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Piper Seneca 1972 POH/Manual

1. 3 9 6 Landing Gear Unsafe is 3 9 7 Rear Cabin and Cargo Doors 2 4 2 3 9 FAA APPROVED March 10 1972 REPORT 423 PAGE 3 1 REVISED April 26 1974 MODLE PA 34 200 SENECA E Enierpeney cuis ind 3 11 l Metectine a Dead anu erar ni ere er 3 11 2 Feathenng Procedur lan 3 1 3 Unfeathering Procedures ssa 3 12 4 Fuel Management During Single Engine penan m 3 12 5 Engine Failure During Takeoff cccsssstssssssecssssnncsssccsansussonsstsesccaes 3 12a 6 Engine Failure During Climb c sssdsencessssnerecconcscoscsrossronsrovecaseesesvewsas 3 13 7 Single Engine Landing ador aedi repete a C ee He aai 3 13 Single Engine id 3 13 9 Manual Extension of Landing 22222 422 4 3 14 10 Landing Gear Unsafe 2 2222 2 2 3 14 11 Gear Up Emergency Landing eee e e ecce esee en eene etes e asc 3 14 12 Electrical Falun 3 14 13 WacuumrSystems Fallur s i c cececseysounsieacensepssnessssnosasaecactseane rccasceoesess 3 16 14 Engine Fire nn Doreen ne A 3 16 SAA pissed 3 17 16 Engine Failure In Icing Eopditionse 3 17 17 Alternator Failure In Icing Conditions
2. Nur qe LA n L1 r a EU EST IU ote A dor Tre A Y 4 Mu a bles ae ERI a E A 4 NETT y gt LAE 2 AP AA Ae s ar DAG 1 A du TA rip rity 29 1 Jom ri gt TR T E CERE n uc Yi o er ER M 2 E 1 t 1 4 MV M ah ad im a ac Ma F INCH cele 7 m rl U rear rJ MT x a gt D 4 4 ry k ee M rJ vi i uen i u EX ale Nds Mns 1 a Ar Ks 1 0 x 19 2 LJ n a r M Nas AN i 1 d X 1 dit HS 1 Y 4 4 I RIS dis e D OPERATING INSTRUCTIONS THIS SECTION IS DESIGNED 1 help you operate your Seneca with safety and confidence 2 more fully acquaint you with the basic performance and handling characteristics of the airplane 3 To more fully explain your Seneca s operation than is permissible to set forth in the Airplane Flight Manual 22002
3. A NO 8 6 Multi Engine Climb Performance ne rr AAN 8 7 Single Engine Climb Performance mc tenen 8 8 Cruise Performance True Airspeed 8 9 Cruise Performance MEER TE 8 10 Stalling Speed vs Weight eene nennen 8 11 Stalling Speed vs Angle of tH TT 8 12 Landing Ground Run Distance eene 8 13 Landing Distance Over 50 MEME T EE 8 14 Power Setting m d 8 16 WARNING Performance information derived by extrapolation beyond the limits shown on the charts should not be used for flight planning purposes BLANK PAGE SENECA 400 Pt TAIN YY NT ACHE THIS CHART SHOULD BE USED TO AND PRESSURE ALTITUDE CONDITIONS FOR USE WITH PERFORMANCE CHARTS 7 E S sc AXE Ne ALTITUDE CONVERSION CHART DETERMINE DENSITY ALTITUDE FROM EXISTING TEMPERATURE EARN MISN3Q 24600 20000 16600 TEMPERATURE F Press Alt 8000 Ft Density Alt 7500 Fi Example Temp 25 F PERFORMANCE CHARTS ISSUED March 10 1972 SENECA 761 50 TAKE OFF GROUND RUN DISTANCE TEMPERATURES WEIGHTS AND WINDS FULL POWER BEFORE BRAKE RELEASE mnes SHORT FIELD EFFORT PAVED LEVEL DRY
4. N EFS DER r an a Y AIRPLANE FLIGHT MANUAL FOR SENECA APPLICABLE TO SERIAL NUMBERS 34 7250001 THRU 34 7250189 WHEN PIPER KIT 760607 IS INSTALLED 34 7250190 THRU 34 7250214 WHEN PIPER KIT 760611 IS INSTALLED AND 34 7250215 THRU 34 7350353 WARNING EXTREME CARE MUST BE EXERCISED TO LIMIT THE USE OF THIS REPORT TO APPLICABLE AIRCRAFT THIS REPORT REVISED AS INDICATED BELOW OR SUBSEQUENTLY REVISED IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED BELOW WHEN APPROVED BY PIPER AIRCRAFT CORPORATION SUBSEQUENT REVISIONS SUPPLIED BY PIPER AIRCRAFT CORPORATION MUST BE PROPERLY INSERTED MODEL PA 34 200 AIRCRAFT SERIAL 34 7350124 REGISTRATION NO N Z 9 75P AIRPLANE FLIGHT MANUAL REPORT NUMBER VB 423 REVISION PIPER AIRCRAFT CORPORATION APPROVAL SIGNATURE AND STAMP NOTE 1244 W BARNHOUSE PIPER AIRCRAFT CORPORATION D O A No SO 1 VERO BEACH FLORIDA DATE OF APPROVAL MARCH 10 1972 APPROVAL BASIS FAR 23 AND FAR PART 21 SUBPART J REPORT VB 423 MODEL PA 34 200 BLANK PAGE AIRPLANE FLIGHT MANUAL Supplements FA eee hee ee ERN Pr LI 2 21 BLANK PAGE SENECA TABLE OF CONTENTS Log OP Revisions ates satura gore sn 3 11 SECTION I Limitations C 971 Engines een ee um in 3 B Buel uenire
5. pursuant to the Federal Aviation Act a oin PaT DIOS lA CORNEA N ed Ves n ted and found to conform lo Ihe Iype to which issued nas been inspectec Qd wn to meel the req noted herein ona on international Gral Aviation except as prowded by Exceptions NONE this tion date 15 otherwise established by the Administrator ONDITIONS termina are m 5 sooner surrendered suspended revoked a tenance preventalive maintenance and alterations pertormed ed m the United as long as the main nd the aircraft 15 register en ofthe Federal Aviation Regulations as sppropriale a accordance with Parts 21 43 DESIGNATION NUMBER DATE OF ISSUANCE v7 D gt SAT FSDO exceeding 3 TESI weding 51 000 or imprisonmen or misuse ATED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL Any alteralen Ae produced ST BE DISPLAYED 1 MU years or both THIS CERTIFICATE a AVIATION REGULATIONS FAA Form 8100 2 2 22 WAYMAN AVIATION SERVICE INC Bldg 209 Musick Rd Opa Locka Airport Opa Locka FL 33054 Ph 305 685 6468 Fax 305 685 6449 Piper Seneca I N 87SP LI April 2009 April 2010 TRANSPONDER April 2008 April 2010 STATIC SYSTEM April 2008 April 2010 ANNUAL April 2009 April 2010 100 HRS 4 629 7 Tach 4 729 7 Tach
6. eee eee esee ee trente 3 17 18 Engine Failure With Rear Cabin and Cargo Doors Removed 3 17 19 iecit cit amt m nee icum 3 8 D Special Operating Procedures 3 18 1 Flight In Known Icing Conditions 3 18a SECTION III aaO Stalls Me O le Power Off Stalls ARA 3 19 2 Power Stalls 3 19 3 Stall Warning System a 3 19 Stalling Speeds MPH Calibrated Airspeed vs Angle of Bank 3 19 C Aircraft Performance With Rear Cabin and Cargo Doors 3 19 SECTION IV Supplements 3 2 A Electric Pitch Trim Installation EIS 3 23 B AutoControl III Installation se etwa rnoes 3 24 C AltiMatic IIIB 1 Installation ceres eren eni c ee 3 25 D AltiMatic V FD 1 and AltiMatic V 1 Installation cccccsccecssessesessocccnensese 3 26 E Windshield Heating Installation ccccscsssssssesssssessceccscsec
7. 2 1 Punfrdilo en se dn A rads 2 1 2 2 Propellers 2 4 Landing Gear System eere E 2 4 Flight Control Systems ao 2 9 Fuel System PRR 2 10 Electrical System acs 2 12 MEeinwIby2uP M O 2 16 Instrument Panel ii dedican ea EEE 2 18 Pitot Static Systems reser eee tenente ntn nnne sete 2 18 Heating Ventilating and Defrosting System 2 20 Ice Protection System 2 22 a RE 2 26 Finish u E 2 26 Baggage Area M 2 26 Stall Warp ss 7 2 27 BLANK PAGE SENECA DESCRIPTION AIRPLANE AND SYSTEMS THE AIRPLANE The Seneca is a twin engine all metal retractable landing gear airplane It has seating for up to seven occupants and two separate luggage compartments AIRFRAME Except for the steel used in the engine mount and landing gear and the fiberglass used in such portions as the nose an
8. DEC 07 2 PAGE 2 OF 8 190 00181 04 Rev B Tomlinson Avionics Inc PH 941 936 6969 511 Danley Page rield Ft Myers FL 33907 Repair Station NO YN1D644K Aircraft Make Mae ADE lt GARMIN GNS 530 VHF Communications Aircraft Model PROP Transceiver VOR ILS Receiver GPS Receiver Aircraft Senal Number di 750 SECTION I GENERAL 1 The GNS 530 System is a fully integrated panel mounted instrument which contains a VHF Communications Transceiver a VOR ILS receiver and a Global Positioning System GPS Navigation computer The system consists of a GPS antenna GPS Receiver VHF VOR LOC GS antenna VOR ILS receiver VHF COMM antenna and a VHF Communications Transceiver The primary function of the VHF Communication portion of the equipment is to facilitate communication with Air Traffic Control The primary function of the VOR ILS Receiver portion of the equipment is to receive and demodulate VOR Localizer and Glide Slope signals The primary function of the GPS portion of the system is to acquire signals from the GPS system satellites recover orbital data make range and Doppler measurements and process this information in real time to obtain the user s position velocity and time 2 Provided the GARMIN GNS 530 s GPS recciver is receiving adequate usable signals it has been demonstrated capable of and has been shown to meet the accuracy specifications for e gt VFR IFR enroute terminal and no
9. LANDING CHECKLIST Seat Backs Erect Fasten Belts Hamess Fuel Selectors On Cowl Flaps Set Electric Fue Pumps On Mixtures Rich Propellers Set Gear Down Flaps Set 125 MPH Max Adjacent to fuel tank filler cap RUEL 100 130 AVIATION GRADE USABLE CAPACITY 46 5 GAL REPORT VB 423 PAGE 3 5 MODEL PA 34 200 SENECA On storm window DO NOT OPEN ABOVE 150 MPH On instrument panel COOLER WINTERIZATION PLATE TO BE REMOVED WHEN AMBIENT TEMPERATURE EXCEEDS 50 F On switch located below engine control pedestal with windshield heating installation WINDSHIELD PANEL HEAT SEE AIRCRAFT FLIGHT MANUAL On engine instrument panel cover to left of engine controls with windshield heating installation WARNING THIS AIRCRAFT IS NOT APPROVED FOR FLIGHT IN ICING CONDITIONS In full view of the pilot for flight with the aft fuselage doors removed FOR FLIGHT WITH AFT DOORS REMOVED CONSULT THE LIMITATIONS AND PROCEDURES SECTIONS OF THE AIRPLANE FLIGHT MANUAL L VACUUM GAUGE The operating limits for the vacuum system are 4 5 to 5 2 inches of mercury for all operations M FLIGHT INTO KNOWN ICING CONDITIONS For flight in icing conditions the following equipment must be installed accordance with Piper drawings or in an FAA approved manner Pneumatic wing and empennage boots 1 2 Electrothermal propeller boots 3 Electric windshield panel 4 Heat
10. Special flight permits may be issued accordance with sections 21 197 and 21 199 of the Federal Aviation Regulations Page 3 of a 99 14 01 14 CFR 21 197 and 21 199 to operate the airplane to a location where the requirements of this AD can be accomplished 9 An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager Small Airplane Directorate FAA 1201 Walnut suite 900 Kansas City Missouri 64106 The request shall be forwarded through an appropriate FAA Maintenance Inspector who may add comments and then send it to the Manager Small Airplane Directorate NOTE 3 Information concerning the existence of approved alternative methods of compliance with this AD if any may be obtained from the Small Airplane Directorate All persons affected by this directive may examine information related to this AD at the FAA Central Region Office of the Regional Counsel Room 1558 601 E 12th Street Kansas City Missouri 64106 This amendment supersedes AD 98 04 27 Amendment 39 10339 g This amendment becomes effective on August 17 1999 FOR FURTHER INFORMATION CONTACT Mr John P Dow Sr Aerospace Engineer FAA Small Airplane Directorate 1201 Walnut suite 900 Kansas City Missouri 64106 telephone 816 426 6932 facsimile 816 426 2169 Page 4217 2 99 14 01 All wing icing inspection lights mus
11. sssesscssssseererssrersrccsecens 4 1 Weight and Balance Data Weighing 22 4 3 Weight and Balance P 4 4 Range and Weight Instructions eese entere tnter 4 7 Instructions for Using the Weight and Balance Plotter e 4 10 Sample Problem ssonssosssesunesnusonsesnnensnesssnnennsnuessnsennesnnennnesnnnassonnonnunssasensunnsnssustsnssnnsnosenenene 4 12 Equipment List 9000 RR ANA l X 4 13 BLANK PAGE INDEX WEIGHT AND BALANCE Log of Revisions sscsscnsscssscceesenensannvsees ORE DR EE 4 Weight and Balance 4 1 Weight and Balance Data Weighing Procedure ceca ene entente 4 3 Weight and Balance Data 4 6 C Range and Weight Instructions eesesasssssnenesnensanenosensnnennesnennensnnnnsnnensnssnrannsnranunssonsssesnensensennenn 4 7 Instructions for Using the Weight and Balance Plotter creer eere eene 4 10 Sample P 4 12 EquipitienP ucc aii dens ed
12. SMOLLAYO 831Au32 HOILYSIVONT Ag O12OYA TYIIIHI MOS IHYH2 314131 miuus 335 TW UAGH DE VIN UNO UO SIMI NO 31Vy34O LENA JHL qv HIWA Q32 AHIE 93 WO Ci OE SE AUDAD YOSHI NOLLIOHOD T TAR OTid Ava 4 0 01 000 ave 4 06 O1 cC OF a SRN RIVED SOND WO N33MOT VOLOJ NI WEMIVULE 1254 AT DOTADO gt 3 WO 1N30 1130 10 36 YO ON ONOI 336 0 ALLA TONEY NY 04 3405 0dx3 ONY DhiNv312 L rudur WO DAYS 4 Worin WED HO rigen bg Y LY NWSE 40 CIE ONY SusTION ELVI ONY 1099 SILON ihvan 30 HANDLING AND SERVICING ISSUED March 10 1972 9 10 SENECA a SPRAY nu nu hd lt at xm HANDLING AND SERVICING ISSUED March 10 1972 9 11 WAYMAN AVIATION SERVICE INC Bldg 209 Musick Rd Opa Locka Airport Opa Locka FL 33054 Ph 305 685 6468 Fax 305 685 6449 Piper Seneca I N887SP E L T April 2009 April 2010 TRANSPONDE
13. 1 Marker Beacon Receiver Remote Unit Cable UGR 2 Glide Slope Receiver Cable Antenna Coupler with dual VHF and or Glide Slope IFD Starlight Transponder Panel Unit Antenna Cable King KN60C DME Receiver Antenna u Cable Antenna Narco 5 Transponder Panel Unit Remote Unit Cable Interconnecting Antenna and Cable ISSUED March 10 1972 Weight Lbs 1 1 0 3 0 2 2 4 2 3 0 1 0 3 6 8 15 0 3 2 0 5 7 0 5 0 3 Arm Aft Cert Datum Moment Basis 121 7 134 TC A7SO 128 0 38 TC A7SO 96 0 19 TC 75 28 6 69 TC A7SO 45 3 32 TC A7SO 553 11 TC A7SO 64 4 148 TC A7SO 52 5 5 TC A7SO 5 5 15 TC A7SO 61 7 420 TC A7SO 112 1 17 75 85 6 26 75 64 4 129 A7SO 20 7 118 75 43 5 22 A7SO 45 0 14 A7SO REPORT VB 424 PAGE 4 27 MODEL PA 34 200 SENECA Weight Arm Cert Item Item Lbs Datum Moment Basis K Radio Equipment Optional Equipment cont Narco AT6 A Transponder Panel Unit 2 0 64 4 129 TC A7SO Remote Unit 5 9 20 7 118 750 Cable Interconnecting 0 5 43 5 22 TC A7SO Antenna and Cable 0 3 45 0 14 TC A7SO Narco AT50 Transponder Panel Unit 3 0 62 3 187 TC A7SO Antenna and Cable TC A7SO King KT76 78 Transponder x Panel Unit 3 1 63 1 196 TC A7SO x Antenna and Cable TC A7SO X King KMA 20 Audio Panel 2 8 65 2 183 TC A7SO Antenna 5 116 3 58 A7SO
14. MODEL PA 34 200 SENECA THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 424 PAGE 4 16b ISSUED August 2 1972 MODEL PA 34 200 SENECA Item Item Instruments Compass Piper Dwg 67462 Tachometer Piper 62177 3 2 lbs each Tachometer Piper 62177 9 2 70 lbs each Engine Cluster Piper 95241 8 2 95 Ibs each Altimeter Piper PS50008 2 or 3 Manifold Pressure Dual Piper PS50031 2 Fuel Flow Gauge Dual Piper 96394 0 Ammeter Piper 66696 2 3 Ibs each Tru Speed Indicator Piper PS50049 6 or 8 ISSUED March 10 1972 REVISED September 19 1973 Weight Lbs 0 9 1 4 19 1 0 1 2 0 6 0 6 Arm Aft Datum 64 9 67 4 65 9 66 2 67 4 66 8 Moment 58 93 93 128 66 79 79 40 40 Basis TSO Cic TC A7SO 75 75 TSO TSO C45 TSO C47 TC A7SO TSO C2b REPORT VB 424 PAGE 4 17 MODEL PA 34 200 SENECA Weight Arm Aft Cert Item Item Lbs Datum Moment Basis Hydraulic Equipment Cylinder Hydraulic Nose Gear Piper Dwg 96860 0 0 9 41 6 37 TC A7SO Cylinder Hydraulic 2 Main Gear Piper Dwg 96860 0 X _ 0 9 Ibs each 1 8 108 4 195 TC A7SO Pump Assembly Piper X Dwg 96110 0 9 0 0 2 2 TC A7SO Switch Pressure Consolidated X Control 211 243 12 0 2 48 9 10 TC A750 Valve Relief AN6245AB4 2350 50 PSI Opening Pressure 0 2 43
15. 5 By using the figures of Item 1 and Item 4 locate a point on the C G range and weight graph If the point falls within the C G envelope the loading meets the weight and balance requirements SAMPLE LOADING PROBLEM Normal Category Arm Weight Datum Moment Inches In Lbs Licensed Basic Weight Pilot and Front Passenger Passengers Center Seats Passengers Rear Seats Passenger Jump Seat The center of gravity C G of this sample loading problem is at inches aft of the datum line Locate this point on the C G range and weight graph Since this point falls within the weight C G envelope this loading meets the weight and balance requirements IT IS THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNER TO INSURE THAT THE AIRPLANE IS LOADED PROPERLY Optional Equipment ISSUED March 10 1972 REPORT VB 424 PAGE 4 7 REVISED May 30 1975 MODEL PA 34 200 ES SENECA C G RANGE AND WEIGHT INSTRUCTIONS 1 Add the weight of all items be loaded to the licensed empty weight 2 Use loading graph to determine the moment of all items to be carried in the airplane 3 Add the moment of all items to be loaded to the licensed empty weight moment 4 Divide the total moment by the total weight to determine the C G location 5 By using the figures of Item 1 and Item 4 locate a point on the C G range and weight graph If the point falls within the C G envelope the loading meets th
16. SSS SSS OPERATING INSTRUCTIONS PREFLIGHT If you are planning a flight in the Seneca 1 Make sure the weather is suitable 2 Plan the navigation if going cross country 3 Check weight and balance for the flight See weight and balance section of this manual 4 Investigate performance and range See performance section of this manual 3 Ml a 4 OPERATING INSTRUCTIONS ISSUED March 10 1972 6 1 SENECA WALK AROUND INSPECTION In Cabin Landing gear control Ensure that it is in the DOWN position Avionics Turn off to save power and wear on the units Master switch Turn on Landing gear lights Three green lights should be illuminated No red light Fuel quantity Ensure adequate for flight plus reserve Cowl flaps Open to facilitate inspection and ensure cooling after engine start Master switch Turn off to save battery Ignition switches should be off to prevent inadvertent start during inspection of propeller Mixture controls should be in idle cut off position again to prevent inadvertent engine start Trim indicators Set to neutral so that tabs may be checked for alignment Flaps Extend and retract to check operation This should be done before engine start so that you can hear any noise which might indicate binding Control locks Unlock and check control motion Fasten seat belts snugly on empty seats
17. 417 1 252 1 9 110 0 209 75 Manual Electric Trim Servo X 1C345 4 321 2 3 196 0 451 780 X__ Cable Assembly 29 106 6 53 75 Reading Light 2 X__ Grimes 10 0154 1 25 Ibs each 0 5 149 3 75 75 Reading Light 2 Grimes 10 0154 1 25 Ibs each 0 5 115 0 58 TC A7SO REPORT VB 424 PAGE 4 22 ISSUED March 10 1972 MODEL PA 34 200 REVISED August 2 1972 Item Item J Autopilots Optional Equipment Autocontrol III X Roll Servo 1C363 1 298R Console 1C338 Attitude Gyro 52D66 Directional Gyro 52054 Cable Assys M TOTAL Altimatic IIIB 1 Roll Servo 1C363 1 208R Pitch Servo 1C508 1 298P Trim Servo 1C345 1 298 Trim Sensor 1C656 298 Relay Box 14526 Console 1C5 9 2 Amplifier 1C515 1 Altitude Selector 10391 2 Altitude Gyro 52D67 Directional Gyro 52D54 Cable Assys TOTAL Radio Coupler 1C388P Glide Slope Coupler 1C493 ISSUED March 10 1972 REVISED July 7 1972 Weight Lbs Arm Aft Datum 121 8 65 0 64 9 63 8 95 5 81 1 121 8 117 6 196 0 135 1 57 8 65 0 126 2 56 4 63 8 106 6 106 7 64 4 60 1 Moment 305 149 204 67 803 SENECA Cert Basis TC A7SO TC A7SO TC A7SO TC A7SO TC A7SO TC A7SO TC A7SO TC A7SO TC A7SO TC A7SO TC A7SO TC 75 TC A7SO TC A7SO A7SO TC A7SO 75 75 REPORT VB 424 PAGE 4 23 MODEL PA 34 200 SENECA Weight Arm Aft Cert Item Item Lbs Dat
18. Vacuum regulators not adjusted correctly The pressure even though set correctly can read lower under two conditions 1 Very high altitude above 12 000 feet 2 Low engine RPM usually on approach or during training maneuvers This is normal and should not be considered a malfunction 10 The shape of the wing fuel tanks is such that in certain maneuvers the fuel may move away from the tank outlet If the outlet is uncovered the fuel flow will be interrupted and a temporary loss of power may result Pilots can prevent inadvertent uncovering of the outlet by avoiding maneuvers which could result in uncovering the outlet Extreme running turning takeoffs should be avoided as fuel flow interruption may occur Prolonged slips or skids which result in excess of 2000 feet of altitude loss or other radical or extreme maneuvers which could cause uncovering of the fuel outlet must be avoided as fuel flow interruption may occur when tank being used is not full 11 The rudder pedals are suspended from a torque tube which extends across the fuselage The pilot should become familiar with the proper positioning of his feet on the rudder pedals so as to avoid interference with the torque tube when moving the rudder pedals or operating the toe brakes 12 Anti collision lights should not be operating when flying through overcast and clouds since reflected light can produce spacial disorientation Do not operate strobe lights when taxiing in the vici
19. 1 6 Ibs each X _ Lycoming 75247 3 2 55 7 178 TC 1E10 Two Alternators 12V 60 Amp x Prestolite ALY 6408 13 Ibs each 26 0 35 0 910 TC A7SO Two Starters 12V Prestolite Model MZ 4206 Left Wing 18 0 33 2 598 TC 1E10 Prestolite Model MZ 4216 X Right Wing 18 0 33 2 598 TC 1E10 Two Oil Coolers PAC Dwg 96809 A Stewart Warner Model 10557 A 5 2 64 2 334 TC A7SO REPORT VB 424 PAGE 4 14 ISSUED March 10 1972 MODEL PA 34 200 SENECA Weight Arm Aft Cert Item Item Lbs Datum Moment Basis C Landing Gear and Brakes Two Main Wheel Brake Assemblies 40 90 Wheel Assembly Cleveland TSO C26a 30 65 Brake Assembly Cleveland TSO C26a Two Main 8 Ply Rating Tires 6 00 6 Type III with Regular Tubes 18 8 bs each 37 6 109 8 4128 TSO C62 One Nose Wheel Assembly 38501 Wheel Assembly Cleveland TSO C26a One 6 Ply Rating Tire 6 00 6 Type III Regular Tube 12 5 255 319 TSO C62 One Nose Wheel Assembly 40 76B Wheel Assembly Cleveland TSO C26a One 6 Ply Rating Tire __ 6 00 6 Type III Regular Tube 12 8 tE 25 5 326 TSO C62 Static position shown retracted position is at sta 5 6 ISSUED March 10 1972 REPORT VB 424 PAGE 4 15 REVISED April 1 1977 MODEL PA 34 200 SENECA Weight Arm Aft Cert Item Item Lbs Datum Moment Basis D Electrical Equipment One Battery 12V 35 Amp Hour X Rebat R 35 27 0 7 8 211 TC A7SO X__ Power Relay 63880 0 1 2 7 8 9 TC A730 Stall Warning Detector Safe x Flight In
20. AND WINDS PAVED LEVEL DRY RUNWAY TOUCHDOWN SPEED 67 MPH 40 S ON ROLLOUT FULL BRAKING 1100 GROUND RUN DISTANCE FT NW BEEHERENEENH LL LRL LL E LLL M 8 20 48 66 30 4008 3600 3200 8 0 20 30 TEMPERATURE F WEIGHT LBS HEADWIND MPH NOTE The above distances may be reduced by approximately 25 when the aircraft is equipped with optional Heavy Duty Wheels Brakes and Tires Reference Aircraft Equipment List in Weight and Balance Section of this Manual Example Temp 70 F Wt 3600 Ibs Ground Run 615 ft Press Alt 2000 ft Hd wind 5 MPH PERFORMANCE CHARTS REVISED April 1 1977 8 13 SENECA LANDING DISTANCE OVER 50 FT OBSTACLE AT VARIOUS ALTITUDES TEMPERATURES WEIGHTS AND WINDS TOUCH DOWN SPEED 67 MPH PAVED LEVEL DRY RUNWAY POWER OFF APPROACH SPEED 87 MPH FLAP SETTING 40 RETRACT FLAPS OM ROLLOUT FULL BRAKING SHORT FIELD EFFORT ILLLLLLLLLLLI Bun EN H HEH AA tt VAAL A DI con 222 LANDING DISTANCE FEET N 20 40 50 80 4900 3600 3200 6 10 20 3 TEMPERATURE F WEIGHT LBS HEADWIND MPH NOTE The above distances may be reduced by approximately 12 when the aircraft is equipped with optional Heavy Duty Wheels Brakes and Tires Reference Aircraft Equipment List in Weight and Balance Section of this Manual Example Temp 70 F Wt 3600 Ibs Landing Dist 1240 ft Press
21. Alt 4000 ft Hd wind 5 MPH PERFORMANCE CHARTS 8 14 REVISED April 1 1977 SENECA THIS PAGE INTENTIONALLY LEFT BLANK PERFORMANCE CHARTS ISSUED March 10 1972 8 15 91 8 2161 OT Ye 13415651 SLUVHD Power Setting Table Lycoming Model 10 360 C Series 200 HP Engine Press Std Alt 110 HP 55 Rated 130 HP 65 Rated 150 HP 75 Rated Press Alt Temp RPM AND MAN PRESS RPM AND MAN PRESS RPM AND MAN PRESS Alt Feet F 2100 2400 2100 2400 2400 Feet SL 59 22 9 20 4 25 9 22 9 25 5 SL 1 000 55 22 1 20 2 25 6 22 7 25 2 1 000 2 000 52 22 4 20 0 25 4 22 9 25 0 2 000 3 000 48 22 2 19 8 25 1 22 2 24 7 3 000 4 000 45 21 9 19 5 24 8 22 0 24 4 4 000 5 000 41 21 7 19 3 FT 21 7 FT 5 000 6 000 38 21 4 19 1 21 5 6 000 7 000 34 21 2 18 9 21 3 7 000 8 000 31 21 0 18 7 21 0 8 000 9 000 2 FT 18 5 9 000 10 000 23 18 3 10 000 11 000 19 18 1 11 000 12 000 16 78 12 000 13 000 12 gt 17 6 13 000 14 000 9 14 000 To maintain constant power correct manifold pressure approximately 0 16 Hg for each 10 F variation in inlet air temperature from standard altitude temperature Add manifold pressure for air temperatures above standard subtract for temperatures below standard VOuNAS HANDLING AND SERVICING HANDLING AND SERVICING 9 1 TOWING onessssossseccosscseonesessnsseronvorscsnesecnssenncnasnsssennnsccann
22. COMPUTED WEIGHT AND BALANCE BASIC EMPTY WEIGHT 2862 8 TOTAL MOMENT 241794 1 NEW C G 84 46 USEFUL LOAD 139 2 N887SP WEIGHT AND BALANCE DATE April 1 2005 _ 17018 AIC PIPER PA 34 200 S N 34 7350124 REG N887SP TACH 4138 9 THIS FORM SUPERSEDES WEIGHT AND BALANCE DATED 12 17 01 ITEM WEIGHT ARM MOMENT LBS IN IN LBS PREVIOUS WEIGHT AND BALANCE 2871 80 84 30 242092 90 REMOVED Left MZ 4216 Starter 18 00 33 20 597 60 INSTALLED Left MZ 6222 Starter 9 00 33 20 298 80 TOTAL 2862 80 84 46 241794 10 NEW EMPTY WEIGHT 2862 80 LBS NEW EMPTY WEIGHT C G 8446 MAX GROSS WEIGHT 4200 00 LBS Take Off USEFUL LOAD 1337 20 LBS SYREK MEE AVIATION 2 a New Page 1 United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number Garmin Intemational Inc 1200 East 151stStreet Olathe KS 66062 This certificate issued to certifies that the change in the type design for the following product with the limitations and conditions therefor as specified hereon meets the airworthiness requirements of Part 23 of the Avision Regulations 3A13 Original Product Type Certificate Number Make Piper Model PA 34 Description of Type Design Change Installation of a Garmin GNS 430 530 VHF NAV COMM GPS System and associated GI 106A Course Deviation Indicators CDI GTX 327 ATCRBS Transponder and GMA 340 Au
23. Combustion Heater prohibits the use of Windshield Heater due to excessive compass error c Operation of the combustion heater above 20 000 feet is not approved 2 PROCEDURES a Normal Operation Refer to Pilot s Operating Manual for normal operation b Emergency Operation In the event of an overheat condition the fuel air and ignition to the heater is automatically cut off Do not attempt 10 restart the heater until it has been inspected and the cause of the malfunction has been determined and corrected 3 PERFORMANCE The airplane performance remains unchanged FAA APPROVED December 20 1972 REPORT VB 423 PAGE 3 29 MODEL PA 34 200 SENECA ee THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 423 PAGE 3 30 FAA APPROVED December 20 1972 MODEL PA 34 200 WEIGHT AND BALANCE Installation Center GARMIN GNS 530 VHF Communications Transceiver VOR ILS Receiver GPS Receiver Repair Station Tomlinson Avienies Ine PH 941 936 6969 Name Ft Myers 33907 Address FAA APPROVED FLIGHT MANUAL SUPPLEMENT GARMIN GNS 530 VHF COMMUNICATIONS TRANSCEIVER VOR ILS RECEIVER GPS RECEIVER AIRCRAFT MAKE OC AIRCRAFT MODEL 22 722222 AIRCRAFT SERIAL 7 This document must be carried the aircraft at all times It describes the operating procedures for the GARMIN GNS 530 navigation system when it has been installed in accordance with GARMIN Installation 1
24. PA 34 220T PA 42 PA 42 720 and PA 42 1000 airplanes all serial numbers certificated in any category NOTE 1 This AD applies to each airplane identified in the preceding applicability provision regardless of whether it has been modified altered or repaired in the area subject to the requirements of this AD For airplanes that have been modified altered or repaired so that the performance of the requirements of this AD is affected the owner operator must request approval for an alternative method of compliance in accordance with paragraph d of this AD The request should include an assessment of the effect of the modification alteration or repair on the unsafe condition addressed by this AD and if the unsafe condition has been eliminated the request should include specific proposed actions to address it Compliance Required as follows unless already accomplished 1 For all affected airplanes except for Models PA 31P PA 31T PA 31T1 PA 31T2 and PA 31P 350 airplanes Within 30 days after March 13 1997 the effective date of AD 98 04 27 2 For all Models PA 31P PA 31T PA 31T1 PA 31T2 and PA 31P 350 airplanes Within the next 30 days after the effective date of this AD To minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions accomplish the following a At the applicable compliance t
25. REGISTRATION NOT TRANSFERABLE uu UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION FEDERAL AYIATION ADMINISTRATION CERTIFICATE OF AIRCRAFT REGISTRATION NATIONALITY AND REGISTRATION marks IN This certificate must be the air craft when operated ICAO Aircraft Address Code 53034564 This certificate is issued for registra tion purposes only and is not certif icate of title The Federal Avie tlon Administration does not determine rights of ownership between private persons CYLINDER SHOP ING 14351 NW 41ST AVE LOCKA FL 33054 2328 15 certified thet the above described aircraft has been entered on the register of the Federal Aviation Administration United States of America in accordance with the Convention on International Civil Aviation dated December 7 1544 end wilh Title 49 United States Code end regulations issued thereunder E OF ISSUE U S Department Transportation Federal Aviation Administration ITED STATES OF AMERICA DEPARTMENT OF TRANSPORT ATION FEDERAL AVIATION STANDARD AIRWORTHINESS CERTIFICATE 3 AIRCRAFT SERIAL NUMBER 34 7350124 NORMAL 2 MANUFACTURER AND MODEL NATIONALITY AND AEGISTRATION MARKS N8875P PIPER PA34 200 the fees that as or the date ol suang
26. by making it impossible to feather any time the engine speed is less than 800 RPM For this reason if an engine is being feathered to save it the pilot must be sure to move the control to feather position before the engine speed drops below 800 RPM LANDING GEAR SYSTEM To increase cruise speed climb and other performance the Seneca is equipped with a retractable tricycle landing gear which is hydraulically operated Rugged gear construction and a heavy duty braking system permit operation from a wide variety of landing areas Hydraulic pressure for gear operation is furnished by an electrically powered reversible pump controlled by a two position selector switch located on the instrument panel to the left of th control quadrant The gear selector switch which has a wheel shaped knob must be pulled out before it is moved to the UP or DOWN position When hydraulic pressure is exerted in one direction the gear is retracted when it is exerted in the other direction the gear is extended If the landing gear is in transit and the hydraulic pump is running it is inadvisable to move the gear selector switch to the opposite direction before it has reached its travel limit because this sudden reversal may be harmful to the electric pump Retraction or extension normally takes SIX to Seven seconds AIRPLANE AND SYSTEMS 2 4 ISSUED March 10 1972 SENECA Mounted on top of the engine is the ported fuel flow divider with four nozzle lines route
