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POH - Glass Cockpit Aviation

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1. WARM UP Eos 1000 to 1200 RPM TAXHNG Chocks ts cae oo oe a EE ERE Een QI ua MR es removed Parking e a 6 release Tari EO ed oon Vorher Dade clear TATO E Eo oops e e ul E apply slowly NM a csc sce hs check orn EET check tese parebat di date check Heater and Ge tne ud Qt vana so raa i iit es Lr check Fuel MICO ou osa iE fob CREE SOL Co ved uro p ios check crossteed LA ee ee eflet ee ue eg n OFF REPORT 1110 ISSUED JANUARY 8 1981 4 8 REVISED FEBRUARY 10 1984 PIPER AIRCRAFT CORPORATION SECTION 4 PA 34 220T SENECA NORMAL PROCEDURES BEFORE TAKEOFF GROUND CHECK Parke SURO S gs eck ot eO Nae Mc aaa Botte ay E E set ior gage tt SR REP Ex quce a a hus FORWARD Prop GDBTEO FORWARD 000 RPM Manifold pressure HNES e eee s Va oe dare drain Se ae check feathering 300 RPM max drop THROU CORON Er EM mE RUE ET 2300 RPM check governor PrOD COMTO eag Z3 re Ra FORWARD AMICO DH CHI Eee REA TOUT ON then OFF co ten ve chou ade eo t Soie 2000 RPM NEUES Aube ORAE e check drop
2. a a a m a aa a CONTROL DISPLAY HOLD pushbutton push on push off FUNCTION Retains the display NAV and weather when button is actuated push on The word HOLD flashes in the upper left corner of the display The weather or ground mapping image last pre sented is retained frozen on indicator display in order to evaluate the significance of storm cell movement Switching back to normal op eration pressng HOLD pushbutton a second time reveals direction and distance of target movement during HOLD period In HOLD the antenna continues to scan and a non updated display will continue to be presented as long as power is supplied to the system change in range selection with indicator in HOLD results in a blank screen Wx pushbutton WXxA pushbutton push on push off MAP pushbutton FLT LOG pushbutton Selects the weather mode Wx when pressed Pushbutton switch returns to normal position when released WX appears in display Selects weather alert mode WxA when pressed Red area flashes Returns to previous mode Wx or MAP upon push off Selects ground mapping mode MAP when pressed Mechanical operation same as Wx Operational only when optional equip ment is connected When actuated will display the flight log information stored in the optional NAV programmer Ten waypoints and course information may be displayed e g from NP 2041A Remote Computer Uni
3. 328005 SILVLS Dtivis 07 1014 ES 3Ni1liOila j SNiVHO SNM 21 15 ONY iOlid HOLIMS 1V3H 10 pe HOLVOIGNI Q33dSutv HO1VOIGNI 9334 W3L3WELTY 70341403 328005 211915 SINIWAYLSNI 5 107402 dl o NOS OOM 0 PITOT STATIC SYSTEM Figure 7 19 REPORT VB 1110 ISSUED JANUARY 8 1981 7 25 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA a a e 7 23 INSTRUMENT PANEL Flight instruments are grouped in the upper instrument panel Figure 7 21 engine instruments are to the left of the radios The autopilot is to the left of pilots control wheel The circuit breaker panel is on the lower right instrument panel The left and right engine instruments are stacked by the pilots control wheel shaft Radios are mounted in the center of the upper instrument panel The control quadrant throttles propeller and mixture controls are in the center of the lower instrument panel To the left of the control quadrant is the landing gear selector An annunciator panel is located to the upper left of the radios and incorporates a press to test feature The annunciator panel inciudes the manifold pressure overboost oil pressure gyro vacuum alternator auxiliary fuel gear unsafe heater overheat and provisions for an optional baggage door ajar and air conditioner
4. dE Sree ak gor FULL FORWARD Landing gear ooo P e OM Ro OS DOWN 130 K1AS max uoces p ba Beh FES KIAS max Approach E es 90 KIAS or above GO AROUND Full takeoff power both engines 40 in Hg maximum manifold pressure Establish positive climb Flaps CEA NAE Ri o retract Gear E IA RETE QUE Ie Wa UP PME adiust AFTER LANDING Clear of runway QUEE retract Cowl flaps pU doque fuliy OPEN SHUTDOWN Heater FAN 2 min then OFF Radios amp electrical CE Ser EY WE Od e Yt ert Ree Me o OFF Vibes full aft idle cut off RARE GER UR UE A E VR URINE ots x OFF Battery SWIC ee omen Gated ve ses 1110 ISSUED JANUARY 8 1981 4 12 REVISED AUGUST 17 1981 PIPER AIRCRAFT CORPORATION SECTION 4 PA 34 2201 SENECA NORMAL PROCEDURES CLIMB TAKEOFF CLIMB B st rate laps UD OR dare deed Ua dues 92 KIAS Best aBgle 00 ives ero ovd haus So tay ae eG CE Eo YN 76 KIAS En casa eX bp dou dede qe 102 KIAS as required
5. When the GS mode arming conditions met the GS mode annunciator will illuminate in conjunction with the active pitch mode Loss of any arming condition prior to GS capture will cause the GS annunciator to extinguish REPORT VB 1110 ISSUED FEBRUARY 10 1984 9 146 12 of 20 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 21 PRESE PR HH gg GS mode activation GS capture is indicated by the active mode annunciator extinguishing leaving only the GS annunciator lighted Smee GS mode activation results from a combination of position and rate information GS capture will probably occur before the GS needle centers in such a manner that the transition on to the GS centerline will be anticipated and therefore very smooth After GS capture loss of vahd GS signal will cause the GS annunciator to flash Also selection of HDG NAV or REV mode will cause GS to flash indicating an inconsistent GS tracking condition APR mode must be selected while tracking glide slope The GS mode may be deactivated by selection of any other pitch mode ATT ALT however automatic reactivation is possible from any pitch mode if APR mode 15 selected NOTE if valid glide slope data is lost after coupling the autopilot will NOT automatically decouple however the GS light will flash The pilot must monitor raw course guidance data during the approach to assur
6. BATTERY 22 L ALT oo ma c CHAR 5 LIGHTER i lt i swiTCH VER meee i OPTIONAL xm LI n SWITOM R H VOLTAGE S ALTERNATOR AND STARTER SCHEMATIC S N 34 8333001 AND UP Figure 7 14 REPORT VB 1110 ISSUED AUGUST 9 1982 7 19a PIPER AIRCRAFT CORPORATION SECTION 7 An optional cabin courtesy light system consists of a front entrance light over the forward cabin door and rear entrance light which replaces the reading light over the aft cabin door These lights are operated individually with switches that are incorporated as part of each light assembly The courtesy light circuit is independent of the aircraft battery switch therefore the lights can be operated regardless of the position of the battery switch Unless the engines are running the courtesy lights should not be left on for extended time periods as battery depletion could result An optional wing tip recognition light system consists of 2 lights one in each wing tip and is operated by a switch mounted adjacent to existing switches on the pilot s side of the instrument panel S N 34 8133001 THRU 34 8233205 Approximately 2000 RPM or more is required to o btain full alternator output of 65 amperes It is normal to have zero output at idle Thisis due to the reduced drive ratio from the engine Dual ammeters and the ALT
7. SONT IAE QA NOLLONS TABLE OF CONTENTS SECTION 6 WEIGHT AND BALANCE Paragraph Page No No General zd 6 1 3 Airplane Weighing Procedure 6 2 5 Weight and Balance Data and 6 5 57 General Loading 6 9 6 9 Weight and Balance Determination for Flight 6 10 6 Instructions for Using the Weight and Balance Plotter 6 15 6 13 Equipment 154 6 19 Propeller and Propeller Accessories 6 20 b Engine and Engine 6 21 c Landing Gear and Brakes 6 22 d Electrical 8 3 6 23 1 P 6 26 f Miscellaneous RE ett e oe 6 28 g Propeller and Propeller Accessories Optional 6 29 h Engine and Engine Accessories Optional Equipment cesse 6 30 1 Landing Gear and Brakes Optional Equipment nnn 6 31 G Electrical Equipment Optional Equipment 6 32 Instruments Optional Equipment 6 34 i Autopilots Optional 6 40 m Radio Equipment Optional Equipment 6 41 n Miscellaneous Optional Equipment 6 55 0 Maximum Zero Fuel Weight Increase 6 65 Equipment List F
8. aH TY YT I T TT 4 7 AMPLIFIED NORMAL PROCEDURES GENERAL The following paragraphs are provided to supply detailed information and explanations of the normal procedures necessary for the operation of the airplane 4 9 PR EPARATION The airplane should be given a thorough preflight and walk around check The preflight should include a determination of the airplane s opera tional status a check that necessary papers and charts are on board and in order and a computation of weight and C G limits takeoff distance and in flight performance Baggage should be weighed stowed and tied down Passengers should be briefed on the use of seat belts and shoulder harnesses oxygen and ventilation controls advised when smoking is prohibited and cautioned against handling or interfering with controls equipment door handles etc A weather briefing for the intended flight path should be obtained and any other factors relating to a safe flight should be checked before takeoff ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 17 1981 4 15 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA 34 220T SENECA nate cme Pai e a aiit a Sr a atta atta a m aa iai aiit m e m m m St 411 PREFLIGHT CHECK CAUTION The flap position should be noted before boarding the airplane The flaps must be placed in the UP position before they will lock and support weight on the step
9. nested ated ue 8 4 8 9 Ground e 8 5 8 11 Engine Induction Air Filters 8 7 8 13 Brake ccc tee eee e een 8 8 8 15 Landing Gear Service 2 2 n nn 8 8 8 17 Propeller Service seen 8 10 919 Requirements nhe rrt 8 11 8 21 Fuck System xii orsus sea ek e i n ig DDR rares 11 8 23 Tire Inflatioft ise 8 14 8 25 Battery SERVICE evo vo based in sy 8 15 8 27 Number redu 8 15 8 29 lubrication EU S A a dpa ns 8 16 8 31 S R 16 8 33 Winterization cscs serre ra RE Re rs RUN 8 20 REPORT VB 1110 8 i PIPER AIRCRAFT CORPORATION SECTION 8 PA 34 220T SENECA HI HANDLING SERV amp MAINT SECTION 8 AIRPLANE HANDLING SERVICING AND MAINTENANCE 8 1 GENERAL This section provides general guidelines relating to the handling servicing and maintenance of the Seneca III Every owner should stay in close contact with his Piper dealer or distributor and Authorized Piper Service Center to obtain the latest information pertaining to his aircraft and to avail himself of the Piper Aircraft Service Back up Piper Aircraft Corporation takes a continuing interest in having the owner get the most efficient use from his aircraft and keeping it in the best mechanical condition Consequently Piper Aircraft from time to time issues Service Bulletins Service Letters and Service Spares Letters
10. 83414 VOUNAS LOTT E W d Gunssi 7861 ST 1861 8 18 5 GN30S3G OL AWIL IANA LUOJAN 605 OIIL HA E ASSOCIATED CONDITIONS FH 145 KIAS 1000 FPM DESCENT Cruise alt 16500 ft Cruise O A T 13 C Destination 3000 ft Destination 22 C to descend 6 1 5 gal Time to descend 16 3 13 min Distance to descend 44 7 37 DESTINATION ane t IB 0 EEH RR teed LEVEL ete i LO H 40 30 20 10 0 10 20 30 40 2 20 30 40 50 60 70 OUTSIDE AIR TEMPERATURE FUEL TIME AND DISTANCE TO DESCEND Ill VOUNAS 4 NOLLVHOdNOO LIVUIONHIV NHddld dONVIAHOAH3Ud NOLLOWS 05 5 18044 QUOSSI 1861 SZ 1861 8 65 211814 3ONV ESIG DNIGNV I _ 34 2201 _ Example O A T 22 Pressure altitude 3000 ft Gross weight 3655 ibs Head wind 10 knots Landing ground roll 1120 ft H 3200 HE 3000 nm uS z Total landing distance over 50 ft barrier 2260 ft 77 Barrier 82 E E 40 20 20 40 4500 4000 3500 OUTSIDE AIR
11. ON jemon MARS 401494 etes he e dar tea eS Ae a ees ON Asie SUC DUMP sarees Qa da sae eni ON LO boost E E A Ea OOP EO E engage ON 3 sec FULL FORWARD to FULL AFT PO am ON 3 sec then OFF 3 sec then ON 3 sec ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED FEBRUARY 10 1984 4 7 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROC E DU RES PA 34 220T SENECA When engine fires leave engaged Primer buttom 3255552 rrr ERR tap until rhythmic firing release Mic qoe E Ros hall travel ca S dac check If engine begins to falter Ve eee eus p Throttle 1000 RPM Pueb DUIS cue totes pep o cee oe CNET OFF after start complete STARTING ENGINES WITH EXTERNAL POWER Babe SWCD oss sce p RR PERI fed due dant Belit os eod een Eee des seia paa PP connect External power 55244 insert in fuselage Proceed with normal start lowest possible RPM power E ouis wo Tea disconnect from fuselage dass etait uA Text ON check ammeter CUL BECSSIE
12. eru ure ea Tete OFF A s puel SD cust vere OFF Use crossfeed in level cruise flight only NOTE Do not crossfeed with full fuel on same side as operating engine since vapor return fuel flow will be lost through the vent system LANDING Fuel selector operating Engine eer rh reet ON Fuel selector nap engine iow dies oce OFF ENGINE DRIVEN FUEL PUMP FAILURE EE retard Aus foel pump oara tiree unlatch on HI t e cnr A BPO reset 756 power or below CAUTION If normal engine operation and fuel flow ts not immediately re established the auxiliary fuel pump should be turned off The lack of a fuel flow indication while on the Hl auxiliary fuel pump position could indicate a leak in the fuel system or fuel exhaustion ISSUED JANUARY 8 1981 REPORT 1110 REVISED APRIL 9 1982 3 7 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA 34 220T SENECA MM CAUTION Actuate the auxiliary fuel pumps if vapor suppression is required LO position or the engine driven fuel pump fails HI position The auxiliary fuel pumps have no standby function Actuation of the switch position when the engine fuel injection system is func tioning normally may cause engine roughness due to excessively rich fuel air mixture LAND
13. 062 Pty xoiddy EE Hd OLR Puy xoiddy H d D 91 274 xouddy 5244 2561 2059 FIMO Gg 3055 Job 4 8 5 DNILLAS 4 Figure 5 25 POWER SETTING TABLE 1110 5 23 FEBRUARY 25 1982 JANUARY 8 1981 ISSUED REVISED PiS Laodaa GASIA TY 4 2861 ET 1 4346 OLII HA GAANASSI 1861 8 AUVONVE un pm 7 om PA N t M e PA 34 220T au X SPEED CRUISE POWER X HIGH SPEED 75 ECONOMY 65 LONG RANGE E N 3 Example Pressure altitude 16500 ft 3171111 Power 5596 Lr True airspeed 172 kts THE Tr 13 H I OUTSIDE AIR TEMPERATURE TRUE AIRSPEED KNOTS 3ONVINASIOA d HI VOANAS LOZC FE Vd NOILOWS NOILVHOdUNOO LIVHOMNHIV 861 ET STS 930551 1861 8 60 5 amsi 418VS1 SNOTIV2D 56 ASIN 32NVM PA 34 220T RANGE CRUISE POWER _ USABLE FUEL 93 GALLONS 4780 LBS GEAR COWL FLAPS CLOSED WING FLAPS UP CLIMB AT M C P
14. 75 THROTTLE 7 H HYDRAULIC 1 4 E 50 M PUMP i i 3 pA MOTOR 1 ete Po k ud DOWN s 9 du i e e i S NO E WO 88 4 wd ican 5 E ip 1 ot HORN 5 LANDING GEAR ELECTRICAL SYSTEM SCHEMATIC Figure 7 5 REPORT VB 1116 ISSUED JANUARY 8 1981 7 8 PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA III 2 DESCRIPTION amp OPERATION T ren TM SS RIGHT MAIN GEAR LEFT MAIN GEAR HYDRAULIC CYLINDER E HYDRAULIC CYLINDER TTA TAA ETT NOSE GEAR HYDRAULIC CYLINDER i PRESSURE if SWITCH un DOWN qoc m lt 4 IS FREE FALL CONTROL 2 i 600 2000 PSI HIGH PRESSURE RESERVOIR CONTROL d LOW PRESSURE CONTROL 16504150 PSI 1 i i i DELIVERED PRESS 400 800 PSI T SHUTTLE VALVE _ M S DOWN EUER EPIS LANDING GEAR HYDRAULIC SYSTEM SCHEMATIC Figure 7 7 ISSUED JANUARY 8 1981 REPORT VB 1110 7 9 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA When the gear is fully extended or fully retracted and the gear selector is in the corresponding position electrical limit switches stop the flow of
15. cero a sb pedro 4 16 13 4 16b 5 Starting Engines Standard Primer System 4 17 7 Starting Engines Optional Primer 4 18 19 Starting Engines When Flooded 4 20 21 Starting Engines In Cold Weather Standard Primer System eve rw erudi 4 20 4 23 Starting Engines With External Power 4 2 4 25 Prehcating ue bee e Sae b VM da wd RA 4 22 4 27 MACH Do us Shes esee S aw a cba n hae ahah 4 24 4 29 TARNE vo scans iC ter hd aee ds api 4 25 4 31 Before Takeoff Ground Cheek oa ed aco ert 4 25 433 Takeoll AS hee EET VA 4 27 4 35 4 29 4 37 deb AA ar Pa bep dta 4 29 4 39 4 31 4 41 Approach and xu vacat Rote det de en 4 20 4 43 S Bol Scd 4 34 4 45 ANCE ESO os Octa eed eRe tame Be ER ers 4 34 4 47 sor dne Pateb d wt 4 34 4 49 MOORES tinea 4 35 4 51 Turbulent eo editos ed at hen 4 35 4 53 Flight With Rear Cabin and Cargo Doors Rem ved 4 35 4 55 Intentional One Engine Inoperative Speed 4 36 4 37 VMc Minimum Single Engine Control 4 36 4 59 Staller cub ake eed qs 4 38 TABLE OF CONTENTS cont SECTION 4 cont REPORT 1110 4 PIPER AIRCRAFT
16. reduce to MCP CRUISE CLIMB Mixture ita Qe uda Vio dioe s full RICH 75 Climb speed 102 KIAS COW re EL E as required CRUISING Power set per power table Mixture controls o2 tanp adjust NO as required DESCENT asus A d Bret adjust with descent a v Fais dein ede uli set COW Sw eodein e E et PO o E SR CLOSED ISSUED JANUARY 8 1981 REPORT 1110 4 11 PIPER AIRCRAFT CORPORATION 24 220 SENECA MOORING Parking Drake ci 4 oats eese RE sax ce Control Wheel 4 Fas dcbet ex eee IT Whee CHOCKS Boe an e A Tie dowHscd poe ISSUED JANUARY 8 1981 4 9 o9 4 9 9 4 v o4 4 c3 5 9 8 4 gt 9 9 SECTION 4 NORMAL PROCEDURES nm aS required ee rear ee secured with belts eee re full up in place secure REPORT VB 1116 4 13 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES P A 34 220T SENECA THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED JANUARY 8 1981 4 14 PIPER AIRCRAFT CORPORATION SECTION 4 PA 34 220T SENECA 1H NORMAL PROCEDURES ar M ee a aa A PATTY eee a aa A MAUI
17. 3 COMPASS SYSTEM NSD 360A For other compass systems refer to appropriate manu facturer s instructions Check slaving switch in SLAVE No No 2 position as appropriate Slaving systems with output provides only slave and free gyro positions b Rotate card to center slaving meter check HDG Heading displayed with magnetic compass heading c Perform standard VOR receiver check b IN FLIGHT PROCEDURE AUTOPILOT 1 Rotate heading bug to desired heading 2 Trim aircraft for existing flight condition all AREN Engage autopilot 3 During maneuvering flight control aircraft through use of the heading bug and the pitch modifier HDG ATT modes REPORT VB 1110 J ISSUED FEBRUARY 10 1984 9 140 60420 PIPER AIRCRAFT CORPORATION SECTION 9 4 PA 34 220T SENECA HI SUPPLEMENT 21 For navigation operations select modes as required by the operation being conducted and in accordance with the mode description provided in Section 7 1 For specific instructions relating to coupled instrument approach operations refer to Special Operations and Information c IN FLIGHT PROCEDURE COMMAND AUTOTRIM SYSTEM 1 2 When the autopilot is engaged pitch trim 15 accomplished and maintained automatically With the autopilot OFF command trim is obtained by pressing and rocking the combination TRIM AP disconnect bar on the pilot s control wheel trim switch d SPECIAL OPERAT
18. PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO 8 FOR BENDIX 2041 AREA NAVIGATION COMPUTER PROGRAMMER PIPER DWG 39673 SECTION 1 GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Bendix 2041 Area Navigation Computer Programmer is installed in accordance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with the complete handbook This supplement has been FAA Approved and must remain in this handbook at all times when the optional Bendix NP 2041A Area Navigation Computer Programmer is installed aitoren COUN WARD EVANS 50 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED JANUARY 8 1981 REPORT VB 1110 i of 6 9 59 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 8 PA 34 220T SENECA II SECTION 2 LIMITATIONS No changes to the basic limitations provided by Section 2 of this Pilot s Operating Handbook are necessary for this supplement SECTION 3 EMERGENCY PROCEDURES No changes to the basic Emergency Procedures provided by Section 3 of this Pilots Operating Handbook are necessary for this supplement SECTION 4 NORMAL PROCEDURES NOTE The 21 VOR and DME receivers supply infor mation to the NAV computer programmer which in turn drives the pilot s navigation displavs ia Tur
19. PO M S 34 8333001 AND UP A single ammeter on the instrument panel indicates both battery charging current and alternator output When the ammeter necdle indicates to the left of center the battery is being discharged when the needle indicates to the right of center the battery is being charged During single engine operation this feature can be used to determine how much the electrical load should be reduced To check the output of each alternator individually usc the press to test buttons located on either side of the ammeter The left button when depressed will cause the ammeter to indicate left alternator output and the right button when depressed will indicate right alternator output These buttons are the momentary tvpe indicate alternator output only while depressed Approximately 2000 RPM or more is required to obtain full alternator output of 65 amperes is normal to have zero output at idle RPM This is due to the reduced drive ratio from the engine Ammeter and the ALT annunciator lights provide a means of monitoring the electrical system operation Should the ammeter indicate a load much higher than the known consumption of the electrical equipment in use an alternator malfunction should be suspected and the respective alternator switch turned off In this event the remaining alternator should show a normal indication on the ammeter after approximately one minute If both alternators indica
20. Power 5596 USABLE FUEL 23 lor 2180 Endurance with reserve 3 78 hrs BERE Endurance with no reserve 4 41 hrs HIGH SPEED 125 ECONOMY 165 LONG RANGE 155 20 000 1 222 pum TUNNET 10 000 Hiii ArH ENDURANCE HRS ENDURANCE HRS WITH 45 MIN RESERVE 45 POWER WITH NO RESERVE Hi VOUNGAS LOCC PE Vd LIVSHOSWIV SONVIAHOJHI d NOLLOUS 85 5 50444 AASIAA 861 ET MAGWALdAS 1861 8 56 5 5 SNOTIVOD 34 220 _ ENDURANCE Eia VEN USABLE FUEL 123 GALLONS 4750 LBS GEAR UP ple COWL FLAPS CLOSED WING FLAPS UP CLIMB AT M C P Cruise altitude 16500 ft DESCENT AT 1000 FPM AND 145 KIAS NO WIND Power 55 4 2 GAL FUEL FOR START TAX AND Endurance with reserve 5 38 hrs Endurance with no reserve 2 00 hrs MIXTURES LEANED IN ACCORDANCE WITH PROCEDURES IN SECTION 4 37 gy Li HIGH SPEED 75 7 ECONOMY 65 58 NOTE ENDURANCE INCLUDES CLIMB amp DESCENT TIMES SEA LEVEL ENDURANCE HRS ENDURANCE HRS WITH 45 MIN RESERVE AT 45 POWER WITH NO RESERVE HONV AOA Ad NOLLDUS NOLLVUOdYOO
21. REPORT 1110 iv PILOT S OPERATING HANDBOOK LOG OF REVISIONS Current Revisions to the PA 34 220T Seneca Pilot s Operating Hand book REPORT VB 1110 issued January 8 1981 FAA Approval Signature and Date Revision Number and Code Revised Description of Revision Pages Rev Revised Warning PR810421 3 15 Revised Warning 4 9 Revised procedure 4 26 Revised para 4 31 5 21 Revised fig 5 21 6 40 Added items 221 and 223 6 48 Revised item 285 6 49 Revised item 291 7 14 Revised para 7 15 7 26 Revised para 7 23 9 1 Revised Table of Contents 9 19 Added Supplement 4 thru KFC 200 Automatic Flight 9 32b Control System with Flight Director 9 33 Added Suplement 5 thru KFC 200 Automatic Flight 9 444 Control System without Flight Director 9 68 Revised sec 4 b 1 9 103 Added Supplement 16 thru Propeller Synchrophaser 9 106 Installation 9 107 Added Supplement 7 thru Century 21 Autopilot 9 112 Installation 9 113 Added Supplement 18 Word TY thru Century 41 Autopilot Ward Evans 9 124 Installation April 21 198 REPORT VB 1110 PILOT S OPERATING HANDBOOK LOG OF REVISIONS cont Revision Number and Code Revised Pages Rev 2 PR810817 4 18 4 19 4 26 REPORT VB 1116 vi O A FAA Approval Signature and Date Description of Revisio
22. VO3NAS LOct rt Vd NOILVNOdNOO UWidid 7 NOLILdINOSAG L NOILO3S SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA IH 7 49 VACUUM SYSTEM The vacuum system operates the air driven gyro instruments The vacuum system Figure 7 17 consists of a vacuum pump on each engine plus plumbing and regulating equipment The vacuum pumps are dry type pumps which eliminates the need for an separator and its plumbing A shear drive protects the engine from damage If the drive shears the gyros will become inoperative The vacuum gauge mounted in the center of the instrument panel below the radios refer to Figure 7 21 provides valuable information to the pilot about the operation of the vacuum system decrease in pressure ina system that has remained constant over an extended period may indicate a dirty filter dirty screens possibly a sticking vacuum regulator or leak in system low vacuum indicator lights are provided in the annunciator panel Zero pressure would indicate a sheared pump drive defective pump possibly a defective gauge or collapsed line In the event of any gauge variation from the norm the pilot should have a mechanic check the system to prevent possible damage to the system components or eventual failure of the system A vacuum regulator is provided in the system to protect the gyros The valve is set so the normal vacuum reads 4 8 to
23. 1 of 12 9 113 SECTION 9_ PIPER AIRCRAFT CORPORATION SUPPLEMENT 18 PA 34 220T SENECA SECTION 2 LIMITATIONS b c d e Autopilot use prohibited above 180 KIAS Autopilot Autopilot OFF during takeoff and landing Required Placard P N 13A990 stating Conduct trim check prior to first flight of day See AFM to be installed in clear view of pilot Autopilot coupled Go Around maneuvers prohibited See Section 4 item a Category 1 operations only SECTION 3 EMERGENCY PROCEDURES a AUTOPILOT gt 2 In the event of an autopilot malfunction the autopilot is not performing as commanded do not attempt to identify the problem system Regain control by overpowering and immediately disconnecting the autopilot This will disable both the autotrim system and the autopilot system If the malfunction was in the auto trim system there may be residual control wheel force after the system is OFF Be prepared for any residual trim force and retrim as necessary using the aircraft s primary trim control system NOTE Do not overpower autopilot in pitch for more than approximately 3 seconds as the autotrim system will cause an increase in pitch over power forces 1 Autopilot may be disconnected by a Depressing OFF bar on pilot s trim switch b Depressing the AP ON OFF switch on the programmer c Depressing master disconnect switch on pilo
24. ENGINE FAILURE DURING TAKEOFF Below 85 KIAS if engine failure occurs during takeoff and 85 KIAS has not been attained M Roe G CLOSE both immediately Stop straight ahead l inadequate runway remains to stop iS etw Val CLOSED apply max braking Baen I d OFF coin e coop ERE OC RO OFF Continue straight ahead turning to avoid obstacles ISSUED JANUARY 8 1981 REPORT VB 1110 3 3 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA 34 220T SENECA er ye NL C IK C ENGINE FAILURE DURING TAKEOFF 85 KIAS or above If engine failure occurs during takeoff ground roll or after lift off with gear still down and 8 KLAS has been attained If adequate runway remains CLOSE both throttles immediately land if airborne and stop straight ahead If runway remaining is inadequate for stopping decide whether to abort or continue H decision is made to continue maintain heading After establishing a climb retract landing gear accelerate to 92 KIAS and feather inoperative engine prop see Engine Securing Procedure WARNING In certain combinations of aircraft weight configuration ambient conditions and speeds negative climb performance may result Refer to One Engine Inoperative Climb Performance chart Figure 5 21 ENGINE FAILURE DURING FLIGHT Below 66 KIAS Ruddem apply toward operative engine
25. ADF PNEUMATIC DE ICE CONTROLS ECS CONTROL SWITCHES AVIONICS EMERGENCY BUS SWITCH CIRCUIT BREAKER PANEL COPILOT S MIKE AND PHONE JACKS CIGAR LIGHTER VOANAS LOCC FEC V d NOLLV HOd00 WAdld NOILVH340 NOLLdINOS30 L NOILOAS PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA HI DESCRIPTION amp OPERATION a v6 6 i i TI 16 53 0 it 8 3 Pos 452 8 8 1 04562 E ai 9 4 Cha Lie v 8 5 55 52 wa 2 no 5 8 di For 18 05 5 ay vy Sb BEBELE aE i 2 5 dol geo gt eA UR vl Et el 3 bE E 2E iE 414 TYPICAL INSTRUMENT PANEL S N 34 8333001 AND UP Figure 7 22 REPORT VB 1110 7 29 ISSUED AUGUST 9 1982 Ganssi 1861 6 LSQDAY 4 46 1 OTEL HA 1409 2 210814 1402 dQ ANY 100 lt 8 lt N S Quo JANWd LNAAMNISNI TVOIdAL P gt t Mo 10 11 12 13 14 15 18 17 18 19 20 21 22 23 24 25 26 27 HOURMETFR RADAR ALTIMETER NAV INDICATOR AIRSPEED INDICATOR TURN AND BANK INDICATOR ATTITUDE GYRO AUTOPILOT ANNUNCIATOR PANEL DIRECTIONAL GYRO ALTIMETER ANNUNCIATOR PANEL VERTICAL SPE
26. For six occupants maximum duration will be obtained with three 3 persons utilizing each unit See preceding chart for number of persons vs duration per unit ISSUED JANUARY 8 1981 REPORT VB 1110 3 of 6 9 5 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT _ _ 34 220 SENECA SECTION 3 EMERGENCY PROCEDURES a Time of useful consciousness at 25 000 feet is minutes 6 If oxygen flow is as evidenced by the flow indicat rs Or hypoxic indication 1 Install another mask unit 2 Install mask c nnection in an unused outlet if available 3 If flow is not restored immediately descend to below 12 500 feet the event an emergency descent becomes necessary CLOSE the throttles and move the propeller controls ful FORWARD Adjust the mixture control as necessary to attain smooth operation Extend the landing gear at 130 KIAS and maintain this airspeed SECTION 4 NORMAL PROCEDURES PREFLIGHT a Check oxygen quantity b eee Forward facing seating arrangement only 1 Remove middle center seat and secure units to seat by use of belts provided 2 Reinstall seat and secure seat by adjusting the middle seat belt tightly around seat aft of the oxygen units ic Installation Club seating arrangement only 1 Install mounting base between center seats utilizing slotted receptacles for front attachment points and bolts foraft attach ment points 2 Slide oxygen bottles into p
27. Oil Viscosity Aviation S A E Grade No 1 Below 40 F 1065 30 2 Above 40 F 1100 50 When operating temperatures indicated ranges use the lighter grade of oil Multi viscosity oils meeting Teledyne Conti nental Motors Specification MHS 24A are approved 1 11 MAXIMUM WEIGHTS a Ramp Weight 1bs 4773 b Max Takeoff Weight 165 4750 c Max Landing Weight 165 4513 d Zero Fuel Weight 165 Std 4470 c Max Weights in Baggage Compartment 158 1 Forward 100 2 Aft 100 113 STANDARD AIRPLANE WEIGHTS Refer to Figure 6 5 for the Standard Empty Weight and the Useful Load 1 15 BAGGAGE SPACE FORWARD AFT ta Maximum Baggage 1bs 100 100 b Baggage Space cu ft 15 3 17 3 Baggage Door Size in 24 x 21 1 17 SPECIFIC LOADINGS a Wing Loading lbs per sq ft 22 8 b Power Loading lbs per hp 10 8 ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 9 1982 1 5 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA 34 220T SENECA 1 19 SYMBOLS ABBREVIATIONS AND TERMINOLOGY The following definitions are of symbols abbreviations and terminology used throughout the handbook and those which may be of added operational significance to the pilot a General Airspeed Terminology and Symbols CAS Calibrated Airspeed means the indicated speed of an aircraft corrected for position and instrument error Calibrated airspeed is equal to true airspeed in
28. PIPER AIRCRAFT CORPORATION SUPPLEMENT 4 PA 34 220T SENECA HI 9 Vertical Mode Switch Trim Up Dn Operation of the vertical trim switch on the Mode Controller provides a convenient means of adjusting the ALT or PAH angle function without disengaging the mode I0 Go Around Mode GA The mode may be engaged at any time by depressing the GO AROUND switch on the left engine throttle GA will illuminate on the annunciator panel indicating mode status The GA mode provides a fixed pitch angle indication on the FDI The AP if engaged will disengage GA will cancel all other vertical modes as well as APPR or NAV CPLD VOR PROCEDURES 1 Tune NAV receiver to appropriate frequency 2 Set desired heading with the HDG BUG to intercept radial and engage HDG and AP Maximum recommended intercept angle 90 3 Select desired radial and engage NAV The FCS will remain on HDG as indicated on the annunciator panel and in ARM on the NAV mode When the airplane approaches the beam the system will automatically couple HDG will decouple and track in NAV mode and indicate CPLD on the annunciator panel 4 A new course may be selected over the VOR station when operating in the NAV mode by selecting a new radial whenthe To From indication changes 5 For VOR approach see approach procedure G APPROACH PROCEDURES 1 Tune ILS or VOR 2 Set CDI for front course 3 Set Heading Bug and engage HDG to intercep
29. Preliminary Control Settings Place the Indicator controls in the following positions before applying power from the aircraft electrical system INTensity Gov ca ake Fully counterclockwise in OFF TIET sva dq ax CEA Uer Fully upward RANGE 24555565 Pees s 10 nautical miles D Display Area See item A B and C for explanation of alphanumeric display A Mode Field Selected mode is displayed as WX CYC MAP or TEST STBY ts displayed if R T is warming up and no mode is selected after turn on WAIT is displayed if a mode is selected prior to end of warm up or when Indicator and Antenna are syn chronizing B Auxiliary FRZ is displayed as a blinking word if Field radar is in freeze mode to remind pilot that radar display is not being updated for incoming target returns 2 3 and color bar legend is displayed in WX C TEST and MAP modes In weather mode color bar is green yellow and red In map mode color bar is cyan yellow and magenta C Range Mark Five labeled range marks are displayed Identifiers on each range Label of furthest mark is same as range selected Range and azi muth marks are displayed in cyan for WX C and TEST green for MAP INDICATOR CONTROLS AND DISPLAY FEATURES Table 4 3 ISSUED JANUARY 8 1981 REPORT VB 1110 3 9 81 SECTION 9 SUPPLEMENT 12 a aea
30. SECTION 2 LIMITATIONS 2 4 GENERAL This section provides the FAA Approved operating limitations instrument markings color coding and basic placards necessary for the operation of the airplane and its systems This airplane must be operated as a normal category airplane in compliance with the operating limitations stated in the form of placards and markings and those given in this section and handbook Limitations associated with those optional systems and equipment which require handbook supplements can be found in Section 9 Supplements 2 3 AIRSPEED LIMITATIONS SPEED KIAS KCAS Design Maneuvering Speed Va Do not make full or abrupt control movements above this speed 4750 ibs 140 140 3205 185 114 115 CAUTION Maneuvering speed decreases at lighter weight as the effects of aerodynamic forces become more pronounced Linear interpolation may be used for intermediate gross weights Maneuvering speed should not be exceeded while operating in rough air ISSUED JANUARY 8 1981 REPORT VB 1110 2 1 SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS PA 34 220T SENECA SPEED KIAS KCAS Never Exceed Speed Do not exceed this speed in any operation 205 203 Maximum Structural Cruising Speed VNo Do not exceed this speed except in smooth air and then only with caution 166 165 Maximum Flaps Extended Speed Vrt Do not exceed this speed with the flaps extended 115 113 Maximum Gear
31. moon Press the AP DISC TRIM INTERRUPT switch on the pilot s control wheel Move the Autopilot ON OFF handle to the OFF position Engage the Go Around mode Pull the AUTOPILOT circuit breaker out OFF Turn off the RADIO POWER switch Operate manual electric trim switch UP or DN The following conditions will cause the Autopilot to auto matically disengage a b Power failure internal Flight Control System failure With the KCS 55A compass system a loss of compass valid displaying HDG flag disengages the Autopilot and Flight Director when a mode using heading information is engaged With the HDG flag present only vertical modes can be selected for FD or Autopilot operation MAXIMUM ALTITUDE LOSSES DUE TO AUTOPILOT MALFUNCTIONS Cruise Climb Descent 400 feet Maneuvering 100 feet APPR 50 feet SE APPR 50 feet CAUTION When the autopilot is engaged manual application of a force to the pitch axis of the control wheel for a period of three seconds or more will result in the autotrim system operating in the direction to create a force opposing the pilot This opposing mistrim force will continue to increase as long as the pilot applies a force to the control wheel and will ultimately overpower the autopilot If the autopilot is disengaged under these conditions the pilot may be required to exert control forces in excess of 50 pounds to maintain the desired airplane attitude The pilot will h
32. ta Adjust oxygen mask ib Turn on system c Monitor flow indicators and quantity CAUTION Do not use oxygen system below 200 PSI to prevent contamination and or moisture from entering depleted cylinder regulator assembly If cylinder has been depleted it must be re moved and refurbished in accordance with the manufacturer s recommended procedures SECTION 5 PERFORMANCE No changes 10 the basic performance provided by Section 5 of this _ Pilovs Operating Handbook are necessary for this supplement REPORT VB 1ITO ISSUED JANUARY 8 1981 9 12 4of4 REVISED SEPTEMBER 23 1983 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 3 PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO 3 FOR AIR CONDITIONING INSTALLATION PIPER DWG 36809 SECTION 1 GENERAL This supplement supplies information necessary for the operation of the airplane when the optional air conditioning system is installed in accor dance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with the complete handbook This supplement has been FAA Approved and must remain in this handbook at ali times when the optional air conditioning system is installed FAA APPROVED Wad Trama WARD EVANS D O A NO 0 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED JANUARY 8 198
33. 1981 REPORT VB 1110 REVISED FEBRUARY 25 1982 11 of 12 9 123 SECTIONS PIPER AIRCRAFT CORPORATION SUPPLEMENT 18 PA 34 220T SENECA THIS PAGE INTENTIONALLY LEFT BLANK REPORT 1110 ISSUED APRIL 21 1981 9 124 12 0712 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 19 m n ee terr A n n aa PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO 19 FOR BENDIX RDR 160XD IN 232A WEATHER RADAR SYSTEM SECTION 1 GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Bendix RDR 160X D IN 232A Weather Radar System is installed in accordance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with the complete handbook This supplement has been FAA Approved and must remain in this handbook at all times when the optional Bendix RDR 160XD IN 232A Weather Radar System is installed FAA WARD EVANS D O A NO SO 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED FEBRUARY 25 1982 REPORT VB 1110 1 of 6 9 125 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 19 PA 34 220T SENECA HI a SECTION 2 LIMITATIONS No changes to the basic limitations provided by Section 2 of this Pilot s Operating Handbook are necessary for this supplement SECTION 3 EMERGENCY PROCEDURES No changes to the basic Emergen
34. 4 pages 17 Century 21 Autopilot Installation 6 pages 18 Century 41 Autopilot 12 pages 9 19 9 33 9 45 9 55 9 59 9 65 9 71 9 75 9 79 9 85 9 91 9 97 9 103 9 107 9 113 REPORT VB 1110 9 i TABLE OF CONTENTS cont SECTION 9 cont Paragraph Supplement Page No No 19 Bendix RDR 160X D IN 212A Weather Radar SuSE nm dian deti an ee RUM EE as 6 pages 9 125 20 EDO Avionics Command Electric Trim System Model 923 4 pages 9 131 M Century 31 Autopilot Installation 20 pages 9 135 REPORT VB 1110 9 ii PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA HI SUPPLEMENTS SECTION 9 SUPPLEMENTS 9 1 GENERAL This section provides information in the form of Supplements which are necessary for operation of the airplane when equipped with one or more of the various optional systems and equipment not provided with the standard airplane of the Supplements listed on the preceding pages are FAA Approved and are required to be aboard the airplane when the related equipment is installed Supplements for equipment installed should be identified to avoid confusion Supplements for equipment not installed may at the owners discretion be segregated or removed from the pilot s operating handbook ISSUED JANUARY 8 1981 REPORT 1110 9 1 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA 34 220T SENECA 11 T
35. 5 Select slaving amplifier No 2 if equipped If not equipped proceed with No 7 below 6 Reset heading while checking slaving meter If proper slaving indication is not obtained proceed with No 7 below 7 Switch to free gyro mode and periodically set card as an unslaved gyro NOTE In the localizer mode the TO FROM arrows may remain out of view depending upon the design of the NAV converter used i in the instal lation REPORT VB 1110 ISSUED APRIL 21 1981 9 116 4 of 12 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA Ili SUPPLEMENT 18 SECTION 4 NORMAL PROCEDURES a NORMAL OPERATING PROCEDURES NOTE This autopilot is equipped with an A P OFF warning horn that will sound for approxi mately 4 seconds anytime the autopilot is disengaged This will be accompainied by an message flash on the autopilot remote annunciator for approximately 5 seconds The horn may be silenced before the 4 second time limit is up by 1 Pressing T bar atop command trim switch 2 by re engaging the autopilot NOTE If this autopilot is equipped with a Flight Director steering horizon the F D must be switched on before the autopilot may be engaged Any autopilot mode may be selected and will be retained upon autopilot engagement CAUTIONS Flight Director Autopilot versions only are equipped with a remote go around switch When G A m
36. 8 5 PREVENTIVE MAINTENANCE The holder of a Pilot Certificate issued under FAR Part 61 may perform certain preventive maintenance described in FAR Part 43 This maintenance may be performed only on an aircraft which the pilot owns or operates and which is not used to carry persons or property for hire except as provided in applicable FAR s Although such maintenance is allowed by law each individual should make a self analysis as to whether he has the ability to perform the work All other maintenance required on the airplane should be accomplished by appropriately licensed personnel If maintenance is accomplished an entry must be made in the appropriate logbook The entry should contain a The date the work was accomplished b Description of the work c Number of hours on the aircraft d The certificate number of pilot performing the work e Signature of the individual doing the work ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED SEPTEMBER 23 1983 8 3 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING SERV amp MAINT o PA 34 220T SENECA in ASA bt sym aa 8 7 AIRPLANE ALTERATIONS If the owner desires to have his aircraft modified he must obtain FAA approval for the alteration Major alterations accomplished in accordance with Advisory Circular 43 13 2 when performed by an A amp P mechanic be approved by the local FAA office Major alterations to the basic airframe or svstems not covered b
37. Center knob in position varies INM digit Center knob out position varies 0 INM digit 8 DUAL CONCENTRIC KNOBS LEFT SIDE OF PANEL a Mode Select Outer knob changes mode from VOR to VOR PAR to RNV to RNV APR and rolls over b WPT Select Center knob selects waypoint fr m 1 to 9 and rolls over 9 COURSE SELECT KNOB Located in remote unit Selects desired course through the VOR ground station waypoint MODE SELECTOR KNOB NAV FREQ DISPLAY WAYPOINT DISTANCE MODE ANNUNCIATOR WAYPOINT RADIAL DATA BUTTON A C waveonr SELECTOR KNOB INPUIT CONTROL USE B TTON ON OFF aN oon IDENT CONTROL KNS 81 DIGITAL AREA NAVIGATION SYSTEM CHECK BUTTON SECTION 5 PERFORMANTE changes to the basic performance provided by Section 5 of this Pilot s Operating Handbook are necessary for this supplement REPORT VB 1110 2222 ISSUED JANUARY 8 1981 9 78 4of4 5 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA IH SUPPLEMENT 12 nri e aaa ri T rr e EP aa atari er m ry iaa tH y PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO 12 FOR RCA COLOR WEATHERSCOUT WEATHER RADAR SYSTEM SECTION 1 GENERAL This supplement supplies information necessary the operation of the airplane when the optional RCA Color WeatherScout 11 Weather Radar System is installed in accordance with
38. GYRO SUCTION FAILURES Pressure below 4 5 in Hg ota eta Bcd Rara t ae Ce eb orate eine Mos increase to 2600 Altitude MP ale net ees xiu us descend to maintain 4 5 in Hg Use electric turn indicator to monitor Directional Indicator and Attitude Indicator performance SPINS T d retard to idle CEA eke full opposite to direction of spin Control Wheel iau a SER n release back pressure Control wheel Pe ee ee EE 2 2 full forward if nose does not drop rra neutral neutralize when rotation stops Control WHEE 12525 coo me Sa oer PPS E aw smooth back pressure to recover from dive EMERGENCY DESCENT 2h Vata Sos roc oe HEIDE M d closed escis ERICH ES ER M RA full forward NEC TER TE TR as required for smooth operation landing aeneus ER ERE A extend Airspeed 30 KIAS REPORT VB 1110 ISSUED JANUARY 8 1981 3 10 REVISED APRIL 9 1982 PIPER AIRCRAFT CORPORATION SECTION 3 34 2207 SENECA EMERGENCY PROCEDURES rr i i M tt BITE AMAA RET T a i A Te COMBUSTION HEATER OVERHEAT Unit will automatically cut off Do not attempt to restart OPEN DOOR ENTRY DOO
39. INDICATOR CONTROLS AND DISPLAY FEATURES cont Table 4 3 cont 2 INT OFF 3 WX C REPORT VB 1110 9 82 4 of 6 PIPER AIRCRAFT CORPORATION PA 34 220T SENECA Rotary control used to regulate bright ness intensity of display On Off function Full CCW rotation of intensity control places system in OFF condition CW rotation from OFF setting turns system on ST BY is displayed until WX C MAP or TEST is selected If WX C or MAP is selected initially or prior to the end of the warm up period WAIT will be displayed until RT warms up approximately 30 seconds if TEST is selected immediately WAIT will be displayed until Antenna is syn chronized less than 4 seconds and then test pattern will appear Alternate action pushbutton switch used to select weather mode cyclic contour mode selected at turn on system will come up in weather mode second depression of switch will select cyclic contour mode ISSUED JANUARY 8 1981 REVISED SEPTEMBER 23 1983 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA 11 4 MAP 5 TEST 6 FRZ 7 2 8 TILT 9 10 25 50 100 200 01 1005 UPPLEMENT 12 REM IRR mE If selected when system is already oper ating in another mode system will return to weather mode second switch depres sion will select cyclic contour mode In cyclic contour mode 3 level red dis play will flash on and off at Tr second
40. Most of the electrical switches including the battery switch and switches for magnetos pumps starters alternators lights and heat are conveniently located on the switch panel Figure 7 15 to the left of the pilot s control wheel An optional starting installation known as Piper External Power PEP 1 accessible through a receptacle located on the lower left side of the nose section An external battery can be connected to the socket thus allowing the operator to crank the engine without having to gain access to the airplane s battery REPORT VB 1110 ISSUED JANUARY 8 1981 7 18 REVISED AUGUST 9 1982 PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA entree eA ee ee ALTERNATOR STARTER FIEL amp LEFT RIGHT ACCSY EY eur Y dus rr wu CLE 1 AUX AVIONICS PL BUS SWITCH TO RADIO BUS 22 i gt EXTERNAL 5 POWER oy OPTIONAL OVERVOLTAGE i CIGAR RELAY i LIGHTER 4 NS 1 VOLTAGE P 6 REGULATOR STARTER sw o STARTER SOLENOID RELAYS LEFT STARTER TO RADIO BUS BAR ALTERNATOR AND STARTER SCHEMATIC S N 34 8133001 THRU 34 8233205 _ Figure 7 13 ISSUED JANUARY 8 1981 REPORT VB 1110 7 19 REVISED AUGUST 9 1982 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA A ETUR amp L ALTERNATOR FIELD a
41. Pressing the AP ON OFF switch on the programmer OFF Depressing Master Disconnect Trim Interrupt switch d Pulling the AP System Circuit breaker OFF 2 Autotrim may be disconnected by Anv action in 1 above or b Pulling the trim system circuit breaker OFF After failed system has been identified leave system circuit breaker open and do not operate until the system failure has been identified and corrected 3 Altitude loss During Malfunction An autopilot malfunction during climb cruise or descent with a 3 second delay recovery initiation could result in as much as 60 of bank and 500 foot altitude loss Maximum altitude loss was recorded at 180 K IAS during descent b An autopilot malfunction during an approach single engine gear down flaps up with second delay in recovery initiation could result in as much as 18 bank and 120 foot altitude loss 4 Single Engine Operations a Engine failure during approach operation Disengage autopilot conduct remainder of approach manually b Engine failure during climb cruise or descent Retrim aircraft perform aircraft engine inoperative procedures c Maintain aircraft Yaw Trim throughout all single engine operations either by aircraft rudder trim or manual rudder application b COMPASS SYSTEM Emergency Operation with Optional NSD 360A HSH Slaved and or Non Slaved a Appearance of HDG Flag Check air supply gauge vac or pressure f
42. T hrobtles aae teh e retard to stop turn Pilch atutade TEE lower nose to accelerate above 66 KIAS Operative increase power as airspeed increases above 66 KIAS if altitude permits a restart may be attempted If restart fails or if altitude does not permit restart see Engine Securing Procedure ONE ENGINE INOPERATIVE LANDING engine DEODou CIS E eds feather When certain of making field Rep iin hee mul Du Sas Pe Benes extend Wina flaps as Tequited lower Maintain additional altitude and speed during approach Final approach speed ior re rr eens 90 KIAS 67 KIAS with aft doors removed REPORT VB 1110 ISSUED JANUARY 8 1981 3 4 REVISED FEBRUARY 25 1982 PIPER AIRCRAFT CORPORATION SECTION 3 34 2207 SENECA EMERGENCY PROCEDURES SHOL AVOIDE D IF AT AL L POSSIBL E i edP reti am Koc o i forward CES ux Ra ated a a ES E i ed NM forward Throttle 52 esatto PRA ER Rer 40 in Hg Max open slowly Fits v a 7155 15 retract Landing gear ieee hae eases Sa Gee ee Ree eee ss retract ____ 92 KIAS 277 tied set Cowl flap operating EPI as required AIR START UNFEATHERING PROCEDURE Fuel selector engine n n DOS
43. a No smoking allowed when oxvgen system is in use b Oxygen duration Bottle pressure 1850 PSI c Six occupants maximum when oxygen is required DURATION IN HOURS AT ALTITUDE Based on 90 Consumption Persons Using System 10 000 15 000 20 000 25 000 127 8 5 2 3 9 4 1 4 2 4 3 3 2 6 2 7 2 8 2 8 4 1 9 20 EN 2 1 5 1 5 1 6 LT 6 1 3 1 4 1 4 1 4 SECTION 3 EMERGENCY PROCEDURES a Time of useful consciousness at 25 000 feet is approximately 3 minutes ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED SEPTEMBER 23 1983 3of4 9 11 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 2 m PA 34 220T SENECA rema a a M MN UP 3 S S ib oxygen flow is interrupted as evidenced by the flow indicators or hypoxic indications d Install another mask unit 2 Install mask connection in an unused outlet if available 3 Uf flow is not restored immediately descend to below 12 500 feet In the event an emergency descent becomes necessary CLOSE the throttles and move the propeller controls full FORWARD Adjust the mixture control as necessary to attain smooth operation Extend the landing gear at 130 KIAS and maintain this airspeed SECTION 4 NORMAL PROCEDURES PREFLIGHT a Check oxygen quantity b Turn on oxygen system and check flow indicators on all masks masks are stored in the seat pockets of the front and middle seats IN FLIGHT
44. is200 NN BM 6 51 FRONT abate poe 4 3 Php ffs BASI 28005 f LIE 2600 n H FOR LL NE C IUE c 2 a 2400 0 lt ES Es E 7 gt lt WEIGHT 2200 ss VS 82 84 86 88 90 92 94 ENVELOPE LOCATION INCHES AFT DATUM 2 2 H Moment change due to retracting Landing Gear 32 in lbs ISSUED JANUARY 8 1981 REPORT 1110 6 17 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 34 220T SENECA THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED JANUARY 8 1981 6 18 TABLE OF CONTENTS SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS oo T TC un 0C d no o Paragraph Page No 7 1 The Airplanes hr 7 1 7 3 7 1 7 5 ______________ 7 2 Propellers 7 5 7 9 Gear 7 6 4214 Brake System 7 1 7 13 Flight Control System n 7 1 7 15 Fuel System 7 1 7 17 Electrical System hh rhe 7 1 7 19 Vacuum 7 2 7 21 Pitot Static System iode ashes ete E een 7 2 723 Instrument 222 7 2 7
45. press number keys corresponding fo the frequency of the VOR station and press the ENTER key WAYPOINT BEARING Press BRG key press number keys corresponding to the waypoint bearing and press the ENTER key WAYPOINT DISTANCE Press DIST key press number keys corresponding to the waypoint distance and press the ENTER key STATION ELEVATION Press EL key press number keys corresponding to the station elevation in hundreds of feet and press the ENTER key INBOUND AND OUTBOUND COURSE Press CRS key press number keys corresponding to the desired inbound or outbound course depending upon whether IN or OUT annun ciator lamp is illuminated and press the ENTER key Press CRS XFR key IN OUT annunciator lamps will switch Press CRS key press number keys correspondingtothe desired inbound or outbound course as annunciated and press the ENTER key h Repeat Step f and g for any or all of the remaining waypoints ISSUED JANUARY 8 1981 REPORT VB 1110 3 of 6 9 61 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 8 PA 34 220T SENECA i Press SBY WPT key press number key corresponding to the waypoint desired to be recalled from memory and verify data G Set the display selector to BRG DST k Press the WPT XFR key totransfer the standby waypoint to active NOTE Provided the KBD NAV 1 COM I selector on the COM NAV unit is set to KBD the NAV receiver and DME will be automatically tuned to th
46. 1 Tap filter gently to remove dirt particles Do not use compressed air or cleaning solvents ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED FEBRUARY 10 1984 8 7 SECTIONS PIPER AIRCRAFT CORPORATION HANDLING SERV amp MAINT PA 34 220T SENECA TH 2 inspect filter H paper element is torn or ruptured or gasket is damaged the filter should be replaced The usable life of the filter should be restricted to one year or 500 hours whichever comes first c Installation of induction Air Filters After cleaning place filter in air box and install cover Secure cover by turning studs Replace 8 13 BRAKE SERVICE The brake system is filled with MIL H 5606 petroleum base hydraulic brake fluid This should be checked periodically or at every 50 hour inspection and replenished when necessary The brake reservoir is located in the forward maintenance area Remove the four screws and rotate the fiberglass nose cone forward and down The reservoir is 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 the Service Manual for brake lining replacement instructions 8 15 LANDING GEAR SERVICE Two jack points are provided for jacking the aircraft for servicing One is located outboard of each main landing gear Before jacking attach a tail support to the tail skid Approximately 500 pounds of ballast should be placed
47. 127 SECTION 9 SUPPLEMENT 19 PIPER AIRCRAFT CORPORATION PA 34 220T SENECA ad Ln CONTROL DISPLAY TRACK button GAIN control BRT control NAV button push on push off 4 RANGE button FUNCTION When pressed the yellow track cursor appears and moves to the left while held depressed Operation is as explained above Varies the radar receiver gain when inthe MAP mode Gain and the STC are preset in TEST function and in the WX modes Adjusts brightness of the display for varying cockpit light conditions Operational only when optional 1U 2023A Remote Computer Unit is connected When actuated provides NAV information super imposed over the MODE selected WX WXA or interface is not connected the words NO NAV will be displayed in the lower left corner Clears the display and advances the indicator to the next higher range each time the button is pressed eg 20 to 40 40 to 80 etc until 240 mile range is reached The range selected is dis played in the upper right corner on the last range mark and the distance to each of the other range marks circles is displayed along the right edge of the circles arcs CONTROL DISPLAY FUNCTIONS cont REPORT VB 1110 9 128 4046 Table 4 3 cont ISSUED FEBRUARY 25 1982 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 19
48. 19 CONTROL DISPLAY FUNCTION Function selector OFF position removes primary power from the system 2 STBY position places system in the standby condition during warm up period and when the system is not in use No display 3 TEST position selects test function to de termine operability of the system A test pattern is displayed NO transmission exists in the TEST condition 4 ON position selects the condition for normal operation Radar transmission exists in the ON position RANGE Ciears the display and places the indicator in button the next lower range each time the button is pressed eg 40 to 20 until minimum range is reached TILT contro Electrically adjusts the antenna to move the radar beam up to 15 degrees above the hori zontal or to a maximum of 15 degrees below the horizontal position The horizontal posi tion 15 indicated as zero degrees on the control TRACK When pressed a yellow track cursor line ap button pears and moves to the right one degree steps while the button is held depressed The track cursor stops when the button is released and remains for about 10 to 15 seconds then disappears unless the button is pressed again The differential heading will be indicated in yellow numerals in the upper left corner of the display and disappears simultaneously with the track cursor CONTROL DISPLAY FUNCTIONS Table 4 3 ISSUED FEBRUARY 25 1982 REPORT VB 1110 3 of 6 9
