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Piper SARATOGA II HP PA-32R-301, Pilot Operating Handbook

The Piper SARATOGA II HP PA-32R-301 Pilot Operating Handbook is a comprehensive manual that provides essential information for operating this high-performance aircraft. Download the manual for free from manualshive.com to ensure safe and efficient flights. Get all the necessary guidelines and procedures at your fingertips for a seamless flying experience.

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Summary of Contents for SARATOGA II HP PA-32R-301

Page 1: ...c REPORT VB 1669 FAA APPROVED BY C DATE OF APPROVAL JUNE 30 1997 PETER E PECK D O A NO S0 1 THE NEW PIPER AIRCRAFT INC VERO BEACH FLORIDA FAA APPROVED IN NORMAL CATEGORY BASED ON CAR 3 THIS HANDBOOK...

Page 2: ...S HAND BOOK IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED ON THE FACE OF THE TITLE PAGE SUBSEQUENT REVISIONS SUPPLIED BY PIPER MUST BE PROPERLY INSERTED REPORT VB 1669 II Published by PUBLICATIONS DEP...

Page 3: ...ER 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 CRITERI...

Page 4: ...ide margin of the page opposite revised added or deleted material A line along the outside margin of the page opposite the page number will indicate that an entire page was added Black lines will indi...

Page 5: ...vised Para 7 17 Aug 10 1998 9 8 Revised Section 3 Date Rev 2 v Added Rev 2 to L of R page q f c k PR981218 9 i Revised T of C Peter E Peck 9 39 Added page 9 40 Added page Dec 18 1998 Date Rev 3 v Adde...

Page 6: ...Rev 4 to L of R page t k Revised T of C Added pages and ChristinaL Mars Supplement 8 Nov 22 1999 Date Added Rev 5 to L ofR page Revised Para 2 25 Revised Para 3 5 Revised Para 3 5 Revised Para 3 27 Re...

Page 7: ...dded pages thru and Supplement 15 9 92 9 93 Added pages thru and Supplement 16 9 98 9 99 Added pages thru and Supplement 17 9 102 Rev 7 VI a Added Rev 7 to L of R PR010705 2 3 Revised Para 2 7 2 4 Rev...

Page 8: ...re 5 37 Moved info to page 8 1b and revised para 8 1 Added page and revised para 8 1 G Added page and moved info from pages 8 1 and 8 2 Moved info to page 8 1b and Albert J Mill revised para 8 3 Revis...

Page 9: ...ons Added page and Rev 12 to L of R Added page Revised para 8 19 Revised Section 1 Added Rev 13 to L of R Revised para 4 5 Revised para 4 5 Revised para 4 7 Revised para 4 7 Revised para 7 15 Revised...

Page 10: ...d Date Added Rev 16 to L of R Revised para 7 23 Revised T of C _ Added pages and Supplement 22 Linda J Dicken July 11 2005 Added Rev 17 to L of R Moved info from page 9 111 Revised Section 2 Linda J D...

Page 11: ...vised Supplement title 9 140 Revised Section 1 9 146 Revised Section 3 9 147 Revised Section 3 9 148 Revised Section 5 9 149 Revised Table 1 9 150 Revised Section 7 9 152 Revised Section 7 9 153 Revis...

Page 12: ...LOT S OPERATING HANDBOOK LOG OF REVISIONS Revision Number and Revised Code Pages REPORT VB 1669 vi f FAA Approved Description of Revisions Signature and Date ISSUED JUNE 30 1997 REVISED JANUARY 16 200...

Page 13: ...SECTION 4 NORMAL PROCEDURES SECTION 5 PERFORMANCE SECTION 6 WEIGHT AND BALANCE SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS SECTION 8 AIRPLANE HANDLING SERVICING AND MAINTENANC...

Page 14: ...TillS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 ISSUED JUNE 30 1997 viii...

Page 15: ...r en m mO Z t m j O rz...

Page 16: ...oduction 1 1 1 3 Engine 1 3 1 5 Propeller 1 3 1 7 Fuel 1 4 1 9 Oil 1 4 1 11 Maximum Weights 1 5 1 13 Standard Airplane Weights 1 5 1 15 Baggage Space 1 5 1 17 Specific Loading 1 5 1 19 Symbols Abbrevi...

Page 17: ...PA 32R 301 SARATOGA II HP THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 ISSUED JUNE 30 1997...

Page 18: ...ining 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 sho...

Page 19: ...PA 32R 301 SARATOGA II HP Wing Area sq ft Min Turning Radius ft from pivot point to wing tip I 78 3 0 0 3 6 6 T7 1 _t _ __f 1 I II REPORT VB 1669 1 2 I l I II I II t 1 11 1 I THREE VIEW Figure 1 1 II...

Page 20: ...e PROPELLER a Number of Propellers b Propeller Manufacturer c Blade Model d Number of Blades e Hub Model f Propeller Diameter inches 1 Minimum 2 Maximum g Propeller Type ISSUED JUNE 30 1997 SECTION 1...

Page 21: ...7 102 100 Green or IOOLL Blue Aviation Grade Refer to latest revision of Lycoming Service Instruction 1070 12 Refer to latest issue of Lycoming Service Instruction 1014 c Oil Viscosity per Average Amb...

Page 22: ...ARD 100 SECTION GENERAL 3600 3600 3615 AFf 100 Refer to Figure 6 5 for the Standard Empty Weight and the Useful Load 1 15 BAGGAGE SPACE a Compartment Volume cubic feet b Entry Width inches c Entry Hei...

Page 23: ...Knots Ground Speed is the speed of an airplane relative to the ground Indicated Airpseed is the speed of an aircraft as shown on the airspeed indicator when corrected for instrument error lAS values...

Page 24: ...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 fi ight speed at which the airp...

Page 25: ...emperature obtained either from inflight temperature indications or ground meteorological sources adjusted for instrument error and compressibility effects The number actually read from an altimeter w...

Page 26: ...Segment ISSUED JUNE 30 1997 The demonstrated ratio of the change in height during a portion of a climb to the horizontal distance traversed in the same time interval The demonstrated crosswind veloci...

Page 27: ...multiplied 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...

Page 28: ...ght plus optional equipment Weight of occupants cargo and baggage Differe nce between takeoff weight or ramp weight if applicable and basic empty weight Maximum weight approved for ground maneuver It...

Page 29: ...SECTION 1 GENERAL I PA 32R 301 SARATOGA ll HP THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 1 12 ISSUED JUNE 30 1997...

Page 30: ...rn em lOo i 1 oO zz rnl...

Page 31: ...d Indicator Markings 2 2 2 7 Power Plant Limitations 2 3 2 9 Power Plant Instrument Markings 2 4 2 11 Weight Limits 2 4 2 13 Center ofGravity Limits 2 5 2 15 Maneuver Limits 2 5 2 17 Flight Load Facto...

Page 32: ...PA 32R 301 SARATOGA II HP THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 2 ii ISSUED JUNE 30 1997...

Page 33: ...and equipment which require handbook supplements can be found in Section 9 Supplements 2 3 AIRSPEED LIMITATIONS SPEED Never Exceed Speed VNE Do not ex ceed this speed in any operation Maximum Structu...

Page 34: ...ding Gear Extension Speed VLO Do not exceed this speed when extending the landing gear Maximum Landing Gear Retraction Speed VLO Do not exceed this speed when retracting the landing gear Maximum Landi...

Page 35: ...ne Maximum red line f Fuel Grade minimum grade g Number of Propellers h Propeller Manufacturer i Propeller Hub and Blade Model j Propeller Diameter inches Minimum Maximum k Blade Angle Limits Low Pitc...

Page 36: ...Head Temperature Not required equipment Green Arc Normal Operationg Range 200 to 500 F 500 F Red Radial Line Maximum e Fuel Flow Pressure Normal Operating Range f Vacuum Pressure Green arc normal ope...

Page 37: ...ered and inboard tapered section It is the responsibility of the airplane owner and the pilot to insure that the airplane is properly loaded See Section 6 Weight and Balance for proper loading instruc...

Page 38: ...a Total Capacity 107 U S GAL b Unusable Fuel 5 U S GAL The unusable fuel for this airplane has been determined as 2 5 gallons in each wing in critical flight attitudes 2 5 gallons is the total per si...

Page 39: ...PA 32R 301 SARATOGA II HP SECTION2 LIMITATIONS INTENTIONALLY LEFT BLANK ISSUED JUNE 30 1997 REPORT VB 1669 2 7...

Page 40: ...V F R I F R DAY AND NIGHT NON ICING FLIGHT WHEN EQUIPPED IN ACCORDANCE WITH FAR 91 OR FAR135 WARNING TURN OFF STROBE LIGHTS WHEN IN CLOSE PROXIMITY TO GROUND OR DURING FLIGHTTHROUGH CWUD FOG OR HAZE I...

Page 41: ...UP DOWN Adjacent to upper door latch rear door 110KIASMAX 132KIASMAX ENGAGE LATCH BEFORE FLIGHT In full view of the pilot SECTION2 LIMITATIONS DO NOT EXCEED 23 INCHES OF MANIFOLD PRESSURE BELOW 2100 R...

Page 42: ...FORMANCE On the inside of the forward baggage compartment MAXIMUM BAGGAGE THIS COMPART MENT 100 LBS SEE THE LIMITATIONS SECTION OF THE AIRPLANE FLIGHT MANUAL On aft baggage closeout MAXIMUM BAGGAGE TH...

Page 43: ...t to fuel tank filler caps SECTION2 LIMITATIONS AVGAS ONLY GRADE 100LL In full view of the pilot GRADE 100 ARMRESTS ARE TO BE IN THE STOWED POSITION FOR TAKEOFF AND LANDING ISSUED JUNE 30 1997 REVISED...

Page 44: ...right hand side ofofconsole top REPORT VB 1669 2 12 MONITOR ALL LOOSE ITEMS AND CONSOLE TOP ARE TO BE IN THE STOWED POSITION FOR TAKEOFF AND LANDING MAXIMUM WEIGIIT ALLOWABLE ON THE CONSOLE TOP IN TH...

Page 45: ......

Page 46: ...Loss of Oil Pressure 3 4 Loss of Fuel Flow 3 4 Engine Driven fuel pump Failure 3 4 High Oil Temperature 3 5 Electrical Failures 3 5 Electrical Overload 3 5 Propeller Overspeed 3 6 Emergency Landing Ge...

Page 47: ...3 23 Engine Driven fuel pump Failure 3 14 3 25 High Oil Temperature 3 14 3 26 Electrical Failures 3 14 3 27 Electrical Overload 3 15 3 29 Propeller Overspeed 3 16 3 31 Emergency Landing Gear Extension...

Page 48: ...the 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...

Page 49: ...open Electric fuel pump OFF Fuel selector OFF Abandon if fire continues ENGINE POWER LOSS DURING TAKEOFF If sufficient runway remains for a normal landing leave gear down and land straight ahead gea e...

Page 50: ...r power off landing POWER OFF LANDING Trim for 83 KIAS Locate suitable field Establish spiral pattern 1000 ft above field at downwind position for normal landing approach When field can easily be reac...

Page 51: ...ld be the determining factor for action in such an emergency LOSS OF OIL PRESSURE Land as soon as possible and investigate cause Prepare for power off landing LOSS OF FUEL FLOW Electric fuel pump ON F...

Page 52: ...FF Reduce electrical loads to minimum ALT circuit breaker check and reset as required ALT switch ON If alternator output not restored ALT switch OFF If alternator output cannot be restored reduce elec...

Page 53: ...oad condition is present and battery charge load is normal ALT switch OFF Electrical load reduce to minimum BAT switch as required Land as soon as possible Anticipate complete electrical failure The L...

Page 54: ...ear selector GEAR DOWN POSITION Iflanding gear still does not check down and locked Landing Gear Pump Circuit Breaker PULL I Emergency gear knob PULL while fish tailing airplane under normal condition...