27. however for engine starting with external power Two solid state voltage regulators are provided to maintain effective load sharing while regulating the electrical system bus voltage to 14 0 volts In each alternator circuit an overvoltage relay is provided to prevent electrical damage to electrical and avionic equipment by taking the alternator off the line if its output goes above 14 0 volts When this occurs a red light located on the left side switch panel illuminates to indicate that the overvoltage relay has tripped This is the only finction of this light it does not necessarily come on for other failures of the alternator system Voltage regulators and overvoltage relays are mounted on the forward side of the bulkhead at station 49 5 Circuit breakers are provided to protect equipment and the electical system These are located on the lower right hand instrument panel and there is room for additional circuit breakers if extra electrical equipment is installed A circuit breaker may trip automatically in case of equipment malfunctions or a sudden surge of current The pilot can then reset it by pushing it in preferably after a few minutes cooling period However he cannot pull out a circuit breaker manually Most of the electrical switches including the master switch and those for the magnetos fuel pumps starter alternators lights and pitot heat are conveniently located on the switch panel to the left of the pilot A press switch ne
28. switch insuring mixture in the idle cut off position turning on the right auxiliary fue pump opening the air intake lever and placing the three position switch in the HEATER position The combustion cabin heater uses gasoline from the fuel line between the engine driven pump and injector on the right engine Heater fuel consumption is one half gallon per hour Fuel used for heater operation should be considered for Flight Planning Purposes If the right fuel selector is in the off position the heater is inoperative In case of right engine failure the heater can be operated by leaving the fuel selector on insuring that the mixture control is in idle cut off position while operating the auxiliary fuel pump Before the heater is operated under these conditions determine that there are no fuel leaks between the tank and the engine Located in the heater is a heat limit overheat switch which acts as a safety device to render the heater system inoperative if a malfunction should occur Operation of this switch results in illumination of the overheat light located on the heater control console The heat limit switch is located in the forward outboard end of the heater vent jacket with a red reset button on the heater shroud and can be reached through the bulkhead access panel into the aft fuselage To prevent activation of the overheat limit switch upon normal heater shutdown during ground operation turn the switch to FAN for two minutes w
29. 2 6 6 Walk Around 00000 6 2 Before Starting 6 3 Starting 6 3 HOS a Mere 6 3 Flooded STET 6 4 Starting Engines With Aid of External Electric Power 6 4 Taxi 6 5 Pretake Off 6 5 Take OT ae euere 6 7 Door Open on Take Off eese eeeeeeee esee eene tenete eene 6 8 _____ __ _____ ________ 6 8 Normal Cruise PER NE tales 6 8 __ __ _ _____ __ BE 6 9 Approach and Landing 2 6 10 Post Landing RR 6 11 Shul POETE TNT 6 11 Airspeed Data 0 2 6 12 Rough Air 222 6 12 Vmc Minimum Single Engine Control Speed 6 12 Operation In Known Icing Conditions rennen eee 6 13 Emergency Procedures 6 14 Piper Automatic Locator sese nennen 6 14 BLANK PAGE SENECA
30. A7SO ______ Cable Nav Antenna 1 1 172 0 189 75 41 VHF Comm Antenna 0 3 190 6 57 TC A7SO Cable 1 VHF Comm Antenna 0 5 122 0 61 TC A7SO _____ 2 VHF Comm Antenna 0 3 225 2 68 TC A7SO Cable 2 VHF Comm Antenna 0 6 139 0 83 TC A7SO Anti Static Kit 1 VHF Comm Antenna 1 0 190 6 191 TC A7SO ro Cable 1 VHF Comm Antenna 0 5 122 0 6 TC A7SO CN 2 VHF Comm Antenna 1 0 225 2 225 TC A7SO a Cable 2 VHF Comm Antenna 0 6 139 0 83 A7SO Low Frequency Antenna 0 6 160 0 96 TC A7SO EM GN Static Wicks 75 2 Narco Comm 10 3 9 62 4 243 A7SO Narco Comm 11 3 6 62 4 225 TC A7SO Narco Dual Comm 11 7 1 62 4 443 TC A7SO Narco Nav 10 1 9 63 6 120 75 _____ Nav 11 2 8 63 6 178 75 Narco 12 3 4 63 6 214 TC A7SO Narco Dual Nav 11 5 6 63 6 356 TC A7SO Narco Nav 14 3 0 62 4 187 TC A7SO REPORT VB 424 PAGE 4 24 ISSUED March 10 1972 MODEL PA 34 200 REVISED November 16 1972 Item Item K Radio Equipment Optional Equipment cont Bendix ADF T 12 C or D Receiver Model 201F Receiver Model 210 C or D Audio Amplifier 102A Servo Indicator 551A Loop Antenna 2321E Cable Interconnecting Sense Antenna and Cable King KX 175 VHF Transceiver King KN 73 Glide Slope King KN 77 VOR LOC Conv King KNI 520 VOR ILS Indicator HEEL King KX 175 VHF Transceiver 2nd King
31. Air Temperature Gauge Piper 99470 0 2 0 2 77 6 16 TC A7SO Clock AN5743 L2 0 4 62 9 25 TC A7SO Turn and Slip Indicator Piper PS50030 2 or 3 2 6 64 7 168 TSO C3A Type II Exhaust Gas Temperature Piper 99027 2 0 7 60 4 42 TC A7SO ISSUED March 10 7972 REPORT VB 424 PAGE 4 31 REVISED July 10 1972 MODEL PA 34 200 SENECA Weight Arm Aft Cert Item Item Lbs Datum Moment Basis L Copilot s Advanced Instrumentation Optional Equipment cont Attitude Gyro Piper 99002 2 3 _____ 4 or 5 2 2 64 4 142 TSO C4c Directional Gyro Piper 99003 2 3 4 or 5 26 64 7 168 TSO C5c Tru Speed Indicator Piper 550049 6 8 6 66 8 40 TSO C2b Turn and Slip Indicator Piper PS50030 2 or 3 2 6 64 7 168 TSO C3a TT Type II Altimeter Piper PS50008 2 or 3 1 0 65 9 66 TSO C10b Indicator Rate of Climb Piper _ 99010 2 4 or 5 1 0 65 9 66 TSO C8b Indicator Rate of Climb Piper 99010 3 5 67 2 34 TSO C8b Clock AN5743 L2 4 62 9 25 TC A7SO REPORT VB 424 PAGE 4 32 ISSUED March 10 1972 MODEL 34 200 REVISED July 10 1972 SENECA Weight Arm Aft Cert Item Item Lbs Datum Moment Basis M Miscellaneous Optional Equipment x Assist Step _ Piper Dwg 68014 0 1 5 147 5 221 TC A7SO Toe Brakes Right X Piper Dwg 95391 0 5 0 54 6 273 TC A7SO Jumpseat Piper Dwg 69068 15 7 8 122 3 954 A7SO Jumpseat X___ Piper Dwg 69595 5 8 1 122 3 991 A7SO Seat Belt Jumpseat 5
32. CHECK A thorough check should be made before take off using a check list Before advancing the throttle to check the magnetos and the propeller action be sure that the engine is warm enough to accept the power if it is a cold day If there is no hesitation in engine action when the throttle is advanced the engine is warm enough 1 Parking brake on 2 Engine run up Mixture controls forward Propeller controls forward Throttle controls forward to 1500 RPM Propeller controls Check the feather position by bringing the propeller controls fully back and then to the full forward position The RPM should drop to 1000 RPM in 3 seconds If more time is required the propeller dome pressure may be excessively low resulting in a danger of propeller overspeed or loss of feathering capability e Throttle controls forward to 2000 RPM f Propeller controls Exercise to check governor Retard contro until a 200 to 300 drop in RPM is indicated This should be done three times on the first flight of the day The governor can be checked by retarding the propeller control until a drop of 100 RPM to 200 RPM appears then advancing the throttle to get a slight increase in manifold pressure The propeller speed should stay the same when the throttle is advanced thus showing that the governor is governing g Propeller controls full forward h Alternate air controls on then off again There should be a drop in RPM when the control is pl
33. Cable 4 90 0 36 TC A7SO Audio Selector Panel _ Piper 99395 0 2 or 3 7 66 3 46 TC A7SO Microphone 5 75 0 38 750 Headset 5 65 0 33 A7SO 4 EU T Narco 64 0 40 9 Blind Encoder REPORT VB 424 PAGE 4 28 ISSUED March 10 1972 MODEL PA 34 200 REVISED August 2 1972 SENECA Weight Arm Aft Cert Item Item Lbs Datum Moment Basis K Radio Equipment Optional Equipment cont Piper Automatic Locator Transmitter 1 7 267 2 454 TC A7SO Antenna amp Coax 2 255 4 51 75 Shelf amp Access Hole 33 266 4 88 TC A7SO IFD Skyline 300 Panel Unit 1 7 65 4 7 Remote Unit 1 8 58 7 106 TC 75 Antenna J 52 5 5 75 Cable 41 53 6 5 A7SO ISSUED March 10 1972 REPORT VB 424 PAGE 4 29 MODEL PA 34 200 SENECA THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 424 PAGE 4 30 ISSUED March 10 1972 MODEL PA 34 200 SENECA Weight Arm Aft Cert Item Item Lbs Datum Moment Basis L Instruments Optional Equipment Suction Gauge Piper 96395 0 5 67 2 34 75 Vacuum Regulator Airborne Mech 133C3 2 7 Ibs each 1 4 70 2 98 TC A7SO Vacuum Filter Piper 66673 0 3 54 8 16 78 Indicator Rate of Climb Piper 99010 2 4 or 5 1 0 65 9 66 TSO C8b Indicator Rate of Climb Piper 99010 3 5 67 2 34 TSO 8 Attitude Gyro Piper 99002 2 3 4 or 5 22 64 4 142 TSO C4c Directional Gyro Piper 99003 2 3 4 or 5 2 6 64 7 168 TSO CSc
34. Do not engage autopilot if airplane is out of trim Maximum airspeed for autopilot operation is 207 MPH 180 KTS CAS During autopilot operation the pilot must be in his seat with the belt e Do not manually overrride autopilot to produce or prevent pitch attitude changes or to increase bank angle f If one engine becomes inoperative adjust rudder trim for single engine operation 2 PROCEDURES a Preflight 1 Manual Electric Trim a b c d e Aircraft Master Switch ON Trim Warning Light OUT Manual Trim Wheel freedom of movement CHECK Actuate Electric Trim Switch and obscene proper direction of movement of trim wheel CHECK Depress the test button next to the trim warning light Light should light and trim should not run If trim runs or if light does not illuminate pull trim disconnect switch and do not reset until problem has been corrected DO NOT ENGAGE AUTOPILOT WITH TRIM DISCONNECTED 2 Autopilot a b c d e Start engines Autopilot Master Switch ON Gyro Check Check attitude gyro for proper erection Set directional gyro if non slaving type Before takeoff Engage autopilot apply force to controls one axis at a time to determine if the autopilot can be overpowered Press HDG VOR APPR REV buttons one at a time place pitch command disc in center detent position and check respective lights on the Flight Controller for operation NOTE Automatic pitch trim w
35. External Power PEP allows the operator to use an external battery to crank engine without having to gain access to the aircraft battery The procedure is as follows l 2 4 0 4 Turn aircraft MASTER SWITCH to OFF Connect RED lead to PEP kit jumper cable to POSITIVE terminal of external 12 volt battery and BLACK lead to NEGATIVE terminal Insert plug of jumper cable into socket located on aircraft fuselage Turn aircraft MASTER SWTICH to ON and proceed with NORMAL engine starting technique After engine has been started turn MASTER SWITCH to OFF and remove jumper cable plug from aircrafl Turn aircraft MASTER SWTICH to ON and check alternator ammeter for indication of output DO NOT ATTEMPT FLIGHT IF THERE IS NO INDICATION OF ALTERNATOR OUTPUT OPERATING INSTRUCTIONS ISSUED March 10 1972 SENECA Following level off for cruise the electric fuel pumps should be checked for being off The cowl flaps should be closed or adjusted as necessary to maintain proper cylinder head temperatures and the airplane should be trimmed to fly hands off The pilot should monitor weather conditions while flying and should be alert to conditions which might lead to induction system icing Snow or freezing rain could result in icing of the air filter Since alternate air is controlled manually by the pilot not automatically it should be turned on any time icing may occur If the flight has been through rain in air that
36. Maintain aircraft in trim throughout all single engine operations Ball centered b Perform normal engine out emergency procedure c Re engage autopilot 4 An autopilot malfunction during climb cruise or descent either single or multi engine with a 3 second delay in the initiation of recovery could result in a 45 bank and a 600 foot altitude loss 5 An autopilot malfunction during approach operations either single or multi engine coupled or uncoupled with a second delay in the initiation of recovery could result in an 18 bank and a 60 foot altitude loss 3 PERFORMANCE The airplane performance remains unchanged FAA APPROVED March 10 1972 REPORT VB 423 PAGE 3 25 MODEL PA 34 200 SENECA f AUTOPILOT RELEASE Disengage the autopilot by operating trim switch on left side of pilot s control wheel Ascertain that servos have disengaged by free movement of controls b Normal Operation Refer to Piper AltiMatic V FD 1 or Piper AltiMatic V Information Manual c Emergency Operation Autopilot 1 In the event a malfunction in the autopilot performance is detected the pilot must immediately disengage the autopilot by momentarily operating the trim switch on the left side of the pilot s control wheel 2 Maximum altitude loss during malfunction tests in the following flight configuration a Cruise Climb 170 Feet b Descent 250 Feet c ILS approach Twin Engine 90 Feet d ILS approach Si
37. ROUGH AIR OR MANEUVERING SPEEDS 2743 LB GW 133 MPH 4200 LB GW 146 MPH 4 GEAR DOWN MPH GEAR UP 125 MPH MAX EXTENDED 150 MPH MAX Near emergency gear release EMERGENCY GEAR EXTENSION PULL TO RELEASE SEE BEFORE RE ENGAGEMENT Near gear selector switch GEAR UP 125 MPH MAX DOWN 150 MPH MAX Adjacent to upper door latch Front and rear doors ENGAGE LATCH BEFORE FLIGHT In view of pilot WARNING TURN OFF STROBE LIGHTS WHEN TAXIING IN VICINITY OF OTHER AIRCRAFT OR DURING THROUGH CLOUD FOG OR HAZE On the inside of forward baggage compartment door MAXIMUM BAGGAGE THIS COMPARTMENT 100 LBS SEE THE LIMITATIONS SECTION OF THE AIRPLANE FLIGHT MANUAL On aft baggage closeout MAXIMUM BAGGAGE THIS COMPARTMENT 100 LBS NO HEAVY OBJECTS ON HAT SHELF REPORT VB 423 PAGE 3 4 FAA APPROVED March 10 1972 MODEL PA 34 200 REVISED April 1 1977 SENECA On instrument panel FAA APPROVED March 10 1972 REVISED May 30 1975 SINGLE ENGINE STALLS NOT RECOMMENDED CAN CAUSE 500 FT LOSS OF ALTITUDE AND 15 PITCH ANGLE On instrument panei TAKEOFF CHECKLIST Fuel Selectors On Electric Fue Pumps On Alternators On Engine Gauges Checked Mixtures Set Propellers Set Alt Air Off Cowl Flaps Set Seat Backs Erect Flaps Set Trim Set Stab amp Rudder Fasten Belts Harness Controls Free Full Travel Doors Latched
38. The FAN position will operate the ventilation blower only and may be used for cabin ventilation or windshield defogging on the ground when heat is not desired The defroster contro lever for the standard muff heater system must be in the HI position in order to energize the defroster blower any time defrosting or defogging is desired with or without heat Optional Equipment AIRPLANE AND SYSTEMS 2 20 REVISED December 20 1972 SENECA For cabin heat the air intake lever located on the heater control console must be partially or fully open and the three position switch set to HEATER This will start fuel flow and ignite the burner simultaneously With instant starting and no need for priming heat should be felt within a few seconds Two safety switches which are installed and activated by the intake valve located aft of the Janitrol heater unit are wired to prevent both fan and heater operation unless the air intake lever is moved off the closed position Regulating the combustion cabin heat and airflow is accomplished by adjusting levers on the heater control console between the pilot s and copilot s seats The right hand lever regulates the air intake valve The left hand lever regulates cabin temperature Cabin temperature and air circulation can be maintained by using various combinations of lever settings to suit individual desires Heat may be supplied to warm the cabin before starting engines by turning on the master
39. adjacent to the alternator switches on the switch panel illuminate to warn of the tripped condition gt The alternator switch must be OFF 10 use the press to test feature of the overvoltage trip lights P FAA APPROVED March 10 1972 REPORT VB 423 PAGE 3 7 MODEL PA 34 200 SENECA 2 ALTERNATOR SYSTEM OPERATION Both alternator switches should be ON for normal operation A preflight check should assure operation of the overvoltage lights and that both ammeters show approximately equal outputs when both engines are at 1500 RPM or more Alternator outputs will vary with the electrical equipment in use and the state of charge of the battery Alternator outputs should not exceed 60 amperes each except during engine cranking 3 CIRCUIT BREAKERS All circuit breakers are grouped in the lower right corner of instrument panel To reset the circuit breakers push in on the reset button 4 FUEL MANAGEMENT a Normal Operation Each engine is normally supplied with fuel from the two interconnected tanks on the same side of the airplane These two interconnected tanks are considered a single tank for tank selection purposes 1 Take off and landing a Fuel selectors in ON position b Electric fuel pumps ON 2 Cruising a Fuel selectors in ON position b Electric fuel pumps OFF b Crossfeed Operation and Single Engine Operation A crossfeed is provided to increase range during single engine op
40. airplane equipment list are installed in the proper location in the airplane Remove excessive dirt grease moisture foreign items such as rags and tools from the airplane before weighing Defuel airplane Then open all fuel drains until all remaining fuel is drained Operate each engine until all undrainable fuel is used and engine stops Drain all oil from the engines by means of the oil drain with the airplane in ground attitude This will leave the undrainable oil still in the system Engine oil temperature should be in the normal operating range before draining Place pilot and copilot seats in fourth 4th notch aft of forward position Put flaps in the fully retracted position and all control surfaces in the neutral position Tow bar should be in the proper location and all entrance and baggage doors closed Weigh the airplane inside a closed building to prevent errors in scale readings due to wind 2 LEVELING a With airplane on scales block main gear oleo pistons in the fully extended position b Level airplane see diagram deflating nose wheel tire to center bubble on level ISSUED March 10 1972 REPORT VB 424 PAGE 4 3 MODEL PA 34 200 SENECA 3 WEIGHING AIRPLANE EMPTY WEIGHT a With the airplane level and brakes released record the weight shown on each scale Deduct the tare if any from each rending Scale Scale Position and Symbol Reading Weight Right Main M
41. allowable gross weight 4200 pounds See Weight and Balance Section for proper loading instructions I UNUSABLE FUEL The unusable fuel in this aircraft has been determined as 2 5 gallons in each wing in critical flight attitudes 2 5 gallons is the total per side each side having two interconnected tanks J USABLEFUEL The usable fuel in this aircraft has been determined as 46 5 gallons in each wing 46 5 gallons is the total per side each side having two interconnected tanks K PLACARDS In full view of the pilot THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS MARKINGS AND MANUALS NO ACROBATIC MANEUVERS INCLUDING SPINS APPROVED THIS AIRCRAFT APPROVED FOR V E R 1 F R DAY AND NIGHT NON ICING FLIGHT WHEN EQUIPPED IN ACCORDANCE WITH FAR 91 OR FAR 135 When properly equipped the above placard shall read THIS AIRCRAFT APPROVED FOR V F R DAY NIGHT AND ICING CONDITIONS WHEN EQUIPPED IN ACCORDANCE WITH FAR 91 OR FAR 135 FAA APPROVED March 10 1972 REPORT VB 423 PAGE 3 3 REVISED August 19 1975 MODEL PA 34 200 SENECA MAXIMUM TAKEOFF WEIGHT 4200 POUNDS MAXIMUM LANDING WEIGHT 4000 POUNDS ALL WEIGHT IN EXCESS OF 4000 POUNDS MUST CONSIST OF FUEL On instrument panel in full view of the pilot I DEMONSTRATED CROSSWIND COMPONENT 15 MPH 2 MINIMUM SINGLE ENGINE CONTROL SPEED 80 MPH 3
42. be moved by using the nose wheel steering bar provided or power equipment that will not damage or cause excess strain to the nose pear assembly The steering bar is stowed aft of the fifth and sixth seats CAUTION When towing with power equipment do not turn nose gear more than 20 degrees in either direction as this will result in damage to the nose gear and steering mechanism TAXIING Before attempting to taxi the airplane ground personnel should be checked out by a qualified pilot or other responsible person Engine starting and shut down procedures should be covered as well When it is ascertained that the propeller back blast and taxi areas are clear apply power to start the taxi roll and perform the following checks Taxi forward a few feet and apply brakes to determine their effectiveness Taxi with propeller set in low pitch high RPM setting While taxiing make slight turns to ascertain the effectiveness of steering Observe wing clearances when taxiing near b ildings or other stationary objects If possible station a guide outside the airplane to observe When taxiing on uneven ground look for holes and ruts Do not operate the engine at high RPM when running up or taxiing over ground containing loose stones gravel or any loose material that may cause damage to the propeller blades pos 0 PARKING When parking the airplane insure that it is sufficiently protected against adverse weather conditions and prese
43. circular motion A severe scratch or mar in plastic can be removed by using jeweler s rouge to rub out the scratch Smooth both sides and apply wax HANDLING AND SERVICING ISSUED March 10 1972 SENECA CLEANING HEADLINER SIDE PANELS AND SEATS a Clean headliner side panels and seats with a stiff bristle brush and vacuum where necessary mE b Soiled upholstery except leather may be cleaned by using an approved foam upholstery cleaner Carefully follow the manufacturer s instructions Avoid soaking or harsh rubbing CAUTION Solvent cleaners require adequate ventilation CLEANING CARPETS Use a small whisk broom or vacuum to remove dirt For soiled spots use a non inflammable dry cleaning fluid POWER PLANT INDUCTION AIR FILTER The induction air filters must be cleaned at least once very 50 hours Depending on the type of condition existing it may be necessary to clean the filters more often REMOVAL OF INDUCTION AIR FILTER a Open the outboard section of the cowling to gain access to the air filter box b Tum the three studs and remove the air filter box cover c the air filter from the filter box CLEANING INDUCTION AIR FILTER a Tap filter gently to remove dirt particles Do not use compressed air or cleaning solvents b Inspect filter If paper element is torn or ruptured or gasket is damaged the filter should be replaced The usable life of the filter should be restricted to one year or 500 hours whichever
44. comes first INSTALLATION OF INDUCTION AIR FILTER a Place filter in air box and install cover b Secure cover by turning studs Close cowl HANDLING AND SERVICING ISSUED March 10 1972 9 5 SENECA BRAKE SERVICE The brake system is filled with MIL H 5606 petroleum base hydraulic brake fluid This should be checked periodically or at every 100 hour inspection and replenished when necessary The brake reservoir is located to the rear of the front baggage compartment Remove the access panel marked Brake Reservoir Behind located at the top rear of the compartment Keep the fluid level at the level marked on the reservoir No adjustment of brake clearance is necessary Refer to Aircraft Service Manual for replacing brake linings LANDING GEAR SERVICE Two jack points are provided for jacking the aircraft for servicing One i is located outboard of each main landing gear and one just aft of the nose gear Landing gear oleos should be serviced according to instruction on the units The main oleo struts should be exposed three and one half inches and the nose oleo strut should be exposed two and one half inches in the static position Refer to Aircraft Service Manual for servicing oleo struts PROPELLER SERVICE The 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 i
45. course guidance to localizer glide slope course guidance will not occur 1t is the pilot s responsibility to ensure correct system navigation data is present on the external indicator before continuing a localizer based approach beyond the final approach fix Refer to the GNS 530 Pilot s Guide for detailed operating instructions 6 DISPLAY OF LIGHTNING STRIKE DATA For installations that interface the BFGoodrich WX 500 Stormscope and GNS 530 lightning strike data detected by the WX 500 will appear on the GNS 530 For detailed operating instructions regarding the interface of the GNS 530 with the WX 500 refer to WX 500 Pilot s Guide and the GNS 530 Pilot s Guide Addendum for the WX 500 Stormscope interface 7 DISPLAY OF TRAFFIC ADVISORY DATA For installations that interface the BFGoodrich SKYWATCH Traffic Advisory System TAS and the GNS 530 traffic data detected by the SKYWATCH will appear on the GNS 530 For detailed operating instructions regarding the interface of the GNS 530 with the SKYWATCH refer to the FAA Approved Flight Manual Supplement for the SKYWATCH the Pilot s Guide for the SKYWATCH and the GNS 530 Pilot s Guide Addendum for the SKYWATCH Traffic Advisory System interface MPA FSDO FAA APPROVED 12 DATE 7 200 PAGE 7 8 190 00181 04 Tomlinson Avionics Inc PH 941 036 6969 911 Danley Page Field Ft Myers FL 33907 Repair Station NO YN1D644K Aircraft Make Pu PER GARMIN GNS 530 V
46. engine rang and to enable the pilot to keep fuel weight balanced When crossfeed has been used during single engine cruise operation prior to landing the fuel selector should be positioned so that fuel is used from the same side as the operating engine The fuel selectors located on the funnel between the pilot and the copilot seats reflect the simplified fuel system Each lever has three positions OFF ON and CROSSFEED NOTE Do not operate with both fuel selectors on CROSSFEED Do not take off with a selector on CROSSFEED To permit the pilot to monitor the system fuel pressure fuel flow and fuel quantity gauges a single fuel gauge for the two tanks in each wing are mounted on the instrument panel Fuel quantity sender units one mounted in each fuel tank transmit electrically the total quantity of fuel in each pair of tanks gascolator fuel filter is located between the fuel selector valve and the electric fuel pump on each side Quick drains are provided for the fuel gascolators 2 for each fuel tank 4 and each crossfeed line 2 Two fuel tank drains are located under each wing crossfeed drains are located under the belly of the aircraft opposite the trailing edge of the right wing flap gascolator drains are on the inboard side of the engine nacelles forward and below the leading edge of the wing The vent system for the fuel tanks consists of a vent in each fuel a vent interconnect between the tanks in each wi
47. for two complete sets of flight instruments plus engine instruments and avionics with ideal grouping and no crowding Dual flight instruments are optional and a wide range of additional optional instruments and avionics permits an equipment selection uniquely suited to individual needs Flight instruments and avionics are grouped in the upper panel while engine instruments autopilot electrical instruments and circuit breakers are located on the lower panel Left engine and right engine instruments are conveniently separated by the control wheel shaft on the left side In spite of the large instrument panel over the nose visibility is good A combination of white post lights optional and red floodlights ensure easy reading of the instruments at night PITOT STATIC SYSTEMS Pitot total pressure for the airspeed indicator is sensed by the aluminum mast mounted under the left wing Static pressure for the altimeter vertical speed and airspeed indicators is sensed by two static pressure units one located on each side of the rear part of the fuselage Differences in static pressure caused by a slip of skid are balanced out by a connection of the two static sources inside the fuselage The pitot mast can be equipped with a heating element to eliminate problems from ice or heavy rain The static pressure sensors are not heated because experience indicates they are not likely to ice up An alternate static source contro valve is located below the in
48. not engage the autopilot If the autopilot is engaged hold the contro wheel firmly and disengage the autopilot e If an unusual roll response or uncommanded roll control movement is observed reduce the angle of attack Do not extend flaps when holding in icing conditions Operation with flaps extended can result in a reduced wing angle of attack with the possibility of ice forming on the upper surface further aft on the wing than normal possibly aft of the protected area If the flaps are extended do not retract them until the airframe is clear of ice Report these weather conditions to Air Traffic Control 5 Incorporating the AFM revisions as required by this AD may be performed by the owner operator holding at least a private pilot certificate as authorized by section 43 7 of the Federal Aviation Regulations 14 CFR 43 7 and must be entered into the aircraft records showing compliance with this AD in accordance with section 43 9 of the Federal Aviation Regulations 14 CFR 43 9 c Special flight permits may be issued in accordance with sections 21 197 and 21 199 of the Federal Aviation Regulations 14 CFR 21 197 and 21 199 to operate the airplane to a location where the requirements of this AD can be accomplished d An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager Small Airplane Directorate FAA 1201 Walnut suite 9
49. power setting in accordance with the Power Setting Table in this manual The mixture should be leaned in accordance with the recommendations for the 10 360 C engine in the Lycoming Operator s Manual which is provided with the aircraft For maximum service life cylinder head temperature should be maintained below 435 F during high performance cruise operation and below 400 F during economy cruise operation If cylinder head temperatures become too high during flight reduce them by enriching the mixture by opening cowl flaps by reducing power or by use of any combination of these methods OPERATING INSTRUCTIONS 6 8 ISSUED March 10 1972 SENECA BEFORE STARTING ENGINES PAD Seats adjusted Seat belts shoulder harness fastened Parking brake set Circuit breakers in Radios off Cowl flaps open Alternate air off Alternators on STARTING ENGINES 1 1 1 NOVA WN gt 1 2 8 Mixture controls idle cut off Throttle controls open 1 2 inch Propeller controls forward Master switch on Ignition switch on Electric fue pumps on Mixture controls Move to rich position until a fuel flow is indicated and stabilized then move to idle cut off Propeller clear Starter engage Mixture control Advance as engine starts Oil pressure Check to see that tbe oil pressure comes up within 30 seconds except in very cold weather when it may take somewh
