Piper Twin Comanche B Owner'S Handbook Manual Download | Manualshive

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Summary of Contents for Twin Comanche B

Page 1: ...PIPER TWIN COMANCHE B OWNER S HANDBOOK ...

Page 2: ...Piper Aircraft Corporation Lock Haven Pa U S A ...

Page 3: ...U WITH THE BASIC PERFORMANCE AND HANDLING CHARACTERISTICS OF THE AIRPLANE 3 TO MORE FULLY EXPLAIN YOUR TWIN COMANCHE S OPERATION THAN IS PERMISSIBLE TO SET FORTH IN THE AIRPLANE FLIGHT MANUAL IF THERE IS ANY INCONSISTENCY BETWEEN THIS HANDBOOK AND THE AIRPLANE FLIGHT MANUAL APPROVED BY THE F A A THE AIRPLANE FLIGHT MANUAL SHALL GOVERN Revised text and illustrations shall be indicated by a black ve...

Page 4: ......

Page 5: ...SECTION SPECIFICATIONS Performance Weights Power Plant Fuel and Oil Baggage Area Dimensions Landing Gear ...

Page 6: ...ing Speed gear and flaps down power off mph 69 Stalling Speed gear and flaps up power off mph 76 Best Rate of Climb ft per min 1460 Best Rate of Climb Speed mph 112 Best Angle of Climb Speed mph 90 Single Engine Rate of Climb ft per min 260 Best Single Engine Rate of Climb Speed mph 105 Absolute Ceiling ft 20 000 Service Ceiling ft 18 600 Single Engine Absolute Ceiling ft 7 100 Single Engine Servi...

Page 7: ...g Range 75 power at 8 000 ft mi 048 Cruising Range 65 power at 12 000 ft mi 1025 Cruising Range 45 power at 16 000 ft mi 1116 84 gal usable fuel Landing Roll short field flaps down ft 700 Landing Over 50 ft Barrier flaps down ft 2100 WEIGHTS Gross Weight lbs 3600 Empty Weight Standard Ibs 2207 USEFUL LOAD Standard 1bs 1393 These weights are approximate 710310 ...

Page 8: ...125 Stroke in 3 875 Displacement cubic in 319 8 Compression Ratio 8 5 1 Dry Weight Ibs 295 FUEL AND OIL Fuel Capacity U S gal 90 Unusable fuel inboard tanks only 6 Fuel Aviation Grade minimum octane 91 96 0il Capacity qts each engine 8 BAGGAGE AREA Maximum Baggage lbs 250 Baggage Space cubic ft 20 Baggage Door Size in 19 x 21 700313 3 ...

Page 9: ...q ft 178 Length ft 25 2 Height ft 8 2 Wing Loading lbs per sq ft 20 2 Power Loading Ibs per hp 11 3 Propeller Diameter in 72 LANDING GEAR Wheel Base ft 7 3 Wheel Tread ft 9 8 Tire Pressure psi Nose 42 Main 42 Tire Size Nose six ply rating 6 00 x 6 Main six ply tating 6 00x 6 4 700313 e ...

Page 10: ...SECTION TWIN COMANCHE B 700313 ...

Page 11: ...l Injection Structures Landing Gear Control System Fuel System Electrical System Vacuum System Instrument Panel Instrument Static Pfessure System Heating and Ventilating System Seats Finish Baggage Area Stall Warning System 10 11 14 16 17 20 21 22 23 23 24 ...

Page 12: ...bottom of the engine nacelles and are manually operated by push pull controls located in the cabin to the right of the power control quadrant Oil coolers are mounted on the left rear baffle of each engine Air passes through the oil coolers before reaching the area of the cowl flaps The propellers are Hartzell HC E2YL 2 constant speed controllable full feathering units These are controlled entirely...

Page 13: ...agm in the regulator A change in power changes the airflow to the engine and across the diaphragm in the regulator Mounted on top of the engine is the ported fuel flow divider with four nozzle lines routed to the cylinders The divider con tains a spring loaded positive shut off valve Within each cylinder are continuous flow air bleed nozzles with provisions to eliminate the adverse effects of low ...

