PILOT'S OPERATING HANDBOOK

(b) Propeller Manufacturer Hartzell ( l) PropelleT Hub and Blade Models .a. Left Right b. Left Right When propeller deicing boots are installed: c. Le ft Right d. Left Right (2) Number of Bl ades McCauley (l) Propeller Hub and Blade Models a. Left b. Right SECTION l GENERAL ') Continental TSI0-360E or TSI0-360EB LTSI0-360E or LTSIG-360EB 200 215 2575 4.438 3.875 360 7.5 : I Six Cylinder, Direct Drive, Horizontally Opposed, Air Cooled BHC-C2YF-2CKF /FC8459-8R BHC-C2YF-2CLKF /F JC8459-8R BHC-C2YF-2CKUF/FC8459-8R BHC-C2YF-2CLKUF{FJC8459-8R BHC-C2YF-2CKF/FC8459B-8R BHC-C2YF-2CLKF /FJC8459B-8R BHC-C2YF-2CK UF /FC8459B-8R B_HC-C2YF-2CLKUF /F JC8459B-8R 2 3AF34C502 / 80HA-4 3AF34C503 / LSOHA-4 When propeller deicing boots are jnstalled : Same as above. 3 (2) Number of Blades (c) Propeller Diameter (1) M aximum (2) Minimum (d) Propeller Type ISSUED: SEPTEMBER 12, 1980 76 75 Constant Speed, Hydraulically Actuated, Full Feathering REPORT: VB-1140 1-3 Downloaded from www.Manualslib.com manuals search engine SECTION 1 GENERAL 1.7 FUEL (a) Fuel Capacity (U.S. gal) (total) (I) Without op ti on al tanks (2) With optional tanks (b) Usable Fuel (U. S. gal) (total) ( I} WithoL t optional tanks (2) With o~tional tanks (C) Fuel (II Minim Jm Grade (2) Altcrn.=1e Fuelf, 1.9 OIL (a) Oil Ca pa cit~ (U.S. quarts) (p er engine) (b) Oil Specific<: tion (c) Oil Viscosit: per Average Ambiem Temp . {l) Below40°F (2) Above ~0° F PIPER AIRCRAFT CORPORATION PA-34-200T. SENECA II 98 128 93 123 JOO Green or IOOLL Blue Av1allon Grade Refer to latest revision of Continental Service Bulletin "Fuel and Oil Grades" 8 Refer to latest issue of Continental Service Bulletin "Fuel and Oil Grades" A\'iation Grade 1065 1100 S.A.E .N o. 30 50 When o peraung temperatures overlap indicated nnges, use the lighter grade of oil. Multi-viscosity oils m ee ting Teledyne Continental Motors· Specifkation MHS-24A are approved. 1.11 MAXIMUM WEIGHTS (a) Maximum Takeoff Weight (lbs)/ (Kg .) (b) Maximum Landing Weight (lbs) / (Kg.) (c) Maximum Zero Fuel Weight (lbs) / (Kg.) - Standard ( d) M axirnum V. eights in Baggage Compartments (lbs) I (Kg.) REPORT: VB-1140 14 FORWARD 100 /45 4407 / 1999 4342 / 1970 4000 / 1814 AFT 100 / 45 rs 'llED: SEPTEMBER 12. 1980 Downloaded from www.Manualslib.com manuals search engine SECTION l GENERAL n n k-13_ ·6.....1-·· --,........,,, PIPER AIRCRAFr CORPORATION PA-34-200T, SENECA II Wing Area (sq. f t. ) '208.7 Min. Turning Radius (ft .) 33 .2 (from pivot point to wingtip) n ~I i------------38' lG.81"------- -----1 ---12' 5.-4 " ------i ~EPORT: VB-1140 .-2 -......,,~ 6 ' 4 " DIAMETER ======~~~~8::!E~~~~~~===~~:::==J1'.:: 0 fmHt0m "-4r/ .. L- rr .er--1 ---------28 ' 7.47"---------t .._.--11' U"-- STATIC GROUND LIME THREE VIEW Figure l · I -1 ,. )"" ISSU E D: SEPTEMBER 12, 1980 Downloaded from www.Manualslib.com manuals search engine PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA 11 l .l INTRODUCTION SECTION 1 GENERAL SECTION l GENERAL This Pilot's Operating Handbook is designed for maximum utilization as an operating guide for the pilot It includes the material required to be furnished to the pilot by FAR 23 and FAR Part 21 Subpan J. 1t aJso contains supplemental data supplied by the airplane manufacturer. This handbook is not designed as a subsiitute for adequa1e and competent flight instruction , knowledge of current airworthiness directives, applicable federal air regulations or advisocy circulars. It is not intended co be a guide for basic flight instruction or a training manual and should not be used for operational purposes unless ke pt in a cu.rrent status. As.surance that the airplane is in an airworthy conditio n is the responsibility of the owner . The pilot in command is responsible for determining that the airplane is safe for flight. The pilot is also responsible for remaining 1Nithin the operating limitations as outlined by instrument markings, placards, and this handbook. Although the arrangement of this handbook is inte nd ed to increase its in-flight capabilities, it should not be used solely as an occasional operating reference. The pilot should study the entire handbook to familiarize himself with the limitations, performance, procedures and operational handling characteristics of the airplane before flight. The han dbook has been divided into numbered (arabic) sections each provided with a "finger-tip'" tab divider for quick reference . The limitations and emergency procedures have been placed ahead of the normal procedures, performance and other sections to provide easier access to infonnation 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 by the deliberate omission o f certain paragraph numbers. figure numbers, item numbers and pages noted as being intentionally left blank. lSS U ED : SEPTEl\"IBE R 12, 1980 REPORT: VB-1140 1-1 Downloaded from www.Manualslib.com manuals search engine SECTION 1 GENERAL EPORT: VB-1140 6 PIPER AIRCRAFT CORPORATION PA-3+200T, SENECA II THlS PAGE lNTENTIONALLY LEFT BLANK JSSUED: SEPTEMBER 12. 1980 Downloaded from www.Manualslib.com manuals search engine PIPER AIRCRAFT CORPORATION PA-34-200T. SENECA ti 1.13 BAGGAGE SPACE (a) Compartment Volume (cubic feet) (b) Entry Width (inches) (c) Entry Height (inches~ I.IS SPECIFIC LOADINGS (a) Wing Loading Obs per sq ft) (b) Power Loading (lbs per hp) ( I) Sea level (2) 12,000 ft. ISSUED: SEPTEMBER 12 . 1980 FORWARD 15.3 24 21 SECTION I GENERAL AFT 17 .3 21.1 I l .0 10.2 REPORT : VB-1140 1-5 Downloaded from www.Manualslib.com manuals search engine SECTION 1 GENERAL Vy (bl Mete o rologi cal Terminology ISA OAT Indic ated Pressure Al titude Pressure Altitude Statio n Pressure Wind (c 1 Power Terminology Takeoff Powe r Maximum Con t inuou s Power .EPORT: VB-l140 ·8 PIPE R AIRCRAFT CORPORATION PA-34- 200T, SENECA II Stalling Speed or the mm1mum steady fligh1 speed at whkh th~ airplane is con tro!la ble. St aUin g Speed or rhe mrnirnum steady flight speed a.t which the airplane is controllable in the landing configu r ation. Inte nt ional One Engine In operative Speed is a minimum speed selected by the manufacturer for intentionally rendering one engine inoperative in flight. Best Angle-of-Climb Speed 1s the airspee d which delivers th~ greatest gain of altitude in the shortest possible ho rizontal distance . Bes t Rate- of-Climb Speed is the airspeed which delivers the greatest gain in al t irude in the shortest possible time . internat ional Standard Atmosp here in whid1: The air is a dry pe r fect gas; The temperature at sea level is 15° Celsius (59° Fahrenheit) ; The pressure at 5ea level is 29.92 mches hg. (lOJ3 mb); The tempe r ature gradiem from sea leveJ lo the altitude ac which che temperatur e i -56 . 5° C (-69.7°F) is -0.00198"C (- 0.003566° F) per foot and z ero above chat altitude . Outside Air Temperature is the free air static temperarurc, obtained either from mtlighl t empera t ure indicauons or ground meteoro logical sources. adjusted for instrument e rror and compressibility effects. The number actuaUy read from an allimeter when the barometric subscale has been set to 29. 92 inches of mercury (I 013 millibars). Altitude measured from standa rd sea-level pressure t2Q.92 in. Hg) by a pressure or barometric altimeter. It is Ihe indicated pressu re al r irud~ corrected for position and instrument error. 1n this handbook, altimeter instrument errors are assumed to be zero . Actual atmospheric pressure at field elevation . The wind velocities recorded as variables on lhe charts of this handbook are to be unders t ood as the headwind or lailwmd components of the reported wind s. Maximum power permissi ble for takeoff. Maximum powe r permissible continuously during flight. JSSl l EO: SEPTEMBER 12, 1980 Downloaded from www.Manualslib.com manuals search engine PI P ER AIRCRAFT C ORPOR ATION P A-34-200T, SENE CA D SECTION J GENERAL 1.17 SYMB OLS . ABBRE VIATI O NS AND T ERMINOLOGY The followmg defmitions are of symbols. abbreviations and terminology used throughout 1..he handbook and those which may be of added operational significance to th e pilot (a' General Airspeed Tenninology and Symbols CAS KCAS GS IAS K.IAS M TAS ISSUED: SE P TEM BE R 12, 1980 Calibraced Auspeed means th e indicated speed of an aircraft. corrected for position and instrument error. Cali brated airspeed is equal m true .airspeed in standard at mosphere at sea level. Calibrated Airspeed expressed in ''Knots." Ground Speed is the speed of an airplane relative to the ground . Indicated Airspeed is the speed of an aircraft as shown on the airspeed mclicat or when corrected for instrument error. IAS values published in t hi s lrnndbook assume zero instrument error . Indicated Airspeed expressed in '' Knots .'' Mach Number is the r atio of true airspeed co the speed of sound. True Airspeed is the airspeed of an airplane relative to undisturbed air which is the CAS corrected for al ti tu de, temperature and compressibility. Maneuvering Speed is Lhe maximum speed at wh.ich application of full available aerodynamic control will not overstress the airplane. Maximum Flap Extended Speed is the highest speed permissible wi th wing flaps in a prescribed extended position. 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 t he maximum speed at which the landing gear can be safely extended or retracted . Air minimum control speed 1s the minimum llight speed at which the airplane is controllable wit11 a bank of not more than 5 degrees when one engine suddenly becomes inoperative and the remaining engine is operating at takeoff power . Never Exceed Speed or Mach Number 1s the speed limit that may nor be ex c eeded at any time . Maximum Struc tural Cruising Speed is the speed that shou ld not be exL·eeded except in smooth .air and then only with caution . REPORT: VB · l140 1-7 Downloaded from www.Manualslib.com manuals search engine SECTl O 1 GENERAL Center of Gniviry (C.G.) C.G. Ann CG Limits Usable Fuel Unusab le Fuel Standard Empty Weight Basic Empty Weight Payload Useful Load Maximum Ramp Weighc Max.unum Takeoff Weight Maximum Landing Weight Maximum Zero Fuel Weight REP ORT : V B- JJ40 l-10 PIPER AIRCRAFT CORPORATION PA-34-200T. SENECA Il The point at which an airplane would balance 1f suspended. I rs distance from the reference datum is found by dividing the total moment by the ro t al weight of the airplane The arm obtained by adding rhe auplane's individual moments and dividing rhe sum by the total weight. The extreme center of gravity locacjon wnhin which the airplane must be operated al a given weighc. Fuel available for flight planning. Fuel remaining after a runout test has been completed m accordance with governmental regulations . Weight of a standard airplane including unusable fuel. full operating fluids and full oil. Standard empty weight plus optional equipment. Weighr of occupan ts. ca rgo and baggage. Difference bet ween takeoff weighL or ramp weight if applicable and basic empty weight . Maximum weight approved for ground maneuver . tll mcludes weight of start, taxi and run up fuel.) Maximum weight approved for