical Speed Bold mode to the current vertical speed of the airplane If altitude is displayed when the CVS is pressed the display will automatically display vertical speed as long as the CVS is depressed CVS does ...

Page 367: ......

Page 368: ...awing No 84376 3 The infor mation 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 limitations procedures and performance information not contained in this supplement consult the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual FAA APPROVED LlOAci ...

Page 369: ... PROCEDURES 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 OBS untilthecourse deviation needle centers with the TO FROM flag giving a FROM indication c Using the appropriate controls select a value for the waypoint radial equal to the OBS value determine...

Page 370: ...emory 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 the data input controls The outer knob controls the 10 and 100 digits the center knob IN position controls the 1 and the center knob OUT position controls the 0 1 digit The selected radial will a...

Page 371: ...akeoff 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 display Depress the DATA button to check the radial and again to check distance in the data display Now depress the USE button to place waypoint I in the USE position The number 1 in the DSP positio...

Page 372: ...se At this point if desired waypoint 2 radial and distance data may be rechecked by depressing the DSP button for each When satisfied depress the USE button to put waypoint 2 data in use The number 2 will appear in the USE annunciated space the number 2 in the DSP space will stop blinking Waypoint 2 frequency will automatically appear Following VOR DME receiver acquisition of the new VORTAC freque...

Page 373: ...RTAC and VOR PAR function will remain I _ annunciated along with the active ILS function Now reselect the same VOR and the ILS annunciation will cancel and it will revert back to VOR PAR mode HLD will cancel since VOR and DME frequency are again the same The DME HOLD button will remain depressed it is a two position button Thus the HOLD button functions as a Hold ARM when in the IN position and ac...

Page 374: ... CUSTOMER COPY UNIT MODEL NO SER NO S o 9 S Kfl3C I AC DATE INSTALLED INSTALLED BY PURCHASED FROM Mid Continent Instruments 7706 E Osie Wichita KS 67207 Phone 316 683 5619 800 821 1212 Fax 316 683 1861 ...

Page 375: ...erefore or by reason thereof All items repaired hereunder shall be warranted for the unexpired portion of the original warranty period Mid Continent will not be responsible for any installation and removal costs that may occur during this warranty period This warranty shall not apply to any product which has not been installed in accordance with the installation manual or has been repaired or alte...

Page 376: ...follows 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 Point MAP Coordinates 4 Missed Approach Fix MAF Coordinates NOTE If flying an autopilot couplt approach the pilot should revert to HEADING mode at the waypoint to make the required course cor rec...

Page 377: ...H OF FINAL APPROACH SEGMENT IN NAUTICAL MILES Approach Category Approach Magnitude of Turn Over Final Category Speed Requirements Approach Waypoint Intercept Angle 10 20 30 40 50 60 A Less than 91 knots 1 0 1 5 2 0 3 0 4 0 5 0 B 91 to 120 knots 1 5 2 0 2 5 3 5 4 5 5 5 C 121 to 140 knots 2 0 2 5 3 0 4 0 5 0 6 0 SECTION S PERFORMANCE No change SECTION 6 WEIGHT AND BALANCE Factory installed optional ...

Page 378: ...e When 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 when switched off In addition it will retain all waypoint data through a power shutdown Additional features include an automatic dimming circuit to compen sate for changes in ambient light level and ...

Page 379: ...int 0 to 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 an ILS frequency d MIN Display I VOR and VOR PAR Modes Displays time to DME ground station 0 to 99 minutes in l minute steps Most significant digit is zero blanked Displays dashes whenever DME goe...

Page 380: ... zero blanked 10 NM digit overflows into or underflows from JOO NM digit The two most significant digits roll over from 190 to ONM and vice versa f USE Display Displays waypoint number of data actually being used by system In VOR Modes only the frequency has meaning Range I to 4 When changed always takes on new value equal to DSP value g DSP Display Displays waypoint number of data being displayed...

Page 381: ...cility Flagged if localizer data is invalid CONTROLS a YOR Button Momentary pushbutton When pushed while system is in either RNV mode causes system to go to YOR mode When pushed while system is in either YOR mode causes system to toggle between VOR and YOR PAR modes b RNA V Button Momentary pushbutton When pushed while system is in either YOR mode causes system to go to RNV ENR mode When pushed wh...

Page 382: ...knob has IN and OUT positions I Frequency Data Outer knob varies I MHz digit A carry occurs from units to tenf position Rollover occurs from 117 to 108 Center knob varies frequency in 50 KHz steps 2 Radial Data Outer knob varies 10 degrees digit A carry occurs from the tens to hundreds position Rollover to zero occurs at 200 NM Center knob IN position varies I NM digit Center knob OUT position var...

Page 383: ...SECTION 9 SUPPLEMENT 2 PIPER AIRCRAFT CORPORATION PA 46 310P MALIBU For additional information consult the King KNS 80 Pilot s Guide REPORT VB 1200 ISSUED JANUARY 11 1984 9 42 14 of 14 ...

Page 384: ... Drawing No 84388 2 The infor mation 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 limitations procedures and performance information not contained in this supplement consult the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual FAAAPPROVED_L J W...

Page 385: ...ities VOR and DME signals originate from the same geographical location SECTION 3 EMERGENCY PROCEDURES No change SECTION 4 NORMAL PROCEDURES AREA NAVIGATION FUNCTIONAL TEST The following procedure applies only to airports equipped with or in range of a co located VOR DME station a Place the KNS 8 I in VOR mode b Find and record the angle from the VOR station by centering the course deviation needl...

Page 386: ...rols 5 Select the waypoint I distance by again depressing the DATA button This will move the from RAD to DST Select the new distance with the data input controls 6 This completes the programming for the first waypoint Follow these procedures for all selected waypoints up to a maximum of nine b CONVENTIONAL VOR 1 The programming technique for conventional navigation directly toward or away from a _...

Page 387: ...igation to the displayed blinking WPT waypoint is desired press the USE button The WPT display will cease blinking and the displayed waypoint becomes the active 1 waypoint RNAV OPERATION If the system is receiving valid signals from a co located VOR DME facility it will supply linear deviation information to the Horizontal Situa tion Indicator or Course Deviation Indicator Enroute RNV sensitivity ...

Page 388: ... the DME time to station display NOTE The RAD switch is not the momentary type therefore the switch must be pressed again for the normal DME information to be displayed CAUT Ofl Whenever flying directly to or from a VORTAC facility always select either the VOR or VOR PAR mode ILS OPERATION Whenever an ILS Frequency is put IN USE the mode display will remain the same either VOR VOR PAR RNAV RNAV AP...

Page 389: ...e figures are in accordance with FAA Advisory Circular 90 45A Appendix D Guidelines for Establishment of I FR Approaches MINJMUM LENGTH OF FINAL APPROACH SEGMENT IN NAUTICAL MILES Approach Category Approach Magnitude of Turn Over Final Category Speed Requirements Approach Waypoint Intercept Angle I 10 20 30 40 50 60 A Less than 91 knots 1 0 1 5 2 0 3 0 4 0 5 0 B 91 to 120 knots 1 5 2 0 2 5 3 5 4 5...

Page 390: ...witch on the right side of the panel and d isplayed in their respective displays The small knob affects the least significant digits while the large knob changes the most significan t digits The tenth s position of waypoint radial and distance can be changed by pulling the small knob to the OUT position The type of data being selected is indicated by the illuminated carets located by either FRQ RA...

Page 391: ...t digit displays only zero or five Rolls over from 11 7 to I08 or vice versa I MHz digit overflows into or underflows from 10 MHz digit 2 RAD Display Displays ground station radial on which the waypoint is located from 0 0 to 359 9 degrees The two most significant digits are zero blanked Displays radial from VOR station when CHK button is de pressed IOdegree digit overflows into or underflows from...

Page 392: ...ts Display Indicates which waypoint data FRQ RAD or DST the incre ment decrement rotary switch will change Display is cycled by depressing the DATA button e DME Display Remote Displays NM to from the waypoint station KT ground speed and MIN time to the waypoint station Displays bearing from the waypoint station instead of ground speed when the KNS 81 RAD button is depressed Displays F for FROM ins...

Page 393: ...waypoint sequence of 1 2 8 9 1 b USE Button Momentary pushbutton which when pressed causes the active waypoint to take on the same value as the displayed waypoinL c RlN Button Momentary pushbutton which when pressed causes the active waypoint to return to the display d RAD Button The KNS 81 is normally operated with the RAD button not de pressed Push on push off button which when pushed on causes ...