50. prevent inadvertent extension of the gear Prior to pulling the emergency gear extension knob it is advisable to place the gear selector in the DOWN position to prevent the pump from trying to raise the gear If the emergency gear knob has been pulled out to lower the gear by gravity due to a gear system malfunction leave the control in its extended position until the airplane has been put on jacks to check the proper function of the landing gears Hydraulic and Electrical systems See Aircraft Service Manual for proper landing gear system check out procedures If the airplane 15 being used for training purposes pilot check out mission and the emergency gear extension has been pulled out it may be pushed in again when desired if there has not been any apparent malfunction of the landing gear system When the gear is fully up or fully down and the selector is in the corresponding position electrical limit switches stop the flow of current to the motor of the hydraulic pump Three green lights indicate that the landing gear is down and locked and a convex mirror on the left engine nacelle enables the pilot to confirm the position of the nose gear When the gear is not in the full up or the full down position a red warning light is illuminated on the instrument panel To add to the pilot s night vision comfort the gear lights are automatically dimmed when the navigation lights are turned on For this reason if the navigation lights are
51. reported Light Moderate and Severe conditions Therefore on the basis of flight tests the following guidelines should be observed 1 Flight into Severe icing is prohibited 2 Moderate icing conditions above 10 000 ft should be avoided whenever possible if moderate icing conditions are encountered above 10 000 ft a descent to a lower altitude should be initiated if practical 3 Light icing is approved at all altitudes Icing conditions of any kind should be avoided wherever possible since any minor malfunction which may occur is potentially more serious in icing conditions Continuous attention of the pilot is required to monitor the rate of ice buildup in order to effect the boot cycle at the optimum time Boots should be cycled when ice has built to between 1 4 and 1 2 inch thickness on the leading edge to assure proper ice removal Repeated boot cycles at less than 1 4 inch can cause a cavity to form under the ice and prevent ice removal boot cycles at thicknesses greater than 1 2 inch may also fail to remove ice Icing conditions can exist in any clouds when the temperature is below freezing therefore it is necessary to closely monitor outside air temperature when flying in clouds or precipitation Clouds which are dark and have sharply defined edges contain high water content and should be avoided whenever possible Freezing rain must always be avoided The following listing contains a few of the more highly recommended operat
52. the total load and the C G position of the airplane for take off If this point is not within the allowable envelope it will be necessary to offload fuel baggage or passengers and or to rearrange baggage and passengers to get the final point to fall within the envelope Fuel burn off and gear movement do not significantly affect the center of pravity SAMPLE PROBLEM A sample problem will demonstrate the use of the wei ght and balance plotter Assume a basic weight and C G location of 2615 pounds at 82 0 inches respectively We wish to carry a pilot and 5 passengers Two men weighing 180 and 200 pounds will occupy the front seats two women weighing 115 and 135 pounds will occupy the middle seats and two children weighing 80 and 100 pounds will ride in the rear Two 25 pound suitcases will be tied down in the front baggage compartment and two suitcases weighing 25 pounds and 20 pounds respectively will be carried in the rear compartment We wish to carry 60 gallons of fuel Will we be within the safe envelope REPORT VB 424 PAGE 4 10 ISSUED March 10 1972 MODEL PA 34 200 SENECA 8 Place a dot on the plotter grid at 2615 pounds and 82 0 inches to represent the basic airplane See illustration Slide the slotted plastic into position so that the dot is under the slot for the forward seats at zero weight Draw a line up the slot to 380 pound position 1 80 20 0 and put a dot Move the slotted plast
53. to enable the pilot quickly and conveniently to 1 Determine the total weight and C G position 2 Decide how to change his load if his first loading is not within the allowable envelope Heat can warp or ruin the plotter if it is left in the sunlight Replacement plotters may be purchased from Piper dealers and distributors When the airplane is delivered the basic weight and basic C G will be recorded on the computer These should be changed anytime the basic weight or C G location is changed The plotter enables the user to add weights and corresponding moments graphically The effect of adding or disposing of useful load can easily be seen The plotter does not cover the situation where cargo is loaded in locations other than on the seats or in the baggage compartments Brief instructions are given on the plotter itself To use it first plot a point on the grid to locate the basic weight and C G location This can be put On more or less permanently because it will not change until the airplane is modified Next position the zero weight end of one of the six slots over this point Using a pencil draw a line along the slot to the weight which will be carried in that location Then position the zero weight end of the next slot over the end of this line and draw another line representing the weight 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
54. unintentionally turned on in the daytime it is difficult to see the landing gear lights If the green lights are not observed after the landing gear switch is put in the DOWN position the first thing to check 15 the position of the switch for the navigation lights If one or two of the three green lights do not illuminate when the gear down position has been selected this could indicate that for each of the lights that is out any of the following conditions might exist a The gear is not locked down b The bulb is burned out c There is a malfunction in the indicating system The square indicating lights can be pulled out and moved around in order to check the bulbs A micro switch incorporated in the throttle quadrant activates a warning horn under the following conditions 1 Gear up and manifold pressure reduced below 14 inches on either one or both engines 2 Gear selector switch in the UP position when the airplane is on the ground AIRPLANE AND SYSTEMS 2 5 REVISED MARCH 23 1979 SENECA eee If the gear selector knob is placed in the UP position when the airplane is on the ground a safety switch located on the left main gear will prevent the hydraulic pump from actuating if the master switch should be turned on On take off when the oleo extends in excess of eight inches the safety switch closes to complete the circuit so that the hydraulic pump can raise the landing gear when the gear switch is moved to the
55. weight of all items to be loaded to the licensed pty weight 2 Use the loading graph to determine the moment of all items to be carried in the airplane 3 Add the moment of all items to be loaded to the licensed empty weight moment 4 Divide the total moment by the total weight to determine the C G location 5 By using the figures of Item 1 and Item 4 locate a point on the C G range and weight graph If the point falls within the C G envelope the loading meets the weight and balance requirements SAMPLE LOADING PROBLEM Normal Category Arm Aft Datum Moment Inches In Lbs The center of gravity C G of this sample loading problem 15 at inches aft of the datum line Locate this point on the range and weight graph Since this point falls within the weight C G envelope this loading meets the weight and balance requirements IT IS THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNER TO INSURE THAT THE AIRPLANE IS LOADED PROPERLY Optional Equipment ISSUED March 10 1972 REPORT VB 424 PAGE 4 7 REVISED May 30 1975 MODEL PA 34 200 SENECA RANGE AND WEIGHT INSTRUCTIONS 1 Add the weight of all items to be loaded to the licensed empty weight 2 Use the loading graph to determine the moment of all items to be carried in the airplane 3 Add the moment of all items to be loaded to the licensed empty weight moment 4 Divide the total moment by the total weight to determine the C G location
56. wing aft of the protected area Accumulation of ice the engine nacelles and propeller spinners farther than normally observed e Since the autopilot when installed and operating may mask tactile cues that indicate adverse changes in handling characteristics use of the autopilot is prohibited when any of the visual cues specified above exist or when unusual lateral trim requirements or autopilot trim warnings are encountered while the airplane is in icing conditions SENECA SECTION I LIMITATIONS The following limitations must be observed in the operation of this airplane A ENGINES Lycoming 10 360 C1E6 with fuel injector Lycoming P N LW 12586 This engine installs on L H side of aircraft Lycoming LIO 360 C1E6 with fuel injector Lycoming P N LW 12586 This engine installs on R H side of aircraft ENGINE LIMITS For all operation 2700 RPM 200 HP FUEL 100 130 Octane Aviation Gasoline Minimum PROPELLERS Hartzell HC C2YK 2 E C7666A 0 or Hartzell HC C2YK 2 EF FC7666A 0 Avoid continuous operation between 2200 2400 RPM Or Hartzell HC C2YK 2CG Y C7666A This model includes damper This model installs on L H side of aircraft Constant Speed Pitch Settings at 30 in station High 79 81 Low 13 5 Diameter Not over 76 inches Not under 74 inches No further reduction permitted Hartzell HC C2YK 2 LE JC7666A 0 or Hartzell HC C2YK 2 JLEF FJC7666A 0 Avoid continuous operation b
57. 0 prior to its use for navigation SECTION EMERGENCY PROCEDURES ABNORMAL PROCEDURES 1 If GARMIN GNS 530 navigation information is not available or invalid utilize remaining operational navigation equipment as required 2 If RAIM POSITION WARNING message is displayed the system will and no longer provide GPS based navigational guidance The crew should revert to the GNS 530 VOR ILS receiver or an alternate means of navigation other than the GNS 530 5 GPS Receiver 3 If RAIM IS NOT AVAILABLE message is displayed the enroute terminal or initial approach phase of flight continue to navigate using the GPS equipment or revert to an alternate means of navigation other than the GNS 53075 GPS receiver appropriate to the route and phase of flight When continuing to use GPS navigation position must be verified every 15 minutes using the GNS 530 s VOR ILS receiver or another IFR approved navigation system TAMPA FSDO FAA APPROVED DATE 07 200 PAGESOFS 190 00181 04 Tomlinson Avionics inc PH 941 936 6969 511 Danley Page rield Ft Myers FL 33907 Station YN1D644K Aircraft Make we E GARMIN GNS 530 VHF Communications Aircraft 7 V 3 22 Transceiver VOR ILS Receiver GPS Receiver Aircraft Serial Number X 7 35 22242 4 IS NOT AVAILABLE message is displayed while on the final approach segment GPS based navigation will continue for up
58. 00 SENECA 9 MANUAL EXTENSION OF LANDING GEAR Check the following before extending the gear manually Circuit breakers check b Master switch ON c Alternators check d Navigation lights OFF daytime To extend the gear reposition the clip covering the emergency disengage control downward clear of the knob and proceed as listed below Reduce power airspeed not to exceed 100 MPH Place Landing Gear Selector Switch in GEAR DOWN LOCKED position Pull emergency gear extension knob Check for 3 green lights Leave emergency gear extension knob out Sao WARNING If the emergency gear extension knob has been pulled out to lower the gear due to a gear system malfunction leave the control in its extended position until the airplane has been put on jacks to check the proper function of the landing gears hydraulic and electrical systems 10 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 on aircraft with serial numbers 34 72500046 and up the light will illuminate when the gear warning horn sounds The gear warning horn will sound at low throttle settings with the gear in the up and locked position 11 GEAR UP EMERGENCY LANDING Approach with power at a normal airspeed Leave flaps u
59. 00 Kansas City Missouri 64106 The request shall be forwarded through an appropriate FAA Maintenance Inspector who may add comments and then send it to the Manager Small Airplane Directorate NOTE 3 Information conceming the existence of approved alternative methods of compliance with this AD if any may be obtained from the Small Airplane Directorate All persons affected by this directive may examine information related to this AD at the FAA Central Region Office of the Regional Counsel Room 1558 601 E 12th Street Kansas City Missouri 64106 This amendment supersedes AD 98 04 27 Amendment 39 10339 g This amendment becomes effective on August 17 1999 FOR FURTHER INFORMATION CONTACT John P Dow Sr Aerospace Engineer FAA Small Airplane Directorate 1201 Walnut suite 900 Kansas City Missouri 64106 telephone 816 426 6932 facsimile 816 426 2169 are posted on the internet at http av info faa gov re R aj gt SENECA NOTE SINGLE ENGINE STALLS ARE NOT RECOMMENDED OPERATION IN KNOWN ICING CONDITIONS The Piper Seneca is approved for flight into known icing conditions when equipped with the complete Piper Ice Protection System Operating in icing conditions in excess of the Continuous Maximum and Intermittent Maximum as defined in FAR 25 Appendix C has been substantiated however there is no correlation between these conditions and forecast or
60. 10 1972 REPORT VB 423 PAGE 3 15 REVISED April 1 1977 MODEL PA 34 200 SENECA 13 VACUUM SYSTEM FAILURES a A malfunction of the vacuum system will become apparent as a reduction of indication on the gauge A red button annunciator will show in case of a feathered engine or vacuum pump failure b In the event of vacuum system malfunction vacuum lower than 4 5 inches of mercury 1 Increase engine RPM to 2700 2 Descend to an altitude if at which 4 5 inches of mercury vacuum can be maintained 3 Use Turn Indicator Electric to monitor the Direction Indicator and Attitude Indicator performance 14 ENGINE FIRE a Incase of engine fire in flight on the affected engine 1 Fuel Selector OFF 2 Throttle CLOSE 3 Propeller FEATHER 4 Mixture IDLE CUT OFF 5 Heater OFF In all cases of fire 6 Defroster OFF In all cases of fire T If terrain permits Land Immediately The possibility of an engine fire in flight is extremely remote The procedure given above is general and pilot judgement should be the deciding factor for action in such an emergency b In case of engine fire on the ground 1 If engine has not started a Mixture IDLE CUT OFF b Throttle OPEN c Turn engine with starter This is an attempt to pull the fire into the engine 2 If engine has already started and is running continue operating to try pulling the fire into the engine 3 In either case stated in 1
61. 1243 TC P920 Hartzell Model HC C2YK 2 LE JC7666A 0 Right Wing 55 0 22 6 1243 TC P920 Hartzell Model HC C2YK 2 7666 0 Right Wing 55 0 22 6 1243 TC P920 Hartzell Model HC C2YK 2CG F 7 C7666A Includes Damper Left Wing 62 9 23 2 1459 920 Hartzell Model HC C2YK 2CLG F J JC7666A Includes Damper Right Wing 62 9 23 2 1459 TC P920 Two Spinners x PAC Dwg 96083 0 Left Wing 4 0 22 9 92 TC A7SO Dwg 96083 1 Right Wing 4 0 22 9 92 75 Dwg 96083 4 Left Wing 4 2 22 9 96 A7SO Dwg 96083 5 Right Wing 4 2 22 9 96 TC A7SO Two Hydraulic Governors Hartzell Model F 6 18A Left Wing 5 5 33 6 185 TC P920 Hartzell Model F 6 18AL Right Wing 5 5 33 6 185 TC P920 ISSUED March 10 1972 REPORT VB 424 PAGE 4 13 REVISED September 19 1973 MODEL PA 34 200 SENECA Weight Arm Aft Cert Item Item Lbs Datum Moment Basis B Engine and Engine Accessories Fuel and Oil Systems Two Engines Lycoming Model IO 360 C1E6 with Fuel Injector Lycoming x P N LW 12586 Left Wing 306 43 2 13219 TC 1E10 Lycoming Model LIO 360 C1E6 with Fuel Injector Lycoming _ P N LW 12586 Right Wing 306 43 2 13219 TC 1E10 Two Fuel Pumps Electric Auxiliary X Airborne 1B5 6 3 2 lbs each 6 4 70 0 448 TC A7SO Two Induction Air Filters x Fram Model CA 144PL 5 Ibs each 1 0 61 7 62 TC A7SO Two Fuel Pumps Engine Driven AC Type JT
62. 1972 8 5 SENECA _ ACCELERATE STOP DISTANCE FOR VARIOUS ALTITUDES TEMPERATURES WEIGHTS AND WINDS FLAP SETTING 0 ACCELERATE TO 80 MPH AND THEN STOP FULL POWER BEFORE BRAKE RELEASE PAYED LEVEL DRY RUNWAY Lt PAT ADT Ta E LAT MM AL AL AE N NIT ANA AN E A 4 ACCELERATE STOP DISTANCE FEET ASEAN 2086 KD ac MEA SN M 1900 eL LLLI pu n SHE AA HHHH DAW LTA NA 0 2 0 00 4200 3800 3400 3080 0 10 20 30 TEMPERATURE F WEIGHT LBS HEADWIND MPH Example Temp 70 F Wh 3600 Ibs Accel Stop Dist 1650 ft Press Alt 2000 ft Hd wind 10 MPH PERFORMANCE CHARTS 8 6 ISSUED March 10 1972 761506 MULTI ENGINE CLIMB PERFORMANCE DENSITY ALTITUDE FEET N N Noe TENN RATE OF CLIMB FT MIN GEAR UP BEST RATE OF CLIMB SPEED MPH CAS Gear down best rate of climb speed is 92 MPH CAS at all altitudes Example Wt 4000 Ibs Rate of Climb 1100 ft min Den Alt 5000 ft Best R C Speed 103 MPH Gear Up PERFORMANCE CHARTS REVISED April 26 1974 SENECA 8 7 SENECA 8 8 DENSITY ALTITUDE FEET 761 506 SINGLE ENGINE CLIMB PERFORMANCE ONE ENGINE INOPERATIVE COWL FLAP OPEN OPERATING ENGINE ONLY GEAR AND FLAPS RETRACTED 9 BANK INTO OPERATIVE ENGINE POWER FULL THROTTLE MIXTU
63. 2 REPORT VB 424 PAGE 4 19 MODEL PA 34 200 SENECA Weight Arm Aft Cert Item Item Lbs Datum Moment Basis H Engine and Engine Accessories Fuel and Oil System Optional Equipment Two Vacuum Pumps Airbome Manufacturing Co Model 201CC Left Wing 4 5 54 5 245 TC A7SO Airborne Manufacturing Co X Model 202CW Right Wing 4 5 54 5 245 TC A7SO Two Oil Filters with Adapters AC OF5578770 3 3 bs each X Lycoming 75528 6 6 58 7 387 TC A7SO REPORT VB 424 PAGE 4 20 ISSUED March 10 1972 MODEL PA 34 200 SENECA Weight Arm Aft Cert Item Item Lbs Datum Moment Basis I Electrical Equipment Optional Equipment Auxiliary Power Receptacle x Piper 62355 8 2 6 7 8 20 TC A7SO External Power Cable Piper 62355 2 4 6 33 0 152 TC A7SO Cabin Speaker Quincy Spkr Co 8B 15052 X orOaktron Ind GEV 1937 0 8 97 5 78 TC A7SO Instrument Lights Post X GLAR BAN 5952 3RH CW 0 2 68 0 14 TC A7SO ISSUED March 10 1972 REPORT VB 424 PAGE 4 21 REVISED August 2 1972 MODEL PA 34 200 SENECA Weight Arm Aft Cert Item tem Lbs Datum Moment Basis I Electrical Equipment Optional Equipment Heated Pitot Head Piper 96392 0 0 4 100 0 40 TC A7SO Anti Collision Lights Whelen Engineering Co Piper Dwg 95267 Power Supply Model HD T3 No A413 with fin and wing i lights 3 0 127 5 383 TC A7SO Lights Wing Tip 2 0 15 Ibs each No A429 0 3 102 4 31 TC A7SO Cable Wing Lights 417 1 298 amp
64. 2 MODEL PA 34 200 SENECA Revision Revised Pages LOG OF REVISIONS Description and Revision Added Combustion Heater Added page Added page Corrected Combustion Heater Weight and Moment Added King KX 175 KN 73 KN 77 and KN 520 Installations Removed King KN 77 and KN 73 Installations Added King KN 65 DME Installation Added Serial No effectivity Added Propellers with Dampers Added 4 5 Spinners Added 9 Tachometer Removed Total Optional Equipment Added Fire Extinguishers Revised Misc Hardware Moment and Total Arm and Moment Added Ice Protection System Inst Added PAC Approval Form NOTE AIRCRAFT DELIVERED WITH MANUALS PRIOR TO THIS REVISION DO NOT REQUIRE THIS REVIS ION Revised fuel capacity Sample Loading Problem Revised Type Tube Cert Basis Added Heavy Duty Wheels Brakes and Tires Approved Date Dec 21 1972 2 44 Dec 21 1972 25 1973 Sept 19 1973 April 26 1974 due di Oct 14 1974 REPORT VB 424 PAGE 4 iv MODEL PA 34 200 ISSUED March 10 1972 REVISED April 1 1977 SENECA LOG OF REVISIONS cont Approved Revised Description and Revision Date Revision Pages Revised general weight and balance March 23 1979 introduction Hap 2 ZIA Tf Added Electrodelta voltage regulator November 30 1987 LM dp REPORT VB 424 PAGE 4 v ISSUED MARCH 23 1979 MOD
65. 3 9 TC A7SO Valve Free Fall Piper Dwg 67522 2 0 3 43 3 13 TC A7SO X Valve Check MS24593 4 0 05 42 4 2 TC A7SO REPORT VB 424 PAGE 4 18 ISSUED March 10 1972 MODEL PA 34 200 SENECA Weight Arm Aft Cert Item Item Lbs Datum Moment Basis G Miscellaneous Forward Seat Belts 2 X _ PS50039 4 2 75 Ibs each 1 5 86 9 130 TSO C22 X Center Seat Belts 2 PS50039 4 3 70 lbs each 1 4 123 0 172 TSO C22 x Rear Seat Belts 2 75 lbs each PS50039 4 4 1 5 163 0 245 TSO C22 Inertia Safety Belts Front Seats 2 PS50039 4 8 X 0 9 lbs each 1 8 120 1 216 75 Toe Brakes Left X Piper Dwg 95392 0 5 0 54 6 273 750 Rear Cabin Door X Piper Dwg 69373 5 16 5 152 2 2511 TC A7SO Cargo Door X _ Piper Dwg 68999 11 6 8 179 0 1217 TC A7SO Right Front Seat X Piper Dwg 99727 5 15 5 93 0 1442 TC A7SO Right Front Seat Piper Dwg 96806 5 15 6 92 7 1446 TC A7SO Center Seats 2 Piper Dwg 99730 0 amp 13 5 Ibs each 27 0 124 1 335 TC A7SO Center Seats 2 Piper Dwg 96827 2 3 11 9 Ibs each 23 8 124 4 2961 75 Rear Seats 2 14 5 lbs each 99730 2 amp 3 29 0 160 7 4660 TC A7SO Rear Seats 2 12 3 Ibs each A 96827 4 amp 5 24 6 161 1 3963 TC A7SO Flight Manual and Logs 2 6 95 247 TC A7SO Alternate Static Source Piper Dwg 95331 2 4 6 X 6 or 10 4 66 0 26 75 Calibrated Alternate Static Source YES NO Placard Required ISSUED March 10 1972 REVISED August 2 197
66. 413 Propellers and Propeller sy ahs oa ys O 4 13 B Engine and Engine Accessories Fuel and Oil 5 2 22 4 14 Landing v 4 15 Ds Electrical 4 16 SHOTS TE ELI 4 17 Hydraulic Equipment 4 18 G Miscellaneous noraine 8 20 OI ee 4 19 Engine and Engine Accessories Fuel and Oil System Optional Equipment 4 20 I Electrical Equipment Optional Equipment eese eee 4 21 J Autopilots Optional Equipment cccssssscssecsssscsssnesecessseresscessssseesensersssscesene 423 Radio Equipment Optional Equipment 4 24 L Instruments Optional Equipment 0ceccosesssessssccesesousorssetsoascatuarssonssonsorgeensenss 4 31 M Miscellaneous Optional Equipment 4 33 ISSUED March 10 1972 REPORT VB 424 PAGE 4 i MODEL PA 34 200 SENECA THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 424 PAGE 4 11 ISSUED March 10 1972 MODEL PA 34 200 SENECA LOG OF REVISIONS _ Approved Date Description and Revision Revi
67. 50039 4 5 1 4 123 0 172 TSO C22 Assist Straps and Coat Hooks 2 Piper Dwg 62353 5 _ 15 Ibs each 0 3 120 0 36 TC A7SO Inertia Safety Belts Center Seats 2 PS50039 4 6 0 7 Ibs each 1 4 133 9 187 TC 75 Inertia Safety Belts Rear Seats 2 PS50039 4 7 Std Fuselage 1 4 lbs each 2 8 182 7 512 75 Inertia Safety Belts Rear Seats 2 PSS0039 4 7 Fuselage w Cargo Door 1 4 and 1 6 lbs each 3 0 181 5 545 TC 75 x Lighter 200462 12V Universal 0 2 67 9 14 TC A7SO Fire Extinguisher Kiddie Compact VI with brackets Piper Dwg 65337 0 5 3 85 0 451 TC A7SO x Sun Visors 2 66991 2 1 05 lbs each 2 1 79 0 166 TC A7SO x Bar Piper Dwg 96331 0 4 4 168 0 739 TC A7SO ISSUED March 10 1972 REPORT VB 424 PAGE 4 33 REVISED August 2 1972 MODEL PA 34 200 SENECA Weight Arm Aft Cert Item Item Lbs Datum Moment Basis M Miscellaneous Optional Equipment cont Adjustable Front Seat Left Piper Dwg 99353 16 3 2 87 5 _ 280 75 x Adjustable Front Seat Left gt Piper Dwg 69568 2 3 1 90 8 281 75 Adjustable Front Seat Right Piper Dwg 99353 17 3 2 87 5 280 75 Adjustable Front Seat Right Piper Dwg 69568 3 2 4 90 8 218 75 Headrests Front 2 99255 3 1 0 Ibs each 2 0 99 5 199 TC A7SO Headrests Front 2 96806 17 1 0 Ibs each 2 2 99 5 219 7 Headrests Center 2 99255 3 1 0 Ibs each 2 0 132 1 264 TC A7SO Headrests Center 2 9
68. 6806 17 1 0 155 each 2 2 132 1 291 75 Headrests Rear 2 99255 3 1 0 Ibs each 2 0 169 7 339 TC A7SO Headrests Rear 2 96806 17 X 1 0 Ibs each 2 2 169 7 373 TC A7SO Windshield Heating Unit 2 6 59 6 155 TC A7SO Combustion Heater Piper Dwg 78424 46 8 193 3 9046 TSO C20 Weight and moment difference between standard and optional equipment REPORT VB 424 PAGE 4 34 ISSUED March 10 1972 MODEL PA 34 200 REVISED September 19 1973 SENECA Weight Arm Aft Cert Jtem Item Lbs Datum Moment Basis M Miscellaneous Optional Equipment cont Fire Extinguisher Scott Aviation with Brackets Piper Dwg 78621 2 5 0 58 6 293 TC A7SO Fire Extinguisher Kiddie amp Co with Brackets Piper Dwg 76167 0 53 71 0 376 75 Fire Extinguisher Scott Aviation with Brackets Piper Dwg 76167 2 5 0 71 0 355 TC A7SO Ice Protection System Instl includes Windshield Heating Unit Heated Pitot Head and Two Vacuum Pumps Piper Dwg 78642 56 3 87 9 4949 TC A7SO Heavy Duty Wheels Brakes and Tires Two Main Wheel Brake Assemblies Piper PS50035 14 Wheel Assembly TSO C26 30 83 Brake Assembly Cleveland TSO C26 Two Main 8 Ply Rating Tires Goodrich 6 00 x 6 Ribbed Type III with Tube 2 0 109 8 318 TSO C62 One Nose Wheel Assembly Piper PS50035 11 Wheel Assembly TSO C26 One 8 Ply Rating Tire Goodrich 6 00 x 6 Ribbed Type III with Tube 2 0 25 5 5 TSO C62 TOTAL OPTIONAL EQUIPMENT EXTERIOR FINISH Ba
69. 90 00181 02 Rev Rev later and FAA Form 337 dated 07 For aircraft with an FAA Approved Airplane Flight Manual this document serves as the FAA Approved Flight Manual Supplement for the GARMIN GNS 530 For aircraft that do not have an approved flight manual this document serves as the FAA Approved Supplemental Flight Manual for the GARMIN GNS 530 The Information contained herein supplements or supersedes the basic Airplane Flight Manual only in those areas listed herein For limitations procedures and performance information not contained in this document consult the basic Airplane Flight Manual np PAL 485 M prs Tor SF Sic e SP FL 5827 FAA APPROVED TAMPAFSDO _____ DEC 07200 PAGE1OFS 190 00181 04 Rev B E X Tomlinson Avionics Inc PH 941 936 6969 511 Danley Page rield Ft Myers FL 33907 Station NO 10044 GARMIN GNS 530 VHF Communications Transceiver VOR ILS Receiver GPS Receiver Aircraft Make _ Aircraft Model _ Table of Contents SEC PION aient NL M LE DS T PAGE A gd 3 EIMIPARIONS A 4 EMERGENCY 5 0 332 5 NORMA PROCEDUR S u 6 PRPO AMAN E A Ted B WEIGHT ANDIBALANGE sa 8 AIRPLANE amp SYSTEM DESCRIPTIONS nn diim seasons 8 FAA APPROVED
70. A 340438 QAF WO 010 30 BLNIOd TIY G1NIOd 30 DICH Aadv HOV3 HOF GONILLIJ 38Y3HD OMU 30 gt 3214439 OL UJHIYINDO NO GNOILODMLSNI Tid 3XV40 ONY Bund 26300 CO ONY UXTIOV JHA Gi 3 LVHL 1N3A109 ZAAL AUG Y HUM NY319 ONY REED ON vornd n 240328 3 709 Y HUM Saliva yo Gaunsound di 221434 260 ANO LON CO LUNG OL HILU 01 SNOLLONULSNI CIENTO THL FPO LON Og F OL UNS Ao LON IOUiNOO BOAO LONDQ CO DNI I3H it Honna 31 Y c 82153 HOLEYO Y 35010400 Hound LAW AG Boyde HIT Lad WON Lr 38 Y3UD SCOPI Won WO 38Y355 ION TIV A Corsar
71. A A 3 1 Propellers PC OOFB BA B E 3 D Instrument Markings Power eco 3 E Airspeed Limitations and Indicator Markings Calibrated Airspeed n 3 2 Flight Load Factors nennen nnne 3 2 G Maximum Weight X 3 3 A 3 3 I U nusable ae ee 3 3 J Usable Fuel ses AAN neue 3 3 Ke Pl cards nenn P E RE nen 3 3 L Vacuum 2 4 3 6 M Flight Into Known Icing Conditions eere 3 6 SECTION H H IIR 3 7 Normal PROGCGUIES u ta nenn erac dT 3 7 1 Wing Settings 00000000s0eoanononstessnnenunssansssonne E E 3 7 2 Gow mare ea men enter 3 7 3 Go Around Procedures 1 1 1 nnn 3 7 B System Operations and Checks E A A ME T 3 7 1 Allemator System Bescnption ss eus cessant EG 3 7 2 Alternator System Operation 41 42 42212 2401 2 24 4 4 04 611 3 8 S Circuit Breaker ecuacion e o age 3 8 4 Fuel 3 8 5 Landing Gear Down Lights ss
72. D BY PIPER AIRCRAFT CORPORATION MUST BE PROPERLY INSERTED MODEL 34 200 AIRCRAFT SERIAL 34 7350124 ___ REGISTRATION NO 77 75 P PILOT S OPERATING MANUAL PART NUMBER 761 506 REVISION 871130 PIPER AIRCRAFT CORPORATION i 7 gt X APPROVAL SIGNATURE AND STAMP _ 7j Assurance that the airplane is in an airworthy condition is the responsibility of the owner The pilot in command is responsible for determining that the airplane is safe for flight The pilot is also responsible for remaining within the operating limitations outlined by the Airplane Fli ght Manual instrument markings and placards This Pilot s Operating Manual is not designed as a substitute for adequate and competent flight instruction knowledge of the current airworthiness directives applicable federal air regulations or advisory circulars It is not intended to be a guide for basic flight instruction or a training manual for transition from single to multi engine flying If an inconsistency of information exists between the Pilot s Operating Manual and the Airplane Flight Manual approved by the FAA the Airplane Flight Manual shall be the authority A complete or partial replacement of this manual Part No 761 506 may be obtained only from Piper Customer Services Published by PUBLICATIONS DEPARTMENT Piper Aircraft Corporation 761 506 Issued March 1972 GENERAL SPECIFICATIONS APPLICABILITY Thi
73. D SYSTEMS 2 8 ISSUED March 10 1972 SENECA een FLIGHT CONTROL SYSTEMS Dual controls are provided as standard equipment with a cable system used between the controls and the surfaces The horizontal tail stabilator is of the all movable slab type with an anti servo tab which also acts as a longitudinal trim tab actuated by a control mounted on the control tunnel between the two front seats The stabilator provides stability and controllability with less size drag and weight than the more conventional horizontal stabilizer elevator combination The ailerons are provided with a differential action and are lightly interconnected by springs with the rudder This arrangement tends to eliminate adverse yaw in turning maneuvers and to reduce the amount of coordination required in normal turns The flaps are manually extended aerodynamically balanced for light operating forces and spring loaded to return to the retracted position The flap contro lever is located between the front seats on the floor A button on the end of the lever must be depressed before moving the control A past center lock incorporated in the actuating linkage holds the flap when it is in the retracted position so that it may be used as a step on the right side Since the flap will not support a step load except when in the full retracted position it should be completely retracted when people are entering and leaving the aircraft The flaps have three extended p
74. Drain pitot and static systems before flight Paperwork Check that the proper aircraft papers are aboard and that the necessary inspections have been performed Outside Airplane 1 Right wing aileron and flap no damage ice Check hinges 2 Right main gear no leaks tires inflated and not excessively worn 3 1 2 inches piston exposed under static load Right wing tip no damage Right leading edge no damage or ice Fuel cap open to check quantity and color of fuel Check cap vent and then secure Right engine nacelle Open doors to inspect engine Check oil quantity six to eight quarts Secure both inspection doors Right propeller no nicks or leaks spinner secure and not cracked Cowl flaps open and secure Fuel drains Drain five on right side two fuel tank drains under wing one gascolator drain near bottom of engine nacelle two crossfeed drains on bottom of fuselage inboard from wing flap 10 Nose section undamaged 11 Nose gear no leaks tire inflated and not excessively worn 2 1 2 inches piston exposed under static load tow bar removed condition of landing light checked 12 Forward baggage door secure and locked Key removable in locked position only 13 Windshield clean and secure 14 Left wing engine nacelle and landing gear inspect as on right side 15 Pitottube hole unobstructed heat checked by feel if need is anticipated 16 Stall warning vanes no damage free movement 17 Rea