rhe start of the takeoff run . Maximum weight approved for the landing t ouchdown. ~aximum weight exclusive of usable fuel. ISSl lED: SEPTEMBER 11, 1980 Downloaded from www.Manualslib.com manuals search engine PIPER AIRCRAFT CORPORATION PA- 34-200T. SENECA ll Maximum Climb Power Maximum Cruise P ower ( d) Engine I nstru me nts EG T Gauge Maximum power pe rm issible during climb . Maximum power permissib le du ring cnuse. Exhaust Gas Temperanire Gauge SECTIO~ I GENERAL (e) Airplane Performan ce and Flight Plannjng Terminology Climb Gradient Demonstrated Crosswind Velocity {DE MO . X- WIND) Accelerate-Stop Distance \1EA Route S egment The dem o nstrated ratio of the change in height dun ng a por tion of a climb . to th e horizontal distance traversed in the same time interval. The demonstrated crosswind velocity is the velocity of the c ro ssw ind component for which adequate control of the airplane during takeo ff and land in g was act ual ly demonstrated during certification tests. Th e distance required to accelerate an airplane to a specified"speed and, assuming failure of an engine at t he instant chat speed is attained. to bring th e airplane to a st op . Minimum en route IFR altit ude. A part of a route . Ea ch end 01 that part LS identified by ( l) a geographical location ; or (2) a point at wh.ich a definite radio fix can be established . (fl Weight and Balance Terminology Refe rence Damm St:ltion Arm Mom1:nt ISS'UED: SEPTEl\'1BER 12, 1980 An imaginary vertical plane from which all horizontal distances axe measured for balance purposes. A location along the airplane fusela ge usually given in tenns of distance from the reference datum . The ho ri zon tal distance from the reference datum to the cen t er of gravity (C.G . ) of an it em . The product of the weight of an item multiplied by its arm. (Mom~n t divjded by a cot1stant is. used to simplify balanc~ i: alcu!Jtion s by reducing t he number of digits.) REPORT: VB-1140 l-9 Downloaded from www.Manualslib.com manuals search engine PIPER AIRCRAFT CORPORATION P A-34-200T. SENECA ll l.19 CONVERSION F ACTI>RS ~ULTIPLY BY acres 0.4047 43560 0.0015625 atmospheres (atm) 76 29.92 1.0133 L033 14.70 2116 bars (bar) 0.98692 14.503768 British Thennal Unit 0.2519958 (BTU) centimete rs (cm) 0.3937 0.032808 centimeters of 0.01316 mercury at O"C 0.3937 (cm Hg) 0.1934 27.85 135.95 centimeters per 0.032808 second (cm/ sec.) 1.9685 O.QTJ37 cubic centimeters 0.03381 (cm 1 ) 0.06102 3.531 x 10·5 0.001 2.642 x ] 0-4 cubic feet (cu.ft.) 28317 0.028317 1728 0.037037 7.481 28.32 cubic feet per minute 0.472 (cu. ft./min.) 0.028317 ISSUED: SEPTEMBER 12, J98(1 TO OBTAIN ha sq. ft. sq. mi. cm Hg in.Hg bar kg/cm 2 Jb./sq. in. Ib./sq. ft. atm. lb./ sq. in. kg-cal in. ft. atm in.. Hg lb./sq. in. lb./sq . ft. kg/m 2 ft./sec. ft ./ min. mph n. oz. cu. in. cu. ft. I U. S. gal cm 3 mJ cu. in. cu. yd. U.S. gal. l I /sec. m 3 /min. MULTIPLY cubic in,ches (cu. in .) cubic meters (m 3 ) cubic meters per minute (m 3 ( min.) cubic yards (cu. yd.) degrees {arc) degrees per second (deg./sec.) drams, fluid (dr. 0.) drams, avdp. (dr. aydp.) feet (fl) feet per minute (ft/min.) BY 16.39 1.639 x 10 · S 5.787 x IO_. 0.554 l 0. 01639 4.329 x 10 3 0.01732 61024 1.308 35.3147 264.2 35.3147 27 0.7646 202 0.01745 0.01745 0 .1 25 0.0625 30.48 0.3048 12 0.33333 0.0606061 1.894 x 10 ·" J.645 x I 04 0.01136 0.01829 0.508 0.00508 SECTION 1 GENERAL TO OBTAIN cm 1 mJ cu. ft. n. oz. I U.S . gal. U.S . qt. cu. in. cu. yd . cu. ft. U.S. gal. cu. ft. / min . cu. ft. m3 U.S. gal. radians radians/ sec. fl. oz. oz. avdp . cm m in. yd. rod m1. NM mph km / hr. cm /sec . m/ sec. REPORT: VB-1140 l · ll Downloaded from www.Manualslib.com manuals search engine SECTION 1 GENERAL EPORT: VB-1140 1l PIPER AIRCRAFT CO RPO RATION PA -34- 200T, SENECA ll ISS l.JED: SEPTEMBER 12, J980 Downloaded from www.Manualslib.com manuals search engine PIPER AIRCRAFT CORPORATION P A-34-200T, SENECA Il JSSUED: SEPTEMBER 12, 198Q SECTION I GENERAL REPORT: VB-1140 1-13 Downloaded from www.Manualslib.com manuals search engine SECTION I GENERAL lEPORT: VB-1140 ~ 14 PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA ll lSSl lEO: SEPTE:\>IBER 12, 1980 Downloaded from www.Manualslib.com manuals search engine Paragraph No. TABLE OF CONTENTS SECTION 2 LIMITATIO NS Page No. 2.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1 2.3 Airspeed Limitatioru . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1 2.5 Affipee d Indicator Marking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2 2.7 Power Plant Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2 2.9 Power Plant lnstrument Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 2. 11 Weight Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4 2. I 3 Center of Gravity Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5 2. JS Maneuver Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5 2.17 Flight Load Factor Limits (Flaps U p) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5 2.19 Types of Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5 2. 21 Fuel Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6 2.23 Gyro Pressure Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6 2.2 5 Flight Into Known Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6 2. 27 Heater Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6 2. 29 Operating Altitude Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6 2.31 Noise Level . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6 2.33 Placards . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . • . . . 2-7 REPORT: VB-1140 2-i Downloaded from www.Manualslib.com manuals search engine Downloaded from www.Manualslib.com manuals search engine PIPER AIRCRAFT CORPORATION PA-34-200T, SENECAil 2.1 GENERAL SECTION 2 LIMITATIONS SECTION 2 LIMITATIONS This section provides the ·'f AA Approved" operating limitations. instrumen t markings. color coding and basic placards .necessary for the safe operation of the PA-34-200T Seneca Il and its systems. Limitations associated with those optional systems and equipment which require handbook supplements can be found in Section 9 (Supplements). 2.3 AIRSPEED LIMITATIO NS SPEED Never Exceed Speed (Vm,) - Do not exceed this speed jn any operation . Maximum Structural Cruising Speed (V No) - Do not exceed this speed except in smooth air and then only with caution. Design Maneuvering Speed (VA) - Do not make full or abrupt control movements above this speed. At 4407 LBS. ( 1999 K_g .) G . W. At 3068 LBS. (1392 Kg. ) G.W . CAUflON KlAS 195 163 135 121 Maneuvering speed decreases at lighter weight as the effects of aerodynamic forces become more pronounced. Linear interpolation may be used for intermediate gross weights. Maneuvering speed should not be exceeded while operating in rough air. Maximum Flaps Extended Sp ee d (V FE) - Do not exceed tlus speed with flaps extended. Maximum Gear Extended Sp eed ( VLE) - Do not exceed this speed with landing gear extended . Max1murn Land ing Gear Extending Speed ( V LO) - Do not. extend landing gear above this speed. lSSlED: SEPTEMBER 12, 1980 10 7 129 129 KCAS 195 165 137 12'2 109 130 1 30 REPORT: VB-1140 2-1 Downloaded from www.Manualslib.com manuals search engine SECTION 2 LIMITATIONS Maximum Landing Gear Retracting Speed (V to) - Do nm retract Landing gear above this speed. Air Minimum Control Speed 01 Mc) - Lowest airspeed at which airplane is controllable with one engine operating and no flaps. Best Single Engine Rate of Climb Speed 2.5 A1RSPEED INDICATOR MARKINGS MARKING Green A.re (N onnal Operating Range) Yellow Arc (Caution Range - Smooth Air) White A.re (Flaps Extended Range) Radial Red Line (Never Exceed - Smooth Air) Radial Red Line (Minimum Control Speed- Single Engine) Rad iaJ Blue Line (Best Rate of Climb Speed - Single Engine) 2.7 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 Sea level 12,000 ft. (2) Maximum Rotational Speed (RPM) (3) Maximum Manifold Pressure (Inches of Mercury) (4) Maximum Cylinder Head Temperature (5) Maximum Oil Temperature (e) Oil Pressure Minimwn (red line) Maximum (red line) (f) Fuel Flow Nonnal Operating Range (green arc) Maximum at Sea Level (red line) lg) Fuel (minimum grade} (h) Number of Propellers ~EPORT ; VB-1140 i PIPER AIRCRAFT CORPORATION PA-34-200T , SENECA 11 KIAS 107 66 89 KCAS 109 69 90 KIAS 63 to 163 l63 to 195 61 to 107 195 66 89 2 Co .n tinental TSI0-360E or TS10-360EB LTSI0-360E or LTSI0-360EB 200 215 2575 40 460"F 240°F 10 PSI I 00 PSI 3 .5 PSI to 20 PSI 25 GPH (20 PSI) 100 or IOOLL A Vlation Grade 2 ISSUED: SEPTEMBER 12, 1980 Downloaded from www.Manualslib.com manuals search engine SECTION 2 LIMITATIONS Maximum Landing Gear Retracting Speed (V LO) - Do not ret ract landing gear above this speed. Air Minimum Control Speed (V Mc) - Lowest airspeed at which airplane is controllable with one engine operating and no flaps. Best Single Engine Rate of Climb Speed 2.5 AIRSPEED INDICATOR MARKINGS MARKING Green Arc (Normal Operating Range) Yellow Arc (Caution Range- Smooth Air) White Arc (Fla ps Extended Range) RadiaJ Red Line (Never Exceed - Smooth Air) RadiaJ Red Line (Minimum Control Speed - Single Engine) Radial Blue Line (Best Rate of Oimb Speed - Single Engine) 2.7 POWER PLANT LIMITATIONS (a) Number of Engines (b) Engine Manufacturer (c) Engine Model Number (1) Left (2) Right (d) Engine Operating Llrnits (I) Rated Horsepower Sea level 12,000 ft. (2) Maximum Rotational Speed (RPM) (3) Maximum Manifold Pressure Unches of Mercury) ( 4) Maximum Cylinder Head Temperature ( 5) ~fax.imum Oil Temperature (e) Oil Pressure Minimum (red line) Maximum (re d line) (0 Fuel FJow Normal Operating Range (green arc) Maxim um at Sea Level (red line) (g) Fuel (minimum grade ) (h) Number of Propellers lEPORT: VB - 1140 I r PIPER AIRCRAFT CORPORATION PA-34-200T. SENECA Il KlAS 107 66 89 KCAS 109 69 90 KIAS 63 to l63 163 to l95 61to107 195 66 89 l Continental TSI0-360E or TSI0-360EB LTSI0-360E. or LTSI0-360EB 200 215 2575 40 460gf 240°F 10 PSI J 00 PSI 3.5 PSI to 20 PSI 25 GPH (20 PSI) 100 or IOOLl. Aviation Grade 2 ISSl ED: SEPTEMBER 12, 1980 Downloaded from www.Manualslib.com manuals search engine PIPER AIRCRAFT CORPORATION PA- 34-200T, SENECA D ( j) Propeller Manufacturer: Hartzell Propeller Hub and Blade Mod els a. Left Right b. Left Right When propeller deicing boots are installed: c. Left Right d . Left Right NOTES SECTJON 2 LIMITATIONS BHC-C2YF-2CKF /F C8459- 8R BHC-C2YF- 2CLKF / FJC8459-8 R BHC-C2YF- 2CKUF /FC8459-8R BHC~2YF- 2CLK UF/ FJ C 8459 - 8R BHC-C2YF-2CKF(FC8459B-8R BHC-C2YF-2CLKF/FJC8459B-8R BHC-C2YF-2CKUF / FC8459B-8R BHC-C2YF-2CLICUF /FJC8459B-8R Avoid continuous operation between 2000 and 2200 RPM above 32 IN. HG. manifold pressure. Avoid continuous ground operation between 1700 and 2100 RPM in cross and tail winds over 10 knots. McCauley Propeller Hub and Blade Models a. Left b. Right When propeller deicing boots are installed: Same as above . (j) Propeller Diameter (inches) Maximum Minimum 2.9 POWER PLANT IN ST RUMENT MARKINGS ( a) Tachometer Green Arc (Normal Operating Range) Red Line ( Maximum) ISSUED: SEPTEMBER 12, 1980 3AF34C502 / 80HA-4 3AF34C503 / L80HA-4 76 75 500 RPM to 2575 RPM 2575 RPM REPORT : V B- 1140 2-3 Downloaded from www.Manualslib.com manuals search engine SECTION 2 LIMITATIONS (b) FueJ Flow and Pressure Green Arc (Normal Operating Range) Red Line (Maximum at Sea Level) Red Line (Minim um) (c) Cylinder Head Temperature Green Arc (Nonna! Range) Red Line (Maximum} (d) Oil Temperature Green Arc (Nonna) Operating Range) Red Line (Maximum) I e) Oil Pressure Green Arc (Normal Operating Range) YeJlow Arc (Caution) Red Line (Min.imwn} Red Line (Maximum) (f) Manifold Pressure Green Arc (Normal Operating Range) Red Line (Maximum) (g) Exhaust Gas Temperature Red Line 2.1 1 WEIGHT LOOTS (a) Maximum Takeoff Weight (b) Maximum Landing Weight (c) Maximum Weights in Baggage Compartments Forward Aft PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA ll 3.5 PSI to 20 PSI 25 GPH (20 PSI) 3.5 PSI either 360• F to 460°F or 240°F to 440°F 460°F either 7 5 °f t:O 240° F or 100°F to 240" F 240°F either 30 PSI to 80 PSI or 30 PSI to 60 PSI 10 PSI co 30 PSI and, either 80 PSI to l 00 PSI or 60 PSI to 100 PSI 10 PSI I 00 PSI 10 IN. to 40 IN . HG. 40 IN. HG. l650°F 4407 LBS { 1999 Kg.) 4342 LBS ( 1970 Kg.) (d) Max.imum Zero Fuel Weight - Slandard (See page 6.6 1 and 6-62. ) 100 LBS {45 Kg.) JOO LBS (45 Kg.) 4000 LBS (1814 Kg.) EPORT: VB-I 140 4 lSSUED: SEPT£)1B£R 12. 