Page 14: ...cated at the point of max imum thickness to pass through the cabin under the rear seat providing unobstructed cabin floor space ahead of the seat LANDING GEAR The nose gear is steerable with the rudder pedals through a 40 degree arc During retraction of the gear the steering mecha nism is disconnected automatically to reduce rudder pedal loads in flight The nose gear is equipped with a hydraulic s...

Page 15: ...e the gear selector switch is the gear up indication The amber light will flash when power is reduced on one engine and the gear is up The warning horn will operate when power is reduced below approximately 12 of manifold pressure on both engines and the gear is not down and locked The pilot should become familiar with the gear warning horn to distinguish it from the stall warning horn GEAR INDICA...

Page 16: ...he nose gear and steering mechanism CONTROL SYSTEM Dual flight controls are Cables connect the movable pedals and control columns Directional and longitudi nal trim is provided by an adjustable trim mechanism for the rudder and stabilator The manual rudder trim control is located to the right of the throttle quadrant Max Lift electrically op erated flaps are used on the Twin Comanche The flaps are...

Page 17: ...ry fuel system consists of two 15 gallon cells all usable installed in the wings just outboard of the main fuel cells Wing tip tanks are available as optional equipment Auxil iary fuel and tip tank fuel is to be used in level flight only The cells should be kept full of fuel during storage of the airplane to prevent accumulation of moisture and deterioration of the cells For storage of more than t...

Page 18: ...4SSOHd MO74 13N4 TYNHON b S 010373S q304 3NIONI 1HOW Ol GONX NIVHQ 3NION3 1431 OL HINIVHLS N L R 2 SR dnnd o RN 303 INISNT SdWNd 13nd ABvMIXNY Rnd 3n3 INIONT 0 0 8 EALXTW 311108HL 371108HL FBNIXIN O O B3ILVIH Ol N o o 1 3ATVA 440 1NHS 390V MO4 q3n4d vng 7 N W3LSAS 73N 12 700313 ...

Page 19: ...ated in the floor panel just aft of the fuel selector handles and pulling up on the knob located in the center of the selector valve The general procedure for draining the fuel system is to open the strainer quick drain for several seconds with the fuel cell selector on the main cell then to change the selector to the auxiliary cell and repeat the process Allow enough fuel flow to clear the lines ...

Page 20: ...e battery Dual generators are avail able as optional equipment Electrical switches for the various systems are located on the lower left instrument panel The circuit breakers located under the floorboard aft of the nose wheel well automatically break the electrical circuit if an overload occurs To reset the circuit breakers simply push in the reset button It may be neces sary to allow approximatel...

Page 21: ...HEAT 15 AMP CIRCUIT PROTECTOR FUEL PUMP 20 AMP CIRCUIT PROTECTOR FLAP SOLENOID 5 AMP CIRCUIT PROTECTOR GEAR SOLENOID 5 AMP CIRCUIT PROTECTOR INSTRUMENT LIGHTS 5 AMP CIRCUIT PROTECTOR FUEL GAGE AND GEAR WARNING 5 AMP CIRCUIT PROTECTOR CYL OIL TEMP AND GEAR LIGHTS 5 AMP CIRCUIT PROTECTOR HEATER 20 AMP CIRCUIT PROTECTOR TURN AND BANK 5 AMP CIRCUIT PROTECTOR ROTATING BEACON 10 AMP CIRCUIT PROTECTOR PO...

Page 22: ...acuum gauge is installed in the instrument panel to pro vide a constant indication of vacuum source Incorporated in the instrument are two red indicators right and left systems During normal operation the indicators are not visible but if vacuum is lost for example on the right side then the right indicator will be visible Suction is indicated onthe gauge in inches of mercury normal operating rang...

Page 23: ... designed to accommodate the cus tomary advanced flight instruments on the left side in front of the pilot and engine instruments on the right side The optional in struments such as the gyro instruments of the flight group are shock mounted The Artificial Horizon and Directional Gyro in this group are operated by an optional vacuum pump on each engine The vacuum system standby is the opfional elec...

Page 24: ...VE ONV NdNnl ve 2 22 1z 02 61 TOYLINOD WVv3o HOLINOW 3dNLIXIN SWITD VI L1Y3A dOLVIIANI INWO 39NV9 NOILDONS olavyd 4dHA 81 Ly 91 Sl vi l 34NSS3dd ATOJINVIN dOlVvIIdNI mMO014 13Nnd d3ILINWNYVY 43LSNTD3 LNIWNHLISNI H3IL3IWOHIOVL olavy 4av 4 bl 0l HOLVIIANI 40V T041NOD 1O0TI401NYy NOZIMOH TVIDI4ILYY 0 A9 TVYNOILIIHIQ Q3adsyly 201D N M 10O 18 700313 ...

