Piper Aircraft Corporation PA-32R-301T Pilot Operating Handbook Download

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Summary of Contents for PA-32R-301T

Page 1: ...le for remaining within the operating limitations as outlined by instrument markings placards and this handbook Although the arrangement of this handbook is intended to increase its in flight capabili...

Page 2: ...AFT CORPORATION PA 32R 301 SARATOGA SP 12 11 36 2 178 3 30 0 Wing Area sq ft Min Turning Radius ft from pivot point to wing tip 5 6 REPORT VB r080 r 2 27 4 THREE VIEW Figure l l 7 1 ll r Zl 11 1 d u o...

Page 3: ...mber d Rated Horsepower e Rated Speed rpm 0 Bore inches g Stroke inches h Displacement cubic inches i Compression Ratio Engine Type 1 5 PROPELLER 2 BLADE PROPELLER a Number of Propellers b Propeller M...

Page 4: ...er inches l Minimum 2 Maximum g Propeller Type r 7 FUEL AVGAS ONLY a Fuel Capacity U S gal total b Usable Fuel U S gal total c Fuel Grade Aviation l Minimum Grade 2 Alternate Fuels REPORT VB 1080 t 4...

Page 5: ...l 2 3 4 a Maximum Takeoff Weight lbs b Maximum Landing Weight lbs c Maximum Ramp Weight lbs d Maximum Weights in Baggage Compartments a Compartment Volume cubic feet b Entry Width inches c Entry Heigh...

Page 6: ...al systems and equipment which require handbook supplements can be found in Section 9 Supplements 2 3 AIRSPEED LIMITATIONS SPEED KIAS KCAS Never Exceed Speed Vr rr Do not ex ceed this speed in any ope...

Page 7: ...Maximum Landing Gear Extension Speed Vlo Do not exceed this speed when extending the landing gear Maximum Landing Gear Retraction Speed Vr o Do not exceed this speed when retracting the landing gear M...

Page 8: ...ine f Fuel Flow Pressure Maximum red line g Fuel AVGAS ONLY mininrum grade h Number of Propellers i Propeller Manufacturer 0 Propeller Hub and Blade Model k Propeller Diameter inches Minimum Maximum l...

Page 9: ...ximum red line 0 Fuel Flow Pressure Maximum red line g Fuel Grade minimum grade h Number of Propellers i Propeller Manufacturer 0 Propeller Hub and Blade Model k Propeller Diameter inches Minimum Maxi...

Page 10: ...245oF Red Line Maximum 245 F c Oil Pressure Green Arc Normal Operating Range 60 PSI to 90 PSI Yellow Arc Caution Range ldle 25 PSI to 60 PSI Yellow Arc Caution Range Start and Warm Up 90 PSI to 100 PS...

Page 11: ...edge at the intersection of the untapered and tapered section It is the responsibility of the airplane owner and the pilot to insure that the airplane is properly loaded See Section 6 Weight and Balan...

Page 12: ...allons is the total per side each side having two interconnected tanks 2 23 NOISE LEVEL The corrected noise level of this aircraft is 77 6 d B A for two bladed propeller installations and 78 4 d B A f...

Page 13: ...or rear cabin door and cargo door removed a The airplane may be flown with the rear cabin door or rear cabin door and cargo door removed Flight with the front door removed is not approved b Maximum sp...

Page 14: ...of thc pilot thc following takeoff and landing checklists will bc installed TAKEOFF CHECKLIST Fuel on Proper Tank Electric Fucl Pump On Enginc Gages Chcckcd Alternate Air Closed Scat Backs Erect Mixt...

Page 15: ...view of the pilot Vro 132 DN I l0 UP Vre t32 MAX Near emergency gcar lever aircraft equipped with lever release EMERGENCY DOWN Near emergency gear knob aircraft equipped with cable releasc EMERGENCY...

Page 16: ...e area of the air conditioner controls when the air conditioner is installed WARNING __ AIR CONDITIONER MUST BE OFF TO INSURE NORMAL TAKEOFF CLIMB PERFORMANCE On the inside of the forward baggage comp...

Page 17: ...F AND LANDIT G On the face of the tachometer 2 blade propeller only AFTER 5 MIt r REDUCE POWER TO 2600 RPM Adjacent to fuel tank filler caps FUEL IOO OR IOOLL AVIATIOn GRADE Adjacent to fuel tank fill...

Page 18: ...he section is devoted to amplified emergency procedures containing additional information to provide the pilot with a more complete understanding of the procedures These procedures are suggested as a...