1980 Downloaded from www.Manualslib.com manuals search engine PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II 2.13 CENTER OF GRAVITY UMITS SECTION 2 LIM.ITATIONS Weight Pounds Forward Limit lnches Aft of Datum Aft Limit Inches Aft of Datum 3400 4407 82.0 89.4 NOTES Straight line variation between the points given. Datum is 78.4 inches forward of wing leading edge from the inboard edge of the in board fuel tank . It is the responsibility of the airplane owner and the pilot to assure that the airplane is properly loaded. Maximwn allowable gross weight is 4407 ( 1999 Kg.) pounds. See "Weight and Ba lance Section" for proper loading instructions. 2 .1 5 MANEUVER LIMITS 94 .6 94 .6 AU int.entional acrobatic maneuvers (including spins) are prohibited. Avoid abrupt maneuvers. 2.17 FLIGHT LOAD FACTOR LIMITS (Flaps Up) (a) Positive Load Factor (Maximwn) (b) Negative Load Factor (Maximum) 2. 19 TYPES OF OPERATIONS 3.8 G No inverted maneuvers approved The airplane is approved for the following operations when equipped in accordance with FAR 91 or FAR 135. (a) Day V .F .R. (b) Night V.F.R. (c) Day l .F.R. (d) Night I.F .R. (e) Icing conditions when equipped pe r Section 2.25. ISSGED: SEPTEMBER 12. 1980 REPORT: VB-J 140 2-5 Downloaded from www.Manualslib.com manuals search engine SECTION 2 LIMITATIONS 2.21 FUEL LIMITATIONS (a) Unusable FueJ PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA ll The unusable fue1 in this aircraft has been determined as 2.5 gallons in each wing in critical flight attitudes (2.5'gallons is the total per side. each side having interconnected tanks) . (b) Usable Fuel The usable fuel in this aircraft has been determined as 46. 5 gallons in each wing or a total of 93 gallons with standard fuel tanks and 61.5 gallons in each wing or a total of 123 gallons with optional fuel tanks installed. 2.23 GYRO PRFSSUR£ LIMITS The ope rating limits for the pressure system are 4.5 co S .2 inches of mercury for all operations as ind1cated by the gyro pressure gauge. '-· ; FLIGHT INTO KNOWN ICING CONDITTONS For flight in icing conditions the following equipment mu.;t be installed in acco rdan ce with Piper drawing.5 or in an FAA approved manner: (a) Pneumatic wing and empennage boots (b) Electrothermal propeller boots {c) Electric windshield panel (d) Heated pitot head (e) Wing ice light ( f) Heated lift detectors (g) Propeller spinners must be instaUed. 2. 27 HEATER LIMITATIONS Operation of the combustion heater above 25,000 feet is not approved. L"" 0 OPERATING ALTITUDE LIMITATIONS Flight above 25,000 feet is not approved. Flight up to and including 25,000 feet is approved if :quipped with oxygen in accordance with FAR 23.1441 and avionics in accordance with FAR 91 or FAR 35. t3 l NOISE LEVEL The noise level of this aircraft is 73. I dB( A) when equipped with two bladed propellers and 76.0 lB(A) when equipped with th ree bladed p rop ellers. No determination has been made by the Federal Aviation Administration that the noise levels of this iirpiane are or should be acceptable or unacceptable for operation at. into, or out of, any airport. : EPORT: VB-1149 .(. TS S l t::D: SEPTEMBER 12. 11980 Downloaded from www.Manualslib.com manuals search engine 'WARN~NG Severe Icing may result from environmental cond itions oulsl de of those for which the airplane Is certificated. Flight In freeting rain, freezing dr1zzle, or m l xed Icing oondltlons (supercooled liquid water and lea crystals) may result In Ice bulld- up on protected surfaces exceedi ng the capabmty or the Ice protection sys1em, or may r esull ln lee forming aft or the protected surfaces. This Ice may not be shed using the lea protection systems, and may seriously degrade the performance and controllablllty of the airplane. • Our1ng flight, se.vere lcinQ conditions that exceed those for which the ai rp lane Is certi ficated s hall be determined by the following 'vtsual cues. If one or rn.ore of these visual cues exists, Immediately requ est priority handling from Air Traffic Con trol to racllitat e a route or an attitude change to exlt the Icing conditions. · - Unusually extensi ve lee accumu lati on on the .airframe and windshi eld In areas not normally observed to collect tee . - Accumulation of Ice on the upper surface or the wi ng. aft or the protecte<l area . ·Accumula tion of Ice on lhe eng in e nace tl.es an propsrter sp inners farther aft than nomlafly observed. • Since the autopilot, when installed an operating, m ay mask tactile cues ltrnl indic ate adverse cnanges in handling charac1erislics, use o1 the autopilot is prohibited when any of the visual cues s~ecirie<1 ~bove ex i ~t . or when unusual lateral trim requ ireme nts or autopilot trim warnings are encountered wlule the airplane •s m severe Ic ing conditions. •All wing icing inspection lights must be operative prior lo flight Into known or forecast icing conditions al night. (NOTE: T his supersedes any relier provided by the Master Minimum Equi pment List (MMEL} .)' Downloaded from www.Manualslib.com manuals search engine SECTION 2 LIMITATIONS PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA ll Near emergency gear release: EMERGENCY GEAR EXTENSION PULL TO RELEASE . SEE P.O.H. BEFORE RE-ENGAGEMENT Near gear selector switch : GEAR UP DOWN l 07 KIAS MAX. 129 K.IAS MAX. Adjacent to upper door latch (Fro nt and rear doors): ENGAGE LATCH BEFORE FUGITT In full view of pilot: WARNING - TURK OFF STROBE LJGHTS WHEN TAXITNG IN VICINITY OF OTHER AIRCRAFT. OR DURlNG FLIGHT TH RO UGH CLOUD. FOG OR HAZE. On the inside of forward baggage compartment door: ·MAXIMUM BAGGAGE TIIlS COMPARTMENT 100 LBS. SEE THE LIMITATIONS SECTION OF THE PILOT'S OPERATING HANDBOOK. On aft baggage closeout : MAXIMUM BAGGAGE THIS COMPARTMENT 100 LBS. NO HEAVY OBJECTS ON HAT SHELF. On instrument p anel: U?.PORT: VB-1140 l-~ SINGLE ENGINE STALLS NOT RECOMMENDED. CAN CAUSE 500 FT. LOSS OF ALTITUDE AND 15° PITCH ANGLE. ISS UE D: SEPTEMBER 12. 1980 Downloaded from www.Manualslib.com manuals search engine PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II SECTJON 2 LIMITATIONS 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 S tandards - Aircraft Type and Airworthiness Certificaton. This aircraft model is in compliance with all FAR 36 noise standards applicable to this type. 2.33 PLACARDS In full view of the pilot: THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND MANUALS. NO ACROBATIC MANEUVERS (INCLUDING SPINS) APPROVED. - nns AIRCRAFr APPROVED FOR V.F.R.. 1.F.R., DAY, NIGHT AND ICING FLIGHT WHEN EQUIPPED IN ACCORDANCE WITH FAR 91 OR FAR 135. In fuJl view of the pilot: MAXIMUM TAKEOFF WEIGHT 4407 POUNDS MAXIMUM LANDING WEIGHT 4342 POUNDS ALL WEIGHT IN EXCESS OF 4000 POUNDS MUST CONSIST OF FUEL (EXCEPT IN CASES SPECIFIED BY SECTlON 6 OF P.O.H.) . MlN1MUM SINGLE ENGlNE CONTROL SPEED 66 KlAS On instrument panel in full view of the pilot: GEAR DOWN GEAR UP EXTENDED VA 135 AT 4407 LBS . (See P.O. H.) 129 KIAS (MAX.) OR V LO 129 DN, 107 UP 107 KIAS(MAX .) VLE 129 MAX . 129 KlAS(MAX.) DEMONSTRATED CROSSWIND COMPONENT 17 KTS OR DEMO X-WlND 17 KTS IS UEO: SEPTEMBER 12. 1980 REPORT: VB-1140 2-7 Downloaded from www.Manualslib.com manuals search engine PIPER AIRCRA.Ff CORPORATION P A-34-200T, SENECA II On instrument panel or sun visor: SECTJON 2 LIMITATIONS TAKEOFF CHECK UST Fuel Selectors On LANDING CHECK LIST .. LANDING CHECK LIST Aux . fuel Pump Off Alternators On Engine Gages Checked Mixtures Set Propellers Set Alt. Air Off Cowl Flaps Open Seat Backs Erect Flaps Set Trim Set (Stab. & Rudder) Fasten Belts I Harness Controls Free - Full Travel Doors Latched I Air Cond . Oft Seat Backs Erect Fasten Belts / Harness Fuel Selectors On Cowl Flaps Set Mixtures Rich Aux. Fuel Pump Off Propellers Set Gear Down Flap Set - 107 KIAS Max. Air Conditio ne r Oft OR Seat Backs Erect Fasten Belts / Harness Fuel Seiectors On Cowl Flaps Set Mixtures Rich Aux . Fuel Pump Off PropeUers Set Gear Down Flap Set - (Wrute Arc) Air Conditioner Off' The '" Air Conditioner Off' item in the above takeoff and landing check lists is mandatory for air conditioned aircraft only. On storm window : DO NOT OPEN ABOVE J 29 KIAS Near windshield pane) heat switch with windshield heating installation= WINDSHIELD PANEL HEAT - SEE PILOT'S OPERATING HANDBOOK . On engine instrument paneJ cm·er to left of engine controls with windshield heatmg installation without the entire lee Protection System instal led ; WARNING - THIS AIRCRAFT IS NOT APPROVED FOR FUGITT IN ICING CONDITIONS. In full view of the pilot f01 flight with the aft fuselage doors removed: FOR FLIGHT WITH AFT DOORS REMOVED , CONSULT THE LIMITATIONS AND PROCEDURES SECTIONS OF THE PILOT'S OPERATING HANDBOOK. Beneath the pitot heat swi t ch: GND. OPP. 3 MIN. MAX. On t he inside of both oil filler access doors: ·OIL COOLER WlNTERIZATION PLATE TO BE REMOVED WHEN AMBIENT TEMPERATURE EXCEEDS 50°F. lSS UEO: SEPTEMBER 12, 1980 REPORT: VB·1140 l-9 Downloaded from www.Manualslib.com manuals search engine SECTION 2 LIMITATIONS PIPER AIRCRAFT CORPORATION PA-34-200T. SENECA II On the throttle quadrant below engine and propeller controls : USE PROP SYNC MANUAL FORT AKE-OFF LANDING AND SINGLE ENGINE OPERATION S. On the executive writing table: CAUTION - nns TABLE MUST BE STOWED DURING TAKEOFF AND LAND ING. On the instrument panel in full view of the pilot: AVOID CONTINl:OUS GROUND OPERATION 1700 - 2IOO RPM IN CROSS / TAIL WlND OVER JO KT AVOID CONTINt;OUS OPERATIONS 2000 · 2200 RPM ABOVE 32" MANIFOLD PRESSURE Adjacent to fuel tank fill caps wilh standard fuel tanks installed: FUEL - 100 / 130 AVIATION GRADE - USABLE CAPACITY 46.5 GAL OR FUEL - JOO OR IOOLL AVIATION GRADE Adjace nt to fuel tank filler caps with optional fuel tank installed: REPORT: VB-1140 2- 4-L) FUEL - 100 / !30 AVIATION GRADE - USABLE CAPACITY 61.5 GAL OR FUEL - 100 OR JOOLL AVIATION GRADE ISSUED: SEPTEM.BER 12. 