75. EL PA 34 200 REVISED NOVEMBER 30 1987 BLANK PAGE SENECA nn e 1i WEIGHT AND BALANCE In order to achieve the performance and flying characteristics which are designed into the aircraft the Seneca must be flown with the weight and center of gravity C G position within the approved envelope The aircraft offers a tremendous flexibility of loading You can carry a large payload distributed in a variety of combinations of passengers and cargo or a large amount of fuel However you cannot fill the aircraft with seven adults and full fuel tanks With the flexibility comes responsibility The pilot must insure that the airplane is loaded within the loading envelope before he makes a takeoff Misloading carries consequences for any aircraft An overloaded airplane will not take off climb or cruise as well as when it is properly loaded The heavier the airplane is loaded the less single engine climb performance it will have and the pilot may be deprived of one of the advantages of twin engine flight Center of gravity is a determining factor in flight characteristics If the C G is too far forward in any airplane it may be difficult to rotate for takeoff or landing If the C G is too far aft the airplane may rotate prematurely on takeoff or try to pitch up during climb Longitudinal stability will be reduced This can lead to inadvertent stalls and even spins and spin recovery becomes more difficult as the center of gravity moves a
76. H 23 1979 SENECA PROPELLERS Counter rotation of the propellers provides balanced thrust during take off and climb and eliminates the critical engine factor in single engine flight The propellers are constant speed controllable pitch full feathering Hartzell propellers operated by oil and nitrogen pressure Compressed air may be used instead of nitrogen provided it contains no moisture Oil pressure sends the propeller toward the high RPM or unfeather position while nitrogen pressure sends the propeller toward the low RPM or feather position and keeps the propeller from overspeeding The recommended nitrogen pressure to be used when charging the unit is listed on placards on the propeller dome and inside the spinner This pressure varies with ambient temperature at the time of charging A governor mounted on each engine supplies oil through the propeller shaf at various pressures to maintain constant RPM settings Each propeller is controlled by use of the propeller control lever located in the center of the power control quadrant Feathering of a propeller is accomplished by moving the control fully aft through the low RPM detent into the feather position Feathering takes place in approximately six seconds Unfeathering is accomplished by moving the propeller control ahead and engaging the starter until the propeller is windmilling A feathering lock operated by centrifugal force prevents feathering during engine shut down
77. HF Communications Aircraft Model lt 1772 7 Transceiver VOR ILS Receiver GPS Receiver Aircraft Serial Number __ ES Z TES SECTION V PERFORMANCE No change SECTION VI WEIGHT AND BALANCE See current weight and balance data SECTION VII AIRPLANE amp SYSTEM DESCRIPTIONS See GNS 530 Pilot s Guide for a complete description of the GNS 530 system TAMPA FSDO FAAAPPROVED___ A DATE DEC 07 agp PAGE 8 OF 8 190 00181 04 Rev B WEIGHT AND BALANCE FOR SENECA APPLICABLE TO SERIAL NUMBERS 34 7250001 THRU 34 7250189 WHEN PIPER KIT 760607 IS INSTALLED 34 7250190 THRU 34 7250214 WHEN PIPER KIT 760611 IS INSTALLED AND 34 7250215 THRU 34 7350353 WARNING EXTREME CARE MUST BE EXERCISED TO LIMIT THE USE OF THIS REPORT TO APPLICABLE AIRCRAFT THIS REPORT REVISED AS INDICATED BELOW OR SUBSEQUENTLY REVISED IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED BELOW WHEN APPROVED BY PIPER AIRCRAFT CORPORATION SUBSEQUENT REVISIONS SUPPLIED BY PIPER AIRCRAFT CORPORATION MUST BE PROPERLY INSERTED MODEL PA 34 200 AIRCRAFT SERIAL NO _ REGISTRATION NO WEIGHT AND BALANCE REPORT NUMBER VB 424 REVISION PIPER AIRCRAFT CORPORATION APPROVAL SIGNATURE AND y ISSUED August 2 1972 REPORT VB 424 REVISED October 14 1974 MODEL PA 34 200 BLANK PAGE WEIGHT AND BALANCE Log of 1 1 5 M 4 111 Weight and Balance
78. ING FUEL TANK VENT ELECTRIC WINDSHIELD PANEL 4 7 PROPELLER GOVERNOR SHIELD DEFLECTOR ELECTROTHERMAL PROPELLER DEICER PADS ICE DETECTION LIGHT HEATED STALL WARNING TRANSMITTERS HEATED PITOT HEAD ANTI ICING FUEL TANK VENT YOUNGS SENECA Power from the timer is cycled to brush assemblies which distribute power to modified Starter ring gears incorporating slip rings The current is then supplied from the slip rings directly to the electrothermal propeller deicer pads Deicing is accomplished by heating the outboard and then the inboard half of the deicer pads in a sequence controlled by the timer The heating sequence of the deicer pads is according to the following cycle Outboard halves of the propeller deicer pads on the right engine Inboard halves of the propeller deicer pads on the right engine Outboard halves of the propeller deicer pads on the left engine Inboard halves of the propeller deicer pads on the left engine ans When the system is turned on heating may begin on any one of the above steps depending upon the positioning of the timer switch when the system was turned off from previous use Once begun cycling will proceed in the above sequence and will continue until the system is turned off A preflight check of the propeller deicers can be performed by turning the PROP DE ICE switch ON and feeling
79. IRSPEED INDICATOR DIRECTIONAL GYRO ATTITUDE GYRO VERTICAL SPEED INDICATOR GEAR UP LIGHT ALTIMETER OMNI INDICATORS OMNI AND GLIDE SLOPE INDICATORS MARKER BEACON RECEIVER LIGHTS MAGNETIC COMPASS AUDIO CONTROL PANEL COMMUNICATIONS AND NAVIGATION TRANSCEIVERS 1 COMMUNICATIONS AND NAVIGATION TRANSCEIVERS NO 2 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 api MH 15 Bed IUSSI ige 445 41 TRANSPONDER ADF RECEIVER OME CONTROL AND INDICATOR TURN AHD BANK INDICATOR COPILOTS AIRSPEED INDICATOR COPILOTS DIRECTIONAL GYRO COPILOTS ALTITUDE GYRO COPILOTS VERTICAL SPEED INDICATOR COPILOTS ALTIMETER COPILOTS CIGAR LIGHTER CLOCK COPILOTS MIKE PHONE JACKS ALTIMATIC IIR I AUTOPILOT LEFT ENGINE AND FUEL INSTRUMENT CLUSTER OMNI COUPLER PITCH TRIM MANIFOLD PRESSURE GAUGE LEFT ENGINE TACHOMETER RIGHT ENGINE AND FUEL INSTRUMENT CLUSTER RIGHT ENGINE TACHOMETER LANDING GEAR DOWN LIGHTS LANDING GEAR SELECTOR LANDING GEAR FREE FALL VALVE CONTROL ALTERNATE AIR CONTROL CONTROL QUADRANT LEFT AMP METER PAHEL LIGHT SWITCH RIGHT AMP METER FUEL FLOW AND PRESSURE GAUGE EGT GAUGE GYRO SUCTION GAUGE CIRCUIT BREAKER PANEL HEAT AND DEFROST CONTROLS AND PHONE JACKS COPILOTS _ 21 dmm imm A m s bm VIHNA
80. KN 77 VOR LOC Conv King KNS 520 VOR ILS Indicator ISSUED March 10 1972 REVISED May 25 1973 Weight Lbs 3 9 3 5 0 8 1 7 1 3 2 5 Arm Aft Datum 64 4 64 4 52 0 65 9 198 8 124 0 182 0 61 6 12 7 12 0 65 5 61 6 12 0 65 5 Moment 251 225 42 112 258 310 Cert Basis 75 75 75 75 TC 75 A7SO 75 75 TC 75 75 A7SO 75 75 75 REPORT 424 PAGE 4 25 MODEL 34 200 SENECA Weight Arm Aft Cert Item Item Lbs Datum Moment Basis Radio Equipment Optional Equipment cont KingKX170 175 7 5 61 6 462 TC A7SO X King Dual KX 170 y175 15 0 61 6 924 TC A7SO King KI 201 2 5 64 9 162 TC A7SO King KT211 3 64 9 214 TC A7SO King Dual 201 5 0 64 9 325 A7SO King KR 85 Receiver 43 64 4 277 TCAISO 2 Servo Indicator 19 66 3 79 A7SO Loop Antenna 1 3 193 2 251 75 _ Loop Cable 1 8 124 0 223 TCATSO Audio Amplifier 8 22 5 42 TC A7SO Sense Antenna amp Cable 4 160 0 64 TC A7SO ___ King KN 65 DME TC A7SO King 265 Indicator 1 0 65 4 65 TC A7SO Remote Unit 8 4 27 2 228 TC A7SO King KA 41 Antenna 0 2 20 9 4 TC A7SO Cable Assy 1 9 42 2 63 A7SO REPORT VB 424 PAGE 4 26 ISSUED March 10 1972 MODEL PA 34 200 REVISED May 25 1973 SENECA Item Item K Radio Equipment Optional Equipment cont
81. L 33907 Repair Station MO YHTDIRAAK Aircraft Make GARMIN GNS 530 VHF Communications Aircraft Model APP BETO Transceiver VOR ILS Receiver GPS Receiver Aircraft Serial Number d When an alternate airport is required by the applicable operating rules it must be served by an approach based on other than GPS or Loran C navigation the aircraft must have the operational equipment capable of using that navigation aid and the required navigation aid must be operational VNAV information may be utilized for advisory information only Use of VNAV information for Instrument Approach Procedures does not guarantee Step Down Fix altitude protection or arrival at approach minimums in normal position to land 5 If not previously defined the following default settings must be made in the SETUP 1 menu of the GNS 530 prior to operation refer to Pilot s Guide for procedure if necessary a dis spd mh sets navigation units to nautical miles and knots b alt vs ft fpm sets altitude units to feet and feet per minute c map datum WGS 84 sets map datum to WGS 84 sce note below d posn deg min sets navigation grid units to decimal minutes NOTE In some areas outside the United States datums other than WGS 84 or NAD 83 may be used If the GNS 530 is authorized for use by the appropriate Airworthiness authority the required geodetic datum must be set in the GNS 53
82. MODEL PA 34 200 SENECA Airplane Serial Number 34 Registration Number Date AIRPLANE BASIC WEIGHT C G Arm Weight X Inches Aft Moment of Datum In L bs Lbs Actual Standard Empty Weight Computed Optional Equipment Unusable Fuel 5 gallon Licensed Empty Weight Total of above items 49 0 1470 02 O 16 quarts Basic Weight Licensed Empty Weight Plus Standard Empty Weight includes paint hydraulic fluid and undrainable engine oil AIRPLANE USEFUL LOAD NORMAL CATEGORY OPERATION Gross Weight Licensed Empty Weight Useful Load 4200 Ibs lbs lbs THIS LICENSED EMPTY WEIGHT C G AND USEFUL LOAD ARE FOR THE AIRPLANE AS DELIVERED FROM THE FACTORY REFER TO APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE REPORT VB 424 PAGE 4 6 ISSUED March 10 1972 MODEL PA 34 200 SENECA C G RANGE AND WEIGHT INSTRUCTIONS 1 Add the weight of all items to be loaded to the licensed many weight 2 Use the loading graph to determine the moment of al items to be carried in the airplane 3 Add the moment of all items to be loaded to the licensed empty weight moment 4 Divide the total moment by the total weight to determine the C G location 5 using the figures of Item 1 and Item 4 locate a point on range and weight graph If the point falls within the C G envelope the loading meets the weight and bal
83. Main HANDLING AND SERVICING 9 8 ISSUED March 10 1972 SENECA MAINTENANCE ADVICE TO OWNERS Proper maintenance and servicing of the Seneca will ensure that it stays in good condition to provide years of satisfactory performance It is usually best to have aircraft maintenance performed at an authorized Piper Service Center because such a shop has the tools Service Manuals parts and training to do the work properly If the work is done elsewhere be sure the mechanic uses a Piper Inspection Report form for the Seneca and a Seneca Service Manual These are available from Piper dealers and distributors When maintenance or repair work is done on the aircraft the owner should make sure that the mechanic makes a complete and accurate record of the work performed in the aircraft or engine log book Preventive maintenance is the key to dependable service Every airplane must have an annual inspection by an FAA authorized inspector In addition if the airplane is to be used commercially it must have an inspection every 100 hours The Inspection Report form for the Seneca lists inspection and maintenance which should be performed every 50 hours in addition to items to be covered at 100 hours 500 hours and 1000 hours When parts must be replaced they should be replaced with Piper parts Bogus parts which are not exactly like or equivalent to the originals are often less expensive than genuine parts These may be made of a poor substitute materi
84. NDICATOR MARKINGS Calibrated Airspeed NEVER EXCEED SPEED 217 MPH MAXIMUM STRUCTURAL CRUISING SPEED 190 MPH DESIGN MANEUVERING SPEEDS Minimum Weight 2743 Ibs 133 Maximum Weight 4200 Ibs 146 MAXIMUM FLAPS EXTENDED SPEED 125 MPH MAXIMUM GEAR EXTENDED SPEED 150 MPH MAXIMUM GEAR RETRACT SPEED 125 MPH MINIMUM CONTROL SPEED Single Engine 80 MPH AIRSPEED INDICATOR MARKINGS Green Arc Normal Operating Range 76 MPH to 190 MPH Yellow Arc Caution Range Smooth Air 190 MPH to 217 MPH White Arc Flaps Extended Range 69 10 125 Radial Red Line Never Exceed Smooth 217 MPH Radial Red Line Minimum Control Speed Single Engine 80 MPH Radial Blue Line Best R C Speed Single Engine 105 MPH FLIGHT LOAD FACTORS Flaps Up Positive Load Factor Maximum 3 8 G Negative Load Factor Maximum No inverted maneuvers approved REPORT VB 423 PAGE 3 2 FAA APPROVED March 10 1972 MODEL PA 34 200 REVISED September 19 1973 SENECA nn G MAXIMUM WEIGHT 4200 LBS MAXIMUM LANDING WEIGHT A000 LBS G RANGE Weight Forward Limit Aft Limit Inches Aft of Datum Inches Aft of Datum 2780 NOTES 1 Straight line variation between the points given 2 is 78 4 inches forward of wing leading edge from the inboard edge of the inboard fuel tank 4 Jtis the responsibility of the airplane owner and the pilot to assure that the airplane is properly loaded Maximum
85. O M Permanent Revision to F M W B and P O M Permanent Revision to F M W B and P O M Permanent Revision to F M and P O M Permanent Revision to F M and P O M Permanent Revision to W B and P O M Permanent Revision to F M and P O M Dated May 8 1972 Dated July 7 1972 Dated August 2 1972 Dated August 2 1972 Dated September 15 1972 Dated November 16 1972 Dated December 20 1972 Dated December 21 1972 Dated May 25 1973 Dated September 19 1973 Dated October 26 1973 Dated April 26 1974 Dated October 14 1974 Dated May 30 1975 Dated August 19 1975 Dated April 1 1977 Dated March 23 1979 Dated June 14 1983 REVISIONS ISSUED cont Current Permanent and Temporary Revisions to the PA 34 Pilot s Operating Manual issued March 10 1972 are as follows continued 761 506 PR871130 Permanent Revision to Dated November 30 1987 W B and P O M BLANK PAGE TABLE OF CONTENTS GENERAL SPECIFICATIONS DESCRIPTION AIRPLANE AND SYSTEMS FLIGHT MANUAL FAA APPROVED EMERGENCY PROCEDURE FAA APPROVED WEIGHT AND BALANCE OPERATING INSTRUCTIONS OPERATING TIPS PERFORMANCE CHARTS HANDLING AND SERVICING BLANK PAGE GENERAL SPECIFICATIONS Performance ERS RR el Altitude Cruising Speeds mph os uoussuonsensessnunsvannsunsnunnonuonnunssnnssnssssssnssensenensasusnsnnnessunnsssesnssenunsen 1 1 Weights n e
86. PANEL LIGHT T STARTER SOLENOID RELAYS Alternator and Starter Schematic Ser Nos 34 7250001 thru 34 7350135 AIRPLANE AND SYSTEMS REVISED April 26 1974 SENECA EST OPTION An MASTER ar J ene ew me SW ALTERNATOR SWITCHES y 3 u OVERVOLTAGE LI L Ee AA ah LEFT OVER VOLTAGE E LIGHT OVER Unc ice VOLTAGE RELAY RELAY k oo RIGHT ALTERNATOR JLEFT ALTERNATOR FIELD RELAY FIELD RELAY Ser nos 34 7250285 thru 347350363 Qt RIGHT VOLTAGE REGULATOR gt e eee _ _ LEFT VOLTAGE REGULATOR ee sleep eg ALTERNATORS RIGHT LEFT ALTERNATOR FIELO LEFT RIGHT ALTERNATOR OUTPUT RIGHT LEFT STARTER amp ACC STARTER SWITCH LEFT STARTER STARTER SOLENOID RELAYS RIGHT STARTER c Alternator and Starter Schematic Ser Nos 34 7350136 thru 34 7350363 AIRPLANE AND SYSTEMS REVISED April 26 1974 2 15 SENECA When all electrical equipment is turned off except the master switch the ammeters will indicate current being used to charge the battery and operate instrumentation If the sum of the two readings is significant this is an indication that the battery has a low charge The pilot should try to determine why it is low and if no cause is apparent the condition of th
87. R April 2008 April 2010 STATIC SYSTEM April 2008 April 2010 ANNUAL April 2009 April 2010 100 HRS 4 629 7 Tach 4 729 7 Tach COMPUTED WEIGHT AND BALANCE BASIC EMPTY WEIGHT 2862 8 TOTAL MOMENT 241794 1 NEW C G 84 46 USEFUL LOAD 1337 2 SENECA RANGE AND WEIGHT INSTRUCTIONS 1 Add the weight of all items to be loaded to the licensed empty weight 2 Use the loading graph to determine the moment of all items to be carried in the airplane 3 Add the moment of all items to be loaded to the licensed empty weight moment 4 Divide the total moment by the total weight to determine the C G location 5 using the figures of Item 1 and Item 4 locate a point on range and weight graph If the point falls within the C G envelope the loading meets the weight and balance requirements SAMPLE LOADING PROBLEM Normal Category Arm Aft Datum Inches Moment In Lbs 2842 8 29 9 525 11 78 licensed Basic Weight Pilot and Front Passenger Passengers Center Seats Passengers Rear Seats m Passenger Jump Seat Fuel 93 Gallon Maximum Baggage Forward The center of gravity C G of this sample loading problem is at inches aft of the datum line Locate this point on the range and weight graph Since this point falls within weight C G envelope this loading meets the weigh
88. RE LEAN DEN LYCOMING INSTRUCTIONS 100 100 300 400 80 100 110 RATE OF CLIMB FT MIN Example Wt 3400 Ibs Den Alt 2000 ft BEST RATE OF CLIMB SPEED MPH CAS Rate of Climb 350 ft min Best R C Speed 98 MPH PERFORMANCE CHARTS REVISED April 26 1974 SENECA GROSS WEIGHT 4200 LBS FLAPS UP GEAR UP IXTURE LEAN PER LYCONING INSTRUCTIONS DENSITY ALTITUDE FEET I I THESE LL LL EEE PERFORMANCE CHARTS REVISED April 26 1974 8 9 SENECA CRUISE PERFORMANCE RANGE 4200 LBS GROSS WEIGHT 98 GAL TOTAL s GAL USABLE BEST ECONOMY NO RESERVE 2 7 45 RESERVE 55 POWER DENSITY ALTITUDE FEET pw UHR dm 100 800 900 1000 1100 1200 RANGE STATUTE MILES PERFORMANCE CHARTS 8 10 REVISED May 30 1975 SENECA 904 194 SY HAM 03345 11 15 GROSS WEIGHT LBS 8 11 PERFORMANCE CHARTS ISSUED March 10 1972 SENECA 8 12 STALL SPEED MPH CAS 761 506 STALLING 5 SPEED Vs ANGLE OF BAN GROSS WEIGHT 4200 LBS POWER OFF AAA LE Lee EI LE 0 u 10 20 30 58 80 10 ANGLE OF BANK DEGREES PERFORMANCE CHARTS ISSUED March 10 1972 SENECA LANDING GROUND RUN DISTANCE AT VARIOUS ALTITUDES TEMPERATURES WEIGHTS
89. RUNWAY a ET S SS O O ee AY VARIOUS ALTITUDES ETTING 02 LIFT OFF SPEED 80 MPH _ 2600 AH A AE 2200 GROUND RUN DISTANCE Hr LIA ZA gt gt m um LAM Y HAY NAG E LY v 200 0 20 40 60 80 4200 3800 3400 50 10 20 30 TEMPERATURE Example Temp 70 F WEIGHT LBS HEADWIND MPH Wt 3600 Ibs Ground run 900 ft Press Alt 2000 Ft Hd wind 10 MPH 8 2 PERFORMANCE CHARTS ISSUED March 10 1972 TAKE OFF GROUND RUN DISTANCE VARIOUS ALTITUDES 781 506 PONER BEFORE BRAKE RELEASE LIFT OFF SPEED 70 MPH T PAVED LEVEL DRY RUNWAY Zu m UNT PR PNJ 25 suns ALIS Mnt Tre TI 9 28 40 60 60 4200 3400 3000 0 18 20 30 TEMPERATURE F WEIGHT LBS HEADWIND MPH Example Temp 70 _ Wt 3600 Ibs Ground Run 810 ft Press Alt 4000 ft wind 10 MPH PERFORMANCE CHARTS ISSUED March 10 1972 GROUND RUN DISTANCE FT SENECA 8 3 SENECA 506 TAKE OFF DISTANCE OVER 50 OBSTACLE AT VARIOUS ALTITUDES TEMPERATURES WEIGHTS AND WINDS FLAP SETTING 25 FULL POWER BEFORE BRAKE RELEASE LIFT OFF SPEED 70 MPH SHORT FIELD EFFORT BARRIER SPEED 80 MPH PAVED LEVEL DRY RUNWAY T AN 761 u
90. S SENECA HEATING VENTILATING AND DEFROSTING SYSTEM The heating and ventilating system is designed to provide maximum comfort and controllability for pilot and passengers with variable temperature fresh air controls on instrument panel and individual fresh air outlets controlled by the occupants Cabin and defrost heat is provided by a heat exchanger mounted on the exhaust manifold of each engine Air is taken in through a scoop on the outboard side of each cowling and is then ducted through the heater muff where it 15 heated by the exhaust manifold A heat and defrost valve located on the forward side of the firewall sends some of the air directly to the windshield outlets when defrost is selected and sends the rest of the air 10 the temperature fresh air control box which regulates the temperature of the air to be introduced into the cabin interior Fresh air for the cabin interior is taken in through inlets located in the leading edge of each wing The fresh air is forced into the temperature fresh air control box where it is mixed with heated air from the heat exchanger as selected and then into the cabin interior The cabin heat and defroster controls are located on the right side of the instrument panel The defroster is equipped with a blower for use during ground operation to defog the windshield The blower is energized when the mechanical defroster control lever is placed in the full on or hi position The blower can
91. Supply PS 815A Computer Amplifier CA 814A Pitch Trim Servo ST 816B Aileron Servo SA 816A Altitude Controller AC 844B Stabilator Servo SE 816A Flight Controller FC 823A Directional Gyro DG 817A Altitude Gyro 2179ACF Shelf and Instl Trim Servo Amp Shelf and Instl Aileron Servo Shelf and Instl Altitude Cont Shelf and Instl Stabilator Servo Miscellaneous Hardware Wire Harness TOTAL ISSUED July 7 1972 REVISED November 16 1972 Weight Arm Aft Lbs 2 5 4 1 3 2 3 3 3 7 1 6 3 6 2 9 2 9 0 7 1 4 2 0 11 0 45 4 Datum 202 1 199 6 197 0 118 5 218 8 267 7 66 7 63 9 64 8 199 7 gt 119 7 218 1 267 1 118 0 145 0 159 6 Moment 505 818 630 39 328 990 107 230 188 579 120 153 374 236 1595 7244 SENECA Cert Basis TC 75 TC A7SO TC 7 TC A7SO TC A7SO TC A7SO TC 75 TC A7SO TC 75 TC A7SO TC 75 TC A7SO TC 75 TC A7SO TC A7SO REPORT VB 424 PAGE 4 23b MODEL PA 34 200 SENECA Weight Arm Aft Cert Item Item Lbs Datum Moment Basis K Radio Equipment Optional Equipment Narco Mark 16 Transceiver Single 7 5 61 9 464 TC A7SO Narco Mark 16 Transceiver Dual 15 0 61 9 929 75 Narco VOA 50M Omni Converter 2 1 64 9 136 TC A7SO Narco VOA 40M Omni Converter 1 9 64 9 123 TC A7SO Narco VOA 40 Omni Converter 19 64 9 123 A7SO Nav Receiving Antenna 0 5 283 1 142 TC
92. TIONALLY LEFT BLANK REPORT VB 423 PAGE 3 20 FAA APPROVED March 10 1972 MODEL PA 34 200 SENECA SECTION SUPPLEMENTS NOTE A FLIGHT MANUAL SUPPLEMENT IS REQUIRED TO BE IN THE AIRPLANE FLIGHT MANUAL ONLY IF THE EQUIPMENT WHICH IS THE SUBJECT OF THE SUPPLEMENT IS INSTALLED Electric Pitch Trim Installation AutoControl Installation AltiMatic 1 Installation AltiMatic V FD 1 and AltiMatic 1 Installation Windshield Heating Installation su mon W gt Cabin Combustion Heater Installation FAA APPROVED March 10 1972 REPORT VB 423 PAGE 3 21 REVISED December 20 1972 MODEL PA 34 200 SENECA THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 423 PAGE 3 22 FAA APPROVED March 10 1972 MODEL PA 34 200 SENECA A ELECTRIC PITCH TRIM INSTALLATION 1 LIMITATIONS There are no limitations for this installation 2 PROCEDURES a Preflight 1 Circuit breaker Set 2 Depress center bar Trim fore and aft 3 Manually override elec tric trim 4 Check manual trim operation 5 Depress center bar No operation 6 Push rocker Fore Aft only No operation 7 If trim fails preflight disengage electric trim by operating push button trim switch on instrument panel until repaired If trim does disengage have unit repaired before further flight b Inflight 1 Depress center 2 Activate rocker fore aft for trim 3 EMERGENCY OPERATION a In Case Of Malfunction Disen
93. UP position On take off the gear should be retracted before an airspeed of 125 MPH is exceeded It may be extended at any speed up to 150 MPH The nose gear is steerable through 42 degree arc by use of the rudder pedals As the gear retracts the steering linkage disengages to reduce rudder pedal loads in flight and the nose wheel straightens as it enters the wheel well A gear centering spring incorporated in the nose gear steering system prevents any tendency to shimmy The hydraulic reservoir for landing gear operation is an integral part of the gear hydraulic pump Access to the combination pump and reservoir is through a panel in the nose baggage compartment For filling instructions see the Seneca Service Manual The three landing gear wheels are the same size 6 00 6 The nose wheel has a 6 ply tire and the main gear has 8 ply tires Struts for nose and main gear are air oil assemblies The brake system which incorporates a single disc double puck brake assembly on each main gear strut is designed to meet all normal braking needs and to assist in the exceptional short field landing capabilities of the Seneca A brake system hydraulic reservoir independent of the landing gear hydraulic reservoir is located behind a panel at the rear top of the nose baggage compartment The fluid should be maintained at the level marked on the reservoir The brake assemblies are actuated by individual toe brake cylinders mounted on the left o
94. above procedure IN THE EVENT THAT AN ENGINE FAILURE SHOULD OCCUR WHILE THE AIRPLANE IS BELOW Vmc IT IS MANDATORY THAT THE THROTTLE ON THE OPERATING ENGINE BE RETARDED AND THE NOSE LOWERED IMMEDIATELY TO MAINTAIN CONTROL OF THE AIRPLANE It should also be noted that when a 25 degree flap setting is used on the take off roll an effort to hold the airplane on the runway too long may result in a wheelbarrowing tendency This should be avoided 5 The distances required using this take off procedure are given on a chart in the Performance section of this manual OPERATING INSTRUCTIONS ISSUED March 10 1972 6 7 SENECA l DOOR OPEN ON TAKE OFF If either the main or rear cabin door is inadvertently left open or partially open on take off fly the airplane in a normal manner and retum 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 in the following manner 1 Maintain airspeed between 100 and 110 MPH 2 storm window 3 Pull the door closed making certain the upper latch is properly positioned 4 Close the upper latch It may be necessary to pull in on the upper portion of the door while the latch is being closed It is necessary to have someone in the airplane in addition to the pilot to carry out this procedure If the door either main or rear cannot be closed in flight it is possible to continue safely for an extended period In this case the
95. accumulation operation of boots with less than 1 4 inch ice accumulation can result in failure to remove ice Do not hold momentary deice switch ON If wing tail deicer panel light illuminates for more than 20 seconds pull surface deice circuit breaker Heat for the stall warning transmitters is activated by the pitot heat switch When ice has accumulated on the unprotected surfaces of the airplane aerodynamic buffet commences between 5 and 10 mph above the stall speed A substantial margin of airspeed should be maintained above the normal stall speeds since the stall speed may increase by up to 12 mph in prolonged icing encounters If ice is remaining on the unprotected surfaces of the airplane at the termination of the flight the landing should be made using full flaps and carrying slight amount of power whenever practical and approach speeds should be increased by 10 to 15 mph Cruise speed may be significantly reduced in prolonged icing encounters If icing conditions are encountered at altitudes above 10 000 feet it may be necessary to descend in order to maintain airspeed above best rate of climb speed 105 mph CAS NOTE Pneumatic boots must be regularly cleaned and waxed for proper operation in icing conditions Pitot windshield and stall warning heat should be checked on the ground before dispatch into icing conditions Performance Installation of ice protection equipment results in a 30 FPM decrease in single engine cli
96. aced in the ON position since heated air is being supplied to the engine Do not check the alternate air on the ground if dusty air conditions prevail i Magnetos check Normal drop 100 RPM Maximum drop 175 RPM Maximum differential drop 50 RPM Altemator output check approximately equal output for both alternators Throttles 800 1000 RPM Bp oe m OPERATING INSTRUCTIONS REVISED April 1 1977 6 5 SENECA 3 Fuel ON position 4 Alternators 5 Engine gauges in the green 6 Vacuum gauge 4 5 to 5 2 in Hg 7 Altimeter set 8 Attitude indicator set 9 Clock wound and set 10 Mixtures set 11 Propellers set in forward position 12 Quadrant friction adjusted 13 Alternate air off 14 Cowl flaps set 15 Seat backs erect 16 Wing flaps set 17 Trim stabilator and rudder set 18 Seat belts and shoulder harness fastened 19 Empty seats seat belts snugly fastened 20 Controls free fun travel 21 Doors latched 22 Electric fuel pumps 23 Pitot heat as required The normally recommended procedure for sea level take off is full throttle at 2700 RPM During pretake off check at a high elevation lean the mixture to obtain maximum power Apply full throttle then Jean the mixture until the fuel flow pointer stabilizes at a fuel consumption mark consistent with the density altitude about 14 9 for 2000 foot elevation 14 0 for 4000 foot elevation and 13 3 for 6000
97. acnnsecensenstnenasseten 9 1 Taxiing cc A anne nenne rer 9 1 Parking 9 1 IN BER 9 2 cc 9 3 Cleaning Engine teen 9 3 Cleaning Landing nennen 9 4 Cleaning Exterior Surfaces 9 4 Cleaning Windshield and WindOWs cmo nnne 9 4 Cleaning Headliner Side Panels and Seats nennen 9 5 Cleaning rer meets 9 5 Power Plant Induction Air Filter a 9 5 Removal of Induction Air Filter een 9 5 Cleaning Induction Air Filter ee em 9 5 Installation of Induction Air Filter 9 5 Brake Service nannte aE 9 6 Landing Gear Service Nu 9 6 Propeller ii tenen mess 9 6 Oil Requirements cc menn 9 7 Fuel System rennes 9 7 Fuel Requirements Tn 9 7 Filling Fuel Tanks 9 7 Draining Fuel Valves and Lines eene 9 7 Draining Fuel System mini emen 9 8 Tire Infanon eiie nto 9 8 Battery Service etnia 9 8 BLANK PAGE SENECA HANDLING AND SERVICING This section contains information on preventive maintenance Refer to the Seneca Service Manual for further maintenance Any complex repair or modification should be accomplished by a Piper Certified Service Center GROUND HANDLING TOWING The airplane may
98. ain Wheel 0 Airplane Empty Weight as Weighed T 4 EMPTY WEIGHT CENTER OF GRAVITY a following geometry applies to the PA 34 200 airplane when airplane is level See Item 2 ARM Level Points N e Fuselage Left Side 78 4 Below Window 2 The datum is 78 4 inches ahead of wing leading edge at the inboard edge of the inboard fuel tank REPORT VB 424 PAGE 4 4 ISSUED March 10 1972 MODEL PA 34 200 SENECA b Obtain measurement A by measuring from a plumb bob dropped from the wing leading edge at the intersection of the straight and tapered section horizontally and parallel to the airplane centerline to the main wheel centerline c Obtain measurement B by measuring the distance from the main wheel centerline horizontally and parallel to the airplane centerline to each side of the nose wheel axle Then average the measurements d The empty weight center of gravity as weighed including optional equipment and undrainable oil can be determined by the following formula Arm 78 4 BIN yg T Arm 78 4 inches 5 LICENSED EMPTY WEIGHT AND EMPTY WEIGHT CENTER OF GRAVITY Empty Weight as weighed Unusable Fuel 5 0 gallon Licensed Empty Weight ISSUED March 10 1972 REPORT VB 424 PAGE 4 5 MODEL PA 34 200 SENECA WEIGHT AND BALANCE DATA
