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Piper Aircraft Corporation Seneca II PA-34-200T, Pilot Operating Handbook

The Piper Aircraft Corporation Seneca II PA-34-200T Pilot Operating Handbook is a comprehensive manual that provides detailed instructions and guidelines for operating this powerful aircraft. Available for free download from manualshive.com, this essential resource equips pilots with the knowledge they need for a safe and efficient flight experience.

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Summary of Contents for Seneca II PA-34-200T

Page 1: ...J AND CONSTITUTES THE APPROVED Al RPLANE FUG HT MANUAL ANO MUST BE CARRIED IN THE A IRPLANE AT ALL TIMES AlRPLANE SERIAL NQ__J _1 _ _7_B_7_ 0_ 0_ 6_ 6___ PILOT S OPERATING HANDBOOK 1999 Kg SENECA II PA 34 200T REPORT VB 1140 FAAAPPROVEDBY LJJ WARD EVANS D O A NO S0 1 PIPER AJRCRAFT CORPORATION VERO BEACH FLORIDA AIRPLANE REGISTRATION NO 9 H RE B DATE 0 0F APPROVAL SEPTEMBER 12 i 980 ...

Page 2: ... FT_ 1 HIS H At DHOOK I ALI D FOR LSE ITH THE AIRPLA E IDENTIFIED 0 THE F CE OF THE TITLE PA GE_ l lBSEQUENT RE I 10 l SL PPLIED Br PIPER AIRCRAFT CORPORATION Ml lST BE PROPERLY 11 SERTED REPORT VB 1140 Published by PUBUCATIO S DEPARTMEJ T Piper Aircraft Corporation j ued S ptem bt r I I l l ...

Page 3: ... additional pages in proper numerical order within each section 3 Page numbers followed by a small letter shall be inserted in direct sequence with the same common numbered page IL Identification of Revised Material Revised text and illustrations shall be indicated by a black vertical line along the outside margin of the page opposite revised added or deleted material A line along the outside marg...

Page 4: ...ca II Pilot s Operating Handbook REPORT VB 1140 issued September 12 1980 Revision Revised FAA Approval Number and Pages Description of Revision Signature and Code Date 4 i llev I Jw Ao 1 tv Ol I Joe k r Mn qe c t 11 QGe l ro L c tl 12AC i l u rL ll 0 r 1A l I 1 I I I 1 I EPORT VB 114i ...

Page 5: ...ON 8 SECTtON 9 SECTION 10 TA BLE OF CONTENTS GENERAL LIMITATIONS EMERGENCY PROCEDURES NORMAL PROCEDURES PERFORMANCE WEIGHT AND BALANCE DESCRIPT ION AND OPE RATION OF THE AIRPLANE AND ITS SYSTEMS AIRPLANE HANDLING SERVICING AND MAINTENANCE SUPPLEMENTS SAFETY TIPS REPORT VB ll40 ...

Page 6: ... No I I int roduction J 1 1 3 Engines 1 3 I 5 Propellers 1 3 1 7 Fuel 1 4 I 9 Qjl 1 4 I I I Maximum Veights 1 4 1 13 Baggage Space 1 5 I 15 Specific Loadings 1 5 1 17 Symbols Abbreviations and Terminology 1 7 I 19 Conversion Factors 1 1 REPORT VB 1140 l i ...

Page 7: ...Cauley l Propeller Hub and Blade Models a Left b Right SECTION l GENERAL Continental TSI0 360E or TSI0 360EB LTSI0 360E or LTSIG 360EB 200 215 2575 4 438 3 875 360 7 5 I Six Cylinder Direct Drive Horizontally Opposed Air Cooled BHC C2YF 2CKF FC8459 8R BHC C2YF 2CLKF FJC8459 8R BHC C2YF 2CKUF FC8459 8R BHC C2YF 2CLKUF FJC8459 8R BHC C2YF 2CKF FC8459B 8R BHC C2YF 2CLKF FJC8459B 8R BHC C2YF 2CKUF FC8...

Page 8: ...de Refer to latest revision of Continental Service Bulletin Fuel and Oil Grades 8 Refer to latest issue of Continental Service Bulletin Fuel and Oil Grades A iation Grade 1065 1100 S A E No 30 50 When operaung temperatures overlap indicated nnges use the lighter grade of oil Multi viscosity oils meeting Teledyne Continental Motors Specifkation MHS 24A are approved 1 11 MAXIMUM WEIGHTS a Maximum Ta...

Page 9: ...34 200T SENECA II Wing Area sq ft 208 7 Min Turning Radius ft 33 2 from pivot point to wingtip n I i 38 lG 81 1 12 5 4 i EPORT VB 1140 2 6 4 DIAMETER 8 E J1 0 fmHt0m 4r L rr er 1 28 7 47 t _ 11 U STATIC GROUND LIME THREE VIEW Figure l I 1 ISSUED SEPTEMBER 12 1980 ...

Page 10: ... responsible for remaining 1Nithin the operating limitations as outlined by instrument markings placards and this handbook Although the arrangement of this handbook is intended to increase its in flight capabilities it should not be used solely as an occasional operating reference The pilot should study the entire handbook to familiarize himself with the limitations performance procedures and oper...

Page 11: ...SECTION 1 GENERAL EPORT VB 1140 6 PIPER AIRCRAFT CORPORATION PA 3 200T SENECA II THlS PAGE lNTENTIONALLY LEFT BLANK JSSUED SEPTEMBER 12 1980 ...

Page 12: ...rtment Volume cubic feet b Entry Width inches c Entry Height inches I IS SPECIFIC LOADINGS a Wing Loading Obs per sq ft b Power Loading lbs per hp I Sea level 2 12 000 ft ISSUED SEPTEMBER 12 1980 FORWARD 15 3 24 21 SECTION I GENERAL AFT 17 3 21 1 I l 0 10 2 REPORT VB 1140 1 5 ...

Page 13: ... sea level is 15 Celsius 59 Fahrenheit The pressure at 5ea level is 29 92 mches hg lOJ3 mb The temperature gradiem from sea leveJ lo the altitude ac which che temperature i 56 5 C 69 7 F is 0 00198 C 0 003566 F per foot and zero above chat altitude Outside Air Temperature is the free air static temperarurc obtained either from mtlighl temperature indicauons or ground meteorological sources adjuste...

Page 14: ...ed co the speed of sound True Airspeed is the airspeed of an airplane relative to undisturbed air which is the CAS corrected for altitude temperature and compressibility Maneuvering Speed is Lhe maximum speed at wh ich application of full available aerodynamic control will not overstress the airplane Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed exten...

Page 15: ...otal weight The extreme center of gravity locacjon wnhin which the airplane must be operated al a given weighc Fuel available for flight planning Fuel remaining after a runout test has been completed m accordance with governmental regulations Weight of a standard airplane including unusable fuel full operating fluids and full oil Standard empty weight plus optional equipment Weighr of occupants ca...

Page 16: ...ication tests The distance required to accelerate an airplane to a specified speed and assuming failure of an engine at the instant chat speed is attained to bring the airplane to a stop Minimum en route IFR altitude A part of a route Each end 01 that part LS identified by l a geographical location or 2 a point at wh ich a definite radio fix can be established fl Weight and Balance Terminology Ref...

Page 17: ... cm 2 Jb sq in Ib sq ft atm lb sq in kg cal in ft atm in Hg lb sq in lb sq ft kg m 2 ft sec ft min mph n oz cu in cu ft I U S gal cm 3 mJ cu in cu yd U S gal l I sec m 3 min MULTIPLY cubic in ches cu in cubic meters m3 cubic meters per minute m3 min cubic yards cu yd degrees arc degrees per second deg sec drams fluid dr 0 drams avdp dr aydp feet fl feet per minute ft min BY 16 39 1 639 x 10 S 5 78...

Page 18: ...SECTION 1 GENERAL EPORT VB 1140 1l PIPER AIRCRAFT CORPORATION PA 34 200T SENECA ll ISS l JED SEPTEMBER 12 J980 ...

Page 19: ...PIPER AIRCRAFT CORPORATION PA 34 200T SENECA Il JSSUED SEPTEMBER 12 198Q SECTION I GENERAL REPORT VB 1140 1 13 ...

Page 20: ...SECTION I GENERAL lEPORT VB 1140 14 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA ll lSSllEO SEPTE IBER 12 1980 ...

Page 21: ...ment Markings 2 3 2 11 Weight Limits 2 4 2 I3 Center of Gravity Limits 2 5 2 JS Maneuver Limits 2 5 2 17 Flight Load Factor Limits Flaps Up 2 5 2 19 Types of Operation 2 5 2 21 Fuel Limitations 2 6 2 23 Gyro Pressure Limits 2 6 2 25 Flight Into Known Icing Conditions 2 6 2 27 Heater Limitations 2 6 2 29 Operating Altitude Limitations 2 6 2 31 Noise Level 2 6 2 33 Placards 2 7 REPORT VB 1140 2 i ...

Page 22: ......

Page 23: ...except in smooth air and then only with caution Design Maneuvering Speed VA Do not make full or abrupt control movements above this speed At 4407 LBS 1999 K_g G W At 3068 LBS 1392 Kg G W CAUflON KlAS 195 163 135 121 Maneuvering speed decreases at lighter weight as the effects of aerodynamic forces become more pronounced Linear interpolation may be used for intermediate gross weights Maneuvering sp...

Page 24: ...a Number of Engines b Engine Manufacturer c Engine Model Number 1 Left 2 Right d Engine Operating Limits 1 Rated Horsepower Sea level 12 000 ft 2 Maximum Rotational Speed RPM 3 Maximum Manifold Pressure Inches of Mercury 4 Maximum Cylinder Head Temperature 5 Maximum Oil Temperature e Oil Pressure Minimwn red line Maximum red line f Fuel Flow Nonnal Operating Range green arc Maximum at Sea Level re...

Page 25: ... Number of Engines b Engine Manufacturer c Engine Model Number 1 Left 2 Right d Engine Operating Llrnits I Rated Horsepower Sea level 12 000 ft 2 Maximum Rotational Speed RPM 3 Maximum Manifold Pressure Unches of Mercury 4 Maximum Cylinder Head Temperature 5 fax imum Oil Temperature e Oil Pressure Minimum red line Maximum red line 0 Fuel FJow Normal Operating Range green arc Maximum at Sea Level r...

Page 26: ... 2CKUF FC8459B 8R BHC C2YF 2CLICUF FJC8459B 8R Avoid continuous operation between 2000 and 2200 RPM above 32 IN HG manifold pressure Avoid continuous ground operation between 1700 and 2100 RPM in cross and tail winds over 10 knots McCauley Propeller Hub and Blade Models a Left b Right When propeller deicing boots are installed Same as above j Propeller Diameter inches Maximum Minimum 2 9 POWER PLA...

Page 27: ...ture Red Line 2 1 1 WEIGHT LOOTS a Maximum Takeoff Weight b Maximum Landing Weight c Maximum Weights in Baggage Compartments Forward Aft PIPER AIRCRAFT CORPORATION PA 34 200T SENECA ll 3 5 PSI to 20 PSI 25 GPH 20 PSI 3 5 PSI either 360 F to 460 F or 240 F to 440 F 460 F either 75 f t O 240 F or 100 F to 240 F 240 F either 30 PSI to 80 PSI or 30 PSI to 60 PSI 10 PSI co 30 PSI and either 80 PSI to l...

Page 28: ...ed Maximwn allowable gross weight is 4407 1999 Kg pounds See Weight and Balance Section for proper loading instructions 2 1 5 MANEUVER LIMITS 94 6 94 6 AU int entional acrobatic maneuvers including spins are prohibited Avoid abrupt maneuvers 2 17 FLIGHT LOAD FACTOR LIMITS Flaps Up a Positive Load Factor Maximwn b Negative Load Factor Maximum 2 19 TYPES OF OPERATIONS 3 8 G No inverted maneuvers app...

Page 29: ...stalled in accordance with Piper drawing 5 or in an FAA approved manner a Pneumatic wing and empennage boots b Electrothermal propeller boots c Electric windshield panel d Heated pitot head e Wing ice light f Heated lift detectors g Propeller spinners must be instaUed 2 27 HEATER LIMITATIONS Operation of the combustion heater above 25 000 feet is not approved L 0 OPERATING ALTITUDE LIMITATIONS Fli...

Page 30: ...andling from Air Traffic Control to racllitate a route or an attitude change to exlt the Icing conditions Unusually extensive lee accumulation on the airframe and windshield In areas not normally observed to collect tee Accumulation of Ice on the upper surface or the wing aft or the protecte l area Accumulation of Ice on lhe engine nacetl es an propsrter spinners farther aft than nomlafly observed...

Page 31: ... of pilot WARNING TURK OFF STROBE LJGHTS WHEN TAXITNG IN VICINITY OF OTHER AIRCRAFT OR DURlNG FLIGHT TH ROUGH CLOUD FOG OR HAZE On the inside of forward baggage compartment door MAXIMUM BAGGAGE TIIlS COMPARTMENT 100 LBS SEE THE LIMITATIONS SECTION OF THE PILOT S OPERATING HANDBOOK On aft baggage closeout MAXIMUM BAGGAGE THIS COMPARTMENT 100 LBS NO HEAVY OBJECTS ON HAT SHELF On instrument panel U P...

Page 32: ...ING LIMITATIONS STATED IN THE FORM OF PLACARDS MARKINGS AND MANUALS NO ACROBATIC MANEUVERS INCLUDING SPINS APPROVED nns AIRCRAFr APPROVED FOR V F R 1 F R DAY NIGHT AND ICING FLIGHT WHEN EQUIPPED IN ACCORDANCE WITH FAR 91 OR FAR 135 In fuJl view of the pilot MAXIMUM TAKEOFF WEIGHT 4407 POUNDS MAXIMUM LANDING WEIGHT 4342 POUNDS ALL WEIGHT IN EXCESS OF 4000 POUNDS MUST CONSIST OF FUEL EXCEPT IN CASES...

Page 33: ...Air Conditioner Off The Air Conditioner Off item in the above takeoff and landing check lists is mandatory for air conditioned aircraft only On storm window DO NOT OPEN ABOVE J29 KIAS Near windshield pane heat switch with windshield heating installation WINDSHIELD PANEL HEAT SEE PILOT S OPERATING HANDBOOK On engine instrument paneJ cm er to left of engine controls with windshield heatmg installati...

Page 34: ...view of the pilot AVOID CONTINl OUS GROUND OPERATION 1700 2IOO RPM IN CROSS TAIL WlND OVER JO KT AVOID CONTINt OUS OPERATIONS 2000 2200 RPM ABOVE 32 MANIFOLD PRESSURE Adjacent to fuel tank fill caps wilh standard fuel tanks installed FUEL 100 130 AVIATION GRADE USABLE CAPACITY 46 5 GAL OR FUEL JOO OR IOOLL AVIATION GRADE Adjacent to fuel tank filler caps with optional fuel tank installed REPORT VB...

Page 35: ...ir Conditioner Off The Air Conditioner Off item m the above takeoff and landing check lists is mandatory for air conditioned aircraft only On storm window DO NOT OPEN ABOVE 129 KIAS Near indsh ield panel heat switch with windshield heating installation WINDSHIELD PMTEL HEAT SEE PILOT S OPERATING HANDBOOK On engine instrument panel cover to left of engine controls with windshield heating installati...

Page 36: ... 66 KIAS Single Engine Landing Single Engine Go Around Air Start Unfeathering Procedure Engine Fire Fuel Management During Single Engine Operation Engine Driven Fuel Pump Failure Landing Gear Unsafe Waming 5 Manual Ex tension of the Landing Gear Gear Up Emergency Landing Engine Failure in king Conditions AJtemator Failure in Icing Conditions Engine Failure with Rear Cabin And Cargo Doors Removed E...

Page 37: ...s The remainder of the section presents amp1ified emergency procedures containing additional infonnation to provide the pilot with a more complete understanding of the procedures These procedures are suggested as a course of action for coping with the particular condition described but are not a substitute for sound judgment and common sense Pilots should familiarize themselves with the procedures...

Page 38: ...SECTION 3 EMERGENCY PROCEDURES PORT VB 1140 2 PlPER AlRCRAFT CORPORATION PA 34 200T SENECA II THJS PAGE INTENTIONALLY LEFf BLANK ISSl f D SEPTE 1B R 12 J980 ...

Page 39: ...BER 12 1980 SECTION 3 EMERGENCY PROCEDURES Prop controJ of inop engine feather _ as reqmred Trim Auxiliary fuel pumps OFF except in case of engine driven pump failure Magnetos of inop engme OFF Cowl flaps close on inop engine as required on operative engine OFF reduce OFF inop engine consider crossfeed Alternator of inop engine Electrical load Fuel management ENGINE FAILURE DURING TAKEOFF Below 85...

Page 40: ...ER Trim adJUSt s bank toward operative eng nop eng complete En gine Securing Proce Oure owl tlap operative eng as required RE PORT IB 1140 3 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA Il ENGINE FAILURE DURING FLIGHT Above 66 JOAS Rudder lnop eng Operative eng apply toward operative engine identify adjust as required Before securing inop engine Fuel flow check if deficient auxiliary fuel p wnp Hl...