Page 394: ...nd the center knob varies the frequency in 05 MHz increments with carry to from the 1 MHz digit regardless of whether the switch is in its IN or OUT position 2 Distance Data The outer knob varies the 10 NM digit with a carry over occur ring from the tens to hundreds place The center knob in the IN position varies the I NM digit and in the OUT position varies to 0 1 NM digit 3 Radial Data The outer...

Page 395: ...SECTION 9 SUPPl EMENT 3 PIPER AIRCRAFT CORPORATION PA 46 310P MALIBll THIS PAGE INTENTIONAi LY I EFT BLANK REPORT VB 1200 ISSlTF D JANUARY 11 1984 9 54 12 of 12 u ...

Page 396: ... Piper Drawing 84398 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 limitations procedures and performance information not contained in this supplement consult the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual FAA APPROVED _L...

Page 397: ... WeatherScout Weather Radar System is installed SECTION 2 LIMITATIONS Do not operate the radar during refueling operation or in the vicinity of trucks or containers accomodating flammables or explosives Do not allow personnel within 15 feet of area being scanned by antenna when system is transmitting SECTION 3 EMERGENCY PROCEDURES No change REPORT VB 1200 9 56 2 of 6 ISSUED JANUARY 11 1984 REVISED...

Page 398: ...nna is not radiating energy in SBY c TEST Weather colors arc displayed for preflight test d WX Normal weather detection mode e CYC Cyclic contour mode activated alternate flashing of red intense storm cells with a black background color for added warming emphasis f MAP Activates groundmapping for identification of prominent terrain features 2 INT Rotary control used to regulate brightness INTensit...

Page 399: ...mode is displayed as WX or CYC When system is first turned on WAIT is w I displayed until system times out 30 40 seconds b PRELIMINARY CONTROL SETTINGS Place the Indicator controls in the following positions before applying power from the aircraft electrical system MODE selector OFF lNTensity control Fully counterclockwise Tl LT control Fully upward RANGE switch 12 nautical miles c OPERATIONAL CON...

Page 400: ...rucks or containers accommodating flammables or explosives do not allow personnel within 15 feet of area being scanned by antenna when system is transmitting 2 Flash bulbs can be exploded by radar energy 3 Since storm patterns are never stationary the display is constantly changing Continued observation is always advis able in stormy areas SECTION S PERFORMANCE No change SECTION 6 WEIGHT AND BALAN...

Page 401: ...SECTION 9 SllPPLF MF NT 4 PIPF R AIRCRAFT CORPORATION PA 46 3IOP MAI IBll THIS PAGE INTENTIONAi LY I EFT RI ANK RF PORT VB 1200 ISSllF D IANllARY II 1984 9 60 6 of 6 ...

Page 402: ...The information con tained 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 limitations procedures and performance information not contained in this supplement consult the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual FAA APPROVED LJGll cl WARD EVANS D 0 ...

Page 403: ...cordance with FAA Approved Piper Data SECTION 2 LIMITATIONS The following placard is installed on the right cabin side panel immedi ately forward of the copilot s air vent and the right aft facing seat aft of the air vent EMERGENCY OXYGEN IN DRAWER UNDER SEAT PULL MASK OUT OF DRAWER FULLY AT FULL EXTENSION GIVE CORD A TUG MAXIMUM DURATION 15 MINS SEE POH NO SMOKING WHILE IN USE REPORT VB 1200 ISSU...

Page 404: ...TES indicating oxygen flow Cabin Altitude REDUCE to 12 500 NOTE or lower before the 15 minute oxygen supply is fully depleted Descent should be started as soon as possible in order to assure that flow rate remains adequate throughout the descent Refer to SECTION 3 of the basic POH and FAA Approved AFM for emergency descent procedures This system once activated cannot be turned off WARNING No smoki...

Page 405: ...rplane Flight Manual SECTION 7 DESCRIPTION AND OPERATION OF THE EMERGENCY OXYGEN SYSTEM The optional emergency oxygen system consists of three two man chemical oxygen generators which provide sufficient oxygen flow for six people during a descent from 25 000 feet to 12 000 feet or below for a 15 minute time period Once an oxygen generator is activated it will continue to produce oxygen until deple...

Page 406: ...scat base The drawer is accessible from the aft side of the base under the scat bottom and is pulled aft to expose the four masks The two inboard masks arc attached to one generator while the two outboard masks arc attached to the second generator Either of the four masks will reach any of the four passenger scat locations Activation of the generators is the same as the crew installation pulling o...

Page 407: ... 3 OUTI FT BASF OF OXYGEN r ENERATOR 4 PROTFrTIVE OVER t IANYARDS Ii C OC KPIT UNIT 1 ARIN UNIT PIPER AIRCRAFT CORPORATION PA 46 310P MAUBll 4 UNIT LOCATION SKETCH A CABIN UNIT 8 SEE SKETCH A Figure 7 1 OxygL n Sy tcm Installation REPORT VB 1200 ISSUED JANUARY II 1984 9 66 6 of 6 ...

Page 408: ...0 2 The information con tained 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 limitations procedures and performance information not contained in this supplement consult the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual FAA APPROVED lJcuJl WARD EVANS D ...

Page 409: ...TIONS AIR COND switch OFF for takeoffs and landings NOTE FAN switch may be in HIGH or LOW position SECTION 3 EMERGENCY PROCEDURES Alternator failure ALTERNATOR annunciator light illuminated AIR COND switch OFF Freon compressor failure AIR COND switch OFF SECTION 4 NORMAL PROCEDURE AIR CONDITIONING SYSTEM OPERATION To turn air conditioning ON AIR COND switch ON FAN HIGH or LOW as desired To turn ai...

Page 410: ...r conditioner operation these changes should be considered in preflight planning To be conservative decrease the true airspeed l knot while operating the air conditioner NOTE To insure maximum climb performance the air conditioner must be turned off manually before takeoff and landing SECTION 6 WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance d...

Page 411: ...fan are located in the tail cone immediately aft of the rear pressure bulkhead Cooling air is pulled into the cooling air duct from the outside of the tailcone thru a flush opening in the skin routed across the condenser coil and discharged into the tailcone The tailcone exit opening provides a path for discharging the air overboard The evaporator assemblies two are located aft of each rear seat b...

Page 412: ...34 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 limitations procedures and performance information not contained in this supplement consult the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual FAA APPROVED lJ J _ a WARD EVANS ...

Page 413: ...rating thunderstorm areas or areas of severe turbulence such intentional use is prohibited NOTE Range selector determines receiver sensitivity and therefore relative range Displayed range is based on signal strength and is not to be used for accurate determination of thunderstorm location b Allow 30 seconds warm up time before activating test functions c Placards Located on the top of the throttle...

Page 414: ...s at both I00 NM range and 200 NM scale selections No signal will normally be seen on the 50 25 NM scales 4 Push clear button CLR to clear dots from screen so new thunderstorm data can be displayed 5 Turn Range Selection switch to desired range in nautical miles 6 For night operation he brightness control BRT controls intensity of dots for comfortable viewing NOTE Operator should be aware that occ...

Page 415: ...f 6 PIPER AIRCRAFT CORPORATION PA 46 310P MAUBll 2 6 5 1 MAPPING DIRECTION INDICATOR 2 MAPPING LINES 3 BRIGHTNESS CONTROL 4 RANGE SELECTION SWITCH 5 CLEAR BUTION 6 TEST BUTION 7 POWER MODE SWITCH WX IOA STORMSCOPE Figure 4 1 3 ISSUED APRIL 30 1984 ...

Page 416: ...nerally the thunderstorm severity The dot patterns will update automatically anywhere from approximately 10 seconds to 5 minutes depending upon the nature and severity of the detected disburances by automatic erasure of oldest signals and display of newly detected signals A random scattered display of signals may only indicate possible areas of atmospheric instability rather than significant thund...

Page 417: ...sociated with I thunderstorms This information with proper interpretation will allow the pilot to detect severe thunderstorm activity A series of green dots will be displayed on the screen to indicate the electrical discharge areas The display scope provides full scale selectable ranges of 200 100 50 and 25 nautical miles along with 30 azimuth sectors REPORT VB 1200 9 76 6 of 6 ISSUED APRIL 30 198...

Page 418: ...o 83980 Heated Windshield Panel Dwg No 83981 and Wing Ice Detection Light Dwg No 83978 The information contained herein upplements or supersedes the information in the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein For limitations procedures and performance informatio n not contained in this supplement consult the basic Pilot s Operating ...

Page 419: ...ECTION 4 NORMAL PROCEDURES Prior to flight the equipment should be functionally checked for proper operation An operational check of the heated windshield panel is accomplished by turning the WSHD HEAT switch ON for a period not exceeding30seconds Proper operation is indicated by the heated panel being warm to the touch NOTE A safety feature prevents activation ofthe panel at ambient temperatures ...

