Piper SENECA III Pilot'S Information Manual Download

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Summary of Contents for SENECA III

Page 1: ...SENECA III PILOT S INFORMATION MANUAL Seneca lif...

Page 2: ...Published by PUBLICATIONS DEPARTMENT Piper Aircraft Corporation Issued January 8 1981 REPORT VB 1110 ii...

Page 3: ...the text of the present handbook and or to add information to cover added airplane equipment L Revisions Revisions will be distributed whenever necessary as complete page replacernents or additions a...

Page 4: ...e physical location of material on a page wil not be identified ORIGINAL PACES ISSUED The original pages issued for this handbook prior to revision are given below Title ii through vii 1 I through I I...

Page 5: ...8 Revised item 285 6 49 Revised item 29 L 7 14 Revised para 7 15 7 26 Revised para 7 23 9 i Revised Table of Contents 9 19 Added Supplement 4 thru KFC 200 Automatic Flight 9 32b Control System with Fl...

Page 6: ...11 to pg 4 16 4 16 Relocated para 4 11 from pg 4 15 moved info to pg 4 16a 4 16a New pg relocated info from pg 4 16 and 4 17 4 16b New pg relocated info and para 4 13 from pg 4 17 added Note to para...

Page 7: ...pg 4 36 moved para 4 59 to pg 4 38 4 38 New pg relocated para from pg 4 37 6 i Changed pg nos 6 I Revised fig 6 9 6 12 Revised fig 6 i 1 6 32 Relocated items 147 thru 15i from pg 6 33 6 33 Moved items...

Page 8: ...em 291 to pg 6 50 6 50 Relocated item 29 l from pg 6 49 6 62 Added new item 441 7 14 Revised para 7 15 7 15 Revised fig 7 11 7 20 Added info 7 21 Revised fig 7 15 9 46 Revised Supplement Section I 9 4...

Page 9: ...ding 5 23 Revised fig 5 25 5 26 Revised fig 5 31 pg base info 5 28 Amended fig 5 35 notation 5 29 Added grid alignment number to fig 5 37 5 30 Amended lettered info to fig 5 39 5 31 Corrected error to...

Page 10: ...89 from pg 6 49 revised item 293 data moved item 295 and 297 to pg 6 51 6 51 Relocated items 295 and 297 from pg 6 50 tevised item 301 data 6 52 Added new item 302 6 54 Revised item 315 revised item 3...

Page 11: ...ion 2 f 9 36 Revised caution note corrected pg no error 9 37 Revised section 3 d 2 9 39 Corrected error 9 4 I Revised section 4 4 9 76 Corrected pg no error 9 l10 Revised note 9 115 Revised note 9 120...

Page 12: ...nfo from pg 3 17 moved info to pg 3 19 3 19 Relocated info from pg 3 18 moved info to pg 3 20 3 20 Relocated info from pg 3 19 moved info to pg 3 21 3 21 Relocated info from pg 3 20 5 17 Revised fig 5...

Page 13: ...ted info from pg 3 23 4 l6a Revised para 4 f l 5 3 Revised para 5 5 a 6 i Revised Table of Contents 6 l Revised para 6 6 2 Revised para 6 3 6 5 Revised para 6 5 6 7 Revised fig 6 7 6 1 I Revised fig 6...

Page 14: ...9 and 5 31 5 24 Revised Figure 5 27 5 25 Revised Figure 5 29 5 26 Resised Figure 5 3l 5 27 Revised Figure 5 33 5 28 Revised Figure 5 35 6 Revised para l5 info 0 Added Caution Redsed parm 7 25 into Rev...

Page 15: ...nfo from pg 4 6 4 8 Revised procedure 4 9 Revised procedure 4 10 Revised procedure 4 16b Revised para 4 13 4 25 Revised para 4 29 4 26 Revised para 31 4 28 Revised para 4 33 7 i Revised Table of Conte...

Page 16: ......

Page 17: ...PROCEDURES 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...

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Page 19: ...No No Ll Introduction 1 1 L3 Engine 1 3 L5 Propeller 3 1 Fuel 1 4 1 9 Oil I 4 1 ll Maximum Weights 1 5 1 13 Standard Airplane Weights 1 5 1 15 Baggage Space 1 5 Ll Specific Loadings 1 5 l 9 Symbols Ab...

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Page 21: ...remaining within the operating limitations as outlined by instrument markings placards and this handbook Ahhough the arrangement of this handbook is intended to increase its m fhght capabilities it s...

Page 22: ...H T10 28 Wing Area sq ft 208 J Min Turning Radius ft 33 2 frompivot point to wingtip 6 4 90 1914T 8 10 87 1T 5 4 414 METER INEDRAL 4 43 1 84 28744 11 CENTERLME1 IN SPAltSTA 108825 STATIC GRTIllNO LINE...

Page 23: ...cubic inches 360 i Compression Ratio 7 5 1 j Engine Type Six Cylinder Direct Drive Horizontally Opposed Air Cooled 1 5 PROPELLER STANDARD ta Number of Propellers 2 b Propeller Manufacturer Hartzell c...

Page 24: ...athering L7 FUEL a Fuel Capacity LLS gal total 1 Without optional tanks 98 2 With optional tanks 128 b l able Fuel LS gat total Without optional tanks 93 2 With optional tanks 123 c Fuel I Minimum Gra...

Page 25: ...Weight lbs 4773 b Max Takeoff Weight Ibs 4750 c Max Landing Weight lbs 4513 d Max Zero Fuel Weight Ibs Std 4470 le Max Weights in Baggage Compartment Ibs I Forward 100 2 Aft 100 1 13 STANDARD AIRPLANE...

Page 26: ...speed of an airplane relative to the ground lAS Indicated Airspeed is the speed of an aircraft as shown on the airspeed indicator when corrected for instrument error lAS values published in this hand...

Page 27: ...than a 5 bank towards the operative engine takeoff power on operative engine landing gear up flaps in takeoff position and most rearward C G VNI i MNE Never Exceed Speed or Mach Number is the speed li...

Page 28: ...7 F is 0 00198 C 0 003566 F per foot and 7ero above that altitude OAT Outside Air Temperature is the free air static temperature obtained either from inflight temperature indications or ground meteoro...

Page 29: ...Exhaust Gas Temperature Gauge el Airplane Performance and Flight Planning Terminology Climb Gradient The demonstrated ratio of the change in height during a portion of a climb to the horizontal distan...

Page 30: ...to the center of gravity C G of an item Moment The product of the weight ofan item multi plied by its arm Moment divided by a constant is used to simplify balance calcu lations bv reducing the number...

Page 31: ...al Weight e4uipment Payload Weight of occupants cargo and baggage Eseful Load Difference between takeoff weight or ramp weight if applicable and basic empty weight Maximum Ramp Maximum weight approved...

Page 32: ......

Page 33: ...trument Markings 2 5 2 11 Weight Limits 2 6 2 13 Center of Gravity Limits 2 6 2 15 Maneuver Limits 2 7 2 17 Flight Maneuvering Load Factors 2 7 2 19 Types of Operation 2 7 2 2 I Fuel Limitations 2 7 2...

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Page 35: ...those given in this section and handbook Limitations associated with those optional systems and equipment which require handbook supplements can be found in Section 9 Supplements 2 3 AIRSPEED LIMITATI...

Page 36: ...speed with landing gear extended 130 I30 Maximum Landing Gear Extending Speed VLo Do not extend landing gear above this speed 130 130 Maximum Landing Gear Retracting Speed VLo Do not retract landing...

Page 37: ...umber 1 Left TSIO 360KB 2 Right LTSIO 360K B d Engine Operating Limits T O Power Max Cont 5 Min Limit Power I Rated Horsepower BHP 220 200 2 Max Rotational Speed RPM 2800 2600 3 Max Manifold Pressure...

Page 38: ...d Right 32AF32C509 P LS2NFA 6 NOTES Avoid continuous operation between 2000 and 2200 RPM above 32 lN HG manifold pres sure Avoid continuous ground operation between 1700 and 2100 RPM in cross and tai...

Page 39: ...Temperature Green Arc Normal Range 240 F to 460 F Red Line Maximum 460 F d Oil Temperature Green Arc Normal Operating Range 100 F to 240 F Red Line Maximum 240 F e Oil Pressure Green Arc Normal Opera...

Page 40: ...2 13 CENTER OF GRAVITY LIMITS Weight Forward Limit Rearward Limit Pounds Inches Aft of Datum Inches Aft of Datum 3400 82 0 94 6 4250 86 7 94 6 4750 90 6 94 6 NOTES Straight line variation between poi...

Page 41: ...owing operations when equipped in accordance with FAR 91 or FAR 135 a Day LF R b Night L F R c Day LF R d Night I F R e Icing conditions when equipped per Ice Protection System Instal lation Supplemen...

Page 42: ...rthiness Certification This aircraft model is in compliance with all FAR 36 noise standards applicable to this type 2 25 HEATER LIMITATIONS Operation of the combustion heater above 25 000 feet is not...

Page 43: ...ICING FLIGHT WHEN EQUIPPED IN ACCORDANCE WETH FAR 9 OR FAR 135 In full view of the pilot MAXIMUM TAKEOFF WEIGH T 4750 POUNDS MAXIMUM LANDING WEIGHT 4513 POUNDS ALL WEIGHT IN EXCESS OF4470 POUNDS MUST...

Page 44: ...ING IN VICINITY OF OTHER AlRCRAFT OR DURING FLlGHT THROUGH CLOUD FOG OR HAZE On the inside of forward baggage compartment door MAXlMUM BAGGAGE THlS COMPARTMENT 100 LBS SEE THE LIMITATIONS SECTlON OF T...

Page 45: ...n Gear Down Seat Backs Erect Flap Set White Arc Flaps Set Air Conditioner Off Trim Set Stab Rudder Fasten Belts Harness Controls Free Full Travel Doors Latched Air Cond Off The Air Conditioner Off ite...

Page 46: ...UST RE STOWED DDRlNG TAKFOFF AND l ANDING On the instrument panel in full t iew of the pilot 2 blade propellers only AVOID CONTINUOUSGROUNDOPERATION 1700 2100 RPM IN CROSS TAll WIND OVER 10 KT AVO1D C...