Page 41: ...s extinguish with best available means If external fire extinguishing is to be applied Fuel selector valves OFF Mixture idle cut off lSSLED SEPTEMBER 12 1980 SECTION 3 EMERGENCY PROCEDURES ENGINE FrRE IN FLIGHT Affected engine Fuel selector Tiuottte Propeller Mixture Heater Defroster OFF close feather idle cut off OFF OFF tf terrain permits land immediately if fm continues FUEL MANAGEMENT DUR ING ...

Page 42: ... reposition clip downward clear of knob ind proceed as follows irspeed ear selector reduce 85 KIAS max GEARDOWN LOCKED position Smerg gear ex tend knob pull ndicator lights 3 green eave emergency gear extension knob out REPORT VB 1140 J 6 PIPER AIRCRAFT CORPORATION PA 34 200T SENF CA II ENGINE FAILURE IN ICING CONDIDONS Select alternate air and attempt restart Ifunable to restart engine lnop prop ...

Page 43: ...G Compass error may exceed 10 with both alternators inoperative GYRO PRESSURE FAILURES Pressure below 4 5 in Hg RPM Altitude increase to 2575 descend to maintain 4 5 in Hg Use electric turn indicator to monitor Directional lndicator and Attitude Indicator performance COMBUSfION HEATER OVERHEAT Unit will automatically cut 0ff Do not attempt to restart ISSCED SEPTEMBER 12 1980 SPINS 11tr0ttles Rudde...

Page 44: ...SECTION 3 EMERGENCY PROCEDURES EPORT VB 1140 8 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA Il THIS PAGE INTEKTIONALLY LEFT BLANK ISSllED EPTEMBI R 12 1980 ...

Page 45: ...he HI position ff power is not immediately restored tum off the auxiliary fuel pump Keep in mind that the minimum single engine control speed is 66 KlAS and the best single engine rate of climb speed is 89 KIAS when beginning the feathering procedure To feather a prope11er maintain direction and an airspeed above 76 KIAS Move the mixture and propeller controls forward The throttle controls should ...

Page 46: ...nt considering loading density altitude obstructions the weather and the pilot s competence If the decision is made to continue the takeoff maintan heading and airspeed Feather the inoperative engine and when climb is established RETRACT the landing gear Refer to Engine Securing Procedures paragraph 3 7 During a short field takeoff with 25 flaps the airplane is momentarily below Vmc In the event t...

Page 47: ... the fuel flow is deficient tum 0 the auxiliary fuel pump to the inoperative engine Check the fuel quantity on the inoperative engme side for a sufficient supply switch the alternate air ON and vary the mixture control posjtion Check the oil pressure and oil temperature and insure that the magneto switches are ON If the engine fails to start it should be secured using the Engine Securing Procedure...

Page 48: ... ENGINE FIRE lN FLIGHT The possibility of an engine fire in light is extremely remote The procedure given below is general and pilot judgment should be the deciding factor for action in such an emergency If an engine fire occurs in light plaoe the fuel selector of the affected engine in che OFF position and close its throttle Feather the propeller on the fauJty engine Move the mixture contro1 to i...

Page 49: ...erating engine For tttls configuration the fuel selector of the operating engine should be on X FEED crossfeed and the fuel selector of the inoperative engine should be OFF The auxiliary fuel pumps should be OFF LANDING NOTE A vapor return line from each engine will return a percentage of fuel back to the tank on the same side as that engine Th erefore a minimum of 30 minutes of fuel should be use...

Page 50: ...Actuation of the HI switch position when the engines are operating nonnally may cause engine roughness and or power Joss 3 15 LANDING GEAR UNSAFE WARNINGS The red landing gear light will illuminate when the landing gear is in transition between the full up position and the down and locked position The pilot should recycle the landing gear if continued illumination of the light occurs Additionally ...

Page 51: ...9 KIAS during final approach Do not ex tend the landing gear or lower the wing flaps until certain of making the field Use 25 flaps rather than fuJl flaps for landing 3 23 ALTERNATOR FAILURE IN ICINGOONDIDONS If an alternator fails during flight in icing conctitions an attempt shouJd be made to reset the alternator overvoltage relay by cycling the corresponding alternator switch OFF and then ON Ch...

Page 52: ...ass error may exceed l 0 with both alternators inoperative NOTE The markings on the ammeters loadmeters requi re mental interpolations to estimate the ampere values noted Operating the alternators at less than 65 amperes wiJI assure that the battery will not be depleted 3 29 GYRO PRESSURE FAILURES A malfunction of the instrument pressure system will be indicared by a reduction of the pressure read...

Page 53: ...end the landing gear at 129 KIAS and maintain this airspeed 3 37 DOOR OPEN ON TAK EOFF 1f either the main or rear cabin door is inadvertently l eft open or partially open on takeoff fly the airplane in a normal manner and return for a landing to close the door on the ground If a landing cannot be made it may be possible to close a door in flight Maintain an airspeed between 85 and 94 KIAS and open...

Page 54: ...er System Starting Engines when Flooded Starting Engines in Cold Weather Standard Primer System _ Starting Engines with External Power Taxiing Before Takeoff Ground Check TakeoTf Climb Cruising Descent Approach and Landing Go Around After Landing _ Shutdown Mooring Turbulent Air Operation Flight Into Known Ic ing Conditions Flight with Rear Cabin and Cargo Doors Removed VSSE Intentional One Engine...

Page 55: ...ons with little emphasis on the operation of the systems The remainder of the section is devoted to amplified normal procedures which provide detailed information and explanations of the procedwes and how to perfonn them Tiris portion of the section is not intended for use as an in flight reference due to the lengthly explanations The short form check lisl should be used for this purpose 4 3 AIRSP...

Page 56: ...SECTION 4 ORMAI PROCEDURES EPORT VB 1140 p PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II TIIlS PAGE ll 1TENTIONALLY LEFT BLA1 1 IS l 0 SEPTEMBER 12 1980 ...

Page 57: ...on board suitable weighed stowed tied within limits planned on board computed and safe INSIDE CABJN Landing gear control Avionics Master switch Landing gear lights Fuel quantity Cowl flaps Master switch Ignition switches Mixture controls Trim indicators Flaps Controls Pitel and static systems Empty seats Cro feed drains DOW position OFF ON 3 GREEN no red adequate plus reserve OPEN OFF OFF idle cut...

Page 58: ...nators REPORT VB 850 adjusted fastened set in OFF OPEN OFF ON PIPER AlRCRAFf CORPORATION PA 34 200T SENECA II STARTING ENGINES AIRPLANE EQUIPPED WITH STANDARD ENGINE PRIMER SYSTEM Fuel selector Mixture Throttle _ Propeller Master switch Ignition switches Propeller Starter Primer button Throttle ON RICH half travel FORWARD ON ON clear engage ON as required retard when engine starts Oil pressure che...

Page 59: ...y hand 3 times ON full RICH full FORWARD full FORWARD ON ON ON LOW boost engage On for 3 sec full FORWARD to full AFT ON 3 sec then OFF 3 sec then ON 3 sec lSSt ED SEPTEMBER 12 1980 SECTION 4 NORMAL PROCEDURES When engme fires Starter Primei button Starter Throttle Oil pressure Ifengine begins to falter Primer button Throttle Auxiliary fuel pump leave engaged tap until rhythrmc firing release half...

Page 60: ...sition adjusted OFF set erect set set fastened seat belts fastened free full travel latched OFF as required PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II TAKEOFF CAUTIONS Do no1 exceed 40 in Hg manifold pressure Fast taxi tums immediately prior to takeoff run can cause temporary malfunction of one engine during takeoff Normal sea level takeoff at 39 in Hg and 2575 RPM Adjust mixture prior to tak...

Page 61: ...l flaps set as required _adjust monitor enrich with descent cruise setting CLOSED JSS UED S PTEMBER 12 1980 SECTION 4 NORMAL PROCEDURES APPROACH AND LANDING Gear warning horn check Airspeed 98 KlAS on downwind leg Seat backs _ erect Seat belts and harness fastened Fuel selectol 3 ON Cowl flaps _ as required Auxiliary fuel pumps _ OFF Mixture controls _ _set Propellers 2250 RPM Landing gear DOWN I2...

Page 62: ...SECTION 4 NORMAL PROCEDURES REPORT VB 1140 4 8 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II THJS PAGE INTENTIONALLY LEFT BLANK ISSt E O SEPTEMB ER 12 1Q80 ...

Page 63: ...t wear on the units and turn the master switch ON Check the landing gear indicator tights to insure that the three green lights have illuminated and the red light has not illwninated Check the fuel supply Adequate fuel should be indicated for the flight plus reserve The cowl naps should be OPEN to facilitate inspection and ensure cooling after engine start Retwn the master switch to OFF to save th...

Page 64: ... of the airplane the windshield should be clean secure and free from cracks or distortion Mewing around to the left wing check the wing engine nacelle and landing gear as described for the right s Don t forget to check the fuel and oil If a pitot cover was instaJled it should be removed before flight and the holes checked for obstructions With the heated pitot switch on check the heated pitot head...

Page 65: ... of 20 F with engines equipped with standard massive electrode spark plugs Below that temperature fine wire spark plugs are highly recommended to ensure engine starts and are a necessity at I 0 F and below In addition the use of external electrical power source is also recommended when ambient temperatures are below 208 F Upon entering the cockpit begin starting procedure by moving the fuel select...

Page 66: ...l to idle cut off and advance the throttle and propeller mtrols fu U forward Turn ON the master switch and ignition switches The auxiliary fuel pump should be FF After ensuring that the propeller is clear engage the starter When the engine fires retard the throttle td ldvance the mixture slowly 19 STARTING ENGINES IN COLD WEATHER lAIRPLANE EQUIPPED WITH STANDARD ENGINE R ER SYSTEM EPORT VB 1140 1 ...

Page 67: ... Ihythmic firing pattern is observed and then release the starter switch and position the throttle at llalf travel Tap the primer button if the engine begins to falter during this period and adjust the throttle to a I000 RPM idle speed The auxiliary fuel pump may be turned OFF as soon as it is determined that the engine will continue to run without i t 4 21 STARTING ENGINES WITH EXTERNAL POWER An ...

Page 68: ...heck the operation of the fuel managemenl controls by moving each fuel selector to CROSSFEED for a short time while the other selector is in the ON position Return the selectors to the ON position DO NOT attempt a takeoff with the fuel selector on CROSSFEED The autopilot if installed should be off during raxi 4 25 BEFORE TAKEOFF GROUND CHECK A thorough check should be m ade before takeoff using a ...

Page 69: ...should be adjusted Check to make sure the alternate air is OFF Adjust the cowl flaps and set the wing naps and trim sLabilator and rudder tabs as required The seat backs should be erect and seat belts and harnesses fastened Fasten the seat belts on the empty seats All controls should be free with full travel and all doors should be securely latched Emure that the auxiliary fuel pumps are OFF Pitot...

Page 70: ...0 IN HG MANIFOLD PRESSURE The flap setting for normal takeoff is 0 In certain short field takeoff efforts when the shortest ossible ground roll and the greatest clearance distance over a 50 ft obstacle is desired a flap setting of 25 recommended Vhea obstacle clearance is no problem a normal flaps up 0 takeoff may be used Accelerate to 6 71 KlAS and ease back on the wheel enough to let the airplan...

Page 71: ...ion of Utis Handbook 4 29 CLIMB On dimtrout after takeoff it is recommended that the best angle of cl imb speed 76 KlAS be maintained only if obstacle clearance is a consideration The best rate of climb speed 89 KJAS should be maintained with full power on the engines until adequate terrain clearance is obtained At this point engine power shouJd be reduced to 31 5 inches manifold pressure and 2450...

Page 72: ...icing is encountered immediate action should be taken to fly out of icing conditions Icing is hazardous due to greatly reduced performance loss of forw d visibility possible longitudinal conrrol difficulties due to increased control sensitivity and jmpaired power plant and fuel system operation The ammeters for the electrical system should be monitored during flight especially dunng night or instr...

Page 73: ...ow and fuel quantity gauging systems are operating If the fuel flow indication is considerably higher than the fuel actuaJly being consumed or if an asymmetric flow gauge indication is observed a fuel nozzle may be clogged and require cleaning There are no mechanical uplocks in the landing gear system In the event of a hydraulic system malfunction the landing gear wilJ free fall to the gear down p...

Page 74: ...250 RPM Se1ect landing gear DOWN and check for three green lights on the a and look for the nose wheel in the nose wheel mirror The landing gear should be lowered at speeds elow 129 KIAS and the flaps at speeds as follow I0 first notch 138 KJAS maximum 5 second notch 121 KIAS maximum 40 third notch 107 KIAS maximum Maintain a traffic pattern speed of 98 KlAS and a final approach speed of 83 KlAS l...

Page 75: ...osswind or high wind landing is necessary approach with higher th an normal speed and with zero to 25 degrees of flaps Im mediately after touch down raise the flaps During a crosswind approach hold a crab angle into the wind until ready to flare out for the landing Then lowe r the wing that is into the wind to eliminate the crab angle without drifting and use the rudder to keep the wheels aligned ...

Page 76: ...th seats Tie down ropes may be attached to mooring rings under each wing and to the ail skid The ailerons and stabilator shou1d be secured by ioopin_g the seat belt through the contro1 wheel md pulling it snug The _rudder need not be secured under normal conditions as its connection to the nose Nheel holds it in position The flaps are locked when in rhe fuUy retracted position 4 45 TURBULENT AIR O...

Page 77: ...rom Air Traffic Conlrol to facililate a route or an allitude change lo exil the severe icing conditions in order to avoid extended exposure to flight conditions more severe than those for which the airplane has been certificated Avoid abrupt and excessive maneuvering that may exacerbate control dirticultie Do not engage lhe autopilot H t he autopilot is engaged hold the control wheer firmly and di...

Page 78: ... or repaired so that the performance ofthe requirements ofthis AD is affected lhe owner operator must request approval for an alrernati e method ofcompliance in accordance with paragraph d ofthis AJ The request should include an assessment of the effect ofthe modification alteration or repair on the unsate condition addressed by this AD and if 1 he unsafe condition has not been eliminated lhe requ...

Page 79: ...in2 ffoiht severe icin conditions that exceed those for which the airplane 1s cenificated shall be detennined by the following visual cues Irone or more of these visual cues exists immediately request priority handling from Air Tratlic Control to facilitate a route or an altitude change to extt the icmg conoi11ons l Jnusually extensive ice accumulation on the airframe and windshield in areas nol n...

Page 80: ...he visual cues specified in the Limitations Section of Lhe AfVJ for identifying severe icing conditions are observed accomplish the following immediately request prionty handling from Air Traffic Control to facilitate a route or an altitude change to exit the severe icing conditions in order to avoid extended exposure to flight conditjons more severe than hose for which the airplane has been certi...

Page 81: ...d d An alternative method ofcompliance or adjustment ofthe compliance tune ihat provides an equivalent eve of safety may be approved by che Manager Small Airplane Directurate FAA 120l Walnut suite 900 Kansas Ciry Missouri 64106 The request shall be forwarded through an appropriate FAA Maintenance lnspeclor ho may add comments and then send 11 to the vlanager Small Airplane Directorate l OTE 3 Jnfo...

Page 82: ...ots should be cycled when ice has built to between 1 4 and I 2 inch thickness on the leading edge to assure proper ice removal Repeated boot cycles at less than l 4 inch can cause a cavity to fonn under the ice and prevent ice removal boot cycles at thicknesses greater than l 2 may also fail to remove ice Icing conditions can exist in any clouds when the temperature is below freezing therefore it ...

Page 83: ...g full flaps and carrying a slight amount of power whenever practicaJ and 1pproach speeds should be increased by l 0 to 15 knots Cruise speed may be significantly reduced in prolonged icing encounters lf icing conditions are ncountered at aJtitudes above 10 000 feet jt may be necessary lo descend in order to maintain airspeed 1bove the best rate of climb speed 89 KlAS NOTE Pneumatic boots must be ...

Page 84: ... It is recommended that all occupants wear parachutes when operating with the rear cabin and cargo doors removed All climb and cruise performance will be reduced by approximately five percent when the airplane is operated with the rear cabin and cargo doors removed 4 51 VssE INTENTIONA1 ONE ENGINE INOPERATIVE SPEED Vsse is a speed selected by the aircraft manufacturer as a training aid for pilot s...

Page 85: ... ground Initiate recovery during the emonstration by immediaieJy reducing power on the operating engine and promptly lowering the nose of 1e airplane IO accelerate to Vsse In the Seneca It more power is available on tile operating engine at higher aJtitudes with the same i ifold pressure hence there can be more asymmetric thrust The Vmc in the Seneca II is lowest at low 1 1des and the airplane wil...