Page 420: ...igure 7 1 WING ICE DETECTION LIGHT Wing icing conditioris may be detected during night flight by use of an ice detection light installed on the left side of the forward fuselage The light is controlled by an ICE LIGHT switch Figure 7 1 located on the de ice switch panel Circuit protection is provided by an ICE circuit breaker located in the LIGHT section of the circuit breaker panel PROP HEAT Eiec...

Page 421: ...SHIELD PANEL An electrically heated windshield panel is installed on the exterior ofthe pilot s windshield The panel is heated by current from the aircraft electrical system and controlled by an ON OFF type WSH D HEAT switch located on the auxiliary switch panel The panel is equipped with a temperature sensing device which auto matically turns the panel on and offduring operation to maintain the d...

Page 422: ...PIPER AIRCRAFT CORPORATION PA 46 JIOP MALIBU AUXILIARY SWITCH PANEi Figure 7 1 ISSUED APRIL 30 1984 SECTION 9 SUPPLEMENT 8 REPORT VB 1200 I 5 of 6 9 81 ...

Page 423: ...SECTION 9 SUPPLEMENT 8 PIPER AIRCRAFT CORPORATION PA 46 310P MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1200 ISSUED APRIL 30 1984 9 82 6 of 6 ...

Page 424: ... installed per the Equipment List 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 limitations procedures and performance information not contained in this supplement consult the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual FAA APPROVED WoJ WARD E...

Page 425: ...ver navigation is predicated on the use of the TI 9100 b VFR RNAV operation of the Tl 9100 is limited to the 48 contiguous states and the District of Columbia IFR RNAV operation is limited to the 48 contiguous states the District of Columbia and offshore areas with the following exclusions See chart page A I in the operator s manual c During RNAV operation of the TI 9100 additional navigation equi...

Page 426: ...l dated 1981 Revision A dated October I 1982 b NAV COUPLED MODE When operating the KAP KFC I50 flight control system in either the navigation NAV or approach APR mode and the NAV LORAN switch has been set to the Tl 9100 as the navigation source all operational procedures which are applicable to these two modes as described in the KAP KFC I50 Operator s Manual and Flight Manual Supplement still app...

Page 427: ...anually selected by the NAV LORAN switch This configuration is annunciated by a mode light adjacent to the HSI The HSI will only display left or right course information to from flags and a Off Warning flag indication from the Tl 9100 The course selector pointer must be manually set to the Loran C course Actual course cannot be determined on the HSI by rotating the course selector pointer When Lor...

Page 428: ...sted below The displayed numbershould represent the computer program version shown in the Tl 9100 Loran C Navigator Operator s Manual KEY 2ND MON s SECTION S PERFORMANCE DISPLAY A371 Installation of the TI 9100 Loran C Navigator does not affect the basic performance information presented in Section Sof this Pilot s Operating Handbook ISSUED APRIL JO 1984 REVISED APRIL 1 1987 REPORT VB 1200 S of 6 ...

Page 429: ...SECTION 9 SUPPLEMENT 9 PIPER AIRCRAFT CORPORATION PA 46 310P MALIBU THIS PAGE INTENTIONALLY LEFT BLANK I REPORT VB 1200 9 86b 6 of 6 ISSUED APRIL 30 1984 REVISED APRIL 1 1987 ...

Page 430: ... in th is manua l is FAA Appr oved mate ri a l 11h ich along 11ith the FAA App ro ved Airpl an e Fli g ht Manual placards and in st ru ment ma rkings is appl ic a ble to the operation of t he a ir pl ane when modi fi ed by the in sta l l ati on o f the King KAS 2978 Vert ical Spe ed and Altitude Selector as per STC SA1778CE D FAA Approved M __ R iLPH V COLf OAS Coordinator King Radio Corpor at i o...

Page 431: ... 1 2 3 4 5 ICING PFS030 6 PIPER MODEL PA 46 310P FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLE ENT TABLE OF CONTENTS General Limitations Emergency Procedures Normal Procedures Performance i 1 6 6 7 9 006 0428 02 ...

Page 432: ...50 Flight Control System The KAS 2979 providu the pilot with the following features ab1 lit to select vertical speed hold ability to select arm and upon approaching the selected altitude automatically transfer into Altitude Hold altitude alerting as specified by F A R 91 51 The KAS 2979 controls and display are further described in Figure 1 Piper Model PA 46 310P Airplane Flight Manual Supplement ...

Page 433: ...eed Hold mode to the current vertical speed of the airplane PHOTOCELL Automatically dims displa accordfog to the cockpit ambient light VERTICAL SPEED CVS ANNUNCIATOR Illuminates when the Vertical Speed Hold mode is engaged I VERTICAL SPEED UP DOWN CARETS C V Indicates whether the selected vertical speed is up or down GAS DISCHARGE DlSPLAY Displays selected altitude from 100 to 35 000 feet or the s...

Page 434: ...small knob selects altitude in 100 foot increments with roll over into the 1000 digits The larger knob outer selects altitude in 1000 foot increments with roll over into the 10 000 digits Vertical speed is displayed and selected when the small knob is in the out position When rotated the small knob selects vertical speed in 100 fpm increments The larger knob selects vertical speed in 1000 fpm incr...

Page 435: ...tude will also cycle the Altitude Select ARM mode off 12 CONTROL WHEEL STEERING CCWS BUTTON Not shown When pressed in addition to the normal autopilot functions the CWS also interfaces ith the KAS 2978 When operaHng in the Vertical Speed Hold mode the CWS will re sync the Vertical Speed Hold mode to the current vertical speed of the airplane If altitude is displayed when the CWS is pressed the dis...

Page 436: ... AUTOPILOT ENCODING ALT FUNCTION Supplies power to the ICC 192 or the KC 191 computer the autopilot pitch and roll servos the Elev Trim Switch Circuit Breaker and the KAS 2978 Supplies power to the King KEA 130A Altimeter Piper Model PA 46 310P Airplane Flight Manual Supplement FAA Approved Date 10 26 83 006 0428 02 Page 5 of 9 ...

Page 437: ...ON 2 LIMITATIONS A Altitude Select captures below 800 feet AGL are prohibited SECTION 3 EMERGENCY PROCEDURES None 006 0428 02 Page 6 of 9 p per Model PA 46 310P A rplane Flight Manual Supplement FAA Approved Date 10126 83 ...

Page 438: ...il desired vertical speed is displayed c VERTICAL SPEED MODE ENG button PUSH to engage the Vertical Speed Hold mode 2 Changing Vertical Speed a Using CWS 1 CWS Button PRESS and HOLD 2 Airplane Establish desired vertical speed 3 CWS Button RELEASE b Using Vertical Trim Control 1 VERTICAL TRI CONTROL PRESS either up or down to increase or decrease the vertical speed Displayed vertical speed changes ...

Page 439: ...N WHEN OPERATING AT OR NEAR THE MAXIMUM AUTOPILOT SPEED IT WILL BE NECESSARY TO REDUCE POWER IN ORDER TO MAINTAIN THE DESIRED RATE OF DESCENT AND NOT EXCEED THE MAXIMUM AUTOPILOT SPEED C ALTITUDE PRESELECT 1 ALTITUDE SELECT knob PUSH small knob to the IN position 2 ALTITUDE SELECT knob ROTATE until the desired altitude is displayed 3 ALTITUDE SELECT MODE CARN button PUSH to arm the Altitude Select...

Page 440: ...RMANCE KING PFS030 6 There is no change to the airplane performance when this ayionics equipment is installed Piper Model PA 46 310P Airplane Flight Manual Supplement FAA Approved Date 10 26 83 006 0428 02 Page 9 of 9 ...

Page 441: ... i ...

Page 442: ...er Drawing No 83965 2 is installed 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 limitations procedures and performance information not contained in this supplement consult the basic Pilot s Operating Handbook and FAA Approved Afrplane Flight Manual FAA...

Page 443: ...onditions more severe than those of FAR 25 Appendix C Therefore flight in those conditions may exceed the capabilities of the ice protection system b Equipment required for flight into known or forecast icing 1 Pneumatic wing and empennage boots 2 Wing ice detection light 3 Electrothermal propeller deice pads on the propeller blades 4 Electrothermal windshield panel 5 Heated lift detector 6 Heated...

Page 444: ... considered and an alternate airport chosen if necessary ALTERNATOR FAILURE IN ICING CONDITIONS ALTERNATOR annunciator light illuminated Verify failure observe runmeter for both alternators Electrical loads reduce below 60 amps AN volt ammeter switch cycle while observing ALTNTR circuit breaker ammeter to determine affected alternator affected alternator check ALTNTR switch affected alternator OFF...