Page 55: ...pen the door will trail slightly open and airspeeds will be reduced slightly To close the door in flight Slow airplane to 90 KIAS Cabin vents close Storm window open Ifdoor latch is open pull on armre...

Page 56: ...l the fire into the engine 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...

Page 57: ...power loss If no fuel flow is indicated check the tank selector position to be sure it is on a tank containing fuel When power is restored move the alternate air to the CLOSED position tum OFF the ele...

Page 58: ...Excess altitude 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...

Page 59: ...e cabin vents should be opened and the cabin heat turned OFF A landing should be made as soon as possible If an engine fire is present switch the fuel selector to OFF close the throttle and move the m...

Page 60: ...f other indications of actual oil pressure loss such as sudden increases in temperatures or oil smoke are apparent and an airport is not close Ifengine stoppage occurs proceed with Power Off Landing 3...

Page 61: ...oper baffle seals a defective gauge or other causes Land as soon as practical at an appropriate airport and have the cause investigated A steady rapid rise in oil temperature is a sign of trouble Land...

Page 62: ...battery charge load persists turn the battery master switch OFF and land as soon as practical All electrical loads are being supplied by the alternator If the electrical overload condition is present...

Page 63: ...emergency extension procedure is performed for training purposes If the landing gear does not check down and locked reduce the airspeed to below 90 KIAS Move the landing gear selector to the DOWN pos...

Page 64: ...armrest while moving the latch handle to the latched position 3 37 ENGINE ROUGHNESS Engine roughness may be caused by dirt in the injector nozzles induction filter icing or ignition problems First adj...

Page 65: ...SECTION3 EMERGENCY PROCEDURES PA 32R 301 SARATOGA II HP THIS PAGE INTENTIONALLY LEFTBLANK REPORT VB 1669 3 18 ISSUED JUNE 30 1997...

Page 66: ...w I a z 0 w 2 0 0 a l J ll IJ a 0 z...

Page 67: ...Cold Engine 4 6 Normal Start Hot Engine 4 7 Engine Start When Flooded 4 7 Starting With External Power Source 4 7 Warm Up 4 8 Taxung 4 8 Ground Check 4 8 Before Takeoff 4 9 Takeoff 4 9 Climb 4 10 Cru...

Page 68: ...mb 4 23 4 25 CruiSing 4 23 4 27 Approach and Landing 4 25 4 29 Go Around 4 26 4 30 After Landing 4 26 4 31 Stopping Engine 4 26 4 33 Parking 4 26 4 35 Stalls 4 27 4 37 Turbulent Air Operation 4 27 4 3...

Page 69: ...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 check list which...

Page 70: ...lane and equipment atmospheric conditions and piloting technique a Best Rate of Climb Speed gear down flaps up 85 KIAS gear up flaps up 93 KIAS b Turbulent Air Operating Speed See Subsection 2 3 134 K...

Page 71: ...no fire hazard exists before starting engine Fuel strainer drain check for water sediment Control wheel release restraints Gear Handle down Parking brake set Avionics OFF All switches OFF Mixture idl...

Page 72: ...drain and check for water sediment and proper fuel Tie down and chock remove Main gear strut proper inflation 4 00 25 in Tire check Brake block and disc check 1 Fresh air inlet clear NOSE SECTION Bagg...

Page 73: ...emove cover holes clear Landing light check Wing tip and nav strobe lights check Aileron and hinges check Flap and hinges check Static wicks check secure FUSELAGE Antennas check Static Vents clear Emp...

Page 74: ...an engine start stop the engine and determine the trouble In cold weather it will take a few seconds longer to get a positive oil pressure indication NOTE Starter manufacturers recommend that starter...

Page 75: ...CE CAUTION It is possible to use the ship s battery in parallel by turning only the battery master switch ON This will give longer cranking capabilities but will not increase the amperage Care should...

Page 76: ...ing check GROUND CHECK Parking brake set Propeller full INCREASE Throttle 2000 RPM Magnetos max drop 175 RPM max diff 50 RPM IVacuum Check within normal operating range Oil temperature check Oil press...

Page 77: ...belts securely fastened Mixture set Propeller set Flaps set Trim _ set Controls free Doors latched Air conditioner OFF TAKEOFF NORMAL TECHNIQUE Flaps retracted Trim set Accelerate to 84 to 88 KIAS dep...

Page 78: ...ic fuel pump OFF at desired altitude CRUISE Power set per power table Mixture adjust APPROACH AND LANDING Fuel selector proper tank Seats Adjusted Locked Seat backs erect Belts harness fasten adjust E...

Page 79: ...sired Electric Fuel Pump OFF Strobe Lights OFF Landing and Taxi Lights as required STOPPING ENGINE CAUTION The flaps must be placed in the up position for the flap stop to support weight Passengers sh...

Page 80: ...ECTION4 NORMAL PROCEDURES PA 32R 301 SARATOGA II HP MOORING Parking brake set Flaps full up Control wheel secured with belts Wheel chocks in place Tie downs secure REPORT VB 1669 ISSUED JUNE 30 1997 _...

Page 81: ...he fuel strainer When the fuel tanks are full it will take approximately six seconds to drain all the fuel in one of the lines from a tank to the fuel strainer If the fuel tanks are less than full it...

Page 82: ...fuel has been drained to verify the proper fuel and insure that all water and sediment is removed The fuel system should be drained daily prior to the first flight and after each refueling CAUTION Wh...

Page 83: ...l tank vent should be clear of obstructions Place a container under the quick drain Drain enough fuel to verify the proper fuel and to insure that all water and sediment has been removed Remove tie do...

Page 84: ...uld be limited to three minutes maximum to avoid damaging the heating elements When all passengers are on board the pilot should check the cabin doors for proper closing and latching procedures The re...

Page 85: ...to the desired setting Check for proper oil pressure indication If the engine does not fire within five to ten seconds disengage the starter and reprime b NORMAL START Hot Engine Open the throttle app...

Page 86: ...xternal power the master switch should be OFF Verify the battery master and alternator switches are OFF magneto switches are ON and all electrical equipment is OFF Insert the plug of the 24 volt power...

Page 87: ...up or taxiing over ground containing loose stones gravel or any loose material that may cause damage to the propeller blades 4 15 TAXIING Before attempting to taxi the airplane ground personnel shoul...

Page 88: ...SECTION4 NORMAL PROCEDURES PA 32R 301 SARATOGA II HP THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 4 20 ISSUED JUNE 30 1997...

Page 89: ...ete range to check for proper operation and then placed in full INCREASE rpm for takeoff To obtain maximum rpm push the pedestal mounted control fully forward on the instrument panel Do not allow a dr...

Page 90: ...re and propeller control levers should be set Fasten the seat belts snugly around the empty seats Exercise and set the flaps and trim tab Insure proper flight control movement and response All doors s...

Page 91: ...visibility over the nose during the climb Upon reaching a safe altitude the electric fuel pump may be turned off 4 25 CRIDSING The cruising speed is determined by many factors including power setting...

Page 92: ...and require cleaning There are no mechanical uplocks in the landing gear system In the event of a hydraulic system malfunction the landing gear will free fall to the gear down position The true airsp...

Page 93: ...used during approach and landing and the speed of the aircraft at contact with the runway should be varied according to the conditions of wind and aircraft loading It is generally good practice to con...

Page 94: ...flaps must be placed in the UP position for the flap step to support weight Passengers should be cautioned accordingly The air conditioner should be turned OFF the propeller set in the full INCREASE...

Page 95: ...to determine if the horn is actuated 4 37 TURBULENT AIR OPERATION In keeping with good operating practice used in ail aircraft it is recommended that when turbulent air is encountered or expected the...

Page 96: ...e owner and pilot to determine that the airplane remains within the allowable weight vs center of gravity envelope while in flight For weight and balance data refer to Section 6 Weight and Balance 4 4...

Page 97: ...lOw 0 z i 0 a t Wffi UJil...

Page 98: ...SECTIONS Paragraph Page No No 5 1 General 5 l 5 3 Introduction Performance and Flight Planning 5 1 5 5 Flight Planning Example 5 3 5 7 Performance Graphs 5 9 List of Figures 5 9 ISSUED JUNE 30 1997 R...

Page 99: ...PA 32R 301 SARATOGA II HP TIDS PAGE INTENTIONALLY LEFT BLANK REPORT VB 160o 5 ii ISSUED JUNE 30 1997...

Page 100: ...y 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 th...

Page 101: ...tory engine cooling has been demonstrated for this model aircraft to an Outside Air Temperature OAT of ISA 22 C for a standard day This is not to be considered as an operating limitation Reference sho...

Page 102: ...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 of gravity position After proper utilization...

Page 103: ...r the takeoff and or the barrier distance The landing distance calculations are performed in the same manner using the existing conditions at the destination airport and when established the landing w...

Page 104: ...ime 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 21 Now subtract the values obtained...

Page 105: ...flight plan The values obtained by proper utilization of the graphs for the descent segment of the example are shown below 1 Time to Descend 12 min minus I min 11 min 2 Distance to Descend 28 nautical...

Page 106: ...e e 2 divided by e 4 217 nautical miles divided by 154 KTS 7 Cruise Fuel e 5 multiplied by e 6 16 5 GPH multiplied by 1 41 hrs t Total Flight Time 217 nautical miles Economy 154 KTAS 16 5 GPH 1 41 hr...

Page 107: ...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 1 Tot...

Page 108: ...offPerformance Flaps 25 5 16 5 13 Maximum Effort Takeoff Ground Roll Flaps 25 5 17 5 19 Maximum Rate of Climb 3600 lbs Gross Weight 5 19 5 21 Fuel Time and Distance to Climb 5 21 5 23 Power Setting Ta...

Page 109: ...SECTIONS PERFORMANCE PA 32R 301 SARATOGA ll HP TillS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 5 10 ISSUED JUNE 30 1997...

Page 110: ...PA 32R 301 SARATOGA II HP TEMPERATURE CONVERSION Figure 5 1 ISSUED JUNE 30 1997 SECTION 5 PERFORMANCE REPORT VB 1669 5 11...

Page 111: ...PRESSURE ALTITUDE VS OUTSIDE AIR TEMPERATURE TEMPERATURE f 80 60 40 20 0 20 40 60 80 100 120 Go Go Go Go Go Go v v 1 6 ir o o 0 o Cl Cl Cl Cl Cl Cl 70 60 50 40 30 20 10 0 10 20 30 40 50 REPORT VB 1669...

Page 112: ...0 a E I 0 co 0 0 I 0 N 0 0 0 0 Cll 0 0 co r l f 033dSl IIV 03J VM811VO AIRSPEED SYSTEM CALIBRATION ALL FLAP DEFLECTIONS Figure 5 3 0 0 I 0 Cll 0 co 0 r 0 I 0 Ill 0 0 C 0 N 0 0 0 0 Cll 0 CQ 0 r 0 0 0...

Page 113: ...city is 17 knots Not a limitation EXAMPLE Wind velocity 30 knots Angle between flight path and wind 30 HeadWind component 26 knots Crosswind component 15 knots t 1 ANGLE BETW EEN FLIGHT AND WIND DEGRE...

Page 114: ...ww mww lL a a omen W __ __ __ 9 Zen en w a 0 i w I I I I 0 0 1 I 00 19 19 I I I I I I I I I I I I SVI I 033dS 11VlS SECTIONS PERFORMANCE 0 0 0 lt 0 0 0 c 1 0 0 en w w 0 t9 w 0 I z Ill LL 0 w _J t9 z...

Page 115: ...86 3400 85 85 I 3300 84 84 1 3200 82 82 1 3100 81 81 I NORMAL PROCEDURE TAKEOFF PERFORMANCE l I EXAMPLE PRESS ALTITUDE 1200Ff OAT 16 C GROSS WEIGHT 3480 LBS WIND lOKNOTHEADWIND ttC r l TAKE OFF DISTAN...