Page 19: ...rough or if it is necessary to clear obstructions Gear selector switch UP Emergency gear lever aircraft equipped with backup gear extender latched in OVERRIDE ENGAGED position If sufficient altitude h...

Page 20: ...TEMBER I 1966 REPORT VB 1080 3 3 CLOSED oFF Mixture adjust as necessary lf power is not restored prepare for power off landing POWER OFF LANDTNG On aircraft equipped with the backup gear extender lock...

Page 21: ...pare for power off landing LOSS OF FUEL FLOW Electric fuel pump oN Fuel selector check on tank containing usable fuel ENGINE DRIVEN FUEL PUMP FAILURE Throttle Mixture Electric fuel pump Throttle Elect...

Page 22: ...d oN If power not restored OFF ALT switch If alternator output cannot be restored reduce electrical loads and land as soon as practical The battery is the only remaining source of electrical power ALT...

Page 23: ...re not reduced ALT switch Land as soon as possible Anticipate complete electrical failure NOTE If the battery is depleted the landing gear must be lowered using the emergency extension procedure The g...

Page 24: ...wn and locked under normal conditions will take approx 10 seconds to be down and locked Emergency gear knob aircraft equipped PULL while fish tailing airPlane with cable release under normal condition...

Page 25: ...n and airspeeds will be reduced slightly To close the door in flight Slow airplane to 92 KIAS Cabin vens c1ose Storm window open Ifupper latch is open 1atch If side latch is open pu11 on armrest while...

Page 26: ...e continues more than a few seconds the fire should be extinguished by the best available external means The fuel selector valve should be oFF and the mixture at idle cut off if an external fire extin...

Page 27: ...cedure refer to the emergency checklist and paragraph 3 l3 3 1T ENGINE POWER LOSS IN FLIGHT Complete engine power loss is usually caused by fuel flow interruption and power will be restored shortly af...

Page 28: ...oss of power occurs at altitude lock emergency gear lever in OVERRIDE ENGAGED position before airspeed drops to 106 KIAS to prevent landing gear from inadvertently free falling on aircraft equipped wi...

Page 29: ...low approximately 103 KIAS and under normal lconditions will tak approximately 10 seconds to be down and locked If a t g r op landing is desi it will be necessary to latch the ovenide lever in the OVE...

Page 30: ...iirt lnt readings huru t of smoke oi other indications sincc the action to bc taken differs somewhat in each case Check for thc source of the fire first lf an clcctrical firc is indicated smoke in the...

Page 31: ...rticularly if othcr indications of ctual oil piessureioss such as suddcn increases in temperatures or oil smoke are apparent and an airport is not close lf cngine stoppage occurs proceed with Power Of...

Page 32: ...airport and have the cause investigated A steady rapid rise in oil temperature is a sign of trouble Land at the nearest airp it and let a mechanic investigate the problem Watch the oil pressure gauge...

Page 33: ...For airplanes with interlocked BAT and ALT switch operation when the electrical load cannot be reduced turn the ALT switch oFF and land as soon as practical The battery is tlie only remaining source...

Page 34: ...when emergency extension procedure is performed for raining purposes If the landing gear does not check down and locked reduce the airspeed to below 92 KIAS Move the landing gear selector to the DOWN...

Page 35: ...stics and normal landing can be made with the door open If bottr upper and side larches are open the door will trail slightly open and airspeed will be reduced slightly To close the door in flight slo...

Page 36: ...moved to f then R then back to BOTH If operation is satisfactory on either magneto proceed on that magneto at reduced powef with full RICH mixture to a landing at the first available airpoft If rough...

Page 37: ...mselves with the procedures given in this section in order to become proficient in the normal operations of the airplane The first portion of this section consists of a short fgrm check list which sup...

Page 38: ...atmospheric conditions and piloting technique a Best Rate of Climb Speed gear down flaps up gear up flaps up b Best Angle of Climb Speed gear down flaps up 76 KIAS gear up flaps up 80 KIAS c Turbulent...

Page 39: ...heck proper oPeration oFF ProPer oPeratron neutral REPORT VB 1080 4 3 WALK AROUND Figure 4 l 4 5 NORMAI PROCEDURES CHECKLIST PREFLIGHT CHECK COCKPIT Control wheel Parking brake Allswitches Avionics Mi...

Page 40: ...Pinner Air inlets Chock Nose gear strut Nose wheel tire Engine baffle seals oil Dipstick Oil filler cap Fuel strainer drain Baggage door Landing light REPORT VB 1080 4 4 dratn check clean check on boa...