Page 445: ...proper indications a ON needle in green arc for approx 90 seconds b OFF for approx 90 seconds Areading below the green arc during the ON cycle is an indication that the propeller blades may not be deicing properly U PROP HEAT switch OFF if failure is indicated WARNING It is imperative that the PROP HEAT switch be turned OFF if vibration persists This can be a symptom of uneven blade deicing which ...

Page 446: ...ts must be cleaned regularly for proper operation in icing The exterior surfaces of the aircraft should be checked prior to flight Do not attempt night with frost ice or snow adhering to the exterior surfaces of the aircraft or landing gear Prior to dispatch into forecast icing conditions all ice protection equip ment should be functionally checked for proper operation PREFLIGHT a An operational c...

Page 447: ...DEICE annunciator light will remain on for approximately eighteen seconds 2 Visually check to insure that the boots have fully deflated to 1 1 indicate proper operation of the vacuum portion of the pneumatic boot pump system e The dual alternators should be checked by cycling the A V volt ammeter switch and observing for indication of output from both alternators on the ammeter I The standby vacuu...

Page 448: ...arily WARNINGS Do not cycle surface boots with less than 1 4 inch of ice accumulation Operation of boots with less than l 4 inch of ice accumulation can result in failure to remove ice Do not hold the momentary SURF DEICE switch on Elevator movement should be periodically checked prior to the first surface boot inflation in order to prevent an ice cap from forming between the elevator and stabiliz...

Page 449: ...proach speeds should be increased by 10 to 15 knots Allow for increased landing distance due to the higher approach speeds CAUTION If cruise airspeed drops below 130 knots in icing conditions increase power to maintain 130 knots If maximum continuous power is re quired to maintain 130 knots immediate action should be taken to exit icing conditions NOTE An icing encounter can render the aircraft ra...

Page 450: ...UTION If cruise airspeed drops below 130 knots in icing conditions increase power to maintain 130 knots If maximum continuous power is re quired to maintain 130 knots immediate action should be taken to exit icing conditions NOTE For additional general information on inflight icing refer to FAA Advisory Circular 91 51 Airplane Deice and Anti ice Systems SECTION 6 WEIGHT AND BALANCE Factory install...

Page 451: ...aximum icing The airplane is not designed to operate for an indefinite period of time in every icing condition encountered in nature Activation of the ice protection system prior to entering icing conditions and attempting to minimize the length of the icing encounter will contribute significantly to the ice flying capabilities of the airplane WING AND EMPENNAGE BOOTS Pneumatic deice boots are ins...

Page 452: ...on the circuit breaker panel When the PROP HEAT switch is actuated power is applied to a timer through the PROP HEAT ammeter which monitors the current through the propeller deice system Power from the timer is cycled to brush assemblies which distribute power to slip rings The current is then supplied from the slip rings directly to the electrothermal propeller deice pads The Hartzell propeller i...

Page 453: ...ted to indicate proper operation of the panel HEATED LIFT DETECTOR A heated lift detector is installed on the left wing It is controlled by a S WRN HEAT switch located on the deice switch panel and is protected by a S WARN HEAT circuit breaker located on the ice protection circuit breaker panel The lift detector has an in line resistor activated by the main gear squat switch which limits the groun...

Page 454: ...URF DEICE switch to activate the deice boots in which case the standby pump is automatically actuated to increase the efficiency of the surface deice system Either pump is capable of operating the surface deice system with the other pump inoperative Therefore the STANDBY VAC PUMP switch should only be actuated when a primary pump failure is indicated by illumination of the VACUUM LOW annunciator l...

Page 455: ...SECTION 9 SUPPLEMENT 10 REPORT VB 1200 9 100 14 of 16 PIPER AIRCRAFT CORPORATION PA 46 JlOP MALIBU DEICE SWITCH PANEL Figure 7 1 ISSUED JULY 30 1984 ...

Page 456: ...PIPER AIRCRAFT CORPORATION PA 46 310P MALIBU MAIN SWITCH PANEL Figure 7 2 ISSUED JANUARY 15 1986 SECTION 9 SUPPLEMENT 10 REPORT VB 1200 15 of 16 9 101 ...

Page 457: ...SECTION 9 SUPPLEMENT 10 PIPER AIRCRAFT CORPORATION PA 46 JIOP MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1200 ISSUED JULY 30 1984 l 9 102 16 of 16 V u ...

Page 458: ...rawing No 84605 3 and Motor Control Installed per Piper Drawing No 84531 2 The information contained herein supplements or supersedes the information in the basic Pilot s Operating Handbook and FAA Approved Airplane Aight Manual only in those areas listed herein For limitations procedures and performance information not contained in this supplement consult the Pilot s Operating Handbook and FAA Ap...

Page 459: ...illuminates continuously HYO PUMP circuit breaker pull and reset Verify normal hydraulic system operation If HYO PUMP annunciator light illuminates second time HYO PUMP circuit breaker pull Land as soon as possible and investigate the cause NOTE It may be necessary to lower the landing gear using the emergency extension control Illumination of the HYO PUMP annuncitor indicates a possible hydraulic...

Page 460: ...exceeding the pump motor duty cycle The unit measures continuous operating time of the motor and should running time exceed 17 seconds automatically deenergizes the electrical circuit When this occurs an amber HYD PUMP annunciator light is illuminated to inform the pilot that a possible hydraulic system malfunction has occurred The unit also counts the number of times the pump motor cycles on and ...

Page 461: ...SECTION 9 SUPPLEMENT 11 PIPER AIRCRAFT CORPORATION PA 46 310P MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1200 9 106 4 of 4 ISSUED APRIL 1 1987 V ...

Page 462: ...iper Dwg 84634 3 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 limitations procedures and performance information not contained in this supplement consult the basic Pilot s Operating Handbook and FAA Approved Airplane Flight I Manual FAA APPROVED J N Ju...

Page 463: ...ing thunderstorm areas or areas of severe turbulence such intentional use is not approved NOTE Range selector determines receiver sensitivity and therefore relative range Displayed range is based on signal strength and is not to be used for accurate determination of thunderstorm location b Allow 30 seconds warm up time before activating test functions c Placards V Located on the top of the throttl...

Page 464: ...sity of dots for comfortable viewing 7 Gyro Status Depress TST and CLR and hold them down to ensure gyro inputs are being used for stabilization If GYRO ON appears on the Model WX 11 Display the dot pattern indicating thunderstorm activity will automatically turn relative to the aircraft heading as the aircraft turns If GYRO OFF appears on the display the dot pattern will remain stationary as the ...

Page 465: ...6 310P MALIBU 2 3 7 6 5 1 MAPPING DIRECTION INDICATOR 2 MAPPING LINES 3 BRIGHTNESS CONTROL 4 RANGE SELECTOR SWITCH 5 CLEAR BUTTON 6 GYRO STATUS 7 TEST BUTTON 8 PQWER MOOE SWITCH WX 11 STORMSCOPE Figure 4 1 IREPORT VB 1200 9 110 4 of 6 ISSUED APRIL 1 1987 u ...

Page 466: ...es and generally the thunderstorm severity The dot patterns will update automatically anywhere from approximately 10 seconds to 5 minutes depending upon the nature and severity of the detected disburances by automatic erasure of oldest signals and disp1ay of newly detected signals A random scattered display of signals may only indicate possible areas of atmospheric instability rather thansignifica...

Page 467: ...charges associated with thunderstorms This information with proper interpretation will allow the U pilot to detect severe thunderstorm activity A series of green dots will be displayed on the screen to indicate the electrical discharge areas The display scope provides full scale selectable ranges of 200 100 50 and 25 nautical miles along with 30 azimuth sectors 1REPORT VB 1100 9 111 6 of 6 ISSUED ...

Page 468: ...9124 2 or Piper Kit 765 348 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 limitations procedures and performance information not contained in this supplement consult the basic Pilot s Operating Handbook and FAA Approved Airplane __ 1 1 light Manual I FA...

Page 469: ...CEDURES ALTERNATOR annunciator light illuminated AUX CABIN HEAT Switch OFF LO BUS annunciator light illuminated U Volt Ammeter VERIFY LOW VOLTAGE AUX CABIN HEAT Switch OFF Electrical Load REDUCE until LO BUS light EXTINGUISHES NOTE If the LO BUS annunciator light does not extinguish after the electrical load has been reduced and low voltage is verified an electrical failure is indicated Refer to E...