99. airspeed should be kept below 125 MPH and above 100 MPH to prevent buffeting as a result of the open door CLIMB On climb out after take off the best angle of climb speed 90 MPH at sea level should be maintained until obstacles are cleared The best rate of climb speed 105 MPH at sea level Should be maintained with full power on the engines until approximately 500 feet AGL The best rate of climb speed decreases slightly with increased density altitude and the best angle of climb speed increases slightly There is no time limit on full power engine operation However since full power requires a high fuel consumption and is unnecessary in most flight situations it is advisable to reduce to a climb power setting any time after 500 feet AGL When reducing power the throttles should be retarded first then the propeller controls An en route climb speed of 120 MPH provides good visibility clirnb performance and engine cooling Cylinder head temperatures should be monitored during climb and should be kept below 475 at all times Better climb performance is attained with cow flaps closed however cow flap position should be adjusted for proper engine cooling during climb The electric fuel pumps may be turned off one at a time above 500 feet AGL and fue pressure should be monitored as cach pump is turned off to see that the pressure stays in the green NORMAL CRUISE When leveling off at cruise altitude the pilot may reduce to a cruise
100. al they may not be properly heat treated or dimensions may differ slightly Because it is possible for a bogus part to look just like the real one and still be deficient it is important to use only genuine Piper parts when servicing the Seneca The FAA occasionally publishes Airworthiness Directives which are mandatory and should be complied with promptly Piper Aircraft Corporation takes a continuing interest in having the owner get the most efficient use from his aircraft and in keeping it in the best mechanical condition From time to time Piper issues Service Bulletins Service Letters and Service Spares Letters relating to the aircraft The Service Bulletins are of special importance and should be complied with promptly Service Letters deal with product improvements and careful attention should be given to Service Letter information The Service Spares Letters offer improved parts and operations which may be of interest to an owner From time to time supplements to the Operating Manual will be distributed by the manufacturer These revisions and additions should be studied and put into the operating Manual If the owner desires to modify the aircraft he must obtain FAA approval for the change Minor changes may be accomplished by a mechanic who records and approves the change on an FAA Form 337 but major changes must be accomplished under a Supplemental Type Certificate STC HANDLING AND SERVICING ISSUED March 10 1972 9 9 SENEC
101. an adjustable back Optional headrests and vertically adjustable front seats are also available jump seat which may be mounted between the two middle seats makes the Seneca a seven place airplane A shoulder harness with inertia reel is standard equipment for each of the two Mont seats and is available as optional equipment for the other seats except Seven seat FINISH All sheet aluminum components are carefully finished to assure maximum service life The exterior of the aircraft is finished with a durable acrylic lacquer in a variety of tasteful colors to suit individual owners Economy size Touch Up spray cans are available from Piper dealers BAGGAGE AREA The large amount of available baggage space permits an exceptional flexibility of loading within the Seneca weight and balance envelope Two separate baggage compartments are provided One located in the nose of the aircraft is easily accessible through a baggage door on the left side of the aircraft It has a maximum weight capacity of 100 pounds and a volume of 15 3 cubic feet The other compartment is located aft of seats five and six and is accessible through the rear cabin door on the left side of the fuselage It has a maximum weight capacity of 100 pounds and a volume of 20 0 cubic feet This compartment is conveniently accessible during flight Tie down straps are provided in both the front and rear compartments and should be used whenever possible An additional cargo loa
102. ance requirements SAMPLE LOADING PROBLEM Normal Category Arm Aft Datum Moment Inches In Lbs The center of gravity C G of this sample loading problem is at inches aft of the datum line Locate this point _ on range and weight graph Since this point falls within the weight C G envelope this loading meets the weight and balance requirements 15 THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNER TO INSURE THAT THE AIRPLANE IS LOADED PROPERLY Optional Equipment ISSUED March 10 1972 REPORT VB 424 PAGE 4 7 REVISED May 30 1975 MODEL PA 34 200 SENECA LOADING GRAPH Y POSSE LNAI 1 SONNOd Qvo1 e 10 N MOMENT 1000 POUND INCHES ISSUED March 10 1972 REPORT VB 424 PAGE 4 8 MODEL PA 34 200 SENECA IT 15 THE RESPONSIBILITY OF THE OWNER AND PILOT TO ASCERTAIN THAT THE AIRPLANE ALWAYS REMAINS WITHIN THE ALLOWABLE WEIGHT V5 CENTER OF GRAVITY ENVELOPE WHILE IN FLIGHT 4200 Max Take Off Wt pe Max Landing Wt CTL 82 84 86 88 90 92 94 Location Inches Aft Datum C G Envelope Moment change due to retracting Landing Gear 32 in Ibs ISSUED March 10 1972 REPORT VB 424 PAGE 4 9 MODEL PA 34 200 SENECA INSTRUCTIONS FOR USING THE WEIGHT AND BALANCE PLOTTER This plotter is provided
103. and 2 if the fire continues longer than a few seconds the fire should be extinguished by the best available external means 4 If external fire extinguishing is to be applied a Fuel Selector Valves OFF b Mixture IDLE CUT OFF REPORT VB 423 PAGE 3 16 FAA APPROVED March 10 1972 MODEL PA 34 200 SENECA 15 SPINS Intentional spins are prohibited In the event that an unintentional spin 15 encountered recovery be accomplished by immediately using the following procedures a Retard both throttles to the idle position b Apply full rudder in the direction opposite the spin rotation c Let up all back pressure on the control wheel If nose does not drop immediately push control wheel full forward d Keep ailerons in neutral e Maintain controls in these positions until spin stops then neutralize rudder Recover from the resulting dive with smooth back pressure on the control f wheel No abrupt contro movement should be used during recovery from the dive as the positive limit maneuvering load factor may be exceeded 16 ENGINE FAILURE IN ICING CONDITIONS If engine failure occurs during icing flight select ALTERNATE AIR and attempt to restart engine If unable to restart engine D Feather inoperative propeller see feathering procedure Maintain airspeed at or above 105 mph CAS Descend if necessary to maintain airspeed Reduce electrical loads per al
104. ar the top of the alternator master switch panel turns on a light which is wired around the master switch and which permits the pilot to inspect the panel at night before turning on the master switch The alternator system has the advantage of being able to produce rated electrical output at low engine speed The pilot of the Sen ca is provided with an easy means of monitoring electrical system operation with dual ammeters and Overvoltage warning lights An ammeter is provided for each alternator This acts as a load meter showing the amount of current being produced by particular alternator A zero reading would indicate that the alternator was not producing current An indication near 60 would show that the electrical demand was taxing the alternator In this case thc pilot should turn off unnecessary electrical equipment to reduce the current required When operating on a single engine the pilot should be on guard against demanding too much from the one operating alternator because an overloaded alternator may burn out or its circuit breaker may trip AIRPLANE AND SYSTEMS 2 12 REVISED MARCH 23 1979 SENECA Switch Panel AIRPLANE AND SYSTEMS ISSUED March 10 1972 2 13 SENECA ALTERNATOR EXTERNAL POWER SUPPLY REGULATOR one z ARE o o SWITCH ii uo La SWITCH PANEL LIGHT SWITCH LEFT STARTER SWITCH
105. at longer If the oil pressure does not show an indication shut down the engine and have it checked Repeat steps 8 through 11 with the other engine N Electric fuel pumps off check fuel pressure 5 Rp cse Mixture controls idle cut off Throttle controls open 1 2 inch Propeller controls forward Master switch on Ignition switches on Electric fuel pumps off Propeller clear Starter engage Mixture control Advance as engine Starts Repeat steps 7 through 9 with the other engine If an engine does not start with the above method which omits the priming use the normal starting procedure which includes priming OPERATING INSTRUCTIONS ISSUED March 10 1972 6 3 SENECA NOTE To prevent starter damage limit starter cranking to 30 second periods If the engine does not start within that time allow a cooling period of several minutes before engaging starter again Do not engage the starter immediately after releasing 11 This practice may damage the starter mechanism FLOODED START COONAN RW No Mixture control idle cut off Throttle contro full forward Propeller control forward Master switch on Ignition switches on Electric fue pump off Propeller clear Starter engage When engine fires retard throttle and advance mixture slowly STARTING ENGINES WITH AID OF EXTERNAL ELECTRIC POWER An optional feature known as Piper
106. be turned off in flight by moving the control lever away from the full on or hi position approximately one inch When cabin heat and defrost hea controls are in the OFF position heated air from the heat exchanger is dumped overboard If maximum defrosting is desired the heat to the cabin interior should be turned off and the defroster turned full on An outlet near the feet of each occupant permits a flow of either heated or ventilating air as selected by the control on the instrument panel Individual overhead fresh air outlets supply fresh air from an inlet located on each side of the lower leading edge of the vertical fin The air is ducted to a plenum chamber and then to each individual adjustable outlet located in the ceiling The amount and direction of air can be regulated for individual comfort Rotating the rim of the outlet regulates the amount of air clockwise to decrease the amount counterclockwise to increase it and moving the outlet in the desired direction of the air flow regulates the direction COMBUSTION HEATER An optional Janitro combustion heater installed in the aft fuselage provides added air for cabin heating and windshield defrosting The combustion heater can be used to supplement the standard muff heater system Operation of the combustion heater is controlled by a three position switch located on a heater control console between the pilot s and copilot s seats and labeled FAN OFF and HEATER
107. calibrated airspeed for the Seneca if zero instrument error is assumed When below 90 MPH IAS this calibration is valid only when level flight 15 maintained using power as required to prevent rapid altitude changes AIRSPEED CORRECTION TABLE Flaps 0 IAS MPH 70 80 90 100 120 140 160 180 200 218 CAS MPH 72 82 92 102 122 142 161 181 200 217 Flaps 40 IAS MPH 70 80 90 100 110 120 127 CAS MPH 70 80 89 99 109 118 125 ROUGH AIR FLIGHT In conditions of extreme turbulence reduce power to slow the airplane to slightly below the design maneuvering speed which varies from 133 MPH at light weight to 146 MPH at 4200 pounds gross weight When flying in extreme turbulence or strong vertical currents and using the autopilot the altitude hold mode should not be used Vmc MINIMUM SINGLE ENGINE CONTROL SPEED Vmc is the calibrated airspeed below which a twin engine aircraft cannot be controlled in flight with one engine operating at take off power at sea level density altitude and the other engine windmilling Vmc for the Seneca has been determined to be 80 MPH Under no circumstances should an attempt be made to fly at a speed below this Vmc with only one engine operating As a safety precaution when operating under single engine flight conditions either in training or in emergency situations maintain an indicated airspeed above 90 MPH The Vmc demonstration required for the FAA flight test for the multi engine rating approaches an uncontro
108. ce the Seneca has one combined fuel tank per engine it is advisable to feed the engines symmetrically during cruise so that approximately the same amount of fuel will be left in each side for the landing A crossfeed is provided and can be used to even up the fuel should it be necessary During flight keep account of time and fuel used in connection with power settings to determine how the fuel flow and fuel quantity gauging systems are operating If the fuel flow indication is considerably higher than the fuel actually being consumed or an asymmetric flow gauge indication is observed you may have a clogged fuel nozzle which should be cleaned There are no mechanical uplocks in the landing gear system In the event of a hydraulic system malfunction the landing gear will free fall to the gear down position The true airspeed with gear down is approximately 75 of the gear retracted airspeed for any given power setting Allowances for the reduction in airspeed and range should be made when planning extended flight between remote airfields or flight over water OPERATING INSTRUCTIONS REVISED October 26 1973 6 9 SENECA DESCENT When power is reduced for descent the mixtures should be enriched as altitude decreases The propellers may be left at cruise setting however if the propeller speed is reduced it should be done after the throttles have been retarded APPROACH AND LANDING Sometime during the approach for a landing the thr
109. d to the cylinders The divider contains a spring loaded positive shut off valve Within each cylinder are continuou s flow air bleed nozzles with provisions to eliminate the adverse effects of low manifold pressure when idling Since fuel metering is provided by the servo regulator rather than the nozzles more uniform cylinder head temperatures result and longer engine life is possible Induction air for the engine enters an air scoop located on the outboard side of the lower cowl The air is directed through a filter and thence to the servo regulator To prevent engine malfunction if the air filter becomes blocked the induction system incorporates method of providing heated alternate air which does not pass through the filter Located in the air box between the filter and servo regulator is a valve which is manually operated by the alternate air control located below the power quadrant Since the alternate air is heated by the crossover exhaust tube it gives extra protection against icing in the system caused by snow or freezing rain Alternate air should not be used during ground operation because the unfiltered air may contain dust and other contamination The primary induction source should always be used for take off All throttle operations should be made with a smooth not too rapid movement 10 prevent unnecessary engine wear or damage to dynamic counterweights on the engines The pilot should read and follow the procedures rec
110. d wing tips the structural components of the airframe are made of aircraft aluminum alloy which has been heat treated and protected from corrosion The airframe has been designed and tested to a limit positive load factor of 3 8 The Seneca is not designed for acrobatic flight and consequently aerobatics are prohibited gt The fuselage is a conventional semi monocoque structure which has a front door on the right side and a rear door on the left An additional large size rear door which facilitates the loading of large pieces of cargo is available The wing is of conventional metal design using one main spar located at approximately 40 of the chord aft of the leading edge to take bending loads and a rear spar for mounting the flaps and ailerons and to assist in taking torque and drag loads Slotted wing flaps which are mechanically operated by a four position handle located between the two front seats are provided to reduce landing speed and to give the pilot a high degree of glide path control Two interconnected fuel tanks form an integral part of each wing Both tanks on one side are filled through a single filler neck located well outboard of the engine nacelle AIRPLANE AND SYSTEMS REVISED JUNE 14 1983 2 1 SENECA The wings are attached to each side of the fuselage by the butt ends of the main spars which are bolted into a spar box carry through an integral part of the fuselage structure There are also fore and aft attac
111. ding door aft of the rear door is an optional feature which facilitates the loading of bulky items All baggage and passenger loading doors use the same key AIRPLANE AND SYSTEMS 2 26 ISSUED April 26 1974 SENECA STALL WARNING An approaching stall is indicated by a stall warning light and horn activated by two lift detectors installed on the leading edge of the left wing outboard of the engine nacelles The inboard detector triggers the warning when the flaps are in the 25 and 40 degree positions the outboard when the flaps are in the other positions The stall warning horn has a different sound from that of the landing gear warning horn AIRPLANE AND SYSTEMS ISSUED April 26 1974 2 27 BLANK PAGE 47 ji 1 El Lm ra oe I F f i JN P gt dr Le La oak 1 e 6 t Wt 4 i i at b 1 gt 4 8 ow B i ri Fee A p ms j X 3 ary res a 1 Am m 4 uo A re Jr I M h Pe rita up LL gt ry fa t WS PE weh e ue 4 qe re A EN Fa A 1 a 3 ls UM E iT AIRPLANE FLIGHT MAN F A APPROVED _
112. dio Panel Data Required 1 Garmin Master Drawing List MDL 005 C0001 00 Revision E dated February 18 2003 and 2 FAA Approved Airplane Flight Manual Supplement AFMS for Piper Modes with Garmin GNS 430 and GNS 530 VHF NAV COMM GPS and GI 106A Course Deviation Indicators Garmin Document Revision B dated February 26 2003 or later FAA Approved Revisions to 1 or 2 Limitations and Conditions Compatibility of this design change with previously approved modifications must be determined by the installer If the holder agrees to permit another person to use this certificate to alter the product the holder shall give the other person written evidence of that permission Date of application May 31 2002 Date of issuance February 27 2003 This certificate and the supporting data which is the basis for approval shall remain in effect until surrendered suspended revoked or a termination date is otherwise established by the Administrator of the Federal Aviation Administration Page m DUPLICATE PIPER This manual is incomplete without an APPROPRIATE FAA APPROVED AIRPLANE FLIGHT MANUAL and an APPROPRIATE WEIGHT AND BALANCE REPORT WARNING EXTREME CARE MUST BE EXERCISED TO LIMIT THE USE OF THIS MANUAL TO APPLICABLE AIRCRAFT THIS MANUAL REVISED AS INDICATED BELOW OR SUBSEQUENTLY REVISED IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED BELOW WHEN APPROVED BY PIPER AIRCRAFT CORPORATION SUBSEQUENT REVISIONS SUPPLIE
113. directional control 2 Adjust airspeed toward the single engine best rate of climb speed of 105 mph 3 Feather inoperative engine see feathering procedure 7 SINGLE ENGINE LANDING a Feather inoperative engine see feathering procedure o nor extend landing gear until certain of making field c Do not lower wing flaps until certain of making field Maintain additional altitude and speed during approach keeping in mind that landing should be made right the first time and that a go around may require the use of full power on the operating engine making control more difficult A final approach speed of 105 miles per hour and the use of 25 rather than full wing flaps will place the airplane in the best configuration for a go around should this be necessary but it should be avoided if at all possible Under some conditions of loading and density altitude a go around may be impossible and in any event the sudden application of power during single engine operation makes control of the airplane more difficult 8 SINGLE ENGINE GO AROUND If a single engine go around cannot be avoided proceed as follows Mixture forward Propeller forward Throttle open Flaps retract Landing Gear retract Airspeed one engine inoperative best rate of climb speed 105 MPH Trim set Cowl Flap as required operating engine Tm mo AO oP FAA APPROVED March 10 1972 REPORT VB 423 PAGE 3 13 MODEL PA 34 2
114. dle cut off Trim as required Maintain 5 bank toward operating engine Electric Fuel Pump of inoperative engine OFF Magnetos of inoperative engine OFF Cowl Flaps close on inoperative engine use as required on operative engine a b d fi g h i k 1 m n 4 s Alternator of inoperative engine OFF Electrical Load reduce to prevent battery depletion u Fuel Management fuel OFF inoperative engine consider crossfeed use v Electric fuel pump operative engine OFF FAA APPROVED March 10 1972 REPORT VB 423 PAGE 3 11 REVISED May 25 1973 MODEL PA 34 200 SENECA 3 UNFEATHERING PROCEDURE j mo oo op Fuel selector inoperative engine ON Electric fuel pump inoperative engine OFF Throttle open 1 4 inch Propeller control forward to cruise RPM position Mixture rich Magneto switches ON Starter engage till prop windmills Throttle reduced power till engine is warm If engine does not start prime by tuming electric fuel pump of inoperative engine on for 3 seconds and then repeat steps g h and i Altemator ON 4 FUEL MANAGEMENT DURING SINGLE ENGINE OPERATION A crossfeed is provided to increase range during single engine operation Fuel system operation 15 as follows a MODEL PA 34 200 Cruising 1 When using fuel from tank on the same side as the operating engine a Fue
115. e GNS 530 System and the course pointer is not automatically driven to the desired track the course pointer on the Hi nust be manually set to the desired track DTK indicated by the GNS 530 For detailed autopilot flight director operational instructions refer to the FAA Approved Flight Manual Supplement for the autopilot flight director FAA APPROVED TAMPAFSDO DATE DEC 07 29 6 190 00181 04 Rev B Tomlinson Avionics Inc PH 941 936 6969 511 Danley Page rield Ft Myers FL 33907 YN1D644K GARMIN GNS 530 VHF Communications Transceiver VOR ILS Receiver GPS Receiver Aircraft Make Aircraft Model Aircraft Serial Number 327 7 272 2 4 CROSSFILL OPERATIONS For dual GNC 500 Product Series or GNC 500 GNC 400 Product Series installations crossfill capabilities exist between the number one and number two Systems Refer to the GARMIN GNS 530 Pilot s Guide for detailed crossfill operating instructions 3 AUTOMATIC LOCALIZER COURSE CAPTURE By default the GNS 530 automatic localizer course capture feature is enabled This feature provides a method for system navigation data present on the external indicators to be switched automatically from GPS guidance to localizer glide slope guidance as the aircraft approaches the localizer course inbound to the final approach fix If an offset from the final approach course is being flown it is possible that the automatic switch from GPS
116. e battery and the electrical system should be checked by a mechanic If during flight both alternators should fail the battery becomes the only source of electrical power Therefore all unnecessary equipment should be turned off How long the battery will be able to supply the necessary equipment depends on the current drain of the equipment time it took the pilot to notice the dual failure and the condition of the battery During night or instrument flight the pilot should continuously monitor the ammeters and warning lights so that he can take prompt corrective action if electrical malfunction occurs Procedures for dealing with electrical malfunction are covered in the Airplane Flight Manual VACUUM SYSTEM The directional gyros and attitude indicators are operated by air drawn from the cabin through a filter and the instruments to the engine nacelle by a vacuum system The vacuum system consists of one vacuum pump installed on each engine plus plumbing and regulating hardware If a second set of gyro instruments 15 installed a second filter will be added for these instruments The instruments are protected by a vacuum regulator mounted on the right aft side of each firewall The regulators maintain a vacuum of 5 0 1 inches of mercury at 2000 RPM Suction is indicated by a vacuum gauge mounted to the left of the right control column A vacuum less than 4 5 indicates a low air flow through the gyro instruments with possibly inaccurate readi
117. e bottom of the engine nacelle and are manually operated by control levers below the throttle quadrant The control levers have three positions open intermediate and closed A lock incorporated into each control lever locks the cowl flap in the selected position To operate depress the lock and move the control to the desired position Release the lock after initial moveinent of the control the flap wil then stop automatically in the next intermediate open or closed position The lock must be depressed for each selection of cowl flap An oil cooler for each engine is mounted on the forward side of the firewall Air is picked up by air scoops on the side of the cowl passed through the oil cooler and ducted overboard in the lower cowling The fuel injection system reduces the possibility of induction system ice and provides better fuel distribution than does a carburetor system Each engine is equipped with a Bendix RSA 5 fuel injection system which operates on the principle of measuring engine air consumption and using the air flow to control fuel flow to the engine Fuel pressure regulation by means of a servo valve causes a minimal drop in fuel pressure throughout the metering system Metering pressure is maintained above vapor forming conditions yet fuel inlet pressure is Jow enough to allow the use of a diaphragm fuel pump Thus vapor lock and associated problems of difficult starting are minimized AIRPLANE AND SYSTEMS 2 2 REVISED MARC
118. e weight and balance requirements SAMPLE LOADING PROBLEM Category Arm Af Weight Datum ene Pilot and Front Passenger Center idi Passenger Jump Seat Fuel 93 Gallon Maximum Baggage Total Losded Airplane gt The center of gravity C G of this sample loading problem is at inches aft of the datum line Locate this point on the C G range and weight graph Since this point falls within the weight C G envelope this loading meets the weight and balance requirements IT IS THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNER TO INSURE THAT THE AIRPLANE IS LOADED PROPERLY Optional Equipment ISSUED March 10 1972 REPORT VB 424 PAGE 4 7 REVISED May 30 1975 MODEL PA 34 200 m a Y p Da u A La
119. ection light electrothermal propeller deicer pads electric windshield panel heated stall warning transmitters heated pitot head anti icing fuel tank vents propeller governor shields and deflectors The pneumatic wing and empennage boots are installed on the leading edges of the wings the vertical stabilizer and the horizontal stabilator A constant suction is applied to all of the Surface deicer boots from the engine driven vacuum pumps to provide smooth streamlined leading edges during normal operation with the surface deicer system off Deicer boots are inflated by a momentary ON type SURFACE DE ICE switch located on the instrument panel directly above the control quadrant Actuation of the SURFACE DE ICE switch activates a system cycle timer which energizes the pneumatic pressure control valves for six seconds The boot solenoid valves are activated and air pressure is released to the boots inflating all surface deicers on the airplane A WING TAIL DE ICER indicator li ght 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 Vacuum suction is then reapplied to the deicer boots The d icer boots do not inflate during the PRESS TO TEST cycle Circuit protection for the surface deicer system is provided by a WING TAIL DE ICERS circuit breaker located in the circuit breaker pa
120. ects to the injector This screen should be cleaned every 50 hours of operation FUEL REQUIREMENTS A minimum octane of 100 130 Aviation Grade fuel must be used in the Seneca Since the use of lower grades of fuel can cause serious damage in a short period of time the engine warranty is invalidated by use of lower octanes FILLING FUEL TANKS Observe all required precautions for handling gasoline Fill the fuel tanks to the bottom of the filler neck with 100 130 octane fuel Each wing holds a maximum of 49 gallons giving a total of 98 gallons of fuel DRAINING FUEL VALVES AND LINES Each gascolator strainer is provided with a quick drain which should be drained before the first flight of the day or after refueling to check for fuel contamination contamination is found fuel should be drained until the contamination Stops if contamination persists after draining fuel for a minute contact a 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 HANDLING AND SERVICING REVISED 30 1975 9 7 SENECA DRAINING FUEL SYSTEM The bulk of the fuel may be drained from the fuel cells by the use of a siphon hose placed in the cell or tank through the filler neck The remainder of the fuel ma
121. ed pitot head 5 Anti icing fuel tank vents 6 Propeller governor shield and deflectors 7 Wing ice light 8 Heated Stall Warning Transmitters REPORT VB 423 PAGE 3 6 FAA APPROVED March 10 1972 MODEL PA 34 200 REVISED April 26 1974 SENECA SECTION II PROCEDURES A NORMAL PROCEDURES 1 WING FLAP SETTINGS Take Off 0 Landing 40 The flaps are manually operated Flap deflection versus handle position is First notch 10 Degrees Second notch 25 Degrees Third notch 40 Degrees COWL FLAPS Cowl flaps are provided to allow manual control of engine temperatures The cow flaps should be open during ground operations and in climbs In no case should the cylinder head temperatures be allowed to exceed 475 F and the oil temperatures allowed to exceed 245 F GO AROUND PROCEDURES If a go around from normal landing with the airplane in the landing configuration becomes necessary Apply takeoff power to both engines Establish positive climb Retract wing flaps Retract landing gear o Adjust cowl flaps for adequate engine cooling SYSTEM OPERATIONS AND CHECKS ALTERNATOR SYSTEM DESCRIPTION The two ammeters continuously indicate the alternator outpuls Certain regulator failures can cause the alternator output voltage to increase uncontrollably To prevent damage overvoltage relays are installed to automatically shut off the alternator s The overvoltage trip lights