1980 Downloaded from www.Manualslib.com manuals search engine PlPER AIRCRAFT CORPORATION PA-34-200T, SENECA II On instrument panel or sun visor: SECTION 2 LIMITATIONS TAKEOFF CHECK UST Fuel Selectors On LA~Dll\G CHECK LIST .. LANDING CHECK UST Aux. Fuel Pump Off Alternators On Engine Gages Checked ;vtixtures Set Propellers Set Alt. Air Off Cowl Flaps Open Seat Backs Erect Flaps Set Trim Set (Stab. & Rudder) Fasten Belts / Harness Controls Free - Full Travel Doors Latched / Air Cond. on Seat Backs Erect Fasten Belts/ Harness Fuel Se.lectors On Cowl Flaps Set Mixtures Rich Aux . Fuel Pump Off Propellers Set Gear Down Flap Set - 107 KlAS Max . Air Conditioner Of{ OR Seat Backs Erect Fasten Belts / Harness Fuel Selectors On Cowl Flaps Set Mixtures Rich Aux . Fuel Pump Off Propellers Set Gear Down FJap Set - {Wh ite Arc ) Air Conditioner Off' The ''Air Conditioner Off' item m the above takeoff and landing check lists is mandatory for air conditioned airc raft only. On storm window: DO NOT OPEN ABOVE 129 KIAS Near \\indsh.ield panel heat switch with windshield heating installation: WINDSHIELD PMTEL HEAT - SEE PILOT'S OPERATING HANDBOOK. On engine instrument panel cover to left of engine controls with windshield heating installation without the entire Ice Protection System installed ~ WARNlNG - THIS AIRCRAFT lS NOT APPROVED FOR FLIGHT IN ICING CONDITJONS. In full view of the pilot for flight with the aft fuselage doors removed: FOR FLIGHT WITH AFT DOORS REMOVED, CONSULT 11IE LIMITATIONS AND PROCEDURES SECTIONS OF THE PILOTS OPERATING HANDBOOK. Benea th the pitot heat switch : GND.OPP. 3 MIKMAX . On the inside of both oil filler access doors : ·OIL COOLER WINTERIZATION PLATE TO BE REMOVED WHEN AMBIENT TEMPERATURE EXCEEDS 50°F. ISSUED: SEPTEMBER 12, 1980 REPORT: VB -1140 2.-9 Downloaded from www.Manualslib.com manuals search engine TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Paragraph No. 3.1 3.3 3.5 3.7 3.9 3.11 3.13 3.15 3.17 3.19 3.21 3.23 3.25 3.27 - 29 .... .31 3.33 3.35 3.37 J . 39 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . • . . . . . . . Emergency Check Llsr . . .. .... ..... . ... ..... .... . ... .. .. • . . . ... Amplified Emergency Procedures (General) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine lnoperative Procedures . .. . . ... . . . .. ... . ............. . .... . Detecting A Dead Engine . . . . . . . . . . . ..... • . ... .. ... ... ..... . . Engine Securing Procedure (Feathering Procedure) .. . ... .. ... .. .... .. ... . Engine Failure During Takeoff (Below 85 KIAS) . . ........... . . .. . .••.• . Engine Failure During Takeoff (85 KIAS or above) . . . . . . • . . . . . . . •• ..... Engine Failure During Climb . .. . ..... ... .... ....... .. ... . - .. • . . Engine Failure During Flight (Below 66 KIAS) ..... .... ... . .......... . . Engine Failure During Flight (Above 66 KIAS) .. .......... .. .... . ..... . Single Engine Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . Single Engine Go-Around . . . . . . . . . . . . . . . . . . . . . . . . . . . . ... . Air Start (Unfeathering Procedure) . ..... . . . . ... . ..... .. ... ...... . . Engine Fire . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Management During Single Engine Operation . . . . . . . . . . . . . . . . . . . . . . . . . Engine Driven Fuel Pump Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Landing Gear Unsafe Waming.5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . ... . Manual Ex tension of the Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . .. . . Gear Up Emergency Landing .... ... .. . .. . . . ... ... .. . .. ......... . . Engine Failure in king Conditions ... . .. . ................ . .... . . ... . AJtemator Failure in Icing Conditions ... . . .. ... .. . . .. . ...... ....... . Engine Failure with Rear Cabin And Cargo Doors Removed ..... .. .. .. . .. ... . Electrical Failures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . - . . Gyro Pressure Failures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . Combustion Heater Overheat ......... .... ....... . ... . .... ..... . Spin Recovery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . Emergency Descent . . . ..... . ..... .... ... ........ ...•.... Door Open on Takeoff . ... . ... . ........... _ .. . ........ ...... . Dual Alternator Fa1lu re . . ..... ........ .. ............... .... ................... . . . Page No. 3- 1 3-3 3.9 3-9 3-9 3-9 3- 10 3-10 3-10 3-1 l 3- 11 3-11 3- 12 3-1 2 3-12 3-13 3- 14 3- 14 3-14 3-15 3-15 3-15 3-15 3- 16 3-16 3-1 6 3- 17 3-17 3-17 3-17 REPORT: \'B-1140 3-i Downloaded from www.Manualslib.com manuals search engine PIPER AIRCRAFf CORPORATION PA-34-200T , SENECA II 3. J GENERAL SECTION 3 EMERGENCY PROCEDURES SECTION3 EMERGENCY PROCEDURES The recommended procedures for coping with various types of emergencies and critica l situations are provided in this section . All of the required (FAA regulations) emergency procedures and those necessary for the safe 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 req u.ire handbook supplements are provided in Section 9 (Supplements). The first portion of this section consists of an abbreviated emerge ncy check list which supplies an action sequence for critical situations with little emphasis on the operation of systems. The remainder of the section presents amp1ified emergency procedures containing a dd itio nal infonnation to provide the pilot with a more complete understanding of the procedures. These procedures are suggested as a course of action for coping with the particular condition described, but are not a substitute for sound judgment and common sense. Pilots should familiarize themselves with the procedures given in thi s sectio n and be prepared to take appr op riate a ctio n should an emergen cy arise. Most basic emergency procedures, s uch 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 review standard emergency procedures periodically to remain proficient in them . ISSLED: SEPTEMBER 12. 1980 REPORT: ' 18-1140 J..I Downloaded from www.Manualslib.com manuals search engine SECTION 3 EMERGENCY PROCEDURES ~£.PORT: VB-1140 -2 PlPER AlRCRAFT CORPORATION PA-34-200T. SENECA II THJS PAGE INTENTIONALLY LEFf BLANK ISSl ,f:D: SEPTE:'\·1B£R 12, J980 Downloaded from www.Manualslib.com manuals search engine PlPER AIRCRAFT CORPORATION PA- 34- 200T. SENECA Il 3.3 EMERGENCY CHECK UST AIRSPEEDS FOR SAFE OPERATIONS M.inimum Single Engine Control . . ..... . Best Single Engine Rate of Oimb . . . .. .. . Best Single Engine Angle of Oimb Maneuvering . Never Exceed . . 66 KIAS 89 KlAS 78 KIAS .. l21 KIAS .. 195 KIAS ENGINE INOPERATIVE PROCEDURES DETECTING DEAD ENGINE Loss of thrust. Nose of aircraft will yaw in direction of dead engine (with coordinated controls). ENGINE SECURING PROCEDURE (FE ATHERING PROCEDURE) To attempt to restore power prior to feathering: Mixtures . . . . . . . . . . . . . . .. . - as required Fuel selector . . . . . . . . . . - . . . . cross feed Magnetos . . . . . . . . . . . left or right only Alternate air .. . _ . - . . . . . . . ........ON Auxiliary fuel pump ......... unlatch, on Jil, if power is not .immediately restored, OFF Feather before RPM drops below 800. ~tinirnum control speed ......... . 66 KIAS Best S.E. R/C ................ 89 KIAS Maintain direc tion and airspeed above 76 KJAS . Mixture controls . . . . . . . .. forward Propeller controls . . . . . . . . . . .. forward Throttle controls . . . . . .... forward Flaps ..... . - .. . Gear ... . .... . . Identify inoperative engine. Th r ottle of inop. engine Mixture of inop. engine (40 in Hg max.) . retract . _ . _ . . . . . retract ... . retard to verify ..... idle cut-off lSS VED~ SEPTEMBER 12. 1980 SECTION 3 EMERGENCY PROCEDURES Prop controJ of inop. engine .. feather _ . as req mred Trim .. . . . . Auxiliary fuel pumps . . ........ OFF (except in case of engine driven pump failure) Magnetos of inop . engme . . . . . . . . . . . OFF Cowl flaps . . . . . . . , .. close on inop . engine. as required on operative engine .. . . OFF . . . . . . . . . . reduce . . . . . . OFF inop . engine. consider crossfeed Alternator of inop. engine . Electrical load ... . . Fuel management .. . ENGINE FAILURE DURING TAKEOFF (Below 85 KIAS) If engine failure occurs during takeoff and 85 KlAS has not been attained: Throttles . . . . . . . . . . . . . . . . . CLOSE both St op straight ahead. If inadequate runway remains to stop : Throttles _ . . . . . . . . . . . Brakes . . . . . ..... immediately .. CLOSED apply max. braking Master switch . .... . ..... OFF Fuel selectors . . . . . . . . . . . . . . . OFF Continue straight ahead. turning to avoid obstacles . ENGLNE FAILURE DURING TAKEOFF (85 KlAS or above) If engine failure occurs during takeoff ground roll or after lift-off with gear still down and 85 KIAS has been attained· If ai:lequate runway rem ains CLOSE both throttles irnmedfately. land i f airborne and stop straight ahead . If runwav remaining is inadequate for stopping, decide whether to abort or continue. If decision i.s made to continue , maintain beading and airspeed, retract landing gear when climb is established and feather inoperative engine prop (see Engine Secwing P r ocedure). REPORT: VB-1140 3-3 Downloaded from www.Manualslib.com manuals search engine SECTION 3 EMERGENCY PROCEDURES ENGJNE FAILURE DURlNG CL™B If engine failure occurs when airspeed js below 66 KlAS : Rudder . . . . .... Throttles . . apply towards operating engine . reduce throttle settings as required to maintain directional control ose . . . . . . . . . . .. lower nose to accelerate best single engine rate of cl imb speed (89 Kli\S) Operative eng. . . . . . . . ... increase power as airspeed increases above 66 KlAS Inoperative engine prop .. . . ..... FEATHER (see Engine Securing Procedure) If engine failure occurs when airspeed is above 66 KlAS : Maintain directional control. Adjust airspeed toward the best single engine rate of climb speed (89 K1AS) . Inoperative engine prop .. . ... ... FEATHER (see Engine Securing Procedure) ENGINE F All.URE DURING FLIGHT <Below 66 KIAS) Rudder . . ... . Throttles (both engines) Pitch attitude . . . . . . .apply towards ope rat ive engine . .. . . retard to stop tum . . . . . . . . lower nose to accelerate above 66 K.IAS (\- 0 .rative eng ..... . . .. .. increase power as airspeed increases above 66 K1AS If altitude permits, a restart may be attempted . lf restart fails or altitude does not permit: lnop. eng. prop. . . . . . . . . . . . . . . . . . . . FEATHER Trim ... .... ......... .. ... . .. ... adJUSt s~ bank. toward operative eng. [nop. eng. ... . .. . . . ........... complete En,gine Securing Proce-Oure :owl tla p (o perative eng.) . . ........ . . as required RE.PORT: \IB -1140 3-"' PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA Il ENGINE FAILURE DURING FLIGHT (Above 66 JOAS) Rudder ..