Page 86: ...BLE OF CONTENTS SECTION 5 PERFORMANCE Page No 5 1 General 5 I 5 3 Introduction to Performance and Flight Planning _ 5 1 5 5 Flight Planning Example 5 3 5 7 Performance Graphs 5 7 List of Figures 5 7 REPORT YB 1140 S i ...

Page 87: ...not make any allowance for varying degrees of pilot proficiency or mechanical deterioration of the aircraft This perfonnance however can be duplicated by following the stated procedures in a properly maintained airplane Effects of conditions not considered on the charts must be evaluated by the pilot such as the effect of soft or grass runway surface on takeoff and landing perforrnance or the effe...

Page 88: ...SECTJON 5 PERFORMANCE EPORT VB 1140 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA Il TH1S PAGE INTENTIONALLY LEFT BLANK ISSUED SEPTt MBER 12 nsu ...

Page 89: ...l to be used bas been established refer to j tern g I l Basic Empty Weight 2 Occupants 3 x 170 lbs 3 Baggage an d Cargo 4 Zero Fuel Weight 4000 lb max allowable 5 Fuel 6 lb gal x 95 6 Takeoff Wejghl 4407 lb max allowable 7 Landing Weight 4342 lb max allowable a 6 minus g J 4290 lbs minus 303 lbs 2790 lbs 510 lbs 420 lbs 3720 lbs 570 lbs 4290 lbs 3987 lbs Our takeoff and landing weights are below t...

Page 90: ...cruise outside air temperature values are the first variables to be considered in determining the climb components from the Time F uel and Distance to Climb graph Figure S 2J After the time fuel and distance 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 obta...

Page 91: ...ng the flight subtract the previously calculated distance to clirnb and distance to descend to establish the totaJ cruise distance Refer to the appropriate Teledyne Continental Motors Operator s Manual and the Power Setting Tables Figures 5 23 or 5 25 when selecting me cruise power setting The established pressure altitude and temperature values and the selected cruise power should now be utilized...

Page 92: ...ght planning example 1 Total Flight Time c 3 plus d I plus e 6 15 hrl plus 23 hrs piu 2 16 hrs g Toral Fuel Required 2 54 hrs Determine the rotaJ fuel required by adding the fuel to climb the fuel to descend and the cruise fuel When the totaJ fuel in gallons is determined multiply this value by 6 lb gaL co determine the total fuel weight used for the flight The toca1 fuel calculations for our exam...

Page 93: ...Table 45 and 55 Power Setting Table 65 and 75 Non Standard Temperature Range With Maximum Power Oimb 93 Usable Gal Standard Temperature Range With Maximum Power Climb 93 Usable Gal Non Standard Temperature Range With Maximu m Power Climb 123 Usable Gal Standard Temperature Range With Maximum Power Climb 123 Usable Gal Speed Power T ime Fuel and Distance to Descend Landing Distance Normal Procedure...

Page 94: ...SECTIO S PERFORMANCE EPORT VB 1140 PIPER AJRCRAFJ CORPORATION PA 34 200T SENECA Il TH1S PAGE JNTENTIONALLY LEFT BLANK I S ll l O SEPTEMBER 12 1980 ...

Page 95: ... v y 110 V I I v v c 160 z A Cl 150 w I I I I I w I 140 V a I I I I c Cl 130 w I I I I I I CIC 120 a c c 1 1 t __ H t I Y IT I 110 c i I v I I J I I IOO 90 110 70 60 I v 1 I t s Y I I o l I _ I u__ I I 1 I I T I I I I I I I I I I o 10 so 90 1oo no no no w1 1so 1s o 110 1110 190 200 INDICATED AIRSPEED KNOTS Example l 22 KlAS l 23 KCAS AIRSPEED CORRECTION NORMAL SYSTEM Figure 5 1 ISSl ED SEPTEMBER 1...

Page 96: ...D BELOW 78 KTS GEAR ANO f FLAPS DOWN __ _ I I I j t I j I I I I I GEAR UP FLAPS UP GEAR DOWN 40 FLAPS o I 1 1 11 _ i I _ __I _ V 1 I _ I _ ___ I __ tl ___I ___ _ i V1 t1 I L I I 1 I _ I 17 _ I _ __ I I 1 I __ V __ I _ 17 i j I v v i I t v I t 1 I I V r IS r 1 1 y I w _ ___ t _ s I I _v I I l v I _ _ I J _ _ I fY 1 _ I I 1 __ __ 50 40 4 c J 31 o l _ IC 30 z C I Cl C I io io t n 20 I0 i c rt 1 70 80...

Page 97: ...SS DURING STAU RECOVERY IS APPROX 550 FT __ __ _ ___ P0W ER 0ff I00 LANDING GEAR UP OR DOWN I 1 i l i I l I I I I 45 40 35 30 25 WEIGHT 100 LBS Example Gross weight 4250 lbs 0 Angle of bank 15 Flap position 0 Calibrated stall speed 64 knots ISSUED SEPTEMBER 12 1980 45 40 35 30 25 WEIGHT 100 LBS STALL SPEEDS Figure 5 5 o 10 20 30 40 50 ANGLE OF BANK DEGREES REPORT VB 1140 11 ...

Page 98: ...ING 4407 POUNDS 1999 KG ZERO W IND PA VED LEVEL DRY RUNWAY I I I I l I I I I I I J I I v 1 II J v I v I I v I v I I I y v A 1 I Y I J V I I I I V I I I I I I I I v I I I I I J A 1 I I j I I 4 I I J I l I fy I I J v v I v I V I I I I J I 1 I v I I I v O 20 0 20 40 GD RO 100 24Ell 2600 3200 3600 4000 OUTS IOE AIR TEMP 0 f ACCELERATE AMD STOP DISTANCE FT 20 0 20 40 OUTSIDE AtR TEMP C Example OAT 40 F...

Page 99: ...VED LEVEL DRY RUNWAY ___ I I NO TE D ISTANCES INCLUDE A THRH SE DMO RECOGHlTION TIME STD TEMP i I I I v y 1 i I I I 1 I I I v y V r I I I 1 11 y I r y 11 I I I I I v I I I I I I I v I I I I v v j I A I I I 1 l I I I I I I I I I I I I r I I v I l v I I 40 20 0 20 40 60 80 1DO 2000 2400 2800 3200 36110 4000 4400 OUTSIDE AIR TEMP 0 f ACCELERATE AND STOP DISTANCE FT 20 0 20 40 OUTSIDE AIR TEMP C Examp...

Page 100: ...H ft I _ v r r 7 t t _I 17 _ r 1 _ S _ _I _ _ ____ I I _ L _ 20 0 20 40 60 80 100 4500 OUTSIDE AIR TEMP F 20 0 20 40 OUTSIDE AIR TEMP C Example OAT 70 F Pressure altitude 2000 ft Gross weight 425 0 lbs Headwind 9 knots Takeoff ground roll I000 fL r t i __ r r i _ i r k r r r 1 1 1 _ _ 4000 3500 3000 WEIGHT POUNDS LIFT OFF 66 KIAS _ _ ____ u 11 1 1 I _J L I cs I _ r I _ I t r tS r f r r t 1 t l _ _...

Page 101: ... r t _ t I v v I r K _ v P r v v _ l r I t L f i v i c f t I t t I I It r v I _ __ r i r r v _ _ v L i __ _ i _ _ V r r r I _i I __ I v f v i s s _ _ zo o 20 40 so ao too 4500 OUTSIDE AIR TEMP 0 f 20 0 20 OUTSIDEAIR TEMP C Example OAT 70 F Pressure altitude 2000 ft Gross weight 4250 lbs Headwind 9 knots Takeoff ground roll 750 ft 40 l 1 i _ r _ r ___ __ t 1 t t i _ _ _ r ___ i r 4000 3500 3000 WEI...

Page 102: ... r v I __ _ _ _ t _ I _ r r i I _ 1 t r t 1 _ t r r _i r d r H __ i _ _ I I I 20 0 20 40 60 80 100 4500 4000 3500 3000 OUTSIDE AIR TEMP F WEIGHT POUNDS 20 0 20 40 OUTSIDE AIR TEMP C Example OAT 40 F Pressure altitude 7586 ft Gross weight 4290 lbs Headwind I0 knots Takeoff distance over 50 ft obstacle 1540 ft H _ r _ _ LL i r7 _ _ _ _ _ J rT K t _ _ t r 2 _ _ _ _ K __ _ l o t t R __ Ii _ r _ b F r ...

Page 103: ...l v v I r t L L I I a 1 7 f 1 _ _ I I i o _ __ 17 t 1 r r I I v L v O I f v tr en 17 t en r I t r I r v itc r r v _ f i C I _ _ t I v I r __ h t r r ___ __ l r 1 r t k k _ 1 i c h I 1 _ 1 r t t r r _ I h l 20 0 20 40 60 80 100 4500 4000 3500 3000 2500 0 5 I0 15 20 25 OUTSIDE AIR TEMP F 20 0 20 40 OUTSIDE AIR TEMP 0 c Example OAT 70 F Pre l ure altilllth 1500 fl Gros weight 4250 lb s Hendwiml 9 kno...

Page 104: ... I WING FLAPS o0 vv 1 v I fl r i 7 H tg _ L V _ V ii e I v v 7 1 i J I y ii v r I cP i v V _1 i v I I f rd _ v _ v vv v r fl _ _ L i _ _ _ v v v r 1 1 1 1 v v v fl I I I v v v CD I CID v V v fl l fl l s I t __ c _ _ I _ v v I 1 l v v z u I v v I z v I L f v c I I g v 7 v __ T J J ft I v v v ye I v f I 40 20 0 20 40 60 80 100 120 0 400 BOO 1200 1600 2000 0 200 400 600 OUTSIDE AIR TEMP 0 f 20 0 20 4...

Page 105: ... _ _ j I II I 11 I I 1 f __ I ilf I IJ 1 J I I 7 I L _ 1 l i l 1 1 1 1 i 2 Olli 1 I l 1 I I I I I I I r A I I I _ Qllllll t t t II 14 s6oo f 4 sboo I I PRESS Ap fi1 I 1 4000 r 1 I I I II I I I 12000 I I 1 I l 0 20 0 20 40 60 80 100 OUTSIDE AIR TEMP F 30 20 10 0 10 20 30 40 OUTSIDE AIR TEMP C I I I II 0 20 40 60 80 TIME DISTANCE FUEL TO CLIMB Example Takeoff pressure altitude 7586 ft Takeoff OAT 40...

Page 106: ...22 J 21 8 2 1 0 20 6 20 0 19 4 18 8 3 1 8 30 8 2Y 8 29 0 55 POW ER APPROX 18 GPH FUEL CONS 2200 I JOU I 2400 I 25 2575 NCl IES MPRCURY 29 28 5 28 0 27 4 2ri r 26 0 25 0 24 S 24 0 28 4 27 6 27 0 2ft 4 25 6 25 0 24 4 23 8 23 4 22 8 27 0 26 4 25 8 25 2 24 8 4 2 23 8 23 0 2 G 22 0 21 6 26 0 2 4 25 0 M 4 25 ti 25 U 24 6 4 0 24 o I 23 8 23 6 I 21 2 23 0 I 22 8 22 6 I 22 4 12 0 21 Cl 20 8 u c1 20 4 20 0 ...

Page 107: ...J 1 6 6000 I I 31 ti 3fLU 29 0 28 0 27 8 3 1 6 n o J 1 4 30 9 8000 I I 10000 10 6 29 6 28 4 27 6 27 4 13 0 31 1 J 0 8 30 J 28 8 27 H 27 0 27 0 32 4 J 1 u 30 2 29 8 12000 I l 14000 I I 28 0 27 2 26 6 26 4 3 1 6 30 4 29 8 29 J 27 4 26 G 26 0 26 0 29 8 29 2 29 0 16000 I 17 18000 2 1 26 7 26 0 25 8 25 6 29 4 28 8 8 l 25 6 25 2 25 0 28 4 28 3 20000 25 24 8 24 8 2H O 22000 28 24 4 24 4 4000 n 24 0 25000...

Page 108: ...75 506 537 529 549 25 505 540 562 575 584 35 526 564 593 607 613 45 533 574 599 613 625 I 55 539 575 5 606 635 65 576 590 595 0 491 526 558 555 568 10 520 558 590 598 60 1 20 537 577 606 623 626 JO 542 584 607 620 636 40 548 582 602 61 2 646 50 580 597 606 30 521 561 594 600 603 20 54 585 617 632 634 10 553 598 6n 63 645 0 560 598 620 632 657 10 20 45 536 I 576 nlO 619 620 35 553 5 627 643 642 25 ...

Page 109: ...KIAS NO WIND 1 1 l 4 2 GAL FUEL FOR START TAXI ANO T O L A GE NO RESERVE _ 2500 RANCE WITH 45 MIN RESERVE 11 _ _ _ _ AT 45 POWER _ __ 1 __ l 11 ffi 2000 I a IX ___ a I T ln L 1 n c t __ 1 1 _ o a 15000 4l I L _ L 1 _ l o __ l a I 1 J l e _ _ I 11 10001 o I 1 c 0 0 I I I Q __ J _ fJ V _ 1 j I d _ 5000 I I II 1 1 I _ _ I on rf 1 II I J J I J _ e iJ1 a I f I 500 600 500 600 700 RANGE NAUTICAL MILES E...

Page 110: ...5 734 25 105 750 800 807 785 35 742 797 840 859 829 45 761 821 857 878 852 55 778 832 864 880 874 65 835 860 874 0 682 731 775 771 759 0 728 782 827 38 812 20 759 816 858 882 48 30 715 839 870 888 868 40 792 843 874 888 890 50 841 869 882 30 724 780 826 833 806 20 762 819 864 886 850 10 781 846 883 904 873 0 800 857 889 905 97 Q 20 45 745 801 848 860 829 35 774 835 879 903 864 25 793 857 892 912 8...

Page 111: ... FLAPS UP CLIMB AT M C P DESCENT AT 1000 FPM AND 129 KIAS NO WIND 4 2 GAL FUEL FOR START TAXI AND T O I I I I I I I I RANCE WITH 45 MIN RESERVE RANGE NO RESERVE 1 I 1 I I AT 45 POWER I I I I I I I 4 5 POWER I 45 POWER I I t _ I I I I I I 55 r 55 1 J I 1 J 65 1 I I I 65 f 7 I 75 I f 17 t I I I I I_ I II J I L I I I I I I I I 1 I I I V1 I I I 1 l r r _ 1 I I 700 800 900 r 100 800 900 1000 RANGE NAUT...

Page 112: ...Y v v l vV I r I _L 7 7 I l7 v I I J v ____ _ __ f t _ I Vi i r b L _ l Lv l i v L I J __ I _ V1 v l 1 v 1 v c _ I I I l I 1 _ II 1 c I v 1 v _ _ L _ __ ti i J v V 1 I v i 7 _ v y t7 hq I v I I I I 40 20 0 20 40 8D 80 100 120 120 OUTSIDE AIR TEMP F 140 160 180 TRUE AIRSPEED KNOTS 20 0 20 40 OUTSIDE AIR TEMP C example OAT 8 F Power 55 Pressurt altilude 16 500 ft Tnie airspeed 16 1 knots _ 1 1 _ __ ...

Page 113: ... I f 1 1 1 I 1r 17 1 It I VI I _ I 1 1 1 1ooo o I I I I I i l j I PRESS ALT FT 8000 1 1 I _ 1 sooo 4000 I I I I I I I 1 i 2000 Js iA LEVEL 40 20 0 20 40 60 80 100 OUTSIDE AIR TEMP F 20 0 20 40 OUTSIDE AIR TEMP C Example Landing pressure altitude 441 I FL Landing OAT S0 F 1 J _ 1 1 l l hvI I I 1 l v 1 I r1 1 0 20 40 60 TIME DISTANCE FUEL TO DESCEND Cruise pressure altitude 16 500 ft Cruis OAT 8 F T...

Page 114: ...b 1 I I 1 j I r 1 i _ i lL I I r i 1 I I I I 1 1 _ v 11 _ r L __ T i _ i l_ i _ c __ __ i 1 _ I r _ _ h r rr to V _ r _ _ o ___ r J I r ___ I 1 l K 20 0 20 40 60 80 I00 4342 4000 3500 3000 2500 0 5 10 15 20 25 OUTSIDE AIR T MP 0 f J 20 0 20 40 OUTSIDE AIR TEMP C Example OAT 50 F Pressure altitude 441 1 ft Gross weight 4006 lbs Headwind 5 knots WEIGHT POUNDS Landing distance over 50 ft obstacle 259...

Page 115: ...h4 l l 1 I I I I I I I I HI II IJJl1 tfttft 1 1 fiiErn ti I __ _ l I 1 1 1 1 _ _ 1 l I 1 _ 1 1 1 1 I 1 r z C 7 z C 3000 c z 2600 c V loo z 22 00 c io c 1800 i c QO V s C 1400 r 4 I I I I J I I I I I I I I II I I I I I I I I I I I I I I I I I I I I I I I I I I I I000 20 0 20 40 60 80 100 4342 4000 3500 3000 OUTSIDE AIR TEMP F j W E IGHT 1 POUNDS 20 0 20 40 OUTSIDE AIR TEMP C Example OAT 70 F Pressu...