122. ed rapidly or airspeed is abruptly increased If an overspeed condition is encountered the propeller will not feather and the following procedure should be used Close throttle Slow aircraft to best rate of climb speed Pull propeller control back to low RPM Slowly increase throttle until propeller governor is engaged Slowly increase propeller and throttle to the desired power setting Continue flight at reduced speed and power and land as soon as practical mono ge If the throttle is retarded below 15 20 IN MP at speeds above 105 MPH the propeller may overspeed again upon reapplying power If this occurs follow the same procedure to regain propeller control REPORT VB 423 PAGE 3 18 FAA APPROVED March 10 1972 MODEL PA 34 200 REVISED August 19 1975 SENECA D SPECIAL OPERATING PROCEDURES 1 FLIGHT INTO KNOWN ICING CONDITIONS Prior to dispatch into forecast icing conditions all ice protection should be functionally checked for proper operation The windshield defroster should be turned on before entering icing conditions Upon entering probable icing conditions accomplish the following Pitot heat On immediately Windshield heat On immediately Propeller Deice On immediately Wing Deice On after 1 4 to 1 2 inch accumulation Relieve propeller unbalance if required by increasing RPM briefly Repeat as required gan TP WARNING Do not cycle pneumatic boots with less than 1 4 inch of ice
123. eration Fuel system operation is as follows 1 Cruising When using fuel from tank on the same side as the operating engine 1 Fuel selector of operating engine in ON position 2 Fuel selector of inoperative engine in OFF position 3 Electric fuel pumps OFF except in case of engine driven pump failure electric fuel pump on operating engine side must be used b When using fuel from tank on the side opposite the operating engine 1 Fuel selector of operating engine in X FEED CROSSFEED position _ 2 Fuel selector of inoperative engine in OFF position 3 Electric fuel pumps OFF except in case of engine driven pump failure electric fuel pump on operating engine side must be used c Use crossfeed in level flight only REPORT VB 423 PAGE 3 8 FAA APPROVED March 10 1972 MODEL PA 34 200 REVISED April 1 1977 SENECA nn 2 Landing a Fuel selector of operating engine in ON position b Fuel selector of inoperative engine in OFF position c Electric fuel pump of operating engine ON c Operation With Both Engines Operating In cruising flight it is permissible to operate both engines from the same tank d Turning takeoffs Fast taxi turns immediately prior to takeoff run can Cause temporary malfunction of one engine during takeoff if the electric boost pumps are not in the ON position 5 LANDING GEAR DOWN LIGHTS The green gear down lights on
124. ere icing conditions are observed accomplish the following Immediately request priority handling from Air Traffic Control to facilitate a route an altitude change to exit the severe weing conditions in order to avoid extended exposure to flight conditions more severe than those Fer which the airplane has been certificated Avoid abrupt and excessive maneuvering that may exacerbate control difficulties not engage the autopilot If the autopilot is engaged hold the control wheel firmly and disengage the autopilot If an unusual roll response or uncommanded roll control movement is observed reduce the angle of attack Do not extend flaps when holding in conditions Operation with flaps extended can result in a reduced wing angle amp fr atr ck Wath the possibility of ice forming on the upper surface further aft on the wing than normal possibly aft of the protected area If the flaps are extended do not retract them until the airframe is clear of ice Report these weather conditions to Air Traffic Control b Incorporating the AFM revisions as required by this AD may be performed by the owner operator holding at least a private pilot certificate as authorized by section 43 7 of the Federal Aviation Regulations 14 CFR 43 7 and must be entered into the aircraft records showing compliance with this AD in accordance with section 43 9 of the Federal Aviation Regulations 14 CFR 43 9
125. etween 2200 2400 RPM Or Hartzell HC C2YK 2CLG Y JC7666A This model includes damper This model installs on R H side of aircraft Constant Speed Pitch Settings at 30 in station High 79 81 Low 13 5 Diameter Not over 76 inches Not under 74 inches No further reduction permitted INSTRUMENT MARKINGS POWER PLANT OIL TEMPERATURE Green Arc Normal Operating Range 75 to 245 F Red Line Maximum 245 F OIL PRESSURE Green Arc Normal Operating Range 60 PSI to 90 PSI Yellow Arc Caution 25 PSI to 60 PSI Red Line Minimum 25 PSI if installed or 60 PSI if installed Red Line Maximum 90 PSI FAA APPROVED March 10 1972 REPORT VB 423 PAGE 3 1 REVISED August 19 1975 MODEL PA 34 200 SENECA TACHOMETER For Hartzell 2 2 HC C2YK 2 HC C2YK 2 or HC C2YK 2 LEF propellers Green Arc Normal operating Range 500 RPM to 2200 RPM amp 2400 RPM to 2700 RPM Red Arc Avoid continuous operation 2200 RPM to 2400 RPM Red Line Maximum 2700 RPM For Hartzell HC C2YK 2CG or HC C2YK 2CLG propeller with dampers Green Arc Normal Operating Range 500 10 2700 Red Line Maximum 2700 RPM FUEL PRESSURE Green Arc Normal Operating Range 14 PSI to 35 PSI Red Line Maximum 35 PSI Red Line Minimum 14 PSI FUEL FLOW Red Line Maximum 19 2 GPH CYLINDER HEAD TEMPERATURE Green Arc Normal Range 200 to 475 Red Line Maximum 475 F AIRSPEED LIMITATIONS AND I
126. foot elevation Leave the mixture in this position for take off Do not overheat the engine when operating with mixture leaned If overheating occurs enrich the mixture enough that temperature returns to normal OPERATING INSTRUCTIONS 6 6 REVISED August 19 1975 SENECA TAKE OFF Take off should not be attempted with ice or frost on the wings Take off distances and 50 foot obstacle clearance distances are shown on charts in the Performance section of this manual The performance shown on charts will be reduced by uphill gradient tailwind component or soft wet rough or grassy surface Avoid fast turns onto the runway followed by immediate take off especially with a low fuel supply As power is applied at the start of the take off roll look at the engine instruments to see that the engines are operating properly and putting out normal power and at the airspeed indicator to see that it is functioning Normal Take off Flaps Up a When obstacle clearance is no problem a normal take off may be used Accelerate 10 80 85 MPH and ease back on the wheel enough to let the airplane lift off After lift off accelerate to the best rate of climb speed 105 MPH or higher if desired retracting the landing gear when a gear down landing is no longer possible on the runway Short Field Take off Flaps Up When a short field effort is required but the situation presents a wide margin on obstacle clearance the safest short field technique to
127. ft of the approved limit A properly loaded aircraft however will perform as intended Before the aircraft is delivered the Seneca is weighed and a basic weight and C G location coniputed Basic weight consists of the empty weight of the aircraft plus the unusable fuel and full oil capacity Using the basic weight and C G location the pilot can easily determine the weight and C G position for the loaded airplane by means of a plotter which is furnished with the aircraft If he wants more precise values or if the plotter is not available he can compute the total weight and moment and then determine whether they are within the approved envelope The basic weight and C G location for a particular airplane are recorded on the plotter for the airplane These values are also entered in the weight and balance section of the Airplane Flight Manual The current values should always be used Whenever new equipment is added or any modification work is done the mechanic responsible for the work is required to compute a new basic weight and basic C G position and to write these in the aircraft log book The owner should make sure he does and should change these values on his plotter JSSUED March 10 1972 REPORT VB 424 PAGE 4 1 REVISED MARCH 23 1979 MODEL PA 34 200 SENECA A weight and balance calculation is necessary in determining the best positions for locating passengers or cargo and can guide the pilot in relocating people baggage s
128. gage electric pitch trim by operating push button trim switch on instrument panel b In Emergency Electric pitch trim may be overpowered using manual pitch trim FAA APPROVED March 10 1972 REPORT VB 423 PAGE 3 23 MODEL PA 34 200 SENECA AUTOCONTROL INSTALLATION l LIMITATIONS a Autopilot use is prohibited above 195 MPH CAS b Use of flaps is limited to 25 or less during autopilot operations c Autopilot OFF for takeoff and landing 2 PROCEDURES a Normal Operation Refer to the current AutoControl III Owner s Handbook b Emergency Operation 1 In an emergency a The AutoControl III can be disconnected by pushing the roll switch to OFF b The AutoControl III can be overpowered at either control wheel 2 An autopilot runaway with a 3 second delay in the initiation of recovery while operating in a climb cruise or descending flight could result in a 45 bank and a 175 foot altitude loss 3 An autopilot runaway with a 1 second delay in the initiation of recovery during an approach operation coupled or uncoupled single or multi engine could result in an 18 bank and a 40 foot altitude loss 3 PERFORMANCE The airplane performance remains unchanged REPORT VB 423 PAGE 3 24 FAA APPROVED March 10 1972 MODEL PA 34 200 SENECA nn D ALTIMATIC V FD 1 OR ALTIMATIC V 1 INSTALLATION 1 LIMITATIONS ao of fastened Autopilot OFF during takeoff and landing
129. hile leaving the air intake lever in the open position before turning the switch to the OFF position During flight leave the air intake lever open for a minimum of 15 seconds after turning OFF the heater switch AIRPLANE AND SYSTEMS ISSUED December 20 1972 2 20a SENECA DEFROSTER OUTLET FRESH AIR OUTLET SILENCER ASSEMBLY DEFROSTER MOTOR DUCT ASSEMBLY FRESH AIR ANO TEMPERATURE CONTROL ASSEMBLY SILENCER ASSEMBLY HEAT AND DEFROST VALVE FRESH AIR INLET HEAT EXCHANGER SOON 4 FRESH AIR E DEFROSTER AIR 4 HEATED AIR SILENCER ASSEMBLY COMBUSTION HEATER FRESH AIR OUTLET DEFROSTER OUTLET DEFROSTER MOTOR DUCT ASSEMBLY FRESH AIR AND TEMPERATURE CONTROL ASSEMBLY SILENCER ASSEMBLY HEAT AND DEFROST VALVE FRESH AIR INLET HEAT EXCHANGER 4 FRESH AIR DEFROSTER AIR AIR Optional Heating and Ventilating System AIRPLANE AND SYSTEMS 2 20b ISSUED December 20 1972 SENECA SSS on r m zm mam Heater and Defroster Controls AIRPLANE AND SYSTEMS ISSUED March 10 1972 2 21 REVISED December 20 1972 SENECA ICE PROTECTION SYSTEM A complete ice protection system is available as optional equipment in the Seneca to provide for flight into known icing conditions when necessary This system consists of the following major components pneumatic wing and empennage boots wing ice det
130. hments at the rear spar and at an auxiliary front spar The empennage of the Seneca consists of a vertical stabilizer a rudder and a horizontal stabilator The rudder has a trim tab capable of relieving the pilot of excessive pedal force during single engine operation The stabilator incorporates an anti servo tab which improves Jongitudinal stability and provides longitudinal trim This tab moves in the direction the stabilator moves but with increased travel ENGINES The 400 total horsepower of the Seneca engines makes possible a high cruise speed and excellent climb performance The aircraft is powered by two four cylinder Lycoming fuel injected engines each rated at 200 horsepower at 2700 RPM Asymmetric thrust is eliminated during take off and climb by counter rotation of the engines the left engine rotating in a clockwise direction when viewed from the cockpit and the right engine rotating counterclockwise The engine compartments are easily accessible for inspection through top hinged side panels on either side of the engine cowlings The cowlings are cantilever structures attached at the firewalls Engine mounts are constructed of steel tubing and dynafocal mounts are provided to reduce vibration The exhaust system is a crossover type with exhaust gases directed outboard of the nacelles into muffler heaters to minimize exhaust noise and provide heated air for the cabin and defroster The cowl flaps are l cated on th
131. hould also be replaced if the transmitter has been used in an emergency situation Or if the accumulated test time exceeds one hour The replacement date is marked on the transmitter label The unit has a three position selector switch placarded OFF ARM and ON The ARM position is provided to set the unit to the automatic position so that it will transmit only after impact and continue to transmit until the battery power is drained to depletion or the switch is manually moved to the OFF position The ARM position is selected when the locator is installed at the factory and should remain in that position whenever the unit is installed in the aircraft The ON position is provided so the unit can be used as a portable transmitter or in the event the automatic feature was not triggered by impact or to check the function of the transmitter periodically The OFF position is provided for the purpose of changing the battery or to prolong the service life of the battery if used as a portable transmitter or rearming the unit if it should be activated for any reason NOTE If the switch has been placed in the ON position for any reason the OFF position has to be selected before selecting ARM If ARM is selected directly from the ON position the transmitter will continue to transmit in the ARM position Attached to the unit is a portable antenna provided so that the locator may be removed from the aircraft in case of an emergency and used as a portable sig
132. ic again to get the zero end of the middle seat slot over this dot Draw a line up this slot to the 250 pound position 115 135 and place the 3rd 901 Continue moving the plastic and plotting points to account for weight in the rear seats 80 100 forward baggage compartment 50 rear baggage compartment 45 and fuel tanks 360 As can be seen from the illustration the final dot shows the total weight to be 3880 pounds with the C G at 89 52 This is well within the envelope There will be room for more fuel As fuel is burned off the weight and C G will follow down the fuel line and stay within the envelope for landing ISSUED March 10 1972 REPORT VB 424 PAGE 4 11 MODEL PA 34 200 SENECA SAMPLE PROBLEM Max Take Off Wt Max Landing 4 TAKE OFF WEIGHT AND C G 82 84 86 88 90 92 C G Location Inches Aft Datum Moment change due to retracting Landing Gear 32 in bs REPORT VB 424 PAGE 4 12 ISSUED March 10 1972 MODEL PA 34 200 SENECA EQUIPMENT LIST The following 15 a list of equipment which may be installed in the PA 34 Items marked with an are items installed when the airplane was delivered by the manufacturer Weight Arm Aft Cert Item Item Lbs Datum Moment Basis A Propellers and Propeller Accessories Two Propellers Hartzell Model 2 2 _ C7666A 0 Left Wing 55 0 22 6 1243 TC P920 Hartzell Mode HC C2YK 2 FC7666A 0 Left Wing 55 0 22 6
133. ide maximum power in the event of a go around The landing gear position should be checked on the downwind leg and again on final approach by checking the three green indicator lights on the instrument panel and looking at the external mirror to check that the nose gear is extended Remember that when the navigation lights are on the gear position lights are dimmed and are difficult to see in the daytime Flap position for landing will depend on runway length and surface wind Full flaps will reduce stall speed during final approach and will permit contact with the runway at a slower speed Good pattern management includes a smooth gradual reduction of power on final approach with the power fully off before the wheels touch the runway to give the horn a chance to blow if the gear is not locked down 1f electric trim is available it can be used to assist a smooth back pressure during flare out OPERATING INSTRUCTIONS 6 10 REVISED October 26 1973 SENECA Maximum braking after touch down is achieved by retracting the flaps applying back pressure to the wheel and applying pressure on the brakes However unless extra braking is needed or unless a strong crosswind or gusty air condition exists it is best to wait until turning off the runway to retract the flaps This will avoid reaching for gear handle instead of the flap handle by mistake and will permit full attention to be given to the landing and landing roll Normal Landing App
134. ill operate during this check and should be reset prior to takeoff REPORT VB 423 PAGE 3 26 MODEL PA 34 200 FAA APPROVED March 10 1972 REVISED November 16 1972 SENECA ALTIMATIC 1 INSTALLATION 1 LIMITATIONS a Autopilot use is prohibited above 195 MPH CAS b Use of flaps is limited to 25 or less during autopilot operations Autopilot OFF for takeoff and landing 2 PROCEDURES a Preflight 1 Circuit breaker Set 2 Depress center bar Trim fore and aft 3 Manually override electric trim 4 Check manual trim operation 5 Depress center bar No operation 6 Push rocker Fore Aft only No operation 7 If trim fails preflight disengage electric trim by operating push button trim switch on instrument panel until repaired If trim does not disengage have unit repaired before further flight b Normal Operation Refer to the current AltiMatic IIIB 1 Owner s Handbook Emergency Operation 1 In the event of malfunction the autopilot can be a Disconnected by pushing the wheel disconnect switch AP OFF b Disconnected by pushing the roll rocker switch OFF Overpowered manually in roll and pitch at either control wheel 2 In the event of malfunction the trim system can be a Disabled by operating the push button trim switch on the instrument panel b Overpowered manually at the trim wheel 3 Single engine operation a Disengage autopilot and retrim aircraft
135. ime presented in the Compliance section of this AD accomplish the equirements of paragraphs a 1 and a 2 of this AD NOTE 2 Operators should initiate action to notify and ensure that flight crewmembers are apprised of this change 1 Revise the FAA approved Airplane Flight Manual AFM by incorporating the following into the Limitations Section of the AFM This may be accomplished by inserting a copy of this AD in the AFM WARNING Severe icing may result from environmental conditions outside of those for which the airplane is certificated Flight in freezing rain freezing drizzle or mixed icing conditions supercooled liquid water and ice crystals may result in ice build up on protected surfaces exceeding the capability of the ice protection system or may result in ice forming aft of the protected surfaces This ice may not be shed using the ice protection systems and may seriously degrade the performance and controllability of the airplane During flight severe icing conditions that exceed those for which the airplane is certificated shall be determined by the following visual cues If one or more of these visual cues exists immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the icing conditions Unusually extensive ice accumulation the airframe and windshield in areas not normally observed to collect ice Accumulation of ice on the upper of the
136. ince the autopilot when installed and operating may mask tactile cues that indicate adverse changes in handling characteristics use of the autopilot is prohibited when any of the visual cues specified above exist or when unusual lateral trim requirements or autopilot trim warnings are encountered while the airplane is in icing conditions All wing icing inspection lights must be operative prior to flight into known or forecast icing conditions at night NOTE This supersedes any relief provided by the Master Minimum Equipment List MMEL 2 Revise the FAA approved AFM by incorporating the following into the Normal Procedures Section of the AFM This may be accomplished by inserting a copy of this AD in the AFM THE FOLLOWING WEATHER CONDITIONS MAY BE CONDUCIVE TO SEVERE IN FLIGHT ICING Visible rain at temperatures below 0 degrees Celsius ambient air temperature Droplets that splash or splatter on impact at temperatures below 0 degrees Celsius ambient air temperature Page 2 94 99 14 01 PROCEDURES FOR EXITING THE SEVERE ICING ENVIRONMENT These procedures are applicable to all flight phases from takeoff to landing Monitor the ambient air temperature While severe icing may form at temperatures as cold as 18 degrees Celsius increased vigilance is warranted at temperatures around freezing with visible moisture present If the visual cues specified in the Limitations Section of the AFM for identifying sev
137. ine Lycoming Rated Horsepower Rated Speed rpm Bore in Stroke in Displacement cubic in Compression Ratio Dry Weight Ibs FUEL AND OIL Capacity U S gal Unusable fuel Fuel Aviation Grade minimum octane Oil Capacity qts each engine BAGGAGE AREA Maximum Baggage lbs Forward Compartment Maximum Baggage lbs Rear Compartment Baggage Space cubic ft Forward Compartment Baggage Space cubic ft Rear Compartment Baggage Door Size in Forward Compartment DIMENSIONS Wing Span ft Wing Area sq ft Length ft Height ft Wing Loading Ibs per sq ft Power Loading lbs per hp Propeller Diameter in 4200 4000 2625 1575 LIO 360 C1E6 IO 360 C1E6 200 2700 5 125 4 375 361 0 8 7 1 350 0 98 5 100 130 8 100 100 1243 24x2 38 88 208 7 28 5 20 1 10 5 76 GENERAL SPECIFICATIONS REVISED May 30 1975 SENECA LANDING GEAR Wheel Base ft 7 0 Wheel Tread ft 11 1 Tire Pressure ps1 Nose 3 Main 50 Tire Size Nose six ply rating 6 00 x 6 Main eight ply rating 6 00 x 6 GENERAL SPECIFICATIONS ISSUED March 10 1972 1 3 SENECA 12 p 64 DIAMETER 7 DINEDRAL mei _ 1 42 7 W 47 20 1 47 CENTER LINE MAIN SPAR STA 106 521 GENERAL SPECIFICATIONS 1 4 ISSUED March 10 1972 DESCRIPTION AIRPLANE AND SYSTEMS DESCRIPTION AIRPLANE AND SYSTEM The Airplane
138. ing Conditions and Item 18 Engine Failure With Rear Cabin and Cargo Doors Removed Added Item D Special Operating Procedures and Item D 1 Flight Into Known Icing April 26 1974 Conditions Added Item C Aircraft Performance With 74 H A Rear Cabin and Cargo Doors Removed _ D Trompler REPORT VB 423 PAGE 3 iv FAA APPROVED March 10 1972 MODEL PA 34 200 REVISED April 26 1974 SENECA LOG OF REVISIONS cont FAA Approved Revision Revised men and Revision Date Added PAC Approval Form Oct 14 1974 NOTE AIRCRAFT DELIVERED WITH MANUALS PRIOR TO THIS REVISION DO NOT REQUIRE THIS REVISION Wark Bone Ward Evans Revised usable fue quantities Item J May 30 1975 Usable Fuel Revised usable fuel capacity aller cap Ward Gane placard Ward Evans Added item 18 Propeller Overspeed revised page nos Revised Oi Pressure Red Line Minimum Added Maximum Landing Weight item G Added item 19 Propeller Overspeed relocated Special Operating Procedures Added page Special Operating Procedures from page 3 18 August 19 1975 Ward Evans Revised emergency gear extension placard Added item 4 b 1 c Deleted info under item 4 c Added item 4 a 3 Added item 9 and Warning relocated info to pg 3 15 Added items 12 3 and 4 fro
139. ing procedures for flight in icing conditions 1 Perform careful functional check of ice protection systems before flight Turn on Pitot Heat Windshield Heat and Propeller Heat for 30 seconds and feel for heat 2 Avoid forecast icing conditions when possible 3 When flying in clouds or precipitation monitor temperature closely 4 Turn on windshield defroster and pitot heat before entering icing conditions 5 Turn on Propeller Heat and Windshield Heat immediately upon entering icing conditions Cycle boots as required 6 Review Flight Manual procedures before any flight which might encounter icing conditions 7 Plan an alternate airport whenever flying ice OPERATING INSTRUCTIONS REVISED April 26 1974 6 13 SENECA EMERGENCY PROCEDURES Procedures for handling in flight emergencies and equipment malfunctions are detailed in the Airplane Flight Manual section These should be read and followed by the pilot PIPER AUTOMATIC LOCATOR The Piper Automatic Locator when installed is located in the aft portion of the fuselage just below the stabilator leading edge and is accessible through a plate on the right side of the fuselage If is an emergency locator transmitter which meets the requirments of FAR 91 52 The unit operates on a self contained battery The battery has a useful life of four years However it comply with FAA regulations it must be replaced after two years of shelf life or service life The battery s
140. is above freezing and is then continued into an air mass which is below freezing moisture which has collected in the air filter may subsequently freeze Since the alternate air system of the Seneca supplies heated air it is an excellent protection against induction icing if it is applied soon enough in an icing situation WARNING Flight in icing conditions is prohibited unless aircraft is equipped with approved deicing equipment If icing is encountered immediate action should be taken to fly out of icing conditions Icing is hazardous due to greatly reduced performance loss of forward visibility possible longitudinal control difficulties due to increased control sensitivity and impaired power plant and fuel system operation The ammeters for the electrical system should be monitored during flight especially during night or instrument flight so that corrective measures can be taken in case of malfunction The procedures for dealing with electrical failures are contained in the Airplane Flight Manual portion of this manual The sooner a problem is recognized and corrective action taken the greater is the chance of avoiding total electrical failure It is not recommended to take off into IFR operation with a single alternator During flight electrical loads should be limited to 50 amperes for each alternator Although the alternators are capable of 60 amperes output limiting loads to 50 amperes will assure battery charging current Sin
141. l selector of operating engine in ON position b Fuel selector of inoperative engine in OFF position c Electric fuel pumps OFF except in case of engine driven pump failure electric fuel pump on operating engine side must be used 2 When using fuel from tank on the side opposite the operating engine a Fuel selector of operating engine in X FEED CROSSFEED position b Fuel selector of inoperative engine in OFF position c Electric fuel pumps OFF except in case of engine driven pump failure electric fuel pump on operating engine side must be used 3 Use crossfeed in level flight only b Landing 1 Fuel selector of operating engine in ON position 2 Fuel selector of inoperative engine in OFF position 3 Electric fuel pump of operating engine ON REPORT VB 423 PAGE 3 12 FAA APPROVED March 10 1972 REVISED April 1 1977 SENECA 5 ENGINE FAILURE DURING TAKEOFF The single engine minimum control speed for this airplane is 80 mph CAS under sea level standard conditions a If engine failure occurs during takeoff ground roll and 100 mph CAS has not been attained CLOSE BOTH THROTTLES IMMEDIATELY AND STOP STRAIGHT AHEAD If inadequate runway remains to stop then 1 2 3 4 5 Throttles CLOSED Brakes apply maximum braking Master switch OFF Fuel selectors OFF Continue straight ahead turning to avoid obstacles as necessar
142. ling 50 fpm left engine out ft 5200 3650 Single Engine Absolute Ceiling left engine out ft 6600 5000 Top Speed mph knots 196 170 195 3 169 8 Cruising Speed 75 power at sea level mph knots 173 150 171 6 149 2 Cruising Speed 7595 power at 6000 mph knots 187 162 186 3 162 Optimum Cruising Speed 65 power 9000 mph knots 185 160 183 4 159 5 Stalling Speed gear and flaps down power off mph knots 67 58 69 60 Stalling Speed gear down and flaps up power off mph knots 73 63 5 76 66 Landing Roll flaps down ft short field 705 Landing Over 50 ft Barrier flaps down ft short field 1335 Fuel Consumption 75 power gph both engines 20 6 20 6 Fuel Consumption 65 power gph both engines 18 3 18 3 Cruising Range 75 power al 6000 ft mi 804 804 Cruising Range 65 power at 9000 ft mi 885 885 200 BHP Counter Rotating Engines 4200 Ib G W Maximum Take off Weight 4000 Ib G W Maximum Landing Weight 5000 Ft Single Engine Service Ceiling Occurs at 4030 Pounds Gross Weight This value applies only for the conditions stated on the Landing Distance vs Density Altitude Chart GENERAL SPECIFICATIONS REVISED May 30 1975 1 SENECA en WEIGHTS Gross Weight 155 Max Take off Max Landing Empty Weight Standard Ibs USEFUL LOAD Standard Ibs These weights are approximate POWER PLANT Right Engine Lycoming Left Eng
143. lled flight condition with power reduced on one engine The demonstration should not be performed at an altitude of less than 3500 feet above the ground Initiate recovery during the demonstration by immediately reducing power operating engine and promptly lowering the nose of the airplane More power is available on the operating engine at lower altitudes and hence there can be more asymmetric thrust The Vmc is highest at low altitudes Since Vmc decreases with altitude at higher altitudes the airplane will approach a stall before reaching Vmc The most critical situation occurs at the altitude where the stall speed and speed coincide Care should taken to avoid this flight condition because at this point loss of directional control occurs at the same time the airplane stalls and a spin could result OPERATING INSTRUCTIONS 6 12 ISSUED March 10 1972 99 14 01 99 14 01 THE NEW PIPER AIRCRAFT INC Amendment 39 11209 Docket No 98 CE 77 AD Supersedes AD 98 04 27 Amendment 39 10339 Applicability Models PA 23 PA 23 160 PA 23 235 PA 23 250 250 PA 30 PA 39 PA 31 PA 31 300 PA 31 325 BA 31 950 PAIT BAR S1T1 PA 31P 3590 34 200 34 200 34 220 42 42 720 and 42 1000 airplanes all serial numbers certificated in category NOTE 1 This AD applies to each airplane identified in the preceding applicability provision regardles
144. m pg 3 14 April 1 1977 Word Eana Ward Evans June 14 1983 Ward Ward Evans Added to Warning Added Caution FAA APPROVED October 14 1974 REPORT VB 423 PAGE 3 REVISED June 14 1983 MODEL PA 34 200 SENECA THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 423 PAGE 3 vi FAA APPROVED October 14 1974 MODEL PA 34 200 AIRWORTHINESS DIRECTIVE Q REGULATORY SUPPORT DIVISION U S Department 2 0 BOX 26460 of Transportation ALAHOMA CITY OKLAHOMA 73125 0460 Federal Aviation Administration E The following Airworthiness Directive issued by the Federal Aviation Administration in accordance with the provisions of Federal Aviation Regulations Part 39 applies to an aircraft model of which our records indicale you may be the registered owner Airworthiness Directives affect aviation safety and are regulations which require immediate attention You are cautioned thal no person may operate an aircraft to which an Airworthiness Directive applies except in accordance with the requirements of the Airworthiness Directive reference FAR Subpart 38 3 99 14 01 THE NEW PIPER AIRCRAFT INC Amendment 39 11209 Docket No 98 CE 77 AD Supersedes AD 98 04 27 Amendment 39 10339 Applicability Models PA 23 PA 23 160 PA 23 235 23 250 PA E23 250 PA 30 PA 39 40 31 PA 31 300 PA 31 325 31 350 PA 31P 31 PA 31T1 PA 31T2 PA 31P 350 PA 34 200 PA 34 200T