Page 25: ...ANV HIV Nigv D 1371N n0 Iv LsnvH X3 Nl1gv D 13710 0 31so y43Qg 137Nl 31so y43g 13710 0 31va H 137Nl 31v3 aH 13710 0 1V HS3N 4 137INI IV HS34 4 YIV LSNVHX3 NIGV D 4w dlv 3LV3H NIEVD m SR 41V HS3 4 Niav AU AN T NmMEWOON N DO W31S AS ONIL VTIL NIA ANV 9NILY 3IH 700313 19 ...

Page 26: ...ernate static source valve should be opened venting the static system to cabin pressure Cabin pressure will vary however with cabin ventilators open cabin heater operating and various airspeeds Use of the alternate static source may result in the following instrument indications The altimeter reads higher than normal indicated airspeed greater than normal and the vertical velocity indicator monent...

Page 27: ...lled by levers on the heater control console The top control regulates a thermostat and provides a wide range of temperature selections Adjustable heat deflectors are on the cabin wall beneath the instrument panel to provide additional comfort Cabin temperature and air circulation can be maintained by using various combinations of lever settings to suit individual desires To minimize the feeling o...

Page 28: ...r while taxiing turn the three position switch to FAN During ground operation the manual switch should be on FAN for several minutes to cool the heater before turning to the OFF position Ventilating air for the cabin interior is obtained from the two ventilators located at each side of the instrument panel The rear seat area is furnished with air by overhead vents from the dorsal fin scoop Each in...

Page 29: ... attractive high gloss colors The application of primer to interior surfaces prevents corrosion of structural and non structural parts on the inside of the airplane BAGGAGE AREA Maximum weight in the X baggage area including bag gage passengers and family seats is 250 pounds with up to 20 cubic feet of available space Baggage may be placed in the aircraft through a 19 x 21 inch door or through the...

Page 30: ...tall is indicated by both a stall warning light and horn activated by a lift detector installed on the left wing outboard of the engine nacelle This warning horn is separate and operated by a different system from the gear warning horn mentioned on page 9 710310 24 ...

Page 31: ...d Take Offs Landing Gear Retraction Deicer Boots Vmc Stalls Spins Spin Recovery Technique Cruising Fuel Management Approach and Landing Post Landing Emergency Procedures Vmc Demonstration Vmc and Stall Speed Mooring Loading and Weight and Balance Operating Tips Flight Conditions Diving Spiral Radio Operation 25 27 27 28 29 29 31 31 32 33 33 33 34 35 36 36 37 39 42 42 49 50 50 50 52 53 54 55 ...

Page 32: ... the landing gear selector switch is in the down position Turn master switch on and check that the green landing gear indicator light is on If the green light is not on make sure that the instrument panel light switch is turned to the OFF position The landing pemm 1 1 1 1 1 1 1 1 i l __________ I i i 1 1 1 o s _________ 6 ____ 5 Seta B Se a 1 vy 1 1 1 1 1 1 1 1 1 1 1 b 1 1 1 1 1 1 e 1 e e 1 1 1 1 ...

Page 33: ...ng or interfering with essential equipment and flight con trols fuel valves switches circuit breakers trim knobs or cranks radios etc 1 Ignition and master switches OFF 2 Fuel strainer sump drained and not leaking 3 Fuel selectors on main cells 4 Control surfaces wing fuselage no damage or oper ational interference 5 Control surface free of obstructions ice and snow 6 Fuel supply adequate 7 Fuel c...

Page 34: ...fuel pumps on till indication on fuel flow gauge Mixtures idle cut off Magneto switches on Propellers clear Starters engage Mixtures advance 0il fuel pressure check FLOODED START nnh wn 4 Magneto switches on Throttles open Mixtures idle cut off Electric fuel pumps off Starters engage When engine fires retard throttle and advance mixture Cranking periods should be limited to 30 seconds with a two m...