Page 41: ...e down MISCELLANEOUS Fuel strainer Masterswitch Pitot heat switch Interior lighting Exterior lighting switches Fuel strainer drain Pitot Stall warning horn ISSUED NOVEMBER 8 1979 REVISED SEPTEMBER 17...

Page 42: ...HT N COLD Throttle Masterswitch Electric fuel pump Mixture Starter Mixture Throttle Oil pressure STARTING ENGINE WHEN HOT Throttle Master switch Electric fuel pump Mixture Starter Mixture Throttle Oil...

Page 43: ...nal power Plug Proceed with normal start Throttle External power Plug Master switch Oil pressure WARM UP Throttle TAXIING Chocks Taxi area Parking brake Throttle Prop Brakes Steering ISSUED NOVEMBER 8...

Page 44: ...4 8 to 5 2 Hg check check check press to test exercise then full INCREASE check oFF check Fuel flow Throttle BEFORE TAKEOFF retard oN check proper tank oN check CLOSED erect Master switch Flight inst...

Page 45: ...climb attitude After breaking ground accelerate to 6l to 7l KIAS depending on aircraft weight Gear OVERRIDE ENCAGED on aircraft equipped with backup gear extender Accelerate to climb speed Flaps r tra...

Page 46: ...s Airconditioner NORMAL TECHNIQUE Flaps Trim Throttle sHoRT FTELD TECHNIQUE 75V0 set Pcr Power table adjust proper tank erect fasten adjust oN set set down 132 KIAS max set white arc oFF as required 9...

Page 47: ...Air conditioner Radios and electrical equiPment Propeller Throttle Mixture Magnetos Master switch PARKING Parking brake Control wheel Flaps Wheel chocks Tie downs retract oFF OFF oFF full INCREASE fu...

Page 48: ...or panel illuminates and check the flaps for proper I p i i Turn OFF the master switch Check the primary flight controls I i p p operation and set the trim to neutral Open the pitot and static drains...

Page 49: ...let is clear of foreign matter NOSE SECTION Check the general condition of the nose section look for oil or fluid leakage and that the cowling is secure Check the windshield and clean if necessary The...

Page 50: ...for damage and operational interference Fairings and access covers should be attached properly Check the baggage to be sure it is stowed properly Check that the lights on the tail are clean and intact...

Page 51: ...losed and ttre overhead latch button turned to the LOCK position The front door should be gently pulled shut the door handle firmly latched and the overhead latch button turned to the LOCK position Se...

Page 52: ...eto switch advance the mixture control to full RICII and move the throttl to the desired setting If the engine does not fire within five to ten seconds disengage the starter and reprime b Starting Eng...

Page 53: ...e power to the lowest possible RPM t reduce sparking and disconnect the jumper cable from the aircraft Turn the master switch ON and check the alternator ammeter for an indication of output DO NOT ATT...

Page 54: ...gup or taxiing over ground containing loose stones gravel or any loose material that may cause damage to the ProPeller blades 4 I5 TAXIING Before attempting to taxi the airplane ground persomel should...

Page 55: ...eration and then placed in full INCREASE rpm for takeoff To obtain maximum rpm push the pedestal mounted control fully forward on the instrument panel Do not allow a drop of more than 5 RPM during thi...

Page 56: ...the gcar prematurely or the aircraft could settle back onto the runway If thc ovcrridc lock is used for takeoff it should be disengaged as soon as sufficicnt airspeed and terrain clearance are obtaine...

Page 57: ...luel selector flaps trim etc while maintaining adequate restraint for the occupant lf the inertia reel type shoulder harness is installed a pull test of its locking restraint feature should tre perfo...

Page 58: ...ow the airplane to accelerate to 58 to 66 KIAS depending on weight and apply back pressure to rotate for lift off After br aking ground accelerate to 6l to 7l KIAS depending on weight and select gear...

Page 59: ...airspeed 4 25 CRUISING The cruising speed is determined by many factors including power setting altitude temperature loading and equipment installed in the airplane The normal maximum cruising power...

Page 60: ...l quantity Saugc systems are Jpe rating lf the fuel flow indication is considerably higher than tti fucl ctu tly beirig consumed a fuel non le may be clogged and rcquire cleaning Thcre are no mechanic...

Page 61: ...ield length and other factors the following procedures are appropriate NORMAL TECHNIQUE No Performance Chart Furnished When available runway length is in excess of required runway length a normal appr...

Page 62: ...to obtain the balked landing climb speed of 80 KIAS Retract the landing gear and slowly retract the flaps when a positive climb is established Allow the airplane to accelerate to the best angle of cli...