Page 47: ...4 220T SENECA IH LIMITATIONS Ad cent to fuel tank filler caps EDF1 100OR 100f I AVIAllON GRADF Adiacent to fuel tank filler caps serial nurnbers 344333042 and up I AVGAS ONLY GRADE ORADE 100LL 100 ISS...

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Page 49: ...s Removed 3 9 Electrical Failures 3 9 Gvro Suction Failures 3 10 Spins 3 10 Emergency Descent 3 f0 Combustion Heater Overheat 3 l I Open Door Entry Door Only 3 I I Propeller Overspeed 3 3 5 Amplified...

Page 50: ...gine Driven Fuel Pump Failure 3 18 3 15 Landing Gear Unsafe Warnings 3 19 3 17 Manual Extension Of The Landing Gear 3 19 3 19 Gear Up Emergency Landing 3 20 3 21 Engine Failure With Rear Cabin and Car...

Page 51: ...ce for critical situations with little emphasis on the operation of systems The remainder of the section is devoted to amplified emergency procedures containing additional information to provide the p...

Page 52: ...er on the operating engine should be reduced when safe to do so DETECTING DEAD ENGlNE Loss of thrust Nose of aircraft will yaw in direction of dead engine with coordinated controls ENGINE SECURlNG PRO...

Page 53: ...ball I 2 to I out Aux fuel pump of inop engine OFF Magnetos of inop engine OFF Cowl flaps close on inop engine as required on operative engine Alternator of inop engine OFF Electrical load reduce Fue...

Page 54: ...of aircraft weight configuration ambient conditions and speeds negative climb performance may result Refer to One Engine Inoperative Climb Performance chart Figure 5 21 ENGINE FAILURE DURING FLIGHT Be...

Page 55: ...rottle open 174 inch Mixture RICH Magneto switches ON Prop control full forward Starter engage until propeller windmills Throttle reduce power until engine is warm Aux luel pump OFF li engine does not...

Page 56: ...ing continue operating to try pulling the fire into the engine If fire continues extinguish with best available means If external fire extinguishing is to be applied Fuel selector valves OFF Mixture i...

Page 57: ...ng engine since vapor return fuel flow will be lost through the vent system LANDlNG Fuel selector operating engine ON Fuel selector inop engme OFF ENGINE DRIVEN FUEL PUMP FAILURE Throttle retard Aux f...

Page 58: ...s gear in transit Recycle gear if indication continues Light will illuminate when gear warning horn sounds at low throttle settings MANUAL EXTENSION OF LANDING GEAR Check following before extending ge...

Page 59: ...rnators OFF then ON one at a time ti alternator outputs are NOT restored Batters switch OFF Alternator switches OFF then ON one at a time li alternator outputs are NOT restored ternator switches OFF B...

Page 60: ...Altitude descend to maintain 4 5 in Hg Use electric turn indicator to monitor Directional Indicator and Attitude Indicator performance SPINS Throttles retard to idle Rudder full opposite to direction...

Page 61: ...d slightly To lose the door in flight S on airplane to 90 KIAS Cab n tents close Stor window open lf upper laich is open latch lf side latch is open pull on arrnrest while moving latch handle to latch...

Page 62: ...SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA 34 220T SENECA III THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED JANUARY 8 1981 3 12...

Page 63: ...d is 92 KlAS To feather a propeller maintain direction and an airspeed above 85 KlAS Move the mixture and propeller controls forward The throttle controls should be moved forward to maimain a safe air...

Page 64: ...e used as necessary on the operative engine The alternator of the inoperative engine should be turned OFF and the electrical load reduced to prevent depletion of the battery Move the fuel selector con...

Page 65: ...erate1092 KlAS and FEATHER the moperative engine refer to Engine Securing Proceduret WARNING ln certain combinations of aircraft weight configuration ambient conditions and speeds negative climb perfo...

Page 66: ...lNOPERATlVE GO AROUND NOTE A one engine inoperative go around should be avoided if at all possible To execute a one engine inoperative go around advance the mixture and propeller levers forward The t...

Page 67: ...erating to try to pull the fire into the engine In either case above if the fire continues longer than a few seconds the fire should be extinguished by the best available external means It an external...

Page 68: ...he tank on the same side as that engine Therefore a minimum of 30 minutes of fuelshould be used from this tank before selecting crossfeed If the tank gauge approaches FULl go back to that tank and ope...

Page 69: ...pump fails HI position The auxiliary fuel pumps have no standby function Actuation of the HI switch position when the engines are operating normally may cause engine roughness and or power loss 3 15...

Page 70: ...the throttles just before touchdown Turn OFF the battery and ignition switches and move the fuel selector valve controls to OFF Contact to the surface should be made at a minimum airspeed 3 21 ENGINE...

Page 71: ...tors at less than 60 amperes will assure that the battery will not be depleted WARNING Compass error may exceed 10 with both alternators moperative If abnormally high alternator outputs are observed a...

Page 72: ...ttery is the only remaining source of electrical power If one alternator shows zero output cycle its switch OFF and then ON If this fails to restore output check the circui t breakers The breakers may...

Page 73: ...the alternators Also anticipate complete electrical power failure NOTE Operation with the alternator ON and the battery switch OFF should be made only when required by electrical failure due to incre...

Page 74: ...ol movement should be used during recovery from the di ve as the positive limit maneu vering load factor may be exceeded NOTE Federal Aviation Admi nistration Regulations do not require spin demonstra...

Page 75: ...y open and airspeed will be reduced slightly To close the door in flight slow the airplane to 90 K IAS close the cabin vents and open the storm window If the top latch is open latch it If theside latc...

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Page 77: ...ng Engines Airplane Equipped With Optional Engine Primer System 4 6 Starting Engines When Flooded 4 7 Starting Engines in Cold Weather Airplane Equipped With Standard Engine Primer System 4 7 Starting...

Page 78: ...Starting Engines With External Power 4 21 4 25 Preheating 4 2 4 27 Warm Up 4 24 4 29 Taxiing 4 25 4 31 Before Takeoff Ground Check 4 25 4 33 Takeoff 4 27 4 35 Climb 429 4 37 Cruising 4 29 4 39 Descen...

Page 79: ...ocedures which are not the same for all aircraft Pilots should familiarize themselves with the procedures given in this section in order to become proficient in the normal operations of the airplane T...

Page 80: ...may vary from published figures depending upon the equipment installed the condition of the engine airplane and equipment atmospheric conditions and piloting technique a Best Rate of Climb Speed 92 K...

Page 81: ...TION Airplane status airworthy papers on board Weather suitable Baggage weighed stowed tied Weight and C G within limits Navigation planned Charts and navigation equipment on board Performance and ran...

Page 82: ...ce Right main gear no leaks Strut proper inflation Tire check Right wing tip check Right leading edge check no ice Fuel cap open check quantity and color secure Right engine nacelle check oit Right pr...

Page 83: ...is pulled before brake appitcation Circuit breakers in Radios OFF Con Dap OPEN Abernate air OFF Alternators ON STARTING ENGINES AIRPLANE EQUIPPED WlTH STANDARD PRIMER SYSTEM Euci selector ON Mnture FU...

Page 84: ...trol FULL FORWARD Battervswitch ON lynition switches nuags1 ON Auxiliary fuelpump OFF Prirner ON See Figure 4 3 for Priming Time Throttle Cl OSE Starter engage At temperatures below 20 E continue pnmi...

Page 85: ...Ignition switche mags ON Auxiiiary fuel pump OFF Propcuer c1car Staner engage R hen engine fires Throttle retard Mature adtance slowa ST ARTlNG ENGINES IN COLD WEATHER AIRPLANE EQUIPPED RITH STANDARD...

Page 86: ...atiers switch OFE All ekctricalequipment OFF Terminals connect External power plug insert in fuselage roCCed W b normal start Throttics lowest possible RPM External power plug disconnect from fuselage...

Page 87: ...Magnetos check max drop 150 RPM max diff drop 50 RPM Alternator output check Gyro suetion gauge 4 8 to 5 1 in Hg Throttles 800 1000 RPM Fuel selectors ON Alternators ON Engine gauges in the green Annu...

Page 88: ...MAI TAKEOFF Flaps up Brakes apply and hold Flaps UP Brakes release Accelerate to and maintain 79 KIAS Cortrol wheel ease back to rotate to climb attitude After obstacle clearance accelerate to best ra...

Page 89: ...ng gear DOWN 130 KIAS max Flaps set I15 KIAS max Approach speed 90 KIAS or above GO AROUND Full takeoff power both engines 40in Hg maximum manifold pressure Establish positive climb Flaps retract Gear...

Page 90: ...76 KlAS En route 102 KlAS Cowlflaps as required Power reducetoMCP CRUlSE CLIMB Mixture full RICH Power 75 Climb speed 102 KIAS Cowl flaps as required CREISING Power set per power table Mixture contro...

Page 91: ...ORATION SECTION 4 PA 34 220T SENECA III NORMAL PROCEDURES MOORING Parking brake as required Control wheel secured with belts Flaps full up Wheel chocks in place Tie downs secure ISSUED JANUARY 8 1981...

Page 92: ...SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA 34 220T SENECA III TH1S PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED JANUARY 8 1981 4 14...

Page 93: ...check that necessary papers and charts are on board and in order and a cornputation of weight and C G limits takeoff distance and in flight performance Baggage should be weighed stowed and tied down...

Page 94: ...o idle cut off to prevent an inadvertent start while checking the propellers Move the trim controls to neutral so that the tabs can be checked for align ment Extend and retract the flaps to check for...

Page 95: ...r and proper inflation If the tow bar was used remove and stow Before moving on to the forward baggage compartment check the condition of the landing light Open the forward baggage compartment and che...

Page 96: ...r harnesses NOTES lf the fixed shoulder harness non inertia reel type is installed it must be connected to the seat belt and adjusted to alow proper accessi bility to all controls including fuel selec...

Page 97: ...he engine starts retard the throttle and monitor the oil pressure gauge l no oil pressure is indicated within 30seconds shut down the engine and have it checked In cold weather it may take somewhat lo...

Page 98: ...priming time see Figure4 3 Close throttle and immediately engage starter With ambient temperatures above 20 F starts may be made by discontinuing priming before engaging starter With ambient temperat...

Page 99: ...TION 4 PA 34 220T SENECA III NORMAL PROCEDURES 20 0 20 40 60 480 100 AMBIENT TEM ERATURE F OPTIONAL ENGINE PRIMER SYSTEM PRIMING TIME VS AMBIENT TEMPERATURE Figure 4 3 ISSUED JANUARY 8 1981 REPORT VB...