Page 35: ...gneto should not exceed 10 seconds Move the propeller controls through their complete range to check feathering action then leave them in the full forward low pitch position Feathering action can be checked by running the engine between 1000 and 1500 RPM and pulling the prop control into feather position momentarily Do not allow a drop of more than 500 RPM and do not feather the propeller when ope...

Page 36: ...ing gear is required under these circumstances TAXIING AND PRE TAKE OFF Start to move the airplane forward During initial taxiing throttle back and apply brakes to check their operation Use differential power and nose wheel steering rather than brakes when taxiing Retard the throttle to the engine on the inside of turn and advance the throttle to the engine on the outside of the turn The autopilot...

Page 37: ...g flaps open the small window to the left of the pilot pull the door shut and lock it Check list 1 2 11 12 13 14 15 30 Pt COPNO G AW Parking brake on Engine run up a Mixture controls forward b Propeller controls forward c Throttle controls forward 1500 rpm d Propeller controls exercise Check feather 500 rpm maximum decrease e Throttle controls forward 2200 rpm f Magnetos check Normal drop 100 rpm ...

Page 38: ...ng take off roll apply light back pressure to the control wheel to avoid porpoising during the take off run Accelerate to single engine minimum control speed Vyc before épplying stronger back pressure for rotation During normal conditions retraction of the landing gear should occur when a gear down landing is no longer possible on the runway Attain the best rate of climb speed and at least 400 fee...

Page 39: ...k instruments If the airplane is off the runway at less than 90 miles per hour it is essential to fly level a few feet off the runway immedi ately after lift off until reaching 90 mph After airspeed has increased initiate a climb at the bestangle of climb speed 90 mph at sea level if an obstacle is to be cleared or at the best rate of climb speed 112 mph at sea level if a normal climb out is desir...

Page 40: ... take off power and the other engine windmilling The Vmc which the FAA has determined for the Twin Comanche is 90 mph CAS Calibrated airspeed is equal tothe airspeed indicator reading corrected for position and instrument error Since calibrated air speed and density altitude and pilot flight techniques vary it is best especially when heavily loaded or on a cold day to fly the aircraft as though Vp...

Page 41: ...n stalls unless maneuver is initiated at least 5000 feet above terrain and with not more than pilot and copilot aboard except during flight checks The left wing on the Twin Comanche with clockwise rotating propellers will generally speaking under conditions of moderate symmetrical power stall more rapidly than the right wing and if recovery is not promptly initiated the airplane will have a tenden...

Page 42: ...ncreases the stalling speed STALL SPEED TABLE CAS Angle of Bank Gear Flaps Up Gear Flaps Down 0 76 69 20 79 71 40 87 79 60 108 98 These figures are at gross weight of 3600 pounds with power off SPINS The Twin Comanche is FAA approved in the normal category and in this category all intentional acrobatic maneuvers in cluding spins are prohibited Spins and other intentionalacrobatic maneuvers may sub...

Page 43: ...dly spin recov ery is begun the more prompt the recovery will be CRUISING The cruising speed of the Twin Comanche is determined by many factors including power setting altitude temperature weight and equipment installed The normal recommended economy cruising power setting of the Twin Comanche is at 65 power At 12 000 feet this gives a True Airspeed of 186 MPH This power setting is obtained under ...

Page 44: ...uld be used from the main fuel cells during take off landing climb and descent Auxiliary fuel and tip tank fuel is to be used in level flight only The electric fuel pumps should be on during take off landing and while switching tanks in order to prevent loss of power at critical times In turning off the electric fuel pumps allow a time delay of approximately 20 seconds between switching each of th...

Page 45: ...el drain valve and allow fuel to drain Observe for flow in clear plastic tube followed by interrupted flow of no fuel for a few seconds further followed by a bubbling flow then full flow Total drain time should not be less than 30 seconds 4 Procedure shall be accomplished for each tip tank separately 5 In addition to above procedure operate the the power plant from each wingtip separately until st...

Page 46: ...ent is inoperative or when attention is drawn to events outside of the cockpit Therefore it is especially im portant to check that the landing gear is down when there is any distraction in the landing situation Lower the gear at speeds below 150 miles per hour and the flaps at speeds below 125 an hour CAUTION Maintain sufficient speed during turns in the traffic pattern It is a good practice to tr...