49. 1981 5 10 PIPER AIRCRAFT CORPORATION SECTION 5 PA 34 220T SENECA III PERFORMANCE 40 100 90 30 80 i 20 60 50 10 40 FAHRENHEIT CELSIUS 30 DEGREES DEGREES 20 10 10 0 20 10 20 30 30 40 40 TEMPERATURE CONVERSION CHART Figure 5 ISSUED JANUARY 8 1981 REPORT 1110 5 11 PA 34 220T SENECA PIPER AIRCRAFT CORPORATION SECTION 5 PERFORMANCE HOUHS LN3IHNHQHISNI OB32 SVDI Ort SvDI 98 0 4814 02 0 9814 Sjduiex3 HH lOcc vt Vd SVO AIRSPEED SYSTEM CALIBRATION Figure 5 3 JANUARY 8 1981 ISSUED VB 1110 REPORT 5 12 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA 34 220T SENECA STALL SPEED KIAS 0002 SaNno d LHOWM S343H041d0 319NV LOZ ve Yd 99 paeds yes 641 4 dn 5 4 ejGue 06 STALL SPEED VS ANGLE OF BANK Figure 5 5 1110 REPORT JANUARY 8 1981 ISSUED 5 13 ris OIII HA L g 911814 SJAOTHVI PINOAQUOOSMd TVIAWON 9311551 7861 SZ AN VONS 1861 8 _ 34 220 NORMAL PROCEDURE TAKEOFF ASSOCIATED CONDITIONS Example 2800 RPM AND 40 INCHES OAT 21 PAVED LEVEL DRY RUNWAY LI
50. 25 Heating Ventilating and Defrosting System 7 3 7 21 Cabin Features OR ORC 7 3 7207 Stall Watnihi seca hw esa teed by awe aye eal 7 3 7 31 Baggage Area 7 3 7 33 ERMITTELT 7 3 7 35 Piper External Power Ee 7 3 7 37 Emergency Locator Transmitter 7 3 7 39 Piper Control Wheel COCK 4 5 0 soit RS Beds 7 3 REPORT VB 1110 7 1 PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA III _ DESCRIPTION amp OPERATION SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS 7 1 THE AIRPLANE The Seneca III is a twin engine all metal retractable landing gear turbocharged airplane It has seating for up to seven occupants and two separate one hundred pound luggage compartments 7 3 AIRFRAME _The basic airframe is of aluminum alloy with steel engine mounts and landing gear and thermo plastic or fiberglass fairings Aerobatics are prohibited in this airplane since the structure is not designed for aerobatic loads The fuselage is a semi monocoque structure There is a front door on the right side and a rear door on the left cargo door is installed aft of the rear passenger door Both rear doors may opened for loading large pieces of cargo A door on the left side of the nose section gives access to the nose section baggage compartment The wing is of a conventional design and employs a lam
51. 28 si g treo ICT 194 pace e OM DQO On Dia d tif Hs BEEN TYPICAL INSTRUMENT PANEL S N 34 8133001 THRU 34 8233205 Figure 7 21 REPORT VB 1110 ISSUED JANUARY 8 1981 7 28 REVISED AUGUST 9 1982 1861 6 180201 V 1861 8 3103 7 1 210814 3409 S07 78 F 100 18 P N S 1002 TIN Vd LNAARNISNI TVOIdAT Luoddy 6CL HOURMETER RADAR ALTIMETER INDICATOR AIRSPEED INDICATOR TURN AND BANK INDICATOR ATTITUDE GYRO AUTOPILOT ANNUNCIATOR PANEL DIRECTIONAL GYRO ALTIMETER ANNUNCIATOR PANEL VERTICAL SPEED INDICATOR DUAL MANIFOLD PRESSURE GAUGE DUAL TACHOMETER AVIONICS MODE SELECTOR AUDIO MARKER PANEL RADIO MASTER SWITCH R NAV DME RADAR AIRSPEED INDICATOR COPILOT TURN ANO BANK INDICATOR ATTITUDE GYRO COPILOT DIRECTIONAL GYRO COPILOT ALTIMETER COPILOT VERTICAL SPEED INDICATOR AUTOPILOT CONTROL PANEL PILOT S MIKE AND PHONE JACKS SLAVING METER SWITCH PANEL ADF INDICATOR PANEL LIGHTS RADIO LIGHTS ENGINE GAUGES DUAL FUEL FLOW GAUGE EMERGENCY GEAR EXTENDER LANDING GEAR SELECTOR DUAL EGT GAUGE LEFT ENGINE ALTERNATE AIR CONTROL LEVER CONTROL LEVERS VACUUM GAUGE AMMETERS RIGHT NGINE ALTERNATE AIR CONTROL LEVER GROUND CLEARANCE SWITCH CONTROL FRICTION LOCK TRANSPONDER
52. 3 quarts per engine It is recom mended that oil be added if the quantity falls to 6 quarts It is recommended that engine oil be drained and renewed every 100 hours or sooner under unfavorable conditions Full flow cartridge type oil filters should be replaced each 50 hours of operation The following grades are required for temperatures OIL VISCOSITY Aviation Grade S A E No Below 40 F 1065 30 Above 40 F 1100 50 8 21 FUEL SYSTEM a Servicing Fuel System The fuel screens in the strainers require cleaning at 50 hour or 90 day intervals whichever occurs first The fuel gascolator strainers are located in the wing between the fuel selector valves and the auxiliary pumps in the nacelles The fuel injector screen is located in the housing where the fuel inlet line connects to the injector This screen should be cleaned every 50 hours of operation b Fuel Requirements The minimum aviation grade fuel for the Seneca is 100 Since the use of lower grades can cause serious engine damage in short period of time the engine warranty is invalidated by the use of lower octanes Whenever 100 or 100LL grade fuel is not available commercial grade 100 130 should be used See Fuel Grade Comparison Chart Refer to the latest issue of Continental Service Bulletin Fuel and Oil Grades ISSUED JANUARY 8 1981 REPORT VB 1110 8 11 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING SERV amp MAINT PA 34 220T SENECA
53. 5 1 inches of mercury a setting which provides sufficient vacuum to operate all the gyros at their rated RPM Higher settings will damage the gyros and with a low setting the gyros will be unreliable The regulator is located behind the instrument panel REPORT VB 1110 ISSUED JANUARY 8 1981 7 22 PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA DESCRIPTION amp OPERATION M Yo D x 4 Na 35 E gt 6 3 5 o A 5 E x 565464 2222982 EEFT ETTE VACUUM SYSTEM Figure 7 17 ISSUED JANUARY 8 1981 m REPORT VB 1110 7 23 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA 7 34 PITOT STATIC SYSTEM Pitot pressure for the airspeed indicator is sensed by an aluminum pitot head installed on the bottom of the left wing and carried through lines within the wing and fuselage to the gauge on the instrument panel refer to Figure 7 19 Static pressure for the altimeter vertical speed and airspeed indicators is sensed by two static source pads one on each side of the rear fuselage forward of the stabilator They connect to a single line leading to the instru ments The dual pickups balance out differences in static pressure caused by side slips or skids An alternate static source control valve is located below the instrument panel to the right of the control quadrant When the valve is set to the al
54. 63 5 BANK TOWARD OPERATING ENGINE E P zi NEN H H MIXTURE LEANED a EHE 2 Ed Li T pt TO 25 F RICH PEAK E T TONE ENGINE ES f INOPERATIVE Ch m gat Fk DA FN WS z FIOR TTT H 1 13 E E M ii 10 Aer tal gt H Pressure altitude 10 000 HEATER NES H ttt Weight 4000 Ibs ES re A Two engine rate of climb 1400 55 th E t H i EET PAPE TE NACL NE i EH GRAN Pann 2 Tritt EUN t mettir rt t E 40 20 20 40 500 1000 1500 2000 0100 600 OUTSIDE AIR TEMPERATURE C RATE OF CLIMB HI 6 LOCC PE Vd NOILVHOdHOO LIVHOMNHIV Widid NOLLOXS ccs 7 211814 WTI OL 3ONVISIG ONY WALL TANA QAXYSIAXH 1661 7861 SZ 1861 8 2201 _ TF ASSOCIATED CONDITIONS 4750 LBS GEAR UP COWL FLAPS 1 2 OPEN 2600 RPM amp 40 IN HG OR FULL THROTTLE Example Departure airport alt 2000 ft Departur
55. 9 1 Added Supplement 21 Revised title Revised text Added pages added Supple ment 21 Century 31 Autopilot Installation Revision Number and Revised Description of Revision Signature and Code Pages Rev 6 9 82 Deleted Note PR830923 9 131 Added Supplement No 20 U ond Sane cont thru Edo Avionics Command Ward Evans 9 134 Electric Trim System Sept 23 1983 Rev 7 4 5 Added Warning moved info 840210 to pg 4 6 4 6 Relocated info from pg 4 5 moved info to pg 4 7 4 7 Relocated info from pg 4 6 4 8 Revised procedure 4 9 Revised procedure 4 10 Revised procedure 4 166 Revised para 4 13 4 25 Revised para 4 29 4 26 Revised para 4 31 4 28 Revised para 4 33 7 1 Revised Table of Contents 1 Relocated info from pg 7 12 7 12 Moved info to pg 7 11 revised para 7 11 8 6 Revised para 5 9 moved info to pg 8 7 K 7 Relocated info from pg 8 6 moved info to pg 8 8 3 8 Relocated info from pg 8 7 9 1 Revised Table of Contents Wed Eana Ward Evans Feb 10 1984 REPORT VB 1110 vied TABLE OF CONTENTS SECTION 1 GENERAL SECTION 2 LIMITATIONS SECTION 3 EMERGENCY PROCEDURES SECTION 4 NORMAL PROCEDURES SECTION5 PERFORMANCE SECTION 6 WEIGHT AND BALANCE SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS SECTION 8 AIRPLANE HANDLING SERVICING AND MAINTENANCE SECTION 9 SUPPLEMENTS SE
56. AA oF 4 gt gt Sot und Lad Lat Sa 1 1 i 1 Perm LI 1 had UG i4 9 ad Q2 4 2 REPORT 1110 3 TABLE OF cont SECTION 3 cont Paragraph No 3 9 Engine Fire On The Ground Engine Fire In Flight ma et re don los Der hb pea 3 11 Management During One Engine Inoperative Operation oor en RO ui ex ndr Ve Eme de ERA ARR dA Mike amen id WIE DT MESA E Eos b Y eae OH 3 13 Engine Driven Fuel Pump Failure 3 15 Landing Gear Unsafe Warnings 3 17 Manual Extension Of The Landing Gear 3 19 Gear Up Emergency 3 21 Engine Failure With Rear Cabin and Cargo Doors a 3 23 Electrical 3 25 Gyro Suction 2 27 2 29 DESCENT 5225 3 24 Combustion Heater Overheat 3 33 DOOL ac he SG et d doi E A ao 3 35 Propeller ONVeraDeed na ves ese Ete Ue E b o REPORT 1110 3 ii PIPER AIRCRAFT CORPORATION
57. AH V OH SOLI 1861 8 Example O A T 10 C P A 43 4 2 2 OT Pressure altitude 10000 ft TTAKEOFF CLIMB PERFORMANCE two engine climb 1680 1pm Cek ASSOCIATED CONDITIONS engine inoperative climb 300 f p m m HE TAKEOFF POWER FULL RICH MIXTURE CUIALGEAR UP WING FLAPS 0 125 COWL FLAPS 1 2 OPEN ON OPERATING ENGINE S CLOSED ON INOPERATIVE ENGINE Do STEER 32 KIAS SCE FF ONE ENGINES 5257 INOPERATIVE 5 SL AREA ABOVE ABSOLUTE 217 j yn Ti He p Fa 4 i ULL 7 40 20 o 7 0 ao 1000 2000 0 100 200 300 400 500 OUTSIDE AIR TEMPERATURE 9 RATE OF CLIMB F P M HSONVIASO DH dd NOILOUS NOILVHOdNOO LIVHONIV VO3NAS LOZC PE Vd 3S1A3H qanssi 1861 12 HAAY 1861 8 12 6 210814 WaAMOd SQNONNIINGOS WOAIXVA GALIVULAY AVAD FONVANOANAd 8ATIO ics 0III HA PA 34 220T PERFORMANCE ASSOCIATED CONDITIONS u ONE ENGINE CLIMB a OPERATING ENGINE MCP COWL FLAPS 1 2 TWO ENGINE CLIMB CISC OPEN amp MIXTURE FULL RICH INOPERATIVE ITT BOTH ENGINES MCP COWL FLAPS 1 2 ENGINE FEATHERED amp COWL FLAPS CLOSED i ttt OPEN amp MIXTURE AS NOTED 92 KIAS 92 KIAS GEAR UP WING FLAPS 0 CET GEAR UP WING FLAPS 0
58. AIRCRAFT CORPORATION GENERAL PA 34 220T SENECA 1 7 1 9 RAE ARA eii m m HH A AR m ois m OPTIONA Number of Propellers 2 b Propeller Manufacturer McCauley c Propeller Hub amp Blade Models 1 Lett AAF32C508 82NFA 6 2 Right 3AF32C509 L82NF A 6 3 32AF32C508 R2NE A 6 4 Right 32AF32C509 1 L82NFE A 6 d Number of Blades 3 c Propeller Diameter in Maximum 76 2 Minimum 75 f Propeller Type Constant Speed Hydraulically Activated Full Feathering FUEL Fuel Capacity U S gal total 1 Without optional tanks 98 2 With optional tanks 128 b Usable Fuel U S gal total 1 Without optional tanks 93 2 With optional tanks 123 c Fuel D Minimum Grade 100 Green 100141 Blue Aviation Grade 2 Alternate Fuels Refer to latest revision ot Continental Service Bulletin Fuel and Grades Ol Oil Capacity US per engine b Specification Refer to latest revision of Continental Service Bulletin Fuel and On Grades The propellers have the same designation when deicing boots are installed REPORT VB 1110 ISSUED JANUARY 8 1981 1 4 REVISED SEPTEMBER 23 1983 PIPER AIRCRAFT CORPORATION SECTION 1 PA 34 220T SENECA HI GENERAL
59. After three to five seconds AUTOTRIM and FAIL continually 3 With TEST button on the Mode Annunciator still depressed verify Trim will not operate in either direction with the Control Wheel Switch 4 Release TEST pushbutton lights except and ATT shall extinguish Any deviation from the above sequence indicates that a failure exists in either the primary system or in the monitor circuits The autopilot and trim system shall not be operated until the failure has been identified and corrected CAUTION Recheck trim position prior to initiating takeoff FLIGHT DIRECTOR 1 Check circuit breaker IN 2 Flight director switch on steering horizon ON Adjacent to instrument on single cue horizon 3 Pitch modifier DN UP check pitch steering indicator moves appropriately 4 HDG bug RT LT check roll steering indicator moves appropriately REPORT VB 1110 ISSUED APRIL 21 1981 9 120 8 of 12 REVISED FEBRUARY 25 1982 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA IH SUPPLEMENT 18 m aa T e i a a a e t Y vt S I T i a e T T aaa t e f COMPASS SYSTEM NSD 360A For other compass systems refer to appropriate manufacturer s instructions 1 Check slaving switch in slave or slave 1 or 2 position as appropriate Slaving systems with R M I output provide only slave and free gyro positions 2 Rotate card to center slaving meter check HDG displayed with
60. CORPORATION DESCRIPTION amp OPERATION 34 220 SENECA NR 7 31 BAGGAGE AREA There are two separate baggage compartments One the nose section baggage compartment is accessible through a baggage door on the left side of the nose section It has a maximum weight capacity of 100 pounds The cabin baggage compartment located aft of seats five and six has weight capacity of 100 pounds This compartment is loaded and unloaded through the rear cabin door and it is accessible during flight Tie down straps are provided and should be used at all times A cargo loading door installed aft of the rear facilitates the loading of bulky items All cargo baggage compartment and passenger doors use the same key A nose section baggage compartment light illuminates automatically whenever the baggage door is opened The baggage compartment light is independent of the aircraft battery switch therefore when the baggage door is opened the light will illuminate regardless of the position of the battery switch When the baggage compartment light option is installed the baggage door should not be left open or ajar for extended time periods as battery depletion could result An optional forward baggage door adjar annunciator system 15 avail able which senses the baggage door latch pin position Failure to latch the forward baggage door will illuminate an amber light on the pilot s annunci ator panel The annunciator when
61. COURSE SELECT KNOB Located in CDI unit Selects desired course through the VOR ground station or waypoint SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of this Pilot s Operating Handbook are necessary for this supplement REPORT VB 1110 4 22 ISSUED JANUARY 8 1981 9 74 4 of 4 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 11 PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO 11 FOR KNS 81 DIGITAL AREA NAVIGATION SYSTEM PIPER DWG 39810 SECTION 1 GENERAL This supplement supplies information necessary for the operation of the airplane when the optional KNS 81 Navigation System is installed in accordance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with the complete hand book This supplement has been FAA Approved and must remain in this handbook at all times when the optional KNS 81 Navigation System is installed FAA APPROVED as es WARD EVANS D O A NO 50 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED JANUARY 8 1981 REPORT VB 1110 1014 9 75 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 11 PA 34 220T SENECA HI SECTION 2 LIMITATIONS No changes to the basic limitations provided by Section 2 of this Pilot s Operating Handbook are necessary for this supplement SECTION 3 EMERGENCY PROCEDURES No changes to t
62. Continued observation is alwavs advisable in stormy areas SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 ofthe Pilot s Operating Handbook are necessary for this supplement REPORT VB 1110 ISSUED JANUARY 8 1981 9 102 6016 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT i6 PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO 16 FOR PROPELLER SYNCHROPHASER INSTALLATION PIPER DWG 87719 SECTION 1 GENERAL This supplement supplies information necessary for the operation of the airplane when the optional propeller synchrophaser is installed in accor dance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with the complete handbook This supplement has been FAA Approved and must remain in this handbook at all times when the optional propeller synchrophaser is installed FAA 2 WARD EVANS D O A NO 50 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED APRIL 21 1981 REPORT 1110 1 of 4 9 103 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 16 PA 34 220T SENECA P A The function of the synchrophaser is to maintain both propellers at the same RPM and at a selected phase angle This eliminates the propeller beat effect and minimizes vibration When the synchrophaser is i
63. DESCENT AT 1000 FPM AND 145 KIAS NO WIND 4 2 GAL FUEL FOR START TAXI AND T o PEPEE EE EER MGH SPEED 75 LEANED IN 1 ECONOMY 8535 5 14 EEEE WITH PROCEDURES IN SECTION 4 37 285 000 MESA NM Example r1 n POWER Cruise altitude 17500 ft H dO Power 55 TEREP i Range with reserve 625 nm finge with no reserve 15 000 7 RANGE INCLUDES CLIMB BEA AMD DESCENT DISTANCES 5 H RANGE INCREASES APPROX E eMe LLL LEES Fi FOR EACH ABOVE 10 000 711 rii 1570 TEMP amp DECREASES APPROX 1 FOR EA j HH i CEULCDELICC BELOW STD TEMP 5000 He npepe Er PR RET ef 4 SEA LEVEL LETEELEELT amp 500 600 700 800 500 700 800 RANGE NAUTICAL MILES RANGE NAUTICAL MILES WITH 45 MIN RESERVE AT 45 POWER WiTH MO RESERVE Hi VOUNAS LOcCvt Vd NOLLVNHOdNOO Nddid NOLLOSS 95 5 4 OIII HA Q3SIA3N Ganssi 16 5 211814 SNOTIVO EUI 18118 AONYA ALTITUDE FEET 861 ET 1861 8 ANVONVE _ 34 220 RANGE CRUISE POWER USABLE FUEL 123
64. Extended Speed Vir Do not exceed this speed with landing gear extended 130 130 Maximum Landing Gear Extending Speed V1 0 Do not extend landing gear above this speed 130 130 Maximum Landing Gear Retracting Speed Do not retract landing gear above this speed 108 109 Lowest airspeed at which airplane is con trollable with one engine operating at takeoff power and no flaps 66 65 One Engine Inoperative Best Rate of Climb Speed VYSE 92 91 2 8 AIRSPEED INDICATOR MARKINGS MARKING KIAS Red Radial Line Never Exceed 205 Red Radial Line One Engine Inoperative Air Minimum Control Speed 66 REPORT VB 1110 ISSUED JANUARY 8 1981 2 2 PIPER AIRCRAFT CORPORATION PA 34 220T SENECA MARKING Blue Radial Line One Engine In operative Best Rate of Climb Speed Yellow Arc Caution Range Smooth Air Green Arc Normal Operating Range White Arc Flap Down 2 POWER PLANT LIMITATIONS a Number of Engines b Engine Manufacturer c Engine Model Number 1 Left 2 Right d Engine Operating Limits 1 Rated Horsepower BHP 2 Max Rotational Speed RPM 3 Max Manifold Pressure Inches of Mercury 4 Max Cylinder Head Temperature 5 Max Oil Temperature e Oil Pressure Minimum red line Maximum red line f Fuel Flow Pressure Normal Operating Range green arc Maximum at Sea Level red line g Fuel Grade min grade h Number of Propellers ISSUED JAN
65. GALLONS 4750 LBS GEAR UP Cruise altitude 16500 ft COWL FLAPS CLOSED WING FLAPS UP CLIMB AT M C P Power 55 DESCENT AT 1000 FPM AND 145 KIAS NO WIND Range with reserve 894 n m 14 2 GAL FUEL FOR START TAXI AND T Range without reserve 1010 n m MIXTURES LEANED iN ACCORDANCE WITH PROCEDURES IN SECTION 32 Iu HIGH SPEED 28 000 H NOTES ECONOMY 165 RANGE INCLUDES CLIMB amp s HH T DESCENT DISTANCES rr BERI BERERRE 7 55 POWER J t 8 0 TEMP amp DECREASES 1 20 000 Ed LUN M FOR EACH C BELOW EEEEEEENF tht i HiH 500 500 700 800 RANGE NAUTICAL MILES RANGE NAUTICAL MILES WITH 45 MIN RESERVE AT 45 POWER WITH NO RESERVE 8 NOILVHOdHOO LIVHONHIV NHidld HI VOUNAS OA3SIAHM 6861 EZ H38IAHLdWS LCS Ganssi t 1861 8 80814 65 6 11814 6 SNOTIVO 6 JONVHOONMH 34 220 eee TTT Tt tt tt ENDURANCE 5 XH GEAR UP COWL FLAPS CLOSED WING FLAPS UP CLIMB AT M C P xample DESCENT 1000 FPM AND 145 KIAS NO WIND Cruise attitude 16500 ft 42 GAL FUEL FOR START TAXI AND
66. Harsh abrasives or alkaline soaps or detergents could make scratches on painted or plastic surfaces or could cause corrosion of metal Cover areas where cleaning solution could cause damage To wash the airplane use the following procedure 1 2 3 4 5 6 Flush away loose dirt with water Apply cleaning solution with a soft cloth a sponge or a soft bristle brush To remove exhaust stains allow the solution to remain on the surface longer To remove stubborn oil and grease use a cloth dampened with naphtha Rinse all surfaces thoroughly Any good automotive wax may be used to preserve 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 ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED FEBRUARY 25 1982 8 17 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING SERV amp MAINT PA 34 220T SENECA IH d Cleaning Windshield and Windows 1 Remove dirt mud and other loose particles from exterior surfaces with clean water 2 Wash with mild soap and warm water or with aircraft plastic cleaner Use a soft cloth or sponge ina straight back and forth motion Do not rub harshly 3 Remove oil and grease with a cloth moistened with kerosene CAUTION Do not use gasoline alcohol benzene carbon tetrachoride thinner acetone or window cleaning sp
67. KEAS and case back on the wheel enough to fet the airplane off and climb past obstacle After obstacle clearance accelerate to the best rate of climb speed 92 KIAS or higher if desired retracting the landing gear when a gear down landing is no longer possible on the runway When the shortest possible ground roll and the greatest clearance distance over 50 foot obstacle ts desired use 25 flap setting second notch Set the stabilator trim indicator slightly nose up irom the takeoff range Apply and hold the brakes and bring the engines to full power before release Release the brakes accelerate to 64 KIAS and rotate firmly so that when passing through the 50 foot height the airspeed ts approximately KIAS Retract the gear when gear down landing is no longer possible on the runway it should be noted that the airplane is momentarily near when using the above procedure IN THE EVENT THAT AN ENGINE FAIL URE SHOULD OCCUR WHILE THE AIRPLANE 15 BELOW IT IS MANDATORY THAT THE THROTTLE ON THE OPERATING ENGINE BE RETARDED AND THE NOSE LOWERED IMMEDI ATELY TO MAINTAIN CONTROL OF THE AIRPLANE It should also be noted that when a 25 flap setting ts used on the takeoff rofl an effort to hold the airplane on the runway too long mav result in wheel barrowing tendency This should be avoided The distances required using this takeoff procedure are given on a chart in the Performance S
68. LJIVHONIV Widld HI VOXNUS LOZC PE Vd QUSIAWN 2861 66 IIHdV 1861 8 11 5 aanssi 61 6 221814 SAVIA 00 4JONVISIOG 4015 _ 34 2201 _ HF ASSOCIATED CONDITIONS Example Hi STANDARD WHEELS TIRES AND BRAKES OAT 21 FULL POWER BEFORE BRAKE RELEASE Pressure altitude 2000 ft 1177 09 WING FLAPS ABORT SPEED 78 KIAS Gross weight 3969 Ibs FEJT BOTH THROTTLES CLOSED AT ENGINE FAILURE Head wind 9 knots Accelerate amp distance 3260 ft DISTANCES INCLUDE A THREE ELL SECOND TIME n H T DTE HILL I UN HN is LL 4000 3500 OUTSIDE AIR TEMPERATURE WEIGHT POUNDS CAINO COMPONENTS KTS Hi VOANAS LOCC PE Vd NOLLVHOdHOO LIVHOMNWIV 83414 BSONVIALOA 5 NOILOAS 81 5 INOd3iN OIII HA 1861 8 O30SSI 1 o1n814 SZ HONV ILSIG 4015 GANY ZLVHOGTNOOV A 3 4 220T ___ ACCELERATE AND STOP DISTANC ASSOCIATED CONDITIONS FULL POWER BEFORE BRAKE RELEASE WING FLAPS 25 ABORT SPEED 64 KIAS DISTANCES INCLUDE A THREE SECOND RECOGNITION TIME MAXIMUM BRAKING PAVED LEVEL DRY RUNWA Example COWL FLAPS 1 2 OPEN HHH debe Dd 1444 41
69. Line Max at Sea Level Cylinder Head Temperature Green Arc Normal Range Red Line Maximum Oil Temperature Green Arc Normal Operating Range Red Line Maximum Oil Pressure Green Arc Normal Operating Range Yellow Arc Caution Ground Operation Only Red Line Minimum Red Line Maximum Manifoid Pressure Green Arc Normal Operating Range Red Line Maximum Exhaust Gas Temperature Red Line Green Arc Yellow Arc 65 to 75 Leaning Limit ISSUED JANUARY 8 1981 500 RPM to 2600 RPM 2600 RPM to 2800 RPM 2800 RPM 3 5 PSI to 18 1 PSI 18 1 PSI to 21 0 PSI 21 0 PSI 240 F to 460 460 F 100 F to 240 F 240 30 PSI to 80 PSI 10 PSI to 30 PSI and 80 PSI to 100 PSI 10 PSI 100 PSI 10 IN to 40 IN 40 IN HG 1650 F 12005 F to 1525 2 1525 F to 1650 F REPORT VB 1110 2 5 SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS PA 34 220T SENECA MENENNEMMWMMMMMMMu O 2 41 WEIGHT LIMITS a Max Ramp Weight 4773 LBS b Max Takeoff Weight 4750 L BS c Max Landing Weight 4513 LBS d Max Weights in Baggage Compartments Forward 100 LBS Aft 100 LBS e Max Zero Fuel Weight Standard Refer to Section 6 Weight and Balance 4470 LBS 2 13 CENTER OF GRAVITY LIMITS Weight Forward Limit Rearward Limit Pounds Inches Aft of Datum Inches Aft of Datum 3400 82 0 94 6 4250 86 7 94 6 4750 9
70. NORMAL PROCEDURES en wee ee Ag Dag quit Beeld free tae S PENES ANE OLE check Navigation and landing lights 0 2 00 n check Cete DUO TER E GE clear BEFORE STARTING ENGINES Elise ci tC QURE UE Sis adjusted secure Seat belts and harness y etr xy ES fasten adjust check inertia reel Parking een SPERA RE oce dx IAE e E scl WARNING No braking will occur if Knob b pulled before brake application ede baci velt sa mdr dco ut dt ee BER in OFF gei e E dorus Eee OPEN EE NR TEL Ree Dee e ae OFF EN 22 aon ON STARTING ENGINES AIRPLANE EQUIPPED WITH STANDARD PRIMER SYSTEM Eur sel Scam ai CAE a dl ON quartet FULE RICH THEW RR coena scis E o bd HER IL tee Sot Bude Uo didis half travel Prop VOU seks utm FULE FORWARD ND MIT Pr ON Ipnition ON Propellets nce ey Era EXE d clear engage adjust when engine starts check Repeat for opposite engine FIO KOREA Pee Profis check 4520 os eet ah be eee check ISSUED JANUARY 8 195 REPORT VB 1116 REVISED FEBRUA
71. OO 4 17 STARTING ENGINES AIRPLANE EQUIPPED WITH OPTIONAL ENGINE PRIMER SYSTEM NOTE Engine starts can be accomplished down to ambient temperatures of 20 F with engines equipped with standard massive electrode spark plugs Below that temperature fine wire spark plugs are highly recommended to ensure engine starts and are a necessity at 10 F and below In addition the use ofexternal electrical power source and preheat is also recommended when ambient temperatures are below 209 Upon entering the cockpit begin starting procedure by moving the fuel selector to ON Advance the mixture to full RICH and the throttle and prop controls to full FORWARD Turn the battery switch and the ignition switches mag ON The auxiliary fuel pump should be OFF Push primer switch and hold for the required priming time see Figure 4 3 Close throttle and immediately engage starter With ambient temperatures above 20 starts may be made by discontinuing priming before engaging starter With ambient temperatures below 20 F starts should be made by continuing to prime during cranking period Do not release starter until engine accelerates through 500 RPM then SLOWLY advance throttle to obtain 1000 RPM Release primer and immediatelv place auxiliary fuel pump switch to LO Auxiliary fuel pump operation will be required for one to three minutes during initial engine warm up When starting at ambient temperatures of 20 F and below oper
72. REPORT VB 1110 ISSUED AUGUST 9 1982 3 24 PIPER AIRCRAFT CORPORATION SECTION 3 PA 34 220T SENECA HI EMERGENCY PROCEDURES BARA RE A pecs 3 33 OPEN DOOR ENTRY DOOR ONLY The cabin door is double latched se the chances of its springing openin fight at both the top and side are remote However should vou forget the upper latch or not fully engage the side latch the door may spring partially open Fhis will usually happen at takeoff or soon afterward A partially open door will not affect normal flight characteristics and a normal landing can be made with door open If both upper and side latches are open the door will trail slightly open and airspeed will be reduced slightly To close the door in flight slow the airplane to 90 KIAS close the cabin vents and open the storm window the top latch is open latch Hf the side latch is open pull on the armrest while moving the latch handle to the latched position If both latches are open close the side latch then the top latch 3 35 PROPELLER OVERSPEED Propeller overspeed ts usually caused by a malfunction in the propeller governor which allows the propeller blades to rotate to full low pitch H propeller overspeed should occur retard the throttle The propeller control shouid be moved to full DECREASE rpm and then set if any control ts available Airspeed should be reduced and throttle used to maintain 2600 RPM ISSUED AUGUST 9 1982 REPORT VB 1110 3
73. REPORT VB 1110 ISSUED FEBRUARY 10 1984 9 138 40420 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 21 T SECTION 4 NORMAL PROCEDURES PREFLIGHT PROCEDURES NOTE During system functional check the system must be provided adequate D C voltage 14 0 VDC min and instrument air 4 2 in Hg min is recommended that the engine s be operated to provide the necessary power and that the aircraft be positioned in a level attitude during the functional check 1 AUTOPILOT AUTOTRIM To be performed before the first fight of each day a Trim system switch on b Engage autopilot c Move the heading bug left and right of the lubber line Observe that the control wheel moves in the direction of the heading bug displacement d Press the DN switch verify that the control wheel moves in the down direction Verify that after approximately 3 second delay the trim moves in the down direction e Press the UP switch verify that the control wheel moves in the up direction Verify that after approximately 3 second delay the trim moves in the up direction Grasp control wheel and override roll and pitch servo actuators to assure override capability g Hold control yoke and disengage autopilot by activating the AP OFF switch on the control wheel h Check controls through full travel in roll and pitch to assure complete autopilot disengagemen
74. S GALS ISSUED JANUARY 8 1981 REPORT VB 1110 2 7 2 PIPER AIRCRAFT CORPORATION LIMITATIONS 2 23 NOISE LEVEL The corrected noise level of this aircraft is 71 44 BCA with the two blade propeller and 74 24 B A with the three blade propeller No determination has been made by the Federal Aviation Adminis tration that the noise levels of this airplane are or should be acceptable or unacceptable for operation at into or out of any airport The above statement notwithstanding the noise level stated above has been verified by and approved by the Federal Aviation Administration in noise level test flights conducted in accordance with FAR 36 Noise Standards Aircraft Type Airworthiness Certification This aircraft model is in compliance with all FAR 36 noise standards applicable to this type 2 25 HEATER LIMITATIONS Operation of the combustion heater above 25 000 feet is not approved 2 27 OPERATING ALTITUDE LIMITATIONS Flight above 25 000 feet is not approved Flight up to and including 25 000 feet is approved if equipped with oxygen in accordance with 23 1441 and avionics in accordance with FAR 91 or FAR 135 2 29 GYRO SUCTION LIMITS The operating limits for the suction system 4 8 to 5 1 inches of mercury for all operations as indicated by the gyro suction gauge 2 31 OPERATION WITH AFT DOORS REMOVED The maximum speed with the aft doors removed is 129 KIAS and the minimum sin
75. SECTION 3 PA 34 220T SENECA EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES 3 1 GENERAL The recommended procedures for coping with various types of emer gencies and critical situations are provided by this section Required FAA regulations emergency procedures and those necessary for the operation of the airplane as determined by the operating and design features of the airplane are presented Emergency procedures associated with those optional systems and equipment which require handbook supplements are provided by Section 9 Supplements The first portion of this section consists of an abbreviated emergency checklist which supplies an action sequence for critical situations with little emphasis on the operation of systems The remainder of the section is devoted to amplified emergency procedures containing additional information to provide the pilot with a more complete understanding of the procedures Pilots should familiarize themselves with the procedures given in this section and be prepared to take appropriate action should an emergency arise Most basic emergency procedures such as power off landings are a normal part of pilot training Although these emergencies are discussed here this information is not intended to replace such training but only to provide a source of reference and review and to provide information on procedures which are not the same for all aircraft It is suggested that the pilot r
76. TEMPERATURE WEIGHT POUNDS 3000 WIND COMPONENTS KTS 10 15 NOLLOXS NOLLVHOdHOO LJVNONIV Widid 8 LOZC F Vd IE S 7861 ST 1861 8 GAASSI Ips 2101814 TIAIA LNOHS 3ONVISIG SNIGNVT Hu ul gt e dL g iR ME D gt m T 49 ed rr F 2 4 m O H S _ 34 2201 LLC STANDARD WHEELS TIRES AND BRAKES THROTTLES CLOSED FULL STALL TOUCHDOWN DH Es d H EE 40 WING FLAPS PAVED LEVEL DRY RUNWAY MAXIMUM Bn Coo r dI 51 uis Hd dic xampte O A T 22 C Pressure altitude 3000 ft Gross weight 3655 ibs Headwind 10 knots Landing ground roll 1120 ft Total landing distance over 50 ft barrier 1880 ft Barrier speed 74 KIAS m m 3500 3000 2500 4 12000 1000 ds as BUE F LINE 4913 LBS Hs WEIG EEEE HEEE EE EEE EHH 40 20 0 29 40 4500 4000 3500 3000 0 7 70 15 OUTSIDE AIR TEMPERATURE WEIGHT POUNDS WIND COMPONENTS KTS A334 3ONVISIO SNIGONVT VOSN3S LOCC PE V d NOILVNOdNOO LIVHOWNIV
77. Tie down ropes may be attached to tie down rings under each wing and to the tail skid The ailerons and stabilator should be secured by looping the seat belt through the control wheel and pulling it snug The rudder not be secured under normal conditions as its connection to the nose wheel holds it in position The flaps are locked when in the fully retracted position 4 51 TURBULENT AIR OPERATION In keeping with good operating practice used in all aircraft it is recom mended that when turbulent air is encountered or expected the airspeed be reduced to maneuvering speed to reduce the structural loads caused by gusts and to allow for inadvertent speed build ups which may occur as a result of the turbulence or of distractions caused by the conditions See Subsection 2 3 4 53 FLIGHT WITH REAR CABIN AND CARGO DOORS REMOVED The airplane is approved for flight with the rear cabin and cargo doors removed Certain limitations must be observed in the operation of this airplane in this configuration The maximum speed with doors removed is 129 KIAS The minimum single engine control speed is 67 KIAS Smoking is not permitted and all loose articles must be tied down and stowed The jumper s static lines must be kept free of pilot s controls and control surfaces Operation is approved for VFR non icing flight conditions only It is recommended that all occu pants wear parachutes when operating with the rear cabin and cargo doors remov
78. Upon entering the cockpit check that the landing gear selector is in the DOWN position turn OFF all avionics equipment to save power and prevent wear on the units and turn the battery switch ON Check the landing gear indicator lights to ensure that the three green lights have illuminated and that the red light has not illuminated Check the fuel supply Adequate fuel should be indicated for the flight plus reserve The cowl flaps should be OPEN to facilitate inspection and ensure cooling after engine start Return the battery switch to OFF to save the battery Check that the ignition switches are OFF and move the mixture controls to idie cut off to prevent an inadvertent start while checking the propellers Move the trim controls to neutral so that the tabs can be checked for align ment Extend and retract the flaps to check for proper operation This check is performed prior to engine start so that vou can hear any noise that might indicate binding The controls should be free and move properly Drain the pitot and static system lines through the drains located on the side panel next to the pilot s seat Fasten the seat belts on the empty seats Before leaving the cockpit drain the two crossfeed drains onthe forward side of the spar box The first item to check during the walk around is to ensure that the crossfeed drains are closed Check the right wing aileron and flap hinges and surfaces for damage and ice Make a close check of the righ
79. WEIGHT AND BALANCE RECORD cont Figure 6 7 cont REPORT VB 1110 ISSUED JANUARY 8 1981 6 8 PIPER AIRCRAFT CORPORATION SECTION 6 PA 34 220T SENECA Ill WEIGHT AND BALANCE 6 7 GENERAL LOADING RECOMMENDATIONS The following general loading recommendation is intended only as a guide The charts graphs instructions and plotter should be checked to assure the airplane is within the allowable weight vs center of gravity envelope b c f g Pilot Only Load rear baggage compartment to capacity first Without aft baggage fuel load may be limited by forward envelope for some combinations of optional equipment 2 Occupants Pilot and Passenger in Front Load rear baggage compartment to capacity first Without aft baggage fuel load may be limited by forward envelope for some combinations of optional equipment 3 Occupants 2 in front in middle Load rear baggage compartment to capacity first Baggage in nose may be limited by forward envelope Without aft baggage fuel may be limited by forward envelope for some combinations of optional equipment 4 Occupants 2 in front 2 in middle Load rear baggage compartment to capacity first Baggage in nose may be limited by forward envelope Without aft baggage fuel may be limited by forward envelope for some combinations of optional equipment 5 Occupants 2 in front 2 in middle in rear Investigation is required to determine optimum locati
80. a PROP DE ICE circuit breaker in the circuit breaker panel When the prop deice switch is actuated power is applied 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 deicer ammeter needle should indicate within the shaded portion of the ammeter for a normal reading Power from the timer is cycled to brush assemblies which distribute power to slip rings The current is then supplied from the slip rings directly to the electrothermal propeller deicer pads The Hartzell 2 blade propellers are deiced by heating the outboard half and then the inboard half of the deicer pads in a timer controlled sequence The heating sequence of the deicer pads is conducted in the following order a Outboard halves of the propeller deicer pads on the right engine b Inboard halves of the propeller deicer pads on the right engine c Outboard halves of the propeller deicer pads on the left engine d Inboard halves of the propeller deicer pads on the left engine The optional McCauley 3 blade propellers are deiced by heating the entire deicer pads alternately in the following sequence a The entire deicer pads on the right engine for 90 seconds b The entire deicer pads on the left engine for 90 seconds 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 syste
81. applying pressure on the brakes However uniess extra braking is needed or unless a strong crosswind or gusts condition exists it is best to wait until turning off the runway to retract the flaps This will permit full attention to be given to the landing and landing roll and will also prevent the pilot from accidentally reaching for the gear handle instead of the flap handle For a normal landing approach with full flaps 40 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 Approach with full flaps at 82 KIAS for a short field landing immedi ately after touch down raise the flaps apply back pressure to the wheel and appls brakes ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 17 1981 4 33 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA 34 220T SENECA IH ir e e unran T aa H Rana aiite n i a itii sra rr e e a a a i a a e APRA TT if a crosswind or high wind landing is necessary 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 wi
82. as displayed waypoint and data display to go to FRQ mode DSP BUTTON Momentary pushbutton Causes displayed waypoint to increment by and data display to go to frequency mode DATA BUTTON Momentary pushbutton Causes waypoint data display to change from FRQ to RAD to DST and back to FRQ OFF PULL ID CONTROL a Rotate counterclockwise to switch off power to the KNS 80 b Rotate clockwise to increase audio level c Pull switch out to hear VOR Ident DATA INPUT CONTROL Dual concentric knobs Center knob has in and out positions a Frequency Data Outer knob varies MHz digit carryover occurs from the units to tens position Rollover occurs from 117 to 108 or vice versa Center knob varies frequency in 05 M Hz steps regardless of whether the switch 1s in its in or out position ISSUED JANUARY 8 1981 REPORT VB 1110 3 of 4 9 73 SECTION 9 SUPPLEMENT 10 PA 34 220T SENECA b PIPER AIRCRAFT CORPORATION Radial Data Outer knob varies 10 degree digit A carryover occurs from tens to hundreds position A rollover to zero occurs at 360 degrees Center knob position varies degree digit Center knob out position varies 0 1 degree digit Distance Data Outer knob varies 10 NM digit A carryover occurs from the tens to hundreds place A rollover to zero occurs at 200 NM Center knob in position varies NM digit Center knob out position varies 0 1 NM digit 9
83. as this will result in damage to the nose gear and steering mechanism Do not tow the airplane when the controls are secured In the event towing lines are necessary ropes should be attached to both main gear struts as high up on the tubes as possible Lines should be long enough to clear the nose and ortail by not less than fifteen feet and a qualified person should ride in the pilot s seat to maintain control by use of the brakes b Taxing Before attempting to taxi the airplane ground personnel should be instructed and approved by a qualified person authorized by the owner Engine starting and shut down procedures as well as taxi techniques should be covered When it 1s ascertained that the propeller back blast and taxi areas are clear power shouid be applied to start the taxi roll and the following checks should be performed 1 Taxi a few feet forward and appiv the brakes to determine their effectiveness 2 Taxi with the propeller set in low pitch high RPM setting 3 While taxiing make slight turns to ascertain the effective ness of the steering 4 Observe wing clearance when taxiing near buildings or other stationary objects If possible station an observer outside the airplane S When taxiing over uneven ground avoid holes and ruts ISSUED JANUARY 8 1981 REPORT VB 1110 8 5 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING SERV amp MAINT 34 220 6 Do not opera
84. be maintained if at all possible Unbalanced wheels can cause extreme vibration on takeoff In the installation of new components it may be necessary to rebalance the wheel with the tire mounted REPORT 1110 ISSUED JANUARY 8 1981 8 14 REVISED FEBRUARY 25 1982 PIPER AIRCRAFT CORPORATION SECTION 8 34 220 SENECA III HANDLING SERV amp MAINT i When checking the pressure examine the tires for wear cuts bruises and slippage 825 BATTERY SERVICE Access to the 12 01 35 ampere hour battery is gained through the nose baggage compartment is located in the forward portion of the nose baggage compartment The battery container has a plastic drain tube which is normally closed off This tube should be opened occasionally to drain off any accumulation of liquid 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 DO NOT fillthe battery above the baffle plates DO NOT fill the battery with acid use distilled water only hydrometer check will determine the percent of charge in the battery 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 the mas
85. current to the motor of the hydraulic pump The three green lights to the left of the landing gear selector switch illuminate to indicate that each of the three landing gears is down and locked convex mirror on the left engine nacelle both serves as a taxiing aid and allows the pilot to visually confirm the condition of the nose gear If the gear is in neither the full up nor the full down position a red warning light on the instrument panel illuminates Should the throttle be placed in a low setting as for a landing approach while the gear is retracted a warning horn sounds to alert the pilot that the gear is retracted The gear warning horn emits a 90 cycle per minute beeping sound The green gear lights are dimmed automatically when the navigation lights are turned on For this reason if the navigation lights are 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 selector switch is placed inthe DOWN position the first thing to check is the position of the navigation lights switch If one or two of the three green lights do not illuminate when the gear down position has been selected any of the following conditions could exist for each light that is out a gear ts not locked down b bulb is burned c There is a malfunction in the indicating system In order to check the bulbs the square indicator lights can be pulled o
86. cylinder once the oxygen flow control knobis each of the oxygen plug in receptacles operates as an automatic on off valve The oxygen evlinder can be recharged through the access door aft of the rear window on the left side of the fuselage On other models the oxygen eylinder is mounted in the forward baggage compartment When fully charged the cylinder contains oxygen at a pressure of 1850 psi at 70 F The oxygen supply gauge is mounted in the co pilot s instrument panel The oxygen flow control knob labeled Oxygen Pull On is also mounted in the copilot s instrument panel The pressure regulator 18 mounted directly on the oxygen cylinder once the oxygen flow control knob is on each of the oxygen plug in receptacles operates as an automatic on off vahe The oxygen cylinder can be recharged through the forward baggage compartment on the left side of the fuselage high altitude flight is anticipated it should be determined that the oxygen supply Is adequate for the proposed flight and that the passengers arc briefed When oxygen is required the control knob shouid be pulled to the ON position allowing oxygen to flow from the cylinder through the system Connecting the constant flow mask fitting to a receptacle and turning it 90 degrees clockwise automatically releases oxygen to the mask through the on off valve feature of the receptacle The occupant then dons the mask and breathes normally for a sufficient supply of oxyge
87. dis plaved in the upper right corner on the last range mark and the distance to each of the other range marks circles is displaved along the right edge of the circles arcs ma a aa a a i a a a a a ai a Ra a a a a AA T button is actuated push on The word HOLD flashes in the upper left corner of the display The weather or ground mapping image last pre sented is retained frozen on indicator displav in order to evaluate the significance of storm cell movement Switching back to normal op eration pressing HOLD pushbutton a second time reveals direction and distance of target movement during HOLD period In HOLD the antenna continues to scan and a non updated display will continue to be presented as long as power is supplied to the system A change in range selection with indicator in HOLD results in a blank screen CONTROL DISPLAY FUNCTIONS cont Table 4 3 cont ISSUED JANUARY 8 1981 REPORT VB 1110 5 of 6 9 101 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTIS PA 34 220T SENECA HI b OPERATING PRECAUTIONS WARNING not operate the radar during refueling operations or in the vicinity of trucks or con tainers accommoding flammables or ex plosives Do not allow personnel within 15 feet of area being scanned by antenna when system is transmitting 1 Flash bulbs can be exploded bv radar energy 2 Since storm patterns are never stationary the display i 1 con stantly changing
88. door open lights The illumination of these lights in flight is an indication of a possible system malfunction The pilot should closely monitor instrument panel gauges to check the condition of a system whose corresponding light on the annunciator panel illuminates illumination of the manifold pressure overboost lights indicates manifold pressure at or above the maximum allowable 40 inches Hg During preflight the operational status of the annunciator panel should be tested by use of the press to test button When the button is depressed all annunciator panel lights should illuminate NOTE When an engine is feathered the aiternator gyro air and engine oil pressure annunciator lights will remain illuminated Optimum cockpit lighting for night flying is achieved by using a combination of the panel lights and the red overhead flood lights The panel lights are adjusted by rheostat switches below the pilot s control shaft The overhead lights are adjusted by rheostat switches adjacent to the lights A white map light can be selected from either overhead flood light Most of the electrical switches are located in the switch panel on the left side of the instrument panel A radio power switch is located near the top of the instrument panel between the radio stacks It controls the power to all radios through the aircraft battery switch The radio power switch has an ON and OFF position REPORT VB 1116 ISSUED JANUARY 8 1981 7 26 REVISED AUG
89. during cold weather Dry nitrogen gas is recommended CHAMBER PRESSURE REQUIREMENTS WITH TEMPERATURE FOR HARTZELL COUNTERWEIGHT TYPE PROPELLERS FOR PROPELLER HUBS BHC C2YF 2CKUF AND BHC C2YF 2CLKUF 70 to 100 40 to 70 40 30 0 NOTE Do not check pressure charge with propeller in feather position The spinner and backing plate should be cleaned and inspected for cracks frequently Before each flight the propeller should be inspected for nicks scratches or corrosion If found they should be repaired as soon as possible bv a rated mechanic since a nick or scratch causes an area of increased stress which can lead to serious cracks or the loss of a propeller tip The back face of the blades should be painted when necessary with flat black paint to retard glare To prevent corrosion all surfaces should be cleaned and waxed periodically The g s charge in the optional unfeathering accumulators should be maintained at 90 100 PSI It is important to use nitrogen only for this purpose since any moisture in the system may freeze and render it inopera tive Do not check this charge pressure while engine is running REPORT VB 1110 ISSUED JANUARY 8 1981 30 REVISED APRIL 9 1982 _ PIPER AIRCRAFT CORPORATION SECTION 8 PA 34 220T SENECA HANDLING SERV amp MAINT 8 19 OIL REQUIREMENTS The oil capacity of the Teledyne Continental engines is 8 quarts per engine with a minimum safe quantity of
90. empty weight includes full oi capacity and 5 0 gallons of unusabie fuel AIRPLANE USEFUL LOAD NORMAL CATEGORY OPERATION Ramp Weight Basic Empty Weight Useful Load 4773 lbs lbs ibs THIS BASIC EMPTY WEIGHT C G AND USEFUL LOAD ARE FOR THE AIRPLANE AS LICENSED AT THE FACTORY REFER TO THE APPROPRIATE AIRCRAFT RECORD WHEN ALTER ATIONS HAVE BEEN MADE Includes fuel allowances for start up taxi and run up 23 Ibs WEIGHT AND BALANCE DATA FORM Figure 6 5 REPORT VB 1110 ISSUED JANUARY 8 1981 6 6 REVISED FEBRUARY 25 1982 PIPER AIRCRAFT CORPORATION SECTION 6 34 220 SENECA EMEN WEIGHT AND BALANCE Moment Running Basic Empty Weight Page Number Moment Weight Change 12 E Z 42 a aee T T a ame an Description of Article or Modification As licensed PA 34 2201 Serial Number WEIGHT AND BALANCE RECORD Figure 6 7 ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 9 1982 6 7 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 34 220T SENECA 1H Page Number Registration Number PA 34 220T Serial Number 100 Moment Running Basic Empty Weight 100 Moment Weight Change Arm lh Wt 4 4 Poppy c eae Description of Article or Modification ula
91. for the operation of the airplane when the optional Century 31 Autopilot Model AK895 is installed in accordance with FAA Approved Piper data SECTION 2 LIMITATIONS a Autopilot OFF during takeoff and landing b Maximum airspeed for autopilot operation is 180 KIAS c Autopilot operation prohibited with more than 2 notches 259 flaps extended d Autopilot coupled single engine approaches to be conducted at 90 KIAS or faster with flaps up e Category 1 operations only Placard in full view of the pilot CONDUCT TRIM CHECK PRIOR TO FIRST FLIGHT OF DAY SEE SECTION 3 EMERGENCY PROCEDURES a AUTOPILOT In the event of an autopilot malfunction or anytime the autopilot 18 not performing as commanded do not atiempt 10 identify the problem system Regain control of the aircraft by overpowering and immediately disconnecting the autopilot Be prepared for any residual trim force and retrim as necessary using the aircraft s primary trim control CAUTION Do not overpower autopilot in pitch for more than approximately 3 seconds as the autotrim system will cause an increase in pitch over power forces REPORT VB 1110 ISSUED FEBRUARY 10 1984 9 136 20 20 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA 1H SUPPLEMENT 21 P bt i PET 1 Autopilot mas be disconnected by Pressing AP OFF bar on pilots trim switch b
92. gear Hydraulic pressure for gear operation is furnished by an electrically powered reversible hydraulic pump refer to Figures 7 5 and 7 7 The pump is activated by a two position gear selector switch located to the left of the control quadrant on the instrument panel Figure 7 3 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 Gear extension or retraction normally takes SIX 10 seven seconds CAUTION If the landing gear is in transit and the hydraulic pump is running it is NOT advisable to move the gear selector switch to the opposite position before the gear has reached its full travel limit because a sudden reversal may damage the electric pump The landing gear is designed to extend even in the event of hydraulic failure Since the gear is held in the retracted position by hydraulic pressure should the hydraulic system fail for any reason gravity will allow the gear to extend When the landing gear is retracted the main wheels retract inboard into the wings and the nose wheel retracts forward into the nose section Aerodynamic loads and springs assist in gear extension and in locking the gear in the down position During gear extension once the nose has started toward the down position the airstream pu
93. intervals Pushbutton switch used to select ground mapping mode Pushbutton switch used to select test mode Special test pattern is displayed In test transmitter does not transmit and range is automatically 100 nm Pushbutton switch used to select freeze mode Radar display is not updated with incoming target return data Asa warning to the pilot FRZ level will flash on and off at 2 second intervals Slide switch used to display three azimuth markers at 30 degree intervals Rotary control that enables pilot to select angles of antenna beam tilt with relation to airframe Rotating control CW tilts beam upward CCW rotation tilts beam downward Pushbutton switches used to select desired range Five range marks are dis played for each range INDICATOR CONTROLS AND DISPLAY FEATURES cont Table 4 3 cont ISSUED JANUARY 8 1981 REPORT VE 1110 5 of 6 9 83 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 12 34 220 ul OPERATING PRECAUTIONS WARNING Do not operate the radar during refueling operations or in the vicinity of trucks or containers accommodating flammables or explosives Do not allow personnel within 15 feet of area being scanned by antenna when system is transmitting 1 Flash bulbs can be exploded by radar energy 2 Since storm patterns are never stationary the display i is con stantly changing Continued observation is always advisable in stor
94. lbs 4 Fuel 6 lb gal x 80 480 165 5 Takeoff Weight 3969 155 6 Landing Weight aX 5 minus gX1 3969 Ibs minus 314 ibs 3655 Ibs The takeoff and landing weights are below the maximums and the weight and balance calculations have determined that the C G position is within the approved limits Takeoff and Landing Apply the departure airport conditions and takeoff weight to the appropriate Takeoff Performance and Accelerate and Stop Distance graphs Figures 5 7 thru 5 15 to determine the length of runway necessary for the takeoff and or the barrier distance The landing distance calculations are performed in the same manner using the existing conditions at the destination airport and when established the landing weight ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 9 1982 5 3 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA 34 220T SENECA The conditions and calculations for the example flight are listed below The takeoff and landing distances required for the example flight have fallen well below the available runway lengths 1 2 3 4 5 Airport Pressure Altitude 2000 ft Temperature 21 Wind Component 9 KTS Headwind Runway Length Available 7400 ft Runway Required Normal Procedure Std Brakes Takeoff 1650 ft Accelerate and Stop 3260 ft Landing NOTE The remainder of the performance charts used in thi
95. micro switch which actuates when the landing gear is retracted turns off the ventilation blower so that in flight the cabin air is circulated by ram air pressure only When the three position switch is in the FAN position during ground operation the ventilation fan blows fresh air through the heater ductwork for cabin ventilation and windshield defogging when heat is not desired When the heater controls are used either for cabin heat or for ventilation air is automatically ducted to the windshield area for defrosting The flow of defroster air to the windshield area can be increased by the activation of a defroster fan The fan is controlled by a defroster switch located on the control console between the two front seats REPORT VB 1110 ISSUED JANUARY 8 1981 7 36 SECTION 7 DESCRIPTION amp OPERATION PIPER AIRCRAFT CORPORATION PA 34 220T SENECA FIOSNOD 1OHINOO2 H3MMO18 H31SOu330 131400 434508330 131100 B31V3H 1311 00 HS3UJ u21V3H ANNI H3AAO 18 HI Y NOLLSPISINOOD U3A O18 LN3A OV3HH3AO TYNOLLdO AJIN HIV HS3u4d 131NI H3iV3H CABIN HEATING VENTILATING AND DEFROSTING SYSTEM Figure 7 23 REPORT VB 1110 ISSUED JANUARY 8 1981 7 31 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA HEATING VENTILATING AND DEFROSTING CONTROL CONSOLE Figure 7 25 REPORT VB 1110 ISSUED JANUARY 8 19
96. mode NOTE Operation of marker test function after APPR CPLD will reduce the flight control system gains If this should occur the APPR switch should be recycled REPORT 1110 ISSUED APRIL 21 1981 9 44b 14 of 16 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 6 PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO 6 FOR ICE PROTECTION SYSTEM INSTALLATION PIPER DWG 37700 SECTION 1 GENERAL This supplement supplies information necessary for the operation of the airplane when the optional ice protection system is installed in accor dance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with the complete handbook This supplement has been FAA Approved and must remain in this handbook at all times when the optional ice protection system is installed p FAA APPROVED Ce WARD EVANS D O A NO SO 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED JANUARY 8 1981 REPORT VB 1110 10110 9 45 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 6 PA 34 220T SENECA For flight into known icing conditions a complete ice protection system Figure 9 1 is required on the Seneca Ill The complete ice protection system consists of the following com ponents pneumatic wing and empennage boots wing ice detection light electrothermal propeller deice pads electric wi