Page 100: ...pit begin the starting procedure by moving the fuel selector to ON Advance the mixture to full RICH and the throttle and prop controls to full FORWARD Turn ON the battery switch and the ignition switc...

Page 101: ...t Turn the battery switch ON and check the alternator ammeter for an indi cation of output DO NOT ATTEMPT FLIGHT IF THERE IS NO INDI CATION OF ALTERNATOR OUTPUT NOTE For all normal operations using th...

Page 102: ...ilin the sump lines cooler filter etc Typically heat is applied to the upper portion of the engine for a few minutes after which the engine is started and normal operation is commenced The operator ma...

Page 103: ...amage ignition wiring and other components b Hot air should be applied primarily to the oil sump and filter area The oil drain plug door or panel may provide access to these areas Continue to apply he...

Page 104: ...leaks are noted preheat the engine for an additional 10 to 15 minutes before restarting 4 27 WARM UP Warm up the engines at 1000 to 1200 RPM Avoid prolonged idlingat low RPM as this practice may resul...

Page 105: ...e made before takeo L using a checklist Belare adsancing the throttic to check the magnetos and the propeller acuan be sure that the engine oil temperature is 75 F or above During engine run up head t...

Page 106: ...et the altirneter attitude indicator directional gyro and clock Set the mixtures and advance the propeller controls to the forward position The friction lock onthe right side of the control quadrant s...

Page 107: ...t on the wings Takeoff distances and 50 foot obstacle clearance distances are shown on charts in the Performance Section of this handbook The performance shown on charts will be reduced by uphill grad...

Page 108: ...and brmgtheenginestofullpower before release Release the brukes accelerate to 64 KlAS and rotate firmly so that when passing through the504oot height the airspeed is approximately 66 KIAS Retract the...

Page 109: ...emperatures within the normal ranges specified for the engine During climbs under hot weather conditions it may be necessary to use LO auxiliary fuel pump for vapor suppression Consistent operational...

Page 110: ...nitored during flight especially during night or instrument flight so that corrective measures can be taken in case of malfunction The procedures for dealing with electrical failures are contained in...

Page 111: ...determine how the fuel flow and fuel quantity gauging systems are operating If the fuel flow indication is considerably higher than the fuel actually being consumed or if an asymmetric flow gauge indi...

Page 112: ...craft should be slowed to approximately 120 KlAS and this speed should be maintained on the down wind leg The landing check should be made on the downwind leg The seat backs should be erect and the se...

Page 113: ...a smooth gradual reduction of power on final approach with the power fully off before the wheels touch the runway This gives the gear warnmg horn a chance to blow if the gear is not locked down If el...

Page 114: ...es necessary apply takeoff power to both engines not to exceed 40 in Hg manifold pressure Establish a positive climb attitude retract the flaps and landing gear and adjust the cowl flaps for adequate...

Page 115: ...ts and to allow for inadvertent speed build ups which may occur as a result of the turbulence or of distractions caused by the conditions See Subsection 2 3 4 53 FLIGHT WITH REAR CABIN AND CARGO DOORS...

Page 116: ...ned to be 66 KIAS Under no circumstances should an attempt be made to fly at a speed below this VMcA with only one engine operating As a safety precaution when operating under single engine flight con...

Page 117: ...ntrol heading and ailerons to maintain 5 bank towards the operative engine lateral attitude At the first sign of either VMCA Of SInl Warning which may be evidenced by an inability to maintain heading...

Page 118: ...all with the gear and flaps retracted may be as much as 400 feet The loss of altitude with the gear down and 40 of flaps may also be as much as 400 feet A power on stall may result in as much as 150 f...

Page 119: ...ENTS SECTION 5 PERFORMANCE Paragraph Page No No 5 I General 5 1 5 3 Introduction Performance and Flight Planning 5 1 5 5 Flight Planning Example 5 3 5 7 Performance Graphs 5 9 List of Figures 5 9 REPO...

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Page 121: ...ytically expanded for the various parameters of weight altitude temperature etc The performance charts are unfactored and do not make any allowance for varying degrees of pilot proficiency or mechanic...

Page 122: ...Example outlines a detailed flight plan using the performance charts in this section Each chart includes its own example to show how it is used WARNING Performance information derived by extrapo latio...

Page 123: ...ravity position The landing weight cannot be determined until the weight ofthe fuel to be used has been established referto item g 1 1 Basic Empty Weight 3122 lbs 2 Occupants 2 x 170 lbs 340 lbs 3 Bag...

Page 124: ...an example assume a no wind condition The effect of winds aloft must be considered by the pilot when computing climb cruise and descent performance c Climb The desired cruise pressure altitude and cor...

Page 125: ...OAT determine the basic fuel time and distance for descent Figure 5 37 These figures must be adjusted for the field pressure altitude and temperature at the destination airport To find the necessary...

Page 126: ...e information provided on Figure 5 25 The cruise time is found by dividing the cruise distance by the cruise speed and the cruise fuel is found by multiplying the cruise fuel flow by the cruise time T...

Page 127: ...lanning example 1 Total Flight Time c 3 plus d l plus e 6 0 22 hrs plus 0 22 hrs plus 1 94 hrs 2 38 hrs g Total Fuel Required Determine the total fuel required by adding the fuel to climb the fuel to...

Page 128: ...SECTIONS PIPER AIRCRAFT CORPORATION PERFORMANCE PA 34 220T SENECA III THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED JANUARY 8 1981 5 8...

Page 129: ...s 5 18 5 17 Takeoff Climb Performance Gear Extended 5 19 5 19 Takeoff Climb Performance Gear Retracted 5 20 5 21 Climb Performance Gear Retracted Maximum Continuous Power 5 21 5 23 Fuel Time and Dista...

Page 130: ...SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 34 220T SENECA HI THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED JANUARY 8 1981 5 10...

Page 131: ...ECTION 5 PA 34 220T SENECA III PERFORMANCE 40 100 90 30 80 70 20 60 50 10 40 FAHRENHEIT CELSIUS O 30 DEGREES DEGREES 20 10 10 0 20 20 30 30 40 40 TEMPERATURE CONVERSION CHART Figure 5 1 ISSUED JANUARY...

Page 132: ...SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 34 220T SENECA III AIRSPEED SYSTEM CALIBRATION Figure 5 3 REPORT VB 1110 ISSUED JANUARY 8 1981 5 12...

Page 133: ...PIPER AIRCRAFT CORPORATION SECTION 5 PA 34 220T SENECA III PERFORMANCE STALL SPEED KIAS CL 4 I STALL SPEED VS ANGLE OF BANK Figure 5 5 ISSUED JANUARY 8 1981 REPORT VB 1110 5 13...

Page 134: ...EVEL DRY RUNWAY LIFTOFF AT 79 KIAS Pressure altitude 2000 ft BARRIER AT 79 KIAS FLAPS O COWL FLAPS 2 OPEN Gross weight 3969 Ibs Headwind 9 knots Takeoff ground roll 1350 f 3000 Takevil distane over 5...

Page 135: ...PIPER AIRCRAFT CORPORATION SECTION 5 PA 34 220T SENECA III PERFORMANCE THIS FIGURE INTENTIONALLY LEFT BLANK Figure 5 9 ISSUED JANUARY 8 1981 REPORT VB 1110 5 15...

Page 136: ...LIFTOFF AT 84 KIAS BARRIER AT 86 KIAS r r FLA S 25 COWi i LAPS 1 2 OPEN Fxarnple OAT 2Pc Pressure altitude 2000 ft L Gross weight 4250 lbs Headwmd 9 Pois Takeoff groor d ro 800 ft 2000 og Takeoff dwan...

Page 137: ...79 KiAC Gross weight 3969 lbs BOTH THROTTLES CLOSED Af ENGINE FAI URE Head wmd 9 knots MAXIMUM BRAKING PAVED LFVEL DRY RUNWAY Accelerate stop distance 3260 ft COWL FLAPS 1 2 OFEN 1 1 REDUCEACCtt ME8t...

Page 138: ...f HROTTLES Ci SED AT ENGINE FAILURE SEC NO RT GNIT ON TIMF MAX1MUM SRAKiMG PAVED lEVEL DRY RUNWAY Example COWL FLAPS 172 OPEN O A T 27C roUCF ACCELERATE Lt ST P DISTANCk Pressure altitude 3000 ft Gros...

Page 139: ...OPERATING TAKEOFF POWER H LANDING GEAR EXTENDED FLAPS UP 92 KIAS MtXTURE FULL RICH COWL FLAPS 1 2 OPEN 00 LBS GROSS WE1GHT ne F ure altitude 8000 ft go O A T 10 C Rate of CI mb 1140 fpm 40 20 0 20 40...

Page 140: ...ATED CONDITIONS One engine inopera ive climb 300 f p m GRFFULSL RICH MIXTURE COWL FLAPS 1 2 OPEN ON OPERATING ENGINE S CLOSED ON 1NOPERAT1VE ENGINE o ENG NE INOPERATIVE ENGINE FEATHERED CUMB CUMB SPEE...

Page 141: ...2 ENGINE FEATHERED COWL FLAPS CLOSED OPEN MIXTURE AS NOTED 92 KiAS 92 K1AS GEAR UP WING FLAPS 0 GEAR UP WiNG FLAPS O 3 5 BANK TOWAAD OPERATING ENGINE u t MIXTURE LEANED a en or ONE ENGINE NO A I I TWO...

Page 142: ...PEED MIXTURE LEANED TO 25 F RICH OF PEAK EST ABOVE 17 000 FEET Cau pc Example Departure alvport alt 2000 ft Denarture arrport O A T 21 C Cruise alt 16500 ft Cruise O A T 13 C Fuel to climb 12 1 11 gal...

Page 143: ...PIPER AIRCRAFT CORPORATION SECTION 5 PA 34 220T SENECA IH PERFORMANCE o or og oc oc C POWER SETTING TABLE Figure 5 25 ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED FEBRUARY 25 1982 5 23...

Page 144: ...RiCH ABOVE 75 POWER MixTURE LEANED IN ACCORDANCE WITH SECTION 4 37 COWL FLAPS CLOSED GEAR UP WING FLAPS UP MID CRUISE WEIGHT 4450 LB oNo I I I I I I 3 ude 16500 ft 40 20 o 20 4o 120 140 160 180 200 OU...