Page 47: ...istent with landing conditions For short slow landings under normal conditions use full wing flaps partial power and hold the nose up as long as possible before and after contacting the ground with the main wheels In high winds and crosswinds it is desirable to approach a landing at higher than normal speeds with half or no wing flaps If a go around is necessary apply full throttle retract the lan...

Page 48: ...ion of the landing gear safety mechanism causing retraction during the landing roll If additional braking is not needed the wing flaps should be retracted after the airplane has been maneuvered to a stop off the runway If a landing must be made without wheel brakes the air plane should be flown to contact the ground at a slower speed and landed short on the longest available runway The procedure f...

Page 49: ...ie downs at appropriate places EMERGENCY PROCEDURES 1 Engine Failure a During Take off Or After Lift off If an engine failure occurs during take off run prior to lift off with adequate stopping distance remaining reduce the power on both engines and stop the airplane straight ahead If an engine failure occurs after lift off with adequate landing distance ahead immediately reduce the power on both ...

Page 50: ...rative engine because there is more asymmetric thrust with the power setting used for climb Trim directionally with rudder trim b During Cruise Flight If engine failure occurs during cruise flight maintain air speed and directional control of airplane immediately advance mixture propeller and throttle controls The airplane will yaw in the direction of the inoperative engine It will rarely be possi...

Page 51: ...g a single engine approach the landing gear should not be lowered until landing is assured It is important however to extend the landing gear soon enough that there will be time to lower it manually in the event of a landing gear malfunction and also so there will be no great change in airplane configuration just prior to landing Maintain additional altitude and speed during approach keeping in mi...

Page 52: ...s been used to ease single engine control pressures the trim should be adjusted as the throttle control is retarded for final approach and landing RECOMMENDED PRACTICE When operating single engine maintain speed above 97 mph This speed 97 mph will not provide optimum single engine climb performance Optimum single engine climb is obtained at the best single engine rate of climb speed 105 mph with t...

Page 53: ...ures To unfeather a propellerin flight the following technique is recommended Ignition switches ON Mixture RICH Throttle open about 1 2 inch Prop control at cruise setting Engage starter until engine starts f Allow engine to idle at 1000 to 1500 RPM until oil temper ature begins to rise Adjust to cruising powerwhen engine warms The Twin Comanche operating under optimum conditions of turbulence and...

Page 54: ... a propeller for practice unless you are within reasonable distance of an airport e Do not feather a propeller for practice in conditions of temperature altitude weight or turbulence which may prevent single engine flight at altitudes wellabove the ground elevations 4 Manual Gear Extension Manual landing gear extension is accomplished with the mechanism located under the floorboard directly aft of...

Page 55: ... on panel indicates landing gear down and locked After the gear has been extended manually do not perform any unnecessaty operation to the gear until the aircraft is placed on jacks NOTE Reducing power and rocking gear extension handle will aid in manually extending the landing gear DO NOT RETRACT WITH HANDLE IN SOCKET DO NOT RE ENGAGE MOTOR IN FLIGHT Given below is the procedure for returning the...

Page 56: ... necessary During a gear up landing use a normal flaps up approach During flare out close the throttles shut off the master and ignition switches turn fuel selectors off and contact the ground at minimum speed VMc DEMONSTRATION WARNING The engine out minimum control speed demon stration required for the FAA flight test for the multi engine rating approaches an uncontrolled flight condition with po...

Page 57: ...ORING The airplane should be moved on the ground with the aid of the nose wheel towing bar provided with each plane The tow bar is stowed on the forward side of the main spar within the cabin Tie down ropes for mooring the airplane can be fastened to the wing tie down rings and tail skid The aileron and stabilator controls should be secured by means of a safety belt or control locks to prevent con...

Page 58: ...able bag gage The two rear family seats if installed are designed and placarded to carry not more than 235 Ibs total With these two rear family seats re moved the area remaining baggage will carry up to 250 lbs depending upon airplane loading It will carry fewer passengers and baggage with full fuel tanks As with any airplane improper loading will cause undesirable flight characteristics if the ai...

Page 59: ... 8 Be sure that all radio switches light switches and pitot heat switch are in the off position before starting engines 9 Due to the responsive trim tab controls a small adjustment in trim gives a rapid change in attitude 10 Engine shut down by use of the mixture controls may cause a rough stop during high ambient temperature conditions A spring loaded device on the throttle will shut down the eng...