• lnop. eng.. . Operative eng . .. .. .. apply toward operative engine . . . . . identify adjust as required Before securing inop . engine : Fuel flow ...... ... ... check (if deficient- auxiliary fuel p wn p Hl BOOST. if power is not restored, OFF Fuel quantity . .. . .. . . . . . . .. .... chec k Fuel selector (in op . eng .) . . . . . . . . . cross feed Alternate arr . . . . . . . . . . . . . . . .ON Mixture . . . . . . . . . . . • . . . . . . check Oil pressure and temp . . .. . ... _ ..... check Magneto switches . . . . . . . . . . . . . . . check If engine does not start. co mple te Engine Securing Procedure. Power (operative eng .) . Mixture (operative eng.) FueJ quantity (operative eng. tank) .. ... . Auxiliary fue I pump . . . . as required . adjust for power . sufficie nt (operative eng.) .... . ..... .. . as required Cowl flap (operative eng.. ) . .. . . . . . ... . . ... .. . as required Trim ( Rudder) ... _ . .. .. .... ..... adjust 5°- bank lOward operative eng . Electrical load ......... . . . decrease to min. required Land as soon as practical at nearest suitable airport . SINGLE ENGINE LANDING Inop. engine prop . . .... . feather When certain of making field: Landing gear . . . . . . . . . . . . . . . . . .extend. Wing flaps . . . . . . . . . . . . . . low er Maintain additional altitude and speed during approach. Final approach speed . . . . . . . . 91 KIAS 2-0 Wing flaps . . . . . . . . . . . . . . • . . . . . :> I ' Sl ' ED; SEPTEMBER 12. 1980 Downloaded from www.Manualslib.com manuals search engine PIPER AffiCRAFT CORPORATION PA-34-200T, SENECA 0 SINGLE ENGINE GO-AROUND (Avoid if at all possible.) Mixture . Propeller . Throttle . Flaps ... Landing gear Airspeed . .. .. .. . Trim . . ... . .. . Cowl fl ap operating engine • forward .. forward .open slowly to 40in Hg . . .. retract ..... retract ..... .. 89 KlAS . .......... set ... ... as required AIR START (UNFEA THE RING PROCEDURE) Fuel selector inop. engine ... . ...... . . . ON Aux . fuel pump inop. engine . . ... ..... OFF Throttle . . . . . . . . . open 1 /4 inch Prop control . . . . . . . forward to Mixture .. Magneto switches Starter . Throttle cruise RPM position .... RICH .... ......... . ..ON . . . .engage un tiJ prop windmills ... reduce power until engine is wann If engine does not start, prime as required. Alternator . . . . . . . . . . . . . . . . . . . . . . ON ENGlNE FIRE ON GROUND If engine has not started: Mixture .. . .. . Throttle Starter . .. idle cut-off ...... open . crank engine If engine has already started and is running , continue o perating to try puJling the fire into the engine. If fire continues , extinguish with best available means. If external fire extinguishing is to be applied: Fuel selector valves ..... .. OFF Mixture . . . . . . . . . . . . . . . ... idle cut-off lS SLE D: SEPTEMBER 12. 1980 SECTION 3 EMERGENCY PROCEDURES ENGINE FrRE IN FLIGHT Affected engine : Fuel selector . .....•. Tiuottte Propeller ... . ...... . Mixture Heater . ... ..... •.. ... Defroster ..... . . . OFF . close feather . idle cut-off . OFF . . OFF tf terrain permits land immediately , if fm continues. FUEL MANAGEME NT DUR.ING S.INGl.E ENGINE OPERATION CRUISING When using fuel from tank on the same si de as the operating engine: FueJ selector operating engine .. . ... ...ON Fuel selector inop . engine ........ . ... OFF Auxiliary fuel pumps . . . . . . . . . . . . . . . OFF When using fuel from tank on the side opposite the operating engine: Fuel selector operating engine . • .. CROSSFEED Fuel selector inop. engine . . . . . . . . . . . . OFF Auxiliary fuel pumps ......... • .... . OFF Use crossfeed in level flight only. NOTE Do not crossfeed with full fuel on same si de as operating engine since vapor return fuel flow will be lost through the vent system . LANDING Fuel selector operating engine Fuel selector inop. engine .. .. .. ....ON . . - .. OFF REPORT: VB-1140 3-5 Downloaded from www.Manualslib.com manuals search engine SECTION 3 EMERGENCY PROCEDURES J:.NGINE DRIVEN FUEL PUMP F AILUR£ Throttle . . . . . . . . . Auxiliary fuel pump Throttle . . retard . unlatch, onHl reset (75% power or below) CAlfIIONS l f normal engine operation and fuel flow is not immediately re~stablished. the auxiliary fuel pump should be turned off. T he lack of a fuel now indication while on the HI auxiliary fuel purn p position t:ould indicate a leak in the fuel system, or fue1 exhaustion. DO NOT actuate the auxiliary fuel pumps unless vapor suppression is required (LO position) or the engine driven fuel pump fails ( ID pos ition) . The auxiliary pumps have no standby functlon. Actuation of the HI swit ch position when the engines are operating, normally may cause engine roughness and/ or power loss. LANDING GEAR UNSAFE WARNING Red light indicates gear intransit. Recycle gear if indication continues. Light will illuminate when gear horn sounds at low throttle settings. MANUAL EXTENSION OF LANDING GEAR C' ·sk following before extending gear manually: C._~uit breakers . . . . . . . . . . ch eck Master switch . . . . . . . . . . . . . .ON Alternators . . . Navigation lights . . . check . ... OFF ( daytime) To extend, reposition clip downward clear of knob ind pro ceed as follows: .\.irspeed . . . . . . :;ear selector . . . . . . reduce (8 5 KIAS max.) .. . GEARDOWN LOCKED position Smerg. gear ex.tend knob .. ... . ... pull ndicator lights . . . . . . ... .. . 3 green ....eave emergency gear extension knob out . REPORT: VB-1140 J-6 PIPER AIRCRAFT CORPORATION PA-34-200T, SENF.CA II ENGINE FAILURE IN ICING CONDIDONS Select alternate air and attempt restart . If unable to restart engine . lnop . prop . . . . . . . . . feather Airspeed . .. .. . _ . . .. .. at or above 89 KlAS Descend if necessary to maintain airspeed. E1ectrica1 load . . .. .. .. . ~ . . . . redu ce Avoid further icing conditions if pos sib le . Land as soon as practical. Maintain at least 89 KIAS on final. Do not ex tend gear or lower flaps until certain of making field Flaps . . . . . . . . . . . • . • • . . . . . . . . . 25 ° ALTERNATOR FAILURE JN ICING CONDITIONS Overvoltage relay Circuit breakers . . . . . . . .. reset .. check a nd reset If unable to restore alternator : Avionics ... . . . Electric Windshield . all off except Nav Com and Transp. . • . . . . . _ ()f"F" to maintain 65A load lf icing c-0ntinues tennina{e flight as soon as practica.J. Prior to landing: Electric windshield . . . . . ON if ne cessary Gear may require free fall exten sion. ENGINE FAILURE WITH REAR CABIN AND CARGO DOORS REMOVED S.E. min. contro l speed of 67 KlAS for this configuration . If airspeed is below 67 KIAS reduce power on operating engine to maintain control. l~Sl'f.D: SEPTEMBER 12. 1980 Downloaded from www.Manualslib.com manuals search engine PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA ll ELECTRICAL F AlLURES ALT annunciator light illuminated. Ammeters . . . . . . . . . . . . . . . . . .observe to determine inop. alt. Jf both ammeters show .zero outpu t , reduce electrical load to a minimum. Tum OFF both alt. switches; then turn them ON momentarily one at a time while observing ammeters. Determine alt. showing LEAST (but not zero) amperes and turn its switch on. Electrical loads . . ..... . re-establish up to 60A If one ammeter shows zero output. cycle its switch off , then on. If power is not restored c heck circuit breakers and reset once if required. If alternator remains inoperative , reduce electrical loads and continue flight. WARNING Compass error may exceed 10° with both alternators inoperative. GYRO PRESSURE FAILURES Pressure below 4 .5 in Hg. RPM Altitude . . .. .. .. .. . . . .. . increase to 25 75 . . descend to maintain 4.5 in Hg Use electric turn indicator to monitor Directional lndicator and Attitude Indicator performance. COMBUSfION HEATER OVERHEAT Unit will automatically cut-0ff . Do no t attempt to restart . ISSCED: SEPTEMBER 12. 1980 SPINS 11tr0ttles . Rudder Control wheel Control wheel Ailerons . . Rudder .. . Control wheel . . SECTION 3 EMERGENCY PROCEDURES . . . retard to idle . . full opposite to direction of spin release back pressure . . . . . . , . . . full forward if nose does not drop . .... neutral . . _ . . . ... . neutralize when rotation stops . _ . smooth back pressure to recover from dive EMERGENCY DESCENT Throttles . . . . . . _ . Propellers . . . . . . Mixture .. . . . Landing gear . . Airspeed .. . .. . . .. closed full fOiward . . . • • . . . . as required for smooth operation . . .. . . .extend . . . . . . . . 129 KIAS REPORT: VB-1140 3-7 Downloaded from www.Manualslib.com manuals search engine SECTION 3 EMERGENCY PROCEDURES . EPORT : VB-1140 ·8 PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA Il THIS PAGE INTEKTIONALLY LEFT BLANK ISSllED: EPTEMBI.R 12 . 1980 Downloaded from www.Manualslib.com manuals search engine PIPER AIRCRAFf CORPORATION PA-34-200T. SENECA II SECTION 3 EMERGENCY PROCEDURES 3.5 AMPLIFIED EMERGENCY PROCEDURES (GENERAL) The following paragraphs are presented to supply add it ional information for the purpose of providing the pilot with a more compJete understanding of the recommended course of action and probabJe cause of an emergency situation. 3.7 ENGINE 1NOPERATIVEPROCED URES DETECTING 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) The propellers can be feathered only while the engine is rotating above 800 RPM. Loss of centrifugal force due to slowing RPM will actuate a stop pin that keeps the propeller from feathering each time the engine is stopped on the ground. Single engine performance will decrease if the propeller of the inopeTative engine is not feathered . NOTE If circumstances permit, in the event of an actual engine failure. the pilot may elect to attempt to restore power prior ro featherin~ If circumstances permit an attempt to restore power prior to feathering. adjust the mixture control as required, mo ve the fuel selector contro l to Crossfeed and select either L (left) or R (right) magneto to check magneto grounding. Move the alternate air control to ON and unlatch the auxiliary fuel pump switch and turn it to the HI po sition . ff power is not immediately restored tum off the auxiliary fuel pump. Keep in mind that the minimum single engine con trol speed is 66 KlAS and the best sin gl e engine rate of climb speed is 89 KIAS when beginn ing the feathering procedure. To feather a prope11er. maintain direction and an airspeed above 76 KIAS. Move the mixture and prope ller controls forward . The throttle controls should be moved forward while monitoring the manifold pressure gauge to ensure that the manifold p ressure does not exceed 40 inches of Hg. Retract the flaps and landing gear and identify the inoperative engine. The airplane will yaw in the direction of the dead engine. Retard the throttle of the suspect engine to verify loss of power. The mixture control of the inoperative engine should be moved to idle cut-off position and the propeller control of the inoperative engine should be moved to the feather position. Trim the aircraft as required and mainta in a 5° bank roward the operating engine. The auxiliary 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 al ternator of the inoperative engine should be turned OFF and the electrical load red uced to prevent depletion of the battery. Move the fuel selector control for the inoperative ~ngine to the OFF position. If necessary, co nsid er the use of crossfeed {re fer to Fuel Management During Single Engme Operation , paragraph 3. 