Page 116: ...1 1 1 I 1 1 t2i v NORMAL PROCEDURE TAKEOFF GROUND ROLL I r IL l J ffi I 1 o I I I _l I I _L EXAMPLE PRESS ALTITUDE 1200 FI OAT 16 C GROSS WEIGHT 3480 LBS WIND I0 KNOT HEADWIND TAKE OFF GROUND ROLL 218...

Page 117: ...Y RUNWAY LIFTOFFI BARRIER SPEED 71 76 KIAS 6000 HwT LBS jTAKE oFF SPEED KIAS t l t t l I n A nt ncn r I j lliiOO 6 t oo _ I 1 I oo r 1 N cl 4000 I 0 00 0 5000 17 I 1 1 3000 0 A U a ffi of 0 z lL _ 1 I...

Page 118: ...o 1 I L 1 i t 1 I r ISL 1 l 1 1 I I I MAXIMUM EFFORT TAKEOFF GROUND ROLL FLAPS25 I Q l 1 t1l I 1 t1l u v iE 1 L J I j L I It r 1 I I I EXAMPLE PRESS ALTITUDE 1200 FT OAT 6 C GROSS WEIGHT 3480 LBS WIND...

Page 119: ...SECTIONS PERFORMANCE REPORT V 1669 PA 32R 301 SARATOGA II HP INTENTIONALLY LEFT BLANK ISSUED JUNE 30 1997...

Page 120: ...c ooc 20 c 40 c FT SL 1582 1305 1057 806 1000 1467 1204 968 734 2000 1368 1111 892 662 3000 1256 1019 805 579 4000 1159 934 725 509 5000 1062 843 645 434 6000 967 754 568 366 7000 866 665 490 299 800...

Page 121: ...SECTIONS PERFORMANCE REPORT VB 1669 5 20 PA 32R 301 SARATOGA II HP INTENTIONALLY LEFT BLANK ISSUED JUNE 30 1997...

Page 122: ...OAT PRESSURE ISA 10 o C ISA ISA 10 a C ALTITUDE FROM SEA LEVEL FT TIME FUEL DIST TIME FUEL DIST TIME FUEL DIST MIN GAL NM MIN GAL NM MIN GAL NM SL 0 0 0 0 0 0 0 0 0 1000 1 1 1 1 1 1 1 1 2 2000 2 1 3...

Page 123: ...8 22 3 21 7 20 2 19 8 19 3 22 4 22 0 21 4 20 0 19 5 19 1 21 2 19 7 19 2 18 8 19 4 19 0 18 5 19 0 18 7 18 3 18 0 NORMAL HIGH RPM SPEED 2200 2300 2400 2500 2700 28 0 n2 26 5 25 9 27 0 27 6 26 9 26 2 25...

Page 124: ...z D E o S iim a a o a J ECI E 1 2 0 2 w1l 0 l _l I I T 0 0 0 0 0 0 0 0 0 N 0 I 0 ICJ 0 J ly 0 1 N I 1 I 1 I 1 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 Ol 0 r Ill L l apnm1v amssaJd It 0 I 1 0 0 0 C SECTION...

Page 125: ...8 1i a u o5 c E t E t a E a 0 C l 0 1 1 1 1 1 l 1 1 1 1 I 1 g E ce E 0 0 0 0 0 0 0 0 0 0 0 0 10 C 1 T T T en GJ uc5 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 J co 1 0 10 1 1 apnm1v amssa...

Page 126: ...0 0 C 1 v 0 Q Q Q 1 I lu Ic t 0 I 1 q 0 1 I 1 r t i t r I 1 1 I I 1 a u 0 5 E Ul ca i _ I E I 8 CD C E s f l l od w 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 C 1 0 CJ OJ 0 I q...

Page 127: ...II N u o r I 1 I 1 I 1 l 1 I I 1 0 8 go cl I ci E I I a D cu I CD Do 2 E G 2 0 oo 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 II co PA 32R 301 SARATOGA HP r 1 1 r 1 1 0 0 0 0 0 0 0 0 0 0 0 0 II N 0 0 0 0 0 co...

Page 128: ...uJ taxi takeoff climb and descent 102 gal uasble fuel 3600 lb gross wt SA zero wind o G lA IGE NO RESERVE J I l l 1 WI l I J Ii 900 500 o 0 y ow 1 HI H P D I 600 700 BOO I I I I 1 900 1000 RANGE NAUTI...

Page 129: ...P ENDURANCE I I LlN R t E E ll 0 y N I AL 5 6 ASSOCIATED CONDITIONS Endurance includes climb and desceni I02 gal uasble fuel 3600 lb gross wt SA zero wind L N Jl N E NO RESERVE HI H 5P D 7 3 4 ENDURAN...

Page 130: ...I 11 I I I 0 o I I 0 0 I I I I o o I o o_ I J 3 fl_ OUTSIDE AIR TEMPERATURE c il Cruise pressure altitude 6000 ft noollnotlnn outside air temp 6 c airport Pressure altitude 400 ft airport outside air...

Page 131: ...J 0 1 M If II rn wm c IL J I Oo a a o Q CD _ If N c M II I t a t d ell II 0 0 0 0 REPORT VB 1669 5 28 0 0 0 0 PA 32R 301 SARATOGA II HP II w s O J u i ct z I w w Cl w Q z Ill z Cl a ct a ow c Cl w z 5...

Page 132: ...ination O A T 24 C Landing weight 3300 lbs approach speed 79 KIAS Wlnd 5 Knots headwind Landing distance 1460 ft Ill I 40 30 20 10 0 10 20 30 40 OUTSIDE AIR TEMPERATURE C APPROACH SPEED KIAS 80 79 78...

Page 133: ...ssu _ Q oQQ 1o o Example Destination pressure altitude 400 H Destination O A T 24 C Landing weight3300 lbs Wind 5 knots headwind Landing Ground Roll 600 fl 40 30 20 10 0 10 20 30 40 OUTSIDE AIR TEMPE...

Page 134: ...PA 32R 301 SARATOGA II HP SECTIONS PERFORMANCE INTENTIONALLY LEFT BLANK ISSUED JUNE 30 1997 REPORT VB 1669 5 31...

Page 135: ...SECTIONS PERFORMANCE REPORT VB 1669 5 32 PA 32R 301 SARATOGA II HP INTENTIONALLY LEFT BLANK ISSUED JUNE 30 1997...

Page 136: ...l m io l j 0 z oO m...

Page 137: ...1 General 6 1 6 3 Airplane Weighing Procedure 6 2 6 5 Weight and Balance Data and Record 6 5 6 7 General Loading Recommendations 6 9 6 9 Weight and Balance Determination for Flight 6 10 Equipment Lis...

Page 138: ...PA 32R 301 SARATOGA II HP TillS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 6 ii ISSUED JUNE 30 1997...

Page 139: ...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 f...

Page 140: ...seful load Note that the useful load includes usable fuel baggage cargo and passengers Following this is the method for computing takeoff weight and e G 6 3 AffiPLANE WEIGHING PROCEDURE At the time of...

Page 141: ...position and all control surfaces in the neutral position Tow bar should be in the proper location and all entrance and baggage doors closed 6 Weigh the airplane inside a closed building to prevent er...

Page 142: ...Basic Empty Weight Center of Gravity 1 The following geometry applies to the PA 32R 301 airplane when it is level Refer to Leveling paragraph 6 3 b C G Ann o 1 78 4 t 1 B 1 A 14 2 B 109 7 Level Point...

Page 143: ...r the 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 factor...

Page 144: ...asic Empty Weight 2412 4 86 2662 Moment ln Lbs 208108 6 0 0 208108 6 The standard empty weight includes full oil capacity and 5 0 gallons of unusable fuel AIRPLANE USEFUL LOAD NORMAL CATEGORY OPERATIO...

Page 145: ...escription of Articl e d llJ llJ Date 5 or Modification d 0 d s C H 07 08 04 As licensed 1J r l 1 1 r l 0 C 0 1 a e a l 1 0 Registration Number N3101Q Weight Change Wt Arm Moment Lb In 100 Page Number...

Page 146: ...tion of Article d Q Date Q 5 or Modification o 0 CC s CPl 1 l C l Cj l J Cj 0 7JJ 7JJ 0 l J 0 t l w 0 1 Ia Ia l Registration Number Weight Change Wt Arm Moment Lb In 100 Page Number Running Basic Empt...

Page 147: ...elope Without aft baggage fuel may be limited by fwd envelope for some combinations of optional equipment d 4 Occupants 2 in front 1 in middle I in rear Load rear baggage compartment first Baggage in...

Page 148: ...sponsibility of the pilot in command to make sure that the airplane always remains within the allowable weight vs center of gravity while in flight 6 9 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT a Ad...

Page 149: ...of this sample loading problem is at 92 6 inches aft of the datum line Locate this point 92 6 on the C G range and weight graph Since this point falls within the weight C G envelope this loading meets...

Page 150: ...is at inches aft of the datum line Locate this point on the C G range and weight graph Since this point falls within the weight C G envelope this loading meets the weight and balance requirements Take...

Page 151: ...32R 301 SARATOGA II HP SECTION6 WEIGHT AND BALANCE tf l Q g 600 550 s 250 s150 1 100 0 6 5 30 40 45 50 55 60 6 MOMENT 1000 POUNDS INCHES LOADING GRAPH Figure 6 13 ISSUED JUNE 30 1997 REPORT VB 1669 6...

Page 152: ...NVELOPE 88 87 8 85 84 1 I 8 7 81 801 7i 78J Ill _ I 0 t I I I 78 80 82 84 86 88 90 92 94 C G LOCATION INCHES AFT DATUM C G RANGE AND WEIGHT Figure 6 15 93 94 St5 I 3600 I 3400 I 3200 I 3000 I 2800 f 1...

Page 153: ...rnu Pm I o_ _ mo z Q j...

Page 154: ...Engine Instrument Engine Monitoring System Landing Gear Flight Controls Fuel System Electrical System Vacuum System Instrument Panel Pitot Static System Cabin Features Baggage Area Heating and Ventila...

Page 155: ...PA 32R 301 SARATOGA II HP THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 7 ii ISSUED JUNE 30 1997...

Page 156: ...l parts the cowling and the lightweight plastic extremities tips of wings tail fin and stabilator etc the basic airframe is of aluminum alloy Aerobatics are prohibited in this airplane since the struc...

Page 157: ...rtical stabilizer an all movable horizontal stabilator and a rudder make up the empennage The stabilator incorporates an anti servo tab which provides longitudinal stability and longitudinal trim This...

Page 158: ...ary through the filter induction source should always be used for takeoffs The fuel injection system consists of a servo regulator which meters fuel flow in proportion to airflow to the engine giving...

Page 159: ...ow RPM The mixture control lever is used to adjust the air to fuel ratio The engine is shut down by the placing of the mixture control lever in the full lean position In addition the mixture control h...

Page 160: ...SECTION PA 32R 301 SARATOGA II HP DESCRIPTION OPERATION CONTROLQUADRANTANDCONSOLE Figure 7 1 ISSUED JUNE 30 1997 REPORT VB 1669 7 5...

Page 161: ...SECTION7 DESCRIPTION OPERATION PA 32R 301 SARATOGA II HP THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 7 6 ISSUED JUNE 30 1997...

Page 162: ...r digital display of the analog instruments engine power electrical system status outside cabin air temperature and fuel management The DDMP displays its information on 6 eight character displays whic...

Page 163: ...exceedence display will continue until the select switch is depressed The red annunciator light will remain illuminated until the parameter is no longer in exceedence If multiple exceedences occur the...

Page 164: ...tal Display Green Red Annunciator Light 11 __ Propeller RPM RPM Oil Temperature 01 and II __ Oil Pressure OP Green Red Annunciator Light lllumlnates Red at 5 usable Gal or Less Left and Right Fuel Qua...

Page 165: ...2 4 flashes second sensor failure ALARM INST MODE FU LEC 8 SELECT TOACK 0 461 CHT TEMP I EXCD PWR Figure 2 ALARM INST MODE FUE LEC SELECT I TOACK 0 CHT FAIL TEMP I EXCD PWR Figure 3 TOP LEVEL OPERATI...