Page 60: ... rudder pedals are suspended from a torque tube which extends across the fuselage The pilot should become familiar with the proper positioning of his feet on the rudder pedals so as to avoid interference with the torque tube when moving the rudder pedals or operating the toe brakes FLIGHT CONDITIONS Do not fly into marginal or deteriorating weather unless you are equipped and qualified to fly as a...

Page 61: ...ure this will then indicate that the automatic alternate induction air system is in operation and the manifold pressure may then be brought back to the desired level with the throttle control A continued drop in manifold pressure would indicate that the automatic induction air system was not working In this case actuate the manual alternate air control which serves as a back up for the automatic s...

Page 62: ...ving the transmitter selector switch to the proper position The switch is located on the selector switch panel A separate three position audio selector switch is provided for each receiver Each receiver audio output may be connected to either the speaker or the headset In addition they may be placed in the OFF or standby position To receive audio Mark 12 must be in operation Power from this radio ...

Page 63: ...ngine Climb Rate and Airspeed Single Engine Climb Rate and Airspeed Altitude Conversion Chart Range vs Density Altitude True Airspeed vs Density Altitude Landing Distance vs Density Altitude Landing Distance Over 50 Foot Obstacle Short Field Power Setting Table Fuel Flow Indicator 56 59 60 61 62 63 65 66 67 ...

Page 64: ...ATURE AND PRESSURE ALTITUDE AT A 2 TRANSFER TO B ON 3600 GROSS WEIGHT LINE 3 TRANSFER PARALLEL TO REFERENCE LINE TO C AT PROPER WEIGHT 4 TRANSFERTODONO NE 5 TRFA NSFEE Z RALLEL TO REFERENCE LINE TOE AT 6 READ TAKEOFF DISTANCE AT F l J 2 2400 N h A ped NN 2000 saou v id i N suun l rtL L 1600 L sonop L r J 2000 Z l l c J B 1200 STB R st LI N s e N J N E F 800 TN N 400 0 20 40 60 80 3600 3400 3200 30...

Page 65: ...AP SETTING 15 B ATTAIN 91 MPH IAS AT 50 FT PAVED LEVEL RUNWAY HOTE THE TAKE OFF DATA SHOWN BELOW WAS PREPARED IN ACCORDANCE WITH CIVIL RIR REGULATION 3 84 J 000 N N 5000 ﬂ A N Q S é i 4000 5 Bm gﬁ E Q é g 3000 u LB ANNSTS S NNN E 20007 E s QSQ Q TEMP N 1 1000 0 20 40 60 80 3600 3400 3200 3000 2800 O 10 20 30 TEMPERATURE F WEIGHT LBS HEADWIND MPH 57 700313 ...

Page 66: ...TWIN COMANCHE B SECTION IV This page intentionally left blank 700313 58 ...

Page 67: ...17711 MULTI ENGINE CLIMB RATE AND SPEED DENSITY ALTITUDE AND WEIGHT _ GEAR AND FLAPS RETRACTED COWL FLAPS OPEN EXCEPT AS NOTED 24000 20000 16000 NN 12000 SAAG e N 8000 X N NN N 4000 3 0 RN st 0 400 800 1200 1600 2000 S0 100 110 RATE OF CLIMB FT MIN BEST RATE OF CLIMB SPEED MPH 59 700313 ...

Page 68: ...ENGINE RATE OF CLIMB VS ALTITUDE AND WEIGHT LEFT ENGINE INOPERATIVE COWL FLAP OPEN GEAR AKD FLAPS RETRACTED 12000 10000 A N 8000 2 N 6000 g N 0 4000 6 I l N 2 S NN NIEAN N 0 AN 0 100 200 300 490 500 90 100 110 RATE OF CLIMB FT MIN BEST RATE OF CLIMB SPEED MPH 700313 60 ...

Page 69: ... BE USED TO DETERMINE DENSITY ALTITUDE FROM EXISTING TEMPERATURE AND PRESSURE ALTITUDE CONDITIONS FOR USE WITH PERFORMANCE CHARTS STD JE NJEwP_ e W s 24000 r n _ A onl L oo L 20000 1 o il I L 5 16000 ﬁﬁ Al 1o wl L N g Q L 8000 o1 7 _ _ 1 T N o N 18 sL 7 A o el 40 20 0 20 40 60 80 100 TEMPERATURE F 61 700313 ...