Page 63: ...d gentle pitching may also precede the stall The gross weight statling speed with power off and full flaps is 5 KIAS With rhe flaps up rhis speed is increased 3 K IS Lossofaltitude duringstalls can be...

Page 64: ...the function and significance of the landing gear position indicators and warning lights The red gear warning light on the instrument panel and the horn operate simultaneouily in flight whin the thro...

Page 65: ...ckup gear extender the landing gear selector must be teftln i e UP position until all gear position indicators ir gr n On aircraft which do N T have the backup gear extcnder a pull iVp l NpING GEAR P...

Page 66: ...r mechanical deterioration of the aircraft This performance holvever can be duplicated by following the stated procedures in a properly maintained airplane Effects of conditions not considered on the...

Page 67: ...nd C G location of the airplane Make use of the Weight and Balance Loading Form Figure 6 ll and the C G Range and Weight graph Figure 6 15 to determine the total weight of the airplane and the center...

Page 68: ...ay necessary for the takeoff and or the barrier distance The landing distance calculations are performed in the same manner using the existing conditions at the destination airport and when establishe...

Page 69: ...e cruise pressure altitude and outside air temperature values have been established apply the existing conditions at the departure field to graph Figure 5 25 Now subtract the values obtained from the...

Page 70: ...e flight plan The values obtained by proper utilization of the graphs for the descent segment of the example are shown below l Time to Descend 12 min minus I min I I min 2 Distance to Descend 28 nauti...

Page 71: ...Cruise Fuel Consumption 13 8 GPH 6 Cruise Time e 2 divided by e 4 256 nautical miles divided by 144 5 KTS 1 77 hrs l hr 46 min 7 Cruise Fuel e 5 multiplied by e 6 13 8 GPH multiplied by 1 77 hrs 24 5...

Page 72: ...en the total fuel in gallons is determined multiply this value by 6lbl galto determine the total fuel weight used for the flight The total fuel calculations for the example flight plan are shown below...

Page 73: ...R 301 SARATOGA SP U 3 ZO o Y o l F illl oo zY o F oo O t oo _gs rL o o o o n o F o o I c o E t F z u l f c F o o G u t I th v o g o o o r o o lo oooo o FO o ooo oFro svc t AIRSPEED SYSTEM CALIBRATION...

Page 74: ...0 ANGLE OF BANK DEGREES STALL SPEED VERUS ANGLE OF BANK Figure 5 5 o s Y I o U u A a J J F t 00 o g V I 8zo U A o J J F aoo 60 REPORT VB 10t0 13 Wing flap up Angle of bank 30 Stall sp ed 65 5 KIAS Exa...

Page 75: ...c E u o i A ds OA ASSOCTATED CONDTTTONS Lift off speed 80 KIAS 27OO RpM AND FULLTHROTTLE BEFORE BRAKE RELEASS Barrier speed 8O K AS PAVED LEVEL DRY RUNWAY E g t F L lz j brl i ti t n Y F2 x X aO 4z 50...

Page 76: ...T ut oO r 6 E E6 ut lfdoud 30v s z ulr1 lSdoud 3 lv 18 6 NORMAL PROCEDURE TAKEOFF GROUND ROLL Figure 5 9 E o o o o o o t I o o o o N E rl 8 6 n t s t a o iE o E cll o 8 Xco g o o s IEEE Yv O F gg or...

Page 77: ...O0 ft Lift off speed 68 KIAS Barrier speed 74 40 30 20 10 0 10 20 30 40 OUTSIDE AIR TEMPERATURE _ C PA 32R 301 PERFORMANCE _ FLAPS O ASSOCIATEO CONDITIONS 27OO RPM AND FULLTHROTTLE BEFORE BRAKE RELEAS...

Page 78: ...t o o o o F v I F z UT z o o E o o o z o o z f o o I F E c 3 a I l G E ul o u t ll l e o f o a 3 z o o J I o o o o D o o o l o o o o o o ll o o d o o o cl o o o r o o o o a Jz u 9 F la lz rO d Ei OB z...

Page 79: ...d 30V lE z REPORT VB 1080 5 1E o Y l z uJ P6 6 o a oO z E o o ro NU qo 3z N3 oO 84 l o OF NI o ur 33 o o o o o9 o I 6 lll NE f F o FE ul 4 oE UI F 9n olu se o r5 o l an l J ul tr u l v al l0 q l E th...

Page 80: ...o F v I F z ul z o o E o o o z D o o o F o I 0 I o o o Ntl 90 3z N oO 3o 6l o OF N o Xu g o o o oo ol ul OE F Pg o o u F oE 5 UJ oO o F of 9o o ISSUED SEPTEMBER 27 1979 REVISED OCTOBER 6 19t0 REPORT V...