1 ! ). ISStJEO: SEPTEMBER 12, 1980 REPORT: VB-1140 3-9 Downloaded from www.Manualslib.com manuals search engine SECTION 3 EMERGENCY PROCEDURES N01E PIPER AIRCRAFT CORPORATlON PA-34-200T. SENECA U When an engine is feathered the alternator, gyro air. and oil annunciator warning lights will remain illuminated. ENGI:t-.'E FAILURE DURING TAKEOFF (Be1ow 85 KIAS) The single engine minim urn control speed fo r this airplane is 66 KIAS under standard conditions. If engine failure oc-eurs during takeoff ground roil or 85 KIAS has not been attain ed . CLOSE bot h throttles imrnediatelv. land if airborne. and stop straight ahead. If inadequate runway remains to stop, close the throttles . land if airborne and apply maximum braking. The master switch and fuel selectors should be turned OFF. Continue path straigh t ahead turning to avoid obstacles as necessary . E 1GINE FAILURE DURING TAKEOFF (85 KIAS or above) l f engine failure during takeoff ground roll or after lift- off with the gear still down and 85 KIAS has n attained the course of action to be ta.ken will depend on the runway remaining. lf ade~uate runway ri:;tnains, CLOSE both throttles immediately, land if airborne and stop straight ahead. If the runway remaining is inadequate for stopping, the pilot must decide whether to abort the takeoff or to continue. The decision must be based on the pilot's judgment considering loading, density altitude. obstructions, the weather , and the pilot's competence. If the decision is made to continue the takeoff, maintan heading and airspeed. Feather th e inoperative engine and when climb is established RETRACT the landing gear. ( Re fe r to Engine Securing Procedures, paragraph 3. 7). During a short field takeoff with 25° flaps, the airplane is momentarily below Vmc. In the event that an engine failure should occur while the airplane is below Vmc. it is mandatory that the throttle on the operating engine be retarded and the nose lowered immediately to maintain control of the airplane. ENGINE FAILURE DUR1NG CLIMB The singie engine minimum control speed for this airplane is 66 KIAS under standard conditions. lf an engine failure occurs when airspeed is below 66 KIAS reduce the power on the operating engine as req llired to maintain directionaJ control. The nose of the airplane should be Jowered to accelerate toward the best single engine rate of climb speed of 89 KJAS. The next step is to feather the inoperati ve engine ( · ..."" r to Engine Securing Procedure. paragraph 3. 7). If engine failure occurs when an airspeed of 66 KIAS has been anained, maintain directional control md adjust airspeed toward the best single engine rate of climb speed of 89 KIAS. The inoperative engine :hould now be feathered by following the Engine Securing Procedure provided by paragraph 3.7. lEPORT: VB - ll40 I-JR lS~ UE D: SEPTEMBER 12. 1980 Downloaded from www.Manualslib.com manuals search engine P1PER AIRCRAFT CORPORATION PA-34-200T, SENECA 11 ENGINE FAIL URE DURING FLIGHT (Below 66 K.IAS) SECTION 3 EMERGENCY PROCEDURES . Should ~ e_ngin~e fai.1 during flight at an airspeed below 66 KlAS. apply rudder towards the operative engme to m~ntam d1rect10nal control. The throttles should be retarded to stop the yaw force produced by the assymetrical th.rust. Lower the nose of the aircraft to accelerate above 66 KIAS and increase the power on the operative engine as the ai.rspeed exceeds 66 KlAS . After an a irspeed abo\'e 76 KIAS has been established, an engine r estart anempt may be made if altitude permits . If the restart has failed. or altitude does. not pe rrrnt .. the engme shou ld be secu r ed. Move the propeller control of the inoperative engine lo FEATHER and complete th e "'Engme Securing Procedure ... Ad just the trim to 5° bank toward the operating engine . The cowl nap on the operative eng i ne should be adjusted as required to maimain engine temperature withm allowable li mits EN GINE FAILURE DURING FLIGHT (Above 66 KIAS) JI an engine fails at an airspeed above 66 KIAS during flight, begin corrective response by i dentifying the inoperative engine. The operative engine should be adjusted as required after the loss of power has been verified. Once the inoperative engine ha s been identified and the operating engine adjusted properly, an engine restart may be attempted if altitude perm i ts and the airspeed is rnaint.ained above 76 KlAS . Prior to securing the inoperative engine, check to make sure the fuel flow to the engine is sufficient. If the fuel flow is deficient, tum 0 the auxiliary fuel pump to the inoperative engine. Check the fuel quantity on the inoperative engme side for a sufficient supply, switch the alternate air"ON'' and vary the mixture contro l posjtion . Check the oil pressure and oil temperature and insure that the magneto switches are ON . If the engine fails to start it should be secured using the Engine Securing Procedure. After the moperat ive engine has been se cured. the operative engine can be adjusted . Power should be mainta ined as req uired and the mixture contro l s hould be ad jus ted for power. Check the fuel supply and lurn ON the aux i liary fuel pump if necessary. The cowl flaps on the operative engine should be adjusted as required to ma in rain engine temperarnres within allowable limits. Trim 5° bank toward che operaung engine. The electrical lo ad should be decreased to a required minimum. Land a s s oO'n as practical at the nearest suitable airport . SINGLE ENGINE LANDING Complete the Engine Securing Procedure (paragraph 3. 7). The landing gear should not be extended and the wing flaps should not be lowered until certain of malting the field. Maintain additional altitude and speed during app roa ch, keeping in mind that landing should be made right the first time and that a go-aro und should be avoided if at all possible . A final approach speed of 91 KIAS and the use of 25° rather than full wing flaps will place the airplane in the best con figu ration for a go-around should this be necessary. UNDER SOME CONDITTONS OF LOADING AND DENSITY ALTITUDE A GO-AROUND MAY BE IMPOSSIBLE. AND 1N ANY EVENT THE SUDDEN APPLICATION OF POWER DURING SINGLE ENGINE OPERATION MAKES CONTROL OF IBE AIRPLA1"1E MORE DIFFICULT. ISSUED: SEPTEMBER 12, 1980 REPORT: VB-1140 3-11 Downloaded from www.Manualslib.com manuals search engine SECTION 3 EMERGENCY PROCEDURES .SINGLE ENGINE GO-AROUND PIPER AIRCRAFT CORPORATION PA-34-200T. SENECA II A SINGLE ENGINE GO-AROUND SHOULD BE A VOIDED IF AT ALL POSSIBLE. To execute a single engine go-around , advance the mixture and propeller levers forward. The thrott le should be advanced slowly to 40 inches of manifold pressure. Retract the flaps and landing gear. Maintain airspeed at the best single engine rate of climb speed of 89 KIAS. Set the trim and cowl flaps as required. AIR START (UNF EATHER ING PROCEDURE) Move the fuel selector for the inoperative engine to the ON position and check to make sure the auxiliary fuel pump for that engine is OFF. Open the throttle 1/4 inch and push t he. propeller control forward to the cruise RPM position. The mixture should be set RICH. Turn ON the magneto s·witches and engage the starter until the propeUer windmills. The throttle should be set at reduced power until the engine is warm. If the engine does not start. prime as necessary. The alternator switch should then be turned ON. - "' ENGINE FIRE lN-FLIGHT The possibility of an engine fire in light is extremely remote. The procedure given below is general and pilot judgment should be the deciding factor for action .in such an emergency. If an engine fire occurs in light . plaoe the fuel selector of the affected engine in che OFF position and close its throttle. Feather the propeller on the fauJty engine. Move the mixture contro1 to idle cut-off. The heater and defroster (in all cases of ftre) should be OFF. A landing shouJd be made if terrain permits. ON THE GROUND The first attempt to extinguish the fire is to try to draw the fire back into the engine. If the engine has not s tarted 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. If the engine has already started and is running, continue operating to try to pull the fire into the engine. In either case (above ). if the fire continues longer than a few seconds the fire should be extinguished by the best available extemaJ means. lf an external fire extinguishing method is to be applied move the fuel selector valves to OFF and the nix ture to idJe cut-off. tEPORT ~ VB-1140 -12 ISSUED: SEPTl!:.MBER 12. 1980 Downloaded from www.Manualslib.com manuals search engine PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA II SECTION 3 EMERGENCY PROCEDURES 3.11 FUEL MANAGEMENT DURJNG SINGLE ENGINE OPERATION A crossfeed is provided to increase range during single engine operation . Use crossfeed in level fligh r only. CRUISING When using fuel from the fuel tank on the same side as the operating engine the fuel selector of the operatmg engine should be ON and the fuel selector for the inope rative engine should be OFF _ The auxiliary fuel pumps should be OFF except in the case of an engine driven fuel pump failu re. If an engine driven fuel pump has failed the auxiliary fueJ pump on the operating engine side must be ON. increased range is available by using fuel from the tank on the opposite side of the operating engine. For tttls configuration the fuel selector of the operating engine should be on X-FEED (crossfeed) and the fuel selector of the inoperative engine should be OFF . The auxiliary fuel pumps should be OFF. LANDING NOTE A vapor return line from each engine will return a percentage of fuel back to the tank on the same side as that engine. Th.erefore, a minimum of 30 minutes of fuel should be 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. During the landing sequence the fuel se1ector of the operating engine must be ON and the fuel selector of the inoperative engine OFF. The auxiliary fuel pump of the operating engine should be OFF except in the case of an engine driven fuel pwnp failure. 