Page 166: ...allons maximum usable fuel and allows the pilot to decrease the fuel loading to lower fuel loading values if desired PARTIAL defaults to 0 gallons and allows the pilono increase the fuel loading value...

Page 167: ...is based on fuel used since last usable fuel load entree FUEL MANAGEMENT DISPLAY 2 FUEL INST MIG 1s EC TODEST GAL D ATDEST TEMP I EXCD GAL PWR Figure 6 MIG Nautical miles gallon of fuel This calculat...

Page 168: ...quence through the appropriate analog instruments and choose the display parameter This process would be repeated until all 6 DDMP windows are configured The default DDMP instrument configuration afte...

Page 169: ...s Display of exceedences is accomplished by placing the rotary knob on EXCD The DDMP will display the most resent exceedence in the format shown in figure 9 Additional exceedence records can be viewed...

Page 170: ...Quantity PERCENT POWER DISPLAY PWR The percent power mode initially displays current cruise power output in 5 increments manifold pressure engine RPM fuel flow and EGT see Figure 11 Any engine powers...

Page 171: ...low using best power 50 F rich of peak EGT leaning procedures If a different engine RPM is desired the Select button is pressed to navigate to the RPM window and the Up Down arrows used to vary the RP...

Page 172: ...N LEC 72F D OtrrSIDE TE P I EXCD 6SF PWR Figure 13 DDMP MAINTENANCE MODE The maintenance mode provides maintenance operations System Self Test and time of day date adjustment functions to the operator...

Page 173: ...ment the numbers to the desired setting using the Up Down arrows This procedure of pressing Select to activate the adjacent digit pairs and incrementing using Up Down arrows is repeated until the new...

Page 174: ...mited ASCII format for each of the following parameters Parameter Units Propeller RPM RPM Manifold Pressure In Hg Exhaust Gas Temperature op Cylinder Head Temperature op Fuel Flow Gal Hr Oil Temperatu...

Page 175: ...l with spring assist on the nose gear into the extended position where the mechanical locks engage If a gear system malfunction has been indicated and the EMERGENCY Gear extension system used it is re...

Page 176: ...te beeping sound in contrast to the stall warning horn which emits a continuous sound The nose gear is steerable through a 22 5 degree arc each side of center through the use of the rudder pedals As t...

Page 177: ...ALLY CLOSED NO NORMALLY OPEN 10 1c r _______ n d r 1 J b I lB1 c lEFT C NOSE c RIGHT _ oN I j I g 3 j LO lPx K ll n _ Q _SWJTa lES GEAR l l 1 NO jl ____ Ni EC j NO J J NC j NO N C NOTE II ION UP ON UP...

Page 178: ...R 0 020 DIA BLEED HOLE t SECTION7 DESCRIPTION OPERATION HIGH PRESSURE CONTROL I ERMAL RELIEF PRESSURE SWITCH GEAR DOWN EMERGENCY FREE FALL VALVE LANDING GEAR HYDRAULIC SYSTEM SCHEMATIC Aircraft equipp...

Page 179: ...ring loaded recentering device The trim control is located on the right side of the pedestal below the throttle quadrant Turning the trim control clockwise gives nose right trim and counterclockwise r...

Page 180: ...itch change in the aircraft This pitch change can be corrected either by stabilator trim or increased control wheel force When the flaps are in the retracted position the right flap is provided with a...

Page 181: ...SCRIPTION OPERATION BUSS 5AMP Flap in Transit In Annunciator Panel PA 32R 301 SARATOGA II HP r I I RELAY I L ___ I RELAY I L _______ J ELECTRIC FLAP SCHEMATIC Figure 7 10 REPORT VB 1669 7 26 ISSUED JU...

Page 182: ...ists of a bladder fuel cell that is interconnected with the inboard tank A flush fuel cap is located in the outboard tank only When using less than the standard I07 gallon capacity of the tanks fuel s...

Page 183: ...ocated under the fuselage 3 Drain the fuel strainer sump by pressing down on the lever located on the right side of the cabin on the forward edge of the wing spar housing Figure 7 13 Move the selector...

Page 184: ...OR IZOH DDMP DISPLAY EGT I FUEL FUM ANALOG GAUGf FUEL CELL FUEL F1 0tl SENSOR ENGINE DFOVEN FUEL PUMP ELECTRIC FUEL PUMP FUEL SELECTOR VALVE HOIIZON FUELQUANTITY INDICATOR 10 l I FUEL CELL FUEL SYSTEM...

Page 185: ...t visible through the filler neck in each wing is installed in the inboard fuel tank This gauge indicates usable fuel quantities from 5 gallons to 35 gallons in the ground attitude The sole purpose of...

Page 186: ...battery for starting and to back up alternator output Electrical power is supplied by a 90 ampere alternator The battery a master switch relay and an external power relay are located on the right hand...

Page 187: ...ories include the navigation lights anti collision strobe lights instrument panel lighting and cabin courtesy lights The cabin courtesy light installation consists of a light and switch above the forw...

Page 188: ...BUSS VOLTAGE ANNUNCIATOR 1 116 II UASTER SOLENOID M R VOLT VOLT REG RED Q BLUE L TO GROUND Jl CLEARANCE RELAY 2 ALT OUT SWITCH 15A BLX CRN TO ANNUNCIATOR lLTENATOR INOP STARTER ACC 4 TO BATTERY AMMET...

Page 189: ...cedures see Section 3 WARNING Anti collision lights should not be operating when flying through cloud fog or haze since the reflected light can produce spatial disorientation Strobe lights should not...

Page 190: ...tem that has remained constant over an extended period may indicate a dirty filter dirty screens possibly a sticking vacuum regulator or leak in the system Vacuum pressure which falls below approximat...

Page 191: ...9 ANN PRESSTOTEST 20 AVIONIC EQUIPMENT 21 AVIONIC EQUIPMENT 22 INTERCOMM SYSTEM 23 AVIONICEQUIPMENT COPILOf JNST OPT 24 AIRSPEED 25 TURN BANK 26 ATITUDE GYRO 27 DIRECTIONAL GYRO 28 ALTIMETER 29 VERT S...

Page 192: ...tery could result To turn ground clearance system off turn battery master on then back off Switch locations are divided between an overhead switch panel and the standard aircraft panel The engine star...

Page 193: ...make sure the pitot cover is removed A heated pitot head which alleviates problems with icing and heavy rain is installed as standard equipment The switch for pitot heat is located in the switch pane...

Page 194: ...PA 32R 301 SARATOGA II HP SECTION7 DESCRIPTION OPERATION PITOT STATIC SYSTEM Figure 7 23 ISSUED JUNE 30 1997 REPORT VB 1669 7 39...

Page 195: ...straint for the occupant Shoulder harnesses should be routinely worn during takeoff landing and whenever an inflight emergency occurs An entertainment executive console is installed aft of the co pilo...

Page 196: ...AGE AREA The airplane has two separate baggage areas each with a 100 pound capacity A 7 cubic foot forward luggage compartment located just aft of the fire wall is accessible through a 16 x 22 inch do...

Page 197: ...t and Balance Section 7 27 HEATING AND VENTILATING SYSTEM Fresh air is ducted from a vent in the forward left lower cowling to the left heater muff by a t1exible hose It is then routed to the right he...

Page 198: ...PA 32R 301 SARATOGA II HP SECTION7 DESCRIPTION OPERATION I I I Ia ffi c _ C c en c I 0 w c w lL c c w w lu c c o HEATING AND VENTILATING SYSTEM Figure 7 25 ISSUED JUNE 30 1997 REPORT VB 1669 7 43...

Page 199: ...all speeds are shown on graphs in the Performance Section The stall warning horn emits a continuous sound The landing gear warning horn is different in that it emits a 90 cycle per minute beeping soun...

Page 200: ...of the cabin Turning the control clockwise increases cooling counterclockwise decreases cooling The fan speed switch and the air conditioning ON OFF switch are inboard of the temperature control The...

Page 201: ...of the fuselage just below the stabilator leading edge and is accessible through a plate on the right side of the fuselage This plate is attached with slotted head nylon screws for ease of removal th...

Page 202: ...an impact it can be turned off by moving the ELT switch OFF Normal operation can then be restored by resetting the switch to ARM It may also be turned off and reset by positioning the remote switch to...

Page 203: ...SECTION7 DESCRIPTION OPERATION PA 32R 301 SARATOGA HP II THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 7 48 ISSUED JUNE 30 1997...

Page 204: ...en r m 0 c 2 a...

Page 205: ...Preventive Maintenance 8 3 8 7 Airplane Alterations 8 4 8 9 Ground Handling 8 5 8 11 Engine Air Filter 8 7 8 13 Brake Service 8 8 8 15 Landing Gear Service 8 10 8 17 Propeller Service 8 11 8 19 Oil R...

Page 206: ...PA 32R 301 SARATOGA II HP TillS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 8 ii ISSUED JUNE 30 1997...

Page 207: ...tallation 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 Sinc...

Page 208: ...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 servic...

Page 209: ...his 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 Ce...

Page 210: ...riate forms and all inspection procedures should be complied with by a properly trained knowledgeable and qualified mechanic at a Piper Authorized Service Center or a reputable repair shop Piper canno...

Page 211: ...ce as defined in the PARs This maintenance may be performed only on an aircraft which the pilot owns and operates and which is not used in air carrier or air taxi commercial operations service All oth...

Page 212: ...apers are in order and in the aircraft a To be displayed in the aircraft at all times I Aircraft Airworthiness Certificate Form FAA 8100 2 2 Aircraft Registration Certificate Folll FAA 8050 3 b To be...

Page 213: ...gear struts as high up on the tubes as possible Lines should be long enough to clear the nose and or tail by not less than fifteen feet and a qualified person should ride in the pilot s seat to mainta...

Page 214: ...et the parking brake first depress and hold the toe brakes and then pull back on the brake lever and depressing the knob on the handle To release the parking brake frrst depress the brake pedals and t...

Page 215: ...emove the pitot head cover before flight 7 Cabin and baggage doors should be locked when the airplane is unattended 8 11 ENGINE Am FILTER a Removing Engine Air Filter 1 Remove the upper cowling 2 Remo...

Page 216: ...brake system is filled with MIL H 5606 petroleum base hydraulic brake fluid The fluid level should be checked periodically or at every 100 hour inspection and replenished when necessary The brake rese...

Page 217: ...PA 32R 301 SARATOGA II HP SECTIONS HANDLING SERV MAINT f ISSUED JUNE 30 1997 1 I I I i I c I Cl I _ I I i BRAKE SYSTEM Figure 8 1 REPORT VB 1669 8 9...

Page 218: ...lowly and fully to allow excess air and oil to escape With the strut still compressed reinsert the valve core and pump up the strut as above In jacking the aircraft for landing gear or other service t...

Page 219: ...oil filter change is not to exceed four 4 months Lycoming Service Bulletin No 446 should also be complied with each 50 hours The following grades are required for temperatures Average Ambient Tempera...

Page 220: ...0 100LL blue 2 0 none none none 100 130 green 3 0 100 green 3 0 100 130 green 3 0 115 145 purple 4 6 none none none 1151145 purple 4 6 Grade IDOLL fuel in some overseas countries is currently colored...

Page 221: ...between each side d Draining Fuel Strainer Sumps and Lines The fuel tank sumps and strainer should be drained before the first flight of the day and after refueling to avoid the accumulation of water...

Page 222: ...sed completely and is not leaking e Draining Fuel System The bulk of the fuel may be drained by opening the individual drain on each tank The remaining fuel may be drained through the fuel strainer CA...

Page 223: ...new components it may be necessary to rebalance the wheels with the tires mounted When checking tire pressure examine the tires for wear cuts bruises and slippage 8 25 BATTERY SERVICE Access to the 24...