145. may settle and make contact with the ground because of lack of flying speed atmospheric conditions rolling terrain 3 In high density areas where high traffic pattern speeds are necessary OF when it 15 advantageous to extend the gear it is permissible to extend the landing gear al speeds up to 150 MPH 4 Flaps may be lowered at airspeeds up to 125 MPH To reduce flap operating loads it s desirable to have the airplane at a slower speed before extending the flaps 5 Before attempting to reset any circuit breaker allow a two to five minute cooling off period 6 Always determine position of landing gear by checking the gear position lights 7 Before starting the engine check that all radio switches light switches and the pitot heat switch are in the off position so as not to create an overloaded condition when the starter is engaged 8 A high fuel pressure indication on the fuel flow indicator is a possible sign of restricted fuel nozzles 9 The vacuum gauge is provided to monitor the pressure available to assure the correct operating speed of the vacuum driven gyroscopic flight instruments also monitors the condition of the common air filter by measuring the flow of air through the filter If the vacuum gauge does not register 5 10 Hg at 2000 RPM the following items should be checked before flight Common air filters could be dirty or restricted Vacuum lines could be collasped or broken Vacuum pumps worn
146. mb rate and a reduction of 850 feet in single engine service ceiling FAA APPROVED August 19 1975 REPORT VB 423 PAGE 3 18 REVISED June 14 1983 MODEL PA 34 200 SENECA CAUTION If the airplane is to be flown with the heated glass panel removed rotate the receptacle plate 180 and replace it to cover the holes in the fuselage skin Also replace the windshield collar screws REPORT VB 423 PAGE 3 18 FAA APPROVED August 19 1975 MODEL PA 34 200 REVISED June 14 1983 SENECA m i SECTION III PERFORMANCE A STALLS 1 POWER OFF STALLS The loss of altitude during a power off stall with gear and flaps retracted may be as much s 450 feet The loss of altitude with gear down and 40 of flaps may be as much as 450 feet 2 POWER ON STALLS The loss of altitude during a power on stall with gear and flaps retracted may be as much as 550 feet The loss of altitude with gear down and 40 of flaps may be as much as 400 feet 3 STALL WARNING SYSTEM The stall warning system is inoperative with the master switch off B STALLING SPEEDS MPH CALIBRATED AIRSPEED VS ANGLE OF BANK C AIRCRAFT PERFORMANCE WITH 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 FAA APPROVED March 10 1972 REPORT VB 423 PAGE 3 19 REVISED April 26 1974 MODEL PA 34 200 SENECA THIS PAGE INTEN
147. n Al 1 44 A TA AL a P 7 gt P DSH ERU I zum INIA SAA MAA NANA 1400 ALA DA aA TAKE OFF DISTANCE FEET nn 5 lt a Ail Vi RRS VCP LPL Ey 4000 SCIEN 2060 SL ENNA Tuy AA ri Hy OHHH ARES 2 40 60 80 4200 3800 3408 3000 6 18 28 TEMPERATURE F WEIGHT LBS HEADWIND MPH Example Temp 70 Wt 3600 lbs T O Dist 1350 ft Press Alt 4000 ft wind 10 MPH PERFORMANCE CHARTS 8 4 ISSUED March 10 1972 SENECA _ TARE OPF DISTANCE OVER 50 FY OBSTACLE AY VARIOUS ALTITUDES TEMPERATURES WEIGHTS AND WINDS FLAP SETTING 0 FULL POWER BEFORE BRAKE RELEASE LIFT OFF SPEED 80 MPH SHORT FIELD EFFORT BARRIER SPEED 85 MPH PAVED LEVEL DRY RUNWAY SCRE TA an AAA AAA NENERBENNG ACE E 761 506 rm IIND s NN AA TANI _ TTA S yA LZ LA e x TAKE OFF DISTANCE FEET EAS TOR en P E a x x F LA Z 0 25 40 60 BO 4200 3800 3400 3000 0 10 20 30 TEMPERATURE F GROSS WEIGHT LBS HEADWIND MPH Example Temp 70 Wt 3600 lbs Dist 1600 ft Press Alt 4000 ft Hd wind 10 MPH PERFORMANCE CHARTS ISSUED March 10
148. n Do not brush the micro switches CLEANING EXTERIOR SURFACES The airplane should be washed with a mild soap and water Harsh abrasive or alkaline soaps or detergents used on painted or plastic surfaces could make Scratches or cause corrosion of metal surfaces Cover areas where cleaning solution could cause damage To wash the airplane the following procedure may be used Flush away loose dirt with water Apply cleaning solution with a rag sponge or soft bristle brush To remove stubbom oil and grease use a cloth dampened with naphtha Where exhaust stains exist allow solution to remain on the surface longer Any good automotive wax may be used to preserve the painted surfaces Soft cleaning cloths or a chamois should be used to prevent scratches when cleaning or polishing A heavier coating of wax on the leading surfaces will reduce the abrasion problems in these areas CLEANING WINDSHIELD AND WINDOWS Remove dirt mud and other marks from exterior surface with clean water Wash with mild soap and warm water or an aircraft plastic cleaner Use a soft cloth or sponge using a straight rubbing motion Do not rub surface harshly Remove oil and grease with a cloth moistened with kerosene NOTE Do not use gasoline alcohol benzene carbon tetrachloride thinner acetone or window cleaning sprays After cleaning plastic surfaces apply a thin coat of hard polishing wax Rub lightly with a soft cloth Do not use a
149. n Combustion Heater Instl 3 11 3 21 3 29 Pages Changed Item 6 Landing Gear Unsafe Warnings Contents moved to Page 3 11 Contents moved to Page 3 12 May 25 1973 FAA APPROVED March 10 1972 REPORT VB 423 PAGE 3 iii REVISED May 25 1973 MODEL PA 34 200 SENECA LOG OF REVISIONS cont FAA Approved Revision Revised Pages Description and Revision Contents moved to Page 3 12a Added Page 4 FA Added Page H W Barnhouse Added Serial No effectivity sept 19 1973 Revised Item C Propeller Limitations Revised Tachometer Limitations W B rmhouse Added Item M Flight Into Known Icing Conditions and B 7 Rear Cabin and Cargo Doors Removed Added Item C 16 Engine Failure In Icing Conditions Item C 17 Alternator Failure In Icing Conditions Item C 18 Engine Failure With Rear Cabin and Cargo Doors Removed Item D Special Operating Procedures and Item D 1 Flight In Known Icing Conditions Added Item C Aircraft Performance With Rear Cabin and Cargo Doors Removed Added Icing Placard and relocated Weight Placard to page 3 4 Added Weight Placard from page 3 3 Added Placard for Aft Fuselage Doors Re moved and M Flight Into Known Icing Conditions Added Item 7 Rear Cabin and Cargo Doors Removed Revised Item c Added Item 16 Engine Failure In Icing Conditions Item 17 Alternator Failure In Ic
150. n case the battery becomes depleted from a weakened condition or from excessive restart cranking it may be necessary to perform the following procedure to get an operating alternator on the line if it has become disconnected for any reason 1 Check alternator circuit breakers reset if tripped 2 Remove heavy electrical loads such as pitot head lighting blower motor minimize radio load Do not use master switch to accomplish this 3 Turn operating alternator switch to on Turn master switch to off Wait a short time period then cycle master switch to on Observe ammeter for output 4 If no output is noted recycle step 3 using longer waiting periods 5 When power is reestablished use electrical equipment so that 50 amperes is not exceeded d Incase of loss of output from one alternator 1 Reduce electrical load as necessary to keep alternator output to 50 amperes or less 2 Check alternator circuit breakers reset if necessary 3 Cycle the alternator switch for the inoperative alternator OFF then ON 4 If step 3 fails to restore output a Maintain conditions of step 1 to continue flight b Take corrective maintenance action before further flights e In case of alternator output loss due to an engine failure reduce the electrical load as necessary to keep the alternator output to 50 amperes or less WARNING Compass error may exceed 10 with both alternators inoperative FAA APPROVED March
151. n precision instrument approach GPS Loran C VOR VOR DME TACAN NDB NDB DME RNAV operation within the U S National Airspace System in accordance with AC 20 138 of the approved sensors for a single or dual GNS 530 installation for North Atlantic Minimum Navigation Performance Specification MNPS Airspace in accordance with AC 91 49 and AC 120 33 e system meets 5 airspace BRNAV requirements of AC 90 96 and in accordance with AC 20 138 and JAA AMJ 20X2 Leaflet 2 Revision 1 provided it is receiving usable navigation information from the GPS receiver Navigation is accomplished using the WGS 84 NAD 83 coordinate reference datum Navigation data is based upon use of only the Global Positioning System GPS operated by the United States of America TAMPA FSDO FAA APPROVED DATE 07 0 190 00181 04 Rev B Tomlinson Avionics Inc PH 941 936 6969 511 Danley Page Field Ft Myers FL 33907 Repair Station NO YN1D644K Aircraft Make 2 _ GARMIN GNS 530 VHF Communications Aircraft Model 263 200 Transceiver VOR ILS Receiver GPS Receiver Aircraft Serial Number GL 772 PEAD ES 8757 SECTION II LIMITATIONS The GARMIN GNS 530 Pilot s Guide P N 190 00181 00 Rev A dated April 2000 or later appropriate revision must be immediately available to the flight crew whenever navigation is predicated on the use of the system 2 The GNS 530 must utilize the following o
152. nal transmitter The locator should be checked during the Ground Check to make certain the unit has not been accidently activated Check by tuning a radio receiver to 121 5 MHz If you hear an oscillating audio sound the locator may have been activated and should be turned off immediately Reset to ARM position and check again to insure against outside interference Optional eqiupment OPERATING INSTRUCTIONS 6 14 REVISED MARCH 23 1979 EAS ie tne e ENS L at aide A er PC A ur im A SA v m I t a a gt Nae zu 5 aa EI DN NX TET TET PLA E e Vui M F LJ TE E t M FT atte EL d PN S Al wf ne L 4 1 CIEL gt 2 x 3 Iu VE e ri EF ow ae 1 m zi M A n 2 E dh Operating Tips OPERATING TIPS pe A ALAS FE A AAA O IAS HA BLANK PAGE SENECA OPERATING TIPS The following Operating Tips are of particular value in the operation of the Seneca 1 Learn to trim for take off so that only a very light back pressure on the wheel is required to lift the airplane off the ground 2 On take off do not retract the gear prematurely The airplane
153. ncrease 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 during cold weather Dry nitrogen gas is recommended CHAMBER PRESSURE REQUIREMENTS WITH TEMPERATURE FOR COUNTERWEIGHT TYPE PROPELLERS Press PSI 2 Press 51 NOTE Do not check pressure or charge with propeller in feather position HANDLING AND SERVICING 9 6 ISSUED March 10 1972 SENECA MEN OIL REQUIREMENTS The oil capacity of the Lycoming engines is 8 quarts with minimum safe quantity of 2 quarts It is recommended that engine oil be drained and renewed every 50 hours or sooner under unfavorable conditions Intervals between oil changes can be increased as much as 100 on engines equipped with full flow cartridge type oil filters provided the element is replaced each 50 hours of operation The following grades are required for temperatures Temperatures above 60 F 5 50 Temperatures between 30 and 90 F S A E 40 Temperatures between 0 F and 70 S A E 30 Temperatures below 10 F S A E 20 FUEL SYSTEM The fuel screens in the strainers require cleaning at 50 hour or 90 day intervals whichever first occurs The fuel gascolator strainers are located between the fuel selector valves and the auxiliary boost pumps in the nacelles The fuel injector screen is located in the housing where the fuel inlet line conn
154. nder the engine to catch waste b With the engine cowling removed spray or brush the engine with solvent or mixture of solvent and degreaser as desired It may be necessary to brush areas that were sprayed where heavy grease and dirt deposits have collected in order to clean them 2 CAUTION Do not spray solvent into the alternator vacuum pump Starter or air intakes c Allow the solvent to remain on the engine from five to ten minutes Then rinse the engine clean with additional solvent and allow to dry CAUTION Do not operate engine until excess solvent has evaporated or otherwise been removed d Remove the protective covers from the magnetos e Lubricate controls bearing surfaces etc per Lubrication Chart HANDLING AND SERVICING ISSUED March 10 1972 9 3 SENECA CLEANING LANDING GEAR 9 4 Before cleaning the landing gear place plastic cover or similar material over the wheel and brake assembly a b Place a pan under the gear to catch waste Spray or brush the gear area with solvent or a mixture of Solvent and degreaser as desired It may be necessary to brush areas that were sprayed where heavy grease and dirt deposits have collected in order to clean them Allow the solvent to remain on the gear from five to ten minutes Then rinse the gear with additional solvent and allow to dry Remove the cover from the wheel and remove the catch pan Lubricate the gear per Lubrication Chart Cautio
155. nel Wing icing conditions may be detected during night flight with the use of an ice detection light installed in the outboard side of the left engine nacelle The light is controlled by an ICE LIGHT switch located on the instrument panel to the right of the SURFACE DE ICE switch A WING ICE LIGHT circuit breaker located in the circuit breaker panel provides circuit protection Electrothermal propeller deicer pads are bonded to the leading edges of the propeller blades Each deicer pad has two separate heaters one for the outboard and one for the inboard half The system is controlled by an ON OFF type PROP DE ICE switch located to the right of the SURFACE DE ICE switch above the control quadrant Power for the propeller deicers is supplied by the airplane s electrical system through a PROP DE ICE circuit breaker located in the circuit breaker panel to the PROP DE ICE switch When the PROP DE ICE switch is actuated power is supplied to a timer through the PROP DE ICER ammeter which monitors the current through the propeller deicing system With the propeller deicing system ON the PROP DE ICER ammeter needle should be within the shaded portion on the ammeter for a normal reading Opuonal equipment AIRPLANE AND SYSTEMS 2 22 REVISED April 26 1974 1581 PLoL 97 tidy SAALSAS NV ANVIdUIV 154 UONDIOIg 39 PNEUMATIC DEICER BOOTS PNEUMATIC DEICER BOOTS ANTI IC
156. ng and an overflow line from the top of each filler neck AIRPLANE AND SYSTEMS 2 10 REVISED MARCH 23 1979 SENECA NA SNIVYO INGA 073 7303 Nar SIT X S BIdAIG MOTI 2 80123135 LNIOd lt Tb BAIVA 80193135 71304 1313 58415913 71313 531220 Fuel Schematic AIRPLANE AND SYSTEMS ISSUED March 10 1972 2 11 SENECA ELECTRICAL SYSTEM The electrical system of the Seneca ts capable of supplying current for complete night IFR equipment Electrical power is supplied by two 60 ampere alternators one mounted on each engine A 35 ampere hour 12 volt battery provides current for starting for use when the engines are not running and for a source of stored electrical power to back up the alternator output The battery which is located in the nose section and 15 accessible through the forward baggage compartment is normally kept charged by the alternators If it becomes necessary to charge the battery it should be removed from the airplane An external power source plug is available as optional equipment and when installed is located on the lower left side of the nose While an external 12 14 volt power source is being plugged in or unplugged the master switch should be in the OFF position to prevent sparking The master switch should be in the ON position
157. ngle Engine _ 90 Feet Pitch Trim 3 If Trim Warning Light illuminates in flight pull the Pitch Trim Disconnect switch and have system inspected poor to operation 4 If a runaway trim should occur with autopilot on the electric trim circuit breaker will open with an out of trim condition of approximately 15 105 3 PERFORMANCE The airplane performance remains unchanged FAA APPROVED July 7 1972 REPORT VB 423 PAGE 3 27 REVISED November 16 1972 MODEL PA 34 200 SENECA WINDSHIELD HEATING INSTALLATION LIMITATIONS UNDER NO CIRCUMSTANCES SHOULD THE UNIT BE TURNED ON FOR A PERIOD EXCEEDING 30 SECONDS UNLESS The aircraft is in flight or b Ice exists on the heated panel 2 PROCEDURES An operational check is accomplished by turning the heated panel switch ON for a period not exceeding 30 SECONDS Proper operation is indicated by the glass section being warm to the touch 3 PERFORMANCE NOTE An additional compass deviation card is required with this installation This card should indicate corrected readings with windshield heat and radios on REPORT VB 423 PAGE 3 28 FAA APPROVED July 7 1972 MODEL PA 34 200 REVISED September 15 1972 SENECA CABIN COMBUSTION HEATER 1 LIMITATIONS a The use of windshield electric anti ice and cabin combustion heater at the same time is prohibited due to excessive compass error b Placards Near the heater controls in full view of the pilot Operation of
158. ngs Also incorporated in the system is a check valve which is located behind the instrument panel on the upper right side of the baggage compartment bulkhead If suction is lost from either vacuum pump or from a leak in the hose of either side the valve automatically closes and vacuum is supplied by one pump In this case one of two red malfunction buttons appears on the face of the vacuum gauge indicating that vacuum is not available from that side Each pump alone has sufficient capacity to operate a dual set of gyro instruments up to a 12 500 foot altitude When operating with a single vacuum pump above that altitude a high RPM setting must be maintained to get adequate suction for dual flight instruments Air filters are incorporated in the vacuum system to increase the life of the gyros They are mounted behind the instrument panel in the upper corners of the baggage compartment and should be cleaned regularly Optional Equipment AIRPLANE AND SYSTEMS 2 16 REVISED April 26 1974 9310551 161 OL IE SWALSAS UNV 11 218019455 VACUUM MANIFOLD CHECK VALVES CENTRAL AIR FILTER DIRECTIONAL GYRO ARTIFICIAL HORIZON REGULATOR u p REGULATOR hL VACUUM GAGE LEFT ENGINE RIGHT ENGINE sa VACUUM PUMP VACUUM PUMP VOHNAS SENECA INSTRUMENT PANEL The wide instrument panel of the Seneca offers sufficient space
159. nity of other aircraft ao oP OPERATING TIPS 7 1 REVISED August 19 1975 SENECA Se eae ae eT 55 13 In effort to avoid accidents pilots should obtain and study the safety related information made available in FAA publications such as regulations advisory circulars Aviation News AIM and safety aids Sluggish RPM control and propeller overspeed with poor RPM recovery after rapid throttle application are indications that nitrogen pressure in the propeller dome 15 low Experience has shown that the training advantage gained by pulling a mixture control or turning off the fuel to simulate engine failure at low altitude is not worth the risk assumed Therefore it is recommended that instead of using either of these procedures to simulate loss of power at low altitude the throttle be retarded slowly to idle position Fast reduction of power may be harmful to the engine OPERATING TIPS REVISED April 1 1977 PERFORMANCE CHARTS a gt PERFORMANCE CHARTS Altitude Conversion TUTO 8 1 Take off Ground Run Distance Flap Setting 0 msn nennen A 8 2 Take off Ground Run Distance Flap Setting 25 A O P 8 3 Take off Distance Over 50 Ft Flap Setting 259 8 4 Take off Distance Over 50 Ft Flap Setting 0 eene 8 5 Accelerate Stop Distance
160. nts no danger to other aircraft When parking the airplane for any length of time or overnight it is recommended that it be moored securely a To park the airplane head it into the wind if possible b Set the parking brake HANDLING AND SERVICING ISSUED March 10 1972 9 SENECA Minimum Turning Radius NOTE Care should be taken when setting brakes that are overheated or during cold weather when accumulated moisture may freeze a brake MOORING The airplane should be moored to insure its immovability protection and security under varying weather conditions The following procedure should be used for proper mooring of the airplane a Head the airplane into the wind if possible b Lock the aileron and stabilator controls using the control wheel lock or control surface blocks E c Block the wheels d Secure tie down ropes to the wing tie down rings and the tail skid at approximately 45 degree angles to the ground f HANDLING AND SERVICING 9 2 ISSUED March 10 1972 SENECA CAUTION Use bowline knots Do not use slip knots NOTE Additional preparations for high winds include using tie down ropes from the landing gear forks and securing the rudder e Install pitot tube cover if possible CLEANING CLEANING ENGINE COMPARTMENT Before cleaning the engine compartment place a strip of tape on the magneto vents to prevent any solvent from entering these units a Place a large pan u
161. o as to keep within allowable limits If is it necessary to remove some of the fuel or payload to stay within maximum allowable gross weight the pilot should not hesitate to do so ghing an airplane in production and in computing basic weight basic C G position and useful load Note that the useful load includes fuel oil baggage cargo and passengers Following these are 1 a method for computing takeoff weight and C G if precision is desired if a plotter is not available or if cargo is carried and 2 an explanation of how to use the weight and balance plotter The following pages are forms used in wei On one side of the weight and balance plotter are some general loading recommendations which will assist the pilot in arranging his load If these are followed much time can be saved without degrading safety REPORT VB 424 PAGE 4 2 ISSUED March 10 1972 MODEL PA 34 200 REVISED MARCH 23 1979 SENECA WEIGHT AND BALANCE DATA WEIGHING PROCEDURE At the time of delivery Piper Aircraft Corporation provides each airplane with the licensed empty weight and center of gravity location The removal or addition of an excessive amount of equipment or excessive airplane modifications can affect the licensed empty weight and empty weight center of gravity The following is a weighing procedure to determine this licensed empty weight and center of gravity location 1 PREPARATION a Be certain that all items checked in the
162. ommended in the Lycoming Operator s Manual for this engine in order to obtain maximum engine efficiency and time between engine overhauls PULL CLOSE COWL FLAP PUSH OPEN Cowl Flap Control AIRPLANE AND SYSTEMS ISSUED March 10 1972 2 3 SENECA The gear system incorporates a number of features Gear extension can be accomplished even in the event of hydraulic failure since the gear is held up by hydraulic pressure If the hydraulic system develops a leak or if the pressure is relieved for any reason gravity will cause the gear to extend Aerodynamic loads and springs assist in extending and locking the gear down When the landing gear is retracted the main wheels fold toward the centerline of the airplane and the nose gear retracts forward Once the nose gear has started toward the down position the airstream pushes against it and assists in moving it to the locked position When the three gears are down and the downlock hooks engage a spring maintains force on each hook in the locked position until it is released by hydraulic pressure To get the gear to extend and lock if the hydraulic pump fails it is necessary only to relieve the hydraulic pressure An emergency gear extension knob located near the center of the instrument panel is provided for this purpose Pulling this knob releases the hydraulic pressure which holds the landing gear in the up position and the gear can then fall free A guard over the knob 15 provided to
163. or that an entire page was added Black lines will indicate only current revisions with changes and additions to or deletions of existing text and illustrations Changes in capitalization spelling punctuation or the physical location of material on a page will not be identified by symbols III Original Pages Issued The original pages issued for this manual prior to revision are given below 1 1 through 14 2 1 through 2 22 3 1 through 3 26 4 1 through 4 34 6 1 through 6 14 7 1 8 1 through 8 16 9 1 through 9 11 REVISIONS ISSUED Current Permanent and Temporary Revisions to the PA 34 Pilot s Operating Manual issued March 10 1972 are as follows 761 506 PR720508 761 506 PR720707 761 506 PR720802 761 506 PR720802 761 506 PR720915 761 506 PR721116 761 506 PR721220 761 506 721221 761 506 730525 761 506 PR730919 761 506 PR731026 761 506 PR740426 761 506 PR741014 761 506 PR750530 761 506 PR750819 761 506 770401 761 506 PR790323 761 506 PR83061 4 Permanent Revision to F M Permanent Revision Permanent Revision to W B Permanent Revision to F M General Specifications Permanent Revision to F M Permanent Revision to F M amp WIB Permanent Revision to F M amp P O M Permanent Revision to W B Permanent Revision to F M amp W B Permanent Revision to F M W B and P O M Permanent Revision to P O M Permanent Revision to F M W B and P
164. ositions 10 25 and 40 degrees Console AIRPLANE AND SYSTEMS JSSUED March 10 1972 2 9 SENECA FUEL SYSTEM The Seneca fuel system offers two 24 5 gallon aluminum tanks in each wing which are interconnected to eliminate probelms of tank selection and fuel management Both tanks in each wing are filled with a single opening in the outboard tank and fuel from the outboard tank flows into the mboard tank as the fuel from the inboard tank is consumed The 98 gallon fuel capacity has only 2 1 2 unusable gallons on each side making a total of 93 usable gallons The fuel must to 100 130 octane light green An engine driven fuel pump 15 the primary means of supplying fuel for each engine An electric fue pump located on the aft side of the firewall is provided for each engine as a back up in case of engine driven fuel pump failure The electric pump should be used during landings and take offs to ensure sufficient fuel pressure in case of an engine driven fuel pump failure during these portions of the flight sequence Switches for the electric fuel pumps are conveniently located on the switch panel to the left of the pilot In normal operation each engine operates with an independent fuel system drawing fuel from the tanks in the wing on the same side as the engine However the two systems are interconnected by crossfeed lines which will permit an engine to use fuel from the tanks on the opposite side in order to extend single
165. ottle controls should be retarded to check the gear warning horn Flying the airplane with the horn inoperative is not advisable It can lead to a gear up landing as it is easy to forget the landing gear especially when approaching for a single engine landing when other equipment is inoperative or when attention is drawn to events outside the cabin Prior to entering the traffic pattern the aircraft should be slowed to approximately 115 MPH and this speed should be maintained on the downwind leg The landing check should be performed on the downwind leg 1 Seat backs erect Seat belts and shoulder harness fastened Fuel selectors ON Cowl flaps set as required Electric fuel pumps on Mixture controls rich Propellers set to 2500 RPM Landing gear down three green lights and nose wheel in mirror Flaps set as required 125 MPH maximum airspeed The landing gear should be lowered at speeds below 150 MPH and the flaps at speeds as follows 10 first notch 160 MPH maximum 25 second notch 140 MPH maximum 40 third notch 125 MPH maximum Maintain a speed of 115 MPH on the downwind leg 110 MPH on base leg 110 MPH during the turn onto final approach and 95 MPH on final approach If the aircraft is lightly loaded the final approach speed may be reduced to 90 MPH When the power is reduced on close final approach the propeller controls may be advanced to the full forward position to prov
166. p to reduce wing and flap damage Close the throttles just before touchdown Turn off the master and ignition switches Turn fuel selector valves to OFF Contact the surface at minimum airspeed Tp 12 ELECTRICAL FAILURES a In the event that both overvoltage lights illuminate 1 Tum off all electrical loads except the master switch 2 Turn both alternator switches OFF to extinguish the warning lights Turn the alternator switches momentarily ON one at a time while observing the ammeters b Determine the alternator showing the LEAST Output amperes and turn its switch ON REPORT VB 423 PAGE 3 14 FAA APPROVED March 10 1972 MODEL PA 34 200 REVISED April 1 1977 SENECA 3 Turn electrical equipment on as required but do not exceed 50 amperes output 4 If both alternators show approximately equal output less than 50 amperes each a Turn both alternators ON b Turn equipment on as required Resume normal operation b In the event that one overvoltage light illuminates 1 Turn off all electrical loads except the master switch 2 Turn off the alternator switch associated with the overvoltage trip warming 3 While observing ammeters turn the alternator switch momentarily on to verify that the alternator output is excessive then leave the alternator switch in the off position 4 Turn electrical equipment on as required but do not exceed 50 amperes output c I
167. pU O O 4d THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 423 PAGE 3 10 FAA APPROVED March 10 1972 MODEL PA 34 200 REVISED May 25 1973 SENECA EMERGENCY PROCEDURES 1 DETECTING A DEAD ENGINE a Loss of Thrust b Nose of aircraft will yaw in direction of dead engine with coordinated controls 2 FEATHERING PROCEDURE The propellers can be feathered only while the engine is rotating above 800 RPM Loss of centrifugal force due to slowing RPM will actuate a stop pin that keeps the propeller from feathering each time the engine is stopped on the ground Single engine performance will decrease if the propeller of the inoperative engine is not feathered NOTE If circumstances permit in the event of an actual engine failure the pilot may elect to attempt to restore power prior to feathering The following actions are su ggested 1 Mixture As Required 2 Fuel Boost Pump On 3 Fuel Selector Crossfeed 4 Magnetos Select L or R only 5 Alternate Air On Minimum Control Speed 80 MPH Best R C Speed Single Engine 105 MPH Maintain Direction and Airspeed above 90 MPH Mixture Controls forward Propeller Controls forward Throttle Controls forward Flaps retract Gear retract Electric Fuel Pumps ON Identify inoperative engine Throttle of inoperative engine retard to verify Propeller of inoperative engine feather Mixture of inoperative engine i
