Piper Aircraft Corporation ARCHER II PA-28-181 Operating Handbook Download

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Summary of Contents for ARCHER II PA-28-181

Page 1: ...lso responsible 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 fl...

Page 2: ...ERAL PIPER AIRCRAFT CORPORATION PA 2 1t1 ARCHER II I t2 te 0t THREE VIEW Figure l l Wing Area sq ft Min Turning Radius ft from pivot point to wingtip z 170 0 30 0 I 8 20 I Lll REPORT VB 1120 t 2 ISSUE...

Page 3: ...Number of Propellers b Propeller Manufacturer c Model d Number of Blades e Propeller Diamete r inches l Maximum 2 Minimum f Propeller Type I 7 FUEL AVCAS ONLY a Fuel Capacity U S gal rorat b Usable Fu...

Page 4: ...Maximum Takeoff Weight lbs c Maximum Landing Weight lbs d Maximum Weights in Baggage Compartment lbs REPORT VB 1120 l 4 200 0 ISSUED JULY 2 1979 REVISED JULY 21 1982 8 Refer to latest issue of Lycomin...

Page 5: ...SECTION 1 GENERAL 1 I5 BAGGAGE SPACE a Compartment Volume cubic feet b Entry Width inches c Entry Height inches r 17 SPECIFIC LOADINGS a Wing Loading lbs per sq ft b Power Loading lbs per hp 24 22 20...

Page 6: ...h the operating limitations stated in the form of placards and markings and those given in this section and this complete handbook Limitations associated with those optional systems and equipment whic...

Page 7: ...ome more pronounced Linear interpolation may be used for intermediate gross weights Maneuver ing speed should not be exceeded while opera ting in rough air Maximum Flaps Extended Speed Do not exceed t...

Page 8: ...red line 8 Fuel AVGAS ONLY minimum grade 9 Number of Propellers l0 Propeller Manufacturer l l Propeller Model l2 Propeller Diameter Minimum Maximum l3 Propeller Tolerancc static RPM at maximum penniss...

Page 9: ...Warm Up Red Line Minimum Red Line Maximum d Fuel Pressure Green Arc Normal Operating Range Red ine Minimum Red Line Maximum 500 r 2650 RPM 2650 to 2700 RPM 27OO RPM 75 to 245 F 245 F 60 PSI tO 90 PSI...

Page 10: ...t Inches Aft of Datum Rearward Limit Inches Aft of Datum 2t30 2050 and less 83 0 82 0 93 0 93 0 NOTES Straight line variation between points given The datum used is 78 4 inches ahead of the wing leadi...

Page 11: ...ted maneuvers approved Entry Speed I13 KIAS I13 KIAS I13 KIAS 2 I9 TYPES OF OPERATION The airplane is approved for the following operations when equipped in accordance with FAR 9l or FAR 135 a Day V F...

Page 12: ...be arpt Ut or unacceptable for operation at into or out of any airport The above statement not withstanding the noise level stated above has Ue n urtn a by and apfroved by the Fci eral Aviation Admin...

Page 13: ...NO ACROBATIC MANEUVERS ARE APPROVED R i RMAL cArEcoRY oPERATIoNS sPINS in i noruBITED FoR NoRMAL AND UTILITY CATEGORY In full view of the Pilot TAKEOFF CHECK LIST Fuel on Proper tank Electric fuel Pum...

Page 14: ...FLIGHT On inside of the baggage compartment door BAGGAGE MAXIMUM 2OO LBS UTILITY CATEGORY OPERATION NO BAG GAGE OR AFT PASSENGERS ALLOWED NOR MAL CATEGORY OPERATION SEE PILOT S OPERATING HANDBOOK WEI...

Page 15: ...S ARE LIMITED TO THE FOLLOWING ENTRY SPEED SPINS PROHIBITED STEEP TURNS LAZY EIGHTS CHANDELLES In full view of the pilot WARNING TURN OFF STROBE LIGHTS WHEN IN CLOSE PROXIMITY TO GROUND OR DURING FLIG...