97. mukti engine rating approaches an uncontrolled 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 on the operating engine and promptly lowering the nose of the airplane to accelerate to VSSE The most critical situation occurs where the stall speed and speed coincide Care should be taken to avoid this flight condition because at this point loss of directional contro occurs at the same time the airplane stalls and a spin could result REPORT VB 1110 ISSUED JANUARY 8 1981 4 36 REVISED AUGUST 17 1981 PIPER AIRCRAFT CORPORATION SECTION 4 PA 34 220T SENECA NORMAL PROCEDURES rr a eee a a B a a AMEN Vaca DEMONSTRATION a Landing Gear b Flaps c Airspeed UP UP at or above 65 KIAS Vsst Propeller Controls Throttle Simulated Inoperative HIGH RPM Engine IDLE f Throttle Other Engine MAX ALLOWABLE g Airspeed Reduce approximately knot per second until either STALL WARNING is obtained CAUTIONS Use rudder to maintain directional control heading and ailerons to maintain 52 bank towards the operative engine lateral attitude At the first sign of either or stall warning which may be evidenced by an inability to maintain heading or lateral attitude aero dynami
98. no correlation between these conditions and forecasts of reported Light Moderate and Severe conditions Therefore on the basis of flight tests the following guidelines should be observed a Flight into severe icing is not approved b 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 c Operation in light icing is approved at all altitudes icing conditions of any kind should be avoided whenever possible since anv 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 build up in order to effect the boot cycle at the optimum time Boots should be when ice has built to between 1 4 and 1 2iachthickness on the leading edge to assure proper ice removal Repeated boot cycles at less than 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 icing conditions can exist in any clouds when the temperature 15 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 have high water content and should be avoided when ever possible Freezing rain must always be a
99. 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 3 19 GEAR UP EMERGENCY LANDING An approach should be made with power ata normal airspeed with the flap position to be used at the pilot s discretion Flaps up will reduce wing flap damage Close the throttles just before touchdown Turn OFF the battery and ignition switches and move the fuel selector valve controls to OFF Contact to the surface should be made at a minimum airspeed 321 ENGINE FAILURE WITH REAR CABIN AND CARGO DOORS REMOVED The minimum single engine control speed this configuration is 67 KIAS If engine failure occurs at an airspeed below 67 KEAS reduce power as necessary on the operating engine and apply rudder to maintain direc tional control 3 23 ELECTRICAL FAILURES S 34 8133001 THRU 34 8233205 an ALT annunciator light illuminates observe the ammeters to determine which alternator is inoperative If both ammeters show zero output reduce electrical loads to the minimum Turn OFF both alternator switches and then turn them momentarily ON one at a time while observing the ammeters The alternator showing the LEAST but not vero current should be turned ON The other alternator should be left OFF Electrical REPORT VB 1110 ISSUED JANUARY 8 1981 3 26 REVISED AUGUST 9 1982
100. own annunciator panel which is located on the instrument panel The modes and indications given on the annunciator panel are placarded on the face of the lenses and illuminate when the respective modes are active The switches on the mode selector are the push on push off type When engaged the corresponding autopilot annunciator light illuminates The autopilot must be engaged before any other mode can be selected n BEFORE ENGAGING FLIGHT CONTROL SYSTEM 1 Check that all circuit breakers for the system are in 2 Allow sufficient time for gyros to come up to speed and system warm up 3 4 minutes 2 PREFLIGHT CHECK Run prior to each flight 1 With no modes engaged and power applied to all systems depress the TEST button on the Mode Controller mode annunciators except FD will be illuminated on the annunciator panel including three marker lights At least four but no more than six flashes must be observed to indicate proper operation of the autotrim manual electric trim feature and an audible warning should sound 2 Engage the AP depress the CWS switch center the flight controls and release the CWS switch Apply force to the controls to determine if the AP can be overpowered REPORT VB 1110 ISSUED APRIL 21 1981 9 40 8 of 16 PIPER AIRCRAFT CORPORATION SECTION 9 P A 34 220T SENECA SUPPLEMENT 5 aane nt rta e a a a S e err i aa a APP PAPA IN a a a e e a Ari aaa aa t
101. pg 3 1 3 4 Revised para 3 3 3 15 Revised para 3 7 REPORT 1110 vi b Ma aa eaaa a a e rS enr PILOT S OPERATING HANDBOOK LOG OF REVISIONS cont Revision Number and Code Rev 3 PR820225 cont Revised Pages 324 4 i 4 ii 4 18 4 30 4 37 5 3 5 14 5 20 5 22 5 23 5 26 5 28 5 29 5 30 FAA Approval Signature and Date Description of Revision Amended para 3 29 Expanded checklist moved info to pg 4 1 Relocated info from pg 4 Revised para 4 17 Corrected error Removed Note Corrected error Revised fig 5 7 heading info Corrected error to fig 5 19 info Revised fig 5 23 heading Revised fig 5 25 Revised fig 5 31 pg base info Amended fig 5 35 notation Added grid alignment number to fig 5 37 Amended lettered info to fig 5 39 Corrected error to fig 5 41 example Revised para 6 1 Revised fig 6 5 info Corrected para 6 7 b Revised para 6 7 Corrected fig 6 9 Corrected fig 6 11 Revised para 6 13 Revised item 11 data Revised item 135 Revised item 177 data Revised item 193 data Revised 223 b data Revised item 227 a data Revised item 255 data Revised and moved item 269 to pg 6 47 REPORT VB 1110 vi c PILOT S OPERATING HANDBOOK LOG OF REVISIONS cont Revision FAA Approval Number and Revised Description o
102. pitch trim will not operate either up or down e Set manual trim for takeoff 5 Daily preflight check must be performed prior to first flight of the dav a Engage the FD and AP and put pitch UP command using the vertical trim switch on Mode Controller Hold the control column to keep it from moving and observe the autotrim run in the nose up direction after approximately three seconds delay Use the vertical trim switch and putin a pitch DN command Hoid the control column and observe the autotrim run in the nose down direction after approximately 3 seconds delay b Engage the mode and the AP Set the HDG bug to command a right turn The control wheel will rotate clock wise Set the HDG bug to command left turn The control wheel will rotate counterclock wise ISSUED APRIL 21 1981 REPORT VB 1110 REVISED FEBRUARY 25 1982 9 0116 9 27 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 4 PA 34 220T SENECA TH O ann e e e i aa a aU ia Mata s M a aa eh A a M AA NCL I WWE WA AT c Run manual electric trim from full nose up to full nose down Time required should be 39 5 seconds CAUTION Disengage the AP and check that the airplane manual pitch trim is in the takeoff position prior to takeoff NOTE it the autopilot circuit breaker ts pulled the red TRIM failure light on the annunciator panel will be disabled the audible warning will continuo
103. pushbutton In addition to the standard VOR and RNAV enroute RNV ENR modes the KNS 80 has a constant course width or parallel VOR mode VOR PAR and an RNAV approach mode RNV APR To place the unit in either of these secondary modes the VOR pushbutton or the RNAV pushbutton as the case may be is pushed a second time Repetitive pushing of the VOR button will cause the system to alternate between the VOR and VOR PAR modes while repetitive pushing of the RNAV button causes the system to alternate between RNV ENR and RNV APR modes b CONTROLS 1 VOR BUTTON Momentary pushbutton When pushed while system is in either RNV mode causes system to goto VOR mode Otherwise the button causes system to toggle between VOR and VOR PAR modes 2 RNAV BUTTON Momentary pushbutton When pushed while system is in either VOR mode causes system to go to RNV ENR mode Otherwise the button causes system to toggle between RNV ENR and RNV APR modes REPORT VB 1110 ISSUED JANUARY 8 1981 9 72 2014 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA HI SUPPLEMENT 10 3 HOLD BUTTON 4 5 6 7 8 Two position pushbutton When in depressed position inhibits DME from channeling to a new station when the VOR frequency is changed Pushing the button again releases the button and channels the DME to the station paired with the VOR station USE BUTTON Momentary pushbutton Causes active waypoint to take on same value
104. relating to the aircraft Service Bulletins are of special importance and should be complied with promptly These are sent to the latest registered owners distributors and dealers Depending on the nature of the bulletin material and labor allowances may apply and will be addressed in the body of the Bulletin Service Letters deal with product improvements and service hints pertaining to the aircraft They are sent to dealers distributors and occasionally at the factory s discretion to the latest registered owners so they can properly service the aircraft and keep it up to date with the latest changes Owners should give careful attention to the Service Letter information Service Spares Letters offer improved parts kits and optional equip ment which were not available originally and which may be of interest to the owner if an owner is not having his aircraft serviced by an Authorized Piper Service Center he should periodically check with a Piper dealer or distributor to find out the latest information to keep his aircraft up to ISSUED JANUARY 8 1981 REPORT VB 1110 8 1 SECTION 8 _ PIPER AIRCRAFT CORPORATION HANDLING SERV amp MAINT PA 34 220T SENECA Piper Aircraft Corporation has a Subscription Service for the Service Bulletins Service Letters and Service Spares Letters This service is offered to interested persons such as owners pilots and mechanics at a nominal fee and be obtained through Pipe
105. rese cass leaks SEU ced bate amet Right Wik Right leading edge Sos RUNE d Check No Ice Fuel CAD eos nsi ER UST EPA TANE open check quantity and color secure Right engine so qu guess check oil Right propeller ms Bioko check Cowl flaps secure Fuel amp uius pd suut drain Nose section Check Nose TP leaks SU EN E EA proper inflation Tite hs m 4 aimee check Tow bar UP oos Iemoved and stowed Landing lights sioe Mer ahaha cee CHEER Windshield pid Gack Maes PS eased pear clean Left wing engine nacelle and landing gear check as on right side Stall warning vanes TOI Pitot mast PERPE ERE clear checked Dorcel Dear Ra oer Ubi tende a Pars ace ed clear Rear doors ERN latched Left static Tr EET Clear Eip nnape T T check no ice REPORT VB 1110 ISSUED JANUARY 8 1981 4 4 REVISED AUGUST 17 1981 PIPER AIRCRAFT CORPORATION SECTION 4 PA 34 220T SENECA
106. result Refer to One Engine Inoperative Climb Performance chart Figure 5 21 ENGINE FAILURE DURING FLIGHT BELOW 66 KEAS Should an engine fail during flight at an airspeed below 66 KIAS apply rudder towards the operative engine to maintain directional control The throttles should be retarded to stop the yaw force produced by the engine Lower the nose of the aircraft to accelerate above 66 KIAS and increase the power on the operative engine as the airspeed exceeds 66 KIAS After an airspeed above 66 KIAS has been established an engine restart attempt be made if altitude permits the restart has failed orif alitude does not permit the engine should be secured see Engine Securing Procedure 7 KIAS with aft doors removed ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED FEBRUARY 25 1982 3 15 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA 34 220T SENECA E e e ani taa PPP PN T a a Mii rn ENGINE INOPERATIVE LANDING Complete the Engine Securing Procedure The landing gear should not be extended and the wing flaps should not be lowered until certain of making the 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 should be avoided if at all possible Establish a final approach speed of 90
107. standard atmosphere at sea level KCAS Calibrated Airspeed expressed in Knots GS Ground Speed is the speed of an airplane relative to the ground IAS Indicated Airspeed is the speed of an aircraft as shown on the airspeed indicator when corrected for instrument error 1 values published in this handbook assume zero instrument error E KIAS indicated Airspeed expressed in nois M Mach Number is the ratio of true airspeed to the speed of sound TAS True Airspeed is the airspeed of an airplane relative to undisturbed air which 15 the CAS corrected for altitude temperature and compressibility VA Maneuvering Speed is the maximum speed at which application of full available aerodynamic control will not overstress the airplane Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position REPORT VB 1118 ISSUED JANUARY 8 1981 1 6 PIPER AIRCRAFT CORPORATION SECTION 1 PA 34 220T SENECA VLE VMCA MNE V NO Vso VSSE ISSUED JANUARY 8 1981 GENERAL Maximum Landing Gear Extended Speed is the maximum speed at which an aircraft can be safely flown with the landing gear extended Maximum Landing Gear Operating Speed is the maximum speed at which the landing gear can be safely extended or retracted Air Minimum Control Speed is the mini mum flight speed at which the airplane is directionally controllabl
108. takeoff prematurely This procedure only compounds an already bad situation Proper procedures require thorough application of preheat to all parts of the engine Hot air should be applied directly to the oil sump and external oil lines as well as the cylinders air intake and oi cooler Excessively hot air can damage non metallic components such as seals hoses and drive belts so do not attempt to hasten the preheat process Before starting is attempted turn the engine by hand or starter until it rotates freely After starting observe carefully for high or low oil pressure and continue the warm up until the engine operates smoothly and all controls can be moved freely Do not close the flaps to facilitate warm up as hot spots may develop and damage ignition wiring and other components Hot air should be applied primarily to the oil sump and filter area The oil drain plug door or panel may provide access to these areas Continue to apply heat for 15 to 30 minutes and turn the propeller bv hand through 6 or 8 revolutions at 5 or 10 minute intervals Periodically feel the top of the engine and when some warmth is noted apply heat directly to the upper portion of the engine for approximately five minutes This will provide sufficient heating of the cvlinders and fuel lines to promote better vaporization for starting If enough heater hoses are available continue heating the sump area Otherwise it will suffice to transfer the s
109. the battery switch ON momentarily while the starter is engaged If cranking speed increases the ship s battery is at a higher level than the external power supply If the battery has been depleted by excessive cranking it must be recharged before the second engine is started All the alternator current will go to the low battery until it receives sufficient charge and it may not start the other engine imme diately ISSUED JANUARY 8 1981 REPORT 1110 4 21 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA 34 220T SENECA iit err rrr ria MH NR NE I 4 25 PREHEATING The use of preheat and auxiliary power battery cart will facilitate starting during cold weather and is recommended when the engine has been cold soaked at temperatures of 10 F and below in excess of two hours Successful starts without these aids can be expected at temperatures below normal provided the aircraft battery is in good condition and the ignition and fuel systems are properly maintained The following procedures are recommended for preheating starting warm up run up and takeoff a Select a high volume hot air heater Small electric heaters which are inserted into the cowling bug eye do not appreciably warm the oil and may result in superficial preheating WARNING Superficial application of preheat to a cold soaked engine can have disastrous results minimum of preheat application may warm the engine enoug
110. the center bar Trim should not operate S Rock switch fore and aft only Do not depress center bar Trim should not operate 6 Operate trim normally grasp trim wheel and check that trim may be overpowered by hand 7 Operate trim Up or Down Depress Interrupt Switch Check that trim action stops REPORT VB 1110 ISSUED SEPTEMBER 23 1983 9 132 2 of 4 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 20 P PPPPI PRPPPPIIPBIBIPRRE ER the trim system fails portion of the ahove check procedures turn the trim master switch OF F and do not operate the trim system until the system is corrected This trim system has been designed to require two separate failures before uncontrolled operation can occur The pre flight inspection procedure is established to identify a system failure that might otherwise go undetected IN FLIGHT PROCEDURES Depress center bar and move switch rocker fore or aft to obtain clectric trim nose down or up Release switch to stop trimming b SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of this Pilots Operating Handbook are necessary for this supplement SECTION 6 WEIGHT AND BALANCE Factory installed optional equipment is included in the delivered weight and balance data in Section 6 of the basic Pilot s Operating Handbook ISSUED SEPTEMB
111. the cruise time Remember The time values taken from the climb and descent graphs are in minutes and must be converted to hours before adding them to the cruise time The following flight time is required for the flight planning example 1 Total Flight Time c 3 plus d 1 plus 6 0 22 hrs plus 0 22 hrs plus 1 94 hrs 2 38 hrs g Total Fuel Required Determine the total fuel required by adding the fuel to climb the fuel to descend and the cruise fuel When the total fuel in gallons is determined multiply this value by 6 16 gal to determine the total fuel weight used for the flight The total fuel calculations for the example flight plan are shown below I Total Fuel Required c 5 plus d 3 plus eX7 11 gal plus 5 gal plus 36 3 gal 52 3 gal 52 3 gal multiplied by 6 Ib gal 313 8 165 ISSUED JANUARY 8 1981 REPORT 1110 5 7 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 34 220T SENECA MM M MM M N I M THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED JANUARY 8 1981 5 8 PIPER AIRCRAFT CORPORATION SECTION 5 PA 34 220T SENECA PERFORMANCE 5 7 PERFORMANCE GRAPHS LIST OF FIGURES Vh CA CA VA CA CA CA VA CA Figure Temperature Conversion 5 11 3 Airspeed System Calibration 5 12 5 Stall Speed Vs A
112. to the desired frequency and press the ENTER Key ISSUED JANUARY 8 1981 REPORT VB 1110 5 of 6 9 63 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 8 PA M 220T SENECA 4 NAV FREQUENCY Set the mode selector to VOR LOC To tune from keyboard mode selector must be set to VOR LOC Press NAV 1 key press number keys correspond ing to the desired frequency and press the ENTER key 5 NAV 2 FREQUENCY Press NAV 2 key press number keys corresponding to the desired frequency and press the ENTER key SECTION 5 PERFORMANCE changes to the basic performance provided by Section 5 of the Pilot s Operating Handbook are necessary for this supplement REPORT VB 1110 ISSUED JANUARY 8 1981 9 64 6 of 6 E PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 9 renmen nmnams an PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT 9 FOR COLLINS ANS 351 AREA NAVIGATION COMPUTER PIPER DWG 87292 SECTION 1 GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Collins ANS 351 Area Navigation Computer 1 installed in accordance with Approved Piper data The information contained within this supplement is to be used in conjunction with the complete handbook This supplement has been FAA Approved and must remain in this handbook at all times when the optional C
113. to update the text of the present handbook and or to add information to cover added airplane equipment p Revisions Revisions will be distributed whenever necessary as complete page replacements or additions and shall be inserted into the handbook in accordance with the instructions given below Revision pages will replace only pages with the same page number Insert all additional pages in proper numerical order within each section 3 Page numbers followed by a smail 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 outside margin of the page opposite revised added or deleted material A line along the outside margin of the page opposite the page number will indicate that an entire page was added REPORT VB 1110 iii Black lines wilf 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 bc identified ORIGINAL PAGES ISSUED The original pages issued for this handbook prior to revision are given below Title ii through vii 1 1 through 1 11 2 1 through 2 12 3 1 through 3 23 4 1 through 4 27 5 1 through 5 31 6 1 through 6 68 7 through 7 39 8 1 through 8 19 9 1 through 9 102 and 10 1 through 10 3
114. turbocharger speed to stabilize The propeller control levers are used to adjust the propeller speed from high RPM to feather ISSUED JANUARY 8 1981 REPORT 1110 REVISED FEBRUARY 25 1982 7 3 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA HH MM M He o PULL CLOSE COWL L R PUSH OPEN COWL FLAP CONTROL Figure 7 1 The mixture control levers are used to adjust the air to fuel ratio An engine is shut down by the placing of the mixture lever in the full lean idle cut off position The friction adiustment lever on the right side of the control quadrant be adjusted to increase or decrease the friction holding the throttle propeller and mixture controls or to lock the controls in a selected position The alternate air controls are located on the control quadrant just below the engine control levers When an alternate air lever is in the up or off position the engine is operating on filtered air when the lever is in the down position the engine is operating on unfiltered heated air Should the primary air source become blocked the automatic alternate air door will automatically select unfiltered heated air The flap control levers Figure 7 1 located below the control quadrant are used to regulate cooling air for the engines The levers have three positions full open fuli closed and intermediate A loc
115. which The air is a dry perfect gas The temperature at sea level is 5 Celsius 59 Fahrenheit The pressure at sea level is 29 92 inches 1013 2 mb The tempera ture gradient from sea level to the altitude at which the temperature is 56 5 69 7 is 0 00198 C 0 003566 F per foot and zero above that altitude Outside Air Temperature is the free air static temperature obtained either from inflight temperature indications or ground meteorological sources adjusted for in strument error and compressibility effects The number actually read from an altimeter when the barometric subscale has been set to 29 92 inches of mercury 1013 2 millibars Altitude measured from standard sea level pressure 29 92 in Hg by a pressure or barometric altimeter is the indicated pressure altitude corrected for position and instrument error In this handbook altimeter instrument errors are assumed to be zero Actual atmospheric pressure at field elevation ISSUED JANUARY 8 1981 REVISED SEPTEMBER 23 1983 PIPER AIRCRAFT CORPORATION SECTION 1 PA 34 220T SENECA Wind c Power Terminology Takeoff Power Maximum Con tinuous Power Maximum Climb Power Maximum Cruise Power d Engine Instruments EGT Gauge GENERAL T A ea I i aa erret RETA a ar T me The wind velocities recorded as variables on the charts of this handbook are to be understood as the headwind or tailwind componen
116. with ambient temperature at the time of charging Although dry nitrogen gas is recommended compressed air may be used provided it contains no moisture For more detailed instructions see Propeller Service in the Handling and Service Section of this handbook Governors one on each engine supply engine oil at various pressures through the propeller shafts to maintain constant RPM settings A governor controls engine speed by varying the pitch of the propeller to match load torque to engine torque in response to changing flight conditions Each propeller is controlled by the propeller control levers located in the center of the power control quadrant Feathering of a propeller is accom plished by moving the control fully aft through the low RPM detent intothe FEATHER position Feathering takes place in approximately six seconds Unfeathering is accomplished by moving the propeller control forward and engaging the starter until the propeller is windmilling An optional propeller unfeathering system may be installed which consists of increased capacity governors gas charged accumulators and latching propeller control lever ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED APRIL 9 1982 _ 7 5 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA tan errr eee a a e a a e eee ttis tie e tete mn The feathering governors are designed to operate in the conventional manner in addition to their accum
117. 0 PIPER AIRCRAFT CORPORATION SECTION 4 PA 34 220T SENECA NORMAL PROCEDURES 4 23 STARTING ENGINES WITH EXTERNAL POWER An optional feature called the Piper External Power PEP allows the operator to use an external battery to crank the engines without having to gain access to the airplane s battery Turn the battery switch OFF and turn all electrical equipment OFF Connect the RED lead of the PEP kit jumper cable to the POSITIVE terminal of an external 12 volt battery and the BLACK lead to the NEGATIVE terminal Insert the plug of the jumper cable into the socket located on the fuselage Note that when the plug is inserted the electrical system is ON Proceed with the normal starting technique After the engines have started reduce power to the lowest possible RPM to reduce sparking and disconnect the jumper cable from the aircraft Turn the battery switch ON and check the alternator ammeter for an indi cation of output DO NOT ATTEMPT FLIGHT IF THERE 15 NO INDI CATION OF ALTERNATOR OUTPUT NOTE For all normal operations using the PEP jumper cables the battery switch should be OFF but it is possible to use the ship s battery in parallel by turning the battery switch ON This will give longer cranking capabilities but will not increase the amperage CAUTION if the ship s battery has been depleted the external power supply can be reduced to the level of the ship s battery This can be tested by turning
118. 0 6 94 6 NOTES Straight line variation between points given The datum used 15 78 4 inches ahead of the wing leading edge at the inboard edge of the fuel tank is the responsibility of the airplane owner and the pilot to ensure that the airplane 15 properly loaded See Section 6 Weight and Balance for proper loading instructions REPORT 1110 ISSUED JANUARY 8 1981 2 6 PIPER AIRCRAFT CORPORATION SECTION 2 PA 34 220T SENECA LIMITATIONS 2 15 MANEUVER LIMITS All intentional acrobatic maneuvers including spins are prohibited Avoid abrupt maneuvers 2 17 FLIGHT MANEUVERING LOAD FACTORS Positive Load Factor Maximum 1 Flaps Up 38G 2 Flaps Down 206 Negative Load Factor Maximum No inverted maneuvers approved 2 19 TYPES OF OPERATION The airplane 1s approved for the following operations when equipped in accordance with FAR 91 or FAR 135 Dav V F R b Night V F R c Dav d Night LF R e Icing conditions when equipped per Ice Protection System Instal lation Suppiement refer to Section 9 2 21 FUEL LIMITATIONS a Standard Fuel Tanks 1 Total Capacity 98 U S GALS 2 Unusable Fuel 5 U S GALS The unusable fuel for this airplane has been determined as 2 5 U S gallons in each wing in critical flight attitudes 3 Usable Fuel 93 U S GALS b Optional Fue Tanks 1 Total Capacity 128 U S GALS 2 Unusable Fuel 5 U S GALS 3 Usable Fuel 123 U
119. 1 REPORT VB 1110 1016 9 13 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 3 PA 34 220T SENECA The air conditioning system is a recirculating air system The major components include an evaporator condenser compressor blower switches and temperature controls The evaporator is located behind the rear baggage compartment This cools the air used for the air conditioning system The condenser is mounted aft of the fire wall on the left engine A retractable condenser scoop extends when the air conditioner is ON and retracts to a flush position when the air conditioner is OFF the air conditioner is operated on the ground the condenser scoop operates to a ground opening position which is larger than the in flight opening circuit through the squat switch on the right main gear prevents the scoop from operating to the ground opening when the aircraft is in flight The compressor is mounted on the rear outboard side of the left engine lt has an electric clutch which automatically engages or disengages the compressor Air from the baggage area is drawn through the evaporator by the blower and distributed through an overhead duct to individual outlets located adjacent to each occupant The switches and temperature control are located on the lower right side of the instrument panel The temperature control regulates the temperature of the cabin Turning the control clockwise increases cooling counterclock wise decre
120. 12 of 16 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA III SUPPLEMENT 5 CAUTION The APPR mode of operation will continue to provide airplane commands and or control without a valid VOR LOC signal NAV flagin view Also erroneous navigation information may result from COMM radio interference with the NAV radio This erroneous infor mation may cause premature APPR captures as well as erroneous steering information Should this occur reselect HDG mode and then reselect APPR mode 8 Back Course Mode BC For BC operation proceed as for normal approach mode but engage BC mode after selecting APPR The BC mode reverses the signals in the computer and cannot be engaged without a LOC frequency selected BC status i5 indicated on the annun ciator panel BC mode can be disengaged by depressing either the BC APPR or by selecting other than a LOC frequency on the NAV receiver 9 Vertical Mode Switch Trim Up Dn Operation of the vertical trim switch on the Mode Controller provides a convenient means of adjusting the ALT hold or PAH angle function without disengaging the mode ISSUED APRIL 21 1981 REPORT VB 1110 13 of 16 9 442 SECTION 9 _ PIPER AIRCRAFT CORPORATION SUPPLEMENT 5 PA 34 220T SENECA 1 VOR PROCEDURES G il 2 3 4 5 Tune receiver to appropriate frequency Set desired heading with the HDG BUG to intercept radial and engage HDG and AP Maximum recomm
121. 150 RPM max diff drop 50 RPM Seat DU DHT es TIE check OVID NOGL erst Reate 4 8 105 1 in Hg PRES Gade ects aa sa Shes AE ee oe 800 1000 RPM ON AQUI ALOI os or REGRET REE ON gia eno dre in the green panel cede vail inte a e ge id ed TR IE arto press to test Ea Xa are ES os e Td set NETTEN set Cruadrant va eds tree aes DX ADJUSTED Alternate dil cos dob E eee at wel uan iot SE OFF Con diu ducked set Sce RU don qol teehee tust erect o Bed eurer ooa orbata dM pA i dod ey set RE TII fi Gis bar SEL See fastened adjusted Shed Etats ON SAE eae SOLE Par seat belts fastened usa ceu scs da A free full travel Mane latched Tue ee ten A RE Val Geta See e a OFF Pitor ex d eR AUS ic doge as required Parking Drake eg fuk EE iot ap dd EE release ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED FEBRUARY 10 1984 4 9 SECTION 4 PIPER AIRCRAFT CORPORATION NORM AL PROCEDU RES PA 34 220T SENECA IH TAKEOFF CAUTION Fast taxi turns immediately prior to takeoff run should be avoided Adjust mixture prior
122. 22 C iy REDUCE ACCELERATE amp STOP DISTANCE Pressure altitude 3000 ft Gross weight 4000 Ibs Head wind 10 knots Accelerate amp s 13 HEAVY DUTY BRAKES 2242262 H i3 M 3 BT m 4334 JONVLISIC 4018 20 40 4500 4000 3500 300 5 10 15 OUTSIDE AIR TEMPERATURE C WEIGHT POUNDS WIND COMPONENTS KTS FON VAN GOA NOILOWS NOILVNOdNOO LIVHOWIV HI VOXN3S LOCC 9 Vd 61 5 1861 8 AUVONVE OIII HA 11 5 JSONVIAWOJNUd SIATIO pA 220T ASSOCIATED CONDITIONS BOTH ENGINES OPERATING TAKEOFF POWER LANDING GEAR EXTENDED FLAPS UP 92 KIAS ni MEXTURE FULL RICH COWL FLAPS 1 2 OPEN 4750 LBS GROSS WEIGHT Pressure altitude 8000 ft LU OAT 10 MM ELE OUTSIDE AIR TEMPERATURE RATE OF CLIMB FPM Hi LOTTE Yd NOILVNOdNOO LIVHONIV 83414 SONVIASEOA3EH d NOLLIS 05 5 61 911814 QAIOVNLAM AVAD QASIAXH Sst 7861 ST
123. 220T SENECA If required the ELT may be removed from the airplane and used as a portable unit To use the ELT as a portable unit in an emergency remove the cover and unlatch the unit from its mounting base The antenna cable is disconnected by a left quarter turn ofthe knurled nut and a pull A sharp tug on the two small wires will break them loose Deploy the self contained antenna by pulling the plastic tab marked PULL FULLY TO EXTEND ANTENNA Move the switch to ON to activate the transmitter In the event the transmitter is activated by an impact it can only be turned off by moving the switch on the ELT unitto OFF Normal operation can then be restored by pressing the small clear plastic reset button located on the top of the front face of the ELT and then moving the switchto ARM A pilot s remote switch located on the left side panel is provided to allow the transmitter to be turned on from inside the cabin The pilot s remote switch is placarded ON and ARMED The switch is normally in the ARMED position Moving the switch to ON will activate the transmitter Moving the switch back to the ARMED position will turn off the trans mitter only if the impact switch has not been activated The ELT should be checked to make certain the unit has not been activated during the ground check Check by selecting 121 50 MHz on an operating receiver If there is an oscillating chirping sound the ELT may have been activated and should be turned off
124. 25 TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES Paragraph 4 1 4 1 4 3 Airspeeds For Safe Operations 4 2 4 5 Normal Procedures 81 4 3 Preparation 2 4 3 Preflight Check sse 4 3 Before Starting Engines 4 5 Starting Engines Airplane Equipped With Standard Primer 4 5 Starting Engines Airplane Equipped With Optional Engine Primer SYSTEM cs aces ae eee 4 6 Starting Engines When Flooded 4 7 Starting Engines in Cold Weather Airplane Equipped With Standard Engine Primer System 4 7 Starting Engines With External Power 4 8 2222222 4 8 EEO V We peu 4 8 Before Takeoff Ground Check 4 9 4 10 Yd a sro s 4 11 UO End Ee bp 4 11 d 4 11 Approach and 4 12 GNE OU pn EAR Ro PUE 4 12 After Landing e Een rei eee 4 12 Shut dON BL d aie paie eres 4 12 ed eheu s Le open es eat 4 13 4 7 Amplified Normal Procedures General 4 15 REPORT 110 4 Paragraph Page No 9 d tia iris 4 15 Preflight
125. 81 7 32 PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA HI DESCRIPTION amp OPERATION MENTRE HR To introduce fresh unheated air into the cabin during flight the air intake should be open and the heater off Ram air enters the system and can be individually regulated at cach floor outlet Overhead outlets also supply fresh air for cabin ventilation The occupant of each seat can manually adjust an outlet in the ceiling to regulate the flow of fresh airto that seat area An optional fresh air blower be installed in the overhead ventilation system to provide additional fresh air flow during ground operation An overheat switch located in the heater unit acts as a safetv device to render the heater inoperative if a malfunction should occur Should the switch deactivate the heater the OVERHEAT light on the annunciator panel will illuminate The overheat switch is located on the forward outboard end of the heater vent jacket The red reset button on the heater shroud can be reached through the bulkhead access panel in the aft cabin close out panel To prevent activation of the overheat switch upon normal heater shut down during ground operation turn the three position switch to FAN for two minutes with the air intake lever in the open position before turning the switch to OFF During flight leave the air intake lever open for a minimum of fifteen s
126. A Return the propeller controls to full forward position and move the alternate air controls to ON then OFF Move the throtties to 2000 RPM and check the magnetos fhe normal drop on cach magneto is 100 RPM and the maximum drop should not exceed 150 The maximum differential drop should not exceed 50 RPM The alternator output should approximately equal for both alternators 4 8 to 5 1 in Hg indication on the gvro suction gauge signifies proper operation of the gyro suction system CAUTION Ensure that the alternators are not indicating full charge prior to takeoff Set the throttles between 800 and 1000 RPM check that the fuel selectors and alternator switches are ON and that all the engine gauges are within their normal operating ranges green arc Press to test the annun ciator light to make sure they all illuminate Set the altimeter attitude indicator directional and clock Set the mixtures and advance the propeller controls to the forward position The friction lock onthe right side of the control quadrant should be adjusted Check to make sure the alternate air is OFF Adjust the flaps and set the wing and trim stabilator and rudder tabs as required The seat backs should be erect and seat belts and harnesses fastened Fasten the seat belts on the empty seats NOTES the fixed shoulder harness non inertia reel tvpe is installed it must be connected to the seat and ad
127. A summary of current grades as well as the previous fuel designations is shown in the following chart Previous Commercial i Current Commercial Fuel Grades AST 10 910 Grade Color red 99 blue 007 120 green 15 145 purple HOOLI Commercial FUFI GRADE COMPARISON CHAR Current Military m Grades 0 5872 Amendment No 3 Fuel Grades AST 12910 75 Grade Coor mi LU 5S gal Max TEL ml U S gal Grade Color ml U S gal NO red 0 5 red 0 5 2 0 none nonc 10 100 green 1 100 F30 green 30 46 15 145 purple 4 6 tees ci MEER ec c M fuel in some overseas countries i current colored green and designated as 71001 7 fuel grade 100 and grade 100 130 both of which are colored greeni having T EI content of up to 4 ml U S gallon are approved for use in all engines certificated use with grade 100 130 fuel The operation of the aircraft is approved with an anti icing additive in the fuel When an anti icing additive is used it must meet the specification MIL 1 27686 must be uniformly blended with the fuel while refueling must not exceed 15 by volume of the refueled quantity and to ensure its effectiveness should be blended at not less than 10 by volume One and one half liquid ozs per ten gallon of fuel would fall within this range blender suppli
128. B 1110 _ ISSUED APRIL 21 1981 9 36 4ofl REVISED FEBRUARY 25 1982 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 5 d AUTOPILOT DISENGAGEMENT e 1 The autopilot can be manually disengaged by the following actions a Press the DISC TRIM INTERRUPT switch on the pilot s control wheel Move the Autopilot ON OFF handle to the OFF position Pull the AUTOPILOT circuit breaker out OFF Turn off the RADIO POWER switch e Operate manual electric trim switch UP or DN 2 The following conditions will cause the Autopilot to auto matically disengage a Power failure b Internal Flight Control System c With the KCS 55A compass system loss of compass valid displaying HDG flag disengages the Autopilot when a mode using heading information is engaged MAXIMUM ALTITUDE LOSSES DUE AUTOPILOT MALFUNCTIONS Cruise Climb Descent 400 feet Maneuvering 00 feet APPR 50 feet SE APPR 50 feet CAUTION When the autopilot is engaged manual application of a force to the pitch axis of the control wheel for a period of three seconds or more will result in the autotrim system operating in the direction to create a force opposing the pilot This opposing mistrim force will continue to increase as long as the pilot applies a force to the control wheel and will ultimately overpower the autopilot lf the autopilot is disengaged under these conditions the pilot may be req
129. CA SUPPLEMENT 4 3 4 Fhght Director Mode The FD must be engaged before the AP can be engaged The FD mode alone indicates and wings level The pilot may choose to fly the FDI commands manually without the AP engaged by depressing the FD switch on the Mode Controller or selecting any of the other modes he wishes to follow When the AP is engaged the airplane will automatically follow the FD commands The FD be disengaged by depressing the FD switch on the Mode Controller If the AP is engaged the FD cannot be turned off without first disconnecting the AP or by pressing the DISC TRIM INTERRUPT switch on the pilot s control wheel FD mode engagement is displayed on the annunciator NOTE The Vertical Trim switch located on the Mode Controller may be used to trim the command pitch attitude at a rate of one degree per second the pitch attitude degrees legend on the airplane attitude indicator will not indicate accurate FDI pitch steering bar pitch attitude in degrees Altitude Hold Mode ALT When the ALT switch on the Mode Controller is pressed the FDI will provide commands for maintaining the pressure altitude existing at the time the switch is depressed Forsmooth operation engage the ALT at no greater than 500 feet per minute climb descent The ALT will automatically disengage when glide slope couples or the go around switch is depressed ALT hold may be turned
130. CONTROL LOCATION CONTROLS Figure 4 1 REPORT VB 1110 ISSUED JANUARY 8 1981 9 92 2 of 6 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA III SUPPLEMENT 14 CONTROL FUNCTION OPERATIONAL USE OFF STBY TEST Controls primary power to radar system Range Selector 2 Places system in standby condition during warmup period and when system is not in use 3 Places system in test mode to determine operability of system No transmission in test mode 4 Selects operating range Enables trans mitter WxiGAIN Wx A In Wx position weather image gain is at preadjusted level Contour operation is Gain Control and automatic and constant Mode Selector 2 In GAIN position 6 levels from MAP maximum gain to MIN may be selected for ground mapping operations Contour operation 15 disabled 3 In Wx position the radar indicator dis play alternately cycles between the Wx position and the GAIN MAP position This will verify if a contour storm cell area is a storm cell and not a lake or some other terrain feature CONTROL FUNCTIONS AND OPERATION Table 4 3 ISSUED JANUARY 8 1981 REPORT VB 1110 3 of 6 9 93 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 14 PA 34 220T SENECA CONTROL FUNCTION OPERATIONAL USE HOLD When the HOLD pushbutton is initially de Pushbutton pressed weather or ground mapping image last presented is retai
131. CORPORATION SECTION 4 34 220 SENECA NORMAL PROCEDURES T a i e i a e i ta taa e e aam Maintain a traffic pattern speed of 100 KIAS and a final approach speed of 90 KIAS If the aircraft is lightly loaded the final approach speed may be reduced to 79 KIAS When the power is reduced on close final approach the propeller controls should be advanced to the full forward position to provide 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 the gear position lights are dimmed and are difficult to sec 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 tinal approach with the power fully off before the wheels touch the runway This gives the gear warning horn a chance to blow if the gear is not locked down If electric trim is available it can be used to assist a smooth back pressure during flare out Maximum braking after touch down is achieved by retracting the flaps applying back pressure to the wheel and
132. CORPORATION SECTION 4 PA 34 220T SENECA NORMAL PROCEDURES SECTION 4 NORMAL PROCEDURES 4 1 GENERAL This section describes the recommended procedures for normal operations for the Seneca Required FAA regulations procedures and those necessary for the operation of the airplane as determined by the operating and design features of the airplane are presented Normal procedures associated with those optional systems and equip ment which require handbook supplements are provided by Section 9 Supplements These procedures are provided to present source of reference and review and to supply information on procedures which are not the same for all aircraft Pilots should familiarize themselves with the procedures given in this section in order to become proficient in the normal operations of the airplane The first portion of this section consists of a short form checklist which supplies an action sequence for normal operations with little emphasis on the operation of the systems The remainder of the section is devoted to amplified normal procedures which provide detailed information and explanations of the procedures and how to perform them This portion of the section is not intended for use as an in flight reference due to the lengthy explanations The short form check list should be used for this purpose data given is for both two and three blade propellers unless otherwise noted ISSUED JANUARY 8 981 RE
133. CTION 10 SAFETY TIPS REPORT 1110 vii TABLE OF CONTENTS SECTION 1 GENERAL Paragraph Page i deck Seas 1 1 3 Cs RI URP Ed QE 2327 yas aA es 1 3 1 5 agen UTD E TA Eo e Ca qe 1 3 tale rece 1 4 1 9 1 4 1 11 Maximum Weights 8 rd un 1 5 1 13 Standard Airplane Weights 1 5 Li Baggage Space 1 5 86 t e MAE 1 5 19 Svmbols Abbreviations and 1 6 REPORT VB 1110 1 PIPER AIRCRAFT CORPORATION SECTION 1 PA 34 220T SENECA Hil GENERAL SECTION I GENERAL 1 1 INTRODUCTION This Pilot s Operating Handbook is designed for maximum utilization an operating guide for the pilot includes the material required to be furnished to the pilot by FAR 23 It also contains supplemental data supplied by the airplane manufacturer This handbook is not designed as a substitute for adequate and com petent flight instruction knowledge of current airworthiness directives and applicable federal air regulations or advisory circulars It is not intended to be a guide for basic flight instruction or a training manual and should not be used for operational purposes unless kept in a current status Assurance tha
134. CTOR SET TO BRG DST Bearing and distance to the selected waypoint is displayed 2 DISPLAY SELECTOR SET TOKTS TTS Ground speed in knots and time to waypoint is displayed in minutes 3 HSI The HSI presents RNAV information with constant deviation i e full scale deviation represents 5 nautical miles off course out to a distance of 00 nautical miles From thereon full scale deviation represents 3 off course 4 DISPLAY SELECTOR SET TO SBY Data stored for stand by waypoint number appearing in SBY window is displayed and can be altered as desired 5 DISPLAY SELECTOR SET TO ACT Data stored for active waypoint number appearing in ACT window is displayed but cannot be altered With the mode selector set to APR the displays are the same as RNAV except full scale deviation represents 1 25 nautical miles off course out to 25 nautical miles From thereon full scale deviation represents 3 off course Program COM and NAV frequencies by performing the following steps NOTE To program the COM NAV Unit from the NP 2041A keyboard the KBD NAV COM selector switches must be set to K BD 1 MODE SELECTOR The mode selector on the NP 2041A can be on in any position other than OFF or TEST to program 22 COM 1 or COM 2 frequencies 2 COM FREQUENCY Press COM I key press number keys corresponding to the desired frequency and press the ENTER key 3 COM 2 FREQUENCY Press COM 2 key press number keys corresponding
135. ED APRIL 21 1981 REPORT VB 1110 9 of 12 9 121 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 18 PA 34 220T SENECA h IN FLIGHT PROCEDURE COMMAND AUTOTRIM SYSTEM i 1 2 3 Trim master switch When the autopilot is engaged pitch trim is accomplished and maintained automatically With the autopilot OFF command trim is obtained by pressing and rocking the combination TRIM AP disconnect bar on the pilot s control wheel trim switch SPECIAL OPERATIONS AND INFORMATION 1 2 Altitude Hold Operation For best results reduce rate of climb or descent to 1000 FPM before engaging altitude hold mode Instrument Approach Operations Initial and or intermediate approach segments should b conducted between 95 110 KIAS with a maximum of one notch 109 flaps extended as desired Upon intercepting the glide path or when passing the final approach fix FAF immediately lower the landing gear and reduce the power for approximately 90 95 KIAS on the final approach segment Adjust power as necessary during remainder of approach to maintain correct airspeed Monitor course guidance information raw data throughout the approach All power changes should be of small magnitude and smoothly applied for best tracking per formance Do not change aircraft configuration during approach whil
136. ED INDICATOR DUAL MANIFOLD PRESSURE GAUGE DUAL TACHOMETER AVIONICS MODE SELECTOR AUDIO MARKER PANEL RADIO MASTER SWITCH DME RADAR AIRSPEED INDICATOR COPILOT TURN AND BANK INDICATOR ATTITUDE GYRO COPILOT DIRECTIONAL GYRO COPILOT ALTIMETER COPH VERTICAL SPEED INDICATOR AUTOPILOT CONTROL PANEL 28 29 30 21 32 33 34 35 36 37 38 38 40 41 42 43 44 45 45 47 48 49 50 51 52 53 54 PILOT S AND PHONE JACKS SLAVING METER SWITCH PANEL ADF INDICATOR PANEL LIGHTS RADIO LIGHTS ENGINE GAUGES DUAL FUEL FLOW GAUGE EMERGENCY GEAR EXTENDER LANDING GEAR SELECTOR DUAL GAUGE TAMMETER PRESS TO TEST BUTTONS LEFT ENGINE ALTERNATE AIR CONTROL LEVER CONTROL LEVERS AMMETER VACUUM GAUGE GROUND CLEARANCE SWITCH RIGHT ENGINE ALTERNATE AIR CONTROL LEVER CONTROL FRICTION LOCK TRANSPONDER ADF PNEUMATIC DE ICE CONTROLS ECS CONTROL SWITCHES AVIONICS EMERGENCY BUS SWITCH CIRCUIT BREAKER PANEL COPILOT S MIKE AND PHONE JACKS CIGAR LIGHTER HI VANAS 10772 4 NOLIVHOdHOO Addld NOILV3IIdO NOILdBHOS IG L NOILO3S SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA 7 25 BEATING VENTILATING AND DEFROSTING SYSTEM Heated air for cabin heat and windshield defrosting is provided by a Janitrol combustion heater located in the aft fuselage behind the cabin baggage compartme
137. EM aa rati t v Cau OB RT lt err Wing Area sq ft 208 7 Min Turning Radius ft 33 2 from pivot point to wingtip 4 DIAMETER SPAR STA 108 628 JE ts o THREE VIEW Figure 1 1 REPORT 1110 ISSUED JANUARY 8 1981 1 2 PIPER AIRCRAFT CORPORATION PA 34 220T SENECA 1 3 1 5 ENGINE Number of Engines b Engine Manufacturer c Engine Model Number 1 Left 2 Right d Rated Horsepower ej Rated Speed rpm f Bore inches g Stroke inches h Displacement cubic inches Compression Ratio G Engine PROPELLER STANDARD a Number of Propellers bj Propelier Manufacturer c Propeller Hub amp Blade Models tl Left 2 Right d Number of Blades e Propeller Diameter in 1 Maximum 2 Minimum f Propeller Type SECTION 1 GENERAL gt Continental TSIO 360K B LTSIO 360K B Power Max Cont 5 Min Limit Power 220 BHP 200 BHP 2800 2600 4 438 3 875 360 7 5 1 Six Cylinder Direct Drive Horizontally Opposed Air Cooled Hartzell BHC C2YF 2CKUF FC8459 8R BHC C2YF 2CLKUF FIC8459 8R 2 76 75 Constant Speed Activated Full Feathering The propellers have the same designation when deicing boots are installed ISSUED JANUARY 8 1981 REPORT VB 1110 1 3 SECTION 1 PIPER
138. ER Cana m ON Aux fuel pump engine csse nnn LO boost THECUS eva ties open 1 4 inch ENT MMC RICH Magneto switches ciis ON Prop full forward eme aes engage until propeller windmills east ee reduce power until engine 1 Warm Aux fuel pump cc reece Hehe hne nn OFF does not start prime as required Alternator after euer o Ru edd st ON AIR START UNFEATHERING PROCEDURE On Airplanes Equipped With Unfeathering Accumulators Fuel selector d Ghandi ON Aux fuel pump engine LO boost open 1 4 inch Snape ou Ra RICH Magneto switches ciis Prop control amp latch push full forward reduce power until engine is warm Dow fuel ES RS ARP ore OFF ISSUED JANUARY 8 1981 REPORT 1110 REVISED APRIL 9 1982 3 5 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA 34 220T SENECA IH ed ll e e t If engine does not start prime as required and engage starter TOU arb eee wad eae ha ON NOTE The starter may be used in conjunction with the unfeathering accumulators if required FIRE ENGINE FIRE ON GROUND engine has not started Mixtu
139. ER 23 1983 REPORT 1110 3 of 4 9 133 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 20 PA 34 220T SENECA aaa t aa MP aa PANNIS a aa a a a MAIS AIR S a a a a a T aa aa aa THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB H10 ISSUED SEPTEMBER 23 1983 9 134 4 of 4 qe PIPER AIRCRAFT CORPORATION SECTION 9 34 220 SENECA TH SUPPLEMENT 21 PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO 21 FOR CENTURY 31 AUTOPILOT MODEL AK895 This supplement must be attached to the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Century 21 Autopilot System Model AK895 is installed in accordance with SEC SA33908 W D The information contained herein supplements or supersedes the infor mation in the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein For limitations procedures and performance information not contained in this supplement consult the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual FAA APPROVED Wed Eas WARD EVANS NO 50 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA DATE OF APPROVAI February 10 1984 ISSUED FEBRUARY 10 1984 REPORT VB 1110 1 of 26 9 135 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 21 PA 34 220T SENECA Hil SECTION 1 GENERAL This supplement supplies information necessary
140. FAA Approved Piper data The information contained within this supplement is to be used in conjunction with the complete handbook This supplement has been FAA Approved and must remain in this handbook at all times when the optional RCA Color WeatherScout 11 Weather Radar System is installed FAA APPROVED Gre eo _ WARD EVANS D O A 50 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED JANUARY 8 1981 REPORT 1110 1 of 6 9 79 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 12 P A 34 220T SENECA SECTION 2 LIMITATIONS Do not operate the radar during refueling operations or in the vicinity of trucks or containers accommodating flammables or explosives Do not allow personnel within 15 feet of area being scanned roy antenna when system 15 transmitting SECTION 3 EMERGENCY PROCEDURES No changes to the basic Emergency Procedures provided by Section 3 of this Pilot s Operating Handbook are necessary for this supplement SECTION 4 NORMAL PROCEDURES a SYSTEM CONTROLS All controls used to operate the radar system are located on the indicator front panel These controls and the display features are indexed and identified in Figure 4 1 and described in Table 4 3 INDICATOR CONTROLS AND DISPLAY FEATURES Figure 4 1 REPORT VB 1110 ISSUED JANUARY 8 1981 9 80 2of6 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 12 b OPERATION
141. FTOFF 79 KIAS Pressure altitude 2000 ft gt BARRIER AT 79 KIAS dead e COWL ee 172 Gross weight 3969 Ibs Headwind 9 knots cer Takeoff ground 1350 ft Takeoff over 50 ft barrier 1650 ft H 4500 4000 3500 OUTSIDE AIR TEMPERATURE C WEIGHT POUNDS WIND COMPONENT KTS 8 1334 32 1810 330391 NOILVHOdNOO LIVNHONIV 8344 HI VOUNAS lt 1077 lt 4 PIPER AIRCRAFT CORPORATION SECTION 5 PA 34 220T SENECA PERFORMANCE nae SH THIS FIGURE INTENTIONALLY LEFT BLANK Figure 5 9 ISSUED JANUARY 8 1981 REPORT VB 1110 8 15 91 6 GU0SSI 1861 8 11 6 2214 SdV id 87 ANAIKVA PA 34 220T __ MAXIMUM EFFORT TAKEOFF FLAPS 259 SSOCIATED CONDITIONS 800 RPM AND 40 INCHES MAP BEFORE HBRAKE RELEASE PAVED LEVEL DRY RUNWAY jLIFTOFF AT 84 KIAS BARRIER AT 66 KIAS OAT 21 Pressure altitude 2000 ft Gross weight 4250 ibs Headwind 9 knots Takeoff ground roH 800 ft Takeoff distance poe 4434 JONVISIG JdO3 vi EE LI T LE LI i 40 4500 4000 3500 3000 OUTSIDE AIR TEMPERATURE C WEIGHT POUNDS WIND COMPONENT KTS 30NVIAHOJAN 4 d NOLLOAS NOLEVNOdNOO
142. HIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED JANUARY 8 1981 9 2 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA HI SUPPLEMENT 1 PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO 1 FOR PORTABLE OXYGEN SYSTEM INSTALLATION SCOTT AVIATION PRODUCTS EXECUTIVE MARK IH PART NUMBER 802180 00 OR 802180 01 SECTION 1 GENERAL This supplement supplies information necessary for the operation of the airplane when the optional portable oxygen system is installed in accor dance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with the complete handbook This supplement has been FAA Approved and must remain in this handbook at all times when the optional portable oxvgen system is installed Fan FAA APPROV WARD EVANS D O A NO 50 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED JANUARY 8 1981 REPORT 1110 1 of 6 9 3 SECTION9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 1 P A 34 220T SENECA This portable oxygen system provides supplementary oxygen for the crew and passengers during high altitude flights above 10 000 feet The system is secured to the middle center seat with the forward facing seating arrangement and mounted between the center seats with the club seating arrangement The major components of the system consist of two console cylinder kits and six