Page 81: ...00 ft Outside air temp 6oC ross weight 30O0 lbs Rate of climb 640 fpm 1 000 200 o 40 o a a c It El r t El a o RATE OF CLIMB FT MIN OUTSIDE AIR TEMPERATURE _ C FOR NONMAL OPEBAIIONS WITH 2 BLADE PROP I...

Page 82: ...p 6 C Gross weight 3480 lbs Rato of climb 6OO fpm 260 RPMI 40 30 20 10 0 10 20 30 40 OUTSIDE AIR TEMPERATURE _ OC o 500 1 0 1600 RATE OF CLIMB _ FT MIN I i o e F E 3 FOR NORMAL OPERATIOiIS wlTH 2 BLAD...

Page 83: ...o N F FJ E 2 z I u A o a I G o o I o il G EF oN s eE a t a I F D 5 e ij 3 E E E EE o o 5 oPoo s g gf oO cc E E E I E J o lt o ul F E F o Y I E N 00 I G o o tt o o o I UJ E f F E ut c u J F E ul o ah...

Page 84: ...En E rro 6 oooEri AO o ir o oo AE6F sssE ttooicy 33E e oo J JFoq o REPORT VB 10t0 s 23 jj o E F u l lt Y I o FUEL TIME AND DISTANCE TO CLIMB Figure 5 25 ti CG EE u J t o E I F J J f r J f 88 F NN E UJ...

Page 85: ...rature Add manifold pressure for air temperature above standard subtract for temperature below standard 195 HP 65V0 Rated Aptryl_ 3 I 3 8 gal t RPM MAN PRESS 2100 2200 2300 2400 23 7 22 8 23 5 22 5 23...

Page 86: ...tr N Y I o o N o o Oo tl RH F o FG ut o oE uJ F 9E ouJ o n 85 o o rf MAXIMUM SPEED PERFORMANCE Figure 5 29 ISSUED NOVEMBER 8 1979 REVISED SEPTEMBER 17 1984 REPORT VB r0t0 5 27 i O J Oo o o o E I g N o...

Page 87: ...u z gt tz OU q F o z t i o E G u t4 f E F o 2 I t o I u l G I G ul o l F G ur o o 5 o o o o o N o SPEED CRUISE POWER Figure 5 31 REPORT VB l080 s 28 ISSUED NOVEMBER 8 1979 REVISED OCTOBER ll 1983 9rrr...

Page 88: ...E STANDARD TEMPERATURE 2 SUBTRACT 1 5 N M RANGE FOR EACH DEGREE CENTIGR l t lal Fl FO Ei z t ut z 9 r0 E I a 1 z 11r G F oc a t Cruise pressure altitude 6000 Cruise outside air temp 6oC Power 65 Range...

Page 89: ...x UJ F F o I E I o t o o o o N o o o o o o o o o o N o o o if lJ 3onrllv tunsstud ENDURANCE Figure 5 39 ISSUED NOVEMBBR 8 1979 REVISED OCTOBER ll 1983 RBPORT VB I080 5 32 ts ss QO D U o H 3 20 oz ise...

Page 90: ...e5 oo g E il e 6 a s o at o t z il d a 6 ot r o s s o o 8 a E o o 2 uJ o 2 u J ul f L F 00 I E N 3 FUEL TIME AND DISTANCE TO DESCEND Figure 5 41 REPORT VB 10E0 5 33 11 lF ld lXt l l Iilt llEil tl ti i...

Page 91: ...R 301 SARATOGA SP aa ul 4 E J J F I r c 2 G ut o J o o 0 o 6 o F tr o N o o o o o rt o I t c f F r ul o E l G i ul _o o F f o GLIDE RANGE Figure 543 REPORT VB 10E0 5 34 ISSUED NOVEMBER I t979 REVISED...

Page 92: ...o ul o z F I o I o z J 2000 I AOO 1 600 1400 Example Destination pressure 400 Destination O A T 24 C Landing weight 33OO lbs approach speed 78 KIAS Wind 5 knots headwindl Landing 1490 ft to o 10 20 3...

Page 93: ...t NtoNv o F v I o F 2 UJ z o o E o a o z o o o o N o at F9 o E ol o oI o 9 YU B o o o o tt o9 o I o u l Nac f F o uJ o o uJ F 9a a o lll q_o o E5 o o I o g o b o 6 F o Y I E N OD I o G J Jlj9 kB o x...