Page 145: ...1000 FrM MD 145 KDs3 PL 4 2 GAL FUEL FOR STA4T TA AND O I i I so T i I I I hi DANCE i C 1Y N437 r 3F 20 000 AND FC NY DIVANC S 1 I netAGE NCAFASFS F NV fDP LAN C R O TEra J FCRFAses ooo SEA 1 EVEL 400...

Page 146: ...START TAXI AND TO Range without reserve 1010 nm wh TURE4 LEANED IN ACCORDANCE i a W1TH PROCEDURES IN SECTION 4 37 HibH SPEED 75 25 000 NOTES 95 I HANGE INCLUDES CUMB LONG RANGL M I DESCENT DISTANCES...

Page 147: ...O WIND Cruise altitude 16500 ft 4 2 GAL FUEL FOR START TAx AND T O Power 55 USABLE FUEL 93 GALi ONS 4750 LBS Endurance with reserve 338 hrs Endurance with no reserve 4 41 hrs c 20 00 55 DESCENT T MES...

Page 148: ...ND 145 KIAS NO WIND Power 55 4 2 GAL FUEL FOR START TAX1 AND TO Endurance with a rve b 38 hrs Endurance with no reserve STl IX URES LEANED N ACCORDANCF iisa sprp 1 i ROC IRES 19 SECTION 4 U ___ Dit r...

Page 149: ...PLAPS ur No enND I i Mt 1 6500 ft Enose O A T 13 C 00 y I Deenaton all 3000 ft I Desonacon O A T 22 C Fue i d scened 6 1 5 l min 4000 Distance to descend 4a 7 37 n m STAT 2000 SEA LEVEL i 4 9 40 30 20...

Page 150: ...RAKING Example 2000 O A T 22 C 30 as 4 82 76 Pressure altitude 3000 ft 2600 Gross weight 3655 lbs Head wind 10 knots 2400 Landing ground roll 1120 ft Total lavrlinr stietance war Wh ha r er Dann ft no...

Page 151: ...UNWAY MAXIMUM BRAKING xample 3000 O A T 22 C Pressure altitude 3000 ft BA S D As Gross weight 3655 es r Headwind 10 knots ci Landing ground roll 1120 ft TotaHanding distance over 50 ft barr er 1880 ft...

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Page 153: ...Brakes 6 22 d Electrical Equipment 6 23 e Instruments 6 26 f Miscellaneous 6 28 g Propeller and Propeller Accessories Optional Equipment 6 29 h Engine and Engine Accessories Optional Equipment 6 30 i...

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Page 155: ...have Center of gravity is a determining factor in flight characteristics If the C G is too far forward in any airplane it may be difficult to rotate for takeoff or landing If the C G is too far aft t...

Page 156: ...ul load Note that the useful load includes usable fuel baggage cargo and passengers Following this is the method for computing takeoff weight and C G 6 3 AIRPLANE WEIGHING PROCEDURES At the time of li...

Page 157: ...ding to prevent errors in scale readings due to wind b Leveling 1 With airplane on scales block main gear cleo pistons in the fully extended position 2 Level airplane referto Figure 6 3 deflating nose...

Page 158: ...ARM 78 4 Level Points Fuselage Left Side Below Window N R L A The datum is 78 4 inches ahead of the BA 0538 wing leading edge at the inboard edge of the mboard fuel tank LEVELING DIAGRAM Figure 6 3 2...

Page 159: ...number and registration number shown The basic empty weight of the airplane as licensed at the factory has been entered in the Weight and Balance Record Figure 6 7 This form is provided to present the...

Page 160: ...standard empty weight includes full oil capacity and 5 0 gallons of unusable fuel AlRPLANE USEFUL LOAD NORMAL CATEGORY OPERATlON Ramp Weight Basic Empty Weight Useful Load 4773 lbs lbs lbs THIS BASIC...

Page 161: ...PIPER AIRCRAFT CORPORATION SECTION 6 PA 34 210T SENECA III WEIGHT AND BALANCE WEIGHT AND BALANCE RECORD Figure 6 7 ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 9 1982 6 7...

Page 162: ...SECTION 6 PIPER AIRCRAFT CORPORATION WElGHT AND BALANCE PA 34 220T SENECA 111 WEIGHT AND BALANCE RECORD cont Figure 6 7 cont REPORT VB lll0 ISSUED JANUARY 8 1981 8...

Page 163: ...e Load rear baggage compartment to capacity first Baggage in nose inay be limited by forward envelope Without aft baggage fuel may be limited by forward envelope for some combinations of optional equi...

Page 164: ...e Loading Graph Figure 6 13 to determine the moment of all items to be carried in the airplane c Add the moment of all items to be loaded to the basic empty weight moment d Divide the total moment by...

Page 165: ...eoff Weight 14250 lbs Max 4750 93 9 446102 The center of gran C G of this sample loading problem is at 939 inches aft of the datum hoe Locate tha point 93 9 on the C G range and weight graph Since thi...

Page 166: ...f gravity C G for the takeoff weight ofthe actual load ng proMem is at inches aft of the datum line Locate this point on the CG range and weight graph f this point falls within the weight C G enselope...

Page 167: ...TION SECTION 6 PA 34 220T SENECA III WEIGHT AND BALANCE 7 650 500 450 aco aso 300 100 0 5 10 15 20 25 30 35 40 45 50 55 00 65 70 MOMENT 1000 POUND INCHES LOADING GRAPH Figure 6 13 ISSUED JANUARY 8 198...

Page 168: ...513 MAX LANDING WT 4470 MAX ZERO FUEL W 4400 88 4200 4000 84 82 3000 2800 T 2600 p t 2400_Q_Q WEIGHT 2200 I I VS 82 84 86 88 90 92 94 C G ENVELOPE C G LOCATlON INCHES AFT DATUM Moment change due to re...

Page 169: ...he seats or in the baggage compartments Brief instructions are given on the plotter itself To use it first plot a point on the grid to locate the basic weight and C G location This can be put on more...

Page 170: ...tter grid at 2850 pounds and 83 5 inches to represent the basic airplane See illustration b Slide the slotted plastic into position so that the dot is under the slot for the forward seats at zero weig...

Page 171: ...ERO FUEL WT 4400 88 4200 TAKEOFF WEI HT 4000 86 ND C FUEL 3800 84 FORWARD AFT BAGGAGE BAGGAGE 3600 REAR SEATS 82 3400 M DDLE SEATS 3200 3000 RN S A BASIC WEIGHT AND C G 2800 2600 2400 WEIGHT 2200 VS 8...

Page 172: ...SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 34 220T SENECA III THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED JANUARY 8 1981 6 18...

Page 173: ...3 Flight Control System 7 2 7 15 Fuel System 7 l3 7 17 Electrical System 7 is 7 19 Vacuum System 7 22 7 2 Pitot Static System 7 24 7 23 Instrument Panel 7 26 7 25 Heating Ventilating and Defrosting Sy...

Page 174: ......

Page 175: ...go A door on the left side of the nose section gives access to the nose section baggage compartment The wing is of a conventional design and employs a laminar flow NACA 65 415 airfoil section The main...

Page 176: ...tion See Winterization in Handling and Servicing Section Asym metric thrust during takeoff and climb is eliminated by thecounter rotation of the engines the left engine rotating in a clockwise directi...

Page 177: ...cess fuelis returned to the fuel tank by the vapor return line The fuel injection system is a continuous flow type To obtain maximum efficiency and time between overhauls from the engines follow the p...

Page 178: ...a selected position The alternate air controls are located on the control quadrant justbelow the engine control levers When an alternate air lever is in the up or off position the engine is operating...

Page 179: ...overspeeding The recommended nitrogen pressure to be used when charging the unit is listed on placards on the propeller domes and inside the spinners This pressure varies with ambient temperature at...

Page 180: ...red position and prevent inadvertent unfeathering These latches must be manually released pushed forward to unfeather the propeller but do not change the feathering procedure With this system installe...

Page 181: ...PIPER AIRCRAFT CORPORATlON SECTION 7 PA 34 220T SENECA Ill DESCRIPTION OPERATION THIS PAGE INTENTIONALLY LEFT BLANK ISSUED APRIL 9 1982 REPORT VB 1110 7 6a...

Page 182: ...e hydraulic pump is running it is NOT advisable to move the gear selector switch to the opposite position before the gear has reached its full travel limit because a sudden reversal may damage the ele...

Page 183: ...free During normal operation this knob is covered by a guard to prevent inadvertent extension of the gear Before pulling the emergency gear extension knob place the landing gear selector switch in th...

Page 184: ...RATION DESCRIPTION OPERATION PA 34 220T SENECA III LANQiNO GEAR HYORAUUC CONTROL B PUMP WARNING LEFT TERMNAL N LENO DRAU NTLE CLOSE OPEN LANDING GEAR ELECTRICAL SYSTEM SCHEMATIC Figure 7 5 REPORT VB 1...

Page 185: ...HYDRAULIC CYLINDER HyOAAU IC cytlNDER O O WN DOWN NOSE GEAR PRESSURE SWITCH RESTRICTOR FREE ALL CONTROL 600 2000 PSI RE ERVO UNTRE THERMAL REMEF 4000 PSI CONTROL 660 h O PSI GEAR UP CNfcMVALVE DELivER...

Page 186: ...the landing gear lights If the green lights are not observed after the landing gear selector switch is placed in the DOWN position the first thing to check is the position of the navigation lights swi...

Page 187: ...ted the nose wheel centers as it enters the wheel well and the steeringlinkage disengages to reduce pedal loads in flight The landing light turns off aut matically when the gear is retracted All three...

Page 188: ...are of the Frise type This design allows the leading edgeof the aileron to extend into the airstream to provide increased drag and improved roll control The differential deflection of the ailerons ten...

Page 189: ...single tank referto Figure 7 11 All tanks on each side are filled through a single filler in the outboard tank and as fuel is consumed from the inboard tank it is replenished by fuel from outboard On...

Page 190: ...e lights dim whenever the pump pressure reduces automatically and manifold pressure is below approximately 21 inches In case of a failed engine driven fuel pump Hl auxiliary fuel pressure should be se...

Page 191: ...PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA III DESCRIPTION OPERATION FUEL SYSTEM SCHEMATIC Figure 7 11 ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 17 1981 7 15...