1 ED : SEPTEMBER 12, 1980 REPORT: VB-1140 3-13 Downloaded from www.Manualslib.com manuals search engine SECTION 3 EMERGENCY PROCEDURES PlPER AIRCRAFr CORPORATlON PA-34-200T, SENECA II 3.13 ENGINE DRIVEN FUEL PUMP FAILURE Sho ul d a malfunction of the engine driven fuel pump occu r, the auxiliary fuel pump system can supply sufficient fuel pressure for engine po wer up ro approximately 75%. Any combinatio n of RPM and Manifold Pressure defined on the Power Setting Table may be used, but leaning may be r equired for smooth operation at altitudes above J 5, 000 feet or for RPM 's below 2300 . Normal cntise, descent and approach procedures should be used . Loss of fuel pressure and engine power can be an indication of failure of the engine driven fuel pwnp. Should these occur and engine driven fuel pump failure is suspected, retard the throttle and unlatch the auxiliary fuel pump and select the HI position . The throttle can then be reset at 75 % power or below. CAlJTION lf normal engine operation and fuel flow is not immediately re-established. the auxiliary fuel pump s hould be turned off. The lack of a fuel flow indication while on the HI auxiliary fuel pump position could indicate a leak in the fuel system, or fuel exhaustion. DO NOT actuate the auxiliary fuel pumps unless vapor suppression is required (LO position) or the engine driven fuel pump fails (HI position) . The auxiliary pumps have uo standby functjon. Actuation of the HI switch position when the engines are operating nonnally may cause engine roughness and/or power Joss. 3.15 LANDING GEAR UNSAFE WARNINGS The red landing gear light will illuminate when the landing gear is in transition between the full up position and the down and locked position . The pilot should recycle the landing gear if continued illumination of the light occurs. Additionally, the tight 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. I 7 MANUAL EXTENSION OF THE LANDING GEAR Severai i tems should be checked prior to extending the landing gear manually. Check for popped ,.:-cuit breakers and ensure the master switch is ON . Now check the alternators. If it is daytim e, turn OFF . .: navigation lights. To execute a manual extension of the landing gear, begin by repositioning the clip covering the emergency disengage control downward, clear of the knob . Power should be reduced to maintain airspeed below 85 KLL\S. Place the landing gear selector switch in the GEAR DOWN LOCKED position and pull the emergency gear extension knob. Check for 3 green indi cator lights. REPORT: VB-1140 3-14 WARNING If the emergency gear extension knob has been pulled out to lower the gear due to a gear system malfunction, leave the control in it s extended position until the airplane has been put on jacks to check the proper function of the landing gears hydraulic and electrical systems.. ISS UED: SEPTEMBER 12. 1980 Downloaded from www.Manualslib.com manuals search engine PIPER AIRCRAFf CORPORATION PA-34-200T, SENECA Il 3. 19 GEAR-UP EMERGENCY LANDING SECTlON3 EM"ERGENCYPROCEDURES An approac h should be made with power at a nonnal airspeed with the flaps up. The flaps are le ft up to reduce wing and flap damage. Close the throttles just before touchdown. Turn OFF the master and ignitio n switches and move the fuel selector valve controls to OFF . Contact to the surface should be made at a minimwn airspeed. 3.21 ENGINE FAILURE IN ICING CONDffiONS If engine failure occurs during icing flight select ALTERNATE AIR and attempt to restart the engine. If the engine restart procedure fails , feather the inoperative propeller (refer to Engine Securing Procedure, paragraph 3. 7). An airspeed at or above 89 KlAS must be maintained . It may be necessary to descend to maintain this airspeed. Reduce the electrical loa ds (refer to Alternator Failure in Icing Conditioru , paragraph 3. 23, for load reduction). Further icing conditions should be avoided if possible and a landing made as soon as practical. Maintain an airspeed of at least 89 KIAS during final approach. Do not ex.tend the landing gear or lo wer the wing flaps until certain of making the field . Use 25 ° flaps rather than fuJl flaps for landing. 3.23 ALTERNAT OR FAILURE IN ICINGOONDIDONS If an alternator fails during flight in icing conctitions. an attempt shouJd be made to reset the alternator overvoltage relay by cycling the corresponding alternator switch OFF and then ON. Check the circuit breakers and, if possible, reset any that have popped . If these attempts to restore the alternator have failed. turn off all avionics except one NAV COM and TRANSPONDER . Tum off the electric windshield to maintain a load less than 65 amperes. If icing conditions continue terminate flight as soon as practical. Prior to Ian ding the electric windshield may be turned on if necessary . 1f the battery has been depleted the gear may require free-fall extension and the green gear lights may not illumin ate . 3.15 ENGINE FAILURE WITH REAR CABIN AND CARGO DOORS REMOVED The minimum single engine control speed for this configuration is 67 KlAS. If engine failure occurs at: an airspeed be1ow 67 KIAS, reduce power as necessary on the operating engine and apply rudder to maintain directional control. ISSUED: SEPTEMBER 12, 1980 REPORT: VB-1140 3-15 Downloaded from www.Manualslib.com manuals search engine SECTION 3 EMERGENCY PROCEDURES PIPER AIRCRAFT CORPORATION PA-34-2-00T, SENECA Il 3.27 ELECfRICAL FAILURES U an ALT annunciator light illuminates observe the ammeters to detennine which altern.ator is inoperative . If both ammeters show zero output, reduce electrical loads to the minimum. Tum 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 zero) current should be rurned ON. The other aJtemaror should be left OFF . Electrical loads may be reins tate d as required to a maximum of 60 amperes_ If one ammeter shows zero output, cycle its switch OFF and th en ON. Jf this fails to restore output check the circuit breakers. The breakers may be reset once if required. If rhe alternator remains inoperative reduce electrical loads if necessary and continue the flight. Corrective maintenance actions should be performed prior to further flights. WARNING Compass error may exceed l 0 ° with both alternators inoperative. NOTE The markings on the ammeters (loadmeters) requi:re mental interpolations to estimate the ampere values noted . Operating the alte rnators at less than 65 amperes wiJI assure that the battery will not be deple ted . 3.29 GYRO PRESSURE FAILURES A malfunctio n of the instrument pressure system will be indica red by a reduction of the pressure reading on the gauge. A red button annunciator will sho w in case of a feathered engine or pressure pump failure . ln the event of a pressure system malfunction, (p ressure lower than 4.5 inches of mercury) increase engine RPM to 2575. Descend to an altitude at which 4.5 inches of m ercury pressure can be maintained . if possible. The electric turn indicator should be used to monitor the performance of the directional and attitude indicators. 3.3 l 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 heate r until it has bee n inspected and the cause of the malfunction has been jetermined and corrected . EPORT: VB -1140 ' ) .t' IS~ l ED: SEPTEMBER 12, l ~80 Downloaded from www.Manualslib.com manuals search engine PIPER AIRCRAFT CORPORATION PA-34-200T, SENECA 11 3.33 SPIN RECOVERY SECTION 3 EMERGENCY PROCEDURES Intentional spins are prohibited in this airplane. ln the event a spin is encoumered u nintentionall y , immediate recovery actions must be taken . To recover from an unintentiona1 spin. immediately retard the throttles to the idle position. Apply full rudder opposite the direction of the spin r otation. 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 resuHant dive should be with smooth back pressure on the control wheeJ. o abrup t control moveme nt should be used during recovery from the dive, as the positive limit maneuvering Joad factor may be exceeded . 3.35 EMERGENCY DESCENT A malfunction of the oxygen system requires an immediate descent to an altitude at or below ?2, 50(1 feet. NOTE Time of useful consciousness at 25 ,000 feet is approximately three minutes. In the event an emergency descent becomes necessary, CLOSE the throttles and move the propeller co ntrols fuU FORWARD. Adjust the mixture control as necessary to attain .smooth operation. Extend the land ing gear at 129 KIAS and maintain this airspeed. 3.37 DOOR OPEN ON TAK.EOFF 1f either the main or rear cabin door is inadvertently l·eft open or partially open on tak eoff, fly the airplane in a normal manner and return for a landing to close the door on the ground . If a landing cannot be made it may be possible to close a door in flight. Maintain an airspeed between 85 and 94 KIAS and open the storm window. Pull the door dosed. making certain the upper latch is properly positioned. Close the upper latch . .It may be necessary to pull in on the upper portion of the door while the latch is being dosed . It is necessary to have someone in the airplane in addition to the pilot to carry out this procedure. If the door . either main or rear, cannot be closed in light. it is possible to continue safely for an extended period. In this case. the airspeed should be kept below 107 KIAS and above 85 KIAS to prevent buffeting as a result -0.f the open door. J.39 DUAL ALTERNATOR FAILURE In the event of a failure of both alternators. immedia1e action should be taken rn red uce the O\·era ll ekccrical load on the system. Assum ing lhe ai rcraft"s battery and electrical system are m normal opera1ing condition. the following approx1ma1e durauons are probable Day VFR with (I) each Transponder. COMM . l\A V. OM E and ADF = 115 minute~ . :\1gh\ lFR with ( l l each Transpondn. COMM. :\AV . DME. ADFand lmarument Panel and posiuon lig.h t~ = 35 mmute~ . ISS\;ED: SEPTEMBER ll, 1980 REPORT: VB-1140 3-17 Downloaded from www.Manualslib.com manuals search engine TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES Paragraph No . 4. 1 4.3 4.S 4.7 4.9 4 . 11 4. 13 4. 15 4. 16 4. l 7 4.19 4. 21 4.23 4.25 4.27 4. 29 4.31 4.33 4.35 4.37 4.39 4.41 4.43 4.45 4.47 4.49 4. 5l 4. 53 4.55 General . . . . . . . . . . . . . . . . . . . . . . . • . . . . . . . . . . . . . ...... . ... . . . Airspeeds for Safe Operations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ... . Normal Procedures Check List . . .. . .. . . .. .. .. . .. ... ..... . ....... . . Amplified Normal Procedures (General ) . . . . . . . . . . . . . . . . . . . . . . .... _ . _ . . Preparation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . • . . . . . . . . . . . . Preflight Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Before Starting Engines .. .. ... . .. .. . .... . ......... . . . .. •. . . .... Starting Engines (Standard Primer System ) . . . . . . . . . . . . . .. . .. . .......•.. Starting Engines (Optional Primer System ) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Starting Engines when Flooded . . . . . . . . . . . . . . . . . . . . . . . .. . ......... . Starting Engines in Cold Weather (Standard Primer System) .. .... _ .. . . . .... . . . Starting Engines with External Power . . . . . . . . . . . . . . . . . . . . . . . .. . .. . . . . Taxiing ..... ..... . ...... . .... . ...... .. . .. ... .. - .. . ..... . . Before Takeoff - Ground Check . . ... . .. . .. .. . . . ... . . . ... .. ...... . . . TakeoTf .... . .. . . ... .. . . ......... . .. . . . . .... . .......... . . Climb . . . .. . ... . ........ . .... ... .. . ..... . ..... ... .... . .. . Cruising . .. . . .... . ... . Descent .. .. ... . . . ... . Approach and Landing . . . . . . Go-Around . .. . . .... . . . Af ter Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . _ . . . • . . Shutdown . .... ... ...... . .. .. ... . .. . ............. . .