Page 70: ... GAL USABLE CRUISE FUEL CONSUMPTION LEANED TO BEST ECONOMY RATED RPM GPH POWER TOTAL é 4 5 iég N RESERVE FUEL 45 MINUTE RESERVE 4 2200 M2 FUEL AT CRUISE ISDOU I J 5 45 5751 45 RATED POWER 65 I 65 12000 I 5 1 5 1 1 15 8000 H ll L I 4000 ll ll 1l l Pl 1 L Ji LA LT st Py 1 600 100 800 900 1000 1100 1200 RANGE STATUTE MILES 700313 62 ...

Page 71: ...MANCHE DENSITY ALTITUDE FT TWIN COMANCHE B T T TRUE AIRSPEED DENSITY ALTITUDE WEIGHT 3600 LBS COWL FLAPS CLOSED VS 16000 12000 8000 4000 o g y s L i o o Q S S g 2 N w w SL 63 220 140 160 180 200 TRUE AIRSPEED MPH 700313 ...

Page 72: ...US ALTITUDES TEMPERATURES WEIGHTS AND WINDS FLAP SETTING 27 TOUCH DOWN 70 MPH IAS PAVED LEVEL RUNWAY 135 t 800 s N 6000 e S e SRS 2000 N ST P PSSV 5 N 5 5 N 700313 1 0 20 40 60 80 3600 3400 3200 3000 2800 0 10 20 30 TEMPERATURE F WEIGHT LBS HEADWIND MPH 1200 800 600 400 200 64 SROUND RUN DISTANCE FT ...

Page 73: ...WER OFF APPROACH SPEED 90 MPH IAS PAVED LEVEL RUNWAY NOTE THE LAMDING DATA SHOWN BELOW WAS PREPARED IN ACCORDANCE WITH CIVIL AIR REGULATION 3 86 i 2800 ot E S I ay j 2400 s T IO IS 400 A s N 2000 e Qc b ﬁ Sl o SRN Y SIS T E S 1600 N 1200 NN E 800 i 400 0 20 40 60 80 3600 3400 3200 30002800 0 10 20 30 TEMPERATURE F WEIGHT LBS HEADWIND MPH 65 700313 LANDING DISTANC E FT ...

Page 74: ... 6 S0z 0Tz 81T 78T 68T S6T 2 0Z 1 8 14 eS g 0z 1z 1 7z Ld L 81 T 6T 861 S0C v L I eg 1d 1 1 91T TET 68T 6T T1 0Z 80C 8 9 p c 0 pC Ld 1 61T L TT S L l L 61 70T 01T s L T ST 9 T T 0 T 8 C y 61 661 90z Iz S 0 LV 9 ST 617 ST 19T L 61 T0T 6 0C 912 8 0 ST 6 ST zZC 8 C 9 C T 661 S0z TIZ 81C s T 9 C ST T9C p 7z 0 T 6 T LW g0z L0 ST Tee ss 1 6 9 ST 9T L z TH 0T p0z 01 L1Z eT 65 IS 00 00 Z 0022 00z 00SZ 00Z...

Page 75: ...IQY3IY JOLVIOIANI MO14d 13nd suylers 104 asuey o_m_m m _ d3dlid H v9 SN M0T14 13N4 AEE _S 153 Ty g 13M04 69 Ly HM L4 8 mblzzf_ s8g 8 g o nrm SL ﬁ aguey 1j0 9ye 13M04 1S9g agduey Jj0 a3yel oun o 0 d oL ooot N 0009 7 0002 K s L1V dd0dive 700313 67 ...

Page 76: ...TWIN COMANCHE B SECTION IV 700313 NOTES 68 ...

Page 77: ...ANCE Tire Inflation Battery Service Brake Service Landing Gear Service Fuel and Oil Requirements Care of Air Filter Care of Windshield and Windows Serial Number Plate Propeller Service Fuel System 69 69 70 71 71 72 72 75 75 76 ...

Page 78: ...d before original installation and the relationship of tire tube and wheel should be maintained upon reinstaliation In the installation of new components it may be necessary to rebalance the wheels with the tires mounted Out of balance wheels can cause extreme vibration in the landing gear BATTERY SERVICE Access to the 12 volt 35 ampere hour battery is gained through the top panel of the fuselage ...