168. ptional on the right set of rudder pedals and handle operated brake cylinder located below and behind the left center of the instrument panel The parking brake is actuated by pulling back on the handle and pushing forward on the button to left of the handle The brake can be released by pulling aft on the handle without touching the button and allowing the handle to swing forward PULL TO RELEASE SEE ATM GEAR EXTEXS 10 BEFORE RE EXCAGEMENT Landing Gear Actuator AIRPLANE AND SYSTEMS 2 6 REVISED April 1 1977 SENECA RIGHT MAIN GEAR LEFT MAIN GEAR B HYDRAULIC CYLINDER HYDRAULIC CYLINDER UP RESTRICTOR 1 DOWN DOWN NOSE GEAR HYORAULIC r CYLINDER dere PRESSURE tt SWITCH f RESTRICTOR CHECK VALVE FREE FALL CONTROL RETRACTION Vn RELIEF TORRE a Eur att A AA HIGH H PRESSURE CONTROL RESERVOIR NOT USED LOW PRESSURE CONTROL GEAR UP CHECK VALVE Hydraulic System Schematic AIRPLANE AND SYSTEMS ISSUED March 10 1972 2 7 SENECA LANDING GEAR i 5 ELECTRO HYDRAULIC PUMP MOTOR dr A 5 TERMINAL 2 LANDING GEAR CONTROL PRESSURE m u 6 SWITCH WARNING 5 AMP SQUAT SWITCH 5 GEAR SELECTOR SWITCH NAV LIGHTS Landing Gear Electrical Schematic AIRPLANE AN
169. r door latched 18 Left static vent unobstructed 19 Dorsal fin air scoop free of obstruction 20 Empennage no damage free of ice hinges secure 21 Stabilator freedom of motion 22 Right static vent unobstructed 23 Antennas secure and undamaged 24 Navigation and landing lights check after master switch and light switches have been turned on in cabin 30 SAS ROM von ANAL OPERATING INSTRUCTIONS 6 2 REVISED NOVEMBER 30 1987 SENECA TAX Before taxiing the brakes should be checked by moving forward a few feet throttling back and applying pressure on the toe pedals As much as possible turns during taxiing should be made using rudder pedal motion and differential power more power on the engine on the outside of the turn less on the inside engine rather than brakes The following equipment may be checked during taxiing 1 Instruments turn indicator directional gyro coordination 2 Heater and defroster especially important on a cold day 3 Fuel selector Place each selector on CROSSFEED for a short time while the other selector is in the ON position Return selectors to the ON position Do not attempt takeoff with selector on CROSSFEED The autopilot if installed should be off during taxiing and the electric fuel pump should be off in order to check the operation of the engine driven fuel pump PRETAKE OFF
170. r later FAA approved software versions 5 The Main software version is displayed the GNS 530 self test page immediately after turn on for 5 seconds The remaining system software versions can be verified on the AUX group sub page 2 SOFTWARE DATABASE VER 3 IFR enroute and terminal navigation predicated upon the GNS 530 s GPS Receiver is prohibited unless the pilot verifies the currency of the data base or verifies each selected waypoint for accuracy by reference to current approved data 4 Instrument approach navigation predicated upon the GNS 530 GPS Receiver must be accomplished in accordance with approved instrument approach procedures that are retrieved from the GPS equipment data base The GPS equipment database must incorporate the current update cycle a Instrument approaches utilizing the GPS receiver must be conducted in the approach mode and Receiver Autonomous Integrity Monitoring RAIM must be available at the Final Approach Fix b Accomplishment of ILS LOC LOC BC LDA SDF MLS or any other type of approach not approved for GPS overlay with the GNS 530 s GPS receiver is not authorized c Use of the GNS 530 VOR ILS receiver to fly approaches not approved for GPS requires VOR ILS navigation data to be present on the external indicator TAMPA FSDO FAA APPROVED DATE DEC 07 2001 PAGE 4 OF 8 190 00181 04 Rev B Tomlinson Avionics inc PH 941 936 6965 511 Danley Page r eld Ft Myers F
171. roach with full flaps 40 degrees and partial power until shortly before touch down Hold the nose up as long as possible before and after contacting the ground with the main wheels Short Field Landin Approach with full flaps at 87 MPH CAS Immediately after touch down raise the flaps apply back pressure to the wheel and apply brakes Crosswind or High wind Landing Approach with higher than normal speed and with zero to 25 degrees of flaps Immediately 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 lower the wing that is into the wind to eliminate the crab angle without drifting and use the rudder to keep the wheels aligned with the runway Avoid prolonged side slips with a low fuel indication The maximum erosswind component for landing is 15 MPH POST LANDING After leaving the runway 1 Wing flaps retract 2 Cowl flaps fully open 3 Electric fuel pumps off SHUT DOWN Radio and electrical equipment off Mixture controls idle cut off Magneto switches off Master switch off Parking brake on ww No OPERATING INSTRUCTIONS ISSUED March 10 1972 6 11 SENECA AIRSPEED DATA All airspeeds quoted in this manual are calibrated unless otherwise noted Calibrated airspeed is indicated airspeed corrected for instrument and position errors The following table gives the correlation between indicated airspeed and
172. s manual is applicable to Piper Model PA 34 200 aircraft having serial numbers 34 7250001 through 34 7250189 when Piper Kit 760 607 is installed 34 7250190 through 34 7250214 when Piper Kit 760 611 is installed and 34 7250215 through 34 7350353 Contact Piper Customer Services for specific information on the application of this manual REVISIONS The information compiled in the Mot s Operating Manual will be kept current by revisions distributed to the airplane owners Revision material will consist of information necessary to update the text of the present manual and or to add information to cover added airplane equipment I Revisions Revisions will be distributed whenever necessary as complete page replacements or additions and shall be inserted into the manual in accordance with the instructions given below Revision pages will replace only pages with the same page number 2 Insert all 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 Identification of Revised Material Revised text and illustrations shall be indicated by a black vertical line along the left band margin of the page opposite revised added or deleted material A line opposite the page number or section title and printing date will indicate that the text illustration was unchanged but material was relocated to a different page
173. s of whether it has been modified altered or repaired in the area subject to the requirements of this AD For airplanes that have been modified altered or repaired so that the performance of the requirements of this AD is affected the owner operator must request approval for an alternative method of compliance in accordance with paragraph d of this AD The request should include an assessment of the effect of the modification alteration or repair on the unsafe condition addressed by this AD and if the unsafe condition has not been eliminated the request should include specific proposed actions to address it Compliance Required as follows unless already accomplished 1 For all affected airplanes except for Models PA 31P PA 31T 31 1 PA 31T2 and PA 31P 350 airplanes Within 30 days after March 13 1997 the effective date of AD 98 04 27 2 For all Models PA 31P PA 31T PA 31T1 PA 31T2 and PA 31P 350 airplanes Within the next 30 days after the effective date of this AD minimize the potential hazards associated with operating the alrplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions accomplish the following At the applicable compliance time presented in the Compliance section of this AD accomplish the requirements of paragraphs 1 and 2 of this AD NOTE 2 Operators should initiate action to notify and ensure
174. se Color _ Registration No Color Trim Color Type Finish Accent Color Weight and moment difference between standard and optional equipment ISSUED December 21 1972 REPORT VB 424 PAGE 4 35 REVISED April 1 1977 MODEL PA 34 200 SENECA THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 424 PAGE 4 36 ISSUED December 21 1972 MODEL PA 34 200 4 i k VN 4 a 4 7 NEN S u TE E AT a Es EL Ls z A 4 tO IL fI EM ee wos LI reda P is 4 E r 2 gt M ELE a el 5 x To PL Ee te ud Lora p See Lar ANAL o o E LE err Aw i V 222 t El s 3 hy Ti Y r Aa 13 Se 4 ree tt 4 4 Be X nar cs 7 AD Ose VII T Sash UL DO Joly ts 152 M e NU rez e d PELA wl x n de gt mh jr oh F ar A t n er E eure gt as A i t E ag y A CHAR VEN nnl 1 3 v re z 1 4 Lis IA AME 7 gd lt A 41 Ilis
175. sion Revised Pages July 7 1972 Corrected AltiMatic 1 totals Added page Added page Added Narco Nav 14 W Bamhouse July 10 1972 94 2 Ense W Bamhouse Correct Instrument Specification Numbers Changed from Turn and Bank Piper 99005 Turn and Slip Indicator PS50030 2 or 3 Changed Instrume nt Specification Numbers 4 August 2 1972 Added page Added New Nose Wheel 40 76B Added page Added page Added Rear Seat Belts Cargo Door Right Front Seat 96806 5 Center Seats 96827 2 3 Rear Seats 99730 2 3 968274 5 Removed Lights Landing Navigation Grimes 15 0083 1 Instrument and Forward Baggage Removed Power Supply No A412A 14 Fin Tip and Cable Added King KX 175 King 7 and KN77 Added King KT76 78 and KMA 20 Added Jumpseat 69595 5 Fire Extinguisher Sun Visors amp Tow Bar Removed Rear Seats amp Rear Seat Belts Removed Fire Extinguisher Sun Visors Tow Bar amp Cargo Door Added Adjustable Front Seats 69568 2 amp 3 and Headrests 96806 17 Sept 15 1972 24 Manas Nov 16 1972 4 34 Added Windshield Heating Unit Changed from V FD to V FD AltiMatic Changed from V to V 1 AltiMatic Changed Comm Antenna Cable Arms and Moments Added Anti Static Kit ISSUED March 10 1972 REPORT VB 424 PAGE 4 1ii REVISED November 16 197
176. sssesersresecenseceoreees 3 28 Cabin Combustion Heater Installation ere eeu 3 29 REPORT VB 423 PAGE 3 ii FAA APPROVED March 10 1972 MODEL PA 34 200 REVISED August 19 1975 SENECA LOG OF REVISIONS Approved Revision Revised Pages Description and Revision Date Changed wording for Items 6 and 10 Changed Item 6 Landing Gear Unsafe Warnings Changed Item 10 Landing Gear Unsafe Warnings Mrs 1972 Wn 1 E W Barnhouse 3 Under Section IV added item Added AltiMatic V FD Installation Added entire contents of page Added page Added page July 7 1972 ee uo W Barnhouse Changed page nos under Item C Section Note added Contents rearranged Contents rearranged 2 2 1972 W Barnhouse Added item E Windshield Heating Installation to Section Added Windshield Heating Placards Added E Windshield Heating Installation Sept 15 1972 Corrected Item D under Section IV Nov 16 1972 Corrected Item D Changed D to V FD 1 or V 1 Changed D 2 b to V FD or V 1 Information Manual for Duo W Bamhouse Dec 20 1972 H W Barntiouse Added Supplement F Added F Cabi
177. sssesreerousenorennesmssevsoeeornsscenecoonosroes 1 2 ee Eee Foel and aan 1 2 AA M 1 2 Dimension nn are A a sal o eis sna nacen Eo Kd 1 2 Landing Gear BLANK PAGE SENECA RENE nes GENERAL SPECIFICATIONS PERFORMANCE Published figures are for Standard PA 34 airplanes flown at gross weight under standard condition at sea level unless otherwise stated Performance for a specific airplane may vary from published figures depending upon the equipment installed the condition of engines airplane and equipment atmospheric conditions and piloting technique Gross Weight pounds 4000 4200 Take off Run ft short field effort flaps 25 750 800 Take off Distance Over 50 ft Barrier ft short field effort flaps 25 1140 1235 Minimum Controllable Single Engine Speed mph 80 80 Best Rate of Climb Speed mph knots 22105 91 5 105 91 5 Best Rate of Climb ft per min 1460 1360 Best Angle of Climb Speed mph knots 90 78 90 78 Best Single Engine Rate of Climb Speed mph knots 105 91 5 105 91 5 Single Engine Rate of Climb S L ft per min 230 190 Service Ceiling it 18 800 17 900 Absolute Ceiling ft 20 000 19 400 Single Engine Service Cei
178. st Corp No C52207 4 2 Ibs each 4 80 2 32 TC A7SO Hom Stall Warn Safe Flight 53514 101 0 2 64 6 13 TSO C30b _ Horn Gear Wam Safe Flight 2024 1 0 2 61 5 12 TSO C30b Switch Landing Gear Selector lt Cutler Hammer 8906 1736 0 1 67 7 7 TC A7SO Two Voltage Regulators Wico Electric No 18150 X 1 01bs each 2 0 49 4 99 TC A7SO Electrodelta No VF 710 0 5 Ibs each 1 0 49 4 49 4 TC A7SO Two Overvoltage Relays Piper NO 550034 1 5 lbs each 1 0 49 1 49 75 Two Starter Relays Piper Dwg 99130 2 1 1 lbs each 22 41 5 91 TC A7SO REPORT VB 424 PAGE 4 16 ISSUED MARCH 10 1972 MODEL PA 34 200 REVISED NOVEMBER 30 1987 SENECA Weight Arm Aft Cert Item Item Lbs Datum Moment Basis D Electrical Equipment cont Two Landing Lights G E Model 4509 8 Ibs each 1 6 27 0 43 TC A7SO Forward Baggage Light Piper 66632 0 0 2 40 8 8 75 Navigation Light rear X Grimes A2064 0 2 316 0 63 TSO C30b Navigation Light Wing 2 Grimes 1285 G 12 A1285 R 12 X 0 2 tbs each 0 4 102 4 4 TSO C30b Instrument Light Grimes 15 0083 1 2 25 Ibs each 0 5 92 7 46 TC A7SO Anti Collision Lights Whelen Engineering Co Piper Dwg 95267 Power Supply Model HS No x A412A 14 with fin light only 2 3 127 5 293 TC A7SO Light Fin Tip A408 0 4 289 5 116 TC A7SO Cable Fin Light 417 1 300 0 4 260 1 104 TC A7SO ISSUED August 2 1972 REPORT VB 424 PAGE 4 16
179. strument panel to the right of the power quadrant When the valve is set to alternate position the altimeter vertical speed indicator and airspeed indicator will be using cabin pressure for static pressure These instruments may then give slightly different readings depending on the situation within the cabin Airspeed setting of the heating and ventilating controls or position of the storm window can influence cabin pressure A pilot can see how his alternate static pressure affects the instruments by switching from one source to the other at different airspeeds and ventilation configurations including open storm window below 150 MPH The holes in the sensors for pitot and static pressure must be fully open and free from dirt bugs and polish If one or more of the pitot static instruments malfunctions these pressure systems should be checked for leaks dirt or water If moisture is present the static system can be drained by turning on the alternate static system The selector valve is located at the low point of the system Another drain is provided in the lower left front side panel to drain moisture from the pressure line running between the pitot mast and the instrument panel AIRPLANE AND SYSTEMS 2 18 ISSUED March 10 1972 er Es S gt Ez 2 eu et Un 61 1 10 11 12 13 14 151 16 ADF INDICATOR CLOCK STALL WARNING LIGHT TURN AND BANK INDICATOR A
180. t and balance requirements IT IS THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNER TO INSURE THAT THE AIRPLANE IS LOADED PROPERLY Optional Equipment ISSUED March 10 1972 REPORT VB 424 PAGE 4 7 REVISED May 30 1975 MODEL PA 34 200 SENECA C G RANGE AND WEIGHT INSTRUCTIONS l Add the weight of all items to be loaded to the licensed Smp weight 2 Use the loading graph to determine moment of all items to be carried in the airplane 3 Add the moment of all items to be loaded to the licensed empty weight moment 4 Divide the total moment by the total weight to determine the C G location 5 By using the figures of Item 1 and Item 4 locate a point on the C G range and weight graph If the point falls within the C G envelope the loading meets the weight and balance requirements SAMPLE LOADING PROBLEM Normal Category Arm Aft Datum Moment Inches In Lbs The center of gravity C G of this sample loading problem is at inches aft of the datum line Locate this point on the C G range and weight graph Since this point falls within the weight C G envelope this loading meets the weight and balance requirements IT IS THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNER TO INSURE THAT THE AIRPLANE IS LOADED PROPERLY Optional Equipment ISSUED March 10 1972 REPORT VB 424 PAGE 4 7 REVISED May 30 1975 MODEL PA 34 200 SENECA C G RANGE AND WEIGHT INSTRUCTIONS 1 Add the
181. t be operative prior to flight into known forecast icing conditions at night NOTE This supersedes any relief provided by the Master Minimum Equipment List MMEL 2 Revise the FAA approved AFM by incorporating the following into the Normal Procedures Section of the AFM This may be accomplished by inserting a copy of this AD in the AFM THE FOLLOWING WEATHER CONDITIONS MAY BE CONDUCIVE TO SEVERE IN FLIGHT ICING Visible rain at temperatures below 0 degrees Celsius ambient air temperature e Droplets that splash or splatter on impact at temperatures below 0 degrees Celsius ambient air temperature PROCEDURES FOR EXITING THE SEVERE ICING ENVIRONMENT These procedures are applicable to all flight phases from takeoff to landing Monitor the ambient air temperature While severe icing may form at temperatures as cold as 18 degrees Celsius increased vigilance is warranted at temperatures around freezing with visible moisture present If the visual cues specified in the Limitations Section of the AFM for identifying severe icing conditions are observed accomplish the following Immediately request priority handling from Air Traffic Contro to facilitate a route or an altitude change to exit the severe icing conditions in order to avoid extended exposure to flight conditions more severe than those for which the airplane has been certificated e Avoid abrupt and excessive maneuvering that may exacerbate control difficulties Do
182. t head mounted under the left wing is installed to provide pitot pressure for the airspeed indicator with heat to prevent ice accumulation from blocking the pressure intake The heated pitot head also has a separate circuit breaker located in the circuit breaker panel and labeled PITOT HEAT AIRPLANE AND SYSTEMS 2 24 ISSUED April 26 1974 SENECA HEATED PITOT AND HEATED STALL WARNING TRANSMITTER CONTROL SWITCHES Ice Protection System Control Switches AIRPLANE AND SYSTEMS ISSUED April 26 1974 2 25 SENECA With the HEATED PITOT switch ON check the heated pitot head and heated lift detector for proper heating CAUTION Care should be taken when an operational check of the heated pitot head and the heated lift detectors is being performed Both units become very hot Anti icing fuel tank vents one installed under each wing are installed to prevent ice formations from blocking the fuel tank vent lines Propeller governor ice shields and deflectors are installed to prevent operational interference from ice and other particles entering through the opening in the front cowling SEATS The front seats are adjustable fore and aft for pilot and passenger comfort An easily accessible catch on the top of the right front seat permits one to slide that seat forward conveniently for ease of entry and exit The center and rear seats are easily removable for added cargo space Each seat is provided with an armrest and
183. ternator failure procedure below Avoid further icing conditions if possible Land as soon as practical Maintain at least 105 mph CAS during final approach Do not extend landing gear until certain of making field Do not lower wing flaps until certain of making field Use 25 flaps rather than full flaps for landing 17 ALTERNATOR FAILURE IN ICING CONDITIONS In the event of an alternator failure during flight in icing conditions a b Attempt to reset alternator overvoltage relay Check circuit breakers and reset if possible If unable to restore alternator C d e f Turn off all avionics except one NAVCOM and TRANSPONDER Turn off electric windshield to maintain 60 AMP load If icing conditions continue terminate flight as soon as practical Prior to landing electric windshield may be turned on if necessary Battery may be depleted and gear may require free fall extension 18 ENGINE FAILURE WITH REAR CABIN AND CARGO DOORS REMOVED The single engine minimum control speed for this configuration is 81 mph CAS If engine failure occurs at an airspeed below 81 mph reduce power s necessary on the operating engine to maintain directional control FAA APPROVED March 10 1972 REPORT VB 423 PAGE 3 17 REVISED April 26 1974 MODEL PA 34 200 SENECA 6 i he nn 19 PROPELLER OVERSPEED Loss of the air charge in the propeller dome may cause the propeller to overspeed if the throttle is advanc
184. that flight crewmembers apprised of this change 1 Revise the FAA approved Airplane Flight Manual AFM by incorporating the following into the Limitations Section of the AFM This may accomplished by inserting a copy of this AD in the AFM WARNING Page 1 of 4 99 14 01 Severe icing may result from environmental conditions outside of those for which the airplane is certificated Flight in freezing rain freezing drizzle or mixed icing conditions supercooled liquid water and ice crystals may result in ice build up on protected surfaces exceeding the capability of the ice protection system or may result in ice forming aft of the protected surfaces This ice may not be shed using the ice protection systems and may seriously degrade the performance and controllability of the airplane During flight severe icing conditions that exceed those for which the airplane is certificated shall be determined by the following visual cues If one or more of these visual cues exists immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the icing conditions Unusually extensive ice accumulation on the airframe and windshield in areas not normally observed to collect ice Accumulation of ice on the upper surface of the wing aft of the protected area Accumulation of ice on the engine nacelles and propeller spinners farther aft than normally observed S
185. the instrument panel indicate when each landing gear is down and locked GEAR INDICATOR LIGHTS ARE DIMMED WHILE THE NAVIGATION LIGHTS ARE ON 6 LANDING GEAR UNSAFE WARNINGS The red landing gear unsafe light will illuminate when the landing gear is in transition between the full up position and the down and locked position Additionally on aircraft with serial numbers 34 7250046 and up the light will illuminate when the gear warning horn sounds The gear warning horn will sound at low throttle settings with the gear in the up position The light is off when the landing gear is in either the full down and locked or full up positions 7 REAR CABIN AND CARGO DOORS REMOVED a Limitations The airplane is approved for flight with the rear cabin and cargo doors removed The following limitations must be observed in the operation of this airplane with the rear cabin and cargo doors removed 1 Maximum speed 150 MPH 2 Minimum single engine control speed 81 MPH 3 No smoking 4 All loose articles must be tied down and stowed 5 Jumper s static lines must be kept free of pilot s controls and control surfaces 6 Operation approval for VER non icing flight conditions only b Procedure 1 When operating with the rear cabin and cargo doors removed it is recommended that all occupants wear parachutes FAA APPROVED MARCH 10 1972 REPORT VB 423 PAGE 3 9 REVISED April 1 1977 MODEL PA 34 200 SENECA U
186. the propeller deicer pads for proper heating sequence The deicer pads should become warm to 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 E 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 electrical power supply and controlled by an ON OFF control switch circuit breaker The control switch circuit breaker is located on the console directly below the control quadrant and placarded WINDSHIELD PANEL HEAT SEE ACFT FLIGHT MANUAL An operational check may be performed by turning the heated windshield panel switch ON for a period not exceeding 30 seconds Proper operation is indicated by the glass section being warm to the touch Two heated lift detectors and a heated pitot head installed on the left wing are controlled by a single ON OFF HEATED PITOT switch located on the switch panel to the left of the pilot The heated lift detectors one inboard and one outboard on the left wing are installed to prevent icing conditions from interferring with operation of the stall warning transmitters A STALL WARN HEAT circuit breaker in the circuit breaker panel protects the system against an overvoltage condition A heated pito
187. to 5 minutes with approach CDI sensitivity 0 3 nautical mile After 5 minutes the system will flag and no longer provide course guidance with approach sensitivity Missed approach course guidance may still be available with 1 nautical mile CDI sensitivity by executing the missed approach 5 In an in flight emergency depressing and holding the Comm transfer button for 2 seconds will select the emergency frequency of 121 500 Mhz into the Active frequency window SECTION IV NORMAL PROCEDURES 1 DETAILED OP TING PR D 5 Normal operating procedures described in the GARMIN GNS 530 Pilot s Guide P N 190 00181 00 Rev A dated April 2000 or later appropriate revision 2 P S DISPLAY The GNS 530 System data will appear on the Pilot s CDI HSI The source of data is either GPS or VLOC as annunciated on the display above the CDI key NOTE It is the pilot s responsibility to assure that published or assigned procedures are correctly complied with Course guidance is not provided for all possible ARINC 424 leg types See the GNS 530 Pilot s Guide for detailed operating procedures regarding navigation capabilities for specific ARINC 424 leg types 3 AUTOPILOT FLIGHT R OP TION Coupling of the GNS 530 System steering information to the director can be accomplished by engaging the autopilot flight director in the NAV or APR mode When the autopilot flight director system is using course information supplied by th
188. um Moment Basis J Autopilots Optional Equipment cont V FD 1 Installation Power Supply PS 815B 25 202 1 505 TC A7SO Corrector 4000202 8501 2 205 8 4 75 Computer Amplifier CA 814A 4 1 199 6 818 TC 750 Directional Gyro SG 832B 3 0 196 8 590 75 Sag Pitch Trim Servo ST 816B 3 2 197 0 630 TC A7SO u Aileron Servo SA 816A 3 3 118 5 391 A7SO Altitude Controller AC 844B 155 218 8 328 TC A7SO Stabilator Servo SE 816A 3 7 267 7 990 TC A7SO Magnetic Flux Sensor 4000191 Tu 8501 3 21 65 TC A7SO 2 Flight Controller FC 823B 1 8 66 7 120 75 Manual Navigation Converter 4000207 1 7 50 8 102 TC A7SO Slaving Meter 4000192 8501 0 1 67 8 7 TC A7SO Horizontal Situation Indicator A IN 831 A 3 5 63 9 224 TC A7SO Director Horizon Ind DH 841A 3 3 64 8 214 TC A7SO TORRE Shelf and Instl Trim Servo Amp 2 9 199 7 579 TC 75 ones Shelf and Instl Aileron Servo 1 0 119 7 120 TC A7SO en Shelf and Inst Altitude Cont 0 7 218 1 153 75 A is Shelf and Instl Stabilator Servo 1 4 267 1 374 TC A7SO m Shelf and Instl Flux Sensor 5 216 5 108 TC A7SO PA Miscellaneous Hardware 2 0 118 0 236 75 _ Wire Harness 11 0 145 0 1595 75 TOTAL 51 7 158 4 8190 REPORT VB 424 PAGE 4 23a MODEL PA 34 200 ISSUED July 7 1972 REVISED April 26 1974 Item J Autopilots Optional Equipment cont Item AltiMatic V 1 Installation Power
189. use is with the flaps up In the event of an engine failure the airplane is in the best flight configuration to sustain altitude immediately after the gear is raised Set the stabilator trim indicator in the take off range Set the brakes and bring the engines to full power before release Accelerate to 80 MPH and rotate the airplane firmly so that the airspeed is approximately 85 MPH when passing through the 50 foot height The airplane should then be allowed to accelerate to the best angle of climb speed 90 MPH at sea level if obstacle clearance is necessary or best rate of climb speed 105 MPH if obstacles are not problem The landing gear should be retracted when a gear down landing is no longer possible on the runway The distances for this take off procedure are given on a chart in the performance section of this manual Short Field Take off 25 degree Flaps When the shortest possible ground roll and the greatest clearance distance over a 50 foot obstacle is desired use a 25 degree flap setting second notch Set the stabilator trim indicator slightly nose up from the take off range 5et the brakes and bring the engines to full power before release Accelerate to 70 MPH and rotate firmly so that when when passing through the 50 foot height the airspeed is approximately 80 MPH Retract the gear when a gear down landing is no longer possible on the runway It should be noted that the airplane is momentarily below Vmc when using the
190. y b If engine failure occurs during takeoff ground roll or after lift off with gear still down and 100 mph CAS has been attained 1 2 If adequate runway remains CLOSE BOTH THROTTLES IMMEDIATELY LAND IF AIRBORNE AND STOP STRAIGHT AHEAD If the runway remaining is inadequate for stopping the pilot must decide whether to abort the takeoff or to continue The decision must be based on the pilot s judgement considering loading density altitude obstructions the weather and the pilot s competence the decision is made to continue then a Maintain heading and airspeed b Retract landing gear when climb is established c Feather inoperative engine see feathering procedure FAA APPROVED May 25 1973 REPORT VB 423 PAGE 3 12a MODEL PA 34 200 SENECA THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 423 PAGE 3 12b FAA APPROVED May 25 1973 MODEL PA 34 200 SENECA NENNEN ae 6 ENGINE FAILURE DURING CLIMB The single engine minimum control speed for this airplane is 80 mph CAS under sea level standard conditions a engine failure occurs when airspeed is below 80 mph CAS reduce the power on the good engine as required to maintain directional control Reduce nose attitude to accelerate toward the single engine best rate of climb speed of 105 mph Then feather inoperative engine see feathering procedure b If engine failure occurs when the airspeed is above 80 mph CAS 1 Maintain
191. y be drained by opening all the drain valves TIRE INFLATION For maximum service from the tires keep them inflated to the proper pressure of 31 psi for nose tire and 53 psi for main tires Interchange the tires periodically for even wear All wheels and tires are balanced before original installation and the relationship of tire tube and wheel should be maintained upon reinstallation In the installation of new components it may be necessary to rebalance the wheels with the tires mounted Out of balance wheels can cause extreme vibration in the landing gear BATTERY SERVICE Access to the 12 volt 35 ampere hour battery is gained through the nose baggage compartment It is located just forward of the nose baggage compartment The battery container has a plastic drain tube which is normally closed off The battery fluid level must not be brought above the baffle plates It should be checked every 30 days to determine that the fluid level is proper and the connections are tight and free of corrosion If the battery is not properly charged recharge it starting with a rate of 4 amperes and finishing with a rate of 2 amperes Quick charges are not recommended __ The external power receptacle if installed is located on the left side of the nose section Be sure that master switch is off while insertin 2 or removing a plug at this receptacle Refer to Aircraft Service Manual for servicing battery 21 Pile Meade Gs 4s

Piper Seneca 1972 POH/Manual

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