143. ING GEAR UNSAFE WARNINGS Red light indicates gear in transit Recycle gear if indication continues Light will illuminate when gear warning horn sounds at low throttle settings MANUAL EXTENSION OF LANDING GEAR Check following before extending gear manually Circuit breakers Arai DA et check Battery switeh A can e per BA d be oe eee E E wee ON AEG Kah tae gate ES MPa te check OFF daytime To extend reposition clip downward clear of knob and proceed as follows AIFSD EU dos a y raa ouo UR IDA ne Ea don e he ae reduce 85 KIAS Gear selector VOI cece ERES STRA GEAR DOWN LOCKED position Emerg pear extend KNOB cecus Red Yd ario duca d op ana ee ning puli Indicator ighis FCR RR Gd Su wa ea uiv aM BEC Leave emergency gear extension knob out GEAR UP LANDING Approach T Normal TADS as desired VAN D CR EE closed prior to touchdown REPORT VB 1110 ISSUED JANUARY 8 1981 3 8 REVISED APRIL 9 1982 PIPER AIRCRAFT CORPORATION SECTION 3 34 2207 SENECA Ili EMERGENCY PROCEDURES Batter OFF ite Ac oaa OFF ouch down at minimum airspeed ENGINE FAILURE WITH REAR CABIN AND CARGO DOORS REMOVED min control speed of 67 KIAS for this configuration If airspeed is below 67 K IAS reduce power on operating engine to ma
144. IONS AND INFORMATION 1 2 Aititude Operation For best results reduce rate of climb or descent to 1000 FPM before engaging altitude hold mode Instrument Approach Operations Initial and or intermediate approach segments should be conducted between 90 109 KIAS with up to2 notches 25 selected if desired Upon intercepting the glide path or when passing the final approach fix FAF immediately lower the landing gear and reduce the power for approximately 90 KIAS on the final approach segment Adjust power as necessary during remainder of approach to maintain correct airspeed Monitor course guidance information raw data throughout the approach All power changes should be of small magnitude and smoothly applied for best tracking performance For optimum performance do not change aircraft configuration during final approach while autopilot is engaged For approaches without glide path coupling adjust pitch attitude in conjunction with power to maintain desired airspeed and descent rate Proper rudder trim must be maintained throughout the approach to insure maximum tracking quality NOTE The autopilot will not decouple from the GS or localizer in the event of radio failure however warnings will flash in the mode appropriate to the failure Monitor course guidance raw data during the approach to assure signal quality ISSUED FEBRUARY 10 1984 REPORT 1110 7 of 20 9 141 SECTION 9 PIPER AIRCRAFT CORP
145. IRECTOR INSTALLATION PIPER DWG 36840 SECTION 1 GENERAL This supplement is to acquaint the pilot with the operation of the KFC 200 Automatic Flight Control System as installed in the PA 34 220T Seneca in accordance with FAA Approved Piper data The must operated within the limitations herein specified This supplement has been FAA Approved based on King STC 1147 and must remain in this handbook at all times when the optional King KFC 200 Automatic Flight Control System is installed FAA WARD EVANS D O A NO SO I PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED APRIL 21 1981 REPORT VB 1110 1 0416 9 33 PIPER AIRCRAFT CORPORATION SECTION 9 34 220 SENECA SUPPLEMENT 5 The 200 is certified in this airplane with two axis control pitch and roll The airplane is equipped with a manual electric trim system which is controlled by pilot operation of the trim switch When the autopilot is coupled the autopilot uses the electric trim to accomplish automatic trimming to unload the autopilot elevator servo so that autopilot disengagement does not result in transient airplane motion An autotrim electric pitch trim monitor is provided in the autopilot Auto trim and or electric pitch trim faults are visually annunciated on the Mode Annunciator and accompanied by an audible warning ABBREVIATIONS AFCS Automatic Flight Control System ALT Altitude or Altitud
146. ISCONNECT ALERT The Autopilot Disconnect Alert wil sound an audible warning for approximately 2 seconds whenever the autopilot engage lever on the KC 290 Mode Controller is disengaged PILOT S CONTROL WHEEL SWITCH FUNCTIONS AP DISC TRIM INTERRUPT This emergency disconnect switch will disengage the AP interrupt the power to the electric trim system and disconnect all FD Modes To resume control a FD Mode and the AP lever on the Mode Controller must be re engaged In the event of electric trim or autotrim failure the switch can be held depressed which removes all power from the trim system to allow the pilot time to turn offthe RADIO POWER switch and pull the PITCH TRIM circuit breaker CWS This switch when depressed and held will allow the pilot to manually fly the airplane without disengaging the AP When the switch is released the AP will resume control within the pitch and roll attitude limits The CWS switch will resync the FDin PAH or ALT hold and will transfer the mode to When the CWS is held depressed Manual Electric Trim may be operated without disengaging the AP ISSUED APRIL 21 1981 REPORT VB 1110 7 of 16 9 25 SECTION9 PIPER AIRCRAFT CORPORATION SUPPLEMENT4 00 _ PA 3 220T SENECA 01 MANUAL PITCH TRIM Manual Electric Pitch Trim is activated bv dual action type switch that requires both parts to be moved simultaneously for actuating up or down trim command
147. KIAS and use wing flaps as required WARNING Under some conditions of loading and density altitude a go around may be impossible and in any event the sudden application of power during one engine inoperative operation makes control of the airplane more difficult ONE ENGINE INOPERATIVE GO AROUND NOTE A one engine inoperative go around should be avoided if at all possible To execute a one engine inoperative go around advance the mixture a propeller levers forward The throttle should be advanced slowly to 40 Hg manifold pressure Retract the flaps and landing gear Maintain sci at the one engine inoperative best rate of climb speed of 92 KIAS Set the trim and cowl flaps as required AIR START UNFEATHERING PROCEDURE Move the fuel selector for the inoperative engine to the ON position and check to make sure the AUX fuel pump forthat engine is on LO boost Open the throttle t 4 inch and the mixtures should be set RICH Turn ON the magneto switches and push the propeller contro latch and propeller control lever full forward On airplanes equipped with the optional unfeathering system the propeller will start to windmill On airplanes not so equipped REPORT VB 1110 ISSUED JANUARY 8 1981 3 16 REVISED APRIL 9 1982 PIPER AIRCRAFT CORPORATION SECTION 3 PA 34 220T SENECA EMERGENCY PROCEDURES pU E Bde engage the starter until the propeller windmills freely 1f the engine does not start prime as necessary After r
148. KTS at all power settings b The decrease in range may be as much as 25 nautical miles for the 93 gallon capacity c The decrease in range may be as much as 35 nautical miles for the 123 gallon capacity Climb performance is affected by the air conditioner operation A decrease in the rate of climb of as much as 80 fpm can be expected at ail altitudes with the air conditioner operating ISSUED JANUARY 8 1981 REPORT 1110 5 of 6 9 17 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 3 PA 34 220T SENECA THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 i ISSUED JANUARY 8 1981 _ _ 9 18 6of6 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 4 ne PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO 4 FOR KFC 200 AUTOMATIC FLIGHT CONTROL SYSTEM WITH FLIGHT DIRECTOR INSTALLATION PIPER DWG 36840 SECTION 1 GENERAL This supplement is to acquaint the pilot with the operation of the KFC 200 Automatic Flight Control System with optional Flight Director as installed in the PA 34 220T Seneca in accordance with FAA Approved Piper data The airplane must be operated within the limitations herein specified This supplement has been FAA Approved based on King STC SA1147CE and must remain in this handbook at all times when the optional King KFC 200 Automatic Flight Control System i
149. L USED ONLY CURSOR WITH QPTIONAL BUTTON POSITIONED EQUIPMENT PLUS WEATHER RANGE MARK 30 MILE PRESS TO PRESS TO INCREASE RANGE LIST OR CHANGE MODES PRESS INDICATES DECREASE RANGE BUTTON PRESSED BUT NAV NOT CONNECTED ANTENNA TILT CONTROL FUNCTION SWITCH LOCKING PRESS LEFT AIGHT RETAIN DISPLAY PRESS TO MOVE TRACK CURSOR IN 2026A CONTROLS AND DISPLAYS Figure 4 1 REPORT VB 1110 ISSUED JANUARY 8 1981 9 98 206 PIPER AIRCRAFT CORPORATION SECTION 9 34 220 SENECA SUPPLEMENT 15 CONTROL DISPLAY Function selector RANGE button TILT control TRACK button FUNCTION OFF position removes primary power from the system 2 STBY position places system in the standby condition during warm up period and when the system 15 not in use No display 3 TEST position selects test function to de termine operability of the system A test pattern is displayed NO transmission exists in the TEST condition 4 ON position selects the condition for normal operation Radar transmission exists in the ON position Clears the display and places the indicator in the next lower range each time the button is pressed eg 40 to 20 until minimum range ts reached Electrically adjusts the antenna to move the radar beam up to 15 degrees above the hori zontal or toa maximum of 15 d
150. MALFUNCTION 1 Emergency Disengagement of Hold the Control Wheel firmly and press the AP DISC TRIM INTERRUPT Switch b ELECTRIC TRIM MAL PUNCTION either manual electric or autotrim 1 DISC TRIM INTERRUPT Switch Press nid hold down until recovery can be made 2 RADIO POWER Switch OFF 3 Aircraft manually retrim 4 PITCH TRIM circuit breaker Pull 5 RADIO POWER Switch CAUTION When disconnecting the autopilot after a trim malfunction hold the control wheel firmly up to 45 pounds of force on the control wheel may be necessary to hold the aircraft level ENGINE FAILURE COUPLED 1 Disengage AP 2 Follow basic Airplane Flight Manual engine inoperative procedures 3 Airplane rudder and aileron axes must be manually trimmed prior to engaging autopilot for engine inoperative operations CAUTION If rudder and aileron trim cannot be main tained when power is changed during a single engine inoperative coupled approach disen gage autopilot and continue approach manually CAUTION At airspeeds below 110 MPH 96 KTS IAS rapid power application may cause a pro nounced pitch up attitude of 20 or more REPORT VB 1110 ISSUED APRIL 21 1981 9 32 4 of 16 REVISED FEBRUARY 25 1982 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA HI SUPPLEMENT 4 d AUTOPILOT DISENGAGEMENT 1 The autopilot can be manually disengaged by the following actions 2 a
151. NG A DEAD ENGINE A loss of thrust will be noted and with coordinated controls the nose of the aircraft will yaw in the direction of the dead engine ENGINE SECURING PROCEDURE FEATHERING PROCEDURE Keep in mind that the one engine inoperative air minimum contro speed is 66 KIAS and the one engine inoperative best rate of climb speed is 92 KIAS To feather a propeller maintain direction and an airspeed above 85 KIAS Move the mixture and propeller controls forward Fhe throttle controls should be moved forward to maintain a safe airspeed Retract the flaps and landing gear and identify the inoperative engine The airplane will in the direction of the dead engine Retard the throttle of the inoperative engine to verify loss of power NOTE lf circumstances permit m the event of actual engine failure the pilot may elect to attempt to restore power prior to feathering circumstances permit an attempt to restore power prior to feathering adjust the mixture control as required move the fuel selector control to ON and select either 1 left or right magneto Movethe ALTERNATE AIR control to ON and the AUX fuel pump to the ON HI position power is not immediately restored turn off the AUX fuel pump ISSUED JANUARY 8 1981 REPORT VB 1116 3 13 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES 34 220 SENECA The propellers can be feathered only while the engine is rotating above 800
152. No changes to the basic Emergency Procedures provided by Section 3 of this Pilot s Operating Handbook are necessary for this supplement SECTION 4 NORMAL PROCEDURES SYSTEM CONTROLS All controls used to operate the radar system are located on the front panel These controls and the display features are indexed and identified in Figure 4 1 and described in Table 4 3 INDICATOR CONTROLS AND DISPLAY FEATURES Figure 4 1 REPORT VB 1110 lt ISSUED JANUARY 8 1981 9 86 2016 PIPER AIRCRAFT CORPORATION PA 34 220T SENECA 4 8 9 OFF INT TILT RANGE 12 30 60 90 12 30 60 120 Range Fieid Test Field Range Mark Identifier Mode Field SECTION 9 SUPPLEMENT 13 On Off function full CCW rotation of INTensity control places system in OFF condition Rotary control used to regulate brightness INTensity of display Rotary control used to adjust antenna elevation position Control indexes incre ments of tilt from 0 to 12 degrees up or down Rotary switch used to select one of four ranges Pushbutton switch used to select contour mode Data is presented alter nately as normal for 0 5 seconds then contoured for 0 5 seconds Pressing switch a second time restores normal or WX mode Maximum selected range is displayed Maximum range 1 always displayed when indicator is in on condition Test block displays three illumination levels Individual
153. ORATION SUPPLEMENT 21 PA 34 220T SENECA 3 Instrument Approach Go Around Maneuver Disconnect the autopilot and manually control the aircraft b Add takeoff power or power as desired c Check that correct attitude and a positive rate of climb is indicated then raise gear and flaps d Sct the heading bug to the desired missed approach heading Rc engage the autopilot SECTION 5 PERFORMANCE No change SECTION 6 WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance data in Section 6 of the basic Pilot s Operating Handbook SECTION 7 DESCRIPTION AND OPERATION The Century 31 Autopilot is a light weight electronic autopilot system utilizing vertical and directional gyro signals and D C electric servos to provide three axis sensing and two surface control The system includes lateral and vertical radio coupling command and automatic elevator trim and navigation and autopilot failure monitor and warning systems REPORT VB 1110 ISSUED FEBRUARY 10 1984 9 142 8 of 20 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 21 The Century 31 is activated with the aircraft master switch and operates in a low power state until the autopilot isengaged Mode selection is made by pushing the desired mode switch on the mode programmer The selected mode will illuminate on the annuneiator panel The annunciator panel contains an ambient light l
154. PILOT S INFORMATION MANUAL SENECA Ill 22 AS 52551 A 25 USES 521 95655 2552205 oS S TATUM S NS 2 n O Vn i SS ES I AS 5552 Dem us oy R eS 5 Sas n SUA DANS eS 5 m a 2 5 T 2s Des A RAR Rd m TE SES 25 VAN 2 15 lt RSE 2 55 21 dn roe Soren Sethe ON URS 5525 us N 552 An me 955 559 T 227 d n d d e x VERA 555 Seneca lli PA 34 220T HANDBOOK PART NO 761 756 Published by PUBLICATIONS DEPARTMENT Piper Aircraft Corporation Issued January 8 1981 REPORT VB 1110 ii APPLICABILITY Application of this handbook is limited to the specific Piper PA 34 220T model airplane designated by serial number and registration number the face of the title page of this handbook This handbook cannot be used for operational purposes unless kept in a current status REVISIONS The information compiled in the Pilot s Operating Handbook with the exception of the equipment list will be kept current by revisions distributed to the airplane owners The equipment list was current at the the air plane was licensed by the manufacturer and thereafter must be maintained by the owner Revision material will consist of information necessary
155. PIPER AIRCRAFT CORPORATION SECTION 3 PA 34 220T SENECA EMERGE NC Y PROCEDURES loads be reinstated as required to maximum of 60 amperes I both alternator outputs cannot be restored both alternator switches should be lett OFF Reduce the electrical load to essential systems and land as soon as practical The battery is the only remaining source of electrical power If one ammeter shows zero output cycle its switch OF Fand then ON If this fails to restore output check the circum breakers The breakers may be reset once required If the alternator remains inoperative reduce electrical loads if necessary and exercise judgment regarding continued flight Corrective maintenance actions should be performed prior to further lights he markings on the ammeters loadmeters require mental interpolations to estimate the ampere values noted Operating the alternators at Jess than 60 amperes will assure that the battery will not be depleted WARNING Compass error may exceed 10 with both alternators inoperative abnormally high alternator outputs are observed and persists more than 30 amps above known electrical loads they may be caused by a low batters a battery fault or other abnormal elecirical load If itis caused low batters the indication should begin to decrease towards normal within 5 minutes Hf this condition is observed proceed with the following Turn the battery switch OFF and the alternat
156. PORT VB 1110 4 1 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA 34 220T SENECA edad 4 3 AIRSPEEDS FOR SAFE OPERATIONS The following airspeeds are those which are significant to the operation of the airplane These figures are for standard airplanes flown at gross weight under standard conditions at sea level Performance for a specific airplane may vary from published figures depending upon the equipment installed the condition of the engine airplane and equipment atmospheric conditions and piloting technique a Best Rate of Climb Speed 92 KIAS b Best Angle of Climb Speed 76 KIAS c Turbulent Air Operating Speed See Subsection 2 3 140 KIAS d Maximum Flap Speed 115 KIAS e Landing Final Approach Speed Flaps 40 Short Field Effort 82 KIAS Intentional One Engine Inoperative Speed 85 KIAS 2 Maximum Demonstrated Crosswind Velocity 17 KTS REPORT VB 1110 ISSUED JANUARY 8 1981 4 2 PIPER AIRCRAFT CORPORATION SECTION 4 PA 34 220T SENECA NORMAL PROCEDURES 4944 WALK AROUND Figure 4 1 4 5 NORMAL PROCEDURES CHECKLIST PREPARATION Airplane STATUS airworthy papers on board UID suitable urhe ke ES EE Vl diee weighed stowed tied Weight and C Goesev emi en within limits eoa e planned Charts and navigation equipment on board Performanc
157. PPR mode is engaged with wings level and there is a centered needle on the CDI In that situation the mode will go directly to APPR CPLD as displayed on the annunciator panel The system can intercept at any angle up to 90 and will always turn toward the course pointer See approach procedure for more detail APPR mode can be disengaged by depressing the APPR switch on the Mode Controller by depressing the GO AROUND switch on the engine throttle control or by engaging HDG when in APPR CPLD or engaging NAV when in APPR CPLD or APPR ARM CAUTION The APPR mode of operation will continue to provide airplane commands and or control without a valid VOR LOC signal NAV view Also erroneous navigation information may result from COMM radio interference with the NAV radio This erroneous infor mation may cause premature APPR captures as well as erroneous steering information Should this occur reselect HDG mode and then reselect APPR mode Back Course Mode BC For BC operation proceed as for normal approach mode but engage BC mode after selecting APPR The BC mode reverses the signals in the computer and cannot be engaged without a LOC frequency selected BC status is indicated on the annun ciator panel BC mode can be disengaged by depressing either the BC APPR or GO AROUND switches or by selecting other than a LOC frequency on the NAV receiver ISSUED APRIL 21 1981 REPORT 1110 13 of 16 9 31 SECTION 9
158. R ONLY If both upper and side latches are open the door will trail slightly open and airspeeds will be reduced slightly To close the door in flight Siew airplane to 90 KIAS bees close ac babes SS oes vg latch latch B OpEN EX AT pull on armrest while moving latch handle to latched position li both latches TET latch side latch then top latch PROPELLER OVERSPEED PARQUE a oos ACE D DR aci ee Sa Res retard Prop COD es vo pe Dr tete oH aeree dodi d full DECREASE rpm then set if any control available Arts peed a oe eus Na S pa Eq pac eda reduce wr d etos as required to remain below 2600 rpm ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED APRIL 9 1982 3 11 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA 34 220T SENECA HI THIS PAGE INTENTIONALLY LEFT BLANK REPORT 1110 ISSUED JANUARY 8 1981 3 12 PIPER AIRCRAFT CORPORATION SECTION 3 PA 34 220T SENECA EMERGENCY PROCEDURES 35 AMPLIFIED EMERGENCY PROCEDURES GENERAL The following paragraphs are presented to supply additional information for the purpose of providing the pilot with a more complete understanding of the recommended course of action and probable cause of an emergency situation 3 7 ENGINE INOPERATIVE PROCEDURES DETECTI
159. RPM Loss of centrifugal force due to slowing RPM will actuate a stop pin that keeps the propeller Jrom feathering each time the engine is stopped on the ground One engine inoperative performance will decrease if the propeller of the inoperative engine is not feathered The propeller control of the inoperative engine should be moved to the feather position and the mixture control of the inoperative engine to idle cut off Trim the aircraft as required and maintain a 3 to 5 bank toward the operating engine The ball will be to for minimum drag The AUX fuel pumps should be off except in the case of an engine driven fuel pump failure Turn OFF the magnetos and close the cowl flaps on the inoperative engine Cowl flaps should be used as necessary on the operative engine The alternator of the inoperative engine should be turned OFF and the electrical load reduced to prevent depletion of the battery Move the fuel selector control for the inoperative engine to the OFF position H necessary consider the use of crossfeed refer to Fuel Management During One Engine Inoperative Operation paragraph 3 11 Turn OFF the operative engine s AUX fuel pump NOTE When an engine is feathered the alternator gyro and oil annunciator warning lights will remain illuminated ENGINE FAILURE DURING TAKEOFF BELOW 85 KIAS The one engine inoperative air minimum control speed for this airplane is 66 KIAS under standard conditions e
160. RY 10 1984 4 5 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDU RES 34 220T SENECA When starting at ambient temperatures 20 F and below operate first engine started with alternator ON at max charging rate not ta exceed 1500 RPM for S minutes minimum before initiating start on second engine STARTING ENGINES AIRPLANE EQUIPPED WITH OPTIONAL ENGINE PRIMER SYSTEM eto us ON lig FULI RICH JT bird FORWARD Prop control ev better a DER we FULL FORWARD RANGE OW HC estet ien doa def ee ee ON mags dogs qua oco ON AU pun er arnt oe de ers het owe hee ps dades OFF BOP REE ES ON see Figure 4 3 for Priming Time T hatt ets sa serae EOE ee ees MON Seo es Boe BE CLOSE SLE TIS C wc ec OR Glare aka engage At temperatures below 207F conunee priming while cranking engine When engine starts amp accelerates thru 590 carts a aM PP release Phe equ advance slowly to obtain 1000 RPM e ees a release Apes Poet AUN P low only as necessary to obtain smooth engine operation 1 3 minutes will be required when temp is below 20 F Oil DICSSHEC check Repeat for opposite engine 252 Ii et ose XO o c
161. SENECA NORMAL PROCEDURES 415 STARTING ENGINES AIRPLANE EQUIPPED WITH STAN DARD ENGINE PRIMER SYSTEM The first step in starting is to move the fuel selector to the ON position Advance the mixture control to full RICH open the throttle half travel and move the propeller control full FORWARD Turn the battery switch and ignition switches ON After ensuring that the propellers are clear engage the starter The primer button should be used ON as required For cold weather starts refer to paragraph 4 21 Starting Engines in Cold Weather When the engine starts retard the throttle and monitor the oil pressure gauge If no oil pressure is indicated within 30 seconds shut down the engine and have it checked In cold weather it may take somewhat longer for an oil pressure indication Repeat the above procedure for the opposite engine After the engines have started check the alternators for sufficient output and the gyro suction gauge for a reading between 4 8 and 5 1 in Hg 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 it This practice damage the starter mechanism ISSUED JANUARY 8 1981 REPORT VB 1116 REVISED AUGUST 17 1981 4 17 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA 34 220T SENECA IH RARE E
162. STEM PIPER DWG 36978 SECTION 1 GENERAL This supplement supplies information necessary for the operation of the airplane when the optional King KNS 80 Navigation System is installed in accordance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with the complete handbook This supplement has been FAA Approved and must remain in this handbook at all times when the optional King KNS 80 Navigation System 1 installed FAA E TR WARD EVANS D O A NO 50 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED JANUARY 8 1981 REPORT VB 1110 1014 9 71 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 16 PA 34 220T SENECA SECTION 2 LIMITATIONS No changes to the basic limitations provided by Section 2 of this Pilot s Operating Handbook are necessary for this supplement SECTION 3 EMERGENCY PROCEDURES No changes to the basic Emergency Procedures provided by Section 3 of this Pilot s Operating Handbook are necessary for this supplement SECTION 4 NORMAL PROCEDURES KNS 80 OPERATION The KNS 80 can be operated in any one of 3 basic modes VOR b RNAV or c ILS To change from one mode to another the appropriate pushbutton switch is pressed except that the ILS mode is entered automatically whenever an ILS frequency is channeled in the USE waypoint The display will annunciate the mode by lighting a message above the
163. Select LOC Localizer NAV Navigation PAH Pitch Attitude Hold Pictorial Navigation Indicator REPORT VB 1110 9 20 2 of 16 ISSUED APRIL 21 1981 REVISED FEBRUARY 25 1982 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SUPPLEMENT 4 SECTION 2 LIMITATIONS a During autopilot operation pilot must be seated at the controls with seat belt fastened Operation is restricted to left side pilot position b Maximum speed for autopilot operation is 200 KIAS c The maximum altitude for operation of the autopilot has not been determined The maximum altitude flight tested was 24 000 feet d Do not extend flaps beyond 25 during autopilot operation The autopilot must be disengaged during takeoff and landing f System approved for Category 1 operation only APPR selected 2 Autopilot attitude command limits Pitch 15 Roll 25 In accordance with FAA recommendations use of Aititude Hold mode is not recom mended during operation in severe turbulence h Placards Location Pilot s control wheel left horn AP TRIM DISC INTERRUPT Pilot s control wheel left horn _ CWS Pilot s control wheel left horn TRIM UP DN Left throttle lever GO AROUND ISSUED APRIL 21 1981 REPORT VB 1110 30116 9 21 SECTION 9 PEPER AIRCRAFT CORPORATION SUPPLEMENT 4 PA 34 220T SENECA SECTION 3 EMERGENCY PROCEDURES AUTOPILOT
164. T VB 1110 ISSUED APRIL 21 1981 9 26 8 of 16 REVISED FEBRUARY 25 1982 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 4 UN ADR d PREELIGHT CHECK Run prior to each flight 1 With no modes engaged and power applied to all systems depress the TEST button on the Mode Controller All mode annunciators will be illuminated on the annunciator panel and the red autotrim failure light will flash At least four but no more than six flashes must be observed to indic te proper operation of the autotrim manual electric trim feature and an audible warning should sound 2 Engage the FD then engage AP depress the CWS switch center the flight controls and release CWS Apply force to the controls to determine if the AP can be overpowered 3 Check that the pilot s emergency disconnect switch disconnects the autopilot 4 Perform the following manual electric pitch trim checks a Actuate the left side switch to the fore and aft positions The trim solenoid should engage but the trim should not run Solenoid engagement may be confirmed by addi tional force required to move trim wheel b Actuate the right side switch to the fore and aft positions The trim solenoid should not engage and the trim should not run c Grasping the manual trim wheel run the trim both up and down and check the overpower capability d Press the AP DISC TRIM INTERRUPT switch down and hold The manual electric
165. TE It may be necessary to apply an external power source and preheat to facilitate engine cranking if the aircraft s battery is deficient of charge Prior to attempting the start turn the propellers through by hand three times after ensuring that the magneto switches are off and mixture controls are in the full aft position Upon entering the cockpit begin the starting procedure by moving the fuel selector to ON Advance the mixture to full RICH and the throttle and prop controls to full FORWARD Turn ON the battery switch and the ignition switches mags The auxiliary fuel pump should be ON in the LO boost position Push the primer button and engage the starter simultaneously Begin moving the throttle control back and forth from full forward to full aft Release the primer button after about 3 seconds of cranking Leave the primer button off for 3seconds of cranking and then reapply primer for about 3 seconds repeat until the engine begins to fire When the engine begins firing leave the starter engaged and tap the primer periodically until a rhythmic firing pattern is observed and then release the starter switch and position the throttle at half travel Tap the primer button if the engine begins to falter during this period and adjust the throttle to a 1000 RPM idle speed The auxiliary fuel pump may be turned OFF as soon as it is determined that the engine will continue to run without it REPORT VB 1110 ISSUED JANUARY 8 1981 4 2
166. UARY 8 1981 SECTION 2 LIMITATIONS KIAS 92 166 to 205 67 to 166 64 to 115 2 Continental 1SIO 360K B LTSIO 360K B 2800 2600 40 460 F 240 10 PSI 100 PSI 3 5 PSI to 18 1 PSI 21 PSI 100 10011 Aviation Grade 2 REPORT VB 1110 2 3 SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS 34 220 7 SENECA Hil ep PH G Propeller Manufacturer Hartzell Two Blade Standard Propeller Hub and Blade Models a Left BHC C YF2CKUF FC8459 8R b Right BHC C2YF2CLKUF FJC8439 8R c Left 32AF32C508 82NFA 6 d Right 32 32 509 L82NFA 6 NOTES Avoid continuous operation between 2000 and 2200 RPM above 32 IN HG manifold pres sure Avoid continuous ground operation between 1700 and 2100 RPM cross and tail winds over 10 knots McCauley Three Blade Optional Propeller Hub and Blade Models a Left 2 508 S2NF A 6 b Right 3AF32C 509 I S2NF A 6 1 Propeller Diameter inches Maximum 76 Minimum 15 REPORT VB 1110 ISSUED JANUARY 8 1981 2 4 REVISED SEPTEMBER 23 1983 PIPER AIRCRAFT CORPORATION PA 34 220T SENECA SECTION 2 LIMITATIONS 2 9 POWER PLANT INSTRUMENT MARKINGS a b d e 8 Tachometer Green Arc Normal Operating Range Yellow Arc Takeoff 5 Min Red Line Maximum Fuel Flow Pressure Green Arc Normal Operating Range Yellow Arc 5 Min Red
167. URES AUTOPILOT in the event of an autopilot malfunction or anytime the autopilot is not performing as commanded do not attempt to identify the problem Regain control of the aircraft by overpowering and immediately disconnecting the autopilot by depressing the AP ON OFF switch on the programmer OFF or by pulling the autopilot circuit breaker Do not operate until the system failure has been identified and corrected 1 Altitude Loss During Malfunction a Anautopilot malfunction during climb cruise or descent with a 3 second delay in recovery initiation could result in as much as 60 of bank and 300 altitude loss Maximum altitude loss was recorded at 180 KI AS during descent at high altitude b An autopilot malfunction during an approach with a second delay in recovery initiation could result in as much as 30 bank and 100 altitude loss Maximum altitude loss measured with one notch 10 degrees flap gear down and operating either coupled or uncoupled single or multi engine b COMPASS SYSTEM 1 Emergency Operation with Optional NSD 360A HSI Slaved Non Slaved NSD 360A a Appearance of HDG Flag I Check air supply gauge vac or pressure for adequate air supply 4 in Hg min REPORT VB 1110 ISSUED APRIL 21 1981 9 108 2046 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 17 2 Check compass circuit breaker 3 Observe display for proper opera
168. UST 9 1982 PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA DESCRIPTION amp OPERATION ALLA T e a a TT t MATT TINTE TP aaa T T An optional ground clearance energy saver system is available to provide direct power to Comm 1 without turning on the master switch An internally lit pushbutton switch located on the instrument panel provides annunciation for engagement of the system When the button is engaged direct aircraft battery power is applied to Comm 1 audio amplifier speaker and radio accessories The switch must be turned off or depletion of battery could result An Auxiliary Avionics Bus Switch is located on the instrument panel to the right of the copilot control wheel shaft The switch is provided to give auxiliary power to the avionics bus in the event of a radio master switch circuit failure The manifold pressure lines have drain valves located behind and below the dua manifold pressure gauge at the bottom of the instrument panel This allows any moisture which may have collected from condensation to be pulled into the engines This is accomplished by depressing the two valves for 5 seconds while operating the engines at 1000 RPM Do not depress the valves when manifold pressure exceeds 25 inches Hg ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 9 1982 7 27 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA
169. a slight amount of power whenever practical and approach speeds should be increased by 10 to 15 knots Cruise speed may be significantly reduced in prolonged icing encoun ters If icing conditions are encountered at altitudes above 10 000 feet it may be necessary to descend in order to maintain airspeed above the best rate of climb speed 92 KIAS NOTE Pneumatic boots must be regularly cleaned and waxed for proper operation in icing conditions Pitot windshield and lift detector heat should be checked on the ground before dispatch into icing conditions ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 17 1981 9 of 10 9 53 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 6 PA 34 220T SENECA SECTION 5 PERFORMANCE WARNING Ice accumulation of the unprotected surfaces can result in significant performance loss Installation of ice protection equipment results in a 30 F P M decrease in single engine climb performance and a reduction of 850 feet in single _ engine service ceiling other performance is unchanged REPORT VB 1110 ISSUED JANUARY 8 1981 9 54 10 of 10 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 5 8 Landing or missed approach a Landing Disengage AP and land b Missed Approach Disengage AP and perform missed approach procedures per Airplane Flight Manual BACK COURSE PROCEDURE Same as front course except that BC is engaged after APPR is en
170. ading may be assumed acceptable for landing IT 15 THE RESPONSIBILITY OF THE PILOT AND AIRCRAFT OWNER TO INSURE THAT THE AIRPLANE IS LOADED PROPERLY SAMPLE LOADING PROBLEM Figure 6 9 ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 9 1982 6 11 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND B BALANCE PA 3 34 2207 SENECA iH LEE TIN Arm Aft Weight Datum Moment l bs E 1n L bs AR ge pei mm Et amo Basic Empty Weight Pilot and Front Passenger sing ir i 1 Passengers Center Seats i E 1 Forward Facing i ra en namena ea ttt Passengers Center Seats _ Facing 100 Lt bs Max Zn RE M aae RETE Zero Fuel Weight 4470 Lbs Max Std Sce equipment list Fuel 93 Gal Max 5td 123 Gal Max Opt Takeoff Weight 4750 M ER A A a a a aai te at a aat Ma PAS PA The center of gravity C G for the takeoff weight of the actual fondle problem ts at inches aft of the datum line Locate this point on the range and weight graph If this point falls within the weight envelope this loading meets the weight and balance requirements Takeoff Weight 4750 Lbs Max B a T a i a ta n ye Minus Estimated Fue Burnoff we Approximately 90 bs per hr Landing Weight 451 3 Lb
171. age lever on the KC 292 Mode Controller is disengaged PILOT S CONTROL WHEEL SWITCH FUNCTIONS AP DISC TRIM INTERRUPT This emergency disconnect switch will disengage the AP interrupt the power to the electric trim system To resume AP control the AP lever on the Mode Con troller must be re engaged In the event of electric trim or autotrim failure the switch can be held depressed which removes all power from the trim system to allow the pilot time to turn off the RADIO POWER switch and puli the PITCH TRIM circuit breaker CWS This switch when depressed and held will allow the pilot to manually fly the airplane without disengaging the AP When the switch is released the AP will resume control within the pitch and roli attitude limits The CWS switch will resync PAH or ALT hold When the CWS is held depressed Manual Electric Trim may be operated without disengaging the AP MANUAL PITCH TRIM Manual Electric Pitch Trimis activated by a dual action type switch that requires both parts to be moved simultaneously for actuating up or down trim commands Operation of the manual electric pitch trim switch will disengage the AP lever switch on the Mode Controller except when CWS switch is held depressed as previously noted ISSUED APRIL 21 1981 REPORT VB 1110 REVISED FEBRUARY 25 1982 7 of 16 9 39 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 5 PA 34 220T SENECA NOTE The flight control system incorporates its
172. aircraft only storm window DO NOT OPEN ABOVE 129 KI AS In full view of the pilot for flight with the aft fuselage doors removed FOR FLIGHT WITH AFT DOORS REMOVED CONSULT THE LIMITATIONS ANDPROCEDURES SECTIONS OF THE AIRPLANE FLIGHT MANUAL REPORT VB 1110 ISSUED JANUARY 8 1981 2 11 SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS PA 34 220T SENECA On the inside of both od Hiter access doors COOLER WINIFRIZATION PLATE TO BF REMOVED WHEN AMBIENT TEMPERATURE EXCEEDS 50 F On the executive writing table CAUTION THIS TABLE MUST BE 5 DURING TAKEOFF AND LANDING On the instrument pane in full view of the pilot 2 blade propellers only AVOID CONTINUOUS GROUND OPERATION 1700 2100 RPM IN CROSS TAIL WIND OVER IO KT AVOID CONTINUOUS OPERATIONS 2000 2200 RPM ABOVE 32 MANIFOLD PRESSURE Near the magnetic compass CAUTION COMPASS CALIBRATION MAY BE IN FRROR WITH ELECTRICAL FQUIPMENT OTHER THAN AVIONICS REPORT 1110 ISSUED JANUARY 8 1981 3 12 REVISED SEPTEMBER 23 1983 PIPER AIRCRAFT CORPORATION SECTION 2 34 220 SENECA IH LIMITATIONS Adiacent to fuel tank filler caps FUET 100 OR 10011 AVIATION GRADE Adiacent to fuel tank filler caps serial numbers 34 8333042 and ISSUED SEPTEMBER 23 1983 REPORT VB 1110 2 13 TABLE CONTENTS SECTION 3 EMERGENCY PROCEDURES Paragraph No esa Sot IC
173. ance requirements NOTES Actual fuel allowance for start up taxi and run up 23 lbs max should be determined based on local operating condition Moment due to gear retraction does not signis cantly affect C G location REPORT 1110 ISSUED JANUARY 8 1981 6 10 REVISED FEBRUARY 25 1982 PIPER AIRCRAFT CORPORATION SECTION 6 34 2207 SENECA WEIGHT AND BALANCE Datum Mament Inches 1n Lbs Basic Empis Weight 88 5 284262 u Pilot and Front Passe _ 85 5 29070 Passengers Center Pik orward Facing Passe ngers Center Seats _ Facing Optional Passe ngers Rear Seats BREMEN p EF T a a a a a e a i ey Zero Fuel Weight 44470 Lbs Std Sec equipment list Fuel 93 Gal 1 Std 123 Gal ene pecan east pepe eeepc en 3 Weight 14750 Ibs ______ 99 446102 The center of gravity C G of this sample loading problem is at 93 9 inches aft of the datum line Locate this point 93 9 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 4750 93 9 446102 Minus FOE Fue a an the center of gravity for the landing weight on the C G range and weight graph If this point falis within the weight C G envelope the Jo
174. ank and 100 altitude 1055 Maximum altitude loss measured with one notch 10 degrees flaps gear down and operating either coupled or uncoupled single or multi engine b COMPASS SYSTEM 1 Emergency Operation with Optional NSD 360A HSI Slaved and or Non Siaved NSD 360A Appearance of HDG Flag 1 Check air supply gauge vac or pressure for adequate air supply 4 in Hg min 2 Check compass circuit breaker 3 Observe display for proper operation ISSUED APRIL 21 1981 REPORT VB 1110 REVISED FEBRUARY 25 1982 3 of 12 9 115 SECTION 9 _ PIPER AIRCRAFT CORPORATION SUPPLEMENT 18 PA 34 220T SENECA IH b disabie heading card pull circuit breaker and use magnetic compass for directional data NOTE If heading card is not operational should not be used c With card disabled VOR Localizer and Glide Slope displays are still functional use card set to rotate card to aircraft heading for correct picture d Slaving Failure i e failure to self correct for gyro drift 1 Check gyro slaving switch is set to No 1 position if equipped with Slave No 1 No 2 switch or Slaved position when equipped with Slaved and Free Gyro Mode Switch 2 Check for HDG Flag Check compass circuit breaker 4 Reset heading card while observing slaving meter Pad siaving meter e or a needle displaced fully one direction indicates a slaving system failure
175. annunciator light provide a means of monitoring the electrical system operation The two ammeters load meters indicate the output of the alter nators Should an ammeter indicate a load much higher than the known consumption of the electrical equipment in use an aiternator malfunction should be suspected and the respective alternator switch turned off In this event the remaining alternator s ammeter should show a normal indication after approximately one minute If both ammeters indicate a load much higher than the known consumption for more than approximately five minutes an electrical defect other than the alternator system should be suspected because a discharged battery will reduce the alternator load as it approaches the charged conditions A zero ammeter reading indicates alternator is not producing current and should be accompanied by illumi nation of the ALT annunciator light A single alternator is capable of supporting a continued light in case of alternator or engine failure in most conditions however with deicing equipment and other high loads care must be exercised to prevent the loads from exceeding the 65 ampere rating and subsequent depletion of the battery For abnormal and or emergency operations and procedures refer to Section 3 Emergency Procedures ISSUED AUGUST 9 1982 REPORT VB 1110 7 19b SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA HI
176. any vertical mode TRIM The TRIM warning light located in the lower right corner of the annunciator panel will flash and be accompanied by an audible warning whenever the following autotrim and or manual electric pitch trim failures occur Trim servo motor running without a command is monitored on the manual electric and auto trim The trim servo motor not running when commanded to run and the trim servo motor running in the wrong direction are monitored on Autotrim only The TRIM warning light should flash at least 4 but not more than six times and the audible warning sounds when the test switch on the Mode Controller is depressed REPORT VB 1110 _ ISSUED APRIL 21 1981 9 38 6 of 16 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 5 e GS The Glide Slope valid GS pointer being view PNI has to be present before GS may couple Hatter GS coupled the valid is lost the system will flash the GS Annunciator and transfer from GS coupled to H the GS valid returns the svstem will revert back to GS NAV FLAG The NAV or APPR Modes ARM or CPLD may be selected and will function with or without a NAV warning flag present The AP will continue to provide steering information with or without valid NAY signal AP DISCONNECT ALERT The Autopilot Disconnect Alert will sound an audible warning approximateiy 2 seconds whenever the autopilot eng
177. ar during refuelling operations or in the vicinity of trucks or con tainers accommoding flammables or ex plosives do not allow personnel within 15 feet of area being scanned by antenna when system is transmitting ISSUED JANUARY 8 1981 REPORT VB 1110 of 6 9 95 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 14 PA 34 220T SENECA III 1 Flash bulbs can be exploded by radar energy 2 Since storm patterns are never stationary the display is con stantly changing and continued observation is always ad visable where areas of turbulence prevail NOTE RDR 160 pilot manual for detailed operating information and analysis of targets SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of the Pilot s Operating Handbook are necessary for this supplement REPORT 1110 ISSUED JANUARY 8 1981 9 96 6 of 6 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA HI SUPPLEMENT 15 PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO 15 FOR BENDIX RDR 160 1N 2026A COLOR WEATHER RADAR SYSTEM SECTION 1 GENERAL This supplement supplies information necessarv for the operation of the airplane when the optional Bendix RDR 160 1N 2026A Color Weather Radar System is installed in accordance with FAA Approved Piper data The information contained within this supplement is to be used in con junction with the complete hand
178. ases cooling The fan speed switch and the air conditioning ON OFF switch are above the temperature control The fan can be operated independently of the air conditioning however the fan must be ON for air conditioner operation Turning either switch OFF will disengage the compressor clutch and retract the condenser door Cooling air should be felt within one minute after the air conditioner is turned on NOTE 1 the system is not operating in 5 minutes turn the system OFF until the fault is corrected REPORT VB 1110 ISSUED JANUARY 8 1981 9 4 2046 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 3 The fan switch allows operation of the fan with the air conditioner turned OFF to aid in cabin air circulation LOW or HIGH can be selected to direct a flow of air through the air conditioner outlets in the over head duct These outlets can be adjusted or turned off individually The condenser door light is located on the annunciator panel and illuminates when the door is open and extinguishes when the door is closed A circuit breaker on the circuit breaker panel protects the aircraft electrical system SECTION 2 LIMITATIONS a To ensure maximum climb performance the air conditioner must be turned OFF manually prior to takeoff to disengage the compressor and retract the condenser door Also the air conditioner must be turned OFF manually before the landing approach in preparation for a po
179. at low altitude is not worth the risk assumed therefore it is recom mended 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 A power setting of 2200 RPM is recommended for simulated one engine operation ISSUED JANUARY 8 1981 REPORT VB 1110 10 3
180. atch front and rear doors ENGAGE LATCH BEFORE FLIGHT In fuil view of pilot WARNING TURN OFF STROBE LIGHTS WHEN TAXIING IN VICINITY OF OTHER AIRCRAFT OR DURING FLIGHT 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 att baggage closeout MAXIMUM BAGGAGE THIS COMPARTMENT 100 LBS NO HEAVY OBJECTS ON HAT SHELF In full view of pilot SINGLE ENGINE STALLS NOT RECOMMENDED CAN CAUSE 400 FT LOSS OF ALTITUDE AND 15 PITCH ANGLE REPORT VB 1110 ISSUED JANUARY 8 1981 2 10 PIPER AIRCRAFT CORPORATION SECTION 2 PA 34 220T SENECA LIMITATIONS enema e a a a ara AREA S a a T a i a ITI e a a it ae aaa Pita a PARANT S a a aa rM SP sun visor TAKEOFF CHECK LIST Fuel Selectors On Aux Fuel Pumps Off Alernators On Engine Gages Checked Mixtures Set Propellers Set LANDING CHECK LIST Seat Backs Erect Fasten Belts Harness Fuel Selectors On Cowl Flaps Set Mixtures Rich Aux Fue Pumps Off Propellers Set Gear Down Flap Set White Arc Conditioner Off Cow Flaps Open Seat Backs Erect Flaps Set Trim Set Stab amp Rudder Fasten Belts Harness Controls Free Full Travel Doors Latched Air Cond The Air Conditioner Off item in the above takeoff and landing check list is mandatory for air conditioned
181. ate counterclock wise Run manual electric trim from full nose up to full nose down Time required should be 39 5 seconds CAUTION Disengage the AP and check that the airplane manual pitch trim is in the takeoff position prior to takeoff ISSUED APRIL 21 1981 REPORT 1110 REVISED FEBRUARY 25 1982 9 of 16 9 41 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 5 PA 34 220T SENECA NOTE ff the autopilot circuit breaker is pulled the red TRIM failure light on the annunciator panel will be disabled and the audible warning will continuously sound indicating that the failure light is disabled In this event the Pitch Prim circuit breaker should be pulled and in flight trim accomplished by using the manual pitch trim wheel h IN FLIGHT OPERATION 1 Engage Procedure REPORT VB 1110 9 42 3 After takeoff clean up airplane and establish climb Monitor flight controls and engage AP The pitch attitude will lock on anv attitude up to 15 pitch attitude Engaging and holding the CWS switch allows the pilot to momentarily revert to manual control while retaining his previous modes and conveniently resuming that profile at this discretion Disengage Procedure While monitoring the flight controls disengage the system by one of the following methods depressing the pilot s AP DISC TRIM INTERRUPT switch operation of the manual trim switch or by the operation of the AP engage le
182. ate recovery actions must be taken To recover from an unintentional spin immediately retard the throttles to the idle position Apply full rudder opposite the direction of the spin rotation Let up all back pressure on the control wheel If the nose does not drop immediately push the control wheel full forward Keep the ailerons neutral Maintain the controls in these positions until spin rotation stops then neutralize the rudder Recovery from the resultant dive should be with smooth back pressure on the control wheel No abrupt control movement should be used during recovery from the dive as the positive limit maneu vering load factor be exceeded NOTE Federal Aviation Administration Regulations do not require spin demonstration of multi engine airplanes therefore spin tests have not been conducted The recovery technique presented is based on the best available information 3 28 EMERGENCY DESCENT In the event an emergency descent becomes necessary CLOSE the throttles and move the propeller controls full FORWARD Adjust the mixture controls as necessary to smooth operation Extend the landing gear at 130 KIAS and maintain this airspeed 3 34 COMBUSTION HEATER OVERHEAT In the event of an overheat condition the fuel air and ignition to the heater is automatically cut off Do not attempt to restart the heater until it has been inspected and the cause of the malfunction has been determined and corrected
183. ate the first engine started with alternator ON at maximum charging rate not to exceed 1500 RPM for 5 minutes minimum before initiating start on second engine NOTE When cold weather engine starts are made without the use of engine preheating refer to TCM Operator s Manual longer than normal elapsed time may be required before an oil pressure indication is observed REPORT VB 1110 ISSUED JANUARY 8 1981 4 18 REVISED FEBRUARY 25 1982 SECTION 4 NORMAL PROCEDURES PIPER AIRCRAFT CORPORATION 34 220 SENECA HI 44 ti pep SONOOS3S JWL AMBIENT TEMPERATURE VS AMBIENT TEMPERATURE Figure 4 3 OPTIONAL ENGINE PRIMER SYSTEM PRIMING TIME 4 19 REPORT VB 1110 ISSUED JANUARY 8 1981 REVISED AUGUST 17 1981 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES 34 220 SENECA arm e AP a I A P T a Ner rrr rr e Aree aaa 4 19 STARTING ENGINES WHEN FLOODED lf an engine is flooded move the mixture control to idle cut off and advance the throttle propeller controls full forward Turn ON the battery switch and ignition switches The auxiliary fuel pump should be OFF After ensuring that the propeller is clear engage the starter When the engine fires retard the throttle and advance the mixture slowiy 4 21 STARTING ENGINES IN COLD WEATHER AIRPLANE EQUIPPED WITH STANDARD ENGINE PRIMER SYSTEM NO
184. ave to maintain this control force while he manually retrims the airplane ISSUED APRIL 21 1981 REPORT VB 1110 50f16 9 23 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 4 PA 34 220T SENECA SECTION 4 NORMAL PROCEDURES a b c The BATTERY switch function 1s unchanged and can be used in an emergency to shut off all electrical power while the problem is isolated The RADIO POWER switch supplies power to the avionics bus bar of the radio circuit breakers AP and TRIM circuit breakers The KFC 200 is controlled by the following circuit breakers AUTOPILOT This suplies power to the FCS KC 295 Computer 290 Mode Controller KA 285 Annunciator Panel KI 256 FDI and AP Pitch and Roll Servos FCS MASTER This in conjunction with the radio power switch supplies power to the avionics bus COMPASS SYSTEM This supplies power to the KCS 55 Compass System PITCH TRIM This supplies power to the FCS Autotrim and manual electric trim systems FCS WARNING FLAGS AND ANNUNCIATORS The KI 256 Flight Director Indicator does not have a warning flag however the command bars will be biased out of view whenever the system is invalid or a FD mode is not engaged HDG This warning flag mounted in the Pictorial Navigation Indicator will be in view whenever the directional gyro information is invalid If a HDG invalid occurs with either NAV APPR or HDG modes selected the AP and or FD is disenga
185. be performed by turning the heated wind shield 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 type PITOT HEAT switch located on the instrument panel below the pilot s control wheel ICE DETECTION LIGHT SURFACE DEICER PROPELLER DEICER AND HEATED WINDSHIELD CONTROL SWITCHES Figure 9 3 ISSUED JANUARY 8 1981 REPORT 1110 REVISED AUGUST 17 1981 5 of 10 9 49 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 6 PA 34 220T SENECA pn M T The heated lift detectors one inboard and one outboard on the left wing are installed to prevent icing conditions from interfering with operation of the stall warning transmitters Stall Warn circuit breaker in the circuit breaker panel protects the system against an overvoltage condition The stall warning svstem should not be depended on when there is ice on the wing heated pitot head mounted under the left wing is installed to provide pitot pressure for the airspeed indicator with heat to alleviate ice accumu lation 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 With the heated pitot switch on check the heated pitot head and heated lift detecto
186. book This supplement has been FAA Approved and must remain in this handbook at all times when the optional Bendix RDR 160 N 2026A Color Weather Radar is installed Ls FAA APPROVED M WARD EVANS D O A NO 50 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED JANUARY 8 1981 REPORT VB 1110 1 of 6 9 97 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 15 _ 34 220 SENECA SECTION 2 LIMITATIONS Do not operate the radar during refueling operations or in the vicinity of trucks or containers accommodating flammables or explosives Do not allow personne within 15 feet of area being scanned by antenna when system is transmitting SECTION 3 EMERGENCY PROCEDURES No changes to the basic Emergency Procedures provided by Section 3 of this Pilot s Operating Handbook are necessary for this supplement SECTION 4 NORMAL PROCEDURES EQUIPMENT OPERATION AND CONTROLS 1 RDR 160 IN 2026A CONTROLS AND DISPLAYS Controls and displays for the RDR 160 IN 2026A Color Weather Radar System are listed in Table 4 3 with a functional description Location of the controls and displays is shown in Figure 4 All operating controls and displays are located on the indicator INDICATES TRACX INDICATES WHEN FUNCTION CURSOR FLASHES IN SELECTED SWITCH iS POSTION HOLD CONDMOR RANGE SELECTED SET TO TEST IN DEGREES SCREEN BRIGHTNESS RADAR RECEIVER GAIN CONTROL CONTRO
187. 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 is being used for training purposes or a 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 ISSUED JANUARY 8 1981 REPORT VB 1110 7 7 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA RCM T ID LANDING G AR HYDRAULIC CONTROL amp PUMP WARNING 8 a r RSE SQUAT SWITCH TERMINAL 3 FLIGHT 1 POS RIGHT lad GEAR i N O DOWN pi Limit Lg sw TERMINAL 2702 zd W ue bu crat tees H NG CO i 21 i H i Pa i 1 i i i H ep EN Lert NOSE RIGHT 2 GREEN GREEN 5 PRESSURE X TERMINAL 6 i atk fuent 2 SwITOM PS Zo i t i NT i 5 i i py TERMINAL 4 TOS P TERMINAL 8 i T M li
188. c stall buffet or stall warning horn immediately initiate recovery reduce power to on the operative engine and immediately lower the nose to regain Vssr One engine inoperative stalls are not recom mended Under no circumstances should an attempt be made to fly at a speed below V MC with only one engine operating ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED FEBRUARY 25 1982 4 37 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA 34 220T SENECA e a m aai e i a aAa e ee a rrr rri at art s e m T A mmm 4 59 STALLS The loss of altitude during a power off stall with the gear and flaps retracted may be as much as 400 feet The loss of altitude withthe gear down and 40 of flaps may also be as much as 400 feet power on stall may result in as much as 150 feet of altitude loss The stall warning system is inoperative with the battery switch OFF REPORT VB 1110 ISSUED AUGUST 17 1981 4 38 TABLE OF CONTENTS SECTION 5 PERFORMANCE Paragraph Page No 5 1 General rereh eee se alee oes ew dew kOe 5 1 5 3 Introduction Performance and Flight Planning 5 5 5 Flight Planning Example 5 3 5 7 Performance Graphs 5 9 Figures 0254 ies 5 9 REPORT 1110 5 PIPER AIRCRAFT CORPORATION SECTION 5 PA 34 220T SENECA PERFORMANCE SECTION 5 PERFORMANCE 5 1 GENERAL This sect