Page 470: ...w voltage monitor system and annunciator must be checked operational before heater operation VENT DEFOG FAN must be checked operational before heater ground operation HEATER OPERATION VENT DEFOG FAN ON AUX CABIN HEAT Switch ON For maximum beat REC BLWR Switch OFF CABIN TEMP Control FULL OUT DEFROST Control AS REQUIRED to CLEAR WINDSHIELD then FULL IN NOTE This unit should be considered primarily a...

Page 471: ...noid through the 35 amp heater fuse and the heater power relay V The 35 amp heater fuse is not accessible to the pilot The electrical load imposed by the heater and the vent defog fan is 40 35 amps Installation is limited to aircraft equipped with dual alternators Emergency interruption of the circuit can be accomplished by disengaging the battery master switch and engaging the emergency bus switc...

Page 472: ... electrical switch panel has been modified to accommodate the adition of th e AUX CABIN HEAT switch refer to Figure 7 2 Refer to Figure 7 3 for a schematic of the Electrical Heater and Voltage Monitor circuits IEJEJBEJEJI W BElEJB 88 BBB ELECTRICAL SWITCH PANEL MODIFICATION Figure 7 2 ISSUED OCTOBER 27 1987 REPORT VB 1200 I S of 6 9 117 ...

Page 473: ...R ASSV I I I I J o u TO MAIN BUS TEMPERATURE SENSORS SWITCH ASSV BATTEAY MASTER _ O A_t _R_ I I ifl t________ 1 I BATTERY EMERGENCY BUS U V d ELECTRIC HEAT AND LOW VOLTAGE MONITOR SCHEMATIC Figure 7 3 REPORT VB 1200 9 118 6 of 6 ISSUED OCTOBER 27 1987 REVISED DECEMBER 16 1987 ...

Page 474: ......

Page 475: ......

Page 476: ...er the Equipment List 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 1 For limitations procedures and performance information not contained in this supplement consult the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual _ FAA APPROVED...

Page 477: ...SECTION 4 NORMAL PROCEDURES WARNING Do not operate the radar during refueling operations or within 15 feet of trucks or containers accommodating flammables or explosives Do not allow personnel within 15 feet of area being scanned by antenna when system is ttansmitting Preflight and normal operating procedures are outlined in the Bendix King RDS 81 82 Digital Weather Radar Pilot s Guide P N 006 085...

Page 478: ... I I I I t PIN OP910528 REV A Digiflo DIGITAL FUEL MANAGEMENT SYSTEM OPERATING MAl oAL ForP Ns 91052X SHADIN Co Inc ...

Page 479: ...ng Input Error 7 3 5 Test Function 8 4 In Flight Operations 9 4 1 Instrument Operation 9 4 2 Warning 9 4 3 Emergency Procedure 9 5 Specifications 10 6 Warranty Information 11 7 Configuration Data Bntry 12 15 NOTE Though references are made in this manual to fuel measured in gallons the information applies equally to measurements in pounds or liters m Shad1n COMPANY INCORPORATED 6831 Oxford Street ...

Page 480: ...llons Powuls or Liters readouls Jd it can be installed on virtually any reciprocating or turbine engine by selecting the proper size fuel flow transducer It can be used with injected or carbureted engines DIGII l O features solid state electronic components and a microprocessor designed to process the pulses generated by the fuel flow transducer Fuel flow is continuously displayed in the lower win...

Page 481: ...ual fuel flow which means that reducing the power or leaning the mixture will result in increasing the time remaining Ifthe calculated time remaining at any particular power setting drops below 45 minutes the Time Remaining digits in the display window will start flashing 1 1 FUEL FLOW TRANSDUCER The fuel flow transducer mounted in the fuel line measures the flow of fuel and generates electrical p...

Page 482: ...d through the manual entry mode but Group I is not accessible If neither of the above settings are used the unit will be in Operate Mode ai Group 2 information will be obtained from non volatile memory Group I information will be obtained from the cWTent switch settings Manual Entrv Mode There are two ways to get to the Manual Entry Page 1 Set Switches I and 2 to Calibrate Mode and power up This a...

Page 483: ...access to both Group J and Group 2 values and one which provides access to only Group 2 values The access to Group 2 values can be obtained while the unit is installed in the aircraft Access to Group l however requires removal of the unit to adjust switch settings Operate Mode vs Calibrate Mode FE IfSwitch 1is set to F and Switch 2 is set to E the unit is in the Calibrate Mode This is the only mod...

Page 484: ...r Test button Fuel used will be reset and the fuel remaining will appear and pause on display for 4 seconds The figure will decrement When the correct figure is reached the longer you press the faster it decrements release both Fuel Used and ENTER buttons To avoid repeating the 4 second pause while decrementing do not release the Fuel Used button but use the ENTER button to control the decrementin...

Page 485: ...Under no circumstances will SHAD N Co Inc be liable for consequential damages sustained in connection with the product and SHADIN Co Inc does not assume for it any obligation or liability whatsoever other than as is expressly set forth hereinabove 11 I 3 5 TEST FUNCTION The Test Function enables the pilot to check the software and hardware against malfunction Press the Enter fest button All digits...

Page 486: ...ower failure in flight the instrument will cease to function After restoring power the left window will resume accurate fuel flow reading but the Time Remaining Fuel Used and Fuel Remaining figures will not be accurate unless the duration of the power failure is known and the fuel consumptir during the electric power failure is caluclated and subtracted fn _ the Fuel Remaining 9 5 SPECJFJCATJONS D...

Page 487: ...ORMAL PROCEDURES CAUTION Comply with manufacturer s Airplane Flight Manual leaning procedure Do not exceed applicable engine or aircraft limitations After establishing desired cruise power depress the LF button to activate the Lean Find Mode As the mixture is leaned one column on the EGT 701 display will begin blinking indicating the exhaust gas temperature for that cylinder has peaked shown J dig...

Page 488: ... mode the leanest cylinder is displayed along with the fuel flow optional at that time Depressing the LF and STEP button simultaneously brings up the adjustable scan rate function OAT in C or 0 f Depress the LF button will change the value of the rate or OAT in C or 0 f Exit by Depressing STEP If the EGT 70 I buttons arc not depressed for IOminutes the system will start scanning automatically Depr...

Page 489: ... airplane is modified by the installation of a Hartzell PHC G3YF 1E 7890 K propeller and C 3535 3 P spinner in accordance with STC SA01616CH The information contained herein supplements or supersedes the basic manual only in those areas listed herein For limitations procedures and performance information not contained in this supplement consult the FAA Approved Airplane Flight Manual _2 JAN 242002...

Page 490: ...P MALIBU LOG OF REVISIONS Description of Revision Date Page 2 of 5 12 20 01 NOTE All changes are indicated by a black vertical line along the left margin il 1 L I_ Iii 2 2 lli A FAAAp QaV l Charles L Smalley Manager Systems and Flight Test Branch Chicago ACO FM Central Region ...

Page 491: ... 9 0 2 degrees Measured at 30 inch station Maximum Diameter Minimum Diameter Hartzell C 3535 3 P No change 80inches 80inches Kinds of Operation Propeller De ice No change If propeller de ice equipment is not installed and operational the aircraft must be placarded against flight in icing conditions Ground operation limited to 1Oseconds for test purposes 3 EMERGENCY PROCEDURES SECTION No change ...

Page 492: ... as good or better than with 2 blade PHC C2YF 1 BF F8052 K installed 6 WEIGHT AND BALANCE SECTION The three blade composite propeller is approximately 9 pounds heavier than the two blade aluminum propeller and the moment arm for the three blade is The STC Installation Instructions contain information for revising the aircraft weight and balance data JAM 2421112 FAA Approve _ oate_____ Charles L Sm...

Page 493: ...d in Hartzell Manual 145 Propeller Owners Manual Electrically heated de ice boots may be fitted to the propeller blades To protect the composite blades from overheating when the propeller is not turning the propeller de ice system is de activated via a weight on wheels switch A push to test switch is provided to test the propeller de ice on the ground Use of the test switch is limited to 10 second...

Page 494: ...s modified by the installation ofthe TCM TSI0 550 C engine and the Hartzell PHC G3YF 1E 7890K propeller in accordance with STC SA01770CH The information contained in this document supplements or supercedes the basic handbook on1y in the areas listed herein For limitations procedures performance and loading infonnation not contained in this supplement consult the basic airplane Pilot s Operating Ha...

Page 495: ...ed by the installation ofthe TCM TSI0 550 C engine and the Hartzell PHC G3YF 1E 7890K propeller in accordance with STC SA01770CH The information contained in this document supplements or supercedes the basic handbook only in the areas listed herein For limitations procedures performance and loading information not contained in this supplement consult the basic airplane Pilot s Operating Handbook _...