Page 192: ...l is also supplied to each cylinder nozzle during priming Normal operation of the auxiliary fuel pump is unchanged Fuel management controls are located on the console between the front seats There is...

Page 193: ...uel drains are provided for each fuel filter 2 each fuel tank 4 and each crossfeed line 2 The fuel filter drains are located on the outboard underside of each engine nacelle two fuel tank drains are l...

Page 194: ...lluminate Voltage regulators and overvoltage relays are located forward of the bottom of the bulkhead separating the cabin section from the nose section The electrical system and equipment are protect...

Page 195: ...EFT RIGHT ACCSY vmes NT TO RA O 5 BATT ALT ExfERNAL POWER tePTFONAL OVERVOLTAGE OVERVOLTAGE OGAR ELAY RELAY LIGHTER L CLTAGE EGULATOR LTAGE RACID ANNUNC AT F ASTER ALT ALTERNATOR AND STARTER SCHEMATIC...

Page 196: ...ALY R ALT L SwtTCH SWITCB ER OVER VOLTAGE VOLTAGE Axth RELAY RELAY OPTOfAL MASTER SWrTON v T GE VD T GE es To avon MASA SW1TCH LT SHUNT SHUNT SA AMNET GHT STARTER STARTER STAWTER SOLENDIDS L _L ALTER...

Page 197: ...light provide a means of monitoring the electrical system operation The two ammeters load meters indicate the output of the alter nators Should an ammeter indicate a load much higher than the known c...

Page 198: ...d much higher than the known consumption of the electrical equipment in use an alternator malfunction should be suspected and the respective alternator switch turned off ln this event the remaining al...

Page 199: ...ELEC TCH TRIM ARK S UNTS L14 TS L GMT MEAT TN 5 AIRPLANE IS EmbPPED wlTM OPflO AL FUELING PNINER SYSTEM SEE A FM o 2...

Page 200: ...ned constant over an extended period may indicate a dirty filter dirty screens possibly a sticking vacuum regulator or leak in system low vacuum indicator lights are provided in the annunciator panel...

Page 201: ...PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA III DESCRIPTION OPERATION VACUUM SYSTEM Figure 7 17 ISSUED JANUARY 8 1981 REPORT VB 1110 7 23...

Page 202: ...instruments may give slightly different readings depending on conditions within the cabin Airspeed setting of heating and ventilating controls or the position of the storm window can influence cabin...

Page 203: ...PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA III DESCRIPTION OPERATION PITOT STATIC SYSTEM Figure 7 19 ISSUED JANUARY 8 1981 REPORT VB 1110 7 25...

Page 204: ...nitor instrument panel gauges to check the condition of a system whose corresponding light on the annunciator panel illuminates Illumination of the manifold pressure overboost lights indicates manifol...

Page 205: ...t An Auxilary Avionics Bus Switch is located on the instrument panel to the right of the copilot control wheel shaft The switch is provided to give auxiliary power to the avionics bus in the event of...

Page 206: ...N 7 PIPER AIRCRAFT CORPORATION DESCRIPTION OPERATION PA 34 220T SENECA III TYPICAL INSTRUMENT PANEL S N 34 8133001 THRU 34 8233205 Figure 7 21 REPORT VB 1110 ISSUED JANUARY 8 1981 7 28 REVISED AUGUST...

Page 207: ...39 LEFT ENGINEALTERNATE AIR CONTROL LEVER 13 DUAL TACHOMETER 40 CONTROL LEVERS 14 AVIONICS 41 VACUUM GAUGE 16 MODE SELECTOR 42 AMMETERS 16 AUDIO MARKER PANEL 43 RlGHT ENGINE ALTERNATEAIR CONTROL LEVE...

Page 208: ...SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION OPERATION PA 34 220T SENECA III TYPICAL INSTRUMENT PANEL SN 34 8333001AND UP Figure 7 22 REPORT VB 1HO ISSUED AUGUST 9 1982 7 29s...

Page 209: ...RESS TO TEST BUTTONS 13 DUAL TACHOMETER 40 LEFT ENGINE ALTERNATE AIR CONTROL LEVER 14 AVIONICS 41 CONTROL LEVERS 15 MODE SELECTOR 42 AMMETER 16 AUDIO MARKER PANEL 43 VACUUM GAUGE 17 BAoio MASTER SWITC...

Page 210: ...tarts fuel flow and ignites the heater and during ground operation it also activates the ventilation blower which is an integral part of the combustion heater With instant starting and no need for pri...

Page 211: ...PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA III DESCRIPTION OPERATION CABIN HEATING VENTILATING AND DEFROSTING SYSTEM Figure 7 23 ISSUED JANUARY 8 1981 REPORT VB 1110 7 31...

Page 212: ...SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION OPERATION PA 34 220T SENECA III HEATING VENTILATING AND DEFROSTING CONTROL CONSOLE Figure 7 25 REPORT VB 1110 ISSUED JANUARY 8 1981...

Page 213: ...t panel To prevent activation of the overheat switch upon normal heater shut down during ground operation turn the three position switch to FAN for two minutes with the air intake lever in the open po...

Page 214: ...n Standard cabin features include a pilot s storm window ashtrays map pockets coat hooks and assist straps a cigar lighter sun visors and pockets on the front and center seat backs Among the options w...

Page 215: ...ble work surface facing forwar place the slots in the table support into the receptacle clips mounted on the hat shelf Make sure the tie down strap is not behind the table With the table fully placed...

Page 216: ...aircraft battery switch therefore whenthe baggage door is opened the light will illuminate regardless of the position ofthe battery switch When the baggage compartment light option is installed the b...

Page 217: ...of common items such as a dime Key knife blade etc If there are no tools available in an emergency the screw heads may be broken off by any means The ELT is an emergency locator transmitter which meet...

Page 218: ...tivate the transmitter Moving the switch back to the ARMED position will turn off the trans mitter only if the impact switch has not been activated The ELT should be checked to make certain the unit h...

Page 219: ...The minutes can now be set by pressing the RST button once again and causing the minutes digits to flash Set the minutes to the next minute to come up at the zero seconds time mark and depress the RST...

Page 220: ......

Page 221: ...irplane Alterations 8 4 8 9 Ground Handling 8 5 8 1 Engine Induction Air Filters 8 7 8 13 Brake Service 8 8 8 15 Landing Gear Service 8 8 8 17 Propeller Service 8 10 8 19 Oil Requirements 8 11 8 2 Fue...

Page 222: ......

Page 223: ...l importance and should becomplied with promptly These are sent to the latest registered owners distributors and dealers Depending on the nature of the bulletin material and labor allowances may apply...

Page 224: ...AD against his aircraft The Owner Service Agreement which the owner receives upon delivery of the aircraft should be kept in the aircraft at all times This identifies the on ner to authorized Piper d...

Page 225: ...ularly 8 5 PREVENTIVE MAINTENANCE The holder of a Pilot Certificate issued under FAR Part 61 may perform certain preventive maintenance described in FAR Part 41 This maintenance may be performed only...

Page 226: ...aft a To be displayed in the aircraft at all times 1 Aircraft Airworthiness Certificate Form FAA 8100 2 2 Aircraft Registration Certificate Form FAA 8050 3 3 Aircraft Radio Station I icense if transmi...

Page 227: ...an fifteen feet and a qualified person should ride in the pilot s seat to maintain control by use of the brakes b Taxiing Before attempting to taxi the airplane ground personnel should be instructed a...

Page 228: ...pedals and then pull out the parking brake knob To release the parking brake first depress and hold the toe brake pedals and then push in on the parking brake knob WARNING No braking will occur if kn...

Page 229: ...remote the pitot head cover before flight 7 Cabin and baggage doors should be locked when the airplane is unattended 8 11 ENGINE INDUCTION AIR FILTERS a Removing induction Air Filter I Remove the uppe...

Page 230: ...f the compartment Keep the fluid level at the level marked on the reservoir No adjustment of brake clearance is necessary Refer to the Service Manual for brake lining replacement instructions 8 15 LAN...

Page 231: ...PIPER AIRCRAFT CORPORATION SECTION 8 PA 34 220T SENECA Ill HANDLING SERV MAINT BRAKE SYSTEM Figure 8 1 ISSUED JANUARY 8 1981 REPORT VB 1110 8 9...

Page 232: ...30 to 0 9 2 NOTE Do not check pressure or charge with propeller in feather position The spinner and backing plate should be cleaned and inspected for cracks frequently Before each flight the propelle...

Page 233: ...The fuel screens in the strainers require cleaning at 50 hour or 90 day intervals whichever occurs first The fuel gascolator strainers are located in the wing between the fuel selector valves and tfie...

Page 234: ...ng I El comem of up to 4 ml E S gallon are approved lor use in all engines certilcated for use wnh grade 100 130 fuel The operation of the aircraft is approved with an anti icing additive in the fueL...

Page 235: ...ted additive to come in contact with the aircraft painted surfaces orthe interior surfaces of the fuel tanks c Filling Fuel Tanks Observe all required precautions for handling gasoline Fill the fuel t...

Page 236: ...n CAUTION When draining fuel be sure that no fire hazard exists before starting the engines e Draining Fuel System The bulk of the fuel may be drained either by opening the valve at the inboard end of...

Page 237: ...y above the baffle plates DO NOT fill the battery with acid use distilled water only A hydrometer check will determine the percent of charge in the battery If the battery is not properly charged recha...

Page 238: ...ch waste 2 With the engine cowling removed spray or brush the engine with solvent or a mixture of solvent and degreaser In order to remove especially heavy dirt and grease deposits it may be necessary...

Page 239: ...t brush the micro 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 plas...

Page 240: ...tic surfaces apply a thin coat of hard polishing wax Rub lightly with a soft cloth Do not use a circular motion 5 A severe scratch or mar in plastic can be removed by rubbing out the scratch with jewe...

Page 241: ...of warm air along the region being cleaned using a portable ground heater As an alternate cleaning solvent use benzol or nonleaded gasoline Moisten the cleaning cloth in the solvent scrub lightly and...

Page 242: ...stalled on the inlet opening of the el cooler outboard chamber of the plenum chamber This kit should be installed whenever the ambient temperature is 50 F or less When the kit is not being used it can...

Page 243: ...ophaser Installation 4 pages 9 55 8 Bendix NP 2041A Area Navigation Computer Programmer 6 pages 9 59 9 Collins ANS 351 Area Navigation Computer 6 pages 9 65 10 King KNS 80 Navigation System 4 pages 9...