Page 224: ...ially heavy dirt and grease deposits it may be necessary to brush areas that were sprayed CAUTION Do not spray solvent into the alternator vacuum pump starter or air intakes 3 Allow the solvent to rem...

Page 225: ...ro switches c Cleaning Exterior Surfaces The airplane should be washed with a mild soap and water Harsh abrasives or alkaline soaps or detergents could make scratches on painted or plastic surfaces or...

Page 226: ...circular motion 5 A severe scratch or mar in plastic can be removed by rubbing out the scratch with jeweler s rouge Smooth both sides and apply wax e Cleaning Headliner Side Panels and Seats I Clean h...

Page 227: ...0 z z 0 li w 1 J 0 UJ 1 Ul...

Page 228: ...visory and Lightning Strike Advisory Data S pages II B F Goodrich Skywatch Traffic Advisory System Model SKY497 6 pages 12 B F Goodrich Aerospace WX 500 Stormscope Series II Weather Mapping Sensor 4 p...

Page 229: ...9 SUPPLEMENTS Page No 22 S TEC ADF 650D System 10 pages 9 16T 23 Avidyne FlightMax Entegra Primary Flight Multi Function Displays With The B C Specialties BC410 Standby Alternator 34 pages 9 177 REPOR...

Page 230: ...when equipped with one or more of the various optional systems and equipment not provided with the standard airplane All of the Supplements provided by this section are FAA Approved and consecutively...

Page 231: ...SECTION SUPPLEMENTS PA 32R 301 SARATOGA II HP TIDS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 9 2 ISSUED JUNE 30 1997...

Page 232: ...ion of the airplane when the optional air conditioning system is installed The information contained herein supplements or supersedes the basic Pilot s Operating Handbook and FAA Approved Airplane Fli...

Page 233: ...climb performance the air conditioner must be turned OFF manually prior to takeoff to disengage the compressor and retract the condenser door Also the air conditioner must be turned OFF manually befo...

Page 234: ...ir conditioner system or indicator bulb malfunction is indicated and further investigation should be conducted prior to flight The above operational check may be performed during flight if an in fligh...

Page 235: ...n extremely hot weather a The decrease in true airspeed is approximately 6 KTS at all power settings b The decrease in range may be as much as 55 nautical miles for the 102 gallon capacity The climb p...

Page 236: ...h Piper Drawing No 87778 3 The information contained herein supplements or supersedes the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein For...

Page 237: ...m pressure falls below 4 8 ln Hg c The auxiliary pump motor assembly and elapsed time indicator must be removed from service after 500 hours accumulated operating time or 10 years whichever occurs fir...

Page 238: ...nd electrical load approximately 15 amps on ammeter 3 Turn off auxiliary vacuum pump and verify AUX ON light extinguished b Inflight Check 1 Turn off non essential electrical equipment 2 Turn on auxil...

Page 239: ...pump is inoperative or when the system vacuum falls below the switch activation level The AUX ON section is controlled by a vacuum switch in the auxiliary pneumatic system and illuminates a blue ligh...

Page 240: ...n the center of the manifold and senses vacuum supplied to the gyros The auxiliary system vacuum switch is located on the manifold between the check valve and the auxiliary pump and senses vacuum gene...

Page 241: ...LY DRIVEN DRY AIR PUMP 4 PRESSURE SENSING SWITCHES 5 SYSTEM REGULATOR PRESS SENSING SWITCH 6 VACUUM SUCTION GAGE 7 ATT1TUDE GYRO 8 DIRECTION GYRO 9 FILTER 10 OVERBOARD VENT 11 FIREWALL t J PRIMARY SYS...

Page 242: ...tem is installed per 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 t...

Page 243: ...able signals it has been demonstrated capable of and has been shown to meet the accuracy specifications of VFR IFR en route oceanic and remote en route domestic terminal and instrument approach GPS Lo...

Page 244: ...nt approach procedures that are retrieved from the KLN 90B data base The KLN 90B data base must incorporate the current update cycle a The KLN 90B Memory Jogger PIN 006 08785 0000 dated 12194 or later...

Page 245: ...pproach operations Do not attempt approach operations in IMC prior to attaining proficiency in the use of the KLN90B A OPERATION Normal operating procedures are outlined in the KLN 90B GPS Pilot s Gui...

Page 246: ...oper selection on the presented waypoint page is necessary to provide adequate route protection on the SID STARS 4 GPS omni bearing or leg GPS CRS OBS LEG course switch annunciator Used to select the...

Page 247: ...ected manually GPS APR and ARM are white ACTV is green 7 RMI NAY presentation switch May be used to select data for presentation on the RMI either NAY 2 data from the number two navigation receiver or...

Page 248: ...en push the inner knob in and select the ACT 7 or ACT 8 page To delete or replace a SID STAR or approach select FPL 0 page Place the cursor over the name of the procedure press ENT to change it or CLR...

Page 249: ...tercepts from inside the arc WARNING Flying final outbound from an off airport vortac on an overlay approach beware of the DME distance increasing on final approach and the GPS distance to waypoint de...

Page 250: ...at a time If the destination airport is the active waypoint at the time of the instrument approach selection the active waypoint will shift automatically to the chosen IAF Checking RAIM prediction for...

Page 251: ...field or under the cursor on the FPL 0 page press CLR then ENT Fly the arc in LEG adjust the HSI or CDI course pointer with reference to the desired track value on the SUPER NAV5 page it will flash to...

Page 252: ...be restored not guaranteed by pressing the GPS APR button changing from ACTV to ARM Fly the missed approach The instrument approach using the KLN 90B may be essentially automatic starting 30 nm out wi...

Page 253: ...SECTION SUPPLEMENT 3 PA 32R 301 SARATOGA II HP TillS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 ISSUED JUNE 30 1997 9 24 12of12...

Page 254: ...al Supplement to the Bendix King 150 Series Flight Control System as installed per STC SA1572CE D An approved operational supplement is provided by Bendix King and will be revised as required by Bendi...

Page 255: ...SECTION9 PA 32R 301 SARATOGA II HP THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 9 26 ISSUED JUNE 30 1997...

Page 256: ...nformation 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...

Page 257: ...ted on aft baggage closeout No baggage allowed this compartment SECTION 3 EMERGENCY PROCEDURES No change SECTION 4 NORMAL PROCEDURES Normal operating procedures are outlined in the King KHF 950 Pilot...

Page 258: ...per the Equipment List The information contained herein supplements or supersedes the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein For limitati...

Page 259: ...it It also houses the data base card which plugs directly into the front of the unit NOTE SID s STAR s and instrument approaches apply only to the KLN 89B The data base card is an electronic memory co...

Page 260: ...e reference datum in accordance with the criteria of AC 20 138 AC 91 49 and AC 120 33 Navigation data is based upon use of only the global positioning system GPS operated by the United States NOTE Air...

Page 261: ...t are retrieved from the KLN 89B data base The KLN 89B data base must incorporate the current update cycle a The KLN 89B Quick Reference PIN 006 08787 0000 dated 5195 or later applicable revision must...

Page 262: ...ated messages SECTION 4 NORMAL PROCEDURES WARNING Familiarity with the en route operation of the KLN 89 B does not constitute proficiency in approach operations Do not attempt approach operations In I...

Page 263: ...sabled for FAF waypoints and those used exclusively in SID STARS where overflight is required For waypoints shared between SID STARS and published en route segments requiring overflight in the SID STA...

Page 264: ...the number one navigation receiver NAV 2 data from the number two navigation receiver or GPS data from the KLN 89 B GPS C PILOTS DISPLAY Left right steering information is presented on the pilot s HSI...

Page 265: ...ct a STAR if appropriate from the APT 7 page Select an approach and an initial approach fix IAF from the APT 8 page NOTES Using the outer knob select the ACT Active Flight Plan Waypoints pages Pull th...

Page 266: ...gation is TO FROM like a VOR without waypoint sequencing b NoPT routes including DME arc s are flown in LEG LEG is mandatory from the FAF to the MAP NOTE Select HOG mode for DME arc intercepts NAY or...

Page 267: ...the desired holding fix and press ENT GENERAL NOTES The data base must be up to date for instrument approach operation Only one approach can be in the flight plan at a time If the destination airport...

Page 268: ...stalled per STC SA8396SW D The information contained herein supplements or supersedes the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein For...

Page 269: ...SECTION9 SUPPLEMENT 7 PA 32R 301 SARATOGA II HP THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 9 40 ISSUED JUNE 30 1997 REVISED DECEMBER 18 1998...

Page 270: ...ceiver Global Positioning System is installed per the Equipment List The information contained herein supplements or supersedes the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual o...

Page 271: ...gnals from the GPS system satellites recover orbital data make range and Doppler measurements and process this information in real time to obtain the user s position velocity and time Provided the GAR...

Page 272: ...e AUX group sub page 2 SOFTWARE DATABASE VER C IFR enroute and terminal navigation predicated upon the GNS 430 s GPS Receiver is prohibited unless the pilot verifies the currency of the data base or v...

Page 273: ...on only Use of VNAV information for Instrument Approach Procedures does not guarantee Step Down Fix altitude protection or arrival at approach minimums in normal position to land E If not previously d...

Page 274: ...n the GNS 430 s GPS receiver appropriate to the route and phase of flight When continuing to use GPS navigation position must be verified every 15 minutes using the GNS 430 s VOR ILS receiver or anoth...

Page 275: ...data is either GPS or VLOC as annunciated on the display above the CDI key C AUTOPILOT FLIGHT DIRECTOR OPERATION Coupling of the GNS 430 System steering information to the autopilot flight director ca...

Page 276: ...final approach course is being flown it is possible that the automatic switch from GPS course guidance to localizer I glide slope course guidance will not occur It is the pilot s responsibility to ens...

Page 277: ...SECTION9 SUPPLEMENT 8 PA 32R 301 SARATOGA II HP TIDS PAGE INTENTIONALLY LEFT BLANK IREPORT VB 1669 9 48 8 of8 ISSUED JUNE 30 1997 REVISED NOVEMBER 22 1999...

Page 278: ...eiver GPS Receiver with Traffic Advisory Lightning Strike Advisory Data is installed per the Equipment List The information contained herein supplements or supersedes the Pilot s Operating Handbook an...

Page 279: ...ain the user s position velocity and time Provided the GARMIN GNS 430 s GPS receiver is receiving adequate usable signals it has been demonstrated capable of and has been shown to meet the accuracy sp...

Page 280: ...ather Data must be immediately available to the flight crew if the BF Goodrich WX 500 Stormscope or the BF Goodrich SKYWATCH Traffic Advisory System TAS is installed B The GNS 430 must utilize the fol...

Page 281: ...be available at the Final Approach Fix F Accomplishment of ILS LOC LOC BC LDA SDF MLS or any other type of approach not approved for GPS overlay with the GNS 430 s GPS receiver is not authorized G Us...

Page 282: ...knots 2 alt vs ft fpm sets altitude units to feet and feet per minute 3 map datum WGS 84 sets map datum to WGS 84 see not below 4 posn deg min sets navigation grid units to decimal minutes NOTE In so...

Page 283: ...an the GNS 430 s GPS receiver appropriate to the route and phase of flight When continuing to use GPS navigation position must be verified every 15 minutes using the GNS 430 s VOR ILS receiver or anot...

Page 284: ...30 systems Refer to the Garmin GNS 430 Pilot s Guide for detailed crossfill operating instructions D AUTOMATIC LOCALIZER COURSE CAPTURE By default the GNS 430 automatic localizer course capture featur...

Page 285: ...nditioner condenser door with throttle movement False lightning strikes cells can be cleared via the remote Stormscope clear button on the panel or using the controls on the GNS 430 GNS 530 if so equi...

Page 286: ...n TransceiverNOR ll S Receiver Global Positioning System is installed per the Equipment List The information contained herein supplements or supersedes the Pilot s Operating Handbook and FAA Approved...

Page 287: ...tain the user s position velocity and time Provided the GARMIN GNS 530 s GPS receiver is receiving adequate usable signals it has been demonstrated capable of and has been shown to meet the accuracy s...