Page 116: ...I I 1 v 1 I STD TEMP i I I I 1 I I 1 I I 1 1 _ _ r ty k I 1 U _ I J f t L J It IC I i t J v N f 1 I b 1 1 L 1 i J l L J r t i t L J i 1 i t 1 l _ fo t __ t 1 M I r f 1 st J lll I I r 1 Ct t 1 t r r I I L t t 1 t t _ I ti r I r _ r _ r t I r r t r J _ 1 f 1 r b r r I I f _ t r r r r r t t 1 c r r t 2 r r r r 20 0 20 40 60 60 100 4342 4000 3500 3000 2500 0 5 10 15 20 25 3800 3400 z 0 n 3000 z n c 26...

Page 117: ...I I I 220 0 n l 1 i p i l I K _ I I _L i L 1 M n r r i I ltr4 i _ i r t y I N IJ iu I I 1 l i 1 1 __ 1 _ r i _ l IT 1 i _i L i _ r _ t _ I t i 1 1800 _i i fl lS fl l f f t r r r r __ 1 r iJ r 1 1 J Do z c J z en c J z M Cl c U I C I C o i V 4 a M I I I I __ __ t r r r r r r t I r _ r Y r __ 1400 I r r r t I I f r i J_j_J I I r I i 1 I I I I I I Tl l I I I t 1000 20 0 20 40 60 80 100 4342 4000 3500...

Page 118: ... t r I r I I _ k J k r j_ _i v I i P s L 9 l tS I s I _ I __ 20 0 20 40 60 80 100 4342 4000 OUTSIDE AIR TEMP 0 f 20 0 20 40 OUTSIDE AIR TEMP C Example OAT 70 F Pressure altitude 2000 ft Gross weight 4000 lbs Headwind 9 knots Landing ground roll I200 ft I I I I I l ____ I I t I _ I I I V II I I QC I I f I I I I I r I I I I r I I v r I I II I r _ r7 ti _ f No 1 r I k N _ I I I I J _ I r 1 r r r I 1 ...

Page 119: ...TD TEMP i 1 1 I l 411 A l l I 1400 r z c z 1200 Q c z c I 0 _ __ __ ___ __ _____ 1000 4 1 4 I B00 I 1 I 1 J l l 4 f l I 600 I I I I I I I I I I I I 1 i l 1 l H11_ 4 i __ __ _ _ _ _ __ _ __ _ _ _ _ __ _ _ _ _ _ _ _ __ __ _ _ _ _ _ l l lo 4 0 0 20 0 20 40 60 80 100 4342 4000 3500 3000 2500 0 5 10 15 20 25 OUTSIDE AIR TEMP F WEIGHT POUNDS 20 0 20 40 OUTSIDE AIR TEMP C Example OAT 70 F Pressure altitu...

Page 120: ...nding Gear and Brakes _ _ d Electrical Equipment e Instruments f Miscellaneous g Engine and Engine Accessories Optional Equipment h Propeller and Propeller Accessories Optional Equipment i Landing Gear and Brakes Optional Equipment U Electrical Equipment Optional Equipment k Instruments Optional Equipment 1 Autopilots Optional Equipment m Radio Equipment Optional Equipment n Miscellaneous Optional...

Page 121: ...oper loaded airplane however will perform as intended Before the airplane is delivered it is weighed and a basic empty weight and C G location is computed basic empty weight consists of the standard empty weight of the airplane plus the optional equipment Using the basic empty weight and CG location lhe pilot can easily determine the weight and C G position for the loaded airplane by computing the...

Page 122: ...SECTION 6 WE1GHT AND BALANCE PORT VE I 140 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA a THJS PAGE INTENTIONALLY LEFT BLANK IS I ED F PTE 8FR 12 RO ...

Page 123: ... items such as rags and tools from the airplane before weighing 3 Defuel airplane Then open aU fuel drains until an remaining fuel is drained Operate each engine until all undrainable fuel is used and engine stops Then add the unusable fuel 5 0 gallons total 2 5 gallons each wing 4 Fill with oil to full capacity 5 P1ace pilot and copilot seats in fourth 4th notch aft of forward position Pm flaps i...

Page 124: ... Wheel U Basic Empty Weight as Weighed T Scale Reading o EIGHING FORM Figure 6 l Ner Tare Weight d Basic Empty Weight Center of Gra vi ty 11 The following geometry applies to the PA 34 200T airplane when it is level Refer to Leveling paragraph 6 3 b __ _ C G ARM 1 t A_SY _ N B R L Leve Points Fuselage Left Side Below Window Tue datum ts 78 4 inches ahead of the wing leading edge at the inboard edg...

Page 125: ...WEIGHT AND BALANCE The basic empty weight center of gravity as weighed including optional equ1pmenc full oil and unusable fuel can be deiermined by the following formula C G Ann N A R L B T Where T N R L J SSLTED SEPTl MBt R 12 1980 inches REPORT YB l 140 6 5 ...

Page 126: ...a oe serial number and stration number shown The basic empty weight of the airplane as delivered from the factory has been entered m the We1ght d Balance Record Figure 6 7 This form is provided 10 present the current status of the airplane basic PtJ weight and a complete history of previous modifications Any change to the permanently installed uipment or modification which affects weight or moment...

Page 127: ...ichcs Schwerpunktlage Ausriistungsliste Stand vom 14 0 2 7 8 siehe Flughandbuch Wagung Auflage Bruno Gewicht Dim links Gll rechtS Glr vorn hiaten G 2 Abziig Ausfliegbarer Kraftstoff Spezifisches Gewkhr Rumpfbehfilter I Rumpfbehalter 2 Fliigelbehfilter l Fliigelbehfilter 2 F Ugelbehfilter 3 Fl ugelbehfilter 4 Dim siehe Flugz eughandbuch Im l xr 1d11 mJ nlhalrcn Khn11cr 1 1t1 Hydraulik und Entdsungs...

Page 128: ... I 0 571 4 538 J uggcwichtsschwerpunktlagen mogliche vordere und himere Lage X und X Beladuno LeerqeT richt Leercewicht o r jrhrc 1rimm1ino l inlv i inn Hochs1zulassige Zuladung Lufuiichtigkeits Gruppe Hochstgewicht Leergewicht h0chsczul Zuladung kg Dim 1477 0 2 197 Normalflu uo 207 Nutzflugi eug 1477 0 596 0 I I Sei te 2 Keruu D GCVP foment mkq 3245 780 zusatzlicbe Angaben fur Flughandbuch und Hi...

Page 129: ...RU I WAZENIA SAMOLOT PA 34 200T Znaki rejestr acyjne SP FPP Nr fabryczny 34 7870066 Data kontroli ci zaru samol otu 10 05 2000 r Civzar pustego sam olotu Paliwo9 olej Ci zar wlasny samolot u v V Ci zar Rami M oment KG Lbs cm Inch In Lbs 146 1 218 2 318790 2 3232 85 9 277628 8 nie zuzywalne stan Xontroler AlR SERVICE CERTYFIMT tKCSP ...

Page 130: ... numtx Uns Fuel JO O 103 0 3 090 0 Basic Empty Weight J 142 8 88 7 278 7 16 8 The standard empty weight includes full oil capacity and 5 0 gallons of wrnsable fuel AIRPLANE USEFUL LOAD NORMAL CATEGORY OPERATION Gross Weight Basic Empty Weight Useful Load 4407 lbs J 143 lbs 1999 kg 1425 kg 1264 lbs 5 74 kg THIS BASIC EMPTY WEIGHT C G AJ D USEFUL LOAD ARE FOR THE AlRPLAl l E AS DELIVERED FROM THE FA...

Page 131: ...SECTION 6 WEIGHT AND BALANCE REPORT B 1140 PIPER AlRCRAFT CORPORATION PA 34 200T SENECA ll THIS PAGE INTENTIONALLY LEFT BLA ...

Page 132: ... I z j m 0 c Serial Number 3t 7B7oo66 Registration Number D G RA Pag c Number Weight Change Running Basic Description of Article or Modification Added Removed Empty Weight Wt Arm Moment Wt Arm Moment Wt Moment Lb In 100 Lb On I 00 Lb I 00 As Delivered J t lLJ 2787 i 31 7 2 8 11 31 O O tT1 i i N r n j j o 0 or n tTl g zO z l l1 ...

Page 133: ... No D t lC J11 Ou I ___ I 1 Scri 11 1 ct mbe1 Rl g is tra lion Nu1111Jer Pag1 Nu111 bcr Weight Change Running Basic Description of Article or Moc 1irication Added Removed Empty Weight Wt Arm Momeni Wt Arm Momcnl Wt Moment Lh In 100 b In I 00 Lb l 00 As Delivcrcu Ill g o Z 0 tJ I ti c tT1 ti j t N gg c l l 10 Z l ...

Page 134: ... Lbs Inches In Lbs Basic Empty Weight Pilot and Front Passenger 340 0 85 5 29070 Passengers Center Seats Forward Facing J18 1 Passengers Center Seats Aft Facing Optional 119 l Passengers Rear Seats l 57 6 Passenger Jump Seat Optional 118 l Baggage Forward 22 5 Baggage Aft 178 7 Zero Fue1 Weight 4000 Lbs Max Std See pages trt and 6 6 f f 1 0 Fuel 93 Gallons Maximum Standard 93 6 123 Gallons Maxi mu...

Page 135: ...irplane Weight Lbs PlPER AIRCRAFf CORPORATION PA 34 200T SENECA a Arm Aft Damm Moment Inches In Lbs 85 5 118 1 119 1 I57 6 118 l 22 5 178 7 93 6 fotals must be within approved weight and C G limits It is the responsibility of the airplane owner and the ilot to insure chat the airplane is loaded properly The Basic Empty Weight C G is noted on the Weight tnd Balance Data Forrn Figure 6 5 If the airp...

Page 136: ... 0 350 0 300 250 200 150 100 50 0 LOADING GRAPH l I I I I L v v L v 1 v v P 1 f l t h o l l ll I l i 1 4 L V l l l l f l t 1 _ v l 1 1 1 l ff f 1 r t t T t t t f _ l 1 4 T t t I L 5 10 15 20 Z5 30 35 40 45 50 55 60 65 70 MOMENT 1000 IPOUN D tNCHES LOADING GRAPH Figure 6 1 3 lSSl D SEPTEMBER 12 J980 REPORT B J 140 6 15 ...

Page 137: ... Max TQ Wt 89 4 92 94 4400 l r 1 4342 Max 82 3400 r f f i i 3200 c er 1J 3 3000 E u 2600 2400 92 94 86 88 90 92 94 C G Location Inches Ah Datum Weight v C G Envelope Moment hange due w re1racrmg Landmg Gear 32 m lbs EPORT VB 1140 C G RA J GE AND WEIGHT Figure 6 1 5 I Sl F D S PTEMBF R 12 l HHI ...

Page 138: ...which will be located in this second position When all the loads have been drawn in this manner the final end of the segmented line locates the total load and the C G position of the airplane for takeoff 1f this point is not within the allowable envelope it will be necessary to remove fuel baggage or passengers and or to rearrange baggage and passengers to get the final point to fall within the en...

Page 139: ...rom the ilJustration the final dot shows the total weight co be 4i15 pounds with the C G at 90 J This is wen withjn the enve ope C 8 There will be room for more fuel As fuel is bu med off the weight and C G will follow down the fuel line and stay within che envelope or landing EPORT VB 1140 SA U LE PROBLE f 4407 lbt 41999 Kg I Mu T Q W 4400 4342 89 4 92 mo i __ 4 __ _ _ __ 1 3000 E T r f l r r t 7...

Page 140: ... 200T SENECA 11 SERIAL NO Jit 7870066 REGISTRATION NO __u _ _ G _ _ A_ ll_ A__ DATE 1 L o 1978 a Propeller and Propeller Accessories ltem No Item Two Propellers Cert Basis TC P920 Hartzell Model BHC C2YF 2CKF FC8459 8R or FC8459B 8R Left Wing Hartzell Model BHC C2YF 2CLKF FJC8459 8R or FJC8459B 8R Right Wing OR Hartzell Model BHC C2YF 2CKUF FC8459 8R or FC8459B 8R Left Wing Hartzell Model BHC C2YF...

Page 141: ...5ECTION 6 l rEIGHT AND BALANCE lEPOR T VB 1140 1 0 u PIPER AIRCRAFT CORPORATlON PA 34 2 00T_SENECA Il THIS PAGE INTENTIONALLY LEFT BLANK ISSUED SEPTEMBER 12 1980 ...

Page 142: ... E9CE Teledyne Continental Model TSI0 360 E or TSI0 360 EB Fuel Injected Turbocharged Left Wing Teledyne Continental Model LTSI0 360 E or l TSI0 360 EB Fuel Injected Turbocharged Right Wing ISSVED SEPTEMBER 12 1980 I Mark if Inst Weight Pounds SECTION 6 WEIGHT AND BALANCE Ann n Aft Datum Moment Lb Jn REPORT 8 1140 6 21 ...

Page 143: ...SECTION 6 WEIGHT AND BALANCE REPORT VB 1140 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA 0 THIS PAGE INTENTIONALLY LEFT BLANK ISSUED SEPTEMBER 12 1980 ...

Page 144: ...Tires with Regular Tubes Cert Basis TSO C62 13 l ose Wheel Assembly a Cleveland Aircraft Products Wheel Assy No 40 76F Cert Basis TSO C26a b McCauJey Industrial Corp Wheel Assy No D 30625 Cert Basis TSO C26b c 6 00 6 Type III 6 Ply Rating Tire with Regular Tubes Cert Basis TSO C62 ISSUED SEPTEMBER 12 1980 Mark if Weight nsU Pounds 4 3 5 5 SECTION 6 WEIGHT AND BALANCE Arm ln Moment Aft Datum Lb In ...

Page 145: ...SECTION 6 WEIGHT AND BALANCE ltEPORT VB 1140 PIPER AIRCRAFf CORPORATION PA 34 200T SENECA II THIS PAGE INTENTIONALLY LEFT BLA J l JS l E D SEPTEMBER 12 J 980 ...

Page 146: ...tion Light Wing 2 Grimes A1285 G 12 Al 285 R 12 Cert Basis TSO C30b 21 Stall Warning Devices Piper Dwg 37063 0 Safe Flight P N 186 501 23 Stall Warning Hom Piper Owg 37063 0 Safe Flight P IN 35214 iSSUED SEPTEMBER 12 1980 Mark if Weight lnstJ Pounds 0 4 0 2 SECTION 6 WEIGHT AND BALANCE Ann ln Moment Aft Datum Lb In 80 2 32 60 9 12 REPORT VB 1140 6 25 ...

Page 147: ...SECTION6 WEIGHT AND BALANCE REPORT VB 1140 6 16 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II THIS PAGE INTENTIONALLY LEFT BLANK ISSll ED SEPTEMBER 12 1980 ...

Page 148: ...ed Indicator Piper PS50049 40S Cert Basis TSO C2b 29 Compass Piper Dwg 67462 Cert Basis TSO C7c 3 I Manifold Pressure Dual Piper 37554 Cert Basis TSO C4 S 33 FueJ Flow Gauge Dual Piper 37341 Cert Basis TSO C47 ISSUED SEPTEMBER 12 1980 Mark if Instl Weight Pounds SECTION 6 WEIGHT AND BALANCE Ann ln Aft Datum Moment lb ln REPORT VB J140 6 27 ...

Page 149: ...iEC110N 6 iVEIGHT AND BALANCE REPORT VB 1140 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA Il THIS PAGE INTENTJONALLY LEFT BLANK ISSUED SEPTEMBER 12 1980 ...

Page 150: ...iper PS50039 4 3 Cert Basis TSO C22f 45 Aft Seat Belts 2 Piper PS50039 4 4 Cert Basis TSO C22f 47 Shoulder Harness Fixed Front 2 Piper PS 50039 4 24 49 4407 lbs Max Gross Weight Kit Piper Dwg 78858 Cert Basis TC A750 JSSUED SEPT EMBER 12 1980 Mark if Weight lnstl Pounds I I SECTION 6 WEIGHT AND BALANCE Arm In Moment Aft Datum Lb ln 120 I 132 REPORT VB l140 6 29 ...

Page 151: ...SECTION 6 WEIGHT A ND BALANCE REPORT VB 1140 t PIPER AIRCRAFT CORPORATION PA 34 200T SENF A D THIS PAGE 1NTENT10NALLY LEFT BLANK lSSl ED SEPTEMBER 12 1980 ...

Page 152: ...gine Accessories Optional Equipmenl Ltern No Item 51 Optional Engine Primer System Piper Dwg 37865 2 Cert Basis TC A 7SO LSSUED SEPTEMBER 12 1980 Mark if Weight Instl Pounds 3 1 SECTION 6 WEIGHT AND BALANCE Arm In Moment Aft Datum Lb ln 38 5 119 REPORT VB 1140 6 31 ...