Page 244: ...Paragraph Supplernent Page to No 19 Bendix RDR f60XD IN 232A Weather Radar System 6 pages 9 l25 20 EDO Asionics Command Electric Trim Ssstem ModelAK923 4pages 9 131 21 Century 31 Autoplot Installatio...

Page 245: ...al systems and equipment not provided with the standard airplane All of the Supplements listed on tlie preceding pages are FAA Approved and are required to be aboard the airplane when the related equi...

Page 246: ...SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA 34 220T SENECA III THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED JANUARY 8 1981 9 2...

Page 247: ...ation necessary for the operation of the airplane when the optional portable oxygen system is installed in accor dance with FAA Approved Piper data The information contained within this supplement is...

Page 248: ...When fully charged each cylinder contains oxygen ata pressure of 1850 psi at 70 F the filler port is enclosed by a cover at the rear of each unit If high altitude flight is anticipated it should be d...

Page 249: ...ept away from oxygen equipment SECTION 2 LIMITATIONS a No smoking allowed b The aircraft is restricted to six occupants with two 2 oxygen units installed c The aircraft is restricted to four occupants...

Page 250: ...URES PREFLIGHT ta Check oxygen quantity b Installation Forward facing seating arrangement only 1 Remove middle center seat and secure units to seat by use of belts provided 2 Reinstaltseat and secure...

Page 251: ...ystem c Monitor flow indicators and quantity CAUTION Use of oxygen unit is prohibited when gauge approaches red area SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of...

Page 252: ...SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEME T I PA 34 220T SENECA IH THIS PAGE UNTENTIONALLY LEFT BLANK REPORT VB IIIS ISSUED JANUARY 8 1981 948 of 6...

Page 253: ...ry lor the operation of the airplane when the optional fixed oxygen system is installed in accor dance with FAA Approved Piper data The information contained within this supplement is to be used in co...

Page 254: ...l knob labeled Oxygen Pull On is also mounted in the copilot s instrument panet The pressure regulator is moumed directly on the oxygen cylinder once the oxygen flow control knob is on each of the oxy...

Page 255: ...forat least three minutes after the control knob is turned off To preclude the possibility of fire by spontaneous combustion oiL grease paint hydraulic fluid and other flammable material should be kep...

Page 256: ...4 NORMAL PROCEDURES PREFLIGHT ta Check oxygen quantity lb Turn on oxygen system and check flow indicators on all masks All masks are stored in the seat pockets of the front and middle seats ILFLIGHT...

Page 257: ...of the airplane when the optional air conditioning system is installed in accor dance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with th...

Page 258: ...the rear outboard side of the left engine It has an electric clutch which automatically engages or disengages the compressor Air from the baggage area is drawn through the evaporator by the blower and...

Page 259: ...lectrical system SECTION 2 LIMITATIONS a To ensure maximum climb performance the air conditioner must be turned OFF manually prior to takeoff to disengage the compressor and retract the condenser door...

Page 260: ...check may be performed during flight if an in flight failure is suspected The condenser door light is located on the annunciator panel and illu minates when the door is open and extinguishes when the...

Page 261: ...irborne This will be the case only in extremely hot weather a The decrease in true airspeed is approximately 4 KTS at all power settings b The decrease in range may be as much as 25 nautical miles for...

Page 262: ...SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 3 PA 34 220T SENECA Ill TH1S PAGE INTENTIONALLY LEFT BLANK REP RT B ill0 i ISSUED JANUARY 8 1981 948 6 of 6...

Page 263: ...0 Automatic Flight Control System with optional Flight Director as installed in the PA 34 220T Seneca III in accordance with FAA Approved Piper data The airplane must be operated within the limitation...

Page 264: ...at autopilot disengagement does not result in transient airplane motion An autotrim etectric pitch trim monitor is provided in the autopilot Autotrim and or electric pitch trim faults are visually ann...

Page 265: ...0 feet d Do not extend flaps beyond 25 during autopilot operation e The autopilot must be disengaged during takeoff and landing f System approved for Category I operation only APPR or BC selected g Au...

Page 266: ...unction hold the control wheel firmly up to 45 pounds of force on the control wheel may be necessary to hold the aircraft level tc ENGINE FAlLURE COUPLED Disengage AP 2 Follow basic Airplane Flight Ma...

Page 267: ...s engaged With the HDG flag present only vertical modes can be selected for FD or Autopilot operation e MAXIMUM ALTlTUDE LOSSES DUE TO AUTOPILOT MALFUNCTIONS Cruise Climb Descent 400 feet Maneuvering...

Page 268: ...S WARNING FLAGS AND ANNUNCIATORS The KI 256 Flight Director Indicator does not have a warning flag however the command bars will be biased out of view whenever the system is invalid or a FD mode is no...

Page 269: ...d an audible warning for approximately 2 seconds whenever the autopilot engage lever on the KC 290 Mode Controller is disengaged e PlLOT S CONTROL WHEEL SWITCH FUNCTIONS AP DISC TRIM INTERRUPT This em...

Page 270: ...engaged with the GA Mode selected and will follow the FDI pitch command to climb at the fixed angle NOTE The flight control system incorporates its own annunciator panel which is located on the instru...

Page 271: ...force required to move trim wheel b Actuate the right side switch to the fore and aft positions The trim solenoid should not engage and the trim should not run c Grasping the manual trim wheel run the...

Page 272: ...tch attitude will lock on any attitude up to 15 pitch attitude Engaging and holding the CWS switch allows the pilot to momentarily revert to manual control while retaining his previous modes except GA...

Page 273: ...to trim the command pitch attitude at a rate of one degree per second the pitch attitude degrees legend on the airplane attitude indicator will not indicate accurate FDI pitch steering bar pitch attit...

Page 274: ...ontroller The annunciator will indicate NAV ARM until capture of the selected course unless the NAV switch is engaged with wings level and a centered needle on the CDI Then the mode will go directly t...

Page 275: ...UND switch on the engine throttle control or by engaging HDG when in APPR CPLD or engaging NAV when in APPR CPLD or APPR ARM CAUTION The APPR mode of operation will continue to provide airplane comman...

Page 276: ...tercept angle 90 3 Seket desired radial and engage NAV The FCS will remain on HDG as indicated on theannunciator panel and in ARM on the NAV mode When the airplane approaches the beam the system will...

Page 277: ...o recenter the GS for GS coupling Failure to follow this procedure will result in the GS mode being inhibited 7 When middle marker signal is received system will auto matically switch to a more stable...

Page 278: ...rplane must be set for descent manually by holding the vertical trim control DN on the Mode Controller or by establishing the desired PAH using the CWS or vertical trim switch SECTION 5 PERFORMANCE No...

Page 279: ...ion of the KFC 200 Automatic Flight Control System as installed in the PA 34 220T Seneca III in accordance with FAA Approved Piper data The airplane must be operated within the limitations herein spec...

Page 280: ...motion An autotrim electric pitch trim monitor is provided in the autopilot Auto trim and or electric pitch trim faults are visually annunciated on the Mode Annunciator and accompanied by an audible...

Page 281: ...0 feet d Do not extend flaps beyond 25 during autopilot operation e The autopilot must be disengaged during takeoff and landing f System approved for Category I operation only APPR or BC Mode selected...

Page 282: ...alfunction hold the control wheel firmly up to 45 pounds of force on the control wheel may be necessary to hold the aircraft level c ENGlNE FAlLURE COUPLED 1 Disengage AP 2 Follow basic Airplane Fligh...

Page 283: ...rmation is engaged e MAX1MUM ALTITUDE LOSSES DUE TO AUTOPlLOT MALFUNCTIONS Cruise Climb Descent 400 feet Maneuvering 100 feet APPR 50 feet SE APPR 50 feet CAUTION When the autopilot is engaged manual...

Page 284: ...d FCS WARNING FLAGS AND ANNUNCIATORS HDG This warning flag mounted in the Pictorial Navigation Indicator will be in view whenever the directional gyro information is invalid If a HDG invalid occurs wi...

Page 285: ...trim system To resume AP controL the AP lever on the Mode Con troller must be re engaged In the event of electric trim or autotrim failure the switch can be held depressed which removes all power fro...

Page 286: ...1 Check that all circuit breakers for the system are in 2 Allow sufficient time for gyros to come up to speed and system warm up 3 4minutes g PREFLIGHT CHECK Run prior to each flight 1 With no modes e...

Page 287: ...akeoff 5 Daily preflight check must be performed prior to first flight of the day a Engage the AP and put in a pitch U P command using the vertical trim switch on Mode Controller Hold the control colu...

Page 288: ...modes and conveniently resuming that proTile at this discretion Disengage Procedure While monitoring the flight controls disengage the system hy one of the following rnethods depressing the pilot s A...

Page 289: ...itch on the Mode Controller and HDG will be displayed on the annunciator panel The AP will command a turn to the heading selected The pilot may then choose any new heading by merely setting the bug on...

Page 290: ...pproach Mode APPR The Approach mode may be selected by tuning the NAV receiver to the desired VOR or LOC frequency setting the CDI to the desired radial or inbound heading and depressing the APPR swit...

Page 291: ...reselect APPR mode 8 Back Course Mode BC For BC operation proceed as for normal approach mode but engage BC mode after selecting APPR The BC mode reverses the signals in the computer and cannot be eng...

Page 292: ...g and engage AP and HDG tointerceptselected CDI course beam at desired angle Maximum recommended intercept angle 90 4 Engage APPR and note APPR ARM on the annunciator 5 When airplane approaches the se...

Page 293: ...on of the airplane when the optional ice protection system is installed in accor dance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with t...

Page 294: ...ation of the surface deice switch activates a system cycle timer that energizes the pneumatic pressure control valves until the system pressure reaches 17 psi or until 6 seconds is reached The boot so...

Page 295: ...PNEUMATIC WINDSLH ANEL D CEURMAT TS CE DETECTIONHE T PITOTHEAD ELECTROTHERMAL PROPELLER DElCER PADS HEATED LIFTDETECTORS y 2 o...

Page 296: ...eicer pads is conducted in the following order a Outboard halves of the propeller deicer pads on the right engine b Inboard halves of the propeller deicer pads on the right engine c Outboard halves of...