Page 16: ...r caps FUEL 100 or l00LL AVIATION GRADE or FUEL IOO I3O AVIATION GRADE MIN USABLE CAPACITY 24 GAL USABLE CAPACITY TO BOTTOM OF FILLER NECK INDICATOR I7 GAL Adjacent to the filler caps serial numbers 2...

Page 17: ...f the section is dpvoted to amplified emergency procedures containing additional information to provide the pilot with a more complete understanding of the procedures These procedures are suggested as...

Page 18: ...landing crank engine idle cut off open OFF OFF Abandon if fire continues ENGINE POWER LOSS DURING TAKEOFF If sufficient runway remains for a normal landing land straight ahcad If insufficient runway...

Page 19: ...uel When power is restored Carburetor heat OFF Electric fuel pump oFF If power is not restored prepare for power off landing Trim for 76 KIAS POWER OFF LANDING Locate suitable field Establish spiral p...

Page 20: ...tric fuel pump Hcatcr and clelroster Procccd with p lwer off landing procedure LOSS OF OIL PRESSURE Land as soon as possible and investigatc cause Preparc for powcr off landing LOSS OF F UEL PRESSURE...

Page 21: ...educe electrical loads to minimum ALT circuit breaker Chcck and rcsct as required ALT switch oN If power not restored ALT switch oFF If alternator output cannot be restored reduce electrical loads and...

Page 22: ...increased system voltage and radio frequency noise operation with ALT switch ON and BAT switch OFF should be made only when required by an electrical system failure If alternator loads are not reduce...

Page 23: ...ure ENCINE ROUGHNESS Carburetor heat If roughness continues after one min Carburetor heat Mixture close latch pull on armrest while moving latch handle to latched position latch side latch then top la...

Page 24: ...This is an attempt to draw the fire back into the engine If the engine has started continue operating to try to pull the fire into the engine In either case above if fire continues more than a few sec...

Page 25: ...aph 3 13 An airspeed of at least 76 KIAS should be maintained If altitude permits switch the fuel selector to another tank containing fuel and turn the electric fuel pump ON Move the mixture control t...

Page 26: ...piral pattern around this field Try to be at 1000 feet above the field at the downwind position to make a normal landing approach When the field can easily be reached slow to 66 KIAS with flaps down f...

Page 27: ...e either partial or complete A partial loss of oil pressure usually indicates a malfunction in the oil pressure regulating system and a landing should be made as soon as possible to investigate the ca...

Page 28: ...3 ELECTRICAL FAILURES Loss of alternator output is detected through zero reading on the ammeter Before executing the following procedure insure that the reading is zero and not merely low by actuating...

Page 29: ...nd ALT switch operation when the electrical load cannot be reduced turn the ALT switch OFF and land as soon as practical The battery is the only remaining source of electrical power Also anticipate co...

Page 30: ...s required to smoothly regain a level flight attitude 3 27 OPEN DOOR The cabin door is double latched so the chances of its springing open in flight at both the top and side are remote However should...

Page 31: ...ss is usually due to carburetor icing which is indicated by a drop in RPM and may be accompanied by a slight loss of airspeed or altitude If too much ice is allowed to accumulate restoration of full p...

Page 32: ...ing at pilot s discretion NOTE Partial carburetor heat may be worse than no heat at all since it may melt part of the ice which will refreeze in the intake system When using carburetor heat therefore...

Page 33: ...emselves with the procedures given in this section in order to become proficient in the normal operations of the airplane The first portion of this section consists of a short form check list which su...

Page 34: ...ondition 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...

Page 35: ...rol wheel Avionics Master switch Fuel quantity gauges Master switch Ignition Exterior Control surfaces Hinges Wings Stall warning Fuel tanks release belts OFF check OFF check for damage check for inte...