189. cessible through a plate on the right side of the fuselage This plate is attached with slotted head nylon screws for ease of removal these screws may be readily removed with a variety of common items such as a dime knife blade ctc M there are no tools available in an emergency the screw heads may be broken off by any means The ELT is emergency locator transmitter which meets the requirements of FAR 91 52 On the ELT unit itself is a three position switch placarded OFF and ARM The ARM position sets the ELT so that it will transmit after impact and will continue to transmit until its battery is drained The ARM position is selected when the ELT is installed in the airplane and it should remain in that position After a forced landing and assistance is desired verifv the operation of the ELT by tuning radio receiver to 121 50 MHz Ifthe EL T transmission can be heard it is functioning properly If there is no ELT transmission remove the ELT access plate in the tail cone and place the ELT selector switch in the ON position After verification that the ELT is transmitting turn off monitoring receiver to conserve the battery If radio communication is attempted place the ELT selector switch in the OFF position until the communication is completed Optional equipment ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED FEBRUARY 25 1982 7 37 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34
190. ction with the complete handbook This supplement has been FAA Approved and must remain in this handbook at all times when the optional Bendix RDR 160 Monochrome Weather Radar System is installed WARD EVANS D O A NO 50 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ETE FAA APPROVED c 05 amp Ec ISSUED JANUARY 8 1981 REPORT VB 1110 1 of 6 9 9 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 14 PA 34 220T SENECA i lh A DM MEE SECTION 2 LIMITATIONS Do not operate the radar during refueling operations or in the vicinity of trucks or containers accommodating flammables or explosives Do not allow personnel within 15 feet of area being scanned by antenna when system is transmitting SECTION 3 EMERGENCY PROCEDURES No changes to the basic Emergency Procedures provided by Section 3 of this Pilot s Operating Handbook are necessary for this supplement SECTION 4 NORMAL PROCEDURES a SYSTEM CONTROLS Table 4 3 lists and describes the system controls all of which are mounted on the panel of the radar indicator Figure 4 1 illustrates the location of these controls Table 4 5 lists the alphanumeric read outs of range range marks and mode selection as a function of switch position ALPHANUMERIC QW SCREEN READOUT ES RANGE MARK SELECTED HOLD SELECTED MODE SPACING N M RANGE N M PUSHSUTTOR RANGE SELECTOR MODE SELECTOR GAIN CONTROL THY CONTROL BRIGHTNESS
191. cy Procedures provided by Section 3 of this Pilot s Operating Handbook are necessary for this supplement SECTION 4 NORMAL PROCEDURES EQUIPMENT OPERATION AND CONTROLS 1 RDR 160XD IN 232A CONTROLS AND DISPLAYS Controls and displays for the RDR 160X D IN 232A Weather Radar System are listed in Table 4 3 with a functional description Location of the controls and displays is shown in Figure 4 1 All operating controls and displays are located on the indicator TRACK FLASHES IN INDICATES INDICATES CURSOR jene AD erto RANGE WHEN FUNCTION POSITION CONDITION MODE SELECTEO SWITCH TS IN DEGREES SET TEST SCREEN S BRIGHTNESS RADAR RECEIVER CONTROL GAIN CONTROL TRACK CUASOR BUTTON POSITIONED PRESS TO RETAIN DISPLAY RANGE MARK BOME PRESS INCREASE RANGE PRESS TO SELECT WEATHER MODE PRESS TO SELECT WEATHER ALERT i MODE PRESS TO SELECT GROUND MAPPING MODE PRESS TO DECREASE RANGE INDICATES ai BUTTON PRESSED BUT NAV OPTION CORNECTED ANTENNA CONTROL FUNCTION SWITCH LOCKING LEFT q RIGHT USED ONLY WITH USED ONLY WITH PRESS TO MOVE OPTIONAL EQUIPMENT OPTIONAL EQUIPMENT TRACK CURSOR IDISPLAYS UP TO TEN PILOT NAV PLUS WEATHER PROGRAMMED WAYPOINTS IN 232A CONTROLS AND DISPLAYS Figure 4 1 REPORT VB 1110 ISSUED FEBRUARY 25 1982 9 126 2 of 6 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT
192. d be drained before the first flight of the day and after re fueling to check for fuel contamination If contamination is found fuel should be drained until the contamination stops contami nation 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 The fuel drained at each quick drain should be collected in a transparent container and examined for contamination CAUTION When draining fuel be sure that no fire hazard exists before starting the engines e Draining Fuel System The bulk of the fuel may be drained either by opening the valve at the inboard end of each tank or by siphoning The remaining fuel in the lines may be drained through the gascolators and the two drains located on the bottom of the fuselage inboard of the right flap 823 TIRE INFLATION For maximum service from the tires keep them inflated to the proper pressures The main gear t res should be inflated to 55 psi and the nose gear tire should be inflated to 40 psi Interchange the tires on the main wheels if necessary to produce even wear All wheels and tires are balanced before original installation and the relationship of the tire tube and wheel should
193. d seating arrangement In the ciub seating arrangement it utilizes the same attach points as the refreshment console _ An optional cabin work table serving the two seats on the right side of the passenger cabin is offered to the club seating arrangement The table must be stowed during takeoff and landing if the table is to be used it should be set up after a level cruise is established REPORT VB 1110 ISSUED JANUARY 8 1981 7 34 REVISED AUGUST 9 1982 PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA DESCRIPTION amp OPERATION To remove the cabin work table from the aft baggage compartment unlock the stud located on the bottom of the close out bulkhead Loosen the white tie down strap and remove the table from the mounting brackets by lifting the table two inches straight up until it clears the mounting brackets Do not twist the table while it is in the brackets To install the cabin work table during flight hold the table in place and tilt the free end of the table upward 30 until the lobed upper knobs on the table supports align with the top holes of the escutcheons located below the right cabin window trim Hold the upper lobes in place and lower the free end of the table to the level work position The retaining springs will click when secure To stow the cabin work table remove the table by lifting the free end of the table upward to disengage the bottom lobes of the table supports Lift until the top support
194. door light is located on the annunciator panel and illu minates when the door is open and extinguishes when the door is closed SECTION 5 PERFORMANCE Operation of the air conditioner will cause slight decreases in cruise speed and range Power from the engine is required to run the compressor and the condenser door when extended causes a slight increase in drag When the air conditioner is turned OFF there is normally no measurable difference in climb cruise or range performance of the airplane NOTE To ensure maximum climb performance the air conditioner must be turned OFF manually before takeoff to disengage the compressor and retract the condenser door Also the air conditioner must be turned OFF manually before the landing approach in preparation for a possible go around The air conditioner must be OFF during all one engine inoperative operations REPORT VB 1110 ISSUED JANUARY 8 1981 9 16 4016 REVISED FEBRUARY 25 1982 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA HI SUPPLEMENT 3 SER Although the cruise speed and range are only slightly affected by the air conditioner operation these changes should be considered in preflight planning To be conservative the following figures assume that the com pressor is operating continuously while the airplane is airborne This will be the case only in extremely hot weather a The decrease in true airspeed is approximately 4
195. e However this svstem does provide a separate primer system as an integral part of the engine fuel svstem An electrically operated diverter valve is located in the metered fuel supply line between the air throttle valve and the manifold valve Other components are two primer nozzles located in the intake mani fold on each side of the engine and the interconnecting fuel lines Actuation of the engine primer switch operates the auxiliary electric fuel pump on H1 and energizes the diverter valve which supplies fuel to each primer nozzle The diverter valve does not shut off fuel fiow to the manifold valve there fore some quantity of fuel is also supplied to each cvlinder nozzle during priming Normal operation of the auxiliary fuel pump is unchanged Fuel management controls are located on the console between the front seats There is a control lever for each of the engines and each is placarded ON OFF X FEED During normal operation the levers are in the ON position and each engine draws fuel from the tanks on the same side as the engine The two fuel systems are interconnected crossfeed lines When the X FEED position is selected the engine will draw fuel from the tanks on the opposite side in order to extend range and keep fuel weight balanced during single engine operation The OFF position shuts off the fuel flow from a side NOTE When one engine is inoperative and the fuel selector for the operating engine is on X FEED the
196. e Center or by a qualified aircraft and power plant mechanic who owns or works for a reputable repair shop The inspection is listed in detail in the inspection report of the appropriate Service Manual An annua inspection is required once a year to keep the Airworthiness Certificate in effect It is the same as a 100 hour inspection except that it must be signed by an Inspection Authorized IA mechanic or a General Aviation District Office representative This inspection is required whether the aircraft is operated commercially or for pleasure REPORT VB 1110 ISSUED JANUARY 8 1981 8 2 REVISED SEPTEMBER 23 1983 PIPER AIRCRAFT CORPURALION SEC IIUN GG PA 34 220T SENECA HANDLING SERV amp MAINT a A Progressive Maintenance program is approved by the FAA and is available to the owner involves routine and detailed inspections at SO0 hour intervals The purpose of the program is to allow maximum utilization of the aircraft to reduce maintenance inspection cost and maintain a maximum standard of continuous airworthiness Complete details are available from Piper dealers spectographic analysis of the oil is available from several sources This svstem if used intelligently provides a good check of the internal condition of the engine For this system to be accurate oil samples must be sent in at regular intervals and induction air filters must be cleaned or changed regularly
197. e Hold AP Autopilot APPR Approach ARM System Arm for Capture BC Back Course CDI Course Deviation Indicator or Control CPLD Coupled CWS Control Wheel Steering DISC Disconnect FCS Flight Control System GS Glide Slope HDG Heading Select LOC L ocalizer NAV Navigation PAH Pitch Attitude Hold PNI Pictorial Navigation Indicator ISSUED APRIL 21 1981 REPORT VB 1110 REVISED FEBRUARY 25 1982 9 34 20416 PIPER AIRCRAFT CORPORATION SECTION 9 34 220 SENECA SUPPLEMENT 5 SECTION 2 LIMITATIONS a During autopilot operation pilot must be seated at the controls with seat belt fastened Operation is restricted to left side pilot position b Maximum speed for autopilot operation is 173 KIAS c The maximum altitude for operation of the autopilot has not been determined The maximum altitude flight tested was 24 000 feet d Do not extend flaps beyond 25 during autopilot operation e The autopilot must be disengaged during takeoff and landing f System approved for Category operation only APPR or BC Mode selected g Autopilot attitude command limits Pitch FD Roll 425 NOTE In accordance with FAA recommendations use of Altitude Hold mode is not recom mended during operation in severe turbulence Placards Location Pilot s control wheel left horn AP TRIM DISC INTERRUPT Pilot s control wheel left horn CWS Pi
198. e airport 21 Cruise alt 16500 ft Cruise 13 C Fuel to climb 12 1 11 gal Time to climb 15 2 13 min Distance to climb 2T s 24 m H 1 20 80 OUTSIDE AIR TEMPERATURE TIME DISTANCE amp FUEL TO CLIMB NOLLOTS NOLLVHOdHOO LIVNONIV Aidid HI LOZC FE Vd SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION 34 220 SENECA ISIN Ut d VIA jou OC puepuzis JoY YJB 10 75 piepuvis 240q 5 9 Youd 20j Hj ppe juvisuos mmut 00052 H O d 229 UPIS H O d 229 000vC 425261 400591 00022 00004 ASE 0008 vig Epe 050 652 00091 m L 6c TS 192 PL 00071 St 8 62 L Ot 815 Ore EST 9 CLE 586 90001 61 0 0 Ot 6 0t oct Lee 850 9C ELT vw 0000 Per 0715 OS LSC 890 Li VC 0008 C 6t ptt tor Tit tSc 290 OLE 0 886 0009 oor Sie 8 950 990 CRE 000 092 890 HiT YRC 16 9002 CLC TRT por TS 009 0055 0092 9052 0025 0092 0052 OORT OOLC 007 0012 0092 0052 0055 0000 0012 1994 NVA 55434 NVIN ONY NYIA NVA GNV UV
199. e and computed and safe PREFLIGHT CHECK INSIDE CABIN Landing gear 1 DOWN position AVIOMCS Su iud round Rp d be e dol OFF ISSUED JANUARY 8 i581 REPORT 1110 4 3 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA 34 220T SENECA IH reete e aa aa RAPERE RI i a IR S a a Pa ar I T e t P sva Pear rna inerat RAR rr i aaa a enira m A H Battery switch i oec e nes nud TTE OTT Landing gear 8 p EU Edd er PE 3 GREEN Fuel adequate plus reserve flaps Battery esee MORD han dpt ERRARE OFF Ignition switches X Bau Ars iol ehe vo OFF Mixture controls Va d laci Se Wig ope ah Gy V3 dedu ddie cut off Trim indicators We Pods Vadis totas Contedls Ea is dein era eng Pitot and static systems mn se Ead Vo Empty seats fasten belts Crossfeed drains Trav D ED PRORA Grain OUTSIDE CABIN Crossfeed drains cu aed soc a oe B Rande e lake ves Check closed Right wing aileron and eee daa ee es Check ice Right main gear decease mese
200. e as determined in accordance with Federal Aviation Regu lations Airplane certification conditions include one engine becoming inoperative and windmilling not more than a 5 bank towards the operative engine takeoff power on operative engine landing gear up flaps in takeoff position and most rearward C G Never Exceed Speed or Mach Number is the speed limit that may not be exceeded at any time Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution Stalling Speed or the minimum steady flight speed at which the airplane is con irollable Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration Intentional One Engine Inoperative Speed is minimum speed selected by the manu facturer for intentionally rendering one engine inoperative in flight for pilot training REPORT VB 1110 1 7 SECTION 1 GENER AI PIPER AIRCRAFT CORPORATION PA 34 220T SENECA HI Best Angie of Climb Speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance Best Rate of Climb Speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time b Meteorological Terminology ISA OAT Indicated Pressure Altitude Pressure Altitude Station Pressure REPORT VB 1110 1 8 International Standard Atmosphere in
201. e autopilot is engaged For approaches without glide path coupling adjust pitch attitude in conjunction with power to maintain desired airspeed and descent rate NOTE Flight director or autopilot will not decouple from the GS or localizer in the event of radio failure however warnings will flash in the mode appropriate to the failure Monitor course guidance raw data during the approach to assure signal quality REPORT VB 1110 ISSUED APRIL 21 1981 9 122 10 0112 _ PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 18 a M PP PAVE 3 Instrument Approach Go Around Maneuver Flight Director Version Only a b 6 Select G mode at the remote G switch Autopilot will disconnect and warning horn will sound Add takeoff power or power as desired Check the correct attitude and that a positive rate of climb is indicated then raise gear and flaps Pilot may hand fly aircraft with reference to flight director steering information After aircraft 15 established in climb gear and flaps up autopilot may be re engaged by pushing ON button on console if flight director steering is switched on Set desired HDG and select HDG mode for lateral maneuvering SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of this Pilot s Operating Handbook are necessary for this supplement ISSUED APRIL 21
202. e frequency stored for the active waypoint The stored inbound course will be displayed in the CRS window for 30 seconds to allow the CRS control OBS on the IN 831 HSI to be set to that course After the waypoint has been passed the CRS XFR key can be pressed to recall the outbound course which will appear for 30 seconds to allow the CRS to be reset The course pointer on the 11 881 HSI will automatically reset to the display course provided its function switch is in the HSI position With the mode selector set to VOR LOC the following data 15 displayed 1 DISPLAY SELECTOR SET TO BRG DST Bearing and distance to the selected VOR DME station are displayed 2 DISPLAY SELECTOR SET TOKTS TTS Ground speed in knots and time to station are displayed in minutes 3 The HSI presents unprocessed information with conven tional angular sensitivity 1 full scale deviation equals 10 off course 4 DISPLAY SELECTOR SET TO SBY Data stored for stand by waypoint number appearing in SBY window is displayed and can be altered as desired 5 DISPLAY SELECTOR SET TO ACT Data stored for active waypoint number in ACT display window is displayed but cannot be altered REPORT VB 1110 _ ISSUED JANUARY 1981 9 62 4 of 6 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 8 m With the mode selector set to the following data is dis n played 1 DISPLAY SELE
203. e signal quality Since GS arm and capture are automatic when the arming and capture sequence is met the GS must be locked out for holding operations on the localizer at the L O M When localizer holding is desired localizer tracking must be performed in mode which will offer the same tracking dynamics as APR mode but will inhibit GS arm and capture When APR clearance Is received select APR mode for completion of the approach 2 Selected Angle intercepts If an 5 1 type heading system is installed selected angle intercepts may be made during VOR or localizer intercept situations by selecting HDG and APR HDG and REV simultaneously as appropriate During a selected angie intercept operation the autopilot will follow the heading bug until reaching the computed On Course Turn Point at which time capture is indicated by extinguishing of the HDG mode annunciator Selected angle intercepts of over 60 are not recommended ISSUED FEBRUARY 10 1984 REPORT 1110 13 of 20 9 147 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 21 PA 34 220T SENECA HI 3 4 5 if radio information becomes invalid Flag after initiation of a selected angle intercept the applicable navigation mode annunciator will flash and the autopilot will remain in HDG mode The automatic mode shift to the invalid radio mode will not occur CWS Mode The system is equipped with a control w
204. e the engines 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 REPORT 1110 ISSUED JANUARY 8 1981 4 24 PIPER AIRCRAFT CORPORATION SECTION 4 34 220 SENECA NORMAL PROCEDURES irem a aiii A a a a ane REA e e a aai e I a At ai ary tantae 4 29 TAXIING Remove chocks from the wheels Release the parking brake by first depressing and holding the toe brake pedals and then pushing on the parking brake knob Check to make sure the taxiarea is clear Always apply the throttles Before taxiing the brakes should be checked by moving forward a few feet throttling back and applying pressure on the toc pedals As much as possible turns during taxiing should be made using rudder pedal motion and differentia power more power on the engine on the outside of the turn less on the inside engine rather than brakes During the taxi check the instruments turn indicator directional gyro courdination ball compass and the heater and defroster Check the operation of the management controls by moving cach fuel selector to CROSSFEED tora short time while the other selector is inthe ON position Return the selectors to the ON position DO NOT attempt a takeoff with the fuel selector on CROSSEEED The autopilot if installed should be off during taxi 431 BEFORE TAKEOFF GROUND CHECK thorough check shou
205. econds after turning the switch to OFF The combustion heater uses fuel from the airplane fuel system An electric fuel pump draws fuel from the left tank at a rate of approximately one half gallon per hour Fuel used for heater operation should be con sidered when planning for a flight 7 237 CABIN FEATURES The front seats are adjustable fore and aft Fach seat recipes and is provided with an armrest The center and rear seats are easily removed to provide additional cargo space NOTE To remove the center seats retainers securing the back legs of the seats must be unlocked Re leasing the retainers is accomplished by de pressing the plunger behind each rear leg Any time the seats are installed in the airplane the retainers should be in the locked position To remove the rear seats depress the plunger behind each front leg and slide seat to rear ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED SEPTEMBER 23 1983 7 33 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA HI An optional jump seat which can be mounted between the two center seats gives the Seneca 11 seven place capabilities Shoulder harnesses with inertia reels are standard equipment for the front seats and are offered as optional equipment for the third fourth fifth and sixth seats but not for the seventh seat The inertia reel should be checked by tugging sharply the strap The reel will lock in place under t
206. ection of this handbook REPORT VB 1110 ISSUED JANUARY 8 1981 4 28 REVISED FEBRUARY 10 1984 PIPER AIRCRAFT CORPORATION SECTION 4 PA 34 220T SENECA NORMAL PROCEDURES 4 35 CLIMB On climb out after takeoff it is recommended that the best angle of climb speed 76 KIAS be maintained only if obstacle clearance is a consid eration The best rate of climb speed 92 K IAS should be maintained with takeoff power on the engines until adequate terrain clearance is obtained At this point engine power should be reduced to approximately 75 power for cruise climb A cruise climb speed of 102 KIAS or higher is also recom mended This combination of reduced power and increased climb speed provides better engine cooling less engine wear reduced fuel consumption lower cabin noise level and better forward visibility When reducing engine power the throttles should be retarded first followed by the propeller controls The mixture controls should remain at full rich during the climb Cowl flaps should be adjusted to maintain cylinder head and oil temperatures within the normal ranges specified for the engine During climbs under hot weather conditions it may be necessary to use LO auxiliary fuel pump for vapor suppression Consistent operational use of cruise climb power settings is strongly recommended since this practice will make a substantial contribution to fue economy and increased engine life and will reduce the incidence of pre
207. ed 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 ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 17 1981 4 35 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA 34 2201 SENECA 4 55 Vsse INTENTIONAL ONE ENGINE INOPERATIVE SPEED Vase is a speed selected by the aircraft manufacturer as a training aid for pilot s in the handling of multi engine aircraft It is the minimum speed for intentionally rendering one engine inoperative in flight This minimum speed provides the margin the manufacturer recommends for use when intentionally performing engine inoperative maneuvers during training in the particular airplane The intentional one engine inoperative speed Vsst for the Seneca is 85 KIAS 4 57 Vaca MINIMUM SINGLE ENGINE CONTROL SPEED Vaca is airspeed below which a twin engine aircraft cannot be con trolled in flight with one engine operating at takeoff power and the other engine windmilling Vaca for the Seneca Hi has been determined to be 66 KIAS Under no circumstances should an attempt be made to fly at a speed below this VMCA with only one engine operating As a safety precaution when operating under single engine flight conditions either in training or in emergency situations maintain an indicated airspeed above 85 KIAS Vsse The Vaca demonstration required for the FAA flight test for the
208. ed by the additive manufacturer should be used Except for the information contained in this section the manufacturer s mixing or blending instructions should be carefully followed CAUTIONS Some fuels have anti icing additives blended in the fuel at the refinery so no further blending should be performed Fuel additive can not be used asa substitute for preflight draining of the fuel system REPORT VB 1110 ISSUED JANUARY 8 1981 8 12 PIPER AIRCRAFT CORPORATION SECTION 8 PA 34 220T SENECA HANDLING SERV amp MAINT FUEL DRAIN Figure 8 3 CAUTION Assure that the additive is directed into the flowing fuel stream The additive flow should start after and stop before the fuel flow Do not permit the concentrated additive to come in contact with the aircraft painted surfaces orthe interior surfaces of the fuel tanks c 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 With optional fuel tanks installed the total fuel capacity is increased to 128 gallons ISSUED JANUARY 8 1981 REPORT VB 1110 8 13 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING SERV amp MAINT PA 34 220T SENECA BEENDEN AA d Draining Fuel Strainer Sumps and Lines Each gascolator strainer is provided with a quick drain which shoul
209. ed in level flight only ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED APRIL 9 1982 3 17 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA 34 220T SENECA RRR CRUISING When using fuel from the fuel tank on the same side as the operating engine the fuel selector of the operating engine should be ON and the fuel selector for the inoperative engine should be OFF The AUX fuel pumps should be OFF except in the case of an engine driven fuel pump failure If an engine driven fuel pump has failed the AUX fuel pump on the operating engine side must be ON HI Increased range is available by using fuel from the tank on the opposite side of the operating engine For this configuration the fuel selector of the operating engine should be on X FEED crossfeed and the fuel selector of the inoperative engine should be OFF The AUX fuel pumps should be OFF NOTE A vapor return line from each engine will return a percentage of fuel back to the tank on the same side as that engine Therefore minimum of 30 minutes of fuel should be used from this tank before selecting crossfeed If the tank gauge approaches FULL go back to that tank and operate for 30 minutes to bring the fuel level down before returning to crossfeed or fuel may be pumped overboard through the fuel vent LANDING During the landing sequence the fuel selector of the operating engi
210. ees 3 Emergency Procedures Checklist oe eee Airspeeds for Safe Engine Inoperative Procedures Ji cM RM NCC prs cd Fuel Management During Engine noperative Operation prir eer ra Gara od Vioc fara Engine Driven Fuel Pump Failure Landing Gear Unsafe Warnings Manual Extension of Landing Gear Up Engine Failure With Rear Cabin and Cargo Doors Removed Rx aw Electrical ES oria ane Gyro Suction SPINS news Emergency Descent aio oC seer eher RO ee EGER Combustion Heater Overheat Open Door Entry Door Propeller OVerspecu 2423 eek e sedes d 5 Amplified Emergency Procedures General 7 Engine Inoperative Procedures Detecting Dead Engine Securing Procedure Procedure Engine Failure During Takeoff Below 85 KIAS Engine Failure During Takeoff 85 KIAS or Above Engine Failure During Flight Below 66 KIAS One Engine Inoperative One Engine Inoperative Go Around Air Start Unfeathering Procedure 3 3 Page No EE
211. efore taking it out to the airplane If difficulty is encountered with the water freezing on boots direct a blast of warm air along the region being cleaned using a portable ground heater As an alternate cleaning solvent use benzol or nonleaded gasoline Moisten the cleaning cloth in the solvent scrub lightly and then with a clean dry cloth wipe dry so that the cleaner does not have time to soak into the rubber Petroleum products such as these are injurious to rubber and therefore should be used sparingly if at all With the deicer boots properly cleaned a coating of Agemaster No should be applied as described in the PA 34 220T Service Manual This treatment helps protect the boot rubber from ozone attack aging and weathering After the Agemaster coating is dry a coating of B F Goodrich Icex may be applied to the boots if icing conditions are anticipated For specific instructions refer to the PA 34 220T Service Manual Optional equipment ISSUED JANUARY 8 1981 REPORT 1110 REVISED SEPTEMBER 23 1983 8 19 SECTION 8 _ PIPER AIRCRAFT CORPORATION HANDLING SERV amp MAINT PA 34 220T SENECA NI 8 33 WINTERIZATION For winter operation a winterization kit is installed on the inlet opening of the oil cooler outboard chamber of the plenum chamber This kit should be installed whenever the ambient temperature is 50 F or less When the kit is not being used it can be stowed in the nose cone compartment left
212. egrees below the horizontal position The horizontal posi tion is indicated as zero degrees on the control When pressed a yellow track cursor line ap pears and moves to the right in one degree steps while the button is held depressed The track cursor stops when the button is released and remains for about 10 to 15 seconds then disappears unless the button 15 pressed again The differential heading will be indicated in yellow numerals in the upper left corner of the display and disappears simultaneously with the track cursor CONTROL DISPLAY FUNCTIONS Table 4 3 ISSUED JANUARY 8 1981 REPORT VB 1110 3 of 6 9 99 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 15 PA 34 220T SENECA ee CONTROL DISPLAY FUNCTION TRACK When pressed the yellow track cursor appears button and moves to the left while held depressed Operation is as explained above GAIN control Varies the radar receiver gain when in the MAP mode Gain and the STC are preset in TEST function and in the WX and WXA modes BRT contro Adjusts brightness of the display for varying cockpit light conditions MODE Pressing momentarily produces an informa button tion list on the display Pressing again while information display is still present advances the indicator display to the next higher mode shown on the list The list disappears after a f
213. en oe CREE A Ee d s ES reduce Avoid further icing conditions if possible Land as soon as practical Maintain at least 89 KIAS on final Do not extend gear or lower flaps until certain of making field ope x CU ar RUE CO ed an aka cR d 237 ALTERNATOR FAILURE IN ICING CONDITIONS Alternator amp witcleso o duck acit ICE Va act SCR ERA OFF then ON Circuit Brea check and reset unable to restore aiternator AVIONICS boosie all off except Nav Comm I and Transp Electric windshield OFF to maintain 65A load icing continues terminate flight as soon as practical Prior to landing Electric windshield aeo qe edt de ON if necessary Gear may require free fal extension WING TAIL DEICER PANEL LIGHT If light is illuminated more than 20 seconds pull surface deice circuit breaker ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 17 1981 7 0410 9 51 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 6 PA 34 220T SENECA HI OOOO Trt ee Tian te taco ee ey SECTION 4 NORMAL PROCEDURES 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 has been substantiated however there is
214. ended intercept angle 90 Select desired radial and engage The FCS will remain on HDG as indicated on the annunciator panel and in AR M on the NAV mode When the airplane approaches the beam the system will automatically couple HDG will decouple and track in NAV mode and indicate CPLD on the annunciator panel A new course may be selected over the VOR station when operating in the NAV mode by selecting a new radial when the To From indication changes For VOR approach see approach procedure APPROACH PROCEDURES 1 2 3 4 5 6 Tune ILS or VOR Set CDI for front course Set Heading Bugand engage AP and to intercept selected CDI course beam at desired angle Maximum recommended intercept angle 90 Engage APPR and note APPR ARM on the annunciator When airplane approaches the selected CDI course APPR will couple HDG will decouple the AP will track LOC or VOR and CPLD will illuminate on the annunciator panel When the glide slope beam is intercepted the glide slope GS will couple automatically and indicates GS on the annunciator panel If the ALT mode was engaged prior to intercepting the glide slope it will automatically disengage when GS couples The AP will now track LOC and GS Adjust throttles to control speed on descent Set HDG bug for missed approach but do not engage HDG When middle marker signal is received system will auto matically switch to a more stable track
215. ented line locates the total load and the C G position of the airplane for takeoff 1f this point is not within the allowable envelope it will be necessary to remove fuel baggage or passengers and or to rearrange baggage and passengers to get the final point to fall within the envelope Fuel burn off and gear movement do not significantly affect the center of gravity ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 9 1982 6 15 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 34 220T SENECA SAMPLE PROBLEM A sample problem will demonstrate the use of the weight and balance plotter Assume a basic weight and C G location of 2850 pounds at 83 5 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 a Place a dot on the plotter grid at 2850 pounds and 83 5 inches to represent the basic airplane See illustration b Slide the slotted plastic into position so that the dot is under the slot for the forward seats at zero weight c Draw a line
216. erated within the limitations herein specified This supplement has been FAA Approved based on EDO Avionics STC SA3422SW D and must remain in this handbook at all umes when the optional EDO Avionics Command Electric Trim System Model AK923 is instalied FAA APPROVED ees WARD EVANS D O A 50 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED SEPTEMBER 23 1983 REPORT 1110 1014 9 131 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 20 PA 34 220T SENECA SECTION 2 LIMITATIONS Placards In full view of pilot CONDUCT TRIM CHECK PRIOR TO FLIGHT SECTION 3 EMERGENCY PROCEDURES AUTOPILOT MALFUNCTION 1 Overpower control wheel forces initially and depress and hold the master interrupt switch on the control wheel This will stop all trim action 2 Retrim aircraft with manual trim system to alleviate control force 3 Move the trim master switch to the OFF position 4 Release interrupt switch while observing trim whee to assure that the trim system is disabled 5 Pull trim circuit breaker Leave circuit breaker open until the trim system is corrected SECTION 4 NORMAL PROCEDURES a PRE FLIGHT INSPECTION BEFORE EACH FLIGHT 1 Circuit breaker IN 2 master switch ON 3 Depress switch center bar and rock switch fore down and aft up check that trim operates in correct direction both Up and Down 4 Release trim switch Depress only
217. erence between takeoff weight or ramp weight if applicable and basicempty weight Maximum weight approved for ground maneuver 1t includes weight of start taxi and run up fuel Maximum weight approved for the start of the takeoff run Maximum weight approved for the landing touchdown Maximum weight exclusive of usable fuel REPORT VB 1110 TABLE OF CONTENTS SECTION 2 LIMITATIONS Paragraph Page No No 2 1 General xv We Ee cae 2 2 3 Airspeed Limitations secs eser eee eee rrt cee 2 2 5 Airspeed Indicator 2 2 2 7 Power Plant Limitations bois Waren es 2 3 2 9 Power Plant Instrument Markings 2 5 2 11 Weight Limits s Dea parus ces OF 2 6 3 13 Center of Gravity Limit amp cuve o res 2 6 2 15 Maneuver 2 7 2 12 Flight Maneuvering Load Factors docu tA 2 7 2 19 Types of Operation iun 2 7 2 21 Fuel diede 2 7 2a NOISE LOVE i kek RE dul esu dope patus 2 8 2 25 Heater cca eser Wa er res 2 8 227 Operating Altitude Limitations 2 8 2 29 Gyro Suction Limits PET 2 8 2 3 Operation with Aft Doors Removed 2 8 2 33 ERs CEL os ac E eB Dae b 2 9 REPORT 1110 24 PIPER AIRCRAFT CORPORATION SECTION 2 PA 34 220T SENECA LIMITATIONS
218. es a metering system which measures the rate at which turbocharged air 15 being used by the engine and dispenses fuel to the cylinders proportionally Fuel is supplied to the injector pump at a greater rate than the engine requires The excess fuel is returned to the fuel tank by the vapor return line The fuel injection system is a continuous flow type To obtain maximum efficiencv and time between overhauls from the engines follow the procedures recommended in the Teledyne Continental Operator s Manual provided with the airplane Engine controls consist of a throttle a propeller control and a mixture control lever for each engine These controls are located on the control quadrant on the lower center of the instrument panel where thev are accessible to both the pilot and the copilot The controls utilize teflon lined control cables to reduce friction and binding The throttle levers are used to adjust the manifold pressure They incorporate a gear up warning born switch which is activated during the last portion of travel of the throttle levers to the low power position the landing gear is not locked down the horn will sound until the gear is down and locked or until the power setting is increased This is a safety feature to warn the pilot of an inadvertent gear up landing All throttle operations should be made with a smooth not too rapid movement to prevent unnecessary engine wear or damage to the engines and to allow time for the
219. eservoir is through a panel in the nose baggage compartment For filling instructions see the PA 34 220T Service Manual The nose gear is stcerable through 27 degree arc either side of center by use of a combination of full rudder pedaltravel and brakes A gear centering spring incorporated in the nose gear steering system prevents shimmy tendencies bungee assembly reduces ground steering effort and dampens shocks and bumps during taxiing When the gear is retracted the nose wheel centers as it enters the whecl well and the stcering linkage disengages to reduce pedal loads in flight The landing light turns off automatically when the gear is retracted All three landing gears carry 6 00 x 6 tires The nose wheel has a 6 ply tire and the main wheels have amp ply tires For information on servicing the tires see Tire Inflation in the Handling and Servicing Section of this handbook Struts for the landing gear are air oil assemblies Strut exposure should be checked during each preflight inspection need for service or adjust ment is indicated refer to the instructions printed on the units Should more detailed landing gear service information be required refer to the P A 34 220T Service Manual 7 11 BRAKE SYSTEM Two single disc double puck brake assemblies one on each main gear are actuated by toe brake pedals mounted on both the pilots and the copilot s rudder pedals A brake system hydraulic reservoir independe
220. estart turn OFF the AUX fuel pump reduce the power until the engine is warm and turn the alternator switch ON required the starter may be used in conjunction with the unfeathering accumulators 3 9 FIRE ENGINE FIRE THE GROUND The first attempt to extinguish the fire is to try to draw the tire back into the engine If the engine has not started move the mixture control to idle cut off and open the throttle Begin to crank the engine with the starter in an attempt to pull the fire into the engine H the engine has already started and is running continue operating to to pull the fire into the engine In either case above if the fire continues longer than a few seconds the fire should be extinguished by the best available external means If an external fire extinguishing method is to be applied move the fuel selector valves to OFF and the mixture to idle cut off ENGINE FIRE IN FLIGHT The procedure given below is general and pilot judgment should be the deciding factor for action in such an emergency an engine fire occurs in flight place the fuel selector of the affected engine in the OFF position Feather the propeller onthe faulty engine Move the mixture control to idle cut off Fhe cowl flap should be open A landing should be made if terrain permits 3 11 FUEL MANAGEMENT DURING ONE ENGINE INOPERATIVE OPERATION A crossfeed 1s provided to increase range during one engine inoperative operation Lise crossfe
221. evel sensor which will automatically dim the annunciator light level during night operations The programmer contains mode recognition lights and dimming is provided by the panel light dimmer switch The electric clevator trim system is a fully redundant type in both the manual and autotrim modes The trim system is powered through a separate system master switch that must be ON during autopilot operations and for the control wheel trim command switch to function when the autopilot is OFF WARNING Several comments are made throughout this supplement about warnings being flashed in NAV APR REV and GS modes in the event valid or GS signal is lost This 15 true only if the aircraft is equipped with navigation and glide slope receivers that have external warning flag pickoffs Pilot should monitor raw data at all time to insure ihgbt safety when the autopilot is engaged ISSUED FEBRUARY 10 1984 REPORT VB 1110 9 of 20 9 143 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 21 PA 34 220T SENECA mE R iQ 7 1 COCKPIT CONTROLS AND FUNCTIONS HDG APR vest ALT 345698 CONTROLLER FLIGHT COMPUTER Figure 7 1 Trim Control Wheel Switch on autopilot control wheel switch Figure 7 3 provides power all autotrim and control wheel electric trim operations 2 Autopilot ON OFF Switch Momentary rocker type switc
222. eview standard emergency procedures periodically to remain proficient in them ISSUED JANUARY 8 1981 REPORT 1110 3 1 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA 34 220T SENECA dR Re rE rd UMP HIS UU EE SABER MB aa e 3 3 EMERGENCY PROCEDURES CHECKLIST AIRSPEEDS FOR SAFE OPERATIONS One engine inoperative air minimum control 66 KIAS One engine inoperative best rate of climb 92 KIAS One engine inoperative best angle of climb 78 KIAS ess sia eh hh EAR de be eee ewes 140 KIAS NEVER exceed Rer ed Eia pa V Aa 205 KIAS ENGINE INOPERATIVE PROCEDURES NOTE The power on the operating engine should be reduced when safe to do so DETECTING DEAD ENGINE Loss of thrust Nose of aircraft will yaw in direction of dead engine with coordinated controls ENGINE SECURING PROCEDURE FEATHERING PROCEDURE Minimum control speed ers 66 KIAS One engine inoperative best rate of climb 92 KIAS Maintain direction and airspeed above 85 KIAS Mixt re sev eva ks vara NASCE ATIS forward Propeller ante uA E Sx eee forward Throttle 40 in Hg forward Fans cba ks aa td Se is eRe retract Gean re eee retract Identify inope
223. evised items 1 and 3 6 29 Added item 129 7 5 Revised para 7 7 7 6 Cont rev para 7 7 moved para 7 9 to pg 7 66 7 6a New page 7 66 New page relocated para 7 9 Crane from pg 7 6 Ward Evans 8 10 Revised para 8 17 April 9 1982 Rev 5 Title Revised Title Page PRS20809 ut Revised para 1 1 Revised para 1 1 1 5 Revised para 1 15 MM Revised Table of Contents 3 9 Revised procedure 3 20 Revised para 3 23 3 21 REPORT 1110 vi f PILOT S OPERATING HANDBOOK LOG OF REVISIONS cont Revision Number and Revised Description of Revision Signature and Code Pages Date Rev 5 3 22 Moved info to pg 3 23 PR820809 and 3 24 cont revised coni para 3 23 3 23 Moved info to pg 3 24 cont revised para 3 23 re 1 5 located info from pg 3 22 3 24 New page relocated info from pg 3 22 3 23 3 25 New page relocated info from pg 3 23 4 16 Revised para 4 11 5 3 Revised para 5 5 a EL Revised Table of Contents 6 Revised para 6 1 6 2 Revised para 6 3 6 5 Revised para 6 5 6 7 Revised fig 6 7 6 11 Revised fig 6 9 6 15 Revised para 6 11 7 18 Revised para 7 17 7 19 Revised fig 7 13 7 19a New page added fig 7 14 7 196 New page cont revised para 7 17 7 20 Cont revised para 7 17 7 26 Revised para 7 23 7 27 7 28 Revised fig 7 21 7 29a New pages added fig 7 22 7 29b UJ 7 3 Revi
224. ew seconds and the mode does not change if the button is not pressed again The following stan dard modes are available in the order shown NAV FLT LOG Functions available with optional 2023 MAP Ground mapping WXA Weather mapping with alert The red area flashes WX Weather mapping NOTE When the top mode is reached the button will not change the mode Y MODE Moves the indicator display to the next lower button mode each time the button is pressed while the list is present The sequence is as listed above NOTE When the bottom mode WX is reached this button will not change the mode CONTROL DISPLAY FUNCTIONS cont Table 4 3 cont REPORT VB 1110 ISSUED JANUARY 8 1981 9 100 4 of 6 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA DISPLAY NAV button push on push off RANGE button HOLD pushbutton push on push off X CONTROL SUPPLEMENT 15 FUNCTION Operational only when optional 1U 2023A Remote Computer Unit is connected When actuated provides NAV information super imposed over the MODE selected WX or MAP If interface is not connected the words NO NAV will be displayed in the lower left corner Clears the display and advances the indicator to the next higher range each time the button is pressed eg 20 to 40 40 to 80 etc until 160 mile range is reached The range selected 15
225. f electrical power if one alternator shows zero output cycle its switch OFF and then If this fails to restore output check the circuit breakers The breakers may be reset once if required If the alternator remains inoperative reduce electrical loads if necessary and exercise judgment regarding continued flight When the ammeter needle indicates to the left of center the battery is being discharged when the needle indicates to the right of center the battery is being charged During single alternator operation the feature can be used to determine haw much the electrical load should be reduced Corrective maintenance actions should be performed prior to further flights NOTE The markings on the ammeter loadmeter require mental interpolations to estimate the ampere values noted Operating the alternators at less than 60 amperes will assure that the batterv will not be depleted WARNING Compass error may exceed 10 with both allernators inoperative REPORT VB 1110 ISSUED JANUARY 8 1981 3 22 REVISED AUGUST 9 1982 PIPER AIRCRAFT CORPORATION SECTION 3 PA 34 220T SENECA HI EMERGENCY PROCEDURES If abnormally high alternator outputs are observed and persists more than 30 amps above known electrical loads they may be caused by a low battery a battery fault or other abnormal electrical load lf itis caused low batters the indication should begin to decrease towards normal within 5 minutes H t
226. f the approved limit A properly loaded airplane however will perform as intended Before the airplane is licensed it is weighed and a basic empty weight and location is computed basic empty weight consists of the standard empty weight of the airplane plus the optional equipment Using the basic empty weight and C G location the pilot can easily determine the weight and C G position for the loaded airplane by computing the total weight and moment and then determining whether they are within the approved envelope ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 9 1982 6 1 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 34 220T SENECA The basic empty weight and C G location are recorded in the Weight and Balance Data Form Figure 6 5 and the Weight and Balance Record Figure 6 7 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 empty weight and C G position and to write these in the Aircraft Log Book and the Weight and Balance Record The owner should make sure that it is done A weight and balance calculation is necessary in determining how much fuel or baggage can be boarded so as to keep the C G within allowable limits Check calculations prior to adding fuel to insure against improper loading The following pages are forms used in weighing an airplane in productio
227. f Revision Signature and Code Pages Date rere je ae a eR am m e ri a a m arena na Rev 3 6 47 Relocated item 269 from pg PR820225 6 46 revised item 272 data cont moved item 277 and 279 to pg 6 48 6 48 Relocated item 277 and 279 from pg 6 47 moved item 285 to pg 6 49 6 49 Relocated item 285 from pg 6 48 moved item 289 to pg 6 50 6 50 Relocated item 289 from pg 6 49 revised item 293 data moved item 295 and 297 to pg 6 51 6 51 Relocated items 295 and 297 from pg 6 50 revised item 301 data 6 52 Added new item 302 6 54 Revised item 315 revised item 319 data 6 56 Revised item 385 f data 6 68 Moved info to new pg 6 69 6 69 New pg relocated info from pg 6 68 added caution note 7 3 7 4 Revised para 7 5 7 12 Revised para 7 11 7 18 Revised voltage info to para 7 17 7 19 Revised fig 7 13 7 20 Revised para 7 17 7 26 Revised para 7 23 7 28 Corrected info listings 29 46 47 7 34 Revised para 7 27 info 7 37 Amended 7 37 8 14 Revised para 8 23 REPORT VB 1110 vi d PILOT S OPERATING HANDBOOK LOG OF REVISIONS cont Revision FAA Approval Number and Description of Revision Signature and Code Date Rev 3 Revised para 8 31 b PR820225 Corrected error cont Corrected error Added info to listing Revised caution note corrected pg no error 9 26 Corrected error 9 27 Revised
228. for approximately 5 seconds then remain OFF 4 Navigation Information Invalid The appropriate navigation mode annunciator will flash when selected and invalid navigation signals are present NAV Flag in view Additionally the appropriate navigation mode annunciator NAV APR REV will flash during a dual mode intercept if invalid navigation information is present 5 GS Information Invalid The GS annunciator will flash when GS information GS Flag in view is invalid after the GS mode is active or when HDG NAV or REV mode is selected after GS capture If valid GS information is not available during the arming sequence the system will not arm and GS capture will not occur ISSUED FEBRUARY 10 1984 REPORT 1110 15 0120 9 149 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 21 _ PA 34 220T SENECA b REMOTE CONTROI SWITCHES AUTOPILOT CONTROL WHEEL SWITCH CAP Figure 7 3 1 Contro Wheel Trim Switch Dual action switch requiring the top bar to be depressed and the rocker to be moved fore or aft to cause the electric trim to function from the control wheel switch Depressing the center bar will disconnect the autopilot 2 Control Wheel Steering CWS Switch See explanation in Special Modes and Operations Section 3 Master Disconnect Trim Interrupt Switch Pressing this switch will disconnect autopilot and interrupt manual electric trim while held depressed Trim operation will resume when the s
229. for the propellers to syn chronize The phase angle of the propellers may then be adjusted by rotating the switch within the PHASE ADJUSTMENT range to obtain the smoothest operation Remember to wait 30 seconds after any switch move ment for the propellers to assume the new phase angle Turn the synchro phaser switch to the OFF position for 30 seconds before changing power settings re establish synchrophaser operation following power changes using the above procedure Pulling the circuit breakers completely de activates the propeller synchrophaser system If the master switch is turned REPORT VB 1110 ISSUED JANUARY 8 1981 9 56 2 of 4 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 7 OFF or if there is an electrical system failure the slave engine will return to the controlled selected RPM plus approximately 25 RPM out of syn chronization regardless of the position of the synchrophaser switch SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of this Pilot s Operating Handbook are necessary for this supplement ISSUED JANUARY 8 1981 REPORT VB 1110 3 of 4 9 57 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 7 PA 34 220T SENECA THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED JANUARY 8 1981 9 58 4 of 4 PIPER AIRCRAFT CORPORATION SECTION 9 34 220 SENECA SUPPLEMENT 8 nb i u
230. fuel can be deter mined by the following formula Arm A R L B inches T Where N 1 REPORT VB 1110 ISSUED JANUARY 8 1981 6 4 PIPER AIRCRAFT CORPORATION SECTION 6 PA 34 220T SENECA WEIGHT AND BALANCE aaa na e a aaa a ei a I I a a t a 6 5 WEIGHT AND BALANCE DATA AND RECORD The Basic Empty Weight Center of Gravity Location and Useful Load listed in Figure 6 5 for the airplane as licensed at the factory These figures apply only to the specific airplane serial number and registration number shown The basic empty weight of the airplane as licensed at the factory has been entered in the Weight and Balance Record Figure 6 7 This form is provided to present the current status of the airplane basic empty weight and complete history of previous modifications change to the perma nently installed equipment or modification which affects weight or moment must be entered in the Weight and Balance Record ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 9 1982 6 5 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 34 220T SENECA MODEL PA 34 220T SENECA Airplane Serial Number Registration Number Date AIRPLANE BASIC EMPTY WEIGHT C G Arm Weight x Inches Aft Moment Item Lbs of Datum In Lbs Actual Standard Empty Weight Computed Optional Equipment Basic Empty Weight The standard
231. gaged and the airplane must be set for descent manually by holding the vertical trim control DN on the Mode Controller if in ALT hold or by establishing the desired PAH using CWS or vertical trim switch SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of this Pilot s Operating Handbook are necessary for this supplement ISSUED APRIL 21 1981 REPORT VB 1110 15 of 16 9 44 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 5 34 220 SENECA III THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 i ISSUED APRIL 21 1981 9 44d 16 of 16 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA Ili SUPPLEMENT 7 a a ATTI PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO 7 FOR PROPELLER SYNCHROPHASER INSTALLATION PIPER DWG 36890 SECTION I GENERAL This supplement supplies information necessary for the operation of the airplane when the optional propeller synchrophaser is installed in accor dance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with the complete handbook This supplement has been FAA Approved and must remain in this handbook at times when the optional propeller synchrophaser 15 installed FAA APPROVED tC T ENEN WARD EVANS D O A 80 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED JANUARY 8 1981 REPORT VB 1110 1
232. ged Basic FD mode may then be re engaged along with any vertical mode and the AP re engaged TRIM The TRIM warning light located in the lower right corner of the annunciator panel will flash and be accompanied by an audible warning whenever the following autotrim and or manual electric pitch trim failures occur The Trim servo motor running without a command 15 monitored on the manual electric and auto trim The trim servo motor not running when commanded to run and the trim servo motor running in the wrong direction are REPORT VB 1110 ISSUED APRIL 21 1981 9 24 6 of 16 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 4 e monitored on Autotrim only The TRIM warning light should flash at least 4 but not more than six times and the audible warning sounds when the test switch on the Mode Controller is depressed GS The Glide Slope valid GS pointer being in view on PNI has to be present before GS may couple If atter GS coupled the valid is lost the system will flash the GS Annunciator and transfer from GS coupled to PAH with the FDI pitch command bar providing pitch attitude steering information If the GS valid returns the system will revert back to GS NAV FLAG The NAV or APPR Modes ARM or CPLD may be selected and wili function with or without a NAV warning flag present The FDI bank steering will continue to provide steering information with or without a valid NAY signal AP D
233. gle engine control speed is 67 KIAS Door off operation is approved for VFR non icing conditions only REPORT VB 1110 ISSUED JANUARY 8 1981 2 8 PIPER AIRCRAFT CORPORATION SECTION 2 PA 34 220T SENECA III LIMITATIONS aiaiai eenaa AAE YA MM TS AE TIS TT rta aaa at a a a PY n 2 33 PLACARDS full view of the pilot THIS AIRPLANE MUST BE OPERATED AS A NOR MAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS MARKINGS AND MANUALS NO ACROBATIC MANEUVERS IN CLUDING SPINS APPROVED THIS AIRCRAFT APPROVED FOR V F R LER DAY NIGHT AND ICING FLIGHT WHEN EQUIPPED IN ACCORDANCE WITH FAR 9I OR FAR 135 in full view of the pilot MAXIMUM TAKEOFF WEIGHT 4750 POUNDS MAXIMUM LANDING WEIGHT 4513 POUNDS ALL WEIGHT IN EXCESS OF 4470 POUNDS MUST CONSIST OF FUEL EXCEPT IN CASES SPECIFIED BY SECTION 6 OF P O H MINIMUM SINGLE ENGINE CONTROL SPEED 66 KIAS On instrument panel in full view of the pilot V 146 AT 4750 LBS SEE Vio 130 DN 108 UP Vit 130 DEMO X WIND 17 KTS Near emergency gear release EMERGENCY GEAR EXTENSION PULL TO RELEASE SEE A F M BEFORE RE ENGAGEMENT ISSUED JANUARY 8 1981 REPORT VB 1110 2 9 SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS 34 2207 SENECA Near gear selector switch GEAR UP 108 KIAS MAX DOWN 130 KIAS MAX Adjacent to upper door l