Page 496: ...EVISIONS Revision No Affected Pgs Description FAA Approved Page 2 of7 Date Vertical bars in RHS margin ofaffected pages indicate where revisions were made FAA Approved Charles L Smalley Manager Systems Flight Test Branch Chicago Aircraft Certification Office Date FEB O 2003 2300 E Devon Ave Des Plains IL 60018 ...

Page 497: ...ches j Compression Ratio k Engine Type 1 5 PROPELLER a Number ofPropellers b Propeller Manufacturer c Blade Model d Number ofBlades e HubModel t Propeller diameter inches g Propeller type 2 0 LildlTATIONS 2 1 GENERAL N C 2 3 AIRSPEED LIMITATIONS N C 552 7 5 1 Six Cylinder Direct Drive Horizontally opposed Air Cooled Turbocharged Fuel injected 1 Hartzell 7890 K 3 PHC G3YF tE 80 Constant Speed Hydra...

Page 498: ...imum red line Normal Maximum red line t Fuel Flow Maximum red line g Fuel AVGAS ONLY Minimum Grade h Number ofPropellers i Propeller Manufacturer j Propeller Hub and Blade Model k Propeller Diameter inches I Blade Angle Limits Low Pitch Stop minimax High Pitch Stop min max 2 9 LEANING LThflTATIONS N C Page 4 of7 1 Teledyne Continental TSI0 550 C 2600RPM 240 F 460 F 1750 F 1850 F 35 5 in Hg 10 psig...

Page 499: ... Caution Range Idle 10 PSI to 30 PSI Yellow Arc Caution Range Start and Warm Up 60 PSI to 100 PSI Red Line Minimum lOPSI Red Line Maximum IOOPSI e Fuel Flow Green Arc Nonna Operating Range 6 to 40 gaJ hr Red Line Maximum 40 gal hr t Turbine Inlet Temperatures Green Arc Norma Operating Range 1200 F to 1750 F Red Line Maximum 1750 F g Cylinder Head Temperatures Green Arc Normal Operating Range 240 F...

Page 500: ...T PROP DE ICE Push Prop Heat Test switch to test prop de ice 10 sec max 5 0 PERFORMANCE The performance ofthis airplane equipped with the TCM TSI0 550 C engine and the Hartzell PHC G3YF 1E 7890 K propeller is equal to or better than the performance listed in the original FAA approved Pilot s Operating Handbook 6 0 WEIGHT AND BALANCE N C EXCEPT AS NOTED BELOW The TCM TSI0 550 C engine and the Hartz...

Page 501: ...opeller is an 80 inch diameter constant speed unit that features three Kevlar epoxy blades in an aluminum hub The spinner is fabricated from aluminum alloy see Propeller Owners Manual Hartzell Manual 145 for a more detailed description Electrically heated de ice boots are fitted to the propeller blades To protect the composite blades from overheating when the propeller is not turning the propeller...

Page 502: ...ING PRECAUTIONARY PROCEDURES ARE IN EFFECT IMMEDIATELY AND SHALL REMAIN IN EFFECT UNTIL THE INSPECTION DESCRIBED IN PART I OF THIS SERVICE BULLETIN HAS BEEN COMPLETED Tl E 0 E P J OP S L BE ClESPONSIBLE FOR ENSURING COMPLIANCE WITH THE FOLLOWING RESTRICTIONS L CH Tl 11 L T E PREFLIGHT CHECKLIST IS PERFORMED ACCORDING TO THE NORMAL PROCEDURES SECTION OF THE POH CHECK CONDITION OF WING SURFACE FOR B...

Page 503: ...er of fuel vent valves used in the affected airplanes has changed the material formulation from the original design fluorosilicone polymer colored orange hereinafter referred to as orange fuel vent valve to a nitrile butadiene rubber colored black hereinafter referred to as black fuel vent valve As currently installed on the airplane the black fuel vent vc tlves may not provide the proper ventilat...

Page 504: ...el Vent Valve Replacement Permanent Corrective Action Part II Fuel Vent Valve Modification and POH changes Temporary Corrective Action Black fuel vent valves require a modification for continued use NQIE Aircraft in compliance with Part II must also comply with Part Ill according to the time intervals stated in the COMPLIANCE TIME section of this service bulletin NOTE Refer to Chapter 28 of the ap...

Page 505: ...e entire black fuel vent valve must be removed from the main fuel tank vent assembly prior to proceeding 4 Using finger pressure fold the umbrella valve portion of the replacement orange fuel vent valve towards the duckbill valve and press the fuel vent valve into the circular opening of the main fuel tank vent assembly continuing until the umbrella portion is completely through the opening and no...

Page 506: ... depth 4 mm 0 16 inches ___M_aximum depth 5 mm 0 20 inches 1Jf o t Black Fuel Vent Valve after modification Main Fuel Tank Vent Assembly DETAILA Figure 1 Main fuel tank vent assembly as removed from aircraft wing NOTE Cutting tool shown for illustration purposes only to clarify depth of cut Remove cutting tool prior to reinstalling the main fuel tank vent assembly ...

Page 507: ...cility This service bulletin is effective upon receipt Please contact your Piper approved service facility to make arrangements for compliance with this service bulletin in accordance with the compliance time indicated NOTE Please notify the factory of any address ownership corrections Changes should include aircraft model serial number current owner s name and address Corrections and or changes s...

Page 508: ...ual inspection Further if valve replacement is necessary for aircraft under warranty Piper will cover parts and labor performed at a Piper Authorized Service Center For older aircraft no longer under warranty Piper will cover the cost of required replacement parts Piper has been made aware that the manufacturer ofcertain fuel vent valves which may have been used in some aircraft in the PA 46 fleet...

Page 509: ...k it must be modified to specifications Fuel vent must be replaced with orange fuel vent within 90 calendar days of service bulletin Black needs mechanic modification then replacement within 90 calendar days of SB Orange needs mechanic sign off ...

Page 510: ...Paragraph No TABLE OF CONTENTS SECTION 10 OPERATING TIPS Page No 10 1 General 10 1 10 3 Operating Tips 10 1 REPORT VB 1200 10 i ...

Page 511: ...laps may be lowered at airspeeds up to 170 KIAS and full flaps up to 120 KIAS but to reduce flap operating loads it is desirable to have the airplane at a slower speed before extending the flaps d Before attempting to reset any circuit breaker allow a two to five minute cooHng off period e Before starting the engine check that all radio switches light switches and the pitot heat switch are in the ...

Page 512: ... should be aware of the need for special physiological training Appropriate training is available for a small fee at approximately twenty three Air Force Bases throughout the United States The training is free at the NASA Center in Houston and at the FAA Aeronautical Center in Oklahoma Forms to be completed Physiological Training Application and Agreement for application for the training course ma...

Page 513: ...Ite111 Propeller Hartzell Part No BHC C2Y F 1BF F8052 Cert Basis TC P920 3 Hydraulic Propeller Governor Hartzdl Part No E 5 2 Cert Basis TC P920 5 Spinner Assembly Hamel Part No D 4810 or D 48 IOP b Engine_ and Engine _A cce soric _ 11 Engine Teledyne Continental Motors Part No TSI0 520 BE Cert Basis TC E8CE 13 Air Filter Donaldson Part No 6 I I5A499 Piper Dwg 84001 2 c Landing Gear a nd Brakes 21...

Page 514: ...7 59 61 63 65 67 240 0025 2 of 10 b Post Lights 24 Grimes Part No A8970B l 327 Piper Dwg 84433 2 Avionics Light Dimmer Calco Part No 8534 Piper Dwg 84414 Ventilation Fans a Left Enviro Systems Inc P N 1250260 1 b Right Enviro Systems Inc P N 1250260 2 Piper Dwg 84333 2 Defroster Defog Fan Electro Mech P N EN 1608 Piper Dwg 84614 2 Ventilation Fan Relay 2 Detrol Part No 20607 82 or Medtex Part No 1...

Page 515: ...mp Relay 2 Deltro Part No 20607 2 or Medtex Part No 187 32C200 87 Hydraulic Pump Gar Kenyon Part No 95380 Piper Dwg 83728 2 89 Hydraulic Pump Relay Cutler Hammer P N 6041 H200 Piper Dwg 84531 2 91 Lift Detector Safe Flight Instruments Part No 187 5 Piper Dwg 84321 93 Stall Warning Gear Warning Horn Safe Flight Instruments Part No 284 24V Piper Dwg 84321 2 95 Variable Rate Cabin Pressure Controller...