Page 153: ...SECTION 6 WEIGHT AND BALANCE REPORT VB 1140 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA Il THIS PAGE lNTENTIONALLY LEFT BLAJ 1 ISSUED SEPTEMBER l 2 l 9811 ...

Page 154: ... 80HA 4 Left Wing McCauley Model 3AF34C503 L80HA 4 Right Wing Cert Basis P 57GL 60 Synchrophasers Piper Dwg 36890 Cert Basis TCA7SO Mark if Weight InstI Pounds 37 2 5 9 Weight and moment difference between standard and optional equipment ISSt ED SEPTEMBER 12 1980 SECTION 6 WEIGHT AND BALANCE Arm ln Moment Aft Datum Lb ln 20 3 755 61 3 362 REPORT VB I 140 6 33 ...

Page 155: ... ECTION 6 l EIGHT AND BALANCE Jlf PORT VB 1140 4 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA ll THIS PAGE INTENTIONALLY LEFT BLA NX ISSUED SEPTEMBER 12 1980 ...

Page 156: ...SO C26a Goodrich 6 00 x 6 Ribbed Type lII 8 Ply Rating Tire with Tube 2 Cert Basis TSO C62 b Goodrich 6 00 x 6 Ribbed Type ill 8 Ply Rating Tire with Tube Cert Basis TSO C62 Mark if Instl x Weight Pounds 2 9 SECTION 6 WEIGHT AND BALANCE Arm ln Aft Datum 109 8 Moment lb In 318 Same as standard equipment Weight and moment difference between standard and optionaJ equipment ISSlJEO SEPTE MBER 12 19gu ...

Page 157: ...SECTION 6 WEIGHT AND BALANCE REPORT B 1140 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA D THIS PAGE INTENTIONALLY LEFT BLANK lSSl ED SEPT 1BER 12 19R41 ...

Page 158: ...asis STC SA3023SW D 85 Auxiliary Power Receptacle Piper Dwg 68815 Cert Basis TC A7S0 87 External Power Cable Piper Dwg 62355 2 Cert Basis TC A7SO 89 Lighter 200462 12 Volt Universal Cert Basis TC A 7SO Mark if Weight Inst Pounds x 0 5 x 0 5 2 9 2 6 2 6 4 6 2 Weight and moment difference between standard and optionaJ equipment ISS LrED SEPTE MBER 12 1980 SECTION 6 WEIGHT AND BALANCE Ann ln Moment A...

Page 159: ... AND BALANCE U ElectricaJ Equipment Opcional Equipment cont Item No iEPORT B IUO Item Mark tf 1nstl PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II Weight Pounds Ann tln Aft Datum Moment Lb ln I L1ED SEPTEMBER 12 198 1 ...

Page 160: ...O C2b 123 Encoding Al ti meter Piper PS50008 6 or 7 Cert Basis TSO CJ Ob C88 124 Altitude Digitizer United Instruments P IN 5125 P3 Cert Basis TSO C88 125 Vertical Speed a Piper Dwg 99010 2 4 or 5 b Piper Dwg 99010 3 Cert Basis TSO C b 127 Turn and Slip Indicator Piper PS50030 2 or 3 Cert Basis TSO C3b Mark if lnstl x x i Weight Pounds 2 2 4 6 4 4 2 2 2 6 5 0 SECTION 6 WEIGHT AND BAJANCE Ann ln Mo...

Page 161: ...o Allimeler 131 Engine Hour Mecer Piper Dwg 37731 0 Cert Basis TC A7SO 133 Oock Cert Basis TC A7SO 135 Air Temperature Gauge Piper Dwg 79316 Cert Basis TC A7SO REPORT YB 1140 Mark if lnstl PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II We1gbt Ann In Moment Pounds Aft Datum Lb In 5 4 l8l 3 979 4 3 188 2 09 0 3 62 9 19 4 67 4 27 2 77 6 16 ISSL ED SEPTEMBER 12 1980 ...

Page 162: ...S50049 40T Cert Basis TSO C2b 143 Vertical Speed a Piper Dwg 99010 2 4 or 5 b Piper Dwg 99010 3 Cert Basis TSO C8b 145 Altimeter Piper PS50008 4 or 5 Cert Basis TSO Cl Ob 147 Tum and Slip Indicator Piper PS50030 2 or 3 Cert Basis TSO C3b 149 Oock Cert Basis TC A7SO lSSUED SEPTEMBER 12 19 80 Mark if Weight Instl Pounds 2 2 2 6 D 6 1 0 5 LO 2 6 0 4 SECTION 6 WEIGHT AND BALANCE Ann In Moment Aft Datu...

Page 163: ...SECTION 6 WEIGHT AND BALANCE REPORT VB 1140 6 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA Il THIS PAGE INTENTIONALLY LEFT BLANK ISS l ED SEPTEMBER 12 1Q80 ...

Page 164: ...and 3 Gyros Cert Basis STC SAi 147CE 167 King KFC 200 flight Control System KG 258 Attitude Horizon Indicator and 3 Gyros Cert Bas is STC SA1147CE 167a S Tec System 65 Flight Control and ST 361 Single CUe Flight Director System Cert Basis STC SA 7157 SW D ISSUED SEPTEMBER 12 1980 Marl if Jnstl x x Weight Pounds 6 7 3 2 0 9 20 l 3 2 0 9 0 9 49 4 49 4 30 6 SECTION 6 WBGHT AND BALANCE Ann ln Moment A...

Page 165: ...SECTION 6 WEIGHT AND BALANCE REPORT VB U40 6 PlPER AIRCRAFT CORPORATJON PA 34 200T SENF A II THIS PAGE INTENTIO ALLY LEFT BLANK ISSll ED SEPTEMBER 12 1980 ...

Page 166: ...O C74c 171 Bendix ADF 2070 Cert Basis TSO C41c C2a 171 Bend ix DME 2030 Cert Basi TSO C66a IH Bendix NCP 2040 Na Programmer 174 Bendix lu 2016A Interface Cert Basis TS DOT 160 C2a 175 Bendix Blower 14VDC Weight includes antenna and cable ISSl E D SEPTEMBER 12 1980 M ark 1 f Veight lost f Pound 16 8 19 J X 2 S 6 0 1 3 5 4 4 9 l l ECTION 6 WEIGHT ANO BALA CE Arm ln Moment t ft Datum Lb In 66 8 ll 22...

Page 167: ...SH TlON 6 WEIGHT ANO BALANCE PIPER AIRCRAFT CORPORATIO J PA J4 200T SENECA II REPORT 8 1140 6 THIS PAGE INTENTIONALLY LEFT BLAJ K ISSL ED SEPTEMBER 12 1980 ...

Page 168: ... J5t VOR LOC GS Indicator Cen Basis TSO C40a C36c Collins GLS 350 Glide Slope Receiver Cert Basis TSO C34c Collins ANS 351 R NAV Cen Ba sis TSO C36c Collins DCE 400 Distance Computing Equipment Cert Basis TSO C40a Collins OM E 45 1 with Ind 450 1 451 Cert Basis TSO C66a Weight includes antenna and cable ISSUED SE PT MBER 12 198 0 Mark if lnstl Weight Pounds 4 0 8 1 3 9 7 9 1 0 2 0 1 3 3 6 3 8 2 1 ...

Page 169: ...er Panel Cert Basis TSO C35d C50b Collins TDR 950 Transponder Cert Basis TSO C74c King KX 170 VHF Comm Nav Transceiver Sing e Transceiver DuaJ Cert Basis TC A SO King KN 53 NAV l REC with GS Receiver King KN 53 NAV I Rec Weight mcludes antenna and cable REPORT VB 1140 6 4 Mark if lnstL Pl PER AIRCRAFT CORPORATION PA 34 200T SENECA Il Weight Pounds 7_0 7 7 3 3 2 8 7 5 15 0 3 2 8 Arm In Aft Datum 12...

Page 170: ...er d KingKI 203 VOR LOC Indicator e King KNJ 520 VOR ILS Indicator Cert Basis TSO C36c C37b C38b C40a 193 Kmg KY 197 Transceiver Cert Basis TSO C37B CJ8B 194 King Kl 201 VOR LOC lndicator Cert Basis TC A7SO 195 King Kl 208 VOR LOC Indicator Cert Basis TSO C34c C36c C40a 196 King Kl 209 VOR LOC GS Indicator Cert Basis TSO C34c C36c C40a ISSUED SEPTEMBER 12 I980 Mark if Weight InstI Pounds 7 5 1 3 2...

Page 171: ...6 King KR 85 D igit al ADF wilh KA 42B Loop and Sense Amenna a Audio Amplifier Cert Basis TSO C4 lb n7 King KR 5 Digital ADF a Audio Amplifier Cert Basis TSO C41 b 208 King KR ti ADF v ith KA 42B Loop and Sense Antenna a Single b Dual c Audio mplifier Cert Basis TC A7SO Weight includes ant nna and cabk REPORT VB 1140 6 ft Mark if Jnstl PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II Weight Ann ln ...

Page 172: ...King KT 76 78 Transponder Cert Basis TSO C746 215 Narco Comm l IA VHF Transceiver a Single b Dual Cert Basis TC A 7SO 217 Narco Comm l lB VHF Transceiver a Single b DuaJ Cert Basis TC A7SO Weu ht mcludes ancenna and cable Weight includes dual antenna and cable ISS Li ED SEPTEMBER 12 1980 Mark if Weight lnstl Pounds 6 7 16 4 0 8 7 7 0 13 9 0 8 1 5 3 7 1 7 3 1 3 6 7 1 3 9 7 7 SECTION 6 WEIGHT AND BA...

Page 173: ...a 14 VHF Receiver Cert Basis TL A7SO 23 1 Narco Na 1l I Cert Basis TSO C36c C40a C66a 233 Narco Na 112 Receiver Cert Basis TSO C36c C40a C66c C34 235 Narco Na l 14 VHF Receiver Cert Basis TSO C38b C40a C36c C34c C66a 237 Narco Nav l 21 VHF Receiver a Single b Dual Cert Basis TSO C36c C40c C66a REPORT VB 1140 6 2 Mark if lnstl PIPER AIRCRAFT CORPORATION PA 34 200T SENECA Il We1ght Ann In Moment Pou...

Page 174: ...arco ID 124 VOR LOC GS Indicator a Single b Dual Cert Basis TSO C34c C35d C36c C40c 249 Narco OC 1 I0 Converter and fount Cert Basis TSO C36c C40a 251 Narco UGR 2A Glide Slope a First b Second c Second Cert Basis TSO C34b 253 Narco UGR 3 Glide Slope Cert Basis TC A7SO Weight includes marker antenna and cable ISSUE D SEPTEMBER J2 1980 Mark if lnstl Weight Pounds 5 3 8 8 5 4 9 0 6 4 t 1 1 4 4 1 2 2 ...

Page 175: ...7SO 267 Narco DME J 90 TSO Cert Basis TSO C66a 269 Narco DME 195 Receiver and Indicator Cert Basis TSO C66a Narco ADF 140 a Single b Dual Cert Basis TSO C4lc 273 Narco ADF 141 a Single b DuaJ Cert Basis TSO C4 lc weight includes dual antenna and cable weight includes antenna and cable REPORT VB 1140 6 4 Mark if Instl PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II Weight Arm In Moment Pounds Aft D...

Page 176: ...VHF Comm c Single ADF Sense Cert Basis TC A7SO 293 Emergency Locator Transrnmer C C C Model Cl R 11 2 a ntenna and Coa x b Shelf and Access Hole Cen Basis TSO C91 294 Emergency Locator Tram muter i rco Model ElT 10 a ntenna and Coax b Shelf and Acee Hole Cen Ba is TSO C91 we1gJH includes antenna and t able JSSl ED SEPTEMBER 12 t980 Mark if Weight InstI Pounds 0 3 0 l O 0 3 0 l O 1 6 0 8 0 9 0 9 2 ...

Page 177: ...peaker Piper Dwg 99820 Cert Basis TC A750 301 Headset Piper Dwg 68856 10 Cert Basis TC A 7SO 303 Bendix Radar Piper Dwg 37916 2 Cert Basis TSO C63b 04 Bendt Radar Piper Lh g 379 I6 4 Cert Ba ois TSO C63b 305 Radio Shelf Piper Dwg 69977 2 Cert Basis TC A7SO REPORT VB l14Q J Mark if InstI PIPER AIRCRAFT CORPORATION PA 34 200T SENECA Il Weight Arm ln Moment Poumis Aft Datum Lb In l 0 3 70 8 11 0 6 69...

Page 178: ...9 RCA Weather Scout 11 Color Radar Piper Dwg 37916 7 Cert Basis TSO C63b I i ASS t IR JCl t1 J i x t 5 lJ RVIC Ol1 J I L a _i Q G S _f u su v u ISS L ED S PTEMB ER U 1980 Mark d Im 11 x X l etghr Pound 15 7 25 0 5 S s s 2 I C 3 SECTION 6 WEIGHT AND BALANCE Arm rln I Moment Aft Dac um Lb In 9 2 144 24 3 607 G4 55 c i 2 3 53 6 I I I Hi 3c 1 13 4 I ae Jtti lplic LSA i ase REPORT B 1140 6 57 ...

Page 179: ...SECTIO 6 WEIGIIT AND BALANCE REPORT VB 1 1 IU PlPER AIRCRAFT CORPORATION PA 34 200T SENECA 0 TJUS PAGE lNTENTIONALLY LEFT BLANK lSSl ED SEPTEMBER J 1980 ...

Page 180: ... Heated Pitot Head and Lift Detectors c Ice Light Kit Piper Dwg 37700 3 d Electrothennal Hartzell Propeller Deicing System Piper Dwg 37700 3 e Electrothermal McCauley Propeller Deicing System Piper Dwg 37700 8 L Pneumatic Deicing System Including Vacuum Pumps Piper Dwg 37700 2 I SLED SEPTEMBER 12 1980 Mark if Weight InstI Pounds 6 0 x 2 6 x 0 4 x 0 4 x 11 6 10 2 x 34 3 SECTION 6 WEIGHT AND BALANCE...

Page 181: ... Seat with seat belts Piper Dwg 78108 9 Cert Basis TC A7SO 369 Club Seating a Wnh Regular Headrest on Center Seat b With O ersize Headrests on Center Seats Piper Dv g 37825 3 Cert Ba 1 s TC A750 J7l Inboard Armrest All Sear Cert Bam TC A7 0 313 Headrest 2l Front Piper D g 79337 1 Cen Basis TC A7SO Mark if Inscl x x x x PIPER AIRCRAFT CORPORATlON PA 34 200T SENECA Il Weight Arm In Momem Pounds Aft ...

Page 182: ...bs each Piper PS50039 4 15 Cert Basis TC A7SO 391 Inert1a Safety Belts Rear 2 0 8 lbs each Piper PS50039 4 14 Cert Basis TC A7SO 392 Shoulder Harness Inertia Front 2 Piper PS50039 4 21 393 Shoulder Harness Fixed Cente 2 Plper PSS0039 4 22 394 Shoulder Harness Inerna Center 2 PipeT PS500J9 4 t9 395 Should t r Harnes Fixed Rean Piper PSS00 39 4 22 ISSUED SEPTEMBER 12 J980 Marie if Weight lnstl Pound...

Page 183: ... 36800 2 Cert Basis TC A7 0 402 Deluxe Carpeting Cert Basis TC A7SO 13 Luxurious Interior Piper Dwg 67954 2 Cert Basis TC A7SO 405 Fire Extinguisher a Piper Dwg 7862 1 2 Scott 42211 00 b Piper Dwg 3568 2 Graviner HA1014 01 Cert Basis TC A750 Mark if Instl PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II Weight Ann nn Moment Pounds Aft Datum Lb ln I 1 1815 16 120 0 36 J 1 9 143 6 273 5 2 143 6 747 7...

Page 184: ...410 Fixed Oxygen System Scott Aviation Ambassador MK HI Sys1em Piper D S 36960 3 a Charged b Uncharged Cert Basis TC A7SO TOTAL OPTIONAL EQUIPMENT EXTERIOR FlNfSH Juneau White Base Color____________ Trim Color___ B _a_J_ _ a _Y _ e _l_ l _ o _ w____ Ocala Orange Accent Color Hi ckorv Brown 1 St ED SEPTEMBER n 1980 Mark if Weigh1 lnstL Pounds x 4 4 41 0 x 41 6 45 5 40 2 SECTION 6 WEIGHT AND BALANCE...

Page 185: ...SECTION 6 WEIGHT AND BALANCE RE PORT VB 1UO PIPER 4 IRCRAFT CORPORATlON PA 34 200T SENECA II THlS PAGE INTENTIONALLY LEFT BLANK ISS l ED SEPTf 1BER 12 1980 ...