Page 94: ...F ts I r PA 32R 301 F z 2 EA trj _ UO F i3 a Z r I 3 C L a Az o o z 22 HF rz oz o tat F o a c ItJ I z o t5 z E FI _6 o t a F r I E u E E to t r o rn E ul o ur o z F at o z z J 2000 1 aoo 600 400 200...

Page 95: ...Figure 5 51 o F Y bl F 2 e o c o o o o o oo ge N o 8x ml Oq OL 0 8 tt o o o o I o o c o o J R i E t ek E U A oE u F oE T U oe No F f oO a o o o o 6 c o 6 6 o o 6 J 2 k8 EE uE i E E 9 E g E I 5 REPORT...

Page 96: ...t will have Center of gravity is a determining factor in ilight characteristics If the C G is too fai forward in any airplane it may be difficult to rotate for takeoff or landing If the c G is too far...

Page 97: ...d Note that the useful load includes usable fuel baggage cargo and passengers Following this is the method for computing takeoff weight and C G 6 3 AIRPLANE WEIGHING PROCEDURE At the time of licensing...

Page 98: ...retracted position and all control surfaces in the neutral position Tow bar should be in the proper location and all entrance and baggage doors closed 6 Weigh the airplane inside a closed building to...

Page 99: ...ale Position and Symbol Nose Wheel N Right Main Wheel R Left Main Wheel L Basic Empty Weight as Weighed WEIGHING FORM Figure 6 l d Basic Empty Weight Center of Gravity l The following geometry applies...

Page 100: ...the airplane as licensed at the factory 1 hese figures apply only to the specific airplane serial number and registration number shown The basic empty weight of the airplane as licensed at the factory...

Page 101: ...al Equipment Basic Empty Weight The standard empty weight includes full oilcapacity and 5 0 gallons of unusable fuel AIRPLANE USEFUL LOAD NORMAL CATECORY OPERATION Ramp Weight Basic Empty Weight Usefu...

Page 102: ...e may be limited by fwd envelope Without aft baggage fuel may be limited by fwd envelope for some combinations of optional equipment d 4 Occupants 2 in front 2 in middle Load rear baggage compartment...

Page 103: ...ment of all items to be carried in the airplane c Add the moment of all items to be loaded to the basic empty weight moment d Divide the total moment by the total weight to determine the C G location...

Page 104: ...problem is at 93 3 inches aft of the datum line Locate this point 93 3 on the C G range and weight graph Since this point falls within the weight C G envelope this loading meets the weight and balance...

Page 105: ...ke off weight of this loading problem is at inches aft of the datum line Locate this point on ttre C C range and weight graph If this point falls within the weight C G envelope this loadlng hebts the...

Page 106: ...32R 301 SARATOGA SP SECTION 6 WEIGHT AND BALANCE 650 600 550 450 400 350 G z D o g F E I IJJ o o J 150 100 o 51015 35 45 50 55 60 65 MOMENT 1 OOO POUNDS INCH ES LOADING GRAPH Figure 6 13 REPORT VN TO...

Page 107: ...2R 30I SARATOGA SP 3600 LBS MAX GROSS WT 91 92 93 94 95 WEIGHT VS C G ENVELOPE 87 89 3 86 85 84 I 81 80 78 80 A2 84 86 88 90 92 94 c G LOCATTON TNCHES AFT DATUM F lt G ao o 6 l 2 F I 2 C G RANGE AND W...

Page 108: ...seats or in the baggage compartments Brief instructions are given on the plotter itsel To use it first plot a point on the grid to locate the basic weight and C G location This can be put on more or l...

Page 109: ...otter grid at 2150 pounds and 83 5 inches to represent the basic airplane See illustration 2 Slide the slotted plastic into position so that the dot is under the slot for the forward seats at zero wei...

Page 110: ...FORWARD MIDDLE SEATS FRONT SEATS 3600 LBS MAX GROSS WT 9t 92 93 94 95 89 WEIGHT vS C c ENVELOPE 88 87 3 85 8 I 8 800 to o 7 lr F T o 240o 2 l lc o 78 80 A2 84 86 88 90 92 94 c G LOCATTON TNCHES AFT DA...

Page 111: ...llaneous steel parts the cowling and the lightweight plastic extremities tips of wings tail fin and stabilator the basic airframe is of aluminum alloy Aerbbatics are prohibited in this airplane since...

Page 112: ...ank A vertical stabilizer an ail movable horizontal stabilator and a rudder make up the empennage The stabilator incorporates an anti servo tab which provides longitudinal stability and longitudinal t...