Page 79: ...L H 5606 petroleum base hydraulic brake fluid This should be checked at every 100 hour inspection and replenished when necessary Refill the brake reservoir on the aft bulkhead of the nose section to the indicated level No adjustment of brake clearance is necessary If the brake blocks become worn to 1 64 inch minimum lining replace them with new brake segments Remove the four cap bolts that join th...

Page 80: ...er position To add oil release the air through the strut valve and allow the strut to extend fully Remove the air valve and fill the unit through its opening Compress the oleo to within one quarter inch of full compression allowing air and excess oil to escape Reinsert the valve core and pump up the strut FUEL AND OIL REQUIREMENTS A minimum octane of 91 96 Aviation Grade fuel mustbe used in the Tw...

Page 81: ...eaned at least once every fifty hours Depending on the type of condition existing it may be necessary to clean the filters more often The following cleaning procedure is recommended by the manufacturer of the filter 1 Remove the filter from the engine compartment 2 Tap filter gently to remove dirt particles Do not use compressed air or cleaning solvents 3 Reinstall air filter CARE OF WINDSHIELD AN...

Page 82: ... OR DANAGED SPRAY 6411 FLAPS REQUIRE CLEANIN G AND LUBRICA TION LO TEMPER ATURE TURBOC HARGED ENGINES CLEAN FILTER N SOLYENT AND AFTER EXPGSU RE TO AN ABNORUA L QUANTIT Y OF WATER y9 TO DRY DIP IN SAE 10 OIL AND ALLOW TO DRAIN FOUR ﬂzcx IM_ X NYLON ROLLERS WILL x mﬂ REQUIRE LUBRICA TION IRCRAFT RECIPRO HOURS EITHER FLAP TRACKS OR ROLLERS s e me ﬁ mﬁﬁ r hﬂ ﬂnﬁ AS 2 BEARING S AND BUSHING S CLEAN EXT...

Page 83: ...uselage access panel or on the fuselage adjacent to the left side of the tail skid Airplane serial numbers should be used when contacting the factory on service or warranty matters PROPELLER SERVICE The air charge in the propeller cylinder should be kept at the pressure specified on the placard located in the spinner cap A copy of the placard is shown on page 76 The pressure in the cylinder will i...

Page 84: ...ressure or charge with propeller in FUEL SYSTEM The fuel screens in the strainers require cleaning at fifty hour or ninety day intervals whichever first occurs The fuel strainers beneath the floor panel are accessible through a plate in the underside center of the fuselage The fuel injector screen is located in the housing where the fuel inlet line connects the injector This screen should be clean...

Page 85: ...TWIN COMANCHE B SECTION V NOTES 700313 77 ...

Page 86: ...gine and Propeller 6 Fuel Injection 7 Structures P 8 Landing Gear 8 Control System 10 Fuel System 11 Electrical System 14 Vacuum System 16 Instrument Panel 17 Instrument Static Pressure System 20 Heating and Ventilating System 21 Seats L 22 Finish 5 o o 2 23 Baggage Area 23 Stall Warning System 24 SECTION I1I Operating Instructions 25 Preflight 25 Starting Engines 27 ...

Page 87: ...Vmc e e e e o e s 4 e e e 33 Stals 34 Spins s w s 235 Spin Recovery Techmque s s s 30 Cruising 36 Fuel Management 37 Approachand Landing 39 PostLanding 42 Emergency Procedures 42 Vmc Demonstration 49 Vmcand StallSpeed 50 Mooring 50 Loading and We1ght and Balance 3 3 5D OperatingTips 52 Flight Conditions 53 Diving Spiral 54 Radio Operation 55 SECTION IV Performance Charts s 5p Take Off Ground Run D...

Page 88: ... vs Density Altitude 64 Landing Distance Over 50 Foot Obstacle Short erld 65 Power Setting Table 66 Fuel Flow Chart 67 SECTION V General Maintenance 69 Tire Inflation 69 Battery Service 69 Brake Service o o o 70 Landing Gear Service 71 Fuel and Oil Requirements 71 Care of Air Filter e e e 72 Care of Windshield and Wmdows w 5 s 72 Serial Number Plate 75 Proper Service 75 FuelSystem 76 ...

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