Page 186: ...34C503 L80HA 4 Right Wing Cert Basis P57GL Synchrophasers Piper Owg 36890 Cert Basis TC A SO Heavy Duty Group 1 o I a Cleveland Aircraft Products 40 120 Wheel Assy 2 30 83 Brake Assy 2 Cert Basis TSO C26a Goodrich 6 00 x 6 Ribbed Type Ill 8 Ply Rating Tire With Tube 2 Cert Basis TSO C62 Sc robe Ligh1s Wing Tip Whelen Piper Dwg 95267 Cer1 Basis TC A750 Vacuum System lnstallation a Two Vacuum Pumps ...

Page 187: ...rmal McCauley Propeller Deicing System Piper Dwg 37700 Cen Basis TC A 7SO 4 2 Pneumatic Deicing System Including Vacuum Pumps Piper Dwg 37700 Cert Basis TC A 7SO 22 4 Fuel Cells Piper Dwg 37077 3 Cert Basis TSO C80 7 9 Air Conditioning lnstallation Piper Dwg 36809 Cen Basis TC A 750 19 3 Total of Installed Item lbs Therefore the new maximum zero fuel wt of the airplane is Standard Max Zero Fuel Wt...

Page 188: ... Electrical System 7 J5 7 J9 Gyro Pressure System 7 J9 7 21 Pitot Sratic System _ 7 21 7 23 lns1rnment Panel 7 25 7 25 Heating Ventilating and Defrosting System 7 27 7 27 Cabin Feature 7 30 7 29 Stall Warning 7 31 7 3 l Baggage Area 7 31 7 33 Finish 7 31 7 35 Emergency Locator Transmitter 7 32 7 37 Piper External Power 7 35 7 39 lee Protectjon System 7 35 7 4 1 Radar 7 39 7 43 Air Conditioning 7 4...

Page 189: ...ly 40 of the chord aft of the leading edge Tile wmgs are attached to the fuselage by the insertion of the butt ends of the spar into a spar box carry through which is an integral part of the fuselage structure The bolting of the spar ends into the spar box carry through stru ture which is located under the center seats provides in effect a continuous main spar The vmgs are also attached fore and a...

Page 190: ...n aiI either to pass into the compressor through Ihe filter or to bypass the filter and supply heated air directly to the turbocharger There is a suck in door which opens in ilie evenc thaI the primary air source becomes blocked Alternate air selection insures induction air flow should the filter become blocked Since the air is heated the alternate air system offers protection against induction sy...

Page 191: ...rol levers When an allemate air lever is in the up or off position the engine is operating on filtered air when the lever is in the down or on position the engine is operating on unfiltered heated air Should the pnmary air source become blocked the suck in door will automatically seiecl unfiltered heated air The cowl nap control levers Figure 7 1 located below the control quadran t are used to reg...

Page 192: ...the propellers shafts to maintain constant RPM settings A governor controls engine speed by varying the pitch of the propeHer to match load torque to engine torque in response to changing flight conditions Perfonnance data listed in Section Five of this handbook is applicable for both two and three b1ade propeUer installations Each propeller is controlled by the propeller control levers located in...

Page 193: ...laced on MAN UAL for JO to 40 seconds then the propellers can be synchronized agarn and the synchrophaser switch returned to AUTO SYNC b Propeller Synchrophaser with adjustable phase angle When this synchrophaser is installed a rotary switch 1s located on the throttle quadrant below the propeller controls It is labeled OFF for manual control or standby and PHASE ADJUSTMENT for propeller synchroniz...

Page 194: ...ition When hydraulic pressure is exerted in one direction the gear is retracted when it is exerted in the other direction t _sear is extended Gear ex tension or retraction normally takes six to seven seconds CAGTION If the landing gear is in transit and the 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 t...

Page 195: ...switch illuminate to indicate that each of the three landing gears is down and locked A convex mirror on the left engine nacelle both serves as a taxiing aid and allows the pilot to visually confirm the cond1tion of the nose gear If the gear is in neither the full up nor the full down position a red warning light on ihe instrument panel illuminates Should the throttle be placed in a low setting as...

Page 196: ...NTROL S WAR G 5A PIPER AIRCRAFT CORPORATlON PA 34 200T SENECA Il TERMINAL TERllllNAL Z LEFT l OSE GEAR AR DOWN UP DOWN Llt lT L Mii LIMIT Nu SW 10 Nc SW 1 NO TERM Nt 4 Ii TERMINALq i __ G R Sc t CT SWITCH UP U l T NOSE REEr i GHT TER P r AL i RIGHT GEAR RIGHT GREE LIGHT 75 OHt f THROTTLE R D GE F IGfjT ON V L IGHTS LA L DING GEAR ELECTRlCAL SYSTEM SCHEMATIC Figure 7 5 REPORT VB 1140 7_0 J l 0 SEPT...

Page 197: ...O E IOTE 11 _ow PP SSUFIE CCI TROL 40SE GE AR HYOF t LJLIC CYU llOER UP DOW N 0 SECTION 7 DESCRIPTION AND OPERATION E MAI GEAR HVQRALJL C c u11 0EP RESTRtCTOR UP DOWN r 1 r ORESSURE SWITCH RESERVOIR OWN JP FREE FA_L CONTROL t ttGf _ P ESSUR E CONTROL T oERMAl RE LIE VALV SE NOTE 2 GEAR UP CnECK VALVE LA NDING GEAR HYDRAUUC SYSTEM SCHL 1ATIC Figure 7 7 ISSl ED SEPTEMBER 12 1980 REPORT YB 1140 7 9 ...

Page 198: ...BRAKE SYSTEM The brake system is designed to meet all normal braking needs Two single disc double puck brake assemblies one on each main gear are actuated either by toe brake pedals mounted on both the pilofs and the copilot s rudder pedals or by a hand operated brake lever located below and behind lhe left center of the instrument panel A brake system hydraulic reservoir independent of the landin...

Page 199: ...tanks or J23 usable gallons with the optional fuel tanks installed The minimum fuel grade is lOO or IOOLL aviation grade The fuel tant vents one installed under each wing feature an ant1 1cmg design ro prevent ice formation from block ng the fuel tank vent lines The fuel injection system is a continuous flow type which utilizes a vapor return line leading back to the fuel tanks This line provides ...

Page 200: ...CCI J1 N 00 fil J I c r n Cfl r n Ii I GAGE ANO NOZZLES vENHl I TO orCK PRF SSlll E OPTIONAL 111 llDOE I FllEL CELL TO t1C AT A FUEi SELECTOR CONTROLS AUXll lllRY IOR l ECTRIC UEL PUMP ll NT e I rr1 a z _ 0 z 5 0 0 E a z ril x i j f l o o z J o ...

Page 201: ...ngine the interconnecting fuel lines and fine wire spark plugs Actuation of the engine primer switch operates the auxiliary electric fuel pump on Hi and energizes the diverter valve which supplies fuel to each primer nozzle The diverter valve does not shut off fuel flow to the manifold valve therefore some quantity of fuel is also supplied to each cylinder nozzle during priming Normal operation of...

Page 202: ...I I I _J TO RADIO BUS BAR REPORT VB 850 7 14 ALTERNATOR FIELD OVERVOLTAGE RELAY L H VOLTAGE RIGHT ALT OVERVOLTAGE RELAY REG RADIO MASTER OFF r NORM _j_ 9 AUX LEFT STARTER STARTER SOLENOID RELAYS R H VOLTAGE REGULATOR TO ANNUNICATOR PANEL RIGHT STARTER ALTERNATOR AND STARTER SCHEMATIC Figure 7 13 I CIGAR LIGHTER STARTER SW ISSUED AUGUST 23 1976 ...

Page 203: ...ammeter indicate a load much higher than the known consumption of the electrical equipment in use it should be suspected of a malfunction and turned off In this event the remaining alternator s ammeter should show a normal indication after approximately one minute If both ammeters indicate a load much higher than the known consumption for more than approximately five minutes an electrical defect o...

Page 204: ...SECTION7 DESCRIPTION AND OPERATION PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II REPORT VB 850 7 16 SWITCH PANEL WITH PRIMER SYSTEM Figure7 15 ISSUED AUGUST 23 1976 REVISED NOVEMBER 30 1987 ...

Page 205: ...pressing it in preferably after a few minutes cooling period The circuit breakers can be pulled out manually Most of the electrical switches including the master switch and switches for magnetos fuel pumps starters alternators lights and pitot heat are conveniently located on the switch panel Figure 7 15 to the left of the pilot WARNING Strobe lights should not be operating when flying through ove...

Page 206: ...I l SECTION7 DESCRIPTION AND OPERATION REPORT VB 850 7 18 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II GYRO PRESSURE SYSTEM Figure 7 17 ISSUED AUGUST 23 1976 ...

Page 207: ...e operation or in the event of malfunction of one of the pressure pumps The instruments receive air from the manifold A pressure gauge on the instrument panel to the left of the copilot s control wheel shaft is connected to the manifold and indicates the pressure the gyros are receiving After air has passed through the gyro instruments it is exhausted overboard through the forward bulkhead The ope...

Page 208: ... f 1 U J 1 w Cl I wo c z Cl a n a w n l n 1 W nt ffi_ o CO CZQ 1 ewwz_w oo ozwuwI Ic o _ a 0 1 1 1 1 ii Ul h oooooot t o wc t t 0 0 0 0 FJ FJ REPORT VB 850 7 20 PITOT STATIC SYSTEM Figure 7 19 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II I l I I _ I I I I I I I I I I I I I ISSUED AUGUST 23 1976 ...

Page 209: ...truments may give slightly different reading depending on conditions within the cabin Airspeed setting of heating and ventilating controls or the position of the storm window can influence cabin air pressure The pilot can determine the effects of the alternate static source on instrument readings by switching from standard to alternate sources at different airspeeds and heating and ventilating con...

Page 210: ...1 R NAV 22 ADF RECEIVER 23 NAVIGATION RECEIVER 24 DME 25 TURN AND BANK INDICATOR COPILOT S 26 AIRSPEED INDICATOR COPILOT S 27 DIRECTIONAL GYRO COPILOT S 28 ATTITUDE GYRO COPILOT S 29 VERTICAL SPEED INDICATOR COPILOT S 30 ALTIMETER COPILOT S 31 CIGAR LIGHTER 32 CLOCK COPILOT S 33 MIKE AND PHONE JACKS 34 ALTIMATIC Ill C AUTOPILOT 35 LEFT ENGINE AND FUEL INSTRUMENT CLUSTER 36 OMNI COUPLER 37 PITCH TR...

Page 211: ...R 25 DME 26 TURN ANO BANK INDICATOR CO PILOT S 27 AIRSPEED INDICATOR CO PILOT S 28 DIRECTIONAL GYRO CO PILOT S 29 ATTITUDE GYRO CO PILOT S 30 VERTICAL SPEED INDICATOR CO PILOT S 31 ALTl METER CO PILOT S 32 CIGAR LIGHTER 33 CLOCK CO PILOT S 34 MIKE AND PHONE JACKS 35 ALTIMATIC lllC AUTOPILOT 36 LEFT ENGINE ANO FUEL INSTR UMENT CLUSTER 37 OMNI COUPLER 38 PITCH TRIM 52 5J 54 55 56 39 LEFT ENGINE TACH...

Page 212: ...SECTION7 DESCRIPTION AND OPERATION PIPER AIRCRAFf CORPORATION PA 34 200T SENECA II REPORT VB 850 7 22b THIS PAGE INTENTIONALLY LEFf BLANK ISSUED AUGUST 30 1978 ...

Page 213: ...he button is depressed all annunciator panel lights except auxiliary fuel pump lights should illuminate NOTE When an engine is feathered the alternator gyro air and engine oil pressure annunciator lights will remain illuminated Instrument panel lighting can be dimmed or brightened by rheostat switches to the right of the control quadrant Back lights are standard equipment and map lights and readin...

Page 214: ...SECTION7 DESCRIPTION AND OPERATION PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II REPORT VB 850 7 24 THIS PAGE INTENTIONALLY LEFf BLANK ISSUED AUGUST 23 1976 ...

Page 215: ...is in the FAN position during ground operation the ventilation fan blows fresh air through the heater ductwork for cabin ventilation and windshield defogging when heat is not desired When the heater controls are used either for cabin heat or for ventilation air is automatically ducted to the windshield area for defrosting The flow of defroster air to the windshield area can be increased by the act...

Page 216: ...V I I I I v C iC q crjoici a c en w a u PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II a a a w en a c w a u LI I w c c I I I I I I i I CABIN HEATING VENTILATING AND DEFROSTING SYSTEM Figure 7 23 REPORT VB 850 7 26 ISSUED AUGUST 23 1976 ...

Page 217: ... __ PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II SECTION7 DESCRIPTION AND OPERATION HEATING VENTILATING AND DEFROSTING CONTROL CONSOLE Figure 7 25 ISSUED AUGUST 23 1976 REPORT VB 850 7 27 ...

Page 218: ...sharply on the strap The reel will lock in place under this test and prevent the strap from extending Under normal movement the strap will extend and retract as required 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 which may be added to suit indivi...

Page 219: ... lift detectors on the leading edge of the left wing outboard of the engine nacelle The inboard detector activates the indicator when the flaps are in the 25 and 40 degree positions the outboard when the flaps are in other positions 7 31 BAGGAGE AREA There are two separate baggage compartments One the nose section baggage compartment is accessible through a baggage door on the left side of the nos...

Page 220: ...ery is drained The ARM position is selected when the ELT is installed in the airplane and it should remain in that position To use the ELT as a portable unit in an emergency remove the cover and unlatch the unit from its mounting base The antenna cable is disconnected by a left quarter tum of the knurled nut and a pull A sharp tug on the two small wires will break them loose Deploy the self contai...

Page 221: ...selected before selecting ARM If ARM is selected directly from the ON position the unit will continue to transmit in the ARM position A pilot s remote switch located on the left side panel is provided to alJow the transmitter to be controJied from inside the cabin The pilot s remote switch is placarded ON AUTO ARM and OFF RESET The switch is normally left in the AUTO ARM position To tum the transm...

Page 222: ...SECTION7 DESCRIPTION AND OPERATION PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II THIS PAGE INTENTIONALLY LEFf BLANK I REPORT VB 850 7 30b ISSUED APRIL 13 1979 ...

Page 223: ...econds The boot solenoid valves are activated and air pressure is released to the boots inflating all surface deicers on the airplane A Wing Tail Deicer indicator light with a press to test feature illuminates when the surface deicer boots inflate When the cycle is complete the deicer solenoid valves permit automatic overboard exhaustion of pressurized air Suction is then reapplied to the deicer b...

Page 224: ... VB 850 7 32 o o II a ww zU C iii 0 J w z u Cl a o t J w J c w Cl 0 z PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II l_j L u 0 w c g ii 0 w I c ICE PROTECTION SYSTEM Figure 7 27 g Jc Cl a a w WU c w 00 a a 1 W o J w J JW w11 0 f 1 c C J z 0 j tJ w 0 w ISSUED AUGUST 23 1976 ...

Page 225: ... the touch The heat provided by the deicer pads reduces the adhesion between the ice and the propeller so that centrifugal force and the blast of airstream cause the ice to be thrown off the propeller blades in very small pieces A heated glass panel is installed on the exterior of the pilot s windshield to provide visibility in icing conditions The panel is heated by current from the airplane s el...

Page 226: ...NECA II ICE DETECTION LIGHT SURFACE DEICER PROPELLER DEICER AND HEATED WINDSHIELD CONTROL SWITCHES REPORT VB 850 7 34 HEATED PITOT AND HEATED STALL WARNING TRANSMITTER CONTROL SWITCHES ICE PROTECTION SYSTEM CONTROL SWITCHES Figure 7 29 ISSUED AUGUST 23 1976 REVISED JULY 9 1979 ...

Page 227: ...ce course In addition to its primary purpose weather mapping the system can be used for navigation A ground mapping feature allows the pilot to identify coastlines water masses islands high ground etc This provides the pilot with a guidance feature which may be useful in adverse weather conditions or over areas where ground based navigational aids are limited For detailed information on the weathe...

Page 228: ...gh the evaporator by the blower and distributed through an overhead duct to individual outlets located adjacent to each occupant The switches and temperature control are located on the lower right side of the instrument panel The temperature control regulates the temperature of the cabin Turning the control clockwise increases cooling counterclockwise decreases cooling The fan speed switch and the...

Page 229: ...ed by a cover at the rear of each unit If high altitude flight is anticipated it should be determined that the oxygen supply is adequate for the proposed flight and that the passengers are briefed When oxygen is re quired insert the mask plug in connector into an outlet and lock by rotating the connector approximately 1 4 turn Don mask s and rotate the ON OFF control knob fully counterclockwise ap...

Page 230: ...the cylinder through the system Connecting the constant flow mask fitting to a receptacle and turning it 90 degrees clockwise automatically releases oxygen to the mask through the on off valve feature of the receptacle The occupant then dons the mask and breathes normally for a sufficient supply of oxygen Each mask assembly oxygen line incorporates a flow indicator When the red pellet in the indic...

Page 231: ...u SECTION 8 AIRPLANE HANDLING SERVICE MAINTENANCE _ ___ ...