Page 297: ...ated glass panel removed rotate the receptacle plate 180 and replace it to cover the holes in the fuselage skin Also replace the windshield collar screws An operational check may be performed by turni...

Page 298: ...Heat With the heated pitot switch on check the heated pitot head and heated lift detector for proper heating CAUTION Care should be taken when an operational check of the heated pitot head and the hea...

Page 299: ...practical Maintain at least 89 KIAS on finaL Do not extend gear or lower flaps until certain of making field Flaps 25 ALTERNATOR FAILURE IN ICING CONDITIONS Alternator switches OFF then ON Circuit br...

Page 300: ...uired to monitor the rate of ice build up in order to effect the boot cycle at the optimum time Boots should be cvcled when ice has built to between I 4 and 1 2 inch thickness on the leading edge to a...

Page 301: ...up to 10 knots in prolonged temg encounters lf ice is remaining on the unprotected surfaces of the airplane at the termination of the flight the landing should be made using full flaps and carrying a...

Page 302: ...the unprotected surfaces can result in significant performance loss Installation of ice protection equipment results in a 30 F P M decrease in single engine climb performance and a reduction of 850 fe...

Page 303: ...s front course except that BC is engaged after APPR is engaged and the airplane must be set for descent manually by holding the vertical trim control DN on the Mode Controller if in ALT hold or by est...

Page 304: ...SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 5 PA 34 220T SENECA III THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED APRIL 21 1981 9 44d 16 of 16...

Page 305: ...n of the airplane when the optional propeller synchrophaser is installed in accor dance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with...

Page 306: ...ser must be in the OFF position forall single engme operations SECTION 4 NORMAL PROCEDURES The rotary switch must be in the OFF position during taxi takeoff landing and single engine operations Aefore...

Page 307: ...return to the controlled selected RPM plus approximately 25 RPM out of syn chronization regardless of the position of the synchrophaser switch SECTION 5 PERFORMANCE No changes to the basic perforrnanc...

Page 308: ...SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 7 PA 34 220T SENECA III THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED JANUARY 8 1981 948 4 of 4...

Page 309: ...en the optional Bendix NP 2041A Area Navigation Computer Programmer is installed in accordance with FAA Approved Piper data The information contained within this supplement is to be used in conjunctio...

Page 310: ...r mation to the NAV computer programmer which in turn drives the pilot s navigation displays a Turn the VHF COM NAV on and set the DMETrequency pairing selector to NL bl Turn the DME on Ici FREQUENCY...

Page 311: ...ponding to the frequency of the VOR station and press the ENTER key 2 WAYPOINT BEARING Press BRG key press number keys corresponding to the waypoint bearing and press the ENTER key 3 WAYPOINT DISTANCE...

Page 312: ...urse which will appear for 30 seconds to allow the CRS to be reset The course pointer on the In 881 HSI will automatically reset to the display course provided its function switch is in the HSI 1 With...

Page 313: ...ACT Data stored for active waypoint number appearing in ACT window is displayed but cannot be altered n With the mode selector set to APR the displays are the same as RNAV except full scale deviation...

Page 314: ...key press number keys correspond ing to the desired frequency and press the ENTER key 5 NAV 2 FREQUENCY Press NAV 2 key press number keys corresponding to the desired frequency and press the ENTER ke...

Page 315: ...ne when the optional Collins ANS 351 Area Navigation Computer is installed in accordance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with...

Page 316: ...Y PROCEDURES No changes to the basic Emergency Procedures provided by Section 3 of this Pilot3 Operating Handbook are necessary for this supplement SECTION 4 NORMAL PROCEDURES AMBIENT LIGHT SENSOR DIS...

Page 317: ...adily on waypoint number indi cates active waypomt Return Button Depressing RTN return button returns the display to the active waypoint when an inactive waypoint is currently being displayed Use Butt...

Page 318: ...d The check button is spring loaded to prevent permanent actuation Ambient Light Automatically adjusts display lighting intensity Sensor as a function of cockpit ambient light b AREA NAVlGATION WAYPOI...

Page 319: ...lector until the desired waypoint number and coordinates are dis played on the ANS 35l a Verify that the waypoint definition is correct hy comparing the display with the flight p an b Uncouple the aut...

Page 320: ...SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 9 PA 34 220T SENECA III THlS PAGE INTENTlONALLY LEFT BLANK REPORT VB 1110 ISSUED ANUARY 8 1981 9 70 6 of 6...

Page 321: ...airplane when the optional King KNS 80 Navigation System is installed in accordance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with the...

Page 322: ...shbutton In addition to the standard VOR and RNAV enroute RNV ENR modes the KNS 80 has a constant course width or parallel VOR mode VOR PAR and an RNAV approach mode RNV APR To place the unit in eithe...

Page 323: ...oint to increment by I and data display to go to frequency mode 6 DATA BUTTON Momentary pushbutton Causes waypoint data display to change from FRQto RAD to DST and back to FRQ 7 OFF PULL ID CONTROL a...

Page 324: ...e Data Outer knob varies 10 NM digit A carryover occurs from the tens to hundreds place A rollover to zero occurs at 200 N M Center knob in position varies 1 NM digit Center knob out position varies 0...

Page 325: ...n of the airplane when the optional KNS Si Navigation System is installed in accordance with FAA Approved Piper data The information contained within this supplement isto be used in conjunction with t...

Page 326: ...y whenever an ILS frequency is channeled The display will annunciate the VOR or RNAV mode by lighting a message beside the waypoint In addition to the standard VOR and RNAV enroute modes the KNS 8 i h...

Page 327: ...OR Audio Level Control Rotate clockwise for increased audio level c VOR IDENT Mute Function Push Pull switch Enables the VOR Ident tone to be heard in out position 7 DATA INPUT CONTROL Dual concentric...

Page 328: ...Center knob selects waypoint from I to 9 and rolls over 9 COURSE SELECT KNOB Located in remote unit Selects desired course through the VOR ground station or waypoint MODE SELECTOR KNOB NAV FREQ DISPL...

Page 329: ...e optional RCA Color WeatherScout 11 Weather Radar System is installed in accordance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with the...

Page 330: ...ansmitting SECTION 3 EMERGENCY PROCEDURES No changes to the basic Emergency Procedures provided by Section 3 of this Pilot s Operating Handbook are necessary for this supplement SECTION 4 NORMAL PROCE...

Page 331: ...IT is displayed if a mode is selected prior to end of warm up or when Indicator and Antenna are syn chronizing B Auxiliary FRZ is displayed as a blinking word if Field radar is in freeze mode to remin...

Page 332: ...the end of the warm up period WAIT will be displayed until RT warms up approximately 30 seconds If TEST is selected immediately WAIT will be displayed until Antenna is syn chronized less than 4 second...

Page 333: ...is automatically 100 nm 6 FRZ Pushbutton switch used to select freeze mode Radar display is not updated with incoming target return data As a warning to the pilot FRZ level will flash on and off at 1...

Page 334: ...nel within 15 feet of area being scanned by antenna when system is transmitting 1 Flash bulbs can be exploded by radar energy 2 Since storm patterns are never stationary the display is con stantly cha...

Page 335: ...the optional RCA WeatherScout II Weather Radar System is installed in accordance with FAA Approved Piper data The infor mation contained within this supplement is to be used in conjunction with the c...

Page 336: ...s transmitting SECTION 3 EMERGENCY PROCEDURES No changes to the basic Emergency Procedures provided by Section 3 of this Pilot s Operating Handbook are necessary for this supplement SECTION 4 NORMAL P...

Page 337: ...ch used to select cyclical contour mode Data is presented alter nately as normal for 0 5 seconds then contoured for 0 5 seconds Pressing switch a second time restores normal or WX mode 6 Range Field M...

Page 338: ...ired range 5 Adjust TILT control for desired forward scan area d PRECAUTIONS If the radar is to be operated while the aircraft is on the ground 1 Direct nose of aircraft such that antenna scan sector...

Page 339: ...9 PA 34 220T SENECA III SUPPLEMENT 13 SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of the Pilot s Operating Handbook are necessary for this supplement ISSUED JANUARY...

Page 340: ...SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 13 PA 34 220T SENECA HI THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED JANUARY 8 1981 9 90 6 of 6...

Page 341: ...e optional Bendix RDR I60 Monochrome Weather Radar System is installed in accordance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with the...

Page 342: ...erating Handbook are necessary for this supplement SECTION 4 NORMAL PROCEDURES a SYSTEM CONTROLS Table 4 3 lists and describes the system controls all of which are mounted on the panel of the radar in...

Page 343: ...ter Wx GAIN Wx A 1 In Wx position weather image gain is at preadjusted level Contour operation is Gain Control and automatic and constant Mode Selector 2 In GAIN position 6 levels from MAP maximum gai...

Page 344: ...g for a second time reveals direction and distance of target movement during hold period During HOLD mode the antenna continues to scan and the display will continue to be presented as long as power i...

Page 345: ...When the HOLD pushbutton is initially depressed the MODE READOUT displays flashing HOLD The MODE READOUT displays TEST ALPHANUMERIC READOUT Table 4 5 b GENERAL OPERATING PRECAUTlONS W4RNING Do not op...

Page 346: ...tantly changing and continued observation is always ad visable where areas of turbulence prevail NOTE See RDR 160 pilot manual for detailed operating information and analysis of targets SECTION 5 PERF...

Page 347: ...optional Bendix RDR 160 IN 2026A Color Weather Radar System is installed in accordance with FAA Approved Piper data The information contained within this supplement is to be used in con junction with...

Page 348: ...ND DISPLAYS Controls and displays for the RDR 160 IN 2026A Color Weather Radar System are listed in Table4 3 with a functional description Location of the controls and displays is shown in Figure 4 l...

Page 349: ...h time the button is pressed eg 40 to 20 until minimum range is reached TILT control Electrically adjusts the antenna to move the radar beam up to 15 degrees above the hori zontal or to a maximum of I...

Page 350: ...sent advances the indicator display to the next higher mode shown on the list The list disappears after a few seconds and the made does not change if the button is not pressed again The following stan...

Page 351: ...each of the other range marks circles is displayed alongthe right edge of the circles arcs HOLD pushbutton Retains the display NAV and weather when push on push ofT button is actuated push on The word...

Page 352: ...l within 15 feet of area being scanned by antenna when system is transmitting I Flash bialbs can be exploded by radar energy 2 Since storm patterns are never stationary the display is con stantly chan...