Page 36: ...lets Alternator belt Required papers Seat belts and harness check proper inflation 3 25 in clear Tow bar and control locks Baggage i 1lil Baggage door stowed properly secure close and secure drain and...

Page 37: ...sure STARTING ENGINE WHEN FLOODED Throttle Master switch Electric fuel pump Mixture Starter Mixture Throttle Oil pressure i t adjust check open full oN OFF idle cut off advance retard check STARTING W...

Page 38: ...r pane1 press to test Carburetor heat check Engine is warm for takeoff when throttle can be opened without engine faltering Elecnic fuel pump OFF Fuel pressure check Throttle retard BEFORETAKEOFF Mast...

Page 39: ...5 to 54 KIAS depending on aircraft weight Accelerate to best flaps up angle of climb speed 64 KIAS slowly retract the flaps and climb past the obstacle Accelerate to best flaps up rate of climb speed...

Page 40: ...uretor heat POWER OFF Carburetor heat Throttle Airspeed Mixture Power APPROACH AND LANDING Fuel selector Seat backs I netts7harness Electric fuel pump Mixture 76 KIAS 64 KIAS 87 KIAS OFF at desired al...

Page 41: ...ps 40o set 102 KIAS max OFF 66 KIAS STOPPING ENGINE Flaps Electric fuel pump Airconditioner retract Radios oFF OFF OFF OFF Throttle Mixture full aft idle cut off OFF Magnetos Master switch PARKING Par...

Page 42: ...t on the steP Upon entering the cockpit release the seat belts securing the control wheel Turn OFF all avionici equipment Turn ON the master switch and ft t tft fuet quantity gauges ioi sufficient fue...

Page 43: ...ng the engine Each quick drain should be checked after closing it to make sure it has closed completely and is not leaking Check all of the fuel tank vents to make sure they are open Next complete a c...

Page 44: ...si bility to all controls including fuel selector flaps trim etc while maintaining adequate restraint for the occupant If the inertia reel type shoulder harness is installed a pull test of its locking...

Page 45: ...engine fires release the magneto switch advance the mixture and retard the throttle d Starting Engine With External Power Source An optional feature called the Piper External Power PEP allows the ope...

Page 46: ...rnal power supply 4 I5 WARM UP Warm up the engine at 800 to 1200 RPM for not more than two minutes in warm weather and four minutes in cold Avoid prolonged idling at low RPM as this practice may resul...

Page 47: ...d 50 RPM Operation on one magneto should not exceed l0 seconds Check the vacuum gauge the indicator should read 5 0 t 1 Hg at 2000 RPM Check the annunciator panel lights with the press to test button...

Page 48: ...and shoulder harness should be fastened and adjusted Fasten the seat belts snugly around the empty seats NOTE If the fixed shoulder harness non inertia reel type is installed it must be connected to t...

Page 49: ...to the flaps up rate of climb speed 76 KIAS if no obstacle is present or 64 KIAS if obstacle clearance is a consideration Slowly retract the flaps while climbing out 4 25 CLIMB The best rate of climb...

Page 50: ...before peak EGT is reached If this occurs the EGT lcorrtsponding to the onset of engine roughness should be used as the peak lreference value Always remember that the electric fuel pump should be turn...

Page 51: ...o the seat belt and adjusted to allow proper accessi bility to all controls including fuel selector flaps trim etc while maintaining adequate restraint for the occupant lf the inertia reel type should...

Page 52: ...raft weight on the main wheels In high wind conditions particularly in strong crosswinds it may be desirable to approach the ground at higher than normal speeds with partial or no flaps 4 33 STOPPING...

Page 53: ...of altitude during stalls varies from 100 to 350 feet depending on configuration and power NOTE The stall warning system is inoperative with the master switch OFF During preflight the stall warning s...

Page 54: ...AND BALANCE It is the responsibility of the owner and pilot to determine that the t airplane remains within the allowable weight vs center of gravity envelope I while in flight For weight and balance...