Page 232: ...SECTION 8 AIRPLANE HANDLING SERVICE MAINTENANCE __ 0 f __ ...

Page 233: ...3 General 8 1 Airplane Inspection Periods 8 3 Preventive Maintenance 8 4 Airplane Alterations 8 5 Ground Handling 8 6 Engine Air Filter 8 8 Brake Service 8 8 Landing Gear Service 8 9 Propeller Service 8 9 Oil Requirements 8 10 Fuel System 8 10 Tire Inflation 8 12 Battery Service 8 12 Serial Number Plates 8 13 Lubrication 8 13 Cleaning 8 13 Winterization 8 15 REPORT VB 850 8 i ...

Page 234: ...BLANK PAGE ...

Page 235: ...Bulletin Service Letters deal with product improvements and service hints pertaining to the aircraft They are sent to dealers distributors and occasionally at the factory s discretion to latest registered owners so they can properly service the aircraft and keep it up to date with the latest changes Owners should give careful attention to the Service Letter information Service Spares Letters offer...

Page 236: ...SECTION 8 HANDLING SERVICING AND MAINTENANCE PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II REPORT VB 850 8 2 THIS PAGE INTENTIONALLY LEFT BLANK ISSUED AUGUST 23 1976 ...

Page 237: ...etion of the owner This inspection is a complete check of the aircraft and its systems and should be accomplished by a Piper Authorized Service Center or by a qualified aircraft and power plant mechanic who owns or works for a reputable repair shop The inspection is listed in detail in the inspection report of the appropriate Service Manual An annual inspection is required once a year to keep the ...

Page 238: ...r interior of the aircraft excluding balanced control surfaces when removal or disassembly of any primary structure or operating system is not required h Replace side windows and safety belts i Replace seats or seat parts with replacement parts approved for the aircraft j Replace bulbs reflectors and lenses of position and landing lights k Replace cowling not requiring removal of the propeller I R...

Page 239: ...n order and in the aircraft a To be displayed in the aircraft at all times 1 Aircraft Airworthiness Certificate Form FAA 8100 2 2 Aircraft Registration Certificate Form FAA 8050 3 3 Aircraft Radio Station License if transmitters are installed b To be carried in the aircraft at all times 1 Pilot s Operating Handbook 2 Weight and Balance data plus a copy of the latest Repair and Alteration Form FAA ...

Page 240: ...uld ride in the pilot s seat to maintain control by use of the brakes Taxiing Before attempting to taxi the airplane ground personnel should be instructed and approved by a qualified person authorized by the owner Engine starting and shut down procedures as well as taxi techniques should be covered When it is ascertained that the propeller back blast and taxi areas are clear power should be applie...

Page 241: ...sed to properly block the wheels d Mooring The airplane should be moored for immovability security and protection The following procedures should be used for the proper mooring of the airplane i 1 Head the airplane into the wind if possible 2 Retract the flaps 3 Immobilize the ailerons and stabilator by looping the seat belt through the control wheel and pulling it snug 4 Block the wheels 5 Secure...

Page 242: ...filter If paper element is torn or ruptured or gasket is damaged the filter should be replaced The usable life of the filter should be restricted to one year or 500 hours whichever comes first c Installation of Induction Air Filters After cleaning place filter in air box and install cover Secure cover by turning studs Replace cow1 8 13 BRAKE SERVICE The brake system is filled with MIL H 5606 petro...

Page 243: ...e gas charge in the propeller cylinder should be kept at the pressure specified on the placard located in the spinner cap The pressure in the cylinder will increase about one third psi for every degree Fahrenheit increase in temperature This effect should be considered when checking pressure The charge maintained must be accurate and free of excessive moisture since moisture may freeze the piston ...

Page 244: ...plates 8 19 OIL REQUIREMENTS The oil capacity of the Teledyne Continental engines is 8 quarts per engine with a minimum safe quantity of 3 quarts per engine It is recommended that oil be added if the quantity falls to 6 quarts It is recommended that engine oil be drained and renewed every 100 hours or sooner under unfavorable conditions Full flow cartridge type oil filters should be replaced each ...

Page 245: ...ns is shown in the following chart FUEL GRADE COMPARISON CHART Current Military Previous Commercial Current Commercial Fuel Grades MIL G 5572E Fuel Grades ASTM D910 Fuel Grades ASTM D910 75 Amendment No 3 Max TEL Max TEL Max TEL Grade Color ml U S gal Grade Color ml U S gal Grade Color ml U S gal 80 87 red 0 5 80 red 0 5 80 87 red 0 5 91 98 blue 2 0 lOOLL blue 2 0 none none none 100 130 green 3 0 ...

Page 246: ...tions should be carefully followed CAUTIONS Assure that the additive is directed into the flowing fuel stream The additive flow should start after and stop before the fuel flow Do not permit the concentrated additive to come in contact with the aircraft painted surfaces or the interior surfaces of the fuel tanks Some fuels have anti icing additives pre blended in the fuel at the refineary so no fu...

Page 247: ... mechanic to check the fuel system Each fuel tank is provided with a fuel quick drain to check for contamination Each tank should be checked for contamination in accordance with the above procedure Crossfeed drains are located on the bottom of the fuselage inboard of the right flap The fuel drained at each quick drain should be collected in a transparent container and examined for contamination CA...

Page 248: ...e extreme vibration on takeoff In the installation of new components it may be necessary to rebalance the wheel with the tire mounted When checking the pressure examine the tires for wear cuts bruises and slippage 8 25 BATTERY SERVICE Access to the 12 volt 35 ampere hour battery is gained through the nose baggage compartment It is located under the floor panel of the nose baggage compartment The b...

Page 249: ...trip of tape on the magneto vents to prevent any solvent from entering these units r 1 Place a large pan under the engine to catch 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 to brush areas that were sprayed CAUTION Do not spray solvent into the ...

Page 250: ...e following procedure 1 Flush away loose dirt with water 2 Apply cleaning solution with a soft cloth a sponge or a soft bristle brush 3 To remove exhaust stains allow the solution to remain on the surface longer 4 To remove stubborn oil and grease use a cloth dampened with naphtha 5 Rinse all surfaces thoroughly 6 Any good automotive wax may be used to preserve painted surfaces Soft cleaning cloth...

Page 251: ...veral available boot care products for proper operation in icing conditions In cold weather wash the boots while the airplane is in a warm hangar if possible If the cleaning is to be done outdoors heat the soap and water solution before taking it to the airplane If difficulty is encountered with water freezing on the boots use a portable type ground heater to direct a blast of warm air along the a...

Page 252: ...SECTIONS PA 34 200T SENECA II REPORT VB 850 8 16 PIPER AIRCRAFT CORPORATION HANDLING SERVICING AND MAINTENANCE THIS PAGE INTENTIONALLY LEFT BLANK ISSUED AUGUST 23 1976 __ _ ...

Page 253: ...u SECTION 9 SUPPLEMENTS 0 ...

Page 254: ...SECTION 9 SUPPLEMENTS __ ...

Page 255: ... Conditioning Installation KFC 200 AFCS With FD Installation KFC 200 AFCS Without FD Installation KNS 80 Navigation System ANS 351 Area Navigation Computer NP 2041A Area Navigation Computer Programmer RDR 160 Weather Radar System RDR 160 IN2026A Weather Radar System Piper Control Wheel Clock Installation RCA Weather Scout II Monochrome Weather Radar RCA Weather Scout II Color Weather Radar 9 3 9 5...

Page 256: ...BLANK PAGE __ ...

Page 257: ...the airplane 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 numbered as a permanent part of this Handbook The information contained in each Supplement applies only when the related equipment is installed in the airplane ISSUED AUGUST 23 1976 REPOR...

Page 258: ...SECTION9 SUPPLEMENTS REPORT VB 850 9 2 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II THIS PAGE INTENTIONALLY LEFT BLANK ISSUED AUGUST 23 1976 ...

Page 259: ...ON 2 LIMITATIONS Under no circumstances should the unit be turned on for a period exceeding 30 seconds unless a The aircraft is in flight or b Ice exists on the heated panel 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 PROCEDURES An operational check is accompl...

Page 260: ...SECTION9 SUPPLEMENTS REPORT VB 850 9 4 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II THIS PAGE INTENTIONALLY LEFT BLANK ISSUED AUGUST 23 1976 ...

Page 261: ...nd must remain in this handbook at all times when the optional oxygen system is installed 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 with one 1 oxygen unit installed d Oxygen duration Persons Using Each Unit I 2 3 4 DURATION IN HOURS AT ALTITUDE 5 000 10 000 15 000 20 000 ...

Page 262: ... oxygen units c Installation Club seating arrangement only 1 Install mounting base between center seats utilizing slotted receptacles for front attachment points and bolts for aft attachment points 2 Slide oxygen bottles into position on top of mounting base ensuring that all mounting lugs engage in the slotted receptacle and that the locking pin is in the raised position d Turn on oxygen system a...

Page 263: ...al fixed oxygen system is installed SECTION 2 LIMITATIONS a No smoking allowed when oxygen system is in use b Oxygen duration Bottle pressure 1850 PSI DURATION IN HOURS AT ALTITUDE Based on 90 Consumption Persons Using Each Unit 2 3 4 5 6 5 000 7 4 3 7 2 5 1 9 1 5 1 2 10 000 7 7 3 9 2 6 1 9 1 5 1 3 SECTION 3 EMERGENCY PROCEDURES 15 000 8 1 4 1 2 7 2 0 1 6 1 4 20 000 8 3 4 2 2 8 2 1 1 7 1 4 a Time ...

Page 264: ...n on system c Monitor flow indicators and quantity CAUTION Do not use oxygen system below 200 PSI to prevent contamination and or moisture from entering depleted cylinder regulator assembly If cylinder has been depleted it must be removed and refurbished in accordance with the manufacturer s recommended procedures SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of t...

Page 265: ...utoControl IIIB can be disconnected by 1 Pushing the AP ON OFF switch OFF 2 Pulling the AP circuit breaker b The autopilot can be overpowered at either control wheel c An autopilot runaway with a 3 second delay in the initiation of recovery while operating in climb cruise or descending flight could result in a 60 bank and 150 foot altitude loss d An autopilot runaway with a 1 second delay in the i...

Page 266: ...ether the card is disabled or not 2 In the localizer mode the TO FROM arrows may remain out of view depending upon the design of the NAY converter used in the installation SECTION 4 NORMAL PROCEDURES PREFLIGHT a AUTOPILOT 1 Place radio coupler in HDG mode if installed and place the AP ON OFF switch to the ON position to engage roll section Rotate roll command knob left and right and observe that c...

Page 267: ...aft is established on course 2 ILS LOC Front Course a Set inbound front localizer course with H S I course knob b Select LOC Normal on radio coupler to intercept and track inbound on the localizer Select LOC REV to intercept and track the localizer course outbound to the procedure turn area c Select HDG mode on autopilot console to engage coupler 3 ILS Back Course a Set inbound front localizer cou...

Page 268: ...nd place the HOG bug on the inbound course heading to the airport Select LOC REV mode with coupler and HOG mode on the autopilot console SECTION S PERFORMANCE No changes to the basic performance provided by Section 5 of the Pilot s Operaging Handbook are necessary for this supplement REPORT VB 850 9 10 ISSUED AUGUST 23 1976 REVISED AUGUST 1 1977 ...

Page 269: ...acard P N 13A660 J Conduct Trim Check prior to flight see P O H to be installed in clear view of pilot e During autopilot operation the pilot must be in his seat with the safety belt fastened SECTION 3 EMERGENCY PROCEDURES This aircraft is equipped with a Master Disconnect Interrupt Switch on the pilot s control wheel When the switch button is depressed it will disconnect the autopilot When depres...

Page 270: ...ely result in higher control wheel forces Be prepared to manually retrim as necessary to eliminate undesirable forces d Altitude Loss During Malfunction 1 An autopilot malfunction during climb cruise or descent with a 3 second delay in recovery initiation could result in as much as 60 of bank and 200 ofaltitude loss 2 Altitude Joss high altitude descent 3 second delay in recovery could result in a...

Page 271: ...d or not 2 In the localizer mode the TO FROM arrows may remain out of view depending upon the design of the NAV converter used in the installation f Single Engine Operations 1 Engine failure during an autopilot approach operation Disengage autopilot conduct remainder of approach manually 2 Engine failure during go around Disengage autopilot retrim aircraft perform normal aircraft engine out proced...

Page 272: ... pull the trim circuit breaker out until trim system is repaired Substitution of any trim system component for another model is not authorized For emergency interrupt information refer to Section 3 of this Supplement Command Electric Trim Switch The Command Electric Trim Switch on the left hand portion of the pilot s control wheel has two functions 1 When the top bar AP OFF is pressed it disconnec...

Page 273: ... Altitude Hold Upon reaching desired or cruising altitude engage altitude hold mode rocker switch As long as Altitude Hold mode rocker is engaged aircraft will maintain selected altitude For maximum passenger comfort rate of climb or descent should be reduced to approximately 500 FPM prior to altitude hold engagement For accurate Altitude Holding below 100 KIAS lower flaps one or two notches NOTE ...

Page 274: ...nd Tracking Tune the localizer frequency and place the HDG bug on the inbound front course heading Select LOC NORM mode on the coupler and engage HDG mode on the autopilot console 3 For LOC Back Course Intercepts and Tracking Tune the localizer frequency and place the HDG bug on the inbound course heading to the airport Select LOC REV mode on the coupler and engage HDG mode on the autopilot consol...

Page 275: ...ture is indicated by lighting of the green Glide Slope engage Annunciator Lamp and by a slight pitch down of the aircraft e Monitor localizer and Glide Slope raw data throughout approach Adjust power as necessary to maintain correct final approach airspeed All power changes should be of small magnitude and smoothly applied for best tracking performance Do not change aircraft configuration during a...

Page 276: ...SECTION9 SUPPLEMENTS REPORT VB 850 9 18 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II THIS PAGE INTENTIONALLY LEFT BLANK ISSUED AUGUST 23 1976 ...

Page 277: ...air conditioner must be turned OFF manually before the landing approach in preparation for a possible go around b Placards In full view of the pilot in the area of the air conditioner controls when the air conditioner is installed AIR CONDITIONER MUST BE OFF PRIOR TO TAKE OFF AND LANDING AND SINGLE ENGINE OPERATION In full view of the pilot beside the condenser door light AIR COND DOOR OPEN SECTIO...

Page 278: ...ce in climb cruise or range performance of the airplane NOTE To insure maximum climb performance the air conditioner must be turned off manually before takeoff to disengage the compressor and retract the condenser door Also the air conditioner must be turned off manually before the landing approach in preparation for a possible go around The air conditioner must be off during all one engine inoper...

Page 279: ... director command presentation or the autopilot can be engaged to steer the airplane to the flight director command presentation The airplane is equipped with an electric trim system which is controlled by pilot operation of the trim switch The autopilot uses the electric trim to accomplish automatic trimming to unload the autopilot elevator servo so that autopilot disengagement does not result in...

Page 280: ...The autopilot must be disengaged during takeoff and landing f System approved for Category I operation only APPR or BC selected g Autopilot attitude command limits Pitch 15 R l h Placards Location Pilot s control wheel left horn AP TRIM DISC INTERRUPT Pilot s control wheel left horn cws Pilot s control wheel left horn TRIM UP DN Left throttle lever GO AROUND SECTION 3 EMERGENCY PROCEDURES a AUTOPI...

Page 281: ...ITUDE LOSSES DUE TO AUTOPILOT MALFUNCTION 1 Cruise Climb Descent 2 Maneuvering 3 APPR 4 SE APPR CAUTION WHEN THE AUTOPILOT IS ENGAGED MANUAL APPLICATION OF A FORCE TO THE PITCH AXIS OF THE CONTROL WHEEL FOR A PERIOD OF THREE SECONDS OR MORE WILL RESULT IN THE AUTOTRIM SYSTEM OPERATING IN THE DIRECTION TO CREATE A FORCE OPPOSING THE PILOT THIS OPPOSING MISTRIM FORCE WILL CONTINUE TO INCREASE AS LON...

Page 282: ...COMPASS SYSTEM This supplies power to the KCS ssA 55 Compass System PITCH TRIM This supplies power to the FCS Trim System and manual electric trim d PILOT S CONTROL WHEEL SWITCH FUNCTIONS AP DISC TRIM INTERRUPT This emergency disconnect switch will disengage the AP interrupt the power to the electric trim system and disconnect all FD Modes To resume AP control a FD Mode and the AP lever on the Mod...

Page 283: ...irectional gyro information is invalid If a HDG invalid occurs with either NAY APPR or HDG modes selected the AP and or FD is disengaged Basic FD mode may then be re engaged along with any vertical mode and the AP re engaged This flag is labeled HDG in the KCS SSA Compass System TRIM The TRIM warning light located in the lower right corner of the annunciator panel will flash and be accompanied by ...

Page 284: ...and using the vertical trim switch on the KC 290 Mode Controller Hold the control column from moving and observe the autotrim run in the nose up direction after approximately a three second delay Use the vertical trim switch and put in a nose down command Hold the control column and observe the autotrim run in the nose down direction after approximately three seconds 6 Engage the HDG mode and AP S...