234. ground speed Radial displayed will be from the station in VOR mode and from the waypoint in RNAV modes d CHK BUTTON Momentary pushbutton Causes radial and distance waypoint parameters to show and distance from VOR station instead DATA BUTTON Momentary pushbutton Causes waypoint data display to change from FRQ to RAD to DST and back to FRQ OFF ON IDENT CONTROL a Power OFF ON Volume Function Rotate clockwise for power b VOR Audio Level Control Rotate clockwise for increased audio level c VOR IDENT Mute Function Push Pull switch Enables the VOR Ident tone to be heard in out position DATA INPUT CONTROL Dual concentric knobs right side of panel Center knob has in and out positions a Frequency Data Outer knob varies 1 MHz digit carry occurs from units to tens position Roliover occurs from 117 to 108 Center knob varies frequency in 50K Hz steps IN or OUT position b Radial Data Outer knob varies 10 degree digit carry occurs from the tens to hundreds position A rollover to zero occurs at 360 degrees Center knob in position varies degree digit Center knob out position varies 0 1 degree digit ISSUED JANUARY 8 1981 REPORT VB 1110 3 of 4 9 77 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 11 PA 34 220T SENECA c Distance Data Outer knob varies 0 digit A carry occurs from the tens to hundreds place A rollover to zero occurs at 200N M
235. h day If the trim system fails any portion of this test turn the trim switch OFF and pull the trim circuit breaker until the system is corrected The command electric trim switch on the left portion of the pilot s control wheel has two functions 1 When the top bar AP OFF is pressed disconnects the autopilot 2 When the top bar is pressed and the rocker is moved forward nose down trim will occur when moved aft nose up trim will occur Command Trim Before the First Flight of Each Day 1 Trim master switch 2 Verify normal trim UP and DOWN operation with control wheel switch 3 Press center bar only then release center bar 4 Push rocker fore and aft only Trim should not operate with either separate action Any failure of the preceding operations indicates that a failure exists in the system and the Command Trim shall not be operated until the failure has been identified and corrected ISSUED APRIL 21 1981 REPORT VB 1110 7 of 12 9 119 SECTION PIPER AIRCRAFT CORPORATION SUPPLEMENT 18 PA 34 220T SENECA III d Autotrim Before the First Flight of Each Day 1 Check trim master switch ON autopilot OFF 2 Press and hold TEST pushbutton on Mode Annunciator Verify the following sequence Each sequence will last approximately two seconds a Allannunciations light with FAIL ind flashing b Autotrim flashes goes steady then flashes c lights go steady d
236. h to permit starting but will not de congeal oil in the sump lines cooler filter etc Typically heat is applied to the upper portion of the engine for a few minutes after which the engine is started and normal operation is commenced The operator may be given a false sense of security by indications of oil and cylinder temperatures as a result of preheat Extremely hot air flowing over the cylinders and oil temperature thermocouples may lead one to believe the engine is quite warm however oil in the sump and filter are relatively remote and will not warm as rapidly as a cylinder For example even when heat is applied directly oil lines are usually lagged with material which does an excellent job of insulating Congealed oil in such lines may require considerable preheat The engine may start and apparently run satisfactorily but can be damaged from lack of lubrication due to congealed oil in various parts of the system The amount of damage will vary and may not become evident for many hours On the other hand theengine may be severely damaged and could fail shortly following application of high power Improper or insufficient application of preheat and the REPORT 1110 ISSUED JANUARY 8 1981 4 22 PIPER AIRCRAFT CORPORATION SECTION 4 PA 34 220T SENECA b c d NORMAL PROCEDURES resulting oil and cylinder temperature indications may encourage the pilot to expedite his ground operation and commence a
237. h which engages or disengages the autopilot roll pitch and trim servos and lights or extinguishes autopilot AP annunciator as appropriate NOTE The autopilot will switch to HDG and ATT modes upon engagement or disengagement with automatic pitch attitude synchronization 222 HDG Mode Selector Switch provides turn control and heading hold through use of the heading index bug on the D G or 5 1 heading instrument REPORT VB 1110 ISSUED FEBRUARY 10 1984 9 144 10 of 20 5 PIPER AIRCRAFT CORPORATION SECTION 9 34 220 SENECA SUPPLEMENT 21 Figure 7 1 cont 4 NAV Navigation Mode Selector Switch provides automatic 45 VOR LOC intercept angie tracking and crosswind correction The autopilot utilizes the HDG bug as the VOR course reference and separate VOR indicator instrument for left right information when using D G or the course indicator and left right needle for reference inputs when using an H S T type compass VOR display The NAV mode provides automatic gain and rate reductions and bank hmiting to improve tracking performance NAV mode should normally be used as an enroute function Select APR mode for LOC and VOR approaches NOTES 1 The heading bug is disabled when using an 5 and APR or REV is selected except when using selected angle intercept feature refer to Special Modes and Operations 2 D G the heading bug must be set to the desired radio course
238. hand side forward of the door using the strap provided REPORT VB 1110 ISSUED SEPTEMBER 23 1983 8 20 SECTION 9 SUPPLEMENTS Paragraph Supplement NO 9 1 Sale pe ee l Portable Oxygen System Installation 6 pages 2 Fixed Oxygen System Installation Part Numbers 36960 3 or 87441 2 4 pages 3 Air Conditioning 6 pages 200 Automatic Flight Control System With Flight 16 pages 5 200 Automatic Flight Control System Without Flight Director 16 pages 6 Protection System Installation 10 pages 7 Propeller Synchrophaser Installation 4 pages 8 Bendix NP 2041A Area Navigation Computer 6 pages 9 Collins ANS 351 Area Navigation Compuler cesna ra FEN AY Cede RE 6 pages 10 King KNS 80 Navigation System 4 pages E KNS 81 Digital Area Navigation System 4 pages 12 RCA Color WeatherScout Weather Radar System cece hh nnn 6 pages 13 RCA WeatherScout Weather Radar System cc ccc 6 pages 14 Bendix RDR 160 Monochrome Weather Radar System eee eee eee nnn 6 pages 15 Bendix RDR 160 1N 2026A Color Weather Radar System hn nn 6 pages 16 Propeller Synchrophaser Installation
239. he magnetic heading indicated by the magnetic compass The unslaved compass card must be manually reset periodically to compensate for precessional errors in the gyro ISSUED FEBRUARY 10 1984 REPORT VB 1110 19 of 20 9 153 SECTION 9 PIPER AIRCRAFT CORPORA TION SUPPLEMENT 21 PA 34 220T SENECA HI THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED FEBRUARY 10 1984 9 154 200f 20 TABLE OF CONTENTS SECTION 10 SAFETY TIPS Paragraph 10 1 General 10 1 10 3 at deu erede ie X da pitas 10 1 REPORT VB 1110 19 i PIPER AIRCRAFT CORPORATION SECTION 10 PA 34 220T SENECA HI SAFETY TIPS 1 Forms to be completed Physiological Training Application and Agreement for application for the training course may be obtained by writing to the following address Chief of Physiological Training AAC 143 FAA Aeronautical Center Box 25082 Oklahoma City Oklahoma 73125 It is recommended that all pilots who plan to fly above 10 000 feet take this training before flying this high and then take refresher training every two or three years Siuggish RPM control and propeller overspeed with poor RPM recovery after rapid throttle application are indications that nitrogen pressure in the propeller dome is low m Experience has shown that the training advantage gained by pulling a mixture control or turning off the fuel to simulate engine failure
240. he airplane should be lowered to a safe altitude immediately Always remove fittings from the oxygen receptacles and stow the masks when they are not in use Connect only those mask assemblies being used to prevent oxygen loss through an unused mask assembly If the control knob is ON and the fitting is in the receptacle oxygen will flow through the mask continuously dual manifold connector is used both masks must be donned Masks may be damaged if they are not properly stowed REPORT VB 1110 ISSUED JANUARY 8 1981 9 4 2 of 6 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA III SUPPLEMENT 1 WARNING Positively no smoking while oxygen is being used by anyone in the airplane To stop the flow of oxygen through the system the control knob should be turned OFF by rotating fully clockwise finger tight To preclude the possibility of fire by spontaneous combustion oil grease paint hydraulic fluid and other flammable material should be kepi away from oxygen equipment SECTION 2 LIMITATIONS a No smoking allowed b The aircraft is restricted to six occupants with two 2 oxygen u units installed c The aircraft is restricted to four occupants with one 1 installed d Oxygen duration DURATION IN HOURS AT ALTITUDE Persons Using Each Unit 10 000 15 000 20 000 25 000 1 63 4 7 3 8 3 3 2 3 2 2 4 1 9 7 3 2 1 1 6 1 3 4 1 6 1 2 0 95 0 8 NOTE
241. he basic Emergency Procedures provided by Section 3 of this Pilot s Operating Handbook are necessary for this supplement SECTION 4 NORMAL PROCEDURES KNS 81 OPERATION The KNS 81 can be operated in any one of 3 modes a VOR b RNAV or c ILS To change from one mode to another the mode select knob is rotated large knob on the left side of the panel except that the ILS mode is entered automatically whenever an ILS frequency is channeled The display will annunciate the VOR RNAV mode by lighting a message beside the waypoint In addition to the standard VOR and RNAV enroute modes the KNS 81 constant course width or parallel VOR mode VOR PAR and RNAV approach mode RNV APR To place the unit in either of these secondary modes the mode selector knob is rotated b CONTROLS 1 USE BUTTON Momentary pushbutton Causes displayed waypoint to become active waypoint and carrot display to go to FRQ mode 2 RTN BUTTON Momentary pushbutton When pushed causes waypoint in use to be displayed and carrot display to go to FRQ mode 3 RAD BUTTON Two position pushbutton The KNS 81 is normally operated with the RAD button not pressed When in depressed position causes DME to display radial REPORT VB 1110 ISSUED JANUARY 8 1981 9 76 2of4 REVISED FEBRUARY 25 1982 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA III SUPPLEMENT 11 4 5 6 7 information instead of
242. he rear door securely and check the left static vent and dorsal fin air scoop for obstructions The empennage should be free of ice and damage and all hinges should be secure Check the stabilator for freedom of move ment and ensure that the right static vent is unobstructed Antennas should be secure and undamaged After turning on the battery switch and light switches in the cockpit check the navigation and landing lights 4 13 BEFORE STARTING ENGINES Before starting engines adjust the seats and fasten the seat belts and shoulder harnesses NOTES If the fixed shoulder harness non inertia reci type is installed it must be connected to the seat belt and adjusted to allow proper accessi bility to all controls including fuel selectors trim ete while maintaining adequate restraint for the occupant If the inertia ree shoulder harness is installed a pull test of its locking restraint feature should be pertormed Set the parking brake by first depressing and holding the toe brake pedals and then pulling out the parking brake knob WARNING No braking will occur tf knob ts pulled prior to brake application Check to make sure all the circuit breakers are tn and the radios are OFF Cowl flaps should be OPEN and alternate air The alternators should now be switched ON REPORT VB 1110 ISSUED AUGUST 17 1981 4 16b REVISED FEBRUARY 10 1984 PIPER AIRCRAFT CORPORATION SECTION 4 34 220
243. he seat belt through the control whecl and pulling it snug 4 Block the wheels REPORT VB 1110 ISSUED JANUARY 8 1981 8 6 REVISED FEBRUARY 16 1984 PIPER AIRCRAFT CORPORATION SECTION 8 PA 34 220T SENECA HANDLING SERV amp MAINT PERMESSO 5 Secure tie down ropes to the wing tie down rings and to the tall skid at approximately 45 degree angles to the ground When using rope of non synthetic material leave sufficient slack to avoid damage to the airplane should the ropes contract CAUTION ise bowline Knots square knots or locked slip Knots Do not use plain slip knots NOTE Additional preparations for high winds include using tie down ropes from the landing gear forks and securing the rudder 6 Install a pitot head cover if available Be sure to remove the pitot head cover before flight 7 Cabin and baggage doors should be locked when the airplane 1s unattended 8 11 ENGINE INDUCTION AIR FILTERS a 1 Remove the upper cowling to gain access to the air filter box 2 Turn the four studs and remove the air filter box cover 3 Lift the air filter from the filter box b Cleaning Induction Air Filters The induction filters must be cleaned at least once every 50 hours and more often even daily when operating in dusty conditions Extra filters are inexpensive and a spare should be kept on hand for use as a rapid replacement To clean the filter
244. heck purses Fee age bel aks check REPORT 1110 ISSUED JANUARY 8 1981 4 6 REVISED FEBRUARY 10 1984 PIPER AIRCRAFT CORPORATION SECTION 4 PA 35 2207 SENECA TH NORMAL PROCEDU RES NOTE When starting at ambient temperatures 20 and below operate first engine started with alternator ON at max charging rate not to exceed 1500 RPM for S minutes minimum before initiating start on second engine STARTING ENGINES WHEN FLOODED coo Ci Beet Mon TUE re wa Sara ev ln desea idie cut off Ae ewe tows hes aa FULL FORWARD Propnellefus FULT FORWARD Batters ete tte lag EE ON lenition switches MAPS eres eu ae ua a x hr ER ON OFF ee ee eS clear SCE ck cura ues Vox Ae SRR RHOD RS ERR s engage When engine fires Throttle retard 2 advance slowly STARTING ENGINES IN COLD WEATHER AIRPLANE EQUIPPED WITH STANDARD ENGINE PRIMER SYSTEM Ign S LC vos pes TRY SEN beware dca OFF bike trees gas Ga d turn through by hand 3 times Wile Mixture ip al FU LI RIC H deret atk diu Eb UOS obses FORWARD Pup GOBEROL sioe seo EE eee FULL FORWARD Hatters S amp Heh
245. heel steering switch on the pilot s control wheel When depressed and held this switch will disengage the autopilot roll and pitch servos to allow manual aircraft maneuvering When released the servos will re engage with the lateral roll mode previously in use activated The pitch mode previously engaged will remain programmed in the following condition a ALT If ALT mode had been in use the ALT mode will synchronize at the new pressure altitude existing at release of the CWS switch b Mode If the ATT mode had been in use the system will synchronize with the aircraft attitude existing at release of the switch System Test Ground Operations Only The system is equipped with a comprehensive test circuit which when activated will test the failure monitor circuits and ali the annunciator lamps Activation of the TEST switch willinitiate the system test only when the autopilot is NOT engaged When autopilot is engaged activation of the TEST switch will test the annunciator lamps if the autopilot is engaged during the test sequence the sequence will terminate immediately Refer to Section 4 for tests required before the first flight of each day Warning System and Interlocks The Century 31 System includes a number of automatic interlocks that will prevent system operation or individual mode operation if the input information is not valid or if other prerequisite conditions do not exist addition to the inte
246. his test prevent the strap from extending Under normal movement the strap will extend and retract as required On earlier aircraft provided with a single strap adjustable shoulder harness for each front seat the shoulder strap is routed over the shoulder adjacent to the windows and attached to the lap belt in the general area of the person s inboard hip Adjust this fixed strap so that all controls are accessible while maintaining adequate restraint for the occupant Shoulder harnesses shall be worn during takeoff and landing Shoulder harnesses should be worn during an emergency situation Standard cabin features include a pilot s storm window ashtrays map pockets coat hooks and assist straps a cigar lighter sun visors and pockets on the front and center seat backs Among the options which may be added to suit individual needs are headrests a fire extinguisher and a special cabin sound proofing package An optional club seating interior is also available In the club seating interior the center seats face aft These seats are equipped with lap belts only of the seats is accomplished by removing the two bolts holding the aft attach points and sliding the seat aft An optional refreshment console is located between the center seats It is removed in a manner identical to the removal of the center seats An optional oxygen system is located between the center seats It is strapped to the jump seat in the standar
247. his condition is observed proceed with the following Turn the battery switch OFF and the alternator output indications should decrease Turn ihe battery switch Should the alternator output indications not decrease leave the battery switch OFF and land as soon as practical electrical load is being supplied by the alternators Also anticipate complete electrical power failure NOTE Operation with the alternator ON and the battery switch OFF should be made only when required by electrical failure due to increased system volt tage and radio frequency noise 3 25 GYRO SUCTION FAILURES malfunction of the instrument suction system will be indicated by a reduction of the suction reading on the gauge In the event of a vacuum failure or a feathered engine jow vacuum warning light on the annunciator panel will illuminate in the event of a suction system malfunction suction lower than 4 5 inches of mercury increase engine RPM to 2600 Descend to an altitude at which 4 5 inches of mercury suction can be maintained if possible The electric turn indicator should be used to monitor the performance of the directional and attitude indicators ISSUED JANUARY 8 1981 REPORT 1110 REVISED AUGUST 9 1982 3 23 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA 34 220T SENECA 3 27 SPINS Intentional spins are prohibited in this airplane In the event a spin is encountered unintentionally immedi
248. icates system failure NSD 360A System includes a slaving selector switch allowing the selection of free gyro mode Refer to emergency procedures for failure instructions HDG index bug for autopilot heading control Compass card Left right portion of VOR LOC Course Needle HDCG Control Knob push in for initial compass setting VOR Course Needle Set Knob 5 GS Indicator with Flag Alarm VOR LOC Bearing Selector Course Needle and Omni Bearing Indicator 10 Heading Warning Flag 11 Navigation Warning Flag c REA oe REPORT 1110 ISSUED FEBRUARY 10 1984 9 152 18 of 26 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA HE SUPPLEMENT 21 a a DIRECTIONAL GYRO Figure 7 9 Non Slaved Directional Gyro Provides a stable visual indication of aircraft heading to the pilot Fhe gyro is air driven Lubber Line Indicates aircraft magnetic heading on compass card 4 Heading Bug Moved knob 5 to select desired heading Compass Card Rotates to display heading of airplane with reference to lubber line 2 on DG Heading Selector Knob Positions heading bug 3 on compass card 4 by rotating the heading selector knob The bug rotates with the compass card Gyro Adjustment Knob PUSH When pushed in allows the pilot to manually rotate the gyro compass card 4 to correspond with t
249. illuminated is Baggage Door advising the pilot of this condition NOTE It is the pilot s responsibility to be sure when baggage is loaded that the airplane C G falls within the allowable C G range See Weight and Balance Section 7 33 FINISH exterior surfaces are finished with acrylic lacquer To keepthe finish attractive economy size spray cans of touch up paint are available from Piper Dealers An optional polyurethane finish is available Optional equipment REPORT 1110 ISSUED JANUARY 8 1981 7 36 REVISED AUGUST 9 1982 PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA HI DESCRIPTION amp OPERATION HR PA I 7 35 PIPER EXTERNAL POWER An optional starting installation known as Piper External Power PEP allows the airplane engine to be started from an external battery without the necessity of gaining access to the airplane battery The cable from the external battery can be attached to a receptacie under the right side of the nose section of the fuselage Instructions placard located on the cover of the receptacle should be followed when starting with external power For instructions on the use of the refer to Starting Engines Section 4 7 37 EMERGENCY LOCATOR TRANSMITTER The Emergency Locator Transmitter EL T is located in the aft portion of the fuselage just below the stabilator leading edge and is ac
250. immediately This requires removal of the access cover and moving the switch to OFF then press the reset button and return the switch to ARM Recheck with the receiver to ascertain the transmitter 15 silent battery replacement date is marked on the transmitter to comply with FAA regulations the battery must be replaced on or before this date The battery must also be replaced if the transmitter has been used in an emer gency situation or if the accumulated test time exceeds one hour or if the unit has been inadvertently activated for an undetermined time period NOTE If for any reason a test transmission is necessary the test transmission should be conducted only in the first five minutes of any hour and limited to three audio sweeps If the tests must be made at any other time the tests should be coordinated with the nearest FAA tower or flight service station REPORT VB 1110 JSSUED JANUARY 8 1981 7 38 PIPER CORPORATION SECTION 7 PA 34 220T SENECA DESCRIPTION amp OPERATION 7 39 PIPER CONTROL WHEEL CLOCK The time and date can be set by the operation of the reset RST button while in the clock mode The month is set by pressing the reset RST button once this will cause the date to appear with the month flashing Pressing the start stop ST SP button advances the months at one per second or one per push until the right month appears To set the date press the reset RST button once agai
251. inar flow NACA 652 415 airfoil section The main spar is located at approximately 40 of the chord aft of the leading edge The wings are attached to the fuselage by the insertion of the butt ends of the spar into a spar box carry through which is an integral part of the fuselage structure The bolting of the spar ends into the spar box carry through structure which is located under the center seats provides in effect a continuous main spar The wings are also attached fore and aft of the main spar by an auxiliary front spar and a rear spar The rear spar in addition to taking torque and drag loads provides a mount for flaps and ailerons The four position wing flaps are mechanically controlled by a handle located between the front seats When fully retracted the right flap locks into place to provide a step for cabin ISSUED JANUARY 8 1981 REPORT VB 1110 7 1 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA 11 entry Each wing contains two fuel tanks as standard equipment An optional third tank may be installed on each side The tanks on one side are filled through a single filler neck located well outboard of the engine nacelle A vertical stabilizer an all movable horizontal stabilator and a rudder make up the empennage The stabilator incorporates an anti servo tab which improves longitudinal stability and provides longitudinal trim This tab moves in the same direction as the stabilat
252. ing indicators to display raw distance and bearing information RNAV computation CDI deviation to from display and autopilot tracking of RNAV path remain unaffected The check button is spring loaded to prevent permanent actuation Ambient Light Automatically adjusts display lighting intensity O Sensor as a function of cockpit ambient light b AREA NAVIGATION WAYPOINT PROGRAMMING 1 Presetting of Waypoint On Ground Waypoints are entered after engine start since the waypoint information will probably be lost during the low voltage condition occurring during engine cranking Waypoint data should always be written in flight planning form to facilitate checking later in flight When power is first applied to the ANS 351 and the system is in the RNAV mode waypoint number will be active waypoint number not blinking and wavpoint bearing and distance preset to zero will appear a Waypoint number coordinates are set into the ANS 351 using concentric knobs under bearing and distance display fields REPORT VB 1110 ISSUED JANUARY 8 1981 9 68 4of6 REVISED APRIL 21 1981 PIPER AIRCRAFT CORPORATION SECTION 9 34 220 SENECA SUPPLEMENT 9 b e a aa t AMAT T a TT TT TT I I TTE a The waypoint selection knob is then rotated to select way point number 2 Note that the waypoint number ts blink ing indicating that the waypoint is at this point inactive Waypoint number 2 beari
253. intain control ELECTRICAL FAILURES ALT warning light illuminated Animeter AMMEtIETS s coner met eva Piden check 1 amp check BIO MIT Goh o h ae A OER DTP reduce to minimum orna EE Lo Gov ser wx Pace ee OFF then ON one at a time alternator outputs are NOT restored Batter such REA EAI ER OFF Alternator SWINE cee Rz oes ee OFF then ON one at a time li alternator outputs are NOT restored S OFF as required If alternator cannot be restored reduce electrical load and land as soon as practical The battery is the only remaining source of electrical power WARNING Compass error may exceed 10 degrees with both alternators inoperative NOTE battery is depleted the landing gear must be lowered using the emergency gear extension procedure Gear position lights will be in operative ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 9 1982 3 9 3 gt PIPER AIRCRAFT CORPORATION E MERGENCY PROCEDURES PA 34 220T SENECA IH mM UM Msc p UD DU Electrical overload alt snators over 30 amps above known electrical load Electrical ad uius PETI D E utis reduce if alternator loads cannot be reduced Battery r2 DE be a ORAN OFF alternator loads are not reduced land as soon s possible Anticipate complete electrical power failure
254. ion contains the required FAA performance information applicable to this aircraft Additional information is provided for flight planning purposes Performance information associated with those optional systems and equipment which require handbook supplements is provided by Section 9 Supplements 5 3 INTRODUCTION PERFORMANCE AND FLIGHT PLANNING The performance information presented in this section is based on measured Flight Test Data corrected to 1 standard day conditions and analytically expanded for the various parameters of weight altitude temperature etc The performance charts are unfactored and do not make any allowance for varying degrees of pilot proficiency or mechanical deterioration of the aircraft This performance however can be duplicated by following the stated procedures in a properly maintained airplane Effects of conditions not considered on the charts must be evaluated by the pilot such as the effect of soft ar grass runway surface on takeoff and landing performance or the effect of winds aloft on cruise and range performance Endurance can be grossly affected by improper leaning procedures and inflight fuel flow and quantity checks are recommended REMEMBER To get chart performance follow the chart procedures ISSUED JANUARY 8 1981 REPORT VB 1118 5 1 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 34 220T SENECA The information provided by paragraph 5 5 Flight Planni
255. istance to climb and distance to descend to establish the total cruise distance Refer to the Power Setting Tables when selecting the cruise power setting The established pressure altitude and temperature values and the selected cruise power should now be utilized to determine the true airspeed from the Speed Power graph Figure 5 27 Calculate the cruise fuel for the cruise power setting from the information provided on Figure 5 25 The cruise time is found by dividing the cruise distance by the cruise speed and the cruise fuel is found by multiplying the cruise fuel flow by the cruise time The cruise calculations established for the cruise segment of the flight planning example are as follows I Total Distance 394 miles 2 Cruise Distance minus c 4 minus d 2 394 miles minus 24 naut miles minus 37 naut miles 333 naut miles 3 Cruise Power 55 rated power 4 Cruise Speed 172 KTS TAS 5 Cruise Fuel Consumption 18 7 GPH 6 Cruise Time 2 divided by e 4 333 naut miles divided by 172 KTS 1 94 hrs 7 Cruise Fuel MK eX 5 multiplied by e 6 18 7 multiplied by 1 94 hrs 36 3 gal reference Figure 5 27 reference Figure 5 25 5 6 REPORT 1110 ISSUED JANUARY 8 1981 PIPER AIRCRAFT CORPORATION SECTION 5 PA 34 220T SENECA PERFORMANCE f Total Flight Time The total flight time is determined by adding the time to climb the time to descend and
256. itch command after approximately three second delay d Grasp control wheel and override roll and pitch servo actuators to assure override capability e Hold control yoke and disengage autopilot by activating the control wheel trim switch f Check controls through full travel in roll and pitch to assure complete autopilot disengagement Retrim aircraft for takeoff REPORT VB 1110 ISSUED APRIL 21 1981 9 118 6 of 12 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 18 men AA e A M Mare as c TRIM SYSTEM The autopilot is provided with an electric elevator trim system having two modes of operation When the autopilot is engaged and the trim master switch is ON automatic electric trim autotrim is provided When the autopilot is disengaged command electric elevator trim is available by use of the control wheel switch provided or by use of the primary trim control wheel The electric elevator trim system has been designed to withstand any type of single failure either mechanical or electrical without uncontrolled operation resulting The automated system self test circuit provided in conjunction with a functional check described below wil uncover internal failures that otherwise could remain undetected and thus compromise the fail safe properties of the system Proper operation of the system is therefore predicated on conducting the following preflight check first flight of eac
257. justed to allow proper accessi bility to alf controls including fuel selectors flaps trim ete while maintaining adequate restraint for the occupant if the inertia type shoulder harness ts installed pull test of locking restraint feature should be performed All controls should be free with full travel and all doors should be securely latched Ensure that the auxiliary fuel pumps are OFF Pitot heat should be used as required Release the parking brake REPORT 1110 ISSUED JANUARY 8 1981 4 26 REVISED FEBRUARY 16 1984 PIPER AIRCRAFT CORPORATION SECTION 4 PA 34 220T SENECA III NORMAL PROCEDURES 4 33 TAKEOFF To achieve the takeoff performance specified in Section 5 is necessary to set rated power 2800 RPM 40 In Hg prior to brake release NOTES Takeoffs are normally made with less than full throttle use throttle only as required to obtain 40 in Hg manifold pressure DO NOT EX CEED 40 IN HG MANIFOLD PRESSURE The overboost indicator lights on the annun ciator panel will illuminate at approximately 39 5 in Hg manifold pressure Do not exceed 40 in Hg manifold pressure Humipation of the yellow overboost light on the annunciator panel does not indicate a malfunction The overboost lights illuminate when manifold pressure approaches the maximum limit The overboost lights should be monitored during takeoff to ensure that an overboost condition does not
258. k incorporated REPORT VB 1110 ISSUED JANUARY 8 1981 7 4 REVISED FEBRUARY 25 1982 PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA DESCRIPTION amp OPERATION in each control lever locks the cowl flap in the selected position To operate the cow flaps depress the lock and move the lever toward the desired setting Release the lock after initial movement and continue movement of the lever The control will stop and lock into place at the next setting The lock must be depressed for each selection of a new cowl flap setting The intermediate lever position is used for climb and single engine operation The full open position is available when abnormal temperatures are encountered 7 7 PROPELLERS _ Counter rotation of the propellers provides balanced thrust during takeoff and climb and eliminates the critical engine factor in single engine flight Two blade constant speed controllabile pitch and feathering Hartzell propellers are installed as standard equipment The propellers mount directly to the engine crankshafts Pitch is controlled by oil and nitrogen pressure Oil pressure sends a propeller toward the high RPM or unfeather position nitrogen pressure sends a propeller toward the low RPM or feather position and also prevents propeller overspeeding The recommended nitrogen pressure to be used when charging the unit is listed on placards on the propeller domes and inside the spinners This pressure varies
259. kes or alternate air inlets 3 Allow the solvent to remain on the engine from five to ten minutes Then rinse the engine clean with additional solvent and allow it to dry CAUTION Do not operate the engine until excess solvent has evaporated or otherwise been removed 4 Remove the protective tape from the magnetos S Lubricate the controls bearing surfaces etc in accor dance with the Lubrication Chart in the PA 34 220T Service Manual REPORT VB 1110 ISSUED JANUARY 8 1981 8 16 PIPER AIRCRAFT CORPORATION SECTION 8 PA 34 220T SENECA HANDLING SERV amp MAINT b Cleaning Landing Gear Before cleaning the landing gear place a plastic cover or similar material over the wheel and brake assembly 1 2 3 4 5 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 Where heavy grease and dirt deposits have collected it may be necessary to brush areas that were sprayed 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 in accordance with the Lubrication Chart in the PA 34 220T Service Manual CAUTION Do not brush the micro switches c Cleaning Exterior Surfaces The airplane should be washed with a mild soap and water
260. l tanks on each side are filled through a single filler in the outboard tank and as fuel is consumed from the inboard tank it is replenished by fuel from outboard Only two and one half gallons of fuel in each wing is unusable giving the Seneca a total of 93 usable gallons with standard fuel tanks or 123 usable gallons with the optional fuel tanks installed The minimum fuel grade is 100 or 10011 Aviation Grade The fuel tank vents one installed under each wing feature an anti icing design to prevent ice formation from blocking the fuel tank vent lines ISSUED JANUARY 8 1981 REPORT VB 1110 7 13 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA m Pad The fuel injection system is a continuous flow type that utilizes a vapor return line leading back to the fuel tanks This line provides a route back to the tanks for vapor laden fuel that has been separated in the injector pump swirl chamber Each engine has an engine driven fuel pump that isa part of the fuel injection system An auxiliary fuel system is provided The purpose of the electrically powered auxiliary fuel system is to supply fuel to the engine in case of engine driven fuel pump shaft failure or maifunction for ground and inflight engine starting and for vapor suppression The two auxiliary fuel pump switches are located on the lower left side of the instru men
261. l Century 21 Autopilot Operator s Manual P N 68S805 dated E 79 for Autopilot Description and Normal Operating Procedures PREFLIGHT PROCEDURES NOTE During system functional check the system must be provided adequate D C voltage 12 0 VDC min and instrument air 4 2 in Hg min is recommended that one engine be operated minimum to provide the necessary power and that the aircraft be positioned in a level attitude during the functional check AUTOPILOT WITH STANDARD c 1 Engage autopilot by pushing programmer OFF ON switch ON 2 Rotate D G HDG bug left then right and verify that control wheel movement corresponds to HDG command input 3 Grasp contro wheel and override roll servo actuator to assure override capability 4 With HDG bug centered select NAV or APPR mode and note control wheel movement toward VOR needie offset 5 Select REV mode and note control wheel movement opposite VOR needle offset 6 Disengage autopilot 7 Check aileron controls through full travel to assure complete autopilot disengagement AUTOPILOT WITH COMPASS SYSTEM NSD 360A For other compass systems refer to appropriate manufacturer s instructions 1 Check slaving switch in slave or slave 1 or 2 position as appropriate Slaving systems with R M I output provide only slave and free gyro positions 2 Rotate card to center slaving meter check displayed with magnetic compa
262. label displayed for each range mark Operating mode is displayed as WX or CYC When system 18 first turned on WAIT is displayed until system times out 30 40 seconds INDICATOR CONTROLS AND DISPLAY FEATURES ISSUED JANUARY 8 1981 Table 4 3 REPORT VB 1110 23 of 6 9 87 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 13 PA 34 220T SENECA HI b c d PRELIMINARY CONTROL SETTINGS Place the Indicator controls in the following positions before applying power from the aircraft electrical system INTensity Fully counterclockwise in OFF TET controle ERG Fully upward RANGE SWHOl ett n Genes cents 12 nautical miles OPERATIONAL CONTROL SETTINGS 1 Rotate INTensity control clockwise to bring system into ON condition 2 Note that WAIT is displayed during warm up period of 30 40 seconds 3 When WX is displayed rotate INTensity control clockwise until display brightness 15 at desired level 4 Set RANGE switch to desired range 5 Adjust TILT control for desired forward scan area PRECAUTIONS If the radar is to be operated while the aircraft is on the ground 1 Direct nose of aircraft such that antenna scan sector is free of _ large metallic objects hangars other aircraft for a distance of 100 vards 90 meters and tilt antenna fully upward WARNING Do not operate the radar during refueling operations or in the vicinity
263. ld be made before using checklist Berore advancing the throttle to check the magnetos and the propeler acuon be vure that the engine oil temperature 1 75 or above During engine run up head the airplane into the wind if possible see crosswind limits for propellers and set the parking brake Advance the mixture and propeller controls forward and the throttle controls 0 1000 RPM Drain the manifold pressure lines by depressing the drain valves located behind and below the dual manifold pressure gauge for 5 seconds Do not depress the valves when the manifold pressure exceeds 25 inches Hg Check the feather position of the propellers by bringing the controls fully aft and then full forward Do not allow more than a 300 RPM drop during the feathering check Move the throttles to 2300 RPM and exercise the propeller controls to check the function of the governor Retard control until a 200 to 300 drop in RPM is indicated This should be donc three times on the first flight of the das 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 indicating proper function of the governor ISSUED JANUARY 8 1981 REPORT 1110 REVISED FEBRUARY 10 1984 4 25 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA 34 220T SENEC
264. lobes disengage at approximately 30 of tilt and remove the table Position the table in the stowage area and with the table work surface facing forward place the slots in the table support into the receptacle clips mounted on the hat shelf Make sure the tie down strap is not behind the table With the table fully placed in the clips bring the tie down strap across the face of the table and lock over the stud located on the bottom of the close out bulkhead 7 29 STALL WARNING An approaching stall is indicated by a stall warning indicator which is activated between five and ten knots above stall speed Mild airframe buffeting and gentle pitching may also precede the stall Stall speeds are shown on a graph in the Performance Charts Section The stall warning indicator consists of a continuous sounding horn located behind the instru ment panel The stall warning horn has a different sound from that of the gear warning horn which has a 90 cycles per minute beeping sound The stall warning indic tor is activated by two lift detectors on the leading edge of the left wing outboard of the engine nacelle The inboard detector activates the indicator when the flaps are in the 25 and 40 degree positions the outboard when the flaps are in other positions A squat switch in the stall warning system does not allow the units to be activated on the ground ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 9 1982 7 35 SECTION 7 PIPER AIRCRAFT
265. lot s control wheel left horn TRIM UP DN ISSUED APRIL 21 1981 REPORT VB 1110 REVISED FEBRUARY 25 1982 3 of 16 9 35 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 5 m 34 2207 SENECA Hi SECTION 3 EMERGENCY PROCEDURES AUTOPILOT MALFUNCTION 1 Emergency Disengagement of AP Hold the Control Wheel firmly and press the DISC TRIM INTERRUPT Switch b ELECTRIC TRIM MALFUNCTION either manual electric or autotrim 1 AP DISC TRIM INTERRUPT Switch Press and hold down until recovery can be made 2 RADIO POWER Switch OFF 3 Aircraft manually retrim 4 PITCH TRIM circuit breaker Pull 5 RADIO POWER Switch CAUTION When disconnecting the autopilot after a trim malfunction hold the contro wheel firmly up 1045 pounds of force on the control wheel may be necessary t hold the aircraft level c ENGINE FAILURE COUPLED 1 Disengage AP 2 Follow basic Airplane Flight Manual engine inoperative procedures 3 Airplane rudder and aileron axes must be manually trimmed prior to engaging autopilot for engine inoperative operations CAUTION If rudder and aileron trim cannot be main tained when power is changed during a single engine inoperative coupled approach disen gage autopilot and continue approach manually CAUTION At airspeeds below 110 MPH 96 KTS IAS rapid power application may cause pro nounced pitch up attitude of 20 or more REPORT V
266. ly and conveniently to a Determine the total weight and C G position b 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 The Basic Empty Weight and Center of Gravity location is taken from the Weight and Balance Form Figure 6 5 the Weight and Balance Record Figure 6 7 or the latest FAA major repair or alteration form 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 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 theairplane 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 segm
267. m 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 deice switch on and feeling the propeller deicer pads for proper heating sequence The deicer pad 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 REPORT VB 1110 ISSUED JANUARY 8 1981 9 48 4of 10 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 6 tma ra taa ua PTT T TA Ta a a a e e e S ia a a aa a a a i manana 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 controlied by an ON OFF control switch circuit breaker The contro switch circuit breaker is located in the right hand side of the deice panel and is placarded WINDSHIELD PANEL HEAT SEE AIRPLANE FLIGHT MANUAL CAUTION 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 An operational check may
268. magentic compass 3 Perform standard VOR receiver check 4 NAV APPR Engage NAV or APPR mode switch and observe steering bar indicates turn torward the VOR needle NOTE If the Omni Bearing Selector is more than 45 from the aircraft heading the flight director steering bar will oniy indicate a turn toward the omni bearing IN FLIGHT PROCEDURE FLIGHT DIRECTOR 1 Century 41 circuit breaker IN Flight director switch ON 2 Adjust HDG bug to aircraft heading and select desired pitch attitude by activation of the CWS Pitch Synch switch or the modifier switch 3 Maneuver aircraft manually to satisfy the commands presented Select other modes as desired refer to Century 41 Operator s Manual for mode description IN FLIGHT PROCEDURE AUTOPILOT FLIGHT DIRECTOR AUTOPILOT 1 Flight director switch ON if F D equipped Rotate heading bug to desired heading 2 Trim aircraft for existing flight condition all axes Engage autopilot 3 During maneuvering flight control aircraft through use of the HDG bug and the pitch modifier HDG ATT modes For use of pitch synch switch see Operator s Manual 4 For navigation operations select modes as required by the operation being conducted and in accordance with the mode description provided in Operators Manual For specific instructions relating to coupled instrument approach operations refer to Special Operations and Information Section 4 item 1 ISSU
269. mature engine overhauls 4 37 CRUISING When leveling off at cruise altitude the pilot may reduce to a cruise power setting in accordance with the Power Setting Table in this handbook For 45 55 and 65 power the mixture should be leaned to 25 rich of peak E G T but not to exceed 1650 F E G T For 75 power the mixture should be leaned to 14 5 G P H but not to exceed 1525 F E G T The mixture should be full rich at powers above 75 For maximum engine service life cylinder head temperatures should be maintained below 420 F and oii temperatures below 200 F during cruise These temperatures can be maintained by opening the cowl flaps reducing the power enriching the mixture or any combination of these methods ISSUED JANUARY 8 1981 REPORT VB 1110 4 29 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA 34 220T SENECA 11 ra e NN The pilot should monitor weather conditions while fiying and should be alert to conditions which might lead to icing If induction system icing 15 expected place the alternate air control in the ON position WARNING Flight in icing conditions is prohibited nless aircraft is equipped with the approved and complete Piper ice protection system see Supplement 6 Section 9 Hf icing is encoun tered immediate action should be taken to out of icing conditions Icing is hazardous due to greatly reduced performance loss of forward visibility pos
270. mpressor inlet Each engine cylinder is supplied with pressurized air in operation from sea level to maximum operating altitude The pressure relief valve protects the engine from inadvertently exceeding 42 inches Hg 40 inches Hg is manually set with the throttles The turbo bypass orifice is preset for 40 inches Hg at 12 000 feet density altitude at full throttle and 2600 RPM REPORT 1110 ISSUED JANUARY 8 1981 7 2 PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA DESCRIPTION amp OPERATION ery EN lA NN ae Nt EN RUIN The intake filter air box incorporates a manually operated two way valve designed to allow induction air cither to pass into the compressor through the filter or to bypass the filter and supply heated air directly to the turbocharger There is an automatic alternate air door which opens in the event that the primary air source becomes blocked Alternate air selection ensures induction air flow should the filter become blocked Since the air ts heated the alternate air system offers protection against induction system blockage caused by snow or freezing rain or by the freezing of moisture accumulated in the induction air filter Alternate air is unfiltered therefore it should not be used during ground operation when dust or other con taminants might enter the system The primary through the filter induction source should always be used for takeoffs The fuel injection system incorporat
271. my areas SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of the Pilot s Operating Handbook are necessary for this supplement REPORT VB H10 ISSUED JANUARY 8 1981 9 84 6 of 6 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA HE SUPPLEMENT 13 PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO 13 FOR RCA WEATHERSCOUT WEATHER RADAR SYSTEM SECTION I GENERAL This supplement supplies information necessary for the operation of the airplane when the optional RCA WeatherScout Weather Radar System is installed in accordance with FAA Approved Piper data The infor mation contained within this supplement is to be used in conjunction with the complete handbook This supplement has been FAA Approved and must remain in this handbook at all times when the optional RCA WeatherScout I Weather Radar System 1 installed FAA 0597 c WARD EVANS D O A NO SO I PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED JANUARY 8 1981 REPORT VB 1110 1 of 6 9 85 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 13 PA 34 220T SENECA SECTION 2 LIMITATIONS Do not operate the radar during refueling operations or in the vicinity of trucks or containers accommodating flammables or explosives Do not allow personne within 15 feet of area being scanned by antenna when system is transmitting SECTION 3 EMERGENCY PROCEDURES
272. n Revised para 3 3 Revised para 3 7 Changed pg nos Changed pg nos Revised para 4 5 Revised para 4 5 Revised para 4 5 Revised para 4 5 Revised para 4 5 Moved para 4 11 to pg 4 16 Relocated para 4 11 from pg 4 15 moved info to pg 4 16a New pg relocated info from pg 4 16 and 4 17 New pg relocated info and para 4 13 from pg 4 17 added Note to para 4 13 Moved info to pgs 4 16 and 4 166 relocated info irom pg 4 18 Moved info to pg 4 17 relocated info from pg 4 19 Moved info to pg 4 18 Revised para 4 31 added Note moved para 4 33 to pg 4 27 Relocated para 4 33 from pg 4 26 Added Note moved info to pg 4 33 Relocated info from pg 4 32 moved info to pg 4 24 PILOT S OPERATING HANDBOOK LOG OF REVISIONS cont FAA Approval Signature and Date Revision Number and Code Revised Description of Revision Pages Relocated info from pg 4 33 moved para 4 49 to pg 4 35 Relocated para 4 49 from pg 4 34 moved para 4 55 to pg 4 36 Reiocated para 4 55 from pg 4 35 moved info to pg 4 37 Relocated info from pg 4 36 moved para 4 59 to pg 4 38 New pg relocated para from pg 4 37 Changed pg nos Revised fig 6 9 Revised fig 6 11 Relocated items 147 thru 15 from pg 6 33 Moved items 147 thru 151 to pg 6 32 added new item 154 reloca
273. n Each mask assembly oxygen line incorporates flow indicator When the red pellet in the indicator disappears oxygen is flowing through the line normally the red indicator appears in any of the lines during a period when oxygen use is essential the airplane should be lowered toa sate altitude immediately When not in usc mask be stowed in the storage pockets behind the front and center seats Always remove fittings from the oxygen receptacles REPORT VB IH10 ISSUED JANUARY 8 1981 910 2of4 _ REVISED FEBRUARY 10 1984 PIPER AIRCRAFT CORPORATION SECTION 9 34 220 SENECA TH SUPPLEMENT 2 MARNE h EE EM MEME ML AL Lcx EA LH and stow the mask when they are not in use Hf the control knob is pulled on and the fitting is in the receptacle oxygen will flow through the mask con nuously Masks may be damaged if they are not properly stowed CAUTION Postively NO SMOKING while oxygen is being used by anyone in the aircraft To stop the flow of oxygen through the system the control knob should be pushed to the OFF position To bleed down low pressure lines it is recommended that the mask assembly be left connected to the outlet least three minutes after the control knob is turned off To preclude the possibility of fire by spontancous combustion oil grease paint hydraulic fluid and other flammable material should be kept away oxygen equipment SECTION 2 LIMITATIONS
274. n and all control surfaces in the neutral position Tow bar should be in the proper location and all entrance and baggage doors closed 6 Weigh the airplane inside a closed building to prevent errors in scale readings due to wind b Leveling 1 With airplane on scales block main gear oleo pistons in the fully extended position 2 Level airplane refer to Figure 6 3 deflating nose wheel tire to center bubble on level c Weighing Airplane Basic Empty Weight 1 With the airpalne level and the brakes released record the weight shown on each scale Deduct the tare if any from each reading Scale Reading Tare Scale Position and Symbol Nose Wheel Right Main Wheel Left Main Wheel Basic Empty Weight as Weighed WEIGHING FORM Figure 6 1 _ ISSUED JANUARY 8 1981 REPORT VB 1110 6 3 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 34 220T SENECA 4 Basic Empty Weight Center of Gravity 1 The following geometry applies to the PA 34 220T airplane when it is level Refer to Leveling paragraph 6 3 b Level Points Fuselage Left Side Below Window A 2253 The datum is 78 4 inches ahead of the 109 8 wing leading edge at the inboard edge of the inboard fuel tank LEVELING DIAGRAM Figure 6 3 2 The basic empty weight center of gravity as weighed including optional equipment full oil and unusable
275. n and in computing basic empty weight C G position and useful load Note that the useful load includes usable fuel baggage cargo and passengers Following this is the method for computing takeoff weight and C G 6 3 AIRPLANE WEIGHING PROCEDURES At the time of licensing Piper Aircraft Corporation provides each plane with the basic empty weight and center of gravity location This data is supplied by Figure 6 5 The removal or addition of equipment or airplane modifications can affect the basic empty weight and center of gravity The following is a weighing procedure to determine this basic empty weight and center of gravity location a Preparation 1 Be certain that all items checked in the airplane equipment list are installed in the proper location in the airplane 2 Remove excessive dirt grease moisture foreign items such as rags and tools from the airplane before weighing 3 Defuel airplane Then open ali fuel drains until all remaining fuel is drained Operate each engine until all undrainable fuel is used and engine stops Then add the unusable fuel 5 0 gallons total 2 5 gallons each wing REPORT VB 1110 ISSUED JANUARY 8 1981 6 2 REVISED AUGUST 9 1982 PIPER AIRCRAFT CORPORATION SECTION 6 PA 34 220T SENECA WEIGHT AND BALANCE 4 Fill with oil to full capacity 5 Place pilot and copilot seats in fourth 4th notch aft of forward position Put flaps in the fully retracted positio
276. n causing the date to flash then press the start stop ST SP button to advance to the correct date To set the correct hour press the RST button two times causing the hours digits to flash Press the ST SP button to advance to the correct hour The minutes can now be set by pressing the RST button once again and causing the minutes digits to flash Set the minutes to the next minute to come up at the zero seconds time mark and depress the RST button to hold the time displayed At the time mark press the ST SP button momentarily to begin time counting at the exact second If the minutes are not advanced when they are flashing in the set mode pressing the RST button will return the clock to the normal timekeeping mode without altering the minutes timing This feature is useful when changing time zones when only the hours are to be changed The calender function will automatically advance the date correctly according to the four year perpetual calendar One day must be added manually on February 29 on leap year The date advances correctly at midnite To display a test function press both the RST and ST SP buttons at the same time ISSUED JANUARY 8 1981 REPORT VB 1110 7 39 TABLE OF CONTENTS SECTION 8 AIRPLANE HANDLING SERVICING AND MAINTENANCE Paragraph 8 1 8 1 8 3 Airplane Inspection nn 8 2 8 5 Preventive Maintenance m 8 3 8 7 Airplane Alterations
277. n the set the DME frequency pairing selector ta NI ib Turn the DME on ic FREQUENCY SELECTION 1 MANUAL Set KBD NAV 1 selectoron 1 Set in frequency of the reference VOR DME station 2 KEYBOARD Set KBD NAV 1 COM I selector on NAV to Set in the frequency of VOR DME station from the kevboard on the NP 2041A Set the mode selector on the NP 2041A to VOR a Set the display selector on the NP 2041A to SBY Address Standby Waypoint 1 by pressing the SBY WPT key and gt the 21 kev i REPORT 110 ISSUED JANUARY 8 1981 9 60 2 of 6 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA HI SUPPLEMENT 8 MUW Program Waypoint I parameters any sequence 1 2 3 4 5 NOTE Pressing the FREQ DST EL or CRS keys causes a flashing dot to appear in the asso ciated display window A flashing dot indicates the parameter that is being addressed As number keys corresponding to data are pressed the numbers appear in the addressed window If valid data is entered into the window the flashing dot will extinguish when the ENTER key is pressed If invalid data is entered in the window the data will be rejected when the ENTER key 1 pressed and the window will revert to a flashing dot which indicates data should be re entered STATION FREQUENCY Press FREQ key
278. ndshield panel heated lift detectors and heated pitot head A single system or any combination of systems may be installed However the warning placard specified in Section 2 of this supplement is required Such a placard is also required if any system is inoperative The pneumatic wing and empennage boots are installed on the leading edges of the wings the vertical stabilizer and the horizontal stabilator During normal operation when the surface deicer system is off the engine driven pneumatic pumps apply a constant suction to the deicer boots to provide smooth streamlined leading edges Deicer boots are inflated bya momentary ON type SURFACE DE ICE switch Figure 9 3 located on the instrument panel to the right ofthe control quadrant Actuation of the surface deice switch activates a system cycle timer that energizes the pneumatic pressure control valves until the system pressure reaches 17 psi or until 6 seconds is reached The boot solenoid valves are activated and air pressure is released to the boots inflating all surface deicers on the airplane A green indicator light illuminates when the wing tail deicer surface boots are inflated above 8 psi The light also incorporates a press to test and turn to dim feature When the cycle is complete the deicer solenoid valves permit automatic overboard exhaustion of pressurized air Suction is then reapplied to the deicer boots The deicer boots do not inflate during the press to