Page 55: ...or the various parameters of weight altitude temperature etc The performance charts are unfactored and do not make any allowance for varying degrees of pilot proficiency or mechanical deterioration of...

Page 56: ...outlines a detailed flight plan using the performance charts in this section I Each chart includes its own example to show how it is used WARNING Performance information derived by extrapo lation beyo...

Page 57: ...Balance Loading Form Figure 6 l l and the C G Range and Weight graph Figure 6 15 to deter mine the total weight of the airplane and the center ol gravity position After proper utilization of the info...

Page 58: ...nditions at the destination airport and when established the landing weight The conditions and calculations for the example flight are listed below The takeoff and landing distances required for the e...

Page 59: ...gment of the flight plan corrected for field pressure altitude and temperature The following values were determined from the above instruc tions in the flight planning example l Cruise Pressure Altitu...

Page 60: ...al cruise distance Refer to the appropriate Avco Lycoming Operator s Manual when selecting the cruise power setting The established pressure altitude and temperature values and the selected cruise pow...

Page 61: ...total fuel required by adding the fuel to ciimb the fuel to descend and the cruise fuel When the total fuel in gallons is determined multiply this value by 6lb gal to determine the total fuel weight...

Page 62: ...110 100 90 80 70 60 50 40 o F o z v I o UJ u r ah E a o u l F tr o J o PA 28 181 60 70 80 90 loo 1 lo 120 130 140 150 160 t70 K AS _ NO INSTRUMENT ERROR 40 50 AIRSPEED SYSTEM CALIBRATION Figure 5 3 RE...

Page 63: ...lo o60 6 c STALL SPEEDS Figure 5 5 P o N rt ot o l0 NJ oE PP IE u l ttc oo uli 7 R9 o Nz o U i H 6 otl Na o uJ F 9 o E o o a o a o ol o ox q xh i No v de o oE 6 iyl I 9 o o o E PSE g 9 tr U F o F I o...

Page 64: ...TLE BEFORE BRAKE RELEASE ul ur ll I E g TE E o E o ro ut o u t J 2 F 2 o lt lt o ul I tl xxt 3500 30q 2500 20q Et F Fg a fE Ft I a r oox c v rl oEi lJr r rE El F EI o F 3 2 E Temperature 21 oC Wind 15...

Page 65: ...DEi bE F E o F z E 2 o FI 3tloo 3200 30 0 Example Depanure airport Pressure altitude 2OOO ft Temperature 21 C Gross weight 24OO lbs Wind 8 knots headwind Takeoff distance 186O ft 40 30 20 10 0 10 20...

Page 66: ...Wind I knots headwind Takeoff roll 1 100 F E u e rg l 1X 0e El EO dE rr Et l 6 n o e z It n o F F F ur ul l I J J o lr o z D o e lt lr o ul I 2400 2200 20q 1 8 0 1600 1400 1200 1000 800 600 400 CA o...

Page 67: ...F F c o F ul UJ L I J J o tr o z f o E 9 lt lt o UJ Y F 2400 2200 2000 1 8 0 1600 1400 120 0 10 0 800 Example Departure airport pressure altitude 20qO ft Temperature 21 C Gross weight 240O lbs Wind 1...

Page 68: ...imb pressure ahitude 3600 ft OAT 1 C Rate ol climb 620 F P M o F 3 l 11 c q9F ZF oE qO LF 3 z o E 1 00 rrco 600 800 RATE OF CLIMB _ F P M 2 rro 30 20 10 0 10 20 30 OUTSIDE AlR TEMP _ C 0 o e E I gr e...

Page 69: ...ULLTHROTTLE 2550 LBS GROSS WEIGHT CHART INCLUDES FUEL ALLOWAN FOESTART TAX AND TAKEOFF Example 40 3 20 10 0 10 20 30 oUisIDE AIR TEMP c 40 Departure airport pressure altitude 20OO ft Departure airpon...