Page 285: ... depressed For smooth operation eng3 ge the ALT at no greater than 500 feet per minute climb descent The ALT will automatically disengage when Glideslope couples or the go around switch is depressed ALT hold may be turned off at any time by depressing the ALT switch ALT engagement is displayed on the annunciator panel NOTE THE VERTICAL TRIM SWITCH LOCATED ON THE KC 290 MODE CONTROLLER PANEL MAY BE...

Page 286: ...ngaging HOG or NAY when in APPR CPLD The annunciator panel indicates the status of the approach mode CAUTION THE APPR MODE OF OPERATION WILL CONTINUE TO PROVIDE AIRPLANE CONTROL WITHOUT A VALID VOR LOC SIGNAL NAY FLAG IN VIEW 8 Back Course Mode For back course BC operation proceed as for normal approach mode but engage BC after selecting APPR The BC switch reverses the signals in the computer and ...

Page 287: ...will now track LOC and GS Adjust throttles to control speed on descent Set HDG bug for missed approach but do not engage HDG I NOTE Operation of marker test function after APPR CPLD will reduce the flight control system gains If this should occur the APPR switch should be recycled 7 Landing or missed approach a Disengage AP and land b Go Around by depressing GA switch on left engine throttle The A...

Page 288: ...AIRCRAFT CORPORATION PA 34 200T SENECA II Installation of the King KFC 200 Flight Control System does not effect the basic performance information presented by Section 5 of this handbook REPORT VB 850 9 30 ISSUED AUGUST 30 1978 REVISED OCTOBER 5 1979 ...

Page 289: ...l pitch and roll The airplane is equipped with an electric trim system which is controlled by pilot operation of the trim switch The autopilot uses the electric trim to accomplish automatic trimming to unload the autopilot elevator servo so that autopilot disengagement does not result in transient airplane motion An autotrim electric pitch trim monitor is provided in the autopilot Autotrim and or ...

Page 290: ...he autopilot must be disengaged during takeoff and landing f System approved for Category I operation only APPR or BC selected g Autopilot attitude command limits Pitch 15 Roll 25 h Placards Location Pilot s control wheel left horn AP TRIM DISC INTERRUPT Pilot s control wheel left horn cws Pilot s control wheel left horn TRIMUP DN Left throttle lever GO AROUND SECTION 3 EMERGENCY PROCEDURES a AUTO...

Page 291: ...r the airplane is trimmed out pull the trim breaker and turn the RADIO POWER switch back on d MAXIMUM ALTITUDE LOSSES DUE TO AUTOPILOT MALFUNCTION 1 Cruise Climb Descent 2 Maneuvering 3 APPR 4 SE APPR CAUTION WHEN THE AUTOPILOT IS ENGAGED MANUAL APPLICATION OF A FORCE TO THE PITCH AXIS OF THE CONTROL WHEEL FOR A PERIOD OF THREE SECONDS OR MORE WILL RESULT IN THE AUTOTRIM SYSTEM OPERATING IN THE DI...

Page 292: ...radio circuit breakers AP and TRIM circuit breakers c The KFC 200 is controlled by the following circuit breakers AUTOPILOT This supplies power to the KC 295 Flight Computer KA 285 Annunciator KC 292 Mode Controller and both AP servos PCS MASTER This in conjunction with the RADIO POWER switch supplies power to the avionics bus COMPASS SYSTEM This supplies power to the KCS 55A 55 Compass System PIT...

Page 293: ... mode This flag is labeled HDG in the KCS 55A Compass System TRIM The TRIM Warning light located in the lower right corner of the annunciator panel will flash and be accompanied by an audible warning whenever autotrim and or manual electric pitch trim failures occur Trim servo motor running without a command is monitored on both trim modes Trim servo motor not running when commanded to run and the...

Page 294: ...and put in a pitch up command using the vertical trim switch on the KC 292 Mode Controller Hold the control column from moving and observe the autotrim run in the nose up direction after approximately a three second delay Use the vertical trim switch and put in a nose down command Hold the control column and observe the autotrim run in the nose down direction after approximately three seconds 6 En...

Page 295: ... the desired heading oil the PNI engage the AP and depress the HDG switch on the Mode Controller HDG and AP will be displayed on the annunciator panel The airplane will turn to the heading selected and hold The pilot may then choose any new heading by merely setting the bug on a new heading The airplane will automatically turn in the direction the heading bug is turned To disengage the HDG Mode de...

Page 296: ...n of the vertical trim switch on the Mode Controller provides a convenient means of adjusting the ALT hold or PAH angle function without disengaging the mode 10 Go Around Mode GA The GA mode may be engaged any time the AP is engaged by depressing the GA switch on the left engine throttle GA will illuminate on the annunciator panel indicating mode status on models with serial numbers 34 8070021 and...

Page 297: ...s should occur the APPR switch should be recycled 7 Landing or missed approach a Disengage AP and land b Go Around by depressing the GA switch on left engine throttle on models with serial numbers 34 8070021 and below The AP will remain engaged and will command a climb APPR MOde may be used for a straight away missed approach or HDG may be engaged to turn to the missed approach heading On models w...

Page 298: ...SECTION9 SUPPLEMENTS I REPORT VB 850 9 40 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II THIS PAGE INTENTIONALLY LEFT BLANK ISSUED JULY25 1980 ...

Page 299: ...ot s Operating Handbook are necessary for this supplement SECTION 4 NORMAL PROCEDURES a KNS 80 OPERATION The KNS 80 can be operated in any one of 3 basic modes a VOR b RNAV or c ILS To change for one mode to another the appropriate pushbutton switch is pressed except that the ILS mode is entered automatically whenever an ILS frequency is channeled in the USE waypoint The display will annunciate th...

Page 300: ...to go to FRQ mode 5 DSP BUTTON Momentary pushbutton Causes displayed waypoint to increment by 1 and data display to go to frequency mode 6 DATA BUTTON Momentary pushbutton Causes waypoint data display to change from FRQ to RAD to DST and back to FRQ 7 OFF PULL ID CONTROL a Rotate counterclockwise to switch off power to the KNS 80 b Rotate clockwise to increase audio level c Pull switch out to hear...

Page 301: ...b in position varies 1 NM digit Center knob out position varies 0 1 NM digit 9 COURSE SELECT KNOB Located in CDI unit Selects desired course through the VOR ground station or waypoint SECTION 5 PERFORMANCE SECTION9 SUP PLEMENTS No changes to the basic performance provided by Section 5 of this Pilot s Operating Handbook are necessary for this supplement ISSUED JULY 25 1980 REPORT VB 850 9 43 ...

Page 302: ...SECTION9 SUPPLEMENTS I REPORT VB 850 9 44 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA Il THIS PAGE INTENTIONALLY LEFT BLANK ISSUED JULY 25 1980 ...

Page 303: ...at all times when the optional ANS 351 Area Navigation Computer is installed SECTION 2 LIMITATIONS No changes to the basic limitations provided by Section 2 of this Pilot s Operating Handbook are necessary for this supplement SECTION 3 EMERGENCY PROCEDURES No changes to basic Emergency Procedures provided by Section 3 of this Pilot s Operating Handbook are necessary for this supplement SECTION 4 N...

Page 304: ...Two concentric knobs set radial information into the display Knobs control information as follows Large knob Changes display in 10 degree increments Small knob pushed in Changes display 1 degree increments Small knob pulled out Changes display in 0 1 degree increments Two concentric knobs set distance information in nautical miles into the display Knobs control information as follows Large knob Ch...

Page 305: ...point is at this point inactive Waypoint number 2 bearing and distance definitions are then set into the ANS 351 I c Set up the rest of the desired waypoints as described above d Press the RTN return pushbutton to display the active waypoint 2 Changing Waypoints In Flight To change a waypoint in flight rotate the waypoint selector until the desired waypoint number and coordinates are displayed on ...

Page 306: ...SECTION9 SUPPLEMENTS REPORT VB 850 9 48 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II THIS PAGE INTENTIONALLYLEFf BLANK ISSUED JULY25 1980 ...

Page 307: ...hanges to the basic limitations provided by Section 2 of this Pilot s Operating Handbook are necessary for this supplement SECTION 3 EMERGENCY PROCEDURES No changes to basic Emergency Procedures by Section 3 of this Pilot s Operating Handbook are necessary for this supplement SECTION 4 NORMAL PROCEDURES NOTE The 1 VOR and DME receivers supply information to the NAY computer programmer which in tur...

Page 308: ...ding 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 Press DIST key press number keys corresponding to the waypoint distance and press the ENTER key 4 STATION ELEVATION Press EL key press number keys corresponding to the station elevation in hundreds of f...

Page 309: ... displayed in minutes 3 HSI The HSI presents unprocessed information with conventional angular sensitivity i e full scale deviation equals l 0 off course 4 DISPLAY SELECTOR SET TO SBY Data stored for standby waypoint number appearing in SBY window is displayed and can be altered as desired 5 DISPLAY SELECTOR SET TO ACT Data stored for active waypoint number in ACT display window is displayed but c...

Page 310: ...ogram COM 1 or COM 2 frequencies 2 COM 1 FREQUENCY Press COM I key press number keys corresponding to the desired frequency and press the ENTER key 3 COM 2 FREQUENCY Press COM 2 key press number keys corresponding to the desired frequency and press the ENTER key 4 NAV 1 FREQUENCY Set the mode selector to VOR LOC To tune NAV I from keyboard mode selector must be set to VOR LOC Press NAV 1 key press...

Page 311: ...l RDR 160 Weather Radar System is installed SECTION 2 LIMITATION No changes to the basic limitations provided by Section 2 of this Pilot s Operating Handbook are necessary for this supplement 1 SECTION 3 EMERGENCY PROCEDURES _ No changes to basic Emergency Procedures by Section 3 of this Pilot s Operating Handbook are necessary for this supplement SECTION 4 NORMAL PROCEDURES a System Controls Tabl...

Page 312: ...UT PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II RANGE MARK SELECTED HOLD SELECTED MOOE SPACING N M RANGE N M PUSHBUTTON t _ _ o _ RANGESELECTOR BRIGHTNESS CONTROL lREPORT VB 950 9 54 LOCATION OF CONTROLS Figure 4 1 TILT CONTROL ISSUED JULY 25 1980 ...

Page 313: ...e selected for ground mapping operations Contour operation is disabled 3 In Wx A position the radar indicator display alternately cycles between the Wx position and the GAIN MAP position This will verify if a contour storm cell area is a storm cell and not a Jake or some other terrain feature When the HOLD pushbutton initially depressed weather or ground mapping image last presented is retained fr...

Page 314: ...URING REFUELING OPERATIONS OR IN THE VICINITY OF TRUCKS OF CON TAINERS ACCOMMODATING FLAMMABLES OR EXPLOSIVES DO NOT ALLOW PERSONNEL 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 constantly changing and continued observation is always advisable where areas of turbu...

Page 315: ...n with the complete handbook This supplement has been FAA Approved as a permanent part of this handbook and must remain in this handbook at all times when the optional RDR 160 IN2026A Weather Radar System is installed SECTION 2 LIMITATIONS No changes to the basic limitations provided by Section 2 of this Pilot s Operating Handbook are necessary for this supplement SECTION 3 EMERGENCY PROCEDURES No...

Page 316: ...AIRCRAFT CORPORATION PA 34 200T SENECA II INDICATES WHEN FUNCTION SWITCH IS SET TO TEST RADAR RECEIVER GAIN CONTROL TRACK CURSOR BUTTON POSITIONED RANGE MARK 30 MILE ANTENNA TILT CONTROL IN 2026A CONTROLS AND DISPLAYS Figure 4 1 a Equipment Operation and Controls 1 RDR 160 IN 2026A Controls and Displays Controls and displays for the RDR 160 IN 2026A Weather Radar System are listed in table 4 3 wit...

Page 317: ...he right in one degree steps while the button is held depressed The track cursor stops when the button is released and remains for about 10 to 15 seconds then disappears unless the button is pressed again The differential heading will be indicated in yellow numerals in the upper left corner of the display and disappears simul taneously with the track cursor When pressed the yellow track cursor app...

Page 318: ...hen button is actuated push on The word HOLD flashes in the upper left corner of the display The weather or ground mapping image last presented is retained frozen on indicator display in order to evaluate the significance of storm cell movement Switching back to normal operation pressing HOLD pushbutton a second time reveals direction and distance of target movement during HOLD period In HOLD the ...

Page 319: ...NS No changes of the basic limitations provided by Section 2 of this Pilot s Operating Handbook are necessary for this supplement SECTION 3 EMERGENCY PROCEDURES No changes of the basic Emergency Procedures provided by Section 3 of this Pilot s Operating Handbook are necessary for this supplement SECTION 4 NORMAL PROCEDURES a SETTING While in the CLOCK mode the time and the date can be set by the o...

Page 320: ... they are flashing in the set mode pressing the RST button will return the clock to the normal timekeeping mode without altering the minutes timing This feature is useful when changing time zones when only the hours are to be changed d AUTOMATIC DATE ADVANCE The calendar function will automatically advance the date correctly according to the four year perpetual calendar One day must be added manua...

Page 321: ...htpath and gives the pilot a 4 level visual display of their intensity Areas of heaviest rainfall level 3 will be brightest areas of less severe and moderate rainfall levels 2 and 1 will be progressively less bright and no rainfall level 0 will be black The radar system performs only the function of weather detection and should not be used nor relied upon for proximity warning or anti collision pr...

Page 322: ...nfall Pressing switch second time restores normal or WX mode Maximum selected range is displayed Maximum range is always displayed when Indicator is in ON condition Test block displays three illuminated levels Individual label displayed for each range mark Operating mode is displayed as CYC When system is first turned on WAIT is displayed until system times out 30 40 seconds SECTION 2 LIMITATIONS ...

Page 323: ...Adjust TILT control for desired forward scan area CAUTION If the radar is to be operated while the aircraft is on the ground a Direct nose of aircraft such that antenna scan sector is free of large metallic objects hangars other aircraft for a distance of 100 feet 30 meters and tilt antenna fully upward b Avoid operation during refueling of aircraft or during refueling operations within 100 feet 3...

Page 324: ...t I SECTION9 SUPPLEMENTS REPORT VB 850 9 66 PIPER AIRCRAFT CORPORATION PA 34 200T SENECA II THIS PAGE INTENTIONALLY LEFT BLANK ISSUED NOVEMBER 19 1980 ...

Page 325: ...ed at one of four video levels 0 1 2 or 3 Level 0 is shown as a dark screen because of weak or no returns levels 1 2 and 3 are shown as green yellow and red displays which represents increasing rainfall from least to heaviest The system consists of three units a Receiver Transmitter Antenna a Digital Indicator and a Weather Scout Interface Unit a Receiver Transmitter Antenna RTA The major assembli...

Page 326: ... 1 2 3 and color bar legend is displayed in WX C TEST and MAP modes In weather mode color bar is green yellow and red In map mode color bar is cyan yellow and magenta Five labelled range marks are displayed on each range Label of furthest mark is same as range selected Range and azimuth marks are displayed in cyan for WX C andTEST green for MAP Rotary control used to regulate brightness intensity ...

Page 327: ...d with incoming target return data As a warning to the pilot FRZ level will flash on and off at 0 5 second intervals c Slide switch used to display three azimuth markers at 30 degree intervals Rotary control that enables pilot to select angles of antenna beam tilt with relation to airfame Rotating control CW tilts beam upward CCW rotation tilts beam downward Pushbutton switches used to select desi...

Page 328: ...ode after it has been operating rotate INT control momentarily to OFF then back to desired viewing position Radar will then remain in STBY with no radiated power until an operating mode is selected CAUTION If the radar is to be operated while the aircraft is on the ground a Direct nose of aircraft such that antenna scan sector is free of large metallic objects hangars other aircraft for a distance...

Page 329: ...0 SECTION 10 SAFETY TIPS ...

Page 330: ...SECTION 10 SAFETY Tl PS ...

Page 331: ...Paragraph No TABLE OF CONTENTS SECTION 10 SAFETY TIPS Page No 10 1 General 10 1 10 3 Safety Tips 10 1 REPORT VB 850 10 i ...

Page 332: ... 1 I I BLANK PAGE __ ...

Page 333: ...weight on the step d Before attempting to reset any circuit breaker allow atwo to five minute cooling off period e Always determine position of landing gear by checking the gear position lights f A high fuel pressure indication on the fuel flow indicator is a possible sign of restricted fuel nozzles g The shape of the wing fuel tanks is such that in certain maneuvers the fuel may move away from th...

Page 334: ...s for a small fee The training is free at the NASA Center in Houston and at the FAA Aeronautical Center in Oklahoma Forms to be completed Physiological Training Application and Agreement for application for the training course may be obtained by writing to the following address Chief of Physiological Training AAC 143 FAA Aeronautical Center P 0 Box 25082 Oklahoma City Oklahoma 73125 It is recommen...

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