Page 353: ...on of the airplane when the optional propeller synchrophaser is installed in accor dance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with...

Page 354: ...LE ENGINE OPER ATIONS SECTION 3 EMERGENCY PROCEDURES The propeller synchrophaser must be in the OFF position for all single engme operations SECTION 4 NORMAL PROCEDURES During taxi takeoff landing or...

Page 355: ...for 30 to 40 seconds then the propellers can be synchronized again and the synchrophaser switch returned to I or 2 Pulling the circuit breakers completely deactives the propeller synchrophaser system...

Page 356: ...SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 16 PA 34 220T SENECA III TH1S PAGE INTENTIONALLY LEFT BLANK REPORT VBRI110 ISSUED APRIL 21 1981 9406 4 of 4...

Page 357: ...is installed in accordance with STC SA3384SW D The information contained within this supplement is to be used in conjunction with the complete handbook This supplement has been FAA Approved as a perm...

Page 358: ...te until the system failure has been identified and corrected 1 Altitude Loss During Malfunction a An autopilot malfunction during climb cruise or descent with a 3 second delay in recovery initiation...

Page 359: ...d with Slave No 1 No 2 switch or Slaved position when equipped with Slaved and Free Gyro Mode Switch 2 Check for HDG Flag L Check compass circuit breaker 4 Reset heading card while observing slaving m...

Page 360: ...fy that control wheel movement corresponds to HDG command input 3 Grasp control wheel and override roll servo actuator to assure override capability 4 With HDG bug centered select NAV or APPR mode and...

Page 361: ...approach operations refer to Special Operations and Information Section e SPECIAL OPERATIONS AND INFORMATION Instrument Approach Operations Initial and or intermediate approach segments should be con...

Page 362: ...SECTION 9 PIPE l AIRCRAFT CORPORATION SUPPI MENT 17 PA 34 220T SENECA HI THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED APRIL 21 1981 9 112 6 of 6...

Page 363: ...ode AK881 FD is installed in accordance with STC SA3371SW D The information contained within this supplement is to be used in conjunction with the complete handbook This supplement has been FAA Approv...

Page 364: ...topilot system If the malfunction was in the auto trim system there may be residual control wheel force after the system is OFF Be prepared for any residual trim force and retrim as necessary using th...

Page 365: ...t malfunction during climb cruise or descent with a 3 second delay in recovery initiation could result in I as much as 60 bank and 700 altitude loss Maximum altitude loss measured at 180 KIAS during d...

Page 366: ...ed position when equipped with Slaved and Free Gyro Mode Switch 2 Check for HDG Flag 3 Check compass circuit breaker 4 Reset heading card while observing slaving meter NOTE Dead slaving meter needle o...

Page 367: ...ector steering horizon the F D must be switched on before the autopilot may be engaged Any autopilot mode may be pre selected and will be retained upon autopilot engagement CAUTIONS Flight Director Au...

Page 368: ...TOPILOT FD Switch ON if F D Equipped a Engage autopilot by pushing programmer OFF ON switch ON b Rotate D G HDG bug left then right and verify that control wheel movement corresponds to HDG command mp...

Page 369: ...er operation of the system is therefore predicated on conducting the following preflight check first flight of each day If the trim system fails any portion of this test turn the trim switch OFF and p...

Page 370: ...in either direction with the Control Wheel Switch 4 Release TEST pushbutton All lights except HDG and ATT shall extinguish Any deviat on from the above sequence indicates that a failure exists in eit...

Page 371: ...djust HDG bug to aircraft heading and select desired pitch attitude by activation of the CWS Pitch Synch switch or the modifier switch 3 Maneuver aircraft manually to satisfy the commands presented Se...

Page 372: ...glide path or when passing the final approach fix FAF immediately lower the landing gear and reduce the power for approximately 90 95 KIAS on the final approach segment Adjust power as necessary durin...

Page 373: ...n raise gear and flaps d Pilot may hand fly aircraft with reference to flight director steering information e After aircraft is established in climb gear and flaps up autopilot may be re engaged by pu...

Page 374: ...SECTI0N 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 18 PA 34 220T SENECA III THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSOED APRII 21 1981 9 124 12 of 12...

Page 375: ...onal Bendix RDR 160XD IN 232A Weather Radar System is installed in accordance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with the comple...

Page 376: ...lays is shown in Figure 4 1 All operating controls and displays are located on the indicator BAG FLASHESlN INDICATES INDiCATES CURSOR HOLD SELECTED RANGE WHEN FUNCTION POSITION CONDITION MODE SELECTED...

Page 377: ...time the button is pressed eg 40 to 20 until minimum range is reached TlLT control Electrically adjusts the antenna to move the radar beam up to 15 degrees above the hori zontal or to a maximum of 15...

Page 378: ...23A push on push off Remote Computer Unit is connected When actuated provides NAV information super imposed over the MODE selected WX WXA or MAP If interface is not connected the words NO NAV will be...

Page 379: ...system A change in range selection with indicator in HOLD results in a blank screen Wx pushbutton Selects the weather mode Wx when pressed Pushbutton switch returns to normal position when released WX...

Page 380: ...l within 15 feet of area being scanned by antenna when system is transmitting 1 Flash bulbs can be exploded by radar energy 2 Since storm patterns are never stationary the display is con stantly chang...

Page 381: ...ric Trim System Model AK923 as installed in the PA 34 220T Seneca 111in accordance with FAA Approved Piper data The airplane must be operated within the limitations herein specified This supplement ha...

Page 382: ...that the trim system is disabled 5 Pull trim circuit breaker Leave circuit breaker open until the trim svstem is corrected SECTION 4 NORMAL PROCEDURES a PRE FLKiHT INSPECTION BEFORE EACH FLIGHT 1 Cir...

Page 383: ...shed to identify a system failure that might otherwise go undetected b IN Fl IGHT PROCEDURFS Depress center har and move switch rocker fore or aft to obtain electric trim nose down or up Release switc...

Page 384: ...SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 20 PA 34 220T SENECA III THIS PAGE INTENTIONAI LY LEFT Bl ANK REPORT VB 1110 ISSUED SEPTEMBER 23 1983 9 134 4 of 4...

Page 385: ...ccordance with STC SA3390SW D The information contained herein supplements or supersedes the infor mation in the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those...

Page 386: ...KIAS or faster with flaps up e Category 1 operations orily f Placard in full view of the pilot CONDUCT TRlM CHECK PRIOR TO FIRST FLIGHT OF DAY SEE AFM SECTION 3 EMERGENCY PROCEDURES a AL TOPlLOT In th...

Page 387: ...ltitude loss Maximum altitude loss was recorded at 180 KIAS during descent b An autopilot malfunction during an approach single engine gear down tlaps up with a i second delay in recovery initiation c...

Page 388: ...Slave No 1 No g switch or SL AVED position when equipped with Slaved and Free Gyro Mode Switch 2 Check for HDG Flag 3 Check compass circuit breaker 4 Reset heading card while observing slaving meter...

Page 389: ...el moves in the down direction Verify that after approximately a 3 second delay the trim moves in the down direction e Press the UP switch verify that the control wheel moves in the up direction Verif...

Page 390: ...TIONS Any failure of the above procedures indicates that a failure exists in the system and the system shan not be operated until the failure has been located and corrected Check the elevator trim pos...

Page 391: ...up to 2 notches 25 flap selected if desired Upon intercepting the glide path or when passing the final approach fix FAF immediately lower the landing gear and reduce the power for approximately 9 KlA...

Page 392: ...o change SECTION 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 DESCRIPTIO...

Page 393: ...e panel Ught dimmer switch The electric elevator trim system is a fully redundant type in both the manual and autotrim modes The trim system is powered througha separate system master switch that must...

Page 394: ...wheel electric trim operations 2 Autopilot ON OFF Switch Momentary rocker type switch which engages or disengages the autopilot roll pitch and trim servos and lights or extinguishes autopilot AP annu...

Page 395: ...selector or OBS and D G and select NAV mode for VOR tracking 5 APR Approach Mode Selector Switch provides automatic 45 VOR LOC intercept angle tracking and crosswind correction during instrument appro...

Page 396: ...used The GS mode may be emered rom either ATT mode or ALT mode from above the GS centerline or below the centerline Activation of the GS mode depends upon satisfying two setsof conditions completion o...

Page 397: ...l NOT automatically decouple however the GS light will flash The pilot must monitor raw course guidance data during the approach to assure signal qualty Since GS arm and capture are automatic when the...

Page 398: ...ystem will synchronize with the aircraft attitude existing at release of the switch 4 System Test Ground Operations Only The system is equipped with a comprehensive test circuit which when activated w...

Page 399: ...o Excitation Absence of valid gyro excitation will cause the autopilot to disengage and the AP annunciator to flash The autopilot cannot be re engaged until this condition is corrected 3 AP Disengagem...

Page 400: ...to cause the electric trim io function from the control wheel switch Depressing the center bar will disconnect the autopilot 2 Control Wheel Steeting CWS Switch See explanation in Special Modes and O...

Page 401: ...symbolic aircraft and the movable background L Roll Altitude lndex Displays airplane roll attitude with respect to the roll attitude scale 4 Roll Attitude Scale Scale marked at 0 10 20 130 160 and 90...

Page 402: ...than 2 3minutes indicatessystemfailure NOTE NSD 360A System includes a slaving selector switch allowing the selection of free gyro mode Refer to emergency procedures for failure mstructions 3 HDG ind...

Page 403: ...ss Card Rotates to display heading of airplane with reference to lubber line 2 on DG 5 Heading Selector Knob Positions heading bug 3 on compass card 4 by rotating the heading selector knob The bug rot...

Page 404: ...SECTION 9 PIPER ATRCRAFT CORPORATION SUPPLEMENT 21 PA 34 220T SENECA III THlS PAGE 1NTENTlONALLY LEFT BLANK REPORT VB Il10 ISSUED FEBRUARY 10 1984 9454 20 of 20...

Page 405: ...TABLE OF CONTENTS SECTION 10 SAFETY TIPS Paragraph Page No No 10 1 General 10 1 10 3 Safety Tips 10 1 REPORT VB 1110 10 i...

Page 406: ......

Page 407: ...years 1 Sluggish RPM control and propeller overspeed with poor RPM recovery after rapid throttle application are indications that nitrogen pressure in the propeller dome is low m Experience has shown...

Page 408: ......

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