Page 70: ...g o o J o o E a o o 9 CJ go ut o o 0 o E G E I o ul u L aa u o z UJ o I d u l F E ur I o F f o ENGINE PERFORMANCE Figure 5 19 REPORT VB l120 20 ISSUED JULY 2 1979 REVISED JULY 5 1985 E ir9oo HSdF o U...

Page 71: ...o n oq t s o rt tO O oo lOF J I OE o c o OF E O E H ooo o o 9 9 9 o E 3 ao o F U alt HF o 2 I I RA Ful o E OU G F o o F o F I o N I o o R J I o F u OF E o u o RA ot q o t SPEED POWER PERFORMANCE CRUIS...

Page 72: ...o o o o F F I o N I o 80 h F O O c Q FEo 5H 3 JGF o 8 o tt a f 6 o o o o a o 9 f O o o NO ol A E oul F oE i u oO 6 F ie I I o E 6 x ul SPEED POWER ECONOMY CRUISE Figure 5 23 REPORT VB l120 22 ISSUED J...

Page 73: ...2 f tr o E J o o U o J o u l 2 ll fto J 2 iE irro ZurG JU a aN q8 E Z iB r9o UJ oO uqn ll 3N F F I N I o o o N o o o o o t q 9o o E G E 98 o J o 6t 3 E 8e 3 rb gnr ri bct 5t F H i i ra9 6 c le g6fiEe...

Page 74: ...F o o 6 o o 6 o J o o ul o l J o o 2 o t Il N ttt o 2 f o E J ut I 1 J o o j 9 rt Y uI E o F o u l z ul J o ut J J F o a a E 3 ul u l I F 2 ut o o ul o F o ql 6 F o F I o1 E o c g g E c oc 8e O l o x...

Page 75: ...F I N I o E o 2 o t o 2 o J o o ui o l J o z 2 o I o ut o 2 E f o 2 u o E l o I u o z E t o z u l I E 3 u c u o U c a 6 i i N xo g He f g P3E s H g g o PE E3E E L O C C I o riJuJ gE sF Il onrll lv lu...

Page 76: ...FEEesFE LANDING GROUND ROLL Figure 5 37 6 o o o o o z v I o z o o N o J I F I 9 UJ 3 F F I o N I o o o o o I G u l F t a ul e o F f o g o o o 1 oo l F O L N i 8 EF sR a gE 1 B E 9E o oJ X B o u a s 5...

Page 77: ...Cruise pressure altitude 6000 ft Cruise OAT 13 C Destination airport pressure altitude 23OO ft Destination airport temperature 21 C Fuel to descend 2 0 gal minus 1 O 9al 1 O gal Time to descend 16 min...

Page 78: ...o u TE G o Fd ir 0av E trt D E Et a t2 trt I gi F c c 12000 10 0 8000 6 00 400 l 2 0G Example Cruise pressure altitude SOOO ft Terrain pressure altitude 20OO ft Glide range 13 5 mil s minus 3 5 miles...

Page 79: ...rl uStuuvs rJ 09 USAO ICNVISIO 9NlONVl LANDING PERFORMANCE Figure 5 35 o o o o o Po F o oz I to z E o o o N o 9ut NCO oJ ot Nr NF OI g9 NUJ 83 t N o o o o ot o oE u l F o0c e IJJ xo 6 F 3 o t F o F I...

Page 80: ...ance it will have Center of gravity is a determining factor in flight 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 t...

Page 81: ...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 82: ...racted 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 pre...

Page 83: ...NG FORM Figure 6 l d Basic Empty Weight Center of Gravity l The following geometry applies to the PA 28 l8l airplane when it is level Refer to Leveling paragraph 6 3 b G Arm Level Points Fuselage 78 4...

Page 84: ...ity Location and Useful Load listed in Figure 6 5 are for the airplane as licensed at the factory These figures apply only to the specific airplane serial number and registration number shown The basi...