Page 288: ...the GNS 530 self test page immediately after tum on for 5 seconds The remaining system software versions can be verified on the AUX group sub page 2 SOFTWARE DATABASE VER D IFR enroute and terminal n...

Page 289: ...ion only Use of VNAV information for Instrument Approach Procedures does not guarantee Step Down Fix altitude protection or arrival at approach minimums in normal position to land F Ifnot previous y d...

Page 290: ...than the GNS 530 s GPS receiver appropriate to the route and phase of flight When continuing to use GPS navigation position must be verified every 15 minutes using the GNS 530 s VORJILS receiver or an...

Page 291: ...T FLIGHT DIRECTOR OPERATION Coupling of the GNS 530 System steering information to the autopilot flight director can be accomplished by engaging the autopilot flight director in the NAV or APR mode Wh...

Page 292: ...S 530 with the WX 500 refer to the WX 500 Pilot s Guide and the GNS 530 Pilot s Guide Addendum for the WX 500 Stormscope interface CAUTION During activation and deactivation of the air conditioning sy...

Page 293: ...ON 6 WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance data in Section 6 of the basic Pilot s Operating Handbook SECTION 7 DESCRIPTION AND OPERATIO...

Page 294: ...odel SKY497 is installed per the Equipment List The information contained herein supplements or supersedes the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas li...

Page 295: ...ic Advisory TA The TA display indicates the relative position of an intruder when it is approximately 30 seconds from Closest Point of Approach CPA In addition all aircraft detected less than 0 55 nm...

Page 296: ...t is advised by ATC to disable transponder altitude reporting SKYWATCH must be turned OFF Operation of the SKYWATCH system requires that the SKYWATCH Pilot s Guide p n 009 10801 001 latest revision be...

Page 297: ...ilable are 6 nm and 2 nm and are selected by 1 pressing the Display Range Button To go back into Standby press the STB button The system will go to the SKY497 STANDBY screen and will not track targets...

Page 298: ...TC for guidance and if you visually acquire the traffic use normal right of way procedures to maintain separation Do not attempt maneuvers based solely on traffic information shown on the SKY497 displ...

Page 299: ...SECTION9 SUPPLEMENT 11 PA 32R 301 SARATOGA II HP TillS PAGE INTENTIONALLY LEFT BLANK I REPORT VB 1669 9 70 6 of6 ISSUED JUNE 30 1997 REVISED JUNE 12 2000...

Page 300: ...is installed per the equipment list The information contained herein supplements or supersedes the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein...

Page 301: ...activity when they reappear after clearing the screen Avoid the clusters and you ll avoid the thunderstorms In the cell display mode even a single discharge point may represent thunderstorm activity...

Page 302: ...sers Guide p n 009 11501 001 Rev A dated September 10 1997 or later appropriate revision SECTION 5 PERFORMANCE No change SECTION 6 WEIGHT AND BALANCE Factory installed optional equipment is included i...

Page 303: ...SECTION9 SUPPLEMENT 12 PA 32R 301 SARATOGA II HP TillS PAGE INTENTIONALLY LEFT BLANK I REPORT VB 1669 9 74 4 of4 ISSUED JUNE 30 1997 REVISED JUNE 12 2000...

Page 304: ...ist The information contained herein supplements or supersedes the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein For limitations procedures and p...

Page 305: ...is installed in accordance with FAA approved Piper data SECTION 2 LIMITATIONS No change SECTION 3 EMERGENCY PROCEDURES To transmit an emergency signal Mode Selection Key ALT Code Selection SELECT 7700...

Page 306: ...During normal operation with the ON mode selected the reply indicator R flashes indicating transponder replies to interrogations NOTE Mode A reply codes are transmitted in ALT also however Mode C code...

Page 307: ...er on the last active identification code will be selected In ALT mode the transponder replies to identification and altitude interrogations as indicated by the Reply Symbol Replies to altitude interr...

Page 308: ...keys 5 Press the CRSR key to confirm list selections Code Selection a Code selection is done with eight keys 0 7 that provide 4 096 active identification codes Pushing one of these keys begins the co...

Page 309: ...tracking capabilities of the ATC facility therefore care should be taken when making routine code changes Keys for Other GTX 327 Functions IDENT Pressing the IDENT key activates the Special Position...

Page 310: ...Down time is entered with the 0 9 keys CONTRAST This page is only displayed if manual contrast mode is selected in Configuration Mode Contrast is controlled by the 8 and 9 keys DISPLAY This page is on...

Page 311: ...o reset the timer to zero 5 If the GTX 327 is configured as having a squat switch installed the timer will pause automatically when the squat switch senses that the aircraft has touched down To operat...

Page 312: ...ALT when a squat switch senses that the aircraft has become airborne Also the mode will change to STBY automatically when a squat switch senses that the aircraft has touched down Additionally a delay...

Page 313: ...SECTION9 SUPPLEMENT 13 PA 32R 301 SARATOGA ll HP THIS PAGE INTENTIONALLY LEFT BLANK IREPORT VB 1669 9 84 10 of 10 ISSUED JUNE 30 1997 REVISED JANUARY 9 2001...

Page 314: ...pplement It is permitted to include the S TEC supplement in this location of the Pilot s Operating Handbook unless otherwise stated by S TEC The information contained in the S TEC supplement may super...

Page 315: ...SECTION9 SUPPLEMENT 14 PA 32R 301 SARATOGA IT HP THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 9 86 ISSUED JUNE 30 1997 REVISED JANUARY 9 2001...

Page 316: ...of S TEC System 55 55X Autopilot Model ST 536 installed in accordance with STC SA8396SW D The info nnation contained herein supplements or supersedes the basic manual For limitations procedures and pe...

Page 317: ...a Note to Normal Operating Procedures regarding altitude hold capture W F D 3 4 5 Changed Operating Limitation Item No 6 and Altitude Loss Information Changed supplement format W F D 1 3 5 10 Added S...

Page 318: ...ound or missed approach prohibited during autopilot operation 4 The autopilot must be disengaged from the aircraft controls for take offand landing 5 Flap limitations a For aircraft with mechanical fl...

Page 319: ...Switch in the OFF position c Momentarily interrupting aircraft electrical power at the battery master switch d Pulling the autopilot circuit breaker 2 Trim a In the event of a trim failure manually co...

Page 320: ...luding system description pre flight and in flight procedures refer to S TEC System 55 Pilot s Operating Handbook PIN 8747 dated 10 16 00 or later revision or S TEC System 55X Pilot s Operating Handbo...

Page 321: ...the co pilot s control wheel ELECTRIC TRIM SYSTEM The S TEC Electric Trim System is designed to accept any single failure either mechanical or electrical without uncontrolled operation resulting duri...

Page 322: ...rgency procedures listed in Section III ofthis AFMS PREFLIGHT TRIM CHECK With Trim Monitor MANUAL ELECTRIC TRIM Test Prior To Each Flight 1 Check trim circuit breaker IN 2 Trim master switch Push ON c...

Page 323: ...witch should flash simultaneously with the trim indicator in the AlP programmer 4 Conduct the same test by slowly applying aft pressure on the elevator control confirming that auto trim runs NOSE DOWN...

Page 324: ...ches as desired See Limitations Section at 110 KIAS and with the aircraft stabilized in altitude hold mode At the glide slope intercept lower the landing gear and adjust power for the desired descent...

Page 325: ...N VI WEIGHT AND BALANCE No change SECTION VII DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS No change SECTION VIII AIRPLANE HANDLING SERVICING AND MAINTENANCE No change SECTION IX SUPPLEME...

Page 326: ...The information contained herein supplements or supersedes the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein For limitations procedures and perf...

Page 327: ...es information necessary for the operation of the airplane when the S TEC ADF 650A System is installed in accordance with FAA approved Piper data SECTION 2 LIMITATIONS No change SECTION 3 EMERGENCY PR...

Page 328: ...on and note the pointer moves to 90 from its prior position Excessive pointer sluggishness wavering or reversals indicate a signal that is too weak or a system malfunction To Operate BFO OFFNOL Contro...

Page 329: ...omatic direction finding modes are navigation modes that result in pointing operation when in range station is selected The ADF mode is used with conventional nondirectional beacons and AM broadcast s...

Page 330: ...sing and holding the spring loaded self test switch while in the ADF mode will cause the bearing pointer to rotate 90 degrees from its prior position if the ADF 650 system is operating properly When t...

Page 331: ...SECTION9 SUPPLEMENT 15 PA 32R 301 SARATOGA ll HP TillS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 9 92 6 of6 ISSUED JUNE30 1997 REVISED JANUARY 9 2001...

Page 332: ...erein 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 perform...

Page 333: ...lluminated INTERCOM VOL Control ICS Adjust to desired listenffig level INTERCOM VOX voice Sensitivity Control ROTATE CONTROL knob clockwise to the middle range and then adjust as required for desired...

Page 334: ...n Off Pilot Intercom System ICS Volume 6 Pilot ICS Voice Activated VOX Intercom Squelch Level 7 Copilot and Passenger ICS Volume Control Pull out for Passenger Volume 8 Copilot Passenger VOX Intercom...

Page 335: ...elected for microphone use When a microphone is keyed the active transceiver s MIC button LED blinks approximately one per second to indicate that the radio is transmitting NOTE Audio level is control...

Page 336: ...N OFF power control and pilot s ICS volume Full CCW detent position is OFF Left Large Knob Pilot ICS mic VOX squelch level CW rotation increases the amount of mic audio VOX level required to break squ...

Page 337: ...pressing the MKR Mute button 2 H no beacon signal is received then a second button press will deselect the marker audio This operation is similar to selecting any other audio source on the GMA 340 How...

Page 338: ...mation contained herein supplements or supersedes the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein For limitations procedures and performance in...

Page 339: ...n Features also include automatic display dimming and waypoint annunciation SECTION 2 LIMITATIONS No change SECTION 3 EMERGENCY PROCEDURES No change SECTION 4 NORMAL PROCEDURES DME OPERATION DME Mode...

Page 340: ...yed in 1 nautical mile increments up to 99 9 NM then in increments of one nautical mile 2 GROUND SPEED DISPLAY KTS Displays ground speed in knots to or from VORTACIWAYPOINT up to 999 knots aircraft mu...

Page 341: ...ast channeled when HOLD was selected and will continue to display information relative to this channel Allows both the NAY 1 and NAY 2 navigation receivers to be set to new operational frequencies wit...

Page 342: ...ent List The information contained herein supplements or supersedes the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein For limitations procedures...

Page 343: ...that When an Air Traffic Control ATC clearance has been obtained no pilot in command PIC may deviate from that clearance except in an emergency unless he obtains an amended clearance Traffic informat...

Page 344: ...ed when the Function Selector ON key is selected 1 DETAILED TRANSPONDER OPERATING PROCEDURES Normal transponder operating procedures are described in the GARMIN GTX 330 Pilot s Guide PIN 190 00207 00...

Page 345: ...licensed weight and balance data in section 6 of the Airplane Flight Manual SECTION 7 DESCRIPTION AND OPERATION See the 400 500 Series Garmin Display Interfaces Pilot s Guide Addendum PIN 190 00140 13...

Page 346: ...ction Displays are 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 thos...

Page 347: ...terfacing with a pair of Garmin GNS 430 530 s and an S TEC System 55X autopilot Figure I depicts the Avidyne FlightMax Entegra Series 700 00006 0XX Primary Flight Display Figure 1 Entegra 700 00006 0X...

Page 348: ...3 Skywatch Traffic Advisory System TAS Bendix King TAS or the Ryan Traffic and Collision Alert Device TCAD system The unit is organized around logical groupings of information presented on Pages Figur...

Page 349: ...nd must be avoided 5 GPSS mode must not be used on the final approach segment of a VLOC approach ILS LOC or non GPS overlay VOR GPSS mode must be deselected i e NAV mode selected prior to the turn ont...