Page 113: ...lter Alternate air is unfiltered therefore it should not be used during ground operation when dust or other contaminants might enter the system The primary through the filter induction source should a...

Page 114: ...gh RPM to low RPM The mixture control lever is used to adjust the air to fuel ratio The engine is shut down by the placing of the mixture control lever in the full lean position In addition the mixtur...

Page 115: ...7 PA 32R 3OI SARATOGA SP DESCRIPTION OPERATION S N 32R 85I3OO1 AND UP f AIRCRAFT EOUIPPEO WTH BACKUP GEAR EXTENDER til CoNTROL QUADRANT AND CONSOLE Figure 7 l ISSUED NOVEMBER I 1979 REVISED SEPTEMBER...

Page 116: ...a selector switch on the instrument panel to the left of the control quadrant Figure 7 3 The landing gear is retracted orextended in about seven seconds Some aircraft also incorporate a pressure sensi...

Page 117: ...placed in the raiscd position can be used to ovcrride the system and gear position is then controlled by the selector switch regardless of airspeed power combinations The emergency gear levcr is provi...

Page 118: ...talled which activatcs the warning horn and light whencver the flaps are extended bcyond the approach position 10 and thc landing gcar are not down and locked The gcar warning horn emits a 90 cyclc pe...

Page 119: ...R DOWN UP UP LIill4IT swtTcH GEAR WARNING HORN LANDING GEAR ELECTRICAL SCHEMATIC Figure 7 5 t2 DOWN Lpc K SWITCH REPORT VB 10t0 7 9 INOTE 5 PS it_r PRESS CYCLE AUTOMATIC GEAR DOWN ACIUATOR NOTE 3 I I...

Page 120: ...REFERENCE IS FOR AIRCRAFT EOUIPPEO WITH BAOKUP GEAR EXTENDER AUTOMATIC GEAR DO A N PRESSURE SENSING CHAMBER NoTE 1 ISSUED NOVEMBER 8 1979 REVISED NOVEMBER 13 1989 LANDING GEAR HYDRAULIC SYSTEM SCHEMAT...

Page 121: ...CONIROL SHUTTLE GEARUP CHECK VALVE PNESSURE NO E GEAF UP ISSUED DECEMBER 10 1986 REVISED NOVEMBER 13 1989 gWTCH REPORT VB 1080 7 L0a VALVE BESTRICTO NIPPLE LANDING GEAR HYDRAULIC SYSTEM SCHEMATIC Airc...

Page 122: ...IS FOR AIRCRAFT EOT IIPPEO WTH EACKUP GEAR EXTENDER LANDING GEAR HYDRAULIC SYSTEM SCHEMATIC Aircraft equipped with Oildyne pump and lever emergency gear release Figure 7 7b REPORT VB 1080 7 10b SHUTTL...

Page 123: ...ESSIUFE CONTROL REUEF 0 020 0rA BLEEO HOI E NOSE GEAR SHUTTLE Et Or t SwlTCH RESTRICTOR LANDING GEAR HYDRAULIC SYSTEM SCHEMATIC Aircraft equipped with Oildyne pump and cable emergency gear release Fig...

Page 124: ...trailing edge This tab serves the dual function of providing trim control and pitch control forces The nim function is controlled by a nim control wheel located on the control console between the two...

Page 125: ...oximate flap position On aircraft serial numbers 32R 8513001 thru 32R 8513016 there are three stops for the flap control lever full up 0o flap lst notch 25o flap and full down 40o flap I On aircraft s...

Page 126: ...SECTION 7 PA 32R 3OI SARATOGA SP DESCRIPTION OPERATION BUSS 5AMP I5 AMP T l N O N C J I I L RELAY L r I I I I I t T 1 I J o N C ELECTRIC FLAP SCHEMATIC Figure 7 10 RELAY _J REPORT VB 1080 7 l2t I I L...

Page 127: ...corner ofthe tank making sure that enough fuel has flowed to ensure the removal of all water and sediment 2 Place a container beneath the fuel strainer sump drain outlet located under the fuselage 3 D...

Page 128: ...ION OPERATION pA 32R 30r SARATOGA Sp VENI LIT E FIEL FLOIV PR SS E GA ELECTRIC FUEL PUMP FUEL SELECTOR VALVE FUEL SYSTEM SCHEMATIC Figure 7 l I REPORT VB 1080 7 t4 FLOa OIVIDER FUEL FUEL CELL FUEL CEL...

Page 129: ...re the fuel not visible through the filler neck in each wing is installed in the inboard fuel tank This gauge indicates usable fuel quantities from 5 gallons to 35 gallons in the ground attitude The s...