•...... Mooring .... ... .. . ... ... . . .. .... .... ....... .. . .......... . Turbulent Air Operation . .. ..... . .......... . . . .... . ...... . .. .. . . Flight Into Known Ic.ing Conditions . .. .. ............ . . . . . ... ..•.• . ... Flight with Rear Cabin and Cargo Doors Removed .... . .. .. .. . .. .. .. .. .... . VS SE - Intentional One Engine Inoperative Speed ...... . ....... .. ........ . VMC - Minimum Single Engine Control Speed . . . . .. . . .. ... .. . .. . Stalls . . . . . . . . . . . . . . . . . .. .. · . . · . . . · . · . . . . . . · · · · · - - · · · · . · · Page No. 4-1 4-1 4-3 4-9 4-9 4-9 4- 10 4- 11 4-ll 4- J 2 4-12 4-13 4-14 4-14 4-15 4- 17 4-18 4- 19 4-20 4-21 4-21 4-22 4-22 4-22 4-23 4-25 4-25 4-26 4-26 REPORT: VB - 1140 4-i Downloaded from www.Manualslib.com manuals search engine PIPER AIRCRAFT CORPORATION PA-34-200T. SENECA IJ 4.1 GENERAL SECTION 4 NORMALPROCFDURES SECTION 4 NORM •.\LPROCEDURES This section describes the recommended procedures for the conduct of normaJ operations for the Seneca IL All of the required (FAA regulations) procedures and those necessary for the safe operati on of the airplane as determined by tbe operating and design features of the airplane are presented. Normal procedures associated with those optiona1 systems and equipment which require handbook supplements are provided by Section 9 (Supplements). These procedures are provided to present a source of reference and review and to supply information on procedures which are not the same for all aircraft. Pilots Miould familiarize themselves with the procedures given in this section in order to become proficient in the normal operations of the airplane. The fust portion of this section consists of a short form check list 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 procedwes and how to perfonn them. Tiris portion of the section is not intended for use as an in-flight reference due to the lengthly explanations. The short form check lisl should be used for this purpose . 4.3 AIRSPEEDS FOR SAFE OPERATIONS The foJlowing airspeeds are those which are significant to the safe 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 mstalled , the condition of the engine. airplane and equipment , atmospheric conditions and piloting technique. (a} Best Rate of Climb Speed (b) Best Angle of Climb Speed (c) Turbulent Air Operating Speed (See Subsection 2.3 ) ( d) Maximum Flap Speed (e) Landing Final Approach Speed (F laps 40°) (I) Intentional One-Engine Inoperative Speed (g) Maximum Demonstrated Crosswind Velocity ISSUED: SEPTEMBER 12. 1980 89 KIAS 76 KIAS 136 KIAS 107 KlAS 79 KIAS 76 KIAS 17 KTS RE1'0RT~ VB~ll40 4-1 Downloaded from www.Manualslib.com manuals search engine SECTION 4 ORMAI. PROCEDURES {EPORT~ VB-1140 p PIPER AIRCRAFT CO RPO RATION PA-34-200T, SENECA II TIIlS PAGE ll\1TENTIONALLY LEFT BLA1'"1]( IS .• l £0: SEPTEMBER 12, 1980 Downloaded from www.Manualslib.com manuals search engine PIP ER AlRCRAFf CORPORATION PA-34-200T. SENECA Il SECTION 4 NORMAL PROCEDURES ·····•······ :.. .. ................ : ................... : ~ LJ I_ LJ I = •... :·......... .. .... ·•· ......... .. .... .: . ·.. .·•· ..... .. ... .. ............. : . ' = • : . .. .... ........... .... .. ........... ..... .. WALK AR O UND Figure 4-1 4.5 NO RMAL PR OCEDU RES CHECK UST P REF LIGH T CHECK PREPARATION Airplane s tatus . . We ath er Bag__1mge Weight and C.G. Navigation . . . . . . . Charts and navigation equ ipment ... . . . Peiformance and range . . . . . . airworthy, papers on board . . . . . suitable .weighed. stowed, tied . . . within limits . planned on board . . computed and safe INSIDE CABJN Landing gear control Avionics .... . . Master switch . . . Landing gear lights Fuel quantity . Cowl flaps ..... ... . . Master switch . . . .... . Ign iti on switches . Mixture controls Trim indicators . . . Flaps ..... . .. . Contr ols . .. .. ..... •.•. Pite l an d static systems Empty seats ... Cro~ feed drains DOW}.; position . . ..... OFF ........ON ... 3 GREEN, no red .adequate plus reserve . .... OPEN . . OFF . . . . OFF . idle cut-off . . neutral check operation . ... free ... . drain . fasten belts .drain ISSUED: SEPTEMBER 12, 1980 REPORT: VB -1140 4-3 Downloaded from www.Manualslib.com manuals search engine SECTION 4 NORMAL PROCEDURES OUTSIDE CABIN Crossfeed drains Right wing , aileron and flap . . . . . . . Right main gear Strut . .. .. . Tire .. Right wing tip . Right leading edge . Fuel cap ... . . . Right engine nacelle Right propeller Cowl flaps ... Fuel drains Nose section v ~se gear . ...... ~ut . Tire . . Tow bar Landing light . Forward baggage door Windshield . . . . . . . . Left wing, engine nacelle and landing gear . . . Pitot tube ..... . St all warning vanes . Rear door .. . .. . Left static vent .. . . Dorsal fin air scoop . Empennage .. . Stabilator ... . r- · ..ht static vent . • ... .. closed . . . check, no i ce .. no leaks . proper inflation . . .. ... check . ... check . . . check, no ice . open. check quan tity and color. secure . .... check .oil ....... check OPEN and secure .... .... drain . . . . . . check . . • .•.. no leaks . proper inflation . ...... check .. . remove-0 and stowed .... check ... . secure and locked . . .... .. .. clean .. check as on right side clear. checked . .. ... . check latched .. clea:r .. cle ar .n.1tennas ..... Navigation and ]anding lights . .. . check , no ice . .. .. .. . free . . cle ar . check . check BEFORE STARTING ENGINES Seats ...... . ... . Seat belts and harness . . Parking brake . Circuit breakers . . . . . . Radios . . . . . .... . Cowl flaps . . ... .. . Alternate air ... . . . Alternators .. . .... . REPORT: VB-850 / . . . . . . adjusted .fastened . .•. ..... set .. . . ... .. in . • . . . . . .. OFF . . . . OPEN . .OF F ......ON PIPER AlRCRAFf CORPORATION PA -34-200T. SENECA II STARTING ENGINES (AIRPLANE EQUIPPED WITH STANDARD ENGINE PRIMER SYSTEM ) Fuel selector Mixture Throttle . . _ . Propeller . . .... Master switch . Ignition switches Propeller . .. . Starter .... . . Primer button Throttle .. . .. . ..ON ... . RICH . . half travel .FORWARD . .ON ...ON . clear . . . . . . .engage . ON as required .retard when engine starts Oil pressure . . . . . . . . . . ch eck Repeat for opposite engine Alternators .. . . . .. check Gyro pressure . .. .... ....... . ... check STAR.TING ENGINES (AIRPLANE EQUIPPED WITH OPTIO NAL ENGINE PRIMER SYSTEM) Fuel sel ector . . ..... . . . ...ON Mixture . . . . . . . . . FULL RICH Throttle . . . . . .FULL FORWARD Prop control . . . . .. . . FULL FORWARD Muter swit ch . . . . . . . . . . . . . . . . . . .ON Ignition switch (mag) . . . . . . . . . . . . . . . . . . . . • . ON Auxiliary fuel pump .... ~ . .. . OFF Primer . . . . . . . . . . . . . , . . .. _ .... .ON See Figure 4-3 for Priming T im e Throttle . . . . . . . . . . . . . . . . . . . . CLOSE Starter . . . . . . . . . . . . . . . . . . . . . . engage At temperatures below +20°F continue priming while cranking until engine starts . When engine starts & accelerates thru 500 RPM : Starter . . .. . .. . ... .... release Throttle . ... .. .. .. .. .. .. advance slowly Primer ....... . Auxiliary fuel pump .. . Oil pressure .. . ... . to obtain l 000 RPM . . ..... . release ... ... iow only as necessary to obtain smooth engine operation (1 -3 minutes will be required when temp. is below 20°F) . ....... check Repeat for opposite engine. I 'SU ED: SEPTEMBER 12. 1980 Downloaded from www.Manualslib.com manuals search engine PlPER AIRCRAFT CORPORATION PA-34-200T, SENECA 11 Alternators . _ . . Gyro pressure . . . NOTE . check . check When starting at ambiem tempe rature s +:20° F and below. operare first engine started with alternator ON (at max charging rate n ot to exceed 1500 RPM) for 5 minutes minimum before initiating start on second engine. STARTING ENGINES ""'HEN FLOODED Mixture . .. ..... ... . . . . idle cut-off Throttle . . . . . . . full FORWARD PropeHer . . . . . ... FORWARD . .. .... . . ...ON . . . . . . . .ON Master switch . Ignition switches Auxiliary fuel pump Propeller . .... - . . . OFF Starter . . ... . . . When engine fires: Thrott1e Mixture . .... .. .. . . . clear .en gage ..... .. ... retard . . . . . advance slowly STARTING ENGINES IN COLD WEAlHER (AIRPLANE EQUIPPED WITH STANDARD ENGINE PRIMER SYSfEM) Props . . .. . Fuel se le ctor Mixture . . . Throttle .. . . Prop control . . . . . Master switch . . .. Ignition switch (m ag) Auxiliary fuel pump .... Starter . Primer . Throttle Primer .. . . . turn through by han d (3 times) .. . ... . ..ON .. ... full RICH . full FORWARD . full FORWARD . .... . . . .ON . .. . . ...ON . . .ON LOW boost . ...... engage . . . On for 3 sec. . full FORWARD to full AFT .•.. . ... ON 3 sec., then OFF 3 sec.• then ON 3 sec. lSSt'ED: SEPTEMBER 12, 1980 SECTION 4 NORMAL PROCEDURES When engme fires : Starter ... .. Primei; button . Starter . . . Throttle . . . Oil pressure If engine begins to falter: Primer button . Thrott le .. . ... . Auxiliary fuel pump . . leave engaged . .. . tap until rhythrmc firing .release . half travel . . . check . .. ... tap 1000 RPM OFF after start complete STARTING WITH EXTERNAL POWER SOURCE Master switch . . . All e]ectrical equipment Terminals . . . . . . External power plug ... Prooeed with nonn al start Throt tl es . . . . . External power plug Master switch .. . . Oil pressure . . . . . WARM -UP Throttles . TAXJING . . .. .. OFF .. .. . OFF ... connect . . insert in fuselage . lowest p ossible RPM . disconnect from fuselage ON-check ammeter . .... check 1000 to 1200 RPM Chocks . . . .... . .. .. . . . ...removed . .. • . . clear . apply slowly Taxi area . . . . . .. - . - . . . Tiuottle . . Brakes . .... . . .. . check Steering . ... . . . . .. . . check Instruments . . . . . . ... - . ...•.. . check . ... check ON . check crossfeed Heater and defroster .... . Fuel selector Autopilot .. . • . . • . . . . ... OFF REPORT: VB-U40 4-S Downloaded from www.Manualslib.com manuals search engine SECTION 4 NORMAL PROCEDURES BEFORE TAKEOFF - GROUND CHECK Parking brake . . .. 'Mix tu re control s . . Prop. controls . . . . Throttle con tr ol Manifold pressure lines Prop. con trols . . . . . . . .. Throttle controls Prop. controls . . Prop. controls .. Alte rn ate air . . . Magnetos . .. . ....ON ...FORWARD .FORWARD . . . 1000 RPM . . . . . ... .. drain . . . check feathering, 300 RPM max . drop 1900 RPM . . . check governor . . full FORWARD . . . ON then OFF . ch eck , max. drop 150 RPM, max. diff. drop 50 RPM Alternator output .. .... . ch e ck G \fro pressure gauge 4.5 to 5.2 in. Hg . 1 1ttles . . . . . . . 80(}. 1000 RPM Fuel selectors . . . . . . . . . . . . . .ON Alternators .. .... . - .... . . ... ... .ON Engine gauges . . . . . . . . . . _ . . . .in the green Annun ciator pane l . .... •• .. . . . press-to-test Altimeter . . . . . . . . . . . . . . . . . . . set Attitu de indicato r . . . . . . . . . . . . ... set D.G. . . . . . .. .. ... . set Clock . . . . . . . . . . . wound and set Mixtures . Propellers . ~uadran t fricti