279. ne must be ON and the fuel selector of the inoperative engine OFF The AUX fuel pump of the operating engine should be OFF 3 13 ENGINE DRIVEN FUEL PUMP FAILURE Should a malfunction of the engine driven fuel pump occur the auxiliary fuel pump system can supply sufficient fuel pressure for engine power up to approximately 7567 Any combination of RPM and Manifold Pressure defined on the Power Setting Fable be used but leaning may be required for smooth operation at altitudes above 15 000 feet or for RPM s below 2300 Normal cruise descent and approach procedures should be used REPORT 1110 ISSUED JANUARY 8 1981 3 18 REVISED APRIL 9 1982 PIPER AIRCRAFT CORPORATION SECTION 3 PA 34 220T SENECA HI EMERGENCY PROCEDURES PRD M AAR Loss of fuel pressure and engine power can be an indication of failure of the engine driven fuel pump Should these occur and engine driven fuel pump failure is suspected retard the throttle and unlatch the auxiliary pump and select the HI position The throttle can then be reset at 750 power or below CAUTIONS If normal engine operation and fuel flow is not immediately re established the auxiliary fuel pump should be turned off The lack of a fuel flow indication while on the Hl auxiliary fuel pump position could indicate a leak in the fuel system or fuel exhaustion Actuate the auxiliary fuel p
280. ned frozen on indicator Video display in order to evaluate the significance Scan of storm cell movement Depressing for a second time reveals direction and distance of target movement during hold period During HOLD mode the antenna continues to scan and the display will continue to be presented as long as power is supplied to the system The word HOLD will be flashing L ______ i TILT Electrically adjusts the antenna to move the radar beam to 15 degrees up or down from Antenna ilt horizontal 0 position Control BRT Control CRT picture intensity Brightness Control NENNEN n CONTROL FUNCTIONS AND OPERATION cont Table 4 3 cont REPORT VB 1110 ISSUED JANUARY 8 1981 9 94 4046 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 14 M M a E T a a i rr i a a ei ttt t T T T T eH Tee A RADAR 160 WEATHER RADAR SYSTEM Range Switch Position Range Range Mark Readout 40 10 5 5 1 10 10 2 20 20 4 40 40 10 80 80 20 160 160 40 Wx MAP Wx Switch Position Mode Readout Wx Wx MAP MAP WxA WXxA When the HOLD pushbutton is initially depressed the MODE READOUT displays flashing HOLD The MODE READOUT displays TEST ALPHANUMERIC READOUT Table 4 5 b GENERAL OPERATING PRECAUTIONS WARNING Do not operate the rad
281. ng Example outlines a detailed flight plan using the performance charts in this section Each chart includes its own example to show how it is used WARNING Performance information derived by extrapo lation beyond the limits shown on the charts should not be used for flight planning purposes REPORT 1110 ISSUED JANUARY 8 1981 5 2 PIPER AIRCRAFT CORPORATION SECTION 5 PA 34 220T SENECA PERFORMANCE POE 55 FLIGHT PLANNING EXAMPLE a b Aircraft Loading The first step in planning the flight is to calculate the airplane weight and center of gravity by utilizing the information provided bv Section 6 Weight and Balance of this handbook The basic empty weight for the airplane as licensed at the factory has been entered in Figure 6 5 If any alterations to the airplane have been made effecting weight and balance reference to the aircraft logbook and Weight and Balance Record Figure 6 7 should be made to determine the current basic empty weight of the airplane Make use of the Weight and Balance Loading Form Figure 6 11 and Range and Weight graph Figure 6 15 to deter mine the total weight of the airplane and the center of gravity position The landing weight cannot be determined until the weight ofthe uel to be used has been established refer to gX1 D Basic Empty Weight 3122 lbs 2 Occupants 2 x 170 lbs 340 ibs 3 Baggage and Cargo 27
282. ng and distance definitions are then set into the ANS 351 Set up the rest of the desired waypoints as described above Press the RTN return pushbutton to display the active waypoint 2 Changing Waypoints In Flight To change a waypoint in flight rotate the waypoint selector until the desired waypoint number and coordinates are dis played on the ANS 351 b C gt SECTION 5 Verify that the waypoint definition is correct by comparing the display with the plan Uncouple the autopilot if tracking RNAV deviation Select the desired reference facility frequency on the associated NAV receiver Depress the USE pushbutton and note that the waypoint identification number stops winking Select the desired course on OBS Recouple the autopilot after deviation and distance to waypoint indications have stabilized PERFORMANCE No changes to the basic performance provided by Section 5 of this Pilot s Operating Handbook are necessary for this supplement ISSUED JANUARY 8 1981 REPORT VB 1110 5 of 6 9 69 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 9 PA 34 220T SENECA Ili THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED JANUARY 8 1981 9 70 6 of 6 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA HI SUPPLEMENT 16 PILOT S OPERATING HANDBOOK i AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO 10 FOR KING KNS 86 NAVIGATION SY
283. ngine occurs during takeoff ground roll and 85 KHAS has not been attained CLOSE both throttles immediately and stop straight ahead If inadequate runway remains to stop close the throttles and apply maximum braking The battery switch and fuel selectors should be turned OFF Continue path straight ahead turning to avoid obstacles as necessary REPORT VB 1110 ISSUED JANUARY 8 1981 3 14 PIPER AIRCRAFT CORPORATION SECTION 3 P 4 34 220T SENECA IH EMERGENCY PROCEDURES ENGINE FAILURE DURING TAKEOFF 85 KIAS OR ABOVE If engine failure occurs during takcotf ground roll or after lift off with the gear still down and 85 KIAS has been attained the course of action to be t ken will depend on the runway remaining adequate runway remains CLOSE both throttles immediately land 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 judgment considering loading density altitude obstruc tions the weather and the pilot s competence If the decision is made to continue the takeoff maintain heading and airspeed When climb 15 estab lished RETRACT the landing gear accelerate to 92 1 5 and FEATHER the inoperative engine refer to Engine Securing Procedure WARNING In certain combinations of aircraft weight configuration ambient conditions and speeds negative climb performance may
284. ngle of Bank 5 13 7 Normal Procedure 5 14 9 This Figure Intentionally Left Blank 5 15 11 Maximum Effort Takeoff 25 Flaps 5 16 3 Accelerate and Stop Distance 0 5 17 15 Accelerate and Stop Distance 25 Flaps 5 18 17 Takeoff Climb Performance Gear 5 19 19 Takeoff Climb Performance Gear Retracted 5 20 21 Climb Performance Gear Retracted Maximum Continuous sehn 5 2 5 03 Fuel Time and Distance to 5 22 5 25 Power Setting Table 5 23 5 27 Speed Cruise Power 5 24 5 29 Range Cruise Power 93 Gallons Usable 5 25 5 31 Range Cruise Power 123 Gallons Usable 5 26 5 33 Endurance 93 Gallons 5 27 5 35 Endurance 123 Gallons Usable 5 28 5 37 Fuel Time and Distance to Descend 5 29 5 39 Landing Distance Normal 5 30 5 41 Landing Distance Short Field Effort 5 31 ISSUED JANUARY 8 1981 REPORT 1110 REVISED SEPTEMBER 23 1983 5 9 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 34 220T SENECA THIS PAGE INTENTIONALLY LEFT BLANK REPORT 1110 ISSUED JANUARY 8
285. ning horn will sound at low throttle settings if the gear is not down and locked The light is off when the landing gear is in either the full down and locked or ful up positions Prior to entering the traffic pattern the aircraft should be slowed to approximately 120 KIAS and this speed should be maintained on the down wind leg The landing check should be made on the downwind leg The seat backs should be erect and the seat belts and shoulder harnesses should be fastened NOTE if the fixed shoulder harness non inertia reel type is installed must be connected to the seat belt and adjusted to allow proper accessi bility to all controls including fuel selectors flaps trim etc while maintaining adequate restraint for the occupant If the inertia reel type shoulder harness ts installed a pull test of its locking restraint feature should be performed Both fuel selectors should be ON and the cow flaps should be set as required The auxiliary fuel pumps should be OFF Set the mixture and propeller controls Select landing gear DOWN and check for three green lights on the pane and look for the nose wheel in the nose wheel mirror The landing gear should be lowered at speeds below 130 KIAS and the flaps at speeds as follows 10 first notch 140 KIAS maximum 25 second notch 122 KIAS maximum 40 third notch 115 KIAS maximum REPORT VB 1110 ISSUED JANUARY 8 1981 4 32 REVISED AUGUST 17 1981 PIPER AIRCRAFT
286. nstalled the left engine is established as the master engine and the right engine is equipped with a slave governor which automatically maintains its RPM with the left engine RPM When the propeller synchrophaser is installed a three position switch is located on the throttle quadrant below the propeller controls It is labeled OFF for manual control and 1 or 2 for propeller synchrophaser A blue press to test light which illuminates when the propellers are out of synchronization is located below the switch SECTION 2 LIMITATIONS Placards On the throttle quadrant below engine and propeller controls USE OFF POSITION FOR TAKEOFF LANDING AND SINGLE ENGINE OPER ATIONS SECTION 3 EMERGENCY PROCEDURES The propeller synchrophaser must be in the OFF position for all single engine operations SECTION 4 NORMAL PROCEDURES During taxi takeoff landing or single engine operations the propeller synchrophaser switch should be in the OFF position The press to test light below the switch will illuminate while the propellers are out of synchronization whether the switch is in the OFF 1 or 2 position When the switch is in the OFF position the propellers can be synchronized manually and the light will go out when propeller synchronization 15 complete For automatic synchronization the propellers should be syn chronized manually to within approximately 10 RPM and the switch placed in the I posi
287. nt close out panel refer to Figure 7 23 Air from the heater is ducted forward along the cabin floor to outlets at each seat and to the windshield area Operation of the combustion heater is controlled by a three position switch located on the control console Figure 7 25 between the front seats and labeled FAN OFF and HEATER Airflow and temperature are regu lated by the two levers on the console The right hand lever regulates air intake and the left hand lever regulates cabin temperature Cabin comfort can be maintained as desired through various combinations of lever positions Passengers have secondary control over heat output by individ ually adjustable outlets at each seat location For cabin heat the air intake lever on the heater control console must be partially or fully open and the three position switch set to the HEATER position This simultaneously starts fuel flow and ignites the heater and during ground operation it also activates the ventilation blower which is an integral part of the combustion heater With instant starting and no need for priming heat should be felt within a few seconds When cabin air reaches the temperature selected on the cabin temperature lever ignition of the heater cycles automatically to maintain the selected temperature Two safety switches activated by the intake valve and located aft of the heater unit prevent both fan and heater operation when the air intake lever is in the closed position
288. nt of the landing gear hydraulic reservoir is located behind a panelinthe reartop of the nose baggage compartment Brake fluid should be maintained at the level marked on the reservoir For further information see Brake Service in the Handling and Servicing Section of this handbook ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED FEBRUARY 10 1984 7 11 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA M The parking brake knob is located on the lower left instrument panel To set the parking brake first depress and hold the toe brake pedals and then pull out the parking brake knob To release the parking brake first depress and hold the toe brake pedals and then push in on the parking brake knob WARNING No braking will occur if knob is pulled prior to brake application 7 43 FLIGHT CONTROL SYSTEM Dual flight controls are installed in the Seneca HI as standard equip ment The controls actuate the control surfaces through a cable system The horizontal tail surface stabilator is of the ali movable slab type with an anti servo tab mounted on the trailing edge This tab actuated by a control mounted on the console between the front seats also acts as a longitudinal trim tab refer to Figure 7 9 The ailerons are of the Frise type This design allows theleadingedge of the aileron to extend into the airstream to provide increased drag and improved roll co
289. ntrol The differential deflection of the ailerons tends to eliminate adverse yaw in turning maneuvers and to reduce the amount of coordination required in normal turns The vertical tail is fitted with a rudder which incorporates a combination rudder trim and anti servo tab The rudder trim control is located on the control console between the front seats The flaps are manually operated and spring loaded to return to the retracted position A four position flap control lever Figure 7 9 between the front seats adjusts the flaps for reduced landing speeds and glide path control The flaps have three extended positions 10 25 and 40 degrees as well as the fully retracted position A button on the end of the lever must be depressed before the control can be moved A past center lock incorporated in the actuating linkage holds the flap when it is in the retracted position so REPORT VB 1110 ISSUED JANUARY 8 1981 7 12 REVISED FEBRUARY 10 1984 PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA DESCRIPTION amp OPERATION CONSOLE Figure 7 9 that it may be used as a step on the right side Since the flap will not support a step load except in the fully retracted position the flaps should be retracted when people are entering or leaving the airplane 7 15 FUEL SYSTEM Fuel is stored in fuel tanks located in each wing The tanks in each wing are interconnected to function as a single tank refer to Figure 7 11 Al
290. ode is selected the AUTOPILOT WILL DISCONNECT and warning horn will sound Pilot may use Flight Director steering for miss d approach guidance After aircraft is stabilized in a proper climb with gear and flaps up the autopilot may be re engaged and will retain G A mode Autopilot only no Flight Director versions do not have a switch If glide slope coupling is not desired while operating on the localizer use NAV or REV mode instead of APPR mode ISSUED APRIL 21 1981 REPORT VB 1110 5 of 12 9 117 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 18 PA 34 220T SENECA CAUTION Refer to Edo Aire Mitchell Century 41 Operator s Manual P N 685803 dated 1 79 for additional System Description and Normal Operating Procedures b PREFLIGHT PROCEDURES NOTE During system functional check the system must be provided adequate D C voltage 12 0 VDC min and instrument air 4 2 in Hg min is recommended that one engine be operating minimum to provide the necessary power and that the aircraft be positioned in a level attitude during the functional check 1 AUTOPILOT F D Switch ON if F D Equipped a Engage autopilot by pushing programmer OFF ON switch b Rotate D G HDG bug left then right and verify that control wheel movement corresponds to HDG command input c Press pitch modifier button first up then down and note that pitch control follows pitch command input Autotrim should follow p
291. of 4 9 55 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 7 PA 34 220T SENECA HI 2 The function of the synchrophaser is to maintain both propellers at the same RPM and at a selected phase angle This eliminates the propeller beat effect and minimizes vibration When the synchrophaser is installed the left engine is established as the master engine and the right engine is equipped with a slave governor which automatically maintains its RPM with the left engine RPM When the propeller synchrophaser is installed a rotary switch is located on the throttle quadrant below the propeller controls is labeled OFF for manual control or standby and PHASE ADJUSTMENT for propeller synchronizing and phase angle adjustment SECTION 2 LIMITATIONS Placards On the throttle quadrant below engine and propeller controls USE OFF POSITION FOR TAKEOFF LANDING AND SINGLE ENGINE OPER ATIONS SECTION 3 EMERGENCY PROCEDURES The propeller synchrophaser must be in the OFF position for ali single engine operations SECTION 4 NORMAL PROCEDURES The rotary switch must be in the OFF position during taxi takeoff landing and single engine operations Before operating the synchrophaser system ensure that the rotary switch isin the OFF position and manually synchronize the propellers to within 40 RPM To operate rotate the switch clockwise out of the OFF detent and slightly into the PHASE ADJUST MENT range It may require up to 30 seconds
292. of trucks or containers accommodating flammables explosives do not allow personnel within 15 feet of area being scanned by antenna when system 15 transmitting 2 Flash bulbs can be exploded by radar energy 3 Since storm patterns are never stationary the display is constantly changing and continued observation is always advisable where areas of turbulence prevail REPORT 1110 ISSUED JANUARY 8 1981 9 88 4 of 6 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 13 SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of the Pilot s Operating Handbook are necessary for this supplement ISSUED JANUARY 8 1981 REPORT VB 1110 5 of 6 9 89 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 13 PA 34 220T SENECA ee a LL THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED JANUARY 8 1981 9 90 6of6 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 14 PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO 14 FOR BENDIX RDR 160 MONOCHROME WEATHER RADAR SYSTEM SECTION 1 GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Bendix RDR 160 Monochrome Weather Radar System is installed in accordance with FAA Approved Piper data The information contained within this supplement is to be used in conjun
293. off at any time by depressing the ALT switch ALT engagement is displayed on the annunciator panel NOTE The Vertical Trim switch located on the Mode Controller may be used to change or trim the command altitude up or down at 500 to 700 FPM without disengaging the mode The new pressure altitude that exists when the switch is released will then be held ISSUED APRIL 21 1981 REPORT 1110 11 of 16 9 29 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 4 PA 34 220T SENECA 9 30 5 6 RUIN Heading HDG Set the heading bug to the desired heading on the depress the HDG switch on the Mode Controller and HDG will be displayed on the annunciator panel The FDI and or will command a turn to the heading selected The pilot may then choose any new heading by merely setting the bug on a new heading The FDI and or AP will automatically command a turn in the direction of the new setting To disengage the HDG mode depress the HDG switch on the Mode Controller and observe the HDG light go out on the annunciator The HDG mode will automatically disengage when APPR or NAV CPLD is achieved Navigation Mode NAV The Navigation mode may be selected by tuning the NAV receiver to the desired frequency setting the CDI to the desired radial and depressing the NAV switch on the Mode Controller The annunciator will indicate NAV ARM until ca
294. ollins ANS 351 Area Navigation Computer is installed FAA WARD EVANS D O A NO 50 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED JANUARY 8 1981 REPORT VB 1116 1 of 6 9 65 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 9 _ 34 220 SENECA SECTION 2 LIMITATIONS changes to the basic limitations provided by Section 2 of this Pilot s Operating Handbook are necessary for this supplement SECTION 3 EMERGENCY PROCEDURES No changes to the basic Emergency Procedures provided by Section 3 of this Pilot s Operating Handbook are necessary for this supplement SECTION 4 NORMAL PROCEDURES AMBIENT LIGHT SENSOR DISTANCE WAYPOINT NUMBER _ RADIAL ENR APPR DISTANCE SELECTOR RADIAL SELECTOR RETURN BUTTON MODE CONTROL WAYPOINT USE CHECK SELECTOR BUTTON BUTTON displays ANS 351 AREA NAVIGATION COMPUTER CONTROLS AND INDICATORS REPORT VB 1110 ISSUED JANUARY 8 1981 9 66 2 of 6 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA Il SUPPLEMENT 9 O EPUM UNO UU ML a CONTROI S CONTROL INDICATOR Mode Contro Wavpoint Selector Return Button Use Button Radial Selector i HAIR RU FUNCTION 8 gr Ar a M Selects ENR enroute or APPR approach modes of operation In
295. on for baggage 5 Occupants in front 2 in middle 2 in rear Load forward baggage to capacity first Rear baggage and or fuel load may be limited by aft envelope 6 Occupants 2 in front 2 in middle 2 in rear With six occupants fuel and or baggage may be limited by envelope load forward baggage compartment to capacity first ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED FEBRUARY 25 1982 6 9 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 34 220T SENECA S a aa NU a a 7 Occupants 2 in front 3 in middle 2 in rear With seven occupants fue and or baggage may be limited by envelope For all airplane configurations it is the responsibility of the pilot in command to make sure that the airplane always remains within the allowable weight vs center of gravity envelope while in flight 6 9 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT a Add the weight of all items to be loaded to the basic empty weight b Use the Loading Graph Figure 6 13 to determine the moment of all items to be carried in the airplane c Add the moment of all items to be loaded to the basic empty weight moment d Divide the total moment by the total weight to determine the C G location e By using the figures of item a and item d above locate a point on the C G range and weight graph Figure 6 15 If the point falls within the C G envelope the loading meets the weight and bal
296. on the tail support CAUTION Be sure to apply sufficient support ballast otherwise the airplane may tip forward and the nose section could be damaged Landing gear oleos should be serviced according to instruction on the units Under normal static load empty weight of airplane plus full fuel and oil main oleo struts should be exposed approximately 3 20 inches and the nose oleo strut should be exposed 2 50 inches Refer to the Service Manual for complete information on servicing oleo struts REPORT VB 1110 ISSUED JANUARY 8 1981 8 8 REVISED FEBRUARY 10 1984 PIPER AIRCRAFT CORPORATION SECTION 8 PA 34 220T SENECA Ili HANDLING SERV amp MAINT BRAKE FLUID RESERVOIR PARKING BRAKE HANDLE BRAKE CYLINDERS BRAKE LINES PARKING BRAKE VALVE BRAKE ASSEMBLY 1 2 3 4 5 BRAKE SYSTEM Figure 8 1 ISSUED JANUARY 8 1981 REPORT 1110 8 9 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING SERV amp MAINT PA 34 220T SENECA er ee a t P e e TH a a TIT T a rr a tratta A 8 17 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 cvlinder will increase about one third psi for every degree Fahrenheit increase in temperature This effect should be considered when checking pressure The charge maintained must be accurate and free of excessive moisture since moisture may freeze the piston
297. or but with increased travel Rudder effectiveness is increased by an anti servo tab on the rudder 7 5 ENGINES The Seneca is powered by two Teledyne Continental six cylinder turbocharged engines each rated at 200 horsepower at 2600 RPM maximum continuous at sea level and 220 horsepower at 2800 RPM takeoff power for five minutes The engines are air cooled and fuel injected and are equipped with oil coolers with low temperature bypass systems and engine mounted oil filters A winterization plate is provided to restrict air during winter operation See Winterization in Handling and Servicing Section Asym metric thrust during takeoff and climb is eliminated by the 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 engines are accessible through removable panels one on either side of each engine cowling Engine mounts are constructed of steel tubing and dynafocal engine mounts are provided to reduce vibration A Ray Jay turbocharger on each engine is operated by exhaust gases Exhaust gases rotate a turbine wheel which inturn drives an air compressor Induction air is compressed supercharged and distributed into the engine air manifold and the exhaust gases which drive the compressor are dis charged overboard Engine induction air is taken from within the cowling is filtered and is then directed into the turbocharger co
298. or adequate air supply 4 2 in Hg min 2 Check compass circuit breaker 3 Observe display for proper operation ISSUED FEBRUARY 10 1984 REPORT 1119 3 of 20 9 137 SECTION 9 PIPER AIRCRAFT CORPORA TION SUPPLEMENT 21 PA 34 220T SENECA Til e a a tA T MET Y b To disable heading card pull circuit breaker and use magnetic compass for directional data NOTE if heading card is not operational autopilot should not be used c With card disabled VOR Localizer and Glide Slope displays are still functional use card set to rotate card to aircraft heading for correct picture d Slaving Failure i e failure to self correct for gyro drift 1 Check gyro slaving switch is set to No 1 position if equipped with Slave No I No 2switch or SLAVED position when equipped with Slaved and Free Gyro Mode Switch 2 Check for HDG Fiag 3 Check compass circuit breaker 4 Reset heading card while observing slaving meter NOTE Dead slaving meterncedle needle displaced fully one direction indicates a slaving system failure S Select slaving amplifier No 2 equipped 6 Reset heading card while checking slaving meter If proper slaving indication is not obtained switch to free gyro mode and periodically set card unslaved gyro In the localizer mode the TO FROM arrows may remain out of view depending upon the design of the NAV converter used in the instal lation
299. or output indications should decrease Turn the battery switch ON Should the alternator output indications not decrease leave the battery switch and land as soon as practical electrical load is being supplied by the alternators Also anticipate complete electrical power failure NOTE Operation with the alternator ON and the battery switch OFF should be made only when required by electrical failure due to increased system voltage and radio frequency noise ISSUED JANUARY 8 1981 REPORT 1110 REVISED AUGUST 9 1982 3 21 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROC EDURES PA 34 2207 SENEC A S 34 8333001 AND UP if an ALT annunciator fight iluminates check the output of cach alternator individually using the prss to test buttons located on either side of the ammeter to determine which alternator is inoperative 1f both alternators show zero output reduce electrical loads to the minimum Turn OFF both alternator switches and then turn them momentarily ON one ata time while observing alternator output The alternator showing the LEAST but not zero current should be turned ON The other alternator should be left OFF Electrical loads may be reinstated as required to a maximum of 60 amperes both alternator outputs cannot be restored both alternator witches should be left Reduce the electrical load to essential systems and land as soon as practical The battery is the only remaining source o
300. orm 240 0010 ENCLOSED WITH THIS HANDBOOK For 1982 and preceding models only For 1983 and subsequent models only REPORT VB 1110 6 i PIPER AIRCRAFT CORPORATION SECTION 6 PA 34 220T SENECA HI WEIGHT AND BALANCE SECTION 6 WEIGHT AND BALANCE 6 4 GENERAL In order to achieve the performance and flying characteristics which are designed into the airplane it must be flown with the weight and center of gravity C G position within the approved operating range envelope Although the airplane offers flexibility of loading it cannot be flown with the maximum number of adult passengers full fuel tanks and maximum baggage With the flexibility comes responsibility The pilot must insure that the airplane is loaded within the loading envelope before a takeoff Misloading carries consequences for any aircraft An overloaded air plane will not take off climb or cruise as well as a properly loaded one The heavier the airplane is loaded the less climb performance it will have Center of gravity is a determining factor in flight characteristics If the C G is too far forward in any airplane it may be difficult to rotate for takeoff or landing If the C G is too far aft the airplane may rotate prematurely on takeoff or tend to pitch up during climb Longitudinal stability will be reduced This can lead to inadvertent stalls and even spins and spin recovery becomes more difficult as the center of gravity moves aft o
301. osition on top of mounting base J ensuring that all mounting lugs engage in the slotted receptacle and that the locking pin is in the raised position d Turn on oxygen system and check flow indicators on all masks Masks for the two aft seats are stowed in the seat pockets of the middle seats All other masks are stowed in the oxygen system containers REPORT VB 1110 ISSUED JANUARY 8 1981 9 6 4of6 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA HT SUPPLEMENT 1 IN FLIGHT a Adjust oxygen mask b Turn on system c Monitor flow indicators and quantity CAUTION Use of oxygen unit is prohibited when gauge approaches red area SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of this Pilot s Operating Handbook are necessary for this supplement ISSUED JANUARY 8 1981 REPORT VBR 1110 5 of 6 9 7 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT _ 34 220 SENECA THiS PAGE INTENTIONALLY LEFT BLANK REPORT 1110 ISSUED JANUARY 8 1981 9 8 6046 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA HI SUPPLEMENT 2 MEER M REPE PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO 2 FOR FIXED OXYGEN SYSTEM INSTALLATION SCOTT AVIATION PRODUCTS AMBASSADOR MARK IH PART NUMBERS 36960 3 87441 2 SECTION 1 GENERAL This supplement supplies information necessar
302. ot s Operating Handbook are necessary for this supplement ISSUED APRIL 21 1981 REPORT VB 1110 REVISED AUGUST 17 1981 3 of 4 9 105 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 16 34 2207 SENECA THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED APRIL 21 1981 9 106 4014 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 200T SENECA IH SUPPLEMENT 17 SUPPLEMENT 17 CENTURY 21 AUTOPILOT INSTALLATION SECTION 1 GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Century 21 Autopilot is installed in accordance with STC SA3384SW D The information contained within this supplement is to be used in conjunction with the complete handbook This supplement has been FA A Approved as a permanent part of this handbook and must remain in this handbook at all times when the optional Century 21 Autopilot is installed FAA kBpROVED o o WARD EVANS D O A NO 80 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED APRIL 21 1981 REPORT 1110 1 of 6 9 107 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 17 PA 34 220T SENECA ee A A SECTION 2 LIMITATIONS a Maximum airspeed for autopilot operation is 180 KIAS Autopilot VMO b Autopilot OFF during takeoff and landing c Autopilot coupled approaches prohibited with more than one notch 10 flap extended SECTION 3 EMERGENCY PROCED
303. ource of heat from the sump to the upper part of the engine Start engine immediately after completion of the preheating process Since the engine will be warm use normal starting procedure NOTE Since the oil in the oil pressure gauge line may be congealed as much as 60 seconds may elapse before oil pressure is indicated If oil pressure is not indicated within one minute shut the engine down and determine the cause ISSUED JANUARY 8 1981 REPORT VB 1116 4 23 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA 34 220T SENECA rr a a Ra a im e nner a PARANT A trap a a re e a tte a LALLA TT e Operate the engine at 1000 RPM until some 01 temperature 15 indicated Monitor pressure closely during this time and be alert for a sudden increase or decrease Retard throttles if necessary to maintain oil pressure below 100 psi If oil pressure drops suddenly to less than 30 psi shut down the engine and inspect lubrication system If no damage or leaks are noted preheat the engine for an additional 10 to 15 minutes before restarting 427 WARM UP Warm up the engines at 1000 to 1200 RPM Avoid prolonged idling at low RPM as this practice may result in fouled spark plugs Takeoff may be made as soon as the ground check is completed pro vided that the throttles may be opened fully without backfiring or skipping and without a reduction in engine oil pressure Do not operat
304. oxygen masks Each console is equipped with a 22 cubic foot oxygen cylinder an oxygen supply gauge an ON OFF flow control knob and two plug in receptacles Two single supply line masks and two dual supply line masks which utilize dual manifold connectors are provided to supply six masks with only four outlets Each cylinder is enclosed in a console carrying case with a separate supply gauge and ON OFF flow control knob mounted on the sloped face of each unit Two plug in outlets are mounted below the gauge and control knob on each console The masks for the rear seats are stowed in the pockets on the center seats and all other masks are stowed in the consoles When fully charged each cylinder contains oxygen ata pressure of 1850 psi at 70 the filler port is enclosed by a cover at the rear of each unit If high altitude flight is anticipated it should be determined that the oxygen supply is adequate for the proposed flight and that the passengers are briefed When oxygen is required insert the mask plug in connector into an outlet and lock by rotating the connector approximately 1 4 turn Don mask s and rotate the ON OFF control knob fully counterclockwise approximately two full turns Each mask assembly oxygen line incorporates a flow indicator When the red pellet in the indicator disappears oxygen is flowing through the line normally If the red indicator appears in any of the lines during a period when oxygen is essential t
305. persist Takeoff should not be attempted with ice or frost on the wings Takeoff distances and 50 foot obstacle clearance distances are shown on charts in the Performance Section of this handbook The performance shown on charts will be reduced bv uphill gradient tailwind component or soft wet rough or grassy surface or poor pilot technique Avoid fast turns onto the runway followed by immediate takeoff especially with a low fuel supply Fast taxi turns immediately prior to takeoff run can cause temporary malfunction of one engine on takeoff As power 15 applied at the start of the takeoff roll look at the engine instruments to see that the engines are operating property and putting out normal power and at the airspeed indicator to see that it is functioning Apply throttle smoothly until 40 in Hg manifold pressure is obtained DO NOT APPLY ADDITIONAL THROTTLE The flap setting for normal takeoff is O In certain short field takeoff efforts when the shortest possible ground roll and the greatest clearance distance over a 50 ft obstacle is desired flap setting of 25 is recom mended ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 17 1981 4 27 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA 34 220T SENECA Ili When obstacle clearance no problem normal flaps up 0 mav be used Apply and hold the brakes Sct the flaps to the up 0 position Release the brakes accelerate ta 79
306. pture of the selected course unless the NAV switch is engaged with wings level and a centered needle on the CDI Then the mode will go directly to NAV CPLD as displayed on the annunciator panel The system can intercept at any angle up to 90 and will always turn toward the course pointer If a condition requiring a capture exists at mode engagement the pilot is required to set up intercept angle using either or FD mode may be disengaged by depressing the NAV switch or by engaging HDG when in NAV CPLD or engaging APPR when in PNAN CPLD or NAV ARM UTION The NAV mode of operation will continue to provide airplane commands and or controi without a valid VOR LOC signal NAV flagin view Also erroneous navigation information may result from COMM radio interference with the NAV radio This erroneous infor mation may cause premature NAV captures as well as erroneous steering information Should this occur reselect HDG mode and then reselect NAV mode REPORT VB H10 ISSUED APRIL 21 1981 12 of 16 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA HI SUPPLEMENT 4 7 8 Approach Mode The Approach mode may be selected by tuning the NAV receiver to the desired VOR or LOC frequency setting the CDI to the desired radial or inbound heading and depressing the APPR switch on the Mode Controller The annunciator will indicate APPR ARM until the course is captured unless the A
307. r dealers and distributors A service manual parts catalog and revisions to both are available from Piper dealers or distributors Any correspondence regarding the airplane should include the airplane model and serial number to ensure proper response 8 3 AIRPLANE INSPECTION PERIODS The Federal Aviation Administration FAA occasionally publishes Airworthiness Directives ADs that apply to specific groups of aircraft are mandatory changes and are to be complied with within a time limit set the When an AD is issued it is sent by the FAA to the latest registered owner of the affected aircraft and also to subscribers of their service The owner should periodically check with his Piper dealer or A amp P mechanic to see whether he has the latest issued AD against his aircraft The Owner Service Agreement which the owner receives upon delivery of the aircraft should be kept in the aircraft at all times This identifies the ow ner to authorized Piper dealers and entitles the owner to receive service in accordance with the regular service agreement terms This agreement also entitles the transient owner full warranty by any Piper dealer in the world One hundred hour inspections are required by law if the aircraft is used commercially Otherwise this inspection is left to the discretion of the owner This inspection is a complete check of the aircraft and its systems and should be accomplished by a Piper Authorized Servic
308. r 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 Ground operation should be limited to 3 minutes maximum to avoid damaging the heating elements SECTION 2 LIMITATIONS a Equipment required for flight into known or forecast icing 1 Pneumatic wing and empennage boots 2 Wing ice detection light 3 Electrothermal propeller deice pads on the propeller blades 4 Electrothermal windshield panel 5 Heated lift detectors 6 Heated pitot head 7 Propeller spinners if ali the equipment listed above is not operative or not installed the following placard must be installed in full view of the pilot b WARNING THIS AIRCRAFT 15 NOT APPROVED FOR FLIGHT IN ICING CONDITIONS REPORT VB 1110 ISSUED JANUARY 8 1981 9 50 6 of 10 REVISED AUGUST 17 1981 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA III SUPPLEMENT 6 m A SECTION 3 EMERGENCY PROCEDURES The malfunction of any required deice equipment requires immediate action to avoid icing conditions ENGINE FAILURE IN ICING CONDITIONS Select alternate air and attempt restart unable to restart engine lop DYOD Acdece fo Neg Sa n bt i ab ON eter e aU ae pian feather 2 above 92 KIAS Descend if necessary to maintain airspeed Electrical load ct oe
309. rative engine Throttle of inop retard to verify REPORT 1110 ISSUED JANUARY 8 1981 3 2 PIPER AIRCRAFT CORPORATION SECTION 3 P A 34 220T SENECA EMERGENCY PROCEDURES I To attempt to restore power prior to feathering Mixtures coe odi uerius tab s emus as required ON eL ee cog paci rd left or right only Aux UT Bur ducc vi POL exea quu nares unlatch ON HI if power is not immediately restored OFF Alternate coo ee ON power cannot be restored continue with feathering procedure uc e eae feather before RPM drops beiow 800 of inop CASING ssa uda EN REESE CES idle cut off TIME ead oae ws as required 3 to 5 of bank toward operative engine bail 1 2 to out Aux fuel pump of OFF of enpllie sisse ee rus ote seep m EE PRAG E AES OFF qas co cr Rr eB ker EE ERE b ee close on inop engine as required on operative engine Alternator of inop e Meat oe Se wes eee deer OFF Electrical Joad va reduce Tie OFF engine consider crossfeed Aux fuel pump operative engine aix OFF Power Gf Operative SORIA AAT Reel as required
310. rays 4 After cleaning plastic surfaces apply a thin coat of hard polishing wax Rub lightly with a soft cloth Do not circular motion S A severe scratch or mar in Wine can be removed by rubbing out the scratch with jeweler s rouge Smooth both sides and apply wax e Cleaning Headliner Side Panels and Seats 1 Clean headliner side panels and seats with a stiff bristle brush and vacuum where necessary 2 Soiled upholstery except leather may be cleaned with a good upholstery cleaner suitable for the material Carefully follow the manufacturer s instructions Avoid soaking or harsh rubbing CAUTION Solvent cleaners require adequate ventilation _ 3 Leather should be cleaned with saddle soap or a mild hand soap and water REPORT VB 1110 _ ISSUED JANUARY 8 1981 8 18 PIPER AIRCRAFT CORPORATION SECTION 8 PA 34 220T SENECA HANDLING SERV amp MAINT LP UM E a MAIRIE MOAN Cleaning Carpets To clean carpets first remove loose dirt with a whisk broom or vacuum For soiled spots and stubborn stains use a nonflammable drv cleaning fluid Floor carpets may be removed and cleaned like any household carpet Cleaning Deicing Equipment The deicers should be cleaned when the aircraft is washed using a mild soap and water solution cold weather wash the boots with the airplane inside a warm hangar if possible If the cleaning is to be done outdoors heat the soap and water solution b
311. re ee idle cut off Throttle We wx ui aus eS crank engine If engine has already started and is running continue operating to try pulling the fire into the engine If fire continues extinguish with best available means If external fire extinguishing is to be applied Fuel valves Rs Piet chee EE Ee OFF enden re cut off ENGINE FIRE IN FLIGHT Affected engine Pet SClCCIOF Rn ddp qu rS e ee Ree ae close ood di Ori Eso feather has eee idle cut off Hester ci res ae ee et de Ud OFF ARR ERIT wie ola If terrain permits land immediately FUEL MANAGEMENT DURING ONE ENGINE INOPERATIVE OPERATION CRUISING When using fuel from tank on the same side as the operating engine Fuel selector operating englle ON REPORT VB 1110 ISSUED JANUARY 8 1981 3 6 REVISED APRIL 9 1982 PIPER AIRCRAFT CORPORATION SECTION 3 PA 34 220T SENECA IH EMERGENCY PROCEDURES Fuel selector ENgIne QFE xa OFF When using fuel from tank on the side opposite the operating engine Fuel selector operating Engine CROSSFEED Fuel selector engine
312. rfields or flight over water For flight above 12 500 feet see FAR 91 32 requirements for oxygen and Section 9 Supplements in this handbook 4 39 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 Cowl flaps should normally be closed and the E G T should be maintained at approximately 13009 or higher to keep the engines at the proper operating temperature ISSUED JANUARY 8 1981 REPORT VB 1110 4 31 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA 34 220T SENECA B t taa 4 41 APPROACH AND LANDING Sometime during the approach for a landing the throttle controls should be retarded to check the gear warning horn Flving the airplane with the horn inoperative is not advisable Doing so can lead to a gear up landing as it 15 easy 10 forget the landing gear especially when approaching for a single engine landing or when other equipment is inoperative or when attention 15 drawn to events outside the cabin 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 the light will illuminate when the gear warning horn sounds The gear war
313. rge it is recommended that electrical loads be adjusted to limit continuous alternator outputs to 55 amps is not recommended to take off into IFR operation with only one aiternator operative even though electrical loads may be less than 55 amps Since the Seneca has combined fuel tank per engine it is advis able 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 in cruise after 30 minutes of flight to balance the fue quantity and extend the range during single engine operation Monitor the fuel quantity for the tank not being used to avoid overflow due to vapor return 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 if an asymmetric flow gauge indication is observed a fuel nozzle may be clogged and require cleaning There are no mechanical uplocks in the landing gear system In the event of a hydraulic system malfunction the landing gear will free fali 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 ai
314. rlocks the system will annunciate various failure conditions as advisory information for the pilot Following is a brief description of the interlocks and warnings provided REPORT VB 1110 ISSUED FEBRUARY 10 1984 9 148 14 of 20 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 21 p R BPMBPRBPE ABB a Interiocks 1 Autopilot engagement is inhibited unless an excitation signal is being provided to the attitude gvro 2 Selection of ALT mode 15 inhibited if the system altitude information is unreliable or if the entire system has not been powered for approximately 3 minutes to allow stabilization of the altitude source 3 During Dual Mode selected angle intercepts if the navigation information becomes invalid theappropriate APR REV annunciator will flash and automatic mode switching from HDG to the coupled navigation mode will be inhibited b Warnings I Low Voltage When the aircraft bus voltage falls below the minimum required for reliable system function any mode annunciator not already ON will flash 2 Attitude Gyro Absence of valid gyro excitation will cause the autopilot to disengage and the AP annunciator to flash The autopilot cannot be re engaged until this condition is corrected 3 AP Disengagement Anytime the autopilot is disen gaged the AP annunciator wil flash
315. rrr a aa aa 3 Check that the pilot s emergency disconnect switch disconnects the autopilot 4 Perform tbe following manual electric pitch trim checks a Ci Actuate the left side switch to the fore and aft positions The trim solenoid should engage but the trim should not run Solenoid engagement may be confirmed by addi tional force required to move trim wheel Actuate the right side switch to the fore and aft positions The trim solenoid should not engage and the trim should not run Grasping the manual trim wheel run the trim both up and down and check the overpower capability Press the AP DISC TRIM INTERRUPT switch down and hold The manual electric pitch trim will not operate either up or down Set manual trim for takeoff 5 Daily preflight check must be performed prior to first flight of the day Engage the AP and put in a pitch command using the vertical trim switch Mode Controller Hold the control column to keep it from moving and observe the autotrim run in the nose up direction after approximately three seconds delay Use the vertical trim switch and put in a pich DN command Hold the control column and observe the autotrim run in the nose down direction after approximately 3 seconds delay Engage the HDG mode and the AP Set the HDG bug to command a right turn The control wheel will rotate clock wise Set the HDG bug to command a left turn The control wheel will rot
316. s Locate the center of gravity for the landing SER on the C G range and weight graph if this point falls within the weight envelope the loading may be assumed acceptable for landing IT IS THE RESPONSIBIL ITY OF THE PILOT AND AIRCRAFT OWNER TO INSURE THAT THE AIRPLANE 1S LOADED PROPERLY WEIGHT AND BALANCE LOADING FORM Figure 6 11 REPORT VB 1110 ISSUED JANUARY 8 1981 6 12 REVISED AUGUST 9 1982 PIPER AIRCRAFT CORPORATION PA 34 220T SENECA SECTION 6 WEIGHT AND BALANCE G O1 MOMENT 1000 POUND INCHES LOADING GRAPH Figure 6 13 ISSUED JANUARY 8 1981 REPORT VB 1110 6 13 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 34 220T SENECA INH 4750 WEIGHT ___ 92 94 4600 L e 4513 MAX LANDING WT __ 4470 MAX ZERO FUEL WT S400 8 4200 4000 82 84 86 88 90 92 94 ENVELOPE 6 LOCATION INCHES DATUM Moment change due to retracting Landing Gear 32 in Ibs C G RANGE AND WEIGHT Figure 6 15 REPORT VB 1110 ISSUED JANUARY 8 1981 6 14 PIPER AIRCRAFT CORPORATION SECTION 6 34 220 SENECA WEIGHT AND BALANCE etra rr a a t Pa a a SYP APA T a a Ma t t HT Tree 6 11 INSTRUCTIONS FOR USING THE WEIGHT AND BALANCE PLOTTER This plotter is provided to enable the pilot quick
317. s Operation of the manuai electric pitch trim switch will disengage the AP lever switch on the Mode Controller except when CWS switch is held depressed as previously noted GA The Go Around switch is located on the left throttle and the operation of the switch will indicate a fixed angle of climb of 6 on the FDI Selection of the Mode when in APPRorNAVCPLD will disengage the mode and revert to the FD Mode wings level for lateral steering The AP if engaged will disengage However the AP may be engaged re engaged with the GA Mode selected and will follow the FDI pitch command to climb at the fixed angle NOTE The flight control system incorporates its own annunciator panel which is located on the instrument panel The modes and indications given on the annunciator panel are placarded on the face of the lenses and illuminate when the respective modes are active The switches on the mode selector are the push on push off type When engaged the corresponding flight director autopilot annunciator light illumi nates The V bars on the flight director indicator will disappear to the bottom of the instrument when a flight director mode is not engaged The V bars must be in view before the autopilot can be engaged BEFORE ENGAGING FLIGHT CONTROL SYSTEM 1 Check that all circuit breakers for the system are in Allow sufficient time for gyros to come up to speed and system warm up 3 4 minutes REPOR
318. s from the reference datum Arm The horizontal distance from the reference datum to the center of gravity of an item Moment The product of the weight ofan item multi pled by its arm Moment divided by constant is used to simplify balance calcu lations by reducing the number of digits Center of Gravity The pomt at which an airplane would balance if suspended Its distance from the reference datum 15 found by dividing the total moment bv the total weight of the airplane Arm The arm obtained by adding the airplane s individual moments and dividing the sum bv the total weight Limits The extreme center of gravity locations within which the airplane must be operated ata given weight Usable Fuel available for flight planning REPORT VB 1110 ISSUED JANUARY 8 1981 1 10 REVISED SEPTEMBER 23 1983 PIPER AIRCRAFT CORPORATION SECTION 1 PA 34 220T SENECA IH Unusable Fuel Standard Empty Weight Basic Empty Weight Payload Useful Load Maximum Ramp Weight Maximum Takeoff Weight Maximum Landing Weight Maximum Zero Fuel Weight ISSUED JANUARY 8 1981 GENERAL Fuel remaining after a runout test has been completed in accordance with govern mental regulations Weight of a standard airplane including unusable fuel full operating fluids and full oil Standard empty weight plus optional equipment Weight of occupants cargo and baggage Diff
319. s flight plan example assume a no wind condition The effect of winds aloft must be considered by the pilot when computing climb cruise and descent performance c Climb Destination Airport 3000 ft 22 10 KTS Headwind 9000 ft 2260 ft The desired cruise pressure altitude and corresponding cruise outside air temperature values are the first variables to be eon sidered in determining the climb components from the Fuel Time and Distance to Climb graph Figure 5 23 After the fuel time and distance for the cruise pressure altitude and outside air temperature values have been established apply the existing conditions at the departure field to the graph Figure 5 23 Now subtract the values obtained from the graph for the field of departure conditions from those for the cruise pressure altitude reference Figure 5 7 reference Figure 5 13 reference Figure 5 39 REPORT VB 1110 5 4 ISSUED JANUARY 8 1981 PiPER AIRCRAFT CORPORATION z SECTION 5 34 220 SENECA PERFORMANCE The remaining values are the true fuel time and distance components for the climb segment of the flight plan corrected for field pressure altitude and temperature The following values were determined from the above instructions in the flight planning example 1 Cruise Pressure Altitude 16 500 ft 2 Cruise OAT 129 3 Time to Climb 15 min minus 2 min 13 min 4 Distance to Climb 27 naut miles min
320. s installed FAA APPROVED lade Oorsee ___ o WARD EVANS D O A NO 0 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED APRIL 21 1981 REPORT 1110 I of 16 9 19 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 4 34 220 SENECA The 200 is certified in thisairplane with two axis control pitch and roll The system may be operated as a flight director alone with the pilot steering the airplane to the flight director command presentation or the autopilot can be engaged to steer the airplane to the flight director command presentation The airplane is equipped with a manual electric trim system which is controlled by pilot operation of the trim switch The autopilot uses the electric trim to accomplish trimming to unload the autopilot elevator servo 0 that autopilot disengagement does not result in transient airplane motion An autotrim electric pitch trim monitor is provided in the autopilot Autotrim and or electric pitch trim faults are visually annunciated on the Mode Annunciator and accompanied by an audible warning ABBREVIATIONS AFCS Automatic Flight Control System ALT Altitude or Altitude Hold AP Autopilot APPR Approach ARM System Arm for Capture BC Back Course CDI Course Deviation Indicator or Control CPLD Coupled CWS Control Wheel Steering DISC Disconnect FCS Flight Control System FD Flight Director FDI Flight Director Indicator GA Go Around GS Glide Slope HDG Heading
321. section 4 g 9 34 Added info to listing 9 35 Revised section 2 f 9 36 Revised caution note corrected pg no error 9 37 Revised section 3 d 2 9 39 Corrected error 9 41 Revised section 4 4 9 76 Corrected pg no error 9 110 Revised note 9 115 Revised note 9 120 Corrected error 9 123 Added heading to section 5 be 9 125 New pgs added MOR CUT A thru supplement 19 Ward Evans 9 130 Feb 25 1982 4 Changed pg nos PR amp 20409 Revised and added to procedure moved info to pg 3 6 Relocated info from pg 3 5 moved info to pg 3 7 Relocated info from pg 3 6 moved info to pg 3 8 Relocated info from pg 3 7 moved info to pg 3 9 REPORT 1110 vi e PILOT S OPERATING HANDBOOK LOG OF REVISIONS cont FAA Approv al Signature and Date Revision Number and Code Revised Description of Kevision Pages Rev 4 3 9 Relocated info from pg 3 8 PR820409 moved info to pg 3 10 cont 3 10 Relocated info from pg 3 9 moved info to pg 3 11 3 11 Relocated info from pg 3 10 3 16 Revised and added to para 3 7 3 17 Added to para 1 7 moved info to pg 3 18 3 18 Relocated info from pg 3 17 moved info to pg 3 19 3 19 Relocated info from pg 3 18 moved info to pg 3 20 3 20 Relocated info from pg 3 19 moved info to pg 3 21 3 2 Relocated info from pg 3 20 5 17 Revised fig 5 13 6 20 R
322. sed para 7 27 Ward Evans August 9 1982 2 35 Revised para 7 29 7 36 Revised para 7 31 and 7 33 REPORT 1110 vi g PILOT S OPERATING HANDBOOK LOG OF REVISIONS cont Revision Number and Code i Rev 30923 Approval Revised Description of Revision Signature and Pages Date 4 Added 3 and 4 a CL ET TETRA RA TERRI ARAL RPM to para 5 Revised barometric pressure mb Deleted MEA Added items 1 c and 1 d to para 2 7 Relocated fuel placard to pg 2 13 Added pg added new and relocated fuel placards Revised Figures 5 27 5 29 and 5 31 Revised Figure 5 27 Revised Figure 5 29 Revised Figure 5 31 Revised Figure 5 33 Revised Figure 5 15 Revised para 7 15 info Added Caution Revised 7 25 into Revised pg no 8 2 Revised 3 info 5 4 Revised para 8 5 into 8 4 Deleted para 8 5 info 8 19 Revised item 8 31 gh relocated para 8 33 8 20 Added pg added para 8 33 94 Kelocated Supplement No 19 to pg 9 1 9 Added pg added Supplements 19 and 20 9 10 Revised Section f info relocated info to pg 9 11 9 11 Added and relocated info 9 12 Added info 9 28 Revised item 1 9 42 Revised item 1 REPORT VB 1110 vi h PILOT S OPERATING HANDBOOK LOG OF REVISIONS cont FAA Approval
323. selector for the inoperative engine must be in the OFF position Do not operate with both sclectors on X FEED Do not take off with a selector on X FEED Fuel and vapor are always returned to the tank on the same side as the operating engine REPORT VB 1110 ISSUED JANUARY 8 1981 7 16 REVISED SEPTEMBER 23 1983 PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA DESCRIPTION amp OPERATION Before each flight fuel must be drained from low points in the fuel system to ensure that any accumulation of moisture or sediment is removed from the system Fuel drains provided for each fuel filter 2 each fuel tank 4 and each crossfeed line 2 The fuel filter drains are located on the outboard underside of each engine nacelle two fuel tank drains are located on the underside of each wing fuel crossfeed drains are located at the lowest point in the fuel system on the underside of the fuselage just inboard of the trailing edge of the right wing flap ISSUED JANUARY 8 1981 REPORT VB 1110 7 17 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA MT A aa ATTE T a a aaa MM MEA 7 17 ELECTRICAL SYSTEM The electrical system of the Seneca is capable of supplying sufficient current for complete night IFR equipment Electrical power is supplied by two 65 ampere alternators Figure 7 13 one mounted on each engine A 35 ampere hour 12 volt battery provides current for star