Page 350: ...disable the WXSOO on the GNS430 For instructions on how to accomplish this refer to the Garmin 400 Series Installation Manual p n 190 00140 02 latest revision reference Section 5 1 Configuration Mode...

Page 351: ...t is not intended as a means for navigation or flight guidance The airplane symbol is not to be used for conducting instrument approaches or departures Position accuracy orientation and related guidan...

Page 352: ...PA 32R 301 SARATOGA II HP SECTION 9 SUPPLEMENT 19 TIDS PAGE INTENTIONALLY LEFT BLANK ISSUED JUNE 30 1997 REVISED DECEMBER 12 2005 REPORT VB 1669 7 of 30 9 111 I...

Page 353: ...n Engine Instruments Refer to Engine page of MFD NOTE The Mechanical Nav Indicator OBS receives nav information directly from the No 2 nav com GPS Only VLOC information is available Maintain attitude...

Page 354: ...timeter Land as soon as practical Invalid Heading Data Indication Heading Bug and Heading Data removed and replaced with Red X s If time and conditions permit PFD Circuit Breaker PULL and RESET Mainta...

Page 355: ...by using standby gyro Maintain heading control by utilizing magnetic compass and other directional indications such as MFD MAP NAY page CAUTION High current loads in the vicinity of the magnetic compa...

Page 356: ...page of MFD NOTE The Mechanical Nav Indicator OBS receives nav information directly from the No 2 nav com GPS Only VLOC information is available Maintain attitude airspeed and heading control using st...

Page 357: ...ages will be displayed on the MFD if an exceedance is detected Check Oil Temp Check Oil Press Check CHT CheckRPM Check Manifold Pressure Iffailure occurs during takeoff Mixture Maintain full rich Prop...

Page 358: ...UTION Any power interruption will result in loss of attitude information from the PFD until the unit can be reinstated on the ground NOTE Consider using the autopilot to reduce workload Using the GPSS...

Page 359: ...owing Reduce PFD and MFD brightness as part of overall electrical system management Pitot heat unless required Airconditioner and ventilation fan if installed Landing light use sparingly Strobe lights...

Page 360: ...ain aircraft control with reference to the standby airspeed altimeter and attitude gyro indicators Battery Switch OFF Ground Clearance Switch if installed ON Land as soon as possible WARNING Compass e...

Page 361: ...nd Clearance Switch if installed ON NOTE Turning ON the ground clearance switch will activate the No I nav com GPS radio Vents OPEN Cabin Heat OFF Land as soon as practical WARNING Compass error may e...

Page 362: ...riate aircraft speed Press the fast erect button If the PFD was not able to perform fast alignment maintain aircraft control with reference to the standby instruments for aircraft attitude information...

Page 363: ...If heading systems differ by more than I0 after compass deviation applied Use Whiskey Compass for primary heading reference CAUTION High current loads in the vicinity of the Whiskey Compass can influ...

Page 364: ...a positive oil pressure indication NOTE Starter manufacturers recommend that starter cranking peri ods be limited to 30 seconds with a two minute rest period between cranking periods Longer cranking...

Page 365: ...ure Prime then idle cut off Propeller CLEAR Starter ENGAGE Mixture Full RICH Throttle ADJUST Oil Pressure CHECK Normal Start Hot Engine Throttle 12 inch open Battery Master Switch ON 1 Primary Flight...

Page 366: ...tery Master Switch ON Primary Flight Display PFD Verify correct aircraft model software Alternator Switch ON Electric Fuel Pump OFF Magneto Switches ON Mixture Idle cut off Propeller CLEAR Starter ENG...

Page 367: ...starter is engaged If cranking speed increases the ship s battery is at a higher level than the external power supply NOTE For all normal operations using external power the battery master and alterna...

Page 368: ...d VNE An altitude tape is provided to the right of the main ADI and also displays a symbol for the Altitude Preselect Altitude Bug The Vertical Speed Indicator VSI is displayed to the right of the alt...

Page 369: ...cting the display format of the navigation data and for selecting the type of compass rose and moving map to be displayed are along the left side of the PFD The active flight plan contained in the GPS...

Page 370: ...de annunciations are shown on the S TEC System 55X computer When included as part of the installation autopilot mode annunciations including autopilot ready and fail indications are provided at the to...

Page 371: ...AV on the PFD and GPSS mode is engaged on the autopilot the autopilot will track the active flight plan in GPSl if VLOCl is selected or GPS2 if VLOC2 is selected and not track VLOCl or VLOC2 as the se...

Page 372: ...cludes redundant means of display of certain aircraft flight and systems parameters Back up Altimeter Airspeed and Attitude instruments are provided to facilitate pilot cross checking of PFD display f...

Page 373: ...data on airports approaches VOR s NDB s intersections airspace definitions and frequencies North American and international databases are available Database information can be updated via the USB port...

Page 374: ...ses curved flight path segments will be depicted as straight lines The GPS navigator and HSI are to be used during approach procedures Reference the Avidyne FlightMax EX5000 Series Pilot s Guide p n 6...

Page 375: ...ocated in dedicated regions within the MFD display An Engine Sensor Unit interfaces with engine mounted sensors and provides data to the MFD for display A leaning function assists the pilot in leaning...

Page 376: ...Indicator is 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 area...

Page 377: ...ght 2 Should the RED TEST annunciator illuminate any time during the self test this is an indication that the battery pack is in need of charging or possible replacement Flight in Instrument Meteorolo...

Page 378: ...ing the end of the test NOTE A green annunciator throughout the test indicates the standby battery is sufficiently charged and should be able to function under normal operation The presence of a red a...

Page 379: ...e to the indicator symbolic airplane The 4300 4XX Electric Attitude Indicator offers the feature of a self contained standby power source Anytime aircraft power is absent selecting the STBY PWR button...

Page 380: ...installed per the Equipment List The I information contained herein supplements or supersedes the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed he...

Page 381: ...ons WARNING No determination has been made as to the capability of this system to remove or prevent ice accumulation CAUTION If ice accretions are permitted to form with the ice protection system off...

Page 382: ...w to be used in the TKS system Some fluids currently used for ground de icing purposes contain thickening agents which may block the porous panels If it is known or suspected that such a fluid has bee...

Page 383: ...id tank filler cap Fuel caution placard to be attached around the TKS fluid tank filler Placard to be fitted adjacent to porous panels T K S ICE PROTECTION CAUTION POROUS DE ICING PANELS MAY BE DAMAGE...

Page 384: ...s continued SECTION 9 SUPPLEMENT 21 Placard prohibiting flight into known icing conditions fitted on the upper control panel in front of the pilot FLIGHT INTO KNOWN ICING CONDITIONS IS PROHIBITED ISSU...

Page 385: ...propeller switch To remove ice which has been accreted select the MAX position on the airframe propeller switch until accreted ice is cleared then select OFF or NORM as required CAUTION If ice accret...

Page 386: ...pump in turbulent conditions with low tank contents NOTE In the event of loss of flow to the airframe and propeller with NORM selected normal flow may be restored by selecting MAX This procedure will...

Page 387: ...frost ON Alternate Air OPEN IImmediately exit icing conditions TKS System Select NORM NOTE If ice has already been accreted select the MAX position until accreted ice is clear then select NORM NOTE Lo...

Page 388: ...ach setting or less recommended when aircraft has encountered icing conditions Landing Distance Increase full flap landing Approach Flaps distance by 20 Airspeed Full flap approach speed 4 KIAS Approa...

Page 389: ...s Panels Check condition and security Check evidence of fluid from all panels and propeller TKS System OFF In Flight FLIGHT INTO KNOWN ICING CONDITIONS IS PROHIBITED Descent Landing Select system as r...

Page 390: ...ate of the quantity offluid on board For the purposes of weight and balance determine the true weight of fluid from the table below Gauge Volume Weight Arm Moment Reading gal lb in in lb 114 1 125 10...

Page 391: ...ls are manufactured with 0 9 mm thick titanium Titanium provides excellent strength durability light weight and corrosion resistance The panel skin is perforated by laser drilling holes 0 0025 inches...

Page 392: ...UPPLEMENT 21 SECTION 7 DESCRIPTION AND OPERATION continued Magnified View of Holes Laser Drilled Through Titanium Figure 7 2 TKS Porous Panel Cross Section Figure 7 3 ISSUED JUNE 30 1997 REVISED JUNE...

Page 393: ...icing are both minimized if the ice protection equipment is operated continuously during unexpected icing encounters The fluid passes through a microfilter prior to distribution to the porous panels...

Page 394: ...ilter roportionlng r Unit Jill Level Metering Fluid Sender Porous Panel on wing r Proportioning Unit r f _ rlh L _ V nt Finger I Drain Strainer Valve I Located In right wing Porous Panel on Stabllator...

Page 395: ...e 1 40 Q Q 2 1 20 1 c 2 1 00 1 0 c I Q 0 40 E i c 0 20 u 2 e a _ v 0 7 f t 7 I v v l 0 00 Empty 1 4 112 3 4 Full 4 25 Gals 1 1 Gals 2 1 Gals 3 2 Gals Fluid Quantity Indication PA 32 TKS System Fluid E...

Page 396: ...ge is an analog gauge located on the instrument panel just below the switch panel This display dims for night operation Contents Indicator Gauge Figure 7 6 L vel lncftcatcr C3 System Electrical Schema...

Page 397: ...quired flow when MAX is selected The system is operated with a three position switch located on the instrument panel The center position is the OFF position deactivating the TKS system The top positio...

Page 398: ...CTION 7 DESCRIPTION AND OPERATION continued Non Avidyne Aircraft Circuit Breakers TKS ICE GAUGE PROTECTID e6rr _J Avidyne Equipped Aircraft TKS System Electrical Controls Figure 7 8 ISSUED JUNE 30 199...

Page 399: ...i mark assures that a uniform distribution of fluid will pass through the porous panel regardless of airspeed and air flow angle of attack angle The reservoir also assures that when properly prepared...

Page 400: ...ditions It is difficult to quantify exact ranges but the 60 to 70 F temperature range is typically where this type of weeping occurs This is a normal characteristic for a TKS system It is not a mainte...

Page 401: ...pecified de icing fluids The filler cap is located on the right I starboard wing inboard of the fuel filler The tank has a total capa ity of 4 25 gallons To preclude the possibility of contaminated fl...

Page 402: ...e of the wing ahead of the landing gear area It is forward of the main spar The valve can be locked open by pressing into the valve stem with a screwdriver and turning the stem 1 4 turn This action wi...

Page 403: ...pump is not self priming and may require priming in the event the I TKS tank is run dry or emptied completely Once prime is established the pump will maintain the prime unless air re enters the pump...

Page 404: ...nels Only the following solvents are permitted for use on porous panels but refer to recommended procedures for cleaning exterior painted surfaces for aircraft Water with soaps or detergents De icing...

Page 405: ...n Servicing Fluid Tank Pipelines and Couplings Proportioning Unit Porous Panels Propeller and Spinner Mounted Equipment Control Switches Overhaul or Replace On condition Every 2 000 aircraft hours Eve...

Page 406: ...anels Only the following solvents are permitted for use on porous panels but refer to recommended procedures for cleaning exterior painted surfaces for aircraft Water with soaps or detergents De icing...

Page 407: ...n Servicing Fluid Tank Pipelines and Couplings Proportioning Unit Porous Panels Propeller and Spinner Mounted Equipment Control Switches Overhaul or Replace On condition Every 2 000 aircraft hours Eve...

Page 408: ...ibility that icing conditions may become so severe that his equipment cannot cope with them At the first indication that such conditions may have been encountered or may be ahead the pilot should reac...

Page 409: ...ding upon circumstances it may be advisable to increase approach and landing speeds because even with the protected regions totally clear of ice a performance degradation will occur due to ice on the...

Page 410: ...t List The information contained herein supplements or supersedes t11e Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those m eas listed herein For limitations procedures a...