Page 85: ...ght 1590 0 87 5 l39 r Pilot and F ront Passenger 340 0 80 5 27370 Passerigers Rear Seats 340 0 lr8 l 40t54 Fuel 48 Gallon Maximum 288 0 95 0 27360 Baggage 200 Lbs Maximum 142 8 Ramp Weight 2558 Lbs No...

Page 86: ...60 Takeoff Weight 2550 Lbs Normal 2130 Lbs Utility Maximum Totals must be within approved weight and C G limits It is the responsi bility of the airplane owner and the pilot to insure that the airplan...

Page 87: ...t ltt ARCHER II SECTION 6 WEIGHT AND BALANCE t 6 L 7 7 I MOMENT I x 0 POUNDS INCHESI LOADING GRAPH Figure 6 13 REPORT VB 1120 6 ll 450 400 350 300 250 200 150 100 d o U o z 3 o g F I ul o o J 051015m2...

Page 88: ...t t IYEIGHT v8 C O ETTVELOPE 2650 LBs mAX GnOSS WT NORMAT CAIEOORY J 92 90 91 a7 88 o 6 J 1 1 ul 700 1600 500 t 00 300 _ _ 1 E2 83 86 86 87 88 89 90 91 92 93 C G TOCATION INCHES AFT OATUMI C G RANGE...

Page 89: ...on the seats or in the baggage compartments Brief instructions are given on the plotter itself To use it first plot a point on the grid to locate the basic weight and C G location This can be put on...

Page 90: ...envelope a Place a dot on the plotter grid at 1300 pounds and 85 00 inches to represent the basic airplane See illustration Figure 6 17 b Slide the sloned plastic into position so that the dot is unde...

Page 91: ...UED MAY 29 1980 REVISED FEBRUARY 2 1990 REPORT VB 1120 6 l2c I I I r B 1 GE SEAT toN L F sE T WEIGHT vs C G ENVELOPE 2550 LBS MAX GROSS WT NORMAL CATEGORY 88 89 90 91 92 93 a7 86 85 84 83 2 o dl J 1 9...

Page 92: ...foil The wings are attached to each side of the fuselage by insertion of the butt ends of the respective main spars into a spar box carry through which is an integral part of the fuselage structure pr...

Page 93: ...SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION OPERATION pA 28 lu ARCHER II MAIN WHEEL ASSEMBLY Figure 7 l REPORT VB 1120 7 2 ISSUED JULY 2 1979...

Page 94: ...ch side of center A shimmy darnpener is also included in the nose gear The three struts are of the air oil type with a normal extension of 3 25 inches for the nose gear and 4 50 inches for the main ge...

Page 95: ...etween the front seats Figure 7 3 A rudder trim adjustment is mounted on the right side of the below the throttle quadrant and permits directional trim as needed refer to Figure 7 5 pedestal in flight...

Page 96: ...SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION OPERATION PA 28 I8I ARCHER II CoNTROL QUADRANT AND CONSOLE Figure 7 5 REPORT V 1120 7 6 ISSUED JULY 2 1979...

Page 97: ...The carburetor heat control lever is located to the right of the control quadrant on the instrument panel The control is placarded with two positions ON down OFF up 7 13 FUEL SYSTEM Fuel is stored in...

Page 98: ...e fire wall has a drain which is accessible from outside the nose section The strainer should also be drained before the first flight of the day Refer to paragraph 8 21 for the complete fuel draining...

Page 99: ...e 7 9 7 15 ELECTRICAL SYSTEM hc clcctrical systcm includes a l4 volt 60 anrp alternator a l2 volt battcry a voltagc regulator an overvoltage relay and a master switch relay Figurc 7 I l I he battcry i...

Page 100: ...ical load and a fully charged battery the Alternator Inop Light may illuminate due to minimal alternator output If the altemator is functional a slight increase in electrical load should extinguish th...