324. shes against it and assists in moving it to the downlocked position After the gears are down and the downlock hooks engage springs maintain force on each hook to keep it locked until it is released by hydraulic pressure REPORT VB 1110 ISSUED APRIL 9 1982 7 6b i PIPER AIRCRAFT CORPORATION SECTION PA 34 220T SENECA 22 DESCRIPTION amp OPERATION UP 108 KIAS MAX HOSE GEAR 21 GEAR OUND OPERATION S TAILWIND OVERIOKT LEFT j RATION 2000 2200 GEAR SUE DOWN 130 KIAS MAX A EMERGENCY GEAR ra 1 MTENSION PULL TO A FM RE ENGAGEMENT LANDING GEAR SELECTOR Figure 7 3 To extend and lock the gears in the event of hydraulic failure it is necessary only to relieve the hydraulic pressure Emergency gear extension must not be attempted at airspeeds in excess of 85 KIAS An emergency gear extension knob located directly beneath the gear selector switch is provided for this purpose Pulling this knob releases the hydraulic pressure holding the gear in the up position and allows the gear to fall free During normal operation this knob is covered by a guard to prevent inadvertent extension of the gear Before pulling the emergency gear extension knob place the landing gear selector switch in 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
325. sible longitudinal control diffi culties 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 Emergency Procedure Section of this handbook The sooner a problem is recognized and corrective action taken the greater is the chance of avoiding total electrical failure Both alternator switches should be ON for normal operation The two ammeters continuously indicate the alternator outputs 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 aiternator light on the annunciator panel will illuminate to warn of the tripped condition Alternator outputs will vary with the electrical equipment in use and the state of charge of the battery Alternator outputs should not exceed 65 amperes REPORT VB 1110 ISSUED JANUARY 8 1981 4 30 REVISED FEBRUARY 25 1982 PIPER AIRCRAFT CORPORATION SECTION 4 PA 34 220T SENECA NORMAL PROCEDURES Should the current requirement exceed 130 amps the alternators will continue at 65 amps each the remainder coming from the battery There fore to insure against battery discha
326. spring loaded OFF primer button switches located adjacent to the starter switches are used to select auxiliary fuel pump operation for priming regardless of other switch positions These primer buttons may be used for both hot or cold engine starts REPORT VB 1110 ISSUED JANUARY 8 1981 7 14 REVISED AUGUST 17 1981 SECTION 7 DESCRIPTION amp OPERATION PIPER AIRCRAFT CORPORATION PA 34 220T SENECA HI 1 uum f ec d m marte NJIHO CM 1353 91H E2373 HO us vn 771 1735 f 3230 S33220N 4 na 09 57081 02 301239735 1303 c u3iv3H OL F 304 d il 4 3 aJnseaud OL O31N1 312208 ONY 2979 97139 n3 7 01140 NMOS NYNA Ji HEYA SONY TVA aI OIOHSNV am jO3NNOOMAINI 73073 Figure 7 11 FUEL SYSTEM SCHEMATIC 7 15 REPORT VB 1110 ISSUED JANUARY 8 1981 REVISED AUGUST 17 1981 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA TET e a a i MA Ma ETT TT TT PHP T a tm I e T Tie On airplanes equipped with an optional primer system identified by Placard below starter switch shown in Figure 7 15 the primer switch location and actuation 15 the same as the basic airplan
327. ss HDG 3 Perform standard VOR receiver check REPORT VB 1110 ISSUED APRIL 21 1981 9 110 4016 REVISED FEBRUARY 25 1982 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SUPPLEMENT 17 4 Perform Steps 1 7 in Section 4 item b except in Steps 4 and 5 substitute course arrow for HDG bug when checking control wheel movement in relation to L R needle HDG bugis inoperative with NAV APPR or REV mode selected d IN FLIGHT PROCEDURE 1 Rotate heading bug to desired heading 2 Trim aircraft for existing flight condition all axes Engage autopilot 3 During maneuvering flight control aircraft through use of the HDG bug HDG mode 4 For navigation operations select modes as required by the operation being conducted and in accordance with the mode description provided in Operator s Manual For specific in structions relating to coupled instrument approach operations refer 10 Special Operations and Information Section e SPECIAL OPERATIONS AND INFORMATION 1 Instrument Approach Operations Initial and or intermediate approach segments should be conducted at approximately 95 110 KIAS with a maximum of 1 notch 10 flaps extended as desired Upon intercepting the glide path or when passing the final approach fix FAF immediately lower the landing gear and reduce the power for approximately 90 95 KIAS on the final approach segment Monitor course guidance information raw da
328. ssible go around b Placards in full view of the pilot in ihe area of the air conditioner controls when the air conditioner is installed WARNING AIR CONDITIONER MUST BE OFF PRIOR TO TAKEOFF AND LANDING AND ONE ENGINE INOPERATIVE OP ERATIONS SECTION 3 EMERGENCY PROCEDURES No changes to the basic Emergency Procedures provided by Section 3 of this Pilot s Operating Handbook are necessary for this supplement ISSUED JANUARY 8 1981 REPORT VB 1116 3 of 6 9 15 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 3 i PA 34 220T SENECA SECTION 4 NORMAL PROCEDURES Prior to takeoff the air conditioner should be checked operation as follows a Check aircraft battery switch ON b Turn the air conditioner control switch to ON and the fan switch to one of the operating positions the DOOR OPEN warning light will illuminate thereby indicating proper air conditioner condenser door actuation c Turn the air conditioner control switch to OFF the A C DOOR OPEN warning light will go out thereby indicating the air conditioner door is in the retracted position If the A C DOOR OPEN light does not respond as specified above an air conditioner system or indicator bulb malfunction isindicated and further investigation should be conducted prior to flight d The above operational check may be performed during flight if an in flight failure is suspected The condenser
329. switch is released will then be held Heading Mode Set the heading bug to the desired heading on the PNI engage the AP depress the HDG switch on the Mode Controller and HDG will be displayed on the annunciator panel The AP will command a turn to the heading selected The pilot may then choose any new heading by merely setting the bug on a new heading The AP will automatically command a turn in the direction of the new setting To disengage the HDG mode depress the HDG switch on the Mode Controller and observe the HDG light go out on the annunciator The HDG mode will automatically disengage when APPR or NAV CPLD is achieved Navigation Mode NAV The Navigation mode may be selected by tuning the NAV receiver to the desired frequency setting the CDI to the desired radial and depressing the switch on the Mode Controller The annunciator will indicate NAV ARM until capture of the selected course unless the NAV switch is engaged with wings level and a centered needle on the CDI Then the mode will go directly to NAV CPLD as displayed on the annunciator panel The system can intercept at any angle up to 90 and will always turn toward the course pointer a condition requiring a ISSUED APRIL 21 1981 REPORT VB 1110 11 of 16 9 43 9 44 7 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 5 PA 34 220T SENECA capture exists at mode engagement the pilot is required to set up an intercept angle using ei
330. t i Press and hold the TEST switch all mode annunciators light with flashing j Release the TEST switch after allannunciator lights except HDG and TEST turn off k Press Pitch Modifier switch DN then UP HDG and TEST remain on L Momentarily press the FEST switch HDG and ATT remain on TEST flashes ISSUED FEBRUARY 16 1984 REPORT 1110 5 of 20 9 139 SECTION 9 PIPER AIRC RAFT CORPORATION Es PPLEMENT 21 PA 34 220T SENECA RII TURNIER rimis adi m Press Pitch Modifier switch DN then UP the TEST light remains off as long as the switch is held n Momentarily press the TEST switch HDG and ATT lights remain on and TEST light turns off 2 COMMAND TRIM SYSTEM To be performed before the first flight of each a Using the control wheel trim switch verify normal trim up and down operation b Press and hold the center bar on the control wheel trim switch Observe that the trim system does not operate c Release the center bar on the control wheel trim switch Move the control wheel trim switch fore and aft Observe that the trim svstem does not operate This completes the test sequences CAUTIONS Any failure of the above procedures indicates that a failure exists in the system and the system shali not be operated until the failure has been located and corrected Check the elevator trim position before takeoff
331. t is not connected the words NO LOG appear in the lower left corner _ CONTROL DISPLAY FUNCTIONS cont Table 4 3 cont ISSUED FEBRUARY 25 1982 REPORT 1110 5 of 6 9 129 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 19 PA 34 220T SENECA b OPERATING PRECAUTIONS WARNING Do not operate the radar during refueling operations or in the vicinity of trucks or con tainers accommoding flammables or ex plosives Do not allow personnel within 15 feet of area being scanned by antenna when system is transmitting 1 Flash bulbs can be exploded by radar energy 2 Since storm patterns are never stationary the display is con st ntly changing Continued observation is always advisable in stormy areas SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of the Pilot s Operating Handbook are necessary for this supplement REPORT VB 1110 ISSUED FEBRUARY 25 1982 9 130 6076 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 20 paree PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO 20 FOR EDO AVIONICS COMMAND ELECTRIC TRIM SYSTEM MODEL 923 SECTION 1 GENERAL This supplement 15 to acquaint the pilot with the operation of the EDO Avionics Command Electric Trim System Mode AK 923 as installed in the PA 34 220T Seneca in accordance with FAA Approved Piper data The airplane must be op
332. t landing gear for leaks proper piston exposure under a static load 3 1 2 inches and that the tires are properly inflated and not excessively worn The right wing tip and leading edge should be free from ice and damage REPORT VB 1110 ISSUED JANUARY 8 1981 4 16 REVISED AUGUST 17 1981 PIPER AIRCRAFT CORPORATION SECTION 4 PA 34 220T SENECA III NORMAL PROCEDURES Open the fuel to check the quantity and color of ihe fuel and cap vent The vent should be free of obstructions Secure the fuel cap properly Proceeding around to the engine nacelle check the oil quantity six to eight quarts Make sure that the dipstick has properlv seated after checking Check and ensure that the oil filler cap is securely tightened and secure the inspection door Check the right propeller for nicks or leaks The spinner should be secure and undamaged check closely for cracks The cow flaps should be open and secure The right fuel drains should be opened to drain moisture and sediment Drain the two fuel tank drains under the wing and the gascolator drain near the bottom of the engine nacelle refer to Section 8 for more detailed draining procedure Check the nose section for damage and the nose landing gear for leaks and proper strut infla
333. t panel and are three position rocker switches LO HI and OFF LO auxiliary fuel pressure is selected by pushing the top of the switch The auxiliary fuel pressure is selected by pushing the bottom of the switch but this can be done only after unlatching the adjacent guard When the HI auxiliary fuel pump is activated an amber light near the annunciation panel is illuminated for each pump These lights dim whenever the pump pressure reduces automatically and manifold pressure is below approximately 21 inches in case of a failed engine driven fuel pump Hl auxiliary fuel pressure should be selected Adequate pressure and fuel flow will be supplied for upto approximately 75 power Manual leaning to the correct fuel flow will be required at altitudes above 15 000 feet and for engine speeds less than 2300 RPM An absolute pressure switch automatically selects a lower fuel pres sure when the throttle is reduced below 21 Hg manifold pressure and the H1 auxiliary fuei pump is on NOTE Excessive fuel pressure and very rich fuel air mixtures will occur if the HI position is ener gized when the engine fuel injection system is functioning normally Low auxiliary fuel pressure is available and may be used during normai engine operation both on the ground and inflight for vapor suppression should it be necessary as evidenced by unstable engine operation or fluctu ating fuel flow indications during idie or at high altitudes Separate
334. t s control wheel X X 2 Autotrim may be disconnected by a Depressing the autopilot ON OFF switch OFF b Placing the autotrim master switch OFF c Depressing master disconnect switch on pilot s control wheel After failed system has been identified pull system circuit breaker and do not operate until the system has been corrected REPORT VB 1110 ISSUED APRIL 21 1981 9 114 2 of 12 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 18 3 Single Engine Operations a Engine failure during autopilot approach operation Disengage autopilot conduct remainder of approach manually Engine failure during normal climb cruise descent Retrim aircraft perform normal aircraft engine out procedures Maintain aircraft yaw trim throughout all single engine operations NOTE Single engine operations below Single Engine Best Rate of Climb Speed Blue Line may require manual rudder appiication to maintain directional trim depending upon aircraft configuration and power applied 4 Altitude Loss During Malfunction a An autopilot malfunction during climb cruise or descent with a 3 second delay in recovery initiation could result in as much as 60 bank and 700 aititude 105 Maximum altitude loss measured at 180 KIAS during descent at high altitude An autopilot malfunction during an approach with one second delay in recovery initiation could result in as much as 30 b
335. t selected CDI course beam at desired angle Maximum recommended intercept angle 90 _ 4 Engage APPR and note APPR ARM on the annunciator 5 When airplane approaches the selected CDI course APPR will couple HDG will decouple the FDI and or AP will give command or steering to track LOC or VOR and CPLD will illuminate on the annunciator panel REPORT 1110 ISSUED APRIL 21 1981 9 32 14 of 16 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA IH SUPPLEMENT 4 6 When the glide slope beam is intercepted the glide slope GS will couple automatically and indicates GS on the annunciator panel If the ALT mode was engaged prior to intercepting the glide slope it will automatically disengage when GS couples FDI and or AP will now provide commands or steering to track LOC and GS Adjust throttles to control speed on descent Set HDG bug for missed approach but do not engage HDG NOTE Should the GA mode be inadvertently selected during APPR mode operation cancel GA mode press CWS prior to re selection of the APPR mode It may be necessary to use some combination of vertical trim and power to recenter the GS for GS coupling Failure to follow this procedure will result in the GS mode being inhibited 7 When middie marker signal is received system will auto matically switch to more stable track mode NOTE Operation of marker test function after APPR CPLD will reduce
336. t the airplane is in an airworthy condition is the responsi bility 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 as outlined by instrament markings placards and this handbook Aithough the arrangement of this handbook is intended to increase its in flight capabilities it should not be used solely as an occasional operating reference The pilot should study the entire handbook to become familiar with the limitations performance procedures and operational handling characteristics of the airplane before flight The handbook has been divided into numbered arabic sections each provided with a finger tip tab divider for quick reference The limi tations and emergency procedures have been placed ahead of the normal procedures performance and other sections 10 provide easier access to information that may be required in flight The Emergency Procedures Section has been furnished with a red tab divider to present an instant reference to the section Provisions for expansion of the handbook have been made bv the deliberate omission of certain paragraph numbers figure numbers item numbers and pages noted as being intentionally left blank ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED AUGUST 9 1982 1 1 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL 34 220 SENECA Pa S S a a a a a ra t
337. ta throughout the approach Ali power changes should be of small magnitude and smoothly applied for best tracking performance Do not change aircraft configuration during approach while autopilot is engaged SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of this Pilot s Operating Handbook are necessary for this supplement ISSUED APRIL 21 1981 REPORT VB 1110 5 of 6 9 111 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 17 PA 34 220T THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 1110 ISSUED APRIL 21 1981 9 112 6 of 6 AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA HI SUPPLEMENT 18 SUPPLEMENT 18 CENTURY 41 AUTOPILOT INSTALLATION SECTION 1 GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Century 41 Autopilot Mode AK865 or Century 4 Flight Director Autopilot Mode 881 FD is installed in accordance with STC SA337ISW D The information contained within this supplement is to be used in conjunction with the complete handbook This supplement has been FAA Approved as a permanent part of this handbook and must remain in this handbook at all times when the optional Century 41 Autopilot or Century 41 Flight Director Autopilot is installed FAA EE WARD EVANS D O A NO 80 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED APRIL 21 1981 REPORT 1110
338. te a load much higher than the known consumption for more than approximately five minutes an electrical defect other than the alternator svstem should be suspected because a discharged battery will reduce the alternator load as it approaches the charged conditions zero ammeter reading indicates alternator is not producing current and should be accompanied by Humi nation of the ALT annunciator light A single alternator is capable of supporting a continued flight in case of alternator or engine failure in most conditions however with deicing equipment and other high loads care must be exercised to prevent the loads from exceeding the 65 ampere rating and subsequent depletion of the For abnormal and or emergency operations and procedures refer to Section 3 Emergency Procedures CAUTION Do not use cigar lighter receptacles as power sources for anv devices other than the cigar lighters supplied with the airplane Any other device plugged into these receptacles mav be damaged REPORT VB 1110 ISSUED JANUARY 8 1981 7 20 REVISED SEPTEMBER 23 1983 1861 LI 1 GASIAA 91581 1861 8 oun tI WALSAS TANVd HOLIMS ELEC PITCH TRIM I PUSH ON OFF RADIO LIGHTS n PRIMERR PANEL LIGHTS THIS AIRPLANE IS EO UPPED WITH OPTIONAL FUELING PRIMER SYSTEM SEE MIKE PHONE
339. te the engine at high RPM when running up or taxiing over ground containing loose stones gravel or loose material that may cause damage to the propeller blades c Parking When parking the airplane be sure that it is sufficiently protected from adverse weather conditions and that it presents no danger to other aircraft When parking the airplane for any length of time or overnight it is suggested that it be moored securely 1 To park the airplane head it into the wind if possible 2 The parking brake knob is located on the lower left of the instrument panel To set the parking brake first depress and hold the toe brake pedals and then pull out the parking brake knob To release the parking brake first depress and hold the toe brake pedals and then push in on the parking brake knob WARNING No braking will occur if knob 5 pulled prior to brake CAUTION Care should be taken when setting brakes that are overheated or during cold weather when accumulated moisture may freeze a brake 3 Aileron and stabilator controls shouid be secured with the front seat belt and chocks used to block the wheels d Mooring The airplane should be moored for immovability security and protection The following procedures should be used forthe proper mooring ol the airplane 1 Head the airplane into the wind if posible 2 Retract the flaps 3 Immobilize the ailerons and stabilator looping t
340. ted items 155 thru 159 from pg 6 34 Moved items 155 thru 159 to pg 6 33 relocated item 173 from pg 6 35 Moved item 173 to pg 6 34 removed previous item 177 added new items 177 and 178 Revised item 223 Added new items 264 and 265 renumbered item 266 moved items 271 and 273 to pg 6 47 Rev 2 PR810817 cont 6 40 6 46 REPORT VB 1110 vi a PILOT S OPERATING HANDBOOK LOG OF REVISIONS cont M Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date E RE Rev 2 6 47 Relocated items 271 and 273 PR810817 from pg 6 46 added new cont item 272 moved items 281 and 283 to pg 6 48 6 48 Relocated items 281 and 283 from pg 6 47 moved item 287 10 6 49 6 49 Relocated item 287 from pg 6 48 moved item 291 to pg 6 50 6 50 Relocated item 291 from pg 6 49 6 62 Added new 441 7 14 Revised para 7 15 7 15 Revised fig 7 11 7 20 Added info 7 21 Revised fig 7 15 9 46 Revised Supplement Section I 9 49 Added Caution Note moved info to pg 9 50 9 50 Relocated info from pg 9 49 9 5 Revised Supplement Section 3 9 53 Revised Supplement Section 3 ve Donner 9 105 Revised Supplement Ward Evans Section 4 Aug 17 981 Rev 3 1 4 Corrected para 1 9 PR820225 34 Expanded checklist moved info to pg 3 1 3 11 Relocated info from
341. ter switch is off while inserting or removing a plug at this receptacle Connect 12 VDC external power source only Refer to the PA 34 220T Service Manual for detailed procedures for cleaning and servicing the battery 8 07 SERIAL NUMBER PLATES The serial number plate is located on the left side of the fuselage near the leading edge of the stabilator The serial number should always be used when referring to the airplane on service or warranty matters ISSUED JANUARY 8 1981 REPORT VB 1110 8 15 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING SERV amp MAINT PA 34 220T SENECA 8 29 LUBRICATION Lubrication at regular intervals is an essential part of the maintenance of an airplane For lubrication instructions and a chart showing lubrication points types of lubricants to be used lubrication methods and recom mended frequencies refer to the PA 34 220T Service Manual 8 31 CLEANING a 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 1 Place a large pan under the engine to catch waste 2 With the engine cowling removed spray or brush the engine with solvent or a mixture of solvent and degreaser In order to remove especially heavy dirt and grease deposits it may be necessary to brush areas that were sprayed CAUTION Do not spray solvent into the alternator pres sure pump starter air inta
342. ternate position the altimeter vertical speed indicator and airspeed indicator will be using cabin air for static pressure During alternate static source operation these instruments may give slightly different readings depending on conditions within the cabin Airspeed setting of heating and ventilating controls or the position of thestorm window can influence cabin air pressure The pilot can determine the effects of the alternate static source on instrument readings by switching from standard to alternate sources at different airspeeds and heating and ventilating configurations including open storm window below 129 KIAS If one or more of the pitot static instruments malfunction the system should be checked for dirt leaks or moisture The pitot and static lines may be drained through separate drains located on the side panel next to the pilot s seat The holes in the sensors for pitot and static pressure must be fully open and free from blockage Blocked sensor holes will give erratic or zero readings on the instruments heated pitot head which alleviates problems with icing and heavy rain is available as optional equipment Static source pads have been demonstrated to be non icing however in the event icing does occur selecting the alternate static source will alleviate the problem REPORT VB 1110 ISSUED JANUARY 8 1981 7 24 _ SECTION 7 DESCRIPTION amp OPERATION PIPER AIRCRAFT CORPORATION PA 34 220T SENECA
343. test cycle Circuit protection for the surface deicer system is provided by a wing tail W T DE ICE circuit breaker located on the circuit breaker panel Wing icing conditions may be detected during night flight by use of an ice detection light installed in the outboard side of the left engine nacelle The light is controlled by a WING ICE LIGHT switch Figure 9 3 located on the instrument panel to the right of the surface deice switch A wing ice light W ICE circuit breaker located in the circuit breaker panel provides circuit protection REPORT VB 1110 _ ISSUED JANUARY 8 1981 9 46 20410 A REVISED AUGUST 17 1981 quassi 1861 8 LHOd AM OL jo 7 6 1 6 2210214 WALSAS NOILOALOUd 321 PNEUMATIC DEICER BOOTS PNEUMATIC ME DEICER BOOTS WINDSHIELD PANEL WIENS LOCCPE Vd NOILVHOdHOO L3JV HOMNIV Wadld ICE DETECTION LIGHT pe D HEATED PITOT HEAD ELECTROTHERMAL ___ PROPELLER DEICER PADS 15 HEATED LIFT DETECTORS 91 144018 6 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 6 PA 34 220T SENECA Electrothermal propeller deicer pads are bonded to the leading edges of the propeller blades The system is controlled by an ON OFF type PROP DE ICE switch Figure 9 3 located to the right of the surface deice switch Power for the propeller deicers is supplied by the airplane s electrical system through
344. th a low fuel indication The maximum demonstrated crosswind component for landing is 17 KTS 4 43 GO AROUND go around from a normal approach with the airplane in the landing configuration becomes necessary apply takeoff power to both engines not to exceed 40 in Hg manifold pressure Establish a positive climb attitude retract the flaps and landing gear and adjust the cowl flaps for adequate engine cooling 4 45 AFTER LANDING After leaving the runway retract the flaps and open the cowl flaps Test the toe brakes a spongy is often an indication that the brake fluid needs replenishing The alternate air control should be OFF 4 47 SHUTDOWN Prior to shutdown switch the heater if on to the FAN position a few minutes for cooling and then turn OFF AH radio and electrical equipment should be turned OFF Move the mixture controls to idle cut off Turn OFF the magneto and battery switches and set the parking brake NOTE The flaps must be placed in the UP position for the flap step to support weight Passengers should be cautioned accordingly REPORT VB 1110 ISSUED JANUARY 8 1981 4 34 REVISED AUGUST 17 1981 PIPER AIRCRAFT CORPORATION SECTION 4 PA 34 220T SENECA NORMAL PROCEDURES er A a aaa ETT a a AM T LAPD PP a A 4 49 MOORING The airplane can be moved on the ground with the aid of the optional nose wheel tow bar stowed aft of the fifth and sixth seats
345. the enroute mode CDI deviation is mile dot 5 miles full scale In approach CDI deflection is 114 mile dot 1 1 4 miles full scale Sequences display waypoints from through 8 Winking wavpoint number indicates inactive wavpoints steadily on waypoint number indi cates active waypoint Depressing RTN return button returns the display to the active waypoint when an inactive waypoint is currently being displayed Depressing the USE button converts the way point being displayed into the active waypoint Two concentric knobs set radial information into the display Knobs control information as follows Large knob Changes display in 10 degree increments Small knob pushed in Changes display in 1 degree increments Smail knob pulled out Changes display in 0 1 degree increments ISSUED JANUARY 8 1981 REPORT VB 1110 3 of 6 9 67 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 9 i PA 34 220T SENECA CONTROL OR INDICATOR FUNCTION Distance Selector Two concentric knobs set distance information in nautical miles into the display Knobs control information as follows Large knob Changes display in 10 mile increments Small knob pushed in Changes display in 1 mile increments Small knob pulled out Changes display in 0 1 mile divisions from 00 0 through 100 miles Beyond 100 nmi changes display in l mile increments Check Button Depressing CHK check button causes DME and bear
346. the flight control system gains If this should occur the APPR switch should be recycled 8 Landing or missed approach a Landing Disengage AP and land b Missed Approach See Go Around procedures k GO AROUND PROCEDURE Depress the GO AROUND switch and perform missed approach procedure as per Airplane Flight Manual The AP will disengage and the FDI will command a 6 climb attitude When established in climb attitude the AP may be re engaged and the APPR mode may be selected for a straight away missed approach or HDG may be selected to turn to the missed approach heading ISSUED APRIL 21 1981 REPORT 1110 15 of 16 9 322 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 4 PA 34 220T SENECA 0 BACK COURSE PROCEDURE Same as front course except that BC is engaged after APPR is engaged and the airplane must be set for descent manually by holding the vertical trim control DN on the Mode Controller or by establishing the desired PAH using the CWS or vertical trim switch SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of this Pilots Operating Handbook are necessary for this supplement VB 1110 ISSUED APRIL 21 1981 9 32b 16 of 16 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 5 PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO 5 FOR KFC 200 AUTOMATIC FLIGHT CONTROL SYSTEM WITHOUT FLIGHT D
347. ther HDG or AP mode NAV may be disengaged by depressing the NAV switch or by engaging HDG when in NAV CPLD or NAV ARM CAUTION The NAV mode of operation will continue to provide airplane commands and or control without a valid VOR LOC signal NAV flagin view Also erroneous navigation information may result from COMM radio interference with the radio This erroneous infor mation may cause premature NAV captures as well as erroneous steering information Should this occur reselect HDG mode and then reselect mode APPR The Approach mode may be selected by tuning the NAV receiver to the desired VOR or LOC frequency setting the CDI to the desired radial or inbound heading and depressing the APPR switch on the Mode Controller The annunciator will indicate APPR ARM until the course is captured unless the APPR mode is engaged with wings level and there is a centered needle on the CDI In that situation the mode will go directly to APPR CPLD as displayed on the annunciator panel The system can intercept at any angle up to 90 and will always turn toward the course pointer See approach procedure for more detail APPR mode can be disengaged by depressing the APPR switch on the Mode Controller or by engaging HDG when in APPR CPLD or engaging NAV whenin APPR CPLD or APPR ARM The annunciator panel indicates the status of the approach mode REPORT VB 1110 ISSUED APRIL 21 1981
348. ting for use of elec trical equipment 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 is accessible through the baggage compart ment is normally kept charged by the alternators If it becomes necessary to charge the battery it should be removed from the airplane Two solid state voltage regulators maintain effective load sharing while regulating electrical system bus voltage to 14 volts An overvoltage relay in each alternator circuit prevents damage to electrical and avionics equipment by taking an alternator off the line if its output exceeds 17 volts this should occur the alternator light on the annunciator panel will ituminate Voltage regulators and overvoltage relays are located forward ofthe bottom of the bulkhead separating the cabin section from the nose section The electrical system and equipment are protected by circuit breakers located on a circuit breaker panel on the lower right side of the instrument panel The circuit breaker panel is provided with enough blank spaces to accommodate additional circuit breakers if extra electrical equipment is installed In the event of equipment malfunctions or a sudden surge of current a circuit breaker can trip automatically The pilot can reset the breaker by pressing it in preferably after a few minutes cooling period The circuit breakers can be pulled out manually
349. tion b To disable heading card pull circuit breaker and use magnetic compass for directional data NOTE If heading card is not operational autopilot should not be used c With card disabled VOR Localizer and Glide Slope displays are still functional use card set to rotate card to aircraft heading for correct picture 4 Slaving Failure 1 failure to self correct for gyro drift 1 Check gyro slaving switch is set to No position if equipped with Slave No No 2 switch or Slaved position when equipped with Slaved and Free Gyro Mode Switch 2 Check for HDG Flag Check compass circuit breaker 4 Reset heading card while observing slaving meter Dead slaving meter needle or a needle displaced fully one direction indicates a slaving system failure 5 Select slaving amplifier No 2 if equipped If not equipped proceed with No 7 below 6 Reset heading card while checking slaving meter proper slaving indication is not obtained proceed with No 7 below 7 Switch to free gyro mode and periodically set card as an unslaved gyro NOTE In the localizer mode the TO FROM arrows may remain out of view depending upon the design of the NAV converter used in the instal lation ISSUED APRIL 21 1981 REPORT VB 1110 3 of 6 9 109 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 17 PA 34 220T SENECA SECTION 4 NORMAL PROCEDURES Refer to Edo Aire Mitchel
350. tion The blue light will go out when synchronization is complete For a given RPM and power setting switch position 2 may provide smoother operation by means of providing a different phase angle Set the switch to position 1 or 2 whichever provides the smoothest operation Normally propeller synchrophasing will take place within a REPORT VB 1110 ISSUED APRIL 21 1981 9 104 2of4 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 16 SEMPER few seconds but occasionally it may take up to a full minute When the power setting is to be changed the synchrophaser switch should be set to OFF for 30 seconds before the power setting is adjusted then the syn chrophaser switch may be returned to the 1 or 2 position whichever provides the smoothest operation If the propeller RPM differential exceeds 50 RPM the switch should be set at OFF for 30 to 40 seconds then the propellers can be synchronized again and the synchrophaser switch returned to I or 2 Pulling the circuit breakers completely deactives the propeller synchrophaser system If the master switch is turned OFF or if there is an electrical system failure the slave engine will return to the controlled selected RPM plus approximately 25 RPM out of synchroni zation regardless of the position of the synchrophaser switch SECTION 5 PERFORMANCE No changes to the basic performance provided by Section 5 of this Pil
351. tion Under a normal static load 2 1 2 inches of strut should be exposed Check the tire for wear and proper inflation If the tow bar was used remove and stow Before moving on to the forward baggage compartment check the condition of the landing light Open the forward baggage compartment and check to make sure that the baggage has been stowed properly Close secure and lock the baggage door the front of the airplane the windshield should be clean secure and free from cracks or distortion Moving around to the left wing check the wing engine nacelle and landing gear as described for the right side Don t forget to check the fuel and oil pitot cover was installed it should be removed before flight and the holes checked for obstructions With the heated pitot switch on check the heated pitot head and heated lift detector for proper heating Check the stall warning vanes for freedom of movement and damage squat switch in the stall warning system does not allow the units to be activated on the ground CAUTION Care should be taken when an operational check of the heated pitot head and the heated hft detectors is being performed Both units become very hot Ground operation should be limited 3 minutes maximum avoid damaging the heating elements ISSUED AUGUST 17 1981 REPORT VB 1110 REVISED AUGUST 9 1982 4 16 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROC EDURES 34 220 SENECA m atch t
352. to takeoff from high elevations Do not overheat Adjust mixture only enough to obtain smooth engine operation Do not exceed 40 in Hg manifold pressure NORMAL TAKEOFF Flaps up Brakes o E xii Piet apply and hold Bo cr E UP release Accelerate to and maintain 79 KIAS Cantor wheel XR o eR ease back to rotate to climb attitude After obstacle clearance accelerate to best rate of climb speed of 92 5 Gear Lr Tx ELICIT UP SHORT FIELD TAKEOFF 25 Flaps VERTES S second notch SI oe Gore dere hte aa do ge det ark bk hOB Nea ae DNA sel sos Shs apply and hold Takeoff power before brake release focis S dies an uds release Accelerate to 64 KIAS Control wheel rotate firmly to attain 66 KIAS through 50 ft UP REPORT 1110 ISSUED JANUARY 8 1981 4 10 REVISED FEBRUARY 10 1984 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROC EDURES PA 34 220T SENECA APPROACH AND LANDING Gear WAEDIBE NOTA ed ege RA check Beat BACKS erect Belts harness PR fasten adijust Fuel selettors eee eod Daniels ON Cowl s as required Auxiliary mel pumps eiras nda nw eaa dua Faves OFF Mixture control uo is cepe m C era Php aae qd qt rich
353. ts of the reported winds Maximum power permissible for takeoff Maximum power permissible continuously during flight Maximum power permissible during climb Maximum power permissible during Cruise Exhaust Gas Temperature Gauge fe Airplane Performance and Flight Planning Terminology Climb Gradient Demonstrated Crosswind Velocity DEMO X WIND Accelerate Stop Distance ISSUED JANUARY 8 1981 The demonstrated ratio of the change in height during a portion of a climb to the horizontal distance traversed in the same time interval The demonstrated crosswind velocity 15 the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during certification tests The distance required to accelerate an air plane to a specified speed and assuming failure of an engine at the instant that speed is attained to bring the airplane to a stop REPORT VB 1110 1 9 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA 34 220T SENECA Route Segment A part of a route Each end of that part is identified by 1 geographical location or 2 a point at which a definite radio fix can be established Weight and Balance Terminology Reference Datum An imaginary vertical plane from which all horizontal distances are measured for balance purposes Station A location along the airplane fuselage usually given in terms of distance in inche
354. tuation of the pitch modifier will cause the autopilot to enter the ATT mode with subsequent operation as described above ALT Altitude Mode Selector Switch Selection of ALT mode will cause the autopilot to maintain the pressure level altitude at the point of engagement Because of the pitch rate control provided by the autopilot altitude mode may be engaged from any rate of climb or descent however for maximum passenger comfort rate of climb or descent should be reduced to 1000 FPM or less prior to ALT mode engagement Test See Section 4 for test procedures SPECIAL MODES AND OPERATIONS 1 Glide Slope GS Mode The GS mode is fully automatic therefore no GS engage switch is used The GS mode may be entered from either ATT mode or ALT mode from above the GS centerline or below the centeriine Activation of the GS mode depends upon satisfying two sets of conditions completion of the ARMING sequence and the salisiving of an equation relating to the aircraft s position relative to the GS centerline and the rate at which the aircraft is approaching or departing from the GS centerline For GS mode arming the following conditions must exist simultaneously No radio must be to a localizer frequency Localizer deviation must be less than 80 Localizer flag not extended valid LOC signal GS Flag not extended valid GS signal Svstem in APR mode Svstem in either ATT or ALT mode
355. uired to exert control forces in excess of 50 pounds to maintain the desired airplane attitude The pilot will have to maintain this control force while he manually retrims the airplane ISSUED APRIL 21 1981 REPORT VB 1110 REVISED FEBRUARY 25 1982 Sof 16 9 37 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 5 _ 34 220 SENECA SECTION 4 NORMAL PROCEDURES a The BATTERY switch function is unchanged and can be used in b c emergency to shut off all electrical power while the problem is isolated The RADIO POWER switch supplies power to thea avionics bus bar of the radio circuit breakers AP and TRIM circuit breakers The KFC 200 is controlled by the following circuit breakers AUTOPILOT This suplies power to the FCS KC 295 Computer KC 292 Mode Controller KA 285 Annunciator Panel and AP Pitch and Servos FCS MASTER This in with the radio power switch supplies power to the avionics bus COMPASS SYSTEM This supplies power to the KCS 55A Compass System PITCH TRIM This supplies power to the FCS Autotrim and manual electric trim systems FCS WARNING FLAGS AND ANNUNCIATORS HDG This warning flag mounted in the Pictorial Navigation Indicator will be in view whenever the directional gyro information is invalid If a HDG invalid occurs with either NAV APPR or HDG modes selected the AP is disengaged Basic AP mode may then re engaged along with
356. ulator unfeathering capability The accumulators store engine under pressure from the governors which is released back to the governors for propeller unfeathering when the propeller control lever is unlatched and moved forward from the feathered position The feathering latches hold the propeller contro lever in the feathered position and prevent inadvertent unfeathering These latches must be manually released pushed forward to unfeather the propeller but do not change the feathering procedure With this system installed the feathering time is 10 17 seconds and unfeathering times is 8 12 seconds depending on the oil temperature A feathering lock operated by centrifugal force prevents feathering during engine shut down by making it impossible to feather any time the engine speed falls below 800 RPM For this reason when airborne and the pilot wishes to feather a propeller to save an engine he must be sure to move the propeller control into the FEATHER position REPORT VB 1110 ISSUED JANUARY 8 1981 7 6 REVISED APRIL 9 1982 PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA DESCRIPTION amp OPERATION THIS PAGE INTENTIONALLY LEFT BLANK ISSUED APRIL 9 1982 1110 7 6 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION amp OPERATION PA 34 220T SENECA HI 7 9 LANDING GEAR The Seneca is equipped with hydraulically operated fully retract able tricycle landing
357. umps if vapor suppression is required LO position or the engine driven fuel pump fails position The auxiliary fuel pumps have no standby function Actuation of the switch position when the engines are operating normally may cause engine roughness and or power loss 3 15 LANDING GEAR UNSAFE WARNINGS The red landing gear light will illuminate when the landing gear is in transition between the full up position and the down and locked position The pilot should recycle the landing gear if continued illumination of the light occurs Additionally the light will illuminate when the gear warning horn sounds The gear warning horn will sound at low throttle settings if the gear is not down and locked 3 17 MANUAL EXTENSION OF THE LANDING GEAR Several items should be checked prior to extending the landing gear manually Check for popped circuit breakers and ensure the battery switch is ON Now check the alternators H it is daytime turn OFF the navigation lights ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED APRIL 9 1982 3 19 SECTION 3 PIPER AIRCRAFT CORPORATION EME RGE NCY PROCEDU RES PA 34 220T SENECA HI To execuic a manual extension of the landing gear power should be reduced to maintain airspeed below 85 KIAS Place the landing gear selector switch in the GEAR DOWN position and pull the emergency gear extension knob Cheek for 3 green indicator lights WARNING the emergency gear extension knob has been pulled
358. up the slot to the 380 pounds position 180 200 and put a dot d Move the slotted plastic again to get the zero end of the middle seat slot over this dot e Draw a line up this slot to the 250 pound position 115 135 and place the 3rd dot f 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 g As can be seen from the illustration the final dot shows the total weight to be 4115 pounds with the at 90 1 This is well within the envelope h 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 REPORT VB 1110 ISSUED JANUARY 8 1981 6 16 PIPER AIRCRAFT CORPORATION SECTION 6 PA 34 220T SENECA HI WEIGHT AND BALANCE SAMPLE PROBLEM 4750 MAX T O WEIGHT 92 94 2 4600 ed one Su xt al _ 1 4513 MAX LANDING 4 _ _ 4470 MAX ZERO FUEL WTZ pI 3225 TE 8 i 4400 4200 sins Sr di TAKEOFF WEIGHT Of 86 AND Ez 4000 i E CORSE FUEL 3800 MN NM 4 BAGGAGE 3600 a las G m Ep ae REAR SEATS 3400 En NUN ded SN MIDDLE SEATS
359. us 3 naut miles 24 naut miles S Fuel to Climb 12 gal minus 1 gal d Descent The descent data will be determined prior to the cruise data to provide the descent distance for establishing the total cruise distance Utilizing the cruise pressure altitude and OAT determine the basic fuel time and distance for descent Figure 5 37 These figures must be adjusted for the field pressure altitude and temperature at the destination airport To find the necessary adjustment values use the existing pressure altitude and temperature conditions at the destination airport as variables to find the fuel time and distance values from the graph Figure 5 37 Now subtract ihe values obtained from the field conditions from the values obtained from the cruise conditions to find the true fuel time and distance values needed for the flight plan The values obtained by proper utilization of the graphs for the descent segment of the example are shown below 1 Time to Descend 16 min minus 3 min 13 min 2 Distance to Descend 44 naut miles minus 7 naut miles 37 naut miles 3 Fuel to Descend 6 gal minus 1 gal 5 gal reference Figure 5 23 reference Figure 5 37 ISSUED JANUARY 8 1981 REPORT VB 1110 5 5 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 34 220T SENECA e Cruise Using the total distance to be traveled during flight subtract the previously calculated d
360. usly sound indicating that the failure light is disabled In this event the Pitch Trim circuit breaker should be pulled in flight wim accomplished by using the manual pitch trim wheel thy IN FLIGHT OPERATION 1 Engage Procedure After takeoff clean up airplane and establish climb Engage the FD mode first monitor flight controls and engage AP The pitch attitude will lock on any attitude upto 5 pitch attitude Engaging and holding the CWS switch allows the pilot to momentarily revert to manual control while retaining his previous modes exeept GA and conveniently resuming that profile at this discretion Disengage Procedure Check the airplane trim by monitoring the command bars before disengaging AP While monitoring the flight controls disengage the system by onc of the following methods de pressing the pilots DISC TRIM INTERRUPT switch operation of the manual trim switch or by the operation of the AP engage lever on the Mode Controller The AP light on the annunciator panel will flash at least four times and remain off and an audible warning will be heard to indicate the AP is disengaged deactivate the Flight Director System depress the FD switch on the Mode Controller or press the AP DISC TRIM INTERRUPT switch on the pilot s control wheel REPORT VB 1110 ISSUED APRIL 21 1981 9 28 10 of 16 REVISED SEPTEMBER 23 1983 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENE
361. ut and interchanged A micro switch incorporated in the throttle quadrant activates the gear warning horn under the following conditions a The gear is not locked down and the manifold pressure has fallen below 14 inches on either one or both engines b The gear selector switch is in the UP position when the airplane is on the ground To prevent inadvertent gear retraction should the gear selector switch be placed in the UP position when the airplane 1s on the ground a squat switch located on the left main gear will prevent the hydraulic pump from actuating if the master switch is turned on On takeoff whenthe landing gear oleo strut drops to its full extension the safety switch closes to complete the REPORT VB 1110 ISSUED JANUARY 8 1981 7 10 PIPER AIRCRAFT CORPORATION SECTION 7 PA 34 220T SENECA DESCRIPTION amp OPERATION arem i Ti a aa A e tata circuit which allows the hydraulic pump to be activated to raise the landing gear when the gear selector is moved to the UP position During the pre flight check be sure the landing gear selector is in the DOWN position and that the three green gear indicator lights are illuminated On takeoff the gear should be retracted before an airspeed of 108 KIAS isexceeded The landing gear may be lowered at any speed up to 130 KIAS The hydraulic reservoir for landing gear operation is an integral part of the gear hydraulic pump Access to the combination pump and r
362. v AC 43 13 2 require a Supplemental Certificate The owner or pilot is required to ascertain that the following Aircraft Papers are in order and in the aircraft a To be displayed in the aircraft at all times I Aircraft Airworthiness Certificate Form 8100 2 2 Aircraft Registration Certificate Form FAA 8050 3 3 Aircraft Radio Station License if transmitters are installed _ b To be carried in the aircraft at all times 1 Pilot s Operating Handbook 2 Weight and Balance data plus a copv of the latest Repair and Alteration Form FAA 337 if applicable 3 Aircraft equipment list Although the aircraft and engine logbooks are not required to be in the aircraft they should be made available upon request Logbooks should be complete and up to date Good records will reduce maintenance cost giving the mechanic information about what has or has not been accomplished REPORT VB 1110 ISSUED JANUARY 8 1981 8 4 REVISED SEPTEMBER 23 1983 PIPER AIRCRAFT CORPORATION SECTION 8 PA 34 220T SENECA HANDLING SERV amp MAINT 89 GROUND HANDLING a Towing The airplane may be moved the ground by the use of the nose wheel steering bar that is stowed in the baggage compartment or by power equipment that will not damage or excessively strain the nose gear steering assembly CAUTIONS When towing with power equipment do not turn the nose gear beyond its steering radius in either direction
363. ver on the Mode Controller The AP light on the annunciator panel will flash at least four times and remain off and an audible warning will be heard to indicate the AP is disengaged AP Mode The AP must be engaged before other mode can engaged The AP Mode alone provides PAH and wings level control The AP will automatically follow any other mode engaged Disengaging the AP disengages all other modes NOTE The Vertical switch located on the Mode Controller may be used to trim the command pitch attitude ata rate of one degree per second ISSUED APRIL 21 1981 16 of 16 REVISED SEPTEMBER 23 1983 PIPER AIRCRAFT CORPORATION SECTION 9 34 220 SENECA SUPPLEMENT 5 4 5 6 Altitude Hold Mode ALT When the AP is engaged and the ALT switch on the Made Controller is pressed the airplane will maintain the pressure altitude existing at the time the switch is depressed For smooth operation engage the ALT at no greater than 500 feet per minute climb or descent The ALT willautomatically disengage when the glide slope couples ALT hold may be turned off at any time by depressing the ALT switch ALT engagement is displayed on the annunciator panel NOTE The Vertical switch located on the Mode Controller may be used to change or trim the command altitude up or down at 500 to 700 FPM without disengaging the mode The new pressure altitude that exists when the
364. voided Prior to dispatch into forecast icing conditions all ice protection should be functionally checked for proper operation Before entering probable icing conditions use the following procedures a Windshield defroster ON immediately b Pitot heat ON immediately c Windshield heat ON immediately d Propeller deice ON when entering icing conditions e Wing deice ON after 1 4 to 1 2 inch accumulation Relieve propeller unbalance if required by increasing RPM briefly Repeat as required REPORT VB 1110 ISSUED JANUARY 8 1981 9 52 8 of 10 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 6 AMA WARNINGS Do not cycle pneumatic boots with less than 1 4 inch of ice accumulation operation of boots with less than 1 4 inch ice accumulation can result in failure to remove ice Do not hold momentary surface deice switch ON Heat for the lift detectors 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 knots above the stall speed A sub stantial margin of airspeed should be maintained above the normal stall speed since the stall speed may increase by up to IO knots in prolonged icing encounters M 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
365. when using NAV APR or REV modes Select desired course on 5 1 course selector or OBS and and select NAV mode for VOR tracking 5 APR Approach Mode Selector Switch provides automatic 45 VOR LOC intercept angle tracking and crosswind correction during instrument approach operations D G 5 operation and function are identicalto NAV mode Select the desired course on 5 1 or O B S and D G course selector and select APR mode 6 REV Back Course Mode Selector Switch for use in tracking the LOC front course outbound or the LOC back course inbound or the published VOR approach course outbound When using an H S L display always set the course selector on the inbound front localizer course or VOR inbound published approach course when using REV mode When using a D G the heading bug must be set to the final approach course 7 Pitch Modifier Attitude Selector Switch The pitch data modifier is a momentary type switch that is used to select the ATT mode or modify the aircraft attitude When the autopilot is engaged automatic pitch synchronization 15 provided to the attitude existing at engagement In ATT mode actuation of the modifier UP or DN will cause a pitch attitude change at a rate of ISSUED FEBRUARY 10 1984 REPORT VB 1110 11 of 20 9 145 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 21 PA 34 220T SENECA aa saa a ne T a a AAA Figure 7 cont 7 per second In ALT mode ac
366. witch is released REPORT VB 1110 ISSUED FEBRUARY 10 1984 9 150 16 of 20 PIPER AIRCRAFT CORPORATION SECTION 9 PA 34 220T SENECA SUPPLEMENT 21 7 3 INSTRUMENTS ATTITUDE GYRO Figure 7 5 Standard 3 Inch Air Driven Attitude Indicator Gyro 2 Symbolic Airplane Serves as a stationary symbol of the aircraft Aircraft pitch and roll attitudes arc displayed by the relationship between the fixed symbolic aircraft and the movable background 3 Roll Attitude Index Displays airplane roll attitude with respect to the roll attitude scale 4 Roll Attitude Scale Scale marked at 0 10 20 30 60 and 90 degrees 5 Pitch Attitude Scale Moses with respect to the symbolic airplane to present pitch attitude Scale graduated at 0 5 10 15 20 degrees 6 Symbolic Aircraft Alignment Knob Provides manual positioning of the symbolic aircraft for level flight under various load conditions ISSUED FEBRUARY 10 1984 REPORT VB 1110 17 of 20 9 151 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 21 PA 34 220T SENECA HI MB E E E NSD 360A NAVIGATION SITUATION DISPLAY _ Figure 7 7 1 NSD 360A Compass System For details of any other compass svstem refer to manufacturer s information Slaving Meter Oscillation of needle indicates that compass Is slaved to magnetic flux detector Needle maintained in either extreme position for more than 2 3 minutes ind
367. y for the operation of the airplane when the optional fixed oxygen system is installed in accor dance with FAA Approved Piper data The information contained within this supplement is to be used in conjunction with the complete handbook This supplement has been FAA Approved and must remain in this handbook at all times when the optional fixed oxygen system ts installed FAA APPROVE Web amp PO EET NEN WARD EVANS D O A NO SO I PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA ISSUED JANUARY 8 1981 REPORT VB 1110 REVISED FEBRUARY 10 1984 1014 9 9 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 2 222 PA 3 220T SENECA TIE arn n e a a A FABIA T T 3 TT THE Y T T TTE T TB MAMMA INT Y eve This fixed oxygen system provides supplementary oxygen for the crew and passengers during high altitude flights above 10 000 feet The major components of the Scott oxygen system are a 63 cubic foot oxygen cylinder an oxygen supply gauge an ON OFF flow control knob a pressure regu lator six plug in receptacles and six oxvgen masks On some models the oxygen cylinder is mounted aft in the tail conc When fully charged the cylinder contains oxygen ata pressure of 1850 psiat 70 The oxygen supply gauge is mounted in the aft overhead vent duct The oxygen flow control knob labeled Oxygen Pull On is mounted in the pilots overhead pancl The pressure regulator is mounted directly on the oxygen

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