Page 411: ...es information necessary for the operation of the airplane when the S TEC ADF 650D System is installed in accordance with FAA approved Piper data SECTION 2 LIMITATIONS No change SECTION 3 EMERGENCY PR...

Page 412: ...t desired station ti equency and select ANT mode Positively identify selected station or beacon Adjust volume control as required If ADF 650D System is used for navigation select ADF or BFO mode immed...

Page 413: ...rol until ADF is displayed Observe the IND 650A Indicator and note that the bearing pointer indicates the relative bearing to the station Push the TEST button while observing the indicator bearing poi...

Page 414: ...TROL TI1e BFO beat frequency oscillator mode is used to amally identify stations that employ keyed CW Carrier Wave rather than amplitude modulation techniques This mode activates the bearing pointer T...

Page 415: ...eption clarity and is normally used for station identit cation Frequency Selection Keypad The Frequency Selection Keypad is used to select the system operating frequency The keypad consists of a row o...

Page 416: ...essing the CLR button will erase the last number entry Pressing the CLR button while in the contrast function reverses the display image and also places the receiver in manual mode NOTE It is not nece...

Page 417: ...e annunciations are temporarily replaced by the text VOLUME with a horizontal till bar The filled portion of the bar indicates t11e current volume setting Contrast The contrast function is activated b...

Page 418: ...setting The brightness is adjusted by pressing the appropriate 1 and v indicators on tl1e volume control Mode Selector The mode selector is used to select one of tl1e tl1ree operating states BFO ADF...

Page 419: ...The text TEST will be displayed in the bottom right corner of the display for approximately 15 seconds During this time the IND 650A Indicator pointer will incrementally rotate 90 Press the TEST butt...

Page 420: ...ction Displays with the B C Specialties BC410 Standby Alternator is installed per the Equipment List The information contained herein supplements or supersedes the basic Pilot s Operating Handbook and...

Page 421: ...capable ofinterfacing with a pair of Garmin GNS 430 530 s and an S TEC System 55X autopilot Figure 1 depicts the Avidyne FlightMax Entegra Series 700 00006 0XX Primary Flight Display Figure 1 Entegra...

Page 422: ...L3 Skywatch Traffic Advisory System TAS Bendix King TAS or the Ryan Traffic and Collision Alert Device TCAD system The unit is organized around logical groupings of information presented on Pages Figu...

Page 423: ...alternator therefore replacing the primary alternator function but not supplementing its output The alternator is gear driven through the engine vacuum pump drive pad The standby alternator is rated...

Page 424: ...and must be avoided 5 GPSS mode must not be used on the final approach segment of a VLOC approach ILS LOC or non GPS overlay VOR GPSS mode must be deselected i e NAV mode selected prior to the turn on...

Page 425: ...disable the WXSOO on the GNS430 For instructions on how to accomplish this refer to the Garmin 400 Series Installation Manual p n 190 00140 02 latest revision reference Section 5 1 Configuration Mode...

Page 426: ...related guidance must be assumed by other means or required navigation Operators with the optional CMax Chart Page must have back up charts available Do not rely upon CMax charts as your sole source...

Page 427: ...on Engine Instruments Refer to Engine page of MFD NOTE The Mechanical Nav Indicator OBS receives nav information directly from the No 2 nav corn GPS Only VLOC information is available Maintain attitud...

Page 428: ...ltimeter Land as soon as practical Invalid Heading Data Indication Heading Bug and Heading Data removed and replaced with Red X s If time and conditions permit PFD Circuit Breaker PULL and RESET Maint...

Page 429: ...l by using standby gyro Maintain heading control by utilizing magnetic compass and other directional indications such as MFD MAP NAV page CAUTION High current loads in the vicinity of the magnetic com...

Page 430: ...page of MFD NOTE The Mechanical Nav Indicator OBS receives nav information directly from the No 2 nav com GPS Only VLOC information is available Maintain attitude airspeed and heading control using s...

Page 431: ...ges will be displayed on the MFD if an exceedance is detected Check Oil Temp Check Oil Press CheckCHT CheckRPM Check Manifold Pressure Iffailure occurs during takeoff Mixture Maintain full rich Propel...

Page 432: ...rcuit breaker check and reset as required ALTR ON If primary alternator power not restored ALTR OFF Ifprimary alternator output cannot be restored maintain an electrical load ofless than 20 amps with...

Page 433: ...rimary and standby alternator are not functioning and the battery is depleted the landing gear must be lowered using the emergency extension procedure The gear position lights will be inoperative The...

Page 434: ...hes If the standby alternator has failed or cannot provide adequate power then electrical power is dependent on available battery storage Duration of battery power available will be dependent on elect...

Page 435: ...ator loads are not reduced continued NOTE Ifthe standby alternator is not functioning and the battery is depleted the landing gear must be lowered using the emergency extension procedure The gear posi...

Page 436: ...tain aircraft control with reference to the standby airspeed altimeter and attitude gyro indicators Battery Switch OFF Ground Clearance Switch if installed ON Land as soon as possible WARNING Compass...

Page 437: ...tch OFF Ground Clearance Switch if installed ON NOTE Turning ON the ground clearance switch will activate the No 1 nav com GPS radio Vents OPEN Cabin Heat OFF Land as soon as practical WARNING Compass...

Page 438: ...ct button If the PFD was not able to perform fast alignment maintain aircraft control with reference to the standby instruments for aircraft attitude information CAUTION In case of engine failure mini...

Page 439: ...ed If heading systems differ by more than 10 after compass deviation applied Use Whiskey Compass for primary heading reference CAUTION High current loads in the vicinity of the Whiskey Compass can inf...

Page 440: ...et a positive oil pressure indication NOTE Starter manufacturers recommend that starter cranking periods be limited to 30 seconds with a two minute rest period between cranking periods Longer cranking...

Page 441: ...xture Prime then idle cut off Propeller CLEAR Starter ENGAGE Mixture Full RICH Throttle ADJUST Oil Pressure CHECK Normal Start Hot Engine Throttle lh inch open Battery Master Switch ON Primary Flight...

Page 442: ...Switch ON Primary Flight Display PFD Verify correct aircraft model software Alternator Switch ON Standby Alternator Switch ON Electric Fuel Pump OFF Magneto Switches ON Mixture Idle cut off Propeller...

Page 443: ...tch momentarily while the starter is engaged If cranking speed increases the ship s battery is at a higher level than the external power supply NOTE For all normal operations using external power the...

Page 444: ...ase electrical load to less than 20 amps STBY ALTR ON annunciator verify ON steady Throttle retard ALTR switch ON Verify normal amperage indication STBY ALTR ON annunciator verify extinguished Before...

Page 445: ...and VNE An altitude tape is provided to the right of the main ADI and also displays a symbol for the Altitude Preselect Altitude Bug The Vertical Speed Indicator VSI is displayed to the right of the...

Page 446: ...lecting the display format of the navigation data and for selecting the type of compass rose and moving map to be displayed are along the left side of the PFD The active flight plan contained in the G...

Page 447: ...ode annunciations are shown on the S TEC System 55X computer When included as part of the installation autopilot mode annunciations including autopilot ready and fail indications are provided at the t...

Page 448: ...NAV on the PFD and GPSS mode is engaged on the autopilot the autopilot will track the active flight plan in GPSl if VLOCl is selected or GPS2 if VLOC2 is selected and not track VLOCl or VLOC2 as the s...

Page 449: ...s a Jeppesen NavData database that is available for display on the Map page In conjunction with GPS supplied position information an own ship symbol is superimposed on the moving map and positioned re...

Page 450: ...sen NavData data and is available for pilot viewing on the Info page Flight plan data supplied by the GPS system provide the pilot with a tabular form of the remaining legs in the active GPS flight pl...

Page 451: ...range of weather data request Engine Instruments The Engine page provides the pilot with engine parameters depicted on simulated gauges and electrical system parameters located in dedicated regions w...

Page 452: ...monitors the aircraft electrical power bus voltage and activates the standby alternator if the bus voltage falls to less than 26 0 volts As long as the electrical load is maintained below standby alt...

Page 453: ...SECTION9 SUPPLEMENT 23 PA 32R 301 SARATOGA II HP TillS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 9 210 34 of 34 ISSUED JUNE 30 1997 REVISED OCTOBER 17 2005...

Page 454: ...i a en m z 0 z en 0...

Page 455: ...TABLE OF CONTENTS SECTION 10 OPERATING TIPS Paragraph Page No No 10 1 General 10 1 10 3 Operation Tips 10 1 ISSUED JUNE 30 1997 REPORT VB 1669 10 i...

Page 456: ...PA 32R 301 SARATOGA II HP THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1669 ISSUED JUNE 30 1997...

Page 457: ...g loads it is desirable to have the airplane at a slower speed before extending the flaps The flap step will not support weight if the flaps are in any extended position The flaps must be placed in th...

Page 458: ...operating the toe brakes h In an effort to avoid accidents pilots should obtain and study the safety related information made available in FAA publications such as regulations advisory circulars Aviat...

Page 459: ...allation Piper Drawing 101000 2 b Cabin Interior Pilot Adjustable Seat leather with headrest armrest and lumbar support Piper Drawings 78087 12 and 89026 12 Copilot Adjustable Seat leather with headre...

Page 460: ...N 62800 001 Piper Code Number 474 657 b Telex Holder PIN 64022 000 and hardware Piper Drawing 79036 023 Pilot s headset Piper drawing 79036 023 a Telex 5161A Airman 760 Headset Piper Code Number 692 2...

Page 461: ...uments part number UI5934PD 3A l34 Cert Basis D 0 86 65 83 56 58 TSO C Ob Piper PS50008 I0 2D Piper Code number 599 549 Vertical Speed United Instruments part number UI 7000 Cert Basis TSO D 0 77 66 7...

Page 462: ...C DME 451 with 450 Indicator installation Piper Drawing 101246 3 also include shelfinstallation item 141 Marketing Option 575 a S TEC DME Installation Kit PS50040 31 26 Piper Code Number 601 212 l S T...

Page 463: ...ess Bracket and Hardware Piper Drawing 104386 2 WX500 Stormscope system installation total weight b TRC 497 Skywatch System Installation Piper Drawing 104278 2 1 SKY 497 Systems Skywatch Piper Drawing...

Page 464: ...141 package options Piper Drawings 101246 003 104386 2 and 99466 026 Marketing options 340 and or 575 a Shelfassembly Piper Drawing I01253 004 Removed standard emergency locator transmitter and antenn...

Page 465: ...r Code number 683 721 b Gannin Antenna Cable and hardware Piper Drawing 101844 100 D 0 61 86 97 53 14 b Gannin GNS 430 System lastallation Dual COMINAV GPS Piper Drawing 101844 101 Cert Basis TSO 37d...

Page 466: ...tallation hardware D 0 14 64 04 9 27 Piper Drawing 101844 I03 f Avidyne Entegra Multi Function Display EX 5000 installation Piper Drawing I0I844 104 I Avidyne Entegra Multi Function Display EX 5000 Av...

Page 467: ...PS50008 10 2D United UI5934PD 3A l34 Cert Basis TSO C Ob 3 Standby attitude Indicator with battery pack option Mid Continent Part MD4300 411 Piper code 602 319 4 Standby flight instruments installatio...

Page 468: ...g 101844 101 Piper Code number 596 664 Avidyne Integrated Weather Data Link installation delta weight S TEC DME 451 with 450 Indicator installation Avidyne Entegra System 59 only Piper Drawing 101844...

Page 469: ...TRC 497 Transmitter Receiver Computer Skywatch L3 Communications PIN 805 10800 00I with Mounting Tray Assembly PIN 805 10870 001 Piper Code Number 601 223 b TRC 497 Installation K i L3 Communications...

Page 470: ...ernational PIN AMA 37781 Piper drawing 99640 Piper Code number 602 275 J Cabin Pressure tube installation Piper Drawing 99978 002 Fresh Air Blower Installation Piper Drawing 36983 18 Aft Remove Cable...

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