Page 101: ...s itEa UGIIEN rll CABI Lt6tt t CASTER soLENO o EXTE NA RECEPTACLE I t_ _______9 r gl L__ 1 ISSUED JULY 2 1979 REVISED JANUARY 14 l98l ALTENNAIOR souncE P0wEi l rl AATIERY 8 swr rctsEs REPORT VB l120...

Page 102: ...indicate battery discharge rather it displays in amperes the load placed on the alternator With all electrical equipment off except master switch the ammeter will be indicating the amount of charging...

Page 103: ...the necessary plumbing The vacuum pump is a dry type pump which eliminates the need for an air oil separator and its plumbing A shear drive protects the pump from damage If the drive shears the gyros...

Page 104: ...er to the avionics bus in event of a radio master switch circuit failure The emergency bus switch is located behind the lower right shin guard left of the circuit breaker panel An engine cluster is lo...

Page 105: ...1 TRANSPONDER t2 MARKER BEACON 13 AUDIO SELECTOR PANEL 14 VHFTRANSCEIVERS I5 ADF RECEIVER 16 DME RECEIVER 17 ENGINE HOUR METE 18 SUCTION GAUGE I9 HEAT DEFROST CONTROL 20 CIGAR UGHTER 21 MIKE JACK 22...

Page 106: ...air for static pressure The storm window and cabin vents must be closed and the cabin heater and defroster must be on during alternate static source operation The altimeter error is less than 50 feet...

Page 107: ...EI ARCHER II DESCRIPTION OPERATION ll L 1 ALTIMETER 2 AIRSPEED INDICATOR 3 PITOT HEAT SwlTCH 4 VERTICAL SPEED INDICATOF 6 PITOT HEAO 6 DRAIN VALVES 7 ALTERNATE STATIC SOUFCE PITOT STATIC SYSTEM Figure...

Page 108: ...AIR INLET 2 INLET OUCT 3 FRESH AIR BLOWER 4 BULKHEAD ASSEMELY 5 FRESH AIR DUCT 6 CABIN EXHAUST OUTLET REPORT VFll2O 7 t HEATING AND VENTILATING SYSTEM Figure 7 19 7 DEFROSTER OUTLET 8 BLOWER SWTCH PA...

Page 109: ...n models without air conditioning This blower is operated by a FAN switch with 3 positions OFF LOW HIGH CAUTION When cabin heat is operated heat duct surface becomes hot This could result in burns if...

Page 110: ...occupants Shoulder harnesses should be routinely worn during takeoff landing and whenever an inflight emergency situation occurs 7 27 BAGGAGE AREA A 24 cubic foot baggage area located behind the rear...

Page 111: ...he air corrditioner is ON and retracts to a flush position when the system is OFF The compressor is mounted on the forward right underside of the engine lt has an electric clutch which automatically e...

Page 112: ...or light is located to ths left of the radio stack in front of the pilot The light illuminates whenever the condenser door is open and remains on until the door is closed I A circuit breaker located o...

Page 113: ...he battery must be replaced on or before this date The battery must also be replaced if the transmitter has been used in an emergency situation or if the accumulated test time exceeds one hour or if t...

Page 114: ...moving the switch to ARM A pilot s remote switch located on the left side panel is provided to allow the transmitter to be turned on from inside the cabin The pilot s remote switch is placarded ON an...

Page 115: ...et by either positioning the remote switch to the ON position for two seconds and tien relocating it to the ARM position or by setting the switch on the EI T to OFF and then back to ARM In the event t...

Page 116: ...mitter is activated by an impact it can be turned off by moving the ELT switch OFF Normal operation can then be restored by resetting the switch to ARM It may also be turned off and reset by positioni...

Page 117: ...heat Refer to Paragraph 3 29 Carburetor lcing in the emergency procedures To adjust the system tbr critical ice detection first turn on the airplanes master switch and then turn on the ice detection u...

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Piper Aircraft Corporation ARCHER II PA-28-181, Operating Handbook

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