Page 516: ...re and CHT Piper Dwg 84007 Turbine Inlet Temperature Gauge T I T Piper Dwg 84007 Flight Hour Meter F W Hobbs Corp Part No 15051 Piper Dwg 51006 0 Piper Dwg 84327 2 Cabin Pressure Rate of Climb Indicator Piper Dwg 83778 Avionics Equipment King KX 165 Nav Comm With Glide Slope Piper Dwg 84386 a Single b Dual King KX 165 Nav Comm Without Glide Slope Piper Dwg 84386 King KT 76A Transponder Piper Dwg 8...

Page 517: ... Servo Bracket and Sector 1 9 302 0 574 j Roll Servo Bracket 1 5 174 4 262 k Pitch Trim Servo Bracket 0 8 245 5 196 I Kl 525A H S I tt 3 9 113 4 442 m KMT 112 Magnetic Flux Detector 0 2 310 0 62 n KA 518 Slaving Acce _ ory 0 2 116 9 23 o KG I02A Remote Directional Gyro 4 3 270 0 1161 Piper Dwg 84395 2 157 No I Comm Antenna Dorne Margolin Part No DMC 70 1 Piper Dwg 84365 2 1 2 161 4 194 159 No 2 Co...

Page 518: ...Dwg 83780 2 207 Pneumatic Shut Off Valve Aero Space Controls Corp Part No 2431TIOO I Piper Dwg 83780 2 209 Ram Air Selector Valve Piper Dwg 83928 2 211 Cabin Temperature Control Valve Piper Dwg 83800 2 213 Tank Aux Vacuum Airesearch Part No 131358 2 Piper Dwg 83778 2 215 Cabin Pressure Outflow Valve Airesearch Part No 103638 5 Piper Dwg 83778 2 217 Cabin Pressure Safety Dump Valve Airesearch Part ...

Page 519: ...lnstl Piper Dwg 83940 5 d Dual Alternator Bus Power lnstl Piper Dwg 84301 4 e Dual Alternator Eng Harness lnstl Piper Dwg 84515 5 f Dual Alternator lnstl Piper Dwg 84125 3 g Heated Windshield Electrical lnstl Piper Dwg 84576 2 h Windshield Deice System Instl Piper Dwg 83325 2 I Heated Prop Electrical lnstl Piper Dwg 84573 2 J Prop Heat System lnstl Piper Dwg 83980 2 k Ice Light Electrical lnstl Pi...

Page 520: ...per Dwg 83940 5 c Right Panel Gyro Instruments Connections f Piper Dwg 83940 6 259 Pitot Static System for Copilot s Instruments Piper Dwg 82233 5 Not Flt in Known Icing Equipped or 82233 7 Flt in Known Icing Equipped 261 Quartz Chronometer Astro Tech LC 2 Piper f Dwg 84295 Exchange Std Equipment 263 Quartz Chronometer Astro Tech LC 6 Piper Dwg 84295 Exchange Std Equipment 265 King KRA IOA Radar A...

Page 521: ...S and with G S Piper Dwg 84407 6 5 8 112 9 655 d With G S rack and connector Piper Dwg 84296 i 2 7 112 l 303 283 King KN 72 VOR LOC Converter Piper Dwg 84296 1 3 269 8 351 285 King KN 63 DME Inst Piper Dwg 84388 6 X 4 8 2 16 4 1039 287 King KFC 150 Autopilot Piper Dwg 84395 4 a Kl 256 Flight Director ti 3 3 113 6 375 b KC 192 Computer Controller 2 5 111 8 280 289 King KR 87 ADF Opt Second ADF W KA...

Page 522: ...cking Gas Cap Assys 2 Piper Dwg 39824 2 335 Relief Tube Instl Piper Dwg 84979 2 337 Carpet Runner Instl Piper Dwg 84763 4 or 5 339 Pilots Control Wheel Mike Button Only 341 Pilots Boom Mike W Control Wheel Button a Telex 5 x 5 Mark 11 P N 62629 343 Copilots Microphone Telex P N IOOT 345 Copilots Boom Mike W Control Mike Button and KAP 150 KFC 150 A P Switches a Telex 5 x 5 Mark 11 P N 62629 Inerti...

Page 523: ...ther by entering the Program Mode and entering rlashes into Channel O or alternately may be entered from the Direct Tune Mode To select frequencies in this mode the MHz oortion of the frequency displayed in tlie STANDRY window may be incremented or decremented in 1 MHz steos by rotatinq the MHz nob either clockwise or counterclockwise MHz frequencies will roll over or roll under at each banrl erlq...

Page 524: ... information pull the 25K MEM knob out and rotate it until the desired channel number appears in the USE window The channel number will be displayed for approximately two 2 seconds after which the USE window wi l display the active frequency The frequency programmed into the channel selected will be displayed in the STANDBY winda aod may be transferred to the Use window by pressing the transfer bu...

Page 525: ...ote rnounted 110mentary contact switch To use this feature the radio must first be n the Channel Modi of ooeratiori oeoress1nq tile recnote channel increment button will t hen ca4se the radio to i c re111ent fhrouqn t1 1e rile111orj cnannels Channels will roll over from 9 to O Any ctianneLi r eviousbY ore gr ed with dashes f i ffl be skiooed and wilt not be displayed Rev 3 Sept ember 1983 IM0035 5...

Page 526: ...ru 1 1 11 JV lot r r1 V _ t 1 t 11 t r Ji 1 n er k JU 9 i 1 1 1 o f 1 J i l i a 1 r ur cl IJOf i i 1 i r 11 J n n 1 _ 1 J l I il n c 9 1 Ji n i 11 l JHr J l i l III 1 t 1 1 l 1t ric J r1 T o t r c t O l tr 1 1 r I I 11 9 3 1 IC U I I j tl 11S I 1 _ _I _I _1 COMM _ STA OBY m J I IJ v 3 September 1983 0035 5 PULL OH HST FIGURE 3 2 PROGRAM MOOE MEMORY MOOE MEMORY 0 PROGRAMMED TO UUU Page 3 4 ...

Page 527: ...o nes Contact LightSPEED if yours does not low frequency ambient sound It functions with a Push ON Push OFF motion A green flashing light indicates ON f Battery Status Indicator When the active circuitry is ON the LED button will flash green When battery power falls to I0 capacity for powering the ANR circuit the LED button will change to flashing red indicating you have 2 hours or less of battery...

Page 528: ...justable GAIN pot It is preset at our facility for optimal performance Should you need to adjust the output contact LightSPEED Aviation Inc T HREE YEA R LIMITED WARRANTY TO O RIGINAL PURCHASER The LightSPEED QFRXCc Aviation Headset is guaranteed against malfunction due to defects in materials and workmanship for a period of 3 years beginning at the date of original purchase If such a malfunction o...

Page 529: ...or DEALER CODE WORK ORDER I REFERENCE SELLING AGENCY IF OTHER THAN INSTALLER CHIBf AIRCKA fl AWHONl CS iNCo Grants Pass Airport 130 l Brookside Blvd Grants fass OR 97526 ORMATION MANUFACTURER IJ w_ MODEL R WARRANTY START DATED I M I Y AIRCRAFT HOURS NEW RETROFIT DEMO SPARE l l l l MODEL NO PART NO FOR FACTORY USE ONLY AEA STANDARD FORM 1002 7 90 INSTALLATION DATED I M I Y r FIXED BACKUP RESERVE l ...

Page 530: ...0 r 1 INCORPORATEO PWR XMT ___ 0 N 0 F F ISO 1 ALL Volume Push Squelch PM3000 M u T E High fidelity Stereo Intercom System Pilot s Guide Part Number 11931 11932 FAA TSO CSOc Also includes 11933 11934 non FAA TSO units 202 193 0001 Revision 2 January 2004 Flying never soundedso goodna ...

Page 531: ...e pilot copilot and passengers the option to listen to music during flight During intercom or aircraft radio reception this music will automatically mute to allow communications 202cl93 0001 2 PM3000 Pilot Guide User Manual E GINEERING 1 INCORPORATED without distraction When the activity ceases the Soft Mute circuit gradually returns the music to the original listening volume By depressing the Mut...

Page 532: ... circuit each for the pilot copilot and passengers Only the microphone ac tually in use is open reducing noise in the system With the engine running set the squelch control knob by slowly ro tating the squelch control knob clockwise until you no longer hear the background noise in the earphones When the microphone is positioned properly near the lips normal speech levels should open the channel Wh...

Page 533: ...s shop and author ized PS Engineering dealer Ifthe unit is being installed by a non certified indi vidual in an experimental aircraft a factory mac le harness must be used for the war ranty to be valid PS Engineering Inc warrants this product to be free from defect in material and workmanship for a period ofone year from the date ofinstallation During this one year warranty period PS Engineering I...