Page 130: ...ted on the left side of the forward fuselage Electrical switches are located on a panel to the pilot s left Figure 7 15 and all circuit breakers are on the lower right instrument panel refer to Figure...

Page 131: ...uated by an adjacent switch An optional wing tip recognition light system consists of 2 lights one in each wing tip and is operated by a split landing light recognition light rocker type swit h mounte...

Page 132: ...ton f 1 L IP tESf 3U orL PRE33 g 1t3 su vc sEfl3 su txYEtIlL 6AltE iY 30L t oto I lcc I6 AIP EXTER ll FOTER RECEPTACLE I REPORT VB 1080 7 r 8 ST RI E R SdEXOtD ro nAoD u0xT3 OIII R ATAiTEI ctaAi L IE...

Page 133: ...ull intensity during daytime flying When aircraft is operated at night and the radio light dimming switch is turned on gear lights will automatically dim IYARNINC Anti collision lights should not be o...

Page 134: ...ATOGA SP CAUTION Do not use cigar lighter receptacles as power sources for any devices other than the cigar lighters supplied with the airplane Any other device plugged into these receptacles may be d...

Page 135: ...n pressure in a system that has remained constant over an extended period may indicate a dirty filter dirty screens possibly a sticking vacuum regulator or leak in system a low vacuum indicator light...

Page 136: ...HSI 8 ALTIMETER 9 VERTICAL SPEED INDICATOE 10 ANNUNCIATOR PANEL 11 GS LOC l OR INDICATOR 12 VOR INDICATOR 25 AUTOPILOT 26 Et GIil INSTRUMENT CLUSTER 27 SLAVEMETER 28 NAV SELECTOF SWITCH 29 MAGilETO A...

Page 137: ...adio MASTER switph circuit failure The emergency bus switch is located behind the lower right shin guard left of the circuit breaker panel A ground clearance energy saver system is available to provid...

Page 138: ...partially or completely blocked pitot head will give erratic or zero readings on the instruments NOTE During preflight check to make sure the pitot cover is removed 7 23 CABIN FEATURES For ease of en...

Page 139: ...CORPORATION SECTION 7 pA 32R 301 SARATOGA SP DESCRIPTION OPERATION J 3 o EE uh O 6 OOI z EO S 8Pe 5 a e 3E fiF EE Ee ES EHEEEEE I Le dd ddF I PITOT STATIC SYSTEM Figure 7 23 REPORT VB 1080 1 ISSUED N...

Page 140: ...ired On earlier aircraft provided with a single strap adjustable shoulder hamess for each front seat the shoulder strap is routed over the shoulder adjacent to the windows and attached to the lap belt...

Page 141: ...ld the upper lobes in place and lower the free end of the table to the level work position The retaining springs will click when securc To stow the cabin work table remove the table by lifting the fre...

Page 142: ...rd baggage door will illuminate an amber light located on the pilot s annun ciator panel The annunciation when illuminated is BAGGAGE DOOR adrising the pilot of this condition NOTE It is the pilot s r...

Page 143: ...I cc EE Eut Iou l t E ulll uJ u l tror i r I I I i I I I I a J o F 2 38 oE E g F LF ui o Htd9 qSdh SeeO uu EFF u6 JOO EEEK quu oot cist q 3 e Y FF F 44 s b 5 ESEi 3 s c c uquqxE ExEx9 t sr33 tdFdot j...

Page 144: ...ll speeds are shown on graphs in the Performance Section The stall warning horn emits a continuous sound The landing gear warning horn is different in that it emits a 90 cycle per minute beeping sound...

Page 145: ...Turning the control clockwise increases cooling counterclockwise decreases cooling The fan speed switch and the air conditioning Oti OFF switch are inboard of the temperature control The fan can be op...

Page 146: ...portion of the fuselage just below the stabilator leading edge and is accessible through a plate on the right side of the fuselage This plate is attached with slotted head nylon screws for ease of re...

Page 147: ...the ELT unit to OFF Normal operation can then be restored by pressing the small clear plastic reset button located on the top of the front face of the ELT and then moving the switch to ARM A pilot s r...

Page 148: ...n be reset by either positioning the remote switch to the ON position for two seconds and then I relocating it to the ARM position or by setting the switch on the ELT to OFF and then back to ARM In th...

Page 149: ...cedures to follow in operating and adjusting the system to its optimum efficiency refer to the appropriate operating and service manuals provided by the radar system manufacturer WARNING Heating and r...

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Piper Aircraft Corporation PA-32R-301T, Pilot Operating Handbook

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