Page 534: ...ts ofthis manual without notification ofany person or agency The contents ofthis pilot s guide may be downloaded stored and reprinted for personal use provided that this copyright information is included Commercial use is strictly prohibited For further information contact the Publications Man ager at PS Engineering Inc 9800 Martel Road Lenoir City TN 37772 Phone 865 988 9800 202_ 193 0001 8 PM300...

Page 535: ...ones refierase al manual separado Pour l installatioa et les raccotdements se referer au manuel separe DIGITAL AUDIO INSTRUCTIONS MANUAL DE INSTRUCCIONES MANUEL D INSTRUCT ONS For customer Use Enter below the Model No and Serial No which are iocated en the top or bottom of the cabinet Retain this information for future reference Model No J S 0 Serial No I 09K 1 3 t 16 GET0171 001 B J ...

Page 536: ...rase Ifa CD is in the unit it will eject when you reset the unit Be careful not to drop the CD Thank you for purchasing a JVC product Please read all instructions carefully before operation to ensure your complete understanding and to obtain the best possible performance from the unit I ow to reset your unit 2 SOUND ADJUSTMENTS 12 How to use the MODE button 3 Adjusting the sound 12 LOCATION OF THE...

Page 537: ...low the power automatically comes 011 You do not have to press this button to tum on the power elect the source d To operate the tuner FM or AM see pages 6 8 To operate the CD see pages 9 11 3 Adjust the volume To increase the volume a FU tr UL Volume level indicator see page 16 To decrease the volume Volume level appears rb 20 T 4 Adjust the sound as you want see pages 12 14 To drop the volume in...

Page 538: ...s If you hold down the button the frequency keeps changing in 200 kHz intervals for FM and 1okHz for AM until you release the button When am fM stereo broadcast is hard to receive 1 Press MODE to enter the functions mode while listening to an FM stereo broadcast 2ass MO monaural while still in the functions t IJde so that the MO indicator lights up on the display Each time you press the button the...

Page 539: ...for the preset statlo you want to 8 MO 10 11 RPT 12 RND Insert a disc into the loading slot The unit turns on draws a CD and starts playback _ automatically Jiil Nate an One Touch Operation When a CD is already in the loading slot pressing CD turns on the unit and starts playback automatically The CD in indicator flashes I CD I nn TI LU J 1 CD Total playing time of the inserted disc Elapsed playin...

Page 540: ...e playing a CD I 2 Press AND Random while still in the functions mode so that the AND indicator lights up ori ti le display Each time you press the button CD random play mode turns on and off alternately MODE 12 RND RND indicator I J When the random play is turned on the AND indi cator lights up on the display A track ran ly selected starts playing To play backtracks repeatedly Repeat Play You car...

Page 541: ...t a sound mode it is stored in memory It will be recalled every time you select the same source and will be shown on the display A sound mode can be stored for each of the following sources FM1 FM2 FM3 AM and CD If you do not want to store the sound mode separately for each playback source but want to use the same sound mode for all the sources see Canceling Advanced SCM SCM LINK on page 15 Select...

Page 542: ...ears on the display 2 Set the hour fT Select CLOCK H if not shown on the display WAdjust the hour mt A it V 3 Set the minute TI Select CLOCK M 1 Adjust the minute m t rn o o o _ it 0 4 Press SEL Select to finish the setting To check the current clock time changing the display mode Press DISP repeatedly Each time you press the button the display mode changes as follows During tuner operation Freque...

Page 543: ...e car detaching or attaching the control panel be c not to damage the connectors on the back of the control panel and on the panel holder Detaching the control panel Before detaching the control panel be sure to turn off the power J Unlock the control panel 2 Lift and pull the control panel out of the unit e 3 Put the etached control panel Into the case provided Attaching the control panel 1 Inser...

Page 544: ...ons about labels and printable discs carefully _ CD RWs Rewritable cannot be played back on this unit CAUTIONS Do not insert 8 cm 3 3 16 discs single CDs into the loading slot Such discs cannot be ejected 0 Do not insert any disc ofunusual shape like a heart orflower otherwise it will cause a ma function 0 Do not expose discs to direct sunlight or any heat source or place them in a place subject t...

Page 545: ... kg 2 9 lbs excluding accessorif_ Design and specifications are subject to change without notice If a kit is necessary for your car consult your telephone directory for the nearest car audio speciality shop l J FONCTIONNEMENT DE BASE J 3 M se soil As tension 1 Mettez l appareil sous tension I I m Remarque sur le tonctionnement monotouche Quand vous choisissez tuner comme source a l etape 2 ci dess...

Page 546: ...trequence continue de changer par intervalle de 200 kHz pour la bande FM et de 10 kHz pour la bande AM jusqu a ce que vous la relachiez Quand une emission FM stereo est difficile arecevoir 1 Appuyez sur MODE pour entrer en mode de fonction pendant l ecoute d une station FM 7a Jpuyez sur MO monaural pendant le mode fonction de fagon que l indicateur MO s allume sur l affichage Chaque fois que Yous ...

Page 547: ...0 11 APT 12 AND FONCTIONNEMENT DU LECTEUR CD l e Lecture d un CD lnserez un disque dans la fente d insertion L appareil se met en marche tire le CD et commence la lecture automatiquement Remarque sur le fonctionnement monotouche Si w1 CD se trouve deja dans lafeme d i11sertion appuyer sur CD met l appareil sous tension et nee la lectllre a1110111atiquement L indicateur de presence de CD clignote C...

Page 548: ...leatoire 1 Appuyez sur MODE pour entrer en mode de tonction pendant l ecoute d un CD 2 Appuyez sur AND aleatoire pendant le mode de fonctions de tai on que l indicateur AND s allume sur l affichage Chaque fois que vous appuyez sur la touche le mode de lecture aleatoire de CD se met alternativement en et hors service MODE 12 RND m Quand le lecture aleatoire est en se l indicateur AND s allume sur l...

Page 549: ... source Vous pouvez choisir et memoriser un ajustement dt A specifique pour chaque source de lecture S vance Selection et memorisation des modes sonores Une fois que vous avez choisi un mode sonore ii est memorise If est rappele et apparaitsurl affichage chaque fois que vous choisissez la meme source Un mode sonore peut etre memorise pour chacune des sources suivantes FM1 FM2 FM3 AM et CD Sivous n...

Page 550: ... les heures L1J Choisissez CLOCK H s il n apparait pas sur l affichage WAjustez les heures mc t 3 Reglez les minutes mChoisissez CLOCK M g_ Ajustez les minutes m 4 Appuyez sur SEL selection pour terminer le reglage Pour verifier l heure actuelle de l horloge modification du mode d affichage Appuyez sur DISP repetitivement Chaque fois que vous appuyez sur la touche le mode d affichage change comme ...

Page 551: ...place du panneau de commande faites attention de ne pas endommager les connecteurs situes al arriere du panneau et sur le porte panneau Comment detacher le panneau de commamle Avant de detacher le panneau de commande assurez vous de mettre l appareil hors tension II Deverrouillez le panneau de commande 2 Levez et tirez le panneau de commande de l appareil 3 Mettez le panneau de commande detache da...

Page 552: ...s et les precautions sur les etiquettes et les disques imprimables Les CD AW reinscriptibles ne peuvent pas litre reproduits sur cet appareil AITENTION N inserezpas des disques de 8 3 3 16 pouces CD single dans la fente d insertion De tels disques ne peuvent pas etre ejectes J N inserezpas des disque avec uneforme inhabituelle comme le creurd unefleur cela pourraitcauser un mauvaisfonctionnement N...

Page 553: ...nse en frequence 40 Hz a15 ooo Hz Separation stereo 35 dB Rapport de synch onisation 1 5 dB liunerAM Sensibilite 20 µV Seleettvife 35 dB SECTION LECTEUR CD Type lecteur de disque compact Systeme de detection de signal capteur sans contact optique semiconduteur laser Nombre de canaux 2 canaux stere9 A Reponse en frequence 5 Hz a20 ooo Hz W Plage dynamique 90 dB Rapport signal sur bruit 95 dB P leur...

Page 554: ...y US RESIDENTS ONLY Having TROUBLE with operation Please reset your unit Refer to page of How to Reset Still having trouble USA ONLY Call 1 800 252 5722 http www jvc com We can help you JVC l I 11A VICTOR COMPANY OF JAPAN LIMITED llS EN SP FR 2003 VICTOR COMPANY OF JAPAN LIMITED 1103KKSFLEJEIN ...